{"id":"F2006B06881","name":"AD/SD3-60/36 Amdt 1 - MLG Rear Pintle Pin Bush","slug":"ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":114761,"registerId":"commonwealth-F2006B06881-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/SD3-60/36 Amdt 1 - MLG Rear Pintle Pin Bush","content":"![](image.001.png)\n\n![](image.001.png)  \nAIRWORTHINESS DIRECTIVE\n\nOn the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/SD3-60/36 and issues the following AD under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\n![](image.001.png)\n\nShort SD3-60 Series Aeroplanes\n\nAD/SD3-60/36\n\nAmdt 1\n\n  \nMLG Rear Pintle Pin Bush 12/2004\n\nApplicability: Model SD3-60 aircraft.\n\nRequirement: 1. Inspect the main landing gear rear pintle pin assemblies for correctly applied sealant in accordance with Shorts Service Bulletin SD360-32-37 original issue, or later EASA approved revision (refer to Accomplishment Instructions, paragraph 2A of Messier-Dowty Service Bulletin 32-70SD Revision 1).\n\n2. If the sealant is incorrectly applied, perform a magnetic flaw detection inspection of the rear pintle pin fork ends in accordance with Shorts Service Bulletin SD360-32-37 original issue, or later EASA approved revision (refer to Accomplishment Instructions, paragraph 2B of Messier-Dowty Service Bulletin 32-70SD Revision 1).\n\nIf pintle pin fork ends are found cracked, before further flight, replace with a serviceable part that has been inspected in accordance with this Directive.\n\nNote: UK CAA AD G-2004-0022 refers.\n\nCompliance: 1. At the next “B” check after 25 November 2004, but no later than 3 months after the effective date of this Directive.\n\n2. At the next “C” check after 25 November 2004, but no later than 12 months after the effective date of this Directive.\n\nThis Amendment becomes effective on 25 November 2004.\n\nBackground: A report was received of the failure of a main landing gear rear pintle pin fork end on a SD3 aircraft. The failure was attributed to stress corrosion cracking. Absence of a fillet of sealant around the flange of the bronze bush was determined to be cause for the moisture ingress that initiated the corrosion.\n\nShort SD3-60 Series Aeroplanes\n\nAD/SD3-60/36 Amdt 1 (continued)\n\nAmendment 1 is issued in response to a new CAA AD, which was prompted by another incident on a SD3 aircraft where the pintle pin fork end cracked. This Directive requires further inspections to identify damaged pintle pin fork ends.\n\n![](image.002.png)  \n\nDavid Villiers\n\nDelegate of the Civil Aviation Safety Authority 14 October 2004\n\n![](image.001.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 3 November 2004.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":true,"description":"Amendment 1 revokes the prior AD and adds further inspections in response to a new CAA AD after an additional incident. It expands the directive to require a sealant check and, where sealant is incorrect, magnetic flaw inspection of pintle pin fork ends, with specific compliance deadlines tied to maintenance checks, thereby broadening the inspection requirements compared with the original AD."},"complexity_factors":["Narrow applicability — only Model SD3-60 aircraft are affected, reducing regulatory breadth.","Technical inspection requirement — magnetic flaw detection requires specialised nondestructive testing skills and equipment.","Dependence on external service documents — inspections are to follow Shorts Service Bulletin SD360-32-37 or later EASA‑approved revisions and Messier‑Dowty SB 32-70SD Revision 1.","Compliance timing tied to maintenance schedule — deadlines are linked to the next “B” and “C” checks, requiring planners to align inspections with maintenance cycles.","Immediate safety action — cracked parts must be replaced before further flight, creating potential for unscheduled part replacement and aircraft downtime.","Some judgement required — determining whether sealant is “correctly applied” may involve interpretation by maintenance personnel."],"plain_english_summary":"This Airworthiness Directive requires operators of Short SD3-60 aircraft to inspect main landing gear rear pintle pin assemblies for correctly applied sealant and, if sealant is missing, to carry out magnetic-flaw detection of the pintle pin fork ends. Any cracked fork ends must be replaced with a serviceable, inspected part before the aircraft returns to flight. The stated purpose is to prevent stress‑corrosion cracking from moisture ingress; compliance times are tied to the next “B” and “C” maintenance checks."},"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":2,"scope_assessment":{"changed":false,"description":"This amendment stays tightly focused on its original safety purpose. Amendment 1 simply expands the inspection requirements in response to a second incident involving the same component — it doesn't broaden to other aircraft types, other landing gear components, or unrelated systems. The scope remains: inspect and if necessary replace the MLG rear pintle pin bush assemblies on SD3-60 aircraft."},"complexity_factors":["Single aircraft model applicability (SD3-60 only)","Two straightforward inspection requirements with clear conditional logic (if sealant bad → inspect further; if cracked → replace)","Simple two-tier compliance schedule based on standard maintenance check intervals ('B' and 'C' checks)","Minimal cross-referencing — only references two specific service bulletins and one UK CAA AD for context","No defined terms section or interpretation provisions","Short document (approximately 300 words) with clear section headers"],"plain_english_summary":"This AD mandates inspections of the main landing gear rear pintle pin assemblies on Short SD3-60 aeroplanes after incidents of stress‑corrosion cracking caused by missing sealant around a bronze bush. Operators must check sealant, perform magnetic crack‑detection where sealant is inadequate, and replace any cracked fork ends before further flight. It affects anyone operating or maintaining these Australian-registered regional turboprops and closes a critical safety gap."}},"importantCases":[],"_links":{"self":"/api/acts/ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush","history":"/api/acts/ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush/history","analysis":"/api/acts/ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush/analysis","conflicts":"/api/acts/ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush/conflicts","importantCases":"/api/acts/ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush/important-cases","documents":"/api/acts/ad-sd3-60-36-amdt-1-mlg-rear-pintle-pin-bush/documents"}}