SBAS LANDING SYSTEM (SLS)MAINTENANCE MANUAL SUPPLEMENT MMS-34436-5 R0 SBAS LANDING SYSTEM (SLS) BOEING 737-300/400/500 STC TCCA SA11-92 EASA 10043626 FAA ST03273NY This document contains

SBAS LANDING SYSTEM – LOG OF REVISONS

SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)

BOEING MMS-34436-5 R0 Page: TITLE

MAINTENANCE MANUAL SUPPLEMENT

MMS-34436-5 R0

SBAS LANDING SYSTEM (SLS)

BOEING 737-300/400/500

STC

TCCA SA11-92

EASA 10043626

FAA ST03273NY

This document contains recommended maintenance instructions for the Dual SBAS Landing

System installed in accordance with Modification Data List MDL-34436-5 Rev: 0 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

.

SBAS LANDING SYSTEM – LOG OF REVISONS


BOEING MMS-34436-5 R0 Page: LOR

REV DATE DESCRIPTION PAGES AFFECTED APPROVED

R0 JUN-28/2019 INITIAL RELEASE ALL

SBAS LANDING SYSTEM – INTRODUCTION


BOEING MMS-34436-5 R0 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.

mailto:[email protected]

SBAS LANDING SYSTEM – LIST OF EFFECTIVE PAGES


BOEING MMS-34436-5 R0 Page: EFF-1

CHAPTER-SECTION

PAGE

EFFECTIVE DATE

34-31-00 - Cover Page (Title) TITLE Initial Release 34-31-00 - Log of Revisions LOR Initial Release 34-31-00 - Introduction INTRO Initial Release 34-31-00 – List of Effective Pages EFF-1 Initial Release EFF-2 Initial Release EFF-3 Initial Release 34-31-00 - Table of Contents TOC-1 Initial Release TOC-2 Initial Release 34-31-00 - Airworthiness Limitations LIM-1 Initial Release 34-31-00 - Description/Operation 1 Initial Release 2 Initial Release 3 Initial Release 4 Initial Release 5 Initial Release 6 Initial Release 7 Initial Release 8 Initial Release 9 Initial Release 10 Initial Release 11 Initial Release 12 Initial Release 13 Initial Release 14 Initial Release 15 Initial Release 16 Initial Release 34-31-00 - Fault Isolation 105 Initial Release 102 Initial Release 103 Initial Release 104 Initial Release 105 Initial Release




CHAPTER-SECTION

PAGE

EFFECTIVE DATE

34-31-00 - Maintenance Practices 201 Initial Release 202 Initial Release 203 Initial Release 204 Initial Release 205 Initial Release 206 Initial Release 207 Initial Release 208 Initial Release 209 Initial Release 34-31-00 - Removal and Installation 401 Initial Release 402 Initial Release 403 Initial Release 404 Initial Release 405 Initial Release 406 Initial Release 407 Initial Release 408 Initial Release 409 Initial Release 410 Initial Release 411 Initial Release 412 Initial Release 413 Initial Release 414 Initial Release 415 Initial Release 416 Initial Release 417 Initial Release 418 Initial Release 419 Initial Release 420 Initial Release




CHAPTER-SECTION

PAGE

EFFECTIVE DATE

34-31-00 - Adjustment / Test 501 Initial Release 502 Initial Release 503 Initial Release 504 Initial Release 505 Initial Release 506 Initial Release 507 Initial Release 508 Initial Release 509 Initial Release 510 Initial Release 511 Initial Release 512 Initial Release 513 Initial Release 514 Initial Release 515 Initial Release 516 Initial Release 517 Initial Release 518 Initial Release 519 Initial Release 520 Initial Release 34-31-00 – Time Limits / Maintenance Checks 601 Initial Release

SBAS LANDING SYSTEM – TABLE OF CONTENTS


BOEING MMS-34436-5 R0 Page: TOC-1

SUBJECT

CHAPTER – SECTION

PAGE

AIRWORTHINESS LIMITATIONS

34-31-00

AIRWORTHINESS LIMITATIONS LIM-1 DESCRIPTION AND OPERATION

34-31-00

Purpose 1 List of Abbreviations 1 General 2 Description 7 Operation 12 100 - FAULT ISOLATION 34-31-00

General 101 Fault Isolation 102 200 - MAINTENANCE PRACTICES

34-31-00

SBAS Landing System De-activation 202 SBAS Landing System Activation 204 SLS Annunciator Panel Lamp Replacement 205 SLS Approach DB Loading 206

SBAS LANDING SYSTEM – TABLE OF CONTENTS


BOEING MMS-34436-5 R0 Page: TOC-2

SUBJECT

CHAPTER – SECTION

PAGE

400 - REMOVAL AND INSTALLATION

34-31-00

Removal of the GLSSU 402 Installation of the GLSSU 404 Removal of the LPV Adapter 406 Installation of the LPV Adapter 408 Removal of the SLS ACP 410 Installation of the SLS ACP 412 Removal of the RSU 414 Installation of the RSU 415 Removal of the SLS CP 417 Installation of the SLS CP 419 500 - ADJUSTMENT/TEST

34-31-00

Operational Test of SLS ACP Indicating 502 Operational Test of the SLS CP 504 Operational Test of GLSSU 507 SLS System Test 511 SLS System Synchronization Test 516 600 - TIME LIMIT / MAINTENANCE CHECKS General 601 Electrical Wiring Interconnection System

(EWIS) ICA 601

SBAS LANDING SYSTEM – AIRWORTHINESS LIMITATIONS


BOEING MMS-34436-5 R0 Page: LIM-1

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.

1.

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

1.1. No airworthiness limitations are introduced by this modification.

SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION


BOEING MMS-34436-5 R0 Page: 1

1. PURPOSE

1.1. This document contains the maintenance procedures for the DUAL SBAS LANDING SYSTEM

(SLS / LPV) functions installed in BOEING 737-300/400/500 in accordance with Logic Air

Modification Data List MDL-34436-5 Rev: 0 or later approved revision.

