DEPARTMENT OF TRANSPORTATION C210_FAAType Cert Data C210 FAAType

User Manual: C210_FAATypeCertData

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DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
3A21
Revision 46
CESSNA
210
210A
210B
210C
210D
210E
210F
T210F
210G
T210G
210H
T210H
210J
T210J

210K
T210K
210L
T210L
210M
T210M
210N
P210N
T210N
210R
P210R
T210R
210-5 (205)
210-5A (205A)
March 31, 2003|

TYPE CERTIFICATE DATA SHEET NO. 3A21
This data sheet which is part of Type Certificate No.3A21 prescribes conditions and limitations under which the product for
which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.
Type Certificate Holder

Cessna Aircraft Company
P. O. Box 7704
Wichita, Kansas 67277

I - Model 210, 4 PCLM (Normal Category), Approved April 20, 1959
Engine

Continental IO-470-E

*Fuel

100/130 minimum grade aviation gasoline

*Engine Limits

For all operations, 2625 r.p.m. (260 b.hp.)

Propeller and
Propeller Limits

or

Page No.
Rev.No.
Page No.
Rev.No.
Page No.
Rev.No.

1
46
21
44
41
44

2
30
22
30
42
44

3
30
23
30
43
46

4
27
24
27

5
27
25
27

1. (a) Hartzell HC-A2XF-1/8433-2
Diameter: not over 82 in., not under 80 in.
Pitch settings at 30 in. sta.:
low 13.5°, high 28.0°
(b) Cessna spinner 0752006
2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.8°, high 25.8°
(b) Cessna spinner 0752004
3. Woodward hydraulic governor 210270, 210280, 210340 or 210345

6
29
26
45

7
27
27
27

8
29
28
29

9
27
29
27

10
27
30
27

11
27
31
27

12
27
32
27

13
31
33
31

14
31
34
31

15
34
35
34

16
36
36
36

17
40
37
40

18
40
38
40

19
44
39
44

20
44
40
44

Page 2 of 43

I - Model 210 (cont’d)
*Airspeed Limits (CAS)

Never exceed
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extension speed

3A21

200 m.p.h.
175 m.p.h.
130 m.p.h.
110 m.p.h.
160 m.p.h.
160 m.p.h.

(174 knots)
(152 knots)
(113 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. Range (Landing
Gear Extended)

(+38.4) to (+46.5) at 2900 lb.
(+34.5) to (+46.5) at 2550 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

2900 lb.

No. of Seats

2 (2 at +36, 2 at +70)

Maximum Baggage

120 lb. (+95)

Fuel Capacity

65 gal. (55 gal. usable); two 32.5 gal. tanks in wings at +48.
See NOTE 1 for data on unusable fuel

Oil Capacity

12 qt. (-19.4), 6 qt. usable
See NOTE 1 for data on undrainable oil

Control Surface Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 25° +1°, -0°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)

Serial Nos. Eligible

Model 210: 618, 57001 through 57575 (1960 Model)

Down
Down
Down
Down
Left

38° +2°, -1°
14° ±2°
22° ±1°
15° +1°, -0°
24° ±1°

II - Model 210A, 4 PCLM (Normal Category), Approved June 14, 1960
Engine

Continental IO-470-E

*Fuel

100/130 minimum grade aviation gasoline

*Engine Limits

For all operations, 2625 r.p.m. (260 b.hp.)

Propeller and
Propeller Limits

1. (a) Hartzell HC-A2XF-1/8433-2
Diameter: not over 82 in., not under 80
Pitch settings at 30 in. sta.:
low 13.5°, high 28.0°
(b) Cessna spinner 0752006
2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.8°, high 25.8°
(b) Cessna spinner 0752004
3. Woodward hydraulic governor 210270, 210280, 210340, 210345

or

Page 3 of 43

II - Model 210A (cont’d)
*Airspeed Limits (CAS)

3A21

Never exceed
200 m.p.h. (174 knots)
Maximum structural cruising
175 m.p.h. (152 knots)
Maneuvering
130 m.p.h. (113 knots)
Flaps extended
110 m.p.h. ( 96 knots)
Landing gear operating speed
160 m.p.h. (139 knots)
Landing gear extended speed
160 m.p.h. (139 knots)

C.G. Range (Landing
Gear Extended)

(+38.4) to (+44.4) at 2900 lb.
(+33.7) to (+44.4) at 2250 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

2900 lb.

No. of Seats

4 (2 at +36, 2 at +70)

Maximum Baggage

120 lb. (+103)

Fuel Capacity

65 gal. (55 gal. usable); two 32.5 gal. tanks in wings at +48.
See NOTE 1 for data on unusable fuel

Oil Capacity

12 qt. (-19.4), 6 qt. usable
See NOTE 1 for data on undrainable oil

Control surface movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 10° +2°, -0°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. Eligible

Model 210A: 616, 21057576 through 21057840 (1961 Model)

III -

Down 38° +2°, -1°
Down 14° ±2°
Down 22° ±1°
Down 25° +2°, -0°
Left 24° ±1°

Model 210B, 4 PCLM (Normal Category), Approved June 27, 1961
Model 210C, 4 PCLM (Normal Category), Approved June 14, 1962

Engine

Continental IO-470-S

*Fuel

100/130 minimum grade aviation gasoline

*Engine Limits

For all operations, 2625 r.p.m. (260 b.hp.)

Propeller and
Propeller Limits

1. (a) Hartzell HC-A2XF-1/8433-2
Diameter: not over 82 in., not under 80 in.
Pitch settings at 30 in. sta.:
low 13.5°, high 28.0°
(b) Cessna spinner 0752006
2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.8°, high 25.8°
(b) Cessna spinner 0752004
3. Woodward hydraulic governor 210270, 210280, 210340, 210345, 210451, 210452

or

Page 4 of 43

3A21

III - Model 210B, Model 210C (cont’d)
*Airspeed Limits (CAS)
Never exceed
225 m.p.h. (196 knots)
Maximum structural cruising
190 m.p.h. (165 knots)
Maneuvering
132 m.p.h. (115 knots)
Flaps extended
110 m.p.h. ( 96 knots)
Landing gear operating speed
160 m.p.h. (139 knots)
Landing gear extended speed
160 m.p.h. (139 knots)
C.G. Range (Landing
Gear Extended)

(+39.2) to (+45.0) at 3000 lb.
(+33.0) to (+45.0) at 2250 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

3000 lb.

No. of Seats

4 (2 at +36, 2 at +70)

Maximum Baggage

120 lb. (+103)

Fuel Capacity

65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48.
See NOTE 1 for data on unusable fuel

Oil Capacity

12 qt. (-19.4), 6 qt. usable.
See NOTE 1 for data on undrainable oil

Control Surface Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 20° +1°, -0°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)

Serial Nos. Eligible

Model 210B: 21057841 through 21058085 (1962 Model)
Model 210C: 21058086 through 21058139 and 21058141 through 21058220
(1963 Model)

Down 40° +1°, -2°
Down 14° ±2°
Down 18° ±1°
Down 20° +1°, -0°
Left 24° ±1°

IV - Model 210-5 (205), 6 PCLM (Normal Category), Approved June 14, 1962
Model 210-5A (205A), 6 PCLM (Normal Category), Approved July 19, 1963
Engine

Continental IO-470-S

*Fuel

100/130 minimum grade aviation gasoline

*Engine Limits

For all operations, 2625 r.p.m. (260 b.hp.)

Propeller and
Propeller Limits

1. (a) Hartzell HC-A2XF-1A13.5/8433-2
Diameter: not over 82 in., not under 80 in.
Pitch settings at 30 in. sta.:
low 13.5°, high 28.0°
(b) Cessna spinner 0752614
2. (a) McCauley D2A36C33/90M-8 or D2A34C49/90A-8 or D2A34C58/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.8°, high 25.8°
(b) Cessna spinner 0752614
3. Woodward hydraulic governor 210270, 210280, 210340, 210345, 210451, 210452

or

Page 5 of 43

IV - Model 210-5 (205), Model 210-5A (205A) (cont’d)
*Airspeed Limits (CAS)
Never exceed
210 m.p.h
Maximum structural cruising
Maneuvering
Flaps extended

3A21

(182 knots)
170 m.p.h. (148 knots)
138 m.p.h. (120 knots)
110 m.p.h. ( 96 knots)

C.G. Range (Landing
Gear Extended)

(+40.5) to (+47.4) at 3300 lb.
(+33.0) to (+47.4) at 2250 lb. or less
Straight line variation between points given.

Empty Wt. C.G. Range

None

*Maximum Weight

3300 lb.

No. of Seats

6 (2 at +36, 2 at +69, 2 at +100)

Maximum Baggage

Reference weight and balance data

Fuel Capacity

65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48.
See NOTE 1 for data on unusable fuel.

Oil Capacity

12 qt. (-19.4), 6 qt. usable.
See NOTE 1 for data on undrainable oil.

Control Surface Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 20° +1°, -0°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. Eligible

Model 210-5 (205)
: 641, 205-0001 through 205-0480 (1963 Model)
Model 210-5A (205A) : 205-0481 through 205-0577 (1964 Model)

Down 40° +1°, -2°
Down 14° ±2°
Down 18° ±1°
Down 20° +1°, -0°
Left 24° ±1°

V - Model 210D, 4 PCLM (Normal Category), Approved July 19, 1963
Engine

Continental IO-520-A

*Fuel

100/130 minimum grade aviation gasoline

*Engine Limits

For all operations, 2700 r.p.m. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley D2A34C58/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 0752004
(c) Woodward hydraulic governor D210452

*Airspeed limits (CAS)

Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

C.G. range (landing
gear extended)

(196 knots)
190 mph.
134 mph.
110 mph.
160 mph.
160 mph.

(165 knots)
(116 knots)
( 96 knots)
(139 knots)
(139 knots)

(+39.2) to (+46.6) at 3100 lb.
(+33.0) to (+46.6) at 2250 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Page 6 of 43

V - Model 210D (cont’d)
Empty wt. C.G. range

3A21

None

*Maximum weight

3100 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data

Fuel capacity

65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48.
See Note 1 for data on unusable fuel.

Oil capacity

12 qt. (-19.4), 6 qt. usable.
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 21° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 20° +1°, -0°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model 210D: 21058221 through 21058510 (1964 Model)

Down
Down
Down
Down
Left

40° +1°, -2°
14°30' ±2°
18° ±1°
10° +1°, -0°
24° ±1°

VI - Model 210E, 4 PCLM (Normal Category), Approved September 17, 1964
Engine

Continental IO-520-A

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C64/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 1250411
(c) Woodward hydraulic governor D210452
2. (a) McCauley E2A34C73/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor D210452

*Airspeed limits (CAS)

Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

(196 knots)
190 mph.
134 mph.
110 mph.
160 mph.
160 mph.

(165 knots)
(116 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. range (landing
gear extended)

(+39.2) to (+46.6) at 3100 lb.
(+33.0) to (+46.6) at 2250 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

Page 7 of 43

VI - Model 210E (cont’d)
*Maximum weight

3A21

3100 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data

Fuel capacity

65 gal. (63.4 gal. usable); two 32.5 gal. tanks in wings at +48.
See Note 1 for data on unusable fuel.

