AIRWORTHINESS DIRECTIVE AD/PA-31/124 Amdt 1
Piper PA-31 Navajo Chieftain · Airworthiness Directives
Overview
This Airworthiness Directive (AD) pertains to the Piper PA-31 series aeroplanes, specifically addressing safety concerns related to the wing spar splice plate in the PA31-350 Chieftain models. The directive mandates the replacement of the main wing spar splice plate and outlines the inspection requirements for any signs of damage such as fretting, corrosion, or cracks. The AD is issued by the Civil Aviation Safety Authority (CASA) and is effective from October 25, 2019. It is crucial for maintaining the airworthiness of the affected aircraft and ensuring safety in operations. Compliance with this directive is necessary for all operators of the specified models to prevent potential structural failures due to fatigue cracking.
- Replace the main wing spar splice plate as per Piper Service Bulletin 1003.
- Inspect the removed splice plate for fretting, corrosion, or cracks.
- Report any defects found in the splice plate to CASA.
- Compliance is required upon reaching 13,000 hours TIS or 2,000 hours after the last inspection, whichever is later.
- This AD is effective from October 25, 2019.
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
- 2019
- Pages
- 2
- File size
- 224 KB
- Publisher
- services.casa.gov.au
Most owners only have the POH. Here's the essential set for the Piper PA-31 Navajo Chieftain.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
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In this document
Applicability
This AD applies to all Piper Chieftain PA31-350, PA31-350/A1, PA31-350/A2, and PA31-350T1020 model aircraft.
Requirement
Operators are required to replace the main wing spar splice plate according to Piper Service Bulletin 1003, dated June 16, 1997. Additionally, the removed splice plate must be visually inspected for fretting, corrosion, or cracks, and any defects must be reported to CASA.
Compliance
The compliance for the replacement and inspection of the wing spar splice plate is set at 13,000 hours of aircraft time in service (TIS) or 2,000 hours TIS after the last inspection, whichever is later.
Background
The directive was issued due to findings of fatigue cracking caused by fretting in both the PA-31 Navajo and PA31-350 Chieftain models. The PA31-350 design includes improvements, but fretting issues still necessitate this control action.
Amendment Details
Amendment 1 clarifies the compliance section and removes the requirement to send removed splice plates to CASA. It also includes the PA31-350T1020 model in the applicability and references the relevant Piper Service Bulletin and FAA AD.
Safety notes
- Fretting has caused fatigue cracking in both PA-31 Navajo and PA31-350 Chieftain models, necessitating this AD.
Full document text
COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39.001 Page 1 of 2 AIRWORTHINESS DIRECTIVE On the commencement date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below repeals Airworthiness Directive (AD) AD/PA-31/124 and issues the following AD under subregulation 39.001 (1) of CASR and subsection 33 (3) of the Acts Interpretation Act 1901. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct an 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-31 Series Aeroplanes AD/PA-31/124 Amdt 1 Wing Spar Splice Plate (Chieftain) 22/2019 Applicability: All Piper Chieftain PA31-350, PA31-350/A1, PA31-350/A2 and PA31-350T1020 model aircraft. Requirement: 1. a. Replace the main wing spar splice plate in accordance with the instructions in Piper Service Bulletin 1003 dated 16 June 1997, as in force at the date of this AD. b. Visually inspect the removed splice plate for any signs of fretting, corrosion or cracks. c. Report any defects found in the splice plate via the CASA defect reporting system. Note 1: For information, FAA AD 98-09-25 mandates Piper Service Bulletin 1003. Compliance: 1. Upon achieving 13,000 hours’ aircraft time in service (TIS), or 2000 hours’ TIS after the splice plate is inspected in accordance with a CASA approved inspection program (see AD/PA-31/37 as in force from time to time), whichever is the later. Note 2: The words “as in force from time to time” require compliance with the most recent version of the referenced document. This AD commences on 25 October 2019. Background: Fretting has caused fatigue cracking in both PA-31 Navajo and PA31-350 Chieftain models. Although the PA31-350 design in this area is an improvement over the PA-31, fretting has been found. This requires control action for those aircraft that have had their life extended without replacement of the splice plate. COMMONWEALTH OF AUSTRALIA Civil Aviation Safety Regulations 1998 CIVIL AVIATION SAFETY AUTHORITY Regulation 39.001 Piper PA-31 Series Aeroplanes AD/PA-31/124 Amdt 1 (continued) Page 2 of 2 Amendment 1 of this AD clarifies the compliance section and removes the requirement to forward removed splice plates to CASA. It also adds the PA31-350T1020 model to the applicability and inserts references to the associated Piper Service Bulletin and FAA AD. Pieter van Dijk Delegate of the Civil Aviation Safety Authority 18 October 2019