{"id":"F2009L03657","name":"AD/F27/103 Amdt 8 - Structural Limitations","slug":"ad-f27-103-amdt-8-structural-limitations","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":141491,"registerId":"commonwealth-F2009L03657-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Fokker F27 Series Aeroplanes","sectionType":"division","heading":"Fokker F27 Series Aeroplanes","content":"### Fokker F27 Series Aeroplanes\n\n| AD/F27/103 Amdt 8 | Structural Limitations | 11/2009 |\n| ----------------- | ---------------------- | ------- |\n\n| Applicability: | All F27 Mk100 to Mk700 model aeroplanes. |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Inspect, modify or retire:(a) Airframe parts as specified in Fokker Structural Integrity Program (SIP) Document 27438 Revision 14 and subsequent revisions.(b) Main landing gear components as specified in Dowty Rotol Service Bulletin No. 32-152B, Revision 7 and subsequent revisions.(c) Nose landing gear components as specified in Dowty Rotol Service Bulletin No. 32-154B Revision 4 and subsequent revisions.2. Retire the airframe from service before exceeding 90,000 flights.Load variability factors derived from Fatigue Meter and operational records may not be used in connection with the times specified in the SIP Document without the specific approval of the Authority.In spite of the allowable crack lengths and crack propagation data which may be provided by the manufacturer, an aircraft shall not be returned to service with known unrepaired cracks without the approval of the Authority or of the operator’s authorised structures design signatory.Note: Netherlands AD NL-1991-049 dated 7 June 1991 refers. |\n| Compliance: | Compliance remains unchanged effective from 25 May 1995. |\n| | This Amendment becomes effective on 22 October 2009. |\n| Background: | Amendment 6 referenced the latest revisions of the reference documents.Amendment 7 removed reference to “subsequent temporary revisions” in documentation, and reformatted the text of the AD. |\n\n| | Amendment 8 changes the Applicability in order to exclude the F27Mk050(2) and Mk0604 models, updates the revision status of the SIP, includes subsequent revisions to the SIP and referenced SB’s to ensure continuity, and removes reference to Note 1 and Note 2. This amendment has been made with the assistance of the manufacturer. |\n| --- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nDavid Villiers \nDelegate of the Civil Aviation Safety Authority\n\n9 September 2009","sortOrder":0},{"sectionNumber":"AD/F27/103 Amdt 8","sectionType":"part","heading":"AD/F27/103 Amdt 8","content":"## AD/F27/103 Amdt 8","sortOrder":1},{"sectionNumber":"Structural Limitations","sectionType":"part","heading":"Structural Limitations","content":"## Structural Limitations","sortOrder":2},{"sectionNumber":"11/2009","sectionType":"part","heading":"11/2009","content":"## 11/2009","sortOrder":3}],"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":true,"description":"Amendment 8 alters scope by changing the Applicability to exclude the F27Mk050(2) and Mk0604 models and by updating the treatment of referenced documents to include subsequent revisions of the SIP and service bulletins. This narrows the set of covered aircraft and ties compliance to up‑to‑date external documents, per the amendment note: \"Amendment 8 changes the Applicability... excludes the F27Mk050(2) and Mk0604 models, updates the revision status of the SIP, includes subsequent revisions to the SIP and referenced SB’s...\""},"complexity_factors":["Multiple external normative references requiring operators to follow current revisions: Fokker SIP Document 27438 Revision 14 and subsequent revisions; Dowty Rotol Service Bulletin No. 32‑152B Revision 7 and No. 32‑154B Revision 4 — Requirement 1(a)–(c).","Firm retirement limit for airframe life (before exceeding 90,000 flights) imposes a hard operational/asset‑life constraint on operators — Requirement 2.","Restrictions on using load variability factors from Fatigue Meter or operational records without specific approval of the Authority create a discretionary approval step and limit alternative means of compliance — Requirement 2 (sentence regarding load variability factors).","Return‑to‑service prohibition for aircraft with known unrepaired cracks without Authority or operator’s authorised structures design signatory approval introduces mandatory engineering signoff and regulatory oversight — Requirement final sentence.","Amendment to Applicability (exclusion of F27Mk050(2) and Mk0604) changes which models are covered and may require fleet‑by‑fleet compliance assessment — Amendment note.","Compliance timing language: states compliance unchanged from 25 May 1995 while the amendment becomes effective 22 October 2009, producing layered effective dates and potential transitional interpretation issues — Compliance block.","Cross‑jurisdictional reference (Netherlands AD NL‑1991‑049) adds an international normative context that operators may need to reconcile — Note.","Operational burdens: recurring inspections/modifications, parts retirement and recordkeeping increase maintenance planning, downtime and cost for operators (implicit in Requirement 1 and 2)."],"plain_english_summary":"This amendment requires operators of Fokker F27 Mk100–Mk700 series aeroplanes to inspect, modify or retire specified airframe, main and nose landing‑gear parts in line with Fokker SIP Document 27438 (Rev 14 and later) and Dowty Rotol service bulletins. It mandates retirement of each airframe before 90,000 flights and forbids relying on load‑variability factors or returning aircraft with known, unrepaired cracks without approval from the Civil Aviation Safety Authority or an authorised structures design signatory."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"The original AD (implied by Amendment 8's description) appears to have covered all F27 models including Mk050(2) and Mk0604 variants. Amendment 8 explicitly narrows applicability to exclude these two models, reducing scope. Additionally, the amendment removes references to 'Note 1 and Note 2' and 'subsequent temporary revisions,' suggesting the original was broader or more permissive regarding documentation flexibility. The scope has contracted rather than expanded, but the regulatory burden on remaining applicable aircraft has tightened through updated revision requirements."},"complexity_factors":["Multiple nested document references requiring cross-checking (Fokker SIP Document 27438 Rev 14, Dowty SB 32-152B Rev 7, Dowty SB 32-154B Rev 4)","Conditional logic around 'subsequent revisions' — operators must track evolving manufacturer documents, not just the AD itself","Exception-within-exception structure: load variability factors generally prohibited, but allowed with 'specific approval of the Authority'; cracks generally prohibited even if manufacturer-allowable, but allowed with dual-path approval (Authority OR authorised signatory)","Amendment history creates interpretive burden — must understand what changed from Amendments 6 and 7 to apply Amendment 8 correctly","Dual effective dates: compliance 'unchanged effective from 25 May 1995' but amendment itself 'becomes effective 22 October 2009'"],"plain_english_summary":"This CASA Airworthiness Directive imposes mandatory structural safety limits on Australian-operated Fokker F27 Mk100–Mk700 series (excluding Mk050(2) and Mk0604). It requires inspections, specific repairs/replacements per Fokker and Dowty Rotol guidance, and absolute retirement at 90,000 flights. Operators may not use their own data to extend limits, and aircraft with known cracks are grounded unless CASA or an authorised engineer grants explicit approval."}},"importantCases":[],"_links":{"self":"/api/acts/ad-f27-103-amdt-8-structural-limitations","history":"/api/acts/ad-f27-103-amdt-8-structural-limitations/history","analysis":"/api/acts/ad-f27-103-amdt-8-structural-limitations/analysis","conflicts":"/api/acts/ad-f27-103-amdt-8-structural-limitations/conflicts","importantCases":"/api/acts/ad-f27-103-amdt-8-structural-limitations/important-cases","documents":"/api/acts/ad-f27-103-amdt-8-structural-limitations/documents"}}