Honeywell RMA-55B Localizer/Glideslope/Receiver User Manual 1276

Honeywell International Inc. Localizer/Glideslope/Receiver 1276

8

Download:
Mirror Download [FCC.gov]
Document ID	1276
Application ID	budwfbSq96H8ogjP9DrIVQ==
Document Description	8
Short Term Confidential	No
Permanent Confidential	No
Supercede	No
Document Type	User Manual
Display Format	Adobe Acrobat PDF - pdf
Filesize	136.76kB (1709464 bits)
Date Submitted	1998-05-08 00:00:00
Date Available	1998-06-29 00:00:00
Creation Date	2001-07-17 14:24:07
Producing Software	Acrobat Distiller 4.0 for Windows
Document Lastmod	2001-07-17 14:24:13
Document Title	1276.pdf
Document Author:	jsoscia

RMA-55B
Multi—Mode Receiver
System
Maintenance Manual
34-55-50
LB. 1155
y%
Coverage Deﬁned on the Title Page
QIIiedSignal Electronic & Avionics Systems
AEROSPAL’L‘
AlliedSignal Electronic and Avionics Systems
Maintenance Manual
RMA-SSB
Multi-Mode Receiver System
1.8.1155 34_55_5O Marks];
AlliedSignaI EIecﬁ-onic and Avionics Syslems
NOTE
IF ANY UNUSUAL OR SPECIAL SERVICE PROBLEMS ARISE,
CONTACT ALLIEDSIGNAL ELECTRONIC AND AVIONICS SYSTEMS
CUSTOMER SUPPORT DEPARTMENT.
PROPRIETARY NOTICE
This document contains proprietary information
and such information may not be disclosed to
others for any purpose, nor used for manufac—
turing purposes without written permission
from AlliedSignaI Inc.
PN—l
34'55‘50 No Date
Alliedsignal Electronic and Avionics Systems
RNA-558 MULTI~MDDE RECEIVER SYSTEM
RECORD OF REVISIONS
MAINTENANCE MANUAL
f'“
REV. n
um
vasioN
DATE
DATE
lNSEﬂTED
REV.
BY um
REVISION
DATE
DATE
INSERTED
_L
I.
av_|
___|_
+__l__
__l_
_]
I___
.B.
1155
34—55-50
RR—l
No Date
AlliedSignaI Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA»SSB MULTI—MOJE RECEIVER SVSTEM
RECORD OF REVISIONS
REVI REVISION DATE REV. REVISION DATE
N0. DAVE INSERTED av ND. DATE INSERIED Bv
_i
— —I —|
III
1.541155 34_55_5O No Siii
AlliedSignal Electronic and Avionitx Systems
MAINTENANCE MANUAL
RNA-558 MULTI-MODE RECEIVER SYSTEM
LIST OF EFFECTIVE PAGES
SUBJECT PAGE DATE SUBJECT PAG DATE
TitTe Page T—l Mar/98 24 Mar/98
25 Mar/98
Proprietary PN—l No Date 26 Mar/98
Notice 27 Mar/98
28 Blank
Record of RR-I No Date
Revisions RR—Z No Date FauTt 1501 ation 101 Mar/98
102 Mar/98
List of LEP—l Mar/98 103 Mar/98
Effective LEP-Z Mar/98 104 Mar/98
Pages 105 Mar/98
106 Mar/98
TabTe of TC-I Mar/BB 107 Mar/98
Contents TC—2 BTank 108 Mar/98
109 Mar/98
Introduction INTRO»1 Mar/98 110 Mar/98
11] Mar/98
Description 0 Mar/98 112 Mar/98
and Operation 1 Mar/98 113 Mar/98
2 Mar/98 114 Mar/98
3 Mar/98 115 Mar/98
4 Mar/98 116 Mar/98
S Mar/98 117 Mar/98
6 Mar/98 118 BTank
7 Mar/98
8 Mar/98 Maintenance 201 Mar/98
9 Mar/98 Practices 202 Mar/98
10 Mar/98 203 Mar/98
11 Mar/98 204 Mar/98
12 Mar/98 205 Mar/98
13 Mar/98 206 Mar/98
14 Mar/98 207 Mar/98
15 Mar/98 208 Mar/98
16 Mar/98 209 Mar/98
17 Mar/98 210 Mar/98
18 Mar/98 211 Mar/98
19 Mar/98 212 Mar/98
20 Mar/98 213 Mar/98
21 Mar/98 214 Mar/98
22 Mar/98 215 Mar/98
23 Mar/98 216 Mar/98
* INDICATES PAGES REVISED, ADDED OR DELETED IN LATEST REVISION
F INDICATES FOLDOUT PAGES — PRINT ONE SIDE ONLV
LEP~1
1.5.1155 34—55—50 Mar/98
AlliedSignal Eledmnic and Avionics Systems
MAINTENANCE MANUAL
RMA-SSB MULTI-MODE RECEIVER SYSTEM
TABLE OF CONTENTS
ParagraphzTitTe 533
DESCRIPTION AND OPERATION ....................... I
FAULT ISOLATION ........................... 101
MAINTENANCE PRACTICES ........................ 20]
IB. 1155 TC—I/TC»2
34-55—50 Mar/98
LB.
1155
AIiiedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA-558 MULTI—MODE RECEIVER SYSTEM
INTRODUCTION
This manuai, 1.8. 1155 (34—55-50), contains
information covering description and operation,
instaiiation, and checkout procedures for the
AiiiedSignai Electronic and Avionics Systems
RMA—SSB Muiti—Mode Receiver System.
34—55—50
INTRO—1
Mar/98
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTI—MODE RECEIVER SYSTEM
59:5
022;
E 23.3
3.6 222
258 322
32: 852/
82:3 255
8.53 222
23.5 282
322 203;
322 2a
238
252
0100700]
RMAVSSB Mu1ti—Mode Receiver
Figure 1
3455-50
Page 0
Mar/98
1155
1.8.
I.
1.8.
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI-MODE RECEIVER SYSTEM
DESCRIPTION AND OPERATION
General
This section contains descriptive information covering the RMA»55I3
Multi-Mode Receiver System, and lists other components required for
system operation. The RMA—SSB Multi-Mode Receiver (MMR) is illustrated
in figure 1.
A.
Purpose of Equipment
The RNA—558 Multi—Mode Receiver (MMR) meets industry defined sensor
requirements for Category III Instrument Landing Systems (ILS),
including requirements for ICAO Annex 10 FM Immunity, and Global
Navigation Satellite Sensor (GNSS) enroute navigation and
non—precision approaches.
The instrument landing system (ILS) function of the MMR consists of
a VHF localizer receiver and a UHF glidevslope receiver, and the
global navigation satellite sensor (GNSS) function consists of the
GNSS receiver. These receivers are used in conjunction with three
antennas (localizer, glide slope, and Leband GNSS), a control head,
and the cockpit displays [course deviation indicator (C01) and
horizontal situation indicator (HSI)].
The primary purpose of the ILS circuitry is to provide lateral
(localizer) and vertical (glide slope) guidance information. This
information is provided via ARINC 429 interfaces to the aircraft
Automatic Flight Control System (AFCS) and instrument systems during
manual and automatically controlled approaches and landings. The
MMR also provides an aural output for the ILS ground station
identification.
The primary purpose of the GNSS receiver is to provide GNSS enroute
navigation and non-precision approach information: latitude and
longitude.
The RMA—SSB MultifMode Receiver (MMR) design conforms to industry
standards Aeronautical Radio Incorporated (ARINC) 755 Multi—Mode
Receiver Characteristics and ARINC 743A—2 Global Positioning System
Receiver Characteristics, Radio Technical Commission for Aeronautics
(RTCA) document numbers DO—192 Minimum Operational Performance
Standards (MOPS) for Airborne ILS Glide Slope Receiving Equipment
Operating Within the Radio Frequency Range of 328.60 — 335.40 MHz,
00—195 MOPS for Airborne JLS Localizer Receiving Equipment Operating
Within the Radio Frequency Range of 108 — 112 MHZ, and D0-208 MOPS
for Airborne GFS Receiving Equipment used for Supplemental Means of
Navigation, European Organisation for Civil Aviation Equipment
(EUROCAE) ED—lZA Minimum Operational Performance Specification for
Airborne GPS Receiving Equipment used for Supplemental Means of
“55 3455-50 52332;
Alliedsignal Eiecvonic and Avionics Syslems
MAINTENANCE MANUAL
RNA—555 MULTI-MODE RECEIVER SYSTEM
Navigation, and digital guidance data conforms to ARINC 429—14 Mark
33 Digital Information Transfer System (BITS) format.
In addition, the MMR provides digital Morse Code decoding, fault
memory, and builtfin test equipment (BITE) interfaces for use in a
Central Fault Display System (CFDS) per ARINC 604 and Airbus
Industrie ABD-004B.
Equipment Part Numbers
Components of the RNA—5513 Multi—Mode Receiver System supplied by
AlliedSignal Electronic and Avionics Systems (EAS) are listed in
figure 2. The figure lists the currently available components of
the system, along with part numbers and equipment type numbers.
EQUIPMENT
TYPE NUMBER EQUIPMENT DESCRIPTION PART NUMBER
RMA—SEB A microprocessor-based instrument landing 066—50029—0101
Multi—Mode system receiver that receives
Receiver ground—based localizer signals from
108.10 MHz to 111.95 MHz and ground—based
glidefslope signals from 329.15 MHz to
335.00 MHz frequency band and processes
these signals to provide digital aircraft
guidance data to the AFCS and instrument
system during manual and automatically
controlled approaches and landings.
Receiver design conforms to ARINC 755 and
EUROCAE ED—72A; digital guidance data
conforms to ARINC 429 format.
In addition to the automatic self—test
feature, the unit contains an
operator—initiated self»test feature,
located on the lLS receiver front panel,
that provides a comprehensive test of all
sections of the unit and operation of its
outputs.
Complies with DO—l78B software
requirements and enhanced BITE
requirements of Airbus, Boeing, and
McDonnell Douglas.
1.8.
RMA—SSB Multi-Mode Receiver System Components
(AlliedSignal Supplied)
Figure 2 (Sheet 1 of Z)
34-55-50 mas
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
EQUIPMENT
TYPE NUMBER
EQUIPMENT DESCRIPTION
PART NUMBER
RMA-SSB
Mu] ti—Mode
Receiver
(Cont)
through the front of the unit.
Meets DO—IGDC Tightning protection and
200 ms power interrupt transparency
requirements.
enroute navigation and non—precision
apprnaches per ARINC 743A—2 and
EUROCAE ED—72A.
CapabIe of interfacing CMC per ARINC 604. 066-50029—0101
Capable of data recording and Toading (Cont)
Meets HIRF requirements and ICAO Annex 10
requirements‘
Same as '~0101, except capabie of GNSS
066—50029—1101
interfacing CFDS per ARINC 504 and
McDonneTI Douglas MDC—QGK9054.
Same as ’—010], except capabTe of 066-50029-0151
enroute navigation and non—precision
approaches per ARINC 743—2 and
EUROCAE ED—72A.
Same as ’—0151, except capabTe of GNSS 066—50029-1151
I.B‘ 1155
RMA—SSB Muiti—Mode Receiver System Components
(AH iedSignaT Supp] ied)
Figure 2 (Sheet 2)
34—55—50
Page 3
Mar/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfSSB MULTI»MODE RECEIVER SYSTEM
C. Equipment Required but Not Supplied
Figure 3
lists equipment required for the RMA-SSB Multi—Mode
Receiver System, but not supplied by AlliedSignal Electronic and
Avionics Systems (EAS).
EQUIPMENT
Control Panel
Power Source
Electronic Horizontal
Situation Indicator
(Digital HSI)
ILS Local izer Antenna
ILS Glide Slope Antenna
GNSS L—Band Antenna
3 MCU Unit Mount
I_
Must provide remote control of frequency
selection, power on—off, and self-test data
using two—wire serial digital command format
defined in ARINC 429.
AC power supply of 115 volts, 400 HZ as
defined in ARINC 413A.
Must accept ILS digital data in ARINC 429
format and display aircraft position data.
DESCRIPTION
Must be capable of receiving localizer signals
over a frequency range from 108 MHZ to
112 MHZ, VSNR of 5:1 maximum, and an impedance
of 50 ohms.
Must be capable of receiving glidefslope
signals over a frequency range from 329 MHZ to
335 MHZ, VSHR of 5:1 maximum, and an impedance
of 50 ohms.
Must be capable of receiving GNSS signals over
a frequency range from 1565.42 MHz to
1585.42 MHZ, VSWR of 20:1 maximum, and an
impedance of 50 ohms.
Must provide a means of mounting RMA—SSB
Multi—Mode Receiver in the aircraft. Designed
per ARINC 600. Mount connector must allow
mating of MMR low—insertion force, size 2
shell, ARINC 600 connector with three inserts.
The connector must accommodate four coaxial
interconnections in its upper insert (TP), 118
service interconnections and two coaxial
interconnections in its center insert (MP),
and two coaxial and power interconnections in
its lower insert (BP)A Keying pins must be
indexed to pin code "03“.
Equipment Required but Not Supplied
I.B. 1155
Figure 3 (Sheet 1 of Z)
Page 4
Mar/98
34-55-50
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSE MULTIfMODE RECEIVER SYSTEM
EQUIPMENT DESCRIPTION
is required for the MMR.
figure 211.
Equipment Required but Not Supplied
Figure 3 (Sheet 2)
D. Related Publications
Cooling Source Aircraft supplied ARINC 600 forced—air cooling
Cables and Connectors Necessary connectors, rf cables, and aircraft
interwiring are shown in RNA—558 Multi—Mode
Receiver System Interwiring Diagram,
_|
Figure 4 lists the publications covering the MMR system and test
procedure supporting the system.
EAS ATA
IDENTIFICATION IDENTIFICATION
PUBLICATION NUMBER NUMBER
RNA—558 Multi—Mode Receiver,
Component Maintenance Manual I.B. IISSA 34—55—51
Related Publications
Figure 4
1.8. 1155 Page 5
34-55—50
Mar/98
AlliedSignaI Electronic and Avionics Syslems
MAINTENANCE MANUAL
RMA—SSB MULTI-MODE RECEIVER SYSTEM
2‘ Configurations AvaiTab'Ie
Figure 5 Tists the avaiiabie configurations of the RNA—558 MuTti—Mode
Receiver and the features contained in each configuration. Figure 6
cantains a brief description of each feature.
FEATURES
INTERFACE
BASIC MCDONNELL
PART NUMBER UNIT WITH ENROUTE BOEING DOUGLAS AIRBUS
DEG—50029 ILS GNSS CMC CFDS CFDS
