1. Reason for the Job
__________________
Self Explanatory
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------
No specific blanking plugs
No specific circuit breaker(s) safety clip(s)
No specific access platform 2.5 m (8 ft. 2 in.)
B. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 49-23-16-000-001 Removal of the Load Compressor-Discharge
Temperature-Sensor (8012KM) (GTCP 36-300)
52-41-00-010-001 Open the APU Doors for Access
49-51-42-991-001 Fig. 401
3. Job Set-up
__________ Subtask 49-51-42-860-053
A. Aircraft Maintenance Configuration
(1)
Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002).
(2)
On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is off.
(3)
Put a warning notice in the cockpit to tell persons not to start the APU.
(4)
Make sure that hydraulic systems are depressurized
(Ref. TASK 29-00-00-864-001).
Subtask 49-51-42-865-050
B. Open, safety and tag this(these) circuit breaker(s):
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41
Subtask 49-51-42-010-050
C. Get Access
(1)
Put the access platformin position below the APU access doors 315AL and 316AR.
(2)
Open the access doors 315AL, 316AR (Ref. TASK 52-41-00-010-001).
(3)
Set the LIGHT control switch to the ON position.
4. Procedure
_________
(Ref. Fig. 401/TASK 49-51-42-991-001) Subtask 49-51-42-020-050
A. Removal of the Surge/Bleed Duct (8049KM)
(1)
Disconnect the electrical connector (1) from the differential pressure transducer.
(2)
Disconnect the electrical connector (2) from the total pressure sensor.
(3)
Put blanking caps on the disconnected electrical connectors.
(4)
Remove and discard the lockwire and remove the bolt (3), the washer
(4) and the retainer (5) which attach the air pipe (6) to the sensor ring.
(5)
Disconnect the air pipe (6) from the sensor ring.
(6)
Remove and discard the O-ring (7) from the air pipe (6).
(7)
Put blanking plugs on the disconnected line ends.
(8)
Remove and discard the lockwire and remove the bolts (8) and the bolts (9) which attach the sensor module assembly (10) to the surge/bleed duct (8049KM) (15).
(9)
Remove the sensor module assembly (10) from the surge/bleed duct (8049KM) (15).
NOTE : Remove the sensor module assembly carefully to prevent damage
____
to the total pressure sensor pipe.
(10)
Remove and discard the gasket (11).
(11)
Put the blanking plugs on the disconnected line ends.
(12)
Remove the load compressor-discharge temperature-sensor (12) for access (Ref. TASK 49-23-16-000-001)
(13)
Remove the V-clamp (13) which attaches the bleed-load control valve
(14) to the surge/bleed duct (8049KM) (15).
(14)
Remove the V-clamp (16) which attaches the surge control valve (17) to the surge/bleed duct (8049KM) (15).
(15)
Put blanking plugs on the disconnected line ends.
(16)
Remove the bracket (18) which holds the fuel drain pipes and cables to the surge/bleed duct (8049KM) (15).
(17)
Hold the surge/bleed duct (8049KM) (15). Remove and discard the lockwire and remove the bolts (19).
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM 機載輔助動力 AIRBORNE AUXILIARY POWER5(22)
