AD/PA-28/96 Amdt 1 - Control Wheel Attachment

This instrument is narrowly technical and operation‑specific. The main concepts are as follows, reflected directly in the AD text:

• Applicability by model and serial number: the AD separates affected aeroplanes into Group A and Group B, each defined by model (PA-28-161 Warrior III, PA-28-181 Archer III, PA-28R-201 Arrow) and precise serial number ranges (Applicability). Those serial ranges determine which aircraft must undergo the Part I inspection and/or the retainer clip installation.

• Inspection threshold for thread engagement: the AD defines a quantitative minimum for acceptable thread engagement on the control wheel attachment screw, “minimum one thread showing past the end of the nut plate” (Requirement 1a). If inspection finds less than this engagement, the screw must be replaced “before further flight” (Requirement 1a).

• Nut plate locking characteristic test and replacement criterion: inspectors must check the nut plate’s locking characteristics, with a simple physical test set out in the AD. If “the screw can be fully inserted into the nut plate by hand (one thread showing past end of nut), then replacement of the nut plate is required before further flight” (Requirement 1b). The AD therefore uses a pass/fail mechanical test as the decision rule.

• Use of thread‑locking compound: after the inspection/replacement steps, reassembly must include the attachment screw installed with Loctite thread‑locking compound (Requirement 1c). The AD prescribes a specific installation practice, not simply inspection.

• Addition of a retainer clip: for both Group A and Group B aircraft the AD requires installation of retainer clip part number 104687-002 per Part II of SB No. 1139A (Requirement 2). This is a retrofit hardware addition intended to secure the attachment.

• Time‑limited compliance windows expressed in hours-in-service after a specific date: the AD specifies two compliance intervals, “Within 25 hours time in service after 11 August 2004” and “Within 100 hours time in service after 11 August 2004” (Compliance). The AD text lists these two items; the AD reiterates that the compliance times remain unchanged by this amendment.

• Source documents and cross‑references: the AD mandates work in accordance with New Piper SB No. 1139A dated 9 April 2004, and it refers to a corrected FAA AD (Note; Background). The amendment exists to correct the SB reference to 1139A.

These concepts convert a safety finding (screw too short, nut plate ineffective) into prescriptive inspection, replacement and retrofit steps, with explicit acceptance criteria and specified fasteners and compounds. The AD makes both immediate corrective actions (replace before further flight when criteria fail) and a retrofit requirement (retainer clip) compulsory for the identified serial ranges.

The AD affects a defined subset of Piper PA-28 series aeroplanes and the people and organisations that operate, maintain, own or certify them. The affected models and serial ranges are set out under the Applicability heading and split into Group A and Group B. Group A includes the following models and serial numbers: PA-28-161 Warrior III serials 2842026 through 2842180; PA-28-181 Archer III serials 2843112 through 2843565; PA-28R-201 Arrow serials 2844014 through 2844099. Group B covers PA-28-161 Warrior III serials 2842181 through 2842203; PA-28-181 Archer III serials 2843566 through 2843588; PA-28R-201 Arrow serials 2844100 through 2844104 (Applicability).

Owners and operators of aircraft in Group A must either confirm their aircraft were already modified in accordance with New Piper SB No. 1139 dated 28 August 2003, in which case an exception applies for Requirement 1, or they must carry out Part I of SB No. 1139A dated 9 April 2004 (Requirement 1). Owners and operators of aircraft in either Group A or Group B must have the retainer clip (part number 104687-002) installed per Part II of SB No. 1139A (Requirement 2).

Maintenance organisations and certificated mechanics who perform the inspections, replacements and installation will be directly engaged. Because the AD requires actions “in accordance with” Parts I and II of SB No. 1139A, those carrying out the work must have access to and follow those SB procedures verbatim (Requirement).

Flight crews and operators are affected operationally because deficient screws or nut plates must be replaced “before further flight” when found, creating an immediate grounding effect until rectified (Requirement 1a-b). The AD’s compliance timeframes are expressed in hours time in service after 11 August 2004, so operators must review flight logs to determine whether the work is yet due and act within the specified hours (Compliance).