~010l X X
—1101 X X X
—0151 X X
—1151 X X X
RNA—558 MuTti—Mode Receiver, Configurations AvaiTabTe
Figure 5
IB. 1155 Page 6
34—55—50 Mar/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
FEATURE DESCRIPTION
Basic Unit Airborne solid—state microprocessor—based
with ILS instrument—landing system receiver which provides
localizer and glide-slope deviation data to cockpit
displays and automatic flight control system in
ARINC 429 digital data format. Microprocessor
circuits control signal processing, tracking,
integrity monitoring, failure warning, and self—test.
A nonvolatile, single—chip fault memory allows the
recording of faults associated with a particular
flight leg. Sixtyffour ﬂight legs are available
with each flight leg made up of a flight—leg
information header containing a fault record section
for recording ten airborne faults and three ground
faults. when all flight legs have been used, the
oldest flight leg is reused.
Digital Morse Code Decoder provides capability of
receiving ground—facility digital Morse Code Ident
signals and decoding them to ARINC 429 data word
format for use on the ILS system ARINC 429 data
output bus.
Enroute GNSS GNSS receiver provides GNSS enroute navigation and
non»precision approach information: latitude and
longitude.
CMC Interface The MMR interfaces fault memory and BITE data between
MMR and line maintenance Centralized Maintenance
Computer (CMC) For the purpose of extracting
maintenance information and initiating tests.
Designed to conform with ARINC 429 interfaces,
ARINC 604.
CFDS Interface The MMR interfaces fault memory and BITE data between
MMR and line maintenance Centralized Fault Display
Interface Unit (CFDIU) for the purpose of extracting
maintenance information and initiating tests.
Designed to conform with ARINC 429 interfaces,
ARINC 604, and McDonnell Douglas MDC—96K9054,
RMA—SSB MultifMode Receiver Features
Figure 6
34-55-50 52359;
Alliedsignal Electronic and Avionics Systems
RNA—55
3.
A. Unit Specifications
Figure 7 iists the
Receiver System.
MAINTENANCE MANUAL
8 MULTI—MODE RECEIVER SYSTEM
System Leading Particu1ars
leading particulars for the RNA-558 Multi—Mode
CHARACTERISTICS
DESCRIPTION
Genera'l
Power Requirements
Weight
Dimensions
Form Factor
Coo] ing
Temperature
Operating
Storage
Warm-up Period
Frequency Seiection
Certification
ILS Loca'l i zer Receiver
Frequency Range
Selectivity
Undesired Response
Rejection
_I_
115 Vac, 380 to 420 Hz, 30 to 35 Watts
Refer to out'line drawing, figure 210
Refer to outiine drawing, figure 210
ARINC 600, 3 MCU
ARINC 600 Forced air; refer to outiine drawing
figure 210 For air ﬂow rate.
—15°C to «170°C (+5°F to +158°F)
—55°C to 485°C (767°F to +185°F)
StabTe operation within one minute after
appTication of power
Seria1 digitai in accordance with ARINC 429
TSO C34e (G/S), C3Ge Class B (LOC), and
C129a—BZ/C2, Ba/ca (GNSS);
DOeIGOC/EUROCAE ED—14 Environmentai Category
/A2/ZBA/B/XXXXXXZEAEZHZ/XXEZ/XX
ICAO Annex 10 FM Immunity
108.10 MHz to 111195 MHZ, 50 kHz channel
spacing (exc1uding VOR Stations)
Attenuation Bandwidth
Less than 6 dB 115 kHz
More than 60 dB 131.5 kHz
80 dB minimum
Leading Particuiars
Figure 7 (Sheet 1 of 3)
1.34 1155
34—55—50
Page 8
Mar/98
AlliedSignaI Electronic and Avionics SysTEMs
MAINTENANCE MANUAL
RNA—555 MULTI—MODE RECEIVER SYSTEM
CHARACTERISTICS
DESCRIPTION
Cross Modulation
Rejection
Receiver Sensitivity:
Aurai Reception
LocaT izer Reception
Audio Frequency
Response
AGC
Audio Output
Audio Output ReguTation
Harmonic Distortion
Centering Accuracy
Warning SiLnais
ILS Glide STope Receiver
ILS LocaTizer Receiver (continued)
60 dB minimum
3 hard microvoits of Tess for 6 dB
signaT-pTus—noise—to—noise, measured at the
audio output
3 hard microvoTts for vaTid data indication
Audio output wiTT not vary more than 6 dB from
350 Hz to 2500 Hz. More than 20 dB attenuation
at 150 Hz and 5 kHz.
Less than 3 dB audio output variation from
5 microvoTts to 100,000 microvoTts
CapahTe of 40 miTiiwatts minimum into a ZOO—ohm
to GOO—ohm resistive Toad with 107microcht
signaT moduTated 30 percent at 1000 Hz.
Factory adjusted for 10 miTTiwatts minimum into
a 60040hm resistive Toad
Less than 6 dB voTtage change from a
40 miTiiwatt reference TeveT into 200 ohms for
resistive Toad variations of 200 ohms to
10,000 ohms
Less than 7.57» with 1000 microvoTts moduTated
30% at 1000 Hz and iess than 20% with 9036
moduTation for rated audio output into a
ZOO—ohm to GOD—ohm resistive Toad
10.003 DDM under standard iaboratory conditions
Per ARINC 424 and ARINC 755
Frequency Range
_1__
329.15 MHz to 335.00 MHZ, 150 kHz channeT
spacing
SeTectivity Attenuation Bandwidth
Less than 6 dB 122 kHz
More than 60 dB 178 kHz
Undesired Response 80 dB minimum
Rejection
Leading ParticuTars
Figure 7 (Sheet 2)
1.5.1155 Page 9
34-55-50
Mar/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAASSB MULTI-MODE RECEIVER SYSTEM
CHARACTERISTICS
DESCRIPTION
15 mi“ New heavy
Cross Modulation
Rejection
Receiver Sensitivity
Centering Accuracy
Warning Signais
(continued)
60 dB minimum
10 microvoits or less for vaTid data indication
19.003 DDM under standard Taboratory conditions
Per ARINC 424 and ARINC 755
GNSS Receiver
2 m/s‘.)
Sensor Unit Autonomous
Position Accuracy:
Horzontai Position
Ground Speed
Track Angie True
Vertical Velocity
Altitude
N-S & E—w Veiocities
Time—to—First-Fix
Reacquisition
Acquisition SenSitivity
Tracking Sensitivity
(Meets performance requirements defined in foilowing
under conditions of aircraft operating speeds of up to
800 knots, acceieration of up to 12.5G, jerk of up to
Assumptions: HDOP = 1.5
VDOP = 2.0
TDOP = 0.8
C/Na = 37.7 dB Hz
SA = Inactive
30 meters per axis
1.25 knots
0.5 degree
200 feet/minute (1.01 meter/second)
130 feet (39.6 meterﬂ
1.0 knot (1851 m/s) for straight/ieveT flight
during zero acceieration
Tess than 75 seconds (95% confidence Tevei)
200 miiiiseconds (5 seconds maximum)
(Veiocity 5200 kts — 5 sec reacquisition time)
(Veiocity )200 kts - 90 sec reacquisition time)
—134<5 dBm at input of antenna preampiifier
Assumption: NF preamp — 2 dB maximum
G preamp 33.0 13 dB
CabTe Loss : 6 to 16 dB
—137.5 dBm at input of antenna preampiifier
Assumption: NF preamp = 2 dB maXimum
G preamp = 33.0 13 dB
Cabie Loss = 6 to 16 dB
ill
1.8. 1155
Leading Particuiars
Figure 7 (Sheet 3)
34-55—50
Page 10
Mar/98
AlliedSignaI Elechonic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTI-MODE RECEIVER SVSTEM
B. Environmental Certification
The RNA—558 Multi—Mode Receiver meets the environmental conditions
of the Radio Technical Commission for Aeronautics (RTCA) document
number DO—lSOC, "Environmental Conditions and Test Procedures for
Airline Electronic/Electrical Equipment and Instruments." The
environmental certification categories of the MMR are
/AZ/ZBA/B/XXXXXXZEAEZWZ/XXEZ/XX (see figure 8).
[_ TEST CATEGORY
Temperature and Altitude A2
Inﬂht Loss of Cooling Z
Temperature Variation B
Humidity A
Operational Shocks and Crash Safety Meetsiﬁcification
Vibration B
L. Mosion Proofness X
Waterproofness X
Fluids Susceptibility X
Sand and Dust X
Fungus Resistance X |
Salt Spray X
Magnetic Effect Z
Power Input E
Voltage Spike A
Audio Frequency Conducted Susceptibility — E
Power Inputs
Induced Signal Susceptibility Z
Radio Frequency Susceptibility w
(Radiated and ConductedL
Emission of Radio Frequency Ener%_ Z T
LiMng Induced Transient Susceptibility XXEZ
Lightn_i_ng Direct Effects X
Icing X
Environmental Certification Categories of MMR
Figure 8
1.5.1155 34—55—50
Page 11
Mar/98
4.
LB.
TOUCH DOWN POINT
AlliedSignal Electronic and Avioniw Systems
MAINTENANCE MANUAL
RMAfSSB MULTI—MODE RECEIVER SYSTEM
System Description
The basic RNA—5513 Multi—Mode Receiver (MMR) System is an ILS receivert
Other versions of the MMR merges a Global Navigation Satellite Sensor
(GNSS) into the MMR. The function of the ILS receiver and GNSS receiver
are independent of each other.
Instrument Landing System (All LRU’s)
An Instrument Landing System (ILS) consists of ground—based
transmitting equipment and one or more sets of airborne receiving
equipment. The ground—based equipment consists of two separate
transmitters to radiate the guidance signals required for ILS
approaches and landings. The glide—slope transmitter generates
frequencies ranging from 329.15 MHZ to 335.00 MHz to provide the
vertical guidance (elevation) data. The localizer transmitter
generates frequencies ranging from 108‘10 MHZ to 111.95 MHZ to
provide the lateral guidance (azimuth) data. Both transmitter
antenna arrays are located near the airport’s ILS runway and produce
the patterns as shown in figures 9, 10, and 11.
The glide-slope path is the angle of descent for an instrument
landing (figure 9). This angle is nominally three degrees above the
ground but depends upon the local terrain. The glide—slope
transmitter antenna array radiates two intersecting lobes. The lobe
above the glide—slope path is modulated with 90 Hz. The lobe below
the glide—slope path is modulated with 150 Hz. When the aircraft is
exactly on the glide—slope path, the modulation signals are equal,
indicating that the aircraft is flying at the proper angle of
descent.
90 Hz FREDOMlNATES
150 Hz PREDOMlNATES
movenomom’u.
unsszn
RUNWAY
GlidefSlope Antenna Pattern
Figure 9
34-55-50 Fiat/é;
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTI-MODE RECEIVER SYSTEM
Above the glide—slope path, the 90—Hz modulated signal is stronger,
indicating that the aircraft is above the glide—slope path. Below
the glide-slope path, the ISO—Hz modulated signal is stronger,
indicating that the aircraft is below the glide—slope path. The MMR
detects the differences in the two modulated signals, and provides
the resultant glideAslope deviation signal to the glide—slope
deviation indicator on the electronic horizontal situation indicator
(EHSI) or digital HSI and to the Automatic Flight Control System
(AFCS).
The localizer course is the centerline of the runway for an
instrument landing (figure 10). Operation of the localizer beam is
similar to the glidefslope beam except the localizer provides
azimuth guidance instead of elevation guidance data. The localizer
transmitter antenna array radiates two intersecting lobes. The lobe
to the left of the runway centerline is modulated with 90 Hz. The
lobe to the right of the runway centerline is modulated with 150 Hzt
When the aircraft is exactly aligned with the runway centerline
(localizer course), the modulation signals are equal, indicating the
aircraft is flying the proper azimuth heading (course).
‘ ’ ”Eu—H?
laneooMlNATF-s
LOCAL‘ZER COURSE
RUNWAY
Asoasm
Localizer Antenna Pattern
Figure 10
To the right of the localizer course, the ISO—MHZ modulated signal
is stronger, indicating that the aircraft is to the right of the
runway centerline. To the left of the localizer course, the 90—MHZ
modulated signal is stronger, indicating that the aircraft is to the
left of the runway centerlinel The MMR detects the differences in
the two modulated signals, and provides the resultant localizer
course deviation signal to the course deviation indicator on the
electronic horizontal situation indicator or digital HST and to the
AFCS‘
Page 13
1.8. 1155 34_55_50 Mar/98
1.8.
AIIiedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTI—MODE RECEIVER SYSTEM
Figure 11 illustrates the combination of both the ground—based
glide—slope and localizer guidance signals for a typical instrument
landing system.
at mum
mean 101x195
want-n. mm
sa u -u m mm on (quasi m mu
m coca wemrxcmm rim to. m
m: w .. un-unwm (nocuurfn sun mum
an 5m mum
mum new ion ums.
n. mummy. murmurs
sum in xurtmmuu,
mm m7 mu PATx
w SLIDE my mmu—in
ma rc 13
.r15 m-
u-xc. 7
an n
u 25x (
mu IS Esuausvss nanmm n n
nan c: 1 5mm. uzvmzns an
lCCAt iswzn.
um mu 5
, “1mm, mu
5 m so m; 150 rz.
u uuctwss in mm»
mm e». MW. in: mus
nmxmmv 1 union
mm sms mm;
Newman
suns mu 9“ "1
mmunou WEEK/[NH m a, 3° “M
unknown.
(mm)
mm mm muss: ~ ' ~
so Ar nest mamas ‘
mm smz 1mm
3231525:
Typical Instrument Landing System
Figure 11
The localizer transmitter also sends out a station identification
code and voice communication, modulated at 1020 Hz.
The airborne equipment typically consists of an ILS Receiver, such
as the one found in the MMR, a localizer antenna, a glide-slope
