{"id":"F2006B09624","name":"AD/F100/23 - Cargo Door Frame","slug":"ad-f100-23-cargo-door-frame","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":54398,"registerId":"commonwealth-F2006B09624-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/F100/23 - Cargo Door Frame","content":"COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 \\- 105 CIVIL AVIATION SAFETY AUTHORITY\n\nSCHEDULE OF AIRWORTHINESS DIRECTIVES\n\n![](image.001.png)  \nFokker F100 (F28 Mk 100) Series Aeroplanes\n\nAD/F100/23 Cargo Door Frame 4/99\n\nApplicability: F.28 Mk.0100 aircraft, serial numbers as listed in Fokker Service Bulletin (SB) F100- 52-050, Revision 1 dated 14 September 1994.\n\nRequirement: Install two reinforcement plates under each hook latch fitting of each large cargo door in accordance with the Accomplishment Instructions of Fokker SB F100-52-050 Revision 1 dated 14 September 1994.\n\nNote: RLD BLA 94-157(A) refers.\n\nCompliance: Unless previously accomplished, before accumulating 11,000 flight cycles since new or 22 May 1999, whichever occurs later.\n\nThis Airworthiness Directive becomes effective on 22 April 1999.\n\nBackground: Stress analyses and destructive tests on the frames of F.28 Mk.0100 large cargo doors have shown that fatigue cracks may develop in the area of the hook latch fittings.\n\nThis AD requires a modification to repair possible existing cracks and to prevent the development of new cracks in the affected large cargo door frames.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a discrete, targeted safety directive addressing a specific structural fatigue issue in a particular aircraft type. The scope remains tightly focused on cargo door frame reinforcement with no evidence of scope creep."},"complexity_factors":["Single, specific technical requirement (install two plates per fitting)","Only one defined term of note ('flight cycles' — implied industry standard)","Clear applicability criteria (specific aircraft model and serial numbers)","Simple compliance deadline structure (whichever is later of two dates)","No nested exceptions or conditional logic","Short length (under 300 words)","Single cross-reference to a service bulletin (Fokker SB F100-52-050)"],"plain_english_summary":"This mandatory Airworthiness Directive requires operators of specified Fokker F100 aircraft to fit reinforcement plates under the cargo door hook latch fittings (or repair detected cracks) to prevent fatigue cracking in the cargo door frame. \n\nIt affects airlines and other operators in Australia for aircraft listed in the Fokker service bulletin and must be done before 11,000 flight cycles or by 22 May 1999, whichever is later, to avoid risk of cargo door failure and rapid decompression."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The directive's requirements align with its stated purpose in the background text (repair existing cracks and prevent new ones). The instrument specifies affected serial numbers and a concrete modification; there is no textual indication the scope was broadened or narrowed from the stated intent."},"complexity_factors":["Technical modification: installation of reinforcement plates requires maintenance shop work and access to service bulletin instructions.","Applicability limited to specific serial-numbered aircraft listed in the service bulletin, requiring operator record checks.","Compliance deadline tied to flight cycles or a calendar date, necessitating tracking of flight-cycle counters and scheduling.","Remedial and preventive aim: may involve locating and repairing existing cracks as well as installing parts to prevent new cracks.","Supply and logistics: operators must source parts and qualified personnel to perform the modification.","Regulatory traceability: operators must document compliance with the AD for airworthiness records."],"plain_english_summary":"This Airworthiness Directive requires certain Fokker F100 (F28 Mk 100) aeroplanes (specified by serial number in the Fokker service bulletin) to have two reinforcement plates fitted under each hook latch of each large cargo door, following Fokker SB F100-52-050 Revision 1. It responds to tests showing possible fatigue cracks. Aircraft operators must arrange and pay for the modification and complete it before the aeroplane reaches 11,000 flight cycles or by 22 May 1999, whichever is later."}},"importantCases":[],"_links":{"self":"/api/acts/ad-f100-23-cargo-door-frame","history":"/api/acts/ad-f100-23-cargo-door-frame/history","analysis":"/api/acts/ad-f100-23-cargo-door-frame/analysis","conflicts":"/api/acts/ad-f100-23-cargo-door-frame/conflicts","importantCases":"/api/acts/ad-f100-23-cargo-door-frame/important-cases","documents":"/api/acts/ad-f100-23-cargo-door-frame/documents"}}