AD/PA-34/52 Amdt 1 - Control Wheel Attachment

The directive is built on four operational concepts: applicability by serial number and grouping, targeted inspection criteria, mandated corrective works and parts, and fixed compliance windows.

Applicability is narrow and precise. The directive applies to PA‑34‑220T Seneca V aircraft within two small serial number ranges. Group A is 3449042 through 3449292 and Group B is 3449293 through 3449301 (Applicability table). The wording creates two distinct obligations: a pre‑existing modification exemption for Group A aircraft already modified per New Piper SB No. 1139 dated 28 August 2003, and a universal retainer clip installation obligation for both groups (Requirement 1 preface; Requirement 2).

Inspection criteria are concrete and measurable. The control wheel attachment screw must show a minimum of one thread past the end of the nut plate; if thread engagement is insufficient, the screw must be replaced before further flight (Requirement 1.a). The nut plate is to be judged on locking characteristics with an explicit test: if the screw can be fully inserted into the nut plate by hand to the point that only one thread shows past the nut plate, the nut plate must be replaced before further flight (Requirement 1.b). These are pass/fail tests that determine immediate grounding until rectified.

Remedial works specify parts, compound and procedure references. Reassembly must be performed using Loctite thread‑locking compound (Requirement 1.c). The directive mandates installation of retainer clip part number 104687‑002 according to Part II of SB No. 1139A dated 9 April 2004, for both applicability groups (Requirement 2). The directive therefore delegates procedural detail to the manufacturer’s service bulletin, tying legal compliance to adherence to that SB.

Time limits are explicit and short. One action must be performed within 25 hours time in service after 11 August 2004 and the other within 100 hours time in service after that date (Compliance: 1-2). The AD was amended to correct a reference within Requirement 1 to SB No. 1139A (Background). The directive also cross‑references a corrected FAA AD (Note), indicating harmonisation with an FAA action that prompted the measure.

The directive affects owners, operators and maintenance organisations of the specified Piper PA‑34‑220T Seneca V aircraft within the stated serial number ranges. The two affected groups are defined by serial number range, Group A: 3449042-3449292, and Group B: 3449293-3449301 (Applicability). Group A aircraft already modified in accordance with New Piper SB No. 1139 dated 28 August 2003 are excluded from the Group A inspection requirement, though the retainer clip installation requirement still applies where the aircraft falls within Group A or B (Requirement 1 preface; Requirement 2).

Who pays. The directive itself does not assign financial responsibility, nor does it stipulate funding or subsidy. The described corrective actions and parts are operational costs that must be borne by the operator or owner of the affected aircraft, because the directive requires physical inspection, possible replacement of screw and nut plate, application of Loctite thread‑locking compound, and installation of retainer clip part number 104687‑002 (Requirements 1.a-c, 2). Those actions imply parts costs, maintenance labour costs, and aircraft downtime; the directive sets no cost allowances or exemptions in its text.

Who decides. The directive is issued by the Delegate of the Civil Aviation Safety Authority and becomes effective on the specified date (signature block; effective date). The procedural details for how to carry out the inspections and installations are prescribed by the referenced New Piper Aircraft Service Bulletin No. 1139A dated 9 April 2004, therefore the manufacturer’s SB determines the technical method. Maintenance organisations and certificated engineers will decide scheduling, execution, and documentation consistent with the SB and their regulatory obligations, though those broader regulatory obligations are not set out in this directive text.

Operational impacts on flight and scheduling. The directive mandates that certain aircraft are not to operate further if an inspection fails the stated tests, because replacement of screw or nut plate is required "before further flight" (Requirement 1.a-b). The compliance windows expressed in hours time in service (25 and 100 hours after 11 August 2004) compel operators to schedule inspections within short intervals from that baseline date (Compliance). The directive therefore imposes near‑term maintenance tasks that may require grounding or planned maintenance slots.

Duties are specified and precise. The directive requires, for Group A aircraft except those already modified per New Piper SB No. 1139 dated 28 August 2003: inspect the control wheel attachment screw for proper thread engagement, defined as a minimum of one thread showing past the end of the nut plate, and replace the screw before further flight if insufficient thread engagement is found (Requirement 1.a). It further requires inspection of the nut plate for locking characteristics, with replacement mandated if the screw can be fully inserted by hand to the point where one thread shows past the nut plate (Requirement 1.b). Reassembly must include application of Loctite thread‑locking compound when installing the attachment screw (Requirement 1.c). For both Group A and Group B aircraft the directive requires installation of retainer clip part number 104687‑002 in accordance with Part II of SB No. 1139A dated 9 April 2004 (Requirement 2).