Regulatory and certification contacts are also involved. The AD is issued by the Civil Aviation Safety Authority (CASA) and is signed by a delegate, David Punshon (signature block). The AD references a related FAA AD and the New Piper SBs, so international maintenance record reconciliation may be necessary for operators who rely on prior modifications or on FAA compliance records (Note; Background).

Finally, the AD affects parts suppliers and spare stock holdings. The retainer clip specified by part number 104687-002 and replacement screws and nut plates must be sourced to accomplish the mandated work (Requirement 2; Requirement 1a-b). The AD does not specify supply channels or price, but it creates a short-term demand for these parts among the owners/operators of the listed serial ranges.

The AD imposes discrete duties, and it contains a narrow exception. The duties are stated in the Requirement block and the Compliance block.

Duties:

• For Group A aircraft (except those already modified per New Piper SB No. 1139 dated 28 August 2003), carry out Part I of New Piper SB No. 1139A dated 9 April 2004. Part I duties comprise: inspect the control wheel attachment screw for proper thread engagement with the pass criterion “minimum one thread showing past the end of the nut plate,” and if insufficient engagement is found, replace the screw before further flight; inspect the nut plate for sufficient locking characteristics, and if the screw can be fully inserted into the nut plate by hand (one thread showing past end of nut), replace the nut plate before further flight; reassemble the control wheel onto the control wheel shaft and install the attachment screw using Loctite thread‑locking compound (Requirement 1 a-c).

• For both Group A and Group B aircraft, install retainer clip part number 104687-002 in accordance with Part II of SB No. 1139A dated 9 April 2004 (Requirement 2).

• Meet the AD’s compliance timeframes: the AD specifies two timetables, “Within 25 hours time in service after 11 August 2004” and “Within 100 hours time in service after 11 August 2004,” which the AD lists numerically as items 1 and 2 in the Compliance block (Compliance). The AD notes the compliance times remain unchanged by this amendment.

Operational effect of the duties:

• Where an inspection fails the specified pass criteria, the AD requires replacement “before further flight” (Requirement 1a-b). This language creates an immediate operational obligation to remedy the defect prior to any subsequent flying.

Rights and exceptions:

• The AD provides a specific exception: a Group A aircraft that is already modified in accordance with New Piper SB No. 1139 dated 28 August 2003 is excluded from the Requirement 1 Part I inspection/replacement sequence (Requirement 1 preface). That is a narrow affirmative exemption for a particular prior modification status; the AD still requires installation of the retainer clip (Requirement 2) for Group A or B.

Procedural obligations:

• The AD mandates that the work be accomplished “in accordance with” Parts I and II of SB No. 1139A dated 9 April 2004 (Requirement). This ties the duty to a specified service bulletin, so compliance is measured against that document’s procedures and not against ad hoc measures.

What the AD does not state as a right:

• The AD text does not set out an appeal route, a compliance relief mechanism, or an administrative variance procedure within the text itself. It also does not state penalties or enforcement mechanisms in the document body. The AD does make clear which physical outcomes are acceptable and which are not, and it sets unambiguous “before further flight” obligations for failed inspections.

Record keeping implication:

• Although the AD does not expressly set record-keeping formalities, the nature of compliance,actions required “in accordance with” a specified SB and with time-in-service deadlines,implies that operators and maintenance organisations must be able to demonstrate that the inspections, replacements and installations were accomplished within the stated timeframes and per the SB procedures.

The AD text does not set out monetary penalties, criminal sanctions or a detailed enforcement procedure. The document is framed as a CASA airworthiness directive, signed by a CASA delegate (David Punshon), and it states mandatory actions and deadlines; it therefore carries the practical enforcement implication that aircraft must not operate in non‑compliant condition, particularly because failures detected by inspection must be corrected “before further flight” (Requirement 1a-b; signature block). The AD’s imperative language,“replace … before further flight,” “required,” “install … in accordance with” and specific compliance windows,creates operating prohibitions until remedial action is taken.

