mms-34436-1 r2 e2maintenance manual supplement mms-34436-1 r2 dual gps sensor installation boeing...

SUPPLEMENT 34‐58‐00 DUAL GPS INSTALLATION

BOEING MMS‐34436‐1 R2 Page: TITLE

MAINTENANCE MANUAL SUPPLEMENT

MMS-34436-1 R2

DUAL GPS SENSOR INSTALLATION

BOEING 737-300/400/500

STC TCCA SA11-92 EASA 10043626 FAA ST03273NY

This document contains recommended maintenance instructions for the Dual GPS Sensor system installed in accordance with Master Document List MDL-34436-2 Rev 2 or a later approved revision. This document supplements the information in the BOEING 737-300/400/500 Aircraft Maintenance Manual in the sections contained herein. For additional information regarding the maintenance of the subject aircraft, consult the basic Aircraft Maintenance Manual and other approved Maintenance Manual Supplements.


BOEING MMS‐34436‐1 R2 Page: LOR

LOG OF REVISIONS

REV DATE DESCRIPTION PAGES

AFFECTED APPROVED

R0 MAY-25/2019 INITIAL RELEASE ALL

R1 NOV-25/2019

- EGPWS added as affected system

- A/C not fitted with Fault panel

4 & 5

R2 JUN-25/2020 Complete Re-issue ALL


BOEING MMS‐34436‐1 R2 Page: INTRO

SUPPLEMENTAL MAINTENANCE INFORMATION CORPORATION LOGIC AIR INC. 91 Gaston-Dumoulin, Blainville (Québec) J7C 6B4 CANADA Technical Publications and Information The information contained herein shall not be reproduced or disclosed in whole or in part without the written authorization of Corporation Logic Air Inc. Distribution: Tel: 579-637-3077 | Fax 579-637-3099 |Email [email protected] Att: Director of Maintenance

Modification of an aircraft and issuance of a new or amended Type Certificate (TC) Data Sheet or a Supplemental Type Certificate obligates the aircraft operator to include the maintenance information contained herein, in the operator’s Aircraft Maintenance Manual and the operator’s Scheduled Aircraft Maintenance Program as specified. It is not the intention of this document to supersede any information in the aircraft manuals, except in those areas listed herein. The information in this document is presented in ATA-100 page numbering format; however, minor deviations may be encountered.


BOEING MMS‐34436‐1 R2 Page: EFF‐1

1. LIST OF EFFECTIVE PAGES CHAPTER-SECTION

PAGE

EFFECTIVE DATE

34-58-00 - Cover Page (Title) TITLE Re-Release Jun-25/20 34-58-00 - Log of Revisions LOR Re-Release Jun-25/20 34-58-00 - Introduction INTRO Re-Release Jun-25/20 34-58-00 - Effectivity EFF-1 Re-Release Jun-25/20 EFF-2 Re-Release Jun-25/20 34-58-00 - Table of Contents TOC-1 Re-Release Jun-25/20 TOC-2 Re-Release Jun-25/20 34-58-00 - Airworthiness Limitations LIM-1 Re-Release Jun-25/20 34-58-00 - Description/Operation 1 Re-Release Jun-25/20 2 Re-Release Jun-25/20 3 Re-Release Jun-25/20 4 Re-Release Jun-25/20 5 Re-Release Jun-25/20 6 Re-Release Jun-25/20 7 Re-Release Jun-25/20 8 Re-Release Jun-25/20 9 Re-Release Jun-25/20 10 Re-Release Jun-25/20 11 Re-Release Jun-25/20 12 Re-Release Jun-25/20 13 Re-Release Jun-25/20 34-58-00 - Fault Isolation 101 Re-Release Jun-25/20 102 Re-Release Jun-25/20 103 Re-Release Jun-25/20 104 Re-Release Jun-25/20 105 Re-Release Jun-25/20 106 Re-Release Jun-25/20 107 Re-Release Jun-25/20 108 Re-Release Jun-25/20 109 Re-Release Jun-25/20 110 Re-Release Jun-25/20


BOEING MMS‐34436‐1 R2 Page: EFF‐2

CHAPTER-SECTION

PAGE

EFFECTIVE DATE

34-58-00 - Maintenance Practices 201 Re-Release Jun-25/20 202 Re-Release Jun-25/20 203 Re-Release Jun-25/20 204 Re-Release Jun-25/20 Re-Release Jun-25/20 34-58-00 - Removal and Installation 401 Re-Release Jun-25/20 402 Re-Release Jun-25/20 403 Re-Release Jun-25/20 404 Re-Release Jun-25/20 405 Re-Release Jun-25/20 406 Re-Release Jun-25/20 407 Re-Release Jun-25/20 408 Re-Release Jun-25/20 409 Re-Release Jun-25/20 410 Re-Release Jun-25/20 Re-Release Jun-25/20 34-58-00 - Adjustment / Test 501 Re-Release Jun-25/20 502 Re-Release Jun-25/20 503 Re-Release Jun-25/20 504 Re-Release Jun-25/20 505 Re-Release Jun-25/20 506 Re-Release Jun-25/20 507 Re-Release Jun-25/20 508 Re-Release Jun-25/20 34-58-00 – Time Limits / Maintence Checks 601 Re-Release Jun-25/20


BOEING MMS‐34436‐1 R2 Page: TOC‐1

GLOBAL POSITIONING SYSTEM – TABLE OF CONTENTS

SUBJECT

CHAPTER – SECTION

PAGE

AIRWORTHINESS LIMITATIONS

34-58-00

AIRWORTHINESS LIMITATIONS LIM-1 DESCRIPTION AND OPERATION

34-58-00

Purpose 1 Abbreviations and Acronyms 1, 2 General 3 GPS Sensor Units 3 Power Interfaces 4 Aircraft Personality Data 4 Antennas, Adapters and Output Buses 4 Fault Indications 5, 6 Figure 1 – GPS Sensor / Antenna 7 Figure-2 Block Diagram (GPS Fault O/HEAD) 8 Figure-3A GPS Fault O/HEAD Configuration 9 Figure-3B M/C GPS Fault O/HEAD 10 Figure-4 Block Diagram (GPS Fault IRS) 11 Figure-5A GPS Fault IRS Configuration 12 Figure-5B M/C GPS Fault IRS 13 FAULT ISOLATION 34-58-00

Component Identification 101 Troubleshooting diagram 108


BOEING MMS‐34436‐1 R2 Page: TOC‐2

SUBJECT

CHAPTER – SECTION

PAGE

MAINTENANCE PRACTICES 34-58-00

System De-activation 201 System Activation 203 Re-lamping 204 REMOVAL AND INSTALLATION

34-58-00

GPS Sensor Removal 402 GPS Sensor Installation 403 GPS Antenna Removal 404 GPS Antenna Installation 406 GPS Fault Indicator Panel (O/HEAD) Removal 407 GPS Fault Indicator Panel (O/HEAD) Installation 407 ADJUSTMENT/TEST

Operational Test of GPS 501 System Test of GPS 503 Fault Indication Test 506 TIME LIMITS / MAINTENANCE CHECKS Time Limits / Maintence Checks 601 APPENDIX A

Customer IPC Supplement IPC-34280-1-(---) APPENDIX B

Customer WDM Supplement IPC-34280-1-(---)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: LIM 1

GLOBAL POSITIONING SYSTEM - AIRWORTHINESS LIMITATIONS

For TCCA The Airworthiness Limitations section is approved by the Minister and specifies maintenance required by any applicable airworthiness or operating rule unless an alternative program has been approved by the Minister. For FAA The Airworthiness Limitations section is FAA-approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations, unless an alternative program has been FAA approved. 1. LIMITATIONS

No airworthiness limitations are introduced by this modification.


