AD/A320/65 Amdt 2 - Fuselage Reinforcement Section 18

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998) , PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES 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.