{"id":"F2006B03305","name":"AD/B767/124 - Wing Front Spar Pitch Load Fittings","slug":"ad-b767-124-wing-front-spar-pitch-load-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42742,"registerId":"commonwealth-F2006B03305-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# AIRWORTHINESS DIRECTIVE\n\n![](image.002.png)\n\n![](image.002.png)  \nFor the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 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.","sortOrder":0},{"sectionNumber":"AD/B767/124 Wing Front Spar Pitch Load F","sectionType":"part","heading":"AD/B767/124 Wing Front Spar Pitch Load Fittings 9/2000","content":"# AD/B767/124 Wing Front Spar Pitch Load Fittings 9/2000\n\nApplicability: Model 767 series aircraft, line numbers 1 through 663.\n\nRequirement: Inspect in accordance with the technical requirements of FAA AD 2000-12-17 Amdt 39-11795.\n\nNote: Boeing Service Bulletin 767-57-0053 Revision 2 refers.\n\nCompliance: As specified in the Requirement document for the initial and repetitive inspection requirements, with a revised effective date of 7 September 2000.\n\nNote: Modification of the nacelle strut and wing structure in accordance with Boeing Service Bulletin (SB) 767-54-0080, SB 767-54-0081, or SB 767-54-0082, as\n\napplicable, and, accomplishment of the lug bore inspections and insurance cut of the pitch load fitting in accordance with SB 767-57-0053 Revision 2; constitutes terminating action for the inspection requirements of this Directive.\n\nThis Airworthiness Directive becomes effective on 7 September 2000.\n\nBackground: The FAA requires certain actions in response to a structural fatigue analysis that shows that the operational loads of the nacelle are higher than the loads used during the initial design of the Model 767 aircraft. The required actions are intended to detect and correct fatigue cracking in the pitch load fittings of the wing front spar.\n\n![Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.](image.003.png)  \n\nDavid Alan Villiers\n\nDelegate of the Civil Aviation Safety Authority 14 July 2000\n\n![](image.002.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 9 August 2000","sortOrder":1}],"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"},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":false,"description":"The AD implements the FAA-required inspection regime for Model 767 line numbers 1–663 and prescribes specified Boeing Service Bulletin modifications as terminating action. It does not broaden applicability beyond the FAA action stated in the Requirement and Applicability sections."},"complexity_factors":["Cross-reference to FAA AD 2000-12-17 and Boeing SB 767-57-0053 Rev 2 creates dependence on an external technical document (Requirement/Note).","Applicability is limited to Model 767, line numbers 1–663, requiring operators to verify airframe serialing (Applicability).","Inspections are initial and repetitive with timing set in the referenced FAA AD, producing an ongoing compliance burden (Requirement/Compliance).","Terminating action is conditional on completing specific Boeing Service Bulletins (SB 767-54-0080, -0081, -0082 and SB 767-57-0053 Rev 2), adding procedural complexity to determine when inspections can stop (Compliance/Note).","Effective date and revised effective date (7 September 2000) impose immediate operational scheduling requirements (Compliance).","Enforcement delegated to CASA under CAR 1998 subregulation 39.1(1), concentrating discretion in the regulator's delegate (preamble/signature).","Technical nature of fatigue inspections and potential structural modifications requires specialised maintenance and engineering resources, affecting cost and downtime (Background/Notes)."],"plain_english_summary":"This AD requires Boeing 767 aircraft (line numbers 1–663) operators to inspect wing front‑spar pitch‑load fittings per FAA AD 2000‑12‑17 and Boeing Service Bulletin 767‑57‑0053 Rev 2 to detect fatigue cracks. Inspections are initial and repetitive from 7 September 2000; specified Boeing structural modifications end the inspection requirement.\n\nOperators pay for inspections and any modifications; the CASA delegate enforces compliance and recognises the listed Boeing SBs as terminating action. The AD follows a structural fatigue analysis showing nacelle loads exceed the original design loads."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard airworthiness directive with focused, original scope. It addresses a specific safety issue (fatigue cracking in pitch load fittings) for a defined aircraft population without expansion into unrelated matters."},"complexity_factors":["Short, single-purpose directive (approximately 250 words)","Only 1 defined applicability criterion (line numbers 1-663)","Heavy reliance on external documents (FAA AD 2000-12-17 and Boeing Service Bulletins) without reproducing their contents","Simple conditional structure: inspect unless modified","Single cross-reference to Civil Aviation Regulations 1998 (subregulation 39.1(1))","No nested exceptions or complex temporal calculations"],"plain_english_summary":"This safety order requires operators of early-production Boeing 767s (serials 1–663) to inspect the wing/engine mount (pitch load fitting) area for metal fatigue cracks per FAA AD 2000-12-17, starting 7 September 2000 and repeated thereafter. It aims to detect stress-induced cracking from nacelle strut loads that could cause catastrophic wing failure. A specified Boeing structural modification and associated inspections can terminate the repeat inspection requirement."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b767-124-wing-front-spar-pitch-load-fittings","history":"/api/acts/ad-b767-124-wing-front-spar-pitch-load-fittings/history","analysis":"/api/acts/ad-b767-124-wing-front-spar-pitch-load-fittings/analysis","conflicts":"/api/acts/ad-b767-124-wing-front-spar-pitch-load-fittings/conflicts","importantCases":"/api/acts/ad-b767-124-wing-front-spar-pitch-load-fittings/important-cases","documents":"/api/acts/ad-b767-124-wing-front-spar-pitch-load-fittings/documents"}}