Rights and exceptions are narrowly defined. The directive expressly excludes Group A aircraft that are already modified in accordance with New Piper SB No. 1139 dated 28 August 2003 from Requirement 1 inspection and replacement obligations (Requirement 1 preface). No other exemptions, variances, or alternative means of compliance are specified in the text. The directive refers to the manufacturer’s service bulletin for procedural detail, which provides the technical instructions that a maintenance organisation will follow; the directive does not itself provide alternative methods.

Timing obligations are affirmative and binding in the text. Two compliance windows are set: certain actions must be completed within 25 hours time in service after 11 August 2004, and others within 100 hours time in service after that date (Compliance: 1-2). The directive states that "The compliance times remain unchanged by this issue," which signals that the amendment corrected a reference but did not alter the scheduling obligations (Compliance; Background).

Delegation of technical specificity. The directive delegates procedural implementation to New Piper SB No. 1139A dated 9 April 2004 by instructing compliance "in accordance with Part I" or "Part II" of that SB as applicable (Requirement 1; Requirement 2). This links the legal duty to the manufacturer’s recommended methods, materials and part numbers. The aircraft owner or operator has the duty to ensure the specified actions are performed per the SB and within the stated compliance windows. The directive does not itself describe recordkeeping, approval processes for maintenance, or documentation required; those matters are not addressed in the text.

The directive text provided does not include express penalty clauses, monetary fines, or criminal sanctions, nor does it detail administrative enforcement mechanisms. The instrument sets out mandatory technical actions, compliance times and an effective date, and it is issued by the Delegate of the Civil Aviation Safety Authority (signature block; effective date). The directive also notes it refers to the corrected FAA AD 2004‑14‑12 Amendment 39‑13721 (Note), but no enforcement provisions from the FAA AD are reproduced in this text.

Because the text does not specify penalties or enforcement procedures, the directive does not itself state what legal consequences will follow non‑compliance. The directive mandates actions to be performed "before further flight" if certain conditions are found (Requirement 1.a-b), which implies operational constraints but does not set out the legal machinery for sanctioning non‑compliance within this document. The only enforcement‑like features within the AD are time‑bound mandatory actions and grounding language by condition, but there is no procedural language on inspections by regulators, audits, or imposition of fines in the provided text.

The amendment note explains that Amendment 1 was issued to correct a reference to the service bulletin version, and that "The compliance times remain unchanged by this issue" (Background; Compliance). The document therefore functions as a prescriptive safety mandate rather than a legislative text with embedded penalty schedules. Any formal enforcement or sanctions would need to be inferred from the broader regulatory framework that governs airworthiness directives and aviation safety, but that broader framework is not contained in this directive text and therefore is not asserted here.

The directive explicitly interacts with manufacturer guidance and an FAA action. It requires compliance "in accordance with Part I" and "Part II" of New Piper Aircraft Service Bulletin No. 1139A dated 9 April 2004 for the substantive inspection and installation tasks (Requirement 1; Requirement 2). The SB therefore supplies the technical procedures and part references that the directive makes mandatory. The directive also refers to a corrected FAA Airworthiness Directive, FAA AD 2004‑14‑12 Amendment 39‑13721, by way of note, and states that Amendment 1 to this Directive was issued in response to the corrected FAA AD which modified certain parts of the text (Note; Background).

The directive does not quote or reproduce statutory aviation safety provisions, nor does it state how compliance with the AD interacts with licensing, continuing airworthiness obligations, or maintenance organisation approvals. It likewise does not indicate whether compliance with the New Piper SB constitutes the sole acceptable method of compliance, or whether alternative means of compliance might be available under other regulatory instruments. The AD does, however, commit to a manufacturer SB as the operative technical standard by specifying that the required actions must be accomplished "in accordance with" parts of the SB, thereby linking the AD to the manufacturer's recommended procedures.

