AD/B747/65 - Fuselage - Main Frame - Tail Section 48
1AD/B747/65 - Fuselage - Main Frame - Tail Section 48
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Image unavailable in extracted text Boeing 747 Series Aeroplanes
AD/B747/65 Fuselage - Main Frame - Tail Section 48 7/88
Applicability: 747 aeroplanes line positions 001 to 200.
Requirement: Action in accordance with Boeing Alert Service Bulletin 747-53A2280.
Note: FAA AD 87-24-02 Amdt 39-5768 refers.
Compliance: Unless already accomplished, as detailed in the Requirement Document.
Background: Two operators have reported cracks on three different splice fittings on three different aeroplanes. Analysis of one of the fittings determined that the fracture initiated due to multiple origin fatigue cracking. Three operators also reported broken tension bolts which failed due to stress corrosion.