Page 1
n
SYSTEM INSTALLATION MANUAL
Global
®
AFIS
®
AIRBORNE FLIGHT INFORMATION SYSTEM
400-045500-0001 through -0006
400-045500-0130 / -0210 / -2010 / -0211 / -2011
42000-01-01, -02-02, -03-03, -04-03
MANUAL NUMBER 150-1255-000
REVISION 11 MARCH, 2001
Page 2
WARNING
Prior to export of this document, review for export license requirement is needed.
COPYRIGHT NOTICE
2000-2001 Honeywell International Inc.
Reproduction of this publication or any portion thereof by any means without the expressed
written permission of Honeywell is prohibited. For further information, contact the Manager
of Technical Publications, Honeywell, Olathe, Kansas 66061. (913) 782-0400
Page 3
Global
AIRBORNE FLIGHT INFORMATION SYSTEM
SECTION 1
GENERAL INFORMATION
Paragraph Page
1.1 INTRODUCTION 1-1
1.2 EQUIPMENT DESCRIPTION 1-1
1.2.1 DATA MANAGEMENT UNIT 1-1
1.2.2 ANTENNA SWITCHING UNIT 1-1
1.2.3 DATA TRANSFER UNIT 1-1
1.2.4 SATELLITE COMMUNICATION UNIT 1-2
1.2.5 HIGH POWER AMPLIFIER/LOW NOISE AMPLIFIER 1-2
1.2.6 SATELLITE ANTENNA 1-2
1.2.7 CONFIGURATION MODULE 1-2
1.2.8 ARNAV MFD 5115 RPU 1-2
1.3 TECHNICAL CHARACTERISTICS 1-3
1.3.1 UNIT SPECIFICATIONS 1-3
1.3.2 SYSTEM SPECIFICATIONS 1-7
1.3.2.1 FUEL FLOW INPUT (ANALOG INPUT) 1-7
1.3.2.2 RS-422A SERIAL DATA INPUT 1-16
1.3.2.3 ARINC 429 INPUT 1-18
1.3.2.4 ANALOG OUTPUTS (DMU) 1-19
1.3.2.5 RS-422A SERIAL DIGITAL OUTPUTS (DMU) 1-20
1.3.2.6 ARINC 429 OUTPUTS 1-21
1.3.2.7 PRINTER INTERFACE 1-22
1.3.2.8 CABIN TERMINAL INTERFACE 1-24
1.3.2.9 DISCRETE INPUTS 1-26
1.4 UNITS AND ACCESSORIES SUPPLIED 1-29
1.4.1 DATA MANAGEMENT UNIT 1-29
1.4.2 FLIGHT PLANNING SERVICE 1-30
1.4.3 DMU CONFIGURATION MATRIX 1-33
1.5 ACCESSORIES REQUIRED 1-35
1.5.1 DMU INSTALLATION KIT 1-35
1.5.2 CONFIGURATION MODULE UNIT 1-35
1.5.3 VHF ANTENNA 1-35
1.6 OPTIONAL ACCESSORIES 1-35
1.6.1 DATA TRANSFER UNIT 1-35
1.6.2 ANTENNA SWITCHING UNIT 1-36
1.6.3 SATELLITE SYSTEM (SATAFIS) 1-37
1.6.4 PRINTER 1-37
1.6.5 CABIN PERSONAL COMPUTER 1-37
1.7 LICENSE REQUIREMENTS 1-37
1.7.1 VHF RADIO 1-37
1.7.2 INMARSAT SATELLITE APPROVAL 1-37
1.7.3 ARNAV RPU INSTALLATION KIT 1-38
1.8 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS 1-38
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AIRBORNE FLIGHT INFORMATION SYSTEM
SECTION 2
MECHANICAL INSTALLATION
Paragraph Page
2.0 INTRODUCTION 2-1
2.1 UNPACKING AND INSPECTING EQUIPMENT 2-1
2.2 GENERAL INSTALLATION REQUIREMENTS 2-1
2.3 DATA MANAGEMENT UNIT (DMU) INSTALLATION 2-2
2.4 DATA TRANSFER UNIT (DTU) INSTALLATION 2-2
2.5 CONFIGURATION MODULE 2-2
2.6 SATELLITE COMMUNICATION UNIT (SCU) INSTALLATION 2-3
2.7 HPA/LNA INSTALLATION 2-3
2.8 ANTENNA INSTALLATION 2-3
2.8.1 BONDING CHECKLIST 2-3
2.8.2 LOW PROFILE JET BLADE ANTENNA INSTALLATION 2-3
2.9 ARNAV RPU INSTALLATION 2-4
2.9.1 INSTALLATION KIT 2-4
2.9.2 INSTALLATION GUIDE 2-4
2.9.3 COOLING CONSIDERATIONS 2-4
2.9.4 INSTALLATION CONSIDERATIONS 2-4
2.9.5 DATABASE CARD 2-4
SECTION 3
ELECTRICAL INSTALLATION
3.0 GENERAL INFORMATION 3-1
3.1 AFIS WX DISPLAY 3-117
SECTION 4
AFIS CONFIGURATION AND CHECKOUT
Paragraph Page
4.0 GENERAL 4-1
4.0.1 SPECIAL EQUIPMENT AND MATERIALS 4-1
4.0.2 GENERAL 4-1
4.1 CONFIGURATION MODULE PROGRAMMING 4-4
FOR GNS-500A SERIES 4/5 WITH DMU P/N 42000-XX-XX
4.2 CONFIGURATION MODULE PROGRAMMING FOR GNS-500A SERIES 4-19
FOR GNS-500A SERIES 4/5 WITH DMU P/N 400-045500-XXXX
4.3 CONFIGURATION MODULE PROGRAMMING FOR GNS-1000, 4-33
GNS X, GNS-XES, GNS-XL OR GNS-XLS WITH DMU P/N 42000-01-01
OR 42000-03-03
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AIRBORNE FLIGHT INFORMATION SYSTEM
SECTION 4
AFIS CONFIGURATION AND CHECKOUT (cont)
4.4 CONFIGURATION MODULE PROGRAMMING FOR GNS-1000, 4-44
GNS X, GNS-XES, GNS-XL OR GNS-XLS WITH DMU P/N
400-045500-0001, -003, OR -005 AND OTHER FMS MANUFACTURES
USING DMU P/N 400-045500-0001, -0002, -0003, -0004, -0005, -0006
OR -0130
4.5 CONFIGURATION MODULE PROGRAMMING FOR GNS-1000, GNS-X, 4-59
GNS-XES, GNS-XL OR GNS-XLS WITH DMU P/N 400-045500-0210 OR
400-045500-2010.
4.6 CONFIGURATION MODULE PROGRAMMING FOR GNS-1000, GNS-X, 4-75
GNS-XES, GNS-XL OR GNS-XLS WITH DMU P/N 400-045500-0211 OR
400-045500-2011.
4.7 CONFIGURATION MODULE PROGRAMMING FOR 739 MCDU AND 4-92
OTHER FMS MANUFACTURERS WITH DMU P/N 400-045500-2011 OR
0211.
