{"id":"F2006L02522","name":"AD/BEECH 200/73 - Main Landing Gear Actuator Nut","slug":"ad-beech-200-73-main-landing-gear-actuator-nut","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":59750,"registerId":"commonwealth-F2006L02522-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Beechcraft 200 (Super King Air) Series A","sectionType":"division","heading":"Beechcraft 200 (Super King Air) Series Aeroplanes","content":"### Beechcraft 200 (Super King Air) Series Aeroplanes\n\n| AD/BEECH 200/73 | Main Landing Gear Actuator Nut | 9/2006 |\n| --------------- | ------------------------------ | ------ |\n\n```html\n

Applicability:

Main Landing Gear (MLG) Actuator nut assembly, part number (P/N)
GMD115-810029-17 or P/N GMD115-810029-23, for the right MLG actuator installed on, but not limited to, the following Raytheon Aircraft Company (Raytheon) (formerly Beech) aeroplanes that are not equipped with a hydraulic MLG or modified to a hydraulic MLG.

Models

Serial Nos.

200

BB-2, BB-6 through BB-733, BB-735 through
BB-792, BB-794 through BB-828, BB-830 through BB-853, BB-872, BB-873, BB-892, BB-893, and
BB-912 (except aircraft that incorporate Beech Kit No. 101-8018).

B200

BB-734, BB-793, BB-829, BB-854 through BB-870, BB-874 through BB-891, BB-894, BB-896 through BB-911, BB-913 through BB-1157, BB–1159 through BB-1166, and BB-1168 through BB-1192 (except aircraft that incorporate Beech Kit No.
101-8018).

200T and B200T

BT-1 through BT-30 (except aircraft that incorporate Beech Kit No. 101-8018).

200C and B200C

BL-1 through BL-72 (except aircraft that incorporate Beech Kit No. 101-8018).

200CT and B200CT

BN-1 through BN-4 (except aircraft that incorporate Beech Kit No. 101-8018).

A200CT (FWC–12D)

FG-1 and FG-2 (except aircraft that incorporate Beech Kit No. 101-8018).

