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 .
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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
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: LOR
REV DATE DESCRIPTION PAGES AFFECTED APPROVED
R0 JUN-28/2019 INITIAL RELEASE ALL
SBAS LANDING SYSTEM – INTRODUCTION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
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.
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.
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
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
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
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
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
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
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
(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
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 2
(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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
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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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 4
Figure 1 – SLS CONTROL PANEL LOCATION
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 5
Figure 2 – LPV ADAPTER & RSU LOCATIONS
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 6
Figure 3 – SLS ACP LOCATION
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 7
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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 8
Figure 4 – SLS Control Panel
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 9
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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 10
(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
Circuit Breaker Label Rating
SLS-R 3A
SLS-R D/A 2A
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 11
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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 12
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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 13
(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.
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 14
Figure 5 – SLS-L Schematic
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 15
Figure 6 – SLS-ACP
SBAS LANDING SYSTEM – DESCRIPTION AND OPERATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 16
Figure 7 – SLS LPV-DLU
SBAS LANDING SYSTEM – 100 - FAULT ISOLATION
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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.
SBAS LANDING SYSTEM – 100 - FAULT ISOLATION
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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.
SBAS LANDING SYSTEM – 100 - FAULT ISOLATION
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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)
Replace or swap to isolate
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.
Replace or swap to isolate
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.
Replace or swap to isolate
fault on-side RSU
Replace RSU
(Ref Sec 400 – 2.7 & 2.8)
Replace or swap to isolate
fault on-side SLS ACP
Replace SLS ACP
(Ref Sec 400 – 2.5 & 2.6)
Inspect/verify aircraft wiring Repair per SWPM
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.
Replace or swap to isolate
fault on-side RSU
Replace RSU
(Ref Sec 400 – 2.7 & 2.8)
Replace or swap to isolate
fault on-side VHF NAV CP
Replace VHF NAV CP
(AMM 34-31-52)
Inspect/verify aircraft wiring Repair per SWPM
6 EHSI does not display selected
VHF Nav CP ILS frequency
when SBAS SEL P/Button is
unlatch or 108.10 when
latched.
Replace or swap to isolate
fault on-side RSU
Replace RSU
(Ref Sec 400 – 2.7 & 2.8)
Replace or swap to isolate
fault on-side DAA
Replace DAA
(AMM 34-28-41)
Inspect/verify aircraft wiring Repair per SWPM
SBAS LANDING SYSTEM – 100 - FAULT ISOLATION
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Table 34-31-00-1 (Cont.)
# Trouble Probable Cause Action / Remedy
7 SLS Distance is not displayed
on ESHI when SBAS SEL
P/Button latch in.
- Assumption: DME distance
display normally when
unlatched.
Replace or swap to isolate
fault on-side LPV Adapter
Replace LPV Adapter
(Ref Sec 400 – 2.3 & 2.4)
Replace or swap to isolate
fault on-side GLSSU
Replace GLSSU
(Ref Sec 400 – 2.1 & 2.2)
Inspect/verify aircraft wiring Repair per SWPM
8 SLS Distance is not displayed
on ESHI when SBAS SEL
P/Button latch in.
- Assumption: DME distance
display fault when unlatched.
Replace or swap to isolate
fault on-side LPV Adapter
Replace LPV Adapter
(Ref Sec 400 – 2.3 & 2.4)
Replace or swap to isolate
fault on-side DAA
Replace DAA
(AMM 34-28-41)
Inspect/verify aircraft wiring Repair per SWPM
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 or swap to isolate
fault on-side LPV Adapter
Replace LPV Adapter
(Ref Sec 400 – 2.3 & 2.4)
Replace or swap to isolate
fault on-side SLS ACP
Replace SLS ACP
(Ref Sec 400 – 2.5 & 2.6)
Inspect/verify aircraft wiring Repair per SWPM
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 or swap to isolate
fault on-side LPV Adapter
Replace LPV Adapter
(Ref Sec 400 – 2.3 & 2.4)
Replace or swap to isolate
fault on-side EFIS SGU
Replace EFIS SGU
(AMM 34-22-41/201)
Inspect/verify aircraft wiring Repair per SWPM
11 SLS Control panel is displaying
fault message
Refer to PAGEBLOCK
34-50-05/501
Consult the fault message
and replace components
as required.
Inspect/verify aircraft wiring Repair per SWPM
12 SLS ACP FAULT light
illuminates
Replace or swap to isolate
fault on-side GLSSU
Replace GLSSU
(Ref Sec 400 – 2.1 & 2.2)
Replace or swap to isolate
fault on-side SLS ACP
Replace SLS ACP
(Ref Sec 400 – 2.5 & 2.6)
Inspect/verify aircraft wiring Repair per SWPM
SBAS LANDING SYSTEM – 100 - FAULT ISOLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 105
Table 34-31-00-1 (Cont)
# Trouble Probable Cause Action / Remedy
13 SLS ACP LP/LPV light fail to
illuminate
Replace or swap to isolate
fault on-side GLSSU
Replace GLSSU
(Ref Sec 400 – 2.1 & 2.2)
Replace or swap to isolate
fault on-side SLS ACP
Replace SLS ACP
(Ref Sec 400 – 2.5 & 2.6)
Inspect/verify aircraft wiring Repair per SWPM
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)
Inspect/verify aircraft wiring Repair per SWPM
15 GLSSU fail self test Replace or swap to isolate
fault on-side GLSSU
Replace GLSSU
(Ref Sec 400 – 2.1 & 2.2)
Inspect/verify aircraft wiring Repair per SWPM
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 201
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.
