A
737-600/700/800/900
MAINTENANCE MANUAL
ALASKA AIRLINES, INC.
Part II
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R = Revised, A = Added, D = Deleted, F = Foldout
O = Overflow or @ = COC Page
D633A101-ASA
Chapter 34
EFFECTIVE PAGES
Page 1
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
ALASKA AIRLINES, INC.
Part II
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R = Revised, A = Added, D = Deleted, F = Foldout
O = Overflow or @ = COC Page
D633A101-ASA
Chapter 34
EFFECTIVE PAGES
Page 2
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
ALASKA AIRLINES, INC.
Part II
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JUN 10/00
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JUN 10/00
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BLANK
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OCT 10/00
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OCT 10/00
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FEB 05/99
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OCT 10/00
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OCT 10/99
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JUN 10/99
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OCT 10/99
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FEB 10/00
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FEB 10/01
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FEB 05/99
¦34-57-00
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FEB 10/01
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OCT 10/99
¦ R 501
FEB 10/01
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OCT 10/00
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OCT 10/00
¦34-46-02
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BLANK
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FEB 10/01
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JUN 10/99
¦34-53-02
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OCT 10/99
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FEB 10/00
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BLANK
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FEB 10/00
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FEB 05/99
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FEB 05/99
¦34-51-00
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FEB 05/99
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FEB 10/00
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FEB 10/00
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OCT 10/00
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OCT 10/00
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R = Revised, A = Added, D = Deleted, F = Foldout
O = Overflow or @ = COC Page
D633A101-ASA
Chapter 34
EFFECTIVE PAGES
Page 3
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
ALASKA AIRLINES, INC.
Part II
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PAGE
DATE
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PAGE
DATE
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PAGE
DATE
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DATE
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¦34-57-01
¦34-61-00
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OCT 10/00
¦ R 501
FEB 10/01
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FEB 05/99
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FEB 10/01
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FEB 05/99
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FEB 10/01
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OCT 10/00
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FEB 10/00
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OCT 10/00
¦ R 505
FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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OCT 10/99
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¦34-57-02
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510
FEB 10/00
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FEB 10/01
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FEB 10/00
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FEB 10/01
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OCT 10/00
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FEB 10/01
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FEB 10/01
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¦ R 516
FEB 10/01
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OCT 10/00
¦ R 517
FEB 10/01
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OCT 10/00
¦ R 518
FEB 10/01
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OCT 10/00
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FEB 10/01
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OCT 10/00
¦ O 520
FEB 10/01
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FEB 10/01
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¦ O 522
FEB 10/01
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OCT 10/00
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502
OCT 10/00
¦34-61-01
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FEB 05/99
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FEB 10/01
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OCT 10/00
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OCT 10/99
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OCT 10/99
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OCT 10/00
¦34-61-01
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JUN 10/00
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OCT 10/00
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JUN 10/00
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FEB 05/99
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FEB 05/99
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JUN 10/00
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FEB 10/01
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OCT 10/00
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OCT 10/00
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FEB 10/01
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FEB 10/01
¦34-61-02
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FEB 10/01
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OCT 10/00
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FEB 10/01
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FEB 05/99
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JUN 10/99
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FEB 10/01
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BLANK
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FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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FEB 10/01
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²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
R = Revised, A = Added, D = Deleted, F = Foldout
O = Overflow or @ = COC Page
D633A101-ASA
Chapter 34
EFFECTIVE PAGES
Page 4
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
Chapter
Section
Subject
_______
Page
____
__________
NAVIGATION
DDG Maintenance Procedures
34-00-00
FLIGHT ENVIRONMENT DATA
_______________________
34-10-00
Effectivity
___________
901
ALL
201
ALL
Servicing
301
ALL
Adjustment/Test
Left Static System Leak Test
Right Static System Leak Test
Alternate Static System Leak
Test
Left Pitot System Leak Test
Right Pitot System Leak Test
Alternate Pitot System Leak
Test
Left Static System Full-range
Leak Test
Right Static System
Full-range Leak Test
Alternate Static System
Full-range Leak Test
501
501
509
517
ALL
STATIC AND TOTAL AIR PRESSURE
SYSTEM
Maintenance Practices
STATIC AND TOTAL AIR PRESSURE
SYSTEM
Removal/Installation
34-11-00
524
529
533
538
545
552
34-11-01
401
ALL
Inspection/Check
601
ALL
Cleaning/Painting
701
ALL
401
ALL
601
ALL
STATIC PORT
Removal/Installation
34-11-02
Inspection/Check
34-CONTENTS PART II
D633A101-ASA
Page 1
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
AIR DATA INSTRUMENTS
Adjustment/Test
Chapter
Section
Subject
_______
Page
____
34-13-00
STANDBY ALTIMETER/AIRSPEED
INDICATOR
Removal/Installation
34-13-01
MACH AIRSPEED WARNING SYSTEM
Adjustment/Test
34-16-00
ATTITUDE & DIRECTION
____________________
AIR DATA INERTIAL REFERENCE
SYSTEM
Maintenance Practices
IR Radial Position Error
Check
Inertial Reference Residual
Groundspeed Error Check
Effectivity
___________
501
ALL
401
ALL
501
ALL
201
206
ALL
34-20-00
34-21-00
209
Adjustment/Test
Air Data Reference - System
Test
AIR DATA INERTIAL REFERENCE
UNIT
Removal/Installation
34-21-01
INERTIAL SYSTEM DISPLAY UNIT
Removal/Installation
34-21-02
IRS MODE SELECT UNIT
Removal/Installation
34-21-03
AIR DATA MODULE
Removal/Installation
34-21-04
ANGLE OF ATTACK SENSOR
Removal/Installation
34-21-05
501
518
ALL
401
ALL
401
ALL
401
ALL
401
ALL
401
ALL
34-CONTENTS PART II
D633A101-ASA
Page 2
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
Chapter
Section
Subject
_______
Page
____
TOTAL AIR TEMPERATURE PROBE
Removal/Installation
Total Air Temperature Probe
Removal
34-21-06
IRS MASTER CAUTION UNIT
Removal/Installation
34-21-07
RADIO MAGNETIC INDICATOR
Removal/Installation
34-22-01
STANDBY MAGNETIC COMPASS
Maintenance Practices
STANDBY MAGNETIC COMPASS
Removal/Installation
STANDBY ATTITUDE REFERENCE SYSTEM
Adjustment/Test
STANDBY ATTITUDE INDICATOR
Removal/Installation
LANDING AND TAXIING AIDS
________________________
Effectivity
___________
401
401
ALL
401
ALL
401
ALL
201
ALL
401
ALL
501
ALL
401
ALL
501
ALL
401
ALL
401
ALL
401
ALL
401
ALL
34-23-00
34-23-01
34-24-00
34-24-01
34-30-00
INSTRUMENT LANDING SYSTEM
Adjustment/Test
34-31-00
ILS GLIDE SLOPE ANTENNA
Removal/Installation
34-31-21
LOCALIZER ANTENNA
Removal/Installation
34-31-31
ILS AND MULTI-MODE RECEIVER
(MMR)
Removal/Installation
34-31-42
NAVIGATION CONTROL PANEL
Removal/Installation
34-31-52
34-CONTENTS PART II
D633A101-ASA
Page 3
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
Chapter
Section
Subject
_______
Page
____
RF POWER DIVIDER
Removal/Installation
34-31-62
LOCALIZER ANTENNA SWITCH
Removal/Installation
34-31-72
MARKER BEACON SYSTEM
Adjustment/Test
MARKER BEACON ANTENNA
Removal/Installation
LOW RANGE RADIO ALTIMETER (LRRA)
SYSTEM
Maintenance Practices
Effectivity
___________
401
ALL
401
ALL
501
ALL
401
ALL
201
ALL
501
ALL
401
ALL
401
ALL
501
ALL
401
ALL
401
ALL
401
ALL
34-32-00
34-32-11
34-33-00
Adjustment/Test
LOW RANGE RADIO ALTIMETER
ANTENNA
Removal/Installation
34-33-11
LRRA RECEIVER/TRANSMITTER
Removal/Installation
34-33-21
INDEPENDENT POSITION DETERMINING
________________________________
34-40-00
WEATHER RADAR (WXR) SYSTEM
Adjustment/Test
34-43-00
WEATHER RADAR ANTENNA
Removal/Installation
34-43-11
WEATHER RADAR WAVEGUIDE
Removal/Installation
34-43-21
WEATHER RADAR
RECEIVER/TRANSMITTER MOUNT
Removal/Installation
34-43-31
34-CONTENTS PART II
D633A101-ASA
Page 4
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
Chapter
Section
Subject
_______
Page
____
WEATHER RADAR
RECEIVER/TRANSMITTER
Removal/Installation
34-43-41
WEATHER RADAR CONTROL PANEL
Removal/Installation
34-43-91
TRAFFIC ALERT AND COLLISION
AVOIDANCE SYSTEM (TCAS)
Adjustment/Test
34-45-01
TRAFFIC ALERT AND COLLISION
AVOIDANCE SYSTEM (TCAS) ANTENNA
Removal/Installation
34-45-02
GROUND PROXIMITY WARNING
COMPUTER
Removal/Installation
34-46-01
GROUND PROXIMITY WARNING MODULE
Removal/Installation
34-46-02
VOR SYSTEM
Adjustment/Test
ALL
401
ALL
501
ALL
401
ALL
401
ALL
201
201
204
ALL
501
ALL
401
ALL
401
ALL
501
ALL
34-46-00
Adjustment/Test
DEPENDENT POSITION DETERMINING
______________________________
401
34-45-00
TRAFFIC ALERT AND COLLISION
AVOIDANCE SYSTEM (TCAS)
COMPUTER
Removal/Installation
GROUND PROXIMITY WARNING SYSTEM
Maintenance Practices
Load the Terrain Database
Verify the Terrain Database
Part Number
Effectivity
___________
34-50-00
34-51-00
34-CONTENTS PART II
D633A101-ASA
Page 5
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
Chapter
Section
Subject
_______
Page
____
VOR/MKR RECEIVER
Removal/Installation
34-51-01
VOR/LOC ANTENNA
Removal/Installation
34-51-02
AIR TRAFFIC CONTROL (ATC) SYSTEM
Adjustment/Test
Air Traffic Control System Operational Test
Air Traffic Control System System Test (With the IFR
ATC-601 Test Set)
401
ALL
401
ALL
501
501
ALL
34-53-00
502
AIR TRAFFIC CONTROL (ATC)
ANTENNA
Removal/Installation
ATC Antenna Removal
34-53-01
AIR TRAFFIC CONTROL (ATC)
TRANSPONDER
Removal/Installation
ATC Transponder Removal
34-53-02
ATC CONTROL PANEL
Removal/Installation
ATC Control Panel Removal
34-53-03
AIR TRAFFIC CONTROL (ATC)
ANTENNA SWITCH
Removal/Installation
34-53-04
DME SYSTEM
Adjustment/Test
Effectivity
___________
401
401
ALL
401
401
ALL
401
401
ALL
401
ALL
501
ALL
401
ALL
401
ALL
34-55-00
DME ANTENNA
Removal/Installation
34-55-11
DME INTERROGATOR
Removal/Installation
34-55-21
34-CONTENTS PART II
D633A101-ASA
Page 6
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
AUTOMATIC DIRECTION FINDER SYSTEM
Adjustment/Test
Chapter
Section
Subject
_______
Page
____
34-57-00
ADF ANTENNA
Removal/Installation
34-57-01
ADF CONTROL PANEL
Removal/Installation
34-57-02
ADF RECEIVER
Removal/Installation
34-57-03
GLOBAL POSITIONING SYSTEM
Adjustment/Test
34-58-00
GPS ANTENNA
Removal/Installation
34-58-02
FLIGHT MANAGEMENT COMPUTING
___________________________
FLIGHT MANAGEMENT COMPUTER SYSTEM
Maintenance Practices
FMC Software Installation
with a Portable Data Loader
FMC Software Crossload
FMC Software Configuration
Check
CDU Software Installation
with a Portable Data Loader
CDU Software Configuration
Check
FMC Diagnostic Data Transfer
Effectivity
___________
501
ALL
401
ALL
401
ALL
401
ALL
501
ALL
401
ALL
201
201
ALL
34-60-00
34-61-00
208
210
211
215
215
Adjustment/Test
501
ALL
201
ALL
Servicing
301
ALL
Removal/Installation
401
ALL
FMCS CONTROL DISPLAY UNIT
Maintenance Practices
34-61-01
34-CONTENTS PART II
D633A101-ASA
Page 7
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
Chapter 34 - NAVIGATION
Part II
TABLE OF CONTENTS
_________________
Subject
_______
FMCS COMPUTER
Removal/Installation
Chapter
Section
Subject
_______
Page
____
Effectivity
___________
34-61-02
401
ALL
34-CONTENTS PART II
D633A101-ASA
Page 8
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
NAVIGATION - DDG MAINTENANCE PROCEDURES
_______________________________________
1.
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General
_______
A. This procedure has the maintenance tasks for the Master Minimum Equipment
List (MMEL) maintenance requirements as shown in the Dispatch Deviations
Procedures Guide (DDPG). These tasks prepare the airplane for flight
with systems/components that are inoperative.
B. This procedure also has the tasks that put the airplane back to its usual
condition.
C. These are the tasks for the components in the navigation system:
(1) MMEL 34-20 (DDPG) Preparation - Low Range Radio Altimeter (LRRA)
Inoperative
(2) MMEL 34-20 (DDPG) Restoration - Low Range Radio Altimeter (LRRA)
Inoperative
(3) MMEL 34-26 (DDPG) Preparation - Ground Proximity Warning System
(GPWS) Inoperative
(4) MMEL 34-26 (DDPG) Restoration - Ground Proximity Warning System
(GPWS) Inoperative
(5) MMEL 34-40 (DDPG) Preparation - Traffic Collision and Avoidance
System (TCAS) Inoperative
(6) MMEL 34-40 (DDPG) Restoration - Traffic Collision and Avoidance
System (TCAS) Inoperative
TASK 34-00-00-040-802
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2.
____________________________________________________________________________
MMEL
34-20 (DDPG) Preperation - Low Range Radio Altimeter (LRRA) Inoperative
A. General
(1) This task gives the maintenance steps which prepare the airplane for
flight with the Low Range Radio Altimeter (LRRA) inoperative.
B. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
C. LRRA Deactivation, Left
SUBTASK 040-002
Open this circuit breaker and attach a circuit breaker lock:
(a) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
LRRA Deactivation, Right
(1)
D.
(1)
SUBTASK 040-003
Open this circuit breaker and attach a circuit breaker lock:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
EFFECTIVITY
34-00-00
ALL
D633A101-ASA
Page 901
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
TASK 34-00-00-440-802
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3.
____________________________________________________________________________
MMEL
34-20 (DDPG) Restoration - Low Range Radio Altimeter (LRRA) Inoperative
A. General
(1) This task puts the airplane back to its usual condition after
operation with the Low Range Radio Alitmeter (LRRA) inoperative.
B. References
(1) AMM TASK 34-33-00-710-801 p501, Low Range Radio Altimeter (LRRA)
System - Operational Test
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
D. LRRA Reactivation, Left
SUBTASK 440-002
Remove the circuit breaker lock and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
LRRA Reactivation, Right
(1)
E.
SUBTASK 440-003
Remove the circuit breaker lock and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
FCC-A Re-initialization (left)
(1)
F.
SUBTASK 440-004
Momentarily open and close this circuit breaker:
(a)
1) Circuit Breaker Panel, P18-1:
a) 18D2
AFCS SYS A FCC DC
FCC-A Re-initialization (right)
(1)
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G.
SUBTASK 440-005
Momentarily open and close this circuit breaker:
(a)
1) Circuit Breaker Panel, P6-2:
a) 6B3
AFCS SYS B FCC DC
LRRA Repair
(1)
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H.
(1)
SUBTASK 740-002
Do this task: Low Range Radio Altimeter (LRRA) System - Operational
Test (AMM TASK 34-33-00-710-801 p501).
EFFECTIVITY
34-00-00
ALL
D633A101-ASA
Page 902
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
(2)
(3)
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SUBTASK 810-003
Go to the Fault Code Index in the FIM and find the fault code (the
first two digits of the fault code are the FIM chapter).
(a) For each correlated maintenance message, find the maintenance
message number to the right side of the fault code.
(b) Find the task number on the same line as the maintenance
message number.
SUBTASK 810-004
Go to the task in the FIM and do the steps in the task.
TASK 34-00-00-040-803
4.
______________________________________________________________________
MMEL
34-26 (DDPG) Preparation - Ground Proximity Warning System (GPWS)
___________
Inoperative
A. General
(1) This task gives the maintenance steps which prepare the airplane for
flight with the Ground Proximity Warning System (GPWS) inoperative.
B. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
C. GPWS Deactivation
(1)
SUBTASK 040-004
Open this circuit breaker and attach a circuit breaker lock:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
TASK 34-00-00-440-803
5.
______________________________________________________________________
MMEL
34-26 (DDPG) Restoration - Ground Proximity Warning System (GPWS)
___________
Inoperative
A. General
(1) This task puts the airplane back to its usual condition after
operation with the Ground Proximity Warning System (GPWS)
inoperative.
B. References
(1) FIM 34-46 TASK 801, GPWS BITE Procedure
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
D. GPWS Reactivation
(1)
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SUBTASK 440-006
Remove the circuit breaker lock and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
EFFECTIVITY
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E.
GPWS Repair
(1)
(2)
(3)
SUBTASK 740-003
Do this task: GPWS BITE Procedure (FIM 34-46 TASK 801).
SUBTASK 810-005
Go to the Fault Code Index in the FIM and find the fault code (the
first two digits of the fault code are the FIM chapter).
(a) For each correlated maintenance message, find the maintenance
message number to the right side of the fault code.
(b) Find the task number on the same line as the maintenance
message number.
SUBTASK 810-006
Go to the task in the FIM and do the steps in the task.
TASK 34-00-00-040-801
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6.
_____________________________________________________________________________
MMEL
34-40 (DDPG) Preparation - Traffic Collision and Avoidance System (TCAS)
___________
Inoperative
A. General
(1) This task gives the maintenance steps which prepare the airplane for
flight with the Traffic Collision and Avoidance System (TCAS)
inoperative.
B. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
C. TCAS Deactivation
(1)
SUBTASK 040-001
Open this circuit breaker and attach a circuit breaker lock:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
TASK 34-00-00-440-801
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7.
_____________________________________________________________________________
MMEL
34-40 (DDPG) Restoration - Traffic Collision and Avoidance System (TCAS)
___________
Inoperative
A. General
(1) This task puts the airplane back to its usual condition after
operation with the Traffic Collision and Avoidance System (TCAS)
inoperative.
B. References
(1) FIM 34-45 TASK 801, Traffic Alert and Collision Avoidance System
(TCAS) BITE Procedure
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
EFFECTIVITY
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D.
TCAS Reactivation
SUBTASK 440-001
Remove the circuit breaker lock and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
TCAS Repair
(1)
E.
(1)
(2)
(3)
SUBTASK 740-001
Do this task: Traffic Alert and Collision Avoidance System (TCAS)
BITE Procedure (FIM 34-45 TASK 801).
SUBTASK 810-001
Go to the Fault Code Index in the FIM and find the fault code (the
first two digits of the fault code are the FIM chapter).
(a) For each correlated maintenance message, find the maintenance
message number to the right side of the fault code.
(b) Find the task number on the same line as the maintenance
message number.
SUBTASK 810-002
Go to the task in the FIM and do the steps in the task.
EFFECTIVITY
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STATIC AND TOTAL AIR PRESSURE SYSTEM - MAINTENANCE PRACTICES
____________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) Pressurization of the Captain's Total Air Pressure System to
simulate an airspeed.
(2) Pressurization of the Static and Total Air Pressure System to
simulate an altitude and airspeed.
TASK 34-11-00-790-803
2.
____________________________________________________
Captain's
Total Air Pressure System - Pressurization
A. General
(1) This task contains the steps to pressurize the Captain's Total Air
Pressure System.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701M2-3 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P75701-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
EFFECTIVITY
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(f)
(g)
(h)
(i)
(j)
(k)
D.
E.
6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(e) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(f) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
Prepare for the Captain's Total Air Pressure System - Pressurization
(1)
(2)
SUBTASK 860-062
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
SUBTASK 860-063
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
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SUBTASK 730-002
CAUTION:
_______
(3)
OBEY THESE PRECAUTIONS BEFORE YOU APPLY PRESSURE TO THE PITOT
SYSTEM. IF YOU DO NOT OBEY THESE PRECAUTIONS, DAMAGE TO THE
EQUIPMENT AND INSTRUMENTS CAN OCCUR.
Obey these precautions before you apply pressure to the pitot
system.
(a) Supply the electrical power for the ADIRS before you make the
total pressure hook-up.
(b) Keep power on until the pressure hook-up is opened.
(c) Pressure changes must be flow controlled to prevent sudden
changes in pressure and possible damage to the air data
hardware.
(d) Keep the total pressure in the range of 3.26 to 41.34 inches
Hg.
(e) When you adjust the pressure, make sure the rate of change of
airspeed is less than 300 knots per minute.
(f) Make sure the difference between the static and pitot line
pressure is not larger than 10 inches Hg.
(g) Make sure the autopilot system stays off during the test.
CAUTION:
_______
(h)
(i)
(j)
(k)
MAKE SURE YOU DO NOT SUPPLY ELECTRICAL POWER TO THE PITOT
PROBE HEATER. THIS CAN CAUSE DAMAGE TO THE PITOT PROBE.
Make sure the pitot probe heaters stay off during the test.
Make sure the AOA vanes are set to zero degrees.
Do not connect or disconnect the test equipment while you have
pressure in the pitot system.
Make sure that you do these steps before installing the
adapter, P75701M2-3, on the probe:
1) Flush the adapter, P75701M2-3, with water.
NOTE:
____
F.
Use equal parts of ethylene glycol and water when
the temperature is between 32° and -40°F.
2) Blow dry, filtered air through the adapter.
3) Wipe the probe with a damp cloth.
Captain's Total Air Pressure System - Pressurization
(1)
SUBTASK 860-064
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
SUBTASK 170-072
EFFECTIVITY
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CAUTION:
_______
(2)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER WITH
WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE. DAMAGE TO
THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter, P75701M2-3, with water.
NOTE:
____
Use equal parts of water and ethylene glycol when the
temperature is between 32° and -40°F.
(3)
SUBTASK 480-084
Blow dry, filtered air through the adapter, P75701M2-3.
(4)
SUBTASK 480-085
Wipe the probe with a damp cloth.
SUBTASK 480-086
CAUTION:
_______
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MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
(5)
Install the adapter, P75701M2-3, on the left pitot probe.
(6)
SUBTASK 480-087
Connect the test set to the adapter, P75701M2-3.
SUBTASK 790-057
CAUTION:
_______
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(7)
(8)
G.
MAKE SURE THAT THE PRESSURE IN THE ADM IS NOT TOO HIGH.
PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL CAUSE DAMAGE
TO THE ADM.
Operate the test set to apply the desired pressure to the pitot
system.
SUBTASK 790-058
Stop for one minute to allow the system to stabilize.
SUBTASK 790-059
(9) Read the appropriate instrument.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-065
Put the system back to ambient pressure.
EFFECTIVITY
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SUBTASK 080-046
CAUTION:
_______
DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE ADM CAN OCCUR.
(2)
Disconnect the test set from the adapter, P75701M2-3.
(3)
SUBTASK 080-047
Remove the adapter, P75701M2-3, from the pitot probe.
(4)
(5)
SUBTASK 860-066
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
SUBTASK 860-067
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
TASK 34-11-00-790-802
3.
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_____________________________________________________
Static
and Total Air Pressure System - Pressurization
A. General
(1) This task contains the steps to pressurize the static and total air
pressure system.
B. References
(1) AMM TASK 24-22-00-860-814 p201, Remove External Power
(2) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
(3) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701M2-3 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P75701-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
EFFECTIVITY
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(2)
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D.
33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(4) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
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Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
EFFECTIVITY
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(e)
F.
231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(f) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
Prepare for the Static and Total Air Pressure System - Pressurization
SUBTASK 730-003
CAUTION:
_______
(1)
OBEY THESE PRECAUTIONS BEFORE YOU APPLY PRESSURE TO THE PITOTSTATIC SYSTEM. IF YOU DO NOT OBEY THESE PRECAUTIONS, DAMAGE TO
THE EQUIPMENT AND INSTRUMENTS CAN OCCUR.
Obey these precautions before you apply pressure to the pitot-static
system.
(a) Supply the electrical power for the ADIRS before you make the
static or total pressure hook-ups.
(b) Keep power on until all pressure hook-ups are opened.
(c) Pressure changes must be flow controlled to prevent sudden
changes in pressure and possible damage to the air data
hardware.
(d) Keep the static pressure in the range of 3.26 to 33.31 inches
Hg.
(e) Do not permit the static pressure to be more than 28 inches Hg.
from the ambient pressure.
(f) Keep the total pressure in the range of 3.26 to 41.34 inches
Hg.
(g) When you adjust the pressure, make sure the rate of change of
altitude is less than 5,000 feet per minute.
(h) When you adjust the pressure, make sure the rate of change of
airspeed is less than 300 knots per minute.
(i) Keep the static line pressure less than the pitot line
pressure.
(j) Make sure the difference between the static and pitot line
pressure is not larger than 10 inches Hg.
(k) Make sure the autopilot system stays off during the test.
CAUTION:
_______
(l)
Make sure the pitot probe heaters stay off during the test.
CAUTION:
_______
(m)
(n)
(o)
MAKE SURE YOU DO NOT SUPPLY ELECTRICAL POWER TO THE PITOT
PROBE HEATER. THIS CAN CAUSE DAMAGE TO THE PITOT PROBE.
MAKE SURE YOU DO NOT SUPPLY ELECTRICAL POWER TO THE
PITOT-STATIC PROBE HEATER. THIS CAN CAUSE DAMAGE TO THE
PITOT-STATIC PROBE.
Make sure the pitot-static probe heaters stay off during the
test.
Connect the captain's, F/O's, and alternate static systems
together during the test.
Apply static pressure to all systems at the same time.
EFFECTIVITY
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(p)
(q)
(r)
(s)
Connect the captain's, F/O's, and alternate pitot systems
together during the test.
Apply pitot pressure to all systems at the same time.
Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
Make sure that you do these steps before installing the
adapter, P75701M2-3, on the probe:
1) Flush the adapter, P75701M2-3, with water.
NOTE:
____
(t)
(u)
(v)
(w)
Use equal parts of ethylene glycol and water when
the temperature is between 32° and -40°F.
2) Blow dry, filtered air through the adapter.
3) Wipe the probe with a damp cloth.
Make sure that the ATC transponders are in standby mode.
Make sure that the Autopilot Flight Director System is off.
Make sure that the seals used on the static ports do not extend
into the static ports.
Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
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(2)
(3)
SUBTASK 860-068
Turn the altimeter BARO knobs on the captain's EFIS control panel,
F/O's EFIS control panel, and standby altimeter through the full
range.
SUBTASK 860-069
Set the altimeter BARO knobs on the captain's EFIS control panel,
F/O's EFIS control panel, and standby altimeter to 29.92 inches of
Hg.
SUBTASK 860-070
WARNING:
_______
(4)
(5)
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
Set the ATC mode switch on the ATC control panel, P8-29, to the STBY
position.
SUBTASK 860-071
Set the AOA vanes to zero degrees.
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EFFECTIVITY
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G.
Installation of Drain Coupling, 1QF2-3-64C (Recommended)
SUBTASK 480-160
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE TAPE INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE TAPE.
(1)
(2)
(3)
Seal these primary static ports with vinyl adhesive tape, Scotch
Brand No.471:
(a) Seal the upper and lower primary static ports on the right side
of the fuselage.
(b) Seal the upper and lower primary static ports on the left side
of the fuselage.
SUBTASK 480-161
Open the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Remove the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-000-801 p401).
SUBTASK 480-162
Remove the caps from the left and right static system
NOTE:
____
(4)
(5)
drains.
The forward drain is for the left system. The aft drain is
for the right system. The forward drain is known as the No.3
Captain's Static Drain. The aft drain is known as the No.4
First Officer's Static Drain.
SUBTASK 480-163
Install the coupling, 1QF2-3-64C, on the left and right static
system drains.
SUBTASK 480-164
Connect the test set to each coupling, 1QF2-3-64C.
EFFECTIVITY
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H.
Installation of Static Port Adapter, 33410LH-125-4 (Alternate):
SUBTASK 480-165
CAUTION:
_______
(1)
Install the adapter, 33410LH-125-4, on the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
SUBTASK 480-166
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT PUSH THE TAPE INTO THE STATIC PORTS. YOU CAN CAUSE
DAMAGE TO THE STATIC SYSTEM IF YOU PUSH TAPE INTO THE STATIC
PORT.
(2)
I.
Seal the static ports at these locations with tape, Scotch Brand
No.471:
(a) The captain's static port on the left side of the fuselage.
(b) The first officer's static port on the left side of the
fuselage.
Static and Total Air Pressure System Pressurization
(1)
(2)
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INSTALL THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
J.
SUBTASK 780-001
Apply the desired pressures to the static and total air pressure
system.
SUBTASK 800-001
Stop for one minute to allow the system to stabilize.
SUBTASK 970-001
(3) Read the appropriate instrument.
Removal of Drain Coupling, 1QF2-3-64
SUBTASK 080-087
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set from each coupling, 1QF2-3-64C.
EFFECTIVITY
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(3)
SUBTASK 080-088
Disconnect each coupling, 1QF2-3-64C, from the left and right static
system drains.
SUBTASK 480-167
Install the cap on the left and right static system drains.
SUBTASK 080-089
WARNING:
_______
(4)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The two primary static ports on the right side of the fuselage.
(b)
The two primary static ports on the left side of the fuselage.
SUBTASK 480-168
Close the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Install the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-400-801 p401).
Removal of Static Port Adapter, 33410LH-125-4, (Alternate)
(5)
K.
SUBTASK 480-169
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
SUBTASK 480-170
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
EFFECTIVITY
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SUBTASK 480-171
WARNING:
_______
(3)
(4)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The captain's static port on the left side of the fuselage.
(b) The first officer's static port on the left side of the
fuselage.
SUBTASK 080-090
Removal of the Probe Adapters:
SUBTASK 080-091
CAUTION:
_______
L.
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(5) Disconnect the test set from each adapter, P75701-4.
Put the Airplane Back to Its Usual Condition
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(1)
(2)
SUBTASK 860-073
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
SUBTASK 860-074
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
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EFFECTIVITY
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STATIC AND TOTAL AIR PRESSURE SYSTEM - SERVICING
________________________________________________
1.
General
_______
A. This procedure supplies instructions for the servicing of the Static and
Total Air Pressure System.
TASK 34-11-00-170-801
2.
________________________________________________
Static
and Total Air Pressure System - Servicing
A. References
(1) AMM TASK 21-33-02-000-801 p401, Cabin Altitude and Differential
Pressure Indicator Removal
(2) AMM TASK 21-33-02-400-801 p401, Cabin Altitude and Differential
Pressure Indicator Installation
(3) AMM TASK 25-21-46-000-801 p401, Sidewall Panel Removal
(4) AMM TASK 25-21-46-400-801 p401, Sidewall Panel Installation
(5) AMM TASK 25-22-00-000-801 p401, Passenger Seat Removal
(6) AMM TASK 25-22-00-400-802 p401, Passenger Seat Installation
(7) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
(8) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
(9) AMM TASK 25-52-09-000-801 p401, Cargo Compartment Ceiling Liner
Removal
(10) AMM TASK 25-52-09-400-801 p401, Cargo Compartment Ceiling Liner
Installation
(11) AMM TASK 34-13-01-000-801 p401, Standby Altimeter/Airspeed Indicator
Removal
(12) AMM TASK 34-13-01-400-801 p401, Standby Altimeter/Airspeed Indicator
Installation
B. Equipment
(1) Air Source, Regulated, Dry Filtered, 0-150 psig
(commercially available)
(2) 1QF2-2-64A Coupling - Quick Disconnect, Pitot System Drain Line
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
C. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 121 Forward Cargo Compartment - Left
(c) 122 Forward Cargo Compartment - Right
(d) 211 Flight Compartment - Left
(e) 212 Flight Compartment - Right
(f) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(g) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
EFFECTIVITY
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D.
Prepare to Flush the Pitot-Static System
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
Flush the Left Static System
(1)
E.
(1)
SUBTASK 010-001
For the applicable passenger seats, do this task:
Removal (AMM TASK 25-22-00-000-801 p401).
(2)
SUBTASK 010-002
For the applicable sidewall panel, do this task:
Removal (AMM TASK 25-21-46-000-801 p401).
Passenger Seat
Sidewall Panel
SUBTASK 020-001
CAUTION:
_______
(3)
(4)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE STATIC SYSTEM
CAN OCCUR.
Disconnect the static hoses at these locations:
(a) The static port located at STA 410, WL 220, LBL 73
(b) The static port located at STA 410, WL 218, RBL 73.
SUBTASK 020-002
Install pressure caps on the disconnected hoses.
EFFECTIVITY
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SUBTASK 020-003
WARNING:
_______
(5)
(6)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSES ARE TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the static hoses to prevent movement.
SUBTASK 010-003
For the applicable ceiling liner in the forward cargo compartment,
do this task: Cargo Compartment Ceiling Liner Removal
(AMM TASK 25-52-09-000-801 p401).
SUBTASK 010-004
CAUTION:
_______
(7)
(8)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE FROM AN AIR DATA MODULE. IF YOU DO NOT,
DAMAGE TO THE AIR DATA MODULE CAN OCCUR.
Disconnect the static hose from the Air Data Module-Left Static
located at STA 409, WL 205, LBL 0.35.
SUBTASK 020-004
Install a pressure cap on the disconnected hose.
SUBTASK 020-005
WARNING:
_______
(9)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSE IS TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the static hose to prevent movement.
SUBTASK 480-001
CAUTION:
_______
DO NOT APPLY PRESSURE TO THE SYSTEM WHEN AN AIR DATA MODULE IS
CONNECTED TO THE SYSTEM. IF YOU DO, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
(10) Use a coupling, 1QF2-3-64C to connect the dry filtered air source,
to the left static system at drain fitting No. 3.
NOTE:
____
Drain fitting No. 3 is located at approximately STA 410,
WL180, LBL 56.
SUBTASK 420-001
(11) Remove the pressure cap from the hose located at STA 410, WL 220,
LBL 73.
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SUBTASK 170-002
(12) Apply 15 psig (103 kPa) of dry filtered air to the left static
system.
SUBTASK 170-003
(13) Make sure that you can feel air come out of the hose.
SUBTASK 170-004
(14) Continue for three minutes or more.
SUBTASK 860-002
(15) Put the system back to ambient pressure.
SUBTASK 020-050
(16) Install a pressure cap on the hose.
SUBTASK 420-002
(17) Remove the pressure cap from the hose located at STA 410, WL 218,
RBL 73.
SUBTASK 170-006
(18) Apply 15 psig (103 kPa) of dry filtered air to the left static
system.
SUBTASK 170-007
(19) Make sure that you can feel air come out of the hose.
SUBTASK 170-008
(20) Continue for three minutes or more.
SUBTASK 860-003
(21) Put the system back to ambient pressure.
SUBTASK 020-051
(22) Install a pressure cap on the hose.
SUBTASK 420-003
(23) Remove the pressure cap from the hose located at STA 409, WL 205,
LBL 0.35.
SUBTASK 170-010
(24) Apply 15 psig (103 kPa) of dry filtered air to the left static
system.
SUBTASK 170-011
(25) Make sure that you can feel air come out of the hose.
SUBTASK 170-012
(26) Continue for three minutes or more.
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SUBTASK 860-004
(27) Put the system back to ambient pressure.
SUBTASK 020-052
(28) Install a pressure cap on the hose.
SUBTASK 080-001
(29) Disconnect the dry filtered air source, from drain fitting No. 3.
SUBTASK 420-004
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE STATIC SYSTEM
CAN OCCUR.
(30) Connect the static hoses at these locations:
(a) The static port located at STA 410, WL 220, LBL 73
(b) The static port located at STA 410, WL 218, RBL 73.
SUBTASK 420-005
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE TO AN AIR DATA MODULE. IF YOU DO NOT, DAMAGE TO
THE AIR DATA MODULE CAN OCCUR.
(31) Connect the static hose to the Air Data Module-Left Static located
at STA 409, WL 205, LBL 0.35.
SUBTASK 410-001
(32) For the applicable ceiling liner in the forward cargo compartment,
do this task: Install the Sidewall Lining for the Cargo Compartment
(AMM TASK 25-52-06-400-801 p401).
SUBTASK 410-002
(33) For the applicable passenger seats, do this task:
Installation (AMM TASK 25-22-00-400-802 p401).
F.
SUBTASK 410-003
(34) For the applicable sidewall panel, do this task:
Installation (AMM TASK 25-21-46-400-801 p401).
Flush the Right Static System
(1)
SUBTASK 010-005
For the applicable passenger seats, do this task:
Removal (AMM TASK 25-22-00-000-801 p401).
(2)
SUBTASK 010-006
For the applicable sidewall panel, do this task:
Removal (AMM TASK 25-21-46-000-801 p401).
EFFECTIVITY
Passenger Seat
Sidewall Panel
Passenger Seat
Sidewall Panel
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SUBTASK 020-009
CAUTION:
_______
(3)
(4)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE STATIC SYSTEM
CAN OCCUR.
Disconnect the static hoses at these locations:
(a) The static port located at STA 410, WL 220, RBL 73
(b) The static port located at STA 410, WL 218, LBL 73.
SUBTASK 020-010
Install pressure caps on the disconnected hoses.
SUBTASK 020-011
WARNING:
_______
(5)
(6)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSES ARE TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the static hoses to prevent movement.
SUBTASK 010-007
For the applicable ceiling liner in the forward cargo compartment,
do this task: Cargo Compartment Ceiling Liner Removal
(AMM TASK 25-52-09-000-801 p401).
SUBTASK 020-012
CAUTION:
_______
(7)
(8)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE FROM AN AIR DATA MODULE. IF YOU DO NOT,
DAMAGE TO THE AIR DATA MODULE CAN OCCUR.
Disconnect the static hose from the Air Data Module-Right Static
located at STA 409, WL 205, RBL 0.35.
SUBTASK 020-013
Install a pressure cap on the disconnected hose.
SUBTASK 020-014
WARNING:
_______
(9)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSE IS TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the static hose to prevent movement.
EFFECTIVITY
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SUBTASK 480-002
CAUTION:
_______
DO NOT APPLY PRESSURE TO THE SYSTEM WHEN AN AIR DATA MODULE IS
CONNECTED TO THE SYSTEM. IF YOU DO, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
(10) Use a coupling, 1QF2-3-64C to connect the dry filtered air source,
to the right static system at drain fitting No. 4.
NOTE:
____
Drain fitting No. 4 is located at approximately STA 410,
WL180, LBL 56.
SUBTASK 420-006
(11) Remove the pressure cap from the hose located at STA 410, WL 220,
RBL 73.
SUBTASK 170-014
(12) Apply 15 psig (103 kPa) of dry filtered air to the right static
system.
SUBTASK 170-015
(13) Make sure that you can feel air come out of the hose.
SUBTASK 170-016
(14) Continue for three minutes or more.
SUBTASK 860-005
(15) Put the system back to ambient pressure.
SUBTASK 020-053
(16) Install a pressure cap on the hose.
SUBTASK 420-007
(17) Remove the pressure cap from the hose located at STA 410, WL 218,
LBL 73.
SUBTASK 170-018
(18) Apply 15 psig (103 kPa) of dry filtered air to the right static
system.
SUBTASK 170-019
(19) Make sure that you can feel air come out of the hose.
SUBTASK 170-020
(20) Continue for three minutes or more.
SUBTASK 860-006
(21) Put the system back to ambient pressure.
EFFECTIVITY
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SUBTASK 020-054
(22) Install a pressure cap on the hose.
SUBTASK 420-008
(23) Remove the pressure cap from the hose located at STA 410, WL180, LBL
56.
SUBTASK 170-022
(24) Apply 15 psig (103 kPa) of dry filtered air to the left static
system.
SUBTASK 170-023
(25) Make sure that you can feel air come out of the hose.
SUBTASK 170-024
(26) Continue for three minutes or more.
SUBTASK 860-007
(27) Put the system back to ambient pressure.
SUBTASK 020-055
(28) Install a pressure cap on the hose.
SUBTASK 080-002
(29) Disconnect the dry filtered air source, from drain fitting No. 4.
SUBTASK 420-009
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE STATIC SYSTEM
CAN OCCUR.
(30) Connect the static hoses at these locations:
(a) The static port located at STA 410, WL 220, RBL 73
(b) The static port located at STA 410, WL 218, LBL 73.
SUBTASK 420-010
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE TO AN AIR DATA MODULE. IF YOU DO NOT, DAMAGE TO
THE AIR DATA MODULE CAN OCCUR.
(31) Connect the static hose to the Air Data Module-Right Static located
at STA 409, WL 205, LBL 0.35.
SUBTASK 410-004
(32) For the applicable ceiling liner in the forward cargo compartment,
do this task: Cargo Compartment Ceiling Liner Installation
(AMM TASK 25-52-09-400-801 p401).
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SUBTASK 410-005
(33) For the applicable sidewall panel, do this task:
Installation (AMM TASK 25-21-46-400-801 p401).
G.
SUBTASK 410-006
(34) For the applicable passenger seats, do this task:
Installation (AMM TASK 25-22-00-400-802 p401).
Flush the Alternate Static System
(1)
Sidewall Panel
Passenger Seat
SUBTASK 010-008
For the applicable sidewall liners in the forward cargo compartment,
do this task: Remove the Sidewall Lining for the Cargo Compartment
(AMM TASK 25-52-06-000-801 p401).
SUBTASK 020-018
CAUTION:
_______
(2)
(3)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE STATIC SYSTEM
CAN OCCUR.
Disconnect the static hoses at these locations:
(a) The static port at STA 430, WL 167, LBL 49
(b) The static port at STA 430, WL 167, RBL 49.
SUBTASK 020-019
Install pressure caps on the disconnected hoses.
SUBTASK 020-020
WARNING:
_______
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSES ARE TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
(4)
Temporarily attach the static hoses to prevent movement.
(5)
SUBTASK 020-021
Do this task: Cabin Altitude and Differential Pressure Indicator
Removal (AMM TASK 21-33-02-000-801 p401).
(6)
SUBTASK 020-022
Install a pressure cap on the disconnected hose.
SUBTASK 020-023
WARNING:
_______
(7)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSE IS TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the static hose to prevent movement.
EFFECTIVITY
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(8)
SUBTASK 010-009
Remove the standby altitude/airspeed indicator. To remove the
standby altitude/airspeed indicator, do this task: Standby
Altimeter/Airspeed Indicator Removal
(AMM TASK 34-13-01-000-801 p401).
SUBTASK 020-024
WARNING:
_______
(9)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSE IS TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the static hose to prevent movement.
SUBTASK 480-003
CAUTION:
_______
DO NOT APPLY PRESSURE TO THE SYSTEM WHEN AN AIR DATA INSTRUMENT
IS CONNECTED TO THE SYSTEM. IF YOU DO, DAMAGE TO THE AIR DATA
INSTRUMENT CAN OCCUR.
(10) Use a coupling, 1QF2-3-64C to connect the dry filtered air source,
to the alternate static system at drain fitting No. 5.
NOTE:
____
Drain fitting No. 5 is located at approximately STA 226, WL
155, RBL 18.
SUBTASK 420-011
(11) Remove the pressure cap from the hose located at STA 430, WL 167,
LBL 49.
SUBTASK 170-026
(12) Apply 15 psig (103 kPa) of dry filtered air to the alternate static
system.
SUBTASK 170-027
(13) Make sure that you can feel air come out of the hose.
SUBTASK 170-028
(14) Continue for three minutes or more.
SUBTASK 860-008
(15) Put the system back to ambient pressure.
SUBTASK 020-056
(16) Install a pressure cap on the hose.
SUBTASK 420-012
(17) Remove the pressure cap from the hose located at STA 430, WL 167,
RBL 49.
EFFECTIVITY
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SUBTASK 170-030
(18) Apply 15 psig (103 kPa) of dry filtered air to the alternate static
system.
SUBTASK 170-031
(19) Make sure that you can feel air come out of the hose.
SUBTASK 170-032
(20) Continue for three minutes or more.
SUBTASK 860-009
(21) Put the system back to ambient pressure.
SUBTASK 020-057
(22) Install a pressure cap on the hose.
SUBTASK 420-013
(23) Remove the pressure cap from the hose located at STA 220, Wl 260,
RBL 3.
SUBTASK 170-034
(24) Apply 15 psig (103 kPa) of dry filtered air to the alternate static
system.
SUBTASK 170-035
(25) Make sure that you can feel air come out of the hose.
SUBTASK 170-036
(26) Continue for three minutes or more.
SUBTASK 860-010
(27) Put the system back to ambient pressure.
SUBTASK 020-058
(28) Install a pressure cap on the hose.
SUBTASK 420-014
(29) Remove the pressure cap from the hose located in the flight
compartment.
SUBTASK 170-038
(30) Apply 15 psig (103 kPa) of dry filtered air to the alternate static
system.
SUBTASK 170-039
(31) Make sure that you can feel air come out of the hose.
SUBTASK 170-040
(32) Continue for three minutes or more.
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SUBTASK 860-011
(33) Put the system back to ambient pressure.
SUBTASK 020-059
(34) Install a pressure cap on the hose.
SUBTASK 080-003
(35) Disconnect the dry filtered air source, from drain fitting No. 5.
SUBTASK 420-015
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE STATIC SYSTEM CAN
OCCUR.
(36) Connect the static hoses at these locations:
(a) The static port located at STA 430, WL 167, LBL 49
(b) The static port located at STA 430, WL 167, RBL 49.
SUBTASK 410-007
(37) For the applicable ceiling liner in the forward cargo compartment,
do this task: Cargo Compartment Ceiling Liner Installation
(AMM TASK 25-52-09-400-801 p401).
SUBTASK 420-016
(38) Do this task: Cabin Altitude and Differential Pressure Indicator
Installation (AMM TASK 21-33-02-400-801 p401).
SUBTASK 410-008
(39) To install the standby altitude/airspeed indicator, do this task:
Standby Altimeter/Airspeed Indicator Installation
(AMM TASK 34-13-01-400-801 p401).
SUBTASK 410-009
(40) For the applicable sidewall panel, do this task:
Installation (AMM TASK 25-21-46-400-801 p401).
H.
SUBTASK 410-010
(41) For the applicable passenger seats, do this task:
Installation (AMM TASK 25-22-00-400-802 p401).
Flush the Left Pitot System
Sidewall Panel
Passenger Seat
SUBTASK 020-029
CAUTION:
_______
(1)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Disconnect the pitot hose from the pitot probe located at STA 192,
WL 225, LBL 34.
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SUBTASK 020-030
CAUTION:
_______
(2)
(3)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Disconnect the pitot hose from the Air Data Module-Left Pitot
located at STA 200, WL 175, LBL 13.
SUBTASK 020-031
Install pressure caps on the disconnected hoses.
SUBTASK 020-032
WARNING:
_______
(4)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSES ARE TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the pitot hoses to prevent movement.
SUBTASK 480-004
CAUTION:
_______
(5)
DO NOT APPLY PRESSURE TO THE SYSTEM WHEN AN AIR DATA MODULE IS
CONNECTED TO THE SYSTEM. IF YOU DO, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Use a coupling, 1QF2-2-64A to connect the dry filtered air source,
to the left pitot system at drain fitting No. 1.
NOTE:
____
Drain fitting No. 1 is located at STA 210, WL 171, LBL 15.
(6)
SUBTASK 420-017
Remove the pressure cap from the hose located at STA 192, WL 225,
LBL 34.
(7)
SUBTASK 170-043
Apply 15 psig (103 kPa) of dry filtered air to the left pitot
system.
(8)
SUBTASK 170-044
Make sure that you can feel air come out of the hose.
(9)
SUBTASK 170-045
Continue for three minutes or more.
SUBTASK 860-012
(10) Put the system back to ambient pressure.
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SUBTASK 020-060
(11) Install a pressure cap on the hose.
SUBTASK 420-018
(12) Remove the pressure cap from the hose located at STA 200, WL 175,
LBL 13.
SUBTASK 170-047
(13) Apply 15 psig (103 kPa) of dry filtered air to the left pitot
system.
SUBTASK 170-048
(14) Make sure that you can feel air come out of the hose.
SUBTASK 170-049
(15) Continue for three minutes or more.
SUBTASK 860-013
(16) Put the system back to ambient pressure.
SUBTASK 020-061
(17) Install a pressure cap on the hose.
SUBTASK 080-004
(18) Disconnect the dry filtered air source, from drain fitting No. 1.
SUBTASK 420-019
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA MODULE
CAN OCCUR.
(19) Connect the pitot hose to the pitot probe located at STA 192, WL
225, LBL 34.
SUBTASK 420-020
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA MODULE
CAN OCCUR.
(20) Connect the pitot hose to the Air Data Module-Left Pitot located at
STA 200, WL 175, LBL 13.
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I.
Flush the Right Pitot System
SUBTASK 020-035
CAUTION:
_______
(1)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Disconnect the pitot hose from the pitot probe located at STA 192,
WL 224, RBL 34.
SUBTASK 020-036
CAUTION:
_______
(2)
(3)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Disconnect the pitot hose from the Air Data Module-Right Pitot
located at STA 200, WL 177, RBL 18.
SUBTASK 020-037
Install pressure caps on the disconnected hoses.
SUBTASK 020-038
WARNING:
_______
(4)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSES ARE TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the pitot hoses to prevent movement.
SUBTASK 480-005
CAUTION:
_______
(5)
DO NOT APPLY PRESSURE TO THE SYSTEM WHEN AN AIR DATA MODULE IS
CONNECTED TO THE SYSTEM. IF YOU DO, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Use a coupling, 1QF2-2-64A to connect the dry filtered air source,
to the right pitot hose at drain fitting No. 2.
NOTE:
____
(6)
(7)
Drain fitting No. 2 is located at STA 204, WL 171, RBL 15.
SUBTASK 420-021
Remove the pressure cap from the hose located at STA 192, WL 224,
RBL 34.
SUBTASK 170-052
Apply 15 psig of dry filtered air to the right pitot system.
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(8)
SUBTASK 170-053
Make sure that you can feel air come out of the hose.
(9)
SUBTASK 170-054
Continue for three minutes or more.
SUBTASK 860-014
(10) Put the system back to ambient pressure.
SUBTASK 020-062
(11) Install a pressure cap on the hose.
SUBTASK 420-022
(12) Remove the pressure cap from the hose located at STA 200, WL 177,
RBL 18.
SUBTASK 170-056
(13) Apply 15 psig (103 kPa) of dry filtered air to the right pitot
system.
SUBTASK 170-057
(14) Make sure that you can feel air come out of the hose.
SUBTASK 170-058
(15) Continue for three minutes or more.
SUBTASK 860-015
(16) Put the system back to ambient pressure.
SUBTASK 020-063
(17) Install a pressure cap on the hose.
SUBTASK 080-005
(18) Disconnect the dry filtered air source, from drain fitting No. 2.
SUBTASK 420-023
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA MODULE
CAN OCCUR.
(19) Connect the pitot hose to the pitot probe located at STA 192, WL
224, RBL 34.
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SUBTASK 420-024
CAUTION:
_______
J.
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA MODULE
CAN OCCUR.
(20) Connect the pitot hose to the Air Data Module-Right Pitot located at
STA 200, WL 177, RBL 18.
Flush the Alternate Pitot System
SUBTASK 020-041
CAUTION:
_______
(1)
(2)
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
DISCONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA
MODULE CAN OCCUR.
Disconnect the pitot hose from the pitot probe located at STA 192,
WL 213, RBL 34.
SUBTASK 020-042
Install a pressure cap on the disconnected hose.
SUBTASK 020-043
WARNING:
_______
(3)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSE IS TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the pitot hose to prevent movement.
SUBTASK 010-010
WARNING:
_______
(4)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSES ARE TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Remove the standby altitude/airspeed indicator. To remove the
standby altitude/airspeed indicator, do this task: Standby
Altimeter/Airspeed Indicator Removal
(AMM TASK 34-13-01-000-801 p401).
SUBTASK 020-044
WARNING:
_______
(5)
YOU MUST MAKE SURE THAT THE DISCONNECTED HOSE IS TEMPORARILY
ATTACHED TO PREVENT MOVEMENT. IF YOU DO NOT, INJURY TO PERSONS
AND DAMAGE TO EQUIPMENT CAN OCCUR.
Temporarily attach the pitot hose to prevent movement.
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SUBTASK 480-006
CAUTION:
_______
(6)
(7)
DO NOT APPLY PRESSURE TO THE SYSTEM WHEN AN AIR DATA INSTRUMENT
IS CONNECTED TO THE SYSTEM. IF YOU DO, DAMAGE TO THE AIR DATA
INSTRUMENT CAN OCCUR.
Connect the dry filtered air source, to the alternate pitot hose
located at STA 192, WL 213, RBL 34.
SUBTASK 170-060
Apply 15 psig (103 kPa) of dry filtered air to the alternate pitot
system.
(8)
SUBTASK 170-061
Make sure that you can feel air come out of the hose.
(9)
SUBTASK 170-062
Continue for three minutes or more.
SUBTASK 860-016
(10) Put the system back to ambient pressure.
SUBTASK 020-064
(11) Install a pressure cap on the hose.
SUBTASK 170-063
(12) Apply 10 psig (69 kPa) of dry filtered air to the alternate pitot
system.
SUBTASK 170-064
(13) Make sure that you can feel air come out of the other disconnected
hose.
SUBTASK 170-065
(14) Continue for three minutes or more.
SUBTASK 860-017
(15) Put the system back to ambient pressure.
SUBTASK 080-006
(16) Disconnect the dry filtered air source, from the alternate pitot
hose located at STA 192, WL 213, RBL 34.
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SUBTASK 420-025
CAUTION:
_______
MAKE SURE THAT THE SYSTEM IS AT AMBIENT PRESSURE BEFORE YOU
CONNECT A HOSE. IF YOU DO NOT, DAMAGE TO THE AIR DATA MODULE
CAN OCCUR.
(17) Connect the pitot hose to the pitot probe located at STA 192, WL
213, RBL 34.
K.
SUBTASK 410-011
(18) To install the standby altitude/airspeed indicator, do this task:
Standby Altimeter/Airspeed Indicator Installation
(AMM TASK 34-13-01-400-801 p401).
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-018
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 730-001
Do this task: (Reference TBD).
TASK 34-11-00-210-801
3.
____________________________________________
Pitot
System - Detailed Inspection of Drains
A. References
(1) AMM TASK 34-11-00-170-801 p301, Static and Total Air Pressure System
- Servicing
B. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 121 Forward Cargo Compartment - Left
(c) 122 Forward Cargo Compartment - Right
EFFECTIVITY
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(d)
(e)
(f)
(g)
C.
211 Flight Compartment - Left
212 Flight Compartment - Right
231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
Procedure
(1)
(2)
SUBTASK 210-001
Do a detailed inspection for moisture for the Captains and First
Officers pitot system drains.
SUBTASK 680-001
If you find moisture in at least one of the locations above, do this
task: Static and Total Air Pressure System - Servicing
(AMM TASK 34-11-00-170-801 p301).
TASK 34-11-00-210-802
4.
_____________________________________________
Static
System - Detailed Inspection of Drains
A. References
(1) AMM TASK 34-11-00-170-801 p301, Static and Total Air Pressure System
- Servicing
B. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 121 Forward Cargo Compartment - Left
(c) 122 Forward Cargo Compartment - Right
(d) 211 Flight Compartment - Left
(e) 212 Flight Compartment - Right
(f) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(g) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
C. Procedure
(1)
(2)
SUBTASK 210-002
Do a detailed inspection for moisture in the static system drains
for these systems:
(a) Alternate Static System
(b) First Officers Static System
(c) Captains Static System
SUBTASK 680-002
If you find moisture in at least one of the locations above, do this
task: Static and Total Air Pressure System - Servicing
(AMM TASK 34-11-00-170-801 p301).
EFFECTIVITY
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STATIC AND TOTAL AIR PRESSURE SYSTEM - ADJUSTMENT/TEST
______________________________________________________
1.
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General
_______
A. This procedure has these tasks:
(1) Left Static System Leak Test
(2)
Right Static System Leak Test
(3)
Alternate Static System Leak Test
(4)
(5)
(6)
(7)
(8)
(9)
Left Pitot System Leak Test
Right Pitot System Leak Test
Alternate Pitot System Leak Test
Left Static System Full-range Leak Test
Right Static System Full-range Leak Test
Alternate Static System Full-range Leak Test
TASK 34-11-00-790-804
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2.
____________________________
Left
Static System Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that the ATC transponders are in standby mode.
(e) Make sure that the Autopilot Flight Director System is off.
(f) Make sure that the seals used on the static ports do not extend
into the static ports.
(g) Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
(h) You must do the static system low-range leak test when you
remove a fitting other than a quick disconnect. You must do
the low-range leak test after you flush the pitot-static
system.
(i) The static system full-range leak test is not required.
However, leaks are easier to detect with the higher pressure.
(j) You can use either the drain coupling or the static port
adapter to pressurize the static system. The drain adapter is
recommended and the static port adapter is alternate.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
(3) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
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(4)
C.
D.
E.
AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
Equipment
(1) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(2) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
EFFECTIVITY
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(e)
F.
231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(f) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
Prepare for the Leak Tests
SUBTASK 860-075
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(1)
Make sure that the ATC transponders are in standby mode.
(2)
SUBTASK 860-076
Make sure that the Autopilot Flight Director System is off.
(3)
(4)
SUBTASK 860-077
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-078
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
EFFECTIVITY
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CAPTAIN'S STATIC
PORT - LEFT
STATIC SYSTEM
FIRST OFFICER'S
STATIC PORT - RIGHT
STATIC SYSTEM
CAPTAIN'S PITOT
PROBE - LEFT
PITOT SYSTEM
ELECTRONIC EQUIPMENT
COMPARTMENT ACCESS
DOOR, 117A
SEE
LEFT ALTERNATE
STATIC PORT
A
FIRST OFFICER'S
PITOT PROBE - RIGHT
PITOT SYSTEM
FIRST OFFICER'S
STATIC PORT - RIGHT
STATIC SYSTEM
CAPTAIN'S STATIC
PORT - LEFT
STATIC SYSTEM
FORWARD CARGO
COMPARTMENT
SEE
B
FORWARD
CARGO
DOOR
RIGHT
ALTERNATE
STATIC PORT
ALTERNATE PITOT
PROBE - ALTERNATE
PITOT SYSTEM
Pitot Static Leakage Test
Figure 501 (Sheet 1)
L33820
34-11-00-990-801
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E5 RACK
FWD
NO. 5
ALTERNATE
STATIC
DRAIN
ELECTRONIC
EQUIPMENT
ACCESS DOOR,
117A
ELECTRONIC EQUIPMENT COMPARTMENT
A
LEFT SIDEWALL
LINING
FWD
RIGHT SYSTEM DRAIN
(NO. 4 FIRST OFFICER'S
STATIC DRAIN)
LEFT SYSTEM DRAIN
(NO. 3 CAPTAIN'S
STATIC DRAIN)
DRAIN ACCESS
PANEL REMOVED
FORWARD CARGO COMPARTMENT
B
Pitot Static Leakage Test
Figure 501 (Sheet 2)
L33638
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SUBTASK 860-079
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Left Static System Leak Test
(5)
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G.
SUBTASK 480-092
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WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE SEAL.
(1)
Seal these primary static ports with vinyl adhesive tape, Scotch
Brand No.471.
(a) Seal the lower static port on the right side of the fuselage.
NOTE:
____
(b)
Seal the upper static port on the left side of the fuselage.
NOTE:
____
(2)
(3)
This port is marked CAPTAIN.
This port is marked CAPTAIN.
SUBTASK 480-093
Open the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Remove the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-000-801 p401).
SUBTASK 480-094
Remove the cap from the left system static drain.
NOTE:
____
The forward drain is for the left system. The aft drain is
for the right system. The forward drain is known as the No.3
Captain's Static Drain. The aft drain is known as the No.4
First Officer's Static Drain.
(4)
SUBTASK 480-095
Install the coupling, 1QF2-3-64C, on the left system static drain.
(5)
SUBTASK 480-096
Connect the test set to the coupling, 1QF2-3-64C.
SUBTASK 790-060
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CAUTION:
_______
(6)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set to apply a vacuum to the static system equal to
5,000 feet of altitude above field elevation (ambient pressure minus
5.25 | 0.25 in. Hg).
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(7)
(8)
(9)
SUBTASK 790-061
When the system reaches 5,000 feet above field elevation, stop for
one minute to allow the system to stabilize.
SUBTASK 790-062
Set the test set for the leak check.
SUBTASK 790-063
Make sure the altitude does not decrease more than 80 feet (0.07 in.
Hg) in one minute.
SUBTASK 860-080
(10) Put the system back to ambient pressure.
SUBTASK 080-053
CAUTION:
_______
DO NOT DISCONNECT THE STATIC SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE AIR DATA MODULE (ADM) CAN OCCUR.
(11) Disconnect the test set and the coupling, 1QF2-3-64C, from the left
system static drain.
SUBTASK 480-097
(12) Install the cap on the left system static drain.
SUBTASK 080-054
EFFECTIVITY
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WARNING:
_______
FAILURE TO REMOVE THE VINYL ADHESIVE TAPE FROM THE STATIC PORTS
BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PLUG OR DEFORM THE HOLES IN THE PORT. MAKE SURE THAT
YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE STATIC PORTS.
THE SURFACE OF THE PORT MUST BE SMOOTH AND CLEAN. IF YOU DO
NOT, THE SYSTEM WILL NOT OPERATE CORRECTLY.
(13) Remove the vinyl adhesive tape, Scotch Brand No.471 from both of
these primary static ports.
(a) Remove the vinyl adhesive tape from the lower static port on
the right side of the fuselage.
(b) Remove the vinyl adhesive tape from the upper static port on
the left side of the fuselage.
H.
SUBTASK 480-098
(14) Close the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Install the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-400-801 p401).
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-081
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-082
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
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EFFECTIVITY
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TASK 34-11-00-790-806
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3.
_____________________________
Right
Static System Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that the ATC transponders are in standby mode.
(e) Make sure that the Autopilot Flight Director System is off.
(f) Make sure that the seals used on the static ports do not extend
into the static ports.
(g) Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
(h) You must do the static system low-range leak test when you
remove a fitting other than a quick disconnect. You must do
the low-range leak test after you flush the pitot-static
system.
(i) The static system full-range leak test is not required.
However, leaks are easier to detect with the higher pressure.
(j) You can use either the drain coupling or the static port
adapter to pressurize the static system. The drain adapter is
recommended and the static port adapter is alternate.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
(3) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
(4) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) 33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
EFFECTIVITY
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(4)
D.
E.
Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(e) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(f) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
EFFECTIVITY
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F.
Prepare for the Leak Tests
SUBTASK 860-091
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(1)
Make sure that the ATC transponders are in standby mode.
(2)
SUBTASK 860-092
Make sure that the Autopilot Flight Director System is off.
(3)
(4)
(5)
SUBTASK 860-093
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-094
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-095
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
EFFECTIVITY
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G.
Right Static System Leak Test
SUBTASK 480-106
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE SEAL.
(1)
Seal these two primary static ports with vinyl adhesivetape, Scotch
Brand No.471.
(a) Seal the lower static port on the left side of the fuselage.
NOTE:
____
(b)
Seal the upper static port on the right side of the fuselage.
NOTE:
____
(2)
(3)
(4)
This port is marked FIRST OFFICER.
SUBTASK 480-107
Open the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Remove the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-000-801 p401).
SUBTASK 480-108
Remove the cap from the right system static drain.
NOTE:
____
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This port is marked FIRST OFFICER.
The forward drain is for the left system. The aft drain is
for the right system. The forward drain is known as the No.3
Captain's Static Drain. The aft drain is known as the No.4
First Officer's Static Drain.
SUBTASK 400-001
For installation of the adapter, 33410LH-125-4 (Alternate), do these
steps:
EFFECTIVITY
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SUBTASK 480-172
CAUTION:
_______
(a)
INSTALL THE adapter, 33410LH-125-4, SLOWLY AND CAREFULLY.
THE ADAPTER CAN COUSE SCRATCHES ON THE STATIC PORT, WHICH
CAN CAUSE FALSE ALTITUDE READINGS.
Install the adapter, 33410LH-125-4, (Alternate) on the static
ports at these locations:
1) The captain's static port on the right side of the
fuselage.
2) The first officer's static port on the right side of the
fuselage.
SUBTASK 400-002
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT
CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO OBSERVE
AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY
CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PUSH THE TAPE INTO THE STATIC PORTS. YOU CAN DAMAGE
THE STATIC SYSTEM IF YOU PUSH TAPE INTO THE STATIC PORT.
(b)
(5)
Seal the static ports at these locations with tape, Scotch
Brand No.471:
1) The captain's static port on the left side of the fuselage.
2) The first officer's static port on the right side of the
fuselage.
SUBTASK 400-003
For installation of the coupling, 1QF2-3-64C (Alternate), do these
steps:
(6)
SUBTASK 480-109
Install the coupling, 1QF2-3-64C, on the right system static drain.
(7)
SUBTASK 480-110
Connect the test set, to the coupling, 1QF2-3-64C.
SUBTASK 790-068
EFFECTIVITY
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CAUTION:
_______
(8)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set, to apply a vacuum to the static system equal
to 5,000 feet of altitude above field elevation (ambient pressure
minus 5.25 | 0.25 in. Hg).
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(9)
SUBTASK 790-069
When the system reaches 5,000 feet above field elevation, stop for
one minute to allow the system to stabilize.
SUBTASK 790-070
(10) Set the test set for the leak check.
SUBTASK 790-071
(11) Make sure the altitude does not decrease more than 80 feet (0.07 in.
Hg) in one minute.
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H.
SUBTASK 860-096
(12) Put the system back to ambient pressure.
Removal of Drain Coupling, 1QF2-3-64:
SUBTASK 080-092
CAUTION:
_______
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1)
Disconnect the test set from each coupling, 1QF2-3-64C.
(2)
SUBTASK 080-093
Disconnect each coupling, 1QF2-3-64C, from the left and right static
system drains.
(3)
SUBTASK 480-173
Install the cap on the left and right static system drains.
SUBTASK 080-094
WARNING:
_______
(4)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The two primary static ports on the right side of the fuselage.
(b)
The two primary static ports on the left side of the fuselage.
EFFECTIVITY
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SUBTASK 480-174
Close the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Install the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-400-801 p401).
Removal of Static Port Adapter, 33410LH-125-4, (Alternate):
(5)
I.
SUBTASK 480-175
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
SUBTASK 480-176
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
SUBTASK 480-177
WARNING:
_______
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
(3)
J.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The captain's static port on the left side of the fuselage.
(b) The first officer's static port on the left side of the
fuselage.
Removal of the Probe Adapters:
SUBTASK 080-095
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set from each adapter, P75701-4.
SUBTASK 080-057
EFFECTIVITY
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CAUTION:
_______
(2)
(3)
DO NOT DISCONNECT THE STATIC SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, and the coupling, 1QF2-3-64C, from the
right system static drain.
SUBTASK 840-038
Install the cap on the right system static drain.
SUBTASK 080-058
WARNING:
_______
FAILURE TO REMOVE THE VINYL ADHESIVE TAPE FROM THE STATIC PORTS
BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PLUG OR DEFORM THE HOLES IN THE PORT. MAKE SURE THAT
YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE STATIC PORTS.
THE SURFACE OF THE PORT MUST BE SMOOTH AND CLEAN. IF YOU DO
NOT, THE SYSTEM WILL NOT OPERATE CORRECTLY.
(4)
Remove the vinyl adhesive tape, Scotch Brand No.471 from both of
these primary static ports.
(a) Remove the vinyl adhesive tape from the lower static port on
the left side of the fuselage.
(b) Remove the vinyl adhesive tape from the upper static port on
the right side of the fuselage.
SUBTASK 480-111
Close the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Install the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-400-801 p401).
Put the Airplane Back to Its Usual Condition
(5)
K.
(1)
SUBTASK 860-097
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
EFFECTIVITY
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(c)
(d)
(e)
(2)
Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-098
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
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TASK 34-11-00-790-808
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4.
_________________________________
Alternate
Static System Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that the ATC transponders are in standby mode.
(e) Make sure that the Autopilot Flight Director System is off.
(f) Make sure that the seals used on the static ports do not extend
into the static ports.
(g) Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
(h) You must do the static system low-range leak test when you
remove a fitting other than a quick disconnect. You must do
the low-range leak test after you flush the pitot-static
system.
(i) The static system full-range leak test is not required.
However, leaks are easier to detect with the higher pressure.
(j) You can use either the drain coupling or the static port
adapter to pressurize the static system. The drain adapter is
recommended and the static port adapter is alternate.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
(3) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
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(b)
D.
P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) 33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(4) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
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E.
F.
Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 121 Forward Cargo Compartment - Left
(c) 122 Forward Cargo Compartment - Right
(d) 211 Flight Compartment - Left
(e) 212 Flight Compartment - Right
(f) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(g) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
Prepare for the Leak Tests
SUBTASK 860-107
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(1)
Make sure that the ATC transponders are in standby mode.
(2)
SUBTASK 860-108
Make sure that the Autopilot Flight Director System is off.
(3)
(4)
SUBTASK 860-109
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-110
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
EFFECTIVITY
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SUBTASK 860-111
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Alternate Static System Leak Test
(5)
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SUBTASK 480-118
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE SEAL.
(1)
Seal the two alternate static ports with vinyl adhesive tape, Scotch
Brand No.471 at these locations:
(a) The alternate static port on the right side of the fuselage.
NOTE:
____
(b)
This port is marked ALTERNATE.
The alternate static port on the left side of the fuselage.
NOTE:
____
(2)
SUBTASK 480-119
Remove the cap from the alternate static drain, in the electronic
equipment compartment, below the E-5 rack.
NOTE:
____
(a)
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(3)
This port is marked ALTERNATE.
This drain is known as the No.5 alternate static drain.
Get access to the drain in the electronic equipment compartment
through the Electronic Equipment Access Door, 117A.
SUBTASK 400-004
For installation of the adapter, 33410LH-125-4 (Alternate), do these
steps:
SUBTASK 480-178
CAUTION:
_______
(a)
INSTALL THE adapter, 33410LH-125-4, SLOWLY AND CAREFULLY.
THE ADAPTER CAN COUSE SCRATCHES ON THE STATIC PORT, WHICH
CAN CAUSE FALSE ALTITUDE READINGS.
Install the adapter, 33410LH-125-4, (Alternate) on the
alternate static port.
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SUBTASK 400-005
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT
CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO OBSERVE
AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY
CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PUSH THE TAPE INTO THE STATIC PORTS. YOU CAN DAMAGE
THE STATIC SYSTEM IF YOU PUSH TAPE INTO THE STATIC PORT.
(b)
(4)
Seal the alternate static port with tape, Scotch Brand No.471:
SUBTASK 400-006
For installation of the coupling, 1QF2-3-64C (Recommended), do these
steps:
(5)
SUBTASK 480-120
Install the coupling, 1QF2-3-64C, on the alternate static drain.
(6)
SUBTASK 480-121
Connect the test set, to the coupling, 1QF2-3-64C.
(7)
SUBTASK 790-076
Operate the test set, to apply a vacuum to the static system equal
to 5,000 feet of altitude above field elevation (ambient pressure
minus 5.25 | 0.25 in. Hg).
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(8)
(9)
SUBTASK 790-077
When the system reaches 5,000 feet above field elevation, stop for
one minute to allow the system to stabilize.
SUBTASK 790-078
Set the test set for the leak check.
SUBTASK 790-079
(10) Make sure the altitude does not decrease more than 80 feet (0.07 in.
Hg) in one minute.
SUBTASK 860-112
(11) Put the system back to ambient pressure.
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H.
Removal of Drain Coupling, 1QF2-3-64:
SUBTASK 080-096
CAUTION:
_______
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1)
Disconnect the test set from each coupling, 1QF2-3-64C.
(2)
SUBTASK 080-097
Disconnect each coupling, 1QF2-3-64C, from the alternate static
system drain.
(3)
SUBTASK 480-179
Install the cap on the alternate static system drains.
SUBTASK 080-098
WARNING:
_______
(4)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
Remove the tape, Scotch Brand No.471, from the alternate static
port.
SUBTASK 480-180
Close the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Install the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-400-801 p401).
Removal of Static Port Adapter, 33410LH-125-4, (Alternate):
(5)
I.
SUBTASK 480-181
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
SUBTASK 480-182
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the alternate static port.
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SUBTASK 480-183
WARNING:
_______
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
(3)
J.
Remove the tape, Scotch Brand No.471, from the alternate static
port.
Removal of the Probe Adapters:
SUBTASK 080-099
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set from each adapter, P75701-4.
SUBTASK 080-061
CAUTION:
_______
(2)
(3)
DO NOT DISCONNECT THE STATIC SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE STANDBY ALTIMETER/AIRSPEED INDICATOR CAN OCCUR.
Disconnect the test set, and the coupling, 1QF2-3-64C from the
alternate static drain.
SUBTASK 080-062
Install the cap on the alternate static drain.
(a) Close the Electronic Equipment Access Door, 117A.
SUBTASK 080-063
WARNING:
_______
FAILURE TO REMOVE THE VINYL ADHESIVE TAPE FROM THE STATIC PORTS
BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PLUG OR DEFORM THE HOLES IN THE PORT. MAKE SURE THAT
YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE STATIC PORTS.
THE SURFACE OF THE PORT MUST BE SMOOTH AND CLEAN. IF YOU DO
NOT, THE SYSTEM WILL NOT OPERATE CORRECTLY.
(4)
Remove the vinyl adhesive tape, Scotch Brand No.471 from both of the
alternate static ports.
(a) Remove the vinyl adhesive tape from the alternate static port
on the right side of the fuselage.
(b) Remove the vinyl adhesive tape from the alternate static port
on the left side of the fuselage.
EFFECTIVITY
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K.
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-113
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-114
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
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TASK 34-11-00-790-810
5.
___________________________
Left
Pitot System Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a pitot system, the rate must not be
more than 300 knots for each minute.
(b) When you release pressure from a pitot system, the rate must
not be more than 300 knots for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that you prepare the adapter, P75701M2-3 before you
install the adapter on the pitot probe.
(e) Make sure that the ATC transponders are in standby mode.
(f) Make sure that the Autopilot Flight Director System is off.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701M2-3 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
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(b)
D.
E.
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P75701-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
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F.
Prepare for the Leak Tests
SUBTASK 860-123
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(1)
Make sure that the ATC transponders are in standby mode.
(2)
SUBTASK 860-124
Make sure that the Autopilot Flight Director System is off.
(3)
(4)
SUBTASK 860-125
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-126
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-127
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Left Pitot System Leak Test
(5)
G.
(1)
SUBTASK 860-128
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
EFFECTIVITY
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(2)
SUBTASK 170-076
Prepare the adapter, P75701M2-3 before you install the adapter on
the pitot probe.
CAUTION:
_______
(a)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER
WITH WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE.
DAMAGE TO THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter with water.
NOTE:
____
(b)
(3)
Use equal parts of water and ethylene glycol when the
temperature is between 32°F and -40°F (-40°C to 0°C).
Blow dry filtered air through the adapter.
SUBTASK 480-129
Wipe the pitot probe with a damp cloth, BMS15-5.
SUBTASK 480-130
CAUTION:
_______
(4)
(5)
MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
Install the adapter, P75701M2-3, on the pitot probe on the left side
of the forward fuselage.
SUBTASK 480-131
Connect the test set, to the adapter, P75701M2-3.
SUBTASK 790-084
CAUTION:
_______
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(6)
(7)
(8)
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(9)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set, to apply pressure of 4.53 |0.16 inches Hg
(gauge), (2.22 |0.08 psig) (153.4 |5.4 mB), or 300 |5 knots on the
airspeed indicator.
SUBTASK 790-085
When the test pressure is reached, stop for one minute to allow the
system to stabilize.
SUBTASK 790-086
Set the test set for the leak check.
SUBTASK 790-087
Make sure the pressure does not decrease more than 0.16 inches Hg
(5.4 mB) (approximately 5 knots) in one minute.
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SUBTASK 860-129
(10) Put the system back to ambient pressure.
SUBTASK 080-069
CAUTION:
_______
DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(11) Disconnect the test set, from the adapter, P75701M2-3.
SUBTASK 080-070
(12) Remove the adapter, P75701M2-3, from the pitot probe.
H.
SUBTASK 860-130
(13) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-131
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C2
HEATERS TEMP PROBE
2) 18C3
HEATERS ALPHA VANE LEFT
3) 18D3
HEATERS ALPHA VANE RIGHT
4) 18D5
HEATERS F/O PITOT
5) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-132
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
EFFECTIVITY
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TASK 34-11-00-790-811
6.
____________________________
Right
Pitot System Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a pitot system, the rate must not be
more than 300 knots for each minute.
(b) When you release pressure from a pitot system, the rate must
not be more than 300 knots for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that you prepare the adapter, P75701M2-3 before you
install the adapter on the pitot probe.
(e) Make sure that the ATC transponders are in standby mode.
(f) Make sure that the Autopilot Flight Director System is off.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701M2-3 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P75701-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
EFFECTIVITY
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(f)
D.
E.
F.
6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
Prepare for the Leak Tests
SUBTASK 860-133
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(1)
Make sure that the ATC transponders are in standby mode.
(2)
SUBTASK 860-134
Make sure that the Autopilot Flight Director System is off.
(3)
(4)
SUBTASK 860-135
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-136
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
EFFECTIVITY
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(c)
(d)
(e)
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-137
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Right Pitot System Leak Test
(5)
G.
(1)
(2)
SUBTASK 860-138
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-3:
1) 18D5
HEATERS F/O PITOT
SUBTASK 170-077
Prepare the adapter, P75701M2-3 before you install the adapter on
the pitot probe:
CAUTION:
_______
(a)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER
WITH WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE.
DAMAGE TO THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter with water.
NOTE:
____
(b)
(3)
Use equal parts of water and ethylene glycol when the
temperature is between 32°F and -40°F (-40°C to 0°C).
Blow dry filtered air through the adapter.
SUBTASK 480-132
Wipe the pitot probe with a damp cloth, BMS15-5.
SUBTASK 480-133
CAUTION:
_______
(4)
(5)
MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
Install the adapter, P75701M2-3, on the upper pitot probe on the
right side of the forward fuselage.
SUBTASK 480-134
Connect the test set, to the adapter, P75701M2-3.
EFFECTIVITY
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SUBTASK 790-088
CAUTION:
_______
ú
ú
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(6)
(7)
(8)
ú
ú
(9)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set, to apply pressure of 4.53 |0.16 inches Hg
(gauge), (2.22 |0.08 psig) (153.4 |5.4 mB), or 300 |5 knots on the
airspeed indicator.
SUBTASK 790-089
When the test pressure is reached, stop for one minute to allow the
system to stabilize.
SUBTASK 790-090
Set the test set for the leak check.
SUBTASK 790-091
Make sure the pressure does not decrease more than 0.16 inches Hg
(5.4 mB) (approximately 5 knots) in one minute.
SUBTASK 860-139
(10) Put the system back to ambient pressure.
SUBTASK 080-071
CAUTION:
_______
DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(11) Disconnect the test set, from the adapter, P75701M2-3.
SUBTASK 080-072
(12) Remove the adapter, P75701M2-3, from the pitot probe.
H.
SUBTASK 860-140
(13) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-3:
1) 18D5
HEATERS F/O PITOT
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-141
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
EFFECTIVITY
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(c)
(d)
(e)
(2)
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D6
HEATERS AUX PITOT
Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-142
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
TASK 34-11-00-790-812
7.
________________________________
Alternate
Pitot System Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a pitot system, the rate must not be
more than 300 knots for each minute.
(b) When you release pressure from a pitot system, the rate must
not be more than 300 knots for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that you prepare the adapter, P75701M2-3 before you
install the adapter on the pitot probe.
(e) Make sure that the ATC transponders are in standby mode.
(f) Make sure that the Autopilot Flight Director System is off.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701M2-3 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P75701-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
EFFECTIVITY
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(b)
D.
E.
F.
18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
Prepare for the Leak Tests
SUBTASK 860-143
WARNING:
_______
(1)
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
Make sure that the ATC transponders are in standby mode.
SUBTASK 860-144
EFFECTIVITY
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(2)
Make sure that the Autopilot Flight Director System is off.
(3)
SUBTASK 860-145
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
(4)
SUBTASK 860-146
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-147
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Alternate Pitot System Leak Test
(5)
G.
(1)
(2)
SUBTASK 860-148
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-3:
1) 18D6
HEATERS AUX PITOT
SUBTASK 170-078
Prepare the adapter, P75701M2-3 before you install the adapter on
the pitot probe:
CAUTION:
_______
(a)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER
WITH WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE.
DAMAGE TO THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter with water.
NOTE:
____
(b)
Use equal parts of water and ethylene glycol when the
temperature is between 32°F and -40°F (-40°C to 0°C).
Blow dry filtered air through the adapter.
EFFECTIVITY
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(3)
SUBTASK 480-135
Wipe the pitot probe with a damp cloth, BMS15-5.
SUBTASK 480-136
CAUTION:
_______
(4)
(5)
MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
Install the adapter, P75701M2-3, on the lower pitot probe on the
right side of the forward fuselage.
SUBTASK 480-137
Connect the test set, to the adapter, P75701M2-3.
SUBTASK 790-092
CAUTION:
_______
ú
ú
ú
ú
(6)
(7)
(8)
ú
ú
(9)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set, to apply pressure of 4.53 |0.16 inches Hg
(gauge), (2.22 |0.08 psig) (153.4 |5.4 mB), or 300 |5 knots on the
airspeed indicator.
SUBTASK 790-093
When the test pressure is reached, stop for one minute to allow the
system to stabilize.
SUBTASK 790-094
Set the test set for the leak check.
SUBTASK 790-095
Make sure the pressure does not decrease more than 0.16 inches Hg
(5.4 mB) (approximately 5 knots) in one minute.
SUBTASK 860-149
(10) Put the system back to ambient pressure.
SUBTASK 080-073
CAUTION:
_______
DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(11) Disconnect the test set, from the adapter, P75701M2-3.
SUBTASK 080-074
(12) Remove the adapter, P75701M2-3, from the pitot probe.
EFFECTIVITY
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H.
SUBTASK 860-150
(13) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-3:
1) 18D6
HEATERS AUX PITOT
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-151
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-152
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
EFFECTIVITY
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TASK 34-11-00-790-813
ú
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8.
_______________________________________
Left
Static System Full-range Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that the ATC transponders are in standby mode.
(e) Make sure that the Autopilot Flight Director System is off.
(f) Make sure that the seals used on the static ports do not extend
into the static ports.
(g) Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
(h) You must do the static system low-range leak test when you
remove a fitting other than a quick disconnect. You must do
the low-range leak test after you flush the pitot-static
system.
(i) The static system full-range leak test is not required.
However, leaks are easier to detect with the higher pressure.
(j) You can use either the drain coupling or the static port
adapter to pressurize the static system. The drain adapter is
recommended and the static port adapter is alternate.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
(3) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
(4) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) 33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
EFFECTIVITY
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(4)
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D.
ú
ú
ú
ú
ú
ú
ú
ú
ú
ú
ú
E.
Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(e) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(f) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
EFFECTIVITY
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F.
Prepare for the Leak Tests
SUBTASK 860-153
WARNING:
_______
(1)
Make sure that the ATC transponders are in standby mode.
(2)
SUBTASK 860-154
Make sure that the Autopilot Flight Director System is off.
(3)
(4)
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MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
SUBTASK 860-155
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-156
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-157
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Left Static System Full-range Leak Test
(5)
G.
(1)
SUBTASK 480-141
Open the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Remove the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-000-801 p401).
EFFECTIVITY
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(2)
SUBTASK 480-142
Remove the cap from the left system static drain.
NOTE:
____
(3)
SUBTASK 400-007
For installation of the coupling, 1QF2-3-64C (Recommended), do these
steps:
(a)
(b)
(4)
The forward drain is for the left system. The aft drain is
for the right system. The forward drain is known as the No.3
Captain's Static Drain. The aft drain is known as the No.4
First Officer's Static Drain.
SUBTASK 480-143
Install the coupling, 1QF2-3-64C, on the left system static
drain (Recommended).
SUBTASK 480-144
Connect the test set, to the coupling, 1QF2-3-64C.
SUBTASK 400-008
For installation of the adapter, 33410LH-125-4 (Alternate), do these
steps:
SUBTASK 480-184
CAUTION:
_______
(a)
INSTALL THE adapter, 33410LH-125-4, SLOWLY AND CAREFULLY.
THE ADAPTER CAN COUSE SCRATCHES ON THE STATIC PORT, WHICH
CAN CAUSE FALSE ALTITUDE READINGS.
Install the adapter, 33410LH-125-4, (Alternate) on the static
ports at these locations:
1) The captain's static port on the right side of the
fuselage.
2) The first officer's static port on the right side of the
fuselage.
EFFECTIVITY
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SUBTASK 400-009
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT
CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO OBSERVE
AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY
CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PUSH THE TAPE INTO THE STATIC PORTS. YOU CAN DAMAGE
THE STATIC SYSTEM IF YOU PUSH TAPE INTO THE STATIC PORT.
(b)
Seal the static ports at these locations with tape, Scotch
Brand No.471:
1) The captain's static port on the left side of the fuselage.
2) The first officer's static port on the right side of the
fuselage.
SUBTASK 790-101
CAUTION:
_______
(5)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set, to apply pressure between -11.00 and -11.20
inches Hg or 372.5 mB and 379.3 mB (approximately 25,000 feet) to
the static system.
NOTE:
____
(6)
(7)
(8)
(9)
The pressure values are absolute values.
SUBTASK 790-102
When the system reaches 25,000 feet, stop for one minute to allow
the system to stabilize.
SUBTASK 790-103
Set the test set for the leak check.
SUBTASK 790-104
Make sure the pressure does not decrease more than 0.20 inches Hg or
6.77 mB (approximately 400 feet) in one minute.
SUBTASK 860-158
Put the system back to ambient pressure.
EFFECTIVITY
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H.
Removal of Drain Coupling, 1QF2-3-64:
SUBTASK 080-100
CAUTION:
_______
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1)
Disconnect the test set from each coupling, 1QF2-3-64C.
(2)
SUBTASK 080-101
Disconnect each coupling, 1QF2-3-64C, from the left and right static
system drains.
(3)
SUBTASK 480-185
Install the cap on the left and right static system drains.
SUBTASK 080-102
WARNING:
_______
(4)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The two primary static ports on the right side of the fuselage.
(b)
The two primary static ports on the left side of the fuselage.
SUBTASK 480-186
Close the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Install the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-400-801 p401).
Removal of Static Port Adapter, 33410LH-125-4, (Alternate):
(5)
I.
SUBTASK 480-187
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
EFFECTIVITY
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SUBTASK 480-188
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
SUBTASK 480-189
WARNING:
_______
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
(3)
J.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The captain's static port on the left side of the fuselage.
(b) The first officer's static port on the left side of the
fuselage.
Removal of the Probe Adapters:
SUBTASK 080-103
CAUTION:
_______
K.
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1) Disconnect the test set from each adapter, P75701-4.
Put the Airplane Back to Its Usual Condition
(1)
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SUBTASK 860-159
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
EFFECTIVITY
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(2)
Circuit Breaker Panel,
1) 18E5
ADIRU LEFT
2) 18E7
ADIRU LEFT
Circuit Breaker Panel,
1) 18E8
ADIRU LEFT
P18-1:
DC
AC
P18-2:
EXC
SUBTASK 860-160
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
TASK 34-11-00-790-814
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9.
________________________________________
Right
Static System Full-range Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that the ATC transponders are in standby mode.
(e) Make sure that the Autopilot Flight Director System is off.
(f) Make sure that the seals used on the static ports do not extend
into the static ports.
(g) Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
(h) You must do the static system low-range leak test when you
remove a fitting other than a quick disconnect. You must do
the low-range leak test after you flush the pitot-static
system.
(i) The static system full-range leak test is not required.
However, leaks are easier to detect with the higher pressure.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
(3) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
(4) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
C. Equipment
(1) Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
EFFECTIVITY
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(2)
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D.
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E.
33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(4) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
EFFECTIVITY
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(e)
F.
231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(f) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
Prepare for the Leak Tests
(1)
SUBTASK 860-161
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(2)
Make sure that the ATC transponders are in standby mode.
(3)
SUBTASK 860-162
Make sure that the Autopilot Flight Director System is off.
(4)
(5)
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SUBTASK 800-002
You can use either the drain coupling or the static port adapter to
pressurize the static system. The drain adapter is recommended and
the static port adapter is alternate.
(6)
SUBTASK 860-163
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-164
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(c) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
(d) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(e) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-165
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
EFFECTIVITY
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G.
Right Static System Full-range Leak Test
(1)
SUBTASK 400-010
Installation of Drain Coupling, 1QF2-3-64C (Recommended):
SUBTASK 480-190
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT
CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO OBSERVE
AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY
CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE TAPE INTO THE STATIC PORTS. DAMAGE TO
THE SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE
TAPE.