4.8 AFIS DATA MANAGEMENT UNIT (DMU) (ProComm Plus Reconfiguration 4-101
Procedure)
4.9 GENERAL 4-109
4.10 SYSTEM TEST AND CHECKOUT WITH CUSTOMER SUPPLIED 4-109
PRE-PROGRAMMED AFIS DISK
LIST OF ILLUSTRATIONS
Figure Page
1-1 AFIS GRAPHICS SERVICE AND DATABASE APPLICATION 1-31
2-1 DMU PN 42000-XX-XX or 400-045500-XXXX 2-5
2-2 DMU TRAY PN 42701-1 2-6
2-3 CONFIGURATION MODULE MOUNTING PROVISION P/N 31990-1 2-7
2-4 CONFIGURATION MODULE OUTLINE AND MOUNTING P/N 31990-1 2-8
2-5 DATA TRANSFER UNIT (DTU) PN 43000-01-01-X 2-9
2-6 TRIPLE PORT DTU PN 15655-XXXX 2-11
2-7 DTU DZUS MOUNTING 2-13
2-8 DTU TRAY MOUNTING 2-13
2-9 DTU INSTRUMENT PANEL MOUNTING PROVISION 2-14
2-10 DTU TRAY PN 43010-X 2-15
2-11 ANTENNA SWITCHING UNIT (ASU) PN 44000-1 2-17
2-12 SATELLITE COMMUNICATION UNIT (SCU) 2-19
2-13 SCU TRAY PN 300-317337-01 2-21
2-14 HIGH POWER AMPLIFIER / LOW NOISE AMPLIFIER (HPA / LNA) 2-23
2-15 LOW PROFILE JET BLADE ANTENNA 2-25
2-16 MFD 5115 RPU 2-27
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AIRBORNE FLIGHT INFORMATION SYSTEM
LIST OF ILLUSTRATIONS (cont)
Figure Page
3-1 DMU FUEL FLOW WIRING USING ELDEC INDICATOR 3-3
3-2 DMU FUEL FLOW WIRING FOR VARIOUS INDICATORS 3-5
3-3 DMU FUEL FLOW INTERTECHNIQUE 3-7
3-4 DMU FUEL FLOW GE 5 VRMS AC 3-9
3-5 DMU FUEL FLOW ELDEC TRANSMITER AS SOURCE 3-11
3-6 DMU TO TRIPLE PORT DTU 3-13
3-7 DMU TO DTU PN 43000-01-01-3 AND PN 43000-01-01-4 3-15
3-8 DMU TO DTU PN 43000-01-01-1 AND PN 43000-01-01-2 3-17
3-9 DMU TO NMU GNS-X 3-19
3-9A CDU-XLS TO AFIS INTERFACE 3-33
3-10 DMU TO FMC GNS-500A SERIES 4/5 3-37
3-11 DMU TO SWITCHED AFIS ANTENNA 3-39
3-12 DMU TO DEDICATED AFIS ANTENNA 3-41
3-13 DMU TO PRINTERS AND TERMINALS 3-43
3-14 DMU TO CONFIGURATION MODULE AND SATFONE SYSTEM 3-45
3-15 DMU TO SCU 3-47
3-16 DISCRETE WIRING 3-51
3-17 DMU FUEL FLOW WIRING USING ELDEC INDICATOR 3-53
3-18 DMU FUEL FLOW WIRING FOR VARIOUS INDICATORS 3-55
3-19 DMU FUEL FLOW INTERTECHNIQUE 3-57
3-20 DMU FUEL FLOW GE 5 VRMS AC 3-59
3-21 DMU FUEL FLOW USING ELDEC TRANSMITTER AS SOURCE 3-61
3-22 DMU TO TRIPLE PORT DTU PN 15655-XXXX 3-63
3-23 DMU TO DTU PN 43000-01-01-3 AND PN 43000-01-01-4 3-65
3-24 DMU TO DTU PN 43000-01-01-1 AND PN 43000-01-01-2 3-67
3-25 DMU TO FMC GNS-1000 3-69
3-26 DMU TO GNS-500A SERIES 4 3-77
3-27 DMU TO SWITCHED AFIS ANTENNA 3-79
3-28 DMU TO DEDICATED AFIS ANTENNA 3-81
3-29 DMU TO PRINTERS AND TERMINALS 3-83
3-30 DMU TO CONFIGURATION MODULE 3-85
3-31 DMU TO SCU 3-87
3-32 DMU TO ARNAV RPU AND GNS-XLS WIRING DIAGRAM 3-91
3-32A DMU TO FLIGHT DATA ACQUISITION AND MANAGEMENT SYSTEM 3-93
3-32B DMU TO 739 MCDU 3-95
3-33 DMU CONNECTOR PN 400-045500-XXXX 3-97
3-34 DMU CONNECTOR PN 42000-XX-XX 3-102
3-35 DTU CONNECTOR PIN ASSIGNMENT PN 43000-01-01-1 AND -2 3-105
3-36 DTU CONNECTOR PIN ASSIGNMENT PN 43000-01-01-3 AND -4 3-106
3-37 DMU J201 PIN ASSIGNMENT 3-107
3-38 CONFIGURATION MODULE CONNECTION 3-108
3-39 ANTENNA SWITCHING UNIT PIN ASSIGNMENT 3-109
3-40 TRIPLE PORT DTU CONNECTOR PIN ASSIGNMENT PN 15655-0X01 3-110
3-41 SCU UNIT CONNECTOR 3-111
3-42 REMOTE PROCESSOR UNIT (RTU) MATING CONNECTOR 3-113
3-43 CONNECTORS USED 3-114
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AIRBORNE FLIGHT INFORMATION SYSTEM
RECORD OF REVISIONS
REV.
NO.
10 05/2000
11 03/2001
REVISION
DATE
1 03/01/88
2 06/01/88
3 04/01/89
4 10/01/92
5 05/94
6 06/95
7 01/98
8 10/98
9 03/2000
DATE
INSERTED
BY
REV.
NO.
REVISION
DATE
DATE
INSERTED
BY
IMAFISJWA RR-1
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AIRBORNE FLIGHT INFORMATION SYSTEM
RECORD OF REVISIONS (cont.)
REV.
NO.
REVISION
DATE
DATE
INSERTED
BY
REV.
NO.
REVISION
DATE
DATE
INSERTED
BY
IMAFISJWA RR-2
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AIRBORNE FLIGHT INFORMATION SYSTEM
SECTION 1
GENERAL INFORMATION
1.1 INTRODUCTION
This manual contains information relative to the physical, mechanical and electrical characteristics
of the Global AFIS unit. General system installation information is also included.
1.2 EQUIPMENT DESCRIPTION
The Airborne Flight Information System (AFIS) consists of the following aircraft components: Data
Management Unit, Antenna Switching Unit (optional), Data Transfer Unit (optional), Satellite
Communication Unit (optional), High Power Amplifier/Low Noise Amplifier (optional), Satellite
Antenna (optional), Configuration Module and ARNAV MFD5115 RPU (optional).
1.2.1 Data Management Unit (see Table 1-10)
The Data Management Unit (DMU) is a standard 1/2 ATR short unit. The DMU formats data
received from the DTU, VHF network or Satellite network. The DMU formats data for sending to
the ground from the aircraft using the VHF or Satellite network. The data is presented to the flight
management system interfaced to the DMU for display on a CRT/CDU. The DMU incorporates a
data quality VHF transceiver. The transceiver is tuned automatically by the DMU to use the
appropriate VHF ground station for the purpose of transmitting data to and receiving data from the
Global Data Center while in flight. The DMU can select between the VHF data network and a
satellite network automatically if the DMU is connected to a satellite network. The DMU is capable
of interfacing with one to six flight management systems. The DMU can be interfaced to two
printers as well as two personal computers.
1.2.2 Antenna Switching Unit (44000-1)
The Antenna Switching Unit (ASU) is a small box that is required for those installations where the
DMU VHF transceiver is to share an existing VHF communication antenna. The ASU contains
switching circuitry which allows the DMU transceiver to share a common antenna with an external
VHF communication transceiver. In receive mode both receivers are connected to the antenna. In
transmit mode, only one of the transmitters is connected to the antenna at any one time. The ASU
switches the transmit side of the antenna between the DMU data transmitter and the voice
transmitter. Pressing the AFIS annunciator on the instrument panel switches the transmit side of
the antenna to the DMU transmitter. Pressing the annunciator again or pressing the “push-to-talk”
button on the VHF communication radio switches the transmit side of the antenna back to the
voice transmitter.
1.2.3 Data Transfer Unit (15655-0101 or 15655-0201)
The Data Transfer Unit (DTU) is a 3.5 inch micro floppy disk unit. It can be mounted on 5.75 inch
DZUS rails or bulkhead mounted with a tray. The DTU contains a microfloppy drive, drive
electronics and control logic. The DTU is used to read AFIS flight plans and weather from a disk
inserted in the DTU. The disk is read by the DTU and the data is transferred to the Data
Management Unit. A ground-to-air transmitted AFIS flight plan can also be written to a disk by the
DTU as the flight plan is received by the Data Management Unit. The DTU is optional. If a
customer does not choose to load information from the disk then the DTU is not required.
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.2.4 Satellite Communication Unit (153-017311-01)
The Satellite Communication Unit (SCU) is an ATR rack mounted unit. The SCU incorporates a
satellite transceiver and instructions for transmitting to and receiving from the satellite “C” network.
The SCU also contains information which allows it to tune to the appropriate satellite operating
region automatically and to the appropriate ground station. The SCU is optional. If a customer
does not choose to use satellite “C” operation then the SCU is not required.
1.2.5 High Power Amplifier/Low Noise Amplifier (153-017310-01)
The High Power Amplifier/Low Noise Amplifier (HPA/LNA) amplifier is a bulkhead mounted unit.
The HPA/LNA amplifies transmitted and received satellite “C” information while minimizing noise
and is connected between the SCU and a Satellite antenna. The HPA/LNA is required if the SCU
is installed.
1.2.6 Satellite Antenna (121-017537-01)
The Satellite Antenna is designed to meet Inmarsat system specifications for satellite “C” system
operation and is required if the SCU and HPA/LNA are installed. The Satellite Antenna is
connected to the HPA/LNA.
1.2.7 Configuration Module (31990-1)
The Configuration Module is mounted on the rack of the DMU. The Configuration module is a
nonvolatile memory that provides to the DMU, at power up, items that are related to the customer
aircraft such as tail number, aircraft basic operating weight, number of flight management systems
and selectable features such as on-off reporting, on-ground position reporting available to the
customer.
1.2.8 ARNAV MFD 5115 RPU (453-2530-08)
The ARNAV MFD 5115 RPU (Remote Processing Unit) is mounted in a frame assembly. The RPU
supplies AFIS
™
AFIS
weather graphical data services then the RPU is not required.
