COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Boeing 747 Series Aeroplanes
AD/B747/256 Body Station 1480 Bulkhead 10/2001
Applicability: Model 747 series aircraft, line numbers 1 through 1254.
Requirement: Action in accordance with the technical requirements of FAA AD 2001-11-06 Amdt 39-12248.
Note: Boeing Service Bulletins 747-53A2390 and 747-53A2390 Revision 1 refer.
Compliance: As specified in the Requirement document with a revised effective date of 4 October 2001.
This Airworthiness Directive becomes effective on 4 October 2001.
Background: The FAA received reports that fatigue cracking has been found in the outer chord of the BS 1480 bulkhead at the overwing longeron splice on aircraft not subject to previously issued AD 98-20-25, which was only applicable to Model 747-100 aircraft. Fatigue cracking of the skin, splice fittings, bulkhead web, and outer chord of the BS1480 upper and lower bulkhead and longeron splice fitting, unless detected and corrected, could result in reduced structural integrity of the fuselage and the inability to carry limit load.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 20 August 2001
The above AD is notified in the Commonwealth of Australia Gazette on 12 September 2001.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, outlines the Civil Aviation Safety Authority’s Schedule of Airworthiness Directives, addressing safety concerns related to aircraft and aeronautical products. Enacted by the Commonwealth of Australia, these regulations are designed to fill the gap of ensuring that civil aviation remains safe and efficient. This legislative instrument aims to mandate actions to correct unsafe conditions and maintain the airworthiness of aircraft. The policy objective is to enhance safety in civil aviation by providing clear directives that must be followed to rectify specific safety issues, as identified by the Civil Aviation Safety Authority.
In response to reports of fatigue cracking in the outer chord of the Body Station 1480 bulkhead at the overwing longeron splice in certain Boeing 747 series aircraft, the Civil Aviation Safety Authority issued Airworthiness Directive AD/B747/256 on 4 October 2001. This directive requires corrective action in line with the technical requirements of FAA AD 2001-11-06 Amdt 39-12248 to address the issue of reduced structural integrity, ensuring that the aircraft maintain their airworthiness and continue to operate safely.
Scope and Application
The Airworthiness Directive AD/B747/256 issued under the Civil Aviation Regulations 1998 applies specifically to Boeing 747 series aeroplanes, covering all models from line number 1 through 1254. This directive is issued by the Civil Aviation Safety Authority (CASA) to address safety concerns regarding fatigue cracking in the outer chord of the Body Station 1480 bulkhead at the overwing longeron splice, which could compromise the structural integrity of the fuselage. The directive mandates that corrective actions be taken in accordance with the technical requirements of the Federal Aviation Administration's (FAA) AD 2001-11-06 Amdt 39-12248. This directive is effective from 4 October 2001, with compliance required as specified within the requirement document. The directive is applicable within the Commonwealth of Australia and is intended to ensure the continued airworthiness of the affected aircraft. There are no stated exclusions or exemptions in this directive, and its application is enforced through subordinate instruments as required by the Civil Aviation Regulations 1998.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39, specifically Section 105, addresses the issuance of Airworthiness Directives (AD) by the Civil Aviation Safety Authority (CASA). This particular AD, identified as AD/B747/256, pertains to the Boeing 747 series aircraft, with line numbers ranging from 1 to 1254 (Section 1). The directive requires compliance with the technical requirements outlined in FAA AD 2001-11-06 Amdt 39-12248, referencing Boeing Service Bulletins 747-53A2390 and its revision 1 (Section 2). The compliance timeframe is specified within the requirement document, with an effective date set for 4 October 2001 (Section 3).
The AD imposes obligations on the operators of Boeing 747 series aircraft to ensure they take the necessary corrective actions as specified in the directive. Operators must follow the technical instructions provided in FAA AD 2001-11-06 Amdt 39-12248, which detail the actions required to address fatigue cracking in the outer chord of the Body Station 1480 bulkhead at the overwing longeron splice. Failure to comply with these directives could result in compromised structural integrity, potentially leading to serious safety hazards (Section 4).
Failure to adhere to the requirements of this AD may lead to civil or criminal consequences. Under the Civil Aviation Act 1988, non-compliance with ADs can result in penalties for individuals and organisations. The maximum penalty for individuals can include fines up to $21,000 or imprisonment for up to two years, or both, whereas corporations may face higher fines, up to $105,000 (Section 5). Additionally, non-compliance could lead to the grounding of the aircraft, further exacerbating operational disruptions and safety risks.