(a)
(b)
(c)
(d)
Seal these primary static ports with vinyl adhesive tape,
Scotch Brand No.471:
1) Seal the upper and lower primary static ports on the right
side of the fuselage.
2) Seal the upper and lower primary static ports on the left
side of the fuselage.
SUBTASK 480-191
Open the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
Do this task: Remove the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-000-801 p401).
SUBTASK 480-192
Remove the caps from the left and right static system
NOTE:
____
(e)
(f)
(2)
drains.
The forward drain is for the left system. The aft drain
is for the right system. The forward drain is known as
the No.3 Captain's Static Drain. The aft drain is known
as the No.4 First Officer's Static Drain.
SUBTASK 480-193
Install the coupling, 1QF2-3-64C, on the left and right static
system drains.
SUBTASK 480-194
Connect the test set to each coupling, 1QF2-3-64C.
SUBTASK 400-011
Installation of Static Port Adapter, 33410LH-125-4 (Alternate):
EFFECTIVITY
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SUBTASK 480-195
CAUTION:
_______
(a)
INSTALL THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY.
THE ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH
CAN CAUSE FALSE ALTITUDE READINGS.
Install the adapter, 33410LH-125-4, on the static ports at
these locations:
1) The captain's static port on the right side of the
fuselage.
2) The first officer's static port on the right side of the
fuselage.
SUBTASK 480-196
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT
CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO OBSERVE
AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY
CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PUSH THE TAPE INTO THE STATIC PORTS. YOU CAN
DAMAGE THE STATIC SYSTEM IF YOU PUSH TAPE INTO THE STATIC
PORT.
(b)
Seal the static ports at these locations with tape, Scotch
Brand No.471:
1) The captain's static port on the left side of the fuselage.
2) The first officer's static port on the left side of the
fuselage.
SUBTASK 790-105
CAUTION:
_______
(3)
MAKE SURE THAT THE PRESSURE IN THE AIR DATA MODULE (ADM) IS NOT
TOO HIGH. PRESSURE THAT IS MORE THAN 39.865 INCHES HG WILL
CAUSE DAMAGE TO THE ADM.
Operate the test set, to apply pressure between -11.00 and -11.20
inches Hg or 372.5 mB and 379.3 mB (approximately 25,000 feet) to
the static system.
NOTE:
____
(4)
The pressure values are absolute values.
SUBTASK 790-106
When the system reaches 25,000 feet, stop for one minute to allow
the system to stabilize.
SUBTASK 790-107
EFFECTIVITY
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H.
(5)
Set the test set for the leak check.
(6)
SUBTASK 790-108
Make sure the pressure does not decrease more than 0.20 inches Hg or
6.77 mB (approximately 400 feet) in one minute.
SUBTASK 860-166
(7) Put the system back to ambient pressure.
Removal of Drain Coupling, 1QF2-3-64:
SUBTASK 080-104
CAUTION:
_______
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1)
Disconnect the test set from each coupling, 1QF2-3-64C.
(2)
SUBTASK 080-105
Disconnect each coupling, 1QF2-3-64C, from the left and right static
system drains.
(3)
SUBTASK 480-197
Install the cap on the left and right static system drains.
SUBTASK 080-106
WARNING:
_______
(4)
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The two primary static ports on the right side of the fuselage.
(b)
(5)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
The two primary static ports on the left side of the fuselage.
SUBTASK 480-198
Close the primary static system
sidewall lining, in the forward
(a) Do this task: Install the
Compartment
drain access panel, on the left
cargo compartment.
Sidewall Lining for the Cargo
(AMM TASK 25-52-06-400-801 p401).
EFFECTIVITY
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I.
Removal of Static Port Adapter, 33410LH-125-4, (Alternate):
SUBTASK 480-199
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
SUBTASK 080-107
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
SUBTASK 080-108
WARNING:
_______
(3)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
1) The captain's static port on the left side of the fuselage.
SUBTASK 480-200
The first officer's static port on the left side of the
fuselage.
Removal of the Probe Adapters:
(a)
J.
SUBTASK 080-109
CAUTION:
_______
K.
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1) Disconnect the test set from each adapter, P75701-4.
Put the Airplane Back to Its Usual Condition
(1)
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SUBTASK 860-167
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
EFFECTIVITY
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(2)
3) 6C17
ADIRU RIGHT DC
Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-168
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
TASK 34-11-00-790-815
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10. Alternate
____________________________________________
Static System Full-range Leak Test (Fig. 501)
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(d) Make sure that the ATC transponders are in standby mode.
(e) Make sure that the Autopilot Flight Director System is off.
(f) Make sure that the seals used on the static ports do not extend
into the static ports.
(g) Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
(h) You must do the static system low-range leak test when you
remove a fitting other than a quick disconnect. You must do
the low-range leak test after you flush the pitot-static
system.
(i) The static system full-range leak test is not required.
However, leaks are easier to detect with the higher pressure.
B. References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
C. Equipment
(1) P75701M2-3 Adapter - Pitot Probe
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
EFFECTIVITY
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(2)
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(5)
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Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
EFFECTIVITY
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E.
F.
01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
(2) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 121 Forward Cargo Compartment - Left
(c) 122 Forward Cargo Compartment - Right
(d) 211 Flight Compartment - Left
(e) 212 Flight Compartment - Right
(f) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(g) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
Prepare for the Leak Tests
(1)
SUBTASK 800-003
You can use either the drain coupling or the static port adapter to
pressurize the static system. The drain adapter is recommended and
the static port adapter is alternate.
SUBTASK 860-169
WARNING:
_______
MAKE SURE THAT THE ATC TRANSPONDERS ARE IN STANDBY MODE WHEN
YOU SIMULATE ALTITUDE. YOU CAN ACCIDENTALLY CAUSE FALSE TCAS
TARGETS. THESE TCAS TARGETS CAN CAUSE AIR TRAFFIC IN THE
VICINITY TO EXECUTE UNNECESSARY EVASIVE MANEUVERS.
(2)
Make sure that the ATC transponders are in standby mode.
(3)
SUBTASK 860-170
Make sure that the Autopilot Flight Director System is off.
(4)
(5)
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SUBTASK 860-171
Make sure that the IRS R and IRS L switches on the IRS Mode Select
Unit, located on the P5-69 panel, are in the off position.
SUBTASK 860-172
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
EFFECTIVITY
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2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-173
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
Alternate Static System Full-range Leak Test
(6)
G.
(1)
SUBTASK 170-079
Prepare the adapter, P75701M2-3 before you install the adapter on
the pitot probe.
CAUTION:
_______
(a)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER
WITH WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE.
DAMAGE TO THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter with water.
NOTE:
____
(b)
Use equal parts of water and ethylene glycol when the
temperature is between 32°F and -40°F (-40°C to 0°C).
Blow dry filtered air through the adapter.
EFFECTIVITY
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SUBTASK 480-153
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE SEAL.
(2)
Seal the two alternate static ports with vinyl adhesive tape, Scotch
Brand No.471 at these locations:
(a) The alternate static port on the right side of the fuselage.
NOTE:
____
(b)
The alternate static port on the left side of the fuselage.
NOTE:
____
(3)
This port is marked ALTERNATE.
This port is marked ALTERNATE.
SUBTASK 480-154
Remove the cap from the alternate static drain, in the electronic
equipment compartment, below the E-5 rack.
NOTE:
____
This drain is known as the No.5 alternate static drain.
(a)
H.
Get access to the drain in the electronic equipment compartment
through the Electronic Equipment Access Door, 117A.
Installation of Drain Coupling, 1QF2-3-64C (Recommended):
I.
SUBTASK 480-155
(1) Install the coupling, 1QF2-3-64C, on the alternate static drain.
Installation of Static Port Adapter, 33410LH-125-4 (Alternate):
(1)
SUBTASK 480-201
Install the adapter, 33410LH-125-4, on the alternate static drain.
SUBTASK 480-202
CAUTION:
_______
INSTALL THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
(2)
Install the adapter, 33410LH-125-4, on the alternate static port.
(3)
SUBTASK 480-156
Connect the test set, to the coupling, 1QF2-3-64C.
EFFECTIVITY
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(4)
SUBTASK 480-157
Wipe the pitot probe with a damp cloth, BMS15-5.
SUBTASK 480-158
CAUTION:
_______
(5)
(6)
MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
Install the adapter, P75701M2-3, on the lower pitot probe on the
right side of the forward fuselage.
SUBTASK 480-159
Connect the test set, to the adapter, P75701M2-3.
SUBTASK 790-109
CAUTION:
_______
(7)
KEEP THE RATE OF STATIC CHANGE BELOW 5000 FEET PER MINUTE, AND
KEEP THE DIFFERENTIAL PRESSURE BETWEEN THE PITOT AND STATIC
SYSTEM LESS THAN 10 INCHES OF MERCURY. FAILURE TO DO THIS
COULD CAUSE DAMAGE TO THE STANDBY ALTIMETER/AIRSPEED INDICATOR
OR EQUIPMENT.
Do the test of the alternate static system as follows:
(a) Operate the test set, to apply vaccum to the alternate pitot
system to keep the pressure difference less than 10 inches Hg.
(b) Operate the test set, to apply pressure between -11.00 and
-11.20 inches Hg or 372.5 mB and 379.3 mB (approximately 25,000
feet) to the static system.
NOTE:
____
(8)
(9)
The pressure values are absolute values.
SUBTASK 790-110
When the system reaches 25,000 feet, stop for one minute to allow
the system to stabilize.
SUBTASK 790-111
Set the test set for the leak check.
SUBTASK 790-112
(10) Make sure the pressure does not decrease more than 0.20 inches Hg or
6.77 mB (approximately 400 feet) in one minute.
SUBTASK 860-174
(11) Put the system back to ambient pressure.
EFFECTIVITY
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SUBTASK 080-082
CAUTION:
_______
DO NOT DISCONNECT THE STATIC SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE STANDBY ALTIMETER/AIRSPEED INDICATOR CAN OCCUR.
(12) Disconnect the test set, and the coupling, 1QF2-3-64C, from the
alternate static drain.
SUBTASK 080-083
(13) Install the cap on the alternate static drain.
(a) Close the Electronic Equipment Access Door, 117A.
SUBTASK 080-084
CAUTION:
_______
DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(14) Disconnect the test set, from the adapter, P75701M2-3.
SUBTASK 080-085
(15) Remove the adapter, P75701M2-3, from the pitot probe.
SUBTASK 080-086
WARNING:
_______
FAILURE TO REMOVE THE VINYL ADHESIVE TAPE FROM THE STATIC PORTS
BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND
ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE
FLIGHT.
CAUTION:
_______
DO NOT PLUG OR DEFORM THE HOLES IN THE PORT. MAKE SURE THAT
YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE STATIC PORTS.
THE SURFACE OF THE PORT MUST BE SMOOTH AND CLEAN. IF YOU DO
NOT, THE SYSTEM WILL NOT OPERATE CORRECTLY.
(16) Remove the vinyl adhesive tape, Scotch Brand No.471 from both of the
alternate static ports.
(a) Remove the vinyl adhesive tape from the alternate static port
on the right side of the fuselage.
(b) Remove the vinyl adhesive tape from the alternate static port
on the left side of the fuselage.
EFFECTIVITY
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J.
Removal of Static Port Adapter, 33410LH-125-4, (Alternate):
SUBTASK 480-203
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
SUBTASK 480-204
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the alternate static port.
SUBTASK 480-205
WARNING:
_______
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
(3)
K.
Remove the tape, Scotch Brand No.471, from the alternate static
port.
Removal of the Probe Adapters:
SUBTASK 080-110
CAUTION:
_______
L.
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1) Disconnect the test set from each adapter, P75701-4.
Put the Airplane Back to Its Usual Condition
(1)
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SUBTASK 860-175
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
EFFECTIVITY
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(c)
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(d)
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(e)
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(2)
Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-176
Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
EFFECTIVITY
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PITOT PROBE - REMOVAL/INSTALLATION
__________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the pitot probe
(2) An installation of the pitot probe.
TASK 34-11-01-000-801
2.
___________________
Pitot
Probe Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-44-000-801 p401, Lockwires Removal
B. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Removal Procedure
(1)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18D5
HEATERS F/O PITOT
3) 18D6
HEATERS AUX PITOT
SUBTASK 140-004
CAUTION:
_______
(2)
(3)
MAKE SURE THAT THE AREA AROUND THE PITOT PROBE [9] IS CLEAR OF
UNWANTED MATERIAL. CONTAMINATION OF THE PITOT SYSTEM CAN
OCCUR.
Use the sealant removal tool to remove the sealant from around the
baseplate [1] of the pitot probe [9].
SUBTASK 020-002
Remove the screws [7] from the baseplate [1] of the pitot probe [9].
SUBTASK 020-003
WARNING:
_______
MAKE SURE THAT THE PITOT PROBE [9] HEAT IS OFF.
PERSONS CAN OCCUR.
CAUTION:
_______
MAKE SURE THAT THE PITOT PROBE [9] HAS NO ADDED WEIGHT ON IT.
THE PITOT PROBE [9] CAN BEND OR TWIST OUT OF TOLERANCE.
(4)
INJURY TO
Do these steps to loosen the pitot probe [9] from the airplane skin:
(a) Hold the probe strut [8].
EFFECTIVITY
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CAPT PITOT
PROBE
SEE
A
F/O PITOT
PROBE
SEE
A
ALT PITOT
PROBE
SEE
A
AIRPLANE
SKIN
[3] GASKET
[1] BASEPLATE
[11] PITOT
HOSE
[10] LONG
FITTING
SCREW
[2] LOCKWIRE
[4] BOLT
(2 LOCATIONS)
[5] WASHER
(2 LOCATIONS)
[6] ELECTRICAL
CONNECTOR
[7] SCREW
(6 LOCATIONS)
[9] PITOT
PROBE
[6] ELECTRICAL
CONNECTOR
[8] PROBE
STRUT
CAPTAIN'S PITOT PROBE SHOWN
(FIRST OFFICER'S AND ALTERNATE ARE OPPOSITE)
A
Pitot Probe Installation
Figure 401
F61610
34-11-01-990-801
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(b)
(c)
Loosen the gasket [3].
Pull the pitot probe [9] out from the airplane skin until you
can get access to the pitot hose fitting [11] and electrical
connector [6] on the base of the pitot probe [9].
SUBTASK 020-004
CAUTION:
_______
(5)
(6)
USE WRENCHES TO APPLY COUNTER PRESSURE ON EACH SIDE OF THE
FITTING DURING DISASSEMBLY. DAMAGE TO THE TUBE OR FITTING CAN
OCCUR.
Disconnect the pitot hose fitting [11] at the base of the pitot
probe [9].
SUBTASK 020-005
Remove the long screw [10] from the pitot probe side of the
electrical connector [6].
(7)
SUBTASK 020-006
Disconnect the electrical connector [6].
(8)
SUBTASK 020-007
Remove the pitot probe [9].
(9)
SUBTASK 420-001
Install the long screw [10] in the electrical connector [6].
SUBTASK 020-008
(10) Temporarily attach the electrical connector [6] and pitot hose
fitting [11] so they do not fall inside the fuselage.
SUBTASK 020-009
(11) Put a cap on the pitot hose fitting [11] that stays on the airplane
to keep out unwanted material.
NOTE:
____
This step is not necessary when you replace the pitot probe
[9] immediately.
SUBTASK 020-010
(12) For the bolts [4] in the baseplate [1], do this task:
Removal (AMM TASK 20-10-44-000-801 p401).
Lockwires
SUBTASK 020-011
(13) Remove the bolts [4], washers [5], and the pitot probe [9] from the
baseplate [1].
EFFECTIVITY
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SUBTASK 020-012
(14) Keep the baseplate [1] for another installation.
NOTE:
____
The baseplates [1] are not interchangeable between positions.
SUBTASK 020-013
(15) Remove the gasket [3] and discard it.
TASK 34-11-01-400-801
3.
________________________
Pitot
Probe Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-34-110-802 p701, Clean Bare, Clad, or Plated Metal
with Solvent
(2) AMM TASK 20-10-44-400-801 p401, Lockwires Installation
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 30-31-00-730-801 p501, Pitot Probe, AOA Sensor, and TAT
Probe Heater Test
(5) AMM TASK 51-31-00-390-803 p201, Hole and Slot Seal Application
B. Equipment
(1) Multimeter - Standard
(commercially available)
C. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
9 ¦ Probe
¦ 34-11-01
01
30 ¦
¦
¦
¦
75 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
F. Installation Procedure
(1)
SUBTASK 110-001
For the surface of the baseplate [1], do this task: Clean Bare,
Clad, or Plated Metal with Solvent (AMM TASK 20-10-34-110-802 p701).
(2)
SUBTASK 390-001
Apply a thin layer of sealant, BMS5-95, on the mating surfaces of
the pitot probe [9] and baseplate [1].
(3)
SUBTASK 420-002
Put the baseplate [1] on the pitot probe [9].
EFFECTIVITY
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(4)
(5)
(6)
SUBTASK 420-003
Install the bolts [4] and washers [5] in the baseplate [1].
SUBTASK 420-004
For the bolts [4], do this task: Lockwires Installation
(AMM TASK 20-10-44-400-801 p401).
SUBTASK 420-005
Put the new gasket [3] into position on the baseplate [1].
SUBTASK 420-006
CAUTION:
_______
(7)
USE WRENCHES TO APPLY COUNTER PRESSURE ON EACH SIDE OF THE
FITTING DURING ASSEMBLY. DAMAGE TO THE TUBE OR FITTING CAN
OCCUR.
Connect the pitot hose fitting [11] at the base of the pitot probe
[9].
(8)
SUBTASK 420-007
Remove the long screw [10] from the pitot probe [9] side of the
electrical connector [6].
(9)
SUBTASK 210-001
Examine the electrical connector [6] for loose, bent, or broken
pins.
SUBTASK 420-008
(10) Connect the electrical connector [6].
SUBTASK 420-009
(11) Install the long screw [10] in the electrical connector [6].
SUBTASK 420-010
(12) Do these steps to put the pitot probe [9] into position:
(a) Hold the probe strut [8].
(b) Put the pitot hose fitting [11] and electrical connector [6] in
the installation hole.
(c) Put the pitot probe [9] into position on the airplane skin.
1) Make sure the airplane skin and the baseplate [1] are
aligned in |0.04 inch or less.
SUBTASK 420-011
(13) Install the screws [7] in the baseplate [1] of the pitot probe [9].
SUBTASK 420-012
(14) Tighten the screws [7] to 25-35 pound-inches.
EFFECTIVITY
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SUBTASK 760-001
(15) Measure the resistance between the bottom of the pitot probe [9] and
the airplane skin with a multimeter.
(a) Make sure the resistance is less than 0.010 ohms.
G.
SUBTASK 860-002
(16) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18D5
HEATERS F/O PITOT
3) 18D6
HEATERS AUX PITOT
Installation Test
(1)
(2)
(3)
(4)
SUBTASK 860-003
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 790-001
For the applicable pitot probe [9], do this task:
SUBTASK 710-001
For the probe heater circuit on the pitot probe [9], do this task:
Pitot Probe, AOA Sensor, and TAT Probe Heater Test
(AMM TASK 30-31-00-730-801 p501).
SUBTASK 390-002
Fill the gap between the baseplate [1] and the airplane skin with
sealant, BMS5-95, (AMM TASK 51-31-00-390-803 p201).
(a) Make sure the baseplate [1] and sealant are flat with the
airplane skin.
EFFECTIVITY
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(Reference TBD).
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PITOT PROBE - INSPECTION/CHECK
______________________________
1.
General
_______
A. This procedure has these tasks:
(1) A detailed inspection of the pitot probe.
(2) A general visual inspection of the pitot probe.
B. Fly Back Limits
(1) Replace the pitot probe for one or more of the conditions that
follow:
(a) The flight crew sees a cross panel airspeed difference that is
not acceptable.
(b) There is mechanical damage.
(2) Do these steps when you see deterioration of the pitot probe:
(a) You can dispatch the airplane from a base without maintenance
facilities until one of the conditions that follow occur:
1) 24 hours elapse
2) The airplane gets to a maintenance base.
TASK 34-11-01-200-803
2.
_________________________________
Pitot
Probe - Detailed Inspection (Fig. 601)
A. References
(1) AMM TASK 34-11-01-000-801 p401, Pitot Probe Removal
(2) AMM TASK 34-11-01-400-801 p401, Pitot Probe Installation
B. Equipment
(1) Micrometer (or alternative tool)
(a) MODEL 966A1 Micrometer, Optical, 200 Power, Depths to .295 In,
Thickness to .440 In, Accuracy +/-.0002 In (recommended)
Edwards Aerospace Co. (Vendor Code 92541)
1841 Business Parkway, Ontario CA 91761
(b) 8400PCK Micrometer - Optical (alternative)
Rene Corp. (Vendor Code 65956)
13619 Saticoy St., Van Nuys CA 91402-6301
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Pitot Probe Inspection (Fig. 601)
(1)
SUBTASK 210-004
Visually examine the pitot probe for damage or unwanted material in
the drain holes, the pitot opening, or the contour of the probe.
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PITOT PROBE
SEE
PITOT PROBE
A
SEE
A
B
SEE
FWD
PITOT PROBE (EXAMPLE)
A
Pitot Probe Inspection
Figure 601 (Sheet 1)
G05728
34-11-01-990-802
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0.025 INCH
PITOT FLAT
B
0.360 INCH MIN
0.420 INCH DIA. NOMINAL
0.470 INCH MAX
PITOT DENT IN
PITOT FLARE OUT
B
B
0.050 INCH (2 NICKS OR CHIPS)
0.060 INCH (1 NICK OR CHIP)
2.0` MAX
0.015 INCH MAX
PITOT NICK
PITOT SCARF
B
B
Pitot Probe Inspection
Figure 601 (Sheet 2)
G05731
EFFECTIVITY
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(2)
SUBTASK 220-012
Use the micrometer, MODEL 966A1 to make sure the edge of the pitot
opening is sharp.
NOTE:
____
(a)
(3)
New probes are sharpened to 0.010 inch (0.254 mm) maximum
flat.
Replace the
inch (0.635
Pitot Probe
Pitot Probe
SUBTASK 220-013
Make sure the inner surface of the probe tip is smooth and rounded.
(a) Make sure the pitot probe has no dents more than 0.360 inch
(9.144 mm).
NOTE:
____
(b)
(4)
(5)
pitot probe if the pitot opening dimension is 0.025
mm) or more These are the tasks:
Removal (AMM TASK 34-11-01-000-801 p401),
Installation (AMM TASK 34-11-01-400-801 p401).
The dent can be at any location around the opening, but
must not affect more than 1/5 (20%) of the lip area.
Replace the pitot probe if the damage is more than this limit
These are the tasks:
Pitot Probe Removal (AMM TASK 34-11-01-000-801 p401),
Pitot Probe Installation (AMM TASK 34-11-01-400-801 p401).
SUBTASK 220-014
Make sure that the outer surface of the probe tip is smooth and
rounded.
(a) Replace the pitot probe if the tip is flared out more than
0.470 inch (11.938 mm) These are the tasks:
Pitot Probe Removal (AMM TASK 34-11-01-000-801 p401),
Pitot Probe Installation (AMM TASK 34-11-01-400-801 p401).
SUBTASK 220-015
Make sure the leading edge of the pitot probe does not have nicks.
(a) Replace the pitot probe if there are two or more nicks between
0.050 and 0.060 inch (1.27-1.52 mm) in depth These are the
tasks:
Pitot Probe Removal (AMM TASK 34-11-01-000-801 p401),
Pitot Probe Installation (AMM TASK 34-11-01-400-801 p401).
(b) Replace the pitot probe if there is a nick more than 0.060 inch
(1.52 mm) in depth These are the tasks:
Pitot Probe Removal (AMM TASK 34-11-01-000-801 p401),
Pitot Probe Installation (AMM TASK 34-11-01-400-801 p401).
EFFECTIVITY
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(6)
SUBTASK 220-016
Make sure the leading edge of the pitot probe axis is even.
(a) Replace the pitot probe if the side to side difference is 0.015
inch (0.381 mm) or more These are the tasks:
Pitot Probe Removal (AMM TASK 34-11-01-000-801 p401),
Pitot Probe Installation (AMM TASK 34-11-01-400-801 p401).
TASK 34-11-01-200-802
3.
__________________________________________________
Pitot
Probe Inspection - General Visual Inspection
A. References
(1) AMM TASK 34-11-01-000-801 p401, Pitot Probe Removal
(2) AMM TASK 34-11-01-400-801 p401, Pitot Probe Installation
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Pitot Probe Inspection
(1)
SUBTASK 210-003
Visually examine the pitot probe for damage or unwanted material in
the drain holes, the pitot opening, or the contour of the probe.
(2)
SUBTASK 220-006
Make sure the edge of the pitot opening is sharp.
(3)
SUBTASK 220-007
Make sure the inner surface of the probe tip is smooth and rounded.
(4)
SUBTASK 220-008
Make sure that the outer surface of the probe tip is smooth and
rounded.
(5)
SUBTASK 220-009
Make sure the leading edge of the pitot probe does not have nicks.
(6)
SUBTASK 220-010
Make sure the leading edge of the pitot probe axis is even.
(7)
SUBTASK 220-011
If the general visual inspection of the pitot probe is not
satisfactory, replace the pitot probe These are the tasks:
Pitot Probe Removal (AMM TASK 34-11-01-000-801 p401),
Pitot Probe Installation (AMM TASK 34-11-01-400-801 p401).
EFFECTIVITY
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PITOT PROBE - CLEANING/PAINTING
_______________________________
1.
General
_______
A. This procedure shows how to clean the inner and outer surfaces of the
pitot probe.
TASK 34-11-01-100-801
2.
____________________
Pitot
Probe Cleaning
A. General
CAUTION:
_______
DO NOT PAINT THE PITOT PROBE. PAINT ON THE PITOT PROBE CAN
CAUSE THE PITOT SYSTEM TO MALFUNCTION.
(1)
(2)
B.
C.
D.
E.
F.
The pitot probe must not be painted.
To make sure that the probes do not have any damage, do this task:
Pitot Probe - Detailed Inspection (AMM TASK 34-11-01-200-803 p601).
References
(1) AMM TASK 34-11-01-000-801 p401, Pitot Probe Removal
(2) AMM TASK 34-11-01-200-803 p601, Pitot Probe - Detailed Inspection
(3) AMM TASK 34-11-01-400-801 p401, Pitot Probe Installation
Equipment
(1) Air Source, Regulated, Dry Filtered, 0-50 psig
(commercially available)
(2) Bit - Drill, 0.026 Inch Diameter
(commercially available)
(3) Bit - Drill, 0.031 Inch Diameter
(commercially available)
Consumable Materials
(1) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 112A
Forward Access Door
Clean the Inner Surface of the Pitot Probe
(1)
(2)
SUBTASK 010-001
Open the Forward Access Door, 112A to get access to the applicable
pitot hose.
SUBTASK 020-001
Disconnect the hose from the pitot probe.
EFFECTIVITY
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SUBTASK 160-001
CAUTION:
_______
(3)
(4)
DO NOT USE MORE THAN 60 PSI (414 KPA) OF DRY, COMPRESSED AIR IN
THE PITOT PROBE. AIR PRESSURE MORE THAN 60 PSI (414 KPA) CAN
CAUSE DAMAGE TO THE PITOT PROBE.
Use the air source (0-50 psig) to force air through the line and out
the ports on the pitot probe.
SUBTASK 170-001
If unwanted material remains, do the steps that follow:
(a) Do this task: Pitot Probe Removal
(AMM TASK 34-11-01-000-801 p401).
(b) Soak or flush the unit with water until it is clean.
(c) Drain the probe.
(d) Do this task: Pitot Probe Installation
(AMM TASK 34-11-01-400-801 p401).
SUBTASK 140-001
CAUTION:
_______
(5)
G.
MAKE SURE THE DRILL BIT DOES NOT MAKE THE DRAIN HOLE LARGER
WHEN YOU CLEAN IT. DAMAGE TO THE PITOT PROBE CAN OCCUR.
If the forced air and soak methods do not clean the pitot probe,
insert first a small drill bit and then a slightly larger drill bit
into the drain hole.
SUBTASK 410-001
(6) Close the Forward Access Door, 112A.
Clean the Outer Surface of the Pitot Probe
SUBTASK 140-002
CAUTION:
_______
(1)
(2)
DO NOT PERMIT SOLVENTS, OIL, OR GREASE TO GET ON THE PITOT
PROBE. SOLVENTS, OIL, OR GREASE CAN CAUSE DAMAGE TO THE PITOT
PROBE.
Use clean water to remove unwanted materials from the outer surface
of the pitot probe.
SUBTASK 140-003
Dry the pitot probe with a cloth, BMS15-5.
EFFECTIVITY
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STATIC PORT - REMOVAL/INSTALLATION
__________________________________
1.
General
_______
A. This
(1)
(2)
(3)
(4)
procedure has these tasks:
A removal of the primary static port
An installation of the primary static port
A removal of the alternate static port
An installation of the alternate static port.
TASK 34-11-02-020-801
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2.
___________________________
Primary
Static Port Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-44-000-801 p401, Lockwires Removal
(2) AMM TASK 25-21-46-000-801 p401, Sidewall Panel Removal
(3) AMM TASK 25-22-00-000-801 p401, Passenger Seat Removal
(4) AMM TASK 25-80-00-000-801 p401, Remove the Insulation Blanket
B. Access
(1) Location Zones
(a) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(b) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
C. Removal Procedure
(1)
SUBTASK 010-005
For the applicable passenger seats, do this task:
Removal (AMM TASK 25-22-00-000-801 p401).
(2)
SUBTASK 010-006
For the applicable sidewall panel, do this task:
Removal (AMM TASK 25-21-46-000-801 p401).
(3)
SUBTASK 010-007
For the applicable insulation blanket, do this task:
Insulation Blanket (AMM TASK 25-80-00-000-801 p401).
(4)
SUBTASK 020-017
Loosen the fitting [1] that connects the hose [2] to the static port
[6].
Passenger Seat
Sidewall Panel
Remove the
SUBTASK 020-018
WARNING:
_______
(5)
DO NOT BEND OR TWIST THE HOSE [2] WHEN YOU DISCONNECT THE HOSE
[2]. A BENT OR TWISTED HOSE [2] CAN CAUSE THE STATIC SYSTEM TO
MALFUNCTION.
Disconnect the hose [2].
EFFECTIVITY
34-11-02
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D633A101-ASA
Page 401
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
STA 420
STA 400
PRIMARY STATIC
PORTS
SEE
A
SEE
FWD
B
RIGHT SIDE PRIMARY STATIC PORT LOCATIONS SHOWN
(LEFT SIDE IS OPPOSITE)
INBD
A
Primary Static Port Installation
Figure 401 (Sheet 1)
34-11-02-990-802
EFFECTIVITY
34-11-02
F74862
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Page 402
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
[2] HOSE
AIRPLANE SKIN
[3] RETAINING
NUT
[4] WASHER
[1] FITTING
[5] WASHER
[9] UNION
[8] O-RING
[7] LOCKWIRE
[6] STATIC
PORT
PRIMARY STATIC PORT ASSEMBLY
(EXAMPLE)
B
Primary Static Port Installation
Figure 401 (Sheet 2)
EFFECTIVITY
34-11-02
F74987
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Page 403
Feb 10/01
A
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MAINTENANCE MANUAL
(6)
SUBTASK 020-019
Remove the fitting [1] from the static port [6].
(7)
SUBTASK 020-020
Remove the O-ring [8] from the static port [6].
(8)
SUBTASK 020-021
Put a cap on the hose [2] to prevent contamination.
(9)
SUBTASK 020-022
Use the sealant removal tool to remove the sealant from around the
static port [6] and retaining nut [3].
SUBTASK 020-023
(10) For the lockwire [7] on the retaining nut [3], do this task:
Lockwires Removal (AMM TASK 20-10-44-000-801 p401).
SUBTASK 020-024
CAUTION:
_______
DO NOT CAUSE DAMAGE TO THE OUTER SURFACE OF THE AIRPLANE SKIN.
THIS CAN CAUSE THE STATIC SYSTEM TO BE INACCURATE.
(11) Remove the retaining nut [3], washer [4] and washer [5].
SUBTASK 020-025
(12) Remove the static port [6] from the mounting hole.
TASK 34-11-02-400-801
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3.
________________________________
Primary
Static Port Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-44-400-801 p401, Lockwires Installation
(2) AMM TASK 25-21-46-400-801 p401, Sidewall Panel Installation
(3) AMM TASK 25-22-00-400-802 p401, Passenger Seat Installation
(4) AMM TASK 25-80-00-400-801 p401, Install the Insulation Blanket
(5) AMM TASK 34-11-00-790-804 p501, Left Static System Leak Test
(6) AMM TASK 34-11-00-790-806 p501, Right Static System Leak Test
(7) AMM TASK 51-21-95-300-801 p701, Alodine Treatment Application
(8) AMM TASK 51-31-00-390-805 p201, Fastener Seal Application
(9) SRM 51-10-01
B. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
6 ¦ Port
¦ 34-11-02
01
10 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
EFFECTIVITY
34-11-02
ú
ALL
D633A101-ASA
Page 404
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
ú
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~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
¦
¦ ASA 001-016;
¦
¦
¦
¦ Port
¦ 34-11-02
01
35 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(b) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
E. Installation Procedure
(1)
(2)
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SUBTASK 390-001
Apply sealant, BMS5-95, on the inner surface of the static port
installation hole.
SUBTASK 420-001
Put the static port [6] in the mounting hole.
(3)
SUBTASK 420-002
Install the washer [5], washer [4] and retaining nut [3] on the
static port [6].
(4)
SUBTASK 420-003
Tighten the retaining nut [3] to 100-105 pound-inches (11.3-11.9
newton-meters).
(5)
SUBTASK 420-004
For the retaining nut [3], do this task:
(AMM TASK 20-10-44-400-801 p401).
(6)
(7)
(8)
(9)
Lockwires Installation
SUBTASK 420-005
Make the static port [6] flush with the airplane skin to + 0.003/0.00 inch (+0.076/-0.00 mm).
(a) Use the microshaving tool, ZT306, to make the static port flush
(SRM 51-10-01).
SUBTASK 220-003
Make sure the surface finish on the static port [6] is 63 AA
maximum.
SUBTASK 210-002
Make sure no burrs or unwanted material are in the static port [6].
SUBTASK 620-001
For the surface of the static port [6], do this task: Alodine
Treatment Application (AMM TASK 51-21-95-300-801 p701).
EFFECTIVITY
34-11-02
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Page 405
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
SUBTASK 420-006
(10) Install the O-ring [8] on the fitting [1].
SUBTASK 420-007
(11) Install the fitting [1] on the static port [6].
CAUTION:
_______
(a)
APPLY COUNTER PRESSURE TO THE STATIC PORT [6]. IF YOU DO
NOT, THE STATIC PORT [6] CAN ROTATE AND CAUSE INCORRECT
OPERATION OF THE STATIC SYSTEM.
Make sure that you apply counter pressure to the static port
[6] while you install the fitting.
SUBTASK 390-002
(12) For the retaining nut [3] and the static port [6], do this task:
Fastener Seal Application (AMM TASK 51-31-00-390-805 p201).
SUBTASK 420-008
(13) Remove the cap from the hose [2].
SUBTASK 420-009
CAUTION:
_______
DO NOT BEND OR TWIST THE HOSE [2] WHEN YOU CONNECT THE HOSE
[2]. A BENT OR TWISTED HOSE [2] CAN CAUSE THE STATIC SYSTEM TO
MALFUNCTION.
(14) Connect the hose [2] to the static port [6].
CAUTION:
_______
(a)
APPLY COUNTER PRESSURE TO THE STATIC PORT [6]. IF YOU DO
NOT, THE STATIC PORT [6] CAN ROTATE AND CAUSE INCORRECT
OPERATION OF THE STATIC SYSTEM.
Make sure that you apply counter pressure to the static port
[6] while you install the fitting [1].
SUBTASK 420-010
(15) Tighten the fitting [1] to 100-125 pound-inches (11.3-14.1
newton-meters).
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SUBTASK 790-001
(16) For the primary static system, do the applicable leak test below:
(a) Do this task: Left Static System Leak Test
(AMM TASK 34-11-00-790-804 p501).
(b) Do this task: Right Static System Leak Test
(AMM TASK 34-11-00-790-806 p501).
SUBTASK 410-001
(17) For the insulation blanket, do this task:
Blanket (AMM TASK 25-80-00-400-801 p401).
EFFECTIVITY
Install the Insulation
34-11-02
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Feb 10/01
A
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MAINTENANCE MANUAL
SUBTASK 410-002
(18) For the sidewall panel, do this task:
(AMM TASK 25-21-46-400-801 p401).
SUBTASK 410-003
(19) For the passenger seats, do this task:
(AMM TASK 25-22-00-400-802 p401).
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Sidewall Panel Installation
Passenger Seat Installation
TASK 34-11-02-000-802
4.
_____________________________
Alternate
Static Port Removal (Fig. 402)
A. References
(1) AMM TASK 20-10-44-000-801 p401, Lockwires Removal
(2) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
B. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
C. Access
(1) Location Zones
(a) 121 Forward Cargo Compartment, Left
(b) 122 Forward Cargo Compartment, Right
D. Removal Procedure
(1)
SUBTASK 010-004
For the applicable cargo liner, do this task: Remove the Sidewall
Lining for the Cargo Compartment (AMM TASK 25-52-06-000-801 p401).
(2)
SUBTASK 020-009
Loosen the fitting [1] that connects the hose [2] to the static port
[6].
SUBTASK 020-010
CAUTION:
_______
DO NOT BEND OR TWIST THE HOSE [2] WHEN YOU DISCONNECT THE HOSE
[2]. A BENT OR TWISTED HOSE [2] CAN CAUSE THE STATIC SYSTEM TO
MALFUNCTION.
(3)
Disconnect the hose [2].
(4)
SUBTASK 020-011
Put a cap on the hose [2] to prevent contamination.
(5)
SUBTASK 020-012
Remove the fitting [1] from the static port [6].
(6)
SUBTASK 020-013
Remove the O-ring [8] from the static port [6].
EFFECTIVITY
34-11-02
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ALL
D633A101-ASA
Page 407
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
FORWARD
CARGO
DOOR
ALTERNATE
STATIC PORT
SEE
A
ALTERNATE
STATIC PORT
ASSEMBLY
SEE
B
FWD
INBD
RIGHT SIDE ALTERNATE STATIC PORT LOCATION SHOWN
(LEFT SIDE IS OPPOSITE)
A
Alternate Static Port Installation
Figure 402 (Sheet 1)
34-11-02-990-803
EFFECTIVITY
34-11-02
F74988
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Page 408
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
[2] HOSE
[3] RETAINING
NUT
[1] FITTING
[7] LOCKWIRE
[8] O-RING
[4] WASHER
[5] WASHER
AIRPLANE
SKIN
[6] STATIC
PORT
ALTERNATE STATIC PORT ASSEMBLY
B
Alternate Static Port Installation
Figure 402 (Sheet 2)
EFFECTIVITY
34-11-02
F75189
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Page 409
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
(7)
SUBTASK 140-002
Use the sealant removal tool to remove the sealant from around the
static port [6] and the retaining nut [3].
(8)
SUBTASK 020-014
For the lockwire [7] on the retaining nut [3], do this task:
Lockwires Removal (AMM TASK 20-10-44-000-801 p401).
SUBTASK 020-015
CAUTION:
_______
(9)
DO NOT CAUSE DAMAGE TO THE OUTER SURFACE OF THE AIRPLANE SKIN.
THIS CAN CAUSE THE STATIC SYSTEM TO BE INACCURATE.
Remove the retaining nut [3], washer [4] and washer [5].
SUBTASK 020-016
(10) Remove the static port [6] from its mounting hole.
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TASK 34-11-02-400-802
5.
__________________________________
Alternate
Static Port Installation (Fig. 402)
A. References
(1) AMM TASK 20-10-44-400-801 p401, Lockwires Installation
(2) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
(3) AMM TASK 34-11-00-790-808 p501, Alternate Static System Leak Test
(4) AMM TASK 51-21-95-300-801 p701, Alodine Treatment Application
(5) AMM TASK 51-31-00-390-805 p201, Fastener Seal Application
(6) SRM 51-10-01
B. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 402
6 ¦ Port
¦ 34-11-02
01
10 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 121 Forward Cargo Compartment, Left
(b) 122 Forward Cargo Compartment, Right
E. Installation Procedure
(1)
SUBTASK 390-003
Apply sealant, BMS5-95, on the inner surface of the static port
installation hole.
EFFECTIVITY
34-11-02
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ALL
D633A101-ASA
Page 410
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
(2)
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SUBTASK 420-011
Put the static port [6] in the mounting hole.
(3)
SUBTASK 420-012
Install the washer [5], washer [4] and retaining nut [3] on the
static port [6].
(4)
SUBTASK 420-013
Tighten the retaining nut [3] to 100-105 pound-inches (11.3-11.9
newton-meters).
(5)
SUBTASK 420-014
For the retaining nut [3], do this task:
(AMM TASK 20-10-44-400-801 p401).
(6)
(7)
(8)
(9)
Lockwires Installation
SUBTASK 420-015
Make the alternate static port flush with the airplane skin to +
0.003/- 0.00 inch (+0.076/-0.00 mm).
(a) Use the microshaving tool, ZT306, to make the static port flush
(SRM 51-10-01).
SUBTASK 220-004
Make sure the surface finish on the static port [6] is 63 AA
maximum.
SUBTASK 210-003
Make sure no burrs or unwanted material are in the static port [6].
SUBTASK 140-003
For the surface of the static port [6], do this task: Alodine
Treatment Application (AMM TASK 51-21-95-300-801 p701).
SUBTASK 420-016
(10) Install the O-ring [8] on the fitting [1].
SUBTASK 420-017
(11) Install the fitting [1] on the static port [6].
CAUTION:
_______
(a)
APPLY COUNTER PRESSURE TO THE STATIC PORT [6]. IF YOU DO
NOT, THE STATIC PORT [6] CAN ROTATE AND CAUSE INCORRECT
OPERATION OF THE STATIC SYSTEM.
Make sure that you apply counter pressure to the static port
[6] while you install the fitting [1].
SUBTASK 390-004
(12) For the retaining nut [3] and the static port [6], do this task:
Fastener Seal Application (AMM TASK 51-31-00-390-805 p201).
EFFECTIVITY
34-11-02
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Page 411
Feb 10/01
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MAINTENANCE MANUAL
SUBTASK 420-018
(13) Remove the cap from the hose [2].
SUBTASK 420-019
CAUTION:
_______
DO NOT BEND OR TWIST THE HOSE [2] WHEN YOU CONNECT THE HOSE
[2]. A BENT OR TWISTED HOSE [2] CAN CAUSE THE STATIC SYSTEM TO
MALFUNCTION.
(14) Connect the hose [2] to the static port [6].
CAUTION:
_______
(a)
APPLY COUNTER PRESSURE TO THE STATIC PORT [6]. IF YOU DO
NOT, THE STATIC PORT [6] CAN ROTATE AND CAUSE INCORRECT
OPERATION OF THE STATIC SYSTEM.
Make sure that you apply counter pressure to the static port
[6] while you install the fitting [1].
SUBTASK 420-020
(15) Tighten the fitting [1] to 100-125 pound-inches (11.3-14.1
newton-meters).
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SUBTASK 790-002
(16) For the alternate static system, do this task: Alternate Static
System Leak Test (AMM TASK 34-11-00-790-808 p501).
SUBTASK 410-004
(17) For the applicable sidewall liner, do this task:
Sidewall Lining for the Cargo Compartment
(AMM TASK 25-52-06-400-801 p401).
EFFECTIVITY
Install the
34-11-02
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Page 412
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MAINTENANCE MANUAL
STATIC PORT - INSPECTION/CHECK
______________________________
1.
General
_______
A. This procedure has these tasks:
(1) A detailed inspection of the static ports and the skin surface near
the port
(2) A visual inspection of the static ports and the skin surface near
the port.
TASK 34-11-02-200-801
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2.
_________________________________
Static
Port - Detailed Inspection (Figs. 601,602)
A. References
(1) AMM 34-11-02
(2) AMM TASK 34-11-02-020-801 p401, Primary Static Port Removal
(3) AMM TASK 34-11-02-400-801 p401, Primary Static Port Installation
(4) SRM 51-10-01
(5) SRM 51-10-03
B. Access
(1) Location Zones
(a) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(b) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
C. Inspection Procedure for the Primary Static Ports
(1)
(2)
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(3)
SUBTASK 220-001
Visually examine the primary static port for damage.
(a) Make sure that the edges of the port are not above the surface
of the airplane skin more than 0.003 inch (0.076 mm).
(b) Make sure that the depth of any scratches on the port are less
than 0.010 inch (0.254 mm).
SUBTASK 210-001
Visually examine the holes in the port for contamination.
SUBTASK 900-001
If there is a problem with a primary static port, replace the port.
(a) These are the tasks:
Primary Static Port Removal (AMM TASK 34-11-02-020-801 p401),
Primary Static Port Installation
(AMM TASK 34-11-02-400-801 p401).
EFFECTIVITY
34-11-02
ALL
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Page 601
Feb 10/01
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MAINTENANCE MANUAL
STA
259.50
STA
360
STA
460
STA
178
WL
208.1
PRIMARY STATIC PORTS
(LEFT SIDE)
STA
460
STA
360
STA
259.50
STA
178
WL
208.1
PRIMARY STATIC PORTS
(RIGHT SIDE)
Primary Static Port Inspection
Figure 601 (Sheet 1)
L49558
34-11-02-990-801
EFFECTIVITY
34-11-02
ALL
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Page 602
Feb 10/01
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MAINTENANCE MANUAL
6 INCH SCALE
LOCATION OF SCALE
0.2 INCH (TYPICAL)
LOCATION
NUMBER
1
SKIN
MEASURE THE MAXIMUM CLEARANCE
DIP
UP
6 INCH SCALE
UPPER
PORT
DOWN
2
SKIN
MAKE THE END OF THE SCALE TOUCH THE SKIN.
MEASURE THE CLEARANCE AT THE HIGH END
BULGE WITH MOVEMENT
3
6 INCH SCALE
LOWER
PORT
4
SKIN
LOCATION
UPPER PORT
LOWER PORT
1
2
WAVINESS
3
4
WAVINESS
LOCATION
UPPER PORT
LOWER PORT
1
2
WAVINESS
3
4
WAVINESS
DIP
THE SCALE IS ON A LEVEL AREA.
MEASURE THE CLEARANCE AT THE TWO ENDS.
LEFT SIDE
BULGE WITH MOVEMENT BULGE WITH PLATEAU
MAXIMUM FORWARD
-0.010
-0.004
-0.007
0.008
0.020
DIP
BULGE WITH PLATEAU
AFT
0.000
0.010
MAXIMUM FORWARD
AFT
MAXIMUM
0.008
0.020
0.007
RIGHT SIDE
BULGE WITH MOVEMENT BULGE WITH PLATEAU
MAXIMUM FORWARD
-0.010
-0.000
-0.005
AFT
MAXIMUM FORWARD
0.008
0.020
AFT
MAXIMUM
0.000
0.010
0.008
0.020
0.014
EXAMPLE CALCULATIONS OF SKIN WAVINESS MEASUREMENT
NEAR PRIMARY STATIC PORTS
Primary Static Port Inspection
Figure 601 (Sheet 2)
L49588
EFFECTIVITY
34-11-02
ALL
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Page 603
Feb 10/01
A
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MAINTENANCE MANUAL
6 INCH SCALE
LOCATION OF SCALE
0.2 INCH (TYPICAL)
LOCATION
NUMBER
1
SKIN
MEASURE THE MAXIMUM CLEARANCE
DIP
UP
6 INCH SCALE
UPPER
PORT
DOWN
2
SKIN
MAKE THE END OF THE SCALE TOUCH THE SKIN.
MEASURE THE CLEARANCE AT THE HIGH END
BULGE WITH MOVEMENT
3
LOWER
PORT
6 INCH SCALE
4
SKIN
LOCATION
DIP
THE SCALE IS ON A LEVEL AREA.
MEASURE THE CLEARANCE AT THE TWO ENDS.
LEFT SIDE
BULGE WITH MOVEMENT BULGE WITH PLATEAU
MAXIMUM FORWARD
UPPER PORT
LOWER PORT
MAXIMUM FORWARD
AFT
MAXIMUM
DIP
RIGHT SIDE
BULGE WITH MOVEMENT BULGE WITH PLATEAU
MAXIMUM FORWARD
LOWER PORT
AFT
1
2
WAVINESS
3
4
WAVINESS
LOCATION
UPPER PORT
BULGE WITH PLATEAU
AFT
MAXIMUM FORWARD
AFT
MAXIMUM
1
2
WAVINESS
3
4
WAVINESS
FORM FOR SKIN WAVINESS MEASUREMENT NEAR PRIMARY STATIC PORTS
Primary Static Port Inspection
Figure 601 (Sheet 3)
L49603
EFFECTIVITY
34-11-02
ALL
D633A101-ASA
Page 604
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
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(4)
SUBTASK 900-003
Measure the step height of the primary static ports.
NOTE:
____
(a)
The step height is the distance between the surface of the
skin and the primary static ports.
Make sure the primary static ports have a step height less than
0.002 inch (0.051mm) below the skin.
NOTE:
____
(b)
(c)
(d)
(5)
(6)
This tolerance is for the installed primary static
ports. When you install new primary static ports, the
tolerance is -0.000 below to +0.003 inch above the skin
(-0.000 to +0.076 mm) (AMM 34-11-02), (SRM 51-10-03).
If the condition above is not satisfactory, then replace the
port. These are the tasks:
Primary Static Port Removal (AMM TASK 34-11-02-020-801 p401),
Primary Static Port Installation
(AMM TASK 34-11-02-400-801 p401).
Make sure the primary static ports have a step height less than
0.006 inch (0.152 mm) above the skin.
If the condition above is not satisfactory, then decrease the
port step height (SRM 51-10-01).
SUBTASK 210-006
Visually examine the airplane skin surface in a three inch radius
around the static port.
(a) Make sure the surface of the skin is not rough.
(b) If the skin is rough, refer to the Structural Repair Manual
(SRM 51-10-01).
SUBTASK 900-004
Find the surface waviness of the airplane skin in the area of each
primary static port:
(a) Find the primary static ports on each side of the airplane.
(b) Measure the skin waviness at a distance of 0.2 inch (5.1 mm)
above and below each primary static port (Fig. 601).
1) Align the center of a metal 6-inch scale with the center of
the static port.
2) Measure horizontally.
(c) Examine the area for a dip or bulge condition (Table 601).
EFFECTIVITY
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TABLE 34-11-02-993-806
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ Skin Condition ¦
Description
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Dip
¦ The skin touches the two ends of the scale
¦
¦
¦ but not the middle part of the scale.
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Bulge
¦ The skin touches the middle part of the scale
¦
¦
¦ but not at the ends of the scale.
¦
¦
¦ There are two types of bulges:
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Bulge
¦ The 6-inch scale can easily
¦
¦ with Movement ¦ move up or down on the bulge.
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
Bulge
¦ The 6-inch scale is on a level area of the
¦
¦ with Plateau ¦ bulge and is resistant to up and down movement. ¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 601
(d)
Measure and record the waviness:
NOTE:
____
1)
2)
3)
Use the table in Figure 601 (Sheet 2) as an example.
Record the data in the table in Figure 601 (Sheet 3). A
dip value is always a negative number. A bulge value is
always a positive number.
For a dip, use these steps:
a) Use a feeler gage to measure the maximum clearance
between the scale and the skin.
b) Record this data as a negative number.
For a bulge with movement, use these steps:
a) Move the scale up or down to make the end touch the
skin.
b) When one end touches the skin, use a feeler gage to
measure the clearance between the high end of the scale
and the skin.
c) Move the other end of the scale against the skin.
d) Measure the clearance.
e) Use the larger of the two values and record the data as
a positive number.
For a bulge with plateau, use these steps:
a) Put the scale on the level area.
b) Use a feeler gage to measure the clearance between the
two ends of the scale and the skin.
c) Use the larger of the two values and record the data as
a positive number.
EFFECTIVITY
34-11-02
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Page 606
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(e)
(f)
(7)
(8)
D.
Calculate the waviness for each of the four static ports.
1) Use this formula if the measurements above and below the
static ports are dips:
a) Waviness = (DIP above + DIP below)/2
2) Use this formula if the measurements above and below the
static ports are bulges with movement:
a) Waviness = (BULGE above + BULGE below)/4
3) Use this formula if the measurements above and below the
static ports are bulges with plateau:
a) Waviness = (BULGE above + BULGE below)/2
4) Use this formula if one measurement is a dip and the other
measurement is a bulge with movement:
a) Waviness = (DIP + 1/2 BULGE)/2
5) Use this formula if one measurement is a dip and the other
measurement is a bulge with plateau:
a) Waviness = (DIP + BULGE)/2
Make sure the waviness is not more than |0.02 inch (|0.51 mm).
SUBTASK 900-005
If the skin waviness is not satisfactory, go to the Structural
Repair Manual (SRM 51-10-01), (SRM 51-10-03).
SUBTASK 900-006
Make sure rivets in a 3-inch radius from the center of a static
pressure port are flush with the skin surface to a tolerance of
+0.003 to -0.000 inch (+0.076 to -0.00 mm).
(a) Make sure the fastener spacing is 2.0 inches (50.8 mm) to 3.0
inches (76.2 mm) in the circular and horizontal directions.
(b) If any of the conditions above are not satisfactory, go to the
Structural Repair Manual (SRM 51-10-01), (SRM 51-10-03).
Inspection Procedure for the Alternate Static Ports
(1)
SUBTASK 220-008
Inspect the alternate static ports with the following steps:
(a) Put the edge of a steel rule horizontally across the center of
the static pressure port.
(b) Measure the space between the skin and the steel rule.
(c) Make sure the surface does not have a space of more than 0.007
inch (0.177 mm) in a 3-inch radius from the center of the
static port.
(d) Make sure rivets in a 3-inch radius from the center of a static
pressure port are flush with the skin surface to a tolerance of
+0.003 to -0.000 inch (+0.076 to -0.000 mm).
(e) Make sure the fastener spacing is 2.0 inches (50.8 mm) to 3.0
inches (76.2 mm) in the circular and horizontal directions.
EFFECTIVITY
34-11-02
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MAINTENANCE MANUAL
FORWARD
CARGO
DOOR
ALTERNATE STATIC PORT
(LEFT SIDE IS OPPOSITE)
SEE
A
STATIC PORT
SEE
MEASUREMENT
B
AIRPLANE SKIN
ALTERNATE STATIC PORT
A
6.0-INCH STRAIGHT EDGE
AIRPLANE SKIN
FEELER GAUGE
STATIC PORT
B
Alternate Static Port Inspection
Figure 602
G03179
34-11-02-990-805
EFFECTIVITY
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34-11-02
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(2)
SUBTASK 220-009
If any of the conditions above are not satisfactory, go to the
Structural Repair Manual (SRM 51-10-01), (SRM 51-10-03).
TASK 34-11-02-200-802
3.
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_______________________________
Static
Port - Visual Inspection
A. References
(1) AMM TASK 34-11-02-000-802 p401, Alternate Static Port Removal
(2) AMM TASK 34-11-02-020-801 p401, Primary Static Port Removal
(3) AMM TASK 34-11-02-400-801 p401, Primary Static Port Installation
(4) AMM TASK 34-11-02-400-802 p401, Alternate Static Port Installation
(5) SRM 51-10-01
B. Access
(1) Location Zones
(a) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(b) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
C. Inspection Procedure
(1)
SUBTASK 220-005
Visually examine the port for damage.
(2)
SUBTASK 210-004
Visually examine the holes in the port for contamination.
(3)
SUBTASK 900-002
If there is a problem with a primary static port, replace the port.
(a)
(4)
(5)
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These are the tasks:
Primary Static Port Removal (AMM TASK 34-11-02-020-801 p401),
Primary Static Port Installation
(AMM TASK 34-11-02-400-801 p401).
SUBTASK 900-007
If there is a problem with an alternate static port, replace the
port.
(a) These are the tasks:
Alternate Static Port Removal (AMM TASK 34-11-02-000-802 p401),
Alternate Static Port Installation
(AMM TASK 34-11-02-400-802 p401).
SUBTASK 220-006
Visually examine the surface of the airplane skin in a three inch
radius around the port:
(a) Make sure that the surface of the skin is not rough.
(b) If the skin is rough, refer to the Structural Repair Manual
(SRM 51-10-01).
EFFECTIVITY
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34-11-02
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MAINTENANCE MANUAL
AIR DATA INSTRUMENTS - ADJUSTMENT/TEST
______________________________________
1.
General
_______
A. This procedure has this task:
(1) A system test of the Standby Altimeter/Airspeed Indicator.
TASK 34-13-00-730-801
2.
__________________________________
Air
Data Instruments - System Test
A. General
(1) These instructions apply to the task:
(a) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(b) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(c) When you apply pressure to a pitot system, the rate must not be
more than 300 knots for each minute.
(d) When you release pressure from a pitot system, the rate must
not be more than 300 knots for each minute.
(e) Do not connect or disconnect the test equipment while you have
pressure in the pitot-static system.
(f) Make sure that you do these steps before installing the probe
adapter on the probe:
1) Flush the probe adapter with water.
NOTE:
____
(g)
(h)
(i)
B.
C.
Use equal parts of water and ethylene glycol when
the temperature is between 32° and -40°F (-40° to
0°C).
2) Blow dry, filtered air through the adapter.
3) Wipe the probe with a damp cloth.
Make sure that the seals used on the static ports do not extend
into the static ports.
Make sure that you do not cause damage to the surface of the
static ports when you remove the seals.
At each test value, permit the pressure to become stable for
one minute.
Do not hit or shake the indicators before you read the values.
(j)
References
(1) AMM TASK 24-22-00-860-813 p201, Supply External Power
(2) AMM TASK 24-22-00-860-814 p201, Remove External Power
Equipment
(1) Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
EFFECTIVITY
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MAINTENANCE MANUAL
(c)
D.
E.
P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(3) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
EFFECTIVITY
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MAINTENANCE MANUAL
F.
Prepare for the System Test
(1)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P18-3:
1) 18C2
HEATERS TEMP PROBE
2) 18D3
HEATERS ALPHA VANE RIGHT
3) 18D5
HEATERS F/O PITOT
4) 18D6
HEATERS AUX PITOT
(2)
SUBTASK 860-002
Do this task: Supply External Power
(AMM TASK 24-22-00-860-813 p201).
(3)
SUBTASK 750-001
Make sure that you feel vibration on the casing of the Standby
Altimeter/Airspeed Indicator.
(4)
SUBTASK 860-004
Set the BARO scale of the standby indicator to 29.92 inches of
mercury (1013 millibars).
SUBTASK 480-001
CAUTION:
_______
(5)
(6)
DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE SEAL.
Seal the alternate static ports with vinyl adhesive tape, Scotch
Brand No.471 at these locations:
(a) The static port located at STA 430, WL 167, RBL 49.
(b) The static port located at STA 430, WL 167, LBL 49.
SUBTASK 480-003
Remove the cap from the alternate static drain located near STA 226,
WL 155, RBL 18, in the electronic equipment compartment below the
E-5 rack.
(7)
SUBTASK 480-007
Install the coupling, 1QF2-3-64C, on the alternate static drain.
(8)
SUBTASK 480-006
Connect the test set, to the coupling, 1QF2-3-64C.
EFFECTIVITY
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MAINTENANCE MANUAL
SUBTASK 170-001
CAUTION:
_______
(9)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER WITH
WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE. DAMAGE TO
THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter, P75701-4, with water.
NOTE:
____
Use equal parts of water and ethylene glycol when the
temperature is between 32° and -40°F (-40° to 0°C).
SUBTASK 480-008
(10) Blow dry, filtered air through the adapter, P75701-4.
SUBTASK 480-009
(11) Wipe the probe with a damp cloth.
SUBTASK 480-004
CAUTION:
_______
MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
(12) Install the adapter, P75701-4, on the lower pitot probe located at
STA 192, WL 213, RBL 34.
SUBTASK 480-005
(13) Connect the test set, to the adapter, P75701-4.
SUBTASK 010-001
(14) Lower the P5 forward overhead panel.
(a) Loosen the 1/4-turn fasteners that hold the P5 forward overhead
panel in position and let the panel rotate downward.
SUBTASK 020-001
(15) Disconnect the static pressure hose located behind the P5 forward
overhead panel.
EFFECTIVITY
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G.
Air Data Instruments Test
(1)
SUBTASK 860-005
Apply pressure to the alternate pitot and alternate static systems
for each test point as shown in (Table 501):
TABLE 34-13-00-993-801
~¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦ TEST ¦ STATIC ¦ PITOT
¦
STBY ALT.
¦ STBY A/S ¦
¦ POINT ¦ (In. Hg) ¦ (In. Hg) ¦
(feet)
¦ (knots) ¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
1
¦ 29.921 ¦ 30.616 ¦
0|30
¦ 90|3.5 ¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
2
¦ 24.896 ¦ 27.996 ¦
5,000|50
¦ 250|3.5 ¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
3
¦ 16.886 ¦ 17.703 ¦
15,000|110 ¦ 130|3.5 ¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
4
¦ 11.104 ¦ 17.013 ¦
25,000|160 ¦ 340|8
¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
5
¦
7.041 ¦ 10.963 ¦
35,000|210 ¦ 279|6
¦
»¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
6
¦
5.286 ¦
7.95
¦
41,000|235 ¦ 233|6
¦
²¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
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Table 501
SUBTASK 780-001
Make sure that the altitude and airspeed information displayed on
the standby altitude/airspeed indicator is in tolerance for each
test point shown in Table 501.
Put the Airplane Back to Its Usual Condition
(2)
H.
(1)
SUBTASK 860-006
Put the system back to ambient pressure.
SUBTASK 080-001
CAUTION:
_______
(2)
(3)
DO NOT DISCONNECT THE STATIC SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE STANDBY ALTIMETER/AIRSPEED INDICATOR CAN OCCUR.
Disconnect the test set, and the coupling, 1QF2-3-64C, from the
alternate static drain located near STA 226, WL 155, RBL 18.
SUBTASK 080-002
Install the cap on the alternate static drain.
EFFECTIVITY
34-13-00
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MAINTENANCE MANUAL
(4)
SUBTASK 080-003
Remove the vinyl adhesive tape, Scotch Brand No.471 from both of the
alternate static ports.
WARNING:
_______
(a)
(b)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM
THE STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT
OPERATE CORRECTLY.
Remove
static
Remove
static
the vinyl adhesive tape,
port located at STA 430,
the vinyl adhesive tape,
port located at STA 430,
Scotch Brand No.471 from the
WL 167, RBL 49.
Scotch Brand No.471 from the
WL 167, LBL 49.
SUBTASK 080-004
CAUTION:
_______
DO NOT DISCONNECT THE PITOT SYSTEM TEST ADAPTER WHEN THE
PITOT-STATIC SYSTEM IS NOT AT AMBIENT PRESSURE. IF YOU DO,
DAMAGE TO THE STANDBY ALTIMETER/AIRSPEED INDICATOR CAN OCCUR.
(5)
Disconnect the test set, from the adapter, P75701-4.
(6)
SUBTASK 080-005
Remove the adapter, P75701-4, from the pitot probe.
(7)
SUBTASK 410-001
Connect the static pressure hose located behind the P5 forward
overhead panel.
(8)
SUBTASK 410-002
Lift the P5 forward overhead panel to the closed position and turn
the 1/4-turn fasteners.
(9)
SUBTASK 860-007
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P18-3:
1) 18C2
HEATERS TEMP PROBE
2) 18D3
HEATERS ALPHA VANE RIGHT
3) 18D5
HEATERS F/O PITOT
4) 18D6
HEATERS AUX PITOT
SUBTASK 860-008
(10) Do this task: Remove External Power
(AMM TASK 24-22-00-860-814 p201).
EFFECTIVITY
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STANDBY ALTIMETER/AIRSPEED INDICATOR - REMOVAL/INSTALLATION
___________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the standby altimeter/airspeed indicator
(2) An installation of the standby altimeter/airspeed indicator.
TASK 34-13-01-000-801
2.
____________________________________________
Standby
Altimeter/Airspeed Indicator Removal (Fig. 401)
A. References
(1) AMM TASK 20-40-12-000-803 p201, Conductive Dust Cap and Connector
Cover Installation
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-3:
1) 6D8
EMER PANEL LTG
(b) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
SUBTASK 020-001
Remove the standby altimeter/airspeed indicator [3]:
(a) Loosen the two adjustment screws [1] adjacent to the indicator
[3] (Fig. 401).
NOTE:
____
CAUTION:
_______
Do not remove the adjustment screws [1]. Loosen the
adjustment screws [1] until the standby
altimeter/airspeed indicator [3] can be removed.
(b)
CAREFULLY PULL THE INDICATOR [3] FROM THE INSTRUMENT
PANEL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE ELECTRICAL
CABLE AND THE HOSES ON THE REAR OF THE INDICATOR [3].
Pull the indicator [3] from the instrument panel until you can
get access to the electrical connector [4], pitot hose [5] and
static hose [6].
NOTE:
____
If the indicator [3] is not easy to remove, loosen the
remaining two mounting screws [2] to make the removal
procedure easier.
EFFECTIVITY
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SEE
A
FLIGHT COMPARTMENT
[2] MOUNTING
SCREW
[4] ELECTRICAL
CONNECTOR
[1] ADJUSTMENT
SCREW
[3] STANDBY
ALTIMETER/
AIRSPEED
INDICATOR
[5] PITOT
HOSE
[1] ADJUSTMENT
SCREW
[6] STATIC
HOSE
[2] MOUNTING
SCREW
A
Standby Altimeter/Airspeed Indicator Installation
Figure 401
F73470
34-13-01-990-801
EFFECTIVITY
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CAUTION:
_______
(c)
(d)
(e)
(f)
DO NOT DISCONNECT THE PITOT-STATIC SYSTEM HOSES WHEN THE
SYSTEM IS NOT AT AMBIENT PRESSURE. THIS CAN CAUSE DAMAGE
TO THE INDICATOR [3].
Disconnect the pitot hose [5] and static hose [6] from the
indicator [3].
Disconnect the electrical connector [4].
Remove the indicator [3].
Do this task: Conductive Dust Cap and Connector Cover
Installation (AMM TASK 20-40-12-000-803 p201).
TASK 34-13-01-400-801
3.
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_________________________________________________
Standby
Altimeter/Airspeed Indicator Installation (Fig. 401)
A. References
(1) AMM TASK 20-40-12-400-803 p201, Conductive Dust Cap and Conductor
Cover Removal
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
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IPC
¦
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¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
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¦ 401
3 ¦ Indicator assy
¦ 34-13-01
01
60 ¦
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C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
D. Installation Procedure
(1)
(2)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-3:
1) 6D8
EMER PANEL LTG
(b) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
SUBTASK 420-001
Install the standby altimeter/airspeed indicator [3]:
(a) Do this task: Conductive Dust Cap and Conductor Cover Removal
(AMM TASK 20-40-12-400-803 p201).
(b) Examine the electrical connector [4] for bent or broken pins.
(c) Connect the electrical connector [4] at the rear of the
indicator [3].
EFFECTIVITY
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CAUTION:
_______
(d)
DO NOT CONNECT THE PITOT-STATIC SYSTEM HOSES WHEN THE
SYSTEM IS NOT AT AMBIENT PRESSURE. THIS CAN CAUSE DAMAGE
TO THE INDICATOR [3].
(e)
Connect the pitot hose [5] and static hose [6] to the indicator
[3].
Make sure the pitot-static system hose connections are locked
in the sealed position.
Install the indicator [3] into the instrument panel.
Tighten the two adjustment screws [1] adjacent to the indicator
[3] (Fig. 401).
(f)
(g)
NOTE:
____
(3)
(4)
(5)
(6)
SUBTASK 860-003
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-004
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-3:
1) 6D8
EMER PANEL LTG
(b) Circuit Breaker Panel, P18-2:
1) 18D10
STBY ALTM/ASI VIB
SUBTASK 750-001
Make sure that the indicator [3] lights are on.
SUBTASK 780-001
If you install a quick-disconnect fitting on the replacement
indicator, do this task: (Reference TBD) for the Auxiliary Pitot
and Alternate Static Systems.
NOTE:
____
(7)
If necessary, tighten the two mounting screws [2].
If you do a replacement or installation of a quick-disconnect
fitting, you must do a leak check. If you only disconnect a
quick-disconnect fitting, no leak check is required.
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MACH AIRSPEED WARNING SYSTEM - ADJUSTMENT/TEST
______________________________________________
1.
General
_______
A. This procedure has this task:
(1) A system test of the Mach Airspeed Warning System.
TASK 34-16-00-730-801
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2.
__________________________________________
Mach
Airspeed Warning System - System Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 25-52-06-000-801 p401, Remove the Sidewall Lining for the
Cargo Compartment
(4) AMM TASK 25-52-06-400-801 p401, Install the Sidewall Lining for the
Cargo Compartment
B. Equipment
(1) Adapter (or alternative tool)
(a) P75701-4 Adapter - Pitot Probe (recommended)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(b) P33410H-125-4 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(c) P75701M2-3 Adapter - Pitot Probe (alternative)
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(2) 33410LH-125-4 Adapter - Static Port
NAV-AIDS, Ltd. (Vendor Code 38002)
2955 Diab St., St. Laurent, Canada H4S 1M1
(3) 1QF2-3-64C Coupling - Quick Disconnect, Static System Drain Fitting
Hydraflow (Vendor Code 24984)
13259 E. 166th St., Cerritos CA 90701-2203
(4) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
EFFECTIVITY
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(e)
C.
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D.
E.
ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
Consumable Materials
(1) G02219 Tape, Yellow vinyl adhesive - Scotch Brand No.471
Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
Prepare for the System Test
(1)
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SUBTASK 910-001
These instructions apply to the task:
(a) You can use either the drain coupling or the static port
adapter to pressurize the static system. The drain adapter is
recommended and the static port adapter is alternate.
(b) When you apply pressure to a static system, the rate must not
be more than 5,000 feet for each minute.
(c) When you release pressure from a static system, the rate must
not be more than 5,000 feet for each minute.
(d) When you apply pressure to a pitot system, the rate must not be
more than 300 knots for each minute.
(e) When you release pressure from a pitot system, the rate must
not be more than 300 knots for each minute.
(f) At each test value, permit the pressure to become stable for
one minute.
EFFECTIVITY
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SUBTASK 860-001
WARNING:
_______
(2)
OPEN THE CIRCUIT BREAKER FOR THE FLAP LOAD RELIEF. IF YOU DO
NOT OPEN THIS CIRCUIT BREAKER, YOU CAN CAUSE INJURY TO
PERSONNEL AND DAMAGE TO EQUIPMENT.
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-2:
1) 6A6
FLIGHT CONTROL FLAP LOAD RELIEF
(b) Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
(3)
SUBTASK 860-002
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(4)
SUBTASK 860-004
Make sure that the vanes are streamlined with the airplane to set
them to zero degrees.
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NOTE:
____
This will minimize the static source error correction of the
air pressures.
SUBTASK 860-016
For the equipment that follows, set the Baro Ref to 29.92 Hg:
(a) Captain's and First Officer's (F/O's) altimeters
(b) The air data test set.
Installation of Drain Coupling, 1QF2-3-64C (Recommended):
(5)
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F.
SUBTASK 480-006
WARNING:
_______
WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION:
_______
DO NOT EXTEND THE TAPE INTO THE STATIC PORTS. DAMAGE TO THE
SURFACE OF THE PORT CAN OCCUR WHEN YOU REMOVE THE TAPE.
(1)
Seal these primary static ports with vinyl adhesive tape, Scotch
Brand No.471:
(a) Seal the upper and lower primary static ports on the right side
of the fuselage.
EFFECTIVITY
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(b)
(2)
(3)
Seal the upper and lower primary static ports on the left side
of the fuselage.
SUBTASK 480-007
Open the primary static system drain access panel, on the left
sidewall lining, in the forward cargo compartment.
(a) Do this task: Remove the Sidewall Lining for the Cargo
Compartment (AMM TASK 25-52-06-000-801 p401).
SUBTASK 480-008
Remove the caps from the left and right static system
NOTE:
____
(4)
G.
drains.
The forward drain is for the left system. The aft drain is
for the right system. The forward drain is known as the No.3
Captain's Static Drain. The aft drain is known as the No.4
First Officer's Static Drain.
SUBTASK 480-009
Install the coupling, 1QF2-3-64C, on the left and right static
system drains.
SUBTASK 480-010
(5) Connect the test set to each coupling, 1QF2-3-64C.
Installation of Static Port Adapter, 33410LH-125-4 (Alternate):
SUBTASK 480-001
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CAUTION:
_______
(1)
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INSTALL THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Install the adapter, 33410LH-125-4, on the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
EFFECTIVITY
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SUBTASK 480-002
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WARNING:
_______
CAUTION:
_______
(2)
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WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE
COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE
ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH
MAY LEAD TO LOSS OF SAFE FLIGHT.
H.
DO NOT PUSH THE TAPE INTO THE STATIC PORTS. YOU CAN CAUSE
DAMAGE TO THE STATIC SYSTEM IF YOU PUSH TAPE INTO THE STATIC
PORT.
Seal the static ports at these locations with tape, Scotch Brand
No.471:
(a) The captain's static port on the left side of the fuselage.
(b) The first officer's static port on the left side of the
fuselage.
SUBTASK 480-003
(3) Connect the test set to the adapter, 33410LH-125-4.
Installation of Probe Adapters:
SUBTASK 170-001
CAUTION:
_______
(1)
MAKE SURE THAT YOU FLUSH THE PITOT SYSTEM TEST ADAPTER WITH
WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE. DAMAGE TO
THE PROBE OR THE ADAPTER CAN OCCUR.
Flush the adapter, P75701-4, with water.
NOTE:
____
Use equal parts of water and ethylene glycol when the
temperature is between 32° and -40°F (-40° to 0°C).
(2)
SUBTASK 170-002
Blow dry, filtered air through the adapter, P75701-4.
(3)
SUBTASK 170-003
Wipe the probe with a damp cloth.
SUBTASK 480-004
CAUTION:
_______
(4)
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MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM
THE TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
Install the adapter, P75701-4, on the pitot probes at these
locations:
(a) The left pitot probe at STA 192, WL 225, LBL 34
(b) The right upper pitot probe at STA 192, WL 213, RBL 34.
EFFECTIVITY
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I.
SUBTASK 480-005
(5) Connect the test set to each adapter, P75701-4.
Test Procedure
(1)
(2)
(3)
(4)
(5)
(6)
SUBTASK 710-001
Push and hold the NO. 1 MACH AIRSPEED WARNING TEST switch on the P5
panel.
(a) Make sure you hear the warning clacker.
SUBTASK 860-005
Release the NO. 1 MACH AIRSPEED WARNING TEST switch.
(a) Make sure you cannot hear the warning clacker.
SUBTASK 710-002
Push and hold the NO. 2 MACH AIRSPEED WARNING TEST switch on the P5
panel.
(a) Make sure you hear the warning clacker.
SUBTASK 860-006
Release the NO. 2 MACH AIRSPEED WARNING TEST switch.
(a) Make sure you cannot hear the warning clacker.
SUBTASK 860-007
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6B7
MACH WARN SYS -2
SUBTASK 720-002
Apply pressure to the captain's pitot and static systems (Mach
Airspeed Warning System No. 1) as shown in the table below.
NOTE:
____
Static Source Error Correction (SSEC) is applied by the ADIRU
to the static pressure input. Therefore, for each of the
following test points, the altitude and airspeed displayed on
the test set will differ from the altitude and airspeed
displayed on the primary flight display (PFD).
~¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼
¦TEST POINT¦
TEST SET
¦ TEST SET
¦ ALTITUDE ¦ AIRSPEED ¦
¦
¦STATIC PRESSRE¦PITOT PRESSURE¦ CPT OR F/O ¦ CPT OR F/O ¦
¦
¦
IN Hg
¦
IN Hg
¦
FEET
¦
KNOTS
¦
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¦
1
¦
24.392
¦
30.805
¦
5,000
¦ 340 - 342 ¦
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¦
2
¦
10.668
¦
17.010
¦
25,000
¦ 340 - 342 ¦
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¦
3
¦
6.757
¦
10.950
¦
35,000
¦ 280 - 282 ¦
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(a)
(b)
For each test point, slowly decrease the pitot and static
pressures on the test set. Stop when the altitude on the
Primary Flight Display (PFD) is at the test point altitude in
the applicable table.
Slowly increase the pitot pressure until you hear the warning
clackers.
1) Make sure the airspeed on the PFD is within the Overspeed
Warning Airspeed range for the test point.
Decrease the pitot pressure until you cannot hear the warning
clackers.
1) Make sure the airspeed on the PFD is below the Overspeed
Warning Airspeed range for the test point.
Do the steps again for Test Points 2 and 3 in the table above.
(c)
(d)
(7)
(8)
(9)
SUBTASK 860-017
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-2:
1) 18E3
MACH WARN SYS-1
SUBTASK 860-018
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6B7
MACH WARN SYS -2
SUBTASK 720-005
Apply pressure to the first officer's pitot and static systems (Mach
Airspeed Warning System No. 1) as shown in the table above.
NOTE:
____
(a)
(b)
(c)
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(d)
Static Source Error Correction (SSEC) is applied by the ADIRU
to the static pressure input. Therefore, for each of the
following test points, the altitude and airspeed displayed on
the test set will differ from the altitude and airspeed
displayed on the primary flight display (PFD).
For each test point, slowly decrease the pitot and static
pressures on the test set. Stop when the altitude on the
Primary Flight Display (PFD) is at the test point altitude in
the applicable table.
Slowly increase the pitot pressure until you hear the warning
clackers.
1) Make sure the airspeed on the PFD is within the Overspeed
Warning Airspeed range for the test point.
Decrease the pitot pressure until you cannot hear the warning
clackers.
1) Make sure the airspeed on the PFD is below the Overspeed
Warning Airspeed range for the test point.
Do the steps again for Test Points 2 and 3 in the table above.
SUBTASK 860-008
(10) Put the systems back to ambient pressure.
EFFECTIVITY
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SUBTASK 860-010
(11) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18E3
MACH WARN SYS-1
Removal of Drain Coupling, 1QF2-3-64:
SUBTASK 080-001
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CAUTION:
_______
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
(1)
Disconnect the test set from each coupling, 1QF2-3-64C.
(2)
SUBTASK 080-006
Disconnect each coupling, 1QF2-3-64C, from the left and right static
system drains.
(3)
SUBTASK 480-012
Install the cap on the left and right static system drains.
SUBTASK 080-003
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WARNING:
_______
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(4)
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The two primary static ports on the right side of the fuselage.
(b)
(5)
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
The two primary static ports on the left side of the fuselage.
SUBTASK 480-013
Close the primary static system
sidewall lining, in the forward
(a) Do this task: Install the
Compartment
drain access panel, on the left
cargo compartment.
Sidewall Lining for the Cargo
(AMM TASK 25-52-06-400-801 p401).
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K.
Removal of Static Port Adapter, 33410LH-125-4, (Alternate):
SUBTASK 480-014
CAUTION:
_______
(1)
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set, from the adapter, 33410LH-125-4.
SUBTASK 480-015
CAUTION:
_______
(2)
REMOVE THE ADAPTER, 33410LH-125-4, SLOWLY AND CAREFULLY. THE
ADAPTER CAN CAUSE SCRATCHES ON THE STATIC PORT, WHICH CAN CAUSE
FALSE ALTITUDE READINGS.
Remove the adapter, 33410LH-125-4, from the static ports at these
locations:
(a) The captain's static port on the right side of the fuselage.
(b) The first officer's static port on the right side of the
fuselage.
SUBTASK 480-016
WARNING:
_______
MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM THE
STATIC PORTS. IF YOU DO NOT, THE SYSTEM WILL NOT OPERATE
CORRECTLY.
(3)
L.
Remove the tape, Scotch Brand No.471, from the static ports at these
locations:
(a) The captain's static port on the left side of the fuselage.
(b) The first officer's static port on the left side of the
fuselage.
Removal of the Probe Adapters:
SUBTASK 080-007
CAUTION:
_______
(1)
M.
MAKE SURE THE PITOT-STATIC SYSTEM IS AT AMBIENT PRESSURE BEFORE
YOU DISCONNECT THE TEST SET. IF THE PITOT-STATIC SYSTEM IS NOT
AT AMBIENT PRESSURE, DAMAGE TO THE AIR DATA MODULES CAN OCCUR.
Disconnect the test set from each adapter, P75701-4.
SUBTASK 080-005
(2) Remove the adapter, P75701-4, from the pitot probes.
Put the Airplane Back to Its Usual Condition:
(1)
SUBTASK 860-014
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-2:
1) 6A6
FLIGHT CONTROL FLAP LOAD RELIEF
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(b)
(2)
Circuit Breaker Panel, P18-3:
1) 18C1
HEATERS CAPT PITOT
2) 18C2
HEATERS TEMP PROBE
3) 18C3
HEATERS ALPHA VANE LEFT
4) 18D3
HEATERS ALPHA VANE RIGHT
5) 18D5
HEATERS F/O PITOT
6) 18D6
HEATERS AUX PITOT
SUBTASK 860-015
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
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AIR DATA INERTIAL REFERENCE SYSTEM - MAINTENANCE PRACTICES
__________________________________________________________
1.
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General
_______
A. This procedure has these tasks:
(1) Air Data Inertial Reference System (ADIRS) alignment from the FMC
CDU
(2) An alignment of the ADIRS from the ISDU
(3) An IR radial position error check procedure
(4) A IR residual groundspeed error check procedure.
TASK 34-21-00-820-801
2.
_______________________________________________________________
Air
Data Inertial Reference System - Alignment from the FMC CDU
A. General
(1) This task provides instructions to align the air data inertial
reference system (ADIRS) at regular latitude and high latitude.
(a) Regular latitude alignment is from latitude 70.2 degrees South
to latitude 70.2 degrees North. A regular latitude alignment
takes 10 minutes.
(b) High latitude alignment is from latitude 70.2 degrees to
latitude 78.2 degrees North or South. The high latitude
alignment takes 17 minutes.
(c) Above the latitude of 78.2 degrees North and below the latitude
of 78.2 degrees South, you cannot accurately align the ADIRS.
(2) You cannot move the airplane while you align the ADIRS.
(3) The local latitude and longitude are necessary to align the ADIRS.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Procedure
(1)
(2)
SUBTASK 860-054
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-055
Make sure that these circuit breakers are closed:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
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(c)
(3)
(4)
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-056
Make sure the Flight Management Computer System is on
(AMM TASK 34-61-00-710-801 p501).
SUBTASK 820-001
Do these steps to align the ADIRS at regular latitude:
(a) Set the mode select switches on the inertial reference system
(IRS) mode select unit (MSU) to the NAV position.
NOTE:
____
(b)
(c)
(d)
A regular latitude alignment takes 10 minutes.
note of the present time for later use in this
procedure.
Make sure the ON DC lights on the IRS MSU come on for a short
time.
Make sure the ALIGN lights on the IRS MSU come on.
Do these steps to enter the latitude and longitude from a
control display unit (CDU):
NOTE:
____
1)
2)
3)
4)
CDU data lines that permit a selection are identified
with a caret (< or >). The CDU has 12 line-select-keys
(LSK). Six keys are on each side of the display. LSK
1L thru 6L are on the left side, and LSK 1R thru 6R are
on the right side.
Push the INIT REF key on the CDU.
Push the LSK 6L adjacent to the <INDEX prompt on the CDU.
a) Make sure the CDU shows the INIT/REF INDEX 1/1 page.
Push the LSK 2L adjacent to the <POS prompt on the CDU.
a) Make sure the CDU shows the POS INIT 1/3 page.
Put the latitude and longitude data in the scratch pad line
of the CDU.
NOTE:
____
Do not put a space between the latitude and
longitude. The format of the latitude and longitude
data is as follows:
Latitude and longitude:
Where:
5)
X
Y
D
M
is
is
is
is
N or S for
E or W for
the number
the number
XDDMM.MYDDDMM.M
latitude
longitude
of degrees
of minutes
Push the LSK 4R adjacent to the SET IRS POS> prompt on the
CDU.
a) Make sure the CDU shows the latitude and longitude
below the SET IRS POS line.
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6)
After 10 minutes, make sure the ALIGN lights on the IRS MSU
go off.
NOTE:
____
(5)
The ADIRS is now aligned and in the navigation mode.
SUBTASK 820-002
Do these steps to align the ADIRS at high latitude:
(a) Set the mode select switches on the inertial reference system
(IRS) mode select unit (MSU) to the ALIGN position.
NOTE:
____
(b)
(c)
(d)
A high latitude alignment takes 17 minutes. Make a note
of the present time for later use in this procedure.
Make sure the ON DC lights on the IRS MSU come on for a short
time.
Make sure the ALIGN lights on the IRS MSU come on.
Do these steps to enter the latitude and longitude from a
control display unit (CDU):
NOTE:
____
1)
2)
3)
4)
CDU data lines that permit a selection are identified
with a caret (< or >). The CDU has 12 line-select-keys
(LSK). Six keys are on each side of the display. LSK
1L thru 6L are on the left side, and LSK 1R thru 6R are
on the right side.
Push the INIT REF key on the CDU.
Push the LSK 6L adjacent to the <INDEX prompt on the CDU.
a) Make sure the CDU shows the INIT/REF INDEX 1/1 page.
Push the LSK 2L adjacent to the <POS prompt on the CDU.
a) Make sure the CDU shows the POS INIT 1/3 page.
Put the latitude and longitude data in the scratch pad line
of the CDU.
NOTE:
____
Do not put a space between the latitude and
longitude. The format of the latitude and longitude
data is as follows:
Latitude and longitude:
Where:
5)
X
Y
D
M
is
is
is
is
N or S for
E or W for
the number
the number
XDDMM.MYDDDMM.M
latitude
longitude
of degrees
of minutes
Push the LSK 4R adjacent to the SET IRS POS> prompt on the
CDU.
a) Make sure the CDU shows the latitude and longitude
below the SET IRS POS line.
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6)
After 17 minutes, set the mode select switches on the IRS
MSU to the NAV position.
a) Make sure the ALIGN lights on the IRS MSU go off.
NOTE:
____
The ADIRS is now aligned and in the navigation
mode.
TASK 34-21-00-820-802
3.
____________________________________________________________
Air
Data Inertial Reference System - Alignment from the ISDU
A. General
(1) This task provides instructions to align the air data inertial
reference system (ADIRS) from the inertial system display unit
(ISDU) at regular latitude and high latitude.
(a) Regular latitude alignment is from latitude 70.2 degrees South
to latitude 70.2 degrees North. A regular latitude alignment
takes 10 minutes.
(b) High latitude alignment is from latitude 70.2 degrees to
latitude 78.2 degrees North or South. The high latitude
alignment takes 17 minutes.
(c) Above the latitude of 78.2 degrees North and below the latitude
of 78.2 degrees South, you cannot accurately align the ADIRS.
(2) You cannot move the airplane while you align the ADIRS.
(3) The local latitude and longitude are necessary to align the ADIRS.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Procedure
(1)
(2)
SUBTASK 860-057
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-058
Make sure that these circuit breakers are closed:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(c) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
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(3)
(4)
SUBTASK 860-059
Make sure the Flight Management Computer System is on
(AMM TASK 34-61-00-710-801 p501).
SUBTASK 820-003
Do these steps to align the ADIRS at regular latitude:
(a) Set the mode select switches on the inertial reference system
(IRS) mode select unit (MSU) to the NAV position.
NOTE:
____
(b)
(c)
(d)
A regular latitude alignment takes 10 minutes.
note of the present time for later use in this
procedure.
Make a
Make sure the ON DC lights on the IRS MSU come on for a short
time.
Make sure the ALIGN lights on the IRS MSU come on.
Do these steps to enter the latitude and longitude from the
ISDU:
1) Set the DSPL SEL switch on the ISDU to the PPOS position.
2) Push the applicable N or S key on the ISDU.
3) Put in the degrees and minutes of the local latitude on the
ISDU.
a) Make sure the latitude shows on the left side of the
ISDU.
b) Make sure the ENT key light on the ISDU comes on.
4) Push the ENT key on the ISDU to transmit the latitude to
the ADIRUs.
5) Push the applicable W or E key on the ISDU.
6) Put in the degrees and minutes of the local longitude on
the ISDU.
a) Make sure the longitude shows on the right side of the
ISDU.
b) Make sure the ENT key light on the ISDU comes on.
7) Push the ENT key on the ISDU to transmit the longitude to
the ADIRUs.
8) After 10 minutes, make sure the ALIGN lights on the IRS MSU
go off.
NOTE:
____
The ADIRS is now aligned and in the navigation mode.
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(5)
SUBTASK 820-004
Do these steps to align the ADIRS at high latitude:
(a) Set the mode select switches on the inertial reference system
(IRS) mode select unit (MSU) to the ALIGN position.
NOTE:
____
(b)
(c)
(d)
A high latitude alignment takes 17 minutes. Make a note
of the present time for later use in this procedure.