™
weather graphical data to the GNS-XLS. If a customer does not choose to use
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3 TECHNICAL CHARACTERISTICS
1.3.1 UNIT SPECIFICATIONS
DATA MANAGEMENT UNIT (DMU)
TSO COMPLIANCE: See Environmental Qualification Appendix
PHYSICAL DIMENSIONS: See Figure 2-1
TEMPERATURE: -55° C to +55° C
ALTITUDE: 55,000 feet
WEIGHT:
400-045500-0001,-0003,-0130,-0210,-0211
400-045500-0002,-0004
400-045500-0005,-2010,-2011
400-045500-0006
42000-01,02,03 (-) 01,02,03
42000-04-03
POWER REQUIREMENTS: 28 VDC
SATELLITE COMMUNICATION UNIT (SCU)
TSO COMPLIANCE: FAA-PMA BEECH MODEL E-90
PHYSICAL DIMENSIONS: See Figure 2-12
TEMPERATURE: -25° C to +55° C
ALTITUDE: 25,000 feet above MSL
WEIGHT: 6.0 Lbs max (2.72 Kg)
11.92 LBS. (5.89 KG.)
12.62 LBS. (6.23 KG.)
12.94 LBS. (6.39 KG.)
13.62 LBS. (6.73 KG.)
11.90 LBS. (5.89 KG.)
12.60 LBS. (6.22 KG.)
7.0 Amps Max - VHF Transmitter ON
2.0 Amps Max - VHF Transmitter OFF
POWER REQUIREMENTS: 27.5 VDC
6.7 Amps Max - Transmitter ON
1.0 Amps Max - Transmitter OFF
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AIRBORNE FLIGHT INFORMATION SYSTEM
DATA TRANSFER UNIT (DTU)
TSO COMPLIANCE: See Environmental Qualification Appendix
PHYSICAL DIMENSIONS: See Figure 2-5
TEMPERATURE: -55° C to +55° C
ALTITUDE: 55,000 feet
WEIGHT: 3.0 Lbs max (1.36 Kg)
POWER REQUIREMENTS: 28 VDC
1.0 Amps Max
ANTENNA SWITCHING UNIT (ASU)
TSO COMPLIANCE: See Environmental Qualification Appendix
PHYSICAL DIMENSIONS: See Figure 2-11
TEMPERATURE: -55° C to +55° C
ALTITUDE: 55,000 feet
WEIGHT: 1.3 Lbs max (0.59 Kg)
POWER REQUIREMENTS: 28 VDC
0.8 Amps Max
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AIRBORNE FLIGHT INFORMATION SYSTEM
HIGH POWER AMPLIFIER / LOW NOISE AMPLIFIER (HPA/LNA)
TSO COMPLIANCE: FAA-PMA BEECH MODEL E-90
PHYSICAL DIMENSIONS: See Figure 2-14
TEMPERATURE: -55° C to +70° C
ALTITUDE: 55,000 feet
HUMIDITY: CAT B Noncondensing
VIBRATION: Random Vibration CAT C
WEIGHT:
POWER REQUIREMENTS:
TX (through coax cable)
RX (through coax cable)
FREQUENCY:
TX BAND
RX BAND
VSWR: 3:1 maximum
INPUT POWER TX: -3 to +20dBm (1626.5 - 1646.5 MHz)
OUTPUT POWER TX: 21 WATTS maximum
LNA GAIN: 42 - 49 dB
CONFIGURATION MODULE
TSO COMPLIANCE: See Environmental Qualification Appendix
4.84 ± 0.44 Lbs (2.18 Kg)
26.5 - 30.0 VDC, 2.8 Amps Max
13 - 16 VDC, 0.05 Amps Max
1626.5 - 1646.5 MHz
1530 -1545 MHz
PHYSICAL DIMENSIONS: See Figure 2-4
TEMPERATURE: -55° C to +55° C
ALTITUDE: 55,000 feet
WEIGHT: 0.102 Lbs (0.045 Kg) max
POWER REQUIREMENTS: Supplied by DMU
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AIRBORNE FLIGHT INFORMATION SYSTEM
LOW PROFILE JET BLADE ANTENNA
TSO COMPLIANCE: FAA-PMA Unit - Sensor Systems, Inc. PMA
Holder
PHYSICAL DIMENSIONS: See Figure 2-15
TEMPERATURE: -54° C to +71° C
ALTITUDE: 55,000 feet
WEIGHT: 1.5 Lbs max (0.68 Kg)
POWER HANDLING: 60 WATTS CW
FREQUENCY:
TX BAND
RX BAND
VSWR: < 1.5: 1
POLARIZATION: RHCP
IMPEDANCE: 50 ohms
REMOTE PROCESSING UNIT (RPU)
TSO COMPLIANCE: TSO Unit - ARNAV Systems Inc. TSO Holder
PHYSICAL DIMENSIONS:
Height
Width
Depth
TEMPERATURE: -20° C to +70° C
ALTITUDE: 50,000 feet
1626.5 - 1660.5 MHz
1530 -1559 MHz
2.0 inches (50.8 mm)
6.25 inches (159 mm)
9.25 inches (235 mm)
WEIGHT: 2.5 Lbs (1.15 Kg)
POWER REQUIREMENTS: 27.5 Vdc at 750 mA
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2 SYSTEM SPECIFICATIONS
The following pages of system characteristics provide details of the various interfaces for the
AFIS.
1.3.2.1 Fuel Flow Input (ANALOG INPUT)
NOTE:
Fuel Flow information is only applicable to DMUs PN 42000-02-02,
PN 42000-04-03, PN 400-045500-0002, PN 400-045500-0004, and
PN 400-045500-0006.
1.3.2.1.1 J.E.T. Fuel Flow System
NOTE:
This interface is provided by a modification to 54-1158-01 module
per J.E.T. SB number SB542-1158-7.
Source LearJet volumetric flow rate transducer
Range See Table 1-1
Accuracy
Scale Factor Flow Rate = 28.125 x frequency
Load 10K ohms minimum
Amplitude +9 volts, ground referenced
J.E.T. Range (PPH) Accuracy Scaling (PPH/V)
Applicable to
J.E.T. SB
542-1158-7
±
0.5% of volume
Where:
Flow Rate = Pounds Per Hour and Frequency = Hertz
0 to 2500
±
0.5% of
volume
28.125 10K Ohms
Output
Impedance
Table 1-1
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1.3.2.1.2 ELDEC Mass Flow Fuel System
Source ELDEC Mass Flow Transducer
Signal Type Each sensor generates two AC signals.
Flow rate information is contained in the phase difference
between the two signals.
Range 150 to 2200 PPH
Amplitude 0.30 to 1.60 V P-P Drum Signal
0.30 to 1.60 V P-P Impeller Signal
Frequency 5.7 to 28 Hz
Phase Delay 0 to 55 msec
Scale Factor See Table 1-2
Load 200K ohms minimum
Global
ELDEC SENSOR MODEL NUMBER TRANSMITTER SCALING (LB/HR/mS)
9-127-27
9-127-33
9-127-51
9-127-39
9-127-12 100
9-231-05 20
Table 1-2
40
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1.3.2.1.3 ELDEC Mass Fuel Flow System
There are two types of indicator outputs: pulse width and DC
voltage. Some of the indicators have both. If this is the case the
pulse width output is preferred.
Pulse Width Output From Indicator
Source ELDEC Fuel Flow Indicator
Ty p e Ground referenced voltage pulse flow rate is proportional
to width.
Global
NOTE:
Amplitude
Indicator
Output
Impedance
Range/
Accuracy/
Impedance
Repetition
Time
Source ELDEC Fuel Flow Indicator
Ty p e DC differential voltage proportions to fuel rate. The signal
VOL = 0 ± 2 Volts
VOH = 12
15K ohms
See Table 1-3
36 to 175 msec
low is 5.1
ence voltage of 6.2
but is unused by the GNS-500.
±
2 Volts
DC Rate Output Indicator
±
1.0 Volts above the power ground. A refer-
±
0.32 VDC is provided by ELDEC,
Signal
Range
Indicator
Output
Impedance
Scaling/
Range/
Accuracy
IMAFISJWA 1-9
0.0 to 5.5 VDC differential
5K ohms each leg
See Table 1-3
March/2001
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AIRBORNE FLIGHT INFORMATION SYSTEM
ELDEC
Indicator
Model No.
Aux
Pulse
Width
Aux
DC
Rate
Range
PPH
Scaling
Pulse
PPH/mSDCV/PPH
Accuracy
Pulse
DC
9-328-01 YES YES 0 to 2200 40 0.0025 ± 2 lb/hr ± 2%
9-328-10 YES YES 0 to 2200 40 0.0025 ± 2 lb/hr ± 2%
9-328-13 YES YES 0 to 3000 100 0.00167 ± 2 lb/hr ± 2%
9-328-17 YES N/A 0 to 2000 40 - - - ± 2 lb/hr - - -
9-328-26 YES - - - 0 to 4000 100 - - - ± 2 lb/hr - - -
9-328-19 YES YES 0 to 3300 100 0.00142 ± 2 lb/hr ± 2%
9-328-20 YES YES 0 to 4000 100 0.00143 ± 2 lb/hr ± 2%
9-394-01 YES TBD TBD 100 ± 2 lb/hr ± 2%
9-422-01 YES N/A 0 to 10000 80 ± 2 lb/hr ± 2%
9-464-02 YES YES 0 to 1000 40 TBD ± 2 lb/hr ± 2%
9-464-06 YES YES 0 to 1000 40 TBD ± 2 lb/hr ± 2%
9-464-09 N/A YES 0 to 1200 - - - TBD ± 2 lb/hr ± 2%
9-464-16 YES YES 0 to 1000 40 - - - ± 2 lb/hr ± 2%
9-464-25 YES YES 0 to 1200 40 .004166 ± 2 lb/hr ± 2%
9-464-41 YES YES 0 to 1200 40 .004166 ± 2 lb/hr ± 2%
1.3.2.1.4 AMETEK Indicator Fuel Flow
Flow rate is proportional to voltage
Source Auxiliary flow rate output from AMETEK
Range 0 to 2400 PPH
Signal Type 0.5 to 5.5 VDC ground referenced
Scaling Flow Rate = 480 (V
Where: Flow Rate = PPH, V
Accuracy
±
50 mV
Table 1-3
NOTE:
.
- 0.5)
sig
= Volts
sig
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.1.5. Gull Indicator Fuel Flow - Model 360-954-XXX
NOTE:
Flow rate is proportional to voltage
.
Source Gull fuel flow indicator
Range 0 to 2000 PPH
Accuracy
Signal Type 1.0 to 5.4 VDC differential
Scaling
1.3.2.1.6 General Electric 5v RMS AC Fuel Flow
Source Pick off type fuel flow transducer
Signal Type Signal 0 to 5 VRMS, 400 Hz differential signal
Range
Scaling F = 800 (Vsig)
±
3%
Flow Rate =
Where: Flow Rate = PPH Vsig = VDC
Flow rate is proportional to RMS voltage.