antenna, and a control panelc For most air transport applications
and to satisfy all Category II & III landing applications, two or
three ILS receiver systems are installed.
The glide—slope and localizer signals from the ground—based
transmitters are picked up by the aircraft antennas connected to
glide—slope and localizer receivers in the MMR. The glide—slope
receiver requires a horizontally polarized antenna capable of
receiving glide—slope signals in the range of 329.15 MHz to 335‘00
MHz. The localizer receiver also requires a horizontally polarized
antenna, but the frequency range is 108t10 MHZ to 111.95 MHz.
Page 14
34-55-50 We
CONTROL ARINC 429 DATA BUs GNss OWPW mu AFCS
PANEL FREQUENCY sELEchoN.
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfSSB MULTI-MODE RECEIVER SYSTEM
Figure 12 shows a simplified block diagram of the RMA—SSB Multi»Mode
Receiver System. Separate aircraft antennas are required for
glide—slope and localizer operation. The MMR receivers process the
rf signals and calculate deviation of the aircraft from the
glidevslope path and localizer path The amount of deviation, based
upon the difference in depth of modulation (DDM) of the signal, from
both receivers is provided as ARINC 429 output words to the primary
displays, the navigation displays, and the automatic flight control
system (AFCS). In manual mode, the pilot is presented with a visual
indication of the amount of deviation from the central axis, both in
the lateral and the vertical directions. The pilot maneuvers the
aircraft to zero out the left/right and up/down deviations. In
automatic mode, the aircraft is maneuvered by the AFCSA
suns sLoPE
ANVENNA
LOCALIZER cuss mrzmu
ANTENNA -1|o114|51|.nu‘s
GNSS ARIN!) 429 DATA BUS
chs was mans
DISPLAYS
ILS ARlNC 429 DATA BUS
commas a wARNwo paw
1551, we coNrnot
CMC
sunun memchnou.
MAlNIENANCE DAM
muse AUDIO
cmcrcms M» MULTl-MODE _.——————> DISTRIBUTION
mmmancs om RECEIVER Moose CODE SYSTEM
lRS/FMS —’———>
ARNC 429 DATA BUS
cuss iNH’IALIZATION mu
iiﬁsowwciz
I.B.
RMA—SSB Multi—Mode Receiver System Block Diagram
Figure 12
“55 34-5 5-50 Kai/é;
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTIfMODE RECEIVER SYSTEM
The station identification and voice communication signals are
recovered from the localizer receiver and are fed to the aircraft
speaker system or the cockpit headsets. The ground station digital
Morse Code identification signal is also provided on the ARINC 429
data output bus.
The localizer and glide—slope frequencies of the MMR are selected by
ARINC 429 words output by a control panel. The pilot tunes the MMR
to match the frequency specified for a particular airport’s runway.
Only the localizer frequency is specified by the control panel. The
glide—slope frequency in the MMR is set depending upon the localizer
frequency. Refer to figure 13 for a list of operating localizer and
glide—slope frequency pairings.
LOCALIZER GLIDE—SLOPE LOCALIZER GLlDE»SLOPE j
FREQUENCY erqueucv 5115005ch FREQUENCY
(MHz) (MHZ) (MHZ) (MHZ)
103.10 334.70 10.10 334.40
103.15 334.55 110.15 334.25
103.30 334.10 110.30 335.00
100.35 333.95 10.35 334.35
105.50 329.90 10.50 329.50
103.55 I— 329.75 110.55 329.45
109.70 330.50 110.70 330.20
108.75 330.35 10.75 330.05
103.90 329.30 10.90 330.00
105.95 329.15 110.95 j 330.55 _|
109.10 331.40 _ 11.10 331.70
109.15 331.25 111.15 T 331.55 1
109.30 332.00 11.30 332.30
_ 109.35 331.85 111.35 332.15
109.50 T 33250 11.50 332.90
109.55 332.45 11.55 332.75
109.70 333.20 7 11.70 333.50
109.75 333.05 11.75 333.35
109.90 333.90 111.90 T 331.10 j
109.95 333.55 11.95 330.95
.B.
Localizer and GlidefSlope Frequency Pairings
Figure 13
”55 34-55-50 Piaf/é:
Alliedsignal Electronic and Avionics Syslems
MAINTENANCE MANUAL
RMA—SSB MULTIfMODE RECEIVER SYSTEM
The MMR also interfaces with the CFDS to allow line maintenance to
initiate the BITE and extract maintenance information pertaining to
faults. The BITE provides information such as the date, time in
Greenwich Mean Time (GMT), flight number, city pairs, aircraft
identification, BITE command, flight phase and the "health" of the
LRU. If a fault had occurred during a flight phase or segment, the
BITE would also indicate which module in the MMR had failed along
with the other information.
Global Navigation Satellite Sensor (—1101, —1151 LRU’s)
A global navigation satellite sensor (GNSS) is a satellite
navigation sensor which uses the C/A code of the NAVSTAR Global
Positioning System (GPS) satellite constellation. The GNSS module
interfaces with the aircraft systems to provide three dimensional
aircraft position and velocities, as well as satellite position,
pseudo range, and delta range information for use in remote hybrid
computations.
The GNSS module is designed to track the RF signal received from the
antenna, determine the signal code phase and carrier phase, compute
the antenna position and output the raw and navigational data.
5. System Component Description
A.
I.B.
RMAASSB Multi—Mode Receiver (MMR)
The MMR is a solid~state, airborne multi—mode receiver consisting of
an instrument landing system (ILS) receiver and in some MMR models a
global navigation satellite system (GNSS) receiver‘ These receivers
are used in conjunction with two ILS antennas (localizer and glide
slope), a GNSS antenna (if used), a control head, and the cockpit
displays. The primary purpose of the RMA—BSB Multi—Mode Receiver is
to provide lateral (localizer) and vertical (glide slope) guidance
ILS information. In MMR models that include a GNSS receiver, the
unit provides additional enroute navigation and non—precision
approach information. This information is provided via ARINC 429
interfaces to the aircraft Automatic Flight Control System (AFCS)
and instrument systems during manual and automatically controlled
approaches and landings. The MMR also provides an aural output for
the ILS ground station identification.
The MMR is completely solid state and is housed in an ARINC 3»MCU
case per ARINC specification 600. A handle is located on the front
panel of the MMR to factlitate installation, removal, and transport
of the MMR receiver.
Page I7
34-55-50 W
AlliedSignaI Electronic and Avionics Syslems
MAINTENANCE MANUAL
RNA—558 MULTI—MODE RECEIVER SYSTEM
The MMR uses a low insertion force, size two shell ARINC 600 rear
panel connector with three inserts. The top insert is used for
antenna connections for GNSS upper antenna and future antenna
connections. The middle insert is used for aircraft
interconnections and future antenna connections. The bottom insert
is used for input power, control panel output power, and coaxial
antenna connectors for the glide slope antenna and localizer
antenna. The keying pins are set to index pin code "03".
Forced air cooling, in accordance with ARINC specification 600, is
required for cooling the MMR.
A front panel display provides an interface to an operator via a
liquid crystal display (LCD) that is visible from the front of the
MMR receiver to display messages in simple language in one of four
modes: normal operation, BITE display, maintenance, and software
loading.
Two pushbutton switches allow operator interface with the MMR
receiver LCD.
In normal operation, the front panel LCD displays the unit’s
characteristics: unit identification, part number, and serial
number, The BITE display mode is activated after manual self-test
has been exercised either from the front panel test pushbutton or
remotely. In the BITE mode, BITE status is reported and in the
event of a detected failure, additional help screens are provided to
locate the detected failure to a module. BITE help pages are
provided. In the maintenance mode, a set of maintenance words are
displayed and decoded showing the names of data fields and the value
of the data. Maintenance help pages are provided.
For loading software, a series of screens direct the operator during
the data loading process. Software version and loading status are
provided during the update process.
The MMR is partitioned into seven subassemblies: ILS rf module, main
processor module, monitor processor module, HIRE/rear interconnect
module, power supply assembly, display assembly, and memory card
module (refer to figure 14). In 71101 and —1151 LRU’s, a GNSS
receiver is added to the MMR.
B. Other Components in the System
Other RMAVSSB Multi—Mode Receiver System components are not supplied
by AlliedSignal Electronic and Avionics Systems. Information on
these units must be obtained from their respective manufacturers.
I.B. 1155 P 18
34—55—50 SEE/98
Alliedsignal E|eclronic and Avionics Systems
MAlNTENANCE MANUAL
RMAfSSB MULTI—MODE RECEIVER SYSTEM
: USED m |
| 4101 E -1151LRU'S l
| cuss I
| ANTENNA
I aNss as man mu I
| chsnMEMARKs l
| GNSS l
| MODULE GNSS 128 OUTPUY BATA |
| |
| |
| FUNCHGNALTESn
mwmma r
L _____________________________________ ___d
Suﬁsmns menu“
ANrENNA ANYENNA
LOCAHIER
M, DElenuN
cunEsLoPE _°Uﬂ75_> w,
RF COMPOSHE '
MODULE
uc comm
| TUNNGVOMC AUDIOOUYPUY
MNN
FRONT LCD NFL“ PROCESSOR
PANEL I names |
DISPLAY HIRF/REAR
CoNNECTOR
SOFYWARE
MEMORY LUADNNLDAD
CARD ‘ '
mun
PRDCESSOR
mm mamas
LDC/GS
pm omnou
OUVPVVENABLE
MONn'oR 15542335“
4——
PROCESSOR
~5V ‘7
<——-——
ﬂzv 4— POWER <—vumc
41V 47 SUPPLY ‘UUNZ
4—— <—
w| 4-
1ﬁsmn‘wu
RMA—SSB Mthi—Mode Receiver, Simphfied B1ock Diagram
Figure 14
Page 19
1.3.1155 34_55_5O Mar/95
6.
1.8.
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—SSE MULTIVMODE RECEIVER SYSTEM
Operation
A.
General
The RMA—SSB Multi—Mode Receiver provides localizer and glide—slope
digital guidance data to the aircraft cockpit display and automatic
flight control systems during approaches and landings. The ILS
receiver performs this function as part of an ILS system that
includes other units not supplied by AlliedSignal Electronic and
Avionics Systems. Also, in —1101 and ~1151 LRU‘s, the MMR provides
enroute navigation and non—precision approach information: latitude
and longitude.
Basic Theory
(1) Its Receiver (All LRU’s)
The [LS receiver consists of seven subassemblies: lLS rf
module, main processor module, monitor processor module,
HIRE/rear interconnect module, power supply assembly, display
assembly, and memory card module (refer to figure 14).
(a) lLS RF Module
Nhen receiving, the lLS receiver rf module converts the rf
signals received by the localizer and glide—slope antennas
into analog signals for processing by the digital—signal
processor (DSP) section of the main processor module. The
rf module consists of two rf sections: one for the VHF
localizer signals and one for the UHF glide—slope signals.
The primary difference between the two sections is in the
front end circuitry due to the frequencies involved. BITE
circuitry is included to both test and continuously
monitor various stages of each receiver.
(b) Main Processor Module
Operation of the lLS receiver is controlled by the main
processor module to process the analog signals from the rf
module to generate the audio and deviation outputs, and
control the aircraft interfaces and the data displayed on
the front panel. The main processor module is divided
into three major sections: digital»signal processor (DSP),
central processing unit (CPU), and input/output (1/0).
1 DSP Section
The USP section is used to process the analog outputs
from the rf module and to generate automatic gain
control (AGE) and test signals to the rf module.
34-55-50 P5255;
I.B.
|N
Iw
1155
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA~SSB MULTI—MODE RECEIVER SVSTEM
The localizer and glide—slope signals from the rf
module are digitized using an A/D converter‘ The A/D
converter is also used to monitor signals from the BITE
test points on the rf module and the power supply
voltages. The digitized data from the A/D converter is
stored in a FIFO which is accessed by the DSP.
Programmable logic devices (PLD’s) are used by the DSP
to generate the control signals for the localizer and
glideeslope frequency synthesizers. A D/A converter
feeds the AGC and test control signals to the rf
module. A second D/A converter provides the audio
outputs which are amplified to provide up to
50 milliwatts into a load ranging from 200 ohms to
600 ohms.
Data is exchanged with the CPU section through a
dual—port RAM (random access memory) providing maximum
throughput of both processors.
CPU Section
