{"id":"F2005L00832","name":"AD/PC-12/39 Amdt 1 - Autopilot & Flap Selection","slug":"ad-pc-12-39-amdt-1-autopilot-flap-selection","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":113158,"registerId":"commonwealth-F2005L00832-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Pilatus PC-12 Series Aeroplanes","sectionType":"division","heading":"Pilatus PC-12 Series Aeroplanes","content":"### Pilatus PC-12 Series Aeroplanes\n\n| AD/PC-12/39 Amdt 1 | Autopilot & Flap Selection | 5/2005 |\n| ------------------ | -------------------------- | ------ |\n\n| Applicability: | All Model PC-12 and PC-12/45 aeroplanes, Manufacturer Serial Numbers (MSN) 101 thru MSN 620 inclusive.                                                                                                                                                                                       |\n| -------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. If not previously accomplished in accordance with the original issue of this Airworthiness Directive, amend the Pilot’s Operating Handbook (POH) by inserting either Temporary Revision (TR) No 11 (Report No 02211) or TR No 40 (Report 01973-001) into Section 2 of the applicable POH. |\n|                | 2. Accomplish the following actions in accordance with Pilatus Service Bulletin 22-004 dated 21 December 2004:                                                                                                                                                                               |\n|                | a. For MSN 101 thru 602 inclusive - Replace pitch actuator Part Number (P/N) 985.92.03.161 with a new pitch actuator with P/N 985.92.03.164.                                                                                                                                                 |\n|                | b. For MSN 321 and MSN 401 thru 620 inclusive - Disconnect wire C97C22 from terminal block TB260-13/H, remove the end connector from the wire then cap and stow the wire.                                                                                                                    |\n|                | c. For MSN 101 through 320 and MSN 322 thru 400 all inclusive - Secure circuit breaker CB906 with safety clip P/N 110.88.07.065.                                                                                                                                                             |\n|                | 3. Remove TR No 11 or No 40, as applicable, from the POH.                                                                                                                                                                                                                                    |\n|                | Note: FOCA Switzerland AD HB-2005-128 refers.                                                                                                                                                                                                                                                |\n| Compliance:    | For Requirement 1 - Before further flight after 19 May 2005.                                                                                                                                                                                                                                 |\n|                | For Requirement 2 - Before 31 December 2006.                                                                                                                                                                                                                                                 |\n|                | For Requirement 3 - Immediately following accomplishment of Requirement 2.                                                                                                                                                                                                                   |\n|                | This Amendment becomes effective on 12 May 2005.                                                                                                                                                                                                                                             |\n\n| Background: | The Swiss Federal Office for Civil Aviation (FOCA) received a report of abrupt nose down pitch occurring following disconnection of the autopilot during an ILS approach on a PC-12 aeroplane. Investigations have shown that when the flaps are at 40°, if the autopilot is disconnected, there is a possibility that an out of trim condition could occur and result in reduced controllability of the aeroplane. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | The original issue of this Directive required, as a temporary measure, revision of the Limitations Section of the POH to include an instruction to disengage the autopilot before a flap selection of 40° is made.                                                                                                                                                                                                  |\n|             | This Amendment limits the MSN effectivity and at the same time, introduces a terminating action with allows the removal of the temporary POH revisions.                                                                                                                                                                                                                                                             |\n|             | The original issue of this Directive became effective on 11 February 2004.                                                                                                                                                                                                                                                                                                                                          |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n31 March 2005","sortOrder":0},{"sectionNumber":"AD/PC-12/39 Amdt 1","sectionType":"part","heading":"AD/PC-12/39 Amdt 1","content":"## AD/PC-12/39 Amdt 1","sortOrder":1},{"sectionNumber":"Autopilot & Flap Selection","sectionType":"part","heading":"Autopilot & Flap Selection","content":"## Autopilot & Flap Selection","sortOrder":2},{"sectionNumber":"5/2005","sectionType":"part","heading":"5/2005","content":"## 5/2005","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This amendment stays within the original safety purpose of addressing the autopilot/flap interaction hazard. It narrows the affected aircraft population (limiting serial number effectivity compared to the original issue) and converts temporary operational limitations into permanent hardware fixes. This represents refinement rather than scope creep."},"complexity_factors":["Multiple serial number ranges with different technical requirements (three distinct hardware modifications depending on MSN)","Cross-references to external documents: Pilatus Service Bulletin 22-004, two Temporary Revisions (TR No 11 and TR No 40), and Swiss FOCA AD HB-2005-128","Staged compliance deadlines (three separate dates for different requirements)","Technical aviation terminology requiring specialized knowledge (pitch actuator, terminal blocks, circuit breakers, part numbers)","Amendment structure referencing 'original issue' and 'terminating action' creating temporal dependency"],"plain_english_summary":"This CASA Airworthiness Directive requires owners/operators of Pilatus PC-12 (S/N 101–620) to address a hazardous autopilot failure that can cause an abrupt nose-down pitch if the autopilot is disconnected with flaps at 40°. \n\nIt mandates an immediate POH warning (by 19 May 2005) and phased hardware modifications (by 31 Dec 2006), replacing or modifying components so pilots can safely remove the temporary warning once fixes are installed."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"Yes. The amendment narrows the affected Manufacturer Serial Number range and introduces a terminating action: specified hardware/wiring modifications (per Pilatus Service Bulletin 22-004) that allow removal of the temporary POH revisions. Previously the original AD only required the temporary POH limitation; this amendment prescribes corrective maintenance so the temporary instruction can be revoked once work is completed."},"complexity_factors":["Multiple technical corrective actions with different applicability by Manufacturer Serial Number ranges (actuator replacement, wire disconnection/capping/stowage, securing a circuit breaker).","Requirement relies on an external document (Pilatus Service Bulletin 22-004 dated 21 Dec 2004) for procedural detail.","Staged compliance timing: immediate POH insertion before next flight, hardware work by a later calendar date, and immediate removal of the temporary POH after completion.","Terminology and interplay between temporary revisions (TR No 11/No 40), original AD, and this amendment introduce traceability and record-keeping burdens for operators.","Safety-critical avionics and mechanical work (pitch actuator replacement, wiring changes, circuit breaker security) requires qualified maintenance, parts availability and workshop time.","Limited effectivity change from original AD (narrowed MSN effectivity) means operators must check serial-number applicability precisely.","Reference to a foreign authority (FOCA Switzerland AD HB-2005-128) adds cross-jurisdictional compliance context and potential for differing national requirements."],"plain_english_summary":"This amendment tells owners/operators of Pilatus PC-12 and PC-12/45 aeroplanes (MSN 101–620) to insert a temporary Pilot’s Operating Handbook notice, carry out specific hardware and wiring modifications per Pilatus Service Bulletin 22-004, and then remove the temporary POH revision once the work is complete. It responds to reports of abrupt nose‑down pitch when the autopilot is disconnected with flaps at 40°; operators pay for parts and maintenance and must meet the directive’s compliance deadlines to restore normal POH limits."}},"importantCases":[],"_links":{"self":"/api/acts/ad-pc-12-39-amdt-1-autopilot-flap-selection","history":"/api/acts/ad-pc-12-39-amdt-1-autopilot-flap-selection/history","analysis":"/api/acts/ad-pc-12-39-amdt-1-autopilot-flap-selection/analysis","conflicts":"/api/acts/ad-pc-12-39-amdt-1-autopilot-flap-selection/conflicts","importantCases":"/api/acts/ad-pc-12-39-amdt-1-autopilot-flap-selection/important-cases","documents":"/api/acts/ad-pc-12-39-amdt-1-autopilot-flap-selection/documents"}}