{"id":"F2008L01098","name":"AD/ATR 42/23 - Rear Pressure Bulkhead Area - Electrical Wire Chafing","slug":"ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":73254,"registerId":"commonwealth-F2008L01098-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Avions de Transport Regional ATR 42 Seri","sectionType":"division","heading":"Avions de Transport Regional ATR 42 Series Aeroplanes","content":"### Avions de Transport Regional ATR 42 Series Aeroplanes\n\n| AD/ATR 42/23 | Rear Pressure Bulkhead Area - ElectricalWire Chafing | 6/2008 DM |\n| ------------ | ---------------------------------------------------- | --------- |\n\n| Applicability: | ATR 42 model aeroplanes, all serial numbers, as follows                                                                                                                                                                  |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n|                | ATR 42-200, 42-300 and 42-320 that have embodied ATR modification (Mod) 00639, except aircraft which have received ATR Service Bulletin (SB)ATR42-92-0018 whilst in service.                                             |\n|                | ATR 42-400 and 42-500, except aeroplanes that have embodied ATR Mod 05780 during production or ATR SB ATR42-92-0018 whilst in service.                                                                                   |\n|                | Note 1: Mod 00639 has been embodied on production aircraft Manufacturer Serial Number (MSN) 109 and MSN 113 and was factory-incorporated from MSN 116.                                                                   |\n|                | Note 2: Mod 05780 is now factory-incorporated on ATR 42-500 from MSN 667.                                                                                                                                                |\n| Requirement:   | 1. Perform a one-time inspection of the electrical routing in the rear baggage zone in accordance with the accomplishment instructions of SB ATR42-92-0015, dated 11 February 2008.                                      |\n|                | 2. If ANY damage is found during the Requirement 1 inspection (chafing and/or contact between bundles of cables and the airframe structure):                                                                             |\n|                | a. Contact and report the finding(s) to ATR (by means of the accomplishment form enclosed in SB ATR42-92-0015) to obtain an approved repair solution and perform the repair in accordance with the ATR instructions, and |\n|                | b. Modify the electrical routing and wire bundle protection in accordance with the accomplishment instruction of SB ATR42-92-0018, dated 11 February 2008.                                                               |\n|                | 3. If damage is not found during the Requirement 1 inspection:                                                                                                                                                           |\n|                | a. Report to ATR the result of inspection by using the form enclosed in SB ATR42-92-0015, and                                                                                                                            |\n|                | b. Modify the electrical routing and wire bundle protection in accordance with the accomplishment instruction of SB ATR42-92-0018.                                                                                       |\n\n|             | The use of later revisions of SB ATR42-92-0015 and SB ATR42-92-0018 approved by the European Aviation Safety Agency (EASA) is acceptable for compliance with the requirements of this Directive.                                                                                                                                                                                     |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |\n|             | Note 3: EASA AD 2008-0062 refers.                                                                                                                                                                                                                                                                                                                                                    |\n| Compliance: | For Requirement 1 - Within the next 550 hours time in service (TIS) after the effective date of this Directive.                                                                                                                                                                                                                                                                      |\n|             | For Requirement 2.a. - Before further flight after the Requirement 1 inspection.                                                                                                                                                                                                                                                                                                     |\n|             | For Requirement 2.b. - Before further flight after any repairs accomplished in accordance with Requirement 2.a.                                                                                                                                                                                                                                                                      |\n|             | For Requirement 3.a. - Within 15 days after accomplishment of the Requirement 1 inspection.                                                                                                                                                                                                                                                                                          |\n|             | For Requirement 3.b. - Within 5 000 hours TIS after the effective date of this Directive.                                                                                                                                                                                                                                                                                            |\n|             | This Airworthiness Directive becomes effective on 18 April 2008.                                                                                                                                                                                                                                                                                                                     |\n| Background: | EASA has advised that an ATR operator reported some spurious “Pitch disconnect” warning and “AIL and R ELEV” Anti-Ice Horn Fault caution annunciations which precluded the use of the autopilot.                                                                                                                                                                                     |\n|             | During the investigation, chafed wiring was found in the rear baggage zone, close to the forward side of the aft pressure bulkhead, due to contact with a structural securing screw. The concerned wiring harness includes rudder trim, pitch trim and stick pusher control wires. Damages on those wires might lead to the loss of fail safe criteria for those critical functions. |\n|             | To address the unsafe condition, this Directive mandates a one-time inspection and a routing modification of the electrical wires in the bulkhead area.                                                                                                                                                                                                                              |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n15 April 2008","sortOrder":0},{"sectionNumber":"AD/ATR 42/23","sectionType":"part","heading":"AD/ATR 42/23","content":"## AD/ATR 42/23","sortOrder":1},{"sectionNumber":"Rear Pressure Bulkhead Area - Electrical","sectionType":"part","heading":"Rear Pressure Bulkhead Area - ElectricalWire Chafing","content":"## Rear Pressure Bulkhead Area - Electrical  \nWire Chafing","sortOrder":2},{"sectionNumber":"6/2008 DM","sectionType":"part","heading":"6/2008 DM","content":"## 6/2008 DM","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"},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":false,"description":"This AD maintains its original narrow scope — addressing a specific wiring chafing issue in the rear pressure bulkhead area of ATR 42 aircraft. The applicability exclusions and conditional requirements are tightly focused on the identified unsafe condition without expanding into broader aircraft systems or unrelated maintenance requirements."},"complexity_factors":["Multiple conditional requirements based on inspection findings (Requirements 2 vs 3)","Nested applicability exclusions involving three different modification/service bulletin combinations (Mod 00639, Mod 05780, SB ATR42-92-0018)","Cross-references to external technical documents (SB ATR42-92-0015 and SB ATR42-92-0018) that contain the actual detailed instructions","Five separate compliance deadlines with different time-in-service calculations","Manufacturer Serial Number (MSN) cut-off points for factory-incorporated modifications (MSN 109, 113, 116, 667)","Reference to European Aviation Safety Agency (EASA) approval for alternative document revisions"],"plain_english_summary":"This AD requires operators of specified ATR 42 series to inspect and fix electrical wiring near the rear pressure bulkhead that is chafing on a screw and could disable rudder trim, pitch trim, or the stick pusher. \n\nIf damage is found the aircraft must be grounded and repaired with ATR-approved actions; if not, operators must report the check and reroute the wiring within a set period. It’s a mandatory safety order to prevent loss of critical flight controls."},"flash_summary":{"complexity_score":4,"scope_assessment":{"changed":false,"description":"The Directive addresses the unsafe condition described (wire chafing near the aft pressure bulkhead) through a one-time inspection, mandatory reporting and routing/protection modification for specified ATR 42 airframes. It does not expand beyond the aircraft/models/modification-status set out in the applicability text and aligns with the referenced EASA AD and ATR service bulletins."},"complexity_factors":["Technical inspection of wiring in a confined structural area (rear baggage/forward side of aft pressure bulkhead)","Applicability depends on aircraft model, serial number and whether specific factory mods or SBs have been embodied (Mod 00639, Mod 05780, SB ATR42-92-0018)","Conditional actions: different steps if damage is found versus not found (reporting, ATR-approved repair then modification, or reporting then modification)","Mandatory interaction with manufacturer (reporting via SB form and obtaining approved repair solution) introduces coordination and approval steps","Multiple compliance timeframes (550 flight hours for inspection; before further flight for repairs/modifications in some cases; 15 days and 5,000 hours for other reporting/modification actions)","Use of later EASA‑approved revisions of the referenced service bulletins is permitted, requiring attention to regulatory equivalence","Reference to an external EASA AD (2008-0062) for background and alignment"],"plain_english_summary":"This directive requires operators of specified ATR 42 aeroplanes to do a one-time inspection of electrical wiring in the rear baggage/bulkhead area and to re-route and protect cable bundles per ATR service bulletins. It applies to ATR 42-200/300/320/400/500 types subject to certain production modifications. Operators must report results to ATR, obtain ATR-approved repairs if chafing is found, and complete mandated routing modifications within set flight-hour or time limits. Operators pay for inspections, repairs and compliance actions; CASA issued the directive and enforces it."}},"importantCases":[],"_links":{"self":"/api/acts/ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing","history":"/api/acts/ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing/history","analysis":"/api/acts/ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing/analysis","conflicts":"/api/acts/ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing/conflicts","importantCases":"/api/acts/ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing/important-cases","documents":"/api/acts/ad-atr-42-23-rear-pressure-bulkhead-area-electrical-wire-chafing/documents"}}