{"id":"F2022L00064","name":"AD/PA-32/42 Amdt 3 Wing Structural Fatigue Life Limitation","slug":"ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":102247,"registerId":"commonwealth-F2022L00064-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Piper PA-32 (Cherokee Six) Series Aeropl","sectionType":"part","heading":"Piper PA-32 (Cherokee Six) Series Aeroplanes","content":"# Piper PA-32 (Cherokee Six) Series Aeroplanes\n\n| AD/PA-32/42 Amdt 3 | Wing Structural Fatigue Life Limitation | 2/2022 |\n| ------------------ | --------------------------------------- | ------ |\n\n| Applicability: | All Piper PA-32 series aircraft, all models.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n| -------------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Retire from service:1.1. The wing main spar assembly; and1.2. The bottom cap of the wing main spar box (carry through).OR2. Inspect the lower wing joint for fatigue cracks in accordance with an approved inspection program.Note 1: For Requirement 1, replace retired components in accordance with approved maintenance data; Regulations 42V and 2A of CAR refer.Note 2: For Requirement 2, an acceptable standard for the inspection program is FAR 23.572 (a) (3) Amdt 23-48 or later or an equivalent level of safety approved by CASA.                                                                                                                                                                                                   |\n| Compliance:    | For models PA-32-260, PA-32-300, PA-32R-300, PA-32S-300, PA-32RT-300, PA‑32RT-300T:For Requirement 1: Retire before 11000 hours component time in service.For Requirement 2: Inspect before 11000 hours component time in service, and thereafter at the intervals specified in the approved inspection program.For models PA-32-301, PA-32R-301, PA-32-301T, PA-32R-301T, PA-32-301FT, PA-32-301XTC:For Requirement 1: Retire before 13700 hours component time in service.For Requirement 2: Inspect before 13700 hours component time in service, and thereafter at the intervals specified in the approved inspection program.Alternative Means Of Compliance or Exclusions approved for AD/PA-32/42 Amdt 2 are approved for AD/PA-32/42 Amdt 3. |\n|                | This AD commences on 27 January 2022.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n\n| Background: | Fatigue analysis predicts the possibility of cracking in the lower wing joint. Such cracking caused a fatal accident to a similar model with the same style of wing joint.The original issue of this Airworthiness Directive became effective on 29 October 1976.Amendment 1 re-affirmed that all Piper PA-32 series models are subject to the life limit, even those released after the original issue of this Directive. Amendment 1 minimised the structure to be retired by limiting it to the components which comprise the lower wing joint.Amendment 1 provided the possibility of inspection as an alternative to retirement.Amendment 2 became effective on 29 May 2009 and adjusted the life limit for Saratoga models with a semi-tapered wing following a review of Piper fatigue reports.Amendment 3 amends Note 2 of the AD to clarify requirements for inspection programs to satisfy Requirement 2 of the AD. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![Delegate signature](image.001.jpeg)\n\nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n21 January 2022","sortOrder":0},{"sectionNumber":"AD/PA-32/42 Amdt 3","sectionType":"part","heading":"AD/PA-32/42 Amdt 3","content":"## AD/PA-32/42 Amdt 3","sortOrder":1},{"sectionNumber":"Wing Structural Fatigue Life Limitation","sectionType":"part","heading":"Wing Structural Fatigue Life Limitation","content":"## Wing Structural Fatigue Life Limitation","sortOrder":2},{"sectionNumber":"2/2022","sectionType":"part","heading":"2/2022","content":"## 2/2022","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"Originally issued in 1976 as a straightforward retirement mandate for wing components, the directive has expanded significantly. Amendment 1 (date unspecified) introduced an inspection alternative to retirement, reducing economic burden but adding regulatory complexity. Amendment 2 (2009) differentiated life limits between model variants based on wing design. Amendment 3 (2022) further elaborates inspection program standards. The scope has shifted from simple 'retire at X hours' to a nuanced system of model-specific thresholds, alternative compliance methods, and referenced external technical standards."},"complexity_factors":["Multiple model variants with different hour thresholds (11,000 vs 13,700 hours)","Two alternative compliance paths (retirement vs inspection) with different ongoing obligations","Cross-references to external standards (FAR 23.572) and CAR regulations (42V and 2A)","Inherited compliance history (references to previous amendments and approved alternative means of compliance from Amendment 2)","Technical aviation terminology requiring domain knowledge (spar assembly, carry through, semi-tapered wing, component time in service)"],"plain_english_summary":"This Airworthiness Directive requires owners/operators of Piper PA-32 (Cherokee Six/Saratoga) aircraft to eliminate the risk of catastrophic wing failure from metal fatigue in the main spar. Before specified flight-hour thresholds (roughly 11,000 for older PA-32s and 13,700 for newer Saratoga variants), you must either replace the main spar assemblies or implement an approved, recurring inspection program.\n\nThe AD—issued after a fatal accident and revised to clarify acceptable inspections—is mandatory in Australia; non‑compliance grounds the aircraft."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":false,"description":"Amendment 3 does not change which PA‑32 models or which lower wing components are subject to the directive or the specified retirement hours. It amends Note 2 to clarify the acceptable standard for an inspection programme to satisfy Requirement 2 (inspection alternative). The instrument therefore clarifies approval criteria rather than expanding or narrowing applicability or retirement limits."},"complexity_factors":["Dual compliance paths (Requirement 1: mandatory retirement of named components; Requirement 2: approved inspection programme alternative) add procedural choice.","Different hours‑in‑service thresholds for two model groups (11,000 h vs 13,700 h) require model‑by‑model tracking of component time.","Inspection programme must meet an approved standard (Note 2 cites FAR 23.572(a)(3) Amdt 23‑48 or equivalent) — introduces cross‑jurisdictional standard references.","Replacement and maintenance must follow approved maintenance data and CAR Regulations 42V and 2A (introduces regulatory cross‑references).","Approval and discretion by CASA over inspection programmes and equivalents creates administrative review and potential case‑by‑case determinations.","Alternative Means of Compliance (AMOC) and exclusions from an earlier amendment are carried forward, requiring review of earlier approvals.","Inspection intervals are set by an approved programme (ongoing operational compliance burden rather than a one‑off action).","Amendment history (original AD, Amendments 1 and 2, now Amendment 3) means operators must reconcile legacy approvals and documentation."],"plain_english_summary":"This Airworthiness Directive requires owners/operators of all Piper PA‑32 series aeroplanes to either retire specific lower wing components (the wing main spar assembly and the bottom cap of the wing main spar box) at model‑specific hours‑in‑service limits, or run an approved fatigue inspection programme before those limits. CASA states the rule addresses predicted fatigue cracking in the lower wing joint after a fatal accident; Amendment 3 narrows how an inspection programme can be accepted. Owners pay for inspections or replacement; CASA approves programmes or alternative compliance."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation","history":"/api/acts/ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation/history","analysis":"/api/acts/ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation/analysis","conflicts":"/api/acts/ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation/conflicts","importantCases":"/api/acts/ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation/important-cases","documents":"/api/acts/ad-pa-32-42-amdt-3-wing-structural-fatigue-life-limitation/documents"}}