Oil capacity

12 qt. (-19.5), 6 qt. usable
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 21° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 20° +1°, -0°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Down
Down
Down
Down
Left

40° +1°, -2°
14°30' ±2°
18° ±1°
10° +1°, -0°
24° ±1°

Model 210E: 21058511 through 21058715 (1965 Model)

VII - Model T210F, 4 PCLM (Normal Category), Approved August 3, 1965
Engine

Continental TSIO-520-C

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 r.p.m., 32.5 in. Hg. mp. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C70/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 11.8°, high 32.0°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor G210452
2. (a) McCauley D3A32C77/82NK-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 13.2°, high 32.5°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor G210452
3. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 14.0°, high 33.0°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor G210452

*Airspeed limits (CAS)

Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

(196 knots)
190 mph.
131 mph.
110 mph
160 mph.
160 mph.

(165 knots)
(114 knots)
( 96 knots)
139 knots)
(139 knots)

Page 8 of 43

VII - Model T210F (cont’d)
C.G. range (landing
gear extended)

3A21

(+39.0) to (+46.6) at 3300 lb.
(+33.0) to (+46.6) at 2480 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

*Maximum weight

3300 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data

Fuel capacity

65 gal. (63 gal. usable); two 32.5 gal. tanks in wings at +48.
See Note 1 for data on unusable fuel.

Oil capacity

12 qt. (-19.4), 6 qt. usable.
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 21° ±2°
Elevator
Up 26°30' ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model T210F: T210-0001 through T210-0197 (1966 Model)

Down
Down
Down
Down
Left

VIII - Model 210F, 4 PCLM (Normal Category), Approved August 3, 1965
Engine

Continental IO-520-A

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C73/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor D210452
2. (a) McCauley D3A32C77/82NK-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 11.3°, high 27.6°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor D210452
3. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 13.8°, high 28.1°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor D210452

40° +1°, -2°
14°30' ±2°
18° ±1°
20° ±1°
24° ±1°

Page 9 of 43

VIII - Model 210F (cont’d)
*Airspeed limits (CAS)

Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

3A21

(196 knots)
190 mph.
131 mph
110 mph
160 mph
160 mph.

(165 knots)
(114 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. range (landing
gear extended)

(+39.0) to (+46.6) at 3300 lb.
(+33.0) to (+46.6) at 2400 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

*Maximum weight

3300 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data

Fuel capacity

65 gal. (63 gal. usable), two 32.5 gal. tanks in wings at +48.
See Note 1 for data on unusable fuel.

Oil capacity

12 qt. (-19.4), 6 qt. usable
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 21° ±2
Elevator
Up 26°30' ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model 210F: 21058716 through 21058818 (1966 Model)

Down
Down
Down
Down
Left

40° +1°, -2°
14°30' ±2°
18° ±1°
20° ±1°
24° ±1°

IX - Model T210G, 4 PCLM (Normal Category), Approved August 23, 1966
Model T210H, 4 PCLM (Normal Category), Approved August 16, 1967
Engine

Continental TSIO-520-C

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm., 32.5 in. Hg. mp. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C70/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 11.8°, high 32.0°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor G210452
(d) McCauley hydraulic governor C290D2/T2 or C290D4/T2
2. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 14.0°, high 33.0°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor G210452
(d) McCauley hydraulic governor C219D2/T2 or C290D4/T2

Page 10 of 43

3A21

IX - Model T210G, Model T210H (cont’d)
Propeller and
3. (a) McCauley D3A32C77/82NK-2 (T-210G Only)
propeller limits
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 13.2°, high 32.5°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor G210452
*Airspeed limits (CAS)

Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

(196 knots)
190 mph
135 mph.
110 mph.
160 mph.
160 mph.

(165 knots)
(117 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. range (landing
gear extended)

(+39.7) to (+47.8) at 3400 lb.
(+35.5) to (+47.8) at 2800 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

*Maximum weight

3400 lbs.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data.

Fuel capacity

90 gal. (89 gal. usable), two 45.0 gal. tanks in wings at +43.
See Note 1 for data on unusable fuel

Oil capacity

12 qt. (-19.4), 6 qt. usable.
See Note 1 for data on undrainable oil

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model T210G: T210-0198 through T210-0307 (1967 Model)
Model T210H: T210-0308 through T210-0392 (1968 Model)

Down
Down
Down
Down
Left

30°
15° ±2°
15° ±1°
5° ±1°
24° ±1°

X - Model 210G, 4 PCLM (Normal Category), Approved August 23, 1966
Model 210H, 4 PCLM (Normal Category), Approved August 16, 1967
Engine

Continental IO-520-A

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C73/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor D210452
(d) McCauley hydraulic governor C290D2/T5 or C290D3/T5

Page 11 of 43

X - Model 210G, Model 210H
(cont’d)

*Airspeed limits (CAS)

3A21

2. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 13.8°, high 28.1°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor D210452
(d) McCauley hydraulic governor C290D2/T5 or C290D3/T5
Never exceed
225 mph
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

(196 knots)
190 mph
135 mph.
110 mph.
160 mph.
160 mph.

(165 knots)
(117 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. range (landing
gear extended)

(+39.7) to (+47.8) at 3400 lb.
(+35.5) to (+47.8) at 2800 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

*Maximum weight

3400 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data

Fuel capacity

90 gal. (89 gal. usable); two 45.0 gal. tanks in wings at +43.
See Note 1 for data on unusable fuel.

Oil capacity

12 qt. (-19.4); 6 qt. usable
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model 210G: 21058819 through 21058936 (1967 Model)
Model 210H: 21058937 through 21059061 (1968 Model)

Down 30°
Down 15° ±2°
Down 15° ±1°
Down
5° ±1°
Left 24° ±1°

XI - Model T210J, 4 PCLM (Normal Category), Approved July 17, 1968
Engine

Continental TSIO-520-H

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm., 32.5 in. Hg. mp. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C70/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 11.8°, high 32.0°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor G210452
(d) McCauley hydraulic governor C290D2/T2 or C290D4/T2

Page 12 of 43

3A21

XI - Model T210J (cont’d)
2. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 14.0°, high 33.0°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor G210452
(d) MCauley hydraulic governor C219D2/T2 or C290D4/T2
Airspeed limits (CAS)

Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

(196 knots)
90 mph.
135 mph
110 mph.
160 mph
160 mph

(165 knots)
(117 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. range (landing
gear extended)

(+39.7) to (+47.8) at 3400 lb.
(+35.5) to (+47.8) at 2800 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

*Maximum weight

3400 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data.

Fuel capacity

90 gal. (89 gal. usable), two 45.0 gal. tanks in wings at +43.
See Note 1 for data on unusable fuel.

Oil capacity

10 qt. (-12.5), 8 qt. usable
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model T210J: 21058140, T210-0393 through T210-0454 (1969 Model)

Down 30°
Down 15° ±2°
Down 15° ±1°
Down
5° ±1°
Left 24° ±1°

XII - Model 210J, 4 PCLM (Normal Category), Approved July 17, 1968
Engine

Continental IO-520-J

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm. (285 b.hp.)

Propeller and
propeller limits

1. (a) McCauley E2A34C73/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor D210452
(d) McCauley hydraulic governor C290D2/T5 or C290D3/T5

Page 13 of 43

XII - Model 210J (cont’d)

*Airspeed limits (CAS)

3A21

2. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78 in.
Pitch settings at 30 in. sta.:
low 13.8°, high 28.1°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor D210452
(d) McCauley hydraulic governor C290D2/T5 or C290D3/T5
Never exceed
225 mph.
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

(196 knots)
190 mph
135 mph.
110 mph.
160 mph.
160 mph.

(165 knots)
(117 knots)
( 96 knots)
(139 knots)
(139 knots)

C.G. range (landing
gear extended)

(+39.7) to (+47.8) at 3400 lb.
(+35.5) to (+47.8) at 2800 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+2456 in.-lb.)

Empty wt. C.G. range

None

*Maximum weight

3400 lb.

No. of seats

4 (2 at +36, 2 at +70)

Maximum baggage

Reference weight and balance data

Fuel capacity

90 gal. (89 gal. usable); two 45.0 gal. tanks in wings at +43.
See Note 1 for data on unusable fuel.

Oil capacity

10 qt. (-12.5); 8 qt. usable
See Note 1 for data on undrainable oil.

Control surface
movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0. W.L.)

Serial Nos. eligible

Model 210J: 21059062 through 21059199 (1969 Model)

Down 30°
Down 15° ±2°
Down 15° ±1°
Down
5° ±1°
Left 24° ±1°

XIII - Model 210K/T210K, 6 PCLM (Normal Category), Approved September 26, 1969
Model 210L/T210L, 6 PCLM (Normal Category), Approved October 7, 1971
Model 210K/210L
Engine

Continental IO-520-L

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

Takeoff (5 min.) at 2850 rpm. (300 hp.)
For all other operations, 2700 r.p.m. (285 hp.)

Page 14 of 43

XIII Model 210K/T210K, Model 210L/T210L (cont’d)
Propeller and
1. Model 210K/210L (S/N 21059200 through 21060539)
propeller limits
(a) McCauley E2A34C73/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 10.3°, high 25.8°
(b) Cessna spinner 1250419
(c) Woodward hydraulic governor 2104562
(d) McCauley hydraulic governor C290D2/T4 or C290D4/T4
2. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 11.5°, high 28.1°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor 210462
(d) McCauley hydraulic governor C290D2/T4 or C290D4/T4
Model T210K/T210L
Engine

Continental TSIO-520-H

*Fuel

100/130 minimum grade aviation gasoline

*Engine limits

For all operations, 2700 rpm., 32.5 in. Hg. mp. (285 b.hp.)

Propeller and
Propeller Limits

1. Model T210K/T210L (S/N 21059200 through 21060539)
(a) McCauley E2A34C70/90AT-8
Diameter: not over 82 in., not under 80 in.
Pitch settings at 36 in. sta.:
low 11.8°, high 32.0°
(b) Cessna spinner 1250415
(c) Woodward hydraulic governor G210452
(d) McCauley hydraulic governor C290D2/T2 or C290D4/T4
2. (a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 14.0°, high 33.0°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor G210452
(d) McCauley hydraulic governor C290D2/T2 or C290D4/T2

Models 210K/210L/T210K/T210L
*Airspeed Limits (CAS)

(IAS)
(See NOTE 4 on use of IAS)

Model 210K/T210K, 210L/T210L (S/N 21059200 through 21061039)
Never exceed
225 m.p.h
(196 knots)
Maximum structural cruising
190 m.p.h (165 knots)
Maneuvering
135 m.p.h (117 knots)
Flaps extended (210K/T210K)
110 m.p.h ( 96 knots)
Flaps extended (210L/T210L)
120 m.p.h (104 knots)
Landing gear operating speed
160 m.p.h (139 knots)
Landing gear extended speed
160 m.p.h (139 knots)
Model 210L/T210L (S/N 21061040 through 21061573)
Never exceed
199 knots
Maximum structural cruising
168 knots
Maneuvering
119 knots
Flaps extended
105 knots
Landing gear operating speed
140 knots
Landing gear extended speed
140 knots

3A21

Page 15 of 43

3A21

Models 210K/210L/T210K/T210L (cont’d)
C.G. Range (Landing
(+42.5) to (+53.0) at 3800 lb.
Gear Extended)
(+37.0) to (+53.0) at 3000 lb. or less
Straight line variation between points given.
Moment change due to retracting landing gear (+3207 in.-lb.)
Empty Wt. C.G. Range

None

*Maximum Weight

3800 lb.

