Cessna_208_C208_675HP_1998_POH_Cessna Caravan Updated To 2004 Cessna 208 C208 675HP 1998 POH
User Manual: Cessna_208_C208_675HP_1998_POH_Cessna-Caravan-updated-to-2004
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TEMPORARYRE'VISION
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208PHTR03
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3 FEBRUARY 2004
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for
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, CESSNA MODEL 208 SERIES
PILOT'S OPERATING HANDBOOKS
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FAA ,APPROVED AIRPLANE
FLIGHT MANUALS
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THIS TEMPORARY REVISION REVISES FUEL QUANTITY VERSUS
DEPTH INFORMATION WHEN USING THE DIPSTICK REQUIRED
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IN THE PILOT'S OPERATING HANDBOOK.
BY CAB04-1 ON BOTH LEFT AND RIGHT WING L.EADING EDGE
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,r-"
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INSERT THE ,PROVIDED LIST OF TEMPORARY REVISIONS, AND
THE TEMPORARY REVISION INTO THE PILOT'S OPERATING
HANDBOOK
'IN
ACCORDANCE
WITH ' THE
FILING
,INSTRUCTIONS IN EACH REVISION.
For Training Purposes Only
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For Training Purposes Only
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LIST OF TEMPORARY REVISIONS
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for .
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CESSNA MODEL 208 SERIES
PILOT'S OPERATING HANDBOOKS
and
FAA APPROVED AIRPLANE
FLIGHT MANUALS
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208PHTR03
3 February 2004
208PHTR .
For Traini"g' Purpos~s Only
LIST OF
TEMPORARY REVISIONS
MODEL
~eERIES208 (
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Pilot's Operating Handbook
All Cessna Model208 ,Series
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Following is the List of Temporary Revisions that may be inserted into this "
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Pilot's Operating Handbook.
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Insert this page opposite the first page of the Log of Effective Pages in the
front of the Pilot's Operating Handbook.
TEMPORARY
REVISION
NUMBER
MANUAL
SECTION/
TOPIC
ISSUE
DATE
20BPHTROl
CANCELLED
REPLACED BY
208PHTR02
CANCELLED
REPLACED BY
208PHTR02
NO
REFERENCE
208PHTR02
2ILlMITATIONS
23 September
2003
CAB03-11Rl
208PHTR02
3/EMERGENCY
PROCEDURES
23 September
2003
CAB03-11Rl
4/NORMAL
PROCEDURES
23 September
2003
CAB03-11Rl
208PHTR02
51
PERFORMANCE
23 September
2003
CAB03-11Rl
208PHTR03
4/NORMAL
PROCEDURES
3 February
2004
CAB04-1
208PHTR02
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SERVICE
BULLETIN
REFERENCE
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TEMPORARY REVISION 208PHTR03
APPROVED BY
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'AA APPROVED UNDER FAR 21SUBPART J
rl\lj Ceqn. Aircraft Co
0010g81100 Option' Authonzalion 00A·230428-Ce
*~_E_
DATE'OFAPPROVAL.3
E=eeRUAAY
For Train!og Purposes Only
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3 February 2004
208PHTR
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Cessna
MODEL SERIES
208
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PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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Description of Change:
Section 4, NORMAL PROCEDURES
Filing Instructions:
Insert this temporary revision into the Pilot's
Operating Handbook.
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In Section 4, NORMAL PROCEDURES, insert the temporary revIsion
pages adjacent to .the ·current Pilot's Operating Handbook Section 4 pages
. containing' the information that is shown in this temporary revision.
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For Training Purposes Only
3 February 2004
208PHTR03
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For Training Purposes Only
PILOT'SOPERATING HANDBOOK
TEMPORARY REVISION
Cessna
MODEL SERIES
208
SECTION 4 - NORMAL PROCEDURES
CHECKLIST PROCEDURES
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PREFLIGHT INSPECTION
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0LEFT WING Leading Edge
A
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WARNING
It is essential in cold weather to remove even small
accumulations of frost, ice, or snow from the wing and
control surfaces. Also, make sure the control surfaces
contain no internal accumulations of ice or debris.
Prior to any flight in icing ' conditions, check that
pitot/static source and stall warning heaters are warm
to touch after turning pitot/static and stall heat switches
on for 30 seconds, then off. Make sure the pitot covers
are removed.
Wing Strut Deice Boots -- CHECK for tears, abrasion and cleanliness.
Wing Tie-Down -- DISCONNECT.
Wing Deice Boots -- CHECK for tears, abrasions and cleanliness.
Stall Warning Vane -- CHECK freedom of movement, audible warning
and warmth.
(For aircraft equipped with a stall warning ground
disconnect switch, check audible warning with elevator off forward
stop).
5. PitoVStatic Tube -- CHECK security, openings for stoppage and
warmth.
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6. Landing and Taxi Lights ~- CHECK condition and cleanliness.
7. Fuel Quantity -- USE DIPSTICK required by CAB04-1 to check fuel
level. See Figure TC-l for fuel quantity versus depth.
1.
2.
3.
4.
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CAUTION
Fuel gages may indicate incorrect fuel quantity.
8.
9.
10;
Fuel Filler Cap -- SECURE.
Outboard Fuel Tank Sump Quick-Drain Valve (if installed and airplane
parked with one wing low on a sloping ramp) -- DRAIN (using fuel
sampler) to check for water, sediment, and proper fuel before each
flight and after each refueling. If water is observed, take further
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samples until clear. Take repeated samples from all fuel drain points ( .(,
until all contamination has been removed.
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NaVigation and Strobe Lights -- CHECK for condition and cleanliness.
3 February 2004
208PHTR03
For Training Purposes Only
208
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Cessna
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
MODEL SERIES · .
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Universal XL
Fuel Gage
Gage Scale
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0.50
0.75
1.00
1.25
1.50
1.75
2.00
2.25
2.50
2.75
3.00
3.25
3.50
3.75
4.00
4.25
4.50
4.75
5.00
5.25
5.50
5.75
6.00
6.25
6.50
6~ 75
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7.00
7.25
Fuel Quantity
Gal
lbs
87.4
91 .1
94.7
98.2
101.8
105.2
108.6
111.9
115.1
118.3
121.5
124.5
127.5
130.5
133.4
136.2
138.9
141.6
144.3
146.8
149.3
151 .8
154.1
156.5
158.7
160.9
163.0
165.0
585
610
634
658
682
705
727
750
771
793
814
834
855
874
894
912
931
949
966
984
1000
1017
1Q33
1048
1053
1078
1092
1106
Generic Fuel
Gage - Inches
ncnes
0.50
0.75
1.00
1.25
1.50
1.75
2.00
2.25
2.50
2.75
3.00
3.25
3.50
3.75
4.00
4.25
4.50
4.75
5.00
5.25
5.50
5.75
6.00
6.33 ·
Fuel Quantity
Gal .
Lbs
88.4
592
92.6 .
621
96.7
648
100.8
675
104.7
702
108.6
727
112.4
753
116.1
778
119.7
802
123.2
826
126.7
849
130.1
871
133.4
894
136.G
915
139.7
936
142.8
956
145.7
976
148.6
996
151.4
1015
154.1 .
1033
156..8
1050
159.3
1068
161.8
1084
165.0
1105
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Figure TC-1. Measure d Fuel Depth vs Fuel Quantity
For Training P\Jrposes On'y
3 February 2004
208PHTR03
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
MODEL
s~e~~~~ 208 '
(
VRIGHT WING Leading Edge
A WARNING
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It is essential in cold weather ,to remove even small
accumulations of frost, ice, or snow from the wing and
control surfaces. Also, make sure the control surfaces
contain no internal accumulations of ice or debris.
1.
2.
Navigation and Strobe Lights -- CHECK condition and cleanliness.
Fuel Quantity -- USE DIPSTICK required by QAB04-1 to check fuel
level. See Figure TC-1 for fuel quantity verSus depth.
A
(
CAUT10N
Fuel gages may indicate incorrect fuel quantity.
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3.
4.
F'uel Filler Cap-- SECURE.
Outboard Fuel Tank Sump Quick-Drain Valve (if installed and airplane
parked with , one wing low on a sloping ramp) -- DRAIN (using fuel
sampler) to check for water, sediment, and proper fuel before each
flight and after each refueling. If water is ' observed, take further
samples until clear. Take repeated samples from all fuel drain points
until all contamination has been removed.
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5. PitoVStatic Tube -- CHECK security, . openings 'for stoppage , and
warmth.
6. Landing and Taxi Lights -~ CHECK conditibn . ~nd cleanliness.
7. Wing Deice Boots-- CHECK for tears, abrasl9~ and cleanliness.
.
8. Radome -- CHECK condition and security. :' \
9. Wing Tie-Down -- DISCONNECT.
' '~
10.. Wing Strut Deice Boots -- CHECK for tears, abrasion,and cleanliness.
11 . Inboard Fuel Tank Sump and External Sump Quick-Drain Valves -DRAIN (using fuel sampler) to check for water, sediment, arid proper
fuel before each flight and after each refueling. If water is observed.
take further samples until clear. Take repeated samples from aliluel
drain pOints until all contamination has been removed.
12. Main Landing Gear -- CHECK proper tire inflation and gear condition.
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3 February 2004
208PHTR03
For Training Purposes Only
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TEMPORARY REVISION
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208PHTR02
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23 SEPTEMBER 2003
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for
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CESSNA MODEL 208 SERIES
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PILOT1SOPERATINGHANDBOOKS
and
FAA APPROVED AIRPLANE
FLIGHT MANUALS
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THIS
TEMPORARY
REVISION
REPLACES
TEMPORARY
. REVISION 208PHTR01 DATED 8 SEPTEMBER 2003 AND REVISES
FLAP USAGE INFORMATION IN ·SECTIONS 2, 3, 4 AND 5 OF
THE PILOT'S OPERATING HANDBOOK.
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INSERT THE PROVIDED LIST OF TEMPORARY REVISIONS, AND
THE TEMPORARY REVISION INTO THE PILOT'S OPERATING
HANDBOOK·
IN
ACCORDANCE
WITH
THE
FILING
INSTRUCTIONS IN EACH REVISION.
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For Training Purposes Only
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,,~. -.,:
For Training Purposes Only
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LIST OF TErv1PORARY REVISIONS
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for
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CESSNA MODEL 208 SERIES
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PILOT'S OPERATING HANDBOOKS
and
FAA APPROVED AIRPLANE
FLIGHT MANUALS
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208PHTR02
23 September 2003
208PHTR
For Training Purposes Only
LIST. OF
Cessna
MODEL SERIES
TEMPORARY REVISIONS
208
.
Pilot's Operating Handbook
All Cessna Model 208 Series
(
The following List of .Temporary Revisions must be inserted into this Pilot's
(
Operating Handbook.
(
Insert this page opposite the first page of the Log of Effective Pages in the
frontof the Pilot's Operating Handbook.
TEMPORARY
REVISION . .
NUMBER
208PHTR01
MANUAL
SECTIONI
TOPIC
(
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ISSUE
DATE
CANCELLED ·
CANCELLED
REPLACED BY
208PHTR02 ..
REPLACED BY
208PHTR02
20BPHTR02
2IUMITATIONS
23 September
2003
20BPHTR02
3/EMERGENCY
PROCEDURES
23 September
2003
20BPHTR02
4/NORMAL
PROCEDURES
23 September
2003
20BPHTR02
51
PERFORMANCE
23 September
2003
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TEMPORARY REVISION 208PHTR02
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APPROVED BY
FAA APPROVED UNDER FAR 21 SUBPART J
The C _ 1.ircr8ft co.
Del"llation Option Authoriulion DOA-23042B-CE
.~f-.w; rJ .t;:-J
~. ~3
ExIlQlliye Engineer
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SE..PTEM&R. :l003
For Training Purposes Only
23 September 2003
208PHTR
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Cessna
208
MODEL SERIES .
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PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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Description of Change:
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Filing Instructions:
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Section
2,
LIMITATIONS,
Section
. EMERGENCY
PROCEDURES,
Section
NORMAL PROCEDURES, and
Section
PERFORMANCE.
3,
4,
5,
Insert this temporary revision into the Pilot's
Operating Handbook.
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In Section 2, LIMITATIONS, insert the temporary revision pages adjacent
to the current Pilot's Operating Handbook Section 2 pages containing the
information that is shown in this -temporary revision.
.
_In Section 3, EMERGENCY PROCEDURES; insert the temporary revision
pages adjacent to the current Pilot's Operating Handbook Section 3 pages
containing the information that is shown in this temporary revision.
In Section 4, NORMAL PROCEDURES, insert the temporary revision
pages adjacent to the current Pilot's Operating Handbook Section 4 pages
containing the information that is shown in this temporary revision.
In Section 5, PERFORMANCE, insert the. temporary revision pages
adjacent to the current Pilot's Operating Handbook Section 5 pages containing
the information that is shown in this temporary revision.
Discard any pages of this temporary revision that are not applicable to
your model/serial airplane.
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For Training Purposes Only
23 September 2003
20BPHTR02
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For Training Purposes Only
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Cessna
MODEL SERIES
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208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 2 • LIMITATIONS
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OTHER LIMITATIONS
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FLAP LIMITATIONS
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U~E
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•
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OF FLAPS IS PROHIBITED
The flap motor and STBY flap motor circuit breakers must be pulled
and collared. (place a tie wrap or equivalent around the pulled circuil
breaker.)
The following placard must be displayed in the cockpit, in clear view 01
the pilot, on the lower right hand portion of the center instrument panel:
I· USE OF FLAPS IS PROHIBITED
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NOTE
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Use 0° Flap Takeoff and . Landing performance and procedures
from Section 5.
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For Training Purposes Only
23 September 2003
208PHTRm
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Intentionally Left Blank
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For Training Purposes Only
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Cessna
MODEL SERIES
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PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 2 - LIMITATIONS
(
'KINDS OF OPERATION LIMITS
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208
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This airplane is equipped for day VFR, and may be equipped for night VFR
and/or IFR operations and for f1ight-into-known icing conditions. The operating
limitations placard reflects the limits applicable at the time of Airworthiness
Certificate issuance.
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The following equipment list identifies the systems and equipment upon which
type certification for each kind of operation was ' predicated, These systems
and equipment items must be installed and operable for the particular kind of
operation indicated. Reference should also be made to the Equipment List
furnished with the airplane for additional equipment information. The pilot is
responsible for determining the airworthiness of his airplane for each flight and
for assuring compliance with curr~nt operating FAR's.
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REQUIRED EQUIPMENT
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DAVVFR:
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Airspeed Indicator (1)
Altimeter (1)*
Auxiliary Boost Pump System
BATIERY HOT And SATIERY
OVERHEAT ·Annunciators (NiCad
Batteries Only)
Elevator Trim System (Manual)
Engine Ignition System
(Flap Motor Disabled)
Flap Position Indicator
FUEL PRESS LOW Annunciator
Fuel Quantity Indicators (2)
Fuel Selectors Off Warning
System
Generator
Inertial Separator System
In Indicator
Magnetic Compass
Ng% RPM Indicator .
OIL PRESS LOW Annunciator
Oil Pressure Gage
Oil Temperature Gage
Outside Air Temperature Gage
Overspeed (Airspeed) Warning
System
Overspeed Governor
Pilots Operating HandbookiAFM
Pitot-Static System (1)
. Propeller APM Indicator
Seat Belts (Each Occupant)
Shoulder Harnesses (Front Seats)
Slip-Skid Indicator (1)
Stall Warning System
Torque Indicator '
Trim Position Indicators (3)
VolVAmmeter
* NOTE
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. When a servoed altimeter is installed,
pneumatic altimeter is also required .
For Training Purposes Only
a
functioning
23 September 2003
208PHTA02
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Intentionally Left Blank
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Cessna
MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 3 - EMERGENCY PROCEDURES
ENGINE FAILURES
ENGINE FAILURE IMMEDIATELY AFTER TAKEOFF
1.
2.
3.
4.
5.
6.
Airspeed •• 95 KIAS with 0° flaps.
Propeller-- FEATHER.
Fuel Condition Lever -- CUTOFF.
Fuel Shutoff -- OFF (pull out).
Fuel Tank Selectors -- OFF (warning horn will sound),
Battery -" OFF.
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23 September 2003
208PHTR02
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For Training Purposes Only
Cessna
MODELSERIES
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208
' PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
.
SECTION 3 - EMERGENCY PROCEDURES
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FORCED LANDINGS
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1,
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2.
3.
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4.
5.
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6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
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EMERGENCY LANDING WITHOUT .ENGINE POWER
Seats, Seat Belts, Shoulder Harnesses -- SECURE,
Airspeed -- 100 KIAS (flaps UP)
Power Lever --IDLE.
Propeller Control Lever -- FEATHER.
Fuel condition Lever -- CUTOFF.
Fuel Boost Switch -- OFF.
Ignition Switch -- NORM,
Standby Power Switch (if installed) -~ OFF.
. Non-essential Equipment (if Installed) -- OFF.
Fuel Shutoff -- OFF (pull out).
Fuel Tank Selectors -- OFF (warning horn will sound).
Crew Doors -- UNLATCH PRIOR TO TOUCHDOWN.
Ba~tery Switch -- OFF when landing is assured.
Touchdown -- SLIGHTLY TAIL LOW.
Brakes -- APPLY HEAVILY.
( .
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PRECAUTIONARY LANDING WITH ENGINE POWER
1.
Seats, Seat Belts, Shoulder Harnesses -- SECURE.
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2 . . Wing Flaps -- 0°.
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3.
4.
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5.
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6.
7.
8.
9.
10.
11.
Airspeed -- 95 KIAS.
Selected Field -- FLYOVER, noting terrain and obstructions.
All Electrical Switches (except Battery and Generator) -- OFF.
Crew Doors -- UNLATCH PRIOR TO TOUCHDOWN.
Generator Switch (if installed) -- OFF.
Battery Switch -- OFF.
Touchdown -- SLIGHTLY TAIL LOW.
Fuel Condition Lever -- CUTOFF.
Brakes -- APPLYHEAVIL Y.
For Training Purposes Only
23 September 2003
208PHTR02
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For Training Purpos~s Only
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Cessna
MODEL SERIES
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208
PILOT'S OPERATING HANDBOOK
TEMPORARY 'REVISION
SECTION 3 • EMERGENCY PROCEDURES
(
FORCED LANDINGS
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{'
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DITCHING
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1.
Radio·· TRANSMIT MAYDAY on 121.5 MHz,giving location and
intentions and SQUAWK 7700 if transponder is installed.
2. Heavy Objects in Cabin •• SECURE if passenger is available to
assist.
3. Seats, Seat Belts, Shoulder Harnesses •• SECURE.
4. , Wing Flaps •• 0°.
,
5.
Power·· ESTABLISH 300 FT/MIN DESCENT AT 100 KIAS.
6. Approach·· High Winds .. INTO THE WIND.
light Winds, Heavy Swells •• PARALLEL TO SWELLS.
7. FACE •• CUSHION at touchdown with folded coat or similar object.
8. Touchdown •• NO FLARE, maintain descent attitude.
9. Airplane·· EVACUATE.
10. Life Vests and Raft·· INFLATE when outside cabin.
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ForTraining Purposes Only
23 September 2003
208PHTRm
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Intentionally Left Blank
For Training Purposes Only
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Cessna
MODEL SERIES
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208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
SECTION 3 - EMERGENCY PROCEDURES
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SMOKE AND FIRE
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ENGINE FIRE IN FLIGHT (Red ENGINE FIRE Annunciator On Or
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Off)
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1.
2.
3.
4.
5.
6.
7.
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Power Lever -- IDLE.
Propeller Control Lever -- FEATHER.
Fuel Condition Lever - CUTOFF.
Fuel Shutoff -- OFF.
Cabin Heat Firewall Shutoff Coritrol-- PULL OFF.
Forward Side Vents -- CLOSE.
Overhead Vents -- OPEN.
8. Ventilation Fans (if installed) -- ON.
9. , Wing Flaps -- 0°.
10. Airspeed _. 100 KIAS .
11. Forced Landing -- EXECUTE (as described in Emergency Landing
Without Engine Power)
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PILOT'S OPERATING HANDBOOK
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SECTION 3 .. EMERGENCY PROCEDURES
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LANDING GEAR MALFUNCTION PROCEDURES
LANDING WITH FLAT MAIN TIRE
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5.
Airplane -- FLY as desired to lighten fuel load.
Fuel Selectors _. POSITION ONE SIDE OFF TO LIGHTEN LOAD ON
SIDE OF FLAT TIRE (maximum fuel unbalance of 200 pounds).
Approach -- NORMAL W flaps).
Touchdown .- INFLATED TIRE FIRST. Hold airplane off flat tire as
long as possible with aileron control.
Directional Control·· MAINTAIN using brake on wheel with inflated
tire as required.
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MODEL SERIES ·
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SECTION 3 - EMERGENCYPROCEDURES
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EMERGENCY DESCENT PROCEDURES
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SMOOTH AIR
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2.
3.
4.
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5.
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Seats, Seat Belts, Shoulder Harnesses -- SECURE.
Power Lever -- IDLE.
Propeller Control Lever -- MAX (full forward).
Wing Flaps -- 0°.
Airspeed -- 175 KIAS .
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PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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SECTION 3 - EMERGENCY PROCEDURES
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INADVERTENT OPENING OF AIRPLANE DOORS
IN FLIGHT
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UPPER HALF OF CARGO DOOR OR UPPER HALF OF
PASSENGER AIRSTAIR DOOR OPEN (Red DOOR WARNING
Annunciator On) .
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2.
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3.
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Airspeed -- MAINTAIN LESS THAN 100 KIAS.
If available or practical. have a second crew member go aft to close
and latch door.
If landing is required with door open:
a. Approach and Landing NORMAl.
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LOWER HALF OF PASSENGER AIRSTAIR DOOR OPEN
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2.
3.
4.
5.
Airspeed -- MAINTAIN 100 KIAS.
Flight Controls -- MANEUVER for return for landing.
Wing Flaps -- 0°.
Approach -- NORMAL.
Landing -- SLIGHTLY TAIL LOW; avoid nose high flare.
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TEMPORARY REVISION
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SECTION 3 - EMERGENCY PROCEDURES
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LANDING WITHOUT ELEVATOR CONTROL
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Using power lever and elevator trim control, trim for approximately 500
fpm descent with 0° flaps at 100 KIAS. Then control the glide angle by
adjusting power.
If required,make small trim changes to maintain
approximately 85KIAS as power is adjusted during the approach.
The landing ' flare can be accomplished by a gentle power reduction
accompanied by nose up trim.' At forward C.G. loadings, it may be necessary
to make a small power increase in the final flare stage to bring the nose up and
prevent touchdown 'on the nose first. After touchdown, mov.e the power lever
to idle:
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208
PILOT'S OPERATING HANDBOOK
.
TEMPORARY REVISION
SECTION 3 - EMERGENCY PROCEDURES
INADVERTENT OPENING OF AIRPLANE DOORS
IN FLIGHT
If any of the airplane doors should inadvertently. open in flight, the
airplane should be slowed to 100 KIAS tei reduce buffeting of the doors. On
the Passenger Version, closing the upper cargo door or upper half of the
passenger airstair door can be accomplished after airspeed has been reduced
by pulling the door forcefully closed and latching the door. If the door cannot
be closed · in flight, a landing should be made as soon as practical in
accordance with the checklist procedures. On Cargo ·Versions. an open cargo
door cannot be closed in flight since the inside of the upper door has no
handle.
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If any cargo pod doors inadvertently open in flight. the airplane should be
slowed to 100 KIAS or less and landed as soon as practical. During the
landing. avoid a nose-high flare to prevent dragging an .open rear cargo pod
door on the runway.
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PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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SECTION 4 - NORMAL PROCEDURES
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.PREFLIGHT INSPECTION
CD
CABIN
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2.
3.
4.
5.
6.
. 7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
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. 18.
19.
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CD
Pilot's Operating Handbook and Other Required Documents -AVAILABLE IN THE AIRPLANE.
Control Locks --REMOVE (DISENGAGE rudder lock, if installed).
Parking Brake -- SET.
All Switches -- OFF.
All Circuit Breakers -- IN.
Static Pressure Alternate Source Valve -- OFF (full in) .
Inertial Separator T-Handle -- NORMAL.
Standby Flap Motor Switch (Overhead) -- GUARDED NORM.
Oxygen Supply Pressure -- CHECK.
Oxygen Masks -- CHECK AVAILABLE.
Fuel Selector Valves -- CHECK ON and FEEL AGAINST STOPS.
Radar -- OFF.
Air Conditioner (if installed) -- OFF.
inverier Switch (if instaiied) -- OFF.
Bleed Air Heat Switch -- OFF.
Emergency ' Power Uwer -- NORMAL, and if applicable, copper
witness wire present and intact.
Trim Controls -- SET.
Fuel Shutoff -- ON.
Cabin Heat Firewall Shutoff Control -- CHECK IN.
Battery Switch -- ON.
Avionics Power Switch No. 2 -- ON. Check audibly that avionics
cooling fan is operating.
Avionics Power Switch No. 2 .- OFF.
Fuel Quantity Indicators -- CHECK QUANTITY.
Wing Flaps -- UP.
.
Pilot/Static and Stall Heal Switches -- ON for 30 seconds, then OFF.
(Ensure pitot/static tube covers are removed.)
.
.Battery Switch -- OFF.
LEFT SIDE
1. Fuel Reservoir Drain (bottom .of fuselage or left side of .cargo pod) -DRAIN (using fuel sampler) to check for water, sediment, and proper
fuel before each flight and after each refueling. If water is observed,
take further samples until. clear. Take repeated samples from all fuel
drain points (see Section 7 Fuel System Schematic for all nine drain
locations) until all contamination has been removed.
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208
PILOT'S OPERATINGHANDBOOK
TEMPORARY REVISION
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SECTION 4 • NORMAL PROCEDURES
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BEFORE TAKEOFF
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1.
2.
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A WARNING
Failure to properly utilize seat belts and shoulder
harnesses could result in SERIOUS or FATAL injury in
the event of an accident.
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3.
4.
5.
6.
7.
8.
9.
10.
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Parking Brake·· SET.
Seats, Seat Belts, Shoulder Harnesses -- CHECK SECURE.
11 .
12.
13.
14.
15.
16.
17.
18.
19~
20.
21.
22.
23.
24.
25.
26.
27.
28.
Flight Controls _. FREE and CORRECT.
Flight Instruments -- CHECK and SET.
Fuel Boost Switch .- RECHECK NORM.
Fuel Tank Selectors -- RECHECK BOTH ON.
Fuel Quantity -- RECHECK.
Fuel Shutoff -- RECHECK FULLY ON.
Elevator, Aileron, and Rudder Trim Controls -- SET for takeoff.
Power Lever -- 400 FT-LBS.
a.
Suction Gage _. CHECK.
b.
Volt/Ammeter -- C HECK and return selector to BATT position.
c.
Inertial Separator -- CHECK. Turn control counterclockwise, pull
to BYPASS position and check torque drop; move control back
to NORMAL position and check that original torque is regained.
d. Engine Instruments .- CHECK (See Section 2, Limitations for
minimum oil temperature required for flight).
Overspeed Governor -- CHECK (stabilized at 1750 ±60 RPM) (See
Systems Checks) .
Power Lever --IDLE.
Quadrant Friction Lock -- ADJUST.
Standby Power (if installed) _. CHECK (See Systems Checks).
Autopilot .- PREFLIGHT TEST (See Systems Checks).
Known Icing System -~ PREFLIGHT COMPLETE (See Systems
Checks) prior to any flight in icing conditions.
Pitot/Static Heat -- On when OAT is below 4°C (40°F).
Ice Protection -- AS REQUIRED.
Avionics and Radar·· CHECK and SET.
GPS/NAV Switch -- SET.
Strobe Lights -.- AS HEQUIRED.
Annunciators -- EXTINGUISHED or considered.
Wing Flaps _. SET at 0°.
Cabin Heat Mixing Air Control-- FLT-PUSH.
Window .- CLOSE.
Brakes -- RELEASE.
Fuel Condition Lever -- HIGH IDLE.
Standby Pow.er Switch (if installed) .- ON (Standby Power INOF
Annunciator .- OFF).
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MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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SECTION 4 • NORMAL PROCEDURES
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TAKEOFF
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NORMAL TAKEOFF
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NOT APPROVED.
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SHORT FIELD TAKEOFF
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NOT APPROVED.
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208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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SECTION 4 • NORMAL PROCEDURES
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LANDING
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NORMAL LANDING
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NOT APPROVED.
(
SHORT FIELD LANDING
(
1. Wing Flaps •• 0°.
2. Airspeed·· 93 KIAS (Refer to Section 5 for speeds at reduced weights).
3. Power Lever •• REDUCE to IDLE after clearing obstacles.
4. Touchdown·· MAIN WHEELS FIRST.
5. Power Lever •• BETA range (lever against spring) after TOUCHDOWN.
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NOTE
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Further reduction of landing roll will result from use of
reverse thrust (see Section 5) .
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6.
Brakes·· APPLY HEAVILY while holding elevator control full aft.
!
BALKED LANDING
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1.
2.
3.
Power Lever·· ADVANCE for takeoff power.
Wing Flaps·· 0°.
Climb Speed .. 100 KIAS MINIMUM until obstacles are cleared.
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MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 5· PERFORMANCE • TAKEOFF
(
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208 (600 SHP)
WITHOUT CARGO POD
(
(
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0°
10'C
TAKEOFF
'NT.
LBS
SPEED
KIAS
LIFT
OFF
AT
PRES
ALT
FT
50
7500
7000
89
B9
89
104
104
104
23 September 2003
20BPHTR02
TOTAL
TOTAL
TOTAl
GRND FEETTC GRNO FEETTC GRND FEET TO GRND FEETTC
ROLL CLEAR ROLL CLEAR ROLL CLEAR
ROLL CLEAR
50FT
50FT
FT
FT
50FT
FT
50FT
FT
1830
3235
1945
3395
2050
3605
2185
3790
2335
3200 I
3560 :
4050 :
2335
4030
2490
4300
2800
4925
2680
4615
3010
5285
3400
6130
3660
6605
4520
6630
.-.
.-
1615
2845
1700
2980
1610
3160
1905
3315
3765
3075
1850
3425
2075
2210
3825
2495
4290
10000
2900
4995
3245
5695
12000
3545
6250
3965
7235
SL
1455
2560
1535
2710
2000
1630
2865
1720
3010
2770
2000
1750
4000
1965
6000
6000
I
3055
2910
1565
OBS
1740
1650
SL
OBS
OBS
OBS
FT
8000
40'C
3O'C ·
20'C
TOTAL
---
4000
1825
3185
1930
3525
2170
2055
3560
2170
3355
3750
2035
6000
2315
3995
2600
4580
8000
2320
3990
2490
4290
2795
4910
3150
5695
10000
2695
4645
3010
5290
3395
6130
.-
12000
3285
5605
3695
6715
4185
800s
.-
(
_.
..-
SL
1350
2395
1425
2515
1500
2635
1575
2760
2000
1510
2655
1590
2790
1675
2930
1765
3070
4000
1690
2955
1785
3105
18es
3265
2010
3490
6000
1905
3300
2010
3470
2140
3700
2405
4235
8000
2145
3695
2300
3970
2585
4545
2910
5265
10000
2490
4300
2760
4890
3135
5670
12000
3035
5365
3410
6205
3860
7390
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..-
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PILOT'S OPERATING HANDBOOK
Cessna
MODEL SERIES
TEMPORARY REVISION
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208
.
208 (600 SHP)
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208 (600 SHP) .
WITHOUT CARGO POD
(
TAKEOFF DISTANCE
(
(GROUND ROLL DISTANCE ANDTOTAL DISTANCE TO CLEAR 50 FEET)
(
FLAPS 0 0
(
CONDITIONS:
(
Flaps 0°
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 5-7
Paved, Level, Dry Runway
Zero Wind
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NOTES:
1. Use Type II or Type IV anti-ice fluid takeoff technique as specified in
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Section 4.
2. Decrease distances 10% for each 11 knots headwind. For operation
with tailwinds up to 10 knots, increase distances by 10% for each 2.5
knots.
.
3. For operation on a dry, grass runway, increase distances by 15% of
the "ground roll" figure.
4. With takeoff power set below the torque limit (1658 ft-Ibs), increase
distance (both ground roll and total distance) by 3% for inertial
separator in BYPASS and 5% for cabin heat on.
5. Where · distance values have been replaced by dashes, operating
temperature limits of the airplane would be greatly exceeded. Those
distance which are included .by the operation slightly exceeds the
temperature limit are provided for interpolation purposes only.
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23 September 2003
20BPHTR02
' Cessna
MODEL SEAlES
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208
.
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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MODEL SEAlES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 5 - PERFORMANCE - TAKEOFF
208 (600 SHP)
CARGO POD INSTALLED
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0°
TAKEOFF
WT.
LBS
SPEED
KIAS
LIFT
OFF
AT
FT
50
7500
7000
B9
89
89
104
104
104
23 September 2003
208PHTR02
40'C
TOTAL
TOTAL
GRNO FEET TO GRND FEET TO GRND FEETTC GRND FEET TO
ROLL
CLEAR
ROLL
CLEAR
ROLL
CLEAR
ROLL
CLEAR
FT
50FT
FT
50 FT
FT
50FT
FT
50FT
1850
3270
3640
OBS
SL
30'C
TOTAL
TOTAL
FT
BOOO
2O'C
10'C
PRES
AlT
1585
2825
OBS
1670
2970
OBS
1760
3115
OBS
2000
1775
3140
1870
3300
1975
3470
2075
4000
1900
3495
2105
3680
2220
3870
2370
4145
6000
2240
3910
2370
4120
2525
4400
2845
5070
8000
2530
4390
2720
4730
3060
5445
3455
6365
10000
2945
5130
3295
5875
3725
6875
---
12000
3605
6470
4055
7570
4610
9235
-
---
SL
1475
2630
1555
2765
1640
2900
1725
3040
2000
1650
2920
1740
3075
1835
3230
1930
3385
3855
4000
1850
3255
1955
3425
2060
3605
2200
6000
2085
3640
2200
3835
2350
4095
2640
4710
8000
2350
4085
2525
4400
2840
5060
3205
5910
---
10000
2735
4765
3060
5455
3455
6385
--
12000
3340
6010
3760
7025
4265
8565
-
SL
1365
2440
1440
2565
1520
2690
1595
2820
2000
1530
2710
1615
2850
1700
2990
1790
3140
4000
1715
3015
1810
3175
1910
3340
2040
3570
6000
1930
3370
2040
3550
2170
3790
2440
4360
8000
2175
3780
2335
4070
2625
4680
2960
5465
10000
2530
4410
2825
5045
3100
5900
12000
3085
5555
3470
6490
3935
7910
---
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For Training Purposes Only
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PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
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208
208 (600 SHP)
(
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208 (600 SHP)
CARGO POD INSTALLED
(
(
Ceasna
MODEL SERIES
/
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
(
FLAPS
(
po
(
CONDITIONS:
Flaps 00
1900 RPM
. Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure5-?
Paved, Level, Dry Runway
Zero Wind
Cargo Pod Installed
(
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.:..,..
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NOTES:
1. Use Type II or Type IV anti-ice fluid takeoff technique as specified in
Section 4.
2. Decrease distances 10% for each 11 knots headwind. For operation
with tailwinds up to 10 knots, increase distances by 10% for each 2.5
knots.
3. For operation on a dry, grass runway, increase distances by 15% 01
the "ground roU" figure.
4. With takeoff power set below the torque limit (1658 ft-Ibs), increase
distance (both ground roll and total distance) by 3% for inertial
separator in BYPASS and 5% for cabin heat on.
5. Where distance values have been replaced by dashes, operatin~
temperature limits of the airplane would be greatly exceeded. · Those
distance which are included by the operation slightly exceeds the
temperature limit are provided for interpolation purposes only.
23 September 2003
For Training Purposes Only
208PHTR02
Cessna
MODEL SERIES
208
.
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
(
IThis Page Intentio!,,)ally Left Blank I
(
(
(
(
(
23 September 2003
208PHTR02
For Training Purposes Only
(
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
Cessna
MODEL SERIES
208
(
(
(
(
:
(
(
(
,
\
(
(
IThisPage Intentionally Left Blank I
(
(
(
(
i
(
,
"
"
(
(
(
(
(
(
('
",
/ \C,,:;~,/, '
for Training Purposes Only
23 September 2003
208PHTR02
Cessna
MODEL SERIES
208
(
PILOT'S OPERATING HANDBOOK
. TEMPORARY REVISION
.
(
SECTION 5· PERFORMANCE· TAKEOFF
208 (675 SHP)
WITHOUT CARGO POD
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0°
WT.
LBS
TAKEOFF
SPEEO
KIAS
AT
LIFT
OFF
BODO
7500
e9
89
50
FT
104
104
10·C
PRES
ALT
FT
SL
7000
89
104
23 September 2003
208PHTR02
3070
3415
3810
4275
5215
6490
8360
1870
2095
2365
2800
3395
4140
3225
3590
4020
4815
5965
7580
1640
1840
2070
2330
2800
3395
4155
2845
3165
3530
3955
4820
5995
7715
1730
1940
2185
2590
3130
3815
2705
3005
3350
3750
4255 .
5230
6590
SL
'SL
1775
1990
2235
2520
3030
3675
4510
1555
1740
1955
2205
2515
3030
3700
6095
2000
4000
6000
8000
10000
12000
..-
2920
3245
3620
4050
4600
5655
7135
3540
4330
_.
.-
1680
1880
2115
2385
2720
3285
4010
10000
12000
6175
9025
7695
3135
3485
3890
4360
4950
2115
2445
2860
3390
6995
3300
3670
4100
4595
5615
1805
2025
2275
2565
2925
3465
3860
4325
5180
6430
2010
2255
2545
3020
3660
4470
1905
2140
2405
2715
3270
3970
4875
2000
4000
6000
8000
2000
4000
6000
8000
10000
12000
40·C
30·C
20·C
TOTAL
TOTAL
TOTAL
TOTAL
GRND FEETTC GRND FEETTC GRND FEETT( GRND FEETTC
ROLL CLEAR ROLL CLEAR ROLL CLEAR ROLL CLEAR
50FT
FT
50FT
5O .FT
FT
50FT
FT
FT
DBS
OBS
oes
OBS
For Training Purposes Only
.-
.-
-2985
3325
3725
4455
5515
6995
..-
_.
_.
1965
2270
2655
3145
.---
3635
4200
4950
5950
..3380
3905
4600
5525
----
.-
-
.-
2905
-
_.
_.
\
.-
_..
1820
2100
2455
!
3130
3615
4255
5105
..-
.
(
(
PILOT'S OPERATING HANDBOOK .
TEMPORARY REVISION
(
208
208 (675 SHP)
(
(
208 (675 SHP)
WITHOUT CARGO POD
(
(
Cessna
MODEL SERIES
./
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
(
.
FLAPS 0°
(
(
CONDITIONS:
Flaps 0°
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 5-8
Paved, Level, Dry Runway
Zero Wirid
(
(
(
,(
(
(
NOTES:
1. Use Type II or Type IV anti-ice fluid takeoff technique as specified ir
Section 4.
2. Decrease distances 10% for each 11 knots headwind. For operatior
with tailwinds up to 10 knots, increase distances by 10% for each ;
knots.
3. For operation on a d,ry, grass runway, increase distances by 15% 0
the "ground roll" figure.
4. With takeoff power set below the torque limit (1865 ft-Ibs), increasE
distance (both ground roll and total distance) by 3% for inertia
separator in BYPASS and increse ground roll 5% and total distancE
9% for cabin heat on.
5. Where distance values have been replaced by dashes, operatin!
temperature limits of the airplane would be greatly exceeded. Thosl
distance which are included by the operation slightly exceeds thl
temperature limit are provided for interpolation purposes only.
(
("-
(
'-:,;-:.
(
(
(
(
(
(
(
(
(
(
(
(
i;
\ "iC"'' '/
I'
(
(
For Training Purposes Only
23 September 2003
2Q8PHTRQ2
Cessna
MODEL SERIES
208
.
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
(
(
(
IThis Page Intentionally Left Blank I
(
23 September 2003
208PHTR02
For Training Purposes Only
(
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
Cessna
208
. MODEL SERIES .
(
(
(
(/
\
(
(
(
(
(
(
IThis Page Intentionally LeftBlank I
(
(
(
(
( /
(
"
(
(
(
(
(
For Training Purposes Only
23 September 2003
208PHTR02
Cessna
MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 5· PERFORMANCE - TAKEOFF
208 (675 SHP)
CARGO POD INSTALLED
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0°
WT,
LBS
SPEED
KIAS
LIFT
OFF
8000
7500
7000
89
89
89
AT
PRES
ALT
FT
50
GRND FEETTC GRND FEET TC GRND FEETTC GRND FEETTC
ROLL
CLEAR
ROLL
FT
50FT
FT
FT
104
104
104
23 September 2003
208PHTR02
3195
1830
CLEAR
50 FT ,
ROLL
FT
1930
3365
ROLL
CLEAR
' FT
50FT
3535
2145
3710
CLEAR
' 50FT
OBS
OBS
OBS
OBS
SL
TOTAL
TOTAL
TOTAL
TOTAL
40'C
30'C
20'C
10'C
TAKEOFF
2035
2000
2050
3560
2165
3750
2285
3940
2480
4300
4000
2305
3975
2440
4190
2580
4425
2905
5085
6000
2605
4455
2755
4705
3065
5320
3445
6145
8000
2970
5070
3320
5770
3720
6650
---
8585
.....
... --
--
-.--
.. a a _
:
10000
3595
6275
4035
7255
12000
4405
8015
4965
9550
4550
-
.....
SL
1700
2975
1795
3130
1895
3290
1995
3450
2000
1905
3310
2015
3485
2125
3665
2300 '
3995
4000
2145
3695
2265
3895
2395
4110
2695
4726
6000
2420
4145
2560
4370
2845
4940
3195
5705
--_._.
...---
8000
2755
4710
3080
5360
3450
6170
10000
3335
5825
3740
6730
4210
7960
12000
4080
7435
4590
8855
--
----
----
..._-
_.. --
SL
1575
2755
1665
2900
1750
3045
1845
3195
2000
1765
3065
1865
3230
1965
3395
2130
3700 '
4000
1985
3425
2095
3605
2215
3805
2490
4370
6000
2235
3835
2365
4045
2630
4570
' 2950
5270
8000
2550
4360
2845
4955
3185
5705
...._-
_.....
10000
' 3080
5385
3450
6215
3880
7350
12000
3765
6865 ,
4230
6170
--
--
--
....--
For Training .Purposes Only
---
...
---
I
\.
(
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
(
.
Cessna
MODEL SERIES
208
208 (675 SHP)
(
(
208 (675 SHP)
CARGO POD INSTALLED
(
(
TAKEOFF DISTANCE
(
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR.50 FEET)
FLAPS 0°
(
(
(
CONDITIONS:
Flaps 0°
1900 RPM
Inertial Separator - Normal
Cabin Heat" Off
Torque Set per Figure 5·8
Paved, LeveJ, Dry Runway
Zero Wind
Cargo Pod Installed
(
(
(
(
(
(/
(
,
"'~
(
(
(
(
(
(
(
(
/
\
_c'
NOTES:
1. l}$e Type II or Type IV anti-ice fluid takeoff technique as specified in
Section 4.
2. Decrease distances 10% for each 11 knots headwind. For operation
with .tailwinds ·up to 10 knots, increase distances by 10% for each 2
knots.
3. For operation on a dry, grass runway, increase distances by 15% of
the "ground roll" figure.
4. With takeoff power set below the torque limit (1865 ft-Ibs), increase
distance (both ground roll and total distance) by 3% for inertial
separator in BYPASS and increse ground roll 5% and total distance
9% for cabin heat on.
'
"
5. Where distance values have been replaced by dashes, operating
temperature limits of the airplane would be greatly exceeded. Those
distance which are included by the operation slightly exceeds the
temperature limit are provided for inteipolation purposes only.
(
(
("
/
For Training Purpose!; Only
23 September 2003
208PHTR02
Cessna
MODEL SERIES
208
.
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
(
(
I ThisPagelntentiona"y Left Blank I
(
( (
(
(
(
\ ""'.
23 September 2003
208PHTR02
For TrairaingPurposes Only
('
(
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
Cessna
MODEL SERIES
208
.
(
(
(
,
,.j,"
( '
\
(
(
(
(
(
(
IThis Page Intentionally LeftBlank I
(
(
(
(
(
(
/
"
"
"
(
(
(
(
,f
,
For Training Purposes Only
23 September 2003
208PHTR02
Cessna
MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 5 - PERFORMANCE - TAKEOFF
2088 (600 SHP)
CARGO POD INSTALLED
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 00
WT.
SPEED
KIAS
LBS
LIFT
OFF
AT
PRES
ALT
FT
50
8300
7800
7300
83
83
83
83
102
102
102
102
23 September 2003
20BPHTR02
TOTAL
GRND FEETTC GRND FEETTC
GRND FEETTC
ROLL
CLEAR
ROLL
CLEAR
ROLL
CLEAR
ROLL
CLEAR
FT
50FT
FT
50 FT
FT
50 FT
FT
5O.FT
5140
2715·
5445
2420
4845
OBS
OBS
OBS
OBS
FT
8750
TOTAl
TOTAL
TOTAl
GRND FEETTC
40'C
30°C
2O'C
10'e::;
TAKEOF.F
2565
2280
4560
2000
2585
5180
2750
5515
2915
5860
3090
6220
4000
2945
5920
3135
6315
3330
6725
3605
7360
6000
3370
6810
. 3590
7940
4530
9770
3875
7885
4225
7275
8725 .
3B75
8000
4940
10770
5845
13795
6405
15430
-'
-5110
SL
10000
4650
9740
5405
11 965
12000
6050
13800
7150
17915
.-
--
-
-.
SL
2145
4285
2275
4550
2410
4825
2550
2000
2430
4865
2585
5175
2740
5500
2905
5835
4000
2770
5555
2945
5920
3125
6305
3380
6895
6000 .
3165
6380
3370
6815
3635
7435
4245
9130
8000
3635
7385
3960
8165
4625
10055
5465
12840
-_.
_.
10000
4355
9105
5060
11160
5985
14345
12000
5655
12850
6670
16620
.-
-4485
, 5105
SL
1995
3985
2120
4230
2245
2000
2260
4520
2405
4810
2550
-_.
2375
4750
2700
5415
6395
4000
2575
5160
2735
5495
2905
5850
3140
6000
2940
5920
3130
6320
3375
6885
3935
8440
8000
3375
6645
3675
7560
4285
9265
5050
11620
--
-.-
10000
4040
8420
4685
10295
5530
13190
12000
5230
11635
6155
15255
.-.
-4150
4725 ·
SL
1850
3690
1965
3915
20BO
2000
2095
4165
2225
4450
2360
---.
2200
4395
2500
5010
4000
2385
4770
2535
5080
2690
5405
2905
5905
6000
2720
5470
2895
5840
3125
6355
3635
m5
6000
3120
6315
3395
6970
3955
6545
4650
10840
10000
3730
7760
4320
9460
5085
12085
12000
4820
10860
5660
13950
._.
---
----
.---
For Training Purposes Only
..-
1.,
(
'208
PILOT'S OPE=RATING HANDBOOK
TEMPORARY REVISION
(
Cessna
MODEL SERIES
(
208B (600 SHP)
(
(
( !
2088 (600 SHP)
CARGO POD INSTALLED
"
(
TAKEOFF DISTANCE
(
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0°
(
(
CONDITIONS:
Flaps 0°
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 5-7
Paved, Level, Dry Runway
Zero Wind
Cargo Pod Installed
(
(
(
(
(
(
,
/
/
(
(
(
(
(
(
(
(
(
NOTES:
1. Use Type II or Type IV anti-ice fluid takeoff technique as specified
in Section 4.
.
2, Decrease distances 10% for each 11 knots headwind.
For
operation with tailwinds up to 10 knots, increase distances by 10%
for each 2.5 knots.
3. For operation on a dry, grass runway, increase distances by 15%
of the "ground roll" figure.
4. With takeoff power set below the torque limit (1658 ft-Ibs),
increase distance (both ground roll and total distance) by 3% fOi
inertial separator .in BYPASS and 5% for cabin heat on.
5. Where distance values have been replaced by dashes, operatin~
temperature limits of the airplane would be greatly exceeded.
Those distance which are included by .the operation slightl~
exceeds the temperature limit are provided for interpolatior
purposes only.
For Tr~ining Purposes Only
23 September 2003
208PHTR02
Cessna
MODEL SERIES
208
'
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
IThis Page
Intentionally Left Blank
I
(
(
{
"" T. ~·_"
23 September 2003
208PHTR02
For Training Purposes Only
(
PILOT'S OPER.ATING HANDBOOK
TEMPORARY REVISION
(
Cessna
MODEL SERIES
208
(
(
(
(
/
\
(
(
(
(
(
(
(
I This PagelntentionaUy Left Blank ,I
(
(
(
(
(,--
(
(
(
23 September 2003
For Training Purposes Only
208PHTR02
Cessna
MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
SECTION 5 - PERFORMANCE - TAKEOFF
2088 (675 SHP)
WITHOUT CARGO POD
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0°
WT.
SPEED
KIAS
LBS
LIFT
OFF
AT
PRES
ALT
FT
50
TOTAL
TOTAL
GRND FEETTC
GRND FEETTC
8300
7800
7300
83
63
83
83
104
104
104
104
SL
GRND FEETTC GRND FEET Te
CLEAR
ROLL
CLEAR
ROLL
CLEAR
ROLL
CLEAR
FT
SOFT
OBS
FT
50FT
OBS
FT
SOFT
OBS
FT
50FT
2040
3790
2170
4025
2300
4270
2435
4520
OBS
2000
231.5
4305
2465
4580
2615
4865
2880
5420
4000
2640
4915
2810
5235
2995
5595
3475
6690
6000
3025
5645
3220
6030
3680
7070
4280
8530
8000
3515
6625
4045
7840
4690
9445
--
10000
4450
8730
5175
10570
6100
13155
12000
5775
12050
6810
15065
--
--
--
SL
2000
1920
2180
3560
2040
2315
3780
2165
2460
4010
4565
229()
4250
2705
5085
4000
2485
4045
4615
2640
4300
4915
6000
2840
5300
3030
5655
-
---
2815
5250
3260
6265
3455
6620
4015
7970
---
---
---
8000
3305
6210
3795
7335
4395
8815
10000
4175 .
8160
4845
9855
5700
12220
12000
5405
11215
6355
13965
--
--
---
SL
1790
3315
1900
3520
2015
3730
2130
3950
2000
2030
3760
2155 .
4000
2290
4245
2515
4725
4000
2310
4290
2460
4565
2620
4875
3030
5810
6000
2645
4920
2815
5250
3210
6135
3725
7370
--
8000
3070
5760
3520
6790
4075
8140
--
10000
3875
7545
4490
9090
5270
11225
-
12000
5000
10320
5870
12800
--
-~~-
--
-3660
SL
1660
3075
1765
3260
1870
3455
1975
2000
1885
3485
2000
3705
2120
3930
2330
4370
4000
2145
3970
2280
4225
2425
4510
2805
5365
3440
6785
6000
2450
4550
2610
4855
2970
5660
8000
2845
5320
3255
6260
3765
7490
10000
3580
4610
6950
9465
4145
8350
4855
10275
5405
11690
---
12000
23 September 2003
208PHTR02
TOTAL
TOTAL
ROLL
FT
8750
40°C
30'C
2O'.C
10'C
TAKEOFF
For Training Pu rposes Only
--
-
---
f
-(
(
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
(
Cessna
MODEL SERIES
208
" .
2088 (675 SHP)
(
208B (675 SHP)
WITHOUT CARGO POD
(
(
\
TAKEOFF DISTANCE
(
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50'FEET)
,
(
FLAPS 0°
(
CONDITIONS:
Flaps 0 0
(
1900 RPM
(
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 5-8
Paved, Level, Dry Runway
Zero Wind
(
(
(
(
(
[
(
"
I
~<
(
(
{
(
(
(
NOTES:
1. Use Type II or Type "IV anti-ice fluid takeoff technique as specified in
Section 4.
2. Decrease distances 10% for each "11 knots headwind. For operation
with tailwinds up to 10 knots, increase distances by 1 0% for each 2
knots.
3. For operation on a dry, grass runway, increase distances by 15% of
" the "ground roll" figure.
.
4. With takeoff power set below the torque limit (1865 ft-Ibs), increase
distance (both ground roll and total distance) by 3% for inertial
separator in BYPASS and increse ground roll 5% and total distance
9% for cabin heat on.
5. Where distance values have been replaced by dashes, operatin~
temperature limits of the airplane would be greatly exceeded. Those
distance which are included by the operation slightly exceeds the
temperature limit are provided for interpolation purposes only.
(
(
('
. ....
.-
~~~)
For Trahling Purposes Only
23 September 2003
208PHTR02
Cessna
MODEl. SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
)
)
IThis Page
)
Intentionally Left Blank
I
j
)
)
)
)
)
)
)
)
)
)
)
23 September 2003
208PHTR02
For Training Purposes Only
(
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
(
Cessna
MODEL SERIES
208
(
(
(
(
('
'I,
(
(
(
(
(
(
IThis Page
(
Intentionally Left Blank
I
(
(
(
.<'
(
( \;
(
(
ForTralning Purposes Only
23 September 2003
20BPHTROi
Cessna
MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
.
SECTION 5 - PERFORMANCE - TAKEOFF
2088 (675 SHP)
CARGO POD INSTALLED
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS 0
Wf.
SPEED
KIAS
LBS
LIFT
OFF
AT
PRES
ALT
FT
50
GRND FEET TC GRND FEETTC
8300
83
83
104
104
CLEAR
ROLL
CLEAR
ROLL
CLEAR
ROLL
CLEAR
FT
50FT
FT
50FT
FT
50FT
FT
50FT
4375
2490
4640
2945
3565
5575
4400
....
8845
7300
83
104
104
23 September 2003
208PHTR02
aBS
OBS
OBS
2350
SL
2085
3880
2215
2000
2370
4410
2520
4695
2675 ·
4990
4000
2700
5045
2875
5380
3065
5750
6000
3095
5805
3300
6205
3n5
7295
6900
---
8000
3605
6825
4150
8105
4825
9810
10000
4575
9045
53301
1005
6295
13795
12000
5955
12585
70401
5865
---
---
SL
1965
3650
2085
3875
2210
4110
2340
4355
2000
2230
2540
4145
2370
4410
2515
4685
'Z770
5230
4735
2705
5050
2880
5395
3345
6465
5445
6395
3100
3895
5815
7580
3545
4520
6830
9150
4125
8260
8000
2910
3385
--
---
10000
4285
8450
4990
10255
5880
12805
----
12000
5570
11705
6570
14690
--
----
--p-
4000
83
OBS
4125
6000
7800
GRND FEETTC GRND FEETTC
ROLL
FT
8750
/
TOTAL
TOTAL
TOTAL
TOTAL
40·C
3O· C
20·C
10·C
TAKEOFF
J
0
-------
---
4050
1830
3395
1940
3605
2060
3825
2180
2075
3855
2205
4100
2340
4355
2575
4855
4000
2365
4400
2515
4690
2680
5010
3105
5990 ·
3825
7630
2705
5055
2885
5400
3290
6325
3145
5930
3615 .
7015
4190
8445
-
10000
3975
7810
4620
9450
5435
11750
--
12000
5155
10765
6065
13450
--
----
----
--
SL
1695
3145
1800
3340
1910
3540
2020
2000
1925
3570
2045
3795
2170
4030
2385
4490
4000
2190
4075
2330
4340
2485
4635
2875
5530
3750
6000
2505
4675
2670
4990
3045
5835
3535
8000
2910
5475
3340
6465
3870
n65
----
7025
..---
10000
3675
7190
4260
8680
5005
10750
12000
4750 .
9865
5580
12275
--
----
-----
--
For Training Purposes Only
)
---
SL
8000
)
-
2000
6000
)
--
)
PILOT'S OPERATING HANDBOOK
TEMPORARY.REVISION
(
208
.
2088 (675 SHP)
(
(
2088 (675 SHP)
CARGO POD INSTALLED
(
I
(
TAKEOFF DISTANCE
\.
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
(
FLAPS 0°
(
CONDITIONS:
Flaps 0°
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 5-8
Paved, Level, Dry Runway
Zero Wind
Cargo Pod Installed
(
(
(
(
(
(
NOTES:
1. Use Type II or Type IV anti-ice fluid takeoff technique as specified in
Section 4.
2. Decrease distances 10% for each 11 knots headwind. For operation
with tailwinds up to 10 knots, increase distances by 10% for each 2
knots.
3. For operation on a dry; grass runway, increase distances by 15% of
the "ground roll" figure.
4. With takeoff power set below the torque limit (1865 ft-Ibs), increase
distance (both ground roll and total distance) by 3% for inertia
separator in BYPASS and increse ground roll 5% and total distance
9% for cabin heat on.
5. Where distance values have been replaced by dashes, operatin~
temperature limits of the airplane would be greatly exceeded. ThoSE
distance which are included by the operation slightly exceeds the
temperature limit are provided for interpolation purposes only.
(
(
Cessna
MODEL SERIES
/
\,
(
(
I
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t· .·./
For Training Purposes Only
23 September 2003
208PHTR02
Cessna
MODEL SERIES
208
PILOT'S OPERATING HANDBOOK
TEMPORARY REVISION
)
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IThis Page Intentionally Left Blank I
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23 September 2003
208PHTR02
For Training Purposes Only
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NOTICE
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This document is for use in a Flig~~S~fety
International classroom training,eri",ironment
only and not tobe used in an .,~iraraft. At the
time of issuance, this Manual,was an exact
duplicate of the official Pilot', Operating
Handbook and is to be used tOr general
purposes only.
'
It will not be kept current and therefore
cannot be used ass'substitute for the official
Pilot's Operating Handbook intended for
operation of theaiJplane.
,
,
FlightSafety International
January 22, 2004
( ,)
--_...._----------_....
ADR#I058
For Training Purposes Only
·
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)
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For Training Purposes Only
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A Textron Company
(
(
Pilot's Operating Handbook
(
and
FAA Approved Airplane Flight Manual
(
(
(
(
(
FAA APPROVED IN THE NORMAL
I
The Cessna Aircraft Company
CATEGORY BASED ON FAR 23. THIS ~=====:;:;:::;:::;:::;:======.
DOCUMEN:r MUST BE CARRIED IN
Model 208
. THE AIRPLANE AT ALL TIMES.
WITH PT6A-114A (675 SHP) ENGINE
APPROVED
B~4d.fJ~A.IflU'.f
Wendell W. Come II
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
[lATE OF APPROVAL
7
Serial No. _ _ _ _ __
Registration No. _ _ __
REFER TO PARAGRAPH 'COVERAGE' ON
PAGE viii OF THIS HANDBOOK FOR AIRPLANE SERIAL EFFECTIVITY.
ApR.I L. 1998
THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT
BY THE FEDERAL AVIATION REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY
THE CESSNA AIRCRAFT COMPANY, AND CONSTITUTES THE FAA APPROVED AIRPLANE
FLIGHT MANUAL THIS HANDBOOK MEETS GAMA SPECIFICATION NO.1 . SPECIFICATION
FOR PILOT'S OPERATING HANDBOOK, ISSUED FEBRUARY 15. 1975 AND REVISED 18
OCTOBER 1996.
@
COPVRIGHT© 1998
The Cessna Aircraft Company
. Wichita, Kansas USA
Member of GAMA
Original Issue - 1 April 1998
For Training Purposes Only
THIS MANUAL WAS PROVIDED FOR THE
AIRPLANE IDENTIFIED ON THE TITLE PAGE ON
SUBSEQUENT
REVISIONS
SUPPLIED
BY
THE
CESSNA
AIRCRAFT COMPANY MUST BE PROPERLY
)
INSERTED.
)
The Cessna Aircraft Company, Aircraft Division
)
)
)
)
)
)
)
)
)
For Training Purposes Only
(
,
. CESSNA
PUBLICATION PART NUMBER
MODEL 208 (675 SHP)
(
(
"
(
(
(
,
Pilot's Operating Handbook
(
(
and
(
FAA Approved Airplane Flight Manual
Serial Numbers 20800277 and On
ORIGINAL ISSUE - 1 April 1998
REVISION 6 - 30 OCTOBER 2002
I
PART NUMBER: D1352-6-13PH
I
iIi
Revision 6
For Traininl! Purooses Onlv
)
)
)
)
)
)
)
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)
)
)
)
)
For Ti'ainingPurposes Oldy
CESSNA
/'
CONGRATULATIONS
MODEL 208 (675 SHP)
,(
CONGRATULATIONS ....
(
Welcome to the ranks of Cessna owner/operators! Your Cessna has been
designed and constructed to give you the most in performance,economy
and comfort. It is our desire that you will find flying it a pleasant and
profitable experience .
This Pilot's Operating Handbook has been prepared as a guide to help you
get the most utility from your airplane. It contains information about your
Cessna's equipment, operating procedures, performance and suggestions
for its servicing and care. Please study it carefully and refer to it often.
The worldwide Cessna Organiz-ation and Cessna Product Support stand
ready to serve you . You will find the following services are offered by each
Cessna Service Station:
,.
(
\
• THE CESSNA WARRANTY, which provides coverage for parts and
labor, is iivailable at Cessna Service Stations worldwide . Specific
benefits and provisions of warranty, plus other important benefits for
you are contained in your Customer Care Program Handbook
supplied with your airplane. Warranty service is available to you at
authorized Cessna Service Stations throughout the world upon
presentation of your Customer Care Card which establishes your
eligibility under the warranty.
• FACTORY-TRAINED PERSONNEL to provide you with cO\Jrteous,
expert service .
• FACTORY-APPROVED SERVICE
efficient and accurate workmanship.
EQUIPMENT
to
provide
you
• A STOCK OF GENUINE CESSNA SERVICE PARTS on hand when
you need them.
• THE LATEST AUTHORITATIVE INFORMATION FOR SERVICING '
CESSNA AIRPLANES, since Cessna Service Stations have all of the
Maintenance Manuals and Parts Catalogs, kept current by Cessna
Service Bulletins and Cessna Service Newsletters, published by
. Cessna Aircraft Comp,any.
We urge all Cessna owners/operators to use the Cessna Organization to
the fullest.
(" .::
~~/
A current Cessna Sales and Service Directory accompanies your new
airplane. The Directory is revised frequently, and a current copy can be
obtained from your Cessna Service Facility. Make your Directory one of
your cross-country flight planning aids.
iii
. 1 April 1998
For Training Purposes Only
CESSNA
MODEL20B (675 SHP)
GENERAL
INFORMATION
GENERAL INFORMATION
WITHOUT CARGO POD
1* SPEED (KTAS) :
Maximum Cruise at 10,000 FT .. . . . . . . . . . . 1B6 KNOTS
Maximum Cruise at 20,000 FT
. . . . . . . . . .. 174 KNOTS
RANGE: With 2224 pounds usable fuel and fuel allowance for
engine start, taxi, takeoff, climb, descent and 45
minutes reserve.
932NM
Max Cruise at 10,000 FT ... . . . .. . . . Range
5.1 HRS
Time
Max Cruise at 20,000 FT .
1220 NM
Range
7.13 HRS
Time
Max Range at 10,000 FT . . . ... ..... Range
10B5 NM
Time
7.0HRS
1295 NM
Max Range at 20,000 FT . . ... .. . .. . Range
Time
B.3 HRS
RATE OF CLIMB AT SEA LEVEL . . ......... . . .
1234 FPM
MAXIMUM OPERATING ALTITUDE . . .. .... . ... .
25,000 FT
TAKEOFF PERFORMANCE :
Ground Roll .. . ... . .. . .......... . .. . . . ....
1160 FT
Total Distance Over 50 FT Obstacle . . . ... ... .. 2053 FT
LANDING PERFORMANCE:
745 FT
Ground Roll ... . .................. . ...... .
Total Distance Over 50 FT Obstacle . . .. . ... . . . 1665 FT
STALL SPEED (KCAS):
Flaps Up, Idle Power . .. .... ..... ....... .
75 KNOTS
Flaps Down, Idle Power . . . .. . . . . . ....... .
61 KNOTS
MAXIMUM WEIGHT:
Ramp
B035 LBS
Takeoff
BOOO LBS
Landing
7800 LBS
"
/
"
)
)
)
)
*
Speeds are based on mid-cruise weight.
)
)
)
iv
29 September 1998
For Training Purposes Only
)
)
CI;:SSNA
MODEL 208 (675 SHP)
GENERAL
INFORMATION
GENERAL INFORMATION
WITHOUT CARGO POD
(Continued)
\
STANDARD EMPTY WEIGHT .. . ... . ..... . .... . 3925 LBS
MAXIMUM USEFUL LOAD .. . . . ..... .. .. . .. . . . 4110 LBS
WING LOADING: Lbs/SqFt . .......... . ........ . . ..
28.6
POWER LOADING Lbs/HP . ... . . . ... . . . .. . . . . . . . . .
11 .9
335.6 GAL
FUEL CAPACITY .... . . . . . .. .. .. . ..... . . .. .
OIL CAPACITY . . . . . . . . . . . . .... . . .... . . . ... . .
14 QTS
PT6A-114A
ENGINE: Pratt & Whitney Canada . . . . .. . . . ....
Free Turbine Flat Rated
at 675 Shaft Horsepower
PROPELLER:
McCauley 3-bladed, Constant Speed,
Full Feathering, Reversible. Diameter:
1061N
NOTE
The above performance figures are based on indicated
weights. standard atmospheric conditions, level, hardsurfaced dry runways and no wind . They are calculated
values derived from flight tests conducted by The Cessna
Aircraft Company under carefully documented conditions
and will vary with individual airplanes and numerous
facto rs affecting performance. Performance for other
operational conditions can be derived by reference . to
operational data in other sections of this handbook.
v
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
GENERAL
INFORMA TION
)
GENERAL INFORMATION'
)
WITH CARGO POD
)
1* SPEED (KTAS):
)
Maximum Cruise at 10,000 FT ............
177 KNOTS
Maximum Cruise at 20,000 FT
. . . . . . . . . . . 165 KNOTS
RANGE: With 2224 pounds usable fuel and fuel allowance for
engine start, taxi, takeoff, climb, descent and 45
minutes reserve.
891 NM
Max Cruise at 10,000 FT .. , ....... . Range
Time
5.1 HRS
1155 NM
Max Cruise at 20,000 FT .. . . . . . . . .. Range
Time
7.1 HRS
1028 NM
Max Range at 10,000 FT ........... Range
Time
6.9 HRS
1199 NM
Max Range at 20,000 FT ........... Range
7.9 HRS
Time
1175 FPM
RATE OF CLIMB AT SEA LEVEL ............ . .
MAXIMUM OPERATING ALTITUDE .. ... . ... . .. .
25,000 FT
TAKEOFF PERFORMANCE:
Ground Roll .... . . ... . .. ....... ... ...... .
1170 FT
Total Distance Over 50 FT Obstacle . .... . .... . 2090 FT
LANDING PERFORMANCE:
Ground Roll .... . ........... . ' . . . .. .. . . .. . .
710 FT
Total Distance Over 50 FT Obstacle . . ........ . 1600 FT
STALL SPEED (KCAS):
, Flaps Up, Idle Power . .. .. ..... . . ... .... .
75 KNOTS
Flaps Down, Idle Power ................. .
61 KNOTS
MAXIMUM WEIGHT:
Ramp
8035 LBS
Takeoff
8000 LBS
Landing
7800 LBS
)
.,
)
)
)
)
)
)
)
)
)
)
)
)
)
)
-,
Speeds are based on mid-cruise weight.
vi
)
29 September 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
GENERAL
INFORMATION
(
GENERAL INFORMATION
(
WITH CARGO POD
(
(Continued)
( /"
\
(
STANDARD EMPTY WEIGHT . . .. . . . . . ...... . . . 4305 LBS
MAXIMUM USEFUL LOAD .. . .. . ..... . . . .... ..
3730 LBS
28.6
WING LOADING: Lbs/Sq Ft .. . . . . . .. . . . ............
POWER LOADING Lbs/HP . .. ... . ... . . . .. .........
11 .9
335.6 GAL
FUEL CAPACITY . . . .... . . . . .. . .. . .... .. .. .
OIL CAPACITY .. .. . . . . ...... . .. . .. .... . . . . ..
14 aTS
ENGINE: Pratt & Whitney Canada .. ...... .. ...
PT6A-114A
Free Turbine Flat Rated
at 675 Shaft Horsepower
PROPELLER:
McCauley 3-bladed, Constant Speed,
Full Feathering, Reversible. Diameter:
1061N
(
(
(
(
(
(
(
(
(
\,
(
NOTE
(
.' The above performance figures are based on indicated
weights, standard atmospheric conditions, level, hardsurfaced dry runways and no wind. They are calculated
values derived from flight tests conducted by The Cessna
Aircraft Company under carefully documented conditions
and will vary with individual airplanes and numerous
factors affecting performance. Performance for other
operational conditions can be derived by reference to
operational data in other sections of this handbook.
(
(
(
j
".
,
\'i .-'
vii
1 April 1998
For Training Purposes Only
GENERAL
INFORMATION .
CESSNA
MODEL 208 (675 SHP)
COVERAGE
The Pilot's Operating Handbook in the airplane at the time of
delivery from The Cessna Aircraft Company contains information
applicable to the Model 208 (675 SHP) airplane by serial number
and registration number shown on the Title Page. This handbook
is applicable to airplane serial number 2080277 and On. All
information is based on data available at the time of publication.
This handbook is comprised of eight sections which cover
operational aspects of a standard-equipped airplane. Section 9,
Supplements, provides expanded operational procedures for the
avionics equipment (both standard and optional). operational
procedures for various optional systems, and provides information
on special operations.
Supplements in Section 9 are stand-alone documents. and may
be issued or revised without regard to ·revision dates which apply
to . the POH itself. These supplements contain their own Log of
Effective ·Pages, which should be used to determine the status of
each and every individual supplement.
)
)
)
ORIGINAL ISSUE AND REVISIONS
This Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual was originally issued on 1 April, 1998. To ensure
that information in this manual is current, revisions must be
incorporated as they are issued. Revision status is noted on Page
i of th.is section, and also in the ~og of Effective Pages table.
The part number of this manual is also coded to .aid the
owner/operator in determining the revision level of the POH. As
revisions to the POH are issued, the Part Number will change to
reflect that revision. Refer to the example below:
01352 - 02 - 13PH
U
Series of Book (Pilot Operating Handbook)
Revision Level
Base Manual Part Number
viii
29 September 1998
For Training Purposes Only
)
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
/" ..•.
(
(
\
GENERAL
INFORMATION
It is the responsibility of the airplane owner to maintain this handbook in a current status when it is being used for operational purposes. Owners should contact their Cessna Service Station whenever the revision status of their handbook is in question.
Revisions are distributed to owners of U.S. Registered aircraft
according to FAA records at the time of revision issuance, and to
Internationally Registered aircraft according to Cessna Owner
Advisory records at the time of issuance. Revisions should be
read carefully upon receipt and incorporated in this POH.
(
(
REVISION FILING INSTRUCTIONS
(
REGULAR REVISIONS
(
(
(
Pages to be removed or inserted in the Pilots' Operating
Handbook and FAA Approved Airplane Flight Manual are
determined by the Log of Effective Pages located in this section.
This log contains the page number and date of issue for each
page within the POH. At original issue, all pages will contain the
same date. As revisions to the POH occur, these dates will
change on effected pages. When two pages display the same
page number, the page with the latest date shall be inserted into
the POH. The date on the Log Of Effective Pages shall also agree
with the latest date of the page in question.
(
TEMPORARY REVISIONS
( /
'.
(
(
(
Under limited circumstances, temporary revisions to the POH may
be issued. These temporary revisions are to be filed in the
applicable section in accordance with filing instructions appearing
on the first page of the temporary revision.
The recession of a temporary revision is accomplished by
incorporation into the POH at revision time or by a superseding
temporary revision. In order to accurately track the status of
temporary revisions as they pertain to a POH, a Temporary
Revision List will be located previous to this section when
required. This list will indicate the date the temporary revision was
incorporated into the POH, thus authorizing the recession of the
temporary revision.
ix
1 April 1998
For Training Purposes Only
GENERAL
INFORMATION
CESSNA
MODEL 208 (675 SHP)
IDENTIFYING REVISED MATERIAL
Additions or revisions to the text in an existing section will be
identified by a vertical line (revision bar) adjacent to the applicable
revised area on the outer margin of the page.
When technical changes cause unchanged text to appear on a
different page, a revision bar will be placed in the outer lower
margin of the page, opposite the page number and date of the
page, providing no other revision bar appears on the page. These
pages will display the current revision date as found in the
Original Issue and Revisions paragraph of this section.
When extensive technical changes are made to text in an existing
section that requires extensive revision, revision bars will appear
the full length of text.
New art
pOinting
number.
adjacent
added to an existing section will be identified by a single
hand indicator adjacent to the figure title and figure
EXisting art which is revised will have a pointing hand
to the portion of the art which has changed . .
WARNINGS, CAUTIONS AND NOTES
'
)
)
)
)
)
)
)
)
)
)
Throughout the text, warnings, cautions and notes pertaining to
airplane handling and operations · are utilized. These adjuncts to
the text are used to highlight or emphasize important points.
WARNING - Calls attention to use of methods, procedures or
limits which must be followed precisely to avoid injury or death
to persons.
CAUTION - Calls attention to methods,procedures or limits
which must be followed to avoid damage to equipment.
)
)
)
NOTE - Calls attention to additional procedures or information
pertaining to the text.
)
)
x
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
(
CONTENTS
(
(
(
~/"
.
,-
\
(
TABLE OF CONTENTS
(
(
(
SECTION
(
(
GENERAL
(
LIMITATIONS
(
(
(
(
{'
i,_.
(
(
(
(
(
(
.........................
2
EMERGENCY PROCEDURES .......... . . .
3
NORMAL PROCEDURES
................
4
PERFORMANCE ..................... . .
5
WEIGHT & BALANCE/EQUIPMENT LIST ......
6
AIRPLANE & SYSTEMS DESCRIPTION ." . . ..
7
HANDLING, SERVICE & MAINTENANCE .....
8
SUPPLEMENTS
9
.......................
xiii/xiv
1 April 1998
For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
)
CESSNA
MODEL 208 (675 SHP)
(
LOG OF EFFECTIVE PAGES
LOG OF EFFECTIVE PAGES
(
The following Log of Effective Pages provides the date of issue for
original and revised pages, as well as a listing of all pages in the
POH. Pages which are affected by the current revision are
indicated by an asterisk (*) preceding the pages listed. Pages which
contain a slash (I) mark indicate a blank page on the backup
(Example: ilii indicates that page ii, which backs up page i, is
blank).
(
(
(
(
(
Revision Level
(
o (Original Issue)
Revision 1
Revision 2
Revision 3
(
(
. .. ..
Date of Issue
1 April 1998
29 September 1998
. .. 8 March 1999
13 October 1999
(
PAGE
(
AlB .. .. .. . . . ....
Title ... . . . . . . . . .
• ~~signment Record .
(
(
(
(
•
(
(
•
*
•
(
t
'.'
"-'4;;'>'
*
DATE
1 April 1998
1 April 1998
1 April 1998
1/11 •• • • ••• • ••• • •••
Revision 6
iii ........... ....
1 April 1998
29 September 1998
iv .... . . . .
v .. ........... ..
1 April 1998
vi .... . . . .
29 September 1998
1 April 1998
viithru x . .. .... . .
xi thru xii ... . . .. . ..
Revision 6
1 April 1998
xiii/xiv . .. .... . . . .
1-1 . . . . . . . . ..
13 October 1999
1 April 1998
1-2 thru 1-3 . . . .. ..
13 October 1999
1-4 . .... . . . ..
1-5 . .... .. ... .. ..
1 April 1998
1-6 thru 1-7 ... . . . . .
Revision 6
1 April 1998
1-8 . .. ... ..... . .
1-9 ........ ..
13 October 1999
1-10 thru 1-15 . . . . .
1 April 1998
1-16 . . . . . . • . . 13 October 1999
2-1/2-2 ..... . . . . .
1 April 1998
2-3 thru 2-5 . .. . ...
1 April 1998
2-6 .. . ... .. 15 November 2000
2-7 .. . .... . . .. . .
1 April 1998
2·8 thru 2-9 ........
ReviSion 6
7 September 2001
2-10 . .. ... .
2-11thru2-15 .....
1 April 1998
2-16 thru 2-17 . . . . ..
Revision 6
1 April' 1998
2-18 ........ . . . .
2-19 thru 2-20 . . . . . .
Revision 6
2-21 . . . . . . . . . . . .
1 April 1998
2-22 .. . . . . . . . . .
8 March 1999
2-23
15 November 2000
Revision Level
Revision 4
Revision 5
Revision 6
PAGE
Date of Issue
15 November 2000
7 September 2001
30 October 2002
DATE
2-24 thru 2-26
1 April 1998
29 September 1998
2-27 . .... .
7 September 2001
2-28 . . ......
3-1 thru 3-2 . 29 September 1998
3-3/3-4 . ...
29 September 1998
1 April 1998
3-5 thru 3-15 ..
3-16
7 September 2001
3-17 ............
1 April 1998
3-18 .. ... .. 15 November 2000
Revision 6
• 3-19 .. ....... . . ..
3-20 thru 3-21
29 September 1998
3-22 thru 3-37
1 April 1998
3-38 .. .. ; .. 15 November 2000
3-39 thru 3-42
29 September 1998
8 March 1999
3-43 . ..........
3-44 .. .... ..... .
1 April 1998
4-1 .. . . . . . . . . . . . . 1 April 1998
4-2 . . ... • . . 15 November 2000
4-3 thru 4-5 .. . ... .
1 April 1998
4-6 .. .. . . . .
7 September 2001
4-7 .. ..... . 15 November 2000
4-8 thru 4-12 . .... .
1 April 1998
29 September 1998
4-13 .. . ...
4-14 thru 4-17 . . 13 October 1999
4-18 thru 4-22
1 April 1998
4-23 .... ... 15 November 2000
4-24 thru 4-25
1 April 1998
4-26 thru 4-27
15 November 2000
4·28 .. . . . . .
7 September 2001
4-28A . .. ...
7 September 2001
4-288 ..... .
7 September 2001
4-29 thru 4-32 . . . . .
1 April 1998
x
Revision 6
for Training Purposes Ollly
LOG OF EFFECTIVE PAGES
, CESSNA
MODEL 208 (675 SHP)
DATE
•
•
•
•
•
•
•
•
4-33 thru 4-34 '29 September 1998
4-35
7 September 2001
4-36 . . . . . . . . . . . .
1 April 1998
4-37 thru 4-38 .. 13 October 1999
4-39 thru 4-48 .....
1 April 1998
4-49
7 September 2001
4-50 .... .... .. ..
1' Apri11998
4-51
29 September 1998
4-52
15 November 2000
5-1 ... . . . . . . . . . . .
Revision 6
5-2 .. . . . . . . . . ;. .
1 April 1998
5-3/5-4 . .......' . .
1 April 1998
5-5 thru 5-6 . .. . .. .
1 April 1998
5-7 . . . .....
7 September 2001
5-8 thru 5-20 . . ....
1 April 1998
5-21
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Revision 6
5-22 thru 5-52 .. .. .
1 April 1998
5-53 .. . . . . . . . . . . .
Revision 6
5-54 thru 5-84 .. ...
1 April 1998
6-1/6-2 ... .... ...
1 April 1998
6-3 ..... . . .. . ...
1 April 1998
6·4 ....... ... 13 October 1999
6-5 thru 6-22 .. . ...
1 April 1998
6-23
7 September 2001
6-24 thru 6-28 . .. ..
1 April 1998
6-29 . . .. .. . . . . . . .
Revision 6
6-30 thru 6-50 .....
1 April 1998
6-51/6-52 .........
1 April 1998
7-1 .. . . . . . . . . . . .
1 April 1998
7-2 ........ . : ....
Revision 6
7-3 . ........... .
1 April 1998
7-4 .... . . . .
7 September 2001
7'5/7-6 . . . . . . . . . .
1 April 1998
7-7 ....... .. . 13 October 1999
7-8 thru 7-15 . . ....
1 April 1998
7-16 " . . . . . . . . . . .
Revision 6
7-17 thru 7-19
29 September 1998
7-20 thru 7-22
1 April 1998
7-23
7 September 2001
7-24 thru 7-40
1 April 1998
7-41
15 November 2000
7-42
7 September 2001
7-43 thru 7-44
1 April 1998
7-45 thru 7-48
Revision 6
7-49 " . . . . . . . . . .
1 April 1998
7·50 . . .. . . . . . . . . .
Revision 6
7·51 thru 7·56 .. ...
1 April 1998
7·57 thru 7-60
29 September 1998
7·61
.. ... .. .. .. .
1 April 1998
7·62
7 September 2001
7-63 thru 7·68
1 April 1998
" 7 -69 ... .. ... . . . . .
Revision 6
7·70 thru 7-77
1 April 1998
• 7-78 thru 7-79
Revision 6
7-80 thru 7-92
1 April 1998
7-93 thru 7-96
7 September 2001
7-97 thru 7-101
1 April 1998
• 7·102 ..... .. . ....
Revision 6
7·10317·104 .. .. ...
1 April 1998
8 -1 thru 8-13 . . .. ..
1 April 1998
• 8-14 thru 8·15 . . . .. .
Revision 6
8-16 thru 8·18 .....
1 April 1998
• 8-19 . .. ........ ..
ReviSion 6
8-20 ............
1 April 1998
• 8·21 thru 8·22
Revision 6
8-23 thru 8·24
1 April 1998
• 8-25 thru 8-29 .. ;. ..
Revision 6
8 -30 thru 8-39 . . . . 8 March 1999
8-40 ... . .... . ...
1 April 1998
8-41 ..... . . . . . .
a March 1999
8-42 thru 8-50 .....
1 April 1998
8-51 thru 8-52 .... 8 March 1999
9-1 . . . . . . . . . . . . .
1 April 1998
9-2 . ...... . 15 November 2000
NOTE
Refer to Section 9 Log of
Approved
Supplements
for
supplements
applicable
to
optional systems.
APPROVED BY
lM~o:.:,,--'
........
_ _ ao • • c.
~~t;,..J
....__ .
~
30 Oc'TIOaUl...
~OOL
)
DATE OF APPROVAL
xii
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Revision 6
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 1
GENERAL
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SECTION 1
GENERAL
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TABLE OF CONTENTS
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Page
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:
Three View . .. . ..... . . .. ... . .. . . . . ... ... . .. . .....
Introduction ... .... . .. ......... .. . . . . . ............
Descriptive Data ... . .............. . ... .. ..........
Engine ........... . ........ . . . .. . .............
Propeller . ........................ .. .......... .
Fuel . . . ....... .. ....... . ... . .. .. . . .... . ... ...
Oil ....... . .... . ....... . ..... . .. ... ... . ... . ..
Maximum Certificated Weights
............... .. . ...
Standard Airplane Weights ...... . .... .. .. .. . ......
Cabin And Entry Door Dimensions .... . .... . .........
Baggage/Cargo Compartment And Cargo Door Entry
Specific Loadings .. ........ .. ........ ... . .......
Symbols, Abbreviations and Terminology .... . ... .. .... .
General Airspeed Terminology And Symbols . . . . . . . ...
Meteorological Terminology .. . . . .... . .... .. . . . . . . . .
Engine Power Terminology . . .. ... . . ... . . . ... . ....
Airplane Performance And Flight Planning Terminology
Weight And Balance Terminology . .. ... ............
Autopilot/Flight Director And IFCS Terminology ........
Ground Operations Stall Warning Disable Switch .... . ....
1-2
1-4
1-5
1-5
1-5
1-6
1-7
1-8
1-9
1-9
1-9
1-9
1·10
1·10
1·11
1·11
1·13
1-14
1-16
1-161
1-1
13 October 1999
For Training Purposes Only
SECTION 1
GENERAL
CESSNA
MODEL 208 (675 SHP)
CABIN SIDE WINDOWS
AND THE RIGHT HAND
AFT PASSENGER DOOR
ARE NOT INSTALLED ON
THE CARGO VERSION.
CARGO VERSION
)
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20'-6"-1
)
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PIVOT POINT
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1 . - - - - - - - - 5 2 ' - 1"
---~---...
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106"
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~11 ' - 8,--1
26857001
26857001
Figure 1-1. Three View (Sheet 1 of 2)
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1-2
1 April 1998
For Training Purposes Only
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(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 1
GENERAL
(
(
(
I/~ -"
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(
,..." ' 1 - - - - - - - - - 3 7 ' - 7" --------.~I
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NOTES:
(
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( (
,-
....,
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1. Dimensions shown are based on standard empty weight
and proper inflation of standard nose and main gear tires.
Tail height may increase with oversize tires.
2. Wing span dimension includes strobe lights.
3. Maximum height shown with nose gear depressed as far as
possible.
.
4. Wheel base length is 11' -7 1/2".
5. Wing area is 279.4 square feet.
S. Minimum turning radius (*pivot point to outboard wing tip
strobe light) is 31' - 10 1/2".
7. McCauley propeller ground clearance with standard tires:
Nose tire inflated and nose gear barrel extended
41/2": 1S".
Nose tire deflated and nose strut fully compressed: 9".
26857001
Figure 1-1. Three View (Sheet 2 of 2)
1-3
1 April 1998
For Training Purposes Only
SECTION 1
GENERAL .
CESSNA
MODEL 208 (675 SHP)
INTRODUCTION
This handbook contains 9 sections, and includes the material
required to be furnished to the pilot by Federal Aviation Regulations:
and additional information provided by Cessna Aircraft Company.
This handbook constitu.tes the FAA Approved Airplane Flight
Manual.
A WARNING
This handbook is not intended to be a guide for
basic flight instruction or a training manual and
should not be used as one. It Is not a substitute
for adequate and competent flight Instruction,
pilot skill, and pilot knowledge of current
airworthiness directives, applicable federal
. aviation regulations and/or advisory circulars.
A WARNING
I
Assuring the airworthiness of the airplane is the
responsibility of the airplane owner or operator.
Determining If the airplane Is safe for flight Is
the responsibility of ~he pilot in command. The
pilot is also responsible for adhering to the
operating limitations set forth by Instrument
markings, placards, and this Pilot's Operating
Handbook and FAA Approved Airplane Flight
Manual.
Genera"y, information in this handbook is applicable to both the
Passenger and Cargo versions. Where differences exist between
the versions, they are noted in both text and illustration.
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1-4
13 October 1999
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
(
SECTION 1
GENERAL
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I
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Section 1 provides basic data and information of general interest. It
also contains definitions or explanations of symbols, abbreviations,
and terminology commonly used.
DESCRIPTIVE DATA
(
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ENGINE
(
Number of Engines: 1
Engine Manufacturer: Pratt & Whitney Canada, Inc.
Engine Model Number: PT6A-114~ ?
Engine Type:
Free turbine, two-shaft engine
utilizing a
compressor section having three axial stages and
one centrifugal stage, an annular reverse-flow
combustion chamber, a one-stage compressor
turbine, a one-stage power turbine, and a single
exhaust. The power turbine drives the propeller
through a two-stage planetary gearbox at the front
of the engine.
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(
(
(
('
\
'"
Horsepower: Flat rated at 675 shaft horsepower.
-'<000 "-??
.
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PROPELLER
(
Propeller Manufacturer: McCauley Accessory Division.
Propeller Model Number: 3GFR34C703/106GA-0.
Number of Blades : 3.
Propeller Diameter:
(
(
(
Maximum : 106 inches.
Minimum: 104 inches.
Propeller Type :
Constant-speed, full-feathering, reversible, hydraulicallyactuated aluminum-bladed propeller, with a feathered
blade angle of 88°, a low pitch blade angle of 15.6°,
and a maximum reverse blade angle of -14° (30-inch
station).
1-~
1 April 1998
For Training Purpos~s Only
CESSNA
MODEL 208 (675 SHP)
SECTION 1
GENERAL
)
)
FUEL
Approved Fuel Grade (Specification):
)
.... JET A (ASTM-D1655) .
JETA-1 (AST M-D1655).
JET B (ASTM-D1655).
JP-1 (MIL-L-5616).
JP-4 (MIL-T-5624).
JP-5 (MIL-T-5624).
JP-8 (MIL-T-83133A) .
)
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Alternate/Emergency Fuels:
)
Aviation Fuel (All grades of military and commercial aviation
gasoline).
)
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A
CAUTION
)
Aviation gasoline is restricted to emergency
use and- shall not be used for more than 150
hours in one overhaul period; a mixture of one
part aviation gasoline and three parts of Jet A,
Jet A-1, JP·1, or JP-5 may be used for
emergency purposes for a maximum of 450
hours per overhaul period.
)
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Approved Fuel Additives:
The following additives are required for anti-icing protection:
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Ethylene Glycol Monomethyl Ether.
Diethylene Glycol Monomethyl Ether.
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1-6
Revision 6
For Training Purposes Only
CESSNA
MODEL 208(675 SHP)
SECTION 1
GENERAL
(
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A
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(
CAUTION
JP-4 and JP-5 fuel per MIL-T-5624 and JP-8 fuel per '
MIL-T-83133A contain the correct premixed quantity
(
of an approved type of anti-icing fuel additive and no
additional anti-ice compounds should be added.
(
If additional anti-static protection is desired, the following additivel
is approved for use:
"
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Dupont Stadis 450
(
If additional biocidal protection is desired, the ' following additive is
permitted for use in certain conditions:
'
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Sohio Biobor JF
Kathon FP 1.5
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NOTE
(
~,
Refer to Section 8 for allowable concentrations of
the above additives and additional information.
(
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Fuel Capacity:
(
Total Capacity:
Total Capacity Each Tank:
Total Usable :
(
/
OIL
335,6 U.S. gallons.
167.8 U.S. gallons.
332.0 U.S. gallons.
" 1'
Oil Grade (Specification):
Oil conforming to Pratt & Whitney Engine Service Bulletin No.
1001, and all revisions or supplements thereto, must be used.
Refer to Section 8 for a listing of approved oils.
r~"
l",::
Total Oil Capacity:
14 U.S ~ quarts (including oil in filter, cooler
, and hoses).
Drain and Refill Quantity:
Approximately 9.5 U.S. quarts.
Revision 6
1·7
For Training Purposes Only
SECTION 1
GENERAL
CESSNA
MODEL 208 (675 SHP)
Oil Quantity Operating Range:
Fill to within 1 112 quarts of MAX HOT or MAX COLD (as
appropriate) on dipstick. Quart markings indicate U.S. quarts
low if oil is hot. For example, a dipstick reading of 3 indicates
the system is within 2 quarts of MAX if the oil is cold and within
3 quarts of MAX if the oil is hot.
.v'()\-k~-Z
A WARNING
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Ensure oil dipstick cap Is securely latched
down. Operating the engine with less than the
recommended 011 level and with the dipstick cap
unlatched will result In excessive 011 loss and
eventual engine stoppage.
)
)
NOTE
To obtain an accurate oil level reading, it is recommended
the oil level be checked within 10 minutes after engine
shutdown while the oil is hot (MAX HOT marking) or prior to
the first flight of the day while the oil is cold (MAX COLD
marking). If more than 10 minutes has elapsed since
engine shutdown and engine oil is still warm, perform an
engine dry motoring run before checking oil level.
)
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MAXIMUM CERTIFICATED WEIGHTS
. volr'5e...: 8'=45'0
/
Ramp:
Takeoff:
Landing:
80351bs.
80001bs.
78001bs.
I
)
NOTE
Refer to Section 6 of this handbook tor recommended
loading arrangements in the Passenger Version and Cargo
Version .
1-8
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 1
GENERAL
(
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.r
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STANDARD AIRPLANE WEIGHTS
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Standard Empty Weight
Pa$senger Version :
Cargo Version :
39251bs
4305 Ibs.
Maximum Useful Load
Passenger Version :
Cargo Version :
4110 Ibs.
37301bs.
(
CABIN AND ENTRY DOOR DIMENSIONS
(
Detailed dimensions of the cabin interior and entry door openings
are illustrated in Section 6.
(
(
BAGGAGE/CARGO COMPARTMENT AND
CARGO DOOR ENTRY DIMENSIONS
(
(
( (
(
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f
Dimensions of the baggage/cargo area and cargo door openings are
illustrated in detail in Section 6 of this handbook.
SPECIFIC LOADINGS
Wing Loading: 28.6 Ibs.lsq.ft.
Power Loading: 11 .9 Ibs'/shp.
I
/
13 October 1999
. 1-9
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 1
GENERAL
SYMBOLS, ABBREVIATIONS AND TERMINOLOGY
"
GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS
KCAS
Knots Calibrated Airspeed is indicated airspeed
corrected for position and instrument error and
expressed in knots. Knots calibrated airspeed is equal
to KTAS in standard atmosphere at sea level.
KIAS
Knots Indicated Airspeed ,is the speed shown on the
airspeed indicator and expressed in knots.
KTAS
Knots True Airspeed is the airspeed expressed in
knots relative to undisturbed air which is KCAS
corrected for altitude and temperature.
Maneuvering Speed is the maximum speed at
which full or abrupt control movements may be used
without overstressing the airframe.
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Maximum Flap Extended Speed is the highest
speed permissible with wing flaps, in a prescribed\
extended position.
)
VMO
Maximum Operating Speed is the speed that may
not be deliberately exceeded at any time.
Vs
Stalling Speed or the minimum steady flight
speed is the minimum speed at which the airplane is
controllable.
VSo
Stalling Speed or the minimum steady flight
speed is the minimum speed at which the airplane is
controllable in the landing configuration at the most
forward centerofgravity.
Vx
Best Angle-of-Cllmb Speed is the speed which
results in the greatest gain of altitude in a given
horizontal distance.
Vy
Best Rate-of-Cllmb Speed is the speed which
results in the greatest gain in altitude in a given time.
1 April 1998
1-10
For Training Purposes Only
)
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(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 1
GENERAL
(
(
(
(
(
METEOROLOGICAL TERMINOLOGY
\.
OAT
Outside Air Temperature is the free air static
temperature. It may be expressed in either
degrees Celsius or degrees Fahrenheit.
Pressure
Altitude
Pressure Altitude is the altitude read from an
altimeter when the altimeter's barometric scale
has been set to 29.92 inches of mercury (1013
mb).
ISA
International Standard Atmosphere is an
atmosphere in which:
1. The air is a perfect dry gas;
2. The temperature at sea level is 15°C;
3. The pressure at sea level is 29.92 inches Hg
(1013 .2 mb);
4. The temperature gradient from sea level to the
altitude at which the temperature is -56.S o C is 1.98°C per 1000 feet.
(
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(""
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ENGINE POWER TERMINOLOGY
(
(
Beta Mode
Beta Mode is the engine operational mode in
which propeller blade pitch is controlled by the
power lever. The beta mode may be used during
ground operations only_
Flameout
Flameout is the unintentional loss of combustion
chamber flame during operation.
Flat Rated
Flat Rated denotes constant horsepower over a
specific altitude and/or temperature.
Gas Generator
Gas Generator RPM indicates the percent of gas
generator RPM based on a figure of 100% being
37,500 RPM .
(
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1 April 1998
For Training Purposes Only
1-11 I
SECTION 1
GENERAL
GCU
Hot Start
CESSNA
MODEL 208 (675 SHP)
GCU is the generator control unit.
)
I
Hot Start is an engine start, or attempted start',
which results in an ITT exceeding 1090°C.
ITT
ITT signifies inter-turbine temperature.
Maximum
Climb Power
Maximum Climb Power is the maximum power
approved for normal climb. Use of this power
setting is limited to climb operations . . This power
corresponds to that developed at the maximum
torque limit, lIT of 765°C or Ng limit, whichever is
less·.
Maximum
Continuous
Power
Maximum Continuous Power is the maximum
power rating not limited by time. Use of this power
should be limited to those circumstances which
require maximum aircraft performance (i.e.,
extreme icing conditions or windshear downdrafts) ..
This power corresponds to that developed at thEl(
maximum torque limit, ITT of 805°C or Ng limit, whichever is less.
Maximum
Cruise Power
Propeller RPM
Maximum Cruise Power is the maximum power
approved for cruise and is not time limited. This
power corresponds to that developed at the
maximum specified cruise, torque (Section 5), In
of 740°C or Ng limit, whichever is less.
)
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)
)
Ng signifies gas generator RPM.
)
Propeller RPM indicates propeller speed in RPM.
)
)
Reverse Thrust Reverse Thrust is the thrust produced when the
propeller blades are .rotated past flat pitch into the
reverse range.
RPM
)
)
[
RPM is revolutions per minute.
\~ ..-
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)
1-12
1 April 1998
For Training Purposes Only
)
)
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 1
GENERAL
(
(
(
(
SHP
SHP is shaft horsepower and is
delivered at the propeller shaft
Takeoff Power
Takeoff Power is the maximum power rating and
is limited to a maximum of 5 minutes under normal
operation. Use of this power should be limited to
normal takeoff operations. This power corresponds
to that shown in the Engine Torque For Takeoff
figure of Section 5.
Torque
Torque is a measurement of rotational
exerted by the engine on the propeller.
Windmill
Windmill
inputs.
/ '
the power
\
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(
is propeller rotation
from
force
airstream
(
AIRPLANE PERFORMANCE AND FLIGHT PLANNING
TERMINOLOGY
(
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(
Demonstrated
Crosswind
Velocity
Demonstrated Crosswind Velocity is the
velocity of the crosswind component for which a
dequate control of the airplane during takeoff and
landing was actually demonstrated during
certification tests. The value shown is not
considered to be limiting.
g
9 is acceleration due to gravity.
NMPG
Nautical Miles Per Gallon is the distance which
can be expected per gallon of fuel consumed at a
specific engine power setting and/or flight
configuration.
GPH
Gallons Per Hour is the amount of fuel consumed
per hour.
Usable Fuel
Usable Fuel is the fuel available for flight planning.
Unusable
Fuel
Unusable Fuel is the quantity of fuel that can not
be safely used in flight.
(
(
("" "
\,~.,,)
1-13
1 April 1998
For Training Purposes Only
SECTION 1
GENERAL
CESSNA
MODEL 208 (675 SHP)
WEIGHT AND BALANCE TERMINOLOGY
Arm
Arm is the horizontal distance from the referehce
datum to the center of gravity (C.G .) of an item.
Basic Empty
Weight
Basic Empty Weight is the standard empty weight
plus the weight of optional equipment.
Center of
Gravity
Center of Gravity is the point at which an airplane
would balance if suspended. Its distance from the
reference datum is found by dividing the total
moment by the total weight of the airplane.
C.G.
Arm
Center of Gravity Arm is the arm obtained by
adding the airplane's individual moments and
dividing the sum by the total weight.
C.G.
Limits
Center of Gravity Limits are the extreme center of
gravity locations within which the airplane ·must be
operated at a given weight.
MAC
MAC-(Mean Aerodynamic Chord) of a wing is the (,
chord of an imaginary airfoil which throughout . the
flight range will have the .same force vectors as
those of the wing.
Maximum
Landing
Weight
Maximum Landing Weight is the maximum
weight approved for the landing touchdown.
Maximum
Ramp
Weight'
Maximum Ramp Weight is the maximum weight
approved for ground maneuver, and includes the
weightot fuel used for start, taxi and runup.
Maximum
Takeoff
Weight
Maximum Takeoff Weight is the maximum weight
approved for the start of the takeoff roll.
Moment
Moment is the product of the weight of an item
multiplied by its arm . (Moment divided by the
constant 1000 is used in this handbook to simplify
balance calculations by reducing the number of
digits.)
1-14
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 1
GENERAL
(
(
(
/<
(
Reference
Datum
Reference Datum is an imaginary vertical plane
100 inches forward of the front face of the firewall.
Residual Fuel
Residual Fuel is the fuel remaining when the
airplane is defueled in a specific attitude by the
normal means and procedures specified for
draining the tanks.
.
Scale Drift
Scale Drift may occur on some types of electronic
scales because of the inability of the scale to
return to a true zero reading after weighing. If
present, this deviation from zero should be
accounted for when calculating the net weight of
the airplane.
Standard
Empty
Weight
Standard Empty Weight is the weight of a
standard airplane, including unusable fuel, full
operating fluids and full engine oil.
Station
Station is a location along the airplane fuselage
given in terms of the distance from the reference
datum.
Arm
Arm is the horizontal distance from the reference
datum to the center of gravity (C.G.) of an item.
Tare
Tare is the weight of chocks, blocks, stands, etc.
used when weighing an airplane, and is included
in the scale readings. Tare is deducted from the
scale reading to obtain the actual (net) airplane
weight.
Useful Load
Useful Load is the difference between ramp
weight and the basic empty weight.
(
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{
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f'
(
"
f
\.
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1-15
1 April 1998
For Training Purposes Only
SECTION 1
GENERAL
CESSNA
MODEL 208 (675 SHP)
AUTOPILOT/FLIGHT DIRECTOR AND IFCS TERMINOLOGY
A WARNING
A thorough understanding of the difference between an autopilot, a flight director, and an IFCS
is required before operating any of the components of the KFC-150 Flight Control system. Refer to Section 9, Supplements for complete operating details.
)
)
Autopilot
Autopilot is a system which automatically controls
attitude and/or flight path of the airplane as directed by the pilot through the system's computer.
Flight Director
Flight Director is a system which provides visual
recommendations to the pilot to allow him to manually control the airplane attitude and/or flight path
in response to his desires as selected through the(
system's computer.
'
Integrated
Flight Control
System (IFCS)
IFCS applies to the union of autopilot and flight
director systems which allows the pilot to manage
his flight by observing computed. visual recommendations while the autopilot automatically follows
these recommendations as selected by the pilot
using the system's controls.
GROUND OPERATIONS STALL WARNING DISABLE SWITCH
)
)
)
The following procedure applies to airplane serials 20800316 and
on, and earlier serials modified with Accessory Kit AK208-22:
)
To preclude or disable nuisance stall warnings during ground
operations, push the control yoke forward to the stop. This will
engage the ground stall warning disable switch.
)
)
)
1-16
13 October 1999
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 2
LIMITATIONS
SECTION 2
LIMITATIONS
(
(
(
(
(
TABLE OF CONTENTS
(
Page
(
Introduction .. . . . . . ............ . . ..... . .... . .. . ...
2-3
Airspeed Limitations .. .. ........ .... . . .. .. . . ... . ...
2-4
Airspeed Indicator Markings ..........................
2-5
Power Plant Limitations . ......... . .. '. . . . . . . . . . . . . . ..
2-6
Power Plant Instrument Markings ... ... . ... .......... . .
2-9
Miscellaneous Instrument Markings .. .. .. .. , ... .......
2-10
Weight Limits . ' .. . . . ... . .... , . . . . ... . . , ... . ,... .
2-11
Center of Gravity Limits ............... . ......... ...
2-11
Maneuver Limits . .. . ...... ..... . .. . ...... . . . .....
2-11
Flight Load Factor Limits .... . . .' . . ..... ......... .. ..
2-12
Flight Crew Limits .. .. ... . ..... . ................. .
2-12
Kinds of Operation Limits
.. ... .... . . . . . . . . . . . . . . . . .
2-12
Fuel Limitations . . . .. . ...... . .... . ....... . ........
2-15
Maximum Operating Altitude Limit ....................
2-17
Outside Air Temperature limits . .. . ......... . . . ..... .
2-17
Maximum Passenger Seating Limits
.. . . . . . . . . . . . . . . . .
2-17
Other Limitations . .. . . . ..... ....... . .. . ... . ...... .
2-17
Flap Limitations ...... ..... . ... . . . . . ' ..... . .. .
2-17
Type II or Type IV Anti-ice Fluid Takeoff Limitations ' ....... 2-17
Flap Limitations . . . .. . . .. . .. .. .. . . ............
2-17
Airspeed Limitations . .. . . ......................
2-17
Flight in Known Icing Visual Cues - As Required by AD 96-09-15,
Paragraph (a) (1) . ............. . . ..... ........
2-18
Placards ....... . . . ... . ............ . . . . . ....... .
2-19
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2-1/2-2
1 April 1998
For Training Purposes Only
)
)
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)
)
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)
)
)
)
)
)
)
)
)
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 2
LIMITATIONS
(
INTRODUCTION
(
(
\
(
Section 2 includes operating limitations, instrument markings, and
basic placards necessary for the safe operation of the airplane, its
engine, standard systems and standard equipment.
(
A WARNING
(
(
The limitations Included In this section and In
Section 9 have been approved by the Federal
Aviation Administration. Observance of these
operating limitations is required by Federal
Aviation Regulations.
(
(
(
NOTE
(
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(
(
(
(
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(
• Operation in countries other than the United States may
require observance of other limitations, procedures or
performance data.
• Refer to Section 9 of this Pilot'~ Operating Handbook for
amended operating limitations, operating procedures,
performance data and other necessary information for
supplemental systel!ls.
• The airspeeds listed in the Airspeed Limitations chart
(Figure 2-1) and the Airspeed Indicator Markings chart
(Figure 2-2) are based on Airspeed Calibration data shown
in Section 5 with the normal static source. If the alternate
static source is · being used, ample margins shOuld be
observed to allow for the airspeed calibration variations
between the normal and alternate static sources as shown
in Section 5.
Your Cessna is certificated under FAA Type Certificate No. A37CE
as Cessna Model No. 208 .
2-3
1 April 1998
For
Trainin~
Purposes Only
SECTION 2
LIMITATIONS
CESSNA
MODEL 208 (675 SHP)
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in .
Figure 2-1.
VMO
SPEED
KCAS
KIAS
Maximum Operating
Speed
175
175
VA
Maneuvering Speed
8000lbs
6300lbs
4600lbs
VFE
Maximum Flap
Extended Speed:
0° - 10°
10° - 20°
20° - 30°
Maximum Window
Open Speed
150
133
114
150
134
115
175
150
125
175
150 ,
125
175
175
)
)
REMARKS
Do not exceed this
speed in any
operation.
)
)
)
Do not make full or
abrupt control
movements above
this speed.
Do not exceed
these speeds with
the given flap
settings.
Do not exceed this
speed with window
open.
)
)
)
)
)
)
. ~
000(""'
s~~: \5''5" KIAS. 'V(JI&'~)
)
)
)
)
)
)
)
)
)
Figure 2-1. Airspeed Limitations
)
2-4
1 April 1998
For Training Purposes Only
)
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 2
LIMITATIONS
(
AIRSPEED INDICATOR MARKINGS
(
/ _'e>
Airspeed indicator markings and their color code significance are
shown in Figure 2-2.
(
(
(
(
MARKING
KIAS
VALUE
OR RANGE
White Arc
50 -125
Full Flap Operating Range. Lower
limit is maximum weight Vso in
landing configuration . Upper limit is
maximum speed permissible with
flaps fully extended.
Green Arc
63 -175
Normal Operating Range . Lower
limit is maximum weight Vs at most
forward C.G. with flaps retracted.
Upper limit is maximum operating
speed.
Red Line
175
Maximum speed for all operations.
(
(
(
(
(
(
(
(
(- '
\,,,
SIGNIFICANCE
(
(
(
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Figure 2-2. Airspeed Indicator Markings
2-5
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
POWER PLANT LIMITATIONS
)
Engine Manufacturer: Pratt & Whitney Canada Inc.
)
Engine Model Number: PT6A-114A
)
Engine Operating Limits: Refer to Figure 2-3.
)
Fuel Grade and Approved Fuel Additives: Refer to Fuel Limitations.
)
Oil Grade (Specification):
)
Oil conforming to Pratt & Whitney Engine Service Bulletin No.
1001, and all revisions or supplements thereto, must be used.
Refer to Section 8 for a listing of approved oils. When adding
oil, service the engine with the type and brand which is
currently being used in the engine.
)
A CAUTION
)
)
Do not mix types or brands of oil.
)
Propeller Manufacturer: McCauley Accessory Division.
)
Propeller Model Number: 3GFR34C703/106GA-0.
)
Propeller Diameter,
Maximum: 106 inches
Minimum: 104 inches.
Propeller Blade Angle at 30-inch Station,
Feathered: 88°.
Low Pitch: 15.6°.
Maximum Reverse: -14°.
Propeller System Operating Limits:
An overspeed governor check shall be performed before the
first -flight of the day, after engine control system maintenance,
or if adjustment has been made.
)
)
)
)
Engine Control Operating Limits:
)
Positioning of power lever below the flight idle stop while the
airplane is in flight is prohibited. Such positioning may lead to
loss of airplane control or may result in an overspeed condition
and consequent loss of engine power.
)
I
\
I
Operation of the emergency power lever is prohibited with the \'.~:>
power lever out of the IDLE position.
2-6
15 November 2000
For Training Purposes Only
(
CESSNA
MODEL.20B (675 SHP)
(
SECTION 2
LIMITATIONS
(
(
(
(
('
.;rpine Starting Cycle Limits:
' '.' .' .
, Using the airplane battery, the starting cycleshall be limited to ·
the following intervals and sequence :
(
(
30 seconds ON· 60 seconds OFF,
30 seconds ON· 60 seconds OFF,
30 seconds ON· 30 minutes OFF.
(
(
(
Repeat the above cycle as required.
(
Using external power, the starting cycle shall be limited to the
following intervals and sequence:
(
20 seconds ON . 120 seconds OFF,
20 seconds ON . 120 seconds OFF,
20 sapQp(js ON . 60 minutes OFF.
(
(
(
t~·· ·
Repeat the" above cycle as required.
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2·7
1 April 1998
For Training Pprposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
POWER
SETTING
OIL
TORQUE MAX GAS GEN PROP
RPM PRESS
FT-LBS ITT (OC) RPM%
PSIG
(3)
.1/_~!o
~~~iec.
~£
SHP
(9)
tf
~(1)
805 (10)
101.6
1900 85 - 105
10 - 99
'tJO
48e6;1970(4)
765
101.6
1900 85 - 105
0-99
675
Maximum
Cruise
+86&,
1970 (4)
740
101 .6
1900 85 - 105
0-99
Idle
---
685
52 Min
~
805
101 .6
Takeoff
Maximum
Climb
Maximum
Reverse (.5)
I
OIL
TEMP
°C
(7)
Transient
Starting
o
0
2400(11) 850 (6) .102.6 (6)
---
Maximum .. -+e65Continuous
(8)
(1 )
090 (6)
---
805
101.6
---
40 Min
1825 85 - 105
-40 - 99
0-99
675
·
675
· --675
· ---
2090
---
. 0 - 99,
P-104 (12)
---
---
-40 Min
---
10 ~ 99
675
1900 85 - 105
·
Per the Engine Torque For Takeoff figure of Section 5.
(18°F) below -30°C (-22°F) ambient temperature, reduce maximum
For every
allowable Ng by 2.2%.
·
.
(3)
Normal oil pressure is 85 to 105 PSI at gas generator speeds above 72% with oil
0
temperature between 60° and 70 e (140° and 158°F). Oil pressures below 85 PSI are
undesirable and should be tolerated only for the completion of the flight, preferably at a
reduced power setting . Oil pressures below normal should be reported as an engine
discrepancy and should be corrected before the next flight. Oil pressures below 40 PSI
are unsafe and require that either the engine be shut down or a landing be made as
soon as possible using the minimum power required to sustain flight.
(4) Propeller RPM must be set so as not to exceed 675 SHP with torque above 1B65 ft-Ibs.
Full 675 SHP rating is available only at RPM setting of 1BOO or greater.
(5) Reverse power operation is limited to one minute.
(6)
These values are time lim~ed to two seconds.
(7)
For increased oil service life, an oil temperature between 74° and SO°C (165° and
176°F) is recommended. A minimum oil temperature of 55°C (130°F) is recommended
for fuel heater operation at takeoff power.
(8)
Use of this rating is intended for abnormal situations (i.e., maintain altitude or climb out
of extreme icing or winds hear conditions).
(9) The maximum allowable SHP is 675. Less than 675 SHP is available under certain
temperature and altitude conditions as reflected in the takeoff, climb. and cruise
performance charts.
(10) When the ITT exceeds 765°C, this power setting is time limited to 5 minutes.
(11 ) These values are time limited to 20 seconds.
1(12) Up to 10 minutes for airplane serial numbers 20800364 and on, and earlier airplanes
equipped with Service Kit SK20B-147.
(2)
)
)
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)
)
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2-8
Revision 6
)
)
For Training Purposes Only
)
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 2
LIMITATIONS
(
POWER PLANT INSTRUMENT MARKINGS
(
Power plant instrument markings and their color significance are
shown in Figure 2-4.
(
INSTRUMENT RED LINE
(Min Limit)
(
(
GREEN
ARC
(Normal
Operating)
YELLOW
ARC
(Caution
Range)
STRIPED
GREEN
ARC
(Alt Power
Range)
RED LINE
(Max Limit)
(
Torque
Indicator
(1 )
---
0-1865
ft-Ibs
---
1865 - 1970
ft-Ibs (2)
1970
ft-Ibs
Inter-Turbine
Temperature
Indicator
(ITT)
---
100°C
to
740°C
---
---
805°C
. Gas
Generator
%RPM
Indicator
(4)
---
52%
to
101 .6%
---
---
101.6%
Propeller
RPM Indicator
---
(
(
(
(
(3)
(
(
(
1"---
(
\.-(
---
1900 RPM
40 PSI
to
85 PSI
---
105 PSI
-40°C to
+10 o e,
---
85 PSI
to
105 PSI
Oil
Temgerature
age
-40°C
+10 o e
to
+99°e
(2)
(3)
(4)
(5)
(6)
,
---
40 PSI '
(1)
.-~..
1600 RPM
to
1900 RPM
Oil Pressure
Gage
/'
'-..
+99°e (5),
+104°C (6)
I
+99°e to
+ 104°C (6)
Incorporates red wedge and T.O. at 1865 ft-Ibs to indicate the takeoff
position.
Propeller RPM must be set so as not to exceed 675 SHP with torque
above 1865 ft-Ibs . Full 675 SHP rating is available only at RPM settings
of 1800 or greater.
Incorporates red triangle at 10900 e and starting temperature limitation
box labeled ST. LIM 1090°.
100% Ng is 37,500 RPM.
Maximum oil temperature indicated by a red wedge.
Airplane serial numbers 20800364 and on, and earlier airplanes
equipped with Service Kit SK208-147.
I
Figure 2-4. Power Plant Instrument Markings
2-9
Revision 6
For Traininl! Purooses Only
SECTION 2
LIMITATIONS
CESSNA
MODEL 208 (675 SHP)
MISCELLANEOUS INSTRUMENT MARKINGS
Miscellaneous instrument markings
significance are shown in Figure 2-5.
INSTRUMENT
and
their
color
code
RED LINE
(Min Limit)
GREEN ARC
(Normal
Operating)
YELLOW
ARC
(Caution
Range)
RED LINE
(Max Limit)
Fuel Quantity
Indicators (1)
E
J2.8 Gal
nusable
Each Tank)
---
---
---
Suction Gage (2)
To 15,000 Ft
To 20,000 Ft
To 25,000 Ft
---
Propeller Anti-ice
Ammeter
---
Oxygen Pressure
Gage
---
I
4.5 - 5.5 in.Hg
4.0 - 5.5 in.Hg
3.5 - 5.5 in.Hg
---
)
)
)
)
---
20 Amps
to
24 Amps
1550 PSI
to
1850 PSI
---
)
)
OPSI
to
300 PSI
2000 PSI
)
)
(1 ) Total unusable when operating with both tanks /on is 3.6 U.S. gallons.
(2)
Incorporates stepped green arc with 15K, 20K, 25K and 30K markings
at the appropriate step locations to indicate the altitude (in thousands of
feet) at which the lower limit of that arc segment is acceptable.
)
)
)
)
)
)
)
Figure 2-5. Miscellaneous Instrument Markings
)
)
)
)
2-10
7 September 2001
)
)
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 2
LIMITATIONS
(
(
,... --
(
(
WEIGHT LIMITS
Maximum Ramp Weight: 80351bs. vo\ t\ ~
Maximum Takeoff Weight: 80001bs.
Maximum Landing Weight: 78001bs.
(
(
(
e':\-~lbs.
NOTE
(
Refer to Section 6 of this handbook for recommended
loading arrangements in the Standard 208 and
Cargomaster.
(
(
CENTER OF GRAVITY LIMITS
(
(
Center of Gravity Range :
(
(
(
Forward:
162.41 inches (7.29% MAC) aft of datum at 4200 Ibs.
or less, with straight line variation to 174.06 inches
(24.83% MAC) aft of datum at 8000 Ibs.
Aft:
184.35 inches (40.33% MAC) aft of datum at all
weights up to 8000 Ibs.
(
\ , --
(
(
r
,
Reference Datum: 100 inches forward of front face of firewalL
Mean Aerodynamic Chord (MAC):
The leading edge of the MAC is 157.57 inches aft of the datum. The MAC length is 66.40 inches.
MANEUVER LIMITS
This airplane is certificated in the normal category. The normal
category is applicable to aircraft intended for non-aerobatic
operations. These include any maneuvers incidental to normal
flying, stalls (except whip stalls), lazy eights, chandelles , and turns
in which the angle of bank is not more than 60°.
Aerobatic maneuvers, including spins, are not approved.
2-11
8 March 1999
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
FLIGHT LOAD FACTOR LIMITS
Flight Load Factors:
*Flaps Up: +3.8g, -1 .52g
*Flaps Down (All Settings): +2.4g ·
* The design load factors are 150% of the above, and in all
cases, the structure meets or exceeds design loads.
)
)
FLIGHT CREW LIMITS
One pilot required in left seat.
)
KINDS OF OPERATION LIMITS
This airplane is equipped for day VFR and may be equipped for
night VFR and/or IFR operations and for flight-into-known icing
conditions. The operating limitations placard reflects the limits
applicable at the time of Airworthiness Certificate issuance.
The following equipment lists identify the systems and equipment i,
upon which type certification for each kind of operation was
predicated. These systems and equipment items must be installed
and operable for the particular kind of . operation indicated.
Reference should also be made to the Equipment List furnished
with the airplane for additional equipment information. The pilot is
responsible for determining the airworthiness of his airplane for
each flight and for assuring compliance with current operating
FAR's.
)
)
)
)
)
)
7 September 2001 .
2-12
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
SECTION 2
LIMITATIONS
KINDS OF OPERATION LIMITS (Co~tinued)
(':-- - ',
REQUIRED EQUIPMENT
(.
\
(
(
DAY VFR:
(
Airspeed Indicator (1)
Ng% RPM Indicator
(
Altimeter (1)*
OIL PRESS LOW Annunciator
Auxiliary Boost Pump System
Oil Pressure Gauge
BATIERY HOT And BATTERY
OVERHEAT Annunciators (NiCad
Batteries Only)
Oil Temperature Gauge
Elevator Trim System (Manual)
Outside Air Temperature Gauge
Engine Ignition System
Overspeed (Airspeed) Warning
System
(
(
(
(
(
Flap Motor (1 )
Overspeed Governor
Flap Position Indicator
Pilots Operating HandbookiAFM
( f"
FUEL PRESS LOW Annunciator
Pitot-Static System (1)
(
Fuel Quantity Indicators (2)
Propeller RPM Indicator
Fuel Seleciors Off Warning
System
Seat Belts (Each Occupant)
Generator
Shoulder Harnesses (Front Seats)
Inertial Separator System
Slip-Skid Indicator (1)
ITT Indicator
Stall Warning System
Magnetic Compass
Torque Indicator
(
~,
(
Trim Position Indicators (3)
Volt/Ammeter
* NOTE
When a servoed altimeter is installed, a functioning pneumatic
altimeter is also required.
2-13
8 March 1999
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
NIGHTVFR:
All Equipment Required For Day
VFA
.
Navigation Lights (3)
Instrument Lights
Strobe Lights (2)
)
IFR:
)
All Equipment Required For Day
VFR
Directional Indicator -Gyro
Stabilized (1)
All Equipment Required For Night
VFR (if a night flight)
Navigation Radios (As required)
Attitude Indicator -Gyro Stabilized
(1 )
Sensitive Altimeter (1)*
Clock
Suction Gauge (If gyros are
vacuum powered)
Communications Radio (VHF) (1)
Turn And Bank Indicator Or Turn
Coordinator (1)
)
)
)
)
)
)
*NOTE
When a servoed altimeter is installed,
pneumatic altimeter is also required.
)
a functioning
)
Fllght-Into-Known Icing:
)
All Equipment Required For Day
VFR, Night VFR, AndlOr IFR, As
Applicable
Pitot-Static Tube Heat System
Horizontal Stabilizer Deice Boots
Standby Electrical System
Ice Detector Light (For night flight)
Stall Warning System Heater
Propeller Anti-Ice Boots
Vertical Stabilizer De-Ice Boot
)
)
Windshield Anti-Ice Panel
)
Wing And Wing Strut De-ice Boots
)
7 September 2001
2-14
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 2
LIMITATIONS
(
FUEL LIMITATIONS '
(
(
(
("- -
.
\.
(
Total Fuel
Both Tanks: .
Each Tank:
335.6 U.S. gallons. (-U.,B. $1,.. Ip~)
167.8 U.S. gallons. (1\2,<{.Uo l")
Usable Fuel
Both Tanks On: 332 U.S. gallons total. ( ztz4.1o/'~)
Single Tank On: 165 U.S. gallons pertank. (noS" $'&')
(
(
(
Unusable Fuel
Both Tanks On: 3.6 U.S. gallons total. (2.".I'Z.lb~)
Single Tank On: 2.8 U.S. ga/lons per tank. (IS. 'U. U:~$}
{
(
(
NOTE
(
To achieve full capacity, fill fuel tank to the top of the filler
neck. Filling fuel tanks to the bottom of the fuel filler collar
(Ievet with flapper valve) allows space for thermal expansion
and results in a decrease in fuel capacity of four gallons per
side (eight gallons total).
(
(
{' ,.
(
'\
I,-..',
With low fuel reserves (FUEL LOW annunciator(s) ON). continuous
uncoordinated flight with the turn and bank "ball" more than onequarter ball out of center position .is prohibited. Unusable fuel
quantity increases when more severe sideslip is maintained.
(
r
(
Due to possible f·uel starvation, maximum full rudder sideslip
duration time is three minutes.
(
Maximum fuel unbalance in flight is 200 Ibs.
Fuel Grade (Specification) and Fuel Additives:
A CAUTION
Aviation gasoline Is restricted to emergency use
and shall not be used for more than 150 hours In
one overhaul period; a mixture of one part
aviation gasoline and three parts of Jet A, Jet A1, JP-1, or JP-5 may be used for emergency
purposes for a maximum of 450 hours per
overhaul period.
( ' . . •. ,
·~0.')
"* R(~c..1
161{;j':' ~CQlb~ ... ~~I"$(~) ': 3!2.S" Ib~
1 April 1998
. ~~ 'b~ : "'e.~ ~
:: 18'3.. (.
,:wc.~
For Training Purposes Only
.... 1
2-15
CESSNA
MODEL 208 (675 SHP)
· SECTION 2
LIMITATIONS
Fuel Grade Specification and Fuel Additives (Continued)
FUEL
GRADE
FUEL
WINIMUM FUEL SPECIFIC
SPECIFICATION EMPEAATURE WEIGHT
FOR
, approved
fIIghl'nlo known Icmg conditions plohibited
This airplime IS c.ertthed 101 the lallowing flight operations as 01 date 01
or iginal allwollhmess cerlilicate:
(
DAY . NIGHT · VFR . IFR
2.
On control lock:
CAUTION
CONTROL lOCK
REMOVE BEFORE STARTING ENGINE
2-19
Revision 6
For Training Purposes Only
SECTION 2
LIMITATIONS
CESSNA
. MODEL 208 (675 SHP)
3. On left sidewall below and forward of instrument panel and
(when right flight instrument panel is installed) on right sidewall
below and forward of instrument panel:
STATIC SOURCE DRAIN
OPEN .lli!!!
lUST IE CLOSED
fOR fUQHT
)
4. On sunvisor or windshield trim-strip:
)
AlTERNATE STATIC SOURCE CORRECTION
CliMBS &APPROACHES : NO CORRECTION REQUIRED.
)
gwg:
CORRECTIONS VARY WITH VENTS OP(N OR
CLOSED. REfER TO SECTION 5 Of PILon OPERATING
HANDBOOK.
)
5. Near airspeed indicator:
MAX WT. MANEUVER SPEED 150 KIAS
SEE POH FOR OTHER WEIGHTS
6. Near torque indicator:
RPM
MO
AX TORQUE
1900
1800
1700
1600
1865
1970
1970
1970
7. A calibration card must be provided to indicate the accuracy of
the magnetic compass in 30 0 increments.
)
)
8: Near wing flap position indicator:
UP to 10°
175 KIAS
(partial flap range with dark blue
color code; also mechanical detent at
10°)
10° to 20°
150 KIAS
(light blue code; also, mechanical
detent at 20°)
20° to FULL
125 KIAS
(white color code)
12-20
Revision 6
For Training Purposes Only
)
)
)
(
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 2
LIMITATIONS
(
9. Below power lever:
(
(
(,"-- ..
. CAUTION
USE BETA AND REVERSE ONLY
WITH ENGINE RUNNING AND
PROPELLER OUT OF FEATHER
(
(
(
10.
On fuel tank selector:
(
(
OFF
(
OFF
FUEL TANK
SELECTORS
(
(
165
GAL
(
(
+
ON
(
t
r
L
-
\, ..
:
(
(
+
+
332 GAL WITH BOTH TANKS ON
MAXIMUM FUEL UNBALANCE IN FLIGHT: 200 LB
ON
165
GAL
.~
.... USa.blc....
(
(
(
11 .
Adjacent to each outboard fuel tank filler cap:
,
JET-A-FUEL
TOTAL CAPACITY 167.8 U.S. GALLONS
....
ANTI·ICE ADDmVE REQUIRED. SEE PILOTS
OPERATING HANDBOOK FOR OTHER APPROVED
FUELS, QUANTITY AND TYPE OF ADDmvE.
-GROUND TO WING TIE-DOWN FITTING.-
2101007·' .....
2-21
1 April 1998
For Training Purposes Only
SECTION 2
LIMITATIONS
CESSNA
MODEL 208 (675 SHP)
12. Adjacent to each inboard fuel tank filler cap (when installed):
JET-A-FUEL
.
TOTAL.INBD CAPACITY
120.3 U.S. GALLONS
.
ANTI-ICE ADDITIVE REQUIRED. SEE PILOT'S
OPERATING HANDBOOK FOR OTHER APPROVED
FUELS, QUANTITY AND TYPE OF ADDITIVE.
-GROUND TO WING TIE-DOWN FITTING.-
CAUTION
I
DO NOT OPEN WHEN FUEL QUANTITY IS IN
EXCESS OF 120.3 U.S. GALLONS.
2106007·)1
13. Adjacent to fuel filter:
1'\11\..
\v
uJo.. ...
4. ".~ C,)Y"\
I
0
FUEL FILTER
DRAIN DAILY
280104103
14. Adjacent to fueldrain can :
"''''
"
.. ~ tIC.
I
~.;o"".LJ"C
EPA CAN - DRAIN
PROPERLY DISPOSE
26050.0 8-2
15. On the brake fluid reservoir:
BRAKE FLUID RESERVOIR
REFill WITH MIL-H-5606 FLUID
~---MIN---~
2806026· 3
8 March 1999
2-22
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 2
LIMITATIONS
(
(
16.
(
(
Adjacent to oil dipstick/filler cap (on inertial separator duct):
"'~-
~
ENGINE OIL
\,
(
TOTAL CAPACITY 14 U.S. QUARTS
DRAIN & FILL 9,5 U.S, QUARTS
(
TYPE: SEE PILOT'S OPERATING HANDBOOK
FOR APPROVED OILS. DO NOT MIX BRANDS.
(
SERVICED WITH : _ _ __
(
2605009 -1
(
17.
(
On side of inertial separator duct:
(
WARNING
(
PRESSURIZED Oil TANK
(
ENSURE
OIL DIPSTICK
IS SECURE
(
(
(
(
(
18.
I
On firewall above battery tray:
I'
CAUTION
24 VOLTS D.C.
THIS AIRCRAFT IS EQUIPPED WITH
GENERATOR AND A NEGATIVE
GROUND SYSTEM
OBSERVE PROPER POLARITY
REVERSE POLARITY WILL DAMAGE'
ELECTRICAL COMPONENTS
2605010-Z
19.
Near ground service plug receptacle :
EXTERNAL POWER
28 VOLTS D.C. NOMINAL
800 AMP
STARTING CAPACITY MIN.
DO NOT EXCEED 1700 AMPS
2-23
15 November 2000
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
20.
. )
On bottom of right hand wing just forward of aileron: .
FLUX VALVE
USE NON-MAGNETIC
TOOLS AND SCREWS
)
21.
On each side of nose strut fairing near tow limit marking (rudder ·Iock placard required when rudder lock installed):
)
WARNING
MAXIMUM
TOW
LIMIT
22.
CAUTION
DO NOT TOW AIRCRAFT
WITH RUDDER LOCK
ENGAGED
2.....5·2
zo ••• n .,
)
Adjacent to left crew door inside door handle :
LOCK OVERRIDE:
TO UNLOCK
PULL & ROTATE
KNOB
TO LOCK
PULL & ROTATE
KNOB
23 .
;
..)
")
Adjacent to upper passenger door outside pushbutton and
door handle (Passenger version only):
DOOR OPERAnON:
)
TO OPEN
PUSH BUTTON &
ROTATE (
HANDLE
TO CLOSE
ROTATE (
HANDLE
2505012·12
2-24
1 April 1998
For Training Purposes Only
(
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
(
(
24.
Adjacent to upper passenger door inside door handle (Passenger version only):
{
(
DOOR OPERATION:
(
TO OPEN
PULL HANDLE
INBD & ROTATE
(
TO CLOSE
ROTATE HANDLE (
& STOW
(
2605013-2
(
(
(
(
25.
At center of lower passenger door on inside and outside (Passenger version only):
(
WARNING
(
OUTSIDE PROXIMITY OF
(
LOWER DOOR MUST BE
CLEAR BEFORE OPENING
(
2605015-5
(
(
(
26.
Adjacent to upper cargo door outside pushbutton and door
handle:
(
(
(
DOOR OPERATION:
(
TO OPEN
PUSH BUTTON &
ROTATE)
HANDLE
(
TO CLOSE
ROTATE)
HANDLE
(
2805012.11
2-25
1 April 1998
For Training Purposes Only
SECTION 2
LIMITATIONS
CESSNA
MODEL 208 (675 SHP)
27. Adjacent to upper cargo door inside door handle (Passenger
version only):
DOOR OPERATION:
TO OPEN
PULL HANDLE )
INBD & ROTATE
TO CLOSE
ROTATE HANDLE)
& STOW
28.
)
)
On right sidewall in Zone 6 (Passenger version only):
)
MAX BAGGAGE j25 LBS . REFER TO
WEIGHT AND BALANCE DATA FOR
BAGGAGE/CARGO LOADING 1201041.\
29.
On left and right sides of aft side of cargo barrier (when installed):
MAX LOAD BEHIND BARRIER
2900 LBS TOTAL
. ZONES FWD OF LAST LOADED
ZONE MUST BEAT LEAST
75% FULL BY VOLUME. SEE
POH FOR EXCEPTIONS.
·CHECK WEIGHT AND BALANCE·
30.
On inside of lower cargo door (Cargo version only):
MAX LOAD BEHIND BARRIER 2900 LBS TOTAL.
ZONES FWD OF 'LAST LOADED ZONE MUST BE AT LEAST
75% FULL BY VOLUME. SEE POH FOR EXCEPTIONS.
·CHECK- WEIGHT AND BALANCE·
LOAD MUST BE PROTECTED FROM SHIFTING· SEE POH 2-26
1 April 1998
For Training Purposes Only
)
(
CESSNA
MODEL 208 (675SHP)
(
SECTION 2
LIMITATIONS
l
(
31.
(
(
(
IF LOAD IN ZONE 5 EXCEEDS
400 LBSA PARTITION NET IS REQD
AFT OR LOAD MUST BE
SECURED TO FLOOR
"
(
32.
(
On right sidewall adjacent to Zone 5 (Cargo version only):
On left and right sides of cabin in appropriate zones (Cargo
version only):
(
ZONE 1
MAX LOAD 1410 LBS
ZONE 2
MAX LOAD 1430 LBS
ZONE 3
MAX LOAD 1410 LBS
ZONE 4
MAX LOAD 1380 LBS
ZONES
MAX LOAD 1270 LBS
ZONE 6
MAX LOAD 320 LBS
(
(
(
(
(
(
(
(
I
f -'
t
33.
On i.nside of cargo pod doors:
{
I
FWD.
COMPARTMENT
MAX. WEIGHT 230 LBS.
MAX. FLOOR LOADING
30 LBS. PER SQ. FT.
NO SHARP EDGES
(
/
CTR. COMPARTMENT
MAX. WEIGHT 310 LBS.
MAX. FLOOR LOADING
30 LBS. PER SQ. FT.
NO SHARP EDGES
AFT COMPARTMENT
MAX. WEIGHT 280 LBS.
MAX. FLOOR LOADING
30 LBS. PER SQ. FT.
NO SHARP EDGES
2-27
29 September 1998
For Training Purposes Only
SECTION 2
LIMITATIONS
34.
I
CESSNA
MODEL 208 (675 SHP)
At each sidewall and ceiling anchor plate (except heavy duty
anchor plates with additional structural support) and at anchor
plate at center of lower cargo door (Cargo version only):
)
/
)
)
)
)
2-28
7 September 2001
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 3
EMERGENCY PROCEDURES
(
(
(
(
...... ..
r
SECTION 3
EMERGENCY PROCEDURES
(
(
TAB LE OF CONTENTS
(
Page
Introduction . . . . ...... . . . . . .. .. ... . .... . . . .. . ... . .
Airspeeds For Emergency Operation . ..... ,
(
0
•
0
•
•
•
•
•
•
•
0
3-5
3-5
•
(
OPERATIONAL CHECKLISTS
(
(
Engine Failures . ... .... .. . .. . . ..... . .... .. ..
Engine Failure During Takeoff Roll
Engine Failure Immediately After Takeoff
Engine Failure During Flight
Engine Flameout During Flight ... . .. . . .... .
Airstart
............
Starter Assist (Preferred Procedure) ... . .. .. .
No Starter Assist ..... . ...
Forced Landings .. . . . . . .. . . .. .... .. . .. . . ... . ..... .
Emergency Landing Without Engine Power .... . .
Precautionary Landing With Engine Power
.. . ..... .. .
Ditching . .. ~
Smoke and Fire .
Engine Fire In Flight (Red Engine Fire
Annunciator On or Off)
Electrical Fire In Flight
Cabin Fire .. ... . . .. . ...........
Wing Fire. . .. . . ... .
Cabin Fire During Ground Operations .
Engine Fire During Start On Ground (Red
Engine Fire Annunciator On or Off
ICing
.,
Weather Conditions Conducive To Severe Icing .. . .. .. .
Procedures For Exiting Severe Icing Environment
Inadvertent Icing Encounter . . ..
. Static Source Blockage (Erroneous
Instrument Reading Suspected) . . . .
0
(
0
•
0
•••••
o.
(
0
0
••••
0
0
•
•
•
0
•
••
•••
0
0
0
(
(
,(
(
(
".c ", '
•
•
•
•••
•
••
•••
•
•
•
••
•
•
•
•
•
•
••
•
•
0
••••
0
•
••
•
•
•
•
0
0
0
••••
0
0
••
•
••
••••
0
0
o
••
•••
•••••
••
••••
•
• .
•••
•
•••
•••••••••
•
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0
•
•
•
•
•
•
••
,
•
•
••
0
••
••
•
0
•
••
••••
0
"
•
0
0
0
•••
•
0
0
•
•
•
0
••
••
•
0
•
•••
0.
0
•••
0
•••
•
•••
0
0
•
•
••••
••
•
•
•
•
•••
0
••
0
•
•
•
•
•
0
•
•
0
0
••
'0
•
0
•
0
•
•
•
•
0
•
•
•
0
•
••
•
0
0
0
•
•
•••••••
0
••
•••
•
•
••
•
0
0
0
0
0"
0
••
•
0
0
•
0
0
0
0
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•
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0
0
•
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•
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•
•
•••••
0
o
•• '
••
•
•
••••••
••
••••
0
0
0
•
3-6
3-6
3-6
3-6
3-7
3-7
3-7
•
0
•••
•••
•
•
•
••
••
••
0
0
0
(
•
••
••
0
•••
0
(
•
0
•
0
•••
•
•
:
•
•
3-8
3-9
3-9
3-10
3-10
3-11
3-11
3-11
3-121
3-13
3-13
3-14
3-14
3-14
3-15
3-16
3-17
3-1
29 September 1998 .
For Trainine Purposes Only
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
TABLE OF CONTENTS (Continued)
Page
3-1S'
Engine Malfunctions . ... .. .......... . ..... . ...... .
Loss Of Oil Pressure (Red Oil
Pressure Low Annunciator On) . . ....... ... . .... .
Fuel Control Unit Malfunction in The Pneumatic Or
Governor Sections (Engine Power Falls Back to Idle) ..
3-1S
Ge~~~~~cfa~~:~~)ati~~ ~~~.~~r. ~~i:. ~~~~~t~~ ....... .
3-18
I
Fuel System Malfunction/Inadvertent Fuel Flow
Interruption Procedures ...... _ .................. .
Loss of Fuel Pressure (Amber Fuel Press Low Ann On)
Fuel Flow Interruption to Fuel Reservoir (Red
,Reservoir Fuel Low Annunciator On) ............. .
Fuel Tank Selector Off During Start (Red Fuel
Select Off Annunciator On and Both Fuel Selector
Warning Horns Activated) ..................... .
Fuel Level Low With Single Tank Selected (Red Fuel
And Amber Left Or Right Fuel Low Annunciators
On and Fuel Selector Warning Horn Activated ...... .
Flap System Malfunction Procedures .' .. .. . ........... .
Asymmetric Flap Extension Or Sudden
Flap Retraction On One Side
.................. .
Flaps Fail To Extend Or Retract
............. .. ... .
Landing Gear Malfunction Procedures .. . ............. .
. ... ... .. .. . .... . .. .. .
Landing With Flat Main Tire
I Landing With Flat Nose Tire ..... . ........ . ...... .
Electrical Power Supply System Malfunctions ........... .
Battery Temperature High' (Amber Battery Hot Ann On)
Battery Overheated (Red Battery Overheat Ann On)
Generator Failure (Red Voltage Low And/Or Red
Generator Off Annunciators On) . . . .. ... . .. ..... .
Starter Contactor Does Not Disengage After Engine
Start (Amber Starter Energized AnnUnciator On)
Emergency Descent Procedures ............... ' . . ... .
Rough Air ........ . ................... " .... . . .
Smooth ,Air .. ........... '...................... .
Inadvertent Opening Of Airplane Doors In Flight ......... .
Upper Half Of Cargo Door Or Upper Half Of
Passenger Airstair Door Open (Red Door
Warning Annunciator On) ......... . .. . ........ .
3-2
3-18
3-18
3-18
3-19
3-19
3-19 t,
3-20 "
3-20
3-20
3-21
3-21
3-21
3-21
3-21
3-22
3-23
3-25
3-25
3-25
3-25
3-26
3-26
29 September 1998
For Training Purposes O"ly
i,,"
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 3
EMERGENCY PROCEDURES
(
(
TABLE OF CONTENTS
(
(Continued)
/<---'-
(
Page
\
Lower Half Of Passenger Airstair Door Open .. ........
Right Or Left Crew Doors Open .. ..... . ;. . ...... . ..
Cargo Pod Door(s) Open ... . ................ . ... .
(
(
(
3-26
3-26
3-26
AMPLIFIED PROCEDURES
(
Engine Failure ... .. .. . . .... . .. .... .. .. . . ....... ..
Forced Landings . ... . . . . .... .. .............. . ....
Landing Without Elevator Control . . ... . .. .. . . .... ... . .
Smoke And Fire .... . . . .. .. . . . . .... . . . . . . . . . . . . . .
Emergency Operation In Clouds (Vacuum System Failure) "
Executing A 180 0 Turn In Clouds
............... . ..
Emergency Descent Through Clouds ... ~ . . . . . . . . . . . .
Recovery From A Spiral Dive
. .. . . . ..... . _ . . . . . . . .
Inadvertent Flight Into Icing Conditions . .. ... ... . _. . . . . .
Static Source Blocked .. . . .. . ... .. . ... . . . ... . .... . .
Spins
. . . . . . . . . . . .. . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine Malfunctions . ........ ......... ... . ...... . .
Loss ot Oil Pressure .... . ... . ...... . .. . ..... .. . .
Fuel Control Unit Malfunction In The Pneumatic
Or Governor Sections . .. . . .. ..... . .. . . .... . . ..
Gear Box Contamination ... . .................... •
Fuel System Malfunction/Inadvertent Fuel Flow
Interruption Procedures .......... .. . . .... . .... .
Electrical Power Supply System Malfunctions . . . . . ... . .. .
BatterY Malfunctions . ... . ... . . . . ... . . .... .. ... . . .
Generator Or Main Bus Malfunctions .. . . . . . ..... . .. .
Loss of Electrical Power .... . . ...... . ........... .
Partial Avionics Power Failure .•. . . .............. ..
Standby Electrical System Malfunctions . .. . .. . .. . . .. .
Inadvertent Opening Of Airplane Doors In Flight . . . .. . . .. .
Emergency Exits ...... ........... .. .......... . .. .
(
(
(
(
(
(
(
\
(
(
(
(
(
(
(
/
,
3-27
3-31
3-32
3-32
3-33
3-34
3-34
3-35
3-35
3-36
3-36
3-37
3-37
3-37
3-381
3-38
3·39
3-39
3-40
3-41
3-41
3-42
3-43
3-43
1
t '- -,
\.
;
~''':';':?J,~'''
3-3/3-4
29 September 1998
For Training Purposes Only
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 3
EMERGENCY PROCEDURES
(
INTRODUCTION
(
(
(
(
Section 3 provides checklist and amplified procedures for coping
with emergencies that may occur. Emergencies caused by airplane
or engine malfunctions are extremely rare if proper preflight
inspections and maintenance are practiced. Enroute weather
emergencies can be minimized or eliminated by careful flight
planning and good judgment when unexpected weather is
encountered. However, should an emergency arise, the basic
guidelines described in this section should be considered and
applied as necessary to correct the problem . Emergency procedures
associated with standard avionics, the ELT, or any optional systems
can be found in Section 9.
.,,'_'
"
(
(
(
(
(
A WARNING
(
(
There Is no substitute for proper and complete
preflight planning habits and their continual
review in minimizing emergencies.
Be
thoroughly knowledgeable of hazards and
conditions which represent potential dangers,
and be aware of the capabilities and limitations
Of the airplane.
(
(
('..
(
{,"'.
(
(
AIRSPEEDS FOR EMERGENCY OPERATION
(
(
(
(
(
'.
\",;;:;'
Engine Failure After Takeoff:
95 KIAS
Wing Flaps Up .. .. ... . . ..... . ........ . .I.C?P
Wing Flaps Down . . . .... . ... . .. . . .. . . ......
80 KIAS
Maneuvering Speed:
8000 Lbs . . . ... .... .. .- .. . ...... ...... 1':16
150 KIAS
134 KIAS
6300 lbs . ... . . .. . ... .. . .. .. . . . . . . .... . .
4600 lbs . . .. . ..... .. ..... . . ..... .. . .. ..
115 KIAS
Maximum Glide:
With Cargo Pod
Without Cargo Pod
8000 Pounds . . . .. . . . .. 96 KIAS
q~
99 KIAS
"fq
88 KIAS
6300 Pounds . . ..... . .. 85 KIAS
1'1
75 KIAS
4600 Pounds . . . . . . .... 72 KIAS
Precautionary Landing ( Engine Power IFlaps Down)
80 KIAS
Landing Without Engine Power:
Wing Flaps Up . . .. . .. .. .. . . . . .. . .... . ... . .
95 KIAS
Wing Flaps Down . . . . . . ... . .. . .. . .. . .... . . .
80 KIAS
3-5
1 April 1998
For Training Purposes Only
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (S75 SHP)
OPERATIONAL CHECKLISTS
Procedures in the Operational Checklists portion of this section
shown in bold faced type are immediate action items which should
be committed to memory.
ENGINE FAILURES
ENGINE FAILURE DURING TAKEOFF ROLL
1.
2.
3.
Power Lever .- BETA range.
Brakes -- APPLY.
Wing Flaps -- RETRACT.
If airplane cannot be stopped on remaining runway:
4.
5.
S.
7.
Fuel Condition Lever -- CUTOFF.
Fuel Shutoff -- OFF (pull out).
Fuel Tank Selectors -- OFF (warning horn will sound).
Battery Switch -- OFF.
ENGINE FAILURE IMMEDIATEL V AFTER TAKEOFF
1.
2.
3.
4.
5.
6.
7.
Airspeed .- 85 KIAS.
Propeller -- FEATHER.
Wing Flaps -- AS REQUIRED (full down recommended).
Fuel Condition Lever -- CUTOFF.
Fuel Shutoff -- OFF (pull out).
.
Fuel Tank Selectors -- OFF (warning horn will sound).
Battery ~- OFF.
ENGINE FAILURE DURING FLIGHT
1.
2.
3.
4.
5.
6.
7.
B.
9.
10.
11 .
Airspeed .- 95 KIAS.
Power Lever -- IDLE.
Propeller Control Lever •• FEATHER.
Fuel Condition Lever •• CUTOFF.
Wing Flaps -- UP.
Fuel Boost Switch -- OFF.
Fuel Shutoff -- OFF (pull out).
Ignition Switch -- NORM.
Standby Power Switch (if installed) -- OFF.
Electrical Load -- REDUCE.
Landing -- Refer to Emergency Landing Without Engine
Power checklist.
3-S
1 April ·199B
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
ENGINE FLAMEOUT DURING FLIGHT
1.
)
)
)
If Gas Generator Speed (N g) Is Above 50%:
a.
Power Lever •• IDLE.
b.
Ignition Switch -- ON.
c.
Power Lever -- AS DESIRED after satisfactory relight
as evidenced by normal ITT and Ng .
d.
Ignition Switch -- OFF if cause of flameout has been
corrected.
2. · If Gas Generator Speed (N g ) Is Below 50%:
a.
Fuel Condition Lever •• CUTOFF.
b.
Refer to Airstart checklists for engine restart.
AIRSTART
)
STARTER ASSIST (Preferred Procedure)
)
)
(.
)
)
)
)
)
)
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
)
)
1
)\.~."'/)
17.
Electrical Load -- REDUCE.
Standby Power Switch (if installed) -- OFF.
Avionics Power Switches -- OFF.
Ignition Switch -- NORM.
Air Conditioner (if installed) -- OFF.
Bleed Air Heat Switch -- OFF.
Emergency Power Lever -- NORMAl.
Power Lever -- IDLE.
Propeller Control Lever -- MIN RPM.
Fuel Condition Lever -- CUTOFF.
Fuel Shutoff -- ON (push in).
Fuel Tank Selectors -- LEFT ON, RIGHT ON.
Battery Switch -- ON.
Fuel Boost Switch -- ON (check AUX FUEL PUMP ON
annunciator ON, FUEL PRESS LOW annunciator OFF).
Altitude -- 20,000 feet maximum.
Starter Switch -- START and OBSERVE.
a.
IGNITION ON Annunciator -- CHECK ON.
b.
Engine Oil Pressure -- CHECK for indication.
c.
Ng -- 12 MINIMUM .
Fuel Condition Lever -- LOW IDLE and OBSERVE.
a.
ITT -- MONITOR (1090°C maximum).
b.
Ng -- 52% MINIMUM.
)
)
)
)
3-7
1 April 1998
For Traininl! Purposes OnlY
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
(
(
(
18;
Starter Switch -- OFF.
A WARNING
If conditions exist, such as heavy precipitation or
nearly empty fuel tanks, turn the Ignition switch
(
ON.
19.
20.
21.
22.
23.
Fuel Boost Switch -- NORM (unless it cycles on and off;
then leave ON).
Fuel Condition Lever -- HIGH IDLE.
Propeller Control Lever -- AS DESIRED.
Power Lever ~- AS DESIRED.
Electrical Equipment -- AS REQUIRED.
NO STARTER ASSIST
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
Generator Switch -- TRIP and release.
Standby Power Switch (if installed) -- OFF.
Avionics Power Switches -- OFF.
Air Conditioner (if installed) -- OFF.
Bleed Air Heat Switch -- OFF.
Emergency Power Lever -- NORMAL.
Power Lever -- IDLE.
Propeller Control Lever -- MIN RPM.
Fuel Condition Lever -- CUTOFF.
Fuel Shutoff -- ON (push in).
Fuel Tank Selectors -- LEFT ON, RIGHT ON.
Battery Switch -- ON.
Fuel Boost Switch -- ON (check AUX FUEL PUMP ON
annunciator ON, FUEL PRESS LOW annunciator OFF).
Ignition Switch -- ON, check IGNITION ON annunciator ON.
Airspeed -- 100 KIAS minimum (140 KIAS if propeller is
feathered) .
Altitude -- 20,000 feet maximum (15,000 feet if propeller is
feathered) .
.
3-8
1 April 1998
For Training Purposes Only
(
CESSNA
SECTION 3
EMERGENCY PROCEDURES
MODEL 208 (675 SHP)
)
)
A CAUTION
)
/""
J.
Do not attempt a restart without starter assist If
Ng tachometer Indicates zero % RPM.
.
\ ,;
)
17.
)
18.
}
)
19.
)
Ng Indicator -- CHECK STABLE.
Fuel Condition Lever -- LOW IDLE and OBSERVE.
a. ITT -- MONITOR (1 090°C maximum).
b. Ng -- 52% MINIMUM.
Ignition Switch -- NORM (N.9 52% or above) unless
conditions warrant leaving ON .
)
A
)
If conditions exist, such as heavy precipitation or
nearly empty fuel tanks, turn the ignition switch
)
)
!
WARNING
ON.
)
)c.~
"
)
20.
21.
22.
23.
24.
)
)
25.
Fuel Boost Switch -- NORM (unless it cycles on and off);
then leave ON .
Fuel Condition Lever -- HIGH IDLE.
Propeller Control Lever -- AS DESIRED.
Power Lever -- AS DESIRED.
Generator Switch -- RESET and release.
Electrical and Avionics Equipment -- AS REQUIRED.
}
j
FORCED LANDINGS .
)
EMERGENCY LANDING WITHOUT ENGINE POWER
)
1.
)
2.
3.
)
4.
)
5.
( )( j
)
)
~ .
6.
7.
8.
9.
Seats, Seat Belts, Shoulder Harnesses -- SECURE.
Airspeed -- 95 KIAS (flaps UP). 80 KIAS (flaps DOWN).
Power Lever -- IDLE.
Propeller Control Lever -- FEATHER.
Fuel Condition Lever -- CUTOFF.
Fuel Boost Switch .- OFF.
Ignition Switch -- NORM .
Standby Power Switch (if installed) -- OFF.
Nonessential Equipment -- OFF.
)
,
)
3-9
1 April 1998
For Training Purposes Only
SECTION 3
EMERGENCY PROCEDURES
. CESSNA
MODEL 208 (675 SHP)
(
(
10.
11 .
12.
13.
14.
15.
16.
Fuel Shutoff -- OFF (pull out).
Fuel Tank Selectors -- OFF (warning horn will sound).
Wing Flaps -- AS REQUIRED(FULL recommended).
Crew Doors -- UNLATCH PRIOR TO TOUCHDOWN.
Battery Switch -- OFF when landing is assured.
Touchdown -- SLIGHTLY TAIL LOW.
Brakes -- APPLY HEAVILY.
('
PRECAUTIONARY LANDING WITH ENGINE POWER
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11 .
12.
13.
Seats, Seat Belts, Shoulder Harnesses -- SECURE.
Wing Flaps -- 10°.
Airspeed -- 90 KIAS.
Selected Field -- FLY OVER, noting terrain and obstructions.
All Electrical Switches (except Battery and Generator) -OFF.
Wing Flaps -- FULL DOWN (on final approach).
Airspeed -- 80 KIAS.
Crew Doors -- UNLATCH PRIOR TO TOUCHDOWN .
Generator Switch -- TRIP and release.
Battery Switch -- OFF.
.
Touchdown -- SLIGHTLY TAIL LOW.
Fuel Condition Lever -- CUTOFF.
Brakes--APPLYHEAVILY.
(
(
(
(
(
(
1
(
(
DITCHING
1.
2.
3.
4.
5.
6.
7.
8.
Radio -- TRANSMIT MAYDAY on 121 .5 MHz, giving location
and intentions and SQUAWK 7700 if transponder is
installed.
Heavy Objects in Cabin -- SECURE if passenger is available
to assist.
Seats, Seat Belts, Shoulder Harnesses -- SECURE.
Wing Flaps -- FULL DOWN.
Power -- ESTABLISH 300 FT/MIN DESCENT AT 80 KIAS.
Approach:
High Winds --INTO THE WIND.
LightWinds, Heavy Swells -- PARALLEL TO SWELLS.
Face -- CUSHION at touchdown with folded coat or similar
object.
Touchdown -- NO FLARE, maintain descent attitude.
3-10
1 April 1998
For Training Purposes Only
(
(
)
CESSNA
MODEL 208 (675 SHP)
)
SECTION 3
EMERGENCY PROCEDURES
)
)
9.
10.
)
{~~-
A WARNING
....
}
The airplane has not been flight tested In actual
dltchings, thus the above recommended
procedure is based entirely on the best
judgment of Cessna Aircraft Company.
)
)
)
)
Airplane -- EVACUATE.
Life Vests and Raft -- INFLATE when outside cabin.
SMOKE AND FIRE
.
)
)
)
)
)
{'
t.
)
)
)
ENGINE FIRE IN FLIGHT (Red ENGINE FIRE Annunciator On or
Off)
1.
2.
3.
4.
5.
Power Lever •• IDLE.
Propeller Control Lever·- FEATHER.
Fuel Condition Lever _. CUTOFF.
Fuel Shutoff _. OFF.
Cabin Heat Firewall Shutoff Control·· PULL OFF.
6.
7.
8.
9.
Forward SideVents -- CLOSE.
Overhead Vents -- OPEN.
Ventilation Fans (if installed) -- ON.
Wing Flaps -- 10°-30°.
Airspeed -- 80 KIAS.
Forced Landing -- EXECUTE (as described in Emergency
Landing Without Engine Power) .
10.
11 .
..l
j
)
)
ELECTRICAL FIRE IN FLIGHT
1.
2.
3.
Battery Switch _. OFF.
Generator Switch -- TRIP and release.
Standby Power Switch (If Installed) .- OFF.
)
A WARNING
)
Without electrical power, all electrically-operated
gyros and engine Instruments, fuel boost pump,
annunciator lights, wing flaps and all avionics
will be inoperative.
J
r";
)~;,'; iY'
)
)
)
4.
Vents _. CLOSED (to avoid drafts).
3-11
1 April 1998
I:/ "
)
Left and Right Fuel Tank Selectors •• ON.
FUEL LEVEL LOW WITH SINGLE TANK SELECTED (Red FUEL
SELECT OFF And Amber LEFT Or RIGHT FUEL LOW
Annunciators On And Fuel Selector Warning Horn Activated)
)
)(
SECTION 3
EMERGENCY PROCEDURES
1.
Left and Right Fuel Tank Selectors •• ON (turning both
fuel tank selectors ON will extinguish the red FUEL SELECT
OFF annunciator and silence the warning horn).
)
)
)
Revision 6
s
On
V
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
FLAP SYSTEM MALFUNCTION PROCEDURES
ASYMMETRIC FLAP EXTENSION OR SUDDEN FLAP
RETRACTION ON ONE SIDE
1.
2.
3.
Apply aileron and rudder to stop the roll.
Flap Selector·· UP.
Airspeed •• SLOW to 100 KIAS or less.
4.
If both flaps retract to a symmetrical setting:
a. Plan a flaps up landing.
b. Refer to Section 5 (notes above landing performance
tables) for increase in approach speed and landing
distance.
If both flaps cannot be retracted to a symmetrical setting:
a . Land as soon as practical.
b. Maintain a minimum airspeed of 90 KIAS on the
approach and avoid a nose high flare on landing.