The CPU section is used to process the data from the
DSP section to provide information to the front panel
display and to provide the data and control signals to
the I/O section
The microprocessor in the CPU section controls all
major functions to the ILS receiver. Application
specific integrated circuit (ASIC’s) and programmable
logic devices (PLD’s) serve as the microprocessor
controller and provide the interfaces to the memory
devices (boot routine, program, fault, and data), the
data recorder/data loader flash card, and the front
panel display driver‘
Data is exchanged with the USP section through a
dual-port RAM. Data is also exchanged with the monitor
processor module through a second dual—port RAM.
I/O Section
The 1/0 section provides the interfaces with other
aircraft systems including the Central Maintenance
Computer (CMC), Data Loader, control panels and
displays, and the automatic flight control system
(AFCS).
Page 21
34'55'50 Mar/98
LB.
1155
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECElVER SYSTEM
ARINC 429 inputs from data loader, CMC, and the tuning
control panel(s) are processed by the ARINC 429 1/0
ASIC. This ASIC also provides the ARINC 429 data
loader, CMC, and deviation outputs. External buffers
are used to satisfy the ARINC 429 characteristics for
the transmitters.
All discrete inputs external to the ILS receiver are
processed by the ARINC 429 1/0 ASIC. This ASIC also
generates the external discrete outputs which are
buffered to prevent damage to the ASIC.
The 1/0 section also contains an RS—Z3ZC test interface
and an IEEE 1149.1 Test Access Port (TAP) for the
boundary scan interface.
Monitor Processor Module
The monitor processor module provides a redundant
dissimilar signal processing path for the localizer and
glide—slope signals from the rf module. In order to
determine if the main CPU section is functioning properly,
the monitor processor calculates the deviation outputs and
compares the results against those being transmitted over
the ARINC 429 lLS receiver ports. If the calculations
from the two microprocessors are excessively different,
the monitor processor will ask the DSP processor in the
main CPU section to set the deviation words to indicate
"Failure." The monitor processor will shut down the
output busses if the SSM of the output words does not
indicate failure when required.
The localizer and glide—slope signals from the rf module
are digitized using an A/D converter. The digitized data
from the A/D converter is stored in a FIFO which is
accessed by the DSP. The DSP does not generate any
control signals for the rf module, but only serves as a
monitor to verify data integrity. The DSP stores the
processed data in a dual—port RAM. The DSP uses the same
memory devices for both program and data storage. A PLD
is used to generate the control signals for the DSP, the
A/D converter, and the FIFO. Data is exchanged with the
CPU section of the main processor module through a
dual—port RAM, providing maximum throughput of both
processors.
ARINC 429 receivers are used to monitor the deviation data
transmitted by the main processor module. The receivers
are controlled by a microprocessor which compares the
calculated deviation outputs with the actual deviation
outputs. A discrete output is used to disable the
34-55-50 95.25/32
AlliedSigna| Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA»555 MULTI-MODE RECEIVER SYSTEM
transmitter on the main processor module in order to
prevent erroneous data from being output by the ILS
receiver. Separate program and data memory is used for
the microprocessor. A PLD is used to generate the control
signals for the microprocessor and ARINC 429 receivers.
(d) Power Supply Module
The 115 volts ac, 400 Hz aircraft power is converted by
the power supply module into the dc operating voltages
required by the various modules within the [LS receiver.
A self—contained, high efficiency switching power supply
is used to minimize power dissipation.
(e) HIRF/Rear Interconnect
To prevent High Intensity Radiation Fields (HIRF) or
lightning from affecting operation by entering via rear
connector cables, 3 HIRF compartment is formed in the rear
of the ILS receiver. The signal and power cables are
filtered by using discrete and distributed filter elements
and limiting devices on the rear interconnect module
located inside this HIRF compartment. The filtered lines
are then fed to the appropriate points in the ILS
receiver.
The 1LS receiver is packaged in an aluminum casting. This
seamless main frame ensures HIRF cannot enter the unit
through structural seams. The slots formed by the
removable side covers are sealed against HIRF with
protective gaskets and metal covers.
(f) Front Panel Display Assembly
The front panel display module is mounted behind the front
panel and provides an interface to an operator via a
low—power liquid crystal display (LCD) that is visible
from the front of the ILS receiver. In addition to the
LCD, the module contains "Light Pipe” back lighting,
temperature compensation circuitry, and a PC board
containing an associated LCD driver, two pushbutton
switches, and a D»sub, nine—pin, R57232 serial type
connector.
1.13. 1155 P 23
34—55-50 333/98
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA-SSB MULTIvMODE RECEIVER SYSTEM
The LCD is a bit-mapped display capable of displaying
alphanumeric and graphical symbols. Simple messages
written in plain language minimize the potential for
misunderstanding or incorrect interpretation. The LCD
displays the following:
Part Number/Software Identification,
Status,
Results of Level 1 BITE Tests,
Maintenance Help Pages,
Shop Maintenance Data,
Flight Fault Memory Contents,
Software Loading Status, and
Capable of Customizing for Airline Unique
Maintenance Messages.
QQOOOCOO
(g) Memory Card Interface Module
The memory card interface module is used to load data into
the CPU or record data from the CPU. The memory card
interface module supports FLASH cards via the front panel
Personal Computing Memory Card Interface Adapter (PCMCTA)
slot' Intel® Series 2 cards with capabilities ranging
from 4, 10, and 20 megabytes (up to 64 megabytes, when
available) are all supported. The FLASH card is inserted
through the front panel. In one mode, data stored on the
flash card memory module is used to update program or data
memory in the ILS receiver. In another mode, the flash
card memory module functions as a data recorder.
GNSS Receiver (—1101 and 71151 LRU’s)
The GNSS receiver consists of an antenna and the GNSS module
(refer to figure 14). The GNSS module has seven operating
modes: self—test, initialization, acquisition, navigation,
altitude/clock aiding, aided and fault Figure 15 illustrates
the automatic transition path between modes of operation.
(a) Self—Test Mode
Upon application of power, the GNSS module is in self test
mode until completion of all internal power—up
built—in—tests (BIT) of the MMR. The self—test mode is
initiated by ARINC 429 tuning input, function test
discrete input, or through the front panel pushbuttons of
the MMR. After self test is completed, the GNSS module
exits to either the initialization mode or if a fault was
detected, the fault mode.
Page 24
34'55‘50 Mar/98
I.B.
MAINYENANCE
POWER on
iissoaomns
(b)
1155
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA-558 MULTI-MODE RECEIVER SYSTEM
ALTITUDE
GNSS Module Mode Transition Diagram
Figure 15
Initialization Mode
After completion of the GNSS module self—test mode, the
GNSS module enters the initialization mode and remains in
this made until the device has initialized the hardware to
enable it to enter the acquisition mode,
Acquisition Mode
The GNSS module operates in the acquisition mode when
insufficient satellite and/or aiding data are available to
produce an initial navigation solution or be in the
navigation, altitude/clock aiding, or aided modes. The
acquisition mode is entered from the initialization,
altitude/clock aided, aided, or navigation modes and exits
to the navigation, altitude/clock aided, or fault modest
Page 25
34‘55‘50 Mar/98
1.8.
1155
A|Iied5ignal Elecironic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI-MODE RECEIVER SYSTEM
To acquire signals from the NAVSTAR Global Position
Satellite (GPS) system, the GNSS module uses:
0 almanac data - which describes the satellite orbits and
is stored in nonvolatile memory,
0 time — which in conjunction with almanac data is used
to estimate the present position of satellites in their
orbits, and
0 approximate location of the GNSS module so a prediction
can be made as to which satellites are visible
(satellites 2.0 degrees or more above the horizon with
respect to current position is considered visible).
When power is applied to the GNSS module, an ARINC 429
bus provides date, time, and position data. The GNSS
module predicts which satellites are visible and acquire
the satellite signals which meet minimum requirements for
acquisition and sensitivity. The GNSS module then
collects ephemeris data by decoding the satellite
down-link data message. (Ephemeris data is a tabulation
of the assigned place for each satellite in the NAVSTAR
GPS system.) After each satellite in View is acquired,
the satellite measurement data is transmitted
continuously. When a sufficient number of satellites are
being tracked, position and velocity can be computed, and
the navigation mode can be entered.
If the GNSS module cannot perform acquisition due to an
absence of almanac data or GNSS module initialization data
from the ARINC 429 bus, the GNSS module then initiates a
"Search the Skies” acquisition. The GNSS module attempts
to acquire all satellites in the GPS constellation. Once
a satellite has been acquired, ephemeris data is decoded
from the satellite down-link message. After sufficient
satellites have been acquired, the GNSS module set the
sign status matrix (SSM) to the appropriate status mode
and enters the navigation mode.
Navigation Mode
When the number of GPS satellites being tracked provide a
sufficient set of measurements for the GNSS module to
compute position, velocity, and time, the GNSS module
enters to navigation mode where the ephemeris data is
decoded to provide a navigation solution. In this mode,
the satellite measurement data continues to be transmitted
without interruption.
34-55-50 Poi/32
LB.
1155
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA-558 MULTI~MODE RECEIVER SYSTEM
Altitude/Clock Aiding Mode
If satellite measurements are not sufficient for the GNSS
module to perform the navigation mode, yet are sufficient
when altitude and clock information is available, the GNSS
module enters into the altitude/clock aiding mode. In the
altitude/clock aiding mode, the GNSS module uses inertial
or pressure altitude and clock drift information to aid
the navigation solution during extended periods of
insufficient satellite coverage and geometry. The GNSS
module enters altitude/clock aiding mode only after the
pressure altitude has been calibrated with a geometric
altitude solution. If both inertial altitude and air data
altitude are available, the GNSS module uses the inertial
altitude.
Aided Mode
(Not available.)
Fault Mode
The GNSS module enters the fault mode during the period of
time in which the GNSS module outputs are affected by one
or more critical system faults. This mode supersedes all
others and will remain active until the next
power—down/power—up cycle.
345 5-50 “91421452
1.84
Alliedsignal Electronic and Avionios Systems
MAINTENANCE MANUAL
RNA—SSE MULTI»MODE RECEIVER SYSTEM
FAULT ISOLATION
Genera]
Fauit isolation is the process of isuiating the source of a system
failure to an LRU (Tine replaceabie unit) or to the aircraft wiring.
Fault iso’lation in the RNA—558 Muiti-Mode Receiver System inciudes a
continuity check of the interwiring, and the assurance that proper
instai'lation techniques and procedures have been followed.
A functional seif test of the LRU may be initiated by pressing the
"test" key pushbutton switch as designated on the front pane'l LCD
(figure 101). Aithough the normai—mode screen indicates that this is
actuated from the right key, the ieft key has the same function if
pressed whiie the RNA-558 Muiti—Mode Receiver (MMR) LCD is in its normal
