AD/PA-38/7 Amdt 6 - Fin Forward Spar Attachment - Inspection, Modification and Life Limit

The directive organises its safety measure around a small set of physical parts, inspection techniques, modification kits and approved repair schemes. Core parts named are the fin forward spar attachment plate, Piper P/N 77553‑05, the fuselage bulkhead assembly P/N 77553‑06, and the forward fin spar modification kit Piper P/N 764427. The inspection technique specified for fissures is dye penetrant inspection once the vertical fin is removed; before that, access to the attachment plate is achieved by removal of the lower fin fairing for a visual inspection for movement, cracking and clamping witness marks. The AD also incorporates by reference or cross‑links to other industry documents: Piper Service Bulletin SB 745 Parts I, II and III, and FAA AD 82‑27‑08 (specific paragraphs (a)(1), (a)(2) and (a)(4) are mentioned), and it relies on CASA‑approved repair scheme drawings identified as Drg. 01‑B‑422, AV‑157‑02 and AV‑151‑02 to determine alternative compliance or altered intervals.

The compliance logic is conditional: inspection frequencies and plate replacement life limits depend on whether the aircraft has certain modifications or assemblies installed. Aircraft lacking the forward fin spar modification kit or the CASA repair scheme Drg. 01‑B‑422/AV‑157‑02 are subject to inspection at each scheduled maintenance event tied to the issue of a maintenance release. Aircraft lacking fuselage bulkhead assembly P/N 77553‑06 or the CASA repair scheme Drg. 01‑B‑422/AV‑157‑02 are subject to inspections at not more than 300 hours time in service. Life‑limit replacement of the attachment plate is set at not more than 3000 hours TIS unless the CASA‑approved repair scheme Drg. 01‑B‑422/AV‑151‑02 is incorporated, in which case the interval extends to not more than 5000 hours TIS.

Amendment mechanics are used to refine prior requirements: Amendment 5 previously relieved some repetitive inspections and extended plate replacement for reinforced aircraft to 5000 hours to reflect similarity with SB 710. Amendment 6 cancels a once‑only inspection obligation (previously Requirement 2(b)) that applied only to aircraft up to a particular serial range; it also aligns the AD references with USA AD 82‑27‑08 and allows credit for the fuselage bulkhead assembly P/N 77553‑06. The AD therefore functions as a targeted safety‑of‑structure directive with conditional compliance paths determined by specific part numbers and CASA approvals.

The AD applies specifically to "All model PA‑38‑112 with S/Nos. 38‑78A0001 to 38‑80A0198." That numeric serial range confines the mandatory audience to the owners, operators and maintainers of those airframes. The instrument directly imposes actions on whoever is responsible for the maintenance release of those aeroplanes, which pragmatically will be the registered owner or operator and the maintenance organisation that signs the maintenance release. It also affects maintenance personnel who must perform the visual and dye penetrant inspections, and the organisations or suppliers who provide replacement fin forward spar attachment plates Piper P/N 77553‑05 and any CASA‑approved repair schemes or modification kits, including Piper P/N 764427. CASA itself is implicated because the directive gives credit for CASA‑approved repair schemes and the document is issued under the signature of a CASA delegate.

The conditional compliance paths create distinct subgroups: aircraft that have incorporated the forward fin spar modification kit Piper P/N 764427 or the CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑157‑02 are treated differently for inspection scheduling, while aircraft that incorporate fuselage bulkhead assembly P/N 77553‑06 or CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑157‑02 are excluded from the 300‑hour inspection requirement. Operators who have not installed those parts or schemes will need to plan for more frequent inspections and earlier replacement of parts and thus bear increased maintenance activity. Parts suppliers and repair facilities that hold or provide CASA‑approved repair scheme drawings Drg. 01‑B‑422, AV‑157‑02, AV‑151‑02 are affected because installation of those schemes alters the regulatory burden for a given aircraft.

