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
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of Australia, aim to ensure the safety of civil aviation within the country. Part 39 of these regulations includes Airworthiness Directives, which are designed to address safety issues that may affect the continued airworthiness of specific aircraft types. One such directive is AD/F100/24, issued by the Civil Aviation Safety Authority (CASA), which pertains to Fokker F100 (F28 Mk 100) series aeroplanes. This directive was introduced to address issues of bleed air leakage at corrujoint seals of the 7th stage low-pressure and 12th stage high-pressure check-valves located in the stubwings, which had led to damage of the fuselage skin and stubwing structure on some aircraft. The policy objective of AD/F100/24 is to ensure the structural integrity of the affected Fokker F100 aircraft through mandatory inspections and repairs, as outlined in the directive.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, encompasses the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, which applies to the aviation industry, particularly to Fokker F100 (F28 Mk 100) series aeroplanes. This legislation mandates certain maintenance and inspection requirements for F.28 Mk.0070 and Mk.0100 aircraft, irrespective of their serial numbers, to ensure their continued airworthiness. The directive mandates compliance with Fokker Service Bulletins F100-36-027, F100-36-026 Rev 1, and F100-53-084, which detail specific engine leak tests, inspections, and seal replacements. It further requires inspecting the fuselage skin in the left and right hand stub wings for heat damage, with subsequent repairs as per Fokker SB F100-53-084. The directive's applicability is national, as it is an instrument of the Commonwealth of Australia and pertains to civil aviation across the country. Compliance with these directives is critical, with specific timelines provided for various actions, including within 3000 flight hours or 12 months after the directive's issue, and further inspections and repairs at intervals specified in the referenced service bulletins. The effective date of this Airworthiness Directive is 22 April 1999.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, which outlines the Civil Aviation Safety Authority Schedule of Airworthiness Directives, includes a directive concerning Fokker F100 (F28 Mk 100) series aeroplanes. This directive, identified as AD/F100/24, pertains to the stubwing upper skin of these aircraft. The directive applies to F.28 Mk.0070 and Mk.0100 aircraft of all serial numbers (105.003). The main requirement of this directive is to determine whether Fokker Service Bulletin (SB) F100-36-027 has been complied with. If it has, no further action under this directive is necessary. However, if it has not been complied with, specific tests, inspections, and repairs must be carried out as detailed in Fokker SB F100-36-026 Rev 1 and SB F100-53-084. Additionally, the directive mandates inspections for heat damage on the fuselage skin in the left and right hand stub wings, following Fokker SB F100-53-087, and requires detailed inspections and repairs if certain conditions such as primer discoloration, missing rivets or missing rivet heads are observed.
Operators of Fokker F100 (F28 Mk 100) series aeroplanes are required to comply with the specified inspections, tests, and repairs outlined in the directive. Compliance with Fokker SB F100-36-027 within 3000 flight hours or 12 months after the issue of this directive, whichever occurs first, is mandatory. Further inspections and tests must be conducted at the intervals specified in Fokker SB F100-36-026 Rev 1 and SB F100-53-084. Detailed inspections for heat damage in the stubwings must be performed within 6 months or 6000 cycles from the effective date of the directive or 6000 cycles from the initial inspection as per Fokker SB F100-53-084, whichever occurs last, and thereafter at every 6000 cycles or next scheduled inspection, whichever occurs first. All repair actions must adhere to the time limits stipulated in Fokker SB F100-53-084.
Failure to comply with the requirements of this Airworthiness Directive may result in serious safety risks, as evidenced by reports of bleed air leakage problems causing damage to the fuselage skin and stubwing structure. This damage has necessitated internal and external repairs to ensure the structural integrity of the aircraft. While the specific offences, penalties, or consequences for non-compliance are not detailed in the text, it is implied that non-compliance could lead to significant safety hazards, potentially resulting in severe penalties or sanctions under aviation safety laws. These could include fines, suspension of airworthiness certificates, or other regulatory actions to ensure compliance and maintain safety standards.