{"id":"F2009L02783","name":"AD/B737/357 - In-Flight Entertainment Systems","slug":"ad-b737-357-in-flight-entertainment-systems","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":79964,"registerId":"commonwealth-F2009L02783-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Boeing 737 Series Aeroplanes","sectionType":"division","heading":"Boeing 737 Series Aeroplanes","content":"### Boeing 737 Series Aeroplanes\n\n| AD/B737/357 | In-Flight Entertainment Systems | 8/2009 |\n| ----------- | ------------------------------- | ------ |\n\n| Applicability: | Model 737-300, -400 and -500 series aeroplanes, as identified in Boeing Service Bulletin (SB) 737-24-1145, dated 4 March 2004 and Model 737-600, -700, -700C,-800 and -900 series aeroplanes, as identified in Boeing SB737-24-1147, Revision 1, dated 1 March 2007.                                                                                                                                                                                        |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | 1. For Model 737-300, -400 and -500 series aeroplanes - Install a new circuit breaker, relays and wiring to allow the flightcrew to turn off electrical power to the in-flight entertainment (IFE) systems through the IFE/galley switch and do all other specified actions as applicable, by accomplishing all the applicable actions specified in the Accomplishment Instructions of SB 737-24-1145.                                                      |\n|                | 2. For Model 737-300 series aeroplanes identified as Group 6 aeroplanes in SB737-24-1145 and equipped with P5-13 module assembly part number (P/N)69-37321-81 - Replace the lightplate assembly of the P5-13 module assembly with a new lightplate assembly and re-identify and test the modified P5-13 module assembly, in accordance with the Accomplishment Instructions of Boeing Component Service Bulletin (CSB) 69-37321-31-03, dated21 August 2003. |\n|                | 3. For Model 737-600, -700, -700C, -800 and -900 series aeroplanes - Install a new circuit breaker, relays and wiring, as applicable, to allow the flightcrew to turn off electrical power to the IFE systems and other non-essential electrical systems through a utility switch in the flight compartment, by accomplishing all of the applicable actions specified in Parts 1, 2 or 3 of the Work Instructions of SB737-24-1147, Revision 1.             |\n|                | 4. For Model 737-600, -700, -700C, -800 and -900 series aeroplanes identified as Groups 3 through 139 inclusive in SB 737-24-1147, Revision 1 and equipped with P5-13 module assembly P/N 285A1840-3 or -4 - Modify the P5-13 module assembly, in accordance with the Accomplishment Instructions of Boeing CSB 285A1840-24-02, dated 28 August 2003.                                                                                                       |\n\n|             | 5. For Model 737-800 series aeroplanes identified in paragraph 1.A.1. of Boeing SB 737-23-1189, dated 27 June 2002 - Install wiring for the No. 4 Video Display Unit (VDU) cluster, an INOP marker and stow clip at the P6-1 circuit breaker panel; reroute certain wiring for the No. 4 VDU cluster between stations 685 and 767; and do a continuity test of the newly installed and rerouted wiring; in accordance with the Accomplishment Instructions of SB 737-23-1189.             |\n| ----------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n|             | Later revisions of the above SBs, approved by the United States Federal Aviation Administration (FAA) as an Alternate Method of Compliance (AMOC) to FAA AD 2009-12-06 are considered acceptable for compliance with the equivalent Requirements of this Directive.                                                                                                                                                                                                                       |\n|             | Note: FAA AD 2009-12-06 Amdt 39-15929 refers.                                                                                                                                                                                                                                                                                                                                                                                                                                             |\n| Compliance: | For Requirement 1 - Within 60 months after the effective date of this Directive.                                                                                                                                                                                                                                                                                                                                                                                                          |\n|             | For Requirement 2 - Prior to or concurrently with Requirement 1.                                                                                                                                                                                                                                                                                                                                                                                                                          |\n|             | For Requirement 3 - Within 60 months after the effective date of this Directive.                                                                                                                                                                                                                                                                                                                                                                                                          |\n|             | For Requirements 4 and 5 - Prior to or concurrently with Requirement 3.                                                                                                                                                                                                                                                                                                                                                                                                                   |\n|             | This Airworthiness Directive becomes effective on 30 July 2009.                                                                                                                                                                                                                                                                                                                                                                                                                           |\n| Background: | This Directive results from an IFE systems review and is issued to ensure that the flightcrew is able to turn off electrical power to IFE systems and other non-essential electrical systems through a switch in the flight compartment. The flightcrew's inability to turn off power to IFE systems and other non-essential electrical systems during a non-normal or emergency situation could result in the inability to control smoke or fumes in the aeroplane flight deck or cabin. |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n16 June 2009","sortOrder":0},{"sectionNumber":"AD/B737/357","sectionType":"part","heading":"AD/B737/357","content":"## AD/B737/357","sortOrder":1},{"sectionNumber":"In-Flight Entertainment Systems","sectionType":"part","heading":"In-Flight Entertainment Systems","content":"## In-Flight Entertainment Systems","sortOrder":2},{"sectionNumber":"8/2009","sectionType":"part","heading":"8/2009","content":"## 8/2009","sortOrder":3}],"analysis":{"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"},"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":false,"description":"The AD remains focused on its original technical purpose: ensuring the flightcrew can remove power from IFE and other non‑essential systems from the flight deck to help control smoke or fumes. The included actions (wiring/circuit breaker installations, specific module modifications and component replacements) are concrete means to that end and do not extend the directive beyond that safety objective. The AD does add model‑ and part‑specific detail and procedural sequencing, but those are implementation specifics not a substantive expansion of scope."},"complexity_factors":["Multiple aircraft models and model groups across two families (300/400/500 and 600/700/800/900 series)","Five discrete requirements with different applicability by model and detailed dependencies (Requirements 1–5)","Cross‑references to multiple Boeing Service Bulletins (SB 737‑24‑1145, SB 737‑24‑1147 Rev 1, SB 737‑23‑1189) and Component Service Bulletins (CSB 69‑37321‑31‑03, CSB 285A1840‑24‑02)","Specific part‑number conditionality (e.g. P/N 69‑37321‑81, P/N 285A1840‑3/‑4)","Sequencing constraints (some tasks required prior to or concurrently with others)","Compliance timeframes with mixed deadlines (60 months for major items; some actions required before/concurrent)","Allowance for later SB revisions only if FAA‑approved as AMOC (adds regulatory cross‑approval complexity)","Required functional tests and re‑identification steps (testing and paperwork add procedural complexity)"],"plain_english_summary":"**What this directive actually requires (mechanical changes first)**\n\n- This Airworthiness Directive (AD) orders operators of specified Boeing 737 aircraft to modify the electrical and in‑flight entertainment (IFE) installations so the flightcrew can switch off electrical power to IFE systems (and, for some models, other non‑essential systems) from the flight deck. The requirements are split by airplane model and equipment configuration: Requirements 1–5 set out which wiring, circuit breakers, relays, module modifications or component replacements are needed for particular model groups and part numbers.  \n\n- Concretely:  \n  - Requirement 1: On 737‑300/‑400/‑500 series, install a new circuit breaker, relays and wiring so the IFE/galley switch in the flight deck can turn IFE power off; follow Boeing Service Bulletin (SB) 737‑24‑1145.  \n  - Requirement 2: For certain 737‑300 Group 6 aeroplanes with a specific P5‑13 module (P/N 69‑37321‑81), replace the module’s lightplate and re‑identify and test the module per Boeing Component Service Bulletin (CSB) 69‑37321‑31‑03.  \n  - Requirement 3: On 737‑600/‑700/‑700C/‑800/‑900 series, install circuit breaker, relays and wiring (as applicable) to allow the flightcrew to shut off IFE and other non‑essential systems using a utility switch in the flight compartment; follow SB 737‑24‑1147 (Work Instructions Parts 1–3).  \n  - Requirement 4: For many 737‑600 to ‑900 groupings equipped with P5‑13 module P/N 285A1840‑3 or ‑4, modify that module per CSB 285A1840‑24‑02.  \n  - Requirement 5: For certain 737‑800 aircraft identified in Boeing SB 737‑23‑1189, install wiring, an INOP (inoperative) marker and stow clip for the No.4 Video Display Unit cluster, reroute wiring between given stations, and do continuity testing per that SB.  \n\n- Timing and dependencies: most retrofit actions (Requirements 1 and 3) must be done within 60 months of the AD’s effective date. Some specific actions (Requirements 2, 4 and 5) must be done prior to or at the same time as the related main requirement for that model. Later revisions of the cited Boeing SBs are acceptable if approved by the U.S. FAA as an Alternate Method of Compliance (AMOC).  \n\n**Who is affected**\n\n- Airline operators and aircraft owners of the listed Boeing 737 models and specific groups/configurations referenced in the service bulletins.  \n- Maintenance organisations and parts suppliers who will perform the installations, module modifications or replacements.  \n\n**Why the regulator says this matters (official rationale)**\n\n- The stated safety reason is that, in a non‑normal or emergency situation where smoke or fumes occur, the flightcrew must be able to remove electrical power from IFE and other non‑essential systems from the flight deck to aid control of smoke/fumes in cockpit or cabin. The AD implements that capability by mandating specific wiring, circuit breaker and module changes. (Background paragraph of the AD.)\n\n**Testing that claimed purpose against cost, incentives and trade‑offs**\n\n- Who pays: aircraft operators bear the direct cost of parts, labour and aircraft downtime to do the mandated modifications. Maintenance organisations incur workload and scheduling impacts.  \n- Implementation and compliance burden: the AD references multiple SBs and CSBs with model‑group and part‑number distinctions; some work must be completed before or concurrently with other items, creating sequencing constraints. Parts availability and shop capacity will affect actual downtime.  \n- Operational trade‑offs: switching capability improves a crew’s ability to isolate electrical sources of smoke, but it also permits turning off passenger IFE during flight‑deck events — potentially reducing passenger amenity and ancillary revenue while the systems are powered down.  \n- Incentives: operators have an incentive to comply within the 60‑month window to remain airworthy and avoid regulatory action. There is also an operational incentive to adopt later FAA‑approved SB revisions (AMOCs) if they reduce cost or downtime.  \n- Risks and unintended consequences: wiring and module modifications carry standard maintenance risks (installation errors, test omissions). The AD mitigates this by requiring compliance with Boeing SB/CSB accomplishment instructions and continuity/testing steps.  \n- Concentration of benefits and distribution of costs: the primary safety benefit is concentrated (improved capability for flightcrew to isolate electrical loads during an emergency); costs are concentrated on aircraft owners/operators who must fund the retrofits.  \n\n**Practical effect in plain terms**\n\n- If you operate the affected 737 variants, you must schedule and pay for the specified electrical and component changes so your flightcrew can shut off IFE/non‑essential systems from the flight deck, and you must do so within the AD’s compliance windows. The AD allows use of FAA‑approved later SB revisions (AMOCs) where applicable."},"kimi_summary":{"content_quality":"ok","complexity_score":6,"scope_assessment":{"changed":false,"description":"This AD maintains focused scope on its original safety purpose: ensuring flight crew can isolate electrical power to in-flight entertainment systems. The multiple requirements and model variations represent necessary technical granularity to address the same underlying safety issue across different 737 configurations, rather than scope creep. The directive does not expand beyond electrical system modifications for emergency power isolation."},"complexity_factors":["Multiple aircraft model groups with different technical requirements (5 distinct requirement categories)","Extensive cross-referencing to external Boeing Service Bulletins (SB 737-24-1145, SB 737-24-1147, CSB 69-37321-31-03, CSB 285A1840-24-02, SB 737-23-1189) — compliance requires obtaining and interpreting separate manufacturer documents","Nested conditional applicability: requirements depend on specific aircraft model, group number within service bulletin, and specific part numbers (P/N) of installed components","Interdependent compliance deadlines: Requirements 2, 4, and 5 must be completed prior to or concurrently with Requirements 1 and 3","Reference to foreign regulatory equivalence (FAA AD 2009-12-06 and AMOC provisions) requiring understanding of US aviation regulatory framework","Technical aviation terminology throughout (circuit breakers, relays, P5-13 module assemblies, lightplate assemblies, VDUs, stations 685 and 767) requiring specialized engineering knowledge"],"plain_english_summary":"This AD requires operators of specified Boeing 737 Classic and Next-Generation models to modify IFE electrical systems so flight crew can shut off in-flight entertainment power from the cockpit (by installing breakers/relays/wiring and related component changes). Compliance is generally required within 60 months from July 2009.\n\nThe change prevents IFE from feeding electrical fires or smoke events, protecting crew ability to manage emergencies."}},"importantCases":[],"_links":{"self":"/api/acts/ad-b737-357-in-flight-entertainment-systems","history":"/api/acts/ad-b737-357-in-flight-entertainment-systems/history","analysis":"/api/acts/ad-b737-357-in-flight-entertainment-systems/analysis","conflicts":"/api/acts/ad-b737-357-in-flight-entertainment-systems/conflicts","importantCases":"/api/acts/ad-b737-357-in-flight-entertainment-systems/important-cases","documents":"/api/acts/ad-b737-357-in-flight-entertainment-systems/documents"}}