The AD further affects record‑keeping and airworthiness documentation practice because Compliance prescribes inspections "at each scheduled maintenance event for the issue of a maintenance release" for a subset of aircraft. That language places the duty to demonstrate compliance in the maintenance records maintained by the person certifying the maintenance release. The background notes reference prior amendments and USA FAA ADs and Piper Service Bulletins, so entities that operate across jurisdictions or that maintain compliance with FAA ADs as well as CASA directives will need to reconcile the different but related documents, particularly for the serial numbers and once‑only inspections that Amendment 6 cancels.

Duties are expressed in numbered Requirement items and in the Compliance column. The principal duties are:

• Requirement 1: Gain access to the vertical fin forward spar attachment plate P/N 77553‑05 by removing the lower fin fairing and visually inspect for signs of movement, cracking and/or clamping witness marks in the vicinity of the fin forward spar attachment to the fuselage. This duty requires physical access and a visual appraisal prior to any further action.

• Requirement 2 (as amended): Remove the vertical fin and, using a dye penetrant method, inspect for cracks in (a) the fin forward spar in the vicinity of attachment plate P/N 77553‑05; (b) was cancelled by Amendment 6; (c) the front and rear faces of bulkhead P/N 77553‑02 in the vicinity of rivets that attach plate P/N 77553‑05 and adjacent flange radius. The text requires both removal of the fin and a specified non‑destructive testing technique for certain structural faces.

• Requirement 3: Replace the fin forward spar attachment plate Piper P/N 77553‑05. Replacement is mandatory and subject to life limits in the Compliance column.

Compliance obligations and conditional pathways are set out clearly:

• For aircraft without the forward fin spar modification kit Piper P/N 764427 or without the CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑157‑02, Requirement 1 and Requirement 2(a) must be performed at each scheduled maintenance event that issues a maintenance release.

• For aircraft without fuselage bulkhead assembly P/N 77553‑06 or the CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑157‑02, Requirement 2(c) must be performed at intervals not exceeding 300 hours time in service.

• For replacement cycles of the fin forward spar attachment plate P/N 77553‑05, aircraft without CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑151‑02 must replace the plate at intervals not exceeding 3000 hours time in service; aircraft that incorporate that CASA‑approved repair scheme must replace at intervals not exceeding 5000 hours time in service.

Rights or alternative compliance possibilities are also explicit in the text. The AD gives credit where a CASA‑approved repair scheme or a specific part assembly is already incorporated, reducing inspection frequency or extending plate replacement intervals. The AD also cross‑references Piper SB 745 Parts I, II and III and USA FAA AD 82‑27‑08(a)(1),(a)(2) and (a)(4), so compliance may be demonstrated by following those referenced service documents where applicable. Amendment 6 cancels Requirement 2(b) because it was a once‑only inspection in prior guidance (Piper SB No. 628A and USA AD 78‑26‑06) that only applied to aircraft up to serial number 38‑78A0749; the cancellation therefore removes that obligation for aircraft outside that specific historic scope. The AD sets out the distinct combination of duties and conditional credits; it does not, within the text provided, set out any appeal process or formal exemption mechanism beyond the CASA‑approved repair scheme pathway named.

The text of the directive does not specify statutory penalties, fines or criminal sanctions for non‑compliance within its printed requirements. It is an AD issued under the authority of a Delegate of the Civil Aviation Safety Authority, and the document records the effective date as 18 December 2008 with the signature line "David Villiers, Delegate of the Civil Aviation Safety Authority" dated 6 November 2008. The presence of a CASA delegate‑signed AD places it within CASA's regulatory architecture for airworthiness, but the AD text as supplied does not enumerate administrative or criminal penalties, nor does it specify an enforcement procedure or the remedies that CASA will apply in cases of breach.

