{"id":"F2006B03289","name":"AD/B767/108 Amdt 1 - Inboard Trailing Edge Flaps Collar Fittings","slug":"ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":42726,"registerId":"commonwealth-F2006B03289-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/B767/108 Amdt 1 - Inboard Trailing Edge Flaps Collar Fittings","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \n\nAIRWORTHINESS DIRECTIVE\n\n![](image.001.png)  \n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B767/108 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\nBoeing 767 Series Aeroplanes\n\nAD/B767/108\n\nAmdt 1\n\n  \nInboard Trailing Edge Flaps Collar Fittings 11/2003\n\nApplicability: Model 767 series aircraft, with line numbers 1 through 749.\n\nRequirement: Action in accordance with the technical requirements of FAA AD 2003-14-09 Amdt 39-13228.\n\nNote: Boeing Alert Service Bulletins 767-57A0066 Revision 1 and 767-57A0066 Revision 3 including Appendices A and B, refer.\n\nCompliance: As specified in the Requirement document, with a revised effective date of 30 October 2003.\n\nThis Amendment becomes effective on 30 October 2003.\n\nBackground: The FAA received a report of a complete fracture of an inboard trailing edge flap collar fitting as a result of stress corrosion cracking. The actions required by this Directive are intended to prevent separation of the inboard trailing edge flap from the wing due to fractured collar fittings.\n\nAmendment 1 is issued in response to a new FAA AD which expands applicability, and adds repetitive inspections of the collar fittings, torque tube, and splined bushings of both inboard trailing edge flaps. It also provides follow-on and corrective actions, if necessary.\n\nThe original issue of the Airworthiness Directive became effective on 25 February 1999.\n\n![Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.](image.002.png)  \n\nDavid Villiers\n\nDelegate of the Civil Aviation Safety Authority 10 September 2003\n\n![](image.001.png)\n\nThe above AD is notified in the Commonwealth of Australia Gazette on 8 October 2003.\n\n  \n\nPage 1 of 1","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"Amendment 1 expands the prior AD's scope by increasing applicability and adding repetitive inspections of collar fittings, torque tubes and splined bushings of both inboard trailing edge flaps, plus follow‑on and corrective actions; it also adopts FAA AD 2003‑14‑09 and references Boeing service bulletins and sets a revised effective date of 30 October 2003 (Background; Requirement; Compliance)."},"complexity_factors":["Narrow technical scope (specific inboard flap collar fittings, torque tube and splined bushings) reduces breadth of affected systems.","Relies on external documents (FAA AD 2003‑14‑09 and Boeing Alert Service Bulletins 767‑57A0066 Revisions) for technical procedures and compliance timing, creating dependency on non‑Australian texts (Requirement; Note).","Adds repetitive inspections plus follow‑on and corrective actions, increasing ongoing maintenance scheduling and parts‑replacement uncertainty (Background; Amendment 1).","Applicability limited to Boeing 767 line numbers 1–749, creating a clear but non‑universal affected population (Applicability).","Regulatory action revokes and replaces a prior AD, requiring operators to track supersession and revised effective dates (revocation note; Compliance).","Compliance enforced by CASA delegate; practical implementation requires interpretation by maintenance organisations, potential for discretionary decisions on corrective measures and recordkeeping (Requirement; Compliance)."],"plain_english_summary":"**This AD requires operators of Boeing 767 aircraft (line numbers 1–749) to carry out the inspections and corrective actions set out in FAA AD 2003‑14‑09 and the referenced Boeing service bulletins to detect and repair stress‑corrosion cracking in inboard trailing edge flap collar fittings, torque tubes and splined bushings (Applicability; Requirement).** CASA’s delegate enforces the directive; operators bear inspection, maintenance and replacement costs and must comply by the revised effective date, 30 October 2003 (Compliance)."},"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":true,"description":"The original 1999 directive addressed collar fitting fractures. Amendment 1 significantly expands scope: it adds repetitive inspections (not just one-time), extends coverage to torque tubes and splined bushings (additional components), applies to both inboard trailing edge flaps (both sides), and includes follow-on corrective actions. The applicability remains the same aircraft models, but the maintenance burden and component coverage has grown substantially."},"complexity_factors":["Short, single-page document with straightforward structure","Only 4 defined sections (Applicability, Requirement, Compliance, Background)","Minimal conditional logic — essentially 'if you own this aircraft, do this inspection'","Heavy reliance on external technical document (FAA AD 2003-14-09) for actual implementation details","No nested exceptions or complex cross-referencing within the document itself","Simple amendment structure — revokes previous AD and replaces with expanded version"],"plain_english_summary":"This FAA safety order replaces a 1999 order for early Boeing 767s (line numbers 1–749) and requires operators to follow AD 2003-14-09: repetitive inspections and corrective maintenance of flap collar fittings, torque tubes, and splined bushings. It addresses stress-corrosion cracking that can cause collar fittings to fail and a flap to separate from the wing. Effective 30 October 2003."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings","history":"/api/acts/ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings/history","analysis":"/api/acts/ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings/analysis","conflicts":"/api/acts/ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings/conflicts","importantCases":"/api/acts/ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings/important-cases","documents":"/api/acts/ad-b767-108-amdt-1-inboard-trailing-edge-flaps-collar-fittings/documents"}}