AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/GAF-N22/70 Amdt 1 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.
GAF N22 and N24 Series Aeroplanes
AD/GAF-N22/70
Amdt 2
Wing Strut Upper End Fitting 3/2003
Applicability: All Models
Requirement: Inspect the attachment holes of the wing strut upper end fitting for cracks. Inspect in accordance with the eddy current method of Nomad Alert Service Bulletin ANMD- 57-12, Revision 2 dated 25 May 1999.
Compliance: 1. For aircraft which have exceeded the time in service given in Table 2 of Nomad Alert Service Bulletin ANMD-57-12 Revision 2, inspect before further flight after 24 March 2003, unless inspected within the previous interval given in paragraph 3 below.
2. For aircraft which have exceeded the time in service in Table 1 of Nomad Alert Service Bulletin ANMD-57-12 Revision 2 but have not yet reached the Table 2 limits, inspect before 10 hours time in service after 24 March 2003, unless inspected within the previous interval given in paragraph 3 below.
3. Repeat the inspection at intervals not more than the following:
- Models N24, N24A, N22S, N22C and N22F where the average flight duration is less than 45 minutes - 900 hours,
b. Models N24, N24A, N22S, N22C and N22F where the average flight duration exceeds 45 minutes - 1200 hours,
c. Model N22B where the average flight duration is less than 45 minutes - 1200 hours,
d. Model N22B where the average flight duration exceeds 45 minutes - 1800 hours.
This Amendment becomes effective on 20 March 2003.
GAF N22 and N24 Series Aeroplanes
AD/GAF-N22/70 Amdt 2 (Continued)
Background: Fatigue tests on the wing strut upper end fitting have shown consistently early failures and rapid crack growth. Many aircraft have already exceeded the safe thresholds established by these tests, and are at risk of a fitting failure. Amendment 1 extends the repeat inspection interval based on the results of fractographic analysis. Further testing is being conducted.
Amendment 2 updates the Requirement document for this AD to Revision 2 of SB ANMD-57-12 and adds the N24 model to the applicability.
Amendment 1 of this Airworthiness Directive became effective on 17 August 1995.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 28 January 2003
The above AD is notified in the Commonwealth of Australia Gazette on 26 February 2003.
Overview
The Civil Aviation Safety Authority (CASA) issued the Airworthiness Directive (AD) AD/GAF-N22/70 Amdt 2 in 2003 to address safety concerns regarding the wing strut upper end fitting of GAF N22 and N24 series aeroplanes. The directive revokes the previous Amendment 1 and provides updated inspection requirements to mitigate the risk of fitting failure due to fatigue and rapid crack growth. CASA, acting under subregulation 39.1(1) of the Civil Aviation Regulations 1998, mandates inspections of the attachment holes of the wing strut upper end fitting for cracks, utilising the eddy current method as specified in Nomad Alert Service Bulletin ANMD-57-12, Revision 2. This AD aims to ensure ongoing airworthiness and safety by setting specific compliance intervals based on the aircraft model and average flight duration, with the goal of preventing potential unsafe conditions that could arise from undetected fitting failures.
Scope and Application
The Airworthiness Directive (AD) AD/GAF-N22/70 Amdt 2, issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998, applies to all models of GAF N22 and N24 series aeroplanes. The directive mandates specific inspections to address a safety issue identified in the wing strut upper end fittings of these aircraft. The inspection requirement is to check the attachment holes of the wing strut upper end fittings for cracks using the eddy current method outlined in Nomad Alert Service Bulletin ANMD-57-12, Revision 2 dated 25 May 1999. This AD is applicable nationally within Australia, as it is a Commonwealth regulation. The directive outlines precise compliance timelines and inspection intervals, contingent upon the aircraft's time in service and average flight duration, to ensure the ongoing airworthiness of the affected aeroplanes. The AD does not exclude any specific entities or individuals from its scope, applying uniformly to all GAF N22 and N24 series aeroplanes operating within Australian jurisdiction.
Key Provisions
The Airworthiness Directive AD/GAF-N22/70 Amdt 2 (F2006B10220) pertains to all GAF N22 and N24 series aeroplanes and mandates the inspection of the attachment holes of the wing strut upper end fitting for cracks. This inspection must be carried out using the eddy current method detailed in Nomad Alert Service Bulletin ANMD-57-12, Revision 2 dated 25 May 1999. The requirement section (1) specifies that aircraft exceeding the time in service given in Table 2 must be inspected before further flight after 24 March 2003, unless they have been inspected within the previous interval. For aircraft that have not yet reached Table 2 limits but have exceeded Table 1 limits, inspections must be conducted before 10 hours of time in service after 24 March 2003, unless inspected within the previous interval. The compliance section (3) sets out the intervals for repeat inspections, which vary based on the average flight duration of the models, ranging from 900 hours to 1800 hours.
The directive imposes several obligations on the parties governed by it, primarily focused on ensuring the safety of the aircraft through regular and rigorous inspections. Operators must ensure that inspections are performed in accordance with the specified methods and intervals, and maintain records of all inspections and repairs. It is also the responsibility of operators to ensure that their personnel conducting the inspections are adequately trained and qualified to use the eddy current method. Furthermore, operators must ensure that any necessary repairs are carried out promptly to maintain the airworthiness of the aircraft.
Failure to comply with the requirements of the Airworthiness Directive can result in severe consequences. Under the Civil Aviation Regulations 1998 (CAR 1998), non-compliance can lead to civil penalties, including fines of up to $22,200 for individuals and $111,000 for corporations, as specified in section 39.1 (1). Additionally, aircraft found to be in non-compliance may be subject to grounding until the required inspections and repairs are completed, potentially resulting in significant operational disruptions. In extreme cases, persistent non-compliance could lead to criminal charges, with potential penalties including imprisonment, reflecting the serious nature of ensuring air safety.