No. of Seats

Standard 6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101)
Optional 4 (2 at +34 to +46, 2 at +77) (210K/T210K)

Maximum Baggage

Reference weight and balance data

Fuel Capacity

90 gal. (89 gal. usable); two 45.0 gal. tanks in wings at +43
See NOTE 1 for data on unusable fuel.

Oil Capacity

10 qt. (-12.5); 8 qt. usable
See NOTE 1 for data on undrainable oil.

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 25° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27°13' ±1°
(measured perpendicular to hinge line)

Serial Nos. Eligible

Down
Down
Down
Down
Left
Left

Models 210K/T210K: 21059200 through 21059351
21059352 through 21059502
Models 210L/T210L: 21059503 through 21059719
21059720 through 21060089
21060090 through 21060539 1974 Model)
21060540 through 21061039
21061040 through 21061041
21061043 through 21061573 (1976 Model)

XIV - Model 210M/T210M, 6 PCLM (Normal Category), October 7, 1976
Model 210M
Engine
*Fuel

Continental IO-520-L
Model 210M (S/N 21061574 through 21062273)
100/130 minimum grade aviation gasoline
Model 210M (S/N 21062274 through 21062953)
100LL/100 minimum grade aviation gasoline

*Engine Limits

Takeoff (5 min.) at 2850 r.p.m. (300 hp.)
For all other operations, 2700 r.p.m. (285 hp.)

30° +1°, -2°
15° ±2°
17° ±1°
10° ±1°
24° ±1°
27°13' ±1°
(1970 Model)
(1971 Model)
(1972 Model)
(1973 Model)
1975 Model)
1976 Model)

Page 16 of 43

XIV - Model 210M/T210M (cont’d)
Propeller and
1. Model 210M (S/N 21061574 through 21062273)
Propeller Limits
(a) McCauley D3A32C88/82NC-2
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 11.5°, high 28.1°
(b) Cessna spinner 1250419-2
(c) Woodward hydraulic governor 210462
(d) McCauley hydraulic governor C290D4/T4
2. Model 210M (S/N 21062274 and up)
(a) McCauley D3A34C404/80VA-0
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 11.0°, high 27.0°
(b) Cessna spinner 1250419
(c) McCauley hydraulic governor C290D4/T4
*Airspeed Limits (IAS)
(See NOTE 4 on use of IAS)

Model T210M
Engine
*Fuel

1. Model 210M (S/N 21061574 through 21062273)
Never exceed
199 knots
Maximum structural cruising
168 knots
Maneuvering
119 knots
Flaps extended
105 knots
Landing gear operating speed
140 knots
Landing gear extended speed
140 knots
2. Model 210M (S/N 21062274 through 21062953)
Never exceed
199 knots
Maximum structural cruising
168 knots
Maneuvering
119 knots
Flaps extended
115 knots
Landing gear operating speed
140 knots
Landing gear extended speed
199 knots
Continental TSIO-520-R
Model T210M (S/N 21061574 through 21062273)
100/130 minimum grade aviation gasoline
Model T210M (S/N 21062274 through 21062953)
100LL/100 minimum grade aviation gasoline

Engine Limits

Takeoff (5 min. at 2700 r.p.m., 36.5 in. Hg. mp. (310 hp.)
For all other operations 2600 r.p.m., 35 in. Hg. mp. (285 hp.)

Propeller and
Propeller Limits

1. (a) McCauley D3A34C402/90DFA-10
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 12.4°, high 28.5°
(b) Cessna spinner 1250419-10
(c) McCauley hydraulic governor C290D4/T2
(d) Woodward hydraulic governor G210452

*Airspeed Limits (IAS)
(See NOTE 4 on use of IAS)

1. Model T210M (S/N 21061574 through 21062273)
Never exceed
195 knots
Maximum structural cruising
165 knots
Maneuvering
119 knots
Flaps extended
105 knots
Landing gear operating speed
140 knots
Landing gear extended speed
140 knots

3A21

Page 17 of 43

3A21

2. Model T210M (S/N 21062274 through 21062953
Never exceed
195 knots
Maximum structural cruising
165 knots
Maneuvering
119 knots
Flaps extended
115 knots
Landing gear operating speed
140 knots
Landing gear extended speed
195 knots
Models 210M/T210M
C.G. Range (Landing
Gear Extended)

(+42.5) to (+53.0) at 3800 lb.
(+37.0) to (+53.0) at 3000 lb. or less
Straight line variation between points given
Moment change due to retracting landing gear (+3207 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

3800 lb.

No. of Seats

6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101)

Maximum Baggage

Reference weight and balance data

Fuel Capacity

90 gal. (89 gal. usable), two 45.0 gal. tanks in wings at +43.
See NOTE 1 for data on unusable fuel

Oil Capacity

10 qt. (-12.5), 8 qt. usable

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 25° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1°
(measured perpendicular to hinge line)

Serial Nos. Eligible

Models 210M/T210M:

Down
Down
Down
Down
Left
Left

30° +1°, -2°
15° ±2°
17° ±1°
10° ±1°
24° ±1°
27° 13' ±1°

21061574 through 21062273 (1977 Model)
21061042, 21062274 through 21062954 (1978 Model)

XV - Model P210N, Pressurized Centurion, 6 PCLM (Normal Category), Approved August 10, 1977
Engine

Model P210N (S/N P21000001 through P21000760: Continental TSIO-520-P
Model P210N (S/N P21000761 and up): Continental TSIO-520-AF

*Fuel

100LL/100 minimum grade aviation gasoline

*Engine Limits

Model P210N (S/N P21000001 through P21000760)
Takeoff (5 min.) at 2700 r.p.m., 36.5 in. Hg. mp. (310 hp.)
For all other operations 2600 r.p.m., 33.5 in. Hg. mp. (285 hp.)
Model P210N (S/N P21000761 and up)
Takeoff (5 min.) at 2700 r.p.m., 35.5 in. Hg. mp. (310 hp.)
For all other operations, 2600 r.p.m., 34.5 in. Hg. mp. (285 hp.)

Page 18 of 43

XV - Model P210N
Propeller and
Propeller Limits

3A21

(cont’d)
1. (a) McCauley D3A34C402/90DFA-10
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 12.4°, high 28.5°
Model P210N (S/N P21000001 through P21000760)
Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. mp.
Model P210N (S/N P21000761 and up)
Avoid continuous operation between 1850 and 2150 r.p.m. above 23 in. mp.
(b) Cessna spinner 1250419
(c) McCauley hydraulic governor C290D4/T2

*Airspeed Limits (IAS)
(See NOTE 4 on use of IAS)

1. Model P210N (S/N P21000001 through P21000150)
Never exceed
200 knots
Maximum structural cruising
167 knots
Maneuvering
130 knots
Flaps extended
115 knots
Landing gear operating speed
140 knots
Landing gear extended speed
200 knots
2. Model P210N (S/N P21000151 and up)
Never exceed
200 knots
Maximum structural cruising
167 knots
Maneuvering
130 knots
Flaps extended
115 knots
Landing gear operating speed
165 knots
Landing gear extended speed
200 knots

C.G. Range (Landing
Gear Extended)

(+43.9) to (+52.0) at 4000 lb.
(+42.5) to (+52.0) at 3800 lb.
(+37.0) to (+52.0) at 3000 lb. or less
Straight line variation between points given
Moment change due to retracting landing gear
(+3207 in.-lb.) S/N P21000001 through P21000150
(+2907 in.-lb.) S/N P21000151 and up

Empty Wt. C.G. Range

None

*Maximum Weight

4000 lb. takeoff and flight
3800 lb. landing
4016 lb. ramp, S/N 21000151 and up

No. of Seats

6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101)

Maximum Baggage

Reference weight and balance data

Fuel Capacity

90 gal. (89 gal. usable), S/N P21000001 through P21000760
90 gal. (87 gal. usable), S/N P21000761 and up
two 45.0 gal. tanks in wings at +43
See NOTE 1 for data on unusable fuel.

Oil Capacity

10 qt. (-12.5); 8 qt. usable

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 25° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1°
(measured perpendicular to hinge line)

Down
Down
Down
Down
Left
Left

30° +1°, -2°
15° ±2°
17° ±1°
10° ±1°
24° ±1°
27° 13' ±1°

Page 19 of 43

XV - Model P210N (cont’d)
Serial Nos. Eligible

Model P210N:

3A21

P21000001 through P21000150 (1978 Model)
P21000151 through P21000385 (1979 Model)
P21000386 through P21000590 (1980 Model)
P21000591 through P21000760 (1981 Model)
P21000761 through P21000811 (1982 Model)
P21000812 through P21000834 (1983 Model)

XVI - Model 210N/T210N, Centurion/Turbo System Centurion, 6 PCLM (Normal Category), approved October 19, 1978
Model 210N
Engine

Continental IO-520-L

*Fuel

100LL/100 minimum grade aviation gasoline

*Engine Limits

Takeoff full throttle (5 min.) at 2850 r.p.m. (300 hp. rating)
For all other operations, full throttle 2700 r.p.m. (285 hp. rating)

Propeller and
Propeller Limits

1. (a) McCauley D3A34C404/80VA-0
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 11.0°, high 27.0°
(b) Cessna spinner 1250419
(c) McCauley hydraulic governor C290D4/T4

*Airspeed Limits (IAS)
(See NOTE 4 on Use of IAS)

1. Model 210N (S/N 21062954 and up)
Never exceed
200 knots
Maximum structural cruising
165 knots
Maneuvering
125 knots
Flaps extended
115 knots
Landing gear operating speed
165 knots
Landing gear extended speed
200 knots

C.G. Range (Landing
Gear Extended)

(+42.5) to (+53.0) at 3800 lb.
(+37.0) to (+53.0) at 3000 lb. or less
Straight line variation between points given
Moment change due to retracting landing gear (+2907 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

3800 lb.
3812 lb. ramp

No. of Seats

6 (2 at +34 to +46, 2 at +61 to +77, 2 at +101)

Maximum Baggage

Reference weight and balance data

Fuel Capacity

90 gal. (89 gal. usable), S/N 21062955 through 21064535
90 gal. (87 gal. usable), S/N 21064536 and up
two 45.0 gal. tanks in wings at +43
See NOTE 1 for data on unusable fuel.