Make sure the ON DC lights on the IRS MSU come on for a short
time.
Make sure the ALIGN lights on the IRS MSU come on.
Do these steps to enter the latitude and longitude from the
ISDU:
1) Set the DSPL SEL switch on the ISDU to the PPOS position.
2) Push the applicable N or S key on the ISDU.
3) Put in the degrees and minutes of the local latitude on the
ISDU.
a) Make sure the latitude shows on the left side of the
ISDU.
b) Make sure the ENT key light on the ISDU comes on.
4) Push the ENT key on the ISDU to transmit the latitude to
the ADIRUs.
5) Push the applicable W or E key on the ISDU.
6) Put in the degrees and minutes of the local longitude on
the ISDU.
a) Make sure the longitude shows on the right side of the
ISDU.
b) Make sure the ENT key light on the ISDU comes on.
7) Push the ENT key on the ISDU to transmit the longitude to
the ADIRUs.
8) After 17 minutes, set the mode select switches on the IRS
MSU to the NAV position.
a) Make sure the ALIGN lights on the IRS MSU go off.
NOTE:
____
The ADIRS is now aligned and in the navigation
mode.
TASK 34-21-00-200-801
4.
______________________________
IR
Radial Position Error Check (Fig. 201)
A. General
(1) This task provides the instructions to do a check of the inertial
reference (IR) radial position error.
(2) At the end of a flight, the radial position error of the IR can be
calculated by comparing the IR final position to the airport
position. The IR position data is available on the control display
unit (CDU).
(3) The IR radial position error limits are shown in a chart in this
procedure.
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40
35
REPLACE - 1 FLIGHT
REPLACE - 2 CONSECUTIVE
FLIGHTS
RADIAL POS ERROR (NMI)
30
25
20
15
OK
10
5
0
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
TIME IN NAV MODE (HOURS)
IR Radial Position Error
Figure 201
H77356
34-21-00-990-804
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B.
Procedure
(1)
SUBTASK 860-073
Make sure the mode select switches on the mode select unit (MSU) are
in the NAV position.
NOTE:
____
(2)
(3)
You must record the IR position data at the end of the flight
while the IR stays in the NAV mode.
SUBTASK 200-001
Do these steps to enter the airport identification into the CDU.
(a) Push the RTE key on the CDU.
1) Make sure the RTE 1/1 shows on the CDU.
(b) Put the airport identification into the CDU scratchpad.
(c) Push the line select key (LSK) adjacent to the DEST on the CDU.
1) Make sure the airport identification shows below the DEST
on the CDU.
SUBTASK 200-002
Do these steps to enter the airplane present position into the CDU:
NOTE:
____
(a)
When the airplane is parked at an airport gate, the present
position of the airplane is the gate latitude and longitude.
Put the gate latitude and longitude into the CDU scratchpad.
NOTE:
____
Do not use a space between the latitude and longitude.
The format of the latitude and longitude data is as
follows:
Latitude and longitude:
Where:
(b)
(c)
(d)
X
Y
D
M
is
is
is
is
N or S for
E or W for
the number
the number
XDDMM.MYDDDMM.M
latitude
longitude
of degrees
of minutes
Push the LEGS key on the CDU.
1) Make sure the LEGS 1/3 page shows on the CDU.
Push the LSK 1L on the CDU.
1) Make sure an identification waypoint of the gate latitude
and longitude shows adjacent to the LSK 1L on the CDU.
Record the number in nautical miles that shows next to the
first identification waypoint.
NOTE:
____
The first identification way point is the active
waypoint that shows at the top of the LEGS 1/3 page.
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(4)
(5)
SUBTASK 200-004
The difference between the gate and the IRS waypoints in nautical
miles is the IR radial position error.
(6)
SUBTASK 200-005
Compare the IR radial position error and the time the IRS was in the
NAV mode to the radial position error limits (Fig. 201).
(7)
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SUBTASK 200-003
Do these steps to transfer the left IRS position from the POS REF
page to the LEGS page on the CDU:
(a) Push the INIT/REF key on the CDU.
1) Make sure the INIT/REF INDEX page shows on the CDU.
(b) Push the LSK adjacent to the <POS prompt on the CDU.
1) Make sure the POS INIT 1/3 page shows on the CDU.
(c) Push the NEXT PAGE key on the CDU.
1) Make sure the POS REF 2/3 page shows on the CDU.
(d) Push the LSK adjacent to the IRS L on the CDU.
1) Make sure the left IRS latitude and logitude data show on
the CDU scratchpad.
(e) Push the LEGS key on the CDU.
1) Make sure the LEGS 1/3 page shows on the CDU.
(f) Push the LSK 2L on the CDU.
1) Make sure an identification waypoint of the IRS latitude
and longitude shows adjacent to the LSK 2L on the CDU.
(g) Record the number in nautical miles that shows next to the
second identification waypoint.
(h) Repeat these steps to record the number in nautical miles for
the right IRS.
SUBTASK 020-001
If one of these conditions occurs, replace the applicable ADIRU:
(a) The IR radial position error is in the REPLACE-1 FLIGHT area.
(b) The IR radial position error is in the REPLACE-2 CONSECUTIVE
FLIGHTS area for the second consecutive flight.
TASK 34-21-00-200-802
5.
___________________________________________________
Inertial
Reference Residual Groundspeed Error Check
A. General
(1) This task provides the instructions to do a check of the inertial
reference (IR) residual groundspeed error.
(2) Groundspeed readout must be taken before the airplane has been
stationary for three minutes. The system may zero the display after
three minutes.
B. References
(1) AMM TASK 34-21-01-000-801 p401, Air Data Inertial Reference Unit
Removal
(2) AMM TASK 34-21-01-400-801 p401, Air Data Inertial Reference Unit
Installation
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C.
Procedure
(1)
SUBTASK 860-075
Set the SYS switch to the L position on the ISDU.
(2)
SUBTASK 200-006
Set the DSPL switch to the TRK/GS position on the ISDU.
(3)
(4)
(5)
SUBTASK 200-007
When the airplane is stationary, the ISDU display shows the residual
groundspeed error.
SUBTASK 200-008
Make sure these conditions do
(a) The residual groundspeed
of two checks, one after
(b) The residual groundspeed
of one check.
not occur:
error is 15 knots or larger after each
the other.
error is 21 knots or larger at the end
SUBTASK 200-009
If one of these conditions occurs, These are the tasks:
Air Data Inertial Reference Unit Removal
(AMM TASK 34-21-01-000-801 p401),
Air Data Inertial Reference Unit Installation
(AMM TASK 34-21-01-400-801 p401)..
(6)
SUBTASK 200-010
Set the SYS switch to the R position.
(7)
SUBTASK 200-011
Do the procedure again for the right ADIRU.
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AIR DATA INERTIAL REFERENCE SYSTEM - ADJUSTMENT/TEST
____________________________________________________
1.
General
_______
A. This
(1)
(2)
(3)
procedure has these tasks:
The Air Data Inertial Reference System (ADIRS) operational test
The Inertial Reference (IR) system test
The Air Data Reference (ADR) system test.
TASK 34-21-00-710-801
2.
_____________________________________________________
Air
Data Inertial Reference System - Operational Test
A. General
(1) This task contains these tests:
(a) The Self-Test of the inertial reference (IR) system
(b) The self-test of the air data reference (ADR) system
(c) The Built-In Test Equipment (BITE) ground test of the IR
(d) The BITE ground test of the ADR.
B. References
(1) AMM TASK 21-27-00-700-802 p501, Equipment Cooling Fans - Operational
Test
(2) AMM TASK 23-43-00-710-801 p501, Flight and Ground Crew Call System Operational Test
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(5) AMM TASK 31-62-00-710-801 p501, Common Display System - Operational
Test
(6) AMM TASK 32-09-10-710-801 p501, Proximity Switch Electronics Unit
(PSEU) - Operational Test
(7) AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
(8) FIM 34-21 TASK 801, ADIRS BITE Procedure
C. Access
(1) Location Zones
(a) 117 Main Equipment Center, Left
(b) 118 Main Equipment Center, Right
(c) 211 Flight Compartment, Left
(d) 212 Flight Compartment, Right
D. Prepare for the Operational Test
(1)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-060
Make sure the equipment cooling system is operational
(AMM TASK 21-27-00-700-802 p501).
(3)
SUBTASK 860-061
Make sure the common display system (CDS) is operational
(AMM TASK 31-62-00-710-801 p501).
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(4)
SUBTASK 860-062
Make sure the flight management computer system (FMCS) is
operational (AMM TASK 34-61-00-710-801 p501).
(5)
SUBTASK 860-063
Make sure the proximity switch electronic unit is operational
(AMM TASK 32-09-10-710-801 p501).
(6)
SUBTASK 860-064
Make sure the flight crew cabin system is operational
(AMM TASK 23-43-00-710-801 p501).
(7)
SUBTASK 860-065
Make sure that these circuit breakers are closed:
(a) Circuit Breaker Panel, P6-1:
1) 6B7
MACH WARN SYS -2
2) 6C14
ADIRU RIGHT AC
3) 6C15
ADIRU RIGHT EXC
4) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-2:
1) 18E3
MACH WARN SYS-1
(c) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(d) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-066
WARNING:
_______
(8)
(9)
FAILURE TO OPEN THE FLAP LOAD RELIEF CIRCUIT BREAKER MAY CAUSE
INJURY TO PERSONNEL.
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-2:
1) 6A6
FLIGHT CONTROL FLAP LOAD RELIEF
SUBTASK 860-004
Make sure the mode select switches on the Mode Select Unit (MSU) are
in the OFF position.
NOTE:
____
Some switches must be pulled before you turn them. If you
try to turn these switches before you pull them, you can
damage them.
SUBTASK 860-005
(10) Set the IRS Transfer switch on the P5 overhead panel to the NORMAL
position.
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SUBTASK 860-006
(11) Set the VHF NAV switch on the P5 overhead panel to the NORMAL
position.
SUBTASK 860-007
(12) Set the CDS switch on the P5 overhead panel to the NORMAL position.
SUBTASK 860-008
(13) Set the EQUIPMENT COOLING switch on the P5 overhead panel to the
NORMAL position.
SUBTASK 860-009
(14) Set the FMCS switch on the P5 overhead panel to the NORMAL position.
E.
SUBTASK 860-010
(15) Set the STBY PWR switch on the P5 overhead panel to the AUTO
position.
Air Data Inertial Reference System - Self-Test
(1)
SUBTASK 740-001
Do these steps to do a self-test of the left IR system:
(a) Set the mode select switches on the MSU to the ALIGN position.
NOTE:
____
(b)
(c)
1) Make sure the ALIGN lights on the MSU are on.
Set the SYS DSPL switch on the Inertial System Display Unit
(ISDU) to the L position.
Set and hold the DSPL SEL switch on the ISDU in the TEST
position.
NOTE:
____
(d)
(e)
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
The DSPL SEL switch is spring-loaded in the TEST
position. It will return to the TK/GS position when
released. Release the switch to stop the test. You
will possibly have to do this step again to see all
results of the test.
For seconds 0-2, make sure that:
1) The display segments and indicators on the ISDU come on.
2) The ALIGN, FAULT, ON DC, and DC FAIL annunciators on the
left side of the MSU come on.
3) The MASTER CAUTION and IRS lights on the captain's
glareshield come on.
For seconds 2-10, make sure that:
1) The display segments and indicators on the ISDU are blank.
2) The ALIGN, FAULT, ON DC, and DC FAIL annunciators on the
left side of the MSU go off.
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3)
(f)
(g)
(h)
(i)
(j)
(2)
The HDG flag comes into view and the compass card goes out
of view on the captain's secondary display.
4) The HDG flag on the Radio Magnetic Indicator (RMI) comes
into view.
5) The ATT flag on the captain's primary display comes into
view.
6) The VSI flag on the captain's secondary display comes into
view.
For seconds 10 and on, make sure that:
1) The 5 ° pitch up shows on the captain's primary display.
2) The 45° roll right shows on the captain's primary display.
3) The 15° heading shows on the captain's secondary display.
4) The 15° heading shows on the RMI.
5) The ground speed of 200 knots shows on the captain's
secondary display.
6) The -10° drift angle shows on the captain's primary
display.
7) The vertical speed of -600 feet/minute shows on the
captain's secondary display.
Push the MASTER CAUTION reset switch.
1) Make sure the MASTER CAUTION and IRS lights on the
captain's glareshield go off.
Set the IRS switch on the P5 overhead panel to BOTH ON R.
1) Make sure the numbers on the captain's compass card go out
of view.
Release the DSPL SEL switch.
Set the IRS Transfer switch on the P5 overhead panel to the
NORMAL position.
SUBTASK 710-001
Do these steps to do the self-test of the right IR system:
(a) Set the mode select switches on the MSU to the ALIGN position.
NOTE:
____
(b)
(c)
1) Make sure the ALIGN lights on the MSU are on.
Set the SYS DSPL switch on the ISDU to the R position.
Set and hold the DSPL SEL switch on the ISDU in the TEST
position.
NOTE:
____
(d)
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
The DSPL SEL switch is spring-loaded in the TEST
position. It will return to the TK/GS position when
released. Release the switch to stop the test. You
will possibly have to do this step again to see all
results of the test.
For seconds 0-2, make sure that:
1) The display segments and indicators on the ISDU come on.
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2)
(e)
(f)
(g)
(h)
(i)
(j)
(3)
The ALIGN, FAULT, ON DC, and DC FAIL annunciators on the
right side of the MSU come on.
3) The MASTER CAUTION and IRS lights on the first officer's
glareshield come on.
For seconds 2-10, make sure that:
1) The display segments and indicators on the ISDU go off.
2) The ALIGN, FAULT, ON DC, and DC FAIL annunciators on the
right side of the MSU go off.
3) The HDG flag comes into view and the compass card goes out
of view on the first officer's secondary display.
4) The HDG flag on the Radio Magnetic Indicator (RMI) comes
into view.
5) The ATT flag on the first officer's primary display comes
into view.
6) The VSI flag on the first officer's primary display comes
into view.
For seconds 10 and on, make sure that:
1) The 5° pitch up shows on the first officer's primary
display.
2) The 45° roll right shows on the first officer's primary
display.
3) The 15° heading shows on the first officer's secondary
display.
4) The 15° heading shows on the RMI.
5) The ground speed of 200 knots shows on the first officer's
secondary display.
6) The 10° drift angle shows on the first officer's primary
display.
7) The vertical speed of -600 feet/minute shows on the first
officer's primary display.
Push the MASTER CAUTION reset switch.
1) Make sure the MASTER CAUTION and IRS lights on the
captain's glareshield go off.
Set the IRS switch on the P5 overhead panel to BOTH ON R.
1) Make sure the numbers on the captain's compass card go out
of view.
Release the DSPL SEL switch.
Set the IRS Transfer switch on the P5 overhead panel to the
NORMAL position.
SUBTASK 710-002
Do these steps to do the self-test of the left ADR system:
(a) Push the MACH AIRSPEED WARNING TEST NO. 1 switch on the the P5
aft overhead panel for a moment.
1) Make sure the overspeed warning clacker comes on
momentarily.
(b) Push the MACH AIRSPEED WARNING TEST NO. 2 switch on the P5 aft
overhead panel for a moment.
1) Make sure the overspeed warning clacker comes on
momentarily.
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(c)
(d)
(e)
(f)
(g)
(h)
(i)
(4)
ú
Set the left mode select switch on the MSU to the ALIGN
position.
Set the left altimeter baro correction data to 29.92 inches of
Hg.
Set the SYS DSPL switch on the ISDU to the L position.
Set and hold the DSPL SEL switch on the ISDU in the TEST
position.
For the 0-2 seconds, make sure the overspeed warning clacker
comes on for 2 seconds.
After 7 seconds, make sure that:
1) The altitude of 10,000 |40 feet shows on the captain's
secondary display.
2) The mach indication on the captain's secondary display is
blank.
3) The true airspeed of 170 |4 knots shows on the captain's
secondary display.
4) Total air temperature of 35.0 | 2°C. shows on the engine
display.
Release the DSPL SEL switch.
SUBTASK 710-003
Do these steps to do the the self-test of the right ADR system :
(a) Push the MACH AIRSPEED WARNING TEST NO. 1 switch on the the P5
aft overhead panel for a moment.
1) Make sure the overspeed warning clacker comes on
momentarily.
(b) Push the MACH AIRSPEED WARNING TEST NO. 2 switch on the P5 aft
overhead panel for a moment.
1) Make sure the overspeed warning clacker comes on
momentarily.
(c) Set the right mode select switch on the MSU to the ALIGN
position.
(d) Set the right altimeter baro correction data to 29.92 inches of
Hg.
(e) Set the SYS DSPL switch on the ISDU to the R position.
(f) Set and hold the DSPL SEL switch on the ISDU in the TEST
position.
(g) For the 0-2 seconds, make sure the overspeed warning clacker
comes on for 2 seconds.
(h) After 7 seconds, make sure that:
1) The altitude of 10,000 |40 feet shows on the first
officer's primary display.
2) The mach indication on the first officer's primary display
is blank
3) The true airspeed of 170 |4 knots shows on the first
officer's secondary display.
4) The total air temperature does not show on the engine
display.
(i) Release the DSPL SEL switch.
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F.
Air Data Inertial Reference System - BITE Test
(1)
SUBTASK 860-012
Do these steps to access the ADIRS maintenance index on the CDU:
NOTE:
____
(a)
(b)
(c)
(2)
CDU data lines that permit a selection are identified with a
caret (< or >). The CDU has 12 line-select-keys. Six keys
are on each side of the display. 1L thru 6L are on the left
side, and 1R thru 6R are on the right side.
Push the
1) Make
Push the
1) Make
Push the
1) Make
INIT REF key.
sure the CDU shows
LSK 6R adjacent to
sure the CDU shows
LSK 4L adjacent to
sure the CDU shows
INIT REF INDEX 1/1 page.
MAINT> prompt on the CDU.
MAINT BITE INDEX 1/1 page.
<ADIRS prompt on the CDU.
ADIRS BITE 1/1 page.
SUBTASK 710-004
Do these steps to access the left ADIRS current faults:
(a) Push the LSK 1L adjacent to the <ADIRS L prompt on the CDU.
1) Make sure the CDU shows the ADIRS L BITE MAIN MENU page.
(b) Push the LSK 1L adjacent to the <CURRENT STATUS prompt on the
CDU.
1) Make sure the CDU shows the ADIRS L BITE CURRENT FAULTS
page.
2) Make sure the CDU shows the NO CURRENT STATUS message.
NOTE:
____
(3)
the
the
the
the
the
If there is a maintenance message that shows on the
CDU, you can go to the ADIRS fault isolation
procedures to fix the fault (FIM 34-21 TASK 801).
SUBTASK 710-005
Do these steps to access the right ADIRS current faults.
(a) Push the LSK 2L adjacent to the <ADIRS L prompt on the CDU from
the ADIRS BITE 1/1 page.
1) Make sure the CDU shows the ADIRS R BITE MAIN MENU page.
(b) Push the LSK 1L adjacent to the <CURRENT STATUS prompt on the
CDU.
1) Make sure the CDU shows the ADIRS R BITE CURRENT FAULTS
page.
2) Make sure the CDU shows the NO CURRENT FAULTS message.
NOTE:
____
If there is a maintenance message that shows on the
CDU, you can go to the ADIRS fault isolation
procedure to fix the fault (FIM 34-21 TASK 801).
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(4)
SUBTASK 740-002
Do these steps to do a BITE ground test of the left and right IR
system:
NOTE:
____
(a)
(b)
You can do a separate ground test of the left ADIRS and the
right ADIRS. The ADIRS L BITE MAIN MENU contains the ground
test for the left ADIRS. The ADIRS R BITE MAIN MENU contains
the ground test for the right ADIRS.
Push the LSK 3L adjacent to the <ADIRS-IR L+R GND TEST prompt
on the CDU from the ADIRS BITE 1/1 page.
1) Make sure the CDU shows the ADIRS-IR L+R BITE GROUND TEST
1/3 page.
Push the LSK 5L adjacent to the <TEST START prompt on the CDU
to start the IR ground test.
NOTE:
____
1)
2)
3)
4)
ú
After you start the test, you can push the LSK 5R
adjacent to the TEST STOP> prompt on the CDU to stop the
test.
For seconds 0-2, make sure that:
a) All the display segments and indicators on the ISDU
come on.
b) The ALIGN, FAULT, ON DC, and DC FAIL annunciators on
the MSU come on.
c) The MASTER CAUTION and IRS lights on the glareshield
come on.
For seconds 2-10, make sure that:
a) All the display segments and indicators on the ISDU are
blank.
b) The ALIGN, FAULT, ON DC, and DC FAIL annunciators on
the MSU go off.
c) The HDG flag comes into view and the compass card goes
out of view on the secondary displays.
d) The HDG flag on the Radio Magnetic Indicator (RMI)
comes into view.
e) The ATT flags on the primary displays come into view.
f) The VSI flag on the captain's secondary display comes
into view.
g) The VSI flag on the first officer's primary display
comes into view.
Push the NEXT PAGE key on the CDU to go to page 2/3 of this
test.
For seconds 10 and on, make sure that:
a) The 5° pitch up angles show on the primary displays.
b) The 45° roll right angles on the primary displays.
c) The groundspeed of 200 knots shows on the ISDU display.
d) The latitude of N22°30.0' shows on the ISDU display.
e) The longitude of E22°30.0' shows on the ISDU display.
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5)
6)
(5)
Push the LSK 5R adjacent to the <TEST STOP prompt on the
CDU to stop the test.
Push the INIT REF key on the CDU to go out of the ADIRS
BITE page.
SUBTASK 710-006
Do these steps to do a ground test for the left and right ADR
system:
(a) Push the LSK 4L adjacent to the <ADIRS-ADR L+R GND TEST prompt
on the CDU from the ADIRS BITE 1/1 page.
1) Make sure the CDU shows the ADIRS-ADR L+R BITE GROUND TEST
1/2 page.
(b) Push the LSK 5L adjacent to the <TEST START prompt on the CDU
to start the ADR ground test.
NOTE:
____
After you start the test, you can push the LSK 5R
adjacent to the <TEST STOP prompt on the CDU to stop the
test.
(c)
G.
For 0-2 seconds, make sure that:
1) The overspeed warning and the flags on the primary displays
come into view.
(d) For 0-7 seconds, make sure that:
1) The ALT flag shows on the captain's secondary display.
2) The ALT flag shows on the first officer's primary display.
3) The total air temperature does not show on the engine
display.
(e) For seconds 7 and on, make sure that:
1) The altitude of 10000 feet shows on the captain's secondary
display.
2) The altitude of 10000 feet shows on the first officer's
primary display.
3) The true airspeed of 170 knots show on the secondary
displays.
(f) Push the LSK 5R adjacent to the <TEST STOP prompt on the CDU to
stop the test.
(g) Push the MASTER CAUTION reset switch.
1) Make sure the MASTER CAUTION and IRS lights on the
captain's glareshield go off.
(h) Push the INIT REF key on the CDU to go out of the ADIRS BITE
page.
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-013
Set the mode select switches on the MSU to the OFF position.
SUBTASK 860-050
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-2:
1) 6A6
FLIGHT CONTROL FLAP LOAD RELIEF
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(3)
SUBTASK 860-014
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-21-00-730-801
3.
________________________________
Inertial
Reference - System Test
A. General
(1) The system test contains these tests:
(a) The ON DC Operation and No Cooling Warning Test
(b) The MSU ALIGN and DC FAIL Annunciator and MCU DC FAIL
Annunciator Test
(c) The Master Dim and Test
(d) The Five Minute Time Delay Check
(e) The ISDU/FMC digital and MCU fault discrete interface test.
B. References
(1) AMM TASK 21-27-00-700-802 p501, Equipment Cooling Fans - Operational
Test
(2) AMM TASK 23-43-00-710-801 p501, Flight and Ground Crew Call System Operational Test
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(5) AMM TASK 31-62-00-710-801 p501, Common Display System - Operational
Test
(6) AMM TASK 32-09-10-710-801 p501, Proximity Switch Electronics Unit
(PSEU) - Operational Test
(7) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(8) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
(9) AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
C. Access
(1) Location Zones
(a) 117 Main Equipment Center, Left
(b) 118 Main Equipment Center, Right
(c) 211 Flight Compartment, Left
(d) 212 Flight Compartment, Right
D. Prepare for the IR System Test
(1)
SUBTASK 860-015
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-067
Make sure the equipment cooling system is operational
(AMM TASK 21-27-00-700-802 p501).
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(3)
SUBTASK 860-068
Make sure the common display system (CDS) is operational
(AMM TASK 31-62-00-710-801 p501).
(4)
SUBTASK 860-069
Make sure the flight management computer system (FMCS) is
operational (AMM TASK 34-61-00-710-801 p501).
(5)
SUBTASK 860-070
Make sure the proximity switch electronics unit (PSEU) is
operational (AMM TASK 32-09-10-710-801 p501).
(6)
SUBTASK 860-071
Make sure the flight crew call system is operational
(AMM TASK 23-43-00-710-801 p501).
(7)
SUBTASK 860-016
Make sure that these circuit breakers are closed:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(c) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 860-017
WARNING:
_______
(8)
(9)
FAILURE TO OPEN THE FLAP LOAD RELEIF CIRCUIT BREAKER MAY CAUSE
INJURY TO PERSONNEL.
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-2:
1) 6A6
FLIGHT CONTROL FLAP LOAD RELIEF
SUBTASK 860-018
Make sure the mode select switches on the MSU are in the OFF
position.
NOTE:
____
Some switches must be pulled before you turn them. If you
try to turn these switches before you pull them, you can
damage them.
SUBTASK 860-019
(10) Set the IRS switch on the P5 overhead panel to the NORMAL position.
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SUBTASK 860-020
(11) Set the VHF NAV switch on the P5 overhead panel to the NORMAL
position.
SUBTASK 860-021
(12) Set the CDS switch on the P5 overhead panel to the NORMAL position.
SUBTASK 860-022
(13) Set the EQUIPMENT COOLING switch on the P5 overhead panel to the
NORMAL position.
SUBTASK 860-023
(14) Set the FMCS switch on the P5 overhead panel to the NORMAL position.
E.
SUBTASK 860-024
(15) Set the STBY PWR switch on the P5 overhead panel to the AUTO
position.
ON DC Operation and No Cooling Warning Test
(1)
SUBTASK 860-025
Do these steps to do a check of the ADIRU ON DC Operation.
(a) Set the mode select switches on the MSU to the ATT position.
NOTE:
____
(b)
(c)
(d)
(e)
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
Open this circuit breaker:
1) Circuit Breaker Panel, P18-1:
a) 18E7
ADIRU LEFT AC
2) Make sure the left ON DC light on the MSU comes on.
3) Make sure the MASTER CAUTION and the IRS lights on the
glareshield come on.
4) After at least 25 seconds, make sure the crew call horn
sounds.
Close this circuit breaker:
1) Circuit Breaker Panel, P18-1:
a) 18E7
ADIRU LEFT AC
2) Make sure the crew call horn stops.
3) Make sure the left ON DC light on the MSU goes off.
Push the MASTER CAUTION button on the pilot's glareshield to
turn off the MASTER CAUTION and the IRS lights.
Open this circuit breaker:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
2) Make sure the right ON DC light on the MSU comes on.
3) Make sure the MASTER CAUTION and the IRS lights on the
captain's glareshield come on.
4) After at least 25 seconds, make sure the crew call horn
sounds.
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(f)
(g)
(2)
Close this circuit breaker:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
2) Make sure the crew call horn stops.
3) Make sure the right ON DC light on the MSU goes off.
Push the MASTER CAUTION button on the captain's glareshield to
turn off the MASTER CAUTION and the IRS lights.
SUBTASK 860-034
Do these steps to do a ADIRU No Cooling Warning Test:
(a) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P6-4:
a) 6C14
EQPT COOLING EXHAUST FAN CONT NORMAL
2) Make sure the EQUIPMENT COOLING OFF light on the P5
overhead panel is on.
3) Within 60 seconds after the EQUIPMENT COOLING OFF light
comes on, make sure the crew call horn sounds.
(b) Close this circuit breaker:
1) Circuit Breaker Panel, P6-4:
a) 6C14
EQPT COOLING EXHAUST FAN CONT NORMAL
2) Make sure the EQUIPMENT COOLING OFF light on the P5
overhead panel goes off.
3) Make sure the crew call horn stops.
(c) Open this circuit breaker:
1) Circuit Breaker Panel, P6-4:
a) 6C12
EQPT COOLING SUPPLY FAN CONT-NORMAL
2) Make sure the EQUIPMENT COOLING OFF light on the P5
overhead panel is on.
3) Within 60 seconds after the EQUIPMENT COOLING OFF light
comes on, make sure the crew call horn sounds.
(d) Close this circuit breaker:
1) Circuit Breaker Panel, P6-4:
a) 6C12
EQPT COOLING SUPPLY FAN CONT-NORMAL
2) Make sure the EQUIPMENT COOLING OFF light on the P5
overhead panel goes off.
3) Make sure the crew call horn stops.
(e) Set the mode select switches on the MSU to the OFF position.
NOTE:
____
F.
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
DC FAIL and ALIGN Annunciators Test
(1)
SUBTASK 730-011
Do these steps to do a DC FAIL and ALIGN Annunciators Test:
(a) Set the left mode select switch on the MSU to the ATT position.
1) Make sure the left ALIGN light on the MSU comes on for not
more than 40 seconds.
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(b)
G.
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
2) Make sure the left DC FAIL light on the MSU comes on.
3) Make sure the MASTER CAUTION and IRS light on the pilot's
glareshield come on.
(c) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
2) Make sure the left DC FAIL light goes off.
(d) Push the MASTER CAUTION button on the pilot's glareshield to
turn off the MASTER CAUTION and the IRS light.
(e) Set the left mode select switch on the MSU to the OFF position.
(f) Set the right mode select switch on the MSU to the ATT
position.
1) Make sure the right ALIGN light on the MSU comes on for not
more than 40 seconds.
(g) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P6-1:
a) 6C17
ADIRU RIGHT DC
2) Make sure the right DC FAIL light on the MSU comes on.
3) Make sure the MASTER CAUTION and IRS lights on the
captain's glareshield come on.
(h) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P6-1:
a) 6C17
ADIRU RIGHT DC
2) Make sure the right DC FAIL light goes off.
(i) Push the MASTER CAUTION button on the captain's glareshield to
turn off the MASTER CAUTION and the IRS light.
(j) Set the mode select switch on the MSU to the OFF position.
Master Dim and Test
(1)
SUBTASK 860-039
Do these steps to do a Master Dim and Test for the ADIRS:
(a) Align the left and right ADIRS in the ALIGN mode
(AMM TASK 34-21-00-820-801 p201) or
(AMM TASK 34-21-00-820-802 p201).
(b) Make sure the mode select switches on the MSU are in the ALIGN
position.
NOTE:
____
(c)
(d)
(e)
(f)
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
Set the DSPL SEL switch on the ISDU to the PPOS position.
Turn the inner DSPL SEL switch (BRT) on the ISDU clockwise.
Set and hold the DIM and TEST switch on the pilot's center
instrument panel to the TEST position.
1) Make sure all of the lights on the ISDU come on bright.
2) Make sure all of the lights on the MSU come on bright.
Release the DIM and TEST switch.
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(g)
(h)
(i)
(j)
Turn the inner DSPL SEL switch (BRT) on the ISDU
counterclockwise.
Set the DIM and TEST switch on the pilot's center instrument
panel to the DIM position.
1) Make sure the ALIGN lights on the MSU are dim.
2) Push the lights on the MSU one at a time.
3) Make sure the lights come on dim one at a time.
Set the DIM and TEST switch on the pilot's center instrument
panel to the BRT position.
1) Make sure only the ALIGN lights on the MSU are on.
Set the mode select switches on the MSU to the OFF position.
NOTE:
____
H.
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
Five Minute Time Delay Check
(1)
SUBTASK 860-041
Do these steps to do a Five Munite Time Delay Check:
(a) Set the mode select switches on the MSU to the ALIGN position.
NOTE:
____
(b)
(c)
Some switches must be pulled before you turn them. If
you try to turn these switches before you pull them, you
can damage them.
Open these circuit breakers:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
2) Circuit Breaker Panel, P18-1:
a) 18E7
ADIRU LEFT AC
3) In less than 30 seconds, make sure the crew call horn
sounds.
Open these circuit breakers:
1) Circuit Breaker Panel, P6-3:
a) 6D1
PSEU PRI
b) 6D2
PSEU ALTN
2) Make sure the crew call horn stops.
3) Set the STANDBY POWER switch on the P5 overhead panel to
the BAT position.
4) Make sure the ALIGN lights on the MSU are on.
5) Make sure the DC lights on the MSU are on.
6) After approximately 5 seconds, make sure the MASTER CAUTION
and IRS lights on the pilot's glareshield come on.
7) After 5 minutes, make sure that:
a) The ALIGN and ON DC lights on the right side of the MSU
are off.
b) The ALIGN and ON DC lights on the left side of the MSU
are on.
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(d)
(e)
(f)
(g)
(h)
(i)
I.
ISDU/FMC
(1)
Close these circuit breakers:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
2) Circuit Breaker Panel, P6-3:
a) 6D1
PSEU PRI
b) 6D2
PSEU ALTN
3) Circuit Breaker Panel, P18-1:
a) 18E7
ADIRU LEFT AC
Push the MASTER CAUTION switch on the pilot's glareshield to
turn off the MASTER CAUTION and the IRS lights.
Set the left and right mode select switches on the MSU to the
OFF position.
1) Make sure the ALIGN lights go off.
Open these circuit breakers and attach DO-NOT-CLOSE tags:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
2) Circuit Breaker Panel, P18-1:
a) 18E7
ADIRU LEFT AC
Wait for approximately 2 seconds, then Remove the DO-NOT-CLOSE
tags and close these circuit breakers:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
2) Circuit Breaker Panel, P18-1:
a) 18E7
ADIRU LEFT AC
Set the STANDBY POWER switch on the P5 overhead panel to the
AUTO position.
Digital and MCU Fault Discrete Interface Test
SUBTASK 860-045
Do these steps to do a ISDU/FMC Digital and MCU Discrete Interface
Test:
(a) Set the left and right mode select switches on the MSU to the
NAV position.
(b) Set the SYS DSPL switch on the ISDU to the PPOS position.
1) Make sure the left and right ALIGN lights on the MSU are
on.
(c) Set the SYS DSPL switch on the ISDU to the L position.
(d) Push the INIT REF key on the CDU 1.
1) Make sure the PERF INIT page shows on the CDU 1.
(e) Push the LSK 6L adjacent to the <INDEX prompt on the CDU.
1) Make sure the INIT/REF INDEX page shows on the CDU 1.
(f) Push the LSK 2L adjacent to the <POS prompt on the CDU.
1) Make sure the POS INIT 1/3 page shows on the CDU 1.
(g) Enter the latitude of N0000.0 and the longitute of E00000.0 on
the CDU 1.
1) Make sure the latitude and longitude show on the scratch
pad of the CDU 1.
(h) Push the LSK 4R adjacent to the POS> prompt on the CDU.
1) Make sure the latitude and longitute show on the line 9 of
the CDU 1.
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2)
Wait until the left and right ALIGN lights on the MSU start
flashing.
NOTE:
____
This may take up to 10 minutes.
3)
4)
(i)
(j)
(k)
(l)
(m)
(n)
(o)
Make sure the ENTER IRS POSITION shows on the CDU 1.
Make sure the latitute of N00°00.0' and the longitute of
E000°00.0' show on the ISDU.
Set the SYS DSPL on the ISDU to the R position.
1) Make sure the latitute of N00°00.0' and the longitute of
E000°00.0' show on the ISDU.
Set the SYS DSPL on the ISDU to the L position.
Re-enter the latitude of N0000.0 and the longitute of E00000.0
on the CDU 1.
1) Make sure the latitude and longitude show on the scratch
pad of the CDU 1.
Push the LSK 4R adjacent to the POS> prompt on the CDU.
1) Make sure the latitude and longitute show on the line 9 of
the CDU 1.
2) Make sure the left and right ALIGN lights on the MSU come
on steadily.
3) Make sure the left and right ALIGN lights start to flash
when the alignment time reaches zero on the ISDU.
Enter the incorrect latitude of N00°00.0' on the ISDU.
Push the ENT key on the ISDU to send the latitude data.
Enter the correct longitute on the ISDU.
NOTE:
____
(p)
(q)
Push the ENT key on the ISDU to send the longitute data.
1) Make sure the left and right ALIGN and FAULT lights come
on.
2) Make sure the MASTER CAUTION and the IRS lights on the
glareshield come on.
Enter the correct latitude on the ISDU.
NOTE:
____
(r)
(s)
(u)
The correct latitude is dependent on the location of the
airplane.
Push the ENT key on the ISDU to send the latitude data.
Enter the correct longitute on the ISDU.
NOTE:
____
(t)
The correct longitude is dependent on the location of
the airplane.
The correct longitude is dependent on the location of
the airplane.
Push the ENT key on the ISDU to send the longitute data.
1) Make sure the left and right FAULT lights go off.
Push the MASTER CAUTION switch on the glareshield to turn off
the MASTER CAUTION and the IRS lights.
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(v)
J.
Set the DSPL SEL switch to the HDG/STS position.
1) Make sure there is no fault code shown on the ISDU.
2) Make sure the left ALIGN light on the MSU comes on steadily
or goes off.
3) Make sure the aircraft true heading shows on the ISDU when
the ALIGN light on the MSU went off.
(w) Set the SYS DSPL switch on the ISDU to the R position.
1) Make sure there is no fault code shown on the ISDU.
2) Make sure the right ALIGN light on the MSU comes on
steadily or goes off.
3) Make sure the aircraft true heading shows on the ISDU when
the ALIGN light on the MSU went off.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-051
Set the mode select switches on the MSU to the OFF position.
NOTE:
____
(2)
(3)
(4)
Some switches must be pulled before you turn them. If you
try to turn these switches before you pull them, you can
damage them.
SUBTASK 860-072
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D15
FMCS CDU 2
SUBTASK 860-052
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-2:
1) 6A6
FLIGHT CONTROL FLAP LOAD RELIEF
SUBTASK 860-053
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-21-00-730-802
4.
________________________________
Air
Data Reference - System Test
A. General
(1) This task contains these tests:
(a) ADM and standby altimeter airspeed indicator test
(b) TAT probe and TAT probe heater test
B. References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
C. Equipment
(1) Analyzer (or alternative tool)
(a) 429EBP Analyzer - Data Bus, ARINC 429 Hand Held, Battery
Powered, Non-Volitile Trap Mode Memory (recommended)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
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(b)
(2)
(3)
DT400H Analyzer - Data Bus, ARINC 429 (alternative)
Atlantic Instrument (Vendor Code 0U2T5)
P.O. Box 1466, Melbourne FL 32902-1466
(c) TYPE 030/026 Analyzer - Data Bus, ARINC 429 (alternative)
FCC Systems Limited
The Old Armoury, Court Barton, Crewkerne, Somerset, TA18 7HP
England
(d) MODEL 429HBA Analyzer - Data Bus, ARINC 429, Hand Held
(alternative)
Interface Technology (Vendor Code 5J927)
300 S. Lemon Creek Drive, Suite A, Walnut CA 91789
Analyzer (or alternative tool)
(a) MODEL 429HBA Analyzer - Data Bus, ARINC 429, Hand Held
(recommended)
Interface Technology (Vendor Code 5J927)
300 S. Lemon Creek Drive, Suite A, Walnut CA 91789
(b) 429EBP Analyzer - Data Bus, ARINC 429 Hand Held, Battery
Powered, Non-Volitile Trap Mode Memory (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(c) DT400H Analyzer - Data Bus, ARINC 429 (alternative)
Atlantic Instrument (Vendor Code 0U2T5)
P.O. Box 1466, Melbourne FL 32902-1466
(d) TYPE 030/026 Analyzer - Data Bus, ARINC 429 (alternative)
FCC Systems Limited
The Old Armoury, Court Barton, Crewkerne, Somerset, TA18 7HP
England
Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
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(g)
ú
ú
ú
ú
ú
ú
D.
E.
ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(4) Thermometer (or alternative tool)
(a) DHS-24X-FM Thermometer - Infared (recommended)
Wahl Instruments Inc. (Vendor Code 08086)
234 Weaverville Highway, Asheville NC 28804-1228
(b) IR-16L3 IS Thermometer - Infrared (Laser Sighted) (alternative)
Minnesota Mining and Mfg. Co. (Vendor Code 57707)
3 M Austin Center, Austin TX 78769-2963
Access
(1) Location Zones
(a) 117 Main Equipment Center, Left
(b) 118 Main Equipment Center, Right
(c) 211 Flight Compartment, Left
(d) 212 Flight Compartment, Right
Prepare for the Air Data Reference System Test
(1)
SUBTASK 730-002
Examine each pitot-static probe before and after this test for
damage to the circular leading edge of its barrel.
(2)
SUBTASK 730-003
Examine each pitot-static probe before and after this test for
blockage in the drain or static ports.
SUBTASK 730-004
CAUTION:
_______
(3)
OBEY THESE PRECAUTIONS BEFORE YOU APPLY PRESSURE TO THE PITOTSTATIC SYSTEM. IF YOU DO NOT OBEY THESE PRECAUTIONS, DAMAGE TO
THE EQUIPMENT AND INSTRUMENTS CAN OCCUR.
Obey these precautions before you apply pressure to the pitot-static
system.
(a) Supply the electrical power for the ADIRS before you make the
static or total pressure hook-ups.
(b) Keep power on until all pressure hook-up are opened.
(c) Pressure changes must be flow controlled to prevent sudden
changes in pressure and possible damage to the air data
hardware.
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(d)
(e)
(f)
(g)
(h)
(i)
(j)
(k)
Keep the static pressure in the range of 3.26 to 33.31 inches
Hg.
Do not permit the static pressure to be more than 28 inches Hg.
from the ambient pressure.
Keep the total pressure in the range of 3.26 to 41.34 inches
Hg.
When you adjust the pressure, make sure the rate of change of
altitude is less than 5,000 feet per minute.
When you adjust the pressure, make sure the rate of change of
airspeed is less than 300 knots per minute.
Keep the static line pressure less than the pitot line
pressure.
Make sure the difference between the static and pitot line
pressure is not larger than 10 inches Hg.
Make sure the autopilot system stays off during the test.
CAUTION:
_______
MAKE SURE YOU DO NOT SUPPLY ELECTRICAL POWER TO THE PITOT
PROBE HEATER. THIS CAN CAUSE DAMAGE TO THE PITOT PROBE.
(l)
(m)
F.
Make sure the pitot probe heaters stay off during the test.
Connect the captain's, F/O's, and alternate static systems
together during the test.
(n) Apply static pressure to all systems at the same time.
(o) Connect the captain's, F/O's, and alternate pitot tubes
together during the test.
(p) Apply pitot pressure to all systems at the same time.
ADM and Standby Altimeter/Airspeed Indicator Test
(1)
SUBTASK 730-007
Do these steps to do an ADM and Standby Altimeter/Airspeed Indicator
Test:
(a) Disconnect and plug the static pressure line at the cabin
differential pressure indicator.
(b) Turn the altimeter BARO knobs on the captain's EFIS control
panel, F/O's EFIS control panel, and standby altimeter through
the full range.
(c) Set the altimeter BARO knobs on the captain's EFIS control
panel, F/O's EFIS control panel, and standby altimeter to 29.92
inches of Hg.
(d) Set the ATC mode switch on the ATC control panel, P8-29, to the
STBY position.
(e) Make sure that the vanes are streamlined with the airplane in
order to set them to zero degrees.
(f) Connect the test set, to the airplane.
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(g)
Apply pressures as shown in the table below for all the test
points.
NOTE:
____
At each test value, permit the pressure to become stable
for one minute.
All values must be in the limits shown.
Do not hit or shake the indicators before you read the
values.
Read the indicators at the same time for each value.
Make sure the indicators move smoothly during pressure
changes.
~¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦ Test ¦ Static ¦ Altitude ¦ Pitot
¦ Airspeed ¦
¦ Point ¦ Pressure ¦
¦ Pressure ¦
¦
¦
¦ in. Hg ¦
feet
¦ in. Hg ¦ Knots
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
1
¦ 29.921 ¦
0 ¦ 30.311 ¦
90
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
2
¦ 24.896 ¦
5,000 ¦ 27.996 ¦
250
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
3
¦ 16.886 ¦ 15,000 ¦ 17.703 ¦
130
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
4
¦ 11.104 ¦ 25,000 ¦ 17.013 ¦
340
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
5
¦
7.041 ¦ 35,000 ¦ 10.963 ¦
280
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
6
¦
5.286 ¦ 41,000 ¦
7.95
¦
233
¦
²¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
1) Make sure all the outputs are within the limits specified
in the applicable table below.
a) For 737-700 aircraft, refer to the table that follows:
~¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦ Test ¦ Primary ¦ Primary ¦ Standby
¦ Standby ¦
¦ Point ¦ Altitude ¦ Airspeed ¦ Altimeter ¦ Airspeed ¦
¦
¦
feet
¦ knots
¦
feet
¦ Knots
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
1
¦
-39|15 ¦
85|2
¦
0|30 ¦
90|3.5 ¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
2
¦ 4,722|25 ¦ 240|2
¦ 5,000|70 ¦ 250|5
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
3
¦ 14,882|25 ¦ 124|2
¦ 15,000|110 ¦ 130|3.5 ¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
4
¦ 24,148|50 ¦ 328|2
¦ 25,000|160 ¦ 340|8
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
5
¦ 34,193|60 ¦ 270|2
¦ 35,000|210 ¦ 279|6
¦
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~¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦ Test ¦ Primary ¦ Primary ¦ Standby
¦ Standby ¦
¦ Point ¦ Altitude ¦ Airspeed ¦ Altimeter ¦ Airspeed ¦
¦
¦
feet
¦ knots
¦
feet
¦ Knots
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
6
¦ 40,230|70 ¦ 224|2
¦ 41,000|235 ¦ 233|6
¦
²¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
b) For 737-900 aircraft, refer to the table that follows:
~¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦ Test ¦ Primary ¦ Primary ¦ Standby
¦ Standby ¦
¦ Point ¦ Altitude ¦ Airspeed ¦ Altimeter ¦ Airspeed ¦
¦
¦
feet
¦ knots
¦
feet
¦ Knots
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
1
¦
-38|15 ¦
85|2
¦
0|30 ¦
90|3.5 ¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
2
¦ 4,6XX|25 ¦ 23X|2
¦ 5,000|70 ¦ 250|5
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
3
¦ 14,8XX|25 ¦ 12X|2
¦ 15,000|110 ¦ 130|3.5 ¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
4
¦ 23,XXX|50 ¦ 32X|2
¦ 25,000|160 ¦ 340|8
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
5
¦ 33,XXX|60 ¦ 26X|2
¦ 35,000|210 ¦ 279|6
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
6
¦ 39,XXX|70 ¦ 22X|2
¦ 41,000|235 ¦ 233|6
¦
²¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
2) Make sure the differences between the captain's and first
officer's primary altimeters and airspeed indicators are
not larger than the values shown in the table below.
~¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼
¦ Test ¦ Altitude ¦ Altimeters ¦ Airspeed ¦ Airspeed
¦
¦ Point ¦ Input
¦
¦ Input
¦ Indicators ¦
¦
¦
feet
¦
feet
¦ knots
¦ knots
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
1
¦
0 ¦
a30
¦
90
¦
a4
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
2
¦
5,000 ¦
a50
¦
250
¦
a4
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
3
¦ 15,000 ¦
a50
¦
130
¦
a4
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
4
¦ 25,000 ¦
a100
¦
340
¦
a4
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
5
¦ 35,000 ¦
a120
¦
280
¦
a4
¦
»¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼«
¦
6
¦ 41,000 ¦
a140
¦
233
¦
a4
¦
²¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¹
(h) Remove the pressure from the pitot static lines.
(i) Disconnect the test set.
(j) Connect the cabin altitude differential pressure indicator to
its static pressure source.
EFFECTIVITY
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G.
TAT Probe and TAT Probe Heater Test
(1)
ú
ú
SUBTASK 860-048
Do these steps to do the TAT probe and TAT probe heater test:
(a) Make sure the test set, test fixtures, adapters, and clamps
were removed from the airplane external probes.
(b) Install the thermometer, DHS-24X-FM into the TAT probe.
(c) Wait until the temperature shown on the thermometer is steady,
then record the TAT temperature value.
(d) Record the TAT temperature shown on the engine display.
(e) Make sure the TAT temperature on the engine display is within
2°of the thermometer temperature.
(f) Remove the thermometer, DHS-24X-FM from the TAT probe.
(g) Open these circuit breakers and attach DO-NOT-CLOSE tags:
1) Circuit Breaker Panel, P18-3:
a) 18C4
HEATERS ELEV PITOT LEFT
b) 18D3
HEATERS ALPHA VANE RIGHT
c) 18D4
HEATERS ELEV PITOT RIGHT
d) 18D6
HEATERS AUX PITOT
(h) Make sure that these circuit breakers are closed:
1) Circuit Breaker Panel, P6-3:
a) 6F16
PROBE INDICATION F/O
b) 6F18
PROBE INDICATION CAPT
2) Circuit Breaker Panel, P18-3:
a) 18C1
HEATERS CAPT PITOT
b) 18C2
HEATERS TEMP PROBE
c) 18C3
HEATERS ALPHA VANE LEFT
(i) Set the PITOT STATIC HEAT A switch on the forward overhead
panel, P5, to the ON position.
1) Make sure the TAT temperature on the engine display
increases after you permit time for the heaters to warm up.
(j) Set the PITOT STATIC HEAT A switch on the forward overhead
panel, P5, to the OFF position.
(k) Connect the analyzer, 429EBP or analyzer, MODEL 429HBA to the
FCC-L test connector J3, pin 88 (HI) and pin 89 (LO) to read
the left ADIRU output, ADR label 270.
(l) Set the PITOT STATIC HEAT A switch on the forward overhead
panel, P5, to the ON position.
1) Make sure the ADR label 270 bits 14, 16, and 17 are set to
"1".
(m) Set the PITOT STATIC HEAT A switch on the forward overhead
panel, P5, to the OFF position.
1) Make sure the ADR label 270 bits 14, 16, and 17 are set to
"0".
(n) Disconnect the analyzer, 429EBP or analyzer, MODEL 429HBA from
the FCC-L test connector J3.
(o) Connect the analyzer, 429EBP or analyzer, MODEL 429HBA to the
FCC-R test connector J3, pin 88 (HI) and pin 89 (LO) to read
the right ADIRU output, ADR label 270.
EFFECTIVITY
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(p)
H.
Make sure that these circuit breakers are closed:
1) Circuit Breaker Panel, P18-3:
a) 18D3
HEATERS ALPHA VANE RIGHT
b) 18D5
HEATERS F/O PITOT
(q) Set the PITOT STATIC HEAT B switch on the forward overhead
panel, P5, to the ON position.
1) Make sure the ADR label 270 bits 14, and 17 are set to "1".
(r) Set the PITOT STATIC HEAT A switch on the forward overhead
panel, P5, to the ON position.
1) Make sure the ADR label 270 bits 16 is set to "1".
(s) Open these circuit breakers and attach DO-NOT-CLOSE tags:
1) Circuit Breaker Panel, P18-3:
a) 18C1
HEATERS CAPT PITOT
b) 18C2
HEATERS TEMP PROBE
c) 18C3
HEATERS ALPHA VANE LEFT
d) 18D3
HEATERS ALPHA VANE RIGHT
e) 18D5
HEATERS F/O PITOT
(t) Set the PITOT STATIC HEAT B switch on the forward overhead
panel, P5, to the OFF position.
1) Make sure the ADR label 270 bits 14, and 17 are set to "0".
(u) Set the PITOT STATIC HEAT A switch on the forward overhead
panel, P5, to the OFF position.
1) Make sure the ADR label 270 bits 16 is set to "0".
(v) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
1) Circuit Breaker Panel, P18-3:
a) 18C1
HEATERS CAPT PITOT
b) 18C2
HEATERS TEMP PROBE
c) 18C3
HEATERS ALPHA VANE LEFT
d) 18C4
HEATERS ELEV PITOT LEFT
e) 18D3
HEATERS ALPHA VANE RIGHT
f) 18D4
HEATERS ELEV PITOT RIGHT
g) 18D5
HEATERS F/O PITOT
h) 18D6
HEATERS AUX PITOT
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 730-009
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
AIR DATA INERTIAL REFERENCE UNIT - REMOVAL/INSTALLATION
_______________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the air data inertial reference unit (ADIRU)
(2) An installation of the ADIRU.
B. Two ADIRUs are installed in the main equipment center. The left and
right ADIRUs are installed on shelf No. 2 in the E5 electronic equipment
rack.
TASK 34-21-01-000-801
2.
________________________________________
Air
Data Inertial Reference Unit Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the air data inertial
reference unit (ADIRU).
NOTE:
____
B.
C.
D.
Removal of the ADIRU will disable the ground crew call
function of the equipment cooling low flow detection. This
cooling low flow condition could cause damage to the
equipment.
(2) The removal instructions are the same for the two ADIRUs.
References
(1) AMM TASK 06-41-00-800-801 p201, Finding an Access Door or Panel on
the Lower Half of the Fuselage
(2) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
Removal Procedure
(1)
(2)
SUBTASK 860-001
Set the applicable mode select switch on the IRS mode select unit
(MSU) to the OFF position.
SUBTASK 860-002
Open the applicable circuit breakers and attach DO-NOT-CLOSE tags:
(a) For the left ADIRU:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADIRU:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
EFFECTIVITY
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c)
(3)
6C17
ADIRU RIGHT DC
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center (AMM TASK 06-41-00-800-801 p201).
SUBTASK 020-001
CAUTION:
_______
(4)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
ADIRU [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE ADIRU [1].
Remove the ADIRU [1] from the shelf
(AMM TASK 20-10-07-000-801 p201).
TASK 34-21-01-400-801
3.
_____________________________________________
Air
Data Inertial Reference Unit Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the ADIRU [1].
NOTE:
____
The air data inertial reference unit is referred as the ADIRU
in this task.
(2)
(3)
The installation instructions are the same for the two ADIRUs.
The installation test makes sure that the ADIRU [1] is installed
correctly.
B. References
(1) AMM TASK 06-41-00-800-801 p201, Finding an Access Door or Panel on
the Lower Half of the Fuselage
(2) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(5) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(6) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Unit
¦ 34-21-01
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
EFFECTIVITY
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MAINTENANCE MANUAL
ELECTRONIC
EQUIPMENT
RACK, E5
SEE
A
ELECTRONIC
EQUIPMENT
ACCESS DOOR, 117A
[1] AIR DATA
INERTIAL
REFERENCE
UNITS (ADIRU)
(E5-2)
ELECTRONIC
EQUIPMENT
ACCESS DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACK, E5
A
Air Data Inertial Reference Unit (ADIRU) Installation
Figure 401
F64121
34-21-01-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
E.
Installation Procedure
(1)
(2)
SUBTASK 860-003
Make sure the applicable mode select switch on the IRS MSU is in the
OFF position.
SUBTASK 860-004
Make sure the applicable circuit breakers are open:
(a) For the left ADIRU:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADIRU:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
SUBTASK 420-001
CAUTION:
_______
(3)
(4)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
ADIRU [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE ADIRU [1].
Install the ADIRU [1] on the shelf (AMM TASK 20-10-07-400-801 p201).
SUBTASK 860-005
Remove the DO-NOT-CLOSE tags and close the applicable circuit
breakers:
(a) For the left ADIRU:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADIRU:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A
(AMM TASK 06-41-00-800-801 p201).
Installation Test
(5)
F.
(1)
SUBTASK 860-006
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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(2)
SUBTASK 860-007
For the applicable ADIRU, do this task: Air Data Inertial Reference
System - Alignment from the FMC CDU (AMM TASK 34-21-00-820-801 p201)
or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
(3)
SUBTASK 860-008
Set the applicable mode select switch on the IRS MSU to the OFF
position.
(4)
SUBTASK 860-009
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
34-21-01
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MAINTENANCE MANUAL
INERTIAL SYSTEM DISPLAY UNIT - REMOVAL/INSTALLATION
___________________________________________________
1.
General
_______
A. This procedure has two tasks:
(1) A removal of the inertial system display unit (ISDU)
(2) An installation of the ISDU.
B. The ISDU is installed on the P5 overhead panel in the flight compartment.
TASK 34-21-02-000-801
2.
____________________________________
Inertial
System Display Unit Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the ISDU [1].
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
C. Removal Procedure
(1)
(2)
(3)
SUBTASK 860-001
Set the two mode select switches on the IRS mode select unit (MSU)
to the OFF position.
SUBTASK 860-002
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(c) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 020-001
Do these steps to remove the ISDU [1]:
(a) Release the quarter-turn fasteners [2] on the front of the ISDU
[1].
CAUTION:
_______
(b)
(c)
CAREFULLY REMOVE THE ISDU [1] FROM THE INSTRUMENT PANEL.
TOO MUCH FORCE CAN CAUSE DAMAGE TO THE ELECTRICAL CABLES
ON THE REAR OF THE ISDU [1].
Carefully lower the ISDU [1] until you can get access to the
electrical connectors [3].
Disconnect the electrical connectors [3] from the rear of the
ISDU [1].
EFFECTIVITY
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MAINTENANCE MANUAL
INERTIAL SYSTEM
DISPLAY UNIT
SEE
A
FLIGHT COMPARTMENT
[3] ELECTRICAL
CONNECTOR
(2 LOCATIONS)
[1] INERTIAL
SYSTEM
DISPLAY
UNIT
[2] QUARTER-TURN
FASTENER
(4 LOCATIONS)
INERTIAL SYSTEM DISPLAY UNIT
A
Inertial System Display Unit Installation
Figure 401
G48059
34-21-02-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
TASK 34-21-02-400-801
3.
_________________________________________
Inertial
System Display Unit Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the ISDU [1].
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Unit assy
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
E. Installation Procedure
(1)
(2)
(3)
SUBTASK 860-003
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
(c) Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
SUBTASK 420-001
Do these steps to install the ISDU [1]:
(a) Connect the electrical connectors [3] to the ISDU [1].
(b) Carefully install the ISDU [1] into the P5 panel.
(c) Lock the quarter-turn fasteners [2] on the front of the ISDU
[1].
SUBTASK 860-004
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C15
ADIRU RIGHT EXC
3) 6C17
ADIRU RIGHT DC
(b) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
EFFECTIVITY
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(c)
F.
Circuit Breaker Panel, P18-2:
1) 18E8
ADIRU LEFT EXC
Installation test
(1)
(2)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-006
Set the two mode select switches on the IRS MSU to the NAV position.
SUBTASK 710-001
Do a test of the ISDU as follows:
(a) Set the SYS DSPL switch on the ISDU [1] to the L position.
(b) Hold the DSPL SEL switch on the ISDU [1] in the TEST position.
(c) Make sure all the annunciators on the left side of the IRS MSU
come on for approximately two seconds.
(d) Release the DSPL SEL switch.
(e) Set the SYS DSPL switch on the ISDU [1] to the R position.
(f) Hold the DSPL SEL switch on the ISDU [1] in the TEST position.
(g) Make sure all the annunciators on the right side of the IRS MSU
come on for approximately two seconds.
(h) Release the DSPL SEL switch.
Put the Airplane Back to Its Usual Condition
(3)
G.
(1)
(2)
SUBTASK 860-007
Set the two mode select switches on the IRS MSU to the OFF position.
SUBTASK 860-008
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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IRS MODE SELECT UNIT - REMOVAL/INSTALLATION
___________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the IRS mode select unit (MSU)
(2) An installation of the IRS MSU.
B. The IRS MSU is installed on the P5-69 aft overhead panel in the flight
compartment.
C. Each mode select switch has a mechanically locked position. The
mechanically locked positions prevent accidental movement of the switch.
When you change the switch position, you need to pull the switch away
from the unit and set the switch to the different position. This will
prevent damage to the switch.
TASK 34-21-03-000-801
2.
____________________________
IRS
Mode Select Unit Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the IRS MSU [2].
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
C. Removal Procedure
(1)
(2)
(3)
SUBTASK 860-001
Set the two mode select switches on the IRS MSU [2] to the OFF
position.
SUBTASK 860-002
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-3:
1) 6D11
INDICATOR MASTER DIM DIM/TST CONT
SUBTASK 020-001
Do these steps to remove the IRS MSU [2]:
(a) Release the quarter-turn fasteners [3] on the front of the IRS
MSU [2].
CAUTION:
_______
(b)
(c)
CAREFULLY REMOVE THE IRS MSU [2] FROM THE INSTRUMENT
PANEL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE ELECTRICAL
CABLE AT THE REAR OF THE IRS MSU [2].
Carefully lower the IRS MSU [2] until you can get access to the
electrical connector [1].
Disconnect the electrical connector [1] from the rear of the
IRS MSU [2].
EFFECTIVITY
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MAINTENANCE MANUAL
MODE SELECT
PANEL
SEE
A
FLIGHT COMPARTMENT
[1] ELECTRICAL
CONNECTOR
(2 LOCATIONS)
1
[3] QUARTER-TURN
FASTENER
(4 LOCATIONS)
[2] MODE
SELECT
UNIT
MODE SELECT UNIT
1
MSUs WITH GPS SWITCH
A
Mode Select Unit (MSU) Installation
Figure 401
G48087
34-21-03-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
TASK 34-21-03-400-801
3.
_________________________________
IRS
Mode Select Unit Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the IRS MSU [2].
(2) The installation test makes sure the IRS MSU [2] is installed
correctly.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
2 ¦ Module assy
¦ 33-11-90
01
455 ¦
¦
¦
¦ 34-26-00
01
60 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
E. Installation Procedure
(1)
(2)
SUBTASK 860-003
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-3:
1) 6D11
INDICATOR MASTER DIM DIM/TST CONT
SUBTASK 420-001
Do these steps to install the IRS MSU [2]:
(a) Connect the electrical connector [1] to the IRS MSU [2].
(b) Carefully install the IRS MSU [2] into the P5-69, aft overhead
panel.
(c) Lock the quarter-turn fasteners [3] on the front of the IRS MSU
[2].
SUBTASK 860-004
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-3:
1) 6D11
INDICATOR MASTER DIM DIM/TST CONT
Installation Test
(3)
F.
(1)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-006
Set the two mode select switches on the IRS MSU [2] to the NAV
position.
EFFECTIVITY
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MAINTENANCE MANUAL
(3)
SUBTASK 750-001
Make sure the two ON DC annunciators on the IRS MSU [2] come on for
approximately 5 seconds.
SUBTASK 750-002
Make sure the two ALIGN annunciators on the IRS MSU [2] come on
after the two ON DC annunciators go off.
Put the Airplane Back to Its Usual Condition
(4)
G.
(1)
SUBTASK 860-007
Set the two mode select switches on the IRS MSU [2] to the OFF
position.
(2)
SUBTASK 860-008
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
AIR DATA MODULE - REMOVAL/INSTALLATION
______________________________________
1.
General
_______
A. This
(1)
(2)
(3)
(4)
procedure has these tasks:
A removal of the pitot air data module (ADM)
A removal of the static ADM
An installation of the pitot ADM
An installation of the static ADM.
TASK 34-21-04-000-801
2.
_____________________________
Pitot
Air Data Module Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the pitot ADM [4]. The
two pitot ADMs [4] are located in the forward equipment compartment
at STA 200, WL 180. They are accessed thru the forward equipment
access door.
(2) The removal instructions are the same for the two pitot ADMs [4].
B. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open the applicable circuit breakers and attach DO-NOT-CLOSE tags:
(a) For the left ADM [4]:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADM [4]:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
SUBTASK 020-001
Do these steps to remove the pitot ADM [4]:
(a) Disconnect the pneumatic connector [3] from the ADM [4].
(b) Put a protective cover on the pneumatic connector [3] of the
ADM [4].
(c) While you hold the ADM [4], loosen the captive screws [1] at
each corner of the ADM [4].
(d) Disconnect the electrical connector [2] from the ADM [4].
(e) Put a protective cover on the electrical connector [2] of the
ADM [4].
(f) Remove the ADM [4].
EFFECTIVITY
34-21-04
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MAINTENANCE MANUAL
PITOT AIR
DATA MODULES
SEE
A
FOWARD EQUIPMENT
ACCESS DOOR
FWD
LEFT PITOT ADM
RIGHT PITOT ADM
SEE
SEE
B
B
FOWARD EQUIPMENT COMPARTMENT
A
Pitot Air Data Module (ADM) Installation
Figure 401 (Sheet 1)
G50457
34-21-04-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
[1] CAPTIVE SCREW
(4 LOCATIONS)
[2] ELECTRICAL
CONNECTOR
FWD
[3] PNEUMATIC
CONNECTOR
[4] ADM
PITOT AIR DATA MODULE (ADM)
(EXAMPLE)
B
Pitot Air Data Module (ADM) Installation
Figure 401 (Sheet 2)
G50519
EFFECTIVITY
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MAINTENANCE MANUAL
TASK 34-21-04-000-802
3.
______________________________
Static
Air Data Module Removal (Fig. 402)
A. General
(1) This procedure gives instructions to remove the static ADM [3]. The
two static ADMs [3] are located in the forward cargo compartment at
STA 405 and STA 435, WL 206, BL 0. They are accessed thru the
forward cargo door.
(2) The removal instructions are the same for the two static ADMs [3].
B. References
(1) AMM TASK 25-52-09-000-801 p401, Cargo Compartment Ceiling Liner
Removal
C. Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
D. Removal Procedure
(1)
(2)
(3)
SUBTASK 860-002
Open the applicable circuit breakers and attach DO-NOT-CLOSE tags:
(a) For the left ADM [3]:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADM [3]:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
SUBTASK 010-001
To remove the ceiling liner for the applicable static ADM [3] in the
forward cargo compartment, do this task: Cargo Compartment Ceiling
Liner Removal (AMM TASK 25-52-09-000-801 p401).
SUBTASK 020-002
Do these steps to remove the static ADM [3]:
(a) Disconnect the pneumatic connector [4] from the ADM [3].
(b) Put a protective cover on the pneumatic connector [4] of the
ADM [3].
(c) While you hold the ADM [3], loosen the captive screws [2] at
each corner of the ADM [3].
(d) Disconnect the electrical connector [1] from the ADM [3].
(e) Put a protective cover on the electrical connector [1] of the
ADM [3].
(f) Remove the ADM [3].
EFFECTIVITY
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A
737-600/700/800/900
MAINTENANCE MANUAL
FORWARD
CARGO
DOOR
STATIC AIR
DATA MODULES
SEE
A
FWD
INBD
LEFT STATIC ADM
(BEHIND CEILING PANEL)
RIGHT STATIC ADM
(BEHIND CEILING PANEL)
SEE
SEE
B
B
CARGO COMPARTMENT
A
Static Air Data Module (ADM) Installation
Figure 402 (Sheet 1)
G47836
34-21-04-990-802
EFFECTIVITY
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MAINTENANCE MANUAL
[1] ELECTRICAL
CONNECTOR
[2] CAPTIVE SCREW
(4 LOCATIONS)
[4] PNEUMATIC
CONNECTOR
[3] ADM
FWD
STATIC AIR DATA MODULE (ADM)
(EXAMPLE)
B
Static Air Data Module (ADM) Installation
Figure 402 (Sheet 2)
G48021
EFFECTIVITY
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MAINTENANCE MANUAL
TASK 34-21-04-400-801
4.
__________________________________
Pitot
Air Data Module Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the pitot ADM [4]. The
two pitot ADMs [4] are located in the forward equipment compartment
at STA 200, WL 180. They are accessed thru the forward equipment
access door.
(2) The installation instructions are the same for the two pitot ADMs
[4].
B. References
(1) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
4 ¦ Module
¦ 34-13-00
02
25 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
E. Installation Procedure
(1)
(2)
SUBTASK 860-003
Make sure the applicable circuit breakers are open:
(a) For the left ADM [4]:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADM [4]:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
SUBTASK 420-001
Do these steps to install the pitot ADM [4]:
(a) Remove the protective cover from the electrical connector [2]
of the ADM [4].
(b) Examine the electrical connector [2] for loose, bent or broken
pins.
EFFECTIVITY
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MAINTENANCE MANUAL
(c)
(d)
(e)
(f)
(g)
Connect the electrical connector [2] to the ADM [4].
Put the ADM [4] into position on the airplane.
Tighten the captive screws [1] at each corner of the ADM [4] to
15-25 inch-pounds (1.7-2.8 newton-meters).
Remove the protective cover from the pneumatic connector [3] of
the ADM [4].
Connect the pneumatic connector [3] to the ADM [4].
SUBTASK 860-004
Remove DO-NOT-CLOSE tags and close the applicable circuit breakers:
(a) For the left ADM [4]:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADM [4]:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
Installation Test
(3)
F.
(1)
(2)
SUBTASK 860-005
To do the ADIRS alignment, do this task:
(AMM TASK 34-21-00-820-801 p201) or
(AMM TASK 34-21-00-820-802 p201).
SUBTASK 740-001
To do the BITE CURRENT STATUS check, do this task: Air Data
Inertial Reference System - Operational Test
(AMM TASK 34-21-00-710-801 p501).
(a) Make sure the NO CURRENT FAULT message shows on the CDU.
TASK 34-21-04-400-802
5.
___________________________________
Static
Air Data Module Installation (Fig. 402)
A. General
(1) This procedure gives instructions to install the static ADM [3].
The two static ADMs [3] are located in the forward cargo compartment
at STA 405 and STA 435, WL 206, BL 0. They are accessed thru the
forward cargo door.
(2) The installation instructions are the same for the two static ADMs
[3].
B. References
(1) AMM TASK 25-52-09-400-801 p401, Cargo Compartment Ceiling Liner
Installation
(2) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
(3) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
EFFECTIVITY
34-21-04
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MAINTENANCE MANUAL
(4)
ú
ú
AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 402
3 ¦ Module
¦ 34-13-00
02
25 ¦
¦
¦
¦
03
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 121 Forward Cargo Compartment - Left
(b) 122 Forward Cargo Compartment - Right
E. Installation Procedure
(1)
(2)
(3)
SUBTASK 860-006
Make sure the applicable circuit breakers are open:
(a) For the left ADM [3]:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADM [3]:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
SUBTASK 420-002
Do these steps to install the static ADM [3]:
(a) Remove the protective cover from the electrical connector [1]
of the ADM [3].
(b) Examine the electrical connector [1] for loose, bent or broken
pins.
(c) Connect the electrical connector [1] to the ADM [3].
(d) Put the ADM [3] into position on the airplane.
(e) Tighten the captive screws [2] at each corner of the ADM [3] to
15-25 inch-pounds (1.7-2.8 newton-meters).
(f) Remove the protective cover from the pneumatic connector [4] of
the ADM [3].
(g) Connect the pneumatic connector [4] to the ADM [3].
SUBTASK 410-001
To install the ceiling liner for the applicable static ADM [3] in
the forward cargo compartment, do this task: Cargo Compartment
Ceiling Liner Installation (AMM TASK 25-52-09-400-801 p401).
EFFECTIVITY
34-21-04
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Page 409
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MAINTENANCE MANUAL
SUBTASK 860-007
Remove DO-NOT-CLOSE tags and close the applicable circuit breakers:
(a) For the left ADM [3]:
1) Circuit Breaker Panel, P18-1:
a) 18E5
ADIRU LEFT DC
b) 18E7
ADIRU LEFT AC
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right ADM [3]:
1) Circuit Breaker Panel, P6-1:
a) 6C14
ADIRU RIGHT AC
b) 6C15
ADIRU RIGHT EXC
c) 6C17
ADIRU RIGHT DC
Installation Test
(4)
F.
(1)
(2)
SUBTASK 860-008
To do the ADIRS alignment, do this task:
(AMM TASK 34-21-00-820-801 p201) or
(AMM TASK 34-21-00-820-802 p201).
SUBTASK 740-002
To do the BITE CURRENT STATUS check, do this task: Air Data
Inertial Reference System - Operational Test
(AMM TASK 34-21-00-710-801 p501).
(a) Make sure the NO CURRENT FAULT message shows on the CDU.
EFFECTIVITY
34-21-04
ALL
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Page 410
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MAINTENANCE MANUAL
ANGLE OF ATTACK SENSOR - REMOVAL/INSTALLATION
_____________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the Angle of Attack (AOA) sensor
(2) An installation of the AOA sensor.
B. Two AOA sensors are installed on the airplane. The left and right AOA
sensors are mounted on the left and right sides respectively, outboard
and above the nose landing gear wheel well.
TASK 34-21-05-000-801
2.
______________________________
Angle
of Attack Sensor Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the AOA sensor [1].
(2) The removal instructions are the same for the two AOA sensors [1].
B. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
C. Access
(1) Location Zones
(a) 115 Area Outboard and Above Nose Landing Gear Wheel Well, Left
(b) 116 Area Outboard and Above Nose Landing Gear Wheel Well,
Right
D. Removal Procedure
(1)
ú
ú
ú
ú
SUBTASK 860-001
Open the applicable circuit breakers and attach DO-NOT-CLOSE tags:
(a) For the left AOA sensor [1]:
1) Circuit Breaker Panel, P18-3:
a) 18C3
HEATERS ALPHA VANE LEFT
2)
ú
(b)
Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
For the right AOA sensor [1]:
1) Circuit Breaker Panel, P6-1:
a) 6C15
ADIRU RIGHT EXC
2) Circuit Breaker Panel, P18-3:
ú
ú
a)
(2)
18D3
HEATERS ALPHA VANE RIGHT
SUBTASK 020-001
Do these steps to remove the AOA sensor [1]:
(a) Use a sealant removal tool to remove the sealant from around
the AOA sensor [1].
(b) Remove the screws [2] from the AOA sensor [1].
EFFECTIVITY
34-21-05
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MAINTENANCE MANUAL
WARNING:
_______
MAKE SURE THAT THE AOA SENSOR [1] HEAT IS OFF.
PERSONS CAN OCCUR.
CAUTION:
_______
DO NOT PULL THE AOA SENSOR [1] AWAY FROM THE FUSELAGE WITH
TOO MUCH FORCE. TOO MUCH FORCE ON THE AOA SENSOR [1] CAN
CAUSE DAMAGE TO THE AOA SENSOR [1], THE ELECTRICAL
CONNECTORS [1], OR THE AIRPLANE SKIN.
(c)
(d)
(e)
(f)
(g)
INJURY TO
Carefully pull the AOA sensor [1] out until you can get to the
electrical connectors [5].
Disconnect the electrical connectors [5] from the AOA sensor
[1].
Temporarily attach the electrical connectors [5] to make sure
that they cannot fall into the fuselage.
Install protective caps on the electrical connectors [5].
Remove the gasket [4] and discard it.
TASK 34-21-05-400-801
3.
___________________________________
Angle
of Attack Sensor Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the AOA sensor [1].
(2) The installation instructions are the same for the two AOA sensors
[1].
B. References
(1) AMM TASK 20-10-34-110-802 p701, Clean Bare, Clad, or Plated Metal
with Solvent
(2) AMM TASK 27-32-00-740-803 p501, Stall Management Yaw Damper (SMYD)
BITE Test - Ground Test
(3) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
C. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
(2) D00015 Grease, Aircraft bearing - BMS3-24
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Sensor
¦ 34-21-51
01
15 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 113 Area Above and Outboard of Nose Landing Gear Wheel Well Left
(b) 114 Area Above and Outboard of Nose Landing Gear Wheel Well Right
EFFECTIVITY
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SEE
A
[1] AOA SENSOR
[2] SCREW
(8 LOCATIONS)
[5] ELECTRICAL
CONNECTOR
(2 LOCATIONS)
[4] GASKET
[3] ALIGNMENT PIN
(2 LOCATIONS)
FWD
A
NOTE:
____
LEFT AOA SENSOR SHOWN, RIGHT AOA SENSOR OPPOSITE.
Angle of Attack (AOA) Sensor Installation
Figure 401
F98950
34-21-05-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
F.
Installation Procedure
(1)
(2)
(3)
SUBTASK 860-002
Make sure the applicable circuit breakers are open:
(a) For the left AOA sensor [1]:
1) Circuit Breaker Panel, P18-3:
a) 18C3
HEATERS ALPHA VANE LEFT
2) Circuit Breaker Panel, P18-2:
a) 18E8
ADIRU LEFT EXC
(b) For the right AOA sensor [1]:
1) Circuit Breaker Panel, P6-1:
a) 6C15
ADIRU RIGHT EXC
2) Circuit Breaker Panel, P18-3:
a) 18D3
HEATERS ALPHA VANE RIGHT
SUBTASK 110-001
To clean the surface around the AOA hole and the surface of the
alignment pins, do this task: Clean Bare, Clad, or Plated Metal
with Solvent (AMM TASK 20-10-34-110-802 p701).
SUBTASK 390-001
Apply a thin layer of grease, BMS3-24, to the alignment pins on the
AOA sensor [1].
SUBTASK 420-001
Do these steps to install the AOA sensor [1]:
(a) Put the new gasket [4] into position on the AOA sensor [1].
(b) Remove the protective caps from the electrical connectors [5].
(c) Examine the electrical connectors [5] for loose, bent, or
broken pins.
(d) Connect the electrical connectors [5] to the AOA sensor [1].
(e) Carefully put the AOA sensor [1] into position.
(f) Install the screws [2] that hold the AOA sensor [1] to the
airplane.
(g) Tighten the screws [2] to 32-39 inch-pounds (3.6-4.4
newton-meters).
(h) Make sure the face of the AOA sensor [1] aligns to within 0.04
inch (1.02 mm) or less of the airplane skin.
(i) Measure the resistance between the base of the AOA sensor [1]
and the airplane skin.
1) Make sure the resistance is less than 0.010 ohm.
(j) Apply sealant, BMS5-95, around the AOA sensor [1].
Installation Test
(4)
G.
(1)
SUBTASK 710-001
To do the IR ground test, do this task: Air Data Inertial Reference
System - Operational Test (AMM TASK 34-21-00-710-801 p501).
EFFECTIVITY
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MAINTENANCE MANUAL
(2)
SUBTASK 710-002
To do the AOA sensor test for the Stall Management Yaw Damper (SMYD)
system interface, do this task: Stall Management Yaw Damper (SMYD)
BITE Test - Ground Test (AMM TASK 27-32-00-740-803 p501).
EFFECTIVITY
34-21-05
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MAINTENANCE MANUAL
TOTAL AIR TEMPERATURE PROBE - REMOVAL/INSTALLATION
__________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the Total Air Temperature (TAT) probe
(2) An installation of the TAT probe.
TASK 34-21-06-000-801
ú
2.
___________________________________
Total
Air Temperature Probe Removal (Fig. 401)
A. General
(1) This task gives instructions to remove the TAT probe [4].
B. Access
(1) Location Zones
(a) 113 Area Above and Outboard of Nose Landing Gear Wheel Well Left
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-3:
1) 18C2
HEATERS TEMP PROBE
SUBTASK 020-001
Do these steps to remove the TAT probe [4]:
(a) Use the sealant removal tool to remove the sealant from around
the TAT probe [4].
(b) Remove the screws [3] from the TAT probe [4].
WARNING:
_______
MAKE SURE THE TAT PROBE [4] HEAT IS OFF.
PERSONS CAN OCCUR.
CAUTION:
_______
DO NOT PULL THE TAT PROBE [4] AWAY FROM THE FUSELAGE WITH
TOO MUCH FORCE. TOO MUCH FORCE ON THE TAT PROBE [4] CAN
CAUSE DAMAGE TO THE ELECTRICAL CONNECTOR [1] OR THE
AIRPLANE SKIN.
(c)
(d)
(e)
(f)
(g)
INJURY TO
Carefully pull the TAT probe [4] from the fuselage to get
access to the electrical connector [1].
Disconnect the electrical connector [1] from the TAT probe [4].
Temporarily attach the electrical connector [1] to make sure it
does not fall into the fuselage.
Install a protective cap on the electrical connector [1].
Remove the gasket [2] and discard it.
TASK 34-21-06-400-801
3.
________________________________________
Total
Air Temperature Probe Installation (Fig. 401)
A. General
(1) This task gives instructions to install the TAT probe [4].
EFFECTIVITY
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MAINTENANCE MANUAL
TOTAL AIR
TEMPERATURE
PROBE
SEE
A
[1] ELECTRICAL
CONNECTOR
[2] GASKET
[3] SCREW
(6 LOCATIONS)
FWD
[4] TAT PROBE
STA 268 (APPROX)
A
Total Air Temperature (TAT) Probe Installation
Figure 401
G24501
34-21-06-990-801
EFFECTIVITY
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B.
References
(1) AMM TASK 20-10-34-110-802 p701, Clean Bare, Clad, or Plated Metal
with Solvent
(2) AMM TASK 30-31-00-730-801 p501, Pitot Probe, AOA Sensor, and TAT
Probe Heater Test
(3) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
C. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
4 ¦ Probe
¦ 34-21-06
04
10 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 113 Area Above and Outboard of Nose Landing Gear Wheel Well Left
F. Installation Procedure
(1)
(2)
(3)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-3:
1) 18C2
HEATERS TEMP PROBE
SUBTASK 110-001
To clean and prepare the surface and the sides of the installation
hole, do this task: Clean Bare, Clad, or Plated Metal with Solvent
(AMM TASK 20-10-34-110-802 p701).
SUBTASK 420-001
Do these steps to install the TAT probe [4]:
(a) Put the new gasket [2] into position on the TAT probe [4].
(b) Remove the protective cap from the electrical connector [1].
(c) Examine the electrical connector [1] for loose, bent, or broken
pins.
(d) Connect the electrical connector [1] to the TAT probe [4].
(e) Carefully put the TAT probe [4] into position.
NOTE:
____
(f)
(g)
(h)
The large intake should point forward.
Install the screws [3] that hold the TAT probe [4] to the
airplane.
Tighten the screws [3] to 18-22 inch-pounds (2-2.5
newton-meters).
Apply sealant, BMS5-95, around the TAT probe [4].
EFFECTIVITY
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SUBTASK 860-003
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-3:
1) 18C2
HEATERS TEMP PROBE
Installation Test
(4)
G.
(1)
(2)
(3)
SUBTASK 760-001
Measure the resistance between the body of the TAT probe [4] and the
airplane skin.
(a) Make sure the resistance is less that 0.010 ohms.
SUBTASK 730-001
Do this task: Pitot Probe, AOA Sensor, and TAT Probe Heater Test
(AMM TASK 30-31-00-730-801 p501).
SUBTASK 710-001
To do the ADR ground test, do this task:
Reference System - Operational Test
(AMM TASK 34-21-00-710-801 p501).
EFFECTIVITY
Air Data Inertial
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MAINTENANCE MANUAL
IRS MASTER CAUTION UNIT - REMOVAL/INSTALLATION
______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the IRS master caution unit (MCU)
(2) An installation of the IRS MCU.
B. The IRS MCU is installed in the P61 panel in the flight compartment.
TASK 34-21-07-000-801
2.
_______________________________
IRS
Master Caution Unit Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the IRS MCU.
B. References
(1) AMM TASK 20-40-12-000-801 p201, ESDS Handling for Printed Circuit
Board Removal
(2) AMM TASK 20-40-12-000-803 p201, Conductive Dust Cap and Connector
Cover Installation
C. Access
(1) Location Zones
(a) 212 Flight Compartment - Right
D. Removal Procedure
(1)
(2)
(3)
SUBTASK 860-001
Set the two mode select switches on the IRS mode select unit (MSU)
to the OFF position.
SUBTASK 860-002
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-3:
1) 6C14
MASTER CAUTION ANNUNCIATOR CONT 4
2) 6D11
INDICATOR MASTER DIM DIM/TST CONT
SUBTASK 020-001
Do these steps to remove the IRS MCU module assy [1]:
(a) Release the quarter-turn fasteners [2] on the front of the IRS
MCU module assy [1].
CAUTION:
_______
(b)
DO NOT TOUCH THE IRS MCU module assy [1] BEFORE YOU DO THE
PROCEDURE FOR DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC
DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
IRS MCU module assy [1].
Before you touch the IRS MCU module assy [1], do this task:
ESDS Handling for Printed Circuit Board Removal
(AMM TASK 20-40-12-000-801 p201).
EFFECTIVITY
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CAUTION:
_______
(c)
(d)
(e)
CAREFULLY REMOVE THE IRS MCU module assy [1] FROM THE
PANEL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE ELECTRICAL
CONNECTORS AT THE REAR OF THE IRS MCU module assy [1].
Carefully pull the IRS MCU module assy [1] away from the panel
until you can get access to the electrical connectors.
Disconnect the electrical connectors from the rear of the IRS
MCU module assy [1].
Install dust caps on the electrical connectors. To install
them, do this task: Conductive Dust Cap and Connector Cover
Installation (AMM TASK 20-40-12-000-803 p201)
TASK 34-21-07-400-801
3.
____________________________________
IRS
Master Caution Unit Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the IRS MCU module assy
[1].
(2) The installation test makes sure the IRS MCU module assy [1] is
installed correctly.
B. References
(1) AMM TASK 20-40-12-400-801 p201, ESDS Handling for Printed Circuit
Board Installation
(2) AMM TASK 20-40-12-400-803 p201, Conductive Dust Cap and Conductor
Cover Removal
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(5) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
C. Access
(1) Location Zones
(a) 212 Flight Compartment - Right
D. Installation Procedure
(1)
SUBTASK 860-003
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-3:
1) 6C14
MASTER CAUTION ANNUNCIATOR CONT 4
2) 6D11
INDICATOR MASTER DIM DIM/TST CONT
EFFECTIVITY
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MAINTENANCE MANUAL
P61 PANEL
SEE
A
FWD
FLIGHT COMPARTMENT
[1] MASTER CAUTION UNIT
[2] QUARTER-TURN FASTENER
(4 LOCATIONS)
[1] MASTER CAUTION UNIT
[2] QUARTER-TURN FASTENER
(4 LOCATIONS)
P61 PANEL
A
1
P61 PANEL
A
2
1
AIRPLANES WITH ONE SWITCH ON THE DATA LOADER CONTROL PANEL
2
AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL
Master Caution Unit Installation
Figure 401
K76628
34-21-07-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
(2)
SUBTASK 420-001
Do these steps to install the IRS MCU module assy [1]:
CAUTION:
_______
(a)
(b)
(c)
Before you touch the IRS MCU module assy [1], do this task:
ESDS Handling for Printed Circuit Board Installation
(AMM TASK 20-40-12-400-801 p201).
Remove the dust caps on the electrical connectors. To remove
them, do this task: Conductive Dust Cap and Conductor Cover
Removal (AMM TASK 20-40-12-400-803 p201).
Connect the electrical connectors to the IRS MCU module assy
[1].
CAUTION:
_______
(d)
(e)
DO NOT TOUCH THE IRS MCU module assy [1] BEFORE YOU DO THE
PROCEDURE FOR DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC
DISCHARGE. ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
IRS MCU module assy [1].
CAREFULLY INSTALL THE IRS MCU module assy [1] INTO THE
PANEL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE ELECTRICAL
CONNECTORS AT THE REAR OF THE IRS MCU module assy [1].
Carefully install the IRS MCU module assy [1] into the P61
panel.
Lock the quarter-turn fasteners [2] on the front of the IRS MCU
module assy [1].
SUBTASK 860-004
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-3:
1) 6C14
MASTER CAUTION ANNUNCIATOR CONT 4
2) 6D11
INDICATOR MASTER DIM DIM/TST CONT
Installation Test
(3)
E.
(1)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-006
Do this task: Air Data Inertial Reference System - Operational Test
(AMM TASK 34-21-00-710-801 p501).
Put the Airplane Back to Its Usual Condition
(2)
F.
(1)
SUBTASK 860-007
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
34-21-07
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MAINTENANCE MANUAL
RADIO MAGNETIC INDICATOR - REMOVAL/INSTALLATION
_______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the radio magnetic indicator (RMI)
(2) An installation of the RMI.
B. The RMI is located on the main display panel, P2-1, in the flight
compartment.
TASK 34-22-01-000-801
2.
______________________________________
Radio
Magnetic Indicator (RMI) Removal (Fig. 401)
A. General
(1) This procedure gives instructions to remove the RMI [1].
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18A5
RADIO NAVIGATION RMI
SUBTASK 020-001
Do these steps to remove the RMI [1]:
(a) Loosen the top right adjustment screw [2] and the bottom left
adjustment screw [2].
NOTE:
____
(b)
Push on the top right adjustment screw [2] and the bottom left
adjustment screw [2] to loosen the clamp.
CAUTION:
_______
(c)
CAREFULLY REMOVE THE RMI [1] FROM THE INSTRUMENT PANEL.
TOO MUCH FORCE CAN CAUSE DAMAGE TO THE ELECTRICAL CABLE AT
THE REAR OF THE RMI [1].
Carefully pull the RMI [1] away from the instrument panel until
you can get access to the electrical connector [4].
CAUTION:
_______
(d)
(e)
Do not loosen the top left screw [3] or the bottom right
screw [3]. These screws hold the clamp behind the
instrument panel.
DO NOT TOUCH THE CONNECTOR PINS ON THE RMI [1]. IF YOU
TOUCH THESE PINS, ELECTROSTATIC DISCHARGE FROM YOUR BODY
CAN CAUSE DAMAGE TO THE RMI [1].
Disconnect the electrical connector [4] from the RMI [1].