2. LIST OF ABBREVIATIONS

(1) A/D - Analog /Digital

(2) AMM - Aircraft Maintenance Manual

(3) AMMS - Aircraft Maintenance Manual Supplement

(4) APV - Approach with Vertical guidance

(5) ARINC - Aircraft Radio Incorporated (now just known as ARINC)

(6) CDU - Control Display Unit (include MCDU and/or ANCDU)

(7) CP - Control Panel

(8) DAA - Digital to Analog Adapter

(9) DME - Distance Measuring Equipment

(10) EASA - European Aviation Safety Agency

(11) EADI - Electronic Attitude Director Indicator

(12) EHSI - Electronic Horizontal Situation Indicator

(13) EGNOS - European Geostationary Navigation Overlay Service

(14) FAA - Federal Aviation Administration

(15) FAR - Federal Aviation Regulation

(16) FAS – Final Approach Fix

(17) FMC - Flight Management Computer

(18) FS - Fuselage Station

(19) GAGAN - GPS Aided Geo-Augmented Navigation

(20) GBAS - Ground Based Augmentation System

(21) GLONASS - Globalnaya Navigatsionnaya Sputnikovaya Sistema or Global Navigation

Satellite System

(22) GLSSU - GPS Landing System Sensor Unit

(23) GNSS - Global Navigation Satellite System

(24) GPS – Global Positioning System

(25) ILS - Instrument Landing System

(26) LAAS – Local Area Augmentation System




(27) LBL - Left Butt Line

(28) LP - Localizer Precision

(29) LPV - Localizer Precision with Vertical guidance

(30) LSK - Line Select Key

3. GENERAL

3.1. The SLS (LPV) system provide precision approach guidance (EFIS, F/D and A/P) solely based

on GPS signal where no ground aids (LOC, DME, GS, etc.) exist. Two identical system are

installed, SLS-L provide information to the Captain side and SLS-R provide information to the

F/O side.

Each system consists of CMC CMA-5024 GPS landing system sensor unit (GLSSU), CMC

CMA-5025 SLS control panel (SLS CP), Logic Air SLS annunciator control panel (SLS ACP),

Logic Air LPV Adapter units and a Logic Air dual channel Remote Switching Unit (RSU).

NOTE: GPS Sensor (GLSSU) and GPS antenna maintenance reference can be found in LGA

MMS-34346-1.

The SLS system provides localizer precision (LP) and localizer precision with vertical (LPV)

RNAV (GNSS) approach capability to runways contained in the GLSSU internal approach

database (FAS Database). The SLS output signal that are “ILS Look Alike” where:

- Lateral guidance is displayed identical to a localizer (LOC) signal.

- Vertical guidance is displayed identical to a glideslope (GS) signal.

- Distance to runways threshold is displayed identical to a DME (associated to an ILS).

NOTE: GPS Sensor (GLSSU) additional information:

In order to provide the enhanced accuracy required for Approach Procedures with Vertical

guidance (APV) operations, GPS Sensor receivers are “augmented” with advanced

technology.




3.2. In order to provide the enhanced accuracy required for Approach Procedures with Vertical

guidance (APV) operations, GPS Sensor receivers are “augmented” with advanced technology.

Two type of “augmentation” currently exist, Space Based augmentation System (SBAS) and

Ground Based Augmentation System (GBAS). GBAS promises greater accuracy to enable

CAT III operation however, it is not currently readily available.

NOTE: Refer to LGA MMS-34346-1 for additional information on various type of GPS signal

augmentation (depending on area).

The system described herein utilize the space base augmentation system hence the chosen

acronyms SLS for SBAS Landing System. Also, SBAS was developed because it is readily

available.

SBAS approaches are known as RNAV(GNSS) approaches in navigation charts and are

allocated unique 5 digit “channel” numbers in the range of 40000 to 99999 The installed system

is capable of two types of RNAV (GNSS) approaches, Localizer Precision (LP) and Localizer

Precision with Vertical guidance (LPV).

3.3. Two SLS control panels (SLS CP) are located in the flight deck on P9 (or P8) pilot stand,

depending on the system installation configuration. In addition to controlling the landing

system, the SLS control panels also relay system status information to users via messages

(see Figure 1).

3.4. Two LPV Adapters are located in the aircraft E&E bay. Their function is to:

(1) Convert GLSSU digital output signal digital to analog signal.

(2) Provide a mean to transfer (switch) from ILS / DME to SLS (LPV) / Distance.

3.5. A single (dual channel) Remote Switching Unit (RSU) is a unit located in the aircraft E&E bay

(under the E&E floor panel) (see Figure 2). The unit intercepts (transfer) VHF Navigation 2x5

tuning lines to provide 108.10 indication in the EHSI.

3.6. Two SLS Annunciator Control panels (SLS ACP) are installed, located in the flight deck, one on

each pilot instrument panel (P1 and P3). Each panel consist off two (2) indicator light and one

(1) push button / indicator light switch (see Fig. 3). The SLS ACP provide indication of level of

service available, system health (Fault Lt) and control function to replace ILS information with

SLS information.




Figure 1 – SLS CONTROL PANEL LOCATION




Figure 2 – LPV ADAPTER & RSU LOCATIONS




Figure 3 – SLS ACP LOCATION




4. DESCRIPTION

4.1. SLS Control Panel

Each SLS is controlled by the SLS Control Panel (SLS CP). The SLS CP mainly used to select

the active FAS database and approach (LPV) channel. It Has the following components:

(Ref Figure 4)

(1) Display that contain 2 lines of 8 alpha numerical character.

(2) Message Button & Message Annunciator.

The message “MSG” provides the capability to display active messages. The message

annunciator is a LED which illuminates either in white or in amber to indicate that one or

more messages are active. The color of the annunciator depends on the priority of the

active message.

(3) Item Selector Knob

The item selector knob provides the control functionality for navigation between screens

display and selection and entry of data. Turning the item selector knob allows for the

selection of an item from a list or for navigation between a series of screens. Pushing the

item selector knob allows for the entry, acceptance, or acknowledgement of data.

(4) Mode Selector Knob

The mode selector knob allows the operators to select the operational mode of the system

from the options “P” (Park), “ACT” (Active), “TUNE STBY” (Tune Standby), “BRT”

(Brightness Adjustment), “TST/SET” (Test / Set), and “M” (Maintenance).

(5) Active/Standby Swap Button

The active / standby swap button provides the capability to make the active approach the

standby approach and vice versa.

(6) Standby Tune Annunciator

The standby tune annunciator is a LED. It illuminates in amber when the mode selector

knob is in the TUNE STBY position to indicate that the information on the display does not

correspond to the currently active approach.

NOTE: The SLS CP, is capable of channeling both SBAS and GBAS approach channel

however, only the SBAS channels are utilized in this system installation.




Figure 4 – SLS Control Panel




4.2. LPV Adapters

The LPV Adapters are 2 MCU format. Their function is to:

(1) Convert digital (Arinc 429) lateral and vertical guidance information from the GLSSU into

analog signal.

(2) Convert digital (Arinc 429) runway threshold distance information from the GLSSU to Arinc

568 signal. (apply to aircraft with Arinc 568 DME only).

(3) Provide a mean to transfer (switch) from ILS / DME to SLS (LPV) / Distance to aircraft

system (DAA, SGU and FCC).

(Ref Figure 5)

4.3. Remote Switching Unit

A single (dual channel) Remote Switching Unit is a unit located in the aircraft E&E bay (under

the E&E floor panel) (see Figure 2). Each channel is identical and therefore interchangeable.

The RSU function is to:

(1) Intercept (transfer) VHF Navigation 2x5 tuning lines from the VHF Nav CP to the DAA.

When LPV is selected, this will provide a fixed 108.10 indication in the EHSI to provide the

pilot with a cue that LPV is selected and indicated.

(Ref Figure-5)

4.4. SLS Annunciator Control panels

Two SLS Annunciator Control panels (SLS ACP) are installed, located in the flight deck, one on

each pilot instrument panel (P1 and P3). Each panel consist off two (2) indicator lights and one

(1) push button / indicator light switch Their function is to:

(Ref Fig. 6).

(1) LP/LPV APP Indicator:

(a) Use to indicate the “Level of Service” available. Illuminates (green) to indicate that

LP/LPV approach is available.

(2) SBAS Fault Indicator:

(a) If the On-side GLSSU detects a fault that prevents it from operating normally, SBAS

fault indicator illuminates AMBER and flight crew must abort / discontinue LPV

approach.




(3) SBAS Control:

(a) If LP/LPV Approach is available, the flight crew selects LPV approach by moving the

SBAS pushbutton switch to latched position. This action triggers the transfer within the

LPV Adapter and RSU to replace normal ILS information with LPV.

The “ON” indication illuminate to confirm that all guidance / displayed signal (lateral /

vertical deviation, distance and 108.10 display) have transferred.

NOTE: Failure of the “ON” light to illuminate in the latched position indicates a fault in the

transfer circuit within the LPV Adapter or RSU. Flight crew must abort / discontinue LPV

approach and initiate go-around procedure if engaged in an LP/LPV landing.

4.5. Electrical Supply

(1) The SLS-L is supply from the 28V DC Standby Bus. System circuit is protected by the

following circuit breakers:

CAPT Electrical System Panel P18-1

Circuit Breaker Label Rating

SLS-L 3A

SLS-L D/A* 2A

LPV DLU** 1A

NOTE: (*) Alternate location possible (P18-2).

(**) Alternate location possible (P18-2). Ground operation only

(2) The SLS-R is supply from the 28V DC Bus 2. System circuit is protected by the following

circuit breakers.

F/O Electrical System Panel P6-1


SLS-R 3A

SLS-R D/A 2A




4.6. Aircraft Personality Data

Each GPS sensor contains an electronic Aircraft Personality Data (APD) File software. This

APD File can be further customized using program pins up-to 16 different configurations to

accommodate a particular aircraft installation. The APD selection is hardwired into the GLSSU

J3 connector. This APD File is read once at each unit power-up.

NOTE: APD File P/N found on unit data plate.

CAUTION!

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.




5. OPERATION

5.1. Normal SLS operation is described below:

NOTE: Description below is for Captain, for F/O substitute Capt for F/O, #1 for #2 and/or -L for -R.

(1) Verify that the level of service is available (LP/LPV light illuminate in SLS ACP-L).

(2) Using the SLS CP-L, enter the unique 5 digits LPV channel, verify / select the desired

runway identifier and approach.

(3) Verify that the selected channel is “Active”.

(4) Verify that the Capt EHSI mode select is in ILS or ILS EXP.

(5) On the SLS ACP-L, selecting the SBAS ON (P/Button latch in) causes:

(a) The transfer relay within the LPV Adapter-L to energize and replaces:

(i) The normal VHF Nav R/X LOC and G/S with GLSSU lateral and vertical signal.

NOTE: The GLSSU output Arinc 429 ILS data bus, this data bus is converted

to analog signal within the LPV adapter.

(ii) The normal DME-1 distance to station with GLSSU computed distance to

runway signal.

NOTE: The GLSSU output Arinc 429 Distance data bus, this data bus is

converted to Arinc 568 signal within the LPV adapter.

NOTE: For aircraft using Arinc 700 DME, the distance converter (429/568) is

not required and not active, only the transfer function (within the LPV Adapter)

from DME to GLSSU Distance is retained.

(b) The transfer relay within the RSU-L to energize and replaces:

(i) The normal 2x5 Tune lines from the VHF Nav CP-1 with a hard-wired

frequency value of 108.10 to the DAA.

NOTE: A discrete interlock check that all the relays within the LPV Adapter and

RSU have energized to cause the “ON” light to illuminate in the SLS ACP

P/Button indicator. The “ON” light not illuminating when the P/Button is in the

latched position indicates a fault in the interlock and SLS operation must be

discontinued.




(6) Normal operation as detailed in e) above will causes the EHSI to display:

(a) ILS-1

(b) 108.10

(c) Distance to runways (provided the selected channel is within 70 Kts of present

position).

NOTE: Distance displayed in EHSI should agree with runway selected distance in the

SLS CP in the Active sub menu.

(d) Lateral and Vertical scale are in view.

NOTE: The Lateral deviation will display direction of turn to the runway selected

depending on actual distance and geometry (aircraft position vs selected runway) the

deviation indication may appear.

(e) No flags are in view.

5.2. Synchronization

The APD software P/N, the designed selected APD files with the crosstalk bus (inter-GLSSU)

make-up synchronization. With synchronization enabled, the last entered LPV channel (in SLS

CP-L or -R) will set both GLSSU to that selection (LPV channel can not be different between

SLS-L and SLS-R).

5.3. SBAS Approach Database

(1) The equipment provide deviation relative to a selected final approach path. The desired

approach path is extracted from an SBAS Approach Database (or SLS NDB) which must

be loaded in each GLSSU on a 28-day cycle.

(2) The SLS NDB is loaded in each GLSSU via a download unit (DLU) connector located

inboard of P18 panel (Load Control Center L) using an Arinc 615-3 portable data loader

(PDL).

(Ref Figure-7 for a typical installation)

(3) The SBAS Approach Database (or SLS NDB) subscription is obtained from CMC.




Figure 5 – SLS-L Schematic




Figure 6 – SLS-ACP




Figure 7 – SLS LPV-DLU

SBAS LANDING SYSTEM – 100 - FAULT ISOLATION



1. GENERAL

1.1. The installed SBAS system provides instrument landing guidance during the Final Approach

Segment (FAS) during LP/LPV approach and acts as a dual GNSS sensor for the installed

FMC system.

Faults are normally indicated by system flags on the EADI, erroneous indications on the system

annunciators, an SBAS FAULT lamp or by fault messages that appear on the SLS Control

Panel.