Fuel flow - G.E. PN 8TJ64GBM-3
500 (vsig - 1.0)
NOTE:
0 to 4000 PPH
Where: F = Flow in PPH, Vsig = VRMS
Reference 115 VRMS nominal, 400 Hz aircraft power
Fuel flow- G.E. PN 8TJ85GBA
Source G.E. AC Fuel Flow Transmitter
Signal Type Signal 0 to 5 VRMS, 400 Hz differential signal
Range 400 to 12,500 PPH
Motor
Frequency
Scale Factor F = 2400 (Vsig)
Reference 115 VRMS nominal, 400 Hz aircraft power
IMAFISJWA 1-11
8 cycles per second
Where: F = Flow in PPH, Vsig = VRMS
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AIRBORNE FLIGHT INFORMATION SYSTEM
Fuel flow - G.E. PN 8TJ85GAT
Source G.E. AC Fuel Flow Transmitter
Signal Type Signal 0 to 5 VRMS, 400 Hz differential signal
Range 400 to 12,500 PPH
Motor
Frequency
Scale Factor F = 2400 (Vsig)
Reference 115 VRMS nominal, 400 Hz aircraft power
1.3.2.1.7 IDC Indicator Fuel Flow
Auxiliary fuel flow rate output from an IDC fuel flow indicator. Some
models have pulse width outputs, DC voltage outputs or both. The
use of the pulse width output is preferred.
Ty p e Ground referenced voltage pulse
Amplitude VOL = 0V, VOH = 5V
8 cycles per second
Where: F = Flow in PPH, Vsig = VRMS
Pulse Width Output Signal From Indicator
(Flow rate is proportional to pulse width.)
NOTE:
Output
Impedance
for Indicator
Repetition
Time
Range/
Accuracy/
Scaling
IMAFISJWA 1-12
10K Ohm pull-up
100 to 500 msec
See Table 1-4
March/2001
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AIRBORNE FLIGHT INFORMATION SYSTEM
DC Rate Output from Indicator
Ty p e DC Differential Voltage proportional to fuel rate
Signal
Range
Output
Impedance
Range/
Accuracy/
Scaling
IDC
Indicator
Model No.
31653-003 YES - - - 0 to 8000 80 - - - ± 20 PPH
31653-004 YES - - - 0 to 8000 80 - - - ± 20 PPH
31653-013 YES YES 0 to 8000 80 0.0005 ± 20 PPH
31653-014 YES YES 0 to 8000 80 0.0005 ± 20 PPH
37804-001 YES - - - 0 to 8000 80 - - - ± 20 PPH
37804-002 YES - - - 0 to 8000 80 - - - ± 20 PPH
37804-011 YES - - - 0 to 8000 80 - - - ± 20 PPH
37804-012 YES - - - 0 to 8000 80 - - - ± 20 PPH
37804-101 YES YES 0 to 8000 80 0.0005 ± 20 PPH
37804-102 YES YES 0 to 8000 80 0.0005 ± 20 PPH
Aux
Pulse
Width
0 to 4.0 VDC
200 Ohms on each leg
See Table 1-4
Aux DC
Rate
Range
PPH
Scaling
Pulse
PPH/mS
DC
V/PPH Accuracy
Table 1-4
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.1.8 RAGEN Data Systems Fuel Flow
RAGEN Data Systems also manufactures fuel systems formerly
manufactured by Consolidated Airborne and Bendix. Flow rate is
proportional to Voltage.
Source Fuel Flow Rate Signal from fuel flow transducer
Signal Type DC Voltage Output
Global
NOTE:
Output
Impedance
Range/
Accuracy/
Scaling
RAGEN
Model
3268-005 0 to 1800 TBD 283.688 TBD
3268-014 0 to 1800 TBD 283.114 TBD
3268-011 0 to 500 TBD 100.000 TBD
1.3.2.1.9 Canadian Marconi Fuel Flow System
See Table 1-5
See Table 1-5
Range
(PPH)
Accuracy
Table 1-5
Scaling
(PPH/V)
Output
Impedance
NOTE:
DC voltage output in which the voltage is proportional to the flow rate.
Source Auxiliary Fuel Flow Rate Signal From Indicator
Signal Type DC Voltage Output
Output
Impedance
Range/
Accuracy/
Scaling
IMAFISJWA 1-14
1K Ohms
See Table 1-6
March/2001
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AIRBORNE FLIGHT INFORMATION SYSTEM
Canadian Marconi
Model No.
Range (PPH)
418-107-103 0 to 4500 900 ±2%
418-107-104 0 to 4500 900 ± 2%
1.3.2.1.10 Aero Systems Fuel flow System
Signal frequency is proportional to fuel flow rate.
Source Aero Systems Model DD-4000-004 Magneson Fuel Flow
Signal Convertor. The DD-4000 converts G.E. Second
Harmonic flow signals to a frequency proportional to fuel
rate for a maximum of four engines
Signal
0 to 2500 Hz
Range
Table 1-6
NOTE:
DC Scaling
(PPH/V)
Accuracy
Signal
Levels
Output
Impedance
Range/
High side of signal switches between 7.5V and 15.0V
whereas the low side is 7.5V above ground.
2 Kohms pull up to +15V.
Transistor switch to 7.5V.
See Table 1-7
Accuracy/
Scaling
Aero Systems
Model No.
Range
(PPH)
Scaling
(PPH/Hz) Remarks
DD-4000-004 0 to 2300 0.92
0 to 3000 1.200 convertor model number.
0 to 4000 1.600 The scaling, however is
0 to 8000 3.200 custom calibrated for
0 to 12000 4.800 each aircraft.
0 to 14000 5.600
Table 1-7
DD-4000-004 is only the
IMAFISJWA 1-15
March/2001
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.1.11 Intertechnique Fuel flow System
Flow rate is proportional to frequency; the fuel relative density signal
is a 3 to 5 VDC signal proportional to the fuel specific gravity
(relative density).
Source Intertechnique totalizer amplifier indicator Models
723-161-1 and 723-161-2. The signals from the indicators
are input to the totalizer.
Global
NOTE:
Range
Reference
Scaling Flow = [Vsig/5.0] x 34.506 x frequency
Signal: Frequency:
1.3.2.2 RS-422A Serial Data Input
1.3.2.2.1 Data Transfer Unit (DTU)
Data Type Both transmit and receive data are two-wire, balanced
0 to 2000 PPH
Where: Flow is PPH, Vsig = Voltage of density signal and
Freq = Frequency of rate signal
Density:
voltage digital signals in accordance with EIA RS-422A
electrical format.
VOL = 0.7 ±TBD V
VOH = 12.0
Pulse width = 2.5
Impedance Output = 270 ohms
Range = 3 to 5.0 VDC
Output Impedance = 3.9 Kohms
±
TBD V
±
TBD V
Receive
Logic Level
Data Rate 22.5 KBS
Bit Stream
Format
Word Type 8 bit with no parity
IMAFISJWA 1-16
Logic 1: +2 to +6V differential
Logic 0: -2 to -6V differential
Asynchronous with 1 start bit, 8 bits of data and 2 stop
bits between words.
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.2.2 Satellite Communications Unit (SCU)
NOTE:
The following information is only applicable to DMUs P/N
42000-03-03, 42000-04-03, 400-045500-0003, 400-045500-0004,
400-045500-0130, 400-045500-0210, 400-045500-0211,
400-045500-2010, and 400-045500-2011.
SAT 422 Receive
Data Type Receive data is a two-wire balanced voltage digital sig-
nals in accordance with EIA RS-422A electrical format.
Receive
Logic Level
Data Rate 4800 bit per second
Bit Stream
Format
Word Type 8 bit with no parity
Data Type CONTROL IN is a two-wire balanced voltage digital
CONTROL IN
Logic Level
Data Rate Changes on software conditions, indicates the current
Data Level ON (high): SCU ready to receive data from DMU
Logic 1: +2 to +6V differential
Logic 0: -2 to -6V differential
Asynchronous with 1 start bit, 8 bits of data and 1 stop bit
between words.
SAT 422 CONTROL IN
signal in accordance with EIA RS-422A electrical format.
Logic 1: +2 to +6V differential
Logic 0: -2 to -6V differential
state of the SCU for receiving data from DMU
OFF (low): SCU not ready to receive data from DMU
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.3 ARINC 429 INPUT - (See Tables 1-8A and 1-8B)
NOTE:
The following information is only applicable to DMU PN 400-045500-XXXX.
Data Type 2 wire serial data meeting ARINC 429 characteristics
Logic State Logic 1: > 5V differential, +6.5 to +13 V
Logic 0: < 5V differential, -6.5 to -13 V
NULL: 0 V differential
Data Rate Changes on software conditions, indicates the current
state of the SCU for receiving data from DMU
Format 32 bit word, including 1 parity bit Return-To-Zero (RZ)
format with at least 4 nulls between words.
NAME LABEL DATA RATES
ISO Alphabet #5 Messages 357 SPECIAL
GMT 125 0.1 Sec
Baro Corrected Altitude 204 0.0625 Sec
True Airspeed 210 0.125 Sec
Static Air Temperature 213 0.5 Sec
DATE 260 1.0 Sec
Present Position Latitude 310 0.2 Sec
Present Position Longitude 311 0.2 Sec
Groundspeed 312 0.04 Sec
Wind Speed 315 0.1 Sec
Wind Direction 316 0.1 Sec
ARINC 429 Digital Input Navigational System
Table 1-8A
NOTE:
The following table is only applicable to DMUs PN 400-045500-0005,
400-045500-0006, 400-045500-2010, and 400-045500-2011.
