{"id":"F2005L00206","name":"AD/PA-44/19 Amdt 1 - Control Wheel Attachment","slug":"ad-pa-44-19-amdt-1-control-wheel-attachment","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":33724,"registerId":"commonwealth-F2005L00206-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Piper PA-44 (Seminole) Series Aeroplanes","sectionType":"division","heading":"Piper PA-44 (Seminole) Series Aeroplanes","content":"### Piper PA-44 (Seminole) Series Aeroplanes\n\n| AD/PA-44/19 Amdt 1 | Control Wheel Attachment | 3/2005 |\n| ------------------ | ------------------------ | ------ |\n\n| Applicability: | Group A aircraft:Models Serial NumbersPA-44-180 Seminole 4496020 through 4496173, and 4496175Group B aircraft:PA-44-180 Seminole 4496174 through 4496176, and 4496180                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. For aircraft listed in Group A of the applicability part of this Directive, with the exception of aircraft listed in Group A that are already modified in accordance with the New Piper Aircraft Service Bulletin (SB) No. 1139, dated 28 August 2003; accomplish the following in accordance with Part I of SB No.1139A dated 9 April 2004:a. Inspect the control wheel attachment screw for proper thread engagement (minimum one thread showing past the end of the nut plate), and replace the screw before further flight if insufficient thread engagement is found.b. Inspect the nut plate for sufficient locking characteristics. 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.c. Reassemble the control wheel onto the control wheel shaft and install the attachment screw using Loctite thread-locking compound.2. For aircraft listed in Group A or Group B of the applicability part of this Directive, install retainer clip part number 104687-002 in accordance with Part II of SB No. 1139A, dated 9 April 2004.Note: Corrected FAA AD 2004-14-12 Amdt 39-13721 refers. |\n\n| Compliance: | 1. Within 25 hours time in service after 11 August 2004.2. Within 100 hours time in service after 11 August 2004.The compliance time remains unchanged by this issue.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n|             | This Amendment becomes effective on 17 March 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 |\n| Background: | The FAA received a report that a Model PA-28-181 aircraft crashed after the pilot lost control of the ailerons and elevator. Investigation revealed that the left control wheel single attachment screw had unscrewed from its nut plate, which resulted in the control wheel spinning freely on the control column. Further investigation revealed the screw was too short and the nut plate lacked proper locking characteristics.Amendment 1 is issued in response to the issue of a corrected copy of the related FAA AD, which corrects certain parts of the text. The only part requiring correction of this Directive was Requirement 1. text, “Part I of SB No. 1139 dated 9 April 2004” which was changed to “Part I of SB No. 1139A dated 9 April 2004”. |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n4 February 2005","sortOrder":0},{"sectionNumber":"AD/PA-44/19 Amdt 1","sectionType":"part","heading":"AD/PA-44/19 Amdt 1","content":"## AD/PA-44/19 Amdt 1","sortOrder":1},{"sectionNumber":"Control Wheel Attachment","sectionType":"part","heading":"Control Wheel Attachment","content":"## Control Wheel Attachment","sortOrder":2},{"sectionNumber":"3/2005","sectionType":"part","heading":"3/2005","content":"## 3/2005","sortOrder":3}],"analysis":{"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"},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"This amendment did not expand the substantive scope of the directive. It corrected the cross‑reference to the applicable Service Bulletin (from SB No. 1139 to SB No. 1139A) so that the required actions were clearly tied to the correct SB revision. No additional inspection or modification obligations were introduced."},"complexity_factors":["Two affected groups (Group A and Group B) with overlapping but different requirements (inspection+reassembly for Group A; retainer clip for Groups A and B).","Reference to external documents: New Piper Service Bulletin No. 1139A (Parts I and II) and a corrected FAA AD (cross‑references require users to consult multiple documents).","Conditional exception: Group A aircraft already modified per the prior SB are excluded from Requirement 1 (exception to requirement).","Two different compliance windows (25 hours and 100 hours after a reference date) create sequencing/timing conditions (Compliance).","Specific part number cited (retainer clip PN 104687‑002) requires parts procurement tracking."],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- This airworthiness directive (AD) requires specific inspections and a minor modification to the control wheel attachment on certain Piper PA‑44 (Seminole) aeroplanes. It targets the single screw that secures the control wheel to the control-column shaft and the nut plate that retains that screw. (Requirement 1(a)–(c); Requirement 2.)\n\n- For Group A aircraft that have not already been modified per New Piper Service Bulletin (SB) No. 1139, Part I of SB No. 1139A must be followed to:\n  - inspect the control‑wheel attachment screw for adequate thread engagement and replace the screw if it is too short (insufficient threads past the nut plate) (Requirement 1(a));\n  - inspect the nut plate for proper locking characteristics and replace it if the screw can be fully inserted by hand (Requirement 1(b)); and\n  - re‑install the control wheel using a thread‑locking compound (Loctite) on the attachment screw (Requirement 1(c)).\n\n- For both Group A and Group B aircraft the directive requires installation of a retainer clip, part number 104687‑002, in accordance with Part II of SB No. 1139A (Requirement 2).\n\n- Timing: the inspections/replacements called for in Requirement 1 must be done within 25 flight hours after 11 August 2004; the retainer‑clip installation in Requirement 2 must be done within 100 flight hours after 11 August 2004 (Compliance). The amendment itself became effective 17 March 2005.