mode.
M M R
P / N 0 6 6 —
5 0 0 2 9 — 0 l 0 1
S / N 0 1 / 0 1
P U S H T 0
J. T E S T i
O O
Typicai "NormakMode" Screen
Figure 101
Figure 102 iliustrates the control ﬂow of the LCD screens (except for
the data loading and data recording screens).
A complete functionai test of the system can be perfumed as described
in paragraph 7.8. in "Maintenance Practices" section 200 of this manuai.
34-55-50 ”3:53;
I.B.
AlliedSignal Electronic and Avionics Syslems
MA
INTENANCE MANUAL
RMA—ESB MULTI—MODE RECEIVER SVSTEM
cums
c w; Mess mm m: u! slur-11 um: cm
a. manuussnwusssmvummmm
um;- w Exyskmnuus
. m mm nun usumv no»; nannies
mum: am WYNE mam muusuouv
sch-mus mums; w PREVIei/s mam L505 M
Mum xx mtvmus mama no: sn my
wmss nsssm
rm mum
DISPLAV-FAULYS HEADER
MODE PAGES
mm
noes
mm
1751 u
"was.“
_—._‘
nu mm!“
725! mum
»®
MAINTENANCE
MuDE FAGES ‘
i—‘_
uNrr Nor nuLEn. v
m" nun I mm mm:
sxv mwkss
new"
m mun-gs Err mums;
nzssuv Nnr Puss"
in non: «a
BISPLAYIAULTS
um
sums
(DJ?
mm mm
sums
an moi:
,_v_
as links
._v_
“MN; MODE PAGES ‘J (D
m. _}—_
tun. FLIGHT'FAULY MEMORY uscKErE
m “if MODE PAGES 59:25;
< ﬁé m we
\ L____
6 r—1 am 4 r_i
; mum . <— ,
mg: n; mg
m m Q7 , ,
T ‘ A
04 mg“: i '
' wwkss
W“ m was 0~ssnumn
was» men
0 mm
‘7 an new
. ———‘— A
. ixvnas C) r—’
__v__
m nun
mm; / w‘ “55:1
1 m i
W" U9 sums
m was
1 muss
A i
Q) ’— m m ,
mm 64— k
mmw J
m ms
‘ mu mg
{n ‘ in ms ‘
v (Ty—J 4;
“mimic:
1155
LCD Control New
Figure 102
34-55—50
Page 102
Mar/98
IAB.
Alliedsignal Electronic and Avionim Syslems
MAINTENANCE MANUAL
RMA»SSB MULTI—MODE RECEIVER SVSTEM
Mod—e
The self—test mode starts by displaying the "Test in Progress" screen
(figure 103) one second after pressing the "test" key. This is
displayed for four seconds with a moving thermometer along the bottom of
the LCD indicating the progress of the test from one to five seconds.
X X X X X X X X X X X
f\ (”i
k) \_/
"Test in Progress" Screen
Figure 103
The "NormaleMode" screen (figure 101) is displayed for the first second
of the test sequence.
Once complete, the "Test Complete, No Failures” screen is displayed
(figure 104), or the "Test Complete, Failures" screen is displayed
(figure 105). Both screens contain two key selections each: "MAINT" and
"RETURN" or "MAINT" and "WHY7", respectively.
0 "MAINT" - For both screens, "MAINT" is located on the left
key. This allows the initiation of the extended
maintenance pages of the system for
troubleshooting. Refer to paragraph 4.
- "RETURN" — In the “Test Complete, No Failures" screen, the
"RETURN" key to the right returns the system to
its "Normal—Mode“ screen (figure 101).
0 "WHY?” » In the "Test Complete, Failures" screen, the
"WHY?" key to the right puts the system into the
display-failures mode where individual system
failures are displayed one per page‘ Refer to
paragraph 3.
while in the self—test mode, not pressing either key for five minutes
causes the system to return to the "Normal—Mode" screen (figure 101).
Page 103
34-55-50 w.
AlliedSignaI Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTI—MODE RECEIVER SYSTEM
M M R
T E S T C 0 M P L E T E
N 0 F A I L U R E S
M A I N T R E T U R N
"Test Complete, No Failures" Screen
Figure 104
M M R
T E 5 T C O M P L E T E
"Test CompTete, Failures" Screen
Figure 105
Page 104
1.8. 1155 34_55_50 Mar/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA-SSB MULTI—MODE RECEIVER SYSTEM
3. Di sgl ay-Failures Mode
One of three failure possibilities exist: the MMR is okay, but there are
external failures (figure 106), the MMR failed and there are external
failures (figure 107), and the MMR failed, but there are no external
failures (figure 108).
F A I L U R E S —
P R E S E N T l
R E T U R N M 0 R E
m ’\
"MMR 0K, External Failures Present” Screen
Figure 106
M M R
F A I L E D
E X T E R N A L
F A I L U R E S —
P R E S E N T l
R E T U R N M 0 R E
fa ﬁx
1 l ’ 3
v p
"MMR Failed, External Failures Also Present" Screen
Figure 107
Page 105
L8. 1155 34_55_50 Mar/98
AlliedSignal Electronic and Avionits Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
Q Q
"MMR Failed, External Failures Not Present" Screen
Figure 108
All “Display—Failures Mode" screens have the "MORE" selection on the
right key. The Only exception is when there is only one failure page.
This only happens when the MMR itself has failed and no other external
failure exists (figure 108).
0 "MORE" — Pressing this key cycles through all of the failures
present. when on the last page, the "MORE" key
causes a return to the first displayed failure page
(figure 106 or 107).
All "Display—Failures Mode" screens have the "RETURN" selection on the
left key.
0 "RETURN" — Pressing this key causes the system to return to the
"Normal—Mode" screen (figure 101).
while in the display—failures mode, not pressing either key for five
minutes causes the system to return to the “Normal—Mode“ screen
(figure 101).
L8. 1155 P 106
34-55-50 ail/gs
AlliedSignal Elecronic and Avionics Systems
MAINTENANCE MANUAL
RMA»SSB MULTI—MODE RECEIVER SYSTEM
Figures 109 through 114 show typicaT displayvfaﬂure modes that may be
encountered.
T U N I N G P 0 R T A
I S S E L E C T E D
T U N I N G P 0 R T A
H I S S I N G I N P U T
P # M P — 1 C / 1 D
R E T U R N M 0 R E
ﬁ> (X
v u
"Tuning Port A Failure" Screen
Figure 109
T U N 1 N G P O R T B
I S S E L E C T E D
T U N I N G P 0 R T B
M I S S 1 N G I N P U T
P # M P — 1 J / 1 K
R E T U R N M 0 R E
”Tuning Port 8 Faﬂure" Screen
Figure 110
Page 107
1.8. 1155 34_55_50 Mar/98
1.
B4
Al|iedSignal Elecmmic and Avionics Syslems
MAINTENANCE MANUAL
RNA—553 MULTI—MODE RECEIVER SYSTEM
R T U R N M 0
”N O
"LOC Antenna Faﬂure" Screen
Figure 111
S A N T E N N
F A I L E D
R T U R N M 0
/ﬁ\ ,
«Q 9
“GS Antenna Faﬂure" Screen
Figure 112
1155 Page 108
34—55-50 Mar/98
Alliedsignal Eledranic and Avionics Systems
MAINTENANCE MANUAL
RNA—558 MULTI—MODE RECEIVER SYSTEM
C M C P 0 R T
M I S S I N G I N P U T
P # M P - l E / 1 F
R E T U R N M 0 R E
m C)
x/ \
”CMC Port Failure“ Screen
Figure 113
R E T U R N M 0 R E
,F\ (A
u u
"Output Interrupt Program Pin InvaIid Strapping" Screen
Figure 114
1.8. 1155 P 109
34—55—50 ail/gs
Alliedsignal Elemronic and Avionics Systems
MAINTENANCE MANUAL
RMA»SSE MULTI—MODE RECEIVER SYSTEM
4. Maintenance Mode
The maintenance mode is entered from either one of the two "Test
Complete" screens (figure 104 or 105). The maintenance mode allows
troubleshooting of all components of the MMR system, both internal and
external.
All pages have the "MORE" selection on the right key.
0 "MORE" — Pressing this key cycles through all of the
maintenance pages. When on the last page, the
"MORE" key causes a return to the first displayed
maintenance screen.
All pages have the "RETURN" selection on the left key.
. "RETURN" — Pressing this key causes the system to return to the
”Normal-Mude" screen (figure 101).
There is no timeout in the maintenance mode when the aircraft is on the
ground. But, while in the air, not pressing a key for five minutes
causes the system to return to the "Normal-Mode" screen (figure 101).
Figures 115 through 122 show typical maintenance»mode pages that may be
encountered.
M M R
S T A T U S O K
F A U L T C 0 D E X X
R E T U R N M 0 R E
NOTE: The "Status" field displays "FAILED" if either an external or an
internal faiiure is detected.
”MMR Status (OK, FAILED)” Screen
Figure 115
1.8. 1155 P 110
34—55—50 ﬂair/98
Alliedsignal Electronic and Avioniu Syslems
MAINTENANCE MANUAL
RMA-SSB MULTI—MODE RECEIVER SYSTEM
P 0 R T X S T A T U S
N 0 R M 1 l 0 l 0
R E T U R N M 0 R E
”Tuning Port Status (NORM, TEST, NCD, NODAT)" Screen
F i g u re 1 16
D 1 S C R E T E S 1
F T S T I N H 0 P E N
P # M P — 1 5 F
F C T T E S T G R N D
P # M P — 4 G
R E T U R N M O R E
”A“ m
\_\;/, \\4/
"Discrete Input Status Page 1 (OPEN, GRND)" Screen
Figure 117
Page 111
L31m5 34_55_50 MHW
Alliedsignal EIecironic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
S D I P R 0 G P I N S
S D I l O P E N
P # M P — 4 H
S D I 2 C 0 M M
P # M P — 4 J
C 0 M M P # M P f 4 K
R E T U R N M 0 R E
1h 3 (h
va \
”SDI Program Pin Status Page (OPEN, COMM)" Screen
Figure 118
A N T E N N A
M 0 N I T O R E N B L E
P R 0 G R A M P I N
S T A T U S C O M M
P # M P — 5 H
C 0 M M = E N A B L E
C O M M P # M P — 4 K
R E T U R N M 0 R E
C Q
"Antenna Monitor Program Pin Status Page (OPEN, COMM)" Screen
Figure 119
Page 112
1155 34-55-50 we
AlliedSignal Electronic and Avionics Sys19ms
MAINTENANCE MANUAL
RNA-SSE MULTLMODE RECEIVER SYSTEM
0 U T D A T A I N T R
I N T R X X X X
P # M P — 5 D
N 0 I N T R X X X X
P # M P - 5 B
C 0 M M = E N A B L E
C 0 M M P # M P — 4 K
R E T U R N M 0 R E
C (xx)
/ l /‘
\_/
”Output Data Interrupt Enable Program Pin Status Page (OPEN, COMM)" Screen
Figure 120
G N S S 0 U T P U T
S P E E D S E L E C T
P R O G R A M P I N
S T A T U S X X X X
P # M P f 5 J
C 0 M M : L 0 u S P D
C 0 M M P # M P — 4 K
R E T U R N M 0 R E
k/
"GNSS Output Speed Seiect Program Pin Status Page (OPEN, COMM)" Screen
Figure i21
LEA 1155 P 113
34—55—50 aﬂZr/gs
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA»558 MULTI—MODE RECEIVER SYSTEM
C M C
P 0 R T S T A T U S
C M C I N A C T I V E
P # M P f I E / 1 F
R E T U R N M O R E
(«I /\
‘a / KE/
”CMC Port Status (ACTIVE, INACTIVE)“ Screen
Figure 122
1.8. 1155 P I14
34—55-50 3311/93
AlliedSignal Elechonic and Avionics Systems
MAINTENANCE MANUAL
RNA—555 MULTI—MODE RECEIVER SYSTEM
5. Flight Fault Memory Mode
when the flight»fault memory contains failures from previous flight
legs, an "Old Failures“ screen (figure 123) is presented as the last
page of the maintenance mode screens. This page allows the viewing of
previous flight leg failures, one flight leg at a time by pressing the
"YES" key. Pressing the “MORE" key from this page bypasses this
function and returns the system back to the first page of the
maintenance data.
Once in the flight fault memory mode, flight legs are displayed from the
most recent, backwards. Four pages are required for each ﬂight leg.
The first page of each flight leg contains the date, flight number,
aircraft number, and departure/destination stations (figure 124). Three
pages follow for each flight leg to contain the 13 possible failures
(figure 125).
All flight fault memory pages have the "MORE“ selection on the right
key.
0 "MORE" — Pressing the key cycles through all of the flight
fault memory pages. When on the last page, the
"MORE" key causes a return to the first page.
All flight fault memory pages have the "RETURN" selection on the left
key.
0 "RETURN" — Pressing this key causes the system to return to
normal mode (figure 101).
There is no timeout in this mode when the aircraft is on the ground.
But, while in the air, not pressing a key for five minutes causes the
system to return to the "Normal—Mode" screen (figure 101).
1.8. 1155 P 115
34—55—50 aﬁir/gg
AlliedSing EIecironic and Avionics Systems
MAINTENANCE MANUAL
RMA-SSB MULTI—MODE RECEIVER SYSTEM
F A 1 L U R E S H A V E
B E E N R E C 0 R D E D
F 0 R P R E V I 0 U S
F L I G H T L E G S
> Y E S T 0 V I E N
> M 0 R E T 0 S K I P
Y E S M 0 R E
C O
“01d FaiTures Page” Screen
Figure 123
F L I G H T L E G X X
D A T E M M M D D
D E P T X X X X
D E S T X X X X
F # X X X X X X X X X X
A / C X X X X X X X
R E T U R N M 0 R E
(A? (“I
\ 4/ \\‘//
"Previous FTight Legs FaiTUres First Page" Screen
Figure 124
1,81 1155 P 116
34-55—50 333,98
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAFSSB MULTI~MODE RECEIVER SYSTEM
C O
NOTE: "F6" is fun code, "UTC" is time, "R" is repetition count,
”P" is phase, “0" is origin.
"Previous Flight Legs Failures Data Page" Screen
(Three Screens per F1ight Leg)
Figure 125
118. 1155 P 117/118
34—55—50 age Mar/98
2.
I.B.
AlliedSignal Electronic and Avionins Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
MAINTENANCE PRACTICES
General
This section of the manual provides service personnel with installation
and maintenance information for the AMA-558 Multi—Mode Receiver (MMR).
Installation instructions are supported by mechanical outline drawings
and an electrical interconnection diagram. These drawings, located at
the back of this section, should be reviewed by the installer, and
requirements peculiar to the airframe should be established before
starting the installation.
Inspection After Unpacking
CAUTION: THIS EQUIPMENT CONTAINS ELECTROSTATIC DISCHARGE SENSITIVE
