COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Fokker F28 Series Aeroplanes 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 CAR 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. AD/F28/87 Stub Wing Fuselage Structure 11/2001 Applicability: All Model F.28 Mk. 1000 through 4000 series aircraft. Requirement: Visually inspect the internal fuselage structure in the Stub Wing areas in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin F.28/53-151, dated 4 June 2001. Whenever damage is found, repair or replace the affected parts within the limits set in Part 2 of the Accomplishment Instructions of the Requirement document. Repair or replacement of damaged parts does not terminate the required repetitive inspections. Note 1: Netherlands CAA AD 2001-093 refers. Note 2: Fokker Services Manual Change Notification – Maintenance Documentation (MCNM) F.28-025 dated 4 June 2001, also pertains to this subject. Compliance: Within 6,000 flight cycles after 20 August 2001; thereafter at intervals not to exceed 6,000 flight cycles. This Airworthiness Directive becomes effective on 1 November 2001. Background: The CAA received several reports of heat damage found on the fuselage skin panels in the stub wing (engine pylon) areas. In both cases, the damage was discovered visually, evidenced by discolouration of the (yellow) primer paint on the inside of the fuselage, and is thought to have been caused by leakage of hot air from one of the bleed air ducts inside the stub wing. Undetected damage could lead to deterioration of the structural integrity of the Stub Wing assembly. David Alan Villiers Delegate of the Civil Aviation Safety Authority 21 September 2001 The above AD is notified in the Commonwealth of Australia Gazette on 10 October 2001.