AIRCRAFT MANUAL SUPPLEMENT To support Instructions for Continued Airworthiness in accordance with Regulations EASA CS-25.1529/FAR 14 CFR-25.1529, Appendix H. B757 – MSN 25622 Document No: AMS-757-25622 Intro Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
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AIRCRAFT MANUAL SUPPLEMENT · MOD-1040 SELCAL Code Change AERODEC MOD-1041 Mode S Code Change AERODEC MOD-1042 Introduction of Mini QAR AERODEC MOD-1043 Installation of a Hot Jug
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AIRCRAFT MANUAL SUPPLEMENT To support Instructions for Continued Airworthiness in accordance with Regulations EASA CS-25.1529/FAR 14 CFR-25.1529, Appendix H.
B757 – MSN 25622 Document No: AMS-757-25622
Intro Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
Issue 4 onwards supplied by 365 Aerospace Ltd. Issue 4 Document re-written as a 365 Aerospace document Supplemental information added throughout to include 365 Aerospace Mod-0006
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
The Aircraft Manual Supplement (AMS) is to be used in conjunction with the related aircraft’s manuals. The information contained within this manual relates to various alterations/changes/modifications that have been carried out on the associated aircraft. A list of effective alterations/changes/modifications can be found in the Introduction pages to this manual. These alterations/changes/modifications are in addition to the initial design of the aircraft and are therefore detailed within this manual using appropriate and related convention. This manual complies with EASA Regulations CS-25.1529 and CS-25 Appendix H, which in turn mirror the FAA regulation 14 CFR 25.1529.
RRA-00 Page 1
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
INTRODUCTION
1. General A. This publication was prepared on behalf of 365 Aerospace Ltd and is in accordance with Air Transport Association of America
Specification No. 100, Specification for Manufacturers Technical Data. The data contained within is related to certain changes/modifications/alterations that are in addition to the associated airplane’s type design.
NOTE: THIS MANUAL IS PREPARED SPECIFICALLY TO COVER THE AIRPLANE LISTED IN THE "INTRODUCTION"
SECTION, FOR THE OWNER/OPERATOR NAMED ON THE TITLE PAGE.
THIS MANUAL IS NOT SUITABLE FOR USE, INCLUDING WITHOUT LIMITATION, GENERAL INSTRUCTIONS OR TRAINING, FOR ANY AIRPLANES NOT LISTED HEREIN.
B. The convention for the use of this publication is in the same convention (ATA 100) as the associated manufacturers AMM,
WDM, and IPC. Therefore, this publication is a SUPPLEMENT to the associated AMM, WDM, and IPC, and instructions on how to use this manual are equivalent to the instructions on how to use the manufacturers AMM, WDM and IPC.
C. This Manual Supplement has been raised to give historic design information pertaining to the following related aircraft
manuals:
WDM – Wiring Diagram Manual
EL – Equipment List
WL – Wire List
IPC – Illustrated Parts Catalogue
AMM – Aircraft Maintenance Manual D. For information on the approval of the technical content of this document, please refer to the Change/Mod/Alteration listing E. Aircraft Effectivity Information:
MODEL/ TYPE
CUST EFFECT CODE
CUST EFFECT CODE
(IPC ONLY)
VARIABLE ENGR
NUMBER
ENGINE SET
NUMBER LINE
NUMBER
MFG SERIAL
NUMBER REGISTRY NUMBER
CUST ASSIGNED AIRPLANE
IDENT
757-28A 239 NB239 NW815 N0230 25622
INTRO-00 Page 1 APR 01/16
Produced on behalf of 365 Aerospace Limited, UK. 365 Aerospace own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission In writing from the owner.
INTRODUCTION
2. Change/Modification/Alteration Listing
A. DOA Mod/STC information – Table 2.1
Mod/STC Ref: Title:
MOD-0006 Installation of a Controller Pilot Data Link Communications (CPDLC) System MOD-0123 Change for the Introduction of Bose A20 Headsets
B. Owner/Operator/Supplier Mod/STC Information – Table 2.2
Mod/STC Ref: Title: Supplier:
MOD-1038 EFIS Strapping Change AERODEC MOD-1039 EGPWS Callout Change AERODEC MOD-1040 SELCAL Code Change AERODEC MOD-1041 Mode S Code Change AERODEC MOD-1042 Introduction of Mini QAR AERODEC MOD-1043 Installation of a Hot Jug in the Galley AERODEC MOD-1044 Installation of SSFDR AERODEC
3. Approval
A. With reference to any Mod/STC indicated in Table 2.1 above, the technical content of the supplement information associated
with any listed Mod/STC above is approved under the authority of DOA No. EASA.21J.575. B. With reference to any Mod/STC indicated in Table 2.2 above, the technical content of the supplement information associated
with any listed Mod/STC above is approved under the authority of the named Owner/Operator/Supplier of the document. The Owner/Operator/Supplier of the document has given the compiler of this supplement rights to use their information in order to produce this manual supplement.
C. The Checking process will include a verification of technical consistency with the associated Mod/STC and Compliance
documentation which may relate to effectivity, description, effects on airworthiness and environmental protection especially when limitations are changed or affected.
Produced by 365 Aerospace Limited, UK, who own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
EQUIPMENT
LIST
INDEX
B757 WIRING DIAGRAM MANUAL
INCORPORATES: EQUIPMENT LIST Section INDEX 365 Aerospace MOD-0006 Page 1
Equip Part Number Used on Dwg Qty Diagram Effectivity Part Description Vendor Location
M09000 14114-1-02 (MOD 3) 2-59475-702 1 23-22-11 NB239 UNIT – DLINK+ ACARS EMTEQ P8 AFT PILOT CONTROL STAND M09001 12854-4 1 23-22-11 NB239 UNIT – PERSONALITY MODULE P8 AFT PILOT CONTROL STAND M09002 81194 365-25-0003 1 23-12-31 NB239 ANTENNA - GPS 365 AEROSPACE LTD STA 690 RBL 5.00 M09003 8055515-4503 2-59475-704 1 23-22-11 NB239 PRINTER – DATA (PTA-45B) EMTEQ P8 AFT PILOT CONTROL STAND M09004 84327-50-200B 365-25-0005 1 23-12-31 NB239 SENSOR – GPS/WAAS 365 AEROSPACE LTD E4-4 SHELF
Produced by 365 Aerospace Limited, UK, who own the copyright of the format of this Manual Supplement, which is supplied in confidence. The contents must not be reproduced without permission in writing from the owner.
WIRE
LIST
INDEX
B757 WIRING DIAGRAM MANUAL
INCORPORATES: WIRE LIST Section INDEX 365 Aerospace MOD-0006 Page 1
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W0110 286N0110 P11-1 MODULE WIRING – LEFT BUSSES 0900 12 23-22-11 SHT 1 P11-1 C539 B P11-1 C9000 B NB239 MOD-0006 0901 16 31-33-01 P11-1 C592 B P11-1 C9001 B NB239 MOD-0006
B757 WIRING DIAGRAM MANUAL
91-21-11
INCORPORATES: WIRE LIST Section W0124 365 Aerospace MOD-0006 Page 1
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W0124 286N0124 P11-1 MODULE WIRING – LEFT – STBY – LOAD SIDE 0110 16 23-12-31. P11-1 C546 L P11-1 C9002 L NB239 MOD-0006 9000 16 23-22-11 SHT 1 P11-1 C9000 L P11-1 D40616J 7 NB239 MOD-0006 9001 22 31-33-01 P11-1 C9001 L P11-1 D40616J 2 NB239 MOD-0006
B757 WIRING DIAGRAM MANUAL
91-21-11
INCORPORATES: WIRE LIST Section W1161 365 Aerospace MOD-0006 Page 1
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W2653 286N2653 VOICE RECORDER TO E/E RACK 9001 24 23-71-11 E4-3 D41551P 20 STA1615
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W4228 286N4228 E/E SHELF DISC TO LEFT WING BODY DISC 9001 24 31-51-33 P8 D9002 G E3-4 D42012P 13 NB239 MOD-0006
B757 WIRING DIAGRAM MANUAL
91-21-11
INCORPORATES: WIRE LIST Section W4471 365 Aerospace MOD-0006 Page 1
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W4471 286N4471 E/E RACK, INTERRACK LEFT 9001 24 31-51-33 E3-4 D41311P 19 P51 D41481P 8 NB239 MOD-0006
B757 WIRING DIAGRAM MANUAL
91-21-11
INCORPORATES: WIRE LIST Section W9001 365 Aerospace MOD-0006 Page 1
Bundle No. Part Number Description From To Info Wire No. GA Diagram Location Equip Term Location Equip Term Effectivity Mod No. W9008 9001 CX1 23-12-31. E4-4 D9008-P2 =A STA 690 D9005 A1 NB239 MOD-0006 9001Z CX1 23-12-31. E4-4 D9008-P2 =C STA 690 D9005 C1 NB239 MOD-0006
ILLUSTRATED
PARTS
CATALOGUE
Contents
IPC-CONTENTS Page 1
Chapter 11 PLACARD & MARKINGS
11-31-04-01Z – PLACARD INSTL – SELCAL AND REGISTRATION
A. ACARS (Aircraft Communications Addressing and Reporting System) is a digital data link system that enhances two-way communications between the airplane and a ground station.