Install protective covers on the electrical connectors [4].
EFFECTIVITY
34-22-01
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MAINTENANCE MANUAL
SEE
A
FLIGHT COMPARTMENT
[3] SCREWS
(NOT FOR
ADJUSTMENT)
[2] ADJUSTMENT
SCREWS
[1] RADIO
MAGNETIC
INDICATOR
[4] ELECTRICAL
CONNECTOR
A
Radio Magnetic Indicator Installation
Figure 401
G79874
34-22-01-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
(f)
Remove the RMI [1].
TASK 34-22-01-400-801
3.
ú
ú
___________________________________________
Radio
Magnetic Indicator (RMI) Installation (Fig. 401)
A. General
(1) This procedure gives instructions to install the RMI [1].
(2) The installation test makes sure the RMI [1] is installed correctly.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(4) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Indicator
¦ 34-22-07
01
50 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
E. Installation Procedure
(1)
(2)
(3)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-1:
1) 18A5
RADIO NAVIGATION RMI
SUBTASK 420-001
Do these steps to install the RMI [1]:
(a) Remove the protective covers from the electrical connectors
[4].
(b) Connect the electrical connector [4] to the rear of the RMI
[1].
(c) Carefully install the RMI [1] into the clamp at the rear of the
instrument panel.
(d) Tighten the top right adjustment screw [2] and the bottom left
adjustment screw [2] on the RMI [1].
SUBTASK 860-003
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A5
RADIO NAVIGATION RMI
EFFECTIVITY
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MAINTENANCE MANUAL
F.
Installation Test
(1)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 750-001
Do this task: Air Data Inertial Reference System - Alignment from
the FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from
the ISDU (AMM TASK 34-21-00-820-802 p201).
(a) Make sure the heading flag does not show on the RMI [1].
(b) Make sure the panel lights on the RMI [1] come on.
Put the Airplane Back to Its Usual Condition
(2)
G.
(1)
(2)
SUBTASK 860-005
Set the two mode select switches on the IRS MSU to the OFF position.
SUBTASK 860-006
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
34-22-01
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MAINTENANCE MANUAL
STANDBY MAGNETIC COMPASS - MAINTENANCE PRACTICES
________________________________________________
1.
General
_______
A. This procedure has two tasks:
(1) Each task is a different procedure that you can use to do a compass
swing of the standby magnetic compass. One procedure is to use a
standby compass calibrator (Calibrator Procedure). The other
procedure is to tow the airplane around a compass rose (Tow Around
Procedure). Use only one of these procedures to do a swing of the
standby compass.
NOTE:
____
Air bubbles can occur in the standby magnetic compass because
of temperature change and/or decrease of liquid. Maintenance
limits made for liquid quantity make sure of satisfactory
compass operation. When air bubble is larger than 3/8 inch
(9.5 mm) wide and 1/8 inch (3.2 mm) high, with the glass
approximately vertical position, replace the standby compass.
(a)
B.
C.
D.
Each task has two parts. The first part is to do a swing of
the standby compass through four compass points (north, east,
south, west). Use this procedure for compass calibration. The
second part is to do a swing the standby compass through 12
compass points that are approximately 30 degrees apart. Use
this procedure to measure the remaining errors and to make sure
the standby compass heading is accurate. Use this data to make
the compass correction card. This card must stay with the
standby compass.
It is not necessary to keep a constant radius or tangency during airplane
tow around the compass rose or swing area. Tow direction is optional.
These make no difference when you calculate the solutions.
Do not park vehicles less than 220 feet (67.1 meters) from the airplane
during the compass swing.
You can use the auxiliary power unit (APU) during the compass swing.
TASK 34-23-00-820-801
2.
_____________________________________________
Standby
Magnetic Compass Calibrator Procedure (Fig. 201)
A. General
(1) Use tools that are not magnetic to adjust the standby magnetic
compass.
B. References
(1) AMM TASK 09-11-00-580-801 p201, Towing
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(4) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(5) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
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C.
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D.
E.
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Equipment
(1) 2591553-901 Kit - Calibration, Standby Compass
Honeywell, Inc. (Vendor Code 94580)
2600 Ridgway Parkway, Minneapolis MN 55413-1719
(2) Tripod - Non-magnetic
(commercially available)
Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
Calibrator Adjustment
(1)
SUBTASK 820-001
Do this procedure to calibrate the standby compass calibrator (SCC)
(kit, 2591553-901) to the magnetic field at the location of the
compass swing area:
(a) Make sure there are no vehicles or airplanes less than 220 feet
(67.1 meters) away.
(b) Make sure there are no buildings less than 220 feet (67.1
meters) away.
(c) Put a tripod at the center of the compass swing area.
(d) Remove the magnet assembly from the SCC.
(e) Remove the knob assembly from the SCC.
(f) Attach a master magnetic compass to the SCC with two mounting
screws.
NOTE:
____
(g)
Put the SCC/master compass assembly on the tripod.
NOTE:
____
(h)
(i)
(j)
(k)
(l)
(m)
(n)
(o)
You can use an accurate standby magnetic compass for a
master magnetic compass. Make sure that the N-S and E-W
adjustment screws are at neutral.
Make sure the assembly is level.
Turn the assembly until the master magnetic compass shows an
indication of magnetic north (N).
Re-install the magnet assembly to the SCC.
Re-install the knob assembly to the SCC.
Turn the top and bottom SCC dials to show an indication of E at
the index line.
Make a record of the heading shown on the master magnetic
compass.
Turn the top and bottom SCC dials to show an indication of W at
the index line.
Make a record of the heading shown on the master magnetic
compass.
Turn the magnetic field cancellation adjustment screw on the
SCC to decrease the heading errors in each direction (E and W)
to a minimum.
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MOUNTING
BRACKET
MAGNET
ASSEMBLY
KNOB ASSEMBLY
TOP AND BOTTOM
DIAL ASSEMBLY
MAGNETIC FIELD
CANCELLATION
ADJUSTMENT SCREW
Standby Compass Calibrator
Figure 201
H48272
34-23-00-990-801
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(p)
Continue to adjust the SCC dials for each direction (E and W).
Then use the magnetic field cancellation adjustment (MFCA)
screw until the errors are at a minimum.
NOTE:
____
F.
Continue to do this procedure until the error in each
direction is at a minimum. When the errors are at a
minimum, do not move the MFCA screw until the compass
swing is completed.
Four Point Calibration Swing Procedure
(1)
SUBTASK 580-001
To tow the airplane to the compass swing area, do this task:
(AMM TASK 09-11-00-580-801 p201).
NOTE:
____
Towing
The compass swing area must be a level area with a smooth
surface. It must be sufficiently strong to hold the weight
of the airplane. The area must be large enough to tow or
taxi the airplane. Make sure no vehicles other than the tow
vehicle are less than 220 feet (67.1 meters) from the
airplane. The horizontal component of the earth's magnetic
field must be constant (|1 degree) in the test area. Measure
the direction of the horizontal component if magnetic
material (such as a new building) is less than 600 (182.9
meters) feet from the compass rose. Do not use the compass
rose if the horizontal component is not constant (|1 degree).
(2)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(3)
SUBTASK 860-002
Energize all of the electronic equipment, radios, and flight
compartment lights for the usual conditions that occur in flight.
(4)
SUBTASK 820-002
Do this task: Air
the
Air
the
Data Inertial Reference System - Alignment from
FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Data Inertial Reference System - Alignment from
ISDU (AMM TASK 34-21-00-820-802 p201).
(5)
SUBTASK 860-003
Set the ND mode selector on the left EFIS control panel on the
glareshield to the VOR/ILS position.
(6)
SUBTASK 860-004
Set the heading reference switch below the captain's ND to the NORM
position.
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(7)
SUBTASK 750-001
Make sure that the captain's ND shows a magnetic heading.
SUBTASK 860-005
CAUTION:
_______
(8)
(9)
USE TOOLS THAT ARE NOT MAGNETIC.
COMPASS ADJUSTMENT ERRORS.
MAGNETIC TOOLS CAN CAUSE
Make sure the N-S and E-W adjustment screws on the standby compass
are at neutral.
SUBTASK 580-002
Turn the airplane to a direction where the captain's ND shows a
magnetic heading of 0 degrees.
SUBTASK 020-001
(10) Remove the lower left and upper right mounting screws on the standby
magnetic compass.
SUBTASK 480-001
(11) Use the two mounting screws to install the SCC on the face of the
standby magnetic compass.
SUBTASK 820-003
(12) Turn the top and bottom SCC dials to show an indication of E at the
index line.
SUBTASK 970-001
(13) Make a record of the heading shown on the standby magnetic compass.
SUBTASK 820-004
(14) Turn the top and bottom SCC dials to show an indication of W at the
index line.
SUBTASK 970-002
(15) Make a record of the heading shown on the standby magnetic compass.
SUBTASK 820-005
(16) Turn the E-W adjustment screw on the standby magnetic compass until
the error in the last two recorded values is at a minimum.
NOTE:
____
Divide the error in each of the two directions as equally as
possible.
SUBTASK 820-006
(17) Turn the top and bottom SCC dials to show an indication of N at the
index line.
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SUBTASK 970-003
(18) Make a record of the heading shown on the standby magnetic compass.
SUBTASK 820-007
(19) Turn the top and bottom SCC dials to show an indication of S at the
index line.
SUBTASK 970-004
(20) Make a record of the heading shown on the standby magnetic compass.
SUBTASK 820-008
(21) Turn the N-S adjustment screw on the standby magnetic compass until
the error in the last two recorded values is at a minimum.
NOTE:
____
Divide the error in each of the two directions as equally as
possible.
SUBTASK 820-009
(22) Continue to adjust the SCC dials for each pair of directions (E-W,
N-S). Then, turn the E-W and N-S adjustment screws until the errors
are at a minimum.
NOTE:
____
G.
Continue to do this procedure until the error in each pair of
directions is at a minimum. Start with E-W and turn the E-W
adjustment screw. Then, do N-S and turn the N-S adjustment
screw.
SUBTASK 820-010
(23) When the errors are at a minimum, do the steps that follow for the
12-point accuracy swing.
Twelve Point Accuracy Swing Procedure
(1)
SUBTASK 580-003
Move the airplane to a location near the center of the compass swing
area.
NOTE:
____
For each of the magnetic headings that follow, the remaining
deviation for the standby magnetic compass must not be more
than |5 degrees.
(2)
SUBTASK 820-011
Adjust the SCC dials to indicate these magnetic headings: 0, 30,
60, 90, 120, 150, 180, 210, 240, 270, 300, and 330 degrees.
(3)
SUBTASK 970-005
Make a record of the magnetic heading, MH, and the standby compass
heading, CH, for each 30 degree increment.
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SUBTASK 970-006
Make a record of the standby compass heading, CH, in the steer
column of the compass correction card for each 30 degree heading
increment.
Put the Airplane Back to Its Usual Condition
(4)
H.
(1)
SUBTASK 860-006
Set the mode select switches on the inertial reference sytem (IRS)
mode select unit (MSU) to the OFF position.
(2)
SUBTASK 860-007
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-23-00-820-802
3.
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_____________________________________________
Standby
Magnetic Compass Tow Around Procedure
A. General
(1) Use tools that are not magnetic to adjust the standby magnetic
compass.
B. References
(1) AMM TASK 09-11-00-580-801 p201, Towing
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(4) AMM TASK 32-09-00-840-801 p201, Prepare to Put the Airplane in the
Air Mode
(5) AMM TASK 32-09-00-840-802 p201, Return the Airplane Systems Back to
Their Normal On Ground Condition
(6) AMM TASK 32-09-00-860-801 p201, Put the Airplane in the Air Mode
(7) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(8) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
EFFECTIVITY
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D.
Four Point Calibration Swing Procedure
(1)
SUBTASK 580-004
To tow the airplane to the compass swing area, do this task:
(AMM TASK 09-11-00-580-801 p201).
NOTE:
____
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Towing
The compass swing area must be a level area with a smooth
surface. It must be sufficiently strong to hold the weight
of the airplane. The area must be large enough to tow or
taxi the airplane. Make sure no vehicles other than the tow
vehicle are less than 220 feet (67.1 meters) from the
airplane. The horizontal component of the earth's magnetic
field must be constant (|1 degree) in the test area. Measure
the direction of the horizontal component if magnetic
material (such as a new building) is less than 600 feet
(182.9 meters) from the compass rose. Do not use the compass
rose if the horizontal component is not constant (|1 degree).
(2)
SUBTASK 860-008
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(3)
SUBTASK 860-009
Energize all of the electronic equipment, radios, and flight
compartment lights for the usual conditions that occur in flight.
(4)
SUBTASK 820-015
Do this task: Air
the
Air
the
Data Inertial Reference System - Alignment from
FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Data Inertial Reference System - Alignment from
ISDU (AMM TASK 34-21-00-820-802 p201).
SUBTASK 840-001
WARNING:
_______
(5)
PREPARE THE SAFETY-SENSITIVE SYSTEMS FOR THE AIR MODE BEFORE
YOU INSTALL THE DEACTUATORS. IN THE AIR MODE, MANY OF THE
AIRPLANE SYSTEMS CAN OPERATE. THIS CAN CAUSE INJURIES TO
PERSONS AND DAMAGE TO EQUIPMENT.
Do this task:
Prepare to Put the Airplane in the Air Mode
(AMM TASK 32-09-00-840-801 p201).
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ú
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(6)
SUBTASK 860-015
Attach deactuators to the face of the air/ground sensors for the
nose and main landing gear. To attach the deactuators, do this
task: Put the Airplane in the Air Mode
(AMM TASK 32-09-00-860-801 p201).
NOTE:
____
(a)
The installation of the deactuators will energize the landing
gear latch solenoid. Because the landing gear latch solenoid
is close to the standby magnetic compass, the solenoid must
be energized to create a normal level of magnetic and
electrical interference during calibration of the compass.
Let the landing gear latch solenoid stay energized for 20
minutes before you continue.
(7)
SUBTASK 860-010
Set the ND mode selector on the left EFIS control panel on the
glareshield to the VOR/ILS position.
(8)
SUBTASK 860-011
Set the heading reference switch below the captain's ND to the NORM
position.
(9)
SUBTASK 750-002
Make sure that the captain's ND shows a magnetic heading.
SUBTASK 860-012
CAUTION:
_______
USE TOOLS THAT ARE NOT MAGNETIC.
COMPASS ADJUSTMENT ERRORS.
MAGNETIC TOOLS CAN CAUSE
(10) Make sure that the N-S and E-W adjustment screws on the standby
compass are at neutral.
SUBTASK 580-005
(11) Turn the airplane to a direction where the captain's ND shows a
heading (|2 degrees) of magnetic north, (MH)n.
SUBTASK 970-007
(12) Make a record of the magnetic heading, (MH)n, and the standby
compass heading, (CH)n.
SUBTASK 970-008
(13) Calculate and make a record of the north heading deviation, Dn, as
follows: Dn = (MH)n - (CH)n
SUBTASK 580-006
(14) Turn the airplane to a direction where the captain's ND shows a
heading (|2 degrees) of magnetic east, (MH)e.
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SUBTASK 970-009
(15) Make a record of the magnetic heading, (MH)e, and the standby
compass heading, (CH)e.
SUBTASK 970-010
(16) Calculate and make a record of the east heading deviation, De, as
follows: De = (MH)e - (CH)e
SUBTASK 580-007
(17) Turn the airplane to a direction where the captain's ND shows a
heading (|2 degrees) of magnetic south, (MH)s.
SUBTASK 970-011
(18) Make a record of the magnetic heading, (MH)s, and the standby
compass heading, (CH)s.
SUBTASK 970-012
(19) Calculate and make a record of the south heading deviation, Ds, as
follows: Ds = (MH)s - (CH)s
SUBTASK 970-013
(20) Calculate and make a record of the north-south single-cycle error
coefficient, C, and its sign as follows: C = 0.5(Dn - Ds)
SUBTASK 820-013
(21) Turn the N-S adjustment screw on the standby compass (while at the
south magnetic heading) to give a compass heading indication of
(CH)s - C.
SUBTASK 580-008
(22) Turn the airplane to a direction where the captain's ND shows a
heading (|2 degrees) of magnetic west, (MH)w.
SUBTASK 970-014
(23) Make a record of the magnetic heading, (MH)w, and the standby
compass heading, (CH)w.
SUBTASK 970-015
(24) Calculate and make a record of the west heading deviation, Dw, as
follows: Dw = (MH)w - (CH)w
SUBTASK 970-016
(25) Calculate and make a record of the east-west single-cycle error
coefficient, B, and its sign as follows: B = 0.5(De - Dw)
SUBTASK 820-014
(26) Turn the E-W adjustment screw on the standby compass (while at the
west magnetic heading) to give a compass heading indication of
(CH)w - B.
EFFECTIVITY
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E.
Twelve Point Correction Swing Procedure
(1)
SUBTASK 580-009
Move the airplane to a location near the center of the compass swing
area.
NOTE:
____
For each of the magnetic headings that follow, the remaining
deviation for the standby magnetic compass must not be more
than |8 degrees for FAA certification. For CAA
certification, the remaining deviation must not be more than
|5 degrees.
(2)
SUBTASK 580-010
Turn the airplane to each of these ND magnetic headings:
90, 120, 150, 180, 210, 240, 270, 300, and 330 degrees.
(3)
SUBTASK 970-017
Make a record of the magnetic heading, MH, and the standby compass
heading, CH, for each 30 degree increment.
0, 30, 60,
SUBTASK 970-018
Calculate and make a record of the deviation, D, for each 30 degree
heading in the steer column of the compass correction card as
follows: D = MH - CH
Put the Airplane Back to Its Usual Condition
(4)
F.
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(1)
SUBTASK 860-016
Remove the deactuators from the nose and main landing gear.
(2)
SUBTASK 840-002
Do this task: Return the Airplane Systems Back to Their Normal On
Ground Condition (AMM TASK 32-09-00-840-802 p201).
(3)
SUBTASK 860-013
Set the mode select switches on the inertial reference system (IRS)
mode select unit (MSU) to the OFF position.
(4)
SUBTASK 860-014
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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STANDBY MAGNETIC COMPASS - REMOVAL/INSTALLATION
_______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the standby magnetic compass
(2) An installation of the standby magnetic compass.
B. The standby magnetic compass is installed below the center of the forward
overhead panel, P5, in the flight compartment.
TASK 34-23-01-000-801
2.
________________________________
Standby
Magnetic Compass Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
B. Removal Procedure
(1)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-3:
1) 6A14
CONTROL CABIN LIGHTING STBY COMPASS
SUBTASK 020-001
CAUTION:
_______
(2)
USE ONLY TOOLS THAT ARE NOT MAGNETIC FOR THE REMOVAL AND THE
INSTALLATION OF THE STANDBY MAGNETIC COMPASS [1]. MAGNETIC
TOOLS CAN CAUSE DAMAGE TO THE INSTRUMENT.
Remove the standby magnetic compass [1]:
(a) Disconnect the electrical connector [3].
(b) Remove the four brass screws [2] that hold the standby magnetic
compass [1] to the mounting bracket.
(c) Remove the standby magnetic compass [1].
(d) Put protective covers on the electrical connector [3] and the
connector on the back of the standby magnetic compass [1].
TASK 34-23-01-400-801
3.
_____________________________________
Standby
Magnetic Compass Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-23-00-820-801 p201, Standby Magnetic Compass Calibrator
Procedure
(4) AMM TASK 34-23-00-820-802 p201, Standby Magnetic Compass Tow Around
Procedure
B. Parts
EFFECTIVITY
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SEE
A
FLIGHT COMPARTMENT
[1] STANDBY
MAGNETIC
COMPASS
[2] SCREW
(4 LOCATIONS)
FWD
[3] ELECTRICAL
CONNECTOR
STANDBY MAGNETIC COMPASS
A
Standby Magnetic Compass Installation
Figure 401
F73159
34-23-01-990-801
EFFECTIVITY
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~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Compass
¦ 34-24-11
01
15 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
D. Installation Procedure
(1)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-3:
1) 6A14
CONTROL CABIN LIGHTING STBY COMPASS
SUBTASK 420-001
CAUTION:
_______
(2)
USE ONLY TOOLS THAT ARE NOT MAGNETIC FOR THE REMOVAL AND THE
INSTALLATION OF THE STANDBY MAGNETIC COMPASS [1]. MAGNETIC
TOOLS CAN CAUSE DAMAGE TO THE INSTRUMENT.
Install the standby magnetic compass [1]:
(a) Remove the protective covers from the electrical connector [3]
and the connector on the back of the standby magnetic compass
[1].
(b) Examine the electrical connector [3] for bent or broken pins,
dirt, and damage.
(c) Connect the electrical connector [3].
(d) Install the standby magnetic compass [1] onto the mounting
bracket.
(e) Install the four brass screws [2] at the corners of the standby
magnetic compass [1].
SUBTASK 860-003
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-3:
1) 6A14
CONTROL CABIN LIGHTING STBY COMPASS
Installation Test
(3)
E.
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 750-001
Make sure the light for the standby magnetic compass [1] is on.
EFFECTIVITY
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(3)
(4)
SUBTASK 820-001
Do this task: Standby Magnetic Compass Calibrator Procedure
(AMM TASK 34-23-00-820-801 p201) or
Standby Magnetic Compass Tow Around Procedure
(AMM TASK 34-23-00-820-802 p201).
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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STANDBY ATTITUDE REFERENCE SYSTEM - ADJUSTMENT/TEST
___________________________________________________
1.
General
_______
A. This procedure has this task:
(1) A system test of the standby attitude reference system.
TASK 34-24-00-730-801
2.
_______________________________________________
Standby
Attitude Reference System - System Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
C. Procedure
(1)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-003
Set the mode selector switch on the standby attitude indicator to
the OFF position.
(3)
SUBTASK 860-004
Let the gyro get to full speed.
NOTE:
____
ú
(4)
SUBTASK 860-006
Pull and release the cage knob on the stanby indicator.
NOTE:
____
(5)
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(6)
(7)
The gyro will reach full speed approximately 3 minutes after
you supply power.
Do not let the knob hit against the front of the indicator.
SUBTASK 750-001
After five minutes, make sure the pitch and roll indications show
the airplane attitude 0 |2.0 degrees.
SUBTASK 860-007
Open this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18D9
STBY ATT IND
SUBTASK 750-002
Make sure the GYRO flag comes into view in less than one second.
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(8)
(9)
ú
SUBTASK 860-008
Close this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18D9
STBY ATT IND
SUBTASK 750-004
Make sure the GYRO flag goes out of view within 3 minutes.
SUBTASK 860-009
(10) Tune the captain's VHF NAV receiver to the frequency of 108.35 MHz.
NOTE:
____
ú
To set the frequency, turn the frequency selector until the
selected frequency shows in the STANDBY display window.
Then, push the TFR switch. The frequency will show in the
ACTIVE display window. The frequency of 108.35 MHz is the
test frequency for the ILS.
SUBTASK 860-010
(11) Set the mode selector switch on the standby attitude indicator to
the APP position.
ú
ú
ú
ú
ú
ú
ú
SUBTASK 740-001
(12) Push the TEST switch on the captain's VHF NAV control panel.
(a) Make sure that the G/S and LOC flags come into view and then go
out of view in less than five seconds.
(b) Make sure the localizer deviation bar moves one mark left and
the glide slope deviation bar moves one mark up.
(c) Make sure the localizer deviation bar moves one mark right and
the glide slope deviation bar moves one mark down.
SUBTASK 860-011
(13) Set the mode selector switch on the standby attitude indicator to
the B/CRS position.
ú
ú
ú
ú
SUBTASK 740-003
(14) Push the TEST switch on the captain's VHF NAV control panel.
(a) Make sure the LOC flag comes into view and then goes out of
view in less than five seconds.
(b) Make sure the glide slope deviation bar and the G/S flag are
out of view.
(c) Make sure the localizer deviation bar moves to the right side
of the center and then to the left side of the center.
SUBTASK 860-012
(15) Set the mode selector switch on the standby attitude indicator to
the OFF position.
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SUBTASK 860-013
(16) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
ú
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ú
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MAINTENANCE MANUAL
STANDBY ATTITUDE INDICATOR - REMOVAL/INSTALLATION
_________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the standby attitude indicator
(2) An installation of the standby attitude indicator.
B. The standby attitude indicator is installed on the center instrument
panel, P2, in the flight compartment.
TASK 34-24-01-000-801
2.
__________________________________
Standby
Attitude Indicator Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
B. Removal Procedure
(1)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-2:
1) 18D9
STBY ATT IND
SUBTASK 000-001
CAUTION:
_______
LET THE GYRO STOP AFTER YOU REMOVE THE ELECTRICAL POWER.
REMOVAL OF THE STANDBY ATTITUDE INDICATOR [1] BEFORE THE GYRO
STOPS CAN CAUSE DAMAGE TO THE GYRO.
(2)
After 9 minutes, when the gyro is stopped, continue.
(3)
SUBTASK 020-001
Remove the standby attitude indicator [1]:
CAUTION:
_______
(a)
(b)
INSTALL A DEVICE TO LOCK THE KNOB IN A CAGED POSITION.
THIS CAN PREVENT DAMAGE TO THE GYRO WHEN THE INDICATOR IS
MOVED.
Pull the cage knob and install a device to lock it in a caged
position.
Loosen the two adjustment screws [2] at the top right corner
and the bottom left corner of the indicator [1].
NOTE:
____
Do not remove the adjustment screws [2]. Loosen the
adjustment screws [2] until the indicator [1] can be
removed. If the indicator [1] is not easy to remove,
loosen the other two screws that attach the clamp to the
forward panel. This will permit easier removal of the
indicator [1].
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SEE
A
FLIGHT COMPARTMENT
[1] STANDBY
ATTITUDE
INDICATOR
[2] ADJUSTMENT
SCREWS
[3] ELECTRICAL
CONNECTOR
A
Standby Attitude Indicator Installation
Figure 401
F72415
34-24-01-990-801
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(c)
(d)
(e)
(f)
Pull the indicator [1] out of the instrument panel until you
can get access to the electrical connector [3].
Disconnect the electrical connector [3] from the indicator [1].
Remove the indicator [1].
Put protective covers on the electrical connector [3] and the
connector on the back of the indicator [1].
TASK 34-24-01-400-801
3.
ú
_______________________________________
Standby
Attitude Indicator Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-24-00-730-801 p501, Standby Attitude Reference System System Test
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Indicator
¦ 34-24-01
01
50 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
D. Installation Procedure
(1)
(2)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-2:
1) 18D9
STBY ATT IND
SUBTASK 420-001
Install the standby attitude indicator [1]:
(a) Remove the protective covers from the electrical connector [3]
and the connector on the back of the standby attitude indicator
[1].
(b) Examine the electrical connector [3] for bent or broken pins,
dirt and damage.
(c) Connect the electrical connector [3] to the indicator [1].
(d) Install the indicator [1] into the instrument panel.
(e) Tighten the two adjustment screws [2] at the top right corner
and the bottom left corner of the indicator [1].
1) Tighten the adjustment screws [2] to a maximum of 30
inch-pounds (3.4 newton-meters).
2) Remove the device that locks the cage knob in a caged
position.
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SUBTASK 860-003
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18D9
STBY ATT IND
Installation Test
(3)
E.
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 750-001
Make sure the panel lights for the indicator [1] are on.
(3)
SUBTASK 730-001
Do this task: Standby Attitude Reference System - System Test
(AMM TASK 34-24-00-730-801 p501).
(4)
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
INSTRUMENT LANDING SYSTEM - ADJUSTMENT/TEST
___________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the instrument landing system.
(2) A system test of the instrument landing system.
TASK 34-31-00-710-801
2.
____________________________________________
Instrument
Landing System - Operational Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Prepare for the Test
(1)
(2)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-001
Do these steps to prepare for the operational test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the APP position.
(d) Set the approach mode selector switch on the standby attitude
indicator to the APP position.
(e) Set the captain's and the first officer's course select
controls on the DFCS mode control panel to the same course as
the airplane heading.
(f) Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
EFFECTIVITY
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D.
Power and Tuning Test
(1)
SUBTASK 860-002
Set a frequency of 108.1 MHz on the captain's and the first
officer's navigation control panels.
NOTE:
____
(2)
(3)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
SUBTASK 860-003
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
SUBTASK 710-002
Push and release the TEST button on the captain's navigation control
panel.
(a) Make sure that these indications show on the captain's display:
NOTE:
____
1)
2)
3)
(4)
(5)
It takes approximately 16 seconds for the test sequence
to complete.
The LOC and G/S flags show momentarily
The glideslope deviation pointer shows one dot up and the
localizer deviation bar shows one dot left.
The glideslope deviation pointer shows one dot down and the
localizer deviation bar shows one dot right.
SUBTASK 860-004
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
SUBTASK 860-005
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
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(6)
SUBTASK 710-003
Push and release the TEST button on the first officer's navigation
control panel.
(a) Make sure that these indications show on the first officer's
display:
NOTE:
____
1)
2)
3)
It takes approximately 16 seconds for the test sequence
to complete.
The LOC and G/S flags show momentarily
The glideslope deviation pointer shows one dot up and the
localizer deviation bar shows one dot left.
The glideslope deviation pointer shows one dot down and the
localizer deviation bar shows one dot right.
SUBTASK 860-006
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
Data Out, Source Select, and ILS Tuned Discrete Test
(7)
E.
(1)
SUBTASK 710-004
Push and release the TEST button on the captain's navigation control
panel.
(a) Make sure that these indications show on the standby attitude
indicator:
NOTE:
____
1)
2)
3)
4)
(2)
(3)
It takes approximately 16 seconds for the test sequence
to complete.
The LOC and G/S flags show momentarily
The glideslope deviation bar shows one dot up and the
localizer deviation bar shows one dot left.
The glideslope deviation bar shows one dot down and the
localizer deviation bar shows one dot right.
The LOC and G/S flags do not show at the end of the test.
SUBTASK 710-005
Set the VHF NAV switch on the instrument switching module to the
BOTH ON 1 position.
(a) Make sure the message EFIS MODE/NAV FREQ DISAGREE does not show
on the captain's and the first officer's displays.
SUBTASK 710-006
Set a frequency of 108.0 MHz on the captain's navigation control
panel.
(a) Make sure the message EFIS MODE/NAV FREQ DISAGREE shows on the
captain's and the first officer's displays.
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(4)
(5)
SUBTASK 710-007
Set the VHF NAV switch on the instrument switching module to the
BOTH ON 2 position.
(a) Make sure the message EFIS MODE/NAV FREQ DISAGREE does not show
on the captain's and the first officer's displays.
SUBTASK 710-008
Set a frequency of 108.0 MHz on the first officer's navigation
control panels.
(a) Make sure the message EFIS MODE/NAV FREQ DISAGREE shows on the
captain's and the first officer's displays.
(6)
SUBTASK 860-007
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
(7)
SUBTASK 860-008
Set the SOURCE switch on the instrument switching module to the ALL
ON 1 position.
(8)
SUBTASK 860-009
Set a frequency of 108.1 MHz on the captain's navigation control
panel.
(9)
SUBTASK 710-009
Set a frequency of 109.75 MHz on the first officer's navigation
control panel.
(a) Make sure 108.1 MHz shows on the captain's display.
(b) Make sure 109.75 MHz shows on the first officer's display.
SUBTASK 710-010
(10) Set the SOURCE switch on the instrument switching module to the ALL
ON 2 position.
(a) Make sure 108.1 MHz shows on the captain's display.
(b) Make sure 109.75 MHz shows on the first officer's display.
SUBTASK 860-010
(11) Set the SOURCE switch on the instrument switching module to the AUTO
position.
TASK 34-31-00-730-801
3.
_______________________________________
Instrument
Landing System - System Test
A. References
(1) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(2) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
(3) AMM TASK 34-31-00-710-801 p501, Instrument Landing System Operational Test
EFFECTIVITY
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B.
C.
D.
Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
Prepare for the System Test
SUBTASK 710-011
Do these steps to prepare for the system test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the APP position.
(d) Set the approach mode selector switch on the standby attitude
indicator to the APP position.
(e) Set the captain's and the first officer's course select
controls on the DFCS mode control panel to the same course as
the airplane heading.
(f) Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
Operational Test
(1)
E.
SUBTASK 710-012
Do this task: Instrument Landing System - Operational Test
(AMM TASK 34-31-00-710-801 p501).
Audio Out and Audio Discrete Test
(1)
F.
(1)
SUBTASK 860-011
Set the voice range filter switch at one of the audio control panels
to the R position.
(2)
SUBTASK 860-012
Push the receiver volume control for NAV-1 on the same audio control
panel to set the volume to on.
EFFECTIVITY
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(3)
SUBTASK 860-013
Turn the receiver volume control clockwise for NAV-1 to make sure
you can hear sound through the flight interphone system.
(4)
SUBTASK 710-013
Put the test set, NAV-402AP-2, near the front of the airplane and a
minimum of 6 feet from the forward localizer antenna.
(5)
SUBTASK 730-001
Use the test set, NAV-402AP-2, to supply an ILS localizer signal
that follows to the tail (VOR) antenna:
OUTPUT LEVEL
-15 dBm
DEFLECTION
Right 1 Dot (0.0775 DDM)
FREQUENCY
108.1 MHz
IDENT TONE
ON
(a)
(6)
Make sure you can hear an ILS tone over the flight interphone
system.
SUBTASK 730-002
Set a frequency of 111.95 MHz on the captain's navigation control
panel.
(a) Make sure you cannot hear an ILS tone over the flight
interphone system.
(7)
SUBTASK 860-014
Push the receiver volume control for NAV-2 on the same audio control
panel to set the volume to on.
(8)
SUBTASK 860-015
Turn the receiver volume control clockwise for NAV-2 to make sure
you can hear sound through the flight interphone system.
SUBTASK 730-003
Set a frequency of 108.1 MHz on the first officer's navigation
control panel.
(a) Make sure you can hear an ILS tone over the flight interphone
system.
Localizer Antenna and Antenna Switch Test
(9)
G.
(1)
SUBTASK 860-016
Make sure the F/D switches on the DFCS mode control panel are in the
OFF position.
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(2)
(3)
(4)
(5)
SUBTASK 730-004
Set a frequency of 108.1 MHz on the captain's navigation control
panel.
(a) Make sure the localizer deviation bars on the captain's and the
first officer's displays show on dot right.
SUBTASK 860-017
Slowly decrease the RF level on the test set, NAV-402AP-2, until the
localizer deviation bars on the captain's and the first officer's
displays do not show.
SUBTASK 860-018
Set the F/D switches on the DFCS mode control panel to the ON
position.
SUBTASK 730-005
Push the APP switch on the DFCS mode control panel.
(a) Make sure the localizer deviation bars on the captain's and the
first officer's displays show one dot right.
SUBTASK 860-019
Set the F/D switches on the DFCS mode control panel to the OFF
position.
Glideslope Antenna Test
(6)
H.
(1)
SUBTASK 730-006
Use the test set, NAV-402AP-2, to supply an ILS glideslope signal
that follows to the nose antenna:
OUTPUT LEVEL
-15 dBm
DEFLECTION
Down 1 Dot (0.0875 DDM)
FREQUENCY
334.7 MHz
(a)
Make sure the glideslope deviation pointers on the captain's
and the first officer's displays show one dot down.
EFFECTIVITY
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ILS GLIDE SLOPE ANTENNA - REMOVAL/INSTALLATION
______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the ILS glide slope antenna
(2) An installation of the ILS glide slope antenna.
B. The ILS glideslope antenna is in the nose radome.
TASK 34-31-21-000-801
2.
_______________________________
ILS
Glide Slope Antenna Removal (Fig. 401)
A. References
(1) AMM TASK 53-52-00-000-801 p401, Nose Radome Removal
(2) AMM TASK 53-52-31-000-801 p401, Glide Slope Director Bar Removal
(3) AMM TASK 53-52-31-400-801 p401, Glide Slope Director Bar
Installation
B. Access
(1) Location Zones
(a) 111 Radome
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
C. Removal Procedure
(1)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 860-002
WARNING:
_______
(2)
DO NOT OPERATE THE WEATHER RADAR SYSTEM WHILE YOU REMOVE THE
GLIDE SLOPE ANTENNA. IF THE WEATHER RADAR OPERATES, INJURY TO
PERSONS CAN OCCUR.
Open the nose radome to get access to the ILS glide slope antenna
[1] (AMM TASK 53-52-00-000-801 p401).
EFFECTIVITY
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SEE
B
SEE
SEE
A
GLIDE SLOPE
ANTENNA
DIRECTOR BAR
C
FWD
NOSE RADOME
A
FWD
B
Glide Slope Antenna Installation
Figure 401 (Sheet 1)
F71790
34-31-21-990-801
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[3] ELECTRICAL
CONNECTORS
GLIDE SLOPE
ANTENNA
MOUNTING
BRACKET
[1] GLIDE
SLOPE
ANTENNA
[2] SCREW
(5 LOCATIONS)
FWD
C
Glide Slope Antenna Installation
Figure 401 (Sheet 2)
F71791
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(3)
SUBTASK 860-003
Make sure the antenna director bar is not damaged.
NOTE:
____
(a)
(4)
The antenna director bar is a 13-inch continuous strip of
aluminum foil tape. The strip is installed horizontally
across the centerline on the inner surface of the nose
radome.
If the antenna director bar is damaged, it must be replaced.
These are the tasks:
Glide Slope Director Bar Removal
(AMM TASK 53-52-31-000-801 p401),
Glide Slope Director Bar Installation
(AMM TASK 53-52-31-400-801 p401).
SUBTASK 020-001
Remove the ILS glide slope antenna [1].
(a) Remove the screws [2] that attach the ILS glide slope antenna
[1] to the airplane structure.
(b) Pull the ILS glide slope antenna [1] assembly away from the
airplane structure to get access to the electrical connectors
[3].
(c) Disconnect the electrical connectors [3].
(d) Put protective covers on the electrical connectors [3].
(e) Remove the ILS glide slope antenna [1].
TASK 34-31-21-400-801
3.
____________________________________
ILS
Glide Slope Antenna Installation (Fig. 401)
A. General
(1) The installation task has an installation test. The installation
test makes sure that the ILS glide slope antenna operates correctly.
B. References
(1) AMM TASK 20-10-34-110-802 p701, Clean Bare, Clad, or Plated Metal
with Solvent
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
(4) AMM TASK 51-21-41-370-802 p701, Apply Alodine 600, 1200 or 1200S
Solution
(5) AMM TASK 51-21-91-620-802 p701, Apply the Corrosion Inhibiting
Compound
(6) AMM TASK 53-52-00-000-801 p401, Nose Radome Removal
(7) AMM TASK 53-52-00-400-801 p401, Nose Radome Installation
(8) SWPM 20-20-00
EFFECTIVITY
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MAINTENANCE MANUAL
C.
Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
D. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
(2) B00083 Solvent, Aliphatic naphtha (for acrylic plastics) - TT-N-95,
Type II
(3) C00259 Primer, Chemical and solvent resistant finish, epoxy resin BMS10-11, Type I
(4) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(5) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
E. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Antenna
¦ 34-31-21
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
F. Access
(1) Location Zones
(a) 111 Radome
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
G. Installation Procedure
(1)
SUBTASK 860-004
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 860-005
WARNING:
_______
(2)
DO NOT OPERATE THE WEATHER RADAR SYSTEM WHILE YOU INSTALL THE
GLIDE SLOPE ANTENNA. IF THE WEATHER RADAR OPERATES, INJURY TO
PERSONS CAN OCCUR.
Open the nose radome to get access to the ILS glide slope antenna
[1] (AMM TASK 53-52-00-000-801 p401).
EFFECTIVITY
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MAINTENANCE MANUAL
(3)
(4)
(5)
(6)
(7)
(8)
SUBTASK 100-001
Clean the mating surfaces of the ILS glide slope antenna [1] and the
airplane structure. To clean the mating surfaces, do this task:
Clean Bare, Clad, or Plated Metal with Solvent
(AMM TASK 20-10-34-110-802 p701).
(a) Apply solvent, TT-N-95, Type II to the mating surfaces of the
ILS glide slope antenna [1] and the airplane structure with a
cloth, BMS15-5.
(b) Use a cloth, BMS15-5 and clean the mating surfaces again.
(c) Do these two steps until the mating surfaces are bright, clean
and dry.
SUBTASK 620-001
If the airplane surface has corrosion or other damage, do these
steps to prepare the airplane mating surface:
(a) Apply a layer of coating, Alodine 600 to the airplane mating
surface. To apply the coating, do this task: Apply Alodine
600, 1200 or 1200S Solution (AMM TASK 51-21-41-370-802 p701).
(b) Apply a layer of primer, BMS10-11, Type I, to the screw holes.
(c) Allow the primer, BMS10-11, Type I, to dry before you install
the screws [2].
SUBTASK 860-006
Apply a layer of compound, BMS3-23, to the airplane and antenna
mating surfaces. To apply the compound, do this task: Apply the
Corrosion Inhibiting Compound (AMM TASK 51-21-91-620-802 p701).
SUBTASK 420-001
Install the ILS glide slope antenna [1]:
(a) Remove the protective covers from the electrical connectors
[3].
(b) Apply sealant, BMS5-95 to the threads of the screws [2].
(c) Connect the electrical connectors [3] to the ILS glide slope
antenna [1].
(d) Align the ILS glide slope antenna [1] to the screw holes that
hold the ILS glide slope antenna [1] to the airplane structure.
(e) Install the screws [2] that attach the ILS glide slope antenna
[1] to the airplane structure.
SUBTASK 760-001
Do a check of the resistance between the ILS glide slope antenna [1]
and the airplane structure (SWPM 20-20-00).
(a) Make sure the resistance is not more than 0.001 ohms.
SUBTASK 410-001
Close the nose radome (AMM TASK 53-52-00-400-801 p401).
EFFECTIVITY
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MAINTENANCE MANUAL
SUBTASK 860-007
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
Installation Test
(9)
H.
(1)
SUBTASK 710-001
Do these steps to prepare for the installation test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the APP position.
(d) Set the captain's and the first officer's course select
controls on the DFCS mode control panel to the same course as
the airplane heading.
(e) Set a frequency of 108.1 MHz on the navigation control panels.
NOTE:
____
(f)
To set the frequency, turn the frequency selector until
the frequency shows in the STANDBY window. Then push
the TFR button. The frequency will show in the ACTIVE
display.
Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
(2)
SUBTASK 860-008
Put the test set, NAV-402AP-2, near the front of the airplane and a
minimum of 6 feet from the glide slope antenna.
(3)
SUBTASK 710-002
Use the test set, NAV-402AP-2, to supply an ILS glide slope signal
that follows to the nose antenna:
OUTPUT LEVEL
-60 dBm
DEFLECTION
Down 1 Dot (0.0875 DDM)
FREQUENCY
334.7 MHz
(a)
Make sure the glide slope deviation pointers on the captain's
and the first officer's displays show one dot down.
EFFECTIVITY
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MAINTENANCE MANUAL
LOCALIZER ANTENNA - REMOVAL/INSTALLATION
________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the localizer antenna
(2) An installation of the localizer antenna.
B. The localizer antenna is in the nose radome.
TASK 34-31-31-000-801
2.
_________________________
Localizer
Antenna Removal (Fig. 401)
A. References
(1) AMM TASK 53-52-00-000-801 p401, Nose Radome Removal
B. Access
(1) Location Zones
(a) 111 Radome
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
C. Removal Procedure
(1)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 860-002
WARNING:
_______
(2)
(3)
DO NOT OPERATE THE WEATHER RADAR SYSTEM WHILE YOU REMOVE THE
LOCALIZER ANTENNA. IF THE WEATHER RADAR OPERATES, INJURY TO
PERSONS CAN OCCUR.
Open the nose radome to get access to the localizer antenna [1]
(AMM TASK 53-52-00-000-801 p401).
SUBTASK 020-001
Remove the localizer antenna [1].
(a) Remove the screws [2] that attach the localizer antenna [1] to
the airplane structure.
(b) Pull the localizer antenna [1] away from the airplane structure
to get access to the electrical connectors [3].
(c) Disconnect the electrical connectors [3].
(d) Remove the localizer antenna [1].
(e) Put protective covers on the electrical connectors [3].
EFFECTIVITY
34-31-31
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A
737-600/700/800/900
MAINTENANCE MANUAL
SEE
SEE
A
B
FWD
A
Localizer Antenna Installation
Figure 401 (Sheet 1)
F80482
34-31-31-990-801
EFFECTIVITY
34-31-31
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A
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MAINTENANCE MANUAL
[1] LOCALIZER ANTENNA
[2] SCREW
(12 LOCATIONS)
[3] ELECTRICAL CONNECTORS
CHANNEL ASSEMBLY
FWD
B
Localizer Antenna Installation
Figure 401 (Sheet 2)
F80483
EFFECTIVITY
34-31-31
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A
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MAINTENANCE MANUAL
TASK 34-31-31-400-801
3.
______________________________
Localizer
Antenna Installation (Fig. 401)
A. General
(1) The installation task has an installation test. The installation
test makes sure that the localizer antenna operates correctly.
B. References
(1) AMM TASK 20-10-34-110-802 p701, Clean Bare, Clad, or Plated Metal
with Solvent
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
(4) AMM TASK 51-21-41-370-802 p701, Apply Alodine 600, 1200 or 1200S
Solution
(5) AMM TASK 51-21-91-620-802 p701, Apply the Corrosion Inhibiting
Compound
(6) AMM TASK 53-52-00-000-801 p401, Nose Radome Removal
(7) AMM TASK 53-52-00-400-801 p401, Nose Radome Installation
(8) SWPM 20-20-00
C. Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
D. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
(2) B00083 Solvent, Aliphatic naphtha (for acrylic plastics) - TT-N-95,
Type II
(3) C00259 Primer, Chemical and solvent resistant finish, epoxy resin BMS10-11, Type I
(4) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(5) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
E. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Antenna
¦ 34-31-31
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
EFFECTIVITY
34-31-31
ALL
D633A101-ASA
Page 404
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A
737-600/700/800/900
MAINTENANCE MANUAL
F.
G.
Access
(1) Location Zones
(a) 111 Radome
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
Installation Procedure
(1)
SUBTASK 860-003
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 860-004
WARNING:
_______
(2)
(3)
(4)
(5)
DO NOT OPERATE THE WEATHER RADAR SYSTEM WHILE YOU INSTALL THE
LOCALIZER ANTENNA. IF THE WEATHER RADAR OPERATES, INJURY TO
PERSONS CAN OCCUR.
Open the nose radome to get access to the localizer antenna [1]
(AMM TASK 53-52-00-000-801 p401).
SUBTASK 100-001
Clean the mating surfaces of the localizer antenna [1] and the
airplane structure. To clean the mating surfaces, do this task:
Clean Bare, Clad, or Plated Metal with Solvent
(AMM TASK 20-10-34-110-802 p701).
(a) Apply solvent, TT-N-95, Type II to the mating surfaces of the
localizer antenna [1] and the airplane structure with a cloth,
BMS15-5.
(b) Use a clean cloth, BMS15-5, and clean the mating surfaces
again.
(c) Do these two steps until the mating surfaces are bright, clean
and dry.
SUBTASK 620-001
If the airplane surface has corrosion or other damage, do these
steps to prepare the airplane mating surface:
(a) Apply a layer of coating, Alodine 600 to the airplane mating
surface. To apply the coating, do this task: Apply Alodine
600, 1200 or 1200S Solution (AMM TASK 51-21-41-370-802 p701).
(b) Apply a layer of primer, BMS10-11, Type I to the screw holes.
(c) Allow the primer, BMS10-11, Type I to dry before you install
the screws [2].
SUBTASK 860-005
Apply a layer of compound, BMS3-23, to the airplane and antenna
mating surfaces. To apply the compound, do this task: Apply the
Corrosion Inhibiting Compound (AMM TASK 51-21-91-620-802 p701).
EFFECTIVITY
34-31-31
ALL
D633A101-ASA
Page 405
Oct 10/00
A
737-600/700/800/900
MAINTENANCE MANUAL
(6)
(7)
(8)
SUBTASK 420-001
Install the localizer antenna [1]:
(a) Remove the protective covers from the electrical connectors
[3].
(b) Apply sealant, BMS5-95, to the threads of the screws [2].
(c) Connect the coaxial connectors [3] to the localizer antenna
[1].
(d) Align the localizer antenna [1] to the screw holes that hold
the localizer antenna [1] to the airplane structure.
(e) Install the screws [2] that attach the localizer antenna [1] to
the airplane structure.
SUBTASK 760-001
Do a check of the resistance between the localizer antenna [1] and
the airplane structure (SWPM 20-20-00).
(a) Make sure the resistance is not more than 0.001 ohms.
SUBTASK 410-001
Close the nose radome (AMM TASK 53-52-00-400-801 p401).
SUBTASK 860-006
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
Installation Test
(9)
H.
(1)
SUBTASK 710-001
Do these steps to prepare for the installation test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the APP position.
(d) Set the captain's and the first officer's course select
controls on the DFCS mode control panel to the same course as
the airplane heading.
(e) Set a frequency of 108.1 MHz on the navigation control panels.
NOTE:
____
To set the frequency, turn the frequency selector until
the frequency shows in the STANDBY window. Then push
the TFR button. The frequency will show in the ACTIVE
display.
EFFECTIVITY
34-31-31
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Page 406
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MAINTENANCE MANUAL
(f)
Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
(2)
SUBTASK 860-007
Put the test set, NAV-402AP-2, near the front of the airplane and a
minimum of 6 feet from the forward localizer antenna.
(3)
SUBTASK 860-008
Set the F/D switches on the DFCS mode control panel to the ON
position.
(4)
(5)
SUBTASK 860-009
Push the APP switch on the DFCS mode control panel.
SUBTASK 710-002
Use the test set, NAV-402AP-2, to supply an ILS localizer signal
that follows to the tail (VOR) antenna:
OUTPUT LEVEL
-60 dBm
DEFLECTION
Right 1 Dot (0.0775 DDM)
FREQUENCY
108.1 MHz
(a)
(6)
Make sure the localizer deviation bars on the captain's and the
first officer's displays show one dot right.
SUBTASK 860-010
Set the F/D switches on the DFCS mode control panel to the OFF
position.
EFFECTIVITY
34-31-31
ALL
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Page 407
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A
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MAINTENANCE MANUAL
ILS AND MULTI-MODE RECEIVER (MMR) - REMOVAL/INSTALLATION
________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of a MMR.
(2) An installation of a MMR.
B. The two MMRs are in the main equipment center. The No. 1 MMR is on the
E1 electronics equipment rack, shelf No. 2. The No. 2 MMR is on the E1
electronics equipment rack, shelf No. 4.
TASK 34-31-42-000-801
ú
ú
ú
ú
ú
2.
ú
ú
ú
_________________________________
Multi-Mode
Receiver (MMR) Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-006
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A.
SUBTASK 020-002
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
MULTI-MODE RECEIVER [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE MULTI-MODE
RECEIVER [1].
To remove the No. 1 or No. 2 Multi-mode Receiver [1], do this task:
E/E Box Removal (AMM TASK 20-10-07-000-801 p201).
TASK 34-31-42-400-801
ú
ú
ú
3.
______________________________________
Multi-Mode
Receiver (MMR) Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
EFFECTIVITY
34-31-42
ALL
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Page 401
Feb 10/01
A
737-600/700/800/900
MAINTENANCE MANUAL
ELECTRONIC
EQUIPMENT
RACK, E1
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] MULTI-MODE
RECEIVER (MMR)
NO. 2 (E1-4)
SEE
[1] MULTI-MODE
RECEIVER (MMR)
NO. 1 (E1-2)
SEE
B
B
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACK, E1
A
Multi-Mode Receiver (MMR) Installation
Figure 401
H40186
34-31-42-990-801
EFFECTIVITY
34-31-42
ALL
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Page 402
Jun 10/99
A
737-600/700/800/900
MAINTENANCE MANUAL
ú
ú
ú
ú
ú
ú
ú
ú
ú
ú
(2)
(3)
(4)
(5)
AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Receiver
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Installation Procedure
(1)
SUBTASK 860-007
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 020-003
CAUTION:
_______
(2)
(3)
(4)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
MULTI-MODE RECEIVER [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE MULTI-MODE
RECEIVER [1].
To install the No. 1 or No. 2 Multi-mode Receiver [1], do this task:
E/E Box Installation (AMM TASK 20-10-07-400-801 p201).
SUBTASK 860-008
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
EFFECTIVITY
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E.
Installation Test
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-002
Do these steps to prepare for the installation test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the APP position.
(d) Set the approach mode selector switch on the standby attitude
indicator to the APP position.
(e) Set the captain's and the first officer's course select
controls on the DFCS mode control panel to the same course as
the airplane heading.
(f) Set a frequency of 108.1 MHz on the captain's and the first
officer's navigation control panels.
NOTE:
____
(g)
(3)
To set the frequency, turn the frequency selector until
the frequency shows in the STANDBY display window. Then
push the TFR button. The frequency will show in the
ACTIVE display window.
Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
SUBTASK 710-003
Do these steps to do an installation test of the No. 1 (captain's)
MMR:
(a) Push and release the TEST button on the captain's navigation
control panel.
1) Make sure that these indications show on the captain's
display:
NOTE:
____
a)
b)
c)
The
The
the
The
the
It takes approximately 16 seconds for the test
sequence to complete.
LOC and G/S flags show momentarily.
glideslope deviation pointer shows one dot up and
localizer deviation bar shows one dot left.
glideslope deviation pointer shows one dot down and
localizer deviation bar shows one dot right.
EFFECTIVITY
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(4)
SUBTASK 710-004
Do these steps to do an installation test of the No. 2 (first
officer's) MMR:
(a) Push and release the TEST button on the first officer's
navigation control panel.
1) Make sure that these indications show on the first
officer's display:
NOTE:
____
a)
b)
c)
(5)
The
The
the
The
the
It takes approximately 16 seconds for the test
sequence to complete.
LOC and G/S flags show momentarily.
glideslope deviation pointer shows one dot up and
localizer deviation bar shows one dot left.
glideslope deviation pointer shows one dot down and
localizer deviation bar shows one dot right.
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
NAVIGATION CONTROL PANEL - REMOVAL/INSTALLATION
_______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the navigation control panel.
(2) An installation of the navigation control panel.
B. The captain's and first officer's navigation control panels are on the
aft electronics panel, P8, in the flight compartment.
TASK 34-31-52-000-801
2.
________________________________
Navigation
Control Panel Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
B. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A15
RADIO NAVIGATION NAV CONT PNL 2
(b) Circuit Breaker Panel, P18-1:
1) 18A3
RADIO NAVIGATION NAV CONT PNL 1
2) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 860-002
On the aft electronics panel, P8, turn the knob of the PANEL control
to the OFF position.
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
NAVIGATION CONTROL PANEL [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE NAVIGATION
CONTROL PANEL [1].
Remove the navigation control panel [1]:
(a) Loosen the four quarter-turn fasteners [2].
(b) Carefully lift the navigation control panel [1] from the aft
electronics panel, P8, to get access to the electrical
connectors [3].
(c) Disconnect the electrical connectors [3].
(d) Put protective covers on the electrical connectors [3].
EFFECTIVITY
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SEE
A
FLIGHT COMPARTMENT
[2] QUARTER-TURN
FASTENER
(4 LOCATIONS)
[1] NAVIGATION
CONTROL
PANELS
[3] ELECTRICAL
CONNECTOR
(2 LOCATIONS)
FWD
AISLE STAND
A
Navigation Control Panel Installation
Figure 401
F96009
34-31-52-990-801
EFFECTIVITY
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TASK 34-31-52-400-801
3.
_____________________________________
Navigation
Control Panel Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ ASA 001-016;
¦
¦
¦ 401
1 ¦ Panel
¦ 34-31-52
01
55 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
D. Installation Procedure
(1)
SUBTASK 860-003
Make sure that these circuit breakers
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV
2) 6A15
RADIO NAVIGATION NAV
(b) Circuit Breaker Panel, P18-1:
1) 18A3
RADIO NAVIGATION NAV
2) 18B1
RADIO NAVIGATION NAV
are open:
SNSR DC-2
CONT PNL 2
CONT PNL 1
SNSR DC-1
SUBTASK 420-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
NAVIGATION CONTROL PANEL [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE NAVIGATION
CONTROL PANEL [1].
Install the navigation control panel [1]:
(a) Remove the protective covers from the electrical connectors
[3].
(b) Examine the electrical connectors [3] for bent or broken pins,
dirt, and damage.
(c) Connect the electrical connectors [3].
(d) Put the navigation control panel [1] in its position on the aft
electronics panel, P8.
(e) Tighten the four quarter-turn fasteners [2].
EFFECTIVITY
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SUBTASK 860-004
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A15
RADIO NAVIGATION NAV CONT PNL 2
(b) Circuit Breaker Panel, P18-1:
1) 18A3
RADIO NAVIGATION NAV CONT PNL 1
2) 18B1
RADIO NAVIGATION NAV SNSR DC-1
Installation Test
(3)
E.
(1)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-007
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
(3)
SUBTASK 860-009
Set the mode selector on the captain's and the first officer's EFIS
control panels to the VOR position.
(4)
SUBTASK 710-001
Set a frequency of 108.00 MHz on the captain's and the first
officer's navigation control panels [1].
NOTE:
____
(a)
(5)
(6)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
Make sure 108.00 MHz shows on the displays.
SUBTASK 710-002
Set a frequency of 115.00 MHz on the captain's and the first
officer's navigation control panels [1].
(a) Make sure 115.00 MHz shows on the displays.
SUBTASK 860-008
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
RF POWER DIVIDER - REMOVAL/INSTALLATION
_______________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of a RF power divider.
(2) An installation of a RF power divider.
B. The No. 1 and No. 2 RF power dividers are on the E1 electronic equipment
rack in the main equipment center.
TASK 34-31-62-000-801
2.
________________________
RF
Power Divider Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
B. Removal Procedure
(1)
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A to get access to the
RF power divider [3].
SUBTASK 020-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE RF
POWER DIVIDER [3]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE RF POWER
DIVIDER [3].
Remove the RF power divider [3]:
(a) Disconnect the coaxial connectors [4].
(b) Remove the screws [1] and washers [2] that attach the RF power
divider [3] to the electronic equipment rack.
(c) Remove the RF power divider [3] from the electronic equipment
rack.
TASK 34-31-62-400-801
3.
_____________________________
RF
Power Divider Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(4) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
EFFECTIVITY
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MAINTENANCE MANUAL
ELECTRONIC
EQUIPMENT
RACK, E1 AND E5
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
RF POWER
DIVIDERS
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
SEE
B
FWD
ELECTRONIC EQUIPMENT RACKS, E1 AND E5
A
RF Power Divider Installation
Figure 401 (Sheet 1)
G34419
34-31-62-990-801
EFFECTIVITY
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[3] RF POWER
DIVIDER NO.1
[3] RF POWER
DIVIDER NO.2
[2] WASHER
(3 LOCATIONS)
[1] SCREW
(3 LOCATIONS)
[4] COAXIAL
CONNECTORS
INBD
FWD
B
RF Power Divider Installation
Figure 401 (Sheet 2)
G33104
EFFECTIVITY
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B.
Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
3 ¦ Divider
¦ 34-31-51
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
E. Installation Procedure
SUBTASK 420-001
CAUTION:
_______
(1)
F.
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE RF
POWER DIVIDER [3]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE RF POWER
DIVIDER [3].
Install the RF power divider [3]:
(a) Align the RF power divider [3] to the holes in the electronic
equipment rack.
(b) Install the screws [1] and washers [2] that attach the RF power
divider [3] to the electronic equipment rack.
(c) Connect the coaxial connectors [4] to the RF power divider [3].
SUBTASK 410-001
(2) Close the Electronic Equipment Access Door, 117A.
Installation Test
(1)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
(2)
SUBTASK 860-002
Do these steps to prepare for the installation test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and first officer's EFIS
control panels to the APP position.
(d) Set the captain's and first officer's course select controls on
the AFCS mode control panel to the same course as the airplane
heading.
(e) Set a frequency of 108.1 MHz on the captain's and first
officer's navigation control panels.
NOTE:
____
(f)
(3)
To set the frequency, turn the frequency selector until
the frequency shows in the STANDBY display window. Then
push the TFR button. The frequency will show in the
ACTIVE display window.
Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
SUBTASK 710-001
Do these steps to do an installation test of the No. 1 (captain's)
RF power divider:
(a) Make sure the F/D switches on the AFCS mode control panel are
in the OFF position.
(b) Put the test set, NAV-402AP-2, near the front of the airplane
and a minimum of 6 feet from the forward localizer antenna.
(c) Use the test set, NAV-402AP-2, to supply an ILS localizer
signal that follows to the tail (VOR) antenna:
OUTPUT LEVEL
-15 dBm
DEFLECTION
Right 1 Dot (0.0775 DDM)
FREQUENCY
108.1 MHz
1)
(d)
(e)
(f)
Make sure the localizer deviation bar on the captain's
display is one dot right.
Set the mode selector on the captain's EFIS control panel to
the VOR position.
Set a frequency of 108.0 MHz on the captain's navigation
control panel.
Use the test set, NAV-402AP-2, to supply a VOR signal that
follows to the tail (VOR) antenna:
EFFECTIVITY
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(g)
(4)
OUTPUT LEVEL
-60 dBm
BEARING
50 degrees
TO/FROM
TO
FREQUENCY
108.0 MHz
Make sure the No. 1 bearing pointer on the captain's and the
first officer's RDMI shows 50 degrees.
SUBTASK 710-002
Do these steps to do an installation test of the No. 2 (first
officer's) RF power divider:
(a) Make sure the F/D switches on the AFCS mode control panel are
in the OFF position.
(b) Put the test set, NAV-402AP-2, near the front of the airplane
and a minimum of 6 feet from the forward localizer antenna.
(c) Use the test set, NAV-402AP-2, to supply an ILS localizer
signal that follows to the tail (VOR) antenna:
OUTPUT LEVEL
-15 dBm
DEFLECTION
Right 1 Dot (0.0775 DDM)
FREQUENCY
108.1 MHz
1)
(d)
(e)
(f)
(g)
(5)
Make sure the localizer deviation bar on the captain's
display is one dot right.
Set the mode selector on the first officer's EFIS control panel
to the VOR position.
Set a frequency of 108.0 MHz on the first officer's navigation
control panel.
Use the test set, NAV-402AP-2, to supply a VOR signal that
follows to the tail (VOR) antenna:
OUTPUT LEVEL
-60 dBm
BEARING
50 degrees
TO/FROM
TO
FREQUENCY
108.0 MHz
Make sure the No. 2 bearing pointer on the captain's and the
first officer's RDMI shows 50 degrees.
SUBTASK 860-003
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
LOCALIZER ANTENNA SWITCH - REMOVAL/INSTALLATION
_______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of a localizer antenna switch.
(2) An installation of a localizer antenna switch.
B. The No. 1 and No. 2 localizer antenna switches are on the E1 electronic
equipment rack in the main equipment center.
TASK 34-31-72-000-801
2.
________________________________
Localizer
Antenna Switch Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
B. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
(b) Circuit Breaker Panel, P18-1:
1) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A to get access to the
localizer antenna switch [3].
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
LOCALIZER ANTENNA SWITCH [3]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE LOCALIZER
ANTENNA SWITCH [3].
Remove the localizer antenna switch [3]:
(a) Disconnect the coaxial connectors [4].
(b) Remove the screws [1] and washers [2] that attach the localizer
antenna switch [3] to the electronic equipment rack.
(c) Remove the localizer antenna switch [3] from the electronic
equipment rack.
EFFECTIVITY
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MAINTENANCE MANUAL
ELECTRONIC
EQUIPMENT
RACKS, E1 AND E5
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
LOCALIZER
ANTENNA
SWITCH
SEE
B
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACKS, E1 AND E5
A
Localizer Antenna Switch Installation
Figure 401 (Sheet 1)
G20161
34-31-72-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
[4] COAXIAL
CONNECTORS
[3] LOCALIZER
ANTENNA
SWITCH NO.2
[1] SCREW
(2 LOCATIONS)
[3] LOCALIZER
ANTENNA
SWITCH NO.1
[2] WASHER
(2 LOCATIONS)
INBD
FWD
B
Localizer Antenna Switch Installation
Figure 401 (Sheet 2)
G20164
EFFECTIVITY
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MAINTENANCE MANUAL
TASK 34-31-72-400-801
3.
_____________________________________
Localizer
Antenna Switch Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(4) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
B. Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
3 ¦ Switch
¦ 34-31-72
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
E. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
(b) Circuit Breaker Panel, P18-1:
1) 18B1
RADIO NAVIGATION NAV SNSR DC-1
EFFECTIVITY
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SUBTASK 420-001
CAUTION:
_______
(2)
(3)
F.
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
LOCALIZER ANTENNA SWITCH [3]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE LOCALIZER
ANTENNA SWITCH [3].
Install the localizer antenna switch [3]:
(a) Align the localizer antenna switch [3] to the holes in the
electronic equipment rack.
(b) Install the screws [1] and washers [2] that attach the
localizer antenna switch [3] to the electronic equipment rack.
(c) Connect the coaxial connectors [4] to the localizer antenna
switch [3].
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
(b) Circuit Breaker Panel, P18-1:
1) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 410-001
(4) Close the Electronic Equipment Access Door, 117A.
Installation Test
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-005
Do these steps to prepare for the installation test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(c) Set the mode selector on the captain's and first officer's EFIS
control panels to the APP position.
(d) Set the captain's and first officer's course select controls on
the AFCS mode control panel to the same course as the airplane
heading.
(e) Set a frequency of 108.1 MHz on the captain's and first
officer's navigation control panels.
NOTE:
____
To set the frequency, turn the frequency selector until
the frequency shows in the STANDBY display window. Then
push the TFR button. The frequency will show in the
ACTIVE display window.
EFFECTIVITY
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(f)
(3)
Make sure the air data inertial reference unit (ADIRU) is
aligned and in the NAV mode. To align it, do this task: Air
Data Inertial Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
SUBTASK 710-001
Do these steps to do an installation test of the No. 1 (captain's)
localizer antenna switch:
(a) Make sure the F/D switches on the AFCS mode control panel are
in the OFF position.
(b) Put the test set, NAV-402AP-2, near the front of the airplane
and a minimum of 6 feet from the forward localizer antenna.
(c) Use the test set, NAV-402AP-2, to supply an ILS localizer
signal that follows to the tail (VOR) antenna:
OUTPUT LEVEL
-15 dBm
DEFLECTION
Right 1 Dot (0.0775 DDM)
FREQUENCY
108.1 MHz
1)
(d)
(e)
(f)
(g)
(4)
Make sure the localizer deviation bar on the captain's
display is one dot right.
Slowly decrease the RF level on the test set, NAV-402AP-2,
until the localizer deviation bar on the captain's display does
not show.
Set the F/D switches on the AFCS mode control panel to the ON
position.
Push the APP switch on the AFCS mode control panel.
1) Make sure the localizer deviation bar on the captain's
display is one dot right.
Set the F/D switches on the AFCS mode control panel to the OFF
position.
SUBTASK 710-002
Do these steps to do an installation test of the No. 2 (first
officer's) localizer antenna switch:
(a) Make sure the F/D switches on the AFCS mode control panel are
in the OFF position.
(b) Put the test set, NAV-402AP-2, near the front of the airplane
and a minimum of 6 feet from the forward localizer antenna.
(c) Use the test set, NAV-402AP-2, to supply an ILS localizer
signal that follows to the tail (VOR) antenna:
OUTPUT LEVEL
-15 dBm
DEFLECTION
Right 1 Dot (0.0775 DDM)
EFFECTIVITY
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FREQUENCY
108.1 MHz
1)
(d)
(e)
(f)
(g)
(5)
Make sure the localizer deviation bar on the first
officer's display is one dot right.
Slowly decrease the RF level on the test set, NAV-402AP-2,
until the localizer deviation bar on the first officer's
display does not show.
Set the F/D switches on the AFCS mode control panel to the ON
position.
Push the APP switch on the AFCS mode control panel.
1) Make sure the localizer deviation bar on the first
officer's display is one dot right.
Set the F/D switches on the AFCS mode control panel to the OFF
position.
SUBTASK 860-006
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
MARKER BEACON SYSTEM - ADJUSTMENT/TEST
______________________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the marker beacon system.
(2) A system test of the marker beacon system.
TASK 34-32-00-710-801
2.
_______________________________________
Marker
Beacon System - Operational Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Prepare for the Operational Test
(1)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-002
Do these steps to prepare for the operational test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the mode selector on the captain's and the first officer's
EFIS control panel to the VOR position.
(c) Set the SOURCE switch on the instrument switching module to the
AUTO position.
Marker Beacon Receiver Self Test
(2)
D.
(1)
SUBTASK 860-003
Set a frequency of 108.00 MHz on the captain's navigation control
panel.
NOTE:
____
(2)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
SUBTASK 710-001
Push and release the TEST button on the captain's navigation control
panel.
(a) Make sure that the marker beacon indication on the captain's
and the first officer's displays agree with the data in
(Table 501):
EFFECTIVITY
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TABLE 34-32-00-993-801
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
TIME
¦ CAPTAIN'S MARKER ¦
FIRST OFFICER'S
¦
¦
(Approx.)
¦ BEACON DISPLAY ¦ MARKER BEACON DISPLAY ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
3 |1 second
¦
Blank
¦
Blank
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ After 3 seconds ¦
FT
¦
FT
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 5 to 35 seconds ¦
Blank
¦
Blank
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 501
(3)
SUBTASK 860-004
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-32-00-730-801
3.
__________________________________
Marker
Beacon System - System Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-32-00-710-801 p501, Marker Beacon System - Operational
Test
B. Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Prepare for the System Test
(1)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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SUBTASK 860-006
Do these steps to prepare for the system test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the mode selector on the captain's and the first officer's
EFIS control panel to the VOR position.
(c) Set the SOURCE switch on the instrument switching module to the
AUTO position.
Operational Test
(2)
E.
SUBTASK 710-002
Do this task: Marker Beacon System - Operational Test
(AMM TASK 34-32-00-710-801 p501).
Marker Beacon Operation Test
(1)
F.
(1)
SUBTASK 860-007
Push the receiver volume controls for marker beacon, MKR, on each
audio selector panel to set the volume to off.
(2)
SUBTASK 730-001
Set up the test set, NAV-402AP-2, to supply a marker beacon signal
of 75 MHz with a 400 Hz modulation.
NOTE:
____
(a)
(3)
(4)
If the antenna on the test set is not a marker beacon test
antenna tuned at 75 MHz, it is not easy to get the test
results. Put the test set near the marker beacon antenna and
at approximately the same height as the marker beacon
antenna.
Make sure the outer marker indication, OM, shows on the
captain's and the first officer's EFIS displays.
SUBTASK 860-008
Push the receiver volume control for marker beacon, MKR, on the
captain's audio control panel to set the volume to on.
SUBTASK 730-002
Turn the receiver volume control clockwise for marker beacon, MKR,
on the captain's audio control panel.
(a) Make sure you can hear a tone through the interphone system.
(b) Make sure you can hear a tone at the captain's audio selector
panel with a headset.
(5)
SUBTASK 860-009
Push the receiver volume control for marker beacon, MKR, on the
captain's audio selector panel to set the volume to off.
(6)
SUBTASK 860-010
Push the receiver volume control for marker beacon, MKR, on the
first officer's audio control panel to set the volume to on.
EFFECTIVITY
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(7)
(8)
(9)
SUBTASK 730-003
Turn the receiver volume control clockwise for marker beacon, MKR,
on the first officer's audio control panel.
(a) Make sure you can hear a tone through the interphone system.
(b) Make sure you can hear a tone at the first officer's audio
selector panel with a headset.
SUBTASK 860-011
Push the receiver volume control for marker beacon, MKR, on the
first officer's audio selector panel to set the volume to off.
SUBTASK 730-004
Use the test set, NAV-402AP-2, to supply a marker beacon signal of
75 MHz with a 1300 Hz modulation.
(a) Make sure the middle marker indication, MM, shows on the
captain's and the first officer's EFIS displays.
SUBTASK 730-005
(10) Use the test set, NAV-402AP-2, to supply a marker beacon signal of
75 MHz with a 3000 Hz modulation.
(a) Make sure the inner marker indication, IM, shows on the
captain's and the first officer's EFIS displays.
SUBTASK 860-012
(11) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
MARKER BEACON ANTENNA - REMOVAL/INSTALLATION
____________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the marker beacon antenna
(2) An installation of the marker beacon antenna.
TASK 34-32-11-000-801
2.
_____________________________
Marker
Beacon Antenna Removal (Fig. 401)
A. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
B. Access
(1) Location Zones
(a) 100 Lower Half of Fuselage
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
SUBTASK 020-001
Remove the marker beacon antenna [1]:
(a) Remove the six bolts [2] from the antenna base.
CAUTION:
_______
(b)
Use force around the marker beacon antenna [1] with the sealant
removal tool until the seal is fully broken.
CAUTION:
_______
(c)
(d)
(e)
BE CAREFUL WHEN YOU USE THE SEALANT REMOVAL TOOL TO BREAK
THE ANTENNA SEAL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE
AIRPLANE SKIN, THE COAXIAL CABLE, OR THE ANTENNA.
LOWER THE ANTENNA ONLY AS FAR AS NECESSARY TO DISCONNECT
THE COAXIAL CONNECTOR. DAMAGE TO THE CABLE CAN OCCUR IF
YOU PULL THE CABLE.
Lower the marker beacon antenna [1] until you can get access to
the coaxial connector [3].
Disconnect the coaxial connector [3] from the marker beacon
antenna [1].
Remove the marker beacon antenna [1].
TASK 34-32-11-400-801
3.
__________________________________
Marker
Beacon Antenna Installation (Fig. 401)
A. References
(1) AMM TASK 20-30-88-910-801 p201, Final Cleaning of Metal Prior to
Non-structural Bonding (Series 88)
EFFECTIVITY
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MARKER BEACON
ANTENNA
SEE
A
FWD
[3] COAXIAL
CONNECTOR
AIRPLANE SKIN
[1] MARKER BEACON
ANTENNA
[2] BOLT
(6 LOCATIONS)
MARKER BEACON ANTENNA
A
Marker Beacon Antenna Installation
Figure 401
F64707
34-32-11-990-801
EFFECTIVITY
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(2)
(3)
(4)
AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
AMM TASK 51-21-31-350-806 p701, Removal and Control of Corrosion for
Plated or Phosphated Surfaces
(5) AMM TASK 51-21-41-370-802 p701, Apply Alodine 600, 1200 or 1200S
Solution
(6) AMM TASK 51-31-00-390-806 p201, Aerodynamic Smoother Application
(7) SWPM 20-20-00
B. Equipment
(1) Ohmmeter - Resistance Measuring Bridge
(commercially available)
(2) Spatula - Fillet Smoothing, Hardwood or Plastic
(commercially available)
(3) NAV-402AP-2 Test Set - VOR/ILS, RAMP
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
C. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
(2) B01008 Solvent, Final Cleaning of Metal Prior to Non-structural
Bonding (AMM 20-30-88/201 or SOPM 20-30-88) - Series 88
(3) C00064 Coating, Aluminum chemical conversion BAC5719,TypeII,ClassA(MIL-C-5541,ClassA)
(4) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(5) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Antenna assy
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 100 Lower Half of Fuselage
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment, Right
F. Installation Procedure
(1)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
EFFECTIVITY
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MAINTENANCE MANUAL
(2)
SUBTASK 100-001
Clean the airplane mating surface:
WARNING:
_______
(a)
(b)
(c)
(3)
(4)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON
YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS.
SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE
FLAMMABLE OR HARMFUL TO THE ENVIRONMENT. REFER TO PRODUCT
MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS
FOR PROPER HANDLING PROCEDURES.
Clean the airplane mating surface with a cloth, BMS15-5
moistened with solvent, Series 88
(AMM TASK 20-30-88-910-801 p201).
Use a clean cloth, BMS15-5 and clean the airplane mating
surface again.
Do these two steps above until the airplane mating surface is
clean and dry.
SUBTASK 100-002
If the airplane surface has corrosion or other damage, do these
steps to prepare the airplane mating surface:
(a) Remove the corrosion from the airplane mating surface. To
remove the corrosion, do this task: Removal and Control of
Corrosion for Plated or Phosphated Surfaces
(AMM TASK 51-21-31-350-806 p701)
(b) To apply a layer of coating,
BAC5719,TypeII,ClassA(MIL-C-5541,ClassA) to the airplane mating
surface, do this task: Apply Alodine 600, 1200 or 1200S
Solution (AMM TASK 51-21-41-370-802 p701).
SUBTASK 420-001
Install the marker beacon antenna [1]:
(a) Apply a very thin layer of compound, BMS3-23 to the surfaces of
the marker beacon antenna [1] that will come in contact with
the skin of the airplane.
(b) Connect the coaxial connector [3] to the marker beacon antenna
[1].
(c) Put the marker beacon antenna [1] in the correct position on
the airplane surface.
(d) Install five of the six bolts [2] in the base of the marker
beacon antenna [1].
(e) Manually tighten the bolts [2] to 15 pound-inch of torque (1.7
newton-meters).
EFFECTIVITY
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(f)
Measure the resistance between the baseplate of the marker
beacon antenna [1] and the airplane skin with an ohmmeter
(SWPM 20-20-00):
NOTE:
____
(g)
(5)
Use the empty bolt hole to get access to the antenna
baseplate.
1) Make sure the resistance is less than 10 milliohms.
Install the last bolt [2].
SUBTASK 390-001
Apply aerodynamic sealant:
(a) Apply an aerodynamic fillet seal around the base of the marker
beacon antenna [1] with sealant, BMS5-95
(AMM TASK 51-31-00-390-806 p201).
(b) Use the spatula to make a smooth 45-degree fillet.
(c) Apply sealant, BMS5-95 to the heads of the bolts
(AMM TASK 51-31-00-390-806 p201).
(d) Let the sealant dry for the correct cure time.
SUBTASK 860-003
Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
Installation Test
(6)
G.
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 730-001
Do this test the marker beacon antenna [1]:
(a) Make sure the MKR controls on all the audio selector panels are
off.
(b) Use the test set, NAV-402AP-2, to supply a marker beacon signal
of 75 MHz with a 400 Hz modulation.
NOTE:
____
1)
(3)
If the antenna on the test set is not a marker beacon
test antenna tuned at 75 MHz, it is not easy to get the
test results. Put the test set near the marker beacon
antenna and at approximately the same height as the
marker beacon.
Make sure OM shows on the captain's display unit for the
outer marker beacon.
SUBTASK 080-001
Remove the test set, NAV-402AP-2.
EFFECTIVITY
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MAINTENANCE MANUAL
(4)
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
LOW RANGE RADIO ALTIMETER (LRRA) SYSTEM - MAINTENANCE PRACTICES
_______________________________________________________________
1.
General
_______
A. This procedure has one task for the low range radio altimeter (LRRA)
system:
(1) A simulation test of radio altitude.
TASK 34-33-00-700-801
2.
______________________________
Radio
Altitude Simulation Test
A. General
(1) This task uses an Atlantis DRA707 Radio Altimeter (RA) test set to
do a simulation test of radio altitude.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
C. Equipment
(1) Test (or alternative tool)
(a) DRA707B1 Test Set - Collins Radio Altimeter (recommended)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(b) 2041595-5201 Test Set - Bendix Radio Altimeter (alternative)
Honeywell, Inc. (Vendor Code 27914)
2100 N.W. 62nd Street, P.O. Box 9414, Fort Lauderdale FL 33309
(c) 9599-607-15902 Test Set - Radio Altimeter (alternative)
TRT/Telecommunications Radioelectriques et Telephoniques SA
(Vendor Code F6170)
88 Rue Brillat Savarin, 75640 Paris, France
(d) ARA-552 Test Set - Radio Altimeter Test (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(e) DRA707 Test Set - Radio Altimeter (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(f) ADC-552 Converter - Digital, Radio Altimeter Tester
(alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(2) Test (or alternative tool)
(a) DRA707 Test Set - Radio Altimeter (recommended)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(b) DRA707B1 Test Set - Collins Radio Altimeter (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(c) 2041595-5201 Test Set - Bendix Radio Altimeter (alternative)
Honeywell, Inc. (Vendor Code 27914)
2100 N.W. 62nd Street, P.O. Box 9414, Fort Lauderdale FL 33309
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(d)
(e)
(f)
D.
E.
9599-607-15902 Test Set - Radio Altimeter (alternative)
TRT/Telecommunications Radioelectriques et Telephoniques SA
(Vendor Code F6170)
88 Rue Brillat Savarin, 75640 Paris, France
ARA-552 Test Set - Radio Altimeter Test (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
ADC-552 Converter - Digital, Radio Altimeter Tester
(alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
Prepare for the Test
(1)
(2)
(3)
SUBTASK 860-019
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 800-002
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 010-002
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center.
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(4)
SUBTASK 480-002
Install the test set, DRA707B1.
(a) Set the POWER switch on the test set, DRA707B1 to OFF.
(b) Connect the correct test cable(s) between the TEST connector on
the test set, DRA707B1 and the TEST connector on the
transceiver(s).
NOTE:
____
You can do a test of each radio altimeter (No. 1 or No.
2) separately, or all together, with these test cables
in the test set, DRA707B1:
Test cable ATLANTIS P/N 110-0440-101 use with Collins
LRA-900
Test cable ATLANTIS P/N 110-0440-106 use with TRT
ERT-530 digital output radio altimeters
(c)
Connect the power cable to the correct primary power source
shown on the front panel of the test set, DRA707B1.
NOTE:
____
If the batteries in the test set, DRA707B1 have the
correct charge, the connection to a primary power source
is not necessary.
SUBTASK 860-020
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
Procedure
(5)
F.
(1)
SUBTASK 860-015
Prepare the test Set, DRA707 for the altitude simulation:
(a) Set the power ON/OFF switch to the ON position.
1) Make sure the 5 VDC and HOLDING lights come on.
(b) Set the NO COMPUTED DATA switches to the NORMAL position.
(c) Push and release the START ALT key.
1) Make sure START ALT shows on the LEDs.
(d) Use the keypad to put in a value of +4000 feet.
NOTE:
____
Do not push the ENTER key.
1)
(e)
Make sure the EFIS displays show a radio altitude between
-8 to -12 feet.
Push and release the ENTER key.
1) Make sure the radio altitude value shown on the EFIS
displays is blank.
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(2)
(3)
(4)
SUBTASK 860-016
Prepare the captain's and the first officer's EFIS control panels
for the simulation.
(a) Push and release the RST (reset) button.
(b) Turn the DH control to show DH 450 at the captain's EFIS
display.
(c) Turn the DH control to show DH 400 at the first officer's EFIS
display.
SUBTASK 860-017
Set these controls on the test Set, DRA707:
(a) Push and release the STOP ALT key.
1) Make sure the LEDs show STOP ALT.
(b) Use the keypad to put in a value of -20 feet.
(c) Push and release the ENTER key.
1) Make sure the LEDs show STOP ALT -20.
(d) Push and release the VERT SPD key.
1) Make sure the LEDs show VERT SPD.
(e) Use the keypad to put in a value of -4000 (feet per minute).
(f) Push and release the ENTER key.
1) Make sure the LEDs show VERT SPD -4000.
SUBTASK 730-009
Do the altitude ramp-down procedure (typical).
(a) Push the RAMP/HOLD key on the test Set, DRA707.
1) Make sure the RAMPING light comes on.
(b) Look for these indications on the captain's and the first
officer's EFIS displays.
1) The radio altitude goes out of view for approximately 22.5
seconds while the altitude on the test Set, DRA707
decreases from 4000 to 2500 feet.
(c) After the time-out of 22.5 seconds (previous step), a radio
altitude of 2500 feet comes into view on the EFIS displays and
decreases to zero.
NOTE:
____
(d)
(e)
The EFIS displays show the radio altitude set on the
test Set, DRA707 within the limit of 2500 feet to -20
feet.
Look for these indications on the captain's EFIS display when
the radio altitude decreases to 450 feet:
1) The DH value changes to a yellow color and flashes for 3
seconds.
2) The radio altitude continues to decrease to zero.
Look for these indications on the first officer's EFIS display
when the radio altitude decreases to 400 feet:
1) The DH value changes to a yellow color and flashes for 3
seconds.
2) The DH value flashes for approximately 3 seconds.
3) The radio altitude continues to decrease toward zero.
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(f)
G.
Look for these indications on the EFIS displays while the radio
altitude decreases to zero feet:
1) The radio altitude value changes to a white color.
2) The DH value changes to the numbers set at the captain's
and the first officer's EFIS control panels.
Put the Airplane Back to Its Usual Condition
(1)
(2)
(3)
(4)
(5)
SUBTASK 860-021
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 080-003
Remove the test set, DRA707B1.
(a) Set the POWER ON/OFF switch on the test set, DRA707B1 to the
OFF position.
(b) Disconnect the power cable for the test set, DRA707B1 from the
primary power source (if the power cable was used).
(c) Disconnect the test cable(s) from the test set, DRA707B1 and
the applicable transceivers.
(d) Put the test cables in the box for the test set, DRA707B1.
SUBTASK 410-002
Install a TEST connector protective cover on the transceiver(s).
SUBTASK 860-022
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 410-003
Close the Electronic Equipment Access Door, 117A.
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LOW RANGE RADIO ALTIMETER (LRRA) SYSTEM - ADJUSTMENT/TEST
_________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the low range radio altimeter (LRRA) system.
(2) A system test of the LRRA system.
B. There are two radio altimeter systems installed on the airplane. Each
radio altimeter system is made up of an LRRA receiver/transmitter (R/T)
and two microstrip antennas. One of the antennas is a transmit antenna
and one is a receive antenna.
C. The radio altimeter system measures the altitude of the airplane in the
range of -4 feet to 2,500 feet. This altitude will show on the common
display system (CDS). The CDS displays radio altitude on the captain's
and first officer's primary display units, on the right side of the
electronic altitude director indicator (EADI).
TASK 34-33-00-710-801
2.
__________________________________________________________
Low
Range Radio Altimeter (LRRA) System - Operational Test
A. General
(1) The operational test includes a LRRA Interface To Display Electronic
Unit test.
(2) The operational test makes sure the interface between the
transceiver and the displays is ok. The operational test does not
include a check of the LRRA antennas.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
D. Procedure
(1)
(2)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-001
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(a) Make sure that -4 |2 feet radio altitude shows on the captain's
and first officer's EFIS displays.
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(3)
(4)
SUBTASK 710-002
Set the SOURCE switch on the instrument switching module to the ALL
ON 1 position.
(a) Make sure that -4 |2 feet radio altitude shows on the captain's
and first officer's EFIS displays.
SUBTASK 710-003
Set the SOURCE switch on the instrument switching module to the ALL
ON 2 position.
(a) Make sure that -4 |2 feet radio altitude shows on the captain's
and first officer's EFIS displays.
(5)
SUBTASK 860-002
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(6)
SUBTASK 860-003
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-33-00-730-801
3.
_____________________________________________________
Low
Range Radio Altimeter (LRRA) System - System Test
A. General
(1) The system test makes sure the interface between the Air/Ground
relays is ok and the transmit and receive antennas operate
correctly.
(2) The system test includes these tests:
(a) The LRRA Air/Ground Discrete Input Test
(b) The LRRA Antenna Coaxial Cable Test.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-33-00-710-801 p501, Low Range Radio Altimeter (LRRA)
System - Operational Test
(4) AMM TASK 34-33-21-000-801 p401, Low Range Radio Altimeter (LRRA)
Receiver/Transmitter (R/T) Removal
(5) AMM TASK 34-33-21-400-801 p401, Low Range Radio Altimeter (LRRA)
Receiver/Transmitter (R/T)
Installation
C. Equipment
(1) Detector - Crystal, Hewlett Packard HPX421A or HPX421B or Generic
1N23 crystal diode
(commercially available)
(2) eccosorb AN74 Material - RF Absorbent, Eccosorb AN74 Emerson Cumming
or Equivalent
(3) Multimeter - Standard
(commercially available)
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D.
E.
Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
Prepare for the System Test
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
Air/Ground Discrete Input Test
(1)
F.
(1)
(2)
(3)
SUBTASK 860-005
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 020-001
Remove the No. 1 and the No. 2 LRRA R/Ts. To remove them, do this
task: Low Range Radio Altimeter (LRRA) Receiver/Transmitter (R/T)
Removal (AMM TASK 34-33-21-000-801 p401).
SUBTASK 730-001
Use a multimeter to measure the resistance between the AIR/GROUND
DISCRETE, pin F4, and the IND 2 STATUS, pin F6, in connector D3667B
for the No. 1 radio altimeter system.
(a) Make sure the multimeter shows 10 KOhms or more than 10 KOhms.
SUBTASK 730-002
WARNING:
_______
(4)
(5)
MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE
CONTROL SURFACES AND LANDING GEAR DOOR AREAS. THE CONTROL
SURFACES, THE LANDING GEAR, AND THE LANDING GEAR DOORS CAN MOVE
WHEN YOU DO THE AIR MODE SIMULATION. THIS CAN CAUSE INJURIES
TO PERSONS AND DAMAGE TO EQUIPMENT.
Push and hold the SYS #1 IN AIR button on the proximity switch
electronics unit in the forward electronics equipment bay.
(a) Make sure that the multimeter shows 100 Ohms or less.
SUBTASK 860-006
Release the SYS #1 IN AIR button.
