**ON A/C ALL
Subtask 05-51-17-941-052
B. Not Applicable Subtask 05-51-17-010-050
C. Get Access
(1) Open the main gear doors and install the safety devices (Ref. TASK 32-12-00-010-001).
Subtask 05-51-17-481-050
D. Safety Precautions
(1) Make sure that the safety devices are installed on the main landing gear (Ref. TASK 32-00-00-481-001).
Subtask 05-51-17-866-050
E. Extension of the Flaps and the Slats
(1) Fully extend the flaps (Ref. TASK 27-50-00-866-008).
(2) Fully extend the slats (Ref. TASK 27-80-00-866-004). Subtask 05-51-17-860-050
F. Aircraft Maintenance Configuration
(1)
Make sure that the hydraulic systems are depressurized (Ref. TASK 29-00-00-864-001).
(2)
Make sure that the electrical circuits are de-energized (Ref. TASK 24-41-00-862-002).
(3)
Put the warning notices in the cockpit to tell persons not to operate the aircraft systems.
(4)
Put the access platform in position.
1EFF : ALL 1 05-51-17Page 604 1 1 Aug 01/05R 1 1 1CES 1
4. Procedure
_________
Subtask 05-51-17-210-051
A. General
NOTE : All these inspections are visual unless the text gives other
____ instructions. You can do non-destructive tests (refer to the Aircraft Non-destructive Test Manual - NTM) if:
-You think it is necessary;
-Your airworthiness authority tells you to. If, because of the inspection, you must disconnect or remove components, pipes, ducts, cables, electrical connectors or mechanical linkages, you must then do a functional test of the related system(s).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 221-221, 224-224, 228-228, R 401-499,
Subtask 05-51-17-210-063
B. Inspection of the Fuselage
-------------------------------------------------------------------------------|ITEM|INSP| INSPECTION TASKS |PHASE|PHASE|PHASE|INSP|REF.| | |CODE| | 1 | 2 | 3 |SIGN|FIG.| |----|----|---------------------------------------|-----|-----|-----|----|----| |1. | | Belly fairing | | | | | | | | | | | | | | | | A.| | Examine externally all the belly | X | | | | | | | | fairing panels, specially the leading-| | | | | | | | | edge roof fairing and upper and lower | | | | | | | | | wing fairings, for : | | | | | | | | | - correct attachment, delamination, | | | | | | | | | damaged paintwork, pulled or torn | | | | | | | | | fasteners. | | | | | | | | | If you find damage : | | | | | | | | | (1) Remove the damaged panel and | | X | | | | | | | internally examine the belly | | | | | | | | | fairing structure. | | | | | | | | | (2) Examine all the components, pipes,| | X | | | | | | | ducts, electrical looms and their | | | | | | | | | mounts, for distortion, cracks, | | | | | | | | | breaks and fluid leakage. | | | | | | | | | | | | | | | |2. | | Fuselage (FR36 to FR46) | | | | | |
R 1EFF : ALL 1 05-51-17Page 605 1 1 Aug 01/05 1 1 1CES 1
-------------------------------------------------------------------------------
|ITEM|INSP| INSPECTION TASKS |PHASE|PHASE|PHASE|INSP|REF.| | |CODE| | 1 | 2 | 3 |SIGN|FIG.| |----|----|---------------------------------------|-----|-----|-----|----|----| | | | | | | | | | | A.| | At the joint of the wing spar box with| X | | | | | | | | the wing, rib1, examine : | | | | | | | | | - the rear-spar web splice, | | | | | | | | | - the fuselage skin panels, | | | | | | | | | - the panel splices. | | | | | | | | | For distortion, cracks, pulled or torn| | | | | | | | | fasteners, damaged paintwork. | | | | | | | | | | | | | | | | B.| | At and around FR46, examine the lower | X | | | | | | | | skin panel of the fuselage between the| | | | | | | | | R stringer 41RH and the L stringer | | | | | | | | | 41LH for : | | | | | | | | | - distortion, cracks, pulled or torn | | | | | | | | | fasteners, damaged paintwork. | | | | | | | | | | | | | | | |3. | | Fuselage (FR29 to FR70) | | | | | | | | | If you find damage (refer to 1 or 2 | | | | | | | | | above): | | | | | | | | | | | | | | | | A.| | From FR26 to FR35 : | | X | | | | | | | - externally examine the skin panels, | | | | | | | | | the splicing and the riveting for | | | | | | R | | | distorsion, cracks, pulling, tears | | | | | | | | | and damaged paintwork. | | | | | | | | | If you find damage : | | | | | | | | | (1) Remove the forward cargo-| | | X | | | | | | compartment panels and examine the| | | | | | | | | floor support structure, frames, | | | | | | | | | skin panels, splicing, rivets and | | | | | | | | | stringers for: | | | | | | | | | - distortion, cracks, pulled and | | | | | | | | | torn fasteners, damaged | | | | | | | | | paintwork. | | | | | | | | | | | | | | | | B.| | At FR35, examine the top of the joint | | | | | | | | | between the R stringer 6 and the L | | | | | | | | | stringer 6 for: | | | | | | | | | - distortion, cracks, pulled or torn | | | | | | | | | fasteners, damaged paintwork. | | | | | | | | | | | | | | | | C.| | From FR35 to FR47: | | | | | | | | | - in the main landing-gear well and on| | X | | | |
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM 時間限制/維護檢查 2(51)
