SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-42 Cheyenne III · Service Bulletins
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority of Australia, specifically for the Piper PA-42 Cheyenne III series aircraft. It outlines mandatory inspection and replacement requirements to ensure the structural integrity of the aileron system. The directive is applicable to various models within the PA-42 series, including the PA-42-720, PA-42-720R, and PA-42-1000, and it addresses potential cracks that could lead to loss of control of the aircraft. Compliance with the directive is crucial for maintaining airworthiness and safety in flight operations.
- Applicable to Piper PA-42, PA-42-720, PA-42-720R, and PA-42-1000 aircraft.
- Inspect for cracks in the aileron hinge area using dye penetrant methods.
- Replace cracked aileron spar assemblies and ribs as necessary.
- Replace inboard aileron hinge brackets with improved design parts P/N 74461-02 and P/N 74461-03.
- Compliance required at 3,000 hours total time in service or within 200 hours after 9 October 1997.
Document
Source
Originally published by services.casa.gov.au. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Service Bulletins
- Year
- 1997
- Pages
- 1
- File size
- 11 KB
- Publisher
- services.casa.gov.au
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- Pilot's Operating Handbook / AFM
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In this document
Applicability
The directive applies to Piper PA-42 series aircraft, specifically the PA-42, PA-42-720, PA-42-720R, and PA-42-1000 models, with serial numbers listed in Piper Service Bulletin 967.
Inspection Requirements
Operators are required to inspect the area beneath and around the inboard aileron hinge bracket on the aileron spar for cracks using dye penetrant methods. If cracks are detected, further inspections and replacements are mandated.
Replacement of Aileron Hinge Brackets
If cracks are found, the inboard aileron hinge brackets must be replaced with improved design parts P/N 74461-02 (left) and P/N 74461-03 (right), as per the instructions in Piper SB 967.
Compliance Timeline
Compliance with the inspection and replacement requirements is mandated upon reaching 3,000 hours total time in service or within 200 hours after 9 October 1997, whichever is later.
Background Information
The FAA issued this directive following reports of cracks in the aileron hinge area, which could lead to structural failure and loss of control. The directive aims to prevent such occurrences.
Safety notes
- Failure to comply with this directive may result in loss of control of the aircraft.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Piper PA-42 (Cheyenne III) Series Aeroplanes AD/PA-42/23 Aileron Hinge 11/97 Applicability: Model PA-42, PA-42-720, PA-42-720R, and PA-42-1000 aircraft with serial numbers as listed in Piper Service Bulletin (SB) 967. Requirement: 1. Inspect (using dye penetrant methods) the area beneath and in the area of the inboard aileron hinge bracket on the aileron spar for cracks in accordance with the Instructions section of Piper SB 967. If cracks are found on the aileron spar: (a) Inspect the corresponding aileron rib at the inboard aileron hinge bracket location; and (b) Replace any cracked spar assembly and any cracked aileron rib in accordance with the maintenance manual; 2. Replace the inboard aileron hinge brackets with a part of improved design P/N 74461-02 (left) and P/N 74461-03 (right), in accordance with the Instructions section of Piper SB 967, unless already accomplished. Note: FAA AD 96-21-03 Amdt 39-9780 refers. Compliance: For Requirement 1 and 2 : Upon the accumulation of 3,000 hours total time in service, or within 200 hours time in service after 9 October 1997, whichever occurs later, unless already accomplished. This airworthiness directive becomes effective on 9 October 1997. Background: The FAA received several reports of cracks in the vicinity of the inboard aileron hinge bracket, aileron spar, and aileron rib. The actions required by this Directive are intended to prevent structural failure of the aileron, which could result in loss of control of the aircraft.
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