AD/B717/8 - Upper Centre Fuselage Longerons (Cth)

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

AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Boeing 717 Series Aeroplanes

AD/B717/8 Upper Centre Fuselage Longerons 8/2003

Applicability: Model 717-200 aircraft, manufacturer's fuselage numbers 5001 through 5056.

Requirement: Modify the longeron to frame installation of the upper centre fuselage between stations Y=655.000 and Y=813.000, at longerons L-5L to L-5R (includes fabrication of the angles and installation of support angles and doublers) in accordance with Boeing Service Bulletin 717-53-0001, dated 20 March 2001.

Note: FAA AD 2003-10-08 Amdt 39-13153 refers.

Compliance: Before the accumulation of 30,000 total flight cycles or within 10 years after 7 August 2003, whichever occurs first.

This Airworthiness Directive becomes effective on 7 August 2003.

Background: The FAA requires certain actions to prevent fatigue cracking of the longerons of the upper centre fuselage. Such cracking could result in reduced structural integrity of the fuselage.

David Punshon Delegate of the Civil Aviation Safety Authority 26 June 2003