{"id":"F2007L00699","name":"AD/AMD 50/40 - Software Integrity Check and Enhanced Avionics System Upgrade","slug":"ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":64283,"registerId":"commonwealth-F2007L00699-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"AMD Falcon 50 and 900 Series Aeroplanes","sectionType":"division","heading":"AMD Falcon 50 and 900 Series Aeroplanes","content":"### AMD Falcon 50 and 900 Series Aeroplanes\n\n| AD/AMD 50/40 | Software Integrity Check and Enhanced Avionics System Upgrade | 4/2007 |\n| ------------ | ------------------------------------------------------------- | ------ |\n\n| Applicability: | Falcon 900EX aeroplanes, serial numbers (S/N) 97, 120 to 170 inclusive and Falcon 900EX (version F900DX) aeroplanes S/N 601 to 607 inclusive.                                                                                                                             |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. Perform a software check using a dedicated software tool named “Flash Integrity Check” (FLICK) in accordance with the accomplishment instructions of Dassault Aviation Falcon SB F900EX-298 dated 7 September 2006 or later Revision approved by the EASA.             |\n|                | 2. Make a temporary amendment to Chapter 5-40 of the Aircraft Maintenance Manual (AMM) to indicate that the MP 45-403 \"Software modules integrity check\" is to be accomplished at 40 day intervals.                                                                       |\n|                | Note 1: To record the temporary inspection schedule, a copy of this Directive may be included in of the AMM as a temporary change.                                                                                                                                        |\n|                | 3. Modify the aircraft in accordance with the accomplishment instructions of SB F900EX-304 (modification M5255) dated 8 February 2007 or later Revision approved by the EASA.                                                                                             |\n|                | This is considered to be a terminating action for the temporary repetitive inspection requirements introduced by the Requirement 2 AMM amendment and the temporary amendment to the AMM may be removed.                                                                   |\n|                | 4. For aircraft with advanced graphics module (AGM) and enhanced ground proximity warning module (EGPWM) modules with a part number (P/N) prior to 7026545-1904 (AGM) and 7028419-1904 (EGPWM), perform a check with the FLICK tool in accordance with the AMM MP 45-401. |\n|                | Note 2: EASA AD 2007-0032 refers.                                                                                                                                                                                                                                         |\n| Compliance:    | For Requirement 1 and 2 - No later than 40 days after the effective date of this Directive.                                                                                                                                                                               |\n|                | For Requirement 3 - Within 12 months after the effective date of this Directive.                                                                                                                                                                                          |\n|                | For Requirement 4 - After each operational software loading.                                                                                                                                                                                                              |\n\n|             | This Airworthiness Directive becomes effective on 12 April 2007.                                                                                                                                                                                                                                                                                                  |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Background: | EASA has advised that during an internal review, it was discovered that some software integrity checks were not fully implemented in modules of the Honeywell EPIC avionics, as used in Falcon EASy aircraft.                                                                                                                                                     |\n|             | Consequently, the continuing integrity of the modules’ software cannot be demonstrated, as required by software requirements. Software corruption may then potentially occur during any upload of the operational software and also as random effects under normal conditions.                                                                                    |\n|             | This Directive mandates the use of the FLICK tool on a regular basis pending a software correction. The software load implementing the terminating actions also includes a software correction for the untimely inhibition of the \"flap asymmetry” detection below 200ft. This is mandated to correct a situation that may not conform to EASA CS 25.671 (c) (1). |\n\n![](image.001.png)  \nDavid Punshon  \nDelegate of the Civil Aviation Safety Authority\n\n26 February 2007","sortOrder":0},{"sectionNumber":"AD/AMD 50/40","sectionType":"part","heading":"AD/AMD 50/40","content":"## AD/AMD 50/40","sortOrder":1},{"sectionNumber":"Software Integrity Check and Enhanced Av","sectionType":"part","heading":"Software Integrity Check and Enhanced Avionics System Upgrade","content":"## Software Integrity Check and Enhanced Avionics System Upgrade","sortOrder":2},{"sectionNumber":"4/2007","sectionType":"part","heading":"4/2007","content":"## 4/2007","sortOrder":3}],"analysis":{"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"},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":true,"description":"Compared with routine maintenance practice, the Directive expands scope by imposing mandatory short‑interval software integrity checks and a formal temporary AMM amendment (Requirements 1–2) and by requiring a specific software/hardware modification within 12 months as a terminating action (Requirement 3). It further adds conditional, after‑load checks for older AGM/EGPWM parts (Requirement 4). Operators bear the inspection, tool‑use and upgrade costs and must follow SB procedures and EASA‑approved revisions, creating a compliance burden tied to specific parts, serial numbers and timelines."},"complexity_factors":["Multiple mandatory actions of different kinds (software integrity check, AMM temporary amendment, hardware/software modification, and conditional post‑load checks) — see Requirements 1–4.","Short recurring inspection interval (40 days) imposed temporarily until a terminating modification is applied — Requirement 2 and Compliance.","Conditional applicability tied to specific serial numbers (S/N 97, 120–170 and S/N 601–607) limits scope but requires accurate fleet tracking — Applicability.","Dependency on manufacturer service bulletins and later EASA‑approved revisions for the exact procedures (Dassault SB F900EX‑298 and SB F900EX‑304) — Requirements 1 and 3.","Part‑number conditional check for older AGM/EGPWM modules (P/Ns prior to specified numbers) requires parts‑level identification during maintenance — Requirement 4.","Terminology of 'terminating action' changes operational practice: temporary repetitive work can be removed only after compliance with the modification — Requirement 3.","Administrative requirement to record the temporary AMM change (option to insert the Directive in the AMM) creates compliance/record‑keeping obligations — Note 1."],"plain_english_summary":"This directive forces operators of specified Falcon 900EX and F900DX aeroplanes (listed serial numbers) to run a dedicated software-integrity tool (FLICK), add a temporary 40‑day inspection requirement to the Aircraft Maintenance Manual (AMM), and install an avionics/software modification within 12 months that removes the temporary checks. It also requires FLICK checks after each software load for certain older AGM/EGPWM modules. The stated purpose is to detect software corruption and fix a flap‑asymmetry detection issue; operators pay for the inspections, tool use and the mandated upgrade."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This is a standard Airworthiness Directive format. The scope remains tightly focused on the specific software integrity issue in the Honeywell EPIC avionics system and the flap asymmetry detection problem. The requirements follow the typical AD structure of immediate inspection, temporary repetitive action, and permanent terminating action."},"complexity_factors":["Multiple serial number ranges with different applicability (Falcon 900EX vs F900DX variant)","Four distinct requirements with different compliance timeframes (40 days, 12 months, and recurring 'after each loading')","Cross-references to external documents: Dassault Aviation Service Bulletin F900EX-298, SB F900EX-304, and EASA AD 2007-0032","Technical aviation terminology requiring domain knowledge (AMM, MP 45-403, part numbers like 7026545-1904)","Conditional logic: Requirement 4 only applies to aircraft with specific part numbers 'prior to' certain versions","Terminating action concept: Requirement 3 cancels the temporary requirements in Requirement 2"],"plain_english_summary":"Owners/operators of certain Dassault Falcon 900EX/F900DX jets (S/N 97, 120–170, 601–607) must comply with a mandatory CASA Airworthiness Directive requiring an urgent software integrity check (FLICK) within 40 days, repeated after certain updates, and a permanent Honeywell EPIC software modification within 12 months. It fixes a risk of software corruption and a flap-asymmetry warning deficiency; non‑compliance grounds the aircraft."}},"importantCases":[],"_links":{"self":"/api/acts/ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade","history":"/api/acts/ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade/history","analysis":"/api/acts/ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade/analysis","conflicts":"/api/acts/ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade/conflicts","importantCases":"/api/acts/ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade/important-cases","documents":"/api/acts/ad-amd-50-40-software-integrity-check-and-enhanced-avionics-system-upgrade/documents"}}