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.
Piper PA-23 (Apache and Aztec) Series Aeroplanes
AD/PA-23/89 (continued)
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.
Overview
The Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Act 1988 aims to address safety concerns identified in the Piper PA-23 (Apache and Aztec) Series Aeroplanes. Specifically, the AD was enacted in response to reports of damage to the flap control torque tube, which, if undetected, could result in failure of the flap operating system. The AD requires inspections and, if necessary, the replacement of the flap control torque tube and wooden end plugs with new plastic end plugs, as outlined in the AD. This directive applies to certain models and serial numbers of the Piper PA-23 aircraft series and became effective on 7 August 2003. The policy objective of the AD is to ensure the continued airworthiness and safety of the affected aircraft by mandating regular inspections and necessary repairs.
Scope and Application
This Airworthiness Directive applies to specific models and serial numbers of Piper PA-23 (Apache and Aztec) series aeroplanes, which includes model PA-23 and PA-23-160 aircraft with serial numbers ranging from 23-1 to 23-2046, model PA-23-235 aircraft with serial numbers 27-505 through 27-622, model PA-23-250 aircraft with serial numbers 27-1 through 27-504 and 27-2000 through 27-8154030, and model PA-E23-250 aircraft with serial numbers 27-2505 through 27-4916 and 27-7304917 through 27-7554168. The directive mandates that the flap control torque tube of these aircraft must be inspected for damage, such as cracks, corrosion, wear, or elongation of the attachment bolt holes, following specific instructions outlined in Piper Mandatory Service Bulletin No. 1051B dated 5 November 2002. Damaged components must be replaced with new parts before further flight, including replacing the flap control torque tube with an approved part and wooden end plugs with plastic ones. The initial inspection must occur after the aircraft has accumulated 2,500 hours of time in service or within 100 hours of 7 August 2003, whichever is later, with subsequent inspections occurring at intervals not exceeding 500 hours of time in service until the replacement of the flap control torque tube is completed.
Key Provisions
The key operative sections of the Airworthiness Directive (AD/PA-23/89) pertain to the inspection and replacement requirements for the flap control torque tube in specified Piper PA-23 aircraft models. Section (a) of the applicability section details the aircraft models and serial numbers that are subject to the AD, including PA-23, PA-23-160, PA-23-235, PA-23-250, and PA-E23-250 series aircraft within certain serial number ranges. Section (b) of the requirement section mandates that the flap control torque tube be inspected for cracks, corrosion, wear, or elongation of the attachment bolt holes, and any damaged components must be replaced with specified parts before further flight. The inspections and replacements must follow the instructions in sections 3 through 10 of the Piper Mandatory Service Bulletin No. 1051B dated 5 November 2002. Section (c) of the compliance section stipulates that the initial inspection must occur after the aircraft accumulates 2,500 hours of service or within 100 hours of 7 August 2003, whichever is later, and subsequent inspections must occur at intervals not exceeding 500 hours of service until the specified replacement parts are installed.
The AD imposes specific obligations on the owners and operators of the affected aircraft. These obligations include conducting the initial and repetitive inspections of the flap control torque tube as per the detailed requirements in the directive. Owners and operators must ensure that any damaged components identified during the inspections are replaced with the specified parts before the aircraft is flown again. This includes replacing the damaged flap control torque tube with a part number 17634-002, 104622-002, or 104622-004 flap control torque tube assembly and replacing wooden end plugs with new plastic end plugs part number 17631-002. Compliance with these inspection and replacement requirements is critical to maintaining the airworthiness of the affected aircraft.
Breach of the requirements outlined in this AD can lead to serious consequences. The AD does not explicitly state civil or criminal penalties for non-compliance; however, failure to adhere to airworthiness directives is generally subject to enforcement actions by the Civil Aviation Safety Authority (CASA). Such actions may include fines, suspension of the aircraft's Certificate of Airworthiness, or other regulatory sanctions. Furthermore, undetected damage to the flap control torque tube could result in the failure of the flap operating system, which poses a significant risk to the safety of the aircraft and its occupants. This underscores the importance of strict compliance with the AD to prevent potential accidents or incidents arising from the failure of critical aircraft components.