{"id":"F2008L00662","name":"AD/PC-12/52 - Elevator Control Stick-Pusher Servo-Cable Tension and Cable Clamp Bolts","slug":"ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":72695,"registerId":"commonwealth-F2008L00662-current","compilationNumber":null,"startDate":"2026-04-02","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-12/52 | Elevator Control Stick-Pusher Servo-Cable Tension and Cable Clamp Bolts | 5/2008 DM |\n| ----------- | ----------------------------------------------------------------------- | --------- |\n\n| Applicability: | Pilatus Aircraft Ltd PC-12, PC-12/45 and PC-12/47 aircraft, Manufacturer Serial Number (MSN) 101 up to MSN 888 inclusive, except MSN 545.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Check the stickpusher servo-cables for correct installation, position and tension in accordance with paragraph 3.B.(1) of Pilatus PC-12 Service Bulletin (SB) No. 27-018 or later NAA approved revision.2. If during the check required by Requirement 1 of this AD, any incorrectly installed or positioned stick-pusher servo-cables are found, adjust the stick-pusher servo-cables tension in accordance paragraph 3.B.(2) of Pilatus PC-12 SB No. 27-018 or later NAA approved revision.3. If during the check required by Requirement 1 of this AD, any stick-pusher servo-cables are found with incorrect tension and/or indications that the cables have moved in the cable clamps, replace the affected parts in accordance with paragraph 3.B.(4) of Pilatus PC-12 SB No. 27-018 or later NAA approved revision.4. If during the check required by Requirement 1 of this AD, no signs are detected that the stick-pusher servo-cables have moved in the cable clamps, replace the affected parts in accordance with paragraph 3.B.(5) of Pilatus PC-12 SB No. 27-018 or later NAA approved revision.Note: EASA AD 2008-0047 dated 28 February 2008 refers. |\n| Compliance:    | 1. Within the next 20 Flight Hours (FH) but not later than 7 April 2008, whichever occurs first after the effective date of this AD, unless previously accomplished.2. Before further flight after the effective date of this AD.3. Before further flight after the effective date of this AD.4. Before further flight after the effective date of this AD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n|                | This Airworthiness Directive becomes effective on 7 March 2008.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         |\n\n| Background: | Some operators have reported occurrences where the rear stick-pusher cable clamp shifted forward on the elevator cable. This condition, if not corrected, may reduce the effectiveness of the stick-pusher and/or limit elevator control movement. This AD requires the inspection of the stick-pusher servo-cables for correct installation, position and tension and replacement of discrepant parts |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n3 March 2008","sortOrder":0},{"sectionNumber":"AD/PC-12/52","sectionType":"part","heading":"AD/PC-12/52","content":"## AD/PC-12/52","sortOrder":1},{"sectionNumber":"Elevator Control Stick-Pusher Servo-Cabl","sectionType":"part","heading":"Elevator Control Stick-Pusher Servo-Cable Tension and Cable Clamp Bolts","content":"## Elevator Control Stick-Pusher Servo-Cable Tension and Cable Clamp Bolts","sortOrder":2},{"sectionNumber":"5/2008 DM","sectionType":"part","heading":"5/2008 DM","content":"## 5/2008 DM","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"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific mechanical defect in a specific aircraft type. It has not expanded beyond its original safety purpose of correcting the stick-pusher cable clamp issue."},"complexity_factors":["Multiple conditional requirements (4 separate requirements with interdependencies — Requirement 2, 3, and 4 all depend on findings from Requirement 1)","Cross-reference to external technical document (Pilatus Service Bulletin No. 27-018) for detailed procedures — the AD itself doesn't contain the actual instructions","Specific applicability criteria with serial number ranges and explicit exclusions (MSN 101-888 except MSN 545)","Tiered compliance deadlines (20 flight hours vs. calendar date vs. 'before further flight')","Reference to international regulatory alignment (EASA AD 2008-0047)"],"plain_english_summary":"Owners/operators of Pilatus PC‑12 (S/N 101–888, except 545) must urgently inspect and, if necessary, repair the elevator stick‑pusher cable/servo assembly. A forward‑shifting rear clamp can degrade stick‑pusher effectiveness and restrict elevator travel, risking stall recovery. Inspections are required within 20 flight hours or by 7 Apr 2008; any discrepant parts must be adjusted or replaced before further flight, and certain parts must be replaced even if no movement is found. This is an immediate safety action."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The AD remains narrowly focused on the reported problem of rear stick‑pusher cable clamps shifting and the resulting risk to stick‑pusher effectiveness and elevator control. It requires inspection, adjustment, or replacement per the manufacturer's service bulletin. The only expansion of mechanism is delegation of procedural detail to the SB and allowance for later NAA‑approved SB revisions; this changes how the work is implemented but does not broaden the AD's substantive scope beyond its original safety purpose."