AD/B747/142 - Fuselage Skin Lap Joints
1AD/B747/142 - Fuselage Skin Lap Joints
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
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Boeing 747 Series Aeroplanes
AD/B747/142 Fuselage Skin Lap Joints 5/95
Applicability: All B747 aircraft listed in Boeing Service Bulletin 747-53-2367 revision 1 dated 27 January 1994.
Requirement: 1. Inspect, using the specified surface high frequency eddy current method, the upper fastener row of the lap joints nominated in Boeing Service Bulletin 747-53-2367 revision 1 dated 27 January 1994.
- If cracks are found, remove the upper row fasteners for one frame bay either side of the crack, and inspect the open holes using the high frequency eddy current inspection method specified in Boeing Service Bulletin 747-53-2367 revision 1, dated 27 January 1994.
Note: FAA AD 94-12-04 refers.
Compliance: 1. Initial inspection, before 22000 full pressure cycles or within 1000 full pressure cycles after 27 April 1995, whichever occurs last.
Re-inspect at intervals not exceeding 3000 full pressure cycles.
- Before further flight.
Note: A full pressure cycle shall be that where the cabin differential pressure equals or exceeds 2.0 psi.
Background: Boeing has completed extended pressure tests on two B747 fuselage test articles.
These tests have identified areas of the fuselage lap joints where fatigue cracking is likely to occur. The inspection and repair of these areas is necessary to ensure continued safe operation of the B747.