5.
FLAPS FAIL TO EXTEND OR RETRACT
1. Flap Motor and STBY Flap Motor Circuit Breakers -- CHECK
IN.
2. If flaps still fail to extend or retract:
.
a.
Guarded and Safetied Standby Flap Motor Switch
(Overhead) -- MOVE GUARD, breaking safety wire, and
POSITION SWITCH TO STBY.
b.
Guarded and Safetied Standby Flap Motor Up/Down
Switch (Overhead) -- MOVE GUARD, breaking safety
wire, and position switch UP or DOWN (hold switch until
flaps reach desired position, except release switch
before flaps reach full up or full down travel).
A CAUTION
With the standby flap system In use, limit
switches which normally shut off the primary
flap motor when reaching the flap travel limits
are electrically inactivated. Therefore, the pilot
must release the standby flap motor up/down
switch before the flaps reach their travel limit to
prevent overloading and damage to the flap
system.
13-20
29 September 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
3. Guarded ·Standby Flap Motor Switch -- Leave in STBY position until after landing when maintenance action can be accomplished .
LANDING GEAR MALFUNCTION PROCEDURES
LANDING WITH FLAT MAIN TIRE
1.
2.
3.
)
4.
)
5.
)
)
)l"'
Jx /
)
)
Airplane -- FLY as desired to lighten fuel load.
Fuel Selectors -- POSITION ONE SIDE OFF TO LIGHTEN
LOAD ON SIDE OF FLAT TIRE (maximum fuel unbalance of
200 pounds).
Approach -- NORMAL (full flaps).
Touchdown -- INFLATED TIRE FIRST. Hold airplane off flat
tire as long as possible with aileron control.
Directional Control -- MAINTAIN using brake on wheel with
inflated tire as required.
LANDING WITH FLAT NOSE TIRE
1.
2.
3.
4.
Passengers and Baggage -- MOVE AFT if practical (remain
within approved C.G. envelope) .
Approach -- NORMAL with full flaps.
Touchdown -- NOSE HIGH. Hold nose wheel off as long as
possible during roll.
Brakes -- MINIMUM necessary.
)
)
ELECTRICAL
POWER
MALFUNCTIONS
SUPPLY
SYSTEM
BATTERY TEMPERATURE HIGH (Amber BATTERY HOT
Annunciator On) (Ni·Cad Battery Equipped Airplanes Only)
)
)
)
)
(~,~
)
)
1.
2.
Battery Switch •• OFF.
Ammeter -- CHECK with selector switch in BATT position.
It ammeter shows zero indication:
a.
(1)
Annunciator light should extinguish.
b.
If ammeter shows charge indication:
(1)
Generator Switch -- TRIP and release.
(2)
Standby Power Switch (if installed) -- OFF.
(3)
All Electrical System Switches -- OFF.
3-211
29 September 1998
I
)
For Training Purposes Only
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
If standby electrical system is NOT installed:
(4)
(5)
(6)
(7)
(8)
Wait five minutes after annunciator extinguished.
Generator Switch -- RESET and release.
Ammeter -- CHECK with selector switch in BAIT
position .
If ammeter shows charge indication :
(a)
Generator Switch -- TRIP and release.
If ammeter shows zero indication:
(a)
Reinstate electrical systems as required.
(b)
Monitor BATTERY HOT annunciator.
I(standby electrical system I~ installed:
(4)
3.
Bus 1 Pwr and Bus 2 Pwr Circuit Breakers -- PULL
OFF (total of six circuit breakers).
(5) Avionics Switches -- OFF.
(6) Standby Power Switch -- ON.
(7) Avionics Standby Power Switch -- LIFT GUARD, TURN
ON.
(8) Avionics Bus Tie Switch -- LIFT GUARD, TURN ON.
(9)
Reinstate essential electrical systems, exercising
caution not to exceed capacity of standby electrical
system.
As Soon as Practical-- LAND.
BATTERY
OVERHEATED
(Red
BATTERY
OVERHEAT
Annunciator On) (Ni-Cad Battery Equipped Airplanes Only)
1.
2.
3.
4.
Battery Switch -- CHECK OFF.
Generator Switch -- TRIP and release.
Standby Power Switch (if installed) -- OFF.
All Electrical System Switches -- OFF.
If standby electrical system is NOT installed:
5.
6.
{
Wait 5 minutes after BAITERY HOT and BATIERY
OVERHEAT annunciators are extinguished.
Generator Switch -- RESET and release.
3-22
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
7. Ammeter -- CHECK with selector switch in BATT position.
)
{
)
)
)
)
)
8.
If standby electrical system IS installed:
5.
)
)
6.
7.
)
8.
9.
)
10.
)
11.
t'
If ammeter shows charge indication:
(1)
Generator Switch -- TRIP and release.
b.
If ammeter shows zero indication:
(1)
Reinstate electrical systems as required.
(2)
Monitor
BATTERY
HOT
and
BATTERY
OVERHEAT annunciators .
As Soon as Practical -- LAND.
a.
Bus 1 Pwr and Bus 2 Pwr Circuit Breakers -- PULL OFF
(total of 6 circuit breakers .)
Avionics Switches -- OFF.
Standby Power Switch -- ON .
Avionics Standby Power Switch -- LIFT GUARD, TURN ON.
Avionics Bus tie Switch -- LIFT GUARD, TURN ON.
Reinstate essential electrical systems, exercising caution not
to exceed capacity of standby electrical system.
As Soon as Practical -. LAND.
~,
)
)
)
)
)
GENERATOR FAILURE (Red VOLTAGE LOW and/or Red
GENERATOR OFF Annunciators On)
1.
VolVAmmeter Selector Switch -- VOLTS. If voltage is near
normal of 28.5 volts, assume fault in VOLTAGE LOW
annunciator . circuit and continue flight to destination
monitoring voltage and generator output.
A
)
)
)
)
)
)t .
)~:",/
CAUTION
A red VOLTAGE LOW warning followed by a BUS
1 or BUS 2 circuit breaker opening may be a
feeder fault that has isolated itself. DO NOT
reset the breaker. The VOLTAGE LOW warning
should extinguish.
If voltage is less than 24.5 volts :
2 . Volt/Ammeter Selector Switch -- GEN and monitor ammeter.
)
)
3-23
1 April 1998
For Training Purposes Only
SECTION 3
EMERGENCY PROCEDURES
3.
4.
CESSNA
MODEL 208 (675 SHP)
If generator output is zero :
a.
GEN CONT and GEN FIELD Circuit Breakers -- PUSH
IN.
b.
Generator Switch -- RESET and release.
If generator output is still zero:
a.
Generator Switch -- TRIP.
b.
Electrical Load -- REDUCE as follows :
(1)
Avionics Bus 2 Switch -- OFF.
(2)
Flashing Beacon -- OFF.
(3)
Strobe Lights -- OFF.
(4)
All Deicing Equipment -- OFF (if pitot heat is
required, pull RIGHT PITOT HEAT circuit breaker
and turn pitot heat switch on).
(5)
Vent Fans -- OFF.
(6)
Air Conditioner (if installed) -- OFF.
(7)
GEN CONT and GEN FIELD Circuit Breakers -PULL (top row, last two breakers on forward end).
(8)
NP CONT Circuit Breaker -- PULL (third row from
bottom , first breaker from forward end).
To reactivate the avionics fan and the disabled section of the (
audio amplifier if desired:
\
Pull all AVIONICS BUS 2 circuit breakers except
AVIONICS FAN and AUDIO AMP breakers (second
row from bottom, last two breakers · on forward
end) .
(2)
Avionics Bus 2 Switch -- ON.
c. Flight --TERMINATE as soon as practical.
(1)
NOTE
If optional standby electrical system is installed, the
flight may be continued to destination with the
GENERATOR OFF annunciator illuminated. Refer to
emergency procedures of Standby Electrical System
supplement in Section 9.
3-24
1 April 1998
For Training Purposes Only
(
.(
(
(
(
.(
(
)
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
5. If generator output resumes:
a. Volt/Ammeter Selector Switch . - VOLTS and monitor
voltmeter. If voltage increases past 29 volts, expect the
generator to trip off again . If this occurs, turn off the
nonessential radio and electrical equipment and land as
soon as practical.
)
{
)
)
STARTER CONTACTOR DOES NOT DISENGAGE AFTER
ENGINE START (Amber STARTER ENERGIZED Annunciator On)
)
)
1. Battery Switch --OFF.
2. Auxiliary Power Unit -- OFF, then DISENGAGE.
3. Fuel Condition Lever·.. CUTOFF.
4. Engine Shutdown -- COMPLETE ,
)
)
)
)
)
EMERGENCY DESCENT PROCEDURES
)
ROUGH AIR
(
1. Seats, Seat Belts, Shoulder Harnesses -- SECURE.
)
2. Power Lever -- IDLE.
3. Propeller Control Lever -- MAX (full forward)
4 . Wing Flaps -. UP.
5. Weights and Airspeed:
8000 Pounds -- 150 KIAS
. 6300 Pounds -- 134 KIAS
4600 Pounds -- 115 KIAS
)
)
)
)
SMOOTH AIR
)
)
1. Seats, Seat Belts , Shoulder Harnesses -- SECURE.
)
2. Power Lever -- IDLE.
3. Propeller Control ,Lever -- MAX (full forward)
4. Wing Flaps -- 10 0 •
5. Airspeed -- 175 KIAS.
)
)
)l
:.
)\:..:~,/
)
)
)
3-25
1 April 1998
For Trainin Pur oses Onl
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
(
(
INADVERTENT OPENING OF AIRPLANE DOORS IN
FLIGHT
UPPER HALF OF CARGO DOOR OR UPPER HALF OF i
PASSENGER AIRSTAIR DOOR OPEN (Red DOOR WARNING
Annunciator On)
(Standard 208 Only)
1.
. 2.
3.
4.
Airspeed -- MAINTAIN LESS THAN 100 KIAS.
Wing Flaps -- FULL (wing downwash with flaps extended
will move the doors near their normally closed position).
If available or practical, have a second crew member go aft
to close and latch door.
If landing is required with door open:
a. Approach and Landing -- NORMAL.
(
(
(
(
(
(
(
(
(
(
LOWER HALF OF PASSENGER AIRSTAIR DOOR OPEN
(Standard 208 Only)
1.
2.
3.
4.
5.
Airspeed -- MAINTAIN LESS THAN 100 KIAS . .
Flight Controls -- MANEUVER for return for landing.
Wing Flaps -- FULL.
Approach -- NORMAL.
Landing -- SLIGHTLY TAIL LOW; avoid nose high flare .
(
(
(
(
(
(
(
RIGHT OR LEFT CREW DOORS OPEN
1.
2.
(
Airspeed -- MAINTAIN LESS THAN 125 KIAS.
Door _. PULL CLOSED and LATCH.
(
(
CARGO POD DOOR(S) OPEN
1.
2.
(
(
Airspeed -- MAINTAIN LESS THAN 125 KIAS.
Land -- AS SOON AS PRACTICAL.
a.
Approach -- NORMAL.
b.
Landing -- AVOID A NOSE HIGH FLARE.
(
(
(
1 April 1998
3-26
For Training Purposes Only
)
CESSNA
MODEL 208 (675 SHP)
)
SECTION 3
EMERGENCY PROCEDURES
)
AMPLIFIED PROCEDURES
)
)
(-'~""',
)
"
)
)
,
The . following Amplified Procedures elaborate upon information
contained ' in the Operational Checklists portion of this section,
These procedures also include information not readily adaptable to
a checklist format, and material · to which a pilot could not be
expected to refer in resolution of a specific emergency.
NOTE
)
)
)
)
If a red or non-dimmable amber annunciator illuminates at
night and becomes an unacceptable distraction to the pilot
because of its brightness level, it may be extinguished for
the remainder of the flight by pushing in on the face of the
light assembly and allowing it to pop out. To reactivate the
annunciator, pull the light assembly out slightly and push
back in. For further details, refer to Section 7, Annunciator
Panel.
ENGINE FAILURE
)
(~-~,' ,:
)
)
)
)
If an engine failure occurs during the takeoff roll, the most important
thing to do is stop the airplane on the remaining runway. Those
extra iter1}s on the checklist will provide added safety after a failure
of this type.
Prompt lowering of the nose to maintain airspeed and establish a
glide attitude is the first response to an engine failure after takeoff.
Feathering the propeller substantially reduces drag, thereby
providing increased glide distance. In most cases, the landing
should be planned straight ahead with only small changes in
direction to avoid obstructions. Altitude and airspeed are seldom
sufficient to execute a 180 0 gliding turn necessary to return to the
runway. The checklist procedures assume that adequate time
exists to secure the fuel and electrical systems prior to touchdown.
After an engine failure in flight. the best glide speed as shown in
Figure 3-1 should be established as quickly as possible Propeller
feathering is dependent on existing circumstances and is at the
discretion of the pilot.
Maximum RPM selection will provide
increased gas generator windmilling speed for emergency restarts
in the event of a starter failure . On the other hand, to obtain the
maximum glide, the propeller must be feathered.
1 April
1998
3-27
For Training Purposes Only
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
While gliding toward a suitable landing .area, an effort should be
made to identify the cause of the power loss. An engine failure
might be identified by abnormal temperatures, mechanical noises or
high vibration levels in conjunction with the power loss; A flameout
will be noticed by a drop in ITT, torque and %N g .
(
(
(
(
(
(
(
A CAUTION
(
Do not attempt to restart an engine that is
definitely known to have failed.
(
(
A flameout may result from the engine running out of fuel, or
possibly may be caused by unstable engine operation. Unstable
engine operation such as a compressor surge (possible due to a
bleed valve malfunction (may be identifiable by an audible popping
noise just before flameout. Once the fuel supply has been restored
to the engine or cause of unstable engine operation eliminated, the
engine may be restarted.
(
The . best airstart technique is to initiate the relight procedure
immediately after a flameout occurs, provided the pilot is certain that
the flameout was not the result of some malfunction that might make
it hazardous to attempt a relight.
(
Regardless of airspeed or altitude, there is always the possibility
that the engine may light up successfully just as soon as the ignition
is turned on. In an emergency, turn on the ignition just as soon as
possible after flameout, provided the gas generator speed has not
dropped below 50%. Under these circumstances, it is not necessary
to shut off the fuel or feather the propeller. The power lever,
however,should be retarded to IDLE position .
(
(
(
(
(
(
(
(
(
(
(
A CAUTION
(
The pilot should determine the reason for power
loss before attempting an alrstart.
(
(
If a flameout has occurred and the gas generator speed has : (
dropped below 50, the fuel condition lever should be moved to the -(
CUTOFF position before an airstart is attempted.
(
3-28
1 April 1998
For Training Purposes Only
)
CESSNA
MODEL 208 (675 SHP)
)
SECTION 3
EMERGENCY PROCEDURES
)
)
)
( ':
0, .
)
. 20,000
)
...--..---...----r----,-----y----,-----._-..""..-,-...----.
* PROPELLER FEATHERED
)
18,000
* FLAPS UP
)
16,000 1---I--+--+--+---+--4~~F":'::
)
)
)
t: 14,000 1--4--+--4---t---+-~,£_z
)
~ 12,000
)
w
~
w 10,000
)
~. .
CI::
>
0
co
«
~
)
)
8000
J:
l?
w
)
J:
BEST GLIDE SPEED
6000
4000 I--__J--~r_--+-IWEIGHT (LBS)
)
)
)
)
14---~---+~~---4---4
8000
6300
4600
2000
KIAS
WITH
KIAS
WITHOUT
CARGO POD CARGO POD
96
99
85
88
75
72
0
0
5
10
15
20
25
30
35
40
GROUND DISTANCE - NAUTICAL MILES
45
50
)
)
)
{ :- }
» -<..
2685Xl054
)
Figure 3-1. Maximum Glide
)
)
1 April 1998
3-29
For Trainin Pur oses Onl
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
Propelle'r feathering is dependent on circumstances and is at the
discretion of the pilat. However, if engine oil pressure dtops below
15 psi, the propeller should be feathered.
If an airstart is to be attempted, follow the checklist procedures. ,
The Starter Assist procedure is preferred since it results in cooler
engine starts. Successful airstarts (with starter assist) may be
achieved at all airspeeds normally flown and up to an altitude of
14,000 feet. However, above 14,000 feet, or with the gas generator
RPM below 10%, starting temperatures tend to be higher and
caution is required.
A
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(
CAUTION
(
The fuel condition lever may be moved
momentarily to CUTOFF and then back to LOW
IDLE
if overtemperature
tendencies
are
encountered. This reduces the flow of fuel to
the combustion chamber.
(
(
(
If the engine starter is inoperative, follow the No Starter Assist
checklist procedures for an airstart.
(
(
A
• If a rise In Ng
CAUTION
(
~nd
ITT are not Indicated within
10 seconds, place fuel condition lever to
CUTOFF and abort start. Refer to Engine
Failure During Flight and Emergency Landing
Without Power checklists.
• Emergency airstarts may be attempted below
10% Ng and outside the normal airspeed
envelope, but In should be closely monitored. ,
The fuel condition lever may be moved
alternately to CUTOFF and then back to LOW
IDLE if overtemperature tendencies are
encountered.
(
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(
1 April 1998
For Training Purposes Only
(
(
' . Do not attempt an alrstart without starter
assist with 0% Ng .
3-30
(
)
)
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
FORCED LANDINGS
)
If all attempts to restart the engine fail and a forced landing is
imminent, select a suitable field and prepare for the landing as
discussed under the Emergency Landing Without Engine Power
checklist.
('
)
)
)
Before attempting an "off airport" landing with engine power
available, one should . fly over the landing area at a safe but low
altitude to inspect the terrain for obstructions and surface
conditions, proceeding as discussed under the Precautionary
Landing With Engine Power checklist.
)
NOTE
)
)
)
)
)
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~..
)
)
The overhead fuel tank selectors control shutoff valves at
. the wing fuel tank outlets. To minimize the possibility of a
fire, these selectors may be turned OFF during the final
stage of an approach to an "off-airport" landing. With the
selectors turned OFF, there is adequate fuel in the fuel
reservoir tank for 3 minutes of maximum continuous power
operation or approximately 9 minutes idle power operation.
A warning horn will sound with both fuel selectors turned
OFF. If it is objectionable, it may be silenced by pulling the
ST ART CaNT circuit breaker.
)
A WARNING
)
)
)
If the precautionary landing Is aborted, turn the
fuel tank selectors back ON after Initiating the
balked landing.
)
)
)
)
~;~)
)
Prepare for ditching by securing or jettisoning heavy objects
located in the baggage area and collect folded coats for protection
of occupants' faces at touchdown. Transmit Mayday message on
121.5 MHz giving location and intentions and squawk 7700 if a
transponder is installed. Avoid a landing flare because of difficulty
in judging height over a water surface. The checklists assume the
availability of power to make a precautionary water landing. If
power is not available, plan to touch down at minimum possible
speed in a normal nose up landing attitude.
)
)
1 April 1998
3-31
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL208 (675 SHP)
·LANDING WITHOUT ELEVATOR CONTROL
(
(
(
(
Using power lever and elevator trim control, trim for approximately
500 fpm descent with 20° flaps at 85 KIAS . Then control the glide ,
angle by adjusting power. If required, make small trim changes to i
maintain approximately 85 KIAS as power is adjusted during the
approach.
The landing flare can be accomplished by a gentle power reduction
accompanied by nose up trim. At forward C.G. loadings, it may be
necessary to make a small power increase in the final flare stage to
bring the nose up and prevent touchdown on the nose first. After
touchdown, move the power lever to idle.
SMOKE AND FIRE
(
(
(
(
(
(
(
(
In the event a fire is encountered, the following information will be
helpful in dealing with the emergency as quickly and safely as
possible.
The preflight checklist in Section 4 is provided to aid the pilot in
detecting conditions which could contribute to an airplane fire. As a
fire requires a combustible material, oxygen and a source of
ignition, close preflight inspection should be given to the engine
compartment and the underside of the wing and fuselage. Leaks in
the fuel or oil systems can lead to aground or inflight fire.
A WARNING
(
(
(
(
(
(
(
(
Flight should not be attempted with known fuel
or oil leaks. The presence of fuel or unusual oil
stains may be an indication of system leaks and
should be corrected prior to flight.
Probable causes of an engine fire are a malfunction of the fuel
control unit and improper starting procedures. Improper procedures
such as starting with the emergency power lever out of NORMAL
position or introducing fuel into the engine when gas generator
speed is below 10% RPM will cause a hot start which may result in !
an engine fire. In the event that this occurs, proceed in accordance
with the Engine Fire During Start On Ground checklist
(
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(
3-32
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
)
SECTION 3
EMERGENCY PROCEDURES
If an airplane fire is discovered on the ground or during takeoff, but
prior to committed flight, the airplane should be stopped and
evacuated as soon as practical,
(
)
)
)
)
)
)
)
)
)
)
(-,'
Engine fires originating in flight must be controlled as quickly as
possible in an attempt to prev.ent major structural damage.
Immediately shut oH all fuel to the engine and shut down the
engine. Close the cabin heat firewall shutoff control and forward
side vents, To avoid drawing fireinto the cabin, open the overhead
vents, turn the ventilation fans ON if they are installed, extend 10°
to 30°· flaps and slow down to 80-85 KIAS.
This provides a
positive cabin pressure in relation to the engine compartment. An
engine restart should not be attempted.
An open foul weather window produces a low pressure in the cabin.
To avoid drawing the fire into the cabin, the foul weather window
should be kept closed.
A fire or smoke in the cabin should be controlled by identifying and
shutting down the faulty system. Smoke may be removed by
opening the cabin ventilation controls. When the smoke is intense,
the pilot may choose to expel the smoke through the foul weather
window. The foul weather window should be closed immediately if
the fire becomes more intense when the window is opened.
The initial indication of an electrical fire is usually the odor of
burning insulation. The checklist 'for this problem should result in
elimination of the fire.
)
)
EMERGENCY OPERATION IN CLOUDS
(Vacuum System Failure)
In the event of a complete vacuum system failure during flight, the
directional indicator and attitude indicator will be disabled, and the
pilot will have to rely on the turn and bank indicator if he
inadvertently flies into clouds. If an autopilot is installed, it too can
be affected and must be turned oH.
Refer to Section 9,
Supplements, for additional details concerning autopilot operation.
The following instructions assume that only the electrically-powered
turn and bank indicator is operative, and that the pilot is not
completely proficient in instrument flying,
3-33
1 April 1998
For Training Purposes Only
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
EXECUTING A 180 0 TURN IN CLOUDS
Upon inadvertently entering the clouds, an immediate plan should
be made to turn back as follows:
1.
2.
3.
4.
5.
6.
Note the compass heading.
Note the tirne of the minute hand and observe the position of
the sweep secondhand on the clock.
When the sweep second hand indicates the nearest half
minute, initiate a standard rate left turn , holding the needle
of the turn and bank indicator in position for a standard rate
left turn for 60 seconds. Then roll back to level flight by
centering the needle, making sure the ball is also centered .
Check accuracy of the turn by observing the compass
heading which should be the reciprocal of the original
heading.
If necessary, adjust heading primarily with skidding motions
rather than rolling motions so that the compass will read
more accurately.
Maintain altitude and airspeed by cautious application of
elevator control. Avoid overcontrolling by keeping the hands
off the control wheel as much as possible and steering only
with rudder.
(
(
(
EMERGENCY DESCENT THROUGH CLOUDS
If conditions preclude reestablishment of VFR flight by a 180 0 turn,
a descent through a cloud deck to VFR conditions may be
appropriate. If possible, obtain radio clearance for an emergency
descent through clouds. To guard against a spiral dive,choose an
easterly or westerly heading to minimize ,compass card swings due
to changing bank angles. In addition, keep hands off the control
wheel and steer a straight course with rudder control by monitoring
the turn and bank indicator.
Occasionally check the compass
heading and make minor corrections to hold an approximate course.
Before descending into the clouds, set up a stabilized let-down
condition as follows:
1.
2.
Reduce power to set up a 500 to BOO feet/minute rate of
descent.
Adjust the elevator, aileron , and rudder trim control wheels
for a stabilized descent at 115 KIAS . .
3-34 '
1 April 1998
For Training Purposes Only
(
(
(
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(
(
)
CESSNA
)
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
(
)
)
)
3.
4.
Keep hands off control wheel.
Monitor turn and bank indicator and make corrections by
rudder alone.
5. Adjust rudder trim to relieve unbalanced rudder force, if
present.
6. Check trend of compass card movement and make cautious
. corrections with rudder to stop turn.
7. Upon breaking out of clouds"resume normal cruising flight.
)
)
)
RECOVERY FROM A SPIRAL DIVE
If a spiral is encountered, proceed as follows:
)
)
)
1.
2.
3.
)
{
4.
)
5.
)
)
6.
Retard the power lever to IDLE.
Stop the turn by using coordinated aileron and rudder
control to center the needle and ball.
Cautiously apply control wheel back pressure to slowly
reduce the airspeed to 115 KIAS.
Adjust the elevator trim control to maintain a 115 KIAS
glide.
Keep hands off the control wheel, using rudder control to
hold a straight . heading.
Use rudder trim to relieve
unbalanced rudder force, if present.
Upon breaking out of clouds, resume normal cruising flight.
)
)
)
)
)
)
INADVERTENT FLIGHT INtO ICING CONDITIONS
Intentional flight into known icing conditions is prohibited unless a
complete flight into known icing equipment package is installed.
During instrument flights, however, icing conditions may be
encountered inadvertently and, therefore, some corrective action will
be required as shown in the chec~list . Initiation of a climb is usually
. the best ice avoidance action to take; however, alternatives are
descent to warmer air or course reversal.
J{ ',
)'\.~>'
)
)
)
)
3-35
1 April 1998
li'n .. TrQlininfT PllrnOQPc. llnlv
CESSNA
MODEL 208 (675 SHP)
SECTION 3 ·
EMERGENCY PROCEDURES
(
STATIC SOURCE BLOCKED
(
If erroneous instrument readings are suspected due to water, ice or
other foreign matter in the pressure lines going to the standard
external static pressure source, the alternate static source valve !
should be pulled on. A chart in Section 5 provides a correction
which may be applied to the indicated airspeeds and altitudes
resulting from inaccuracies in the alternate static source pressures.
(
(
NOTE
The altitude hold mode of the autopilot should be
disengaged before actuating the alternate static source
valve.
(
(
SPINS
Intentional spins are prohibited in this airplane.
Should an
inadvertent spin occur, the following recovery technique may be
used.
1.
2.
3.
4.
5.
6.
RETARD POWER LEVER TO IDLE PO'SITION.
PLACE AILERONS IN NEUTRAL POSITION.
APPLY AND HOLD FULL RUDDER OPPOSITE TO THE '
DIRECTION OF ROTATION.
IMMEDIATELY AFTER THE RUDDER REACHES THE
STOP, MOVE THE CONTROL WHEEL BRISKLY
FORWARD FAR ENOUGH TO BREAK THE STALL. Full
down elevator may be required at aft center 01 gravity
loadings to assure optimum recoveries.
HOLD THESE CONTROL INPUTS UNTIL ROTATION
STOPS. Premature relaxation of the control inputs may
extend the recovery.
AS ROTATION STOPS, NEUTRALIZE RUDDER .. AND
MAKE A SMOOTH RECOVERY FROM THE RESULTING
DIVE.
NOTE
If disorientation precludes a visual determination of the
direction of rotation, the needle of the turn and bank
indicator or the symbolic airplane of the turn coordinator
may be referred to for this information.
3-36
1 April 1998
For Training Purposes Only
(
(
)
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
)
(-- ..
'.~
)
)
)
)
)
)
)
ENGINE MALFUNCTIONS
LOSS OF OIL PRESSURE
The complete loss of oil pressure, as evidenced by the low oil
pressure annunciator being illuminated and confirmed by the oil
pressure gauge reading, implies that the pilot will eventually lose
control of the propeller as the propeller springs and counterweights
Also, the engine will
drive the propeller blades into feather.
eventually seize. Therefore, if the pilot elects to continue to operate
the engine after loss of oil pressure, engine and propeller operation
shou ld be closely monitored for indication of the bnset of propeller
feathering or engine seizure and the engine failure checklist should
be completed at that time . Operation of the engine at a reduced
power setting (preferably at the minimum power required for the
desired flight regime) will generally prolong the time to loss of
engine/propeller thrust.
)
Operation of the engine with the oil pressure in the yellow arc is not
considered critical, but is a cause for concern and should be
tolerated only for the completion of the flight. Continued monitoring
of the oil pressure gauge will provide an early indication of dropping
oil pressure due to insufficient oil supply or a malfunctioning oil
pump, and will give the pilot additional time to divert to a suitable
emergency landing area with the engine operating.
)
FUEL CONTROL UNIT MALFUNCTION IN THE PNEUMATIC OR
GOVERNOR SECTIONS
)
le'''
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)
)
)
)
)
)
)-:-" ':
A malfunction in the pneumatic or governor sections of the fuel
control unit may cause engine power to decrease to minimum flow
idle~ Symptoms of this type failure would be an ITT indication in the
typical idle range of 500 to 600°C, Ng of 48% or above (increases
with altitude), and no engine response to power lever movement. If
this type of malfunction has occurred, the emergency power lever
(fuel control manual override) may be used to restore engine power.
To use the manual override system, place the power lever at its
IDLE position and move the emergency power lever forward of its
IDLE gate and advance as required.
),,;;.:./
)
3-37
1 April 1998
For Trainin2 Purposes Onl
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
A CAUTION
I
When using the fuel control manual override system,
engine response may be more rapid than when using
the power lever. Utilize slow and smooth movement of
the emergency power lever to avoid engine surges,
and/or exceeding ITT, Ng, and torque limits . .
NOTE
• When using emergency power lever, monitor gas generator
RPM when reducing power near idle, to keep it from
decreasing below 65% in flight.
The emergency power lever may have a dead band, such
that no engine response is observed during the initial
forward travel from the IDLE position.
GEAR BOX CONTAMINATION
Contamination of the reduction gear box as evidenced by the chip
detector annunciator being illuminated does not by itself demand
any immediate action by the pilot.
If this annunciation is ,
accompanied by signs of engine distress (fluctuation in engine \
power gage indications, or erratic engine operation), engine
operation may be continued at the discretion of the pilot consistent
with crew satety. However, the power gages should be closely
monitored for further degradation in torque or RPM indications, or
engine operation, which implies that seizure is imminent.
The
engine tailure checklist should be completed at that time.
FUEL SYSTEM MALFUNCTION I INADVERTENT
FUEL FLOW INTERRUPTION PROCEDURES
Fuel flows by gravity from the wing tanks, through fuel tank Shutoff
valves at the inboard end of each wing tank, and on to the reservoir
located under the center cabin floorboard. After engine start, the
main ejector pump (located in the reservoir) provides fuel to the
engine-driven fuel pump at approximately 10 psi.
(
(
If the main ejector pump should malfunction, a pressure switch will . (
activate the amber FUEL PRESS LOW annunciator as well as turn ( . (
on the auxiliary boost pump (when the fuel boost switch is in the ' . c,c
NORM position) anytime the fuel pressure drops below
(
approximately 4.75 psi.
3-38
15 November 2000
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
)
)
Anytime the level of fuel in the reservoir drops to approximately onehalf full, the red RESERVOIR FUEL LOW annunciator will
illuminate. If this occurs, the pilot should immediately verify that
both fuel tank selectors (located in the overhead panel) are ON and
turn on the ignition and fuel boost switches.
)
)
..
-" - ~
t
SECTION 3
EMERGENCY PROCEDURES
.
'"
)
A WARNING
)
)
There is only enough fuel in the reservoir for
approximately 1-1/2 minutes of engine operation
maximum continuous power after illumination
of the RESERVOIR FUEL LOW annunciator.
at
)
)
)
If the fuel tank selectors have been left off, turning them on will
quickly fill the reservoir and extinguish the RESERVOIR FUEL LOW
annunciator. Once the cause of the RESERVOIR FUEL LOW
condition has been determined and corrected (annunciator
extinguished), the ignition and fuel boost switches can be returned
to their NORM positions.
)
)
)
)
A fuel selector off warning system advises the pilot if both fuel tank
. selectors are in the OFF position before engine start, if either fuel
tank selector is OFF during engine start, or if one fuel tank selector
is OFF and the fuel level in the tank being used drops below
approximately 25 gallons. The warning system includes a red
annunciator labeled FUEL SELECT OFF and two warning horns. If
the FUEL SELECT WARN circuit .breaker has popped or the START
CONT circuit breaker has been pulled (possibly for ground
maintenance), the FUEL SELECT OFF annunciator will be
illuminated even with both fuel tank selectors in the ON position.
This is a warning to the pilot that the fuel selector off warning
system has been deactivated. See Section 7 for further details on
the fuel· selector off warning system.
I(
\.. ..
)
)
)
)
)
)
)
)
ELECTRICAL POWER SUPPLY SYSTEM
MALFUNCTIONS
)
)
),[
:
)\ ;.,;,..J
)
BATTERV MALFUNCTIONS
If the optional nickel cadmium ' battery is installed, a battery
temperature monitoring system is provided to detect an incipient
thermal problem . The BATTERY HOT annunciator indicates
)
)
3-39
129 September 1998
"or Tr .. inina Pllrnn<:p<: Onlv
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
internal battery temperature is 140°F or higher. The BATIERY
OVERHEAT annunciator indicates battery temperature has reached
160°F. In either case, it is necessary to stop providing charging
current to the battery from the airplane power system. This is accomplished by turning the battery switch off using the checklist procedures. During these procedures, the volt/ammeter (in BATT position) should be used to verify that charging current is reduced to zero. A battery temperature of 160°F may be critical . and the flight
should be terminated as soon as practical. A battery temperature of
140°F is critical if the temperature and charging current continue to
rise. Under high ambient temperature (above 100°F) conditions, a
battery temperature of 140°F is not critical if a decreasing charging
current trend is · verified and maintained by monitoring the
volt/ammeter selected to the BAIT position.
GENERATOR OR MAIN BUS MALFUNCTIONS
Illumination of the VOLTAGE LOW annunciator is a warning that the
power distribution bus voltage is low enough to start discharging the
battery. The volt/ammeter (in VOLTS position) is used to verify the
low bus voltage. A low or zero reading of the volt/ammeter (in GEN
position) confirms that the charge is insufficient or generator output
current is zero. If the GENERATOR OFF annunciator is illuminated,
it indicates that the generator contactor has disconnected the
generator from the power distribution bus. The most likely causes
of a generator trip (disconnection) are line surges, tripped circuit
breakers or accidental switch operation. In these cases, follow the
checklist procedures to restore generator operation.
The airplane is equipped with two starter contactors. One is used
for starts on external power and the other for battery starts. If either
contactor does not open after reaching approximately 46% N g, the
amber STARTER ENERGIZED annunciator will remain illuminated.
In most cases when this occurs, the generator will not transfer to the
generate mode, and the GENERATOR OFF annunciator will remain
illuminated. Under these conditions, it will be necessary to shut
down the engine using checklist procedures and correct the
malfunction prior to flight.
(
(
(
(
(
(
13-40
29 September 1998
For Training Purposes Only
)
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
)
(
)
)
)
)
)
)
)
)
)
)
('
)
)
)
)
)
)
The electrical power distribution system consists of a primary power
distribution bus in the engine compartment which receives power
from the battery and the generator, and two (No. 1 & No. 2) main
power buses located in the circu it breaker panel. The main buses
are each connected to the power distribution bus by three feeder
cables. Each feeder cable is protected by a fuse link and a circuit
breaker. This multiple feeder system provides automatic isolation of
a. feeder cable ground fault. If one of the three 30-amp feeder circuit breakers on .either bus opens, it should be assumed that a feeder cable ground fault has been isolated, and attempted resetting of
these breakers prior to troubleshooting is not recommended. The
electrical load on the affected bus should be maintained below the
remaining 60-ampere capacity.
LOSS OF ELECTRICAL POWER
The design of the electrical power system, due to the self-exciting
feature of the generator and the multiple protected busing system,
minimizes the possibility of a ' complete electrical power loss.
However, a fault to ground (airframe) on the generator or battery
cables can be identified by one or more of the following: illumination
of the GENERATOR OFF annunciator, sudden dimming of lights,
contactor chattering , circuit breaker tripping, or arcing noises. The
volt/ammeter provides further information concerning the location of
the fault, or the system affected by the fault. In the event of the
above indications, the portion of the system containing the fault
should be isolated. The battery should be disconnected first by
turning the battery switch to OFF. Then , following the checklist
procedures for Generator Failure should result in restoration of
electrical power to the distribution buses. The volt/ammeter should
be monitored to assure that ground fault currents have been shut off
and the capacity of the remaining power source(s) is not exceeded.
)
)
)
~(~}
PARTIAL AVIONICS POWER FAILURE
Avionics power is supplied to the No. 1 and No. 2 avionics buses
from the power distribution bus in the engine compartment through
separate protected feeder cables. In the event of a feeder cable
failure, both avionics buses can be connected to the remaining
feeder by closing the guarded avionics bus tie switch. If a ground
fault has occurred on one feeder, it will be necessary to verify the
)
)
)
)
129 September 1998
3-41
For Traininl! Purooses On Iv
SECTION 3
EMERGENCY PROCEDURES
CESSNA
MODEL 208 (675 SHP)
avionics power switch/breaker associated with the affected feeder is
off before the avionics bus tie switch will restore power to both
avionics buses. The maximum avionics load with one feeder should
be limited to 30 amperes. Nonessential avionics equipment should
be turned off.
STANDBY ELECTRICAL SYSTEM MALFUNCTIONS
An operational check of the standby electrical system is performed
by following the Normal Procedures, Before Takeoff checklist. With
the generator supplying the electrical load and the standby power
switch ON, both the amber annunciators, STBY ELECT PWR ON
and STBY ELECT PWR INOP, should be extinguished.
The volt/ammeter should indicate zero amps in the AL T position. If
the STBY ELECT PWR INOP annunciator is illuminated, it indicates
that the alternator has no output.
If a line voltage surge or
temporary condition has tripped the ACU (alternator control unit),
then cycling the standby power switch to OFF, then back ON, may
reset the ACU and restore standby power.
If, due to a power system malfunction, the standby electrical system
is carrying part of the electrical load (more than 10 amps), the STBY
ELECT PWR ON annunciator will be illuminated and the
volt/ammeter (in ALT position) will indicate the amount of current
being supplied by the standby electrical system.
To attempt to restore main power, refer, to the Section 3 emergency
If this attempt is
procedures for Loss Of Electrical Power.
successful, the standby electrical system will revert to its normal noload condition and the STBY ELECT PWR ON annunciator will
extinguish. If main electrical power cannot be restored, reduce
nonessential loads as necessary to remain within the 75-amp
capability of the standby electrical system. Loads in excess of this
capability will be indicated by illumination of the VOLTAGE LOW
annunciator and the volt/ammeter showing discharge current (in the
BATT position).
13-42
29 September 1998
For Training Purposes Only
)
)
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
)
(-
)
)
)
)
INADVERTENT OPENING OF AIRPLANE DOORS
IN FLIGHT
If any of the airplane doors should inadvertently open in flight, the
airplane should be slowed to 125 KIAS or less to reduce buffeting of
the doOrs. If the upper cargo dqor is open, slow to 100 KIAS or less
and lower flaps to full down so that wing downwash will move the
door towards its normally closed position. Closing the upper cargo
door (or upper half of the passenger door on the Standard 208) can
be accomplished after , airspeed has been reduced by pulling the
door forcefully closed and latching the door. If the door cannot be
closed in flight, a landing should be made as soon as practical in
accordance with the checklist procedures. On the Cargomaster, an
open cargo door cannot be closed in flight since the inside of the
upper door has no handle.
EMERGENCY EXITS
)
)
Use of the crew entry doors, the passenger entry doors, and the
cargo doors for emergency ground egress from the Standard 208 is
illustrated in Figure 3-2.
Emergency ground egress from the
Cargomaster is accomplished by exiting the airplane through the left
and right crew entry doors as shown in Figure 3-2.
)
A WARNING
)
)
)
Do not attempt to exit the Cargo master through
the cargo doors. Since the inside of the upper
door has no handle, exit from the airplane
through these doors is not possible.
}
When exiting the airplane, avoid the propeller
area.
)
)
)(:
)''''-0./
)
)
)
)
129 September 1998
3-43
CESSNA
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
(
(
.// // / / / / // / // /,1
~
WHEN EXITING AIRPLANE ,I
~
AVOIO PROPEllER
~
//////////////'"
~
'.f 'DP£N~
@
//~~,
~
~
/'
~
WA RNING :
~
lH
CREW
DOOR
jx
~
INSTRUCTION
PLACARO
EXIT
CREW
DOOR
~l
~EXIT
\~\,~~
-:Fi\ gg I I
~
1-
'. , ' "
r1~
-
~
PULL HANDLE IN AND
"
~
0
0
'''''' ""n"""""
~
TO OPEN POSITION
PUSH UPPER
CCOROUT
"
~
•~I
'-
~3
LOWER~
.
~
~
"
( ~l:J
r- :::0~
(
PUSH UPPER
DOOR OUT
(
(STANDARD
20B ONLY) / / / / / / / / / / / / / / . 1 .
~
WARNING:
'/
~ OUTSIDE PROXIMITY OF ~
'/ LOWER DOOR MUST BE
",I CLEAR BEFORE OPENING I.
(
(
'//////////////'"
\I:,
3
~
LIfT UP LOWER
--DOORHANDlE
~ ~'fi
r'-- ~ J]
i»,
~
. TO OPEN
.~EN
, ~"
PUSH DOOR OUTWAAO " STEP TH ROUGH OPENING
WHILE HOLDING DOOR IN
OPEN POSITION ANO
EXIT AIRPLANE
.,
_
0\
"
ie
POS~:~~N
(
~4
,
TO OPEN
&I ",. ' .'j'
~
'
n,", -;. ' ,,'
ROTATECLDCKWISE
~!JJI"
•
~.\
..,,' .. ..,
,"cc'"''''''''''
,
C~':O
DOOR
(STANDARD
208 ONlY)
OPEN
(
L:::::;:::;..../----\.-==:J
l\!.
LIFT
DOORUP
HANDLE
TO OPEN
(
CREW
DOOR
NOTE:
PUSH LOWER
ODOR OUT AND
EXIT AIRPLANE
SEATING CONFIGURATION MAY NOT
AGREE WITH YOUR AIRPLANE
,
'
/"
26B5M6018
Figure 3-2. Emergency Exit
3-44
1 April 1998
For Training Purposes Only
(
)
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
)
SECTION 4
)
NORMAL PROCEDURES
)
TAI3LE OF CONTENTS
)
)
,
}
Introduction ,., .......... . .... . . . .. . . . .. . .. . ... . . .
Speeds For Normal Operation . .. . ... .. ... . ........ .. .
)
Page
4-3
4-3
CHECKUSTPROCEDURE~
)
)
)
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f"
,;"
)
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)
)
)
()
)
)
Preflight Inspection .... . ... ... ... . ... . ........... . . '
Cabin .. .. ... . . ..... .. ...... . . . ... . .. .. ..... . .
Left Side .... .... .......... . .. . .... . ... . .. . .. . .
Left Wing, Leading Edge .. . ... . . .... .... . ...... .. .
Left Wing, Trailing Edge ..... .... . . ............ .. .
... .. ..... . ... . .................. .
Empennage
Right Wing, Trailing Edge ............... ... ..... . .
Right Wing
....... . ............ . ... .. . ... .... .
Nose ............. . ......... . .... .. .. .. . . .. .
Before Starting Engine ...................... .. ... .
Starting Engine (Battery Start) ...................... .
Starting Engine (Auxiliary Power Start) ... , .. .. ........ .
...................................... .
Taxiing
Before Takeoff
. . . . . . . . . . . . . . .................. .
Takeoff
. ........ .. . . ... . ................. . ... .
Normal Takeoff .. . . . ..... . ....... .. ........... .
Short Field Takeoff .. . ........... , .. .. . . . .. .. . . .
Type I! or Type IV Anti-ice Fluid Takeoff . .. ... ... . ... .
Enroute Climb .. . . . .. .. .. ...... . . . ............ .
Cruise Climb ........... ' .......... . ...... , .... .
Maximum Performance Climb . ............... . ... .
Cruise .. '.... . . ... . ......... . . . . ............ .
Descent ,. . . . . . ................. . . . .. .. ... . .. .
Before Landing ... . ...... . ..... .. . . ........... .
Landing ....... . .... . .......... . .. . ...... . .. .
Normal Landing .............................. .
Short Field Landing
........ .. ........... ... ... .
Balked Landing ... ......., . . ................ , . .
After Landing . ... . . . . . . . . . . . . . . . . . . . . . . . . . . . ..
Shutdown And Securing Airplane
' . '.. .. . .... . ..... .
4-5
4-5
4-6
4-7
4-8
4-8
4-9
4-9
4-10
4-12
4-13
4-14
4·16
4·16
4·18
4·18
4·18
4-18
4-19
4-19
4-19
4-20
4-20
4·21
4·21
4·21
4-22
4·22
4-23
4-23
)
)
)
4·1
1 April 1998
For Trainin Pur oses Only
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
TABLE OF CONTENTS (Continued)
Page
(
SYSTEMS CHECKS
(
Overspeed Governor Check . , , , ... . .. . . . .... , . . . . . . . .
Autopilot Check (King KFC-150)
.....................
Before Takeoff Reliability Tests ........ . ....... . ...
Autopilot Check (Bendix/King KFC-22S) .. . ... ..... . . . ..
Before Takeoff Reliability Tests . ..... ... ....... ,. ..
Standby Power Check . . . . . . . . . . .... . . . .... ... .. .. .
Known Icing Check .... ....... , . ... .. .. .... ... . .. .
Preflight Inspection .. ...... . .. .. . ... , .. . .. , . ....
Before Takeoff ..... , . .. . . .. . . . . ... ,...........
4-24
4-25
4-25
4-26
4-26
4-27
4-28
4-28
4-28
(
(
(
(
AMPLIFIED PROCEDURES
(
4-29
Preflight Inspection ............... . ...... . ....... .
Before Starting Engine ...... , ..... . .. ... . ... . .. . . .
4-31
Starting Engine ............... . ..... ... ... . ..... .
4-33
Engine Clearing Procedures (Dry Motoring Run)
. . . . . . .. . 4-36
4-37
Engine Ignition Procedures .... . ... . .. ..... . . . ... . . .
Engine Inertial Separator Procedures .............. . .. .
4-37 ',
4-38
Taxiing
.. .. .. . ................ . , . , ...... . . . . "
Before Takeoff ............... .... . ... '... . ..... ..
4-40
. 4-41
Takeoff
.......... .. .. . .... . .......... , ... ... . .
Power Setting ...... . .. . .... . ......... ,., ..... .
4-41
Wing Flap Settings ...... . . . , ... , ....... ... .... .
4-41
Short Field Takeoff ...... . .. , ..... ... .......... .
4-41
Type II or Type IV Anti-ice Fluid Takeoff ...... . ...... .
4-42
Crosswind Takeoff ...... . .. . ... . ........... . .. .
4-42
Enroute Climb . . . ...... . .... ... .. . ........ . ... . . .
4-42
Cruise
. , .. , .. ... .. . .... . . . ...... .... . . ... . .. .
4-44
Stalls
.. . ... . . . . .. . ....... , ...... ......... . . . .
4-47
Landing ...... ... . ... . . ..... . .......... .. . . , . . .
4-47
4-47
Normal Landing .................... ... ....... .
4-48
Short Field Landing ............. , .. . ........... .
4-49
Crosswind Landing ......... , . . ................ .
Balked Landing . .. ...... . ... , ........... , ..... .
4-49
4-49
After Shutdown .... . ................ , .......... . .
4-50 i
Cold Weather Operation .......................... .
4-51 '.
High Altitude Operation , . . ..... , . .. . . ... . .... . .... .
4-51
Engine Compressor Stalls .. . ...... . .... . . ......... .
4-51
Noise Characteristics ...... . . . ..... ' .. .. . .... ... . . .
15 November 2000
4-2
For Training Purposes Only
(
(
{
(
(
(
(
(
(
(
(
(
(
(
(
)
)
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NO~MALPROCEDURES
)
INTRODUCTION
)
)/
~,
Section 4 provides checklist and amplified procedures for the
conduct of normal operation. Normal procedures associated with
optional systems can be found in Section 9.
)
A WARNING
)
)
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)
)('
A
)
)
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)
)
)
)
)
)
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)e-'
) <',,):"
)
There is no substitute for proper and complete
preflight planning habits and their continual
Be
review In minimizing emergencies.
thoroughly knowledgeable of hazards and
conditions which represent potential dangers,
and be aware of the capabilities and limitations
of the airplane.
SPEEDS FOR NORMAL OPERATION
Unless otherwise noted, the following speeds are based on a
maximum weight of 8000 pounds and may be used for any lesser
weight. However, to achieve the performance specified in Section 5
for takeoff distance, climb performance, and landing distance, the
speed appropriate to the particular weight must be used.
Takeoff:
. . . . . . . . . . . .. . .. . ... .. .. ..
85-95 KIAS
Normal Climb Out
.......
82 KIAS
Short Field Takeoff, Flaps 20°, Speed at 50 Feet
Type II or Type IV Anti-ice Fluid Takeoff (Flaps 0°)
89 KIAS
Enroute Climb, Flaps Up:
, Cruise Climb
.. ..... .. .. .. . ...... ........
115-125 KIAS
Best Rate of Climb, Sea Level
. .. . .. . .. .. . .. . . . ..
107 KIAS
Best Rate of Climb, 10,000 Feet
..... ...... .. ... . .
101 KIAS
Best Rate of Climb, 20,000 Feet
. _. __ . .. __ _ . _.. _ . .
91 KIAS
Best Angle of Climb
.. ... ... . ...... .......... . .
90 KIAS
Landing Approach:
95-110 KIAS
Normal Approach, Flaps Up
. . .. .. . .... . .... . . .
78·85 KIAS
Normal Approach, Flaps 30° , ..... . ..... . . ... . .. .
Short Field Approach, Flaps 30 0
• . • • • • • • • •• • • • • • • • • •
78 KIAS
Balked Landing :
77 KIAS
Takeoff Power, Flaps 20° ..... ... ... . . . .. . ....... .
Maximum Recommended Turbulent Air Penetration Speed:
150 KIAS
8000 Lbs
.. . .. . .... . . . ... . ...... . ... . .... . .
134 KIAS
6300 Lbs
. . .... , ..... . .. .. .. , .. .. . " . .. . .. .
115 KIAS
4600 Lbs
. . . ... ....... .. . . . . ..... .... , . . .. .
Maximum Demonstrated Crosswind Velocity :
20 KNOTS
. ... .. .... ..... .. . ..... . . .
Takeoff or Landing
)
)
4-3
1 April 1998
For Training Purposes Only
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
PREFLIGHT INSPECTION WARNINGS
A WARNING
•
Visually check airplane for general condition during
walk-around Inspection and remove any Inlet, exit or
exhaust covers. If cargo pod is installed, check its
Installation for security during the walk-around
inspection. Use of a ladder will be necessary to gain
access to the . wing for visual checks, refueling
operations, , checks of the stall warning and pitot
heat, and to reach outboard fuel tank sump drains.
•
It Is the pilot's responsibility to ensure that the
airplane's fuel supply is clean before flight. Any
traces of solid contaminants such as rust, sand,
pebbles, dirt, microbes, ' and bacterial growth or
liquid contamination resulting from water, Improper
fuel type, or additives that are not compatible with
the fuel or fuel system components must be
considered hazardous. Carefully sample fuel from
all fuel drain locations during each preflight
Inspection and after every refueling.
•
It is essential in cold weather to remove even small
accumulations of frost, ice, or snow from wing, tall,
and control surfaces (exercise caution to avoid
distorting vortex generators on horizontal stabilizer
while deicing).
Also, make sure that control
surfaces contain no internal accumulations of ice or
debris. Prior to any flight in icing conditions, check
that pitot/statlc source and stall warning heaters are
warm to touch within 30 seconds with appropriate
switches on. If these requirements are not
performed, aircraft performance will be degraded to
a point where a safe takeoff and climb out may not
be possible.
(
(
•
If a night flight is planned, check operation of all
lights, and make sure a flashlight is available and
properly stowed.
4-4
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
CHECKLIST PROCEDURES
PREFLIGHT INSPECTION
)
)
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)
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26856017
)
)
)
)
G)CABIN
)
)
~(~~./
)
1.
2.
3.
4.
Pilot's Operating Handbook and Other Required Documents
-- AVAILABLE IN THE AIRPLANE.
Control Locks -- REMOVE (DISENGAGE rudder lock, if
installed).
Parking Brake -- SET.
All Switches -- OFF.
)
)
1 April 1998
4-5
or Traini
Pur oses Onl
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16
.
17.
18.
19.
1
20.
21.
22.
23.
24.
25.
26.
G
1.
All Circuit Breakers -- IN.
Static Pressure Alternate Source Valve -- OFF.
Inertial Separator T-Handle -- NORMAL.
Standby Flap Motor Switch (Overhead) -- GUARDED
NORM.
Oxygen Supply Pressure (if installed) -- CHECK.
Oxygen Masks (if installed) -- CHECK AVAILABLE.
Fuel Selector Valves -- CHECK ON and FEEL AGAINST
STOPS.
Fuel Totalizer (if installed) -- RESET as required.
Radar (if installed) -- OFF.
Air Conditioner (if installed) -- OFF.
Bleed Air Heat Switch -- OFF.
Emergency Power Lever -- NORMAL, and if applicable,
copper witness wire present and intact.
Trim Controls -~ SET.
Fuel Shutoff -- ON.
Cabin Heat Firewa" Shutoff Control -- CHECK IN.
Battery Switch -" ON.
Avionics Power Switch No. 2 -- ON. Check audibly that
avionics cooling fan is operating.
Avionics Power Switch No.2 -- OFF.
Fuel Quantity Indicators --:- CHECK QUANTITY.
Wing Flaps -- FULL DOWN.
PitoUStatic and Stall Heat Switches -- ON for 30 seconds ,
then OFF. (Ensure pitot/static tube covers are removed.)
'
Battery Switch -- OFF.
,
(
(
LEFT SIDE
Fuel Reservoir Drain (bottom of fuselage or left side of
cargo pod) -- DRAIN (using fuel sampler) to check for water,
sediment, and proper fuel before each flight and after each
refueling. If water is observed, take further samples until
clear. Take repeated samples from all fuel drain points (see
Section 7 Fuel System Schematic for all nlne drain
locations) until all contamination has been removed.
(
(
NOTE
Properly dispose of samples from all fuel drains, since
aviation turbine fuel will deteriorate asphalt surfaces.
(
(
-(
4-6
7 September 2001
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
2. Main Landing Gear -- CHECK proper tire inflation and con)
"--"
y;
)
)
dition cif gear.
3 . Inboard Fuel Tank Sump and External Sump Quick-Drain
Valves -- DRAIN (using fuel sampler) to check for water,
sediment, and proper fuel before each flight and after each
refueling. If water is observed, take further samples until
clear. Take repeated samples from all fuel drain points until
all contamination has been removed.
o
)
)
LEFT WING Leading Edge
)
A
\
WARNING
I
)
)
)
1'" ,
t'-
"
)
)
)
)
)
)
)
)f
)\,"'-""
It is essential in cold weather to remove even
small accumulations of frost, Ice, or snow from
the wing and control surfaces. Also, make sure
the control surfaces contain no Internal
accumulations of Ice or debris. Prior to any flight
In Icing conditions, check that pltot/statlc source
and stall warning heaters are warm to touch after
turning pltot/statlc and stall heat switches on for
30 seconds, then off. Make sure the pltot covers
are removed.
1. Wing Strut Deice Boots (if installed) -'- CHECK for tears,
abrasion and cleanliness.
2. Wing Tie-Down -- DISCONNECT.
. 3. Wing Deice Boots (if installed) -- CHECK for tears, abrasion
and cleanliness .
4. Stall Warning Vane -- CHECK freedom of movement,
au. dible warning and w
. armth. (For aircraft equipped with
stall ,warning ground disconnect switch, check audible
warning with elevator control off forward stop).
5. Pitot/Static Tube -- CHECK security, openings for stoppage
and warmth.
6. Landing and Taxi Lights -- CHECK condition and
cleanliness.
7. Fuel Quantity -- Visually check for desired level.
8. Fuel Filler Cap -- SECURE.
al
)
)
)
)
15 November 2000
4-7
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
9. Outboard Fuel Tank Sump Quick-Drain Valve (if installed
and airplane parked with one wing low on a sloping ramp) -DRAIN (using fuel sampler) to check for water. sediment and
proper fuel before each flight and after each refueling. If
water is observed, take further samples until clear. Take
repeated samples from all fuel drain points until all
contamination has been removed.
10.' Navigation and Strobe Lights -- CHECK for condition and
cleanliness.
8
1.
2.
3.
4.
5.
o
i
LEFT WING ,Trailing Edge
Fuel Tank Vent.-- CHECK for obstructions.
Aileron and Servo Tab -- CHECK condition and security.
Static Wicks -- CHECK condition.
Spoiler -- CHECK condition and security.
Flap -- CHECK condition and security.
EMPENNAGE
A WARNING
It js essential in cold weather to remove even
small accumulations of frost, ice, or snow from
the tail and control surfaces. Exercise caution to
avoid distorting vortex generators on the
horizontal stabilizer while deicing. Also, make
sure the control surfaces contain no Internal
accumulations of Ice or debris.
1.' Baggage -- CHECK SECURE through cargo door.
2, Cargo Door -- CLOSED and LATCHED.
3. Tail Tie-Down -- DISCONNECT.
)
4. Deice Boots (if installed) -- CHECK for tears, abrasion and
cleanliness.
5. Rudder Gust Lock (if installed) -- DISENGAGE.
6. Control Surfaces and Elevator Trim Tabs -- CHECK
condition, security, freedom of movement and tab position .
7. Static Wicks -- CHECK condition .
8. Passenger Entry Door (if installed) -- CLOSED and
LATCHED.
1 April 1998
4-8
For Training Purposes Only
(
(
(
)
CESSNA
MODEL 208 (675 SHP)
)
)
G
)
)
)( --- .,
\,
)
RIGHT WING Trailing Edge
1.
Flap -- CHECK condition and security.
Spoiler -- CH~CK condition and security.
Aileron and Trim Tab -- CHECK condition and security.
Static Wicks -- CHECK condition.
Fuel Tank Vent -- CHECK for obstructions.
2.
3.
4.
5.
)
G)
)
)
SECTION 4
NORMAL PROCEDURES
RIGHT WING Leading Edge
A
)
)
WARNING
It Is essential In cold weather to remove even
small accumulations of frost, ice, or snow from
the wing and control surfaces. Also, make sure
the control surfaces contain no Internal
accumulations of Ice or debris.
)
)
)
1.
)
)f
\ ,
)
2.
3.
4.
)
)
)
)
)
5.
)
6.
)
7.
)
)
)[ " :
) ' rj
8.
9.
10.
Navigation and Strobe Lights -- CHECK condition and
cleanliness.
Fuel Quantity -- VISUALLY CHECK for desired level.
Fuel Filler Cap -- SECURE.
Outboard Fuel Tank Sump Quick-Drain Valve (if installed
and airplane parked with one wing low on a sloping ramp) -DRAIN (using fuel sampler) to check for water, sediment and
proper fuel before each flight and after each refueling. If
water is observed, take further samples until clear. Take
repeated samples from a/l fuel drain pOints until all
contamination has been removed.
Pitot/Static Tube -- CHECK security, openings for stoppage
. and warmth.
.
Landing and Taxi Lights -- CHECK condition and
cleanliness.
Wing Deice Boots (if installed) -- CHECK for tears, abrasion
and Cleanliness.
Radome (if installed) --CHECK condition and security.
Wing Tie-Down -- DISCONNECT.
Wing Strut Deice Boots (if installed) -- CHECK for tears,
abrasion, and cleanliness.
)
)
)
1 April 1998
4-9
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675SHP)
11 . Inboard Fuel Tank Sump and External Sump Quick-Drain
Valves -. DRAIN (using fuel sampler) to check ' for water,
sediment, and proper fuel before each flight and after each
refueling. If water is observed, take further samples until
clear. Take repeated samples from all fuel drain points until
all contamination has been removed.
12. Main Landing Gear _. CHECK proper tire inflation and
condition of gear.
CV
\
NOSE
A WARNING
It is essential in cold weather to remove even
small accumulations of frost, ice, or snow from
the propeller blades and spinner, and the air
Inlets (starter/generator, 011 cooler and engine
Inlets).
1.
2.
3.
Exhaust Cover (if installed) -- REMOVE.
Cowling -- OPEN right side of upper cowling for access and
CHECK condition and security.
•
Engine (right side) -- CHECK for general condition, security,
fuel and oil leakage and damage to any components.
A WARNING
Avoid touching the output connectors or
coupling nuts or ignition excitor with bare hands.
4.
5.
6.
7.
8.
9.
Battery -- CHECK condition and security, and power cables
secure.
Exhaust System -- CHECK condition, security, cracks,
distortion and damage.
Cowling -- CLOSE and LATCH right side.
Air Inlet Covers -- REMOVE.
Air Inlets-- CHECK starter/generator blast tube opening and
oil cooler inlet (right) and engine induction air inlet (left) for
condition, restrictions, and debris.
Propeller Anchor -- REMOVE.
4-10
1 April 1998
For Training Purposes Only
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
)
10.
)
Ie'
~:
)
11.
12.
)
)
13.
)
14.
)
15.
)
16.
)
)
Propeller -- CHECK blades for nicks, gouges, looseness of
material, erosion, cracks and debonds. Also, inspect blades
for lightning strike (darkened area near tips), Anti-ice boots
for security, and evidence of grease and oil leaks.
Propeller Spinner -- CHECK condition and security.
Nose Wheel Strut and Tire -- CHECK for condition, red overtravel indicator block and cable intact (not fallen into view),
and proper inflation of tire.
Cowling -- OPEN left side of upper cowling for access and
CHECK condition and security.
Engine (left side) -- CHECK for general condition, security,
fuel and oil leakage and damage to any components.
Inertial Separator Bypass Outlet -- CHECK CLOSED and
duct free of debris.
Oil Dipstick/Filler Cap -- CHECK oil level, then check
dipstick/filler cap SECURE. Fill to within 1 112 quarts of
MAX HOT or MAX COLD (as appropriate) on dipstick.
Markings indicate U.S. quarts low if oil is hot.
)
A WARNING
)
Ensure oil dipstick cap is securely latched down.
Operating the engine with less than the
recommended oil level and with the dipstick cap
unlatched will result in excessive 011 loss and
eventual engine stoppage.
)
17.
18.
19.
20.
)
)
){--
.
;':.,;/;'
21.
22.
Fuel Filter -- CHECK FUEL FILTER BYPASS FLAG for
proper location (flush).
Brake Fluid Reservoir -- CHECK LEVEL.
Cowling -- CLOSE and LATCH left side.
Fuel Filter Quick-Drain Valve -- DRAIN (using fuel sampler)
to check for water, sediment, and proper fuel before each
flight and after each refueling. If water is observed, take
further samples until clear. Take repeated samples from all
fuel drain pOints until all contamination has been removed.
Fuel Drain Can -- DRAIN until empty.
Fuel Pump Drain Reservoir (if installed) -- DRAIN until
empty.
)
)
)
1 April 1998
4-11
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
BEFORE STARTING ENGINE
1.
2.
3.
4.
5.
6.
7.
8.
Preflight Inspection and Weight and Balance Check -COMPLETE.
All Key Locking Cabin Doors -- UNLOCKED (except cargo :
configured aircraft. Cargo door may be locked if no
passengers occupy cargo section of aircraft) .
Passenger Briefing -- COMPLETE.
Cabin Doors -- LATCHED (check aft doors) .
Left Crew Door Lock Override Knob and Right Crew Door
Inside Lock -- UNLOCKED.
Parking Brake -- SET (pull control out and depress brake
pedals) .
Control Lock -- REMOVE .
Seats, Seat Belts, Shoulder Harnesses -- ADJUST and
SECURE (crew seat lock indicator pin(s) extended).
A
WARNING
Failure to properly utilize seat belts and shoulder
harnesses could result in serious or fatal Injury
in the event of an accident.
9.
10.
11.
12.
13.
14.
15.
Switches -- OFF.
Ignition Switch -- NORM .
Circuit Breakers -- CHECK IN.
Fuel Tank Selectors -- LEFT ON, RIGHT ON.
Radar (if installed) -- OFF.
Air Conditioner (if installed) -- OFF.
Bleed Air-Heat Switch -- OFF.
A
(
(
CAUTION
.(
Leaving the bleed air heat switch ON may result
in a hot start or abnormal acceleration to Idle.
16.
17.
18.
19.
20.
21.
22.
Cabin Heat Mixing Air Control-- FLT-PUSH.
Emergency Power Lever -- NORMAL.
Power Lever -- IDLE.
Propeller Control Lever -- MAX (full forward).
Fuel Condition Lever -- CUTOFF.
Rudder Lock (if installed) -- TURN and PUSH to unlock.
Fuel Shutoff -- ON (push in).
4-12
1 April 1998
I
For Training Purposes Only
\ . .
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
23.
24.
25.
)
)
(0
26.
27.
)
)
)
28.
)
Battery Switch -- ON,
Wing Flaps -- UP.
No Smoking/Seat Belt Sign Switches (if installed) -- ON as
required/desired.
Fire Detector Test Switch -- PRESS-TO-TEST.
Annunciator Panel Lamp Test Switch -- PRESS-TO-TEST
(all annunciator lamps illuminate and both Fuel Selectors Off
Warning Horns are activated).
'
Annunciator Panel Day/Night Switch -- SET.
sT ARTING ENGINE (Battery Start)
)
)
1.
2.
)
3.
Battery Switch -- ON.
Volt/Ammeter -- CHECK (24 volts minimum).
Emergency Power Lever -- NORMAL (full aft) position
(check EMERGENCY POWER LEVER annunciator OFF).
)
A CAUTION
)
Ensure that the emergency power lever Is In the
NORMAL (full aft) position or an overtemperature condition will result during engine
start.
)
1'.
),;
\,
) ¥ " -.'
)
4.
)
5.
)
)
6.
)
7,
)
)
)
)" ,
Propeller Area -- CLEAR.
Fuel Boost Switch -- ON and OBSERVE.
a.
AUX FUEL PUMP ON Annunciator -- ON.
b.
FUEL PRESS LOW Annunciator -- OFF.
c.
No fuel flow.
Starter Switch -- START and OBSERVE.
a.
IGNITION ON Annunciator -- CHECK ON.
b.
Engine Oil Pressure -- CHECK for indication.
Ng -- STABLE (12% minimum) .
.
c.
Fuel Condition Lever -- LOW IDLE and OBSERVE.
a.
Fuel Flow -- CHECK for 80 to 110 pph.
b.
ITT -- MONITOR (1090°C maximum. limited to 2
seconds) .
A CAUTION
...
)(0'/
If ITT climbs rapidly · towards 1090°C, be
prepared to return the fuel condition lever to
CUTOFF.
)
)
4-131
29 September 1998
)
J;"" ...
Troinin(1' Put'"nnc::"c (lnl"
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
A
CAUTION
Under hot OAT and/or high ground elevation
conditions, idle ITT may exceed maximum idle ITT
limitation of S8SoC. Increase Ng and/or reduce
accessory load to maintain ITT within limits.
8.
9.
10.
11.
12.
13.
14.
15.
16.
c. Ng -- 52% MINIMUM.
Starter Switch -- OFF (check STARTER ENERGIZED annunciator OFF).
Engine Instruments -- CHECK.
Generator -- CHECK GENERATOR OFF annunciator OFF
and battery charging.
Fuel Boost Switch -- NORM (check AUX FUEL PUMP ON
annunciator OFF).
Avionics No.1 and No.2 Power Switches -- ON.
Navigation Lights and Flashing Beacon (if installed) -- ON as
required.
Suction Gauge -- CHECK.
Cabin Heating, Ventilating and Defrosting Controls -- AS
DESIRED.
Radios -- AS REQUIRED.
STARTING ENGINE (Auxiliary Power Start),
(24-28 Volt, Minimum 800 Amp and Maximum 1700 Amp
Capacity)
.
(
(
(
(
(
(
(
(
(
(
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
Battery Switch -- ON.
External Power Switch -- OFF.
Volt/Ammeter -- CHECK (20 volts minimum).
Battery Switch -- OFF.
Auxiliary Power Unit -- ENGAGE; then ON.
External Power Switch -- BUS.
Volt/Ammeter -- CHECK 24 -28.5 Volts.
Battery Switch -- ON.
External Power Switch -- STARTER.
Emergency Power Lever -- NORMAL (check EMERGENCY
POWER LEVER annunciator OFF).
A
Ensure that the emergency power lever Is in the
NORMAL position .or an overtemperature
condition will result during engine start.
13 October 1999
For Training Purposes Only
(
(
(
(
(
CAUTION
4-14
(
CESSNA
MODEL 208 (675 SHP)
)
SECTION 4
NORMAL PROCEDURES
)
11 .
12.
)
)
f"
if
~\.,
Propeller -- CLEAR.
Fuel Boost Switch -- ON and OBSERVE.
a.
AUX FUEL PUMP ON Annunciator -- ON.
b.
FUEL PRESS LOW Annunciator -- OFF.
c.
No fuel flow.
)
A CAUTION
}
If the auxiliary power unit drops off the line,
Initiate engine shutdown.
)
13.
)
)
)
14.
)
)
Starter Switch -- START and OBSERVE.
a.
IGNITION ON Annunciator -- CHECK ON.
b.
Engine Oil Pressure -- CHECK for indication.
c.
Ng -- STABLE (12% minimum).
Fuel Condition Lever -- LOW IDLE and OBSERVE.
a.
Fuel Flow -- CHECK for 80 to 110 pph .
b.
In -- MONITOR (1090°C maximum, limited to 2
seconds).
)
A CAUTION
)
)(
• If ITT climbs rapidly towards 1090°C, be prepared
to return the fuel condition lever to CUTOFF.
)
• Under hot OAT and/or high ground elevation
conditions, Idle ITT may exceed maximum Idle ITT
limitation of 685°C. Increase Ng and/or reduce
accessory load to maintain ITT within limits.
)
)
15.
)
)
16.
17.
18.
19.
)
20.
)
)
)r~ "."j , ~~:
)
-;.-
c.
Ng - - 52% MINIMUM.
Starter Switch -- OFF (check STARTER ENERGIZED
annunciator OFF).
'
Engine Instruments -- CHECK.
External Power Switch -- OFF.
Auxiliary Power Unit -- OFF, then DISENGAGE.
Generator -- CHECK GENERATOR OFF annunciator OFF
and battery charging.
Fuel Boost Switch -- NORM (check AUX FUEL PUMP ON
annunciator OFF).
Avionics No.1 and No. 2 Power Switches -- ON .
Navigation Lights and Flashing Beacon (if installed) -- ON as
required .
(Continued Next Page)
)
)
)
)
4-15
13 October 1999
For Trainin Purposes Only
I
SECTION 4
NORMAL PROCEDURES
I
23.
24.
I
25.
CESSNA
MODEL 208 (675 SHP)
Suction Gauge -- CHECK.
Cabin Heating, Ventilating and Defrosting Controls -- AS
DESIRED.
Radios -- AS REQUIRED.
(
(
(
(
TAXIING
1.
(
Brakes -- CHECK.
(
NOTE
For improved brake life" propeller BETA range may be
used during taxi with minimum blade erosion up to the
point where Ng increases (against beta range spring) .
2.
(
Parking Brake -- SET.
Seats, Seat Belts, Shoulder Harnesses --CHECK SECURE.
A
10.
(
(
WARNING
Failure to properly utilize seat belts and shoulder
harnesses could result In serious or fatal Injury
In the event of an accident.
3.
4.
5.
6.
7.
8.
9.
(
Flight Instruments -- CHECK.
BEFORE TAKEOFF
. 1.
2.
(
Flight Controls -- FREE and CORRECT.
Flight Instruments -- CHECK and SET.
Fuel Boost Switch -- RECHECK NORM.
Fuel Tank Selectors -- RECHECK BOTH ON.
Fuel Quantity -- RECHECK.
Fuel Shutoff -- RECHECK FULLY ON.
Elevator, Aileron, and Rudder Trim Controls -- SET for
takeoff.
.
Power LeveJ -- 400 FT-LBS.
Suction Gauge -- CHECK.
a.
b.
Volt/Ammeter -- CHECK and return selector to BATT
position.
c.
Inertial
Separator
CHECK.
Turn
control
counterclockwise, pull to BYPASS pOSition and check
torque drop; move control back to NORMAL position
and check that original torque is regained ~
d.
Engine Instruments -- CHECK (See Section 2,
Limitations for minimum oil temperature required for
flight).
4-16
13 October 1999
For Training Purposes Only
(
(
(
(
(
(
(
(
(
(
(
(
(
)
)
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
)
)
)
11. . Overspeed Governor -- CHECK (stabilized at 1750 ±60
{ -<_..
J(",
12.
)
14.
)
13.
15.
)
)
16.
)
)
)
)
)
)
() "
)
17.
18.
19.
20.
21.
22.
23.
24.
25 .
26.
27.
28 .
RPM) (See Systems Checks) .
Power Lever -- IDLE.
Quadrant Friction tock -- ADJUST.
Standby Power (if installed) -- CHECK (See Systems
.
Checks) .
Autopilot (if installed) -- PREFLIGHT TEST (See Systems
Checks) .
(if installed)
PREFLIGHT
Known Icing System
COMPLETE (See Systems Checks) prior to any flight in
icing conditions.
PitoVStatic Heat -- ON when OAT is below 4°C (40°F) .
Ice Proteclion -- AS REQUIRED.
Avionics and Radar (if installed) -- CHECK and SET.
GPS/NAV Switch -- SET.
Strobe Lights -- AS REQUIRED.
Annunciators -- EXTINGUISHED or considered.
Wing Flaps -~ SET for takeoff (10° normal, 20° short field).
Cabin Heat Mixing Air Control -- FLT-PUSH.
Window -- CLOSE.
Brakes -- RELEASE.
Fuel Condition Lever -- HIGH IDLE.
Standby power. Switch (if installed) -- ON (Standby powerl
!NOP Annunciator -- OFF).
)
A, WARNING
)
)
)
)
)
Y' · .
When ground Icing conditions are present, a
pre-takeoff contamination check should be
conducted by the pilot In command within 5
minutes of takeOff, preferably Just prior to
taxIIng onto the active runway. Critical areas
of the airplane - such as empennage, wings,
windshield, control surfaces and engine
Inlets • should be checked to ensure they
are free of Ice, slush and snow; and that the
deice or Anti·lce fluid Is stili protecting the
airplane.
)\,.;,;,:.>.
)
4-17
13 October 1999
For Traininl! Purooses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
(
(
(
TAKEOFF
(
(
NORMAL TAKEOFF
1.
2.
3.
4.
5.
6.
(
0
Wing Flaps -- 0° to 20° (10 recommended).
Power -- SET FOR TAKEOFF (observe Takeoff ITT and Ng
limits). Refer to Section 5 for takeoff power.
Annunciators -- CHECK.
Rotate -- 70-75 KIAS.
Climb Speed -- 85-95 KIAS.
Wing Flaps -- RETRACT after reaching 90 KIAS.
SHORT FIELD TAKEOFF
1.
2.
3.
4.
5.
6.
7.
8.
3.
4.
5.
(
(
(
Wing Flaps -- 20 0 •
Brakes -- APPLY.
Power -- SET FOR TAKEOFF (observe Takeoff ITT and Ng
limits). Refer Section 5 for takeoff power.
Annunciators -- CHECK.
Brakes -- RELEASE.
Rotate -- 70 KIAS.
Climb Speed -- 82 KIAS until all obstacles are cleared.
Refer to Section 5 for speeds at reduced weights.
Wing Flaps -- RETRACT after reaching 90 KIAS.
to
TYPE /I OR TYPE IV Anti-ice FLUID TAKEOFF
1.
2.
(
(
(
(
(
(
Wing Flaps -- 00.
Power -- SET FOR TAKEOFF (observe Takeoff ITT and Ng
limits) Refer to Section 5 for takeoff limits.
Annunciators -- CHECK.
Rotate -- 89 KIAS.
Climb Speed -- 104 KIAS.
(
(
(
(
(
(
(
(
(
(
4-18
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
)
SECTION 4
NORMAL PROCEDURES
)
)
ENROUTE CLIMB
CRUISE CLIMB
{'
1.
)
2.
)
4.
3.
Ice Protection ~ - AS REQUIRED .
Pitot/Static Heat -- ON when OAT is below 4°C (40°F).
Airspeed -- 115-125 KIAS.
Propeller -- 1600-1900 RPM .
)
NOTE
)
To achieve maximum flat rated horsepower, use
of 1800 RPM.
)
)
5.
)
)
)
Torque -- SET (refer to RPM/MAX TORQUE placard for
corresponding RPM; observe Maximum Climb lIT and Ng
limits).
NOTE
Engine operations which exceed
engine life.
)
a minimum
~'
A
"-
740°C ITT may reduce
CAUTION
)
For every 10° below -30°C ambient temperature,
reduce maxiinum allowable N g by 2.2%.
)
)
MAXIMUM PERFORMANCE CLIMB
)
1.
2.
)
)
3.
)
4.
Ice Protection -- AS REQUIRED.
Pitot/Static Heat -- ON when OAT is below 4°C (40°F) .
Airspeed -- 107 KIAS at sea level to 101 KIAS at 10,000 feet
to 91 KIAS at 20,000 feet.
Propeller -- 1900 RPM.
)
)
)
t";
) "" ..
,. ~ ,
:,
)
)
)
)
13 October 1999
4-19
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
5. Torque -- 1865 FT-LBS MAXIMUM (observe . Maximum
Climb ITT and Ng limits).
(
(
NOTE
Engine operations which exceed 740°C ITT may reduce
engine life.
A
CAUTION
(
For every 10° below -30°C ambient temperature, reduce
.
maximum allowable Ng by 2.2%.
(
(
(
CRUISE
1.
2.
3.
4.
(
Ice Protection -- AS REQUIRED.
Pitot/Static Heat -- ON when OAT is below 4°C (40°F).
Propeller--1600to 1900 RPM.
Power -- SET per Cruise Power Tables (observe Maximum
Cruise ITT and Ng limits).
(
(
(
NOTE
(
Engine operations which exceed 740°C ITT may reduce
engine life.
A CAUTION
(
For every 10° below -30 o e ambient temperature,
reduce maximum allowable Ng by 2.2%.
DESCENT
1.
2.
3.
4.
5.
6.
(
.(
Ice Protection -- AS REQUIRED.
Pitot/Static Heat -- ON when OAT is below 4°C (40°F).
No Smoking/Seat Belt Sign Switches (if installed) -- AS
REQUIRED.
Altimeter -- SET.
GPS/NAV Switch -- SET.
Power -- AS REQUIRED to give desired rate of descent.
(
(
(
(
(
4-20
1 April 1998
For Training Purposes Only
)
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
)
)
BEFORE LANDING
)
l
)
)
NOTE
Refer to Landing Distance table in Section 5 for anticipated
ground roll and total distance requirements.
1.
Seats, Seat Belts, Shoulder Harnesses -- SECURE.
)
A WARNING
)
)
Failure to properly utilize seat belts and shoulder
harnesses could result in serious or fatal injury _
in the event of an accident.
)
)
)
2.
3.
)
4.
)
S.
6.
7.
)( )
Fuel Tank Selectors -- LEFT ON, RIGHT ON.
Fuel Condition Lever -- HIGH IDLE.
Propeller Control Lever -- MAX (full forward).
Radar (if installed) -- STANDBY or OFF.
Autopilot (if installed) -- OFF.
Wing Flaps -- AS DESIRED (0° to -10 0 below 175 KIAS, 10 0
to 20° below 150 KIAS, 20° to 30° below 125 KIAS) .
)
LANDING
)
NORMAL LANDING
)
)
)
)
)
1.
2.
3.
4.
S.
6.
Airspeed -- 95-110 KIAS (flaps UP).
Wing Flaps -- AS DESIRED (flaps down preferred).
Airspeed -- 75-85 KIAS (flaps FULL DOWN).
Touchdown -- MAIN WHEELS FIRST.
Power Lever -- BETA range after TOUCHDOWN.
Brakes -- AS REQUIRED.
)
)
)t .--"!
)
)
)
)
)
13 October 1999
4-21
SECTION 4
NORMAL PROCEDURES
(
CESSNA
MODEL 208 (675 S,HP)
(
.(
SHORT FIELD LANDING
(
1.
2.
3.
4.
5.
Wing Flaps -- FULL DOWN.
Airspeed -- 78 KIAS (Refer to Section 5 for speeds at ,
reduced weights) .
Power Lever -- REDUCE to IDLE after clearing obstacles.
Touchdown -- MAIN WHEELS FIRST.
Power Lever -- BETA range (lever against spring) after
TOUCHDOWN .
'
(
(
(
(
(
NOTE
(
Further reduction of landing roll will result from use of
reverse thrust (see Section 5).
6.
7.
(
(
Brakes -- APPLY HEAVILY while holding elevator control full
aft.
Wing Flaps -- RETRACT for maximum brake effectiveness
(
(
BALKED LANDING
(
1.
2.
3.
4.
Power Lever -- ADVANCE for takeoff power.
Wing Flaps -- RETRACT to 20°.
Climb Speed -- 77 KIAS until obstacles are cleared.
Wing Flaps -- RETRACT after reaching safe altitude and 90
KIAS.
(
(
(
(
(
(
(
(
(
(
(
. ..
4-22
1 April 1998
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
)
SECTION 4
NORMAL PROCEDURES
)
)
AFTER LANDING
)
)( ':
1.
2.
3.
4.
)
)
5.
)
6.
)
Wing Flaps ~- UP.
Ice Protection Equipment -- OFF.
Standby Power Switch (if installed) -- OFF.
Strobe Lights -- OFF.
Landing and Taxi Lights -- AS REQUIRED.
Fuel Condition Lever -- LOW IDLE when
runway.
A
)
)
J
)
)
J(
~
)
CAUTION
If the fuel condition lever is moved past the LOW
IDLE position and the engine N~ falls below
53%, moving the lever back to the LOW IDLE
position can cause an ITT over-temperature
condition. If the engine has started to shutdown
In this situation, allow the engine to complete Its
shutdown sequence, and proceed to do a normal
engine start using the "Starting Engine"
checklist.
)
)
clear of th.l
SHUTDOWN AND SECURING AIRPLANE
)
)
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
)
11,
)
)
)
)
)
Parking Brake -- SET.
Avionics Switches -- OFF.
Standby Power Switch (if installed) -- OFF.
Fuel Boost Switch -- OFF.
Bleed Air Heat, Ventilation Fans and Air Conditioner·- OFF.
Power Lever -- IDLE.
ITT -- STABILIZED at minimum temperature for one minute.
Propeller Control Lever -- FEATHER.
Fuel Condition Lever -- CUTOFF.
Oxygen Supply Control Lever (if installed) -- OFF.
Lighting Switches -- OFF.
)( ';
) ~~;;,..,,/
)
)
)
4-23
15 November 2000
For TntininlJ Purnoses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
(
(
(
12.
13.
14.
15.
16.
17.
18.
Battery Switch -- OFF.
Controls -- LOCK.
Fuel Tank Selectors
LEFT OFF or RIGHT OFF (turn high
wing tank off if parked on a sloping surface to prevent cross '
.
feeding).
Tie-Downs and Chocks -- AS REQUIRED.
External Covers _0 INSTALL.
Fuel Filter -- CHECK FUEL FILTER BYPASS FLAG for
proper location (flush) .
Oil Breather Drain Can -- DRAIN until empty.
(
i
_0
NOTE
(
(
(
(
(
(
Possible d~lays of subsequent flights, or even missed
flights, are' often eliminated by routinely conducting a
brief postflight inspection. Usually, a visual check of the
airplane for condition, security, leakage, and tire inflation
will alert the operator to potential problems, and is
therefore recommended.
(
(
(
(
(
SYSTEMS CHECKS
(
OVERSPEED GOVERNOR CHECK
1.
(
(
Overspeed Governor
CHECK (first flight of the day and
after maintenance).
a.
Propeller Control Lever -- MAX (full forward).
b.
Overspeed Governor Test Switch -- PRESS and
HOLD.
c.
Power Lever -- ADVANCE (propeller should stabilize at
1750 ±60 RPM).
d.
Power Lever -- IDLE.
e.
Overspeed Governor Test Switch -- RELEASE.
0-
(
(
(
(
(
(
(
(
(
(
(
(
4-24
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
)
SECTION 4
NORMAL PROCEDURES
)
)
AUTOPILOT CHECK KING KFC-150 (If Installed)
)
Refer to Section 9, Supplements, for complete ,information on the
KFC-150 check procedures.
t ·---'·:
NOTE
)
When autopilot is turned on while airplane is on the ground,
the control wheel should be held to prevent ailerons from
banging stops.
)
)
BEFORE TAKEOFF RELIABILITY TESTS
)
NOTE
)
Steps 1 thru 10 are to be performed prior to each flight.
)
)
1.
)
2.
3.
)
)
{ ,"-" ':,
"\',,-,. .'
'
)
)
Gyros -- Allow 3-4 minutes for gyros to come up to speed.
AVIONICS POWER 1 Switch -- ON.
PREFLIGHT TEST Button -- PRESS momentarily and
NOTE:
a.
All annunciator lights on (TRIM annunciator flashing).
b.
All legends and digits are displayed on the KAS-297B
Vertical Speed and Altitude Selector (Optional).
c.
After approximately 5 seconds, all' annunciator lights
off except AP, which will flash approximately 12 times
and then remain off.
NOTE
)
)
)
)
)
)
)
)( " ' ,
),~i
)
If trim, warning light stays on, the autotrim did not pass the
preflight test. The autopilot circuit breaker should be pulled
(the autopilot and manual electric trim will be inoperative).
4.
Manual Electric Trim -- TEST as follows:
a.
Actuate left side, of split switch unit to the fore and aft
positions. The trim wheel should not move on its own.
Rotate the trim wheel manually against the engaged
c.lutch to check the pilot's trim overpower capability.
b.
Actuate right side of split switch unit to the fore and aft
positions. The trim wheel should not move on its own
and normal trim wheel force is ' required to move it
manually.
c.
Press the AlP DISCrrHIM INTER switch down and
hold. Manual electric trim should not operate either
nose up or nose down.
)
)
)
4-25
1 April 1998
For Training Purposes Only
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
5. Flight Director -- ENGAGE by pressing FD or CWS button.
6. Autopilot -- ENGAGE by pressing AP ENG button.
7. Yaw Damper (Optional) -- ENGAGE by pressing YAW
DAMP switch button.
.
8. Flight Controls -- MOVE fore , aft, left, and right to verify that
the autopilot/yaw damper can be overpowered.
9. AlP DISCITRIM INTER Switch -- PRESS. Verify that the
autopilot and yaw damper (optional) disconnects and all
flight director modes are canceled.
10. TRIM -- SET to takeoff position.
(
(
(
(
AUTOPILOT CHECK BENDIX/KING KFC-22S
.
4-47
1 April 1998
For Traininl! Purooses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
Actual touchdown should be made with idle power and on .the main
wheels first, just slightly above stall speed. The nose wheel is then
gently lowered to the runway, the power lever repositioned to the
BETA range, and brakes applied as required. When clear of the ,
runway, reposition the fuel condition lever from HIGH IDLE to LOW ·
IDLE. This will reduce cabin and exterior noise levels as well as
reduce braking requirements when the power lever is positioned
ahead of the REVERSE range. Landings on rough or soft fields are
accomplished in a similar manner except that the nose wheel is
lowered to the runway at a lower speed to prevent excessive nose
gear loads.
(
(
(
(
(
NOTE
The use of BETA range after touchdown is recommended . to
reduce brake wear. Generally, the power lever can be
moved aft of the IDLE gate until it contacts a spring in the
control quadrant without substantial propeller erosion from
loose debris on the runway or taxiway.
SHORT FIELD LANDING
(
(
(
(
For short field landings, make a power approach at ·78 KIAS with
the propeller control lever at MAX (full forward) and with full flaps.
After all approach obstacles are cleared, reduce power to idle.
Maintain 78 KIAS approach speed by lowering the nose of the
airplane. Touchdown should be made with the power lever at IDLE,
and on the main wheels first. Immediatelyatter touchdown, lower
the nose gear, reposition the power lever against the spring in the
BETA range, and apply heavy braking as required.
(
(
(
For maximum brake effectiveness after all three wheels are on the
ground, hold full nose up elevator and apply maximum possible
brake pressure without sliding the tires.
A CAUTION
(
When the small high-pressure tires are Installed
and when flying at light weights, it Is possible to
slide the tires with only moderate pressure on
the brake pedals. Care must be exercised to
prevent overbraklng.
4-48
1 April 1998
For Training Purposes Only
(
(
,(
(
CESSNA
MODEL 208 (675 SHP)
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SECTION 4
NORMAL PROCEDURES
The landing performance in Section 5 is based on the above
procedure. A reduction in ground roll of approximately 10% will I
result from the use of reverse thrust (power lever full aft to provide
increased power from the gas generator and a reverse thrust
propeller blade angle) .
A CAUTION
(
(
To minimize propeller blade erosion or possible
propeller blade damage, reverse thrust should
be used only when necessary to shorten the
ground roll.
Bringing the propeller out of
reverse
before
decelerating
through
approximately 25 knots will minimize propeller
erosion.
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CROSSWIND LANDING
(
For crosswind approaches, either the wing-low, crab or combination
method may be used. A flap setting between 10° and 30° is
recommended. Use a minimum flap setting for the field length.
After touchdown, lower the nose wheel and maintain control. A
straight course is maintained with the steerable nose wheel,
ailerons, and occasional braking if necessary.
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BALKED LANDING
(
In a balked landing (go-around) climb, the wing flap setting should
be reduced to 20° after takeoff power is applied. After all obstacles
are cleared and a safe altitude and airspeed are obtained, the wing
flaps should be retracted.
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AFTER ·SHUTDOWN
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If dusty conditions exist or if the last flight of the day has been
completed, install engine . inlet covers to protect the engine from
debris. The covers may be installed after the engine has cooled
down (ITT indicator showing "off scale" temperature). Secure the
propeller to prevent windmilling since no oil pressure is available for
engine lubrication when the engine is not running.
4-49
7 September 2001
For Trainine Purposes Only
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
(
(
COLD WEATHER OPERATION
Special cansideratian; shauld be given ta the aperatian of the "
airplane fuel system during the winter seasan .or priar ta any flight in
cald temperatures. Proper preflight draining .of the fuel system is
especially impartant and will eliminate any free water accumulatian.
The use .of an additive is required far Anti-ice pratectian. Refer ta
Section 8 for informatianan the proper use of additives.
Cold weather often causes conditions which require special care
priar to flight. Operating the elevatar and aileron trim tabs through
their full travel in both directians will assure smaoth operation by
reducing any stiffness in these systems caused by the cold weather
effects on system lubrication. Even small accumulations .of frost,
ice, .or snaw must be removed, particularly from wing, tail and all
control surfaces to assure satisfactory flight perfarmance and
handling. Also, control surfaces must be free of any internal
accumulations of ice or snow.
The use of an
engine and the
the oil trapped
temperatures.
external pre-heater reduces wear and abuse to the
electrical system. Pre-heat will lower the viscosity of ~
in the oil coaler, prior to starting iii extremely cald '
.
Use .of an APU is recommended when ambient temperatures are
belaw OaF (-18°C). , Assure that oil temperature is in the green arc
(1 aoc to 99°C) priar to takeoff.
If snow or slush covers the takeoff surface, allowance must be made
far takeoff distances which will be increasingly extended as the
snow or slush depth increases. The depth and consistency of this
cover can, in .fact, prevent takeoff in many instances.
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4-50
1 April 1998
ForTraining Purposes Only
CESSNA
MODEL 208 (675SHP)
SECTION 4
NORMAL PROCEDURES
HIGH ALTITUDE OPERATION
(
/-- 1
\
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At altitudes above 20,000 feet, a compressor surge may be
experienced if engine power is very rapidly re-applied immediately
after a power reduction. This characteristic is not detrimental to the
engine and can be eliminated completely by turning on cabin bleed
heat to at least the one-half setting.
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ENGINE COMPRESSOR STALLS
An engine compressor stall may be noted by a single or multiple
loud "popping" noise from the engine compartment. This situation
may be resolved by reducing the engine power to a point where the
"popping" discontinues, and slowly advancing the throttle to the
necessary setting for continued flight. The use of cabin bleed heat
may also help eliminate engine compressor stalls if this situation is
encountered.
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NOISE CHARACTERISTICS
(
Increased emphasis on improving the quality of our environment
requires renewed effort on the part of all pilots to minimize the
effect of airplane noise on the public.
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We, as pilots, can demonstrate our concern for environmental
improvement, by application of the following suggested procedures,
and thereby tend to build public support for aviation:
1.
2.
Pilots operating aircraft under VFR over outdoor assemblies
of persons, recreational and park areas, and other noisesensitive areas should make every effort to fly not less than
2000 feet above the surface, weather permitting, even
though flight at a lower level may be consistent with the
provisions of government regulations.
During departure from or approach to an airport, climb after
takeoff and descent for landing should be made so as to
avoid prolonged flight at low altitude near noise-sensitive
areas.
4-511
29 September 1998
For Training Purposes Only
SECTION 4
NORMAL PROCEDURES
CESSNA
MODEL 208 (675 SHP)
(
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NOTE
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The above recommended procedures do not apply where
they would conflict with Air Traffic Control clearances or
instructions, or where, in the pilot's judgment, an altitude of
less than 2000 feet is necessary for him to adequately
exercise his duty to see and avoid other aircraft.
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The certificated noise level for the Model 208 at 8000 pounds
Imaximum weight is 79.0 d8(A). These measurements were obtained
using a takeoff profile. No determination has been made by the
IFederal Aviation Administration that the nOise levels of this airplane
are or should be acceptable or unacceptable for operation at, into,
or out of, any airport.
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4·52
15 November 2000
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
(
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SECTION 5
PERFORMANCE
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SECTION 5
PERFORMANCE
TABLE OF CONTENTS
Page
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Introduction
. . .. . . ... . . .. . . . .. . . . . . . .. . . .. ... . . .
Use of Performance Charts ... . ......................
Sample Problem .................... . .............
Takeoff
. ......... .......... .......... ... ...
Cruise
.......... .......... ............. ...
Fuel Required ........................ . .......
Landing
.......... '.' .. . . . . . . . . . . . . . . . . . . . . . .
Figure 5-1
Airspeed Calibration - Normal Static Source ...
Airspeed Calibration - Alternate Static Source
Figure 5-2
Altimeter Correction - Alternate Static Source ..
Figure 5-3
Pressure Conversion - Inches of Mercury
to Millibars ..........................
Figure 5-4 Temperature Conversion Chart ............
ISA Conversion And Operating
Figure 5-5
Temperature Limits . ........ . .. " . . . .
Stall Speeds ..........................
Figure 5·6
Figure 5-7
Wind Components ................... . ..
Engine Torque For Takeoff .......... . . . . .
Figure 5-8
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5-15
5-16
5-17
5-18
5-19
5-20
AIRPLANES WITHOUT CARGO POD
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5-5
5-6
5-6
5-7
5-8
5-8
5-11
5-12
5-13
5-14
Figure
Figure
Figure
Figure
. Figure
Figure
Figure
Figure
Figure
5-9
Takeoff Distance - Short Field
............ .
5-10 Takeoff Distance - Flaps Up .............. .
Rate Of Climb - Takeoff Flap Setting ....... .
.... . . .
Climb Gradient - Takeoff Flap Setting
Maximum Rate Of Climb - Flaps Up ........ .
Maximum Climb Gradient - Flaps Up .... . .. .
Cruise Climb - Flaps Up - 120 KIAS ........ .
.......... .
Rate Of Climb - Balked Landing
Time, Fuel, And Distance To Climb
-Maximum Rate Of Climb
............. .
Figure 5-18 Time, Fuel, Distance To Climb
-Cruise Climb - 120 KIAS ............. .
5-11
5-12
5-13
5-14
5-15
5-16
5-17
5-21
5-22
5-23
5-24
5-25
5-261
5-27
5-28
5-29
5-30
5·1
Revision 6
For Traininl! Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
(
TABLE OF CONTENTS (Continued)
Page
Figure 5-19 . Cruise Performance - Notes . ....... . ... .. .
Cruise Performance - 2000 Feet . .. .. ...... ... . . . .
Cruise Performance - 4000 Feet . .. . .. . .... . . . .. . .
Cruise Performance - 6000 Feet . ........ .. . . . .. . .
Cruise Performance - 8000 Feet . .. . ... ........ .. .
Cruise Performance - 10,000 Feet .... .. . . .. . .. .. .
Cruise Performance - 12,000 Feet .. . .... .. . . . . . . .
Cruise Performance - 14,000 Feet . .. .. .. . .. .. . . . .
Cruise Performance - 16,000 Feet .. . ....... .... . . .
Cruise Performance - 18,000 Feet . .... . .... .. . . . .
Cruise Performance - 20,000 Feet ............... .
Cruise Performance - 22~000 Feet . . .. .. . . . . .. . .. .
Cruise Performance - 24,000 Feet ........... . ... .
Figure 5-20 Fuel And Time Required
- Maximum Cruise Power ...... . . . .. . . .
Figure 5~21 Fuel and Time Required
- Maximum Range Power .. . . .. .... . .. .
Figure 5-22 R~nge Profile ... . .. . . .. .. . . . . .. ....... .
Figure 5-23 Endurance Profile ..... . ........ .. ... .. .
Figure 5-24 Time, Fuel, And Distance To Descend . ..... .
Figure 5-25 Landing Distance - 7800 Lbs .. .. ....... . . .
Landing Distance - 7300/6800 Lbs
. ... . ... .
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5-31
5-32
5-33
5-34
5-35
5-36
5-37
5-38
5-39
5-40
5-41
5-42
5-43
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5-44
5-46 '
5-48 :
5-49
5-50
5-51
5-52
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AIRPLANES WITH CARGO POD INSTALLED
Figure 5-26
Figure 5-27
Figure 5-28
Figure 5-29
Figure 5-30
Figure 5-31
Figure 5-32
Figure 5-33
Figure 5-34
Takeoff Distance- Short Field .......... .. .
Takeoff Distance - Flaps UP .... . .. . .. . . . .
Rate Of Climb - Takeoff FlapSetting ..... . . .
Climb Gradient - Takeoff Flap Setting
.. . . .. .
Max!mum R~te Of CIi'!1b - Flaps Up ... • .....
Ma~lmulT! Climb Gradient - Faps Up
..... .. .
CrUise Climb - Flaps Up - 120 KIAS . . .. . ... .
..... , .... .
Rate Of Climb - Balked Landing
Time, Fuel, Distance To ClimbMaximum Rate Of Climb
............. .
Figure 5-35 Time, Fuel, Distance To Climb ... . .... . .... .
Cruise Climb - 120KIAS
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5-53
5-54
5-55
5-56
5-57
5-58
5-59
5-60
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5-61
5-62
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5-2
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
I
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SECTION 5
PERFORMANCE
(
TAB LE OF CONTENTS
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(Continued)
Page
Figure 5-36 Cruise Performance - Notes ............. . .
Cruise Performance - 2000 Feet . . , ........... ,...
Cruise Performance - 4000 Feet ,. , .. . , .. . ,.. . . ...
Cruise Performance - 6000 Feet . . . . . . .... ..... ...
Cruise Performance - 8000 Feet . . , ... . .. , ... ,....
Cruise Performance - 10,000 Feet .... ,...... . . . . .
Cruise Performance - 12,000 Feet .... ,... . ... . . . .
Cruise Performance - 14,000 Feet . . . . . . . . . . . . . . . .
Cruise Performance - 16,000 Feet ..... . . . . . . . . . . .
Cruise Performance - 18,000 Feet . .. ........ . ....
Cruise Performance - 20,000 Feet . . . . . . . . . . . . . . . .
Cruise Performance - 22,000 Feet . . . . . . . . . . . . . . . .
Cruise Performance - 24,000 Feet ... . .... ... . . . . .
Figure 5-37 Fuel And Time Required
- Maximum Cruise Power ., . .. ..... . , ..
Figure 5-38 Fuel and Time Required
- Maximum Range Power ......... , ... .
Figure 5-39 Range Profile . . . ....... ..... ,..........
Figure 5-40 Endurance Profile . . ...... .. . ,..........
Figure 5-41 Time, Fuel, And Distance To Descend ... _ . "
Figure 5-42 Landing Distance - 7800 Lbs ..... . .. .. ....
Landing Distance - 7300/6800 Lbs
... .. _ . "
5-63
5-64
5-65
5-66
5-67
5-68
5,69
5-70
5-71
5-72
5-73
5-74
5-75
5-76
5-78
5-80
5-81
5-82
5-83
5-84
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5-3/5-4
1 April 1998
For Traininl! Purposes Only
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For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 5
PERFORMANCE
(
INTRODUCTION
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Performance data charts on the following pages are presented so
that you may know what to expect from the airplane under various
conditions, and also, to facilitate the planning of flights in detail and
with reasonable accuracy. The data in the charts has been
computed from actual flight tests using average piloting techniques
and an airplane and engine in good condition .
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A, WARNING
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To ensure 'that performance In this section can
be duplicated, the airplane and engine must be
maintained . in good condition. Pilot proficiency
and proper preflight planning using data
necessary for all flight phases Is also required to
assure expected performance with ample
margins of safety.
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It should be noted that the performance information presented in the
range and endurance profile charts allows for 45 minutes reserve
fuel at the specified cruise power and altitude. Some indeterminate
variables such as engine and propeller condition, .and air turbulence
may account for varrations of 10 or more in range and endurance.
Therefore, it is important to utilize all available information to
estimate the fuel required for the particular flight.
Notes have been provided on various graphs and ' tables to
approximate performance with the inertial separator in BYPASS
and/or cabin heat on~ The effect will vary, depending upon airspeed,
temperature, and altitude At lower altitudes, where operation on the
torque limit is possible, the effect of the inertial separator will be
less, depending upon how much power can be recovered after the
separator vanes have been extended.
In some cases, performance charts in this section include data for
temperatures which are outside of the operating limits (Figure 5-5).
This data has been included to aid in interpolation.
5-5
1 April 199a
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
USE OF PERFORMANCE CHARTS
Performance data is presented in tabular or graphical form to '
illustrate the effect of different variables. Sufficiently detailed '
information is provided in the tables so that conservative values can
be selected and used to determine the particular performance figure
with reasonable accuracy.
SAMPLE PROBLEM
(
The following sampfe flight problem utilizes information from the
various charts to determine the predicted performance data for a
typical flight of an airplane not equipped with a cargo pod. A similar
calculation can be made for an airplane ' with a cargo pod using
charts identified as appropriate for this configuration. The following
information is known:
(
(
AIRPLANE CONFIGURATION (WITHOUT CARGO POD)
Takeoff weight:
Usable fuel:
'
7850 Pounds
2224 Pounds
(
TAKEOFF CONDITIONS
Field pressure altitude:
Temperature:
Wind component:
Field length:
(
3500 Feet
16°C (standard + 8°C)
12 Knot Headwind
4000 Feet
(
(
(
CRUISE CONDITIONS
Total distance:
Pressure altitude:
Temperature:
Expected wind enroute:
(
650 Nautical Miles
11 ,500 Feet .
8°C
10 Knot Headwind
(
(
LANDING CONDITIONS
Field pressure altitude:
Tem~erature :
Fiel length:
(
1500 Feet
25°C
3000 Feet
5-6
1 April 1998
For Training Purposes Only
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CESSNA
MODEL 208
SECTION 5
PERFORMANCE
(675 SHP)
TAKEOFF
The Takeoff Distance chart, Figure 5-9, should be consulted,
keeping in mind that the . distances shown are based on the short
field technique . Conservative distances can be established by
reading the chart at the next higher value of weight, altitude and
temperature. For example, in this particular sample problem, the
takeoff distance information presented for a weight of
8000
pounds, pressure altitude of 4000 feet and a temperature of 20°C
should be used and results in the following:
1530 Feet
2655 Feet
Ground roll:
Total distance to clear a 50-foot obstacle:
These distances are well within the available takeoff field length.
However, a correction for the effect of wind may be made based on
Note 2 of the takeoff chart. The correction fora 12 knot headwind
is:
12 Knots
11 Knots
X 10% = 11 % Decrease
This results in the following distances, corrected for wind:
Ground roll, zero wind:
Decrease in ground roll
(1530 feet X 11%):
1530 Feet
Corrected ground roll:
1362 Feet
I
168 Feet
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Total distance to clear a
50-foot obstacle, zero wind:
Decrease in total distance
(2655 feet X 11 %):
Corrected total distance
to clear a 50-foot obstacle:
2655 Feet
292 Feet
I
2363 Feet
The Engine Torque For Takeoff chart, Figure 5-8, should be
consulted for takeoff power setting. For the above ambient
conditions, the power setting is:
1865 Ft-Lbs
Takeoff torque :
5-7
7 September 2001
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
CRUISE
The cruising altitude should be selected based on a consideration of
trip length, winds aloft, and the airplane's performance. A cruising .
altitude and the expected wind enroute have been given for this
sample problem. However, the power setting selection for cruise
must be determined based on several considerations. These include
the cruise performance characteristics presented in Figure 5-19, the
Fuel And Time Required charts presented in Figures 5-20 and 5-21,
the Range Profile chart presented in Figure 5-22, and the
Endurance Profile chart presented in Figure 5-23.
!.
The Range Profile chart, Figure 5-22, shows range at maximum
cruise power and also . at maximum range power. For this sample
problem, maximum cruise power and 1900 RPM will be used.
The Cruise Performance chart for 12,000 feet pressure altitude is
entered using 10°C temperature. These values most nearly
correspond to the planned altitude and expected temperature
conditions. The torque setting for maximum cruise power is 1291 FtLbs torque at 1900 RPM which results in the following: .
True airspeed:
Cruise fuel flow:
(
(
173 Knots
306 PPH
FUEL REQUIRED
The total fuel requirement for the flight may be estimated using the
performance information in Figures 5-18, 5-19 and 5-24 or in
Figures 5-.20 and 5-21 . The longer detailed method will be used for
this sample problem, but the use of Figures 5-20 and 5-21 will
provide the desired information for most flight planning purposes.
Assuming a maximum climb, Figure 5-18 may be used to determine
the time, fuel and distance to climb by reading values for a weight
of 8000 pounds and a temperature 20°C above standard. The
difference between the values shown in the table for 4000 feet and
12,000 feet results in the following:
Time :
Fuel:
Distance :
10
60
20
Minutes
Pounds
Nautical Miles
1 April 1998
5-8
For Training Purposes Only
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CESSNA
MODEL 20a (675 SHP)
(
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SECTION 5
PERFORMANCE
(
Similarly, Figure 5-24 shows that a descent from 12,000 feet to sea
level results in the following:
(
(
Time
15 Minutes
(
Fuel
65 Pounds
(
Distance
43 Nautical Miles
(
(
The distances shown on the climb and descent charts are for zero
wind. A correction for the effect of wind may be made as follows:
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(
(
Distance during climb with no wind
20
Decrease in distance due to wind
(10/60 X 10 knot headwind)
02
Corrected distance to climb:
18 n.m.
(
Similarly, the distance for descent may be corrected for the effect
of wind and results in 40 nautical miles
(
(
The cruise distance is then determined by subtracting the distance
during climb and distance during descent.
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Total distance
650
(
Distance during climb and descent
(
Cruise distance
(
-58
592 Nautical Miles
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1 April 199a
For Traininl! Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
(
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With an expected 10 knot headwind, the ground speed for cruise is
predicted to be:
173
(
:1Q
(
163 Knots
(
Therefore, the time required for the cruise portion of the trip is:
590 Nautical Miles
163 Knots
= 3.6 Hours
The fuel ,required for cruise is:
3.6 hours X 306 pounds/hour = 1102 Pounds
A 45-minute reserve requires:
45
60 X 306 pounds/hour = 230 Pounds
The total estimated fuel required is as follows:
Engine start, taxi, and takeoff
35
Climb
60
Cruise
1102
Descent
65
Reserve
230
Total fuel required (pounds)
(
1492
(
Once the flight is underway, ground speed checks will provide ' a
more accurate basis for estimating the time enroute and the
corresponding fuel required to complete the trip with ample reserve.
1 Apri11998
5-10
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
(
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LANDING
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SECTION 5
PERFORMANCE
(~ .
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A procedure similar to takeoff should be used for estimating the
landing distance at the destination airport. The estimated landing
weight is as follows :
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Takeoff weight
7850
(
Fuel required for climb,
cruise, and descent
1262
Landing weight
6588 Pounds
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Figure 5-25 presents landing distance information for the short field
technique. The landing distances for a weight of 6800 pounds and
corresponding to 2000 feet pressure altitude and a temperature of
30°C should be used and are as follows:
.
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Ground roll
700 Feet
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":"-.-'
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Total distance to clear a 50-foot obstacle
1585 Feet
A correction for the effect of wind may be made based on Note 2 of
the landing chart using the same procedure as outlined for takeoff.
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5-11
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
AIRSPEED CALIBRATION
NORMAL STATIC SOURCE
CONDITIONS:
8000 Pounds
Power required for level flight or maximum rated RPM dive.
NOT,E
Where airspeed values have been replaced by dashes, the
airspeed would be either below stall speed at maximum
weight or above the maximum approved operating limit
speed for the condition.
FLAPS
UP
KIAS
KCAS
-----
80
79
100
98
120
118
140
139
160 175
160 . 175
---
. (
- --
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.
FLAPS
10°
KIAS 75
KCAS 75
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80
79
100
98
120
118
140
139
160
160
175
175
70
70
80
79
90
89
100
99
110
109
130
129
(
FLAPS
20°
KIAS 65
KCAS 66
150
150
(
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FLAPS
30°
KIAS 65
KCAS 65
(
70
69
80
79
90
89
100
99
110
110
125
125
---
-- -
Figure 5-1. Airspeed Calibration (Sheet 1 of 2)
5-12
1 April
For Training Purpos~s Only
1998
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CESSNA
MODEL 208 (675 SHP)
(
SECTION 5
PERFORMANCE
(
AIRSPEED CALIBRATION
(
ALTERNATE STATIC SOURCE
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(' .'
VENTS CLOSED
(
FLAPS UP
(
NORMAlKIAS
ALTERNATE KIAS
(
80
80
100
101
120
123
140
144
160
166
175
183
- -.
. -.
70
73
80
81
100
10
120
124
140
146
160
167
175
183
60
61
70
71
80
82
100
103
120
125
140
146
150
156
60
63
70
71
80
82
90
93
100
104
110
115
125
130
FLAPS 10°
(
NORMALKIAS
(
ALTERNATE KIAS
(
FLAPS 20°
(
NORMALKIAS
ALTERNATE KIAS
(
FLAPS 30°
(
NORMAlKIAS
ALTERNATE KIAS
(
(
VENTS OPEN
(
(
FLAPS UP
(
NORMAlKIAS
ALTERNATE KIAS
(
100
95
120
117
140
139
160
161
175
177
.. -
70
69
80
78
100
100
120
121
140
143
160
164
175
180
60
58
70
69
80
79
100
100
120
122
140
144
150
154
60
60
70
69
80
80
90
91
100
102
110
113
125
128
---
FLAPS 10°
NORMAlKIAS
ALTERNATE KIAS
(
(
FLAPS 20°
(
NORMALKIAS
ALTERNATE KIAS
(
FLAPS 30°
(
NORMAlKIAS
ALTERNATE KIAS
(
(
80
75
C,:.,,'
Figure 5-1. Airspeed Calibration (Sheet 2 of 2)
5-13
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
ALTIMETER CORRECTION
ALTERNATE STATIC SOURCE
NOTES:
1. Add correction to desired aliilUde to obtain indicated altitude to fly.
2 . Where altimeter correction values have been replaced bV dashes. the correction is unnecessary be!:ause of conditions in which airspeed is not -attainable in level flight.
VENTS -CLOSED
CORRE
CONDITION
o BE AO[ ED - FEE
KIAS
ION
80
90
100
120
14
160
175
0
25
35
45
65
50
70
95
135
75
105
145
205
100
135
185
265
115
155
-
FLAPS UP
Sea Level
10,000 Ft.
20,000 Ft.
5
5
30,000 Ft.
5
15
20
25
35
FLAPS 100
Sea Level
10,000 Ft.
5
5
20
25
30
40
55
80
85
110
105
140
110
150
FLAPS 30°
Sea Level
10,000 Ft.
20
30
30
40
40
55
60
80
-
-
-
-
-
VENTS OPEN
CORRECTI IN
CONDITION
FLAPS UP
Sea Level
10,000 Ft.
20,000 Ft.
30,000 Ft.
FLAPS 100
Sea Level
10,000 Ft.
FLAPS 300
Sea Level
10.000 Ft.
BE ADDEI
-FEET
KIAS
80
90
100
120
14C
160
-25
- 25
-50
-75
-25
- 25
- 45
- 65
-20
- 25
-40
-55
-10
-15
-20
-30
5
5
10
20
25
35
50
-
-10
-15
-5
a
10
10
30
40
50
65
70
90
105
5
10
15
20
25
30
40
50
5
-
-
-
175
30
45
-
BO
-{
Figure 5-2. Altimeter Correction
1 April 1998
5-14
For Training Purposes Only
(
(
CESSNA
SECTION 5
PERFORMANCE
MODEL 208 (675 SHP)
(
(
PRESSURE CONVERSION
(
(
(
1050
(
1040
(
1030
(
(J")
1020
(
a::
(
:::::i 1010
(
:r
==
(
(
(
cC
CD
I
1000
UJ
cr
::::>
(J")
(J")
990
UJ
a::
c...
980
(
970
(
960
(
950
28.00
26.50
29;00
29 . 50
30 . 00
30 . 50
31.00
PRESSURE - INCHES OF MERCURY
(
(
(
(
(
EXAMPLE :
PRESSURE - 29 . 55 INCHES OF MERCURY .
PRESSURE - 1000 . 6 MILLIBARS .
(
(
(
(
5985T7002
Figure 5-3. Pressure Conversion - Inches of Mercury to Millibars
5-15
1 April 1998
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
TEMPERATURE CONVERSION CHART
100
80
~
w
:r:
z
w
0::
:r:
60
ex:
I.J..
U1
40
w
W
0::
a
w
0
20
o
-20
-4 0
-40
- 20
0
20
40
60
DEGREES - CELSIUS
2685T1050
Figure 5-4. Temperature Conversion Chart
5-16
1 April 1998
For Training Purposes Only
CESSNA
SECTION 5
MODEL 208 (675 SHP)
PERFORMANCE
ISA CONVERSION
AND OPERATING TEMPERATURE LIMITS
(
(
/" -
(
f
A. CAUTION
'(
(
Do not Operate In shaded area of chart.
(
(
30
25
(
(
Ii:
o
(
g
.
20 .
(
(
(
(
(
(
UJ
0
:J
t:: 15
~
~
UJ
a::
:J
Ul
Ul
~ 10
Il.
(
5
0
-70
·60
-50
-40
-30
-20
-10
0
10
OUTSIDE AIR TEMPERATURE
20
30
40
_·c
2685T1010
Figure 5-5. ISA Conversion and Operating Temperature Limits
5-17
1 April 1998
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
STALL SPEEDS AT 8000 POUNDS
Conditions:
Power Lever - Idle
Fuel Condition Lever- High Idle
MOST REARWARD CENTER OF GRAVITY
ANGLE OF BANK
FLAP
SETTING
KIAS KCAS KIAS
UP
10°
20
30
0
63
60
56
50
45°
30°
0°
75
66
62
61
60°
KCAS KIAS KCAS KIAS
68
64
60
54
81
71
67
66
75
71
67
59
89
78
74
73
KCAS
106
93
88
86
89
85
79
71
MOST FORWARD CENTER OF GRAVITY
ANGLE OF BANK
FLAP
SETTING
UP
10
20
30°
0
0
0
KIAS KCAS KIAS
63
75
68
61
67
66
57
63
61
50
45
300
61
54
KCAS
81
72
68
66
60 0
0
KIAS KCAS KIAS KCAS
75
73
68
S9
89
80
75
73
89
86
81
71
106
95
89
86
NOTES:
1.
Altitude loss during a stall recovery may be as much as 300 feet
from awings-Ievel stall and even greater from a turning stall.
2.
KIAS values are approximate .
Figure 5-6 _ Stall Speeds
5-18
1 April 1998
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
(
WIND COMPONENTS
(
NOTE: Maximum demonstrated crosswind velocity is 20 knots
(not a limitation).
(
(
(
(
rn
t-
oZ
~
,
>(
(
~
Z
~,
30
,,, " ,."'"'
:~-l--
::::l
a:
~
[I
'
i
:.
i;
...J
(
(
(
W
...J
...J
~
0:
I-
Z
~ ,"'0
W
(
Z
0
c..
:E
(
(
I· . • .
10
0
u
0
z
'.i'
?;
. ._~ : i
(
0
,¥
-'"
-10
0
~O
! '
: i
:~
(
!' ,
' !
'1'.
~ 1500
1;;
~
'5k /'/
UJ
,., 1.<::
C>
If"
/0
,
/0
{.>
°0
I-
i:::
~
rY?
A'/ ,
1500
C:l
~
~
1400
130~.m
-20
- 10
0
10
20
30
40
OUTS IDE AIR TEMPERATURE - 'C
50
60
2685T1011
Figure 5-8. Engine Torque for Takeoff
5-20
1 Apri l 1998
For Training Purposes Only
CESSNA
SECTION 5
MODEL 208 (675 SHP)
PERFORMANCE
WITHOUT CARGO POD
TAKEOFF DISTANCE
(
(
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
SHORT FIELD
tI'"-- .
i,
NOTES:
CONDITIONS:
1. USE SHORT FIELD TECHNIQUES AS SPECIFIED IN SECTION 4 .
10% FOR EACH 11 KNOTS HEADWIND.
FOR
OPERATION WITH TAILWINDS UP TO 10 KNOTS. INCREASE DISTANCES BY 10%
FOR EACH 2 KNOTS.
3. FOR OPERATION ON A DRY. GRASS RUNWAY. INCREASE DISTANCES BY 15%
DFTHE "GROUND ROLL" FIGURE.
4. WITH TAKEOFF POWER SET BELOW THE TORQUE LIMIT 11865 FHBS).
INCREASE DISTANCE (BOTH GROUND ROLL AND TOTAL DISTANCE) BY 3% FOR
INERTIAL SEPARATOR IN BYPASS AND INCREASE GROUND ROLL 5% AND
TOTAL DISTANCES 9% FOR CABIN HEAT ON.
5. WHERE DISTANCE VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED .•
THOSE DISTANCES WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY
EXCEEDS THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION
PURPOSES ONLY.
6. FOR OPERATIONS ABOVE 40°C AND BELOW THE TEMPERATURE OPERATING
LIMITATIONS MULTIPLY TAKEOFF DISTANCES AT 40"C BY 1 2
FLAPS 20 DEGREES
19.00 RPM
INERTIAL SEPARATOR · NORMAL
CABIN HEAT· OFF
TORQUE SET PER FIGURE 5·8
PAVED. LEVEL. DRY RUNWAY
ZERO W IND
(
(
2. DECREASE DISTANCES
(
(
(
I
(
W~
(
.E
,AKEOFF
SPEED
K AS
FF
(
8
o
o
(
PRESS
-10'e
Al T GRD TOTAL
n ROLL TO
0 F
FT 50 FT
82
SL 1000 1790
I !~~~I 10~~ !~~~
I 7110rl '17~ 7111111
3000 1195 2115
4000 127~ ;2240
I ~nnrl nss
"7S
6000 1445 2520
1275
1355
1445
1540
2240
2375
2515
2675
20'C
30'C
40'C
GRO TOTAL, GRD ITOTAl GRD TOTAL
ROLL TO
ROLL TO
ROLL TO
FI 50 FT fl 50 fT
fl 50 f I
FT 50 FI
1125 2000 1195 2110 1260 2220 1330 2335
1195 ~!~~ 1270 2230 1340 2350 1430 2505
Inn 77~~ !l!in Hhn 141'i ?lIqo! 1555 2725
1355 2370 1435 2500 1520 2640 1690 2975
14~0 2510 1530 2655 1625 2815 1840 3250
1535 2665 1630 1820 . 1770 30BO I ;1nn~ ~;;~5
1640 2835 1740 3000 1950 3420 2215 3970
900( 1760
1880
3230
2090
JT AT
72
o
(
I
(
7
5
(
70
m~ ~~~g I ~~~~ ~~~~ ~~~~ ~~~~ ~~~~ ~m. m~ ~~~~ ==== :==:
2000 2280
SL
855
80
I
!~~~
!~~g ~~~g I !~~~ ;~~~ I ~~~~ ~;~~
1150
2005
1220
2115
1305
2Z~5
2390
BH~
1480
ZHD II~u~
1085
mg
2130
1310
mg
~~~~ ~~~~ ~~~~ I ~~~g ~~~g I ~m ~:~~ I ~m ~i~~ ==== ===:
o
o
(
SL
1930
7Z5
2010
1!~~
l23n
1~~~ ~!~~ ~~~~ ~~~~ ~~~~ ~~?5
2500
2720
1390
3300
Z97f
I
2560
3315
1285
1595
2165
770
1770
27Z0
3765
1360
2435
915
3045
4310
1430
~~; t~~~
~!~ ;~~g
~~~ ~~~~
300
865
920
975
1510
m }~~~
6000 1040
1655
1435
1560
z:.901695
1865 1870
~m m~ ~~~~ }~~~ m~. }~~g ~m I m~ ~~~~ ~~:: ~~~~
!~~
~~g
2530
2230
.--1975
1795
1895
9000 1495
1200
---1135
----
!g~~
1290
1585
1880
----
1895
2010
2130
2260
77
3790
1075
4885
;~~~
i
6205
1790
2680
;~~~ ~g~ !~~~ ,~~~
;~~~:
3295
1015
4185
5245
1695
(
(
2360
2895
960
~~g?
3975
1525
3640
4540
1610
3000 1020
400! 10~~
I ~nnr 1!~~
60m 1230
67
3035
2565
905
(
7
i
. ~~~~~I
(
o
~!~~ ~OO~
17nn7"~
;~~~ ~~~~ ~~~~ . ~~~~ ;~~~ ~~~~ ~~~~ m~ m~ ~~~~ ~~~: ~~~~
o
o
(
10'C
GRO TOTAL
RO LL TO
I ~~~~I
(
(
O'C
GRO TDTRL
ROl l TO
Fl 50 FT
1060 18S5
1790
,~~~
1110
1595
}m
1895
I
;~~~
1175
1685
;
~~~
2005
1995
2760
860
3480
5010
1505
~~~ ~~:g
1035
;
1780
;~~ ;~~~
125.0
2120
2255
3160
910
1
5985
1585
------960
.-----1665
~~~ ;~~~ ~~~~ ~ ~~~
1095
;
4020
1970
1210
2090
~~~ ;~~~ m~ ~~~~
1395
2390
1570
2730
(
~~~~ .it~~ ~~~~ g:~ ~n~ I ;~~~ ~~~~ I ~~;~ ~~~~ n~~ ~~~~ ~~~~ ~~~~
(
~~~g~ ;~~g ~~~g ~~~~ ~~g~ ;~~g ~~~g ~~~~ ~~~~ ;~~~ !i~~ ==== :==:
("'.,..
...
900
1265
2140
1345
2275
1495
2540
1675
2880
1890
3300
----
----
2000 1625
2755
1BI5
3110
2035
3535
2300
4075
2625
4775
----
----
Figure 5-9. Takeoff Distance - Short Field
Revision 6
5-21
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
WITHOUT CARGO POD
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEETI
FLAPS UP
CONDITIONS :
FLAPS 0 DEGREES
1900 RPM
INERTIAL SEPARATOR - NORMAL
CABIN HEAT - OFF
TOROUE SE1 PE R FIGURE 5-8
PAVED. LEVEL. DRY RUN~AY
ZERO ~INO
WE I GH
LBS
. 8000
7500
7000
NOTES:
1. USE TYPE II DR TYPE IV ANII-ICE FLUID TAKEOff
TECHNIOUES AS SPECIFIED IN SECTI ON 4.
2. DECREASE DISTANCES 10% fOR EACH 11 KNOTS HEADWIND.
FOR OPERATION WITH TAILWINOS UP TO 10 KNOTS,
INCREASE DISTANCES BY 10% FOR EACH 2 KNOTS_
3. fOR OPERAT I ON ON A DRY, GRASS RUNWAY. INCREASE
DI STANCES BY 15% OF THE "GROUND ROLL' FIGURE .
4 . HITH TAKEOFF POHER SET BELOH THE TORDUE L 1M IT
11865 FT -LBS l. I NCREASE DISTANCE 1BOTH GROUND ROLL
AND TOTAL OISTANCEI BY 3% FOR INERTIAL SEPARATOR
IN BYPASS AND INCREASE GROUND ROLL 51. AND TOTAL
DISTANCE 9% FOR CABIN HEAT ON .
S. WHERE DISTANCE VALUES HAVE BEEN REPLACED BY DASHES
OPE RAT I NG TEMPERATURE LI MI TS OF THE AIRPLANE WOULD
BE GREATLY EXCEEDED . THOSE OISTANCES WHICH ARE
INCLUDED BUT THE OPERATION SLIGHTLY EXCEEDS THE
TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION
PURPOSES ONL y,
TAKEOFF
-20'C
SPEED PRESS
KIAS
AU GRD TOTAL
IF
AT FT
ROll TO
FF o F
FT 50 FT
89 104
SL 1520 26'70
2000 1700 2965
4000 1'l0~ 3300
6000 2145 36BS
8000 2425 4130
4645
2000 3155 5320
B9 104
SL 1410 24.B5
2000 1580 2760
400e 11775 3070
6000 1995 3425
BODO 2250 3840
lOOOO 12550 4315
2000 2925 4945
89 104
SL 1310 2305
2000 141>5 2555
4000 1640 2845
6000 1845 3175
8000 2085 3555
0000 12355 3995
2000 2705 4570
- 10·C
O'C
10'C
GRO TOTAL GRO TOTAL GRD TOTAL
ROLL TO
ROLL TO
ROLL TO
FT 50 FT
o FT
FT 50 FT
FT
1610 2820 1710 2975 1805 3135
1B05 3135 1915 3310 2025 3485
?0?5 3490 7150 3h'l0 ??75 3890
2285 3905 2425 4130 2565 4360
2580 43BO 2740 4635
2925 4'130 3185 5405
3490 5'155 3885 6730
---1500 2630 1590 2770 1680 2920
3080 1880 3245
1680
3430 2115 3620
1885
2120 3630 2250 3840 2385 4050
2395 4070 2545 4310
2715 4580 2960 5020 ---3240 5530 3600 6245
1390 2435 1470 2570 1555 2705
1555 2700 1645 2850 1740 3005
1745 3010 1850 3180 1955 3'150
1965 3360 2085 3555 2205 3750
2215 3770 2355 3990
2510 4240 2735 4645
2'190 5115 3320 5770
----
---- ------- -------
.m~ ~~~~
---- ---------- ----
---- ------- -------
Figure 5-10. Takeoff Distance - Flaps Up
5-22
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
(
(
WITHOUT CARGO POD
(
( (~--
RATE OF CLIMB - TAKEOFF FLAP SETTING
(
CONO I TIONS I
TAKEOFF POWER
1900 RPM
INERTIAL SEPARATOR - NORMAL
ZERO WINO
NOTES:
1. 00 NOT EXCEED TORaUE LIMIT FOR TAKEOFF PER ENGINE TOROUE FOR TAKEOFF
CHART. WHEN ITT EXCEEDS 765"C. 1HIS POWER SETTING IS TIME LIMITED
TO 5 MINUTES.
2. WITH CLIMB POWER SET BELOW THE TORaUE LIMIT. DECREASE RATE OF CLIMB
BY 20 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 45 rPM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLI MB VALUES HAVE BEEN REPLACED BY- DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEEDS
THE TEHPERATURE LIHIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
PRESS
CLlHB
RATE OF CLIHB - FPH
WEIGHT
All
SPEED
DoC
FT
KIAS
LBS
-20 C
20 C 40 C
1110 1090 1070 1050
8000
SL
92
1090 1065 1045
2000
92
975
4000
1065 1040 1015
875
91
1040 10.10
985
760
6000
91
845
BODO
1005
9BO
6ZO
90
970
900
700
480
10000
BB
750
340
87
915
555
12000
1230 1210 1190 1170
7500
SL
92
1210 1185 1165 1090
2000
91
990
4000
1185 1160 1135
90
875
1105
1160
1130
6000
90
960
725
1125 1100
8000
BB
1090 1015
810
580
87
10000
435
860
660
1035
12000
85
1365 1345 1325 1305
7000
SL
91
13 liD
1320 1300 1225
2000
90
1320 1295 1270 1115
4000
89
995
1290 1265 1240
6000
B9
8~0
B7
1260 1235 1090
BODO
935
690
1225 1150
10000
86
775
5~0
84
1170
985
12000
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
FLAPS 20°
(
Figure 5-11. Rate of Climb - Takeoff Flap Setting
5-23
1 April 1998
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
WITHOUT CARGO POD
CLIMB GRADIENT - TAKEOFF FLAP SETTING
FLAPS 20·
CONDIT IONS I
TAKEOFF POWER
1900 RPI1
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTES:
1. DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TORQUE FOR TAKEOFF
CHART. WHEN ITT , EXCEEDS 765 °C. THIS POWER SETTING IS TIME LIMITED
TO 5 MINUTES.
2 . WITH CLIMB POWER SET BELOW THE TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 10 FlINM FOR INERTIAL SEPARATOR IN BYPASS AND 30 FTINM FOR CABIN
HERT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH BRE INCLUDED BUT THE OPERATION SLIGHTLY EXCEEDS
THE TEMPERATURE LiMiT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
CLII1B GRADIENT - FT/NI1
PRESS
CLlI1B
WEIGHT
All
SPEED
OuC
40·C
2D"C
-20·C
FT
KIRS
LBS
760
725
BODO
SL
77
850
805
2000
76
760
720
650
805
4000
76
160
715
615
570
670
6000
76
630
485
715
8000
76
870
625
530
385
76
560
430
10000
625
295
12000
76
570
455
330
205
7500
SL
74
960
910
865
820
2000
74
860
745
910
B15
<1000
74
860
770
815
660
6000
74
815
765
720
565
8000
74
765
720
610
460
10000
74
715
645
505
360
73
12000
655
530
400
270
7000
SL
72
lOBS
1030
980
935
2000
1030
975
72
930
B50
<1000
72
9BO
925
B80
760
875
6000
925
72
825
660
8000
72
875
820
710
545
10000
71
820
740
595
440
12000
71
155
620
485
340
~.'- '
Figure 5·12 . Climb Gradient - Takeoff Flap Setting
5-24
1 April 1998
For Training Purposes Only
.
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 5
PERFORMANCE
(
(
WITHOUT CARGO POD
( ( -'
( \
(
(
(
(
(
(
(
(
(
(
(
(
(
FLAPS UP
CONDITIONS:
1900 RPH
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTES:
1. TOROUE SET AT 1865 FT-LBS OR LESSER VALUE MUST NOT EXCEED MAXIHUM
CLIHB ITT OF 755·C OR NG OF 101.51..
2. WITH CLIMB PO~ER SET BELOW THE TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 30 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 65 FPM fOR CABIN
HEAT ON.
3. WHERE RRTE OF CLIMB VALUES HAVE BEEN REPLRCED BY DASHES. AN
APPRECIABLE RATE OF CLlHB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED
OR OPERATING TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY
EXCEEDED. THOSE RATES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION
SLIGHTLY EXCEEDS THE TEHPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION
PURPOSES ONLY.
PRESS
CLIMB
RATE OF CLIMB - FPM
IoIEIGHT
AU
SPEED
FT
LBS
KIAS -1l0 C -20 C
o C 20 C 40· C
BODO
SL
107
1275
1260 1245 1230
985
4000
IDS
1235
1220 1200 1085
705
8000
103
1190
1170 1090
795
1155
12000
99
1130
1000
780
520
220
16000
870
9S
1185
690
240
-20000
91
565
395
195
-211000
87
275
110
---7500
107
1400 1385 1310 1355 1100
SL
4000
104
1360 1345 1330 1210
Blo
BODO
102
1315
1295 1210
905
545
12000
99
1255 1120
895
615
300
16000
91l
985
BOD
585
40
330
20000
90
670
1190
285
40
370
211000
86
200
-7000
106
1535 1525 1510 1495 1225
SL
11000
104
11185 1470 1345
1500
920
1455
Itl35 1350 1025
8000
6115
101
1395 1255 1015
12000
98
725
390
425
16000
93
1110
920
695
120
785
20000
89
600
380
125
-475
24000
85
300
90
--
--
(
(
(
(
--
(
(
(
(
MAXIMUM RATE OF CLIMB
, :,y
I "',
--
,
--
--
Figure 5-13, Maximum Rate of Climb - Flaps Up
5-25
1 April 1998
For Traininl! Purooses Onlv
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
WITHOUT CARGO POD
MAXIMUM CLIMB GRADIENT
(
FLAPS UP
CONDITIONS:
TRKEOFF POWER
1900 RPM
INERTIAL SEPARATOR - NORMAL
ZERO WINO
NOTES:
1. 00 NOT EXCEEO TOROUE LIMIT FOR TAKEOFF PER ENGINE TORQUE FOR TAKEOFF
CHRRT. HHEN ITT EXCEEDS 765"C. THIS POWER SETTING IS LIMITED TO
5 MINUTES.
2. WITH CLIMB POWER SET BELOW .THE TORQUE LIMIT. DECREASE RATE OF CLIMB
BY 10 FT/NN FOR INERTIAL SEPARATOR IN BYPRSS ANO 40 FT/NN FOR CABIN
HEAT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEEDS
THE TEMPERATURE CIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY .
CLIMB GRADIENT - FTlNM
PRESS
eLi MB
HEIGHT
SPEED
AU
40·C
-20 C
o C 20·e
fT
KI AS
LBS
755
785
SL
825
605
8000
90
790
750
715
510
2000
90
630
420
750
715
4000
90
715
675
535
340
6000
89
445 ' 265
675
610
8000
89
10000
BB
635
515
365
200
545
420
285
130
12000
88
7500
920
880
840
680
SL
89
B80
840
800
2000
88
585
11000
840
800
710
IIS0
88
87
800
760
610
1105
6000
760
8000
87
685
515
325
430
10000
8,6
720
585
255
12000
1190
340
86
620
180
7000
770
SL
87
1025
980
940
2000
87
980
940
900
665
4000
9110
805
86
895
565
1175
6000
86
895
855
695
775
8000
85
B50
595
390
670
10000
85
810
500
315
84
705
,V
~611l0
e(),9lk
v
{'l.~
>--::~~
V
-,600
,/
~
k::
k-'"
...-- ....-:
"-
v
v
~
40111
i""
~
... ..-::;;,.F"
I 40
I 211l
II
I 1Il0
211l11l
~
O\:,S
....
~
0
\."\\il.l.... 1"""
...
II
II
~
...
~
15
f>.'-::':'"
4
"",
2o
II
(jill
V
/
lr
!/
II
V
V
I
II
'"
V
V
V
V
V
1/
/
1/
V
V
1/
/
V
/"
/
,f
V
V
/
...
v
V
V
V
V
I
:1
o
/
1/
'"--"j
"
~
V
60
DISTANCE - NAUTICAL MILES
Figure 5-21. Fuel and Time Required - Maximum Range Power
40 - 200 Nautical Miles (Sheet 1 of 2)
5-46
1 April 1998
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
(
(
WITHOUT CARGO POD
FUEL AND TIME REQUIRED
MAXIMUM RANGE POWER (200 -1000 Nautical Miles)
(
(
CONDITIONS:
8000 Pounds
1900 RPM
Inertial Separator - Normal
(
(
Standard Temperature
NOTES:
1.) Fuel required includes the fuel used for engine start, taKi, takeoH, maximum climb from sea level, descent to sea
level and 45 minutes reserve. Time required Includes the time during a maximum climb and descent.
2.) With inertial separator in BYPASS or cabin heat on, increase time by 3% and fuel by 2%.
(
2~11I111
(
(
211100
V
1/
1/
(
s-fJ
(
f-t- ~9
(v.~:z..r- -~"
~?Y
",0
<'d
~ 12111111
(
(
...
V
!l01i1
V
1/ V
1"11
V
IL
IL
1/
7
V
il...Jo!"olfl 1-1c;§J(!:",o,
(
(
,o~
~0111
0«-.'<>
V
5
~~
~\-.
(
4
P.
~
1-1-
6
3
........
-1-1-
~
2
1
V
V
V
1/
V
1/
1/
Ii
J
I",
'"
611
I
lL
I",
fTJ
V
Ii
1/
II
.f
103;
!71'li
lL
IL
lL
V
V
V
V
1/
V
1/1..11
P)'
II
l[
DISTANCE - NAUTICAL MILES
Figure 5-21. Fuel and Time Required - Maximum Range Power
200 - 1000 Nautical Miles (Sheet 2 of 2)
1 April 1998
5-47
For Trainine Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
WITHOUT CARGO POD
(
RANGE PROFILE
45 MINUTES RESERVE
2224 LBS USABLE FUEL
(
(
NOTES;
CONDITIONS ;
1. This chart allows for the fuel used for engine start,
taxi, takeoff, climb and descent. The distance
during a maximum climb and the distance during
descent are inCluded .
8000 Pounds
1900 RPM
Standard Temp
Zero Wind
Inertial Separator - Normal
2. With the inertial separator in BYPASS or cabin heat
on, decrease range by 2% .
25000
IIIIII
1111 II
1-H-H-H-l++-H-'H-+++-H-+++174 KTAS+-H-++++Jf.IH.-j:·W
nfS
1-H-I++-HI++-H-H4...J+H4...J+++!+++-H*+-lA-1+I-I158 KTAS-HH-I-+H
2ililil0
....w
w
lL
H-l1++++4-++++4++-1182 KTAS-I-I-hl''-I-I-'I++.J..I...lf4160 KTA,I>+l-H-H-++H
15000
HH++H++H-H-H4+H~ CT!~
~?-
51/1111111
(
(
SL
4.111
5.111
B.1lI
7.111
B.III
9.111
ENDURANCE - HOURS
Figure 5·23. Endurance Profile
5·49
1 April 1998
For Traininl! Purooses Onlv
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675SHP)
WITHOUT CARGO POD
TIME, FUEL AND DISTANCE TO DESCEND
(
CONDITIONS:
Flaps Up
8000 Pounds
140 KIAS Above 16,000 feet,
160 KIAS Below 16,000 feet
Power Set for 800 FPM Rate of Descent
1900 RPM
PRESSURE
ALTITUDE
(FEET)
24,000
20,000
16,000
12,000
8,000
4,000
Sea Level
(
(
(
DESCEND TO SEA LEVEL
TIME
(MIN)
FUEL USED
(POUNDS)
DIST
(NM)
30
25
20
15
10
5
0
118
102
86
65
45
23
91
· 7S
59
43
28
14
0
a
NOTE
. (
(
(
(
Distances shown are based on zero wind.
(
(
Figure 5-24. Time, Fuel and Distance to Descend
5-50
1 April 1998
For Training Purposes Only
»
LANDING DISTANCE
"0
~,
MAXIMUM WEIGHT 7800 LBS
SHORT FIELD
________________________________
-L
<.0
<.0
co
"T1
cO'
c:;:
CD
,
(J'\
N
~
"!l
..,
I
==
~
CONDITIONS:
NO~S:------------------
Flaps 30·
Power lever - Idle after clearing
obstacles, BET A range (lever
against spring) after
touchdown.
Propeller Control lever - MAX
Maximum Brak.ing
Paved, Level, Dry Runway
Zero Wind
1. Short field technique as specified in Section 4.
2. Decrease distances 10% for each 11 k.nots headwind. For operation with tailwinds up to 10
k.nots, increase distances by 10% for each 2.5 k.nots.
.
3. For operation on a dry. grass runway, increase distances by 40% of the 'ground roll" figure.
4. If a landing with flaps up is necessary. increase the approach speed by 15 KIAS and allow
for 40% longer distances.
5. Use of maximum reverse thrust after touchdown reduces ground roll by approximately 10%.
6. Where distance values have been replaced by dashes. operating temperatUre limits of the
airplane would be greatly exceeded. Those distances which are included but the operation
slightly eKceeds the temperature limit are provided for interpolation purposes only
..
-
~
~
-
c.
~
S'
:;-
-
."
-
1565
1605
1645
1690
1735
1780
1830
1880
1935
o
oC
--
to
to
CO
- - - - - - ---._-- ...-, .-..--------. >
(
(
CARGO POD INSTALLED
TAKEOFF DISTANCE
(
(
(
(
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
SHORT FIELD
NOTES :
CONDITIONS:
FLAPS 20 DEGREES
1900 RPM
INERTIAL SEPARATOR· NORMAL
CABIN HEAT · OFF
TORQUE SET PER FIGURE 5·8
PAVED. lEVEL. DRY RUNWAY
ZERO WIND
(
(
1 USE SHORT FIELD TECHNIQUES AS SPECIFIED IN SECTION 4 .
2. DECREASE DISTANCES 10% FOR EACH 11 KNOTS HEADWIND.
FOR
OPERATION WITH TAILWINDS UP TO 10 KNOTS. INCREASE DISTANCES BY 1(1%
FOR EACH 2 KNOTS .
3. FOR OPERATION ON A DRY, GRASS RUNWAY, INCREASE .DISTANCES BY 15%
OF THE -GROUND ROLL' FIGURE.
4. WITH TAKEOFF ' POWER SET BELOW THE TORQUE LIMIT (1865 FT·LBS).
INCREASE DISTANCE (BOTH GROUND ROLL AND TOTAL DISTANCE) BY 3% FOR
INERTIAL SEPARATOR IN BYPASS AND INCREASE GROUND ROLL 5% AND
TOTAL DISTANCES 10% FOR CABIN HEATON.
5. WHERE DISTANCE VALUES HAVE BEEN REPLACED BY DASHES, OPERATlM3
TEMPER ATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED.
THOSE DISTANCES WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY
EXCEEDS THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION
PURPOSES ONLY
6, FOR OPERATIONS ABOVE 40"C AND BELOW THE TEMPERATURE OPERATING
LIMITATIONS. MULTIPLY TAKEOFF DISTANCES AT 40' C BY 1.2.
(
(
WI I ~~~~~r
LE KIAS
Al
50 F
8 72
82
0
0
0
(
(
-10'C
RESS
AL T
FT
b~~
(
(
I
SL
1000
200C
3000
~~~L
'~~HL
FT 50 FT
1010 1820
1070 1925
1135 2035
1205 2150
O'C
~~~L
I,O,AL
TO
FT 50 FT
1010 1925
1135 2035
1210 2155
1285 2280
6000 1460
1555
~~gg
I~~n
9000 1775
2570
1555
1660
_1775
3100 1900
]:
l~~gg ~~~~ i~~~
1
5
0
0
10
BO
200
SL
2310
860
~~gg ~.1O
70
3000
4000
5000
6000
1000
BOOU
9000
(
DODO
IIOOC
1
0
0
0
67
77
1030
1095
HS5
1240
1320
1410
1510
1615
1760
1950
730
115
820
810
4070
1545
1635
lJ25
1820
1930
2045
2165
2300
2445
2605
~~j8
3390
2000
1305
SL
1375
1000
1450
200e
1535
3000
1620
4000
500t
.1715
6000 1050 1820
7000
1930
BoDe
2050
9000 1215 2180
1360
l~~g~ 1480
2000 1640 2810
m
~~~~
mg
2725
~m
3300
3660
~~~~ <1120
2595 4665
915 1635
910 1725
1030 1825
1095 1930
1165 2045
1240 2165
1320 2300
1410 ' 2445
1505 2600
1610 2770
1770
19S:; ~~;~
21B5 3855
175 1380
820 1455
870 1535
925 1620
1115
1
1 A15
1115 1925
1190 2045
1210 2115
1360 2315
1495 2550
1655 2840
1835 3175
~~~
20'C
10'C
~~~L
rr
1135
1205
1285
1365
~~g~ ~m ~~~~ 1~~~ ~~~~ ~~~~
i'
\"
(
SECTION 5
PERFORMANCE
C.ESSNA
MODEL 208 (675 SHP)
1655
1765
1 ~I 0
2115
~~~~
2930
970
~~Hl
50 FT
2035
2150
2275
2415
mg
2890
~~~g
3125
4180
<17<10
5415
1725
~~~L
'¥~AL
FT SO FT
1205 2145
1280 2270
1360 2405
1450 2550
50 FT
2260
FT 50 fl
1345 2380
1445 2550
1570 2180
1105 3035
3320
3640
2240 4010
2495 4615
~, ~~~
2690
~~:~ ;~~~ 1~;g
11~
~~70
<15
1755
1940
7150
2390
~~~~
3345
1025
3065
i~~g
4295
4865
5510
6445
1815
1160
1235
1315
1405
m~
mg
CWU l'OIRl
ROLL TO
1~~0
mg
1790
fT
1215
1355
1230
1310
1395
1490
2150
2515
1915
3500
3925
~~~~ 44'1n
2115 5035
3040 5175
3il15 6730
3855 7995
1085 1915
2025
}~~~ 21110
1305 2270
1390 2415
1515 2S110
1670 2925
4425
1455
1535
1&20
1110
1815
1920
2040
3560
2195
870
~~~
10<10
1110
1180
1260
5115
1530
1615
1105
1805
1915
2030
2155
~~~~ i~~~10 m~
1~
25B5
1690
m~ ~~~~
3615
~~~~
---- ------- --_.
---- -------- --'
----
1145
g~~
---.
2010
2155
?34
1450 2550
1515
1715
1890 3375
2100 3795
~~~~
}~~~ ~~:~ ~~;g ~~~~ ---- ----
2015
4125
4680
5365
3205 6215
915 1610
915 1100
1035 1795
1100 1900
1115 20Z5
1280 2205
1410 2435
1555
1720
1910 3375
2280
;~~; ~~i~ ~~~~ :~~~ ~~~~
2460
820
870
925
985
1045
1115
lI85
1265
1365
1510
1665
1850
2060
40'C
II~~AL
1535
~g~~ m~ ~~~~
2040
2160
2295
2435
2590
'195
3110
30'C
oRu
ROLL
I
2330
2940
3285
1"~"
4180
~~~~
--------- ----
- --- -- -------
910 1690
1040
1125
1220 2125
1325 2310
1440 2515
1590 2185
1760 3115
i~~~
~---
- --.
---- ------- ---m~ ~~~g ---- ---2655 4920 ---- ----
Figure 5-26. Takeoff Distance - Short Field
5-53
Revision 6
For Traininp Pnrnnses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
TAKEOFF DISTANCE
(GROUND RDLL DISTANCE AND TOTAL DISTANCE TD CLEAR 50 FEET)
FLAPS UP
COND IT IONS,
FLAPS 0 DEGREES
1900 RPM
I NERTf AL SEPARATOR - NORMAL
CRB I N HEAT - OFF
TDROUE SET PER FIGURE 5-8
PRVED. LEVEl. DRY RUNHAY
ZERO WIND
WEIGH
LBS
8000
7500
NOTES:
1. USE TYPE II OR TYPE IV ANIT-ICE FLUID TAKEOFF
TECHNIDUES AS SPECIFIED IN SECTION 4.
2. DECREASE OISTANCES 10% FOR EACH 11 KNOTS HEADWINO.
FOR OPERATIONNITH TAILWINDS UP TO 10 KNOTS.
INCREASE 0 IS TANCES BY lOY. FOR EACH 2 KNOTS.
3. FOR OPERATION ON A DRY. GRASS RUNIIAY. INCREASE
DISTANCES BY 15% OF THE "GRDUNO ROLL' FIGURE.
4. WITH TAKEOFF POWER SET BELOW THE TORDUE LIMIT
11865 FT-LBS I. INCREASE DISTANCE IBOTH GROUND ROLL
ANO TOTAL DISTANCE I BY 3Y. FOR INERTIAL ,SEPARATOR
IN BYPASS AND INCREASE GROUND ROLL 5% AND TOTAL
OISTANCE 9% FOR CABIN HEAT ON.
5. WHERE DISTANCE VALUES HAVE BEEN REPLACED BY DASHES
OPERATING TEMPERATURE LIMITS OF THE AIRPLANE WOULD
BE GREATL Y EXCEEDED. THOSE DISTANCES HHICH ARE
INCLUDED BUT THE DPERATION SLIGHTL Y EXCEEDS THE
TEMPERATURE II MIT ARE PRDV IDEO FOR I NTERPDLAT ION
PURPOSES ONL Y.
TAKEOFF
_10· C
O·C
-2D·C
10·C
SPEED PRESS
KIAS
AU GRD TOTAL GRD TOTAL GRO TOTAL GRO TOTAL
IF
AT FT
ROLL TO
ROLL TO
ROLL TO
ROLL TO
FF o F
FT 50 FT
FT 50 FT
FT 50 FT
FT 50 FT
B9 104
SL 1535 2720 1630 2875 1730 3035 1830 3195
2000 1720 3020 1830 3195 1940 3375 2050 3560
4000 1930 3365 2055 3565 :>180 3765 .2305 3975
6000 2175 3760 2315 3985 2455 4220 2605 4455
8000 2455 4220 2615 4475 21BO 4745
lOOOO 2785 4750 2965 5050 3235 5545
..
2000 3200 5455 3545 6125 3945 6955
89 104
Sl 1430 2535 1520 2675 1610 2825 1700 2975
2000 1600 2810 1700 2975 1800 3140 1905 3310
400U 1795 '3130 1910 3315 ?O?S ,50S .21A5 3695
6000 2020 3500 2150 3710 2285 3925 2420 4145
8000 2285 3925 2430 4160 2580 4410
LOOOO 12585 4415 2755 4690 3000 5150
2000 2910 5065 3290 5690 3660 6455 ---- ..
89 104
SL 1325 2350 1405 2480 1490 2620 1575 2755
2000 1480 2605 1575 2755 1670 2910 1765 3065
4000 1665 2900 1165 3070 1875 3245 1985 3425
600n IB70 3240 1990 3435 2110 3630 2235 3835
122451 3850 12385 4080 1 ____
1l~ 1 3630
Il.ll.!BI~~~I!
.' ,,<,.
@~i'l 25(:: I 4340 2775 I 4765 ---- ~
~lOrJ 1:745 lj095 [3D40 5L~!l p375 ,L:>S05
---- ------- ------- - _---- ------- ------
7000
i
I
I
1----I
-_.__-1._-- . . I ..._ . .__ __El
. .__ _. _'-1
u
Figure 5-27. Takeoff Distance· Flaps Up
5-54
1 April 1998
For Training Purposes Only
(
(
(
(
(
CESSNA
(
MODEL 208 (675
(
(
PERFORMANCE
CARGO POD INSTALLED
(
RATE OF CLIMB - TAKEOFF FLAP SETTING
(
FLAPS 20°
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
SECTION 5
SHP)
(~/
eONO I TIONS:
TAKEOFF POHER
1900 RPM
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTESr
1. DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TORQUE FOR TAKEOFF
CHART. HHEN ITT EXCEEDS 765°C. THIS POHER SETTING IS LIMITED TO
5 HINUTES.
2. WITH CLIMB POWER SET BELOW THE TORQUE LIMIT. DECREASE RATE OF CL!MB
BY 20 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 45 FPM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEEo~
THE TEMPERATURE LIMIT ARE PROVIOEO FOR INTERPOLATION PURPOSES ONLY.
PRESS
CLIMB
RATE OF CLIMB - FPM
WEIGHT
ALT
SPEED
O"C 20 C liD C
LBS
FT
KIAS -20"C -. l~C
BOOO
SL
lOiS 1065 1055 1030 1010
92
2000
1055 1040 1030 1005
92
930
11000
1030 1015 1000
975
91
830
6000
1000
9B5
970
940
91
no
9iO
BODO
90
955
940
805
575
10000
BB
920
860
935
660
435
710
12000
B7
B80
800
515
300
7500
SL
92
1195 1180 1170 1150 1125
2000
11iO
91
1160 1145 1125 1050
1I000
11115
90
1135 1120 1095
9115
6000
1120 1105 1090 1060
90
830
8000
88
1085 1070 1055
920
680
975
87
1050 1035
770
535
10000
910
820
620
395
12000
995
85
1325 1315 1305 1280 1260
7000
SL
91
2000
90
1300 1290 1280 1255 1180
/1000
1280 1265 1255 1225 1070
89
950
6000
89
1250 1235 1225 1195
795
87
1220 1205 1190 1045
8000
890
6115
10000
86
1185 1170 1105
945
735
tl95
8t1
1130 lOtiO
12000
Figure 5-28. Rate of Climb - Takeoff Flaps Setting
5-55
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
CLIMB GRADIENT - TAKEOFF FLAP SETTING
FLAPS 20
0
(
CONDITIONS:
TAKEOFF PololER
1900 RPI1
INERTIAL SEPARATOR - NORMAL
ZERO HIND
NOTES:
1. DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TORQUE FOR TAKEOFF
CHART . IolHEN ITT EXCEEDS 765°C. THIS POHER. SETTING IS LIMITED TO
5 MINUTES.
2. HITH CLIMB POWER SET BELOW THE TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 10 FT/NN FOR INERTIAL SEPARATOR IN BYPASS AND 30 FT/NM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLII1B VALUES HAVE BEEN REPLACED BY DASHES . nPERAIING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLII1B WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEED!
THE TEI1PERATURE LIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
CLIMB GRADIENT - FliNN
CLlI1B
PRESS
SPEED
WEIGHT
ALT
(loC
20 C 40 C
-20 C - 10 C
KIAS
FT
LBS
705
785
745
810
77
830
8000
SL
635
740
700
765
785
76
2000
655
550
700
720
740
76
4000
465
615
655
675
695
76
6000
370
510
610
630
650
76
BODO
275
540
410
585
610
76
10000
190
435
315
495
76
555
12000
845
805
890
915
74
940
SL
7500
800
725
845
865
890
74
2000
640
795
750
820
74
845
4000
745
iDS
550
'170
795
74
6000
440
700
595
720
745
74
8000
345
4B5
675
625
700
74
10000
250
515
3B5
640
580
73
12000
915
960
1035 1010
1065
7000
SL
72
960
910
830
985
1010
n
2000
860
740
905
930
960
4000
72
640
855
810
B80
905
6000
n
525
805
690
830
855
8000
n
420
575
775
725
800
10000
'11
320
605 . 465
670
740
'11
12000
(
(
(
(
(
(
(
(
(
(
{
(
(
(
(
i
' {-~:. : .
(
Figure 5-29. Climb Gradient - Takeoff Flap Setting
1 April 1998
5-56
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
(
CARGO POD INSTALLED
"F'
;t.'
\
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
,
SECTION 5
PERFORMANCE
l"
\.
MAXIMUM RATE OF CLIMB
FLAPS UP
CONDITIONS.
1900 RPM
INERTIAL SEPARATOR - NORMAL
ZERO WINO
NOTES I
1. TORDUE SET AT 1865 FT-LBS OR LESSER VALUE MUST NOT EXCEED MAXIMUM
CLIMB ITT OF 765'C OR NG OF 101.61..
2. WITH CLIMB POWER SET BELOW THE TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 3D FPM FOR INERTIAL SEPARATOR IN BYPASS AND 65 FPM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. AN
APPRECIABLE RATE OF CLIMB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED
OR OPERATING TEMPERATURE LIHITS OF THE AIRPLANE WOULD BE GREATLY
EXCEEDED. THOSE RRTES OF CLIMB WHICH RRE INCLUDED BUT THE OPERATION
SLIGHTLY EXCEEDS THE TEMPE~ATURE LIMIT ARE PROVIDED FOR INTER~OlATIO~
PURPOSES ONLY.
