{"id":"F2006B09244","name":"AD/DHC-8/85 - Fuselage to Wing Rear Spar Fittings","slug":"ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":53152,"registerId":"commonwealth-F2006B09244-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AIRWORTHINESS DIRECTIVE","sectionType":"part","heading":"AIRWORTHINESS DIRECTIVE","content":"# ![](image.001.png)![](image.001.png)AIRWORTHINESS DIRECTIVE\n\n![](image.001.png)For 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.\n\nBombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes","sortOrder":0},{"sectionNumber":"AD/DHC-8/85 Fuselage to Wing Rear Spar F","sectionType":"part","heading":"AD/DHC-8/85 Fuselage to Wing Rear Spar Fittings 3/2002","content":"# AD/DHC-8/85 Fuselage to Wing Rear Spar Fittings 3/2002\n\nApplicability: Models 102, 103, 106, 201, and 202, serial numbers 003 through 539 (except 097).\n\nModel 301, serial numbers 100 through 200.\n\nModels 311, 314, and 315, serial numbers 202 through 539 (except 395).\n\nRequirement: 1. Accomplish the following in accordance with Bombardier Service Bulletin 8-27- 83, dated 19 October 2001:\n\n    Perform visual inspections on the rear spar fittings part numbers 85320053, 85322060, and 85334180 for cracks and wear damage in accordance with Tables 1 and 2 of the Requirement document.\n\n    b. Replace the damaged fittings before further flight if any of the following conditions are present:\n\n    (i) The wear damage before blending is greater than the limits specified in Table 2 of the Requirement document.\n\n    (ii) The area removed after blending is greater than that specified in Table 3 of the Requirement document.\n\n    (iii) If the fitting is cracked.\n\n2. Re-inspect /repair fittings in accordance with the requirements of the compliance table specified in the Requirement document.\n\nNote 1: Incorporation of modification 8/3149 will terminate the inspection requirements of this Directive.\n\nNote 2: Transport Canada AD CF-2001-42 refers.\n\nCompliance: 1. Within 12 months after the effective date of this Directive.\n\n2. As specified in the Requirement document.\n\nThis Airworthiness Directive becomes effective on 21 March 2002.","sortOrder":1}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"Scope remains limited to the specified DHC‑8 models and serial‑number ranges and requires inspection/repair actions as set out in the Bombardier Service Bulletin. The AD includes a terminating modification (8/3149) and does not expand obligations beyond those aircraft or the referenced procedures. (See Applicability; Requirement; Note 1; Compliance.)"},"complexity_factors":["Targeted applicability with multiple models and serial‑number ranges, including an exclusion (Applicability).","Requirement relies on an external manufacturer document (Bombardier Service Bulletin 8‑27‑83) for inspection procedures and acceptance criteria (Requirement 1).","Technical acceptance thresholds are specified in tables in the Requirement document (wear limits, area removed after blending) (Requirement 1, Tables 1–3).","Immediate operational consequence for failures: fittings must be replaced 'before further flight' if cracked or beyond limits (Requirement 1.b).","Ongoing re‑inspection/repair schedule is set by a compliance table in the Requirement document rather than in the AD text itself (Requirement 2, Compliance table).","Termination mechanism: incorporation of modification 8/3149 cancels the inspection requirement (Note 1).","Cross‑reference to a foreign authority AD (Transport Canada AD CF‑2001‑42) for related guidance (Note 2).","Fixed primary compliance deadline (within 12 months) plus unspecified subsequent intervals governed by the referenced Requirement document (Compliance)."],"plain_english_summary":"**What it does:** Requires operators of certain Bombardier DHC‑8 aeroplanes to inspect specific fuselage‑to‑wing rear spar fittings for cracks and wear, and to repair or replace fittings in accordance with Bombardier Service Bulletin 8‑27‑83 within 12 months to address an unsafe condition.\n\nWho it affects and why it matters: Applies to listed models and serial‑number ranges and affects aircraft owners/operators and maintenance organisations responsible for inspections, repairs and any terminating modification (incorporation of modification 8/3149)."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard airworthiness directive with focused scope. It addresses a specific structural safety issue on specific aircraft models without expanding beyond its original safety purpose."},"complexity_factors":["Multiple serial number ranges with specific exclusions (e.g., '003 through 539 (except 097)')","Cross-reference to external technical document (Bombardier Service Bulletin 8-27-83) for detailed procedures","Three specific part numbers requiring identification","Conditional logic for replacement decisions (three alternative triggers for replacement)","Reference to modification 8/3149 as terminating action","Dual compliance timeline (initial 12-month window plus ongoing schedule)"],"plain_english_summary":"This safety order requires operators of specified Bombardier DHC‑8 (Dash 8) Series 100/200/300 aircraft to inspect and, if necessary, replace rear spar fittings that attach the wing to the fuselage because cracking or wear could lead to wing separation.  \n\nInitial inspections were required within 12 months of March 2002, with ongoing checks and mandated replacement or repair limits per the referenced technical bulletin; it aligns with Transport Canada AD CF‑2001‑42."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings","history":"/api/acts/ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings/history","analysis":"/api/acts/ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings/analysis","conflicts":"/api/acts/ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings/conflicts","importantCases":"/api/acts/ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings/important-cases","documents":"/api/acts/ad-dhc-8-85-fuselage-to-wing-rear-spar-fittings/documents"}}