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(6)
SUBTASK 730-003
Use a multimeter to measure the resistance between the AIR/GROUND
DISCRETE, pin F4, and the IND 2 STATUS, pin F6, in connector D3669B
for the No. 2 radio altimeter system.
(a) Make sure that the multimeter shows 10 KOhms or more than 10
KOhms.
SUBTASK 730-004
WARNING:
_______
(7)
(8)
MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE
CONTROL SURFACES AND LANDING GEAR DOOR AREAS. THE CONTROL
SURFACES, THE LANDING GEAR, AND THE LANDING GEAR DOORS CAN MOVE
WHEN YOU DO THE AIR MODE SIMULATION. THIS CAN CAUSE INJURIES
TO PERSONS AND DAMAGE TO EQUIPMENT.
Push and hold the SYS #2 IN AIR button on the proximity switch
electronics unit in the forward electronics equipment bay.
(a) Make sure that the multimeter shows 100 Ohms or less.
SUBTASK 860-007
Release the SYS #2 IN AIR button.
SUBTASK 420-001
Install the No. 1 and the No. 2 LRRA R/Ts. To install them, do this
task: Low Range Radio Altimeter (LRRA) Receiver/Transmitter (R/T)
Installation (AMM TASK 34-33-21-400-801 p401).
Operational Test
(9)
G.
(1)
SUBTASK 860-008
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 710-004
Do this task: Low Range Radio Altimeter (LRRA) System - Operational
Test (AMM TASK 34-33-00-710-801 p501).
LRRA Antenna Coaxial Cable Test
(2)
H.
(1)
(2)
SUBTASK 860-009
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
SUBTASK 730-005
Hold the detector on the transmit antenna for the No. 1 radio
altimeter system.
(a) Make sure the multimeter shows 30 mVDC or more than 30 mVDC.
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(3)
(4)
(5)
(6)
(7)
(8)
(9)
SUBTASK 730-006
Cover the receive antenna for the No. 1 radio altimeter system with
material, eccosorb AN74.
(a) Make sure the radio altitude display on the captain's EFIS
display is blank.
SUBTASK 860-010
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
SUBTASK 860-011
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 730-007
Hold the detector on the transmit antenna for the No. 2 radio
altimeter system.
(a) Make sure the multimeter shows 30 mVDC or more than 30 mVDC.
SUBTASK 730-008
Cover the receive antenna for the No. 2 radio altimeter system with
material, eccosorb AN74.
(a) Make sure the radio altitude display on the first officer's
EFIS display is blank.
SUBTASK 860-012
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 860-013
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
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LOW RANGE RADIO ALTIMETER ANTENNA - REMOVAL/INSTALLATION
________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the low range radio altimeter (LRRA) antenna
(2) An installation of the LRRA antenna.
B. There are four LRRA antennas installed on the bottom of the airplane.
The No. 1 (M1737) and No. 2 (M1738) transmit antennas are the outer
antennas. The No. 1 (M1739) and the No. 2 (M1740) receive antennas are
the inner antennas.
TASK 34-33-11-000-801
2.
________________________________________________
Low
Range Radio Altimeter (LRRA) Antenna Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 123 Area Below Forward Cargo Compartment - Left
(b) 124 Area Below Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
B. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 080-001
Remove the LRRA antenna [1]:
(a) Remove the bolts [2] from the antenna [1].
CAUTION:
_______
(b)
(c)
(d)
(e)
LOWER THE ANTENNA ONLY AS FAR AS NECESSARY TO DISCONNECT
THE COAXIAL CONNECTOR. DAMAGE TO THE CABLE CAN OCCUR IF
YOU PULL THE CABLE.
Lower the antenna [1] until you can get access to the coaxial
connector [4].
Disconnect the coaxial connector [4] from the antenna [1].
Remove the O-Ring [3] from the antenna base.
Remove the antenna [1].
TASK 34-33-11-400-801
3.
_____________________________________________________
Low
Range Radio Altimeter (LRRA) Antenna Installation (Fig. 401)
A. References
(1) AMM TASK 20-30-84-910-801 p201, Final Cleaning of Metal Prior to
Painting (Series 84)
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LRRA
TRANSMIT
ANTENNA
LRRA
RECEIVE
ANTENNAS
SEE
SEE
A
LRRA
TRANSMIT
ANTENNA
SEE
A
A
[4] COAXIAL
CONNECTOR
FWD
[3] O-RING
AIRPLANE SKIN
[1] LRRA ANTENNA
[2] BOLT
(4 LOCATIONS)
LRRA ANTENNA
(EXAMPLE, 4 LOCATIONS)
A
Low Range Radio Altimeter (LRRA) Antenna Installation
Figure 401
F80235
34-33-11-990-801
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(2)
AMM TASK 51-21-31-350-801 p701, Removal and Control of Corrosion for
Aluminum and Aluminum Alloys
(3) AMM TASK 51-21-41-370-802 p701, Apply Alodine 600, 1200 or 1200S
Solution
(4) AMM TASK 51-21-91-620-802 p701, Apply the Corrosion Inhibiting
Compound
(5) SWPM 20-20-00
B. Equipment
(1) Ohmeter (or alternative tool)
(a) C15292 Ohmeter - Electrical Bonding (Model T477W) (recommended)
Avtron Manufacturing, Inc. (Vendor Code 01014)
7900 E. Pleasant Valley Road, Independence OH 44131
(b) MODEL 1010-A Ohmeter - Micro, Autoranging/Autotest, 10 Micro
Ohms to 200 Ohms, Accuracy: 0.05% (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(c) M-1 Ohmeter - Micro-ohm, Automatic, Stores 128 Readings, RS-232
Data Port, Range: 0.01 - 19.999 Milliohms, 4 1/2 Digit Display,
Accy: 0.1% of Readings (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
C. Consumable Materials
(1) B01004 Solvent, Final Cleaning of Metal Prior to Painting (AMM
20-30-84/201 or SOPM 20-30-84) - Series 84
(2) D00015 Grease, Aircraft bearing - BMS3-24
(3) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(4) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Antenna
¦ 34-33-11
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 123 Area Below Forward Cargo Compartment - Left
(b) 124 Area Below Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
F. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
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(b)
(2)
Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 110-001
Clean the airplane mating surface:
WARNING:
_______
(a)
(b)
(c)
(3)
(4)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON
YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS.
SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE
FLAMMABLE OR HARMFUL TO THE ENVIRONMENT. REFER TO PRODUCT
MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS
FOR PROPER HANDLING PROCEDURES.
Clean the airplane mating surface with a cloth, BMS15-5 that is
moist with solvent, Series 84(AMM TASK 20-30-84-910-801 p201).
Use a cloth, BMS15-5 and clean the mating surface again.
Do these steps until the mating surface is clean and dry.
SUBTASK 300-001
If the airplane mating surface has corrosion, do these steps to
prepare the airplane mating surface:
(a) Remove the corrosion from the airplane mating surface. To
remove the corrosion, do this task: Removal and Control of
Corrosion for Aluminum and Aluminum Alloys
(AMM TASK 51-21-31-350-801 p701).
(b) Apply a layer of alodine coating to the airplane mating
surface. To apply the coating, do this task: Apply Alodine
600, 1200 or 1200S Solution (AMM TASK 51-21-41-370-802 p701).
SUBTASK 420-001
Install the LRRA antenna [1]:
(a) Apply compound, BMS3-23, to the antenna base. To apply the
compound, BMS3-23, do this task: Apply the Corrosion
Inhibiting Compound (AMM TASK 51-21-91-620-802 p701).
(b) Put the O-Ring [3] on the antenna base.
(c) Connect the coaxial cable to the antenna [1].
(d) Put a thick layer of grease, BMS3-24, around the connector on
the antenna base.
1) Make sure the layer of grease, BMS3-24, is above the screws
ends that show for the antenna connector.
2) Make sure the grease, BMS3-24, extends approximately 1 inch
up the antenna connector.
(e) Put the antenna [1] in the correct position on the airplane
surface.
(f) Install the three of the four bolts [2].
1) Make sure you manually tighten the bolts to 20-25
pound-inches (2.3-2.8 newton-meters).
EFFECTIVITY
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(5)
SUBTASK 760-001
Measure the resistance between the LRRA antenna baseplate and the
airplane skin with an ohmeter, C15292 (SWPM 20-20-00).
NOTE:
____
(a)
(6)
Use the empty bolt hole to get access to the antenna
baseplate.
Make sure the resistance is less than 0.001 ohm.
SUBTASK 420-002
Install the last bolt [2].
(a) Make sure you tighten the bolt [2] to 20-25 pound-inches
(2.3-2.8 newton-meters).
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
Installation Test
(7)
G.
(1)
(2)
(3)
SUBTASK 860-004
Set the SOURCE switch on the instrument switching module to the AUTO
position.
SUBTASK 710-001
Make sure the captain's primary EFIS display shows -4 feet |2 feet.
SUBTASK 710-002
Make sure the first officer's primary EFIS display shows -4 feet |2
feet.
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LRRA RECEIVER/TRANSMITTER - REMOVAL/INSTALLATION
________________________________________________
1.
General
_______
A. This procedure has two tasks:
(1) A removal of the low range radio altimeter (LRRA)
receiver/transmitter (R/T)
(2) An installation of the LRRA R/T.
B. The two LRRA R/Ts are in the main equipment center. The No. 1 LRRA R/T,
is on the E3 electronics equipment rack, shelf No. 1. The No. 2 LRRA R/T
is on the E3 electronics equipment rack, shelf No. 2.
TASK 34-33-21-000-801
2.
___________________________________________________________________
Low
Range Radio Altimeter (LRRA) Receiver/Transmitter (R/T) Removal
(Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center.
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE LRRA
R/T [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE LRRA R/T [1].
To remove the LRRA R/T [1], do this task:
(AMM TASK 20-10-07-000-801 p201).
EFFECTIVITY
E/E Box Removal
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ELECTRONIC EQUIPMENT
RACKS, E2, E3 AND E4
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] LEFT RA RECEIVER/
TRANSMITTER (E3-2)
[1] RIGHT RA RECEIVER/
TRANSMITTER (E3-1)
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACKS, E2, E3 AND E4
A
Low Range Radio Altimeter (LRRA) Receiver-Transmitter
Installation
Figure 401
G02071
34-33-21-990-801
EFFECTIVITY
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TASK 34-33-21-400-801
3.
________________________________________________________________________
Low
Range Radio Altimeter (LRRA) Receiver/Transmitter (R/T) Installation
(Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
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¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
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¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Transceiver
¦ 34-33-21
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 420-001
CAUTION:
_______
(2)
(3)
(4)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE LRRA
R/T [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE LRRA R/T [1].
To install the LRRA R/T [1], do this task:
(AMM TASK 20-10-07-400-801 p201).
E/E Box Installation
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
(b) Circuit Breaker Panel, P18-1:
EFFECTIVITY
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E.
1) 18B4
Installation Test
RADIO NAVIGATION RADIO ALTM 1
(1)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-005
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(3)
SUBTASK 710-001
Make sure -4 |2 feet radio altitude is displayed on the captain's
and the first officer's EFIS displays.
(4)
SUBTASK 860-006
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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WEATHER RADAR (WXR) SYSTEM - ADJUSTMENT/TEST
____________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) An Operational Test
(2) A System Test.
TASK 34-43-00-710-802
2.
_____________________________________________
Weather
Radar (WXR) System - Operational Test (Fig. 501)
A. General
(1) The operational test uses the TEST MODE switch on the WXR control
panel. In the TEST mode, the self test circuits monitor the
performance of the weather radar system.
(2) During the self test the weather radar system operates as follows:
(a) It makes a test pattern which finds most system failures
without test equipment.
(b) AIRPLANES WITHOUT PREDICTIVE WINDSHEAR;
The receiver/transmitter operates for 1 seconds.
(c) AIRPLANES WITH PREDICTIVE WINDSHEAR;
The receiver/transmitter operates for 6 seconds.
(d) A special test pattern is made on the Captain's (First
Officer's) Display Units (DU).
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
D. Procedure
(1)
(2)
SUBTASK 860-062
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-063
Make sure the air data inertial reference unit (ADIRU) is aligned to
the NAV mode. To align it, do this task: Air Data Inertial
Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
(a) Make sure the ATT flags on the captains and first officers
EADIs are not in view.
EFFECTIVITY
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(3)
(4)
(5)
SUBTASK 860-065
Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 860-190
Set the switches on the captain's and the first officer's EFIS
control panels as follows:
(a) Set the left and right ADF/VOR control to OFF.
(b) Set the mode selector to VOR.
SUBTASK 710-009
Select WX on the WXR control panel.
(a) Set the SOURCE switch on the instrument switching module to the
ALL ON 1 (ALL ON 2) position.
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR
REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY
WHILE FUEL IS ADDED OR REMOVED IN AN AREA 200 FEET (61
METERS) OR LESS FROM THE ANTENNA. THIS CAN CAUSE AN
EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR
LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF
ENERGY CAN CAUSE INJURIES TO PERSONS.
(b)
(c)
Push the WXR switch on the captain's (first officer's) EFIS
control panel to the ON position.
Select TEST on the WXR control panel.
NOTE:
____
1)
2)
(6)
The conditions will take between 3 and 15 seconds to
show.
AIRPLANES WITH PREDICTIVE WINDSHEAR ACTIVE;
Make sure the aural warning "MONITOR RADAR DISPLAY" and "GO
AROUND, WINDSHEAR AHEAD, WINDSHEAR AHEAD,WINDSHEAR AHEAD"
are heard.
Make sure WXR TEST display on the captain's and first
officer's display unit (DU) is as shown on Figure 501.
SUBTASK 860-229
If no more test are necessary, Open this circuit breaker and attach
a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
EFFECTIVITY
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WINDSHEAR
ICON
HALF
RANGE
MESSAGE
TEST
PASS
MESSAGE
MAGENTA
RED
YELLOW
WXR
TEST
20
GREEN
TEST
+15
ANTENNA
TILT
MESSAGE
TEST PASS DISPLAY
(EXAMPLE)
TEST
FAIL
FAIL
MESSAGES
WXR
FAIL
RT ANT CON ATT WEAK
TEST FAIL DISPLAY
(EXAMPLE)
WX TEST PASS/ DEFECTIVE
LRU(S)
TEST FAIL
(CYAN)
(YELLOW)
WXR
WXR
WXR
WXR
WXR
WXR
TEST
FAIL
FAIL
FAIL
FAIL
FAIL
BLANK
T/R
ANT
CTL
ATT
WEAK
CONDITION
WXR TEST
PATTERN
TEST PASSED
ON
RECEIVER/TRANSMITTER FAULT OFF/ON
ANTENNA FAULT
OFF
CONTROL PANEL FAULT
OFF
ON
ATTITUDE INPUT FAULT
ON
CALIBRATION FAULT
TEST PASS/TEST FAIL MESSAGES
Weather Radar Test and Fault Display
Figure 501
K31950
34-43-00-990-803
EFFECTIVITY
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TASK 34-43-00-730-802
3.
________________________________________
Weather
Radar (WXR) System - System Test
A. General
(1) The system test supplies a full test of the weather radar (WXR)
system. Tests that show radar video, the airplane should be pointed
so the antenna sector can scan hills, mountains or various height in
the distance.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(4) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
C. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
D. Prepare for the System Test
(1)
SUBTASK 580-001
Point the airplane away from all large metal objects and to an open
area.
NOTE:
____
(2)
(3)
(4)
The antenna scan can include hills or mountains at different
heights in the distance.
SUBTASK 940-001
Set the warning lights around the front of the airplane in an arc 50
feet from the radome.
SUBTASK 860-161
Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 860-073
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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(5)
(6)
SUBTASK 860-162
Make sure the air data inertial reference unit (ADIRU) is aligned to
the NAV mode. To align it, do this task: Air Data Inertial
Reference System - Alignment from the FMC CDU
(AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
(a) Make sure the ATT flags on the captains and first officers
EADIs are not in view.
SUBTASK 860-163
Set the switches on the captain's and the first officer's EFIS
control panels as follows:
(a) Set the range selector to 40.
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR
REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY
WHILE FUEL IS ADDED OR REMOVED IN AN AREA 200 FEET (61
METERS) OR LESS FROM THE ANTENNA. THIS CAN CAUSE AN
EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR
LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF
ENERGY CAN CAUSE INJURIES TO PERSONS.
(b)
(c)
(d)
(e)
(7)
Push the WXR switch to the ON position.
Set the left and right ADF/VOR control to OFF.
Set the mode selector to VOR.
Push the CTR push-button as required.
1) Make sure the Captain and First Officer display unit (DU)s
are in expanded scale.
SUBTASK 860-164
AIRPLANES WITH COLLINS 622-5129-105 CONTROL PANELS;
Set the controls on the WXR control panel as follows:
(a) Push the WX mode switch ON.
(b) Turn the GAIN knob fully Counter Clockwise to the CAL position.
(c) Make sure the IDNT button is OFF.
(d) Turn the TILT knob to 0 degrees.
(e) Push the STAB button ON.
EFFECTIVITY
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E.
Mode Test
(1)
SUBTASK 730-116
AIRPLANES WITH COLLINS 622-5129-105 CONTROL PANELS;
Set the switches on the WXR control panel as follows:
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR
REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY
WHILE FUEL IS ADDED OR REMOVED IN AN AREA 200 FEET (61
METERS) OR LESS IN FRONT OF THE ANTENNA. THIS CAN CAUSE
AN EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR
LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF
ENERGY CAN CAUSE INJURIES TO PERSONS.
(a)
Make sure the mode messages are shown on the captain's (First
Officer's) display unit (DU) as given below
1) Push the mode WX button.
a) Make sure that WX shows on the Captain's and First
officer's display unit (DU).
2) Push the mode WX+T button.
a) Make sure that WX+T shows on the Captain's and First
officer's display unit (DU).
3) Push the mode MAP.
a) Make sure that MAP shows on the Captain's and First
officer's display unit (DU).
4) Push the mode STAB button.
a) Make sure that STAB shows on the Captain's and First
officer's display unit (DU).
EFFECTIVITY
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F.
Gain Test
SUBTASK 700-011
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR REMOVED
FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY WHILE FUEL IS
ADDED OR REMOVED IN AREA 200 FEET (61 METERS) OR LESS OF THE
ANTENNA. THIS CAN CAUSE AN EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR LESS
FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF ENERGY CAN
CAUSE INJURY TO PERSONS.
(1)
Do the Gain Test.
NOTE:
____
(a)
The full gain test will not be possible when there are no
radar targets from weather, mountains or large buildings.
When there are no targets, only the gain message part of this
test will be done.
AIRPLANES WITH COLLINS 622-5129-105 CONTROL PANEL;
Set the switches on the WXR control panel as follows:
1) Select MAP mode switch on the WXR control panel.
2) Turn the TILT control to get good radar targets on each
display unit (DU).
3) Turn the GAIN control as necessary to get a middle level of
radar targets.
a) Make sure the captain's (first officer's) display unit
(DU) mode message reads VAR/MAP.
4) Turn the GAIN control counterclockwise.
a) Make sure the radar targets decrease in intensity on
each display unit (DU).
5) Turn the GAIN control clockwise.
a) Make sure the radar returns increase in intensity on
each display unit (DU).
6) Set the GAIN control to the full clockwise (calibrate)
position.
a) Make sure VAR is OFF on the captains and first officers
display unit (DU).
7) Turn the LEFT TILT controls to 0 degrees.
EFFECTIVITY
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G.
Antenna Tilt Test
(1)
SUBTASK 720-003
Do the antenna tilt test.
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR
REMOVED FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY
WHILE FUEL IS ADDED OR REMOVED IN AREA 200 FEET (61
METERS) OR LESS OF THE ANTENNA. THIS CAN CAUSE AN
EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR
LESS FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF
ENERGY CAN CAUSED INJURY TO PERSONS.
(a)
(b)
(c)
(d)
(e)
(f)
(g)
(h)
(i)
(j)
Push the WX MODE switches on the WXR control panel.
Set the range switch on the EFIS control panel to adjust the
radar returns in the center of each display unit (DU).
Set the WX mode on the weather radar control panel.
Turn the TILT control to get good radar targets on the
captain's (first officer's) display unit (DU).
1) Make sure the tilt messages on the captain's display unit
(DU) shows the correct tilt angle |0.5 degrees.
Turn the TILT control in steps from 0 to +4.75 degrees.
1) Make sure the tilt messages on the captain's (first
officer's) display unit (DU) show the correct tilt angle |1
degree.
2) Make sure the intensity of the close-in targets on the
captain's (first officer's) display unit (DU) decrease.
Turn the antenna TILT control in steps from +5 to 15.00
degrees.
1) Make sure the tilt messages on the captain's (first
officer's) display unit (DU) show the correct tilt angle |2
degree.
Turn the TILT control to 0 degree.
Turn the TILT control in steps from 0 to -4.75 degrees.
1) Make sure the tilt messages on the captain's (first
officer's) display unit (DU) show the correct tilt angle |1
degree.
2) Make sure the intensity of the close-in targets on the
captain's (first officer's) display unit (DU) increase.
Turn the antenna TILT control in steps from -5 to 15.00
degrees.
1) Make sure the tilt messages on the captain's (first
officer's) display unit (DU) show the correct tilt angle |2
degrees.
Turn the TILT control to 0 degree.
EFFECTIVITY
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H.
Ground Clutter Suppression Test
SUBTASK 730-137
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR REMOVED
FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY WHILE FUEL IS
ADDED OR REMOVED IN AREA 200 FEET (61 METERS) OR LESS OF THE
ANTENNA. THIS CAN CAUSE AN EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR LESS
FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF ENERGY CAN
CAUSE INJURY TO PERSONS
(1)
I.
Do the ground clutter suppression test.
(a) AIRPLANES WITH 622-5129-105 CONTROL PANELS;
Do the steps that follow:
1) Push the WX switch on the Weather Radar Control Panel.
2) Turn the TILT control on the WXR control panel to get a
ground target on the Captain's or First Officer's display
unit (DU).
3) Push the IDENT switch on the Weather Radar Control Panel.
a) Make sure the ground targets do not show on the display
unit (DU).
4) Push the IDENT switch on the Weather Radar Control Panel.
a) Make sure the ground targets show on the display unit
(DU).
Stabilization Test
SUBTASK 860-131
WARNING:
_______
DO NOT OPERATE THE WEATHER RADAR WHILE FUEL IS ADDED OR REMOVED
FROM THE AIRPLANE. DO NOT TRANSMIT RF ENERGY WHILE FUEL IS
ADDED OR REMOVED IN AREA 200 FEET (61 METERS) OR LESS OF THE
ANTENNA. THIS CAN CAUSE AN EXPLOSION.
WARNING:
_______
MAKE SURE NO PERSONS ARE IN THE AREA 15 FEET (5 METERS) OR LESS
FROM THE ANTENNA WHEN IT TRANSMITS RF ENERGY. RF ENERGY CAN
CAUSE INJURY TO PERSONS.
(1)
Do the Stabilization Test.
(a) Push the WX MODE switch on the WXR control panel.
1) Make sure that the WXR message on the two DUs are shown.
(b) Push the STAB switch on the WXR control panel to remove
stabilization.
1) Make sure the WXR and STAB messages show on the DUs.
(c) Push the STAB switch on the WXR control panel to the on
position.
1) Make sure the WXR and STAB messages do not show on the DUs.
(d) Set these switches on the inertial system display unit (ISDU)
as follows:
1) Set the SYS DSPL switch to the L position.
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2)
J.
Set and hold the DSPL SEL switch to the TEST position.
a) Make sure the WXR ATT message shows on each DU.
3) Release the DSPL SEL switch to the TK/GS position.
a) Make sure the WXR ATT message does not show on the DUs.
(e) Set the IRS select switch to the BOTH ON R position.
(f) Set these switches on the ISDU as follows:
1) Set the SYS DSPL switch to the R position.
2) Set and hold the DSPL SEL switch to the TEST position.
a) Make sure the WXR ATT message shows on each DU.
3) Release the DSPL SEL switch to the TK/GS position.
a) Make sure the WXR ATT message does not show on the DUs.
4) Set the SYS DSPL switch to the L position.
WXR System Displays Test
(1)
SUBTASK 710-022
Select WX on the WXR control panel.
(2)
SUBTASK 710-023
Set the SOURCE switch on the instrument switching module to the ALL
ON 1 position.
(3)
SUBTASK 710-027
Push the WXR power switch on the Captain's EFIS control panel to the
ON position.
(4)
SUBTASK 710-024
Select TEST on the WXR control panel.
(a) Make sure these indications occur:
(b)
NOTE:
____
Read through these indications before you do the test.
If necessary, you can do the test more than once to do a
check of the indications.
NOTE:
____
Anytime the PWS automatic activation criteria are active
or the airplane is in the air, no flight deck effects of
the PWS will show when you do the WXR test. If the WXR
is in the test mode and an actual PWS alert occurs, the
WXR Transceiver (XCVR) switches to the WXR mode and
shows a WXR return and PWS icon data on the map display
with the WXR mode annunciation. As a result, no valid
PWS icons will show with the WXR TEST pattern. If the
mode switch on the WXR control panel is still in the
TEST position, the WXR will go back to the test pattern
on the map display when the PWS alert stops.
NOTE:
____
All times are approximate.
Make sure these indications occur in 0-2 seconds:
1) Amber WINDSHEAR shows on the Captain's display unit (DU).
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2)
(c)
(d)
(e)
(5)
MONITOR RADAR DISPLAY is heard on the flight deck aural
warning speakers.
Make sure these indications occur in 6-9 seconds;
1) GO AROUND, WINDSHEAR AHEAD, (pause) WINDSHEAR AHEAD,
WINDSHEAR AHEAD is heard on the flight deck aural warning
speakers
2) Red WINDSHEAR shows on the Captain display unit (DU).
Make sure these indications occur in 9-12 seconds;
1) PWS FAIL shows ON the Captain's display.
2) WINDSHEAR SYS (Advisory) EICAS Message is ON.
After 15 seconds:
1) MAKE SURE the weather radar test display on the Captains
display unit (DU) is as follows (see Figure 501):
a) Make sure the tilt code on the DU reads 0.
b) Make sure a WXR TEST message shows.
c) Make sure the range arcs (marks) have equal space
between them.
d) Make sure the half range message shows in the center.
2) Turn the inner INBD DU BRT control knob on the captains
(first officers) instrument panel (P1/P3).
a) Make sure there is a change in intensity of the test
pattern on the captains INBD DU.
SUBTASK 710-025
Set the SOURCE switch on the instrument switching module to the ALL
ON 2 position.
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(6)
SUBTASK 710-026
Push the WXR power switch on the First Officers's EFIS control panel
to the ON position.
(a) Make sure these indications occur:
(b)
(c)
(d)
(e)
NOTE:
____
Read through these indications before you do the test.
If necessary, you can do the test more than once to do a
check of the indications.
NOTE:
____
Anytime the PWS automatic activation criteria are active
or the airplane is in the air, no flight deck effects of
the PWS will show when you do the WXR test. If the WXR
is in the test mode and an actual PWS alert occurs, the
WXR Transceiver (XCVR) switches to the WXR mode and
shows a WXR return and PWS icon data on the map display
with the WXR mode annunciation. As a result, no valid
PWS icons will show with the WXR TEST pattern. If the
mode switch on the WXR control panel is still in the
TEST position, the WXR will go back to the test pattern
on the map display when the PWS alert stops.
NOTE:
____
All times are approximate.
Make sure these indications occur in 0-2 seconds:
1) Amber WINDSHEAR shows on the First Officers display unit
(DU).
2) MONITOR RADAR DISPLAY is heard on the flight deck aural
warning speakers.
Make sure these indications occur in 6-9 seconds;
1) GO AROUND, WINDSHEAR AHEAD, (pause) WINDSHEAR AHEAD,
WINDSHEAR AHEAD is heard on the flight deck aural warning
speakers
2) Red WINDSHEAR shows on the First Officer display unit (DU)
Make sure these indications occur in 9-12 seconds;
1) PWS FAIL shows on the First Officers display unit (DU).
2) WINDSHEAR SYS (Advisory) EICAS Message is ON
After 15 seconds:
1) MAKE SURE the weather radar test display on the First
officer's display unit (DU) is as follows (see Figure 501):
a) Make sure the tilt code on the DU reads 0.
b) Make sure a WXR TEST message shows.
c) Make sure the range arcs (marks) have equal space
between them.
d) Make sure the half range message shows in the center.
2) Turn the inner INBD DU BRT control knob on the captains
(first officers) instrument panel (P1/P3).
a) Make sure there is a change in intensity of the test
pattern on the captains (first officers) INBD DU.
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SUBTASK 860-230
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(a) Make sure the test pattern stays on the Captain's and First
Officers display unit (DU).
Put the Airplane Back to Its Usual Condition
(7)
K.
(1)
SUBTASK 860-169
Push the WXR switch on the captain's and the first officer's EFIS
control panels to the off position.
(2)
SUBTASK 860-170
If the air data inertial reference unit (ADIRU) is not necessary,
set the ADIRU switch to the OFF position.
(3)
(4)
SUBTASK 860-171
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 860-143
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
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WEATHER RADAR ANTENNA - REMOVAL/INSTALLATION
____________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the weather radar antenna [4] flat plate.
(2) A removal of the weather radar antenna drive unit [5].
(3) An installation of the weather radar antenna [4] flat plate.
(4) An installation of the weather radar antenna drive unit [5].
(5) An installation test of the weather radar antenna [4].
B. The weather radar antenna [4] is located in the radome.
TASK 34-43-11-000-801
2.
________________________________________
Weather
Radar Antenna Flat Plate Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 111 Radome
(2) Access Panels
(a) 111
Radome
B. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 020-001
Do these steps to open the Radome, 111:
(a) Remove the screws that attach the Radome, 111, to the fuselage
bulkhead.
WARNING:
_______
(b)
DO NOT OPEN THE RADOME IF THE WIND IS MORE THAN 15 KNOTS.
THE RADOME CAN MOVE QUICKLY IF YOU OPEN THE RADOME IN THE
WIND. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Open the Radome, 111.
NOTE:
____
(3)
Install support rods on each side to hold the Radome,
111, in the open position.
SUBTASK 020-002
Do these steps to remove the weather radar antenna [4] flat plat:
CAUTION:
_______
(a)
DURING THE ANTENNA FLAT PLATE [4] REMOVAL, MAKE SURE THE
ANTENNA DRIVE UNIT [4] DOES NOT MOVE. REMOVE THE ANTENNA
FLAT PLATE CAREFULLY TO PREVENT DAMAGE TO THE EQUIPMENT.
Remove the four screws [9] and washers [10].
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NOSE RADOME,
111
WEATHER RADAR
ANTENNA
SEE
A
[5] ANTENNA
DRIVE
UNIT
FORWARD ACCESS
DOOR, 112A
SEE
[3] BOLTS
(4 LOCATIONS)
D
[6] ELECTRICAL
CONNECTOR
[4] ANTENNA
FLAT PLATE
[2] WAVEGUIDE
QUICK
DISCONNECT
[1] WAVEGUIDE
ASSEMBLY
(RIGID AND
FLEXIBLE)
WEATHER RADAR ANTENNA
A
Weather Radar Antenna Installation
Figure 401 (Sheet 1)
G42389
34-43-11-990-801
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CAUTION:
_______
FLAT PLATE IS COUNTERBALANCED
BY A TORQUE SPRING. PREVENT
ROTOR ASSEMBLY MOVEMENT WHEN
YOU REMOVE THE FLAT PLATE FROM
THE ROTOR ASSEMBLY.
[11] FLAT PLATE
WAVEGUIDE
FLANGE
[12] WAVEGUIDE
FLANGE
[10] WASHER
(4 LOCATIONS)
[9] SCREW
(4 LOCATIONS)
[13] FLAT PLATE
RING MOUNT
[5] ANTENNA DRIVE
UNIT
[8] WASHER
(8 LOCATIONS)
[7] SCREW
(8 LOCATIONS)
Weather Radar Antenna Installation
Figure 401 (Sheet 2)
G40608
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(b)
Remove the eight screws [7] and washers [8] from the flat plate
ring mount [13].
WARNING:
_______
(c)
(d)
DURING A ANTENNA FLAT PLATE [4] REMOVAL, USE TWO PERSONS
AND A SAFELY INSTALLED WORKSTAND. THE ANTENNA FLAT PLATE
[4] WEIGHS APPROXIMATELY 7 POUNDS (3.2 KILOS). REMOVE THE
ANTENNA FLAT PLATE [4] CAREFULLY TO PREVENT INJURY TO
PERSON OR DAMAGE TO THE EQUIPMENT.
Remove the antenna [4] flat plate [4].
Install dust caps on end of the waveguide flange [12].
TASK 34-43-11-400-801
3.
_____________________________________________
Weather
Radar Antenna Flat Plate Installation (Fig. 401)
A. References
(1) AMM TASK 34-43-11-700-801 p401, Weather Radar Antenna Installation
Test
B. Parts
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¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
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¦ 401
4 ¦ Antenna
¦ 34-43-11
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 111 Radome
(2) Access Panels
(a) 111
Radome
D. Installation Procedure
(1)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
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(2)
SUBTASK 420-001
If the Radome, 111 is not open, do these steps to open the Radome,
111:
(a) Remove the screws that attach the Radome, 111, to the fuselage
bulkhead.
WARNING:
_______
(b)
DO NOT OPEN THE RADOME IF THE WIND IS MORE THAN 15 KNOTS.
THE RADOME CAN MOVE QUICKLY IF YOU OPEN THE RADOME IN THE
WIND. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Open the Radome, 111.
NOTE:
____
(3)
SUBTASK 420-002
Do these steps to install the weather radar antenna [4] flat plate.
(a) Remove dust cap from the waveguide flange [12].
WARNING:
_______
(b)
(c)
(d)
(e)
(f)
(4)
Install support rods on each side to hold the Radome,
111, in the open position.
USE TWO PERSONS AND A WORKSTAND DURING THE INSTALLATION OF
THE ANTENNA FLAT PLATE [4]. THE ANTENNA FLAT PLATE [4]
WEIGHS APPROXIMATELY 7 POUNDS (3.2 KILOS). INSTALL THE
ANTENNA FLAT PLATE [4] CAREFULLY TO PREVENT INJURY TO YOU
OR DAMAGE TO THE EQUIPMENT.
Install the antenna [4] flat plate to the flat plate ring mount
[13].
Install the eight screws [7] and washers [8] on the flat plate
ring mount [13].
Tighten the screws [7] and [8] to between 24 and 33
pounds-inches (2.7-3.7 newton-meters).
Align the waveguide flange [12] to flat plate waveguide flange
[11].
Install the four screws [9] and washers [10].
SUBTASK 020-003
Do this task: Weather Radar Antenna Installation Test
(AMM TASK 34-43-11-700-801 p401).
TASK 34-43-11-000-802
4.
________________________________________
Weather
Radar Antenna Drive Unit Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-44-000-801 p401, Lockwires Removal
B. Access
(1) Location Zones
(a) 111 Radome
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(2)
C.
Access Panels
(a) 111
Radome
Removal Procedure
(1)
(2)
SUBTASK 860-004
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 020-004
Do these steps to open the Radome, 111:
(a) Remove the screws that attach the Radome, 111, to the fuselage
bulkhead.
WARNING:
_______
(b)
DO NOT OPEN THE RADOME IF THE WIND IS MORE THAN 15 KNOTS.
THE RADOME CAN MOVE QUICKLY IF YOU OPEN THE RADOME IN THE
WIND. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Open the Radome, 111.
NOTE:
____
(3)
Install support rods on each side to hold the Radome,
111, in the open position.
SUBTASK 020-005
Do these steps to remove the weather radar drive unit [5]:
(a) Release the waveguide quick disconnect [2] to disconnect the
waveguide [1].
(b) Disconnect the electrical connector [6].
(c) If the bolts [3] have a drilled hole, remove the twisted
lockwires (AMM TASK 20-10-44-000-801 p401).
(d) Remove the two bottom bolts [3] on the drive unit [5].
(e) Loosen the top two bolts [3] on the drive unit [5].
WARNING:
_______
(f)
(g)
(h)
USE TWO PERSONS AND A WORKSTAND DURING THE REMOVAL OF THE
ANTENNA DRIVE UNIT [5]. THE ANTENNA DRIVE UNIT [5] WEIGHS
APPROXIMATELY 18 POUNDS (8.2 KILOS). REMOVE THE ANTENNA
DRIVE UNIT [5] CAREFULLY TO PREVENT INJURY TO PERSON OR
DAMAGE TO EQUIPMENT.
Lift the drive unit [5] up and forward to remove the drive unit
[5] from the two top bolts [3].
Install dust caps to the ends of the waveguide [1].
Install dust cap to the electrical connector [6] if you do not
replace the antenna drive unit [5] immediately.
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TASK 34-43-11-400-802
5.
_____________________________________________
Weather
Radar Antenna Drive Unit Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-44-400-801 p401, Lockwires Installation
(2) AMM TASK 34-43-11-700-801 p401, Weather Radar Antenna Installation
Test
(3) SWPM 20-20-00
B. Parts
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¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
5 ¦ Drive unit
¦ 34-43-11
01
25 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 111 Radome
(2) Access Panels
(a) 111
Radome
D. Installation Procedure
(1)
(2)
SUBTASK 860-005
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 420-003
If the Radome, 111, is not opened, do these steps to open the
Radome, 111:
(a) Remove the screws that attach the Radome, 111, to the fuselage
bulkhead.
WARNING:
_______
(b)
DO NOT OPEN THE RADOME IF THE WIND IS MORE THAN 15 KNOTS.
THE RADOME CAN MOVE QUICKLY IF YOU OPEN THE RADOME IN THE
WIND. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Open the Radome, 111.
NOTE:
____
Install support rods on each side to hold the Radome,
111, in the open position.
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(3)
SUBTASK 420-004
Do these steps to install the weather radar antenna drive unit [5]:
(a) Remove the dust caps from the waveguide [1] and the electrical
connector [6].
(b) Install the base of the weather radar antenna drive unit [5] to
the two top bolts [3].
(c) Install the two bottom bolts [3].
(d) Tighten all four bolts [3] to 220-240 pound-inches (24.9-27.1
newton-meters).
(e) If the bolts [3] have a drilled hole, install a double twisted
lockwires, (AMM TASK 20-10-44-400-801 p401).
(f) Install the electrical connector [6].
(g) Connect the waveguide [1] to the antenna at the waveguide quick
disconnect [2].
NOTE:
____
(4)
(5)
Make sure you install the O-ring gasket.
SUBTASK 020-006
Do an electrical bonding test between the airplane structure and the
weather radar antenna (SWPM 20-20-00).
(a) Make sure the resistance is less than 0.001 ohms.
SUBTASK 020-007
Do this task: Weather Radar Antenna Installation Test
(AMM TASK 34-43-11-700-801 p401).
TASK 34-43-11-700-801
6.
_______________________________________
Weather
Radar Antenna Installation Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
B. Access
(1) Location Zones
(a) 111 Radome
(2) Access Panels
(a) 111
Radome
C. Installation Test
(1)
SUBTASK 860-007
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
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(2)
(3)
(4)
(5)
SUBTASK 860-008
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 710-001
Do this test of the weather radar antenna:
SUBTASK 710-002
Make sure the air data inertial reference system is aligned. To
align it, do this task: Air Data Inertial Reference System Alignment from the FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
SUBTASK 710-003
Push the WXR switch on the Captain's EFIS Control Panel to turn on
the weather radar system.
SUBTASK 860-009
Turn the TILT control knob on the weather radar control panel, P8,
to +15 and -15 degrees.
(a) Make sure the tilt position that shows in the tilt field on the
display unit agrees with the tilt position on the weather radar
control panel.
Put The Airplane Back to Its Usual Condition
(6)
D.
(1)
(2)
SUBTASK 860-011
Set the TILT control knob on the WXR control panel to 0.
SUBTASK 860-012
Push the WXR switch on the captain's EFIS control panel to turn off
the weather radar system.
(3)
SUBTASK 860-013
Remove the support rods that hold the Radome, 111, open.
(4)
SUBTASK 860-014
Close the Radome, 111.
(5)
SUBTASK 860-010
Install the screws that attach the Radome, 111, to the fuselage.
(6)
SUBTASK 860-015
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
EFFECTIVITY
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WEATHER RADAR WAVEGUIDE - REMOVAL/INSTALLATION
______________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the weather radar (WXR) waveguide
(2) An installation of the WXR waveguide.
B. The WXR waveguide is in the nose radome and in the lower nose
compartment.
TASK 34-43-21-000-801
2.
_____________________
WXR
Waveguide Removal (Fig. 401)
A. General
(1) You must do the Prepare for Removal section before any of the
waveguide assemblies are removed. You can remove one or all parts
of the waveguide when necessary.
B. References
(1) AMM TASK 34-43-41-000-801 p401, Weather Radar Receiver/Transmitter
Removal
C. Access
(1) Location Zones
(a) 111 Radome
(b) 112 Area Forward of Nose Landing Gear Wheel Well
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 111
Radome
(b) 112A
Forward Access Door
D. Prepare for Removal
(1)
(2)
(3)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 010-001
Open the Forward Access Door, 112A.
SUBTASK 020-001
For easier access to the waveguide, do this task: Weather Radar
Receiver/Transmitter Removal (AMM TASK 34-43-41-000-801 p401).
EFFECTIVITY
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MAINTENANCE MANUAL
NOSE RADOME
111
SEE
FWD ACCESS
DOOR 112A
SEE
D
A
ANTENNA
DRIVE UNIT
[1] WAVEGUIDE
ASSEMBLY
(RIGID AND
FLEXIBLE)
SEE
B
FWD
SEE
C
A
Weather Radar Waveguide Installation
Figure 401 (Sheet 1)
F84256
34-43-21-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
ANTENNA
DRIVE
UNIT
[2] QUICK-DISCONNECT
[1] WAVEGUIDE
ASSEMBLY
(RIGID AND
FLEXIBLE)
[4] SCREW
[5] WASHER
[6] NUT
FWD
[3] WAVEGUIDE
CLAMP
B
[1] WAVEGUIDE
ASSEMBLY
(RIGID AND
FLEXIBLE)
FWD
[7] SCREW
(7 LOCATIONS)
[9] PRESSURE
SEAL FLANGE
[10] GASKET
[8] SCREW
C
Weather Radar Waveguide Installation
Figure 401 (Sheet 2)
F86408
EFFECTIVITY
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[11] WAVEGUIDE
ASSEMBLY
(RIGID)
RECEIVER/
TRANSMITTER
SEE
E
FWD
D
[1] WAVEGUIDE
ASSEMBLY
(RIGID AND
FLEXIBLE)
[11] WAVEGUIDE
ASSEMBLY
(RIGID)
MOUNT
WAVEGUIDE
RECEIVER/
TRANSMITTER
[12] SCREW
[13] WASHER
(4 LOCATIONS)
[14] ROUND
GASKET
RECEIVER/
TRANSMITTER
MOUNT
FWD
E
Weather Radar Waveguide Installation
Figure 401 (Sheet 3)
F86675
EFFECTIVITY
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E.
Waveguide Assembly [1] Removal
SUBTASK 010-002
CAUTION:
_______
(1)
DO NOT OPEN THE NOSE RADOME IF THE WIND IS MORE THAN 15 KNOTS.
IF YOU OPEN THE NOSE RADOME IN A WIND, THE RADOME CAN MOVE
QUICKLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Open the Radome, 111:
(a) Remove the screws that attach the nose radome to the fuselage
bulkhead.
(b) Open the nose radome and hold it in the open position by the
installation of the support rods on each side.
SUBTASK 020-002
CAUTION:
_______
(2)
DO NOT LET THE WORKSTANDS HIT OR TOUCH THE WEATHER RADAR
ANTENNA OR OTHER RADOME EQUIPMENT. THIS CAN CAUSE DAMAGE TO
EQUIPMENT.
Remove waveguide assembly [1]:
(a) Remove the screws [12] and washers [13] that attach waveguide
assembly [1] to waveguide assembly [11](in lower nose
compartment).
(b) Release the quick disconnect [2] that holds waveguide assembly
[1] to the antenna drive unit.
(c) Do these steps at the pressure seal flange [9]:
1) Remove the screws [7] and screw [8].
NOTE:
____
Screw [8] is longer than the other screws.
a) Make a note of the location of screw [8].
Remove screw [4], washer [5], nut [6], and waveguide clamp [3].
Carefully remove waveguide assembly [1], with the gasket [10].
Remove round gasket [14] from one end of waveguide assembly
[1].
(g) Put dust caps on the ends of the waveguides.
Waveguide Assembly [11] Removal
(d)
(e)
(f)
F.
(1)
SUBTASK 020-003
Remove waveguide assembly [11]:
(a) Remove the screws [12] and washers [13] that attach waveguide
assembly [11] to the mount waveguide.
(b) If waveguide assembly [1] is installed (because you did not
remove it), then do this step:
1) Remove the screws [12] and washers [13] that attach
waveguide assembly [11] to waveguide assembly [1].
(c) Remove waveguide assembly [11].
(d) Make sure the round gasket [14] at each end of waveguide
assembly [11] is removed.
EFFECTIVITY
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(e)
Put dust caps on the ends of the waveguides.
TASK 34-43-21-400-801
3.
__________________________
WXR
Waveguide Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-43-00-710-802 p501, Weather Radar (WXR) System Operational Test
(3) AMM TASK 34-43-41-400-801 p401, Weather Radar Receiver/Transmitter
Installation
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Waveguide assy
¦ 34-43-21
01
50 ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
11 ¦ Waveguide assy
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 111 Radome
(b) 112 Area Forward of Nose Landing Gear Wheel Well
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 111
Radome
(b) 112A
Forward Access Door
D. Procedure
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
Waveguide Assembly [1] Installation
(1)
E.
SUBTASK 860-003
CAUTION:
_______
(1)
DO NOT OPEN THE NOSE RADOME IF THE WIND IS MORE THAN 15 KNOTS.
IF YOU OPEN THE NOSE RADOME IN A WIND, THE RADOME CAN MOVE
QUICKLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
EQUIPMENT.
Make sure the nose radome is open.
EFFECTIVITY
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MAINTENANCE MANUAL
SUBTASK 420-001
CAUTION:
_______
DO NOT LET THE WORKSTANDS HIT OR TOUCH THE WEATHER RADAR
ANTENNA OR OTHER RADOME EQUIPMENT. THIS CAN CAUSE DAMAGE TO
EQUIPMENT.
(2)
F.
Install waveguide assembly [1]:
(a) Remove the dust caps from the ends of the waveguides.
(b) Examine the waveguide assembly [1] for damage, dirt, and
moisture.
(c) Install a new gasket [10] on the pressure seal flange [9].
(d) Install a new round gasket [14] at one end of waveguide
assembly [1].
(e) Move waveguide assembly [1] through the hole in the forward
bulkhead and put in the correct position.
1) Make sure gasket [10] and round gasket [14] are correctly
installed.
(f) Install screws [7] and screw [8] to hold the pressure seal
flange [9] to the bulkhead.
1) Make sure the longer screw [8] is installed in the correct
location.
(g) Install the quick disconnect [2] that holds waveguide assembly
[1] to the antenna drive unit.
(h) Install the clamp [3], screw [4], washer [5], and nut [6].
1) Adjust the clamp to make sure it does not bend waveguide
assembly [1].
(i) If you did not remove waveguide assembly [11], then do this
step:
1) Install the screws [12] and washers [13] that attach
waveguide assembly [1] to waveguide assembly [11].
Waveguide Assembly [11] Installation
(1)
(2)
SUBTASK 420-002
Install waveguide assembly [11]:
(a) Remove the dust caps from the ends of the waveguides.
(b) Examine the waveguide assembly [11] for damage, dirt and
moisture.
(c) Make sure a new round gasket [14] is installed at each end of
waveguide assembly [11].
(d) Install the screws [12] and washers [13] that attach waveguide
assembly [11] to the mount waveguide.
(e) Install the screws [12] and washers [13] that attach waveguide
assembly [11] to waveguide assembly [1].
SUBTASK 420-003
If you removed the WXR receiver/transmitter, then do this task:
Weather Radar Receiver/Transmitter Installation
(AMM TASK 34-43-41-400-801 p401).
EFFECTIVITY
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(3)
(4)
SUBTASK 860-004
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 410-001
Close the Forward Access Door, 112A.
SUBTASK 410-002
Close the Radome, 111.
(a) Install the screws that attach the nose radome to the fuselage
bulkhead.
Installation Test
(5)
G.
(1)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 710-001
Do this task: Weather Radar (WXR) System - Operational Test
(AMM TASK 34-43-00-710-802 p501).
EFFECTIVITY
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A
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MAINTENANCE MANUAL
WEATHER RADAR RECEIVER/TRANSMITTER MOUNT - REMOVAL/INSTALLATION
_______________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the weather radar receiver/transmitter (R/T)
(2) An installation of the R/T mount [1].
B. The R/T mount [1] is in the lower nose compartment.
mount [1]
TASK 34-43-31-000-801
2.
________________________________________________
Weather
Radar Receiver/Transmitter Mount Removal (Fig. 401)
A. References
(1) AMM TASK 34-43-41-000-801 p401, Weather Radar Receiver/Transmitter
Removal
B. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 212 Flight Compartment - Right
(2) Access Panels
(a) 112A
Forward Access Door
C. Removal Procedure
(1)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
(2)
SUBTASK 010-001
Open the Forward Access Door, 112A to get access to the weather
radar R/T mount [1].
(3)
SUBTASK 010-002
Do this task: Weather Radar Receiver/Transmitter Removal
(AMM TASK 34-43-41-000-801 p401).
(4)
SUBTASK 020-001
Remove the weather radar R/T mount [1]:
(a) Disconnect the electrical connector [8].
(b) Remove the screws [3] and washers [4] that attach the waveguide
assembly [6] to the waveguide [7].
(c) Remove the screws [2] that attach the connector assembly [9] to
the rear of the weather radar R/T mount [1].
(d) Remove the screws [10] from the bottom of the weather radar R/T
mount [1].
(e) Make sure you support the connector assembly [9] and waveguide
assembly [6], while you carefully remove the weather radar R/T
mount [1].
(f) Remove the gasket [5].
EFFECTIVITY
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MAINTENANCE MANUAL
FORWARD ACCESS
DOOR, 112A
SEE
A
RECEIVER/
TRANSMITTER
[1] RECEIVER/
TRANSMITTER
(R/T) MOUNT
SEE
B
FWD
A
Weather Radar Receiver/Transmitter Mount Installation
Figure 401 (Sheet 1)
G14864
34-43-31-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
[6] WAVEGUIDE
ASSEMBLY
[3] SCREW
[4] WASHER
(4 LOCATIONS)
[2] SCREW
(4 LOCATIONS)
[7] WAVEGUIDE
[5] GASKET
[8] ELECTRICAL
CONNECTOR
[10] SCREW
(4 LOCATIONS)
[9] CONNECTOR
ASSEMBLY
[1] R/T MOUNT
B
Weather Radar Receiver/Transmitter Mount Installation
Figure 401 (Sheet 2)
G14867
EFFECTIVITY
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(g)
Put protective covers on the electrical connector [8],
connector assembly [9], and the waveguides.
TASK 34-43-31-400-801
3.
_____________________________________________________
Weather
Radar Receiver/Transmitter Mount Installation (Fig. 401)
A. References
(1) AMM TASK 34-43-41-400-801 p401, Weather Radar Receiver/Transmitter
Installation
B. Equipment
(1) Ohmeter (or alternative tool)
(a) C15292 Ohmeter - Electrical Bonding (Model T477W) (recommended)
Avtron Manufacturing, Inc. (Vendor Code 01014)
7900 E. Pleasant Valley Road, Independence OH 44131
(b) MODEL 1010-A Ohmeter - Micro, Autoranging/Autotest, 10 Micro
Ohms to 200 Ohms, Accuracy: 0.05% (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(c) M-1 Ohmeter - Micro-ohm, Automatic, Stores 128 Readings, RS-232
Data Port, Range: 0.01 - 19.999 Milliohms, 4 1/2 Digit Display,
Accy: 0.1% of Readings (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Mount
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 212 Flight Compartment - Right
(2) Access Panels
(a) 112A
Forward Access Door
E. Installation Procedure
(1)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
EFFECTIVITY
34-43-31
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MAINTENANCE MANUAL
(2)
(3)
(4)
(5)
(6)
SUBTASK 420-001
Install the weather radar R/T mount [1]:
(a) Remove the protective covers from the electrical connector [8],
connector assembly [9], and waveguides.
(b) Examine the electrical connector [8] and connector assembly [9]
for bent or broken pins, dirt and damage.
(c) Examine the waveguides for damage, dirt and moisture.
(d) Carefully move the weather radar R/T mount [1] into position
with the connector assembly [9] aligned correctly.
(e) Install a new gasket [5] between the waveguide assembly [6] and
the waveguide [7].
(f) Install the screws [10] that attach the weather radar R/T mount
[1] to the support structure.
(g) Install the screws [2] that attach the connector assembly [9]
to the weather radar R/T mount [1].
(h) Install the screws [3] and washers [4] to attach the waveguide
assembly [6] to the waveguide [7].
(i) Install the electrical connector [8].
SUBTASK 760-001
Use an ohmeter, C15292 to measure the resistance between the R/T
mount [1] and the support structure.
(a) Make sure the maximum resistance is 0.001 ohms or less.
SUBTASK 410-001
Do this task: Weather Radar Receiver/Transmitter Installation
(AMM TASK 34-43-41-400-801 p401).
SUBTASK 860-003
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 410-002
Close the Forward Access Door, 112A.
EFFECTIVITY
34-43-31
ALL
D633A101-ASA
Page 405
Jun 10/99
A
737-600/700/800/900
MAINTENANCE MANUAL
WEATHER RADAR RECEIVER/TRANSMITTER - REMOVAL/INSTALLATION
_________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the weather radar receiver/transmitter
(2) An installation of the weather radar receiver/transmitter.
B. The weather radar receiver/transmitter is in the lower nose compartment.
TASK 34-43-41-000-801
2.
ú
__________________________________________
Weather
Radar Receiver/Transmitter Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 212 Flight Compartment - Right
(2) Access Panels
(a) 112A
Forward Access Door
C. Removal Procedure
(1)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
(2)
SUBTASK 010-001
Open the Forward Access Door, 112A.
(3)
SUBTASK 020-003
Disconnect the pneumatic connector from the pilots ADM.
(4)
SUBTASK 860-006
Put a protective cover on the pneumatic connector of the ADM.
SUBTASK 020-001
CAUTION:
_______
(5)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
RECEIVER/TRANSMITTER [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
RECEIVER/TRANSMITTER [1].
To remove the receiver/transmitter [1], do this task:
Removal (AMM TASK 20-10-07-000-801 p201).
E/E Box
TASK 34-43-41-400-801
3.
_______________________________________________
Weather
Radar Receiver/Transmitter Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
EFFECTIVITY
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MAINTENANCE MANUAL
FORWARD ACCESS
DOOR, 112A
SEE
A
[1] RECEIVER/
TRANSMITTER
FWD
A
Weather Radar Receiver/Transmitter Installation
Figure 401
G15151
34-43-41-990-801
EFFECTIVITY
34-43-41
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A
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MAINTENANCE MANUAL
(2)
(3)
AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
AMM TASK 34-43-00-710-802 p501, Weather Radar (WXR) System Operational Test
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Transceiver
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 212 Flight Compartment - Right
(2) Access Panels
(a) 112A
Forward Access Door
D. Installation Procedure
(1)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 420-001
CAUTION:
_______
(2)
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
RECEIVER/TRANSMITTER [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
RECEIVER/TRANSMITTER [1].
To install the receiver/transmitter [1], do this task:
Installation (AMM TASK 20-10-07-400-801 p201).
E/E Box
SUBTASK 020-004
Remove protective cover from the pneumatic connector.
SUBTASK 410-002
WARNING:
_______
(4)
THE PITOT CONNECTOR MUST BE RECONNECTED AFTER INSTALLATION OF
THE RECEIVER/TRANSMITTER AND PRIOR TO THE FIRST FLIGHT.
POSSIBLE LOSS OF CAPTAINS AIR DATA MAY RESULT.
Connect the pneumatic connector.
NOTE:
____
Make sure that a blue band is visible around quick
disconnect. This will make sure that a positive connection
has been made.
EFFECTIVITY
34-43-41
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Page 403
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A
737-600/700/800/900
MAINTENANCE MANUAL
(5)
SUBTASK 410-001
Close the Forward Access Door, 112A.
SUBTASK 860-003
Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
Installation Test
(6)
E.
(1)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 710-001
Do this task: Weather Radar (WXR) System - Operational Test
(AMM TASK 34-43-00-710-802 p501).
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WEATHER RADAR CONTROL PANEL - REMOVAL/INSTALLATION
__________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the weather radar control panel.
(2) An installation of the weather radar control panel.
B. The weather radar control panel is located in the flight compartment on
the aft electronics panel, P8.
TASK 34-43-91-000-801
2.
___________________________________
Weather
Radar Control Panel Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
B. Removal Procedure
(1)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 020-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
WEATHER RADAR CONTROL PANEL [1]. IF YOU TOUCH THESE
CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
WEATHER RADAR CONTROL PANEL [1].
Do these steps to remove the weather radar control panel [1]:
(a) Loosen the four quarter-turn fasteners [2].
(b) Carefully lift the weather radar control panel [1] from the aft
electronics panel, P8, to get access to the electrical
connector [3].
(c) Disconnect the electrical connector [3].
(d) Put a protective cover on the electrical connector [3].
TASK 34-43-91-400-801
3.
________________________________________
Weather
Radar Control Panel Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
B. Parts
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SEE
A
[2] QUARTER-TURN
FASTENER
(4 LOCATIONS)
[1] WEATHER RADAR
CONTROL PANEL
[3] ELECTRICAL
CONNECTOR
FWD
AISLE STAND
A
Weather Radar Control Panel Installation
Figure 401
G27861
34-43-91-990-801
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~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Panel
¦ 34-43-91
01
35 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Installation Procedure
(1)
SUBTASK 860-003
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 420-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
WEATHER RADAR CONTROL PANEL [1]. IF YOU TOUCH THESE
CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE
WEATHER RADAR CONTROL PANEL [1].
Do these steps to install the weather radar control panel [1]:
(a) Remove the protective cover from the electrical connector [3].
(b) Examine the electrical connector for bent or broken pins, dirt,
and damage.
(c) Connect the electrical connector [3].
(d) Put the weather radar control panel [1] in its position on the
aft electronics control panel, P8.
(e) Tighten the four quarter-turn fasteners [2].
SUBTASK 860-004
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
Installation Test
(3)
E.
(1)
SUBTASK 860-005
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-006
Set the TILT control knob on the weather radar control panel to 0
degrees.
(3)
SUBTASK 860-010
Set the GAIN control knob on the weather radar control panel to the
CAL/AUTO position.
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(4)
SUBTASK 860-011
Set the RANGE on the captain's and first officer's EFIS control
panel to 40.
(5)
SUBTASK 860-012
Make sure that the captain's and first officer's EFIS displays are
on.
(6)
SUBTASK 860-007
Make sure the air data inertial reference system is aligned. To
align it, do this task: Air Data Inertial Reference System Alignment from the FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Air Data Inertial Reference System - Alignment from the ISDU
(AMM TASK 34-21-00-820-802 p201).
(7)
SUBTASK 860-008
Push the WXR switch on the captain's EFIS control panel to turn on
the weather radar system.
(8)
SUBTASK 210-001
Make sure that a green, yellow, red, magenta test pattern shows on
the captains display unit.
(9)
SUBTASK 860-009
Turn the TILT control knob on the weather radar control panel, P8,
to +15 and then to -15 degrees.
(a) Make sure the tilt position that shows in the weather radar
tilt field on the display unit agree with the tilt position on
the weather radar control panel.
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TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) - ADJUSTMENT/TEST
_____________________________________________________________________
1.
General
_______
A. This
(1)
(2)
(3)
procedure has these tasks:
TCAS operational test
TCAS system test (With the IFR TCAS-201 Test Set)
TCAS System Test (With the TIC T-49 Test Set).
TASK 34-45-00-710-801
2.
_______________________
TCAS
- Operational Test
A. General
(1) This test makes sure the TCAS operates correctly. It uses only the
system's Built In Test Equipment (BITE) functions. Special test or
ground equipment is not necessary.
B. References
(1) AMM TASK 23-51-00-710-801 p501, Flight Interphone System Operational Test
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(4) AMM TASK 31-62-00-710-801 p501, Common Display System - Operational
Test
(5) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
(6) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(7) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
(8) AMM TASK 34-33-00-710-801 p501, Low Range Radio Altimeter (LRRA)
System - Operational Test
(9) AMM TASK 34-53-00-710-801 p501, Air Traffic Control System Operational Test
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
D. Prepare for the Operational Test
(1)
(2)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-002
Make sure these systems are serviceable:
(a) Air Data System (AMM TASK 34-21-00-710-801 p501)
(b) Air Traffic Control System (AMM TASK 34-53-00-710-801 p501)
(c) Common Display System (AMM TASK 31-62-00-710-801 p501)
(d) Flight Interphone System (AMM TASK 23-51-00-710-801 p501)
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(e)
ú
(3)
(4)
(5)
(6)
Low Range Radio Altimeter System
(AMM TASK 34-33-00-710-801 p501).
SUBTASK 860-003
Do this task: Air
the
Air
the
Data Inertial Reference System - Alignment from
FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Data Inertial Reference System - Alignment from
ISDU (AMM TASK 34-21-00-820-802 p201).
SUBTASK 860-034
Wait until the align light on the MSU goes off.
SUBTASK 860-004
Put the display mode switch on the EFIS control panel to the MAP
position.
SUBTASK 860-035
Set the range knob on the EFIS control panel to 10.
(7)
SUBTASK 860-005
Put the mode select switch on the TCAS/ATC control panel to the
TA/RA position.
(8)
SUBTASK 860-006
Push the TFC switch on the EFIS control panel.
(a) Make sure the inboard display shows TFC.
(9)
SUBTASK 860-007
Put the transponder select switch on the TCAS/ATC control panel
(referred to as the control panel for the rest of this section) to
the 1 position.
(a) Make sure the FAIL lamp on the control panel is off.
SUBTASK 860-008
(10) Put the mode select switch on the control panel to the STBY
position.
(a) Make sure the inboard displays show the TCAS OFF indication.
SUBTASK 860-009
(11) Put the mode select switch on the control panel to the TA position.
(a) Make sure the inboard displays show the TA ONLY indication.
SUBTASK 860-010
(12) Put the mode select switch on the control panel to the TA/RA
position.
(a) Make sure TA ONLY continues to show on the inboard displays.
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E.
Procedure
(1)
ú
SUBTASK 740-001
Do the operational test as follows:
(a) Press and release the TEST switch on the mode select switch
located on the control panel.
(b) Make sure these results occur:
1) The inboard displays show a test pattern as described below
(Fig. 501):
a) TCAS TEST shows on the left side of the inboard
displays
b) The word TRAFFIC shows on the right side of the inboard
displays
c) An R/A (red square) shows at 3 o'clock, range of 2
miles, 200 feet above and flying level (no arrow)
d) A Traffic Advisory (yellow circle) shows at 9 o'clock,
range of 2 miles, 200 feet below and climbing (up
arrow)
e) Proximity Traffic (solid white diamond) shows at 1
o'clock, range 3.6 miles, 1000 feet above and
descending (down arrow)
f) Non-Threat Traffic (open white diamond) shows at 11
o'clock, range of 3.6 miles, 1000 feet above and flying
level (no arrow).
2) Make sure the outboard displays show the DO NOT CLIMB and
DO NOT DESCEND resolution advisory.
3) A TCAS TEST PASS synthesized voice announcement comes on at
the end of the test if the test passes.
(2)
SUBTASK 740-002
Do the operational test again with the transponder select switch on
the control panel set to the 2 position.
(3)
SUBTASK 860-011
If electrical power is not necessary, do this task:
Electrical Power (AMM TASK 24-22-00-860-812 p201).
Remove
TASK 34-45-00-730-801
3.
___________________________________________________
TCAS
- System Test (With the IFR TCAS-201 Test Set)
A. General
(1) This test is a complete system test of the TCAS system. The system
test first runs the TCAS/ATC Operational Test, and then does a test
of TCAS with ground test equipment.
B. References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(2) AMM TASK 32-00-01-480-801 p201, Landing Gear Downlock Pins
Installation
(3) AMM TASK 34-45-00-710-801 p501, TCAS - Operational Test
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0000.0 z
GS 0
--- NM
TAS ---
TRK
130
M
TRAFFIC
5
TCAS
TEST
+10
-10
-02
+02
---/---
EFIS OUTBOARD DISPLAYS
(EXAMPLE)
0.0-R
0.0-L
EFIS INBOARD DISPLAYS
RA FLIGHT
BOUNDARY
"FLY-OUT-OF"
AREA
EFIS OUTBOARD DISPLAYS
(EXAMPLE)
TCAS Test Pattern
Figure 501
G38327
34-45-00-990-801
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C.
Equipment
(1) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
(g) ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(2) Test (or alternative tool)
(a) 2041595-5201 Test Set - Bendix Radio Altimeter (recommended)
Honeywell, Inc. (Vendor Code 27914)
2100 N.W. 62nd Street, P.O. Box 9414, Fort Lauderdale FL 33309
(b) DRA707B1 Test Set - Collins Radio Altimeter (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(c) 9599-607-15902 Test Set - Radio Altimeter (alternative)
TRT/Telecommunications Radioelectriques et Telephoniques SA
(Vendor Code F6170)
88 Rue Brillat Savarin, 75640 Paris, France
(d) ARA-552 Test Set - Radio Altimeter Test (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
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(e)
D.
E.
DRA707 Test Set - Radio Altimeter (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(f) ADC-552 Converter - Digital, Radio Altimeter Tester
(alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(3) Test (or alternative tool)
(a) TCAS-201-2 Test Set - TCAS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 201-110 Test Set - TCAS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-49C Test Set - TCAS/ATC Test, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
Prepare for the System Test
SUBTASK 840-001
CAUTION:
_______
(1)
DO NOT OPERATE THE TEST SET WHEN THE TEST SET ANTENNA IS WITHIN
15 INCHES (38 CM) OF AIRPLANE ANTENNA. DAMAGE TO THE TEST SET
CAN OCCUR.
Do the steps that follow to set up the test set, TCAS-201-2:
(a) Put the test set, TCAS-201-2, antenna approximately 50 feet (15
meters) from the top TCAS antenna at an angle of 45 degrees off
of the airplane center line.
NOTE:
____
1)
Use the antenna stand to prevent unnecessary movements
to the test set antenna. Unnecessary movements can
cause TCAS to loose tracking.
Make sure there is no obstruction between the TCAS
antennas.
NOTE:
____
If ground equipment, walkways or other objects that
could cause a signal obstruction or a multipath
problem are in the area, choose a more suitable
location for the test set and change the setup in
the test set accordingly.
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(b)
Point the , antenna in the direction of the applicable TCAS
antenna.
NOTE:
____
(c)
(d)
(e)
(f)
(g)
Push the POWER switch to supply power to the test set,
TCAS-201-2.
Push the SET/CONT key on the test set, TCAS-201-2.
Enter the distance (|5 feet) between the test set, TCAS-201-2,
antenna and the airplanes top TCAS antenna in the HORIZ field.
Enter 17 feet in the VERT field.
Enter the gain of the test set, TCAS-201-2, antenna in the GAIN
field.
NOTE:
____
(h)
The antenna gain should be listed on the test set
antenna.
Enter the loss of the cable in the LOSS field.
NOTE:
____
F.
This allows the correct TCAS antenna to receive the
strongest signal.
The cable loss values should be listed on the cable.
Test the TCAS system
(1)
(2)
SUBTASK 710-001
Do this task: TCAS - Operational Test
(AMM TASK 34-45-00-710-801 p501).
(a) Make sure the Operational Test passes.
SUBTASK 730-001
Do the TCAS Bearing Accuracy Test as follows:
(a) Put the transponder select switch on the TCAS/ATC control panel
(referred to as the control panel for the rest of this section)
to the 1 position.
(b) Put the mode select switch on the control panel to the TA
position.
(c) Shield the bottom TCAS antenna.
NOTE:
____
(d)
(e)
(f)
This is to test the top TCAS antenna. You may have to
get up high to be able to interrogate the top TCAS
antenna from the rear of the airplane.
Push the SCEN key on the test set, TCAS-201-2, to show the
scenario menu.
Set up this SCENARIO:
1) INTRUDER TYPE: ATCRBS
2) ALT = OFF
3) RANGE: 8.0 nMi
4) RATE: 0 kts
Push the RUN/STOP key to start the test.
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(g)
Use the test set, TCAS-201-2, to interrogate the four quadrants
of the TCAS antenna at bearings of 0, 45, 90, 180, 225, 270
degrees.
NOTE:
____
Make sure your inboard displays show the correct bearing
of the intruder.
1)
(h)
Make sure the inboard displays show the intruder's correct
bearing |15 degrees.
Shield the top TCAS antenna or move the test set, TCAS-201-2,
antenna close to the bottom TCAS antenna (out of the line of
sight from the top TCAS antenna).
NOTE:
____
WARNING:
_______
(i)
(j)
(k)
(3)
This is to test the bottom antenna. If you move the
test set, TCAS-201-2, you have to change the values in
the setup screen accordingly.
MAKE SURE THE GROUND LOCKS ARE INSTALLED ON ALL THE
LANDING GEAR BEFORE YOU MOVE THE CONTROL LEVER. WITHOUT
THE GROUND LOCKS, THE LANDING GEAR CAN RETRACT AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Make sure the ground locks are installed on the nose and main
landing gear. To do this, do this task: Landing Gear Downlock
Pins Installation (AMM TASK 32-00-01-480-801 p201).
Put the landing gear lever in the OFF position.
Do the steps in the Bearing Accuracy Test again for the bottom
antenna.
SUBTASK 860-012
Do the Self-Test inhibit test:
(a) Open these circuit breakers and attach circuit breaker locks:
1) Circuit Breaker Panel, P6-3:
a) 6C15
LANDING GEAR AIR/GND SYS 2
b) 6C16
LANDING GEAR AIR/GND SYS 1
c) 6D1
PSEU PRI
d) 6D2
PSEU ALTN
e) 6D18
LANDING GEAR AURAL WARN
(b) Push and release the TEST switch on the control panel.
1) Make sure a TCAS self-test does not occur.
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(4)
SUBTASK 860-013
Prepare to do the TCAS intruder Climb Resolution Advisory Test:
(a) Put the mode select switch on the control panel to the STBY
position.
(b) Use the pitot/static test set, to apply an altitude of 40,000
feet (Reference TBD).
NOTE:
____
(c)
(d)
The 40,000 feet barometric altitude is chosen to
minimize false TCAS alert to TCAS equipped airplanes
nearby.
Connect the radio altimeter test test set, 2041595-5201, to the
airplane.
Use the radio altimeter test test set, 2041595-5201, and set
the radio altitude to 2400 feet.
NOTE:
____
Increase the radio altitude by 600 feet per minute (fpm)
or less. TCAS RAs are inhibited below 1100 feet during
climb. So TA ONLY shows below 1100 feet.
1)
(e)
(f)
(g)
Make sure the inboard displays do not show the TA ONLY
indication when radio altitude is greater than 1100 feet.
Put the EFIS control panel to the MAP mode and a range of 20 on
the inboard displays.
Push the SCEN key to show the scenario menu.
Set up this scenario:
1) INTRUDER TYPE: ATCRBS
2) ALT = ON
3) RANGE: 8.0 nm
4) RATE: +500 kts
5) ALTITUDE: 39,900 ft
NOTE:
____
6)
Make sure the intruder's altitude is 100 feet below
your airplanes barometric altitude. You can change
the airplane's altitude or intruder setup on the
test set to do this.
RATE: 0 fpm.
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(5)
SUBTASK 860-014
Do the TCAS intruder Climb Resolution Advisory Test:
(a) Push the RUN/STOP key to start the scenario, and look for this
sequence on the EFIS display and flight compartment speaker:
1) The intruder moves down the 45 degree bearing mark toward
the airplane symbol
2) The intruder has the correct relative altitude
NOTE:
____
The relative altitude shown can be -00 or -01
depending on your actual vertical separation. This
is because TCAS can only display relative altitude
by 100 foot increments.
3)
The intruder begins as Non-threat Traffic (open white
diamond)
4) The intruder changes to Proximate Traffic (solid white
diamond)
5) The intruder changes to a Traffic Advisory (solid yellow
circle)
6) The TCAS gives a "TRAFFIC, TRAFFIC" voice announcement on
the flight compartment speaker
7) The intruder changes to a Resolution Advisory (solid red
square), and gives a "climb climb climb" voice announcement
on the flight compartment speaker
8) The outboard displays show an RA resolution to pull up
9) Shortly before the intruder reaches the closest point of
approach, the TCAS gives an "increase climb" voice
announcement on the flight compartment speaker
10) Shortly after the intruder reaches the airplane symbol on
the inboard displays , TCAS gives a "Clear of Conflict"
voice announcement on the flight compartment speaker.
NOTE:
____
(b)
(6)
The "Clear of Conflict" voice announcement sometimes
may not be given.
Push the RUN/STOP key on the test set, TCAS-201-2.
SUBTASK 860-015
Prepare to do the TCAS intruder Descend Resolutionary Advisory Test:
(a) Put the transponder select switch on the control panel to the 2
position.
(b) On the test set, TCAS-201-2, push the SCEN key to display the
scenario menu.
(c) Set up this scenario:
1) INTRUDER TYPE: Mode S
2) RANGE: 8.0 nm
3) RATE: +500 kts
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4)
ALTITUDE:
NOTE:
____
5)
(7)
40,100 ft
Make sure the intruder's altitude is 100 feet above
your airplanes barometric altitude. You can change
the airplane's altitude or intruder setup on the
test set to do this.
RATE: 0 fpm.
SUBTASK 730-002
Do the TCAS intruder Descend Resolutionary Advisory Test:
(a) Push the RUN/STOP key to start the scenario, and look for this
sequence on the EFIS display and flight compartment speaker:
1) The intruder moves down the 45 degree bearing mark toward
the airplane symbol.
2) The intruder has the correct relative altitude.
NOTE:
____
The relative altitude shown can be +00 or +01
depending on your actual vertical separation. This
is because TCAS can only display relative altitude
by 100 foot increments.
3)
The intruder begins as Non-threat Traffic (open white
diamond).
4) The intruder changes to Proximate Traffic (solid white
diamond)
5) The intruder changes to a Traffic Advisory (solid yellow
circle).
6) The TCAS gives a "TRAFFIC, TRAFFIC" voice announcement on
the flight compartment speaker.
7) The intruder changes to a Resolution Advisory (solid red
square), and gives a "descend, descend, descend" voice
announcement on the flight compartment speaker.
8) The outboard displays show an RA resolution to push down.
9) Shortly before the intruder reaches the closest point of
approach, the TCAS gives an "increase descent" voice
announcement on the flight compartment speaker.
10) Shortly after the intruder reaches the airplane symbol on
the inboard displays , TCAS gives a "Clear of Conflict"
voice announcement on the flight compartment speaker.
NOTE:
____
(b)
The "Clear of Conflict" voice announcement sometimes
may not be given.
Push the RUN/STOP key to stop the Scenario.
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(8)
SUBTASK 860-016
Prepare to do the High Altitude Climb Inhibit Test:
(a) Use the pitot/static test set, to make a simulated altitude of
48,500 feet.
NOTE:
____
(b)
Push the SCEN key on the test set, TCAS-201-2, to show the
scenario menu.
Set up this scenario:
1) RANGE: 4.2 nMi
2) RATE: +500 kts
3) ALTITUDE: 48,300 ft
4) RATE: 0 fpm
(c)
(9)
Let the VSI return to zero after the simulated altitude
is reached.
SUBTASK 860-017
Do the High Altitude Climb Inhibit Test:
(a) Push the RUN/STOP key to start the scenario.
(b) Make sure that the relative altitude of the intruder is -02.
NOTE:
____
(c)
(d)
If the relative altitude of the intruder is not -02,
increase or decrease your airplane's accordingly.
Make sure TCAS gives the "TRAFFIC, TRAFFIC" annunciation.
Make sure TCAS gives the "Monitor Vertical Speed" annunciation.
NOTE:
____
A crossing descend resolution advisory may be given
instead of the Monitor Vertical Speed resolution
advisory. Decrease the intruder's altitude or increase
the airplane's altitude to correct this.
SUBTASK 860-018
(10) Return the airplane back to field level altitude.
SUBTASK 860-019
(11) Use the radio altimeter test test set, 2041595-5201, and set the
radio altitude to 0 feet.
ú
ú
NOTE:
____
(a)
ú
Decrease the radio altitude by 600 feet per minute (fpm) or
less.
Make sure the inboard displays show the TA ONLY indication when
radio altitude is less than 900 feet.
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G.
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 860-020
Remove the circuit breaker locks and close these circuit breakers:
(a) Circuit Breaker Panel, P6-3:
1) 6C15
LANDING GEAR AIR/GND SYS 2
2) 6C16
LANDING GEAR AIR/GND SYS 1
3) 6D1
PSEU PRI
4) 6D2
PSEU ALTN
5) 6D18
LANDING GEAR AURAL WARN
SUBTASK 860-021
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-45-00-730-802
4.
_______________________________________________
TCAS
- System Test (with the TIC T-49 Test Set)
A. General
(1) This test is a complete system test of the TCAS. The system test
first runs the TCAS Operational Test, and then does a test of the
TCAS using ground test equipment.
B. References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(2) AMM TASK 32-00-01-480-801 p201, Landing Gear Downlock Pins
Installation
(3) AMM TASK 34-45-00-710-801 p501, TCAS - Operational Test
C. Equipment
(1) Test (or alternative tool)
(a) Test Set - Air Data (Select from Alternative Tools)
(recommended) (recommended)
(commercially available)
(b) 18910480000 Test Set - Air Data Model FLMTS (Flight Line
Maintenance) (alternative)
Sequa Corp. (Vendor Code 89944)
220 Daniel Webster Hwy. S., Merrimack NH 03054-4809
(c) D60340 Tester - Pitot/Static, computer controlled, includes
remote control display unit, power and interface cables.
(alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(d) DPS500 Test Set - Air Data (alternative)
Barfield Instrument Corp. (Vendor Code 21844)
4101 N.W. 29th Street, P.O. Box 7705, Miami FL 33142-7705
(e) ADTS405F Test Set - Air Data (alternative)
Druck Ltd. (Vendor Code 0R667)
Fir Tree Lane, Groby, Leicester LE6 0FH England
(f) 6005KTQA1-103 Unit - Control, Air Data test set, Automatic
(alternative)
Smiths Industries (Vendor Code 35012)
14180 Roosevelt Blvd., P.O. Box 5389, Clearwater FL 33462
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(g)
D.
ADC800 Set - Test, Air Data (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(h) TES9463 Test Set - Air Data (Ref to GN11335) (alternative)
(i) D60302 Test Set - Air Data Computer-Controlled (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(j) D60383 Test Set - Air Data (alternative)
Penny & Giles Data Recorders Ltd. (Vendor Code K1474)
15 Airfield Road, Christchurch, England
(k) 01-0987-00 Test Set - Air Data, RVSM Compliant (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(2) Test (or alternative tool)
(a) 2041595-5201 Test Set - Bendix Radio Altimeter (recommended)
Honeywell, Inc. (Vendor Code 27914)
2100 N.W. 62nd Street, P.O. Box 9414, Fort Lauderdale FL 33309
(b) DRA707B1 Test Set - Collins Radio Altimeter (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(c) 9599-607-15902 Test Set - Radio Altimeter (alternative)
TRT/Telecommunications Radioelectriques et Telephoniques SA
(Vendor Code F6170)
88 Rue Brillat Savarin, 75640 Paris, France
(d) ARA-552 Test Set - Radio Altimeter Test (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(e) DRA707 Test Set - Radio Altimeter (alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(f) ADC-552 Converter - Digital, Radio Altimeter Tester
(alternative)
Atlantis Aerospace Corp. (Vendor Code 38202)
1 Kenview Blvd., Brampton, Canada, L6T 5E6
(3) Test (or alternative tool)
(a) T-49C Test Set - TCAS/ATC Test, RAMP (recommended)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
(b) 201-110 Test Set - TCAS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) TCAS-201-2 Test Set - TCAS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
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E.
Prepare for the System Test
(1)
SUBTASK 860-022
Do the steps that follow to set up the test set, T-49C:
(a) Put the test set, T-49C, antenna about 50 feet (15 meters) in
front of the airplane on the center line.
1) Make sure there is no obstruction between the TCAS
antennas.
NOTE:
____
(b)
(2)
If ground equipment, people, walkways or other
objects that could cause a signal obstruction or a
multipath problem are in the area, move the test set
within 15 to 30 feet (4.6-9.1 meters) of the
airplane.
Point the test set, T-49C, antenna in the direction of the
applicable TCAS antenna.
SUBTASK 860-023
Connect the cable of the test set, T-49C, antenna to the test set,
T-49C, antenna connector.
SUBTASK 860-024
Put the transponder select switch on the TCAS/ATC control panel
(referred to as the control panel for the rest of this section) to
the 1 position.
Test the TCAS system
(3)
F.
(1)
(2)
SUBTASK 710-002
Do this task: TCAS - Operational Test
(AMM TASK 34-45-00-710-801 p501).
(a) Make sure the Operational Test passes.
SUBTASK 860-025
Do the Self-Test Inhibit Test:
(a) Open these circuit breakers and attach circuit breaker locks:
1) Circuit Breaker Panel, P6-3:
a) 6C15
LANDING GEAR AIR/GND SYS 2
b) 6C16
LANDING GEAR AIR/GND SYS 1
c) 6D1
PSEU PRI
d) 6D2
PSEU ALTN
e) 6D18
LANDING GEAR AURAL WARN
(b) Press and release the TEST switch on the mode select switch on
the control panel.
1) Make sure a TCAS self-test does not occur.
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(3)
SUBTASK 860-026
Prepare to do the TCAS Bearing Accuracy Test:
(a) Connect the radio altimeter test set, 2041595-5201, to the
airplane.
(b) Use the radio altimeter test set, 2041595-5201, to make a radio
altitude of 2400 feet.
NOTE:
____
Increase the radio altitude by 600 feet per minute (fpm)
or less. RAs are inhibited below 1100 feeet during
climb. So TA ONLY will show below 1100 feet.
1)
(c)
(d)
Make sure the inboard displays do not show the TA ONLY
indication when the radio altitude is greater than 1100
feet.
Connect a pitot/static test set, to the airplane so you can
pressurize the two air data computers (Reference TBD).
Use the pitot/static test set, to make a barometric altitude of
40,000 feet.
NOTE:
____
(e)
(f)
(g)
(4)
The 40,000 feet barometric altitude is chosen to
minimize false TCAS alert to TCAS equipped airplanes
nearby. Make sure to have altitude reporting function
of the ATC off or put the ATC system on standby during
this procedure.
Put the EFIS control panel to MAP mode and a range of 20 on the
inboard displays.
Put the mode select switch on the control panel to the TA
position.
Supply power to the test set, T-49C.
SUBTASK 860-027
Do the TCAS Bearing Accuracy Test:
(a) Put the intruder type switch on the test set, T-49C, to the
ATCRBS position.
(b) Put the scenario switch on the test set, T-49C, to the fixed
intruder scenario position (+1000).
(c) Shield the bottom TCAS antenna.
NOTE:
____
(d)
This is to test the top TCAS antenna. You may have to
get up high to be able to interrogate the top TCAS
antenna from the rear of the airplane.
Push the interrogate switch on the test set, T-49C.
1) Make sure the test set, T-49C, display shows the type of
intruder selected.
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(e)
(f)
(g)
Use the test set, T-49C to interrogate the four quadrants of
the TCAS antenna at bearings of 0, 45, 90, 180, 225, and 270
degrees.
1) Make sure the inboard displays show the intruders bearing
within |15 degrees.
Put the scenario switch on the test set, T-49C to the fixed
intruder scenario position (-1000).
Put the power setting to low (LO) on the test set, T-49C.
NOTE:
____
(h)
A HI power setting can increase the likelihood of
multipath problem.
Shield the top TCAS antenna or move the test set antenna to the
bottom TCAS antenna (out of the line of sight from the top TCAS
antenna).
NOTE:
____
WARNING:
_______
This is to test the bottom TCAS antenna. You may have
to get up high to be able to interrogate the top TCAS
antenna from the rear of the airplane.
(i)
(j)
(k)
(5)
MAKE SURE THE GROUND LOCKS ARE INSTALLED ON ALL THE
LANDING GEAR BEFORE YOU MOVE THE CONTROL LEVER. WITHOUT
THE GROUND LOCKS, THE LANDING GEAR CAN RETRACT AND CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Make sure the ground locks are installed on the nose and main
landing gear. To do this, do this task: Landing Gear Downlock
Pins Installation (AMM TASK 32-00-01-480-801 p201).
Put the landing gear lever in the OFF position.
Use the test set to interrogate the four quadrants of the TCAS
antenna at bearings of 0, 45, 90, 180, 225, and 270 degrees.
1) Make sure the inboard displays show the intruders bearing
within |15 degrees.
SUBTASK 860-028
Do the TCAS Intruder Test:
(a) Put the mode select switch on the control panel to the TA/RA
position.
(b) Put the test set, T-49C, directional antenna 45 degrees to the
right of the center line of the airplane with a 50 feet
separation from the airplane.
NOTE:
____
(c)
(d)
The directional antenna will send signals to the TCAS
antenna.
Put the scenario switch on the test set, T-49C, to the straight
approach 14 nMi position.
Put the intruder type switch on the test set, T-49C to the MODE
S position.
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(e)
(f)
(g)
(h)
Push the interrogate switch.
1) Make sure the test set, T-49C, display shows the correct
intruder type.
Push the interrogate switch to start the scenario.
1) Make sure the test set, T-49C, display shows the airplane's
altitude |100 feet and the correct scenario (Range 14nMi,
Co-Altitude, Closure rate 720 kts).
Increase the airplane's altitude by 200 feet.
Make sure this sequence shows on the EFIS secondary display and
the voice announcements are heard on the flight compartment
speakers:
1) The intruder ascends to the airplane symbol from the 45
degree bearing mark.
2) The intruder begins as Non-threat Traffic (open white
diamond).
3) The intruder changes to Proximate Traffic (solid white
diamond).
4) The intruder changes to a Traffic Advisory (solid yellow
circle).
5) The TCAS gives a "TRAFFIC, TRAFFIC" voice announcement on
the flight compartment speaker.
6) The intruder changes to a Resolution Advisory (solid red
square), and gives a "climb, climb, climb" voice
announcement on the flight compartment speaker.
7) The outboard displays show a vertical resolution to pull
up.
8) Before the intruder gets to the closest point of approach,
the TCAS possibly will give an "increase climb" voice
announcement on the flight compartment speaker.
9) Shortly after the intruder reaches the airplane symbol on
the inboard displays, TCAS gives a "Clear of Conflict"
voice announcement on the flight compartment speaker.
NOTE:
____
(i)
(j)
(k)
(l)
(m)
Some test set, T-49C, software will not allow the
"Clear of Conflict" voice announcement to occur.
Put the intruder type switch on the test set, T-49C, to the
TCAS position.
Push the interrogate switch.
1) Make sure the test set, T-49C, display shows the correct
intruder type.
Push the interrogate switch to start the scenario.
1) Make sure the test set, T-49C, display shows the airplane's
altitude |100 feet and the correct scenario (Range 14 nMi,
Co-Altitude, Closure rate 720 kts).
Decrease the airplane's altitude by 200 feet.
Make sure this sequence shows on the inboard displays display:
1) The intruder descends to the airplane symbol from the 45
degree bearing mark.
2) The intruder begins as Non-threat Traffic (open white
diamond).
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3)
4)
The intruder changes to Proximate Traffic (solid white
diamond).
The intruder changes to a Traffic Advisory (solid yellow
circle).
The TCAS gives a "TRAFFIC, TRAFFIC" voice announcement on
the flight compartment speaker.
The intruder changes to a Resolution Advisory (solid red
square), and gives a "descend, descend, descend" voice
announcement on the flight compartment speaker.
The outboard displays show a vertical resolution to push
down.
Before the intruder gets to the closest point of approach,
the TCAS possibly will give an "increase descent" voice
announcement on the flight compartment speaker.
Shortly after the intruder reaches the airplane symbol on
the inboard displays, TCAS gives a "Clear of Conflict"
voice announcement on the flight compartment speaker.
5)
6)
7)
8)
9)
NOTE:
____
Some test set, T-49C, software will not allow the
"Clear of Conflict" voice announcement to occur.
SUBTASK 860-029
Do the High Altitude Climb Inhibit Test:
(a) Put the transponder select switch on the control panel to the 2
position.
(b) Use the pitot/static test set, to make a simulated altitude of
49,000 feet.
(c) Do the previous TCAS intruder scenario test again.
1) Make sure TCAS does not give a CLIMB corrective action.
Put the Airplane Back to Its Usual Condition
(6)
G.
(1)
SUBTASK 860-030
Return the airplane back to field level altitude.
(2)
SUBTASK 860-031
Put the radio altitude to 0 feet.
NOTE:
____
Decrease the radio altitude by 600 feet per minute (fpm) or
less.
ú
(a)
ú
(3)
Make sure the inboard displays show the TA ONLY indication when
radio altitude is less than 900 feet.