\n\n**Who this affects**\n\n- Owners and operators of Piper PA‑44‑180 Seminole aeroplanes in the serial number ranges listed for Group A and Group B (Applicability).\n- Aircraft maintenance organisations and certificated mechanics who perform the inspections, part replacements and the retainer‑clip installation called for by the SB (Requirement; Compliance).\n- The regulator (Civil Aviation Safety Authority) enforces compliance with the AD.\n\n**Why it matters (purpose and background)**\n\n- The AD responds to an accident investigation where a similar aircraft lost control because the control‑wheel attachment screw had backed out and the nut plate did not lock properly; the control wheel turned freely on the column (Background). The mandated inspections, retention compound and retainer clip are intended to prevent recurrence by ensuring sufficient thread engagement, adequate nut‑plate locking, and secondary retention.\n\n**Costs, incentives and trade‑offs (practical effects)**\n\n- Who pays: aircraft owners/operators pay for labour, any replacement screws or nut plates that fail inspection, the retainer clip (PN 104687‑002), and associated downtime (Requirement; Compliance).\n- Behaviour change: maintenance providers must inspect and, where necessary, replace parts and apply thread‑locking compound; operators must schedule aircraft out of service within the specified compliance windows.\n- Implementation risk and compliance burden: the work is procedural and based on an FAA‑issued service bulletin (SB No. 1139A). Risks are: availability of the correct parts; correct interpretation and execution of the SB; and record‑keeping to show compliance. These are standard maintenance burdens rather than discretionary regulatory obligations.\n- Effects on private enterprise and markets: the AD imposes a small, one‑off compliance cost on PA‑44 owners and provides business to maintenance shops and parts suppliers. It does not restrict who may perform the work so long as the organisation/person is authorised; it does not change aircraft operating rules or ownership rights.\n- Concentrated benefits and diffuse costs: the safety benefit is concentrated on aircraft occupants and the wider public by reducing the risk of loss of control; the monetary cost is concentrated on the specific owners/operators of the affected serial numbers (Applicability; Requirement).\n\n**What changed in this amendment**\n\n- The amendment corrects the textual reference to the Service Bulletin to SB No. 1139A (Part I of SB No. 1139A) rather than the earlier SB No. 1139. No new technical requirements were added by this amendment; it clarifies which SB edition is mandatory (Background)."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is Amendment 1 to an existing Airworthiness Directive. The amendment is purely technical and minimal — it corrects a document reference from 'SB No.1139' to 'SB No.1139A' in Requirement 1. The scope, applicability, and safety intent remain identical to the original AD. No expansion of regulatory reach or additional aircraft populations were introduced."},"complexity_factors":["Two distinct aircraft groups with overlapping and non-contiguous serial number ranges","Nested exception: Group A aircraft already modified per Service Bulletin 1139 are exempt from Requirement 1 only","Cross-reference to external technical document (Piper Service Bulletin 1139A) for detailed procedures","Two-tier compliance schedule with different deadlines for different requirements","Technical specifications requiring specialised aviation knowledge (thread engagement measurements, Loctite compound, specific part numbers)"],"plain_english_summary":"This is an **Airworthiness Directive (AD)** — a mandatory safety order issued by Australia's Civil Aviation Safety Authority (CASA) that requires specific repairs or inspections on certain aircraft.\n\n**What it does:**\nThis directive fixes a dangerous defect in Piper PA-44 Seminole aeroplanes where the control wheel (the pilot's steering wheel) could detach from the control column during flight. This happened because the attachment screw was too short and the nut plate lacked proper locking features.\n\n**Who it affects:**\n- **Group A aircraft:** Specific PA-44-180 Seminole models with serial numbers 4496020 through 4496173, and 4496175\n- **Group B aircraft:** PA-44-180 Seminole models with serial numbers 4496174 through 4496176, and 4496180\n\n**What owners/operators must do:**\n\n**For Group A aircraft (unless already fixed):**\n- Inspect the control wheel attachment screw to ensure at least one thread sticks out past the nut plate — replace the screw if not\n- Check the nut plate still grips properly — if you can screw it in by hand, replace the nut plate\n- Reassemble using special thread-locking glue (Loctite)\n\n**For all aircraft (Groups A and B):**\n- Install a retainer clip (part number 104687-002) as an extra safety measure\n\n**When it must be done:**\n- The screw and nut plate inspection: within 25 flight hours after 11 August 2004\n- The retainer clip installation: within 100 flight hours after 11 August 2004\n\n**Why it matters:**\nA similar defect caused a fatal crash in a related aircraft model when the pilot lost control because the control wheel spun freely. This directive prevents the same catastrophic failure in these Piper aircraft."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pa-44-19-amdt-1-control-wheel-attachment","history":"/api/acts/ad-pa-44-19-amdt-1-control-wheel-attachment/history","analysis":"/api/acts/ad-pa-44-19-amdt-1-control-wheel-attachment/analysis","conflicts":"/api/acts/ad-pa-44-19-amdt-1-control-wheel-attachment/conflicts","importantCases":"/api/acts/ad-pa-44-19-amdt-1-control-wheel-attachment/important-cases","documents":"/api/acts/ad-pa-44-19-amdt-1-control-wheel-attachment/documents"}}