COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
GAF N22 and N24 Series Aeroplanes
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/GAF-N22/65 Amdt 2 and issues the following 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.
AD/GAF-N22/65
Amdt 3
Rear Fuselage Frame 6/2000
Applicability: All model N22 and N24 aircraft which have NOT been modified in accordance with ASTA Modification N806.
Requirement: 1. Inspect the forward face of the rear fuselage frame for cracks in accordance with ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.A, (Part 1 - Inspection).
2. Modify the aircraft by installing ASTA Modification N806 in accordance with ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.C, (Part 3 - Mod N806 Incorporation).
Note: ANMD-53-15 Revision 3 describes the same inspection as that required by previous amendments to this AD.
Compliance: For Requirement Para 1: As detailed in the Requirement Document Para 1.D.(2).
For Requirement Para 2: As detailed in the Requirement Document Para 1.D.(4). Aircraft which have already exceeded the applicable compliance time must be modified within 12 months time in service after 15 June 2000.
This Amendment becomes effective on 15 June 2000.
Background: The initial issue of this directive was issued following receipt of a number of reports of aircraft with cracks around the rivet heads on the rear bulkhead frame. Frame failure may lead to loss of structural integrity and possible subsequent loss of aircraft control. This amendment adopts the inspection procedures and compliance times specified by the manufacturer, and requires installation of the preventive modification which is terminating action for the inspections.
Amendment 2 of this Airworthiness Directive became effective on 30 September 1993.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Amendment 1 of this Airworthiness Directive became effective on 25 May 1993. The original issue of this Airworthiness Directive became effective on 25 May 1993.
Bernard Malcolm Hole
Delegate of the Civil Aviation Safety Authority 5 May 2000
The above AD is notified in the Commonwealth of Australia Gazette on 17 May 2000.
Overview
The Civil Aviation Regulations 1998, amended through the Legislative instrument F2006B10214, specifically address safety concerns related to the GAF N22 and N24 series aeroplanes by issuing Airworthiness Directives (AD). Enacted by the Civil Aviation Safety Authority (CASA) under subregulation 39.1(1) of the Civil Aviation Regulations 1998, these directives were introduced to address the problem of structural integrity risks identified in the rear fuselage frames of these aircraft models. The primary policy objective of these ADs is to ensure the continued airworthiness of affected aircraft through required inspections and modifications, thereby mitigating the risk of frame failure that could lead to loss of control. The directive mandates specific inspection and modification actions to be undertaken by aircraft operators, ensuring compliance within specified timeframes to maintain safety standards.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39 - 105, specifies the scope and application of Airworthiness Directives issued by the Civil Aviation Safety Authority (CASA). This particular Airworthiness Directive AD/GAF-N22/65 Amdt 3 applies to all model N22 and N24 aircraft that have not been modified in accordance with ASTA Modification N806. The directive mandates specific actions to address an unsafe condition concerning the rear fuselage frame of these aircraft, which if left unrectified, could result in structural failure and loss of control. The directive requires an inspection of the forward face of the rear fuselage frame for cracks and mandates the installation of a corrective modification to prevent such failures. The directive applies nationally across Australia and is enforceable under the authority of the Civil Aviation Safety Regulations 1998. Compliance with this directive is mandatory for the specified aircraft unless they have already undergone the required modifications. The directive does not specify any exclusions or exemptions but does provide a compliance timeline, with existing aircraft required to undergo the modifications within twelve months of the directive's effective date.
Key Provisions
This legislative instrument outlines an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 (CAR 1998). Specifically, AD/GAF-N22/65 Amdt 3 addresses issues with the rear fuselage frame of model N22 and N24 aircraft that have not been modified according to ASTA Modification N806. The AD mandates that all applicable aircraft must undergo an inspection of the forward face of the rear fuselage frame for cracks, following procedures specified in ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.A. Additionally, the aircraft must be modified by installing ASTA Modification N806, as outlined in ASTA Nomad Alert Service Bulletin ANMD-53-15 Revision 3, Section 2.C.
The AD imposes several obligations on the parties it governs. First, operators of N22 and N24 aircraft that have not yet been modified in accordance with ASTA Modification N806 must conduct the specified inspection of the rear fuselage frame. This inspection must be performed according to the detailed instructions in the referenced service bulletin, which outlines the specific inspection procedures and frequency. Second, following the inspection, if any cracks are found, the aircraft must be modified by installing ASTA Modification N806. This modification is a preventive measure aimed at correcting the unsafe condition identified in the initial reports. The modification instructions are also detailed in the referenced service bulletin, and the aircraft must be modified within the compliance period specified in the AD.
Failure to comply with the requirements of this AD can result in significant consequences. While the specific penalties for non-compliance are not detailed in the AD, under the Civil Aviation Act 1988, non-compliance with an AD can result in severe civil or criminal penalties. Civil penalties may include fines, while criminal penalties could involve imprisonment, depending on the severity of the non-compliance and any resulting harm or risk. The AD itself specifies compliance timeframes: for inspections, compliance must be achieved as detailed in the requirement document paragraph 1.D.(2), and for modifications, aircraft that have already exceeded the applicable compliance time must be modified within 12 months of service after 15 June 2000. This ensures that all affected aircraft are brought up to the required safety standards in a timely manner.