COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Boeing 727 Series Aeroplanes
AD/B727/94
Amdt 1
Forward Cargo Compartment Sidewall Frame 1/93
Applicability: All models B727-100 and -100C series aircraft with line numbers 1 to 478 and 480.
Requirement: Visually inspect internally the forward cargo compartment sidewall frames from BS 480 to BS 680 for cracks in accordance with Boeing SB 727-53-0068 Revision 4.
Note: FAA AD 90-20-14 refers.
Compliance: Inspect before 15600 flights, or within 2000 flights after 7 January 1993, or within 9000 flights since the last internal inspection in accordance with the original issue of this AD, or within 4000 flights since the last external inspection in accordance with the original issue of this AD, whichever occurs last.
Re-inspect at intervals not exceeding 9000 flights until modified in accordance with Boeing SB 727-53-0068.
Background: Cracking of the forward cargo compartment frames was detected during fatigue testing and a number of operators have experienced cracks in those frames.
Amendment 1 eliminates the previous option of the external inspection procedure. This procedure has been reassessed as inadequate to prevent a hazardous depressurisation.
Overview
The Civil Aviation Regulations 1998 were enacted to provide for the regulation of civil aviation in Australia, ensuring safety and efficiency in the operation of aircraft within Australian airspace. One particular legislative instrument, F2006B02798, focuses on addressing the safety issue of cracking in the forward cargo compartment sidewall frames of Boeing 727 series aeroplanes. This problem was identified during fatigue testing and has led to incidents of structural failure, posing a risk of hazardous depressurisation during flight. The objective of this legislation is to mandate regular inspections of the specified aircraft components to mitigate such risks. The Civil Aviation Safety Authority, as the regulatory body, enforces these directives to maintain high safety standards in civil aviation. This particular amendment, AD/B727/94 Amendment 1, eliminates the option of external inspections in favour of more stringent internal inspections to ensure thorough detection of cracks, thereby enhancing aircraft safety.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 pertaining to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, applies to Boeing 727 series aeroplanes, namely the B727-100 and -100C models with line numbers 1 to 478 and 480. This legislation mandates a visual inspection of the forward cargo compartment sidewall frames from BS 480 to BS 680 for cracks, aligning with Boeing Service Bulletin 727-53-0068 Revision 4. The requirement to conduct this inspection arises before the aircraft accumulates 15,600 flights or within specific intervals following certain key dates or previous inspections, ensuring that any identified issues are addressed in a timely manner. Amendment 1 to this directive has rendered the previously allowed external inspection procedure obsolete, recognising its inadequacy in preventing hazardous depressurisation. This legislative instrument therefore applies directly to the specified aircraft models within the designated flight intervals, ensuring compliance with stringent safety standards to mitigate potential risks associated with the identified structural issue.
Key Provisions
The main operative sections of the Civil Aviation Regulations 1998, specifically within PART 39 - 105, mandate that all models B727-100 and -100C series aircraft with line numbers 1 to 478 and 480 undergo a visual inspection of the forward cargo compartment sidewall frames. This inspection must be conducted internally, from bolt slots (BS) 480 to BS 680, to detect any cracks, as detailed in Boeing Service Bulletin (SB) 727-53-0068 Revision 4 (Section 1/93). The directive emphasises the necessity of this inspection due to previously detected cracking during fatigue testing and reported incidents of such cracks in operational aircraft. This requirement supersedes the earlier option of an external inspection procedure, which has been deemed inadequate to prevent hazardous depressurisation.
The obligations imposed by this regulation are clear and specific. Aircraft operators must ensure that the specified inspection is performed before the aircraft reaches 15,600 flights, or within 2000 flights after 7 January 1993, or within 9000 flights since the last internal inspection, or within 4000 flights since the last external inspection, whichever occurs last. Additionally, re-inspections must be conducted at intervals not exceeding 9000 flights until the aircraft is modified in accordance with Boeing SB 727-53-0068. These stringent timelines ensure that the aircraft remain compliant with safety standards and are maintained to prevent structural failure.
The consequences for non-compliance with these provisions are significant. While the regulations do not explicitly state civil or criminal penalties, failure to adhere to these airworthiness directives could lead to serious safety issues, including potential depressurisation of the aircraft during flight. This could result in a range of adverse outcomes, including the need for costly repairs, grounding of the aircraft, and potential legal actions against the operator for negligence. Additionally, non-compliance may also affect the operator's reputation and could lead to loss of licence or other regulatory sanctions imposed by the Civil Aviation Safety Authority (CASA).