{"id":"F2006B01864","name":"AD/A320/116 Amdt 1 - Wing Fuel Boost Pump Wiring","slug":"ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":41060,"registerId":"commonwealth-F2006B01864-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"1","sectionType":"section","heading":"AD/A320/116 Amdt 1 - Wing Fuel Boost Pump Wiring","content":"![](image.001.png)\n\n![](image.001.png)  \nAIRWORTHINESS DIRECTIVE\n\nFor the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/A320/116 and issues the following AD under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.\n\n![](image.001.png)\n\nAirbus Industrie A319, A320 and A321 Series Aeroplanes\n\nAD/A320/116\n\nAmdt 1\n\n  \nWing Fuel Boost Pump Wiring 6/2002\n\nApplicability: All Model A319/A320/A321 aeroplanes without both Airbus Industrie modifications 30861 and 31612 embodied or Airbus Industrie Service Bulletin (SB) A320-28-1093 incorporated.\n\nRequirement: 1. If not previously accomplished, revise the Limitations Section of the Aeroplane Flight Manual (AFM) by inserting the following:\n\nFUEL SYSTEM\n\nIn case any wing fuel tank fuel pump circuit breaker 1QA, 2QA, 7QA or 8QA is tripped, do not re-engage.\n\nThis may be accomplished by inserting a copy of this Directive or the revised Temporary Revision 2.04.00/31 into the AFM.\n\n    2. If wing fuel tank pump circuit breaker 1QA, 2QA, 7QA or 8QA trips, either:\n\n    remove the applicable fuel pump fairing and perform visual inspections of the following to detect any damage caused by electrical arcing and, if necessary, carry out the rectification specified in sub-paragraphs 2.a.(i), 2.a.(ii) or 2.a.(iii).\n\n    (i) Electrical wiring \\- If any damage to the wiring is detected replace the wire with new wire or repair it in accordance with the Aircraft Wiring Manual (AWM), Electrical Standard Practices Manual (ESPM), Chapter 20.\n\n    (ii) Fairing \\- If any damage to the fairing is detected replace the fairing with a new serviceable fairing using the appropriate installation and sealing procedures.\n\n    (iii) Wing skin within the fairing area \\- If any damage to the wing structure is detected repair the damaged structure in accordance with the aircraft Structural Repair Manual (SRM) or another approved method.\n\nCaution: When replacing the fairing following the inspection, ensure that fuel boost pump wiring is not pinched or otherwise damaged. Incorrect replacement of the fairing could cause damage to the wiring.\n\nor,\n\n    b. ensure that the applicable circuit breaker cannot be reset by collaring the circuit breaker(ie secure the circuit breaker in the open position by a positive means).\n\nNote 1: If the Requirement 2.b. option is adopted, the aircraft may be dispatched in accordance with an approved MEL (based on associated DGAC MMEL 28-21).\n\n    3. If a circuit breaker is collared opened in accordance with Requirement 2.b. carry out the Requirement 2.a. inspection.\n\n    4. If any damage is detected during the Requirement 2.a. inspections submit a report to Airbus Industrie including the following details:\n\n    description of the damage found,\n    aeroplane serial number,\n    total number of landings,\n    total time in service (hours), and\n    details of the last maintenance actions performed on the fuel boost pump and/or fairing.\n\n    Modify the engine feed pump electrical harness and underwing fairings in accordance with SB A320-28-1093 and remove the AFM amendment introduced by Requirement 1.\n\nNote 2: DGAC AD 2002-221(B) refers.\n\nCompliance: For Requirement 1 \\- Remains unchanged as ‘Within ten days after the effective date of the original issue of this Directive’.\n\nFor Requirement 2 \\- Before further flight unless SB A320-28-1093 has been incorporated in accordance with Requirement 5.\n\nFor Requirement 3 \\- Within ten days of the circuit breaker being collared open in accordance with Requirement 2.b.\n\nFor Requirement 4 \\- Within ten days after accomplishing the Requirement 2.a. inspection.\n\nFor Requirement 5 \\- Before 30 April 2004.\n\nThis Amendment becomes effective on 13 June 2002.\n\nBackground: The original issue of this Directive superseded AD/A320/111, clarified the inspection requirements and allowed despatch of the aircraft with wing fuel tank pumps rendered inoperable. AD/A320/111 was issued to limit the risk of electrical arcing between the wing fuel tank boost pump wiring and the wing structural skin by the introduction of an AFM limitation.\n\nThis Amendment introduces terminating action for Requirements 1 and 2.