(ESDS) DEVICES. EQUIPMENT, MODULES, AND ESDS DEVICES MUST BE
HANDLED WITH APPROPRIATE PRECAUTIONS.
Visually inspect the RMA—SSB Multi‘Mode Receiver (MMR) and all
associated equipments for possible damage which may have occurred during
shipment. Inspect for dents, deep abrasions, chipped paint, etc. If
any equipment is damaged, notify the transportation carrier immediately.
An AlliedSignal Electronic and Avionics Systems (EAS) test and
inspection record and quality report tag is included with each shipped
unit. This ensures the customer that the necessary production tests and
inspection operations have been performed on that particular unit.
One copy of the quality report tag is affixed to each unit by the first
assembly inspector. As the unit proceeds through production and stock
to the shipping area, the appropriate blocks on the test and inspection
record of the tag are stamped. This tag accompanies the unit when it is
shipped to the customer. Customers are requested to complete the
quality report portion of the tag and return it to the AlliedSignal
Electronic and Avionics Systems, Quality Assurance Department, Redmond,
Washington. This portion of the tag provides CAS with the necessary
information required to evaluate shipping methods as well as test and
inspection effectiveness.
Completed cards are accumulated to provide information for a periodic
analysis.
“55 34-55-50 “32.52;
AlliedSignaI Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
3. Preinstallation Testing
The components in the MMR have been adjusted and tested prior to
shipment. Therefore, preinstallation testing is not required. However,
if preinstallation testing of the units is desired, refer to the
customer acceptance criteria given in the Component Maintenance Manual
for the appropriate unit in the system. Refer to figure 4 in the
"Description and Operation" section of this manual for a list of related
Component Maintenance Manuals.
4. Equipment Changes and Marking
AlliedSignal Electronic and Avionics Systems use a standardized marking
system to identify equipment and their subassemblies which have had
changes incorporated. Refer to the front of the appropriate Component
Maintenance Manual for a list of Service Bulletins affecting the unit.
5. Interchangeability
The MMR will operate in any installation that complies with ARINC
Characteristics 743 and 755 and EUROCAE EDf7ZA. Refer to aircraft
system interwiring diagram figure 211 for particulars.
6. Installation
A. General
The MMR should be installed in the aircraft in a manner consistent
with acceptable workmanship and engineering practices, and in
accordance with the instructions set forth in this publication. To
ensure that the system has been properly and safely installed in the
aircraft. the installer should make a thorough visual inspection and
conduct an overall operational and functional check of the system on
the ground prior to flight.
CAUTION: AFTER INSTALLATION OF THE CABLING AND BEFORE INSTALLATION
OF THE EQUIPMENT, A CHECK SHOULD BE MADE WITH AIRCRAFT
PRIMARY POWER BEING SUPPLIED TO THE MOUNT CONNECTORS TO
ENSURE THAT POWER IS APPLIED ONLY TO THE PINS SPECIFIED IN
AIRCRAFT SYSTEM INTERWIRING DIAGRAM FIGURE 211.
B. Location of Equipment
Location of the MMR in the aircraft is not critical, as long as the
environment is compatible with the equipment design and is not near
equipment operating with high pulse current of high power outputs
such as radar. Refer to the Leading Particulars, figure 7, in the
"Description and Operation" section of this manual‘ Forced air
cooling is required for cooling the MMR in accordance with ARINC
Characteristic 600, The associated cooling equipment must be
mounted in accordance with the manufacturer’s instructions. Refer
Page 202
1.8. 1155 34_55_50 Mar/98
1.8.
AlliedSignaI Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA—555 MULTI—MODE RECEIVER SYSTEM
to outline diagram figure 210 for specific "air flow rate" for the
MMR Part Number being installed.
Antenna and mounting should be in accordance with the manufacturer’s
instructions for the antenna being used. The coaxial cable
connecting the antenna to the mount should be as short and direct as
possible and any required bends should be gradual. when two or more
MMR’s are installed in an aircraft, it is necessary to provide
adequate space isolation between antennas of each system to ensure
that the use of one system does not interfere with the reception
from another system. A minimum of 35 dB of space isolation should
be provided, and any steps which can be taken to provide further
isolation should be considered.
Control unit location and mounting can be determined by mutual
agreement between the user and airframe manufacturer.
Interwiring and Cable Fabrication
(1) General
Figure 211 is a complete aircraft system interwiring diagram
for a single RNA-558 Multi-Mode Receiver System and associated
components. This diagram requires thorough study before the
installer begins installation of the aircraft wiring.
when two or more systems are being installed in the aircraft,
the interconnecting wiring shown in figure 211, as well as all
other installation instructions must be duplicated.
Cabling must be fabricated by the installer in accordance with
figure 21]. Hires connected to parallel pins should be
approximately the same length, so that the best distribution of
current can be effected. AlliedSignal Electronic and Avionics
Systems recommends that all wires, including spares, shown on
aircraft system interwiring diagram figure 211 be included in
the fabricated harness. However, if full ARINC wiring is not
desired, the installer should ensure that the minimum wiring
requirements for the features and functions to be used are
incorporated.
NOTE: To allow for inspection or repair of the connector, or
the wiring to the connector, sufficient lead length
should be left so that the rear connector assembly can
be pulled forward several inches when the mounting
hardware for the rear connector assembly is removed. A
bend should be made in the harness near the connector
to allow water droplets, that might form on the harness
from condensation, to drip off at the bend and not
collect at the connector.
“55 34-55-50 this;
AlliedSignal Electronic and Avionics Syslems
MAINTENANCE MANUAL
RMA-SSB MULTI-MODE RECEIVER SYSTEM
when the cables are installed in the aircraft, they must be
supported firmly enough to prevent movement and should be
carefully protected against chafing. Additional protection
should also be provided in all locations where the cables may
be subject to abuse. In wire bundles, the cabling should not
be tied tightly together as this tends to increase the
possibility of noise pick—up and similar interference, Nhen
routing cables through the airframe, try to avoid running
cables or wire close to power sources (400—HZ generator, etc).
If unavoidable, the cables should cross high-level lines at a
right angle, or high—quality shielded conductors should be
used.
if a cable must pass through a bulkhead between pressurized and
unpressurized zones, this passage must conform to the aircraft
manufacturer’s specifications.
The assembler must be knowledgeable of any system variations
peculiar to the installation, and must thoroughly understand
the complexities associated with handling related problems of
line lengths, capacitance, and of susceptibility to
interference.
The fo lowing determinants are the responsibility of the
installation agency for fabrication of the wiring harness, see
figures 201 and 211.
PIN N0. TVPE SIGNAL NAME FUNCTION
L TP»1 — Reserved
TP-Z Input GNSS Upper Antenna Required for GNSS receiver
input signal .
"(P—3 — Reserved
TP—4 — Reserved
RNA—558 MultifMode Receiver Connector Determinants
Figure 201 (Sheet 1 of 11)
LB. 1155 P 204
34—55-50 ﬂair/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI-MODE RECEIVER SYSTEM
PIN NO. TYPE SIGNAL NAME —I FUNCTION
MP—AI Output ILS Look-Alike One of two low speed ARINC 429
Output Port #1 (A) data output ports to provide
(AFCS) localizer and glide—slope
deviation outputs to the AFCS.
Used to transmit the frequency
word, the ILS ground station
identification, and to repeat
the runway heading and ISO
_ _ ~ ATphabet No. 5—encoded ILS
MP 31 Output éhgpbgogoﬂ'ﬁ (B) facility identifier if received
(AFCS) over the frequency tuning
interfaces. Maintenance data
information is also transmitted
on these ports.
Connect to automatic flight
control system (AFCS).
MP—Cl Input Tune/Funct Select One of two low speed 4129 data
Data Input Port A input ports to receive tuning
(A) information, runway heading,
and ILS ISO Alphabet No. 5
Pip-01 Input Tumé/FUInct 5919“ identifier ARINC 429 labeis.
Data Input Port A
(B)
MP—El Input OMS/CFDS RX A Low speed ARINC 429 data input
port receives maintenance data
and flight leg information from
MP-FI Input OMS/CFDS RX B an onboard maintenance system
(OMS).
RMAfSSB Multi—Mode Receiver Connector Determinants
Figure 201 (S eet 2)
1.8. 1155
34—55—
P 205
50 ﬂair/98
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfSSB MULTI—MDDE RECEIVER SYSTEM
PIN NO. TYPE—1 SIGNAL NAME FUNCTION
MP—Gl Output ILS Look—Alike One of two low speed ARINC 429
Output Port #2 (A) data output ports to provide
(INST) localizer and glide—slope
deviation outputs to other data
utilization devices. Used to
transmit the frequency word,
the ILS ground station
identification, and to repeat
the runway heading and ISO
MP—Hl Output ILS Look—Alike Alphabet No. 5—encoded [LS
OUtDUt Port #2 (B) facility identifier if received
(INST) over the Frequency tuning
interfaces. Maintenance data
information is also transmitted
on these ports. Connect to
other utilization devices
(INST)‘
MP-Jl Input Tune/Funct Select One of two low speed 429 data
Data Input Port 8 input ports to receive tuning
(A) information, runway heading,
and ILS ISO A abet No. 5
”P40 “Put Tune/Fun“ SeleCt identifier ARINC 429 labels.
Data Input Part B
(B)
MP—AZ Output GNSS Time Mark #1 One of three identical but
Out A mutually isolated ports that
provide GNSS time—marked output
, - for use by other aircraft
MP 82 Output giﬁselime Mark “ systems to synchronize the GPS
data
MP—CZ Output GNSS Data #1 TX A One of three identical but _\
mutually isolated ports that
provide the high or low bit
rate data output labels for
each satellite in track in the
l— space vehicle1(SX) raw data
a measurement b oc .
MP DZ Output GNSS Data wl TX B The GNSS data rate is
determined by the GNSS Output
Bus High/Low Program discrete
on MP»J5.
RMAaSSB Multi—Mode Receiver Connector Determinants
Figure 201 (Sheet 3)
LE 1155 Page 206
34—55-50 Mar/98
AlliedSignal Electronic and Avionics Syslems
MAINTENANCE MANUAL
RNA—553 MULTI-MODE RECEIVER SYSTEM
PIN NO. TYPE J SIGNAL NAME FUNCTION I
Reserved
Reserved
Output GNSS Time Mark #2
Out A
Output GNSS Time Mark #2
Out B
Output GNSS Data #2 TX A
One of three identical but
mutua'Hy isolated ports that
provide GNSS time-marked output
for use by other aircraft
systems to synchronize the GPS
data.
One of three identica'l but
mutuaHy isolated ports that
provide the high or Tow bit
rate data output IabeIs For
each sateHite in track in the
SV raw data measurement Mock.
The GNSS data rate is
determined by the GNSS Output
Bus High/Low Program discrete
MP—KZ Output GNSS Data #2 TX B
on MP—JS.
MP-A3 — Reserved
MPABS - Reserved
MP—C3 — Reserved
MP—D3 — __|_Reserved
MP-E3 - Reserved
MP—F3 7 Reserved
MP—G3 f _'7eserved |
MP—H3 7 Reserved I
MP—J3 — Reserved __1
MP—K3 — Reserved
MP—A4 Input Air/Ground Discrete Discrete input that presents a
standard "open" circuit whiIe
the aircraft is on the ground
and a standard "ground" when
the aircraft is airborne.
_._,__
MP—B4 — Reserved J
RNA—558 MuIti—Mode Receiver Connector Determinants
Figure 20] (S eet 4)
I.B. 1155 P 207
34—55—50 “air/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA-SSB MULTI—MDDE RECEIVER SYSTEM
PIN NO.
TYPE SIGNAL NAME
FUNCTION
MP—C4
Input Freq/Funct Data
Source Select
Discrete
MP—D4
— Spare
MP-E4
MPVFA
MP—G4
- Reserved
7 Reserved
Functional Test
Discrete
Discrete input determines which
input tuning port will be
selected. Port "A" (MPQB &
MPQC) are used when the
discrete is in the “ground"
state. Port "B" (MPI3B &
MP13C) are used when the