PRESS
CLI MB
RATE OF CLIMB - FPM
WEIGHT
All
SPEEO
LBS
FT
KIRS -1I0'C -20'C
o C 20'C 40 C
8000
107
1220 1205
SL
1190 1170
925
4000
105
1185 1165 1145 1025
645
BODO
1140 1115 1030
103
735
390
lOBO
12000
99
945
725
460
155
820
16000
95
640
430
-185
20000
515
345
140
91
-24000
87
230
65
7500
1340 1325 1310 1295 1035
SL
107
11000
104
1305 12B5 1265 11115
745
8000
102
1260 1235 1150
840
480
12000
99
1200 1060
835
555
235
930
745
16000
94
530
270
620
440
20000
90
230
'- 211000
325
86
155
-1475 1465 1450 lil30 1160
7000
SL
106
14110 1425 1405 1280
11000
104
850
1400 1375 1285
575
8000
101
960
1340 1195
955
12000
98
660
325
1060
860
635
365
55
16000
93
545
70
'135
325
20000
89
-425
24000
250
35
85
--
--
--
-
--
--
--
--
Figure 5-30. Maximum Rate of Climb - Flaps Up
5-57
1 April 1998
Fnr TraininlJ Purnoses Onlv
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
CARGO POD INSTALLED
MAXIMUM CLIMB GRADIENT
FLAPS UP
CONDITIONS:
TAKEOFF POHER
1900 RPtI
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTES I
1. 00 NOT EXCEED TOROUE LIMIT FOR TRKEoFF PER ENGINE . TOROUE FOR TAKEOFF
CHART. WHEN ITT EXCEEDS 76S·C. THIS POWER SETTING IS LIHITED TO
5 MINUTES.
2. WITH CLIMB POWER SET BELOW THE .TOROUE LIMIT. DECREASE RATE OF CLIMB
BY 10 FT/NM FOR INERTIAL SEPARATOR IN BYPASS AND 40 FTINM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLltlB VALUES ~AVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LltlITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES ofCLIM6 WHICH ARE INCLUDED BUT THE OPERATION SLIGHTLY EXCEED~
THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
[LIMB GRADIENT - FT/Nt!
PRESS
CLIMB
WEIGHT
ALI
SPEED
FT
KIAS
o C 20·C 4()·C
LBS
-20C -10 [
760
730
7BO
580
8000
SL
90
800
690
485
2000
765
745
725
90
4000
705
690
605
400
90
725
650
6000
670
515
315
89
690
585
425
245
8000
89
650
635
490
10000
88
615
555
340
180
12000
400
260
88
525
460
110
7500
SL
89
890
870
850
815
655
2000
815
775
855
835
560
88"
4000
775
88
795
6B5
465
815
735
6000
87
175
755
585
380
8000
665
87
735
715
490
300
10000
86
695
635
560
405
230
4S5
12000
535
86
600
320
160
7000
87
975
745
SL
995
955
915
2000
87
955
935
910
875
640
11000
870
86
890
775
5110
910
6000
870
830
670
450
86
850
8000
85
825
805
750
570
365
10000
785
645
475
B5
720
295
540
12000
84
615
385
215
680
Figure 5-31. Maximum Climb Gradient - Flaps Up.
5-58
1 April 1998
For Training Purposes Only
('
(
CESSNA
MODEL 208 (675 SHP)
(
(
(
CARGO POD INSTALLED
(
CRUISE CLIMB
/- -
(
{
(
(
(
(
(
(
(
(
(
(
(
j~."<.. ,
FlRPS UP
CONOI TIONS:
1900 RPM
INERTIAL SEPARATOR - NORMRL
ZERO WINO
NOTES.
1. TORQUE SET AT 1865 FT-lBS OR lESSER VALUE MUST NOT EXCEED MAXIMUM
CLIMB ITT OF 76S·C OR NG OF 101.6r..
2. WITH CLIMB POWER SET BELOW THE TORQUE LIMIT. DECREASE RATE OF CLIMB
BY 50 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 70 FPM FOR CABIN
HERT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. AN
APPRECIABLE RATE OF CLIMB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED
OR OPERATING TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY
EXCEEDED. THOSE RRTES OF CLIMB WHICH ARE INCLUDED BUT THE OPERATION
SLIGHTLY EXCEEDS THE TEMPERRTURE LIMIT ARE PROVIDED FOR INTERPOLATIO~
PURPOSES ONLY.
PRESS
CLIMB
RATE OF CLIMB - FPM
WEIGHT
SPEED
RLT
KIAS -<10"C -zo C
LBS
FT
o C 20 C 40 C
1140 1115
8000
120
1190
1165
650
SL
2000
4000
6000
8000
10000
12000
(
(
(
7500
SL
(
2000
(
6000
8000
10000
12000
~lOOO
(
(
SECTION 5
PERFORMANCE
7000
SL
2000
11000
6000
8000
10000
12000
(
,/
120
120
120
120
120
120
120
120
120
120
120
120
120
120
120
120
120
120
120
120
1165
1140
1110
1080
1045
1005
1305
1280
1255
1225
1195
1155
1115
1435
1410
1380
1355
1320
1280
1240
1140
1110
1080
1045
955
755
1280
1255
1225
1195
1155
1060
850
1405
1380
1350
1320
1280
1180
955
1115
1080
1025
830
635
440
1255
1225
1195
11110
930
725
520
1385
1355
1320
1265
1040
825
605
965
800
630
445
265
90
1230
1075
900
715 -
520
330
145
1355
1190
1005
810
- 605
400
205
495
3<10
180
10
---
735
570
1105
235
60
---
830
655
1180
300
110
---
Figure 5-32. Cruise Climb - Flaps Up
5-59
1 April 1998
For Training Purposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
(
(
(
CARGO POD INSTALLED
RATE OF CLIMB - BALKED LANDING
FLAPS 30
0
COND IT IONS:
TAKEOFF POWER
1900 RPM
INERTIAL SEPARATOR - NORMAL
ZERO WIND
NOTES:
1 . DO NOT EXCEED TORQUE LIMIT FOR TAKEOFF PER ENGINE TOROUE FOR TAKEOFF
CHART. WHEN ITT -EXCEEDS 765"C. THIS POWER SETTING IS LIMITED TO
5 MINUTES .
2 . WITH CLIMB POWER SET BELOW THE TOROUE LI~IT. DECREASE RATE OF CLIMB
BY 15 FPM FOR INERTIAL SEPARATOR IN BYPASS AND 45 FPM FOR CABIN
HEAT ON.
3. WHERE RATE OF CLIMB VALUES HAVE BEEN REPLACED BY DASHES. OPERATING
TEMPERATURE LIMITS OF THE AIRPLANE WOULD BE GREATLY EXCEEDED. THOSE
RATES OF CLIMB WHICH ARE INCLUDED BUT TH~ OPERATION SLIGHTLY EXCEED!
THE TEMPERATURE LIMIT ARE PROVIDED FOR INTERPOLATION PURPOSES ONLY.
PRESS
CLIMB
RATE OF CLIMB - FPM
WEIGHT
ALT
SPEED
40·e
KIAS
O°C 2O·C
LBS
FT
-20 C -10 C
970
7800
85
980
945
920
Sl
990
84
970
940
B45
2000
955
915
4000
B4
940
910
BB5
745
925
850
640
6000
83
910
895
880
BODO
B2
880
860
845
715
500
765
10000
81
840
580
365
825
79
705
440
12000
785
625
235
7300
84
SL
1110 1095 1085 1060 1035
2000
83
1085 1070 1060 1030
960
4000
lOllS
83
1055
1030 1000
860
6000
83
1030 101.5 1000
965
745
BODO
81
995
980
965
B25
600
10000
80
9110
880
465
960
685
79
12000
900
820
735
540
330
6800
83
12110 1225 1215 1190 1165
SL
2000
83
1215
1200 1190 1165 lOBS
4000
82
1190
1175 1160 1135
985
82
6000
1160 1145 1130 1100
865
BODO
BO
1125
1110
1095
955
715
10000
19
1075 10lD
805
570
1090
77
12000
9115
655
430
1030
855
Figure 5-33. Rate of Climb - Balked Landing
5-60
1 April 1998
For Training Purposes Only
(
(
(
(
CESSNA
MODEL 208 (675
SECTION 5
PERFORMANCE
SHP)
CARGO POD INSTALLED
TIME. FUEL. AND DISTANCE TO .CLIMB
HAXIMUM RATE OF CL1HB
CONDITIONS:
FLAPS UP
1900 RPM
INERTIAL SEPARATOR - NORMAL
NOTES:
1. TORQUE SET AT 1865 FT-LBS OR LESSER VALUE MUST NOT EXCEED MAXIMUM
CLIMB ITT OF 765°[ OR NG OF 101.Gr..
2. ADO 35 POUNDS OF FUEL FOR ENGINE START. TAXI. AND TAKEOFF ALLOWANCES.
3. DISTANCES SHDIolNARE BASED ON ZERO !oIINO.
II. IJITH INERTIAL SEPARATOR SET IN BYPASS. INCREASE TIME . FUEL. AND
DISTANCE NUMBERS BY 1% FOR EACH 2000 FEET OF CLIMB AND FOR CABIN
HEAT ON INCREASE TINE. FUEL. AND DISTANCE NUMBERS BY 1% FOR EACH
1000 FEET OF CLIMB .
5. WHERE TIME. FUEL. AND DISTANCE VALUES HAVE BEEN REPLACED BY DASHES.
AN APPRECIABLE RATE OF CLIMB FOR THE WEIGHT SHOWN CANNOT BE EXPECTED .
CLIMB FROM SEA LEVEL
20 DEG ( BELOW
STANDARD
20 DEC ( ABOVE
PRESS (LIMB STRNDARD TEI1P
TEMPERATURE STANDARD TEMP
All
WE IGHT
SPEED
TIHE FUEL DIST TIME FUEL OIST TIME FUEL DIST
FT
K)AS
MIN LBS NI1 MIN LBS NH MIN LBS NM
LBS
BODO
SL
107
0
a 0
0
0
0
0
0
0
lIODO
105
4
25
II
6
26
6
~
29
8
8000
12000
16000
20000
SL
103
99
95
91
87
107
1I000
8000
12000
16000
20000
211000
102
99
94
90
86
2aooo
7500
SL
700()
1I000
8000
12000
11)000
20000
211000
lOll
106
104
101
98
93
89
85
7
50
76
15 105
21 ll10
33 192
0
D
3
22
45
6
ID 69
14
911
19 124
28 165
12
19
28
17
110
26
62
0
5
42
11
7
17
10
25
35
52
15
0
20
41
62
85
0
5
10
15
22
31
19
illl
28
7
11
0
3
6
3
12
17
24
111
1114
13
311
52
80
113
156
226
0
23
46
72
100
136
186
0
3
0
21
6
9
III
42
0
5
10
611
17
89
119
157
25
37
55
12
0
3
22
21
33
50
83
O·
6
12
19
29
43
66
9
15
24
38
--
a
59
94
137
202
--
0
4
26
B
53
13
82
118
167
20
31
17
29
47
78
-
-
0
7
15
26
110
G2
-- -- --
0
3
7
12
18
26
1I2
0
23
117
171
162
152
151
175
169
160
150
149
173
167
158
149
1862
1700
1500
1300
12B5
1865
1700
1500
1300
1280
1865
1700
1500
noo
(
390
359
327
3ZZ
419
388
356
325
320
411
385
354
323
317
415
384
351
321
115
414
383
350
~~~
1600 RP"
FUEL
FLOW
424
396
365
335
325
422
393
362
332
320
419
390
359
329
315
1~9
1910
1800
1600
1400
1335
1970
1800
1600
1400
1315
1970
1800
1600
1400
1305
1910
1900
1600
1400
1290
1970
1800
1600
1400
1295
1970
1800
1600
1400
1280
1910
1900
1600
1400
1175
1910
1900
1600
~!~
~!~~
;!~
~~~
163
157
~16
386
35&
326
310
413
383
353
323
307
410
380
350
nD·
303
408
377
347
317
3DO
407
377
346
KTAS
PPH
1464
(
TORDUE
FT-LBS
PPH
1253
to
(
HAS
3D
20
(
1750 RP"
FUEL
FLOW
~O
(
(
SECTION 5
PERFORMANCE
IS3
170
1&3
154
151
175
169
lSI
152
149
173
167
159
151
146
171
165
158
149
144
169
1S3
IS6
147
142
167
161
154
145
140
165
159
152
144
138
163
157
150
142
1]6
162
156
149
141
35
1431
1430
1662
1500
1415
1880
1700
~500
405
1970
1800
1600
1400
1385
1970
1800
1600
1400
1380
1970
1800
1600
1400
1360
1970
IBOO
1600
1400
1345
1970
1800
1600
1400
1340
1970
1800
1600
1400
1325
IHO
1800
1600
1400
13ZD
1970
1800
1600
~~~~
335
335
365
341
330
395
367
~~~
405
319
349
32Z
320
401
375
346
318
315
397
312
343
315
309
393
369
339
311
304
390
365
336
J08
300
387
361
332
i~~
' 384
359
329
302
291
383
356
328
;~1
89
152
152
160
154
150
161,
160
~~~
168
162
155
146
146
161
161
153
145
144
165
159
152
143
142
IS3
151
150
142
i39
161
156
148
140
138
159
154
141
}38
35
157
152
145
131
133
156
151
144
}~~
Figure 5-36. Cruise Performance (Sheet 3 of 13)
1 April 1998
5-65
For Traininl! Purooses Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
CRUISE PERFORHANCE
PRESSURE ALTITUDE BODO fEET
CONOrTIONS.
8000 POUNDS
INERTIAL SEPARATOR - NOR"AL
REFER TO SHEET 1 FOR RPPROPRIRTE NOTES RPPLICABLE TO THIS CHART
190
TORQUE
H-Las
RP"
FUEL
FlOU
HRS
TORQUE
rT -Las
PPH
35
1146
324
156
25
1444
1300
1250
ISZ!!
1500
1300
1230
1814
l700
1500
1300
1230
1865
1700
1500
1300
1230
1965
1100
1500
1300
H2O
1865
1700
1500
1300
1205
1865
1700
1500
1300
1200
1865
1700
1500
1300
1205
1965
1700
1500
1300
1210
353
166
158
155
172
167
156
153
178
173
IS5
155
151
178
171
163
153
149
176
170
161
151
147
174
167
159
149
144
15
5
-5
-15
-25
-35
-<15
-54
~~~
381
360
3lS
311
413
390
357
325
314
421
389
355
323
312
419
387
353
321
308
417
385
350
319
304
415
383
348
316
301
413
382
345
314
300
412
380
344
313
298
In
165
157
148
142
169
163
155
145
140
167
161
153
144
139
1331
1305
1539
1400
_1300
173l
1600
1400
1290
1928
1800
1600
1400
1280
1970
1800
IS00
1400
1275
1910
1800
1600
1400
1255
1970
1800
1600
1400
1135
1970
1800
1600
1400
1230
1910
1800
1600
1400
1230
1970
1800
1600
1400
1225
750 RP"
FUEL
~~~U
KTRS
324
320
353
332
316
381
360
155
154
164
158
319
312
413
389
351
326
308
419
381
354
323
304
416
384
351
320
259
152
171
165
156
150
176
l1Z
164
155
148
176
170
162
153
147
174
169
160
151
144
~13
112
381
349
311
2g3
411
379
345
315
290
408
316
142
312
288
405
374
340
310
166
158
150
284
lQl
170
164
156
148
139
168
162
154
146
_138
ISS
160
152
144
136
1600 RPn
TORQUE
fUEL
FT -Las· ~~~~
1419
1380
1635
1500
1370
1835
1700
1500
1355
1970
1800
1600
1400
1345
1970
1800
1600
1400
1330
1970
1800
1600
1400
1310
1970
1900
IS00
1400
1295
1970
1800
1600
1400
1295
1970
1900
1600
1400
1280
1970
1800
1600
1400
12SS
KTAS
324
153
318
152
353
162
333
156
314
150
381
168
360
163
330
154
308
148
400 ' 171
37Z
165
341
157
312
148
305
146
397
169
368
163
339
156
309
141
299
144
393
161
' 162
364
335
15~
306
145
293
141
389
165
361
160
332
152
144
303
1]9
288
387
164
358
158
329
151
142
300
285
131
384
162
354
156
325
149
297
140
280
135
391
160
352
154
322
141
294
139
275
133
Figure 5-36. Cruise Performance (Sheet 4 of 13)
1 April 1998
5-66
For Training Purposes Only
J
(
CARGO POD INSTALLED
TE"P
OEG C
(
(
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
(
CRUISE PERFORHANCE
(
PRESSURE RLTITUDE 8000 FEET
(
CONOITI01IS.
8000 POUNDS
INERTIAL SEPARATOR ~ NOR"AL
REFER TO SHEET 1 FOR APPROPRIRTE NOTES RPPLICRBLE TO THIS CHART
(
(
(
(
.qon RPM
TEMP
OEG C TOROUE
FUEL
rT-LBS
nDW
PPH
lZ14
30
311
166
155
10
1569
1400
1200
1190
1140
1600
1400
lZ00
1175
1865
1700
1500
1300
1175
1865
1700
1500
364
336
304
302
396
368
334
302
Z98
419
386
348
316
296
417
395
346
In
~~~~
;~~
1865
1700
1500
1300
1170
1865
1700
1500
1300
1160
415
383
344
311
290
413
391
342
309
287
0
-10
-20
(
(
lZ96
1260
1495
1300
1250
1667
1500
1300
1250
1849
1100
1500
1300
1235
1970
1800
1600
339
307
(
(
157
1395
1205
(
(
FT -LBS
2D
(
(
TOROUE
KrRS
-3~
(
-40
(
(
164
153
153
178
17Z
163
151
150·
181
175
166
156
149
179
172
164
154
147
177
170
162
152
145
174
169
160
150
142
-50
(
(
-54
(
(
1865
1700
1500
1300
1160
1865
1700
1500
1300
1165
410
379
341
307
286
410
378
341
306
Z86
172
166
157
149
140
171
165
157
147
140
FLDW
PP"
311
305
339
309
301
3G~
337
306
298
396
358
334
303
294
411
385
34B
121
1970
1800
1600
14~~
3~:
Z8
414
392
345
~~~~
;~~
1970
1800
1600
1400
1200
1970
1800
1600
1400
~200
411
380
342
310
Z81
409
115
(
1750 RPIt
FUEL
1970
IBoD
1600
1400
1200
11An
1910
1800
1600
1400
1200
1180
377
340
308
279
275
41lS
3N
338
3115
276
27~
4114
373
337
304
~75
7Z
KrRS
156
15~
164
155
152
171
16~
153
51
176
171
162
152
148
179
173
165
156
146
177
171
163
154
144
175
169
161
152
141
172
167
159
150
140
139
170
164
157
148
138
137
169
164
156
147
137
1'6
TORQUE
FT -LBS
1381
1335
1577
1400
1325
1765
1600
1400
1310
1954
1800
1600
1400
1290
1910
1900
1600
1400
1210
1970
1800
1600 RPH
FUEL
~~OW
PH
311
304
338
311
299
364
338
308
295
396
367
334
305
299
396
364
331
302
284
392
360
328
KTAS
154
151
162
153
1119
IG8
1400
1260
1970
lBoO
1600
1400
388
358
325
296
U50
275
1970
1900
1600
395
35.5
322
293
271
161
152
I'll
1"73
168
160
151
IllS
172
166
158
1119
1113
1"70
164
156
148
14'
168
162
155
146
139
166
160
153
144
137
382
352
319
290
266
164
159
151
143
135
381
352
318
299
264
163
159
150
I'll
134
HOD
HOD
1Z45
1970
1900
1600
HOD
1235
1970
1800
1600
1400
1225
233
279
Figure 5-36. Cruise Performance (Sheet 5 of 13)
5-67
1 April 1998
For Traininl! Purooses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
CRUISE PERFORHANCE
PRESSURE ALTITUDE 10000 FEET
CONDITIONS.
8000 POUNDS
INERTIAL SEPARATOR - NORKRL
REFER TO SHEET 1 FOR RPPROPRIRTE MOTES RPPLICRBLE TO THIS CHRRT
1E~P
OEG C
25
15
5
-5
- 15
-25
-35
-~5
-5~
TOROuE
fT -LOS
1181
1115
1343
1200
1170
1506
1400
1200
1155
1663
1500
1300
1150
1900 RPn
FUEL
FLOW
KTAS
PPH
157
298
291
157
322
166
299
157
294
155
349
173
167
329
291
155
290
153
319
178
3~6
171
311
160
286
151
1806
1700
1500
1300
1145
405
384
345
309
283
182
118
169
158
149
1865
1100
1500
1300
1135
415
382
182
\15
1865
1100
1500
1300
1135
1865
1100
1500
1300
1130
1865
1700
1500
1300
1125
3~3
lin
307
Z80
156
141
412
380
342
180
173
165
154
145
30~
218
411
318
3~0
302
216
410
377
339
301
213
111
171
162
152
143
175
169
160
151
141
TOROUE
f1-Las
1260
lZ15
1430
1300
1205
1601
1400
1210
175D RPn
FUEL
FLOII
PPH
298
291
322
302
281
349
315
,00
KTAS
156
153
164
157
152
171
285
161
150
1167
1600
1400
1200
,379
176
1919
1800
1600
1400
1200
J190
1910
1800
1600
1400
1200
1115
1910
180G
1600
'1'100
1200
1160
191G
1800
1600
140G
1200
1150
1910
IBOG
1600
1'100
1200
1145
405
383
345
310
219
211
412
380
342
306
Z16
212
410
378
340
304
214
268
401
3~1
16~
312
281
159
148
315
337
301
212
264
405
31.
336
299
210
261
180
175
167
158
141
146
180
TORQUE
FT -LOS
1341
1290
1517
1400
1290
1694
1500
1300
1280
1865
1100
1500
1300
1255
1910
1800
1600
1400
1240
RP~
FUEL
FLOW
PPH
298
KTAS
313
204
211
395
363
326
296
272
153
150
161
155
149
168
159
149
148
173
166
158
141
145
175
169
160
151
143
173
161
159
150
140
290
322
304
201
349
316
291
283
319
341
17~
197G
180G
165
156
145
1400
1215
391
359
323
293
266
191G
18GG
1600
1400
UOO
388
356
3Z0
290
261
111
165
157
148
138
38~
1~2
1910
1800
160G
1400
1200
353
318
287
258
169
163
155
147
136
139
113
161
160
151
140
137
197G
laOG
1600
1'100
1200
1190
380
351
316
284
256
254
161
161
154
145
135
134
limo
1~~
177
111
163
15~
144
141
175
169
161
153
Figure 5-36. Cruise Performance (Sheet 6 of 13)
5-68
1 April 1998
ForTraining Purposes Only
(
CESSNA
MODEL 20B.(675 SHP)
(
(
(
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
(
CRUISE PERFORHRNCE
PRESSURE ALTITUDE 12000 FEET
(
CONDITIOIIS.
(
8000 POUNDS
INERTIRL S£PRRRT1IR - NDR"RL
REFER TO SHEET 1 FOR RPPRoPRIATE NOTES RPPLlCRBLE TO THIS CHART
(
fg[jji RPK
TEKP
(
OEG C TOR DUE
KTRS
rr -lBS
157
1213
170n
1368
1195
750 RPK
FUEL
FLolI
PPH
284
'87
306
279
lORQUE
(
20
1137
FUEL
FlOII
PPH
284
(
10
1285
1155
306
285
165
157
(
0
1435
1300
1145
333
301
281
112
164
154
1525
t400
333
310
!~~~
~?7
75
-10
1583
1400
1200
IB5
1106
1600
1400
1200
1125
1828
1100
1500
1300
1115
361
325
289
177
361
326
323
281
274
408
380
341
302
271
181
176
166
155
150
184
119
170
159
148
1681
1500
1300
U8!;
1812
liDO
1500
1300
1165
IS41
1800
1600
1400
1865
1100
1500
1300
1105
415
379
339
300
261
183
176
167
157
145
1865
1700
1500
1300
1110
413
180
174
165
155
rr - LBS
(
(
(
-20
(
(
( -
,
-30
l·
"-
(
(
-40
(
(
-50
(
(
-54
(
(
1865
1700
1500
UOO
1105
(
Z7A
384
363
377
33B
299
266
412
376
331
299
264
188
i~~
1~4
IBD
173
16Q
154
143
~;~
384
363
324
288
267
408
379
341
303
155
154
163
153
170
164
~~~
175
167
157
i5n
179
174
165
155
147
181
176
168
159
~;~~
~~~
~:~
1970
1800
1600
41Z
376
339
300
26B
260
410
374
336
299
266
255
409
373
335
298
265
253
lBO
174
166
157
14.
143
178
1~00
1200
IlSO
1910
1800
1600
1~00
!~~g
1970
1800
16DO
1400
!200
125
RPK
FUEl
1I;0~
KTRS
172
164
155
144
I ~O
177
171
163
154
143
139
TORQUE
FT-LBS
!~~~
1450
1300
1275
1614
1500
~:~~
1776
1600
1400
174n
1912
1800
1600
1400
1725
IS70
1800
1600
1400
1205
FLOII
KTRS
PPH
284
781
306
283
279
333
311
280
273
361
327
293
769
383
160
152
ISO
161
162
151
148
172
165
362
324
290
264
391
359
3Z1
297
258
1970
1800
1600
3BB
355
319
1~00
28~
}~~
~~~
176
111
163
153
14<1
176
169
161
152
141
17<1
161
159
150
139
1195
25~
1910
1800
1600
1400
lZOO
1180
1970
1800
1600
1400
1200
1175
385
352
317
28Z
112
IGS
158
~52
138
137
49
383
351
316
280
251
247
1~9
171
165
157
148
137
136
(
(
(
(
.
~ ~..
';'~~-j
Figure 5-36. Cruise Performance (Sheet 7 of 13)
5-69
1 April 199B
For Trllininp Purnoses Onlv
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
CARGO POD INSTALLED
CRUISE PERFORMRNCE
PRESSURE RLTITUDE 14000 FEET
CONDlnONS.
8000 POUNDS
INERTlRl SEPRRRTOR - MORltRl
REFER TD SHEET 1 FOR RPPROPRIATE NOTES IIPPLICIIBLE TO THIS CHIIRT
TEHP
OEG C roROUE
FT -L9S
1900 AP"
FUEL
FLOW
PPH
no
KIRS
087
1226
1150
1363
1200
. 1135
1495
1300
1120
291
278
317
284
273
342
303
269
176
165
154
-25
1606
1500
1300
1115
362
341
301
266
180
174
164
151
-35
1721
1600
1400
1200
1100
386
359
319
280
262
182
177
167
156
149
1159
1304
1185
1449
1300
l' 7[)
1589
1400
1200
1165
1101
1600
1400
1200
1160
1827
1100
1500
1300
1150
-45
1844
1700
1500
1300
1100
1080
1865
1100
1500
1300
1100
1080
410
380
337
298
260
251
412
379
33G
297
259
256
185
119
110
160
141
146
184
171
1GB
158
145
U4
1957
1800
1600
1400
1200
1135
1970
1800
1600
1400
!ZOO
1120
15
5
-5
-15
-54
L55
164
159
171
161
IORQUE
FI-lBS
l56
1750 RP~
FUEL
FLOW
PPH
270
291
271
317
~::
342
305
'.
269
263
362
342
303
266
260
386
359
320
282
251
410
319
337
299
263
252
410
316
335
297
2£0
248 '
KTRS
153
IS2
154
169
ISO
152
174
ISS
153
150
117
113
IS3
151
49
180
175
16&
156
141
193
177
169
159
148
1'14
181
115
161
158
14£
141
10ROUE
FT-LBS
1600 RPH
FUEL
~~~N
KIRS
50
159
151
166
1678
1500
1300
1235
1801
1600
1400
1215
270
290
271
317
291
2&7
342
308
272
262
362
324
296
257
171
162
151
141
174
165
155
145
1927
1800
1600
1400
1200
1190
1970
1800
1600
1400
1200
1180
1970
1800
386
359
320
284
253
251
392
356
318
282
250
246
388
353
111
17Z
164
154
142
142
111
110
162
152
141
140
175
168
IGOO
31S
ISO
1400
1200
1170
Z80
247
243
151
140
138
1232
1383
1260
1533
~~~~
!~~
Figure 5-36. Cruise Performance (Sheet 8 of 13)
5-70
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
CRUISE PERFORHANCE
PRESSURE ALTITUDE 16000 FEET
CONDITIONS.
POUNDS
aooo
INERTIRL SEPRRRTOR - NDRKAL
REFER TO SHEET 1 FOR RPPROPRIRTE NOTES RPPLICABLE TO THIS CHRRT
TEMf
OEG C
10
0
-10
-20
-30
-40
- 50
- 54
TORQUE
FT-LBS
1040
1168
1125
1292
1110
LSOO RP"
FUEL
FLOW
PPH
256
277
26S
301
265
HRS
1~3
162
159
169
157
140.
1300
1110
150B
1400
1200
1085
1611
1500
1300
1100
1010
1130
1600
1400
1200
1045
322
301
263
342
319
219
256
365
33B
298
259
25Z
386
359
316
277
241
174
168
155
178
160
152
1Bl
175
164
151
\49
184
179
169 .
156
145
1729
1600
1400
1200
1035
395
358
315
271
244
183
177
167
155
144
In
lORQUE
FT-LBS
1 09
1243
1195
1373
1200
1165
1493
1300
11.0
1602
1400
1200
1145
1715
·1600
1400
1200
1125
IUS
1100
1500
1300
1115
1934
1700
1500
1300
1110 .
150 RP"
FUEL
FLOW
PPH
256
211
266
301
261
260
322
284
257
341
302
263
253
364
339
300
262
248
386
359
317
219
244
384
358
316
Z1B
242
KTRS
151
160
156
167
156
153
172
161
152
175
165
153
150
179
174
164
152
147
181
176
167
156
145
180
115
166
156
143
bon RPM
FUEL
FLOW
PPH
1111
256
1311
Z71
1260
267
1'452
300
Z71
1300
1245
261
1517
3Z2
ZBB
1400
1235
257
341
1691
304
1500
1300
266
1210
251
364
1810
1700
340
1500.
301
1300
265
246
1190
1935
385
359
1800
1600
317
1400
281
245
1200
241
1180
1934
383
357
1900
1600
316
1400
290
244
1200
237
1160
TORQUE
Fl-LBS
KTRS
141
151
153
164
154
151
169
159
149
112
163
15Z
146
115
111
llil
151
144
179
113
164
1511
143
142
171
172
163
154
142
140
Figure 5-36. Cruise Performance (Sheet 9 of 13)
5-71
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
(
CRUISE PERFORHANCE
(
PRESSURE ALTITUDE 18000 FEET
CONDITIONS.
8000 POUNDS
INERTIftL SEPRRATOR - NOR"Rl
REFER TO SHEET 1 FOR APPROPRIfiTE NOTES APPLICABLE TO THIS CHRRT
TE"P
DEC [
1900 RPM
FUEL
rt-LBS
FLOW
TDRDUE
1750 RPM
FUEL
FT -LBS
FLOW
KfAS
5
-5
-15
993
1109
1075
1223
1100
-25
1060
1319
1200
-35
-45
-54
1060
1412
1300
1100
1035
1511
1400
1200
1015
1560
1400
1200
995
KTAS
FT -LBS
PPH
PPH
2q3
2&3
256
285
260
252
303
27S
251
321
298
258
245
342
318
276
240
350
316
275
235
TORIlUE
lDRDUE
1600 RPM
FUEL
FLON
KTAS
PPH
150
160
157
167
158
154
172
1058
1119
1140
1299
1120
243
263
255
295
250
147
157
154
165
152
1 23
1250
1225
1374
1205
741
263
258
285
252
1401
164
1200
153
176
169
155
150
179
173
161
146
179
171
159
143
1105
1500
1300
1095
303
264
245
321
281
241
1&9
157
150
173
162
147
1603
1400
1200
1015
1653
1500
1300
1100
1010
342
299
2GO
23&
350
318
211
240
234
176
1&6
154
145
1481
1300
11'10
1584
1400
1200
1170
1694
1500
1300
1150
1745
1600
1400
303
2&9
247
321
284
247
242
342
301
177
170
159
145
lq3
~~g~
43
154
151
161
149
16&
155
349
319
280
244
141
170
160
147
145
113
164
153
142
l1q
161
151
145
231
140
;;~
(
(
(
(
(
(
(
(
(
Figure 5-36. Cruise Performance (Sheet 10 of 13)
5-72
1'April 1998
For Training Purposes Only
{
(
CESSNA
MODEL 208 (675 SHP)
(
CARGO POD INSTALLED
CRUISE PERFORHANCE
(
(
(
SECTION 5
PERFORMANCE
PRESSURE
COIIO IT lOllS I
7500 PDUIIDS
[NEIITIRL SEPRIIRTDII -
ALTITUDE 20000 FEET
~ORIML
REFEII TO SHEET 1 FOR APPROPRIRTE NOTES RPPLlCRBLE TO THIS CHRRT
(
TEKP
DEG C
(
(
(
{
(
0
-10
- 20
9~2
1900 RPK
FUEL
FLOW
PPH
229
10~1
2~9
990
1150
100S
238
268
239
-30
1136
IB4
-40
1100
990
1322
1200
1000
257
235
301
276
236
225
321
296
255
222
319
296
254
220
(
9~5
-50
(
(
TOROUE
FT -lBS
-54
(
1414
1300
1100
935
140B
1300
1100
925
HRS
lSI
160
155
167
155
172
162
153
175
167
152
1750 R?K
FUEL
FLOW
PPH
1003 .
229
TOROUE
FT -lBS
1I1~
2~9
1050
1222
1100
1035
1312
1200
1020
236
26B
1~0~
1100
1010
2~5
231
184
262
227
102
261
224
KTAS
1~5
1499
1300
1100
990
171
171
158
143
149~
320
Z7B
239
21B
liB
1300
1100
1000
239
220
112
ISS
211
1600 RP"
FUEL
flOW
KTRS
PPH
1~8
10S~
229
1~4
158
153
165
156
150
169
162
148
173
161
146
1180
1130
1293
1110
2~9
239
269
233
154
150
161
148
1~7
178
TORQUE
FT -l9S
176
165
152
143
175
164
151
143
1388
1200
1100
I~B3
1300
1100
1075
1582
1400
1200
1060
1579
1~00
1200
1050
284
24B
229
302
265
227
223
320
281
24~
21B
31B
280
243
216
166
154
145
170
159
145
1~3
173
163
151
140
172
162
150
140
{
(
(
(
(
Figure 5-36. Cruise Performance (Sheet 11 of 13)
1 April 1998
5-73
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
CRUISE PERFORMANCE
(
PRESSURE RLTJTUDE 22000 FEET
CONonIOIIS.
'1000 POUNDS
INERTIRL SEPARRTOR - NOR"RL
REFER TO SHEET 1 FOR RPPROPRIATE NOTES RPPLlCRBLE TO THIS CHRRT
TOROUE
Fr-lBS
-25
-35
-4S
-54
KTRS
TORQUE
Fr-lBS
PPH
PPH
-5
-15
1751) RPn
FUEL
HOH
. BBB
9B4
925
1073
925
16
234
. 222
251
221
152
161
155
167
154
94:;
1046
975
1141
1000
950
1153
1000
910
1234
1100
900
860
1269
1100
900
B70
266
235
211
283
254
214
206
290
253
213
207
111
159
151
175
166
147
144
115
164
141
144
IllS
1100
9AO
1311
1200
1000
925
1347
1200
1000
915
15
234
219
251
223
214
266
241
210
283
259
220
206
289
258
219
203
1600 RP"
FUEL
fLOH
KrRS
PPH
49
15B
152
IS.5
153
149
169
160
147
173
166
151
144
173
164
149
142
1003
1109
1045
1208
1100
1035
1296
1100
1010
1387
12DO
1000
9SO
142S
1300
1100
970
(
(
CARGO POD INSTALLED
1900 RP"_
TE"P
OEG C TOR DUE
FUEl
rT -LBS
HOH
KrRS
(
Z15
234
221
251
230 .
211
266
227
211
283
244
20B
20S
289
262
224
201
4:;
155
149
161
153
141
166
152
144
169
158
142
141
170
163
149
139
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
Figure 5-36. Cruise Performance (Sheet 12 of 13)
5-74
1 April 1998
For T raining Purposes Only
(
(
(
CESSNA
MODEL 208 (675 SHP)
(
CARGO POD INSTALLED
(
CRUISE PERFORHANCE
PRESSURE ALTITUDE 24000 FEET
(
(
(
(
(
{
(
CONDITIONS.
6600 POUNDS
INEATIAL SEPAAATOR - NORMAL
REFER· TO SHEET 1 FOR RPPROPRIATE NOTES APPLICRBLE TO THIS CHRRT
TEMP
1900 RPM
FUEL
OEG C TORQUE
Fl-LBS
FLOW
PPH
-10
936
203
-20
925
220
855
Z06
-30
IDOl
235
860
205
-40
(
(
SECTION 5
PERFORMANCE
-50
1750 RPM
KIRS
153
162154
167
153
1076
900
915
1151
1000
805
249
213
196
265
Z3Z
193
171
156
141
175
163
144
1144
1000
905
263
232
192
173
163
144
(
-54
(
( ('
t
( ~
TORQUE
F)-LBS
990
994
890
1066
900
880
1143
1000
810
1222
1100
900
850
1216
1100
900
810
FUE~
FLOII
PPH
2 3
ZZO
lOl
l35
202
198
249
220
195
265
Z38
199
190
263
238
199
ill
KIRS
151
159
150
165
150
148
169
159
146
17Z
164
148
143
171
164
141
144
1600 RPH
FUEL
FLOW
PPH
945
203
1043
2Z0
970
205
l34
1129
1000
209
950
ZOO
1210
249
1100
227
930
195
264
1Z92
ZZ4
1100
910
190
TOROUE
FT -LBS
1Za8
1100
900
263
2Z4
187
KTRS
146
156
148
161
151
146
166
158
143
169
156
140
168
156
139
(
(
(
(
(
(
(
(
(
(
(
Figure 5-36. Cruise Performance (Sheet 13 of 13)
5-75
1 April 1998
For Training PUrposes Only
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
(
CARGO POD INSTALLED
FUEL AND TIME REQUIRED
MAXIMUM CRUISE POWER (40 • 200 Nautical Miles)
(
CONDITIONS :
BOOO Pounds
1900 RPM
Inertial Separator - Normal
Standard Temperature
(
NOTES :
1.) Fuel required includes the tuel used tor engine slart, ta xi, takeoH, maximum climb trom sea tevel, descen t 10 sea
tevel and 45 minutes reserve. Time required includes the time during a maximum climb and descent.
2.) With inertial separator in BYPASS or cabin heat on, increase lime by 3% and tuel by 2%.
12 00
~\..
1000
~
~
'O
J:
W
3
~/.~
(
~
o
-
~
2
1-- -1-1-
69
--
I!? ~40
0'"
z c
'" <
, ~20
II
r-t-
V
.I
I~
/
II
I
I ...
/'OJ
60
1/
II
~/I "
"'I
'0
/
II
V
V
1/
1.1
1/
1/
V
IL
V
I~
V
DISTANCE - NAUTICAL MILES
Figure 5-37. Fuel and Time Required - Maximum Cruise Power
200 - 1000 Nautical Miles (Sheet 2 of 2)
1 April 1998
5·77
For Trllininll Purnoses Onlv
SECTION 5
PERFORMANCE
CESSNA
MODEL 208 (675 SHP)
(
CARGO POD INSTALLED
FUEL AND TIME REQUIRED
MAXIMUM RANGE POWER (40 - 200 Nautical Miles)
CONDITIONS:
8000 Pounds
1900 RPM
Inertial Separator· Normal
Standard Temperature
NOTES:
(
1.) Fuel required includes the luel used lor engine start, taxi, takeoff, maximum climb from sea level, descent to sea
level and 45 minutes reserve. Time required includes the time during a maximum climb and descent.
2.) With inertial separator in BYPASS or cabin heat on, increase lime by 3% and fuel by 2%.
(
(
(
18111111
~f?"
"'~
AIJ;;
~fl110
(
IIIQlI'
V
I-'""
;:;j61l0
=>
I-'""
...
...
V
"",P'
k
"=I;:::P'"
~ZOOO
P
all0
1.1
20121
(
120
,00 "'
!:i
w
O~S
"'~
15e
(
140
!
\.."1\"1~
-
1-
80
2
~
60
w
::!!
;::
40
1.0>'
....
(
:.-J
,6.r§IJ
20
(
(
-- P
(
1/
,.
(
(
1/
!-
(
V
·!-I:t;·
--
t-.
I'!I
V
1/
...
(
611
DISTANCE· NAUTICAL MILES
(
Figure 5-38. Fuel and Time Required - Max Range
40 - 200 Nautical Miles (Sheet 1 of 2)
5-78
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
(
SECTION 5
PERFORMANCE
CARGO POD INSTALLED
FUEL AND TIME REQUIRED
(
(~
(
MAXIMUM RANGE POWER (200 -1000 Nautical Miles)
CONDITIONS:
8000 Pounds
1900 RPM
Inertial Separator - Normal
Standard Temperature
NOTES:
(
1.) Fuel required Includes the luel used for engine start, taxi, takeoff, maximum climb from sea level, descent to sea
level and 45 minutes resorve. Time required includes \he lime during a maximum climb and doscent.
2.) Wilh inertial separalor in BYPASS or cabin heal on. increase lime by 3% and luel by 2%.
(
(
ZUII'"
(
(
~
(
/'
IL
(
I
/'
V
B00
7
b
~...
~
(
(
~r-'1
~I2"'11J
(
1
V
:;-
(
(
.
~~-Sj..I-1-~ IL 0/ /
~'t,
\f'~ ~~
~r- J()'
\~~ ()
~ 'l-()'
"
IV
IT
400
5g?
:;)
o
'"
~
i{c;,
(
6
L.
4:1:
w
I~ \:}0
V
II
II
V
I
'"
10,
1;/
V
1/
1./
17
1/
1/
V
1/
V..il
~/I~
I""
II
I
1/
It!
IW
V
If
V /
DISTANCE - NAUTl~AI.. HII..ES
Figure 5-38. Fuel and Time Required - Max Range
200 - 1000 Nautical Miles (Sheet 2 of 2)
1 April 1998
5-79
For Trainin~ Purooses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
(
(
CARGO POD INSTALLED
(
RANGE PROFlLE
45 MINUTES RESERVE
2224 LBS USABLE FUEL
(
NOTES:
CONDITIONS:
(
1. 'This chart allows for the fuel used for engine start,
taxi, takeoff, climb and descent. The distance
during a'maximum climb and the distance during
descent are included.
8000 Pounds
1900 RPM
Standard Temp
Zero Wind
Inertial Separator. Normal
2. With the inertial separator in BYPASS or cabin heat
on, decrease range by 2% .
25000
(
(
111111
IIII III
IIII II r
15M~~S
'65 KTA
(
153 KTAS
(
21i!000
173 KTAS
I-
W
W
I.J..
(
150 KTAS
!t)
1::1000
{
if
;'
r
III
::::J
0.
-i
"I
:i-
to
S-
0
en·
Q
~
ill
::::J
"I
=
"
"
:l
en
~
~
0
(l)
!II
:T
:s
(l)
2~
SP~£D
WEIGHT
LBS
7800
1. Short~fi~le~ld~tec~hn~i~qu~e~a~s~sp~e~c~ffi~ed~in~Soc~ti~0-n~4-.----~-------------------------2 . Decrease distances 10% for each 11 knots headwind. For operation with tailwinds up to 10
knots. increase distances by 10% for each 2 .5 knots.
3. For operation on a dry. grass runway. increase distances by 40% of the "ground roll" figure.
4. If a landing with flaps up is necessary, increase the approach speed by ·'5 KIAS and allow
for 40% longer distances.
.
5. Use of maximum reverse thrust after touchdown reduces ground roll by approximately 10%.
6 . Where distance values have been replaced by dashes. operating temperature limits of the
airplane would be greatly exceeded. Those distances which are included but the operation
slightly exceeds the temperature limit are provided for Interpclation purposes only.
O'C
~ 1O'C
KIAS
PRESS
AU
FT
78
S.l.
AT
50 FT
1000
2000
3000
4000
5000
6000
7000
8000
9000
10.000
11.000
12.000
1\)>
0
NOTES:
CONDITIONS: .
Aaps 30·
Power lever - Idle after clearing
obstacles, BET A range (lever
against spring) after
touchdown.
Propeller Control lever - MAX
Maximum Braking
Paved, level, Dry Runway
Zero Wind
Cargo Pod Installed
5·
:II
oen
men
,z
MAXIMUM WEIGHT 7800 LBS
SHQRT FIELD
-'(0
(0
"I
S':o
Om
LANDING DISTANCE
"0
GRD
ROLL
FT
650
670
695
725
750
780
810
· 840
875
905
945
980
1020
1O'C
20'C
50 FTOBS
GRO
ROll
FT
TOTAlFT
TO CLEAR
50 FT08S
GRO
ROll
FT
TOTAL FT
TO CLEAR
50 FTOBS
GRO
ROLL
FT
TOTAL FT
TO CLEAR
50 FT OBS
GRO
ROlL
FT
TOTAL FT
TO CLEAR
50 FTOBS
GRD
ROll
FT
TOTAL FT
TO CLEAR
50 FTOBS
1500
1540
1580
1620
1665
J710
1755
1805
1855
1910
1965
2020
20BO
675
700
725
750
780
810
840
870
905
940
980
1020
1060
1540
· 1580
1620
1665
1710
1755
1805
1855
1905
1960
2015
2075
2135
700
725
750
780
810
840
870
905
1580
1620
1665
1710
1755
1805
1850
1905
1955
20 15
2070
2130
2195
720
750
775
805
835
870
900
935
975
1620
1660
1705
1750
1800
1850
1900
1955
2010
2065
2125
2185
2250
745
775
805
835
865
900
930
970
1005
1045
1085
1130
1175
1660
1705
1750
1795
1845
1895
1945
2000
2060
2115
2180
2240
2310
770
800
830
1700
1745
1790
1835
1885
1940
1995
2050
21 0 5
TOTAL FT
TO CLEAR
940
975
1015
1055
--l OSS
lOla
1050
1090
1135
860
895
925
965
1000
1040
-
-
-
m
.......
01
en
0
J:
~
>
:u
C)
0
4O'C
30'C
en
_.
-
--
-
."
0
0
Z
en
~
rr-
m
0
-u
m
:D
"en
Om
:Do
.
(1l
(X)
w
~-l
»zO
2
0
m
U'l
U1
""O(/)
I
co
.J::>.
cO'
co
U1
~
~
.,
Q
I\)
.,-l
WEIGHT
lBS
7300
SPEED
AT
SOFT
KIAS
75
r-
I>l
Q)
S·
:J
E:i"
0.
S·
IJCI
<0
~
.,=
0
Q
S"
II>
~
II>
:J
0
n
co
«"
CJj
:I
'::J
co
co
I \)
9-
~
»
-0
~
to
to
co
7300 LBS AND 6800 LBS
SHORT FIELD
:DO
6800
72
- 1O"C
PRESS
'"T1-i
0-
GAD
ROLL
FT
O'C
10'C
20'C
3O'C
TOTAL FT
TO CLEAR
50 FTOBS
GAD
ROll
FT
TOTALFT
TO ClEAR
50 FTOBS
GAO
ROll
FT
TOTAL FT
TO CLEAR
50 FT OBS
GAO.
ROll
FT
TOTAL FT
TO CLEAR
SO FTOBS
10,000
11 ,000
12,000
610
630
655
680
705
730
760
785
820
8[;0
885
920
955
1430
1-465
1505
1545
1585
1625
1670
1715
1765
181!;
1865
1920
1975
630
655
680
705
730
760
785
815
850
880
915
955
990
1465
1505
1545
15B5
1625
1670
1715
1765
1815
186[;
1915
1970
2030
655
680
705
730
755
785
815
845
880
915
950
990
1030
1505
1545
1585
1625
1670
1715
1760
1810
1860
1915
1970
2025
2085
675
700
730
755
785
815
845
875
910
945
985
1025
1065
1540
1580
1625
1665
1710
1755
1805
1855
1910
1960
2020
2075
2140
S.L.
1000
2000
3000
4000
5000
6000
7000
aooo
9000
10,000
11,000
12,000
565
585
605
630
655
680
705
730
760
790
820
855
890
1360
1395
1435
1470
1510
1550
1590
1635
1680
1725
1775
1825
18BO
585
610
630
655
680
705
730
760
790
820
850
885
920
1400
1435
1470
1510
1550
1590
1635
1680
1725
1775
1825
1875
1930
610
630
655
680
705
730
760
785
820
850
885
920
955
630
650
675
700
730
755
785
a15
B45
880
915
950
990
1470
1505
1545
1585
1630
1675
1720
1765
1815
1865
1920
1975
2035
AlT
FT
S.L.
1000
2000
3000
4000
5000
6000
7000
8000
gOOD
00'
"C
:DC)
s::Z
»U1
Z
()
REFER TO SHEET 1 FOR APPROPRIATE CONDITIONS AND NOTES
"'Tl
t:
....
mm
LANDING DISTANCE
'-
1435
1470
1510
1550
1590
1630 ,
1675
1725
1770
1820
1870
1925
1980
-
GRD
ROll
FT
I
700
725
755
780
810
B40
875
905
4O'C
TOTAL FT
TO ClEAR
SO FT OBS
980
1020
1060
1100
1580
1620
'1660
1705
1755
1800
1850
1900
1955
2010
2070
2130
2190
650
675
700
725
755
780
810
845
875
910
945
985
1025
1505
1545
1585
1625
1670
1715
1760
1810
1860
1915
1970
2025
20B5
940
GRD
ROll
FT
725
m
TOTAL FT
TO CLEAR
50 FT OBS
750
780
805
835
870
900
935
975
1615
1655
1700
1745
1795
1845
1895
1945
2000
:lJ
G>
0
-._.
.-
(J)
670
695
725
750
780
810
840
870
905
1540
1580
1620
1665
1710
1755
1805
1855
1905
_.
-.
_.-
-
...
_.-.
_.
-
-
'-
-.
0
~
"1:1
0
0
z
-4
l>
r
r
m
0
s::
°
CJ
r
m
I\)
0
CO
~()
(}'1m
en(/)
:::r:(/)
Z
-u
-»
SECTION 6
WEIGHT & BALANCE/
. EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
(
"
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
'\
(
(
(
TABLE OF CONTENTS
Page
Introduction ......................................
Airplane Weighing Procedures
.... ...... ........... ..
Weight And Balance . . . ......... .. .. ...... ... . . . ...
Weight And Balance Platter ... ... .. . ..............
Crew/Passenger Loading ........... . .... . ......... .
Baggage/Cargo Loading ......... ... .. . . ... . ... . . . .
Cabin Area .. .. .... . ... . .. ... . . ... . ... . ..... . .
Maximum Zone/Compartment Loadings ...... ........
Cargo Pod . ... . .. . . . . . . .. . . . .. . .. .......... . .
Center Of Gravity Precautions .. .. .................
Cargo Load Restraint .............................
Prevention Of Movement . ....... .. . ........ . .....
Loading Of Piercing Or Penetrating Items
.... ...... ..
Transportation Of Hazardous Materials
... ........... ..
Equipment List .. ..... . ... . .... ..... .. . ..........
6-3
6-6
6-8
6-11
6-11
6-12
6-12
6-17
6-18
6-18
6-19
6-19
6-21
6-21
6-21
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6-1/6-2
1 April 1998
For Traininl! Purooses Onlv
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For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
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INTRODUCTION
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SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
This section describes the procedure for establishing the basic
empty weight and moment of the airplane. Sample forms are
provided for reference. Procedures for calculating the weight and
moment.for various operations are also provided.
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In order to achieve the performance and flight characteristics which
are designed into the airplane, it must be flown with approved
weight and center of gravity limits. Although the airplane offers
flexibility of loading, it cannot be flown with full fuel tanks and a full
complement of passengers or a normal crew and both cabin and
cargo pod (if installed) loading zones filled to maximum rapacity ..
The pilot must utilize the loading flexibility to ensure the airplane
. does not exceed its maximum weight limits and is loaded within the
center of gravity range before takeoff.
Weight is important because it is a basis for many flight and
structural characteristics. As weight increases, · takeoff speed must
be greater since stall speeds are increased, the rate of acceleration
decreases, and the required takeoff .distance. increases. Weight in
excess of the maximum takeoff weight may be a contributing factor
to an accident, especially when coupled with other factors such as
temperature ~ field elevation, and runway conditions, all of which may
adversely affect the airplane's performance. Climb, cruise, and
landing performance will also be affected. Flights at excess weight
are possible, and may be within the performance capability of the
airplane, but loads for which the airplane was not designed may be
imposed on the structure, especially during landing.
The pilot should routinely determine the balance of the airplane
since .it is possible to be within the maximum weight limit and still
exceed the center of gravity limits. An airplane loading which
exceeds the forward center of gravity limit may place heavy .Ioads
on the nose wheel, and the airplane will be slightly more difficult to
rotate for takeoff or flare for landing. If the ·center of gravity is too far
aft, the airplane may rotate prematurely on takeoff, depending on
trim settings.
6-3
1 April 1998
1{or TrSlininp Pnrnoses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
MODEL 208
CARAVAN I
WEIGHT AND
BALANCE DATA
_ _ _ _ _ _ REGISTRATION NUMBER _ _ _ _ _ __
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AIRPLANE WEIGHING FORM
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CARGO POD REMOVED
FOR CLARITY
AFT JACK POINT· Fa 207.44
(WITHOUT CARGO POD INSTAlLED· AT LH ANO RH
ilL 23." WITHIN IAAIN GEAR FAIRING OPENING)
50
~1;w.,~RffI =grT'~~~~6rciu't1,~~MA~
GEAR
TRUNMON BEARING CAP WITH MAIN GEAR FAIRING
REMOVED)
100
60
200
160
250
300
350
450
400
500
FUSELAGE STATION (FSI-INCHES
LOCADNG CG WITH AIRPLANE ON LANDING GEAR
FORMULA IOf Loogitudinal CG
(X) c (A) _
(No•• G••r Nel WolghlX
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Nos. and Main landing Ge.r Wolgl1t TOlaled(
CG Ann 0/ A1rplano • 100 + (X). (
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) Inch ••
LOCATING CO WITH AIRPLANE ON JACK PADS
LEVEUNG PROVISIONS
FORMULA lor Longibdnal CG
Airplane
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101.44 X
CG Ann.1
.207.44 -
(No•• Jack Polot Net Walghl)(
Noaa and Aft Jack Point
W.'ght Totolod(
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Inches
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LONGITUDINAL - LEFT SlOE OF
Allot
F.':r~~E_A:~~=-~WC:
Datum
PILOT AND FRONT PASSENGER SEATS
AIRPLANe AS WEIGHED TABLE
LOCADNG PERCENT MAC
FORMUlA lor P."",nt MAC
CG Poroant MAC.
POSITION
SCALE READINO
SOALEDAIFT
TARE
NETWEIOK!'
LEFT SIDE
(OG Arm 01 Al/pIano) - 167.57
AlGK!'SIDE
0.6B40
NOSE
AIRPLANE TOTAL AS WEIGHED
BASIC EMPTY WEIGHT AND CENTER"()F GRAVlTVTABLE
ITEM
WEIGHT
CGAIIII
AIRPLANE (CALCULATED OR AS WEIGHED)
(INCLUDES ALLUNDRAINABLE FLUIDS AND FULL Olll
ORAINABLE UNUSABLE FUEL AT 6.7 POUNDS PER GALLON
BAS
/POUNDS)
!INCIII!81
24.1
186.4
(.;~OO)
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CESSNA AIRCRAFT COMPANY, AIRCRAFT DIVISION, P.O. BOX 7704, WICHITA, KANSAS 672n
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FORM NUMBER 2055. 8 February .999
Figure 6-1. Airplane Weighing Form
13 October 1999
6-4
For Training Pu rposes Oldy
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SAMPLE WEIGHT AND BALANCE RECORD
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(X)
(CONTINUOUS HISTORY OF CHANGES IN STRUCTURE OR EQUIPMENT AFFECTING WEIGHT AND BALANCE)
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AIRPLANE MODEL
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ISERIAL NO.
IPAGE NUMBER
(1)
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ITEM NO.
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DATE
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RUNNING
BASIC EMPTY
WEIGHT
WEIGHT CHANGE
DESCRIPTION
OF ARTICLE OR
MODIFICATION
ADDED (+)
WT.
(LB.)
ARM ~OMEN
(IN.) 11000
REMOVED (-)
WT.
(LB.)
ARM
(IN.)
MOMEN
11000
WT. MOMENT
(LB.)
11000
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
A properly loaded airplane, however, will perform as intended.
Before the airplane is licensed, a basic. empty weight, center of
gravity (C.G.) and moment are computed. Specific information
regarding the weight, arm, moment, and installed equipment for this .
airplane as delivered from the factory can be found in the plastic(
envelope in the back of this handbook. Using the basic empty
weight and moment, the pilot can determine the weight and moment
for the loaded airplane by computing the. total weight and moment
and then determining whether they are within the approved Center
of Gravity Moment Envelope.
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A WARNING
It Is the responsibility of the pilot to ensure that
Operation
the airplane Is loaded properly.
outside of prescribed weight and .balance
limitations could result in an accident and
serious-or fatal injury.
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AIRPLANE WEIGHING PROCEDURES
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1. Preparation:
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a. Remove all snow, ice or water which may be on the \
airplane.
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b. Inflate tires to recommended operating pressure.
c. Lock open fuel tank sump quick-drains and fuel r.eservoir
quick-drain to drain all fuel. Drain fuel can.
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d. Service engine oil as required to obtain a normal full
indication (MAX HOT or MAX COLD, as appropriate, on
dipstick).
e. Move sliding pilot and front passenger seats to position
the seat locking pins on the back legs of e.ach seat at
station 145. Aft passenger seats (if installed) have
recommended fixed positions identified with a code on
the seat rails to show the position of each seat front
attachment. In the event the aft seats were moved to
accommodate a custom loading, they should be returned
to the coded locations prior to weighing.
f. Raise flaps to fully retracted position.
g. Place all control surfaces in neutral position.
6-6
13 October 1999
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
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SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
2. Leveling:
a. Place scales under each wheel (minimum scale
capacity, 2000 pounds nose, 4000 pounds each main).
The main landing gear must be supported by stands,
blocks, etc., on the main gear scales to a position at
least four (4) inches higher than the nose gear as it rests
on an appropriate scale. This initial elevated position will
compensate for the difference in waterline station
between the main and nose gear so that final leveling
can be accomplished solely by deflating the nose gear
tire.
b. Deflate the nose tire to properly center the bubble in the
level (see Figure 6-1). Since the nose gear strut contains
an oil snubber for shock absorption rather than an airfoil
strut,it can not be deflated to aid in airplane leveling.
3. Weighing.:
a.
Weigh airplane in a closed hangar to avoid errors
caused by air currents.
b. With the airplane level arid brakes released, record the
weight shown on each scale. Deduct the tare from each
reading .
4. Measuring:
a. Obtain measurement A by measuring horizontally (along
airplane centerline) from a line stretched between the
main wheel centers to a plumb bob dropped from the
center of the nose jack point located below the firewall
and housed within the nose strut fairing.
b. Obtain measurement B by measuring .horizontally and
parallel to the airplane centerline, from center of nose
wheel axle, left side, to a plumb bob dropped from the
line between the main wheel centers. Repeat on right
side and average the measurements.
5. Using weights from item 3 and measurements from item 4,
the airplane weight and C.G. can be determined.
6. Basic Empty Weight may be determined by completing
Figure 6-1.
6-7
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
WEIGHT AND BALANCE
The following information will enable you to operate your Cessna
within the prescribed weight and center of gravity limitations. TO i
figure weight and balance, use the Sample Loading Problem, \
Weight and Moment . Tables,and Center of Gravity Moment
Envelope as follows:
Take the basic empty weight and moment from appropriate weight
and balance. records carried in your airplane, and enter them in the
column titled YOUR AIRPLANE on the Sample Loading Problem.
NOTE
In addition to the basic empty weight and moment noted on
these records, the C.G. arm (fuselage station) is also
shown, but need not be used on the Sample Loading
Problem. The moment which is shown must be divided by
100,0 and this value used as the momentl1000 on the
loading problem.
Use the Weight and Moment Tables to determine the momentl1000
for each additional item to be carried; then list these on the loading
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prob~m.
NOTE
Information on the Fuel Weight And Moment Tables is
based on average fuel density at fuel temperatures of 60°F.
However, fuel weight increases approximately 0.1 Ib./gal.
for each 25°F decrease in fuel temperature. Therefore,
when environmental conditions are suCh that the fuel
temperature is different than shown in the chart headings,
new fuel weight calculation should be made using the 0 .1
Ib.lgal. increase in fuel weight for each 25°F decrease in
fuel temperature. As an example, consider the chart for' Jet
A fuel which has an average density of 6.7 Ibs.lgal.
Assume the tanks are completely filled and the fuel
temperature is at 35°F (25°F below the 60°F noted on the
chart).
a
6-8
13 October 1999
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
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Information on the Fuel Weight And Moment Tables is
based on average fuel density at fuel temperatures of 60°F.
However, fuel weight increases approximately 0.1 Ib.lgal.
for each 25°F decrease in fuel temperature. Therefore,
when environmental conditions are such that the fuel
temperature is different than shown in the chart headings, a
new fuel weight calculation should be made using the 0.1
Ib.!gal. increase in fuel weight for each 25°F decrease in
fuel temperature. As an example, consider the chart for Jet
A fuel which has an average density of 6.7 Ibs.lgal.
Assume the tanks are completely filled and the fuel
temperature is at 35°F (25°F below the 60°F noted on the
chart).
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Calculate the revised fuel weight by multiplying the total
usable fuel by the sum of the average density (stated on
chart) plus the increase in density estimated for the lower
fuel temperature. In this particular sample, as shown by the
calculation below, the resulting fuel weight increase due to
lower fuel temperature will be 33.6 Ibs. over the 2224 Ibs.
(for 332 gallons) shown on the chart, which might be
significant in an actual loading situation:
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Then calculate the revised fuel moment. The revised
moment is in direct proportion to the revised fuel weight:
x
(revised moment)
408.8 (average moment)
:;:2257.6 (revised weight)
=2224 (average weight)
x= (408.8 X 2257.6) + 2224
The revised moment of X = 414.97. A value of 415 would
be ' used on the Sample Loading Problem as the
momenV1000 in conditions represented by this sample.
1 April 1998
For Trainine Purposes Only
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
NOTE
Information
on
the Crew
And
Passenger
and
Baggage/Cargo Weight And Moment Tables is based on
the pilot and front passenger sliding seats positioned for
average occupants (e.g., station 135.5), the aft passenger
fixed seats (if installed) in the recommended position coded
on the seat rails, and the baggage or cargo uniformly
loaded around the center (e.g., station 168.4 in zone 1) of
the zone fore and aft boundaries (e.g., stations 155.4 and
181.5 in zone 1) shown on the Loading Arrangements
diagrams. For · loadings which may differ from these, the
Loading Arrangements diagrams and Sample Loading ,
Problem lists fuselage stations for these items to indicate
their forward and aft C.G. range limitations (seat travel and
baggage/cargo area limitations). Additional moment
calculations, based on the actual weight and C.G. arm
(fuselage station) of the item being loaded, must be made if
the position of the load is different from that shown on the
Weight And Moment Tables. For example, if seats are in
any position other than stated on the Internal Cabin
Loading Arrangements . diagram, the moment must be
calculated by multiplying the occupant weight times the
arm {n inches. A point 9 inches forward of the intersection
of the seat bottom and seat back (with cushions
compressed) can be assumed to be the occupant C.G. For
a reference in determining the arm, the forward face of the
raised aft baggage floor is fuselage station 284.0.
Total the weights and moments/1QOOahd plot these values on the
Center of Gravity Moment Envelope to determine whether the point .
falls within the envelope, and if the loading is acceptable.
A WARNING
It is the responsibility of the pilot to ensure that
the airplane Is loaded properly. Operation
outside of prescribed weight and balance
limitations could result in an accident and
serious or fatal Injury_
6-10
13 October 1999
For Training Purposes Only
CESSNA
MODEL20a (675 SHP)
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SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
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WEIGHT AND BALANCE PLOTTER
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CREW/PASSENGER LOADING
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A Weight And Balance Plotter is provided to quickly determine the
weight and balance of the airplane when loading. If the plotter
shows a marginal condition developing, or if there is a' question
concerning the results in any way, then a more precise weight and
balance should be determined using the weight and balance
procedure in this section. Instructions for use of the plotter are
included on the plotter.
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Six-way adjustable seats are provided for the pilot and front
passenger, and these seats slide fore and aft on tracks having
adjustment holes for seat position. On the Standard 208, aft
passenger , seating is available in two configurations, Commuter
seating and Utility seating. In Commuter seating, two individual,
fixed-position passenger seats are located on the left side of the
cabin, and three two-place, fixed-position, bench-type seats are
located on the right side of the cabin. An "0" code marking on the
aft seat tracks represents the recommended position for placement
of the front leg plunger of each Commuter seat. In Utility seating,
all seats are individual, fixed-position, collapsible seats which, if
removed, can be folded for storage in the aft baggage area. Four
passenger seats are located on the left side of the cabin, and four
seats are located on the right side. An "X" code marking on the aft '
seat tracks represents the ' recommended position for placement of
the front leg plunger of each Utility seat. Refer to the Internal Cabin
Loading Arrangements diagram for the C.G. arm (fuselage station)
of the pilot and al,l passenger seating pOSitions.
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A WARNING
None of the airplane seats are approved for
Installation facing aft. Also, the left-hand oneplace seats In the commuter configuration must
not be Installed on the outboard and middle seat
' tracks used for the right-hand two-place seats of
the commuter configuration, even though the
one-place collapsible seats In the utility '
configuration are normally installed In this
location.
6-11
1 April 1998
For Trainine Purposes Only
SECTION 6
WEIGHT & BALANCE!
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
BAGGAGE/CARGO LOADING
CABIN AREA
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To facilitate the carrying of large or bulky items, all aft seats'(
(Standard 208 only) and the front passenger seat may be removed ' (
from the airplane. If a cargo barrier and its three barrier nets are
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available for installation, removal of the front passenger seat may
not be desired. Mission requirements will dictate whether the
barrier is to be used and the number of seats removed. If seats are
removed for hauling cargo and the cargo barrier and its nets added,
the basic empty weight and c.g. moment of the airplane should be
adjusted so that these values accurately represent the weight and
moment of the airplane before loading. To calculate the new weight
and moment, refer to the airplane equipment list and acquire the
weight andc.g. arm of each item of equipment to be removed or
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added, then record these values on Figure 6-2, Sample Weight And
Balance Record, to ' assist in the calculation . 'For each item of
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equipment, multiply its weight by its c.g. arm to provide the moment
for that item. Subtract weights of removed items (seats) and add .(
weights of installed items (cargo barrier and its nets) to the original
basic empty weight to provide a new basic empty weight Likewise, i
subtract the moments , of removed items and add the moments of \
installed items to the original moment to provide a new airplane
moment. (Remember that the moment value is to be divided by
1000 to reduce the number of digits.) The new basic empty weight
and momentl1000 can be used as illustrated in the Sample Loading
Problem when figuring airplane loading with the selected items of
equipment removed/installed.
With all the seats except the pilot's seat removed, a large cabin
volume (341.4 cubic feet, less the ,volume required for the pilot) is
available for baggage/cargo; if a cargo barrier is installed, the total
volume available for cargo behind the barrier is 254 cubic feet.
Cargo can be loaded through the large, almost square, two-piece
cargo door. The floor is flat from the firewall at station 100, except in
the rudder pedal area, to the aft side of the cargo door (station 284),
and has a 200 pound per square toot allowable loading.
Strategically located nutplates are provided which will allow the
installation of plywood flooring (standard eqUipment on the
Cargomaster) for ease of loading and distribution of concentrated
loads (see Figure 6-11 ). Between stations 284 and 308, additional
baggage/cargo space is provided ,on a raised floorboard
approximately 5 inches above the main floorboard.
6-12
13 October 1999
For Training Purposes Only
· CESSNA
MODEL 208 (675 SHP)
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SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
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In the area of the removed front passenger peat, "I" section seat
tracks are installed from station 125 to 159.98, and tie-down block
assemblies (available from any Cessna Dealer) which clamp to the
tracks can be installed to serve as tie-down attach points. ' From
station 158 aft to the raised baggage/cargo floor, the seat tracks are
designed to receive quick-release tie-down fittings which can be
snapped into the tracks at intervals of 1 inch. The raised
baggage/cargo floor contains eight (8) anchor plates to which quickrelease tie-down fittings can be attached. If rope, cable or other
fittings are used for tie-downs, they should be rated at a minimum of
2100 pounds when used with all fittings noted in the table on Figure
6-9, except the double-stud quick-release tie-downs which require a
3150 pound rating.
Maximum allowable cargo loads will be
determined by the individual zone weight limitations and by the
airplane weight and C.G. limitations. The number of tie-downs
required is dependent on the load(s) to be secured. Figure 6-9
shows the maximum allowable cargo weight for each type of cargo
tie-down attachment
On the Cargomaster, the sidewalls in the cargo area are marked
with vertical lines to facilitate the identification of the six (6) loading
zones. Markings located on the sidewalls between the lines identify
each zone by number and display the maximum load which can be
carried Y.(ithin the zones. Refer to Maximum Zone/Compartment
Loadings for maximum zone weight limits.
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CAUTION
The maximum load values marked In each zone
are predicated on all cargo being tied down with·
In the zones.
A horizontal line, labeled 75%, is prominently marked along each
sidewall as a loading reference. As indicated on a placard on the
lower cargo door, zones forward of the last loaded zone must be at
least 75% full by volume. Whenever possible, each zone should be
loaded to its maximum available volume prior to loading the next
zone. An additional placard located on the right sidewall between
zones 5 and 6 cautions that if the load in zone 5 exceeds 400
pounds, a cargo partition net (if available) is required aft of the load
or the load must be secured to the floor.
6-13
1 April 1998
For Training Purposes Only
. SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP) '
A cargo barrier and three barrier nets are available for installation
directly behind the pilot's and front passenger's seats. The barrier
and nets preclude loose cargo from moving forward into the pilot's
and front passenger's stations during an abrupt deceleration. The
barrier consists of a U-shaped assembly of honeycomb composite (
construction. The assembly attaches to the four pilot and front
passenger seat rails at the bottom at station 153 and to the wing
carry-thru spar at the top at approximately station 166. The cargo
barrier nets consist of three nets: one for the left sidewall, one for
. the right sidewall, and one for the center. The left and right netsfi"
in the space between the barrier assembly and the airplane
sidewalls. The side nets are fastened to the airplane sidewalls and
the edge of the barrier with six (6) quick-release fasteners each,
three on each side. The center net fills in the opening in the top
center of the barrier. The center net is fastened with four (4)
fasteners, two on each side. Horizontal lines, labeled 75, are
marked on the 'aft side of the cargo barrier. Placards above the
horizontal lines caution that the maximum allowable load behind the
barrier is 2900 pounds total, and that zones forward of the last
loaded zone must be at least 75 full by volume. Refer to Figure 6-6
for additional details.
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A WARNING
13 October 1999
For Training Purposes Only
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When utilized, the cargo barrier and its attached
nets provide cargo forward crash load restraint
and protection of the ' pilot and front passenger;
however, the cargo must stili be secured to
prevent It from shifting due to takeoff, flight,
and
taxi
accelerations
and
landing,
. deceleratIons.
On the Standard 208, If
passengers as well as cargo are located aft of
the barrier, cargo - placement must allow
movement and exit of the passengers and the
cargo must be secured for crash load restraint
conditions. Refer to cargo load restraint in this
section for additional information concerning
cargo restraint with and without a cargo barrier.
6-1 4
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. CESSNA
MODEL 208 (675 SHP)
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SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
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Ensure the barrier net fasteners are secured
takeoff, landing, and Inflight operations, and
momentarily detached only for movement of
nets for loading/unloading of Items through
crew area.
for
are
the
the
Three cargo partition nets are available and can be installed to
divide the cargo area into convenient compartments. Partitions may
be installed in all of the five locations at stations 181.5, 208, 234,
259, and 284. The cargo partitions are constructed of canvas with
nylon webbing reinforcement straps crisscrossing the partition for
added strength. The ends of the straps have quick-release fasteners
which attach to the floor tracks and two floor-mounted anchor plates
located .just forward of the raised cargo floor and other anchor
plates on the sidewalls and ceiling. Four straps have adjustable
buckles for tightening the .straps during installation of the partition.
Refer to Figure 6-7 for additional details.
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WARNING
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Zones divided by cargo partitions can be loaded without additional
tie-downs provided a total loaded density for each partitioned zone
does not exceed 9.75 pounds per cubic foot and the zone is more
Cargo loading that does not meet these
than 75% full.
requirements must be secured to the cabin floor.
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CAUTION
The maximum cargo partition load Is ·the sum of
any two lones. no more than two adjacent
zones can be divided by one partition. The
partitions .are designed to prevent the cargo
from shifting forward and aft . In flight; they
should not be considered adequate to withstand
crash loads and do not replace the need fo r a
cargo barrier.
6-15
1 April 1998
For Training Purposes Only
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
A restraining net is available and can be installed on the inside of
the airplane over the cargo door opening. The restraining net
precludes loose articles from falling out the cargo door when the
doors are opened ..The restraining net consists of two . halves which
part in the center of the door opening. The front and rear halves r
slide fore and aft, respectively, on a rod to open the net. The net is
attached to the sidewall by screws and nutplates along the front and
rear edges of the net. When the net is closed, the two halves are
held together by snap-type fasteners. Refer to Figure 6-8 for
additional details.
Various tie-down belt assemblies and tie-down ring anchors are
available for securing cargo within the airplane; the belts may also
be used for ·tying down the airplane. A standard configuration is
offered and contains three 3000-pound rated belt assemblies ·with
ratchet-type adjusters and six single-stud, quick-release tie-down
ring anchors. A heavy-duty configuration consists -of three 5000pound rated belts with ratchet-type adjusters and six double-stud,
Three SOOO-pound rated belts with
quick-release anchors.
overcenter-type locking devices are also available for heavy-duty
use. The six single-stud and double-stud tie-down ring anchors are
also available separately. The single-stud anchors can be attached ,
to any tie-down point in the airplane which isn't placarded for 'c
attachment of partition nets only, whereas the double-stud anchors
can be attached to the aft seat tracks only. See Figure 6-9 for
maximum load ratings and tie-down ring anchorspacing restrictions.
Refer to Maximum Zone/Compartment Loading for. maximum zone ·
weight limits.
A CAUTION
The maximum zone weight limits in each zone
are predicated on all cargo being tied down
within the zones.
.
6-16
13 October 1999
For Training Purposes Only
(
. CESSNA
MODEL 208 (675 SHP)
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
MAXIMUM ZONE/COMPARTMENT LOADINGS
(
(
(
Maximum zone loadings are as follows:
(
t
(
(
(
Zone/
Com partment
Fuselage
(
(
1
2
3
4
5
6
(
(
Cargo Pod
A
B
(
C
Volume
(Cubic
Feet)
Weight Limits (Lbs)
·Secured
"Unsecured
By
Using Partitions
Tie-Downs
or in Cargo Pod
C.G.
(Station
Location)
40.6
1410
49.4
1430
48.9
1410
1380
43.5
40.1
1270
31.5 320(Cargomaster)
325(Std. 208)
395
480
475
420
390
305
168.4
194.8
221 .0
246.5
271.5
296.0
23.4
31.5
28.8
230
310
280
132.3
182.1
239.6
(
'THIS IS THE MAXIMUM CARGO ALLOWED IN THE BAY INDICATED.
(
(
\"
"OENSITY MUST BE 9.75 LBS/FTJ OR lESS AND BAY 75% OR MORE FULl.
(
(
(
(
(
(
(
6-17
1 April 1998
For Training Purposes Only
SECTION 6
WEIGHT & BALANCE/
CESSNA
MODEL 208 (675 SHP)
EQUIPMENT LIST
CARGO POD
The airplane can be equipped with an 83.7 cubic foot capacity
cargo pod attached to the bottom of the fuselage. The pod is .
divided into three compartments (identified as zones A, B, and C) ,
by bulkheads and has a maximum floor loading of 30 pounds per
square foot and maximum load weight limit of 820 pounds. Each
compartment has .a lo~ding door located on the left side ofthe pod.
The doors are hinged at the. bottom, and each has two latches.
When the latch handles are rotated to the horizontal position with
the doors closed, the doors are secured. Refer ·to Figure 6-4 and 613 for additional details.
CENTER OF GRAVITY PRECAUTIONS
Since the airplane can be used for cargo missions, carrying various
types of ' cargo in a variety of loading configurations, precautions
must be taken to protect the forward and aft C.G. limits. Load
planning shoul.d include a careful comparison of the mission
requirements with the volume and weight limitation in each loading
zone and the final airplane C.G. Cargo loaded in the forward zones
may need to be balanced by loading cargo in one or . more aft I
zones. Conversely, loadings can not be concentrated in the rear of \
the airplane, but must be compensated by forward cargo to maintain
balance. Under ideal conditions, loadings should be accomplished
with heavy items on the bottom and the . load distributed uniformly
around the C.G. of the cabin cargo area zone and/or cargo pod
compartment. Loading personnel must maintain strict accountability
for loading correctly and accurately, but may not always be able to
achieve an ideal loading. A means of protecting the C.G. aft limit is
provided by supplying and aft C.G. location warning area between
38,33 MAC and the maximum allowable aft C.G. of 40.33 MAC. The
warning area is indicated by shading on the C.G. Moment Envelope
(Figure 6-18) and C.G. Limits (Figure 6-19). This shaded area
should be used only if accurate C.G. determination can be
obtained.
6-18
13 October 1999
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
A
(
( I"
\.
(
(
(
CAUTION
Exercise caution while loading or unloading
heavy cargo through the cargo doors. An ideal
loading in every other respect can stili cause tail
tipping and structural damage if proper weight
distribution Is Ignored. For example, heavy cargo
loaded through
the doors and placed
momentarily In zones 4 and 5, plus the weight of
personnel required to move It to a forward zone,
could cause an out-of-balance condition during
loading.
0
(
(
CARGO LOAD RESTRAINT
(
(
PREVENTION OF MOVEMENT
(
Cargo restraint requires the prevention of movement in five principal
directions: forward, aft, upward (vertical), left (Side). and right (Side)
These movements are the result of forces exerted upon the cargo
due to acceleration or deceleration of the airplane in takeoffs and
landings as well as forces due to air turbulence in flight. Correct
restraint . provides the proper relationship between airplane
configuration (with or without barrier), weight of the cargo, and the
restraint required. Restraint is required for flight, landing, and taxi
loads and for crash loads.
0
(
(to
\
(
(
(
(
(
Cargo must be tied down for flight, landing and taxi load restraint
and/or crash load restraint. When a cargo barrier is not installed,
all cargo mu~t be prevented from movement in the· five principal
directions and secured to provide crash load restraint.
The
maximum rated loads specified for loadings without a barrier in the
table on Figure 6-9 should be used for each tie-down. Consistent
use of these loading criteria is important, and it is the responsibility
of the pilot to assure the cargo is restrained properly. When a
cargo barrier Is Installed, cargo aft of the barrier must also be
secured !o prevent movement in the five principal directions, but
0
0
6-19
1 April 1998
For Trainine Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
only to the extent that shifting due to flight, landing, and taxi loads is
provided. The maximum rated loads specified for loadings with a
barrier installed shown in the table of Figure 6-9 should be used for
each tie-down. With a barrier installed, all cargo must be loaded I
such that loading zones forward of the last loaded zone must be
75% full by volume.
,A WARNING
In special loading arrangements which allow the
carriage of passengers as well as cargo behind
the barrier on the Standard 208, all cargo must
be secured to prevent movement in the five
principal directions and provide the same 'crash
load restraint as though a barrier was not
installed using the maximum rated loads
specified for loading without a barrier. In this
arrangement, cargo placement must allow for
movement and exit of the passengers. The pilot
must be responsible to ensure proper load
restraint In all loadings.
(
.(
Refer to Figure 6-15 for diagrams of typical cargo tie-down methods
for prevention of movement. Also, the cargo partition nets available
for the airplane can be installed at stations 181.5, 208, 234, 259
and 284 to divide the cabin cargo area into compartments. If the
partitions are used, they must be used in conjunction with the cargo
barrier. Since partitions are not designed to withstand crash loads,
they cannot be considered as a replacement for the barrier. Each
partition will withstand the forward and aft operational loads applied
during takeoff, flight and landing by any two (2) zones forward or aft
of the partition. Use of the partitions will allow loading of the zones
without tying down the cargo if the load density is not more than
9.75 pounds per cubic foot and the zone is more than 75% full.
Cargo loading that does not meet these requirements must be
secured to the cabin floor.
.
13 October 1999
6-20
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
LOADING OF PIERCING OR PENETRATING ITEMS
(
(
(
Regardless of cargo location, items of a piercing or penetrating
nature shall be located so that other cargo is loaded between the
.barrier/nets, cargo partitions, and rear wall and the piercing or
penetrating items to provide a buffer. The density of this cargo shall
be sufficient to restrain the piercing or penetrating , items from
passing through the barrier/nets, partitions, and rear wall under
critical emergency landing conditions. If the condition cannot be
complied with, the piercing or penetrating items shall be tied down
separately.
TRANSPORTATION OF HAZARDOUS MATERIALS
Special protection of the airplane and training of personnel are key
considerations in conducting approved transportation of hazardous
materials.
(
(
(
(
(
Protection against the damaging effects of leakage of hazardous
materials has not been provided in the cabin cargo area or cargo
pod. Therefore provisions should be made to ensure this protection
if carriage of these materials is planned.
In addition to the pilot-in-command and flight crew member (if used),
,other personnel such as cargo receiving and loading personnel
should be properly trained concerning the acceptance, handling,
storage, loading and unloading of hazardous materials if these
materials are to be carried. Information and regulations pertaining
to the air transportation of hazardous materials . is outlined in the
Code of Federal Regulations (CFR) Title 49 and in the International
Civil Aviation Organization (ICAO) Technical Instructions for the
Safe Transport of Dangerous Goods by Air. Additional details on
training subject matter and location references for this information
are included in the Cargo Loading Manual for this airplane. Some
general guidelines important to safe carriage of hazardous materials
are also described in the Cargo Loading
(
(
(
"
.
~,:.. ,,:'
EQUIPMENT LIST
For a complete list of the required and optional eqUipment installed
in the airplane as delivered from the manufacturer, refer to the
equipment list furnished with the airplane.
6-21
1 April 1998
For Traininl! Purposes Only
CESSNA
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
MODEL 208 (675 SHP)
(
CARGO DOOR (LEFT SIDE)
PASS. DOOR (RIGHT SIDE)
CABIN HEIGHT
MEASUREMENTS
CARGO BARRIER/NETS
(
(
DOOR OPENING DIMENSIONS
WIDTH
(TOP)
WIDTH
(MIDI
OVERALL)
CREW ODORS
11 7/S"
355/S"
31 7/S"
CARGO DOOR
49"
49"
49"
PASSENGER DOOR
24"
, 24"
24 "
WIDTH
(BOTTOM)
HEIGHT
(FRONT)
, 243/S"
HEIGHT
(MIDI
OVERALL}
HEIGHT
(REAR)
41 3/4"
44 3/4"
50"
50",
50"
50"
50"
50"
(
(
- - - WIDTH - '
• LWR. WINDOW LINE
CABIN WIDTH
MEASUREMENTS
(
* .CABIN FLOOR
(
(
(
(
(
STATIONS
100
118
166
234
284
308
26856019
Figure 6-3. Internal Cabin Dimensions (Passenger Version)
(Sheet 1 of 2)
,
6-22
13 October 1999
For Training Purposes Only
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
(
(
(
CARGO DOOR ILEFT SIDE)
(
(
(
I
RGO BARRIER/NETS
CABIN HEIGHT
MEASUREMENTS
(
(
(
(
(
(
(
DOOR OPENING DIMENSIONS
(
WIDTH
ITOP, ,
WIDTH
CMIDI
OVERALL'
WIDTH
IBOTTOM'
HEIGHT
IFRONT,
CREW DOORS
11 7/8"
35 Sir'
317/8"
2.. 3/8"
413/4"
44 3/4"
CARGO OOOR
49"
49"
48"
SO"
60"
50"
(
(
(
(
HEIGHT
CMIDI
OVERAlLI
HEIGHT
CREAR'
(
(
(
(
CABIN WIDTH
MEASUREMENTS
-WIDTH-• MAX. CABIN BREADTH
CABIN FLOOR
*
I
('
100
118
Figure 6-3. Internal Cabin Dimensions (Cargo Version)
(Sheet 2 of 2)
6-23
7 September 2001
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
(
(
CARGO POD HEIGHT
MEASUREMENTS
(
FORWARD DOOR
(
(
164.76
100
NOTES:
1. Height dimensions are
approximate and measur.d
at fuselage station shown
from bottom of fuselage to
inside floor.
2. Width dimensions are
approximate and measured
at fus.lage station shown
and on waterline 68.00
inside pod.
(
284
209.35
(
DOOR OPENING DIMENSIONS
HEiGHT
(FRONT)
WIDTH
HEIGHT
(MID)
(
HEIGHT
(REAR)
(
fORWARD DOOR
27 112"
MIDDLE DOOR
201/2"
- ----
AFT DOOR
301/2"
131/2"
15 1/4."
-. -.-
. -.
81/2"
14 1/2"
(
(
(
(
CARGO POD WIDTH
MEASUREMENTS
(
(
(
(
STATIONS
100
/
CARGO POD
DOOR MARKINGS
(
(
FWD. COMPARTMENT
MAX. WEIGHT 230 LBS.
CTR. COMPARTMENT
MAX , WEiGHT 310 LBS.
AfT COMPARTMENT
MAX. WEIGHT 280 LBS,
MAX. FLOOR LOADING
3D LBS. PER SQ. FT.
MA><' FLOOR LOADING
MAX. FLOOR LOADING
NO SHARP EDGES
30 LBS. PER
sa.
FT.
30 LBS. PE R SQ. fT.
NO SHARP EDGES
NO SHARP EDGES
2685X1078
(
(
(
(
Figure 6-4. Internal Pod Dimensions and Load Markings
(
6-24
1 April 1998
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCEI
EQUIPMENT LIST
(
(
ZONE 4
MAX LOAD 1380 LBS
(
ZONE 6
MAX LOAD 320 LBS
(
(
(
(
(
(
(
I
I I I
STATION
(C.G.
ARM) 100
155.4
(
lB1.5
I
234
208
MAX LOAD BEHIND BARRIER
2900 lBS TOTAL
ZONES FWD OF LAST LOADED
ZONE MUST BE AT LEAST
75% FULL BY VOLUME. SEE
POH FOR EXCEPTIONS.
• CHECK WEIGHT AND BALANCE -
(
(
(
(
(
CARGO
BARRIER
(AFT SIOEI
IF LOAD IN ZONE 5 EXCEEDS
400 LBS A PARTITION NET IS
MAX LOAD BEHIND BARRIER
2900 LBS TOTAL
ZONES FWD OF LAST LOADED ZONE
MUST BE AT LEAST 75% FULL BY
VOLUME . see POH FOR EXCEPTIONS.
NOTE:
Left sidewall zone and
maximum load markings
same as on right sidewall.
- CHECK WEIGHT AND BALANCE ·
(
(
..
REaD AFT OR LOAD MUST BE
SECURED TO FLOOR
(
(
CARGO RESTRAINT
STOWAGE
75% FULL IVOLUME) LINE
(TYPICAL)
LOAD MUST BE PROTECTED FROM
SHIFTING - see POH •
CABIN
LEFT SIDE~=F
__:;;:::
__:;;:::
__::=:;
__::=:_-::::-::;:---:l:~::-:::::==:;?
(
(
(
~ L~===.J.
I I
STATION
IC.G.
ARM) 308
284
259
I
_____ ._______________"-..u-----=__
234
208
1B1.6
166.4
100
2685X1081
Figure 6-5. Internal Cabin Load Markings (Cargomaster Only)
1 April 1998
6-25
For Training Purposes Only
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
~~~~~----CABIN TOP STRUCTURE
AT WING SPAR
RIGHT SIDE N E T - - - - - - - i , '11
(WITH 6 QUICKRelEASE FASTENERS)
(
(
(
(
CARGO
BARRIER------<~
"it,f'-~'f-IJo~$I--CENTER NET
(WITH 4 QUICKRELEASE FASTENERS)
PILOT AND FRONT-----_-4~
PASSENGER
SEAT RAILS
(
LEFT SIDE NET
IWITH 6 QUICK·
RELEASE FASTENERS)
(
FORWARD ATTACH PIN
LOCATED AT STATION 163
ON SEAT RAI LS
(
(
(
NOTES :
1. The cargo barrier and attached
nets must be installed to provide
forward crash load restraint .
2. The quick-release fasteners which
secure the center and side nets
allow momentary detachment of
the nets for loading/unloading
of items through the crew area.
MAX LOAD BEHIND BARRIER
2900 LBS TOTAL
ZONES FWD OF LAST LOADED
ZONE MUST BE AT LEAST
75% FULL BY VQLUME. SEE
POH FOR EXCEfi'rIONS.
- CHECK WEIGHT AND BALANCE
CARGO
BARRIER
(AFT SIDE)
LOAD MARKINGS
(
(
(
(
(
(
(
26856020
Figure 6-6. Cargo Barrier/Nets and Load Markings
6-26
13 October 1999
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 6
WEIGHT & BALANCEI
. EQUIPMENT LIST
(
(
Uf+----SIDEWALL AND CEILING ANCHO.R PLATE (TYPICAL)
(
(
~" 'fYuili'O-~"'--+/--OUICK-RELEASE FASTENER
f';-O'._---PARTITION REINFORCEMENT
(
(
,---·CA.RGiO PARTITION
NETS (TYPICAL)
"lH}'II4----ADJUSTABLE
BUCKLE
(
(
(
(
(
(
(
(
(
(
QUICK-RELEASE FASTENER--1'1;:!J(,
FLOOR-MOUNTED
ANCHOR PLATE FORWARD~'
OF RAISED CAR60
. _ •
FLOOR
..,.
PARTITION
REINFORCEMENT
(
NOTES:
1. Partition nets are available for installation at stations
181.5.208.234.259 and 284.
2. If partitions are used. they must be used in conjunction
with the cargo barrier. Since partitions are not designed
to withstand crash loads. they cannot be considered as 8
replacement for the berrier.
3. Each partition will withstand the forward and aft oper·
ational loads applied during takeoff. flight and landing by
any two (2) lones forward or aft of the partition. Use of
the partitions will allow loading of the zones without tying
down the cargo if tho load dansity is no more than 9 .75
pounds per cubic foot and the zone is more than 75%
full. Cargo loading that does not meet these raquiremenl6
must be secured to the cabin floor.
26856021
Figure 6-7. Cargo Partition Nets
6-27
1 April 1998
For Trllininl7 Pnrnoses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
(
(
(
VIEWED FROM INSIDE AIRPLANE
NOTES:
1.
2.
Restraining net installed Inside of
airplane over cargo door opening.
Net halves should be pulled closed
and snapped together to prevent
articles from tailing out of door
opening when cargo doors are
opened.
(
(
(
(
(
(
(
(
(
FRONT HALF OF
RESTRAINING NET
NET SUPPO
ROD
(
(
(
(
REAR HALF OF---101
RESTRAINING NET
(
SNAP-TYPE - - -__rfrIJ
FASTENER
(TYPICAL)
(
(
(
(
(
(
26856022
Figure 6-8. Cargo Door Opening Restraining Net
(
(
(
13 October 1999
6-28
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
'MAXIMUM RATED LOAD (POUNDS)
ITEM
LOCATION
Tie-Down Block on Seal Track On Front Passenger Seat Tracks
(
(
(
(
100
100
Single-Stud Quick-Release
Tie-Down on Seat Track
On Aft Passenger Seat Tracks
100
200
Single-Stud Quick-Release
Tie-Down on 8aggage Floor
Anchor Plate
On Raised Baggage Floor
100
200
Double-Stud Ouick-Release
Tie-Down on Seat Track
On Aft Passenger Seal Tracks
150
300
• Tie-downs are required forward and aft of cargo load to prevent the toad from shifting. The type of tledowns available, the sum at their individual rated loads, and the height and length of the load, whether
configured with or without a cargo barrier/nets, and whether passengers are carried aft of the cargo
barrier/nets, are the determining factors in selecting the number of tie-downs needed.
FOR EXAMPLE:
(
(
..
(
(
WITH CARGO
BARRIER/NETS
INSTALLED
When utilizing the aft seat rails tor tying down carg o, minimum spacing for single-stud quick-release tiedown rings Is six inches; minimum spacing for double-stud quick-release tie-down rings is 12 inches .
(
(
f,v,THOUT CARGO
BARRIER/NETS
INSTALLED
,~
A 600·pound load which has a height d imension that is equal to or less than its length dimension,
requires a minimum of six (6) tie·downs (3 forward and 3 alt). When the cargo barrier/nets are installed,
the number. of tie-downs can be reduced by 1/2 as long as load shifting can be prevented. The
min imum number of tie-downs for this example would then be 4 (3+ 1, to utilize an even number of tiedowns). Regardless at whether the cargo barrier/nets are installed, if the cargo height is greater than its
length, then the minimum number 01 tie-downs must be doubled. If passengers are carried aft 01 the
cargo barrier/nets, cargo must be secured per the requirements without the barrier/nels Installed. Refer
to Cargo Load Restraint in this section for additional information.
I
(
TIE-DOWN BLOCK
BOLT MUST BE
TIGHTENED TO
A MINIMUM OF
50 INCH POUNDS
FRONT PASSENGER
SEAT TRACK
I
.~
SINGLE STUD QUICK RELEASE TIE-DOWN
RING/STRAP ASSEMBLY
BAGGAGE FLOOR
ANCHOR PLATE
AFT PASSENGER
SEAT TRACK
26856016
26192012
26191007
Figure 6-9. Cargo Tie-Dawn Equipment (Sheet 1 of 2)
6-29
Revision 6
For Traininl! Purooses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
(
(
(
(
RATCHET
ADJUSTER
(
RATCHET
ADJUSTER
(
(
(
(
(
CARGO
TIE-DOWN
BELT ASSEMBLY
(
CARGO
TIE-DOWN
BELT ASSEMBLY
(
(
(
(
(
DOUBLE STUD
QUICK RELEASE
TIE-DOWN
RING ANCHOR
(
(
~
(
(
#
I
(
(
(
AFT PASSENGER
SEAT TRACK
(
(
26192004
26192012
Figure 6-9. Cargo Tie-Down Equipment (Sheet 2 of 2)
6-30
1 April 1998
For Training Purposes Only
(
(
CESSNA
(
SECTION 6
WEIGHT & BALANCEI
MODEL 208 (675 SHP)
EQUIPMENT LIST
(
(
(
( 1l"
.
"(
'.
(
(
-
(
NOTE
PLYWOOD
FLOORING
Plywood flooring and
anchor plates are secured by screws.
STATION
100 - - -------------
(
(
.... _- ....,
,
,,,
,
(
,,,
,
· - .. _ .... -t
~,
.,~
,~::"
(
(
(
{
(
(
(
ANCHOR
PLA.TES
(TYPICAL)
2685X1082
Figure 6-10. Floor Track, Anchor Plate and Plywood Flooring
Arrangement
6-31
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
115
(
LARGER ITEMS MAY
BE LOADED DEPENDING
ON SHAPE OF ITEM
110
(
105
100
95
90
(
85
(
80
(
If)
w
G 75
:z
~
~
,
(
70
z
w
-l
65
(
60
55
MAXIMUM 48-INCH HIGH
RECTANGULAR CONTAINER
WHICH CAN BE LOADED
50
(
(
45
5
10
15
20
25
30
35
40
45
50
\J I DTH ( I NCHES )
2685T1052
Figure 6-11. Maximum Cargo Sizes
(
.(
1 April 1998
6-32
For Training Purposes Only
,
"
.....,
----
'""'-
~
"""
~,
' ",,", '
"""" -... -...
C".....,."
---
----
--- ---
""""
~.-....~-.....--....--....~
,.~,
\.,'
s::()
~
Om
-0
~
oCJ)
STANDARD
SEATING ARRANGEMENT
-'"
to
to
"
CD
cO'
c.....
C.G. ARM
c,
"".•_,...,
-u~
en'
en -
CI)::l
::l-
,~
co~
,oj
CI)::l
;.
~lll
f® ,"",X'"
--f--------------
_0)
,
--._------(~II "" 1;1 "" ;-j "" )1
~-;g~----------"---------
"~~if (~I
~------k
.~:
II
I
I
"E~t ~," I~;;-i-;;;;:-i-,-.~;;I i 1-~.- -~- ~
::
J
roN'
.....,"' ,.. '"
· 155.4
i
1
181.5
roNE
" , . ZO:'
208
~
259
2~
mC/)
rZ
I\)~
o
co
m
.......
01
(f)
::t:
.3!
~
~lll
<()
;
"""E
i::l::l
5.g:
;.
=
,~
,
-r
~
_co
** 194.8
_0
~
(f)lll
:::ra.
CI)
_.
CI)::l
;:,
......
;
** 246.5
~
.~
w::l
_CO
CI)
:J
** 296.0
Cil
'"
<»
CD
(l1
,
w
w
* it cargo or 8aggage area center of gravity in Zones 0 thru 6 .
4
'"w
'"
o
L____ ~_____
I.pLAC~
SEATING
:E
NOTE:
1.
~1-2S4
3
CI)
0)
an average occupant with the ..at locking pin at slation 145.0. Numbers
in parentheses indicate forward and aft limits of occupant center of gravity
range.
""U3@.
.. ",.
~
o_lll
~
* Pilot or front passenge< center of gravity on adjustable seats positioned for
2
2.
-308
The forward face of the raised aft baggage floor (Station
284.0) can be used .liS a convenient reference point for
determining the location of occupant, car9Q or baggage
fuselage station.
When ca@ barrier is installed. Commuter seats 4 and 5
or Utility seat! 3 and 4 must be removed. ",ission requirements will dictate if any aft pa5Sl!nge< seating is to
remain instalied.
m
m-
OG)
-..,
"OQo
c::t:
S::roCJ)
m~m
Zr(J
-I~-l
rZO
CJ)()Z
"'~O)
0>
I
OPTIONAL
W
.p..
SEATING ARRANGEMENTS
AFT PASSENGER
SEAT LOCATION CODE
SEATING POSITIONS
"
PILOT -
cO'
t:
-U.....
C.G. ARM
Pol
I\)
c/).
100
~5"
~. ~ * 135.5 -
f-l@ lS]
*
135.5
1133.5· 146.51
1
169.9
* * 194.B - - f - - - - 2
::::
;::; »**
.., 2 2 1 . 0 - - + - - - 3
217.9
0
'"
_Pol
233.9
Wt5
-m
C.G. ARM
o
= COMMUTER SEAT
x
~UTlUTY
SEAT
C.G. ARM
1 0 0 - - --------- - ---~
100--
ZONE
~. ~ * * 168.4 - - f - - - :::T9:
m:::J
mco
®
.1.
...::::::::::..-
< - 1133.5 - 146.51
m (")
r--------~
CJ) Pol
THRU
C.G. ARM
.J..
""' Pol
CD
--.1--------------
::l -
CO~
2,...
_0
CD
PASSENGERS -
* * 246.5 --4+--- 4
~~
-4---[(1)(~DJ
~~~6-l0 0J
-l0 ®J
'-.V
*
135.5
1133.5 - 146.51
166.5
193.5
220.5
l@l@
~ ~
~ ~
~ ~
245.5
o
><0)
191.5--
o
XjoX Q
207.5-- 0 Q
213.5-XX
223.5--
o
159.5-- x x
175.5--
Q
186.5--
x x
0
240.5 - - x x
xx
o
x x
248.5
s:
oo
m
r
3
amrn * *
271.5
--\t---
I\)
5
o
CD
** 296.0 -~-\--
* * 296.0 - - + - - 6
m
L ___________ J
g:
2·PLACE SEATING
o
I\)
...
~
10000I.ACE SEATING
ICOMMUTERI
IO-PLACE SEATING
(UTILITYI
...---------I
~(")
Olm
en en
::r:CJ)
Z
-u
-»
" ."
-,
""'""'"
---.
"'"" """
'"'
,(If~
---
.-..,
--
"""""""""""" --....
~.-.,
,~
'.
--....
..-.,
:!:
mCJ)
STANDARD
."'-::i~.'---'--"
~
ill' '~l!
SEATING ARRANGEMENT
"'T1
(X)
C·
I
:
e.G. ARM
cp
....
lOa
::S"~'
~
~!I
I
II
--I--------------t
, n .. n_
n.~~.
..,:J
* 136.6
oeo
W
CD
(]I
W
(j\
~
* * Cargo or BIggilge area center of gravity in Zo.- 0 thru 6.
** 246.5
W'"
(J')
l~~i
1\)>
:
in parentheses indieate forward and aft limits of occupant center of gravitY
range.
~~
=
STATION "
136.7
.~
rZ
I
'
, I
I ZONE I ZONE I ZON~ONE I ZONE I ZONE I
j-l~2-r3 I 4-t-5-J-6~
-I\)
a·
Ql-
..-- ---- -------------------,
~-~
,.....
.........
e..,
m
-i
'"'
om
oCJ)
to
to
"'I
~
s:a
»
"C
;'
--- ---
~.
~
8
'"
c..>
308
~
m
m-
aG')
I
c_-I
"'OQo
6
___________
J
~lJ)cn
m»m
zr- a
-l»-I
rZO
(j)0Z
-l~c:n
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
(
(
(
KDiDi~ !
I~O.~N' I ZON'
~A
B
I
C
I
STATION
(C.G. ARM)
154.75
100
209.36
284
(
(
(
(
(
(
(
C.G. ARM
1 0 0 - - - -_ _
(
(
* 132.4 --+--
(
(
* Cargo area center of gravity
in Zones A, B and C
* 182.1 - + - - B
(
(
(
(
(
* 239.6 --+--- C
(
(
NOTE :
Compartment bulkheads separating Zones A
and B (Station 154.75) and Zones B ande
(Station 209.35) can be used as a reference
po int' for determining the location of cargo
fuselage 5tation.
(
(
(
(
(
2685Xl079
Figure 6-13. Cargo Pod Loading Arrangements
6-36
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION E
WEIGHT & BALANCE
EQUIPMENT LlSl
,,
f
INTERNAL:
CABIN
:
(NO
I
PARTITIONS):
NOTE :
It cargo partitions are not utilized. individual loads must be secured by adequate
tie-downs over tarps.
OF F-LOAD SEQUENCE
LOAD C-j-LOAD B
CARGO
POD
NO TIE-DOWN
REO~
'I"
~
-LOADA~\
NO TIE -DOWN
REQD .
26B5X10BO
Figure 6-14. Loading Tie-Down by Zone and Load
(Off-Loading Sequence)
1 April 1998
6-37
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
(
-~CARGO PROPERLY TIED.
NO SHIFTS OCCUR.
(
(
(
CARGO I MPROPERL Y TIED.
SHIFTS OCCUR .
(
(
(
(
(
(
(
MULTIPLE FORCES SECURED BY FEWER STRAPS.
(
(
(
(
(
UPWARD CARGO RESTRAINT .
CYLINDRICAL CARGO TIE-DOWN
(
(
(
(
(
(
(
PROPER TIE-DOWN FOR ALL FORCES
(
-- (
268SX1083
Figure 6-15. Typical Cargo Restraint Methods
6-38
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
(
(
(
CREW AND PASSENGERS (COMMUTER SEATING)
r-'-
PILOT/
AFT PASSENGER SEATS
FRONT PASS.
WEIGHT SEATSCDANOC!) 0A ND
(DANDCD
(!)AND@
(POUNDS)
ARM=135.5
ARM=169.9 ARM=185.9 ARM =201.9 ARM =217.9 ARM=233.9
0
CD
CD
MOMENT/IOOO
(
10
20
30 -
40
50
60
70
80
90
100
110 120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
330
340
350
360
370
380
390
400
1.4
2.7
4.1
5.4
6.8
8.1
9.5
10.8
12.2
13.5
14.9
16.3
17.6
19.0
20.3
21.7
23.0
24.4
25.7
27.1
28.5
29.8
31.2
32.5
33_9
35.2
36.6
37.9
39.3
40.6
42.0
43.4
44.7
46.1
47.4
48.8
50.1
51.5
52.8
54.2
1.7
3.4
5.1
6.B
8.5
10.2
11 .9
13.6
15.3
17.0
18.7
20.4
22.1
23_8
25.5
27.2
28.9
30_6
32.3
34.0
35.7
37.4
39;1
40.8
42.5
44.2
45.9
47.6
49.3
51.0
52.7
54.4
56_1
57.8
59.5
61.2
62.9
64.6
66.3
68.0
1.9
3.7
5.6
7.4
9.3
11.2
13_0
14.9
16.7
18_6
20.4
22.3
24.2
26.0
27.9
29.7
31 .6
33.5
35.3
37.2
39.0
40.9
42.8
44~ 6
46.5
2.0
4.0
6.1
B.l
10.1
12.1
14.1
16.2
18.2
20.2
22.2
24.2
-26.2
28.3
30.3
- 32.3
34.3
36.3
38.4
40.4
42.4
44.4
46.4
48.5
50.5
52.5
54.5
56.5
58.6
60.6
62.6
64.6
66.6
68.6
70.7
72.7
74.7
76.7
78.7
80.8
2.2
4.4
6.5
8.7
10.9
13.1
15.3
17.4
19.6
21.S
24.0
26.1
28.3
30.5
32.7
34.9
37.0
39.2
41.4
43.6
45.8
47.9
50.1
52.3
54.5
2.3
4.7
7.0
9.4
11.7
14.0
16.4
18.7
21.1
23.4
25.7
2B.l
30.4
32.7
35.1 37.4
39.8
42.1
44.4
46.8
49.1
51 .5
53_8
56.1
58.5
60.8
63.2
65.5
67.8
70.2
72.5
74.8
77.2
79.5
81.9
84.2
86.5
88.9
91.2
- 93.6
Figure 6-16. Weight And Moment Tables (Sheet 1 of 9)
6-39
1 April 1998
For Traininl! Purnoses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
(
CREW AND PASSENGERS (UTILITY SEATING)
(
PilOT!
AFT PASSENGER SEATS
FRONT PASS.
@
WEIGHT SEATSCDAN00 0AN00 0ANO® Q)ANOCD
ARM~166.5 ARM~193.6 ARM =220.6 ARM~248.5 ARM =245.5
ARM~135.5
(POUNDS)
MOMENT/l000
(
(
CD
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
330
340
350
360
370
380
390
400
1.4
,
2.7
4.1
5.4
B.8
8.1
9.5
10.8
12.2
13.5
14.9
16.3
17.6
19.0
20.3
21.7
23.0
24.4
25.7
27.1
28.5
29.8
31.2
32.5
33.9'
35.2
36.6
37.9
39.3
40.6
42.0
43.4
44:7
46.1
47.4
48.8
50.1
51.5
52.8
54.2
1.7
3.3
5.0
6.7
8.3
10.0
11.7
13.3
15.0
16.6
18.3
20.0
21.6
23.3
25,0
26.6
28.3
30.0
31.6
33.3
35.0
36.6
38.3
1.9
3.9
5.8
7.7
9.7
11.6
13.6
15.5
17.4
19.3
21.3
23.2
25.2
27.1
29.0
31.0
32.9
34.8
36.8
. 38.?
40.6
42.6
44.5
40.0
46.4
41.6
43.3
45.0
46.6
48.3
49.9
51.6
53.3
54.9
56.6
58.3
59.9
61.6
63.3
64.9
66.6
48.4
50.3
62.2
64.2
56.1
58.0
60.0
61.9
63.9
65.8
67.7
69.7
71.6
73.5
75.5
77.4
2.2
4.4
6.6
8.B
11.0
13.2
15.4
17:6
19.8
22.0
24.3
26.5
28.7
30.9
33:1
35.3
37.5
39;7
41.9
44.1
46.3
48:5
50.7
52.9
55.1
57.3
59.5
61.7
63.9
66.1
68.4
70.6
72.8
75.0
77.2
79.4
81.6
83.8
86.0
88.2
2.5
5.0
7.5
9.9
12.4
14.9
17.4
19.9
22.4
24.8
27.3
29.8
32.3
34.8
37.3
39.8
42.2
44.7
47.2
49.7
52.2
54.7
57.2
59.6
62.1
64.6
67.1
69.6
72.1
74.5
77.0
79.5
82.0
84.5
87.0
89.5
91.9
94.4
96.9
99.4
(
(
2 .5
4.9
7.4
9 .B
12.3
14.7
17.2
19.6
22.1
24.5
27.0
29.5
31.9
34.4
36.8
39.3
41 .7
44.2
46.6
49.1
51.6
54.0
66.5
58.9
61.4
63.8
66.3
68.7
71.2
73.6
76.1
76.6
81.0
83.5
85.9
86.4
90.8
93.3
' 95.7
96.2
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
..
, (
Figure 6-16. Weight And Moment Tables (Sheet 2 of 9)
(
(
1 April 1998
6-40
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
FUEL (JET A. JET A-l. JET B. JP-l AND JP-8 WITH DENSITY OF 6.7 LBS.lGAL. AT 60°F)
(
('
GALLONS
WEIGHT
(POUNDS)
MOMENT/lOOO
ARM VARIES
5
10
15
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
100
105
110
115
120
125
130
135
140
145
150
155
160
165
170
33
. 67
100
134
167
201
234
268
301
335
36B
402
435
469
502
536
569
B03
636
670
703
737
770
804
837
87i
904
938
971
.1005
1038
1072
1105
1139
6.1
12.3
18.6
24.8
31 .0
37 .2
43.4
49.6
55.8
62.0
68.2
74.4
80.6
86.8
93.0
99.2
105.4
111 .B
117.B
123.9
130.1
136.3
142.5
148.7
154.8
161.0
167.2
173.3
179.5
185.7
191.8
198.0
204.1
210.3
GALLONS
WEIGHT
(POUNDS)
MOMENT/1000
ARM VARIES
175
180
185
190
195
200
205
210
215
220
225
230
235
240
245
250
255
260
265
270
275
280
285
290
295
300
305
310
315
.320
325
327
330
332
1172
1206
1239
1273
1306
1340
1373
1407
1440
1474
1507
1541
1574
1608
1641
1675
1708
1742
1775
1809
1842
1876
1909
1943
1976
2010
2043
2077
2110
2144
2177
2189
2211
2224
216.5
222.6
228.8
. 234.9
241 .1
247.2
253.3
259.5
265.6
271 .8
277.9
284.0
290.2
296.3
302.4
308.5
314.7
320.8
32B.9
333.0
339.1
345.2
351.4
357.5
363.6
369.7
375.8
381.9
388.0
394.1
400.2
402.3
406.3
408.8
Figure 6-16. Weight And Moment Tables (Sheet 3 of 9)
6-41
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
(
FUEL (JP-4 WITH DENSITY OF 6.5 LBS.lGAl. AT 60°F)
WEIGHT
GALLONS (POUNDS)
5
10
15
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
100
105
110
115
120
125
130
135
140
146
150
155
160
165
170
33
65
98
130
163
195
228
260
293
325
358 .
390
423
455
488
520
553
585
618
650
683
715 .
748
780
813
846
878
910
943
975
1008
1040
1073
1105
MOMENT/1000
ARM VARIES
5.9
12.0
18.0
24.0
30.1
36.1
42.1
48.1
54.2
60.2
66.2
72.2
78.2
84.2
90.2
96.2
102.2
108.2
114.2
120.2
126.2
132.2
138.2
144.2
150.2
166.2
162.2
168.2
174.1
180.1
18S.1
192.1
198.1
204.0
WEIGHT
GALLONS (POUNDS)
176
180
18.5
190
195
200
205
210
215
220
225
230
235
240
245
250
255
260
265
270
275
280
285
290
295
300
306
310
315
320
325
327
330
332
1138
1170
1203
1235
1268
1300
1333
1365
1398
1430
1463
1495
1528
1560
1593
1625
1658
1690
1723
1755
1788
1820
1853
1885
1918
1950
1983
2015
2048
20BO
2113
2123
2145
2158
MOMENT/1000
ARM VARIES
210.0
216.0
221 .9
22i.9
233.9
239.8
245.8
251 .7
257.7
263.6
269.6
275.5
281.5
287.4
293.4
299.3
305.3
311.2
317.1
323.1
329.0
334.9
340.9
346.8
352.7
358.S
364.S
370.5
376.4
382.3
388.2
390.1
(
(
(
(
(
(
(
(
(
,
\
(
(
(
(
(
394.1
396,S
(
(
(
(
(
(
(
(
Figure 6-16. Weight And Moment Tables (Sheet 4 of 9)
1 April 1998
For Training Purposes Only
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
FUEL (JP-5WITH DENSITY OF 6.8 LBS.lGAL. AT 60°F)
WEIGHT
GALLONS (POUNDS)
34
68
102
136
170
204
238
272
306
340
374
408
442
476
510
544
578
612
646
680
714
748
782
816
850
884
918
952
986
1020
1054
1088
1122
1156
5
10
15
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
(
',:"
"
\c,\..
95
100
105
110
115
120
125
130
135
140
145
150
155
160
165
170
MOMENT/l000
ARM VARIES
GALLONS
WEIGHT
(POUNDS)
MOMENT!1000
ARM VARIES
6.2
12.5
18.8
25.1
31.4
37.8
44.1
50.4
56.6
62.9
69:2
75.5
81 .8
88.1
94.4
100.7
107.0
113.2
119.5
125.8
132.1
138.3
144.6
150.9
157.1
163.4
169.7
175.9
182.2
188.4
194.7.
200.9
207.2
213.4
175
180
185
190
195
200
205
210
215
220
225
230
235
240
245
250
255
260
265
270
275
280
285
290
295
300
305
310
315
320
325
327
330
332
1190
1224
1258
1292
1326
1360
1394
1428
1462
1496
1530
1564
1598
1632
1666
1700
1734
1768
1802
1836
1870
1904
1938
1972
2006
2040
2074
2108
2142
2176
2210
2223
2244
2258
21.9.7
225.9
232.2
238.4
244.7
250.9
257.1
263.4
269.6
275.8
282.0
288.3
294.5
300.7
306.9
313.1
319.4
325.6
331 .8
338.0
344.2
350.4
356.6
362.8
369.0
375.2
381.4
387.6
393.8
400.0
406.2
40B.4
412.3
414.9
Figure 6-16. Weight And Moment Tables (Sheet 5 of 9)
6-43
1 April 1998
For Trainln£!: Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE!
EQUIPMENT LIST
(
(
(
FUEL (AVIATION GASOLINE WITH DENSITY OF 6.0 LBS.lGAL. AT 60°F!
WEIGHT
GALLONS (POUNDS!
5
10
15
20
25
30
35
40
45
50
55
60
65
70
75
80
85
90
95
100
105
110
115
120
125
130
135
140
145
150
155
160
165
170
30 .
60
90
120
150
180
210
240
270
300
330
360
390
420
450
480
510
540
570
600
630
660
690
720
750
780
810
840
870
900
930
960
990
1020
MOMENT/1000
ARM VARIES.
GALLONS
5.5
11.1
16.6
22.2
27.7
33.3
38.9
44.4
50.0
55.5
61.1
66.6
72.2
77.7
83.3
88.8
94.4
99.9
105.5
111.0
116.5
122.1
127.6
133.1
136.6
144.2
149.7
155.2
160.7
166.3
171.8
177.3
182.8
188.3
175
180
185
190
195
200
205
210
215
220
225
230
236
240
245
250
255
260
265
270
275
280
285
290
295
300
305
310
315
320
325
326
330
332
WEIGHT
(POUNDS!
1050
1080
1110
1140
1170
1200
1230
1260
1290
1320
1350
1380
1410
1440 .
1470
1500
1530
1560
1.590
1620
1650
1680
1710
1740
1770
1800
1830
1860
1890
1920
1950
1957
1980
1992
MOMENT/1000
ARM VARIES
193.8
199.3
204.9
21Cl.4
215.9
221.4
226.9
232.4
237.9
243.4
248.9
254.3
269.8
265.3
270.8
276.3
281 .8
287.3
292.7
298.2
303.7
309.2
314.6
320.1
325.6
331 .1
336.5
342.0
347.5
352.9
358.4
359.6
363.8
366.1
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
{
(
(
(
Figure 6-16. Weight And Moment Tables (Sheet 6 of 9)
(
(
(
1 April 1998
6-44
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
BAGGAGE/CARGO (CABIN LOCATIONS)
WEIGHT
(POUNDS)
ZONE 0
ARM = 136.7
ZONE 1
ARM = 16B.4
ZONE 2
ARM=194.8
ZONE 3
ARM = 221.0
MOMENT/l000
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
lBO
190
200
210
220
230
240
250
260
270
2BO
290
300
310
320
330
340
350
360
370
380
390
400
410
420
430
440
450
460
470
480
490
500
(
{
1.4
2.7
4.1
5.5
6.B
B.2
9.6
10.9
12.3
13.7
15.0
16.4
17.8
19.1
20.5
21.9
23;2
24.6
26.0
27.3
2B.7
30.1
31 .4
32.8
34.2
35.5
36.9
38.3
39.6
41 .0
42.4
43.7
45.1
46.5
47.8
1.7
3.4
5.1
6.7
8.4
10.1
11 .8
13.5
15.2
16.8
lB.5
20.2
21 ;9
23.6
25.3
26.9
28.6
30.3
32.0
33:7
35.4
37.0
38.7
40.4
42.;
43.8
45.5
47.2
48.8
50.5
52.2
53.9
66.8
57.3
58.9
60.6
62.3
64.0
65.7
67.4
69.0
70.7
72.4
74.1
75.8
77.5
79.1
80.B
B2.5
84.2
1.9
3.9
5.B
7.B
9.7
11.7
13.6
15.6
17.5
19.6
21 .4
23.4
25.3
27.3
29.2
31 .2
33.1
35.1
. 37.0
39.0
40.9
42.9
44.8
46.8
4B.7
50.6
52.6
54.5
56.5
5B.4
60.4
62.3
64.3
66.2
68.2
70.1
72.1
74.0
76.0
77.9
79.9
81 .8
83.8
B5.7
B7.7
B9.6
91 .6
93.5
95.5
97.4
2;2
4.4
6.6
8.8
11.0
13.3
15.5
17.7
19.9
22.1
24.3
26.5
28.7
30.9
33.1
35.4
37.6
39.B
42.0
44.2
46.4
48.6
50.8
53.0
55.3
57.5
59.7
61.9
64.1
66.3
6R5
70.7
72.9
75.1
77.3
79.6
81 .8
84.0
86.2
88.4
90.6
92.B
95.0
97.2
99.4
101.7
103.9
106.1
108.3
110.5
,
~
Figure 6-16. Weight And Moment Tables (Sheet 7 of 9)
6-45
\ 1 April 1998
For Training rllrposesOnly
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
(
BAGGAGE/CARGO (CABIN LOCATIONS)
WEIGHT
(POUNDS)
ZONE 4
ARM=246.5
ZONE 5
ARM =271.5
ZONE 6
ARM =296.0
----
MOMENT/1000
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
150
170
180
190
200
210
220
230
240
260
260
270
280
290
300
310
320
325
330
340
350
360
370
380
390
400
410
420
430
440
460
460
470
480
490
500
2.5
4.9
7.4
9.9
12.3
14.8
17.3
19.7
22.2
24.6
27.1
29.6
32.0
34.5
37.0
39.4
41.9
44.4
46.8
49.3
51.8
54.2
56.7
59.2
61.6
64.1
66.6
69.0
71 .5
73.9
76.4
78.9
80.1
Bl .3
B3.B
86.3
88.7
91 .2
93.7
96.1
98.6
101.1
103.5
106.0
108.5
110.9
2.7
6.4
8.1
10.9
13.6
16.3
19.0
21 .7
24.4
27.1
29.9
32.6
35.3
38.0
40.7
43.4
46.2
48.9
51 .6
54.3
67.0
59.7
62.4
66.2
6,7.9
70.6
73.3
76.0
78.7
81 .4
84.2
86.9
88.2
89.6
92.3
95;0
97.7
100.5
103.2
105.9
108.6
3.0
5.9
8.9
11.8
14.8
17.8
20.7
23.7
26.6
29.6
32.6
35.5
38.5
41.4
44.4
47.4
50.3
63.3
66.2
69.2
62.2
65.1
68.1
71.0
74.0
77.0
79.9
82.9
85.8
88.8
91.8
94.7
96.2
(
(
Moment and
weight limits
shown for Zones
o thru 6 are
recommendations
only; maximum
loadlncf is
limite by floor
loading 1200 Ibs.!
sq.
and loaded
airplane C.G.
The addition of
plYwood flooring
IS recommended
to distribute
concentrated load
on seat tracks and
. floor structure.
ft.'
(
(
(
(
/
\. (
Figure 6-16. Weight And Moment Tables '(Sheet 8 of 9)
1 April 1998
6-46
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
BAGGAGE/CARGO (CARGO POD LOCATIONS)
WEIGHT
ZONE A
ARM = 132.4
ZONE B
AAM = 182.1
ZONEC
ARM=239.6
(LBS.)
MOMENT/1000
25
50
75
100
125
150
175
200
225
250
275
300
325
3.3
6 .6
9.9
13.2
16.5
19.9
23.2
26.5
29.8
33.1
4.6
9.1
13.7
18 .2
22.8
27.3
31.9
36.4
41 .0
45.5
50.1
54.6
59.2
6.0
12.0
18.0
24.0
29.9
35.9
41 .9
47.9
53 .9
59.9
65.9
71 .9
Figure 6-16. Weight And Moment Tables (Sheet 9 of 9)
6-47
1 April 1998
For Traininl! Purooses Onlv
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
SAMPLE
LOADING PROBLEM
1. Basic Empty Weight (USB the data pertaining to
your airplane as it is presently equipped. Includes
unusable fuel and full oil) .. .. .. .. . . .. . . . ... . . . .
2"Usable Fuel 1332 Gal. Maximum) . . .. . . . ...... . . .
3. Pilot,lSeat 1) (Sta. 133.5 to 146.5) .. . .. ...... . . • .
4. Front Passenger ISaal 2) ISta.133.5 to 146.5) ......
5. "Aft Passengers ICommuler Seating):
Seat 3 ISla. , 85.9) ..... .. .. . '.. .. .. . .. ; . .•• . .
Seats 4 and 5 ISta. 169.9) ..... , . , ... ..... ...
Seat 6 (Sta. 217.9) .... .. .. ...... .. .... . . .. ..
Seats 7 and 8 ISta. 201 ,9) .. ... ... .. . .... . . ..
Saats 9 and 10 (Sta. 233.9) .. .. , .... .... .....
H Aft Passengers (Utility Seating):
Seats 3 and 4 ISta. 166.5) .. ........... ......
Seats 5 and 6 ISta. 193.5) ....... .... .. ... .. .
Seats 7 and 8 ISta. 220.5) ...... ........... ..
Seat 9 ISta. 248.5) . . . .. .. .. ...... . ....... .. .
Seat 10 (Sta. 245.5) .. . .. . . . . . . .. . . .. . ... . . ..
6. Baggage/Cargo:
Zone 0 ISta. 118 to 155.4) .... .. .... . ,
Zone 1 ISta. 155.4 to 181.5) . .... .. . .. . . . . . . ..
Zone 2 (Sta. lBl :5 to 208) .. .. .... ..... .... .
Zone 3 ISta. 208 10 234) . . . . .. . . .. .. '.. ; . . . :...
Zone 4 (Sta. 234 to 259) ..... .. .. . ........ . . .
Zone 5 (Sta. 259 to 284) . .... .. . . .. .. . ....• . .
Zone 6 (Sta. 284 to 308) ..... . . .. .... . .... .. .
7. Cargo (Cargo Pod Locations):
Zone A ISla. 100 to 154.75) .. . . . . . . ...... .. . .
Zone B (Sta. 154.75 to 209.35) .. ...... . ..... , .
Zone:CJISta. 209.35 to 284) .. . . ... . .. . .. . ... .
SAMPLE
AIRPLANE
Weight
IIbs.)
,.
YOUR
AIRPLANE
Moment
Moment
(lb.-in.
Ilb.-in. Waight
/1000)
11000)
(Ibs.)
4:'65
0
70
.OC
190
38n
17
340
300
35.3
64.6
37.0
68.6
7 .2
..... ..
(
~
(
300
88.8
B. RAMP WEIGHT AND MOMENT . . .. .. . . . . . . . . .. .
8035
1459.0
9. Fuel allowance for engine start, laxi, and runup .. .
-35
-6.4
10. TAKEOFF WEIGHT AND MOMENT
(Subtract Step 9 from Step 8) .. .. . . . . . . ... . . .
BOOO
1452.6
(
(
11. Locate this point (8000 at 1452.6) on the Center of Gravity Moment Envelope, and
since this point falls wilhin the envelope, the loading is acceptable.
.*
* Refer to Weight and Moment Tables for .weight and moment of fuel being used.
Refer to Loading Arrangemenls Diag ram for aft passenger seating arrangements. Do
not combine Commuter seating and Utility sealing .
(
(
(
(
(
Figure 6-17. Sample Loading Problem (Sheet 1 of 2)
6-48
1 April 1998
For Training Purposes Only
(
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
CESSNA
MODEL 208 (675 SHP)
YOUR
AIRPLANE
Weight
(Ibs.)
Moment
(lb.-in.'
!1000)
YOUR
YOUR
YOUR
AIRPLANE
AIRPLANE
AIRPLANE
Weight
(Ibs.)
Moment
(lb.-in.'
!1000}
Weight
(lbs.)
Moment
(lb.-in.'
Weight
Moment
(lb.-in.'
11000)
(lbs.)
11000)
When several loading configurations are representative of your 0rcerations. It mB~ be
useful to fill out one or more of the above columns so that specific oedings are avai able
at a glance.
WARNING
It Is the responsibility of the pilot to ensure that the airplane Is loaded properly.
Operation outside of prescribed weight and balance limitations could result In en
accident and 8eriou8 or fetel injury.
A
,._:'.-
Figure 6-17. Sample Loading Problems (Sheet 2 of 2)
6-49
1 April 1998
For TrllininlJ PurDoSeS
Onlv
CESSNA
MODEL 208(675 SHP)
SECTION 6
WEIGHT & BALANCE/
EQUIPMENT LIST
LOADED AI RPLANE MOMENT/l000 (KI LOG.RAM-MILLIMETERSI
6000
6000
7000
8000
9000 10,000 11,000 12,000 13,000 14,000 15,000 16,000 17,000
8600
37&1
8000
(
3500
CENTER OF GRAVITY
MOMENT ENVELOPE
7500
(
32&1
7000
~
iii
c
~
g
...
«
CODE
Z
6500
-
30CXl
TAKEOFF AND LANDING
TAKEOFf ONLY
~w
6000
...:5
esoo
2750
t%
(
.,
~
;;:
...
(
w
2500
II:
c
..J
W
Z
~
8
g
%
C)
It:
(
...It:5
(
fil
(
;;:
6000
2250
0
g
«
0
4600
..J
NOTE
2000
To prevent loadings beyond the alt C,G,
lim ii, loadings which r..ult in the C.G.
falling within &haded area should be Uled
only if an accurate e.G. determination
4000
(
(
1750
has been obtained for that loading.
(
3600
(
3000
400
500
600
700
800
900
1000
1100
1200
1300
1400
1500
(
LOADED AIRPLANE MOMENTI1000 (POUND-INCHESI ·
A
(
WARNING
(
It is the responsibility of the pilot to ensure that the airplane Is
loaded properly. Operation outside ' of prescribed weight and
balance limitations could result in an accident and serious or
fatal injury,
(
(
(
(
(
2685X1084
Figure 6-1 8. Center of Gravity Moment Envelope
1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 6
WEIGHT & BALANCEI
EQUIPMENT LIST
AIRPLANE C.G. LOCATION - MILLIMETERS AFT OF DATUM (STA. 0.0)
4100
8500
J
4200
4300
4400
4500
4600
I
I
I
I
I
11
CENTER OF
GRAVITY LIMITS 1-1-1-1-:-4- "1-
8000
3750
t- :- \ I~
7500
en
o
Z
4700
Ie-
7000
3500
3250
:J
o
E:
I-
3000
I
6500
:t
"s:
jjj
t-
6000
w
z
~
CODE
5500
Co.
-
TAKEOFF
AND LANDING
- - - TAKEOFF ONLY
a:
.
Propeller . . ........ . .. . . . . .. . . ... . .. .' ... . .. . . . .
7-59
(
Overspeed Governor Test Switch . ... . . . .. ... . . ... .
(
Revision 6
7-2
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AI RPLANE AND
SYSTEry1S DESCRIPTION
(
TABLE OF CONTENTS (Continued)
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
Page
Fuel System ..................... . . . ............ .
7-59
Firewall Fuel Shutoff Valve ...................... .
7-63
Fuel Tank Selectors ........................... .
7-63
Fuel Selectors Off Warning System . .. ............. .
7-63
Auxiliary Boost Pump Switch ..................... .
7-64
Fuel Flow Indicator ............................ .
7-64
Fuel Quantity Indicators ............ . ... ; ....... .
7-65
Wing Tank Fuel low Warning Annunciators
......... . 7-65
Reservoir Fuel lqw Warning Annunciator
........... . 7-65
Fuel Pressure low Warning Annunciator ..........•.. 7-66
Auxiliary Fuel Pump On Annunciator .... : .......... .
7-66
. . . . . ............... . ............ .
Drain Valves
7-66
Fuel Drain Can ............ . . . ... . .......... .
7-67
Fuel Pump Drain Reservoir .................... . .7-67
Brake System .. ................................ .
7-68
Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-69
Generator Control Unit ....................... .
7-69
Ground Power Monitor ............... ... ..... .
7-73
Battery Switch ............................. .
7-73
Starter Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-73
Ignition Switch ........... .. ......... . ...... .
7-73
7-74
Generator Switch ........................... .
7-74
Avionics Power Switches ..................... .
Avionics Bus Tie Switch .......... . ........... .
7-74
External Power Switch ....... . ...... . ...... . . .
7-75
7-75
Circuit Breakers . ..... . ......... ... .... . .... .
7-76
Volt/Ammeter And Selector Switch .............. .
7-76
Annunciator Lights ................. . .... . ... .
7-76
Ground Service Plug Receptacle .. . . ... ....... . . .
7-77
lighting Systems ......................... . ...... .
7-77
Exterior lighting
........................... .
7-77
Navigation lights . .. . .. ~ ................. . .. .
7-77
landing lights .... ; ...... . . . ............... .
7~78
Taxi/Recognition lights ......... . . . . ......... . .
7-78
Strobe lights .............................. .
7-79
Flashing Beacon light ..... .. ......... . ...... .
7-79
Courtesy lights . ............ . ....... . ...... .
7-80
Interior lighting ....... .. ..................... .
left Flight Panel/left Flood lighting Control
....... . 7-80
Right Flight Panel/Right Flood lighting Control
..... . 7-80
7-3
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
{
TABLE OF CONTENTS (Continued)
Page
Lower Panel/Overhead Light,ng Controls . . .. .... ... .
Engine Instruments/Radio Lighting Control Knobs
Control Wheel Maplight ..... . ... . .... . . .. .... .
Cabin Lights
.............. ... .... . ... . . . . .. .
Passenger Reading Lights . . ... . ... . .. . ....... .
. No Smoking/Seat Belt Sign
. .. . . ... . . . . . . ... . . .
Cabin Heating, Ventilating And Defrosting System . . ... . . .
. . . . .... . . ... . .... . .. . . .
Bleed Air Heat Switch
Temperature Selector Knob
. . .. . .. . .. . . . .. . . .. .
Mixing Air Push-Pull Control ... .. . . .. . . .. ... . . . .
Aft/Forward Cabin Push-Pull Control . . ........ . .. .
Defrost/Forward Cabin Push-Pull Control
. . . .... . . .
Cabin Heat Firewall Shutoff Knob . ..... .. .. . . ... .
Vent Air Control Knobs . . ..... . ........... . ... .
Instrument Panel Vent Knobs ... . .. . ...... . .... .
Ventilating Outlets ............. . ... .. .. . ... . .
. Oxygen System ... .. . .. . . .. .. . . . . . .. .. . . .. . . . . .. .
Pitot-Static System And Instruments . . ... . .. . ..... . . . . .
Right Flight Instrument Panel Pitot-Static System
Airspeedlndicator(s)
.. . . . .. J . . . .. . . . . . . . . ... .
Vertical Speed Indicator(s) ... . . . .. . .. . ........ .
Altimeter(s) ........... . ....... . .. . .... . .. . . .
.. . ..... . . .. . ... ... .
Vacuum System And Instruments
Attitude Indicator .. . . . . ..... . . . .. ... . ..... . .. .
Directional Indicator . . . .. .. . . . .. . .. . ........ . .
Suction Gage . ... .. ... . . . .... . . . . .. .... . .. . .
Vacuum-Low Warning Annunciator ... . .... . . . .. . .
Outside Air Temperature (OAT) Gage . ......... . . . ... .
Stall Warning System . . . . . ..... . • . .. . .... . .. ... . . .
Avionics Support Equipment .... . .. . . . .. . .... .... . . .
Avionics Cooling Fan . ... .. ..... ... . ... . . .. . . .
Microphone-Headset Installations . ....... . ...... .
Static Dischargers .. ... ... ....... ... .. .... . .. . .
7-4
7-81
7-81
7-81 (
7-82 '
7-82
7-82
7-83
7-86
7-86
7-87
7~87
7-88
7-88
7-89
7-89
7-89
7-89
7-90
7-91
7~92 '
7-92 (
7-92
7-93
H~I
7-96
7-96
7-96
7-97
7-97
7-97
7-98
7 September 2001
For Training Purposes Only
(
(
(
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
TABLE OF CONTENTS (Continued)
Page
(
Cabin Features
......... ....................... .
Cabin Fire Extinguisher . . . . . . . . . . . . . . . . . . . . . . .
Sun Visors ................................
Map And Storage Compartments . . . . . . . . . . . . . ..
Beverage Cup Holders ..................... . .
Miscellaneous Equipment .............. . ..........
Cargo Barrier/Nets .. ... . ... " ... . ....... . ....
Cargo Partitions ............................
Cargo Door Restraining Net .............. , . . . .
Cargo/Airplane Tie-Down Equipment .............
Cargo Pod ... .. ........... . .. . . . ..........
Engine Inlet Covers and Propeller Anchor
. . . . . . ..
Refueling Ladder ................ . .. . .......
Hoisting. Rings .......... ..... .. .. ..........
.Crew Entry Step Assemblies
................. .
Relief Tube ... ........... . ... . .... . ... . ....
Oil Quick-Drain Valve . .......................
7-99
7-99
7 -100
7-100
7-100
7-101
7-101
7-101
1 April 1998
7-5/7-6
(
(
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(
(
(
(
(
7-101
7-101
7-101
7-102
7 -102
7-102
7-103
7-103
7-103
(
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(
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1<'0 .. Train;n ... Pnrnoli:pli: Onlv
(
(
(
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(
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
INTRODUCTION
This section provides description and operation of the airplane and
its systems. Some equipment described herein is optional and may
not be installed in the airplane. Refer to Section 9, Supplements,
for detai.ls of other optional systems and equipment.
(
j\WARNING
Complete familiarity with the airplane and Its
systems . will not only Increase the pilot's
proficiency and ensure optimum operation, but
could provide a basis for analyzing system
malfunctions In case an emergency Is
encountered. Information In this section will
assist in . that familiarization. The responsible
pilot will want to be prepared to make proper
and precise responses in every situation.
(
(
I
AIRFRAME
The airplane is an all-metal, high-wing, . single-engine airplane
equipped with tricycle landing gear and designed for general utility
purposes. The construction of the fuselage is a conventional
formed sheet metal bulkhead, stringer, and skin design referred to
as semimonocoque. Major items of structure are the front and rear
carry-through spars to which the wings are attached, a bulkhead
and forgings for main landing gear attachment and a bulkhead with
attaching plates at its base for the struHa-fuselage attachment of
the wing struts.
(
(
(
(
(
(
(
(
(
(
.,
.....
( C,;)
The externally braced wings, having integral fuel tanks, are
constructed of a front and rear spar with formed sheet metal ribs,
doublers, and stringers. The entire structure is covered with
aluminum skin. The front spars are equipped with wing~to-fuselage
and wing-to-strut attach fittings. The aft spars are equipped with
wing-tO-fuselage attach fittings. The integral fuel tanks are formed
by the front and rear spars, upper and lower skins, and inboard and
outboard .closeout ribs. Extensive use of bonding is employed in the
fuel tank area to reduce fueled tank sealing.
7-7
13 October 1999
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
(
Round-nosed ailerons and single-slot type flaps are of conventional formed sheet metal of each flap, is of conventional construction . The left aileron incorporates a servo tab while the right aileron
incorporates a trimmable servo tab, both mounted on the outboard ;
end of the aileron trailing edge.
\
The empennage (tail assembly) consists of a conventional vertical
stabilizer, rudder, horizontal stabilizer, and elevator. The vertical
stabilizer consists of a forward and aft spar, sheet metal ribs and
reinforcements, four skin panels, formed leading edge skins, and a
dorsal fin. The rudder is constructed of a forward and aft spar"
formed sheet metal ribs and reinforcements" and a wrap-around skin
panel. The top of the rudder incorporates a leading edge extension
which contains a balance weight. The horizontal stabilizer is
' constructed of a forward and aft spar, ribs and stiffeners, four upper
and four loWer skin panels, and two left and two right wrap-c;lround
skin panels which also form the leadingedges.~ The horizontal
stabilizer also contains dual jack screw type actuators for the
elevator trim tabs. Construction of the elevator consists of a forward
and aft spar, sheet metal ribs, upper and lower skin panels, and
wrap-around skin panels for the leading and trailing edges. An
elevator trim tab is attached to the trailing edge of each elevator by {
full length piano-type hinges. Dual push rods from each actuator \
located in the horizontal stabilizer transmit actuator movement to
dual horns on each elevator trim tab to provide tab movement. Both
elevator tip leading edge extensions provide aerodynamic balance
and incorporate balance weights. , A row of vortex generators on the
top of the horizontal stabilizer just forward of the elevator enhances
nose down elevator and trim authority.
To assure extended service life of the airplane, the entire airframe is
corrosion proofed. Internally, all ' assemblies and sub-assemblies are
coated with a chemical film conversion coating a~d are then epoxy
primed. Steel parts in contact with aluminum str4c1.ure are given a
chromate dip before assembly. Externally, the complete ,airframe is
painted with. an overall coat of polyurethane paint which enhances
resistance to corrosive elements in the atmosphere. Also, aI/ control
cables for the flight control system are of stainless steel
construction.
1 April 1998
7-8
For Training Purposes Only
(
(
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
FLIGHT CONTROLS
(
The airplane's flight control system (see Figure 7-1) consists of
conventional aileron, elevator and rudder control surfaces and a pair
of spoilers mounted above the outboard ends of the flaps. The
control surfaces are manually operated through mechanical linkage
using a control wheel for the ailerons, spoilers and elevator and
rudder/brake pedals for the rudder. The wing spOilers improve
lateral control of the airplane at low speeds by disrupting lift over
the appropriate flap. The spoilers are interconnected with the aileron
system through a push-rod mounted to an arm on the aileron
bellcrank. Spoiler travel is proportional to aileron travel for aileron
deflections in excess of 5° up_ The spoilers are retracted throughout
the remainder of aileron travel. Aileron servo tabs provide reduced
maneuvering control wheel forces. Fences on ailerons enhance
lateral stability.
(
TRIM SYSTEMS
(
/
(
(
(
(
,
\
(
(
(
(
Manually-operated aileron, elevator, and rudder trim systems are
provided (see Figure 7-1). Aileron trimming is achieved by a
trimmable servo tab attached to the right aileron and connected
mechanically to a knob located on the control pedestal. Rotating the
trim knob to the right (clockwise) will trim right wing down;
conversely, rotating it to the left (counterclockwise) will trim left wing
down.
Elevator trimming is accomplished through two elevator trim tabs by
utilizing the vertically mounted trim control wheelan the top left side
of the control pedestal. Forward rotation of the control wheel will
trim nose-down; conversely, aft rotation will trim nose-up. The
airplane may also be equipped with an electric elevator trim system.
Details of this system are presented in Section 9, Supplements.
(
(
(
(
Rudder trimming is accomplished through the nose wheel steering
bungee connected to the rudder control system and a ' trim control
wheel mounted on the control pedestal by rotating the horizontally
mounted trim control wheel either left or right to the desired trim
( " " position. Rotating the trim wheel to the right will trim nose-right;
.': .) conversely, rotating it to the left will trim nose-left.
"'-",;." .,
7-9
13 October 1999
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
(
(
AILERON/SPOILER CONTROL SYSTEM
,.......~.~.,.I~•
......
.
:.:... ..
....
.....:.......
(
.....
.......
(
(
(
/
(
AILERON TRIM CONTROL SYSTEM
26856025
26856026
Figure 7- 1. Flight Control And Trim Systems (Sheet 1 of 3)
. 1 April 1998
7-10
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
ELEVATOR CONTROL SYSTEM
(
(
(
(
(
.....
.
(
.:::':'~'"
......... :." .::'.
.........
.....
(
(
(
(
.....
(
<::::"":':~::'
(
(
r
(
f
I"
ELEVATOR TRIM CONTROL SYSTEM
(
(
(
(
.......
(
(
"
•
I
• •••• •~'.
1'0.......
: : : .:";:~ .:•.-..'. ~.:.•. :.,. :..:.:.:.:..•.:'..:,.,'..,..,...,.:.'.."~••.
-~l.:~,:..
\.;." .,!.~:
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·:.:,:.'.·:.:.;r"
,'.::·.:.·:$::..J:;:·'" . ". '-'..,
..
:: .
... ~~r·
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.. ' ·· ...... "':::··:.::,·:,".c,·.:.: ...
(.;,,)
.......
·"::.:.·,:;:':'._.::.'.:.:.1:..
. .:.:. . . ...,,:.::.':.:... '
(
(
:
..... ....:'.~ ... ..
....
................
..<:.:::::.' \:.....
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....•.
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~.:,l~.:.,'.;~,: : :: '::;: :;
.:
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" ....-'......::.::~,~;~::~:~:
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.....
•• - . .
• • •• •• • .:::. .. ......
{~~
... . \~/" I'
.,•. " ...... ..,'
...
<"::~ <>. >: ...
..... " ..........
;:.~.];~;[::>
26856027
26856028
(
(
<.\1·::
ao
co
1ft
•
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....
26656030
Figure 7-2. Typical Instrument Panel (Sheet 1 of 2)
1 April 1998
7-14
For Training Purposes Only
~~~~~~~
~~~~~
(~'
/""~"::'\,
~;'
}>
-0
~
CD
CD
CO
..,~
..,
~
;;rJQ
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=
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....-:-'
U1
~~~~~~~~~~
1.
2.
3.
4.
5.·
6.
7.
,~ ..... \
....
~()
Altitude Alerter
Propeller Anti-ice Ammeter
Suction Gage
31.
Fright Hour Recorder
32.
Right Auxilairy Mic and Phone Jacks
Clock
34. instrument Panel Ventilating Outlet
35. Map Compartment
Airplane Registration Number
Additional Instrument Space
Fire Detection Test and Annunciator Panel
Function Switches
8. Autopilot Roll Trim Indicator and
Autopilot Annunciators
9. PHot's Flight Instrument Group
10. Annunciator Panel
11. ADF Bearing Indicator (No. 2)
12. Torque Indicator
13. DME, Course Deviation Indicator (No. 21
andADF Bearing Indicator (No. "
14. PropeUer aPM Indicator
15. Magnetic£ompass
16. ITT Indicator
17. Marker Beacon Indiccitor Lights and
Switchesl Audio Control Panel
18. N,'l6 RPM Indicator
19. NAV/COM Radios
20. OilPressure Gage/Oil Temperature Gage
21. Transponder
22. Fuel Flow Indicator
23. Autopilot Control Unit
24. Left Fuel Quantity Indicator
25. HF Radio
26. Right Fuel Quantity Indicator
27. Weather Radar
28. Fuel Totalizer
29. ADF Radios
30. Right R ight Instrument Group
Om
oen
men
33 . . Instrument Panel Ventilating Control
36.
37.
38.
39.
40.
41 .
42.
43.
44.
45.
46.
47.
48.
49.
50.
51 .
52.
53.
54.
55.
56.
57.
Right Control Wheel Location
cabin Heat Switch and Control Panel
Rudder lock Control Handle
Wing Aap Selector lever and Position Indicator
ProPeller Control lever .
Quadrant Friction lock
Fuel Condition Lever
Fuel ShUtoff Control
Cabin Hllat Firewall Shutoff Control
Rudder Trim Control Wheel and Position Indicator
Aileron Trim Control Knob and Position Indicator
Elevator Trim Control Wheel and Position Indicator
Emergency Power Lever
Power lever
Inertial Separator Control
Instrument, Radio Dial, and Control Panel Lighting
Rheostats
Parking Brake Handle
Pftofs Controf Wheel Location
DlHce/Anti-ice Switch Panel
Lighting Control Panel
Volt/Ammeter Selector Switch
Static Pressure Alternate Source Valve
58. Volt/Amineter
59. Pilot's Auxiliary Mic and Phone Jacks
60. Instrument Panel Ventilating Outlet
61. Instrument Panel Ventilating Control
62. Overspeed Governor Test Switch
rZ
1\)>
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m
--.J
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en
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..3!
en
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en
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m
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arm
:n»a
_Z--i
-om_
~»O
OZZ
ZO--.J
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
LEFT SIDEWALL SWITCH AND CIRCUIT BREAKER PANEL
Most of the engine control switches and all circuit breakers are ,
located on a separate panel mounted on the left cabin sidewall \.
adjacent to the pilot. Switches and controls on this panel are
illustrated in Figure 7-3.
ANNUNCIATOR PANEL
The annunciator panel (see Figure, 7-4) is located at the top edge of
the instrument panel directly in front of the pilot. The panel contains
separate indicator lamps which illuminate green, amber or red 'when
a specific condition occurs in the associated airplane system . A
green colored lamp is illuminated to indicate a normal or safe
condition in the system. An illuminated amber lamp indicates that a
cautionary condition exists which mayor may not require immediate
corrective action. When a hazardous condition exists requiring
immediate corrective action, a red lamp illuminates.
I
NOTE
Some annunciator lights shown in Figure 7-4 are
optional.
Two annunciator panel function switches, labeled LAMP ' TEST and
DAY/NIGHT, are located to the left of the panel. When activated, the
LAMP TEST switch illuminates all lamps on the annunciator panel
and activates both of the fuel selector . off warning horns. The
DAY/NIGHT switch provides variable intensity down to a preset
minimum dim level for the green lamps and some of the amber
lamps (when in the NIGHT position). This variable intensity is
controlled by the ENG INST lighting ~heostat.
NOTE
If a red or non-dimmable amber annunciator
illuminates at night and becomes an unacceptable
distraction to the pilot because of its brightness
leve', it may be extinguished for the remainder of the
flight ·by pushing in on the face of the light assembly
and allowing it to pop out. To reactivate the
annunciator, pull the light assembly out slightly and
push back in.
Revision 6
7-16
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
(
(
AVIONICS
STANDBY
STANDBY
POWER
POWER
SWITCH/BREAKER SWITCH
AVIONICS
BUS TIE
GENERATOR
SWITCH
--~~~
~---
SWITCH/BREAKER~\ 1t'=it. w,,~
EXTERNAL
POWER
SWITCH
(
(
(
(
BATTERY
SWITCH
AVIONICS
POWER
SWITCH/
BREAKER (2)
r-
0 1
I':
(
I
(
(
~~ Hl~~' =1. =~~ ~~L
!::-'
~e~~~~~0)~@5.
_
I" - Ul
I
II
(
:!: ;: i::i ::i
'.l
In
run
"'At
m
u"
Jill
'IL
nil'
_
_
lLU'
III
WI'
.n
_
un
.,
o
FUEL
BOOST
SWITCH
_
"':--l
"Tft "'I·ItI ..n.1CI
~@~~~~~~~~
I
GENERAL
CIRCUIT
BREAKERS
BUS 1
~~(@G~~~~~0il-41--1-~ GENERAL
CIRCUIT
BREAKERS
BUS2
(
(
,I ,
(
I
(
(
(
I
'hiI ...I
I'''''
1m
I
I
M'~'::II
I
I
,tt,
II ....
IIIDI
••
ilI~
itll
M
i
I0Il1
AVIONICS -I4--+-!tI-!-~O~00~O~O~
CIRCUIT
BREAKERS
BUS 1
(
AVIONICS
CIRCUIT
BREAKERS
BUS2
(
(
(
26182010C
Figure 7-3. Typical Left Sidewall
Switch and Circuit Breaker Panel
(
7-17
1 April 1998
For Traininl! Purooses Onlv
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
21
20
19
18
17
ILLUMINATION CODE
ti:;i~~~~~:il RED - HAZARDOUS CONDITION (Requires Immediate
Corrective Action)
1: 1 AMBER - CAUTIONARY CONDITION (May Require
Immediate Corrective Action)
[==:J GREEN - NORMAL OR SAFE CONDITION
I
I UNUSED ANNUNCIATOR SPACE
2685M6008
24
23
22
1. VOLTAGE LOW (RED) - Indicates electrical system bus voltage
is low and power is being supplied from the battery.
2, ENGINE FIRE (RED) - Indicates an excessive temperature
condition and/or possible fire has occurred in the engine
compartment.
3. VACUUM LOW (RED) -Indicates the vacuum system suction is
less then approximately 3.0 in. Hg.
4. OIL PRESSURE LOW (RED) - Indicates engine oil pressure is
less than 38 psi.
5. RESERVOIR FUEL LOW (RED) - Indicates the tuellevel in the
reservoir tank is approximately one-half full or less.
.
6. GENERATOR OFF (RED) - Indicates the generator is not
connected to the airplane bus.
7. LEFT FUEL LOW (AMBER) - Indicates fuel quantity in the left
fuel tank is 25 gallons or less.
8. EMERGENCY POWER LEVER (RED) - Indicates the emergency
power lever is advanced out of the NORMAL position.
Figure 7-4. Typical Annunciator Panel (Sheet 1 of 2)
7-18
1 April 1998
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
9.
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
RIGHT FUEL LOW (AMBER) - Indicates fuel quantity in the
right fuel tank is 25 gallons or less.
10. AUXILIARY FUEL PUMP ON (AMBER) - Indicates the auxiliary fuel pump is operating.
11. STANDBY ELECTRICAL POWER ON (AMBER) - Indicates
the standby alternator is supplying electrical power to the
bus.
12. FUEL PRESSURE LOW (AMBER) - Indicates fuel pressure
in the fuel manifold assembly is below 4.75 psi.
13. . NOT USED.
14. STARTER ENERGIZED (AMBER) - Indicates the startergenerator is operating in the starter mode.
15. FUEL SELECT OFF (RED) - Indicates one or both fuel tank
selectors are off.
16. IGNITION ON (GREEN) - Indicates electrical power is
being supplied to the engine ignition system.
17. DE-ICE PRESSURE (GREEN) - Indicates pressure in the
de-ice boot system has reached approximately 15 psig.
18. WINDSHIELD· ANTI-ICE · (GREEN) - Indicates electrical
power is being supplied to the. windshield anti-ice power
relay.
19. STANDBY ELECTRICAL POWER INOPERATIVE (AMBER)
- Indicates electrical power is not available from the
standby alternator.
20. CHIP DETECTOR (AMBER) - Indicates that metal chips
have been detected in either the reduction gearbox case, or
accessory gearbox case.
21. BATTERY HOT (AMBER) - Indicates the electrolyte
temperature in the optional Ni Cad battery is excessively
high.
22. BATTERY OVERHEAT (RED) - Indicates the electrolyte
temperature in the optional Ni Cad battery is critically high.
23. NOT USED.
24. DOOR WARNING (RED) - Indicates the upper cargo door
and/or upper aft passenger doors (Standard 208 only) are
not latched;
(
(
Figure 7-4. Annunciator Panel (Sheet 2 of 2)
7-19
29 September 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION .
CESSNA
MODEL 208 (675 SHP)
GROUND CONTROL
Effective ground control while taxiing is accomplished through nose
wheel steering by using the rudder pedals; left rudder pedal to steer i
left and right rudder pedal to steer right. When a rudder pedal is \.
depressed,a spring-loaded steering bungee (which is connected to
the nose gear and to the rudder bars) will turn the nose wheel
through an arc of approximately 15° each side of center. By
applying either left Or right brake, the degree of turn may be
increased up 10 56° each side of center.
Moving the airplane by hand is most easily accomplished .by
attaching a tow bar (stowed in aft baggage/cargo compartment) to
the nose gear fork axle holes. If a tow bar is not available, or
pushing is required, use the wing struts as push points. Do not use
the propeller blades .or spinner to push or pull the airplane. If the
airplane is to be towed by vehicle, never turn the nose wheel
beyond the steering limit marks either side of center. If excess force
is exerted beyond the turning limit, a red over-travel indicator block
(frangible stop) will fracture and the block, attached to a cable, will
fall into view alongside the nose strut. This should be checked . .
routinely during preflight inspection to prevent operation with a i
damaged nose gear.
The minimum turning radius of the airplane, using differential
braking and nose wheel steering during taxi, is as shown in Figure
.
7-5
1 April 1998
7-20
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
(
(
1 4 - - - 63.75 FEET (WITH STROBE LIGHTS)
(
,-~--~
(
(
"
31 ..875 FEET
(WITH STROBE LIGHTS)
/:
(
11 .67
FEET
"\
12.97 FEET
.,. ~~-"
(
\
\
/
(
(
(
'1
(
(
(
I
{
i
'-'"
(
j
i
(
(
NOTE:
MINIMUM TURNING RADIUS WITH
INBOARDWHEEL BRAKE LOCKED,
FULL RUDDER AND POWER
(
(
(
(
(
(
(
(
(
26856009
(
Figure 7·5. Minimum Turning Radius
(
(
7-21
1 April 1998
F()r Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP) ·
......,
....
...-.•.~..
:
.......
"
....
\ .•. ...•.;:...
,:.;~t"
.', . .
...:..............
......
26856033
Figure 7-6. Wing Flap System
WING FLAP SYSTEM
The wing flaps are large span, single-slot type (see Figure 7-6) and
are driven by an electric motor. The wing flaps are extended or
retracted by positioning the wing flap selector lever on the control
pedestal to the desired flap deflection position. The selector lever is
moved up or down in a slotted panel that provides mechanical
stops at the 10 0 and 20 0 positions. For flap deflections greater
than 10 0 , move the selector lever to the right to clear the stop and
position it as desired. A scale and white-tipped pOinter on the left
side of the selector lever provides a flap position indication. The
wing flap system is protected by a "pull-off" type circuit breaker,
labeled FLAP MOTOR, on the left sidewall switch and circuit
breaker panel.
.
A standby system can be used to operate the flaps in the event
the primary system should malfunction. The standby system
consists of a standby motor, a guarded standby flap motor switch
and a guarded standby flap motor up/down switch located on the
overhead panel. Both guarded switches are safetied in the closed
position with breakable copper wire.
1 April 1998
7-22
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
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SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
The guarded standby flap motor switch located on the overhead
panel has NORM and STBY positions. The guarded NORM position
of the switch permits operation of the flaps using the control
pedestal mounted selecto'r; the STBY position is used to disable the
dynamic braking of the primary flap motor when the standby flap
motor system is operated.
The standby flap motor up/down switch has UP, center off and
' DOWN positions. The switch is guarded in the center off position. I
To operate the flaps with the standby system, lift the guard breaking
safety wire, and place the standby flap motor switch in STBY
position; then, lift the guard, breaking safety wire and actuate the
standby flap motor up/down switch momentarily to UP or DOWN, as
,desired. Observe the flap position indicator to obtain the pesired
flap position. Since the standby flap system does not have limit
switches, actuation of the standby flap motor up/down switch should
be terminated before the flaps reach full up or down travel. After
actuation of the standby flap motor system, switch guards should be
resafetied to the closed position by maintenance personnel when
maintenance action is accomplished. The standby flap system is
protected by a "pull-off" type circuit breaker, labeled STBY FLAP
MOTOR, located on the left sidewall switch and circuit breaker
panel.
