COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Fokker F28 Series Aeroplanes
AD/F28/78 Lap Joint at Stringer 16/17 and 58/59 11/96
Applicability: Models F28 Mk. 1000 through to 4000 Series, S/Nos. 11017 to 11241 that do not have SB F28/53-121 incorporated.
Requirement: Action in accordance with Fokker SB F28/53-144.
Note: RLD AD 1996-081(A) refers.
Compliance: Unless already accomplished; on aircraft that have accumulated between:
- 25 000 and 32 000 flight cycles at 01 July 1996 - before 10 December 1996;
b. 20 000 and 25 000 flight cycles at 01 July 1996 - before 10 January 1997; and
c. 15 000 and 20 000 flight cycles at 01 July 1996 - before 10 February 1997. This Directive has effect from 10 October 1996.
Background: Cracking has been discovered in these lap joints before the inspection threshold mandated in the Structural Integrity Programme, and before the cycles threshold of AD/F28/75. This Directive requires a one time inspection of the area using the existing LFEC technique and if cracking is found, installation of a terminating repair.
Overview
The Civil Aviation Regulations 1998 (Cth), as amended, form a critical part of Australia's aviation safety framework. One specific legislative instrument within this framework, F2006B09812, pertains to airworthiness directives for Fokker F28 Series aeroplanes. This directive was introduced to address the issue of cracking discovered in the lap joints at stringers 16/17 and 58/59 of certain Fokker F28 models. The policy objective of this legislation is to ensure the safety and airworthiness of these aircraft by mandating specific inspections and repairs before the aircraft accumulate a certain number of flight cycles. The directive applies to Fokker F28 models from the Mk. 1000 through to 4000 series with specific serial numbers, excluding those that have already incorporated certain service bulletins.
Enacted by the Commonwealth of Australia, this regulation aims to mitigate potential safety risks associated with identified structural weaknesses in the specified Fokker aircraft models. The directive requires a one-time inspection using the existing LFEC technique, with subsequent terminating repairs if any cracking is detected. Compliance with this directive is mandatory, with different deadlines based on the number of flight cycles accumulated as of 1 July 1996.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, establish the requirements for airworthiness directives issued by the Civil Aviation Safety Authority, governing the maintenance and operation of aircraft within Australia. This particular directive, AD/F28/78, pertains to Fokker F28 Series aeroplanes, specifically models F28 Mk. 1000 through to 4000 series with serial numbers ranging from 11017 to 11241, and applies to aircraft that have not incorporated Service Bulletin F28/53-121. The directive mandates a one-time inspection of the specified lap joints at stringers 16/17 and 58/59 using the existing Load-Factor Fatigue Endurance Crack (LFEC) technique. If any cracking is detected, a terminating repair must be performed. Compliance with this directive is necessary based on the number of flight cycles accumulated by the aircraft as of 1 July 1996, with varying deadlines for inspections set between 10 December 1996 and 10 February 1997. This directive became effective on 10 October 1996 and references RLD AD 1996-081(A) for further guidance.
Key Provisions
The Civil Aviation Regulations 1998, Part 39 - 105, under the Civil Aviation Safety Authority, mandates specific Airworthiness Directives (AD) for Fokker F28 Series Aeroplanes. For instance, AD/F28/78 pertains to the lap joint at Stringer 16/17 and 58/59. This directive applies to Fokker F28 models Mk. 1000 through to 4000 series, excluding those with Serial Numbers (S/Nos.) 11017 to 11241 that have already incorporated Service Bulletin F28/53-121. The directive mandates compliance with Fokker Service Bulletin F28/53-144, referencing RLD AD 1996-081(A).
The directive specifies the action required in relation to the aircraft's flight cycles. For aircraft that have accumulated between 25,000 and 32,000 flight cycles by 1 July 1996, the action must be completed before 10 December 1996. For those with between 20,000 and 25,000 flight cycles by the same date, the deadline is 10 January 1997. Lastly, for aircraft with 15,000 to 20,000 flight cycles by 1 July 1996, the compliance must be achieved before 10 February 1997. These dates ensure a phased approach to compliance based on the number of flight cycles the aircraft has accumulated.
The obligations under this directive involve conducting a one-time inspection of the specified lap joints using the Low-Frequency Eddy Current (LFEC) technique. This inspection is critical for detecting any cracking in the lap joints, a known issue that has surfaced before the mandated Structural Integrity Programme inspections and before the cycles threshold specified in AD/F28/75. If any cracking is identified during the inspection, a terminating repair must be installed. This repair is designed to prevent further deterioration and ensure the aircraft's continued airworthiness.
Failure to comply with the requirements of AD/F28/78 can result in significant consequences. The primary concern is the potential for compromised structural integrity, which could lead to in-flight failures. While the Civil Aviation Regulations do not explicitly detail the penalties for non-compliance in this directive, general regulations under the Civil Aviation Act 1988 may apply. These could include fines, imprisonment, or both, depending on the severity of the non-compliance and its impact on aviation safety. The exact penalties would be determined in the context of the broader legal framework governing aviation safety in Australia.