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AIRBORNE FLIGHT INFORMATION SYSTEM
NAME LABEL DATA RATES
ISO Alphabet #5 Messages 304 SPECIAL
SDU System Status 270 1.0 Sec
ARINC 429 Digital Input Satellite and SATFONE System
1.3.2.4 ANALOG OUTPUTS (DMU)
1.3.2.4.1 Valid Discretes DTU and DMU
Data Type Indicates system is operating
Logic State Ground (<10 ohms) indicates a valid output
Open (>1M ohm) indicates an invalid output
Global
Table 1-8B
Response
Time
Current Load 250 mA
1.3.2.4.2. PTT Line
Ground (50 ohms or less between PTT line and DC ground) turns the transmitter ON. Open
(50,000 ohms or more between PTT line and DC ground) turns the transmitter OFF.
1.3.2.4.3. AFIS Annunciator
The following information is only applicable to DMU PN
400-045500-XXXX installations using the Antenna Switching Unit.
Logic State DMU J1 pin 42: Ground (<10 ohms) indicates AFIS is Disabled
1.0 ± 0.5 seconds valid to invalid
2.5 ± 0.5 seconds invalid to valid
NOTE:
Open (> 1 M ohm) indicates AFIS is Enabled
DMU J1 pin 80: Ground (<10 ohms) indicates AFIS is Enabled
Open (> 1 M ohm) indicates AFIS is Disabled
Signal Type Level
Current Capacity .5 Amp Maximum
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.5 RS-422A SERIAL DIGITAL OUTPUTS (DMU)
1.3.2.5.1 Data Transfer Unit (DTU)
Data Type Both transmit and receive data are two-wire balanced digital signals in
accordance with EIA RS-422A electrical format.
Transmit Logic Level Logic 1: +2V to +6V differential
Logic 0: -2V to -6V differential
Data Rate 22.5 KBS
Bit Stream Format Asynchronous with 1 start bit, 8 bits of data and 2 stop bits between
words.
Word Type 8 bit with no parity
1.3.2.5.2 Satellite Communications Unit (SCU)
NOTE:
The following information is only applicable to DMUs PN 42000-03-03,
42000-04-03, 400-045500-0003, 400-045500-0004, 400-045500-0130,
400-045500-0210, 400-045500-0211, 400-045500-2010 and
400-045500-2011.
SAT 422 Transmit
Data Type Transmit data is a two-wire balanced voltage digital signal in accordance
with EIA RS-422A electrical format.
Transmit Logic Level Logic 1: +2V to +6V differential
Logic 0: -2V to -6V differential
Data Rate 4800 bits per second
Bit Stream Format Asynchronous with 1 start bit, 8 bits of data and 1 stop bit between
words.
Word Type 8 bit with no parity
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AIRBORNE FLIGHT INFORMATION SYSTEM
SAT 422 CONTROL OUT
Data Type CONTROL OUT is a two-wire balanced voltage digital signal in
accordance with EIA RS-422A electrical format.
CONTROL OUT
Logic Level
Data Rate Changes on software conditions, indicates the current state of the
Data Level ON (high): The DMU is ready to receive data from SCU
Data Type Transmit data is a two-wire balanced voltage digital signal in accordance
Transmit
Logic Level
Data Rate 4800 bits per second
Bit Stream
Format
Logic 1: +2V to +6V differential
Logic 0: -2V to -6V differential
DMU for receiving data from SCU.
OFF (low): The DMU is not ready to receive from SCU.
SAT NAV DATA 422 Transmit
with EIA RS-422A electrical format.
Logic 1: +2V to +6V differential
Logic 0: -2V to -6V differential
Asynchronous with 1 start bit, 8 bits of data and 1 stop bit between words.
Stream of data appears once a second if satellite configured and present
position information available.
Word Type 8 bit with no parity
1.3.2.6 ARINC 429 OUTPUTS (See tables 1-9A & B)
NOTE:
The following information is only applicable to DMU Part Number
400-045500-XXXX.
Data Type 2-wire serial data meeting electrical characteristics of ARINC 429
Logic State Logic 1: + 10 ± 1 V differential balance to ground
Logic 0: - 10 ± 1 V differential balance to ground
NULL: ± 2.5 V differential
Data Rate 12.5 KBS
Format 32 bit word including 1 parity bit, Return-to-Zero (RZ) format with a least
4 nulls between words.
IMAFISJWA 1-21
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AIRBORNE FLIGHT INFORMATION SYSTEM
NAME LABEL DATA RATES
AFIS System Status 270 SPECIAL
AFIS Data Status 271 SPECIAL
Fuel Flow - Engine 347 0.1 Sec
ISO Alphabet #5 message 357 SPECIAL
ARINC 429 Digital Output
Table 1-9A
NOTE:
The following table is applicable to DMUs PN 400-045500-0005,
400-045500-0006, 400-045500-2010 and 400-045500-2011.
ISO Alphabet #5 message 307 SPECIAL
ARINC 429 Digital Output Satellite & SATFONE System
1.3.2.7 Printer Interface
Four signal lines are required between the AFIS DMU and the
printer: Printer Serial Data Out, Printer Serial Data Return, Printer
DTR (Data Terminal Ready) IN, and Printer DTR return.
NAME LABEL DATA RATES
AFIS System Status 270 1.0 Sec
Table 1-9B
NOTE:
1.3.2.7.1 Printer Serial Data Out
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AIRBORNE FLIGHT INFORMATION SYSTEM
Electrical
Direction
Signal Format Asynchronous, serial transmission. 11 bit times comprised of
Order of Bit Transmission First bit is start bit, followed by least significant data bit,
Data Rate 1200 bits per second
Data Stream 1 - 80 printable characters transmitted
File Structure File contains 1 - 4000 printable characters (hexadecimal 20 -
RS-232C electrical characteristics. Two wire system.
Data from DMU to printer.
1 start bit, 8 data bits, and 2 stop bits.
8 data bits defined by ASCII character set.
No parity bit
followed by remaining 7 data bits, followed by 2 stop bits.
Carriage return (CR) and linefeed (LF) are transmitted
following the last printable character.
7E), CR characters (hexadecimal 0D), and LF characters
(hexadecimal 0A).
Control character, ETX (hexadecimal 03), is sent as last
character of a file transmission to indicate that the file is
completed and can be used for printer buffer control.The
printer may ignore the ETX character if buffer control is not
needed.
A CR and LF is transmitted at the beginning of each new file.
The file is transmitted in groups of 80 characters or less with a
CR character and a LF character following each group of 80
characters or less.
The printer must be capable of printing 80 columns or have
auto wrap so that the 80 characters can be printed without
including the CR and LF characters until the end of the 80
character or less transmission.
1.3.2.7.2 Printer Serial Data Return
IMAFISJWA 1-23
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AIRBORNE FLIGHT INFORMATION SYSTEM
Electrical Return line associated with the Serial Data Out line.
1.3.2.7.3 Printer DTR In
Electrical Discrete input with RS-232C electrical characteristics.
Two wire system.
Signal Format Low Voltage Level: Printer Inoperative
Printer Paper out
Printer power off
Printer ribbon out
Printer busy
Any printer status that does not
permit the printer to receive data
High Voltage Level: Printer operative and ready to
receive data
Direction: Printer to DMU
Data Rate Voltage level maintained at appropriate level as long as
condition exists. DMU will not transmit serial data when
Printer DTR In has low voltage.
1.3.2.7.4 Printer DTR Return
Electrical Return line associated with the Printer DTR in signal line.
1.3.2.8 Cabin Terminal Interface
NOTE:
Cabin Terminal Interface is only applicable to DMU Part Numbers
42000-03-03, 42000-04-03, 400-045500-0003, 400-045500-0004,
400-045500-0130, 400-045500-0210 and 400-045500-0211 when
used with Satellite systems.
Six signal lines are required between the AFIS DMU and each cabin
terminal: Cabin Data In, Cabin Data In return, Cabin Data out, Cabin
Data Out return, Cabin Terminal Control In, Cabin Terminal Control
In return.
IMAFISJWA 1-24
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1.3.2.8.1 Cabin Data In
Global
AIRBORNE FLIGHT INFORMATION SYSTEM
Electrical
Direction
Signal Format Asynchronous, serial transmission. 11 bit times comprised of 1
Order of
Transmission
Data Rate 9600 bits per second
Data Stream Defined by AFIS cabin terminal software
File Structure Defined by AFIS cabin terminal software
1.3.2.8.2 Cabin Data In Return
Electrical Return line associated with Cabin Data In signal line
RS-232C electrical characteristics. Two wire system.
Data from Cabin Terminal to DMU.
start bit, 8 data bits, and 2 stop bits.
8 data bits defined by ASCII character set.
No parity bit.
First bit is start bit, followed by 8 data bits, followed by 2 stop
bits.
1.3.2.8.3 Cabin Data Out
Electrical
Direction
Signal Format Asynchronous, serial transmission. 11 bit times comprised of 1
Order of
Transmission
Data Rate 9600 bits per second
Data Stream Defined by AFIS cabin terminal software.
File Structure Defined by AFIS cabin terminal software.
RS-232C electrical characteristics. Two wire system.
Data from DMU to Cabin Terminal.
start bit, 8 data bits, and 2 stop bits.
8 data bits defined by ASCII character set.
No parity bit.