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 1

GLOBAL POSITIONING SYSTEM – DESCRIPTION AND OPERATION

1. Purpose The Global Positioning System (GPS) uses navigation satellites to supply airplane position to airplane systems and to the flight crew. 2. Abbreviations and Acronyms

ADIRU - Air Data Inertial Reference Unit AMM - Aircraft Maintenance Manual Annc - Annunciator APD – Aircraft Personality Data ARINC - Aircraft Radio Incorporated CDU - Control Display Unit (FMC) (also MCDU or ANCDU) CMC - Esterline CMC Electronics (GPS Sensor OEM) DADC - Digital Air Data Computer DC - Direct Current DO - Design Organization DU - Display Unit (EFIS) EASA - European Aviation Safety Agency EGNOS - European Geostationary Navigation Overlay Services (Europe) FAA - Federal Aviation Administration FAR - Federal Aviation Regulation FMC - Flight Management Computer FMS – Flight Management System F/O - First Officer FS – Fuselage Station GAGAN - GEO Augmentation Navigation (India) GLSSU - GPS/SBAS Landing System Sensor Unit GNSSU - Global Navigation System Sensor Unit GPS - Global Positioning System Inop. – Inoperative I/O - Input / Output IRS - Inertial Reference System L – Left LBL - Left Buttock Line LNAV – Lateral Navigation LSK – Line Select key (FMS CDU)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 2


2. Abbreviations and Acronyms (Cont.)

MMR - Multi Mode Receiver MSAS - Multifunction Satellite-based Augmentation System (Japan) MSU - Mode Select Unit (IRS) NCD - No Computed Data PNL – Panel PP - Program Pin PPOS - Present Position R – Right RBL - Right Buttock Line RCVR – Receiver RF - Radio Frequency RNAV – Area Navigation RNP - Required Navigation Performance RTCA – Radio Technical Commission for Aeronautics SAT - Satellite (space vehicle) SDI – Source Designation Indicator SDS – System Description Section (AMM) SEL – Select STA – Station STC - Supplemental Type Certificate SBAS - Space Based Augmentation System SV - Space Vehicle (Satellite) TCCA - Transport Canada Civil Aviation TSO – Technical Standard Order UTC - Universal Time (Coordinated) V – Volts WAAS - Wide Area Augmentation System (FAA) WL - Water Line


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 3

GLOBAL POSITIONING SYSTEM – DESCRIPTION AND OPERATION 3. General NOTE: Aircraft Maintenance Manual (AMM) Chapter 34-58 may contain information regarding GPS navigation and the use of GPS signals on the aircraft. (Applicable to Boeing GPS provisioned (either at delivery or per S/B) aircraft) The dual Global Positioning System (GPS) uses navigation satellites to supply airplane position to airplane systems and to the flight crew via 3 separate ARINC 429 data buses. Left and right (L and R) sensors are installed. Each sensor utilizes a dedicated GPS antenna and computes:

Latitude Longitude Time Horizontal figure of merit Horizontal integrity limit.

This information is then provided to the aircraft’s FMC (s). Refer to Figure 1 for the GPS sensor and antenna locations. GPS Sensor Units There are 2 possible GPS sensor unit configurations. The system can be either equipped with dual CMA-3024 GNSSUs or dual CMA-5024 GLSSUs. Both units are compliant with RTCA/DO-229D, TSO-C145c Class Beta-3. The CMA-5024 GLSSU is additionally compliant with TSO-C146c Class Delta-4 (required for SLS (LPV) operation). NOTE: Intermix between GPS Sensor (CMA-3024 / CMA-5024) is not permitted. The GPS system operates both within and outside the SBAS coverage area. Its compliance to RTCA/DO229D ensures interoperability with the signals-in-space provided by the FAA Wide Area Augmentation System (WAAS) and other international SBAS service providers like the European Geostationary Navigation Overlay Service (EGNOS), Japan's Multi-functional Transport Satellite (MTSAT) Satellite-based Augmentation System (MSAS), and India’s GPS and GEO Augmented Navigation (GAGAN).