It is assumed that all indicating lamp operate normally from the aircraft BRT/DIM/TEST circuit.

1.2. This section provides guidance for fault resolution for most common equipment and system

faults.

CAUTION!

Where a troubleshooting procedure prescribes “Swapping” units, ALWAYS place

the suspected faulty unit in a known serviceable unit position first.

Installing a known serviceable unit in a [position suspected fault may cause

damage to a serviceable unit.

1.3. The installed SBAS landing system output signal are similar to the ILS system. The LPV

Adapters provide the transfer between SLS and ILS therefore, knowing if a fault exists in SLS

only or SLS and ILS will help guide trouble shooting action.

NOTE: Because the signal from ILS and SLS are similar, the aircraft AMM troubleshooting

guidance are still applicable when a fault exists with the DFCS (F/D, A/P) and/or EFIS.

Serviceability of the ILS should be established as a first step.

1.4. SLS/ILS dynamic test (per Section 500 - 2.4) is to be conducted:

(1) After any SLS/ILS replacement.

(2) After any wiring repair.

(3) Whenever system performance is in doubt.




2. FAULT ISOLATION

2.1. Prepare for troubleshooting:

(1) Ensure all applicable circuit breakers on P6 and P18 are closed:

(a) VHF NAV VOR/ILS

(b) IRS

(c) EFIS

(d) DAA

(e) Flight Instruments

(f) Instrument Transfer

(g) GPS

(h) SLS

(i) SLS/DA

(2) Ensure that both SLS ACP “ON” P/Button are in the unlatched position (“ON” light off).

(3) Ensure that both IRS are aligned and in NAV per AMM 34-28-01/201.

(4) If installed, set the VHF NAV CP (P8) to the MANUAL mode.

(a) Set an ILS frequency (other then 108.10 or local ILS).

(5) Set the EFIS in CP (P8) in EXP VOR/ILS position.

NOTE: Verify that the EHSI lateral and vertical scale appear.

(6) Align/set the course on the DFCS MCP to current aircraft heading

2.2. Perform troubleshooting per table 34-31-00-1.




Table 34-31-00-1

# Trouble Probable Cause Action / Remedy

1 FMC indicates a GPS sensor

fault.

- Refer to MMS-34436-1

2 SLS ACP “ON” light fail to

illuminate when SBAS SEL

P/Button latch in.

Check the annunciator

bulbs for operation (P1-3

BRT/DIM/TEST switch)

Re-lamp as necessary

(Ref Sec 200 – 2.3))

Replace or swap to isolate

fault on-side LPV Adapter

Replace LPV Adapter

(Ref Sec 400 – 2.3 & 2.4)


fault on-side RSU

Replace RSU

(Ref Sec 400 – 2.7 & 2.8)

3 SLS ACP “ON” light fail to

illuminate when SBAS SEL

P/Button latch in.


fault on-side SLS ACP

Replace SLS ACP

(Ref Sec 400 – 2.5 & 2.6)

Inspect/verify aircraft wiring Repair per SWPM

4 EHSI does not display “108.10”

SBAS SEL P/Button latch in.

- Assumption: EHSI frequency

display normal P/Button is

unlatched.


fault on-side RSU

Replace RSU

(Ref Sec 400 – 2.7 & 2.8)



Replace SLS ACP

(Ref Sec 400 – 2.5 & 2.6)


5 EHSI does not display selected

VHF Nav CP ILS frequency

when SBAS SEL P/Button is

unlatch.

- Assumption: EHSI display

“108.10 when P/Button is

latched.


fault on-side RSU

Replace RSU

(Ref Sec 400 – 2.7 & 2.8)


fault on-side VHF NAV CP

Replace VHF NAV CP

(AMM 34-31-52)


6 EHSI does not display selected

VHF Nav CP ILS frequency

when SBAS SEL P/Button is

unlatch or 108.10 when

latched.


fault on-side RSU

Replace RSU

(Ref Sec 400 – 2.7 & 2.8)


fault on-side DAA

Replace DAA

(AMM 34-28-41)





Table 34-31-00-1 (Cont.)


7 SLS Distance is not displayed

on ESHI when SBAS SEL

P/Button latch in.

- Assumption: DME distance

display normally when

unlatched.



Replace LPV Adapter

(Ref Sec 400 – 2.3 & 2.4)


fault on-side GLSSU

Replace GLSSU

(Ref Sec 400 – 2.1 & 2.2)


8 SLS Distance is not displayed

on ESHI when SBAS SEL

P/Button latch in.

- Assumption: DME distance

display fault when unlatched.



Replace LPV Adapter

(Ref Sec 400 – 2.3 & 2.4)


fault on-side DAA

Replace DAA

(AMM 34-28-41)


9 Lateral vertical deviation not

displayed (or erroneous) and/or

lateral/vertical flag in view on

ESHI when SBAS SEL

P/Button latch in.

- Assumption: ILS display

normal when unlatched.



Replace LPV Adapter

(Ref Sec 400 – 2.3 & 2.4)



Replace SLS ACP

(Ref Sec 400 – 2.5 & 2.6)


10 Lateral vertical deviation not

displayed (or erroneous) and/or

lateral/vertical flag in view on

ESHI when SBAS SEL

P/Button latch in.

- Assumption: ILS display fault

when unlatched.



Replace LPV Adapter

(Ref Sec 400 – 2.3 & 2.4)


fault on-side EFIS SGU

Replace EFIS SGU

(AMM 34-22-41/201)


11 SLS Control panel is displaying

fault message

Refer to PAGEBLOCK

34-50-05/501

Consult the fault message

and replace components

as required.


12 SLS ACP FAULT light

illuminates


fault on-side GLSSU

Replace GLSSU

(Ref Sec 400 – 2.1 & 2.2)



Replace SLS ACP

(Ref Sec 400 – 2.5 & 2.6)





Table 34-31-00-1 (Cont)


13 SLS ACP LP/LPV light fail to

illuminate


fault on-side GLSSU

Replace GLSSU

(Ref Sec 400 – 2.1 & 2.2)



Replace SLS ACP

(Ref Sec 400 – 2.5 & 2.6)


14 SLS CP fail self test Replace or swap to isolate

fault on-side SLS CP

Replace SLS CP

(Ref Sec 400 – 2.9 &

2.10)


15 GLSSU fail self test Replace or swap to isolate

fault on-side GLSSU

Replace GLSSU

(Ref Sec 400 – 2.1 & 2.2)


SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES



1. GENERAL

1.1. This section contains these tasks:

(1) SBAS Landing System Deactivation.

(2) SBAS Landing System Activation.

(3) SLS Annunciator Panel Lamp Replacement.

(4) SLS Approach DB Loading.