Because the instrument uses mandatory language in "Requirement" and "Compliance" columns, operators and maintenance organisations will be required by regulatory practice to demonstrate compliance when presenting the aircraft for airworthiness certification and maintenance release. The AD refers to CASA‑approved repair schemes and to Piper and FAA service bulletins and ADs as compliance pathways or cross‑reference material, which implies that CASA will treat adherence to those documents as meeting the AD. The AD text does not describe monitoring, audit or enforcement steps, and it does not provide a mechanism for exemption or variation within the page of text supplied.

Practically, enforcement of ADs is undertaken by the airworthiness authority and its inspectors under their broader statutory powers. That context is not set out in this AD text, and the document does not state any specific penalty amounts, suspension rules or enforcement timelines. The AD does, however, create enforceable maintenance obligations for the specified serial numbers through the Requirements and Compliance instructions; establishing a maintenance release without having performed the required inspections or replacements would therefore expose the person issuing that release to regulatory consequences under CASA's general enforcement framework, although those consequences are not detailed in the AD itself.

The AD explicitly cross‑references and aligns with other safety‑of‑flight instruments and manufacturer service material rather than setting out a broad interaction with statutes. It names Piper Service Bulletin SB 745 Parts I, II and III, and USA FAA AD 82‑27‑08 (specifically paragraphs (a)(1), (a)(2) and (a)(4)) as related documents in the Requirement text. The background notes record that Amendment 6 cancels a prior requirement based on Piper SB No. 628A and USA AD 78‑26‑06, and that the AD changes a reference from USA AD 81‑04‑07 to 82‑27‑08. The Compliance text relies on CASA‑approved repair scheme drawings (Drg. 01‑B‑422, AV‑157‑02, AV‑151‑02) to create alternative compliance routes and to change inspection and replacement intervals.

These cross‑references mean the AD functions as part of a network of airworthiness directives and service bulletins; aircraft that have complied with particular SBs or FAA ADs, or that have adopted CASA‑approved repair schemes, receive explicit credit or different intervals under this AD. The AD therefore interacts with the regulatory regime by recognising approved repair schemes issued or approved by CASA, and by aligning with corresponding FAA ADs and Piper service material for the same structural area. For operators who maintain compliance across jurisdictions, the text signals that possessing certain work performed to the Piper SBs or FAA ADs will be accepted in Australia where the CASA‑approved repair schemes are present.

The directive does not reference any civil aviation statutes by citation, nor does it reference criminal or administrative penalty regimes in the text provided. It does not identify interaction with employment law, contract law, insurance law or other regulatory instruments beyond the named FAA ADs, Piper service bulletins and CASA repair scheme drawings. It therefore operates as a targeted safety directive that relies on and recognizes existing service and AD material as the mechanism to achieve conformity, rather than creating an integrated set of cross‑statutory obligations within the page of text supplied.

Amendment history is set out in the Background and the header information. The document is presented as "AD/PA‑38/7 Amdt 6" and records that it is Amendment 6 to the original AD. The effective date of this Amendment 6 is 18 December 2008 and the AD is signed by a CASA delegate on 6 November 2008. The background notes describe the content of Amendment 5 and the changes made by Amendment 6. According to the background text, Amendment 5 relieved some of the repetitive inspections in the area of the fin forward spar attachment and extended the repeat replacement interval of the fin forward spar attachment plate to 5000 hours for aircraft with the CASA‑approved reinforcement. That extension reflected similarity with Piper Service Bulletin SB 710.

Amendment 6 makes three principal changes which the background identifies: first, it cancels Requirement 2(b) on the basis that the once‑only inspection described in Piper SB No. 628A and USA AD 78‑26‑06 applied only to aircraft with serial numbers up to 38‑78A0749; second, it provides credit for fuselage bulkhead assembly P/N 77553‑06 at Requirement 2(c) to match USA AD 82‑27‑08 (a)(2); and third, it updates a reference from USA AD 81‑04‑07 to USA AD 82‑27‑08. The background therefore records the evolution from earlier amendment content (relief and interval extension in Amendment 5) to the specific tailoring and reference updates in Amendment 6, including the cancellation of an inspection obligation that had been limited by serial number in older material.