Because the AD cross‑references an FAA AD and a New Piper SB, the practical interaction is that operators must follow the SB procedures to meet CASA's directive, and that the directive reflects or harmonises with an FAA action regarding a similar safety issue (Note; Background). The directive does not state any interaction with other domestic laws, regulations, or international obligations within the text provided. Any such interactions would need to be located in the broader regulatory framework and enforcement regime outside this document.

The provided text records one amendment, labelled Amendment 1 to AD/PA‑34/52. The original directive text contained a reference to New Piper SB No. 1139 dated 9 April 2004 within Requirement 1, and Amendment 1 was issued to correct that reference to "Part I of SB No. 1139A dated 9 April 2004" (Background). The Background section explains that Amendment 1 responds to the issue of a corrected copy of the related FAA AD, and that the only necessary correction in this directive was to change the Requirement 1 text to refer to SB No. 1139A (Background).

The Compliance section states that "The compliance times remain unchanged by this issue" (Compliance). This indicates that the amendment was textual and reference‑correcting rather than substantive to the timing obligations. The amendment document itself became effective on 17 March 2005, and the signature block shows the instrument was signed by David Punshon, Delegate of the Civil Aviation Safety Authority, on 4 February 2005 (effective date; signature).

The directive includes a note that it "refers" to corrected FAA AD 2004‑14‑12 Amendment 39‑13721, signalling that a prior FAA AD revision prompted the need to correct the SB reference in this instrument (Note; Background). No other prior amendments, revocations, or replacements are mentioned in the text. The table header and multiple title repetitions in the supplied text suggest formatting duplicates, but substantively the document registers a single amendment action whose purpose was to align the AD’s reference to the correct version of the New Piper service bulletin.

The instrument as provided contains no record of litigation, no reference to judicial review, and no mention of any court decisions or disputes arising from the directive. The Background describes an accident investigation concerning a different aircraft model, a Model PA‑28‑181, which revealed a control wheel screw issue and led to the corrective action reflected in this directive, but the text does not recount any legal proceedings, appeals, or administrative litigation challenging the directive (Background).

The directive does reference corrective action taken by the FAA in FAA AD 2004‑14‑12 Amendment 39‑13721, and it notes the amendment to align the Australian directive with the corrected FAA AD (Note; Background). However, there is no mention within this directive of any litigation around the FAA AD nor of any legal challenge to the CASA delegate’s issuance of this AD. Given the absence of litigation material in the text, no cases, remedies, or disputes are recorded in this document.

Several specific features of the directive present operational or compliance pitfalls that operators and maintenance organisations should note, based on the strict wording of the text.

Narrow serial number applicability. The directive is limited to specific PA‑34‑220T Seneca V serial number ranges: Group A 3449042-3449292, Group B 3449293-3449301 (Applicability). Operators must verify serial numbers carefully. Misreading the serial number ranges could result in failing to apply the AD where it applies, or unnecessarily applying it where it does not.

Exception carve‑out for prior modification. Group A aircraft "already modified in accordance with the New Piper Aircraft Service Bulletin (SB) No. 1139, dated 28 August 2003" are excepted from Requirement 1 inspection and replacement obligations, but the text requires retainer clip installation for Group A or Group B aircraft nonetheless (Requirement 1 preface; Requirement 2). Operators must confirm the precise SB referenced and whether the aircraft has the earlier modification. The amendment changes the required SB reference to SB No. 1139A dated 9 April 2004 for the mandatory work, so documentation of prior SB compliance must be clear and specific.

Tight compliance windows. The instrument requires completion of certain tasks within 25 hours time in service after 11 August 2004 and other tasks within 100 hours time in service after 11 August 2004 (Compliance: 1-2). Although the amendment text states that the compliance times remain unchanged, the dates create a short window that may have already passed by the time an operator reads the directive. The directive does not provide a calendar date equivalent or alternative scheduling; the mandated hours‑in‑service basis must be applied from the 11 August 2004 baseline.

Concrete pass/fail inspection criteria. The inspection tests are literal: minimum one thread showing past the end of the nut plate is required for the screw, and if the screw can be fully inserted by hand to the point of one thread showing past the end of the nut plate, then the nut plate must be replaced (Requirement 1.a-b). Those tests are specific and do not provide for subjective judgment; operators and maintenance personnel must apply the measurement precisely and document the outcome.