First bit is start bit, followed by 8 data bits, followed by 2 stop bits
IMAFISJWA 1-25
March/2001
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.8.4 Cabin Data Out Return
Electrical Return line associated with Cabin Data Out signal line
1.3.2.8.5 Cabin Terminal Control In
Electrical Discrete input with RS-232C
electrical characteristics.
Two wire system.
Signal Format Low Voltage Level: Cabin Terminal Inoperative
Cabin Terminal power off
Cabin Terminal not running AFIS
cabin software.
High Voltage Level: Cabin Terminal operative and
running AFIS cabin terminal
software.
Direction: Cabin Terminal to DMU
Data Rate Voltage level maintained at
appropriate level as long as
condition exists. DMU will not
transmit serial data when Cabin
Handshake has low voltage.
1.3.2.8.6 Cabin Terminal Control In Return
Electrical Return line associated with the Cabin Handshake In (DTR)
signal line.
1.3.2.9 DISCRETE INPUTS
NOTE:
The following information is only applicable to DMUs PN
400-045500-XXXX configured for Special Features item #5 ACARS
reports.
IMAFISJWA 1-26
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.9.1 Brake Release
Data Type Logic Input
Logic State The OPEN condition is defined as a resistance to DC ground
from the AFIS DMU connector of 100,000 ohms or more, or a
DC level greater then 12 volts and not more than 36 volts.
The CLOSED condition is defined as a DC ground, zero ± 2 volts
with a maximum current of 2 ma.
Logic Format Atlantic Coast Airlines
An OPEN condition indicates the brakes are set.
A CLOSED condition indicates the brakes are released.
Mesaba Airlines
An OPEN condition indicates brakes are released.
A CLOSED condition indicates brakes are set.
1.3.2.9.2 Oil Pressure
Data Type Logic Input
Logic State The OPEN condition is defined as a resistance to DC ground
from the AFIS DMU connector of 100,000 ohms or more, or a DC
level greater then 12 volts and not more than 36 volts.
The CLOSED condition is defined as a DC ground, zero ± 2 volts
with a maximum current of 2 ma.
Logic Format An OPEN condition indicates there is oil pressure
A CLOSED condition indicates there is no oil pressure.
IMAFISJWA 1-27
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.3.2.9.3 Weight On Wheels
Data Type Logic Input
Logic State The OPEN condition is defined as a resistance to DC ground
from the AFIS DMU connector of 100,000 ohms or more, or a DC
level greater then 12 volts and not more than 36 volts.
The CLOSED condition is defined as a DC ground, zero ± 2 volts
with a maximum current of 2 ma.
Logic Format An OPEN condition indicates the aircraft is in the air.
A CLOSED condition indicates the aircraft is on the ground.
1.3.2.9.4 Engine Stop Switch
Data Type Logic Input
Logic State The OPEN condition is defined as a resistance to DC ground
from the AFIS DMU connector of 100,000 ohms or more, or a DC
level greater then 12 volts and not more than 36 volts.
The CLOSED condition is defined as a DC ground, zero ± 2 volts
with a maximum current of 2 ma.
Logic Format An OPEN condition indicates normal engine operation.
A CLOSED condition held for at least 2 seconds indicates the
engine is shut down.
1.3.2.9.5 Door Switch
Data Type Logic Input
Logic State The OPEN condition is defined as a resistance to DC ground
from the AFIS DMU connector of 100,000 ohms or more, or a DC
level greater than 12 volts and not more than 36 volts.
The CLOSED condition is defined as a DC ground, zero ± 2 volts
with a maximum current of 2 ma.
Logic Format An OPEN condition indicates the door is closed.
A CLOSED condition indicates the door is open.
IMAFISJWA 1-28
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AIRBORNE FLIGHT INFORMATION SYSTEM
1.4 UNITS AND ACCESSORIES SUPPLIED
1.4.1 DATA MANAGEMENT UNIT
The Data Management Unit (DMU) is available in the following variations.
PN 400-045500-0003 which is the standard DMU and supports VHF and AERO-C (SATAFIS)
data communications.
PN 400-045500-0005 which supports aeronautical 741 satellite data communications (e.g.
Honeywell/Racal) as well as VHF data communications.
PN 400-045500-0130 which supports regional airline data entry, displays and VHF
Communications and AERO-C (SATAFIS) data communications.
PN 400-045500-0210 which supports WX Graphics capability on GNS-XLS and supports VHF
and AERO-C (SATAFIS) data communications.
PN 400-045500-2010 which supports WX Graphics capability on GNS-XLS and supports
AERO-H (741) satellite data communications (e.g. Honeywell/Racal) as well as VHF data
communications.
PN 400-045500-0211 which supports Dual GNS-XLS WX Graphics capability, as well as, NZ
2000 WX Graphics and supports VHF, AERO-C (SATAFIS) data communications.
PN 400-045500-2011 which supports Dual GNX-XLS WX Graphics capability, as well as, NZ
2000 WX Graphics and supports VHF, AERO-C (SATAFIS), AERO H/H+, AERO I
(ARINC741) satellite data communications. Supports Honeywell Aircraft Condition Monitoring
System (ACMS) which is a part of the Honeywell Flight Data Acquisition Management System
(FDAMS)
Other DMUs no longer manufactured:
PN 400-045500-0001 supports VHF data communication only.
PN 400-045500-0002 support VHF data communication only and has fuel flow information to
be used with a GNS 500 navigational system.
PN 400-045500-0004 supports VHF and aeronautical-’C’ data communications and has fuel
flow information to be used with a GNS-500 navigational system.
PN 400-045500-0006 supports aeronautical 741 satellite data communications, VHF data
communications and fuel flow information to be used with a GNS-500 navigational systems.
PN 42000-01-01 supports VHF data communication only and can only be used with GNS 500
and 1000 flight management systems.
PN 42000-02-02 supports VHF data communication only, has fuel flow information to be used
with a GNS 500 navigational system and can only be used with GNS 500 and 1000 flight
management systems.
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AIRBORNE FLIGHT INFORMATION SYSTEM
PN 42000-03-03 supports VHF and aeronautical ’C’ data communications. This DMU can only
be used with GNS flight management systems.
PN 42000-04-03 supports VHF, aeronautical ’C’ data communications and has fuel flow
information to be used with a GNS 500 navigational system. This DMU can only be used with
GNS flight management systems.
1.4.2 FLIGHT PLANNING SERVICE
Flight Planning Service includes planning and pre-departure clearance service. Services include
weather briefing, flight plan creation and filing, pre-departure delivery and arrival/departure
reservations.
Details on subscription fees and specifically what other capabilities are available can be obtained
by contacting the Global Data Center, telephone number 1-888-634-3330.
The following page (figure 1-1) contains a copy of the AFIS Graphics Service and Database
Application. After printing off a copy, complete all entries and fax to the number shown on the
form.
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AIRBORNE FLIGHT INFORMATION SYSTEM
Figure 1-1
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AIRBORNE FLIGHT INFORMATION SYSTEM
THIS PAGE IS RESERVED
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1.4.3 DMU CONFIGURATION MATRIX
OPTIONS
67 PIN CONNECTOR YES YES YES YES NO NO NO NO NO NO NO NO NO NO NO
106 PIN CONNECTOR NO NO NO NO YES YES YES YES YES YES YES YES YES YES YES
FUEL FLOW NO YES NO YES NO YES NO YES NO YES NO NO NO NO NO
Global
DMU 42000-XXXX DMU 400-045500-XXXX
-01-01 -02-02 -03-03 -04-03 -0001 -0002 -0003 -0004 -0005 -0006 -0130 -0210 -2010 -0211 -2011
COLOR CDU DISPLAY NO NO YES YES
10 LINE MONO CDU NO NO YES YES
GLOBAL SCU SAT SYSTEM NO NO YES YES NO NO YES YES YES NO YES YES YES YES YES
ARINC 429 FMS INTERFACE NO NO NO NO YES YES YES YES YES YES YES YES YES YES YES
TRIPLE PORT DTU PN 15655-X YES YES YES YES YES YES YES YES YES YES YES YES YES YES YES
DTU PN 43000-01-01-X YES YES YES YES YES YES YES YES YES YES YES YES YES YES YES
OTHER MFG. SAT SYSTEMS NO NO NO NO NO NO NO NO YES YES NO NO YES NO YES
ARINC 739 FMS INTERFACE NO NO NO NO NO NO NO NO NO NO NO NO NO YES YES
MOD4 MOD4
MOD4 MOD4
YES YES YES YES YES YES YES YES YES
YES YES YES YES YES YES YES YES YES
FDAMS INTERFACE NO NO NO NO NO NO NO NO NO NO NO NO NO NO YES
Table 1-10
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1.5 ACCESSORIES REQUIRED
1.5.1 DMU INSTALLATION KIT
The DMU Installation Kit PN 149-017305-6850 is required to install DMU PN 400-045500-XXXX.
1/2 ATR Short Tray PN 42701-1 Qty 1 ea
DMU Connector PN 129-214251-01 Qty 1 ea
The DMU Installation Kit PN 149-017301-5970 is required to install DMU PN 42000-XX-XX.
1/2 ATR Short Tray PN 42701-1 Qty 1 ea
DMU Connector PN 42770-1 Qty 1 ea
1.5.2 CONFIGURATION MODULE UNIT
The Configuration Module Unit is to be mounted on the rear of the 1/2 ATR Short Tray.
Configuration module PN 31990-1 Qty 1 ea
1.5.3 VHF ANTENNA
If the VHF antenna is to be shared with another VHF radio then the optional Antenna Switching
Unit (ASU) is required.