SUBTASK 860-032
Remove the circuit breaker locks and close these circuit breakers:
(a) Circuit Breaker Panel, P6-3:
1) 6C15
LANDING GEAR AIR/GND SYS 2
2) 6C16
LANDING GEAR AIR/GND SYS 1
3) 6D1
PSEU PRI
4) 6D2
PSEU ALTN
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5)
(4)
6D18
LANDING GEAR AURAL WARN
SUBTASK 860-033
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
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____________________________________________
TRAFFIC
ALERT AND COLLISION AVOIDANCE SYSTEM
(TCAS) COMPUTER - REMOVAL/INSTALLATION
______________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the TCAS computer
(2) An installation of the TCAS computer.
B. The TCAS computer, M1485, is installed on the E1 rack in the electronic
compartment.
TASK 34-45-01-000-801
2.
_____________________
TCAS
Computer Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
C. Procedure
(1)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
SUBTASK 020-001
CAUTION:
_______
(2)
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE TCAS
COMPUTER. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE TCAS COMPUTER.
To remove the TCAS computer [1], do this task:
(AMM TASK 20-10-07-000-801 p201).
E/E Box Removal
SUBTASK 020-002
Install dust caps on the electrical connectors.
TASK 34-45-01-400-801
3.
__________________________
TCAS
Computer Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
B. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
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ELECTRONIC
EQUIPMENT
RACK, E1
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] TCAS
COMPUTER
(E1-1)
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACK, E1
A
TCAS Computer Installation
Figure 401
F28157
34-45-01-990-801
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C.
Procedure
(1)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
SUBTASK 420-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE TCAS
COMPUTER. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE TCAS COMPUTER.
Remove the dust caps from the electrical connectors.
SUBTASK 420-002
To install the TCAS computer [1], do this task:
Installation (AMM TASK 20-10-07-400-801 p201).
Installation Test
(3)
D.
(1)
(2)
(3)
E/E Box
SUBTASK 860-004
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
SUBTASK 740-007
On the ATC control panel, push and release the test switch.
SUBTASK 740-003
Make sure you hear "TCAS test pass" on the flight compartment
speakers.
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___________________________________________________
TRAFFIC
ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS)
ANTENNA - REMOVAL/INSTALLATION
______________________________
1.
General
_______
A. This procedure has these tasks.
(1) A removal of the TCAS directional antenna
(2) An installation of the TCAS directional antenna.
B. There are two TCAS antennas installed on the airplane. One is installed
on the top of the airplane, at station 385. The other is installed on
the bottom of the airplane, at station 305.
TASK 34-45-02-000-801
2.
____________________
TCAS
Antenna Removal (Fig. 401)
A. References
(1) AMM TASK 20-30-31-910-801 p201, Cleaners and Polishes
B. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
C. Consumable Materials
(1) B00184 Solvent, Presealing, Cleaning Solvent - BMS11-7
D. Access
(1) Location Zones
(a) 221 Passenger Compartment - Aft of Control Compartment to
Forward Entry Door - Left
(b) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
E. Procedure
(1)
(2)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
SUBTASK 020-001
Do these steps to remove the TCAS antenna:
(a) Remove the sealant from around the edge of the antenna [3] and
the top of the screw heads [4]
(AMM TASK 20-30-31-910-801 p201).
(b) Remove the screws [4] from the antenna base.
CAUTION:
_______
(c)
BE CAREFUL WHEN YOU USE THE SEALANT REMOVAL TOOL TO BREAK
THE ANTENNA SEAL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE
AIRPLANE SKIN, THE COAXIAL CABLE OR THE ANTENNA.
Use force around the antenna with the sealant removal tool
until the seal is fully broken.
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TOP TCAS ANTENNA
(STA 385)
SEE
A
BOTTOM TCAS ANTENNA
(STA 305)
SEE
[1] COAXIAL
CONNECTOR
(4 LOCATIONS)
A
[2] O-RING
WEATHER
AERODYNAMIC
SEALANT
[3] ANTENNA
[4] WASHER
(4 LOCATIONS)
[5] BOLT
(4 LOCATIONS)
1
FWD
[6] COTTON BALL
(4 LOCATIONS)
BOTTOM TCAS ANTENNA
(TOP TCAS ANTENNA EQUIVALENT)
1
INSTALLED IN THE FOUR
INNER COUNTERSUNK HOLES
A
TCAS Directional Antenna Installation
Figure 401
G49511
34-45-02-990-801
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CAUTION:
_______
(d)
(e)
MOVE THE ANTENNA THE SMALLEST DISTANCE NECESSARY TO
DISCONNECT THE ANTENNA CONNECTORS. DAMAGE TO THE ANTENNA
CABLES CAN OCCUR IF YOU PULL THE CABLES.
Move the antenna [3] until you can get access to the antenna
cable connectors.
Disconnect the antenna cables [1].
NOTE:
____
(f)
(g)
Do not let the antenna cables retract into the airplane.
Install dust caps on the connector at the end of the antenna
cables.
Remove the TCAS antenna [3].
(3)
SUBTASK 140-001
Remove the sealant from the airplane skin around the antenna area
(AMM TASK 20-30-31-910-801 p201).
(4)
SUBTASK 110-001
Use a clean rag and some solvent, BMS11-7, to clean the airplane
surface around the antenna area (AMM TASK 20-30-31-910-801 p201).
TASK 34-45-02-400-801
3.
_________________________
TCAS
Antenna Installation
A. References
(1) AMM TASK 20-30-11-910-801
(2) AMM TASK 20-30-31-910-801
(3) AMM TASK 20-40-11-760-801
(4) AMM TASK 51-21-91-620-802
B.
C.
p201,
p201,
p201,
p701,
Adhesives, Cements, and Sealants
Cleaners and Polishes
Electrical Bonding
Apply the Corrosion Inhibiting
Compound
Equipment
(1) Ohmeter (or alternative tool)
(a) C15292 Ohmeter - Electrical Bonding (Model T477W) (recommended)
Avtron Manufacturing, Inc. (Vendor Code 01014)
7900 E. Pleasant Valley Road, Independence OH 44131
(b) MODEL 1010-A Ohmeter - Micro, Autoranging/Autotest, 10 Micro
Ohms to 200 Ohms, Accuracy: 0.05% (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(c) M-1 Ohmeter - Micro-ohm, Automatic, Stores 128 Readings, RS-232
Data Port, Range: 0.01 - 19.999 Milliohms, 4 1/2 Digit Display,
Accy: 0.1% of Readings (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
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(2)
D.
E.
B00083 Solvent, Aliphatic naphtha (for acrylic plastics) - TT-N-95,
Type II
(3) D00015 Grease, Aircraft bearing - BMS3-24
(4) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
Access
(1) Location Zones
(a) 221 Passenger Compartment - Aft of Control Compartment to
Forward Entry Door - Left
(b) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
Procedure
(1)
(2)
SUBTASK 860-002
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
SUBTASK 210-001
Visually examine the contact surfaces of the antenna [3] and the
airplane for corrosion and unwanted substances.
NOTE:
____
If the surfaces are not clean, the electrical ground between
the antenna and the surface will not be sufficient, and
incorrect system operation will occur.
(3)
SUBTASK 110-002
Clean the contact surfaces with some solvent, TT-N-95, Type II
(AMM TASK 20-30-31-910-801 p201).
(4)
SUBTASK 620-001
Apply compound, BMS3-23, to the contact surfaces of the antenna and
the airplane (AMM TASK 51-21-91-620-802 p701).
(5)
(6)
SUBTASK 620-002
Apply a layer of grease, BMS3-24, on the O-ring and O-ring groove.
SUBTASK 420-001
Install the TCAS antenna:
(a) Make sure that an O-ring is installed on the new antenna [3].
(b) Remove the dust caps on the antenna cables.
(c) Examine the connectors [1] for bent or broken pins, dirt, and
damage.
(d) Connect the antenna cable connectors [1] to the antenna [3] as
follows:
CABLE SLEEVE COLOR
__________________
TCAS ANTENNA CONNECTOR
______________________
Yellow
J1
Black
J2
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(e)
(f)
(g)
(7)
(8)
(9)
J3
Red
J4
Tighten the TCAS Antenna connectors 4 to 6 in-lbs (0.45-0.68
newton-meters) (hand tight plus 1/8 turn).
Put the antenna [3] into position.
Install all of the screws except one.
NOTE:
____
(h)
Blue
Leave one screw out to do the electrical bond check.
Tighten the screws to 20-25 pound-inches (2.3-2.8
newton-meters) of torque.
SUBTASK 760-001
Use a ohmeter, C15292, to make sure the resistance from the antenna
base to the airplane skin is not greater than 0.001 ohm
(AMM TASK 20-40-11-760-801 p201).
SUBTASK 420-002
Install the last screw in the antenna.
(a) Tighten the screw to 20-25 pound-inches (2.3-2.8 newton-meters)
of torque.
SUBTASK 390-001
Apply the sealant, BMS5-95, to the antenna [3],
(AMM TASK 20-30-11-910-801 p201).
(a) Apply the sealant, BMS5-95, to the outer edge of the antenna
[3] (AMM TASK 20-30-11-910-801 p201).
(b) Fill the screw-holes with cotton until a gap of less than 1/8
inch is left.
NOTE:
____
(c)
If foam plugs are supplied with the antenna, install the
foam plugs instead of cotton in the screw-hole.
Apply sealant, BMS5-95, to fill in the screw-holes
(AMM TASK 20-30-11-910-801 p201).
NOTE:
____
Do not apply more than 1/8 inch of sealant into the
screw-holes.
SUBTASK 140-002
(10) Remove the unwanted sealant from around the antenna base
(AMM TASK 20-30-11-910-801 p201).
SUBTASK 860-003
(11) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B6
TCAS
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F.
TCAS Antenna Test
(1)
SUBTASK 740-001
Do a TCAS operational test:
(a) On the ATC control panel, put the mode switch to the test
position:
1) Make sure you hear "TCAS test pass" on the flight
compartment speakers.
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GROUND PROXIMITY WARNING SYSTEM - MAINTENANCE PRACTICES
_______________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) Load the terrain database into the ground proximity warning computer
(GPWC)
(2) Verify the terrain database part number.
TASK 34-46-00-470-801
2.
ú
ú
_________________________
Load
the Terrain Database (Fig. 201)
A. General
(1) This task provides instructions to load the terrain database into
the ground proximity warning computer (GPWC).
(2) The terrain database load is inhibited when the airplane is in the
air. The database will automatically load into the GPWC after you
install the database flash card into the card slot on the front
panel of the GPWC.
(3) You can ignore caution notes (shown on the PCMCIA card) about damage
if you put in or remove the card when the power is on. The EGPWC
automatically applies or removes PCMCIA card power.
B. References
(1) AMM TASK 34-46-00-700-801 p201, Verify the Terrain Database Part
Number
(2) AMM TASK 34-46-00-710-804 p501, Ground Proximity Warning System Operational Test
C. Equipment
(1) Card - Flash, PCMCIA, Loaded with the Terrain Database
(commercially available)
D. Access
(1) Location Zones
(a) 117 Main Equipment Center, Left
(b) 118 Main Equipment Center, Right
E. Procedure
(1)
SUBTASK 860-259
Make sure the ground proximity warning system (GPWS) is operational
(AMM TASK 34-46-00-710-804 p501).
(2)
SUBTASK 860-260
Make sure the COMPUTER OK light on the front panel of the GPWC is
on.
(3)
SUBTASK 860-261
Make sure the EXTERNAL FAULT and the COMPUTER FAIL lights on the
front panel of the GPWC are off.
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[1] GPWC
SEE
ELECTRONIC
EQUIPMENT
RACK, E1
SEE
A
B
ELECTRONIC
EQUIPMENT
ACCESS DOOR,
117A
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACK, E1
SELF TEST
SWITCH
A
STATUS
INDICATORS
HEADPHONE
JACK
UPLOAD/DOWNLOAD
STATUS INDICATORS
MEMORY CARD
SLOT
DOOR
RE-232
CONNECTOR
HANDLE
GROUND PROXIMITY WARNING COMPUTER (GPWC)
B
Ground Proximity Warning Computer
Figure 201
34-46-00-990-801
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(4)
(5)
(6)
SUBTASK 860-262
Open the door on the front panel of the GPWC.
SUBTASK 860-263
Make sure the IN PROG, CARD CHNG, XFER COMP, and XFER FAIL lights on
the GPWC are off.
SUBTASK 470-001
Do these steps to load the terrain database:
(a) Insert the card for the terrain database into the card slot on
the GPWC.
NOTE:
____
(b)
(c)
After the card is installed, the terrain database will
automatically load into the GPWC. It takes
approximately 7 minutes to load the terrain database.
Make sure the IN PROG light on the GPWC comes on.
If the CARD CHNG light on the GPWC comes on, do these steps to
change the card:
NOTE:
____
When the CARD CHNG light comes on, it indicates that
more than one card is necessary to load the terrain
database.
1)
2)
(d)
(e)
(f)
(g)
ú
ú
ú
ú
ú
(7)
Push the eject button on the GPWC and remove the card.
Insert the next card for the terrain database into the card
slot on the GPWC.
3) Make sure the IN PROG light on the GPWC comes on.
If the XFER FAIL light on the GPWC comes on, it indicates that
the terrain database load has failed. You need to load the
terrain database again.
After the load of the terrain database is complete, make sure
the IN PROG light on the GPWC goes off and the XFER COMP light
comes on.
Push the eject button on the GPWC and remove the card.
Make sure the COMPUTER OK light on the GPWC is on and all the
other lights are off.
SUBTASK 700-002
Do this task: Verify the Terrain Database Part Number
(AMM TASK 34-46-00-700-801 p201).
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TASK 34-46-00-700-801
3.
ú
ú
ú
ú
ú
ú
ú
_______________________________________
Verify
the Terrain Database Part Number (Fig. 201)
A. General
(1) This task provides instructions to verify the terrain database part
number. The GPWC level 3 self-test provides aural anunciations of
the current configuration that include the terrain database part
number.
(2) The GPWC level 3 self-test can only be activated when the airplane
is on the ground.
B. References
(1) AMM TASK 34-46-00-470-801 p201, Load the Terrain Database
C. Equipment
(1) Headphone - 600 Ohm, with 1/4 Inch Mono RCA Audio Plug
(commercially available)
D. Access
(1) Location Zones
(a) 117 Main Equipment Center, Left
(b) 118 Main Equipment Center, Right
E. Procedure
NOTE:
____
(1)
(2)
You must know the correct part number for the terrain database.
For the ground proximity warning computer to be an approved
installation, a terrain database with the correct part number must
be installed.
SUBTASK 860-265
Make sure the ground proximity warning system (GPWS) is operational.
SUBTASK 860-266
Make sure the COMPUTER OK light on the front panel of the GPWC is on
and the other lights are off.
(3)
SUBTASK 860-267
Make sure the TERR switches on the EFIS control panels, P7, are on.
(4)
SUBTASK 860-268
Open the door on the front panel of the GPWC.
(5)
SUBTASK 480-001
Plug the headphone into the headphone jack of the GPWC.
(6)
SUBTASK 860-269
Make sure there is no card in the card slot of the GPWC.
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(7)
SUBTASK 700-001
Do these steps to do the level 3 self-test of the GPWC:
NOTE:
____
(a)
(b)
(c)
(d)
The GPWC self-test has six levels that operate in sequence.
The level 3 self-test will occur after the level 2 self-test.
Push the self-test switch on the GPWC for one second.
After the level 1 self-test starts, push the self-test switch
for one second to go to the level 2 self-test.
After the level 2 self-test starts, wait until the PRESS TO
CONTINUE annunciation occurs, then push the self-test switch
for one second to go to the level 3 self-test.
You will hear a sequence of the configuration annuciations for
the GPWS over the headphone.
1) Make sure you hear the terrain database part number the
TERRAIN DATABASE VERSION annunciation.
NOTE:
____
(e)
(f)
Record the terrain database part number.
After you hear the terrain database part number, continue to
push the self-test switch until you hear the PRESS TO CONTINUE
annunciation.
NOTE:
____
(g)
After the PRESS TO CONTINUE annunciates, the level 3
self-test is complete. If you do not push the self-test
switch again, the self-test sequence will stop.
Make sure the terrain database part number or version is
correct.
NOTE:
____
ú
ú
ú
There are several configuration annunciations in the
level 3 self-test. To advance to the terrain
database part number annunciation, you need to push
the self-test switch after each annunciation.
1)
The terrain database part number is provided by your
approval airline department.
If the part number or version is not correct, then do this
task: Load the Terrain Database
(AMM TASK 34-46-00-470-801 p201).
(8)
SUBTASK 860-270
Remove the headphone from the headphone jack on the GPWC.
(9)
SUBTASK 860-271
Close the door on the front panel of the GPWC.
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GROUND PROXIMITY WARNING SYSTEM - ADJUSTMENT/TEST
_________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the ground proximity warning system (GPWS)
(2) A system test of the GPWS.
NOTE:
____
This test uses GPS data. The airplane must be moved to a
position where the GPS antennas have a clear view of the GPS
satellites.
TASK 34-46-00-710-804
2.
__________________________________________________
Ground
Proximity Warning System - Operational Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 27-32-00-710-801 p501, Stall Warning System - Operational
Test
(4) AMM TASK 31-62-00-710-801 p501, Common Display System - Operational
Test
(5) AMM TASK 34-21-00-710-801 p501, Air Data Inertial Reference System Operational Test
(6) AMM TASK 34-31-00-710-801 p501, Instrument Landing System Operational Test
(7) AMM TASK 34-33-00-710-801 p501, Low Range Radio Altimeter (LRRA)
System - Operational Test
(8) AMM TASK 34-43-00-710-802 p501, Weather Radar (WXR) System Operational Test
(9) AMM TASK 34-58-00-710-801 p501, Global Positioning System Operational Test
(10) AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
B. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
C. Prepare for the Operational Test
(1)
(2)
SUBTASK 860-185
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-186
Make sure that this circuit breaker is closed:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
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SUBTASK 860-187
Make sure these systems are on:
(a) Common Display System (AMM TASK 31-62-00-710-801 p501).
(b) Low Range Radio Altimeter System
(AMM TASK 34-33-00-710-801 p501).
(c) Air Data Inertial Reference System
(AMM TASK 34-21-00-710-801 p501).
(d) Weather Radar System (AMM TASK 34-43-00-710-802 p501).
(e) Stall Warning System (AMM TASK 27-32-00-710-801 p501).
(f) Instrument Landing System (AMM TASK 34-31-00-710-801 p501).
(g) Global Positioning System (AMM TASK 34-58-00-710-801 p501).
(h) Flight Management Computer System
(AMM TASK 34-61-00-710-801 p501).
Procedure
(3)
D.
(1)
(2)
(3)
(4)
SUBTASK 860-188
Set the DISPLAYS - SOURCE switch on the instrument switching module,
P5-28, to the ALL ON 1 position.
SUBTASK 860-293
Set the mode switch on the WXR control panel to the TEST position.
SUBTASK 860-294
Do these steps on the two EFIS control panels:
(a) Set the mode switch to the MAP position
(b) Set the range switch to 40 nautical miles
(c) Set the WXR switch to the on position
SUBTASK 750-135
Make sure the weather radar data shows on the displays.
(5)
SUBTASK 750-136
Set the TERR switch on the two EFIS control panels to the on
position.
(6)
SUBTASK 750-131
Make sure the terrain data and the blue TERR messages show on the
displays.
NOTE:
____
Horizontal position data must be available to obtain the blue
TERR message. The amber TERR POS message shows when there is
not enough accuracy in the horizontal position data, or if
the horizontal position data is not available.
NOTE:
____
GPS data can be confirmed by selecting the FMC-CDU to the POS
REF page.
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(7)
(8)
(9)
SUBTASK 750-097
Push and momentarily hold the INOP light on the ground proximity
warning module to do a test of the light.
(a) Make sure the INOP light comes on while you push the INOP
light.
SUBTASK 740-055
Push and hold the GPWS SYS TEST switch on the ground proximity
warning module for approximately six seconds.
(a) Make sure the INOP light comes on within six seconds.
SUBTASK 750-099
Make sure the aural and visual indications occur as follows:
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
GPWS INDICATIONS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
LIGHT/MESSAGE
¦
LIGHT/MESSAGE
¦ AURAL SOUND ¦
¦
(ON)
¦
(OFF)
¦ FROM SPEAKERS ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦Amber GPWS INOP
¦
¦
¦
¦light; cyan TERR
¦
¦
¦
¦TEST on the displays¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦Amber GPWS INOP
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦The two amber
¦
¦GLIDESLOPE
¦
¦BELOW G/S lights
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦The two amber
¦
¦
¦
¦BELOW G/S lights
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦Red PULL UP message ¦Cyan TERR TEST on
¦PULL UP
¦
¦on Capt's and F/O's ¦the displays
¦
¦
¦displays; TERR FAIL ¦
¦
¦
¦on the displays
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦Red PULL UP message ¦
¦
¦
¦on Capt's and F/O's ¦
¦
¦
¦displays
¦
¦
¦
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦Red WINDSHEAR
¦
¦Two tone siren ¦
¦message on Capt's
¦
¦WINDSHEAR
¦
¦and F/O's displays ¦
¦WINDSHEAR
¦
¦
¦
¦WINDSHEAR
¦
¦
¦
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
GPWS INDICATIONS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
LIGHT/MESSAGE
¦
LIGHT/MESSAGE
¦ AURAL SOUND ¦
¦
(ON)
¦
(OFF)
¦ FROM SPEAKERS ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦Red WINDSHEAR
¦
¦
¦
¦message on Capt's
¦
¦
¦
¦and F/O's displays; ¦
¦
¦
¦TERR FAIL on the
¦
¦
¦
¦displays
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦Red PULL UP message ¦
¦TERRAIN,
¦
¦on Capt's and F/O's ¦
¦TERRAIN¦
¦displays; red
¦
¦PULL UP
¦
¦TERRAIN message and ¦
¦
¦
¦test pattern on the ¦
¦
¦
¦displays
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦Red PULL UP message ¦
¦
¦
¦on Capt's and F/O's ¦
¦
¦
¦displays; red
¦
¦
¦
¦TERRAIN message and ¦
¦
¦
¦test pattern on the ¦
¦
¦
¦displays
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦GPWS INOP light;
¦
¦
¦
¦Amber TERRAIN
¦
¦
¦
¦message on the
¦
¦
¦
¦displays
¦
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦Amber TERRAIN
¦
¦
¦
¦message on the
¦
¦
¦
¦displays
¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦SINK RATE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦PULL UP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TERRAIN
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦PULL UP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦DON'T SINK,
¦
¦
¦
¦DON'T SINK
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TOO LOW TERRAIN¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TOO LOW GEAR
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
GPWS INDICATIONS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
LIGHT/MESSAGE
¦
LIGHT/MESSAGE
¦ AURAL SOUND ¦
¦
(ON)
¦
(OFF)
¦ FROM SPEAKERS ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TOO LOW FLAP
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TOO LOW TERRAIN¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦GLIDESLOPE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦BANK ANGLE
¦
¦
¦
¦BANK ANGLE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦MINIMUMS¦
¦
¦
¦MINIMUMS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦Two tone siren ¦
¦
¦
¦WINDSHEAR
¦
¦
¦
¦WINDSHEAR
¦
¦
¦
¦WINDSHEAR
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TOO LOW TERRAIN¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦CAUTION TERRAIN¦
¦
¦
¦CAUTION TERRAIN¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦
¦TERRAIN,
¦
¦
¦
¦TERRAIN-PULL UP¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦GPWS INOP light and ¦
¦
¦
¦test pattern on the ¦
¦
¦
¦displays
¦
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
ú
SUBTASK 860-191
(10) Set the DISPLAYS - SOURCE switch on the instrument switching module
to the ALL ON 2 position.
SUBTASK 750-137
(11) Make sure the terrain data and the TERR messages show on the
displays.
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SUBTASK 740-056
(12) Push and hold the GPWS SYS TEST switch on the ground proximity
warning module.
NOTE:
____
(a)
Do not hold the GPWS SYS TEST switch longer than 2 seconds.
Make sure the red PULL UP message shows on the captain's and
first officer's displays.
NOTE:
____
E.
All other aural and visual annunciations may be ignored.
SUBTASK 860-192
(13) Set the DISPLAYS SOURCE SELECT switch on the instrument switching
module to the AUTO position.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-193
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-46-00-730-804
3.
_____________________________________________
Ground
Proximity Warning System - System Test
A. General
(1) The system test does an internal GPWC check and a check of system
interfaces.
(2) Various systems interface with the GPWC. Some systems send data.
Some systems send a single discrete signal.
(3) The systems that send data have verbal error messages. In this
procedure, you do a check of these signals when you turn a system
off and hear an aural message annunciated.
(a) Some systems supply two sources and are redundant. You turn
one system off and hear an aural message. The GPWC will still
function with data from the redundant system. Then, you turn
the second system off and look for the INOP light on the ground
proximity warning module to come on.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 27-61-00-800-802 p201, Remove Pressure from the Spoiler
Hydraulic Systems A and B
(4) AMM TASK 32-09-00-840-802 p201, Return the Airplane Systems Back to
Their Normal On Ground Condition
(5) AMM TASK 32-09-00-860-801 p201, Put the Airplane in the Air Mode
(6) AMM TASK 32-31-00-730-802 p501, System Test - Landing Gear Control
System
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
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D.
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment, Right
(2) Access Panels
(a) 112A
Forward Access Door
Prepare for the System Test
(1)
SUBTASK 860-194
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-196
Set the left and right ADIRS mode select switches to the NAV
position.
(3)
(4)
(5)
(6)
(7)
SUBTASK 750-134
Make sure the green COMPUTER OK light on the GPWC front panel is on.
(a) Make sure the yellow EXTERNAL FAULT light on the GPWC front
panel is not on.
(b) Make sure the red COMPUTER FAIL light on the GPWC front panel
is not on.
SUBTASK 860-197
Set the FMC transfer switch to the NORMAL position.
(a) Make sure the green COMPUTER OK light on the GPWC front panel
is on.
(b) Make sure the yellow EXTERNAL FAULT light on the GPWC front
panel is not on.
(c) Make sure the red COMPUTER FAIL light on the GPWC front panel
is not on.
SUBTASK 860-295
Set the FMC transfer switch to the BOTH ON R position.
(a) Make sure the green COMPUTER OK light on the GPWC front panel
is on.
(b) Make sure the yellow EXTERNAL FAULT light on the GPWC front
panel is not on.
(c) Make sure the red COMPUTER FAIL light on the GPWC front panel
is not on.
SUBTASK 860-296
Set the FMC transfer switch to the NORMAL position.
SUBTASK 750-100
Make sure the captain's and first officer's BELOW G/S switch-lights
on the P1-1 and P3-1 panels are not on.
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(8)
(9)
SUBTASK 750-101
Make sure these messages do not show on the captain's and first
officer's displays:
(a) PULL UP
(b) WINDSHEAR
SUBTASK 750-102
Make sure the INOP light on the ground proximity warning module is
not on.
SUBTASK 860-200
(10) Make sure the FLAP INHIBIT, GEAR INHIBIT, and TERR INHIBIT switches
on the ground proximity warning module are in the NORMAL position.
SUBTASK 860-202
(11) Make sure the landing gear lever is in the DOWN position.
E.
SUBTASK 860-203
(12) Make sure the LIGHTS switch on the P1-3 panel is in the BRIGHT
position.
Program Pin Test
(1)
(2)
(3)
SUBTASK 740-057
Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 740-058
After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
SUBTASK 740-059
After the level 2 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 3 self-test.
NOTE:
____
(a)
The level 3 self-test starts with the voice annunciation
"SYSTEM CONFIGURATION".
Make sure you hear these aural messages in the sequence that
follows:
1) PART NUMBER XXX-XXXX-XXX-XXX-XXX
2) MOD STATUS X
3) SERIAL NUMBER XXX
4) APPLICATION SOFTWARE VERSION XXXXX
5) CONFIGURATION SOFTWARE VERSION XXXXX
6) TERRAIN DATABASE VERSION XXX
7) ENVELOPE MOD DATABASE VERSION XXX
8) BOOT CODE VERSION XXXX
9) AIRCRAFT TYPE ONE NINE SIX
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10) AUDIO MENU ZERO
11) ALTITUDE CALLOUT MENU TWO EIGHT
ú
ú
12)
13)
14)
15)
16)
17)
OPTIONAL INPUTS SELECTED
DUAL GPS SELECTED
DUAL RADIO ALTIMETER SELECTED
WINDSHEAR CAUTION DISABLED
PWS OPTION 1 SELECTED
BANK ANGLE OPTION 1 SELECTED
SUBTASK 740-086
When you hear the "PRESS TO CONTINUE", wait approximately 30 seconds
for the GPWC to stop the self-test mode.
System Interface Test
(4)
F.
(1)
(2)
(3)
SUBTASK 860-204
Make sure the VHF NAV switch is in the NORMAL position.
SUBTASK 860-205
Set a frequency of 109.00 MHz on the captain's and first officer's
VHF NAV control panels.
SUBTASK 860-206
Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
(4)
SUBTASK 750-103
Make sure the INOP light on the ground proximity warning module does
not show.
(5)
SUBTASK 740-060
Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
(6)
(7)
(8)
SUBTASK 860-207
After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural message "RADIO ALTIMETER BUS 1 INACTIVE" is
annunciated.
SUBTASK 860-208
Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
SUBTASK 750-104
Make sure the INOP light on the ground proximity warning module
shows in 20 seconds or less.
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(9)
SUBTASK 860-209
Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B4
RADIO NAVIGATION RADIO ALTM 1
SUBTASK 750-105
(10) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-210
(11) Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A16
RADIO NAVIGATION RADIO ALTM 2
SUBTASK 750-106
(12) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-211
(13) Open these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
SUBTASK 750-107
(14) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 740-061
(15) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-212
(16) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural messages "IRS BUS 1 INACTIVE" and "AIR DATA
BUS 1 INACTIVE" are annunciated.
SUBTASK 860-213
(17) Open these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C17
ADIRU RIGHT DC
SUBTASK 750-108
(18) Make sure the INOP light on the ground proximity warning module
shows in 20 seconds or less.
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SUBTASK 860-214
(19) Close these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18E5
ADIRU LEFT DC
2) 18E7
ADIRU LEFT AC
SUBTASK 750-109
(20) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 740-062
(21) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-215
(22) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural messages "IRS BUS 2 INACTIVE" and "AIR DATA
BUS 2 INACTIVE" are annunciated.
SUBTASK 860-216
(23) Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6C14
ADIRU RIGHT AC
2) 6C17
ADIRU RIGHT DC
SUBTASK 750-110
(24) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 710-004
(25) Enter the IRS present position in the Inertial System Display Unit
(ISDU).
(a) Set the SYS DSPL switch on the ISDU to the PPOS position.
(b) Enter the latitude on the ISDU.
(c) Push the ENT key on the ISDU to send the latitude data.
(d) Enter the longitude on the ISDU.
(e) Push the ENT key on the ISDU to send the longitude data.
SUBTASK 860-217
(26) Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 740-063
(27) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
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SUBTASK 860-218
(28) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural messages "ILS BUS 1 INACTIVE" and "GPS BUS
1 INACTIVE" are annunciated.
NOTE:
____
Ignore the INOP light on the ground proximity warning
module if it shows, and ignore all other aural messages
that you hear.
SUBTASK 860-219
(29) Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
SUBTASK 860-220
(30) Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 740-064
(31) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-221
(32) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural message "GPS BUS 2 INACTIVE" is
annunciated.
SUBTASK 860-222
(33) Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
SUBTASK 750-111
(34) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-223
(35) Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 750-112
(36) Make sure the INOP light on the ground proximity warning module
shows in 6 seconds or less.
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SUBTASK 860-224
(37) Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 750-113
(38) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-225
(39) Open this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18E5
SMYD-1 CMPTR DC
SUBTASK 750-132
(40) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 740-065
(41) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-226
(42) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural message "SMYD BUS 1 INACTIVE" is
annunciated.
SUBTASK 860-227
(43) Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6B5
SMYD-2 CMPTR DC
SUBTASK 750-114
(44) Make sure the INOP light on the ground proximity warning module
shows in 20 seconds or less.
SUBTASK 860-228
(45) Close this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18E5
SMYD-1 CMPTR DC
SUBTASK 750-115
(46) Make sure the INOP light on the ground proximity warning module does
not show.
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SUBTASK 860-229
(47) Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6B5
SMYD-2 CMPTR DC
SUBTASK 750-116
(48) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-230
(49) Open this circuit breaker:
(a) Circuit Breaker Panel, P18-2:
1) 18D5
DISPLAY DEU 1 PRI
SUBTASK 740-066
(50) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-231
(51) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural message "EFIS BUS 1 INACTIVE" is
annunciated.
SUBTASK 860-232
(52) Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D11
DISPLAY DEU 2 PRI
SUBTASK 740-067
(53) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-233
(54) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural messages "EFIS BUS 1 INACTIVE" and "EFIS
BUS 2 INACTIVE" are annunciated.
SUBTASK 860-234
(55) Close these circuit breakers:
NOTE:
____
(a)
(b)
The DEU may take several minutes to become operational.
Circuit Breaker Panel, P6-1:
1) 6D11
DISPLAY DEU 2 PRI
Circuit Breaker Panel, P18-2:
1) 18D5
DISPLAY DEU 1 PRI
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SUBTASK 750-118
(56) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-235
(57) Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 750-119
(58) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 740-068
(59) Push the GPWS SYS TEST switch on the ground proximity warning module
for one second.
SUBTASK 860-236
(60) After the level 1 self-test starts, push the GPWS SYS TEST switch on
the ground proximity warning module for one second to go to the
level 2 self-test.
(a) Make sure the aural message "WEATHER RADAR HAZARD BUS 1
INACTIVE" is annunciated.
SUBTASK 860-237
(61) Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D13
WEATHER RADAR RT
SUBTASK 750-120
(62) Make sure the INOP light on the ground proximity warning module does
not show.
SUBTASK 860-238
(63) If terrain data does not show on the displays, push the TERR switch
on the EFIS control panel to the on position.
SUBTASK 750-141
(64) Make sure the terrain data and the blue TERR messages show on the
displays.
NOTE:
____
Horizontal position data must be available to obtain the blue
TERR message. The amber TERR POS message shows when there is
not enough accuracy in the horizontal position data, or if
the horizontal position data is not available.
NOTE:
____
GPS data can be confirmed by selecting the FMC-CDU to the POS
REF page.
EFFECTIVITY
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SUBTASK 860-239
(65) Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A7
TERRAIN DISPLAY
SUBTASK 730-003
(66) Make sure the TERR FAIL message shows on the displays.
SUBTASK 860-241
(67) Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A7
TERRAIN DISPLAY
G.
SUBTASK 730-004
(68) Make sure the terrain data shows on the displays.
Air/Ground Discrete Test
(1)
SUBTASK 740-069
Do these steps to do a level 6 self-test:
(a) Push the GPWS SYS TEST switch on the ground proximity
module for one second.
(b) After the level 1 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 2 self-test.
(c) After the level 2 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 3 self-test.
(d) After the level 3 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 4 self-test.
(e) After the level 4 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 5 self-test.
(f) After the level 5 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 6 self-test.
warning
TEST
second to
TEST
second to
TEST
second to
TEST
second to
TEST
second to
SUBTASK 860-243
WARNING:
_______
(2)
DO THE DEACTIVATION PROCEDURE FOR THE SPOILERS OR MOVE ALL
PERSONS AND EQUIPMENT AWAY FROM THE SPOILERS. THE SPOILERS CAN
MOVE QUICKLY AND CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
Deactivate the spoilers or move all persons and equipment away from
the control surfaces. To deactivate the spoilers, do this task:
Remove Pressure from the Spoiler Hydraulic Systems A and B
(AMM TASK 27-61-00-800-802 p201).
EFFECTIVITY
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(3)
(4)
(5)
(6)
SUBTASK 740-087
Use the PSEU BITE to put the airplane in the air mode. To do this,
do this task: do this task: Put the Airplane in the Air Mode
(AMM TASK 32-09-00-860-801 p201).
SUBTASK 740-088
Make sure the display shows SYS 1 IS IN AIR for approximately 2
seconds and then shows SET SYS 1 ON GND?.
SUBTASK 740-089
Make sure the aural message "NOT ON GROUND" is annunciated.
SUBTASK 860-244
Do these steps to put the PSEU in ground mode:
(a) Push and release the YES switch on the PSEU BITE panel.
1) Make sure the display shows ARE YOU SURE?.
(b) Push and release the YES switch on the PSEU BITE panel.
1) Make sure the display shows SYS 1 IS ON GND for
approximately 2 seconds and then shows SET SYS 1 IN AIR?.
2) Make sure the aural message "ON GROUND" is annunciated.
(c) Push and release the ON/OFF switch on the PSEU BITE panel.
1) Make sure the display shows TURN OFF DISPLAY?.
(d) Push and release the YES switch on the PSEU BITE panel.
NOTE:
____
(7)
(8)
(9)
SUBTASK 860-299
Close the Forward Access Door, 112A.
SUBTASK 860-300
Put the airplane systems back to their usual on-ground condition.
To do this, do this task: do this task: Return the Airplane
Systems Back to Their Normal On Ground Condition
(AMM TASK 32-09-00-840-802 p201).
SUBTASK 860-245
Push and release the GPWS SYS TEST switch on the ground proximity
warning module.
NOTE:
____
H.
The display should be blank after this step.
This step will end the level 6 self-test.
Flap Discrete Test
(1)
SUBTASK 740-071
Do these steps to do a level 6 self-test:
(a) Push the GPWS SYS TEST switch on the ground proximity warning
module for one second.
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(b)
(c)
After the
switch on
go to the
After the
switch on
go to the
After the
switch on
go to the
After the
switch on
go to the
After the
switch on
go to the
(d)
(e)
(f)
(2)
(3)
(4)
SYS TEST
one second to
SYS TEST
one second to
SYS TEST
one second to
SYS TEST
one second to
SYS TEST
one second to
SUBTASK 750-121
Set the FLAP INHIBIT switch on the ground proximity warning module
to the INHIBIT position.
(a) Make sure the aural message "LANDING FLAPS" is annunciated.
SUBTASK 860-246
Set the FLAP INHIBIT switch on the ground proximity warning module
to the NORMAL position.
(a) Make sure the aural message "NOT LANDING FLAPS" is annunciated.
SUBTASK 860-247
Push and release the GPWS SYS TEST switch on the ground proximity
warning module.
NOTE:
____
I.
level 1 self-test starts, push the GPWS
the ground proximity warning module for
level 2 self-test.
level 2 self-test starts, push the GPWS
the ground proximity warning module for
level 3 self-test.
level 3 self-test starts, push the GPWS
the ground proximity warning module for
level 4 self-test.
level 4 self-test starts, push the GPWS
the ground proximity warning module for
level 5 self-test.
level 5 self-test starts, push the GPWS
the ground proximity warning module for
level 6 self-test.
This step will end the level 6 self-test.
Landing Gear Handle Discrete Test
(1)
SUBTASK 740-072
Do these steps to do a level 6 self-test:
(a) Push the GPWS SYS TEST switch on the ground proximity
module for one second.
(b) After the level 1 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 2 self-test.
(c) After the level 2 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 3 self-test.
(d) After the level 3 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 4 self-test.
(e) After the level 4 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 5 self-test.
EFFECTIVITY
warning
TEST
second to
TEST
second to
TEST
second to
TEST
second to
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(f)
After the level 5 self-test starts, push the GPWS SYS TEST
switch on the ground proximity warning module for one second to
go to the level 6 self-test.
SUBTASK 750-122
WARNING:
_______
(2)
(3)
(4)
THE GROUND LOCKING PINS MUST BE INSTALLED IN THE LANDING GEAR
BEFORE YOU MOVE THE LANDING GEAR LEVER. IF YOU DO NOT, YOU CAN
INJURE PEOPLE OR DAMAGE EQUIPMENT.
Set the landing gear lever to the OFF position
(AMM TASK 32-31-00-730-802 p501).
(a) Make sure the aural message "LANDING GEAR UP" is annunciated.
SUBTASK 860-248
Set the GEAR INHIBIT switch on the ground proximity warning module
to the INHIBIT position.
(a) Make sure the aural message "LANDING GEAR DOWN" is annunciated.
SUBTASK 860-249
Set the GEAR INHIBIT switch on the ground proximity warning module
to the NORMAL position.
(a) Make sure the aural message "LANDING GEAR UP" is annunciated.
(5)
SUBTASK 860-250
Set the landing gear lever to the DOWN position.
(a) Make sure the aural message "LANDING GEAR DOWN" is annunciated.
(6)
SUBTASK 860-251
Push and release the GPWS SYS TEST switch on the ground proximity
warning module.
NOTE:
____
J.
This step will end the level 6 self-test.
Terrain Inhibit Discrete Test
(1)
SUBTASK 740-073
Do these steps to do a level 6 self-test:
(a) Push the GPWS SYS TEST switch on the ground proximity
module for one second.
(b) After the level 1 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 2 self-test.
(c) After the level 2 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 3 self-test.
(d) After the level 3 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 4 self-test.
EFFECTIVITY
warning
TEST
second to
TEST
second to
TEST
second to
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(e)
(f)
After the
switch on
go to the
After the
switch on
go to the
(2)
(3)
(4)
SYS TEST
one second to
SYS TEST
one second to
SUBTASK 860-252
Set the TERR INHIBIT switch on the ground proximity warning module
to the INHIBIT position.
(a) Make sure the aural message "TERRAIN OFF" is annunciated.
SUBTASK 860-253
Set the TERR INHIBIT switch on the ground proximity warning module
to the NORMAL position.
(a) Make sure the aural message "TERRAIN ON" is annunciated.
SUBTASK 860-254
Push and release the GPWS SYS TEST switch on the ground proximity
warning module.
NOTE:
____
K.
level 4 self-test starts, push the GPWS
the ground proximity warning module for
level 5 self-test.
level 5 self-test starts, push the GPWS
the ground proximity warning module for
level 6 self-test.
This step will end the level 6 self-test.
Glideslope Cancel Test
(1)
(2)
SUBTASK 740-074
Do these steps to do a level 6 self-test:
(a) Push the GPWS SYS TEST switch on the ground proximity
module for one second.
(b) After the level 1 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 2 self-test.
(c) After the level 2 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 3 self-test.
(d) After the level 3 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 4 self-test.
(e) After the level 4 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 5 self-test.
(f) After the level 5 self-test starts, push the GPWS SYS
switch on the ground proximity warning module for one
go to the level 6 self-test.
warning
TEST
second to
TEST
second to
TEST
second to
TEST
second to
TEST
second to
SUBTASK 750-123
Push and hold the captain's BELOW G/S switch-light on the P1-1
panel.
(a) Make sure the aural message "GLIDESLOPE CANCELED" is
annunciated.
EFFECTIVITY
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(3)
(4)
(5)
(6)
SUBTASK 750-124
Release the captain's BELOW G/S switch-light on the P1-1 panel.
(a) Make sure the aural message "GLIDESLOPE ENABLED" is
annunciated.
SUBTASK 750-125
Push and hold the first officer's BELOW G/S switch-light on the P3-1
panel.
(a) Make sure the aural message "GLIDESLOPE CANCELED" is
annunciated.
SUBTASK 750-126
Release the first officer's BELOW G/S switch-light on the P3-1
panel.
(a) Make sure the aural message "GLIDESLOPE ENABLED" is
annunciated.
SUBTASK 860-255
Push and release the GPWS SYS TEST switch on the ground proximity
warning module.
NOTE:
____
L.
This step will end the level 6 self-test.
Master Dim and Test
(1)
SUBTASK 740-075
Push and release the GPWS SYS TEST switch the ground proximity
warning module.
(a) Make sure the captain's and first officer's BELOW G/S
switch-lights come on bright.
NOTE:
____
(2)
(3)
SUBTASK 860-256
Set the LIGHTS switch on the P1-3 panel to the DIM position.
SUBTASK 740-076
Push and release the GPWS SYS TEST switch on the ground proximity
warning module.
(a) Make sure the captain's and first officer's BELOW G/S
switch-lights come on dim.
NOTE:
____
(4)
Ignore the other self-test aural warnings and
indications. Wait 30 seconds for the GPWC to stop the
self-test.
Ignore the other self-test aurals and indications.
SUBTASK 860-257
Set the LIGHTS switch on the P1-3 panel to the BRIGHT position.
EFFECTIVITY
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M.
Put the Airplane Back to Its Usual Condition
(1)
(2)
SUBTASK 410-004
Close the Forward Access Door, 112A.
SUBTASK 860-258
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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GROUND PROXIMITY WARNING COMPUTER - REMOVAL/INSTALLATION
________________________________________________________
1.
General
_______
A. This subject has these tasks:
(1) A removal of the ground proximity warning computer (GPWC)
(2) An installation of the GPWC.
B. The GPWC is on the E1 electronic equipment rack, shelf No. 1, in the main
equipment center.
TASK 34-46-01-000-801
2.
_________________________________________
Ground
Proximity Warning Computer Removal (Fig. 401)
A. References
(1) AMM TASK 06-41-00-800-801 p201, Finding an Access Door or Panel on
the Lower Half of the Fuselage
(2) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center (AMM TASK 06-41-00-800-801 p201).
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE GPWC
[1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE
CAN CAUSE DAMAGE TO THE GPWC [1].
Remove the GPWC [1] (AMM TASK 20-10-07-000-801 p201).
TASK 34-46-01-400-801
3.
______________________________________________
Ground
Proximity Warning Computer Installation (Fig. 401)
A. References
(1) AMM TASK 06-41-00-800-801 p201, Finding an Access Door or Panel on
the Lower Half of the Fuselage
(2) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
EFFECTIVITY
ú
ú
ú
ú
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ELECTRONIC
EQUIPMENT
RACK, E1
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] GPWC
SEE
B
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACK, E1
A
Ground Proximity Warning Computer Installation
Figure 401 (Sheet 1)
F83533
34-46-01-990-801
EFFECTIVITY
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MAINTENANCE MANUAL
GROUND PROXIMITY
WARNING COMPUTER
B
Ground Proximity Warning Computer Installation
Figure 401 (Sheet 2)
H80595
EFFECTIVITY
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ú
ú
(5)
AMM TASK 34-46-00-700-801 p201, Verify the Terrain Database Part
Number
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Computer
¦ 34-46-01
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Installation Procedure
(1)
SUBTASK 860-005
Make sure that this circuit breaker is open:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 420-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE GPWC
[1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE
CAN CAUSE DAMAGE TO THE GPWC [1].
Install the GPWC [1] (AMM TASK 20-10-07-400-801 p201).
SUBTASK 860-002
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
Installation Test
(3)
E.
ú
ú
ú
ú
(1)
SUBTASK 860-003
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 740-003
Make sure the green COMPUTER OK light on the front panel of the GPWC
is on.
(3)
SUBTASK 750-001
Do this task: Verify the Terrain Database Part Number
(AMM TASK 34-46-00-700-801 p201).
EFFECTIVITY
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(4)
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A
(AMM TASK 06-41-00-800-801 p201).
(5)
SUBTASK 860-004
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
ú
ú
ú
ú
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MAINTENANCE MANUAL
GROUND PROXIMITY WARNING MODULE - REMOVAL/INSTALLATION
______________________________________________________
1.
General
_______
A. This subject has these tasks:
(1) A removal of the ground proximity warning module
(2) An installation of the ground proximity warning module.
B. The ground proximity warning module is on the first officer's instrument
panel, P3.
TASK 34-46-02-000-801
2.
_______________________________________
Ground
Proximity Warning Module Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 212 Flight Compartment - Right
B. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-3:
1) 6B10
PANEL & INSTR 28V PRI F/O
2) 6F12
INDICATOR MASTER DIM SECT 6
(b) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 020-001
Remove the ground proximity warning module [1]:
(a) Loosen the quarter turn fasteners [2] on the module [1].
(b) Pull the module [1] from the instrument panel until you can get
to the electrical connector [3].
(c) Disconnect the electrical connector [3] from the module [1].
(d) Remove the ground proximity warning module [1].
TASK 34-46-02-400-801
3.
ú
____________________________________________
Ground
Proximity Warning Module Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Module assy
¦ 31-11-51
03
200 ¦
¦
¦
¦ 33-11-90
03
315 ¦
¦
¦
¦ 34-46-02
01
200 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
EFFECTIVITY
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SEE
A
FLIGHT COMPARTMENT
[1] GROUND PROXIMITY
WARNING MODULE
1
2
[2] QUARTER-TURN
FASTENER
(4 LOCATIONS)
1
MODULES WITH GEAR
INHIBIT SWITCH
2
MODULES WITH TERR
INHIBIT SWITCH
[3] ELECTRICAL
CONNECTOR
FWD
A
Ground Proximity Warning Module Installation
Figure 401
F99483
34-46-02-990-801
EFFECTIVITY
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C.
D.
Access
(1) Location Zones
(a) 212 Flight Compartment - Right
Installation Procedure
(1)
(2)
(3)
(4)
(5)
(6)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-3:
1) 6B10
PANEL & INSTR 28V PRI F/O
2) 6F12
INDICATOR MASTER DIM SECT 6
(b) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 420-001
Install the ground proximity warning module [1]:
(a) Connect the electrical connector [3] to the module [1].
(b) Lightly push the module [1] into the instrument panel.
(c) Tighten the quarter turn fasteners [2] that attach the module
[1] to the instrument panel.
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-3:
1) 6B10
PANEL & INSTR 28V PRI F/O
2) 6F12
INDICATOR MASTER DIM SECT 6
(b) Circuit Breaker Panel, P18-1:
1) 18B7
GND PROX WARN
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 750-001
Make sure the lights on the module [1] are on.
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
VOR SYSTEM - ADJUSTMENT/TEST
____________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the VOR system.
(2) A system test of the VOR system.
TASK 34-51-00-710-801
2.
_____________________________
VOR
System - Operational Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Prepare for the Operational Test
(1)
(2)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-001
Do these steps to prepare for the operational test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the IRS transfer switch on the instrument switching module
to the NORMAL position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the VOR position.
(d) Set the captain's and F/O's EFIS control panel ADF/VOR 1 and
ADF/VOR 2 switches to VOR 1 and VOR 2 position.
(e) Push the CTR button on the captain's and F/O's EFIS control
panels until full VOR display is present on the captain's and
F/O's navigation display (ND).
(f) Set the narrow and wide pointer source select switch
"rabbit-ear" on the standby RMI to the VOR position.
(g) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(h) Set the mode select switches on the IRS to the ATT position.
(i) Push H and put 000 (heading 0°) on the IRS inertial system
display unit (ISDU).
(j) Push the ENT key on the IRS ISDU.
NOTE:
____
A wait of 30 seconds can be necessary for a valid
heading.
EFFECTIVITY
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(k)
D.
Turn the course select controls on the AFCS mode control panel
until the course windows show 000 degrees.
1) Make sure the heading flag on the two EHSIs and the standby
RMI does not show.
VOR Receiver Self Test
(1)
SUBTASK 860-002
Set a frequency of 108.00 MHz on the captain's navigation control
panel.
NOTE:
____
(2)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
SUBTASK 710-002
Push and release the TEST button on the captain's navigation control
panel.
(a) Make sure that these indications agree with the data in
(Table 501):
1) The deviation bar is in view, the TO/FROM indication, and
the VOR flag on the captain's EHSI
2) The No. 1 bearing pointer and VOR flag on the standby RMI.
TABLE 34-51-00-993-801
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
¦
RMI
¦
RMI
¦
ND
¦
ND
¦
ND
¦
¦
TIME
¦ VOR BEARING ¦ VOR FLAG ¦ VOR FLAG ¦
FROM
¦ DEVIATION ¦
¦
(Approx.)
¦
POINTER
¦ IN VIEW ¦ IN VIEW ¦ INDICATOR ¦ BAR IN VIEW ¦
¦
¦
¦
¦
¦ IN VIEW ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
3 |1 second
¦
N/A
¦
YES
¦
YES
¦
NO
¦
NO
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ After 3 seconds ¦ 180° | 3° ¦
NO
¦
NO
¦
YES
¦ Centered
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦After 23 seconds ¦
N/A
¦
YES
¦
NO
¦
NO
¦
NO
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 501
(3)
SUBTASK 860-003
Set the VHF NAV switch on the instrument switching module to the
BOTH ON 1 position.
EFFECTIVITY
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(4)
(5)
SUBTASK 860-004
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
(6)
SUBTASK 860-005
Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
(7)
(8)
(9)
E.
SUBTASK 710-003
Push and release the TEST button on the captain's navigation control
panel.
(a) Make sure that these indications agree with the data in
(Table 501)
1) The deviation bar, the TO/FROM indication, and the VOR flag
on the captain's and the first officer's EHSI
2) The No. 1 bearing pointer and VOR flag on the standby RMI.
SUBTASK 710-004
Push and release the TEST button on the first officer's navigation
control panel.
(a) Make sure that these indications agree with the data in
(Table 501):
1) The deviation bar, the TO/FROM indication, and the VOR flag
on the first officer's EHSI
2) The No. 2 bearing pointer and VOR flag on the standby RMI.
SUBTASK 860-006
Set the VHF NAV switch on the instrument switching module to the
BOTH ON 2 position.
SUBTASK 710-005
Push and release the TEST button on the first officer's navigation
control panel.
(a) Make sure that these indications agree with the data in
(Table 501):
1) The deviation bar, the TO/FROM indication, and the VOR flag
on the captain's and the first officer's EHSI
2) The No. 2 bearing pointer and VOR flag on the standby RMI.
SUBTASK 860-007
(10) Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
EHSI Source Annunciator Test
(1)
SUBTASK 710-006
Set the VHF NAV switch and the navigation control panel (NCP) to
each position that shows in (Table 502).
(a) Make sure the EHSI source annunciators agree with the data in
(Table 502).
EFFECTIVITY
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TABLE 34-51-00-993-802
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ CAPT & F/O NCP ¦ VHF NAV ¦ CAPT EHSI ¦ F/O EHSI
¦
¦
FREQUENCY
¦ SWITCH
¦ ANNUNCIATOR ¦ ANNUNCIATOR ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
108.00 MHz
¦ NORMAL
¦
VOR 1
¦
VOR 2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
108.00 MHz
¦ BOTH ON 1 ¦
VOR 1
¦
VOR 1
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
108.00 MHz
¦ BOTH ON 2 ¦
VOR 2
¦
VOR 2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
108.10 MHz
¦ NORMAL
¦
ILS 1
¦
ILS 2
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
108.10 MHz
¦ BOTH ON 1 ¦
ILS 1
¦
ILS 1
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
108.10 MHz
¦ BOTH ON 2 ¦
ILS 2
¦
ILS 2
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 502
(2)
SUBTASK 860-008
Set a frequency of 108.00 MHz on the captain's navigation control
panel.
(3)
SUBTASK 860-009
Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
(4)
SUBTASK 860-010
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
(5)
(6)
SUBTASK 860-011
Open these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
2) 18A3
RADIO NAVIGATION NAV CONT PNL 1
3) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 710-007
Make sure the indications that
(a) The No. 1 bearing flag is
first officer's RDMI
(b) The No. 1 bearing flag is
(c) The No. 1 bearing flag is
follow occur:
in view on the captain's and the
in view on the standby RMI
in view on the captain's EHSI.
EFFECTIVITY
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(7)
(8)
(9)
SUBTASK 860-012
Open these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A12
RADIO NAVIGATION VOR 2
3) 6A15
RADIO NAVIGATION NAV CONT PNL 2
SUBTASK 710-008
Make sure the indications that
(a) The No. 2 bearing flag is
first officer's RDMI
(b) The No. 2 bearing flag is
(c) The No. 2 bearing flag is
follow occur:
in view on the captain's and the
in view on the standby RMI
in view on the first officer's EHSI.
SUBTASK 860-013
Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A12
RADIO NAVIGATION VOR 2
3) 6A15
RADIO NAVIGATION NAV CONT PNL 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
2) 18A3
RADIO NAVIGATION NAV CONT PNL 1
3) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 860-014
(10) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-51-00-730-801
3.
________________________
VOR
System - System Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-51-00-710-801 p501, VOR System - Operational Test
B. Equipment
(1) Test (or alternative tool)
(a) NAV-402AP-2 Test Set - VOR/ILS, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 402AP-110 Test Set - VOR/ILS, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-30D Test Set - VOR/ILS, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
EFFECTIVITY
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D.
(b) 212 Flight Compartment - Right
Prepare for the System Test
(1)
(2)
SUBTASK 860-015
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-009
Do these steps to prepare for the system test:
(a) Set the VHF NAV switch on the instrument switching module to
the NORMAL position.
(b) Set the IRS switch on the instrument switching module to the
NORMAL position.
(c) Set the mode selector on the captain's and the first officer's
EFIS control panel to the VOR position.
(d) Set the VOR/ADF selectors on the standby RMI to the VOR
position.
(e) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(f) Set the mode select switches on the mode select unit (MSU) to
the ATT position.
(g) Push H on the inertial system display unit (ISDU).
(h) Push 000 on the ISDU for a heading of 0°.
(i) Push the ENT key on the ISDU.
NOTE:
____
A wait of 30 seconds can be necessary for a valid
heading.
(j)
E.
Turn the course select controls on the DFCS mode control panel
until the course windows show 000 degrees.
1) Make sure the heading flag on the two EHSIs and the standby
RMI does not show.
VOR System Test
(1)
SUBTASK 710-010
Do this task: VOR System - Operational Test
(AMM TASK 34-51-00-710-801 p501).
(2)
SUBTASK 860-016
Set a frequency of 108.00 MHz on the captain's navigation control
panel.
NOTE:
____
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
EFFECTIVITY
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MAINTENANCE MANUAL
(3)
SUBTASK 730-001
Set up the test set, NAV-402AP-2, to supply a 0° omni radial at a
frequency of 108.00 MHz.
NOTE:
____
(a)
(b)
(c)
(4)
Omni radial is a signal that is along a line in the magnetic
direction (from the station) shown by the number of the
radial. For example, 0° omni radial is north of the station.
Make sure the deviation bar shows on
Make sure the VOR flag does not show
Make sure the No. 1 bearing pointers
first officer's RDMI and the standby
SUBTASK 730-002
Turn the captain's course select control on the DFCS mode control
panel until the deviation bar is in the center.
(a) Make sure the course window on the DFCS mode control panel
shows 000 |002°.
NOTE:
____
(b)
(5)
(6)
(7)
(8)
the captain's EHSI.
on the captain's EHSI.
on the captain's and the
RMI show 180 |4°.
The deviation bar can also be in the center when the
course counter shows 180°. Do not use this radial.
Make sure a FROM indication shows on the captain's EHSI.
SUBTASK 730-003
Turn the captain's course select control on the DFCS mode control
panel until the deviation bar on the captain's EHSI is on the second
left dot.
(a) Make sure the course window on the DFCS mode control panel
shows 350 |004°.
SUBTASK 730-004
Turn the captain's course select control on the DFCS mode control
panel until the deviation bar on the captain's EHSI is on the second
right dot.
(a) Make sure the course window on the DFCS mode control panel
shows 010 |004°.
SUBTASK 860-017
Turn the captain's course select control on the DFCS mode control
panel until the course window shows 000.
SUBTASK 730-005
Set the VOR bearing selector on the test set, NAV-402AP-2, to the
omni radials shown in (Table 503).
(a) Make sure that these indications agree with the data in
(Table 503):
1) The No. 1 bearing pointers on the captain's and the first
officer's RDMI
2) The No. 1 bearing pointer on the standby RMI
EFFECTIVITY
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3)
The TO-FROM indication and the deviation bar in the
captain's EHSI.
TABLE 34-51-00-993-803
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ BEARING SELECTOR ¦
RDMI BEARING
¦ TO - FROM ¦ DEVIATION BAR
¦
¦
SETTING
¦ POINTER INDICATION ¦
FLAG
¦
INDICATION
¦
¦ (OMNI RADIAL)
¦
¦ INDICATION ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
000°
¦
180 | 4°
¦
FROM
¦ Centered
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
315°
¦
135 | 4°
¦
FROM
¦ Moved full scale ¦
¦
¦
¦
¦ to the right
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
270°
¦
90 | 4°
¦
---¦ Moved full scale ¦
¦
¦
¦
¦ to the right
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
225°
¦
45 | 4°
¦
TO
¦ Moved full scale ¦
¦
¦
¦
¦ to the right
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
180°
¦
000 | 4°
¦
TO
¦ Centered
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
135°
¦
315 | 4°
¦
TO
¦ Moved full scale ¦
¦
¦
¦
¦ to the left
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
90°
¦
270 | 4°
¦
---¦ Moved full scale ¦
¦
¦
¦
¦ to the left
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
45°
¦
225 | 4°
¦
FROM
¦ Moved full scale ¦
¦
¦
¦
¦ to the left
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
000°
¦
180 | 4°
¦
FROM
¦ Centered
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
45°
¦
225 | 4°
¦
FROM
¦ Moved full scale ¦
¦
¦
¦
¦ to the left
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
90°
¦
270 | 4°
¦
---¦ Moved full scale ¦
¦
¦
¦
¦ to the left
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
135°
¦
315 | 4°
¦
TO
¦ Moved full scale ¦
¦
¦
¦
¦ to the left
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
180°
¦
000 | 4°
¦
TO
¦ Centered
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
225°
¦
45 | 4°
¦
TO
¦ Moved full scale ¦
¦
¦
¦
¦ to the right
¦
Table 503
EFFECTIVITY
34-51-00
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TABLE 34-51-00-993-803
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦ BEARING SELECTOR ¦
RDMI BEARING
¦ TO - FROM ¦ DEVIATION BAR
¦
¦
SETTING
¦ POINTER INDICATION ¦
FLAG
¦
INDICATION
¦
¦ (OMNI RADIAL)
¦
¦ INDICATION ¦
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
270°
¦
90 | 4°
¦
---¦ Moved full scale ¦
¦
¦
¦
¦ to the right
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
315°
¦
135 | 4°
¦
FROM
¦ Moved full scale ¦
¦
¦
¦
¦ to the right
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
000°
¦
180 | 4°
¦
FROM
¦ Centered
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 503
(9)
SUBTASK 730-006
Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
(a) Make sure the No. 2 bearing pointers on the captain's and the
first officer's RDMI and standby RMI show 180 |4°.
SUBTASK 730-007
(10) Turn the first officer's course select control on the DFCS mode
control panel until the deviation bar on the first officer's EHSI is
in the center.
(a) Make sure the course window on the DFCS mode control panel
shows 000 |002°.
NOTE:
____
(b)
The deviation bar can also be in the center when the
course counter shows 180°. Do not use this radial.
Make sure a FROM indication shows on the first officer's EHSI.
SUBTASK 730-008
(11) Turn the first officer's course select control on the DFCS mode
control panel until the deviation bar on the first officer's EHSI is
on the second left dot.
(a) Make sure the course window on the DFCS mode control panel
shows 350 |004°.
SUBTASK 730-009
(12) Turn the first officer's course select control on the DFCS mode
control panel until the deviation bar on the first officer's EHSI is
on the second right dot.
(a) Make sure the course window on the DFCS mode control panel
shows 010 |004°.
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SUBTASK 860-018
(13) Turn the first officer's course select control on the DFCS mode
control panel until the course window shows 000.
SUBTASK 730-010
(14) Set the VOR bearing selector on the test set, NAV-402AP-2, to the
omni radials shown in (Table 503).
(a) Make sure that these indications agree with the data in
(Table 503):
1) The No. 2 bearing pointers on the captain's and the first
officer's RDMI
2) The No. 2 bearing pointer on the standby RMI
3) The TO-FROM indication and the deviation bar in the first
officer's EHSI.
SUBTASK 860-019
(15) Set the VHF NAV switch on the instrument switching module to the
BOTH ON 1 position.
SUBTASK 860-020
(16) Set a frequency of 108.10 MHz on the first officer's navigation
control panel.
SUBTASK 860-021
(17) Turn the captain's course selector control on the DFCS mode control
panel until the course window shows 000.
SUBTASK 730-011
(18) Set the VOR bearing selector on the test set, NAV-402AP-2, to a 135°
omni radial.
(a) Make sure the No. 1 bearing pointers on the captain's and the
first officer's RDMI and standby RMI show 315 |4°.
(b) Make sure the deviation bars on the two EHSIs are full scale in
the left direction.
(c) Make sure a TO indication shows on the two EHSIs.
SUBTASK 860-022
(19) Set the VHF NAV switch on the instrument switching module to the
BOTH ON 2 position.
SUBTASK 860-023
(20) Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
SUBTASK 860-024
(21) Set a frequency of 108.10 MHz on the captain's navigation control
panel.
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SUBTASK 860-025
(22) Turn the first officer's course selector control on the DFCS mode
control panel until the course window shows 000.
SUBTASK 730-012
(23) Set the VOR bearing selector on the test set, NAV-402AP-2, to a 315°
omni radial.
(a) Make sure the No. 2 bearing pointers on the captain's and the
first officer's RDMI and standby RMI show 135 |4°.
(b) Make sure the deviation bars on the two EHSIs are full scale in
the right direction.
(c) Make sure a FROM indication shows on the two EHSIs.
F.
SUBTASK 860-026
(24) Set a frequency of 108.00 MHz on the captain's navigation control
panel.
System Frequency Control and Aural Outputs Test
NOTE:
____
No adjustment of the receiver gain squelch is necessary.
should be detected regardless of the noise level.
The tone
(1)
SUBTASK 860-027
Set a frequency of 108.10 MHz on the first officer's navigation
control panel.
(2)
SUBTASK 860-028
Use the switches on the test set, NAV-402AP-2, to supply a signal of
1020 Hz.
(3)
SUBTASK 860-029
Push the receiver volume controls for NAV-2 on each audio selector
panel to set the volume to off.
(4)
SUBTASK 860-030
Push the receiver volume controls for NAV-1 on each audio selector
panel to set the volume to on.
(5)
SUBTASK 730-013
Turn the receiver volume controls clockwise for NAV-1 on each audio
selector panel.
(a) Make sure you can hear a tone through the interphone system.
(b) Make sure you can hear a tone at each audio selector panel with
a headset.
(c) Make sure you cannot hear the tone when you change the
frequency on the test set, NAV-402AP-2, to a different
frequency.
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(6)
SUBTASK 860-031
Push the receiver volume controls for NAV-1 on each audio selector
panel to set the volume to off.
(7)
SUBTASK 860-032
Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
(8)
SUBTASK 860-033
Set a frequency of 108.10 MHz on the captain's navigation control
panel.
(9)
SUBTASK 860-034
Push the receiver volume controls for NAV-2 on each audio selector
panel to set the volume to on.
SUBTASK 730-014
(10) Turn the receiver volume controls clockwise for NAV-2 on each audio
selector panel.
(a) Make sure you can hear a tone through the interphone system.
(b) Make sure you can hear a tone at each audio selector panels
with a headset.
(c) Make sure you cannot hear the tone when you change the
frequency on the test set, NAV-402AP-2, to a different
frequency.
SUBTASK 860-035
(11) Push the receiver volume controls for NAV-2 on each audio selector
panel to set the volume to off.
G.
SUBTASK 860-036
(12) Set a frequency of 108.00 MHz on the captain's navigation control
panel.
Heading Input Test
(1)
SUBTASK 860-037
Make sure the captain's navigation control panel is set to a
frequency of 108.00 MHz.
(2)
SUBTASK 860-038
Make sure the first officer's navigation control panel is set to a
frequency of 108.00 MHz.
(3)
SUBTASK 860-039
Use the test set, NAV-402AP-2, to supply a 315° omni radial at a
frequency of 108.00 MHz.
(a) Make sure the deviation bar shows on the captain's EHSI.
(b) Make sure the VOR flag does not show on the captain's EHSI.
EFFECTIVITY
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(4)
(5)
(6)
(7)
(8)
(9)
SUBTASK 860-040
Make sure the VHF NAV switch on the instrument switching module is
in the NORMAL position.
SUBTASK 860-041
Open these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A12
RADIO NAVIGATION VOR 2
3) 6A15
RADIO NAVIGATION NAV CONT PNL 2
SUBTASK 730-015
Put headings of 45°, 120°, 240°, and 000° into the ISDU for the left
inertial reference system (IRS).
(a) Make sure the compass card and the No. 1 bearing pointer in the
captain's RDMI move counterclockwise at the same time.
(b) Make sure the No. 1 bearing pointer follows the compass card's
movement at a slower speed.
(c) Make sure the compass card and the No. 1 bearing pointer in the
first officer's RDMI do not move.
SUBTASK 860-042
Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A12
RADIO NAVIGATION VOR 2
3) 6A15
RADIO NAVIGATION NAV CONT PNL 2
SUBTASK 860-043
Open these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
2) 18A3
RADIO NAVIGATION NAV CONT PNL 1
3) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 730-016
Put headings of 45°, 120°, 240°, and 000° into the ISDU for the
right inertial reference system (IRS).
(a) Make sure the compass card and the No. 2 bearing pointer in the
first officer's RDMI move counterclockwise at the same time.
(b) Make sure the No. 2 bearing pointer follows the compass card's
movement at a slower speed.
(c) Make sure the compass card and the No. 2 bearing pointer in the
captain's RDMI do not move.
SUBTASK 860-044
(10) Close these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
2) 18A3
RADIO NAVIGATION NAV CONT PNL 1
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3)
18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 860-045
(11) Set the IRS switch on the instrument switching module to the BOTH ON
1 position.
SUBTASK 860-046
(12) Open these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
2) 18A3
RADIO NAVIGATION NAV CONT PNL 1
3) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 730-017
(13) Put headings of 45°, 120°, 240°, and 000° into the ISDU for the left
inertial reference system (IRS).
(a) Make sure the compass card and the No. 2 bearing pointer in the
RDMIs move counterclockwise at the same time.
(b) Make sure the No. 2 bearing pointer follows the compass card's
movement at slower speed.
SUBTASK 860-047
(14) Close these circuit breakers:
(a) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
2) 18A3
RADIO NAVIGATION NAV CONT PNL 1
3) 18B1
RADIO NAVIGATION NAV SNSR DC-1
SUBTASK 860-048
(15) Set the IRS switch on the instrument switching module to the BOTH ON
2 position.
SUBTASK 860-049
(16) Open these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A12
RADIO NAVIGATION VOR 2
3) 6A15
RADIO NAVIGATION NAV CONT PNL 2
SUBTASK 730-018
(17) Put headings of 45°, 120°, 240°, and 000° into the ISDU for the
right inertial reference system (IRS).
(a) Make sure the compass card and the No. 1 bearing pointer in the
RDMIs move counterclockwise at the same time.
(b) Make sure the No. 1 bearing pointer follows the compass card's
movement at a slower speed.
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SUBTASK 860-050
(18) Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A10
RADIO NAVIGATION NAV SNSR DC-2
2) 6A12
RADIO NAVIGATION VOR 2
3) 6A15
RADIO NAVIGATION NAV CONT PNL 2
SUBTASK 860-051
(19) Set the IRS switch on the instrument switching module to the NORMAL
position.
SUBTASK 860-052
(20) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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VOR/MKR RECEIVER - REMOVAL/INSTALLATION
_______________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the VOR/MKR receiver.
(2) An installation of the VOR/MKR receiver.
B. The two VOR/MKR receivers are in the main equipment center. The No. 1
VOR/MKR receiver is on the E1 electronics equipment rack, shelf No. 2.
The No. 2 VOR/MKR receiver is on E1 electronics equipment rack, shelf No.
4.
TASK 34-51-01-000-801
2.
ú
________________________
VOR/MKR
Receiver Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A12
RADIO NAVIGATION VOR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A to get access to the
VOR/MKR receiver.
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
VOR/MKR RECEIVER. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE VOR/MKR RECEIVER.
To remove the No. 1 or No. 2 VOR/MKR receiver [1], do this task:
E/E Box Removal (AMM TASK 20-10-07-000-801 p201).
EFFECTIVITY
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ELECTRONIC
EQUIPMENT
RACK, E1
A
SEE
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] VOR/MKR
RECEIVER
NO. 1
(E1-2)
[1] VOR/MKR
RECEIVER
NO. 2
(E1-4)
FWD
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
ELECTRONIC EQUIPMENT RACK, E1
A
VOR/MKR Receiver Installation
Figure 401
G13489
34-51-01-990-801
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TASK 34-51-01-400-801
3.
_____________________________
VOR/MKR
Receiver Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Receiver
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A12
RADIO NAVIGATION VOR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
SUBTASK 420-001
CAUTION:
_______
(2)
(3)
(4)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE
VOR/MKR RECEIVER. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE VOR/MKR RECEIVER.
To install the VOR/MKR receiver [1], do this task:
Installation (AMM TASK 20-10-07-400-801 p201).
E/E Box
SUBTASK 860-003
Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A12
RADIO NAVIGATION VOR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
EFFECTIVITY
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E.
Installation Test
(1)
(2)
(3)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-001
Tune the captain's and first officer's navigation control panels to
a local VOR station.
(a) Make sure you can hear the station identification code over the
flight interphone system.
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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VOR/LOC ANTENNA - REMOVAL/INSTALLATION
______________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the VOR/LOC antenna
(2) An installation of the VOR/LOC antenna.
B. The VOR/LOC antenna (M41) is installed at the top of the vertical
stabilizer (fin).
TASK 34-51-02-000-801
2.
_______________________
VOR/LOC
Antenna Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
(c) 326 Vertical Fin - Fin Tip
B. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A12
RADIO NAVIGATION VOR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
SUBTASK 020-001
Remove the VOR/LOC antenna [2]:
(a) Remove the screws [6] that attach the leading edge [1] to the
VOR/LOC antenna [2] and the vertical stabilizer.
(b) Remove the leading edge [1] of the fin tip from the VOR/LOC
antenna [2].
(c) Disconnect the electrical connectors [7].
(d) Put protective covers on the electrical connectors [7].
(e) Remove the screws [5] that attach the VOR/LOC antenna [2] to
the vertical stabilizer.
NOTE:
____
(f)
(3)
Do not remove the screws that attach the trailing edge
to the VOR/LOC antenna [2]. The trailing edge can be
removed with the VOR/LOC antenna [2].
Remove the VOR/LOC antenna [2] and the attached trailing edge
from the vertical stabilizer.
SUBTASK 020-002
Remove the static discharger [3].
(a) Remove the screws [4] from the static discharger [3].
EFFECTIVITY
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SEE
A
[3] STATIC
DISCHARGER
(2 LOCATIONS)
[2] VOR/LOC
ANTENNA
[4] SCREW
(2 LOCATIONS)
TRAILING EDGE
RESISTANCE
MEASUREMENT
TEST POINT
AREA
[1] LEADING
EDGE
[7] ELECTRICAL
CONNECTOR
(2 LOCATIONS)
[5] SCREW
[6] SCREW
(40 LOCATIONS)
(12 LOCATIONS)
FWD
VOR/LOC ANTENNA
(REMOVED)
A
VOR/LOC Antenna Installation
Figure 401
F57010
34-51-02-990-801
EFFECTIVITY
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(b)
Remove the static discharger [3] from the the trailing edge.
NOTE:
____
Keep the static discharger [3] for installation on new
VOR/LOC antenna [2] assembly.
TASK 34-51-02-400-801
3.
____________________________
VOR/LOC
Antenna Installation (Fig. 401)
A. General
(1) The installation task has an installation test.
(2) The installation test makes sure that the VOR/LOC antenna [2]
operates correctly.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 51-21-91-620-801 p701, Prepare the Surface to Apply the
Corrosion Inhibiting Compound
(3) AMM TASK 51-21-91-620-802 p701, Apply the Corrosion Inhibiting
Compound
(4) SWPM 20-20-00
C. Consumable Materials
(1) C00308 Compound, Corrosion preventive, petroleum hot application
(medium film) - MIL-C-11796, Class II
D. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
(c) 326 Vertical Fin - Fin Tip
E. Installation Procedure
(1)
(2)
(3)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A12
RADIO NAVIGATION VOR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
SUBTASK 100-001
Clean the mating surfaces of the VOR/LOC antenna [2] and the
airplane structure. To clean the surfaces, do this task: Prepare
the Surface to Apply the Corrosion Inhibiting Compound
(AMM TASK 51-21-91-620-801 p701).
SUBTASK 620-001
Apply a layer of compound, MIL-C-11796, Class II to the mating
surfaces of the VOR/LOC antenna [2] and the airplane structure. To
apply it, do this task: Apply the Corrosion Inhibiting Compound
(AMM TASK 51-21-91-620-802 p701).
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(4)
(5)
SUBTASK 420-001
If the trailing edge is not installed, attach the trailing edge to
the VOR/LOC antenna [2].
SUBTASK 420-002
Install the static discharger [3]:
NOTE:
____
(a)
Use static discharger [3] removed during removal of VOR/LOC
antenna [2] unless they are missing or damaged. If missing
or damaged, new static discharger [3] are required.
(b)
Insert the static discharger [3] into the slots on the trailing
edge.
Install the screws [4] that attach the static discharger [3] to
the trailing edge.
(6)
(7)
SUBTASK 420-003
Install the VOR/LOC antenna [2]:
(a) Align the VOR/LOC antenna [2] to the screw holes that hold the
VOR/LOC antenna [2] to the vertical stabilizer.
(b) Remove the protective covers from the electrical connectors
[7].
(c) Examine the electrical connectors [7] for bent or broken pins,
dirt, and damage.
(d) Connect the electrical connectors [7].
(e) Align the leading edge [1] with the screw holes on the top of
the vertical stabilizer.
(f) Apply compound, MIL-C-11796, Class II to the screw [6] threads.
To apply it, do this task: Apply the Corrosion Inhibiting
Compound (AMM TASK 51-21-91-620-802 p701).
(g) Apply compound, MIL-C-11796, Class II to the screw [5] threads.
To apply it, do this task: Apply the Corrosion Inhibiting
Compound (AMM TASK 51-21-91-620-802 p701).
(h) Install the screws [6] that attach the leading edge [1] to the
VOR/LOC antenna [2] and the vertical stabilzer.
(i) Install the screws [5] that attach the VOR/LOC antenna [2] to
the vertical stabilizer.
SUBTASK 760-001
Do a check of the resistance between the VOR/LOC antenna and the
airplane skin (SWPM 20-20-00).
NOTE:
____
(a)
Refer to
(Fig. 401) for resistance test point locations.
Make sure the resistance is not more than 0.001 ohms.
EFFECTIVITY
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SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A12
RADIO NAVIGATION VOR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A1
RADIO NAVIGATION VOR/MKR BCN 1
Installation Test
(8)
F.
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-005
Set a local VOR frequency on the captain's navigation control panel.
NOTE:
____
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
(3)
SUBTASK 860-006
Push the receiver volume controls for NAV-1 and NAV-2 on each audio
selector panel to set the volume to off.
(4)
SUBTASK 860-007
Push the receiver volume controls for NAV-1 on the captain's audio
selector panel to set the volume to on.
(5)
SUBTASK 730-001
Turn the receiver volume controls clockwise for NAV-1 on the
captain's audio selector panel.
(a) Make sure you can hear the station identification tone through
the interphone system.
(6)
SUBTASK 860-008
Push the receiver volume controls for NAV-1 on the captain's audio
selector panel to set the volume to off.
(7)
SUBTASK 860-009
Set a local VOR frequency on the first officer's navigation control
panel.
(8)
SUBTASK 860-010
Push the receiver volume controls for NAV-2 on the first officer's
audio selector panel to set the volume to on.
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(9)
SUBTASK 730-002
Turn the receiver volume controls clockwise for NAV-2 on the first
officer's audio selector panel.
(a) Make sure you can hear the station identification tone through
the interphone system.
SUBTASK 860-011
(10) Push the receiver volume controls for NAV-2 on the first officer's
audio selector panel to set the volume to off.
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AIR TRAFFIC CONTROL (ATC) SYSTEM - ADJUSTMENT/TEST
__________________________________________________
1.
General
_______
A. This procedure has these tasks for the ATC system:
(1) Air Traffic Control System - Operational Test
(2) Air Traffic Control System - System Test (With the IFR ATC-601 Test
Set)
(3) Air Traffic Control System - System Test (With the TIC 48 or T-49
Test Set)
(4) Air Traffic Control System - Mode S Address Test
B. The operational test is a fast check of the ATC system that uses the ATC
system BITE function. No test equipment is needed.
C. The system test is a complete test of the ATC system. It does an
operational test first then it uses test equipment to examine the ATC
code reception, altitude reporting, transponder sensitivity, side lobe
suppression, transmitter frequency and diversity.
D. Because the ATC transponder responds to signals from the antenna with the
strongest signal strength, it is necessary to put the test set antenna
close to the airplanes antenna.
TASK 34-53-00-710-801
2.
_____________________________________________
Air
Traffic Control System - Operational Test
A. General
(1) The operational test is a fast check of the ATC system. It uses
only the system's BITE function. No special test or ground
equipment is necessary.
(2) The ATC transponder BITE circuitry does a self-test on all internal
circuitry. This includes the injection of Mode S signals into the
receiver unit to examine if the signals are processed properly. If
the Mode S function fails, the red fail LED indicator comes on.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Procedure
(1)
(2)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-002
On the ATC control panel do these steps:
(a) Put the ATC transponder select switch to the No. 1 position.
(b) Put the ATC mode select switch to the ALT OFF position.
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(3)
(4)
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center.
SUBTASK 860-023
Do the left ATC transponder (No. 1) BITE test:
(a) Push and release the TEST switch on the front panel of the left
ATC transponder (No. 1) at the E1-2 shelf.
NOTE:
____
1)
(5)
(6)
The TEST switch must be depressed for 1.5 seconds.
Make sure the sequence that follows occurs:
a) All the LEDs come on for approximately one second and
then go off
b) The pass lamp annunciates PASS.
c) All the LEDs go off.
SUBTASK 860-004
Put the ATC transponder select switch to the No. 2 position.
SUBTASK 860-024
Do the left ATC transponder (No. 2) BITE test:
(a) Push and release the TEST switch on the front panel of the
right ATC transponder (No. 2) at the E1-2 shelf.
NOTE:
____
1)
(7)
The TEST switch must be depressed for 1.5 seconds.
Make sure the sequence that follows occurs:
a) All the LEDs come on for approximately one second and
then go off
b) The pass lamp annunciates PASS.
c) All the LEDs go off.
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
TASK 34-53-00-730-801
3.
________________________________________________________________________
Air
Traffic Control System - System Test (With the IFR ATC-601 Test Set)
A. General
(1) This system test is a more complete check of the ATC system. The
system test first does the ATC - Operational Test, then it uses
ground test equipment to examine the left and right ATC systems.
(2) The IFR 601 test set is used to test the functionality of the mode S
transponder. All the tests can be run automatically in the AUTO
mode or individually in single test mode. The results from the last
test are shown on the individual test pages. The PASSED/FAILED
indication is shown on top of the page. To do a single test, use
the select keys to get to the desired test and push the RUN/STOP
key.
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B.
ú
ú
C.
D.
E.
References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(2) AMM TASK 32-09-00-860-801 p201, Put the Airplane in the Air Mode
(3) AMM TASK 32-09-00-860-802 p201, Return the Airplane to the Ground
Mode
(4) AMM TASK 34-53-00-710-801 p501, Air Traffic Control System Operational Test
(5) WDM 34-53-11, 34-53-21
(6) WDM 34-53-21, sheet 2
Equipment
(1) ATC-601-2 Test Set - ATC Transponder, Ramp (Mode S Tester)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 143 Area Below Aft Cargo Compartment - Left
(d) 144 Area Below Aft Cargo Compartment - Right
(e) 200 Upper Half of Fuselage
(f) 211 Flight Compartment - Left
(g) 212 Flight Compartment - Right
Prepare for the System Test
(1)
(2)
SUBTASK 710-001
Do this task: Air Traffic Control System - Operational Test
(AMM TASK 34-53-00-710-801 p501).
SUBTASK 840-001
Prepare the test set, ATC-601-2, for the ATC System Test:
CAUTION:
_______
(a)
DO NOT PLACE THE REMOTE TEST SET ANTENNA CLOSER THAN 15
INCHES (0.40 METERS) TO THE AIRCRAFT ANTENNA WITH THE TEST
SET ON. THIS WILL CAUSE DAMAGE TO THE TEST SET.
Put the test set, ATC-601-2, antenna approximately 30 feet from
the necessary ATC antenna.
NOTE:
____
(b)
(c)
The antenna must be within the line of sight of the ATC
antenna and positioned towards the antenna.
Connect the test test set, ATC-601-2, antenna coax cable to the
test set, ATC-601-2 ANTENNA connector.
Push the POWER button on the .
NOTE:
____
This is a source of interference for radio and L-band
radar equipment operating on the airplane and located
near the test set. Turn the test set off as soon as the
test is completed or when you must perform other radio
checks on the airplane.
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(d)
(e)
(f)
(g)
(h)
(i)
(j)
(k)
(3)
(4)
Push the SELF TEST key on the test set, ATC-601-2.
Push the RUN/STOP key to start the self test.
1) Make sure the test set, ATC-601-2, display shows PASSED.
Push the SETUP key to enter the SETUP menu.
Enter 30 feet in the RANGE field for the TOP and BOTTOM
antenna.
Enter 17 feet for the HEIGHT field for the TOP antenna and 3
feet for the BOTTOM antenna.
1) Use the SLEW keys to change the values.
2) Use the SELECT keys to change the items.
3) Use the SLEW keys to select the necessary antenna.
Choose the necessary antenna on the SELECTED field.
Enter the gain listed on the test set, ATC-601-2, antenna into
the GAIN_1030 and GAIN_1090 field.
Enter the cable loss listed on the cable in the LOSS field.
SUBTASK 860-006
Set the captain's and first officer's altimeter to 29.92 inches of
mercury.
SUBTASK 860-007
On the ATC control panel do these steps:
CAUTION:
_______
(a)
(b)
(c)
(5)
(6)
DO NOT USE CODES 7500, 7600-7677, AND 7700-7777.
THESE CODES ONLY IN EMERGENCIES.
YOU USE
Set the code switches to a desired ATC ID code.
Set the transponder select switch to the No. 1 position.
Set the Mode Select switch to the ALT ON position.
SUBTASK 860-008
Open these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
(b) Circuit Breaker Panel, P6-3:
1) 6D18
LANDING GEAR AURAL WARN
SUBTASK 860-025
Put the airplane in the air mode with the BITE in the Proximity
Switch Electronics Unit (PSEU), do this task: Put the Airplane in
the Air Mode (AMM TASK 32-09-00-860-801 p201).
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F.
ATC System Test
(1)
SUBTASK 860-009
Do the ATC System Test:
(a) Push the AUTO TEST key on the test set, ATC-601-2.
NOTE:
____
(b)
(c)
(d)
(e)
Use the RUN/STOP key to start or stop the individual
tests and the SELECT key to select each individual test.
The results from the AUTO test show at each individual
test display.
Do a check of the REPLY DELAY TEST.
1) Make sure the reply delay is 128.00øs (|0.25øs) for mode S
and ITM.
2) Make sure the reply delay is 3.00øs (|0.50øs) for ATC A and
C.
Do a check of the REPLY JITTER TEST.
1) Make sure the reply jitter is a 0.05øs for mode S.
2) Make sure the reply jitter is a 0.06øs for ITM A and C.
3) Make sure the reply jitter is a 0.1øs for ATC A and C.
Do a check of the ATCRBS REPLY TEST.
1) Make sure the spacing of the F1 to F2 pulse is 20.3øs
(|0.10øs).
2) Make sure the duration of the F1, F2 pulse is 0.45øs
(|0.10øs).
Do a check of the SLS LEVEL TEST.
1) Make sure the reply is received when the SLS pulse is -9dB
and no reply is received when the SLS pulse is 0dB.
NOTE:
____
(f)
(g)
(h)
(i)
You must do the SLS level test in less than 95 feet
(28.96 meters) from the UUT antenna.
Do a check of the ATC ONLY ALL-CALL TEST.
1) Make sure the mode S transponder did not reply to the
interrogation (PASSED TEST).
Do a check of the MODE S ALL CALL TEST.
1) Make sure the test set shows PASSED and the airplane's mode
S address.
Do a check of the INVALID MODE S ADDRESS TEST.
1) Make sure the mode S transponder did not reply (PASSED
TEST).
Do a check of the SPR ON/OFF TEST.
1) Make sure a reply is receive when SPR is ON and no reply is
receive when SPR is OFF.
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(j)
Do a check of the MODE S UF0 TEST.
1) Make sure (Down-link format) DF=0, AC=(airplane's altitude)
and ADDRESS=(airplane's mode S address)
(WDM 34-53-11, 34-53-21).
NOTE:
____
(k)
(l)
(m)
(n)
Do a check of the MODE S UF4 TEST.
1) Make sure DF=4, AC=(airplane's altitude) and
ADDRESS=(airplane's mode address).
Do a check of the MODE S UF5 TEST.
1) Make sure DF=5, ID=(selected ATC ID code on the ATC control
panel) and ADDRESS=(airplane's mode S address).
Do a check of the MODE S UF11 TEST.
1) Make sure DF=11 and AA=(airplane's address).
Do a check of the MODE S UF16 TEST.
1) Make sure DF=16, AC=(airplane's altitude) and
ADDRESS=(airplane's mode S address).
NOTE:
____
(o)
(r)
No reply to the UF20 test is not a failure of the
ATC system.
Do a check of the MODE S UF21 TEST.