Binding technical reference. The directive requires the work be done "in accordance with Part I" and "Part II" of New Piper SB No. 1139A dated 9 April 2004 (Requirement 1; Requirement 2). The AD does not reproduce procedural detail, and it does not state whether alternatives to the SB are permissible. If a maintenance organisation relies on an alternative approved method, that alternative is not authorised by this document’s text.

Parts specification. The retainer clip is specified by part number 104687‑002 (Requirement 2). Using an incorrect part number or an equivalent without explicit authority would not satisfy the literal wording of the directive. The directive does not provide latitude for substitution within its text.

No enforcement detail. The AD contains no stated penalties, enforcement process, or administrative review mechanism (Penalties and enforcement). Operators should not assume the absence of stated penalties equals absence of regulatory consequences, but the directive itself does not articulate those consequences.

Reference corrections. Amendment 1 was issued to correct the SB reference to SB No. 1139A dated 9 April 2004, and the AD notes that it refers to the corrected FAA AD (Background; Note). Operators relying on earlier drafts or versions of the SB must ensure they are using the SB version specified in the AD.

Follow the directive's mandatory steps and the referenced New Piper SB parts exactly, and complete the work within the stated time limits.

Step 1, identify applicability. Confirm the aircraft model and serial number. If the aircraft is a PA‑34‑220T Seneca V within serial numbers 3449042-3449292 (Group A) or 3449293-3449301 (Group B), the AD applies (Applicability). If a Group A aircraft has already been modified under New Piper SB No. 1139 dated 28 August 2003, Requirement 1 inspection and replacement is excepted for that aircraft, but the retainer clip installation per Part II of SB No. 1139A remains required (Requirement 1 preface; Requirement 2).

Step 2, consult the mandated technical source. Obtain New Piper Aircraft Service Bulletin No. 1139A dated 9 April 2004 and identify Part I and Part II. The AD requires work "in accordance with" those parts, therefore follow the SB’s procedural steps, torque values, hardware specifications and any special tools identified by the SB (Requirement 1; Requirement 2).

Step 3, perform the Group A inspection tasks (where applicable). For Group A aircraft not already modified per the earlier SB, inspect the control wheel attachment screw for thread engagement, confirming at least one thread shows past the end of the nut plate. If the inspection shows insufficient engagement, replace the screw before further flight. Inspect the nut plate for locking characteristics, and if the screw can be fully inserted by hand leaving one thread past the end of the nut plate, replace the nut plate before further flight. On reassembly, install the attachment screw using Loctite thread‑locking compound as specified (Requirement 1.a-c).

Step 4, install the retainer clip for Group A and Group B. Install retainer clip part number 104687‑002 in accordance with Part II of SB No. 1139A dated 9 April 2004 on every Group A or Group B aircraft within the applicability ranges (Requirement 2).

Step 5, meet timing constraints. Complete the specified tasks within 25 hours time in service and within 100 hours time in service after 11 August 2004 as the AD specifies for the relevant actions (Compliance: 1-2). Identify which action maps to which time limit by consulting the SB and the AD wording, and document hours in service calculations to demonstrate compliance.

Step 6, document the work. Although the AD text does not state recordkeeping requirements, best practice in applying an AD is to retain maintenance records, parts invoices (notably for retainer clip P/N 104687‑002 and any replacement screws or nut plates), and references to the SB work cards used. The AD itself binds the work to SB No. 1139A dated 9 April 2004, so retaining a copy of that SB and the maintenance entry that records compliance will show the operator implemented the AD’s requirements as written.

Step 7, confirm conformity with the AD text. Ensure the inspection results meet the literal pass/fail criteria the AD sets: one thread beyond nut plate is the minimum for the screw; hand‑insertable screw past one thread on the nut plate is a fail that requires replacement. Ensure the retainer clip installed matches part number 104687‑002. Use Loctite thread‑locking compound when reinstalling the screw as the AD mandates (Requirement 1.a-c; Requirement 2).

Step 8, check for amendment or related directives. The AD was amended to reference SB No. 1139A dated 9 April 2004 in response to a corrected FAA AD; ensure that the SB version used matches the AD’s citation and that any FAA or manufacturer revisions that the AD expressly adopts are the ones followed (Background; Note).

The AD is effective as issued by the Delegate of the Civil Aviation Safety Authority and became effective on 17 March 2005 (effective date). Complete the prescribed works exactly as required by the AD text and the SB to satisfy the directive’s explicit obligations.