\n```\n\n| Requirement: | 1. Check the maintenance records to determine whether the following replacements have been made:a) Actuator nut assembly, P/N GMD115-810029-17, for the right MLG actuator; orb) Actuator nut assembly, P/N GMD115-810029-23, for the right MLG actuator.2. If you find as a result of the check required by requirement 1 of this AD that there is no record of the specified assembly replacement, inspect the aeroplane, in accordance with General Machine Diecron Inc. Service Bulletin GM-D32-30-01/102505 dated 21 November 2005, for installation of the following:a) Actuator nut assembly, P/N GMD115-810029-17, for the right MLG actuator; orb) Actuator nut assembly, P/N GMD115-810029-23, for the right MLG actuator.You may choose to do the inspection detailed in requirement 2 of this AD without doing the maintenance records check detailed in requirement 1 of this AD.3. If during the check required by requirement 1 or the inspection required by requirement 2 of this AD, you find either actuator nut assembly, P/NGMD115-810029-17 or P/N GMD115-810029-23, for the right MLG actuator, replace the specific assembly, with a new actuator nut assembly, P/NGMD115-810029-23B or approved equivalent P/N in accordance with General Machine Diecron, Inc. Service Bulletin GM-D 32-30-01/102505.4. Do not install any actuator nut assembly, P/N GMD115-810029-17 or P/N GMD115-810029-23, for the right MLG actuator.Note: FAA AD2006-12-25Amdt 39-14651 dated 9 June 2006 refers. |\n| ------------ | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n| Compliance: | 1. Within the next 50 hours time-in-service (TIS) or 30 calendar days after the effective date of this AD, whichever occurs first, unless already done.2. Within the next 50 hours TIS or 30 calendar days after the effective date of this AD, whichever occurs first, unless already done.3. Before further flight after the check required by requirement 1 or the inspection required by requirement 2 of this AD.4. From the effective date of this AD. |\n\n| | This Airworthiness Directive becomes effective on 31 August 2006. |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Background: | This AD results from several reports of failures of the actuator nut assembly, P/N GMD115-810029-17 and P/N GMD115-810029-23, on the right MLG actuator. The actions specified in this AD are intended to prevent failure of the actuator nut assembly for the right MLG actuator, which could result in failure of the MLG. This failure could prevent the extension or retraction of the MLG. |\n\n![](image.001.png) \nJames Coyne \nDelegate of the Civil Aviation Safety Authority\n\n21 July 2006","sortOrder":0},{"sectionNumber":"AD/BEECH 200/73","sectionType":"part","heading":"AD/BEECH 200/73","content":"## AD/BEECH 200/73","sortOrder":1},{"sectionNumber":"Main Landing Gear Actuator Nut","sectionType":"part","heading":"Main Landing Gear Actuator Nut","content":"## Main Landing Gear Actuator Nut","sortOrder":2},{"sectionNumber":"9/2006","sectionType":"part","heading":"9/2006","content":"## 9/2006","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"This AD remains focused on the original safety purpose: preventing failure of a specific actuator nut assembly on the right main landing gear. It prescribes inspection/replacement of the suspect parts and prohibits their future installation. The instrument does not broaden scope beyond that safety correction (no new categories of parts, no expanded compliance constructs, and no new certification or operational requirements)."},"complexity_factors":["Four distinct part numbers referenced (affected: P/N GMD115-810029-17 and -23; replacement: P/N GMD115-810029-23B; plus allowance for an 'approved equivalent' part)","Four explicit requirements (records check; optional direct inspection; mandatory replacement if found; prohibition on future installation)","Single short compliance window for initial actions (50 flight hours or 30 calendar days) and a 'before next flight' rule for replacements","Cross-reference to one external procedural document: General Machine Diecron Inc. Service Bulletin GM-D32-30-01/102505 (21 Nov 2005)","Applicability determined by model and a detailed list of serial-number ranges across multiple sub-models","Exceptions to applicability (aircraft with hydraulic MLG or modified to hydraulic MLG; aircraft with Beech Kit No. 101-8018)","Simple conditional logic (if records lack evidence, inspect; if part found, replace), with no nested exceptions beyond the stated exclusions"],"plain_english_summary":"**What this instrument does (mechanically):**\n\n- Applies to specified Beechcraft 200/B200 series aeroplanes (lists models and serial number ranges) that are equipped with the right main landing gear (MLG) actuator using actuator nut assemblies P/N GMD115-810029-17 or P/N GMD115-810029-23, and that are not fitted with a hydraulic MLG or modified to a hydraulic MLG (aircraft fitted with Beech Kit No. 101-8018 are excepted). \n\n- Requires operators/maintainers to do one of the following within 50 flight hours or 30 calendar days (whichever comes first): \n - Check maintenance records to see whether the suspect actuator nut assemblies (P/N GMD115-810029-17 or -23) have been fitted to the right MLG actuator (Requirement 1); or \n - Skip the records check and carry out a physical inspection of the right MLG actuator to determine whether either suspect actuator nut assembly is installed, in accordance with General Machine Diecron, Inc. Service Bulletin GM-D32-30-01/102505 (Requirement 2). \n\n- If either suspect nut assembly is found by the records check or inspection, require replacement of that assembly before the next flight with a new actuator nut assembly P/N GMD115-810029-23B (or an approved equivalent part number), following the referenced service bulletin (Requirement 3). \n\n- Prohibits installation, from the effective date, of the older nut assemblies P/N GMD115-810029-17 or P/N GMD115-810029-23 on the right MLG actuator (Requirement 4).