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 202
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.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
(2) Open these circuit breakers and install safety locks.
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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.
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 203
(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 ----
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 204
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:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
(2) Remove/discard safety locks and close these circuit breakers.
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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 energized.
(3) Perform SLS System Test per Section 500 - 2.4.
(4) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 205
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.
---- END OF TASK ----
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 206
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
(1) Energize aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
(2) Open these circuit breakers and install safety locks
CAPT Electrical System Panel P18-2
Circuit Breaker Label Rating
AIRBORNE DATA
LOADER
3A
OR
FMC CMPTR (-L) 3A
(3) Verify that these circuit breakers are closed. CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L (*) 3A
NOTE: (*) Alternate location possible (P18-2). F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 207
(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
Circuit Breaker Label Rating
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.
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 208
(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)
(9) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 200 - MAINTENANCE PRACTICES
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 209
Figure 201 – SLS DB
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 401
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).
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 402
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
Circuit Breaker Label Rating
SLS-L(*) 3A
GPS-L 3A
* NOTE: (*) Alternate location possible (P18-2). F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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.
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 406
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:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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!
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) Install protective cover on LPV Adapter connector.
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 407
Figure 402 – LPV Adapter / RSY Location (Typical)
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 408
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.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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!
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
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 409
(4) Remove safety tags and close these circuit breakers:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
SLS-R D/A 2A
(5) Perform SLS system test per Section 500 - 2.4.
(6) Close access Door 1201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 410
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:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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!
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
(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.
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 411
Figure 403 – SLS ACP (Typical)
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 412
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:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
SLS-R D/A 2A
(2) Gain access to the flight deck compartment Capt panel P1-3.
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
(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).
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 413
(4) Remove safety tags and close these circuit breakers:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
SLS-R D/A 2A
(5) Perform SLS system test per Section 500 - 2.4.
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 414
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:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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!
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
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 415
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.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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).
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 416
(4) Remove safety tags and close these circuit breakers.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
SLS-R D/A 2A
(5) Perform SLS system test per Section 500 - 2.4.
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 417
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.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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!
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
---- END OF TASK ----
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 418
Figure 405 – SLS CP (Typical)
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 419
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.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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!
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
(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.
SBAS LANDING SYSTEM – 400 - REMOVAL & INSTALLATION
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 420
(4) Remove safety tags and close these circuit breakers:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
(5) Perform SLS system test per Section 500 - 2.4
---- END OF TASK ----
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 501
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.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 502
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:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 503
(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.
(6) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ---
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 504
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.
(1) Supply Electrical Power per AMM task AMM 24-22-00/201.
(2) Verify that these circuit breakers are closed.
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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.
(4) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 505
Figure 501 – SLS CP Bite
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 506
Figure 502 – SLS CP Bite Sequence
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 507
2.3. Operational test of the GLSSU
A. Purpose
(1) This test is used to:
(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.
(1) Supply Electrical Power per AMM task AMM 24-22-00/201.
(2) Verify that these circuit breakers are closed:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
SLS-R 3A
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 508
(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.
(4) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 509
Figure 503 – GLSSU Bite
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 510
Figure 504 – GLSSU Bite Sequence
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 511
2.4. SLS System Test
A. Purpose
(1) This test is used to:
(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.
(1) Supply Electrical Power per AMM task AMM 24-22-00/201.
(2) Verify that these circuit breakers are closed:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 512
(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”.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 513
(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.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 514
NOTE: Aircraft with ILS capable standby horizon indicator, set the function switch to
OFF per AMM TASK 34-25-02-715-036.
(11) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 515
Figure 505 – CDI/GS TEST Bite
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 516
2.5. SLS System Synchronization Test
A. Purpose
(1) This test is used to:
(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.
(2) Verify that these circuit breakers are closed:
CAPT Electrical System Panel P18-1
Circuit Breaker Label Rating
SLS-L(*) 3A
SLS-L D/A(*) 2A
* NOTE: (*) Alternate location possible (P18-2).
F/O Electrical System Panel P6-1
Circuit Breaker Label Rating
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.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 517
(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:
(i) The “ON” light is illuminated.
(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.
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 518
(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:
(i) The “ON” light is illuminated.
(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.
(7) Remove aircraft electrical power per AMM PAGEBLOCK 24-22-00/201.
---- END OF TASK ----
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 519
Figure 506 – LPV Channel Entry
SBAS LANDING SYSTEM – 500 - ADJUSTMENT / TEST
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 520
Figure 507 – LPV Channel Active
SBAS LANDING SYSTEM – 600 - TIME LIMITS / MAINTENANCE CHECKS
SUPPLEMENT 34-31-00 SBAS LANDING SYSTEM (SLS)
BOEING MMS-34436-5 R0 Page: 601
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.