R EFF : 001-049, 101-105, 107-107, 151-199, 49-16-43Page 405 201-210, Config-2 Aug 01/05
CES D. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
20-28-00-912-004 Electrical Bonding of Components With Conductive Bolts and Screws and Bonding Straps in the Fuselage and in the Wings (this does not include the tanks)-
24-42-00-861-001 Energize the Ground Service Network from the External Power 24-42-00-862-001 De-energize the Ground Service Network Supplied from the External Power 29-00-00-864-001 Put the Related Hydraulic System in the Depressurized Configuration before Maintenance Action 49-16-00-710-003 Operational Test of the Air Intake Flap and Diverter
(131-9(A)) 49-16-43-991-005 Fig. 401 49-16-43-991-006 Fig. 402
3. Job Set-up
__________
Subtask 49-16-43-860-053
A. Aircraft Maintenance Configuration
(1)
Energize the ground service network
(Ref. TASK 24-42-00-861-001).
(2)
On the panel 25VU, make sure that the APU MASTER SW p/bsw is OFF.
(3)
Make sure that hydraulic systems are depressurized
(Ref. TASK 29-00-00-864-001).
(4)
Make sure that the access platform is below the APU compartment.
(5)
Set the LIGHT SW 11LJ to the ON position.
(6)
Make sure that the air intake flap actuator is in the retracted position.
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CES Subtask 49-16-43-865-057
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------121VU APU/APU/CTL 2KD L42 121VU APU/ECB/SPLY 1KD L41
4. Procedure
_________ Subtask 49-16-43-210-054
A. Preparation for Installation
(Ref. Fig. 401/TASK 49-16-43-991-005)
(1)
Make an inspection of the air intake flap (13) for damage, dents and cracks and make an inspection of the seal lip (14) for damage. Replace the flap if necessary.
(2)
Make an inspection of the seal profile (20) for damage. If necessary, replace the seal profile.
Subtask 49-16-43-560-052
B. Preparation of a Replacement Component
(Ref. Fig. 401/TASK 49-16-43-991-005)
(1)
Remove the seal profile (15).
(a)
Remove the screws (18), the washers (17) and the bracket (16).
(b)
Remove the seal profile (15) from the flap (8).
(2)
Installation of the the new seal profile (15).
(a)
Put the new seal profile (15) and the bracket (16) in position.
(b)
Apply SPECIAL MATERIALS (Material No. 05-002) to the screws (18) and the washers (17).
(c)
Install the seal profile (15).
(d)
Install the screws (18) and the washers (17). Do not fully tighten the screws at this time.
R EFF : 001-049, 101-105, 107-107, 151-199, 49-16-43Page 407 201-210, Config-2 Aug 01/05 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 POWER3(16)