1.6 OPTIONAL ACCESSORIES
1.6.1 DATA TRANSFER UNIT
The Data Transfer Unit (DTU) is required if flight plan or weather information is to be loaded into
the DMU via a disk from the AFISCOM system. The DTU is available in the following variations:
Triple Port DTU which is used to provide data base information to GWS flight management
systems and data information to DMU:
Triple Port DTU PN 15655-0101 (Gray)
Triple Port DTU PN 15655-0201 (Black)
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Single Port DTU (no longer manufactured) supplies data information to DMU:
PN 43000-01-01-1 Gray +8 VDC / +12 VDC
PN 43000-01-01-2 Black +8 VDC / +12 VDC
PN 43000-01-01-3 Gray +28 VDC
PN 43000-01-01-4 Black +28 VDC
PN 43000-01-01-5 Gray +8 VDC / +12 VDC
PN 43000-01-01-6 Black +8 VDC / +12 VDC
PN 43000-01-01-7 Gray +28 VDC
PN 43000-01-01-8 Black +28 VDC
1.6.1.1 DTU INSTALLATION KIT
The DTU installation kit is required if DTU is installed. Select one of the following options:
DTU Installation Kit, Grey, for DTU PN 43000-01-01-X
PN 149-017302-5983 (kit no longer available from Honeywell)
DTU Connector PN 12893-1 Qty 1 ea
Grey with Tray PN 43010-1 Qty 1 ea
DTU Installation Kit, Black, for DTU PN 43000-01-01-X
PN 149-017302-5984 (kit no longer available from Honeywell)
DTU Connector PN 12893-1 Qty 1 ea
Black with Tray PN 43010-2 Qty 1 ea
Triple Port DTU Installation Kit PN 129-215678-01
DTU Connector PN 129-215678-01 Qty 1 ea
1.6.2 ANTENNA SWITCHING UNIT
The ANTENNA SWITCHING UNIT (ASU) is required if a VHF antenna is going to be shared
between the DMU and another VHF communication radio.
Antenna Switching Unit PN 44000-1
If an ASU is being installed, the Antenna Switching Unit Installation Kit is required:
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ASU Installation Kit PN 149-017303-5990
ASU Connector PN 12893-2 Qty 1 ea
1.6.3 SATELLITE SYSTEM (SATAFIS)
If the aeronautical “C” satellite system, SATAFIS, is to be installed the following equipment
is required:
EQUIPMENT PART NUMBER
Satellite Communication Unit (SCU) 153-017311-01
High Power Amplifier/Low Noise Amplifier (HPA/LNA) 153-017310-01
Low Profile Jet Blade Antenna 121-017537-01
Jet Blade Antenna (no longer manufactured) 121-017308-01
SCU Installation Kit - PN 149-017536-0001
Global
Mounting Tray PN 300-317337-01 Qty 1 ea
SCU Connector PN 129-217338-01 Qty 1 ea
Coaxial Cable Adapter PN 123-117429-01 Qty 1 ea
1.6.4 PRINTER
Details on specifically what printer will operate with the DMU and other requirements can be
obtained by contacting the Global Data Center.
1.6.5 CABIN PERSONAL COMPUTER
Details on specifically what Personal Computer is supported with the DMU and other requirements
can be obtained by contacting the Global Data Center.
1.7 LICENSE REQUIREMENTS
1.7.1 VHF RADIO
Aircraft must have proper VHF radio license to operate on frequencies between 128.000 Mhz to
132.000 Mhz for DMU.
1.7.2 INMARSAT SATELLITE APPROVAL
Aircraft must be registered with INMARSAT for use of the SATAFIS system if installed.
INMARSAT approval is coordinated through the Honeywell Global Data Center.
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1.7.3 ARNAV RPU INSTALLATION KIT
The ARNAV RPU installation kit, PN 453-0083, is required to install the ARNAV MFD 5115 RPU,
PN 453-2503-08. Assemble tray per sheet 1 of Figure 2-16.
DESCRIPTION ARNAV PART NUMBER QTY
RPU Rear Panel Assembly 452-0116 1
Shield Plate 402-1277 1
RPU Frame (marked with kit assy, PN 453-0083 402-1276 1
Washer, Flat #4 x 1/4 SS 246-0004 1
Screw, PHP 4-40 x 1/4 SS 201-0404 7
Screw, PHP 3-48 x 3/8 STL 201-0306 2
Base, Cable Tie 182-1032 1
Receptacle, Panel 24 pin 150-1151 1
Screw, 6-32 x 1/2 PH Slot SS 207-0602 8
1.8 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
The instructions for continued airworthiness given in the TC or STC approvals for this product
supplements or supersedes the instructions for continued airworthiness in this manual. Most
Honeywell products are designed and manufactured to allow "on condition maintenance." On
condition maintenance is described as follows; There are no periodic service requirements
necessary to maintain continued airworthiness. No maintenance is required until the equipment
does not properly perform it’s intended function. When service is required, a complete
performance test should be accomplished following any repair action. Consult the appropriate unit
Maintenance/Overhaul Manual for complete performance test information.
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AIRBORNE FLIGHT INFORMATION SYSTEM
SECTION 2
INSTALLATION
2.0 INTRODUCTION
The component sizes, centers of gravity, tray dimensions and installation locations are shown in
Figures 2-1 through 2-15.
NOTE:
The conditions and tests required for TSO approval of this article are minimum
performance standards. It is the responsibility of those desiring to install this
article either on or within a specific type or class of aircraft to determine that the
aircraft installation conditions are within TSO standards. The article may be
installed only if further evaluation by the applicant documents an acceptable
installation and is approved by the Administrator.
2.1 UNPACKING AND INSPECTING EQUIPMENT
Exercise extreme caution when unpacking equipment. Perform a visual inspection of the unit for
evidence of physical damage incurred during shipment. If a damage claim must be filed, save the
shipping container and all packing materials to substantiate your claim. The claim should be filed
as soon as possible. The shipping container and packing materials should be retained in the
event that storage or re-shipment of the equipment is necessary.
2.2 GENERAL INSTALLATION REQUIREMENTS
(a) For GNS-1000 Installations: The maximum recommended cable length between the
DMU and Flight Management Computer (FMC) is 50 feet. Do not bundle DMU/FMC
data lines or antenna cables with any power cables.
(b) For GNS-500A Installations: The maximum recommended cable length between the
DMU and Control Display Unit (CDU) is 50 feet. Do not bundle DMU/CDU data lines or
antenna cables with any power cables.
(c) For GNS-X, GNS-XLS, GNS-XL, GNS-XES flight management systems Installations:
The maximum cable length between the DMU and the flight management systems is 50
feet. Do not bundle DMU/flight management systems data lines or antenna cables with
any power cables.
(d) The maximum recommended cable length between the DMU and DTU is 50 feet. Do
not bundle DMU/DTU data lines or antenna cables with any power cables.
(e) The maximum recommended cable length between the DMU and SCU is 100 feet. Do
not bundle DMU/SCU data lines or antenna cables with any power cables.
(f) The maximum cable length between the Jet Blade antenna and HPA/LNA is 10 feet,
refer to Figure 3-31, Table 1. The maximum cable length between Low Profile Jet Blade
antenna and HPA/LNA is 10 feet, refer to Figure 3-31, Table 1.
(g) The maximum cable length between the SCU and HPA/LNA is determined by the type
of cable used. Refer to Table 2 in Figure 3-31 for cable length information.
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(h) The DMU has heat removed by conduction: make sure the unit is installed in a location
where the ambient temperatures are -67° F to +131° F (-55° C to +55° C).
(i) The DTU should be mounted within the pressure vessel in a temperature controlled
environment of +5° F to +131° F (-15° C to +55° C).
(j) Mount SCU tray to provide good electrical bonding to airframe ground. Lightning strike
protection, RF susceptibility and emission characteristics are dependent on good
electrical grounding of the tray and cable shield returns.
(k) The SCU should be mounted within the pressure vessel in a temperature controlled
environment of -13° F to +131° F (-25° C to +55° C).
2.3 DATA MANAGEMENT UNIT (DMU) INSTALLATION
(a) See Figures 2-1 and 2-2.
(b) Mount DMU 1/2 ATR short tray.
(c) Install DMU in tray.
2.4 DATA TRANSFER UNIT (DTU)
(a) See Figures 2-5 through 2-10.
(b) Mount DTU in aircraft cockpit in a location easily accessible to pilot.
(c) Two mounting provisions are available; DZUS or tray mounting.
NOTE:
The DTU uses AUL-SPEC Dzus fasteners as standard mounting provisions.
However, for aircraft not equipped with these fastener strips see Figure 2-9.
2.5 CONFIGURATION MODULE IN DATA MANAGEMENT UNIT (DMU) TRAY
(a) For ease of assembly it is recommended that the DMU be wired to the configuration
module per Section 3, ELECTRICAL INSTALLATION prior to installing configuration
module. The wires are to be soldered to the tray pins.
NOTE:
The location and number of the configuration module pins are stamped on
the tray for reference during wiring.
(b) Remove configuration module from packing, be sure not to bend pins of module.
(c) Place module on tray as shown in Figures 2-2 and 2-3 aligning pins with holes in tray.
Tighten screws once module is fitted properly. Do not force seating of module.
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2.6 SATELLITE COMMUNICATION UNIT (SCU)
(a) See Figures 2-12 and 2-13.
(b) Mount 1/4 ATR short rack per Paragraph 2.2.
(c) Install SCU in rack and secure hold down mechanism.
2.7 HIGH POWER AMPLIFIER/LOW NOISE AMPLIFIER INSTALLATION (HPA/LNA)
(a) See Figure 2-14.
(b) The HPA/LNA should be mounted in an area that ensures optimum antenna placement.
