AD/A320/65 Amdt 2 - Fuselage Reinforcement Section 18
1AD/A320/65 Amdt 2 - Fuselage Reinforcement Section 18
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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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Airbus Industrie A319, A320 and A321 Series Aeroplanes
AD/A320/65
Amdt 2
Fuselage Reinforcement Section 18 2/98
Applicability: All models without Airbus Industrie modification 22764 embodied, or Service Bulletins A320-53-1110 and A320-53-1131 incorporated.
Requirement: Reinforce the fuselage at section 18 in accordance with the instructions of: Airbus Industrie Service Bulletin A320-53-1110 for frames 68 and 69; and, Airbus Industrie Service Bulletin A320-53-1131 for frames 65, 66, and 67.
Note: DGAC AD 97-315-109 (B) refers.
Compliance: Before 13 January 2002.
The compliance of the previous issue of this Directive remains unchanged. This amendment becomes effective on 29 January 1998.
Background: This directive was issued to increase the marginal strength of the rear fuselage to enable it to cope with an undetected tail scrape.
Amendment 1 reflected the amended compliance of the related DGAC AD.
Amendment 2 is issued in response to a new DGAC AD which introduces additional frames for reinforcement.
Amendment 1 of this airworthiness directive became effective on 2 January 1997. The original issue of this airworthiness directive became effective on 28 March 1996.