B. ACARS enhances air/ground communications by easing the flight compartment work load, and
eliminating much of the air/ground voice communication traffic. ACARS enables a high-speed computer controlled digital data link between the airplane and ground facilities using: a VHF transceiver, ARINC or other data link stations, landlines, a central control station, and airline terminals. The data link exchanges routing airlines operations information.
C. ACARS receives data inputs from airplane sensors, external systems, and the pilot inputs.
Data communications is displayed to the pilot via Dlink+ ACARS Display. Outgoing data communications are sent automatically or manually. Data is sent using ARINC assigned frequencies in ARINC encoded audio frequency tone modulation over the ground data link stations.
D. ACARS receives power from the left 28v dc bus. The system circuit breaker is on the
overhead panel P11. 2. Component Details (Fig. 1)
A. Dlink+ ACARS Unit.
(1) The Dlink+ ACARS Unit provides Aircraft Communication Addressing and Reporting System (ACARS) message functionality by combining three ARINC devices into one cockpit equipment panel mounted device. The three devices are: (a) ARINC 7248 Communication Management Unit (CMU) (b) ARINC 750 VHF Data Link (VDL) Radio (c) ARINC 739 Multi-purpose Control Display Unit (MCDU)
Dlink+ ACARS Unit provides air to ground and ground to air data only communication. The system sends and receives free text messages and ACARS messages to support Aircraft Operational Control (AOC) communications over the ACARS VHF data link. The system has a Personality Module (PM) which is a serial EEPROM that houses the unit's configuration and database. When the unit power-up it reads the configuration from the PM into its internal Random Access Memory (RAM). This defines the system's hardware configuration and many of its settings.
(1) The personality Module (PM) stores database used by the DI ink+ ACARS Unit. When the Dlink+ Unit is power-up it reads the configuration from the (PM) into its internal Random Access Memory (RAM). This defines the system's hardware configuration and many of its settings.
(2) The Personality Module (PM) is a cable wrapped to one of the Dlink+ ACARS Unit mating
connector's cable. The Personality Module has a pigtail of four wires that are inserted into the associated mating connector. These wires are used to load the stored database to the Dlink+ ACARS Unit (RAM) and download new database information.
C. Data Printer
(1) The printer is used to print the various Dlink+ ACARS Unit screen forms. Additionally,
if connected to other compatible subsystem, it will also print the screen forms for that subsystem.
3. Operation
A. Functional Description
(1) Off mode
(a) Dlink+ ACARS Unit is off when 28v de left bus power is removed from the unit. There is no system activity or indications.
(2) Operation
(a) When the Dlink+ ACARS Unit is power on, the unit reads the configuration of the
Personality Module PM to random access memory (RAM), internal to the Dlink+. Once powered, the unit can provide the capabilities for sending and receiving free text messages and ACARS messages to support end-to-end Aircraft Operational Control (AOC) communication over the ACARS data link.
A. This procedure contains the task to install the Spectralux Dlink+ ACARS Unit software into the Personality Module using a Laptop computer and the Ethernet maintenance port located on the P61 maintenance panel.
2. ACARS Software Installation with a Laptop Computer
A. References
(1) AMM 24-22-00/201, Electrical Power- Control.
B. Access
(1) Location Zones
211/212 Flight Compartment
C. Procedure
(1) Make sure the following circuit breaker is close:
(a) P11-1 Overhead Circuit Breaker:
1) ACARS
(2) On the P61 maintenance panel, connect the Laptop computer containing the Laptop Loader Software to the Ethernet port.
(3) Turn the Laptop computer ON and start the Laptop Loader Software containing the Dlink+
configuration files for the aircraft.
(4) To load the Dlink+ ACARS configuration to the personality module click on the Write Config button and select the appropriated file that is provided for the aircraft.
(5) Once the appropriated file is selected, click OPEN to access the configuration software
file.
(6) Enter the Tail Number and the ICAO address for the aircraft and press OK.
NOTE: The Laptop Loader will close and the DI ink+ ACARS Unit will reboot.
(7) After the Dlink+ ACARS Unit reboot is completed, start the Laptop Loader Software and click the Write DB button.
(8) Select the customer or test database file provided for the aircraft and click OPEN.
NOTE: The Laptop Loader will close and the Dlink+ Unit will reboot
(9) Turn off the Laptop and disconnect the Ethernet cable from the P61 maintenance panel's
Ethernet port.
(10) Do an ACARS System Test per AMM 23-22-00/501.
A. There are two tasks in this procedure. The first task is the operational test of the Dlink+ Aircraft Communications Addressing and Reporting System (ACARS). The second is the system test of the ACARS.
B. The operational test is a minimum check of the basic ACARS System.
C. The system test contains checks of all of the primary ACARS functions. The test includes
checks of the OOOI operation, and the ACARS interfaces.
D. When the ACARS cannot make a link with the ground station it is not a system failure. This is usually one of the following conditions:
(1) The RF path between the VHF antenna and the ground station is blocked. It can help to
move the airplane to a better position.
(2) The ground station has a problem. Tell them that you cannot make a link. If they have a problem, other airplanes that use the data link will also get no ACARS communication.
E. If you tow the airplane, or move it with its power, open the ACARS circuit breaker. If you
do not, the ACARS may transmit the Out time. 2. ACARS Operational Test
(a) Locate the aircraft on the airfield away from any existing structures that may
shadow the reception from a remote VHF ground station.
(b) From the main menu of the Dlink+ ACARS Unit, locate the maintenance menu by navigating thru the unit's menu selection.
NOTE: The menus will look different depending on specific aircraft type and
installation. The maintenance menu can be located from a MISC or MAINT selection on the Dlink+ ACARS Unit main menu.
(c) From the Dlink+ ACARS Unit main menu, select the Line Select Key (LSK) adjacent to
the MISC or MAINT menu option as required to access the maintenance menu pages.
NOTE: The Dlink+ ACARS Maintenance Menu pages will normally contain radio status and OOOI status on the A half of the first page and typically contains a menu to check specific systems on page B.
(a) From the Dlink+ ACARS Unit maintenance menu (page B), select the Line Select Key
(LSK) adjacent to the PING TEST prompt.
(b) From the PING TEST screen, select the Line Select Key (LSK) L2 adjacent to the TEST CONTROL prompt and verify that the display changes form STOP to GO.
(c) Verify for proper VHF connection and that the Ping Test passes by verifying that
the TEST CONTROL display changes to WAIT and then returns to STOP.
NOTE: The DELAY CNT will count the seconds until the response is received. The AVG SEC will show the time it takes to receive a response. If no test response is received after the timeout period the TEST CONTROL will display a FAIL message.
(3) Annunciator Lights Test
(a) On the Dlink+ ACARS Unit, press and hold the A/B Line Select Key (LSK).
(b) Verify that the Dlink+ ACARS Unit annunciator lights (MSG, TEMP and FAIL) come on.
D. Put the Airplane back to its Initial Condition
(1) Return the Dlink+ ACARS display to the main menu page.
(2) Remove electrical power (AMM 24-22-00/201).
3. ACARS System Test
A. References (1) AMM 24-22-00/201, Electrical Power- Control (2) AMM 31-31-00/501, Flight Data Recorder System (3) AMM 31-41-00/501, EICAS System (4) AMM 32-09-02/501, Air/Ground Relay System (5) AMM 32-44-00/501, Parking Brake System (6) AMM 33-13-00/501, Integral Panel Lights (7) AMM 34-12-00/501, Left Air Data Computer System (8) AMM 34-21-00/501, Inertial Reference System (9) AMM 34-61-00/501, Left Flight Management System (10) AMM 52-71-00/501, Door Warning System Proximity Sensors
B. Prepare for the System Test
(1) Supply electrical power (AMM 24-22-00/201)
(2) Make sure all aircraft doors are closed.
(3) Make sure the parking brake is set.
(4) Make sure these circuit breakers are closed:
(a) P11-1 Overhead Circuit Breaker Panel:
1) A CARS 2) Data Printer
C. Procedure
(1) Test Setup
(a) Locate the aircraft on the airfield away from any existing structures that may shadow the reception from a remote VHF ground station.
(b) From the main menu of the Dlink+ ACARS Unit, locate the maintenance menu by navigating thru the unit's menu selection.