Concrete enforcement features apparent from the AD text:

• Immediate operational restriction for defective hardware. If an inspection finds insufficient thread engagement or an ineffective nut plate, the AD requires replacement before the aircraft can fly again (Requirement 1a-b). That is an operational enforcement mechanism because it directly prevents lawful further flight absent correction.

• Prescriptive source documents. The AD requires compliance “in accordance with” Parts I and II of SB No. 1139A dated 9 April 2004 (Requirement). That instruction narrows what constitutes compliant action and allows regulators and certifying authorities to judge compliance against the SB text.

What the AD does not record:

• The AD does not list specific penalties or fines for non‑compliance. The document does not describe administrative processes such as notification, grace periods beyond the stated hours-in-service windows, or appeals. The text also does not specify which enforcement body will take action in the event of non-compliance, nor does it detail investigative or enforcement steps.

Implications for operators and maintenance organisations:

• Because the AD prescribes corrective action “before further flight” where a defect is found, operators have the immediate compliance burden to ground a non‑conforming aircraft until repaired. That creates a direct commercial cost,downtime, maintenance labour, parts procurement,although the AD does not quantify those costs.

• Documentation and audit risk are implicit. An operator who cannot demonstrate compliance with the specific SB parts and the AD compliance windows may face enforcement action under the broader CASA regulatory framework, but the AD itself does not specify the process or penalties.

In sum, the AD imposes mandatory corrective and retrofit duties with immediate operational effect on aircraft found to be deficient, but it leaves the specific penalties and enforcement procedures outside the AD’s text.

The AD explicitly cross‑references other regulatory and manufacturer instruments and thus interacts with them as follows:

• New Piper Service Bulletin (SB) No. 1139 and 1139A: The AD requires actions “in accordance with Part I of SB No. 1139A dated 9 April 2004” for the Group A inspection/replacement sequence and “in accordance with Part II of SB No. 1139A dated 9 April 2004” for the retainer clip installation (Requirement 1; Requirement 2). It also recognises an earlier New Piper SB No. 1139 dated 28 August 2003 by providing an exception for Group A aircraft already modified to that SB standard (Requirement 1 preface). The AD thus makes compliance effectively conditional upon following those SB documents; those SBs become the procedural standard against which the AD actions are to be carried out.

• FAA airworthiness directive (corrected FAA AD 2004-14-12 Amdt 39-13721): the AD contains a note that the corrected FAA AD is relevant, and the Background explains that Amendment 1 (this document) was issued in response to a corrected copy of the related FAA AD which corrected certain parts of the text (Note; Background). That establishes an international regulatory link: CASA’s AD references, and was adjusted to align with, the FAA’s corrective action on the same safety issue.

• Existing AD/PA-28/96: The heading identifies this as AD/PA-28/96 Amendment 1. That shows the document is an amendment to a prior AD with the same base number. The AD states the amendment corrects the reference to Part I of the SB from “SB No. 1139 dated 9 April 2004” to “SB No. 1139A dated 9 April 2004” (Background). Therefore, this instrument modifies or clarifies existing regulatory obligations rather than creating an entirely new compliance program.

• Operational airworthiness and “before further flight” restrictions: The AD’s requirement that defective parts be replaced “before further flight” interacts directly with operational safety duties under broader aviation safety law and airworthiness certification principles, insofar as the AD sets a mandatory remediation threshold that prevents lawful flight where the defect exists (Requirement 1a-b). While the AD text does not restate the broader statutory enforcement apparatus, the directive’s wording is intended to be read and applied within that regulatory environment.

• Parts and maintenance standards: By specifying part number 104687-002 for the retainer clip and requiring use of Loctite thread‑locking compound during reassembly, the AD narrows acceptable maintenance practices and spare parts to particular items and materials (Requirement 1c; Requirement 2). That interacts with aviation maintenance procedures and parts inventory practices, and may require operators to reconcile their spare parts holdings with the AD’s specified part numbers.