Oil Capacity

10 qt. (-12.5), 8 qt. usable

Page 20 of 43

Model 210N (cont’d)
Control Surface
Movements

Serial Nos. Eligible

Model T210N
Engine

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 25° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1°
(measured perpendicular to hinge line)
Model 210N:

3A21

Down
Down
Down
Down
Left
Left

21062955 through 21063640
21063641 through 21064135
21064136 through 21064535
21064536 through 21064772
21064773 through 21064822
21064823 through 21064897

30° +1°, -2°
15° ±2°
17° ±1°
10° ±1°
24° ±1°
27° 13' ±1°
(1979 Model)
(1980 Model)
(1981 Model)
(1982 Model)
(1983 Model)
(1984 Model)

Continental TSIO-520-R

Fuel

100LL/100 minimum grade aviation gasoline

*Engine Limits

Takeoff (5 min.) at 2700 r.p.m., 36.5 in. Hg. mp. (310 hp. rating)
For all other operations 2600 r.p.m., 35 in. Hg. mp. (285 hp. rating)

Propeller and
Propeller Limits

1. (a) McCauley D3A34C402/90DFA-10
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 12.4°, high 28.5°
Avoid continuous operation between 1850 and 2150 r.p.m..
above 24 in. mp.
(b) Cessna spinner 1250419
(c) McCauley hydraulic governor C290D4/T2 or Woodward hydraulic
governor G210452

*Airspeed Limits (IAS)
(See NOTE 4 on Use of IAS)

1. Model T210N (S/N 21062954 and up)
Never exceed
203 knots
Maximum structural cruising
168 knots
Maneuvering
130 knots
Flaps extended
115 knots
Landing gear operating speed
165 knots
Landing gear extended speed
203 knots

C.G. Range (Landing
Gear Extended)

(+43.9) to (+52.0) at 4000 lbs.
(+42.5) to (+53.0) at 3800 lbs.
(+37.0) to (+53.0) at 3000 lbs.
Straight line variation between points given
Moment change due to retracting landing gear (+2907 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

4000 lb. takeoff and flight
3800 lb. landing
4016 lb. ramp

No. of Seats

6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101)

Maximum Baggage

Reference weight and balance data

Page 21 of 43

Model T210N (cont’d)
Fuel Capacity

3A21

90 gal. (89 gal. usable), S/N 21062955 through 21064535
90 gal. (87 gal. usable), S/N 21064536 and up
two 45.0 gal. tanks in wings at +43
See NOTE 1 for data on unusable fuel.

Oil Capacity

10 qt. (-12.5); 8 qt. usable

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 23° ±1°
Elevator tab
Up 25° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1
(measured perpendicular to hinge line)

Serial Nos. Eligible

Model T210N:

Down
Down
Down
Down
Left
Left

30° +1°, -2°
15° ±2°
17° ±1°
10° ±1°
24° ±1°
17° 13' ±1°

21062955 through 21063640 (1979 Model)
21063641 through 21064135 (1980 Model)
21064136 through 21064535 (1981 Model)
21064536 through 21064772 (1982 Model)
21064773 through 21064822 (1983 Model)
21064823 through 21064897 (1984 Model)

XVII - Model P210R, Pressurized Centurion, 6 PCLM (Normal Category), Approved September 24, 1984
Engine

Continental TSIO-520-CE

*Fuel

100LL/100 minimum grade aviation gasoline

*Engine Limits

For all operations 2700 r.p.m., 37 in. Hg. mp. (325 hp.)

Propeller and
Propeller Limits

1. (a) McCauley D3A36C410/80VMB-0
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 14.2°, high 36.5°
(b) Cessna spinner 2150150
(c) McCauley hydraulic governor C290D4/T2

*Airspeed Limits (IAS)

Never exceed
200 knots
Maximum structural cruising
Flaps extended
Maneuvering
Landing gear operating speed
Landing gear extended speed

167 knots
115 knots
130 knots
165 knots
200 knots

C.G. Range (Landing
Gear Extended)

(+42.0) to (+52.0) at 4100 lb.
(+37.0) to (+52.0) at 3350 lb. or less
Straight line variation between points given
Moment change due to retracting landing gear (+2907 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

4100 lb. takeoff and flight
3900 lb. landing
4116 lb. ramp

No. of Seats

6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101)

Maximum Baggage

Reference weight and balance data

Page 22 of 43

XVII - Model P210R
Fuel Capacity

3A21

(cont’d)
Std.: 90 gal. (87 gal. usable)
Two 45.0 gal. tanks in wings at +42.5
Opt.: 120 gal. (115 gal. usable)
Two 60.0 gal. tanks in wings at +42.5
See NOTE 1 for data on unusable fuel

Oil Capacity

10 qt. (-12.5), 8 qt. usable

Maximum Operating Altitude

25,000 ft.

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 25° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1°
(measured perpendicular to hinge line)

Serial Nos. Eligible

Model P210R:

Down
Down
Down
Down
Left
Left

30° +1°, -2°
15° ±2°
20° ±1°
15° ±1°
24° ±1°
27° 13' ±1°

P21000835 through P21000866 (1985 Model)
P21000867 through P21000874 (1986 Model)

XVIII - Model T210R, Turbo System Centurion, 6 PCLM (Normal Category), Approved December 4, 1984
Model 210R, Centurion, 6 PCLM (Normal Category), Approved December 20, 1984
Model 210R
Engine

Continental IO-520-L

*Fuel

100LL/100 minimum grade aviation gasoline

*Engine Limits

Takeoff full throttle (5 min.) at 2850 r.p.m. (300 hp. rating)
For all other operations, full throttle 2700 r.p.m. (285 hp. rating)

Propeller and
Propeller Limits

1. (a) McCauley D3A34C404/80VA-0
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 11.0°, high 27.0°
(b) Cessna spinner 1250419
(c) McCauley hydraulic governor C290D4/T4

*Airspeed Limits (IAS)
(See NOTE 4 on use of IAS)

Never exceed
200 knots
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

C.G. Range (Landing)
Gear Extended)

(+40.33) to (+52.0) at 3850 lb.
(+37.0) to (+52.0) at 3350 lb. or less
Straight line variation between points given
Moment change due to retracting landing gear (+2907 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

3850 lb.
3862 lb. ramp

No. of Seats

6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101)

167 knots
125 knots
115 knots
165 knots
200 knots

Page 23 of 43

XVIII - Model T210R, 210R
Maximum Baggage

3A21

(cont’d)
Reference weight and balance data

Fuel Capacity

Std.: 90 gal. (87 gal. usable)
Two 45.0 gal. tanks in wings at +42.5
Opt: 120 gal. (115 gal. usable)
Two 60 gal. tanks in wings at +42.5
See NOTE 1 for data on unusable fuel.

Oil Capacity

10 qt. (-12.5), 8 qt. usable

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 25° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1°
(measured perpendicular to hinge line)

Serial Nos. Eligible
Model T210R
Engine

Model 210R:

Down
Down
Down
Down
Left
Left

30° +1°, -2°
15° ±2°
20° ±1°
15° ±1°
24° ±1°
27° 13' ±1°

21064898 through 21064949 (1985 Model)
21064950 through 21065009 (1986 Model)

Continental TSIO-520-CE

*Fuel

100LL/100 minimum grade aviation gasoline

*Engine Limits

For all operations 2700 r.p.m., 37 in. Hg. mp. (325 hp.)

Propeller and
Propeller Limits

1. (a) McCauley D3A36C410/80VMB-0
Diameter: not over 80 in., not under 78.5 in.
Pitch settings at 30 in. sta.:
low 14.2°, high 36.5°
(b) Cessna spinner 2150150
(c) McCauley hydraulic governor C290D4/T2

*Airspeed Limits
(IAS)

Never exceed
203 knots
Maximum structural cruising
Maneuvering
Flaps extended
Landing gear operating speed
Landing gear extended speed

C.G. Range (Landing
Gear Extended)

(+42.0) to (+52.0) at 4100 lb.
(+37.0) to (+52.0) at 3350 lb.
Straight line variation between points given
Moment change due to retracting landing gear (+2907 in.-lb.)

Empty Wt. C.G. Range

None

*Maximum Weight

4100 lb. takeoff and flight
3900 lb. landing
4116 lb. ramp

No. of Seats

6 (2 at +34 to 46, 2 at +61 to +77, 2 at +101)

Maximum Baggage

Reference weight and balance data

167 knots
130 knots
115 knots
165 knots
200 knots

Page 24 of 43

Model T210R (cont’d)
Fuel Capacity

3A21

Std.: 90 gal. (87 gal. usable)
Two 45.0 gal. tanks in wings at +42.5
Opt: 120 gal. (115 gal. usable)
Two 60 gal. tanks in wings at +42.5
See NOTE 1 for data on unusable fuel

Oil Capacity

10 qt. (-12.5), 8 qt. usable

Control Surface
Movements

Wing flaps
Up 0°
Ailerons
Up 20° ±2°
Elevator
Up 25° ±1°
Elevator tab
Up 20° ±1°
Rudder
Right 24° ±1°
(measured parallel to 0.0 W.L.)
Rudder
Right 27° 13' ±1°
(measured perpendicular to hinge line)

Serial Nos. Eligible

Model T210R:

Data Pertinent to All Models
Datum

Fuselage station 0.0 (front face of firewall)

Down
Down
Down
Down
Left
Left

30° +1°, -2°
15° ±2°
20° ±1°
15° ±1°
24° ±1°
27° 13' ±1°

21064898 through 21064949 (1985 Model)
21064950 through 21065009 (1986 Model)

Leveling Means

Baggage compartment floor (except for 210-5(205) and 210-5A(205A)) Top of tailcone (except 210K/T210K/P210N and up, screws on left side tailcone)

Certification Basis

Models 210/210A: Part 3 of the Civil Air Regulations effective
May 15, 1956, with no amendments.
Models 210B, 210C, 210D, 210E, 210F, T210F, 210G, T210G, 210H, T210H,
210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, 210R,
210-5(205), 210-5A(205A): Part 3 of the Civil Air Regulations
effective May 15, 1956, and Paragraph 3.112 as amended October 1,
1959. FAR 36 dated December 1, 1969, plus Amendments 36-1 through
36-4 for Models 210M/T210M/210N/210R; Amendments 36-1 through 36-9 for
the T210N. In addition, FAR 23.1559 effective March 1, 1978, for
the Models 210N/T210N/210R.
Models P210N, P210R: Part 3 of the Civil Air Regulations dated
May 15, 1956, Paragraph 3.112 as amended October 1, 1959, and 23.365,
23.571, 23.775, 23.841, 23.843, 23.901, 23.909, 23.1041, 23.1043,
23.1143, 23.1305, 23.1325, 23.1441 and 23.1527 of FAR 23 effective
February 1, 1965, as amended to February 14, 1975. FAR 36 dated
December 1, 1969, plus Amendments 36-1 through 36-6 for P210N; Amendments
36-1 through 36-12 for P210R. Also FAR 23.1559 effective March 1, 1978,
for P21000151 and up. Also for P210R, FAR 23.1323 effective September 1,
1977, and FAR 23.1545 effective December 1, 1978.
Model T210R: Part 3 of the Civil Air Regulations dated May 15, 1956,
Paragraph 3.112 as amended October 1, 1959, and 23.901, 23.909, 23.1041,
23.1043, 23.1143, 23.1305 of FAR 23 effective February 1, 1965, as
amended to February 14, 1975; FAR 23.1323 effective September 1, 1977;
FAR 23.1545 effective December 1, 1978; and FAR 23.1559 effective
March 1, 1978; FAR 36 dated December 1, 1969, plus Amendments 36-1
through 36-12.
Compliance with ice protection has been demonstrated in accordance with
FAR 23.1419, as amended through Amendment 23-14, when ice protection
equipment is installed in accordance with the airplane equipment list
(Models P210N, T210N, P210R, and T210R only).

