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.
Lockheed P2V (SP-2H) Series Aeroplanes
AD/P2V/1 Wing Lower Surface Between Fuselage and
Inboard Engine Nacelle
13/2002
DM
Applicability: All Model P2V-7 (SP-2H) aircraft.
Requirement: 1. Accomplish a dye penetrant inspection to detect cracks on the left and right lower wing surfaces between the fuselage and inboard engine nacelle at the following locations:
- On the external surface within 3 inches from the edge of all access holes.
- On the internal surface or doubler within 1 inch from the edge of all access holes.
Ensure that the surfaces are thoroughly cleaned and dried before doing the dye penetrant inspection, and free of contaminants, paint, and other coatings that could prevent dye penetrant from entering discontinuities.
2. Accomplish a detailed visual inspection to detect cracks of the areas adjacent to those identified in Requirements 1.a. and 1.b.
3. Accomplish a detailed visual inspection to detect cracks of the surface around all access holes located on the left and right external lower wing surface between the fuselage and inboard engine nacelle, and adjacent areas.
If any crack is detected during any inspection required by this Directive, before further flight, repair in accordance with a method approved by the Manager, Denver Aircraft Certification Office, FAA, USA.
Note: FAA AD 2002-19-13 Amdt 39-12893.
Compliance: Requirements 1 and 2: For aircraft on which a repair has been done to correct cracking on the lower wing surface between the fuselage and the inboard engine nacelle, accomplish at the following compliance times:
Within 50 flight cycles after 6 November 2002, and thereafter at intervals not to exceed 50 flight cycles.
Lockheed P2V (SP-2H) Series Aeroplanes
AD/P2V/1 (continued)
Requirements 1 and 2: For aircraft on which a repair has NOT been done to correct cracking on the lower wing surface between the fuselage and the inboard engine nacelle, accomplish at the following compliance times:
Within 5 days after 6 November 2002, and thereafter at intervals not to exceed 50 flight cycles.
Requirement 3: For all aircraft, accomplish at following compliance times:
Within 5 days after 6 November 2002, and thereafter at intervals not to exceed 5 flight cycles.
This Airworthiness Directive becomes effective on 6 November 2002.
Background: The FAA requires certain actions to detect and correct stress-related cracking on the lower wing surfaces, which could result in structural failure of the wings and consequent loss of control of the aircraft.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 1 November 2002
The above AD is notified in the Commonwealth of Australia Gazette on 6 November 2002.
Overview
The Civil Aviation Safety Authority (CASA) has issued an Airworthiness Directive (AD) for the Lockheed P2V (SP-2H) Series Aeroplanes to address stress-related cracking on the lower wing surfaces. This AD, effective from 6 November 2002, was enacted to ensure the safety of these aircraft by requiring specific inspections and repairs. The directive mandates that all Model P2V-7 (SP-2H) aircraft undergo dye penetrant and visual inspections to detect and repair cracks on the lower wing surfaces. The inspections are to be conducted at specific intervals, with the frequency depending on whether previous repairs have been made to address similar issues. This directive is a critical measure to prevent potential structural failure and loss of control of the aircraft, aligning with the overarching policy objective of maintaining air safety and reliability.
Scope and Application
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under subregulation 39.1 (1) of the Civil Aviation Regulations 1998 applies specifically to all Model P2V-7 (SP-2H) aircraft within Australia. This directive mandates particular inspections and repairs to prevent stress-related cracking on the lower wing surfaces between the fuselage and the inboard engine nacelle, which could lead to structural failure and loss of control. The AD requires a comprehensive dye penetrant inspection and visual inspection of specified areas on the wings, with stringent cleaning protocols before inspection to ensure accuracy. Repairs must be conducted in accordance with methods approved by the Manager, Denver Aircraft Certification Office, FAA, USA. The directive stipulates compliance timelines, with inspections occurring within specific periods post the AD's effective date of 6 November 2002 and subsequently at intervals not exceeding 50 or 5 flight cycles, depending on whether a previous repair has been done. This AD extends its regulatory scope through the Commonwealth of Australia Gazette notification, ensuring its enforceability across all relevant jurisdictions within Australia.
Key Provisions
The Airworthiness Directive (AD) issued under subregulation 39.1(1) of the Civil Aviation Regulations 1998 (CAR 1998) applies to all Model P2V-7 (SP-2H) aircraft (section 1). The primary objective of this AD is to address stress-related cracking on the lower wing surfaces of these aircraft, which could lead to structural failure and loss of control. The directive mandates specific actions to detect and correct these issues.
The AD outlines three main requirements. Firstly, it requires a dye penetrant inspection to detect cracks on the left and right lower wing surfaces between the fuselage and inboard engine nacelle (section 1). This inspection must be conducted on both the external and internal surfaces, ensuring they are clean and free of contaminants. Secondly, a detailed visual inspection must be performed to detect cracks in the areas adjacent to those specified in the dye penetrant inspection. Lastly, another detailed visual inspection must be conducted on the surface around all access holes and adjacent areas on the left and right external lower wing surface.
The AD imposes several obligations on the parties involved. Aircraft owners and operators must ensure that the required inspections are performed by qualified personnel. They must adhere to the specified compliance times, which vary depending on whether a repair has already been made to correct cracking on the lower wing surface (section 2). For aircraft that have had repairs, inspections must be conducted within 50 flight cycles after 6 November 2002, and then at intervals not exceeding 50 flight cycles. For aircraft without such repairs, inspections must be conducted within 5 days after 6 November 2002, and then at intervals not exceeding 50 flight cycles. All aircraft must also undergo inspections according to the requirements within 5 days of 6 November 2002, and at intervals not exceeding 5 flight cycles.
Failure to comply with the requirements of this Airworthiness Directive can result in serious consequences. If any crack is detected during the inspections, it must be repaired in accordance with a method approved by the Manager, Denver Aircraft Certification Office, FAA, USA, before further flight. Non-compliance with the AD could lead to the aircraft being deemed unairworthy, potentially resulting in grounding and legal action. The directive became effective on 6 November 2002, and its provisions must be strictly followed to ensure the continued airworthiness and safety of the affected aircraft.