1) Make sure DF=21, ID=(selected ATC ID code on the ATC
control panel) and ADDRESS=(airplane's mode S address).
NOTE:
____
(q)
No reply to the UF16 test is not a failure of the
ATC system.
Do a check of the MODE S UF20 TEST.
1) Make sure DF=20, AC=(airplane's altitude) and
ADDRESS=(airplane's mode S address).
NOTE:
____
(p)
Make sure the reported altitude is within | 125 feet
of the local field elevation altitude shown on the
captain's and first officer's altimeter (applicable
for all altitude reporting check).
No reply to the UF21 test is not a failure of the
ATC system.
Do a check of
1) Make sure
seconds.
2) Make sure
specified
Do a check of
1) Make sure
MHz|1MHz.
the SQUITTER TEST.
the squitter's period is between 0.8 to 1.2
the squitter address agrees with mode S encoding
in the chart on (WDM 34-53-21, sheet 2).
the FREQUENCY TEST.
the reply frequency of the transponder is 1090
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(s)
Do a check of the DIVERSITY TEST.
1) Make sure the power level difference is f 20dB between 'on'
antenna squitters and 'off' antenna squitters.
NOTE:
____
(t)
(u)
(v)
Do a check of the MTL DIFFERENCE TEST.
1) Make sure the Minimum Threshold Level (MTL) difference
between mode A and mode C is a 1.0dBm.
Do the POWER TEST for the top antenna.
1) Insert the antenna shield over the bottom ATC antenna.
2) Move the test set, ATC-601-2, antenna so that it is in the
line of sight of the top ATC antenna.
3) Push the PWR TEST key on the test set, ATC-601-2.
4) Push the SETUP key on the test set.
a) Enter the appropriate range for the top antenna.
5) Use the SELECT key on the test set, ATC-601-2, and select
the top antenna.
6) Push and release the button on the test set, ATC-601-2,
antenna.
7) Slowly move the test set, ATC-601-2, antenna 3 feet
vertically from the ground, at less than 1 FT/SEC (30
CM/SEC).
8) Push and release the button on the test set, ATC-601-2,
antenna a second time to stop the test when the test set,
ATC-601-2, antenna is approximately 6 feet high.
Do a check of the POWER TEST results.
1) Make sure the peak power output of the transponder is
between 125W (ERP = 51.0 dBM) and 500W (ERP = 57.0 dBm).
NOTE:
____
2)
3)
4)
Do
1)
2)
Effective Radiated Power (ERP) is the product of the
antenna output power and antenna gain.
Make sure the Minimum Threshold Level (MTL) sensitivity is
-74dBm (|3dBm).
NOTE:
____
(w)
To make sure the dynamic range is f 20dB, a
diversity test must be run at a distance of less
than 50 feet (15.2 meters) from the airplane
antenna.
An additional 3dBm loss is allowed to compensate for
antenna coupling errors. Also, make sure to correct
for other factors that would change the sensitivity
measurement.
Make sure the test set, ATC-601-2, shows PASSED for the TOP
AVG (dBm).
Remove the antenna shield from the bottom ATC antenna.
the POWER TEST for the bottom antenna.
Move the test set, ATC-601-2, antenna so that it is not in
the line of sight of the top ATC antenna.
Push the PWR TEST key on the test set, ATC-601-2.
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3)
4)
5)
6)
7)
(x)
Do
1)
Push the SETUP key on the test set, ATC-601-2.
a) Enter the appropriate range for the bottom antenna.
Use the SELECT key on the test set, ATC-601-2, and select
the bottom antenna.
Push the antenna push button switch.
Slowly move the test set, ATC-601-2, antenna 3 feet
vertically from the ground, at less than 1 FT/SEC (30
CM/SEC).
Push the antenna push button switch a second time to stop
the test when the test set, ATC-601-2, antenna is
approximately 6 feet high.
a check of the POWER TEST results.
Make sure the peak power output of the transponder is
between 125W (ERP = 51.0 dBm) and 500W (ERP = 57.0 dBm).
NOTE:
____
2)
Make sure the Minimum Threshold Level (MTL) sensitivity is
-74dBm (|3dBm).
NOTE:
____
3)
(2)
(3)
Effective Radiated Power (ERP) is the product of the
antenna output power and antenna gain.
An additional 3dBm loss is allowed to compensate for
antenna coupling errors. Also, make sure to correct
for other factors that would change the sensitivity
measurement.
Make sure the test set, ATC-601-2, shows PASSED for the BOT
AVG (dBm).
SUBTASK 860-010
Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
SUBTASK 860-011
Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
SUBTASK 710-002
Do the system test again for the No. 2 ATC system and use the No. 2
air data source.
Put the Airplane Back to Its Usual Condition
(4)
G.
(1)
SUBTASK 860-012
Close these circuit breakers:
(a) Circuit Breaker Panel, P6-3:
1) 6D18
LANDING GEAR AURAL WARN
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
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ú
ú
(2)
SUBTASK 840-004
Do this task: Return the Airplane to the Ground Mode
(AMM TASK 32-09-00-860-802 p201).
(3)
SUBTASK 860-013
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-53-00-730-802
4.
ú
ú
_____________________________________________________________
System
Test - ATC System (With the TIC T-48 or T-49 Test Set)
A. General
(1) This system test is a full check of the ATC system. The system test
first does the ATC - Operational Test and then uses the test set,
T-48D, or test set, T-49C test set to examine the left and right ATC
systems.
(2) The test set can do all of the tests automatically except the
DIVERSITY CHECK, the MAX TRUE AIRSPEED TEST and the IDENT BUTTON
CHECK. You must do these tests manually with the TEST button on the
test set. If a test has failed, the automatic test sequence will
stop and a failed message will show. At the end of the automatic
test all data will show.
(3) You can manually do each test individually. Push the TEST button to
do each test individually. The test results will show after each
test is done.
(4) Operation with the antenna coupler, TAP-115, TAP 118, TAP 119 or TAP
125 used with the applicable test set, is necessary to do a check of
the output power, receiver, sensitivity and radio frequency. For
the diversity check, the TAP 125 is necessary.
B. References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(2) AMM TASK 32-09-00-860-801 p201, Put the Airplane in the Air Mode
(3) AMM TASK 32-09-00-860-802 p201, Return the Airplane to the Ground
Mode
(4) AMM TASK 34-53-00-710-801 p501, Air Traffic Control System Operational Test
C. Equipment
(1) MODEL 43 Meter - RF Power, Thruline R.F. wattmeter with type 50c
element
Bird Electronic Corporation (Vendor Code 70998)
30303 Aurora Road, Solon OH 44139-2743
(2) T-48D Test Set - ATC Transponder, RAMP
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
(3) T-49C Test Set - TCAS/ATC Test, RAMP
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
D. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
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E.
(b) 118 Electrical and Electronics Compartment - Right
(c) 143 Area Below Aft Cargo Compartment - Left
(d) 144 Area Below Aft Cargo Compartment - Right
(e) 200 Upper Half of Fuselage
(f) 211 Flight Compartment - Left
(g) 212 Flight Compartment - Right
Prepare for the System Test
(1)
(2)
SUBTASK 710-003
Do this task: Air Traffic Control System - Operational Test
(AMM TASK 34-53-00-710-801 p501).
SUBTASK 940-001
Prepare the test set, T-48D, or test set, T-49C for the ATC system
test:
(a) Pull the pull-ring on the antenna coupler to seperate the
spring loaded clamp.
(b) Insert the antenna coupler over the necessary ATC antenna.
NOTE:
____
(c)
(d)
(e)
Push and hold antenna coupler so the EMI gasket compresses to
the airplane skin.
Release the pull-ring to keep the coupler in its correct
position.
Connect the antenna coupler coax connector to the test set
ANTENNA connector.
NOTE:
____
(f)
Make sure the antenna coupler is centered.
If you use the TAP 125, the unused coupler cable does
not need to be connected to the test set. You test only
one antenna at a time.
Push the INTERROGATE button.
NOTE:
____
1)
To read the display push and hold the INTERROGATE
switch.
The test set will momentarily display:
TEL Instrument
T-4X Rev.XX
2)
(3)
After the test set has determined the type of transponder
under test (Mode S, Mode A, Mode C, etc) the display will
change to:No Reply from XPNDR.
SUBTASK 860-026
Put the airplane in the air mode with the BITE in the Proximity
Switch Electronics Unit (PSEU), do this task: Put the Airplane in
the Air Mode (AMM TASK 32-09-00-860-801 p201).
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(4)
SUBTASK 860-015
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-3:
1) 6D18
LANDING GEAR AURAL WARN
SUBTASK 860-016
Set the captain's and first officer's altimeter to 29.92 inches of
mercury.
ATC System Test
(5)
F.
SUBTASK 860-017
CAUTION:
_______
(1)
(2)
DO NOT USE CODES 7500, 7600-7677, AND 7700-7777.
CODES ONLY IN EMERGENCIES.
On the ATC control panel do these steps:
(a) Set the code switches to a desired ATC ID code.
(b) Set the transponder select switch to the No. 1 system.
(c) Set the mode select switch to the ALT ON position.
SUBTASK 730-001
Push the INTERROGATE switch.
(a) Make sure the test set shows the correct transponder type.
NOTE:
____
(3)
(4)
If the test set shows "no reply from xpdr", do a check
on the test antenna connections. Also, make sure the
ATC system is operational.
SUBTASK 730-002
Push the INTERROGATE switch on the test set.
(a) The test set will determine the transponder type.
SUBTASK 860-018
Push the INTERROGATE button again and the test set will initiate a
sequence of tests on the tranpsonder.
(a) These tests must be done to complete the ATC system test:
1) ATCRBS/A & SLS
2) ATCRBS/C
3) ATCRBS/A Mode S All
4) ATCRBS/C Mode S All
5) ATCRBS/A only
6) ATCRBS/C only
7) Mode S Surv Identity
8) Mode S Surv Altitude
9) Mode S Surv Short
10) Undesired Replies
11) Squitter
EFFECTIVITY
ú
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YOU USE THESE
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12) Diversity
NOTE:
____
This test is only available for test sets with the
TAP 125 option and must be done manually.
13) MAX TRUE AIRSPEED
NOTE:
____
(5)
This test must be done manually.
SUBTASK 210-001
Make sure the display is as follows when the test is complete:
CCCC
ZZZ W
(a)
(b)
(d)
(e)
(f)
mmm dbm
YYYYY'
nnn MHZ
CCCC is code selected.
XXXXXX is airplane registry number
NOTE:
____
(c)
XXXXXX
This may appear as the mode S address in
hexadecimal.
YYYYY is airplane altitude in feet (must be
|125' of the Capt's and F/O's altimeter).
ZZZ is the transmitter power output (must be >
125 and < 500 Watts).
mmm is the receiver sensitivity (must be between
-77 to -68 dbm).
nnn is the frequency deviation (|1 MHz maximum
allowed).
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(6)
SUBTASK 730-003
Do the DIVERSITY CHECK that follows for the test sets with the TAP
125 couplers:
NOTE:
____
(a)
(b)
This test can only be done with the TAP 125 coupler. If you
do not have the TAP 125 coupler, do the test that uses the
Bird RF through-line wattmeter.
Push the TEST button on the test set until you get to the
DIVERSITY CHECK.
1) Make sure to pause between each push of the TEST button to
allow the test set to do that test step.
The test set will show DIVERSITY and then either PASS of FAIL.
NOTE:
____
(7)
(8)
The test may initially fail due to strong local
radiation. This is usually a temporary situation,
repeat the test, any PASS indicates a good system.
SUBTASK 730-004
Do the Diversity Check that follows for the test set without the TAP
125 coupler:
(a) Disconnect the antenna cable at the top antenna switch
connector, D2703, and connect the RF through-line wattmeter,
MODEL 43, in its place.
(b) Make a note of the maximum power output and the minimum power
output measured by the RF through-line wattmeter, MODEL 43,
during the mode S squitter transmission period.
1) Make sure the minimum power output is 100 times or 20 db
lower than the maximum power output.
(c) Disconnect the RF through-line wattmeter, MODEL 43.
(d) Connect the antenna cable at the top antenna switch connector,
D2703.
SUBTASK 760-001
Do these steps that follow for the MAX TRUE AIRSPEED TEST:
(a) Push the TEST button on the test set until you get to the MAX
TRUE AIRSPEED TEST.
1) Make sure to pause between each push of the TEST button to
allow the test set to do that test step.
(b) The test set will show the max true airspeed that has been pin
programmed at each transponder.
1) The test set display must be:
MAX TRUE AIRSPEED
GT 300 & LE 600 kts
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(9)
SUBTASK 730-005
Do the steps that follow for the IDENT BUTTON CHECK:
(a) On the ATC control panel do the steps that follow:
CAUTION:
_______
(b)
(c)
(d)
(e)
(f)
G.
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DO NOT USE CODES 7500, 7600-7677, AND 7700-7777.
THESE ARE EMERGENCY CODES.
1) Set the code switches to a desired ATC ID code
2) Put the ATC select switch to the No. 1 position
3) Put the mode select switch to the ALT ON position.
Make sure the test set displays the desired ATC ID code.
Turn the test set off.
Wait a moment, then push the INTERROGATE button.
1) Allow the test set to determine the type of transponder
under test.
At the same time push the control panel IDENT button and the
test set TEST button.
Make sure the message IDENT is displayed on the test set.
SUBTASK 730-006
(10) Do the test again as necessary, for the right system.
(a) To test the right system, put the ATC select switch to the No.
2 position.
Put the airplane back to its Usual Condition.
(1)
SUBTASK 860-019
Put the mode select switch to the STBY position.
(2)
SUBTASK 840-002
Disconnect and remove the ATC test set.
(3)
(4)
(5)
SUBTASK 840-005
Do this task: Return the Airplane to the Ground Mode
(AMM TASK 32-09-00-860-802 p201).
SUBTASK 860-020
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-3:
1) 6D18
LANDING GEAR AURAL WARN
SUBTASK 840-003
If the electrical power is no longer necessary, do this task:
Remove Electrical Power (AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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AIR TRAFFIC CONTROL (ATC) ANTENNA - REMOVAL/INSTALLATION
________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the ATC antenna
(2) An installation of the ATC antenna.
B. The bottom ATC antenna is installed at STA 355, and the top antenna at
STA 430.
TASK 34-53-01-000-801
2.
___________________
ATC
Antenna Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 123 Area Below Forward
(b) 124 Area Below Forward
(c) 211 Flight Compartment
(d) 212 Flight Compartment
B. Removal Procedure
(1)
(2)
Cargo Compartment - Left
Cargo Compartment - Right
- Left
- Right
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
2) 6E14
ATC ANT SWITCH
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
SUBTASK 020-001
Remove the ATC antenna [3]:
(a) Remove the bolts [4] that attach the ATC antenna [3]
airplane structure.
CAUTION:
_______
(b)
(c)
MOVE THE ANTENNA [3] ONLY AS FAR AS NECESSARY TO
DISCONNECT THE COAXIAL CABLE [1]. DAMAGE TO THE CABLE [1]
CAN OCCUR IF YOU PULL THE CABLE [1].
Move the ATC antenna [3] away from the airplane structure to
get access to the coaxial cable [1].
Disconnect the coaxial cable [1] from the ATC antenna [3].
NOTE:
____
(d)
(e)
to the
Do not let the coaxial cable [1] retract into the
fuselage.
Remove the ATC antenna [3].
Put a protective cover over the electrical connector on the ATC
antenna [3].
EFFECTIVITY
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TOP ATC
ANTENNA
SEE
A
BOTTOM
ATC ANTENNA
SEE
A
AIRPLANE
SKIN
[1] COAXIAL
CONNECTOR
[2] O-RING
[3] ATC ANTENNA
FWD
[4] BOLT
(4 LOCATIONS)
ATC ANTENNA
(REMOVED)
A
ATC Antenna Installation
Figure 401
G35395
34-53-01-990-801
EFFECTIVITY
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TASK 34-53-01-400-801
3.
________________________
ATC
Antenna Installation (Fig. 401)
A. References
(1) AMM TASK 20-30-84-910-801 p201, Final Cleaning of Metal Prior to
Painting (Series 84)
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(4) FIM 34-53 TASK 801, Air Traffic Control (ATC) Transponder BITE
Procedure
(5) SWPM 20-20-00
B. Equipment
(1) Ohmeter (or alternative tool)
(a) C15292 Ohmeter - Electrical Bonding (Model T477W) (recommended)
Avtron Manufacturing, Inc. (Vendor Code 01014)
7900 E. Pleasant Valley Road, Independence OH 44131
(b) MODEL 1010-A Ohmeter - Micro, Autoranging/Autotest, 10 Micro
Ohms to 200 Ohms, Accuracy: 0.05% (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(c) M-1 Ohmeter - Micro-ohm, Automatic, Stores 128 Readings, RS-232
Data Port, Range: 0.01 - 19.999 Milliohms, 4 1/2 Digit Display,
Accy: 0.1% of Readings (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
C. Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
(2) B01004 Solvent, Final Cleaning of Metal Prior to Painting (AMM
20-30-84/201 or SOPM 20-30-84) - Series 84
(3) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(4) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
D. Access
(1) Location Zones
(a) 123 Area Below Forward Cargo Compartment - Left
(b) 124 Area Below Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
E. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these
(a) Circuit Breaker
1) 6D14
ATC
2) 6E14
ATC
(b) Circuit Breaker
1) 18B5
ATC
circuit breakers are open:
Panel, P6-1:
2
ANT SWITCH
Panel, P18-1:
1
EFFECTIVITY
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SUBTASK 110-001
WARNING:
_______
(2)
(3)
(4)
(5)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR
SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE
HAZARDOUS MATERIALS. SOLVENTS MAY BE FLAMMABLE OR HARMFUL TO
THE ENVIRONMENT. REFER TO PRODUCT MATERIAL SAFETY DATA SHEETS
(MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING PROCEDURES.
Clean the airplane mating surface with solvent, Series 84
(AMM TASK 20-30-84-910-801 p201).
(a) Make a cloth, BMS15-5, moist (not soaked) with solvent.
(b) Rub the airplane mating surface with the cloth, BMS15-5, until
the surface is clean.
SUBTASK 390-001
Apply a layer of compound, BMS3-23, to the mating surfaces of the
antenna and the airplane structure.
SUBTASK 420-001
Install the ATC antenna:
(a) Remove the protective cover from the antennas electrical
connector.
(b) Install the o-ring [2] on the ATC antenna [3].
(c) Apply sealant, BMS5-95, to the threads of the bolts [4].
(d) Examine the coaxial connector [1] for bent or broken pins,
dirt, and damage.
(e) Connect the coaxial cable connector [1] to the ATC antenna [3].
(f) Put the ATC antenna [3]in the correct position on the airplane
surface.
(g) Install three of the four bolts [4].
SUBTASK 760-001
Measure the resistance between the ATC antenna baseplate and the
airplane skin with an ohmeter, C15292 (SWPM 20-20-00).
NOTE:
____
(a)
(6)
(7)
Use the empty bolt hole to get access to the antenna
baseplate.
Make sure the resistance is less that 0.001 ohm.
SUBTASK 420-002
Install the last bolt [4].
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
2) 6E14
ATC ANT SWITCH
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
EFFECTIVITY
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F.
ATC Antenna Test
(1)
ú
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SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 420-003
(2)
Do these steps to do a test of the ATC antennas:
(a) Set the transponder select switch on the ATC control panel to
the left (No. 1) position.
(b) Push and release the TEST button on the front panel of the left
(No. 1) ATC transponder.
NOTE:
____
The PUSH TO TEST button must be pushed for 1.5 seconds.
1)
2)
(c)
(d)
If XPDR PASS light comes on, then the BITE test passed.
If a different light comes on, then do this task: Air
Traffic Control (ATC) Transponder BITE Procedure
(FIM 34-53 TASK 801).
Set the transponder select switch on the ATC control panel to
the right (No. 2) position.
Push and release the TEST button on the front panel of the
right (No. 2) ATC transponder.
NOTE:
____
1)
2)
(3)
The PUSH TO TEST button must be pressed for 1.5 seconds.
If XPNR PASS light comes on, then the BITE Test passed.
If a different light comes on, then do this task: Air
Traffic Control (ATC) Transponder BITE Procedure
(FIM 34-53 TASK 801).
SUBTASK 860-006
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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AIR TRAFFIC CONTROL (ATC) TRANSPONDER - REMOVAL/INSTALLATION
____________________________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the ATC transponder
(2) An installation of the ATC transponder.
B. The two ATC transponders are installed in the main equipment center on
the E1 rack. The left ATC transponder (No. 1), M163, is installed on
shelf No. 2 and the right ATC transponder (No. 2), M381, is installed on
shelf No. 5.
TASK 34-53-02-020-801
2.
_______________________
ATC
Transponder Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center.
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE ATC
TRANSPONDERS. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE ATC TRANSPONDERS.
To remove the ATC transponder [1], do this task:
(AMM TASK 20-10-07-000-801 p201).
E/E Box Removal
TASK 34-53-02-400-801
3.
____________________________
ATC
Transponder Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
EFFECTIVITY
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ELECTRONIC
EQUIPMENT
RACK, E1
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] ATC NO. 1
(E1-2)
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
[1] ATC NO. 2
(E1-5)
FWD
ELECTRONIC EQUIPMENT RACK, E1
A
ATC Transponder Installation
Figure 401
F98584
34-53-02-990-801
EFFECTIVITY
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B.
C.
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
Installation procedure
(1)
SUBTASK 860-002
Make sure that these
(a) Circuit Breaker
1) 6D14
ATC
(b) Circuit Breaker
1) 18B5
ATC
circuit breakers are open:
Panel, P6-1:
2
Panel, P18-1:
1
SUBTASK 420-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE ATC
TRANSPONDERS. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE ATC TRANSPONDERS.
To install the ATC transponder, do this task:
(AMM TASK 20-10-07-400-801 p201).
E/E Box Installation
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
Installation Test
(3)
D.
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 740-001
Do the installation test:
(a) Set the transponder select switch on the ATC control panel to
the 1 position.
(b) Push and release the TEST switch on the left ATC transponder.
NOTE:
____
(c)
The PUSH TO TEST switch needs to be held for 1.5
seconds.
1) Make sure the self-test passes and no faults are detected.
Set the transponder select switch on the ATC control panel to
the 2 position.
EFFECTIVITY
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(d)
Push and release the TEST switch on the right ATC transponder.
NOTE:
____
1)
(3)
(4)
The PUSH TO TEST switch needs to be held for 1.5
seconds.
Make sure the self-test passes and no faults are detected.
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
SUBTASK 860-005
If electrical power is not necessary, do this task:
Electrical Power (AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
Remove
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ATC CONTROL PANEL - REMOVAL/INSTALLATION
________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the air traffic control (ATC) control panel
(2) An installation of the ATC control panel.
B. The ATC control panel is on the aft aisle stand panel, P8, in the flight
compartment.
TASK 34-53-03-000-801
2.
_________________________
ATC
Control Panel Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
B. Removal Procedure
(1)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
SUBTASK 020-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE ATC
CONTROL PANEL [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE ATC CONTROL
PANEL [1].
Remove the ATC control panel [1]:
(a) Turn the four quarter-turn fasteners [2] to release the ATC
control panel [1] from the aisle stand.
(b) Lift the ATC control panel [1] to get access to the electrical
connectors [3].
(c) Disconnect the electrical connectors [3].
(d) Put protective covers on the electrical connectors [3].
TASK 34-53-03-400-801
3.
______________________________
ATC
Control Panel Installation
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
EFFECTIVITY
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SEE
A
FLIGHT COMPARTMENT
[2] QUARTER-TURN
FASTENER
(4 LOCATIONS)
[1] ATC/TCAS
CONTROL PANEL
FWD
[3] ELECTRICAL
CONNECTORS
AISLE STAND
A
ATC/TCAS Control Panel Installation
Figure 401
H54136
34-53-03-990-801
EFFECTIVITY
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~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
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¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Panel
¦ 34-53-03
01
50 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Installation Procedure
(1)
SUBTASK 760-001
Make sure that these
(a) Circuit Breaker
1) 6D14
ATC
(b) Circuit Breaker
1) 18B5
ATC
circuit breakers are open:
Panel, P6-1:
2
Panel, P18-1:
1
SUBTASK 420-001
CAUTION:
_______
(2)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE ATC
CONTROL PANEL [1]. IF YOU TOUCH THESE CONDUCTORS,
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE ATC CONTROL
PANEL [1].
Install the ATC control panel [1]:
(a) Remove the protective covers from the electrical connectors
[3].
(b) Examine the electrical connectors [3] for bent or broken pins,
dirt, and damage.
(c) Connect the electrical connectors [3].
(d) Put the ATC control panel [1] into its position in the aisle
stand.
(e) Turn the quarter-turn fasteners [2] that attach the ATC control
panel [1].
SUBTASK 760-002
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
Installation Test
(3)
E.
(1)
SUBTASK 860-002
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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(2)
SUBTASK 860-003
Do the installation test:
(a) Set the transponder select switch on the ATC control panel to
the 1 position.
(b) Push and release the PUSH TO TEST switch on the left ATC
transponder.
NOTE:
____
(c)
(d)
1) Make sure the self-test passes and no faults are detected.
Set the transponder select switch on the ATC control panel to
the 2 position.
Push and release the PUSH TO TEST switch on the left ATC
transponder.
NOTE:
____
1)
(3)
The PUSH TO TEST switch needs to be held for 1.5
seconds.
The PUSH TO TEST switch needs to be held for 1.5
seconds.
Make sure the self-test passes and no faults are detected.
SUBTASK 860-004
If electrical power is not necessary, do this task:
Electrical Power (AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
Remove
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__________________________________________
AIR
TRAFFIC CONTROL (ATC) ANTENNA SWITCH ____________________
REMOVAL/INSTALLATION
1.
General
_______
A. This procedure has two tasks. One is the removal of the ATC antenna
switch, the other is the installation of the ATC antenna switch.
B. The top and bottom ATC antenna switch, S00942 and S00943, installations
are the same. The ATC antenna switches are installed left of the E1-5
shelf on the E1 rack.
TASK 34-53-04-000-801
2.
__________________________
ATC
Antenna Switch Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
B. Prepare for the Removal
(1)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
2) 6E14
ATC ANT SWITCH
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get to the main
equipment center.
Procedure
(2)
C.
(1)
SUBTASK 020-001
Remove the ATC antenna switch [1]:
(a) Disconnect the electrical connectors [4] from the ATC antenna
switch [1].
(b) Put protective covers on the electrical connectors [4].
(c) Remove the screws [2] and washers [3] that hold the ATC antenna
switch [1] to the bracket.
(d) Remove the ATC antenna switch [1] from the bracket.
TASK 34-53-04-400-801
3.
_______________________________
ATC
Antenna Switch Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-34-120-801 p701, Hand Clean Metal Surfaces with
Abrasives
(2) AMM TASK 20-40-11-760-801 p201, Electrical Bonding
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
EFFECTIVITY
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ELECTRONIC
EQUIPMENT
RACK, E1 AND E5
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
ATC ANTENNA
SWITCH,
E1-3
SEE
B
FWD
ELECTRONIC EQUIPMENT RACKS, E1 AND E5
A
ATC Antenna Switch Installation
Figure 401 (Sheet 1)
G34342
34-53-04-990-801
EFFECTIVITY
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[1] ATC
ANTENNA
SWITCH
[4] ELECTRICAL
CONNECTORS
[1] ATC
ANTENNA
SWITCH
FWD
INBD
[3] WASHER
(2 LOCATIONS)
[2] SCREW
(2 LOCATIONS)
ATC ANTENNA SWITCH
B
ATC Antenna Switch Installation
Figure 401 (Sheet 2)
G34343
EFFECTIVITY
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(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
Equipment
(1) Ohmeter (or alternative tool)
(a) C15292 Ohmeter - Electrical Bonding (Model T477W) (recommended)
Avtron Manufacturing, Inc. (Vendor Code 01014)
7900 E. Pleasant Valley Road, Independence OH 44131
(b) MODEL 1010-A Ohmeter - Micro, Autoranging/Autotest, 10 Micro
Ohms to 200 Ohms, Accuracy: 0.05% (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(c) M-1 Ohmeter - Micro-ohm, Automatic, Stores 128 Readings, RS-232
Data Port, Range: 0.01 - 19.999 Milliohms, 4 1/2 Digit Display,
Accy: 0.1% of Readings (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
C. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Switch
¦ 34-53-51
01
15 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
D. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
E. Prepare for the Installation
B.
SUBTASK 860-002
Make sure that these
(a) Circuit Breaker
1) 6D14
ATC
2) 6E14
ATC
(b) Circuit Breaker
1) 18B5
ATC
Procedure
(1)
F.
(1)
circuit breakers are open:
Panel, P6-1:
2
ANT SWITCH
Panel, P18-1:
1
SUBTASK 420-001
Install the ATC antenna switch [1]:
(a) Remove the protective covers from the electrical connectors
[4].
(b) Examine the electrical connectors [4] for bent or broken pins,
dirt and damage.
EFFECTIVITY
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(c)
(d)
(e)
(f)
(2)
(3)
Make sure the bracket for the ATC antenna switch [1] has no
corrosion.
1) If there is corrosion, clean the mating surfaces. To do
this, do this task: Hand Clean Metal Surfaces with
Abrasives (AMM TASK 20-10-34-120-801 p701).
Use the electrical bond fastener to install the ATC antenna
switch [1] on the bracket. To do it, do this task: Electrical
Bonding (AMM TASK 20-40-11-760-801 p201).
Put the switch [1] into position on the bracket.
Install the screws [2] and washers [3] that hold the ATC
antenna switch [1] to the bracket.
SUBTASK 760-001
Use the ohmeter, C15292, and make sure the resistance from the ATC
antenna switch [1] to the E2 rack is less than 0.001 ohm.
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D14
ATC 2
2) 6E14
ATC ANT SWITCH
(b) Circuit Breaker Panel, P18-1:
1) 18B5
ATC 1
Installation Test
(4)
G.
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-005
Do the installation test:
(a) Set the transponder select switch on the ATC control panel to
the 1 position.
(b) Push and release the PUSH TO TEST switch on the left ATC
transponder.
NOTE:
____
(c)
The PUSH TO TEST switch needs to be held for 1.5
seconds.
1) Make sure the self-test passes and no faults are detected.
Set the transponder select switch on the ATC control panel to
the 2 position.
EFFECTIVITY
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(d)
Push and release the PUSH TO TEST switch on the left ATC
transponder.
NOTE:
____
H.
The PUSH TO TEST switch needs to be held for 1.5
seconds.
1) Make sure the self-test passes and no faults are detected.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-006
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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DME SYSTEM - ADJUSTMENT/TEST
____________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the distance measuring equipment (DME)
system.
(2) A system test of the DME system.
TASK 34-55-00-710-801
2.
_____________________________
DME
System - Operational Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 32-09-00-860-801 p201, Put the Airplane in the Air Mode
B. Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
(2) Access Panels
(a) 112A
Forward Access Door
C. Prepare for the Operational Test
(1)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-002
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
(3)
SUBTASK 860-074
Set the SOURCE switch on the instrument switching module to the AUTO
position.
SUBTASK 860-003
Set the display select switch on the captain's and first officer's
EFIS control panels to the VOR position.
DME Self Test
(4)
D.
(1)
SUBTASK 860-075
Make sure DME 1 and DME 2 are not tuned to a local station's
frequency.
EFFECTIVITY
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(2)
(3)
(4)
SUBTASK 740-002
Push and hold the TEST
panel to start the DME
(a) Make sure the DME
1 self test.
(b) Make sure the DME
approximately two
(c) Make sure the DME
of the test.
button on the captain's navigation control
1 self test.
2 shows dashes on the displays during the DME
1 has a flag on the displays for
seconds.
1 shows dashes on the displays until the end
SUBTASK 860-005
Release the TEST button on the captain's navigation control panel.
SUBTASK 860-046
Open the Forward Access Door, 112A, to get access to the proximity
switch electronics unit.
SUBTASK 860-006
WARNING:
_______
(5)
(6)
MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE
CONTROL SURFACES AND LANDING GEAR DOOR AREAS. THE CONTROL
SURFACES, THE LANDING GEAR, AND THE LANDING GEAR DOORS CAN MOVE
WHEN YOU DO THE AIR MODE SIMULATION. THIS CAN CAUSE INJURIES
TO PERSONS AND DAMAGE TO EQUIPMENT.
Do this task:
Put the Airplane in the Air Mode
(AMM TASK 32-09-00-860-801 p201).
SUBTASK 730-002
Push and hold the TEST button on the captain's navigation control
panel to start the DME 1 self test.
(a) Make sure the self test sequence for DME 1 did not start.
(7)
SUBTASK 860-007
Release the TEST button on the captain's navigation control panel.
(8)
SUBTASK 860-008
Release the SYS #1 IN AIR button.
(9)
SUBTASK 730-003
Set the SOURCE switch on the instrument switching module to the ALL
ON 2 position.
SUBTASK 730-004
(10) Push and hold the TEST
control panel to start
(a) Make sure the DME
2 self test.
(b) Make sure the DME
approximately two
button on the first officer's navigation
the DME 2 self test.
1 shows dashes on the displays during the DME
2 has a flag on the displays for
seconds.
EFFECTIVITY
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(c)
Makes sure the DME 2 shows dashes on the displays until the end
of the test.
SUBTASK 860-009
(11) Release the TEST button on the first officer's navigation control
panel.
SUBTASK 860-010
WARNING:
_______
MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE
CONTROL SURFACES AND LANDING GEAR DOOR AREAS. THE CONTROL
SURFACES, THE LANDING GEAR, AND THE LANDING GEAR DOORS CAN MOVE
WHEN YOU DO THE AIR MODE SIMULATION. THIS CAN CAUSE INJURIES
TO PERSONS AND DAMAGE TO EQUIPMENT.
(12) Do this task:
Put the Airplane in the Air Mode
(AMM TASK 32-09-00-860-801 p201).
SUBTASK 730-005
(13) Push and hold the TEST button on the first officer's navigation
control panel to start the DME 2 self test.
(a) Make sure the self test sequence for DME 2 did not start.
SUBTASK 860-011
(14) Release the TEST button on the first officer's navigation control
panel.
SUBTASK 860-012
(15) Release the SYS #2 IN AIR button.
SUBTASK 860-047
(16) Close the Forward Access Door, 112A.
SUBTASK 860-013
(17) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-55-00-730-801
3.
________________________
DME
System - System Test
A. General
(1) This task gives procedures for more than one DME test set. It is
necessary to use only one of the DME test sets to do a test of the
DME system.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 34-55-00-710-801 p501, DME System - Operational Test
EFFECTIVITY
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C.
D.
E.
Equipment
(1) Test (or alternative tool)
(a) ATC-600A-2 Test Set - ATC Transponder/DME, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 601-110 Test Set - ATC Transponder, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-48D Test Set - ATC Transponder, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
(2) Test (or alternative tool)
(a) T-24B Test Set - DME (recommended)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
(b) 01-0331-00 Test Set - DME (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(c) 600A-110 Test Set - ATC Transponder/DME (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
Access
(1) Location Zones
(a) 112 Area Forward of Nose Landing Gear Wheel Well
(b) 117 Electrical and Electronics Compartment - Left
(c) 118 Electrical and Electronics Compartment - Right
(d) 211 Flight Compartment - Left
(e) 212 Flight Compartment - Right
Prepare for the System Test
(1)
SUBTASK 860-014
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-015
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
SUBTASK 860-016
Set the SOURCE switch on the instrument switching module to the ALL
ON 1 position.
Operational Test
(3)
F.
(1)
SUBTASK 710-001
Do this task: DME System - Operational Test
(AMM TASK 34-55-00-710-801 p501).
EFFECTIVITY
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G.
No. 1 DME System Test (with the use of the test set, ATC-600A-2)
(1)
SUBTASK 860-023
Do these steps to prepare for the No. 1 DME system test:
CAUTION:
_______
(a)
DO NOT PUT THE TEST SET ANTENNA LESS THAN 15 INCHES (38
CM) FROM THE DME ANTENNA WITH THE TEST SET ON. YOU CAN
CAUSE DAMAGE TO THE TEST SET.
Put the test set, ATC-600A-2, approximately 21 inches (53 cm)
from the DME antenna.
NOTE:
____
(b)
The test antenna should be approximately the same height
as the airplane antenna.
Set the controls on the test set, ATC-600A-2, as follows:
SWITCH NAME
SWITCH POSITION
PWR Switch
AC or BAT as appropriate
Mode Switch
DME
Velocity Select Switch
Range
Velocity HI/LO Switch
HI
Squitter Switch
SQTR
X/Y Switch
X
(2)
SUBTASK 860-024
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(3)
SUBTASK 860-076
Set a frequency of 109.00 MHz on the captain's and the first
officer's navigation control panels.
NOTE:
____
(a)
(b)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
Make sure the DME 1 shows dashes on the displays.
Make sure the DME 2 shows dashes on the displays.
EFFECTIVITY
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(4)
(5)
(6)
(7)
SUBTASK 730-016
Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Make sure the DME 2 has a flag on the displays.
SUBTASK 860-025
Set a frequency of 108.00 MHz on the captain's navigation control
panel.
SUBTASK 860-026
Set the X/Y switch on the test set, ATC-600A-2, to Y.
SUBTASK 730-017
Use the SLEW switch to set a distance of 6 miles on the test set,
ATC-600A-2.
(a) Make sure the DME 1 shows dashes on the displays.
(8)
SUBTASK 730-018
Set the X/Y switch on the test set, ATC-600A-2, to X.
(a) Make sure the DME 1 shows 6 |0.5 nmi on the displays.
(9)
SUBTASK 860-027
Set the voice/range filter switch on one of the audio control panels
to the B position.
SUBTASK 860-028
(10) At the same audio control panel, push the receiver volume control
for NAV-1 to set the volume to on.
SUBTASK 860-029
(11) At the same audio control panel, turn the receiver volume control
clockwise for NAV-1 to adjust the volume level.
SUBTASK 860-030
(12) At all other audio control panels, push the receiver volume control
for NAV-1 to set the volume to off.
SUBTASK 860-031
(13) Push the receiver volume control for NAV-2 on all the audio control
panels to set the volume to off.
SUBTASK 730-019
(14) Use the switches on the test set, ATC-600A-2, to supply an
identification tone.
(a) Make sure you can hear a tone through the flight interphone
system.
EFFECTIVITY
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SUBTASK 860-032
(15) Push the receiver volume control for NAV-1 on the audio control
panels to set the volume to off.
H.
SUBTASK 860-033
(16) Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
No. 2 DME System Test (with the use of the test set, ATC-600A-2)
(1)
SUBTASK 860-034
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(2)
SUBTASK 860-077
Set a frequency of 109.00 MHz on the captain's and the first
officer's navigation control panels.
NOTE:
____
(a)
(b)
(3)
(4)
(5)
(6)
(7)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
Make sure the DME 1 shows dashes on the displays.
Make sure the DME 2 shows dashes on the displays.
SUBTASK 860-078
Set a frequency of 109.00 MHz on the captain's navigation control
panel.
SUBTASK 730-020
Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
(b) Make sure the DME 1 has a flag on the displays.
SUBTASK 860-036
Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
SUBTASK 860-037
Set the X/Y switch on the test set, ATC-600A-2, to Y.
SUBTASK 730-021
Use the SLEW switch to set a distance of 6 miles on the test set,
ATC-600A-2.
(a) Make sure the DME 2 shows dashes on the displays.
EFFECTIVITY
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(8)
SUBTASK 730-022
Set the X/Y switch on the test set, ATC-600A-2, to X.
(a) Make sure the DME 2 shows 6 |0.5 nmi on the displays.
(9)
SUBTASK 860-038
Set the voice/range filter switch on one of the audio control panels
to the B position.
SUBTASK 860-039
(10) At the same audio control panel, push the receiver volume control
for NAV-2 to set the volume to on.
SUBTASK 860-040
(11) At the same audio control panel, turn the receiver volume control
clockwise for NAV-2 to adjust the volume level.
SUBTASK 860-041
(12) At all other audio control panels, push the receiver volume control
for NAV-2 to set the volume to off.
SUBTASK 860-042
(13) Push the receiver volume control for NAV-1 on all the audio control
panels to set the volume to off.
SUBTASK 730-023
(14) Use the switches on the test set, ATC-600A-2, to supply an
identification tone.
(a) Make sure you can hear a tone through the flight interphone
system.
SUBTASK 860-043
(15) Push the receiver volume control for NAV-2 on the audio control
panels to set the volume to off.
SUBTASK 860-044
(16) Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
SUBTASK 860-045
(17) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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I.
No. 1 DME System Test (with the use of the test set, T-24B)
(1)
SUBTASK 860-053
Do these steps to prepare for the No. 1 DME system test:
CAUTION:
_______
(a)
DO NOT PUT THE TEST SET ANTENNA LESS THAN 15 INCHES (38
CM) FROM THE DME ANTENNA WITH THE TEST SET ON. YOU CAN
CAUSE DAMAGE TO THE TEST SET.
Put the test set, T-24B, approximately 21 inches (53 cm) from
the DME antenna.
NOTE:
____
(b)
The test antenna should be approximately the same height
as the airplane antenna.
Set the controls on the test set, T-24B, as follows:
SWITCH NAME
SWITCH POSITION
POWER
ON
IDENT
OFF
DIST/VEL
DIST
Squitter Switch
ON
(2)
SUBTASK 860-054
Set the SOURCE switch on the instrument switching module to the AUTO
position.
(3)
SUBTASK 860-079
Set a frequency of 109.00 MHz on the captain's and the first
officer's navigation control panels.
NOTE:
____
(a)
(b)
(4)
To set the frequency, turn the frequency selector until the
frequency shows in the STANDBY display window. Then push the
TFR button. The frequency will show in the ACTIVE display
window.
Make sure the DME 1 shows dashes on the displays.
Make sure the DME 2 shows dashes on the displays.
SUBTASK 730-024
Open this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Make sure the DME 2 has a flag on the displays.
EFFECTIVITY
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(5)
(6)
SUBTASK 860-055
Set a frequency of 108.00 MHz on the captain's navigation control
panel.
SUBTASK 730-025
Use the DISTANCE switch to set distance of 6 miles on the test set,
T-24B.
(a) Make sure the DME 1 shows 6 |0.5 nmi on the displays.
(7)
SUBTASK 860-056
Set the voice/range filter switch on one of the audio control panels
to the B position.
(8)
SUBTASK 860-057
At the same audio control panel, push the receiver volume control
for NAV-1 to set the volume to on.
(9)
SUBTASK 860-058
At the same audio control panel, turn the receiver volume control
clockwise for NAV-1 to adjust the volume level.
SUBTASK 860-059
(10) At all other audio control panels, push the receiver volume control
for NAV-1 to set the volume to off.
SUBTASK 860-060
(11) Push the receiver volume control for NAV-2 on all the audio control
panels to set the volume to off.
SUBTASK 730-026
(12) Push the IDENT switch on the test set, T-24B, to supply an
identification tone.
(a) Make sure you can hear a tone through the flight interphone
system.
SUBTASK 860-061
(13) Push the receiver volume control for NAV-1 on the audio control
panels to set the volume to off.
J.
SUBTASK 860-062
(14) Close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
No. 2 DME System Test (with the use of the test set, T-24B)
(1)
SUBTASK 860-063
Set the SOURCE switch on the instrument switching module to the AUTO
position.
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(2)
(3)
(4)
(5)
SUBTASK 860-080
Set a frequency of 109.00 MHz on the captain's and the first
officer's navigation control panels.
(a) Make sure the DME 1 shows dashes on the displays.
(b) Make sure the DME 2 shows dashes on the displays.
SUBTASK 730-027
Open this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
(b) Make sure the DME 1 has a flag on the displays.
SUBTASK 860-065
Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
SUBTASK 730-028
Use the DISTANCE switch to set a distance of 6 miles on the test
set, T-24B.
(a) Make sure the DME 2 shows 6 |0.5 nmi on the displays.
(6)
SUBTASK 860-066
Set the voice/range filter switch on one of the audio control panels
to the B position.
(7)
SUBTASK 860-067
At the same audio control panel, push the receiver volume control
for NAV-2 to set the volume to on.
(8)
SUBTASK 860-068
At the same audio control panel, turn the receiver volume control
clockwise for NAV-2 to adjust the volume level.
(9)
SUBTASK 860-069
At all other audio control panels, push the receiver volume control
for NAV-2 to set the volume to off.
SUBTASK 860-070
(10) Push the receiver volume control for NAV-1 on all the audio control
panels to set the volume to off.
SUBTASK 730-029
(11) Push the IDENT switch on the test set, T-24B, to supply an
identification tone.
(a) Make sure you can hear a tone through the flight interphone
system.
SUBTASK 860-071
(12) Push the receiver volume control for NAV-2 on the audio control
panels to set the volume to off.
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SUBTASK 860-072
(13) Close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
SUBTASK 860-073
(14) Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
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DME ANTENNA - REMOVAL/INSTALLATION
__________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the DME antenna
(2) An installation of the DME antenna.
B. The two DME antennas are installed on the bottom centerline of the
airplane fuselage.
TASK 34-55-11-000-801
2.
___________________
DME
Antenna Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 123 Area Below Forward
(b) 124 Area Below Forward
(c) 211 Flight Compartment
(d) 212 Flight Compartment
B. Removal Procedure
(1)
(2)
Cargo Compartment - Left
Cargo Compartment - Right
- Left
- Right
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
SUBTASK 020-001
Remove the DME antenna [3]:
(a) Remove the bolts [4] from the antenna base.
CAUTION:
_______
(b)
(c)
(d)
(e)
LOWER THE ANTENNA ONLY AS FAR AS NECESSARY TO DISCONNECT
THE COAXIAL CONNECTOR. DAMAGE TO THE CABLE CAN OCCUR IF
YOU PULL THE CABLE.
Lower the DME antenna [3] until you can get access to the
coaxial connector [1].
Disconnect the coaxial connector [1] from the DME antenna [3].
Remove the DME antenna [3].
Put a protective cover on the electrical connector.
TASK 34-55-11-400-801
3.
________________________
DME
Antenna Installation (Fig. 401)
A. References
(1) AMM TASK 20-30-84-910-801 p201, Final Cleaning of Metal Prior to
Painting (Series 84)
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 51-21-91-620-802 p701, Apply the Corrosion Inhibiting
Compound
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DME 1 ANTENNA
DME 2 ANTENNA
SEE
SEE
A
A
AIRPLANE
SKIN
NUTPLATES
[1] COAXIAL
CONNECTOR
[2] O-RING
[3] DME ANTENNA
FWD
[4] BOLT
(4 LOCATIONS)
DME ANTENNA
(REMOVED)
A
DME Antenna Installation
Figure 401
F70667
34-55-11-990-801
EFFECTIVITY
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B.
C.
D.
(4) SWPM 20-20-00
Equipment
(1) Ohmeter (or alternative tool)
(a) C15292 Ohmeter - Electrical Bonding (Model T477W) (recommended)
Avtron Manufacturing, Inc. (Vendor Code 01014)
7900 E. Pleasant Valley Road, Independence OH 44131
(b) MODEL 1010-A Ohmeter - Micro, Autoranging/Autotest, 10 Micro
Ohms to 200 Ohms, Accuracy: 0.05% (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(c) M-1 Ohmeter - Micro-ohm, Automatic, Stores 128 Readings, RS-232
Data Port, Range: 0.01 - 19.999 Milliohms, 4 1/2 Digit Display,
Accy: 0.1% of Readings (alternative)
Barberree Custom Design (Vendor Code 3AD17)
1401 Laurier House, 1600 Beach Ave., Vancouver, BC Canada V6G
1Y6
(2) Test (or alternative tool)
(a) ATC-600A-2 Test Set - ATC Transponder/DME, RAMP (recommended)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(b) 601-110 Test Set - ATC Transponder, RAMP (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
(c) T-48D Test Set - ATC Transponder, RAMP (alternative)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
(3) Test (or alternative tool)
(a) T-24B Test Set - DME (recommended)
Tel-Instrument Electronics Corp. (Vendor Code 92606)
728 Garden Street, Carlstadt NJ 07072-1621
(b) 01-0331-00 Test Set - DME (alternative)
JCAIR Inc. (Vendor Code 41364)
400 New Century Parkway, New Century KS 66031-0009
(c) 600A-110 Test Set - ATC Transponder/DME (alternative)
IFR Americas, Inc. (Vendor Code 51190)
10200 W. York St., Wichita KS 67215-8935
Consumable Materials
(1) A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
(2) B01004 Solvent, Final Cleaning of Metal Prior to Painting (AMM
20-30-84/201 or SOPM 20-30-84) - Series 84
(3) G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(4) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
Parts
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~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
3 ¦ Antenna
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 123 Area Below Forward Cargo Compartment - Left
(b) 124 Area Below Forward Cargo Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
F. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
SUBTASK 110-001
WARNING:
_______
(2)
(3)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR
SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE
HAZARDOUS MATERIALS. SOLVENTS MAY BE FLAMMABLE OR HARMFUL TO
THE ENVIRONMENT. REFER TO PRODUCT MATERIAL SAFETY DATA SHEETS
(MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING PROCEDURES.
Clean the airplane mating surface with solvent, Series 84
(AMM TASK 20-30-84-910-801 p201).
(a) Make a cloth, BMS15-5, moist (not soaked) with solvent.
(b) Rub the airplane mating surface with the cloth, BMS15-5, until
the surface is clean.
SUBTASK 420-001
Install the DME antenna [3]:
(a) Remove the protective cover from the electrical connector.
(b) Apply a thin layer of compound, BMS3-23, to the unpressurized
and pressurized sides of the o-ring groove. To apply the
compound, BMS3-23, do this task: Apply the Corrosion
Inhibiting Compound (AMM TASK 51-21-91-620-802 p701).
(c) Install the o-ring [2] on the antenna [3].
(d) Apply sealant, BMS5-95 to the threads of the bolts [4].
(e) Examine the coaxial connector [1] for bent or broken pins,
dirt, and damage.
(f) Connect the coaxial connector [1] to the antenna [3].
(g) Put the antenna [3] in the correct position on the airplane
surface.
(h) Install three of the four bolts [4].
EFFECTIVITY
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(4)
SUBTASK 760-001
Measure the resistance between the DME antenna baseplate and the
airplane skin with an ohmeter, C15292 (SWPM 20-20-00).
NOTE:
____
(a)
(5)
Use the empty hole to get access to the antenna baseplate.
Make sure the resistance is less than 0.001 ohm.
SUBTASK 420-002
Install the last bolt [4].
SUBTASK 860-006
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
Installation Test
(6)
G.
(1)
(2)
SUBTASK 860-003
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-005
Do these steps to prepare for the installation test:
CAUTION:
_______
(a)
DO NOT PUT THE TEST SET LESS THAN 15 INCHES (38 CM) FROM
THE DME ANTENNA WITH THE TEST SET ON. YOU CAN CAUSE
DAMAGE TO THE TEST SET.
Put the DME test set approximately 21 inches (53 cm) from the
DME antenna.
NOTE:
____
(b)
The test antenna should be approximately the same height
as the airplane antenna.
For the DME test test set, T-24B, put the switches in these
positions:
SWITCH NAME
SWITCH POSITION
POWER
ON
IDENT
OFF
DIST/VEL
DIST
Squitter Switch
ON
EFFECTIVITY
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(c)
For the DME test test set, ATC-600A-2, put the switches in
these positions:
SWITCH NAME
(d)
(e)
(f)
(3)
(4)
SWITCH POSITION
PWR Switch
AC or BAT as appropriate
Mode Switch
DME
Velocity Select Switch
Range
Velocity HI/LO Switch
HI
Squitter Switch
SQTR
X/Y Switch
X
Set the NAV switch on the instrument switching module to the
NORMAL position.
Set the SOURCE switch on the instrument switching module to the
AUTO position.
Set the display select switch on the captain's and the first
officer's EFIS control panels to the VOR position.
SUBTASK 710-001
Do these steps to do a test of the No. 1 (captain's) DME antenna
with the use of test set, ATC-600A-2:
(a) Set a frequency of 108.00 MHz on the captain's navigation
control panel.
(b) Set a frequency of 109.00 MHz on the first officer's navigation
control panel.
(c) Set the X/Y switch on the DME test test set, ATC-600A-2, to Y.
(d) Use the SLEW switch to set a distance of 6 miles on the DME
test test set, ATC-600A-2.
1) Make sure the DME 1 shows dashes on the displays.
(e) Set the X/Y switch on the DME test test set, ATC-600A-2, to X.
1) Make sure the DME 1 shows 6 |0.5 nmi on the displays.
SUBTASK 710-003
Do these steps to do a test of the No. 1 (captain's) DME antenna
with the use of test set, T-24B:
(a) Set a frequency of 108.00 MHz on the captain's navigation
control panel.
(b) Set a frequency of 109.00 MHz on the first officer's navigation
control panel.
(c) Use the DISTANCE switch to set a distance of 6 miles on the DME
test test set, T-24B.
1) Make sure the DME 1 shows 6 |0.5 nmi on the displays.
EFFECTIVITY
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(5)
(6)
SUBTASK 710-002
Do these steps to do a test of the No. 2 (first officer's) DME
antenna with the use of DME test test set, ATC-600A-2:
(a) Set a frequency of 109.00 MHz on the captain's navigation
control panel.
(b) Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
(c) Set the X/Y switch on the DME test test set, ATC-600A-2, to Y.
(d) Use the SLEW to set a distance of 6 miles on the DME test test
set, ATC-600A-2.
1) Make sure the DME 2 shows dashes on the displays.
(e) Set the X/Y switch on the DME test test set, ATC-600A-2, to X.
1) Make sure the DME 2 shows 6 |0.5 nmi on the displays.
SUBTASK 710-004
Do these steps to do a test of the No. 2 (first officer's) DME
antenna with the use of DME test test set, T-24B:
(a) Set a frequency of 109.00 MHz on the captain's navigation
control panel.
(b) Set a frequency of 108.00 MHz on the first officer's navigation
control panel.
(c) Use the DISTANCE switch to set a distance of 6 miles on the DME
test test set, T-24B.
1) Make sure the DME 2 shows 6 |0.5 nmi on the displays.
EFFECTIVITY
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DME INTERROGATOR - REMOVAL/INSTALLATION
_______________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the distance measuring equipment (DME) interrogator.
(2) An installation of the DME interrogator.
B. The two DME interrogators are in the main equipment center. The No. 1
DME interrogator is on the E1 electronic equipment rack, shelf No. 2.
The No. 2 DME interrogator is on the E1 electronic equipment rack, shelf
No. 5.
TASK 34-55-21-000-801
2.
________________________
DME
Interrogator Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center.
SUBTASK 020-001
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE DME
INTERROGATOR [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE DME INTERROGATOR [1].
To remove the DME interrogator [1], do this task:
(AMM TASK 20-10-07-000-801 p201).
EFFECTIVITY
E/E Box Removal
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ELECTRONIC
EQUIPMENT
RACK, E1
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] DME INTERROGATOR
NO. 2 (E1-5)
[1] DME INTERROGATOR
NO. 1 (E1-2)
FWD
ELECTRONIC EQUIPMENT RACK, E1
A
DME Interrogator Installation
Figure 401
G04046
34-55-21-990-801
EFFECTIVITY
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TASK 34-55-21-400-801
3.
_____________________________
DME
Interrogator Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Interrogator
¦
TO BE FURNISHED
¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 117 Electrical and Electronics Compartment - Left
(b) 118 Electrical and Electronics Compartment - Right
(c) 211 Flight Compartment - Left
(d) 212 Flight Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Installation Procedure
(1)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
SUBTASK 420-001
CAUTION:
_______
(2)
(3)
(4)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE DME
INTERROGATOR [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE DME INTERROGATOR [1].
To install the DME interrogator [1], do this task:
Installation (AMM TASK 20-10-07-400-801 p201).
E/E Box
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A.
SUBTASK 860-003
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A14
RADIO NAVIGATION DME 2
(b) Circuit Breaker Panel, P18-1:
1) 18B3
RADIO NAVIGATION DME 1
EFFECTIVITY
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E.
Installation Test
(1)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(2)
SUBTASK 860-005
Set the VHF NAV switch on the instrument switching module to the
NORMAL position.
(3)
SUBTASK 860-007
Set a frequency of 109.00 MHz on the captain's and the first
officer's navigation control panels.
(4)
SUBTASK 710-001
Do these steps to do a test of the No. 1 DME interrogator:
(a) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(b) Push the TEST button on the captain's navigation control panel
to start the DME 1 self test.
(c) Make sure this sequence occurs on the captain's and the first
officer's displays:
NOTE:
____
1)
2)
(5)
The DME 1 has a flag on the displays for approximately two
seconds.
The DME 1 is dashes on the displays until the end of the
test.
SUBTASK 710-002
Do these steps to do a test of the No. 2 DME interrogator:
(a) Set the SOURCE switch on the instrument switching module to the
AUTO position.
(b) Push the TEST button on the first officer's navigation control
panel to start the DME 2 self test.
(c) Make sure this sequence occurs on the captain's and the first
officer's displays:
NOTE:
____
1)
2)
(6)
The DME 2 shows dashes on the displays during the DME 1
self test.
The DME 1 shows dashes on the displays during the DME 2
self test.
The DME 2 has a flag on the displays for approximately two
seconds.
The DME 2 is dashes on the displays until the end of the
test.
SUBTASK 860-008
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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AUTOMATIC DIRECTION FINDER SYSTEM - ADJUSTMENT/TEST
___________________________________________________
1.
General
_______
A. The system test is a full functional check of the ADF system and its
interfaces.
TASK 34-57-00-730-802
2.
_______________________________________________
Automatic
Direction Finder System - System Test
A. General
(1) Some of the tests need radio reception from local AM commercial
broadcast stations or ADF beacon transmitting stations.
NOTE:
____
B.
C.
D.
ADF bearing checks on the ground, in hangers, or near other
airplanes, metal buildings and equipment, etc. may show
inaccurate bearings or weak signals.
References
(1) AMM TASK 23-51-00-710-801 p501, Flight Interphone System Operational Test
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(4) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(5) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(b) 211 Flight Compartment - Left
(c) 212 Flight Compartment - Right
Prepare for the Test
(1)
SUBTASK 840-005
Do these steps to prepare for the test:
(a) Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
(b) Make sure the Flight Interphone System is on
(AMM TASK 23-51-00-710-801 p501).
(c) Make sure the Air Data Inertial Reference System is on
(AMM TASK 34-21-00-820-801 p201) or
(AMM TASK 34-21-00-820-802 p201).
(d) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P6-1:
a) 6A17
RADIO NAVIGATION ADF 2
(e) Set the left and right VOR/ADF switches on the RMI to the ADF
position.
(f) Set the CDS switch on the P5 panel to the AUTO position.
(g) On the captain's and first officer's EFIS control panels, set
the VOR1/OFF/ADF1 switches to the ADF 1 position.
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(h)
(2)
On the captain's and first officer's EFIS control panels, set
the VOR2/OFF/ADF2 switches to the ADF 2 position.
SUBTASK 860-055
For the audio select panels, do these steps:
(a) Set the ADF 1 audio selector to the ON position.
NOTE:
____
(b)
(c)
Make sure that the volume for the ADF 1 system is set to
a comfortable level.
Set the volume controls for all other audio selects to the OFF
position.
Set the VOICE/RANGE switch to the BOTH position.
SUBTASK 860-058
On the ADF control panel, set the switches as follows:
(a) The ADF 1 mode switch to the ADF position.
(b) The ADF 2 mode switch to the ADF position.
(c) The TONE switch to the OFF position.
ADF BITE Test
(3)
E.
(1)
SUBTASK 740-017
Do these steps to do a test of the ADF BITE:
(a) On the ADF control panel, push and release the TEST switch on
the ADF 1 mode switch.
1) Make sure the narrow pointer on the RMI slews to 135°
relative to the Heading Lubber Line.
(b) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-1:
a) 18A4
RADIO NAVIGATION ADF 1
(c) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P6-1:
a) 6A17
RADIO NAVIGATION ADF 2
(d) On the ADF control panel, push and release the TEST switch on
the ADF 2 mode switch.
1) Make sure the narrow pointer on the RMI slews to 135°
relative to the Heading Lubber Line.
(e) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-1:
a) 18A4
RADIO NAVIGATION ADF 1
(f) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P6-1:
a) 6A17
RADIO NAVIGATION ADF 2
ú
(g)
ú
(h)
SUBTASK 750-032
AIRPLANES WITH THE EFIS DISPLAY FORMAT;
Make sure the narrow needles on the captain's and first
officer's RDMI's point to the selected bearing.
AIRPLANES WITH THE PFD/ND DISPLAY FORMAT;
Make sure the ADF pointers on the captain's and first officer's
ND's point to the selected bearing.
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ú
(i)
ú
AIRPLANES WITH THE PFD/ND DISPLAY FORMAT;
Make sure the ADF frequencies which show on the bottom left
corner of the captain's and first officer's ND's are the same
as the frequency from the ADF control panel.
SUBTASK 860-062
AIRPLANES WITH THE EFIS DISPLAY FORMAT;
Make sure the narrow needle flags show on the captain's and
first officer's RDMI's.
(k) AIRPLANES WITH THE PFD/ND DISPLAY FORMAT;
Make sure the yellow ADF flags show on the captain's and first
officer's ND's.
ADF-1 and ADF-2 System Test
(j)
ú
F.
(1)
(2)
(3)
(4)
(5)
SUBTASK 860-064
Set the ADF 1 frequency control on the ADF control panel to a local
AM broadcast or NDB station.
SUBTASK 750-033
Do these steps to do a check of the ADF-1 system test:
(a) Make sure you hear a loud and clear ADF audio signal at all
audio select locations.
(b) Make sure the narrow needle on the RMI points to the selected
bearing.
(c) Make sure the ADF-1 pointers on the captain's and first
officer's ND's point to the selected bearing.
(d) Make sure the ADF L frequencies which show on the bottom left
corner of the captain's and first officer's ND's are the same
as the frequency from the ADF control panel.
SUBTASK 860-066
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
(b) Make sure the narrow needle flag shows on the RMI.
(c) Make sure the yellow ADF flags show on the captain's and first
officer's ND's.
SUBTASK 860-067
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 860-068
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
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(6)
(7)
SUBTASK 860-069
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
SUBTASK 860-070
For the audio select panels, do these steps:
(a) Set the ADF 2 audio selector to the ON position.
NOTE:
____
(b)
(c)
(8)
(9)
ú
ú
ú
ú
Make sure that the volume for the ADF 2 system is set to
a comfortable level.
Set the volume contols for all other audio selects to the OFF
position.
Set the VOICE/RANGE switch to the BOTH position.
SUBTASK 860-071
Set the ADF 2 frequency control on the ADF control panel to a local
AM broadcast or NDB station.
SUBTASK 750-034
Do these steps to do a check of the ADF-2 system:
(a) Make sure you hear a loud and clear ADF audio signal at all
audio select locations.
(b) Make sure the wide needle on the RMI points to the selected
bearing.
(c) Make sure the wide needles on the captain's and first officer's
RDMI's point to the selected bearing.
(d) Make sure the ADF-2 pointers on the captain's and first
officer's ND's point to the selected bearing.
(e) Make sure the ADF R frequencies which show on the bottom right
corner of the captain's and first officer's ND's are the same
as the frequency from the ADF control panel.
SUBTASK 860-073
(10) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Make sure the wide needle flag shows on the RMI.
(c) Make sure the wide needle flags show on the captain's and first
officer's RDMI's.
(d) Make sure the yellow ADF flags show on the captain's and first
officer's ND's.
SUBTASK 860-074
(11) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
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G.
SUBTASK 860-075
(12) Remove the DO-NOT-CLOSE tag and close this circuit breaker:
(a) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
Put the Airplane Back to Its Usual Position
(1)
SUBTASK 860-076
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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ADF ANTENNA - REMOVAL/INSTALLATION
__________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the automatic direction finder (ADF) antenna
(2) An installation of the ADF antenna.
B. The left and right ADF antennas are installed on the top of the
The left ADF antenna is installed at station 694.00. The right
antenna is installed at station 727A+9.00.
C. ASA 001-016;
The left and right ADF antennas are installed on the top of the
The left ADF antenna is installed at station 694.00. The right
antenna is installed at station 727A+9.00.
fuselage.
ADF
fuselage.
ADF
TASK 34-57-01-000-801
2.
___________________
ADF
Antenna Removal (Fig. 401)
A. References
(1) AMM TASK 51-31-00-390-806 p201, Aerodynamic Smoother Application
B. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
(c) 240 Subzone - Passenger Compartment - Body Station 663.75 to
Body Station 1016.00
D. Removal Procedure
(1)
(2)
(3)
SUBTASK 860-001
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 140-003
Remove the aerodynamic smoother from around the edge of the
applicable ADF antenna [1] (AMM TASK 51-31-00-390-806 p201).
SUBTASK 860-019
ASA 001-016;
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
EFFECTIVITY
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SEE
A
[1] ADF ANTENNA
A
[4] MOUNTING BOLT
(12 LOCATIONS)
1
[2] O-RING
A
[3] COAXIAL
CONNECTOR
ADF ANTENNA
A
1
FWD
CAPTIVE MOUNTING BOLTS ARE USED ON THE ANTENNA BASEPLATE
ADF Antenna Installation
Figure 401 (Sheet 1)
H01817
34-57-01-990-801
EFFECTIVITY
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PREFERRED RESISTANCE
MEASUREMENT COUNTERBORE
NAMEPLATE
AERODYNAMIC/
WEATHER
SEAL
ALTERNATE RESISTANCE
MEASUREMENT
SEE
B
AERODYNAMIC/WEATHERPROOFING SEALANT
(TOP VIEW)
A-A
RESISTANCE MEASUREMENT
SEE
C
ALTERNATE RESISTANCE MEASUREMENT
(SIDE VIEW)
B
RESISTANCE MEASUREMENT
RESISTANCE MEASUREMENT
(BOTTOM VIEW)
C
ADF Antenna Installation
Figure 401 (Sheet 2)
G15009
EFFECTIVITY
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(4)
(5)
SUBTASK 140-008
ASA 001-016;
Remove the aerodynamic smoother from around the edge of the
applicable ADF antenna [1] (AMM TASK 51-31-00-390-806 p201).
SUBTASK 020-001
Remove the ADF antenna [1]:
(a) Loosen the mounting bolts [4] and until they disengage from the
airplane nutplates.
CAUTION:
_______
(b)
BE CAREFUL WHEN YOU USE THE SEALANT REMOVAL TOOL TO BREAK
THE SEAL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE AIRPLANE
SKIN, THE ANTENNA CABLE, OR THE ADF ANTENNA [1].
Use force around the ADF antenna [1] with the sealant removal
tool until the seal is fully broken.
CAUTION:
_______
(c)
(d)
LIFT THE ADF ANTENNA [1] ONLY AS FAR AS NECESSARY TO
DISCONNECT THE CABLE. DAMAGE TO THE ANTENNA CABLE CAN
OCCUR IF YOU PULL THE CABLE.
Lift the ADF antenna [1] until you can get access to the
coaxial connector [3].
Disconnect the coaxial connector [3] from the ADF antenna [1].
NOTE:
____
(e)
(f)
Do not let the coaxial connector [3] fall into the
fuselage.
Remove the ADF antenna [1] and the o-ring [2].
Put a protective cover on the coaxial connector [3].
TASK 34-57-01-400-801
3.
________________________
ADF
Antenna Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(3) AMM TASK 51-21-00-100-801 p701, Airplane Surface Preparation for
Application of Finish
(4) AMM TASK 51-21-31-350-801 p701, Removal and Control of Corrosion for
Aluminum and Aluminum Alloys
(5) AMM TASK 51-31-00-390-804 p201, Fillet Seal Application
(6) AMM TASK 51-31-00-390-805 p201, Fastener Seal Application
B. Equipment
(1) Ohmmeter - Resistance Measuring Bridge
(commercially available)
(2) Spatula - Fillet Smoothing, Hardwood or Plastic
(commercially available)
C. Consumable Materials
(1) A00230 Compound, Electrical Insulating Coating - BMS5-37
EFFECTIVITY
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(2)
(3)
(4)
(5)
(6)
A00247 Sealant, Pressure and Environmental-Chromate Type - BMS5-95
A02315 Sealant, Low density, synthetic rubber. 2 part - BMS5-142
B00083 Solvent, Aliphatic naphtha (for acrylic plastics) - TT-N-95,
Type II
C00064 Coating, Aluminum chemical conversion BAC5719,TypeII,ClassA(MIL-C-5541,ClassA)
C00175 Primer, Urethane Compatible, Corrosion Resistant (less than
1% aromatic amines) - BMS10-79, Type III
D00015 Grease, Aircraft bearing - BMS3-24
G02185 Coating, Green, strippable - Guardsman 598-5002
(7)
(8)
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Antenna
¦ 34-57-01
01
315 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
(c) 240 Subzone - Passenger Compartment - Body Station 663.75 to
Body Station 1016.00
F. Installation Procedure
(1)
(2)
(3)
SUBTASK 860-002
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 860-013
ASA 001-016;
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 110-001
Clean the airplane skin (AMM TASK 51-21-00-100-801 p701):
(a) Remove the old sealant from the airplane skin in the ADF
antenna [1] area.
(b) Clean the mating surface with solvent, TT-N-95, Type II.
EFFECTIVITY
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(4)
(5)
SUBTASK 620-001
If the airplane skin has corrosion or other damage, do these steps:
(a) To remove the corrosion, do this task: Removal and Control of
Corrosion for Aluminum and Aluminum Alloys
(AMM TASK 51-21-31-350-801 p701).
(b) Apply a layer of coating,
BAC5719,TypeII,ClassA(MIL-C-5541,ClassA), on the airplane skin
in the area where the ADF antenna [1] touches the skin.
(c) Apply two layers of primer, BMS10-79, Type III, on top of the
alodine.
SUBTASK 420-001
Install the ADF antenna [1]:
(a) Apply a thin layer of compound, BMS5-37, to the antenna base.
(b) Apply a thin layer of compound, BMS5-37, to the pressurized and
unpressurized sides of the o-ring [2].
NOTE:
____
(c)
(d)
(e)
(f)
(g)
(h)
(i)
(j)
Do not get the compound on the o-ring [2] or in the
o-ring groove and the coaxial connector [3].
Apply a layer of compound, BMS5-37, in the nutplate and the
open area where the antenna cable connects to the ADF antenna
[1].
Apply the coating, Guardsman 598-5002 to the antenna base.
Apply a layer of grease, BMS3-24, on the o-ring [2] and o-ring
groove.
Install the o-ring [2] on the ADF antenna [1].
Remove the protective cover from the coaxial connector [3].
Connect the coaxial connector [3] to the ADF antenna [1].
Put the ADF antenna [1] into position on the airplane surface.
Lightly tighten the mounting bolts [4] in a diagonal pattern to
hold the ADF antenna [1] in the correct position.
NOTE:
____
CAUTION:
_______
Refer to the IPC for the bolt part number.
TIGHTEN THE BOLTS MANUALLY TO THE CORRECT TORQUE VALUE.
USE OF POWER OR AIR TOOLS TO TIGHTEN THE SCREWS CAN CAUSE
DAMAGE TO THE ADF antenna [1] SURFACE.
(k)
G.
Manually tighten the mounting bolts [4] and to 20-25
pound-inches (2.3-2.8 newton-meters) of torque.
(l) Remove the unwanted compound, BMS5-37, from around the edge of
the ADF antenna [1].
Resistance Measurement (Preferred)
(1)
SUBTASK 760-001
Do a check of the electrical continuity between the ADF antenna [1]
baseplate and the airplane skin:
(a) Loosen one mounting bolt [4] from the ADF antenna [1].
EFFECTIVITY
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(b)
H.
Connect the ohmmeter between the bolt counterbore and the
airplane skin.
1) Make sure the measurement of continuity is 1 milliohm or
less.
(c) If the resistance measurement caused damage, apply the sealant,
BMS5-142 or sealant, BMS5-95, to the damaged area of the
airplane skin.
(d) Manually, tighten the mounting bolt [4] to 20-25 pound-inches
(2.3-2.8 newton-meters) of torque.
Resistance Measurement (Alternate)
SUBTASK 760-002
Do a check of the electrical continuity from the inside of the
airplane between the ADF antenna [1] baseplate and the airplane
skin:
(a) Connect the ohmmeter between the ADF antenna [1] baseplate and
the airplane skin.
1) Make sure the measurement of continuity is 1 milliohm or
less.
(b) If the resistance measurement caused damage, apply the sealant,
BMS5-142 or sealant, BMS5-95 , to the damaged area of the
airplane skin.
ADF Antenna Sealing
(1)
I.
(1)
(2)
(3)
(4)
SUBTASK 390-001
Fill the mounting bolt [4] counterbores with approximately 0.3
inches (7.6 mm) of cotton plug.
SUBTASK 390-002
Seal all the mounting bolts [4] with sealant, BMS5-142 or sealant,
BMS5-95 , until flush with the ADF antenna [1] surface
(AMM TASK 51-31-00-390-805 p201).
SUBTASK 390-003
Apply the sealant, BMS5-142 or sealant, BMS5-95 , to seal around the
ADF antenna [1] (AMM TASK 51-31-00-390-804 p201).
SUBTASK 390-004
Use the spatula to make a smooth 45-degree bead.
SUBTASK 140-002
Remove unwanted sealant from the area around the ADF antenna [1]
base.
ADF Antenna Installation Test
(5)
J.
(1)
SUBTASK 860-003
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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(2)
(3)
(4)
SUBTASK 860-009
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 860-015
ASA 001-016;
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 860-005
On the ADF control panel, set the controls to these positions:
(a) The mode switch to the ADF position
(b) The frequency controls to a broadcast station between 190 and
1750 kHz.
SUBTASK 750-001
Set the bearing source switches on the RMIs to the ADF position.
(a) Make sure that the RMIs show the correct bearing.
Put the Airplane Back to Its Usual Condition
(5)
K.
(1)
SUBTASK 860-006
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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ADF CONTROL PANEL - REMOVAL/INSTALLATION
________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the automatic direction finder (ADF) control panel
(2) An installation of the ADF control panel.
B. The ADF control panel is installed on the aisle control stand, P8.
TASK 34-57-02-000-801
2.
_________________________
ADF
Control Panel Removal (Fig. 401)
A. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
B. Removal Procedure
(1)
(2)
(3)
SUBTASK 860-004
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
(a) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 020-001
Loosen the quarter-turn fasteners [2] on the ADF control panel [1].
SUBTASK 020-002
Move the control panel out to get access to the electrical connector
[3].
(4)
SUBTASK 020-003
Disconnect the electrical connector [3].
(5)
SUBTASK 020-004
Remove the ADF control panel [1].
TASK 34-57-02-400-801
3.
______________________________
ADF
Control Panel Installation (Fig. 401)
A. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
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¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Panel
¦ 34-57-02
01
85 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
EFFECTIVITY
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SEE
A
FLIGHT COMPARTMENT
[1] ADF CONTROL
PANEL 1
[2] QUARTER-TURN
FASTENER
(4 LOCATIONS)
[3] ELECTRICAL
CONNECTOR
FWD
1
THE LOCATION ON THE AISLE STAND CAN
BE DIFFERENT FOR SOME AIRPLANES
AISLE STAND
A
ADF Control Panel Installation
Figure 401
34-57-02-990-801
EFFECTIVITY
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C.
Installation Procedure
(1)
SUBTASK 860-005
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
(2)
SUBTASK 420-001
Connect the electrical connector [3] to the ADF control panel [1].
(3)
SUBTASK 420-002
Install the ADF control panel [1].
(4)
SUBTASK 420-003
Tighten the quarter-turn fasteners [2] on the ADF control panel [1].
(5)
(6)
(7)
ú
ú
ú
SUBTASK 860-006
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 860-015
ASA 001-016;
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 750-001
Make sure the panel lights are on.
(a) Do the ADF System - System Test (AMM 34-57-00/501).
(b) Remove electrical power if it is not necessary (AMM
24-22-00/201).
EFFECTIVITY
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ADF RECEIVER - REMOVAL/INSTALLATION
___________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the automatic direction finder (ADF) receiver
(2) An installation of the ADF receiver.
B. The ADF receivers are installed on the E3-1 rack in the main equipment
center.
TASK 34-57-03-000-801
2.
____________________
ADF
Receiver Removal (Fig. 401)
A. References
(1) AMM TASK 06-41-00-800-801 p201, Finding an Access Door or Panel on
the Lower Half of the Fuselage
(2) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. Removal Procedure
(1)
(2)
SUBTASK 860-005
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center (AMM TASK 06-41-00-800-801 p201).
SUBTASK 020-002
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE ADF
RECEIVER [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE ADF RECEIVER [1].
Remove the applicable ADF receiver [1]. To remove it, do this task:
E/E Box Removal (AMM TASK 20-10-07-000-801 p201).
TASK 34-57-03-400-801
3.
_________________________
ADF
Receiver Installation (Fig. 401)
A. References
(1) AMM TASK 06-41-00-800-801 p201, Finding an Access Door or Panel on
the Lower Half of the Fuselage
(2) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
EFFECTIVITY
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ELECTRONIC EQUIPMENT
RACK, E2, E3 AND E4
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] ADF
RECEIVER
NO. 2
(E3-1)
[1] ADF
RECEIVER
NO. 1
(E3-1)
ELECTRONIC
EQUIPMENT
ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACKS, E2, E3 AND E4
A
ADF Receiver Installation
Figure 401
G75212
34-57-03-990-801
EFFECTIVITY
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(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
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¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦
¦ ASA 101-999;
¦
¦
¦ 401
1 ¦ Receiver
¦ 34-57-03
02
10 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
C. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
D. Installation Procedure
(1)
SUBTASK 860-006
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
SUBTASK 420-002
CAUTION:
_______
(2)
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE ADF
RECEIVER [1]. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE ADF RECEIVER [1].
Install the applicable ADF receiver [1]. To install it, do this
task: E/E Box Installation (AMM TASK 20-10-07-400-801 p201).
SUBTASK 410-001
Close the Electronic Equipment Access Door, 117A
(AMM TASK 06-41-00-800-801 p201).
SUBTASK 860-007
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6A17
RADIO NAVIGATION ADF 2
(b) Circuit Breaker Panel, P18-1:
1) 18A4
RADIO NAVIGATION ADF 1
ADF Receiver Installation Test
(4)
E.
(1)
SUBTASK 860-022
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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(2)
SUBTASK 860-004
Set the ADF/VOR switch on the RMI to the ADF position.
(3)
SUBTASK 860-010
Push and release the applicable TEST switch on the ADF receiver.
(4)
(5)
SUBTASK 750-002
Make sure these indications occur on the RMI:
(a) The left and right ADF/VOR warning flags come into view.
(b) The left and right bearing pointers go to 135 degrees.
SUBTASK 860-026
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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GLOBAL POSITIONING SYSTEM - ADJUSTMENT/TEST
___________________________________________
1.
General
_______
A. This procedure has these tasks:
(1) An operational test of the global positioning system (GPS).
(2) A system test of the global positioning system.
NOTE:
____
The airplane must be moved to a position where the GPS
antennas have a clear view of the GPS satellites.
TASK 34-58-00-710-801
2.
____________________________________________
Global
Positioning System - Operational Test
A. General
(1) This task does a GPS position check.
B. References
(1) AMM TASK 09-11-00-580-801 p201, Towing
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Procedure
(1)
(2)
(3)
(4)
SUBTASK 860-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-008
Make sure that these circuit breakers are closed:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 580-001
Move the airplane to a position where the GPS antennas have a clear
view of the GPS satellites. To move the airplane to the compass
swing area, do this task: Towing (AMM TASK 09-11-00-580-801 p201).
SUBTASK 710-001
Do these steps to see the GPS position on the CDU:
(a) Push the INIT REF key on the CDU.
(b) Push the line select key (LSK) that is adjacent to <INDEX.
(c) Push the LSK that is adjacent to <POS.
(d) Push the NEXT PAGE key on the CDU.
EFFECTIVITY
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(e)
Make sure the steps that follow occur:
1) The GPS L position on the CDU agrees with the known
airplane position.
NOTE:
____
2)
As much as 5 minutes of time can be necessary for
the positions to show on the CDU.
The GPS R position on the CDU agrees with the known
airplane position.
NOTE:
____
As much as 5 minutes of time can be necessary for
the positions to show on the CDU.
TASK 34-58-00-730-801
3.
_______________________________________
Global
Positioning System - System Test
A. General
(1) This procedure does a GPS interface check.
(2) The airplane must be moved to a position where the GPS antennas have
a clear view of the GPS satellites.
B. References
(1) AMM TASK 09-11-00-580-801 p201, Towing
(2) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(3) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
C. Access
(1) Location Zones
(a) 211 Flight Compartment, Left
(b) 212 Flight Compartment, Right
D. Procedure
(1)
(2)
(3)
(4)
SUBTASK 580-002
Move the airplane to a position where the GPS antennas have a clear
view of the GPS satellites. To move the airplane to the compass
swing area, do this task: Towing (AMM TASK 09-11-00-580-801 p201).
SUBTASK 860-003
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-004
Make sure that these circuit breakers are closed:
(a) Circuit Breaker Panel, P6-1:
1) 6A13
RADIO NAVIGATION MMR 2
(b) Circuit Breaker Panel, P18-1:
1) 18A2
RADIO NAVIGATION MMR 1
SUBTASK 710-004
Do these steps to see the GPS position on the CDU:
(a) Push the INIT REF key on the CDU.
(b) Push the line select key (LSK) that is adjacent to <INDEX.
EFFECTIVITY
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(c)
(d)
(e)
Push the LSK that is adjacent to <POS.
Push the NEXT PAGE key on the CDU.
Make sure the steps that follow occur:
1) The GPS L position on the CDU agrees with the known
airplane position.
NOTE:
____
2)
As much as 5 minutes of time can be necessary for
the positions to show on the CDU.
The GPS R position on the CDU agrees with the known
airplane position.
NOTE:
____
As much as 5 minutes of time can be necessary for
the positions to show on the CDU.
SUBTASK 710-003
Do these steps to do a check of the GPS annunciator on the IRS MSU
(P5 panel):
(a) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-1:
a) 18A2
RADIO NAVIGATION MMR 1
2) Make sure the GPS L position goes out of view on the CDU.
3) Make sure the GPS R position stays in view on the CDU.
4) Make sure the GPS annunciator on the IRS MSU (P5) stays
off.
(b) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P6-1:
a) 6A13
RADIO NAVIGATION MMR 2
2) Make sure the GPS R position goes out of view on the CDU.
3) Make sure the GPS L position stays out of view on the CDU.
4) Make sure the GPS annunciator on the IRS MSU (P5) comes on
after approximately 10 seconds.
(c) Remove the DO-NOT-CLOSE tags and close these circuit breakers:
1) Circuit Breaker Panel, P6-1:
a) 6A13
RADIO NAVIGATION MMR 2
2) Circuit Breaker Panel, P18-1:
a) 18A2
RADIO NAVIGATION MMR 1
(d) Make sure the GPS annunciator on the IRS MSU goes off.
(e) Stop for approximately 5 minutes until the GPS L and GPS R
positions are shown again.
Put the Airplane Back to Its Usual Condition
(5)
E.
(1)
SUBTASK 860-007
Remove electrical power, if it is not necessary
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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GPS ANTENNA - REMOVAL/INSTALLATION
__________________________________
1.
General
_______
A. This procedure has these tasks:
(1) A removal of the GPS antenna.
(2) An installation of the GPS antenna.
B. There are two GPS antennas on the airplane: GPS Antenna 1, M2103, and
GPS Antenna 2, M2102. The two antennas are installed near station 500A.
GPS Antenna 2 is forward and to the right of GPS Antenna 1.
C. The tasks are the same for the two antennas.
TASK 34-58-02-000-801
2.
___________________
GPS
Antenna Removal (Fig. 401)
A. References
(1) AMM TASK 51-31-00-160-801 p201, Prepare For Sealing
B. Equipment
(1) Tool - Sealant Removal, Hardwood or Plastic
(commercially available)
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
(c) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(d) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
D. Removal Procedure
(1)
(2)
SUBTASK 020-001
To remove the sealant from around the edge of the GPS antenna [1],
do this task: Prepare For Sealing (AMM TASK 51-31-00-160-801 p201).
SUBTASK 020-002
Do these steps to remove the GPS antenna [1]:
(a) Remove the seals that are above the screw holes on the antenna.
(b) Remove the screws [2] from the GPS antenna [1].
CAUTION:
_______
(c)
BE CAREFUL WHEN YOU USE THE SEALANT REMOVAL TOOL TO BREAK
THE SEAL. TOO MUCH FORCE CAN CAUSE DAMAGE TO THE AIRPLANE
SKIN, THE COAXIAL CABLE, OR THE ANTENNA.
Use the sealant removal tool to break the seal all around the
GPS antenna [1].
EFFECTIVITY
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GPS ANTENNA 2
(STA 500A,
RBL 5)
GPS ANTENNA 1
(STA 500A,
LBL 5)
SEE
SEE
A
[1] GPS ANTENNA 2
A
[1] GPS ANTENNA 1
[2] SCREW
(4 LOCATIONS)
AIRPLANE
SKIN
[4] O-RING
[3] COAXIAL
CONNECTOR
FWD
GPS ANTENNA
A
GPS Antenna Installation
Figure 401
F62451
34-58-02-990-801
EFFECTIVITY
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CAUTION:
_______
(d)
(e)
MOVE THE ANTENNA THE LEAST DISTANCE NECESSARY TO PERMIT
YOU TO DISCONNECT THE COAXIAL CONNECTOR. DAMAGE TO THE
COAXIAL CABLE CAN OCCUR IF YOU PULL THE CABLE WITH TOO
MUCH FORCE.
Carefully pull the GPS antenna [1] until you can get access to
the coaxial connector [3].
Disconnect the coaxial connector [3].
NOTE:
____
(f)
(g)
Make sure the coaxial cable and connector [3] do not
fall into the airplane fuselage.
Remove the GPS antenna [1] and the O-ring [4].
Put protective covers on the coaxial connector [3].
TASK 34-58-02-400-801
3.
________________________
GPS
Antenna Installation (Fig. 401)
A. References
(1) AMM TASK 20-30-84-910-801 p201, Final Cleaning of Metal Prior to
Painting (Series 84)
(2) AMM TASK 20-30-92-910-801 p201, Final Cleaning Prior to General
Sealing (Series 92)
(3) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(4) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(5) AMM TASK 25-21-45-000-801 p401, Sculptured Ceiling Panel Removal
(6) AMM TASK 25-21-45-400-801 p401, Sculptured Ceiling Panel
Installation
(7) AMM TASK 51-21-21-100-801 p701, Clean the Surface to be Painted
(8) AMM TASK 51-21-31-350-801 p701, Removal and Control of Corrosion for
Aluminum and Aluminum Alloys
(9) AMM TASK 51-21-41-370-802 p701, Apply Alodine 600, 1200 or 1200S
Solution
(10) AMM TASK 51-21-91-620-802 p701, Apply the Corrosion Inhibiting
Compound
(11) AMM TASK 51-31-00-390-804 p201, Fillet Seal Application
B. Equipment
(1) Ohmmeter - Resistance Measuring Bridge
(commercially available)
(2) Spatula - Fillet Smoothing, Hardwood or Plastic
(commercially available)
C. Consumable Materials
(1) A02315 Sealant, Low density, synthetic rubber. 2 part - BMS5-142
(2) B01004 Solvent, Final Cleaning of Metal Prior to Painting (AMM
20-30-84/201 or SOPM 20-30-84) - Series 84
(3) B01012 Solvent, Final Cleaning Prior to General Sealing (AMM
20-30-92/201 or SOPM 20-30-92) - Series 92
(4) C00064 Coating, Aluminum chemical conversion BAC5719,TypeII,ClassA(MIL-C-5541,ClassA)
EFFECTIVITY
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(5)
C00175 Primer, Urethane Compatible, Corrosion Resistant (less than
1% aromatic amines) - BMS10-79, Type III
D00015 Grease, Aircraft bearing - BMS3-24
G00009 Compound, Organic Corrosion Inhibiting - BMS3-23
(6)
(7)
D. Parts
~¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
AMM
¦
¦
IPC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼«
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ FIG
ITEM ¦
NOMENCLATURE
¦ SUBJECT
FIG ITEM ¦
»¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 401
1 ¦ Antenna
¦ 34-58-02
01
05 ¦
²¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
E. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
(c) 231 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Left
(d) 232 Forward Passenger Compartment - Forward Entry Door to Sta
663.75 - Right
F. Installation Procedure
(1)
SUBTASK 110-001
Clean the airplane skin as follows:
(a) To remove the remaining sealant from the airplane skin in the
antenna area, do this task: Clean the Surface to be Painted
(AMM TASK 51-21-21-100-801 p701).
WARNING:
_______
(b)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON
YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS.
SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE
FLAMMABLE OR HARMFULL TO THE ENVIRONMENT. REFER TO
PRODUCT MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL
REQUIREMENTS FOR PROPER HANDLING PROCEDURES.
Clean the airplane skin in the antenna area with solvent,
Series 84(AMM TASK 20-30-84-910-801 p201).
EFFECTIVITY
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MAINTENANCE MANUAL
(2)
SUBTASK 840-001
If there is corrosion on the airplane skin below the antenna,
prepare the airplane skin as follows:
(a) To remove the corrosion, do this task: Removal and Control of
Corrosion for Aluminum and Aluminum Alloys
(AMM TASK 51-21-31-350-801 p701).