The header repeats the AD identity (AD/PA‑38/7 Amdt 6) and a short title "Fin Forward Spar Attachment - Inspection, Modification and Life Limit" together with the issue date "13/2008" and the effective date. The AD also includes a short "Note" in the Requirement text pointing maintenance readers to Piper SB 745 Parts I, II and III and to FAA AD 82‑27‑08(a)(1), (a)(2) and (a)(4) for related material. The amendment history is therefore constrained to the AD numbering, the stated reasons for change, the specific cancellations and credits, and the alignment to US FAA material, as recorded in the AD's Background paragraph.

The AD text supplied contains no reference to any litigation or legal proceedings, and it names no cases. It cites FAA ADs and Piper Service Bulletins as technical and regulatory cross‑references, but it does not mention judicial review, administrative appeals, or any court decisions concerning this AD. The instrument is an administrative airworthiness directive issued by a Delegate of the Civil Aviation Safety Authority and the only legal or quasi‑legal act recorded on the face of the document is the Delegate's signature and the effective date.

Because the AD does not list any enforcement outcomes, penalties, or litigation matters, the document is silent on any historical court challenges, compliance disputes, or contested interpretations arising from its issuance. The background explains the practical reasons for Amendment 6 in terms of cancelling a previously applicable once‑only inspection and aligning cross‑references, but it does not indicate that these choices were the product of litigation or legal constraints. In short, there is no litigation history contained within the supplied text to summarise, and no cases are named that would indicate prior judicial consideration of the AD.

Where parties need to assess precedent or contested interpretations of similar directives, they will need to look beyond this AD text to CASA enforcement records, court decisions or tribunal files, none of which are referenced in the AD as printed. The document itself remains a technical regulatory instrument without embedded litigation material.

Several specific operational and administrative pitfalls are implicit in the directive's wording and amendment history. First, the AD is narrowly applicable by serial number "All model PA‑38‑112 with S/Nos. 38‑78A0001 to 38‑80A0198." Operators must verify that the aircraft's serial number falls within that range before applying the AD requirements. Confusion can arise because Amendment 6 cancels a once‑only inspection that previously applied only to aircraft with serial numbers up to 38‑78A0749; operators with aircraft in that narrower historic subset must confirm whether that earlier once‑only inspection has been performed and recorded, otherwise the cancellation may not provide relief.

Second, the conditional compliance framework depends on accurate identification of installed parts and repair schemes. The AD gives altered inspection frequencies and life limits where aircraft incorporate the forward fin spar modification kit Piper P/N 764427, fuselage bulkhead assembly P/N 77553‑06, or CASA‑approved repair scheme drawings Drg. 01‑B‑422, AV‑157‑02 and AV‑151‑02. Operators must ensure maintenance records, parts manifest and logbooks clearly record these installations to secure the credit the AD provides. Absent clear records, an operator cannot rely on the reduced inspection cadence or extended life limit.

Third, procedural content can be overlooked. Requirement 1 requires removal of the lower fin fairing to access plate P/N 77553‑05 for a visual inspection for movement, cracking and clamping witness marks; Requirement 2 requires removal of the vertical fin and a dye penetrant inspection in specific locations. These tasks are time‑consuming and may require scheduled shop visits, jigs or specialized non‑destructive testing capability. Operators planning maintenance releases must account for the additional labour and possible out‑of‑service time.

Fourth, part numbers and drawings are precise. Replacement is to Piper P/N 77553‑05; the AD does not supply alternatives. Similarly, CASA‑approved repair scheme drawings are specified by number. Substituting different parts or schemes without CASA approval will not generate the credits described in the Compliance column.