\n\nThe original issue of this Airworthiness Directive became effective on 28 February 2001.\n\n![](image.002.png)  \n\nJames Coyne\n\nDelegate of the Civil Aviation Safety Authority 3 May 2002\n\n![](image.001.png)  \n\nThe above AD is notified in the Commonwealth of Australia Gazette on 22 May 2002.","sortOrder":0}],"analysis":{"flash_summary":{"complexity_score":5,"scope_assessment":{"changed":true,"description":"This amendment adds a defined terminating action (mandatory incorporation of SB A320‑28‑1093 by a specified date) and clarifies inspection/dispatch options (including collaring breakers and MEL dispatch). It thereby shifts the measure from a temporary AFM limitation and emergency inspection regime to a path allowing retrofit termination of operational restrictions, and replaces the prior AD while keeping prior limitations until modification is embodied."},"complexity_factors":["Multiple compliance options: immediate inspection/repair or collar (secure open) of circuit breakers (Requirements 2–3)","Technical repair standards referenced: Aircraft Wiring Manual, Electrical Standard Practices Manual, Structural Repair Manual (Requirement 2.a.(i)–(iii))","Reporting requirement to manufacturer including serial/time-in-service/maintenance history (Requirement 4)","Terminating action depends on embodiment of SB A320‑28‑1093 and specific Airbus modifications, linking ongoing operational constraints to a retrofit solution (Requirement 5)","Interplay with MEL/MMEL for dispatch when breaker is collared (Note 1)","Defined deadlines and staged compliance times (Compliance section)","Applicability limited to aircraft lacking specific modifications or SB incorporation (Applicability)"],"plain_english_summary":"This AD requires operators of Airbus A319/A320/A321 aeroplanes (without Airbus mods 30861 and 31612 or SB A320‑28‑1093) to add a limitation to the AFM forbidding re‑engaging specified wing fuel pump circuit breakers, inspect and repair pump wiring/fairings if those breakers trip (or collar the breakers to keep them open), report any damage to Airbus, and ultimately incorporate SB A320‑28‑1093 as terminating action (Requirements 1–5). CASA mandates compliance; operators and maintenance organisations bear the inspection, repair and modification costs."},"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 is Amendment 1 to an existing AD. The amendment adds 'terminating action' (Requirement 5) to end the temporary measures, but does not expand beyond the original scope of addressing wing fuel boost pump wiring safety on A320 family aircraft. The original purpose remains intact."},"complexity_factors":["Multiple interdependent requirements (Requirements 1-5) with cross-references between them (e.g., Requirement 3 triggers if 2.b is adopted)","Conditional logic throughout: 'If not previously accomplished', 'If wing fuel tank pump circuit breaker...trips', 'If any damage is detected'","Technical aviation terminology requiring specialized knowledge (AFM, MEL, DGAC MMEL, SB, ESPM, SRM, circuit breaker collaring)","Dual compliance paths (Requirement 2.a inspection vs 2.b circuit breaker collaring) with different downstream obligations","Specific Airbus modification numbers and service bulletin references (30861, 31612, A320-28-1093) that must be cross-referenced","Multiple compliance deadlines varying by requirement (10 days, before further flight, before 30 April 2004)"],"plain_english_summary":"This AD applies to Airbus A319/A320/A321 aircraft without a specific wiring modification. It fixes a hazardous condition where wing fuel-pump wiring can arc against the metal wing skin, risking fire or explosion. Operators must immediately update flight manuals to prohibit resetting the pump circuit breaker; if it trips, inspect and repair wiring or lock the breaker open (if MEL allows) and inspect within 10 days, report damage to Airbus, and complete the permanent wiring/fairing fix by 30 April 2004."}},"importantCases":[],"_links":{"self":"/api/acts/ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring","history":"/api/acts/ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring/history","analysis":"/api/acts/ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring/analysis","conflicts":"/api/acts/ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring/conflicts","importantCases":"/api/acts/ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring/important-cases","documents":"/api/acts/ad-a320-116-amdt-1-wing-fuel-boost-pump-wiring/documents"}}