Page 25 of 43

Certification basis (cont’d)

3A21

Application for type certificate dated August 13, 1956.
Type Certificate No. 3A21 issued April 20, 1959, obtained by the
manufacturer under delegation option procedures.
Equivalent Safety Items (S/N 21061040 through 21064897 (T210 only),
and S/N P21000001 through P21000835)
Airspeed Indicator
Operating Limitations

CAR 3.757 (See NOTE 4 for effectivity)
CAR 3.778(a)
(210 S/N 21061040 through 21065009)
(T210 S/N 21061040 through 21064897)
(P210 S/N P21000001 through P21000834)

Airspeed Indicating System CAR 3.663
(210N, S/N 21062955 through 21064897)
(210R, S/N 21064898 through 21065009)
Production Basis

Equipment

Production Certificate No. 4. Delegation Option Manufacturer No. CE-1 authorized to
issue airworthiness certificates under delegation option provisions of Part 21 of the
Federal Aviation Regulations.
The basic required equipment as prescribed in the applicable airworthiness regulations
(see Certification Basis) must be installed in the aircraft for certification. This
equipment must include a current Airplane Flight Manual effective S/N 21062955 and
up and P21000151 and up. In addition, the following item of equipment is required:
1.

Stall warning indicator, Cessna Dwg. 0511062-4: S/N 21057001 through 21058818
S/N T210-0001 through T210-0197
Cessna Dwg. S-1672-1: S/N 21058819 and up
S/N T210-0198 through T210-0454
S/N P21000001 and up

NOTE 1.

Current weight and balance report including list of equipment included in certificated empty weight, and
loading instructions when necessary must be provided for each aircraft at the time of original certification.
The certificated empty weight and corresponding center of gravity location must include unusable fuel of
60 lb. at (+46) on Models 210 and 210A, 9 lb. at (+46) on the 210B, 210C, 210D, 210E, 210-5(205)
210-5A(205A); 12 lb. at (+46) on the 210F, T210F; and 6 lb. at (+23) on the 210G, T210G, 210H, T210H,
210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N through S/N's 21064535
and P21000760; and 18 lb. at (+38) on S/N's 21064536 and up, and P21000761 and up; and undrainable oil
of 0 lb. at (-19) through S/N 21061039 and full oil of 18.8 lb. at (-12.5) S/N 21061040 and up, and
S/N P21000001 and up.

NOTE 2.

The following placards must be displayed in locations as indicated:
A. Applicable to Models 210/210A
(1) In full view of the pilot:
(i) "This airplane must be operated as a normal category airplane in compliance with the
operating limitations as stated in the form of placards, markings and manuals. No acrobatic
maneuvers, including spins, approved. Maximum maneuvering speed - 130 m.p.h. - CAS.
Maximum design weight 2900 lb. Maximum flight maneuvering load factors - Flaps up +3.8,
-1.52; Flaps down +3.5. Maximum gear extension speed 160 m.p.h. - CAS. Maximum flap
extension speeds 10° flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. - CAS.
Before takeoff
1. Set tabs
2. Flaps 0°-20°
3. Check induction air-cold
4. Mixture rich
5. Propeller full in
6. Check cowl flaps open
7. Check fuel selector on fullest tank

Before landing
1. Gear down
2. Flaps down
3. Check induction air-cold
4. Mixture rich
5. Propeller full in
6. Check cowl flaps closed
7. Check fuel selector on fullest tank”

Page 26 of 43

NOTE 2. (cont’d)

or
(i)

3A21

“This airplane must be operated as a normal category airplane in compliance with the
operating limitations as stated in the form of placards, markings and manuals. No
acrobatic maneuvers, including spins, approved. Maximum maneuvering speed - 130 mph CAS. Maximum design weight 2900 lb. Maximum flight maneuver load factors - Flaps up
+3.8, -1.52; Flaps down +3.5. Maximum gear extension speed 160 mph - CAS. Maximum
flap extension speeds 10° flaps - 160mph - CAS; 10° - 40° flaps - 110 mph - CAS.
Before takeoff
1. Set tabs
2. Fuel selector full tank
3. Cowl flaps open
4. Mixture rich
5. Propeller full in
6. Flaps 0° -20°

Before landing
1. Gear down
2. Fuel selector full tank
3. Cowl flaps closed
4. Mixture rich
5. Propeller full in
6. Flaps down”

(2) On the control lock: "Control lock - remove before starting engine."
(3) On the upper pack cover: "To extend gear manually, place gear handle in full down position, pull
emergency handle and pump vertically."
(4) On fuel selector valve plate: "Both off. Left tank - 27.5 gal. Right tank 27.5 gal. Use full rich
mixture to switch tanks. Take off and land on fullest tank."
(5) On the baggage door: "Maximum baggage 120 lb. For additional loading instructions see weight
and balance data."
(6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130."
(7) On the instrument panel directly below the fuel gauge indicators: "Avoid landing approaches in
red arc and over 30 second slips under 1/2 tank. (Reference Owner's Manual)."
(8) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
B.

Applicable to Models 210B/210C
(1) In full view of the pilot:
"This airplane must be operated as a normal category airplane in compliance with the operating
limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers
including spins approved. Maximum maneuvering speed - 132 m.p.h. - CAS. Maximum design
weight 3000 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down
+3.5. Maximum gear extension speed 160 m.p.h. - CAS; Maximum flap extension speeds 10°
flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. - CAS.
Before Takeoff
1. Set tabs
2. Fuel selector
3. Cowl flaps open
4. Mixture rich
5. Propeller full in
6. Flaps 0°-20°

Before Landing
1. Gear down
2. Fuel selector full tank
3. Cowl flaps closed
4. Mixture rich
5. Propeller full in
6. Flaps down.”

(2) On the control lock: "Control lock - remove before starting engine."
(3) On the upper pack cover: "To extend gear manually, place gear handle in full down position, pull
emergency handle and pump vertically."

Page 27 of 43

3A21

(4) On fuel selector valve plate: "Both off. Left tank - 31.7 gal. Right tank - 31.7 gal. Use full rich
mixture to switch tanks. Take off and land on fullest tank."
(5) On the baggage door: "Maximum baggage 120 lb. For additional loading instructions see weight
and balance data."
(6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130."
(7) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
C.

Applicable to Model 210-5(205) and 210-5A(205A)
(1) In full view of the pilot:
"This airplane must be operated as a normal category airplane in compliance
with the operating limitations as stated in the form of placards, markings and
manuals. No acrobatic maneuvers including spins approved. Maximum
maneuvering speed - 138 m.p.h. - CAS. Maximum design weight 3300 lb.
Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down
+3.0; altitude load in stall recovery 200 ft.; Flap extension speed - 110 m.p.h. - CAS."
(2) On the control lock: "Control lock - remove before starting engine."
(3) On fuel selector valve plate: "Both off. Left tank - 31.7 gal.
Right tank - 31.7 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank."
(4) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130."
(5) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189013 FOR EXPANDED INSTRUCTIONS."

D.

Applicable to Models 210D/210E
(1) In full view of the pilot:
"This airplane must be operated as a normal category airplane in compliance
with the operating limitations as stated in the form of placards, markings and
manuals. No acrobatic maneuvers including spins approved. Maximum
maneuvering speed - 134 m.p.h. - CAS. Maximum design weight 3100 lb.
Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down
+3.5. Maximum gear extension speed 160 m.p.h. - CAS; Maximum flap
extension speeds 10°, flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. CAS; altitude loss in stall recovery 130 ft.
Before Takeoff
1. Set tabs
2. Fuel selector full tank
3. Cowl flaps open
4. Mixture rich
5. Propeller full in
6. Flaps 0°-20°

Before Landing
1. Gear down
2. Fuel selector full tank
3. Cowl flaps closed
4. Mixture rich
5. Propeller full in
6. Flaps down.”

(2) On the control lock: "Control lock - remove before starting engine."
(3) On the upper pack cover: "To extend gear manually, place gear handle in full
down position, pull emergency handle out and pump vertically."

Page 28 of 43

NOTE 2.

3A21

(4) On fuel selector valve plate: "Both off. Left tank - 31.7 gal.
Right tank - 31.7 gal. Use full rich mixture to switch tanks. Take off and land on fullest tank."
(5) On baggage door: "Maximum weight each child's seat, 140 lb. Refer to weight
and balance data for baggage/cargo loading."
(6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130."
(7) Above selector valve: "Turn pump on 'HI' when switching from a dry tank to a tank containing
fuel."
(8) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2
SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
E.

Applicable to Models 210F/T210F
(1) In full view of the pilot:
"This airplane must be operated as a normal category airplane in compliance
with the operating limitations as stated in the form of placards, markings and
manuals. No acrobatic maneuvers including spins approved. Maximum
maneuvering speed - 131.0 m.p.h. - CAS. Maximum design weight 3300 lb.
Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down
+3.0. Maximum gear extension speed 160 m.p.h. - CAS; Maximum flap
extension speeds 10° flaps - 160 m.p.h. - CAS; 10°-40° flaps - 110 m.p.h. CAS; Altitude loss in stall recovery 240 feet.
Before Takeoff
1. Set tabs
2. Fuel selector full tank
3. Cowl flaps open
4. Mixture rich
5. Propeller full in
6. Flaps 0°-20°

Before Landing
1. Gear down
2. Fuel selector full tank
3. Cowl flaps closed
4. Mixture rich
5. Propeller full in
6. Flaps down.”

(2) On control lock: "Control lock - remove before starting engine."
(3) On the power pack cover: "To extend gear manually, place gear handle in full
down position, pull emergency handle and pump vertically."
(4) On fuel selector valve plate: "Both off. Left tank - 31.5 gal. Right tank - 31.5
gal. Use full rich mixture to switch tanks. Take off and land on fullest tank."
(5) On baggage door: "Maximum weight each child's seat, 140 lb. Refer to weight
and balance data for baggage/cargo loading."
(6) On the fuel tank filler cap: "Tank capacity 32.5 U.S. gallons, 100/130."
(7) Above selector valve: "Turn pump on 'HI' when switching from a dry tank to
a tank containing fuel."

Page 29 of 43

NOTE 2. (cont’d)

3A21

(8) Near the engine power instruments: (T210F only)
*Altitude in Feet
Manifold
Fuel Flow
Sea Level to:
Pressure in. Hg.
Gal/Hr
19,000
32.5
28
20,000
31.5
26
22,000
29.5
24
24,000
27.5
22
26,000
25.5
20
28,000
23.5
19
30,000
21.5
18
75% power climb - 2500 r.p.m. - 27.5 manifold pressure - 20 g.p.h."
(9) On instrument panel above fuel boost pump switch:
"Use 'HI' for emergency only ↓."
(10) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
F.