2. MAINTENANCE PRACTICES

2.1. SBAS Landing System Deactivation

A. General

(1) This procedure removes electrical power to the SBAS Landing System.

(2) This procedure can be used to de-activate the SLS.

B. Procedure

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



SLS-L(*) 3A

SLS-L D/A(*) 2A

* NOTE: (*) Alternate location possible (P18-2).

(2) Open these circuit breakers and install safety locks.



SLS-R 3A

SLS-R D/A 2A

C. Try-out

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

(2) Verify that the SLS CP -L and -R displays are blank (de-energized).

(3) On the CAPT and F/O SLS ACP, select ON (P/Button latched) and verify that:

(a) The “ON” light does not illuminate.




(4) With Capt and F/O SLS ACP, still selected ON (P/Button latch), verify ILS per AMM

TASK 34-31-02-715-001.

(a) Ensure On-side ILS operates normally.

(5) With Capt and F/O SLS ACP, still selected ON (P/Button latch), verify DME per AMM

TASK 34-55-02-715-001.

(a) Ensure On-side DME operates normally.

(6) On the Capt and F/O SLS ACP, select OFF (P/Button unlatched).

(7) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.

--- END OF TASK ----




2.2. SBAS Landing System Activation

A. General

(1) This procedure restores electrical power to the SBAS Landing System.

(2) This procedure can be used to activate the SLS for operation.

B. Procedure

(1) Remove/discard safety locks and close these circuit breakers:



SLS-L(*) 3A

SLS-L D/A(*) 2A


(2) Remove/discard safety locks and close these circuit breakers.



SLS-R 3A

SLS-R D/A 2A

C. Try-out


(2) Verify that the SLS CP -L and -R displays are energized.

(3) Perform SLS System Test per Section 500 - 2.4.


---- END OF TASK ----




2.3. SLS ACP Lamp Replacement

A. General

(1) This procedure replaces the indicator lamp within the SLS ACP.

B. Procedure

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

indicator capsule groove and gently pull capsule out.

NOTE: Capsules are hinged to indicator.

(2) Replace defective lamp with new lamp P/N CM6839.

(3) Insert capsule into indicator and push forward until seated correctly (snap sound).

(4) Perform SLS ACP operational test.





2.4. SLS Approach Database Loading

A. General

(1) This procedure installs FAS approach database into each GLSSU.

B. Tooling

(1) An Arinc 615-3 portable data loader unit is required. List (but not limited to) of capable

unit:

(i) P/N 30100 / Mfg Demo System LLC.

(ii) P/N AE-615-MPDL / Mfg MBS Electronics System GmbH.

(iii) P/N 30100 / Mfg Teledyne Control.

(iv) P/N 11615-50 / Mfg Aero Instrument and Avionics.

C. Procedure


(2) Open these circuit breakers and install safety locks



AIRBORNE DATA

LOADER

3A

OR

FMC CMPTR (-L) 3A

(3) Verify that these circuit breakers are closed. CAPT Electrical System Panel P18-1


SLS-L (*) 3A

NOTE: (*) Alternate location possible (P18-2). F/O Electrical System Panel P6-1


SLS-R 3A




(4) Verify that the aircraft is on ground.

(5) On the DATA TRANSFER UNIT RECEPTACLE (P37):

(a) Remove dust cover. (b) Connect an Arinc 615-3 PDL cable to the unit receptacle. (c) Verify that the LOAD SELECT switch is in the center OFF position.

(6) Verify that these circuit breakers are closed: CAPT Electrical System Panel P18-2


AIRBORNE DATA

LOADER

3A

OR

FMC CMPTR (-L) 3A

(7) Portable Data Loader (PDL).

(a) Energize the PDL unit (refer to the PDL operating instruction). (b) Verify NO DISK message appear on the PDL. (c) On the DATA TRANSFER UNIT RECEPTACLE panel (P37):

(i) Move the LOAD SELECT switch to the LOAD-L position. (d) Insert a disk (containing the correct NDB cycle as obtain from CMC).

(i) Data transfer operation start automatically (as observed on the PDL display files count down).

(ii) Data transfer is completed when the LOAD COMPLETE or COMP message appear on the PDL display.

(iii) Eject NDB disk from PDL. (e) On the DATA TRANSFER UNIT RECEPTACLE panel (P37):

(i) Move the LOAD SELECT switch to the LOAD-R position. (f) Insert a disk (containing the correct NDB cycle as obtain from CMC).

(i) Data transfer operation start automatically (as observed on the PDL display files count down).

(ii) Data transfer is completed when the LOAD COMPLETE or COMP message appear on the PDL display.

(iii) Eject NDB disk from PDL. (g) On the DATA TRANSFER UNIT RECEPTACLE panel (P37).

(i) Move the LOAD SELECT switch to the LOFF position. (h) De-energize the PDL unit (refer to the PDL operating instruction).

(i) Dis-connect the PDL cable and stow PDL. (ii) R-install dust cover.




(8) Do this task: Verify that the loaded SLS NDB cycle number is available on the SLS-L

and -R system. (a) Set the Mode Selector Knob to TST/SET.

(i) DBASE INFO? will be displayed (b) Rotate the Item Select Knob clockwise to access the 7 Database submenu.

(Reference Figure-201)






Figure 201 – SLS DB

SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION



1. General

1.1. This section has the following tasks.

(1) Removal of the GLSSU.

(2) Installation of the GLSSU.

(3) Removal of the LPV Adapter.

(4) Installation of the LPV Adapter.

(5) Removal of the SLS ACP.

(6) Installation of the SLS ACP.

(7) Removal of the Remote Switching Unit (RSU).

(8) Installation of the Remote Switching Unit (RSU).

(9) Removal of SLS CP.

(10) Installation of SLS CP.

1.2. Equipment Locations:

A. The GLSSU-L is located in the cabin overhead area between Sta 500A/B and stringer S-5R

and S-6R.The GLSSU-R is located in the cabin overhead area between Sta 500B/C and

stringer S-5R and S-6R. (Reference Figure 401).

B. The LPV Adapter-L is located in the E&E compartment in E2-2 shelf. The LPV Adapter-R is

located in the E&E compartment in E3-4 shelf. (Reference Figure 402)

C. The SLS ACP-L is located on the captain instrument panel P1-3 (adjacent to the

annunciator master BRT/DIM /TEST switch).The SLS ACP-R is located on the F/O

instrument panel P3-1 (adjacent to the altimeter). (Reference Figure 403)

D. The RSU (channel -L / -R) are located E&E compartment under floor panel.

E. The SLS CP -L / -R are located in P8 / P9 forward electronics panel (pilot stand).




2. Removal/Installation tasks 2.1. Removal of the GLSSU – L/-R

A. Procedure NOTE: The procedure given herein is for both units (GLSSU -L and -R). GLSSU-L is the forward unit and GLSSU-R is the aft unit.