LANDING GEAR SYSTEM
(
The landing gear is of the tricycle type with a steerable nose wheel
and two main wheels. Shock absorption is provided by the tubular
spring-steel main landing gear struts, an interconnecting springsteel tube between the two main landing gear struts, and the nose
gear oil-filled shock strut and spring-steel drag link. Each main gear
wheel is equipped with a hydraulica"y actuated single-disc brake on
the inboard side of each wheel. To improve operation from
unpaved runways, and in other conditions, the standard nose gear
fork and standard tires can be replaced with a three-inch extended
nose gear fork and oversized nose and main gear tires.
. 7-23
7 September 2001
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
BAGGAGE/CARGO COMPARTMENT .
(
The space normally .used for baggage consists of the raised area
(
from the back of the cargo doors to the aft cabin bulkhead. Access . ·
to the baggage area is gained through the cargo doors, the aft ! (
passenger door (Passenger version only), or from within the cabin.
Quick-release tie-down ring/strap assemblies are provided for
securing baggage and are attached to baggage floor anchor plates
provided in the airplane. When utilizing the airplane as a cargo
carrier (Passenger version and Cargo version) refer to Section 6 for
complete cargo loading details.
When loading the Passenger
version,passengers should not be placed in the baggage area
unless the airplane is equipped with special seating for this area.
Also, any material that might be hazardous to the airplane or
occupants should not be placed anywhere in the airplane. For
baggage/cargo area and door dimensions, refer to Section 6.
SEATS
Standard seating consists of both a pilat's and front passenger's
Six-way adjustable seat. Additional cabin seating is available on the ;
Passenger version which consists of three rows of two place fixed \
seats and two rows of two place fixed seats and two rows of oneplace fixed seats in the Commuter configuration, or four rows of
one-place, fixed-position collapsible seats on each side of the oabin
in the Utility configuration.
.
A WARNING
None of the airplane seats are approved for
installation facing aft.
PILOT'S AND FRONT PASSENGER'S SEATS
The six-way adjustable . pilot's or front passenger's seats may be
moved forward or aft, adjusted for height, and the seat back angle
changed. Position the seat by pulling on the small T-handle under
the center of the seat bottom and slide the seat into position; then
release the handle, and check that the seat is locked in place by
attempting to move the seat and by noting that the small pin on the
end of the T -handle protrudes.
1 April 1998
7-24
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
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SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
The seat is not locked if the pin is retracted or only partially extends.
Raise or lower the seat by rotating a large crank under the front
right corner of the seat. Seat back angle is adjusted by rotating a
small crank under the front left corner of the seat. The seat bottom
angle will change as the seat back angle changes, providing proper
support. Armrests can be moved to the side and raised to a
pOSition beside the seat back for stowage.
PASSENGERS' SEATS (COMMUTER) (Passenger version Only)
The third and sixth seats are individual fixed-position seats with
fixed seat backs. Seats for the fourth and fifth, seventh and eighth,
and ninth and tenth positions are two-place, fixed-position bench
type seats with fixed seat backs. All seats are fastened with quickrelease fasteners in the fixed position to the seat tracks. The seats
are lightweight and quick-removable to facilitate cargo hauling.
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PASSENGERS' SEATS (COLLAPSIBLE) (Passenger version
Only)
Individual collapsible seats are available for the aft eight passenger
positions. The seats, when not in use, are folded into a compact
space for stowage in the aft baggage area. When desired, the seats
can be unfolded and installed in the passenger area. The seats are
readily fastened with quick-release fasteners to the seat tracks in
anyone of the eight seat pOSitions.
HEADRESTS
Headrests are available for all seat ·configurations except the aft
passenger's collapsible seats. To adjust a pilot or front passenger
seat headrest, apply enough pressure to it to raise or lower it to the
desired level. The aft passenger seat headrests are not adjustable.
SEAT BELTS AND SHOULDER HARNESSES
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All· seat positions are equipped with seat belts and separate
shoulder harnesses.
The pilot's and front passenger's seat
positions are equipped with shoulder harnesses with inertia reels.
A WARNING
Failure to properly utilize seat belts and shoulder
harnesses could result In serious or fatal Injury In the
event of an accident.
7-25
7 September 2001
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
AFT PASSENGERS SEATS
.
(Left Hand Commuter Seating Shown)
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NARROW
RELEASE
STRAP
FREEENDOF
HARNESS
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SEAT BELT ·
BUCKLE
HALF
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SEAT BELT
LINK HALF
AND SHOULDER
HARNESS
RETAINING
STUD
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26656031
Figure 7-7. Seat Belts and Shoulder Harnesses (Sheet 1 of 2)
1 April 1998
7-26
For Training Purposes Only
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
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PILOT'S &PASSENGERS SEATS
(Typical)
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SHOULDER
HARNESS
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SEAT BELT
BUCKLE
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....
\.~
CROTCH
STRAP
FREE END
OF SEAT
BELT
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NARROW
ADJUSTER
STRAP
LOCK -~_~____
INDICATOR
PIN (SEAT
FORE AND AFT
ADJUSTMENT)
SEAT HEIGHT
ADJUSTMENT
SEAT BACK ANGLE
ADJUSTMENT
; (~:#
26192017A
Figure 7·7. Seat Belts and Shoulder Harnesses (Sheet 2 of 2)
7-27
7 September 2001
For Trllining Purooses On Iv
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
- MODEL 208 (675 SHP)
SEAT BELTS, STRAP AND SHOULDER HARNESS
(Pilot/Front Passenger Seats)
(
Both the pilot's and front passenger's seat positions are equipped (
with a five-point restraint system which combines the function of \
conventional type seat belts, a crotch strap, and an inertia reel
equipped double-strap shoulder harness in a single assembly. The
seat belts and crotch strap attach to fittings on the lower seat frame
and the inertia reel for the shoulder harness attaches to the frame of
the seat back.
(
The right half of the seat belt contains the buckle, which is the
connection point for the left belt half, crotch strap and harnesses.
The left belt, crotch strap and harnesses are fitted with links which
insert into the buckle. Both halves of the seat belt have adjusters
with narrow straps to enable the belt halves to be lengthened prior
to fastening.
To use the restraint system, , lengthen each half of the belt as
necessary by pulling the buckle (or connecting link) to the lap with
one hand while pulling outward on the narrow adjuster strap with .
the other hand. Insert the left belt link into the left slot of the buckle. t, (
Bring the crotch strap upward and insert its link into the bottom slot
in the buckle. Finally, position each strap of the shoulder harness , (
over the shoulders and insert their links into the upper slots in the
buckle.
The seat belts should bei tightened for a snug fit by
grasping the free end of each belt and pulling up and inward
During flight operations, the inertia reel allows complete freedom of
upper body movement; however, in the event of a sudden
deceleration, the reel jwililock automatically to protect the occupant.
During flight operations, the inertia reel allows complete freedom of
upper body movement; however, in the event of ' a sudden
deceleration, the reel will lock automatically to protect the occupant.
A WARNING
Failure to properly utilize seat belts and shoulder
harnesses could result in SERIOUS or FATAL
injury in the event of an accident.
7-28 \
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
Release of the belts, strap, and harnesses is accomplished by simply twisting the front section of the buckle in either direction and
pulling all connecting links free.
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CABIN ENTRY DOORS
Entry to, and exit from the airplane is accomplished through an
entry door on each side of the cabin at the pilot's and front
passenger's positions and, on the Passenger version only, through
a two-piece, airstair type door on the right side of the airplane just
aft of the wing (refer to Section 6 for cabin and cabin entry door
dimensions). A cargo door on the left side of the airplane also can
be used for cabin entry.
CREW ENTRY DOORS
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The left crew entry door incorporates a conventional exterior door
handle, a key-operated door lock, a conventional interior door
. handle, a lock override knob, and an openable window. The right
crew entry door incorporates a conventional exterior door handle, a
conventional interior door handle, and a manually-operated inside
door lock. To open either entry door from outside the airplane (if
unlocked), rotate the handle down and forward to the OPEN
position. To close the door from inside the airplane, use the
conventio'nal door handle and door pull. The inside door handle is a
three-position handle with OPEN, CLOSE and LATCHED positions.
Place the handle in the CLOSE position and pull the door shut; then
rotate the handle forward to the LATCHED position. When the
handle is rotated to the LATCHED position, an over-center action
will hold it iii that position.
A CAUTION
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Failure to properly close and latch the crew
doors may allow them to open In flight.
A lock override knob on the inside of the left crew door provides a
means of overriding the outside door lock from inside the airplane.
To operate the override, pull the knob and rotate it in the placarded
direction to unlock or lock the door. Both crew doors should be
latched ,prior to flight, and should not be opened intentionally during
flight. To lock the crew entry doors when leaving the airplane, lock
the right entry door with the manually-operated inside door lock,
close the left crew entry door, and using the key, lock the door.
7-29
7 September 2001
.
/
For Training Purposes Only
SECTION 7
CESSNA
AIRPLANE AND
MODEL 208 (675 SHP)
SYSTEMS DESCRIPTION
PASSENGER ENTRY DOOR (Passenger Version Only)
The passenger entry door consists of an upper and lower section.
When opened, the upper section swings upward and the lower ,
section drops down providing integral steps to aid in boardin'g or (
exiting the airplane. , The upper door section incorporates a
conventional exterior door handle with a separate key-operated lock,
a pushbutton exterior ,door release, and an interior door handle
which snaps into a locking receptacle. The lower door section
features a flush handle which is accessible from either inside or
outside the airplane. This handle is designed so that when the
upper door is closed, the handle cannot be rotated to the open
position. The lower door also contains integral door support cables
and a door lowering device. A cabin door open warning system is
provided as a safety feature so that if the upper door is not properly
latched, a red light, labeled DOOR WARNING, located on the
annunciator panel, illuminates to alert the pilot.
To enter the airplane through the passenger entry door, depress the
exterior pushbutton door release, rotate the exterior door handle on
the upper door section counterclockwise to the open pOSition, and .
raise the door section to the over-center position. Following this !
action, the gas spring telescoping door lift automatically raises the i ,
door to the ful/l,Jp position. Once the upper section is open, release
the lower section by pulling up on the inside door handle and
rotating the handle to the OPEN position. Lower the door section
until it is supported by the integral support cables. The door steps
deploy automatically from their stowed positions.
A
WARNING
The outside proximity of the lower door section
must be clear before opening the door.
Closing the passenger entry door . from inside the airplane is
accomplished by grasping the support cables of the lower door
section and pulling the door up until the top edge is within reach,
then grasping the center of the door and pulling inboard until the
door is held snugly against the fuselage door frame. Latch the
lower door section by rotating the inside handle forwa~d to the
. CLOSE position.
7-30
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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Check that the lower front and rear latches are properly engaged.
After the lower door section is secured, grasp the pull strap on the
upper door section and pull down and inboard. As the door nears
the closed position, pull inboard firmly to assure engagement of the
latching pawls. Once the latching pawls are engaged, the inside
handle should be · rotated counterclockwise to the horizontal
(latched) position, but do not use excessive force. If the handle will
not rotate easily, the door is not fully closed. A more firm closing
motion should allow the latching pawls to engage and permit the
door handle to rotate to the latched position. Then snap the interior
handle into its locking receptacle.
A CAUTION
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Refer to Section 3, EMERGENCY PROCEDURES,
for proper operational procedures to be followed
if the passenger entry door should Inadvertently
open In flight.
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Exit from the airplane through the passenger entry door is
accomplished by pulling the upper door section inside handle from
its locked position receptacle, rotating the handle clockwise to the
open position, and pushing the door outward. Once the door is
partially open, the automatic door lift will raise the upper ·door
section to the fully open position. Next, rotate the lower section
door handle up and aft to open position and push the door outward.
The telescoping damper will lower the door to its fully open position
and the integral steps will deploy.
A
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WARNING
(
The outside proximity of the lower door section
must be clear before opening the door
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7-31
7 September 2001
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
Closing the passenger entry door from outside the airplane is accomplished by raising the lower door section until the door is held
firmly against the fuselage door frame. Latch the lower door section
by rotating the inside handle' forward and down to the CLOSE position . After the lower door section is secured, grasp the pull strap on'
the upper door section and pull down. As the door nears the closed
position, grasp the edge of the door and push inward firmly to assure engagement of the latching pawls. Once engaged, the outside
door handle can be rotated clockwise to the horizontal (latched) position. After entering the airplane, snap the upper door interior handle into its locking receptacle (unless cargo obstructs access to the
door) . If desired when leaving the airplane parked, lock the handle
in the horizontal position by use of the key in the outside key lock.
A WARNING
Do not use the outside key lock to lock the door
prior 10 flight since the door could not be
opened from the Inside If It were needed as an
emergency exit.
The exterior pushbutton-type lock release,located on the · upper ..
door section just forward of the exterior door handle, operates in
(
conjunction with the interior door handle and is used whenever it is
desired to· open the door from outside the airplane while the interior
(
door handle is in the .Iocked position. Depressing the pushbutton
releases the interior door handle lock and allows the exterior door
handle to function normally to open the door.
CARGO DOORS
A two-piece cargo door is installed on the left side of the airplane
just aft of the wing trailing edge. The cargo door is divided into an
upper and a lower section. When opened, the upper section swings
upward and the lower section swings forward to create a large
opening in the side of the fuselage which facilitates the loading of
bulky cargo into the cabin . The upper section of the cargo door
incorporates a conventional exterior door handle with a separate
key-operated lock, and, on the Passenger version only, a
pushbutton exterior emergency door release, and an interior door
handle which snaps into a locking receptacle.
1 April 1998
7-32
For Training Purposes Only
(
CESSNA
SECTION 7
MODEL 208 (675 SHP)
(
AIRPLANE AND
SYSTEMS DESCRIPTION
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The upper door also incorporates two telescoping door lifts which
raise the door to the fully open position, when opened. A cargo door
open warning system is provided as a safety feature so that if the
upper door is not properly latched, a red light, labeled DOOR
WARNING, located on the annunciator panel, illuminates to alert the
pilot. The lower door section features a flush handle which is accessible from either inside or outside the airplane. The handle is
designed so that when the upper door is closed, the handle cannot
be rotated to the open position.
(
A
CAUTION
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Failure to properly latch the upper cargo door
section will result In illumination of the red door
warning annunciator. inattention to this safety
feature may allow the upper cargo door to open
In flight.
To open the cargo door from outside the airplane, depress the
upper door section exterior pushbutton door release (Passenger
version only) and rotate the exterior door handle clockwise to the
open position. Following this action, the telescoping door lifts will
automatically raise the door to the full up position. Once the upper
section is open, release the lower section by pulling up on the
inside door handle and rotating the handle to the OPEN position.
Open the door forward until it swings around next to the fuselage
where it can be secured to the fuselage by a holding strap or chain.
To close the cargo door from outside the airplane, disconnect the
holding strap or chain from the fuselage, swing the door aft to the
closed position, and hold the door firmly against the fuselage door
frame to assure engagement of the latching pawls. Latch the lower
door section by rotating the inside handle forward and down to the
CLOSE position. After the lower door section is secured, grasp the
pull strap on the upper door section and pull down.
(
7-33
7 September 2001
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
As the door nears the closed position, grasp the edge of the .door
and push inward firmly to assure engagement of the latching pawls.
Once engaged, the exterior door handle can be rotated
counterclockwise to the horizontal (latched) position.
On the ,
Passenger version only, after entering the airplane, snap the upper ',
. door interior handle into its locking receptacle (unless cargo
obstructs access to the door). 11 desired when leaving the airplane
parked, lock the handle in the horizontal position by use of the key
in the outside, key lock. To open the cargo door from inside the
airplane (Passenger version only), open the upper door section by
pulling the inside door handle from its locked position receptacle,
rotating the handle counterclockwise to the vertical position, and
pushing the door outward. Once the door is partially open, the
automatic door lifts will raise the upper door section to the fully open
position. Next, rotate the lower section door handle up and aft to
the open position and push the aft end of the ,door outward. The
door may be completely opened and secured to ' the fuselage with
the holding strap or chain from outside.
A
WARNING
Do not attempt to exit the Cargo version through
the cargo doors, since the inside of the upper
door has no handle, exit from the airplane
through these doors is not possible.
To close the cargo door from inside the airplane (Passenger version
only), disconneqt the holding strap or chain from the fuselage and
secure it to the door. Pull the door aft to the closed position and
hold the aft edge of the door firmly against the fuselage door frame
to assure engagement of the latching pawls. Latch the lower door
' section by rotating the inside handle forward and down to the
CLOSE position.
1 April 1998
7-34
For Training Purposes Only
(
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CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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After the . lower door section is secured, grasp the pull strap on ·tl:1e
upper door section and pull down. As the door nears the closed
position, grasp the edge of the door and pull inward firmly to assure
engagement of the latching pawls. Once engaged, the interior door
handle can be rotated clockwise to the horizontal position. Snap the
handle into its locking receptacle.
A WARNING
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If the airplane has utility seating, the aft left seat
Is In close proximity' to the cargo door handles.
extra precaution should be taken to ensure that
the occupant of this seat does not Inadvertently
actuate the upper cargo door handle to the open
position while In flight.
CABIN WINDOWS
The airplane is equipped with a two-piece windshield reinforced
with a metal center strip. The Passenger version has twelve cabin
side windows of the fixed type, including one each in the two crew
entry doors, two windows in the cargo door upper section, and one
window in the upper section of the passenger entry door. The side
window installed adjacent to the pilot's position incorporates a small
triangular foul weather window. The foul weather window may be
opened for ground ventilation and additional viewing by utilizing the
twist latch which is integral to the window. The Cargo version has
two cabin side windows, one each in the two crew entry doors.
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7-35
7 September 2001
For Trainin!! Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
CONTROL LOCKS
A control lock is provided to lock the aileron and elevator control .
surfaces to prevent damage to the these systems by wind buffeting ;
while the airplane is, parked. . The lock consists of a shaped steel '
rod and flag. The flag identifies it as a control lock and cautions
about its removal before starting the engine. To install the control
lock, align the hole in the left side of the pilot's control wheel shaft
with the hole in the left side of the shaft collar on the instrument
panel and insert the rod into the aligned holes. Installation of the
lock will secure the ailerons in a neutral position and the elevators
in a slightly trailing edge down position. Proper installation of the
lock will place the flag over the left sidewall switch panel.
A rudder gust lock is operated by an external handle on the left side
o'f the tailcone. For information and operating procedures pertaining
to this type of lock, refer to Aero Twin Rudder Gust Lock in Section
.. 9, Supplements.
NOTE ,
(
The control lock, rudder lock, and any other type of locking
device should be removed or unlocked prior to starting the
engine.
ENGINE
The Pratt & Whitney Canada Inc. PT6A-114A powerplant is a free.,
turbine engine. It utilizes two independent turbines; one driving a
compressor in the gas generator section, and the second driving a
reduction gearing for the propeller.
7-36
1 April 1998
For Training Purposes Only
(
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CESSNA
MODEL208 (675 SHP)
(
SECTION 7
.
AIRPLANE AND
SYSTEMS DESCRIPTION
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Inlet air enters the engine through an annular plenum chamber
formed by the compressor inlet case where it is directed to the
compressor. The compressor consists of three axial stages
combined with a single centrifugal stage, assembled as an integral
unit. It provides a compression ratio of 7.0:1.
A row of stator vanes located · between each stage of compressor
rotor blades diffuses the air, raises its static pressure and directs it
to the next stage of compressor rotor blades. The compressed air
passes through diffuser ducts which turn it 90° in direction. It is
then routed through straightening vanes into the combustion
chamber.
The combustion chamber liner located in the gas generator case
consists of an annular reverse-flow weldment provided with varying
sized perforations which allow entry of compressed air. The flow of
air changes direction to enter the combustion chamber liner where it
reverses direction and mixes with fuel. The location of the
combustion chamber liner eliminates the need for a long shaft
between the compressor and the compressor turbine, thus reducing
the overall length and weight of the engine.
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Fuel is injected into the combustion chamber liner by 14 simplex
nozzles supplied by a dual manifold. The mixture is initially ignited
by two spark igniters which protrude into the combustion chamber
liner. The resultant gases expand from the combustion chamber
liner, reverse direction and pass through the compressor turbine
guide vanes to the compressor turbine. The turbine guide vanes
ensure that the expanding gases impinge on the turbine blades at
the proper angle, with a minimum loss of energy. The still
expanding gases pass forward through a second set of stationary
guide vanes to drive the power turbine.
(
7-37
7 September 2001
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
2
25
24
9
23
22
21
20
10
19
"
12
18
13
14
15
16
17
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1. Propeller Shaft
2.·
3.
4.
5.
6.
7.
8.
9.
10.
Propeller Governor Drive Pad
Second Stage Planetary Gear
First Stage Planetary Gear
Power Turbine Shaft
Fuel Nozzle
Power Turbine
Combustion Chamber
Compressor Turbine
Centrifugal Compressor
Impeller
11. Axial-Flow Compressor
Impellers (3)
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
Compressor Air Inlet
Accessory Gearbox Drive Shaft
Accessory Gearbox Cover
Starter-Generator Drive Shaft
Oil Scavenge Pump
Number 1 Bearing
Compressor Bleed Valve ·
Number 2 Bearing
Number 3 Bearing
Number 4 Bearing
Exhaust Outlet
Chip Detector
Roller Bearing
Thrust Bearing
26857004
Figure 7-8. Typical Engine Components
1 April 1998
7-38
For Training Purposes Only
CESSNA
(
SECTION 7
MODEL 208 (675 SHP)
AIRPLANE AND
SYSTEMS DESCRIPTION
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The compressor and power turbines are located in the approximate
center of the engine with their shafts extending in opposite
directions. The exhaust gas from the power turbine is directed
through an exhaust plenum to the atmosphere via a single exhaust
port on the right side of the engine.
The engine is flat rated at675 shaft horsepower (1865 foot-pounds
torque at 1900 RPM varying linearly to 1970 foot-pounds torque at
1800 RPM; below 1800 RPM, the maximum torque value remains
constant at 1970 foot-pounds). Between 1800 and 1600 propeller
RPM, the gearbox torque limit of 1970 foot-pounds will not allow the
full flat rating of 675SHP to be achieved. The speed of the gas
generator (compressor) turbine (Ng) is 37,500 RPM at 100 Ng :
Maximum permissible speed of the gas generator is 38,100 RPM
which equals 101.6 N . The power turbine speed is 33,000 RPM at
a propeller shaft speed of 1900 RPM (a reduction ratio of 0.0576:1).
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All engine-driven accessories, with the exception of the propeller
tachometer-generator and the propeller governors, are mounted on
the accessory gearbox located at the rear of. the engine. These are
driven by the compressor turbine with a coupling shaft which
extends the drive through a conical tube in the oil tank center
section.
The engine oil supply is contained in an integral tank which forms
part of the compressor inlet case. The tank has a capacity of 9.5
U.S. quarts and is provided with a dipstick and drain plug.
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The power turbine drives the propeller through. a two-stage
planetary reduction gearbox located on the front of the engine. The
gearbox embodies an integral torquemeter device which is
instrumented to provide an accurate .indication of the engine power
output.
ENGINE CONTROLS
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The engine is operated by four separate controls consisting of a
power lever, emergency power lever, propeller control lever, and a
fuel condition lever. The power and fuel condition levers are engine
controls while the propeller control lever controls propeller speed
and feathering .
7-39
7 September 2001
For Traininl! Purnoses Onlv
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
POWER LEVER
The power lever is connected through linkage to a cam assembly
mounted in front of the fuel control unit at 'the rear of the engine. ,
The power lever controls engine power through the full range from \
maximum takeoff power back through idle to full reverse. The lever
also selects propeller pitch when in the BETA range. The power
lever has MAX, IDLE, and BETA and REVERSE range positions.
The range from MAX position through IDLE enables the pilot to
select the desired power output from the engine. The BETA range
enables the pilot to control propeller blade pitch from idle thrust
back through a zero or no-thrust condition to maximum ' reverse
thrust.
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CAU~ION
The propeller reversing linkage can be damaged
if the power lever is moved aft of the IDLE
position when the propeller Is feathered.
EMERGENCY POWER LEVER
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The emergency power lever is connected through linkage to the "
manual override lever on the fuel control unit and governs fuel
supply to the engine should a pneumatic malfunction occur in the
fuel control unit. When the engine is operating, a failure of any
pneumatic signal input to the fuel control unit will result in the fuel
flow decreasing to minimum idle (about 48% Ng at sea level and
increasing with altitude). The emergency power lever allows the pilot
to restore power in the event of such a failure. The emergency
power lever has NORMAL, IDLE, and MAX positions. The NORMAL
pOSition is used for all normal engine operation when the fuel
control unit is operating normally and engine power is selected by
the power lever. The range from IDLE position to MAX governs
engine power and is used when a pneumatic malfunction has
occurred in the 'fuel control unit and the power lever is ineffective. A
mechanical stop in the lever slot requires that the emergency power
lever be moved to the left to clear the stop before it can be moved
from the NORMAL (full aft) pOSition to the IDLE position.
1 April 1998
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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NOTE
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The knob on the emergency power lever has crosshatching. The cross-hatching is visible when the lever
is in MAX position. Also, the emergency power lever is
annunciated on the annunciator panel whenever it is
unstowed from . the NORMAL position. These
precautions are intended to preclude starting of the
engine with the emergency power lever inadvertently
placed in any position other than NORMAL.
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CAUTION
• The emergency power lever and Its associated
manual override system Is considered to be an
emergency system and should be used only In
the event of a fuel control unit malfunction.
When attempting a normal start, the pilot must
ensure that the emergency power lever is In the
NORMAL (full aft) position; otherwise, an overtemperature condition may result.
• When using the fuel control manual override
system, engine response may be more rapid
than when using the power lever. Additional
care Is required during engine acceleration to
avoid exceeding engine limitations.
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Operation of the emergency power lever is prohibited with the
primary power lever out of the IDLE position. The emergency
power lever overrides normal fuel control functions and results in
the direct operation of the fuel metering valve. The emergency
power lever will override the automatic fuel governing and engine
acceleration scheduling controlled during normal operation by the
primary power lever.
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CAUTION
Inappropriate use of the emergency power lever
may adversely affect engine operation and
durability. Use of the emergency power lever
during normal operation of the power lever may
result In engine surges, or exceeding the ITT,
Ng, and torque limits.
7-41
15 November 2000
For Traininl! Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
Airplane serials 20800351 and on, and earlier airplanes
incorporating Service Kit SK208-142, have a copper witness wire
installed that indicates when the emergency power lever has been
In the event that the
moved from the NORMAL position.
emergency power lever is required due to an engine malfunction,
moving the emergency power lever out of ' the NORMAL position
and into the IDLE position easily breaks the copper wire.
After EPL use, the witness wire should be replaced after
appropriate maintenance action.
An entry shall be made in the
airplane logbook indicating the circumstances of the EPL use and
the action taken.
PROPELLER CONTROL LEVER
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The propeller control lever is connected through linkage to the
propeller governor mounted on top of the front section of the
engine, and controls propeller governor settings from the maximum
RPM position to full feather. The propeller control lever has MAX,
MIN, and FEATHER positions. The MAX position is used when high
RPM is desired and governs the propeller ,speed at 1900 RPM.
Propeller control lever settings from the MAX position to MIN permit
the pilot to select the desired engine RPM for cruise. The i
FEATHER position is used during normal engine shutdown to stop "
rotation of the power turbine and front section of the engine. Since
lubrication is not available after the gas generator section of the
engine has shut down, rotation of the forward section of the engine
is not desirable. Also, feathering the propeller when the engine is
shut down minimizes propeller windmilling during windy conditions.
A mechanical stop in the lever slot requires that the propeller
control lever be moved to the left to clear the stop before it can be
moved into or out of the FEATHER position.
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FUEL CONDITION LEVER
The fuel condition leve'r is connected through linkage to a combined
lever and stop mechanism on the fuel control unit. The lever and
stop also function as an idle stop for the fuel control unit rod. The
fuel condition lever controls the minimum RPM of the gas generator
turbine (N g) when the power lever is in the IDLE position. The fuel
condition lever has CUTOFF, LOW IDLE, and HIGH IDLE positions.
The CUTOFF position shuts off all fuel to the engine fuel nozzles.
LOW IDLE positions the control rod stop to provide an RPM of 52%
N.9' HIGH IDLE positions the control rod stop to provide an RPM of
65% Ng .
7-42
7 September 2001
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
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SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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QUADRANT FRICTION LOCK
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A quadrant friction lock, located on the _right side of the pedestal, is
provided to minimize creeping of the engine controls once they have
been set. The lock is a knurled knob which increases friction on the
engine controls when rotated clockwise.
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ENGINE INSTRUMENTS
Engine operation is monitored by the following. instruments: torque
indicator, propeller _ RPM indicator, ITT indicator, N g% RPM
indicator, fuel flow indicator, oil pressure gauge, and oil temperature
gauge.
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TORQUE INDICATOR
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The torque indicator is located on the upper portion of the
instrument panel and indicates the torque being produced by the
engine. On some Cargo Versions, the torque indicator is . electrically
powered and operates in conjunction with a transmitter located on
the top of the reduction gearbox front case. The transmitter senses
the difference between the engine torque pressure and the pressure
in the engine case and transmits this data to the torque indicator.
The torque indicator converts this information into an indication of
torque in foot-pounds. The torque indicator system is powered by
28-volt DC power through a circuit breaker, labeled TRQ IND, on
-the left sidewall switch and circuit breaker panel.
On other Cargo Versions and the Passenger Version, the torque
indicator is pressure actuated. Two independent lines enter the
back of the torque indicator. One line measures the engine torque
pressure and one line measures the reduction gearbox internal
pressure. The torque indicator monitors the engine torque pressure
and - converts this pressure into an indication of torque in footpounds. Instrument markings indicate that the normal operating
range (green arc) is from 0 to 1865 foot-pounds, the alternate power
range (striped green arc) is from 1865 to 1970 foot-pounds, and
maximum torque (red line) is 1970 foot-pounds. Maximum takeoff
torque is denoted by ''1.0.'' and a red wedge at 1865 foot-pounds.
7-43
15 November 2000
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
PROPELLER RPM INDICATOR
The propeller RPM indicator is located on the upper portion of the
instrument panel. The instrument is marked in increments of 50
RPM and indicates pr,opeller speed in revolutions per minute. The
instrument is electrically-operated from the propeller tachometergenerator which is mounted on the right side of the front case.
Instrument markings indicate a normal operating range (green arc)
of from 1600 to 1900 RPM and a maximum (red line) of 1900 RPM.
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ITT INDICATOR
The lIT (interturbine temperature ) indicator is located on the upper
portion of the instrument panel. The instrument displays the gas
temperature between the compressor and power turbines.
Instrument markings indicate a normal operating range (green arc)
of from 100°C to 740°C, and a maximum (red line) of 805°C. Also,
instrument markings indicate a maximum starting temperature (red
triangle) of 1090°C.
Ng % RPM INDICATOR
The Ng% RPM indicator is located on the upper portion of the (
instrument panel. The instrument indicates the percent of gas
generator RPM based on a figure of 100% at 37,500 RPM. The
instrument is electrically-operated
from the gas generator
tachometer-generator mounted on the lower right-hand portion of
the accesSory case. Instrument markings indicate a normal
operating range (green arc) of from 52% to 101 .6% and a maximum
(red line) of 101.6%.
FUEL FLOW INDICATOR
Details of the fuel flow indicator are included under Fuel System in
a later paragraph in this section.
7-44
7 September 2001
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
OIL PRESSURE GAGE
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instrument I
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The oil pressure gage is the left half of a dual-indicating
mounted on the upper portion of the instrument panel. A direct
pressure oil line from the engine delivers oil at engine operating
pressure to the oil pressure gage. Instrument markings indicate a I
minimum operating pressure (red line) of 40 psi, a cautionary range
(yellow arc) of from 40 to 85 psi, a normal operating range (green
arc) of from 85 to 105 psi, and a maximum (red line) of 105 psi.
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. OIL TEMPERATURE GAGE
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dual-indicating I
The oil temperature gage is the right half of a
instrument mounted on the upper portion of the instrument panel.
The instrument is operated by an electrical-resistance type
temperature sensor which receives power from the airplane
electrical system.
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Instrument markings:
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Airplane serials 20800277 thru 20800363 not equipped with
Service Kit SK208-147 : Minimum operating temperature (red
line) -40°C, cautionary range (yellow arc) from -40°C to 10°C,
normal operating range (green arc) from 10°C to 99°C, and
maximum (red line) ggoC.
Airplane serials 20800364 and on, and earlier airplanes
equipped with Service Kit SK208-147:
Minimum operating
temperature (red line) -40°C, cautionary range (yellow arc) from
-40°C to 10°C, normal operating range (green arc) from 10°C to
99°C, 10-minute transient range (yellow arc) 99°C to 104°C,
and maximum (red line) 104°C.
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NEW ENGINE BREAK-IN AND OPERATION
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Co;)
There are no specific break-in procedures required for the Pratt &
Whitney Canada Inc. PT6A-114A turboprop engine. The engine
may be safely operated throughout the normal ranges authorized by
the manufacturer at the time of delivery of your airplane.
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7-45
Revision 6
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
ENGINE LUBRICATION SYSTEM
The lubrication system consists of a pressure system, a scavenge
system and a breather system. The main components of the :
lubrication system include an integral oil tank at the back of the '
engine, an oil . pressure pump at the bottom of the oil tank, an
external double-element scavenge pump located on the back of the
accessory case, an internal. double-element scavenge pump located
inside the accessory gearbox, an oil-to-fuel heater located on the
top rear of the accessory case, an oil filter located internally on the
right side of the oil tank,and an oil cooler located on the right side
of the nose cowl.
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A large capacity oil cooler is installed to increase the hot day
outside air temperature limits for flight operations. Oil is drawn from
the bottom of the oil tank through a filter screen where it passes
through a pressure relief valve . for regulation of oil pressure. The
pressure oil is then delivered from the main oil pump to the oil filter
where extraneous matter is removed from the oil and precluded
from further circulation.Pressure oil is then routed through
passageways to the engine bearings, reduction gears, accessory
. drives, torque meter, and propeller governor. Also, pressure oil is (
routed to the oil-to-fuel heater where it then returns to the ,oil tank.
After cooling .and lubricating the engine moving parts, oil is
scavenged as follows: Oil from the number 1 bearing compartment
is returned by -gravity into the accessory gearbox. Oil from the
number 2 bearing is scavenged by the front element of the internal
scavenge pump back into the accessory gearbox. Oil from the
number 3 and number 4 bearings is scavenged by the front element
of the external scavenge pump into the accessory gearbox. Oil from
the propeller governor, front thrust bearing, reduction gear
accessory .drives, and torquemeter is scavenged by the rear
elemen~ of the external scavenge pump where it is routed through a
thermostatically-controlled oil cooler and then returned to the oil
tank. Also, the rear element of the internal scavenge pump
scavenges oil from the accessory case and routes itthroLigh the oil
cooler where it then returns to the oil tank.
Revision 6
h-46
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
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SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
. Breather air from the engine bearing compartments and from the
accessory and reduction gearboxes is vented overboard through a
centrifugal breather .installed in the accessory gearbox. The bearing
compartments ' are connected to the accessory gearbox by cored
passages and existing scavenge oil return lines. A bypass valve,
immediately upstream of the front element of the internal scavenge
. pump, vents the accessory gearbox when the engine is operating at
high power.
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An oil dipstick/filler cap is located at the rear of the engine on the
left side and is accessible when the left side of the upper cowling is
raised. Markings which indicate U.S. quarts low if the oil is hot are
provided on the dipstick to facilitate oil servicing. The oil tank
capacity is 9.5 U.S. quarts and total system capacity is 14 U.S.
quarts. For engine oil type and brand, refer to Section 8.
IGNITION SYSTEM
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The ignition system consists of two igniters, an ignition exciter, two
high-tension leads, an ignition monitor light, an ignition switch, and
a starter switch. Engine ignition is provided by two igniters in the
engine combustion chamber. The igniters are energized by the
ignition exciter mounted on the engine mount on the right side of
the engine compartment. Electrical energy from the ignition exciter
is transmitted through two high-tension leads to the igniters in the
engine. The ignition system is normally energized only during
engine start.
Ignition is controlled by an ignition switch and a starter switch
located on the left sidewall switch and circuit breaker panel. The
ignition switch has two positions, ON and NORMAL. The NORMAL
pOSition of the switch arms the ignition system so that ignition will
be obtained when the starter switch is placed in the START
position. The NORMAL position is used during all ground starts and
during air starts with starter assist. 'The ON position of the switch
provides continuous ignition regardless of the position of the starter
switch. This position is used for air starts without starter assist, for
operation on water or slush-covered runways, during flight in heavy
precipitation, during inadvertent icing encounters until the inertial
separator has been in bypass for 5 minutes, and when near fuel
exhaustion as indicated by illumination of the RESERVOIR FUEL
LOW annunciator.
7-471
Revision 6
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
The main function of the starter switch is control of the starter for
rotating the gas generator portion of the engine during starting,
However, it also provides ignition during starting. For purposes of
this discussion, only the ignition functions of the switch are :
described. For other functions of the starter switch, refer to
paragraph titled Starting System, in this section. The starter switch
has three positions, OFF, START, and MOTOR. The OFF position
shuts off the ignition system and is the normal position at all times
except during engine start or engine clearing. The START position
energizes the engine ignition system provided the ignition switch is
in the NORMAL position. After the engine has started during a
ground or air start, the starter switch must be manually positioned to
OFF for generator operation.
A green annunciator, located on the annunciator panel, is labeled
IGNITION ON, and will illuminate when electrical power is being
applied to the igniters. The ignition system is protected by a "pulloff" type circuit breaker, labeled IGN, on the left sidewall switch and
circuit breaker panel.
AIR INDUCTION SYSTEM
The engine air inlet is located at the front of the engine nacelle to
the left of the propeller spinner. Ram air entering the inlet flows
through ducting and an inertial separator system and then enters
.the engine through a circular plenum chamber where it is directed
to the compressor by guide vanes. The compressor air inlet
incorporates a screen which will prevent entry of large articles, but
does not filter the inlet air.
INERTIAL SEPARATOR SYSTEM
An inertial separator system in the engine air inlet duct prevents
moisture particles from entering the compressor air inlet plenum
when in bypass mode. The inertial separator consists of two
movable vanes and a fixed airfoil which, during normal operation,
route the inlet air through a gentle turn into the compressor air inlet
plenum. When separation of moisture particles is desired, the vanes
are pOSitioned so that the inlet air is forced to execute a sharp turn
in order to enter the inlet plenum. This sharp turn causes any
moisture particles to separate from the inlet air and discharge
overboard through the inertial separator outlet in the left side of the
cowling.
Revision 6
h-48
For Training Purposes Only
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CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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NOTE
Above view shows inertial
separator in NORMAL
position. Auxiliary view
shows inertial separator In
BYPASS position.
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10
CODE
1-
I§TII
RAM AIR
BI
RAM AIR COMPRESSED WHILE FLOWING
THROUGH THREE STAGES OFAXIAL·FLOW
IMPELLERS
g
r;,":;";:'"j
RAM AIR COMPRESSED WHilE FLOWING
THROUGH CENTRIFUGAL IMPELLER
COMPRESSED AIR INJECTED WITH
FUEL AND IGNITED
BURNED FUEL·AIR MIXTURE IS EX·
PANDED AND DRIVES COMPRESSOR
TURBINE AND POWER TURBINE. AND
IS THEN EXHAUSTED
2.
~.
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~.
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~.
10.
~1.
12.
Primary Exhaust Pipe
Power Turbine
Compressor Turbine
Centrifugal Impeller
Axial·Flow Impellers (3)
Engine Air Inlet
Inertial Separator Outlet
Inertial Separator Rear Vane
Inertial Separator Airfoil
Inertial Separator Front Vane
Induction Air Inlet Plenum
Induction Air Inlet Duct
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26856032
Figure 7-9. Engine Air Flow
7-49
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP) .
Inertial separator operation is controlled by a T-handle located on
the lower instrument panel. The T-handle is labeled BYPASS-PULL,
NORMAL-PUSH. The inertial separator control should be moved to
the BYPASS position prior to running the engine during ground or '
flight operation in visible moisture (clouds, rain, snow, ice crystals)
with an OAT of 4°C or less. It may also be used for ground
operations or takeoffs from dusty, sandy field conditions to minimize
ingestion of foreign particles into the compressor. The normal
position is used for all other operations.
The T-handle locks .in the NORMAL position by rotating the handle
clockwise 1/4 turn to its vertical position. To unlock, push forward
slightly and rotate the handle 90° counterclockwise. The handle can
then be pulled into the BYPASS position. Once moved to the
BYPASS position, air loads on the movable vanes hold them in this
position.
NOTE
When moving the inertial separator control from bypass to
normal position during flight, reduction of engine power will
reduce the control forces.
EXHAUST SYSTEM
The exhaust system consists of a primary exhaust pipe attached to
the right side of the engine . just aft of the propeller reduction
gearbox. A secondary exhaust duct, fitted over the end of the
primary exhaust . pipe, carries the exhaust gases away from the
cowling and into the slipstream. The juncture of the primary exhaust
pipe and secondary exhaust duct is located directly .behind the oil
cooler. Since the secondary exhaust duct is of larger diameter than
the primary exhaust pipe, a venturi effect is produced by the flow of
exhaust. This venturi effect creates a suction behind the oil cooler
which augments the flow of cooling air through the cooler. This
additional airflow improves oil cooling during ground operation of
the engine.
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Revision 6
17-50
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
ENGINE FUEL SYSTEM
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The engine fuel system consists of a~ oil-to-fuel heater, an enginedriven fuel pump, a fuel control unit, a flow divider and dump valve,
a dual fuel manifold with 14 simplex nozzles, and two fuel drain
lines. The system provides fuel flow to satisfy the speed and power
demands of the engine.
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Fuel from .the airplane reservoir is delivered to the oil~to-fuel heater
which is essentially a heat exchanger which utilizes heat from the
engine lubricating oil system to preheat the fuel in the fuel system .
A fuel temperature-sensing oil bypass valve regulates the fuel
temperature by either allowing oil to flow through the heater circuit
or bypass it to the engine oil tank.
Fuel from the oil-la-fuel heater then enters the engine-driven fuel .
pump chamber through a 74-micron inlet screen. The inlet screen is
spring-loaded and should it become blocked, the increase in
differential pressure will overcome the spring and allow unfiltered
fuel to flow into the pump chamber. The pump increases the fuel
pressure and delivers it to the fuel control unit via a 10-micron filter
in the pump outlet. A bypass valve and cored passages in the pump
body enables unfiltered high pressure fuel to flow to the fuel control
unit in the event the outlet filter becomes blocked.
The fuel control unit consists of a fuel metering section, a
temperature compensating section, and a gas generator (N g )
pneumatic governor. The fuel control unit determines the proper fuel
schedule to provide the power required as established by the power
lever input. This is accomplished by controlling the speed of the
compressor turbine. The temperature compensating section alters
the acceleration fuel schedule to compensate for fuel density
differences at different fuel , temperatures, especially during engine
start. The power turbine governor, located in the propeller governor
housing, provides power turbine overspeed protection in the event
of propeller governor failure. This is accomplished by limiting fuel to
the gas generator. During reverse thrust operation, maximum power
turbine speed is controlled by the power turbine governor. The
temperature compensator alters the acceleration fuel schedule of
the fuel control unit to compensate for variations in compressor inlet
air temperature. Engine characteristics vary with changes in inlet air
temperature , and the acceleration fuel schedule must, in turn, be
altered to prevent compressor stall and/or excessive turbine
temperatures.
7-51
15 November 2000
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
The flow divider schedules the metered fuel, from the fuel control
unit, between the primary and secondary fuel manifolds. The fuel
manifold and nozzle assemblies deliver fuel to the combustion
chamber through 10 primary and 4 secondary fuel nozzles. During ,
engine start, metered fuel is delivered initially by the primary '
nozzles, with the secondary nozzles cutting in above a preset value.
All nozzles are operative at idle and above.
When the fuel cutoff valve in the fuel control unit closes during
engine shutdown, both primary and secondary manifolds are
connected to a dump valve port and residual fuel in the manifolds is
allowed to drain into the fuel drain can attached to the firewall
where it can be drained daily.
COOLING SYSTEM
No external cooling provIsions are provided for the PT6A-114A
engine in this installation. However, the engine incorporates an
extensive internal air system which provides for bearing
compartment sealing and for compressor and power turbine disk
cooling. For additional information on internal engine air systems,
refer to the engine maintenance manual for the airplane.
STARTING SYSTEM
The starting system consists of a starter/generator, a starter switch,
and a starter annunciator light. The starter/generator functions as a
motor for engine starting and will motor the gas generator section
until a speed of 46% Ng is reached, at which time, the start cycle
will automatically be terminated by a speed sensing switch located
in the starter/generator. The starter/generator is controlled by a
three-position starter switch located on the left sidewall switch and
circuit breaker panel. The switch has OFF, START, and MOTOR
pOSitions. The OFF position de-energizes the ignition and starter
circuits and is the normal position at all times except during engine
start. The 5T ART position of the switch energizes the
starter/generator which rotates the gas generator portion of the
engine for starting. Also, the START position energizes the ignition
system, provided the ignition switch is in the NORMAL position.
When the engine has started, the starter switch must be manually
placed in the OFF position to de-energize the ignition system and
activate the generator system. The MOTOR position of the switch
motors the engine without having the ignition circuit energized and
is used for motoring the engine when
7-52
7 September 2001
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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an engine and start is not desired. This can be used for clearing
fuel an engine start is not desired. This can be used for clearing fuel
from the engine, washing the engine compressor, etc. The MOTOR
position is spring-loaded back to the OFF position. Also, an interlock
between the MOTOR position of the starter switch and the ignition
switch prevents the starter from motoring unless the ignition switch
is in the NORMAL position. This prevents unintentional motoring of
the engine with the ignition on. Starter contactor operation is
indicated
by an amber annunciator, labeled STARTER
ENERGIZED, on the annunciator panel.
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ENGINE ACCESSORIES
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All engine-driven accessories, with the exception of the propeller
tachometer-generator and the propeller governors, are mounted on
the accessory gearbox located at the rear of the engine. These
accessories are driven from the compressor turbine by a coupling
shaft which extends the drive through a conical tube in the oil tank
center section.
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OIL PUMP
Pressure oil is circulated from the integral oil tank through the
engine lubrication system by a self-contained, gear-type pressure
pump located in the lowest part of the oil tank. The oil pump is
contained in a cast housing which is bolted to the front face of the
accessory diaphragm, and is driven by the accessory gear shaft.
The oil pump body incorporates .a circular mounting boss to
accommodate a check valve, located in the end of the filter housing .
A second mounting boss on the pump accommodates a pressure
relief valve.
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F
C~i/
7-53
15 November 2000
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
FUEL PUMP
The engine-driven fuel pump is mounted on the accessory gearbox
at the 2 o'clock position. The pump is driven through a gear shaft
and splined coupling.' The coupling splines are lubricated by oil mist :
from the auxiliary gearbox through a hole in the gear shaft. Another
splined coupling shaft extends the drive to the fuel control unit
which is bolted to the rear face of the pump. Fuel from the oil-to-fuel
heater enters the fuel pump through a 74-micron inlet screen. Then,
fuel enters the pump gear chamber, is boosted to high pressure,
and delivered to the fuel control unit through a 10-micron pump
outlet filter. A bypass valve and cored passages in the pump caSing
enable unfiltered high pressure fuel to flow from the pump gears to
the fuel control unit should the outlet filter become blocked. An
internal passage originating at the mating face with the fuel control
unit returns bypass fuel from the fuel control unit to the pump inlet
downstream of the inlet screen. A pressure regulating valve in this
line serves to pressurize the pump gear bushings.
Ng TACHOMETER-GENERATOR
The Ng tach~met~r-gen~rator produces an electric. curr~nt .which . is !
used In conjunction With the gas generator RPM Indicator to '
indicate gas generator RPM. The Ng tachometer-generator drive
and mount pad is located at the 5 o'clock position on the accessory
gearbox and is driven from the internal scavenge pump. Rotation is
counterclockwise with a drive ratio of 0.1121 :1.
PROPELLER TACHOMETER-GENERATOR
The propeller taChometer-generator produces an electric current
which is used in conjunction with the propeller RPM indicator. The
propeller taChometer-generator drive and mount pad is located on
the right side of the reduction gearbox case and rotates clockwise
with a drive ratio of 0.1273:1.
TORQUEMETER
The torquemeter is a hydro-mechanical torque measuring device
located inside the first stage reduction gear housing to provide an
accurate indication of engine power output. The difference between
the torquemeter pressure and the reduction gearbox internal
pressure accurately indicates the torque being produced.
7-54
7 September 2001
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
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The two pressures are internally routed to bosses located on the top
of the reduction gearbox front case and are then plumbed to the
torquemeter indicator which indicates the correct torque pressure.
(
STARTER/GENERATOR
The starter/generator is mounted on the top of the accessory case
at the rear of the engine. The starter/generator is a 28-volt, 200-amp
engine-driven unit that functions as a motor for engine starting and,
after engine start, as a generator for the airplane electrical system.
When operating as a starter, a speed sensing switch in the
starter/generator will automatically shut down the starter, thereby
providing overspeed protection and automatic shutoff. The
starter/generator is air cooled by an integral fan and by ram air
ducted from the front of the engine cowling.
.
INTERTURBINE TEMPERATURE SENSING SYSTEM
(
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The interturbine temperature sensing system is designed to provide
the operator with an accurate indication of engine operating
temperatures taken between the compressor and power turbines.
The system consists of twin leads, two bus bars, and eight
individual chromel-alumel thermocouple probes connected in
parallel. Each probe protrudes through a threaded boss on the
power turbine stator housing into an area adjacent to the leading
edge of the power turbine vanes. The probe is secured to the boss
by means of a floating, threaded fitting which is part. of the
thermocouple probe assembly. Shielded leads connect each bus
bar assembly to a terminal block Which provides a connecting pOint
for external leads to the ITT indicator in the airplane cabin.
PROPELLER GOVERNOR
(
The propeller governor is located in the 12 o'clock position on the
front case of the reduction gearbox. Under normal conditions, the
governor acts as a constant speed unit, maintaining the propeller
speed selected by the pilot by varying the propeller blade pitch to
match the load to the engine torque. The propeller governor also
has a power turbine governor section built into the unit. Its function
is to protect the engine against a possible power turbine overspeed
in the event of a propeller governor failure.
7-55
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
If such an overspeed should occur, a governing orifice in the
propeller governor is opened by . flyweight action to' bleed ·off
compressor discharge pressure through the governor and
computing section of the fuel control unit. When this occurs,
compressor discharge pressure, acting on the fuel control unit
governor bellows, decreases and moves the metering valve in a
closing direction, thus reducing fuel flow to the flow divider.
PROPELLER OVERS PEED GOVERNOR
The propeller overspeed governor is located at the 10 o'clock
position on the front case of the reduction gearbox. The governor
acts as a safeguard against propeller overspeed should the primary
propeller governor fail. The propeller overspeed governor regulates
the flow of oU to the propeller pitch-change mechanism by means of
a flyweight and speeder spring arrangement similar to the primary
propeller governor. Since it has no mechanical controls, the
overspeed governor is equipped with a test solenoid that resets the
governor below its normal overspeed setting for ground test. The
overspeed governor test switch is located on the left side of the
instrument panel. For a discussion of this switch, refer to the
paragraph titled Propellers in this section.
ENGINE FIRE DETECTION SYSTEM
The engine fire detection system consists of a heat sensor in the
engine compartment, a warning light, labeled ENGINE FIRE, on the
annunciator panel, and a warning horn above the pilot. The heat
sensor consists of three flexible closed loops. When high engine
compartment temperatures are experienced. the heat causes a
change in resistance in the closed loops. This change in resistance
is sensed by a control box, located on the aft side of the firewall,
which will illuminate the annunciator light and trigger the audible
warning horn. Fire warning is initiated when temperatures in the
engine compartment exceed 425°F (218°C) on the first section
(firewall), 625°F (329°C) on the second section (around the
exhaust), or 450°F (232°C) on the third section (rear engine
compartment). A test switch, labeled FIRE DETECT TEST, is
located adjacent to the annunciator panel. When depressed, the
ENGINE FIRE annunciator will illuminate and the warning horn will
sound indicating that the fire warning circuitry is operational. The
system is protected by a "pull-off" type circuit breaker, labeled FIRE
DET, on the left sidewall switch and circuit breaker panel.
1 April 1998
7-56
For Training Purposes Only
i
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
ENGINE GEAR REDUCTION SYSTEM
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The reduction gear and propeller shaft, located in the front of the
engine, are housed in two magnesium alloy castings which are
bolted together at the exhaust outlet. The gearbox contains a twostage planetary gear train, three accessory drives, and propeller
shaft. The first-stage reduction gear is contained in the rear case,
while the second-stage reduction gear, accessory drives, and
propeller shaft are contained in the front case. Torque from the
power turbine is transmitted to the first-stage reduction gear, from
there to the second-stage reduction gear, and then to the propeller
shaft. The reduction ratio is from a maximum power turbine speed
of 33,000 RPM down to a propeller speed of 1900 RPM or a
reduction ratio of 0.0576:1 .
The accessories, located on the front case of the reduction gearbox,
are driven by a bevel gear mounted at the rear of the propeller shaft
thrust bearing assembly. Drive shafts from the bevel drive gear
transmit rotational power to the three pads which are located at the
12, 3 and 9 o'clock positions.
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Propeller thrust loads are absorbed by a flanged ball bearing
assembly located on the front face of the reduction gearbox center
bore. The bevel drive gear adjusting spacer, thrust bearing. and
seal runner are stacked and secured to the propeller shaft by a keywasher and spanner nut. A thrust bearing cover assembly is
secured by bolts at the front t.lange of the reduction gearbox front
case.
.
CHIP DETECTORS (Optional)
Some airplanes have two chip detectors installed on the engine, one
on the underside of the reduction gearbox case and one on the
underside of the accessory gearbox case. The chip detectors are
electrically connected to an annunciator, labeled CHIP DETECTOR,
on the instrument panel. The annunciator will illuminate when metal
chips are present in one or both of the chip detectors. Illumination of
the CHIP DETEC-TOR annunciator necessitates the need for
inspection of the engine for abnormal wear.
OIL BREATHER DRAIN CAN
The airplane has an oil breather drain can mounted on · the
rightlower engine mount truss. This can collects any engine oil
discharge coming from the accessory pads for the alternator drive
7-571
29 September 1998
For Tralnin!! PurDoses Onlv
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
pulley, starter/generator and air conditioner compressor (if installed),
and the propeller shaft seal. This can should be drained after every
flight.
A drain valve on the bottom right side of the engine
cowling enables the pilot to drain the contents of the oil breather .
drain can into a suitable container. The allowable quantity of oil '
discharge per hour of engine operation 14 cc for airplanes with air
conditioning and 11 cc for airplanes without air conditioning. If the
quantity of oil drained from the can can is greater than specified, the
source of the leakage should be identified and corrected prior to
further flight.
PROPELLER
The airplane is equipped with a McCauley three-bladed aluminum
propeller. It is constant-speed, full-feathering, reversible, singleacting, and governor-regulated. A setting is introduced into the
governor with · the propeller control lever which establishes the
propeller speed. The propeller utilizes oil pressure which opposes
the force of springs and counterweights to obtain correct .pitch for
the engine load. Oil pressure from the propeller governor drives the
blades toward low pitch ' (increases RPM) while the springs and
counterweights drive the blades toward high pitch (decreasing {
RPM). The source of oil ~ressure for propeller operation is furnished \
by the engine oil system, boosted in pressure by the governor gear
pump, and supplied to the propeller hub through the propeller
flange.
To feather the propeller blades, the propeller control lever on the
control pedestal .is placed in the FEATHER position; counterweights
and spring tension will continue to twist the propeller blades through .
high . pitch and into .the streamlined or feathered position.
Unfeathering the propeller is accomplished by positioning the
propeller control lever forward of the feather gate. The unfeathering
system uses engine oil pressure to force the propeller out of feather.
Reversed propeller pitch is available for decreasing landing ground
roll during landing. To accomplish reverse pitch, the power lever is
retarded .beyond IDLE and well into the BETA range. Maximum
reverse power is accomplished by retarding the power lever to the
MAX REVERSE position which increases power output from the gas
generator as well as positions the propeller blades at full reverse i
pitch. An externally grooved feedback ring is provided with the "',.:."
propeller. Motion of the feedback ring is proportional to propeller
h-58
29
For Training Purposes Only
~eptember
1998
(
CESSNA
MODEL 208 (675 SHP}
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
blade angle, and is picked up by a carbon block running in the
feedback ring. The relationship between the axial position of the
feedback ring and the propeller blade angle is used to maintain
control of blade angle from idle to full reverse.
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A
CAUTION
The .propeller reversing linkage can be damaged
if the power lever Is moved aft of the · idle
position when the propeller Is feathered.
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OVERSPEED GOVERNOR TEST SWITCH
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An overspeed governor test switch is located on the left side of the
instrument panel. The switch is the push-to-test type and is used to
test the propeller overspeed governor during engine run-up. The
switch, when depressed, actuates a solenoid on the propeller
overspeed governor which restricts propeller RPM when the power
lever is advanced. To check for proper operation of the overspeed
governor during engine run-up, depress the press~to-test switch and
advance the power lever unti' propeller RPM stabilizes; propeller
RPM should not exceed 1750 ±60 RPM.
FUEL SYSTEM
(
The airplane fuel system (see Figure 7-10) consists of two vented,
integral fuel tanks with shutoff valves, a fuel selectors off warning
system, a fuel reservoir, an ejector fuel pump, an electric auxiliary
boost pump, a reservoir manifold assembly, a firewall shutoff valve,
a fuel filter, an oil-to-fuel heater, an engine-driven fuel pump, a fuel
control unit, a flow divider, dual manifolds, and 14 fuel nozzle
assemblies. A fuel drain can and drain Is also provided. Refer to
Figure 7-11 for fuel quantity data for the system. .
j\WARNING
(. '. '.
\ "",;c/'
Unusable fuel levels for this airplane were
determined In accordance with Federal Aviation
Regulations. Failure to operate the airplane In
compliance with the fuel limitations specified in
Section 2 may further reduce the amount of fuel
. available In flight.
7-591
29 September 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
Fuel flows from the tanks through the two fuel tank shutoff valves at
each tank. The fuel tank shutoff valves are ' mechanically controlled
by two fuel selectors, labeled LEFT,. ON and OFF and RIGHT, ON
and OFF, located on the .overhead panel. By manipulating the fuel ,selectors, the pilot can select either left or right fuel tanks or both at ;
the same time. Normal operation is with both tanks on. Fuel flows
by gravity from the shutoff valves in each tank to the fuel reservoir.
The reservoir is located at the low point in the fuel system which
maintains a head of fuel around the ejector boost pump and
auxiliary boost pump which are contained within the reservoir. This
head of fuel prevents pump cavitation .in low-fuel quantity situations,
especially during inflight maneuvering. Fuel in the reservoir is
pumped by the ejector boost pump or by the electric auxiliary boost
pump to the reservoir manifold assembly. The ejector boost pump,
which is driven by motive fuel flow from the fuel control unit,
normally provides fuel flow when the engine is operating. In the
event of failure of the ejector boost pump, the electric boost pump
will automatically turn on, thereby supplying fuel flow to the engine.
The auxiliary boost pump is also used to supply fuel flow during
starting. Fuel in the reservoir manifold then flows through a fuel
shutoff valve located on the aft side of the firewall. This shutoff valve ,.
enables the pilot to cut off aI/ fuel to the engine.
.
After passing through the shutoff valve, fuel is routed through a fuel
filter located on the ', front side of the firewall. The fuel filter
incorporates a bypass feature which allows fuel to bypass the filter
in the event the filter becomes blocked with foreign material. A red
filter bypass flag on the top of the filter extends upward when the
filter is bypassing fuel. Fuel from the filter is then routed through the
oiHo-fuel heater to the engine-driven fuel pump where fuel is
delivered under pressure .to the fuel control unit. The fuel control
unit meters the fuel and directs it to the flow divider which
distributes the fuel to dual manifolds and 14 fuel nozzles located in
the combustion chamber. For additional details concerning the flow
of fuel at the engine, refer to the Engine Fuel System paragraph in
this section.
Fuel rejected by the engine on shutdown drains into a fireproof fuel
can located on the front left side of the firewall. The can should be '
drained during preflight inspection. If left unattended, the drain can
fuel will overflow overboard.
29 September 1998
h-60
For Training Purposes Only
CESSNA
MODEL 208 (675' SHP)
(
SECTION 7
AIRPLANE AND
SYStEMS DESCRIPTION
(
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~U[LNOZlU'
>t.:giEin, fUELSU".LY
PRIMARY
nCONDAfl Y
~PRI!SSUIIE .F E EO fUEL
[][][]] MOTIV£-FlOW FUEL
_
METERED fUEL
~ORA INFUEl
-..
===VI!NT
- ___ MECHAMCAI. CONNECTION
---------- ~ 9'·'
EMEAOE..CV
- - £l £CTfUCAL CONNEeTIO'"
A
---.----------:a
. -.. . . -.. . _- R
~::
WARNING
'UEL
bURlNG 'RUUOHT INIIPlCTfON AND
,t,FTm AN.. fUll &VSU.M 8e1VICtNG..
TAkE
fun IAMP1..E1I
"'I)"
-
AU
DRAIN loc,mONS, MAKE NilE fUfl
'ANK flliER caps .flE "-CUlli,
CHECK fUEL B"STUI VEN'T$ fOil
OBSTRUCnoNS, 1C£ OR WAU"
- -
COHDITION
LEVf R
"teO
AURAl WARNING HOIINS
--;;U:~~I-'.!!''!!~:: VALVE
.J"
-----
•
-
-0
flMiWALl
~~.:~10fFr-_ _ _ ,~~~_j
r--r--r ':"""'~'LO"'MwHT
n ....
lOW
Mm'~1!
I
LOW PRESSURE
SWITCH
~=-....,..c::::-----~
ANNUHtlATOlt .." .......
TOruEl
1I!l[CI'OIID,f
WARNING RfLAY
A&lfMIlV
fUEL QUANTITY INDICA TO"'
IWClOflOfF
WARNtHOIUl.AY
. . . . . . Ly
2685M3001
Figure 7-10. Fuel System
1 April 1998
7-61
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
Fuel system venting is essential to system operation. Complete
blockage of the vent system will result in decreased fuel flow and
eventual engine stoppage. Venting is accomplished by check valve
equipped vent lines, one from each fuel tank, which protrude from .
the trailing edge of the wing at the wing tips. Also the fuel reservoir
is vented to both wing tanks.
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FUEL QUANTITY DATA
UNITS
OF
MEASURE
FUEL
LEVEL
(OUANTITY EACH
TANK)
TOTAL
TOTAL
FUEL UNUSABLE
TOTAL
USABLE
ALL FLT
CONDIT·
IONS
FULL
(OUTBOARD FILLERS)
POUNDS
1124.25
2248.5
24.1
2224.4
GALLONS
(u .s .)
167.8
335.6
3.6
332
FULL
(INBOARD FILLERS)
POUNDS
806
1612
24.1
1587.9
GALLONS
(U.S.)
120.3
240.6
3.6
237
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NOTES:
1. Pounds are based on a fuel specific weight of 6.7 pou nds
per U.S. gallon.
A
WARNING
To achieve full capacity, fill fuel tank to the top
of the fuel filler neck. FIlling fuel tanks to the
bottom· of the fuel filler collar (level with flapper
valve) allows space for thermal expansion and
results in a decrease in fuel capacity of four
gallons per side (eight gallons total).
I
Figure 7·11 , Fuel Quantity Data
7 September 2001
For Training Purposes Only
(
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CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
·SYSTEMS DESCRIPTION
FIREWALL FUEL SHUTOFF VALVE
(
A manual firewall fuel shutoff valve,located on the aft side of the
firewall, enables the pilot to shut off all fuel flow from the fuel
reservoir to the engine. The shutoff valve is controlled by a red
push-pull know labeled FUEL SHUTOFF - FUEL OFF and located
on the right side of the pedestal. The push-pull knob has a pressto-release button in the center which locks the knob in position
when the button is released.
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FUEL TANK SELECTORS
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Two fuel tank selectors, one for each tank, are located on the
overhead console. The selectors - labeled LEFT, ON and OFF(left
tank) and RIGHT, ON and OFF (right tank) - mechanically control
the ppsition of the two fuel tank shutoff valves for that tank. When a
fuel tank selector is .in the OFF position; the shutoff valves for that
tank are closed. When in the ON position, both shutoff valves in the
tank are open, allowing fuel from that tank to flow to the reservoir.
Normal fuel management is with both fuel tank selectors in the ON
position.
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Before refueling, or when the airplane is parked on a slope, turn off
one of the fuel tank selectors (if parked on a slope, turn high wing
tank off). This action prevents crossfeeding from the fuller or higher
tank and reduces any fuel seepage tendency from the wing tank
vents.
FUEL SELECTORS OFF WARNING SYSTEM
f' "
A fuel selectors off warning system is incorporated to alert the pilot
if one or bother of the fuel tank selectors are left in the OFF position
inadvertently. The system includes redundant warning horns, a red
annunciator light labeled FUEL SELECT OFF, actuation switches,
and miscellaneous electrical hardware. The dual aural warning
system is powered through the START CONT circuit breaker with a
non-pullable FUEL SEL WARN circuit breaker installed in series to
protect the integrity of the start system. The annunciator is powered
from the ANN PANEL circuit breaker.
\ . ;, ;)
7-63
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
The warning system functions as follows: (1) If both the left and right
fuel tank shutoff valves are closed (fuel tank selectors in the OFF
position), the ·red FUEL SELECT OFF annunciator illuminates and
one of the fuel selector off warning horns is activated; (2) During an
engine start operation (STARTER sWitch in START or MOTOR posi- (
tion) with either the left or right fuel tank shutoff valves closed, the
red FUEL SELECT OFF annunciator illuminates and both of the fuel
select off warning horns are activated; (3) With one fuel tank selector OFF and fuel remaining in the tank being used less than approximately 25 gallons, the FUEL SELECT OFF annunciator illuminates and one of the fuel selector off warning horns is activated.
If the FUEL SEL WARN circuit breaker has popped or the START
CONT circuit breaker has been pulled (possibly for ground
maintenance), the FUEL SELECT OFF annunciator will be
illuminated even with both fuel tank selectors ON. This is a warning
to . the pilot that the fuel selector warning system has been
deactivated.
AUXILIARY BOOST PUMP SWITCH
An auxiliary boost pump switch, located on the left sidewall switch (
and circuit breaker panel , is labeled FUEL BOOST and has OFF, "
NORM, and ON positions. When the switch is in the OFF position,
the auxiliaw boost pump is inoperative. When the switch is in the
NORM position, the auxiliary boost pump is armed and will operate
when fuel pressure in the fuel manifold assembly drops below 4.75
psi. This switch position is used for all normal engine operation
where main fuel flow is provided by the ejector boost pump and the
auxiliary boost pump is used as a standby. When the auxiliary boost
pump switch is placed · in the ON position, the auxiliary boost pump
will operate continuously. This position is used for engine start and
any other time that the auxiliary boost pump cycles on and off with
the switch in the NORM position.
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FUEL FLOW INDICATOR
A fuel flow indicator, located at the top of the instrument panel,
indicates the fuel consumption of the engine in pounds per hour
based on Jet A fuel. The indicator measures the flow of fuel ( (
downstream of the fuel control unit just before being routed into the \~ _,
flow divider. When power is removed from the indicator, the needle
(
will stow below zero in the OFF band.
7-64
1 April 1998
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
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("--
The fuel flow .indicator receives power from a "pull~off" type circuit
breaker lab~led ,FUEL FLOW, on the left sidewall switch and circuit
breaker pan~t: .
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FUEL QUANTITY ,INDICATORS
Fuel quantity is ' measured by eight fuel quantity' transmitters (four in
each tank) and indicated by two electrically-operated fuel quantity
indicators on 'the upper portion of the instrument panel. The fuel
quantity indicators, which measure volume, are calibrated in pounds
(based on the weight of Jet A fuel on a standard day) andga"ons.
An empty tank is indicated by a red line and the letter E. When an
indicator shows an empty tank, approximately 2.8 gallons remain in
the tank as unusable fuel. The left and right fuel quantity indicators '
each receive power from a "pull-off" type circuit breaker. The
breakers are labeled LEFT FUEL QTY and RIGHT FUEL QTY,
respectively, and are located on the left sidewall switch and circuit
breaker panel.
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A WARNING
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Because of the relatively long fuel tanks, fuel
quantity Indicator accuracy Is affected by
uncoordinated flight or a sloping ramp if reading
the Indicators while on the ground. Therefore, to
obtain accurate fuel quantity readings, verify that
the airplane is parked in a laterally level
condition, or If In flight, make sure the airplane
Is In a coordinated and stabilized condition.
'
WING TANK FUEL LOW WARNING ANNUNCIATORS
Two amber fuel low warning annunciators, one for each wing tank,
are located on the annunciafor panel. The annunciators are labeled
LEFT FUEL LOW and RIGHT FUEL LOW. Each annunciator will
illuminate when the fuel in the respective tank is 25 gallons or less.
RESERVOIR FUEL LOW WARNING.ANNUNCIATOR
(..,,=)
A red reservoir fuel low warning annunciator is located on the
annunciator panel. The annunciator is labeled RESERVOIR FUEL
LOW, and wi.II illuminate when the level of fuel in the reservoir drops
to approximately one-half full.
7-65
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
(
FUEL PRESSURE LOW WARNING ANNUNCIATOR
An amber fuel pressure low warning annunciator is located on the
annunciator panel. The annunciator is labeled FUEL PRESS LOW, :
and will illuminate when fuel pressure in the reservoir fuel manifold \
assembly is below 4.75 psi.
AUXILIARY FUEL PUMP ON ANNUNCIATOR
An amber auxiliary fuel pump on annunciator is located on the
annunciator panel. The annunciator is labeled AUX FUEL PUMP
ON and Will illuminate when the auxiliary boost pump is operating,
such as when the auxiliary boost pump switch is placed in the ON
position or when the auxiliary boost pump switch is in the NORM
position and fuel pressure in the fuel manifold assembly drops
below 4~ 75 psi.
DRAIN VALVES
The fuel system is equipped with drain valves to provide a means
for the examination of fuel in the system for contamination and
grade. Drain valves are located on the lower surface of each wing at (
the inboard end of the fuel tank, in fuel tank external sumps, on the
underside of the reservoir tank, and on the underside of the fuel
filter. Outboard fuel tank drain valves may be installed, and their
use is recommel)ded if the airplane is parked with one wing low on
a sloping ramp '(as evidenced by the ball of the turn and bank
indicator displaced from center). The drain valves for the wing
tanks (and their external sumps, if installed) are tool-operated
poppet type and are flush-external mounted. The wing tank and
external sump drain valves are constructed so that the Phillips
screwdriver on the fuel sampler which is provided can be utilized to
depress the valve and then twist to lock the drain valve 'in the open
position. The drain valve for the reservoir consists of a recessed Thandle · which can be depressed and then turned to lock the valve
open. The drain valve for the fuel filter consists of a drain pipe
which can be depressed upward to drain fuel from the filter. The
fuel sampler · can be used on all of these drain valves for fuel
sampling and purging of the fuel system . The fuel tanks should be
filled after each flight when practical to minimize condensation.
1 April 1998
7-66
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP) ·
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
(
( ('
\
Before each flight of the day and after each refueling, use a clear
sampler and drain fuel from the inboard fuel tank sump (and
external sump, if installed) quick-drain valves, fuel reservoir quickdrain valve, and fuel filter quick-drain valve to determine if
contaminants are present, and that the airplane has been fueled
with the proper fuel. If the airplane is parked with one wing Iowan
a sloping ramp, draining of the outboard fuel tank sump quick-drain
valves (if installed) is also recommended.
If contamination is
detected, drain all fuel drain points again. Take repeated samples
from all fuel drain points until ·all contamination has been removed.
If after repeated sampling, evidence of contamination still exists, the
fuel tanks should be completely drained and the fuel system
cleaned. Do not fly the airplane with contaminated or unapproved
.
fuel.
.
AWARNING
JP-4 and other naphtha based fuels. tan cause
severe skin and eye Irritation.
FUEL DRAIN CAN
(
When the engine is shut down, residual fuel in the engine drains
into a fuel drain can mounted on the front left side of the firewall.
This can should be drained once a day or at an interval not to
exceed six engine shutdowns. A drain valve on the bottom side of
the cowling enables the pilot to drain the contents of the fuel drain
can into a suitable container.
FUEL PUMP DRAIN RESERVOIR
To control expended lubricating oil from the engine fuel pump drive
coupling area and provide a way to determine if fuel is leaking past
the fuel pump seal, airplanes are equipped with a drainable
reservoir to collect this allowable discharge of oil and any fuel
seepage. The reservoir is mounted on the front left side of the
firewall. It should be drained once a day or at an interval not to
exceed six engine shutdowns. A drain valve on the bottom side of
the cowling enables the pilot to drain the .contents of the reservoir
into a suitable container. A quantity of up to 3 cc of oil and 20 cc of
fuel discharge per hour of engine operation is allowable. If the
quantity of oil or fuel drained from the reservoir is greater than
specified, the source of leakage should be identified and corrected
prior to further flight.
7-67
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
BRAKE SYSTEM
The airplane has a single-disc, hydraulically-actuated brake on each
main landing gear wheel. Each brake is connected, by a hydraulic ..
line, to a master cylinder attached to each of the pilat's rudder \
pedals. The brakes are 'operated by applying pressure to the top of
either the left (pilot's) or right (front passenger's) , set of rudder
. pedals, which are interconnected. When the airplane is parked, both
main wheel brakes may beset by utilizing the parking brake which
is operated by a ' handle on the lower left side of the instrument
panel. To apply the parking brake,set the brakes 'With the rudder
pedals and pull the handle aft. To release the parking brake, push
the handle fully in.
A brake fluid reservoir, located just forward of the firewall on the left
side of the engine compartment, provides additional brake fluid for
the brake master cylinders. The fluid in the reservoir should be
checked for proper level prior to each flight.
For maximum brake life, keep the brake system properly
maintained. Airplanes are equipped with metallic type brakes, and
require a special brake burn~in before delivery (or after brake "
replacement). When conditions permit, hard brake application is (,
beneficial in that the resulting higher brake temperatures tend to
maintain proper brake glazing and will prolong the expected brake
life. Conversely, the habitual use of light and conservative brake
application is detrimental to metallic brakes.
Some of the symptoms of impending brake failure are: gradual
decrease in braking action after brake application, noisy or dragging
brakes, soft or spongy pedals, and excessive travel and weak
braking action. If any of these symptoms appear, the brake system
is in need of immediate attention. If, during taxi or landing roll,
braking action decreases, let up on the pedals and then re-apply the
brakes with heavy pressure. If the brakes become spongy or pedal
travel increases, pumping the pedals should build braking pressure.
If one brake becomes weak or fails, use the other brake sparingly
while using opposite rudder, as required, to offset the good brake.
1 April 1998
7-68
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
(
(
(
(
(
(
(
ELECTRICAL SYSTEM
The airplane is equipped with a 28-volt, direct-current electrical
system (see Figure 7-12). The system uses a 24-volt lead-free
battery; or 24-volt sealed lead acid battery; or 24-volt Ni-Cad battery
located on the front right side of the firewall, as a source of
electrical energy. A 200-amp engine-driven starter-generator is
used to maintain the battery's state of charge. Power is supplied to
most general electrical and all avionics circuits through two general
buses, two ' avionics buses, and a battery bus. The battery bus .is
energized continuously for memory keep-alive, clock, and
cabin/courtesy lights functions. The two general buses are on
anytime the battery switch is turned on. All DC buses are on
anytime the battery switch and the two avionics switches are turned
on.
I
(
An optional standby electrical system, which consists of an enginedriven alternator and separate busing system, may be installed in
the airplane. For details of this system, refer to Section 9,
Supplements.
(
(
/
GENERATOR CONTROL UNIT
The generator control unit (GCU) is mounted inside the cabin on the
left forward fuselage sidewall. The .unit provides the electrical
control functions necessary for the operation of the startergenerator. The GCU provides for automatic ' starter cutoff when
engine RPM is above 46. Below 46, the starter-generator functions
as a starter, and above 46, the starter-generator functions as a
generator when the starter switch is OFF. The GCU provides
voltage regulation plus high voltage protection and reverse current
protection. In the event of a high-voltage or reverse current
condition, the generator is automatically disconnected from the
buses. The generator contactor (controlled by the GCU) connects
the generator output to the airplane bus. If any GCU function
causes the generator contactor to de-energize, the red
GENERATOR OFF light on the annunciator panel will come on.
7-69
Revision 6
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
.SYSTEMS DESCRIPTION
(
(
(
GENERATOR
.(
GEHEIIATOA
SHUNT
GENiAAtOA
CDNTACTOA
fiELD
(
fADM
r - -....---~!).-- ~~~10L
CiRCUIT
BREAKER
STAATER
SW,,.CM
G'N
CONTROL
(
UNO
CONT
"NSE
(
I _____·I __..JGRJ~ND
TO 1110. 1
BUS
I'OW1!R
tolONITOR
TO HO . 1
BUS
(
(
VOLT
AMM£TIfI
TO NO.2
BUS
(
(
TO NO. 2
BUS
UNI£ COMT ... CTOft UNSf
fAOM
START
CONTROL
51 .... /IT
eo,.,."oL.PO'W(P.
STAATCONTACTOR
\0----...1
(
1------01:(1
CIRCUIT
TONO. l
8AfAKER
IIU5
(JENERATOfl CONTROL UNIT
......
SWlTCt11
8f11EAKEA
TO HO. 2
AviONICS
"""'.
_TCHI
BREAKI"
COOl
ell) ~~tL~~F=~S'i!;O."ESETI
rv
fUSE
'*
_
IUllA"
.-a
!WI1tHIClDSiDI
DIODE
BATTERY
BUS
2685M7002
Figure 7-12. Electrical System (Sheet 1 of 3)
1 April 1998
For Training Purposes Only
(
(
TO NO. 1
AVIONICS
7-70
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
(
(
s~ TO
.-DlJI- TO
STAN)BY FLAP ,..,TOR
.......DlJI- TO
IONITION EXCITER
.f-oDlJIIl-
5", "'""
y FLAP ..,T(I01
TO rt.E.L SCLECT(J1 rlFP:
\tARN I NJ SYSTEM
(
at--
STAt.()8V AL TERND.TM' SYSTEM
.~:3I>--ro PRI ....
TO SUNDBY AL TERN,uOR
SYSTE"
TO LEFT V[I.ITILATION SLOVER
. - I " '___ TO AUXILIARY 'fUEL PUHP 5\1 .
--{3.......(3r-ro
ENGINE FUEL CONTROl
HEUER
.-I"'~ TO .1 GHT TURN ANO BANK
TO STARTER SU, AN> CiCU
INOICATOR
.f--QlI~ TO UP'T TLAN N.O BAN< IN)ICAT('A
(
.H"'~ TO A..NUNC I ATOll PANEL
.-II"l1I~ TO STALL .'RNING SYSTEM
.......I"l1I~ TO
(
AIR -CONOIJIONER
.~~>-- TO PlRE DETICTOA SVSTIM
(
.-<~-1'O ITT INDICATOR
.-I::3~TO Fl£L TOTALIZER
_-<""-TO FUEL
_-I~~TO OIL TEKJERATUfE GAGE
.-<~-fO AIIiHT FUEL OUANTITY
IICHI' nil. or, INDICATOR
--cllll_-<3- TO ....EEO AIR HEATIR
.~:3-TO AIR COOOITIONIt«l SYSTEM
.~3
(
(
nov
.-I:'-lII~TO.LEFT Fl.£L ClJANTITY It..olCAlm
___ TO LEFT
.-1[31- TO
fO A I RSPE£D \JAANING SVSTEH
I'IIIJIlII
o.po
TQT
PilOT !-EATER
_-IrnI~ TO u'NlSHIELD ANTI-ICE t-£ATER
INOICATOR
....
TO PROPELLER OVERSPEED
VALVE ASSEMBLY
1'0 WING ANO STABIL IlER
DE ~ It£ SYSTEM
.-<'111>-- TO
R I CHT PilOT HEATEA
"1101 .... '
ulp.()SHIElD ANTI-Ice CONTROl.
.-<'111>-- SYSTEM
TO PROPELLER
ANT I - I C IHG
.-<~-TO PROPELLER ANTI-ICING
....
~ICl CONTROL
(
. H r n i - T O RIGHT LAhOlNG LIGHT
.......('j!I~
TO T"MI LIGHTS
.H"'~ TO ••• IGATION LIGHTS
--{~!.r-CllJI-
TO READING LIOHTS
.-<".- TO "DIO 'NO
FLOOD LIGHTS
TO R. H . AnlTLDE GYRO
_-<""TO
. . . . .' .,.. NO
F"STlfH SEAT BEL T AND
5MOt(ING SIGN
TO [NCODING ALTIHETER
.f--nlI~ TO ElEVATOR TRIM $VSTEH
2685T6007
Figure 7-12. Electrical System (Sheet 2 of 3)
1 April 1998
7-71
For Trainin2 Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
~~JX~Y --~:\---.....--·g1t-~Dcm~~ONSINA'IIO"TION RECEtVER
~
PIllER
.---51'_
SWITCHI
BREAKER
r:JI' -
!"'AOM PO\.IER--A
DISTRIBUTION
BUS
---Ir~t"- TO
fa RECEIVER I
_-<:llIII--TO t(RIZ()IITAI..
Nt.t1EIEA I
AVIONICS
POI/ER
SW',TCtv
aREAKEflr_ _
SITUATI~
.---51'_
-It~~~TO
51'_
NDIO
CONTROl..
CONSOLE
HARKER
BE"CQoI
REa
I Y£R
_
ftVIONICS
I
~-
AVIONICS
SINGlY
INJICATm
MIl
-----Ir-9P,--TO NI'
rAOH POWER
DISTRIBUTION
BUS
(
RECEIVER 2
(
.-<3-TOtIE
.-
~::,,: "'-·~'-'~·I
/I0:,~ "'~'"
'oilJ
/"
TO CABIN
TO DEfROST
HEAT
SELECTOR
AlA/FORWARD
CABIN AlA
VALVE
VALVE
SELECTOR
VALVE
O
----- ~1
(
VENTILATING AIR DOOR
II
II
TO
MIXING
AIR
FIReWAll
SHUTOFF VALVE
CONTROL
CABIN HEAT SELECTOR VALVE
tONE EACH SIDE)
DEFROST AlA/ FORWARD CABIN
AIR SHECTOR V",LV'E
(
INSTRUMENT PANEL
VENTII.ATING OUTLETS
AND CONTROLS (2)
(
AQJUSTABlE PILOT AND
FRONT PASSENGER OVERHEAD
VENTILATING ouTLETS 121
(
,
(
\
(
\
,
VENT A.IR CONTROL
\ \ '~N-@'AD CONSOLEI
("
(
~
(
SHUTOFF VALVE
(ONE EACH WING)
(
..
MIXING AIR VALVE OPE RATING MODES;
(
I
~
li.
Mixin!) air vllva In GAO pOlll lon
&, Jlower ItltinlP below S9~.
Us.d on 'htl' ground al cold
temperllum.
•
....
¢
• .. • '
(
Two vent knobs, Jabeled VENT, PULL ON, are located one on each
side of the instrument panel. Each knob controls the flow of
ventilating air from , an outlet located adjacent to each knob. Pulling
each knob opens a small air door on the fuselage exterior which
pulls in ram air for distribution through the ventilating outlet.
VENTILATING OUTLETS
Adjustable ventilating outlets (one above each seat position) permit
individual ventilation to the airplane occupants. The pilot's and front
passenger's outlets are the swivel type for optimum positioning, and
airflow volume is controlled by rotating the butlet nozzle which
controls an internal valve. Eight additional rear seat passenger
outlets on the Standard 208 are adjustable fore and aft, and each
have a separate rotary type control beside the outlet, with pOSitions
labeled AIR ON and AIR OFF, "to control airflow volume through the
outlet.
(
(
OXYGEN SYSTEM
( ',
" ,-"ci
The airplane is equipped with oxygen system provIsions which
consist of the system plumbing for a 10-port system. If the airplane
is equipped with a complete 2-port or 10-port oxygen system, refer
to Section 9, Supplements, for complete details and operating
instructions.
7-89
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
PITOT-STATIC SYSTEM AND INSTRUMENTS
The pitot-static system supplies ram air pressure to the airspeed
indicator and static pressure to the airspeed indicator, vertical speed .
indicator, and altimeter. The system is composed of a heated pitot- \
static tube mounted on the leading edge of the left wing, a static
pressure alternate source valve located below the de-ice/anti-ice
switch panel; a drain valve located on the left sidewall beneath the
instrument panel, an airspeed pressure switch located behind the
instrument panel, and the associated plumbing necessary to
connect the instruments and sources.
The pitot-static heat system consists of a heating element in the
pitot-static tube, a two-position toggle switch, labeled PITOT/STATIC
HEAT, on the de-ice/anti~ice switch panel, and a "pull-off" type
circuit breaker, labeled LEFT PilOT HEAT, on the left sidewall
switch and circuit breaker panel. When the pitot-static heat switch is
turned on, the element in the pitot-static tube is heated electrically
to maintain proper operation in possible icing conditions.
A static pressure alternate source valve is installed below the deice/anti-ice switch panel, and can be used if the static ' source is i
malfunctioning. This valve supplies static pressure from inside the
cabin instead of from the pitot-static tube. If erroneous instrument
readings are suspected due to water or ice in the pressure line
going to the static pressure source, the alternate source valve
should be pulled on. Pressures within the cabin will vary with vents
open or closed. Refer to Sections 3 and 5 for the effect of varying
cabin pressures on airspeed and altimeter readings.
A drain valve is incorporated into the system and is located on the
left cabin sidewall beneath the instrument panel. The valve is used
to drain suspected moisture accumulation in the system by lifting
the drain valve lever ' to the OPEN position as indicated by the
placard adjacent to the valve. The valve must be returned to the
CLOSED position prior to flight.
An airspeed pressure switch in the pitot-static system is used to
actuate an airspeed warning horn in the event excessive airspeed is
(
inadvertently attained. The horn is located behind the headliner in \ (
the area above the pilot, and will sound when airspeed exceeds --' VMO (175 KIAS). A warning signal may also be heard in the pilot's
(
headset.
1 April 1998
7-90
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
RIGHT FLIGHT INSTRUMENT PANEL PITOT-STATIC SYSTEM
(
A second, independent pitot-static system is included whenever the
right flight instrument panel is installed. The system supplies ram
air pressure to the airspeed indicator and static pressure to the
airspeed indicator, vertical speed indicator, and altimeter utilized in
the right flight panel instrument group. The system is composed of a
heated pitot-static tube on the leading edge of the right wing, a
drain valve on the right cabin sidewall beneath the instrument panel,
and the plumbing necessary to connect the instruments to the
sources. The right pitot-static system is not connected to the pilot's
flight instrument pitot-static (left) system.
(
(
(
(
The pitot-static heat system for the right flight instrument panel
consists of a heating element in the right pitot-static tube, the
standard system two-position toggle switch, labeled PITOT/STATIC
HEAT, on the de-ice/anti-ice switch panel, a "pull-off" type circuit
breaker, labeled RIGHT PITOT HEAT, on the left sidewall switch
and circuit breaker panel, and the associated wiring.
(
(
(
(
(
/--
( {Ie
.
.
.... - .
(
(
(
The drain valve incorporated into the right flight panel static system
functions identically to the standard system drain valve. Use the
right valve to drain suspected moisture accumulation in the system
lines as indicated by the placard, labeled STATIC SOURCE DRAIN,
OPEN, CLOSED, adjacent to the valve. Make sure the valve is
returned to the CLOSED position prior to flight.
(
7-91
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANEAND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
AIRSPEED INDICATOR(S)
The airspeedindicator(s) is calibrated in knots. Limitation and
range markings (in KIAS) include the white arc (full flap operating ,
range of 50 to 125 knots), green arc (normal operating range of 63 '·
to 175 knots), and a red line (maximum speed of 175 knots). The
left-hand instrument is a true airspeed indicator and is equipped
with a rotatable ring which works in conjunction with the airspeed
indicator dial in a manner similar to the operation of a flight
computer. To operate the indicator, first rotate the ring until pressure
altitude is aligned with outside air .temperature in pressure altitude,
momentarily set the barometric scale on the altimeter to 29.92 and
read pressure altitude on the altimeter. Be sure to return the
altimeter barometric scale to the original barometric setting after
pressure altitude has been obtained. Having set the ring to correct
for altitude and temperature, read the true airspeed shown on the
rotatable ring by the indicator pointer. For best accuracy, the
indicated airspeed should be corrected to calibrated airspeed by
referring to the Airspeed Calibration chart in Section 5. Knowing the
calibrated airspeed, read true airspeed on the ring opposite the
calibrated airspeed .
. VERTICAL·SPEED INDICATOR(S) '
The vertical speed indicator(s) depicts airplane rate of climb or
descent in feet per minute. The pointer is actuated by atmospheric
pressure changes resulting from changes of altitude as supplied by
the static source(s).
AL TIMETER(S)
Airplane altitude is depicted by a barometric type altimeter(s). A
knob near the lower left portion of the indicator provides adjustment
of the instrument's barometric scale to the current altimeter setting.
1 April 1998
7-92
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
VACUUM SYSTEM AND INSTRUMENTS
A vacuum system (see Figure 7-14) provides the suction necessary
to . operate the left-hand attitude indicator and directional indicator.
Vacuum is obtained by passing regulated compressor outlet bleed
air through a vacuum ejector. Bleed air flowing through an orifice in
the ejector creates the suction necessary to operate the
instruments. The vacuum system consists of the bleed air pressure
regulator, a vacuum ejector on the forward left side of the firewall, a
vacuum relief valve and vacuum system air filter on the aft side of
the firewall, vacuum operated instruments and a suction gage on
the left side of the instrument panel, and a vacuum-low warning
annunciator on the annunciator panel.
(
(
(
ATTITUDE INDICATOR
(
The attitude indicator gives a visual indication of flight attitude,
Bank attitude is presented by a pOinter at the top of the indicator
relative to the bank scale which has index marks at 10°, 20°, 30°,
60°, and 90 0 either side of the center mark. Pitch and roll attitudes
are presented by a miniature airplane superimposed over a
symbolic horizon area divided into two sections by a white horizon
bar. The upper blue "blue sky" and the lower "ground" area have
arbitrary pitch reference lines useful for pitch attitude control. A
knob at the bottom of the instrument is provided . for inflight
adjustment of the miniature airplane to the horizon bar for a more
accurate flight attitude indication.
(
(
/.~.
t
(
\ .._..
(
(
(
(
I
When the airplane is equipped with a right flight instrument panel,
the attitude indicator is .electricallY .powered. Th. e inst.rument iSI
protected by a "pull-off" .type circuit breaker, labeled RH ATT
GYRO on the left sidewall switch and circuit breaker panel. The
instrument is energized any time the battery switch is on and the
circuit breaker is pushed in.
(
(
t
\~,v'
·
Special procedures for caging the attitude indicator must be
followed when caging the gyro prior to flight. If takeoff is soon after
engine start, cage the gyro immediately after engine start by
exercising a moderate even pull on the caging knob. Hold for
approximately five seconds and release the caging knob smoothly
but quickly.
7-93
7 September 2001
For Traininl! Purooses Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
'A19803
BLEED
AIR
BLEED AIR
EXHAUST
PRESSURE
REGULATOR
VACUUM RELIEF VALVE
VACUUM-LOW
WARNING
ANNUNCIATOR
(
.
(
(
(
(
(
r-----------CODE----------~
~ BLEED AIR
c::::J
,.:•.•:§:.:.j VACUUM
INLET A I R _ ELECTRIC
26856038
I
Figure 7-14. Typical Vacuum System
7 September 2001
7-94
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
Allow the gyro to attain full speed and do not re-cage unless the
gyro will not erect after approximately five minutes.
If time between engine start and takeoff is ten minutes or more, the
alternate caging procedure is recommended. After engirie start, do
not cage the gyro. Allow gyro te run until ready fer the Befere
Takeoff checklist. If necessary, cage the gyro just before takeoff. In
many cases, the gyro will have erected itself sufficiently so that
caging is not necessary.
&
CAUTION
Avoid re-caglng once the gyro has been caged.
Repe~ted caging may cause Internal damage.
DIRECTIONAL INDICATOR
(
The directional indicator displays airplane heading en a compass
card in relation te a fixed simulated airplane image and index. The
directienal indicator will precess slightly over a peried .of time.
Therefere, the cempass card sheuld be set in accordance with the
magnetic cempass just prior te takeoff, and occasionally -re-adjusted
on extended flights. A knob on the lower left edge of the instrument
is used to adjust the cempass card to cerrect for any precessien.
I
SUCTION GAGE
The suction gage, lecated en the left side .of the instrument panel, isl
calibrated in inche~ of mercury and indicates suction available for
eperatien .of the attitude and directional indicators. The . desired
suction range is 4.5 to 5.5 inches of mercury up to 15,000 feet
altitude, 4.0 to 5.5 inches .of mercury from 15,000 to 20,000 feet,
and 3.5 to 5.5 inches of mercury from 20,000 to 25,000 feet. The
15K, 20K,25K and 30K markings at the apprapriate step lecations
indicate the altitude (in thousands of feet) at which the lower limit .of
that arc segment is acceptable. A suctian reading out .of these
ranges may indicate a system malfunction .or improper adjustment,
and in this case, the attitude and directional indicaters shauld not be
considered reliable.
7.-95
7 September 2001
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
(
. VACUUM-LOW WARNING ANNUNCIATOR
A red vacuum-low warning annunciator is installed on the
annunciator ' panel to warn the pilot of a possible low-vacuum
condition existing in the vacuum system. Illumination of the/
lannunciator warns the pilot to check the suction gage and to bel
alert for possible erroneous vacuum-driven gyro instrument
indications. The annunciator is illuminated by operation of a
warning switch which is activated . anytime suction is less than
approximately 3.0 in. Hg . .
(
(
(
(
(
IOUTSIDE AIR TEMPERATURE (OAT) GAGE
(
I
An .outside air temperature (OAT) gage is in.stalled in the upper left "
side of the windshield.
The gage is calibrated in degrees
(
Fahrenheit and Celsius.
(
STALL WARNING SYSTEM
The airplane is equipped with a vane-type stall warning unit, in the
leading edge · of the left wing, which is electrically' connected to a
stall warning horn located overhead .of the pilot's position. The vane /' .(
in the wing senses the change in airflow over the wing, and \ (
operates the warning horn . at airspeeds between 5 and 10 knots
above the stall in all configurations.
The stall warning system should be checked during the preflight
inspection by momentarily turning on the battery switch and
actuating the vane in the wing. The system is operational if the
warning horn sounds as the vane is pushed upward. Aircraft
, equipped with a stall warning ground disconnect switch will require
that the elevator control be off the forward stop before the stall
warning horn is enabled.
A "pull-off" type circuit breaker, labeled STALL WRN, protects the
stall warning system. Also, it is provided to shut off the warning
horn in the event it should stick in the on position.
7 September 2001
7-96
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
A
(
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
WARNING
This circuit breaker must be pushed In for
landing.
\
The vane and sensor unit in the wing leading edge is equipped with
a heating element. The heated part of the system is operated by the
STALL HEAT switch on the de-icelanti-ice switch panel, and is
protected by the STALL WRN circuit breaker on the left sidewall
switch and circuit breaker panel.
(
AVIONICS SUPPORT EQUIPMENT
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Various avionics support equipment is .instaUed in the airplane, and
includes an avionics cooling fan, microphone-headset installation,
and control surface static dischargers. The following paragraphs
discuss these items. Description and operation .of radio equipment is
covered in Section 9 of this handbook.
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AVIONICS COOLING FAN
'-~---'
An avionics cooling fan system is provided in the airplane to supply
internal cooling air for prolonged avionics equipment life. The fan
will operate when the battery switch is on and the number 2
avionics power switch is on. If the fan malfunctions, it can be shut
off using the "pull-off" type circuit breaker, ,labeled AVN FAN,
located on the left sidewall switch and circuit breaker panel.
MICROPHONE-HEADSET INSTALLATIONS
The airplane is equipped with a padded microphone-headset for the
pilot. A padded microphone-headset is also available for the front
seat passenger. The microphone-headsets utilize remote keying
switches located on the left grip of the pilot's control wheel and the
right grip of the front passenger's control wheel. Use of the keying
switches permits radio communications without interrupting other
control operations to handle a hand-held microphone. A hand-held
microphone, which plugs into a mic jack on the left side of the
control pedestal, is also available and can be used with the airplane
speaker when a microphone-headset is not being utilized . .
7-97
1 April 1998
For Training Plirposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
The microphone stows' in a hanger on the front of the pedestal.
Microphone and headset jacks are located on the ,left side of the
instrument panel for the pilot and the right side of the instrument
panel for the front passenger. Audio to the headsets is controlled by ,
the individual audio selector switches and adjusted for volume level \
by using the selected receiver volume controls.
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NOTE
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To ensure audibility and clarity when transmitting with the
hand-held microphone, always hold it as closely as possible
to the lips, then key the microphone and speak directly into
it.
Avoid covering the opening on the back side of
microphone for optimum noise cancelling.
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STATIC DISCHARGERS
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As an aid in IFA flights, wick-type static dischargers are installed to
improve radio communications during flight through dust or various
forms of precipitation (rain, snow or ice crystals). Under these
conditions, the build-up and discharge of static electricity from the (
trailing edges of the wings, rudder, elevator, propeller tips, and radio '
antennas can result in loss of usable radio signals on all
communications and navigation radio equipment. Usually the ADF is
first to be affected and VHF communication equipment is the last to
be affected.
Installation of static dischargers reduces interference from
precipitation static, but it is possible to encounter severe
precipitation static conditions which might cause the loss of radio
signals, even with static dischargers installed. Whenever possible,
avoid known severe precipitation areas to prevent loss of
dependable radio signals. If avoidance is impractical, minimize
airspeed and antiCipate temporary loss of radio Signals while in
these areas.
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1 April 1998
7-98
For Training Pu rposes Only
CESSNA
MODEL 208 (675 SHP)
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SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
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Static dischargers lose their effectiveness with age, and therefore,
should be checked periodically (at least at every annual inspection)
by qualified avionics technicians, etc. If testing equipment is not
available, it is recommended that the wicks be replaced every two
years, especially if the airplane is operated frequently in IFR
conditions. The discharger wicks are designed to unscrew from their
mounting bases to facilitate replacement.
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CABIN FEATURES
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CABIN FIRE EXTINGUISHER
A portable Halon 1211 (Bromochlorodifluoromethane) fire
extinguisher is available for installation on the inside of the pilot's
entry door where it would be accessible in case of fire. The
extinguisher has an Underwriters Laboratories classification of 5B:C. ·
If installed, the extinguisher should be checked prior to each flight to
ensure that its bottle pressure, as indicated by the gauge on the
bottle, is within the green arc (approximately 125 psi) and the
operating lever lock pin is securely in place.
(.
To operate the fire extinguisher:
1. Loosen retaining clamp(s) and remove extinguisher from
bracket. "
2. Hold extinguisher upright, pull operating lever lock pin, and
press lever while directing the discharge at the base of the fire
at the near edge. Progress toward the back of the fire by
moving the nozzle rapidly with a side-to-side sweeping motion.
A
CAUTION
Care must be taken not to direct the Initial
discharge directly at the burning surface at
close range (less than five feet) because tt!e
high velocity stream may cause splashing and/or
scattering of the burning material.
3. Anticipate approximately eight seconds of discharge duration,
7-99
1 April 1998
For Training Purposes Only
SECTION 7
AIRPL.:ANE AND
SYSTEMS DESCRIPTION
A
CESSNA
MODEL 208 (675 SHP)
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WARNING
Veli.tllate the cabIn promptly after successfully
extinguishing the fire to .reduce the gases
produced by .thermal decomposition. Occupants
should use oxygen masks until the smoke
clears.
Fire extinguishers should be recharged by a qualified fire
extinguisher agency after each use. Such agencies are listed under
"Fire Extinguisher'" in the telephone directory. After recharging,
secure the extinguisher to its mounting bracket; do not allow it to lie
loose on shelves or seats.
SUN VISORS /
Two sun visors are mounted overhead of the pilot and front
passenger. The visors are mounted on adjustable arms which
enable them to be swung 'and telescoped into the . desired
windshield area.
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MAP AND STORAGE COMPARTMENTS
A map compartment is located in the lower right side of the
instrument panel. A hinged door covers the compartment and can
be opened to gain access , into the compartment. Storage pockets
are also installed on the back of the pilot's and front passenger's
seats and along the bottom edge of each crew entry' door and can
be used for stowage of maps and other small objects.
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BEVERAGE CUP HOLDERS
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Two beverage c'up holders, one for the pilot and one for the right
front passenger, are installed under the instrument panel. The
holders are hinge-mounted and swing out from under the instrument
panel where they can be used for holding beverage cups. When
' not in use, the cup holders should be returned to their stowed
pOSition.
1 April 1998
7-100
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
MISCELLANEOUS EQUIPMENT
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CARGO BARRIER/NETS
(
The airplane may be equipped with a cargo barrier and three
barrier nets installed directly behind the pilot's and front
passenger's seats t() prevent the movement of cargo into the
forward position of the cabin during abrupt deceleration. Refer to
Section 6 for complete details of the cargo barrier and its nets.
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CARGO PARTITIONS
(
Cargo partitions are available and can be installed to divide the
cargo area into convenient compartments. . Partitions may be
installed in all of the five locations at stations 181.5, 208.0, 234.0,
259.0, and 284.0. Refer to Section 6 for complete details of the
cargo partitions.
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CARGO DOOR RESTRAINING NET
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A restraining net may be installed on the inside of the airplane over
the cargo door opening.
The restraining net precludes loose
articles from falling out the cargo door opening when the doors are
opened. Refer to Section 6 for complete details of the cargo door
restraining net.
CARGO/AIRPLANE TIE·DOWN EQUIPMENT .
Various items of tie-down equipment are available for securing
cargo within the airplane and/or tying down the airplane. This
equipment consists of tie-down belt assemblies having various load
ratings and adjustment devices and two types of quick-release tiedown ring anchors for securing the belts to the cabin seat tracks
and anchor plates. Refer to Section 6 for the recommended use
and restrictions of this equipment.
CARGO POD
The airplane may be equipped with a cargo pod which provides
additional cargo space. Refer to Section 9, Supplements, for
complete details of the cargo pod.
7-101
1 April 1998
For Training Purposes Only
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
CESSNA
MODEL 208 (675 SHP)
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ENGINE INLET COVERS AND PROPELLER ANCHOR
Various covers and an anchor are available to close engine .
openings and restrain the propeller during inclement weather I
conditions and when the airplane is parked for extended periods of
time" such as overnight. The covers preclude the entrance of dust,
moisture, bugs, etc. into the engine and engine compartment. Two
covers are provided which plug into the two front inlets, thereby
closing off these openings. The engine inlet covers may be installed
after the engine has cooled down (ITT indicator showing "off scale"
temperature) . To prevent the propeller from windmilling during
windy conditions, the propeller anchor can be installed over a blade
of the propeller and its anchor strap hook engaged over the lower
forward flange of the nose gear fairing. During towing operations,
the hook should be moved to the bracket on the lower right hand
cowl .near the secondary exhaust.
IHOISTING RINGS
Provisions are made for the installation of four hoisting rings which
attach to the left and right sides of both front and rear spar wing-to- /
fuselage attach fittings. Each hoisting ring consists of a hinge '.
which replaces the washer on the attachment bolt of the fitting. The
upper half of the hinge contains a ring which is used for attaching
the hoist when the airplane is being hoisted. When not in use, the
upper hinge half folds down out of the way. To gain access to the
hoisting rings, when installed, it is necessary to remove the wing-tofuselage fairing strips.
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7-102
Revision 6
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 7
AIRPLANE AND
SYSTEMS DESCRIPTION
(
(
CREW ENTRY STEP ASSEMBLIES
(
The airplane is equipped with a crew entry step for the left crew
entry door. A second crew entry step is available for the right crew
entry door. The step assemblies attach to the floorboard just inside
the entry doors and extend toward ground level,providing two steps
for entering or exiting the airplane. When not in use, the step
assemblies fold and stow just inside the cabin, inboard of the pilot's
and front passenger's entry doors.
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RELIEF TUBE
(
Provisions are made for the installation of a relief tube in the aft
cabin area on the Standard 208. The relief tube is installed on the
right sidewall, just aft of the passenger entry door.
(
OIL QUICK·DRAIN VALVE
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An oil quick-drain valve is available to replace the drain plug on the
bottom of the engine oil tank,and provides quicker, cleaner draining
of the engine oil. To drain the oil with this valve, slip a hose over
the end of the valve, cut the safety wire securing the valve on-off
lever in the off pOSition, and rotate the lever to the on position. After
draining, rotate the valve on-off lever to the off position, remove the
hose to check for leakage, and resafety the on-off lever in the off
position.
7-1 03/7-104
1 April 1998
For Training Purposes Only
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For Training Purposes Only
(
. CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
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......
SECTION 8
AIRPLANE HANDLING,
SERVICE & MAINTENANCE
(
TABLE OF CONTENTS
(
PAGE
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' Introduction .. ........ . .. ... . . ... . .......... '..... .
Identification Plate .. ...... . ............. . ......... .
Cessna Owner Advisories .. . .. .. . . .. . ... . ... . . . . . .. .
Publications ................. . ... . . . ' ..... . ... .
Airplane File . .. .... . ... . .. . ........ . ... . . . .. . ... .
Airplane Inspection Periods ... . .... .. ... . ... .. ...... .
FAA Required Inspections . .. .. . . .. .. . .. .... .. . ... .
Cessna Progressive Care ....... . ... . ........ . ... .
Cessna Customer Care Program .. ... . ........ . ... . .
CESCOM System ... .. .. . . ..... . ... . ... . . . ..... .
Engine Condition Trend Monitoring . . . . . ... . . •. . . ....
Pilot Conducted Preventive Maintenance ........ . .... .
Alterations Or Repairs .............. .. ... . ..... . .. .
Ground Handling .. .. .. . .. .. . . . . ... . . . .... . . . .... .
Towing ..... .... .. . .. . ..... . .. . .... . .... . ... .
Parking .. . ............. . ........ . ... :. : .... . .
Tie-Down ......... . .. . . . .... . .... . .... .. ... . .
Jacking .. .. . .... ... .. ... ' . .. .. ........ . ... ... .
L~v.eling ........... . . . ... . .................. .
Servicing . .. .. .. . . .. .... '. . . . . . . . . . . . . . . . . ... . . . .
Oil
. .. ..... .... . . . . .... . .. ... . . . . . . . . .. . . .
Fuel
. .. ... . .. . ..... . . ... . . . . . .. . . ... . . . . . . .
Landing ,Gear '. .... . . ... '. . .... . . . ..... ... . .... .
Oxygen .. . . , .. .. .. . .. . .... .... .. . .. . ... . .. . . .
Ground Deice/Anti-Ice Operations ..... . .. . .... . ... .
Cleaning And Care .. . .. . . . ... .. . .. . .. ........... .
Windshield-Windows .......... .... . . .. . . .. ... . . .
Painted Surfaces ..... . . . ... . ............ . ..... .
1 April 1998
8-3
8-4
8-4
8-5
8-6
8-6
8-6
8-7
8-8
8-8
8-8
8-9
8-10
8-10
8-10
8-11
8-11
8-12
8-14
8-14
8·15
8·18
8·23
8-24
8-24
8-38
8-38
8-40
8·1
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
TABLE OF CONTENTS (Continued)
PAGE
Stabilizer Abrasion Boot Care ...... . ........... .. .
Deice/Anti-Ice Boot Care . ....... .. ... . .. .. ...... .
Propeller Care ...... .................... ... ..... .
Engine Care . . ... . ............... . ... .. . . ...... .
Engine Exterior/Compartment Cleaning .......... . .. .
Engine Compressor Wash . . . . . .. .. .. . .. . ; . . . . ... .
Compressor Turbine Blade Wash . . . .......... . ... .
Interior Care .................. .. .......... '. . ... .
Prolonged Out-Ot-Service Care . .............. . ..... .
........ . ...... . .... .
Bulb Replacement During Flight
8-42 :,
8-43
8-:45
8-46
8-46
8-46
8-48
8-48
8-49
8-51
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1 April 1998
8-2
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
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INTRODUCTION
(
This section contains factory-recommended procedures for proper
ground handling and routine care and servicing of your Cessna. It
also identifies certain inspection and maintenance requirements
which must be followed if your airplane is to retain that new-plane
performance and dependability. It is wise to follow a planned
schedule of lubrication and preventive maintenance based on
climatic and flying conditions encountered in your locality.
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Keep in touch with your Cessna Service Station and take advantage
of his knowledge and experience. He knows your ,airplane and how
to maintain it. He will remind you when lubrications and oil changes
are necessary, and about other seasonal and periodic services.
A WARNING
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The airplane should be regularly ,Inspected and
maintained In accordance with Information found
In the airplane Maintenance Manual and In
company Issued Service Bulletins and Service
Newsletters. All recommendations for product
Improvements called for by Service Bulletins
should be accomplished and the airplane should
receive repetitive and required Inspections.
Cessna does not condone modifications,
whether by Supplemental Type Certificate or ·
otherwise, unless these certlf.lcates are held
and/orapproved by Cessna. Ottier modifications
may void warranties on the " airplane slnce ~
Cessna has no way of knowing the full effect on
the overall airplane. Operation of an airplane
that has been modified may be a risk to the
occupants, and operating procedures and
performance data set forth In the operating
handbook may no longer be considered accurate
for the modified airplane.
8-3
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
IDENTIFICATION PLATE
All correspondence regarding your airplane should include the .
SERIAL NUMBER. The Serial Number, Model Number, Production (
Certificate Number (PC) and Type Certificate Number (TC) can be '
found on the Identification Plate, located on the forward doorpost of
(
the left crew door on early serial airplanes or on the left side of the
tailcone below the horizontal stabilizer on later serial airplanes. A
(
Finish and Trim Plate is located on the forward doorpost of the left
crew door of all airplanes and contains a code describing the
interior color scheme and exterior paint combination of the airplane.
The code may be used in conjunction with an applicable Parts
Catalog if finish and trim information is needed.
CESSNA OWNER ADVISORIES
Cessna Owner Advisories are sent to Cessna Aircraft owners at no
charge ·to inform them about mandatory and/or beneficial aircraft
service requirements and product improvements:
United States Aircraft Owners
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If your aircraft is registered in the U.S., appropriate Cessna
Owner Advisories will be mailed to you automatically according
to the latest aircraft registration name and address provided to
the FAA.
If you require a duplicate Owner Advisory to be sent to an
address different from the FAA aircraft registration address,
please complete and return an Owner Advisory Application
(otherwise no action is required on your part).
International Aircraft Owners
To receive Cessna Owner Advisories, please complete and
return an Owner Advisory Application.
Receipt
Cessna
for U.S.
renewal
will
of a valid Owner Advisory Application
establish your
Owner AdviSOry service (duplicate Owner Advisory service .
aircraft owners) for one year, after which you will be sent a \;
notice.
1 April 1998
8-4
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
PUBLICATIONS
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Various publications and flight operation aids are furnished in the
airplane when delivered from the factory. These items are listed
below.
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CESCOM/CUSTOMER CARE PROGRAM HANDBOOK
PILOT'S OPERATING HANDBOOK AND FAA APPROVED
AIRPLANE
FLIGHT MANUAL
PILOT'S CHECKLISTS
CESSNA SALES AND SERVICE DIRECTORY
The following additional publications, plus many other supplies that
are applicable to your airplane, are available from your Cessna
Service Station.
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•
INFORMATION MANUAL (Contains Pilot's Operating
Handbook Information)
MAINTENANCE MANUALS and PARTS CATALOGS for your
airplane, engine, accessories, avionics and autopilot.
Your Cessna Service Station has a Customer Care Supplies and
Publications Catalog covering all available items, many of which he
keeps on hand. He will be happy to place an order for any item
which is not in stock.
NOTE
A Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual which is lost or destroyed may be replaced
by contacting your Cessna Service Station or Cessna
Product Support. An affidavit containing the"owner's name,
airplane sedal number and registration number must be
included in replacement requests since the Pilot's
Operating Handbook and FAA Approved Airplane Flight
Manual is identified for specific airplanes only
8·5
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
AIRPLANE FILE
A. To be displayed in the airplane at all times:
1. Aircraft Airworthiness Certificate (FAA Form 8100-2).
2. Aircraft Registration Certificate (FAA Form 8050-3) .
3. Aircraft Radio Station License, if transmitter installed (FCC
Form 556}.
B. To be carried intheairplane at all times:
1. Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual.
2. Weight and .Balance, and associated papers ·(latest copy of the
Repair and Alteration Form, FAA Form 337, if applicable).
.
3. Equipment List.
C. To be made available upon request:
1. Aircraft Maintenance Record.
2. Engine Maintenance Record.
3. Propeller Maintenance Record.
4. Avionics Maintenance Record.
Most of the items listed are required by .the United States Federal
Aviation Regulations. Since the Regulations of other nations may
require other documents and data, owners/operators of airplanes t
not registered in the United States should check with their own
aviation officials to determine their individual requirements.
Cessna recommends that these items, plus the Pilot's Checklists,
CESCOM/Customer Care Program Handbook and Customer Care
Card, be carried in the airplane at all times.
AIRPLANE INSPECTION PERIODS
FAA REQUIRED INSPECTIONS
As required by Federal Aviation Regulations, all civil aircraft of U.S .
registry must undergo a complete inspection (annual) each twelve
calendar months. In addition to the required ANNUAL inspection,
aircraft operated commercially (for hire) must · have a complete
inspection every 100 . hours of operation .
1 April 1998
8-6
For Training Purposes Only
(
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CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
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The FAA may require other inspections by the issuance of
airworthiness directives applicable to the airplane, engine, propeller
and components. It is the responsibility of the owner/operator to
ensure compliance with all applicable airworthiness directives and,
when the i~~pections are repetitive, to takEl appropriate steps to
',' ,
prevent inadvertent noncompliance.
In lieu of the 100 HOUR and ANNUAL inspection requirements, an
airplane may be inspected ' in accordance with a progressive
inspection schedule, which allows the work load to be divided into
smaller operations that can be accomplished in shorter time
periods.
.
The Cessna Progressive Care Program has been developed to
provide a modern progressive inspection schedule that satisfies the
complete airplane inspection requirements of both the 100 HOUR
and ANNUAL inspections as applicable to Cessna airplanes. The
program assists the owner/operator in his responsibility to comply
with all FAA inspection requirements, while ensuring timely
replacement of life-limited parts and adherence to factoryrecommended inspection intervals and maintenance procedures.
CESSNA PROGRESSIVE CARE
The Cessna Progressive Care Program has been designed to help
you realize maximum utilization of your airplane at a minimum cost
and downtime. Under this program, your airplane is inspected and
maintained in four operations. The four operations are recycled
each 400 hours and are recorded in a specially provided Aircraft
Inspection Log as each operation is conducted.
The Cessna Aircraft Company recommends Progressive Care for
airplanes that are being flown 400 hours or more per year, and the
1OO~hour inspection for all other airplanes. The procedures for the
Progressive Care Program and the 100-hour inspection have been
carefully worked out by the factory and are followed by the Ce9sna
Service Organization. The complete familiarity of Cessna Authorized
Caravan Service Stations with Cessna equipment and factoryapproved procedures provides the highest level of service for
Cessna ownersioperators.
8-7
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
Regardless of the inspection method selected by the
owner/operator, he should keep in mind that FAR Part 43 and FAR
Part 91 establishes the requirement that properly certified agencies
or personnel accomplish all .required FAA inspections and most of ,'
the manufacturer recommended inspections.
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CESSNA CUSTOMER CARE PROGRAM
Specific benefits and provisions of the Cessna Warranty plus other
importani benefits for you are contained in your CESCOM/Customer
Care Program Handbook supplied with your airplane. You will want
to thoroughly review your CESCOM/Customer Care Program
Handbook and keep it in your airplane at all times.
You will also want to contact your Service Station either at 100
hours for your first Progressive Care Operation, or for your first 100hour inspection depending on which program you choose to
establish for your airplane. While these important inspections will be
performed for you by any Cessna Caravan Service Station, in most
cases you will prefer to have the facility from whom the airplane was
purchased accomplish this work.
CESCOM SYSTEM
CESCOM is Cessna's Computerized Maintenance Records System.
This comprehensive system provides you with an accurate and
simple method of monitoring and scheduling inspections, Service
Bulletins, Service Kits, Airworthiness Directives as well as
scheduled and unscheduled maintenance activities. For detail
information about CESCOM, refer to the ' CESCOM Instruction
Manual supplied with your airplane.
ENGINE CONDITION TREND MONITORING
Pratt & Whitney Canada Inc. Engine Condition Trend Monitoring is a
system of recording engine instrument readings, correcting the
readings for ambient c(:>nditions, and comparing actual engine
operation to typical engine operating characteristics. It has been
established that engine operating characteristics, such as output .
torque (Tq), propeller RPM (Np) , interturbine temperature (ITT), gas i
generator RPM (Ng, and fuel flow (Wf) are predictable for various '<
engine types under specific ambient conditions.
1 April 1998
8-8
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAl NTENANCE
(
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Because aircraft engines operate at a wide range of altitudes, outside air temperatures, and airspeeds, corrections for varying ambient conditions are also incorporated into the Trend Monitoring process .
Additional information about both of these methods may be obtained
from the following sources:
• A Caravan Service Station.
• Cessna Propeller Aircraft Product Support.
(
• Pratt & Whitney Canada, Inc.
1000 Marie - Victorin, Longueuil, Quebec
Canada, J4G 1A 1
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Attention: Customer Support, Small Turboprops
Mail Code: 1RC1
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Tel: (514) 677-9411
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• The publication "Engine Condition Trend Monitoring and
Power Management for PT6A-114, PT6A-114A Installed in the
Cessna Caravan I" supplied in this Pilot's Operation
Handbook, or from.sources listed above.
•
Pratt & Whitney Canada Aircraft Gas Turbine Operation
Information Letter, No. 23.
PILOT CONDUCTED PREVENTIVE
MAINTENANCE
A certified pilot who owns or operates an airplane not used as an air
carrier is authorized by FAR Part 43 to perform limited maintenance
on his airplane. Refer to FAR Part 43 for a list of the specific
maintenance operations which are allowed.
NOTE
Pilots operating airplanes of other than U.S. registry should
refer to the regulations of the country of certification for
information on preventive maintenance that may be
performed by pilots.
8-9
1 April 1998
For Training Purposes Only .
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
A 208 Series Maintenance Manual should be obtained · prior to
performing any preventive maintenance to ensur~ that proper
procedures are followed. You Cessna Service Station should be
contacted for further information or for required maintenance which
must be accomplished by appropriately licensed personnel.
ALTERATIONS OR REPAIRS
GROUND HANDLING
TOWING
The airplane is most easily and safely maneuvered by hand with the
tow-bar attached to the nose wheel. The tow bar is stowed in Zone
6. Moving the airplane by hand will require that the individual
steering with the tow bar be assisted by personnel pushing at the I
wing struts.
\
CAUTION
. Do not push or pull the airplane using the
propeller blades or control surfaces.
In any towing operation, especially when towing with a vehicle, do
not exceed the nose gear turning angle of 56° either side of · center
as shown by the steering limit marks. If excess force is exerted
beyond the turning limit, a red over-travel indicator block (frangible
stop) will fracture and the block, attached to a cable, will fall into
view alongside the nose strut. This should be checked routinely
during preflight inspection to prevent operation with a damaged
nose gear.
1 April 1998
8-10
For Training Purposes Only
,(
{
It is essential that the FAA be contacted prior to any alterations on
, the airplane to ensure that airworthiness of the airplane is not
violated.
Alterations or repairs to the airplane must be
accomplished by licensed personnel.
A
{
(
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CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
(
A
(
CAUTION
Disengage rudder lock (If Installed) and remove
any external rudder locks beforetowing.
If the airplane is towed or pushed over a rough surface during
hangaring, watch that the normal cushioning action of the nose gear
does not cause excessive vertical movement of the tail and the
resulting contact with low hangar doors or structure. A flat nose tire
will also increase tail height.
(
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PARKING
(
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\,
When parking the airplane,head into the wind and set the parking
brakes. Do not set the ' parking brakes during cold weather when
accumulated moisture may freeze the brakes, or when the brakes
are overheated. ' Install the control wheel lock, engage the rudder
lock (if installed), and chock the wheels (if the brakes are not
utilized) to prevent airplane movement. In severe weather and high
wind , conditions, tie the airplane down as outlined in the following
paragraph.
A CAUTION
(
(
Any time the airplane Is loaded heavily, the
footprint pressure (pressure of the airplane
wheels upon the contact surface of the parking
area or runway) will be extremely high, and
surfaces such as hot asphalt or sod may not
adequately support the weight of the airplane.
precautions should be taken to avoid airplane
parking or movement on, such surfaces.
(
TIE-DOWN
Proper tie-down ' procedure is the best precaution against damage to
the parked airplane by gusty or strong winds. To tie-down the
airplane securely, proceed as follows:
1.
2.
Head the airplane into the wind, if possible.
Set the parking brake.
8-11
1 April 1998
For Training Purposes Oilly
. CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
&-MAINTENANCE
A CAUTION
Do not set the parking brake during cold weather
when accumulated moisture may freeze the
brakes or when the brakes are overheated. If the
brakes are not utilized, chock the nose and main
wheels to prevent airplane movement.
3.
4.
5.
6.
7.
8.
9.
10.
Install the control wheel lock and engage the rudder lock (if
installed).
Set aileron and elevator trim tabs to neutral position so that
tabs fair with control surfaces.
Install a pitot tube cover(s), if available.
Secure ropes or chains of sufficiently strong tensile strength
to the wing tie-down fittings and secure to ground anchors.
Attach a rope or chain to the tail tie-down, and secure to a
ground anchor.
If additional security is desired, attach a rope (no chains or
cables) to the nose gear torque link and secure to a ground
anchor.
If dusty conditions exist, or the last flight of the day has been (
completed, install the two engine inlet covers to protect the
engine from debris. The covers may be installed after the
engine has cooled down (ITT indicator showing "off . scale"
temperature).
To prevent the propeller from windmilling, install the
propeller anchor over a blade of the propeller and secure its
anchor strap around the nose gear or to the bracket located
on the lower right hand cowl.
JACKING
Several jack points or jacking locations are available. depending on
whether a cargo pod is installed. A fuselage jack point directly
below the firewall and housed within the nose gear strut fairing is
accessible for nose gear jacking regardless of the installation of a
cargo pod. Two additional fuselage jack points are located at the
main . gear supports, but are not accessible with the cargo pod
installed. Their use is generally reserved for maintenance such as
main gear removal or raising the entire airplane whenever the cargo
pod is not installed.
1 April 1998 .
8-12
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
(
SECTION 8
HANDLING, SERVICE
- & MAINTENANCE
(
Anytime the cargo pod is installed, if the main gear-to-fuselage
fairings ·are removed, jacks can be positioned adjacent to the sides
of the cargo pod and raised to engage the receptacle on the end of
the jacks over the head of the outboard bolt which secures the main
gear attach trunnion bearing cap (aft) on the left and right gear.
These jacking locations serve essentially the same purpose as the
fuselage jack paints ·at the main gear supports. An additional jack
point on each main gear axle fitting is used primarily when the
cargo pod is installed and it is desired to jack a single main gear for
tire replacement, etc. If desired, jack stands with wing jack pads
may be fabricated so that the front wing spar at stations 141.2 or
155.9 on each wing may be used as jacking locations. A tail jack
must be used in conjunction with wing jacking.
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A CAUTION
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• A . tall Jack stand must be used when
conducting . maintenance . Inside . the tail
section, and should be installed In most
Jacking operations. Be sure the stand Is
suitably heavy to keep the tail stable under all
conditions and Is strong enough to support
the airplane. Placing a Jack stand under the
nose jack point (if not used for Jacking) will
provide additional stability.
•
Do not use cargo pod structure for jacking or
as a blocking surface.
•
Raise the airplane no more than required for
the maIntenance being performed.
(
In some
rings for
Refer to
hoisting,
instances, it may be necessary to use a sling or hoisting
the initial lift, . to be followed with jacking at the jack points.
the Maintenance Manual for procedures on jacking and
and information concerning jacking equipment.
8-13
1 April 1998
For Training Purnoses Onlv
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
LEVELING
Longitudinal leveling of the ,airplane for weighing will require that .<'
the main landing gear be supported by stands. blocks, etc. on the \,
main gear scales to a position at least four inches higher than the
'nose gear as it rests on an appropriate scale. This initial. elevated
position will compensate for the difference in waterline station
between the main and nose gear so that final leveling can be
accomplished solely by deflating the nose gear tire.
.
NOTE
Since the nose gear strut on this airplane contains an oil
snubber for shock absorption rather than an air/oil shock
strut, it can not be deflated to aid in airplane leveling.
The airplane can also be leveled longitudinally by raising or
lowering the airplane at the jack points. Longitudinal leveling points
are provided by backing out the two leveling -screws located on the
left side of the fuselage just forward of the cargo doors. Place a
spirit level on the screws, then deflate the nose gear tire (if placed
on scales) or adjust the jacks to center the bubble in the level. The i
pilot's seat rails can also be used for longitudinal leveling by \
moving ,the seat to the most forward position and placing the level
on the rail just a1tof the seat. To level the airplane laterally, center
a spirit level across the seat rails aft of the pilot and right front
passenger seats and raise or lower one side of the airplane. Refer
to the 208 Series Maintenance Manual for a,dditional information.
SERVICING
In addition to the PREFLIGHT INSPECTION covered in Section 4,
COMPLETE servicing, inspection, and test requirements for your
airplane are detailed in the 208 Series Maintenance Manual. The
Maintenance Manual outlines all items which require attention at
100, 200, and 400 hour intervals plus those items which require
servicing, inspection, and/or testing at special intervals. Since
Cessna Service Stations have the training and equipment
necessary to conduct all service, inspection, and test procedures in
accordance with applicable Maintenance Manuals, it is ,, !
recommended that you contact your Cessna Service Station '" .,
concerning these requirements and begin scheduling your airplane
r
for service at the recommended intervals.
i
I
8-14
Revision 6
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
(
Cessna Progressive Care ensures that these requirements are accomplished at the required intervals to comply with the 100-hour or
ANNUAL inspection as previously covered.
(
Depending on various flight operations, your ' local Government
Aviation Agency may require additional service, inspections, or
tests. For these regulatory requirements, owners/operators should
check with local aviation officials where the airplane is being
operated.
(
(
(
For quick and ready reference, quantities, materials,
specifications for frequently used service items are as follows:
(
and
(
OIL
(
OIL GRADE (SPECIFICATION) --
(
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(
(
'-.....
.
.
(
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Oil conforming to Pratt & Whitney Engine Service Bulletin No.1 001 ,
and aU revisions or supplements thereto, must be used. The oils
listed below comply with the engine manufacturers specification
PWA521 and have a viscosity Type II rating. These oils are fully
approved for use in Pratt & Whitney Canada Inc. commercially
operated engines. When adding oil, service the engine with the type
and brand which is currently being used in the engine. Refer to the
airplane and engine maintenance records for this information.
Should oils of different viscosities or brands be inadvertently mixed,
the oil system servicing instructions in the Maintenance Manual
shall be carried out.
BP Turbo Oil 2380
c...
~
/
Exxon Turbo Oil ETO 85 (Third generation lubricant)
Aero Shell Turbine Oil 500
Aero Shell Turbine Oil 555
Aero Shell Turbine Oil 560 (Third generation lubricant)
Royco Turbine Oil 500
Royco Turbine Oil 555
Royco Turbine Oil 560 (Third generation lubricant)
Mobil Jet Oil II
Mobil Jet Oil 254 (Third generation lubricant)
Castrol 5000
Turbonycoil 600
I
I
8-15
Revision 6 ·
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
A
CAUTION
,
(
(
•
Do not mix brands or types of oils.
•
When changing from an existing lubricant
formulation to a 'third generation' lubricant
formulation (see ,list above), the engl'ne
manufacturer strongly recommends that such
a change should only be made when an
engine is new or freshly overhauled. For
additional Information on use of third
generation oils,
refer to the engine
manufacturer's pertinent oil service bulletins
(
NOTE
The oils listed above are recommended when operation will
result in frequent cold soaking at ambient temperatures of
O°F (-18°C). Refer to Pratt & Whitney Engine Service
B!Jlletin No.1 001 for additional oils which are approved.
If one or more of the following conditions exist, the accessory
gearbox scavenge pump inlet screen and any drained oil should be
inspected for the presence of carbon particles, per airplane and
engine maintenance manual procedures and the engine '
manufacturer's pertinent engine and oil service bulletins:
1.
Engine oil has been switched to a "third generation"
lubricant during mid-life.
2.
High oil consumption.
3.
Oil leaking from engine intake.
If carbon particles are found, refer to the above referenced
maintenance manuals and service bulletins for corrective action.
8-16
,1 April 1998
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
TOTAL OIL CAPACITY:
14 U.S. Quarts (including oil in filter, cooler and hoses).
DRAIN AND REFILL QUANTITY:
Approximately 9.5 U.S. Quarts.
OIL QUANTITY OPERATING RANGE:
Fill to within 1 1/2 quarts of MAX HOT or MAX COLD (as
appropriate) on dipstick. Quart markings indicate U.S. quarts
low if oil is hot. For example, a dipstick reading of 3 indicates
the system is within 2 quarts of MAX, if the oil is cold and within
3 quarts of MAX if the oil is hot.
j\WARNING
Ensure oil dipstick cap Is securely latched down.
Operating the engine with less than the
recommended 011 level and with the dipstick cap
unlatched will result In excessive 011 loss and
eventual engine stoppage.
NOTE
To obtain an accurate oil level reading, it is recommended
the oil level be checked either within 10 minutes after
engine shutdown while the oil is hot (MAX HOT marking) or
prior to the first flight of the day while the oil is cold (MAX
COLD marking). If more than 10 minutes has elapsed since
engine shutdown, and engine oil is still warm, perform an
engine dry motoring run before checking oil level.
OIL DRAIN PERIOD:
For engines operated in corporate or utility airplanes with a typical
utilization of 50 hours per month or less, it is recommended the oil
be changed every 400 hours or 12 months, whichever occurs first.
For engines operated in high utilization commuter airline type
operation, a basic oil drain period of 1200 hours or 12 months is
recommended. Regardless of the degree of utilization, if operating
in a sandy or dusty environment, the oil change interval must be at
least every 6 months.
8-17
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
FUEL
APPROVED FUEL GRADE (SPECIFICATION):
i
t,
Jet A (ASTM-D1655).
Jet A-1 (ASTM-D1655).
Jet B (ASTM-D1655).
JP- 1 (MIL-L-5616
JP-4 (MIL-T-5624).
JP-5 (MIL-T-5624).
JP-8 (MIL-T-83133A).
ALTERNATE/EMERGENCY FUEL:
Aviation Fuel (All grades of military and commercial aviation
gasoline).
A CAUTION
Aviation gasoline is restricted to emergency use
and shall not be used for more than 150 hours In
one overhaul period; A mixture of one part
aviation gasoline and three parts of Jet A, Jet A·
1, JP-1, OR JP-5 may be used for emergency
purposes fora maximum of 450 hours per
overhaul period.
CAPACITY EACH TANK:
167.8 U.S. Gallons
A
CAUTION
To obtain accurate fuel quantity Indicator
readings, verify the airplane Is parked in a
laterally level condition, or, If In flight, make sure
the airplane is In a coordinated and stabilized
condition (ball of turn-and-bank Indicator
centered).
1 April 1998
8-18
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
FUEL ADDITIVES :
A variety of fuels may be used in the airplane; however, each must
have an anti-icing additive, (EGME) or (DIEGME), incorporated orl
added to the fuel during refueling.
It is recommended that fuel anti-icing additive be used to control
bacteria and fungi. The anti-ice additives EGME/OIEGME have
shown, through service experience, that they provide acceptable
protection from microorganisms such as bacteria and fungi that can
rapidly multiply and cause serious ,corrosion in tanks and may block
filters , screens and fuel metering equipment.
A
CAUTION
•
JP-4 and JP-5 fuels per MIL-T-5624 and JP-8
fuel per MIL-T-83133A . contain the correct
premixed quantity otan approved type of
anti-Icing fuel additive and no additional antlIce compounds should be added.
•
Proper mixing of EGME or DIEGME
compound with the fuel Is extremely
important. A concentration In excess of that
recomr.nended (0.15 percent by volume
maximum) will result In detrimental effects to
the fuel tanks, such as deterioration .of
protective primer and sealants and damage
to o-rings and seals In the fuel system and
engine components. Use only blending
equipment that Is recommended by the
manufacturer to obtain proper proportioning.
'ROCEDURE FOR ADDING FUEL ANTI-ICING ADDITIVE
Vhen the airplane is being refueled, use the following procedure to
,lend anti-icing additive tonontreated fuel :
1.
Attach additive to refuel nozzle, making sure blender tube
discharges in the refueling stream.
8-19
evision 6
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
2. Start refueling while simultaneously fully depressing and slipping
ring over trigger of blender.
AWAANING
Anti-icing additives containing ethylene glycol
monomethyl ether (EGME) are harmful If Inhaled,
swallowed or absorbed through the skin, and will
cause eye. Irritation.
It Is also combustible.
Before using this material, refer to all safety
information ali the container.
A CAUTION
•
ether
Diethylene
glycol
monomethyl
(DIEGME) is slightly toxic if swallowed and
may cause eye redness, swelling and
irritation. It Is also combustible. Before
using this material, refer to all safety
information on the container.
•
Assure the additive is directed into the
flowing fuel stream with the additive flow
started after the fuel flow starts and stopped
before fuel flow stops. Do not allow
. concentrated additive to contact coated
Interior of fuel tank or airplane painted
sui1ace.
.
•
Use not less than 20 fluid ounces of additive
per 156 gallons of fuel or more than 20 fluid
ounces of additive per 104 gallons of fuel.
(
1 April 1998
8-20
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
PROCEDURE FOR CHECKING FUEL ADDITIVES
,r ~-'
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1.
Prolonged storage of the airplane will result in a water
buildup in the fuel which "leaches out" the additive. An
indication of this is when an excessive amount of water
accumulates in the fuel tank sumps. The concentration of
additive can be checked using an anti-icing additive
concentration test kit: For additional information about this
kit, refer to Chapter 12 of the 208 series maintenance
manual. It is imperative that the instructions for the test kit
be followed explicitly when checking the additive
concentration . The additive concentrations by volume for
EGME/OIEGME shall be 0.10 percent minimum and 0.15
percent maximum, either individually or mixed in a common
tank. Fuel, when added to the tank, should have a minimum
concentration of 0.10 percent by volume.
A CAUTION
(
(
(
( '.
':, .,.:
.
If the fuel additive concentration has fallen
below 0.035% by volume, the airplane should be
defueled and refueled.
(
(
If additional anti-static protection is desired, the following additive
is approved for use :
(
Dupont Stadis 450
A
I
I
CAUTION
These additives shall not exceed a maximum
concentration of 1 part per million by weight.
If additional biocidal protection is desired, an additive is permitted
for use in certain conditions. Fuel tank maintenance practices are of
prime importance in controlling microbial growth. However, other
factors such as climate, airplane design, route structure and
utilization also affect microbial growth; therefore, occasional use of
a biocide may be required.
8-21
Revision 6
For Trainine Purposes Only .
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
(
(
Biocide additive may be used on a limited .basis, defined as
intermittent or non-continuous use in a single application, to sterilize
airplane fuel systems suspected, or found to be contaminated by
microbial organisms. For those operators, where the need for
biocide use is dictated, Pratt & W/litney Canada Inc. recommends,
as a guide, a dosage interval ·ofonce a month. This interval can
then be adjusted, either greater or lesser, as an operator's own
experience dictates. An engine operated in private and corporate
airplanes, where utilization rates are relatively low, may use the
ladditive continuously. The following additives are permitted for use:
I
Sohio Biobor JF
Kathon FP 1.5
A CAUTION
I
AddItive shall not
exceed a maxImum
concentration of 270 parts per million by weight.
FUEL CONTAMINATION:
Fuel contamination is usually the result of foreign material present !
in the fuel system, and may consist of water, rust, sand, dirt,
microbes or bacterial growth. In addition, additives that are not
compatible with fuel or fuel system components can cause the fuel
to become contaminated.
Before each flight and after each refueling, use a clear sampler and
drain at least one sampler full of fuel from the inboard fuel tank
sump quiek-drain valves, fuel tank external sump quick-drain
valves, fuel reservoir quick-drain valve (actuated by a push-pull
drain control on cargo pod), and fuel filter quick-drain valve to
determine if contaminants are present, and that the airplane has
been fueled with the proper fuel . If the airplane is parked with one
wing low on a sloping ramp ·(as evidenced by the ball of the turn
and bank indicator displaced from center). draining of the outboard
fuel tank sump quick-drain valves (if installed) is also
recommended.
If contamination is detected, drain all fuel drain points again. Take t
repeated samples from aI/ fuel drain points until all contamination \
has been removed . If after repeated sampling, . evidence of
contamination still exists, the fuel tanks should be completely
drained and the fuel system cleaned.
Revision 6
8-22
For Training Purposes Only
(
.(
SECTION a
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
(
Do not fly the airplane with contaminated or unapproved fuel.
Anytime the filter bypass flag (red warning button) is found to be
extended, the filter element has become clogged. Disassemble the
filter, clean the element, and check the fuel system to determine the
cause of contamination before further flight.
(
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In addition, owners/operators who are not acquainted with a
particular fixed base operator should verify that the fuel supply has
been checked for contamination and is properly filtered before
allowing the airplane to be serviced. Also, fuel tanks should be kept
full between flights, provided weight and balance considerations will .
permit, to reduce the possibility of water condensing on the inside
walls of partially filled tanks.
(
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("0:
~'-.
To further reduce the possibility of contaminated fuel, routine
maintenance of the fuel system should be performed in accordance
with the airplane Maintenance Manual. Only the proper fuel, as
recommended in this handbook, should be used, and fuel additives
should not be used unless approved by Cessna and the Federal
Aviation Administration.
A WARNING
-
(
It is the pilot's. responsibility to ensure that the
airplane's fuel supply is clean before flight. Any
traces of solid contaminants such as rust, sand,
pebbles, dirt, microbes and bacterial growth or
liquid contamination resulting from water,
Improper fuel type, or additives that are not
compatible with the fuel or fuel system
components must be considered hazardous.
Carefully sample fuel from all fuel drain
locations during each preflight Inspection and
after every refueling.
LANDING GEAR
NOSE WHEEL TIRE PRESSURE:
53-63 PSI on 6.50, a-Ply Rated Tire . .
30-42 PSI on 22x8.00-8, 6-Ply Rated Tire.
8-23
1 April 1998
For Trainin~ Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
MAIN WHEEL TIRE PRESSURE;
(
83 PSI on 6.50-10, 8-Ply Rated Tires.
48"52 PSI on 8.50-10, 8-Ply Rated Tires.
35 PSI (minimum) on 29x11 .00-1 0, 10-Ply Rated Tires.
NOSE GEAR SHOCK STRUT;
Keep filled with MIL~H-5606 hydraulic fluid per filling instructions
placard. No air pressure is required in strut.
BRAKES:
Service brake fluid reservoir with MIL-H-5606 hydraulic fluid as
placarded on reservoir. As placarded on early serial airplanes, refill
reservoir to within three-quarters inch (3/4") of the .098 diameter
vent hole, whenever the fluid level drops to 1/2 full . . As placarded
on later serial airplanes , maintain fluid level between MIN and MAX
markings.
OXYGEN
AVIATOR'S BREATHING OXYGEN:
Spec. No. MIL-O-27210.
MAXIMUM PRESSURE (cylinder temperature stabilized after fitling):
1850 PSI at 21°C (70°F).
Refer to Oxygen Supplements (Section 9) for filling pressures.
GROUND DEICE!ANTI-ICE OPERATIONS
,
.
During cold weather operations, flight crews are responsible for
ensuring that the airplane is free of ice contamination. Type I deice,
and Type II or Type IV anti-ice fluids may be used sequentially to
ensure compliance with FAA regulations, which require that all
critical components (wings, control surfaces and engine inlets as an
example) be free of snow, ice, or frost before takeoff. The deicing f
process is intended to restore the airplane to a clean configuration ', '. ,
so that neither aerodynamic characteristics nor mechanical
interference from contaminants will occur.
1 April 1998
8-24
For Training Pu rposes Only
(
CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
A WARNING
Type II and Type IV anti-Ice fluid is designed for use on
airplanes with a VR speed of 85 knots or greater.
Whenever Type II or Type IV anti-ice fluid Is applied to the
airplane, the takeoff flap setting Is limited to 0° and the VR
Is 88 KCAS. Refer to Section 2 for limitations and Section
5 for takeoff distances with 0° flaps setting and liftoff
speeds in KIAS. The takeoff distance charts for 0° flaps
setting start with the airplane's maximum weight for
normal operations. However, when icing conditions exist,
the airplane should only be loaded to its maximum weight
for flight Into known Icing conditions.
NOTE
It is recoml1)ended that flight crews refamiliarize .themselves
seasonally with the following publications for expanded deice
and anti-ice procedures:
•
•
•
•
Cessna 208 Series Maintenance Manual Chapter 12.
FAA Advisory Circular AC135-17, dated 12-14-94, or later.
FAA Advisory Circular AC20-117, dated 12... 17-82, or later.
FAA Flight Standards Information Bulletin FSAT 01-09,
dated 10-05-01, or later.
I
Deicing and anti-icing fluidS are aqueous solutions which work by
lowering the freezing point of water in either the liquid or crystal
phase, thus delaying the onset of freezing. For this reason, they are
referred to as Freezing Point Depressant (FPD) fluids. Deicing fluid
is classified as Type I. Anti-icing fluid is classified as Type \I or
Type IV. Deicing and anti-icing with fluids may be performed as a
one-step or two-step process. The one-step deicing procedure
involves using Type I deice fluid to remove ice and slush from the
airplane prior to departure and to provide minimal anti-icing
protection, as provided in the Type I holdover timetable (refer to
FSAT 01-09, dated 10-05-01, or later). The two-step deice/anti-ice
procedure · involves applying Type II or Type IV anti-ice fluid to
ensure the airplane remains clean after deicing. Type 1/ or Type IV
fluid is used to provide longer -term anti-icing protection, as provided
in. the Type II, or Type IV holdover timetable (refer to FSAT 01-09'1
dated 10-05-01, or later). Type I, Type II, and Type IV fluids have
time limitations before refreezing begins, at which time additional
deicing is required.
I
8-25
Revision 6
For Training Purposes Only
CESSNA
MODEL208 (675 SHP)
SECTION 8
HANDLlNG,SERVICE
& MAINTENANCE
(
(
This time limitation is referred to as "holdover time". Because hold(
over time is highly dependent on a number of factors, charts can
provide only approximate estimates. Refer to FSAT 01-09, dated .' (
10-05-01, or later for Type I, Type II, and Type IV holdover times. It l. (
remains the responsibility of the pilot in command to determine the
effectiveness of any deicing or ami-icing procedure.
I
(
A CAUTION
(
Type I, Type"11 and Type IV fluids are not compatible
Additionally, most
and may not be mixed.
manufacturers prohibit the mixing of brands within
a type. Line personnel should be supervised by the
pilot In command to ensure proper application of .
Type I deice, and Type II and IV anti-Ice fluids (refer
to Figures 8-1 thru 8-4).
NOTE
Deicing fluids are ' not intended for use in removing .
snow deposits. Snow is best removed by mechanically
sweeping or brushing it from the airplane structure.
Use caution not to damage any airplane structure or
antennas when removing snow.
Deicing may be accomplished \Jsing the ambient temperature
available from a heated hangar or by mechanical means using a
A
glycol-based Freezing Point Depressant (FPD) Type I fluid.
heated hangar is an excellent option to deice airplanes and should
b,e utilized whenever possible. Care must be exercised however, to
ensure that all melted precipitation is removed from the airplane to
prevent refreezing once the airplane is moved from the hangar to
the flight line. Type I deicing fluids should be sprayed on the
airplane (with engine shutdown) in a manner which minimizes heat
loss of fluid to the air. The fluid should be applied in a temperature
range from 160°F to 180°F (71°C to 82°C) using a solid cone
pattern of large coarse droplets. Fluid should be sprayed as close
as possible 10 the ' airplane surfaces, but not closer than
approximately 10 feet if a high pressure nozzle is used.
8-26
Revision 6
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
& MAl NTENANCE
(
(
(
Application techniques for Type II and Type IV fluids are the same
as Type I, except that since the airplane is already clean, the
application should last only long enough to properly coat the
airplane surfaces. Type II or Type IV fluid should be applied
undiluted at ambient temperature to a "clean" airplane within three
minutes after deicing is completed, due to the limited holdover
times of Type I deice fluid. Type' II or Type IV fluid is however
sometimes heated and sprayed as a deicing fluid . For this case, it
should be considered a Type I fluid, as the heat may change the
characteristics of the thickening agents in the fluid. Type II or Type
IV fluid therefore, applied in this manner, will not be as effective as
it would be if it were applied at ambient temperature.
(
(
(
Refer to Figure 8-1 for areas to spray Type I deicing fluid, Figure 82 for areas to spray Type" and Type IV anti-icing fluid, Figure 8-3
for areas to avoid spraying directly, and Figure 8-4 for sequence of
application.
Heated solutions of FPD are , more effective than
unheated solutions because thermal energy is used to melt the ice,
snow, or frost formations. Type ' I deicing fluids are used in the
diluted state, with specific ratios of fluid-to-water dependent on
ambient temperature. Type I deicing fluids have a very limited
holdover time (refer to FSAT 01-09, dated 10-05-01, OJ later).
A
(
I
CAUTION
Type ,I fluids should never be used full strength
(undiluted).
Undiluted glycol fluid is quite
viscous below 14°F (-10°C) and can actually
produce 11ft reductions of about 20 percent.
Additionally, undiluted glycol has 8 higher
freezing point than 8 glycol/water mixture.
(
8-27
Revision 6
For Trainin~ Purposes Only
SECTIONS
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
. NOTE
•
Deicing and anti-icing procedures must be closely
coordinated between the pilot in command and ground
crews, and carried out in a timely manner. Ultimate
responsibility for safety of flight rests with the pilot in
command, and any decisions to deice or anti-ice an
airplane must be accomplished under his or her direct
supervision.
• The first area to be deiced and anti-iced should be
visible ·from the cockpit and should be used to provide
a conservative
estimate
for
subsequent
ice
accumulations on unseen areas of the airplane before
initiating takeoff.
• Due to the weight and C.G. changes which occur while
deicing the airplane, a tail stand should be placed under the tail to prevent the airplane from tipping on its
tail.
HOLDOVER TIMETABLE (TYPE I, TYPE II, AND TYPE IV FLUIDS)
NOTE
Refer to FAA Flight Standards Information Bu"etin
FSAT 01-09, dated 10-05-01", or later, for holdover
timetables.
I
The length of time that deicing and anti-icing fluids remain effective
. is known as "holdover time". The holdover timetables for Type I
deicing, and Type II or Type IV anti-iCing fluids are only an
estimation and vary depending on many factors, such as
temperature, precipitation type, wind and aircraft skin temperature.
Holdover times are based on the mixture ratio appropriate for the
OAT. Holdover times start when the last application has begun.
(
.
Guidelines for maximum holdover times anticipated by SAE Type I, /
Type II, or Type IV, and ISO Type I, Type II or Type IV fluid mixtures '\" .(
are a function of weather conditions and outside air temperature
(
(OAT).
Revision 6
For Training Purposes Only
.
(
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
A CAUTION
•
Aircraft operators are solely responsible for
ensuring that holdover timetables contain
current data.
•
The tables are for use In departure planning
only and should be used In conjunction with
pretakeoff contamination check procedures.
•
The time of protectIon will be shortened In
heavy weather conditions.
High wind
velocity and jet blast may cause a
degradation of the protective film. If these
conditions occur, the time of protection may
be shortened considerably. This Is also the
case when fuel temperature Is significantly
lower than OAT.
(
(
(
f
(
{
(
(
\,,,,
.'
NOTE
• Holdover timetables in FSAT 01-09, dated 10-05-01, or
later, do not apply to other than SAE or ISO Type I, Type
" or Type IV fluids.
I
• The responsibility for the application of this data remains
with the user.
A WARNING
(
When ground Icing conditions are present, a
pretakeoff contamination check should be conducted by the pilot in command within 5 minutes
of takeoff, preferably just prior to taxiing onto
the active runway. Critical areas of the airplane
such as empennage, wings, windshield, control
surfaces, and engine Inlets should be checked
to ensure they are free ' of Ice, slush, and snow
and that the deice or anti-Ice fluid is stili protectIng the airplane.
Revision 6
8-29
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
CESSNA
MODEL 208 (675 SHP)
(
TYPE I DEICE FLUID
I
(
NOTE
•
Freezing point of Type I fluid mixture must be at least
10°C (18°F) below OAT.
•
Holdover time starts when last application has begun.
•
Type I fluid should be sprayed on the airplane (with
engine off) in a manner which minimizes heat loss to
the air. If possible, fluid should be sprayed in a solid
cone pattern of large coarse droplets at a temperature
of 160°F to 180°F. The fluid should be sprayed as
close as possible to the airplane surfaces, but not
closer than 10 feet if a high pressure nozzle is used.
(
(
(
(
A WARNING
When ground icing conditions are present, a
pretakeoff contamination check should be
conducted by the pilot In command within 5
minutes of takeoff, preferably just prior to taxiing
onto the active runway. Critical areas of the
airplane such as empennage, wings, windshield,
control surfaces, and engine inlets should be'
checked to ensure they are free .of ice, slush,
and snow and that the deice or anti-ice fluid Is
still protecting the airplane.
f
\
(
(
(
(
I ..
!
8 March 1999
8-30
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
TYPE" ANTI-ICE FLUID
(
(
NOTE
( II
I
• Freezing point of Type II fluid mixture must be at least
1O°C (18°F) below OAT.
• Holdover time starts when last application has begun.
(
• Application techniques for Type II fluid are the same as for
Type I, except that since the airplane is already clean, the
application should last only long enough to properly coat
the airplane surfaces.
(
(
(
(
(
(
(
(
(":,~.
• Type II fluid should be applied undiluted at ambhmt temperature to a "clean" airplane within three minutes after
deicing is completed, due to the limited holdover times of
Type I deice fluid. Type II fluid is however, sometimes
heated and sprayed as a deicing fluid. For this case, it
should be considered a Type I fluid, as the heat may
change the characteristics of the thickening agents in the
fluid. Type II fluid therefore, applied in this manner, will
not be as effective as it would be if it were applied at am:
bient temperature.
<'
(
(
(
(
(
8-31
8 March 1999
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
(
(
(
,A WARNING
When ground icing conditions are present, a pre-takeoff
.contamination check should be conducted by the pilot in
command within 5 mlniJtes of takeoff, preferably just prior to taxiing onto the actlv.e runway. Critical areas of the
airplane such as empennage, wings, windshield, control
surfaces, and engine Inlets should be checked to ensure
they are free of Ice, slush, and snow and that the deice or
anti-ice fluid Is stili protecting the airplane.
TYPE IV ANTI-ICE FLUID
I
A
CAUTION
The time of protectlon .wlll be shortened In heavy weather
conditions.
Heavy precipitation rates, high . moisture
. content, high wind velocity, or jet blast may reduce
holdover time below the lowest time stated in the range.
Holdover time may be reduced when aircraft skin
temperature is lower than OAT.
NOTE
•
Freezing point of Type IV fluid mixture must be at least
1Q°C (18°F) below OAT.
•
Holdover time starts when last application has begun.
•
Application techniques for Type IV fluid are the same
as for Type I, except that since the airplane is already
clean, the application should last only long enough to
properly coat the airplane surfaces.
. 8-32
8 March 1999
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
CESSNA
MODEL 208 (675 SHP)
(
& MAINTENANCE
(
NOTE
Type IV fluid should be applied undiluted at ambient
temperature ·to a "clean" airplane within three minutes
after deicing is completed, due to the limited holdover
times of Type I deice fluid. Type IV fluid is however,
sometimes heated and sprayed as a deicing fluid. For
this case, it should be considered a Type I fluid, as the
heat may change the characteristics of the thickening
agents in the fluid . Type IV fluid therefore, applied in
this manner, will not be as effective as it would be if it
were applied at ambient temperature.
.
.
(
(
(
(
I
(
A
(
•
Some Type IV fluids could form a thick or
high strength gel during "dry-out" and when
rehydrated form a slippery film.
•
Some Type IV fluid exhibit poor aerodynamic
elimination (flow-off) qualities at colder
temperatu res.
•
Heated areas of aircraft (I.e.; heated leading
edge) should be avoided due to the fact that
fluid may "dry-out" Into hard globu lar
nodules.
•
Type IV fluid should not be used undiluted
below -24DC (-11°F).
(
(
(:
CAUTION
(
/
/
8-33
8 March 1999
'For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
(NOTE 1)
(
!
(
(
(
(
NOTE 1:
GIVE SPECIAL ATTENTION TO THE GAPS
BETWEEN THE FLIGHT CONTROLS.
ALL
SNOW, ICE AND SLUSH MUST BE REMOVED
FROM THESE GAPS.
(
(
(
NOTE 2:
REMOVE SNOW, ICE AND SLUSH FROM PITOT
TUBES BY HAND ONLY.
SHADED AREAS INDICATE ESSENTIAL
AREAS TO BE DEICED.
DIRECT SPRAY
AVOIDANCE AREAS:
I
ENGINE INLETS AND EXHAUST, BRAKES,
PITOT STATIC TUBES, WINDSHIELDS, CABIN
WINDOWS, AND STALL WARNING VANE.
2685X1D35
Figure 8-1 . Essential Areas to be Deiced
8-34
8 March 1999
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
(
(
(
(
. ...
\
(
(
(
(
(
(
(
r
<-
- ..
"
,
NOTE: .ANTI-ICE FLUID SHOULD BE APPLIED AT LOW
PRESSURE TO FORM A THIN FILM ON
SURFACES.
FLUID SHOULD JUST COVER
AIRPLANE WITHOUT RUNOFF.
{
(
(
SHADED AREAS INDICATE ESSENTIAL AREAS
WHERE ANTI-ICE FLUID IS APPLIED.
(
(
(
(
DIRECT SPRAY
AVOIDANCE AREAS:
(
PITOT STATIC TUBES, WINDSHIELDS,
CABIN WINDOWS, AND STALL WARNING
VANE.
{~.j
2685X1035
Figure 8-2 . Essential Areas to Apply Anti-ice Fluid
I
8-35
8 March 1999
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 'SHP)
,(
(
(
(
WINDOWS
(
(
(
PITOT -STATIC .
TUBE
(
(
(
(
PITOT-STATIC
TUBE
ENG INE INLETS
AND EXHAUST
(
(
STALL
WARNING
VANE
(
(
(
(
(
DIRECT SPRAY
AVOIDANCE AREAS:
(
ENGINE INLETS AND EXHAUST, BRAKES,
PITOT ST ATle TUBES, WINDSHIELDS, CABIN
WINDOWS,AND STALL WARNING VANE.
(
(
(
26851035
I Figure 8-3.
\
(
\ ...: , :..:.-,..
(
Deice and Anti-ice Fluid Direct Spray Avoidance Areas
(
.(
8 March 1999
8-36
For Training Purposes Only
(
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
(
(
(
(
(
(
(
(
NOTE: BY STARTING DEICE AND ANTI-ICE APPLICATION
AT THE LEFT FRONT AREA OF THE AIRPLANE, THE
PILOT CAN GET A CONSERVATIVE ESTIMATE OF
ICE REFORMATION FROM INSIDE THE COCKPIT.
SINCE THIS WAS THE FIRST AREA DEICED OR
ANTI-ICED, IT WILL BE THE FIRST AREA WHERE
ICE WILL REFORM .
