{"id":"F2008L02660","name":"AD/F100/89 - Flight Warning Computer","slug":"ad-f100-89-flight-warning-computer","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":74697,"registerId":"commonwealth-F2008L02660-current","compilationNumber":null,"startDate":"2026-04-02","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/F100/89 | Flight Warning Computer | 8/2008 |\n| ---------- | ----------------------- | ------ |\n\n| Applicability: | F28 Mark 0100 aircraft, all serial numbers, and F28 Mark 0070 aircraft serial numbers 11521, 11528 through 11537, 11545, 11547, 11553, 11557, 11561, 11562, 11566, 11567, 11571, 11572, 11576 through 11579, 11581 through 11583 (all fitted with centre wing fuel tank).                                                                                         |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Remove Flight Warning Computer (FWC) units with part number (P/N)80-0610-3-45 and P/N 80-0610-3-50 from the aircraft and replace with modified units with P/N 80-0610-3-55 in accordance with the Accomplishment Instructions of Fokker Services SBF100-31-067 dated 31 January 2008 or later revision approved by the European Aviation Safety Agency (EASA). |\n|                | 2. Amend the Airplane Flight Manual (AFM) as specified in Fokker Services Manual Change Notification - Operational Documentation (MCNO) F100-050 dated 31 January 2008 or using AFM pages supplied by Fokker Services.                                                                                                                                            |\n|                | 3. FWC units having P/N 80-0610-3-45 or P/N 80-0610-3-50 may not be installed as a replacement on any aircraft that has previously complied with Requirement 1 and 2, unless it has been modified to P/N 80-0610-3-55 standard in accordance with Honeywell SB 80-0610-31-0003 dated 13 February 2008.                                                            |\n|                | Note: EASA AD 2008-0090 dated 13 May 2008 refers.                                                                                                                                                                                                                                                                                                                 |\n| Compliance:    | For Requirement 1 - Within 36 calendar months after the effective date of this Directive.                                                                                                                                                                                                                                                                         |\n|                | For Requirement 2 - Concurrent with the accomplishment of the Requirement 1 replacement of the FWC unit.                                                                                                                                                                                                                                                          |\n|                | For Requirement 3 - After accomplishment of the Requirement 1 replacement of the FWC unit.                                                                                                                                                                                                                                                                        |\n|                | This Airworthiness Directive becomes effective on 31 July 2008.                                                                                                                                                                                                                                                                                                   |\n\n| Background: | A recent design review has been carried out on the F28 Mark 0070/0100 fuel system in accordance with the guidelines related to FAA SFAR 88 (Fuel Tank Safety Program) and JAA INT/POL/25/12. The review revealed that under certain failure conditions, prolonged dry running of the fuel transfer pumps may result in an ignition source in the centre wing fuel tank. This condition, if not corrected, could lead to ignition of flammable fuel vapours, resulting in fuel tank explosion and consequent loss of the aircraft.To address and correct this unsafe condition, new software (version V13.55) has been developed for the FWC. This software update introduces a decreased time delay of the centre wing fuel tank low pressure alert from 15 minutes to 60 seconds, to stop prolonged dry running of the fuel transfer pumps. |\n| ----------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n13 June 2008","sortOrder":0},{"sectionNumber":"AD/F100/89","sectionType":"part","heading":"AD/F100/89","content":"## AD/F100/89","sortOrder":1},{"sectionNumber":"Flight Warning Computer","sectionType":"part","heading":"Flight Warning Computer","content":"## Flight Warning Computer","sortOrder":2},{"sectionNumber":"8/2008","sectionType":"part","heading":"8/2008","content":"## 8/2008","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The directive's scope aligns with its stated safety purpose: it targets specific FWC part numbers and defined aircraft serials fitted with centre wing tanks to mitigate a fuel‑tank ignition risk by mandating replacement and AFM changes. It does not expand obligations beyond the listed aircraft, parts, or the specified corrective actions."},"complexity_factors":["Technical software change to the Flight Warning Computer (FWC V13.55) that alters alert timing (Background).","Multiple part numbers and replacement rules: remove P/N 80-0610-3-45/3-50 and fit P/N 80-0610-3-55; old units may not be reinstalled unless modified (Requirement 1 & 3).","Mandatory AFM amendment concurrent with the hardware/software change (Requirement 2).","Narrow applicability by aircraft model and serial numbers, requiring operators to check fleet records (Applicability).","Fixed compliance timeframe of 36 calendar months creates scheduling and resource-allocation needs (Compliance).","Dependence on external technical documents and approvals: Fokker Services SBF100-31-067, Honeywell SB 80-0610-31-0003, and EASA AD cross-references increase administrative steps (Requirement notes).","Regulatory approval constraint: replacements/modifications must follow EASA‑approved revisions or specified service bulletins (Requirement 1 & 3).","Rooted in fuel‑system safety review (SFAR 88 / JAA guidance), so technical validation and potential operational testing may be required (Background)."],"plain_english_summary":"This Airworthiness Directive requires certain Fokker F100/F28‑0070 aircraft fitted with a centre wing fuel tank to have specific Flight Warning Computer units (P/N 80‑0610‑3‑45 and 80‑0610‑3‑50) replaced by P/N 80‑0610‑3‑55 and the Airplane Flight Manual amended. The new FWC software (V13.55) shortens the centre tank low‑pressure alert delay from 15 minutes to 60 seconds to stop prolonged dry running of fuel transfer pumps.\n\nOperators pay for replacements and the AFM update; CASA enforces a 36‑month compliance window and older units cannot be reinstalled unless modified per Honeywell or EASA‑approved procedures."},"flash_summary_failed":{"failed":true,"reason":"Unauthenticated. Configure AI_GATEWAY_API_KEY or use a provider module. Learn more: https://ai-sdk.dev/unauthenticated-ai-gateway","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive with a focused, single-purpose scope: addressing a specific fuel tank safety issue through FWC software modification. The scope remains tightly constrained to the identified safety risk and the specific aircraft fleet affected."},"complexity_factors":["Specific part number tracking required (three distinct P/Ns: 80-0610-3-45, 80-0610-3-50, and 80-0610-3-55)","Serial number-specific applicability (complex list of affected F28 Mark 0070 aircraft)","Cross-reference to external technical documents (Fokker Services SBF100-31-067, Honeywell SB 80-0610-31-0003, EASA AD 2008-0090)","Staged compliance requirements with interdependencies (Requirement 3 only applies after Requirement 1 is completed)","Reference to international regulatory frameworks (FAA SFAR 88, JAA INT/POL/25/12) in background section"],"plain_english_summary":"This AD requires owners/operators of specified Fokker F100/F28 aircraft to replace older Flight Warning Computer units with a modified version and update the flight manual within 36 months. The change installs software that cuts fuel-pump failure warning delay from 15 minutes to 60 seconds.\n\nThe upgrade prevents centre-wing fuel pumps running dry and the resulting spark/ignition risk; once upgraded, the old units must not be reinstalled unless modified to the new standard."}},"importantCases":[],"_links":{"self":"/api/acts/ad-f100-89-flight-warning-computer","history":"/api/acts/ad-f100-89-flight-warning-computer/history","analysis":"/api/acts/ad-f100-89-flight-warning-computer/analysis","conflicts":"/api/acts/ad-f100-89-flight-warning-computer/conflicts","importantCases":"/api/acts/ad-f100-89-flight-warning-computer/important-cases","documents":"/api/acts/ad-f100-89-flight-warning-computer/documents"}}