What the AD does not do, as per its text:

• The AD does not amend aviation safety legislation or other statutory instruments within the text. It does not purport to change certification of the aircraft models, nor does it explicitly alter pilot licensing or operational regulations. It is narrowly focused on the hardware defect and the remedial/retrofit instructions.

In short, the AD functions as a focused regulatory instrument that links CASA’s mandatory directive to specific manufacturer SBs and a related FAA AD. Compliance necessarily involves following those SBs and installing specified parts and materials, and it interfaces with existing airworthiness compliance obligations.

The document before you is titled AD/PA-28/96 Amdt 1, indicating it is an amendment to an earlier AD numbered AD/PA-28/96. The amendment’s stated purpose and the specific history contained in the AD are as follows:

• Reason for amendment: Amendment 1 was issued in response to a corrected copy of the related FAA AD, which corrected certain parts of the text. The AD says the only part requiring correction in the directive was the wording of Requirement 1, which originally read “Part I of SB No. 1139 dated 9 April 2004” and was changed to “Part I of SB No. 1139A dated 9 April 2004” (Background). The amendment therefore corrects a reference to the service bulletin number.

• Effective date: The AD states that this amendment becomes effective on 17 March 2005 (Compliance; Effective date line).

• Date and signature: The AD is signed and dated (4 February 2005) by David Punshon, Delegate of the Civil Aviation Safety Authority (signature block). The signature and date indicate the administrative action and delegation under which the amendment was issued.

• Relationship to prior materials: The AD explicitly cross‑references New Piper SB No. 1139 dated 28 August 2003 (as an exclusion for some Group A aircraft) and SB No. 1139A dated 9 April 2004 (as the operative procedural reference) (Requirement 1 preface; Requirement). The amendment clarifies that Part I actions must be performed in accordance with SB No. 1139A dated 9 April 2004.

• Compliance times unchanged: The AD notes explicitly that “The compliance times remain unchanged by this issue” (Compliance). That language indicates that the amendment was not intended to alter the operational deadlines already set in the original AD; rather, it only corrected the textual reference to the SB number.

• Reference to FAA correction: The AD includes a note that the corrected FAA AD 2004-14-12 Amdt 39-13721 refers, and the Background makes clear that the FAA correction prompted the amendment to this CASA AD (Note; Background).

What the AD does not record about amendment history:

• The AD text does not include any earlier amendment dates beyond the numbering, any discussion of secondary amendments, or a history log. It does not provide a tracked list of earlier versions or the initial issue date of AD/PA-28/96. The document’s amendment history is limited to the explanation that Amendment 1 corrects the SB reference and leaves compliance times unchanged.

For users reconciling compliance records, the amendment history implies two things: first, if compliance actions were logged against an earlier SB reference, operators should verify the SB number actually used (1139 versus 1139A); second, the substantive required actions and timeframes were not changed by Amendment 1, so prior compliance taken in line with the original deadlines remains relevant but should be recorded against the correct SB reference where necessary.

The AD text contains no record of litigation, legal challenges, court decisions, or administrative appeals concerning AD/PA-28/96 or this Amendment 1. The only judicial-type content present in the document is the procedural history explaining that Amendment 1 was issued in response to a corrected FAA AD and to correct a cross-reference to the New Piper SB No. 1139A (Background).

Therefore, based solely on the supplied text:

• There is no litigation history mentioned.
• There are no citations to court decisions or administrative rulings.
• There are no recorded appeals or disputes referenced.

Users seeking to know whether this AD has been litigated, cited in decisions, or otherwise the subject of legal proceedings must consult extrinsic sources beyond the AD text provided here. The AD itself limits its historical notes to the technical correction and the rationale tied to the FAA correction.

The AD’s concise technical language nonetheless contains several practical pitfalls and potential sources of compliance error. These are drawn strictly from the text of the AD and its structure.

1. Applicability precision and serial number ranges:

   • The AD identifies narrow serial number ranges for Group A and Group B. Operators must match aircraft serial numbers exactly to the listed ranges. Misreading the ranges or misclassifying an aircraft between Group A and Group B will lead to incorrect compliance obligations (Applicability). The AD provides an exception for certain Group A aircraft based on prior modification status; misapplying that exception could leave an aircraft non‑compliant.

