{"id":"F2006B09665","name":"AD/F100/8 - RH Wing Skin at Fuel Adaptor Position","slug":"ad-f100-8-rh-wing-skin-at-fuel-adaptor-position","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":115794,"registerId":"commonwealth-F2006B09665-current","compilationNumber":null,"startDate":"2026-04-03","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/F100/8 - RH Wing Skin at Fuel Adaptor Position","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/F100/8 RH Wing Skin at Fuel Adaptor Position 4/99\n\nApplicability: F.28 Mk.0100 aircraft, serial numbers 11244 through 11286, 11289 through 11293,\n\n11295, 11297, 11300, 11303, 11306, 11308, 11310 and 11312.\n\nRequirement: Install internal and external doubler plates around the fuel adapter position in accordance with the Accomplishment Instructions of Fokker Service Bulletin (SB) F100-57-008 Revision 2, dated 22 September 1995. On aircraft that have already been modified in accordance with Fokker SB F100-57-008, Revision 1 (including changes as advised by the manufacturer), no further action is required.\n\nNote: RLD BLA 1991-131/3(A) refers.\n\nCompliance: Unless previously accomplished, before accumulating 12,000 flight cycles since new.\n\nThis Airworthiness Directive becomes effective on 22 April 1999.\n\nBackground: Fatigue tests on the F.28 Mk.0100 have shown that cracks may develop in the lower skin of the RH wing at the attachment bolt holes of the fuel adapter. This condition, if not corrected, reduces the fatigue life of the affected structure beyond acceptable limits. This AD requires a modification to prevent cracking.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":2,"scope_assessment":{"changed":false,"description":"This is a standard airworthiness directive with narrow, targeted scope addressing a specific structural fatigue issue on specific aircraft. It has not expanded beyond its original safety purpose."},"complexity_factors":["Single, specific technical requirement with clear reference to manufacturer instructions","Limited applicability to specific aircraft serial numbers only","Simple compliance condition: 12,000 flight cycles or previously accomplished","No nested exceptions or conditional logic beyond the single exemption for aircraft already modified under Revision 1","Short document (under 300 words) with minimal defined terms"],"plain_english_summary":"CASA requires owners/operators of specific Fokker F100s (listed serial numbers) to install internal and external strengthening plates (“doublers”) at the right-hand wing fuel adapter per Fokker Service Bulletin F100‑57‑008 Revision 2.  \n\nThe mandatory fix—before 12,000 flight cycles unless previously done—stops fatigue cracking around the fuel-line bolt holes, preserving structural life and preventing possible wing failure."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The AD targets a fixed set of serial-numbered Fokker F100 airframes and mandates a specific structural modification per the cited Service Bulletin. It excludes aircraft already modified under the earlier SB revision. The directive does not broaden to other models or additional inspections beyond the stated modification."},"complexity_factors":["Narrow applicability to specific serial numbers (Applicability)","Single prescriptive technical remedy: install doubler plates per SB F100-57-008 Rev 2 (Requirement)","Exception for aircraft already modified under SB Rev 1 (Requirement)","Compliance measured by accumulated flight cycles rather than calendar time (Compliance)","Dependency on an external technical document (manufacturer Service Bulletin) for execution details (Requirement)","Operational impacts: structural work implies maintenance scheduling, downtime and cost for operators (Requirement/Background)","Reference to prior inspection/test material (RLD BLA) increases documentary cross-references (Note)"],"plain_english_summary":"This Airworthiness Directive requires operators of listed Fokker F100 (F28 Mk 100) aeroplanes to install internal and external doubler plates around the right-hand wing fuel-adaptor using Fokker Service Bulletin F100‑57‑008 Revision 2 to prevent fatigue cracking. Operators must complete the modification before the aircraft reach 12,000 flight cycles unless the earlier SB Revision 1 modification was already done. The operator/owner pays for and schedules the structural work; CASA enforces compliance and the requirement may cause aircraft downtime."}},"importantCases":[],"_links":{"self":"/api/acts/ad-f100-8-rh-wing-skin-at-fuel-adaptor-position","history":"/api/acts/ad-f100-8-rh-wing-skin-at-fuel-adaptor-position/history","analysis":"/api/acts/ad-f100-8-rh-wing-skin-at-fuel-adaptor-position/analysis","conflicts":"/api/acts/ad-f100-8-rh-wing-skin-at-fuel-adaptor-position/conflicts","importantCases":"/api/acts/ad-f100-8-rh-wing-skin-at-fuel-adaptor-position/important-cases","documents":"/api/acts/ad-f100-8-rh-wing-skin-at-fuel-adaptor-position/documents"}}