(1) Open these circuit breakers and install safety tags: CAPT Electrical System Panel P18-1


SLS-L(*) 3A

GPS-L 3A

* NOTE: (*) Alternate location possible (P18-2). F/O Electrical System Panel P6-1


SLS-R 3A

GPS-R 3A

(2) Remove / retain sculptured ceiling panel -R from STA 460 to STA 500C per AMM

PAGEBLOCK 25-21-45-004-001.

(3) Remove electrical connectors and antenna coaxial connector from the GLSSU 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 – GLSSU (GPS Sensor) Location (Typical)




2.2. Installation of the GLSSU -L/ -R

A. Procedure

NOTE: The procedure given herein is for both unit (GLSSU -L and -R). (1) Open these circuit breakers and install safety tags:



SLS-L(*) 3A

GPS-L 3A

* NOTE: (*) Alternate location possible (P18-2). F/O Electrical System Panel P6-1


SLS-R 3A

GPS-R 3A

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

mounting screws and washers.

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

CAUTION!




(4) Remove safety tags and close these circuit breakers:



SLS-L(*) 3A

GPS-L 3A







SLS-R 3A

GPS-R 3A

(5) Perform GPS Sensor system test per MMS-34436-1 PAGEBLOCK 34-58-00 P. 503

(6) Perform SLS system test per Section 500 - 2.4.

(7) Install retained sculptured ceiling panel -R per AMM PAGEBLOCK 25-21-45-404-006.





2.3. LPV Adapter (-L/-R) Removal

NOTE: The procedure given herein is for the LPV Adapter-L, for the LPV Adapter-R, substitute -L for -R and E2-2 for E3-4. A. Procedure

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



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

(2) Gain access to the E&E compartment using Access Door 1201.

(3) Locate LPV Adapter-L (E2-2) and remove the Rack-Mounted E/E Box per AMM

PAGEBLOCK 20-10-07/201.

CAUTION!




(4) Install protective cover on LPV Adapter connector.





Figure 402 – LPV Adapter / RSY Location (Typical)




2.4. LPV Adapter (-L/-R) Installation

A. Procedure

NOTE: The procedure given herein is for the LPV Adapter-L, for the LPV Adapter-R, substitute -L for -R and E2-2 for E3-4.

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



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

(2) Gain access to the E&E compartment using Access Door 1201.

(3) Install the LPV Adapter:

(a) Remove unit protective cover. (b) Install the applicable LPV Adapter-L (E2-2) per AMM PAGEBLOCK 20-10-07/201.

CAUTION!










SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A


(6) Close access Door 1201.





2.5. SLS ACP (-L / -R) Removal A. Procedure

NOTE: The procedure given herein is for the SLS ACP-L, for the SLS ACP-R substitute Capt for F/O and P1-3 for P3-3.

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



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

(2) Gain access to the flight deck compartment Capt panel P1-3.

(a) Release the 5 quarter turn fasteners. (b) Push the pin index to release the safety lock and slide out the panel (approximately

5“).

CAUTION!




(3) Remove the SLS ACP-L:

(a) Release the 2-latch spring and remove the electrical connector. (b) Install protective cover. (c) Remove / retain the 2 SLS ACP mounting screw. (d) Remove the SLS ACP.





Figure 403 – SLS ACP (Typical)




2.6. SLS ACP (-L / -R) Installation

A. Procedure

NOTE: The procedure given herein is for the SLS ACP-L, for the SLS ACP-R substitute Capt for F/O and P1-3 for P3-3. (1) Open these circuit breakers and install safety tags:



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

(2) Gain access to the flight deck compartment Capt panel P1-3.

CAUTION!




(3) Install the SLS ACP: (a) Remove unit protective cover. (b) Engage the unit connector and close the 2 latch springs. (c) Position the unit in the instrument panel (rear panel mount) cut-out and install the 2

mounting screws (10 to 12 in-lb). (d) Slide the instrument panel forward and engage the 5 quarter turn fasteners. (Verify

the pin index (safety lock) is engage).







SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A






2.7. Remote Switching Unit (RSU) Removal

A. Procedure

NOTE: RSU-L and -R are housed within one unit therefore, replacement of the -L or -R independently is not possible. (1) Open these circuit breakers and install safety tags:



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

(2) Gain access to the E&E compartment through access Door 1201.

(3) Remove / retain the 11-floor panel retaining fasteners.

(Ref. Fig 401).

(4) Raise / Remove the floor panel and remove / retain the 4 RSU retaining fasteners. (a) Rotate the RSU (connector end forward) and remove the 2-connector locking

screw for RSU-L and RSU-R. (b) Install protective cover (x2). (c) Remove the RSU.

CAUTION!








2.8. Remote Switching Unit (RSU) Installation

A. Procedure

NOTE: RSU-L and -R are housed within one unit therefore, replacement of the -L or -R independently is not possible (1) Verify that these circuit breakers are opened and tagged.



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

(2) Gain access to the E&E compartment through access Door 1201.

(3) Install the RSU:

(a) Remove RSU protective cover (x2). (b) Position the RSU under floor (connector end forward) and engage each connector

(RSU-L and RSU-R) and secure the 2 each locking screws. (c) Position the RSU under floor (connector end E3-4) and install the 4 RSU mounting

screws (15 to 17 in-lb). (d) Align and close the floor panel.

(i) Verify RSU wiring harness is correctly routed and free of conflict. (e) Install the 11-floor panel mounting screws (58 to 62 in-lb).




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



SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A






2.9. Removal of SLS CP

A. Procedure

NOTE: The procedure given herein is for the SLS CP-L, for the SLS CP-R, substitute -L for -R. (1) Verify that these circuit breakers are opened and tagged.



SLS-L(*) 3A




SLS-R 3A

(2) Gain access to the P8 Panel located in the Flight Deck.

(3) Release the three clamping fingers holding the GLS CP front-panel to the flight

instrument panel & slide out CP.

(Ref. Figure 404)

(4) Disconnect the aircraft wiring harness to the rear panel connector J1.

CAUTION!








Figure 405 – SLS CP (Typical)




2.10. Installation of SLS CP

A. Procedure

NOTE: The procedure given herein is for the SLS CP-L, for the SLS CP-R, substitute -L for -R.

(1) Verify that these circuit breakers are opened and tagged.



SLS-L(*) 3A




SLS-R 3A

(2) Hold the GLS CP wiring harness connector through the cutout and connect it to the

rear-panel connector J1 on the GLS CP.