2. Exception for prior SB No. 1139 work:

   • 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. The AD does not describe acceptable proof of that prior modification beyond the plain textual statement. Operators must retain and produce documentation that the SB No. 1139 work was actually done, otherwise the exception will not practically shield them from performing Part I of SB No. 1139A (Requirement 1 preface).

3. Ambiguity in the compliance block numbering and attachment:

   • The Compliance block lists two timeframes, “1. Within 25 hours time in service after 11 August 2004” and “2. Within 100 hours time in service after 11 August 2004,” but the AD text does not on its face re-state which numbered Requirement each timeframe applies to. The numerical correspondence between the Compliance items and the Requirement items suggests the first timeframe applies to Requirement 1 and the second to Requirement 2, but practitioners should confirm this by reference to the SB parts and CASA guidance or clarifying material if necessary (Compliance).

4. Precise pass/fail mechanical tests:

   • The AD specifies a minimum “one thread showing past the end of the nut plate” for thread engagement as the pass criterion and also uses “one thread showing past end of nut” as a threshold for nut plate replacement if the screw “can be fully inserted … by hand” (Requirement 1a-b). The language is specific and somewhat repetitive; mechanics must ensure they apply the AD’s exact measurement and the specified manual test rather than a subjective judgment. Misinterpreting “one thread showing past” or inconsistently applying the manual insertion test could lead to improperly retained hardware.

5. Before further flight language:

   • Where inspection fails the criteria, the AD requires replacement “before further flight” (Requirement 1a-b). That creates immediate operational grounding until the issue is fixed. Practitioners should be aware that discovering a deficient screw or nut plate will have direct commercial implications through downtime and possible scheduling disruption.

6. Parts and compound specificity:

   • The AD mandates installation of retainer clip part number 104687-002 and the use of Loctite thread‑locking compound on reassembly (Requirement 1c; Requirement 2). Procuring the specified part number and an acceptable Loctite compound is necessary; substituting an unapproved part number or a non‑specified compound risks non‑compliance.

7. Amendment focus on SB reference:

   • Amendment 1 corrects the SB reference to 1139A. An operator or maintenance organisation that previously recorded compliance against SB No. 1139 dated 9 April 2004 could have a mistaken record. Practitioners must reconcile records to ensure the work performed conforms to SB No. 1139A dated 9 April 2004 if that is what the AD requires (Background).

8. No stated enforcement penalties in the AD text:

   • The AD does not enumerate enforcement actions or monetary penalties. Whilst the directive’s mandatory language and the “before further flight” criteria imply enforcement risk, practitioners should not assume specific penalty amounts or processes from this AD alone (Penalties and enforcement). Clarification from CASA or the regulatory enforcement framework would be needed for precise enforcement expectations.

9. Retainer clip installation for both groups:

   • Some users might assume the retainer clip is only for one group; the AD clearly requires installation for Group A and Group B (Requirement 2). Failing to notice this could leave Group B aircraft non‑compliant.

10. Time-reference for compliance:

• The compliance windows are measured as hours time in service after 11 August 2004. Operators must correctly compute hours‑in‑service since that date, not since the AD issue or effective date (Compliance). Mistakes computing the baseline may misplace compliance obligations.

These items are practical compliance risks and record‑keeping traps implied by the AD’s wording and structure. Addressing them requires careful review of serial numbers, prior SB compliance paperwork, precise mechanical inspection per the AD text, sourcing correct parts, and conservative operational decisions when defects are found.

The AD’s text mandates precise steps “in accordance with” specified parts of New Piper SB No. 1139A dated 9 April 2004. The following is a practical, source‑grounded checklist to achieve compliance, with actions tied to the AD’s numbered requirements and compliance windows. This checklist is strictly an implementation restatement of the AD text.

1. Confirm applicability:

   • Verify the aircraft model and serial number against the Group A and Group B ranges in the Applicability block. Do not proceed without exact serial number matching (Applicability).