discrete is in the "open“
state. When the RIA-35B is
installed in an aircraft in
which a dedicated control panel
supplies the tuning
information, Port "B" should be
used. when the RIA—3SB is
installed in an aircraft in
which a Centralized Radio
Management system supplies the
tuning information, Port ”A"
should be used as the primary
control source, and Port "8" as
the secondary or backup control
source.
__I
Discrete input that activates
LRU functional test function.
Gnd/Low = activate functiona
test.
MP—H4
MP»J4
SDI Input #I
Input
Input SDI Input #2
Program Common
Used for encoding the location
(system number) of the MMR in
the aircraft; used with pin
MP—K4 ro ram common)‘
Ground for the SDI code inputs
from pins MP7H4 and/or MPfJA,
for the Output Data
Interrupt/Not Interrupt Program
inputs from pins MP—BS and
MP—DS, and for the Antenna
Monitor Program pin MP—HS.
I.BI 1155
RNA—558 Multi-Mode Receiver Connector Determinants
Figure 201 (Sheet 5)
34—55—50
Page 208
Mar/98
Alliedsignal Electronic and Avionics Sys|ems
MAINTENANCE MANUAL
RMA—5SB MULTI—MODE RECEIVER SYSTEM
PIN Not TVPE SIGNAL NAME FUNCTION
MP-AS — Reserved
MP-BS Input Output Data Not For any faiIures which
Interrupt Program
Reserved
Output Data
Interrupt Program
Spare
Spare
Spare
Antenna Monitor
Program
compromise the integrity of the
setting of the sign/status
matrix (SSM) bits, the MMR wil]
not interrupt data transmission
on ILS Look—Aiike Output
Port #1 (AFCS) and Its
Look-Alike Output Port #2
(INST); used with pin MP—KA
(program common)4
For any faiIures which
compromise the integrity of the
setting of the sign/status
matrix (SSM) hits, the MMR
interrupts data transmission on
ILS Look—Alike Output Port #1
(AFCS) and IL5 Look—AIike
Output Port #2 (INST); used
with pin MP—K4 (program
common .
Discrete output supplies the
ground for the antenna monitor
enable when connected to
Program Common, pin MP—KA.
Antenna monitoring function is
disabied when MP—HS is open.
GNSS Bus Hi/Lo
Program
Discrete output determines the
output rate for the GNSS output
buses.
Gnd/Low = Low Speed ARINC 429;
Open/High = High Speed
ARINC 429.
Spare
LB. 1155
RMA—SSB MuIti—Mode Receiver Connector Determinants
Figure 20] (Sheet 6)
34-55-50 “51:53?
AlliedSignal EIectmnic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
I—‘
PIN N0. TVPE
SIGNAL NAME
FUNCTION
MP-A6
S are
Spare
GNSS Time Mark #3
Out A
GNSS Time Mark #3
Out B
One of three identical but
mutuaﬂy isoIated parts that
provide GNSS time—marked output
for use by other aircraft
systems to synchronize the GPS
data.
MP—G7
MP—H7
MP-J7
MP-K7 Spare
MP—AB IRS #I RX A One of two ARINC 429 high speed
inputs for inertia] system to
p_ IRS ﬂ RX B initialize time and position
M 88
RNA—558 MuIti-Mode Receiver Connector Determinants
Figure 201 (Sheet 7)
1.8. 1155
34-55-50 Paairiéz
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfSEB MULTI—MODE RECEIVER SYSTEM
r___________
PIN NO. TYPE SIGNAL NAME FUNCTION
MP—CB Input DADS #1 RX A One of two ARINC 429 low speed
DADS #1 RX 5 altitude.
Reserved
data.
inputs from digital air data
computer system to initialize
Reserved
IRS #2 RX A One of two ARINC 429 high speed
inputs for inertial system to
IRS #2 RX B initialize time and position
DADS #2 RX A
DADS #2 RX B altitudes
One of two ARINC 429 low speed
inputs from digital air data
computer system to initialize
Spare
MP-BQ
Spare
Spare
Spare
MP—EQ Output GNSS Data #3 TX A One of three identical but
mutually isolated ports that
provide the high or low bit
rate data output labels for
each satellite in track in the
7 SV raw data measurement block‘
MP F9 Output GNSS Data #3 TX B The GNSS data rate is
determined by the GNSS Output
Bus High/Low Program discrete
on MP—J5.
MP—G9 - Spare
MP—H9 — Spare
MPfJQ - Spare
MP—K9 ~ Spare
MP—AIO — Spare
MP—BIO - Spare
RNA—558 Multi-Mode Receiver Connector Determinants
Figure 201 (Sheet 8)
1.8. 1155 Page 21
34—55—50
Mar/98
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RNA-558 MULTI—MODE RECEIVER SYSTEM
PIN NO. TYPE SIGNAL NAME FUNCTION
— Spare
Spare
Output (HI) Locah‘zer audio output to audio
Output (LO) distribution system.
i]
MP7F13 — | Spare
MP-EH — | Reserved I
MP-FH — | Reserved I
NIP—£15 — | Reserved 1
RMAASEB Multi—Mode Receiver Connector Determinants
Figure 201 (Sheet 9)
LB. 1155 P 212
34—55—50 3313/93
Alliedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
PIN NO. | TYPE SIGNAL NAME FUNCTION
MP7F15 Input Tune/Functional Inhibits re—tuning the ILS
Test Inhibit receiver from the channel
Discrete selected for an automatically
coupled approach or place in
the self-test condition once an
approach has been started‘
BP—l — Spare
BP—2 - Spare
BP-3 — Spare
BP—4 Output Control Panel 115VAC, 400Hz is available on
115VAC Power Output pins BP—4 and BP~6 for routing
(HOT) to a control panel in those
installations which use an
individual control panel rather
than an integrated
Frequency/Function Selection
system supplied with aircraft
power directly.
BP-5 — Spare
BP-G Output Control Panel llSVAC, 400HZ is available on
115VAC Power Output pins BP—4 and BP-G for routing
(COLD) to a control panel in those
installations which use an
individual control panel rather
than integrated
Frequency/Function Selection
system supplied with aircraft
power directly.
BP77 Input llSVAC (COLD) Primary power return
BP—B Input Chassis Ground Chassis ground
BP-9 Input 115VAC (HOT) Primary input power to MMR
(2A Circuit
Breaker)
BPflo — Spare
BP—II , Spare
RNA—55 Multi—Mode Receiver Connector Determinants
Figure 201 (Sheet 10)
LB. 1155 Page 213
34—55—50
Mar/98
AlliedSignal Electronic and Avionics Sysiems
MAINTENANCE MANUAL
RNA—558 MULTI—MODE RECE
IVER SYSTEM
Lem N0. | we I
SIGNAL NAME
FUNCTION
BP~12 Input
BP—13 Input
Localizer Antenna
Glide—Slope Antenna
Required for localizer input
signal.
Required for glide»slope input
_|_signal .
.—
RMA—55B Multi—Mode Receiver Connector Determinants
Figure 201 (Sheet 11)
Reserve
(2)
d and Spare Wires
If the installer does not wish to connect all wires, he/she may
select wires reserved for optional functions which his/her
system does not contain and delete these wires.
He/she should
also decide which future spare wires to include in the
install
ation.
Reserved and spare wires are identified in
figure 201 and in interwiring diagram figure 209.
(3)
Source/Destination Identifier (SDI) Program Encoding
A connection is required from the ”program common" pin MP—K4 to
the appropriate source/destination identifier (SDI) pin to
identify each MMR in multiple system installations (refer to
figure
a connection identifying it as the No. 1 system.
202).
Installations having only one MMR should include
These
connections should not be omitted from any installation.
MMR NUMBER
SDI 2, MP—J4
CONNECTOR PIN
SDI 1, MP—H4
Not Applicable
Open
Open
Open
To MP—K4
To MP—K4
To MP—K4
Open
To MP—K4
1.8. 1155
SDI Encoding Pin Conf
Figure 202
iguration
34—55—50
Page 214
Mar/98
AIIiedSignal Electronic and Avionics Syslems
MAINTENANCE MANUAL
RMAASSB MULTIfMODE RECEIVER SYSTEM
(4) Output Data Interrupt Program
For any failures which compromise the integrity of the setting
of the sign/status matrix bits, the MMR stops all data
transmissions on ILS Look Alike (AFCS) Bus #1 and IL5 Look
Alike (INST) Bus #2 when the Output Data Interrupt Program pin
and the Output Data Not Interrupt Program pin are set as shown
in figure 203.
CONNECTOR PIN
OUTPUT DATA NOT OUTPUT DATA
STATUS INTERRUPT, MP-BS INTERRUPT, MPfDS
Not Valid Open Open I
Interrupt Open To MP—K4 I
Not Interrupt To MP—K4 Open
Not Valid To MP—K4 To MP-K4
Output Data Interrupt Encoding Pin Configuration
Figure 203
D. Installation of System
(1) Mounting Base
The selected mounting base for the RMA~SSB Multi—Mode Receiver
should be wired according to the system interwiring diagram,
figure 211, and installed according to the manufacturer’s
instructions The mounts are designed to be removed without
rewiring the connectors Follow the equipment manufacturer’s
installation instructions to install the mount into the
airframes
IIB. 1155 P 215
34—55-50 aair/QS
LB.
(2)
(3)
1155
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfSSB MULTI—MODE RECEIVER SYSTEM
To wire the mounts into the system, first remove the mount
connector cover and connector plate assembly. Then crimp or
solder (as applicable) the interconnecting wiring to the
appropriate connector pins. Finally, return the connector
plate assembly and cover to their original positions.
NOTE: To allow for inspection or repair of the connector, or
the wiring to the connector, sufficient lead length
should be left so that the rear connector assembly can
be pulled forward several inches when the mounting
hardware for the rear connector assembly is removed. A
bend should be made in the harness near the connector
to allow water droplets, that might form on the harness
from condensation, to drip off at the bend and not
collect at the connector.
RMA-SSB Multi-Mode Receiver (MMR)
The MMR is installed in the mount as follows:
(a) Slide the MMR into the mount until the guide pins are
aligned and the electrical connectors are firmly engaged.
(b) Secure the front of the MMR to the mount by tightening the
two knurled screw clamps (located on the front of the
mount) until they are firmly seated over hold—down hooks
located on the front of the unit.
(c) Safety—wire the two screw clamps.
MMR Control Panel
The selected MMR control panel should be wired according to the
system interwiring diagram, figure 211, and the manufacturer’s
instructions. For installation procedure and mounting
dimensions, refer to the applicable manufacturer’s
instructions.
Electronic Horizontal Situation Indicator
The electronic horizontal situation indicator (EHSI) should be
mounted in the aircraft instrument panel to provide easy
visibility and to conform to customer requirements and the
installation instructions of the manufacturer. lnterwiring
should be in accordance with figure 211, system interwiring
diagram.
34-55-50 “3253:
LB.
(5)
(5)
(7)
1155
AlliedSignal Electronic and Avionics Sysiems
MAINTENANCE MANUAL
RNA—558 MULTI»MODE RECEIVER SYSTEM
Localizer Antenna
Install the localizer antenna in accordance with the
manufacturer’s instructions. An important consideration is the
placement of the localizer antenna with respect to other
antennas, especially the antenna used with vhf transmitters.
Localizer operation can be seriously affected by the output (at
least 25 watts) from the transmitter antenna. It is therefore
recommended that at least 35 dB (preferably 45 dB) of space
attenuation (isolation) be supplied between the localizer
antenna and vhf transmitter antenna.
The system installation requires a coaxial cable between the
mount and the antenna. This cable should be as short and
direct as possible to limit attenuation. Any required bends
should be gradual. Any signal loss attributed to the cable
will be detrimental to localizer reception and must be held to
a minimum. The interconnecting coaxial cable must have an
impedance of 50 ohms. Additionally, the antenna system should
present less than a 5:1 VSWR under all conditions including
precipitation and icing.
Gl ide-Slope Antenna
Install the glide-slope antenna in accordance with the
manufacturer’s instructions. The system installation requires
a coaxial cable (type RG-SS/U) between the antenna and the
mount. This cable should be as short and direct as possible to
limit attenuation. Any required bends should be gradual. Any
signal loss attributed to the cable will be detrimental to
glide»slope operation and must be held to a minimum. The
interconnecting coaxial cable must have an impedance of
50 ohms. Additionally, the antenna system should present less
than a 5:1 VSNR under all conditions including precipitation
and icing.
GNSS Antenna (if required)
Install the GNSS antenna in accordance with the manufacturer’s
instructions. The system installation requires a coaxial cable
between the antenna and the mount. This cable should be as
short and direct as possible to limit attenuation. Any
required bends should be gradual. Any signal loss attributed
to the cable will be detrimental to GNSS receiver operation and
must be held to a minimum. The interconnecting coaxial cable
must have an impedance of 50 ohms. Additionally, the antenna
