{"id":"F2005L02838","name":"AD/F100/72 - Landing Gear - Brake Control Levers","slug":"ad-f100-72-landing-gear-brake-control-levers","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":37826,"registerId":"commonwealth-F2005L02838-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Fokker F100 (F28 Mk 100) Series Aeroplan","sectionType":"division","heading":"Fokker F100 (F28 Mk 100) Series Aeroplanes","content":"### Fokker F100 (F28 Mk 100) Series Aeroplanes\n\n| AD/F100/72 | Landing Gear - Brake Control Levers | 11/2005 |\n| ---------- | ----------------------------------- | ------- |\n\n| Applicability: | Fokker Aircraft B.V. Model F28 Mark 0070 and Mark 0100 aeroplanes serial numbers 11244 through 11585. |\n| -------------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | 1. Inspect the brake control levers for excessive wear in accordance with Section 3. Accomplishment Instructions of Fokker Service Bulletin (SB) F100-32-142 dated 12 August 2005 or a later CAA-NL approved revision and when no significant wear is found on the brake control levers, no further action is required and the aircraft may be returned to service.(a) When the remaining material thickness is determined to be less than 2 mm (0.08 inch), replace the affected brake control levers with serviceable parts in accordance with Section 3 of the Accomplishment Instructions of Fokker SB F100-32-142 or later CAA-NL approved revision.(b) When the remaining material thickness is determined to be between 2 mm (0.08 inch) and 4 mm (0.16 inch), replace the affected brake control levers in accordance with Section 3 of the Accomplishment Instructions of Fokker SB F100-32-142 or later CAA-NL approved revision.Note: CAA-NL AD NL-2005-011and EASA Reference No 2005-2602 dated 29 August 2005 refers. |\n| Compliance: | 1. Within the next 1,500 flight cycles or 12 months after the effective date of this directive, whichever occurs first.(a) Before further flight.(b) In accordance with the schedule as indicated in paragraph B(9) of Section 3 of the Accomplishment Instructions of Fokker SB Fl 00-32-142 or later CAA-NL approved revision. |\n| | This Airworthiness Directive becomes effective on 27 October 2005. |\n\n| Background: | After landing, the flight crew of a Fokker 100 (F28 Mark 0100) noted that an extreme difference in pedal angle was required to achieve equal brake action on the left hand (LH) and right hand(RH) Main Landing Gear (MLG) brakes. The brake temperature of the LH brake system was reported to be higher than that of the RH brake system. During the subsequent troubleshooting, it was noted that the attachment holes in the control levers of the RH MLG (Normal and Alternate) brake cables were worn out to an extent that imminent failure was likely to occur. The aircraft (and the affected levers) had accumulated 21,460 flight hours and 15,583 flight cycles. Further investigation showed that the abnormal brake behaviour had been caused by a (unrelated) failure of the RH Normal Brake Control Valve. Fokker Services have determined that a disconnect of one or two of the lower cables would not affect the intended braking action on the MLG involved. However, this condition, if not corrected, can lead to unintended (uncommanded) braking due to the loss of cable tension on the lower side of the levers, possibly resulting in loss of control of the aircraft during the take-off run, landing roll-out or taxiing. Since an unsafe condition has been identified that may exist or develop on aircraft of the same type design, this Airworthiness Directive requires a one-time inspection and, if necessary, replacement of the brake control levers. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png) \nJames Coyne \nDelegate of the Civil Aviation Safety Authority\n\n16 September 2005","sortOrder":0},{"sectionNumber":"AD/F100/72","sectionType":"part","heading":"AD/F100/72","content":"## AD/F100/72","sortOrder":1},{"sectionNumber":"Landing Gear - Brake Control Levers","sectionType":"part","heading":"Landing Gear - Brake Control Levers","content":"## Landing Gear - Brake Control Levers","sortOrder":2},{"sectionNumber":"11/2005","sectionType":"part","heading":"11/2005","content":"## 11/2005","sortOrder":3}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a targeted safety directive addressing a specific mechanical wear issue identified through incident investigation. The scope remains precisely limited to brake control lever inspection and replacement on affected Fokker F100 aircraft, consistent with the original purpose of preventing unintended braking failures."},"complexity_factors":["Short, single-purpose directive focused on one mechanical component","Only 4 defined thresholds (2mm, 4mm, 1,500 flight cycles, 12 months)","Simple conditional structure: inspect → if A then replace immediately, if B then replace on schedule, if neither then clear","References external technical document (Fokker Service Bulletin) but incorporates key requirements directly","No nested exceptions or recursive definitions","Single applicability criterion (specific serial number range)"],"plain_english_summary":"This AD mandates operators of certain Fokker F100 passenger jets (serials 11244–11585) to inspect brake control levers for dangerous wear and replace them if necessary. Worn levers can cause unexpected braking and loss of control.\n\nAirlines and maintenance crews must inspect within 1,500 flight cycles or 12 months. If lever thickness is under 2 mm, replace before the next flight; if 2–4 mm, follow the scheduled replacement requirement. This is a mandatory safety requirement."},"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The AD limits action to the identified Fokker F100 serial numbers and mandates a one‑time inspection and replacement according to defined thickness thresholds and the referenced service bulletin. It does not expand to recurring inspections or to aircraft outside the listed serial range; obligations (inspection, measurement, replacement) fall on the operator/owner under the stated timelines."},"complexity_factors":["Narrow applicability tied to specific serial numbers (Applicability) — reduces population but requires accurate fleet identification.","Decision depends on measured remaining material thickness with two thresholds (<2 mm; 2–4 mm) that trigger replacement actions (Requirement, items (a) and (b)).","Multiple compliance timings: within 1,500 flight cycles or 12 months, and 'before further flight' for cases of significant wear (Compliance) — creates different operational urgencies.","Work must follow Section 3 of Fokker SB F100‑32‑142 or a later CAA‑NL approved revision (Requirement) — dependence on an external service bulletin and regulatorally approved revisions affects what actions are acceptable.","Replacement requires 'serviceable parts' (Requirement) — entails parts sourcing, inventory and fitment logistics for operators/owners.","Risk basis drawn from an incident report of worn attachment holes causing unequal brake action and potential unintended braking (Background) — justifies urgency but links mandated work to a specific failure mode.","Regulatory cross-references to CAA‑NL AD NL‑2005‑011 and EASA reference (Note) — adds tracking and compliance complexity for operators subject to multiple authorities."],"plain_english_summary":"Requires a one‑time inspection of brake control levers on Fokker F100 aeroplanes (serials 11244–11585) and replacement if wear reduces material below prescribed thickness limits. It responds to reports that worn attachment holes can produce unequal or unintended braking during take‑off, landing or taxi. Compliance deadlines are set (1,500 flight cycles or 12 months; or before further flight for severe wear) and work must follow Section 3 of Fokker Service Bulletin F100‑32‑142 or a later CAA‑NL approved revision."},"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-f100-72-landing-gear-brake-control-levers","history":"/api/acts/ad-f100-72-landing-gear-brake-control-levers/history","analysis":"/api/acts/ad-f100-72-landing-gear-brake-control-levers/analysis","conflicts":"/api/acts/ad-f100-72-landing-gear-brake-control-levers/conflicts","importantCases":"/api/acts/ad-f100-72-landing-gear-brake-control-levers/important-cases","documents":"/api/acts/ad-f100-72-landing-gear-brake-control-levers/documents"}}