NOTE: The menus will look different depending on specific aircraft type and
installation. The maintenance menu can be located from a MISC or MAINT selection on the Dlink+ ACARS Unit main menu.
(c) From the Dlink+ ACARS Unit main menu, select the Line Select Key (LSK) adjacent to
the MISC or MAINT menu option as required to access the maintenance menu pages.
NOTE: The Dlink+ ACARS Maintenance Menu pages will normally contain radio status and OOOI status on the A half of the first page and typically contains a menu to check specific systems on page B
(2) Annunciator Lights Test
(a) On the Dlink+ ACARS Unit, press and hold the NB Line Select Key (LSK).
(b) Verify that the Dlink+ ACARS Unit annunciator lights (MSG, TEMP and FAIL) come on.
(3) Dlink+ OOOI Interface Test
(a) From the Dlink+ ACARS Unit maintenance (page A}, verify that the OOOI are
operating by changing the discrete states on the aircraft and verifying that they change state in the OOOI status maintenance menu screen:
(e) From the EDIT CONFIGURATION screen (page 1), verify that the correct aircraft registration number and ICAO address is displayed.
(f) Return to the Dlink+ ACARS Unit to the maintenance menu screen.
(g) If any changes were made to the EDIT CONFIGURATION screen. Follow the steps to
return to the Dlink+ ACARS Unit maintenance menu screen.
1) Select the Line Select Key (LSK) adjacent to the RETURN prompt, and verify that the CONFIRMATION menu is displayed.
2) On the CONFIRMATION menu screen, press the Line Select Key (LSK) until the NO
or YES option is displayed.
NOTE: Pressing the LSK will cycle the selection to NO, CANCEL and YES.
3) Once the NO or YES option is selected, select the Line Select Key (LSK) adjacent to the RETURN prompt to return the Dlink+ ACARS Unit to the maintenance menu screen.
(6) Dlink+ Monitor Bus Status Test
(a) From the Dlink+ ACARS Unit maintenance menu (page B), select the Line Select Key
(LSK) adjacent to the MONITOR prompt.
NOTE: The Monitor menu will display the status of each of the 429 busses and some of the key variables interfaced to the Dlink+ ACARS Unit.
(b) From the MONITOR Bus Status screen, verify that each of the following 429 busses
EICAS, FMC, ADC and IRU display a GOOD status.
(c) Open each of the respective C/B for the EICAS, FMC, ADC and IRU systems. Verify that each of the respective 429 busses EICAS, FMC, ADC, and IRU display a FAIL status.
(d) Reset the C/B for the EICAS, FMC, ADC and IRU systems. Verify that each of the
following 429 busses EICAS, FMC, ADC, and IRU display a GOOD status.
(e) If there are any Variables displayed on the MONITOR Bus Status screen, verify that each of the variables display a value and not XXX.
(f) Return to the Dlink+ ACARS Unit maintenance menu screen.
(7) Dlink+ Printer Interface Test
(a) From the Dlink+ ACARS Unit maintenance menu (page B), select the Line Select Key
(LSK) adjacent to the PRINT TEST prompt.
(b) From the PRINTER TEST screen, select the Line Select Key (LSK) adjacent to the PRINT prompt and verify that the data printer prints the information selected on the Dlink+ ACARS screen.
(c) Return to the Dlink+ ACARS Unit maintenance menu screen.
(8) Dlink+ VHF Ping Test
(a) From the Dlink+ ACARS Unit maintenance menu (page B}, select the Line Select Key
(LSK) adjacent to the PING TEST prompt.
(b) From the PING TEST screen, select the Line Select Screen (LSK) L2 adjacent to the TEST CONTROL prompt and verify that the display changes form STOP to GO.
(c) Verify for proper VHF connection and that the Ping Test passes by verifying that the TEST CONTROL display changes to WAIT and then returns to STOP.
NOTE: The DELAY CNT will count the seconds until the response is received. The
AVG SEC will show the time it takes to receive a response. If no test response is received after the timeout period the TEST CONTROL will display a FAIL message.
(d) Return to the Dlink+ ACARS Unit menu screen.
(9) Dlink+ Free Text Message Test
(a) From the Dlink+ ACARS Unit menu screen page A, select the Line Select Key (LSK)
adjacent to the FREE TEXT prompt.
(b) Select FREE TEXT option.
(c) From the FREE TEXT MSG screen (page A), Type in a message with a minimum length of 24 characters. The outgoing message should request the recipient to reply with a text message.
(d) Select (page B) of the FREE TEXT MSG screen and select the Line Select Key (LSK)
adjacent to the SEND option.
(e) Verify that the free text message was transmitted.
(f) Return to the Dlink+ ACARS Unit menu screen.
(g) Verify that the Dlink+ MSG (white) annunciator illuminates when the up-linked message is received. Confirm the received message is in response to the sent message.
D. Put the Airplane back to its Initial Condition
(1) Return the Dlink+ ACARS display to the main menu page.
A. There are two tasks in this procedure. The first task is the removal of the Dlink+ ACARS Unit. The second task is the installation of the Dlink+ ACARS Unit.
B. The Dlink+ ACARS Unit is installed on the P8 Aft Electronic Control Panel.
2. Dlink+ ACARS Unit - Removal
A. Access
(1) Location Zones
211/212 Flight Compartment
B. Procedure
(1) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) P11-1 Overhead Circuit Breaker:
1) ACARS 2) PRINTER
(2) Remove the Dlink+ ACARS Unit (AMM 20-10-01/401).
(a) Loosen the four quarter-turn fasteners that attach the Dlink+ ACARS Unit to the
panel.
(b) Lift the Dlink+ Unit to get access to the electrical connectors.
(c) Disconnect the electrical connectors.
(d) Put a protective cover on the electrical connector. 3. Dlink+ ACARS Unit- Installation
A. Access
(1) Location Zones
211/212 Flight Compartment
B. References
(1) 24-22-00/201, Electrical Power - Control
C. Procedure
(1) Make sure these circuit breakers are open:
(a) P11-1 Overhead Circuit Breaker Panel
1) ACARS 2) PRINTER
(2) Install the Dlink+ ACARS Unit (AMM 20-10-01/401).
(a) Remove the protective cover from the electrical connector.
(b) Examine the electrical connectors for bent or broken pins, dirt, and damage.
PERSONALITY MODULE- REMOVAL/INSTALLATION 1. General
A. There are two tasks in this procedure. The first task is the removal of the Personality Module. The second task is the installation of the Personality Module.
B. The Personality Module is installed to one of the Dlink+ ACARS Unit mating connector harness
located in the P8 Aft Electronic Control Panel. 2. Personality Module - Removal
A. Access
(1) Location Zones
211/212 Flight Compartment
B. Procedure
(1) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) P11-1 Overhead Circuit Breaker:
1) ACARS 2) PRINTER
(2) Remove the Personality Module (AMM 20-10-01/401).
(a) Remove the Dlink+ ACARS Unit from PS aft electronic control panel (AMM 23-22-
01/401).
(b) Cut the tie cords that secure the Personality module to the connector harness.
(c) Disconnect the electrical connector.
(d) Put a protective cover on the electrical connector. 3. Personality Module - Installation
A. Access
(1) Location Zones
211/212 Flight Compartment
B. References
(1) 24-22-00/201, Electrical Power - Control
C. Procedure
(1) Make sure these circuit breakers are open:
(a) P11-1 Overhead Circuit Breaker Panel
1) ACARS 2) PRINTER
(2) Install the Personality Module (AMM 20-10-01/401 ).
(a) Remove the protective cover from the electrical connector.
(b) Examine the electrical connectors for bent or broken pins, dirt, and damage.
FLIGHT DATA RECORDER SYSTEM - DESCRIPTION AND OPERATION 1. General (Fig. 1)
A. The system consists of a digital flight data acquisition unit (DFDAU) and a digital flight data recorder (SSFDR). It also consists of a flight recorder control panel, an accelerometer, and relay sensors.
B. All input signals are connected to the DFDAU. The DFDAU conditions the input
signals to produce a digital output which is sent to the SSFDR for recording. The recorded data is stored in a crash protected container inside the SSFDR.
C. The system is turned on automatically when the airplane is in flight, or on the
ground when an engine is running. The system may also be turned on manually or tested by means of a toggle switch on the flight recorder control panel.
D. The flight recorder system is monitored continuously by BITE during operation.
System failures are displayed on the flight recorder control panel and on the DFDAU and EICAS.
2. Component Details (Fig. 1)
A. Flight Recorder Control Panel (1) The flight recorder control panel (FRCP) provides system manual power control
and indicates system status. The control panel consists of a function (ON-NORM-TEST) switch, a relay and OFF annunciator.