Applicable to Models 210G, T210G, 210H, T210H, 210J, T210J
(1) In full view of the pilot:
"This airplane must be operated as a normal category airplane in compliance
with the operating limitations as stated in the form of placards, markings and
manuals. No acrobatic maneuvers, including spins, approved. Maximum
maneuvering speed - 135 m.p.h. - (CAS). Maximum design weight 3400 lb.
Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down
+3.0. Maximum gear extension speed - 160 m.p.h. - (CAS); Maximum flap
extension speeds 10° flaps - 160 m.p.h. - (CAS); 10°-30° flaps - 110 m.p.h. - (CAS);
Altitude loss in stall recovery 250 feet.
Before Takeoff
1. Set tabs
2. Fuel selector full tank
3. Cowl flaps open
4. Mixture rich
5. Propeller full in
6. Flaps 0°-20°

Before Landing
1. Gear down
2. Fuel selector full tank
3. Cowl flaps closed
4. Mixture rich
5. Propeller full in
6. Flaps down.”

(2) On control lock: "Control lock - remove before starting engine"
(3) On the power pack cover: "To extend gear manually, place gear handle in full
down position, pull emergency handle out and pump vertically."
(4) On fuel selector valve plate: "Both off. Left-44.5 gal. Right-44.5 gal. Use
full rich mixture to switch tanks. Take off and land on fullest tank."
(5) On baggage door: "Maximum weight each child's seat 140 lb. Refer to weight
and balance data for baggage/cargo loading."
(6) Aft of the filler cap on the adapter plate: "Tank capacity 45.0 U.S. gallons.
Service this airplane with 100/130 minimum grade aviation gasoline."

Page 30 of 43

NOTE 2. (cont’d)

3A21

(7) Above selector valve: "Turn pump on 'HI' when switching from a dry tank to
a tank containing fuel."
(8) Near the engine power instruments: (T210G/T210H/T210J)
*Altitude in Feet
Manifold
Fuel Flow
Sea Level to:
Pressure in. Hg.
Gal/Hr
19,000
32.5
28
20,000
31.5
26
22,000
29.5
24
24,000
27.5
22
26,000
25.5
20
28,000
23.5
19
30,000
21.5
18
75% power climb - 2500 r.p.m. - 27.5 manifold pressure - 20 g.p.h."
(9) On instrument panel above fuel boost pump switch:
"Use 'HI' for emergency only ↓."
(10) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
G.

Applicable to Model 210K/T210K (S/N 21059200 through 21059351)
(1) In full view of the pilot:
"This airplane must be operated as a normal category airplane in compliance with the operating
limitations as stated in the form of placards, markings and manuals. No acrobatic maneuvers,
including spins, approved. Maximum maneuvering speed - 135 m.p.h.(CAS). Maximum design
weight 3800 lb. Maximum flight maneuvering load factors - Flaps up +3.8, -1.52; Flaps down
+2.0. Maximum gear extension speed - 160 m.p.h.- (CAS); Maximum flap extension speed 10°
flaps - 160 m.p.h. - (CAS); 10°-30° flaps - 110 m.p.h. - (CAS); Altitude loss in stall recovery
300 feet.
Checklist Placard
Before Takeoff
Before Landing
1. Adjust trim controls
1. Fuel selector full tank
2. Fuel selector full tank
2. Gear down
3. Cowl flaps open
3. Cowl flaps closed
4. Mixture rich
4. Mixture rich
5. Propeller full in
5. Propeller full in
6. Flaps down.”
6. Flaps 0°-10°
(2) On control lock: "Control lock - remove before starting engine."
(3) On the power pack cover: "To extend gear manually, place gear handle in full
down position, pull emergency handle and pump vertically."
(4) On fuel selector valve plate: "Both off. Left on-44.5 gal. Right on -44.5 gal.
Take off and land on fuller tank."
(5) On baggage door: "Maximum baggage 120 lb. Refer to weight and balance
data for baggage/cargo loading."
(6) Aft of the filler cap on the adapter plate: "Tank capacity 45.0 U.S. gallons.
Service this airplane with 100/130 minimum grade aviation gasoline."

Page 31 of 43

NOTE 2. (cont’d) G.

3A21

(7) Above selector valve: "When switching from a dry tank turn pump on 'HI' momentarily."
(8) Above fuel flow and manifold pressure indicator: (Model 210K)
"Fuel flow at Full Throttle
2700 r.p.m.
Sea Level
23 gal/hr
4000 ft.
21 gal/hr
8000 ft.
19 gal/hr

2850 r.p.m.
24 gal/hr
22 gal/hr
20 gal/hr”

(9) Near the engine power instruments: (Model T210K)
*Altitude in Feet
Manifold
Fuel Flow
Sea Level to:
Pressure in. Hg.
Gal/Hr
19,000
32.5
28
20,000
31.5
26
22,000
29.5
24
24,000
27.5
22
26,000
25.5
20
28,000
23.5
19
30,000
21.5
18
75% power climb - 2500 r.p.m. - 27.5 manifold pressure - 20 g.p.h."
(10) On flap control indicator:
"a. 0°-10° - T.O. (Takeoff range with blue color code and 160 m.p.h.
callout; also mechanical detent at 10°)"
"b. 10°-20° - Full (Indices at these positions with white color code and
110 m.p.h. callout; also, mechanical detent at 20°."
(11) In plain view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS.”
H.

Applicable to Model 210K/T210K (S/N 21059352 through 21059502)
Applicable to Model 210L/T210L (S/N 21059503 through 21061039)
(1) In full view of the pilot:
(a) Applicable to Model 210K/T210K (S/N 21059352 through 21059502)
Applicable to Model 210L/T210L (S/N 21059503 through 21061039)
"This airplane must be operated as a normal category airplane in
compliance with the operating limitations as stated in the form of
placards, markings, and manuals.
MAXIMUMS
Maneuvering speed
135 m.p.h. CAS (117 knots)
Gear extension speed
160 m.p.h. CAS (139 knots)
Gross weight
3800 lbs.
Flight load factor
Flaps up +3.8, -1.52
Flaps down +2.0
No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery - 300 ft.
Known icing conditions to be avoided. This airplane is certificated for the following flight
operations as of date of original airworthiness certificate:
DAY - NIGHT - VFR - IFR" (As applicable)

Page 32 of 43

NOTE 2. (cont’d) H.

3A21

(1) (b) Applicable to Model 210L/T210L (S/N 21061040 and up)
"This airplane must be operated as a normal category airplane in accordance
with the operating limitations as stated in the form of placards, markings, and manuals.
MAXIMUMS
Maneuvering speed (IAS)
119 knots
Gear extension speed (IAS)
140 knots
Gross weight
3800 lbs
Flight load factor
Flaps up +3.8, -1.52
Flaps down +2.0
No acrobatic maneuvers, including spins, approved. Altitude loss in a stall
recovery - 300 ft. Flight into known icing conditions prohibited. This
airplane is certified for the following flight operations as of date of
original airworthiness certificate:
DAY - NIGHT - VFR - IFR" (As applicable)
Checklist Placard (Model 210K/T210K)(S/N 21059352 through 21059502)
Before Takeoff
1. Adjust trim controls
2. Fuel selector full tank
3. Cowl flaps open
4. Mixture rich
5. Propeller full in
6. Flaps 0°-10°

“Checklist Placard
Before Landing
1. Fuel selector full tank
2. Gear down
3. Cowl flaps closed
4. Mixture rich
5. Propeller full in
6. Flaps down.”

Checklist (Model 210L/T210L)(S/N 21059503 through 21060539)
(Stowed - not required for flight)
"Cessna 210L & T210L or Centurion & Centurion II (as applicable)
Checklist
Before Takeoff
Before Landing
1. Controls - free and correct
1. Fuel selector - fullest tank
2. Elevator and rudder trim - set
2. Landing gear - DN 160 m.p.h. max
3. Fuel seelctor - fullest tank
3. Mixture - rich
4. Cowl flaps - open
4. Propeller - high r.p.m.
5. Propeller - high r.p.m.
5. Airspeed - 100 m.p.h. flaps up
6. Mixture - as required
90 m.p.h. flaps down”
7. Flaps - 0° to 10°
8. Instruments - check and set
9. Seats and belts - secure
(2) On control lock: "Control lock - remove before starting engine."
(3) On the power pack cover: (210K/T210K) (S/N 21059200 through 21059502)
To extend gear manually, place gear handle in full down position, pull emergency handle out and
pump vertically."
On hand pump cover: (210L/T210L) (S/N 21059503 and up)
"Manual gear extension: 1. select gear down; 2. pull handle forward; 3. pump vertically."
(4) On fuel selector valve plate: "Off. Left on -44.5 gal.
Right on -44.5 gal. Takeoff and land on fuller tank."
(5) On baggage door: "Maximum baggage 120 lb. Refer to weight and balance data for
baggage/cargo loading."

Page 33 of 43

NOTE 2. (cont’d) H.

3A21

(6) Aft of the filler cap on the adapter plate: "Service this airplane with 100/130 minimum aviation
grade gasoline. Total capacity 45.0 gal."
(7) Above fuel selector valve: "When switching from dry tank, turn pump on 'HI' momentarily"
(210L/T210L) (S/N 21059503 through 21060089)
Above fuel selector valve: "When switching from dry tank, turn Auxiliary fuel pump 'ON'
momentarily" (210L/T210L) (S/N 21060090 and up).
(8) In front of pilot on lower instrument panel knee pad: "Alternate static air ↓ on."
(9) Above ammeter: "Do not turn off alternator in flight except in emergency." (Model 210K/T210K)
(S/N 21059200 through 21059502)
(10) Adjacent to overvoltage light: "High voltage" (Models 210L/T210L)
(S/N 21059503 and up)
(11) Above left fuel gauge: "Do not turn off alternator in flight except in emergency." (Models
210L/T210L) (S/N 21059503 through 21059719)
(12) Above fuel flow and manifold pressure indicator:
(Model 210K/210L)
"Fuel flow at full throttle
S.L.
400 ft.
8000 ft.

2700 r.p.m.
138 lbs/hr
126 lbs/hr
114 lbs/hr

2850 r.p.m.
144 lbs/hr
132 lbs/hr
120 lbs/hr”

(13) Near the engine power instruments
(Models T210K/T210L)
"Max. allowable manifold press. & climb fuel flow
Alt.-ft/1000
SL-19
20
22
24
26
M.P.-In. Hg.
32.5
31.5
29.5
27.5
25.5
Fluel flow-lbs/hr
168
156
144
132
120
75% power climb - 2500 r.p.m., 27.5 in. M.P., 120 lbs/hr"

28
23.5
114

30
21.5
108

(14) On lower surface of right hand wing just outboard of fuselage:
"Oxygen filler door." (All models with oxygen)
(15) On flap control indicator: (210K/T210K) (S/N 21059352 through 21059502)
"a. 0°-10° (Takeoff range with blue color code and 160 m.p.h. callout; also mechanical detent
at 10°)"
b.

10°-20° Full (Indices at these positions with white color code and 110 m.p.h. callout; also
mechanical detent at 20°)"

On flap control indicator: (210L/T210L) (S/N 21059503 through 21061039)
"a. 0°-10° (Takeoff range with blue color code and 160 m.p.h. callout; also mechanical detent
at 10°)"
b.

10°-20° Full (Indices at these positions with white color code
120 m.p.h. callout; also mechanical detent at 20°)"

Page 34 of 43

3A21

NOTE 2. (cont’d) H. (15) On flap control indicator: (210L/T210L) (S/N 21051040 and up)
"a. 0°-10°
(Takeoff range with blue color code and 140 knots callout; also mechanical
detent at 10°)"
b. 10°-20° - Full (Indices at these positions with white color code and 105 knots callout; also
mechanical detent at 20°)"
(16) On inside nose wheel doors:
"WARNING - before working in wheel well area pull hydraulic pump circuit breaker off." (Model
210L/T210L) (S/N 21059503 and up)
(17) In full view of the pilot:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
J.

