SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-23 Aztec · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) of Australia concerning the Piper PA-23 series aircraft, specifically the Apache and Aztec models. The directive addresses safety concerns related to the flap control torque tube, which has been reported to suffer from damage such as cracks, corrosion, and wear. The AD mandates inspections and potential replacements of the flap control torque tube to ensure the safety and airworthiness of the aircraft. Compliance with the directive is crucial for maintaining operational safety and preventing failure of the flap operating system, which could lead to serious in-flight issues.
- Initial inspection required after 2,500 hours of service or within 100 hours after 7 August 2003.
- Repetitive inspections must occur at intervals not exceeding 500 hours of service.
- Inspect for cracks, corrosion, wear, or elongation of attachment bolt holes on the flap control torque tube.
- Replace any damaged flap control torque tube or end plugs before further flight.
- Compliance with this AD is mandatory to ensure safety and airworthiness.
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
- Airworthiness Directives
- Year
- 2003
- Pages
- 2
- File size
- 21 KB
- Publisher
- services.casa.gov.au
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- Pilot's Operating Handbook / AFM
- Checklist
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- Parts Catalog (IPC)
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- Service Bulletins
- Type Certificate (TCDS)
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In this document
Applicability
The Airworthiness Directive applies to the following models of the Piper PA-23 series: PA-23 and PA-23-160 (serial numbers 23-1 through 23-2046), PA-23-235 (serial numbers 27-505 through 27-622), PA-23-250 (serial numbers 27-1 through 27-504 and 27-2000 through 27-8154030), and PA-E23-250 (serial numbers 27-2505 through 27-4916 and 27-7304917 through 27-7554168).
Requirement
Operators are required to inspect the flap control torque tube for any signs of damage, including cracks, corrosion, wear, or elongation of the attachment bolt holes. This inspection must be conducted according to the Piper Mandatory Service Bulletin No. 1051B. If any damage is found, the damaged components must be replaced before further flight.
Compliance
The initial inspection of the flap control torque tube must be completed after accumulating 2,500 hours of service or within 100 hours after 7 August 2003, whichever is later. Subsequent inspections must occur at intervals not exceeding 500 hours of service until a replacement torque tube or assembly is installed.
Background
The directive was issued following reports received by the FAA regarding damage found in the flap control torque tube on affected aircraft. The potential for undetected damage poses a risk of failure in the flap operating system, which is critical for safe aircraft operation.
Safety notes
- Undetected damage to the flap control torque tube could result in failure of the flap operating system.
Full document text
COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Page 1 of 2 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 CASR 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. Piper PA-23 (Apache and Aztec) Series Aeroplanes AD/PA-23/89 Flap Control Torque Tube 8/2003 Applicability: Model PA-23 and PA-23-160 aircraft, serial numbers 23-1 through 23-2046. Model PA-23-235 aircraft, serial numbers 27-505 through 27-622. Model PA-23-250 aircraft, serial numbers 27-1 through 27-504, and 27-2000 through 27-8154030. Model PA-E23-250 aircraft, serial numbers 27-2505 through 27-4916, and 27- 7304917 through 27-7554168. Requirement: Inspect the flap control torque tube for cracks, corrosion, wear, or elongation of the attachment bolt holes (referred to as damage); in accordance with sections 3 through 10 of the Accomplishment Instructions section of Piper Mandatory Service Bulletin No. 1051B, dated 5 November 2002. Replace, before further flight after the inspection where damage is found, any damaged flap control tube, and any wooden end plugs with new plastic end plugs part number 17631-002. Replace the flap control tubes with either a part number 17634- 002 flap control torque tube or a part number 104622-002 or 104622-004 flap control torque tube assembly. The part number 17631-002 end plugs are part of the part number 104622-002 and 104622-004 flap control torque tube assemblies, but must be obtained for the part number 17634-002 installation. Note: FAA AD 2003-09-13 Amdt 39-13142 refers. Compliance: Initially inspect upon accumulating 2,500 hours time in service on the flap control torque tube or within 100 hours time in service after 7 August 2003, whichever occurs later. Repetitively inspect thereafter at intervals not to exceed 500 hours time in service; until a replacement flap control torque tube or flap control torque tube assembly as specified in the Requirement part of this Directive, is installed. This Airworthiness Directive becomes effective on 7 August 2003. COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Piper PA-23 (Apache and Aztec) Series Aeroplanes AD/PA-23/89 (continued) Page 2 of 2 Background: The FAA received several reports of damage found in the flap control torque tube on the affected aircraft. Undetected damage to the flap control torque tube could result in failure of the flap operating system. David Punshon Delegate of the Civil Aviation Safety Authority 26 June 2003 The above AD is notified in the Commonwealth of Australia Gazette on 16 July 2003.