(2) The function switch is normally set to the NORM position. In this position,
power to the system is automatically controlled through the system power relays. The ON position is used manually to turn on the DFDAU and the SSFDR. The TEST position is spring-loaded and is used to turn on power to the DFDAU and the SSFDR for testing purposes.
(3) The OFF light on the FRCP comes on when the SSFDR and/or the DFDAU fails, the
system is not turned on, or in the absence of electrical power.
B. Accelerometer (1) The flight recorder accelerometer is installed in the left wheel well.
(2) The accelerometer provides vertical, lateral, and longitudinal acceleration
signals to the DFDAU. The accelerometer measures vertical acceleration from -3G to +6G. It measures lateral and longitudinal accelerations from -1G to +1G.
C. Flight Recorder/System Relays.
(1) The flight recorder system relays include the left and right ENG START-TO-STOP relays and the SYS NO. 2 AIR/GND relay. The ENG START-TO-STOP relays provide AC power to the SSFDR when the corresponding engine is running. The SYS NO. 2 AIR/GND relay also provides AC power to the SSFDR when the airplane is airborne.
D. Flight Data Acquisition Unit (FDAU)
(1) The FDAU is a microprocessor controlled unit that sequentially receives specific data from various airplane systems and sensors. The acquired data is scaled and formatted into a digital data format. The FDAU outputs this data to the SSFDR for recording.
B757 AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
31-31-00 AIRPLANES WITH HONEYWELL SSFDR Page 2 AERODEC MOD 1044 APR 01/16
(a) A BITE and S/W PN positions switch - the toggle switch allows the operator to perform the BITE check of the FDAU and initiate the software configuration check. 1) Setting the switch to the BITE position will initiate the integrity
check of the FDAU. The FDAU, SSFDR, and the DMM or ACMS will light up in sequence. If no fault occurs then the status display will indicate NO FAULT. If a fault does occur, then the appropriate LED fault indicator will remain illuminated and the status display will read FDAU ERROR or ACMS ERROR.
2) Setting the switch to the S/W PN position enables the FDAU to display
the software configuration and part number.
(b) LED fault indicators - There are three fault indicators on front of the FDAU. They are the FDAU, SSFDR and the DMM or ACMS. If a fault occurs, the appropriate LED indicator will illuminate to identify the culprit.
(c) ATE connector - the connector allows the operator to connect the test
equipment to the FDAU for testing and trouble shooting the FDAU.
E. Digital Flight Data Recorder (SSFDR) (1) The flight data recorder writes the data for the last 25 hours of airplane
operation. The data is stored in solid state memory. The solid state memory is in a crash-proof container in the flight data recorder.
(2) The SSFDR is installed on the voice and flight recorder rack E7. This rack is
located above the aft galley ceiling. The exterior of the SSFDR is painted bright orange and has reflective tape affixed to it to aid in its location in the event of an accident.
(3) The underwater locator beacon (ULB) aids in location of a submerged SSFDR by
sending out an acoustic signal when the unit is submerged in water.
(4) The ULB is contained in a cylindrical watertight case designed to withstand high impact shock and deep water immersion. It is mounted on the front panel of the SSFDR.
(5) The ULB is battery operated and is designed to operate for at least 30 days
when immersed. It will withstand water depths of 20,000 feet and has a maximum detection range of 2,000 to 4,000 yards.
3. Operation
A. Functional Description (1) Power Distribution and Control
(a) During normal operation, ac power is supplied to the flight recorder system through the left and right ENG START-TO-STOP relays. The relays are wired in parallel so that any one relay can provide power to the SSFDR.
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(b) The left and right ENG START-TO-STOP relays are actuated when the corresponding engine is first started. The engine ignition switches control the operation. At engine start, when an engine ignition switch is first turned on, the corresponding ENG START-TO-STOP relay (left or right) is energized. After the fuel control switch is set to RUN, it will cause the flight recorder control relay to remain energized after the ignition switch is selected to OFF. The relays remain energized until the fuel control switches are set to CUTOFF.
(c) The system No. 2 AIR/GND relay is also wired in parallel with the ENG
START-TO-STOP relays to provide power to the SSFDR. This relay de-energizes when the airplane becomes airborne, resulting in a contact closure that provides an additional means to maintain power to the SSFDR during flight.
(d) Manual power switching is accomplished with the ON-NORM-TEST switch on the
flight recorder control panel. During normal operation, the switch is set to NORM and power is controlled by the automatic switching network. When the switch is set to either ON or to the momentary TEST position, power is supplied to the system.
(e) The OFF light on the flight recorder control panel is a status indicator.
It is controlled by the status relay within the control panel. When the flight recorder system is powered and no faults exist, the status relay is energized and the OFF light is off. 28v dc from the SSFDR system status output and a ground from the FDAU BITE output energizes the relay. If power is interrupted or if a system fault occurs, the network opens, the status relay de-energizes and the OFF light comes on.
(2) Parameter Inputs
(a) The FDAU receives inputs from sensors and signals from other airplane systems. The inputs are grouped as analog, discrete, and ARINC 429 digital inputs.
(b) Accelerometer
1) The accelerometer receives 28-volt dc power from the DFDAU.
2) The unit consists of three independent accelerometers, one for each axis. Each accelerometer operates as a closed loop servo system that is responsive to linear acceleration along its sensitive axis. An applied acceleration results in a force on a seismic pendulum which disturbs the servos capacitive balanced bridge. As a result of this imbalance, the servo applies current to a torquer coil to return the pendulum to its original position. A sensing resistor in series with the torquer coil, provides a voltage that is proportional to the acceleration input. The voltage is then amplified and output to the FDAU.
(c) ARINC 429 DITS Inputs
1) The left and right engine EPR transmitters provide the EPR signals.
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2) The left or right EICAS computer, via the EICAS select switch provides control surface signals. These signals are: a) Thrust Reverser In-Transit and Deployed b) Left and Right Aileron posiiton c) Left and Right Elevator Position d) Left and Right Rudder Position
3) The left or right ADC provides altitude and airspeed signals.
4) The left or center EFIS symbol generator provides pitch and roll
attitude and magnetic heading signals.
5) The left IRU provides longitude and latitude signals.
(3) Flight Data Acquisition Unit Function (a) The FDAU receives 115v ac power from the FLIGHT RECORDER AC circuit
breaker. The FDAU contains a switching regulator power supply that generates the necessary internal voltages and provides excitation outputs as follows:
(b) The FDAU receives the flight parameters to be recorded. It processes and
formats the signals. It then transmits the date to the SSFDR for recording. Data acquisition, signal processing and output data streams are controlled by the central processing unit (CPU).
(c) The FDAU BITE continuously performs internal circuit checks as soon a
power is applied. A BITE detected fault is output in a status word to the SSFDR and stored in a non-volatile memory for access by shop test equipment. The stored fault data provides a history of intermittent faults as well as identifying current faults. Current faults are indicated by the fault indicator on the FDAU's front panel.
(4) SSFDR Functions
(a) The SSFDR receives 115V ac power from the FLIGHT RECORDER AC circuit breaker through either the manual or automatic switching network. The SSFDR contains a regulated power supply that generates the necessary operating voltages.
(b) Under normal operation the FLT DATA REC message are not shown on the EICAS
status message. If the SSFDR malfunctions this will cause a discrete signal to be sent to the EICAS to generate the FLT DATA REC status message (Ref 31-41-00).
(5) Underwater Locator Beacon
(a) The underwater locator beacon is powered by a self contained battery. The ULB is activated when its water switch is immersed in water. The water switch is part of a low-current trigger circuit that turns on the oscillator circuit. The oscillator output drives a transducer that is mechanically coupled to the units case, radiating 37 kHz acoustic energy into the surrounding water. It sends out acoustic rf pulses when it is immersed in water up to 20,000 feet. It has a detection range of 2,000 to 4,000 yards.
(6) System Self Test
(a) A system self-test may be performed by momentarily setting the function switch on the control panel to the TEST position. The OFF light will extinguish if no fault is
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FLIGHT DATA RECORDER SYSTEM - ADJUSTMENT/TEST 1. General
A. This procedure has these tasks.
(1) An operational test of the flight data recorder system. (2) A system test of the flight data recorder system.
TASK 31-31-00-715-001-003 2. Flight Data Recorder System - Operational Test
A. General
(1) The operational test makes sure the switches for the manual and automatic power sources operate correctly. A BITE test is also included in this operational test. No test equipment is necessary.
B. References
(1) AMM 24-22-00/201, Electrical Power Control (2) AMM 31-31-01/401, Flight Data Recorder (3) AMM 31-31-03/401, Digital Flight Data Acquisition Unit (4) AMM 32-09-02/201, Air/Ground Relays (5) FIM 31-31-00/101, Fig. 104
C. Prepare for the Test
S 865-002-003
(1) Supply electrical power (AMM 24-22-00/201).