system should present less than a 20:1 VSNR under all
conditions including precipitation and icing.
34-55-50 “3353;
Ailiedsignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfSSB MULTI»MODE RECEIVER SYSTEM
7. Inspection and System Check Procedures
NOTE: Inspection and check procedures for the RNA—558 MultiAMode
Receiver (MMR) includes checkout of all interfacing units that
may affect performance of the MMR.
A. Inspection
Figure 204 is a visual inspection check procedure and should be
performed after system installation, prior to system checkout. In
addition, the procedure should be used as a periodic inspection
check.
EQUIPMENT INSPECTION/CHECK PROCEDURE
3 MCU Unit As defined by manufacturer’s instructions.
Mount
RMA-SSB (1) Check that unit is fully inserted in mount and that
Multi—Mode the knurled screw clamps which secure the unit in
Receiver the mount are tight and safety wired.
(2) Inspect the case for deformation, dents, corrosion,
and damage to finish; ensure that ventilation holes
in the unit are not clogged.
(3) Check that ARINC 600 cooling source is securely in
place.
Control Panel As defined by manufacturer’s instructions.
Electronic As defined by manufacturer‘s instructions.
Horizontal
Situation
Indicator
Localizer As defined by manufacturer’s instructions
Antenna
Glide—Slope As defined by manufacturer’s instructions
Antenna
GNSS Antenna As defined by manufacturer’s instructions
Inspection/Check Procedures
Figure 204
1.8. 1155 P 218
34—55—50 331/93
1.8.
B.
(1)
(2)
(3)
1155
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—5SB MULTI—MODE RECEIVER SYSTEM
System Checkout
General
After installation of the RNA—558 MultivMode Receiver System,
and inspection of the equipment per previous figure 204,
perform a continuity and visual check of the system interwiring
per paragraph 7.8.(2). A post-installation test per paragraph
7.3.(3) should then be performed.
System Interwiring Check
Visually check the system interwiring for abnormalities, such
as cables rubbing unprotected metal edges or tightly stretched
cables. Check continuity of all interwiring. In particular,
check the following:
(a) Check that the MMR is properly installed and the hold-down
screw clamps are tight.
(b) Check wiring harness connectors for security and
connection to the MMR.
(c) Check that antenna transmission line connectors are
securely fastened.
(d) Check that control panel connectors are securely fastened.
(e) Check that EHSI connectors are securely fastened.
(f) Check that cables do not interfere with aircraft controls
or other equipment.
Post—Installation Check
(a) Test Equipment Required
None Required.
(b) System Test
A functional self test of the LRU may be initiated by
pressing the "test" key pushbutton switch as designated on
the front panel LCD (figure 205). Although the
normal-mode screen indicates that this is actuated from
the right key, the left key has the same function if
pressed while the MMR LCD is in its normal mode.
34-55-50 ”3355:
I.B.
Alliedsignal Electronie and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
M M R
P N 0 6 6 ,
0 0 2 9 — 0 1 0 1
S w 0 I / 0 1
P U S H T 0
L T E S T J
F f‘\
x\_// ‘xu
Typica] ”NormaT-Mode" Screen
Figure 205
The self-test mode starts by dispTaying the "Test in
Progress" screen (figure 206) one second after pressing
the "test” key. This is displayed for four seconds with a
moving thermometer aTong the bottom of the LCD indicating
the progress of the test from one to five secondsi
M M R
T E S T I N
P R O G R E S S
5 0 l O 0
X X X X X X X X X X
(Aw
x/
”Test in Progress" Screen
Figure 206
1155
34-55-50 ”3253:
1.8
1155
AlliedSigml Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTIVMODE RECEIVER SYSTEM
The "Normal—Mode" screen (figure 205) is displayed for the
first second of the test sequence.
Once complete, the "Test Complete, No Failures" screen is
displayed (figure 207), or the "Test Complete, Failures"
screen is displayed (figure 208). Both screens contain
two key selections each: "MAINT" and "RETURN" or "MAINT"
and "WHY’3", respectively.
0 "MAINT" — For both screens, "MAINT" is located
on the left key. This allows the
initiation of the extended
maintenance pages of the system for
troubleshooting Refer to
paragraph 4 of "Fault Isolation"
section 100 of this manual.
5 "RETURN" — In the "Test Complete, N0 Failures"
screen, the "RETURN" key to the right
returns the system to its normal mode
screen (figure 205).
0 "WHY?" — In the "Test Complete, Failures"
screen, the "WHY?" key to the right
puts the system into the
display—failures mode where
indiVidual system failures are
displayed one per page. Refer to
paragraph 3 of "Fault Isolation"
section 100 of the manual.
while in the selﬁtest mode, not pressing either key for
five minutes causes the system to return to the
"Normal-Mode“ screen (figure 205),
34-55-50 “3:53;
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMAfESB MULTI—MODE RECEIVER SYSTEM
M M R
T E S T C O M P L E T E
N O F A I L U R E S
M A I N T R E T U R N
"Test CompTete, No FaiTuv‘es" Screen
Figure 207
M M R
T E S T C 0 M P L E T E
"Test CompTete, Faﬂures" Screen
Figure 208
Page 222
LB. 1155 34_55_5O Mar/98
AlliedSignal EIecironic and Avionics Systems
MAINTENANCE MANUAL
RMA-SSB MULTI—MDDE RECEIVER SYSTEM
C. Ramp Test
(1) Figure 209 describes one test set that can be used for ramp
testing to verify the operational readiness of the RMA—SSB
Multi-Mode Receiver.
Test sets other than that listed in
figure 209 can be used if their characteristics meet the
requirements listed under "Characteristics Required" in
figure 209.
DESCRIPTION
CHARACTERISTICS
REQUIRED
Nav Test Set
(Must include LDC/GS
functions)
Must have at least one
LOC and one GS
frequency (1000134
accuracy); internally
stepped or adjustable
LOC and GS modulation;
and rf signal must be
radiated from an
antenna.
LOG/GS centering
accuracy = $002 DDM.
REPRESENTATIVE TYPE
Instrument Flight
Research Corp. (IFR)
Model NAV—401L
Table of Test Equipment
Figure 209
(2) Locate ramp test set near localizer and glide—slope antennas.
Set up ramp test set according to manufacturer’s instructions
to radiate a 0 DDM localizer and glide—slope signal.
NOTE:
For MMR’s equipped with GNSS Receiver (—1101, -1151),
locate aircraft at the compass rose of the air field or
some known surveyed spot on the air field for making
latitude and longitude measurements.
(3) Set aircraft ILS control panel frequency selector to correspond
to the ILS frequency of the test set.
on—off switch to ON.
(4) Observe cockpit display localizer indications.
course deviation indicator should be centered.
status indication should be normal.
(5) Observe cockpit display glide—slope indications.
indicator should be centered.
should be normal.
1.8. 1155
34—55-50
Set ILS control panel
Localizer
Local izer
Gl ide—slooe
Gl ide—sl ope status indication
Page 223
Mar/98
1.8.
(5)
(7)
(8)
(9)
(10)
(11)
(12)
(13)
(14)
(15)
1155
AlliedSignal Electronic and Avionics Systems
MAlNTENANCE MANUAL
RMA—S5B MULTI-MODE RECEIVER SYSTEM
Set test set controls to generate a localizer test signal of
+0.155 DDM (90 Hz tone predominant)‘ Cockpit display course
deviation indicator should deflect right. Localizer status
indication should be normal.
Set test set controls to generate a localizer test signal of
-0.155 DDM (150 Hz tone predominant). Cockpit display
deviation indicator should deflect left. Localizer status
indication should be normal.
Set test set localizer controls for an output signal with the
90 Hz signal equal to the 150 Hz signal (0 DDM). Cockpit
display course deviation indicator should be normal.
Set test set localizer controls to individually remove the
90 Hz and 150 Hz signals. Localizer status indication should
be no computed data (NCD) when either signal is removed.
Set test set controls to generate a glide-slope test signal of
+0.175 DDM (90 Hz tone predominant). Cockpit display
glide—slope indicator should deflect down. Glidefslope status
indication should be normal.
Set test set glide—slope controls to generate a glide—slope
test signal of -0.]75 DDM (150 H7. tone predominant). Cockpit
display glide—slope indicator should deflect up. Glide—slope
status indication should be normal.
Set test set glide-slope controls for an output signal with the
90 Hz signal equal to the 150 Hz signal (0 DDM). Cockpit
display course deviation indicator should be centered.
Localizer status indication should be normal.
Set test set glide—slope controls to individually remove the
90 Hz and 150 Hz signals. Cockpit display glide—slope status
indication should he NCD when either signal is removed.
Check aircraft audio system for ILS station identification tone
during ILS operation of MMR. Tone should identify station
generated by the test set.
For —1101 and —1151 MMR’s, verify that the cockpit displays the
correct latitude and longitude of the aircraft as shown for the
compass rose of the air—field chart or the known surveyed spot
in the air field.
34-55-50 “3.2.52;
AIIiedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI—MODE RECEIVER SYSTEM
Flight Tests
(1) Set aircraft MMR control panel to select the frequency of a
nearby ILS station.
(2) Apply power to MMR system.
(3) Fly toward ILS runway and perform ILS approach using both the
localizer and glide-slope functions. Observe EHIS for proper
localizer and glide»slope indications during approach.
8. Removal and Replacement
A.
Removal
(1) Loosen the two knurled screw clamps (located on the front of
mount) that secure the MMR to the mount.
(2) Gently pull the MMR forward until it is disconnected from the
rear connector and guide pins.
Replacement
(1) Slide the MMR onto the tray of the mount and then gently push
the MMR until the guide pins are aligned and the connectors
make a firm connection.
(2) Tighten the two knurled screw clamps located on the front of
the mount until they are firmly seated over the hold—down hooks
located on the front of the radio altimeter.
(3) Safety wire the two knurled screw clamps.
9. Maintenance Procedures
A.
Adjustments and Alignments
There are no adjustments or alignments required for the MMR. All
alignment and adjustment procedures are accomplished during bench
maintenance. The technician should remove the unit from the
aircraft and reference should be made to the related maintenance
manual when unit performance indicates an adjustment or an alignment
is required.
System Protection
The system should be protected by a Z—ampere circuit breaker located
at the circuit breaker panel in the aircraft.
1.8. 1155 P 225
34—55—50 3513/98
AlliedSignal Electronic and Avionics Systems
MAINTENANCE MANUAL
RMA—SSB MULTI-MODE RECEIVER SYSTEM
C. Lubrication Practices
There are no requirements for periodic Tubrication of any RNA—558
Multi~Mode Receiver System component.
D. Cieaning
when deemed necessary, depending upon the environment to which the
equipment is exposed and the intensity of use, periodic cieaning
shouid be performed. Any dust on the RNA-SSE Multi-Mode Receiver
System LRU’s shouid be wiped off with a iint—free cioth.
NOTE: Any cleaning of equipment interiors should be iimited to
that required when performing overhaui (bench—type) work
Page 226
I.Bt 1155 34_55_5O Mar/98
baunmwni magma nan 53:78 minim
xzzqmzzﬁm 35:72.
xzyvmmw xcrjnzog mmnmzmn mzc>r
Eﬁwmwm 3:57:03 xmnmE—mm m m2. 7; 15; 22:72 5 S7 57 wma 7 3 WE. m 775 ax: 7
7 i 7 7 7 ‘ 7 . , 7 ‘ ‘ m ‘ 7
33507 $42 N E N
3353
57>th 77777345? $223. 9777272271 5:75. 0:53
223 ED 252 5
. v N2 Ms
77m 73m ”whﬂmlum‘mo 3m 5&5

Source Exif Data:

File Type                       : PDF
File Type Extension             : pdf
MIME Type                       : application/pdf
PDF Version                     : 1.3
Linearized                      : Yes
Create Date                     : 2001:07:17 14:24:07
Producer                        : Acrobat Distiller 4.0 for Windows
Author                          : jsoscia
Title                           : 1276.pdf
Modify Date                     : 2001:07:17 14:24:13-04:00
Page Count                      : 82

EXIF Metadata provided by EXIF.tools

Honeywell RMA-55B Localizer/Glideslope/Receiver User Manual 1276

Honeywell International Inc. Localizer/Glideslope/Receiver 1276

8

FCC ID Filing: AOIRMA-55B

Navigation menu

Namespaces

Views

Navigation