{"id":"F2006B03468","name":"AD/BAe 146/14 - Electric Flap Control Unit","slug":"ad-bae-146-14-electric-flap-control-unit","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":43022,"registerId":"commonwealth-F2006B03468-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/BAe 146/14 - Electric Flap Control Unit","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)  \nBritish Aerospace BAe 146 Series Aeroplanes\n\nAD/BAe 146/14 Electric Flap Control Unit 8/89\n\nApplicability: All series 100 and 100A aircraft constructors number E1002 and subsequent. All series 200 and 200A aircraft constructors number E2012 and subsequent. All series 300 and 300A aircraft constructors number E3118 and subsequent.\n\nRequirement: 1. Action in accordance with BAe Mandatory Service Bulletin 11-36-01104A and B.\n\n2. Action in accordance with BAe Mandatory Service Bulletin 27-95-70420A. Compliance: Requirement 1 prior to 10 October 1989. Requirement 2 prior to 10 May 1990\\. Background: These modifications are intended to:\n\ndeter flight crew from removing or re-racking the flap system E.C.U. or pulling associated circuit breakers in light and thus endangering the aircraft during a legitimate flap system fault condition.\n\novercome spurious warnings caused by slow start-ups after prolonged cold soak conditions.\n\novercome the need to provide additional warning against re-racking in flight.\n\novercome the need to reduce the computer lightning susceptibility to an approved level.","sortOrder":0}],"analysis":{"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a discrete airworthiness directive with a narrow, specific scope (modifications to the Electric Flap Control Unit of BAe 146 aircraft). It has not expanded beyond its original safety purpose."},"complexity_factors":["Short, single-purpose directive (approximately 200 words)","Only 2 specific compliance requirements with clear deadlines","Limited applicability criteria based on aircraft series and constructor numbers","No nested conditional logic or exceptions","Minimal defined terms (only standard aviation abbreviations like E.C.U. and BAe)","Straightforward background section explaining rationale in plain language","References to external technical documents (Service Bulletins) but does not reproduce their content"],"plain_english_summary":"This AD mandates a safety-critical hardware modification to the Electric Flap Control Unit on specified BAe 146 Series 100/200/300 aircraft, requiring owners and operators to install British Aerospace’s mandatory changes.  \n\nThe upgrade prevents in‑flight removal/reset of the flap computer, eliminates spurious startup warnings, and improves lightning protection—removing the need for additional crew warnings and reducing the risk of flap-system failures that could endanger the aircraft."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The AD's scope aligns with its stated safety objectives. It mandates the specified BAe service-bulletin modifications to address re‑racking/breaker pulling, spurious cold‑soak warnings, re‑racking warnings and lightning susceptibility, and applies only to the listed constructor-numbered aircraft (Applicability; Requirements; Background). It does not broaden obligations beyond those aircraft or the specified modifications."},"complexity_factors":["Applicability is precise: three series with constructor-number thresholds, so determining whether an aircraft is covered requires checking serial records (Applicability).","Two separate mandatory service bulletins are required, each with its own compliance date (Requirement 1 prior to 10 October 1989; Requirement 2 prior to 10 May 1990).","Technical content covers ECU behaviour, warning logic after cold soak, and computer lightning susceptibility—each requiring specialised maintenance actions (Background).","Compliance imposes scheduling and direct costs on operators and maintenance organisations (operators must ‘action’ the service bulletins as required).","Regulatory enforcement is prescriptive: actions must be 'in accordance with' the BAe Mandatory Service Bulletins, creating dependency on manufacturer procedures.","Potential operational impact where work timing intersects service schedules or availability of parts and approved technicians."],"plain_english_summary":"This Airworthiness Directive requires operators of specified BAe 146 series aircraft (series 100, 200 and 300 from listed constructor numbers) to carry out two manufacturer-mandated modifications to the Electric Flap Control Unit and related systems by set deadlines. It falls on aircraft operators and maintenance organisations to schedule and pay for the work; the stated aims are to deter in‑flight re‑racking or breaker pulling, stop cold‑soak spurious warnings and reduce lightning susceptibility."}},"importantCases":[],"_links":{"self":"/api/acts/ad-bae-146-14-electric-flap-control-unit","history":"/api/acts/ad-bae-146-14-electric-flap-control-unit/history","analysis":"/api/acts/ad-bae-146-14-electric-flap-control-unit/analysis","conflicts":"/api/acts/ad-bae-146-14-electric-flap-control-unit/conflicts","importantCases":"/api/acts/ad-bae-146-14-electric-flap-control-unit/important-cases","documents":"/api/acts/ad-bae-146-14-electric-flap-control-unit/documents"}}