{"id":"F2008L04421","name":"AD/PA-38/7 Amdt 6 - Fin Forward Spar Attachment - Inspection, Modification and Life Limit","slug":"ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":76409,"registerId":"commonwealth-F2008L04421-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Piper PA-38 (Tomahawk) Series Aeroplanes","sectionType":"division","heading":"Piper PA-38 (Tomahawk) Series Aeroplanes","content":"### Piper PA-38 (Tomahawk) Series Aeroplanes\n\n| AD/PA-38/7 Amdt 6 | Fin Forward Spar Attachment - Inspection, Modification and Life Limit | 13/2008 |\n| ----------------- | --------------------------------------------------------------------- | ------- |\n\n| Applicability: | All model PA-38-112 with S/Nos. 38-78A0001 to 38-80A0198.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n| -------------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Gain access to vertical fin forward spar attachment plate P/N 77553-05 by removing lower fin fairing. Visually inspect for signs of movement, cracking and/or clamping witness marks in vicinity of fin forward spar attachment to fuselage.2. Remove vertical fin and using a dye penetrant method inspect for cracks in:(a) Fin forward spar in vicinity of attachment plate P/N 77553-05.(b) Cancelled.(c) Front and rear faces of bulkhead P/N 77553-02 in vicinity of rivets that attach plate P/N 77553-05 and adjacent flange radius.3. Replace the fin forward spar attachment plate, Piper P/N 77553-05.Note: Piper SB 745 Parts I, II and III; and FAA AD 82-27-08(a)(1), (a)(2) and (a)(4) refer.                                                                                                                                            |\n| Compliance:    | 1 and 2(a). For aircraft which do not incorporate forward fin spar modification kit Piper P/N 764427 or CASA-approved repair scheme Drg. 01-B-422 and AV-157-02 inspect at each scheduled maintenance event for the issue of a maintenance release.2(c). For aircraft which do not incorporate fuselage bulkhead assembly P/N77553-06 or CASA-approved repair scheme Drg. 01-B-422 and AV-157-02 inspect at intervals not exceeding 300 hours time in service.3. For aircraft which do not incorporate CASA-approved repair scheme Drg.01-B-422 and AV-151-02 replace fin forward spar attachment plates at intervals not exceeding 3000 hours time in service; orfor aircraft which incorporate CASA-approved repair scheme Drg. 01-B-422 andAV-151-02, replace fin forward spar attachment plates at intervals not exceeding 5000 hours time in service. |\n\n|             | This Amendment becomes effective on 18 December 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| ----------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Background: | Amendment 5 relieved some of the repetitive inspections in the area of the fin forward spar attachment. For aircraft with the CASA-approved reinforcement, repeat replacement of the fin forward spar attachment plate was extended to 5000 hours reflecting similarity with SB 710.Amendment 6 cancels requirement 2(b) based on a once-only inspection in Piper SB No. 628A and USA AD 78-26-06 which were only applicable to aircraft with serial numbers through to 38-78A0749. At requirement 2 (c), amendment 6 gives credit for fuselage bulkhead assembly P/N 77553-06 to match USA AD 82-27-08 (a)(2). Amendment 6 also changes the reference from USA AD 81-04-07 to 82-27-08. |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n6 November 2008","sortOrder":0},{"sectionNumber":"AD/PA-38/7 Amdt 6","sectionType":"part","heading":"AD/PA-38/7 Amdt 6","content":"## AD/PA-38/7 Amdt 6","sortOrder":1},{"sectionNumber":"Fin Forward Spar Attachment - Inspection","sectionType":"part","heading":"Fin Forward Spar Attachment - Inspection, Modification and Life Limit","content":"## Fin Forward Spar Attachment - Inspection, Modification and Life Limit","sortOrder":2},{"sectionNumber":"13/2008","sectionType":"part","heading":"13/2008","content":"## 13/2008","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"Amendment 6 narrows and adjusts the original obligations: it cancels the once‑only inspection requirement 2(b) that applied only to earlier serial numbers, grants credit for fuselage bulkhead assembly P/N 77553‑06 (thereby reducing inspection frequency for aircraft with that part), and extends replacement intervals for aircraft with CASA‑approved reinforcement to match SB 710 (5000 hours) rather than 3000 hours. It also updates the referenced FAA AD from 81‑04‑07 to 82‑27‑08."