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 4

GLOBAL POSITIONING SYSTEM – DESCRIPTION AND OPERATION Power Interface Refer to Figure 2 - System Block Diagram. L system shown; R system is similar. Each GPS sensor is powered by 28 VDC. The left GPS sensor is powered from the aircraft Standby Bus and the right GPS sensor is powered by the aircraft DC Bus 2. Power to the sensors is not switched and they are active as long as their respective buses are energized. Aircraft Personality Data Each GPS sensor contains an electronic Aircraft Personality Data (APD) File. This APD File is read once at each unit power-up. The APD File contains a set of up to 16 different APD Configurations, each specific to a particular aircraft and installation. NOTE: Use of an APD File (P/N) that does not match the approved configuration invalidates the approval and may seriously affect the safe operation of systems dependent on GPS data. Antennas / Output Buses Each GPS sensor receives ARINC 429 data from its On-Side and OFF-Side IRU and DADC system. This data enables optimal system initialization and assists operation during periods of low satellite coverage. Each GPS sensor uses a dedicated active GPS antenna. Antenna structure, either installed on aircraft delivery or separate STC, must be inspected at existing intervals. NOTE: Use of a GPS Antenna that does not match the approved configuration invalidates the approval and may seriously affect the safe operation of systems dependent on GPS data. The following systems receive GPS sensor data:

FMC IRU IRS Master Caution Unit (when Boeing Provisioned) ATC Transponder (when ADS-B provisioned) EGPWS (When EGPWS system not fitted with dedicated GPS antenna) Heads Up Display (If fitted)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 5

GLOBAL POSITIONING SYSTEM – DESCRIPTION AND OPERATION Fault Indications There are two possible GPS Fault Indicator configuration: - O/Head Configuration - IRS Configuration O/Head Configuration GPS Fault Indicator panel, located in the pilot overhead panel P5 (aft) (Figure-3A), receives signals from each GPS Sensor’s internal data bus monitoring circuits. The fault light is integrated in the normal airplane Bright / Dim / Test circuit (P1-3). Additionally, each installed FMCS also monitors each GPS Sensor’s data (on-side and off-side GPS data) (Figure-2) for validity. A GPS-L (or -R) message will appear in the FMS CDU (scratch pad) when the FMC no longer receives valid information from the GPS system.

Fault Light – GPS Fault Indicator Panel Installed Condition: A single GPS Sensor fault will cause:

(1) A GPS-L (/-R) message which will appear in the FMS CDU (scratch pad). (2) The FMS annunciator to illuminate in each pilot station’s A/P Status Annunciator.

Action: Pressing the CLR key on either CDU will:

a. Erase the message in both CDU scratch pad. b. Extinguish both FMS annunciators.

Condition: A dual GPS Sensor fault will cause:

(1) The System Master Caution Annunciator-R “OVERHEAD” to illuminate (Figure-3B). (2) Both Master Caution Light to come ON (Figure-3B). (3) The GPS FAULT Light to come ON (Figure-3A).

Action: Pressing either Master Caution Light will:

a. Extinguish both Master Caution Lights. b. Extinguish the System Master Caution Annunciator “OVERHEAD”.

NOTE: The GPS Fault Indicator will remain ON (illuminated) until at least one GPS sensor become valid.


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 6

GLOBAL POSITIONING SYSTEM – DESCRIPTION AND OPERATION Fault Indications – (Cont.) GPS Fault Indicator is integrated in the IRS MSU panel, located in the pilot overhead panel P5 (aft) (Figure-5A). The IRS Master Caution unit (P10) receives signals from each GPS Sensor’s and monitor the validity (Figure-4). The fault light is integrated in the normal airplane Bright / Dim / Test circuit (P1-3). Additionally, each installed FMCS also monitors each GPS Sensor’s data (on-side and off-side GPS data) (Figure-4) for validity. A GPS-L (or -R) message will appear in the FMS CDU (scratch pad) when the FMC no longer receives valid information from the GPS system.