S 865-003-003 (2) Make sure these circuit breakers are closed:
(a) On the overhead equipment panel P11:
1) 11J2, EICAS CMPTR LEFT 2) 11J3, EICAS UPPER IND 3) 11J7, FLIGHT RECORDER AC 4) 11J8, FLIGHT RECORDER DC 5) 11J29, EICAS CMPTR RIGHT 6) 11J30, EICAS LOWER IND 7) 11J31, EICAS DISPLAY SW 8) 11S15, AIR/GND SYS 1 9) 11S19, AIR/GND SYS 2
S 865-004-003
(3) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) On the miscellaneous equipment panel P6: 1) 6E1, FUEL VALVES L SPAR 2) 6E2, FUEL VALVES R SPAR
(b) On the overhead equipment panel P11:
1) 11D19, ENGINE START CONT LEFT 2) 11D20, ENGINE START CONT RIGHT
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S 715-026-003 (11) At the pilots overhead panel, set the right engine start switch on the engine
start/RAT control panel to the GND position. (a) Make sure the OFF light on the FRCP is off.
S 715-027-003
(12) Set the right engine start switch to the AUTO position. (a) Make sure the OFF light on the FRCP comes on.
S 865-028-003
(13) Open this circuit breaker and attach a DO-NOT-CLOSE tag: (a) On the P6 panel:
1) 6C2, FUEL COND CONT R
(b) Make sure the OFF light on the FRCP goes off.
S 865-029-003 (14) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) On the P11 panel: 1) 11D20, ENGINE START CONT RIGHT
(b) Make sure the OFF light on the FRCP comes on.
G. BITE Test
S 745-342-003
(1) Do the steps that follow: (a) Set the FRCP function switch to the ON position.
1) Make sure the OFF light on the FRCP go off.
(b) At the main equipment rack, set the BITE S/W PN switch on the DFDAU to the BITE position then release. 1) On the DFDAU make sure the eight charater display segments and the all
BITE LED's come on then go off.
2) Make sure the DFDAU display shows NO FAULT.
(c) Set the function switch on the FRCP to the NORM position. 1) Make sure the OFF light comes on.
H. EICAS Message Test
S 865-032-003
(1) Open these circuit breakers and attach DO-NOT-CLOSE tags: (a) On the P11 panel:
1) 11K9, LEFT ENGINE OIL PRESS 2) 11K35, RIGHT ENGINE OIL PRESS
S 865-033-003
(2) Make sure these circuit breakers are closed: (a) On the P11 panel:
1) 11D19, ENGINE START CONT LEFT 2) 11D20, ENGINE START CONT RIGHT
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S 865-034-003 (3) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) On the P6 panel: 1) 6C1, FUEL COND CONT L 2) 6C2, FUEL COND CONT R
S 865-035-003
(4) Set the function switch on the FRCP to the ON position.
S 865-036-003 (5) Push the ECS MSG and AUTO EVENT switch on the EICAS MAINT panel on the right
side panel, P61.
S 865-037-003 (6) Push the ERASE switch on the EICAS MAINT panel for 1 second.
S 865-038-003
(7) Set the L and R FUEL CONT switches on the P10 panel to the RUN position and wait a minimum of 4 minutes.
S 715-039-003
(8) Set the COMPUTER switch on the EICAS DISPLAY select panel to the L position. (a) Make sure these EICAS messages, FLT DATA REC and FLT DATA ACQ, do not show
on the bottom display.
S 715-040-003 (9) Set the COMPUTER switch on the EICAS DISPLAY select panel to the R position.
(a) Make sure these EICAS message, FLT DATA REC and FLT DATA ACQ, do not show on the bottom display.
S 865-041-003
(10) Open these circuit breakers and attach DO-NOT-CLOSE tags: (a) On the P11 panel:
1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC
S 025-042-003
(11) Remove the flight data recorder (FDR) (AMM 31-31-01/401).
NOTE: Wait a minimum of 60 seconds before you do the next step.
S 865-043-003 (12) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) On the P11 panel: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC
S 715-044-003
(13) Set the COMPUTER switch on the EICAS DISPLAY select panel to the L position. (a) Make sure the EICAS message, FLT DATA REC, shows on the bottom display.
(b) Make sure the EICAS message, FLT DATA AQC, does not show on the bottom
display.
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S 715-045-003 (14) Set the COMPUTER switch on the EICAS DISPLAY select panel to the R position.
(a) Make sure the EICAS message, FLT DATA REC, shows on the bottom display.
(b) Make sure the EICAS message, FLT DATA AQC, does not show on the bottom display.
S 865-046-003
(15) Open this circuit breaker and attach the DO-NOT-CLOSE tag: (a) On the P11 panel:
1) 11J7, FLIGHT RECORDER AC
S 025-047-003 (16) Remove the DFDAU (AMM 31-31-03/401).
S 865-048-003
(17) Remove the DO-NOT-CLOSE tag and close this circuit breaker: (a) On the P11 panel:
1) 11J7, FLIGHT RECORDER AC
S 715-049-003 (18) Make sure the EICAS message, FLT DATA AQC, shows on the bottom display.
S 715-050-003
(19) Make sure the EICAS message, FLT DATA REC, does not show on the bottom display.
S 715-051-003
(20) Set the COMPUTER switch on the EICAS DISPLAY select panel to the L position. (a) Make sure the EICAS message, FLT DATA AQC, shows on the bottom display.
(b) Make sure the EICAS message, FLT DATA REC, does not show on the bottom
display.
S 015-052-003 (21) Open these circuit breakers and attach the DO-NOT-CLOSE tags:
(a) On the P11 panel: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDED DC
S 425-053-003
(22) Install the FDR (AMM 31-31-01/401).
S 425-054-003 (23) Install the DFDAU (AMM 31-31-03/401).
S 865-055-003
(24) Remove the DO-NOT-CLOSE tags and close these circuit breakers: (a) On the P11 panel:
1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDED DC
(b) Return the L and R FUEL CONT SWITCHES to the CUTOFF position.
(c) Set the FRCP to the NORM position.
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S 865-056-003 (25) Remove the DO-NOT CLOSE tags and close these circuit breakers:
(a) On the P11 panel: 1) 11D7, ENGINES STBY IGNITION LEFT 1 2) 11D8, ENGINES STBY IGNITION LEFT 2 3) 11D9, ENGINES STBY IGNITION RIGHT 1 4) 11D10, ENGINES STBY IGNITION RIGHT 2 5) 11K9, LEFT ENGINE OIL PRESS 6) 11K35, RIGHT ENGINE OIL PRESS 7) 11L1, LEFT ENGINE IGN 1 8) 11L28, RIGHT ENGINE IGN 1
S 865-057-003
(26) Remove the DO-NOT-CLOSE tags and close these circuit breakers: (a) On the P6 panel:
1) 6E1, FUEL VALVES L SPAR 2) 6E2, FUEL VALVES R SPAR
TASK 31-31-00-705-058-003 3. Flight Data Recorder System - System Test
A. General (1) The system test does a test of the input parameters that are connected to the
flight data recorder. (2) Test equipment is necessary to do this task. (3) These tasks use the word SUBFRAME 0, 5, or 6 to make a selection of a
parameter. Some portable testers or on board test equipment do not have a switch position for SUBFRAME 0, 5, or 6. On these test sets, make a selection of SUBFRAMES as follow:
For SUBFRAME 0, use SUBFRAME 1, 2, 3, and 4. For SUBFRAME 5, use SUBFRAME 1 and 3. For SUBFRAME 6, use SUBFRAME 2 and 4.
B. Equipment
(1) Portable Tester - Teledyne P/N 2229738-1 Teledyne Controls 12333 West Olympic Boulevard West Los Angeles, CA 90064
(2) A31007-59 Adapter Cable - Tester (3) 964-0446-001 Hand Held Download Unit (HHDLU)
27914 AlliedSignal Inc., DBA AlliedSignal Aerospace 2100 Northwest 62nd Street Fort Lauderdale, FL 33309 (a) AIRPLANES WITH FDR P/N 980-4700-042;
The HHDLU must have mod 1 completed. (4) 704-2567-001 Adapter Cable - Tester (5) Multi-Purpose AIDS Display Units - AACO Inc.
