(2.00 to 26.00 lbf.ft)
B.
Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 31-32-00-860-001 Procedure to Get Access to the SYSTEM REPORT/TEST
Menu Page 49-00-00-710-008 Operational Test of the APU (APS 3200) 49-00-00-790-005 Air Leak Test with closed APU Doors 52-41-00-010-001 Open the APU Doors for Access 52-41-00-410-001 Close the APU Doors after Access 49-51-53-991-001-A Fig. 401 49-51-53-991-002 Fig. 402
3. Job Set-up
__________
Subtask 49-51-53-860-051
A. Aircraft Maintenance Configuration
(1)
Make sure that the aircraft electrical circuits are energized (Ref. TASK 24-41-00-861-002).
(2)
On the panel 25VU, make sure that the APU MASTER SW pushbutton switch is off.
(3)
Make sure that there is 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).
(5)
Make sure that the access platform is in position below the APU compartment.
(6)
Make sure that the APU access doors are open (Ref. TASK 52-41-00-010-001).
(7)
Make sure that the LIGHT control switch 11LJ is set to the on position.
Subtask 49-51-53-865-051
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41
4. Procedure
_________
(Ref. Fig. 401/TASK 49-51-53-991-001-A, 402/TASK 49-51-53-991-002) Subtask 49-51-53-420-050-A
A. Installation CAUTION : YOU MUST USE TWO WRENCHES AND HOLD THE COMPONENT WHEN YOU
_______ REMOVE/INSTALL THE PIPE COUPLINGS AND/OR UNIONS. THIS PREVENTS DAMAGE TO THE COMPONENT.
CAUTION : -YOU MUST NOT INCREASE THE TIGHTENING TORQUE MORE THAN THE
_______ MAXIMUM VALUE. -APPLY ALL TIGHTENING TORQUES WITH A TORQUE WRENCH OR A CALIBRATED SCREWDRIVER.
CAUTION : DO NOT TORQUE THE V-CLAMP(S) TO MORE THAN THE SPECIFIED VALUE.
_______
YOU CAN DAMAGE THE FLANGE SURFACES IF YOU DO.
NOTE : With incorporation of VSB 4500001-49-89 the LCDT Sensor (P29) has
____
been replaced by filler plug P/N 4504985.
(1)
Position the V-band clamps (9), (15) and (18) on the ducts.
(2)
Position the valve and attach the V-band clamp (15).
(3)
Position the valve and attach the V-band clamp (9).
(4)
Align the valve with duct (17) and attach the V-band clamp (18).
(5)
Attach the tube (22) to the valve union.
(6)
Attach the tube (21) to the valve elbow.
(7)
Attach the tubes (6) and (23) to the valve T-piece.
(8)
Attach the tube (12) to the valve union.
(9)
Attach the tube (13) to the valve union.
(10)
Attach the tube (20) to the valve union.
(11)
Attach the tube (14) to the valve union.
(12)
TORQUE the V-band clamps (15) and (9) to between 0.4 and 0.5 m.daN
(35.39 and 44.24 lbf.in).
(13)
TORQUE the V-band clamp (18) to between 0.4 and 0.5 m.daN (35.39 and
44.24 lbf.in).
(14)
TORQUE the tube nut (21) to between 1.02 and 1.13 m.daN (90.26 and
99.99 lbf.in).
(15)
TORQUE the tube nut (22) to between 1.5 and 1.7 m.daN (11.06 and
12.53 lbf.ft).
(16)
TORQUE the tube nut (6) on the T-piece to between 1.5 and 1.7 m.daN
(11.06 and 12.53 lbf.ft).
(17)
TORQUE the tube nut (23) on the T-piece to between 1.0 and 1.13 m.daN
(88.49 and 99.99 lbf.in). 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320飞机维护手册 AMM 机载辅助动力 AIRBORNE AUXILIARY POWER5(41)