},"complexity_factors":["Aircraft and serial‑number limited applicability (PA‑38‑112 S/N 38‑78A0001 to 38‑80A0198)","Multiple inspection methods required (visual access through lower fairing; dye‑penetrant after fin removal)","Different compliance intervals depending on installed modification or parts (maintenance event, ≤300 hours, ≤3000 hours, ≤5000 hours)","Several alternative compliance paths (Piper modification kits, CASA‑approved repair schemes Drg. 01‑B‑422, AV‑157‑02, AV‑151‑02)","Specific part‑number references (plate P/N 77553‑05; bulkhead P/N 77553‑06) that determine obligations","Cross‑references to external service bulletins and FAA ADs (Piper SB 745, SB 628A, FAA ADs 78‑26‑06, 82‑27‑08), requiring implementers to consult other documents","One provision cancelled only for a subset of serial numbers, creating asymmetrical obligations across the fleet","Operational burden includes removing the fin for dye‑penetrant inspection and replacing structural parts at life limits","Discretion and approval by CASA for repair schemes affects compliance route and replacement intervals"],"plain_english_summary":"This AD requires owners/operators of specified Piper PA-38-112 Tomahawks (S/N 38-78A0001 to 38-80A0198) to inspect the vertical fin forward spar attachment plate P/N 77553-05 (visual access, and dye‑penetrant after fin removal), and to replace that plate on a fixed hours schedule unless certain CASA‑approved modifications or parts are fitted. Amendment 6 removes one narrowly applicable once‑only inspection, gives credit for bulkhead assembly P/N 77553‑06, and aligns longer replacement intervals where reinforcement is installed, changing who pays and how often maintenance must be done."},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This remains a targeted airworthiness directive focused on a specific structural failure mode in a single aircraft type. Amendment 6 narrows the scope slightly by removing requirement 2(b) for post-1978 aircraft, but does not expand beyond the original safety purpose of preventing fin attachment failures."},"complexity_factors":["Multiple conditional compliance paths based on modification status (unmodified vs. reinforced aircraft)","Cross-references to external documents: Piper Service Bulletins (SB 745, SB 628A, SB 710), FAA ADs (78-26-06, 81-04-07, 82-27-08), and CASA-approved repair schemes (Drg. 01-B-422, AV-151-02, AV-157-02)","Nested exceptions: different inspection intervals (300h vs. each maintenance event) and replacement intervals (3000h vs. 5000h) depending on which modifications are installed","Technical aviation terminology requiring specialised knowledge (dye penetrant, time in service, maintenance release, part numbers)","Amendment structure requires understanding of previous versions (Amendment 5) to fully grasp what has changed"],"plain_english_summary":"This AD mandates inspections and eventual replacement of the fin forward spar attachment plate on Piper PA-38-112 Tomahawks (S/N 38-78A0001 to 38-80A0198) to prevent fin detachment. It requires periodic visual and dye‑penetrant inspections (300‑hour intervals for unmodified aircraft) and plate replacement every 3,000 flight hours (5,000 if a CASA‑approved bulkhead reinforcement is fitted). Amendment 6 removes an obsolete early‑production check and credits the approved bulkhead modification. Non‑compliance grounds the aircraft."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit","history":"/api/acts/ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit/history","analysis":"/api/acts/ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit/analysis","conflicts":"/api/acts/ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit/conflicts","importantCases":"/api/acts/ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit/important-cases","documents":"/api/acts/ad-pa-38-7-amdt-6-fin-forward-spar-attachment-inspection-modification-and-life-limit/documents"}}