Coax lengths should be within maximum length limits per Figure 3-31 Table 2.
(c) The HPA/LNA should be well bonded to the aircraft skin per Paragraph 2.8.1.
2.8 ANTENNA INSTALLATION
2.8.1 Bonding Checklist
(a) The recommended bonding jumper for DC and low frequency AC (50 kHz) is braided
wire. For radio frequencies greater than 50 khz use a flat metal strap with a length to
width ratio of 1. For brass and copper alloys the strap should be 0.025 inch thick. For
aluminum alloys the strap should be 0.040 inch thick.
(b) Periodic inspections should be made of aircraft bonding devices since they are
subject to wear and breakage.
(c) After major modification, painting, or repairs, inspect control surfaces, inspection
plates, and drain masts to assure that proper metal-to-metal contact is maintained.
2.8.2 Low Profile Jet Blade Antenna Installation (See Figure 2-15)
(a) The Jet Blade antenna should be mounted on the center line of the aircraft on the
aircraft skin which is horizontal during enroute flight.
(b) The antenna should be mounted on the top of the aircraft, over the cockpit or on top of
the tail of the aircraft.
NOTE:
This location reduces the possibility of obstructing satellite signals because of
shadowing.
(c) The antenna should be mounted as far as possible from other radiating devices (3 feet
minimum VHF comms, HF comms, etc.).
(d) The antenna should be well bonded to the aircraft skin per Paragraph 2.8.1 (a).
(e) The antenna should be sealed to the aircraft to prevent corrosion from forming
between the skin of the aircraft and the antenna.
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2.9 ARNAV RPU INSTALLATION
2.9.1 Installation Kit
An ARNAV MFD 5115 Installation Kit P/N 453-0083 is required to install the ARNAV MFD
5115 RPU.
2.9.2 Installation Guide
See figures 2-16 and 2-17.
2.9.3 Cooling Considerations
It is highly recommended to use forced air cooling. A duct port is provided on the install
tray. Make sure that the unit is installed in a location where the ambient temperature is
between -20° C and +70° C.
2.9.4 Installation Considerations
Wiring length between the RPU and the GNS-XLS CDU should be no more than 15 feet.
Wiring between the RPU and the DMU is unlimited.
Global
Must be mounted inside the pressure vessel.
Should have access to front, to facilitate changing of the database PCMCIA card.
2.9.5 Database Card
To begin database service and receive the database card, please complete the form in
figure 1-1 and fax it to (602) 436-1501.
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AIRBORNE FLIGHT INFORMATION SYSTEM
DATA MANAGEMENT UNIT (DMU) PN 42000-XX-XX OR PN 400-045500-XXXX
Figure 2-1
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Note: All dimensions are in inches (centimeters).
DMU TRAY PN 42701-1
Figure 2-2
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DMU RACK
NOTE:
1. Weight 0.102 lbs. (0.045 Kg) max.
Configuration Module Mounting Provision P/N 31990-1
Figure 2-3
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Configuration Module Outline and Mounting P/N 31990-1
Figure 2-4
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NOTE:
All dimensions are in inches (millimeters).
DATA TRANSFER UNIT (DTU) PN 43000-01-01-X
Figure 2-5
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THIS PAGE IS RESERVED
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NOTES:
1. All dimensions are in inches (millimeters).
Triple Port DTU PN 15655-XXXX
Figure 2-6
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AIRBORNE FLIGHT INFORMATION SYSTEM
Figure 2-7
Figures 2-7 and 2-8 are
provided for DTU mounting
reference only.
DTU TRAY MOUNTING
Figure 2-8
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DTU INSTRUMENT PANEL MOUNTING PROVISION
Figure 2-9
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AIRBORNE FLIGHT INFORMATION SYSTEM
DTU TRAY PN 43010-X
Figure 2-10
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AIRBORNE FLIGHT INFORMATION SYSTEM
THIS PAGE IS RESERVED
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AIRBORNE FLIGHT INFORMATION SYSTEM
ANTENNA SWITCHING UNIT (ASU) PN 44000-1
DWG. NO. 155-06047-0000
Figure 2-11
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SATELLITE COMMUNICATION UNIT (SCU)
DWG. NO. 153-017311-01 REV AA
Figure 2-12
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NOTE: All dimensions are in inches (millimeters).
SCU TRAY PN 300-317337-01
Figure 2-13
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THIS PAGE IS RESERVED
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AIRBORNE FLIGHT INFORMATION SYSTEM
HIGH POWER AMPLIFIER/LOW NOISE AMPLIFIER (HPA/LNA)
DWG. NO. 153-017310-01 REV AA
Figure 2-14
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LOW PROFILE JET BLADE ANTENNA
DWG. NO. 153-017537-01 REV AA
Figure 2-15
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MFD 5115 RPU
DWG. NO. 155-05453-0000, REV A, Sheet 1 of 4
Figure 2-16
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MFD 5115 RPU
DWG. NO. 155-05453-0000, REV A, Sheet 2 of 4
Figure 2-16
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AIRBORNE FLIGHT INFORMATION SYSTEM
MFD 5115 RPU
DWG. NO. 155-05453-0000, REV A, Sheet 3 of 4
Figure 2-16
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AIRBORNE FLIGHT INFORMATION SYSTEM
MFD 5115 RPU
DWG. NO. 155-05453-0000, REV A, Sheet 4 of 4
Figure 2-16
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SECTION 3
ELECTRICAL INSTALLATION
3.0 GENERAL
The basic system interconnect wiring is shown in Figure 3-1 through Figure 3-31 and the
connectors for each system component are shown in Figures 3-32 through 3-43.
Transmitter designation applies to the signal function for that unit. Example, a DMU transmitter (H)
and (L) will connect to a DTU receiver (H) and (L).
All signal and power shields are to be grounded at one end, preferably at the point of origination
and shield continuity shall be maintained through bulkhead disconnects.
All digital data shields are to be grounded at both ends and shield continuity shall be maintained
through bulkhead disconnects.
NOTE:
This equipment has been designed to be installed in aircraft locations where it is
not subjected to falling water (generally the result of condensation), rain, or
sprayed water in the course of normal aircraft operations.
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THIS PAGE IS RESERVED
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DMU FUEL FLOW WIRING USING ELDEC INDICATOR
Dwg. No. 155-01712-4001 Rev 0
Figure 3-1
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DMU FUEL FLOW WIRING FOR VARIOUS INDICATORS (see note 5)
Dwg. No. 155-01712-4002 Rev A
Figure 3-2
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU FUEL FLOW INTERTECHNIQUE
Dwg. No. 155-01712-4003 Rev A
Figure 3-3
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DMU FUEL FLOW GE 5 VRMS AC
Dwg. No. 155-01712-4004 Rev A
Figure 3-4
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DMU FUEL FLOW Eldec Transmitter As Source
Dwg. No. 155-01712-4005 Rev A
Figure 3-5
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO TRIPLE PORT DTU
Dwg. No. 155-01712-4006 Rev 0
Figure 3-6
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO DTU PN 43000-01-01-3 and PN 43000-01-01-4
Dwg. No. 155-01712-4007 Rev A
Figure 3-7
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO DTU PN 43000-01-01-1 and PN 43000-01-01-2
Dwg. No. 155-01712-4008 Rev 0
Figure 3-8
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DMU TO NMU GNS-X
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 1 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO GNS-XLS
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 2 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO GNS XL
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 3 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO Honeywell FMS NZ-2000
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 4 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO Honeywell FMS IAC (F-900 EX)
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 5 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO COLLINS FMS
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 6 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO UNIVERSAL FMC UNS-1C
Dwg. No. 155-01712-4009 Rev C
Figure 3-9 (Sheet 7 of 7)
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AIRBORNE FLIGHT INFORMATION SYSTEM
CDU-XLS TO AFIS INTERFACE
Dwg. No. 155-01657-0000 Rev -
Figure 3-9A (Sheet 1 of 2)
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AIRBORNE FLIGHT INFORMATION SYSTEM
CDU-XLS TO AFIS INTERFACE
Dwg. No. 155-01657-0000 Rev -
Figure 3-9A (Sheet 2 of 2)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO FMC GNS-500A SERIES 4/5
Dwg. No. 155-01712-4010 Rev 0
Figure 3-10
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO SWITCHED AFIS ANTENNA
Dwg. No. 155-01712-4011 Rev A
Figure 3-11
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO DEDICATED AFIS ANTENNA
Dwg. No. 155-01712-4012 Rev 0
Figure 3-12
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO PRINTERS AND TERMINALS
Dwg. No. 155-01712-4013 Rev A
Figure 3-13
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO CONFIGURATION MODULE AND SATFONE SYSTEM
Dwg. No. 155-01712-4014 Rev B
Figure 3-14
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO SCU
Dwg. No. 155-01712-4015 Rev B
Figure 3-15 (Sheet 1 of 2)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU TO SCU
Dwg. No. 155-01712-4015 Rev B
Figure 3-15 (Sheet 2 of 2)
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AIRBORNE FLIGHT INFORMATION SYSTEM
DISCRETE WIRING
Dwg. No. 155-01712-4016 Rev 0
Figure 3-16
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU FUEL FLOW WIRING USING ELDEC INDICATOR
Dwg. No. 155-01711-0001 Rev A
Figure 3-17
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU FUEL FLOW WIRING For Various Indicators (see note 5)
Dwg. No. 155-01711-0002 Rev A
Figure 3-18
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AIRBORNE FLIGHT INFORMATION SYSTEM
DMU FUEL FLOW INTERTECHNIQUE
Dwg. No. 155-01711-0003 Rev A
Figure 3-19
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