COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F100 (F28 Mk 100) Series Aeroplanes
AD/F100/24 Stubwing Upper Skin 4/99
Applicability: F.28 Mk.0070 and Mk.0100 aircraft, all serial numbers.
Requirement: 1. Determine if Fokker Service Bulletin (SB) F100-36-027 has been complied with.
If so, no further action for this Airworthiness Directive is required.
2. Carry out the engine leak tests, inspections and seal replacements listed in Fokker SB F100-36-026 Rev 1 and SB F100-53-084 as applicable. Repair as required in accordance with Part 6A or 6B as applicable of SB F100-53-084.
3. Inspect the fuselage skin in the Left and Right Hand stub wings for heat damage in accordance with Fokker SB F100-53-087.
If primer discoloration, missing rivets or missing rivet heads are found, then carry out the detailed inspections listed in Parts 4A, 4B and 4C as applicable of the Accomplishment instructions of Fokker SB F100-53-084, before further flight.
Repair as required in accordance with Fokker SB F100-53-084.
Note 1: Compliance with Fokker SB F100-36-027 constitutes terminating action for this Directive.
Note 2: RLD BLA 1995-076/3(A) refers.
Compliance: 1. Within 3000 flight hours or 12 months after issue of this directive, whichever occurs first.
2. Within 3000 flight hours or 12 months after issue of this directive, whichever occurs first, and then at the intervals required by Fokker SB F100-36-026 Rev 1 and Fokker SB F100-53-084.
Repair action is to be carried out in accordance with the time limits listed in Fokker SB F100-53-084.
3. Within 6 months or 6000 cycles of the effective date of this Directive or 6000 cycles from the initial one off inspection required by Fokker SB F100-53-084, whichever occurs last. Thereafter at every 6000 cycles or next scheduled inspection, whichever occurs first.
Repair action is to be carried out in accordance with the time limits listed in Fokker SB F100-53-084.
This Airworthiness Directive becomes effective on 22 April 1999.
Background: Several operators have reported bleed air leakage problems at corrujoint seals of the 7th stage low-pressure and 12th stage high-pressure check-valves, which are located in the stubwings (engine pylons). On a few aircraft, leakage of hot air from these joints has resulted in damage to the fuselage skin and stubwing structure. Internal and external repairs were required to ensure structural integrity.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES