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/F100/19
Amdt 1
Horizontal Stabiliser Structure 6/99
Applicability: All F.28 Mk.0100 specified in Fokker Service Bulletin (SB) F100-55-021 Revision 2, except those aircraft which have already fully complied with Fokker SB F100-55-021 Revision 1.
Requirement: 1. Unless modified per requirement 2a before 1000 flight cycles since new, inspect the horizontal stabiliser main hinge fitting Hi-lok bolt holes in accordance with Part 5 of the Accomplishment Instructions of Fokker SB F100-55-021 Revision 2.
2. Modify the horizontal stabiliser main hinge fittings and replace or modify, as applicable, the connecting angles at Rib 215 in accordance with either:
- Part 3 or Part 4 of the accomplishment instructions of Fokker SB F100-55-021 Revision 2, for aircraft with less than 1000 flight cycles since new at time of modification, or;
b. Part 6 or Part 7 of the accomplishment instructions of Fokker SB F100-55-021 Revision 2, for aircraft with 1000 flight cycles, or more, since new, or;
c. Instructions issued by Fokker Aircraft Services for inspection, modification or repair where cracks indications during requirement 1 inspection are beyond the limits listed in Fokker SB F100-55-021 Revision 2.
3. Modify Rib 215 of the horizontal stabilizer either;
- In accordance with Part 8 of the accomplishment instructions of Fokker SB F100-55-021 Revision 2, or;
b. Instructions issued by Fokker Aircraft Services for inspection, modification or repair where cracks indications during requirement 1 inspection are beyond the limits listed in Fokker SB F100-55-021 Revision 2.
Note: RLD BLA 93-137/2(A) refers.
Compliance: 1. Inspect before accumulating 15,000 flight cycles since new or before 17 August 1999, whichever occurs later.
2. Unless already accomplished, before further flight following the inspection in accordance with Requirement 1.
3. Before further flight following the inspection in accordance with Requirement 1 or in conjunction with requirement 2 compliance.
This Amendment becomes effective on 17 June 1999.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Background: During fatigue tests on the F.28 Mk.0100 for the stabilisers, cracks were found in the flanges of the LH and RH main hinge fittings. If not corrected, these cracks may lead to a deteriorated fatigue life of the horizontal stabiliser main hinge fitting structure. This AD requires an inspection and modification to detect cracks at an early stage and to improve fatigue life.
Amendment 1 is issued to update the service bulletin reference, as experience has resulted in revisions to the Accomplishment Instructions. Aircraft that have been modified in accordance with previous revision do not require further work.
The initial issue of this Airworthiness Directive became effective on 22 April 1999.
Overview
The Civil Aviation Regulations 1998, amended by the Commonwealth of Australia, address safety concerns related to the Fokker F100 (F28 Mk 100) series aeroplanes through the Civil Aviation Safety Authority's Schedule of Airworthiness Directives. Specifically, AD/F100/19 Amendment 1 targets the horizontal stabiliser structure to prevent potential deterioration in the fatigue life of the main hinge fitting structure, identified through fatigue tests that revealed cracks in the flanges of the left and right main hinge fittings. The directive mandates inspections and modifications to ensure early detection and improvement of the structural integrity. Compliance with this amendment is essential to maintain the airworthiness of affected Fokker F100 aircraft, with inspections required before accumulating 15,000 flight cycles since new or before 17 August 1999, whichever occurs later.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, mandates Airworthiness Directives for ensuring the safety of aircraft within the Commonwealth of Australia. This particular directive, AD/F100/19 Amendment 1, applies to all Fokker F100 (F28 Mk 100) series aeroplanes specified in Fokker Service Bulletin (SB) F100-55-021 Revision 2, excluding those that have already fully complied with Fokker SB F100-55-021 Revision 1. The directive is concerned with the structural integrity of the horizontal stabiliser main hinge fittings and Rib 215, requiring inspections and necessary modifications to prevent potential fatigue-related cracks. The directive is enforced by the Civil Aviation Safety Authority, which has the jurisdiction to oversee compliance with these airworthiness standards. Compliance is mandatory, with inspections required before the aircraft accumulates 15,000 flight cycles since new or before 17 August 1999, whichever comes later. Modifications must be completed before further flights following the inspection. This directive became effective on 17 June 1999, updating a previous service bulletin to reflect revisions in the Accomplishment Instructions.
Key Provisions
The Airworthiness Directive (AD) pertains to the Fokker F100 (F28 Mk 100) series aeroplanes and is specifically targeted at addressing structural integrity issues identified in the horizontal stabiliser of these aircraft. The directive applies to all F.28 Mk.0100 specified in Fokker Service Bulletin (SB) F100-55-021 Revision 2, with an exception for those aircraft that have already complied with Fokker SB F100-55-021 Revision 1 (section 1). The main requirements of this AD are threefold: first, an inspection of the horizontal stabiliser main hinge fitting Hi-lok bolt holes (section 1); second, a modification of the horizontal stabiliser main hinge fittings and the connecting angles at Rib 215 (section 2); and third, a modification of Rib 215 of the horizontal stabiliser (section 3). These requirements are detailed in Fokker SB F100-55-021 Revision 2 and must be carried out in accordance with specific parts of the accomplishment instructions provided within the bulletin, depending on the number of flight cycles since the aircraft was new.
Operators of the affected Fokker F100 series aeroplanes are obligated to comply with the AD by conducting the specified inspections and modifications within stipulated timeframes. Specifically, the inspection must be performed before the aircraft accumulates 15,000 flight cycles since new or before 17 August 1999, whichever is later (section 1). Additionally, unless the modifications have already been completed, they must be carried out before further flight following the inspection (section 2). The modifications of Rib 215 must also be completed before further flight following the inspection or in conjunction with the compliance of requirement 2 (section 3). Failure to adhere to these compliance timelines could result in the aircraft being deemed unairworthy.
Breach of the requirements set out in this AD could result in serious consequences, including potential safety risks. The AD stipulates that the aircraft must not be flown until the required inspections and modifications have been performed. Any deviation from the outlined procedures and timelines could lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Although the specific penalties for non-compliance are not detailed within the AD, general penalties under the Civil Aviation Act 1988 and Civil Aviation Regulations 1988 may apply. These penalties can include fines and potential imprisonment for individuals found guilty of contravening the regulations, alongside penalties for corporations that may include substantial fines based on the severity and frequency of the offence.