Applicable to Model 210M/T210M, 210N/T210N, 210R/T210R
(1) In full view of the pilot:
(a) Applicable to Model 210M/T210M (S/N 21061574 through 21062273)
"This airplane must be operated as a normal category airplane in
compliance with operating limitations as stated in the form of placards,
markings and manuals.
MAXIMUMS
Maneuvering speed (IAS)
119 knots
Gear extension speed (IAS)
140 knots
Gross weight
3800 lbs.
Flight load factor
Flaps up +3.8, -1.52
Flaps down +2.0
No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery - 300 ft.
Flight into known icing conditions prohibited. This airplane is certified for the following
flight operations as of date of original airworthiness certificate:
DAY - NIGHT - VFR - IFR" (As applicable)
(b) Applicable to Model 210M/T210M (S/N 21061042, 21062274 through 21062954
"This airplane must be operated as a normal category airplane in compliance with the
operating limitations as stated in the form of placards, markings and manuals.
MAXIMUMS
Maneuvering speed (IAS)
Gross weight
Flight load factor
Flaps up
Flaps down

119 knots
3800 lbs.
+3.8, -1.52
+2.0

No acrobatic maneuvers, including spins, approved. Altitude loss in a stall recovery 300 ft.
Flight into known icing conditions prohibited. This airplane is certified for the following
flight operations as of date of original airworthiness certificate:
DAY - NIGHT - VFR - IFR" (As applicable)
(c) Applicable to Models 210N/T210N (S/N 21062955 through 21064535)
"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 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.
No acrobatic maneuvers, including spins, approved.
Flight into known icing conditions prohibited.

Page 35 of 43

NOTE 2. (cont’d) J.

3A21

(1) (c) This airplane is certified for the following flight operations as of date of original airworthiness
certificate:
DAY - NIGHT - VFR - IFR" (As applicable)
(2) On control lock through 21064535: "Control Lock - Remove Before Starting Engine."
(3) On the hand pump cover:
(S/N 21061574 through 21062273)
"Manual gear extension: 1. Select gear down; 2. pull handle forward; 3. pump vertically."
(S/N 21061042, 21062274 through 21064535)
"Manual gear extension: 1. Select gear down; 2. pull handle forward; 3. pump vertically.
CAUTION: Do not pump with gear up selected"
(4) On fuel selector valve plate through 21064535:
"Off. Left on - 44.5 gal. Right on - 44.5 gal.
Takeoff and land on fuller tank."
(5) 210M/T210M (S/N 21061042, 21061574 through 21062954)
On baggage door: "Maximum baggage 120 lb. Refer to weight and balance data for
baggage/cargo loading."
210N/T210N (S/N 21062955 through 21064535)
On baggage door: "Maximum baggage 200 lbs. total. Refer to weight and balance data for
baggage/cargo loading."
(6) Near the wing filler caps:
(S/N 21061574 through 21062273)
"Service this airplane with 100/130 minimum aviation grade gasoline. Total capacity 45.0 gal."
(S/N 21061042, 21062274 through 21064535)
"Service this airplane with 100LL/100 minimum aviation grade gasoline. Total capacity 45.0 gal."
(7) Near fuel selector valve through 21064535:
"When switching from dry tank, turn auxiliary fuel pump on momentarily."
(8) In front of pilot on lower instrument panel:
(S/N 21061574 through 21062273)
"Alternate static air ↓ pull on."
(S/N 21061042, 21062274 through 21064535)
"Alternate static air pull on."
(9) 210M/T210M (S/N 21061042 through 21062954)
Adjacent to overvoltage light: "High Voltage."
210N/T210N (S/N 21062955 through 21064535)
Adjacent to low voltage light: "Low Voltage"
(10) Near the engine power instruments (Model 210M, S/N 21061574 through
21062954):
"Fuel Flow at Full Throttle
2700 r.p.m.
2850 r.p.m.
S.L.
138 lbs/hr
144 lbs/hr
400 ft.
126 lbs/hr
132 lbs/hr
8000 ft.
114 lbs/hr
120 lbs/hr”
"Max. power setting
Takeoff (5 min. only) 2850 r.p.m.
Max. continuous power 2700 r.p.m."

Page 36 of 43

NOTE 2. (cont’d) J.

3A21

(10)
Near the engine power instruments (Model 210N, S/N 21062955 through 21064535:
"Min. Fuel Flows at Full Throttle
2700 r.p.m.
2850 r.p.m.
S.L.
138 lbs/hr
144 lbs/hr
4000 ft.
126 lbs/hr
132 lbs/hr
8000 ft.
114 lbs/hr
120 lbs/hr
12000 ft.
102 lbs/hr
108 lbs/hr”
(11) Near the engine power instruments (T210M):
(S/N 21061574 through 21062273)
"Maximum power setting & fuel flow
T.O. (5 min. only): 2700 r.p.m. Normal climb: 2500 r.p.m.
36.5 in. mp., 186 lbs/hr
30.0 in. mp., 126 lbs/hr
Max. continuous power: 2600 r.p.m.
Alt.-ft/1000
SL-17
18
M.P.-In. Hg.
35
34
Fluel flow-lbs/hr
162
156

20
32
144

22
30
132

24
28
120

26
26
108

28
24
102

30
22
96”

"Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. M.P."
(S/N 21061042, 21062274 through 21062953)
"Maximum power setting & fuel flow
T.O. (5 min. only): 2700 r.p.m.
Normal climb: 2500 r.p.m.
36.5 in. mp., 186 lbs/hr
30.0 in. mp., 120 lbs/hr
Max. continuous power: 2600 r.p.m.
Alt.-ft/1000
SL-17
18
20
22
24
26
M.P.-In. Hg.
35
34
32
30
28
26
Fluel flow-lbs/hr
162
156
144
132
120
108

28
24
102

30
22
96”

"Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. M.P."
Near the engine power instruments (T210N, S/N 21062955 through 21064535):
"Minimum Fuel Flows
T.O.: 2700 r.p.m.
36.5 in. mp., 186 lbs/hr
Maximum continuous power: 2600 r.p.m.
Alt.-ft/1000
SL-17
18
20
22
24
26
28
M.P.-In. Hg.
35
34
32
30
28
26
24
Fluel flow-lbs/hr
162
156
144
132
129
108
102

30
22
96”

"Avoid continuous operation between 1850 and 2150 r.p.m. above 24 in. M.P."
(12) On lower surface of right hand wing just outboard of fuselage through 21064535:
“Oxygen filler door." (All models with oxygen.)
(13) On flap indicator:
(S/N 21061574 through 21062273)
a. "0° - 10° - (Partial flap range with blue color code and 140 knots callout; also, mechanical
detent at 10°)"
b. "10°- 20° - Full - (Indices at these positions with white color code and 105 knots callout;
also, mechanical detent at 20°)"

Page 37 of 43

3A21

NOTE 2. (cont’d) J. (13) (S/N 21061042, 21062274 through 21063640)
a. "0° - 10° - (Partial flap range with blue color code and 150 knots callout; also, mechanical
detent at 10°)"
b. "10°- 20° - Full - (Indices at these positions with white color code and 115 knots callout; also,
mechanical detent at 20°)"
(S/N 21063641 through 21064535)
a. "0° - 10° - (Partial flap range with dark blue color code and 160 knot callout; also, mechanical
detent at 10°)"
b. "10°- 20° - (Indices at these positions with light blue color code and 130 knot callout; also,
mechanical detent at 10°)"
c. "20°- 30° - (Indices at these positions with white color code and 115 knot callout)"
(14) On inside nose wheel doors, strut doors and main wheel doors through 21062954 and on inside of
nose wheel doors S/N 21064535: "Warning - Before working in the wheel well area pull hydraulic
pump circuit breaker off."
(15) Applicable to the Model 210M:
Near the gear selector handle:
"Maximum speed IAS
Gear oper.
140 knots
Gear down
199 knots"
(16) Applicable to the Model T210M:
Near the gear selector handle:
"Maximum speed IAS
Gear oper.
140 knots
Gear down
195 knots"

(S/N 21062274 through 21062954)

(S/N 21061042, 21062274 through 21062953)

(17) Applicable to the Model 210N: (S/N 21062955 through 21064535)
Near the gear selector handle:
"Maximum speed IAS
Gear oper.
165 knots
Gear down
200 knots"
(18) Applicable to the Model T210N: (S/N 21062955 through 21064535)
Near the gear selector handle:
"Maximum speed IAS
Gear oper.
165 knots
Gear down
203 knots"
(19) Near the airspeed indicator
(a) Model 210N (S/N 21062955 through 21064535)
"Maneuver Speed 125 KIAS"
(b) Model T210N (S/N 21062955 through 21064535)
"Maneuver Speed 130 KIAS"
(20) Near the fuel cap
Models 210N/T210N (S/N 21062955 through 21063640)
"For 32 gal. fuel load fill to bottom of filler neck extension."
Models 210N/T210N (S/N 21063641 through 21064535)
"Capacity 33.5 gallons to bottom of filler neck extension."

Page 38 of 43

3A21

NOTE 2. (cont’d) J. (21) Near the oil filler
Models 210N/T210N (S/N 21062955 through 21064135)
"Oil 10 qts."
(22) On the nose gear strut
Models 210N/T210N (S/N 21062955 through 21064135)
"WARNING
Release air and fluid pressure before removing any part of this assembly."
(23) In full view of the pilot:
(a) Models 210M/T210M (S/N 21061574 through 21062954)
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
(b) Model 210N (S/N 21062955 through 21063640)
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2 SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE P.O.H. FOR EXPANDED INSTRUCTIONS."
(c) Model T210N (S/N 21062955 through 21064535)
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON, ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE P.O.H. FOR EXPANDED INSTRUCTIONS."
(24) Effective S/N 21064536 and up:
"All placards required in the Pilot's Operating Handbook and FAA Approved
Airplane Flight Manual must be installed in the appropriate locations."
K.

Applicable to Model P210N and P210R
(1) In full view of the pilot:
Model P210N (S/N P21000001 through P21000150)
"This airplane must be operated as a normal category airplane in compliance with the operating
limitations as stated in the form of placards, markings and manuals.
MAXIMUMS
Operating altitude
Maneuvering speed (IAS)
Gross weight
Takeoff
Landing
Flight load factor
Flaps up
Flaps down

23,000 ft.
130 knots
4000 lbs.
3800 lbs.
+3.8, -1.52
+2.0

No acrobatic maneuvers, including spins, approved. Landing with cabin pressurized is prohibited.
Altitude loss in a stall recovery - 300 ft. Flight into known icing conditions prohibited. This
airplane is certified for the following flight operations as of date of original airworthiness
certificate:
DAY - NIGHT - VFR - IFR" (As applicable)

Page 39 of 43

NOTE 2. (cont’d) K. (1)

3A21

Model P210N (S/N P21000151 and up)
"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
Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.
No acrobatic maneuvers, including spins, apaproved.
Landing with cabin pressurized is prohibited.
Flight into known icing conditions prohibited.
This airplane is certified for the following flight operations as of date of original airworthiness
certificate:
DAY - NIGHT - VFR - IFR" (As applicable)

(2) On control lock through P21000760: "Control Lock - Remove Before Starting Engine."
(3) On the hand pump cover through P21000760:
"Manual gear extension: 1. Select gear down; 2. pull handle forward;
3. pump vertically. CAUTION: Do Not Pump With Gear Up Selected."
(4) On fuel selector valve plate through P21000760: "Off. Left on - 44.5 gal., Right on - 44.5 gal.,
Takeoff and land on fuller tank"
(5) On baggage door through P21000760:
"Maximum baggage 200 lbs. total. Raised area aft of baggage door 80 lbs. maximum.
Refer to weight and balance data for baggage cargo loading."
(6) Near the wing filler caps through P21000760: "Service this airplane with 100LL/100 minimum
aviation grade gasoline. Total capacity 45.0 gal."
(7) Near fuel selector valve through P21000760: "When switching from dry tank, turn auxiliary fuel
pump on momentarily."
(8) P210N (S/N P21000001 through P21000150)
Adjacent to over voltage light: "HIGH VOLTAGE"
P210N (S/N P21000151 through P21000760)
Adjacent to low voltage light: "LOW VOLTAGE"
(9) Near the engine power instruments through P21000760:
“Minimum Fuel Flows
TAKEOFF
MAX. CONTINUOUS POWER: 2600 RPM
2700 R.P.M.
ALT-FT/1000
SL-17
18
19
20
21
36.5 In.M.P
M.P. IN. HG.
35.5
34.5
33.5
32.5
31.5
180 LBS/HR Fuel Flow - lbs/hr
162
156
150
144
138

22
30.5
132

23
29.5
126”

(10) On flap indicator:
P210N (S/N P21000001 through P21000385)
a. "0° - 10° - (Partial flap range with dark blue color code and 150 knots callout; also,
mechanical detent at 10°)"
b. "10°- 20° - Full - (Indices at these positions with white color code and 115 knot callout; also,
mechanical detent at 20°)"
P210N (S/N P21000386 through P21000760)
a. "0° - 10° - (Partial flap range with dark blue color code and 160 knot callout; also,
mechanical detent at 10°)"
b. "10°- 20° - Full - (Indices at these positions with light blue color code and 130 knot callout;
also, mechanical detent at 20°)"
c. "20°- 30° - (Indices at these positions with white color code and 115 knot callout)"
(Full)

Page 40 of 43

NOTE 2. (cont’d) K. (11) On inside nose wheel doors, strut doors and main wheel doors:
"Warning - Before working in wheel well area pull hydraulic pump circuit breaker off."
(12) Near the gear selector handle:
P210N (S/N P21000001 through P21000150)
"Maximum speed IAS
Gear oper.
140 knots
Gear down
200 knots"
P210N (S/N P21000151 through P21000760)
"Maximum speed IAS
Gear oper.
165 knots
Gear down
200 knots"
(13) Near the pilot's outside door handle through P21000760:
"Close
Open

"

(14) Near the emergency button to unlock the pilot's cabin door from the outside
through P21000760:
"Emergency
Push to unlock"
(15) Near the secondary lock for the inside pilot's door handle through P21000760:
“Door Handle Safety Lock
Push Flush to Lock
Pull To Unlock"
(16) Near the pilot's inside door handle through P21000760:
"Close
Open ←→ Lock"
(17) Near the right exit handle through P21000760:
"Open ←→ Close ←→ Latch
Push Flush
to Lock
Close and Lock for Flight"
(18) Near the airspeed indicator:
P210 (S/N P21000151 through P21000760)
"Maneuver Speed - 130 KIAS"
(19) Near the oil filler:
P210N (S/N P21000151 through P21000760)
"Oil 10 qts"
(20) Near the fuel cap:
P210N (S/N P21000151 through P21000760)
"For 32 gal. fuel load fill to bottom of filler neck extension."
(21) On emergency exit through P21000760:
"Emergency Exit - To Open
1. Lift handle (Do not pull inward)
2. Rotate counter clockwise to 'OPEN' position
3. Push door outward"

3A21

Page 41 of 43

3A21

NOTE 2. (cont’d) K. (22) On the main cabin door through P21000760:
"Door Handle Safety Lock
Push Flush To Lock
Pull to Unlock"
And
"To Open Door
1. Unlock safety lock (pull out)
2. Rotate handle to 'OPEN' position
3. Push door outward"
(23) In full view of the pilot:
S/N P21000001 through P21000150
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE PROCEDURE CARD D1189-13 FOR EXPANDED INSTRUCTIONS."
S/N P21000151 through P21000760:
"MAJOR FUEL FLOW FLUCTUATIONS/POWER SURGES
1. AUX FUEL PUMP ON ADJUST MIXTURE
2. SELECT OPPOSITE TANK
3. WHEN FUEL FLOW STEADY, RESUME NORMAL OPERATIONS
SEE P.O.H. FOR EXPANDED INSTRUCTIONS."
(24) When equipped with optional EGT gauge: - On the left forward side panel near instrument panel
(S/N P21000001 through P21000150):
"EGT LIMITATION
USE OF EGT GAUGE IS PROHIBITED
AT ALL R.P.M. SETTINGS ABOVE 2500
R.P.M. AT ALL ALTITUDES"
(25) When equipped with optional EGT gauge: - On the left side panel near
instrument panel (S/N P21000001 through P21000150):
"EGT LIMITATIONS
USE OF EGT GAUGE IS PROHIBITED AT ALL POWER SETTINGS
ABOVE 80% AT ALL ALTITUDES; OR ABOVE THE FOLLOWING
POWERS AT THE LISTED ALTITUDES WHEN OAT IS ABOVE STANDARD.
75% AT 17,000 FEET OR HIGHER
70% AT 20,000 FEET OR HIGHER
65% AT 22,000 FEET OR HIGHER
CONTINUOUS OPERATION LEANER THAN SHOWN IN THE TABLE IS PROHIBITED."
EXHAUST GAS TEMPERATURE (°F RICH OF PEAK)
POWER
2500 R.P.M.
2400 R.P.M.
76 to 80%
100%
75%
71 to 75%
75°
75°
66 to 70%
75°
50°
61 to 65%
50°
50°
56 to 60%
50°
25°
51 to 55%
25°
25°
46 to 50%
Peak EGT
25°
45% or less
Peak EGT
Peak EGT

2300 R.P.M.
75%
50°
50°
25°
25°
Peak EGT
Peak EGT
Peak EGT

2200 R.P.M.
50%
50°
25°
25°
Peak EGT
Peak EGT
Peak EGT
Peak EGT
2105030-1

Page 42 of 43

NOTE 2.

K. (26) Effective P21000761 and up:
"All placards required in the Pilot's Operating Handbook and FAA Approved Airplane
Flight Manual must be installed in the appropriate locations."

NOTE 3.

The cylinder head thermistors must be installed as follows:
Model
210, 210A
210B, 210C, 210D
210E,210F,210G,210H,210J
210F,T210G,T210H,T210J
210K
T210K
210L
T210L
T210L
210M
210M
T210M
P210N
210N
T210N
T210N
T210N
P210N
210N, 210R
210N, 210R
T210N
P210R, T210R

NOTE 4.

Cylinder Head Number
(1960-61 Model)
3
(1962-63-64 Model)
1
(1965-66-67-68-69 Model)
2
(1966-67-68-69 Model)
5
(1970-71 Model)
3
(1970-71 Model)
5
(1972-73-74-75-76 Model)
3
(1972-73 Model)
5
(1974-75-76 Model)
1
(1977 Model)
3
(1978 Model)
1
(1977-78 Model)
1
(1978-81 Model)
5
(1979-81 Model)
1
(1979 Model)
1
(1980-81 Model)(Non-Air Cond)
5 or 1
(1980-81 Model)(With Air Cond)
1
(1982-83 Model)
4
(1982 Model and up)(Non Air Cond)
4
(1982 Model and up)(With AirCond)
1
(1982 Model and up)
3
(1985 Model and up)
1

The marking of the airspeed indicator with I.A.S. provides an equivalent level of safety
to CAR 3.757 when the approved airspeed calibration data presented in Section V of the
Pilot's Operating Handbooks listed below is available to the pilot:
210L
Cessna P/N D1069-13 (S/N 21061040 through 21061573)
T210L
Cessna P/N D1070-13 (S/N 21061040 through 21061573 except 21061042)
210M
Cessna P/N D1094-13 (S/N 21061574 through 21062273)
T210M
Cessna P/N D1095-13 (S/N 21061574 through 21062273)
210M
Cessna P/N D1122-13 (S/N 21062274 through 21063954)
T210M
Cessna P/N D1123-13 (S/N 21061042, 21062274 through 21062954)
P210N
Cessna P/N D1124-13 (S/N P21000001 through P21000150)
210N
Cessna P/N D1151-13PH (S/N 21062955 through 21063640)
T210N
Cessna P/N D1152-13PH (S/N 21062955 through 21063640)
P210N
Cessna P/N D1153-13PH (S/N P21000151 through P21000385)
210N
Cessna P/N D1186-13PH (S/N 21063641 through 21064135)
T210N
Cessna P/N D1187-13PH (S/N 21063641 through 21064135)
P210N
Cessna P/N D1188-13PH (S/N P21000386 through P21000590)
210N
Cessna P/N D1207-13PH (S/N 21064136 through 21064535)
T210N
Cessna P/N D1208-13PH (S/N 21064136 through 21064535)
P210N
Cessna P/N D1209-13PH (S/N P21000591 through P21000760)
210N
Cessna P/N D1226-13PH (S/N 21064536 through 21064772)
T210N
Cessna P/N D1227-13PH (S/N 21064536 through 21064772)
P210N
Cessna P/N D1228-13PH (S/N P21000761 through P21000811)
210N
Cessna P/N D1244-13PH (S/N 21064773 through 21064822)
T210N
Cessna P/N D1245-13PH (S/N 21064773 through 21064822)
P210N
Cessna P/N D1246-13PH (S/N P21000812 through P21000834)
210N
Cessna P/N D1265-13PH (S/N 21064823 through 21064897)
T210N
Cessna P/N D1266-13PH (S/N 21064823 through 21064897)
210R
Cessna P/N D1288-13PH (S/N 21064898 through 21065009)

3A21

Page 43 of 43

NOTE 5.

3A21

Service information applicable to Models P210N and P210R:
Components subject to the establishment of a retirement life as shown below with the corresponding
retirement life hours:
Component Name
Windshield, rear cabin top windows
Side windows, and ice detector light lens

NOTE 6.

Retirement Hours
13,000 hours

14-volt electrical system
(210/T210 series through S/N 21059502)
(205 series through S/N 205-0577)
28-volt electrical system
(210/T210 series effective S/N 21059503 and up)
(P210 series effective S/N P21000001 and up)

In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Sections I
through XVIII of this data sheet must also be displayed by permanent markings.

“WARNING: Use of alcohol-based fuels can cause serious performance degradation and fuel
system component damage, and is therefore prohibited on Cessna airplanes.”

...END...



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