FAA-0032-001 AACO Inc. 5011 Barton Place Seattle, WA 98118
(6) EGA-0005-001, Adapter Cable - MADU
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ATC600A Set - Test, ATC Transponder / DME, RAMP (alternative) IFR Systems Inc. 10200 West York St. Wichita, KS 67215-8935
C. References
(1) AMM 22-10-00/501, Autopilot/Flight Control System (2) AMM 22-32-00/501, Thrust Management System (3) AMM 22-21-00/501, YAW Damper System (4) AMM 22-41-00/501, Maintenance Control Display Panel (5) AMM 23-11-00/501, HF Communications System (6) AMM 23-12-00/501, VHF Communications System (7) AMM 24-22-00/201, Electrical Power - Control (8) AMM 27-32-00/501, Stall Warning System (9) AMM 27-41-00/501, Horizontal Stabilizer Trim Control System (10) AMM 27-51-00/501, Trailing Edge Flap System (11) AMM 27-81-00/501, Leading Edge Slat System (12) AMM 29-11-00/201, Main Hydraulic Systems (13) AMM 31-25-00/501, Clocks (14) AMM 31-41-00/501, Engine Indicating and Crew Altering System (15) AMM 32-09-02/201, Air/Ground Relays (16) AMM 34-12-00/501, Air Data Computing System (17) AMM 34-21-00/201, Inertial Reference System (18) AMM 34-21-00/501, Inertial Reference System (19) AMM 34-22-00/501, Flight Instrument System (20) AMM 34-26-00/501, Air Data Inertial Reference System (21) AMM 34-31-00/501, Instrument Landing System (22) AMM 34-33-00/501, Radio Altimeter System (23) AMM 34-46-00/501, Ground Proximity Warning System (GPWS) (24) AMM 34-51-00/501, VOR Navigation System (25) AMM 34-55-00/501, Distance Measurement Equipment System (26) AMM 34-61-00/501, Flight Management Computer System
D. Access
(1) Location Zone
212 Flight Compartment, Right
E. Prepare for the Test
S 215-396-003 (1) Do this task: DFDAU Software Configuration Check (AMM 31-31-03/201).
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S 865-059-003 (2) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) On the overhead equipment panel P11: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC
S 865-060-003
(3) If you use test equipment other than the hand-held download unit (HHDLU), install the tester to the test connector at the right side panel, P61.
S 865-061-003
(4) If you use the hand-held download unit (HHDLU), attach the HHDLU to the test connector at the front side of the flight data recorder.
NOTE: To get access to the FDR, open the lower ceiling panel No. 1 above the
aft galley (AMM 25-22-02/401). The HHDLU can only be connected to the AlliedSignal flight data recorder (FDR).
S 865-062-003
(5) Remove the DO-NOT-CLOSE tags and close these circuit breakers: (a) On the P11 panel:
1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC 3) 11S1, MISC SYS AIDS SENSOR
S 865-063-003
(6) Supply electrical power (AMM 24-22-00/201).
S 865-064-003 (7) With the Data Signal Display Unit (DSDU), set the control switches on the
tester as follows: (a) Set the power switch to the ON position. (b) Set the INPUT switch to the ARINC INPUT DATA position. (c) Set the SYNC switch to the SYNC B position. (d) Set the DATA PARAMETER/DOCUMENTARY switch to the DATA PARAMETER position. (e) Set the OCTAL DISPLAY switch to the 12 BIT position. (f) Set the SUBFRAME and WORD as specified.
S 865-065-003
(8) With the Teledyne tester (P/N 2222786), set the switches on the tester as follows: (a) Set the POWER switch to the ON position. (b) Set the READOUT switch to the ACTF DATA position. (c) Set the UPDATE switch to the AUTO position. (d) Set the DFDAU/DFDR DATA SELECTOR switch to the DFDAU position. (e) Set the DATA switch to the 12 BIT position.
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S 715-199-003 (1) Make sure the yaw damper system operates correctly (AMM 22-21-00/501).
S 865-200-003 WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE
THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(2) Supply hydraulic power (AMM 29-11-00/201).
S 715-201-003
(3) Make sure the IRS operates correctly (AMM 34-21-00/501).
S 865-202-003 (4) Make sure the IRUs are aligned (AMM 34-21-00/201).
S 715-203-003
(5) Make sure the left and right yaw dampers are not engaged.
S 735-204-003 (6) On the tester, set the SUBFRAME to 0 and the WORD to 120.
(a) Make sure the BIT (DISCRETE) 2 shows a 0. (b) Make sure the BIT (DISCRETE) 1 shows a 0.
S 865-205-003
(7) Push the left yaw damper switch on the P5 panel to the ON position. (a) Make sure the BIT (DISCRETE) 2 shows a 1.
S 865-206-003
(8) Push the left yaw damper switch on the P5 panel to disengage the left yaw damper.
S 865-207-003
(9) Push the right yaw damper switch on the P5 panel to the ON position. (a) Make sure the BIT (DISCRETE) 1 shows a 1.
S 865-208-003
(10) Push the right yaw damper switch on the P5 panel to disengage the right yaw damper.
X. VHF Omnidirectional Range (VOR) Data Bus Test
S 715-209-003
(1) Make sure the VOR navigation system operates correctly (AMM 34-51-00/501).
S 865-210-003 (2) Set a frequency of 110.00 MHZ on the left VOR control panel.
S 735-211-003
(3) On the tester, set the SUBFRAME to 4 and the WORD to 222. (a) Make sure the tester display shows 4000 or 4001.
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S 865-212-003 (4) Set a frequency of 109.60 MHZ on the right VOR control panel.
S 735-213-003
(5) On the tester, set the SUBFRAME 2. (a) Make sure the tester display shows 2260 or 2261.
Y. Master Warning Test
S 865-214-003
(1) Make sure these circuit breakers are closed: (a) On the P11 panel:
1) 11A31, IND LTS TEST 2) 11A34, IND LTS 3 3) 11F4, GND PROX CMPTR
S 865-215-003
(2) On the tester, set the SUBFRAME to 0 and the WORD to 134.
S 735-216-003 (3) Momentarily set the test switch on the miscellaneous test panel to the GND
PROX position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.
S 735-217-003
(4) Push the MASTER WARNING light switch. (a) Make sure the BIT (DISCRETE) 2 shows a 1.
Z. Brake Pressure Test
S 715-218-003
(1) Make sure you put chocks on the wheels.
S 865-219-003
WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(2) Pressurize the right hydraulic system and reservoir (AMM 29-11-00/201).
S 715-220-003
(3) Make sure the engine indicating and crew alerting system (EICAS) operates correctly (AMM 31-41-00/501).
S 865-221-003
(4) Push the ELEC/HYD switch on the EICAS MAINT panel on the right side panel, P61.
S 715-222-003
(5) Make sure the parking brake is released.
S 865-223-003 (6) On the tester, set the SUBFRAME to 0 and the WORD to 187.
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S 735-262-003 (3) On the captain's control wheel, set the trim switch to the down position.
(a) On the tester display, make sure the BIT(DISCRETE) 2 shows a 1.
S 865-263-003 (4) Release the trim switch on the control wheel.
(a) Make sure the BIT (DISCRETE) 2 shows a 0.
S 735-264-003 (5) On the captain's control wheel, set the trim switch to the up position.
(a) On the tester display, make sure the BIT (DISCRETE) 1 shows a 1.
S 865-265-003 (6) Release the trim switch on the control wheel.
(a) Make sure the BIT (DISCRETE) 1 shows a 0.
AO. Automatic/Manual Electrical Pitch Trim Test
S 865-266-003 (1) Make sure the horzontal stabilizer trim control system operates correctly (AMM
27-41-00/501).
S 865-267-003 (2) On the tester, set the SUBFRAME to 0 and the WORD 46.
S 865-268-003
(3) On the control wheel, set the control wheel trim switch to the NOSE DOWN position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.
S 735-269-003
(4) Release the control wheel trim switch. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 1.
S 865-417-003
(5) On the tester, set the WORD to 41.
S 735-271-003 (6) On the control wheel, set the control wheel trim switch to the NOSE UP
position. (a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.
S 735-272-003
(7) Release the control wheel trim switch. (a) On the tester display, make sure the BIT (DISCRETET) 2 shows a 1.
AP. Flap Alternate Test
S 715-273-003
(1) Make sure the trailing edge flap operates correctly (AMM 27-51-00/501).
S 865-274-003 (2) On the P3-1 panel, push the T.E. FLAP arm switch to the armed position.
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S 735-275-003 (3) On the tester, set the SUBFRAME to 0 and the WORD to 106.
(a) Make sure the BIT (DISCRETE) 2 shows a 1.
S 735-276-003 (4) On the P3-1 panel, push the TE FLAP arm switch to the disarmed position.
(a) On the tester display, make sure the BIT (DISCRETE) 2 shows a 0.
AQ. Slat Alternate Test
S 865-277-003 (1) On the P3-1 panel, set the LE flap arm switch to the armed position.
S 735-278-003
(2) On the tester, set the SUBFRAME to 0 and the WORD to 106. (a) Make sure the BIT (DISCRETE) 1 shows a 1.
S 735-279-003
(3) Set the LE flap switch to the disarmed position. (a) On the tester display, make sure the BIT (DISCRETE) 1 shows a 0.