Fault Light - IRS Indicator Panel Installed t Condition: A single GPS Sensor fault will cause:

(1) A GPS-L (/-R) message which will appear in the FMS CDU (scratch pad). (2) The FMS annunciator to illuminate in each pilot station’s A/P Status Annunciator.

Action: Pressing the CLR key on either CDU will:

a. Erase the message in both CDU scratch pads. b. Extinguish both FMS annunciators.

Action: Pressing the System Master Caution Annunciator-L (Re-Call) will:

a. System Master Caution Annunciator-L “IRS” will illuminate (Figure-5B). b. Both Master Caution Light will illuminate (Figure-5B). c. The GPS FAULT Light will illuminate (Figure-5A).

NOTE: Indicating a single GPS sensor as failed.

Condition: A single GPS Sensor fault will cause:

(1) The System Master Caution Annunciator-L “IRS” to illuminate (Figure-5B). (2) Both Master Caution Lights illuminate (Figure-5B). (3) The GPS FAULT Light illuminates (Figure-5A).

Action: Pressing either Master Caution Light will:

a. Extinguish both Master Caution Lights. b. Extinguish the System Master Caution Annunciator-L IRS.

NOTE: The GPS Fault Indicator will remain ON (illuminated) until at least one GPS

sensor becomes valid.


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 7


Figure 1 – GPS Sensor / Antenna Location


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 8


Figure 2 – System Block Diagram (GPS Fault O/Head Config)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 9


Figure 3A – GPS Fault (O/HEAD Configuration)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 10


Figure 3B – M/C GPS Fault (O/HEAD Configuration)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 11


Figure 4 – System Block Diagram (GPS Fault IRS Config)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 12


Figure 5A – GPS Fault (IRS Configuration)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 13


Figure 5B – GPS Fault (IRS Configuration)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 101

GLOBAL POSITIONING SYSTEM – FAULT ISOLATION

COMPONENT FIG QTY ACCESS / AREA AMM REF GENERAL ARRANGEMENT 101 - - -

CIRCUIT BREAKER - GPS -L 102 1 Flight Deck - GPS-R 103 1 Flight Deck -

GPS SENSOR (-L/-R) 104 1 Main Cabin -R 34-58-00 GPS FAULT IND (O/HEAD) 105A 1 Flight Deck P5 Aft -

GPS FAULT IND (IRS) 105B Flight Deck P5 Aft 34-58-00 ANTENNA GPS (-L/-R) 106 1 Top Fuselage 34-58-00

- Fault Isolation-1 (O/HEAD) 107 - -

Fault Isolation-1 (IRS) - 34-58-00 Fault Isolation-2 108 - -

-

Figure 101 – General Arrangement


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 102


Figure 102 – GPS-L Circuit Breaker Location

(Alternate location possible within panel)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 103


Figure 103 – GPS-R Circuit Breaker Location

(Alternate location possible within panel)


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Figure 104 – GPS Sensor Location


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Figure 105A – GPS Fault (O/HEAD Configuration)


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Figure 105B – GPS Fault (IRS Configuration)


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Figure 106 – GPS Antenna


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 108


1. General

A. This procedure uses the GPS system test (P. 503) to carry out a check for failure in the GPS -L/-R system.

B. If this procedure does not correct the problem, use the installation wiring diagram as a reference to carry out a check of the airplane wiring.


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 109


Figure 107 – Fault Isolation Flow Diagram (GPS Fault O/HEAD)


BOEING 737‐300/400/500 MMS‐34436‐1 R2 Page: 110


Figure 108 – Fault Isolation Flow Diagram


BOEING MMS‐34436‐1 R2 Page: 201

GLOBAL POSITIONING SYSTEM – MAINTENANCE PRACTICES

1. General The modification has been reviewed per the guidance provided in FAA AC-25-27A. It has been determined that the design change does not necessitate a revision to the EWIS ICA that were required to be developed by §26.11(c).

A. This section contains these tasks:

(1) Global Positional System Deactivation.