(
(
(
(
(
(
(
(
(
I'
START
26851035
Figure 8-4. Deicing and Anti-icing Application
8 March 1999
I
8-37
For Training Purposes Only
SECTION 8
HANDLING. SERVICE
& MAINTENANCE
Ct:::;t>NA
MODEL 208 (675 SHP)
CLEANING"AND CARE
WINDSHIELD-WINDOWS
The windshield and windows are constructed of cast acrylic. The
surface hardness of acrylic is approximately equal to that of copper
or brass. Do not use a canvas cover on the windshield unless
freezing rain or sleet is anticipated. Canvas covers may scratch the
plastic surface. When cleaning and "waxing the windshield and
windows. use only the following prescribed methods and materials
I(see Figure 8-5).
.
WINDSHIELD AND WINDOW MAINTENANCE PROCEDURES
The fol/owing procedures provide the most current information
regarding cleaning and servicing windshields and . windows.
Improper cleaning. or use of unapproved cleaning agents, can
cause .damage to these surfaces.
CLEANING INSTRUCTIONS
A
CAUTION
Windshields and windows can be easily damaged by
improper handling and cleaning techniques.
1.
2.
3.
4.
5.
Place airplane inside hangar or in shaded area and allow to
cool from heat of sun's direct rays.
Using clean (preferably running) water, flood the surface.
Use bare hands with no jewelry to feel and dislodge any dirt
or abrasive materials.
Using a mild soap or detergent (such as a dishwashing
liquid) in water, wash the surface. Again, use only the bare
hand to provide rubbing force. (A clean cloth may be used to
transfer the soap solution to the surface, but extreme care
must be exercised to prevent scratching the surface.)
On acrylic windshields and windows, if sails which cannot
be removed by a mild detergent remain, Type " aliphatic
naphtha, applied with a soft clean cloth, may be used as a
cleaning solvent. Be sure to frequently refold the cloth to
avoid redepositing soil and/or scratching the windshield and[
windows with any abrasive particles.
Rinse surface thoroughly with clean fresh water and dry with (
a clean cloth.
(
8-38
8 March 1999
For T raining Pu rposes Only
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
(
A CAUTION
(
"".,..~-
(
-,
~
Do not use any of the following on, or for
cleaning, windshields and windows: methanol,
denatured alcohol, gasoline, benzene, xylene,
MEK, acetone, carbon tetrachloride, lacquer
thinners, commercial or household window
. cleaning sprays.
When In doubt about 'any
product, do not use It.
(
(
(
(
6.
(
(
(
7.
(
(
(
(
A
( -"':;
.
Hard polishing wax should be applied to acrylic surfaces.
(The ..wax has an index of refraction nearly the same as
transparent acrylic and wi" tend to mask any shallow
scratches.
Acrylic surfaces may be polished using a polish meeting
Federal
Specification
P-P-560
applied
per
the
manufacturer's instructions.
CAUTION
On acrylic surfaces, use only rain repellents
which conform to specification MIL-W-6882.
Refer to Figure 8-5 for specific rain repellent
products approved by Cessna.
" . ,'
(
(
I
NOTE
(
When. applying or removing wax or polish, use a clean soft
cloth.
(
(
(
(
8.
Windshields may have rain repellent applied per the
manufacturer's instructions. Caution should be used not to
get rain repellent on painted surfaces surrounding the
windshield.
(
(
~ ()
8-39
8 March 1999
For Tr~illing Purpos~s Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
WINDSHIELD AND WINDOW PREVENTIVE MAINTENANCE
A
CAUTION
Utilization of the following techniques will help
minimize windshield and window crazing.
1.
2.
3.
4.
5.
6.
Keep all surfaces of windshields and windows clean.
If desired, wax acrylic surfaces.
Carefully cover all surfaces during any painting, powerplant
cleaning or other procedure that calls for the LIse of any type
of solvents or chemicals.
The following coatings are
approved for use in protecting surfaces from solvent attack:
a. White Spray Lab, MIL-C-6799, Type I, Class II.
b. WPL-3 Masking Paper - St. Regis, Newton, MA.
c. 5 X N - Poly-Spotstick - St. Regis, Newton, MA.
d. Protex 40 - Mask Off Company, Monrovia, CA and
Southwest Paper Co., Wichita, KS.
e. Protex 10VS - Mask Off Company, Monrovia, CA and
Southwest Paper Co., Wichita, KS
.
f. Scotch 344 Black Tape - 3M Company
Do not park or store the airplane where it might be . . (
subjected to direct contact with or vapors from: methanol, (
denatured alcohol, gasoline, . benzene, xylene, MEK,
acetone, carbon tetrachloride, lacquer thinners, commercial
or household window cleaning sprays, paint strippers, or
other types of solvents.
Do not use solar screens or shields installed on inside of
airplane or leave sunvisors up against windshield. The
reflected
heat ·from these items causes elevated
temperatures which accelerate crazing . .
Do not use power drill motor or .powered device to clean,
polish or wax surfaces.
PAINTED SURFACES
The painted exterior surfaces of your new Cessna have a durable,
long lasting finish. Approximately 10 days are required for the paint
to cure completely; in most cases, the curing period will have been
completed prior to delivery of the airplane. In the event that
polishing or buffing is required within the curing period, it is
recommended that the work be done by someone experienced in
handling uncur~d paint.
Any Cessna Service Station can
accomplish this work.
1 April 1998
8-40
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
(
Materials Required For Acrylic Windshields and Windows
(
MATERIAL
( i,/
(
(
(
(
(
(
(
(
"
t'~
\ "'-. ",.
USE
Mild soap or detergent
(hand dishwashing type
without abrasives)
Commercially available
Cleaning windshields and
windows.
Aliphatic naphtha Type II
conforming to Federal
Specification TT-N-95
Commercially available
Removing deposits which
cannot be removed with
mild soap solution on
acrylic windshields and
windows.
Waxing acrylic windshields and windows.
Polishing wax:
(Refer to Note 1)
(
(
MANUFACTURER
Turtle Wax (paste)
Turtle Wax, Inc.
Chicago, IL 60638
Great Reflections
Paste Wax
E.!. duPont de Nemours
and Co., (Inc.)
Wilmington, DE 19898
Slip-stream Wax
(paste)
Acrylic polish
conforming to Federal
Specification P-P-560
such as:
Permatex plastic
cleaner Number 4030
Mirror Glaze
MGH-17
Soft cloth, such as:
Colton flannel or cotton
terry cloth material
Rain repellent conforming
to Federal Specification
MIL-W-6882, such as:
REPCON
(Refer to Note 2)
Classic Chemical
Grand Prairie, TX 75050
Cleaning and polishing
acrylic windshields and
windows.
Permatex Company, Inc.
Kansas City, KS 66115
Mirror Bright Polish Co.
Pasadena, CA
Commercially available
Applying and removing
wax and polish.
Rain shedding
on acrylic windshields.
UNELKO Corp.
7428 E. Karen Dr.
Scottsdale, AZ 85260
NOTE 1:
These are the only polishing waxes tested and approved for use
by Cessna Aircraft Company.
NOTE 2:
This is the only rain repellent approved for use by Cessna Aircraft
Company for use on Cessna Model 208 series airplanes.
Figure 8-5. Materials For Acrylic Windshields and Windows
8 March 1999
I
8-41
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
Generally, the painted surfaces can be kept bright by washing with
water and mild soap, followed by a rinse with water and drying with
cloths or a chamois. Harsh or abrasive soaps or detergents which
cause corrosion or scratches should never be used. Remove
.stubborn oil and grease with · a cloth moistened with Stoddard t,
solvent.
.
i
.
To seal any minor surface chips or scratches and protect against
corrosion, the airplane should be waxed regularly. with a good
automotive wax applied in accordance with the manufacturer's
instructions. If the airplane is operated in a seacoast or other salt
water environment, it must be washed and waxed more frequently to
assure adequate protection. Special care should be taken to seal
around rivet heads and skin . laps, which are the areas mO,st
susceptible to corrosion . A heavier coating of wax on the leading
edges of the wings and tail and on the cowl nose cap and propel/er
spinner will help reduce the abrasion encountered in these areas.
Reapplication of wax will generally be necessary after cleaning with
soap solutions or after chemical deiCing operations.
When the airplane is parked outside in cold climates and it is
necessary to remove ice before flight, care should be taken to ,
protect the painted surfaces du ring ice removal with chemical \,
liquids. Isopropyl alcohol will satisfactorily remove ice accumulations
without damaging the paint. However, keep the isopropyl alcohol
away from the windshield and cabin windows since it will attack the
plastic and may cause it to craze.
STABILIZER ABRASION BOOT CARE
If the airplane is equipped with stabilizer abrasion boots, keep them
clean and free from oil and grease which can swell the rubber.
Wash them with mild soap and water, using Form Tech AC cleaner
or naphtha to remove stubborn grease. Do not scrub the boots, and
be sure to wipe off all solvent before it dries. Boots with loosened
edges or small tears should be repaired. Your Cessna Service
Station has the proper material and knowledge how to do this
correctly.
.
1 April 1998
8-42
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
DEICE/ANTI-ICE BOOT CARE
(
(
<"",--' .'"
(
{
,
\
The wing, wing strut and stabilizer deice boots are electricallyconductive through all plies and the edge sealer to bleed off static
charges which cause radio interference and may perforate the
boots.
Fueling and other servicing operations should be done
carefully to avoid damaging or tearing the boots.
To prolong the life of deice boots, they should be washed and
serviced on a regular basis. Keep the boots clean and free from oil,
grease and other solvents which cause rubber to swell and
deteriorate. Outlined below are recommended cleaning and
servicing procedures.
(
(
A CAUTION
(
Use only the following
cleaning boots. Disregard
recommend petroleum base
leaded gasoline, etc.) which
material.
(
(
(
(
(1.
(
Instructions when
Instructions whIch
liquids (MEK, noncan harm the boot
Clean boots with mild soap and water, then rinse thoroughly
. with clean water.
(
A CAUTION
(
(
Temperature of water for cleaning de-Ice/antl-Ice
boots shall not exceed 140°F.
(
NOTE
Isopropyl alcohol or toluene can be used to remove grime
which can not be' removed using soap. If isopropyl alcohol
or toluene is used for cleaning, wash area with mild soap
and water, then rinse thoroughly with clean water.
(~-'!!
~.iY"
2.
Allow the boots to dry, then apply a coating of Age Master
No. 1 to the boots in accordance with application
instructions on the container.
8-43
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
A
CAUTION
Do not apply Age Master No. 1 to boots treated
with BFG Resurfacing Kit 74-451-L.
NOTE
Age Master No. 1 is beneficial for its ozone and weather
resistance features.
3.
After the boots have been treated with Age Master No. 1
apply a coating of ICEX II to the boots in accordance with
application instructions on the ICEX IIcontainer.
J
NOTE
ICEX 1/ may be beneficial as an ice adhesion
depressant. 80th Age Master No. 1 and ICEX II are
distributed by the BFGoodrich Company.
A
CAUTION
(
ICEX II contains Silicone, which lessens paint
,adhesion. Use care when applying ICEX II, and
protect adjacent surfaces from overspray, since
overspray of ICEX U will make touch-up painting
almost Impossible.
Age Master No. 1 and ICEX II coatings last approximately 50 hours
on the wing and stabilizer de-ice boots and 150 hours on propeller
anti-ice boots.
Small tears and abrasions on pneumatic de-ice boots can be
repaired temporarily without removing the boots and the conductive
edge sealer can be renewed. Your Cessna Service Station ,has the
proper materials and knowledge how to do this correctly. '
(
f(
'",,;(
1 April 1998
8-44
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 8
SERVICE
& MAINTENANCE
~ANDL1NG,
(
(
(
(
PROPELLER CARE
"
Always conduct a 'preflight inspection and occasionally wipe the
blades i with a cloth dampened with oil to clean off grass and bug
stains, minimize corrosion and assure a longer blade life. Waxing
the blades with an automotive type paste wax on a regular basis will
further minimize corrosion. Damaged or blistered paint should be
repainted. During the preflight inspection, check the blades for
nicks, gouges, scratches, corrosion pits, etc., the anti-ice boots for
security, the propeller hub for evidence of grease and oil leaks, and
the propeller spinner for condition and security.
(
(
(
Repair of small nicks and scratches may be performed by qualified
mechanics in accordance with procedures specified in FAA Advisory
Circular 43.13-1 A. However, whenever a significant amount of
metal 'is removed, or in the case of previously reworked blades
which may be at or near minimum width and thickness limits, the
appropriate McCauley Service Manual should be consulted to
determine if minimum allowable blade width and thickness limits
If these limits are exceeded, blade
have been exceeded.
replacem~nt is required . After filing and polishing, the damaged
area should be inspected by the dye penetrant method to verify that
all damage has been removed and the blade is not cracked. The
area should then be reprotected by localized application of chemical
film per MIL-C-5541 (e.g. Alodine) and repainted as necessary.
Large nicks or scratches or other damage involving such things as
bent blades, balance, diameter reduction, etc. should be corrected
by an FAA approved propeller repair station.
(
(
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.\
,c'
(
(
(
(
(
(
(
"
&~
8-45
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
ENGINE CARE
ENGINE EXTERIOR/COMPARTMENT CLEANING
The engine exterior and compartment may be cleaned, using a
suitable solvent. Most efficient cleaning is done using a spray-type
cleaner. Before spray cleaning, ensure that protection is afforded for
components which might be adversely ,affected by the solvent. Refer
to the · Maintenance Manual for proper lubrication · of controls and
components after erigine cleaning.
ENGINE COMPRESSOR WASH
The benefits of performance improvements and . increased service
life of hot section parts accruing from instituting a regular ·
A
compressor wash program cannot be overemphasized.
compressor wash ring is installed · on the top of the engine adjacent
to the induction air inlet screen to facilitate this maintenance
program.
Compressor washes can be performed by either motoring the {
engine with the starter or running the engine. Depending on the
nature of the operating environment and the type of deposits in the
engine gas path. either of the two wash methods can be used to
remove salt or dirt and other baked on depOSits which accumulate
over a period of time and cause engine performance deterioration.
When the wash is performed solely to remove salt deposits, it is
known as a "desalination" wash.
1 April 1998 .
8-46
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
(
(
(
(
(
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(
\
A wash performed to remove baked on deposits to improve engine
. performance is known as a "performance recovery" wash. A
motoring wash is conducted at a gas generator RPM of 14-25%; the
running wash is carried out at an Ng of approximately 60% (23,000
RPM). The water or cleaning mixture and rinsing solution.
dependent on ambient temperature, is injected at different pressure,
depending on the wash method being conducted.
Operating environment determines the nature of the wash, the
frequency, and wash method recommended. If operating in a
continuously salt laden environment, a desalination wash, is
recommended following the last flight of the day by means of the
laden environments may
motoring method. Occasionally salt
necessitate a desalination wash each week using the motoring
method. Less severe and more general oper~ting environments are
not as conducive to rapid deposit buildup but eventually can
contribute to performance deterioration and necessitate a
performance recovery wash at intervals of 100-200 hours. In these
general environments, a motoring wash is recommended for light
soil and multiple motoring or a running wash is suggested for heavy
soil.
& CAUTION
(
(
(
SECTION 8
HANDLING. SERVICE
& MAINTENANCE
Always observe engine starting cycle limits
when conducting motoring wash procedures.
A number of cleaning agents are recommended for addition to water
to form the cleaning solution used for compressor wash. The
mixture proportion of all the cleaning agents is not identical,
however. Depending on the prevalent ambient temperature, aviation
kerosene and methanol must be added to the c,leaning solution in
various proportions. The quality of ·the water used is also important;
any drinking quality water is permissible for a motoring wash, but
demineralized water only is recommended for a running wash.
Detailed information concerning the cleaning mixture components.
mixture formulation, recommended quantity and application
equipment can be found in Pratt & Whitney Aircraft Gas Turbine
Operation Information Letter No.7.
8-47
1 April 1998
For Tr~ining Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
COMPRESSOR TURBINE BLADE WASH
Pratt & Whitney Canada Inc. has developed a procedure for
performing a compressor turbine blade motoring wash. This
technique will facilitate the removal of . contaminants from the :
compressor turbine blade airfoil surfaces, thereby minimizing
sulphidation attack of these surfaces. This serves as an aid for
obtaining optimum blade service life. With this method, a water or
water/methanol solution is injected directly into the combustion
chamber by way of a special spray tube which is installed in one of
the igniter plug ports. This method. of engine wash does not replace
the need for a normal engine compressor wash for performance
recovery or desalination purposes.
Compressor turbine blade washing is accomplished using water of
drinking quality (potable) only at ambient temperatures of +2°C
(36°F) and above. Use a water/methanol solution at ambient
temperatures below + 2°C (36 OF). Consult the Engine
Maintenance Manual for solution strength according to ambient
temperature and review Special Instruction P & WC: 4-84 for
washing procedures and limitations.
INTERIOR CARE
The instrument panel, control wheel, and control knobs need only
be wiped off with a damp cloth. Oil and grease on the control wheel
and control knobs can be removed with a cl01h moistened with
Stoddard solvent. Volatile solvents, such as mentioned in
paragraphs on care of the windshield, must never be used since
they soften and craze the plastic.
The plastiC trim, headliner, door panels, and floor covering in the
crew area of both versions and the rear cabin headliner and
sidewalls of the Passenger Version need only be wiped off with a
damp cloth. In Cargo VerSions, the sidewalls, cargo doors, and
overhead in the cargo area are not easily soiled or stained. Dust
and · loose dirt should be picked up with a vacuum cleaner.
Stubborn dirt can be wiped off with a cloth moistened in clean
water. Mild soap suds, used sparingly, will remove grease. The
soap should be removed with a clean damp cloth.
1 April 1998
8-48
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
The protective plywood floor . panels (if installed) and aft bulkhead
covering in the cargo area should be vacuum cleaned to remove
dust and dirt. A cloth moistened with water will aid in removing
heavy soil. Do not use excessive amounts of water which would
deteriorate the protective floor panels.
(
To remove dust and loose dirt from seating upholstery,clean the
seats regularly with a vacuum cleaner.
Blot up any spilled liquid on the seats promptly with cleansing tissue
or rags.
Don't pat the spot;. press the blotting material firmly ' and
hold it for several seconds. Continue blotting until no more liquid is
taken up. Scrape off 'sticky materials with a dull knife, then spot.
clean the area.
(
(
Oily spots on the seats may be cleaned with household spot
removers, L!sed sparingly.
Before using any solvent, read the
instructions on the container and test it on an obscure place on the
fabric to be cleaned. Never saturate the fabric with a volatile
solvent; it may damage the padding and backing materials.
(
(
(
(~-,)
Soiled seating upholstery may be cleaned with foam type detergent,
used according to the manufacturer's instructions. To minimize
wetting the fabric, keep the foam as dryas possible and remove it
with a vacuum cleaner.
PROLONGED OUT-Of-SERVICE CARE
(
{
(
(
Prolonged out-of-service care applies to all airplanes which will not
be flown for an indefinite period (less than 60 days) but which are to
be kept ready to fly with the least possible preparation. If the
airplane is to be stored temporarily, ~r indefinitely, refer to the
airplane Maintenance Manual for proper storage procedures. The
Maintenance Manual provides amplification for the following
procedures:
1.
The procedure to . be followed for preservation of an engine
in service depends on the period of inactivity and whether or
not the engine may be rotated during the inactive period.
The ·expected period of inactivity should be established and
'reference made to the Engine Preservation Schedule. The
preservation carried out should be recorded in the engine
maintenance record and on tags secured to the engine. The
following preservation schedule lists procedures to be
followed :
8-49
1 April 1998
For Training Purposes Only
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
CESSNA
MODEL 208 (675 SHP)
A CAUTION
UNDER
NO
CIRCUMSTANCES
should
preservative oil be sprayed Into the compressor
or exhaust ports of the engine. Dirt particles
deposited on blades and vanes during engine
operation will adhere and alter the airfoil shape,
adversely affecting compressor efficiency.
2.
3.
a. 0 to 7 Days -- The engine may be left in an inactive
state, with no preservation protection, provided the
engine is sheltered, humidity is not excessively high,
and the engine is not subjected to extreme temperature
changes that would produce condensation.
b. 8 to 28 Days -~ An engine inactive for up to 28 days
requires no preservation provided all engine openings
are sealed off and relative humidity in the engine is
maintained at less than 40 percent. Humidity control is
maintained by placing desiccant bags and a humidity
indicator on wooden racks in the engine exhaust duct.
Suitable windows must be provided in the exhaust /
closure to facilitate observation of the humidity [,
indicators.
'
.
c. 29 to 90 Days -- An engine inactive for a period
exceeding 28 days, but less than 91 days, need only
have the fuel system preserved, engine openings
covered, and desiccant bags and humidity indicators
installed.
d. 91 Days and Over -- An engine inactive over 90 days in
the airframe or removed for long term storage in a
container, must, in addition to the 29 to 90 day
procedure, have the engine oil drained and unused
accessory drive pads sprayed.
Place a cover over the pitot tube, and install the two engine
inlet covers. To prevent the propeller from windmilling, install
the propeller anchor over a blade of the propeller and
secure the strap around the nose gear or to the bracket
located on the lower right hand cowl. Cover all other
openings to prevent entry of foreign objects.
Keep the fuel tanks full to minimize condensation in the
tanks.
1 April 1998
8-50
For Training Purposes Only
(
(
CESSNA
MODEL 208 (675 SHP)
4.
(
5;
(
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6.
7.
(
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",-"
(
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."
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
If the airplane will be out of service for 5 days or more,
disconnect the battery. If the battery is left in the airplane, it
should be removed and serviced regularly to prevent
discharge. If the battery is removed from the airplane, check
it regularly for state of charge.
.
If .the airplane is stored outside, tie-down the airplane in
accordance with the proc,edure in this section. Chock the
nose and main wheels; do not set the parking brake if a long
period of inactivity is anticipated as brake seizing can result
Every two weeks, move the airplane to prevent flat areas on
the tires. Mark the tires with tape to ensure the tires are
placed approximately 90 0 from their previous position.
Drain all fuel drain points every 30 days and check for water
accumulation. Prolonged storage of the airplane will result in
a water buildup in the fuel which "leaches out" the fuel
additive. An indication of this is when an excessive amount
of water accumulates at the fuel drain paints. Refer to Fuel
Additive in this section for minimum allowable additive
'
concentrations.
BULB REPLACEMENT DURING FLIGHT
Figure 8-6 provides instructions to aid the pilot in the replacement of.
defective light bulbs during flight without tools. It is suggested that
spare bulbs be stored in the map compartment. However, if a spare
bulb is not available, an identical bulb which is found to be available
from other lights listed herein can be substituted for the defective
bulb. For a listing of other bulb requirements and specific tools
needed, refer to the Maintenance Manual for this airplane,
8-51
8 March 1999
For Training Purposes Only
CESSNA
MODEL 208 (675 SHP)
SECTION 8
HANDLING, SERVICE
& MAINTENANCE
(
(
ANNUNCIATOR PANEL LIGHTS
Push In on' face of light asser:nbIY~nd a,lIow
assembly to pop OU\., Pull assemblyout'to, '
limit of its hinged retain~~andallow it to
rotate 90 degrees down, Retainer will keep
light assembly suspended in this position,
Lift ' defective bulb out of assembly and
replace with MS25237-327 bulb (MS252378918 14-volt bulb in ' lGNITION ON ' light
assembly only). Rotate light assembly
upward into position and press into place.
NOTE
Each light assembly contains two
bulbs, and, if necessary. remains
sufficiently illuminated with one
bulb defective..
POST LIGHTS
'Grasp lens cap and pull straight out from
socket. Pull bulb from cap and replace
with MS25237-327 bulb. Replace cap in
socket and rotate cap to direct light in
desired direction.
I
CONTROL WHEEL MAP LIGHT
(
Grasp rim of bulb, push straight up and
turn counterclockwise as far as possible,
then pull bulb straight. down and out of
socket. Replace with 24RB bulb. To install
new bulb in socket, align pins on bulb with
slots in socket, then push straight up and
rotate bulb clockwise as far as possible.
i
2685)(10.4B
I
Figure
a-6. Bulb Replacement
8 March 1998
8-52
For Training Purposes Only
\
SECTION 9
SUPPLEMENTS
CESSNA
MODEL 208 (675 SHP)
SUPPLEMENTS
:-
INTRODUCTION
This section consists of a series of supplements, each covering a
single system which may be installed in the airplane. Each
supplement contains a brief description,and when applicable,
operating limitations, emergency and normal procedures, and
performance.
)
Operators should refer to each supplement to ensure that all
limitations and procedures appropriate for their airplane are
observed.
j\WARNING
•
Complete familiarity with the airplane and Its
systems will not only Increase the pilot's
proficiency and ensure optimum · operation,
but could provide a basis for analyzing
system malfunctions in case of an
emergency Is encountered. Information in
this section will assist In that familiarization ..
The responsible pilot will want to be prepared
to make proper and precise responses In
every situation.
•
Limitations contained In the following
supplements are FAA approved. Observance
of these operating limitations is required by
Federal Aviation Regulations.
9-1
1 April 1998
For Training Purposes Only
SECTION 9
SUPPLEMENTS
CESSNA
MODEL 208 (675 SHP)
NOTE
Some supplements contain references to equipment
manufacturers pilot's manuals which are supplied with the
airplane at the time of delivery from the factory, or whenever
equipment is installed after delivery. These manuals must
be kept up-to-date with the latest revisions issued by the
publisher. These vendor manuals contain a user registration
form or instructions for obtaining future revisions or
changes.
.
I
Supplements for installed optional equipment must be maintained to
the latest supplement revision. Supplements for optional equipment
not installed in the airplane do not have to be retained in the basic
manual, and may be discarded, if desired.
A Log of Approved Supplements is provided for convenience only
beginning on page Log-1 . This log is a numeriCal list of all the
individually approved supplements and their revisions published for
this airplane. An installed equipment column is provided in the log
to allow owners to mark which supplements apply to their airplane. (
Each signed supplement contains its own Log of Effective Pages,
and each supplement page number includes an "S" and the
supplement number (Le. S1-1). A~ditionally, the part number of the
supplement provides information on ·the revision level. Refer to the . (
following example:
(
01352 - 81- 04
TT
Revision level of Supplemenl
Supplement Number
L-_ _ _ _ _
Manual Supplement Applies To
f\ .. .
...,
9-2
15 November 2000
For Training Purposes Only
.
(
MODEL 208 (675 SHP)
(
(
SUPPLEMENTS
LOG OF APPROVED SUPPLEMENTS
(
(
SECTION 9
CESSNA
(
(
(
(
(
NOTE
IT IS THE AIRPLANE OWNER'S RESPONSIBILITY TO ASSURE THAT
THEY HAVE THE LATEST REVISION TO EACH SUPPLEMENT OF A
PILOT'S OPERATING HANDBOOK, AND THE LATEST ISSUED "LOG
OF APPROVED SUPPLEMENTS".
THE LOG OF APPROVED
SUPPLEMENTS FURNISHED WITH THIS REVISION WAS THE LATEST
VERSION AS OF THE DATE IT WAS SHIPPED BY CESSNA;
HOWEVER, SOME CHANGES MAY HAVE OCCURRED, AND THE
OWNER SHOULD VERIFY THIS IS THE LATEST, MOST UP-TO-DATE
VERSION BY REFERRING TO THE LATEST CESSNA PROPELLER
AIRCRAFT REVISION STATUS CHECKLIST OR BY CONTACTING
CESSNA PROPELLER PRODUCT SUPPORT: TELEPHONE (316) 5175800, FAX (316) 942-9006.
SUPPLEMENT
NUMBER
(
REVISION EQUIPMENT
NUMBER INSTALLED
NAME
01
Known Icing Equipment
3 .
02
Emergency Locator Transmitter
(ELT) (Socata ELT 90) (French)
0
03
Bendix/King Digital ADF (Type KR-87
with KI 227-01 Indicator)
0
04
Bendix/King Dual Digital ADF (Type
KR-87 with KI 228-01 Indicator)
0
05
Bendix/King KCS~55A Slaved
Compass System with KI-525A HSI
Indicator
0
06
Northern Airborne Technology
NPX138 FM Transceiver
0
(
07
Air Conditioning System
0
(
08
Cargo Doors Removed Kit ·
0
09
Cargo Pod
0
10
Digital Clock, Astro Tech LC-2
0
11
Electric Elevator Trim Sys1em
0
12
DELETED
13
Fuel Totalizer System
14
Inflight Openable Cargo Door
15
RESERVED
16
Oxygen System (2-Port)
(
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t~-· · ·
~
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D1352-22-13Sl
6 January 2004
For Training Purposes Only
o
o
o
Log-1
SECTION 9
SUPPLEMENTS
(
CESSNA
. MODEL 208 (67~ SHP) .
(
(
LOG OF APPROVED SUPPLEMENTS
SUPPLEMENT
NUMBER
NAME
REVISION EQUIPMENT
NUMBER INSTALLED
17
Oxygen System (10-Port)
0
18
Propeller Anti-Ice System
0
19
Rudder Gust lock (Aero Twin)
0
20
Standby Electrical System
3
21
Ventilation Fan System
0
22
Windshield Anti-Ice System
0
23
Pointer Model 3000-111
Model 4000-11 Emergency locator
Transmitter (ElT)
Bendix/King GPS Navigation System
(Type KLN 89B)
2
25
Bendix/King Audio Control System
(Type KMA-24)
0
26
Bendix/King Flight Control System
(Type KFC-1S0)
0
27
Bendix/King Audio Control System
(Type KMA-24H-70) and Optional PA
(Passenger Address) System
0
(
.
(
(
(
(
t
(
28
RESERVED
29
Bendix/King Digital ADF (Type KR-B7)
with KI-227 Indicator or KI-229
Optional RMI
0
30
Bendix/King DME (Type KN-63)
0
31
Bendix/King HF Transceiver (Type
KHF-950)
0
32
Bendix/King Marker Beacon (Type
KR-21)
0
33
Bendix/King Nav/Com (Type KX-165)
with Optional Integral Glide Slope
34
Bendix/King Radar Altimeter (Type
KRA-10A)
0
35
Bendix/King Radio Magnetic Indicator
(Type KI-229)
0
(
(
(
(
(
(
\......' ,-
(
6 January 2004
For Training Purposes Only
(
f
(
24
Log-2
(
(
LOG OF APPROVED SUPPLEMENTS
(
SUPPLEMENT
NUMBER
, ,.-r . ..
(
I
37
Bendix/King Mode S Transponder
(Type KT-70and KT-71) and
Encoding Altimeter (Type KEA-130 or
Type 5035P·P45)
0
38
Bendix/King Digital Weather Radar
System (Type ADR 2000)
0
39
Airplanes Certified to Russian
Configuration
40
Bendix/King GPS Navigation System
(Type KLN 89B) Interfaced with the
KNI582 RMI
0
41
Bendix/King (AlliedSignal) StandAlone - VFR Only GPSNavigation
System (Type KlN 89B with Software
level 02102)
0
42
High Altitude Takeoff and landing
Performance (Above 12,000 Feet
Pressure Altitude)
43
BFGoodrich SkywatchSKY497
Traffic Advisory System
44
BFGoodrlch Stormscope
WX-1000+/1000E
Weather Mapping System
0
45
Arctic Diesel Fuel
0
46
300-Amp Starter/Generator
Installation
0
47
Takeoff Procedures for European
Airports with Noise Limitations
0
48
Bendix/King Flight Control System
(Type KFC-225)
0
49
RESERVED
50
Bendix/King KLN 94 GPS Navigation
System
(
(
[-I,
REVISION EQUIPMENT
NUMBER
INSTALLED
Bendix/King Radio Magnetic Indicator
(Type KNI-582)
(
(
NAME
36
(
(
SECTION 9
SUPPLEMENTS
CESSNA
MODEL 208 (675 SHP)
(
:.
\ ,,,: '
(
(
(
(
(
( :;
";' ;;,)
Log-3
6 January 2004
For Training Purposes Only
SECTION 9
SUPPLEMENTS
CESSNA
MODEL 208(675 SHP)
LOG OF APPROVED SUPPLEMENTS
SUPPLEMENT
NUMBER
51
REVISION EQUIPMENT
NUMBER INSTALLED
Airplanes Certified to China
AAD-CAAC Configuration
0
52
Artex 406 Three Frequency
Emergency locator Transmitter (El T)
0
53
Airplanes without Vacuum
Powered Gyros
0
54
Garmin GMA 340 Audio Panel
0
55
Garmin GTX 327 Transponder
56
Bendix/King KGP 560 General Aviation·
Enhanced Ground Proximity Warning
System .(GA·EGPWS)
2
57
RESERVED
58
Garmin GNS 530 or GNS 430
Navigation/Communication System
59
Bendix/King KMD 850
Multi-Function Display
0
BFGoodrich Stormscope WX-500
Weather Mapping System
0
61
Fairchild F1000 Flight Data Recorder
0
62
Dual HSI and FDI with Bendix/King
KFC-225 Autopilot
0
Fairchild FA2100 Cockpit Voice
Recorder
0
Bendix/King KI 825 Electronic Horizontal
Situation Indicator
0
Honeywell KMH 880 Integrated Hazard
Awareness System (I HAS)
0
Honeywell KTA 870 Traffic Advisory
System (TAS)
0
67
2-Port Oxygen System
0
68
Honeywell KDR 510 Flight Information
Services (FIS)
0
69
Garmin GTX 330 Transponder
0
60
63
I
NAME
64
65
66
Log-4
I
\~;:..:..'-
6 January 2004
For Training Purposes Only
(
CESSNA
MODEL 208 (675 SHP)
(
SECTION 9
SUPPLEMENTS
,LOG OF APPROVED SUPPLEMENTS
(
(
(
SUPPLEMENT
NUMBER
{
\.
REVISION EQUIPMENT
NUMBER INSTALLED
70
Bendix/King KRA·405B Radar
Altimeter
o
71
U,S. Registered Airplanes with
Requirements for British (CM)
Certification
o
72
Altair Avionics Corporation ADAS+
Engine Trend Monitor
o
(
(
NAME
I
(
(
\
(
(
~
( .
(
t
\.:..
.. -
,
,J
(
(
(
f
Log-5/(Log-6 )
6 January 2004
For Training Purposes Only
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
For Training Purposes Only
(
(
(
(
~
(
CeSSriii
(
A Textron Company
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 1
(
\
KNOWN ICING EQUIPMENT
(
(
(
SERIAL NO.
(
REGISTRATION NO.
(
This, supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual when the flight into known icing equipment package is installed.
(
(
(
APPROVED
(
B!imu(dfJ/:~ee~' €
Wendell W . Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
(
(
DATE OF APPROVAL
7 APR11.1998
(
C
":';07
COPYRiGHT ., 199B
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
o
Member of GAMA
1 APRIL 1998
D1352·81·03
REVISION 3 • 25 JUNE 2001
S1-1
ForTraining Purposes Only
S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
SUPPLEMENT 1
KNOWN ICING EQUIPMENT
(
Use the Log of Effective Pages to determine the current status of this i,
supplement. Pages affected by the current revision are indicated by an
asterisk (*) preceding the page number.
, Revision Level
o (Original)
Revision 1
Revision 2
Revision 3
(
(
(
(
Date of Issue
(
1 April 1998
8 September 1999
12 October 2000
25 June 2001
(
(
LOG OF EFFECTIVE PAGES
(
PAGE
•
,
*
•
S1 -1 thru S1-3
S1 -4
S1-5 thru S1 -24
S1-25/S1-26
DATE
REVISION NO.
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25 June 2001
1 April 1998
25 June 2001
25 June 2001
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APPROVED BY
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25 June 2001
S1-2
For Training Purposes Only
51
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
. MODEL 208 (675 8HP)
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SUPPLEMENT
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KNOWN ICING EQUIPMENT
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SECTION 1
GENERAL
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The flight into known icing equipment package allows flight penetration of
icing conditions as defined by FAR Part 25 envelopes for continuous
maximum and intermittent maximum icing. These conditions do not include,
nor were tests conducted in, all icing conditions that may be encountered
(e.g., freezing . rain, freezi!Jg drizzle, mixed conditions or conditions defined as
severe). Flight in these conditions must be avoided. Some icing conditions
not defined in FAR Part 25 have the potential of producing hazardous ice
accumulations, which (1) exceed the .capabilities of the airplane's ice
protection equipment, and/or (2) create unacceptable airplane performance.
Flight into icing conditions which are outside the FAR defined conditions is
not specifically prohibited, however, pilots are advised to be prepared to
divert the flight promptly if hazardous ice accumulations occur.
NOTE
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Whenever icing conditions are encountered, immediate action
should be taken to leave these conditions before airplane
performance is degraded to a point where a climb, which is
normally the best action to take, may not be achievable due to
the residual ice buildup.
The flight into known icing equipment package includes pneumatic deicing
boots on the wings and wing struts, main landing gear legs and cargo pod
nose cap (if installed), horizontal and vertical stabilizer leading edges,
electrically-heated propeller blade anti-ice boots, detachable electric
windshield anti-Ice panel, pitot/static heat system, and a standby electrical
system. The wing, wing strut, landing gear, cargo pod and stabilizer deice
system includes a. deice pressure annunciator. A light is provided that
illuminates the LH inboard wing to aid in visually detecting ice accumulation
during night operations. Some airplanes may also be equipped with a
windshield ice detector light, and a low airspeed advisory system.
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As used in this supplement, rime ice formation is opaque "milky" like ice that
roughly conforms to the wing airfoil shape. Clear ice formation is translucentlike ice that forms a double horn type shape with horns protruding above and
below the wing airfoil leading edge.
Mixed ice formations have
characteristics of both rime and clear ice to some extent. The known icing
equipment will not provide complete protection for continuous operation in
extremely wide-spread areas of heavy cloud freezing moisture content.
81-3
25 June 2001
For Training Purposes Only
S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
The inflight ice protection equipment is not designed to rernove ice, snow or
frost accumulations on a parked airplane sufficiently enough to ensure a safe
takeoff or subsequent flight. Other means (such as a heated hangar or .
approved deicing fluids) must be used to ensure that all wing, wing strut,
landing gear, cargo pod, tail, control, propeller, and windshield surfaces and
the fuel vents are free of ice, snow, and frost accumulations, and that there
are no internal accumulations of · ice or debris in the control surfaces, engine
intakes, pitot-static system ports, and fuel vents prior to takeoff.
A WARNING
If these requirements are not accomplished, aircraft
performance will be . degraded to a point where a safe
takeoff and climbout may not be possible.
WING, WING STRUT, MAIN LANDING GEAR LEG, CARGO POD
NOSECAPAND STABILIZER DEICE BOOTS
The pneumatic deice boot system installed on the leading edges of the wings,
wing struts, main landing gear legs, cargo pod nosecap and horizontal and
vertical stabilizers is designed to remove ice after accumulation in flight rather
than prevent ice formation. The system components include the pressure line
which leads from the engine bleed air system pressure regulator to the
vacuum eJector used in the airplane vacuum system, three flow control valves
and pressure switches, a timer, a system switch and circuit breaker, an
annunciator, and the supply lines and pneumatically-operated surface deice
boots. In operation, the boots expand and contract, using pressure from the
engine bleed · air system to the flow control valves when they are closed or
vacuum created by the dumping action of the flow control valves when they
are open. Normally, vacuum is applied to all boots to hold them against the
leadirig edge surfaces. When a deicing cycle is initiated, vacuum is removed
and pressure is applied to inflate the boots. Ice on the boots will then be
removed by normal in flight air forces.
Controls for the normal operation of the deicing system consist of a . threeposition toggle switch, labeled BOOT PRESS, on the deice/anti-ice switch
panel, a pressure indicator light in' the annunciator panel, and a "pull-off" type
circuit breaker on the left sidewall circuit breaker panel. When the switch is
placed in the AUTO (upper) position and released, it will activate one deicing
cycle. Each time a cycle is desired, the switch must be pushed to the AUTO
position and released. The switch is off when placed in the middle position.
In the event of a malfunction in the timer, causing erratic operation of a
sequence of a cycle, the switch can be held momentarily in the MANUAL
(lower) position to achieve simultaneous inflation of all the deice boots. If
necessary, the system can be stopped at any point in the cycle (deflating the
boots) by pulling the circuit breaker labeled DE-ICE BOOT.
51-4
1 April 199B
For Training Purposes Only
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KNOWN ICING EQUIPMENT
POH SUPPLEMENT
S1
MODEL 208 (675 SHP)
During a normal deicing cycle, the boots will inflate according to the following
sequence: first the horizontal and vertical stabilizer boots will inflate for
approximately six seconds, then the inboard wing, main landing gear leg and
cargo pod nosecap boots inflate for the next six seconds, followed by the
outboard wing boots and wing strut boots for another six seconds. The total
time required for one cycle is approximately 18 seconds.
The pressure indicator . annunciator, labeled DE·ICE PRESSURE, should
illuminate initially within approximately three seconds after initiating a cycle
and remain on approximately three additional seconds to the end of the first
sequence. Through each of the remaining two sequences of the cycle, the
annunciator will remain off during pressure buildup for about three seconds
and then illuminate for about three seconds. The system may be recycled six
seconds after the completion of a cycle, if necessary. The absence of
illumination during anyone of the three sequences of a cycle indicates
insufficient pressure for proper boot inflation and effective deicing ability.
Additionally, any deviation from the sequence described above could indicate
a malfunction of some other portion of the system, and icing conditions
should be avoided.
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PROPELLER ANTI-ICE BOOTS
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The propeller anti-ice system provides protection for the propeller blade
surfaces when icing conditions are encountered. The system is operated by
a three-position toggle switch, labeled PROP, on the DE-ICE/ANTI-ICE switch
panel. When the switch is placed in the AUTO (upper) position, electric
current flows to an anti-ice timer which cycles the current Simultaneously to
the heating elements in the anti-ice boots on the three propeller blades in
intervals of 90 s.econds ON and 90 seconds OFF. The anti·ice timer will
reset when the anti-ice switch is placed in the OFF position.
This 90 second cycle allows ice to buildup on the propeller boots, then sheds
it during the ON cycle.
Due to the propeller blade ice shedding
characteristics, a slight propeller vibration occurring at the start of the
propeller anti-ice ON cycle and lasting 20-30 seconds is considered norma!.1
However, if the vibration continues longer than 30 seconds, or is perceived
by the pilot as being excessive. exercising the propeller control lever and
returning it to MAX position will shed the remaining ice on the blades. If the
vibration continues, refer to the Propeller Anti-Ice System Malfunction
checklist in Section 3 of this supplement.
81-5
25 June 2001
For Training Purposes Only
51
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
An oil-operated pressure switch installed in the electrical circuit
is utilized to prevent the propeller anti-ice system from being .
turned on without the engine running . A failure of this switch will
be undetected unless the ammeter is monitored continuously.
The switch is off when placed in the middle position. In the event of a
malfunction in the anti-ice timer, the switch can be held for 90 seconds in the
MANUAL (lower) position to achieve emergency propeller anti-icing. When
operating in the MANUAL (lower) switch position, it is important to cycle the
switch in intervals of 90 seconds ON and 90 seconds OFF, the same cycling
that occurs when the switCh is in the AUTO position.
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WARNING
If the propeller anti-ice switch Is held In the MANUAL
position wIthout beIng cycled every 90 seconds, Ice on the
boots melts and runs back past the boots and refreezes.
This buildup of runback ice may cause a loss in propeller
efficiency which reduces airplane performance.
Operation of the anti-ice system can be checked by monitoring an ammeter.
labeled PROP ANTI-ICE AMPS, near the upper left corner of the instrument '
panel. The system is protected by two "pull-off" type circuit breakers, a (,
control circuit breaker labeled PROP ANTI-ICE CONT and a heater circuit
breaker labeled PROP ANTI-ICE. Both ' circuit breakers are located on the
left sidewall switch and circuit breaker panel. '
WINDSHIELD ANTI-ICE PANEL
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The windshield anti-ice system assures adequate visibility for a landing during
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flight conditions where ice may form on the windshield.
A detachable,
electrically heated, glass panel mounts to the base of the windshield in front
of the pi/ot.A quick disconnect feature utilizing a spring-loaded release pin is
provided to facilitate ease of installation and removal. The panel may be
stowed in the airplane when ncit in use; a . padded cover is provided for
protection against scratches, breakage, and wiring damage. Windshield antiicing is controlled by a three-position toggle switch,. labeled W/S on the de(
ice/anti-ice switch panel. Some aircraft are equipped with a large sized
windshield anti-ice panel, Which contains two heat elements and is controlled
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by two three-position toggle switches labeled PRIMARY and SECONDARY.
When the switch(es) is(are) placed in the AUTO (upper) position, . electric
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current regulated by a controller flows to the anti-ice panel to prevent the
formation of ice in the protected segment of the windshield. An annunciator, ;, (
labeled WINDSHIELD ANTI-ICE, illuminates to indicate that the system is (,
operating.
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25 June 2001
S1-6
For Training Purposes Only
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S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
NOTE
The, SECONDARY heat element in the large windshield antiice panel is slaved to the temperature controller of the
PRIMARY panel. and will only function in AUTO if the
PRIMARY switch is in the AUTO position. and the automatic
controller is operative.
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The switch(es) is(are) off when placed in th. e m
. iddle position . In the event of
a malfundion in the system controller circuitry. the switch (es) can be held in
the Manual (lower) position to achieve windshield anti-icing, The system is
protected by two "pull-off" type circuit breakers. a control circuit breaker
labeled W/S ANTI-ICE CaNT and a heater circuit breaker labeled W/S ANTIICE. Both circuit breakers are located on the lett sidewall switch and circuit
breaker panel. The , larg.e anti-ice panel is protected by three "pull-off" type
circuit breakers: a control circuit breaker labeled W/S ANTI-ICE CaNT and
two heater circuit breakers labeled W/S ANTI-ICE PRIMARY and WIS ANTIICE SEC. Circuit breakers for the windshield anti-ice panel are located on
the left sidewall switch and circuit breaker panel.
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A WARNING
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The heated glass panel should be installed whenever icing conditions are a
possibility on a proposed flight. especially if the freezing level is near or at
the surface.
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With heavy ice accumulations on the windshield, or
when Ice forms aft of the curved sections on the
windshield, a straight in or · precision approach should
be given priority over a Circling non-precision approach_
PITOT·STATIC HEAT SYSTEMS
A left pitot-static heat system is installed to assure proper airspeed
indications in the event icing conditions are encountered. The system is
designed to prevent ice formation rather than remove it. once formed.
System components include heating elements in the left pitot-static tube. a
two-position toggle switch. labeled PITOT/STATIC HEAT. on the delce/antiice panel. and a "pull-off" type circuit breaker. labeled LEFT PITOT HEAT.
on the left sidewall switch and · circuit breaker panel. When the pltot-static
heat switch is turned on. the elements in the pitot-static tube are heated
electrically to maintain proper operation in icing conditions.
A second. independent pitot-static system is included for operation of the
right flight instruments only. The system has a heated pitot-static tube on the
leading edge of the right wing. The heating elements in the right pitot-static
tube are controlled by the two-position toggle switch. labeled PITOT/STATIC
HEAT. on the deice/anti-ice switch panel. Circuit protection is provided by a
"pull-off" type circuit breaker. labeled RIGHT PITOT HEAT. on the left
sidewall switch and circuit breaker panel.
S1-7
25 June 2001
I
For Training Purposes Only
S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
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STANDBY ELECTRICAL SYSTEM
The standby electrical system serves as a standby power source after
starting in the event the main generator system malfunctions in flight. The
system includes an alternator operated at a 75-amp capacity rating. The ;'
alternator is belt-driven from an accessory pad on the rear of the engine. '
The 'system also ,includes an alternator control unit located forward of the
circuit breaker panel, a standby alternator contactor assembly on the left front
side of the firewall and two switches on the left sidewall switch panel.
The standby system switches are a two-position toggle-type switch , labeled
STBY POWER, and a guarded two-position switch/breaker, labeled AVIONICS
STBY PWR. The guard covering the standby avionics power switch must be
lifted in order to select the ON position. Circuit protection and isolation is
provided by two circuit breakers, labeled STBY PWR, on the left sidewall
circuit breaker panel. ' Field excitation to the alternator control unit is supplied
through diode logic from a circuit breaker in the standby alternator relay
assembly at the KEEP ALIVE No. 2 circ,uit breaker in the main power relay
box. System monitoring is provided by two amber annunciators. labeled
STBY ELECT PWR ON and STBY ELECT PWR INOP, In the annunciator
panel. Total amperage supplied from the standby electrical system can be
monitored on the airplane volt/ammeter with the selector switch in the AL T
position.
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Any time the standby electrical system is turned on, standby power will ,
automatically be supplied to the main buses if system voltage drops.
A WARNING
In the event of a generator system failure, the alternatordriven standby electrical system, which has 75-amp
capacity rating, can supply essential equipment when
nonessential loads are eliminated. During a night flight In
icing conditions, It Is possible to have an electrical load of
approximately 110 amps.
This electrical load can be
reduced to the standby electrical system capacity (75-amps)
by turning off the following equipment:
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All external lights.
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the failed generator (TRIP).
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Autopilot and weather radar andlor enough other
nonessential avionics and lights to prevent battery
discharge, as indicated by the ammeter with the BATT
position selected or illumination of the red VOLTAGE
LOW annunciator.
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For airplanes equipped with the large windshield anti-ice
panel turn the SECONDARY switch to OFF. .
81-8
25 June 2001
For Training Purposes Only
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51
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
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MODEL 208 (675 SHP)
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WING ICE DETECTOR LIGHT
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An ice detector light is flush-mounted in the left wing leadin,9 edge-Iofuselage fairing to facilitate the detection of wing ice at night by lighting the ,
leading edge of the wing.
Components of the system include the ice
detector light, a two-position toggle-type switch, labeled WING LIGHT, on the
deice/anti-ice switch panel, and a "pull-off" type circuit breaker, labeled ICE
DET LIGHT, on the left sidewall circuit breaker paneL The switch is springloaded to the OFF (lower) position and must be held in the ON (upper)
position to keep the ice detector light illuminating.
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WINDSHIELD ICE DETECTOR LIGHT (Aircraft with large anti·lce panel)
A red Windshield Ice Detector Light is located on the lower inboard portion of
the pilOt's windshield. It is activated by moving the DAY/NIGHT switch to
NIGHT. If the windshield is clear of ice, distinct red circles will be present
above the light. If the windshield is contaminated , the red circles will become
more diffuse and the area of red light will increase. The windshield ice
detector light should not be relied on as the only means to detect ice.
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LOW AIRSPEED ADVISORY SYSTEM (Aircraft with large anti-ice panel)
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An advisory annunciator labeled BELOW 105 KIAS is located just above ' the
annunciator panel. This annunciator illuminates when the pitot heat switch is
in the ON 'position and the airspeed is less than 105 knots . The light will
illuminate as a reminder of the minimum speed of 105 KIAS during flight in
icing conditions with the flaps up. This does not limit speeds for takeoff or
approach phases of flight.
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ENGINE INERTIAL
SYSTEMS
SEPARATOR
AND
HEATED
STALL
WARNING
See Section 7 of the basic Pilot's Operating Handbook for descriptions of
these standard/required equipment items.
S1·9 ,
25 June 2001
For Training Purposes Only
S1
MODEL 208 (675 SHP) •.
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
SECTION 2
LIMITATIONS
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REQUIRED EQUIPMENT
This airplane is approved for flight into icing conditions as defined by FAR
Part 25 continuous maximum and maximum intermittent icing envelopes only
if the following Cessna (drawing number 2601066) and FAA approved
equipment is installed and is fully operational:
1. Wing and wing strut leading edge deice boots.
2. Horizontal stabilizer leading edge deice boots.
3. Vertical stabilizer leading edge deice boots.
4. Propeller anti-ice boots.
5. Windshield anti-ice panel.
6. Pitot-static' tube heat system (left hand).
7. Standby electrical system.
8. lee detector light.
9. Engine inertial separator (required equipment on standard airplane).
10. Heated stall warning system (included equipment on standard
airplane).
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The following additional equipment is not required for flight into icing (.
conditions as defined by FAA 25, but may be installed on early serial , (
airplanes by using optional accessory Kit AK208-6. On later serial airplanes,
this equipment may be included with the flight into known icing package. If
installed, this equipment must be fully operatio~al:
11. Lower main landing gear leg leading edge deice boots.
12. Cargo pod nosecap deice boot.
In addition, refer to Section 2 of the basic handbook for a complete listing of
other required equipment.
181-10
25 June 2001
For Training Purposes Only
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
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S1
MODEL 208 (675 SHP)
ENVIRONMENTAL CONDITIONS
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Known icing conditions are defined by FAA Part 25, Appendix C. These
conditions do not include, nor were tests conducted in, all icing conditions
that may be encountered (e.g., freezing rain, freezing drizzle, mixed
.conditions or conditions defined as severe). · Flight in these conditions must
be avoided. Some icing conditions not defined in FAA Part 25 have the
potential of producing hazardous ice accumulations, which (1) exceed the
capabilities of the airplane's ice protection equipment; and/or (2) create
unacceptable airplane performance. Flight into icing 'conditions which are
outside the FAR defined conditions is not specifically prohibited, however,
pilots are advised to be prepared to divert the flight promptly if hazardous ice
accumulations occur. Inadvertent operation in these conditions may be
detected by heavy ice accumulations on the windshield , or when ice forms
aft of the curved sections on the windshield. Another indication is when ice
forms aft of the protected surfaces of the wing struts. If these conditions are
encountered, the pilot should take immediate action to leave these
conditions. This may best be achieved by climbing .to warmer air above the
freezing rain or drizzle. Maximum climb power with the flaps retracted should
be used.
MINIMUM SPEED IN ICING CONDITIONS
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Minimum speed during flight in iCing conditions with the flaps up is 105 KIAS.
This does not limit speeds for takeoff or approach phases of flight.
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FLAP SETTINGS FOR HOLDING IN ICING CONDITIONS
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When holding in icing conditions the flaps must be UP.
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FLAP SETTINGS FOR LANDING IN ICING CONDITIONS
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With ice suspected on the airframe, or operating at 4°C or less in visible
moisture, Do Not Extend Flaps Beyond 20° for Landing.
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AUTOPILOT OPERATION IN ICING CONDITIONS
Autopilot operation is prohibited when operating in icing conditions which are
outside the FAA defined conditions as stated in the Environmental Conditions
paragraph above.
PLACARDS
The following placards must be installed in the airplane:
1. Near the compass (airplanes equipped with the large anti-ice panel) :
OPERATION OF THE ANTI-ICE PANEL MAY CAUSE A
COMPASS DEVIATION OF MORE THAN 10 DEGREES.
(Continued Next Page)
S1-11
25 June 2001
For Training Purposes Only
51
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
PLACARDS (Continued)
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The following placards must be installed in the airplane
2. In full view of the pilot:
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(ContinU~d):
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The markings and placards Installed In this airplane .contain
operating limitations which must be complied with when operating
this airplane In the Normal Category. Other operating limitations
which must be complied with when Operating this airplane In this
category are contained In the Pllol's Operating Handbook and FAA
Approved Airplane Flight Manual.
No acrobatic maneuvers, including spins, approved.
This airplane Is approved for flights Into Icing conditions If
the proper optional equipment is installed and operational.
This airplane is certified for the . following flight operations as of
date of original airworthiness certificate:
DAY - NIGHT - VFR • IFR
SECTION 3
EMERGENCY PROCEDURES
ENGINE INERTIAL SEPARATOR MALFUNCTION
1. Inertial Separator Control -- BYPASS.
2. Engine Torque Indicator -- MONITOR for proper operation by noting
torque drop (typically 100 to 150 foot-pounds).
If inertial separator fails to operate to the BYPASS mode:
3. Ignition Switch -- ON.
4. Leave icing conditions as soon as possible.
25 June 2001
81 -12
For Training Purposes Only
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KNOWN ICING EQUIPMENT
POH SUPPLEMENT
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51
MODEL 208(675 SH P)
PROPELLER ANTI-ICE SYSTEM MALFUNCTION
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If uneven anti-icing of the propeller blades is indicated by excessive vibration:
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1. Propeller Control Lever -- EXERCISE, then return to MAX.
2 : Prop Anti-ice and Prop Anti-Ice Control Circuit Breakers -- PUSHED IN.
3. Prop AntHce Ammeter -- CHECK for proper operation. The ammeter
should indicate 20 to 24 amps for 90 seconds and then zero amps for
90 seconds.
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4. If ammeter continuously indicates zero amps:
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a. Prop Anti-ice Switch -- CHECK in AUTO position.
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If zero amps indication perSists:
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b. Prop Anti-ice Switch -- MANUAL and hold for 90 seconds. Repeat
procedure at 90-second intervals.
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If zero amps indication still persists :
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c. Leave icing conditions as soon as possible.
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A WARNING
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When operating propeller anti-Ice system In the MANUAL
mode, which requires that the switch be held In the lower
position, It Is Important to cycle the switch In Intervals of 90
seconds ON and 90 seconds OFF. If the switch Is held In
the MANUAL position without being cycled OFF every 90
seconds, runback Ice may build up on the propeller blades
causing a loss in propeller efficiency, which reduces
airplane performance.
This characteristic may be more
pronounced with the Hartzell composite propeller.
5. If ammeter reading is below the green arc indicating that the propeller
blades may not be deiced uniformly:
a. Prop Anti-ice Switch -- OFF.
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b. Cycle propeller control lever from MAX to MIN and back to MAX at
frequent intervals to aid in ice shedding.
c. Leave Icing conditions as .soon as possible.
s1-131
25 June 2001
For Training Purpos~s Only
S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
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NOTE
• A slight propeller vibration occurring at the start of the propeller
anti-ice ON cycle and lasting 20-30 seconds is due to propeller
blade ice shedding characteristics and is considered normal.
This vibration may be more pronounced with the Hartzell
composite propeller .
• To check the heating elements and anti-ice timer for one
complete cycle, the system must be left on for approximately
three minutes.
A CAUTION
If, after leaving Icing conditions, engine roughness or
vibration develops or persists that is not traceable to icing
or another cause, reduce propeller RPM to smoothest
condition, plan a landing at the nearest airport, and check
the security of the anti-ice boots and leads as a possible
cause.
WING, WING STRUT, MAIN LANDING GEAR LEG, CARGO
NOSECAPAND STABILIZER DEICE SYSTEM MALFUNCTIONS
POD
ICE REMAINS ON LEADING EDGES AND DEICE PRESSURE
ANNUNCIATOR DOES NOT ILLUMINATE DURING ALL 3 SEQUENCES OF
INFLATION CYCLE (Annunciator verified operational):
NOTE.
The deice pressure annunciator should illuminate 3 times,
approximately 3 seconds each time, during the 18-second cycle.
1. Deice Boot Circuit Breaker -- PUSHED IN.
2. Suction Gage -- CHECK.
If instrument vacuum is below normal and/or there is an audible leak in the
forward cabin or left wing root area, expect a broken engine bleed air Hne
and:
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3. Leave icing conditions as soon as possible using available nonvacuum powered instruments for attitude information.
IS1-14
25 June 2001
For Training Purposes Only
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KNOWN ICING EQUIPMENT
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POH SUPPLEMENT
If instrument vacuum is normal:
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3. Boot Press Switch -- MANUAL and HOLD for approximately 9 seconds.
4. Leading Edges -- VISUALLY OBSERVE for simultaneous inflation of all
visible leading edge boots.
5. Deice Pressure Annunciator -- OBSERVE (should illuminate within 6
seconds after activating boot press switch to MANUAL position).
If the deice pressure annunciator does not illuminate or any of the leading
edge boots do not inflate:
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6. Leave Icing conditions as soon as possible.
7. Maintain a minimum airspeed of 105 KIAS or higher to stay above prestall buffet.
If unable to maintain this airspeed, allow altitude to
decrease.
8. If there are unshed ice accumulations along the wing, wing strut, and
stabilizer leading edges during an approach and landing, follow the
procedures listed under Inadvertent Icing Encounters in Section 3 of
the basic handbook.
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MODEL 208 (675 5HP)
C::.
WARNING
• With heavy Ice accumulations on the horizontal stabilizer
leading edge, do not extend flaps while enroute or holding.
When landing is assured, select the minimum flap setting
required, not to exceed 20°, and maintain extra airspeed
consistent with available field length. Do not retract the
flaps once they have been extended, unless required for goaround. Then retract flaps In Increments while maintaining 5
to 10 knots extra airspeed.
• With Inoperative deice boots, Increase engine power to
. maximum continuous power and leave Icing conditions as
soon as possible. In heavy Icing conditions, It may not be
possible to maintain altitude or proper glide path on
approach; In this case, It Is Imperative that a safe airspeed
be maintained.
The aural stall warning horn may not
function and there may be little or no pre-stall buffet with
heavy Ice loads on the wing leading edges.
LEADING EDGE DEICE BOOTS REMAIN INFLATED (Green Deice Pressure
Annunciator Illuminated)
1. Boots -- OBSERVE horizontal stabilizer, wing inboard, main landing
gear leg, wing outboard and wing strut boots for any that may remain
inflated.
51-151
25 June 2001
For Training Purposes Only
S1
MODEL 208 (675 SHP)
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
If it can be visually verified that all leading edge boots are deflated,
assume a fault in a pressure switch or the annunciator system and:
2. Proceed to destination using visual monitoring of leading edge boots
during and after each cycle to verify proper function.
If any of the leading edge boots remain inflated after the normal cycle
period:
3. Deice Boot Circuit Breaker -- PULL to deflate boots.
4. Boots -- OBSERVE for any that may remain inflated and:
a. If all boots are deflated, continue flight; be prepared to reset circuit
. breakers long enough to inflate boots with boot press switch for an
additional cycle and again pull the circuit .breaker, as required if
deicing conditions continue.
b. If any boots remain inflated, leave icing conditions as soon as
possible; expect a 1Q-knot increase in stall speeds if any of the
wing leading edge boots are inflated.
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WINDSHIELD ANTI·ICE PANEL MALFUNCTION
I
1. (Small Panel) Windshield Anti-ice Switch -- CYCLE to OFF and then
AUTO.
(Large Panel) PRIMARY Switch -- CYCLE TO OFF AND THEN AUTO.
2. W/S Anti-ice and W/S Anti-ice Control Circuit Breakers-- PUSHED IN.
3. Windshield Anti-ice (Green) Annunciator -- CHECK ILLUMINATED.
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If windshield anti-ice annunciator does not illuminate:
4. (Small Panel) Windshield Anti-ice Switch -- MANUAL and HOLD.
(Large Panel) PRIMARY and SECONDARY Windshield Anti-ice
Switches -- MANUAL and HOLD.
(Large Panel) If either the PRIMARY or SECONDARY heat element
malfu nctions:
5. CONTINUE to destination and plan a STRAIGHT-IN-APPROACH, if
possible.
NOTE
Circling approaches were demonstrated with either the
PRIMARY or SECONDARY panels of the large windshield antiice panel failed. In the event that a straight-in approach is not
pOSSible, preference should be given to a circling approach with
turns that are in the direction of the operating half of the
windshield anti-ice panel.
If ice remains on windshield anti·ice panel during landing approach:
6. Execute a forward slip as required for visibility through the left-hand
portion of the windshield.
25 June 2001
S1-16
For Training Purposes Only
S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
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MODEL 208 (675 SHP)
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HEATED PITOT/STATIC TUBE MALFUNCTION
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1. Left Pitot Heat and Right Pitot Heat Circuit Breakers -- PUSHED IN.
If ice begins to form near the static port of the left-hand pitot/static tube
(from compensation ring to aft end of tube) or if erroneous readings on
the pilot's flight instruments are suspected:
2. Confirm a malfunction in the left-hand pitot/static tube heater system by
referring to the right-hand flight panel instrument (if the right pitot/static
tube is clear of ice) .
3. Static Pressure Alternate Source Valve -- PULL ON.
NOTE
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The static pressure alternate source is connected to the lefthand flight panel instruments only.
4. Refer to Section 5 of the basic handbook for airspeed and altimeter
corrections when using alternate static air.
If ice begins to form near the pitot port (forward end) of the pitot/static
tube:
5. Indicated Airspeed -- EXPECT NO RELIABLE INDICATION,
6. Fly the airplane using attitude, altitude, and power instruments until
leaving icing conditions.
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GENERATOR · MALFUNCTION , (Red Generator Off and/or Amber Stby
Elect Pwr ON Annunciators illuminated)
I
Refer to the Standby Electrical System supplement in Section 9 for
emergency procedures in the event of a generator failure.
In the event of a generator system failure, the alternator-driven standby
electrical system has the capacity to supply essential equipment when
nonessential loads are shed. The possible load of 110 ·amps during a night
cruise flight in icing conditions can be reduced , to the standby electrical
system capacity by turning off the following equipment:
1. All external lights.
2. The failed generator (TRIP) .
3. Autopilot and weather radar and/or enough other nonessential avionics
and lights to prevent battery discharge as indicated by the ammeter
with the BAn position selected or illumination of the red VOLTAGE
LOW annunciator.
4. For airplanes equipped with the large windshield anti-ice panel, turn the
SECONDARY switch to OFF.
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S1-17
25 June 2001
For Training Purposes Only
S1
MODEL 208 (675 SHP)
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
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HEATED STALL WARNING TRANSDUCER MALFUNCTION
If ice is observed forming on the stall warning vane or its mounting plate:
1. Stall Wrn Circuit Breaker -- PUSHED IN.
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2. With continued ice buildup, expect no stall warning horn during slow
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speed operation .
3. Approach Speeds -- MONITOR indicated airspeed ~
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SECTION 4
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NORMAL PROCEDURES
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PREFLIGHT INSPECTION
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1. Wing Ice Detector Light Switch -- ON and CHECK for illumination.
2. DAY/NIGHT Switch to NIGHT -- Windshield Ice Detector Light (if
3.
4.
5.
6.
7.
8.
9.
10.
11.
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installed) CHECK for Illumination .
PITOT/STATIC and Stall Heat Switches -- ON (for 30 seconds
maximum, ensure pitot covers are removed) .
LOW AIRSPEED ADVISORY SYSTEM (if installed) -- CHECK for
illumination when pitot heat is ON.
PITOT/STATIC and Stall Heat Switches -- OFF.
Battery Switch -- OFF.
Stall Warning Transducer -- PERCEPTIBLY WARM.
PitoVStatic Tubes -- CLEAR and VERY WARM.
Wing, Wing Strut, Main Landing Gear Leg; Cargo Pod Nosecap and
Stabilizer Deice Boots -- CHECK for tears, abrasions and cleanliness.
Propeller Anti-ice Boots -- CHECK condition of boots and heating
elements.
Control Surface Static Dischargers -- CHECK condition.
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BEFORE STARTING ENGINE
1. Inertial Separator -- BYPASS if visible moisture is present below ' 4°C
(40°F) .
. BEFORE TAKEOFF
A CAUTION
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To prevent blistering the cargo pod deice boot (If
Installed), ground operation In a right crosswind or
operating the propeller In beta or feather should be kept
toa minimum.
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S1 -18
25 June 2001
For Training Pu rposes Only
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
51
MODEL 208 (675 SHP)
1; (Small Windshield Anti-ice Panel) Windshield Anti-ice Switch -- AUTO
and MANUAL. Observe increase in generator output and illumination
of WINDSHIELD ANTI-ICE annunciator in both switch positions.
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(Large Windshield Anti-ice Panel).
PRIMARY Windshield Anti-ice Switch -- AUTO.
SECONDARY Windshield Anti-ice Switch -- AUTO and MANUAL.
PRIMARY Windshield Anti-ice Switch -- MANUAL.
For each switch movement, observe change in generator output and
illumination of WINDSHIELD ANTI-ICE annunciator.
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10.
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12.
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14.
15.
Prop Anti-ice Switch -- AUTO.
Prop Anti-ice Ammeter -- CHECK in green arc range and for periodic
cycling. . The ammeter should indicate 20 to 24 amps for 90
seconds, and 0 amps for 90 seconds.
Prop Anti-ice Switch -- MANUAL.
.
Prop Anti-ice Ammeter -- CHECK in green arc range .
Power Lever -- ADJUST for 400 FT-LBS TORQUE.
Boot Press Switch -- AUTO and release. Visually check inflation and
deflation cycle of stabilizer, wing inboard, main landing gear leg,
wing outboard and wing strut deicing boots.
DE-ICE PRESSURE Annunciator -- CHECK ON within three seconds,
and OFF after 18 seconds with approximate two-second OFF
periods after 6 and 12 seconds.
.
.
Boots -- CHECK VISUALLY FOR COMPLETE DEFLATION to the
vacuum hold-down condition.
Boot Press Switch -- MANUAL and hold. Visually check inflation of
all visible boots and illumination of DE,ICE PRESSURE annunciator
within 6 seconds.
Inertial Separator -- CHECK for torque drop between NORMAL and
BYPASS modes. Return control to BYPASS if moisture is present
below approximately 4°C (40°F) .
Power Lever -- IDLE.
Standby Power -- CHECK per Supplement 3 (Standby Electrical
System).
Pitot/Static Heat -- ON when OAT is below 4°C (40°F).
Stall Heat, Windshield Anti-ice and Propeller Anti-ice Switches, and
Inertial Separator Control -- AS REQUIRED for takeoff and climb out
conditions.
.
A CAUTION
Do not operate pilot/static, stall warning, and propeller anti·
ice healers for prolonged periods on ground.
S1-19
25 June 2001
For Training Purposes Only
S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 8HP)
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IN FLIGHT
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1. Before Visible Moisture Is Encountered Below Approximately 4°C
(40°F).
a. Inertial Separator Control -- Bypass.
b. PitoVStatic Heat Switch -- Verify ON.
c. Stall Heat Switch -- ON.
d. (Small Windshield Anti-ice Panel) Windshield Anti-ice Switch .AUTO.
(Large Windshield·Anti·ice Panel).
PRIMARY Windshield Anti-ice Switch -- AUTO.
SECONDARY Windshield Anti-ice Switch -- AUTO.
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NOTE
Under non-Icing conditions (espeCially at night), turn the
windshield anti-ice switch (es) OFF to avoid a mild impairment
(distortion) of vision through the panel that occurs when the
heating elements in the panel are activated during the on cycle .
I
e. Prop Anti-ice Switch -- AUTO.
f. Prop Anti-ice Ammeter -- MONITOR.
A CAUTION
If the ammeter indicates unusually high or loW amperage
during the 90-second cycle of operation, a malfunction has
occurred and it Is imperative that (1) the system be turned
off, since uneven anti-icing may result, causing propeller
unbalance and engine roughness, and (2) that Icing
conditions be avoided.
NOTE
A slight propeller vibration occurring at the start of the propeller
anti-ice ON cycle and lasting 20-30 seconds is due to propeller
blade ice shedding characteristics and is considered normal .
Rapid cycling of the propeller control lever from 1900 RPM to
1600 RPM and back up to 1900 RPM will aid the propeller antiice boots in shedding any residual ice. Repeat this procedure
as required .
I
2. During Icing Encounters:
I
a. Propeller -- 1900 RPM.
b. Power -- INCREASE as required to maintain safe airspeed or to
climb out of icing conditions, if feasible. When climbing through
icing conditions, it is recommended that the Maximum Climb Power
rating be used (1900 RPM and 1865 FT-LBS, not to exceed 765°C
ITT or 101.6% Ng) .
81-20
25 June 2001
For Training Purposes Only
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S1
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
c.
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Climb Airspeed -- 120 KIAS RECOMMENDED to reduce ice
buildup on the areas aft of the deice boots. which include the
underside of the wings, horizontal stabilizer and bottom of cargo
pod (cargo pod boots optional) or ·fuselage . However, if a climb
through icing conditions can be accomplished fairly quickly to
. clear or non-icing conditions on top, then a climb at Vy speed is
recommended to minimize exposure time to the icing conditions.
A WARNING
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MODEL 208 (675 SHP)
• In a performance critical situation, Increase power to the
Maximum Continuous rating (1900 RPM and 1865 FT-lBS
torque, not to exceed 805°C ITT or 101.6% Ng) as soon as
possible to climb or maintain airspeed In moderate or heavy
clear Icing conditions. This power may be used without
time limit at the discretion of the pilot.
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• Inadvertent operation in a freezing rain or freezing drizzle
environment may cause ice formation on unprotected areas
of the airplane such as aft of the wing or tail deice boots.
These conditions may be detected by heavy ice
accumulations on the windshield, or when ice forms aft of the
curved sections on the windshield. Another indication is
when ice forms aft of the protected surfaces on · the wing
struts. If these conditions Bre encountered, the pilot should
take immediate action to leave these conditions. This may
best be achieved by climbing to warmer air above the
freezing rain or drizzle. Maximum climb power with the flaps
retracted should be used.
• With heavy Ice Bccumulations on the windshield, or when ice
forms aft of the curved sections on the windshield, or aft of
the protected surfaces of the wing struts, a straight In or
precision approach should be given priority over a cirCling ·
non-precision approach.
• This airplane should not depart from or be flown Into an
airport where freezing rain ·or drizzle conditions are ·being
reported.
NOTE
Inadvertent operation in freezing rain or freezing drizzle
conditions may be detected by ice formation on the windshield
near or aft of the curved sections of the windshield, or aft of the
protected surfaces of the wing struts.
81-21
25 June .2001
For Training Purposes Only
51
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
When ice is no longer forming near or outboard of the curved
portion of the windshield , the airplane has exited the freezing
rain or drizzle conditions.
d. Ice Detector Ught Switch -- ON as required.
e. Ice Buildup -- MONITOR until approximately 3/8 to 3/4 inch thick on
leading edges.
NOTE
• Deicing boots 'are intended for removal of ice after it has ,
accumulated rather than prevent its formation.
• In rime ice conditions, best results can be obtained by not, using
the deice system until approximately 1/2 to 3/4 inch of ice has
accumulated. Clear the accumulation with one or two cycles of
operation. Do not repeat deicing procedure until ice has again
accumulated.
• In clear ice conditions, good clearing of the leading edges can
be obtained when cycling the deice system with as little as 1/4
to 3/8 inch of ice on the wing leading edges. This procedure is
recommended due to the ,high drag penalties associated with
clear ice shapes (double horn type). As with rime ice, use
multiple cycles of the deice system if required ; Do not repeat
the deicing procedure until ice has again accumulated.
1:
Boot Press Switch -- AUTO and release. The switch must be
actuated after each complete boot cycle if additional cycles are
, required.
NOTE
Cycling the deice boots during high speed cruise or descent
produces a mild nose-up pitching moment which is easily
controlled by less than 10 pounds of control wheel force. Also,
cycling the deice boots increases stall speeds by up to 10 knots.
These stalls are preceded by mild stall buffet which serves as a
good warning.
IS1-22
25 June 2001
For Training Purposes Only
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91
KNOWN ICING EQUIPMENT
POH SUPPLEMENT
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MODEL 208 (675 SHP)
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g. Enroute Airspeed .- MAINTAIN A MINIMUM 105 KIAS with 1/2 inch
or more of rime ice accumulation. This will minimize ice buildup on
the underside of the wings. If necessary to maintain a minimum airspeed of 105 KIAS, allow altitude to decrease. A significantly higher
airspeed may be required with 1/2 inch or more of clear ice accumulation.
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NOTE
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During prolonged icing encounters in cruise, increase engine
power to maintain cruise speed as ice accumulates on the
unprotected areas, and to preclude ice buildup on the fuselage
under surfaces, cargo pod nosecap and lower wing surfaces.
• An accumulation of one inch of ice .on the leading edges can
cause a large (up to 500 FPM) loss in rate of climb, a cruise
speed reduction of up to 40 KIAS, as well as a significant buffet
and stall speed increase (up to 20 knots) . Even after cycling the
deicing boots, the ice ac:cumulation remaining on the
unprotected areas of the airplane can cause large performance
losses. With residual ice from the initial one-inch accumulation,
losses up to 200 FPM in climb, 20 KIAS in cruise, and a stall .
speed increase of 5 knots can result.
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• An accumulation of one inch of clear ice on the leading edges .
may cause even larger performance losses than those
associated with rime ice.
• The autopilot may be used in icing conditions. However, every
10-15 minutes the autopilot should be disconnected to c;letect
any out of trim conditions caused by ice buildup. If significant
out of trim conditions are detected, the autopilot should . remain
off for the remainder of the icing encounter so that the pilot may
monitor for additional force buildup.
A WARNING
When disconnecting the autopilot with Ice buildup on the
airplane, the pilot should be alert for out of trim forces. Pilot
control .wheel Input should be applied as required to prevent
potential undesired flight path deviations.
3. Before Landing -- SELECT MINIMUM FLAP SETTING AND MAINTAIN
EXTRA AIRSPEED consistent with available field length.
81-231
25 June 2001
For Training Purposes Only
51
KNOWN ICING EQUI PMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
• Prior to a landing ' approach, cycle all deice boots to , shed any
accumulated ice. Since pre-stall buffet onset and stall speed are
increased slightly when deice boots are actuated, maintain extra
airspeed (10 KIAS) before actuating boots.
• With ice suspected on the airframe, or operating at 4°C or less
in visible moisture,Do Not Extend Flaps Beyond 20° , for
landing.
• After a light rime ice encounter, maintain extra airspeed , (10-20
KIAS) on approach to compensate for the increased pre-stall
buffet associated with ice on the unprotected areas and the
Under moderate or severe rime icing
increased weight.
conditions, limit flap setting to no more than required by available
field length, but Do Not Extend Flaps Beyond 20° for landing.
With flaps up, maintain a MINIMUM approach speed of 105
KIAS.
A WARNING
• During moderate or heavy clear icing encounters, increase
power to maximum continuous rating and maintain maximum
possible airspeed on approach (observe VMO and flap
limitations) to limit ice accretion. Land with partial power
still applied as required.
• Do not cycle the boots during landing since boot inflation
may increase stall speeds by as much as 10 knots.
4. During Landing Rollout -- DO NOT USE REVERSE THRUST, unless
, required , to prevent residual ice on the airframe from being drawn into
the propeller.
A
CAUTION
Leave inertial separator in BYPASS mode after landing to
preclude any possible Ingestion of Ice being shed from
internal inlet dueting:
IS1-24
25 June 2001
For Training Purposes Only
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
Refer to Section 8 of the basic handbook for care and maintenance of the
wing, wing strut, main landing gear leg, cargo pod nosecap and stabilizer deice boots and propeller anti-ice boots.
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51
KNOWN ICING EQUIPMENT
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f~~'
NOTE
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Optimum performance of the deice and anti-ice boots is
dependent on keeping the boots clean and coated with an ice
adhesion depressant such as ICEX II.
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SECTION 5
PERFORMANCE
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There is a slight reduction of 1 KTAS in cruise performance (no ice
accumulation) as a result of the leading edge deice boot installation, and an
additional 1 KTAS reduction as a result of landing gear strut and cargo pod
deice boot installation.
{
NOTE
(
. Large changes ' in performance may occur with
ice
accumulation. Make appropriate allowances for the possibility of
these losses occurring when planning a flight into or through
forecast or reported icing conditions.
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When making a landing approach using a 10 KlAS higher airspeed than
normal, expect a 25% increase in landing distance.
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Observe applicable notes in the Performance section of the basic handbook
for performance losses associated with the inertial separator in bypass and
cabin heat on.
If a landing is performed with flaps up, increase the approach speed by 15
KlAS and allow for 40% longer landing distances.
S 1-2S/S1-26
25 June 2001
For Training Purposes OnJy
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For Training Purposes Only
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CeSSri8
A Texlron Company
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Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
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CESSNA MODEL 208 (675 SHP)
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SUPPLEMENT 2
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EMERGENCY lOCATOR TRANSMITTER (ElT)
(SOCATA ELT90)
<'
For
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FRENCH CERTIFIED AIRPLANES
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SERIAL NO.
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REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating
Handbook and FAA Approved Airplane Flight Manual for Cessna Model 208
(675 SHP) airplanes which have the French DGAC Kit installed.
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APPROVED
B~4
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SOCATA ELT 90 (FRENCH)
POH SUPPLEMENT
4. MASTER FUNCTION SELECTOR SWITCH (3-position toggle switch):
MAN RESET -- Activates transmitter instantly.' Used for test purposes
and if "G" switch Is inoperative. The MAN RESET
position bypasses the automatic activation switch.
With Ihe switch in MAN RESET position, the
annunciator on the ELT will illuminate. (If the ELT is
installed in the airplane the red "XMIT ALERT"
annunciator on .' the remote · control panel should
illuminate).
After automatic activation by the "G"
switch, positioning the switch from AUTO 10 MAN
RESET then back to AUTO resets the "Gil switCh,
deactivating the transmitter and extinguishing the
annunciators.
OFF -Deactivates transmitter during handling and following rescue.
(The red annunciators on the ELT unit and· on the remote
control panel should extinguish).
AUTO -- Arms transmitter for automatic activation if "Gil switch senses
a predetermined deceleration leveL
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52
MODEL 208 (675 8HP)
()
5. REMOTE CONTROL PANEL SWITCH (2-position toggle switch):
MAN RESET -- Remotely activates transmitter for . test or emergency
situations. Red "XMIT ALERT" annunciator on remote
control panel illuminates to indicate that the transmitter
is transmitting a distress signal.
To deactivate
transmitter after manual activation, position the switch
from MAN RESET to AUTO. After automatic activation
by the "G" switch, positioning the switch from AUTO to
MAN RESET then back to AUTO resets the "G"
switch, deactivating the transmitter and extinguishing
the annunciator.
AUTO -- Arms transmitter for automatic activation if "G" switch senses
a predetermined deceleration level.
6. REMOTE CONTROL PANEL ANNUNCIATOR:
XMIT ALERT -- Illuminates red to indicate the transmitter is transmitting
a distress signal.
Figure 1. ELT Control Panel and Remote Control Panel (Sheet 2 of 2)
(
SECTION 2
LIMITATIONS
(
The following information must be present in the form of a placard located on
the upper right side of the aft cabin partition :
EMERGENCY LOCATOR TRANSMITIER INSTALLED AFT OF THIS PARTITION
MUST BE SERVICED IN ACCORDANCE WITH FAR PART 91 .207
82-5
1 April 1998 .
For Training Purposes Only
(
52
80CATA ELT 90 (FRENCH)
POH SUPPLEMENT
MODEL 208 (675 SHP)
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SECTION 3
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EMERGENCY PROCEDURES
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Before performing a forced landing, especially · in remote and mountainous \,
areas, activate the ELT transmitter by positioning the switch on the remote
cortrol panel to the MAN RESET position.
The red "XMIT ALERT"
annunciator on the remote control panel should be illuminated.
Immediately after a forced landing where emergency assistance is required ,
the ELT should be .utilized as follows:
NOTE
The ELT remote control panel system could be inoperative if
damaged during a forced landing . If inoperative, the inertia "G"
switch will activate automatically. However, to turn the ELT OFF
and ON again requires manual switching of the master function
selector switch which is located on the ELT unit.
1. ENSURE EL T ACTIVATION:
a. Position remote control panel switch to the MAN RESET position
even if annunciator light is already on.
b. If airplane radio is operable and can be safely used (no threat of fire ..
or explosion), turn ON and select 121.5 MHz. If the ELT can be (
heard transmitting, it is working properly.
c. Ensure that antenna is clear of obstructions.
NOTE
When the ELT is activated, a decreasing tone will be heard
before the typical warbling tone begins.
2. PRIOR TO SIGHTING RESCUE AIRCRAFT -- Conserve airplane
battery. Do not activate radio transceiver.
3. AFTER SIGHTING RESCUE AIRCRAFT -- Position remote control
panel switch from the MAN RESET position to the AUTO position to
prevent radio interference. Attempt contact with rescue aircraft with the
radio transceiver set to a frequency of 121.5 MHz. If no contact is
established return the remote control panel switch to the MAN RESET
position immediately.
4. FOLLOWING RESCUE -- Positiori remote control panel switch to the
AUTO . position, terminating emergency transmissions.
82-6
1 April 1998
For Training Purposes Only
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MODEL208 (675 SHP)
SECTION 4
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52
SOGATA ELT 90 (FRENCH)
POH SUPPLEMENT
NORMAL PROCEDURES
As long as the remote control panel switch is in the AUTO position and the
ELT master function selector switch remains in the AUTO position, the ELT
automatically activates when the unit senses longitudinal inertia forces as
required in EO-62.
Following a lightning strike, or an exceptionally hard landing, the ELT may
activate . although no emergency exists.
If the remote control panel
illuminates, the ELT has inadvertently activated itself. Another way to check
is to select 121.5 MHz on the radio transceiver and listen for an emergency
tone transmission. If the remote control panel annunciator is illuminated or
an emergency tone is heard, position the remote control panel switch to MAN
RESET then back to AUTO to deactivate the transmitter.
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INSPECTIONfTEST
1. The emergency locator transmitter should be tested every 100 hours.
NOTE
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Test should only be conducted within the first 5 minutes of each
hour.
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2.
3.
4.
5.
6.
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7.
8.
9.
Disconnect antenna cable from ELT.
Turn airplane battery switch and avionics power switches ON.
Turn airplane transceiver ON and set frequency to 121.5 MHz.
Place remote control panel switch in the MAN RESET position. The
annunciator should illuminate.
Permit only three emergency tone
transmissions, then immediately reposition the remote control panel
switch to the AUTO position.
Place the ELT master function selector switch in the MAN RESET
position. Verify that the transmitter annunciator light on the ELT and
the remote control panel annunciator on the instrument panel are
illuminated.
Place the ELT master function selector switch in the OFF position.
Reposition ELT master function selector switch to AUTO.
Reconnect antenna cable to ELT.
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82-7
1 April 1998
For Training Purposes Only
S2
SOCATA ELT 90 (FRENCH)
POH SUPPLEMENT
MODEL 208(675 SHP)
(
A CAUTION
A test with the antenna connected should be approved and
confirmed by the nearest control tower.
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NOTE
• Without its antenna connected, the ELT will produce sufficient
signal to reach the airplane transceiver, yet it will not disturb
other communications or damage output circuitry.
• After accumulated. test or operation time equals 1 hour, battery
pack replacement is required.
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IN-FLIGHT MONITORING AND REPORTING
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Pilots are encouraged to monitor 121 .5 MHz and/or 243.0 MHz while in flight
to assist in identifying possible emergency ELT transmissions. On receiving a
signal, report the following information to the nearest air traffic control facility:
1.
2.
3.
4.
Your pOSition at the time the signal was first heard.
Your position at the time the signal was last heard.
Your position at maximum signal strength.
Your flight altitude and frequency on which the emergency signal was
heard -- 121.5 MHz or 243.0 MHz. If pOSSible, positions should be
given relative to a navigation aid. If the aircraft has homing equipment.
provide the bearing to the emergency signal with each reported
pOSition.
SECTION 5
PERFORMANCE
There is no change to the airplane performance data when this equipment is
installed.
(
.(
82-8
1 April 1998
For Training Purposes Only
(
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(
CeSSri8
(---:
A Texlron Company
"
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP)
(
(
(
SUPPLEMENT 3
(
(
BENDIX/KING DIGITAL ADF
(
(TYPE KR-87 with KI 227-01 INDICATOR)
(
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King Digital ADF (Type
KR-87 with KI 227-01 Indicator).
(
(
(
APPROVED
(
B~4{ef.J0(;.um·f
Wendell W . Corneil
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
(
(
DATE OF APPROVAL
7
APRIL. 19'98
(
(
(
:
, \;",--"
COPYRIGHT 1) 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of GAMA
1 APRIL 1998
D1352-S3-00
S3-1
For Training Purposes Only
S3
KR-87 ADFI K1227-01 INDICATOR
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 3
BENDIX/KING DIGITAL ADF
(TYPE KR-87 with KI 227-01 INDICATOR)
Use the Log of Effective Pages to determine the current status of
this sUPP,lement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
S3-1 thru S3-10
DATE
1 April 1998
REV. NUMBER
o
(
\,
1 April 1998
S3-2
For Training Purposes Only
(
KR-87 ADF/K1227-01 INDICATOR
POH SUPPLEMENT
S3
MODEL 208 (675 SHP)
SUPPLEMENT
BENDIX/KING DIGITAL ADF
(TYPE KR~87 with K1227-01 INDICATOR)
SECTION 1
GENERAL
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(
(
The Bendix/King Digital ADF is a panel-mounted, digitally tuned automatic
direction finder. It is designed to provide continuous i-kHz digital tuning in
the frequency range of 200 kHz to 1799 kHz and eliminates the need for
mechanical band switching. The system is comprised of a receiver, a built-in
electronics timer, a bearing indicator, and a KA-44B combined loop and
sense antenna. The system incorporates a KI 227-01 Indicator in conjunction
with a KCS 55A Compass System. The compass card on the KI 227-01
Indicator is synchronized to the KI 525A Compass Card by rotating the Sync
Knob of the KI 227-01 Indicator, until the reading matches that of the KI 525A
Compass Card. Once aligned, the two compass cards will track concurrently.
Operating controls and displays for the Bendix/King Digital ADF are shown
and described in Figure 1. The audio system used with this ADF system for
speaker-phone selection is shown and described in the Bendix/King Audio
Control System (Type KMA-24 or KMA-24H-70) supplements in Section 9 of
this handbook.
The Bendi)(/King Digital ADF can be used for position plotting and homing
procedures, and for aural reception of amplitude-modulated (AM) signals.
The "flip-flop" frequency display allows switching between pre-selected
"STANDBY" and "ACTIVE" frequencies by pressing the frequency transfer
button. Both pre-selected frequencies are stored in a non-volatile memory
circuit (no battery power required) and displayed in .self-dimming gas
discharge numerics. The active frequency is continuously displayed in the left
window, while the right window will display either the standby frequency or the
selected readout from the built-in electronic timer.
The built-in electronic timer has two se·parate and independent timing
functions. An automatic flight timer that starts whenever the unit is turned on.
This timer functions up to 59 hours and 59 minutes. An elapsed timer which
will count up or down for up to 59 minutes and 59 seconds. When a preset
time interval has been programmed and the countdown reaches :00, the
display will flash for 15 seconds. Since both the flight timer and elapsed timer
operate independently , it is possible to monitor either one without disrupting
the other. The pushbutton controls and the bearing indicators are internally
lighted. Intensity is controlled by the RADIO light dimming rheostat
S3-3
1 April 1998
For Training Purposes Only
53
KR-87 ADF/KI227-01 INDICATOR
POH SUPPLEMENT
MODEL 208 (675 SHP)
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2
4
5
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KR-B7
RECEIVER
13
12
11
10
9
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15
..,
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14
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16
17
K1227-01 INDICATOR
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066-1072-04
066-3063-01
(
Figure 1_ Bendix/King Digital ADF Operating
Controls/Indicator (Sheet 1 of 3)
83-4
1 April 1998
For Training Purposes Only
(
(
KR-87 ADF/KI 227-01 INDICATOR
POH SUPPLEMENT
' 53
MODEL 208 (675 SHP)
1. MODE ANNUNCIATOR -- Antenna (ANT) is selected by the "out"
position of the ADF button . This mode improves the aural reception
and is usually used for station identification. The bearing pointer is
deactivated and will park in. the 90 0 relative position. Automatic
Direction Finder (ADF) mode is selected by the depressed position of
the AQF button. This mode activates the bearing pointer. The bearing
pointer will point in the direction of the station relative to the aircraft
heading.
2. ACTIVE FREQUENCY DISPLAY -- The frequency to which the ADF is
tuned is displayed here. The active ADF frequency can be changed
directly when either of the timer functions are selected.
3. BEAT FREQUENCY OSCILLATOR (BFa) -- The BFa mode, activated
and annunciated when the "BFa" button is depressed, permits the
carrier wave and associated morse code identifier broadcast on the
. carrier wave to be heard.
(
NOTE
(
CW signals (Morse Code) are unmodulated and no audio will
be heard without use of BFO. This type of signal is not used
in the United States air navigation. It is used in some foreign
countries and marine beacons.
(
4. STANDBY FREQUENCY ANNUNCIATION (FRQ) -- When FRQ is
(
(,-,.
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(:j
displayed the STANDBY frequency is displayed in the right hand
display. The STANDBY frequency is selected using the frequency
select knobs.
The selected STANDBY frequency is put into the
ACTIVE frequency windows by pressing the frequency transfer button.
5. STANDBY FREQUENCY DISPLAY -- Either the standby frequency , the
flight timer, or the elapsed time is displayed in this position. The flight
.timer and elapsed timer are displayed replacing the standby frequency
which goes into "blind" memory to be called back at any time by
depressing the FRQ button. Flight time or elapsed time are displayed
and annunciated alternatively by depressing the FLTIET button.
6. TIMER MODE ANNUNCIATION -- Either the elapsed time (ET) or flight
time (FLT) mode is annunciated here.
7. FREQUENCY SELECTOR KNOBS -- . Selects the standby frequency
when FRO is displayed and directly selects the active frequency whenever either of the time functions is selected. The frequency selector
knobs may be rotated either clockwise or counterclockwise. The small
knob is pulled out to tune the 1'so The small knob is pushed in to tune
the 10's. The outer knob tunes the 100's with rollover into the 1000's.
These knobs are also used to set the desired time when the elapsed
timer is used in the countdown mode.
_t ........
Figure 1. Bendix/King Digital ADF Operating Controls/Indicators
(Sheet 2 of 3)
S3-5
1 April 1998
For Training Purposes Only
S3
MODEL 208 (675 SHP)
KR-87 ADF/KI 227-01 INDICATOR
POH SUPPLEMENT
8. OFFIVOLUME CONTROL (OFFIVOL) -- Controls primary' power and
audio .output level. Clockwise rotation from OFF position . applies
primary power to the receiver; further clockwise rotation increases
audio level. Audio muting causes the audio output to be muted unless,'
the receiver is locked on a valid station.
9. SET/RESET BUnON (SET/RST) "- The set/reset button when pressed
resets the elapsed timer whether it is being displayed or not.
10. FLIGHT TIME/ELAPSED TIME MODE SELECTOR BUTTON (FL T/ET) -The Flight Timer/Elapsed Time mode selector button when pressed
alternatively selects either Flight Timer mode or Elapsed Timer mode.
11 . FREQUENCY TRANSFER BUTTON (FRQ) -- The FRO transfer button
when pressed exchanges the active and standby frequencies. The new
frequency becomes active and the former active frequency goes into
standby.
12. BFO BUnON -- The BFO button selects the BFO mode when in the
depressed position. (See note under item 3).
13. ADF SUnON -- The ADF button selects either the ANT mode or the
ADF mode . The ANT mode is selected with the ADF button in the out
position. The ADF mode is selected with the ADF button in the ,
depressed position.
(
'.
14. POINTER -- Indicates the magnetic bearing to the ADF station.
15. HEADING INDEX -- Indicates the airplane magnetic heading on the
azimuth card.
16. ROTATING AZIMUTH (COMPASS) CARD -- Rotates as the airplane
turns so that the airplane magnetic heading is continuously displayed at
the heading index.
17. SYNCKNOS -- Used to manually rotate compass bard to synchronize
with airplane. heading.
Once synchronized, compass card will
continuously display aircraft heading.
(
(
Figure 1. Bendix/King Digital ADF Operating Controls/ Indicators
(Sheet 3 of 3)
1 April 1998
S3-6
For Training Purposes Only
{
\:
(
(
KR-87 ADF/KI' 227-01 INDICATOR
POH SUPPLEMENT
S3
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
There .are no changes to the airplane Limitations when this avionics
equipment is installed.
SECTION 3
EMERGENCY PROCEDURES
There are no changes to the airplane Emergency Procedures when this
avionics equipment is installed.
SECTION 4
NORMAL PROCEDURES
TO OPERATE AS AN AUTOMATIC DIRECTION FINDER:
1. OFFNOL Control -- ON.
2. Frequency Selector Knobs -- SELECT desired frequency in the standby
frequency display.
3. FRO Button -- PRESS to move the desired frequency from the standby
to the active position.
4. ADF SPEAKER/PHONE Selector Switch (on audio control panel) -SELECT as desired.
5. OFFNOL Control "- SET to desired volume level.
6. ADF Button -- SELECT ADF mode and note relative bearing on
indicator.
ADF TEST (PRE-FLIGHT or IN-FLIGHT):
1. ADF Button -- SELECT ANT mode and note pointer moves to 90 0
position.
2. ADF Button -- SELECT ADF mode and note the pointer moves without
hesitation to the station bearing.
Excessive pointer sluggishness,
wavering or reversals indicate a signal that is too weak or a system
malfunction.
53-7
1 April 1998
For Training Purposes Only
S3
MODEL 208 (675 SHP)
KR-B7 ADF/KI227~01INDICATOR
POH SUPPLEMENT
TO OPERATE BFO:
1. OFFIVOL Control -- ON.
.(
2. BFO Button -. PRESS on.
3. ADF SPEAKER/PHONE Selector Buttons (on audio control panel) •.
SET to desired mode.
4. VOL Control ·· ADJUST to desired listening level.
NOTE
A 1000· Hz tone and Morse Code identifier is heard in the audio
output when a CW signal is received.
(
TO OPERATE FLIGHT TIMER :
(
1. OFFIVOL Control·· ON.
2. FLTfET Mode Button .. PRESS (once or twice) until FLT is annunciated.
Timer will already be counting since it is activated by turning the unit
on.
3. OFFIVOL Control .- OFF and then ON if it is desired to reset the flight
timer.
TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY:
1. OFFIVQL Control·· ON.
2. ADF Button -- SELECT ANT mode.
3. Frequency Selector Knobs .- SELECT desired frequency in the standby
frequency display.
4. FRO Button _. PRESS to move the desired frequency from the standby
to the active position.
5. ADF SPEAKER/PHONE Selector Buttons (on audio control panel) . SET to desired mode.
6. VOL Control .- ADJUST to desired listening level.
TO OPERATE ELAPSED TIME TlMER·COUNT UP MODE :
1. OFFIVOL Control·· ON.
2. FLT/ELT Mode Button . - PRESS (once or twice) until ET is
annunciated.
3. SETfRST Button .- PRESS untillhe ET annunciation begins to flash.
4. SETfRST Button .- PRESS to start timer.
5. SETfRST Button .- PRESS to stop timer. Timer will reset zero . When
the. SETfRST button is released the timer will start to count again
unless the SETfRST button is held until the ET annunciation flasheq.
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\ ,(
1 April 1998
S3-8
For Training Purposes Only
(
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KR-87 ADF/K1227-01 INDICATOR
POH SUPPLEMENT
S3
MODEL 208 (675 8HP)
NOTE
The Standby Frequency which is in memory while Flight Time or
Elapsed Time modes are being displayed may be called back by
pressing the FRQ button, then transferred to active use by
pressing the FRO button again.
TO OPERATE ELAPSED TIME TIMER-COUNT DOWN MODE:
(
1. OFFIVOL Control -- ON.
2. FLTIEL T Mode Button -- PRESS (once or twice) until ET is
annunciated.
3. SETfRST Button -- PRESS until the ET annunciation begins to flash.
4. FREQUENCY SELECTOR KNOBS -- SET desired time in the elapsed
time display. The $mall knob is pulled out to tune the 1's. The small
knob is pushed in to tune the 10's. The outer knob tunes minutes up
to 59 minutes.
NOTE
. Selector knobs remain in the time set mode for 15 seconds after
the last entry or until the SETfRST, FLTfET or· FRO button is
pressed.
5. SETfRST Button -- PRESS to start countdown. When the timer reaches
0, it will start to count up as display flashes for 15 second~.
NOTE
(
(
While FLT or ET are displayed, the active frequency on the left
side of the window may be changed, by using the frequency
selector knobs, without any effect on the stored standby
frequency or the other modes.
ADF OPERATION NOTES:
ERRONEOUS ADF BEARING DUE TO RADIO FREQUENCY PHENOMENA:
f
\
(
In the U.S., the FCC, whichas&.igns AM radio frequencies, occasionally will
assign the same frequency to more than one station in an area. Certain
conditions, ·such as Night Effect, may cause signals from such stations to
overlap. This should be taken into consideration when using AM broadcast
station for navigation.
Sunspots and atmospheric phenomena may occasionally distort reception so
that signals from two staUons on ' the same frequency will overlap. For this
reason, it is always wise to make positive identification of the station being
tuned, by switching the function selector to ANT and listening for station call
letters.
83-9
1 April 1998
For Training Purposes Only
S3
MODEL 208 (675 SHP)
KR-87 ADF/KI 227-01 INDICATOR
POH SUPPLEMENT
(
ELECTRICAL STORMS:
In .the vicinity of electrical storms, an ADF indicator pointer tends to swing
from the station tuned toward the center of the storm.
(
NIGHT EFFECT:
(
This is a disturbance particularly .strong just after sunset 'and just after dawn.
An ADF indicator pOinter may swing erratically at these times. If possible,
tune to the most powerful station at the lowest frequency. If this is not
possible, take the average of pointer oscillations to determine relative station
bearing.
(
(
MOUNTAIN EFFECT:
Radio waves reflecting from the surface of mountains may cause the pointer
to fluctuate or sho"" an erroneous bearing. This should be taken into account
when taking bearings over mountainous terrain.
.
(
(
COASTAL REFRACTION:
Radio waves may be refracted when passing from land to sea or when
moving parallel to the coastline. This also should be taken Into account.
(
(
SECTION 5
PERFORMANCE
(
(
The is no change to the airplane performance when this avionics equipment
is installed: However, the installation of an externally mounted antenna or
related external antennas, will result in a minor reduction in cruise
.
performance.
(
(
(
S3-10
1 April 1998
For Training Purposes Only
(
(
~
(
(
CeSSri8
(~
A Te"',on Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 4
BENDIX/KING DUAL DIGITAL ADF SYSTEM
(TYPE KR.,87 with KI 228-01 INDICATOR)
(
(
(
('. --'.:
':~,/~.)
SERIAL NO.
(
REGISTRATION NO.
(
This·supplement must be ins'erted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King Dual Digital ADF
System (Type KR·87 with 228-01 Indicator).
(
(
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( (~j
(
APPROVED
B*dtffi~...,t1,".f
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
7 APRIl.. 1998
COPYRIGHT 01998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of G~MA
1 APRIL 1998
01352-54-00
(
S4·1
For Training Purposes Only
S4
MODEL 208 (675 SHP)
DUAL KR-87 ADF/K1228-01 INDICATOR
POH SUPPLEMENT
(
(
(
SUPPLEMENT 4
(
BENDIX/KING DUAL DIGITAL ADF SYSTEM
(
(TYPE KR-87 with KI 228-01 INDICATOR)
(
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
(
(
(
(
(
LOG OF EFFECTIVE PAGES
(
S4~1
PAGE
DATE
thru S4-10
1 April 1998
(
REV. NUMBER
(
0
(
(
(
(
(
(
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(
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,
i
\.. ..
1 April 1998
54-2
For Training Purposes Only
(
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(
DUAL KR-87 ADF/K1228-01 INDICATOR
POH SUPPLEMENT
S4
MODEL 208 (675 SHP)
(
SUPPLEMENT
(
BENDIX/KING DUAL DIGITAL ADF SYSTEM
(TYPE KR-87 with K1228-01 INDICATOR)
SECTION 1
GENERAL
The Bendix/King Digital ADF is a panel-mounted, digitally tuned automatic
direction finder. It is designed to provide continuous 1-kHz digital tuning in
the frequency range of 200 kHz to 1799 kHz and eliminates the need for
mechanical band switching. The Dual Digital ADF system is comprised of two
receivers, two built-in electronics timers, two KA-44B combined loop and
sense antennas, and one dual-painter bearing indicator.
The system
incorporates a KI 228-01 Indicator in conjunction with a KCS 55A Compass
System. The compass card on the KI 228-01 Indicator is synchronized to the
KI 525A Compass Card by rotating the Sync Knob of the KI 228-01 Indicator,
until the reading matches that of the KI 525A Compass Card. Once aligned,
the two compass cards will track concurrently.
Operating controls and
displays for the Bendix/King Djgital ADF are shown and described in Figure 1.
The audio system used with this ADF system for speaker-phone selection is
shown and described in the Bendix/King Audio Control System (Type KMA-24
or KMA-24H-70) supplements in Section 9 of this handbook.
The Bendix/King Digital ADF can be used for position plotting and homing
procedures; and for aural reception of amplitude-modulated (AM) signals.
(
The "flip-flop" frequency display allows switching between pre-selected
"STANDBY" and "ACTIVE" frequencies by pressing the frequency transfer
button. Both pre-selected frequencies are stored in a non-volatile memory
circuit (no battery power required) and displayed in self-dimming gas
discharge numerics. The active frequency is continuously displayed in the left
window, while the right window will display either the standby frequency or the
selected readout from the built-in electronic timer.
The built-in electronic timer has two separate and independent timing
functions. An automatic flight timer that starts whenever the unit is turned on.
This timer functions up to 59 hours and 59 minutes. An elapsed timer which
will count up or down for up to 59 minutes and 59 seconds. When a preset
time interval has been programmed and the countdown reaches :00, the
display will flash for 15 seconds. Since both the flight timer and elapsed timer
operate independently, it is possible to monitor either one without disrupting
the other. The pushbutton · controls and the bearing indicators are internally
lighted. Intensity is controlled by the RADIO light dimming rheostat.
S4-3
1 April 1998
For Training Purposes Only
S4
MODEL 208 (675 SHP)
1
KR-87
RECEIVER ·
(ADF 1 or ADF 2)
(
DUAL KR-87 ADF/KI228-01 INDICATOR
POH SUPPLEMENT
3
2
13
12
4
11
5
10
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6
9
8
7
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15
(
(
16
14
(
18
(
K1228-01 INDICATOR
066-1072-04
066-3059-01
Figure 1. Bendix/King Digital ADF Operating
Controls/Indicators (Sheet 1 of 3)
1 April 1998
S4-4
For Training Purposes Only
\..
DUAL KR-87 ADF/K1228-01 INDICATOR
POH SUPPLEMENT
54
MODEL 208 (675 SHP)
MODE ANNUNCIATOR -- Antenna (ANT) is selected by the "out"
position of the ADF button. This mode improves the aural reception
and is usually used for station identification. The bearing pointer is
deactivated and will park in the 90° relative position. .Automatic
Direction Finder (ADF) mode is selected by the depressed position of
the ADF button. This mode activates the bearing pointer. The bearing
pointer will point in the direction of the station relative to the aircraft
heading.
ACTIVE FREQUENCY DISPLAY -- The frequency to which the ADF is
tuned is displayed here. The active ADF frequency can be changed
directly when either of the timer funCtions are selected.
BEAT FREQUENCY OSCILLATOR (BFO) -- The BFO mode, activated
and annunciated when the "BFO" button is depressed, permits the·
carrier wave and associated morse code identifier broadcast on the
carrier wave to be heard.
NOTE
CW signals (Morse Code) are unmodulated and no audio will be
heard without use of BFO. This type of signal is not used in the
United States air navigation. It is used in some foreign countries
and marine beacons.
(
.
(
....... '..•. :\
.
4. STANDBY FREQUENCY ANNUNCIATION (FRQ) -- When FRQ is
displayed the STANDBY frequency is displayed in the right hand
display. The STANDBY frequency is selected using the frequency
The selected STANDBY frequency is put into the
select knobs.
ACTIVE frequency windows by pressing the frequency transfer button.
5. STANDBY FREQUENCY DISPLAY -- Either the standby frequency, the
flight timer, or the elapsed time is displayed in this position. The flight
timer and elapsed timer are displayed replacing the standby frequency
which goes into "blind" memory to be called 'back at any time by
depressing the FRQ button . Flight time or elapsed time are displayed
and annunciated alternatively by depressing the FLT/ET button_
6. TIMER MODE ANNUNCIATION -- Either the elapsed time (ET) or flight
time (FLT) mode is annunciated here_
7. FREQUENCY SELECTOR KNOBS -- Selects the standby. frequency
when FRQ is displayed and directly selects the active frequency
whenever either of the time functions is selected. The frequency
selector knobs may be rotated either clockwise or counterclockwise.
The small knob is pulled out to tune the 1's. The small knob is pushed
in to tune the 1D's. The outer knob tunes the 1~O's with rollover into
the 1000's. These knobs are also used to set the desired time when
the elapsed timer is used in the countdown mode.
Figure 1. Bendix/King Digital ADF Operating Controls/Indicators
(Sheet 2 of 3)
S4-5
1 April 1998
For Training Purposes Only
54
MODEL 208 (675 SHP)
(
DUAL KR-87 ADF/KI 228-01 INDICATOR
POH SUPPLEMENT
(
8. OFFIVOLUME CONTROL .(OFFIVOL) -- Controls primary power and
audio output level. Clockwise rotation from OFF position applies
primary power to the receiver; further clockwise rotation increases .·
audio level. Audio muting causes the audio output to be muted unless;
the receiver is locked on a valid station.
(
(
(
(
9. SETfRESET BUnON (SETfRST) -- The set/reset button when pressed
resets the elapsed timer whether itis being displayed or not.
10. FLIGHT TIME/ELAPSED TIME MODE SELECTOR BUTTON (FLT/ET) -The Flight Timer/Elapsed Time mode selector button when pressed
alternatively selects either Flight Timer mode or Elapsed Timer mode.
.(
(
(
11. FREQUENCY TRANSFER BUTTON (FRQ) -- The FRO transfer button
when Pressed exchanges the active and standby frequencies. The new
frequency becomes active and the former active frequency goes into
standby.
(
12. BFO BUTTON -- The BFO button selects the BFO mode when in the
depressed position. (See note under item 3).
13. ADF BUTTON -- The ADF button selects either the ANT mode or the
ADF mode. The ANT mode is selected with the ADF button in the out
Position. d Th~. ADF mode is selected with the ·ADF button in the
d epresse poSition.
(
I. '
.(
14. SINGLE-BAR POINTER -- Indicates magnetic bearing to the ADF
station tuned 6n ADF 1.
15. HEADING INDEX -- Indicates airplane magnetic heading on the azimuth
card.
16. ROTATING AZIMUTH (COMPASS) CARD -- Rotates as the airplane
turns so that the airplane magnetic heading is continuously displayed at
the heading index.
(
17. DOUBLE-BAR POINTER - Indicates magnetic bearing to the ADF
station tuned on ADF 2.
(
18. SYNC KNOB -- Used to manually rotate compass card to synchronize
Once synchronized, compass card will
with airplane · heading.
continuously display aircraft heading.
Figure 1. Bendix/King Digital ADF Operating Controls/Indicators
(Sheet 3 of 3)
S4-6
1 April 1996
For Training Purposes Only
(
(
(
'';;::;r
DUAL KR-87 ADF/KI 228-01 INDICATOR
POH SUPPLEMENT
(
(
(
S4
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
(
There are no changes to the airplane Limitations when this avionics
equipment is installed.
SECTION 3
EMERGENCY PROCEDURES
There are no changes to the airplane Emergency Procedures when this
avionics equipment is installed.
(
(
SECTION 4
NORMAL PROCEDURES
/
\
TO OPERATE AS AN AUTOMATIC DIRECTION FINDER:
(
( C',." )·
"
(
(
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(
(
(
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1. OFFIVOL Control -- ON.
2. Frequency Selector Knobs -- SELECT desired frequency in the standby
frequency display.
.
3. FRO Button -- PRESS to move the desired frequency from the standby
to the active position.
4. ADF SPEAKER/PHONE Selector Switch (on audio ' control panel) -SELECT as desired.
5. OFFIVOL Control -- SET to desired volume level.
6. ADF Button -- SELECT ADF mode and' note relative bearing on
indicator.
ADF TEST (PRE-FLIGHT or IN-FLIGHT):
1. ADF Button -- SELECT ANT mode and note pointer moves to 90°
position.
2. ADF Button -- SELECT ADF mode and note the pointer moves without
Excessive pointer sluggishness,
hesitation to the station bearing.
wavering or reversals indicate a signal that is too weak or a system
malfunction.
( (~,j
(
54·7
1 April 1998
For Training Purposes Only
S4
MODEL 208 (675 SHP)
DUAL KR-87 ADF/KI228-01INDICATOR
POH SUPPLEMENT
(
(
(
TO OPERATE BFO:
1. OFFIVOL Control -- ON.
2. BFO Button -- PRESS on.
3. ADF SPEAKER/PHONE Selector Buttons (on audio control panel) -- i
SET to desired mode.
4. VOL Control-- ADJUST to desired listening level.
(
NOTE
A 1000-Hz tone and Morse Code identifier is heard in the audio
output when a CW signal is received.
TO OPERATE FUGHT TIMER:
1. OFFIVOL Control -- ON.
2. FLTfET Mode Button -- PAESS (once or twice) until FlT is annunciated.
Timer · will already be counting since it is activated by turning the unit
on.
3. OFFIVOL Control -- OFF and then ON if it is desired to reset the flight
timer.
TO OPERATE AS A COMMUNICATIONS RECEIVER ONLY:
1. OFFIVOL Control -- ON.
2. ADF Button -- SELECT ANT mode.
3. Frequency Selector Knobs -- SELECT desired frequency in the standby
frequency display.
4. FRQ Button -- PRESS to move the desired frequency from the standby
to the active position.
.
5. ADF SPEAKER/PHONE Selector Buttons . (on audio control panel) -SET to desired mode.
6. VOL Control -- ADJUST to desired listening level.
TO OPERATE ELAPSED TIME TIMER-COUNT UP MODE:
1. OFFIVOL Control -- ON.
2. FLTfELT Mode Button _. PRESS (once or twice) until ET is
annunciated.
3. SETfAST Button -- PRESS until the ET annunciation begins to flash.
4. SETfAST Button -- PAESS to start timer.
5. SETfAST Button -- PRESS to stop timer. Timer will reset zero. When
the SETfRST button is · released the timer will start to count again
unless the SETfRST button is held until the ET annunciation flash
S4-8
1 April 1998
For Training Purposes Only
(
(
(
DUAL KR-87 ADF/KI 228-01 INDICATOR
POH SUPPLEMENT
S4
MODEL 208 (675 SHP)
NOTE
(
The Standby Frequency which is in memory while Flight Time or
Elapsed Time modes are being displayed may be called back by
pressing the FRQ button, then transferred to active use by
pressing the FRQ button again.
(
(
(
TO OPERATE ELAPSED TIME TIMER-COUNT DOWN MODE:
(
1. OFFIVOL Control·· ON.
2. FLTfELT Mode Button •. PRESS (once or twice) until ET is
annunciated.
3 .. SETfRST Button ., PRESS until the ET annunciation begins to flash.
4. FREQUENCY SELECTOR KNOBS .. SET desired time in the elapsed
time display. The small knob is pulled Qut to tune the 1'5. The small
knob is pushed in to tune the 10's. The outer knob tunes minutes up
to 59 minutes.
(
(
(
(
NOTE
(
Selector .knobs remain in the time set mode for 15 seconds after
the last· entry or until the SETfRST, FLT/ET or FRQ button is
pressed.
5. SETfAST Button .. PAESS to start countdown. When the timer reaches
0, it will start to count up as display flashes for 15 seconds.
(
(
NOTE
(
WhileFLT or ET are displayed; the active frequency on the left
side of the window may be changed, by using the frequency
selector knobs, without any effect on the stored standby
frequency or the other modes.
(
(
ADF OPERAION NOTES:
(
ERRONEOUS ADF BEARING DUE TO RADIO FREQUENCY PHENOMENA:
(
In the U.S., the FCC, which assigns AM radio frequencies, occasionally will
assign the same frequency to more than one station in an area. Certain
conditions, such as Night Effect, may cause signals from such stations to
overlap. This should be taken into consideration when using AM broadcast
station for navigation.
(
(
r
( \J./
(
Sunspots and atmospheric phenomena may occasionally distort reception so
that signals from two stations on the same frequency will overlap. For this
reason, it is always wise to make positive identification of the station being
tuned, by switching the function selector to ANT and listening for station call
letters.
.
1 April 1998
84-9
For Training Purposes Only
54
MODEL 208 (675 8HP)
DUAL KR-87 ADF/K1228-01 INDICATOR
POH SUPPLEMENT
ELECTRICAL STORMS:
(
In the vicinity of electrical storms, an AOF indicator pointer tends to swing
from the station tuned toward the center of the storm.
(
(
NIGHT EFFECT:
(
This is a disturbance particularly strong just after sunset and just after dawn.
An ADF indicator pointer .may swing erratically at these times. If possible,
tune to the most powerful station at the lowest frequency. If this is not
possible, take the average of pointer oscillations to determine relative station
bearing.
(
MOUNTAIN EFFECT:
(
(
Radio waves reflecting from the surface of mountains may cause the pointer
to fluctuate or show an erroneous bearing. This should be taken into account
when taking bearings over mountainous terrain.
COASTAL REFRACTION:
Radio waves may be refracted when passing from land to sea or when
moving parallel to the coastline. This also should be taken into account.
(
(
SECTION 5
PER'FORMANCE .
(
The is no change to the airplane performance when this avionics equipment
is installed. However, the installation of an externally mounted antenna or
related external antennas, will result in a minor reduction in cruise
performance.
1 April 1998
84-10
For Training Purposes Only
(
(
(
(
(
("
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT',S
(
BENDIX/KING KCS-55A SLAVED COMPASS
SYSTEM with KI-525A HSIINDICATOR
(
(
(
(
("
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual when the airplane is not equipped with an autopilot system, and
the Bendix/King KCS-55A Slaved Compass System with KI-525A HSI
Indicator is installed,
(
(
(
(
(
(
APPROVED
B*d(ff.i~*,,'t
WendeliW. Corneil
Executive Engineer
Cessna Aircraft Company
Delegation Option Manutacturer eE·3
DATE OF APPROVAL
(
~ '~d
7
APRIl. 19'98
COPYRIGHT ~ 1998
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS, USA
o
Member of GAMA
1 APRIL 1998
D1352·S5·00
S5-1
For Training Purlloses Only
S5
KCS-55A SLAVED COMPASS
POH SUPPLEMENT
MODEL 208 (675SHP)
(
SUPPLEMENT 5
BENDIX/KING KCS-55A SLAVED COMPASS
SYSTEM with KI-525A HSIINDICATOR
I
,
i
to determine the current status
(
of this supplement. Pages affected by the current revision are
indicated by an asterisk CO) preceding the page number.
(
Use the Log of Effective Pages
Revision Level
Date of Issue
o (Original)
·1 April 1998
LOG OF EFFECTIVE PAGES ·
PAGE
S5-1 thru S5-6
DATE
1 April 1998
REV. NUMBER
(
o
(
(
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(
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!
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1 April 1998
S5-2
For Training Purposes Only
(
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KCS-55A SLAVED COMPASS
POH SUPPLEMENT
SUPPLEMENT
(
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(
55
MODEL20B (675 SHP)
BENDIX/KING KCS-55A SLAVED COMPASS
SYSTEM with KI-525A HSIINDICATOR
(
SECTION 1
(
GENERAL
(
The Bendix/King KCS-55A Slaved Compass System with KI-525A HSI
Indicator is designed for aircraft which do not inc9rporate an autopilot system.
The KCS-55A compass system includes a slaving control and compensator
unit, magnetic slaving transmitter and a directional gyro. The information
obtained from the KCS-55A compass system is displayed on the KI-525A
Indicator.
(
(
(
(
(
The panel-mounted KI-525A indicator combines the display functions of both
the standard Directional Gyro and the Course Deviation Indicator's
VOR/LOC/Glideslope information to provide the pilot with a single visual
presentation of the complete horizontal navigation situation.
(
(
(
(
This system also incorporates a slaving meter. This meter indicates any
difference between the displayed heading and the magnetic heading. Right
or up deflection indicates a clockwise error of the compass card. Left or
down deflection indicates a counterclockwise error of the compass card.
Whenever the aircraft is in 'a turn and the compass card rotates, it is normal
for this met~H to show a full deflection to one side or the other.
(
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234
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14
5
(
13
7
12
6
7
B
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11
10
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9
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2685X6014
(
Figure 1. Bendix/King KI-525A HSI Indicator (Sheet 1 of 3)
S5-3
1 April 1998
For Training Purposes Only
S5
MODEL 208 (675 SHP)
KSC-55A SLAVED COMPASS
POH SUPPLEMENT
1.
KI-525A HORIZONTAL SITUATION INDICATOR (HSI) - Provides a
pictorial presentation of airplane deviation relative to VOR radials or
localizer beams.
It also displays glideslope deviations and gives
heading reference with respect to magnetic north. The gyro is driven
electrically.
2.
NAV FLAG - Flag is in view when the NAV receiver signal is
inadequate.
3.
LUBBER LINE - Indicates aircraft magnetic heading on compass card
(10).
4.
HEADING WARNING FLAG (HOG) - When flag is in view, the heading
display is invalid.
5.
COURSE BEARING POINTER - Indicates selected VOR course or
localizer course on the compass card (10) . The selected VOR radial or
localizer heading remains set on the compass card when the compass
card (10) rotates.
6
TO/FROM INDICATOR FLAG - Indicates direction of VOR station
relative to the selected course.
7.
DUAL GLIDESLOPE POINTERS - Indicate on the glideslope scale (8)
airplane displacement from glideslope beam center.
Glideslope _
pointers in view indicate a usable glideslope signal is being received. :'
(Glideslope pointers not shown.)
'
8.
GLIDESLOPE SCALES · - Indicate displacement from glideslope beam
center. A glideslope deviation bar displacement of 2 dots represents
full scale (0.7°) deviation above or below glideslope beam centerline.
9.
HEADING SELECTOR KNOB - POSITIONS THE HEADING BUG (14)
ON COMPASS CARD (10) BY ROTATING THE HEADING SELECTOR
KNOB. THE BUG ROTATES WITH THE COMPASS CARD.
10.
COMPASS . CARD _. Rotates to display heading of airplane with
reference to .Iubber line (3) on GSI.
11.
COURSE SELECTOR KNOB - Positions the course bearing pointer (5)
on the corripasscard (10) by rotating the course selector knob.
12.
COURSE DEVIATION BAR (D-BAR) - The center portion of the omni
bearing pointer moves laterally to pictorially indicate the relationship of
airplane to the selected course.
It indicates degrees of angular
displacement from VOR radials and localizer beams, or displacement in
nautical miles from RNAV courses.
Figure 1. Bendix/King KI-525A HSI Indicator (Sheet 2 of 3)
1 April 1998
S5-4 .
For Training Purposes Only
(
S5
KC8-55A SLAVED COMPASS
POH SUPPLEMENT
(
MODEL 208 (675 8HP)
(
13.COURSE DEVIATION SCALE - A course deviation bar displacement of 5
dots represents full scale (VOR = ± 10°, LOC = ± 2-1/2°, RNAV =
5nm, NAV APR = 1-1 /4nm) deviation from beam centerline.
(
(
(
14.
(
HEADING BUG - Moved by heading selector knob (9) to select desired
heading .
(
Figure 1. Bendix/King KI -525A H811ndicator (Sheet 3 of 3)
(
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2
3
(
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4
( (~ ":
~~,~;
.'.
26B5X6015
(
1.
KA-51B SLAVING ACCESSORY AND COMPENSATOR UNIT - Controls
the KCS-55A Compass System.
2.
MANUAL/AUTOMATIC (FREE/SLAVE) COMPASS SLAVE SWITCH Selects either the manual or automatic slaving mode for the Compass
System.
3.
CW/CCW
COMPASS MANUAL SLAVE SWITCH - With the
manual/automatic compass slave switch in the FREE position, allows
manual compass card
slaving in either the clockwise or
counterclockwise direction. The switch is spring loaded to the center
position.
4.
SLAVING METER - Indicates the difference between the displayed
heading and the magnetic heading.
Up . deflection indicates a
clockwise error of the compass card . Down deflection indicates a
counterclockwise error of the compass card.
Figure 2. KA-51 B Slaving Accessory and Compensator Unit
85-5
1 April 1998
For Training Purposes Only
S5
MODEL 208 (675 SHP)
(
KSC-SSA SLAVED COMPASS
POH SUPPLEMENT
(
(
SECTION 2
(
. LIMITATIONS
There is no change to the airplane limitations when the Bendix/King KCS-55A
Slaved Compass System with KI-525A HSllndicator is installed.
(
SECTION 3
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when the
Bendix/King KCS-55A Slaved Compass System with KI -525A HSI Indicator is
. installed.
SECTION 4
NORMAL PROCEDURES
There is no change to the airplane normal procedures when the Bendix/King
KCS-55A Slaved Compass System with KI-525A HSllndicator is installed.
SECTIONS
PERFORMANCE
(
(
There is no change to the airplane performance when the Bendix/King KCS55A Slaved Compass System with KI-525A HSI Indicator is installed.
(
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1 April 1998
8S-6
For Training Purposes Only
(
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/
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(
CeSSria
(
A T",,~on Compa1l)l .
(
(
Pilot's Operating Handbook and
(
FAA Approved Airplane Flight Manual
(
.
.
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 6
(
(
NORTHERN AIRBORNE TECHNOLOGY
NPX138 FM TRANSCEIVER
(
(
(
( C'"
':
-.~
".i.'.-
(
SERIAL NO.
(
REG ISTRATlON NO.
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual when the airplane is equipped with The Northern Airborne
Technology NPX138 FM Transceiver.
(
(
(
(
APPROVEDBr4md{ff.i~ Hf".f
(
Wendell W, Cornell
Executive Engineer
Cessna Aircraft Company
DelegationOplioll Manufacturer CE·3
(
(
(
(
DATEOFAPPROVAL
(
,
' ",1'9':
(
(
7
APRII../998
COPYRIGHT 1)1996
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
o
Member of GAM A .
1 APRIL 1998
01352-S6-00
56·1
For Training Purposes Only
S6
(
NPX138 FM TRANSCEIVER
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
SUPPLEMENT 6
(
NORTHERN AIRBORNE TECHNOLOGY
NPX138 FM TRANSCEIVER
(
Use the Log of Effective Pages to determine the current status
oJ this supplement. Pages affected by the ·current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
(
LOG OF EFFECTIVE PAGES
PAGE
S6-1 thru S6-4
DATE
1 April 1998
REV. NUMBER
o
(
(
(
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\,
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(
86-2
1 April 1998
For Training Purposes Only
(
S6
NPX138 FM TRANSCEIVER
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
SUPPLEMENT
(
(
/ -"'''' ,
(
(
(
NORTHERN AIRBORNE TECHNOLOGY
NPX138 FM TRANSCEIVER
SECTION 1
GENERAL
(
(
(
(
(
The Northern Airborne Technology NPX138 FM Transceiver is a stand-alone,
panel mount radio used for FM communication within the · high band of the
VHF spectrum. The NPX138 covers a frequency range of 138 MHz to 174
MHz in 5.0/12.5 kHz increments, and each of the 100 available channels is
capable of including a receive frequency and CTCSS tone, transmit frequency
and CTCSS tone, and an alpha/numeric identifier.
The NPX138 FM
Transceiver has separate controls for selecting channel display mode, preset
channels, display brightness, editing mode, receiver volume, channel scan
mode, and guard mode. However, for this installation, all guard features will
not be operational.
SECTION 2
LIMIT ATIONS
(
The NPX Panel Mount Radio Installation and Operation Manual must be
aboard the aircraft whenever the NPX138 FM Transceiver is used for
communications.
(
(
(
NOTE
Operations have been demonstrated to 85 nautical miles, and
drop-outs in signal coverage have been observed in various
quadrants beyond 85 nautical miles.
SECTION 3
EMERGENCY PROCEDURES
There are no changes to the airplane emergency procedures when this
avionic equipment is installed.
S6-3
1 April 1998
For Training Purposes Only
56
MODEL 208 (675 SHP)
(
NPX138 FM TRANSCEIVER
POH SUPPLEMENT
. SECTION 4 '
(
(
..">.
NORMAL PROCEDURES
The operating procedures -are the same as those in the NPX Panel Mount ,
Radio Installation and Operation Manua', except all guard features described I.
will not be operational for this installation .
(
(
(
SECTION 5
PERFORMANCE
(
(
There are no changes to the airplane performance when this aVIOniC
equipment is installed. However, the installation of the externally mounted
antenna will result in a minor reduction in cruise performance.
(
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:..::.,: -
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1 April 1998
S6-4
For Training Purposes Only
(
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~
(
A Textron Company
Cessna
(
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
CESSNA MODEL 208 (675 SHP)
(
SUPPLEMENT 7
(
(
(
AIR CONDITIONING SYSTEM
(Standard 208 Only)
(
(
SERIAL NO.
(
REGISTRATION NO.
(
(
This supplement must be inserted into Section 9 of the Cessna Model20B
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with an air conditioning system.
(
(
APPROVED
(
(
(
(
(
(
B!4eu({PfJ~fW'f
Wendell W. Corneil
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
7
APRIl. 19'38
COPYRIGHT tl1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
C
Member of GAMA
1 APRIL 1998
D1352·S7·00
S7-1
For Training Purposes Only
57
AIR CONDITIONING SY8TEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 7
AIR CONDITIONING SYSTEM
Use the Log of Effective Pages to determine the Current status ~
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revi'slon Level .
Date of Issue
o (Original)
1 April 1998
(
(
(
(
(
LOG OF EFFECTIVE PAGES .
(
PAGE
DATE
S7-1 thru 87-9/87-10
1 April 1998
87-2
For Training Purposes Only
REV. NUMBER
o
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
57
MODEL 208 (675 SHP)
SUPPLEMENT
AIR CONDITIONING SYSTEM
SECTION 1
GENERAL
(
(
(
(
(
(
(
(
The air conditioning system provides comfortable cabin
temperatures during hot weather operations, both on the ground or
in flight. In this system (see (Figure 1), a belt-driven compressor is
located on the engine accessory section. Three evaporator units
with integral blowers are located, one each in the left and right wing
root area, and one in the tail cone behind the aft cabin bulkhead.
The evaporator units direct coolep air to a series of overhead outlets
in the cabin headliner. The system condenser is mounted in the
engine compartment beneath the engine and is provided with an
inlet and an ·outlet in the lower left side of the engine cowling to
supply cooling airflow through the condenser. Refrigerant lines
under the floorboards and in the fuselage sides interconnect the
compressor, evaporators, and the condenser.
Controls for the air conditioning system are located at the lower
edge of the instrument panel directly above the control pedestal.
Controls consist of one three-position, toggle-type air conditioning
switch, and three two-position, toggle-type fan switches. Placing the
three-position switch, labeled OFF, VENTILATE, COOL, from the
OFF position to the COOL position starts the system compressor
and evaporator fans. Placing the switch in the VENTILATE position
activates only the system evaporator fans, providing uncooled
ventilating air to the cabin. The three two-position switches, all
labeled .AC FANS, provide separate HIGH or LOW speed control of
each evaporator fan. System electrical protection is provided by
four 15-ampere "pull-off" type circuit breakers, labeled LEFT VENT
BLWR, RIGHT VENT BLWR, AFT VENT BLWR, and AIR COND
CONT, located on the left sidewall switch and circuit breaker panel.
(
When the air conditioning system is operating, cooled air is supplied
to the cabin through 16 overhead adjustable outlets (one each
above the pilot and front passenger, 11 directly above the rear-seat
passengers, and three directing air forward from the aft cabin
bulkhead).
S7-3
1 April 1998
For Training Purposes Only
S7
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
TO SYSTEM
COMPRESSOR AND
EVAPORATOR
fAN SII ITCHES
COMPRESSOR
CONDENSER
CONDENSER AIR INLET~
(
- A I R DIIlIIIIJII"'I( flll6
CD.
_,
LU1
11'1 _
RIIlIT
IJ'fQJ
(
_'LAlE
TO LEfT
TO AFT
TO RIGHT
EVAPORATOR EVAPORATOR EVAPORATOR
fAN
FAN
fAN
0,
HIGH PRESSURE
SAFETY S~ I TeH
(
'
CONDENSER AIR DUTLET~ ·
RECEI VER/DRYER~~_t'=~~~~~lJ
RETURN AIR FLOII CONTROL
. VALVE INORMALLY SPRINGLOAOED CL05EO-ORA~N OPEN
IIHEN VENTILATING AIR ·
SHUTOFF VAL YE 15 CLOSED
DURING AIR CONDItiONING)
lONE EACH UING)
VENTILATING AIR INLET
( IN UPPERUI NG STRUT
FA IRING!
VENTILATING AIR DOOR
lONE EACH SIDE)
(CLOSED DURING AIR CONDI TIONI NGt
INSTRUMENT PANEL VENT ILAT ING
OUTlET ~NO CONTROL
(ONE EACH SIDE)
ADJUSTA8'LE PILOT AND FRONT
PASSENGER OvERHEAD OUTLETS
lONE EACH. 5IDE)
VENTILATING AIR
I NLET I IN UPPER
t====:::::;~o
. IIING STRUT fAIRING
L
SHUTOFF VALVE
lONE EACH UING)
OVERHEAD
vENT AI R CONTROL
(CLOSED OURING
AI R CONO 1l 10NING)
LEfT EVAPORATOR
1\lITH CONDENSATE DRAIN)
ANO fAN
ADJUSTABLE REAR
PASSENGER OVERHEAO
VENTILATING OUTLETSIS)
RIGHT EVAPORATOR
(II ITH CONDENSATE ORA IN)
AND FAN
NOTE
The reciver/dryer end. Schreder valves
ere acceSSible fol' serviCing through
the engine comportment ; the sight
gless Is Ilccesslble beneath an
Inspection cover behind the front
passenger ' s S811t .
o
AFT CAB I N OUTLETS
RETURN AI R DUCT
AFT EVAPORATOR
IUITH CONDENSATE DRAIN)I~~1ZlIZI_tI
AND fAN
_
RAM AIR fLOIi
RETURN AIR
-
COLO AIR
0Ii0:lIE:
L1DUID REFRIGERANT
(
= . VAPOR REFRIGERANT
(
(
DRAIN LINE
- - - ELECTRICAL CONNECTION
MECHAN I CAL CONNECT I ON
2665T1006
Figure 1. Air Conditioning System
1 April 1998
S7-4
For Training Purposes Only
(
(
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
(
57
MODEL 208 (675 SHP)
(
The pilot's and passenger's overhead outlets are the swivel type for
optimum positioning, and airflow volume is controlled by rotating the
outlet nozzle which controls an internal valve. The three aft cabin
outlets are directionally adjustable; Each rear passenger outlet has
a separate rotary-type control beside the outlet, with positions
labeled AIR ON and AIR OFF, to control airflow volume through the
outlet.
(
(
(
(
(
Access for servicing the system is provided through the engine
cowling to the receiver/dryer and through a .floorboard inspeQtion
cover behind the front passenger's seat to the sight glass and
Schrader valves.
(
(
(
SECTION 2
LIMITATIONS
When the takeoff torque setting per the Engine Torque For Takeoff
chart in Section 5 of the basic handbook is less than 1865 ft. Ibs,
the air conditioner must be turned off for any takeoff or landing
under those conditions.
(
(
(
A WARNING
(
The following placards must be Installed In view
of the pilot.
(
(
WHEN TAKEOFF TORQUE SETIINGS ARE BELOW
1865 FT. LBS, THE AIR CONDITIONER MUST BE OFF
FOR TAKEOFF AND LANDING.
(
(
(
(
(
OPERATION OF THE AIR CONDITIONER MAY CAUSE A
COMPASS DEVIATION OF MORE THAN 10 DEGREES.
(
(
( E:
(
\:"y/
(
(
(
1 April 1998
S7-5
For Training Purposes Only
S7
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when the ;
air conditioning system is installed. ·
\
SECTION 4
NORMAL PROCEDURES
PREFLIGHT INSPECTION
During the preflight (walk around) inspection, open cabin doors to
aid in cool-down of the cabin .before flight. Air conditioning system
components should be inspected as follows:
1. Check compressor condition and drive belt for tightness.
2. Check hoses (where visibility permits) from compressor to the
condenser and evaporators for evidence of damage or
leakage.
3. Check condenser inlet and outlet louvers on lower left side of
cowling for installation, condition, and blockage.
,;
(
(
OPERATION ON GROUND
After preflight inspection and engine start, use the following
procedures for quickest reduction of hot cabin temperatures prior to
takeoff:
Cabin Doors and Windows -- CLOSED.
Instrument Panel Vent Controls -- PUSHED IN.
Overhead Vent Air Outlets -- CLOSE.
Overhead Air Outlets "- OPEN.
Fuel Condition Lever -- ADVANCE as required tor minimum
Ng ot ·54 percent.
6.Air Conditioning Fan Switches -- HIGH.
7. Air Conditioning Switch -- COOL.
1.
2.
3.
4.
5.
(
(
t
\ J
~ •• l.L" "
1 April 1998
S7-6
For Trai?ing Purposes Only
(
57
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
A CAUTION
(
(
Under extremely hot OAT and/or high ground
elevation conditions, the Idle ITT may exceed
(
(
the maximum Idle ITT limitation of 685°C.
(
Advance the fuel condition lever towards HIGH
IDLE to Increase the Idle N~ as required to
maintain a satisfactory ITT (685 C or lower)
(
(
NOTE
(
•
For increased cooling during ground static conditions,
increase Ng to 60-65 percent for a higher air
conditioning compressor RPM.
•
Ground operation of the air conditioner with the propeller
in beta range for prolonged periods will cause the air
conditioning compressor pressure safety switch to
disengage the compressor clutch,and therefore should
be avoided.
•
If the temperature of the air coming from the outlets
does not start to cool within a minute or two, the system
may be malfunctioning and should be turned off.
(
(
(
(
(
(
R After Initial Cool-Down -- REPOSITION air conditioning fan
switches to LOW if desired.
BEFORE TAKEOFF
(
1. Air Conditioner Switch -- AS DESIRED (OFF or VENTILATE
if takeoff torque is below 1865 ft-Ibs). Refer to Section 5 for
takeoff power.
(
{
(
OPERATION IN FLIGHT
(
(
(~;/
Initially, it may be desirable to operate the system with the air
conditioner fans on HIGH for fast cool-down. Later in the flight,
operation of the fans on LOW speed and opening of the overhead
vent air controls may be more comfortable.
(
(
S7-7
1 April 1998
For Training Purposes Only
57
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
During extended flight when temperature and humidity are
extremely high, the evaporator coils may frost over. Normally, the
compressor cycles off when temperatures in the evaporators nears
32°F (O°C). If frost does form as evidenced by reduced cooling
airflow, turn the air conditioner switch to VENTILATE and select the '
This should increase evaporator ,
HIGH speed fan positions.
discharge temperature sufficiently to clear the frost.
NOTE
A high pressure safety switch in the air conditioning system
disengages the compressor clutch and stops system
operation in the event the system becomes overloaded.
The system will cycle on again when the pressure reduces.
However, if cooling ability cannot be restored within a
reasonable 'amount of ,' time , the system may be
malfunctioning and should be turned off.
The blower portion of the system m~y be used anytime air
circulation (outside or cabin air) is desired. This is accomplished by
placing the air conditioner switch in ,the VENTILATE position and
placing the fanswitches in LOW or HIGH positions as desired.
BEFORE LANDING
1. Air Conditioner Switch -- AS DESIRED (OFF or VENTILATE
if takeoff torque under landing conditions would be set below
1865ft-lbs).
AFTER LANDING
1. Air Conditioner Switch -- AS DESIRED.
SECTION 5
PERFORMANCE
There is a 10 FPM reduction in climb performance, 1 to 2 KTAS
decrease in cruise performance, and approximately 1% increase in
fuel required for a given trip as a result of the air conditioner
installation.
1 April 1998
S7-8
For Training Purposes Only
!",
(
AIR CONDITIONING SYSTEM
POH SUPPLEMENT
(
(
This reduction ·in climb and cruise performance may be eliminated
by installation of the condenser duct inlet and exit cover plates
during flights when the air conditioner will not be used .
(
(
.
57
MODEL 208 (675 SHP)
( '\
When the air conditioner is operating (compressor engaged), the
following additional' performance changes are also applicable:
(
(
TAKEOFF
(
The air conditioner installation has no appreciable effect on takeoff
distances.
(
(
. CLIMB
(
When climbing at altitudes . above the critical altitude for 675 SHP
(ITT at maximum climb ITT limit and torque below 1865·ft-lbs), there
is a 25 FPM loss in maximum rate of climb.
(
(
CRUISE
(
(
(~--
(
(
(
When cruising at altitudes where the maximum allowable cruise
power is below the torque limit (as noted in the Cruise Performance
tables in Section 5 of the basic handbook), reduce this setting by 40
ft-Ibs when the air conditioner is operating. This will result in an
approximate 2 KTAS decrease in maximum cruise performance and
a slight increase (1 percent) in fuel required for a given trip.
(
(
(
(
(
(
(
(
(
(J:;CO
(
(
(
S7-9/S7-10
1 April 1998
For Training Purposes Only
·
(
(
(
For Training Purposes Only
(
(
(
(
(
(_
.~
CeSSrii
...
( ..
ATexlron Company
\'"
(
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
CESSNA MODEL 208 (675SHP)
(
(
(
SUPPLEMENT 8
(
(
(
(
(
c.
CARGO DOORS REMOVED KIT
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, ifthe airplane is equipped with a cargo doors removed kit.
(
(
(
APPROVED
(
BY}leytdfi~fAI,'f
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
(
(
DATE OF APPROVAL
7
(
(
(
(
f'
~..,;.;
COPYRIGHT c 1998
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS. USA
APRIl. /998
o
Member of GAMA
1 APRIL 1998
01352-58-00
(
(
88-1
For Training Purposes Only
S8
CARGO DOORS REMOVED KIT
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 8
CARGO DOORS REMOVED KIT
Use the Log of Effective Pages to determine the current status;
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision ·Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
88-1 thru 88-4
DATE
1 April 1998
REV. NUMBER
o
1 April 1998
88-2
For Training Purposes Only
J
CARGO DOORS REMOVED KIT
POH SUPPLEMENT
(
S8
MODEL 208 (675 SHP)
(
SUPPLEMENT
(
(
(
(
,'-
CARGO DOORS REMOVED KIT
\
SECTION 1
GENERAL
Tlie cargo doors removed kit is designed to improve passenger
comfort and facilitate passenger-to"pilot communications ' during
special purpose operations such as skydiving, aerial photography,
emergency air drops, etc. The kit consists of a vented spoiler
installed on the forward cargo door hinges to minimize airflow
buffeting within the cabin with the cargo doors removed.
(
(
SECTION 2
LIMITATIONS
1. Intentional stalls with cargo doors removed prohibited.
2. Removal of the cargo doors requires that the spoiler be
installed.
3. With cargo door removed, maximum airspeed must not
exceed 155KIAS.
4. Removal of the cargo doors is not approved in conjunction
with installation of the amphibian or floatplane options.
A WARNING
With the cargo doors removed and the spoiler
Installed, the following placards must be
installed
1. On aft side of spoiler:
r":
PASSENGER AIRSTAIR DOOR MUST NOT BE OPENED IN
FLIGHT WITH CARGO DOOR REMOVED
~..,,,,,,j
S8-3
1 April 1998
For Training Purposes Only
S8
MODEL 208 (675SHP)
CARGO DOORS REMOVED KIT
POH SUPPLEMENT
2. Adjacent to the static pressure alternate source valve:
CAUTION
WITH CARGO DOORS REMOVED, DO NOT
USE ALTERNATE STATIC SOURCE.
3. On the pilot's instrument panel near the airspeed indicator:.
MAXIMUM AIRSPEED 155 KIAS
WITH CARGO DOORS REMOVED
J
(
(
(
SECTION 3
EMERGENCY PROCEDURES
There are no changes to the airplane emergency procedures when
the cargo doors removed kit is installed.
SECTION 4
NORMAL PROCEDURES
Both cargo doors (upper and lower) must be removed in order to
install the spoiler. Installation of the spoiler substantially reduces
airflow buffeting in the cabin; however, all loose equipment should
be removed ' or secured. Face protection is also recommended for
passengers near the door opening.
With the cargo doors removed kit installed, flight characteristics are
essentially unchanged.
SECTION 5
PERFORMANCE
Airplane performance information ' provided in the basic handbook
does not apply when the airplane ,is flown with the cargo doors
removed kit installed since significant performance decrements ,
result. For example, takeoff distance is increased by as much as \" .(
200 feet, maximum rate of climb is reduced by approximately 150 ' ..
FPM, and cruise speed is reduced by approximately 15 knots.
1 April 1998
S8-4
For Training Purposes Only
(
(
(
~
(
(
(
(
CeSSri8
("
'.
A T""lron Company
-
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP)
(
(
(
SUPPLEMENT 9
(
(
(
(
CARGO POD'
('.
:
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a cargo pod.
(
(
APPROVEDB~~~*,,~'~
(
(
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
(
(
DATE OF APPROVAL
(
(
( '';";...,i..;... i
(
(
7
APR'I..I998
COPYRIGHT c 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS. USA
o
Member of GAMA
1 APRIL 1998
01352·S9·00
S9·1
For Training Purposes Only
59
CARGOpob
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 9
CARGO POD
Use the Log of Effective Pages to determine the current status:
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
DATE
S9-1 thru 89-5/89-6
1 April 1998
REV. NUMBER
o
1 April 1998
89-2
For Training Purposes Only
(
S9
CARGO POD
POH SUPPLEMENT
(
MODEL 208(675 SHP)
(
SUPPLEMENT
(
(
(
- -.
CARGO POD
SECTION 1
GENERAL
(
(
The cargo pod provides additional cargo and baggage space. The
pod attaches to the bottom of the fuselage with screws and can be
removed,if desired, for increased performance and useful load.
The pod is fabricated with a Nomex inner housing,a layer of Kevlar,
and an outer layer of fiberglass.
(
(
(
(
(
(
(
(
(
(
The volume of the cargo pod is 83.7 cubic feet and has a loadcarrying capacity of 870 pounds. The pod is divided into three
separate compartments divided by aluminum bulkheads. Each
compartment has an individual loading door, which is hinged at the
bottom, on the left side q.tthe pod. Each door is secured in the
closed position by two handJes which latch the doors when rotated
90 degrees to the horizontal position. Dimensions of the pod and its
loading door openings are contained in Section 6 of the basic
handbook.
(
Complete instructions for installation and removal of the cargo pod
are contained in the Maintenance Manual. This includes installation
and removal of the DME and transponder antennas mounted on the
bottom of the pod, installation and removal of the fuel drain lines for
the fuel line connector covers, and installation and removal of the
fuel drain lines which are routed from the reservoir tank to the left
side of the pod.
(
(
(
(
(
(
(
(
(
(
{
~
, ·' ~.~:<:'yt·i;
(
(
89-3
1 April 1998
For Training Purposes Only
S9
CARGO POD
POH SUPPLEMENT
MODEL 208 (675 SHP)
SECTION 2
LIMITATIONS
A
WARNING
The following Information must be presented In
the form of placards located on the inside of the
cargo pod doors~
FWD. COMPARTMENT
MAX. WEIGHT 230 LBS.
MAX. FLOOR LOADING
30 LBS. PER SQ. FT.
NO SHARP EDGES
eTR. COMPARTMENT
MAX. WEIGHT 310 LBS.
MAX. FLOOR LOADING
30 LBS. PER SQ. FT.
NO SHARP EDGES
AFT COMPARTMENT
MAX. WEIGHT 280 LBS.
MAX. FLOOR LOADING
. 30LBS. PER SQ. FT.
NO SHARP EDGES
. SECTION 3
EMERGENCY PROCEDURES
INADVERTENT OPENING OF AIRPLANE DOORS IN FLIGHT
CARGO POD DOOR(S) OPEN
1. Airspeed -- MAINTAIN LESS THAN 125 KIAS.
2.
Land -- As soon as practical.
a. Approach -- NORMAL.
b. Landing -- AVOID A NOSE-HIGH FLARE.
1 April 1998
89-4
For Training Purposes Only
(
59
CARGO POD
(
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
(
/ '- '
( f\. .
(
20,000
(
* PROP.ELLER FEATHERED 1_-1-_40
* FLAPS UP * ZERO WIND
18,000
(
16,000
(
(
f-
u.
14,000
z
(
~
a:
a:
(
12,000
LU
f-
(
LU
>
10,000
0
(
III
~
(
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(
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f-
("
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(
8000
(!)
W
:r
6000
4000
(
(
2000
(
a
(
a
5
10
15
20
25
30
35
40
45
50
GRQUND DISTANCE - NAUTICAL MILES
(
26856035
(
(
(
(
(
(
("~,
(
Figure 1. Maximum Glide
(
89-5/S9-6
1 April 1998
(
For Trainine Purposes Only
(
{
For Training Purposes Only
(
(
(
~
(
(
CeSSna
(
A Texln>n Company
(
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
CESSNA MODEL 208 (675 SHP)
(
(
(
SUPPLEMENT 10
(
(
ASTROTECH LC-2 DIGITAL CLOCK
(
(r-'~~
( ~- . ;)
.•.,"',.,'
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with an Astro Tech LC-2 Digita I Clock
(
(
APPROVEDB~U"Rfi(;;M'n'f
(
(
Wendell·W . Cornell
EXBculive Engineer
Cessna Aircraft Company
Delegalion Option Manufacturer CE-3
(
(
DATE OF APPROVAL
(
( r· ,
(
(
~;/
7
COPYRIGHT (J 1998
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS. USA
APRII.I998
o
Member of GAMA
1 APRIL 1998
01352-810-00
{
(
810-1
For Trajning Purposes Only
S10
DIGITAL CLOCK
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 10
ASTRO TECH LC-2 DIGITAL CLOCK
Use the Log of Effective Pages to determine the current status
of this supplement. . Pages affected by the current revision are
. indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
810-1 thru
810-7/810-8
DATE
1 April 1998
REV. NUMBER
o
1 April 1998
810-2
For Training Purposes Only
S1 0
DIGITAL CLOCK
POH SUPPLEMENT
(
(
:
MODEL 208 (675 SHP)
SUPPLEMENT
( "
ASTRa TECH LC-2 DIGITAL CLOCK
\
SECTION 1
GENERAL
(
(
The Astra Tech LC-2 Quartz Chronometer (see Figure 1) is a
precision, solid state time keeping device which will display to the
pilot the time-of"day, the calendar date, and the elapsed time
interval between a series of selected events, such as in-flight check
points or legs of a cross-country flight, etc. These three modes of
operation function independently and can be alternately selected for
viewing on the four digit liquid crystal display (LCD) on the front
face of the instrument. Three push button type switches directly
below the display control all time keeping functions; These control
functions are summarized in Figure 2 and 3.
(
(
(
(
(
(
(
(
(
( ":
\;< "
(
(
The digital display features an internal light (back light) to ensure
good visibility under low cabin lighting conditions or at night. The
intensity of the back light is controlled by the L FLT PANEL lights
rheostat. In addition, the display incorporates a test "function (see
Figure 1) which allows checking that all elements of the display are
operating. To activate the test function, press the LH and RH
buttons at the same time.
(
SECTION 2
LIMITATIONS
(
(
There is no change to the airplane limitations when the digital clock
is installed.
(
(
SECTION 3
(
EMERGENCY PROCEDURES
(
(
(
(
(~"::
There is no change to the airplane emergency procedures when the
digital clock is installed.
(
S10-3
1 April 1998
For Training Purposes Only
S10
DIGITAL CLOCK
POH SUPPLEMENT
MODEL 208 (675 SHP)
rest Mode
Display
",,--Activity Indicator
(Colon I
-A
Timer Mode
Indicator
LH Push
Button
A-
~
'
TIMER
SET
.
§(T/AV
CLOCK
MODE
::JRSI
. .)
.
Clock Mode Indicator
(12 Hour Format Onlyl
n/SV
~
Center Push
Button
AH Push
Button
.
2685X1089
Figure 1. Digital Clock
SECTION 4
NORMAL PROCEDURES
CLOCK AND DATE OPERATION
(
When operating in the clock mode (see Figure 2), the display
shows the time of day in hours and minutes while the activity
indicator (colon) will blink off for one second each ten seconds to
indicate proper functioning. If the RH push button is pressed
momentarily while in the clock mode, the calendar date appears
numerically on the display with month of year to the left of the
colon, and day of the month shown to the right of the colon. The
display automatically returns to the clock mode after approximately
1.5 seconds. However, if the RH button is pressed continuously
longer than approximately two seconds,the display will return from
the date to the clock mode with the activity indicator (colon)
blinking altered to show continuously or be blanked completely
from the display. Should this occur, simply press the RH button
again for two seconds or longer, and correct colon blinking will be
restored.
1 April 1998
S10-4
For Training Purposes Only
t,
(
S10
DIGITAL CLOCK
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
Seconds
Digits
('
(Until
59 min.
59 sec.
(
then min.
digits,
(
(
('
Timer
(
Mode
Indicator
(
(
(
(
(
(
(
(
(
(
(
(
(
LH Button: Sets date and time
of day (when used with
RH) button.
Center Button: Alternately
displays clock or timer
status.
RH Button: Shows calendar
d~te momentarily; display
returns to clock mode after
1.5 seconds
LH Button: Resets timer to
'zero.'
Center Button: Alternately
displays clock or timer
status.
RH Button: Alternately starts
and stops timer; timer starts
from any F.reviously accumulated tota.
Figure 2. Clock Mode
Figure 3. Timer Mode
(
NOTE
(
(
( { :~
{ ~;;:4-
The clock mode is set at the factory to operate in the 24-hour
format. However, 12-hour format operation may be selected by
changing the position of an internal slide switch accessible
through a small hole on the bottom of the instrument case. Notice
that in the 24-hour format, the clock mode indicator does not
appear.
1 April 1998
S10-5
For Training Purposes Only
S10
MODEL 208 (675 SHP)
DIGITAL CLOCK
POH SUPPLEMENT
SETTING CORRECT DATE AND TIME
The correct date and time are set while in the clock mode using the
LH and RH push buttons as follows: press the LH button once to
cause the date to appear with the month flashing. Press the RH \
button to cause the month to advance at one per second (holding
button), or one per push until the correct month appears. Push the
LH button . again to cause the day of month to appear flashing, then
advance as before using RH button until correct day of month appears.
Once set correctly, the date advances automatically at midnight
each day. February 29 of each leap year is not programmed into
the calendar mode, and the date will advance to March 1. This may
be corrected the following day by resetting the mode back to March
1.
Pressing the LH button two additional times will cause the time to
appear with the hours digits flashing. USing the RH button as before, advance the hour digits to the correct hour as referenced to a
known time standard. Another push of the LH button will now cause
the minutes digits to flash . Advance the minutes digits to the next (
whole minute to be reached by the time standard and "hold" the \
display by pressing the LH button once more. At the exact instant
the time standard reaches the value "held" by the display, press the
RH button to restart normal clock timing, which will now be synchronized to the time standard.
In some instances, however, it may not be necessary to advance
the minutes digits of the clock; for example when changing time
zones. In such a case, do not advance the minutes digits while
they are flashing. Instead, press the LH button again, and the clock
returns to the normal time keeping mode without alerting the minutes timing.
TIMER OPERATION
The completely independent 24-hour elapsed time (see Figure 3) is
operated as follow: press the center (MODE) push button until the
timer mode indicator appears. Reset the display to "zero" by press- { .
. \~.
ing the LH button.
1 April 1998
S10-6
For Training Purposes Only
(
510
DIGITAL CLOCK
(
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
(
(
("',
(
(
(
(
(
Begin timing an event by pressing the RH button. The timer will
begin counting in minutes and seconds and the colon (activity
indicator) will blink off for 1/1 0 second each second. When 59
minutes 59 seconds have accumulated, the timer changes to count
in hours and minutes up to a maximum of 23 hours, 59 minutes.
Ouring the count in hours and minutes, the colon blinks off for one
second each ten seconds. .To stop timing the event, press the RH
button once again and the time shown by the display is "frozen."
Successive pushes of the RH button will alternately restart the count
from the "held" total or stop the count at a new total. The hold
status of the timer can be recognized by lack of colon activity, either
continuously on or continuously off. The timer can be reset to
"zero" at any time using the LH button .
(
SECTION 5
PERFORMANCE
(
(
There fs no change to the airplane performance when the digital
clock is installed.
(
(
(
(
~~,.
(
(
(
(
(
(
(
(
(
(
(
(~~~;
(
(
(
51 0-7/51 0-8
1 April 1998
For Training Purposes Only
(
(
(
(
(
('
(
(
(
(
.
(
(
(
(
(
(
(
(
(
For Training Purposes Dilly
(
(
(
~
(
CeSSri8
(
A Texlron COOlpany
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
CE~SNA MODEL 208 (675 SHP)
(
(
(
SUPPLEMENT 11
(
ELECTRIC ELEVATOR TRIM
SYSTEM
(
(
(
SERIAL NO.