WARNING:
_______
(b)
(c)
(d)
(3)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON
YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS.
SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE
FLAMMABLE OR HARMFUL TO THE ENVIRONMENT REFER TO PRODUCT
MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS
FOR PROPER HANDLING PROCEDURES.
Clean the airplane skin in the area of the corrosion with
solvent, Series 84(AMM TASK 20-30-84-910-801 p201).
To apply a layer of coating,
BAC5719,TypeII,ClassA(MIL-C-5541,ClassA), on the airplane skin
in the area where the GPS antenna [1] touches the skin, do this
task: Apply Alodine 600, 1200 or 1200S Solution
(AMM TASK 51-21-41-370-802 p701).
1) Extend the area of the coating,
BAC5719,TypeII,ClassA(MIL-C-5541,ClassA), by approximately
0.25 inch (6.35 mm) around the edge of the GPS antenna [1]
area.
On top of the coating,
BAC5719,TypeII,ClassA(MIL-C-5541,ClassA), apply two layers of
primer, BMS10-79, Type III.
SUBTASK 390-001
Prepare the GPS antenna [1] as follows:
(a) To apply a very thin layer of compound, BMS3-23, on the base of
the GPS antenna, do this task: Apply the Corrosion Inhibiting
Compound (AMM TASK 51-21-91-620-802 p701).
1) Make sure you apply the compound, BMS3-23, to each side of
the O-ring groove.
NOTE:
____
(b)
(c)
(d)
Do not get the compound on the O-ring [4] or O-ring
groove.
Apply a layer of grease, BMS3-24, on the O-ring [4] and the
O-ring groove.
Install the O-ring [4] on the GPS antenna [1].
1) Make sure the O-ring [4] is not damaged and is installed
correctly in the O-ring groove.
To apply a layer of compound, BMS3-23, in the holes in the
airplane skin for the screws and the coaxial cable, do this
task: Apply the Corrosion Inhibiting Compound
(AMM TASK 51-21-91-620-802 p701).
EFFECTIVITY
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(e)
(4)
ú
To apply a layer of compound, BMS3-23, on the threads and shank
of the screws [2], do this task: Apply the Corrosion
Inhibiting Compound (AMM TASK 51-21-91-620-802 p701).
SUBTASK 420-001
Install the GPS antenna [1]:
(a) Remove the protective covers from the coaxial connector [3].
(b) Examine the coaxial connector [3] for dirt and damage.
(c) Connect the coaxial connector [3].
(d) Tighten the connector 1/8th turn past hand tight.
(e) Put the GPS antenna [1] into its position on the airplane.
(f) Install three of the screws [2] that hold the GPS antenna [1].
WARNING:
_______
(g)
(5)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON
YOUR SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS.
SOLVENTS ARE HAZARDOUS MATERIALS. SOLVENTS MAY BE
FLAMMABLE OR HARMFUL TO THE ENVIRONMENT. REFER TO PRODUCT
MATERIAL SAFETY DATA SHEETS (MSDS) AND LOCAL REQUIREMENTS
FOR PROPER HANDLING PROCEDURES.
Remove the unwanted compound, BMS3-23, from around the antenna
with solvent, Series 84(AMM TASK 20-30-84-910-801 p201).
SUBTASK 760-001
Do a check of the resistance between the GPS antenna [1] and the
airplane skin as follows:
(a) Connect an ohmmeter between the base of the antenna and the
airplane skin.
NOTE:
____
1)
(6)
You can get access to the base of the antenna through
the hole for the last screw.
Make sure the measured resistance is 0.025 ohms or less.
SUBTASK 420-002
Install the last screw [2] that holds the GPS antenna [1].
SUBTASK 420-003
WARNING:
_______
(7)
DO NOT GET SOLVENTS IN YOUR MOUTH, OR YOUR EYES, OR ON YOUR
SKIN. DO NOT BREATHE THE FUMES FROM SOLVENTS. SOLVENTS ARE
HAZARDOUS MATERIALS. SOLVENTS MAY BE FLAMMABLE OR HARMFUL TO
THE ENVIRONMENT. REFER TO PRODUCT MATERIAL SAFETY DATA SHEETS
(MSDS) AND LOCAL REQUIREMENTS FOR PROPER HANDLING PROCEDURES.
Remove the unwanted compound, BMS3-23, from around the head of each
screw [2] with solvent, Series 92(AMM TASK 20-30-92-910-801 p201).
EFFECTIVITY
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G.
Aerodynamic Fillet Seal Installation
(1)
SUBTASK 390-002
To apply a bead of sealant, BMS5-142, around the antenna where it
touches the airplane skin, do this task: Fillet Seal Application
(AMM TASK 51-31-00-390-804 p201).
NOTE:
____
(2)
Apply the sealant all around the edge of the antenna. Make
sure that no air bubbles are in the sealant. Use a
sufficient quantity of the sealant to permit you to make the
surface smooth.
SUBTASK 390-003
To make the bead into an aerodynamic fillet seal approximately 0.70
inches wide with the spatula, do this task: Fillet Seal Application
(AMM TASK 51-31-00-390-804 p201).
(3)
SUBTASK 140-001
Remove all the unwanted sealant from the area around the antenna.
(4)
SUBTASK 390-004
Fill the screw holes with sealant, BMS5-142.
NOTE:
____
H.
Make the sealant smooth in relation to the antenna surface.
Pressure Fillet Seal Installation
(1)
(2)
SUBTASK 010-001
To remove the ceiling panel beneath the GPS antenna [1], do this
task: Sculptured Ceiling Panel Removal
(AMM TASK 25-21-45-000-801 p401).
SUBTASK 390-005
To apply a bead of sealant, BMS5-142 around the edge of the circular
hole for the GPS antenna [1] where it touches the GPS antenna [1],
do this task: Fillet Seal Application
(AMM TASK 51-31-00-390-804 p201).
NOTE:
____
(a)
(b)
(3)
Apply the sealant around the inner edge of the circular hole.
Make sure that no air bubbles are in the sealant. Use a
sufficient quantity of the sealant to permit you to make the
surface smooth.
Make a smooth 45-degree bead of sealant with the spatula.
Remove the unwanted sealant from the area around the antenna.
SUBTASK 410-001
To install the ceiling panel, do this task: Sculptured Ceiling
Panel Installation (AMM TASK 25-21-45-400-801 p401).
EFFECTIVITY
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I.
GPS Antenna Installation Test
(1)
(2)
SUBTASK 860-004
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-001
Do these steps to see the GPS position on the CDU:
(a) Push the INIT REF key on the CDU.
(b) Push the line select key (LSK) that is adjacent to <INDEX.
(c) Push the LSK that is adjacent to <POS.
(d) Push the NEXT PAGE key on the CDU.
(e) Make sure the steps that follow occur:
1) The GPS L position on the CDU agrees with the known
airplane position.
NOTE:
____
2)
The GPS R position on the CDU agrees with the known
airplane position.
NOTE:
____
J.
As much as 5 minutes of time can be necessary for
the GPS positions to show on the CDU.
As much as 5 minutes of time can be necessary for
the GPS positions to show on the CDU.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-005
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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FLIGHT MANAGEMENT COMPUTER SYSTEM - MAINTENANCE PRACTICES (Fig. 201)
_________________________________________________________
1.
General
_______
A. This procedure contains these tasks:
(1) An installation of the FMC software with a portable data loader
(PDL).
(2) A crossload of the FMC software.
(3) An FMC software configuration check.
(4) An installation of the CDU software with a portable data loader
(PDL).
(5) A CDU software configuration check.
(6) An FMC diagnostic data transfer.
B. For general information for software installation times, do this task:
On-Airplane Software Installation (AMM TASK 20-15-11-400-801 p201).
C. The airplane must be on the ground before you can do these tasks.
TASK 34-61-00-470-805
ú
2.
_____________________________________________________
FMC
Software Installation with a Portable Data Loader
A. General
(1) This procedure tells you how to install software into the FMC with a
portable data loader.
(a) The FMC must contain these pieces of software:
1) operational software (OPS)
2) navigation database (NDB)
3) software options database (OPC)
4) model/engine database (MEDB).
(b) The FMC can contain these pieces of optional software:
1) performance defaults database (Perf Defaults)
2) ACARS datalink configuration database (Datalink)
(2) If you install a new operational program, the databases are deleted.
(a)
B.
ú
C.
ú
ú
You must install the NDB, OPC, and MEDB databases again after
the OPS program is installed
(b) If your airline uses any of the optional databases, Perf
Defaults or Datalink, they must also be installed again.
(3) The portable data loader (PDL) is not a Boeing supplied item.
References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-61-00-470-806 p201, FMC Software Crossload
Equipment
(1) Loader (or alternative tool)
(a) Loader - Data, Portable (recommended) (recommended)
(commercially available)
(b) 11615-02 Loader - Data, Portable, ARINC 615-3 (alternative)
Qualtair Equipment and Engineering (Vendor Code 1HEC2)
15720 Mill Creek Boulevard, Suite 200, Mill Creek, WA 98012
(c) 11615-20 Loader - Data, Portable, ARINC 615-3 with Mass Storage
Device (alternative)
Qualtair Equipment and Engineering (Vendor Code 1HEC2)
15720 Mill Creek Boulevard, Suite 200, Mill Creek, WA 98012
EFFECTIVITY
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P61 PANEL
SEE
A
FWD
FLIGHT COMPARTMENT
SEE
B
DATA
LOADER
SELECTOR
SWITCH
(EXAMPLE)
DATA
TRANSFER
UNIT
RECEPTACLE
FWD
INBD
P61 PANEL
A
B
FMC Software Installation
Figure 201 (Sheet 1)
34-61-00-990-811
EFFECTIVITY
ú SINGLE SWITCH DATA LOADER CONTROL PANEL
H69254
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P61 PANEL
SEE
C
FWD
FLIGHT COMPARTMENT
SEE
D
DATA LOAD SELECTOR
L
CAPT
UPR
C
SINGLE SYS
R
F/O
LWR
SYSTEM SELECT
NORMAL
FMC
CDU
ACARS/CMU
INOP
INOP
EICAS
EFIS
SATCOM
FCC
INOP
ACMS
DFDAU
PFIDS
INOP
TCAS
APU
EEC-R
EEC-L
ADIRU
DATA
LOADER
SELECTOR
SWITCHES
(EXAMPLE)
DATA
TRANSFER
UNIT
RECEPTACLE
FWD
INBD
P61 PANEL
D
C
FMC Software Installation
Figure 201 (Sheet 2)
EFFECTIVITY
TWO SWITCH DATA LOADER CONTROL PANEL
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(d)
(e)
(f)
(g)
ú
ú
(h)
ú
ú
(i)
(j)
(k)
D.
E.
465130-01-01 Loader - Data, Portable, ARINC 615, 3.5 Inch
Diskette (alternative)
Litton Systems, Inc. (Vendor Code 30782)
6101 Condor Drive, Moorpark CA 93021-2602
964-0400-025 Loader - Data, Portable, ARINC 615, 3.5 Inch
Diskette, 1 Megabyte Database (alternative) RTCA DO-160B ARINC
615 FMC DATA LOADER
Honeywell, Inc. (Vendor Code 97896)
15001 N.E. 36 St., P.O. Box 97001, Redmond WA 98073-9701
964-0400-024 Loader - Data, Portable, ARINC 615, 3.5 Inch
Diskette, 1 Megabyte Database (alternative) RTCA DO-160B ARINC
615 FMC DATA LOADER
Honeywell, Inc. (Vendor Code 97896)
15001 N.E. 36 St., P.O. Box 97001, Redmond WA 98073-9701
30100 Loader - Data, Portable, ARINC 615, 3.5 Inch Diskette
(alternative)
Demo Systems, Inc. (Vendor Code 0BAW0)
379 Science Dr., Moorpark CA 93021
80000-03-01010203 Loader - Data, Portable, ARINC 615/A with
Mass Storage Device (alternative)
Demo Systems, Inc. (Vendor Code 0BAW0)
379 Science Dr., Moorpark CA 93021
18000-02 Loader - Data, Portable, ARINC 615/A with Mass Storage
Device (alternative)
Qualtair Equipment and Engineering (Vendor Code 1HEC2)
15720 Mill Creek Boulevard, Suite 200, Mill Creek, WA 98012
2231560-1-B Loader - Data, Portable, ARINC 615 with Two 3.5
Inch Disk Drives (alternative)
Teledyne Controls (Vendor Code 98571)
12333 W. Olympic Blvd., Los Angeles CA 90064-1021
YV68A110 Loader - Data, Portable, ARINC 615 (alternative)
SFIM (Vendor Code F6158)
SA 13 AV Marcel Ramofo Garmier, Massy, 91301 France
Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
Procedure
(1)
(2)
SUBTASK 760-006
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 840-002
Use a portable data loader (PDL) to install software in the FMC.
EFFECTIVITY
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(3)
SUBTASK 840-003
Do these steps to prepare for software installation:
(a) AIRPLANES WITH ONE SWITCH ON THE DATA LOADER CONTROL PANEL
(P61);
Make sure the data load select switch is set to NORM.
(b) AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL
(P61);
Make sure the system select switch is set to NORMAL.
CAUTION:
_______
(c)
MAKE SURE THE CIRCUIT BREAKER FOR THE DATA LOADER IS OPEN
BEFORE YOU CONNECT OR REMOVE THE INTERFACE CABLE. IF THE
CIRCUIT BREAKER IS NOT OPEN, DAMAGE TO EQUIPMENT CAN
OCCUR.
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
CAUTION:
_______
(d)
(e)
(f)
(g)
(h)
(i)
MAKE SURE THE POWER SWITCH FOR THE PORTABLE DATA LOADER IS
SET TO OFF BEFORE YOU CONNECT OR REMOVE THE INTERFACE
CABLE. IF THE POWER SWITCH IS NOT OFF, DAMAGE TO THE
PORTABLE DATA LOADER CAN OCCUR.
Set the power switch on the PDL to the off position.
Connect the interface cable from the PDL to the DATA TRANSFER
UNIT RECEPTACLE on the P61 panel.
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
AIRPLANES WITH ONE SWITCH ON THE DATA LOADER CONTROL PANEL
(P61);
Set the data load select switch to FMC.
AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL
(P61);
Do these steps at the data loader control panel:
1) Set the upper switch to L.
2) Set the system select switch to FMC.
Set the FMC source select switch to the NORMAL position.
NOTE:
____
If the switch is in the BOTH ON L or NORMAL position,
the software will be installed into the left FMC. If
the switch is in the BOTH ON R position, the software
will be installed into the right FMC.
EFFECTIVITY
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ú
ú
ú
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(j)
Set the power switch on the portable data loader to the on
position.
NOTE:
____
(4)
For more information on how to use the data loader,
refer to the suppliers instructions for the portable
data loader.
SUBTASK 470-008
Do these steps to install the software:
NOTE:
____
If you install the operational program (OPS), do this
procedure again for the NDB, OPC, and MEDB databases after
the OPS program is installed.
ú
ú
ú
ú
ú
If your airline uses any of the optional databases, Perf
Defaults or Datalink, they must also be installed again.
(a)
Put the correct software disk into the disk drive of the data
loader.
NOTE:
____
(b)
(c)
The FMC automatically starts the data load sequence and
the CDU shows the FMCS DATA LOADER page.
Follow the prompts on the FMCS DATA LOADER page.
If the message INSERT NEXT DISK shows, do these steps:
1) Push the eject button on the data loader and remove the
disk.
2) Put the next disk into the data loader.
3) Repeat the previous two steps as necessary.
EFFECTIVITY
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(d)
When the message LOAD COMPLETE shows, push the eject button on
the data loader and remove the disk.
NOTE:
____
Because of data loader incompatibility, LOAD COMPLETE
may not be shown on the CDU after the completion of a
successful data load. If the CURRENT RECORD on line 3
of the FMCS DATA LOADER page increments to the number
shown for TOTAL RECORDS on line 5, then a successful
data load occurred.
NOTE:
____
After you eject the diskette from the data loader, the
FMC will restart. After the FMC restarts, you can
continue to install software into the FMC regardless of
the page shown on the CDU.
NOTE:
____
If a failure occurs, the CDU will show LOAD FAILURE and
DATA LOAD INOP and one of these messages:
CHECK DBL OR INTERFACE
- data loader or interface
wiring failure
DB EXCEEDS FMC MEMORY
- data on disk is too large for
FMC memory
RESET COUNT EXCEEDED
- five load attempts have failed
DB-OFP INCOMPATIBLE
- data is not compatible with
the FMC OFP
CHECK MEDIA
- a portion of data on the disk
is not able to load
INCORRECT DISK INSERTED - the wrong disk is put in after
INSERT NEXT DISK is shown
(e)
Set the power switch on the PDL to the off position after all
the software is loaded into the FMC.
(5)
SUBTASK 470-009
AIRPLANES WITH ONE SWITCH ON THE DATA LOADER CONTROL PANEL (P61);
Set the data load select switch to NORM.
(6)
SUBTASK 470-011
AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL (P61);
Set the system select switch to NORMAL.
EFFECTIVITY
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(7)
SUBTASK 840-004
Do these steps to put the airplane back to its usual condition:
CAUTION:
_______
(a)
ú
(b)
(c)
ú
ú
(8)
MAKE SURE THE CIRCUIT BREAKER FOR THE DATA LOADER IS OPEN
BEFORE YOU CONNECT OR REMOVE THE INTERFACE CABLE. IF THE
CIRCUIT BREAKER IS NOT OPEN, DAMAGE TO EQUIPMENT CAN
OCCUR.
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
Remove the loader, interface cable from the DATA TRANSFER UNIT
RECEPTACLE on the P61 panel.
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
SUBTASK 470-012
Do this task: FMC Software Crossload
(AMM TASK 34-61-00-470-806 p201).
TASK 34-61-00-470-806
ú
3.
______________________
FMC
Software Crossload
A. General
(1) This procedure tells you how to crossload software from one FMC to
the other FMC. A crossload will install the software into the
second FMC significantly faster than the data loader.
(2) After a dual FMC power-up, the OP PROGRAM CROSSLOAD page or the
DATABASE CROSSLOAD page is shown automatically on the CDU if the two
FMCs have different software installed.
(3) When the CROSSLOAD> prompt is shown on the FMCS BITE page, you can
push the LSK to manually select the OP PROGRAM CROSSLOAD page or
the DATABASE CROSSLOAD page.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-61-00-750-801 p201, FMC Software Configuration Check
C. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
D. Procedure
(1)
SUBTASK 760-007
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
EFFECTIVITY
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(2)
SUBTASK 470-013
Do these steps to crossload the software:
(a) Make sure the CDU shows one of these two pages, the OP PROGRAM
CROSSLOAD page or the DATABASE CROSSLOAD page.
(b)
NOTE:
____
The CROSSLOAD> prompt is not shown if an FMC is failed,
or only one FMC is powered, or only one FMC is installed
in a dual FMC configuration.
NOTE:
____
The OP PROGRAM CROSSLOAD page lets you install the
operational program and databases into the other FMC.
The DATABASE CROSSLOAD page lets you install only the
databases into the other FMC.
NOTE:
____
If the OP PROGRAM INVALID page shows, you must set the
FMC source select switch to the position shown on the
CDU.
Push the CDU LSK next to COPY FROM LEFT(RIGHT) to select the
FMC you want to copy from.
NOTE:
____
(c)
(d)
(e)
If you see the message SET FMC SOURCE SELECT TO
BOTH-ON-L(R), make sure the switch is in the correct
position.
Push the EXEC key on the CDU.
The CROSSLOAD IN PROGRESS message shows during the FMC
crossload.
The CROSSLOAD COMPLETE message shows for a successful
crossload.
NOTE:
____
The CROSSLOAD FAIL message is shown if the FMC crossload
fails. Possible causes for a failure are loss of
communication between the FMC's, loss of power to one
FMC, or failure of the FMC receiving the data. A second
attempt may be made to do the crossload. Select the
INDEX prompt to return to the FMC BITE page. Then
select the CROSSLOAD> prompt to repeat the crossload
operation.
NOTE:
____
A database crossload failure causes the NEXT MISMATCH
prompt to show with the CROSSLOAD COMPLETE message. The
prompt can also show for mismatches in the analog input
discretes or the performance factors. Select the NEXT
MISMATCH prompt to continue.
EFFECTIVITY
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(3)
SUBTASK 750-003
Do this task: FMC Software Configuration Check
(AMM TASK 34-61-00-750-801 p201).
TASK 34-61-00-750-801
4.
________________________________
FMC
Software Configuration Check
A. General
(1) This procedure tells you how to check the FMC software installation.
(2) You must know the correct part number for the FMC software. For the
FMC to be an approved installation, software with the correct part
number must be installed.
B. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
C. Procedure
(1)
SUBTASK 750-004
Do these steps to do a software configuration check of the FMC:
(a) Set the FMCS transfer switch to the NORMAL position.
(b) Make sure the CDU display shows the IDENT 1/2 page.
(c) Do these steps if the IDENT 1/2 page is not shown:
1) Push the INIT/REF key on both CDUs.
2) Push the LSK next to IDENT on both CDUs.
(d) Do a check of the FMC operational program and navigational
database software:
1) Make sure the correct part number for the operational
program shows below OP PROGRAM on the CDU.
2) Make sure the correct part number for the navigation
database shows below NAV DATA on the CDU.
3) Make sure the correct date range shows below ACTIVE on the
CDU.
(e) Push the NEXT PAGE button on the CDU.
(f) Make sure the CDU display shows the IDENT 2/2 page.
(g) Do a check of this FMC software:
1) Make sure the correct part number for the software options
database shows below SW OPTIONS on the CDU.
NOTE:
____
You must install the software options database for
the FMC to operate. If you did not install a
software options database the CDU will show
DEFAULT050 below SW OPTIONS.
EFFECTIVITY
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2)
Make sure the correct part number for the model/engine
database shows below MODEL/ENGINE DATA on the CDU.
NOTE:
____
You must install the model/engine database for the
FMC to operate. If INVALID shows on the CDU, the
medel/engine database was not installed. If PROGRAM
PIN NOT IN MODEL/ENGINE DATABSE shows, the
model/engine database installed does not match the
airframe/engine program pin configuration.
TASK 34-61-00-470-808
5.
ú
ú
ú
_____________________________________________________
CDU
Software Installation with a Portable Data Loader
A. General
(1) This procedure tells you how to install software into the CDU with a
portable data loader.
(2) The portable data loader is not a Boeing supplied item.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-61-00-750-802 p201, CDU Software Configuration Check
C. Equipment
(1) Loader (or alternative tool)
(a) Loader - Data, Portable (recommended) (recommended)
(commercially available)
(b) 11615-02 Loader - Data, Portable, ARINC 615-3 (alternative)
Qualtair Equipment and Engineering (Vendor Code 1HEC2)
15720 Mill Creek Boulevard, Suite 200, Mill Creek, WA 98012
(c) 11615-20 Loader - Data, Portable, ARINC 615-3 with Mass Storage
Device (alternative)
Qualtair Equipment and Engineering (Vendor Code 1HEC2)
15720 Mill Creek Boulevard, Suite 200, Mill Creek, WA 98012
(d) 465130-01-01 Loader - Data, Portable, ARINC 615, 3.5 Inch
Diskette (alternative)
Litton Systems, Inc. (Vendor Code 30782)
6101 Condor Drive, Moorpark CA 93021-2602
(e) 964-0400-025 Loader - Data, Portable, ARINC 615, 3.5 Inch
Diskette, 1 Megabyte Database (alternative) RTCA DO-160B ARINC
615 FMC DATA LOADER
Honeywell, Inc. (Vendor Code 97896)
15001 N.E. 36 St., P.O. Box 97001, Redmond WA 98073-9701
(f) 964-0400-024 Loader - Data, Portable, ARINC 615, 3.5 Inch
Diskette, 1 Megabyte Database (alternative) RTCA DO-160B ARINC
615 FMC DATA LOADER
Honeywell, Inc. (Vendor Code 97896)
15001 N.E. 36 St., P.O. Box 97001, Redmond WA 98073-9701
(g) 30100 Loader - Data, Portable, ARINC 615, 3.5 Inch Diskette
(alternative)
Demo Systems, Inc. (Vendor Code 0BAW0)
379 Science Dr., Moorpark CA 93021
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(h)
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(i)
(j)
(k)
D.
E.
80000-03-01010203 Loader - Data, Portable, ARINC 615/A with
Mass Storage Device (alternative)
Demo Systems, Inc. (Vendor Code 0BAW0)
379 Science Dr., Moorpark CA 93021
18000-02 Loader - Data, Portable, ARINC 615/A with Mass Storage
Device (alternative)
Qualtair Equipment and Engineering (Vendor Code 1HEC2)
15720 Mill Creek Boulevard, Suite 200, Mill Creek, WA 98012
2231560-1-B Loader - Data, Portable, ARINC 615 with Two 3.5
Inch Disk Drives (alternative)
Teledyne Controls (Vendor Code 98571)
12333 W. Olympic Blvd., Los Angeles CA 90064-1021
YV68A110 Loader - Data, Portable, ARINC 615 (alternative)
SFIM (Vendor Code F6158)
SA 13 AV Marcel Ramofo Garmier, Massy, 91301 France
Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
Procedure
(1)
(2)
(3)
SUBTASK 760-010
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 470-016
Use a portable data loader (PDL) to install the CDU software.
SUBTASK 840-006
Do these steps to prepare for software installation:
(a) AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL
(P61);
Make sure the system select switch is set to NORMAL.
CAUTION:
_______
(b)
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
CAUTION:
_______
(c)
(d)
ú
MAKE SURE THE CIRCUIT BREAKER FOR THE DATA LOADER IS OPEN
BEFORE YOU CONNECT OR REMOVE THE INTERFACE CABLE. IF THE
CIRCUIT BREAKER IS NOT OPEN, DAMAGE TO EQUIPMENT CAN
OCCUR.
MAKE SURE THE POWER SWITCH FOR THE PORTABLE DATA LOADER IS
SET TO OFF BEFORE YOU CONNECT OR REMOVE THE INTERFACE
CABLE. IF THE POWER SWITCH IS NOT OFF, DAMAGE TO THE
PORTABLE DATA LOADER CAN OCCUR.
Set the power switch on the PDL to the off position.
Connect the loader, interface cable from the PDL to the DATA
TRANSFER UNIT RECEPTACLE on the P61 panel.
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(e)
(f)
(g)
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL
(P61);
Do these steps at the data loader control panel:
1) Set the upper switch to CAPT or F/O.
2) Set the system select switch to CDU.
Set the power switch on the portable data loader to the on
position.
NOTE:
____
(4)
For more information on how to use the data loader,
refer to the suppliers instructions for the portable
data loader.
SUBTASK 470-017
Do these steps to install the software:
(a) Put the correct software disk into the disk drive of the data
loader.
NOTE:
____
(b)
The data load sequence starts automatically.
Follow the prompts on the DATA LOADER page.
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(c)
When the message LOAD COMPLETE shows, push the eject button on
the data loader and remove the disk.
NOTE:
____
Because of data loader incompatibility, LOAD COMPLETE
may not be shown on the CDU after the completion of a
successful data load. If the CURRENT RECORD on line 3
of the FMCS DATA LOADER page increments to the number
shown for TOTAL RECORDS on line 5, then a successful
data load occurred.
NOTE:
____
After you eject the diskette from the data loader, the
CDU DATA LOADER page will be removed from the display.
NOTE:
____
If a failure occurs, the CDU will show LOAD FAILURE and
DATA LOAD INOP and one of these messages:
CHECK DBL OR INTERFACE
EXCEEDS CDU MEMORY
RESET COUNT EXCEEDED
OPS INCOMPATIBLE
CHECK MEDIA
(d)
(e)
(5)
- data loader or interface
wiring failure
- data on disk is too large for
CDU memory
- five load attempts have failed
- data is not compatible with
the CDU OPS
- a portion of data on the disk
is not able to load
Set the power switch on the PDL to the off position after all
the software is loaded into the FMC.
AIRPLANES WITH TWO SWITCHES ON THE DATA LOADER CONTROL PANEL
(P61):
Set the system select switch to NORMAL.
SUBTASK 840-007
Do these steps to put the airplane back to its usual condition:
CAUTION:
_______
(a)
(b)
(c)
MAKE SURE THE CIRCUIT BREAKER FOR THE DATA LOADER IS OPEN
BEFORE YOU CONNECT OR REMOVE THE INTERFACE CABLE. IF THE
CIRCUIT BREAKER IS NOT OPEN, DAMAGE TO EQUIPMENT CAN
OCCUR.
Open this circuit breaker and attach a DO-NOT-CLOSE tag:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
Remove the interface cable from the DATA TRANSFER UNIT
RECEPTACLE on the P61 panel.
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-2:
a) 18A9
DATA LOADER
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(6)
SUBTASK 750-006
Do this task: CDU Software Configuration Check
(AMM TASK 34-61-00-750-802 p201).
TASK 34-61-00-750-802
ú
6.
________________________________
CDU
Software Configuration Check
A. General
(1) This procedure tells you how to check the CDU software installation.
B. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
C. Procedure
(1)
SUBTASK 750-007
Do these steps to do a software configuration check of the CDU:
(a) Set the FMC source select switch to the NORMAL position.
(b) On the MENU page, push the LSK next to FMC.
(c) Make sure the CDU shows the IDENT 1/2 page.
(d) Do this step if the IDENT 1/2 page is not shown:
1) Push the INIT/REF key on the applicable CDU.
(e) Push these LSKs in sequence on the applicable CDU:
1) MAINT
2) FMCS
3) FMC LEFT(RIGHT)
4) LCD CDU
5) CONFIG.
(f) Make sure the CDU shows the CDU CONFIGURATION page.
(g) Make sure the correct part number is shown below SOFTWARE P/N.
TASK 34-61-00-810-801
7.
____________________________
FMC
Diagnostic Data Transfer
A. General
(1) This procedure tells you how to transfer diagnostic data to a 3.5
inch diskette after an FMC failure occurs.
(2) A portable data loader (PDL) is necessary for this procedure.
B. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
C. Procedure
(1)
SUBTASK 700-014
Do a check of FMC INFLIGHT FAULTS (FIM 34-61 Task 801) to make sure
an FMC failure occurred.
NOTE:
____
You only get data for FMC failures from this procedure.
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(2)
SUBTASK 750-008
Use the FMCPREP PC software to format the disk.
(a) You must make a copy of the FMCPREP software on the root
directory of a PC hard drive.
(b) To format a disk, enter the text that follows on your PC:
>FMCPREP<DRIVE>:<Airline ID
where: <drive> is the letter "A" or "B" of the PCs 3.5
inch disk drive.
Airline ID> is the name of the airline maintenance
site (11 characters maximum).
example:
(3)
FMCPREP B: Cincinatti
SUBTASK 750-009
Make sure the MAINT BITE INDEX 1/1 page shows on the CDU.
(a) If the MAINT BITE INDEX 1/1 page is not shown, do these steps:
1) Push the INIT REF key.
2) Push the LSK adjacent to MAINT> to show the MAINT BITE
INDEX 1/1 page.
(4)
SUBTASK 750-010
Push the LSK adjacent to FMC DOWNLOAD>.
(5)
SUBTASK 750-011
Follow the directions on the FMC DATA LOADER page.
(6)
SUBTASK 750-012
Push the LSK adjacent to CONTINUE.
NOTE:
____
(7)
If you push the LSK adjacent to PRESS HERE TO EXIT>, the FMC
will do a cold start power-up.
SUBTASK 750-013
Put the formatted disk into the data loader disk drive.
NOTE:
____
If the disk is write protected, the FMC download will not
continue from this page. Remove the disk and set the writeprotected tab to the write position. Put the disk back into
the data loader disk drive.
NOTE:
____
The disk may only contain FMC download data.
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(8)
SUBTASK 750-014
The FMC automatically starts the data transfer sequence.
NOTE:
____
(9)
When the data transfer is complete, the FMC DATA LOADER page
shows DOWNLOAD COMPLETE.
SUBTASK 750-015
Remove the disk and push the LSK adjacent to PRESS HERE TO EXIT>.
NOTE:
____
D.
If you push the LSK adjacent to PRESS HERE TO EXIT>, the FMC
will do a cold start power-up.
SUBTASK 750-016
(10) After you make a copy of the data on the disk, send the disk to the
vendor.
Data Transfer Failure Indications
(1)
SUBTASK 750-017
If the disk that you put into the data loader disk drive contains an
FMC operational program or database, the FMC DATA LOADER page shows
this message:
(a)
(2)
SUBTASK 750-018
If the disk that you put into the data loader
write-protected and contains data (may be FMC
data from the currently selected FMC) that is
program or database, the FMC DATA LOADER page
(a)
(b)
(3)
WARNING: DISK UNUSABLE
OFP OR DB DISK INSERTED
Replace the disk with a correctly formatted disk.
is not
transfer
operational
message:
WARNING: DISK UNUSABLE
DISK CONTAINS DATA
Remove the disk from the data loader disk drive.
Push the LSK adjacent to PRESS HERE TO RETRY>.
SUBTASK 750-019
If the disk that you put into the data loader disk drive is not
write-protected and is not formatted by the FMCPREP software, the
FMC DATA LOADER page shows this message:
(a)
(b)
WARNING: DISK UNUSABLE
FORMAT DISK USING THE
FMCPREP PC UTILITY
Remove the disk from the data loader disk drive.
Push the LSK adjacent to PRESS HERE TO RETRY>.
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disk drive
diagnostic
not an FMC
shows this
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(4)
SUBTASK 750-020
If the diagnostic data transfer is not successful for any other
reason, the FMC DATALOADER page shows this message:
(a)
DEVICE NOT PRESENT
DISK WAS REMOVED OR
INTERFACE HAS FAILED
Push the LSK adjacent to PRESS HERE TO RETRY>.
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FLIGHT MANAGEMENT COMPUTER SYSTEM - ADJUSTMENT/TEST
___________________________________________________
1.
General
_______
A. This
(1)
(2)
(3)
procedure has these tasks:
An operational test of the flight management computer system (FMCS).
A system test of the FMCS.
An adjustment of the FMCS performance factors.
TASK 34-61-00-710-801
2.
ú
ú
____________________________________________________
Flight
Management Computer System - Operational Test
A. General
(1) The operational test does a quick check of the flight management
computer system. The test makes sure that the system is
serviceable.
(2) You can do the tests in sequence or one at a time. The Prepare For
Test steps must be done before each test or sequence of tests.
(3) The two Control Display Units (Captain's and First Officer's CDU)
are necessary for this procedure. This procedure uses two CDUs to
make sure the operational test is conducted from the two
corresponding Flight Management Computers (Left and Right FMC).
(4) The FMCS transfer switch allows the operation of the Left FMC to be
displayed on the two CDUs when the transfer switch is in the NORMAL
position. If the transfer switch is in the BOTH ON L or BOTH ON R
position, the two CDUs will display simultaneously the Left or Right
Flight Management Computer output and software database
configuration, respectively.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 34-21-00-820-801 p201, Air Data Inertial Reference System Alignment from the FMC CDU
(3) AMM TASK 34-21-00-820-802 p201, Air Data Inertial Reference System Alignment from the ISDU
(4) AMM TASK 34-61-00-470-805 p201, FMC Software Installation with a
Portable Data Loader
C. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
D. Prepare For Test
(1)
(2)
SUBTASK 860-035
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-040
Do this task: Air
the
Air
the
Data Inertial Reference System - Alignment from
FMC CDU (AMM TASK 34-21-00-820-801 p201) or
Data Inertial Reference System - Alignment from
ISDU (AMM TASK 34-21-00-820-802 p201).
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E.
Procedure
(1)
SUBTASK 710-025
Do this test of the operational program and databases:
(a) Set the FMC transfer switch to the BOTH ON L position.
(b) Push the INIT REF key on the two CDUs.
(c) Push the line select key (LSK) adjacent to INDEX on the two
CDUs.
(d) Push the LSK adjacent to IDENT on the two CDUs.
(e) Make sure the two CDUs show the IDENT 1/2 page.
(f) Make sure the part number of the OP PROGRAM is correct on the
two CDUs.
NOTE:
____
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ú
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The applicable airline department has the correct part
number for the OP PROGRAM.
1)
(g)
If the OP PROGRAM is incorrect, then do this task: FMC
Software Installation with a Portable Data Loader
(AMM TASK 34-61-00-470-805 p201).
Make sure the part number of the NAV DATA is correct on the
CDU.
NOTE:
____
ú
ú
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The applicable airline department has the correct part
number for the NAV DATA.
1)
(h)
If the NAV DATA is incorrect, then do this task: FMC
Software Installation with a Portable Data Loader
(AMM TASK 34-61-00-470-805 p201).
Make sure the date of the NAV DATA is correct on the two CDUs.
NOTE:
____
(i)
(j)
Push the NEXT PAGE button on the two CDUs.
Make sure the part number of the PERF DEFAULTS is correct on
the two CDUs.
NOTE:
____
ú
ú
ú
You can find the dates for the active navigation
database below ACTIVE. The applicable airline
department has the correct date.
1)
DEFAULT03P will be shown if no PERF DEFAULTS diskette is
installed. The applicable airline department has the
correct part number for the PERF DEFAULTS.
If the PERF DEFAULTS is incorrect, then do this task:
Software Installation with a Portable Data Loader
(AMM TASK 34-61-00-470-805 p201).
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(k)
Make sure the part number of the SW OPTIONS is correct on the
two CDUs.
NOTE:
____
ú
ú
ú
DEFAULT03O will be shown if no software options database
diskette is installed. The applicable airline
department has the correct part number for the SW
OPTIONS.
1)
(l)
If the SW OPTIONS part number is incorrect, then do this
task: FMC Software Installation with a Portable Data
Loader (AMM TASK 34-61-00-470-805 p201).
Make sure the part number of the MODEL/ENGINE DATA is correct
on the two CDUs.
NOTE:
____
ú
ú
ú
1)
(2)
The applicable airline department has the correct part
number for the MODEL/ENGINE DATA.
If the MODEL/ENGINE DATA part number is incorrect, then do
this task: FMC Software Installation with a Portable Data
Loader (AMM TASK 34-61-00-470-805 p201).
SUBTASK 710-026
Do this test of the FMCS sensor status:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Push the INIT REF key on the two CDUs.
(c) Push the line select key (LSK) adjacent to INDEX on the two
CDUs.
(d) Push the LSK adjacent to MAINT on the two CDUs.
(e) Push the LSK adjacent to FMCS on the two CDUs.
(f) Push the LSK adjacent to L FMC on the Captain's CDU.
(g) Push the LSK adjacent to R FMC on the First Officer's CDU.
(h) Push the LSK adjacent to SENSORS on the two CDUs.
(i) Make sure the two CDUs agree with the data shown below
(Table 501):
TABLE 34-61-00-993-801
~¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
LRU
¦
LEFT
¦ RIGHT
¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ VOR
¦
OK
¦
OK
¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ DME
¦
OK
¦
OK
¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ ADIRS
¦
OK
¦
OK
¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ MMR
¦
OK
¦
OK
¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ DFCS
¦
OK
¦
---¦
Table 501
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TABLE 34-61-00-993-801
~¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
LRU
¦
LEFT
¦ RIGHT
¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ FQIS
¦
OK
¦
---¦
»¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ CLOCK
¦
OK
¦
---¦
²¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
Table 501
(j)
(k)
(l)
(3)
Push the NEXT PAGE button on the two CDUs.
Make sure the status of CDS DEU LEFT and CDS DEU RIGHT is OK.
Push the INIT REF button on the two CDUs.
SUBTASK 710-027
Do this test of the FMCS fixed outputs:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Set the master dim and test switch to the BRT position.
(c) Push the INIT REF key on the two CDUs.
(d) Push the line select key (LSK) adjacent to INDEX on the two
CDUs.
(e) Push the LSK adjacent to MAINT on the two CDUs.
(f) Push the LSK adjacent to FMCS on the two CDUs.
(g) Push the LSK adjacent to L FMC on the Captain's CDU.
(h) Push the LSK adjacent to R FMC on the First Officer's CDU.
(i) Push the LSK adjacent to FIXED OUTPUTS on the two CDUs.
(j) Turn the mode selector switch on the captain's and first
officer's EFIS control panels to the MAP position.
(k) Make sure that the captain's and first officer's EFIS display
shows "FMC INTERFACE OK".
(l) Make sure that the OFST, FAIL and MSG annunciators on the two
CDUs come on.
(m) Make sure that the Thrust Mode Annunciator on Engine Format
above the N1 Display cycles through these thrust modes: CRZ,
CLB, ---, CON, TO, GA.
(n) Push the INIT REF button on the two CDUs.
TASK 34-61-00-730-801
3.
_______________________________________________
Flight
Management Computer System - System Test
A. General
(1) The system test does a complete check of the flight management
computer system. The test makes sure that the system operates
correctly.
(2) You can do the tests in sequence or one at a time. All tests must
be done to make sure system operates correctly. The Prepare For
Test steps must be done before each test or sequence of tests.
B. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
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(3)
(4)
C.
D.
AMM TASK 32-00-01-080-801 p201, Landing Gear Downlock Pins Removal
AMM TASK 32-00-01-480-801 p201, Landing Gear Downlock Pins
Installation
(5) AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
(6) AMM TASK 34-61-00-800-801 p501, FMCS Performance Factors Adjustment
Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
(2) Access Panels
(a) 192CL
ECS Access Door
(b) 192CR
ECS Access Door
Prepare For Test
(1)
SUBTASK 760-001
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 800-001
Do this task: Flight Management Computer System - Operational Test
(AMM TASK 34-61-00-710-801 p501).
Procedure
(2)
E.
(1)
SUBTASK 710-028
Do this test of the annunciators:
(a) Set the FMC transfer switch to the the BOTH ON L position.
(b) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
NOTE:
____
This circuit breaker must be closed for at least 15
seconds before you continue.
1)
(c)
(d)
(e)
ú
ú
ú
Circuit Breaker Panel, P18-2:
a) 18A6
FMCS CMPTR 1
Make sure that the FMC P/RST annunciator on the captain's and
first officer's autoflight status annunciator (ASA) comes on.
Make sure that the FAIL annunciator on the two CDUs comes on.
Set the master dim and test switch to the TEST position.
1)
(f)
ú
(g)
Make sure that the MSG,
annunciators on the two
Set the master dim and test
1) Make sure that the MSG,
annunciators on the two
2) GAX 001-068;
Make sure that the MSG,
annunciators on the two
Set the master dim and test
1) Make sure that the FAIL
bright.
DSPY, FAIL, OFST, and EXEC
CDUs come on.
switch to the DIM position.
DSPY, FAIL, OFST, and EXEC
CDUs go off.
DSPY, FAIL, OFST, and EXEC
CDUs go off.
switch to the BRT position.
annunciator on the two CDUs is
EFFECTIVITY
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(h)
(i)
(j)
Push the FMC P/RST annunciator on the captain's or first
officer's ASA.
1) Make sure that the FMC P/RST annunciator on the two ASAs
goes off.
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
1) Circuit Breaker Panel, P18-2:
a) 18A6
FMCS CMPTR 1
Do these steps to do a test of the annunciators for the right
FMC:
1) Set the FMC transfer switch to the BOTH ON R position.
2) Open this circuit breaker and attach a DO-NOT-CLOSE tag:
NOTE:
____
This circuit breaker must be closed for at least 15
seconds before you continue.
a)
3)
4)
5)
6)
7)
8)
9)
(2)
Circuit Breaker Panel, P6-1:
<1> 6D16
FMCS CMPTR 2
Make sure that the FMC P/RST annunciator on the captain's
and first officer's autoflight status annunciator (ASA)
comes on.
Make sure that the FAIL annunciator on the two CDUs comes
on.
Set the master dim and test switch to the TEST position.
a) Make sure that the MSG, DSPY, FAIL, OFST, and EXEC
annunciators on the two CDUs come on.
Set the master dim and test switch to the DIM position.
a) Make sure that the MSG, DSPY, OFST, and EXEC
annunciators on the two CDUs go off.
b) Make sure that the FAIL annunciator on the two CDUs is
dim.
Set the master dim and test switch to the BRT position.
a) Make sure that the FAIL annunciator on the two CDUs is
bright.
Push the FMC P/RST annunciator on the captain's or first
officer's ASA.
a) Make sure that the FMC P/RST annunciator on the two
ASAs goes off.
Remove the DO-NOT-CLOSE tag and close this circuit breaker:
a) Circuit Breaker Panel, P6-1:
<1> 6D16
FMCS CMPTR 2
SUBTASK 730-001
Do this test of the pack valves:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Push this sequence of keys on the two CDUs to show the FMCS
ANALOG DISCRETE 1/4 page:
1) Push the INIT REF mode key on the two CDUs.
2) Push line select key (LSK) adjacent to INDEX on the two
CDUs.
3) Push LSK 6R, adjacent to MAINT on the two CDUs.
4) Push the LSK adjacent to FMCS on the two CDUs.
EFFECTIVITY
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(c)
(d)
(e)
(f)
(g)
5) Push the LSK adjacent to L FMC on the Captain's CDU.
6) Push the LSK adjacent to R FMC on the First Officer's CDU.
7) Push LSK 4L, adjacent to DISCRETES on the two CDUs.
Make sure the L PACK and R PACK switches, located on the P5
overhead panel, are in the OFF position.
Make sure the BLEED 1 and BLEED 2 switches are in the ON
position.
Open the ECS Access Door, 192CL, to get access to the left pack
valve.
Remove connector D41500 from the left pack valve, V18.
Make sure the two CDUs agree with the data shown below
(Table 502):
TABLE 34-61-00-993-802
~¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦Test ¦ Switch ¦ Switch ¦ CDU Discrete ¦Discrete Status¦
¦Step ¦ Name
¦ Position ¦
Name
¦Left
Right¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1
¦ L PACK ¦
AUTO
¦ ECS PACK
¦ ON
OFF ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2
¦ L PACK ¦
HIGH
¦ ECS PACK
¦ ON
OFF ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 502
(h)
(i)
(j)
Open the ECS Access Door, 192CR, to get access to the right
pack valve.
Remove connector D41600 from the right pack valve, V19.
Make sure the two CDUs agree with the data shown below
(Table 503):
TABLE 34-61-00-993-803
~¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦Test ¦ Switch ¦ Switch ¦ CDU Discrete ¦Discrete Status¦
¦Step ¦ Name
¦ Position ¦
Name
¦Left
Right¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1
¦ R PACK ¦
OFF
¦ ECS PACK
¦ ON
OFF ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2
¦ R PACK ¦
AUTO
¦ ECS PACK
¦ ON
ON ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 3
¦ R PACK ¦
HIGH
¦ ECS PACK
¦ ON
ON ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 4
¦ L PACK ¦
OFF
¦ ECS PACK
¦ OFF
OFF ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 503
(k)
(l)
(m)
(n)
Connect connector D41500 to the left pack valve, V18.
Close the ECS Access Door, 192CL.
Connect connector D41600 to the right pack valve, V19.
Close the ECS Access Door, 192CR.
EFFECTIVITY
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(o)
Make sure the two CDUs agree with the data shown below
(Table 504):
TABLE 34-61-00-993-804
~¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦Test ¦ Switch ¦ Switch ¦ CDU Discrete ¦Discrete Status¦
¦Step ¦ Name
¦ Position ¦
Name
¦Left
Right¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1
¦ L PACK ¦
OFF
¦ ECS PACK H/L ¦ HI
HI ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2
¦ L PACK ¦
AUTO
¦ ECS PACK H/L ¦ LO
HI ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 3
¦ L PACK ¦
HIGH
¦ ECS PACK H/L ¦ HI
HI ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 4
¦ R PACK ¦
OFF
¦ ECS PACK H/L ¦ HI
HI ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 5
¦ R PACK ¦
AUTO
¦ ECS PACK H/L ¦ HI
LO ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 6
¦ R PACK ¦
HIGH
¦ ECS PACK H/L ¦ HI
HI ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 504
(p)
(3)
Put the L PACK and R PACK switches to the OFF position.
SUBTASK 730-002
Do this test of the isolation valve:
(a) Set the FMC transfer switch to the NORMAl position.
(b) Make sure that the FMCS ANALOG DISCRETES 1/4 page is shown on
the two CDUs.
1) If the FMCS ANALOG DISCRETES 1/4 page is not shown, push
this sequence of keys on the CDU:
a) Push the INIT REF mode key on the two CDUs.
b) Push line select key (LSK) 6L, adjacent to INDEX on the
two CDUs.
c) Push LSK 6R, adjacent to MAINT on the two CDUs.
d) Push the LSK adjacent to FMCS on the two CDUs.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
f) Push the LSK adjacent to R FMC on the First Officer's
CDU.
g) Push LSK 4L, adjacent to DISCRETES on the two CDUs.
(c) Put the L PACK and R PACK switches on the Pilot's Forward
Overhead Panel (P5) to the HIGH position.
(d) Put the ISOLATION VALVE switch on the Pilot's Forward Overhead
Panel (P5) to the CLOSE position.
1) Make sure the ISOL VALVE discrete on the two CDUs shows CL.
(e) Put the ISOLATION VALVE switch to the OPEN position.
1) Make sure the ISOL VALVE discrete on the two CDUs shows OP.
(f) Put the L PACK and R PACK switches on the Pilot's Forward
Overhead Panel (P5) to the OFF position.
EFFECTIVITY
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(4)
SUBTASK 730-003
Do this test of the anti-ice discretes:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Make sure that the FMCS ANALOG DISCRETES 1/4 page is shown on
the two CDUs.
1) If the FMCS ANALOG DISCRETES 1/4 page is not shown, push
this sequence of keys on the CDU:
a) Push the INIT REF mode key on the two CDUs.
b) Push line select key (LSK) 6L, adjacent to INDEX on the
two CDUs.
c) Push LSK 6R, adjacent to MAINT on the two CDUs.
d) Push the LSK adjacent to FMCS on the two CDUs.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
f) Push the LSK adjacent to R FMC on the First Officer's
CDU.
g) Push LSK 4L, adjacent to DISCRETES on the two CDUs.
(c) Put the L PACK and R PACK switches on the forward overhead
panel (P5) to the HIGH position.
(d) Make sure the ENG ANTI-ICE 1 and ENG ANTI-ICE 2 switches are
set to the OFF position.
(e) Make sure the WING ANTI-ICE switch is set to the OFF position.
WARNING:
_______
(f)
(g)
(h)
(i)
(j)
(k)
MAKE SURE THAT THE GROUND LOCKS ARE INSTALLED IN ALL OF
THE LANDING GEAR. WITHOUT THE GROUND LOCKS, THE LANDING
GEAR CAN RETRACT AND CAUSE INJURIES TO PERSONS AND DAMAGE
TO EQUIPMENT.
Make sure the ground locks are installed in the nose and main
landing gear (AMM TASK 32-00-01-480-801 p201).
Make sure EXISTING FAULTS shows on the PSEU control panel,
M02601.
1) If the PSEU control panel is off, push the ON/OFF button.
2) If EXISTING FAULTS? does not show, push the MENU button.
a) Push the MENU button until EXISTING FAULTS? shows.
Push the DOWN ARROW button on the PSEU control panel three
times.
1) Make sure AIR/GND OVRD? shows on the PSEU control panel.
Push the YES button on the PSEU control display panel.
1) Make sure SET SYS1 IN AIR? shows on the PSEU control panel.
Push the YES button on the PSEU control panel.
1) Make sure ARE YOU SURE? shows on the PSEU control panel.
Push the YES button on the PSEU control panel.
1) Make sure SYS1 IS IN AIR changes to SET SYS1 ON GND? on the
PSEU control panel.
NOTE:
____
2)
The flight deck PSEU fault light will stay ON while
the AIR/GND system is overridden.
Make sure the OLEO SWITCH discrete on the two CDUs changes
from GND to AIR.
EFFECTIVITY
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(l)
(m)
(n)
(o)
(p)
(q)
(r)
(s)
(t)
(u)
(5)
Put the WING ANTI-ICE switch to the ON position.
1) Make sure the WING A/ICE discrete on the two CDUs changes
to ON.
Put the WING ANTI-ICE switch to the OFF position.
1) Make sure the WING A/ICE discrete on the two CDUs changes
to OFF.
Push the MENU button on the PSEU control panel.
1) Make sure RESET OVRD? shows on the PSEU control panel.
Push the YES button on the PSEU control display panel.
1) Make sure ARE YOU SURE? shows on the PSEU control panel.
Push the YES button on the PSEU control panel.
1) Make sure OVRD RESET changes to AIR/GND OVRD? on the PSEU
control panel.
2) Make sure the OLEO SWITCH discrete on the two CDUs changes
from AIR to GND.
Put the ENG ANTI-ICE 1 switch to the ON position.
1) Make sure the COWL A/ICE LEFT discrete on the two CDUs
changes to ON.
2) Make sure the COWL A/ICE RIGHT discrete on the two CDUs
shows OFF.
Put the ENG ANTI-ICE 1 switch to the OFF position.
1) Make sure the COWL A/ICE LEFT discrete on the two CDUs
changes to OFF.
Put the ENG ANTI-ICE 2 switch to the ON position.
1) Make sure the COWL A/ICE LEFT discrete on the two CDUs
shows OFF.
2) Make sure the COWL A/ICE RIGHT discrete on the two CDUs
changes to ON.
Put the ENG ANTI-ICE 2 switch to the OFF position.
1) Make sure the COWL A/ICE RIGHT discrete on the two CDUs
changes to OFF.
Put the L PACK and R PACK switches to the OFF position.
SUBTASK 730-004
Do this test of the air/ground discrete:
(a) Set the FMC transfer switch to the NORMAL position.
(b) If the FMCS ANALOG DISCRETES 1/4 page is not shown, push this
sequence of keys on the CDU:
1) Push the INIT REF mode key on the two CDUs.
2) Push line select key (LSK) 6L, adjacent to INDEX on the two
CDUs.
3) Push LSK 6R, adjacent to MAINT on the two CDUs.
4) Push the LSK adjacent to FMCS on the two CDUs.
5) Push the LSK adjacent to L FMC on the Captain's CDU.
6) Push the LSK adjacent to R FMC on the First Officer's CDU.
7) Push LSK 4L, adjacent to DISCRETES.
EFFECTIVITY
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WARNING:
_______
(c)
(d)
(e)
(f)
(g)
(h)
MAKE SURE THAT THE GROUND LOCKS ARE INSTALLED IN ALL OF
THE LANDING GEAR. WITHOUT THE GROUND LOCKS, THE LANDING
GEAR CAN RETRACT AND CAUSE INJURIES TO PERSONS AND DAMAGE
TO EQUIPMENT.
Make sure the ground locks are installed in the nose and main
landing gear (AMM TASK 32-00-01-480-801 p201).
Make sure EXISTING FAULTS shows on the PSEU control panel,
M02601.
1) If the PSEU control panel is off, push the ON/OFF button.
2) If EXISTING FAULTS? does not show, push the MENU button.
a) Push the MENU button until EXISTING FAULTS? shows.
Push the DOWN ARROW button on the PSEU control panel three
times.
1) Make sure AIR/GND OVRD? shows on the PSEU control panel.
Push the YES button on the PSEU control display panel.
1) Make sure SET SYS1 IN AIR? shows on the PSEU control panel.
Push the YES button on the PSEU control panel.
1) Make sure ARE YOU SURE? shows on the PSEU control panel.
Push the YES button on the PSEU control panel.
1) Make sure SYS1 IS IN AIR changes to SET SYS1 ON GND? on the
PSEU control panel.
NOTE:
____
The flight deck PSEU fault light will stay ON while
the AIR/GND system is overridden.
2)
(i)
(j)
(k)
Make sure the OLEO SWITCH discrete on the two CDUs changes
from GND to AIR.
Push the MENU button on the PSEU control panel.
1) Make sure RESET OVRD? shows on the PSEU control panel.
Push the YES button on the PSEU control display panel.
1) Make sure ARE YOU SURE? shows on the PSEU control panel.
Push the YES button on the PSEU control panel.
1) Make sure OVRD RESET changes to AIR/GND OVRD? on the PSEU
control panel.
2) Make sure the OLEO SWITCH discrete on the two CDUs changes
from AIR to GND.
WARNING:
_______
(l)
(6)
MAKE SURE THAT THE GROUND LOCKS ARE REMOVED IN ALL OF THE
LANDING GEAR. WITH THE GROUND LOCKS, THE LANDING GEAR CAN
NOT RETRACT AND CAUSE INJURIES TO PERSONS AND DAMAGE TO
EQUIPMENT.
Make sure the ground locks are removed from the nose and main
landing gear (AMM TASK 32-00-01-080-801 p201).
SUBTASK 730-005
Do this test of the engine bleed discretes:
(a) Push the NEXT PAGE button on the two CDUs.
(b) Set the FMC transfer switch to the NORMAL position.
EFFECTIVITY
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(c)
(d)
(e)
Make sure that the FMCS ANALOG DISCRETES 3/4 page is shown on
the two CDUs.
1) If the FMCS ANALOG DISCRETES 3/4 page is not shown, push
this sequence of keys on the CDU:
a) Push the INIT REF mode key on the two CDUs.
b) Push line select key (LSK) 6L, adjacent to INDEX on the
two CDUs.
c) Push LSK 6R, adjacent to MAINT on the two CDUs.
d) Push the LSK adjacent to FMCS on the two CDUs.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
f) Push the LSK adjacent to R FMC on the First Officer's
CDU.
g) Push LSK 4L, adjacent to DISCRETES on the two CDUs.
2) Push the NEXT PAGE button two times on the two CDUs.
Make sure the BLEED 1 and BLEED 2 switches, located on the P5
forward overhead panel, are in the OFF position.
Make sure the two CDUs agree with the data below (Table 505):
TABLE 34-61-00-993-805
~¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦Test ¦ Switch ¦ Switch ¦ CDU Discrete ¦Discrete Status¦
¦Step ¦ Name
¦ Position ¦
Name
¦NO. 1
NO. 2¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 1
¦ BLEED 1 ¦
ON
¦ ENGINE BLEED ¦ ON
OFF ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 2
¦ BLEED 1 ¦
OFF
¦ ENGINE BLEED ¦ OFF
OFF ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 3
¦ BLEED 2 ¦
ON
¦ ENGINE BLEED ¦ OFF
ON ¦
»¼¼¼¼¼î¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ 4
¦ BLEED 2 ¦
OFF
¦ ENGINE BLEED ¦ OFF
OFF ¦
²¼¼¼¼¼…¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 505
(7)
SUBTASK 730-006
Do this test of the program pins:
(a) Push the PREV PAGE button two times on the two CDUs.
(b) Set the FMC transfer switch to the NORMAL position.
(c) Make sure that the FMCS ANALOG DISCRETES 2/4 page is shown on
the two CDUs.
1) If the FMCS ANALOG DISCRETES 2/4 page is not shown, push
this sequence of keys on the CDU:
a) Push the INIT REF mode key on the two CDUs.
b) Push line select key (LSK) 6L, adjacent to INDEX on the
two CDUs.
c) Push LSK 6R, adjacent to MAINT on the two CDUs.
d) Push the LSK adjacent to FMCS on the two CDUs.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
f) Push the LSK adjacent to R FMC on the First Officer's
CDU.
EFFECTIVITY
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(d)
g) Push LSK 4L, adjacent to DISCRETES on the two CDUs.
h) Push the NEXT PAGE button on the two CDUs.
Make sure the two CDUs agree with the data below (Table 506):
ú
TABLE 34-61-00-993-806
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
Discrete
¦ State
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ JAA FLT RULES
¦ DISABLE ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ KILOGRAM OPTION ¦ DISABLE ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ MAG/TRUE
¦ MAG
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ SRCE/DEST IDENT ¦*[1] *[2] ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ ASPIRATED TAT
¦ DISABLE ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ °C/°F DEFAULT
¦ °C
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ PERF CODE
¦ 1
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
ú
ú
ú
ú
ú
ú
ú
ú
ú
*[1]
*[2]
The SOURCE/DEST IDENT
shows LEFT on the left
CDU.
The SOURCE/DEST IDENT
shows RIGHT on the right
CDU.
Table 506
(e)
(f)
(g)
(h)
ú
ú
(i)
Push the NEXT PAGE button on the two CDUs.
Set the FMC transfer switch to the NORMAL position.
1) Make sure the FMCS ANALOG DISCRETES 3/4 page is shown on
the two CDUs.
Make sure the MODEL/ENG discrete on the two CDUs shows VALID.
Push the NEXT PAGE button on the two CDUs.
1) Make sure the FMCS ANALOG DISCRETES 4/4 page is shown on
the two CDUs.
Make sure the two CDUs agree with the data below (Table 507):
EFFECTIVITY
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TABLE 34-61-00-993-914
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
Discrete
¦ State
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ VOR INHIBIT
¦ DISABLE ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ FLIGHT NUMBER
¦ ENABLE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ TOGA RW POS UPD ¦ *[3] *[4]¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ TAKEOFF PROFILE ¦ DISABLE ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ TAKEOFF SPEEDS
¦ ENABLE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ NAVAID SUPPRESS ¦ ENABLE
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ SEL CRS INHIBIT ¦ *[1] *[2]¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ ACARS INSTALLED ¦ OFF
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
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*[1]
*[2]
*[3]
*[4]
ASA 001-006 PRE-SB
34-1583; The SEL CRS
INHIBIT shows DISABLE.
ASA 001-006 POST-SB
34-1583, 007-999; The SEL
CRS INHIBIT shows ENABLE.
ASA 001, 002; The TOGA RW
POS UPD shows DISABLE.
ASA 003-999; The TOGA RW
POS UPD shows ENABLE.
Table 507
ú
ú
(j)
(8)
Press LSK 6L, adjacent to INDEX.
SUBTASK 730-007
Do this test of the model/engine configuration:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Make sure that the FMCS BITE page is shown on the two CDUs.
1) If the FMCS BITE page is not shown, push this sequence of
keys on the CDU:
a) Push the INIT REF mode key.
b) Push line select key (LSK) 6L, adjacent to INDEX.
c) Push LSK 6R, adjacent to MAINT.
d) Push the LSK adjacent to FMCS.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
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f)
(c)
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(d)
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Push the LSK adjacent to R FMC on the First Officer's
CDU.
Push LSK 1R, adjacent to MODEL/ENG.
1) Make sure the FMCS MODEL/ENG CFG 1/1 page is shown on the
two CDUs.
ASA 001-100;
Make sure the two CDUs agree with the data below
(Table 508):
TABLE 34-61-00-993-941
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦ Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
MODEL
¦ 737-700 ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
BRAKE OPT
¦ CAT_F
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
ENGINE
¦ CFM56-7B ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
ENGINE OPT ¦ SAC
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
ENG RATINGS ¦
¦
¦
FULL
¦ 24K
¦
¦
TO-1
¦ 22K
¦
¦
TO-2
¦ 20K
¦
¦
BUMP
¦ NONE
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
Table 508
(e)
ASA 101-999;
Make sure the two CDUs agree with the data below
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(Table 509):
TABLE 34-61-00-993-942
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦ Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
MODEL
¦ 737-900 ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
BRAKE OPT
¦ CAT_G
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
ENGINE
¦ CFM56-7B ¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
ENGINE OPT ¦ SAC
¦
Table 509
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TABLE 34-61-00-993-942
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦ Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦
ENG RATINGS ¦
¦
¦
FULL
¦ 26K
¦
¦
TO-1
¦ 24K
¦
¦
TO-2
¦ 22K
¦
¦
BUMP
¦ NONE
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
Table 509
(f)
(9)
ú
ú
Push LSK 6L, adjacent to INDEX.
SUBTASK 730-008
Do this test of the software options:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Make sure that the FMCS BITE page is shown on the two CDUs.
1) If the FMCS BITE page is not shown, push this sequence of
keys on the CDU:
a) Push the INIT REF mode key.
b) Push line select key (LSK) 6L, adjacent to INDEX.
c) Push LSK 6R, adjacent to MAINT.
d) Push the LSK adjacent to FMCS.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
f) Push the LSK adjacent to R FMC on the First Officer's
CDU.
(c) Push LSK 2R, adjacent to SW OPTIONS.
1) Make sure the FMCS SW OPTIONS page is shown on the two
CDUs.
(d) ASA 001, 002 PRE-SB 34-1576;
Make sure the two CDUs agree with the data below (Table 510):
TABLE 34-61-00-993-856
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦
Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ NDB SIZE
¦
2056K WORDS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ OPTION CODE
¦
0000000B83C0
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ DEFAULT RNP
¦
¦
¦
OCEANIC
¦
12.0
¦
¦
ENROUTE
¦
2.00
¦
¦
TERMINAL
¦
1.00
¦
¦
APPROACH
¦
0.50
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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Table 510
EFFECTIVITY
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(e)
ASA 003-010 PRE-SB 34-1576;
Make sure the two CDUs agree with the data below
(Table 511):
TABLE 34-61-00-993-857
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦
Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ NDB SIZE
¦
2056K WORDS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ OPTION CODE
¦
0000000B83C4
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ DEFAULT RNP
¦
¦
¦
OCEANIC
¦
12.0
¦
¦
ENROUTE
¦
2.00
¦
¦
TERMINAL
¦
1.00
¦
¦
APPROACH
¦
0.50
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
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Table 511
(f)
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ASA 001, 002 POST-SB 34-1576;
Make sure the two CDUs agree with the data below
(Table 512):
TABLE 34-61-00-993-966
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦
Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ NDB SIZE
¦
2056K WORDS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ OPTION CODE
¦
0000004B83C0
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ DEFAULT RNP
¦
¦
¦
OCEANIC
¦
12.0
¦
¦
ENROUTE
¦
2.00
¦
¦
TERMINAL
¦
1.00
¦
¦
APPROACH
¦
0.50
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 512
(g)
ASA 003-010 POST-SB 34-1576;
ASA 011-999;
Make sure the two CDUs agree with the data below
EFFECTIVITY
(Table 513):
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TABLE 34-61-00-993-949
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦
Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ NDB SIZE
¦
2056K WORDS
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ OPTION CODE
¦
0000004B83C4
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼«
¦ DEFAULT RNP
¦
¦
¦
OCEANIC
¦
12.0
¦
¦
ENROUTE
¦
2.00
¦
¦
TERMINAL
¦
1.00
¦
¦
APPROACH
¦
0.50
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¹
Table 513
(h)
ú
Push LSK 6L, adjacent to INDEX.
SUBTASK 730-009
(10) Do this test of the performance factors:
(a) Set the FMC transfer switch to the NORMAL position.
(b) Make sure that the FMCS BITE page is shown on the two CDUs.
1) If the FMCS BITE page is not shown, push this sequence of
keys on the CDU:
a) Push the INIT REF mode key.
b) Push line select key (LSK) 6L, adjacent to INDEX.
c) Push LSK 6R, adjacent to MAINT.
d) Push the LSK adjacent to FMCS.
e) Push the LSK adjacent to L FMC on the Captain's CDU.
f) Push the LSK adjacent to R FMC on the First Officer's
CDU.
(c) Push LSK 3R, adjacent to PERF FACTR.
1) Make sure the FMCS PERF FACTORS 1/1 page is shown on the
two CDUs.
(d) Make sure the two CDUs agree with the data below (Table 514):
NOTE:
____
The values shown in the table below are factory
defaults. If a different value is desired, do this
task: FMCS Performance Factors - Adjustment
(AMM TASK 34-61-00-800-801 p501).
[1] FMC WITH OPERATIONAL PROGRAM SOFTWARE BEFORE U10.2;
The
value is 100.
[2] FMC WITH OPERATIONAL PROGRAM SOFTWARE U10.2 AND ON;
The value is 300.
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TABLE 34-61-00-993-810
~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼
¦
Parameter
¦ Value
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ DRAG FACTOR
¦ +0.0
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ F-F FACTOR
¦ +0.0
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ MNVR MARGIN
¦ 1.30
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ MIN CRZ TIME ¦ 1
¦
»¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼î¼¼¼¼¼¼¼¼¼¼«
¦ MIN R/C
¦
¦
¦
CLB
¦ 300
¦
¦
CRZ
¦ [1] [2] ¦
¦
ENG OUT
¦ 100
¦
²¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼…¼¼¼¼¼¼¼¼¼¼¹
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Table 514
F.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 760-002
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
TASK 34-61-00-800-801
4.
_____________________________________
FMCS
Performance Factors - Adjustment
A. General
(1) This task gives steps to adjust these performance factors:
(a) Drag factor
(b) F-F factor
(c) Maneuver margin
(d) Minimum cruise time
(e) Minimum rate of climb (climb) margin
(f) Minimum rate of climb (cruise) margin
(g) Minimum rate of climb (engine out) margin.
(2) You can do these adjustments in sequence or one at a time. The
Prepare For Test steps must be done before each adjustment or
sequence of adjustments.
NOTE:
____
(3)
If a factor has had its entry capability disabled by a
loadable performance defaults database, you cannot change its
value using this procedure. You must load a new performance
defaults database with the new factor value.
The Control Display Unit (CDU) is necessary for this procedure.
can use CDU No. 1 or CDU No. 2 to do this procedure.
EFFECTIVITY
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B.
C.
D.
References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
Prepare For Test
(1)
(2)
SUBTASK 860-043
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 860-044
Set the FMC transfer switch to the NORMAL position.
SUBTASK 940-001
Push this sequence of keys on the CDU:
(a) Push the INIT REF key.
(b) Push line select key (LSK) 6L, adjacent to INDEX.
(c) Push LSK 6R, adjacent to MAINT.
(d) Push the LSK adjacent to FMCS.
(e) Push the LSK adjacent to L FMC on the Captain's CDU.
(f) Push the LSK adjacent to R FMC on the First Officer's CDU.
(g) Push LSK 3R, adjacent to PERF FACTR.
(h) Push this sequence of keys on the CDU: "A", "R", "M".
(i) Push LSK 6R, adjacent to ---.
Procedure
(3)
E.
(1)
SUBTASK 820-001
Do this adjustment of the drag factor:
(a) Push the sequence of keys for the new DRAG FACTOR value.
NOTE:
____
(b)
(2)
Values between -9.9 and +9.9 (%) are permitted.
default value is +0.0 (%).
Push LSK 2L.
1) Make sure the new value of DRAG FACTOR is shown adjacent to
LSK 2L.
SUBTASK 820-002
Do this adjustment of the f-f factor:
(a) Push the sequence of keys for the new F-F FACTOR value.
NOTE:
____
(b)
Values between -9.9 and +9.9 (%) are permitted.
default value is +0.0 (%).
The
Push LSK 3L.
1) Make sure the new value of F-F FACTOR is shown adjacent to
LSK 3L.
EFFECTIVITY
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The
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(3)
SUBTASK 820-003
Do this adjustment of the maneuver margin:
(a) Push the sequence of keys for the new MNVR MARGIN value.
NOTE:
____
(b)
(4)
SUBTASK 820-004
Do this adjustment of the minimum cruise time:
(a) Push the sequence of keys for the new MIN CRZ TIME value.
(b)
Values between 1 and 20 (minutes) are permitted.
default value is 1.
SUBTASK 820-005
Do this adjustment of the minimum rate of climb (climb) margin:
(a) Push the sequence of keys for the new MIN R/C CLB value.
(b)
Values between 0 and 999 are permitted.
value is 300.
The default
Push LSK 3R.
1) Make sure the new value of MIN R/C CLB is shown adjacent to
LSK 3R.
SUBTASK 820-006
Do this adjustment of the minimum rate of climb (cruise) margin:
(a) Push the sequence of keys for the new MIN R/C CRZ value.
NOTE:
____
(b)
Values between 0 and 999 are permitted.
value is 100.
The default
Push LSK 4R.
1) Make sure the new value of MIN R/C CRZ is shown adjacent to
LSK 4R.
EFFECTIVITY
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The
Push LSK 5L.
1) Make sure the new value of MIN CRZ TIME is shown adjacent
to LSK 5L.
NOTE:
____
(6)
The default
Push LSK 4L.
1) Make sure the new value of MNVR MARGIN is shown adjacent to
LSK 4L.
NOTE:
____
(5)
Values between 1.20 and 1.60 are permitted.
value is 1.30.
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(7)
SUBTASK 820-007
Do this adjustment of the minimum rate of climb (engine out) margin:
(a) Push the sequence of keys for the new MIN R/C ENG OUT value.
NOTE:
____
Values between 0 and 500 are permitted.
value is 100.
The default
(b)
F.
Push LSK 5R.
1) Make sure the new value of MIN R/C ENG OUT is shown
adjacent to LSK 5R.
Put the Airplane Back to Its Usual Condition
(1)
SUBTASK 860-039
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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FMCS CONTROL DISPLAY UNIT - MAINTENANCE PRACTICES
_________________________________________________
1.
General
_______
A. This procedure contains four tasks. The first task is the cleaning of
the FMCS Control Display Units (CDU) cooling vent and surfaces. The
second task is the cleaning of the CDU display. The third task is the
removal of the CDU keyboard. The fourth task is the installation of the
CDU keyboard.
B. You can find the CDU(s) in the flight compartment on the forward
electronic panel, P9. You can replace the keyboard when one of the keys
does not operate.
TASK 34-61-01-100-801
2.
___________________________________________
FMCS
CDU Cooling Vent and Surfaces Cleaning
A. References
(1) AMM TASK 20-30-31-910-801 p201, Cleaners and Polishes
(2) AMM TASK 34-61-01-000-802 p401, FMCS Control Display Unit (CDU)
Removal
(3) AMM TASK 34-61-01-400-802 p401, FMCS Control Display Unit (CDU)
Installation
B. Equipment
(1) Vacuum - Source, 24 inch Hg minimum
(commercially available)
C. Consumable Materials
(1) B00673 Detergent, Liquid - Liqui-Nox
(2) G00034 Cloth, Process Cleaning Absorbent Wiper (cheesecloth, gauze)
- BMS15-5
D. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
E. Control Display Unit (CDU) Cooling Vent and Surfaces Cleaning
(1)
(2)
SUBTASK 020-001
Do this task: FMCS Control Display Unit (CDU) Removal
(AMM TASK 34-61-01-000-802 p401).
SUBTASK 140-001
Clean the cooling vent:
(a) Use a vacuum to remove blockage from the air inlet and outlet
holes on the CDU.
(b) Clean the grills with a paper towel or soft cloth moist with
detergent, Liqui-Nox, and water
(AMM TASK 20-30-31-910-801 p201).
(c) Dry the grills with a cloth, BMS15-5.
(d) Use a vacuum to remove blockage from the air outlet hole below
the Pilot's Forward Electronic Panel (P9).
EFFECTIVITY
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(3)
(4)
SUBTASK 160-001
Do these steps to clean the CDU surfaces:
(a) Remove dust and dirt with a vacuum.
(b) Clean the surfaces with a paper towel or soft cloth moist with
detergent, Liqui-Nox, and water
(AMM TASK 20-30-31-910-801 p201).
(c) Remove the remaining detergent with a cloth, BMS15-5, moist
with water.
SUBTASK 420-001
Do this task: FMCS Control Display Unit (CDU) Installation
(AMM TASK 34-61-01-400-802 p401).
TASK 34-61-01-100-802
3.
_________________________
FMCS
CDU Display Cleaning
A. Consumable Materials
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(1)
(2)
Cleaner, Optical Cleaning, Calotherm Solution - Supaspray
Cloth, Calocoat Hi-Tech Lenscloth - Supacloth
(3)
B.
C.
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ú
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B50012
B50013
G02457 Cleaner, Wet/Dry Anti-static Sachet - ALGLAS Visial ALG/CR
215
Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
Procedure
(1)
SUBTASK 100-002
Clean the display surface of the FMCS control display unit (CDU)
with the cleaner, Supaspray, and the cloth, Supacloth, or the
cleaner, ALGLAS Visial ALG/CR 215:
(a) Apply 2 or 3 sprays of the Supaspray to the Supacloth, or open
the wet sachet.
(b) Use the moist cloth or the wet sachet to clean the display
surface in a straight line from top to bottom.
(c) Gradually move from one side of the display surface to the
other side while you clean from top to bottom.
(d) When the display surface is clean, use a clean, dry area of the
cloth or the dry sachet in a straight line from top to bottom
to dry the display surface.
EFFECTIVITY
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TASK 34-61-01-000-801
4.
_________________________
FMCS
CDU Keyboard Removal (Fig. 201)
A. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
B. Procedure
(1)
(2)
SUBTASK 860-046
Open these circuit breakers
(a) Circuit Breaker Panel,
1) 6D15
FMCS CDU 2
2) 6D16
FMCS CMPTR
(b) Circuit Breaker Panel,
1) 18A6
FMCS CMPTR
2) 18A7
FMCS CDU 1
and attach DO-NOT-CLOSE tags:
P6-1:
2
P18-2:
1
SUBTASK 000-001
Do these steps to remove the Control Display Unit (CDU) keyboard:
(a) Loosen the six captive screws that hold the keyboard to the
front chassis.
(b) Carefully move the keyboard away from the front chassis to get
access to the cable assembly.
(c) Remove the display gasket.
(d) Unlock and disconnect cable assembly connector W1P1 from
connector DS1J1.
TASK 34-61-01-400-801
5.
______________________________
FMCS
CDU Keyboard Installation (Fig. 201)
A. References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(2) AMM TASK 34-61-01-710-801 p301, CDU Lamp Test
B. Access
(1) Location Zones
(a) 210 Subzone - Control Compartment - Body Station 178.00 to
Body Station 259.50
C. Procedure
(1)
SUBTASK 400-001
Do these steps to install the Control Display Unit (CDU) keyboard:
NOTE:
____
(a)
(b)
(c)
Make sure you install a keyboard with the same part number as
the one you removed.
Make sure the display gasket is correctly aligned.
Connect and lock cable assembly connector W1P1 to connector
DS1J1.
Position keyboard on the front chassis.
EFFECTIVITY
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CAPTIVE
SCREW
(6 LOCATIONS)
LIGHTED
SWITCH
PANEL
CONTROL DISPLAY UNIT
Control Display Unit - Lighted Switch Panel Replacement
Figure 201
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EFFECTIVITY
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(d)
Tighten the six captive screws that hold the keyboard to the
front chassis.
SUBTASK 860-047
Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D15
FMCS CDU 2
2) 6D16
FMCS CMPTR 2
(b) Circuit Breaker Panel, P18-2:
1) 18A6
FMCS CMPTR 1
2) 18A7
FMCS CDU 1
CDU Keyboard Test
(2)
D.
(1)
SUBTASK 860-005
Prepare for the CDU keyboard test:
(a) Make sure that the BAT switch on the Pilot's Forward Overhead
Panel is in the ON position.
(b) Set the STANDBY POWER switch on the Pilot's Forward Overhead
Panel to the AUTO position.
SUBTASK 740-001
Do these steps to do the CDU keyboard test:
(a) Push the INIT REF key on the CDU.
(b) Push the line select key (LSK) adjacent to INDEX.
(c) Push the LSK adjacent to MAINT.
(d) Push the LSK adjacent to FMCS.
(e) Push the LSK adjacent to FMC LEFT (RIGHT).
(f) Push the LSK adjacent to CDU TEST or LCD CDU.
(g) Push the LSK adjacent to KEY TEST.
(h) Make sure that the CDU display shows the legends of all the
keys the same as on the CDU keyboard.
1) Push each key on the CDU.
2) Make sure that the same key legend on the CDU display comes
on.
(i) Push the LSK adjacent to INDEX to go back to the CDU MAINT BITE
INDEX page.
(j) Push the LSK adjacent to EXIT to go back to the FMCS BITE page.
(k) Do this task: CDU Lamp Test (AMM TASK 34-61-01-710-801 p301).
Put the Airplane Back to Its Usual Condition
(2)
E.
(1)
SUBTASK 860-027
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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FMCS CONTROL DISPLAY UNIT - SERVICING
_____________________________________
1.
General
_______
A. This procedure contains the task for the CDU lamp test.
B. You can find the FMCS control display units (CDUs) in the flight
compartment on the forward electronic panel, P9. The CDU has four
annunciators (DSPY or CALL, FAIL, MSG, and OFST) and a lighted EXEC key.
Two of the annunciators are on the left of the CDU (DSPY or CALL/FAIL),
and two are on the right of the CDU(MSG/OFST).
C. The CDU has lamps for the annunciators and the EXEC key that are not line
replaceable. This requires replacement of the keyboard or the CDU.
TASK 34-61-01-710-801
2.
_____________
CDU
Lamp Test
A. References
(1) AMM TASK 24-22-00-860-811 p201, Supply Electrical Power
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Procedure
(1)
SUBTASK 860-008
Do this task: Supply Electrical Power
(AMM TASK 24-22-00-860-811 p201).
SUBTASK 710-002
Do the CDU Lamp Test:
(a) Hold the LIGHTS switch in the TEST position. You can find the
LIGHTS switch on the pilots' center instrument panel (P2).
(b) Make sure that the DSPY (or CALL), FAIL, MSG, OFST, and EXEC
lights on the two CDUs come on.
(c) Set the LIGHTS switch to the BRT or DIM position if it is
necessary.
Put the Airplane Back to Its Usual Condition
(2)
D.
(1)
SUBTASK 860-018
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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FMCS CONTROL DISPLAY UNIT - REMOVAL/INSTALLATION
________________________________________________
1.
General
_______
A. This procedure contains two tasks:
(1) The first task is for the removal of the flight management computer
system (FMCS) control display unit (CDU)
(2) The second task is for the installation of the FMCS CDU.
B. You can find the FMCS CDU No. 1 on the left corner of the Pilots' Forward
Electronics Panel, P9. You can find the CDU No. 2 on the right corner of
the Pilots' Forward Electronics Panel, P9.
C. Six quick-release fasteners hold the CDU in position. An electrical
connector attaches the electrical cable to a connector (J1) on the rear
panel of the CDU.
TASK 34-61-01-000-802
2.
_______________________________________
FMCS
Control Display Unit (CDU) Removal (Fig. 401)
A. References
(1) AMM TASK 32-00-01-480-801 p201, Landing Gear Downlock Pins
Installation
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Prepare for the Removal
(1)
SUBTASK 860-006
Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) Circuit Breaker Panel, P6-1:
1) 6D15
FMCS CDU 2
(b) Circuit Breaker Panel, P18-2:
1) 18A7
FMCS CDU 1
SUBTASK 480-001
WARNING:
_______
(2)
MAKE SURE THAT THE GROUND LOCKS ARE INSTALLED IN ALL OF THE
LANDING GEAR. IF THE GROUND LOCKS ARE NOT INSTALLED, THE
LANDING GEAR CAN RETRACT AND CAUSE INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
Make sure the ground locks are installed in the nose and main
landing gear (AMM TASK 32-00-01-480-801 p201).
EFFECTIVITY
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SEE
A
[1] CDU
[2] QUARTER-TURN
FASTENER
(6 LOCATIONS)
FLIGHT COMPARTMENT
[3] ELECTRICAL
CONNECTOR
FWD
FORWARD ELECTRONIC PANEL
A
CDU Installation
Figure 401
F47844
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D.
Procedure
SUBTASK 860-007
CAUTION:
_______
DO NOT TOUCH THE CONDUCTOR PINS OR OTHER CONDUCTORS ON THE CDU.
IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN
CAUSE DAMAGE TO THE CDU.
CAUTION:
_______
DO NOT LET THE CDU PUSH AGAINST OR FALL ON OTHER COMPONENTS ON
THE AISLE STAND. THIS CAN OCCUR WHEN YOU DISCONNECT THE
CONNECTOR FROM THE REAR OF THE CDU. DAMAGE TO EQUIPMENT CAN
OCCUR.
(1)
Do these steps to remove the CDU [1]:
(a) Loosen the six quick-release fasteners [2] on the front of the
CDU [1].
(b) Pull the CDU [1] out of the panel until you can get access to
the electrical connector [3].
(c) Disconnect the electrical connector [3].
(d) Remove the CDU [1] from the panel.
(e) Put a protective cover on the electrical connector [3].
TASK 34-61-01-400-802
3.
____________________________________________
FMCS
Control Display Unit (CDU) Installation (Fig. 401)
A. References
(1) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
(2) AMM TASK 34-61-00-470-808 p201, CDU Software Installation with a
Portable Data Loader
B. Access
(1) Location Zones
(a) 211 Flight Compartment - Left
(b) 212 Flight Compartment - Right
C. Procedure
SUBTASK 420-003
CAUTION:
_______
(1)
DO NOT TOUCH THE CONDUCTOR PINS OR OTHER CONDUCTORS ON THE CDU.
IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN
CAUSE DAMAGE TO THE CDU.
Do these steps to install the CDU [1]:
(a) Remove the protective cover from the electrical connector [3].
(b) Examine the electrical connector [3] for bent or broken pins,
dirt, and damage.
(c) Connect the electrical connector [3] to the CDU [1].
(d) Carefully lower the CDU [1] into the panel.
(e) Tighten the six quick-release fasteners [2].
EFFECTIVITY
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(2)
SUBTASK 860-020
Close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D15
FMCS CDU 2
(b) Circuit Breaker Panel, P18-2:
1) 18A7
FMCS CDU 1
SUBTASK 470-001
AIRPLANES WITH LCD CDUs (P/N S242A600-XXX) AND A TWO SWITCH DATA
LOADER CONTROL PANEL;
do this task: CDU Software Installation with a Portable Data Loader
(AMM TASK 34-61-00-470-808 p201)
Installation Test
(3)
D.
SUBTASK 710-001
Do an installation test
(a) Make sure that the
(b) Set the MASTER DIM
(c) Make sure that the
the CDU are on.
Put the Airplane Back to Its
(1)
E.
(1)
of the control display unit (CDU):
CDU display shows the IDENT 1/2 page.
and TEST switch to the TEST position.
DSPY, FAIL, MSG, OFST, and EXEC lights on
Usual Condition
SUBTASK 860-022
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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FMCS COMPUTER - REMOVAL/INSTALLATION
____________________________________
1.
General
_______
A. This procedure contains these tasks:
(1) A removal of the FMCS computer
(2) An installation of the FMCS computer.
B. You can find the FMCS computer in the main equipment center on the E5-2
shelf.
TASK 34-61-02-000-801
2.
_____________________
FMCS
Computer Removal (Fig. 401)
A. References
(1) AMM TASK 20-10-07-000-801 p201, E/E Box Removal
B. Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
C. FMCS Computer Removal
(1)
(2)
SUBTASK 860-034
Open these circuit breakers
(a) Circuit Breaker Panel,
1) 6D15
FMCS CDU 2
2) 6D16
FMCS CMPTR
(b) Circuit Breaker Panel,
1) 18A6
FMCS CMPTR
2) 18A7
FMCS CDU 1
and attach DO-NOT-CLOSE tags:
P6-1:
2
P18-2:
1
SUBTASK 010-001
Open the Electronic Equipment Access Door, 117A, to get access to
the main equipment center.
SUBTASK 860-004
CAUTION:
_______
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE FMCS
COMPUTER. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE FMCS COMPUTER.
To remove the FMCS computer [1], do this task:
(AMM TASK 20-10-07-000-801 p201).
E/E Box Removal
TASK 34-61-02-400-801
3.
__________________________
FMCS
Computer Installation (Fig. 401)
A. References
(1) AMM TASK 20-10-07-400-801 p201, E/E Box Installation
(2) AMM TASK 24-22-00-860-812 p201, Remove Electrical Power
EFFECTIVITY
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ELECTRONIC
EQUIPMENT
RACK, E5
SEE
A
ELECTRONIC EQUIPMENT
ACCESS DOOR, 117A
[1] LEFT FMCS COMPUTER
(E5-2)
[1] RIGHT FMCS COMPUTER
(E5-2)
ELECTRONIC
EQUIPMENT ACCESS
DOOR, 117A
FWD
ELECTRONIC EQUIPMENT RACK, E5
A
FMCS - Computer Installation
Figure 401
H61498
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EFFECTIVITY
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(3)
B.
C.
AMM TASK 34-61-00-710-801 p501, Flight Management Computer System Operational Test
Access
(1) Location Zones
(a) 118 Electrical and Electronics Compartment - Right
(2) Access Panels
(a) 117A
Electronic Equipment Access Door
Installation Procedure
(1)
SUBTASK 860-035
Make sure that these circuit breakers are open:
(a) Circuit Breaker Panel, P6-1:
1) 6D15
FMCS CDU 2
2) 6D16
FMCS CMPTR 2
(b) Circuit Breaker Panel, P18-2:
1) 18A6
FMCS CMPTR 1
2) 18A7
FMCS CDU 1
SUBTASK 860-008
CAUTION:
_______
(2)
(3)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE FMCS
COMPUTER. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE FMCS COMPUTER.
To install the FMCS computer [1], do this task:
Installation (AMM TASK 20-10-07-400-801 p201).
E/E Box
SUBTASK 010-002
Close the Electronic Equipment Access Door, 117A.
SUBTASK 860-036
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) Circuit Breaker Panel, P6-1:
1) 6D15
FMCS CDU 2
2) 6D16
FMCS CMPTR 2
(b) Circuit Breaker Panel, P18-2:
1) 18A6
FMCS CMPTR 1
2) 18A7
FMCS CDU 1
Installation Test
(4)
D.
SUBTASK 710-003
Do this task: Flight Management Computer System - Operational Test
(AMM TASK 34-61-00-710-801 p501).
Put the Airplane Back to Its Usual Condition
(1)
E.
(1)
SUBTASK 860-024
Do this task: Remove Electrical Power
(AMM TASK 24-22-00-860-812 p201).
EFFECTIVITY
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