CAUTION!




(3) Slide the GLS CP way back into the instrument panel cutout and tighten evenly the

three finger clamps.

(a) Ensure CP is clamped tightly.







SLS-L(*) 3A




SLS-R 3A

(5) Perform SLS system test per Section 500 - 2.4


SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST



1. General

1.1. This procedure has these tasks:

(1) An operational test of the SLS ACP Indicating.

(2) An operational test of the SLS CP.

(3) An operational test of the GLSSU.

(4) SLS System Test.

(5) SLS System Synchronization Test.

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

GPS satellites or hangar with GPS repeater.




2. System Adjustment & Testing

2.1. Operational test of the SLS ACP Indicating

A. Purpose

(1) This test is used to verify:

(a) All the lamps are operational.

(b) The unit lamps test circuitries are operational.

(c) The unit following normal replacement.

B. Procedure

NOTE: This procedure applies to SLS ACP-L and -R.

(1) Supply Electrical Power per AMM task AMM 24-22-00/201.

(2) Verify that these circuit breakers are closed:



SLS-L(*) 3A




SLS-R 3A

(3) Verify that the SLS ACP-L /-R (P1-3 / P3-3):

(a) The “ON” P/Button are unlatched and the “ON” light is not illuminated.

(i) The “SBAS SEL” light is illuminated.

(b) The “LP/LPV” light is not illuminated.

(c) The “SBAS FAULT” light is not illuminated.

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

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

(b) Verify that all SLS ACP-L /-R (P1-3 / P3-3) annunciator illuminates bright.




(5) Select Master Bright / Dim / Test switch (P1-3) to NORM and verify that the SLS ACP

-L/-R (P1-3 / P3-3) and verify that:

(a) The “ON” P/Button are unlatched and the “ON” light is not illuminated.

(i) The “SBAS SEL” light is illuminated.

(b) The “LP/LPV” light is not illuminated.

(c) The “SBAS FAULT” light is not illuminated.


---- END OF TASK ---




2.2. Operational test of the SLS CP

A. Purpose

(1) This test is used to:

(a) Verify unit display and annunciator lamps are operational.

(b) Verify SLS CP / GLSSU communication operation.

(c) Verify the unit following normal replacement.

B. Procedure

NOTE: This procedure applies to CP-L and -R. SLS CP-L/-R self test can be initiated from

SLS CP-L/-R.


(2) Verify that these circuit breakers are closed.



SLS-L(*) 3A




SLS-R 3A

(3) Bite Test:

(a) Use the Mode Select knob and Item Select knob to enter the GLS CP TEST menu

as detailed in Figure-501.

(i) Push the Item Select Knob (PUSH-ENT) to initiate test.

(ii) The self test will sequence as detailed in Figure-502.

(b) Verify “IBIT PASSED” is displayed at the end of the test.






Figure 501 – SLS CP Bite




Figure 502 – SLS CP Bite Sequence




2.3. Operational test of the GLSSU

A. Purpose


(a) Verify the unit internal operation.

(b) Verify SLS CP / GLSSU and GLSSU inter-communication operation.

(c) Verify the unit following normal replacement.

B. Procedure

NOTE: This procedure applies to GLSSU-L and -R.





SLS-L(*) 3A




SLS-R 3A




(3) Bite Test:

(a) Use the Mode Select knob and Item Select knob to enter the GLSSU TEST menu

as detailed in Figure-503.

(i) Push the Item Select Knob (PUSH-ENT) to initiate test.

NOTE: This will initiate test on GLSSU-L and -R.

(ii) The self test will sequence as detailed in Figure-504.

(b) Verify “TEST PASSED” is displayed at the end of the test.






Figure 503 – GLSSU Bite




Figure 504 – GLSSU Bite Sequence




2.4. SLS System Test

A. Purpose


(a) Verify the complete SLS system, SLS LRU’s and integration into aircraft.

(b) Whenever a function of the SLS operation is in doubt

(c) Following SLS wiring repair.

B. Procedure

NOTE: Detailed procedure applies to SLS-L, interchange -L for -R, #1 for #2, and Capt for

F/O for the system -R.

NOTE: Move the aircraft to a position where the GPS antennas have a clear view of the

GPS satellites (or use of GPS repeater is acceptable) per AMM TASK 09-11-00-580-801.





SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

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

(4) Verify that:

(a) There is no fault message in the SLS CP-L.

(b) The SBAS fault light in the SLS ACP-L is not illuminated.

(c) The SBAS SEL “ON” P/Button is in the unlatched position in the SLS ACP-L and

verify that the “ON” light is not illuminated.




(5) Set:

(a) The Capt VHF Nav CP to an ILS frequency (other than 108.10)

(b) The Capt EFIS to VOR/ILS (EXP or FULL).

(c) The Capt course bar to actual aircraft heading (MCP).

NOTE: Aircraft with ILS capable standby horizon indicator must be set to ILS per

AMM TASK 34-25-02-715-036

Apply to SLS system -L test only.

(d) Verify that the Capt EHSI displays:

(i) ILS 1 (bottom L)

(ii) The lateral and vertical scale

(iii) DME blank (top L)

(e) Verify that the Capt EADI displays:

(i) The lateral and vertical scale

(f) Set the SBAS SEL “ON” P/Button to the latched position in the SLS ACP-L and

verify that:

(i) The “ON” light is illuminated.

(ii) VOR 1 is displayed on the Capt EHSI (bottom L)

(iii) 108.10 ILS frequency on the Capt EHSI (bottom R)

(iv) The lateral scale is displayed on the Capt EHSI.

(v) DME blank (top L).

(6) Guidance Test:

(a) On the SLS CP-L, use the Mode Select knob and Item Select knob to enter the

CDI/GS TEST menu as detailed in Figure-505.

(i) Rotate Item Select Knob to select GLSSU 1.

(ii) Push the Item Select Knob (PUSH-ENT) to initiate guidance test.

(b) On the SLS CP-L, verify that the display show “TEST IN PROGRESS”.




(7) After a short moment (5 Sec ~), verify that the Capt EHSI displays:

(a) ILS 1 (bottom L).

(b) 108.10 ILS frequency (bottom R)

(c) The lateral and vertical scale

(d) The lateral and vertical deviation shows one dot -L and one dot UP.

(e) DME 34.5 Kn (top L).

(8) Verify that the Capt EADI displays:

(a) The lateral and vertical scale and deviation agree with the EHSI.

(b) After a short moment (5-10 Sec ~), verify that The lateral and vertical deviation on

the Capt EHSI and EADI slew to center and then to one dot -R and one dot DN.