AR. Flap Handle Position Test
S 865-280-003
(1) Make sure the flap handle operates correctly (AMM 27-51-00/501).
S 865-281-003 (2) Make sure the flap handle is set at the 0 (UP) position.
S 735-282-003
(3) On the tester, set the SUBFRAME to 0 and the WORD to 107. (a) Make sure the tester display shows between 0000 and 2211.
S 735-283-003
(4) Set the flap handle to 15. (a) Make sure the tester display shows between 4426 and 5156.
S 865-284-003
(5) Set the flap handle back to the normal position.
AS. Leading Edge Slat Position Test
S 865-285-003 (1) Make sure the leading edge slat system operates correctly (AMM 27-81-00/501).
S 865-286-003
WARNING: KEEP PERSONS AND EQUIPMENT CLEAR OF THE FLIGHT CONTROL SURFACES, THE
THRUST REVERSERS, AND THE LANDING GEAR. THESE COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(2) Pressurize the left hydraulic system and reservoir (AMM 29-11-00/201).
S 865-287-003
(3) On the tester, set the SUBFRAME to 0 and the WORD to 44.
B757 AIRCRAFT MAINTENANCE MANUAL
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FLIGHT DATA RECORDER – MAINTENANCE PRACTICES 1. General
A. Use the applicable copy recorder to make a copy of the flight data recorder (FDR) data.
B. The FDR is installed in the voice and flight recorder rack, E7.
TASK 31-31-01-912-322
2. Make a Copy of the Flight Data with a Sundstrand Held Download Unit
A. General
(1) This task uses a hand held download unit (HHDLU) to make a copy of the flight data from a flight data recorder that records on solid state.
(2) You can use the HHDLU to make a copy of the flight data without the removal of
the solid state flight data recorder (FDR) from the airplane. A different procedure to access the flight data is to remove the FDR from the airplane (AMM 31-31-01/401). The flight data is then removed from the FDR.
(3) The ATE connector is on the front of the FDR.
B. Equipment
(1) 964-0446-001 Unit - Hand Held Download
97896 Honeywell International Inc. 15001 NE 36TH ST. P.O. Box 97001 Redmond, WA 98052-5317
(a) AIRPLANES WITH FDR P/N 980-4700-042;
The HHDLU must have mod 1 completed.
C. References
(1) AMM 24-22-00/201, Electrical Power - Control (2) AMM 25-22-02/401, Lower Ceiling Panel
D. Access
(1) Location Zone
253 Area Above Passenger Cable Ceiling, LH
E. Prepare to Make a Copy of the Flight Data from the FDR
S 862-224
(1) Supply electrical power (AMM 24-22-00/201).
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S 862-183 (2) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) On the overhead equipment panel, P11:
1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC
S 012-233
(3) To get access to the FDR, lower the ceiling panel No. 1 above the aft galley (AMM 25-22-02/401).
S 422-226
(4) Connect the connector of the HHDLU cable to the FDR ATE connector.
S 422-227 (5) Install the removable media into the HHDLU.
S 862-184
(6) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) On the P11 panel: 1) 11J7, FLIGHT RECORDER AC 2) 11J8, FLIGHT RECORDER DC
S 862-185
(7) At the P61 panel, set the ON-NORM-TEST switch on the flight recorder control panel (FRCP) to the ON position.
S 862-186
(8) Push the power switch, installed adjacent to the HHDLU's RS-422 port.
NOTE: When power is first applied to the HHDLU, the HHDLU display will not be on. After approxiamtely 30 seconds. The HHDLU display will show the main menu.
(a) Make sure the HHDLU display shows DNLD in the main menu.
F. Procedure
S 912-187
(1) Push the DNLD key.
(a) Make sure the DOWNLOAD MENU shows on the display.
NOTE: The maximum quantity of flight data the HHDLU can make a copy of is 27.2 hrs. If file DOWNLOAD01.DLU already exists on the removable media, the HHDLU will change the filename until a filename that is not used is found. To change the time or filename, push the TIME or FILE key.
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(a) If the HHDLU display shows DISK FULL, do these steps:
1) Push a key. 2) Make sure the DELETE FILE menu shows on the display. 3) Use the NEXT or PREV key to move up and down the filenames.
4) Push the DEL key to make a selection of the file to be erased.
a) Make sure the CONFIRM DELETE menu shows on the display.
5) Push the YES key to erase the file.
6) Erase files until sufficient memory is available to make a copy of the
flight data.
NOTE: After each file is erased, the HHDLU makes sure the HHDLU has sufficient memory space. If there is sufficient memory, the HHDLU will start to make a copy.
7) Make sure the HHDLU display shows REC BLKS and XFER BLKS.
NOTE: REC BLKS is the number of blocks the HHDLU will move to the
removable media. XFER BLKS is the number of blocks the HHDLU will move from the FDR. The REC BLKS and XFER BLKS fields will change during the copy procedure.
(b) After the copy procedure is completed, push a key to show the main menu.
G. Put the Airplane to Its Usual Condition
S 862-267
(1) On the HHDLU, push the red power switch to remove the power.
S 022-266 (2) Remove the media from the HHDLU.
S 862-229
(3) At the P61 panel, set the FRCP to the NORM position.
S 862-230 (4) Disconnect the interface cable from the FDR.
S 862-231
(5) Put the cover on the FDR ATE connector.
S 862-232 (6) Remove electrical power if it is not necessary (AMM 24-22-00/201).
B757 AIRCRAFT MAINTENANCE MANUAL
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QUICK ACCESS RECORDER (MINI) – MAINTENANCE PRACTICES 1. General A. This procedure has this task: 1) The return to service test of the mini Quick Access Recorder (QAR). 2. Return to Service Test A. Test Equipment and Material
Reference Description 802-0208 RSU II Kit or functionally equivalent computer with USB port. 700-0179 miniQAR MKII HS USB I/F Software (included with 805-0005) 605-0177 Portable Test Interface (PTI) Cable 805-0005 miniQAR MKII, HS USB I/F KIT Includes PTI cable (605-0177)
and software (700-0179) B. Test Setup
1) Connect PTI cable P/N 605-0177 to the UUT DB9 connector.
NOTE: Do not Connect the USB connector of the PTI cable P/N 605-0177.
C. Procedures
1) Turn-on the PC or RSU II and allow it to boot.
2) If the RSU Menu is displayed, select File, Exit to Windows (refer to the RSU II Operations Manual, Part Number 900-0208 – included in the RSU II Kit.)
3) On the Windows toolbar, select Start, Programs, Avionica, and MiniQAR Support
Util.
4) Connect the USB connector of the PTI cable P/N 605-0177 to the USB Port of the PC or RSU II.
5) Make sure that the BIT LED of the Unit Under Test is illuminated.
6) Select “Tools”.
7) A “Return to service” prompt appears. Select “Yes”
8) A message “Return To Service In-Progress Please Wait” will be displayed.
9) The “Please Wait” will be replaced by a Results screen. Make sure all results
indicate PASSED.
10) Select “Continue”.
11) Verify that the miniQAR LED is blinking.
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DATA PRINTER - DESCRIPTION AND OPERATION 1. General
A. The Data Printer is a general purpose airborne message, thermal line printer designed specifically for commercial aircraft.
B. The Data Printer contains a power supply, stepper motor, controller module, print drive
module, selector light module, and stationary thermal printer head to produce prints.
C. Data Printer meets the specifications of ARINC 740 to include the following capabilities:
• Interfaces with up to 12 ARINC 429 subsystems using prioritized polling • Variable print formats - 40, 64, 80, 80 sideways • Up to 80 characters per line and 7 lines per inch • Multiple print characters sets available (32K byte font memory) • Supports paper width of 4.375 inches, 100 feet per roll • Print rate of 120 40-character lines per minute
D. Data Printer receives power from the left 115v ac bus. The system circuit breaker is on the
(1) The Data Printer is a single Line Replaceable Unit (LRU) designed to fit standard flight deck instrument rails.
(2) All Data Printer processing and control is performed by a single plug in circuit board,
the controller module. The controller contains a 32K byte EPROM in which the operational software and character fonts are individually partitioned. Print messages are buffered in two RAMs, which provide data protection from power interrupts by retaining data for up to two minutes upon power interruption. Fault diagnostic is provided by a single digit hexadecimal display, viewed when the paper access panel is open.
(3) The printer drive module contains all the circuitry for interfacing the print head
mechanism as well as the high current drivers for the print head and stepper motor.
(4) The stepper motor supplies the mechanical drive to advance the paper during printing operations or paper feeding operations.
(5) The sensor light module is a reflective object sensor which deactivates the print head
when there is no paper left on the spindle, preventing print head damage.
(6) Data Printer uses thermal printer paper (non-perforated) rolls that are 4.375 inches wide with a maximum diameter of 2.1 inches.