Fifth, recordation requirements are implicit in the instruction to inspect "at each scheduled maintenance event for the issue of a maintenance release." Failure to document the inspection when issuing the maintenance release may leave the operator exposed during audits. Finally, the AD references Piper SB 745 Parts I, II and III and FAA AD 82‑27‑08; operators relying on those external documents must ensure they consult the correct paragraphs referred to in this AD and reconcile any differences between the referenced documents and the AD's conditional compliance pathways.

Follow the AD's numbered Requirements and the Compliance column precisely and ensure traceability in records. Practical steps based on the AD text are:

1. Applicability check. Confirm the aircraft is within the serial number range 38‑78A0001 to 38‑80A0198. If it is not within that range, the AD as printed does not apply.

2. Requirement 1 (visual inspection). Gain access to the vertical fin forward spar attachment plate P/N 77553‑05 by removing the lower fin fairing. Perform a visual inspection for signs of movement, cracking and/or clamping witness marks in the vicinity of the fin forward spar attachment to the fuselage. Record the inspection in the maintenance records associated with the maintenance release.

3. Requirement 2(a) and 2(c) (non‑destructive testing). Remove the vertical fin. Using a dye penetrant method, inspect for cracks in: (a) the fin forward spar in the vicinity of attachment plate P/N 77553‑05; and (c) the front and rear faces of bulkhead P/N 77553‑02 in the vicinity of rivets that attach plate P/N 77553‑05 and in the adjacent flange radius. Note that Requirement 2(b) has been cancelled by Amendment 6; the AD notes that the once‑only inspection in Piper SB No. 628A and USA AD 78‑26‑06 applied only to aircraft with serial numbers through 38‑78A0749 and was cancelled accordingly.

4. Requirement 3 (replacement). Replace the fin forward spar attachment plate with Piper P/N 77553‑05 where replacement is indicated or at the prescribed life‑limit interval set out below. Ensure replacement parts are correct P/Ns and that installation conforms to the manufacturer and CASA‑approved repair scheme details where applicable.

5. Follow the Compliance intervals and conditional rules. If the aircraft does not incorporate the forward fin spar modification kit Piper P/N 764427 or the CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑157‑02, perform Requirement 1 and Requirement 2(a) at each scheduled maintenance event for the issue of a maintenance release. If the aircraft does not incorporate fuselage bulkhead assembly P/N 77553‑06 or the CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑157‑02, perform Requirement 2(c) at intervals not exceeding 300 hours time in service.

6. Plate replacement life limits. For aircraft that 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. For aircraft that incorporate the CASA‑approved repair scheme Drg. 01‑B‑422 and AV‑151‑02, replace the plates at intervals not exceeding 5000 hours time in service.

7. Referenced documents. Consult Piper SB 745 Parts I, II and III and FAA AD 82‑27‑08(a)(1),(a)(2) and (a)(4) for related procedures and context as noted in the AD's Requirement section. Where CASA‑approved repair schemes are referenced (Drg. 01‑B‑422, AV‑157‑02, AV‑151‑02), ensure those repair schemes are properly approved by CASA and that copies are on file for audit or inspection. Record any reliance on those CASA‑approved schemes in the aircraft maintenance records.

8. Record keeping and maintenance release. When inspections or replacements are carried out, document the work in maintenance logs and the maintenance release, noting the part numbers, the inspection method (visual and dye penetrant), the dates, the time in service at which work was done, and any repairs or replacements performed. This is necessary to demonstrate compliance with the AD's instruction that certain inspections occur "at each scheduled maintenance event for the issue of a maintenance release."

9. Implementation timing. Note the AD's effective date is 18 December 2008. Ensure that any compliance scheduling accounts for that effective date and for the life‑limit counting method (hours time in service) used by your maintenance programme.

Adhering strictly to the part numbers, inspection methods and CASA‑approved repair scheme identifiers named in the AD will ensure the conditional compliance credits and life‑limit extensions are properly claimed and supported in the maintenance record.