(
REGISTRATION NO • .
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the electric elevator trim system.
(
(
(
APPROVED
(
B~4dfJ/:r;;+<*"~'f
Wendell W. Corneil
.
Executive Engineer
Cessna Aircraft Company
DelegalionOplion Manufacturer CE·3
(
(
DATE OF APPROVAL
7 APR11.1998
f) .Member of GAMA
(
(
(
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COPYRIGHT c 1998
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS. USA
1 APRIL 1998
01352-511-00
S11-1
For Training Purposes Only
511
MODEL 208 (675 SHP)
ELECTRIC ELEVATOR TRIM SYSTEM
POH SUPPLEMENT
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SUPPLEMENT 11
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ELECTRIC ELEVATOR TRIM SYSTEM
Use the Log of Effective Pages to determine the current status\·
of this supplement. Pages aHected by the current revision are
indicated by an asterisk (*) preceding the page number.
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Date of Issue
o (Original)
1 April 1998
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811-1 thru
811-5/S11-6
1 April 1998
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S11~2
. 1 April 1998
For Training Purposes Only
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ELECTRIC ELEVATOR TRIM SYSTEM
POH SUPPLEMENT
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511
MODEL 208 (675 SHP)
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SUPPLEMENT
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ELECTRIC ELEVATOR TRIM SYSTEM
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SECTION 1
GENERAL
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The electric elevator trim system provides a simple method of
relieving pitch control pressures without interrupting other control
operations to adjust the manual elevator trim wheel. The system is
controlled by a dual-segmented, 3-position trim ,switch with each
segment labeled DN and UP, a red momentary pushbutton autopilot
disengage/trim disconnect switch labeled APITRIM DISC, and a
"pull-off" type circuit breaker, labeled ELEV TRIM.
The dual
segmented trim switch and pushbutton autopilot switch are located
on t he left control wheel grip; the "pull-off" circuit breaker is on the
left sidewall switch and circuit . breaker panel.
Simultaneously
pushing the dual segments of the trim switch forward to the ON
position moves the elevator trim tabs and the trim wheel in the
"nose down" direction; conversely pulling the dual segments aft to
the UP ppsition moves the tabs and trim wheel in the -"nose up"
direction. The dual segments of the trim switch are spring-loaded to
automatically return to the center off position when they are
released from the DN or UP positions, thus stopping movement of
the trim tabs and elevator trim wheel.
During normal operation of the electriC elevator trim . system, a trim
actuator (which includes an electric motor, a solenoid gear engage
mechanism, and an override slip clutch) moves the trim tabs in the
selected direction. When the dual segments of -the trim switch are
in .the center off position, the trim actuator is disconnected from the
trim system and does not impede manual adjustment olthe trim
tabs by the elevator trim wheel.
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SECTION 2
LIMITATIONS
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There is no change to the airplane limitations when the electric
elevator trim system is installed.
S11-3
1 April 1998
For Training Purposes Only
S11
ELECTRIC ELEVATOR TRIM SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
. (
1. Elevator Control -- OVERPOWER as required. .
2. AlP TRIM DISC PushbuHon -- PUSH and RELEASE.
3. ELEV TRIM Circuit Breaker -- PULL OFF for the remainder
of the flight.
4. Manual Trim -- AS REQUIRED.
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SECTION 4
NORMAL PROCEDURES
BEFORE TAKEOFF
The following electric trim system checks should be made prior to
each flight:
1. Elevator Trim Switch Segments -- INDIVIDUALLY PUSH
FORWARD to ON position and HOLD momentarily,
OBSERVE · NO MOVEMENT of elevator trim wheel, then
release elevator trim switch to center off position.
r
2. Elevator Trim Switch Segments -- .INDIVIDUALLY PULL AFT \
to UP position and HOLD momentarily, OBSERVE NO
MOVEMENT of elevator trim wheel, then release elevator
trim switch to center off pO$ition.
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CAUTION
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If movement of the elevator trim wheel is noted
during steps 1 or 2, the electric elevator trim
system has malfunctioned.
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3. Both Segments of Electric Trim Switch "- PUSH FORWARD
SIMULTANEOUSLY and HOLD .and OBSERVE MOVEMENT of elevator trim wheel and elevator trim tab in proper
direction.
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4. APITRIM DISC Pushbutton -- MOMENTARILY DEPRESS
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while trim is moving and observe that movement of the . ( (
elevator. trim system stops.
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. 811-4
1 April 1998
For Training Purposes Only
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ELECTRIC ELEVATOR TRIM SYSTEM
POH SUPPLEMENT
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S11
MODEL 208 (675 SHP)
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5. Elevator Trim Switch -- RELEASE TO CENTER OFF
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POSIT!ON to reactivate system.
6. Both Segments of Electric Elevator Trim Switch -- REPEAT
steps 3, 4, and 5, inapposite direction.
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it. CAUTION
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If movement of the elevator trim wheel is
observed after the APITRIM DISC pushbutton is
depressed and released during step 4, the
electric elevator trim system has malfunctioned.
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IN FLIGHT
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To operate the electric elevator trim system during flight, proceed as
follows:
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1.
2.
3.
4.
Battery Switch -- ON.
Elevator Trim Circuit Breaker -- PUSH TO RESET, if off.
Dual Segmented Trim Switch -- ACTUATE as desired.
Elevator Trim Position Indicator -- CHECK.
SECTION 5
PERFORMANCE
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There is no change to the airplane performance when the electric
elevator trim system is installed.
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S 11-5/S11-6
1 April 1998
For Training Purposes Only
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For Training Purposes Only
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CeSSri8
A Textron COO1pany
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Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
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CESSNA MODEL 208 (675 SHP)
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SUPPLEMENT 13
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FUEL TOTALIZER SYSTEM
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SERIAL NO.
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REGISTRATION NO.
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This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a fuel totalizer system.
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APPROVED
B!J/e.&ee4~Lt+""f
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
7
APRIl.I998
COPYRIGHT c 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS. USA
f)
Member of GAMA
1 APRIL 1998
D1352-S13-00
813-1
For Training Purposes Only
513
FUEL TOTALIZER SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
SUPPLEMENT 13
(
FUEL TOTALIZER SYSTEM
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(
Use the Log of Effective Pages to determine the current status '.
Pages affected by the current revision are
. indicated by an asterisk (*) preceding the page number.
of this supplement.
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Revision Level
Date of Issue
a (Original)
1 April 1998
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LOG OF EFFECTIVE PAGES
PAGE
813-1 thru 813-4
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DATE
1 April 1998
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REV. NUMBER
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1 April 1998
S13-2
For Training Purposes Only
513
FUEL TOT ALiZER SYSTEM
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
SUPPLEMENT
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. FUEL TOTALIZER SYSTEM
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SECTION 1
GENERAL
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The fuel totalizer system is available to aid the pilot in monitoring
the total fuel consumed each flight. The totalizer system utilizes the
fuel flow indicator system circuitry and an additional signal
conditioner and totalizer indicator to display pounds of fuel
consumed. The indicator (see Figure 1) is located on the right side
of the instrument panel and is labeled . FUEL CONSUMED,
POUNDS. A five-digit display is centered in the indicator. The
display can be reset by means of a display reset pushbutton
mounted to the left of the display. A display pushbutton lock located
below the pushbutton can be rotated to engage the button and
prevent inadvertent zeroing of the display. The fuel flow indicator
and fuel totalizer. systems are protected by "pull-off" type circuit
breakers labeled FUEL FLOW and FUEL TOTAL, respectively.
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In operation, the fuel flow transducer in the standard fuel system
generates an electrical signal which is proportional to fuel flow rate
and transmits this signal ·to the standard fuel flow indicator where it
is registered in pounds per hour. The voltage output from the fuel
flow indicator is then sent to a totalizer signal conditioner where it is
conditioned and sent to the fuel totalizer indicator which displays its
value to the pilot in total pounds of fuel consumed.
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FUEL CONSUMED
DISPLAY RESET
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~+--- DISPLAY PANEL
PUSHBUTTON
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PUSHBUTTON - - -
LOCK
(~.
26B5X1088
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Figure 1. Fuel Totalizer Indicator
S13-3
1 April 1998
For Training Purposes Only
S13
MODEL 208 (675 SHP)
FUEL TOTALIZER SYSTEM
POH SUPPLEMENT
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SECTION ·2
LIMITATIONS
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There is no change to the airplane limitations when the fuel totalizer
system is installed.
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SECTION 3
EMERGENCY PROCEDURES
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There is no change to the airplane emergency procedures when the
fuel totalizer system is installed.
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SECTION 4
NORMAL PROCEDURES
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Depending on pilot preference, the fuel totalizer indicator display
can be reset to zero prior to flight or after completion of the flight in
preparation for subsequent flight. Also, the indicator might be
zeroed for recording the fuel consumed during separate legs of a
flight. After zeroing the display, -ho additional operation is required
other than monitoring the indicator readout. The indicator display is
reset to zero as follows:
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1. Pushbutton Lock -- ROTATE COUNTERCLOCKWISE to
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unlock pushbutton.
2. Pushbutton -- PRESS to zero display.
3. Pushbutton Lock -- ROTATE CLOCKWISE to lock
pushbutton to prevent inadvertent zeroing of the display.
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SECTION 5
PERFORMANCE
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There is no change to the airplane performance when the fuel
totalizer system is installed.
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1 April 1998
S13-4
For Training Purposes Only
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f:,::"
Cessna
A T",lron Company
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Pilot's Operating Handbook and
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FAA Approved Airplane Flight Manual
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CESSNA MODEL 208 (675 SHP)
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SUPPLEMENT 14
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INFLIGHT OPENABLE
CARGO DOOR
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[ --
t
...;,.,..... ~
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SERIAL NO.
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REGISTRATION NO.
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This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with an inflight openable cargo door.
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APPROVED
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a:iwd(ffJ/: C;:;.4.
900
cr:
BOO
U'l
U'l
UJ
0..
UJ
<..:l
<0:
700
<..:l
600
500
400
300
200
100
a0
1
2
3
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5
6
7
8
9
10
OXYGEN DURATION - (HOURS) lONE PERSON ONLY)
2685T1051
Figure 2. Oxygen Duration Chart
S16-6
1 April 1998
For Training Purposes Only
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2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
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S16
MODEL 208 (675 SHP)
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The Oxygen Duration Chart (Figure 2) . should be used in
determining the usable duration (in hours) of the oxygen supply in
your airplane. The following procedure outlines the method of
finding the duration from the chart.
1. Note the available oxygen pressure shown on the pressure
gauge.
2. Locate this pressure on the scale on the left side of the
chart, then go across the chart horizontally to the right until
you intersect the line representing the altitude at which the
flight will be conducted. After intersecting the . line, drop
read the
down vertically to the bottom of the chart and
duration in hours given on the scale. This duration is for
one person only and will have to be divided by the number
of persons using oxygen to obtain the total
duration in
hours.
3. As an example of the above procedure, 1700 PSI of '
pressure will safely sustain the pilot only, flying at 20,000
feet
altitude, for 6 hours. If a right front passenger is
aboard, the total duration at 20,000 feet altitude for two
persons is 3 hours.
NOTE
Reliance on oxygen available below 200 ' PSI is not
recommended. At this reduced pressure, flow rates are not
predictable.
When ready to,use the oxygen system, proceed as follows:
1. Mask and Hose -- SELECT. Adjust mask to face and adjust
metallic nose strap for snug mask fit.
A WARNING
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Permit no smoking when using oxygen. Oil,
grease, soap, lipstick, lip balm, and other fatty
materials constitute a serious fire hazard when
In contact with oxygen. Be sure hands and
clothing are oil-free before handling oxygen
equipment.
(
2. Delivery Hose -- PLUG INTO OUTLET nearest to the seat
you are occupying.
S16-7
1 April 1998
For Training Purposes Only
S16
2-PORTOXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
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NOTE
When the oxygen system is turned on, oxygen will flow
continuously at the proper rate , of flow for any altitude
without any manual adjustments.
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3. Oxygen Supply Control Knob -- ON.
4. Face Mask Hose Flow Indicator -~ CHECK. Oxygen is
flowing if the indicator is being forced toward the mask.
.
5. Delivery Hose -- UNPLUG from outlet when discontinuing
use of oxygen. This automatically stops the flow of oxygen.
6. Oxygen Supply Control Knob -- OFF when oxygen is no
longer required .
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SECTION 5
PERFORMANCE
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There is no change to the airplane performance when oxygen
equipment is ,installed.
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1 April 1998
S16-8
For Training Purposes Only
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CeSSrii
".;
.... ,' . , /
A Texlron Company
.
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP)
(
SUPPLEMENT 1'7
(
10-PORT OXYGEN SYSTEM
(
(
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f '
\
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model20B
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manuai, if the airplane is equipped with the optional10-port oxygen system.
(
(
(
APPROVED
(
B~4,eeJ/:~4,*M,'f
Wendell W. Cornell
Executive Engineer
,
Cessna Aircralt Company
Delegation Option Manufacturer CE-3
(
(
DATEOFAPPROVAL
7
APRIL. 1998
f)
(
(
(
(
(~j
COPYRIGHT (') 199B
CESSNA AIRCRAFT
COMPANY .
WICHITA, KANSAS, USA
Member of GAMA
1 APRIL 1998
01352-S17-00
S17-1
For Trainine Purposes Only
517
1a-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 17
(
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10-PORT OXYGEN SYSTEM
(
Use the Log of Effective Pages to determine the current statusl
of this supplement. Pages affected by the currerit revision are
indicated by an asterisk (*) preceding thepage number.
(
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Revision Level
Date of Issue
a (Original)
1 April 1998
(
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LOG OF EFFECTIVE PAGES
PAGE
S17-1 thru S17-8
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DATE
1 April 1998
REV. NUMBER
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S17-2
1 April 1998
For Training Purposes Only
517
1O-PORT OXYGEN SYSTEM
POH SUPPLEMENT
(
MODEL 206 (675 SHP)
SUPPLEMENT
(
c···
10-PORT OXYGEN SYSTEM
SECTION 1
GENERAL
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A 10-port oxygen system provides the supplementary oxygen
necessary for continuous flight at high altitude. In this system, a
116.95 cubic foot capacity oxygen cylinder, located in the fuselage
tailcone, supplies the oxygen. Cylinder pressure is reduced to an
operating pressure of 70 PSI by a pressure regulator attached tathe
cylinder.
A shutoff valve is included as part of the regulator
assembly. The system also contains an altitude compensating
regulator, located between the . pressure regulator and the oxygen
supply lines, which varies the flow of oxygen to the masks,
depending on altitude. An oxygen cylinder filler valve is located on
the right side of the airplane (under a cover plate), just aft of the
passenger entry door. Cylinder pressure is indicated by a pressure
gauge located on the overhead console ·above the pilot's and front
passenger's seats. Ten oxygen outlets are provided in the cabin
ceiling, one each just outboard of the pilot's and front passenger's
seats, and one adjacent to each of the aft passenger ventilating air
outlets. However, to meet FAR oxygen requirements, a maximum
of 12 oxygen masks are allowed to be plugged into the oxygen
outlets at a time. One permanent, microphone-equipped mask is
provided for the pilot, and twelve permanent masks are provided for
the passengers. All masks are·the partial rebreathing type, equipped
with vinyl plastic hoses and flow indicators. The oxygen hoses are
the high-flow ·type and are color coded with a blue band adjacent to
the plug-in ·fitting.
NOTE
The pilot's mask is equipped with a microphone to
facilitate use of the radio when using oxygen. An
adapter cord is furnished with the microphoneequipped mask to mate the mask microphone lead
to the microphone jack located on the left side of the
instrument panel. To connect the oxygen mask
microphone, . connect the mask lead to the adapter
cord and plug the cord into the microphone jack.
S17-3
1 April 1998
For Traipinl! Purposes Only
517
(
1O-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
NOTE
(Continued)
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If an optional microphone-headset combination has been in
use, the microphone lead from this equipment is already
plugged into the microphone jack. It will be necessary to
disconnect this lead from ,the microphone jack so that the
adapter cord from the oxygen mask microphone can be
plu~1ged into the jack. A switch is incorporated on the lefthand control wheel to operate the microphone.
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AMBIENT
TEMP (FD)
0
10
20
30
40
FILLING
PRESSURE
, (PSIG)
1650
1700
1725
1775
1825
AMBIENT
TEMP (P)
50
60
70
80
90
FILLING
PRESSURE
(PSIG)
1875
1925
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1975
2000
2050
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Figure 1. Oxygen Filling Pressures
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A remote shutoff valve control in the overhead console above the
pilot's and front passenger's seats is used to shut off the supply of
oxygen to the system when not in use. The control is mechanically
connected to the shutoff valve at the cylinder. With the exception
of the shutoff function, the system is completely automatic and
requires no manual regulation for change of altitude.
(
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The oxygen cylinder, when fully charged, contains 116.95 cubic
feet of aviator's breathing oxygen (Spec. No. MIL-O-2721 0), under
a pressure of 1850 PSI at 70DF (21 DC). Filling pressures will vary,
however, due to ambient temperature in the filling area, and the
temperature rise resulting from compression of the oxygen.
\ ., (-.
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1 April 1998
S17-4
For Training Purposes Only
1a-PORT OXYGEN SYSTEM
POH SUPPLEMENT
(
517
MODEL 208 (675 SHP)
(
-Because of this, merely filling to 1850 PSI will not result in a
properly filled cylinder. Fill to pressures indicated in Figure 1 for
ambient temperatures.
(
A WARNING
011, grease or other lubricants in contact with
oxygen create a serious fire hazard, and such
contact · must be avoided when handling -oxygen
equipment.
(
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SECTION 2
LIMITATIONS
(
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When oxygen is being used by passengers at night, the reading
light above each passenger using oxygen must be turned on in
order to check face mask hose flow indicator.
(
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SECTION 3
EMERGENCY PROCEDURES
[-- :.
~ ..)
There is no change to the airplane emergency procedu res when
oxygen equipment is installed.
(
SECTION 4
(
NORMAL PROCEDURES
(
For FAA requirements concerning supplemental oxygen, refer to
FAR 91.211 . Supplemental oxygen should be used by all occupants
when cruising above 12,500 feet. As described in the Cessna
booklet "Man At Altitude," it is often advisable to use oxygen at
altitudes lower than 12,500 feet under conditions of night flying,
fatigue, or periods of' physiological or emotional disturbances, Also,
the habitual and excessive use of tobacco or alcohol will usually
necessitate the use of oxygen at less than 10,000 feet.
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-'~,J
Prior to flight, check to be sure that there is an adequate oxygen
supply for the trip, by noting the oxygen pressure gauge reading.
and referring to the Oxygen Duration Chart (Figure 2) . Also, check
that the face masks and hoseS are accessible and in good
condition.
517·5
1 April 1998
For Training Purposes Only
517
1O-PORT OXYGEN SYSTEM
POH SUPPLEMENT"
MODEL 208 (675 SHP)
OXYGEN DURATION CHART
(
(116.95 CUBIC FEET CAPACITY)
(
NOTE:
OXYGEN DURATION IN HOURS = TOTAL HOURS DURATION
NUMBER OF PERSONS
(
1800
1700
1600
1500
(
1400
1300
1200
Ui
1100
I
1000
~
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LU
c:
=>
U1
900
(
BOO
(
U1
LU
c:
0..
W
<.::l
cC
<.::l
700
600
500
400
(
300
(
200
(
(
100
(
o0
2
4
6
BID
12
14
16
1B 20
22
OXYGEN DURATION - (HOURS) (ONE PERSON ONLY)
2685T6010
Figure 2. Oxygen Duration Chart
1 April 1998
517-6
For Training Purposes Only
(
S17
1O-PORT OXYGEN SYSTEM
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
(
(
('
\ .
The Oxygen Duration Chart .(Figure 2) should be used in
determining the usable duration (in hours) of the oxygen supply in
your airplane. The following procedure outlines the method of
finding the duration from the chart.
1. Note the available oxygen pressure shown on the pressure
gauge.
2. Locate this pressure on the scale on the left side of the
chart, then go across the chart horizontally to the right until
you intersect the line representing the altitude at which the
flight will be conducted. After intersecting the line, drop
down vertically to the bottom of the chart and read the
duration in hours given on the scale. This duration is for
one person only and will have to be divided by the number
of persons using oxygen to obtain the total duration in hours.
3. As an example of the above procedure, 1700 PSI of
pressure will safely sustain the pilot only, flying at 15,000
feet altitude, for 16 hours. If 9 passengers are aboard, the
total duration at 15,000 feet altitude for 10 persons (pilot and
passengers) is 1.6 hours or 1 hour and 36 minutes.
(
(
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(
(
(
NOTE
(
Reliance on oxygen available below 200 PSI is not
recommended. At this reduced pressure, flow rates are not
predictable.
(
(
When ready to use the oxygen system, proceed as follows:
(
(
1. Mask and Hose -- SELECT. Adjust mask to face and adjust
metallic nose strap for snug mask fit.
(
A WARNING
(
(
(
(
(
(
/'
l,o/
Permit no smoking when using oxygen. 011,
grease, soap, lipstick, lip balm, and other fatty
materials constitute a serious fire hazard when
In con.tact with oxygen. Be sure hands and
clothing are oil-free before handling oxygen
eqUipment.
2. Delivery Hose -- PLUG INTO OUTLET nearest to the seat
you are occupying.
S17-7
1 AprillQ98
For Training Purposes Only
S17
1O-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
When the oxygen system is turned on, oxygen will flow
continuously at the proper rate of flow for ' any altitude
without any manual adjustments.
3. Oxygen Supply Control Knob -- ON.
4. Face Mask Hose ' Flow Indicator -- CHECK. Oxygen is
flowing if the indicator is being forced toward the mask.
5. Delivery Hose -- UNPLUG from outlet when discontinuing
use of oxygen. This automatically stops the flow of oxygen.
6. Oxygen Supply Control Knob -- OFF when oxygen is no
longer required. .
SECTION 5
PERFORMANCE
There is no change to the airplane performance when oxygen
equipment is installed.
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-(
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(
S17·8
1 April 1998
For Training Purposes Only
(
(
(
(
~
(
CeSSrii
( (~')
A Texlron C(JT1pa11y
(
Pilot's Operating Handbook and
(
FAA Approved Airplane Flight Manual
(
(
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 18
(
(
PROPELLER ANTI-ICE SYSTEM
(
(
(
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual if the airplane is equipped with propeller anti-ice.
(
(
(
(
APPROVED
B~&ffi0w+1'" f
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
(
(
DATE OF APPROVAL
(
7
I)
(
(
(
APRII../998
c.".
COPYRIGHT " 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
Member of GAMA
1 APRIL 1998
01352-518-00
S18-1
For Training Purposes Only
518
PROPELLER ANTI-ICE EQUIPMENT
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
SUPPLEMENT 18
(
PROPELLER ANTI-ICE SYSTEM
Use the Log of Effective Pages to determine the current status '
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
DATE
S18-1 thru
S 18-5/S 18-6
1 April 1998
REV. NUMBER
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1 April 1998 .
S18-2
For Training Purposes Only
PROPELLER ANTI-ICE SYSTEM
POH SUPPLEMENT
518
MODEL 208 (675 SHP)
(
SUPPLEMENT
(
(
(
PROPELLER ANTI-ICE SYSTEM
(-':
SECTION 1
GENERAL
The propeller anti-ice system provides a measure of protection for
the propeller blade surfaces if unexpected icing conditions are
encountered. The system is' operated by a three-position toggle
switch, labeled DE-ICE/ANTI-ICE, PROP, on the de-ice/anti-ice
switch panel. When the switch is placed in the AUTO (upper)
position, electric current flows to an anti-ice timer which cycles the
current simultaneously to the heating elements in the anti-ice boots
on the three propeller blades in intervals of 90 seconds on and 90
seconds off.
(
(
(
NOTE
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An oil-operated pressure switch installed in . the electrical
circuit is utilized to prevent activation of the 'propeller antiice system in the AUTO mode without the engine running.
The switch is off when placed in the middle position. In the event of
a malfunction in the anti-ice timer, the switch can be held in the
momentary MANUAL (lower) position to achieve emergency
Operation of the ' anti-ice system can be
propeller anti-icing.
checked by monitoring an ammeter, labeled PROP ANTI-ICE
AMPS, near the upper left corner of the instrument panel. The
system is protected by two "pull-off" type circuit .breakers, a control
circuit breaker labeled PROP ANTI-ICE CONT and a heater circuit
breaker labeled PROP ANTI-ICE. Both circuit breakers are located
on the left sidewall switch and circuit breaker panel.
SECTION 2
LIMITATIONS
(
There is no change to the airplane limitations when the propeller
anti-ice system in installed; intentional flight into known icing
conditions is prohibited, unless a complete flight into known iCing
equipment package is installed.
S18-3
1 April 1998
For Training Purposes Only
S18
PROPELLER ANTI-ICE SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
Flight into known icing conditions is prohibited unless a complete !
. flight into know icing equipment package is installed. If unexpected
icing conditions are encountered, the Inadvertent Icing Encounter
checklist in Section 3 of the basic handbook should be followed . In
additiqn, the following procedure is recommended:
I.
1. Battery Switch -- ON.
2. Prop Anti-Ice Switch -- AUTO (upper position).
3. Prop Anti-Ice Ammeter -- CHECK in green .arc range (20 to
24 amps) during the on portion of the cycle and a zero
reading during the off portion of the cycle.
NOTE
•
To check the heating elements and the anti-ice timer for
one complete cycle, the · system must be left on for
approximately three minutes.
•
In the event of a malfunction .in the anti-ice timer, the
prop anti-ice switch can be held in the MANUAL
position to achieve emergency propeller anti-icing. If
operating in the emergency MANUAL mode, the . pilot
must hold the switch for approximately gO seconds and
repeat this procedure at gO-second intervals.
CAUTION
If the anti-ice . ammeter indicates unusually high
or low amperage (out of the green arc range
limits) anytime during te on portion of a cycle, a
malfunction has occurred. It Is Imperative that
the system be turned off, since uneven antlIcing may result, causing propeller unbalance
and engine roughness. If, after . leaving icing
conditions, engine roughness or vibration
develops or persists that is not traceable to
.icing or another cause, reduce propeller RPM to
smoothest condition, plan a landing at . the
nearest airport, and check the security of the
anti-Ice boots as a possible cause.
1 April 1998
818-4
For Training Pu rposes Only
(
(
SECTION 3
EMERGENCY PROCEDURES
A
(
\,
(
(
(
(
PROPELLER ANTI-ICE SYSTEM
POH SUPPLEMENT
(
(
4. Prop Anti-Ice Switch -- OFF when anti-icing is no longer
.
required.
(
(
(
518
MODEL 208 (675 SHP)
(' "
SECTION 4
NORMAL PROCEDURES
(
There is no change to the airplane normal procedures when the
propeller anti-ice system is installed.
'
(
(
Refer to Section 8 of the ·basic handbook for care and maintenance
of the propeller anti-ice boots.
(
/
(
SECTION 5
(
PERFORMANCE
(
There is no change to the airplane performance when the propeller
anti-ice system is installed.
(
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('.-: ~
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'.
C,,~ , ~-:...~;
:'
S 18-5/S 18-6
1 April 1998
For Tr~injng Purposes Only
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f
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For Training Purposes Only
(
(
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' ~
c-
,CeSSri8
A Textron Company
(
(
Pilot's Operating Handbook and
(
FAA Approved Airplane Flight Manual
(
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 19
(
(
(
(
(
AERO TWIN RUDDER GUST LOCK
.
c-
"
'
\: oJ_._
SERIAL NO.
~J
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual if the airplane is equipped with rudder gust lock. This supplement is
a reissue of PublJcation Number 01342-13, FAA-approved on 22 September
1988 in conjunction with STC SA3649NM and originally issued 3 January
1994. The original approval page of that supplement has been electronically
reproduced on page 519-3 of this supplement.
(
(
(
(
(
APPROVED
(
DATE OF APPROVAL
(
(
(
,
B!:4et4df¥~*,"'.e
Wendell W, Cornell
Executive Engineer
Cessna Aircralt Company
Delegation Option Manufacturer CE-3
(
(
..
7
COPYRIGHT Q1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
APRII,../998
o
Member of GAMA
1 APRIL 1998
01352-S19-00
;'
819-1
For Training Purposes Only
519
AERO TWIN RUDDER GUST LOCK
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
SUPPLEMENT 19
(
AERO TWIN RUDDER GUST LOCK
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original}
1 April 1998
(
(
. (
(
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LOG OF EFFECTIVE PAGES
PAGE
819-1 thru S19-6
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DATE
1 April 1998
REV. NUMBER
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1 April 1998
S19-2
For Training Purposes Only
519
AERO TWIN RUDDER GUST LOCK
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
(
AERO TWIN RUDDER GUST LOCK
(~" '
,
(
"
'
FLIGHT MANUAL SUPPLEMENT APPROVAL
.
AERO TWIN, INC.
(
2404 Merrill Field Dr.
Anchorage, Alaska 99501
(
(
FAA APPROVED
(
AIRPLANE FLIGHT MANUAL SUPPLEMENT
(
FOR
(
CESSNA MODEL 2081208A1208B
(
WITH
(
AERO TWIN RUDDER GUST LOCK
(
(
(
(~~
Reg. No. _ _ _ _ _ _ __
"
Ser. No. _ _ _ _ _ _ __
(
(
This supplement must be attached to the FAA Approved airplane Flight
Manual when the Aero Twin Rudder Gust Lock is installed in accordance
with STC SA3649NM. The, information contained herein supplements or
supersedes the basic manual only in those areae listed herein. For
limitations, procedures. performance and handling/service information not
conlwned in this supplement. 'COnsult the basic Airplane Flight Manual.
(
FAA Approved:
(
Maneger, Aircraft Certif,ication Ol1iC9
Federal, Aviation Administration
Anchorage, Alaska
(
(
SE_P_2_2_'_008_'__
Date: _ _
(
(
(
~7.~
( :~.::
..
Electronic reproduction of the original approval page from
Publication Number 01342-13, FAA approved on 22 September
1988 and originally issued 3 January 1994.
1 April 1998
519-3
..or Tr~ining Purposes Only
S19
MODEL 208 (675 SHP)
AERO TWIN RUDDER GUST LOCK
POH SUPPLEMENT
(
SUPPLEMENT
AERO TWIN RUDDER GUST LOCK
SECTION 1
GENERAL
The Aero Twin Rudder Gust Lock is a positive locking device
consisting of a bracket assembly and a bolt action lock attached to
the rear bulkhead inside the tailcone stinger below the rudder.
When engaged, the rudder is locked in the neutral position. A
placard located below the lock · handle shaft on the left side of the
tailcone explains the operation of the rudder gust lock. The rudder
gust lock is manually engaged and disengaged on the ground by
turning the airfoil-shaped handle mounted on the shaft projecting
from the left side of the tailcone. The lock is engaged by turning
the handle so that its trailing edge points upward at an angle of
about 60 degrees to the horizontal; however, the rudder must be
centered prior to engaging the rudder lock. The lock is manually
disengaged by turning the handle downward so that its trailing edge
points nearly due aft.
(
(
(
The rudder gust lock also has a fail-safe connection to the elevator \. . (
control system to ensure that it will always be disengaged before
(
This fail-safe connection
the airplane becomes airborne.
automatically disengages the lock when the elevator is deflected
upward about one-fourth of its travel from neutral. The pilot is
responsible for disengaging the rudder gust lock during the ·preflight
inspection and operating the fail-safe disengagement mechanism by
momentarily deflecting the elevator to the full up position after the
control lock is removed and before starting the engine. If these
procedures are not followed the rudder and rudder pedals will be
locked in the neutral position making ground steering impOSSible.
In the event that the engagement of the rudder gust lock goes
completely unnoticed and the pilot commences a takeoff run with
the rudder system locked, the upward elevator deflection during
rotation will disengage the rudder gust lock.
Because of the fail-safe system, the elevator lock should always be . (
engaged prior to engaging the rudder lock when securing the l (
airplane after shutdown.
""~ (
(
1 April 199B
819-4
For Training Purposes Only
(
519
AERO TWIN RUDDER GUST LOCK
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
SECTION 2
LIMITATIONS
(
(
(
('
(
There is no change to the airplane limitations when this rudder gust
lock is installed.
(
PLACARDS
(
This placard is required to be installed on the left side of the
tailcone stinger, affixed to rudder lock shaft cover plate:
(
(
""
UNLOCK
(
'" I'
,,"',1'
<:
(
, ~
lOCK
UNLOCK
BEFORE TAXI AND FLIGHT
(
(
(
('
SECTION 3
EMERGENCY PROCEDURES
(
(
There is no change to airplane emergency procedures when -this
rudder gust lock is installed.
(
(
SECTION 4
(
NORMAL PROCEDURES
(
PREFLIGHT INSPECTION
(
(
EMPENNAGE
(
Rudder Gust Lock -- UNLOCK (left side of tailcone stinger).
(
(
C'<,
. ~:...'"
('
S19-5
1 April 1998
For Training Purposes Only
519
AERO TWIN RUDDER GUST LOCK
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
BEFORE STARTING ENGINE
Elevator Control -- FULL UP then RETURN (to trip fail-safe rudder
lock release).
A CAUTION
If the rudder gust lock is not disengaged
manually or by tripping the fail-safe rudder lock
release, steering on the ground by using the
rudder pedals will not be possible.
SHUTDOWN AND SECURING AIRPLANE
Rudder Gust Lock -- LOCK (left side of tailcone stinger).
NOTE
Control lock must be engaged and the rudder must be
centered prior to engaging rudder gust lock.
(
I
\.
(
SECTION 5
PERFORMANCE
There is no change to the airplane performance when this rudder
gust lock is installed.
(
(
(
(
(
(
1 April 1998
819-6
For Training Purposes Only
(
(
~
(
(
(
( '"
;
CeSSri8
A TeKlron Company
;
... ,...
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP)
(
(
(
SUPPLEMENT 20
(
(
STANDBY ELECTRICAL SYSTEM
(
{
(~- .
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a standby electrical system.
(
(
(
APPROVED
(
(
(
DATE OF APPROVAL
7 ApR.! L./998
f)
(
(
B~ddfi~..,,'f
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
..-
l;.;c. .:
COPYRIGHT © 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
Member of GAMA
1 APRIL 1998
01352-820-03
REVISION 3 - 6 FEBRUARY 2001
520-1
For Training Purposes Only
520
MODEL 208 (675 SHP)
STANDBY ELECTRICAL SYSTEM
POH SUPPLEMENT
(
(
SUPPLEMENT 20
(
STANDBY ELECTRICAL SYSrE~
(
Use the Log of Effective Pages to determine the current status 0(this supptement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
13 October 1999
15 March 2000
6 February 2001
Revision 1
Revision 2
Revision 3
(
LOG OF EFFECTIVE PAGES
(
DATE
PAGE
* S20-1 thru S20-2
S20-3 thru S20-4
* S20-5 thru S20-6
* S20-7/S20-8
6 February 2001
1 April 1.998
6 February 2001
6 February 2001
(
REVISION
NUMBER
(
(
3
o
3
3
APPROVED BY
FAA APPROVED tJfrII)ER FAA 21 SUBPART .
'hec..n.ItJtr.nItCo
(
~OpoIoo_"'DOM'''''.-C'
4-u~&""'''E.'''''••'
(
DATE OF APPROVAL
" FE.'6"U~~'( ~oo I
(
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..
(
'-..,:;.'
(
(
6 February 2001
520-2
For Training Purposes Only
(
STANDBY ELECTRICAL SYSTEM
POH SUPPLEMENT
(
520
MODEL 208 (675 SHP)
SUPPLEMENT
(
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(
(
(
(
(
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(
(
SECTION 1
GENERAL
(
(
STANDBY ELECTRICAL SYSTEM
c.-'
(- ;
A standby electrical system (see Figure 1) may be installed for use
as a standby power source in the event the main generator system
malfunctions in flight. The system includes an alternator operated
at a 75-amp capacity rating. The alternator is belt-driven from an
accessory pad on the rear of the engine. The system also includes
an alternator control unit located forward of the circuit breaker
panel, a standby alternator contactor assembly on the left front side'
of the firewall and two switches on the left sidewall switch panel.
The standby system switches are a two-position toggle-type switch,
labeled STBY PWR, and a guarded two-position toggle-type
switch/breaker, labeled .AVIONICS STBY PWR. The guard covering
the standby avionics power switch must be lifted in order to select
. the ON position. Circuit protection and isolation are provided by
two 40-amp circuit breakers, labeled STBY PWR, on the left
sidewall circuit breaker panel. Field excitation to the alternator '
control uoit is supplied through diode logic from either a circuit
breaker in the standby alternator relay assembly. or the KEEP ALIVE
No. 2 circuit breaker in the main power relay box.
System
monitoring is provided by two amber lights, labeled STBY ELECT
PWR ON;md STBY ELECT PWR INOP, in the annunciator panel.
Total amperage supplied from the standby electrical system can be
monitored on the airplane volt/ammeter with the selector switch in
the ALT position,
Any time the standby ~Iectrical system is turned on, standby power
will automatically be supplied to the main buses if system voltage
drops. The AVIONICS STBY PWR switch/breaker and AVIONICS
BUS TIE switch must be ON to utilize the 7S-ampere capacity. Also,
the ·AVIONICS 1 and 2 power switches should 'be OFF to avoid
feeding a possible fault in the primary power system when operating
on standby power. The primary power supply system can be
completely ,isolated by pulling the six 30-ampere bus feeder circuit
breakers in the event of a fault in the primary power relay box.
820-3
1 April 1998
For Training Purposes Only
S20
MODEL 208 (675 SHP)
STANDBY ELECTRICAL SYSTEM
POH SUPPLEMENT
,
(
CODI
~
CI RCUIT BREAKER
(PUl l . OFF PUSH·TO- RESETI
rv
fUSE
BUS BA.R
1M
flES1STOR
*
OIOOf
AEMOTE5EttSE ....- - -. .
FIELD
U NE eotnACTO A
ALTERNATOR
CONTROL UNIT
(
(
(
I
\
BATTERY
BUS
STANDBV' POWER
SWITCH
(
26857008
Figure 1. Standby Electrical System
(
(
(
1 April 1998
S20-4
For Training Purposes Only
(
STANDBYELECTRfcAL SYSTEM
POH SUPPLEMENT
(
520
MODEL 208 (675 SHP)
(
SECTION 2
(
(
(
(_..
\
...
".'
-
(
; When operating on the standby electrical system, the maximum
electrical load is 75 amps from sea level to 21,000 feet. To assure
adequate alternator cooling at higher altitudes, reduce maximum
electrical IO.ad 5 amps per 1000 feet above 21,000 feet up to the
maxim am operating altitude.
SECTION 3
(
EMERGENCY PROCEDURES
(
GENERATOR FAILURE - GENERATOR OFF ANNUNCIATOR
ILLUMINATEO
'
(
(
1. Generator Switch -- TRIP, then RESET.
(
(
If primary poiNer is not restored:
(
(
LIMITATIONS
(~~ ..
2. GEN CONTROL and GEN FLO Circuit Breakers -- RESET
(if tripped) and repeat step 1. .
If GENERATOR OFF annunciator remains illuminated and STBY
ELECT PWR INOP annunciator is illuminated:
(
3. STBY PWR Switch -- OFF, then ON. Check STBY ELECT
PWR INOP annunciator extinguished and STBY ELECT
PWRON annunciator illuminated.
4. AVIONICS STBY PWR and AVIONICS BUS TIE Switches -ON.
5. AVIONICS 1 and 2 Switches -- OFF.
6. Volt/Ammeter -- SELECTALT and verify alternator load is
75 amperes or less. REDUCE LOAD as required to prevent
battery discharge.
(
(
(
(
(
(
If GENERATOR OFF annunciator remains illuminated and STBY I
ELECT PWR ON annunciator is illuminated:
(
(
(,,'./
3. Perform steps 4,5, and 6 above.
S20-5
6 February 2001
For Training Purposes Only
520
MODEL 208 (675 SHP)
STANDBY ELECTRICAL SYSTEM .
POH SUPPLEMENT
(
STANDBY POWER FAILURE - STBY ELECT PWR INOP ANNUNCIATOR ILLUMINATED
.
1.
2.
(
.
STBY PWR Switch -- OFF, then ON.
STBY ELECT PWR INOP Annunciator -- CHECK extin- (
guished.
.
(
/".- ,
If STBY ELECT PWR INOP annunciator remains illuminated:
3.
4.
STBY PWR Switch -- OFF;
Flight -- COMPLETE utilizing primary power.
NOTE
If the STBY ELECT PWR INOP annunciator illuminates, the
alternator system may still be operational. A bus voltage .
surge may have temporarily tripped the ACU (alternator
control unit). If so, the ACU can be restored by cycling the
standby power switch.
SECTION 4
NORMAL PROCEDURES
AFTER ENGINE START
1. STBY PWR Switch --OFF.
2. STBY ELECT PWR INOP Annunciator -- ON.
(
BEFORE TAKEOFF
(
The following functional check of the standby electrical system
should be accomplished before takeoff,and must be completedprior to any icing flight.
1. Standby Power Switch -- ON.
2. Generator -:- - LOAD to approximately 30 amps or greater
(use taxi lights if required).
3. Volt/Ammeter -- SELECT ALT position and verify alternator
output near zero.
4. Generator Switch -- TRIP.
I
(Continued Next Page)
520-6
6 February 2001
For Training Pu rposes Only
(
(
(
(
STANDBY ELECTRICAL SYSTEM
POH SUPPLEMENT
(
S20
MODEL 20S (675 SHP)
(
5. Volt/Ammeter -- CHECK for alternator output and check
voltage approximately one volt less than with generator ON.
(
(
( (~"
NOTE
A fully charged battery will carry part of the electrical
load , when initially switching from generator to
standby alternator power because of the generator's
higher'voltage regulation.
(
(
(
(
6.
7.
S.
9.
(
(
STBY ELECT PWR ON Annunciator -- CHECK ON.
Generator Switch -- RESET.
STBY ELECT PWR ON Annunciator -- CHECK OFF.
Volt/Ammeter Selector Switch -- RETURN tq BATT position.
(
NOTE
(
(
(
(
I
("'
(
(
The STBY ELECT PWR INOP annunciator will not
, illuminate, except in the event of a broken alternator
drive belt, an electrical malfunction in the standby
electrical system, or the Standby Power Switch is OFF.
, 10. STBY PWR Switch -- ON (STSY ELECT PWR INOP
Annunciator -- OFF).
ENGINE SHUTDOWN
(
(
(
(
(
(
(
The standby alternator receives field current from the keep alive 2
circuit so in an emergency condition, the standby alternator can be
brought on line without turning on the batteryswlich.
Normal
engine shutdown procedures call for turning the standby power
switch off prior to shutting the engine down and turning the battery
switch off. If the standby power switch is inadvertently left on,
several of the red lights in the annunciator panel will remain
illuminated after the battery switch is turned off. The illuminated
annunciators ,serve as a reminder to turn off the standby power
switch and thereby preclude draining the airplane's battery.
(
SECTION 5
PERFORMANCE
( CoY>
There is no change to the airplane performance when the standby
electrical system is installed.
'
S20-7/820-S
6 February 2001
For Training Purposes Only
(
(
(
(
(
(
( (
"'C:'r
For Training Purposes Only
~
eessna
A rsldron Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 21
VENTILATION FAN SYSTEM
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a ventilation fan.
c
APPRoveDB:J/e.d4--~-,-
DATE OF APPROVAL .,
(
(
M~'( 2.00\
(
(
(
(
(,.... . .....(
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,
(
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S23-2
4 May 2001
For Training Purposes Only
POINTER 3000-11/4000-11 ELT
POH 8U PPLEMENT
(
9231
MODEL 208 (675 SHP)
SUPPLEMENT ·
(
(
(
1''\
POINTER MODEL 3000-11/MODEL 4000-11
EMERGENCY LOCATOR TRANSMITTER (ELT)
SECTION 1
GENERAL
(
(
(
This supplement provides information which must be observed
when operating the Pointer Model 3000-11/Model 4000-111
Emergency Locator Transmitter (ELT).
(
(
(
(
(
(
(
(
(
(
(
(
I
{ .•..
\.~., '
The Pointer Model 3000-11/Model 4000-11 ELT consists of a self-I
contained dual-frequency solid-state transmitter powered by a
battery pack consisting of five alkaline "C" cell batteries and is
automatically activated by a deceleration sensing inertia "G" switch,
which is designed to activate when the unit senses longitudinal
inertia forces as required in TSO-C91 A.
Also, a remote
switch/annunciator is installed on the top center location of the
copilot's iostrument panel for control of the ELT from the flight crew
station. The annunciator, which is in the center of the rocker
switch, illuminates when the ELT transmitter is transmitting. The
ELT emits an omni-directional signal on the international distress
frequencies of 121.5 MHz and 243.0 MHz. General aviation and
commercial aircraft, the FAA and CAP monitor 121 .5 MHz, and
243.0 MHz is monitored by the military.
The ELT is contained in a high impact, fire 'retardant, waterproof
case with carrying handle and is mounted .behind the aft cabin
partition wall on the right side of the tailcone. To gain access to the
unit, open the zipper in the aft cabin canvas partition. The ELT is
operated by a control panel at the forward facing end of the unit or
by the remote switch/annunciator located on the top center portion
of the copilot's instrument panel (see Figure 1).
( .. .. : Power for the transmitter is provided by an alkaline battery pack
( '-.... inside the transmitter case.
823-3
4 May 2001
For Training Purposes Only
IS23
POINTER 3000-1114000-11 ELT
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
AWAANING
In accordance with FAA regulations, the ELT'sbattery pack
must be replaced after 2 years shelf or service life or for any of
the following reasons:
a. After the transmitter has been used in an emergency
situation (including any inadvertent activation of
unknown duration).
b.
After the transmitter has been operated for more than
one cumulative hour (e.g. time accumulated in several
tests and inadvertent activation of known duration).
c.
On or before ' battery replacement date.
Battery
replacement date Is marked on the battery pack and the
label on the transmitter.
.
(
(
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ON
(
1
A
u
T
0
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•
1
f
L
1\
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T
RESET
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4
3
2
5
2685P6011
2685P6012
{
(
1. REMOTE CABLE JACK --Connects to ELT remote SWitch/annunciator
located on the copilot's instrument panel.
2.
(
ANTENNA RECEPTACLE -- Connects to antenna mounted on top of
tailcone .
.
3. TRANSMITTER ANNUNCIATOR LIGHT -- Illuminates red to indicate the
transmitter is transmitting a distress signal.
(,. .(
....--:..::-~:.:
Figure 1.
ELT Control Panel and Remote Switch/Annunciator
(Sheet 1 of 2)
4 May 2001
523-4
ForTraining Purposes Only
(
(
(
POINTER 3000-11/4000-11 ELT
POH SUPPLEMENT
(
(
4. MASTER FUNCTION SELECTOR SWITCH (3-position toggle switch):
(
AUTO .. '
(
(
(
5231
MODEL 208"(675 8HP)
r"" "
\.
ON ..
(
OFF/RESET --
(
(
Arms transmitter for automatic activation if "G" switch
senses a predetermined deceleration level.
Activates transmitter instantly. Used for test purposes
and if "G" switch is inoperative.
The , ON position
bypasses the automatic activation (The red annunciator
in the center of the remote switch/annunciator should
illuminate).
"
Deactivates transmitter during handling, following "rescue
and to reset the automatic activation function_ (The red
annunciator ' in
the
center
of
the
remote
switchiannunciator should extinguish).
(
\
5. REMOTESWITCH/ANNUNCIATOR (3-position rocker switch):
(
ON -(
(
AUTO ..
(
RESET --
(- (
\,«..
Remotely activates the tranSmitter for test or emergency
situations. Red annunciator in center of rocker switch
illuminates to indicate that the transmitter is transmitting
a distress signal. "
Arms transmitter for automatic activation if "G" switch
senses a predetermined deceleration level.
Deactivates and rearms transmitter after automatic
activation by the "G" switch; " Red annunciator in center
of rocker switch should extinguish.
(
Figure 1.
(
ELT Control Panel and Remote Switch/Annunciator
(Sheet 2 of 2)
(
SECTION 2
LIMITATIONS
(
(
The following information must be present in the form of a placard
located on the upper right side of the aft cabin partition:
(
,
EMERGENCY LOCATOR TRANSMITTER INSTALLED AFT OF THIS
PARTITION MUST BE SERVICED IN ACCORDANCE WITH FAR
PART 91.207
\
(
(
(
(
C-.,
,,:.~.;.. ~.,
The following information must be presented in the form of
placard on the right, outside skin, adjacent to the ELT:
a.
ELT IS LOCATED BEHIND THIS SURFACE
(
(
823-5
4 May 2001
For Training Purposes Only
1523
POINTER 3000-11/4000-11 ELT
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
SECTION 3
(
EMERGENCY PROCEDURES
(
Before performing a forced landing, especially in remote and (
mountainous areas, activate the ELT transmitter by positioning the
remote switch/annunciator to the ON position. The annunciator in
center of rocker switch should be illuminated.
Immediately after a forced landing where emergency assistance is
required, the EL T should be utilized as follows:
(
(
(
(
NOTE
The ELT remote switch/annunciator system could be ,
inoperative if damaged during a forced landing. If
inoperative,the inertia "G" switch will activate
automatically. However, ' to turn the ELT OFF .and ON
again requires manual switching of the master function
selector switch which is located on the ELT unit.
(
(
1. ENSURE ELT ACTIVATION:
(
a. Position remote switch/annunciator to the ON position even
if annunciator light is already on.
b. 11 airplane radio is operable and can be safely used (no
threat of fire or explosion), turn ON and select 121.5 MHz.
If the ELT can be heard transmitting, it is working properly.
c. Ensure that antenna is clear of obstructions.
i
(
(
NOTE
When the ELT is activated, a decreasing tone will be
heard before the typical warbling tone begins.
(
(
2. PRIOR TO SIGHTING RESCUE AIRCRAFT -- Conserve
airplane battery. Do not activate radio transceiver.
3. AFTER SIGHTING RESCUE AIRCRAFT -- Position remote
switch/annunciator to the RESET position and release to the
AUTO position to prevent radio interference. Attempt contact
(
with rescue aircraft with the radio transceiver set to a
frequency of 121.5 MHz. If no contact is established, return i (
the remote switch/annunciator to the ON position immedlately. '«.: ~ ' (
4. FOLLOWING RESCUE -- Position remote switch/annunciator
to the AUTO position, terminating emergency transmissions.
4 May 2001
S23-6
For Training Purposes Only
POINTER 3000-11/4000-11 ELT
POH SUPPLEMENT
(
S231
.
MODEL 20B (675 SHP)
(
(
SECTION 4
(
NORMAL PROCEDURES
(
I\ , '
As long as the remote switch/annunciator is in the AUTO position
and the ELT master function selector switch remains in the AUTO
position, the ELT automatically activates when the unit senses
longitudinal inertia forces as required in TSO-C91 A.
(
(
Following a lightning strike, or an exceptionally hard landing, the
ELT may activate although no emergency exists. If the remote
switch/annunciator illuminates, the ELT has inadvertently activated
itself. Another way to check is to select 121.5 MHz on the radio
transceiver and listen for an emergency tone transmission . If the
remote switch/annunciator is illuminated or an emergency tone is
heard, position the remote switch/annunciator in the RESET position
and release to the AUTO position.
(
(
(
The ELT must be serviced in accordance with FAR Part 91.207.
(
INSPECTIONITEST
(
f'
( (
\., .
(
.
1. The emergency .locator transmitter should be tested every 100
hours.
(
NOTE
(
Test should only be conducted within the first 5
minutes of each hour.
(
(
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(
(
(
(
(
( ,..,,.
2. Disconnect antenna cable from ELT.
3. Turn airplane battery switch and avionics power switches ON.
4. Turn airplane transceiver ON and set frequency to 121.5 MHz.
5. Place remote switch/annunciator in the ON position. The
annunciator should illuminate. Permit only three emergency
tone transmissions, then immediately reposition the remote
switch/annunciator to the RESET position and release to the
AUTO position.
6. Place the ELT master function selector switch in the ON
position. Verify that the transmitter annunciator light on the
ELT and the remote switch/annunciator on the instrument
panel are illuminated.
7. Place. the ELT master function selector swi~ch · in the
OFF/RESET position.
S23-7
4 May 2001
For Trainine: Purposes Only
IS23
MODEL 208 (675 SHP)
POINTER 3000-11/4000-11 ELT
POH SUPPLEMENT
8. Reposition EL T master function selector switch to AUTO.
9. Reconnect antenna cable to ELT.
A CAUTION
A test with the antenna connected should be
approved and confirmed by the nearest control
tower.
NOTE
e.
Without its antenna connected, the ELT will produce
sufficient signal to reach the airplane transceiver, yet it
will not disturb other communications or damage
output circuitry.
e
After accumulated test or operation time equals 1
hour, battery pack replacement is required.
INFLIGHT MONITORING AND REPORTING
(
Pilots are encouraged to monitor 121.5 MHz and/or 243.0 MHz (
while in flight to assist in identifying possible emergency ELT
transmissions.
On receiving a signal, .report the following
information to the nearest air traffic control facility:
(
(
1. Your position at the time the signal was first heard.
2. Your position at the time the signal was last heard.
(
3. Your position at maximum signal strength.
4. Your flight altitude and frequency on which the emergency
signal was heard -- 121.5 MHz or 243.0 MHz. If possible,
positions should be given relative to a navigation aid. If the
aircraft has homing equipment, provide the bearing to the
emergency signal with each reported position.
(
SECTION 5
PERFORMANCE
(
There is no change to the airplane performance data when this
equipment is installed.
4 May 2001
S23-8
For Training Purposes Only
(
.(
(
(
" ;\'0_,
(
(
(
(
(
(
( '-
A TaM'ron Company
(
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
(
CESSNA MODEL 208 (675 SHP) -
(
SUPPLEMENT 24
(
(
BENDIX/KING GPS NAVIGATION SYSTEM
(
(
(
(Type KLN 89B)
c--
\_- -- -
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model20B
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane FIi~ht
Manual, if the airplane is equipped with the Bendix/King GPS Navigation
System (Type KLN 89B). r
(
(
(
APPROVED
(
B:J/e.d<~r;;:;+< .. ~
C'·
Wendell W. Cornell
Execulive Engineer
(
Cessna Alrcrafl Company
Delegalion Option Manufaclurer CE-3
(
DATE OF APPROVAL
7 APRII../998
(
(
(
(
(;-.",
COPYRIGHT "199B
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS. USA
f)
Member of GAMA
1 APRIL 1998
01352·S24-02
REVISION 2 - 16 DECEMBER 1998
(
824-1
For Training Purposes Only
S24
BENDIX/KING KLN 89B (GPS)
POH 8UPPLEMENT
MODEL 208 (675 8HP)
SUPPLEMENT
BENDIX/KING GPS NAVIGATION SYSTEM
(Type KLN 89B)
.(
(
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
25 June 1998
16 December 1998
(
(
Revision 1
Revision 2
LOG OF EFFECTIVE PAGES
PAGE
DATE
824-1 thru824-2
824-3 thru 824-4
* 824-5
824-6 thru 824-8
* 824-9 thru 824-14
16 December 1998
1 April 1998
16 December 1998
1 April 1998
16 December 1998
*
REV. NUMBER
2
0
2
0
2
APPROVEDBV
~)kyt;.~
Q
Wendell W. Comail
Exe~utive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
ICo"'D~1!.ILI~~e
('
\ :. ;;.:.,.'
824-2
16 December 1998
For Training Purposes Orily
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
(
524
MODEL 208 (675 SHP)
(
SUPPLEMENT
(
(
( '--
\.
BENDIX/KING GPS NAVIGATION SYSTEM
(Type KLN 89B)
f
SECTION 1
GENERAL
(
GPS (Global Positioning System) is a three-dimensional (3-D)
precise location and navigation system based on a constellation of
24 satellites orbiting the earth.
Receiver Autonomous Integrity
Monitoring (RAIM) is a function that every IFR-certified GPS receiver
must continuously perform to assure an accurate position. The high
order. of accuracy that is obtained from RAIM availability requires 5
or more satellites in view, or 4 satellites in view and a pressure
altitude input from the airplane's altimeter. If there are not enough
satellites in view to assure the position integrity, the KLN 89B GPS
navigation system notifies the pilot.
(
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~fi
The Bendix/King GPS Navigation System (Type KLN 89B) consists
of a panel-mounted control display unit, an externally-mounted flat
GPS antenna on the top forward portion of the fuselage and GPS
annunciator/switches mounted below the HSI.
The left
annunciator/switch consists of a pushbutton switch labeled GPS
APPROACH, which incorporates a two-segment annunciator labeled
ARM and ACTV. This pushbutton switch manually arms the GPS
approach mode· at a distance greater than 30 NM from an airport
when an approach is loaded in the flight plan for that airport and
illuminates , the ARM annunciator. This pushbutton switch also
disarms the GPS approach mode after it has been manually or
automatically activated and extinguishes the ARM annunciator.
Also, this pushbutton switch cancels the GPS approach active mode
which is automatically engaged by KLN 89B GPS unit and cycles
back to the arm mode and extinguishes the ACTV annunciator while
illuminating the ARM annunciator. The center annunciator consists
of a three-segment annunciator labeled GPS WAYPOINT, MSG and
ALT (GPS WAYPOINT and GPS MESSAGE when the ALT
annunciator is not installed).
i
(
S24-3
1 April 1998
For Training Purposes Only
524
MODEL 208 (675 SHP)
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
The right annunciator/switch consists of a pushbutton switch,
incorporating a two-segment annunciator labeled HSI NAV 1 and
HSI GPS. This pushbutton switch has a press-to-cycle feature that
controls whether NAV 1 or GPS information is being displayed on .
the HSI. The NAV 1 or GPS annunciator will be illuminated to '
indicate which position has been selected.
When the HSI GPS annunciator switch is illuminated, Course
Deviation, To/From and Flag .information from the KLN 89B GPS is
displayed on the HSI. The HSI, while in the enroute mode,
indicates linear distance and has three sensitivity scale settings: ±S
nautical mile (factory default), ±1.0 nautical mile and ±0.3 nautical
mile, full scale deflection. When transitioning to the approach arm
mode, the HSI scale ' factor will change to ±1.0 NM (full scale
deflection) in the next 30 seconds and the ARM annunciator will
illuminate. When transitioning to the approach active mode, the HSI
scale factor will change to ±O.3 NM (full scale deflection) and the
ACTV annunciator will illuminate.
When the autopilot is in the NAV mode, it will couple to NAV 1,
VOA/ILS or KLN 898 GPS, depending on the state of the selector
switch panel.
A single 5-amp circuit breaker labeled GPS/LORAN on the bottom
row breaker panel powers the KLN 89B Navigation System.
Operation of the KLN 89B GPS Navigation System shall be in
accordance with the Bendix/King KLN 89B Pilot's Guide (supplied
with the airplane). The Pilot's Guide should be thoroughly studied
and VFA operations conducted so that you are totally familiar with
the GPS system of naVigation before actually using this equipment
in IFR conditions.
A NavData Card with .a current . database is supplied with the KLN
89B GPS. Since this database information is updated every 28
days, it is important to monitor the database expiration date. Once
the database has expired, the GPS system provides and advisory
message which must be acknowledged by the operator. Although
the system will continue to operate normally, the warning message
will be repeated on each power-up to remind the user that the t' C. .
database is out of date.
. \ ('.. .
S24-4
1 April 1998
For Training Purposes Only
(
S24
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
(
(c··
To eliminate this warning the database must be updated.
update is performed by installing a current NavData Card.
A
(
(
(
CAUTION
The database must be updated only while the
aircraft Is on the ground. The KLN 89B does not
perform any navigation function while the
database Is. being LJpdated.
(
(
This
NOTE
A current database is required by regulation in order to use
the KLN 89B GPS system for non-precision approaches.
SECTION 2
LIMITATIONS
NAVIGATION OPERATIONAL APPROVALS (FOR UNITS WITH
SOFTWARE MODIFICATION 01/05, or 01/06)
The Bendix/King KLN 89B GPS Navigation System is approved
under TSO C 129 A 1, with software modification level 01/05, or
01/06, and meets the requirements for the following operations:
1.
Enroute and Terminal - In accordance with AC20-138A,
provided it is receiving usable navigation information from:
a. GPS (meets requirements of AC90-94)
2.
Non-Precision Approach - In accordance with AC20-138A
and AC90-94 provided the GPS is receiving usable
The ' KLN 89B has been
navigation information.
demonstrated to meet the accuracy specifications for nonprecision GPS approach operations within the conterminous
United States and Alaska.
(Continued Next Page)
824-5
16 December 1998
For Traininl! Purposes Onlv
S24
BENDIX/KING KLN 898 (GPS)
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
(
(
(
(
GPS
APPROACH
HSI
NAV ' l
GPS
WAYPOINT
2
ARM
3
ACTV
4
MSG
6
HSI
GPS
ALT
7
9
WITH ALTITUDE (ALT) ANNUNCIATOR LIGHT INSTALLED
GPS
APPROACH
GPS
WAYPOINT
BE]
GPS
MESSAGE
/
*
I
I
HSI
NAV 1
HSI
GPS
I
I
(
(
6
, * WITHOUT ALTITUDE (ALT) ANNUNCIATOR LIGHT INSTALLED
2685T1040
2685T1041
Figure 1. GPS Annunciator/Switch (Sheet 1 of 3)
1 April 1998
S24-6
For Training Purposes Only
"' (
(,
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
(
S24
MODEL 208 (675 SHP)
(
(
1.
GPS ANNUNCIATOR/SWITCH - The left annunciator/switch labeled
GPS APPROACH consists of a two-segment annunciator/switch
labeled ARM (Armed) and ACTV (Active). The center annunciator
consists of a three-segment annunciator labeled GPS WAYPOINT,
MSG (Message) and ALT (Altitude) . When the altitude function is not
installed, the center annunciator consists of a two-segment
annunciator labeled GPS WAYPOINT (Same) and GPS MESSAGE.
The right annunciator/switch consists of a press-to-cycle pushbutton
selector switch to select NAV 1 or GPS information to be displayed in
the HSI. The switch also incorporates a two-segment annunciator
labeled HSI and HSI GPS.
2.
GPS APPROACH ANNUNCIATOR/SWITCH - Pressing the GPS
APPROACH switch manually selects or disarms the approach ARM
mode and also cancels the approach ACT V mode after being
automatically engaged by the KLN 89B GPS system. Illumination of
the . GPS APPROACH annunciator is controlled through the
annunciator panel Day/Night switch and is only illuminated when the
switch is in the night position. The white background color of the
GPS APPROACH annunciator makes it visible in daylight
3.
ARM ANNUNCIATOR LIGHT - ARM annunciator will illuminate when
the KLN 89B GPS system automatically selects the approach ARM
mode or when the approach ARM mode is manually selected. The
approach ARM mode will be automatically selected when the
airplane ;is within 30 NM of an airport, and an approach is loaded in
the flight plan for that airport.
The approach ARM mode can be
manually selected at a greater distance than 30 NM from the airport
by pressing the GPS APPROACH switch; however, this will not
change the COl scale until the airplane reaches the 30 NM point.
The approach ARM mode can also be disarmed by pressing the
GPS APPROACH switch.
4.
ACTIVE (ACTV) ANNUNCIATOR LIGHT - ACTV annunciator will
illuminate when theKLN 89B GPS system automatically engages the
approach ACTV . mode (the ACTV mode can only be engaged by the
KLN 898 GPS system which is automatic.) To cancel the approach
ACTV mode, press the GPS APPROACH switch, this will change the
mode to · the approach ARM mode and illuminate the ARM
annunciator.
5.
GPS WAYPOINT ANNUNCIATOR LIGHT - GPS WAYPOINT
annunciator will begin to flash approximately 36 seconds prior to
reaching a Direct To waypoint.
Also, when . turn anticipation is
enabled in the KLN 898 GPS unit, the annunciator will begin to flash
20 seconds prior .to the beginning of turn anticipation, then illuminate
steady at the very beginning of turn anticipation.
(
(~ -.
(
~
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c-':
(
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(
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()
I
I
i
Figure 1. GPS Annunciator/Switch (Sheet 2 of 3)
S24-7
1 April 1998
For Training Purposes Only
524
BENDIX/KING KLN 898 (GPS)
POH SUPPLEMENT
MODEL 208 (675 SHP)
6.
MESSAGE (MSG) ANNUNCIATOR LIGHT - MSG (GPS MESSAGE
when the ALT annunciator is not installed) will begin flashing
whenever the message prompt (a large "Moo on the left side of the
screen) on the KLN 898 GPS unit begins flashing to alert the pilot
that a message is waiting. Press the Message (MSG) key to display-(
the message.
If a message condition exists which requires a '
specific action by the pilot, the message annunciator will remain on
but will not flash.
7.
ALTITUDE (ALT) ANNUNCIATOR LIGHT - ALT annunciator
illun;tinates simultaneously with an aural alarm, which is connected to
the audio panel so the alarm is heard through the airplane speakers
or headphones, and activates:
a.
1000 feet prior to reaching the selected altitude -- three short
tones, AL T annunciator illuminates with tones.
b.
Upon reaching the selected altitude -- two short tones , ALT
annunciator illuminates with tones.
c.
Deviating above or below the selected altitude by more than the
warn altitude -- four short tones, ALT annunciator illuminates with
tones.
.
A CAUTION
The altitude alerting feature will only be accurate If the
altimeter baro correction Is kept updated. If altitude
alerting is used, it is a good idea to update the altimeter
baro set on the ALT 1 page each time you make a
change to the airplane's altimeter setting.
NOTE
There may be some difference (less than 100 feet) betwe.en
the indicated .altitude ·and the airplane's actual altitude it the
altitude input to the KLN 89B is from an altitude encoder,
because these encoders only provide altitude in 100 foot
increments.
.
.
8.
9.
HSI NAV 1 ANNUNCIATOR/SWITCH - HSI NAV 1 annunciator will
illuminate steady to inform the pilot that NAV 1. information is being
displayed on the HSI.
(
r
HSI GPS ANNUNCIATOR/SWITCH - HSI GPS annunciator will i
illuminate 'steady to inform the pilot that GPS information is being \. (
displayed on the HSI.
Figure 1. GPS Annunci~tor/Switch (Sheet 301 3)
1 April 1998
S24-8
For Training Purposes Only
(
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
.
(
524
MODEL 208 (675 SHP)
(
OPERATING LIMITATIONS (FOR UNITS WITH
MODIFICATION 01/05, or 01/06)
(
(
1.
The Bendix/King KLN 89B GPS Navigation System Pilot's
Guide, part number 006-08786-0000, dated May 1995 (or
later revision), as applicable to the specific software
modification status, must be immediately available to the
pilot whenever navigation is predicated on use of the GPS
system. The Operational Revision Status (ORS) of .the
Pilot's Guide must match the ORS level annunciated on the
Self Test page. Software level 01105, or 01106 must bel
installed in order to conduct non-precision instrument
approaches. The software level status can be found on
page OTH 6, and must be "HOST 00880-0004" for 18vell
01/05, or "HOST 00880-0005" for level 01/06.
2.
The Bendix/King KLN 89B GPS Navigation System Quick
Reference, Part Number 006-08787-0000, dated May 1995
(or later revision), must be immediately available to the pilot
during instrument approach operations.
3.
The Bendix/King KLN 89B GPS Navigation System must
utilize Operational Revision Status (ORS) level 02 or later
F~A approved revision.
4.
IFR navigation is prohibited unless the pilot verifies the
currency of the database or verifies each selected waypoint
for accuracy by reference to current approved data.
5.
The Bendix/King KLN 89B GPS Navigation System is not
approved for IFR precision approaches (ILS, LOC, LOC-BC,
LOA, SDF and MLS). However, the eqUipment meets FAA
TSOClass A-1 specifications, which approve this unit for
enroute, terminal and non-precision approaches.
6.
Instrument approaches must be accomplished in accordance
with approved instrument approach procedures that are
retrieved from the GPS equipment database. The GPS
equipment database must incorporate the current update
cycle.
7.
Instrument approaches must be conducted in the approach
mode and RAIM must be available at the Final Approach
Fix.
(
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S.OFTWAREI
(Continued Next Page)
I
S24-9
16 December 1998
For Training Purposes Only
S24
MODEL 208 (675 SHP)
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
(
(
(
SECTION '2
LIMITATIONS
('
(continued)
8.
APR ACT V mode must be annunciated at the Final
Approach Fix.
9,
When an alternate airport is required by the applicable
operating rules, it must be served by an approach based on
other than GPS, the airplane must have operational
equipment capable of using that navigation aid, and the
required navigation aid must be operational.
10.
The KLN 89B GPS Navigation System can only be used for
approach guidance if the reference coordinate datum system
for the instrument approach is WGS-84 or NAO-83 (all
approaches in the KLN 89B database use the WGS-84 or
the NAO-83 geodetic datums) . .
11 .
The airplane must have other approved navigation ,'
equipment installed and operating appropriate to the route ot(,
flight.
(
(
(
NAVIGATION OPERATIONAL APPROVALS (FOR UNITS WITH
. SOFTWARE MODIFICATION 02/02)
The Bendix/King KLN 898 GPS Navigation System . is approved
under TSO C129 A 1, with software mod level 02/02, and meets the
requirements for the following operations:
1.
Enroute and Terminal - In accordance with AC20-138A
including BRNAV/RNP5 in accordance with AC90-96 and
JAA AMJ 20X2, provided it is receiving . usable navigation
information from:
(
(
(
(
a. GPS (meets requirements of AC90~94)
\ (
(Continued Next Page)
S24-10
(
16 December 1998
For Training Purposes Only
(
(
BENDIX/KING KLN 898 (GPS)
POH SUPPLEMENT
(
524
MODEL 208 (675 SHP)
(
2.
(
(
(
(4.;
\<
)
Non-Precision Approach - In accordance with AC20-138A
and AC90-94 provided the , GPS is receiving usable
navigation information.
The · KLN 898 has been
demonstrated to meet the accuracy specifications for nonprecision GPS approach operations within the conterminous
United States and Alaska.
OPERATING LIMITATIONS
MODIFICATION 02/02)
(
The Bendix/King KLN 89B GPS Navigation System Pilot's
Guide, part number 006-08786-0000, dated May 1995 (or
later revision), as applicable to the specific software
modification status, must be immediately available to the
pilot whenever navigation is predicted on use of the GPS
system. The Operational Revision Status (ORS) of the
Pilot's Guide must match the ORS level annunciated on the
Self Test page. Software level 02/02 must be installed in
order to conduct non-precision instrument approaches. The
software level status can be found on page OTH 6, and
must be "HOST 00880-0005" and "Rcvr01621-0001".
2.
8endix/King KLN 898 GPS Navigation System Part Number
066-01145-0102 must be installed in .the airplane.
3.
The Bendix/King KLN 898 GPS Navigation System Quick
Reference, Part Number 006-08787-0000, dated May 1995
(or later revision), must be immediately available to the pilot
during instrument approach operations.
4.
The Bendix/King KLN 898 GPS Navigation System must
utilize Operational Revision Status (ORS) level 02 or later
FAA approved revision.
5.
IFR navigation is prohibited unless the pilot verifies the
currency of the database or verifies each selected waypoint
for accuracy by reference to current approved data.
6.
The Bendix/King KLN 898 GPS Navigation System is not
approved for IFR precision approaches (ILS, LOC, LOC·BC,
LOA, SDF, and MLS). However, the equipment meets FAA
TSO Class A-1 specifications, which approve this unit for
enroute, terminal, and non-precision approaches.
(
(
(
(
(
(
(-
\,-
,
(
(
(
(
(
SOFTWARE
1.
(
(
(FOR UNITS WITH
(
(
(«,
S24-11
16 December 1998
For Training Purposes Only
S24
MODEL 208 (675 SHP)
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
7.
Instrument approaches must be accomplished in accordance
with approved instrument approach procedures that are
retrieved from the GPS equipment database. The GPS
equipment database must incorporate the current update ('cycle .
.
8.
Instrument approaches must be conducted in the approach
mode and RAIM must be available at the Final Approach
Fix.
9.
APR ACTV mode must be annunciated at the
Approach Fix.
Final
10.
When an alternate airport is required by the applicable
operating rules. it must be served by an approach based on
other then GPS. the airplane must have operational
equipment capable of using that navigation aid. and the
required navigation aid must be operational.
11.
The KLN 89B GPS Navigation System can only be used for
approach guidance if the reference coordinate datum system
for the instrument approach is WGS·84 or NAD·83 (all (.
approaches in the KLN 898 database use the WGS-84 or
the NAD-83 geodetic datums).
12.
The airplane must have other . approved navigation
equipment installed and operating appropriate to the route of
flight.
SECTION 3
EMERGENCY PROCEDURES
If sensor information is intermittent or lost. utilize remaining
operational navigation (or later revision) supplied with the airplane.
and the current FAA TSO specifications that apply to the use of this
equipment.
16 December 1998
S24·12
For Training Purposes Only
(
524
BENDIX/KING KLN 89B (GPS)
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
SECTION 4
NORMAL PROCEDURES
(
(
""..
( f\;,
(
The Bendix/King KLN 89B GPS Navigation System shall be
operated per the Pilot's Guide, 006-08786-0000, dated May 1995.
A
(
(
The KLN 89B Pilot's Guide supplied with your
. airplane should be thoroughly studied and VFR
operations conducted, so that you are totally
.familiar with the GPS system of navigation
before actually using this equipment in IFR
conditions.
.
(
(
(
(
NOTE
(
(
•
The Autopilot, KFC-150 or Flight Control Systems will
remain coupled to the selected NAV regardless of
whether the NAV information is valid or not (flagged).
It is the
This also applies to GPS operation.
responsibility of the pilot to assure that the NAV
information is valid.
•
The autopilot and flight control
navigation informati~n from the HSI.
•
When operating with the autopilot or flight control
systems coupled and the KLN 898 GPS navigating in
the LEG mode (default mode when the KLN 89B starts
up) the course to the active waypoint is selected by the
GPS navigation system, which is also displayed on the
HSI. The OBS setting should be updated occasionally to
agree with the desired track (Dtk). While navigating in
the OBS mode with the autopilot or flight control systems
coupled, the pilot selects the course "to" or "from" the
This course is then
active waypoint on the HSI.
displayed on the GPS.-mounted antenna or related
external antennas, will result in a minor reduction in
cruise performance.
(
(
(
~.
(
(
(
(
(
(
(
(
(
(
(
(
WARNING
(=...
systems
receive
(
s24-131
16 December 1998
For Training Purposes Only
S24
BENDIX/KING KLN 89B (GPS)
MODEL 208 (675 SHP)
(
POH SUPPLEMENT
(
(
SECTION 5
PERFORMANCE
.(
(
There is no change to the airplane performance when this avionics
equipment is installed.
However, installation of an externallymounted antenna or related external antennas, will result in a minor
reduction in cruise performance.
(
(
(
(
(
(
(
.
(
(
(
(
(
(
(
(
(
(
(
I
I
\;c
(
(
(
IS24-14
16 December 1998
For Training Purposes Only
(
(
(
~
(
(
CeSSri8
(~-
(
A Texlron Company
\~-
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
(
(
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 25
(
(
BENDIX/KING AUDIO CONTROL SYSTEM
(
(Type KMA-24)
(
(
(
(
SERIAL NO.
(
REGISTRATION NO.
(
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a Bendix/King Audio Control
System (Type KMA-24)
(
(
(
APPROVED
(
B:J/e.d{fI'J~k
..."f
Wendell W. Cornell
Executive Engineer
'
Ce,ssna Aircraft Company
Delegation Option Manufacturer CE-3
(
(
DATE OF APPROVAL
7
APR' l.. /998
(
.
(
:; "~M"''''''>'' '
,
COPYRIGHT ('J 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS , USA
o
Member of GAMA
1 APRIL 1998
D1352-S25-00
525-1
For Training Purpos~s Only
525
KMA-24 AUDIO CONTROL SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 25
(
(
(
BENDIX/KING AUDIO CONTROL SYSTEM
(
(Type KMA-24)
(
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
o (Original)
. Date of Issue
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
S25-1thru
. S25-7/S25-8
DATE
1 April 1998
REV. NUMBER
o
(
(
(
(
S25-2
1 April 1998
For Training Purposes Only
KMA-24 AUDIO CONTROL PANEL
POH SUPPLEMENT
(
S25
MODEL 208 (675 SHP)
(
SUPPLEMENT
(
(
(
(
[- -.
~.-.
'.
BENDIX/KING AUDIO CONTROL SYSTEM
(Type KMA-24)
(
with
(
MARKER BEACON RECEIVER
(
SECTION 1
GENERAL
(
(
Two Bendix/King Audio Control Systems are available. The only
difference between the two systems is the choice of the third MIG
function that can be either HF functions (to accommodate a HF
Radio Installation) or TEL functions (to accommodate the Airborne
Radio Telephone Installation).
(
(
(
( / _ Both audio control systems have a combination audio amplifier, an
( : ... ' audio distribution panel, and a marker beacon receiver. The audio
'-. - amplifier is for amplification of the audio signals for the speaker
(
system. All receiver audio distribution functions are controlled by
two
rows of alternate-action pushbuttons. Both rows are completely
(
independent of each other, allowing simultaneous use of speaker
and/or headphones. A rotary selector switch on the right side of the
console connects the microphone to either Telephone (or HF radio),
(
Com 1 or Com 2. Both audio control panels and all operating
controls
are shown and described in Figure 1.
(
(
Whenever the microphone selector switch is placed in the "OFF"
position, power is cut off to the speaker amplifier and the marker
beacon receiver; however, the headphone amplifier remains in
operation.
(
(
(
Separate "Auto" push buttons for speaker and headphones provide
automatic switching of the receiver according to the position of the
microphone selector.
(
( (
(
,
~,~-.-.'
NOTE
Phone sidetone may be selected by pushing the AUTO
selector button in the PHONE position.
525-3
1 April 1998
For Training Purposes Only
S25
MODEL 208 (675 SHP)
KMA-24 AUDIO CONTROL PANEL
POH SUPPLEMENT
(
(
A crystal-controlled superheterodyne marker beacon receiver with 3light presentation is incorporated within the unit. Dimming circuitry
(
for the marker lamps automatically adjusts brightness appropriate to
the cockpit ambient lightleve!. Hi and Lo sensitivity and lamp test .· -'(
functions are also provided.
(
Light dimming for the audio control panel is manually controlled by
the RADIO light dimming rheostat
MARKER FACILITIES
MARKER
IDENTIFYING TONE
(
L1GHT*
Continuous 6 dots/second '
(3000 Hz)
White
72-95 two dot combinations per
minute (3000 Hz)
White
Middle
Alternate dots and dashes
(1300 Hz)
Amber
Outer
2 Dashes/second (400 Hz)
Blue
Airway, Inner
& Fan
Back Course
(
(
(
NOTE
*
(
(
When the identifying tone is keyed, the respective
indicating light will blink accordingly.
(
(
SECTION 2
LIMITATIONS
(
There is no change to the airplane limitations when this avionic
equipment is installed.
(
(
(
SECTION 3
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when this I, (
avionic equipment is installed.
(
1 April 1998
S25-4
For Training Purposes Only
KMA-24 AUDIO CONTROL PANEL
POH SUPPLEMENT
S25
MODEL 208 (675 SHP)
AUDIO CONTROL PANEL WITH TELEPHONE TRANSCEIVER CAPABILITIES
(
1
( C' ;
2
3
4
(
(
7
6
4
5
2685X1055
AUDIO CONTROL PANEL WITH HF TRANSCEIVER CAPABILITIES
1
2
3
4
6
4
(
(
(~ /;
(
7
(
(
2685X1056
1.
MARKER BEACON ANNUNCIATOR LIGHTS:
AIRWAY, INNER and FAN " Light illuminates white to Indicate
passage of airways, ILS inner, fan and back course marker beacons.
OUTER - Light illuminates blue to indicate passage of outer marker
beacon.
MIDDLE - Light illuminates amber to indicate passage of middle
marker beacon.
(
(
(
2.
TEST BUTTON (TST) - Illuminates all marker beacon annunciator
lights in the full bright position to .verify operation of annunciator
lights.
3.
SPEAKER AUDIO SELECTOR BUTTONS (SPEAKER) - Selector
buttons for speaker audio output.
When pressed in, enables
operator to select anyone or more audio signals.
f
(0
5
Figure 1_ KMA-24 System Operating Controls (Sheet 1 of 2)
S25-5
1 April 1998
For Training Purposes Only
525
MODEL 208 (675 SHP)
4.
5.
KMA-24 AUDIO CONTROL PANEL
POH SUPPLEMENT
AUDIO SELECTOR BUnONS (AUTO) - Separate AUTO
pushbuttons ' for speaker and headphones allows automatic
switching of the receiver with rotation of the microphone selector
switch.
(
""--i
MICROPHONE SELECTOR SWITCH (MIC) - Turns on speaker\,
amplifier and marker beacon receiver. Connects the microphone to '-<
TEL (telephone), HF (HF Xcvr) , COM 1 or COM 2. All receiver
(
outputs are electronically muted whenever the microphone is
keyed, to prevent undesirable transmitter feedback. When placed
in the INT position, provides hot mic intercom when control wheel
mic switches and auxiliary mic jacks are installed. The EXT
(
position si not used.
(
NOTE
(
When the optional HF Transceiver radio is installed, the TEL
(telephone) positions are replaced with HF positions on the
audio control panel.
6.
7.
(
(
HEADPHONE AUDIO SELECTOR BUnONS (PHONE) - Selector
buttons for headphone audio output. When pressed in, enables
(
operator to select any 'one or move audio signals. Headphone
, amplifier remains in operation even with the microphone selectorc" -"(
switch off.
, \,. .1
MARKER BEACON SENSITIVITY BUTTON (SENS) - Selects LO
sensitivity with the pushbutton in the out position and HI sensitivity
with pushbutton depressed .
I
(
(
(
(
(
(
(
~~(
,"
\,J
{'
Figure 1. KMA-24 System Operating Controls (Sheet 2 of 2)
(
(
S25-6
1 April 1998
For Training Purposes Only
KMA-24 AUDIO CONTROL PANEL
POH SUPPLEMENT
(
SECTION 4
(
NORMAL PROCEDURES
(
(
f"'~' ,
\.,
(
i AUDIO CONTROL SYSTEM OPERATION:
1.
(
2.
3.
(
(
MIC Selector Switch -- Turn to desired transmitter. This
turns on the speaker amplifier.
SPEAKER andlor PHONE Audio Select Buttons(s) -SELECT desired receiver(s).
AUTO Select Button(s) -- SELECT AUTO SPEAKER and/or
PHONE as desired.
NOTE
(
•
When the AUTO SPEAKER and/or PHONE button is
depressed, rotation of the MIC selector switch selects
the COM audio automatically.
•
When the AUTO PHONE button is depressed, sidetone
will be head over the headphones.
(
(
(
S25
MODEL 208 (675 SHP)
r-:'.. .
,~
MARKER BEACON RECEIVER OPERATION:
(
1.
(
2.
3.
(
4.
(
{
\
MIC SELECTOR SWITCH -- TURN to any MIC position.
This turns on the marker beacon receiver.
TST BUTTON -- PRESS to verify all lights are operational.
SPEAKER and/or PHONE Audio Select Button(s) -- SELECT
desired MKR audio.
SENS Button -- SELECT HI (depress button) sensitivity for
airway flying or LO (button in out position) for ILS/LOC
approaches.
(
SECTION 5
PERFORMANCE
(
(
(
(~~:.
There is no change to the airplane performance when this avionic
equipment is installed. However, the installation of n externally
mounted antenna or several related external antennas, will result in
a minor reduction in cruise performance ..
(
825-7/S25-8
1 April 1998
For Training Purposes Only
(
(
(
(
(
i
(
\-
(
(
(
(
(
(
(
(
(
(
i'
(
\,
(
(
(
(
(
(
(
(
(
(
(
(
\
''-~:y
(
(
(
For Training Purposes Only
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
CESSNA MODEL 208 (675 SHP)
(
(
SUPPLEMENT 26
(
KING FLIGHT CONTROL SYSTEM
(Type KFC-1S0)
(
(
,
I'
SERIAL NO.
..
r
(
(
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model20B (675 SHP)
Pilot's Operating Handbook and FAA Approved Airplane Flight Manual if the
airplane is equipped with the King Flight Control System (Type KFC-1S0). This
supplement is a reissue of Publication Number 01336-13, FAA approved on 10
April 1992 and originally issued 15 July 1992 in conjunction with STC SA2053CE-D.
The original approval pag.e of that supplement has been electronically reproduced
on page 526-3 of this supplement.
I
I
(
(
,
(
(
APPROVED
Br4mtfdti.~u'1
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
COPYRIGHT
CESSNA
C>
7 APRIL. 1998
o
Member of GAMA
1998
AIRCRAFT
COMPANY
. WICHITA, KANSAS, USA
1 APRIL 1998
D1352-S26-00
526-1
For Training Purposes Only
S26
KFC-150 FLIGHT CONTROL SYSTEM
MODEL 208 (675 SHP) .
POH SUPPLEMENT
(
(
SUPPLEMENT 26
(
KING FLIGHT CONTROL SYSTEM
(
(Type KFC-150)
(
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
(
(
LOG OF EFFECTIVE PAGES
PAGE
826-1 thru 826-28
DATE
1 April 1998
REV. NUMBER
o
(
(
(
(
(
(
(
(
(
1 April 1998
S26-2
For Training Purposes Only
526
KFC·150 FLIGHT CONTROL SYSTEM
POHSUPPLEMENT
(
(
(
(
(
,,~-
(
\.
MODEL 208 (675 SHP)
KING FLIGHT CONTROL SYSTEM AIRPLANE
FLIGHT MANUAL SUPPLEMENT APPROVAL
KING
King Radio Corp.
400 N. Rogers Road
Olathe, Kansas 66062
CFS026-3
(
(
(
FAA APPROVED
(
AIRPLANE FLIGHT MANUAL SUPPLEMENT
(
FOR
CESSNA MODEL 208/208A/208B
WITH
KING KFC-150 FLIGHT CONTROL SYSTEM
(
( r '
,
\
Reg. No. _ _ _ _ _ _ __
, _.,"
Ser. No. _ _ _ _ _ _ __
(
(
(
(
This supplement musl be attached to the FAA Approved Airplane Flight
Manual when the King KFC-150 Automatic Flight Control System "is installed in accordance with STC SA2053CE-O. The information conlalned
herein supplements or supersedes the basic manual only in thOse areas
listed herein. For limitallons. procedures and performance information flot
contained In this supplement. consult the basic Airplane Flight Manual.
(
"FAA Approved:
(
c... L
Q ....,i'
(
Chris Durkin
DAS Coordinator
King Radio Corporation
(
DAS4CE
Date:
(
( (~',y
(
q. /0 - 9 r2..
Electronic reproduction of the original approval page from
Publication Number 01336-13, FAA approved on 10 April 1992
and originally issued 15 July 1992.
(
1 April 1998
S26-3
For Traininl! Purnoses Onlv "
S26
MODEL 208 (675 SHP)
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
SUPPLEMENT
(
KING FLIGHT CONTROL SYSTEM
(Type KFC-1SO)
(
(
SECTION 1
GENERAL
(
(
This supplement is provided to acquaint the pilot with the limitations
as well as normal and emergency operating procedures of the King
KFC-150 Automatic Flight Control System. The limitations presented
are pertinent to the operation of the KFC-150 System as installed in
Cessna Model 208 airplane (675 SHP). The flight control systems
must be operated within the limitations herein specified.
The 150 AFCS is certified in this airplane with 2 axis autopilot
control (pitch and roll). A third axis autopilot control for yaw damping
is available as an option.
(
(
(
(
(
The 150 AFCS has an electric pitch trim syst~mf which PlroviTdes .(
autotrim during autopilot operation and electric trim or the pi ot. he ;,
. trim system is designed to withstand any single inflight malfunction. '. (
Trim faults are visually and aurally annunciated.
A lockout device prevents autopilot engagement until the system .
has been successfully preflight tested.
The following conditions will cause the autopilot to automatically
disengage:
(
1.
2.
3.
4.
Electrical power failure.
Internal flight control system failure.
With the KCS-55A Compass System, a loss 01 valid
compass (display HOG flag) disengages the autopilot when
a mode using heading information is engaged. With the
HOG flag present, the autopilot may be reengaged in the
basic wings-level mode along with any vertical mode.
Roll rates in excess of 14° per second will cause the
autopilot to disengage except when the CWS switch is held (
\
depressed.
(
(
(
(
(
(
S26-4
1 April 1998
For Training Purposes Only
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
526
MODEL 20B (675 SHP)
(
5.
(
(
Pitch rates in excess of 60 per second will cause the
autopilot to disengage except when the CWS switch is held
depressed.
A
,(
\ .
WARNING
(
A thorough understanding of this supplement, to
include the difference between a flight director
and an autopilot; is required before operating
any of the components of this system.
(
(
Definition of Terms:
AUTOPILOT -This autopilot system incorporates electrically-driven
actuators that trim the airplane by moving the airplane control
surfaces which are the ailerons, rudder (when optional yaw damper
is installed), elevators, and the elevator trim. In addition, the system
incorporates a panel-mounted computer that determines what
control inputs are needed to satisfy selected operating modes such
as pitch stabilization, roll stabilization, yaw stabilization (when
optional yaw damper is installed), altitude hold, heading hold, VOR
intercept and tracking, and ILS intercept and tracking, and
electrically "authorizes" the appropriate actuator(s) to automatically
satisfy those needs.
(
(
(
(
/
(
..
\...
(
(
(
NOTES
(
(
•
The autopilot can only be ' coupled to the NAV 1
receiver.
•
The fight director (FO) mode must be selected before
the autopilot engage mode (AP ENG) can be selected.
(
(
(
(
(
( ( '
(
.
~-,,i
(
S26-5
1 April 1998
For Training Purposes Only
526
MODEL 208 (675 SHP) .
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
FLIGHT DIRECTOR - The Flight director system incorporates a
panel-mounted computer that calculates intercept angles and displays them to the pilot as pitch and steering recommendations on
the Fight Command Indicator (Fel). The computer is programmed ,
through . the mode selection to follow heading or navigation radio I,
courses as well as pitch attitudes or pressure altitudes. The recommended pitch and steering display serves as a reminder to the pilot
as to which way he should fly the airplane to get the desired results
of his mode selector input The flight director may .be used with the
autopilot engaged or disengaged. . In the latter case, the pilot manually flies the airplane to satisfy the command bar on the FCI which
is positioned by the computer rather than allowing the autopifot to
satisfy the computed commands.
(
(
(
(
(
(
The following circuit breakers are used to protect the ,elements of
the King KFC-1S0 Flight Control System:
LABEL
NP
CONT
ENC
ALTM
' ELEV
TRIM
FUNCTION
Supplies power to the KC-192 Computer, the
autopilot pitch and roll seNDS, the KA-185
Annunciator, the ELEV TRIM Circuit Breaker
and the KC-296 Yaw Computer and Yaw
Servo (optional) .
Supplies power to the KAS-2978 Vertical
Speed and Altitude Selector (optional).
Supplies power to the autotrim and manual
electric pitch trim systems.
(
(
(
(
HSI1
Supplies power to the KCS-5SA Compass
System.
(
(
The airplane BATIERY, GENERATOR and STBY PWR SWITCH
functions are unchanged and can be used in an emergency to shut
off electrical power to all flight control systems while the problem is
isolated.
(
(
(
The AVIONICS POWER 1 switch supplies power to the autopilot ( (
and El-EV TRIM circuit breakers.
';,,,;
(
(
S26-6
1 April 1998
For Training Purposes Only
(
.\
526
KFC-150 FLIGHT CONTROL SY8TErJ!
POH SUPPLEMENT
;,
(
MODEL 208 (675 SHP)
(
(
2
1
(
; 3
4
3
5
6
16
/ --
-
(
I
I II
'i\ .
(
(
(
15
(
14 13 12
11
10
9
8
7
2685X1057
(
(
KC-192 AUTOPILOT AND FLIGHT GIRECTOR COMPUTER
(
(
1.
KFC-150 SYSTEM KC-192 AUTOPILOT COMPUTER - Complete
Flight Director and Autopilot computer', including system mode
annunciators and system controls.
2.
YAW DAMPER (YO) ANNUNCIATOR - Illuminates when the yaw
damper (optional) is engaged.
3.
MODE ANNUNCIATORS - Illuminate when a mode is selected by
the corresponding mode selector button (PUSH ON - PUSH OFF).
4.
GLIDE SLOPE (GS) ANNUNCIATOR - Illuminates continuously
whenever the autopilot is coupled to the glide slope signal. The
GS annunciator will flash if the glide slope signal is lost (GS flag in
COl .or' absence of glide slope pointers in KI-525A). The autopilot
reverts to pitch attitude hold operation. If a valid glide slope signal
returns within six seconds, the autopilot will automatically recouple
in the GS mode, If the valid signal does not return within six
seconds, the autopilot will ' remain in pitch attitude hold mode until
such time that a valid glide slope. returns and the airplane passes
through the glide slope. At that point, GS couple will re-occur.
(
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~
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(
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~. '
Figure
1.
King
Controls/Indicators
KFC-150
Flight .
Control
System
(Sheet 1 of 11)
(
826-7
1 April 1998
For TrainmgPurposes Only
526
MODEL 208(675 SHP)
5.
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
TRIM WARNING LIGHT . (TRIM) - Illuminates continuously whenever
trim power is not on or the system has not been preflight tested. The
TRIM warning light illuminates and is accompanied by an audible
(
warning whenever a manual trim fault is detected. The Manual Trim
{
System is monitored . for the trim servo running without a command.
The TRIM warning light will illuminate. and be accompanied by an \. (
audible warning whenever an autotrim failure occurs The autotrim
system is monitored for the following failures: trim . servo running
without a command, trim servo not running when commanded to run,
and trim servo running in the wrong direction.
6.
AUTOPILOT (AP) ANNUNCIATOR
Illuminates continuously
whehever the autopilot is engaged. Flashes approximately 12 times
whenever the autopilot is disengaged (an aural alert will also . sound
. for 2 seconds).
7.
AUTOPILOT ENGAGE (AP ENG) BUnON - When pushed, engages
autopilot if all logic conditions are met.
8.
PREFLIGHT TEST (TEST) BUTTON - When momentarily pushed,
initiates preflight test sequence which automatically turns on all
annunciator lights, tests the roll and pitch rate monitors, tests the
autotrim fault monitor, checks the manual trim drive voltage and tests
all autopilot valid and dump logic. If preflight is successfully passed,
the AP annunciator ·Iight will flash for approximately 6 seconds (an
aural tone will also sound simultaneously with the annunciator
flashes) . The autopilot cannot be engaged until ' autopilot preflight
tests are successfully passed.
(
( (
9. . BACK COURSE APPROACH (BC) MODE SELECTOR BUTTON When pushed will select the Back Course Approach mode. This
modefunctionsidentica.lly to the approach mode except that
response to LOC signals is reversed. Glide slope coupling is
inhibited in the Back Course Approach mode.
10.
APPROACH (APR) MODE SELECTOR BUnON - When pushed, will
setect the' Approach mode. This mode provides all angle intercept,
automatic beam capture, and tracking,of VOR, RNAV, or LOC signals
plus glide slope coupling in the case of an ILS. The tracking gain of
the APR mode is greater than the gain in the NAV mode. The APR
annunciator on the Autopilot Computer will flash until the automatic
capture sequence is initiated. On the KA-185 Remote Mode
Annunciator, APR ARM will annunciate until the automatic capture
sequence is initiated. At beam capture, APR CPLD will annunciate.
(
(
((
Figure 1. King KFC-150 Flight Control System Controls/Indicators
(Sheet 2 of 11)
S26-8
1 April 1998
For Training Purposes Only
" ~-.:.~~
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
11.
NAVIGATION (NAV) MODE SELECTOR BUTTON - When pushed will
select the navigation mode. The mode provides all angle intercept
(with HSI), automatic beam capture and tracking of VOR, RNAV, or
LOC signals. The NAV annunciator on Autopilot Computer will flash
until the automatic capture sequence is initiated. On KA-185 Remote
Mode Annunciator; NA V ARM will annunciate until the automatic
capture sequence is Initiated. At beam capture, NAV CPLD will
annunciate.
12.
HEADING (HDG) MODE SELECTOR BUTTON - When pushed will
select heading mode, which commands the airplane to turn to and
maintain the heading selected by the heading bug on the HSI. A new
heading may be selected at any time and will . result in the airplane
turning to the new heading with a maximum bank and about 20
degrees. Selecting HDG mode will cancel NAV, APR, or BC track
modes.
13.
ALTITUDE HOLD (ALT) MODE SELECTOR BUnON - When pushed
will select the altitude hold mode, which commands the airplane to
maintain the pressure altitude existing at the moment of selection.
Engagement may be accomplished in climb, descent or level flight.
In the APR mode, altitude hold will automatically disengage when the
glide slope is captured.
14.
FLIGHT DIRECTOR (FD) MODE SELECTOR BUTTON - When
pushed will select .the flight director mode, bringing the command bar
in view on the KI-256 and will command wings-level and pitch attitude
hold. The FD mode must be selected prior to autopilot engagement.
15.
VERTICAL TRIM CONTROL - A spring-Ioaded-to-center rocker
switch which will provide up or down pitch command changes: while
in ALT, will adjust altitude at rate of about 500 fpm; when not in ALT,
will adjust pitch attitude at a rate of .7 deg/sec. Will . cancel GS
couple. The airplane must pass through the glide · slope again to
allow GS recouple. When in the Vertical Speed Hold mode (optional),
this control can be used to slew the vertical speed up or down at 100
fpm for every second the rocker .switch is held down. If altitude is
being displayed at the time the rocker switch is depressed, vertical
speed will be displayed until 1-2 seconds after the rocker switch is
released.
16.
YAW DAMPER SWITCH (OPTIONAL) - May be used .to engage or
disengage the yaw damper independent of the autopilot.
r'" '
\;
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826
MODEL 20B (675 8HP)
~ (,,:.
Figure 1. King KFC-150 Flight Control System Controlsllndicators
(Sheet 3 of 11)
1 April 1998
826-9
For Training Purposes Only
526
KFC-150 FLIGHT CONtROL SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
17
3
18
19
3
6
2
3
3
20
4
5
2685Xl058
KA-185 REMOTE MODE ANNUNCIATOR
17.
KA-185 REMOTE MODE ANNUNCIATOR - Provides mode annunciation in the pilot's primary scan area as well as three marker
beacon lights.
18.
ARMED (ARM) ANNUNCIATOR c Illuminates continuously along
with NA V or APR when either the NAV or APR mode selector
button is depressed. The ARM annunciator will continue to illuminate until the automatic capture sequence ·is initiated at which
time ARM will extinguish and CPLD will annunciate.
(
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24
(
23
22
2685X1059
AUTOPILOT CONTROL WHEEL SWITCH CAP
Figure 1. King KFC-150 Flight Control System Controls/Indicators
(Sheet 4 of 11)
1 April 1998
S26-10
For Training Purposes Only
(
(
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
526
MODEL 208 (675 SHP)
(
(
(
-~
(
f
19.
COUPLED (CPLD) ANNUNCIATOR - Illuminates continuously along
with NAV or APR at the initiation of automatic beam capture sequence in either the NAV or APR modes. Normally the CPLD condition follows an ARM condition but may be entered into directly if the
beam capture criteria is met when NAV or APR is selected.
20.
REMOTE MARKER BEACON LIGHTS - Remote airway, outer and
middle marker beacon lights driven by the marker beacon receiver.
21 .
CONTROL WHEEL STEERING (CWS) BUTTON - When depressed,
allows pilot to manually control the airplane (disengages the pitch
and roll servos) without cancellation of any of the selected ' modes.
Will engage the flight director mode if not previously engaged. Auto·
matically synchronizes the flight director/autopilot to the pitch attitude
present when the CWS switch is released , or to the present pressure
altitude when operating in the ALT hold mode. Will cancel GS couple.
The airplane must pass through the glide slope again to allow GS recouple. When operating in the Vertical Speed Hold mode (oplional),
the CWS will re-sync the Vertical Speed Hold mode to the current
vertical speed of the airplane. If altitude is displayed when the CWS
button is pressed, the display will automatically display vertical speed
as long as the CWS button is depressed . CWS does not affect the
Altitude Select mode.
22.
AUTOPILOT CONTROL WHEEL SWITCH ASSEMBLY - Switch assembly mounted on the pilot's control wheel associated with the autopilot and manual electric trim systems.
23.
MANUAL ELECTRIC TRIM CONTROL SWITCHES - A split switch
unit in which the left half provides power to engage the trim servo
clutch and the right half to control the direction of motion of the trim
servo motor. 'Soth halves of the split trim switch must be actuated in
order for the manual trim to operate in the desired direction. When
the autopilot is engaged, operation of the manual electric trim will
automatically disconnect the autopilot.
24.
AUTOPILOT DISCONNECTITRIM INTERRUPT (AlP DISCITRIM INTER) SWITCH - When depressed will disengage the autopilot and
yaw damper, (optional) and cancel all operating fight director modes.
When depressed and held. will interrupt all electric trim power (stop
trim motion). disengage the autopilot and yaw damper (optional) and
cancel all operating flight director modes
..
~..:~
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{'(
,~
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(
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(
Figure 1. King KFC-1S0 Flight Control System Controls/Indicators
(Sheet 5 of 11)
S26-11
1 April 1998
For Training Purposes Only
526
MODEL 208 (675 SHP)
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
25.
DECISION HEIGHT (DH) ANNUNCIATOR LIGHT - Non-operatio"nal
(Not Used).
26.
KI~265 FLIGHT ' COMMAND INDICATOR (FCI) - Displays airplane
(
attitude as a conventional attitude gyro and displays commands for .' . (
flight director operation. The gyro is air-driven.
\, (
27.
ROLL ATTITUDE INDEX - Displays airplane roll attitude With respect
to the roll attitude scale.
'
28.
ROLL ATTITUDE SCALE - Scale marked at 0, ±10, 20, 30, 60, and
90 degrees.
29.
PITCH ATTITUDE SCALE - Moves with respect to the symbolic
airplane to present pitch attitude. Scale graduated at 0, ±5, 10, 15,
20, and 25 degrees.
I
30.
31 .
COMMAND BAR
Displays computed steering commands
referenced to the symbolic airplane. The command bar is visible
only when FD mode is selected. The command bar will be biased out
of view,whenever the system is invalid or a flight director mode is not
engaged.
(
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FCI SYMBOLIC AIRPLANE - Airplane pitch . and roll attitude is
displayed by relationship between the fixed symbolic ' airplane and the . (
movable background. During flight director operation, the symbolic \ (
airplane is flown to align it with the command to satisfy the .flight .
. director commands.
(
32.
KI-525A HORIZONTAL SITUATION INDICATOR (HSI) - Provides a
pictorial presentation of airplane deviation relative to VOR radials or
localizer beams. It also displays glide slope deviations and gives
heading reference with respect to magnetic north. The gyro is driven
electrically.
33.
NAV FLAG - Flag is in view when the NAV receiver signal is
inadequate. When a NAV flag is present in the navigation indicator
(KI-525A) the autopilot operation is not affected. The pilot must
monitor ' the navigation indicator for "a NAV flag to ensure that the
autopilotand/or flight director are tracking valid navigation
information.
34.
(
(
LUBBER LINE - Indicates aircraft magnetic heading on compass card
(41) . .
Figure 1. King KFC-150Flight Control System Controls/lndicators
(Sheet 6 of 11)
1 April 1998
S26-12
For Training Purposes Only
c(
....,..'=:,<~:
(
(
526
KFC·150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
MODEL 208 (675 SHP)
(
(
(
r -',
26
( :
27
28
"<:,
(
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29
25
(
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30
(
(
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31
(
KI-256 FLIGHT COMMAND INDICATOR
(
E~>
(
"',",0_
(
32
33
34 35
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45
36
44
37
38
38
39
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43
(
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40
42
41
(
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( C'
;,
KI-S25A HSI
~;;
26B5X1060
26B5X1061
(
(
Figure 1. King KFC-150 Flight Control System Controls and
Indicators (SheetS of 9)
S26-13
1 April 1998
For Training Purposes Only
526
MODEL 208 (675 SHP)
35.
36.
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COURSE BEARING POINTER - Indicates selected VOR course or
localizer course on the compass card (41). The selected VOR radial
or localizer heading remains set on the compass card when the
compass card (41) rotates.
TO/FROM INDICATOR FLAG - Indicates direction of VOR station
relative to selected course.
38.
DUAL GLIDE SLOPE POINTERS - Indicate on the glide dope scale
(39) airplane displacement from glide slope beam center. Glide slope
pointers in view indicate a glide slope signal is being received. (Glide
slope pointers not shown.)
40.
(
HEADING WARNING FLAG (HDG) - When flag is in view, the
heading display invalid. If a HDG flag appears and a tateral mode
(HDG, NAV, APR, or APR BC) is selected, the autopilot will be
disengaged. The autopilot may be re-engaged in the basic wingslevel mode along with any vertical mode. The. CWS switch wOuld be
used to manually maneuver the aircraft laterally.
37.
39.
(
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
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GLIDE SLOPE SCALES - Indicate displacement from ' glide slope
beam center. A glide slope deviation bar displacement of 2 dots
represents full. scale (0.7°) deviation above or below glide slope
beam centerline.
(
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HEADING SELECTOR KNOB - Positions the heading bug (45) on
compass card (41) by rotating the heading selector knob. The bug
rotates with the compass card .
(
41 .
COMPASS CARD - Rotates to display heading of airplane with
reference to lubber line (34) on HSI.
'
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42.
COURSE SELECTOR KNOB - Positions the course bearing pointer
(36) on compass card (41) by rotating the course selector knob.
43.
COURSE DEVIAnON BAR (D-BAR) - The center portion of the omni
bearing pointer moves laterally to pictorially indicate the relationship
of airplane to the . selected course. It indicates degrees of angular
displacement from VOR radials and localizer beams, .or displacement .
in nautical miles from RNAVcourses.
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Figure 1. King KFC-150 Flight Control SystemControls/lndicators
(Sheet 8 of 11)
1 April 1998
S26·14
For Training Purposes Only
" "
(
(
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
(
526
MODEL 208 (675 SHP)
(
46
47
48
r-'-'
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49
26B5Xl062
KA-S1B SLAVING ACCESSORY AND COMPENSATOR UNIT
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\C.
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44.
COURSE DEVIATION SCALE - A course deviation bar displacement
of 5 dots represents full scale (VOR = ±10°, LOC = ±2-1/2°,
RNAV = 5 nm,RNAV APR =1-1/4 nm) deviation from beam
centerline.
45.
HEADING BUG - Moved by knob (40) to select desired heading.
46.
KA-51B SLAVING ACCESSORY AND COMPENSATOR UNIT
COntrols the KCS-55A Compass System.
47.
MANUAL/AUTOMATIC (FREE/SLAVE) COMPASS SLAVE SWITCH Selects either the manual or automatic slaving mode for the
compass system ..
48.
CW/CCW · COMPASS MANUAL SLAVE SWITCH - With the
manual/automatic compass slave switch in the FREE position,
allbws manual compass card slaving in either the clockwise or
counterdockwise direction. The switch is spring loaded to the center
position.
49.
SLAVING METER - Indicates the difference between the displayed
heading and the magnetic heading. Up deflection indicates a
clockwise error of the compass card. Down deflection ' indicates a
counterclockwise error of the compass card.
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Figure 1. King KFC-150 Flight Control System Controls/Indicators
(Sheet 9 of 11)
S26-15
1 April 1998
For Traininl! Purooses Onlv
S26
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
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50
51
52
53
54
55
(
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56
(
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60
59
58
57
2685X1063
KAS-2978 VERTICAL SPEED AND ALTITUDE SELECTOR
50.
VERTICAL SPEED MODE (ENG) BUTTON - When pressed, will
engage the Vertical Speed Hold mode. When pressed a second
time, will disengage the Vertical Speed Hold mode. When pressed
with altitude displayed, will engage the ' Vertical Speed Hold mode
and re-sync the Vertical Speed Hold mode to the current vertical
speed of the airplane.
51.
PHOTOCELL - Automatically dims display according to the cockpit
ambient light.
52.
VERTICAL SPEED (VS) ANNUNCIATOR - Illuminates when the
Vertical Speed Hold mode is engaged.
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53.
54.
55.
(
VERTICAL SPEED UP/DOWN CARETS - Indicates whether the
selected vertical speed is up or down.
(
GAS DISCHARGE DISPLAY - Displays selected altitude from 100
to 35,000 feet Dr the selected vertical speed from 0 to 3000 feet
per minute up or down.
ALTITUDE ALERT (ALERT) ANNUNCIATOR - The ALERT
annunciator is illuminated 1000 feet prior to the selected altitude,
goes out 300 feet prior to the selected altitude and illuminates
momentarily when the selected altitude is reached. Once the
selected altitude is reached, the light signifies that the 300 feet
"safe band" has been exceeded and will remain on until 1000 feet
from the selected altitude. The alert light is accompanied by a :2
second aural tone anytime the light initially comes on or the
selected altitude is reached.
Figure 1. King KFC-150 Flight Control System Controls/Indicators
(Sheet 10 of 11)
1 April 1998
S26-16
For Training Purposes Only
(
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KFC-150 FLIGHT CONTROL·SYSTEM
POH SUPPLEMENT
56.
(
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Altitude is displayed and selected when the small (inner) knob is in
the "in" position. When rotated, the small knob selects altitude in 100
foot increments with roll over into the 1000 digits. The large (outer)
knob selects altitude in 1000 foot increments with roll over into the
10,000 digits.
Vertical speed is displayed and selected when ·the small (inner) knob
is in the "out" position. When rotated, the small knob selects vertical
speed in 100 fpm increments. The large (outer) knob selects vertical
speed in 1000 fpm increments up to a maximum of 3000' fpm.
(
57.
MODE (FT or FT/MIN) ANNUNCIATOR - Indicates FT/MIN when in
the · Vertical Speed Hold mode and FT when in the Altitude Select
mode.
58.
ALTITUDE CAPTURE (CAPT) ANNUNCIATOR - Indicates the KAS297B has switched the autopilot from Pitch Altitude Hold or Vertical
Speed Hold mode into the pitch roundout mode (CAPT). The point
just prior to transfer into Altitude Hold, at which the CAPT mode ·
becomes active varies with the vertical speed, i.e., the higher the
.rate of climb, ·the sooner the CAPT mode becomes active; at low
rates of climb, the activation of the CAPT mode and transfer to
altitude hold occur almost simultaneously.
59.
ALTITUDE SELECT ARM (ARM) ANNUNCIATOR - Indicates that the
Altitude Select mode is armed to.capture the selected altitude.
60.
ALTITUDE SELECT MODE (ARM) BUTTON - When pressed and the
selected altitude is displayed, will arm the Altitude Select mode. The
Altitude Select (ARM) mode will cancel altitude hold (AL if AL T is
already engaged. If Altitude Select (ARM) mode is present when GS
couple occurs, the GS mode will cancel Altitude Select (ARM) mode .
.The engagement of ALT by the pilot's use of the ALT switch will
cancel the Altitude Select (ARM) mode.
Reselection of a new
altitude will also cycle the Altitude Select (ARM) mode off.
(
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VERTICAL SPEED/ALTITUDE SELECT KNOB- Concentric knobs
which allow easy setting of altitude or vertical speed. The small
(inner) knob has an .in and out position.
1'-
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526
MODEL 208 (675 SHP)
\..'
(
n
·Figure 1. King KFC-150 Flight Control System Controlsllndicators
(Sheet 11 of 11)
1 April 1998
S26-17
For Training Purposes Only
S26
MODEL 208 (675 SHP) .
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
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SECTION 2
LIMITATIONS
(
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The following autopilot limitations must be followed during airplane (
-\
operation.
1.
During autopilot operation, a pilot with seat belt fastened
must be seated at the left pilot position.
2.
The autopilot and yaw damper (optional) must be OFF
during takeoff and landing.
.
_3.
The System Is Approved for Category 1 Operation Only -Approach Mode Selected.
(
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4.
The Autopilot Must Be Disconnected Below 200 feet AGL.
5.
Autopilot Must Be Off During Use .of the- Standby Flap
System .
6.
Altitude Select (optional) captures below 800 feet AGL are
(
prohibited.
.
( (
(
A WARNING
(
IN
ACCORDANCE
WITH
FAA
RECOMMENDATION (AC 00-24K), USE OF BASIC
PITCH
ATTITUDE
HOLD
MODE
IS
RECOMMENDED
DURING
OPERATION
IN
SEVERE TURBULENCE.
(
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(
1 April 1998
S26-18
For Training Purposes Only
(
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
526
MODEL 208 (675 SHP)
(
(
SECTION 3
EMERGENCY PROCEDURES
(
(
r
IN CASE OF AUTOPILOT/YAW DAMPER MALFUNCTION:
(
NOTE
(
Accomplish Items 1 and 2 simultaneously.
(
1.
Airplane Control Wheel -- GRASP FIRMLY and
OPERATE as required to manually override the autopilot.
2.
A/P DISCITRIM INTER Switch -- PRESS and HOLD.
3.
AlP DISCITRIM INTER SWITCH -- RELEASE while
observing pitch trim wheel. If pitch trim wheel is in
motion, follow the electric trim malfunction procedure.
(
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IN CASE OF. ELECTRIC TRIM MALFUNCTION (Either manual
electric or autotrim):
(
(
(
1.
(
2.
3.
(
AlP DISCITRIM INTER Switch -- PRESS and HOLD
throughout recovery.
ELEV TRIM Circuit Breaker -- PULL OFF.
Aircraft -- RETRIM manually.
(
A WARNING
(
WHEN
DISCONNECTING
THE
AUTOPILOT
AFTER A TRIM MALFUNCTION, HOLD THE
CONTROL WHEEL FIRMLY; , UP TO 45 POUNDS
OP FORCE ON THE CONTROL WHEEL MAY BE
NECESSARY TO HOLD THE AIRCRAFT LEVEL.
(
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(~'.J
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S26-19
1 April 1998
For Training Purposes Only
526
MODEL 208 (675 SHP)
MAXIMUM
ALTITUDE
MALFUNCTION:
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
LOSSES
DUE
TO
AUTOPILOT
(
(
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Configuration -- Altitude Loss.
(
Cruise, Climb, and Descent -- 500 Ft.
Maneuvering -- 100 Ft.
Approach -- 100 Ft.
AUTOPILOTIYAW DAMPER DISENGAGEMENT (The autopilot
and/or yaw damper may be manually disengaged by any of the
following methods): .
(
(
1.
2.
3.
4.
5.
Press the AlP DISCITRIM INTER switch on the pilat's
control wheel.
Operate the pilot's electric trim switch UP or DOWN to
automatically disengage the autopilot.
Press the APJENG button to the OFF position.
Pull the AlP CaNT circuit breaker out.
Turn off the AVIONICS POWER 1 switch.
(
(
YAW DAMPER (OPTIONAL) DISENGAGEMENT (The yaw damper ! (
only may be disengaged by the following method):
.
\
1.
Press the yaw damper switch button to the OFF position.
SECTION 4
(
(
(
NORMAL PROCEDURES
(
BEFORE TAKEOFF RELIABILITY TESTS: (Preform Steps 1 thru
10 prior to each flight)
(
(
1.
2.
3.
Gyros -- Allow 3-4 minutes for gyros to come up to speed.
AVIONICS POWER 1 Switch -- ON.
PREFLIGHT TEST Button -- PRESS momentarily and
(
NOTE:
a.
All annunciator lights on (TRIM annunciator flashing) .
(
All legends and digits are displayed on the KAS-297B
(
b.
Vertical Speed and Altitude Selector (Optional).
c.
After approximately 5 seconds, all annunciator lights
off except AP, which will flash approximately 12 times . . . (
and then remain off.
l (
S26-20
·1 April 1998
For Training Purposes Only
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
526
MODEL 208 (675 SHP)
(
(
NOTE
(
f~'- '
(
(
",
(
If trim warning light stays on, the autotrim did not pass the
preflight test. · The autopilot circuit breaker should be pulled.
The autopilot and manual electric trim will be inoperative.
4.
(
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(--.
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5.
6.
7.
8.
(
9.
(
10.
(
Manual Electric Trim -- TEST as follows.
a.
Accurate left side of split switch unit to the fore and aft
positions. The trim wheel should not move on its own .
Rotate the trim wheel manually against the engaged
clutch to check the pilot's trim overpower capability.
b.
Actuate right side of split switch unit to the fore and aft
positions. The ' trim wheel should not move on its own
and normal trim wheel force is required to move it
manually.
c.
Press the AlP DlSCITRIM INTER switch down and
hold. Manual electric trim should not operate either
nose up or nose down.
Flight Director -~ ENGAGE by pressing FD or CWS button.
Autopilot -- ENGAGE by pressing AP ENG button.
Yaw Damper (Optional)-- ENGAGE by pressing YAW
DAMP switch button.
Flight Controls -- MOVE fore, aft, left and right to verify that
the autopilot/yaw damper,can be overpowered.
NP DISCITRIM INTER Switch -- . PRESS. Verify that the
autopilot and yaw damper (optional) disconnects and all
flight director modes are cancelled.
TRIM -- SET to takeoff position.
(
AUTOPILOT OPERATION
(
BEFORE TAKEOFF: ' .
(
1.
NP DISCITRIM INTER SWITCH -- PRESS to disengage AP.
(
(
,
(
(:'~,~. ;~,.>.-
IN FLIGHT AUTOPILOT
ENGAGEMENT:
1.
2.
AND
YAW
DAMPER
(OPTIONAL)
FD Mode Selector Button -- PRESS.
AP ENG Button -- PRESS. Note AP annunciators on. If no
other modes are selected, the autopilot will operate in wingslevel and pitch attitude 'hold.
S26-21
1 April 1998
For Training Purposes Only
526
MODEL 208 (675 SHP)
3.
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
(
(
YAW DAMP Button -- PRESS. Note YO annunciators on.
(
A WARNING
{ .
DO . NOT HELP THE AUTOPILOT AS THE
AUTOPILOT WILL RUN THE PITCH TRIM TO
OPPOSE YOUR HELP.
(
\
(
(
CLIMB or DESCENT:
1;
2.
3.
(
(
Using CWS:
(
a. . CWS Button -- PRESS and MOVE airplane nose to the
desired attitude.
(
b.
CWS Button -- RELEASE.
Autopilot will maintain
(
airplane pitch attitude up to the pitch limits of +15
degrees or -10 degrees.
Using Vertical Trim:
'.
a.
VERTICAL TRIM Control -- PRESS either up or down
to modify airplane attitude at a rate of .7 deg/sec. up to
the pitch limits of + 15 degrees or -10 degrees.
b.
VERTICAL TRIM Control -- RELEASE when desired
airplane attitude is reached.
The autopilot will (
maintain the desired pitch attitude.
'.
Using Vertical Speed Select (Optional):
a.
Vertical Speed/Altitude Select Knob -- Pull inner knob
to "out" position and rotate knob until desired vertical
speed is displayed.
b.
VS ENG Button -- PRESS to engage the vertical speed
hold mode.
Or Using Vertical Trim:
(
a.
Vertical Trim Control -- PRESS either up or down to
increase or decrease displayed vertical speed.
(
Vertical speed display will change 100 fpm for every
second the trim control is held down.
b.
Vertical Trim Control -- RELEASE when desired
vertical speed is displayed.
(
(
\
..
(
(
1 April 1998
S26-22
For Training Purposes Only
(
KFC-1S0 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
(
,
A
(
(
",'
( \
.
.
.
(
(
(
(
•
(
(
.
('
( \
( (
(
(
(
(
{
(
(
WARNING
WHEN OPERATING AT OR NEAR THE
BEST RATE OF CLIMB AIRSPEED AND
USING THE VERTICAL SPEED HOLD, IT IS
EASY TO DECELERATE TO AN AIRSPEED
ON THE BACK SIDE OF THE POWER
CURVE WHERE
A DECREASE IN
AIRSPEED RESULTS IN A DECREASE IN
RATE OF CLIMB. CONTINUED OPERATION
ON THE BACK SIDE . OF THE POWER
CURVE IN THE VERTICAL SPEED HOLD
MODE WILL RESULT IN A STALL.
WHEN OPERATING AT OR NEAR THE
: MAXIMUM OPERATING SPEED (VMO), IT
WILL BE NECESSARY TO REDUCE POWER
IN ORDER TO MAINTAIN THE DESIRED
RATE OF DESCENT AND NOT EXCEED
THE MAXIMUM OPERATING SPEED (VMO).
ALTITUDE HOLD:
t.
(
(
526
MODEL 208 (675 SHP)
2.
ALTMode Selector Button -- PRESS. Note ALT mode
annunciator ON.
Autopilot will maintain the selected
pressure altitude.
Change Selected Altitudes:
a.
Using CWS (recommended for altitude changes
greater than 100 ft.).
(1)
CWS Button -- PRESS and fly airplane to
desired pressure altitude.
(~)
CWS Button -- RELEASE when desired
pressure altitude is reached. Theautopilc;>t will
maintain the desired pressure altitude.
b.
Using Vertical Trim (recommended for altitude
changes less than 100 ft.).
(1)
Vertical Trim Control -- PRESS either up or
down. Vertical Trim will seek an altitude rate of
change about 500 fpm.
.
(2)
Vertical Trim Control -- RELEASE when desired
pressure altitude is reached.
S26-23
1 April 1998
"nr Tr<1linina
Pllrnm:p~
Onlv
526
MODEL 208 (675 SHP)
c.
(
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
Using Altitude Preselect (Optional):
(1)
Vertical Speed/Altitude Select Knob -- PUSH
.
inner knob to "in" position and rotate until the
desired altitude is displayed.
(2)
AL T ARM Button -- PRESS to arm the altitude
select mode.
(3)
Airplane -- ESTABLISH ATTITUDE necessary to
intercept the selected altitude.
(
(
(
(
l
(
(
HEADING CHANGES:
1.
(
(
Manual Heading Changes:
a.
CWS Button -- PRESS and MANEUVER airplane to
the.desired heading.
CWS Button -- RELEASE.
Autopilot will maintain
b.
airplane in wings-level attitude.
(
(
NOTE
(
(
Aircraft 'heading may change in the wings-level mode due to
an airplane out of trim condition.
2.
3.
.(
Heading Hold:
a.
Heading Selector Knob -- SET BUG to desired
heading.
_HOG Mode Selector Button -- PRESS. Note HDG
b.
mode annunciator ON. Autopilot will automatically turn
the airplane to the selected heading~
Command Turns (Heading Hold Mode ON):
a.
Heading Selector Knob -- MOVE BUG to the desired
heading. Autopilot will automatically turn the airplane
to the new selected heading.
(
(
(
(
(
(
(
(
(
(
(
(
(
(
I
\::~.. -:.
(
(
S26-24
1 April 1998
For Training Purposes Only
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
526
MODEL 208 (675 SHP)
(
NAV COUPLING :
(
(
(
(---
1.
2.
Iz
(
3.
(
(
(
(
(
(
(
Course Bearing Pointer -- SET to desired course.
Heading Selector Knob -- SET BUG to provide desired
intercept angle.
NAV Mode Selector Button -- PRESS.
a.
If the Course Deviation Bar is greater than 2 to 3 dots:
the airplane will continue in HOG mode (or wings-level
if HOG not selected) with the NAV annunciator
flashing; when the computed capture point is reached,
the HOG will disengage, the NAV annunciator will
illuminate steady, and the selected course will be
automatically captured and tracked.
b.
If the O-Bar is less than 2 to 3 dots; the HOG mode will
disengage upon selecting NAV mode, the NAV
annunciator will illuminate steady and the capture/track
sequence will automatically begin.
APPROACH (APR) COUPLING:
(
1.
2.
(
{
3.
(
(
(
(
(
(
(
Course Bearing Pointer -- SET to desired course.
Heading Selector Knob -- SET BUG to provide desired
intercept angle.
APR Mode Selector Button -- PRESS.
a.
If the Course Deviation Bar is greater than 2 to 3 dots:
the airplane will continue in HOG mode (or wings-level
if HOG not selected) with the APR annunciator
flashing; when the computed capture point is reached,
the HOG will disengage, . and the BC and APR
annunciators will illuminate steady and the selected
course will be automatically .captured and tracked.
If the O-Bar is less than 2 to 3 dots: the HOG mode will
b.
disengage upon selecting APR mode; the APR
annunciator will illuminate steady and the capture/track
sequence will automatically begin.
(
A WARNING
(
(
C,-
•
ALTITUDE SELECT CAPTURES BELOW 800
FEET AGL ARE PROHIBITED.
1 April 1998
S26-25
For Trllining PlJrposes Only
526
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
MODEL 208 (675SHP)
A WARNING
(
•
USE OF THE ALTITUDE PRESELECT
SYSTEM (OPTIONAL) FOR LEVEL OFF AT
MDA- OR DH SHOULD BE AVOIDED DUE TO
THE LACK OF DEFINITION OF SELECtED
ALTITUDE.
(
BC APPROACH COUPLING:
1.
2.
3.
Course Bearing ' Pointer -- SET to the ILS front course
inbound heading.
Heading Selector Knob -- SET BUG to provide desired
intercept angle.
BC Mode Selector Button -- PRESS.
a.
If the course Deviation Bar is greater than 2 to 3 dots:
the airplane will continue in HOG mode (or wings-level
if ·HOG not selected) when the computed capture point
is reached, the HDG will disengage, and the Be and
APR annunciators w.ill illuminate steady and the ,,· (
selected course will be automatically captured and ~.
tracked .
,
b.
If the D-Bar is less than 2 to 3 dots: the HOG mode will
. disengage upon selecting Be mode; the APR BC
annunciator will illuminate steady and the capture/track
sequence will automatically begin.
(
(
GLIDE SLOPE COUPLING:
NOTE
(
Glide slope coupling is inhibited when operating in NAV or
APR Be modes. Glide slope coupling occurs automatically
in the APR mode.
(
(
1.
2.
APR Mode -- ENGAGED.
Alt Glide Slope Centering -- NOTE GS annunciator ON.
(
( (
'~.~
- .-
(
1 April 1998
826-26
For Training Purposes Only
KFC-150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
526
MODEL 208 (675 SHP)
(
NOTE
(
The autopilot can capture the glide slope from above or
below the beam while operating in either pitch attitude hold
or alt hold modes.
;-'
(
(
(
MISSED APPROACH:
(
1. AlP DISCITRIM INTER Switch -- PRESS to disengage AP.
2. Missed Approach -- EXECUTE.
3. CWS Button -- PRESS as desired to activate FD mode
during go-around maneuver.
4. AP ENG button -- PRESS (if AP operation is desired). Note
AP annunciators ON.
(
(
(
If AP is used during missed approach:
(
5.
{
Altitude Select (Optional) -- SELECT missed approach altitude and PRESS ARM button.
(
(
f
(
(
(
NOTE
If it is desired to track the ILS course outbound as part of
the missed approach procedure, use the NAV mode to prevent inadvertent GS coupling.
.
BEFORE LANDING:
(
(
(
1.
AlP DISCITRIM INTER Switch -- PRESS to disengage AP
and yaw damper (optional).
FLIGHT DIRECTOR OPERATION
(
NOTE
(
(
(
~ ("e,
(
The flight director modes of operation are the same as those
used for autopilot operations except the autopilot is not engag'ed and the pilot must maneuver the airplane to .satisfy
the flight director commands.
(
S26-27
1 April 1998
For Training Purposes Only
S26
. MODEL 208 (675 SHP)
(
KFC:.150 FLIGHT CONTROL SYSTEM
POH SUPPLEMENT
(
(
SECTION 5
PERFORMANCE
(
(
There is no change to the airplane performance data when this
avionic equipment is installed.
(
(
(
(
(
(
(
(
(
(
lc (
(
(
(
(
(
(
(
(
(
(
\..-.:.,: ~-~..
(
(
(
1 April 1998
S26-28
For Training Purposes Only
(
(
~
eessna
A Texlron
Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 27
BENDIX/KING AUDIO CONTROL SYSTEM
(Type KMA-24H-70)
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a Bendix/King Audio Control
System (Type KMA-24H-70).
APPROVED
BiJ/e,&RfJ/r;;k*ct',f
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option ManulaclurerCE·3
DATE OF APPROVAL
7
Aplttlo. 1998
COPYRIGHT CJ 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of GAMA
1 APRIL 1998
01352·S27-00
827-1
For Traininl! Purposes Only
S27
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 27
BENDIX/KING AUDIO CONTROL SYSTEM
(Type KMA·24H·70)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*)preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
827-1 thru
827 -9/S27 -10
DATE
1 April 1998
REV. NUMBER
o
(
(
(
(
(
(
1 April 1998
827-2
For Training Purposes Only
(
(
S27
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
MODEL 208 (6758HP)
(
SUPPLEMENT
(
(C
BENDIX/KING AUDIO CONTROL SYSTEM
(Type KMA-24H-70)
(
and
(
Optional PA (Passenger Address system)
(
SECTION 1
GENERAL
(
(
(
(
(
(
(
(
(
(
(
(
(
The King Audio Control Panel (Type KMA-24H-70) is a compact
solid state unit containing all operating controls on the front of the
unit.
There are two control knobs on the far left of the panel for intercom
control, ten push button switches on the top center of the panel for
speaker audio control, ten push button switches on the bottom
center of the panel for phone audio control and two control knobs
on the far right of the panel for a multiple function Mic select switch
(includes PA position) and a speaker auto switch.
The electrical power required for operation of the audio control
panel's headphone and/or marker beacon functions is supplied by
AVIONICS BUS 1 through a "pull-off" type circuit breaker labeled
AUO/MKR.
The electrical power requirement for the speaker
function of the audio control panel is supplied by AVIONICS BUS 2
through a "pull-off" type circuit breaker labeled AUDIO AMP. The
audio control panel is functional anytime AVIONICS BUS's 1 and 2
are turned on.
(
(
(
INTERPHONE (INTERCOM SYSTEM)
The interphone system consists of a hot mic volume control and an
intercom VOX (Voice) sensitivity control which are controlled by the
two concentric control knobs on the far left of the panel. The inner
control knob controls the intercom volume only and does not affect
the other inputs.
The outer control knob when rotated fully
clockwise to the detent position provides hot mic operation When
rotated to the m'iddle range, the control knob adjusts intercom VOX
(voice) sensitivity.
1 April 1998
827-3
For Training Purposes Only
S27
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
SPEAKER/PHONE
PUSHBUnONS
(COM/NAV/OME/MKR
&
ADF)
(
MONITOR
The audio panel incorporates, in the center of the panel, two rows of ,
ten pushbutton switches, labeled SPEAKER on the top row and :,
labeled PHONE on the bottom rovv. These push buttons permit the
pilot or copilot to monitor the various communication and navigation
systems available to the operator.
When depressed, each
pushbutton connects its respective navigation and/or communication
system to either the speaker (top row of pushbuttons) or the
headphones (bottom row of pushbuttons).
To disconnect a
communication or navigation system from either the speaker or
headphones, depress the desired pushbutton a second time.
A
(
(
(
(
(
CAUTION
Cockpit speaker audio is muted when the MIC se·
lect switch Is on PA and the optional PA system
Is Installed.
MIC SELECT SWITCH (INCLUDING EMG, PA & EXT POSITIONS)
(
(
A multiple function MIC selector. control switch is located on the far
right of the panel and is the outer control knob. In the COM position
(1 thru 4). microphone audio and -keying are routed to the selected
transceiver and the receiver audio is connected to the headphones.
The PA (passenger address) speaker is functional only if the
optional PA system is installed. The EXT (external ramp hail
speaker) position is not used in this installation. In the EMG
position, the microphone and headphones are connected directly to
COM 1 as a means of fail-safe communications in the event of a
failure within the Audio Control Panel.
SPEAKER AUTO SELECT SWITCH
The SPKR AUTO selector control is located on the far right of the
panel and is the inner control knob, When the SPKR AUTO switch
(
is pulled out, it will automatically select the audio from -the (
transceiver selected by the MIC select switch to be heard on the \; -f
cockpit speaker.
1 April 1998
S27-4
For Training Purposes Only
(
KMA~24H-70AUDIO
(
PANEL
527
MODEL 208 (675 SHP)
POH SUPPLEMENT
PA (PASSENGER ADDRESS) SYSTEM (OPTIONAL)
(
(
. The PA (passenger address system) consists of two or four
speakers in the passenger area of the cabin. Passenger address is
. accomplished by placing the MIG selector switch to the PA position
and keying either the control wheel mic for headphones or the
handheld microphone. With PA selected, received communication
inputs are not muted from either the headphones or the PA
speakers, but are muted from the cockpit speakers.
The PA
speakers cannot be reliably heard in the cockpit during flight.
Switching the mic select switch out of PA will re-enable the cockpit
speakers and mute the PA system.
(
(
(
(
(
(
During operations where monitoring ATC orCTAF communications
is required or advisable, the PA position should not be selected
unless the pilot is using headphones and phone audio is selected.
(
(
SECTION 2
LIMITATIONS
(
(
(--
\
There is no change to the airplane limitations when this avionic
equipment is installed.
(
(
SECTION 3
EMERGENCY PROCEDURES
(
(
There is no change to the airplane emergency procedures when this
avionic equipment is installed.
(
(
.•
(
(
(
(
(
(
( ~;
This type of audio control panel has independent
Circuits for speaker and headphone functions. Thus,
one failure does not cause the loss of both
headphone and speaker audio. In case of · failure to
transmit over the headset MIC, the operator may still
be able to transmit using the hand-held MIC. (The
hand mic jack is connected in parallel with the
copilot's headset jack. For better modulation and less
background noise, · unplug the copilot's headset when
using the hand-held MIC).
(
827-5
1 April 1998
For Training Purposes Only
S27
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
(
(
If a complete failure of the audio control panel occurs, place
the MIC select switch in the EMG position. The microphone
and headphones will be connected directly to, COM 1. as a .
means of failsafe communications.
•
SECTION 4
NORMAL PROCEDURES
AUDIO CONTROL PANEL OPERATIONS:
1.
MIC Select Switch -- SELECT desired communications
transceiver (COM 1, 2, 3 or 4 position) for transmitting, or
PA for passenger address (optional) .
A
CAUTION
With optional PA system Installed, · ·cockpit
speaker audio is muted when MIC select switch
is on PA. Avoid selection of PA position (unless
pilot Is using headphones) when operating in
controlled or advisory airspace In order to
assure receiving ATC/CTAF communications.
2.
3.
4.
5.
6.
(
(
(
SPEAKER and/or PHONE Audio Select Button(s) -- SELECT
the COM/NAV System desired, to monitor audio over either
the speaker (top row of pushbuttons) or the headphones
(bottom row of pushbuttons).
SPEAKER AUTO Selector Knob _. PULL OUT for automatic
speaker audio on selected communications receiver.
Transceiver and/or Receiver Audio Control .·- ADJUST to
desired listening level.
InterphonelNTERCOM VOL Control -- ADJUST to desired
listening level while using hot mic.
INTERCOM VOX (voice) Sensitivity Control -- ROTATE
CONTROL knob clockwise to the middle range and then
adjust as required for desired voice activation or hot mic
intercom.
(
1 April 1998
S27-6
For Training Purposes Only
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
527
MODEL 208 (675 SHP)
5
3
2
6
2685Xl064
1.
VOX RELEASE ADJUSTMENT - The VOX release pot is accessible
through the small hole in the lower left corner of the front panel.
Clockwise adjustment will increase the time that the .intercom
remains on after speed has ended. VOX release should be adjusted
to suit user preference.
2.
INTERCOM VOX (VOICE) SENSITIVITY CONTROL - Rotate the
outer concentric knob to the fully clockwise detent position for hot
mike operation. In the middle range, the control selects VOX and
the rotation of this knob adjusts the sensitivity of the voice activated
switch. In order to setthe proper VOX sensitivity, first turn the VOX
sensitivity control clockwise until a hissing should is head in the
headphones. Next turn the control counterclockwise until the hissing
sound stops. The VOX is now properly set for the present noise
environment. It is normal to have to reset the VOX sensitivity level
whenever the noise in the cockpiVcabin changes, such as when
making large power changes.
· 3.
INTERCOM VOLUME CONTROL - The inner concentric knob is the
intercom volume control. This adjusts the intercom volume without
affecting the volume of the selected receiver audio inputs. When
. either the pilot or copilot keys the microphone to transmit, all other
intercom microphone inputs are muted to ensure that the keyed
microphone is the single source of transmitted audio. All receiver
inputs are also muted during transmissions.
4.
SPEAKER AUDIO SELECTOR BUTTONS (SPEAKER) - Selector
buttons for speaker audio output.
When pressed in, enables
operator to select any ore or more audio signals. To disconnect.
depress the pushbutton a second time.
Figure 1. Bendix/King Audio Control System Operating Controls
(Sheet 1 of 2)
S27-7
1 April 1998
For Trainin2 Purposes Only
527
MODEL 208 (675 SHP)
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
(
(
5.
SPEAKER AUTO SWITCH - When the inner concentric knob is pulled
out, it automatically selects the audio from the transceiver selected
by the MIC select switch to be heard on the cockpit speaker. Audio
from the transceiver selected by the MIC select switch is always .
head on the headphones.
. .
t
6.
MIC SELECT SWITCH (includes EMG, PA and EXT positions) - When
the outer concentric knob is in the EMG (emergency) position,
microphone audio, microphone key and headphones are connects
directly to COM 1. this provides fail-safe communications in the
event of audio panel failure. In COM positions (1 thru 4), microphone
audio and keying is connected to the appropriate transmitter and
audio from ' the selected receiver will be heard on the headphones
and on the speaker when the AUTO SPKR knob is pulled out.
During COM transmit, all received audio is muted and sidetone from
the selected transmitter is heard on speaker and phones. The PA
position is functional only if the optional PA system is installed. In
PA, all received audio is muted frbm the cockpit speakers, but not
from the headphones or PA speakers.
The EXT position is
nonfunctional in this installation . The fire warning, overspeed warning
and deciSion height alert from the radio altimeter (if installed) are
unmuted.
7.
HEADPHONES AUDIO SELECTOR BUTTONS (PHONE) - Selector -'
,buttons for headphone audio output. when pressed in, enables ( (
To '
headphone operation to anyone or more audio signals.
disconnect, depress the pushbutton(s) a second time.
(
Figure 1. Bendix/King Audio Control System Operating Controls
(Sheet 2 of 2)
1 April 1998
S27-8
For Training Purposes Only
KMA-24H-70 AUDIO PANEL
POH SUPPLEMENT
527
MODEL 208 (675 SHP)
SECTION 5
PERFORMANCE
There is no change to the airplane performance when this avionic
equipment is installed.
~
..
S27-9/S27 -10
1 April 1998
For Trainin~ Purposes Only
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
(
{
(
\ --,.
(
For Training Purposes Only
)
)
)
)
~
)
CeSSri8
(
Ar""lron Conpany
)
)
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 29
)
)
BENDIX/KING DIGITAL ADF
)
(Type KR-87)
)
y
f"
SERIAL NO.
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna Model20S
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual. if the airplane is equipped with a Bendix/King Digital ADF (Type KR87).
)
)
)
)
APPROVED
B:4eadfi~+fft'..e
Wendell W. Comell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
7
APRIL.I998
)
}f ' .
)~~,/
)
COPYRIGHT " 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS , USA
f)
Member of GAMA
1 APRIL 1998
01352·S29·00
)
)
829-1
For Trainin~ Purposes Only
S29
BENDIX/~ING ADF (TYPE KR-87)
MODEL 208 (675 SHP)
POH SUPPLEMENT
SUPPLEMENT 29
BENDIX/KING DIGITAL ADF
(Type KR-87)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o(Original)
1 April 1998
)
LOG OF EFFECTIVE PAGES
PAGE
S29-1 thru
S29-11/829-12
DATE
1 April 1998
REV. NUMBER
o
)
)
)
)
'1 April 1998
S29-2
For Training Purposes Only
)
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
SUPPLEMENT
)
r
BENDIX/KING DIGITAL ADF
(Type KR-87)
)
SECTION 1
GENERAL
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529
MODEL 208 (675 SHP)
The King Digital ADF is a panel-mounted, digitally tuned automatic
direction finder. It is designed to provide continuous 1-kHz digital
tuning in the frequency range of 200-kHz to 1799-kHz and
eliminates the need for mechanical band switching. The system is
comprised of a receiver, a built-in electronic timer, a bearing
indicator, and a KA-44B combined loop and sense antenna.
Depending on the avionics options installed, the indicator can be a
KI-227 or KI-229. Operating controls and displays for the King
Digital ADF are shown and described in Figure 1. The audio
system used in conjunction with this radio for speaker-phone
selection is shown and described in Supplement 25.
The King Digital ADF can be used for position plotting and homing
procedures, and for aural reception of amplitude-modulated (AM)
signals. The "flip-flop" frequency display allows switching between
pre-selected "STANDBY" and "ACTIVE" frequencies by pressing
the frequency transfer button. Both pre-selected frequencies are
stored in a non-volatile memory circuit (no battery power required)
and displayed in self-dimming gas discharge numerics. The active
frequency is continuously displayed in the left window, while the
right window will display .either the standby . frequency or the
selected readout from the built-in electronic timer.
The built-in electronic timer has two separate' and independent
timing functions. An automatic flight timer that starts whenever the
unit is turned on. This timer functions up to 59 hours and 59
minutes. An elapsed timer which will count up or down for up to 59
minutes and 59 seconds. When a preset time interval has been
programmed and the countdown reaches :00, the display will flash
for 15 seconds. Since both the flight timer and elapsed timer
operate independently, it is possible to monitor either one without
disrupting the other. The pushbutton controls and the bearing
indicators are internally lighted. Intensity is controlled by the RADIO
light dimming rheostat.
)
)
1 April 1998
829-3
For Trainin~ Purposes Only
529
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
MODEL 208 (675 SHP)
14
15
17
18
19
16
KI-227 INDICATOR
KI-229 OPTIONAL RMI
INDICATOR
2685X1065
2685X1066
2685X1067
Figure 1. King Digital ADF Operating Controls and Indicators
(Sheet 1 of 3)
829-4
1 April 1998
For Training Purposes Only
\',.
529'
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
)
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1.
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MODEL 208 (675 SHP)
MODE ANNUNCIATION . Antenna (ANT) is selected by the "out"
position of the ADF button. This mode improves the aural reception
and is usually used for station identification. The bearing pointer is
deactivated and will park in the 90 relative position . Automatic
Direction Finder (ADF) mode is selected by the depressed position
of the ADF bulton. This mode activates the bearing pointer. The
bearing pointer will point in the direction of the station relative to the
aircraft heading.
0
)
2.
ACTIVE FREQUENCY DISPLAY - The frequency to which the ADF is
tuned is displayed here. The active ADF frequency can be changed
directly when either of the timer functions are selected.
3.
BEAT FREQUENCY OSCILLATOR (BFO) - The BFO mode, activated
and annunciated when the "BFO" button is depressed. permits the
carrier wave and associated morse code identifier broadcast on the
carrier wave to be heard .
)
)
NOTE
)
CW signals (Morse Code) are unmodulated and no audio will
be heard without use of BFO. This type of signal is not used
in the United States air navigation. It is used in some foreign
countries and marine beacons.
)
/
,(
4.
STANDBY FREQUENCY ANNUNCIATION (FRO) - When FRO is
displayed the STANDBY frequency is displayed in the right hand
display. The STANDBY frequency is selected using the frequency
select knobs. The selected STANDBY frequency is put into the
ACTIVE frequency window by pressing the frequency transfer button.
5,
STANDBY FREOUENCY DISPLAY - Either the standby frequency.
the flight timer, or the elapsed time is displayed in this position. The
flight timer and elapsed timer are displayed replacing the standby
frequency which goes into "blind" memory to be called back at any
time by depressing the FRO button. Flight time or elapsed time .are
displayed and annunciated alternatively by depressing the FLTIET
button.
6.
TIMER MODE ANNUNCIATION - Either the elapsed time (ET) or
flight time (FLT) mode is annunciated here.
7.
FREQUENCY SELECTOR KNOBS - Selects the standby frequency
when FRO is displayed and directly selects the active frequency
whenever either of the timer functions is selected. The frequency
selector knobs may be rotated either clockwise or counterclockwise.
The small knob is pulled out to tune the 1's. The small knob is
pushed in to tune the 1D's. The outer knob tunes the 100's with rollover into the 1000's. These knobs are also used to set the desired
time when the elapsed timer is used in the countdown mode.
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Figure 1. King Digital ADF Operating Controls and Indicators
(Sheet 2 of 3)
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829-5
1 April 1998
For Trainine Purposes Only
S29
MODEL208 (675 SHP)
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
8.
OFFIVOLUME CONTROL (OFFIVOL) - Controls primary power and
audio output level. Clockwise rotation from OFF position applies
primary power to receiver; further clockwise rotation increases audio
level. Audio muting causes the audio output to be muted unless the
receiver is locked on a valid station.
9.
SET/RESET BUTTON (SET/RST) - The set/reset button when
pressed resets the elapsed timer whether it is being displayed or not.
10.
FLIGHT TIME/ELAPSED TIME MODE SELECTOR BUTTON (FLT/ET)
- The Flight Timer/Elapsed Time mode selector button when pressed
alternatively selects either Flight Timer mode or Elapsed Timer
mode.
11 .
FREQUENCy 'TRANSFER BUTTON (FRB) - The FRQ' transfer button
when pressed exchanges the active and standby frequencies. The
new frequency becomes active and the former active frequency goes
into standby.
12.
BFO BUTTON - The BFO button selects the BFO mode when in the
depressed position. (See note under item 3.)
13.
ADF BUTTON - The ADF button selects either the ANT mode or the
ADF mode. The ANT mode is selected with ; the ADF button in the
out position. The ADF mode is selected with the ADF button in the
depressed position. '
14.
INDEX (ROTATABLE CARD) - Indicates relative, magnetic, or true
heading of aircraft, as selected by H DG control. '
15.
POINTER - Indicates station bearing in degrees of azimuth, relative
to the nose of .the aircraft. When heading control is adjusted,
indicates relative; magnetic, or true bearing of radio signal.
16.
HEADING CARO CONTROL (HOG) - Rotates card to set in relative ,
magnetic, or true bearing information.
'
17.
' DOUBLEcBAR POINTER - Indicates bearing of selected AOF station.
18.
HEADING INDEX - Indicates the airplane magnetic heading on the
azimuth card.
19.
ROTATING AZIMUTH CARD - Slaved to remote heading source;
rotates as the airplane turns so that the airplane magnetic heading is
continuously displayed at the heading index.
Figure 1. King Digital ADF Operating Controls and Indicators
(Sheet 3 of 3)
1 April 1998
829-6
For Training Purposes Only
)
)
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
529
MODEL 208 (675 SHP)
)
SECTION 2
LIMITATIONS
)
)
~.
There is no change to the airplane limitations. when this avionic
equipment is installed.
)
SECTION 3
)
EMERGENCY PROCEDURES
)
There is no change to the airplane emergency procedures when this
avionic equipment is installed.
SECTION 4
)
NORMAL PROCEDURES
)
)
TO OPERATE AS AN AUTOMATIC DIRECTION FINDER:
1.
2.
3.
4.
)
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5.
6.
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>
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ADF TEST (PRE-FLIGHT or IN-FLIGHT):
1.
)
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OFFIVOL Control-~ ON.
Frequency Selector Knobs -- SELECT desired frequency in
the standby frequency display.
.
FR& Button ;- PRESS to move the desired frequency from
the standby to the active position.
ADF SPEAKER/PHONE Selector Switch (on audio control
.
panel) -- SELECT as desired.
OFFIVOL Control -- SET to desired volume level.
. ADF Button -- SELECT ADF mode and note relative bearing
on indicator.
2.
ADF Button -- SELECT ANT mode and note pOinter moves
to the 900 position.
ADF Button -- SELECT ADF mode and note the pointer
moves without hesitation to the station bearing. Excessive
pOinter sluggishness, wavering or reversals indicate a signal
that is too weak or a system malfunction .
TO OPERATE BFO:
1 . OFFIVOL Control -- ON.
J';~./
2. BFO Button- PRESS on.
\
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S29-7
1 April 1998
For Training Purposes Only
829
MODEL 208 (675 SHP)
3.
4.
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
ADF SPEAKER/PHONE SELECTOR BUnONS (on audio
control panel) -- SET to desired mode.
VOL Control -- ADJUST to desired listening level.
NOTE
A 1000-Hz tone and Morse Code identifier is heard in the
audio output when a CW signal is received.
TO OPERATE FLIGHT TIMER:
1.
2.
3.
OFFIVOL Control -- ON.
FLTfET rytode Button -- PRESS (once or twice) until FLT is
annunciated. Timer will already be .counting since it is
activated by turning the unit on . .
OFFIVOL Control -- OFF and then ON if it is desired to reset
the flight timer.
TO OPERATE ASA COMMUNICATIONS RECEIVER ONLY:
1.
·2.
3.
4.
5.
6.
OFFIVOL Control -- ON.
ADF Button -- SELECT ANT mode.
Frequency Selector Knobs -- SELECT desired frequency in
the standby frequency display.
FRB Button -- PRESS to move the desired frequency from
the standby to the active position.
ADF SPEAKER/PHONE Selector Buttons (on audio control
panel) - - SET to desired mode.
VOL Control -- ADJUST to desired listening level.
TO OPERATE ELAPSED TIME TIMER-COUNT UP MODE:
1.
2.
3.
4.
5.
OFFIVOL Control-- ON.
FLT/ET Mode Button -- PRESS (once or twice) until ET is
annunciated .
SET/RST Button -- PRESS until the ET annunciation begins
to flash.
SETfRST Button -- PRESS to start timer.
SETfRST Button -- PRESS to stop timer. Timer will reset
zero. When the SETfRST button is released the timer will
start to count again L!nless the SETfRST button is held until
the ET annunciation flashes.
. S29-8
1 April 1998
For Training Purposes Only
BENDIXfKING ADF (TYPE KR-87)
POH SUPPLEMENT
)
529
MODEL 208 (675 SHP)
NOTE
)
The Standby Frequency which is in memory while Flight Time or
Elapsed Time modes are being displayed may be called back by
pressing the FRO button, then transferred to active use by preSSing
the FRO button again.
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TO OPERATE ELAPSED TIME TIMER-COUNT DOWN MODE:
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1.
2.
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3.
)
4.
)
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OFFIVOL Control -- ON.
FLTfET Mode Button .- PRESS (once or twice) until ET is
annunciated.
SETfRST Button -- PRESS until the ET annunciation begins
to flash.
'
FREOUENCY SELECTOR KNOBS -- SET desired time in
the elapsed time display. The small knob is pulled out to
tune the 1D's. The small knob is pushed in to tune the 10's.
The outer knob tunes minutes up to 59 minutes.
)
NOTE
t
Selector knobs remain in the time set mode for 15 Seconds
after the last entry or until the SET/RST, FLTIET or FRO
button is pressed.
)
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5.
SETfRST Button -- PRESS to start countdown . When the
timer reaches 0, it will start to count up as display flashes
for 15 sec- ends.
NOTE
)
While FLT or ET are displayed, the active frequency on the
left side of the window may be changed, by using the frequency selector knobs, without any effect on the stored
standby frequency or the other modes.
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529-9
1 April 1998
For Training Purposes Only
529
MODEL 208 (675 SHP)
BENDIX/KING ADF (TYPE KR-87)
POH SUPPLEMENT
ADF OPERATIONAL NOTES:
ERRONEOUS ADF BEARING DUE TO RADIO FREQUENCY
PHENOMENA:
In the U.S., the FCC, which assigns AM radio frequencies,
occasionally will assign the same frequency to more than one
station in an area. Certain conditions, such as Night Effect, may
cause signals from such stations to overlap. This should be taken
into consideration when using AM broadcast station for navigation.
)
Sunspots and atmospheric phenomena may occasionally distort
reception so that signals from two stations on the same frequency
will overlap. For this reason it is always wise to make positive
identification of the station being tuned, by switching the function
selector to ANT and listening for station call letters.
ELECTRICAL STORMS:
In the vicinity of electrical storms, an ADF indicator pointer tends to
swing from the station tuned toward the center of the storm .
.
NIGHT EFFECT:
This is a disturbance particularly strong just after sunset and just
after dawn. An ADF indicator pointer may swing erratically at these
times. If possible, tune to the most powerful station at the lowest
frequency. If this is not .possible take the average of pointer
oscillations to determine relative station bearing.
j
MOUNTAIN EFFECT:
Radio waves reflecting from the surface of mountains may cause
the pointer to fluctuate or show an erroneous bearing . This should
be taken into account when taking bearings over mountainous
terrain.
1 April 1998
529·10
For Training Purposes Only
)
BENDIX/KING ADF (TYPEKR-87)
529
MODEL 208 (675 SHP)
POH SUPPLEMENT
COASTAL REFRACTION:
Radio waves may be refracted when passing from land to sea or
when moving parallel to the coastline. This also should be taken
into account.
SECTION 5
PERFORMANCE
)
)
There is no change to the 'airplane performance when this avionic
equipment is installed. However, the installation of an externally
mounted antenna or related external antennas, will result in a minor
reducti~n in cruise performance.
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529-11/829-12
1 April 1998
For Training Purposes Only
.>
For Training Purposes Only
)
~
)
CeSSri8
~
ATextron Company
)
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 30
)
)
BENDIX/KING DME
(Type KN-63)
)
{
SERIAL NO.
)
REGISTRATION NO.
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a Bendix/King DME KN-63.
)
)
APPROVED
B~&tfi~41fW'f
Wendell W. Corneil
Executive Engineer
Cessna Aircraft Cornpany
Delegation Option Manufacturer CE·3
DATE OF APPROVAL
~(,,/
)
7
APRIl.. 1998
COPYRIGHT c 199B
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
I)
Member of GAMA
1 APRIL 1998
01352-530-00
)
S30-1
For Training Purposes Only
530
BENDIX/KING KN-63
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 30
BENDIX/KING DME
(TYPE KN-63)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o(Original)
1 April 1998
LOG
)
)
OF EFFECTIVE PAGES
PAGE
S30-1 thru S30-6
DATE
1 April 1998
REV. NUMBER
o
)
1 April 1998
530-2
For Training Purposes Only
)
)
)
S30
BENDIX/KING KN-63
POH SUPPLEMENT
MODEL 208 (675 8HP)
SUPPLEMENT
J
j
BENDIX/KING DME (Type KN-63)
)
SECTION 1
GENERAL
)
The Bendix/King DME (Type KN-63) is the airborne "interrogator"
portion of a navigation system which supplies continuous, accurate,
slant range distance information from a fixed ground station to an
aircraft in flight.
)
)
)
)
)
)
Except for selection of the operating channel, which is selected by
the VHF navigation receiver frequency selector switches, the
Bendix/King DME is capable of ,independent operation. The
equipment consists of a KDI-572 Panel Display which contains all of
the operating controls and displays, and a remotely mounted KN-63
Receiver-Transmitter. The KN-63 transmits interrogating pulse pairs
on 200 channels between 1041 MHz and 1150 MHz; it receives
associated ground-to-air replies between 978 MHz and 1213 MHz.
The KDI-572 Panel Display digitally displays distances in nautical
miles, ground speed in knots, and time-to-station in minutes. All
displays are in self-dimming gas discharge numerics. All operating
controls and displays for the DME are shown in Figure 1, and the
functions of each are described.
NOTE
An interlock is incorporated in the DME so that information
from the other receiver cannot be displayed on the DME
when an RNAV mode is in use.
SECTION 2
LIMITATIONS
)
)/
There is no change . to the airplane limitations when this avionic
equipment is installed.
)\,
)
)
830-3
1 April 1998
For Training Purposes Only
S30
BENDIX/KING KN-63
POH SUPPLEMENT
MODEL 20a (675 SHP)
1
2
4
3
5
)
)
6
, 2685Xl068
)
)
1.
DISTANCE
DISPLAY
(NM)
DME
distance
to
VORTAC/WAYPOINT displayed in .1' nautical mile increments up
to 99.9 NM, then in increments of one nautical mile to 389 NM.
2.
DME MODE ANNUNCIATOR - Displays the DME operating mode;
NAV 1 (1); NAV 2(2); NAV 1 HOLD (1 H); NAV 2 HOLD (H2); of
the mode selector switch (6).
3.