},"complexity_factors":["Short, focused instrument (single technical issue) limiting overall length and branching","Applicability specified by serial number range (MSN 101–888 inclusive) with one explicit exclusion (MSN 545)","Four requirement branches depending on inspection outcome (check → adjust or replace, with different SB paragraph cross‑references)","Cross‑reference to external documents: Pilatus SB No. 27‑018 and any later NAA approved revision","Reference to an external authority's AD (EASA AD 2008‑0047) increases dependency on outside material","Multiple compliance deadlines: initial inspection within 20 flight hours or by a calendar date; corrective actions required before further flight","Procedural detail is delegated to the manufacturer's service bulletin rather than contained in the AD (adds practical dependency but keeps AD text short)"],"plain_english_summary":"**What this instrument does (mechanics first)**\n\n- Requires operators of specified Pilatus PC-12 aeroplanes to inspect the stick‑pusher servo‑cables for correct installation, position and tension, following the procedures in Pilatus Service Bulletin (SB) No. 27‑018 (or a later version approved by the relevant national aviation authority).\n- If the inspection finds incorrectly installed or positioned cables, the cables must be adjusted as directed in the SB.\n- If the inspection finds incorrect cable tension or signs that the cable has slipped in its clamp, the affected parts must be replaced as directed in the SB.\n- Even if there are no obvious clamp‑slip marks, the AD still requires replacement of affected parts in the circumstances specified in the SB.\n\n**Who is covered**\n\n- Applies to Pilatus PC‑12, PC‑12/45 and PC‑12/47 aeroplanes with Manufacturer Serial Numbers (MSN) 101 through 888 inclusive, except MSN 545 (see \"Applicability\").\n\n**When it must be done**\n\n- The initial inspection must be completed within the next 20 flight hours after the AD takes effect, or by 7 April 2008 — whichever comes first (the AD effective date is 7 March 2008).\n- Any required adjustments or part replacements identified by that inspection must be carried out before the aircraft is next flown.\n\n**Why this was issued (source claim)**\n\n- The AD cites reports that the rear stick‑pusher cable clamp had shifted forward on the elevator cable. The stated safety concern is that a shifted clamp could reduce stick‑pusher effectiveness and/or limit elevator control movement (see \"Background\").\n\n**Practical effects, costs and incentives**\n\n- Who pays: aircraft operators (owners or maintenance organisations) pay for the inspection, any adjustments, and replacement parts and labour. Parts and labour will also involve the supply chain (maintenance shops, parts suppliers).\n- Operational cost: the short compliance window (20 flight hours or a calendar deadline) creates scheduling pressure and possible aircraft downtime, which can reduce available revenue from the affected aeroplanes.\n- Behavioural change: maintenance personnel must follow the Pilatus SB procedures exactly (or the later NAA approved revision). Operators will prioritise these inspections and corrective work before returning an aircraft to service.\n- Regulatory reliance: the AD requires compliance with a manufacturer service bulletin or a later NAA‑approved revision, which means procedural details can change if the SB is revised and approved by an authority.\n- Benefit concentration: the direct safety benefit accrues to operators and passengers of the affected PC‑12 fleet; the cost is borne by those same operators. The number of affected aircraft is limited by the serial‑number range specified.\n\n**Trade‑offs and implementation risks**\n\n- Trade‑offs: faster compliance reduces exposure to the identified hazard but increases short‑term maintenance demand and possible grounding. Delaying corrective work is not permitted under the AD.\n- Implementation risk: correct assessment depends on maintenance staff identifying clamp movement or tension issues per the SB. If operators use different maintenance interpretations, inconsistent fixes could result.\n\n**Cross‑references**\n\n- The AD requires following Pilatus SB No. 27‑018 (or later NAA approved revision) and references EASA AD 2008‑0047. The AD does not itself detail adjustment or replacement steps — those are in the SB.\n\n(References: Applicability, Requirement paragraphs 1–4, Compliance, Background.)"}},"importantCases":[],"_links":{"self":"/api/acts/ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts","history":"/api/acts/ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts/history","analysis":"/api/acts/ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts/analysis","conflicts":"/api/acts/ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts/conflicts","importantCases":"/api/acts/ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts/important-cases","documents":"/api/acts/ad-pc-12-52-elevator-control-stick-pusher-servo-cable-tension-and-cable-clamp-bolts/documents"}}