(2) Global Positioning System Activation. (3) GPS Fault Indicator Panel Re-lamping (O/HEAD)

2. Global Positioning System Deactivation

A. General

(1) This procedure removes electrical power to the Global Positioning System.

B. Procedure

(1) Open these circuit breakers and install safety tags:

CAPT Electrical System Panel P18-2 (*) Row Col Number Name

A 4 C1236 GPS - L F/O Electrical System Panel P6-1 (*)

Row Col Number Name A 13 C1236 GPS - R

(*) Alternate location possible (within same panel)




3. Global Positioning System – Tryout NOTE: This tryout is to make sure that the GPS is in a zero-energy state.

(1) Make sure that these circuit breakers are open and are equipped with safety tags:

CAPT Electrical System Panel P18-2 (*)

Row Col Number Name A 4 C1236 GPS - L

F/O Electrical System Panel P6-1 (*)



(2) Do these steps at the FMS CDU:

(a) Navigate to POS REF page 2/3.

(b) Ensure GPS position not shown. NOTE: Wait at least 5 minutes to make sure the position does not show on the CDU.

---- END OF TASK----




4. Global Positioning System – Activation

A. General

(1) This procedure adds electrical power to the Global Positioning System.

B. Procedure (1) Remove these safety tags and close these circuit breakers:






(2) Perform GPS Operational Test per section 500.

---- END OF TASK ----




5. Global Positioning Fault Panel Re-lamping (O/HEAD Configuration)

A. General (1) This procedure replaces the Fault indicator lamps

B. Procedure (1) Using Lamp Capsule Removal Tool P/N 58T-101 (Eaton Corporation), insert grip vertical

capsule groove and gently pull capsule out.

(2) Replace lamp with P/N CM 6839. (3) Close capsule and push until capsule is seated correctly (snap sound). (4) Perform GPS Fault Indicator Panel Test per P. 504.




GLOBAL POSITIONING SYSTEM – REMOVAL AND INSTALLATION

General

A. This Procedure has the following tasks:

(1) GPS sensor removal.

(2) GPS sensor installation.

(3) GPS antenna removal.

(4) GPS antenna installation. (5) GPS Fault Indicator Panel removal (O/HEAD). (6) GPS Fault Indicator Panel installation (O/HEAD).

NOTE: Refer to applicable AMM section for GPS Fault IRS Configuration

B. Location (1) The GPS sensors are located in the aircraft cabin overhead area between STA 500A to STA

500C for -300 and -400 type aircraft and, STA 460 to STA 482A for -500 type aircraft. Reference Figure 401

(2) The GPS antennas are located on top of the forward fuselage. The exact antenna locations

are dependent on the installation configuration. Reference Figure 402

(3) The GPS Fault Indicator Panel is located in the flight deck area on the P5 Overhead Panel.

Reference Figure 403




1. GPS Sensor Removal (-L or -R)

A. Removal Procedure (1) Open these circuit breakers and install safety tags:






(2) Remove/retain cabin ceiling panels from STA 460 to STA 500C

(3) Remove electrical connector(s) and antenna coaxial connector from the GPS Sensor and

apply protective covers.

CAUTION!

DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTOR IN THE GPS SENSOR. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE GPS SENSOR

(4) While supporting the weight of the GPS Sensor, remove and retain the four (4) mounting

screws and washers.

(5) Carefully, remove the GPS Sensor.





Figure 401 – GPS Sensor Location




2. GPS Sensor Installation (-L or -R)

A. Installation Procedure

(1) Open these circuit breakers and install safety tags.





(2) While supporting its weight, position the GPS Sensor in place and install the four (4)

mounting screws and washers.

(3) Remove the protective covers from the electrical connector and antenna coaxial connector and connect to the GPS Sensor.

CAUTION!

DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTOR IN THE GPS SENSOR. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE GPS SENSOR

(4) Remove the safety tags and close these circuit breakers.



F/O Electrical System Panel P6-1 (*) Row Col Number Name

A 13 C1236 GPS - R (*) Alternate location possible (within same panel)

(5) Perform GPS operational test per section 500.