.GROUND SPEED DISPLAY (KT) - Displays ground speed in knots
to or from VORTAC/WAYPOINT up to 999 knots (aircraft must be
flying directly to or from the VORTACIWAYPOINT for true ground
speed indication) .
4.
RNAV ANNUNCIATOR (RNV)- Indicates RNV when displayed data
is in relation to the RNAV waypoint. If the wrong DME mode is
selected during RNAVoperation, the RNV annunciator will flash.
5.
TIME-TO-STATION DISPLAY (MIN) - Displays time-to-station
(VORTAC/ WAYPOINT) in minutes up to 99 minutes (aircraft must
be flying directly to or from the Vortac/Waypoint for true time-tostation indication)
Figure 1, Bendix/King DME (Type KN-63)
(Sheet 1 of 2)
''"'' • .1'- '
1 April 1998
S30-4
For Training Purposes Only
~
S30
BENDIX/KING KN-63
MODEL 208 (675 8HP)
POH SUPPLEMENT
6.
DME MODE SELECTOR SWITCH (OFF, N1, HLD, N2) - Applies
power to the DME and selects DME operating mode as follows :
OFF:
f
NAV 1
(N1 ):
)
)
HOLD
(HLD) :
)
)
Turns DME power off . .
Selects DME operation with NO. 1 VHF navigation set;
enables channel selection by NAV 1 frequency selector
controls.
Selects DME memory circuit; DME remains channeled to
station to which it was last channeled when HOLD was
selected and will continue to display information relative to
this channel. Allows both the NAV 1 and NAV 2 navigation
receivers to be set to new operational frequencies without
affecting the previously selected DME operation.
NOTE
In the HOLD mode there is no annunciation of the VOR/DME station
frequency. However, an annunciator, labeled "1 H" or "H2",
illuminates on the DME display to flag the pilot that the DME is in the
HOLD mode.
)
)
{"
NAV2
(N2):
\. ,
)
)
Selects DME operation with No, 2 VHF navigation set;
enables channel selection by NAV 2 frequency selector
switches. Brightness of the labels for this switch is
controlled by the RADIO light dimming rheostat.
)
)
)
)
)
)(
)\
~
..
Figure 1, Bendix/King DME (Type KN-63)
(Sheet 2 of 2)
)
) .
)
)
830-5
1 April 1998
For Training Purposes Only
S30
BENDIX/KING KN-63
POH SUPPLEMENT
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when this .
.
equipment is installed.
SECTION 4
NORMAL PROCEDURES
DME OPERATION:
)
1. DME Mode Selector Switch -- SET to N1 or N2.
2. NAV 1 and NAV 2 VHF Navigation Receivers -- ON; SET
FREQUENCY selector switches to VOR/DME station
frequencies,as required.
NOTE
When the VOR frequency is selected, the appropriate DME
frequency is automatically channeled.
3.
DME SPEAKER/PHONE selector buttons (on audio control
panel) -- SET to desired mode.
SECTION 5
PERFORMANCE
. There is no change to the airplane performance when this avionic
equipment is installed. However, the installation · of an externally
mounted antenna, or several related external antennas, will result in
a minor reduction in cruise performance.
1 April 1998
S30-6
For Training Purposes Only
~
CeSSna
ATexlron Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 31
)
BENDIX/KING HF TRANSCEIVER
)
(Type KHF-950)
)
~
SERIAL NO.
)
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a Bendix/King HF Transceiver (Type
KHF-9S0).
)
)
)
APPROVED
)
)
)
.
B~dteeir;;4UW'~
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
DATEOF",PPROVAL
7
APRtl./998
f)
Member of GAMA
COPYRIGHT " 199B
)(
CESSNA AIRCRAFT
\
COMPANY
)"
WICHITA, KANSAS , USA
)
1 APRIL 1998
01352-S31 -00
)
)
831-1
For Training Purposes Only
S31
BENDIX/KING HF (TYPE KHF-950)
POH SUPPLEMENT
MODEL 208 (675SHP)
SUPPLEMENT 31
BENDIX/KING HF TRANSCEIVER
(Type KHF-950)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the _current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o(Original)
1 April 1998
)
)
LOG OF EFFECTIVE PAGES
)
PAGE
S31 ·1 thru S31 -12
DATE
1 April 1998
REV. NUMBER
o
)
)
)
".c_.
1 April 1998
S31-2
For Training Purposes Only
)
BENDIX/KING HF (TYPE KHF-950)
POH SUPPLEMENT
531
MODEL 208 (675 SHP)
SUPPLEMENT
BENDIX/KING HF TRANSCEIVER
(Type KHF-950)
j
)
SECTION 1
GENERAL
)
)
)
)
)
)
)
~
)
)
)
)
)
)
)
)
The Bendix/King KHF-950 is a solid-state HF single sideband
transceiver system providing the pilot access to 99 programmable
channels plus 280,000 operating frequencies in the 2000 to
29,999.9 kHz range. It provides receive-only and simplex operation,
as well as semi-duplex capability (transmission on one frequency,
reception on another) to interface with maritime radio-telephone
networks (public correspondence). The HF Transceiver system
consists of a KCU-9S1 panel-mounted control display unit, a remote
mounted KAC-9S2 power amplifier/antenna. coupler, a remotemounted KTR-953 Receiver exciter and an external-mounted, fixedwire. mediuml high frequency antenna.
The KCU-9S1 Control Display Unit uses electronic gas discharge
read outs to display frequency, channel and mode of operation. The
99 channels can be programmed by the pilot on the ground or in
the air, and the nonvolatile memory stores this information even
when the system is turned off. To add to the operational
convenience, the antenna coupler will automatically tune the
antenna to the specific frequency desired simply by keying the
mike.
.
All operating controls for the KCU-951 Contr"
)
30
KI·206 VOR /LOC/ILS INDICATOR
Figure 1. Bendix/King Nav/Com (Type KX-165)
Operating Controls and Indicators (Sheet 1 of 4)
)
833-5
28 March 2001
For Training Purposes Only
S33
MODEL 208 (675 SHP)
BENDIX/KING KX-165 NAV/COM
POH SUPPLEMENT
1.
OPERATING COMM FREQUENCY DISPLAY (USE) -- Displays
ACTIVE communication frequency.
2.
TRANSMIT INDICATOR -- "T"
transceiver is in the transmit mode.
3.
STANDBY COMM FREQUENCY DISPLAY (STANDBY) -- Displays
STANDBY communication frequency.
4.
OPERATING NAV FREQUENCY DISPLAY (USE) -- Displays ACTIVE
. navigation frequency.
5.
STANDBY NAV FREQUENCY DISPLAY (STANDBY/RAD) -- Displays
STANDBY navigation frequency or VOR radial.
6.
NAV FREQUENCY SELECTOR KNOBS -- The larger selector knob is
used to change the MHz portion of the frequency display; the smaller
knob (PULL RAD) changes the kHz portion in 50-kHz steps. At either
band-edge of the 108.00 to 117.95 MHz frequency spectrum , an offscale rotation will ·wrap the display around to the other frequency
band-edge (Le., 117.95 advance to 108.95 with MHz knob rotation, or
117.00 with kHz knob rotation). Remote DME and internal glide slope
frequencies are also controlled by these selector knobs . When small
knob is pulled out, the radial from the VOR in USE is displayed in the
STANDBY/RAD frequency display. If VOR signal is too weak, or an
ILS frequency has been selected , a digital warning flag is activated
consisting of three dashes "---" displayed in · the STANDBY/RAD i
window. Any frequency selection made with the radial display (RAD) .
active will be displayed in the USE display, without any effect on the ·
(non-displayed) stored standby frequency.
appears
to
indicate
that
the
i.
NAV FREQUENCY TRANSFER BUTTON -frequencies in the USE and STANDBY displays.
8.
NAV VOLUME CONTROL (PULL IDENT) -- Adjusts volume of
navigation receiver audio. When the knob is pulled out, the Ident
Signal plus voice may be heard.
9.
COMM FREQUENCY SELECTOR KNOBS -- The outer, larger
selector knob is used to change the MHz portion of the frequency
display; the smaller knob (PULL 25K) changes the kHz portion. This
smaller knob is designed to change the indicated frequency in steps
of 50-kHz when it is pushed in, and in 25-kHz steps when it is pulled
out. At either band-edge of the 118-135 MHz frequency spectrum, an
off scale rotation will wrap the display around to the other frequency
band-edge (Le., 135 MHz advances to 118 MHz) .
10.
COMM FREQUENCY TRANSFER BUTTON -- Interchanges the
frequencies in the USE and STANDBY displays.
Interchanges
the
Figure 1. Bendix/King Nav/Com (Type KX-165)
Operating Controls and Indicators (Sheet 2 of 4)
28 March 2001
IS33-6
For Training Purposes Only
)
BENDIX/KING KX-165 NAV/COM
POH SUPPLEMENT
533
MODEL 208 (675 SHP)
)
11.
COMM VOLUME CONTROL (OFF/PULL TEST) -- Rotary switch turns
set on/off and adjusts volume of communication receiver audio.
When pulled out disables automatic squelch control.
12.
KI-525A HORIZONTAL SITUATION INDICATOR (HSI) -- Provides a
pictorial presentation of aircraft deviation relative to VOR radials or
localizer beams. It also displays glide slope deviations. and gives
heading reference with respect to magnetic north. The gyro is
electrically driven.
13.
NAV FLAG - Flag IS In view when the NAV receiver signal is
inadequate. When a NAV flag is present in the navigation indicator
(KI-525A). KAP/KFC-150 autopilot operation is not affected. The
pilot must monitor the navigation indicator for a NAV flag to ensure
that the autopilot and/or flight director are tracking valid navigation
information. THE KFC-225 will revert to ROL mode with a NAV flag.
)
14.
LUBBER LINE - Indicates aircraft magnetic heading on compass
card (21).
)
15.
HEADING WARNING FLAG (HOG) - When flag is in view. the
heading display is invalid. If an HOG flag appears, and a lateral
mode (HOG. NAV. APR, or APR BC) is' selected. the autopilot will be
disengaged. The autopilot may be re-engaged in the basic wingslevel mode along with any vertical mode. The CWS switch would be
used to manually maneuver the aircraft laterally.
16.
COURSE BEARING POINTER - Indicates selected VOR course or
localizer course on the compass card (21). The selected VOR radial
or localizer heading remains set on the compass card when the
compass card (21) rotates.
17.
TO/FROM INDICATOR FLAG - indicates direction of VOR station
relative to the selected course.
18.
DUAL GLIDE SLOPE POINTERS - Indicate on the glide slope scale
(19) airplane displacement from glide slope beam center. Glide
slope pOinters in view indicate a usable glide slope signal is being
received. (Glide slope pointers not shown).
19.
GLIDE 'SLOPE SCALES - Indicate displacement from glide slope
beam center. A glide slope deviation bar displacement of 2 dots
represents full-scale (0:7°) deviation above or below glide slope
beam centerline.
20.
HEADING SELECTOR KNOB . Positions the heading bug (25) on
compass card (21) by rotating the heading selector knob. The bug
rotates with the compass card.
)
)
l
)
)
)
)
)
)
)
z
)
)
)
)
)
}
\
)'
)
"
Figure 1. Bendix/King Nav/Com (Type KX-165)
Operating Controls and Indicators (Sheet 3 of 4)
)
)
)
833-7
28 March 2001
For Trainim! Purposes Only
S33
MODEL 208 (675 SHP)
BENDIX/KING KX-165 NAV/COM
POH SUPPLEMENT
21.
COMPASS CARD - Rotates to display heading of airplane with
reference to lubber line (14) on HSI.
22 .
COURSE SELECTOR KNOB - Positions the course bearing
pointer (16) on the compass card (21) by rotating the course
selector knob.
.
23 .
COURSE DEVIATION BAR (D-BAR) - The center portion of the
omni bearing pointer moves laterally to pictorially indicate the
relationship of airplane to the selected course.
It indicates
degrees of angular displacement, or nautical miles from RNAV, or
GPS courses .
24.
COURSE DEVIATION SCALE - A course deviation bar
displacement of 5 dots represents full scale (VOR = ±10°, LOC
= ±2 112°, RNAV = Snm, RNAV APR = 1 1/4nm . GPS = Snm.
1nm, or 0.3nm) deviation from beam centerline.
25.
HEADING BUG - Moved by heading selector knob (20) to select
desired heading .
26.
COURSE INDEX - Indicates selected VOR course.
27.
NAVIGATION FLAG (NAV) - When visible, red NAV flag indicates
unreliable VOR signals, or improperly operating equipment. Flag
disappears when a reliable VOR signal is being received.
28 .
TO-FROM INDICATOR - Operates only with a VOR signal. With ;
usable VOR signal, indicates whether selected course is "TO" or
"FROM" station . With usable localizer signal. the indicator is not
in view.
29.
GLIDE SLOPE DEVIATION NEEDLE - Indicates deviation from
ILS glide slope.
30.
COURSE DEVIATION POINTER - Indicates course deviation from
selected omni course or localizer centerline .
31.
RECIPROCAL COURSE INDEX - Indicates reciprocal or selected
VOR course .
32.
OMNI BEARING SELECTOR (OBS) - Rotates OBS course card to
select desired course.
33 .
OBS COURSE CARD - Indicates selected VOR course under
course index.
34.
GLIDE SLOPE FLAG (GS) - When visible, red GS flag indicates
unreliable glide slope signal or improperly operating equipment.
Flag disappears when reliable glide slope signal is being .
received .
"
Figure 1. Bendix/King Nav/Com (Type KX-165)
Operating Controls and Indicators (Sheet 4 of 4)
833-8
28 March 2001
For Training Purposes Only
)
)
)
)
)
-;!
BENDIX/KING KX-165 NAV/COM
POH SUPPLEMENT
SECTION 3
EMERGENCY PROCEDURES
)
)
~.
)
)
533
MODEL 208 (675 SHP)
There is no change to the airplane emergency procedures when
this avionic equipment is installed. However, if the frequency
readouts fail, the radio will remain operational on the' last frequency
selected. The frequency control should not be moved due to the
difficulty of obtaining a known frequency under this condition .
SECTION 4
NORMAL PROCEDURES
)
)
COMMUNICATION RECEIVER-TRANSMITTER OPERATION : .
1.
)
2.
{
3.
OFF/PULL TEST Volume Control -- Turn clockwise; pull out
and adjust to desired audio level; push control back in to
activate the automatic squelch.
MIC Selector Switch (on audio control panel) -- SET to COM
1.
4.
5.
6.
)
SPEAKER/PHONE Selector Buttons (on audio control panel)
-- SET to desired mode.
COMM Frequency Selector Knobs -- Select desired
operating frequency.
COMM Transfer Button -- PRESS to transfer desired
frequency from ' the "STANDBY" display into the "USE"
display.
Mic Button:
a.
To transmit -- DEPRESS and SPEAK in microphone.
)
NOTE
)
•
During COMM Transmission, a lighted "T" will
appear between the "USE" and "STANDBY"
displays to indicate that the transceiver is operating
in the transmit mode.
•
)'-,
Phone sidetone may be selected by pushing the
AUTO selector button (on audio control panel) in the .
PHONE position.
)
b.
)
)
)( .
\
To Receive -- RELEASE mic button.
)
)
)
28 March 2001
For Training Purposes Only
833
BENDIX/KING KX-165 NAV/COM
POH SUPPLEMENT
MODEL 208 (675 SHP)
NAVIGATION RECEIVER OPERATION:
I
A
WARNING
The pilot should be aware that on the Cessna
Model 208 equipped with the vertical fin mounted
combination glide slope and omni antenna, the
propeller RPM should be set at MAX (1900 RPM)
during ILS approaches to avoid any possibility of
oscillations of the glide slope deviation pointer
caused by propeller Interference.
1.
2.
3.
4.
I
5.
6.
7.
8.
NAV Volume Control (PULL IDENT) -- SET to desired audio
level.
SPEAKER/PHONE Selector Buttons (on audio control panel)
-- SET to desired mode.
PULURAD Knob -- PULL out to display the VOR radial from
the station in use.
NAV Frequency Selector Knobs -- SELECT desired
operating frequency.
NAV TRANSFER BUTTON -- PRESS to transfer desired .
frequency from the "STANDBY" display into the "USE" \
display.
NAV Volume Control-a.
ADJUST to desired audio level.
b.
PULL out to identify station.
NAV Frequency Selector Knobs -- SELECT new standby
frequency, if desired.
PULL RAD Knob -- PULL out to display the VOR radial from
the station in USE.
.l
NOTE
The VOR radial will be displayed in the NAV
STANDBY/ RAD display. If the signal is too weak, or
an ILS frequency was selected, three dashes "---"
will be displayed instead. Pulling out this knob does
not affect the stored standby frequency. Any further
NAV frequency selection will be displayed directly in
the USE display until the smaller knob is pushed
back in. The Transfer button function is unchanged
during radial display use.
28 March 2001
533-10
For Training Purposes Only
)
)
I
BENDIX/KING KX-165 NAV/COM
)
POH SUPPLEMENT
I
,
S33
MODEL 208 (675 SHP)
)
)
9.
I
)
Course Selector Knob (on HSI indicator) or OBS Knob (on
KI-206) -- SELECT desired VOR radial or localizer course.
l
SECTION 5
PERFORMANCE
)
)
)
There is no change to the airplane performance when this avionics
equipment is installed. Since this avjonics equiPme.nt is .standard I
on this airplane model, all airplane performance data in the Pilot's
Operating Handbook includes the effect of this installation.
)
)
)
)
)
)
)
I
?
y(
)
)
)
)
)
)
)
)
)
y\ ,
S33-11/S33-1
28 March 2001
For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
)
~
CeSSna
/'
ATexlron Company
J.
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 34
)
)
BENDIX/KiNG RADAR ALTIMETER
)
(TYPE KRA-10A)
)
}.
"
SERIAL NO.
)
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a Bendix/King Radar Altimeter
(Type KRA-1 OA).
)
)
)
)
APPROVED
)
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
)
)
DATE OF APPROVAL
)
)(
)
)
B+&ffi~fW'~
\
,
7 APRtL./998
COPYRIGHT " 199B
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of GAMA
1 APRIL 1998
D1352·S34-00
)
)
834-1
For Training Purposes Only
534
RADAR ALTIMETER (KRA-10A)
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 34
BENDIX/KING RADAR ALTIMETER
(TYPE KRA-10A)
Use the Log of Effective Pages to determine the current status
. of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
. Revision Level
o (Original)
Date of Issue
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
S34-1 th ru S34-6
DATE
1 April 1998
REV. NUMBER
o
)
1 April 1998
534·2
For Training Purposes Only
RADAR ALTIMETER (TYPE KRA-10A)
POH SUPPLEMENT
S34
MODEL 208 (675 SHP)
)
)
SUPPLEMENT
J
BENDIX/KING RADAR ALTIMETER
(Type KRA-10A)
SECTION 1
GENERAL
)
)
)
)
\.
)
)
The The Bendix/King Radar Altimeter (Type KRA-10A), shown in
Figure 1, consists of a panel-mounted indicator, a remote mounted
receiver/transmitter and an antenna.
The Radar Altimeter (depending upon terrain reflectivity and aircraft
bank angle) gives an absolute altitude indication from 2500 feet
AGL to 35 ± 15 feet AGL. It provides continuous selection of
warning altitude and annunciation of descent to that altitude by both
a DH (decision height) light and an aural warning. Climbing through
the selected warning altitude extinguishes the DH light. The DH light
is automatically dimmed by a photo cell. Indicator lighting is
controlled by the RADIO light dimming rheostat.
The Radar Altimeter remote receiver/transmitter is all solid-state and
operates on 28-volt primary power. Complete self-test may be
accomplished both on preflight and in-flight.
)
SECTION 2
LIMITATIONS
)
)
)
There is no change to the airplane limitation when this avionic
eqUipment is installed.
)
SECTION 3
EMERGENCY PROCEDURES
)
}
)
There is no change to the airplane emergency procedures when this
avionic equipment is installed.
)
. \.
)
)
)
)
)
834-3
1 April 1998
For Training Purposes Only
S34
MODEL 208 (675 SHP)
RADAR ALTIMETER (TYPE KRA-10A)
POH SUPPLEMENT
2
3
6--+
4
5---
)
)
2685X1074
1.
DECISION HEIGHT LIGHT (DH)· - Alerts that the airplane is at or
below the selected decision height.
2.
POINTER - Indicates the airplane's absolute altitude.
3.
DH BUG - Indicates the selected alert altitude which. when reached.
will trigger an aural and visual warning .
4.
ALTITUDE SCALE - Indicates height above ground level in feet from
2500 to 20.
5.
DH SELECTITEST KNOB (PUSH TO TEST fj, ) - Rotates to select the
position of the DH Bug and presses to test the altimeter for proper
operation.
6.
MASK - Hides pointer when above 2500 feet AGL or the receiver
experiences loss of signal.
Figure 1. King Radar Altimeter (Type KRA-10A)
1 April 1998
S34-4
For Training Purposes Only
)
RADAR ALTIMETER (TYPE KRA-10A)
POH SUPPLEMENT
S34
MODEL 208 (675 SHP)
)
SECTION 4
NORMAL PROCEDURES
)
)
)
)
)
)
)
PREFLIGHT AND IN-FLIGHT SELF-TEST:
1.
2.
3.
4.
)
)
5.
)
)
AVIONICS MASTER Switch -- ON.
DH Bug -- SET to 20 feet.
DH SelectlTest Knob -- DEPRESS and HOLD. The indicated
altitude should be 50 ±5 feet and the DH lamp should be
off.
DH SelectlTest Knob _. DEPRESS and TURN slowly
clockwise. The DH lamp should light and a two-second
audio tone will sound when the DH bug reaches 50 ±S feet.
DH SelectiTest Knob -- RELEASE. The DH lamp will go out
and the painter will move clockwise behind the mask. When
flying at an altitude below 2500 feet AGL, pointer will remain
in view.
)
NOTE
)
)
)
)
)
)
)
Ground operation near large hangars, other aircraft, water
puddles and other nearby objects may cause the pointer to
come into view. This does not indicate a system malfunction
since 'the reflections constitute a real signal.
NORMAL OPERATION:
1.
2.
AVIONICS MASTER Switch -- ON.
DH Bug -- SET as desired.
A CAUTION
)
)
)
)
)
The radar altimeter must not be used to Identify
the MDA (Minimum Descent Altitude) or DH
(Decision Height) while making an Instrument
approach.
):
)
)
)
)
)
1 April 1998
F r Trainin Pur oses Only
S34
RADAR ALTIMETER (TYPE KRA-10A)
POH SUPPLEMENT
MODEL 208 (675 SHP)
OPERATIONAL NOTES:
1.
2.
3.
4.
5.
6.
During take-off, radar altimeter indications are unreliable
until after approximately the first 15 seconds after climbing ;
above 50 feet altitude.
'
Depending upon terrain reflectivity, initial and/or reliable
indications during descents through the 2500-foot level may
not occur until the aircraft has reached absolute altitudes as
low as 1500 feet.
Accuracy in level flight or in descents at rates up to 1000
FPM is within 7% or 80 feet, whichever is greater.
The pointer will disappear from view below 2500 feet if the
ground return Signal is lost. The pointer may also disappear
from view momentarily when the aircraft is in a bank in
excess of 15° (above 2000 feet) or 45° (below 1000 feet) .
Once the indicator has reached 35 ±15 feet during landing
approach, further indications in this range are unreliable,
since the indicator may dwell briefly in this range even as
the aircraft descends further.
The pOinter will move to the OFF pOSition if primary power is
lost.
SECTION 5
PERFORMANCE
)
)
)
There is no change to the airplane performance when this avionic
equipment is installed. However, the installation of an externally
mounted antenna or several related external antennas, will result in
minor reduction in cruise performance.
)
)
)
)
)
)
)
1 April 1998
S34·6
For Training Purposes Only
)
)
)
~
)
)
Cessna
f
ATextron Company
)
)
Pilot's Operating Handbook and
)
FAA Approved Airplane Flight Manual
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 35
)
)
BENDIX/KING RADIO MAGNETIC INDICATOR
)
(TYPE KI-229)
)
{
)
SERIAL NO.
)
REGISTRATION NO.
)
This supplement must be inserted into Section 9 of the Cessna Model 20B
(675 SHP) Pilot's Operating t"iandbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with a Bendix/King Radio Magnetic
Indicator (Type KI-229).
)
)
APPROVEDB+&ffi~+,,,·t
)
)
Wendell W. Comell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
)
)
DATE OF APPROVAL
J(
)
",-
J
- -'-
7 ApR., L. 1998
COPYRIGHT" 1998
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS. USA
o
Member of GAMA
1 APRIL 1998
01352-S35-00 '
)
)
)
S35-1
For Traininl! Purooses Onlv
535
BENDIX/KING AMI (TYPE KI-229)
POH SUPPLEMENT
MODE.L 208 (675 SHP)
SUPPLEMENT 35
BENDIX/KING RADIO MAGNETIC INDICATOR
(TYPE KI-229)
)
)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revi sion Level
Date of Issue
o (Original)
1 April 1998
)
)
)
)
)
)
LOG OF EFFECTIVE PAGES ·
)
PAGE
835-1 thru
835-7/S35-8
DATE
REV. NUMBER
)
)
1 April 1998
o
)
)
)
)
)
)
)
)
. 1 April 1998
835-2
)
For Training Purposes Only
BENDIX/KING RMI (TYPE KI -229)
POH SUPPLEMENT
535
MODEL 208 (675 SHP)
SUPPLEMENT
BENDIX/KING RADIO MAGNETIC INDICATOR
(TYPE KI-229)
SECTION 1
GENERAL
)
)
)
X
)
)
)
)
)
)
)
)
The Bendix/King Radio Magnetic Indicator (RMI) is used in
conjunction with other airborne navigation equipment to aid the pilot
in navigating the airplane. The RMI eliminates the need for many of
the mental computations necessary for determining the airplane
position.
The RMI is a panel mounted navigation instrument that combines
the display of VOR and ADF bearing information with the airplane
heading on a single instrument. The VOR and ADF magnetic
bearings to the selected stations are displayed by individual rotating
pointers against the background of a rotating azimuth card. The
azimuth card is driven by the slaved magnetic compass system in
the airplane and continuously indicates airplane heading. Thus, the
relative bearing between the aircraft heading and the station is
pictorially displayed.
Each pointer in the Type KI-229 RMI is dependent on its associated
receiver for indicating bearings. A single-bar pointer indicates VOR
bearings and a double-bar pointer indicates ADF bearings. Two
NAV receivers supply VOR signals to the RMI for selection. When
one of the VOR receivers is a KNS-81 Area. Navigation System, the
single-bar pointer can indicate the RNAV waypoint bearing. A twoposition selector switch (NAV 11NAV 2) on the instrument panel
selects the desired VOR signal for display of bearing information.
The KI-229 RMI is internally lighted. Intensity is controlled by the
RADIO light dimming rheostat.
)
SECTION 2
LIMIT AllONS
)
There is no change to the airplane limitations when this avionic
equipment is installed.
)
1 April 1998
S35-3
For Training Purposes Only
S35
BENDIX/KING RMI (TYPE KI-229)
MODEL 208 (675 SHP)
POH SUPPLEMENT
3
2
)
)
4
)
5
)
)
)
6--';"
6
)
6
NAV:1
2.
i
RMI
\,
HAV'
RMI
1.
)
4
4
)
2685X1075
2685X1076
ROTATING AZIMUTH (COMPASS) CARD - Rotates as the airplane
turns so that the airplane magnetic heading is continuously displayed
at the heading index.
HEADING INDEX - Indicates the airplane magnetic heading on the
azimuth card.
3.
DOUBLE-BAR POINTER - Indicates the magnetic bearing to the
station to which the ADF is tuned.
4.
INDICES - Four reference marks spaced 45 degrees between the
Heading Index and Cardinal Points.
5.
SINGLE-BAR POINTER - Indicates the magnetic bearing to the
selected VOR station.
)
)
)
6.
CARDINAL POINT - One of the four main points on a compass.
Cardinal points are spaced 90 degrees apart.
)
7.
NAV I / NAV 2 FUNCTION SWITCH - Selects either NAV 1 or NAV 2
VOR signal for display by the single-bar pOinter.
)
Figure I. King Radio Magnetic Indicator (Type KI-229)
1 April 1998
835-4
For Training Purposes Only
)
)
BENDIX/KING RMI (TYPE KI-229)
POH SUPPLEMENT
535
MODEL 208 (675 SHP)
)
SECTION 3
)
EMERGENCY PROCEDURES
)
J
)
There is no change to the airplane emergency procedures when this
avionic equipment is installed.
SECTION 4
)
NORMAL PROCEDURES
)
)
NORMAL OPERATION:
)
NOTE
)
)
)
)
)
{
)
Operation of the RMI is dependent upon input information
from the compass system (slaved directional gyro or HSI),
the associated VHF navigation and ADF receivers. Refer to
the appropriate supplements in this section for operation of
this equipment.
1.
Compass Cards (on RMI and HSI) -- CHECK heading
indications on RMI and HSI the same.
2.
AOF Receiver -- SELECT STATION on receiver. The doublebar pointer will indicate the magnetic bearing to the station.
)
)
)
)
)
)
)
NOTE
If the 'ADF receiver is turned OFF, the double-bar pointer
will remain fixed in its last position .
3.
NAV 1-2 Selector Switch (for RM I) -- SET to NAV 1 or NAV
2 and select VOR station on the associated NAV receiver.
The single-bar pointer will indicate the magnetic bearing to
the station.
)
NOTE
)
)
)
This reading is equivalent to the "TO" course reading
obtained with the standard COl omni bearing selector. The
"FROM" radial of the VOR station is obtained by reading
the opposite end of the pointer.
)
)
S35-5
1 April 1998
For Training Purposes Only
S35
BENDIX/KING RMI (TYPE KI-229)
POH SUPPLEMENT
MODEL 208 (675 SHP)
AWAANING
• If the AMI Compass Card Is not tracking the
Directional Gyro or HSI, the VOR bearings are
invalid. This may be caused by a failure In the
AMI, Slaved Compass System, or a loss of
power from the Autopilot Computer or AC
Inverter on aircraft without autopilot.
• The ADF Indications are valid relative to the
nose of the aircraft only and may be used by
referring to the Heading Index and 45 degree
. indices on the RMI.
RMI TEST:
1.
ADF Receiver -- TUNE to usable frequency with ADF
mode selected.
2.
ADF Button (On KR-87 Receiver) -- SELECT ANT mode.
Double- bar pointer will slew to the three o'clock position.
3.
ADF -- SELECT ADF mode and OBSERVE that double-bar
pointer (on RMI) returns to the same station bearing as in
step 1 to indicate a normal operation.
NOTE
If the ADF Receiver is turned OFF, the double-bar pointer
will remain fixed in its last position.
4.
5.
VOR Receiver -- TUNE to usable VOR frequency.
VOR Receiver -- TURN OFF. Single-bar pointer will slew to
the three o'clock position.
6.
VOR Receiver -- TURN ON and OBSERVE that the singlebar painter (on RMI) returns to the same station bearing as
in step 4 to indicate a normal operation.
S35-6
1 April 1998
For Training Purposes Only
BENDIX/KING RMI (TYPE KI-229)
POH SUPPLEMENT
S35
MODEL 208 (675 SHP)
)
)
NOTE
)
If the selected VOR Receiver is turned off or a reliable
signal is not being received , or an ILS frequency is
selected, the single-bar pointer will move to the stowed
position (fixed at the 3 o'clock position).
)
)
SECTION 5
PERFORMANCE
)
)
)
There is no change to the airplane performance when this avionic
equipment is installed in addition to that which occurs with
installation of the ADF or VOR antennas.
)
)
x~
)
)
)
)
)
)
)
)
Jr .
) \ ',::, ," .
)
)
)
S35-7/S35-8
1 April 1998
For Trllining Purposes Only
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purlloses Only
)
)
)
~
)
)
Cessna
J
A Texlron Company
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 36
)
)
BENDIX/KING RADIO MAGNETIC INDICATOR
(TYPE KNI-582)
)
)
J,
SERIAL NO.
)
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, ifthe airplane is equipped with a Bendix/King Radio Magnetic
Indicator (Type KNI-582).
)
)
)
APPROVED
)
)
)
DATE OF APPROVAL
APRIl.. 1998
Member of GAMA
COPYRIGHT " 1998
)(
\
'<_ , ,~, _ .:.i
)
7
f)
)
)
B:»utdfJ/: ~*,,,,~
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE· 3
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS, USA
1 APRIL 1998
D1352-S36-01
REVISION 1 - 13 OCTOBER 1999
)
)
)
S36-1
For Training Purposes Only
S36
BENDIX/KING RMI (TYPE KNI-582)
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 36
BENDIX/KING .RADIO MAGNETIC INDICATOR
(TYPE KNI-582)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
)
)
Revision Level
Date of Issue
)
o (Original)
1 April 1998
13 October 1999
)
Revision 1
LOG OF EFFECTIVE PAGES
)
PAGE
DATE
• 836-1 thru 836-3
836-4 thru 836-6
13 October 1999
1 April 1998
1 April 1998
836-7 JS36-8
REV. NUMBER
1
o
o
APPRO~~........:;
Wendell W. Comeil
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
DATE OF APPROVAL
13 Oc. TOIl£~ 1Sf)~
536-2
13 October 1999
For Training Purposes Only
)
)
BENDIX/KING RMI (TYPE KNI-582)
POH SUPPLEMENT
536
MODEL 208 (675 SHP)
)
SUPPLEMENT
)
)
j
BENDIX/KING RADIO MAGNETIC INDICATOR
(TYPE KNI-582)
)
SECTION 1
GENERAL
)
)
)
r
)
}
)
)
The Bendix/King KNI-582 Radio Magnetic Indicator (RMI) is used in
conjunction with other airborne navigation equipment to aid the pilot
in navigating the airplane. -The RMI eliminates the need for many of
the numerical and graphical computations necessary for
determining the airplane position.
The RMlis a panel mounted navigation instrument that combines
the display of NAV and ADF bearing information with the airplane
heading on a single instrument. The NAV and ADF magnetic
bearings to the selected stations are displayed by individual rotating
pointers against the background of a rotating azimuth card. The
azimuth card is driven by the slaved magnetic compass system in
the airplane and continuously indicates airplane heading. Thus, the
relative bearing between the aircraft heading and the station is
pictorially displayed.
Each pointer in the KNI-582 RMI is dependent only on its
associated receiver for indicating bearings. A single-bar pointer
indicates NAV 1 or ADF bearings and a double-bar pointer indicates
NAV 2 or ADF bearings. The choice of NAV or ADF information
displayed by each pointer is determined by the corresponding front
panel display switch.
For airplanes equipped with a single NAV/COM, the single-barl
pointer and the double-bar pointer both indicate NAV 1 or ADF.
)
Should a localizer frequency be selected or the NA V receiver
indicate a flagged condition, the NAV pointer will slew to the 3
o'clock position.
x' --
A H DG flag falls into view in the upper left corner of the display
when the heading information being displayed is invalid.
)
)
)
)
)
13 October 1999
S36-3
For Training Purposes Only
S36
BENDIX/KING RMI (TYPE KNI-582)
POH SUPPLEMENT
MODEL 208 (675 SHP)
1
9
2
)
)
3
)
)
)
4
6
-
5
Indicates the airplane
2685X1077
1.
HEADING INDEX
the azimuth card.
magnetic
heading on
2.
ROTATING AZIMUTH (COMPASS) CARD - Rotates as the airplane \
turns so that the airplane magnetic heading is continuously displayed
at the heading index.
3.
DOUBLE-BAR POINTER - Indicates the magnetic bearing to NAV 2
or the ADF station. Will slew to the 3 o'clock position if in NAV mode
and a ,localizer frequency is selected, or the NAV receiver flags.
4.
DOUBLE -BAR POINTER DISPLAY SWITCH - Dual
pushbutton switch used to select either NAV 2 or ADF mode.
5.
DOUBLE-BAR POINTER MODE INDICATOR - Indicates either NAV 1
or ADF mode.
6.
SINGLE-BAR POINTER MODE INDICATOR - Indicates either NAV 1
or ADF mode.
1.
SINGLE-BAR POINTER DISPLAY SWITCH - Dual position pushbutton
switch used to select either NAV 1 or ADF mode.
B.
COMPASS (HDG) FLAG - Comes into view whenever heading
information is in- valid .
9.
SINGLE-BAR POINTER - Indicates the magnetic bearing to NAV 1 or ,
the ADF station. Will slew to the 3 o'clock position if in nav mode and '
a localizer frequency is selected, or the NAV receiver flags.
!
position
Figure 1. King AMI (Type KNI-582)
Operating Controls and Indicators
For Training Purposes Only
)
)
)
)
1 April 1998
836-4
)
BENDIX/KING RMI (TYPE KNI-582)
POH SUPPLEMENT
SECTION 2
LIMITATIONS
)
{.
)
There is no change to the airplane limitations when this avionic
equipment is installed.
SECTION 3
EMERGENCY PROCEDURES
)
)
)
There is no change to the airplane emergency procedures When this
avionic equipment is installed.
SECTION 4
)
NORMAL PROCEDURES
)
)
S36
MODEL 208 (675 SHP)
NORMAL OPERATION:
)
NOTE
)
(
)
Operation of the RMI is dependent upon input information
from the compass system (slaved directional gyro), the
associated VHF navigation and ADF receivers. Refer to the
appro'prlate supplements in this section for operation of this
equipment.
1.
Compass Cards (on AMI and HSI) -- CHECK heading
indications on RMI and HSI the same.
2.
ADF Receiver -- TUNE to usable frequency with ADF mode
selected.
3.
Single or Double Bar Pointer Display Switch -- SELECT ADF
mode.
4.
READ magnetic bearing to the ADF station under the
selected pointer.
)
)
)
)
)
)
)
NOTE
l \,.:..,:~;.:;~/
)
)
If the ADF receiver is turned off, the selected painter will
remain fixed in its last position .
)
)
S36-5
1 April 1998
For Training Purposes Only
S36
MODEL 208 (675 SHP)
5.
6.
7.
BENDIX/KING RMI (TYPE KNI-582)
POH SUPPLEMENT
NAV Receiver - TUNE to usable VOR frequency.
Single or Double-Bar Pointer Display Switch - SELECT NAV
mode. Choose double-bar pointer if NAV 2 is desired or
single-bar pointer for NAV 1.
.
READ indicated magnetic bearing to the VOR station under :
the selected pointer.
NOTE
•
If the NAV receiver is turned off or a IQcalizer frequency
is selected, the pointer will slew to the 3 o'clock position.
•
This reading is equivalent to the "TO" course reading
obtained with the standard COl omni bearing selector.
The radial of the VOR station is obtained by reading the
opposite end of the.pointer.
RMI TEST:
1.
2.
3.
4.
ADF Receiver -- TUNE to usable frequency with ADF mode
selected.
Single or Double Bar Pointer Display Switch -- SELECT ADF (
mode.
.
ADF Button (On KR-87 Receiver) -- SELECT ANT mode.
Selected RMI pointer will slew to the 3 o'clock position.
ADF Button (On KR-87 Receiver) -- SELECT ADF mode and
OBSERVE that selected RMI pointer returns to the same
station bearing as in step 2 to indicate normal operation.
NOTE
If the ADF receiver is .turned off, the selected pointer will
remain fixed in its last position.
5.
6.
7.
NAV Receiver (NAV 1 or NAV 2) -- TUNE to usable VOR
frequency.
Single or Double Bar Pointer Display Switch (as appropriate
to the selected NAV) -- SELECT NAV mode.
NAV Receiver -- TURN OFF. Appropriate RMI pointer will
slew to the 3 o'clock position.
1 April 1998
836-6
For Training Purposes Only
)
BENDIX/KING RMI (TYPE KNI-582)
POH SUPPLEMENT
8.
)
)
536
MODEL 208 (675 SHP)
NAV Receiver -- TU RN ON and observe that the appropriate ·
RMI pOinter returns to the same station bearing as in step 6
to indicate normal operation .
j
NOTE
)
If the selected NAV receiver is turned off or a reliable signal
)
is not being received, or an ILS frequency is selected, the
appropriate pointer will stow at the 3 o'clock position. ,
)
)
SECTION 5
PERFORMANCE
)
)
There is no change to the airplane performance data when this
avionic equipment is installed.
)
)
)
)
):
)
)
)
)
)
)
x\ .. ;
)
"
)
)
)
S36-7/S36-8
1 April 1998
For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
}
)
~
)
)
r
)
)
CeSSri8
ATox lron Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
CESSNA MODEL 208 (675 SHP)
)
SU PPLEMENT 37
)
BENDIX/KING MODE S TRANSPONDER
(TYPE KT-70)
J
)
BENDIX KING TRANSPONDER
(TYPE KT-71 )
J
)
{
J
)
BENDIX/KING ENCODING ALTIMETER
(TYPE KEA-130)
....
UNITED INSTRUMENTS ENCODING ALTIMETER
(TYPE 5035P-P45)
)
SERIAL NO.
)
REGISTRATION NO.
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with above-listed avionic components.
)
APPROVED
)
B~rUf.li~u'J!
Wendell W. Comell
Executive Engineer
)
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
7
)
DATEOFAPPROVAL
J(
COPYRIGHT 0 1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS , USA
)
APRII-I998
o
Member of GAMA
1 APRIL 1998
01352·S37 -00
)
)
)
S37-1
For Training Purposes Only
S37
KT-70 / KT-71 TRANSPONDERS
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 37
BENDIX/KING MODE S TRANSPONDER
(TYPE KT-70)
)
BENDIX KING TRANSPONDER
(TYPE KT-71)
)
BENDIX/KING ENCODING ALTIMETER
(TYPE KEA-130)
UNITED INSTRUMENTS ENCODING ALTIMETER
(TYPE 5035P-P45)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
1 April 1998
LOG OF EFFECTIVE PAGES
PAGE
DATE
S37-1 thru S37-9/S37-10
1 April 1998
REV. NUMBER
o
1 April 1998
S37-2
For Training Purposes Only
)
KT-70/KT-71 TRANSPONDERS
POH SUPPLEMENT
}
537
MODEL 208 (675 SHP)
SUPPLEMENT
)
BENDIX/KING MODE S TRANSPONDER
(TYPE KT-70)
)
)
BENDIX KING TRANSPONDER
(TYPE KT-71)
)
)
BENDIX/KING ENCODING ALTIMETER
(TYPE KEA-130)
)
)
)
UNITED INSTRUMENTS ENCODING ALTIMETER
(TYPE 5035P-P45)
)
)
SECTION 1
)
GENERAL
)
I
)
)
)
)
)
)
)
)
t
)
)
\
The Bendix/King Mode S Transponder (Type KT-70), Shown in
Figure 1, is the airborne component of an Air Traffic Control Radar
Beacon System (ATCRBS). The transponder enables the ATC
ground controller to "see" and identify more readily the airplane on
the radarscope. The Mode S capability enables the ground station
to individually select the airplane by its Aircraft Address assigned to
the airplane by the FAA. The Bendix/King KT-71 Transponder is a
Mode C transponder and is the same as the KT -70 except it does
not have the Mode S capability. The encoding altimeter (also
shown in Figure 1) enables the transponder to automatically report
airplane altitude to ATC.
The Bendix/King Transponder system consists of a panel-mounted
unit, an externally-mounted antenna and a control wheel-mounted
XPDR IDENT switch. The transponder receives interrogating pulse
signals on 1030 MHz and transmits coded pulse-train reply Signals
on 1090 MHz. It is capable of replying to Mode A (aircraft
identification) and also to Mode C (altitude reporting) interrogations
on a selective reply basis on any of 4096 information code
selections.
When a panel-mounted KEA-130 or 5035P-P45
Encoding Altimeter (not part of KT-70 or KT-71 Transponder
system) is included in the avionic configuration, the transponder can
provide altitude reporting in 100-foot increments between -1000 and
)
)
S37-3
1 April 199a
For Training Purposes Only
S37
MODEL 208 (675 SHP)
KT-70/KT-71 TRANSPONDERS
POH SUPPLEMENT
The KT-70 and KT-71 feature an all solid-state transmitter with
microprocessor control and LSI (Large Scale Integrated) encoding
circuitry. Mode and code selection are performed by five front panel
mounted knobs, and all functions including the flight level altitude
are presented on a gas discharge display. All display segments are ·
automatically dimmed by a photocell type sensor.
A VFR programming sequence, described in Section 4, allows the
pilot to preprogram any single code such as "1200" into the KT-70
and KT-71. Pressing the function selector knob instantly returns to
the preprogrammed code without having to turn any other knobs.
All Bendix/King Transponder operating controls, with the exception
of the . operational altitude encoding altimeter setting knob, are
located on the front panel of the unit The altimeter setting knob is
located on the encoding altimeter.
Functions of the operating
controls are described in Figure 1.
SECTION 2
LIMITATIONS
There is no change to the airplane limitations when this avionic
equipment is installed.
SECTION 3
EMERGENCY PROCEDURES
TO TRANSMIT AN EMERGENCY SIGNAL:
1. Function Selector Knob -- ON (or ALT) .
2. Code Selector Knobs -- SELECT 7700 operating code.
TO TRANSMIT A SIGNAL REPRESENTING LOSS OF ALL
COMMUNI-CATIONS (WHEN IN A CONTROLLED
ENVIRONMENT):
)
)
1. Function Selector Knob -- ON (orALT) .
2. Code Selector Knobs -- SELECT 7600 operating code.
1 April 1998
S37-4
For Training Purposes Only
)
)
537
KT-70/KT-71 TRANSPONDERS
POH SUPPLEMENT
8
*
MODEL 208 (675 SHP)
*3 · *4
6
7
Indication when the Function
Selector Knob is in TST Mode
2685X1108
KT-70 Transponder shown
KT-71 Transponder same
9
10
15
11
12
13
2685X1109
IDENT SUnON (lOT) - When depressed, selects special identifier
pulse to be transmitted with transponder reply to effect immediate
identification of the airplane on the ground controller's display. (The
"Rn shaped reply indicator annunciator light will glow for
approximately 18 seconds.) Pressing the Ident Button will terminate
a normal 5-second delay associated with the selection of a Mode A
reply code . Button illumination is controlled by the RADIO light
dimming rheostat.
ALTITUDE DISPLAY - Displays FL and flight level altitude (pressure
altitude) in hundreds of feet when used in conjunction with an
encoding altimeter and ALT mode is selected. Should an invalid
code be detected from the altimeter, dashes will appear in the
display window and altitude reporting will be disabled.
3. MODE ANNUNCIATORS - Displays the operating mode of the
transponder.
Figure 1. Bendix/King Transponder and Encoding Altimeter
Operating Controls (Sheet 1 of 3)
)
S37-5
1 April 1998
v
S37
MODEL 208 (675 SHP)
KT-70/KT-71 TRANSPONDERS
POH SUPPLEMENT
4. REPLY INDICATOR (R) - "R" flashes to indicate transmission of reply
pulses: glows for 18 seconds after pressing the Ident Button.
5. CODE DISPLAY - Displays selected Mode A reply code. Code is also
written into nonvolatile memory so that the code will not change due to {
power interruption.
\
6. FUNCTION SELECTOR KNOB - Push to select VFR code. Controls
application of power and selects transponder operating mode as
follows :
OFF - Turns set off.
SBY - Turns set on for standby power and code selection. ·SBY" is
annun-ciated.
TST - SelHest function, when selected: causes transponder to respond
to internal interrogation verifying all memory data and making
hardware and squitter checks. The transmitter is disabled. All
display segments will illuminate. Should a squitter error occur,
the transmitter is considered inoperative and the message "FO
1" will appear in altitude display (KT-70 only). Should a memory
error occur, the message "FO 2" (internal) or "FO 3" (external)
will appear. Should a hardware failure occur, normal operation is
prohibited and the message "FO 4" will appear. If no errors are ,
detected, the unit will remain in the test mode.
I,.
GND - Turns set on and enables transponder to transmit Mode S reply
pulses (KT-70 only). 10 code 4096 is shown on right side of
"GND" is
display with altitude shown on the left side.
arinunciated. Mode A and C interrogations are inhibited.
ON - Turns set on and enables transponder to transmit Mode A
(aircraft identification) and Mode S (aircraft address) reply pulses
(KT-70 only). ON is annunciated.
ALT - Turns set on and enables transponder to transmit Mode A
(aircraft identification) . Mode C (altitude reporting) , Mode S
(aircraft address) reply pulses selected automatically by the
interrogating signal (KT-70 only). ALTON is annunciated.
7, CODE SELECTOR KNOBS - Each of the four selector knobs selects a
separate digit of the assigned Mode A reply code,
8. PHOTOCELL - Automatically dims display according to the cabin
ambient light.
Figure 1. Bendix/King Transponder and Encoding Altimeter
Operating Controls (Sheet 2 of 3)
537-6
1 April 1998
For Training Purposes Only
)
KT-70/KT-71 TRANSPONDERS
POH SUPPLEMENT
)
l
)
)
)
)
)
)
)
)
)
)(
537
MODEL 208 (675 SHP)
9 . 10,000-FOOT POINTER AND LOW ALTITUDE WARNING DISC Pointer indicates altitude readout in1 0,000 foot increments between 1000 feet and +35,000 feet. Low altitude warning disc rotates with
pointer as altitude is gained or reduced. (Refer to Item 13.)
10. 1000-FOOT POINTER - Indicates altitude in 1000 foot increments
between 0 feet and 10,000 feet.
11. ALTIMETER SETTING SCALE (IN. HG .) - Indicates selected altimeter
setting in the range of 28 .1 to 31.0 inches of mercury.
12. 100-FOOT POINTER - Indicates altitude in 1~O-foot
between 0 feet and 1000 feet with 20-foot subdivisions.
increments
13. LOW ALTITUDE WARNING FLAG - Complete flag is visible when
altitude indicates O-feet altitude. As the airplane gains altitude, the low
altitude · warning flag will start to be covered over by the disc attached
to the 10,000-foot pointer (mentioned in Item 9). When the airplane
reaches an altitude of approximately 17,000 feet, the low altitude
warning flag will be completely covered over (out of view) by the disc.
As the airplane starts descending, the flag will start coming into view at
approximately 17,000 feet and progress proportionately into view as the
airplane descends to sea level.
14. ALTIMETER SETTING KNOB - Dials in desired altimeter setting in the
range of 28.1 to 31.0 inches of mercury or 946 to 1050 millibars.
)
)
)
15. ALTIMETER SETTING SCALE (MILLIBARS) - Indicates selected
altimeter setting in the range of 946 to 1050 millibars.
Figure 1. Bendix/King Transponder and Encoding Altimeter
Operating Controls (Sheet 3 of 3)
)
SECTION 4
NORMAL PROCEDURES
)
)
)
)
)
)(
) "-'- -
)
)
BEFORE TAXI:
1. Function Selector Knob -- GND (KT-70), SBY (KT-71).
BEFORE TAKEOFF :
1. Function Selector Knob -- GND (KT-70), SBY (KT-71).
S37-7
1 April 1998
For Trainin Pur oses Onl
537
KT~70/KT-71
TRANSPONDERS
POH SUPPLEMENT
MODEL 208 (675 SHP)
TO TRANSMIT MODE A (AIRCRAFT IDENTIFICATION) AND
MODE S (AIRCRAFT ADDRESS) CODES IN FLIGHT (KT-71 will
not transmit Mode S):
1. Code Selector Knobs -- SELECT assigned code.
2. Function Selector Knob -- ON.
NOTE
)
• During normal operation with function selector
knob in ON position, reply indicator "Rn flashes,
indicating transponder replies to interrogations.
• . Mode A reply codes are transmitted in ALT also;
however, Mode C codes only are suppressed when
the Function Selector Knob is positioned to ON.
3. Ident Button (lOT) -- DEPRESS momentarily when instructed
by ground controller to "squawk IDENT" ("A" reply indicator
will glow for approximately 18 seconds, indicating IDENT
operation).
.
TO TRANSMIT MODE C (ALTITUDE REPOATING) AND MODE S
(AIRCRAFT ADDRESS) CODES IN FLIGHT (KT-71 will not transmit
Mode S):
1. Encoder Altimeter Setting Knob -- SET IN local altimeter
setting.
2. Transponder Code Selector Knobs -- SELECT assigned code.
3. Function Selector Knob -- ALT.
NOTE
• When directed by ground controller to "stop altitude
squawk", turn Function Selector Knob to ON for Mode
A and Mode S operation only (KT-71 will not transmit
Mode S).
(Continued next page)
1 April 1998
S37-8
For Training Purposes Only
KT-70/KT-71 TRANSPONDERS
POH SUPPLEMENT
)
)
~
)
)
)
•
537
MODEL 208 (675 SHP)
Altitude transmitted by the transponder for altitude squawk
and displayed on the KT-70 and KT-71 panel is pressure
altitude (independent of altimeter setting) and conversion to
indicated altitude is done in the ATC computers. Altitude
displayed on the airplane encoding altimeter will agree 'with
altitude indicated on the ATC radar only when the local
altimeter setting in use by the ground controller is set in the
pilot's encoding altimeter. Altitude displayed on the airplane
encoding altimeter will agree with the altitude displayed on
the KT-70 and KT-71 panel only when the encoding
altimeter setting is 29.92 inches of mercury.
AFTER LANDING
)
)
)
)
)
)
)
)
)
1. Function Selector Knob -- GND.
TO SELF-TEST TRANSPONDER OPERATION:
1. Function Selector Knob _. TST Check all displays.
presence of Reply Indicator.
2. Function Selector Knob -- SELECT desired function.
Verify
TO PROGRAM VFR CODE:
1. Function Selector Knob -- SBY.
2. Code Selector Knobs -- SELECT desired VFR code.
3. lOT Button -- PRESS AND HOLD.
a. Function Selector Knob -. PRESS to place new VFR code
in nonvolatile memory for subsequent call up.
)
)
SECTION 5
)
PERFORMANCE
)
)
)
)(
There is no change to the airplane performance when this
avionic equipment ·is installed.
However, the installation of an
externally-mounted antenna, or several related external antennas,
will result in a minor reduction in cruise performance.
) \ ..-~- .
)
)
S37-9/837-10
1 April 1998
For Trainin Pur oses Onl
(
)
)
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
~
)
)
Cessna
A Textron Company
j
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 38
)
)
BENDIX/KING DIGITAL WEATHER RADAR SYSTEM
(Type RDR 2000)
)
)
SERIAL NO.
)
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King Digital Weather
Radar System (Type RDR 2000).
)
)
)
APPROVED
)
Wendell W. Cornell
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE·3
)
)
DATE OF APPROVAL
)
)(
..... ..•
) -"'"'-"
)
B~&ffi~MH'.e
7
APRIL.. 1998
COPYRIGHT "1998
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of GAMA
1 APRIL 1998
D1352-838-00
)
)
)
838-1
For Trainin Pur oses Onl
538
MODEL 208 (675 SHP)
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
SUPPLEMENT 38
BENDIX/KING DIGITAL WEATHER RADAR SVSTEN
(Type RDR 2000)
(
)
Use the Log of Effective Pages to determine the current status of
)
this supplement.,
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
Revis/on Level
Date of Issue
o (Original)
1 April 1998
)
)
LOG OF EFFECTIVE PAGES
)
PAGE
838-1 thru 838-13/838-14
DATE
REV, NUMBER
)
1 April 1998
o
)
)
)
)
)
)
)
)
)
)
1 April 1998
838-2
For Training Purposes Only
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
S38
MODEL 208 (675 SHP)
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SUPPLEMENT
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BENDIX/KING DIGITAL WEATHER RADAR SYSTEM
(Type RDR 2000)
SECTION 1
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GENERAL
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The Bendix/King Digital Weather Radar System (Type RDR 2000) consists of
a wing pod mounted receiver-transmitter and stabilized 12-inch X-band radar
antenna, and a panel-mounted radar indicator. All operating controls are
mounted on the front panel of the radar indicator and operating controls and
functions are described in Figure 1.
The Bendix/King Digital Weather Radar System (Type RDR 2000) is designed
to detect Significant enroute weather formations up to a distance of 240
nautical miles (when set to maximum range) to preclude undesired
penetration of heavy weather and its usually associated turbulence. The
antenna is fully stabilized to compensate for up to ±30° of airplane pitch and
roll.
The indicator provides a four-color weather display, showing four
separate levels of rainfall intensity in green, yellow, red and magenta. In
addition the indicator displays evenly-spaced blue segmented concentric
range arcs, displays blue alphanumerics, displays degrees away from the
airplane heading in yellow numbers, and also provides an amber antenna tilt
angle readout. In addition to its primary purpose of weather mapping, a
ground mapping mode permits displaying prominent topographical features
such as lakes, bays, islands, shore lines and urban areas.
A WARNING
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This system generates microwave radiation In the Wx, WxA
and MAP operating modes. Improper use, or exposure, may
cause serious bodily Injury. DO NOT OPERATE UNTIL YOU
HAVE READ AND CAREFULLY FOLLOWED ALL SAFETY
PRECAUTIONS AND INSTRUCTIONS CALLED OUT IN
SECTION
4
(NORMAL
PROCEDURES)
OF
THIS
SUPPLEMENT.
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S38-3
1 April 1998
o
rainin Pur oses Onlv
S38
BENDIX/KING DIGITAL WEATHER RADAR
MODEL 208 (675 8HP)
POH SUPPLEMENT
For expanded information and operating instructions, refer to the RDR 2000
Pilot's Guide supplied with your airplane.
A WARNING
Users of this equipment are strongly urged to familiarize
themselves with FAA Advisory Circular AC No. 00-248(1-2083), subject: "Thunderstorms".
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VIEW OF WEATHER MODE
2618T1104
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Figure 1. Bendix/King RDR 2000 Operating Controls and Indicators
(Sheet 1 of 4)
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1 April 1998
838-4
For Training Purposes Only
BENDIX/KING OIGITALWEATHER RADAR
POH SUPPLEMENT
538
MODEL 208 (675 SHP)
18
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11
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10
VIEW OF VERTICAL PROFILE MODE
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2618T1105
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1. BRT CONTROL KNOB - Use to adjust the display
accommodate existing cockpit ambient light conditions.
brightness
to
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2. TRACK CENTERLINE READOUT - Displays the number of degrees the
track line is slewed left or right of the airplane nose.
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3. ANTENNA TILT CONTROL READOUT - Displays the tilt angle in degrees in
the upper right corner that has been selected by the TILT control.
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4. FUNCTION SELECTOR SWITCH - Controls application of power and
selects mode of operation lor transmitting, testing and warmup.
positions are as follows:
Switch
OFF - Primary power is removed from the system.
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SBY - (Standby)
After 60 seconds in this mode, places system in
operational ready status.
Use during warmup and in-flight periods
when the system is not in use. The word "STBY" is displayed in the
lower left corner.
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Figure 1. Bendix/King RDR 2000 Operating Controls and Indicators
(Sheet 2 of 4)
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S38-5
1 April 1998
v
538
MODEL 208 (675 SHP)
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
TST - (Test) Selects test 'function to determine operability of the system.
No transmission exists in the TST
A test pattern is displayed.
condition. The word "TEST" is displayed in the lower left corner.
ON - Selects the condition for normal operation.
Radar transmission
exists in the ON position. The Wx mode and 80 mile range are
automatically selected when turned on. Wx will be displayed in the
lower left corner and 80 will be displayed just above the right end of
the top concentric range mark.
LOG - Not used (used only when Bendix/King radar graphics units are
installed, and with compatible long range navigation system).
5. RANGE INCREASE PUSHBUTTON (I\RNG) - Clears the display and
advances the indicator to the next higher range each time the pushbutton is
pressed (eg : 20 to 40, 40 to 80, etc.), until 240 mile range is reached. The
range selected is displayed in the upper right corner on the last range mark,
and the distance to each of the other range mark arcs is displayed along
the right edge of the arcs.
6. RANGE DECREASE PUSHBUTTON (VRNG) - Clears the display and
places the indicator in the next lower range each time the pushbutton is
pressed (eg: 40 to 20, etc.), until minimum range is reached.
7. TRACK LEFT PUSHBUnON « TRK) - Provides a yellow track centerline
for the horizontal sector scan and vertical profile. With the track button
pushed and held, a yellow line will Cippear on the screen and start to slew
left in 1 degree steps at about 15 degrees per second from the nose of the
airplane. In the upper left corner of the display, a yellow number will display
the number of degrees the track line is positioned from the nose of the
airplane. To stop the track line at a desired position, release the track
button. II the track button is not pressed for 15 seconds, the track line .will
disappear from the display. When the track button is pressed while in the
VP mode, · the track line moves in 2 degree steps to select the vertical
"slice" to be displayed.
The display will complete the upward scan if
currently in progress, and then transition to the bottom rail at the track line
azimuth. Once the horizontal track line is positioned, the display will provide
a vertical scan of ±30 degrees of that location.
8. TRACK RIGHT BUTTON (TRK » - Same as track left pushbutton except
with the track button pushed and held the track line will slew to the right.
9. ANTENNA TILT CONTROL - Turn the knob to adjust antenna tilt. Adjusts
the antenna to move the radar beam up to + 15 degrees above the
horizontal, or to a maximum of -15 degrees below the horizontal position.
The horizontal position is indicated as zero degrees on the control. The tilt
angle selected is displayed in the upper right corner of the indicator. Pulling
this knob out disables stabilization and "NO STAB" will appear in the upper
left .comer of the screen . Disabling the stabilization is generally only
necessary in case of a gyro malfunction.
Figure 1. Bendix/King ADA 2000 Operating Controls and Indicators
(Sheet 3 of 4)
1 April 1998
838-6
For Training Purposes Only
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
S38
MODEL 208 (675 SHP)
10. DISPLAY . RANGE/RANGE MARKS - Displays selected range and range
marks in nautical miles. The following six ranges are available for display
using the . range (RNG) pushbuttons as desired: 10/2.5, 20/5; 40/10, 80/20,
160/40 and 240/60.
11 . MODE DISPLAY - Displays selected mode of operation for ground mapping
(MAP), weather (Wx) or weather alert WxA).
12. LOCKING PAWL (Each Side) - Locks radar indicator in mounting cover.
13. GAIN CONTROL - Permits adjusting the radar receiver gain in the terrain
MAP mode only.
NOTE
In the test (TST) function as well as in all weather modes the
receiver gain is preset, thus no adjustment is required.
14. NAVIGATION PUSHBUnON (NAV) . Not used (this button is effective only
when an optional radar graphics unit and Flight Management System is
installed). If activated without these units installed. "NO NAV" will appear at
lower left corner of the screen.
15. GROUND MAPPING PUSHBUTTON (MAP) . Selects ground mapping
mode. When pressed, "MAP" is displayed in the lower left corner of the
screen. The GAIN control setting becomes an operator function. Manual
GAIN .control is important in obtaining a definitive presentation during varying
topographic conditions. Prominent terrain features are presented in green
for weak returns, yellow for moderate returns and magenta for intense
returns.
16. VERTICAL PROFILE PUSHBUTTON (VP) . Selects and deselects the
vertical profile mode when pressed. "PROFILE" is displayed in the upper
left corner of the screen. When VP is selected on the indicator the ART will
provide a vertical scan of ±30 degrees at the location of the horizontal track
line. Selecting the VP mode of operation will not change the selected mode
of operation: TST, Wx, WxA or GND MAP. Once in VP, these modes may
be changed as desired.
17. WEATHER AND WEATHER·ALERT PUSHBUTTON (Wx/WxA) - Alternately
selects between Wx (weather) and . WxA (weather . alert) modes when
pressed. "Wx" or "WxA" will appear in the lower left corner of the display.
Wx or WxA colors are black for no returns, green for weak returns, yellow
for moderate returns, red for heavy returns and magenta for intense returns.
When the WxA mode is selected, magenta areas of storms flash between
magenta and black at a 1 HZ rate.
18. VERTICAL PROFILE MODE DISPLAY· Displays "PROFILE" in the upper
left corner of the screen when operating in the vertical profile mode.
19. RELATIVE ALTITUDE DISPLAY - Displays, while in the vertical profile mode,
plus thousands of feet and minus thousands of feet from the relative altitude
reference line "0". The altitude values vary with selected range x 100.
Figure 1. Bendix/King RDR 2000 Operating Controls and Indicators
(Sheet 4 of 4)
538-7
1 April 1998
For Training Purposes Only
S38
MODEL 208 (675 SHP)
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
SECTION 2
LIMITATIONS
There is no change to the airplane limitations when this avionics equipment is
installed. However, the following radar limitations must be followed during
airplane operation.
1.
2.
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Do not operate radar during refueling.
Do not operate radar within 15 feet of ground personnel or
containers holding flammable or explosive material.
Do not operate radar above 25,000 feet flight altitude.
SECTION 3
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures when this avionics
equipment is installed.
SECTION 4
NORMAL PROCEDURES
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PRIOR TO FLIGHT:
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A WARNING
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The radar system generates microwave radiation and
Improper use, or exposure, may cause serious bodily Injury.
DO NOT OPERATE THIS EQUIPMENT UNTIL YOU HAVE
READ AND CAREFULLY FOLLOWED THE FOLLOWING
SAFETY PRECAUTIONS AND INSTRUCTIONS:
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SAFETY PRECAUTIONS AND INSTRUCTIONS TO BE FOLLOWED PRIOR
TO RADAR OPERATION ON THE GROUND:
1. Do not turn on, or operate radar within 15 feet of ground personnel or
containers holding flammable or explosive material.
2. Do not turn o~, or operate radar during refueling operations.
S38·8
1 April 1998
For Training Purposes Only
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BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
S3:
MODEL 208 (675 SHF
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PREFLIGHT CHECKS PRIOR TO ENERGIZING RADAR:
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A
1"
WARNING
IN .ORDER TO PREVENT POSSIBLE SERIOUS BODILY
INJURY TO GROUND PERSONNEL OR IGNITION OF
FLAMMABLE OR EXPLOSIVE MATERIALS, THE FOLLOWING
TESTS MUST BE ACCOMPLISHED WITH THE FUNCTION
SELECTOR SWITCH ALWAYS IN THE TEST (TST) MODE OF
OPERATION.
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1. Function Selector Switch -- SBY (standby) position and after E
seconds select TST (test) position.
2 . Antenna TILT Control -- Set to +5°.
3 . BRT Control -- ADJUST to mid-range .
. 4. Indicator Test Display -- CHECK TEST PATTERN for the followir
indications:
a. After 7 to 8 seconds four equally spaced blue range marks shou'
be visible, the word "TEST" and the number "SO" should appe,
and be visible in blue displays in opposite corners of the display.
b. No video noise distortion should appear on the display.
c. There are four colored bands appearing on the indicator.
d. Starting with the closest band to the origin, the bands will be greel
yellow, red, and magenta.
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NOTE
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The width of the test pattern bands is not critical, nor is the
position of the bands relative to the rang~ marks.
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e. The update action may be observed as a small "ripple" movir
along the outer magenta band, indicating that the antenna
scanning.
5. Function Selector Switch -- SBY position .
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S38
1 April 1998
For Trainin Pur oses Only
S38
MODEL 208 (675 SHP)
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
PREFLIGHT CHECKS WITH RADAR ENERGIZED:
A WARNING
IN ORDER TO PREVENT POSSIBLE BODilY INJURY TO
GROUND PERSONNEL OR IGNITION OF FLAMMABLE OR
EXPLOSIVE MATERIALS, THE AIRPLANE MUST BE TAXIED
WITH THE FUNCTION SWITCH IN THE OFF, SBY, OR TST
POSITIONS ONLY TO A "CLEAR-AHEAD" AREA WHERE
METAL BUILDINGS, AIRPLANES, GROUND PERSONNEL,
ETC., ARE NOT IN THE LlNE-OF-SIGHT OF THE RADAR
UNIT. OBSERVE THE SAFETY PRE-CAUTIONS AND
INSTRUCTIONS AT THE START OF SECTION 4 PRIOR TO
PERFORMING THE FOllOWING CHECKS WITH THE RADAR
UNIT ENERGIZED.
)
1. Ensure safety precautions have been observed.
2. Function Selector Switch -- ON position.
The indicator will
automatically be in the weather (Wx) mode.
3. RNG (Range) Selector Push buttons -- 40-10 range.
4. Wx/WxA Mode Selector Pushbutton -- SELECT WxA mode and observe
that magenta areas (if any) alternate from magenta to black
approximately once per second.
5. BRT Control -- ADJUST as required.
6. Antenna TILT Control -- TILT UP (+ degrees) and DOWN (- degrees)
in small increments. Close-in ground targets should appear on the
display at low tilt angles and any local moisture laden weather should
appear at higher angles.
7. TRK (Track) Selector Pushbuttons -- PRESS and hold Track Left «
TRK), a track line will appear and slew left in 1 degree steps. Repeat
for Track Right (> TRK). (If neither button has been pressed for 15
seconds, the track line will disappear).
8. VP (Vertical Profile) Selector Pushbutton -- SELECT VP mode and the
vertical profile "slice" will be taken at the position of the track line. If
the track buttons are pressed. the vertical scan will change position
with the track line and the track line will move in 2 degree steps.
9. Function Selector Switch -- SBY position for taxi maneuvers.
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S38-10
1 April 1998
For Training Purposes Only
BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
538
MODEL 208 (675 SHP)
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OPERATIONAL NOTES:
FALSE RETURN DISPLAY:
1. Ground radar stations or other airborne weather radars may
occasionally cause interference with the presentation of the return.
The effect of this interference is to create one or more radial bands of
, false signal or noise extending from the bottom center outward to the
outer range scale. These effects are usually of short duration and are
dependent on the airplane's position and range from the ground
station, the signal strength, and other factors.
EXTENDING LIFE OF THE MAGNETRON TRANSMITIING TUBE:
1. The RDR 2000 Color Weather Radar System is designed so that full
operation is possible approximately 60 seconds after turn on.
Therefore, tne pilot may choose to leave the function switch in OFF
rather than SBY if no significant weather is in the immediate area of the
airplane. The life of the magnetron transmitting tube will be extended
by leaving the system "OFF" when possible. This in turn will reduce
the cost of maintenance ;
EFFECT OF SOME SUNGLASSES ON THE RADAR DISPLAY SCREEN:
1 . The RDR 2000 Color Indicator utilizes a special filter to assure optimum
video contrast to the pi lot in the presence of high cockpit ambient light.
Some sunglasses may interfere with the effectiveness of this filter. To
check for this, cock your head to one side while viewing the display
and note any dramatic change in brilliance. If the brilliance decreases
sharply, some compromise such as removing or changing sunglasses
should be effected.
OPERATING TEMPERATURE LIMITS:
1 . Operating temperature limits for the IN-182A Indicator is -20°C (-4°F)
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Jt~" ,
to +55°C (+131°F).
TURN·OFF PROCEDURES (On the ground):
1 . The ART 2000 AntennaJReceiverlTransmitter will tilt the antenna down,
for increased radar receiver protection, when the indicator is switched
to SBY and OFF position. Always turn the indicator function switch to
SBY or OFF before disengaging the avionics master switch in the
airplane.
The system will power-down in about 5 seconds alter
switched to the OFF position, to allow time for the antenna to move to
the down position.
)
538-11
1 April 1998
For Trainin Pur oses Onl
S38
MODEL 208 (675 SHP)
, BENDIX/KING DIGITAL WEATHER RADAR
.
POH SUPPLEMENT
)
GROUND MAPPING DISPLAYS:
1. The display resulting from ground mapping resembles an ordinary
Cities,open ground and bodies of water are
pilotage chart.
distinguished by the intensity of the signals that they reflect back to the i
signal sourc;:e.Cities usually provide the most intense reflections and '
appear magenta on the display. Open ground and water provide
progressively less intense reflections and appear as yellow and green.
Calm bodies of water provide very weak signal returns, and are usually
not displayed, while very rough water provides a stronger return Signal
and will usually appear as green color.
RANGE REDUCTION WITH RADAR POD ABRASION BOOT:
1. A circular polyurethane film abrasion boot may be installed on the
nosecap, of the radar pOd to protect the pod frontal surface from the
abrasive effects of objects contacting the pod during ground and lowlevel flight operations. However, installation of the boot will decrease
the effective ranges of the radar by approximately 6%.
NORMAL OPERATION:
WEATHER DETECTION
1. Function Selector Switch -- ON position (allow 60 seconds warm-up if
previously in the "OFF" position).
A WARNING
The Indicator will automatically be in the Weather (Wx)
mode when Function Selector Switch is placed In the ON
position. In the ON position, the radar system will be
generating microwave radiation.
2. Wx/WxA Weather and Weather-Alert Pushbutton -- PRESS to select
desired mode.
Wx - Weather.
WxA - Weather Alert.
3. BRT Control -- ADJUST as required for ambient light conditions.
4. Antenna TILT Control -- +4° to +6° (approximate minimum angle
relative to horizon without ground return) .
5. RNG (Range) Selector Pushbuttons -- SELECT desired range.
6. Airplane -- MAINTAIN SPEED and HEADING to assure an accurate
picture of relative motion of storm in next step.
7. Wx/WxA Weather and Weather-Alert Pushbutton -- PRESS to select
Weather-Alert (WxA) , which causes the strongest storm cell displayed
in magenta color to flash for easier identification.
1 April 1998
838-12
For Training Purposes Only
)
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BENDIX/KING DIGITAL WEATHER RADAR
POH SUPPLEMENT
538
MODEL 208 (675 8HP)
)
VERTICAL PROFILING :
NOTE
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The vertical profile feature of this radar should only be used after
the operator is very fami liar with this equipment.
1 . Function Selector Switch -- ON position (allow 60 seconds warmup if
previously in the "OFF" position).
2 . RNG (Range) Selector Pushbuttons -- SELECT desired range .
3. TRK · (Track) Selector Pushbuttons -- SELECT desired track line
position.
4 . VP (Vertical Profile) Mode Selector Pushbutton -- PRESS.
5 . BRT Control -- ADJUST as required.
6. Function Selector Switch -- OFF position before landing.
GROUND MAPPING
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NOTE
Ground mapping is a secondary feature of this radar which
should only be used after the operator is very familiar with this
equipment.
1. Function Selector Switch _. ON position (allow 60 seconds warmup if
previously in the "OFF" position).
2. RNG (Range) Selector Pushbuttons -- SELECT desired range .
3 . MAP Mode Selector Pushbutton .- PRESS . Set GAIN as desired for
clearest ground mapping interpretation .
4. BRT Control -- ADJUST as required.
5 . Antenna TILT Control .- ADJUST for clearest display.
6 . Function Selector Switch .. OFF position before landing.
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SECTION 5
PERFORMANCE
)
There is no change to the airplane performance when this radar equipment is
installed. However, installation of the wing mounted radar pod will result in a
minor reduction of 1 KTAS cruise speed performance .
S38-13/838-14
1 April 1998
For Trainin Pur oses Onl
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For Training Purposes Only
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CeSSri8
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A ToJttron Company
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Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
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CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 39
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AIRPLANES CERTIFIED TO RUSSIAN
CONFIGURATION
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{
SERIAL NO.
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REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual. if the airplane is certified to Russian configuration.
)
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APPROVED BY
)
Me. ~
~Wendell W, Cornell
)
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
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DATE OF APPROVAL
11 :I'/JAItf
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x
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COPYRIGHT 0 1999
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS . USA
' '1'1
Member of GAMA
17 JUNE 1999
01352·S39-01
REVISION 1 - 12 FEBRUARY 2002
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S39-1
For Traininl! Purposes Only
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT
AIRPLANES CERTIFIED TO RUSSIAN
CONFIGURATION
Use the Log of .Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
17 June 1999
12 ·February 2002
Revision 1
)
LOG OF EFFECTIVE PAGES
PAGE
DATE
* 839-1 thru 839-2
*
*
*
*
839-3
839-4 thru S39-8
S39-9
S39-10
S39-11
839-12
S39-13/839-14
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REV. NUMBER
12 February 2002
17 June 1999
1
0
, 12 February 2002
17 June 1999
12 February 2002
. 17 June 1999
12 February 2002
12 February 2002
1
0
1
0
1
1
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DATE OF APPROVAL
14 t=!.&1W~"I' tooL
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S39-2
12 February 2002
For Training Purposes Only
539
RUSSIAN CONFIGURATION
POH SUPPLEMENT
)
MODEL 208 (675 SHP)
)
SUPPLEMENT
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j/
AIRPLANES CERTIFIED TO RUSSIAN
CONFIGURATION
)
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SECTION 1
GENERAL
)
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This supplement must be placed in Section 9 of the basic Pilot's
Operating Handbook and FAA Approved Airplane Flight Manual, if
the airplane is certified to Russian configuration. The information
contained herein supplements the information of the basic Pilot's
Operating Handbook and FAA Approved Airplane Flight· Manual.
For limitations, procedures, and performance information not
contained in this supplement, consult the basic Pilot's Operating
Handbook and FAA Approved Airplane Flight Manual.
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SECTION 2
LIMITATIONS
)
The following Limitations supersede and/or are in addition to the
Limitations set forth in the basic Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual:
{)
)
KINDS OF OPERATION LIMITS
)
This airplane is equipped for day VFR and/or IFR operations and for
f1ight-into-known icing conditions. The operating limitations placard
reflects the limits applicable at the time of Airworthiness Certificate
issuance.
)
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The aircraft can operate in CIS airspace on routes covered by ATC
ground facilities using RBS mode.
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GPS (if installed) can be used only for enroute and terminal
navigation, but not as primary means.
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A minimum flight crew performing
instrument flight rules (IFR) is2 pilots.
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commercial
flights
using
(Continued Next Page)
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S39-3
17 June 1999
sOl
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
KINDS OF OPERATION LIMITS (Continued)
I
The aircraft is approved for Category I instrument approach
operations only.
Airplanes performing commercial flights must be equipped with a
Flight Data Recorder (FOR) in compliance with AP 23.1459.
If the crew consists of two pilots, and performs regular commercial
flights carrying six or more passengers, a Cockpit Voice Recorder
must be installed and operational in the aircraft.
The following equipment lists identify the systems and equipment
upon which type certification for each kind of operation was
predicated. These systems and equipment items must be installed
and operable for the particular kind of operation indicated.
Reference should also be made to the Equipment List furnished
with the airplane for additional equipment information. The pilot is
responsible for determining the airworthiness of the airplane for
each flight, and for assuring compliance with current operating AP
requirements.
REQUIRED EQUIPMENT
DAYVFR:
Airspeed Indicator (1)
Altimeter (1)·
Allimeler - Metric (1)
Ammeter displaying current draw of
Pitot Heaters (2)
Auxiliary Boost Pump System
BATIERY HOT and BATIERY OVERHEAT
Annunciators (NiCad Batteries ONLY)
Elevator Trim System (Manual)
Engine Ignition System
Flap Motor (1)
Flap Position Indicator
Flasher on VACUUM LOW Annunciator
FUEL PRESS LOW Annunciator
Fuel Quantity Indicators (2)
Fuel Selectors Off Warning System
Generator
Horizontal Stabilizer Deice Boots
Ice Detector Light (For Night Flight)
Inertial Separator
ITT Indicator
KHF-950 HF Radio
Magnetic Compass
Ng % RPM Indicator
OIL PRESS LOW Annunciator
Oil Pressure Gage
Oil Temperature Gage
Outside Air Temperature Gage
\ Overspeed (Airspeed) Warning System
Overspeed Governor
Pilot's Operating HandbookiAFM
Pilot-Static System (1)
Pitot-Static Tube Heat System
Propeiler Anti-Ice Boots
Propeller RPM Indicator
Seat Belts (Each Occupant)
Shoulder Harness (Front Seats)
Slip -Skid Indicator (1)
Stall Warning System
Stall Warning System Heater
Standby Electrical Systems
Torque Indicator
Trim Position Indicators (3)
Vertical Stabilizer Deice Boot
VolVAmmeter
Windshield Anti-Ice Panel
Wing And Wing Strut Deice Boots
(Continued Next Page)
12·February 2002
S39-4
For Training Purposes Only
)
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
)
REQUIRED EQUIPMENT (Continued)
)
°NME
)
)
When a servoed altimeter is installed,
pneumatic altimeter is also required.
)
IFR:
)
All Equipment Required for Day VFR
Attitude Indicator (Gyro Stabilized) (1)
Clock
Communications Radio (VHF) (1)
Directional Indicator (Gyro Stabilized) (1)
Instrument Lights
Two-axis Autopilot with Yaw Damper
Navigation Lights (3)
Taxi-Landing Lights
)
)
)
a functioning
Navigation Radios (As Required)
Right Hand Flight Panel
Sensitive Altimeter (2)'
Strobe Lights
Suction Gage (If gyros are vacuum
powered)
Turn and Bank Ind icator or
Turn Coordinator (1)
I
)
MINIMUM OIL TEMPERATURE
)
The minimum oil temperature allowed during engine starts is -35°C.
)
FUEL LIMITATIONS
l'
2 Standard Tanks
)
)
)
Total Fuel
Both Tanks:
Each Tank:
335.6 U.S. gallons.
167.8 U.S. gallons.
Usable Fuel
Both Tanks On: 332 U.S. gallons total.
Single Tank On: 165 U.S. gallons per tank.
)
)
Unusable Fuel
Both Tanks On: 3.6 U.S. gallons total.
Single Tank On: 2.8 U.S. gallons per tank.
)
)
)
NOTE
)
)
)(
\.
To achieve full capacity, fill fuel tank to the top of the filler
neck. Filling fuel tanks to the bottom of the fuel filler collar
(level with the flapper valve) allows space for thermal
expansion and results in a decrease in fuel capacity of four
gallons per side (eight gallons total) .
)
(Continued Next Page)
)
12 February 2002
839-5
r Trainin Pur oses Onl
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
FUEL LIMITATIONS (Continued)
With low fuel reserves (FUEL LOW annunciator(s) ON), continuous
uncoordinated flight with the turn and bank "ball" more .than one- ,
quarter ball out of center position is prohibited. Unusable fuel '.
quantity increases when more severe sideslip is maintained.
Due to possible fuel starvation, maximum full rudder sideslip
duration time is three minutes.
Maximum fuel unbalance in flight is 200 Ibs.
Fuel Grade Specification and Fuel Additives :
Th~
I
following fuel grades and fuel additives are approved.
FUEL
FUEL
MINIMUM FUEL
GAADE
SPECIFICATION
TEMPERATURE FDA
TAKEOFF
)
Jet A
ASTM-D1655
-35°C
)
Jet A: 1
ASTM~D1655
-40°C
)
Jet B
ASTM-D1655
-45°C
JP-l
MIL-L-5616
-35°C
JP-4
MIL-T-5624
-54°C
JP-5
MIL-T-5624
-40 a C
JP-B
MIL-T -83133A
-40°C
AT
GOST-10227 -86
-35°C
TS-1
GOST-10227-86
-45°C
(1) Fuel used must contain anti-icing fuel additive in compliance
with MIL-I-27686 (EGME), MIL-I-85470, (DIEGME).
A
CAUTION
JP-4 and JP-5 fuels per MIL-T-5624 and JP-8 fuel per
MIL-T·83133A contain the correct premixed quantity of
an approved type of antl·lclng fuel additive and no
additional antl·icing compounds should be added.
(Continued Next Page)
12 February 2002
S39-6
For Training Purposes Only
539
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
FUEL LIMITATIONS (Continued)
)
)
NOTE
-
j
•
The fuel used requires the addition of anti-ice fuel
additives. Maximum concentration of anti-ice additives
. Fluid I (GOST 8313), and Fluid I-M (TU6-10-14S8), are
.30% by volume. Minimum concentration is .10% by
volume additive for effective protection . Fluid I-M is a
mixture of Fluid I and Methanol (GOST 2222) in a 1-to-1
proportion.
•
When using RT and TS-1 . fuels, and anti-icing additives
Fluid I and Fluid I-M, maintenance requirements of Pratt &
Whitney Canada (P&WC) Service Bulletin SB1244, Rev
17, or later version , must be complied with.
•
The fuel used requires anti-static additive Sigbol (TU38101741), maximum concentration .0005% by mass.
)
)
)
)
)
)
)
)
(2)
)
)(
NOTE
Starts may be attempted with fuel at lower
temperatures providing other specified engine
limitations are not exceeded.
)
)
)
MAXIMUM OPERATING ALTITUDE LIMIT
)
Certificated Maximum Operating Altitude: 4,200 Meters (13,780
Feet).
)
Cold Day:
)
-40°C for Ground Operations.
-54°C for Flight Operations.
)
)
Hot Day:
Ground Operations :
)
)
)
)
)
I
OUTSIDE AIR TJ:MPERATURE LIMITS
)
)
I
The minimum starting temperature is that given, or the
minimum allowable oil temperature (-35°C), whichever is
warmer.
)\
)
I
\c
"
+53°C from sea level to 1,524 me.ters (5,000 feet); ISAI
+3JDC above 1,524 meters (5,000 feet).
Flight Operations:
ISA +35°C from sea level to 4,200 meters (13,780 feet).
12 February 2002
I
S39-7
For Trainin Pur oses Onl
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 8HP)
TAKEOFF AND LANDING OPERATIONAL LIMITS
ALLOWABLE RUNWAY SURFACE CONDITIONS
Runway paved with hard surface.
Contaminated, paved hard surface runway with precipitation.
Average depth and type as follows :
- Water, not to exceed 0.4 inch depth (10.0 mm)
- Slush, not to exceed 0.4 inch depth (10.0 mm)
-Loose snow, not to exceed 1.2 inch depth ( 30.0 mm)
Unpaved runway.
- Surface hardness not less than 5 kgf/cm 2 .
- Packed snow surface hardness not less than 5 kgf/cm 2 .
A WARNING
Landing on soft, wet, unpaved runways Is prohibited.
MAXIMUM CROSSWIND ON CONTAMINATED RUNWAYS
Contaminated, paved hard surface runway with no more than:
0.4 inches (10.0 mm) of water, or
0.4 inches (10.0 mm) of slush, or
1.2 inches (30 mm)of loose snow
.........
5 knots (3m/s)
Paved hard surface runway with no more than 0.125 inches (3
mm) of precipitation and braking coefficient of friction (lJ)of:
IJ = 0.3 (poor braking)
... ... . ...... ..
IJ = 0.4 (average braking)
. . . . ... . . . . .
IJ = 0.5 (good braking, dry and equivalent
to dry runway)
. ..... . . .. .. .....
10 knots (5 m/s)
15 knots (7 m/s)
20 knots(10 m/s)
(Continued Next Page) .
12 February 2002
839-8
For Training Purposes Only
)
S39
RUSSIAN CONFIGURATION .
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
)
)
MAXIMUM CROSSWIND
(Continued)
ON
•
For intermediate values of coefficient of friction (IJ)
crosswind is estimated by interpolation.
•
Operation is prohibited on a runway covered with ice at a
coefficient of friction IJ < 0'.3.
)
)
)
)
)
)
)
)
RUNWAYS
NOTE
f
)
CONTAMINATED
CABIN CARGO LIMITS
The maximum allowable cargo weight in the cabin area of the plane
is limited to 2,900 pounds.
The minimum allowable distance be~ween the seat back of the last
occupied seat and cargo in the cabin is 12 inches.
)
SECTION 3
EMERGENCY PROCEDURES
{
)
)
)
)
The procedures outlined within this section are in addition to the
procedures described in Section 3 Emergency Procedures in the
basic Pilot's Operating Handbook.
VHF EMERGENCY RADIO (P·S55A1)
)
NOTE
)
)
)
For aircraft operating in uninhabited C!reas, the VHF
Emergency Radio (P-855A 1) with attached instructions is
located in the pouch behind the copilot's seat.
)
)
)(
) . ~."
)
)
)
)
S39-9
Original Issue
For TrllininlJ Purnoses Onlv
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
EMERGENCY PROCEDURES
(Continued)
FLASHING RED VACUUM LOW ANNUNCIATOR
NOTE
The flashing "VACUUM LOW" annunciator warns that the
left hand vacuum driven attitude indicator and the right hand
vacuum driven directional gyro (if installed) are not
operating correctly. Attitude and heading information should
be derived from the appropriate back-up procedures.
SECTION 4
NORMAL PROCEDURES
The procedures outlined within this section are in addition to the
procedures described in Section 4 Normal Procedures in the basic
Pilot's Operating Handbook.
NOTE
When operating along routes of ± 5 km width not covered by
VOR/DME facilities, it is necessary to verify aircraft position using i
any possible means, including ATC verification, every 60 minutes.
\.
)
COLD WEATHER OPERATIONS
)
NOTE
During aircraft operation at very low ambient air
temperatures (-40°C and lower) and at an altitude of 3,000
meters and higher, the rate of engine power lever
advancement from Flight Idle to Takeoff position should not
be less than 5 seconds.
COLD SOAK
If prolonged cold soak is anticipated, refer to maintenance manual
procedures to prepare the aircraft for cold soak. If the airplane has
cold soaked on the ground for more than two hours at temperatures
colder than -i8°e, refer to maintenance manual procedures to
prepare the aircraft for flight.
I
BEFORE STARTING ENGINE
1. Battery Switch -- ON.
2. Verify Red "Vacuum Low Annunciator IS Flashing".
12 February 2002
839-10
For Training Purposes Only
)
RUSSIAN CONFIGURATION
POH SUPPLEMENT
SECTION 5
PERFORMANCE
)
)
)
)
S39
MODEL 208 (675 8HP)
OPERATION ON CONTAMINATED RUNWAY
The takeoff distance on a paved runway with no more than 0.125
inches (3 mm) of precipitation is equal to the dry runway takeoff
distance.
)
The takeoff distance on a paved runway with precipitation exceeding
0.125 inches (3 mm) is increased by 20% as compared with dry
runway takeoff distance.
)
The takeoff distance on an unpaved runway with packed snow is
increased by 20% as compared with paved runway takeoff distance.
)
)
)
To determine the required landing distance on contaminated paved
runway the dry runway landing distance shall be multiplied by the
following coefficients corresponding to different I.l factors:
)
I
~
K = 1.67, when I.l ~ 0.5 (good braking, dry and equivalent to
dry runway)
)
)
K = .1.72, when 0.5 > I.l
=:: 0.4 (average braking)
K = 2.0, when 0.4 > I.l ~ 0.3 (poor braking)
)
)
The required landing distance on a paved runway with precipitation
exceeding 0.125 inches (3 mm) is determined by multiplying the dry
runway landing distance by K = 2.0.
)
)
The required landing distance on an unpaved runway is determined
by multiplying the paved runway landing distance by K = 2.0.
)
)
)
l" )
)
)
)
)
839-11
Original Issue
For Training Purposes Only
S39
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
CONVERSION FROM FEET TO METERS
10,000
en 8000
a:
w
.-w
:E 6000
4000
2000
o
o
5000 10,000 15,000
,"v,'vvv '::'''',''"'vv
,000 35,000
FEET
2684T1007
Figure 5-1. Conversion From Feet To Meters
',.• .
- .-
)
)
12 February 2002
839-12
For Training Purposes Only
539
RUSSIAN CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
)
METRIC ALTIMETER CORRECTION
ALTERNATE STATIC SOURCE
f
)
)
)
NOTES: ------------------------______________________
1.
Add correction to desired altitude to obtain indicated altitude to fly .
2.
Where altimeter correction values have been replaced by dashes, the correction is
unnecessary because of cond itions in which airspeed is not attainable in level flight.
)
VENTS CLOSED
)
CORRECTION TO BE ADDED - METERS
)
CONDITION
)
)
)
)
(
)
KIAS
80
90
100
120
140
160
FLAPS UP
Sea Level
3,000 m
0
2
5
6
8
11
15
21
23
32
35
47
FLAPS 20"
Sea Level
3,000 m
2
2
6
9
8
12
17
24
26
34
34
46
FLAPS 3~ "
Sea Level
3,000 m
6
9
9
12
12
17
18
24
--
---
--
)
)
VENTS OPEN
)
)
CORRECTION TO BE ADDED - METERS
CONDITION
)
)
)
)
)
):
FLAPS UP
Sea Level
3,000 m
FLAPS 20"
Sea Level
3,000 m
FLAPS 30"
Sea Level
3,000
m
KIAS
60
90
100
120
140
160
-8
-8
-8
-8
-6
-8
-3
-5
2
2
12
-3
-5
0
-2
3
3
9
12
20
2
3
5
6
6
9
12
--
15
15
--
9
24
32
---
) '<..
)
Figure 5-2. Metric Altimeter Correction
)
)
)
12 February 2002
839-13/839-14
For Trainin Pur oses Onl
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
)
)
)
(
A Te Klron Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 40
)
)
BEN DIX/KI NG
GPS NAVIGATION SYSTEM (TYPE KLN 89B)
)
INTERFACED WITH THE KNI 582 RMI
)
I
SERIAL NO.
A
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King GPS Navigation
System (Type KLN 89B) Interfaced with the KNI 582 RMI.
) .
)
)
)
)
APPROVED BY
)j,ld«lpdi:e. ·, .
0
Wendell W. Corneil
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
DATE OF APPROVAL
I~ "1)a.c:.!.M."'I..~ 15198
)
)
COPYRIGHT 1) 1998
CESSNA AIRCRAFT
COMPANY
WICHITA. KANSAS . USA
)
01352-540-00
>c .
f)
Member of GAMA
16 DECEMBER 1998
)
S40-1
For Trainin Pur oses Onl
S40
MODEL 208 (675 SHP)
BENDIX/KING KLN 89B GPS/KNI 582 RMI
POH SUPPLEMENT
SUPPLEMENT
BENDIX/KING GPS NAVIGATION SYSTEM (TYPE
KLN 89B) INTERFACED WITH THE KNI 582 RMI
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
Revision Level
Date of Issue
)
o (Original)
16 December 1998
)
)
)
LOG OF EFFECTIVE PAGES
PAGE
DATE
S40-1 thru S40-4
16 December 1998
REV. NUMBER
o
)
)
)
)
)
)
)
)
)
)
16 December 1998
S40-2
For Training Purposes Only
)
)
BENDIX/KING KLN 89B GPS/KNI 582 RMI
POH SUPPLEMENT
S40
MODEL 208 (675 8HP)
)
SUPPLEMENT
)
)
f
)
)
BENDIX/KING
GPS NAVIGATION SYSTEM (TYPE KLN 898)
INTERFACED WITH THE KNI 582 RMI
)
SECTION 1
GENERAL
)
)
)
)
)
)
)
The KNI 582 RMI is a dual NAV dual ADFcapabieRMI. A remote
NAV1/GPS source select switch interfacing between the RMI and
KLN 898 GPS allows the pilot to switch RMI navigation between
NAV1 and GPS. The remote source select switch is a pushbutton
toggle switch. The switch is divided in half horizontally, the top half
illuminated green is the RMI/NAV1 selector, the bottom half
illuminated cyan is the RMI/GP8 selector.
(/
1-
SECTION 2
LIMITATIONS
)
)
)
)
)
NAV1 (the single solid needle) must be selected on the KNI 582
RMI to enable the RMI to display NAV data from the remote
NAV1/GPS source select switch. The KLN 89B GPS must have an
active flight plan loaded.
)
SECTION 3
EMERGENCY PROCEDURES
)
)
)
No change.
)
X
\
)
)
840-3
16 December 1998
For Trainin Pur oses Onl
S40
MODEL 208 (675 SHP)
BENDIX/KING KLN 898 GPS/KNI 582 RMI
POH SUPPLEMENT
'SECTION 4
NORMAL PROCEDURES
With RMI/GPS selected on the remote source select switch, the
NAV1 (single solid needle) will point to the active waypoint on the
KLN 89B flight plan.
)
)
SECTION 5
)
PERFORMANCE
)
No change.
)
)
)
)
16 December 1998
S40-4
For Training Purposes Only
)
)
~
)
)
CeSSna
A Te,drun Company
J
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208.(675 SHP)
)
SUPPLEMENT 41
)
)
BENDIX/KING (ALLIEDSIGNAL)
ST AND·ALONE • VFR ONLY
GPS NAVIGATION SYSTEM
)
)
(TYPE KLN 898 WITH SOFTWARE LEVEL 02102)
)
l
SERIAL NO.
)
REGISTRATION NO.
)
)
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
. (675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King (AlliedSignal) StandAlone - VFR Only GPS Navigation System (Type KLN 89B with software
level 02/02), not coupled to any other airplane system (FMS or Autopilot),
and certified for VFR use only.
)
APlPROViD
)
)
f)
Member of GAMA
)
)(
) \ ',:,.
)
_v>:de ftef:«b..«:R
W.nden W. Comell
ElcIC\lU". I!ngln_
Ce..nl Aircraft Company
CellllHan Option Manufacturer OE-3
DATI! 0' APPROVAL
COPYRIGHT C> 1999
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS , USA
1& APIlII" 1m
12 APRIL 1999
o1352-S41 -00
)
S41-1
For Training Purposes Only
S41
BENDIX/KING (ALLIEDSIGNAL)
GPS (TYPE KLN 89B) VFR ONLY
MODEL 208 (675 SHP)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 41
BENDIX/KING (ALLIEDSIGNAL)
.STAND-ALONE - VFR ONLY
GPS NA VIGA TION SYSTEM
)
)
)
(TYPE KLN 89B WITH SOFTWARE LEVEL 02102) .
)
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
12 April 1999
)
)
LOG OF EFFECTIVE PAGES
PAGE
S41-1 thru
S41-5/841-6
DATE
12 April 1999
REV. NUMBER
o
Original Issue
841-2
For Training Purposes Only
BENDIX/KING (ALLIEDSIGNAL)
GPS (TYPE KLN 89B) VFR ONLY
541
M'ODEL 208 (675 SHP)
SUPPLEMENT
)
)
BENDIX/KING (ALLIEDSIGNAL)
STAND-ALONE - VFR ONLY
GPS NAVIGATION SYSTEM
{
)
)
(TYPE KLN 898 WITH SOFTWARE LEVEL 02/02)
)
SECTION 1
GENERAL
)
)
GPS (Global Positioning System) is a three-dimensional (3-D)
precise locati9n and navigation system based on a constellation of
24 satellites orbiting the earth. The Bendix/King (AlliedSignal) GPS
Navigation System (Type KLN 89B) consists of a panel-mounted
control display unit, and an externally-mounted flat GPS antenna on
.
the top forward portion of the fuselage
)
)
)
)
)
. A single 5-amp circuit breaker labeled GPS/LORAN on the bottom
row breaker panel powers the KLN 89B Navigation System.
Operation- of the KLN 89B G PS ,Navigation System shall be in
accordance with the Bendix/King (Allied Signal) KLN 89B Pilot's
Guide (supplied with the airplane).
)
)
A NavData Card with a current database is supplied with the KLN
89B GPS. Since this database information is updated every 28
days, it is important to monitor the database expiration date. Once
the database has expired, the GPS system provides an advisory
message which must be acknowledged by the operator. Although
the system will continue to operate normally, the warning message
will be repeated on . each power-up to remind the user that the
database is out of date. To eliminate this warning, the database
must be updated. This update is performed by installing a current
NavData Card.
)
)
)
).
)
)
)
)(
) \ ;.• ,>
)
Jj.CAUTION
,
The database must be updated only while the aircraft
is on the ground. The KLN 898 does not perform
any navigation function while the database is being
updated.
)
S41-3
Original Issue
For Training Purposes Only
S41
MODEL 208 (675 SHP)
BENDIX/KING KLN 89B(ALLIEDSIGNAL)
GPS (TYPE KLN 89B) VFR ONLY
SECTION 2
LIMITATIONS
1. The Bendix/King KLN 89B GPS Navigation System Pilot's Guide, ;
part number 006-08786-0000, dated May 1995 (or later revision),
as applicable to the specific software modification status, must be
immediately available to . the pilot whenever navigation is
predicated on use of the GPS system. - The Operational Revision
Status (ORS) of the Pilot's Guide must match the ORS level
annunciated on the Self Test page.
2. The Bendix/King (AlliedSignal) KLN 89B GPS Navigation
System must utilize Operational Revision Status (GRS) level 02,
or later FAA approved revision.
3. The Bendix/King (AlliedSignal) KLN 898 GPS Navigation
System. as installed, is a stand-alone panel-mounted VFR
navigation system. It may not be coupled to the KAP-150
Autopilot, KFC-150 or KFC-250 Flight Control System (if
installed).
4. IFR
navigation is prohibited
Navigation System as installed.
using the
KLN
)
)
)
)
)
89B GPS
)
5. The
Bendix/King (Allied Signal) KLN 89B GPS Navigation
System is not approved for IFR precision or non-precision
approaches.
6. The followin'g placard must be installed on the instrument panel
)
)
adjacent to the control display unit, signifying that the
Bendix/King (AlliedSignal) KLN 898 GPS Navigation System is
"Not Approved for IFR":
)
)
GPS NOT APPROVED
FOR IFR
Original Issue
S41-4
For Training Purposes Only
BENDIX/KING (ALLIEDSIGNAL)
GPS (TYPE KLN 89B) VFR ONLY
541
MODEL 208 (675 SHP)
)
)
SECTION 3
EMERGENCY PROCEDURES
)
j
)
If sensor information is intermittent or lost, utilize remaining
operational navigation equipment as required.
)
)
SECTION 4
)
NORMAL PROCEDURES
)
)
)
The Bendix/King (AlliedSignal) KLN 89B GPS Navigation System
shall be operated per the Pilot's Guide, 006-08786~OOOO, dated May
1995 (or later revision) supplied with the airplane, and the current
FAA TSO specifications that apply to the use of this equipment.
)
)
SECTION 5
PERFORMANCE
)
)
)
There is no change to the airplane performance when this avionics
equipment is installed.
However, installation of an externallymounted antenna, or related external antennas, will result in a minor
reduction in cruise performance.
)
)
)
)
)
)
841-5/S41-6
Original Issue
For Training Purposes Only
)
)
)
)
)
)
)
)
For Training Purposes Only
~
)
)
J
A.
)
CeSSna
ToJChon Company
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
J
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 42
).
HIGH ALTITUDE TAKEOFF
AND LANDING PERFORMANCE
J
)
(ABOVE 12,000 FEET PRESSURE ALTITUDE)
)
)
l
SERIAL NO.
)
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if takeoff and landing operations are to be conducted above 12,000
. feet pressure altitude.
)
)
)
)
APPROVED
)
)
f)
Member of GAM A
)
ByLd:f{A.· :p
Wendell W. Comail
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
DATE OF APPROVAL
)(
"<.. -~ ,
COPYRIGHT 1999
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
D1352-S42-01
I'
1-'\1\'( 199'
11 MAY 1999
REVISION 1 - 19 JULY 2002
)
S42-1
For Trainin Pur oses Onl
S42
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 8HP)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 42
HIGH ALTITUDE TAKEOFF
AND LANDING PERFORMANCE
)
(ABOVE 12,000 FEET PRESSURE ALTITUDE)
Use the Log of Effective Pages to determine the current status of
Pages affected by the current revision are
this supplement.
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
11 May 1999
19 July 2002
Revision 1
)
LOG OF EFFECTIVE PAGES
Page
*
Revision 8tatus
Revision No.
Revision
Revision
Revision
Added
Added
Added
Added
Added
1
1
1
1
1
1
1
842-1 thru 842-2
* 842-3/842-4
• 842-5 thru 842-14
* 842-15/S42-16
* 542-17 thru 842-28
• 842-29/842-30
• 842-31 thru 842-32
• 842-33/842-34
)
)
)
1
)
)
APPROVED BY
)
fMAPPROVED IN)ER FM: 2' SU8MRT J
ThoC-_ec
)
Dek_'-'_~a.cE
~-~
DATE OF APPROVAL 19
J Ul.Y 2oo~
Revision 1
842-2
For Training Purposes Only
)
)
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
)
542
208 (675 SHP)
SUPPLEMENT
)
) -
HIGH ALTITUDE TAKEOFF
AND LANDING PERFORMANCE
f
)
MO~EL
(ABOVE 12,000 FEET PRESSURE ALTITUDE)
)
SECTION 1
GENERAL
)
)
)
)
I
This supplement provides an engine torque for takeoff graph, and.
airplane performance charts for takeoff and landing operations
between 12,000 feet and 16,000 feet pressure altitudes.
)
SECTION 2
LIMITATIONS
)
)
)
No change.
~•....
SECTION 3
EMERGENCY PROCEDURES
)
)
)
No change.
)
SECTION 4
)
NORMAL PROCEDURES
)
No change.
)
SECTION 5
PERFORMANCE
)
)
)
)
)
For engine torque for takeoff above 12,000 leet pressure altitude,
refer to the Engine Torque for Takeoff graph in Figure 1 of this
supplement.
For takeoff and landing operations above 12,000 feet pressure
altitude, refer .to airplane performance charts in Figure 2 thru Figure
19 of this supplement.
)
)
)
542·3/S42-4
Revision 1
For Trainin Pur oses Only
)
)
)
)
)
)
For Training Purposes Only
HIGH ALTITUDE TAKEOFF AND
LAN DING (ABOVE 12,000 FEET)
S42
MODEL 208 (675 8HP)
ENGINE TORQUE FOR TAKEOFF
CONDITIONS:
i
)
)
)
1900 RPM
60 KIAS
Inertial Separator - Normal
NOTES:
1. Torque increases approximately 10 Ft-Lbs from 0 to 60 KIAS.
)
2. Torque on this chart shall be achieved without exceeding 805°C ITT or 101 .6 percent
Ng. When the lIT exceeds 765°C, this power setting is time limited to 5 minutes,
)
3 . With the inertial separator in BYPASS and takeoff power set below the torque limit
(1865 Ft-Lbs). decrease torque setting by 15 Ft-Lbs.
)
4 . With the cabin heater on and takeoff power set below the torque limit (1865 Ft-Lbs).
decrease torque setting by 65 Ft-Lbs.
)
A25674
)
(
)
)
(J)
~
Ii:
)
)
w
:J
0
a::
0
l-
)
)
)
)t " ,
>' :>
OUTSIDE AIR TEMPERATURE· ·C
)
Figure 1_ Engine Torque for Takeoff
)
)
Revision 1
842-5
For Traininl! Purposes Only
U>
~
'"
m
-
(WITHOUT CARGO POD)
~
::::
Inertial Separator - Nonnal
Cabin Heat - Off
Torque Set per Figure 5-8
Paved, Level, Dry Runway
Zero Wind
0
""l
0
III
5"
5"
pj
"'0
:::I
0
Ci)"
OQ
=
"C
(l)
en
til
~
II>
~
=
~
"
c:
co"
en
~
(l)
~
~
::D
(l)
2-
:E
=i
:::J:
0
c:
.....
l>
1. Short field technique, as specified in Section 4 . .
2. Decrease dislancesl 0% for each 11 knots headwind. For operation with tailwinds up to 10 knots,
Increase distances by 10% for each 2 knOts"
3. For operation on a dry, grass runway, refer to Figure 2A to determine takeoff ground roll distance.
4. With takeoff power set below the torque limit (1865 ft-Ibs), increase distance (both ground roll and
total distance) by 3% for Inertial separator in BYPASS,and increase ground roll 5% and total
distances 9% for cabin heat on.
5. Where distance values have been replaced by dashes, operating temperature limits of the airplane
would be greatly exceeded. Those distances which are Included, but the operation slightly exceeds
the temperature limit,are provided for interpolation purposes only"
0
'"0
:J:
.3!
(")
NOTES:
""l
0
CJ)
1900 RPM
7'
""l
'-'
01
Flaps 20°
ll)
-3
0>
CONDITIONS:
!"
ro
f\)
0
co
CD
0
~N
r
SHORT FIELD
"TI
cO"
c:
~
~cn
O~
TAKEOFF DISTANCE
:a
C>
0
"tJ
0
c
rJ:
»ZG'>
OI
Z»
G'>~
~~
IIlC
00
:J
15000 2830
16000 3175
5055
5780
3185
3S85
6830
3315
2165
2410
2690
3765
2435
4310
2760
4245
2720
3095
4810
3045
3435
3885
4890
5595
6490
8040
12000
1735
2955
1930
::l.
1925
3300
'"
'"0"'
13000
"
a:
en:::r
14000 2140
15000 2385
16000 2665
3700
4170
4725
2145
2390
2675
4190
4755
3020
5500
3000
5430
3395
6345
12000 1465
13000 1620
14000 1795
15000 2000
16000 2230
2..a5
2745
1625
1805
2755
3075
1815
2020
3110
3060
3430
3860
2005
2235
3445
3880
2250
3920
2515
2500
4395
2820
4445
5065
:::r
0
7500
70
80
CO·
<0
~
I\)
g,
!:9
(J)
~
I\)
~
-
G)r
~
3610
4075
c
:.
ZGl
OJ:
5820
8730
en
0
~-
TAKEOFF
20·C
-2Q°C
-i0·C
O·C
iD·C
WEIGHT SPEED
LBS
KIAS
PRESS GRD TOTAL GRD TOTAL GRO lOTAL GRD lOTAL GRD lOTAL
ROU TO
ROLL
TO
ROLL TO
ROLL TO
TO
ALT ROU
UFT AT
FT
50FT
FT
50FT
50FT FT 50FT FT 50FT
FT
FT
OFF 50FT
8000
72
82
12000 2045 3520 2280 3975 2565 4540 2895 5245 3295 6205
13000 2275 3950 2545 4480 2865 5155 3240 6015 3705 7225
14000 2535 4455 2840 5085 3210 5895 3645 6980 4190 8595
<0
...
rI
z~
Il:l
"'Q
;:
'-
REFER TO SHEET 1 FOR APPROPRIATE CONDITIONS AND NOTES
c
ro
~
'-~.
"'-""
(WITHOUT CARGO POD)
cO"
0
'-'-
'--
'.
TAKEOFF DISTANCE
SHORT FIELD
CD
:::l
~'--
'-"'-'--""-"
""-"
3no
4125
8275 4765 10730
4885 10140 -
7840
3480
3940
-
5020
5755
6675
7920
-
>~
CUC
0 0
ac
..:10
::I:
-t
n
~
::u
mz
G)
0
"lJ
0
C
s::
0
0
7000
67
n
3485
3535
2270 1-> 3980
2535 4510
2850 5160
3210 5960
2035
2300
2575
2885
3255
-
4075
4620
52eo
6125
-
m
r
I\)
0
00
en
---I
(J1
(J)C/J
J:~
.3!1\)
S42
H IGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
WITHOUT CARGO POD
TAKEOFF DISTANCE
(DRY GRASS GROUND ROLL DISTANCE)
FLAPS 20°
A26012
7000 ~
~
Iii
~
en
.,-·-T... ~~'·. ":" ..!'~" "~ '-.~
~
i
..
6000 i
~;
:~ -~: >',:'-':1':::
: :
t
;'
1"
~.
i
~
~.
1. ,
i. '- ,
,
,- - : - "
j
"
~
~
"I
:
:
;
~ !
-1
j
! :,
~ 2ooot'i ~ f ':':":I~J:f~!'i- -Fl'-";"-":-;,:'r 'i:':r"l : ','Ei:_:rr-:r-'f{"
t ',' i' - ,- L, .
I ;-I, -I'! "-,- + i--I
, C!l
.! '
- .j -
/
~ '~IU~iJii.J}HIlnJ J:tlIH1111
o
1000
2000
3000
4000
5000
DRY PAVED GROUND ROLL DISTANCE - FEET
Figure 2A. Takeoff Distance - Grass Runway - Short Field
S42-8
Revision 1
For Training Purposes Only
)
)
S42
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
)
WITHOUT CARGO POD
TAKEOFF DISTANCE
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS UP
)
)
)
)
CONDITIONS:
NOTES:
Flaps 0 Degrees
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 1
Paved, Level, Dry Runway
Zero Wind
Use Type " or Type IV Anti-ice Fluid takeoff
techniques, as specified in Section 4 of the POH.
2. Decrease distances 10% for each 11 knots headwind.
For operation with tailwinds up to 10 knots. increase
distances by 10% for each 2 knots.
3. For operation on a dry, grass runway, refer to Figure
3A to determine ground roll distance.
4. With takeoff power set below the torque limit (1865 FtLbs), increase distance (both ground roll and total
distance) by 3% for inertial separator in BYPASS, and
increase .ground roll 5% and total distance 9% lor
cabin heat on.
5. Where distance values have been replaced by dashes,
operating temperature limits of the airplane would be
greatly exceeded. Those distances which are included,
but the operation slightly exceeds the temperature limit,
are provided for interpolation purposes only.
1.
)
)
)
)
)
l
)
TAKEOFF
SPEED
PRESS
LBS
KIAS
ALT
ORND
FT
)
LIFT
AT
8000
89
104
)
)
7500
89
104
)
)
7000
89
)
104
·10·C
10'C
O'C
TOTAL
GRNO
ROLL
TO
ROLL
TO
ROLL
TO
ROLL
TO
FT
50 FT
FT
50FT
FT
50 FT
FT
50FT
12000
13000
14000
3155
3480
3845
5320
5925
6620
3490
3880
4270
5955
6660
7485
3885
4295
4760
6730
7570
8575
4330
4805
5335
7690
8740
10065
15000
16000
4260
4725
7440
8425
4740
5270
6485
9730
5295
5900
9855
11570
5955
6660
11950
15120
12000
2925
4945
3240
5530
3600
6245
4010
7135
13000
14000
3230
3565
5500
6145
3575
3955
61BO
6940
39BO
4405
7020
7950
444S
4935
8100
9325
15000
16000
3945
4375
6900
78tO
4385
4875
7865
9015
4895
5450
9130
10720
5500
6145
11070
14010
12000
13000
14000
2705
2980
3290
4570
SOBS
5675
2990
3300
3850
5115
5710
6410
3320
3670
4060
5770
6485
7335
3700
4095
4540
6585
7480
8605
15000
16000
3540
4030
6375
7210
4045
7260
5060
8315
4510
5015
6425
4490
9885
5645
10210
12930
OFF 50 FT
)
·20· C
WEIGHT
TOTAL GRND TOTAL
GRNO TOTAL
)(
) '. .
Figure 3. Takeoff Distance - Flaps Up
)
)
)
)
S42-9
Revision 1
For Training Purposes Only
542
MODEL 208 (675 8HP)
HIGH ALTITUDE TAKEOFF AND
• LANDING (ABOVE 12,000 FEET)
WITHOUT CARGO POD
TAKEOFF DISTANCE
(DRY GRASS GROUND ROLL)
FLAPS UP
A28013
Figure 3A. - Takeoff Distance - Grass Runway - Flaps Up
Revision 1
842-10
For Training Purposes Only
542
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
)
)
WITHOUT CARGO POD
)
RATE OF CLIMB - TAKEOFF FLAP SETTING
f.
FLAPS 20°
)
)
)
)
CONDITIONS:
Takeoff Power
1900 RPM
Inertial Separator· Normal
Zero Wind
NOTES:
)
)
)
)
1.
Do not exceed torque limit for takeoH per ENGINE TORQUE FOR TAKEOFF chart.
When ITT exceeds 765°C, this power setting Is time limited to 5 minutes.
2. With climb power set below the torque limit, decrease rate 01 climb by 20 Ipm lor inertial
separator set in BYPASS and 45 fpm for cabin heat on.
3. Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greaUyexceeded. Those rates of climb which are included, but
the operation slightly exceeds the temperature limit, are provided for interpolation
purposes only.
)
WEIGHT
LBS
8000
)
)
)
7500
)
)
)
PRESS
CLIMB
ALT
SPEED
FT
KIAS
12000
13000
14000
15000
16000
87
86
85
85
84
915
640
765
695
620
750
675
605
530
460
555
485
415
345
275
340
275
205
12000
13000
14000
15000
16000
85
85
84
83
83
1035
955
B80
605
730
860
785
710
635
560
660
585
515
440
370
435
365
295
12000
13000
14000
15000
16000
84
84
83
82
81
1170
1085
1005
925
650
985
905
830
750
675
775
700
625
550
475
540
465
395
RATE OF CLIMB - FPM
·20°C
DoC
20°C
40°C
..
..
..
..
)
7000
)
>(
..
..
)
)
Figure 4. Rate of Climb - Takeoff Flap Setting
)
)
)
842-11
Revision 1
For Training Purposes Only
S42
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
WITHOUT CARGO POD
CLIMB GRADIENT· TAKEOFF FLAP SETTING
FLAPS 20·
CONDITIONS:
}
Takeoff Power
1900 RPM
Inertial Separator - Normal
Zero Wind
NOTES:
1. Do not exceed torque limit for takeoff per ENGINE TORQUE FOR TAKEOFF chart_
When ITT exceeds 76S' C, this power setting is time limited to S minutes. .
2. With climb power set below the torque limit, decrease rate of climb by 10 FT/NM for
inertial separator sel in BYPASS and 30 FT/NM for cabin heal on.
3. Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greatly exceeded. Those rates of climb which are included, but
the operation slightly exceeds the temperalure limit, are provided for interpolation
purposes only.
WEIGHT
LBS
'8000
7500
7000
PRESS
ALT
F"J:
CLIMB
SPEED
KIAS
CLIMB GRADIENT - FT/NM
-20°C
O°C
20°C
40°C
12000
13000
14000
15000
16000
76
. 76
76
76
76
570
515
465
415
365
455
405
355
310
265
330
285
240
200
155
205
165
125
12000
· 13000
14000
15000
16000
73
73
73
73
73
655
600
545
490
440
530
480
430
380
330
400
355
305
260
215
270
225
180
12000
13000
14000
15000
16000
71
71
71
71
70
755
. 695
620
565
510
455
405
485
430
380
330
285
340
290
245
635
580
525
---
--
--
---
Figure 5. Climb Gradient - Takeoff Flap Setting
Revision 1
S42-12
For Training Purposes Only
542
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
)
MODEL 208 (675 SHP)
WITHOUT CARGO POD
)
MAXIMUM CLIMB GRADIENT
J
FLAPS UP
CONDITIONS:
Takeoff Power
1900 RPM
Inertial Separator - Normal
Zero Wind
)
)
NOTES:
)
1. Do not exceed torque limit for takeoff per ENGINE TORQUE FOR TAKEOFF chart.
When ITT exceeds 765°C. this power setting is time limited to 5 minutes.
)
2. With climb power set below the torque limit. decrease rate of climb by 10 FT/NM for inertial
separator set in BYPASS and 40 FT/NM for cabin heat on.
3. Where rate of climb values have been replaced by dashes, operating temperature limits of
the airplane would be greatly exceeded; Those rates of climb which are included, but the
operation slightly exceeds the temperature limit, are provided for interpolation purposes
only.
)
)
)
)
WEIGHT
LBS
)
8000
)
)
)
)
7500
)
PRESS
ALT
FT
CLIMB
CLIMB GRADIENT - FTfNM
SPEED
KIAS
-20°C
DoC
20·C
40·C
88
88
87
545
500
455
405
16000
87
87
420
380
335
295
365
250
205
165
130
12000
13000
14000
15000
16000
86
85
85
85
84
620
570
525
475
425
490
445
400
355
310
340
300
260
220
180
180
145
115
12000
13000
14000
15000
16000
84
705
240
655
600
550
500
565
515
470
420
375
410
83
83
82
81
365
200
165
12000
13000
14000
15000
285
245
130
100
70
---
---
)
7000
)
)
4
.
)
325
280
235
--
--
"",,"",..;'
)
Figure 6_ Maximum Climb Gradient - Flaps Up
)
)
)
S42-13
Revision 1
For Trainin Pur oses Onl
S42
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
WITHOUT CARGO POD
CRUISE CLIMB
FLAPS UP
CONDITIONS:
1900 RPM
Inertial Separator · Normal
Zero Wind
NOTES:
1. Torque set at 1865 foot-pounds or lesser value must not exceed maximum climb
In of .765°C or Ng of 101.6%.
.
2.
With climb power sel. below the torque limit. decrease rate of climb by 50 fpm lor Inertial
separator set in BYPASS and 70fpm for cabin heat on.
3. Where rate 01 climb values have been replaced by dashes, an appreciable rate of climb
for the weight shown cannot be expected or operating temperature limits 01 the airplane
would be greatly exceeded. Those rates of climb which are included. but the operation
slightly exceeds the temperature limit, are provided for interpolation purposes only.
WEIGHT
LBS
8000
7500
7000
PRESS
ALT
CLIMB
SPEED
FT
KIAS
12000
13000
14000
15000
16000
120
120
120
120
120
1100
1015
920
820
715
850
755
655
560
475
540
445
360
270
180
195
105
20
t2000
13000
14000
15000
16000
120
120
120
120
120
1215
1130
1025
920
815
955
850
750
645
555
625
525
435
340
245
260
165
70
12000
13000
14000
15000
16000
120
120
120
120
120
1350
1255
1145
1030
920
720
610
515
415
315
325
225
130
RATE OF CLIMB · FPM
·40°C
·20°C
1065
960
850
740
645
O°C
20°C
..
..
..
..
..
..
Figure 7. Cruise Climb - Flaps Up, 120 KIAS
Revision 1
842-14
For Training Purposes Only
542
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
WITHOUT CARGO POD
RATE OF CLIMB - BALKED LANDING
FLAPS 30°
)
CONDITIONS:
)
TakeoH Power
1900 RPM
Inertial Separator· Normal
Zero Wind
)
NOTES:
)
)
1.
Do not exceed torque limit for takeoff per ENGINE TORQUE FOR TAKEOFF chart.
When ITT exceeds 765°C, this power setting Is time limited to 5 minutes.
2. With climb power set below the torque limit, decrease rate of climb by 15 fpm for inertial
3.
)
separator set in BYPASS and 45 fpm for cabin heat on.
Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greatly exceeded. Those rates of climb which are included, but
the operation slightly exceeds the temperature limit, are provided for interpolation
purposes only.
)
(
)\
WEIGHT
LBS
)
7800
)
PRESS
ALT
FT
CLIMB
SPEED
KIAS
12000
13000
14000
15000
16000
79
78
78
77
76
RATE OF CLIMB - FPM
-20°C
O°C
20°C
815
740
670
600
530
655
585
515
445
375
470
405
340
270
205
270
205
140
935
855
785
710
640
765
690
620
550
480
575
505
435
' 365
295
360
295
230
1065
985
910
830
755
890
810
740
665
590
690
615
545
470
400
465
400
330
)
7300
)
)
)
6800
)
)(
12000
13000
14000
15000
16000
79
78
12000
13000
14000
15000
16000
77
77
77
76
76
76
75
75
40°C
---
---
---
)
Figure 8. Rate of Climb - Balked Landing
)
)
)
S42-15/S42-16
Revision 1
For Training Purposes Only
)
For Training Purposes Only
542
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
)
WITHOUT CARGO POD
)
TIME, FUEL, AND DISTANCE TO CLIMB
),
CRUISE CLIMB
)
)
CONDITIONS:
)
Flaps Up
1900 RPM
Inertial Separator· Normal
)
NOTES:
)
1. Torque set at 1865 foot-pounds or lesser value must not exceed maximum climb
In of 765°C or Ng of 101.6%.
)
2.
3.
4.
)
)
Add 35 pounds of fuel for engine start, taxi, and takeoff allowance.
Distances shown are based on zero wind .
With inertial separator set in BYPASS or cabin heat on, increase time, fuel , and distance
numbers by 1% for each 1000 fee! of climb.
)
)
.
CLIMB FROM SEA LEVEL
l
PRESS
CLIMB
20 DEQ C BELOW
STANDARD
20 DEG C ABOVE
STANDARD TEMP
TEMPERATURE
STANDARD TEMP
)
WEIGHT
ALT
SPEED
TIME
FUEL
DIST
TIME
FUEL
DIST
TIME
FUEL
LBS
FT
KIAS
MIN
LBS
NM
MIN
LBS
NM
MIN
LaS
• NM
)
8000
12000
120
11
75
22
12
82
27
21
120
120
12
13
82
89
25
27
14
16
91
101
31
35
24
28
118
134
153
47
13000
14000
55
85
)
)
)
7500
)
)
)
7000
DIST
15000
120
14
97
30
18
112
40
33
176
n
16000
120
16
106
34
20
123
45
40
207
95
12000
120
10
68
20
11
74
24
120
11
74
22
12
82
27
18
21
103
118
40
13000
14000
120
12
81
. 25
14
90
31
24
131
55
15000
120
13
88
27
16
100
35 ,
27
148
65
16000
120
14
95
30
18
109
40
32
170
n
12000
120
9
61
18
16
90
35
120
10
11
67
73
20
67
74
22
13000
10
11
25
18
22
13
81
28
20
101
113
41
47
B9
97
31
23
27
127
35
55
64
"
14000
120
15000
16000
120
120
12
79
25
14
13
86
27
16
143
47
y'
\.,
)
Figure 9. Time, Fuel, and Distance to Climb - Cruise Climb
)
)
)
S42-17
Revision 1
For Training Purposes Only
-
?:ow
O~
. LANDING DISTANCE
~r\)
SHORT FIELD
(WITHOUT CARGO POD)
r
I\)
0
ex>
CONDITIONS:
en
Flaps 30°
.
Power Lever - Idle after clearing obstacles. Beta
range (lever against spring) after touchdown.
Propeller Control Lever- MAX
Maximum Braking
Paved. Level, Dry Runway
Zero Wind
~
(}1
en
.3!
:r:
:E
::j
:t
0
NOTES: - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -
1. Short field technique as specified in Section 4.
2. Decrease distances 10% for each 11 knots headwind.
c:
-I
0
For operation with
tailwinds up to 10 knots. increase distances by 10% for each 2 knots.
3. For operation on a dry. grass runway, increase distances by 40% of the
"ground roll" figure.
4.lf a landing with flaps up is necessary. increase the approach speed by 15
KIAS and allow for 40% longer distances.
5. Use of maximum reverse thrust after touchdown reduces ground roll by
approximately 10%.
, 6. Where distance values have been · replaced by dashes. operating
temperature limits of the airplane would be greatly exceeded.
Those
distances which are included, but the operation slightly exceeds the
temperature limit, are provided for interpolation purposes only.
»
lJ
rJ:
G')
»ZG)
0
'U
Z»
0
0
o:::r:
~~
»-1
roc
00
::a
Q
0
"tI
0
c
s:
0
0
m
I
I\)
0
CD
m
'"
~(J)
:J:~
~N
en
~
I\)
-
?:oCJ)
TAKEOFF DISTANCE
o~
,~N
I
I\)
SHORT FIELD
o
(CARGO POD INSTALLED)
I\)
0
ex>
m
--.J
CONDITIONS:
Aaps20°
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 5-8
Paved, Level, Dry Runway
Zero Wind
NOTES:
1. Short field technique, as specified In Section 4.
2. Decrease distances 10% for each 11 knots headwind. For operation with tailwinds up to 10 knots,
increase distances by 10% for each 2 knots.
3. For operation on a dry, grass runway, refer to Figure 11A to detennine takeoff ground roll distance.
4. With takeoff power set below the-torque limit (1865 ft-Ibs), increase distance (both ground roll and
total distance) by 3% for inertial separator in BYPASS, and increase ground roll 5% and total
distances 10% for cabin heat on.
5. Where distance values have been replaced by dashes. operating temperature limits of the airplane
would be greatly exceeded. Those distances which are included but the operation slightly exceeds
the temperature limit are provided for Interpolation purposes onlY.
01
C/)
:I:
:]
0
»
:D
C)
0
"0
0
c
Z
':I:
-t
O:I:
en
»
r
r
m
c
»ZG)
Z»
G),
_-i
»-i
mc
00
=i
roC
TAKEOFF
~
'"I
GL~
REFER TO SHEET 1 FOR APPROPRIATE CONDITIONS AND NOTES
(1)
"rl
ol:
-»
Zr
(CARGO POD INSTALLED)
."
c::
CD
0
»ZG)
SHORT FIELD
C;;O
c:i"
r:r:
TAKEOFF DISTANCE
(1)
FT
50FT
2065
2300
3595
4045
2565
4570
2870
3220
5205
2795
3125
3505
3950
-L»
1\)/\
- m
go
FT
-
3390
3805
4300
2185
2440
2725
3855
4355
4950
3140 2040
3565
3525
2275
4020
3975
4510
2545
2855
4565
5220
-
4425
5040
5790
2795
3135
5175
3535
6965
3485
6750
4005
8365
3945
8030
2060
2295
2570
2885
3615
4080
4635
5325
6180
2460
2755
3090
3255
-
2330
2605
2925
3300
-
5960
-
4180
4755
5455
6360
-
0
0."
."."
:II
mz
l>
G')
0
m»
.:jO
"tI
ac
Z
Ul
-f
l>
r
r-
m
c
s:
0
0
m
r
I\)
0
(X)
m
--..J
~(J)
:r:~
.:gN
S42
MODEL 208 (675 SHP)
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
CARGO POD INSTALLED
TAKEOFF DISTANCE
(DRY GRASS GROUND ROLL)
FLAPS 20°
A28014
)
)
)
)
)
)
Figure 11 A. Takeoff Distance - Grass Runway - Short Field
Revision 1
S42-22
For Training Purposes Only
S42
HIGH ALTITUDE TAKEOFFAND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
CARGO POD INSTALLED
)
)
TAKEOFF DISTANCE
(
(GROUND ROLL DISTANCE AND TOTAL DISTANCE TO CLEAR 50 FEET)
FLAPS UP
)
)
)
)
)
CONDITIONS:
NOTES:
Flaps 0 Degrees
1900 RPM
Inertial Separator - Normal
Cabin Heat - Off
Torque Set per Figure 1
Paved, Level, Dry Runway
Zero Wind
1. Use Type II or Type IV Anti-Ice Fluid takeoff techniques,
as specified in Section 4 of the POH.
Decrease distances 10% for each 11 knots headwind .
For operation with tailwinds up to 10 knots, increase
distances by 10% for each 2 knots.
3. For operation on a dry, grass runway, refer to Figure 12A
to determine ground roll distance.
4. With takeoff power set below the torque limit (1865 FtLbs), increase distance (both ground roll and total
distanpe) by 3% for inertial separator in BYPASS, and
increase ground roll ' 5% and total distance 9% for cabin
heat on.
5. Where distance values have been replaced by dashes,
operating temperature limits of the airplane would be
greatly exceeded. Those distances which are included,
but the operation slightly exceeds the temperature limit,
are provided for interpolation purposes only.
)
)
)
)
(
)
TAKEOFF
-10'C
WEIGHT
SPEED
PRESS
LBS
KfAS
ALT
GRND TOTAL GRND TOTAL GAND TOTAL GRND TOTAL
FT
ROLL
TO
ROLL
TO
ROLL
TO
ROLL
TO
FT
50 FT
FT
50FT
FT
50FT
FT
50FT
12000
3200
3545
3920
3945
8010
6875
4345
mo
4370
4845
6955
7870
4405
3535
3910
5455
6090
6830
6125
13000
14000
8995
4890
5440
9200
10790
15000
4330
4810
n20
4625
5370
8660
5395
10500
6075
10330
6015
12755
6800
13375
19795
12000
2970
5065
3290
5690
3660
6455
4080
7430
13000
3280
5655
6380
40SO
3625
6340
7205
4485
7300
8340
4525
14000
3635
4025
5025
8525
10000
15000
16000
4010
7160
4990
12400
9575
5555
9735
11620
5610
8170
4465
4965
8235
4450
6275
18385
12000
2745
4685
3040 ·
5260
3375
3765
6860
'13000
3025
5225
5895
14000
3345
5860
3355
3710
8655
3735
4135
5965
6740
7695'
4170
4625
7870
9225
15000
16000
3700
6615
4115
7600
4590
4100
7540
4570
6835
5110
8980
10910
5160
5760
11445
17005
LIFT
)
AT
OFF SOFT
)
2.
8000
89
104
)
)
16000
7500
89
104
)
)
7000
89
)
)
104
·20'C
8810
O'C
10'C
>
( ,
)
"",;,,;.; /
Figure 12. Takeoff Distance
)
/
~
Flaps Up
\
)
)
S42-23
Revisioh 1
For Training Purposes Only
S42
MODEL 208 (675 SHP)
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
CARGO POD INSTALLED
TAKEOFF DISTANCE
)
(DRY GRASS GROUND ROLL)
)
FLAPS UP
)
1126015
)
)
)
)
)
)
)
)
Figure 12A. Takeoff Distance - Grass Runway - Flaps Up
Re~ision
542·24
For Training Purposes Only
1
)
542
HIGH ALTITUDE TAKEOFF AND
)
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
)
)
CARGO POD INSTALLED
)
RATE OF CLIMB - TAKEOFF FLAP SETIING
l
FLAPS 20°
)
CONDITIONS:
)
Takeoff Power
1900 RPM
Inertial Separator · Normal
Zero W ind
)
)
NOTES:
)
1. Do not exceed torque limit for takeoff per ENGtNE TORQUE FOR TAKEOFF chart.
When ITT exceeds 765·C, this power setting Is time limited to 5 minutes.
)
Wilh climb power set below the torque limit, decrease rate of climb by 20 fpm for inertial
separator set in BYPASS and 45 fpm for cabin heat on.
3. Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greatly exceeded. Those rates of climb which are included but
the operation slightly exceeds the temperature limit are provided for interpolation
purposes only.
2.
)
)
)
)
f
'\~ :..
)
WEIGHT
LBS
8000
)
)
7500
)
)
FT
CLIMB
SPEED
KIAS
12000
13000
14000
15000
16000
87
86
85
85
84
880
805
730
655
585
800
725
650
575
505
710
635
565
490
420
515
445
375
305
235
300
230
165
12000
13000
14000
15000
16000
85
85
84
83
83
995
920
840
765
690
910
835
620
545
475
400
330
395
320
255
685
610
820
745
670
595
520
12000
13000
14000
15000
16000
84
84
83
82
81
1130
1045
965
885
810
1040
960
880
800
725
945
865
79Q
710
635
735
655
580
505
430
495
425
350
PRESS
ALT
RATE OF CLIMB· FPM
·20
0
e
· 10 0 e
760.
O°C
20°C
40°C
..
..
..
..
)
7000
..
..
Figure 13. Rate of Climb· Takeoff Flap Setting
)
S42-25
Revision 1
For Trllinin Pur oses Onl
542
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
CARGO POD INSTALLED
CLIMB GRADIENT - TAKEOFF FLAP SETTING
FLAPS 20°
CONDITIONS:
Takeoff Power
1900 RPM
Inertial Separator - Normal
Zero Wind
NOTES:
1_ Do not exceed torque limit for takeoff per ENGINE TORQUE FOR TAKEOFF chart_
When ITT exceeds 765°C, this power setting is time limited to 5 minutes.
2. With climb power set below the torque limit, decrease rate of climb by 10 FT/NM for
Inertial separator set in BYPASS and 30 FT/NM for cabin heat on.
3. Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greatly exceeded. Those rates of climb which are included but
the operation slightly exceeds the temperature limit are provided for interpolation
purposes only.
WEIGHT
LBS
8000
7500
7000
PRESS
ALT
CLIMB
CLIMB GRADIENT - FTINM
DoC
-10 oe
20°C
40°C
FT
SPEED
KIAS
12000
13000
14000
15000
16000
76
76
76
76
76
555
500
445
395
350
495
445
395
345
300
435
385
340
290
245
315
270
225
180
140
190
145
105
12000
13000
14000
15000
16000
73
73
73
73
73
640
580
525
475
420
580
525
470
420
365
515
460
410
360
310
365
335
290
245
200
250
205
165
12000
13000
14000
15000
16000
71
71
71
71
70
740
675
615
560
505
670
615
555
500
445
605
545
495
440
390
465
415
365
315
265
320
275
230
-20°C
---
---
--
--
Figure 14. Climb Gradient - Takeoff Flap Setting
Revision 1
S42-26
For Training Purposes Only
}
).
.542
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 20B (675 SHP)
)
)
CARGO POD INSTALLED
)
MAXIMUM CLIMB GRADIENT
x
)
FLAPS UP
CONDITIONS:
)
Takeoff Power
1900 RPM
Inertial Separator - Normal
Zero Wind
)
)
NOTES:
)
1_
Do not exceed torque limit for takeoff per ENGINE TORQUE FOR TAKEOFF chart.
When ITT exceeds 765·C, this power se"lng Is lime limited to 5 minutes. .
2.
With climb power se.t below the torque limit, decrease rate of climb by 10 FT/NM for
inertial separator set in BYPASS and 40 FT/NM for cabin heal on.
Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greatly exceeded . Those rates of climb which are included but
the operation slightly exceeds the temperature limil are provided for interpolation
purposes only.
)
)
3.
WEIGHT
LBS
BODO
PRESS
ALT
FT
CLIMB
SPEED
KIAS
12000
13000
14000
15000
16000
BB
BB
B7
87
87
525
475
430
385
340
460
415
375
330
285
400
355
315
270
230
260
220
lB5
145
105
110
75
45
12000
13000
14000
15000
16000
86
85
85
B5
84
600
550
500
450
405
535
485
440
395
350
465
420
375
330
285
320
280
240
195
155
160
125
90
12000
13000
14000
15000
16000
84
83
83
82
81
680
630
580
525
475
615
565
515
465
415
540
495
445
400
350
385
345
300
255
210
215
180
145
. CLIMB GRADIENT - FT/NM
-20· e
-10· e
O· C
20· C
40°C
---
)
7500
)
)
7000
)
)(
---
-.
--
\:....."
) -'''-
)
)
Figure 15. Maximum Climb Gradient - Flaps Up
542-27
Revision 1
For Training Purposes Only
S42
H IGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 SHP)
CARGO POD INSTALLED
CRUISE CLIMB
FLAPS UP
CONDITIONS:
1900 RPM
Inertial Separator - Normal
Zero Wind
NOTES:
1. Torque set at 1865 foot-pounds or lesser value must not exceed maximum climb
ITT of 765°C or Ng of 101_6%.
2. With climb power set below the torque limit. decrease rate of climb by 50 fpm for inertial
separator set in BYPASS and 70 fpm for cabin heat on.
3. Where rate of climb values have been replaced by dashes, an appreciable rate of climb
for the weight shown cannot be expected or operating temperature limits of the airplane
would be greatly exceeded. Those rates of climb which are included but the operation
slightly exceeds the temperature limit are provided for interpolation purposes only.
WEIGHT
LBS
8000
7500
7000
PRESS
ALT
FT
CLIMB
SPEED
KIAS
12000
13000
14000
15000
16000
120
RATE OF CLIMB - FPM
-40"C
-20°C
O°C
20°C
755
655
555
460
370
440
345
260
165
75
90
120
1005
925
820
720
615
12000
13000
14000
15000
16000
120
120
120
120
120
1115
1030
925
815
705
850
745
640
540
445
520
415
325
225
130
145
50
12000
13000
14000
15000
16000
120
1240 ·
120
1150
1035
920
805
955
845
735
625
525
605
495
400
295
190
205
105
5
120
120
120
120
120
120
--
--
---
----
--
--
Figure 16. Cruise Climb - Flaps Up
Revision 1
S42-28
For Training Purposes Only
)
)
S42
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
)
MODEL 208 (675 SHP)
)
)
CARGO POD INSTALLED
)
RATE OF CLIMB· BALKED LANDING
f
FLAPS 30°
)
CONDITIONS:
)
Takeoff Power
1900 RPM
Inertial Separator - Normal
Zero Wind
)
)
' NOTES:
)
1. Do not exceed torque limit lor takeoff per ENGINE TORQUE FOR TAKEOFF chart.
When In exceeds 765°C, this power setting is time limited to 5 minutes.
)
2.
W ilh climb power set below the torque limit. decrease rate of climb by 15 fpm for inertial
separator set in BYPASS and 45 fpm for cabin heat on .
3. Where rate of climb values have been replaced by dashes, operating temperature limits
of the airplane would be greatly exceeded, Those rates of climb which are included but
the operation slightly exceeds the temperature limit are provided for interpolation
purposes only.
)
)
)
(
WEIGHT
LBS
PRESS
ALT
FT
CLIMB
SPEED
KIAS
12000
13000
14000
15000
16000
79
78
78
RATE OF CLIMB - FPM
·20°C
-WC
O°C
20°C
40°C
)
7800
)
)
)
)
7300
)
)
705
635
565
495
425
625
555
485
415
345
440
375
305
240
175
235
175
110
76
785
71,0
640
570
500
12000
13000
14000
15000
16000
79
78
77
76
76
900
825
755
680
610
820
745
675
600
530
735
660
590
515
445
540
475
405
335
265
330
265
195
12000
13000
14000
15000
16000
77
77
1030
955
875
800
725
945
870
795
720
645
855
780
' 705
630
560
655
585
510
440
365
430
365
295
77
---
..
--
)
6800
)
)
r(.
)
76
75
75
---
" ,.'
)
Figure 17 . Rate of Climb - Balked Landing
)
)
S42-29/S42-30
Revision 1
For Training Purposes Only
)
)
)
)
\
J
)
)
)
)
For Training Purposes Only
)
)
)
842
HIGH ALTITUDE TAKEOFF AND
LANDING (ABOVE 12,000 FEET)
MODEL 208 (675 8HP)
)
CARGO POD INSTALLED
)
TIME, FUEL, AND DISTANCE TO CLIMB
{
CRUISE CLIMB
)
)
CONDITIONS :
)
Flaps Up
1900 RPM
Inertial Separator - Normal
NOTES:
)
1. Torque set at 1865 loot-pound!! or lesser value must not exceed maximum climb
In of 765°C or Ng of 101.6%.
)
2. Add 35 pounds oj,fuel for engine start, taxi, and takeoff allowance.
3. Distances shown are based.on zero wind.
4. W ith inertial separator set in BYPASS or cabin heat on, Increase time, fuel, and distance
numbers by 1% lor each 1000 feet of climb,
)
)
)
CLIMB FROM SEA lEVEL
! -
J,
)
PRESS
CLIMB
WEIGHT
['IT
SPEED
LaS
FT
KIAS
8000
12000
13000
14000
15000
120
120
120
12
13
14
16000
120
120
16
17
81
69
97
107
116
12000
13000
14000
15000
16000
120
120
120
120
120
10
73
11
eo
13
14
15
12000
13000
14000
120
120
120
9
10
15000
120
11
13
16000
120
14
)
)
)
7500
)
)
)
)
)
20 OEG C BELOW
STANDARD TEMP
TIME
OIST
FUEL
MIN
lBS
NM
7000
STANDARO
20 OEG C ABOVE
TEMPERATURE
TIME
STANOARD TEMP
TIME
FUEL
015T
MIN
LBS
NM
DI5T
MIN
FUEL
lBS
30
14
16
18
91
102
114
70
86
20
23
127
142
25
30
37
47
75
143
168
199
33
37
30
34
39
45
52
249
373
1'"
185
88
96
104
22
24
27
30
33
12
14
16
18
20
82
91
101
112
125
27
30
3S
40
46
21
25
30
37
48
122
141
164
194
244
49
58
70
87
116
6S
72
79
20
22
24
11
12
14
73
81
90
24
27
30
16
99
18
110
35
40
106
120
138
160
190
42
49
58
B6
18
22
25
30
37
94
24
27
NM
27
31
57
70
68
{-~-- ,
Figure 18. Time, Fuel, and Distance to Climb - Cruise Climb
842-31
Revision 1
For Trainin Pur oses Onl
en
~
'"
w
-
I\)
'TI
cO'
c::::
.....
CD
!:oCJ)
LANDING ·DISTANCE
O~
~N
r
SHORT FIELD
(CARGO POD INSTALLED)
I\)
0
co
CONDITIONS:
m
--..J
~
<.0
r
w
:::l
9:
"!'.l
.,
.,~
s·
s·
<0
"0
:::l
C
:::l
II'
0
Cii"
.....
Flaps 30°
Power Lever - Idle after clearing obstacles.
(lever against spring) after touchdown.
Propeller Control.Lever- MAX
Maximum Braking
Paved, Level, Dry Runway
Zero Wind
(J'1
(")
.,C
CD
'0
c
'"/I>
'"0
1. Short field technique as specified in Section 4.
0
2. Decrease distances 10% for each 11 · knots headwind.
.,
~
=
~
(fi'
c.
W
=r
CD
CD
.....
~
::D
CD
<
w
·
c:r
:::l
NOTES:------------------------------------------------------
C/J
=r
8.
~
I
~
0
l>
::D
C)
0
W
(JQ
en
Beta range
"D
0
c
Z
For operation with tailwinds up to 10
(J)
knots, increase distances by1 0% for each 2 knots.
3. For operation on a dry, grass runway, increase distances by 40% of the "ground roll" figure .
4. If a landing with flaps up is necessary, increase the approach speed by 15 KIAS and allow for
40% longer distances.
5. Use of maximum reverse thrust after touchdown reduces ground roll by approximately 10%.
. 6. Where distance values have been replaced by dashes, operating temperature limits of the
airplane would be greatly exceeded. Those distances which are included, but the operation
slightly exceeds the temperature limit, are provided for interpolation purposes only .
l>
r
r
m
0
-4
rI
»ZG)
OI
Z»
~~
»-i
alC
00
..
I
w
~ .
en
.J:>..
I\:)
I
W
.J:>..
!9
6800
75
O·C
0 0
20·C
10·C
f..J
)
)
)
)
S43-7/S43-8
9 August 2001
For Training Purposes Only
)
)
)
)
)
)
)
)
.
For Training Purposes Only
)
)
)
)
)
~
)
Cessna
~
A TeJlhon Company
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 44
)
)
)
BFGOODRICH STORMSCOPE WX-1000+/1000E
WEATHER MAPPING SYSTEM
)
)
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Cessna Model
208 (675 SHP) Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual, if the airplane is equipped with the BFGoodrich
Stormscope WX-1 000+/1 OOOE Weather Mapping System.
)
APPROVED
)
BvkAI L. ~
f.A" Wendell W. Cornell
)
f)
Member of GAMA
)
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
DATE OF APPROVAL
}~~
• •!
COPYRIGHT 0 1999
CESSNA AIRCRAFT
COMPANY
a PI!UlH4"1/I: I'If<1
2 DECEMBER 1999
WICHITA, KANSAS, USA
)
01352-544-00
)
)
)
S44-1
S44
BFGOODRICH WX-1 000+/1 OOOE
WEATHER MAPPING SYSTEM
MODEL 208 (675 SHP)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 44
BFGOODRICH STORMSCOPE WX-1000+/1000E
WEATHER MAPPING SYSTEM
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages. affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
o (Original)
Date 01 Issue
2 December 1999
LOG OF EFFECTIVE PAGES
DATE
PAGE
S44-1 thru 844-6
2 December 1999
REV. NUMBER
0
)
2 December 1999
S44-2
For Training Purposes Only
).
)
BFGOODRICH WX-1000+/1 OOOE
WEATHER MAPPING SYSTEM
S44
MODEL 208 (675 SHP)
)
SUPPLEMENT
)
f
)
BFGOODRICH STORMSCOPE WX-1000+/1000E
WEATHER MAPPING SYSTEM
)
SECTION 1
GENERAL
)
)
)
ThiS supplement provides information which must be observed
when operating the BFGoodrich Stormscope WX-1000+/1 OOOE
Weather Mapping System .
)
)
)
)
(
The Stormscope WX-1000+/1 OOOE provides information to the
flight crew about the presence of thunderstorm activity allowing the
pilot to make appropriate flight path changes . The Stormscope
maps electrical discharge activity in ranges of 360 degrees and 120
degrees around the aircraft up to a distance of 200 nautical miles.
The system is heading stabilized, allowing it to maintain proper
display orientation during turns.
)
The processor continuously provides storm data acquisition and
self-test functions regardless of . the display mode selected.
Electrical discharge data is acquired continuously, even if the
system is not in the weather mapping mode, to ensure that the data
presented to the pilot is always current.
)
)
)
)
)
)
(,:
) "c"':''':
)
The Stormscope incorporates electronic checklists. The checklists
are not pilot programmable but can be field programmed to meet
the pilot's specific requirements. Up .to six checklists with thirty
items each are available. ' The electronic clock provides current time
and date, an elapsed time counter and' a stopwatch for timed
approaches.
With the Navaid option installed and enabled, simultaneous
presentation of weather mapping data and ' navigation data is
displayed: With the Navaid Option. the MAIN MENU includes a
Navaid display selection and the OPTIONS menu includes a Navaid
Setup function. Hefer to the Stormscope Series II Weather Mapping
Systems Pilot's Handbook for further information . .
)
)
)
S44-3
2. December 1999
For Training Purposes Only
S44
MODEL 208 (675 SHP)
BFGOODRICH WX-1 000+/1 OOOE
WEATHER MAPPING SYSTEM
The WX-1000+/1000E displays weather information on a BFG WX1000+/1 OOOE/SKY497 CRT display of green symbols and text. The
display can be dedicated to the WX-1000+/1000E, or shared with a
BFGoodrich SKYWATCH SKY497 Traffic Advisory System (if in- ..
stalled). However, the display does not show traffic and storm in- (
formation simultaneously. The pOSition of a green light, push-button
type SKYWATCH/STORMSCOPE mode switch, located adjacent to
the display, determines whether the display shows traffic or storm
information. If the mode switch is in the STORMSCOPE pOSition
and the SKY497 detects traffic that may pose an immediate threat
to the aircraft, the display switches temporarily to SKYWATCH
mode.
The following functions apply to Stormscope operations:
Inhibit - Processor data acquisition is inhibited while the mic key is .
depressed. If the system is inhibited for more than one minute,
"MIC KEY STUCK" will be displayed.
Heading Stabilization Unavailable - "FLAG" will appear where
heading information is normally displayed.
See the Pilot's
Handbook for operating without heading stabilization.
(
Navaid Unavailable - "NAV FLAG" will appear below the weather
display when the receiver fails to acquire a consistent signal. See
the Pilot's Handbook for operating without heading stabilization.
NOTE
It may be useful to validate the lightning strike data
by pressing the CLEAR button and then monitoring
the reappearance of the ·thunderstorm activity on the
display.
SECTION 2
LIMITATIONS
The BFGoodrich Stormscope Series II Weather Mapping Systems ,
Pilot's Handbook PIN 75-0299-7690-1 (Rev. B 7/2/98 or later), must !,~"
be readily available to the flight crew when operating the ......
Stormscope system.
2 December 1999
S44-4
For Training Purposes Only
BFGOODRICH WX-1 000+/1 OOOE
WEATHER MAPPING SYSTEM
544
MODEL 208 (675 SHP)
Pilots must not use the Stormscope weather mapping display to attempt thunderstorm penetration.
The system is intended only to
help the pilot make better thunderstorm avoidance decisions.
1
: The electronic checklists must contain FAA approved operating
piOcedures.
It is the operator's responsibility to ensure that
checklist contents are consistent with current .Pilot's Operating
Handbook procedures.
The optional Navaid presentation is not approved as a primary or
sole means of navigation information display. Other approved
navigation information displays must be installed and operable, as
required by the FAR's applicable to the specific type of operation
(i.e. VOR , DME, etc.).
)
SECTION 3
EMERGENCY PROCEDURES
)
)
)
/'
No Change.
SECTION 4
NORMAL PROCEDURES
(
)
)
)
A CAUTION
Static discharge from the static wicks on the
wi,ng and tail may cause false indications of
lightning strikes at the 9 o'clock, 3 o'clock, and 6
o'clock positions, with the 200nm range
selected.
Refer to the Stormscope Series II Weather Mapping Systems Pilot's
Handbook.
The operating procedures are the same as those in the Pilot's
Operating Handbook except as follows :
IF ANY OF THE FOLLOWING ERROR MESSAGES "ERROR 01 CONTINUED OPERATION IS NOT POSSIBLE", "ERROR 46 -WEATHER MAPPING IS INHIBITED" OR "ERROR 44 OR 45 WEATHER MAPPING 18 INHIBITED" APPEAR ON THE
STORMSCOPE DISPLAY.
844-5
2 December 1999
)
For Training Purposes Only
S44
MODEL 208 (675 SHP)
BFGOODRICH WX-1 000+/1OOOE
WEATHER MAPPING SYSTEM
SKYWATCH/STORMSCOPE switch (if installed) - SKYWATCH.
Or
Stormscope - OFF.
SECTION 5
PERFORMANCE ·
No Change.
2 December 1999
844-6
For Training Purposes Only
)
A Textron Company
~
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 45 .
)
)
ARCTIC DIESEL FUEL ,
)
)
)
( '
..
J"........
.
SERIAL NO.
)
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna
Model 208 (675 SHP) Pilot's Operating Handbook and FAA
Approved Airplane Flight Manual when using Automotive Arctic
Diesel (Arctic Grade) Fuel.
)
)
)
)
APPROVED
)
)
)
),:/
f) ,.Member of GAMA
DATE OF APPROVAL :u, A,\I6U:'T "!l9
.
)t"".'"
.-.
)
BYdfzclc~f{+r " e
Wendell W. Comell
Executive engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
COPYRIGHT C> 1999
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
26 AUGUST 1999
D13S2-S4S·00
)
)
)
S45-1
For Training Purposes Only
S45
ARCTIC DIESEL FUEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 45
ARCTIC DIESEL FUEL
Use the Log of Effective Pages to determine the current status
of this supplement. Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
26 August 1999
)
)
. LOG OF EFFECTIVE PAGES
DATE
PAGE
545-1 thru 545-4
26 August 1999
REV. NUMBER
0
)
)
)
)
Original Issue
845·2
For Training Purposes Only
S45
ARCTIC DIESEL FUEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT
ARCTIC DIESEL FUEL
;
)
SECTION 1
)
GENERAL
)
This supplement provides information concerning use of Automotive
Arctic Diesel (ArctiC Grade) fuel in the Model 208 (675 SHP) fuel
system.
SECTION 2
LIMITATIONS
)
)
)
~"'.
FUEL.GRADE
FUEL SPECIFICATION
(PerP&WC 581244)
AUTOMOTIVE ARCTIC
DIESEL
(ARCTIC GRADE)
ASTM 0975, GRADE 1D or
VV-V-800, GRADE DF-A or
CAN/CGSB-3.6-M90, TYPE A
MINIMUM FUEL
TEMPERATURE
AND OAT FOR ALL FLIGHT
AND GROUND OPERATION
-15°C
),< ... ,: 1~ Fuel used . must contain anti-icing additiv.e in compliance with
)
MIL-I-27686 or MIL-I-85470. Refer to Section 8 of the Pilot's
Operating Handbook for allowable concentrations of additives,
and other information.
2, Minimum OAT applies to minimum OAT within last 24 hours for
ground cold soak, unless fuel temperature is checked.
)
)
)
)
y ..'
~-.:.,.
)
3. It is the operator's responsibility to insure that the fuel is free ' of
water and other liquid and solid contaminants to the same extent
as normal aviation fuels. If there is doubt, a sample of fuel as
delivered by the refueling equipment should be tested and
compared to the cleanliness standards for Jet A fuel per ASTM
D1655.
4. Other types and grades of Diesel fuel, or Arctic Diesel fuel
containing dyes, must not be used. Arctic Diesel fuel without dye
is straw colored similar to Jet A fuel.
A
CAUTION
Use of Arctic Diesel Fuel containing dyes may have
detrimental effects on the . engine fuel system and
hot section parts.
)
)
S45-3
Original Issue
For Training Purposes Only
S45
ARCTIC DIESEL FUEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
There are no changes to the airplane ' emergency procedures when :'
using Arctic Diesel Fuel.
.
)
SECTION 4
NORMAL PROCEDURES
There · are no changes to the airplane normal procedures when
using Arctic Diesel Fuel.
. SECTION 5
PERFORMANCE
There are no changes to' airplane performance when using Arctic
Diesel Fuel,
)
)
)
)
)
)
)
)
545·4
Original Issue
For Training Purposes Only
. ~
Cessna
A Textron Company
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight ManLJal
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 46
)
)
300-AMP STARTER-GENERATOR
INSTALLATION
)
)
)
I
/'
.
'.
J..
SERIAL NO.
)
REGISTRATION NO.
)
)
)
)
This supplement must be inserted into Section 9 of the Cessna
Model 208 (675 SHP) Pilot's Operating Handbook and FAA
Approved Airplane Flight Manual , if the airplane is equipped with a
300-amp starter-generator.
)
)
APPROVED
)
)
f)
Member of GAMA
)
{
) -<., -
)
Bv'd/::4"'¥: ~
Wendell W. Corneil
COPYRIGHT C> 1999
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
EK8cutlv8 Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
DATE OF APPROVAL
2.
'QEPT£MU& . " ,
2 SEPTEMBER 1999
01352-546-00
)
)
)
S46-1
For Training Purposes Only
S46
300-AMP STARTER-GENERATOR
POH SUPPLEMENT
MODEL 208 (675 8HP)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 46
)
300-AMP STARTER-GENERATOR
INSTALLATION
)
)
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are
indicated by an asterisk ,(*) preceding the page number.
Revision Level
Date of Issue
o(Original)
2 September 1999
.