2. Determine prior modification status (Group A only):

   • For aircraft in Group A, check maintenance records for evidence that the aircraft was modified in accordance with New Piper SB No. 1139 dated 28 August 2003. If such modification documentation exists, Requirement 1 Part I is excepted for that aircraft, though Requirement 2 (retainer clip) still applies (Requirement 1 preface; Requirement 2).

3. Obtain and follow SB No. 1139A dated 9 April 2004:

   • The AD requires actions “in accordance with” Part I (for Group A) and Part II (for Group A and Group B) of SB No. 1139A dated 9 April 2004 (Requirement). Acquire the SB and ensure maintenance personnel read and follow its detailed procedural steps verbatim.

4. Perform Part I inspections and actions (Group A, unless excepted):

   • Inspect the control wheel attachment screw for proper thread engagement. Use the AD’s criterion: minimum one thread showing past the end of the nut plate. If insufficient thread engagement is found, replace the screw before further flight (Requirement 1a).
   • Inspect the nut plate for locking characteristics. Perform the manual insertion test described: if the screw can be fully inserted into the nut plate by hand such that one thread shows past the end of the nut, replace the nut plate before further flight (Requirement 1b).
   • After replacement or verification, reassemble the control wheel onto the control wheel shaft and install the attachment screw using Loctite thread‑locking compound (Requirement 1c).

5. Perform Part II modification (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 (Requirement 2). Confirm the exact part number during procurement and installation.

6. Observe compliance timeframes:

   • The AD specifies two compliance windows measured in hours time in service after 11 August 2004: “Within 25 hours” and “Within 100 hours” (Compliance). The AD lists these as numbered items. Practically, map the first compliance timeframe to the short‑term inspection/replacement requirement and the second to the retainer clip retrofit, consistent with the AD’s numerical structure, and confirm this mapping by reviewing SB No. 1139A and any CASA guidance. Ensure work is completed within the stated time-in-service windows.

7. Grounding and pre‑flight obligation:

   • If an inspection reveals insufficient thread engagement or an inadequate nut plate, the AD requires replacement “before further flight” (Requirement 1a-b). Treat such a finding as a grounding issue and do not permit further flight until the replacement is completed and reassembly uses the specified thread‑locking compound.

8. Parts, tools and materials:

   • Obtain the specified retainer clip, part number 104687-002, and ensure availability of Loctite thread‑locking compound consistent with SB instructions (Requirement 1c; Requirement 2). Confirm compatibility and part authenticity before installation.

9. Record keeping:

   • Document the inspection results, any replacements made (screw, nut plate), the retainer clip installation including part numbers and batch numbers where applicable, the date and hours time in service at completion, and reference SB No. 1139A dated 9 April 2004 and AD/PA-28/96 Amdt 1. Although the AD does not specify record formats, clear documentation will aid any regulator audit and will be necessary to demonstrate compliance.

10. Reconcile prior records and the amendment:

• Where work was previously done in reliance on New Piper SB No. 1139 dated 28 August 2003, reconcile records to show either that the prior SB work matches the AD exception, or perform the Part I SB No. 1139A actions if no adequate evidence exists (Requirement 1 preface).

11. Consult CASA guidance if uncertain:

• If there is any ambiguity,particularly about which compliance time applies to which Requirement,seek clarification from CASA or consult the full SB text before undertaking or signing off work. The AD notes that compliance times remain unchanged by this amendment, but it does not restate which numbered item maps to which action; confirm mapping before completion (Compliance; Background).

12. Safety verification:

• After reassembly and retainer clip installation, perform the operational checks required by SB No. 1139A and any standard control wheel rigging or control function inspections to confirm no residual free play or abnormal movement exists.

Following these steps, which directly reflect the AD’s own requirements, will place an operator in compliance with the directive’s stated obligations: inspection and replacement where necessary, use of the specified thread‑locking compound, installation of the specified retainer clip, and adherence to the AD’s time‑in‑service limits measured from 11 August 2004.