B. Operation
(1) Data Printer is off when 115v ac left bus power is removed.
(2) Message Printing:
(a) Print message priority is determined by port number allocation, port #1 has the highest priority. Print message polling is defined by ARING 740.
(b) When a message has finished printing, the Data Printer will automatically advance
A. This procedure contains the task to replace the paper roll in the Data Printer.
B. Data Printer uses thermal printer paper (non-perforated) rolls that are 4.375 inches wide with a maximum diameter of 2.1 inches.
C. The Data Printer is installed on the P8 Aft Electronic Control Panel.
2. Data Printer - Paper Roll Replacement
A. Access
(1) Location Zones
211/212 Flight Compartment
B. Procedure
(1) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) P11-1 Overhead Circuit Breaker: 1) PRINTER
(2) Paper Roll Replacement (Figure 1):
(a) On the face of the Data Printer, turn the thumbscrew counterclockwise to release the
front panel.
(b) Open the front panel to the 180° position.
(c) Release the hinged paper roll spindle by pushing to the right and pulling straight out to the full 90° position. Remove the empty paper roll.
(d) Load new paper roll onto the spindle with the end of the paper facing towards the
printer.
(e) Close the spindle with the paper roll and lock into place by pushing to the right.
(f) Thread the end of the paper through the guide (drag) bar as indicated by the arrows until end of paper extends under the finger bar and rest on the platen roller. Continue to thread the paper out of the paper cutter slot at the bottom of the front panel.
(g) Close the front panel and secure with the thumbscrew.
(3) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) P11-1 Overhead Circuit Breaker:
1) PRINTER
(4) Depress the Data Printer SLEW switch. Ensure the paper feeds though the print head
A. There are two tasks in this procedure. The first task is the operational test of the Data Printer. The second is the system test of the Data Printer.
B. The operational test is a self-test of the Data Printer.
C. The system test contains the operational test and checks the interface between the Data
Printer and ACARS. 2. Data Printer Operational Test
A. References
(1) 24-22-00/201, Electrical Power - Control
B. Access
(1) Location Zones
211/212 Flight Compartment
C. Prepare for the Operational Test
(1) Supply electrical power (AMM 24-22-00/201 ).
(2) Make sure these circuit breakers are closed:
(a) P11-1 Overhead Circuit Breaker Panel:
1) ACARS 2) PRINTER
D. Procedure
(1) Data Printer Self-Test:
(a) On the front panel of the Data Printer, depress the TEST button.
(b) The Data Printer outputs a graphical test pattern (printer fonts) and no fault code
messages.
E. Put the Airplane back to the Initial Condition
(1) Remove electrical power (AMM 24-22-00/201) 3. Data Printer System Test
A. References
(1) 24-22-00/201, Electrical Power - Control (2) 23-22-00/501, ACARS
A. There are two tasks in this procedure. The first task is the removal of Data Printer. The second task is the installation of the Data Printer. The installation task includes an operational test of the Data Printer.
B. The Data Printer is installed on the P8 Aft Electronic Control Panel.
2. Data Printer - Removal
A. Access
(1) Location Zones
211/212 Flight Compartment
B. Procedure
(1) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) P11-1 Overhead Circuit Breaker:
1) PRINTER
(2) Remove the Data Printer:
a) Loosen the four quarter-turn fasteners that attach the Data Print to the panel.
b) Lift the Data Printer to get access to the electrical connector.
c) Disconnect the electrical connector.
d) Put a protective cover on the electrical connector. 3. Data Printer - Installation
A. References
(1) 24-22-00/201, Electrical Power - Control
B. Access
(1) Location Zones
211/212 Flight Compartment
C. Procedure
(1) Make sure these circuit breakers are open:
(a) P11-1 Overhead Circuit Breaker Panel
1) PRINTER
(2) Install the Data Printer:
(a) Remove the protective cover from the electrical connector.
(b) Examine the electrical connector for bent or broken pins, dirt, and damage.
ELECTRONIC FLIGHT INSTRUMENT SYSTEM - ADJUSTMENT/TEST 1. General
A. This procedure has two tasks, to carry out a left and Right EFIS Test, and a Center EFIS Symbol Generator Test.
B. Any other test associated with the Electronic Flight Instrument System in
accordance with 34-22-00 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.
2. Left and Right EFIS Test A. Procedure
(1) Carry out the Left and Right EFIS Test in accordance with 34-22-00 Page Block 501.
(2) Make sure that the Hex Codes displayed on the EADIs are as follows:
UPPER CODE MIDDLE CODE LOWER CODE
00101F4 801C008 E080000
3. Center EFIS Symbol Generator Test A. Procedure
(1) Carry out the Center EFIS Symbol Generator Test in accordance with 34-22-00 Page Block 501.
(2) Make sure that the Hex Codes displayed on the EADI is as follows:
GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST 1. General
A. This procedure has three tasks:
(1) To carry out a Level 1 Self Test of the Enhanced Ground Proximity Warning System.
(2) To carry out a Level 2 Self Test of the Enhanced Ground Proximity Warning
System. (3) To carry out a Level 3 Self Test of the Enhanced Ground Proximity Warning
System.
B. Any other test associated with the Ground Proximity Warning System in accordance with 34-46-00 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.
2. Level 1 Self Test A. Procedure
(1) Carry out the Level 1 Self Test in accordance with 34-46-00 Page Block 501.
(2) Make sure that the following Altitude Callouts are enunciated over the
AIR TRAFFIC CONTROL (ATC) SYSTEM - ADJUSTMENT/TEST 1. General
A. This procedure has two tasks:
(1) To carry out a system test of the Left Mode S ATC Transponder System (2) To carry out a system test of the Right Mode S ATC Transponder System
B. Any other test associated with the Air Traffic Control System in accordance
with 34-53-00 Page Block 501 of the associated manual, are not affected by the AeroDEC modification listed below, and can therefore be accomplished as instructed.
2. Left Mode S ATC Transponder System A. Procedure
(1) Carry out a system test of the Left Mode S ATC Transponder System in accordance with 34-53-00 Page Block 501.
(2) Make sure that the Mode S ATC Transponder Address Code is as follows:
AIRCRAFT REGISTRATION
SERIAL NUMBER HEXADECIMAL
CODE OCTAL CODE
OO-TFA 25622 44D0C1 21150301
3. Right Mode S ATC Transponder System A. Procedure
(1) Carry out a system test of the Right Mode S ATC Transponder System in accordance with 34-53-00 Page Block 501.
(2) Make sure that the Mode S ATC Transponder Address Code is as follows:
(5) Install the gel gasket, making sure it is aligned with the screw holes, and gently bring the coaxial cable through the hole in the middle of the gasket.
(6) Apply a layer of the BMS 3-27 (preferred) or BMS 3-38 (alternate) corrosion inhibiting
compound on the threads and shank of the antenna screws.
(7) Install the GPS antenna.
(a) Connect the electrical connector to the antenna.
(b) Apply a large quantity of Dow Corning 4 grease, D00254, to the outside coaxial connector, and at the exterior connector/antenna interface.
(c) Put the antenna into its position on the airplane.
(d) Install three of the bolts that hold the antenna.
NOTE: For GPS antenna connectors with hex nuts, make sure the bolts are tightened
to 8 to 12 in-lbs. For the coaxial connector that does not have hex nuts, these bolts are installed manually. Do not use power or pneumatic tools to install these bolts.
(8) Do a check of the resistance between the antenna and the airplane skin as follows:
(a) Connect the ohmmeter between the base of the antenna and the airplane skin.
NOTE: Get access to the base of the antenna through the hole for the last screw.
1) Make sure the measured resistance is 0.025 ohms or less.
(9) Install the last screw that holds the antenna.
(10) Remove the unwanted BMS 3-27 corrosion inhibiting compound from around the head of each
screw with the BMS 11-7 solvent (AMM 20-10-22/701).
(11) Apply the aerodynamic seal as follows (AMM 51-31-01/201):
(a) Apply the BMS 5-95 sealant around the antenna where it touches the airplane skin.
NOTE: Make sure no air bubbles are in the sealant. Use a sufficient quantity of the sealant to make the surface smooth.
(b) Make an aerodynamic fillet seal with the fillet smoothing spatula.
(c) Remove all the unwanted BMS 5-95 sealant from the area around the antenna.
(d) Fill the screw holes with the BMS 5-95 sealant.
NOTE: Make the sealant smooth in relation to the antenna surface.
F. GPS Antenna Installation Test
(1) Supply electrical power (AMM 24-22-00/201).
(2) Remove the DO-NOT-CLOSE tags on the overhead circuit breaker panel and close this
circuit breakers:
(a) C9002, GPS
(3) Move the airplane to a position where the GPS antennas have a clear view of the GPS satellites.
(4) Set the FMC source select switch to the NORMAL position.