)
)
LOG OF EFFECTIVE PAGES
PAGE
DATE
846-1 thru 846-4
2 September 1999
REV. NUMBER
0
)
)
Original Issue
846-2
For Training Purposes Only
300-AMP STARTER-GENERATOR
POH SUPPLEMENT
S46
MODEL 208 (675 SHP)
SUPPLEMENT
)
~:
)
300-AMP STARTER-GENERATOR
INSTALLATION
)
)
SECTION 1
)
GENERAL
)
)
)
)
)
)
,( ~
The starter~generator is mounted on the top of the accessory case
at the rear of the engine. The starter-generator is a 28 volt, 300amp engine-driven unit that functions as a motor for engine starting,
and after engine start, as a generator for the airplane electrical
system. When operating as a starter, a speed sensing switch in the
starter-generator will automatically shut down the starter, thereby
providing overspeed protection and automatic shutoff. The startergenerator is air cooled by an integral fan,and by ram air drawn
from the engine cowling.
)
)
) .
)
.
)
)
)
)
)
I
)
)(
Figure 1. VolVAmmeter
)"'c~;,.",
)
)
)
)
S46-3
Original Issue
For Training Purposes Only
546
MODEL 208 (675 SHP)
30Q-AMP STARTER-GENERATOR
POH SUPPLEMENT
.SECTION 2
LIMITATIONS
GROUND
1. Do not exceed a load of 105 amps (first triangle on the
volt/ammeter) with engine power set at Ground Idle (52% Ng
min).
2. Do not exceed a load of 170 amps (second triangle on the
volt/ammeter) with engine power set at or above Flight Idle
(64% Ng min).
FLIGHT
1. The 300-amp starter-generator is certified to produce 300
amps (red line on the volt/ammeter) up · to FL 180. Above
FL 180, the 300-amp starter-generator is limited to a load of
250 amps (third triangle on the volt/ammeter) if the airplane is ~
operating at a speed below 100 KIAS .
.
)
SECTION 3
EMERGENCY PROCEDURES
)
)
There are no changes to the airplane emergency procedures.
SECTION 4
NORMAL PROCEDURES
There are no changes to the airplane normal procedures.
)
SECTIONS
PERFORMANCE
)
There are no changes to airplane performance.
)
Original Issue
S46-4
For Training Purposes Only
)
~
)
Cessna
)
A TeJClron Com pany
j
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 47
)
)
TAKEOFF PROCEDURES FOR
EUROPEAN AIRPORTS WITH
NOISE LIMITATIONS
)
)
)
l
SERIAL NO.
" ~' '''
REGISTRATION NO.
)
)
)
This supplement must be inserted into Section 9 of the Cessna
Model 208 (675 SHP) .Pilot's Operating Handbook and FAA
Approved Airplane Flight Manual, if the airplane is operated out of
European airports that have noise limitations.
)
)
)
)
@
Member of GAMA
Wendell Corneil
Executive Engineer
Cessna Aircraft Company
Delegation Option Manufacturer CE-3
DATE OF APPROVAL
COPYRIGHT 0 2000
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA'
21 M,,1t.C." 1000
27 MARCH 2000
01352-S47·00
)
)
S47-1
For Training Purposes Only
S47
MODEL 208 (675 SHP)
TAKEOFF PROCEDURES FOR EUROPEAN
AIRPORTS WITH NOISE LIMITATIONS
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 47
TAKEOFF PROCEDURES FOR
EUROPEAN AIRPORTS WITH
NOISE LIMITATIONS
Use the Log of Effective Pages to determine the current status of
this suppl/3ment.
Pages affected by the current revision are
preceding the page number.
indicated by an asterisk
n
Revision Level
Date of Issue
o(Original) .
27 March 2000
LOG OF EFFECTIVE PAGES
)
PAGE
DATE
. S47-1 thru S47-8
27 March 2000
REV. NUMBER
o
Original Issue
547-2
For Training Purposes Only
)
)
S47
TAKEOFF PROCEDURES FOR EUROPEAN
AIRPORTS WITH NOISE LIMITATIONS
MODEL 208 (675 SHP)
)
)
)
{
. T AKEOFFPROCEDURES FOR
E·UROPEANAIRPORTS WITH
NOISE LIMITATIONS
)
)
SECTION 1
GENERAL
)
J
)
)
)
)
)
)
~~ ..
)
)
)
)
This supplement is to' be used when operating out of European
airports that have noise limitations, In order to meet the limitations
for operations out of these airports, climbout procedures are
amended. Takeoff will be accomplished as prescribed in Section 4
of the basic Pilot's Operating Handbook. After reaching an altitude
of 600 ft AGL, the propeller setting is reduced to 1750 RPM, and
maintained through 1000 feetAGL, or until clear of noise sensitive
area.
Also included in this supplement is a Performance Section
containing new figures and tables which incorporate the takeoff
procedures for operation in the designated airports with noise
limitations',
The Model 208 (675 SHP) without the cargo pod has the same, or
better, noise signature as the Model 208 (675 SHP) with the cargo
pod.
SECTION 2
LIMITATIONS
)
)
)
)
There are no changes to the airplane Limitations when these
procedures are used.
)
SECTION 3
EMERGENCY PROCEDURES
)
)/
)\~
There are no changes to the airplane Emergency Procedures when
these procedures are used.
)
)
)
)
Original Issue
S47-3
For Trainin Purposes Only
S47
MODEL 208 (675 SHP)
TAKEOFF PROCEDURES FOR EUROPEAN
AIRPORTS WITH NOISE LIMITATIONS
SECTION 4
NORMAL PROCEDURES
)
CHECKLIST PROCEDURES
)
TAKEOFF
)
NORMAL TAKEOFF
1. Wing Flaps -- 20°.
2. Power -- SET FOR TAKEOFF (observe Takeoff ITT and Ng
limits). Refer to Section 5 of the Pilot's Operating Handbook for
takeoff power.
3. Annunciators -- CHECK.
4. Rotate -- 70-75 KIAS.
5. Climb Speed -- 85-95 KIAS.
6. PROPELLER -- 1750 RPM between 600 ft AGL and 1000 ft .
AGL,or until clear of noise sensitive area.
7. Wing Flaps -- RETRACT.
)
)
)
SHORT FIELD TAKEOFF
1. Wing Flaps -- 20°.
2. Brakes -- APPLY.
3. Power -- SET FOR TAKEOFF (observe Takeoff ITT and Ng
limits). Refer to Section 5 of the Pilot's Operating Handbook for
takeoff power.
4. Annunciators -- CHECK.
5. Brakes -- RELEASE.
6. Rotate -- 70 KIAS.
7. Climb Speed -- 83 KIAS, until all obstacles are cleared. Refer
to Section 5 for speeds at reduced weights.
8. Propeller -- 1750 RPM between 600 ft AGL and 1000 ft AGL, or
until clear of noise sensitive area.
9. Wing Flaps -- RETRACT.
Original Issue
S47-4
For Training Purposes Only
)
)
547
TAKEOFF PROCEDURES FOR EUROPEAN
AIRPORTS WITH NOISE LIMITATIONS
MODEL 208 (675 SHP)
)
AMPLIFIED PROCEDURES
)
)
{
)
)
TAKEOFF
Refer to the engine torque for takeoff figure in Section 5 of the
Pilot's Operating Handbook to determine the torque corresponding
to the surface altitude and OAT conditions. This torque should be
obtainable without exceeding 805°C ITT or 101.6%' Ng.
Takeoff roll
power lever
brakes · and
torque (from
is most smoothly initiated by gradually advancing the
until propeller RPM nears 1900. Smoothly release the
continue advancing the power lever until · the takeoff
Section 5) is reached.
)
)
)
)
(
)
)
)
NOTE
As airspeed increases during takeoff, an increase in
torque at a fixed power lever position is normal and
need not be reduced, provided torque limit (1865
foot-pounds) is not exceeded.
At 600 feet AGL, reduce propeller setting to 1750 RPM. Maintain
1750 RPM and takeoff engine torque for the day through 1000 feet
AGL, or until clear of the noise sensitive area, and then retract flaps
and resume normal climb power setting.
)
SECTION 5
PERFORMANCE
)
)
)
)
)
When operating from European airports with noise limitations, the
following climb performance charts represent aircraft performance at
the reduced power setting.
)
(Continued Next Page)
(/
)
)
)
847-5
Original Issue
. For-Training Purposes Only
S47
MODEL 208 (675 SHP)
TAKEOFF PROCEDURES FOR EUROPEAN
AIRPORTS WITH NOISE LIMITATIONS
(WITHOUT CARGO POD)
RATE OF CLIMB· CUTBACK PROCEDURE
FLAPS 20°
CONDITIONS:
Takeoff Torque
1750 RPM
Inertial Separator - Normal
NOTES:
1 _ Do not exceed torque limit for takeoff per ENGINE TORQUE FOR
TAKEOFF chart. When ITT exceeds 765°C, this power setting is
time limited to 5 minutes.
2 . With inertial separator set in BYPASS or cabin heat on, and climb
power set below the torque limit, decrease rate of climb by 50 fpm for
each condition.
3. Where rate of climb values have been replaced by dashes, operating
temperature limits of the airplane would be greatly exceeded. Those
rates of climb which are included but the operation slightly exceeds
the temperature limit are provided for interpolation purposes only.
WEIGHT
lBS
8000
7500
PRESS
AlT
FT
CLIMB
SPEED
KIAS
S.L.
2000
4000
6000
8000
10,000
12,000
91
91
90
90
89
89
89
S.l.
2000
4000
8000
8000
10,000
12,000
7000
s.L.
2000
- 4000
6000
8000
10,000
12,000
)
RATE OF CUMB· FPM
-2()'C
O'C
20'C
40'C
930
910
S9()
866
896
870
846
816
840
810
915
890
870
840
810
780
776
690
976
845
S10
680
650
410
275
90
90
B9
89
BB
BB
87
1040
1020
1020
1000
1000
976
950
920
890
980
89 \
89
B8
B8
B7
87
B6
1160
1146
1126
1100
1076
1046
101S
950
925
895
800
1145
1125
1100
1075
1050
1020
920
n6
630
490
1005
980
955
-925
B05
735
690
980
920
790
650
505
1125
1105
lOBO
1050
1010
855
705
1105
1085
1045
905
760
615
465
985
366
)
)
,
\.
Figure 1. Rate of Climb - Takeoff Flap Setting
Original Issue
547-6
For Training Purposes Only
TAKEOFF PROCEDURES FOR EUROPEAN
S47
AIRPORTS WITH NOISE LIMITATIONS
MODEL 208 (675 SHP)
(CARGO POD INSTALLED)
)
r
X
)
)
)
)
)
)
)
)
)
)
>(
)
RATE OF CLIMB - CUTBACK PROCEDURE
FLAPS 20·
CONDITIONS:
Takeoff Torque
1750 RPM
Inertial Separator - Normal
Cargo Pod Installed
NOTES:
1. Do not exceed torque limit for takeoff per ENGINE TORQUE FOR
TAKEOFF chart. When lIT exceeds 765°C, this power setting Is
time limited to 5 minutes.
2. With . inertial separator set in BYPASS or cabin heat on, and climb
power set below the torque limit, decrease rate of climb by 50 fpm for
each condition.
3. Where rate of climb values have been replaced by dashes, operating
temperature limits of the airplane would be greatly exceeded. Those
rates of climb which are included but the operation slightly exceeds
the temperature limit are provided for interpolation purposes only.
WEIGHT
LBS
BOOO
)
)
)
7500
)
)
7000
)
)
FT
CLIMB
SPEED
KIAS
S.L.
2000
4000
6000
8000
10,000
12,000
PRESS
ALT
RATE OF CLIMB - FPM
-20·C
O·C
20·C
40·C
91
90
90
89
89
89
88
890
870
870
845
820
795
765
730
640
850
825
796
7e5
725
580
440
825
800
760
e30
495
s.L.
2000
4000
6000
8000
10,000
12,000
90
89
89
88
88
88
87
995
975
955
930
905
875
840
975
955
930
905
875
935
910
870
735
696
750
955
930
905
875
835
685
640
S.L
2000
4000
6000
8000
10,000
12,000
89
89
88
88
87
87
86
1115
1095
1075
1050
;025
996
960
1095
1075
1OS5
1025
995
965
870
1075
1055
1030
1000
956
800
650
1055
1030
990
850
705
845
820
795
765
730
845
_.0-
....
.---
)
)(
)tc./
)
Figure 2_ Rate of Climb - Takeoff Flaps Setting
)
)
)
547-7
Original Issue
For Trainin p"r oses Onl
S47
MODEL 208 (675 SHP)
TAKEOFF PROCEDURES FOR EUROPEAN
AIRPORTS WITH NOISE LIMITATIONS
SECTION 6
WEIGHT & BALANCE /
EQUIPMENT LIST
)
There are no changes to the airplane Weight & Balance/ Equipment
List when these procedures are used.
)
)
)
Original Issue
847-8
For Training Purposes Only
)
)
~
)
CeSSri8
A Te.lron
)
Company
{
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 48
)
)
)
BENDIX/KING FLIGHT CONTROL SYSTEM
(TYPE KFC-225)
)
)
)
{
SERIAL NO.
REGISTRATION NO;
)
)
)
)
This supplement must be ·inserted into Section 9 of the Pilot's
Operating Handbook and FAA Approved Airplane Flight Manual for
Cessna Model 208 (675 SHP) airplanes equipped with the
Bendix/King Flight Control System (Type KFC-22S) .
)
APPROVED BY
)
)
)
)
o
Member of GAMA
DATE OF APPROVAL
(p ~O"&\I\&aR.. ~6oo
)
){ -,.
. )\;~~if
)
COPYRIGHT () 2000
CESSNA .AI RCRAFT
COMPANY
WICHITA, KANSAS, USA
6 NOVEMBER 2000
o1352-S48-00
)
)
S48-1
For Trainin2 Purposes Only
548
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
MODEL 208 (675 SHP)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 48
)
BENDIX/KING FLIGHT CONTROL SYSTEM
(TYPE KFC-22S)
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
)
Revision Level
Date of Issue
)
o(Original)
6 November 2000
)
)
LOG OF EFFECTIVE PAGES
)
DATE
PAGE
S48.:.1 thru S48-12
6 November 2000
REV. NUMBER
0
Original Issue
S48-2
For Training Purposes Only
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
)
548
MODEL 208 (675 SHP)
)
BENDIX/KING FLIGHT CONTROL SYSTEM
)
)
/
(TYPE J
)
)
)
)
S48-5
Original Issue
e 0 Iv
548
MODEL 208 (675 SHP)
. BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
SECTION 3
, EMERGENCYPROCEDURES
IN CASE OF AUTOPILOTIYAW DAMPER MALFUNCTION :
NOTE
)
Accomplish Items 1 and 2 simultaneously.
1. Airplane Control Wheel -- GRASP FIRMLY and OPERATE as
)
required to manually override the autopilot.
2. NP DISCITRIM INTER Switch -- PRESS and HOLD.
3. NP DISCITRIM INTER Switch -- RELEASE while observing
pitch trim wheel. If pitch trim wheel is in motion, follow the
electric trim malfunction procedure.
IN CAS E OF ELECTRIC TRIM MALFUNCTION (Either manual
electric or autotrim):
1. AlP DISCITRIM INTER Switch --PRESS and HOLD (
,th roughout recovery.
2. SERVO Circuit Breaker -- PULL.
3. Aircraft -- RETRIM manually.
A WARNING
When disconnecting the autopilot after a trim
malfunction, hold the control wheel firmly; up to 30
pounds of force on the control wheel may be
necessary to hold the aircraft level.
.
MAXIMUM ALTITUDE LOSS DUE TO AUTOPILOT
MALFUNCTION :
Configuration
Altitude loss
Cruise, Climb, and Descent
Maneuvering
Approach
300 Ft.
150 Ft.
100 Ft.
Original Issue
848-6
For Training Purposes Only
)
)
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
)
548
MODEL 208 (675 SHP)
)
AUTOPILOTfYAW DAMPER DISENGAGEMENT (The autopilot
and/or yaw damper may be manually disengaged by any of the
following methods):
)
)
[
1 . Press the AlP DISCITRIM INTER switch on the pilot's control
wheel.
)
2.
Operate the pilot's electric trim switch UP or DOWN to
automatically disengage the autopilot only . The yaw damper
remains engaged.
3.
)
Press the APIENG button to the OFF position.
damper remains engaged.
)
4. Pull the SERVO or AlP COMP circuit breakers out.
)
5.
)
)
)
)
.
{'
)
The yaw
Turn off the AVIONICS POWER 1 switch.
YAW DAMPER (OPTIONAL) DISENGAGEMENT (The yaw damper
only may be disengaged by the following method):
1 . Press the yaw damper switch button to the OFF position.
In case of "CHECK PITCH TRIM" aural message (An out of trim
condition has existed for 16 seconds):
1. Airplane Control Wheel -- GRASP FIRMLY, press CWS, and
check for an out of pitch trim condition. Manually retrim as '
required.
)
2.
CWS Button -- RELEASE.
)
3.
AUTOPILOT OPERATION -- CONTINUE if satisfied that the
out' of trim condition was temporary.
DISCONTINUE if
evidence indicates a failure of the autotrimfunction.
)
)
)
)
)
)( :
" .~;""
)
FLASHING PT:
A flashing PT autotrim annunciation with an up or down arrowhead
in the display of the autopilot computer suggests a failure of the
, autotrim function to relieve pitch servo loading in a timely manner.
1.
FLASHING PT ANNUNCIATION -- OBSERVE aircraft pitch
behavior.
If pitch behavior is sqtisfactory, wait 5 - 10
seconds for the annunciation to stop.
)
(Continued Next Page)
)
)
)
S48-7
Original Issue
For Training Purposes Only
548
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
MODEL 208 (675 SHP)
2.
If annunciation continues, Airplane Control Wheel -~ GRASP
FIAMLY, press CWS and check for an out of' pitch trim
condition. Manually retrim as required.
3.
CWS Button -- RELEASE.
4.
AUTOPILOT OPERATION -- CONTINUE, if satisfied that the
out of trim indication was temporary. DISCONTINUE, if
evidence indicates a failure of the auto trim function.
RED "P" or "R" (A red P or R annunciation on the face of the
autopilot computer):
.
1.
A red P annunciati(;>n is an indication that the pitch axis of the
autopilot has been disabled, and the autopilot cannot be
engaged.
NOTE
If the red P lamp was the result of some abnormal
accelerations on the airplane, the annunciation should
extinguish within approximately one minute, and
normal use of the autopilot will be reestablished . This
annunciation may be present during power up.
2. A red R annunciation is an indication that the roll axis of the
autopilot has been disabled, and the autopilot · cannot be
en.gaged.
FLASHING MODE
A flashing mode annunciation on the display of the autopilot
computer, or on the remote mode annunciator, is normally an
indication of mode loss.
1.
Flashing HOG -- Indication of a failed heading input. PRESS
HOG button to terminate flashing.
2.
Flashing NAV, APR, or REV -- Usually an indication of a
flagged navigation source, or an interruption of nqvigation .
signal. The autopilot will default to ROL mode. PRESS the
NAV, APR, or REV button to terminate flashing. Select a
valid navigation source.
Original Issue
548-8
For Training Purposes Only
S48
_BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
)
MODEL 208 (675 SHP)
)
)
NOTE
)
A flashing NAV, APR, or REV annunciation can also be
caused by a failed heading, or course datum input.
f
)
3. Flashing G8 -- Indication of a flagged glideslope (or a fault in
)
the KFC-225 pressure sensor). The autopilot will default to
PIT mode. GS will rearm automatically if a valid GS signal is
received.
)
)
)
NOTE
)
To continue tracking the localizer, observe the
appropriate minimums for a non-precision approach.
(Press V8 to terminate the flashing GS and allow
vertical speed control of the pitch axis).
)
J
)
SECTION 4
)
NORMAL PROCEDURES
/'
J(
)
)
)
BEFORE TAKEOFF (Perform Steps 1 thru 8 prior to each flight)
1 . Gyros -- Allow 3-4 minutes for gyros to come up to speed.
2. AVIONICS POWER 1 Switch -- ON.
3. PREFLIGHT TEST -- Performed automatically on power up.
)
NOTE
)
I
If TRIM warning light stays on, the autotrim did not
pass the preflight test. The autopilot circuit breaker
should be pulled. The autopilot and manual electric
trim will be inoperative.
)
)
)
)
)
~(,;j~
4.
Manual Electric Trim -- TEST as follows:
a. Actuate left side of split switch unit to the fore and aft
positions. The trim wheel should not move on its own.
Rotate the trim wheel manually against the engaged
clutch to check the pilot's trim overpower capability.
)
(Continued Next Page)
)
)
)
Original Issue
848-9
'n
r os s Onl
548
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
MODEL 208 (675 SHP)
5.
b.
Actuate right side of split switch unit to the fore and aft
positions. The trim wheel should not move on its own
and normal trim wheel force is required to move it
manually.
c.
Press the AlP DISCfTRIM INTER switch down and hold.
Manual electric trim should not operate either nose up or
nose down.
'
Autopilot -- ENGAGE by pressing the AP button.
The
optional yaw damper will alsoengage.
Flight Controls-- MOVE fore, aft, left, and right to verify that
the autopilot/yaw damper can be overpowered.
AlP DISCITRIM INTER Switch -- PRESS. Verify that the
autopilot and yaw damper (optional) disconnects and all flight
director modes are canceled.
TRIM -- SET to takeoff position.
6.
7.
8.
AUTOPI LOT OPERATION
A
CAUTION
Retract and extend flaps In Increments of 10° In
order 10 minimize altitude deviations during
config uratio" changes.
BEFORE TAKEOFF:
1.
AlP DISCITRIM INTER Switch -- PRESS to disengage AP.
2.
Refer to the Bendix/King KFC-22S Pilot's Guide, part number
006-18035-0000, dated April 1999, or later version, for
autopilot operation .
CLIMB
A
CAUTION
When operating at or near the best rate of climb
airspeed, and using vertical speed hold (VS), avoid
slowing to an airspeed on the back side. of the power
curve where a decrease in airspeed results ina
reduced rate of climb. Continued opera.ion on the
back side of the power curve In VS mode may result
In a stall.
848-10
Original Issue
For Training Purposes Only
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
S48
MODEL 208 (675 SHP)
)
MISSED APPROACH:
)
)
1.
i
2. Missed Approach -- EXECUTE.
AlP DISCITRIM INTERSwitch -- PRESS to disengage AP.
3. GA Button -- PRESS as desired to activate FD. mode during
)
4.
)
go-around maneuver.
AP ENG button -- PRESS (if AP operation is desired). Note
AP annunciators ON.
)
.A
)
CAUTION
When operating at or near the best rate of climb
airspeed, and using vertical speed hold .(VS), avoid
slowing to an airspeed on the back side of the
power curve where a decrease In airspeed results
in a reduced rate of climb. Continued operation on
the back side of the power curve in VS mode may
. result in a stall.
)
)
)
)
If AP is used during missed approach:
)
/
) 1\.
5. Altitude Select -- SELECT missed approach altitude, and
verify that ALT ARM is illuminated.
)
NOTE
)
If it is desired to track the ILS course outbound as part
of the missed approach procedure, use the NAV mode
to prevent inadvertent GS coupling.
)
)
BEFORE LANDING:
)
1. AlP DISCITRIM INTER Switch -- PRESS to disengage AP
)
and yaw damper (optional) .
)
FLIGHT DIRECTOR OPERATION
)
NOTE
)
)(
)
)
)
)
.. ;
' .'.
The flight director modes of operation are the same as
those used for a'utopilot operations, except the
autopilot is not engaged, and the pilot must maneuver
the airplane to satisfy the flight director commands.
S48-11
Original Issue
For Traininl!. PurDoses Only
S48
MODEL 208 (675 SHP)
BENDIX/KING FLIGHT CONTROL
SYSTEM (TYPE KFC-225)
SECTION 5
PERFORMANCE
There is no change to the airplane performance data when this
avionics equipment is installed.
)
)
)
)
)
)
)
Original Issue
848-12
For Training Purposes Only
)
)
. ~
)
A Textron Company
Cassna
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 50
)
)
BENDIX/KING KLN 94
GPS NAVIGATION SYSTEM
)
)
)
SERIAL NO.
REGISTRATION NO.
)
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual. if the airplane is equipped with the Bendix/King KLN 94 GPS
Navigation System.
)
APPROVED BY
)
_ _ _ _I 1 . _ J
)
)
)
)
)l;
)
)
o
Member of GAMA
""'~-=";_CI!
>J-,~-....
DATE OF APPROVAL
e JANIJAA'C
COPYRIGHT c 2001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
01352-550-01
~oo,
8 JANUARY 2001
REVISION 1 -16 DECEMBER2002
)
850-1
)
)
For Trainin Pur oses Only
550
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT
)
BENDIX/KING KLN 94
GPS NAVIGATION SYSTEM
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
Revision Level
Date of Issue
o (Original)
8 January 2001
16.December 2002
1 (Revision 1)
)
LOG OF EFFECTIVE PAGES
PAGE
DATE
* 550-1 thru 850-2
550-3 thru 850-11
* 550-12
REV. NUMBER
-16 December 2002
8 January 2001
16 December 2002
1
o
)
)
1
APPROVED BY
f.ltAAPNOYID utaR FAA It -..wrr J
-.c::.,=~
:4--~
)
__
)
DATE OF APPROVAL/("
'DliC~"
)
.400.L
)
)
)
)
)
)
850-2
16 December 2002
For Training Purposes Only
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
S50
MODEL 208 (675 SHP)
. SUPPLEMENT
)
)
{.
BENDIX/KING KLN 94
GPS NAVIGATION SYSTEM
)
SECTION 1
GENERAL
GPS (Global Positioning System) is a three-dimensional (3-D)
precise location and navigation system based on a constellation of
24 satellites orbiting the earth. Receiver Autonomous Integrity
Monitoring (RAIM) is a function that every IFR-certified GPS receiver
must continuously perform to assure an accurate position. The high
order of accuracy that is obtained from RAIM availability requires 5
or more satellites in view, or 4 satellites in view and a press'ure
altitude input from the airplane's altimeter. If there are not enough
satellites in view to ensure the position integrity, the KLN 94 GPS
navigation system notifies the pilot.
,\
)
)
)
) .
r
)\
The Bendix/King KLN 94 GPS Navigation System consists of a
panel-mounted control display unit, an externally mounted flat GPS
antenna on the top forward portion of the fuselage and GPS
annunciator/switches mounted below the HSI.
The left
annunciator/switch consists of a pushbutton switch labeled GPS
APPROACH, which incorporates a two-segment annunciator labeled
ARM and ACTV. The center annunciator consists of a threesegment annunciator labeled GPS WAYPOINT, MSG and ALT (GPS
WAYPOINT and GPS MESSAGE when the ALT annunciator is not
installed). The right annunciator/switch consists ofa pushbutton
switch incorporating a two-segment annunciator labeled HSI NAV 1
and HSI GPS. This pushbutton switch has a press-to-cycle feature
that controls whether NAV 1 or GPS information is being displayed
on the HSI. The NAV 1 or GPS annunciator illuminates to indicate
which position has been selected.
)
)
)
)
)
)
)(
~~:" ..'
)
)
)
.
·When the HSI GPS annunciator switch is illuminated, Course
Deviation, To/From and Flag information from the KLN 94 GPS is
displayed on the HSI. The HSI, while in the enroute mode,
indicates linear distance and has three sensitivity scale settings: ±5
nautical mile (factory default), ±1.0 nautical mile and ±0.3 nautical
mile, full scale deflection. When transitioning to the approach ARM
8 January 2001
)
S50-3
For Trainin Pur oses Onl
S50
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
MODEL 208 (675 SHP)
mode, the HSI scale factor changes to ±1.0 NM
deflection) over 30 seconds and the ARM annunciator
When transitioning to the approach active mode, the
factor changes to ±0.3 NM (full scale deflection) and
annunciator illuminates.
(full scale
illuminates.
HSI scale
the AeTV.
)
When the autopilot is in the NAV mode, it will couple to NAV 1,
VOR/ILS or KLN 94 GPS, depending on the state of the NAVlGPS
switch.
A single 5-amp circuit breaker labeled GPS/LORAN on the bottom
row breaker panel powers the KLN94 Navigation System.
Operation of the KLN 94 GPS Navigation System shall be in
accordance with the Bendix/King KLN 94 Pilot's Guide (supplied
with the airplane). The Pilot's Guide should be thoroughly studied
and VFR operations conducted prior to .using this equipment in IFR
conditions.
A NavData Card with a current database is supplied with the KLN
94 GPS. Since this database information is updated every 28 days,
it is important to monitor the database expiration date. ' Once the
database has expired, the ' GPS system provides an advisory .
message that must be acknowledged by the operator. Although the
system will continue to operate normally, the warning message will
be repeated on each power-up to remind the user that the database
is out of date . . To eliminate this warning the database must be
updated.
A
CAUTION
The database must be updated only while the aircraft
Is on the ground. The KLN 94 does not perform any
navigation function while the database Is being
updated . .
NOTE
A current database is required by regulation to use the
KLN 94 GPS system for nonprecision approaches.
8 January 2001
S50-4
For Training Purposes Only
)
)
550
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
MODEL 208 (675 SHP)
7
4
)
/
/
)
GPS
APPROACH
)
)
1
/
ARM
)
)
)
2
HSI
NAV 1
GPS
WAVPOINT
ACTV
HSI
GPS
ALT
MSG
/ / / /
3
5
/
8
6
)
WITH ALTITUDE (ALT) ANNUNCIATOR LIGHT INSTALLED
)
",
;
)
GPS
APPROACH
GPS
WAYPOINT
I ARM IIACTV I
GPS
MESSAGE
HSI
NAV 1
I
)
)
I
HSI
GPS
I
I
/
)
*5
)
)
* WITHOUT ALTITUDE (ALT) ANNUNCIATOR LIGHT INSTALLED
)
)(
)
' ..
~.
\.""",','
2685T1040
2685T1041
)
)
)
)
Figure 1. . GPS Annunciator/Switch (Sheet 1 of 4)
8 January 2001
S50-5
For Trainin~ Purposes Onl
550
MODEL 208 (675 SHP)
1.
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
GPS APPROACH SWITCH/ANNUNCIATOR - Used to
manually select or deselect approach ARM (or deselect
approach ACTV). The remote switch annunciator also
annunciates the stage of approach operation; either armeq
(ARM) or activated (ACTV). Sequential button pushes if in
ACTV would first result in approach ARM and then approach
ARM cancelled.
Subsequent button pushes will cycle
between the armed state (if an approach is in the flight plan)
and approach ARM cancelled. Approach ACTV cannot be
selected manually.
Illumination of the GPS APPROACH annunciator is
controUed through the annunciator panel , Day/Night switch
and is only illuminated when the switch is in the night
position.
The , white background color of the GPS
APPROACH annunciator makes it visible in daylight.
2.
ARM ANNUNCIATOR LIGHT - ARM annunciator will
illuminate when the KLN 94 GPS system automatically
selects the approach ARM mode or when the approach
ARM mode is manually selected. The approach ARM mode
will be automatically selected when the airplane is within 30;'
NM of an airport and an approach ,is loaded in the flight plan~
for that airport. The approach ARM mode can maryually be .
selected at a greater distance than 30 NM from the airport
by pressing the GPS APPROACH switch; however, this will
not change the COl scale until ,the airplane reaches the 30
NM point.
3. ACTIVE (ACTV) ANNUNCIATOR LIGHT - ACTV annunciator
illuminates when the KLN 94 GPS system automatically
engages the approach 'ACTV mode (the ACTV mode can
only be engaged by theKLN 94). To cancel the approach
ACTV mode, press the GPS APPROACH switch, this will
change the mode to the approach ARM mode and illuminate
the ARM annunciator.
Figure 1. GPS Annunciator/Switch (Sheet 2 of 4)
8 January 2001
S50-6
For Training Purposes Only
)
S50
BENDIXlKINGKLN 94 GPS
POH SUPPLEMENT
)
MODEL 208 (675 SHP)
)
)
4.
GPS WAYPOINT ANNUNCIATOR LIGHT
GPS
WAYPOINT annunciator will begin to flash approximately
36 seconds prior to reaching a-Direct To waypoint. Also,
when turn anticipation is enabled in the KLN 94 GPS unit,
the annunciator will begin to flash 20 seconds prior to the
beginning of turn anticipation, then illuminate steady at the
very beginning of turn anticipation.
5.
GPS MESSAGE-ANNUNCIATOR LIGHT· GPS MESSAGE
(MSG when the ALT annunciator is .installed) will begin
flashing whenever the message prompt (a large "M" on the
right side of the screen) on the KLN 94 GPS unit begins
flashing to alert the pilot that a message is waiting. Press
the Message (MSG) key to display the message. If a
message condition exists which requires a specific action
by the pilot, the mes-sage annunciator will remain on but
will not flash.
6.
ALTITUDE (ALT) ANNUNCIATOR LIGHT· If installed, the
ALT annunciator illuminates simultaneously with an aural
alarm, which is connected to the audio panel so the alarm
is heard through the airplane speakers or headphones, and
activates:
)
/
1,
\
)
)
)
)
)
)
)
)
l"
\
)
)
)
a.
1000 feet prior to reaching the selected altitude •• three
short tones, ALT annunciator Illuminates with tones.
b. Upon reaching the selected altitude •• two short tones,
ALT annunciator illuminates with tones.
)
)
c. Deviating above or below the selected altitude by more
than the warn altitude .- four short
annunciator illuminates with tones.
A
)
tones,
ALT
CAUTION
The altitude alerting feature will only be accurate
If the altimeter baro correction Is kept updated.
If altitude alerting Is used, It is a good Idea to
update the altimeter baro set on the ALT 1 page
each time you make a change to the airplane's
altimeter setting.
Figure 1. GPS Annunciator/Switch (Sheet 3 of 4)
)
S50-7
8 January 2001
For Training Purposes Only
S50
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
There may be some difference (less than 100 feet)
between the indicated altitude and the airplane's
actual altitude if the altitude input to the KLN 94 is
from an altitude encoder, because these encoders
only provide altitude in 100-foot increments.
7. HSI NAV 1 ANNUNCIATOR/SWITCH - HSI NAV 1
annunciator will illuminate to inform the pilot that NAV 1
information is · being displayed on the HSI. Pressing this
switch will toggle between NAV 1 and GPS as the displayed
navigation source.
8. HSI GPS ANNUNCIATOR/SWITCH - HSI GPS annunciator
will illuminate to inform the pilot that GPS information is
being displayed on the HSI. . Pressing this switch will toggle
between NAV 1 and GPS as the displayed navigation
source.
Figure 1. GPS Annunciator/Switch (Sheet 4 of 4)
SECTION 2
LIMITATIONS
NAVIGATION OPERATIONAL APPROVALS
The Bendix/King KLN 94 GPS Navigation System is approved
under TSO C 129 Aland meets the requirements for the following
operations:
1. Enroute and Terminal - In accordance with AC20-138A
including BRNAV/RNP5 in accordance with AC90-96 and
JAA AMJ 20X2, provided it is receiving usable navigation
information from the internal GPS receiver (meets
requirements of AC90-94).
(Continued Next Page)
8 January 2001
550-8
For Training Purposes Only
)
)
.
BENDIX/KING KLN 94 GPS .
POH SUPPLEMENT
S50
MODEL 208 (675 SHP)
)
f
)
)
)
2. Non-Precision Approach - In accordance with AC20-138A
and AC90~94 provided the GPS is receiving usable
navigation information. The KLN 94 has been demonstrated
to meet the accuracy specifications for non-precision GPS
approach operations within the U.S. National Airspace
System. The advisory VNAV function does not meet the
requirements for approach VNAV.
OPERATING LIMITATIONS
)
)
)
)
)
1. The Bendix/King KLN 94 GPS · Navigation System Pilot's
Guide, part number 006·18207~0000, dated September
2000 (or later revision), as applicable to the specific software
modification status, must be Immediately available to the
pilot whenever navigation is predicated on use of the GPS
system. The Operational Revision Status (ORS) of the
Pilot's Guide must match the ORS level annunciated on the
Self Test page.
2. Navigation is prohibited within 60 n.m. of the north and
south poles (Le, greater than 89° north and south latitudes),
)
)
3. IFR operations are limited as follows:
a. The Bendix/King KLN 94 GPS Navigation System must
utilize Operational Revision Status (ORS) level 01 or
later FAA approved revision.
)
)
b. The data on the self-test page must be verified prior to
use.
)
)
)
)
)( - :;
)~:,)'
c.
IFR en route and terminal navigation is prohibited unless
the pilot verifies the currency of the database or verifies
each selected waypoint for accuracy by reference to
current approved data.
d. The airplane must have other . approved navigation
equipment installed and operating appropriate to the
route of flight.
)
S50-9
8 January 2001
'nin Pur oses Onl
550
MODEL 208 (675 SHP)
4.
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
Instrument approach limitations:
a. The Bendix/King KLN 94 GPS Navigation System Quick
Reference, Part Number 006-18228"-0000, Rev. 1 dated
August 2000 (or later revision), must be immediately
available to the pilot during instrument approach
operations ..
b. Instrument
approaches must be accomplished in
accordance
with approved
instrument , approach
procedures that are retrieved from the GPS equipment
database.,
The GPS equipment database must
incorporate the current update cycle.
c. APR ACTV mode must be annunciated at the Final
Approach Fix;
d. When an alternate airport is required by the applicable
operating rules, it must be served by an approach based
on other than GPS, the airplane must have operational
equipment capable of using that navigation aid, and the
required navigation aid must be operational.
e.
f.
The KLN 94 GPS Navigation System can onlybe used
for approach guidance if the reference coordinate datum
system for the instrument approach is WGS-84 or NAD83 (all approaches in the KLN 94 database use the
WGS-84 or the NAO-83 geodetic datums).
.
)
The Bendix/King KLN 94 GPS Navigation System is not
approved for the following approaches: ILS, LOC, LOCBC, ' LOA, SDF, and MLS.
These are approaches
contained within the KLN 94 database only to provide
greater situational awareness when conducting these
procedures with approved sensors.
5. For BRNAV operations in the European region:
a. With 23 (24 if the altitude input to the ' KLN 94 is not
available) or more satellites projected to be operational .
for the flight, the aircraft can depart without further
action.
I,
(Continued on Next Page)
8 January 2001
S50-10
For Training Purposes Only
"
.
S50
BENDlXlKINGKLN 94 GPS
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
b. With 22 (23 if the altitude input to the KLN 94 . is not
available) or fewer satellites projected to be operational for
the flight, (the availability of the GPSintegrity (RAIM) should
be confirmed for the intended flight (route and time). This
should be obtained from a prediction program run outside
the aircraft. The prediction program must comply with the
criteria of Appendix 1 of AC90-96. In the event of a
predicted continuous loss of RAIM of more than 5 minutes
for any part of the intended flight, the flight should be
delayed, cancelled, or rerouted on a track where RAIM
requirements can be met.
)
)
(
)
)
)
)
SECTION 3
)
EMERGENCY PROCEDURES
If information from the KLN 94 GP5 Navigation System is
intermittent or lost, utilize remaining . operational navigation
equipment as required.
Refer to the KLN 94 Pilot's Guide, Appendices Band C, for
appropriate pilot actions to be accomplished in response to
annunciated messages.
SECTION 4
NORMAL 'PROCEDURES
)
The Bendix/King KLN 94 GPS Navigation System shall be operated
per the Pilot's Guide, 006-18207-0000, dated September 2000 (or
later revision) supplied with the airplane.
)
NOTE
)
)( "
.
)' ,;.i'/
The KAP-150 Autopilot, KFC-150 ' or KFC-250 Flight
Control Systems will remain coupled to the selected
NAV regardless of whether the NAV information is valid
or not (flagged). This also applies to GPS operation. It
is the responsibility of the pilot to assure that the NAV
information is valid.
)
(Continued Next Page
)
)
550-11
8 January 2001
For Training Purposes Only
550
BENDIX/KING KLN 94 GPS
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
•
The KFC-225 Automatic Flight Control System will
revert to ROt Mode if NAV information is lost, or
becomes invalid (flagged).
•
The autopilot and flight control systems receive
navigation information from the HSI.
•
Airplanes equipped with KLN 94 part number 0690134-0102 (displayed in the AUX pages) will have a
roll steering input to the KFC 225 Autopilot. With
this system, the autopilot does · not require
adjustments to the course needle after making leg
changes. However, it is recommended that the
course needle be changed to the correct value to
enhance the pilot's situational awareness.
•
When operating with the autopilot or flight control
systems coupled and the KLN 94 GPS navigating in
the LEG mode (default mode when the KLN 94
starts up) the course to the active waypoint is
selected by the GPS navigation system, which is
also displayed on the HSI. The CBS setting should
be updated occasionally to agree with the desired
track (Dtk). While navigating in the OBS mode with
the autopilot or flight control systems coupled, the
pilot selects the course "to" or "from" the active
waypoint on the HSI. This course is then displayed
on the GPS.
)
)
)
SECTION 5
PE~FORMANCE
There is no change to the airp'lane performance when this avionics
equipment is installed.
However, installation of an externallymounted antenna or related external antennas, will result in a minor
reduction in cruise performance.
Revision 1
IS50-12
For Training Purposes Only
)
)
)
~
)
Cessna
)
A TeMlron Company
(
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual .
)
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 51
)
)
AIRPLANES CERTIFIED TO CHINA
AAD-CAAC CONFIGURATION
)
)
)
)
SERIAL NO.
I,
REGISTRATION NO.
)
this supplement must be inserted into Section 9 of the Cessna 208 (675
SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane has been modified by Cessna Drawing 2601449, and
conforms to China AAD-CAAG certification requirements. This supplement
is approved by the FAA on behalf of the China AAD-CAAC.
)
)
)
)
APPROVED BY
)
FAAAPPRovtOUHDERFM21 $U8PART J
lhec..w~Co
O. . . . . _
_ IJOA.2JOO'a.cE
)
~"'~ ex-ME'g""
)
)
DATE OF APPROVAL
2. F e.Sl\IJ"'R,( ::too I
)
)(
)
)
",.,;..;..
,
COPYRIGHT 0 2001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
o
Member of GAMA
2 FEBRUARY 2001
.01352-S51-00
)
S51-1
)
For Training Purposes OQly
S51
CHINA AAD-CAAC CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT
AIRPLANES CERTIFIED TO CHINA
AAO-CAAC CONFIGURATION
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by ,the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
2 February 2001
)
)
)
)
LOG OF EFFECTIVE PAGES
PAGE
DATE
S51-1 thru S51-8
2 February 2001
REV. NUMBER
o
)
)
)
)
)
)
)
S51-2
2 February 2001
For Training Purposes Only
CHINA AAD-CAAC CONFIGURATION
POH SUPPLEMENT
)
S51
MODEL 208 (675 SHP)
SUPPLEMENT
)
(
AIRPLANES CERTIFIED TO CHINA
AAD-CAAC CONFIGURATION
SECTION 1
GENERAL
INTRODUCTION
This supplement, written especially for operators of airplanes
conforming to China AAD - CAAC requirements, provides
information not found ·in the basic Pilot's Operating Handbook/FAA
Approved Airplane Flight Manual. It contains additional information
specifically required for operation of Model 208 airplanes equipped
and certified in accordance with China AAD - CAAC requirements.
Information contained in the basic handbook is generally not
repeated in this supplement, and the basic handbook should be
used for that information.
EMERGENCY EXITS
On airplanes conforming to China AAD - CAAC requirements, the
cargo door has been identified as an emergency exit by the addition
of a lighted EXIT sign inside the cabin and a placard and an arrow
on the outside of the door. Reterto Figure 3-1 for illustrated
emergency exit procedures.
)
)
EMERGENCY EXIT '-IGHT
Alighted EXIT sign located above the cargo door inside the cabin
provides a visual means to quickly locate and use the door as an
emergency exit when the airplane is on the ground. The NAV/EXIT
switch on the instrument panel controls illumination of the light.
[
)~_)
) . -"
)
Normal and emergency power for exit sign lighting is provided
through the clock circuit which will illuminate the interior exit light
anytime the NAV/EXIT switch is in the ON position, regardless of
the position of the battery switch.
)
)
)
851-3
2 February 2001
For Training Purposes Only
551
MODEL 208 (675 SHP)
CHINA AAD-CAAC CONFIGURATION
POH SUPPLEMENT
EMERGENCY EXIT MARKINGS
The cargo door is identified as an emergency exit on the outside of
the door by a placard and an arrow. On the inside of the cabin, the
cargo door is marked with a lighted EXIT sign.
)
)
, SECTION 2
LIMITATIONS
)
There is no change to the airplane limitations for airplanes equipped
and certified in accordance with China AAD - CAAC requirements.
Limitations in Section 2 of the basic handbook shall be observed.
PLACARDS
Placards in the passenger area of the cabin and near the exterior
door handle of the passenger entry door on the right side of the
airplane aft of the wing are bilingual (English/Chinese) placards.
Other placards on the airplane are shown in English only.
SECTION 3
EMERGENCY PROCEDURES
There is no change to the airplane emergency procedures for
airplanes equipped and certified in accordance with China AAD CAAC requirements, other than the designation of the cargo door as
an emergency exit. Use of the crew entry doors, the passenger
entry door, and the cargo door (emergency exit) for emergency
ground egress is illustrated in Figure 3-1.
)
)
2 February 2001
851-4
For Training Purposes Only
)
)
)
551
CHINA AAD-CAAC CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
)
A17957
)
(
////'/////////"
)
~
~
,
WARNING .
~
WHEN EXITING AIRPLANE ;'
AVOID PROPELLER
~
////'//////////
)
4~~-l
)
)
EXIT
)
fA}
CREW
DOOR
EMERGENCY eXIT
(CARGO DOOR)
)
CJ/"~ ULlJ~
,
EXIT
~
PUSH UPPER
ODOR OUT
.
.
.
.
Il~
'~,~
•
.::JJI
Q
RDlInE COUNTERCLOCKWISE
--
1
-
~"
TO OPEN POSITION
ODOR
~~
O.~.' ~
/;U LL H4NO LE IN AND
CREW
~ ~
)
)
EXIT
~
CARGO
~ \
~. ._
, i
(
-.
.
,"U
"M","""
TO OPEN POSITION
RDTATECLDCKWISE
,.
O~N
;;;.,
2'-"" ,,_ ~..,.
]]1
• • •_
'"""
~
'I ",'"
Ii',
~
PUSH UPI'ER
~OOR OUT
"~
...-.:::=:- 3
\
E. R~~
"
_
ODOR
HANDLE
lIFTUFlOW
.
TO O'EH
)
)
)
)
. OPEN
.-'/i;:({l
"yg/
~
._--C=:;_-4~
•
.
,
#'
)
~
.
PUSH DOOR OUTWARD .
'\ STEP THROUGH OPENING
WHilE HOLDING ODOR IN
OPEN PosmON AND
EXIT AIRPLANE
'-
(~~;'"
NOlE
S~ATI"'G C~NFICURATION
MAY NOT
AGREE WlfH 'fOUR AIRPLANE
26851037
)
)
Figure 3-1. Emergency Exit
)
)
851-5
2 February 2001
For Training Purposes Only
S51
MODEL 208 (675 SHP)
CHINAAAD-CAAC CONFIGURATION
POH SUPPLEMENT
SECTION 4
NORMAL PROCEDURES
There is no change to the airplane normal procedures for airplanes
equipped and certified in accordance with China AAD - CAAC
requirements.
.
Since the airplane can be used for both passenger and cargo
missions, and loaded in a variety of loading configurations,
precautions must be taken during loading to ensure the airplane
does not exceed its maximum weight limits and is loaded within the
center of gravity range before takeoff. The pilot is responsible for
conducting a careful preflight check and weight and balance
calculatiOn for each loading configuration.
In addition to the maximum weight and center of gravity
considerations required during the loading of baggage and cargo,
the pilot should ensure that loadings are accomplished with heavy
items on the bottom .and the loads are distributed uniformly. A
sample loading of items of various weights is illustrated in
Figure 4-1.
2 February 2001
S51-6
For Training Purposes Only
551
CHINA AAD-CAAC CONFIGURATION
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
)
l
)
110 LBS
I 10 LBS
I~
150 lBS 1150 lBS II ::: I
BB
100 LBS
20LBS
100 LBS
50 LBS
CARGO LOADED WITH HEAVIEST ITEMS ON THE
BOTTOM AND LOADS DISTRIBUTED UNIFORMLY
)
l
)
NOTE
)
Loading information in Section 6 of the basic handbook should
be consulted for other considerations regarding the carriage of
cargo. These include the weight and C.G. effects of seat
removal, use of a cargo barrier, selection 01 tiedown
equipment, use of cargo partition nets, maximum loads in
specific cargo zones, center 01 gravity precautions, prevention
of cargo movement, the loading of piercing or penetrating
items of cargo, and the transportation of hazardous materials.
)
)
)
)
Figure
)
4~ 1.
Cargo Weight Considerations
)
)(
)
. '
'''''
)
)
)
)
S51-7
2 February 2001
F01' Training Purposes Only
551
CHINA AAD-CAAC CONFIGURATION
MODEL 208 (675 SHP)
POH SUPPLEMENT
SECTION 5
PERFORMANCE
There is no change to the airplane performance for airplanes
equipped and certified in accordance with China AAD -CAAC
~
requirements.
)
)
)
)
)
)
)
2 February 2001
S51-8
For Training Purposes Only
)
)
~
)
)
CeSSna
;:
A Tel'lron Company
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 52
) .
)
)
)
l
.
ARTEX406
THREE FREQUENCY
EMERGENCY LOCATOR TRANSMITTER (ELT) .
A
SERIAL NO.
)
REGISTRATION NO.
)
)
)
)
)
This supplement must be inserted into Section 9 of the Pilot's Operating
Handbook and FAA Approved Airplane Flight Manual for Cessna Model 208
(675 SHP) airplanes which have the Artex 406 Three Frequency
Emergency Locator Transmitter . (EL T) installed.
APPAOVEDBY
)
)
)
)
/\L/:
)
.f)
COPYRIGHT () 2001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS , USA
Member of GAMA
30 MARCH 2001
01352-S52-00
)
)
852-1
)
)
For Training Purposes Only
552
MODEL 208 (675 SHP)
ARTEX 406 THREE FREQUENCY ELT
POH SUPPLEMENT
SUPPLEMENT 52
ARTEX 406
THREE FREQUENCY
EMERGENCY LOCATOR TRANSMITIER (ELT)
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
30 March 2001
)
LOG OF EFFECTIVE PAGES
PAGE
S52-1 thru S52-6
DATE
30 March 2001
REVISION NO.
o
)
)
)
S52-2
30 March 2001
)
)
For Training Purposes Only
ARTEX 406 THREE FREQUENCY ELT
POH SUPPLEMENT
·S52
MODEL 208 (675 SHP)
SUPPLEMENT 52
)
ARTEX406
(
THREE FREQUENCY
EMERGENCY lOCATOR TRANSMITIER (ElT)
)
SECTION 1
GENERAL
The Artex 406 Three Frequency Emergency Locator Transmitter
(ELT) is located under the floor near the passenger entry door of the
Cessna Model 208. A remote, two-position switch is provided on
the copilot's instrument panel and is labeled "ON" and "ARMED".
The ELT has two activation monitors to warn the pilot if the ELT is
inadvertently activated. The aural monitor provides a distinct signal
that is easily heard by the pilot or a search and rescue effort. The
visual monitor flashes an annunciator directly above the remote ELT
switch to inform the pilot that the ELT has been activated.
)
)
)
)
(
)\~ .. .
)
)
)
)
)
)
>
)
>
>( ..:
)" ..:.~"
The Artex 406 ELT automatically activates during a crash and
transmits the standard swept tone on 121 .5 MHz and 243.0 MHz.
Every 50 seconds, the 406.025 MHz transmitter turns on and
tn;lnsmits a short burst of information for approximately a half a
second. During that time an encoded digital message is sent to a
s.atellite. The information in that message will be the Aircraft 10,
country code, 10 code and position coordinates (if available) . The
406.025 MHz transmitter will operate for 24 hours and then shut
down automatically. The 121.5 MHz and 243.0 MHz transmitter will
continue to .operate until the unit has exhausted the battery power
which typically will be ' at least 72 hours. This will enable search
and rescue operations to be launched immediately and usually to
within 1 to 2 kilometers accuracy.
If position coordinates are
available through a GPS NAV source, the search and rescue
accuracy improves to within 100 meters of the transmitter location.
'
)
)
)
852-3
30 March 2001
For Training Purposes Only
552
MODEL 208 (675 SHP)
ARTEX 406 THREE FREQUENCY ELT
POH SUPPLEMENT
SECTION 2
LIMITATIONS
There are no additional limitations when the Artex 406 Three
Frequency ELT is installed in the aircraft. Refer to the current
FAR/AIM regulations concerning the testing and servicing of an
Emergency Locator Transmitter.
)
SECTION 3
EMERGENCY PROCEDURES
Shortly before performing a forced landing, especially in remote or
mountainous terrain, consider activating the. ELT transmitter by
positioning the remote switch to the "ON" position.
The .
annunciator just above the switch should flash and the aural monitor
should sound.
After a landing where search and rescue assistance is required, use
the ELT as follOws:
1. ENSURE ELT ACTIVATION:
a.
Position remote switch to "ON" if the annunciator is not
already flashing.
b. Listen for aural buzzer; and/or, if aircraft radio is operable
and can be safely used (no threat of fire or explosion), turn
ON and select 121.5 MHz. The ELT swept tone should be
audible if working correctly.
)
)
c.
Turn the aircraft radio off to conserve the battery.
d. Ensure antenna (on top of fuselage above passenger entry
door) is clear of obstructions.
NOTE
)
The ELT is designed to withstand most crash situations;
however, the ELT remote switch and/or aircraft radios
could be inoperative if damaged during landing,
30 March 2001
S52·4
For Training Purposes Only
)
552
ARTEX 406 THREE FREQUENCY ELT
POH SUPPLEMENT
MODEL 208 (675 SHP)
2. FOLLOWING RESCUE:
)
)
r'
)(
)
)
)
)
)
)
Reset remote switch to the "ARM" position to terminate
emergency transmissions. If remote switch is inoperative,
gain access to the ELT under the floor by the passenger door
and turn the switch to the "OFF" position.
Following a lightning strike, or an exceptionally hard landing, the
ELT may activate although no emergency exists. If the annunciator
just above the remote ELT switch is flashing and the aural monitor
is audible, the ELT has activated itself. Another way to confirm that
the ELT has activated is to select 121.5 MHz on the aircraft radio
and' listen for the emergency tone. Press the remote switch to
"ON" momentarily and then back to "ARM" to cease the
transmissions.
)
SECTION 4
)
NORMAL PROCEDURES
)
l
)
)
)
)
).
)
The Artex 406 Three Frequency
accordance with 14CFR Part 91.207.
ELT must be serviced in
INSPECTIONITEST (First 5 minutes at the top of the hour)
1. The emergency locator transmitter should be tested every 100
hours.
2. Remove cover panel on floor and disconnect the antenna
cable from the ELT.
)
3. Turn aircraft battery switch and avionics power switches ON.
)
4. Tune the aircraft radio to 121.5 MHz.
)
5. Place the ELT remote switch in the "ON" position.
)
)e"
) .~ -
Permit
ONLY THREE emergency tone transmissions before returning
the switch to the "ARM" position.
6. Reconnect the antenna cable to the ELT.
)
)
)
)
S52-5
30 March 2001
For Trainin Pur oses Onl
S52
MODEL 208 (675 SHP)
ARTEX 406 THREE FREQUENCY ELT
POH SUPPLEMENT
NOTE
)
With the antenna disconnected, the ELT will produce a
sufficient signal to be received by the aircraft radio, but
should not disturb other communications.
)
)
A CAUTION
)
)
(
Tests with the antenna connected should be
approved and confirmed by the nearest air traffic
control tower.
SECTION 5
PERFORMANCE
There are no changes to airplane performance when the Artex 406
Three Frequency ELT is installed in the airplane.
)
)
)
)
)
)
)
)
)
)
30 March 2001
S52-6
For Training Purposes Only
)
~
Cessna
A le.lron Company
)
Pilot's Operating Handbook and
FAA Approved Ai rplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 53
)
)
AIRPLANES WITHOUT
VACUUM POWERED GYROS
SERIAL NO.
REGISTRATION NO.
This supplement must be inserted into Section 9 of the Pilot's Operating
Handbook and FAA Approved Airplane Flight Manual for Cessna Model 208
(675 SHP) airplanes optionally equipped without vacuum powered
gyroscopic flight instruments.
)
)
APPROVED BY
)
FAA APPROVED Uf.I)ER fARi1 SlIIPMT J
Tho eou.. _Co.
)
OeleoallMOl!llon~
)
Y~
)
DATE OF APPROVAL.
)
/ ,'
)~
)
DQl..23OIQ8.CE
......,~J ~ ~e.v-
~J
".:c..'.
.
7 .)0",, __ 200\
COPYRIGHT c 2001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
.
f)
Member of GAMA
7 JUNE 2001
D1352-553-00
)
)
S53-1
)
For Training Purposes Only
S53
MODEL 208 (675 SHP)
AIRPLANES WITHOUT VACUUM GYROS
POH SUPPLEMENT
SUPPLEMENT 53
AIRPLANES WITHOUT
VACUUM POWERED GYROS
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
7 June 2001
)
)
LOG OF EFFECTIVE PAGES
PAGE
S53-1 th ru S53-4
DATE
7 June 2001
REVISION NO.
o
)
)
)
)
)
7 June 2001
853-2
)
)
For Training Purposes Only
AIRPLANES WITHOUT VACUUM GYROS
POH SUPPLEMENT
)
S53
MODEL 208 (675 SHP)
)
SUPPLEMENT 53
)
)
AI RPLANES WITHOUT
VACUUM POWERED GYROS
SECTION 1
GENERAL
)
The Cessna Model 208 (675 SHP) may be optionally equipped
without vacuum powered gyroscopic flight instruments. An electric
attitude gyro, electric directional gyro or horizontal situation indicator
(HSI), and an electric turn coordinator or turn and bank indicator, all
on the pilot's instrument panel will provide the pilot necessary
.
attitude and heading references.
)
)
)
)
)
NOTE
)
The power source for each gyroscopic instrument is
marked on the face of the unit.
A
The electrically powered gyros are protected by pull-off type circuit
breakers labeled: LH An GYRO, LH DIR GYRO, and LEFT
TURN/BANK.
.
)
SECTION 2
)
LIMITATIONS
)
Airplanes equipped without vacuum powered gyros on the pilot's
instrument panel are limited to flight only under Visual Flight Rules
(VFR) unless the aircraft is also equipped with the optional standby
power system.
)
)
)
SECTION 3
EMERGENCVPROCEDURES
)
)(
)'
)
...
0.'
ELECTRICAL SYSTEM FAILURE (aircraft not equipped with
standby power system):
1.
Land as soon as practical using vis·ual references, the
magnetic compass, and pitot-static instruments.
)
)
S53-3
7 June 2001
For Training Purposes Only
553
MODEL 208 (675 8HP)
AIRPLANES WITHOUT VACUUM GYROS
POH SUPPLEMENT
SECTION 4
NORMAL PROCEDURES
)
CAGING THE ELECTRIC ATTITUDE GYRO
)
NOTE
)
If takeoff is soon after engine start, cage the gyro
immediately. Otherwise, gyro will erect itself within
10 minutes.
1.
2.
3.
Caging knob -- PULL.
Hold approximately 5 seconds.
Release smoothly but quickly.
A CAUTION
Avoid re-caging once the attitude gyro has been
caged.
Repeated . caging may cause internal
damage.
)
SECTION 5
PERFORMANCE
)
There are no changes to aircraft performance when an electric
attitude gyro is installed in the aircraft.
)
)
)
)
)
7 June 2001
853-4
For Training Purposes Only
)
::i
)
)
Cessna
i
A lexlron Company
)
Pilot's Operating Handbook and
. FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 54
)
)
GARMI N GMA 340
AUDIO PANEL
(....
J
""
SERIAL NO.
REGISTRATION NO.
)
)
)
)
)
)
)
)
)
)(;-~. :
This supplement must be ' inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Garmin GMA 340 Audio Panel.
APPROVEDBV
FM~==~~.u.","J
_.f. . . .
~OpIIQn/whlriutiDrl
~ .* tp....J
.~
DATE OF APPROVAL
D04-I3042'·CE
2.1
.
A,Uo.lJ'ST 1.00 I
~
COPYRIGHT (') 2001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of GAMA
21 AUGUST 2001
)
01352-S54-00
)
)
S54-1
)
)
. For Training Purposes Only
S54
GARMINGMA 340 AUDIO PANEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 54
)
GARMIN GMA 340
AUDIO PANEL
)
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
)
)
Revision Level
Date of Issue
o (Original)
21 August 2001
LOG OF EFFECTIVE PAGES
·PAGE
DATE
854-1 thru S54-4
854-5/554-6
21 August 2001
21 August 2001
REVISION NO.
)
o
o
)
)
)
)
21 August 2001
S54-2
For Training Purposes Only
)
GARMIN GMA 340 AUDIO PANEL
POH SUPPLEMENT
554
MODEL 208 (675SHP)
)
SUPPLEMENT 54
)
)
/ '''.
GARMIN GMA 340
AUDIO PANEL
)\
)
)
SECTION 1
GENERAL
)
)
The Garmin GMA 340 Audio Panel contains an audio speaker
amplifier, audio distribution circuitry, and an internal marker beacon
receiver. Audio functions are controlled by two rows of buttons
located on the face of the unit. Included are controls for up to three
communication transceivers, the capability to monitor all radio
navigation aids, a passenger address system (if installed), and a
multi-place intercom. The intercom controls allow the flight crew a
variety of isolation options.
)
)
)
)
)
)
SECTION 2
LIMITATIONS
(
)
There are no additional limitations when the Garmin GMA 340
Audio Panel is installed .
)
)
SECTION 3
)
)
EMERGENCY PROCEDURES
.
)
)
There are ' no additional emergency procedures required when the
Garmin GMA 340 Audio Panel is installed. It isa fail-safe design
that connects the pilot's headset and microphone directly to COM1
in the event that. power is interrupted to the GMA340.
)
SECTION 4
NORMAL PROCEDURES
}
)
;0
)
POWER ON/OFF
The GMA340 is powered on when the small knob on the left side of
the unit is turned clockwise to bring the switch out of its detent.
)
)
S54-3
21 August 2001
For Training Purposes Only
S54
GARMIN GMA 340 AUDIO PANEL
POH SUPPLEMENT
MODEL 208 (675 SHP)
VHF COMMUNICATIONS
Selecting a radio for transmission and audio reception is
accomplished by pressing COM1 MIC, COM2 MIC, or (if installed)
COM3 MIC. Additional audio sources may be overlaid by selecting
the smaller GOM1, COM2, (if installed) COM3, NAV1, NAV2, DME,
ADF1, ADF2, and MKR buttons located just above the MIC buttons.
When transmitting, the active MIG button will blink at a rate of
approximately once per second.
PA SYSTEM (If Installed)
Pressing the PA button activates the Passenger Address system.
When the pilot's, copilot's, or hand MIC switches are keyed, audio
is broadcast over the cabin speakers.
NOTE
The SPKR button does not need to be pressed in
order for the PA to function.
INTERCOM SYSTEM (ICS)
Intercom volume is controlled by the small inner knobs. The pilot's
side knob controls the pilot's volume and the copilot's side knob
controls the copilot's volume. Plllling the copilot's knob out will
control volume for the passengers (if installed). Squelch is similarly
controlled by the large ·knobs on each side of the GMA 340 audio
panel.
Full counter-clockwise rotation provides a hot mic (no
squelch).
The GMA 340 has three intercom modes: PILOT, CREW, and ALL.
These modes are controlled by two buttons marked PILOT and
CREW. With the PILOT button selected, the pilot is isolated on a
separate circuit while allowing the copilot to communicate with the
passengers. Depressing the CREW button allows the pilot and
copilot to communicate while isolating the passengers to a separate
circuit. Deselecting both the PILOT and CREW modes allow pilot,
copilot, and passengers to ALL communicate.
MARKER BEACON RECEIVER
The Garmin GMA 340 Audio Panel contains an integral marker
beacon
receiver with the corresponding marker beacon
annunciators and tones illustrated in Figure 1.
S54-4
21 August 2001
For Training Purposes Only
\'",:~
GARMIN GMA 340 AUDIO PANEL
POH SUPPLEMENT
)
554
MODEL 208 (675 SHP)
)
)
) ~'-
(
PITCH
400 Hz
)
)
1300 Hz
)
)
3000 Hz
)
COPE
- - - - - - --.-
LAMP
BLUE "0"
OUTER
MARKER
.- .- .-
AMBER "M"
MIDDLE
MARKER
.............
WHITE "A"
INNER
MARKER OR
AIRWAYS
-
)
)
Figure 1. Marker Beacon Annunciators and Tones
)
The tones are mutable through the MKR MUTE button, however
they will automatically unmute after the marker has been passed.
Sensitivity is controlled by the SENS button, and the sensitivity level
(H I / La) is displayed just above the SENS button.
)
)
l
"
\'"
.
)
SECTION 5
.PERFORMANCE
)
There is no change to airplane performance when this avionics
equipment is installed.
)
)
)
)
)
)
)
)(..
)
~ -, ~,
)
)
)
)
S54-5/S54-6
21 August 2001
For Training Purposes Qnly
)
)
. ,i
)
)
)
)
For Training Purposes Only
)
)
~
)
) .-"
CeSSna
A Toxtron Companv
A:
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 55
)
)
GARMIN GTX 327
TRANSPONDER
)
)
.
(
J\.
SERIAL NO.
)
REGISTRATION NO.
)
This supplement must be inserted into Section 9 of the Cessna ' Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Garmin GTX 327 Transponder,
)
)
)
APPROVED BY
_ _ OVEOUHDER FAR I. aU.PORT J
)
",.,c-_eo
_ _ -noo ...CE
~QoIoo
~4tp....J
)
.~
)
DATE OF APPROVAL
)
)
.)(~W
)
°
.._ ......
2.1
COPYRIGHT 2001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
A..\J6U",-Y
:too I
f)
Member of GAMA
21 AUGUST 2001
01352-S55-01
)
REVISION 1 ·20 FEBRUARY 2002
)
S55-1
)
)
.
For Training Purposes Only
S55
GARMIN GTX 327 TRANSPONDER
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 55
GARMIN GTX 327
TRANSPONDER
)
)
Use the Log of Effective Pages to determine the current status of
Pages affected by the current revision are
this supplement.
indicated by an asterisk (*) preceding the page number.
Revision Level
Date of Issue
o (Original)
21 August 2001
20 February 2002
Revision 1
)
)
LOG OF EFFECTIVE PAGES
PAGE
DATE
* S55-1 thru S55-4
REVISION NO.
20 February 2002
20 February 2002
* S55-5/S55-6
1
1
)
APPROVED BY
MA~_'Nl.lt.-T.
--,DoIOn
__eo
_ _E
"" .....
)
~~~-"-
~
)
DATE OF APPROVAL :2.0 Fe.BR~"'Q.'C 2/:)02..
)
)
)
)
S55-2
20 February 2002
)
)
For Training Purposes Only
GARMIN GTX 327 TRANSPONDER
POH SUPPLEMENT .
555
MODEL 208 (675 SHP)
SUPPLEMENT 55
GARMIN GTX 327
TRANSPONDER
)
)
Je······
)
SECTION 1
GENERAL
)
)
The Garmin GTX 327 Transponder is capable of both Mode A and
Mode C operations. In addition to altitude ·and location reporting
functions, the GTX 327 also provides a pressure altitude display
with trend indications, a flight time display, a count up timer, and a
count down timer. A remote IDENT button is located on the pilot's
control wheel in addition to the button on the face of the GTX 327.
)
)
)
)
)
Some installations contain two GTX 327 Transponders. A toggle
switch is located next to the. units on the instrument panel to select
the active transponder. The inactive transponder will automatically
be placed in STBY mode.
I
SECTION 2
LIMIT ATIONS
)
The avionics cooling fan must be operational when operating at
outside air temperatures above 41 ce.
)
SECTION 3
EMERGENCY PROCEDURES
)
)
There are no additional emergency procedures when the Garmin
GTX 327 Transponder is installed in the airplane. Refer to current
FAR/AIM procedures for emergency codes and transponder
inoperative situations.
NOTE
)
)
)(
;
).";s,.,;'
)
When two GTX 327 Transponders are installed, toggle to
the STBY transponder in the case of transponder failure.
However, both transponders receive altitude information
from the same encoding altimeter, so if a failure occurs in
the encoding altimeter, neither transponder will have
mode C (altitude reporting) capability. Mode A (position
reporting) may still be available.
)
)
)
855-3
20 February 2002
For Training Purposes Only
S55
MODEL 208 (675 SHP)
GARMIN GTX 327 TRANSPONDER
POH SUPPLEMENT
SECTION 4
NORMAL PROCEDURES
MODE SELECTION
OFF
Powers off the GTX 327.
STBY Powers on the GTX 327, but does not allow a reply to
interrogations.
'
ON
Powers on the GTX 327 for Mode A operations.
AL T
Powers on the GTX 327 for both Mode' A and Mode C
operations.
CODE SELECTION
Code selection is accomplished using the numerical keys (0 - 7).
Pushing one of these keys begins the code selection sequence.
The new code will not be active until the fourth digit is entered.
Pressing the CLR button will move the cursor back to the previous
digit. Pressing the CLR button when the cursor is on the first digit,
or pressing the CRSR button at any time will cancel the entry and .
restore the previous code.
'
NOTE
Numerical keys 8 and 9 are not used for code entry,
only for entering a Count Down time.
OTHER FUNCTIONS
IDENT
Pressing IDENT or the remote IDENT button on the
pilot's control wheel activates the Special Position
Identification (SPI) pulse for 18 seconds, identifying the
transponder return from others on the air traffic
controller's screen. The word "IDENT" will appear in
the upper left corner of the display when IDENT mode is
active.
.
VFR
Sets the transponder code to 1200 (unless configured
otherwise). Pressing the VFR button again will restore
the previous code.
(Continued Next Page)
1855-4
20 February 2002
For Training Purposes £?nly
GARMIN GTX 327 TRANSPONDER
POH SUPPLEMENT
555
MODEL 208 (675 SHP)
)
)
)
,'."'.
-\,, ':
)
)
FUNC
Multiple presses of the FUNC button changes the function page to one of the following:
PRESSURE Displays pressure altitude in hundreds of
ALT
feet.
FLIGHT
TIME
Controlled by the START/STOP button, or
can be configured to START when the
aircraft exceeds 30 KTS GPS ground
speed, and STOP when the aircraft slows
below 30 KTS .
COUNT UP
TIMER
Controlled by the START/STOP button.
Use CLR to reset to 0:00.
COUNT
DOWN
TIMER
Enter time using numerical keys, and use '
START/STOP button to activate. UseCLR
to reset to 0:00.
)
)
)
)
)
)
)
)
(~)
)
)
)
)
ALTllUDE TREND INDICATOR
When the PRESSURE ALT page is displayed, an arrow maybe
displayed to the right of the altitude, indicating that the altitude is
increasing or decreasing. Two sizes of arrows may be displayed
depending on rate of climb/descent.
AUTOMATIC ALl/STBY MODE SWITCHING
When interfaced with a Garmin GNS 530 or GNS 430, the GTX 327
automatically switches to AL T mode when ground speed exceeds
approximately 30 knots GPS ground speed. The unit automatically
returns to STSY mode when the aircraft slows below 30 knots.
)
NOTE
)
)
)
The ON (Mode A), ALT (Mode C), and STBY buttons
can be used at any time to manually override the
automatic ALT/STBY mode switching.
)
SECTION 5
PERFORMANCE
)( ;
) :;;;,;;F
)
There is no change to airplane performance when this aVionics
equipment is installed.
)
)
)
S55-5/S55-6
20 February 2002
For Training Purposes Only
l
)
)
)
)
)
)
)
For Training Purposes Only
CESSNA MODEL 208 (675 SHP)
PILOT'S OPERATING HANDBOOK
SUPPLEMENT 56
REVISION 2
D1352-S56-02
3 DECEMBER 2003
BENDIX/KING KGP 560
GENERAL AVIATION ENHANCED GROUND PROXIMITY
WARNING SYSTEM (GA-EGPWS)
THE FOLLOWING SUPPLEMENT 56 • REVISION 2, PRINTED IN ITS
ENTIRETY, REPLACES THE ORIGINAL ISSUE DATED 20 AUGUST 2001
AND REVISION 1 DATED 30 JANUARY 2003. INSERT IT INTO SECTION
9 OF THE PILOT'.S OPERATING HANDBOOK, IF THE AIRPLANE IS
EQUIPPED WITH THE BENDIX/KING KGP 560 GA-EGPWS.
)
)
)
THE LOG OF APPROVED SUPPLEMENTS FURNISHED WITH THIS
SUPPLEMENT REPLACES ALL EARUER DATED VERSIONS OF THE
LOG.
NOTE
)
)
)
)
)(
)
)
\
\J;i~
IT IS · THE AIRPLANE OWNER'S RESPONSIBILITY TO ASSURE
THAT THEY HAVE THE LATEST REVISION TO EACH SUPPLEMENT
OF A PILOT'S OPERATING HANDBOOK, AND TME LATEST ISSUED
"LOG OF APPROVED SUPPLEMENTS." THE LOG OF APPROVED
SUPPLEMENTS FURNISHED WITH THIS REVISION WAS THE
LATEST VERSION AS OF THE DATE IT WAS SHIPPED BY CESSNA;
HOWEVER, SOME CHANGES MAY HAVE OCCURRED, AND THE
OWNER SHOULD VERIFY THIS IS THE LATEST, MOST Up·TO·DATE
. VERSION BY CONTACTING CESSNA PROPELLER AIRCRAFT
PRODUCT SUPPORT AT (316)517-5800.
For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
)
\
'<,
)
)
For Training Purposes Only
)
)
)
~
""
r
)\ :
J
Cessna
A Tell'ron Company
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675SHP)
)
)
SUPPLEMENT 56
)
)
)
)"
,
)(--
BENDIX/KING KGP 560
GENERAL AVIATION ENHANCED GROUND PROXIMITY
WARNING SYSTEM (GA-EGPWS)
)
SERIAL NO.
REGISTRATION NO.
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 20B
(675 -SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King KGP 560 GA·
EGPWS.
APPROVED BY
J
)
o
)
)( )
)
)
)
COPYRIGHT 02001
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
o1352·S56·02
Member of GAMA
20 AUGUST "2001
REVISION 2 - 3 DECEMBER 2003
)
)
S56·1
For Training Purposes Orlly
S56
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 56
BENDIX/KING KGP 560
GENERAL AVIATION ENHANCED GROUND PROXIMITY
WARNING SYSTEM (GA-EGPWS)
)
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are indicated by an asterisk
(*) preceding the page number.
)
I
SUPPLEMENT STATUS
DATE
Original
Revision 1
Revision 2
20 August 2001
30 January 2003
3 December 2003
)
LOG OF EFFECTIVE PAGES
PAGE
PAGE STATUS
856-1 thru S56-2
856-3 thru S56-4
856-5
856-6 thru S56-8
856-9 thru S56-10
856-11/S56-12
Revision
Original
Revision
Original
Revision
Revision
Revision
Number
)
2
o
)
1
)
o
)
2
2
)
)
RIVIIIIDH 2 APPIIOYlll tv
)
fAl< .tH'f'ftOtfD UClEJI,AR I I Ill......, J
tNC:-~Co
~a.-~~
;J.-1~·-OAT!
O~VAL :3 De~I!."'IU'"
:2,oo:?o
S56-2
Revision 2
For Training Purposes Only
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
S56
MODEL 208 (675 SHP)
SUPPLEMENT 56
)
)
BENDIX/KING KGP 560
GENERAL AVIATION ENHANCED GROUND PROXIMITY
WARNING SYSTEM (GA-EGPWS)
SECTION 1
GENERAL
)
)
)
)
)
('
)
)
)
)
)
)
)
)
)
)
)( .. \
~:~;;
The KGP 560 GA-EGPWS uses Global Positioning System (GPS)
information from either an airplane-installed GPS receiver, or an
internal GPS receiver in the KGP 560 to provide Terrain Awareness
.and Warning.
The GPS Signals provide both a vertical and
horizontal position reference.
Additional inputs are uncorrected
barometric pressure (from the encoding altimeter) and outside air
temperature data for vertical position accuracy.
This threedimensional . position in space is then compared to the terrain,
obstacle, and runway database contained Inside the KGP 560 to
alert and warn the pilot of danger with respect to controlled flight
into terrain and man-made obstacles. The KGP 560 is .interfaced
with a cockpit display to provide greater situational awareness' by
showing airplane position relative to terrain and obstacles.
Should the airplane fly into .danger where a conflict with terrain ora
known obstacle is imminent, the KGP 560 will . provide visual and
aural alerts and warnings to the pilot. Alerting is also present for
excessive rates of descent and inadvertent altitude loss after takeoff.
Additional features include . an aural callout when 500 feet above
runway elevation during a landing approach, .and monitoring of the
altimeter system in the airplane for possible altimeter malfunctions.
All visual and aural alerts and warnings may .be inhibited by
pressing the "Terrain Inhibit" switch (located on the right side of the
pilot's Instrument panel) once. Pressing the "Terrain Inhibit" switch
again will re-engage the visuaJ and aural alerts and warnings.
)
S56-3
20 August 2001
For Training Purposes Only
556
BENDIX/KING KGP 560 GA-EGPWS
.
POH SUPPLEMENT
MODEL 208 (675 SHP)
A
CAUTION
The terrain, obstacle, and runway database Is not
all-inclusive.
TERRAIN AWARENESS DISPLAY
The primary purpose of the terrain awareness display is to show
Additional information is also
terrain ahead of the airplane.
available to the pilot including altitude, track, range, and elevations
of the highest and lowest points on the terrain display. The
information may be displayed either as a partial arc for terrain
ahead of the airplane, or a full circle for terrain around the airplane
within a selectable radius. The color and density of the display
corresponds to the terrain elevation relative to the altitude at which
the airplane is flying. The table in Figure 1 outlines a" of the
various colors used by the KGP 560 GA-EGPWS.
COLOR
Solid Red
Solid Yellow
50% Red Dots
INDICATION
)
Terrain/Obstacle Threat Area •• Warning.
Terrain/Obstacle Threat Area .. Caution.
Terrain/Obstacle that is more than 2000 feet above airplane altitude.
50% Yellow Dots
Terrain/Obstacle that is between 1000 and 2000 feet above airplane
altitude.
\
25% Yellow Dots
Terrain/Obstacle that is 250 feet below to 1000 feet above airplane
altitude.
Solid Green
Shown only when no Red or Yellow Terrain/Obstacle.areas are within
range on the display. Shows highest Terrain/Obstacle not within 250
feet of airplane altitude.
50% Green Dots
, Terrain/Obstacle that is 250 to 1000 feet below airplane altitude.
When there are no Red or Yellow terrain areas within range on the
display, depicts a middle elevation band.
16% Green Dots
Terraln/Obsfacle that is 1000 to 2000 feet below airplane altitude.
When there are no Red or' Yellow terrain areas within range on the
display, depicts a lower elevation band.
Black
16% Cyan
Magenta Dots
No significant Terrain/Obstacles.
Area having sea level elevation (0 feet MSL).
Unknown Terrain.
shown.
No terrain data In the database for the area
Figure 1. Terrain Awareness Display Color Indications
S56-4
20 August 2001
For Training Purposes Only
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
S56
MODEL 208 (675 SHP)
I
"LOOK-AHE~D"
)
)
ALERTING AND WARNING
The -"Look-Ahead" function compares the airplane flight path to
terrain and obstacle database information, and distance to known
runways. When the "Look-Ahead" function detects a terrain or
obstacle threat at least 30 seconds ahead of the airplane, the voice
alert "Caution Terrain, Caution Terrain" (or "Caution Obstacle,
Caution Obstacle") sounds, and a bright yellow threat area is shown
on the Terrain Display. The alert will be repeated approximately
every 7 seconds. · If the airplane flight path approaches within 15 to
30 seconds of a threat area, the voice message "Terrain, Terrain,
Pull Up, Pull Up" (or "Obstacle, Obstacle, Pull Up, Pull Up") sounds
continuously and the -threat area on the Terrain Display will be
shown as solid red. When the airplane flight path changes to avoid
the threat, the alerts and warnings will cease and the threat areas
shown on the Terrain Display will be removed.
A
)
)
CAUTION
The KGP 560 GA-EGPWS "Look-Ahead" function is
gradually desensitized as an airplane nears a known
runway. Airplanes operating In close proximity to
known runways may experience very short or no
advance warnings with respect to terrain or
obstacles In the area.
)
)
)
)
)
)
556-51
Revision 1
For Training Purposes Only
S56
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
MODEL 208 (675 SHP)
RUNWAY FIELD CLEARANCE FLOOR
When the airplane is within 5 nm of a known runway, the system
establishes a "floor" of protection below the airplane. The floor is
300 feet above the field from 5 nm to 2.5 nm and then decreases to
field elevation 1 nm from the runway. Penetration of this floor will
cause the yellow caution alert annunciator to illuminate, and the
voice alert "Too Low Terrain" to be heard. If the airplane continues
to descend, the voice alert will be repeated at an increasing
If the airplane climbs back above the floor, the
frequency.
annunciator will extinguish and the voice alerts will cease.
A
CAUTION
The KGP 560 GA-EGPWS Runway Field Clearance
Floor function is gradually desensitized as an
airplane nears a known runway. Airplanes operating
in close proximity to known runways may experience
very short or no advance warnings with respect to
terrain or obstacles In the area.
EXCESSIVE RATE OF DESCENT
When the KGP 560 GA-EGPWS determines that the airplane is
descending toward terrain at a high rate for its relative altitude
above terrain, the system will provide alerting and warning to the
pilot. Initially, the voice alert "Sink Rate" will be heard, and the
yellow caution annunciator will illuminate. If the airplane continues
to descend at that rate, the voice alert will be repeated at an
increasing frequency. Should the airplane penetrate an altitude
boundary above the terrain, the voice alert "Pull Up, Pull Up" will be
heard continuously and the red warning annunciator will illuminate.
If the airplane slows its rate of descent sufficiently, the annunciator
will extinguish and the voice warnings will cease.
LOSS OF ALTITUDE AFTER TAKEOFF
Should the airplane experience a loss of altitude within
approximately 700 feet above runway elevation after takeoff, the
KGP 560 GA-EGPWS will illuminate the yellow caution annunciator
and sound the "Don't Sink, Don't Sink" voice alert. The voice alert
will be repeated with increasing frequency. When a positive rate of
climb is re-established, the annunciator will extinguish and the voice
alerts will cease.
20 August 2001
S56-6
For Training Purposes Only
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
S56
MODEL 208 (675 SHP)
ALTITUDE MONITORING
)
..
{~
)
)
When an abnormal altitude discrepancy is detected by the KGP 560
GA-EGPWS, there will be a single voice callout of "Check Altitude".
There will also be a text message CHK ALT shown on the Terrain
Display (if installed) as long as the condition that triggered the alert
persists.
. NOTE
An incorrectly set altimeter or failed encoding altimeter
will not cause a "Check Altitude" message.
.
)
)
)
ALTITUDE CALLOUT
)
)
)
.
l
'-<....
)
When the airplane is within 5 nm of a known runway, the KGP-560
provides a single "Five-Hundred" voice alert when the airplane
passes through approximately 500 feet above runway elevation.
There is no associated annunciator lamp. The callout will be reset ·
when the airplane climbs to more than 700 feet above runway
elevation.
)
SECTION 2
LIMITATIONS
)
)
)
)
)
Navigation must not he predicated upon the use of the Terrain
Awareness Display. The Terrain Awareness Display is intended to
serve as a situational awareness tool only, and may not provide the
accuracy and/or fidelity on which to solely base terrain or obstacle
avoidance maneuvering decisions.
)
)
)
)C:,'
)
)
)
20 August 2001
S56-7
For Training Purposes Only
S56
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
MODEL 208 (675 SHP)
SECTION 3
EMERGENCY PROCEDURES
)
GA-EGPWS ALERTS AND WARNINGS
"PULL UP"
)
In IMC or Night VMC:
1: Level wings and simultaneously pitch up to achieve best
angle of climb airspeed.
2. Apply maximum climb power. .
3. Continue climb until all visual and aural warnings cease.
In Day VMC:
1. Take corrective action as necessary to avoid terrain and/or
obstacles.
"TERRAIN, TERRAIN" or "OBSTACLE, OBSTACLE"
1. Take immediate action to adjust flight path away from threat
until warning ceases.
"CAUTION TERRAIN" or "CAUTION OBSTACLE"
.1. Adjust flight path as required away from threat until alert
ceases.
1. Adjust flight path to recover safe terrain clearance until alert
ceases.
"CHECK ALTITUDE"
)
)
1. Cross-check against copilot's altimeter (if installed) and
reference altitude displayed on terrain display.
"DON'T SINK"
1. Ae-establish positive rate of climb.
"SINK RATE, SINK RATE"
1. Reduce rate of descent.
20 August 2001
For Training Purposes Only
)
)
"TOO LOW TERRAIN"
556-8
)
)
BENDIX/KING KGP 560 GA-EGPWS
POH SUPPLEMENT
S56
MODEL 208 (675 SHP)
)
SECTION 3
EMERGENCY PROCEDURES
FORCED LANDINGS
)
)
)
)
)
)
)
)
)
), ,- -
A
)
)
EMERGENCY LANDING WITHOUT ENGINE "POWER
1. Seats, Seat Belts, Shoulder Harnesses -- SECURE.
2. Airspeed -- 95 KIAS (flaps UP). 80 KIAS (flaps DOWN).
3. Power Lever -- IDLE.
4. Propeller Control Lever -- FEATHER.
5. Fuel Condition Lever -- CUTOFF.
6. Fuel Boost Switch -- OFF.
7. Ignition Switch -- NORM.
Standby Power Switch (if installed) -- OFF.
9. KGP 560 GA-EGPWS INHIBIT Switch -- CONSIDER
pressing.
10. Nonessential Equipment -- OFF.
11. Fuel Shutoff -- OFF (pull out).
12. Fuel Tank Selectors -- OFF (warning horn will sound).
13. Wing Flaps -- AS REQUIRED (FULL recommended).
14. Crew Doors -- UNLATCH PRIOR TO TOUCHDOWN.
15. Battery Switch -- OFF when landing is assured.
16. Touchdown -- SLIGHTLY TAIL LOW.
17. Brakes --APPLY HEAVILY.
a.
PRECAUTIONARY LANDING WITH ENGINE POWER
)
1. Seats, Seat Belts, Shoulder Harnesses -- SECURE,
)
2. Wing Flaps -- 100 •
3. KGP 560 GA-EGPWS INHIBIT Switch -- CONSIDER
)
)
pressing.
4. Airspeed -- 90 KIAS.
5. Selected
)
)
)
)(
:
) ,- ~;,.(
)
The FA2100 CVR system consists of a recorder unit mounted on a
shelf in the tailcone and a control unit/area microphone assembly
installed in the center radio instrument panel between the pilot and
copilot. It is interfaced with the audio system to record all pilot and
copilot radio, intercom, warning, and PIA audio activity.
Power to the unit is supplied from the main electrical bus. An
external annunciator is installed on the center radio panel to
indicate eVR system failure.
Power to the unit is interrupted upon impact by a G-switch mounted
in the tailcone to prevent recording over existing data.
)
)
)
)
A bulk erase feature is interlocked through the cabin doors to
prevent accidental erasure.
The FA2100 system is qualified to TSO C123a and Jncludes an
underwater locator beacon qualified to TSO C121.
)
SECTION 2
LIMIT ATIONS
)
)
)
)
There is no change in limitations when the FA2100 eVR is
installed.
)(~""
)
)
)
)
)
563-3
11 February 2002
For Training Purposes Only
563
MODEL 208 (675 SHP)
FAIRCHILD FA21 00
COCKPIT VOICE RECORDER
SECTION 3
EMERGENCY PROCEDURES
There is no change in emergency procedures when the FA2100 ·
eVR is installed.
SECTION 4
NORMAL PROCEDURES
)
)
To verify proper operation of the eVR, press the self-test button. If
a headset is plugged into the eVR speaker jack, a tone is generated
in the headset speaker. Illumination of a green light indicates ·
proper completion of the self-test sequence.
If the eVR FAIL annunciator illuminates, the unit is not functioning
and should be serviced for proper operation.
)
To activate the bulk erase feature, press the Bulk Erase button for a
minimum of two seconds while one of the rear cabin doors is in the
open position.
}
)
SECTION 5
PERFORMANCE
}
There is no change in airplane performance when the FA2100 CVR
is installed.
)
)
)
11 February 2002
>
)
For Training Purposes Only
)
)
)
«
~
)
)
CESSNA MODEL 208 (675 SH~)
PILOT'S OPERATING HANDBOOK
SUPPLEMENT 64
ORIGINAL ISSUE
)
)
01352-S64-00
)
)
6 JANUARY 2004
) .
)
)0
)
(:
)
)
BENDIX/KING KI 825
ELECTRONIC HORIZONTAL
SITUATION INDICATOR
THE FOL.LOWING SUPPLEMENT S64 - ORIGINAL ISSUE, MUST BE
INSERTED INTO SECTION 9 OF THE PILOT'S OPERATING
HANDBOOK, IF THE AIRPLANE IS EQUIPPED WITH THE
BENDIX/KING KI 825 ELECTRONIC HORIZONTAL SITUATION
INDICATOR
)
)
)
)
)
)
)<
)l o;/
)
)
THE LOG OF APPROVED SUPPLEMENTS FURNISHED WITH THIS
SUPPLEMENT REPLACES ALL EARLIER DATED VERSIONS OF THE
LOG.
NOTE
IT IS THE AIRPLANE OWNER'S RESPONSIBILITY TO ASSURE
THAT THEY HAVE THE LATEST REVISION TO EACH SUPPLEMENT
OF A PILOT'S OPERATING HANDBOOK, AND THE LATEST
THE LOG OF
ISSUED "LOG OF APPROVED SUPPLEMENTS".
APPROVED SUPPLEMENTS FURNISHED WITH THIS REVISION
WAS THE LATEST VERSION AS OF THE DATE IT WAS SHIPPED
BY CESSNA; HOWEVER, SOME CHANGES MAY HAVE OCCURRED,
AND THE OWNER SHOULD VERIFY THIS IS THE LATEST, MOST
UP-TO-DATE VERSION BY REFERRING TO THE LATEST CESSNA
PROPELLER AIRCRAFT REVISION STATUS CHECKLIST OR BY
CONTACTING CESSNA PROPELLER
PRODUCT SUPPORT:
TELEPHONE (316) 517-5800, FAX (316) 942-9006.
)
For Trainin Pur oses Onl
)
)
)
For Training Purposes Only
~
)
)
CeSSrii
A TaxIrCJn Company
)
( \,
)
, Pilot's Operati ng Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 64
)
)
)
)
)
)
)("'.
)
BENDIX/KING KI 825
ELECTRONIC HORIZONTAL
SITUATION INDICATOR
SERIAL NO.
REGISTRATION NO. _ _ _ __
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Bendix/King KI 825 Electronic
Horizontal Situation Indicator.
'
)
)
APPROVED BY
)
)
FMIIPPROVf,;1l UNDER fAR 21 SUBPART J
The c - AIftnft CO,
Oelegalion 0pIIan AuIIOIUIiIrI ~
)
4--~~E-'"~
~
)
)(, " :
) ',,0~""
)
,
DATE OF APPROVAL 'COPYRIGHT © 2004
CESSNA AIRCRAFT COMPANY
WICHITA. KANSAS, USA
f)
JA..WU~n.)' tOb1
Member of GAMA
)
)
)
01352-564-00 '
Original Issue-6 January 2004
Page 864-1
For Trainin Pur oses Onl
S64
PILOT'S OPERATING HANDBOOK
SUPPLEMENT
BENDIX/KING KI 825 EHSI
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 564
BENDIX/KING KI 825
ELECTRONIC HORIZONTAL
SITUATION INDICATOR
Use the Log of Effective Pages to determine the current status of this
supplement. .
Pages affected by the current revision are indicated by an asterisk
the page number.
Supplement Status
Date
Original
6 January 2004
n preceding
LOG OF EFFECTIVE PAGES
Page
Status
Page
"
S64-1 thru
864-7/(S64-8 Blank)
Original
Revision
Number
o
)
)
)
)
864-2
Original Issue
For Training Purposes Only
)
S64
PILOT'S OPERATING HANDBOOK
SUPPLEMENT
)
SUPPLEMENT S64
)
)
BENDIX/KING KI 825 EHSI
CESSNA MODEL 208 (675 SHP)
.<~
.<
) ~,.
BENDIX/KING KI 825
ELECTRONIC HORIZONTAL
SITUATION INDICATOR
)
)
)
SECTION 1
GENERAL
)
)
The KI 825 can be operated in one of three display modes: HSI mode, 360 Map
mode, and Arc Map mode.
)
)
)
(
..
)
In HSI mode, the KI 825 displays navigation information in a 360-degree
compass format. The display contains information found on a standard HSI
including compass card, heading bug, course arrow with course deviation
indicator, TO/FROM indicator, and glideslope deviation indicator. Additional
information available with the KI 825 includes digital heading and course
readout, primary navigation source annunciation, groundspeed, and time to
station.
In 360 Map mode, the KI 825 displays navigation information is in a 360-degree
compass format. The same information available in HSI mode is displayed,
except there is no course arrow and the COl is moved to the bottom of the
display.
In 360 Map mode, the KI 825 can display GPS moving map
information such as flight plan, direct to waypoints, course lines, and map scale.
)
)
)
In Arc Map mode, the KI 825 displays the same information as it does in the
360 Map mode, but the display only shows approximately 45-degrees each side
of the aircraft heading.
)
)
Refer to the Bendix/King KI 825 Pilot's guide pIn 006-18282-000 (Revision 1
later) for more detailed information on the operation of the unit.
)
01
)
)
)
(
-~.'
)
)
)
)
)
S64-:
Original Issue
For Training Purposes OnlY
S64
BENDIX/KING KI 825 EHSI
CESSNA MODEL 208 (675 SHP)
PILOT'S OPERATING HANDBOOK
SUPPLEMENT
SECTION 4
NORMAL PROCEDURES
0"
j
'.
(Continued)
MENU OPTIONS
1.
2.
MENU Button •• PRESS momentarily, then PRESS and hold for
second.
COURSE Knob and HEADING Knob •• SELECT from the table below:
DESCRIPTION
LH KNOB
RHKNOB
Display Brightness
BRITE
(Adjust)
Map Range
RNG
2 NM to 320 NM
Navigation Source
NAV
GPS
VOR (lOC)
Display Mode
MODE
HSI
360
ARC
Bearing Pointer Source
BRG
GPS
VOR (lOC)
Lightning Overlay
LGHTN
NotAvaiiable
Clear Lightning Strikes
CLR
Not Available
Memory Functions
MEMRY
See Pilot's Guide
Groundspeed I Time to Station
GSTTS
GSorTTS
A
WARNING
IT IS POSSIBLE TO DIM THE DISPLAY BRIGHTNESS UNTIL THE DISPLAY
IS TOTALLY DARK. CARE SHOULD BE TAKEN WHEN ADJUSTING THE
DISPLAY BRIGHTNESS IN FLIGHT. THE MENU WILL DISAPPEAR AFTER A
SHORT PERIOD OF INACTIVITY, AND IF THE SCREEN IS DARK AT THAT
TIME, THE PILOT WILL BE UNABLE TO ADJUST THE DISPLAY
BRIGHTNESS USING ONLY THE RH KNOB (REFERENCE • EMERGENCY
PROCEDURES).
NOTE
The KI 825 is unable to accept a remote navigation source switch. Switching /
between GPS and VOR (LOC) navigation sources may only be accomplished ~
by using the MENU option - NAV. Gannin equipped airplanes will receive a "'"
message on the GNS 530 that the COl function has been disabled. The COl
function on the GNS 430 will function correctly for the No. 2 NAV course
deviation indicator.
Original Issue
S64·6
For Training Purposes Only
S64
)
PILOT'S OPERATING HANDBOOK
SUPPLEMENT
)
BENDIX/KING KI 825 EHSI
CESSNA MODEL 208 (675 SHP)
)
)
SECTION 5
PERFORMANCE
/
1,
)
Airplane performance does not change when the KI 825 Electronic Horizontal
Situation Indicator is installed in the airplane.
)
)
)
)
)
)
)
)
l
...... ,.
)
)
)
)
)
)
)
)
)
)
)( - ;
)\z:y,
)
)
)
)
S64-7/(S64-8 Blank)
Original Issue
For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
)
.
)
.
~
CeSSri8
{
A Textron Company
' ..
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 65
)
HONEYWELL KMH 880
INTEGRATED HAZARD
AWARENESS SYSTEM (IHAS)
)
)
)
)
I
A,
SERIAL NO.
)
REGISTRATION NO.
)
)
This supplement must be inserted into Section 9 of the Cessna Model
208 (675 SHP) Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual, if the airplane is equipped with the Honeywell KMH880
Integrated Hazard Awareness System (IHAS).
)
)
)
)
)
i)
)
Member of GAMA
DATE OF APPROVAL
)
)(
)"" ",.. ,
)
.
COPYRIGHT Q 2002
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
13 M.... RCH loo2.
13 MARCH 2002
. 01352-565-.00
)
)
)
S65-1
For Training Purposes Only
S65
MODEL 208 (675 SHP)
HONEYWELL KMH 880 INTEGRATED
HAZARD AWARENESS SYSTEM (IHAS)
SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 65
HONEYWELL KMH 880
INTEGRATED HAZARD
AWARENESS SYSTEM (IHAS)
Use the Log of Effective Pages to determine the current status of
this supplement. . Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number.
)
Revision Level
Date of Issue
a (Original)
13 March 2002
)
LOG OF EFFECTIVE PAGES
DATE
PAGE
S65-1 thru.S65-4
13 March 2002
REV. NUMBER
0
)
)
865-2
13 March 2002
For Training Purposes Only
)
HONEYWELL KMH880 INTEGRATED
HAZARD AWARENESS SYSTEM (IHAS)
565
MODEL 208 (675 SHP)
)
SUPPLEMENT
)
)
,
{
HONEYWELL KMH 880
INTEGRATED HAZARD
)
AWARENESS SYSTEM (IHAS)
)
)
SECTION 1
GENERAL
)
)
)
)
)
)
L,
( .
)
)
)
)
The .Honeywell KMH 880 Integrated Hazard Awareness System
(IHAS) combines the KGP 560 General Aviation Enhanced Ground
Proximity Warning System (GA-EGPWS) with the KTA 870 Traffic
Advisory System (TAS) into one unit. The system consists of a
processjng unit located in the tail of the airplane, a configuration
module, directional antenna on the top of the fuselage, an omnidirectional antenna on the bottom of the fuselage or cargo pod, and
.8 GPS antenna (optional). Graphical data is displayed on the KMD
850 Multi-function Display. Aural warnings are sounded through
cockpit speakers and the airplane audio panel (if installed). The
KTA 870 TAS may also be configured to display on the Garmin
GNS 530 or Garmin GNS 430 NAV/COM/GPS. See the individual
supplements for the KGP 560 GA-EGPWS 'and KTA 870 TAS for
detailed operating instructions, limitations, and emergency
procedures.
)
SECTION 2
LIMITAllONS
)
)
)
There are no additional limitations when the KGP 560 and KTA 870
systems are combined into · the KMH 880 IHAS. Reference the
appropriate supplements for limitations unique to each system.
)
)("j;
)
)
)
S65-3
13 March 2002
)
For Training Purposes Only
S65
MODEL 208 (675 SHP)
HONEYWELL KMH 880 INTEGRATED
HAZARD AWARENESS SYSTEM (IHAS)
SECTION 3
EMERGENCY PROCEDURES
There are no additional emergency procedures required when thei
KGP 560 and KTA 870 systems are combined into the KMH 880
IHAS.
Reference the appropriate supplements for .emergency
procedures unique to each system.
)
)
)
NOTE
In the event of a simultaneous warning from the KGP
560 and KTA 870 systems, the warning from the KGP
560 GA-EGPWS will have priority over the KT A 870
TAS.
SECTION 4
NORMAL PROCEDURES
No additional normal procedures are required when the KGP 560 ,
and KT A 870 systems are combined into the KMH 880 IHAS. :.
Reference the appropriate supplements for · normal procedures
unique to each system.
SECTIONS
PERFORMANCE
. Airplane performance does not change when the KMH 880 IHAS is
installed in the airplane.
13 March 2002
S65-4
For Training Purposes Only
)
)
)
)
)('~'
J\."
A Textron Company
:f
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 66
)
)
)
)
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
)
I
/
;f' - '
"
f
J\ '
SERIAL NO.
)
REGISTRATION NO.
)
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model
208 (675 SHP) Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual, if the airplane is equipped with the Honeywell KTA 870
Traffic Advisory System (TAS).
)
APPROVED BY
FAA _
APp~O
UNJEA
FM D()j\.iDIM2tICE
21 8uiIWn' J
~
_
_
nwc..........,.,.Co.
)
/
~.)
i)
Member of GAMA
DATE OF APPROVAL 13 MARcl-I;ZOO2..
)
~(~,,>
)
.....
COPYRIGHT 1)2002
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, U5A
13 MARCH 2002
01352-566-00
)
866-1
)
For Training Purposes Only
S66
MODEL 208 (675 SHP)
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
SUPPLEMENT
CESSNA MODEL 208 (675SHP)
)
SUPPLEMENT 66
)
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
)
)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected by the current revision are indicated by an asterisk
(*') preceding the page number.
Revision Level
Date of Issue
o(Original)
13 March 2002
LOG OF EFFECTIVE PAGES
DATE
PAGE
S66-1 thru S66-6
S66-7/S66-8
13 March 2002
13 March 2002
)
REV. NUMBER
)
o
o
)
)
)
13 March 2002
S66-2
For Training Purposes Only
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
566
MODEL208 (675 SHP)
SUPPLEMENT
j
)
(
,
--
,
)
HONEYWELL KTA 870
TRAFFIC ~DVISORY SYSTEM (T AS)
SECTION 1
'GENERAL
)
The Honeywell . KT A 870 Traffic Advisory System (TAS) is an ,
airborne system used for detecting and tracking aircraft near your
own airplane. The KTA 870 processor and antennae detect and
track other aircraft by interrogating their transponders. Aircraft
tracked and displayed by the KTA 870 TAS are referred to as
Intruders.
'
NOTE
The KT A 870 is unable to detect an intruding aircraft if
the intruder is not equipped with an operating
, transponder. TAS can detect and track aircraft with
either Mode A, Mode C, or Mode S transponders.
)
)
)
)
)
)
~(~/ .'
)
Due to aircraft geometry, the relative bearing to a Mode
A (Non-Altitude Reporting) aircraft may appear erratic
when the intruding aircraft is at close horizontal range
with a large vertical separation. In this case, the NonAltitude Reporting traffic symbol may momentarily
disappear or move rapidly around the TAS display.
Continue to use visual scan techniques to scan for this
and all other i~truding ,aircraft.
The KTA 870 analyzes the transponder replies to determine range,
bearing and relative altitude (if the Intruder aircraft is reporting
altitude). Using this data, the KTA 870 predicts the time to, and
separation at, the Intruder's Closest Point of Approach (CPA).
Should the KTA 870 determine that a collision hazard exists, it
issues visual and aural warnings in the form of a Traffic Advisory
(TA) to the flight crew. It is highly recommended that the pilot read
and understand the contents of the KTA 870/KMH 880 Traffic
Advisory System/Multi-hazard Awareness System Pilot's Guide PIN
006-18265-0000 Rev a or later before operating the KTA 870 TAS
as a traffic avoidance tool.
)
)
13 March 2002
S66-3
For Training Purposes Only
S66
MODEL 208 (675 SHP)
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
The KT A 870 TAS will display three different traffic symbols on the
The symbols change shape and color as
traffic display{s).
separation decreases between your airplane and the Intruder. The
traffic symbols also have an associated altitude tag that shows
RELATIVE altitude in hundreds of feet. A trend arrow appears
when the Intruder's vertical rate is 500 feet per minute or greater.
)
)
)
1. Open White Diamond: Intruder's relative altitude is greater
than +/- 1200 feet and/or its distance is greater than 5 nm.
2.
Filled White Diamond: Intruder aircraft is less than +/- .1200
feet and its distance is less than 5 nm, but the intruder is not
considered a threat.
3.
Yellow Circle: Intruder aircraft is less than +/- 1200 feet
and its distance is less than 5 nm and the intruder is
considered a threat. The KTA 870 will display a T A when
the CPA is 15 to 30 seconds away.
4.
No Bearing Traffic: . Traffic advisories will include range and
relative . altitude, but no symbol may be generated (when the
KTA 870 is unable to calculate azimuth).
The maximum range of the KTA 870 TAS is 18 nm laterally and
+/- 10,000 feet vertically. However, there are instances when traffic
. up to 36 nm away may be tracked. The KTA 870 automatically
reduces its range in high traffic density areas to reduce the number
of receptions that the KTA 870 processes and for interference
limiting. The KTA 870 can track as many as 45 aircraft and display
up to the 30 closest aircraft. For airplanes equipped with a Radio
Altimeter, the KTA 870 will be made slightly less sensitive below
2000 feet AGL in order to reduce nuisance traffic advisories in the
terminal area.
The KTA 870 T AS may be configured to display on any combination
of the Honeywell KMD 850 Multi-function Display, the Garmin GNS
530 NAV/COM/GPS, and/or the Garmin GNS 430 NAV/COM/GPS.
13 March 2002
S66-4
For Training Purposes Only
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
566
MODEL 208 (675 SHP)
BENDIX/KING KMD 850
)
/
\
jr
)
)
Press the TRFC butten at the bottom ef the ,unit. If the airplane is
also equipped with another traffic advisery system, press the TRFC
butten again to' toggle between the two' systems. Use the RANGE
buttons en the right side ef the unit to' scale the display range. The
MODE butten will toggle the display between ABOVE, NORMAL,
and BELOW viewing modes. The KTA 870 TAS data may also be
overlaid onto ether pages of the KMD 850 such as terrain
avoidance, weather, andlor the meving map. When KTA 870 data
is overlaid onto ether pages, the airplane symbo.l will change from
gray to' yellew. Refer to' the BendixlKing KMD 850 Pilet's Guide
PIN 006-18222-0000 Rev. 0 or later for specific operating
instructions regarding displaying and overlaying KTA 870 T AS data.
If the KT A 870 T AS detects traffic that may pese an immediate
threat to the airplane, the KMD 850 will autematically display the
TRFC page regardless of whether the KTA 870 data is overlaid on
the current page.
)
GARMIN GNS 430 OR GNS 530
)
«:,"
Select theNAV3 page to display the KTA 870 TAS Data. Use the
RANGE buttons on the right side of the unit to scale the display
range. The MENU butten and the Right Control Knebs (inner and
outer) are used to' central the centents ef the NAV3 page. Other
external situational awareness systems may also be displayed on
this page. The KTA 870 TAS data may also be overlaid ante the
meving map page(s) of the Garmin GNS 430 er GNS 530 using the
MAP SETUP functien .
)
)
)
)
)
Refer to' the Garmin GNS 400 Series Pilet's Guide Addendum
"Display Interface fer Traffic and Weather Data" PIN 190-00140-10
Rev. B or later or the Garmin GNS 530 Pilot's Guide PIN 19000181-00 Rev A or later for specific operating instructions regarding
displaying and overlaying KTA 870 TAS data.
)
)
NOTE
)
,
~(,~,...
)
:'
In airplanes where the KTA 870 data is displayed in
multiple places, one display (usually the Bendix/King
KMD 850) is designated as the master control. A pilotselected SELF-TEST and system standby (STBY) may
enly be initiated from the master control. All ether
functions will eperate independently on each display.
)
S66-5
13 MarCh 2002
For Training Purposes Only
566
MODEL 208 (675 SHP)
HONEYWELL KT A 870
TRAFFIC ADVISORY SYSTEM (TAS)
SECTION 2
LIMITATIONS
Evasive traffic avoidance maneuvers must not be based solely on
the traffic display or a Traffic Advisory from the KTA 870 TAS.
These displays and advisories are intended to assist the flight crew
in visually locating traffic.
)
)
SECTION 3
EMERGENCY PROCEDURES
)
No additional emergency procedures are required when the KTA
870 TAS is installed in the airplane.
NOTE
If the airplane is also equipped with a KGP
EGPWS. the KGP 560 GA·EGPWS ·warnings
priority over the KT A 870 TAS warnings in
instance 'that warnings are issued from both
simultaneously.
560 GAwill have
the rare
systems
SECTIONA
)
NORMAL PROCEDURES
)
BEFORE TAKEOFF 1. Pilot Initiated Self-Test - Complete.
a.
b.
c.
d.
Traffic Advisory (Yellow Circle) - 9 o'clock, range 2
miles, 200 feet below and climbing.
Proximity Traffic (Solid White Diamond) - 1 o'clock,
range 3.6 miles, 1000 feet below and descending.
Non-Threat Traffic (Open White Diamond) - 11 o'clock,
range 3.6 miles, 1000 feet above.
.
Voice Annunciation "TAS SYSTEM TEST OK":
2. TAS - STBY.
13 March 2002
566-6
For Training Purposes Only
)
,I
)
)
HONEYWELL KTA 870
TRAFFIC ADVISORY SYSTEM (TAS)
566
MODEL 208 (675 SHP)
)
TAKEOFF
)
)
i '·
X., r
)
)
)
)
1. TAS - ON (Recommend range 10 nm or less).
CLIMB
1. Range -(Recommend 10 nm or greater).
2. Display Volume Mode - (Recommend ABOVE) .
CRUISE
1. Range - (Recommend 10 nm orgreater).
2. Display Volume Mode - (Recommend NORM).
DESCENT
)
)
1. Range - (Recommend 10 nm or less in terminal area).
2 . Display Volume Mode - (Recommend BELOW).
LANDING
)
(
1 , TAS oSTBY (Below 400 ft AGL for aircraft not equipped with
a Bendix/King KRA. 4058 Radio Altimeter).
NOTE
)
Use of the TAS self-test function in flight will inhibit TAS
operation for up to eight seconds.
)
)
SECTION 5
PERFORMANCE
)
)
)
)
Aircraft performance does not change when the KTA 870 TAS is
installed in the airplane.
)
~(~,~ ,
)
)
S66-7/S66-8
13 March 2002
For Training Purposes Only
)
)
)
)
}
)
I
\
)
)
)
i
\
)
j
)
)
)
)
)
)
)
j
)
)
For Trllining Purpo~es Only
)
)
)
~
)
)
CeSSriB
(r' ~
A TOMtron Company
~,)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
)
CESSNA MODEL 208 (675 SHP)
)
)
)
SUPPLEMENT 67
)
)
)
2·PORT OXYGEN SYSTEM
.
~)
SERIAL NO..
)
REGISTRATION NO.
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the optional 2-port oxygen system.
)
)
. APPROVED BY
~
)
)
;.,J-.,~ ~
~
)
)
DATE OF APPROVAl2.S FEBItUA.RV lD02.
)
(
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rAAAWROIIED UNDER FAIl Z1l5UaM11T J
lboCooono_eo
_
_ POW"'21-Ce
...
) "',;,->,.-
;
COPYRIGHT q) 2002
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
f)
Member of GAMA
25 FEBRUARY 2002
D1352-S67-00
)
)
)
S67-1
For Training Purposes Only
S67
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 67
2-PORT OXYGEN SYSTEM
Use the Log of Effective Pages to determine the current status:
of this supplement. Pages affected by the current revision are
indicated by an asterisk (.. ) preceding the page number.
Revision Level
o (Original)
Date of Issue
)
)
25 February -2002
)
LOG OF EFFECTIVE PAGES
)
)
PAGE
DATE
867-1 thru S67-8
567 -9/S67 -10
25 February 2002
25 February 2002
REV. NUMBER
0
0
)
)
)
)
)
)
S67·2
25 February 2002
For Training Purposes Only
S67
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
)
MODEL 208 (675 SHP)
)
SUPPLEMENT
)
)
( --
~PORTOXYGENSYSTEM
\ ...
SECTION 1
GENERAL
)
)
)
)
)
)
A two-port oxygen system provides supplemental oxygen necessary
for continuous flight at high altitude. In this system, a 50.67 or
116.95 cubic foot capacity oxygen cylinder, located in the fuselage
tailcone, supplies the oxygen. Cylinder pressure is reduced to an
operating pressure of 70 PSI by a pressure regulator attached to the
cylinder. . A shutoff valve is included as part of the regulator
assembly. The system also contains an altitude compensating
regulator, located between the pressure regulator and the oxygen
supply lines, which varies the flow of oxygen to the masks,
depending on altitude. An oxygen cylinder filler valve is located on
the righf side of the airplane (under a cover plate), at the forward
end of the tail cone.
)
(-,' -~
)
)
Cylinder pressure is indicated by a pressure gage located on the
overhead console above the pilot's and front passenger's seats.
Two oxygen outlets are provided in the cabin ceiling, one each just
outboard of the pilot's and front passenger's seats. One permanent,
microphone-equipped mask is provided for the pilot, and a second
permanent mask is provided for the front passenger. Both masks
are the partial rebreathing type, equipped with vinyl plastic _hoses
and flow indicators . . The oxygen hoses are the high-flow type and
are color-coded with a blue band adjacent to the plug-in fitting .
NOTE
)
)
)
)
)(
)"--"
The pilot's mask is equipped with a microphone to
facilitate use of the radio when using oxygen. An
adapter cord is furnished with the microphoneequipped mask to mate the mask microphone lead
to the microphone jack located on the left side of the .
instrument panel. To connect the oxygen mask
microphone, connect the mask lead to the adapter
cord and plug the .cord into the microphone jack.
S67-3
25 February 2002
For Training Purposes Only
567
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
NOTE
If an optional microphone-headset combination has been in
use, the microphone lead from this equipment is already
plugged into the microphone jack. It will be necessary to
disconnect this lead from the microphone jack so that the
adapter cord from the oxygen mask microphone can be
plugged into the jack. A switch is incorporated on the lefthand control wheel to operate the microphone.
)
)
AMBIENT
TEMPERATURE
(P)
FILLING
PRESSURE
(PSIG)
AMBIENT
TEMPERATURE
(F0)
FILLING
PRESSURE
(PSIG)
0
1650
50
1875
' 10
1700
60
1925
20
1725
70
1975
30
1775
80
2000
40
1825
90
2050
Figure 1. Oxygen Filling Pressures
A remote shutoff valve control in the overhead console above the
pilot's and front passenger's seats is used to shut off the supply of
oxygen to the system when not in use. The control is mechanically
connected to the shutoff valve at the cylinder. With the exception
of the shutoff function, the system is completely automatic and
requires no manual regulation for change of altitude.
The oxygen cylinder, when fully charged, contains 50.67 or 116.95
cubic feet of aviator's breathing oxygen (Spec. No. MIL-O-2721 0).
under a pressure of 1850 PSI at 70°F (21°C). Filling pressures
will vary, however, due to ambient temperature in the filling area,
and the temperature rise resulting from compression of the
oxygen.
~67-4
25 February 2002
For Training Purposes Only
)
)
)
2·PORT OXYGEN SYSTEM
POH SUPPLEMENT
567
MODEL 208 (675 SHP)
)
)
)
(""
Because of this, merely filling to 1850 PSI will not result in a
properly filled cylinder: Fill to pressures indicated in Figure 1 for
ambient temperatures.
A WARNING
)
011, grease or other lubricants in contact with
oxygen create a serious .flre hazard, and such
contact must be avoided when handling oxygen
equipment.
)
)
)
SECTION 2
LIMITATIONS
)
)
)
)
There is no change to the airplane limitations when oxygen
equipment is installed . .
)
SECTION 3
EMERGENCY PROCEDURES
)
{'
)
There is no change to the airplane emergency procedures when
oxygen equipment is installed.
)
SECTION 4
)
NORMAL PROCEDURES
)
)
)
)
Prior to flight, check to be sure that there is an adequate oxygen
supply for the trip, by noting the oxygen pressure gage reading, and
referring to the Oxygen Duration Chart (Figure 2 or Figure 3). Also,
check that the face masks and hoses are accessible and in good
condition.
)
)
)
f.=,,:
The Oxygen Duration Chart (Figure 2 or Figure 3) should be used in
determining the usable duration (in hours) of the oxygen supply in
your airplane. The following procedure outlines the method of
finding the duration from the chart:
1.
Note the available oxygen bottle size and pressure shown
on the pressure gage.
)
)
(Continued Next Page)
867-5
25 Feoruary 2002
For Training Purposes Only
S67
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
OXYGEN DURATION CHART
(50.67 CUBIC FEET CAPACITY)
NOTE:
OXYGEN DURATION IN HOURS
NUMBER OF PERSONS
=
TOTAL HOURS DURATION
1800
1700
1600
1500
1400
1300
1200
~
iii 1100
~
I
w
a::
~
U1
U1
UJ
a::
c..
w
t.:)
ct:
1000
900
BOO
700
t.:)
600
500
400
300
200
100
o
I
2
3
4
5
7
8
9
10
OXYGEN DURATION - (HOURS) (ONE PERSON ONLY)
2685Tl051
Figure 2. Oxygen Duration Chart - 50.67 Cubic Feet Capacity
25 February 2002
S67-6
For Training Purposes Only
567
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
)
OXYGEN DURATION CHART
)
(116.95 CUBIC FEET CAPACITY)'
>(
NOTE:
OXYGEN DURATION IN HOURS = TOTAL HOURS DURATION
NUMBER OF PERSONS
'"
)
)
1700
)
1600
)
1500
1400
1300
1200
iIi 1100
-a...
1000
w
c:::
=>
U1
900
w
c:::
BOO
(f1
0W
t:l
ct:
700
0
600
)
500
)
400
)
300
)
200
).
100
)
~(~.,:, .
.
o0
2
6
B
10
12
14
16
I B20
22
OXYGEN DURATION - (HOURS) lONE PERSON ONLY)
26B5T6010
)
Figure 3. Oxygen Duration Chart - 116.95 Cubic Feet Capacity
)
)
S67~7
25 February 2002 .'
For
Tr~jnjng
Purposes Only
S67
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
2.
3.
Locate this pressure on the scale on the left side of the
appropriate chart, then go across the chart horizontally to
the right until you intersect the line representing the altitude
at which the flight will be conducted. After intersecting the
line, drop down vertically to the bottom of the chart and
This
read the duration in hours given on the scale.
duration is for one person only and will have to be divided
by the number. of persons using oxygen to obtain the total
duration in hours.
As an example of the above procedure, 1700 PSI of
pressure will safely sustain the pilot only, flying at 20,000
feet altitude, for 6 hours (50.67 cubic foot bottle). If a right
front passenger is aboard, the total duration at 20,000 feet
)
)
J.
altitude for two persons is ,3 hours.
NOTE
)
Reliance on oxygen available below 200 PSI is not
recommended. At this reduced pressure, flow rates
are not predictable.
)
When ready to use the oxygen system, proceed as follows:
1.
Mask and Hose -~ SELECT. Adjust mask to face and adjust
metallic nose strap for snug mask fit. .
A WARNING
Permit no smoking when using oxygen. 011,
grease, soap, lipstick, lip balm, and other fatty
materials constitute a serious fire hazard when
in contact with oxygen. Be sure hands and
clothing are oil-free before handling oxygen
equipment.
2.
Delivery Hose -- PLUG INTO OUTLET nearest to the seat
you are occupying;
S67 -8
25 February 2002
For Training Purposes Only
567
2-PORT OXYGEN SYSTEM
POH SUPPLEMENT
MODEL 208 (675 SHP)
)
NOTE
)
)
f '·
".
.
When the oxygen system is turned on, oxygen will flow
continuously at the proper rate of flow for any altitude
without any manual adjustments.
)
)
)
)
)
3. Oxygen Supply Control Knob -- ON.
4. Face Mask Hose Flow Indicator -- CH ECK. Oxygen is
flowing if the indicator is being forced toward the mask.
5. Delivery Hose -- UNPLUG from outlet when discontinuing
use of oxygen. This automatically stops the flow of oxygen.
6. Oxygen Supply Control Knob -- OFF when oxygen is no
longer required.
)
)
SECTION 5
PERFORMANCE
)
)
)
There is no change to
equipment is installed.
airplane performance when
oxygen
( ..
)
)
)
,)
)
)
)
)
)
)
~C
)
)
)
S67-9/S67-10
25 February 2002
For Training Purposes Only
)
)
)
)
)
)
)
For Training Purposes Only
)
)
)
)
)
/
A Textron Company
A
"
)
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 68
)
)
HONEYWELL KDR 510
FLIGHT INFORMATION SERVICES (FIS)
)
)
)
{-)
SERIAL NO.
REGISTRATION NO. '. _ _ _ _ __
)
This supplement must be inserted into Section 9 of the Cessna Model
208 (675 SHP) Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual, if the airplane is equipped with the Honeywell KDR 510
Flight Information Services (FIS) Installation.
-
)
)
)
)
APPROVED BY
f AA "",PROVED UNDER FAA 21 SUSMRT J
The
;'''0'''' Co
OptIOn A&Jh)ItUlion OOA-230426oCE
)
DeMv.• ro n
~~h__'l"_
)
)
f)
Member of GAMA
DATE OF APPROVAL31 Mt..'( 200z..
)
)(
)
)
.c.,,,,,,
"
"'.~. ".
COPYRIGHT c 2002
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
31 MAY 2002
01352-S68-00
)
)
)
S68-1
For Training Purposes Only
S68
MODEL 208 (675 SHP)
HONEYWELL KDR 510
FLIGHT INFORMATION SERVICES (FIS)
CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 68
)
HONEYWELL KDR 510
FLIGHT INFORMATION SERVICES (FIS)
Use the Log of Effective Pages to determine the current status of
this supplement.
Pages affected ' by the current revision are indicated by an asterisk
(*) preceding the page number.
Revision Level
Date of Issue
o (Original)
31 May 2002
LOG OF EFFECTIVE PAGES
PAGE
DATE
S68-1 thru S68-4
31 May 2002
REVISION NO.
o
)
)
)
S68-2
31 May 2002
For Training Purposes Only
HONEYWELL KDR 510
FLIGHT INFORMATION SERVICES (FIS)
S68
MODEL 208 (675 SHP)
)
SUPPLEMENT
)
)
~~
...
HONEYWELL KDR 510
FLIGHT INFORMATION SERVICES (FIS)
j
)
SECTION 1
GENERAL
)
)
I
)
)
)
)
(~
)
)
The Honeywell KDR 510 Flight Information Services (FIS)
installation provides weather information and other flight advisory
information to pilots to enhance situational awareness.
The
services rely on a network of ground based VHF transmitters that
continuously broadcast data to any aircraft within line-of-sight of the
transmitter. The aircraft must. be equipped with a dedicated VHF
antenna and receiver. Data is then presented to the pilot using the
KMD 850 Multi-function display. FIS information is intended to be
used as a strategic planning tool to help the pilot make decisions
about AVOIDING inclement weather areas that are beyond his
visual range. FIS lacks the sufficient resolution and update rate
necessary for severe weather penetration.
NOTE
.
)
)
)
)
)
Cessna Aircraft Company does not guarantee the
quality, accuracy, or availability of FIS data. Some data
is available to all KDR 510 installations while other data
is available only by subscription.
The network of
transmitters may not cover the entire area where the
aircraft is operated, and the ·aircraft may need to be
above 5000 feet AGL to receive FIS data in areas where
coverage does exist.
)
SECTION 2
LIMIT AllONS
)
)
~(.;
Use of the Honeywell KDR 510 Flight Information Services (FIS) for
severe weather penetration is prohibited.
)
)
)
)
S68-3
31 May 2002
For Training Purposes Only
868
MODEL 208 (675 SHP)
HONEYWELL KDR 510
FLIGHT INFORMATION SERVICES (FIS)
SECTION 3
EMERGENCY PROCEDURES
)
No additional emergency procedures are required when the KDR ;'
510 Flight Information Services (FIS) equipment is installed in the
airplane .
)
)
SECTION 4
NORMAL PROCEDURES
Press the WX function select key of the KMD 850 Multi-function
display to toggle through weather related systems installed on the
aircraft that display on the KMD 850. The MODE button toggles
between different weather related information · displays such · as
switching between METARs and PIREPs. It is highly recommended
that the pilot read the Honeywell subscription agreement and the
FIS addendum to the KMD 550/850 Pilot's guide PIN 006-182220000 to understand the entire range of information available. It is
possible that data availability and subscription services may change
over time.
SECTION 5
PERFORMANCE
Airplane performance does not change when the KDR 510 Flight
Information Services (FIS) eqUipment is installed.
)
31 May 2002
S68-4
For Training Purposes Only
~
)
Cessna
{
A Teldron Company
)
Pilot's Operating Handbook and .
FAA Approved Airplane Flight Manual
)
)
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT 69
)
)
GAR MIN GTX 330
TRANSPONDER
)
)
I"
),)
SERIAL NO.
)
REGISTRATION NO.
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual, if the airplane is equipped with the Garmin GTX 330 Transponder.
)
)
)
APPROVED BY
)
FAA AI'PIIO\IED UNDER fAA 21 SUBPART J
ThIIC_"_Co.
OoIogo11cn 0ptIan_OOW3Of2I-C
)
~~E._E"-
)
DATE OF APPROVAL
)
)(
...
) ;-:~.;,-
)
COPYRIGHT "2003
CESSNA AIRCRAFT
COMPANY
WICHITA, KANSAS, USA
8J9NllA1'.Y 2.003
'>
Member ofGAM A
8 JANUARY 2003
01352-869-00
)
)
)
S69-1
For Training Purposes Only
S69
GARMIN GTX 330 TRANSPONDER
POH SUPPLEMENT
MODEL 208 (675 SHP)
SUPPLEMENT 69
)
GARMIN' GTX 330
TRANSPONDER
)
)
Use the Log of Effective Pages to determine the current status of
this supplement. . Pages affected by the current revision are
indicated by an asterisk (*) preceding the page number. .
Revision Level
Date of Issue
P (Original)
8 January 2003
LOG OF EFFECTIVE PAGES
PAGE
DATE
* S69-1 thru S69-6
.8 January 2003
REVISION NO.
o
)
)
)
)
Original Issue
869-2
For Training Purposes Only
GARMIN GTX 330 TRANSPONDER
POH SUPPLEMENT
S69
MODEL 208 (675 SHP)
SUPPLEMENT 69
GARMIN GTX 330
TRANSPONDER
)
i
)
SECTION 1
GENERAL
)
)
)
The ,Garmin GTX330 Transponder is capable of both Mode A
(location) and Mode C (altitude) reporting. In addition, the Mode S
capability of the transponder allows information unique to the
, airplane such as tail number and maximum level airspeed to be
interrogated by various air traffic control facilities.
)
)
)
)
(" ,
\ ",
)
The face of the Garmin GTX 330 will display pressure altitude, an
altitude deviation alert, flight time, a count up timer,and a count
down timer. All audio functions have been disabled for the GTX
330 installation due to redundant alerting tones elsewhere in the
cockpit. An OAT input is not available for the GTX 330, so the
OAT/DALT display listed in the pilot's guide is not available. A
remote IDENT button is located on the pilot's control wheel in
addition to the button on the face of the GTX 330.
)
Some installations may contain two transponders. A toggle switch
is located next to the units on the instrument panel to select the
active transponder. The inactive transponder will automatically be
placed in STBY mode.
)
SECTION 2
LIMIT AllONS
)
The avionics cooling fan must be operational when operating at
outside air temperatures above 41 cC.
The Altitude Trend 'Indicator arrows descibed in the pilot's guide
must be set to a trigger level of 9999 feet per minute in the
configuration mode (factory setting). Changing this setting may
provide misleading or inaccurate information to the pilot.
S69-3
. Original Issue
For Training Purposes Only
S69
MODEL 208 (675 SHP) .
GARMIN GTX 330 TRANSPONDER
,
POH SUPPLEMENT
SECTION 3
EMERGENCY PROCEDURES
There are no additional emergency procedures when the Garmin l.
GTX 330 Transponder is installed in the airplane. Refer to current
FAR/AIM procedures for emergency codes and transponder
inoperative situations.
)
)
NOTE
When two transponders are installed, toggle to the STBY
transponder in the case of transponder failure. However,
. both transponders . receive altitude informaiton from the
same encoding altimeter, so if a failure occurs in the
encoding altimeter, neither transponder will have Mode C ·
(altitude reporting) capability. Mode A (position reproting)
and Mode S (aircraft information) may still be available.
)
)
SECTION 4
NORMAL PROCEDURES
MODE SELECTION
OFF
Powers off the GTX 330.
STB), Powers on the GTX 330, but does not allow a reply to
interrogations.
ON
Powers on the GTX 330 for Mode A, Mode C, and Mode
S operations.
Powers on the GTX 330 for both Mode A and Mode C
operations.
NOTE ,
When interfaced .with a Garmin GNS 430 or GNS 530, the
transponder will display GND after landing. This is to alert
the .pilot that the transponder has discontinued Mode A,
Mode C, and Mode S reporting. Otherwise, the
transponder functions as if in STBY mode.
ALT
)
)
)
)
)
Original Issue
569-4
For Training Purposes Only
GARMIN GTX 330 TRANSPONDER
POH SUPPLEMENT '
S69
MODEL 208 (675 SHP)
)
)
)
)(
)
)
)
CODE SELECTION
Code selection is accomplished using the numerical keys (0 - 7).
Pushing one of these keys begins the code selection sequence.
The new code will not be active until the fourth digit is entered.
Pressing theCLR button will move the cursor back to the previous
digit. Pressing the CLR button when the cursor is on the first digit,
or pressing the CRSR button at any time will cancel the entry and
restore the previous code.
NOTE
)
)
Numerical keys 8 and 9 are not used for code entry,
only for entering a Count Down time.
)
OTHER FUNCTIONS
Pressing IDENT or the remote IDENT button on the
pilot's control wheel activates the Special Position
. Identification (SPI) pulse for 18 seconds, identifying the
transponder return from others on the air traffic
controller's screen. The word "IDENT" will appear in
the upper left corner of the display when IDENT mode is
active.
Sets the , transponder code to 1200 (unless configured
otherwise). Pressing the VFR button again will restore
the previous code.
Multiple presses of the FUNC button changes the
function page to one of the following :
PRESSURE Displays pressure altitude in hundreds of
ALT
feet.
FLIGHT
TIME
)
~(,>./
Controlled by the START/STOP button, or
can be configured to ' START when the
aircraft exceeds ·30 KTS GPS ground
speed, and STOP when the airplane slows
below 30 KTS.
)
)
)
)
S69-5
Original Issue
For Training Purposes Only
GARMIN GTX 330 TRANSPONDER
POH SU PPLEMENT
ALTITUDE
MONITOR
S69
MODEL 208 (675 SHP)
Controlled by START/STOP button.
Displays altitude deviation (in hundreds of .
feet) after the reference altitude is set i
using the START button. If altitude
deviation is greater than 1000 feet, the
Altitude Monitor function will turn itself to
OFF .
COUNT UP . Controlled by the START/STOP button.
Use CLR to reset to 0:00.
TIMER
COUNT
DOWN
TIMER
Enter time using numerical keys, and use
START/STOP button to activate. Use CLR
to reset to 0 :00.
AUTOMATIC ALT/STBV MODE SWITCHING
When interfaced with a Garmin GNS 430 or GNS 530, the GTX 330
automatically switches to ALT mode when ground speed exceeds
approximately 30 knots GPS ground speed. The unit automatically
switches to GND mode when the airplane slows below 30 knots.
NOTE
The ON, ALT, and STBY buttons can be used at any
time to manually override the automatic ALT/STBY
mode switching.
SECTIONS
PERFORMANCE
)
There is no change to airplane performance when the Garmin GTX
330 Transponder is installed.
Original Issue
S69-6
For Training Purposes Only
~
)
Cessua
A Textron Company
)
)
( '-'
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
)
CESSNA MODEL 208 (675 SHP) .
)
)
SUPPLEMENT 570
)
)
BENDIX/KING KRA·405B
RADAR ALTIMETER
)
)
)
)
SERIAL NO.
)
(-
REGISTRATION NO.
~ ,~~
)
This supplement must be inserted into Section 9 of the Cessna Model 208 (675
SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight Manual, if
the airplane Is equipped with the Bendix/King KRA-4058 Radar Altimeter.
)
)
)
APPROVED8V
)
"AAAPPROVED UNDER FAR 21 SUIIWn' J
The C - AlRnftCo,
)
00Maetian 0pIIan AIIIIaIIzIIIIan 00WIMaC2
4--~ rp...., ...........
)
~
)
)
.
DATE OF APPROVAL .2.
J U""'~ 2.00 3
)
)(
COPYRIGHT
e 2003
4".;,,- CESSNA AIRCRAFT COMPANY
)
WICHITA, KANSAS, USA
f) Member of GAMA
2 June 2003
Page 870-1
)
)
D1352-870-00
For Training Purposes Only
S70
BENDIX/KING KRA-405B
RADAR ALTIMETER
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
'S UPPLEMENT S70
BENDIX/KING KRA-405B
RADAR ALTIMETER
Use the Log of Effective Pages to determine the currentstatU$ of this
supplement.
Pages affected by the current revision are indicated by an asterisk (.) preceding
the page number.
Supplement Status
Date
Original
2 June 2003
LOG OF EFFECTIVE PAGES
Page
Page
Status
S70-1 thru
S70-7/S70-8
Original
Revision
Number
o
Original Issue
S70·2
For Training Purposes Only
S70
BENDIX/KING KRA-405B
RADAR ALTIMETER
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
)
)
SUPPLEMENT
)
(
)
BENDIX/KING KRA-40S8
RADARAL TIMETER
"
)
)
SECTION 1
GENERAL
)
)
)
)
)
The Bendix/King KRA-405B Radar Altimeter System provides the pilot with
dependable accurate AGL altitude Information during the critical approach phase
of a flight. The system has the capability of alerting the pilot when a
predetermined altitude (Decision Height) is reached. The system also provides
altitude information to the Flight Control System during the approach.
)
) .~-- . .
(
~I,.-~
)
)
)
)
)
)
)
The Radar AHimeter (depending upon terrain reflectivity and airplane bank
angle) gives an absolute decision height of 0 to 2000 feet (0 to 609.60 m) with
an altitude accuracy of 0 to 500 feet: ±S feet (1 .5 m), or ±5% (whichever is
greater), and an altitude accuracy of 500 to 2000 feet: ±7%. It provides
continuous selection of warning altitude and annunciation of descent to that
altitude by both a DH (decision height) light and an aural waming which sounds
through both the speaker and headsets. Climbing through the selected warning
altitude extinguishes the DH light.
The Radar Altimeter System operates on 28-volts and consists of a panel
mounted KNI-415 Indlcator,a remote, right-hand tailcone mounted KRA-405B
ReceiverlTransmitter, and KDA-687 audio adapter. In addition, two aft bellymounted antennas are Installed. The front antenna is the transmitting antenna .
and the aft antenna is the receiving antenna.
Indicator lighting is controlled by the L FLT PANEL dimming rheostat mounted
on the lower portion of the instrument panel. All Indicators and operating
controls for the altimeter are shown and described in Figure 1.
)
)
~Ci.·
)
)
)
S70-3
Original Issue
ForTr~ining
Purposes Only
570
BENDIX/KING KRA-4058
RADAR ALTIMETER
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
2
3
5
7
KNI-415 RADAR ALnMETER INDICATOR
i
1.
DECISION HEIGHT LAMP (DH) -- Lamp will illuminate to alert the pilot '.
when the selected Decision Height is reached. The lamp can be turned
off by pushing the lamp in. The lamp can be turned on again, when below
the Decision Height, by depressing the lamp a second time.
Once turned off, the DH lamp will be automatically armed upon climb out
as the aircraft passes through the DH altitude. Pressing the self~test
button will also tum on the DH lamp if the DH bug is set above 50 feet.
2.
FLAG -- When in view, indicates invalid altitude information is being
displayed or self-test button is ~epressed.
3.
ALTITUDE . SCALE -- The KNI-415 indicates accurate altitude indications
from -20 to +2006 feet. From -20 to +500 feet, .each mark on the scale
represents 1o. feet. From 500 to 2000 feet, each mark represents 100
feet.
4.
INDICATOR NEEDLE (Not Shown) -- The AGL altitude in feet is displayed
beneath this needle. Needle will be clockwise behind mask when above
2000 feet.
Figure 1. King Radar Altimeter Operating Controls and Indicators
(Sheet 1 of 2)
S70-4
Original Issue
For Training Purposes Only
S70
)
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
)
5.
)
)
( . _-. 6.
)
7.
)
BENDIX/KING KRA-405B
RADAR ALTIMETER
DH ·BUG -- Indicates altitude during an approach at which the DHlamp will
illuminate and ' an aural warning will sound simultaneously through the
overhead speaker and headsets.
DH BUG KNOB ( V ) -- The DH knob controls the DH (decision height)
bug. Turning the knob clockwise, the DH bug will Increase in altitude;
rotated counterclockwise, the DH bug will decrease in altitude.
SELF-TEST BUTTON (TEST) -- The test button is used to test the Radar
Altimeter ReceiverfTransmltter and Indicator. When the TEST button is
depressed, the flag will come into view and 50 ±5 feet will be displayed.
)
)
Figure 1. King Radar Altimeter Operating Controls and Indicators
(Sheet 2 of 2)
)
)
SECTION 2
)
LIMITATIONS
)
)
There is no change to airplane limitations when this avionic equipment is
installed.
(~
)
SECTION 3
)
EMERGENCYPROCEDUR~S
)
)
There is no change to ' the airplane emergency procedures when this avionic
equipment is Installed. However, should errors occur during self~testing the
following procedures should be followed:
)
SELF-TEST ERRORS
)
1.
Altimeter does not indicate 50 ±5 feet when initiating SELF-TEST-DISREGARD the RADAR ALTIMETER SYSTEM.
2.
Flag will not come in view but the Indicated Altitude is correct -ALTIMETER SYSTEM MAY BE USED (However, keep in mind
subsequent failures will not be indicated by the flag).
)
)(
)
,'
,,",,',','
3.
Failure of the DH lamp to light during SELF-TEST means -- Pilot must
watch the indicator closely since the Decision Height will not be
annunciated.
)
)
)
S70-5
Original Issue
For Training Purposes Only
S70
BENDIX/KING KRA-405B
RADAR ALTIMETER
PILOT'S OPERATING
HANDBOOK SUPPLEMENT .
CESSNA MODEL 208 (675 SHP)
SECTION 4
NORMAL PROCEDURES
PREFLIGHT SELF-TEST
1.
2.
3.
4.
5.
AVIONICS MASTER Switch -- ON.
DH Bug -- SET to 25 feet.
TEST Button -- DEPRESS and HOLD. The indicated altitude should be
50 :1:5 feet and the flag should come into view, The DH lamp should
be off.
TEST Button -- DEPRESS and TURN DH Bug slowly clockwise until
the DH lamp illuminates and an aural warning is sounded over the
speaker and headset. The DH Bug should be at 50 :1:5 feet. The DH
lamp should be illuminated and the aural warning will sound at all
altitudes above 50 feet.
TEST Button -- RELEASE. The warning flag should move out of view
and the indicated altitude should be 0 feet, nominal.
TAXIING
When taxiing to and from the ramp, the DH light can sometimes be distracting.
The light may be turned off by simply pressing the DH lamp button. Once off,
the lamp may be turned on again by pressing the DH lamp button or pressing
the TEST button, if the DH bug Is set above 50 feet. Climbing past the decision
height (indicated by the DH bug) arms the DH lamp so during the approach the
lamp will light upon reaching the decision height.
INFLIGHT OPERATION
At normal cruise altitudes above 2000 feat, the Indicator pointer is behind the
mask and the warning flag is hidden from -view above 2500 feet. _ A Flight
Control System (FCS) warning is applied to · the autopilot or flight director
system indicating that usable information is not available.
When the approach plates are reviewed prior to beginning the actual approach,
the pilot should set ,the DH to the Decision Height altitude, and check altimeter
operation as follows:
1.
Depress the Self-TEST Button and Hold:
a.
b.
c.
50 :1:5 feet should be indicated.
The flag should come Into view.
The DH lamp should illuminate (if the DH setting is above 50 feet).
Original Issue
S70-6
For Training PurposesOn'ly
)
)
)
)
)
)
('-"
S70
PILOTS OPERATING
HANDBOOK SUPPLEMENT
CESSNA MODEL 208 (675 SHP)
BENDIX/KING KRA 4058
RADAR ,ALTIMETER
2.
Verify that the pointer comes on scale at 2000 feet AGL by using the
barometric altitude as a reference.
3.
If altimeter does not come on as specified above, refer to Section 3,
Emergency Procedures.
.
,
)\
'.
)
)
NOTE
)
During the actual approach, .the radar altimeter system
, provides altitude ' information to the flight control system. When
the Decision Height is reached, the ' DH lamp illuminates to
alert the pilot that a decision is to be made. The DH lamp
may then be turnedoff by pressing the lamp.
)
)
)
)
)
NORMAL OPERATION
1.
2.
AVIONICS MASTER Switch -- ON.
DH Bug -- SET as desired.
)
SECTION 5
)
)('
)
)
PERFORMANCE
There is no change to airplane performance when this avionic equipment is
Installed.
)
)
)
)
)
)
)
)
)( :
) ..
)
)
)
S70-7/S70-8
Original Issue
For Training Purposes Only
)
)
)
)
)
)
)
)
For Training Purposes Only
'~
)
)
Cessna
II Textron Company
)
)
)(-)
,
Pilot's Operating Handbook and
FAA Approved Airplane Flight Manual
,
)
"CESSNA MODEL 208 (675 SHP)
SUPPLEMENT 571
)
)
)
)
u.s. REGISTERED AIRPLANES
,
)
)
)
,
'
WITH REQUIREMENTS FOR
BRITISH (CAA) CERTIFICATION
)
$ERIALNO.
J(-)
REGISTRATION NO.
)
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual for u.s. 'registered Cessna 208 (675 SHP) airplanes which have the
British (CAA) kit installed.
)
APPROVED BY
)
.1.
FAA APP'ROIIED UNDI!It I'M ZtIlUlll'Alfr J
nw c-MnII CD,
CE
~()pUanAuIIIMrIIIIDII DCM
)
~~J6!8r'
)
JAAi
)
DATE OF APPROVAL
J«
COPYRIGHT 0 2003
, ,',' CESSNA AIRCRAFT COMPANY
) -'- "
WICHITA. KANSAS. USA
1,/r/,t!),J
~ Member of GAMA
.1
)
)
5 June 2003
Page 871-1
01352-S71-00
J
FQr Training Purposes Only
S71
BRITISH (eM) KIT ON U.S. REGISTERED AIRPLANES PILOT'S OPERATING
MODEL 208 (675 SHP)
HANDBOOK SUPPLEMENT
SUPPLEMENT S71
u.s. REGISTERED AIRPLANES
WITH REQUIREMENTS FOR
BRITISH (CAA) CERTIFICATION
J
Use the Log of Effective Pages to determine the current status of this
supplement.
.
Pages affected by the current revision are indicated by an asterisk (.) preceding,
the page number.
"
Supplement Status
Date
5 June 2003
Original
LOG OF EFFECTIVE PAGES
Revision
Page
~
Number
S71-1 thru
S71-5/S71-6
Original
o
)
S71-2
Original Issue
For Training Purposes Only
)
S71
PILOT'S OPERATING BRITISH (CAA) KIT ON U.S. REGISTERED AIRPLANES
. MODEL 206 (675 SHP)
HANDBOOK SUPPLEMENT
)
SUPPLEMENT
)
jr- -"
{
U.S. REGISTERED AIRPLANES
WITH REQUIREMENTS FOR
BRITISH (CAA) CERTIFICATION
)
)
)
)
)
SECTION 1
)
,GENERAL
)
This supplement contains information on equipment installed as a part of
the British (CM) kit when installed on U.S. registered airplanes. The
descriptions of the following equipment are similar to those found' in Section 7
of the Model 208 British Aeroplane Flight Manual.
)
)
c" " l
\) ,---
SECTION 2
LIMITATIONS
)
The limitations do not change when the British (CAA) kit is installed.
)
)
SECTION 3
)
EMERGENCY PROCEDURES
)
)
)
)
)
)() ' ", "
GENERATOR OVERHEATED (Red GENERATOR OVERHEAT Annunciator ON)
1. Generator Switch· TRIP and release.
2. GENERATOR OFF Annunciator· CHECK Illuminated.
3. Standby Power Switch· ON.
4. AVIONICS STBY PWR and AVIONICS BUS TIE Switches· ON.
5. AVIONICS 1 and 2 Switches - OFF.
6. Volt/Ammeter· SELECT ALT and ' verify alternator load Is 75 amps or
less. REDUCE LOAD as required to prevent battery discharge.
",,:
(Continued Next Page)
)
)
)
Original Issue '
S71·3
For Training Purposes Only
S71
BRITISH (eM) KIT ON U.S. REGISTERED AIRPLANES
PILOT'S OPERATING
MODEL 208 (675 SHP)
HANDBOOK SUPPLEMENT
STANDBY ALTERNATOR OVERHEATED (Red STDBY ALT OVRHT Annunciator
ON)
1. Standby Power Switch· OFF.
2. STBY ELECT PWR INOP Annunciator - CHECK ON.
)
SECTION 4
)
NORMAL PROCEDURES
)
The normal procedures do not change when the British (CAA) kit is installed.
SECTION 5
PERFORMANCE
)
Airplane performance does not change when the British (CAA) kit is installed.
SECTION 6
)
('
WEIGHT AND BALANCE
Airplane weight and balance does not change when the British (CM) kit is
installed. '
)
)
SECTION 7
AIRPLANE
)
AND SYSTEM DESCRIPTION
)
WING FLAP SYSTEM
For flap deflection, slide the selector lever to the 100 stop. For 20° flap
deflection, push down on the selector lever to clear the 10° stop then release
and slide the lever to the 20° stop. Repeat for 300 flap deflection. To retract the
. flaps, slide the selector lever from 30° to the 20° stop. Retraction to the 10° or
0° positions can be accomplished in the same manner as during extensions past
those intermediate stops.
(Continued Next Page)
571-4
Original Issue
For Training Purposes Only
)
)
S71
)
PILOT'S OPERATING BRITISH (CAA) KIT ON U.S. REGISTERED AIRPLANES
HANDBOOK SUPPLEMENT
MODEL 208 (675SHP)
)
)
)
('"
STARTER GENERATOR
\ ""
)
A red annunciator, labeled GENERATOR OVERHEAT, indicates when the
temperature of the cooling air being exhausted from the starter generator
exceeds 300°F (149°C).
)
)
PROPELLER
)
An amber annunciator, labeled BETA, Indicates when the propeller blade angle
has been reduced into the BETA range.
" .
.
)
The power lever incorporates a design, which only allows it to be positioned in
the BETA range from the idle stop position. This prevents the power lever from
Inadvertently being positioned in the BETA range before reaching the idle stop.
)
)
ELECTRICAL SYSTEM
)
{
)
\-
)
A red indicator light, labeled, STDBY ALT OVRHT, is installed in the upper left
portion of the instrument panel to the left of the clock to monitor the alternator
upper operating temperature limit. The light operates in conjunction with an
overheat sensor installed at the exhaust area of the alternator cooling fan. The
light will illuminate if the temperature of the cooling air being exhausted from the
alternator exceeds 30QoF (149°C).
)
)
)
)
)
)
)
)
;(:,~:
)
)
)
)
Original Issue
S71·5/871-6
'For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
)
)
CESSNA MODEL 208 (675 SHP)
)
)
PILOT'S OPERATING HANDBOOK
)(, "
)
SUPPLEMENT S72
)
ORIGINAL ISSUE
)
) .
01352-572-00
6 JANUARY 2004
)
)
)
)
"" ....
)(
)
)"
)
)
)
)
)
)
)
)
)1 ,
) '\..':<:.,/
)
)
ALTAIR AVIONICS CORPORATION
ADAS+
ENGINE TREND MONITOR
THE FOLLOWING SUPPLEMENT S72 - ORIGINAL ISSUE SHOULD
BE ' INSERTED INTO SECTION 9 OF THE PILOT'S OPERATING
HANDBOOK, IF THE AIRPLANE IS EQUIPPED WITH THE ALTAIR
ADAS+ ENGINE TREND MONITOR.
THE LOG OF APPROVED SUPPLEMENTS FURNISHED WITH THIS
SUPPLEMENT REPLACES ALL EARLIER DATED VERSIONS OF THE
LOG.
NOTE
IT IS THE AIRPLANE OWNER'S RESPONSIBILITY TO ASSURE
THAT THEY HAVE THE LATEST REVISION TO EACH SUPPLEMENT
OF A PILOT'S OPERATING HANDBOOK, AND THE LATEST
ISSUED "LOG OF APPROVED SUPPLEMENTS".
THE LOG OF
APPROVED SUPPLEMENTS FURNISHED WITH THIS REVISION
WAS THE LATEST VERSION AS OF THE DATE IT WAS SHIPPED
BY CESSNA; HOWEVER, SOME CHANGES MAY HAVE OCCURRED,
AND THE OWNER SHOULD VERIFY THIS IS THE LATEST, MOST
UP-TO-DATE VERSION BY REFERRING TO THE LATEST CESSNA
PROPELLER AIRCRAFT REVISION STATUS CHECKLIST OR BY
CONTACTING
CESSNA PROPELLER
PRODUCT
SUPPORT:
TELEPHONE (316) 517-5800, FAX (316) 942-9006.
)
)
For Training Purposes Only
)
)
)
)
)
)
)
)
)
)
)
)
)
For Training Purposes Only
~
Cessna
ATemon Company
Pilot's Operating Handbook and
)
)
FAA Approved Airplane Flight Manual
CESSNA MODEL 208 (675 SHP)
)
SUPPLEMENT 572
)
)
)
)
)
)
ALTAIR AVIONICS CORPORATION
ADAS+
.ENGINE TREND MONITOR
)
{
SERIAL NO.
)
REGISTRATION NO.
)
)
)
This supplement must be inserted into Section 9 of the Cessna Model 208
(675 SHP) Pilot's Operating Handbook and FAA Approved Airplane Flight
Manual for airplanes that have Altair ADAS+ Engine Trend Monitor Installed.
)
APPROVED BY
)
FAA APPROVED UNDEH FAR 21 SUBPART J
The c.... AInnft Co.
)
Oelegalion 0pUan Aulhaltrallan DOA-23IMa.c&
cd.k--- .
)
)
)
,.
~;~;.
DATE OF APPROVAL (.
COPYRIGHT I{;) 2004
CESSNA AIRCRAFT COMPANY
WICHITA, KANSAS, USA
o
J~UA.1\)' ZOO~
Member of GAMA
)
)
)
)
6 January 2004
Page 572-1
01352·572-00
For Training Purposes Only
572
ALTAIR AVIONICS CORPORATION
ADAS+ ENGINE TREND MONITOR
MODEL 208 (675 SHP)
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
SUPPLEMENT S72
)
ALTAIR AVIONICS CORPORATION
'ADAS+
ENGINE TREND MONITOR
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Use the Log of Effective Pages to determine the current status of this
supplement.
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Pages affected by the current revision are indicated by an asterisk (.) preceding
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the page number.
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Date
Supplement Status
4 January 2004
Original
LOG OF EFFECTIVE PAGES
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Number
S72-1 thru
S72-5/S72-6
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Original Issue
S72-2
For Training Purposes Only
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572
ALTAIR AVIONICS CORPORATION
ADAS+ ENGINE TREND MONITOR
MODEL 208 (675 SHP)
PILOTS OPERATING
HANDBOOK SUPPLEMENT
SUPPLEMENT
ALTAIR"AVIONICS CORPORATION
ADAS+
ENGINE TREND MONITOR
SECTION 1
GENERAL
The Altair ADAS+ Engine Trend Monitor is an engine trend recording device
and an engine parameter exceedance monitor. The Altair ADAS+ Engine
Trend Monitor allows operators to monitor the health of a particular engine
throUgh periodic sampling of engine parameters. The Engine Trend Monitor
contains logic to determine when the airplane Is In a stable cruise flight regime
before automatically taking a trend sample. The pilot may also initiate a trend
sample by pressing the cockpit annunciator.
The Altair ADAS+ Engine Trend Monitor also contains software to indicate to
the pilot by means of a white "ETM"annunciator when an engine limitation has
been exceeded. If an exceedance event is allowed to continue for a time
specified by "the Pratt & Whitney engine maintenance manual, the amber
"ENGINE" annunciator will solidly iIIuminafe during the event. The annunciator
will extinguish when the exceedance event has been corrected or when the pilot
presses the annunciator.
If an event occurs, the white "ETM" light .will flash after shutdown and prior to
engine start to alert maintenance personnel or the pilot(s) of subsequent flights
that an exceedance event has occurred. If the exceedance event(s) caused a
white "ETM" light only, the annunciation can be extinguished by pressing the
annunciator. If the exceedance event(s) caused an amber "ENGINE" light, the
exceedance annunciation cannot be extinguished by pressing the annunciator.
Downloading the Engine Trend Monitor's log file clears these reminder
annunciations.
The Engine Trend Monitor will automatically record engine parameters when an
exceedance event occurs, until it is corrected. This will help determine the
severity of the exceedance event for maintenance purposes.
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CAUTION
A flashing white "ETM" annunciation after shutdown or
prior to engine start indicates a previous exceedance of
an engine limitation.
Engine damage may have
occurred. The "ETM" annunciation will extinguish when "
the engine is operating.
(Continued Next Page)
Original Issue
S72-3
For Training Purposes Only
572
ALTAIR AVIONICS CORPORATION
ADAS+ ENGINE TREND MONITOR
MODEL 208 (675 SHP)
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
NOTE
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This is an advisory system only. The airplanes engine
gages are still the primary source ·of detecting and
correcting conditions where · engine limitations are
exceeded.
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The system will perform a self-test at initial power-up.
Both amber "ENGINE" and white "ETM" annunciators
will be illuminated for approximately 5 seconds.
SECTION 2"
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LIMITATIONS
There are no additional airplane limitations with the Altair Engine Trend Monito
installed.
SECTION 3
EMERGENCY PROCEDURES
Both the amber "ENGINE" and white "ETM' annunciator remain continuousll
illuminated (after self-test).
1.
Flight -- CONTINUE. This indicates a failure of the selHast.
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White "ETM" annunciator flashing after "shutdown or prior to engine start (afte
self-test):
1.
2.
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Annunciator· PRESS
a.
Annunciator -- EXTINGUISHED: Indicates only a white "ETM'
annunciated event has occurred.
b.
Annunciator .- NOT EXTINGUISHED:
"ENGINE" annunciated event has occurred.
Indicates
an
ambe;
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Engine parameter Exceedance Condition - INVESTIGATE for previouE
exceedance condition(s).
(Continued Next Page)
Original Issue
S72-4
For Training Purposes Only
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S72
PILOT'S OPERATING
HANDBOOK SUPPLEMENT
ALTAIR AVIONICS CORPORATION
ADAS+ ENGINE TREND MONITOR
MODEL 208 (675 SHP)
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SECTION 3
EMERGENCVPROCEDURES
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(Continued)
White "ETM" or amber "ENGINE" annunciator continuously illuminated after
engine start:
1.
Engine Gages - CHECK,
2,
Engine Parameter Exceedance Condition - CORRECT, as necessary.
White "ETM' annunciator only, continuously illuminated after shutdown or prior
to engine start after self-test:
1.
Annunciation -- CONTINUOUSLY ILLUMINATED: Indicates a sensor
fault condition has been detected, or memory is 'at or near full capacity.
SECTION 4
NORMAL PROCEDURES
Before Starting Engine:
1.
White "ETM " annunciator - CHECK EXTINGUISHED.
Manual Engine Trend:
1,
Annunciator -- PRESS.
approximately 5 seconds.
White "ETM ' annunciator will flash for
SECTION 5
PERFORMANCE
There is no performance change with the Altair Engine Trend Monitor installed.
S72-5/S72-€
Original Issue
For Training Purposes Only
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For Training Purposes Only
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