SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-28R Arrow III · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA) of Australia, specifically addressing safety concerns related to the Piper PA-28 series aircraft, including the PA-28R Arrow. The directive outlines necessary actions to correct unsafe conditions identified in the aircraft's control wheel attachment system. It applies to specific serial numbers of the PA-28R Arrow and provides detailed inspection and modification requirements to ensure the safety and airworthiness of the aircraft. The AD emphasizes compliance timelines and references related service bulletins for guidance on corrective actions.
- The AD applies to Piper PA-28R-201 Arrow aircraft with serial numbers 2844014 through 2844099 and 2844100 through 2844104.
- Inspect the control wheel attachment screw for proper thread engagement; at least one thread must show past the end of the nut plate.
- If the screw can be fully inserted into the nut plate by hand, replace the nut plate before further flight.
- Install retainer clip part number 104687-002 as specified in the service bulletin.
- Compliance is required within 25 hours and 100 hours of service after 11 August 2004.
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
- 2005
- Pages
- 2
- File size
- 22 KB
- Publisher
- services.casa.gov.au
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- Parts Catalog (IPC)
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- Type Certificate (TCDS)
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In this document
Applicability
The AD applies to specific models of the Piper PA-28 series, including the PA-28R-201 Arrow, with serial numbers ranging from 2844014 to 2844099 for Group A and 2844100 to 2844104 for Group B. This categorization helps identify which aircraft are subject to the requirements outlined in the directive.
Requirement
The directive mandates inspections and modifications for the control wheel attachment. For Group A aircraft, pilots must inspect the control wheel attachment screw for proper thread engagement and replace it if necessary. Additionally, the nut plate must be checked for locking characteristics, and if inadequate, it must be replaced. For both Group A and B aircraft, a retainer clip must be installed as per the referenced service bulletin.
Compliance
Compliance with the directive is required within specified timeframes: inspections must be completed within 25 hours of service after 11 August 2004, and modifications must be accomplished within 100 hours of service after the same date. These timelines are crucial for maintaining the aircraft's airworthiness.
Background
The directive was issued following an incident involving a PA-28-181 aircraft that crashed due to loss of control attributed to a failure in the control wheel attachment. Investigations revealed that the attachment screw was too short and the nut plate did not provide adequate locking. This amendment addresses these safety concerns by mandating inspections and modifications.
Safety notes
- Failure to comply with the AD may result in loss of control of the aircraft.
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 On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/PA-28/96 and issues the following AD under subregulation 39.001(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-28 Series Aeroplanes AD/PA-28/96 Amdt 1 Control Wheel Attachment 3/2005 Applicability: Group A aircraft: Models Serial Numbers PA-28-161 Warrior III 2842026 through 2842180 PA-28-181 Archer III 2843112 through 2843565 PA-28R-201 Arrow 2844014 through 2844099 Group B aircraft: PA-28-161 Warrior III 2842181 through 2842203 PA-28-181 Archer III 2843566 through 2843588 PA-28R-201 Arrow 2844100 through 2844104 Requirement: 1. For aircraft listed in Group A of the applicability part of this Directive, with the exception of aircraft listed in Group A that are already modified in accordance with the New Piper Aircraft Service Bulletin (SB) No. 1139, dated 28 August 2003; accomplish the following in accordance with Part I of SB No.1139A dated 9 April 2004: a. Inspect the control wheel attachment screw for proper thread engagement (minimum one thread showing past the end of the nut plate), and replace the screw before further flight if insufficient thread engagement is found. b. Inspect the nut plate for sufficient locking characteristics. If the screw can be fully inserted into the nut plate by hand (one thread showing past end of nut), then replacement of the nut plate is required before further flight. c. Reassemble the control wheel onto the control wheel shaft and install the attachment screw using Loctite thread-locking compound. 2. For aircraft listed in Group A or Group B of the applicability part of this Directive, install retainer clip part number 104687-002 in accordance with Part II of SB No. 1139A, dated 9 April 2004. COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES Piper PA-28 Series Aeroplanes AD/PA-28/96 Amdt 1 (continued) Page 2 of 2 Note: Corrected FAA AD 2004-14-12 Amdt 39-13721 refers. Compliance: 1. Within 25 hours time in service after 11 August 2004. 2. Within 100 hours time in service after 11 August 2004. The compliance times remain unchanged by this issue. This Amendment becomes effective on 17 March 2005. Background: The FAA received a report that a Model PA-28-181 aircraft crashed after the pilot lost control of the ailerons and elevator. Investigation revealed that the left control wheel single attachment screw had unscrewed from its nut plate, which resulted in the control wheel spinning freely on the control column. Further investigation revealed the screw was too short and the nut plate lacked proper locking characteristics. Amendment 1 is issued in response to the issue of a corrected copy of the related FAA AD, which corrects certain parts of the text. The only part requiring correction of this Directive was Requirement 1. text, “Part I of SB No. 1139 dated 9 April 2004” which was changed to “Part I of SB No. 1139A dated 9 April 2004”. David Punshon Delegate of the Civil Aviation Safety Authority 4 February 2005