NOTE: Aircraft with ILS capable standby horizon indicator, verify that the lateral and

vertical agree with the Capt EHSI/EADI per AMM TASK 34-25-02-715-036.

(9) After a short moment (5-10 Sec ~), verify that:

(a) The SLS CP -L show “TEST COMPLETE.”

(b) VOR 1 is displayed on the Capt EHSI (bottom L).

(c) 108.10 ILS frequency on the Capt EHSI (bottom R).

(d) The lateral scale is displayed on the Capt EHSI (deviation out of view).

(e) DME blank on the Capt EHSI (top L).

(f) The lateral scale is displayed on the Capt EHSI (deviation out of view).

NOTE: Aircraft with ILS capable standby horizon indicator, verify that the lateral and

vertical deviations are bias out of view per AMM TASK 34-25-02-715-036).

(10) Select the SBAS SEL “ON” P/Button to the unlatched position in the SLS ACP-L and

verify that:

(a) ) “ON” light is not illuminated.

(b) Verify that the Capt EHSI displays:

(i) ILS 1 (bottom L).

(ii) Selected (VHF Nav CP) ILS frequency (bottom R)

(iii) The lateral and vertical scale.

(iv) DME blank (top L).

(c) Verify that the Capt EADI displays:

(i) The lateral and vertical scale.




NOTE: Aircraft with ILS capable standby horizon indicator, set the function switch to

OFF per AMM TASK 34-25-02-715-036.






Figure 505 – CDI/GS TEST Bite




2.5. SLS System Synchronization Test

A. Purpose


(a) Verify the inter-system synchronization (inter system data bus) and APD correct

selection / operation.

(b) Whenever a function of the SLS APD operation is in doubt.

(c) Following SLS inter-system wiring repair.

B. Procedure

NOTE: Move the aircraft to a position where the GPS antennas have a clear view of the

GPS satellites (or use of GPS repeater is acceptable) per AMM TASK 09-11-00-580-801.

NOTE: Knowledge of two LPV approach channels within 50 Nm will be required.

(1) Supply Electrical Power per AMM TASK AMM 24-22-00/201.




SLS-L(*) 3A

SLS-L D/A(*) 2A




SLS-R 3A

SLS-R D/A 2A

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




(4) Verify that:

(a) There is no fault message in the SLS CP-L.

(b) The LP/LPV light in the SLS ACP-L is illuminated.

(c) The SBAS fault light in the SLS ACP-L is not illuminated.

(d) The SBAS SEL “ON” P/Button is in the unlatched position in the SLS ACP-L and

verify that the “ON” light is not illuminated.

(5) Set:

(a) The Capt VHF Nav CP to an ILS frequency (other than 108.10).

(b) The Capt EFIS to VOR/ILS (EXP or FULL).

(c) The Capt course bar to actual aircraft heading (MCP).

(d) Verify that the Capt EHSI displays;

(i) ILS 1 (bottom L).

(ii) Selected ILS frequency (bottom R).

(iii) The lateral and vertical scale.

(iv) DME blank (top L).

(e) Verify that the Capt EADI displays:

(i) The lateral and vertical scale.

(6) Synchronization Test:

(a) On the SLS CP-L, use the Mode Select knob and Item Select knob to enter the

“TUNE STBY” menu as detailed in Figure-506.

(i) Enter a LPV channel (within 50 Nm from current location).

(ii) Press the Active/Standby “SWAP” button to make the selected channel active.

(Ref Figure-4).

(b) On the SLS CP-L, use the Mode Select knob and Item Select knob to verify that

the entered LPV channel is now active as detailed in Figure-507.

(c) Set the SBAS SEL “ON” P/Button to the latched position in the SLS ACP-L and

verify that:


(ii) ILS 1 is displayed on the Capt EHSI (bottom L).

(iii) 108.10 ILS frequency on the Capt EHSI (bottom R).

(iv) The lateral scale and deviation is displayed on the Capt EHSI/EADI.

(v) DME distance (in NM) shown on the Capt EHSI (top L) agree with the runway

distance shown on the SLS CP-L display.




(d) On the SLS CP-R, set the Mode Select knob to “ACT”, navigate the sub-menu and

verify that the following agrees with same information available on the SLS CP-L:

(i) LPV channel.

(ii) Runway identifier.

(iii) Distance.

(e) Set the SBAS SEL “ON” P/Button to the latched position in the SLS ACP-R and

verify that:


(ii) ILS 2 is displayed on the F/O EHSI (bottom L).

(iii) 108.10 ILS frequency on the F/O EHSI (bottom R).

(iv) The lateral scale and deviation is displayed on the F/O EHSI/EADI.

(v) DME distance (in NM) shown on the F/O EHSI (top L) agree with the runway

distance shown on the SLS CP-R display.

(f) On the SLS CP-R, use the Mode Select knob and Item Select knob to enter the

“TUNE STBY” menu as detailed in Figure-506.

(i) Enter a “different” LPV channel (within 50 Nm from current location).

(ii) Press the Active/Standby “SWAP” button to make the selected channel active.

(Ref Figure-4)

(g) On the Capt and F/O instrument panel, verify that:

(i) The “ON” light is illuminated on both SLS ACP.

(ii) ILS 2 is displayed on the F/O EHSI (bottom L).

(iii) ILS 1 is displayed on the Capt EHSI (bottom L).

(iv) 108.10 ILS frequency on the both EHSI (bottom R).

(v) The lateral scale and deviation is displayed on both EHSI/EADI.

(vi) DME distance (in NM) shown on both EHSI (top L) agree with the runway

distance shown on the SLS CP-R display.

(vii) The LPV channel displayed in the SLS CP-L agree with the channel entered in

the SLS CP -R.

(h) Set the SBAS SEL “ON” P/Button to the unlatched position in both SLS ACP and

verify that:

(i) Both “ON” light are extinguished.






Figure 506 – LPV Channel Entry




Figure 507 – LPV Channel Active

SBAS LANDING SYSTEM – 600 - TIME LIMITS / MAINTENANCE CHECKS



1. General

1.1. There are no scheduled maintenance or inspection introduced by this modification The SLS

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

2. Electrical Wiring Interconnection System (EWIS) ICA

2.1. The modification has been reviewed per the guidance provided in FAA AC 25-27. It has been

determined that the modification does not necessitate a revision to the EWIS ICA that were

required to be developed by § 26.11(b) / § 25.1729.

Documents

SBAS LANDING SYSTEM (SLS)MAINTENANCE MANUAL SUPPLEMENT MMS-34436-5 R0 SBAS LANDING SYSTEM (SLS) BOEING 737-300/400/500 STC TCCA SA11-92 EASA 10043626 FAA ST03273NY This document contains