\n\n- The service bulletin GM-D32-30-01/102505 dated 21 November 2005 is the procedural reference for the inspection and replacement tasks.\n\n**Who this affects:**\n\n- Primary: Operators and owners of the specified Beechcraft 200/B200-series aeroplanes listed by model and serial number (unless the aircraft has a hydraulic MLG or incorporates Beech Kit No. 101-8018). \n- Secondary: Maintenance organisations, licensed aircraft engineers, parts suppliers (particularly suppliers of the replacement P/N GMD115-810029-23B), and airworthiness authorities overseeing compliance.\n\n**Why it matters (stated purpose and operational effect):**\n\n- Stated purpose: this directive responds to reported failures of the actuator nut assemblies P/N GMD115-810029-17 and -23 on the right MLG actuator. The required actions are intended to prevent failure of that assembly, which otherwise could lead to failure of the main landing gear to extend or retract.\n\n**Practical implications, costs and incentives:**\n\n- Who pays: aircraft owners/operators pay for the checks, inspections, any replacement parts, and labour/downtime.\n- Who decides: the operator or their authorised maintenance organisation carries out the records check or inspection and arranges replacement where required. The Civil Aviation Safety Authority (or its delegate) enforces compliance by issuing the directive.\n- Behaviour changes required: review records or perform a physical inspection within the short compliance window (50 TIS or 30 days), replace any affected assemblies before next flight if found, and do not install the older P/Ns on the right MLG actuator thereafter.\n- Compliance burden: short-notice inspections and possible aircraft downtime; cost of purchasing replacement parts (P/N GMD115-810029-23B or approved equivalent) and fitting them; reliance on the referenced service bulletin for correct procedures.\n- Implementation risk: accurate identification of the installed part requires access to reliable maintenance records or physical inspection skills; parts availability could delay compliant replacements; small operators may face disproportionate scheduling and cost impacts.\n- Trade-offs and substitution effects: operators might consider installing the excluded hydraulic MLG configuration or fitting Beech Kit No. 101-8018 (if acceptable and available) to avoid applicability, but such modifications have their own costs and certification implications.\n- Concentrated benefits and costs: the safety benefit (reduced risk of MLG failure) accrues to operators and their passengers/crew, a concentrated and immediate benefit; costs (inspection time and replacement parts) are concentrated on those same operators. The replacement-parts supplier(s) may see increased demand for the approved PN, which is a predictable market effect of a mandated replacement.\n\n**Reference mechanics:**\n- Compliance timing: requirements 1 and 2 — within 50 hours TIS or 30 days; requirement 3 — replacement before next flight if an affected assembly is found; requirement 4 — prohibition effective immediately on the AD's effective date. \n- Procedural reference: General Machine Diecron, Inc. Service Bulletin GM-D32-30-01/102505 (21 Nov 2005) for inspection and replacement steps.\n\nOverall, the instrument mandates a short-term records check or inspection followed by mandatory replacement of specified actuator nut assemblies on the right MLG where they are found, and forbids fitting the older assemblies in future. The stated goal is to remove a part suspected of causing landing-gear failures; compliance imposes direct inspection and replacement costs on affected operators and creates predictable demand for the specified replacement part."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This AD maintains a narrow, targeted scope focused specifically on the right main landing gear actuator nut assembly for identified Beechcraft models. It does not expand beyond its original safety purpose of addressing the reported failures of specific part numbers."},"complexity_factors":["Multiple specific part numbers (P/N GMD115-810029-17, P/N GMD115-810029-23, P/N GMD115-810029-23B) that must be tracked and distinguished","Extensive serial number ranges across 7 different aircraft models with multiple gaps and exceptions (e.g., 'BB-735 through BB-792, BB-794 through BB-828')","Nested conditional logic: Requirement 3 triggers only if Requirement 1 OR Requirement 2 finds the part; Requirement 2 can be skipped if Requirement 1 is done (but not vice versa)","Cross-reference to external technical document (General Machine Diecron Inc. Service Bulletin GM-D32-30-01/102505) for inspection procedures","Exception clause excluding aircraft with 'Beech Kit No. 101-8018' across all model categories","Dual compliance timeframes (flight hours vs calendar days) with 'whichever occurs first' logic","Reference to corresponding FAA AD (2006-12-25) creating potential for confusion about which authority's rules apply"],"plain_english_summary":"CASA requires owners/operators of specified Beechcraft 200‑series aircraft to check for and, if present, replace a faulty right main landing‑gear actuator nut (P/Ns GMD115‑810029‑17/‑23) because failures can prevent gear extension/retraction. Inspect records or the part within 50 flight hours or 30 days; replace any faulty unit before the next flight and do not install the old part numbers (ban effective 31 Aug 2006)."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-beech-200-73-main-landing-gear-actuator-nut","history":"/api/acts/ad-beech-200-73-main-landing-gear-actuator-nut/history","analysis":"/api/acts/ad-beech-200-73-main-landing-gear-actuator-nut/analysis","conflicts":"/api/acts/ad-beech-200-73-main-landing-gear-actuator-nut/conflicts","importantCases":"/api/acts/ad-beech-200-73-main-landing-gear-actuator-nut/important-cases","documents":"/api/acts/ad-beech-200-73-main-landing-gear-actuator-nut/documents"}}