{"id":"F2007L02140","name":"AD/A330/34 Amdt 1 - MLG Retraction Actuator Lower Pin","slug":"ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":67312,"registerId":"commonwealth-F2007L02140-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Airbus Industrie A330 Series Aeroplanes","sectionType":"division","heading":"Airbus Industrie A330 Series Aeroplanes","content":"### Airbus Industrie A330 Series Aeroplanes\n\n| AD/A330/34 Amdt 1 | MLG Retraction Actuator Lower Pin | 8/2007 |\n| ----------------- | --------------------------------- | ------ |\n\n| Applicability: | AIRBUS A330-200 and A330-300 aircraft equipped with main landing gear (MLG) retraction actuator lower pin(s) (P-Pin) part number (PN) 201275602.No action is required by this AD on the aircraft, on which AIRBUS modification 46903 (install PN 201478612) in production or AIRBUS Service Bulletin (SB)A330-32-3096 in service has been embodied.                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Requirement:   | 1. Visually inspect P-Pins PN 201275602, to check for correct positions of the grease holes in accordance with AIRBUS AOT A330-32A3181 and report the inspection results to Messier-Dowty using the pro-forma contained in the VSB MD-L SB A33/34-32-229 referenced in the AOT.2. Replace any P-Pin is found fractured.3. If the positions of the grease holes are not correct:a. Replace the P-pin.b. Pending replacement of the P-Pin, perform an external visual inspection of the P-Pin in order to check for pin migration.c. If the P-Pin is found to be migrating during the external visual inspection, the P-Pin must be replaced.4. Examine any P-Pin PN 201275602 that is used as a replacement part, for the correct positions of the grease holes.Note: DGAC AD F-2004-084 dated 23 June 2004 refers. |\n| Compliance:    | For Requirement 1:- For P-Pins fitted to aircraft, remains unchanged as within 100 Flight Cycles or 3 months from 16 June 2004 (the effective date of the original issue of this AD), whichever occurs first.- For P-Pins fitted to spare units, before fitment to the aeroplane.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  |\n\n|             | For Requirement 2: Before further flight.For Requirement 3:a. Within 800 flight hours following the visual inspection as detailed in Requirement 1 of this Directive.b. Before the first flight of the day.c. Before further flight.For Requirement 4: Before fitment to an aeroplane following the effective date of this Directive.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n|             | This Amendment becomes effective on 2 August 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 |\n| Background: | A P-Pin PN201275602 connecting the lower end of the retraction actuator to the main fitting was found fractured upon removal during MLG overhaul. Investigation concluded that the crack that caused fracture initiated from the centre grease hole of the P-Pin. In this case, the centre grease hole was machined in an incorrect position, 90° from its normal position. This failure and possibly resulting migration of theP-Pin may lead to an undamped extension of the landing gear. Upon fully extending, the landing gear would be submitted to high loads possibly compromising its structural integrity. This AD requires a visual inspection in order to detect and replace incorrectly manufactured P-Pins.This amendment changes the P/N of the pin referred to in the applicability section of this AD to P/N 201478612 from 201275612, which was referred to in the original telex AD issued by the DGAC. There are no other changes.The original issue of this AD became effective 16 June 2004. |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n21 June 2007","sortOrder":0},{"sectionNumber":"AD/A330/34 Amdt 1","sectionType":"part","heading":"AD/A330/34 Amdt 1","content":"## AD/A330/34 Amdt 1","sortOrder":1},{"sectionNumber":"MLG Retraction Actuator Lower Pin","sectionType":"part","heading":"MLG Retraction Actuator Lower Pin","content":"## MLG Retraction Actuator Lower Pin","sortOrder":2},{"sectionNumber":"8/2007","sectionType":"part","heading":"8/2007","content":"## 8/2007","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"This amendment updates the part‑number reference in the applicability (amending the pin P/N referenced in the original telex AD to P/N 201478612 from the earlier P/N used) but states there are no other changes to the original directive; the original AD remained effective from 16 June 2004."},"complexity_factors":["Targeted hardware requirement but multiple distinct compliance deadlines (e.g. 100 flight cycles or 3 months from 16 June 2004; before further flight; within 800 flight hours; before first flight of the day).","Reporting obligation to Messier‑Dowty using a pro‑forma referenced in the Directive increases administrative steps.","Different rules for installed P‑pins, spare units and replacement parts (inspect before fitment) create parts‑handling controls.","Conditional inspection frequency and interim monitoring for pin migration (external daily checks pending replacement) add operational disruption risk.","Applicability depends on specific part numbers and whether Airbus modification 46903 or SB A330‑32‑3096 has been embodied, so tracking configuration status is required.","Amendment updates or clarifies part number references between original telex and this AD, requiring records reconciliation."],"plain_english_summary":"This airworthiness directive requires operators of Airbus A330‑200/300 aircraft fitted with main‑landing‑gear retraction lower P‑pins (PN 201275602) to visually inspect pins for correct grease‑hole position, report results to Messier‑Dowty, replace fractured or incorrectly manufactured pins, and check spare pins before fitment. It responds to a fracture caused by a mis‑located grease hole that can allow gear overextension. Airlines must carry out inspections and replacements on the timetables set by the directive and bear the associated maintenance and reporting costs."},"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"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is an amendment to an existing Airworthiness Directive. The scope remains identical to the original 2004 directive — it addresses the same safety defect in the same aircraft type. The amendment only corrects a part number reference in the applicability section without expanding or altering the substantive safety requirements."},"complexity_factors":["Technical aviation terminology throughout (P-Pin, MLG, retraction actuator, part numbers)","Multiple conditional requirements with different compliance timeframes (100 flight cycles OR 3 months, 800 flight hours, before first flight of day, before further flight)","Nested decision tree logic (if grease holes incorrect → replace; pending replacement → inspect; if migrating → replace immediately)","Cross-references to external technical documents (Airbus AOT, Service Bulletin, DGAC AD)","Applicability exclusions based on prior modifications or service bulletins","Dual applicability tracks (pins fitted to aircraft vs. pins fitted to spare units)"],"plain_english_summary":"This CASA Airworthiness Directive mandates inspection and, where needed, replacement of a specific P‑Pin (PN 201275602) on Airbus A330‑200/‑300 aircraft after a crack was found originating from a grease hole drilled in the wrong position. Operators with the affected pin must inspect, report findings to Messier‑Dowty, replace any cracked pins before flight and correct misdrilled pins within 800 flight hours; spare parts must be checked before installation. The amendment only corrects a part‑number reference."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin","history":"/api/acts/ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin/history","analysis":"/api/acts/ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin/analysis","conflicts":"/api/acts/ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin/conflicts","importantCases":"/api/acts/ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin/important-cases","documents":"/api/acts/ad-a330-34-amdt-1-mlg-retraction-actuator-lower-pin/documents"}}