3. GPS Antenna Removal (-L or -R)

A. Removal Procedure.

(1) Open these circuit breakers and install safety tags.






(2) Refer to Boeing AMM 34-58-21-024-001 for Antenna removal.

CAUTION!

DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTOR IN THE GPS ANTENNA. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE GPS SENSOR





Figure 402 – GPS Antenna Location




4. GPS Antenna Installation

A. Installation Procedure

(1) Ensure these circuit breakers are opened and safety tags are installed.

CAPT Electrical System Panel P18-2 (*)Row Col Number Name

A 4 C1236 GPS – L F/O Electrical System Panel P6-1 (*)

Row Col Number Name A 13 C1236 GPS – R


(2) Refer to Boeing AMM 34-58-02 34-58-21-424-004 for GPS Antenna installation.

CAUTION!

DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTOR IN THE GPS ANTENNA. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE GPS SENSOR

(3) Remove the safety tags and close these circuit breakers:





(4) Perform GPS Operational Test per section 500.

----- END OF TASK ----



GLOBAL POSITIONING SYSTEM – REMOVAL AND INSTALLATION 5. GPS Fault Panel Removal

A. Removal Procedure

(1) Ensure these circuit breakers are opened and safety tags are installed:





(2) Release the 4 ¼ turn fasteners and gently pull out the indicator panel (See figure 402).

(3) Disconnect unit and install protective covers. 6. GPS Fault Panel Installation

A. Installation Procedure (1) Gain access to the flight deck and P5 overhead panel. (2) Remove protective covers and connect harness to unit. (3) Insert panel until flush with P5 and Secure the 4 ¼ turn fasteners. (4) Close these circuit breakers:




(5) Perform the system test per Section 500 of this manual.

---- END OF TASK----




Figure 403 – GPS Fault Indicator Panel (O/HEAD Configuration)




Figure 404 – GPS Fault Indicator Pane



GLOBAL POSITIONING SYSTEM – ADJUSTMENT / TEST

General

A. This procedure has these tasks:

(1) An operational test of the Global Positioning System. (2) A system test of the Global Positioning System. (3) GPS fault indication test.

NOTE: The aircraft must be moved to a position where the GPS antennas have a clear view of

the GPS satellites.




1. Global Positioning System – Operational Test

A. General (1) This task does a general GPS position check

B. Procedure

(1) Ensure these circuit breakers are closed:





(2) Move the aircraft to a position where the GPS antennas have a clear view of the GPS

satellites. To move the airplane, do this task: AMM TASK 09-11-00-580-801.

(3) Do these steps to access the GPS position coordinates from the FMS CDU:

(a) Push the INIT REF key on the CDU.

(b) Push the INDEX LSK on the CDU

(c) Push the POS LSK on the CDU.

(d) Navigate to page 2 by using the NEXT PAGE key on the CDU. (4) Make sure that the POS REF 2/3 page.

(a) Make sure the GPS-R position is shown on the line above RADIO.

(b) Make sure the GPS-L position is shown on the line above GPS-R position.

NOTE: As much as 10 minutes of time can be necessary for the position to show on the CDU.




Figure 501 – Sample GPS position on FMC CDU.

(5) Put the Airplane Back to its usual condition.

(6) Remove electrical power, if it is not necessary (AMM TASK 24-22-00-860-812).





2. Global Positioning System – System Test

A. General

(1) This procedure does a system test of the GPS.

(2) This procedure tests the validity of the GPS sensor output and fault indication.

B. System Test Procedure






(2) Move the aircraft to a position where the GPS antennas have a clear view of the GPS satellites. To move the airplane, do this task: AMM TASK 09-11-00-580-801.

(a) Verify that the FMS is operating normally. (34-62-00)

(b) Verify that both IRU’s are aligned and in NAV. (34-28-01/201)

(3) Do these steps to access the GPS position coordinates from the FMS CDU:


(b) Push the INDEX LSK on the CDU.

(c) Push the POS LSK on the CDU.

(d) Push the NEXT PAGE LSK on the CDU.




(4) Make sure that the POS REF 2/3 page.

(a) Make sure the GPS-R position is shown on the line above RADIO.

(b) Make sure the GPS-L position is shown on the line above GPS-R position.

NOTE: As much as 10 minutes of time can be necessary for the position to show on the CDU.

(5) Do these steps to access the sensor status page the FMC-L from the CDU:


(b) Push the INDEX LSK on the CDU.

(c) Push the MAINT LSK on the CDU.

(d) Push the FMCS LSK on the CDU.

(e) Push the FMC-L LSK on the CDU.

(f) Push the SENSOR LSK on the CDU.

(g) Verify that GPS is displayed below IRS and that: (a) GPS-L shows OK (b) GPS-R shows OK

(6) Repeat step (5) for FMC-R (if fitted).

(7) Put the Airplane Back to its usual condition.






3. Global Positioning System – Fault Indication Test

A. General

(1) This procedure does a test of the GPS Fault Indication Panel.

B. Test Procedure

(1) Energize aircraft electrical power. (AMM 24-22-00/201)






(3) Select Master Bright / Dim / Test switch (P1-3) to TEST and:

(a) Verify all flight deck annunciators operate normally (ref AMM 33-18-00).

(b) Verify that the GPS Fault Indicator (P5) illuminates. (4) Select Master Bright / Dim / Test switch (P1-3) to BRT and verify that:

(a) The GPS Fault Indicator (P5) is not illuminated.

(5) Move the aircraft to a position where the GPS antennas have a clear view of the GPS satellites. To move the airplane, do this task: AMM TASK 09-11-00-580-801.

(a) Verify that the FMS is operating normally. (34-62-00)




(3) Do these steps to access the sensor status page the FMC-L from the CDU:

(a) Push the INIT REF key on the CDU. (b) Push the INDEX LSK on the CDU. (c) Push the MAINT LSK on the CDU. (d) Push the FMCS LSK on the CDU. (e) Push the FMC-L LSK on the CDU. (f) Push the SENSOR LSK on the CDU. (h) Verify that GPS is displayed below IRS and that:

(a) GPS-L shows OK (b) GPS-R shows OK

(4) Open circuit breaker:


A 4 C1236 GPS - L (*) Alternate location possible (within same panel)

(5) Verify that:

(a) The GPS Fault Indicator (P5) is not illuminated. (b) The GPS-L status changes from OK to FAIL on the CDU.

(6) Open circuit breaker:

F/O Electrical System Panel P6-1 (*) Row Col Number Name

A 13 C1236 GPS - R





(7) Verify that:

(a) The GPS-R status changes from OK to FAIL on the CDU (b) The GPS Fault Indicator (P5) illuminates. (c) The two (2) master caution (M/C) lights illuminate. (d) The R M/C Annunciator OVERHEAD illuminates. (e) Push the Capt M/C light (Cancel) and verify that the OVERHEAD light extinguishes. (f) Verify that the GPS fault indicator (P5) is illuminated. (g) Push the R M/C annunciator and verify that the OVERHEAD light illuminates.

(8) Close these circuit Breakers:





(9) Verify that:

(a) The GPS Fault Indicator (P5) extinguishes. (b) R M/C annunciator OVERHEAD light extinguishes. (c) The GPS-L status changes from FAIL to TEST and to OK in the CDU.

(Allow 2 to 5 minutes) (d) The GPS-L status change from FAIL to TEST and to OK in the CDU.

(Allow 2 to 5 minutes)

(10) Secure aircraft from test.





GLOBAL POSITIONING SYSTEM - TIME LIMITS/MAINTENANCE CHECKS

1. General A. There are no scheduled maintenance or inspection introduced by this modification.

- The GPS system and associated components are categorized as CM (Condition Monitoring).

NOTE: This modification makes use of existing GPS antenna structure therefore, any existing limitation, inspection interval or procedure as specified under the GPS antenna structure introduction documentations remain unaffected and applicable.

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