{"id":"F2007L01109","name":"AD/CESSNA 180/88 Amdt 1 - Flexible Fuel Hose End Fittings","slug":"ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":65141,"registerId":"commonwealth-F2007L01109-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Cessna 180, 182 and Wren 460 Series Aero","sectionType":"division","heading":"Cessna 180, 182 and Wren 460 Series Aeroplanes","content":"### Cessna 180, 182 and Wren 460 Series Aeroplanes\n\n| AD/CESSNA 180/88 Amdt 1 | Flexible Fuel Hose End Fittings | 6/2007 DM |\n| ----------------------- | ------------------------------- | --------- |\n\n| Applicability: | Cessna Aircraft Models 182T and T182T with the following serial numbers (S/N) - all inclusive:Model 182T S/N 18281527 through 18281889, 18281892, 18281895, 18281897, 18281899, 18281901, and 18281904; andModel T182T S/N T18208381 through T18208659, T18208661, T18208663 through T18208678, T18208680 through T18208686, T18208689, and T18208690.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Group 1 - Cessna 182 Aircraft - NOT equipped with the Garmin G1000 System:1. Inspect the two end fittings on each of the following hoses in the engine compartment using the instructions of Cessna Service Bulletin (SB) No.SB07-71-01, Revision 1, dated 16 March 2007 or later FAA approved revisions; and the procedures given in the appendix to this AD:i) Fuel strainer to engine fuel pump.ii) Engine fuel pump to fuel injector servo.iii) Fuel injector servo to fuel manifold valve (except turbo models).iv) Turbo models only: Fuel injector servo to fuel flow transducer.v) Turbo models only: Fuel flow transducer to fuel manifold valve.vi) Fuel injector servo fuel return to firewall fitting.2. If any incorrect torque values are found during the inspection in accordance with Requirement 1 of this AD, establish the correct torque values in accordance with the instructions of Cessna SB07-71-01, Revision 1 or later FAA approved revisions; and the procedures given in the appendix to this AD. |\n\n|             | Group 2 - Cessna 182 Aircraft - Equipped with the Garmin G1000 System:1. Inspect the two end fittings on each of the following hoses in the engine compartment using the instructions of Cessna Service Bulletin (SB) No.SB07-71-01, Revision 1, dated 16 March 2007 or later FAA approved revisions; and the procedures given in the appendix to this AD:i) Fuel strainer to engine fuel pump.ii) Engine fuel pump to fuel injector servo.iii) Fuel injector servo to fuel flow transducer.iv) Fuel flow transducer to fuel manifold valve.v) Fuel injector servo fuel return to firewall fitting.2. If any incorrect torque values are found during the inspection in accordance with Requirement 1 of this AD, establish the correct torque values in accordance with the instructions of Cessna SB07-71-01, Revision 1 or later FAA approved revisions; and the procedures given in the appendix to this AD.Note: FAA AD 2007-08-03 Amendment 39-15020 dated 5 April 2007 refers.FAA AD 2007-08-03 supersedes FAA AD 2006-17-04 amendment 39-14725. |\n| ----------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | 1. Within the next 5 hours time-in-service (TIS) after the effective date of this AD.2. Before further flight.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          |\n|             | This Amendment becomes effective on 25 April 2007.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      |\n| Background: | There have been four reports of loose fuel lines connected to the fuel servo or fuel flow transducer. Two reports were of in-flight engine failure on a Model T182T airplane. A third report was of in flight-engine failure on a Model 206H airplane. A fourth report was of a Model 172S airplane that lost engine power on final approach. The intent of this AD is to detect and correct potential loss of fuel flow, which may result in partial or complete loss of engine power and/or fire due to fuel leak.Amendment 1 of this AD expands the applicability through addition of aircraft serial numbers and provides additional instructions for compliance in the appendix.                                                                                                                                                                                                                                                                                                                                                                   |\n\n|     | The original issue of this AD became effective on 4 September 2006. |\n| --- | ------------------------------------------------------------------- |\n\n![](image.001.png)  \nDavid Villiers  \nDelegate of the Civil Aviation Safety Authority\n\n19 April 2007\n\n  \nAppendix: Inspection Instructions\n\nCessna Aircraft Models 182T and T182T\n\n1. Remove upper and side cowlings to perform torque procedure.\n\n2. Remove all signs of old torque putty or paint.\n\n3. Using a suitable tool loosen the hose end fitting of each joint, while using a suitable tool to restrain the other end fitting of the joint to preclude rotation.\n\n4. Using the applicable fitting torque from Cessna Service Bulletin (SB) No. SB07-71-01, Revision 1, dated 16 March 2007 or later FAA approved revisions, torque the hose end fitting to the proper torque, while using a suitable tool to restrain the other end fitting of the joint to preclude rotation.\n\n5. After proper torque has been applied to the hose end fitting, apply the applicable torque paint or putty to the hose end fitting joint.\n\n6. If during any torque procedure any of the non-hose end fittings rotate, stop the torque procedure. Totally disconnect the hose end joint and remove any fitting that has rotated. After the cleaning, visual examination, and/or replacement of the fitting and/ or any seals or sealant, reinstall the fitting and torque it to the applicable requirement. Then reconnect the hose end fitting and repeat Step 4 to step 6 of this appendix, as applicable.","sortOrder":0},{"sectionNumber":"AD/CESSNA 180/88 Amdt 1","sectionType":"part","heading":"AD/CESSNA 180/88 Amdt 1","content":"## AD/CESSNA 180/88 Amdt 1","sortOrder":1},{"sectionNumber":"Flexible Fuel Hose End Fittings","sectionType":"part","heading":"Flexible Fuel Hose End Fittings","content":"## Flexible Fuel Hose End Fittings","sortOrder":2},{"sectionNumber":"6/2007 DM","sectionType":"part","heading":"6/2007 DM","content":"## 6/2007 DM","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":6,"scope_assessment":{"changed":true,"description":"Amendment 1 expanded the AD’s applicability by adding additional aircraft serial numbers and added more detailed compliance instructions in the appendix. The AD’s original issue was effective 4 September 2006; Amendment 1 became effective 25 April 2007 and broadened the population subject to mandatory inspection and corrective action (Background)."},"complexity_factors":["Detailed applicability by specific serial numbers across two model variants increases identification and record-checking effort (Applicability).","Two operator groups defined by Garmin G1000 equipage create dual requirement lists for hose runs to inspect (Requirement: Group 1 / Group 2).","Mandatory reference to an external document (Cessna SB07‑71‑01 Rev 1 or later FAA‑approved revisions) means procedures and torque values are set outside the AD text (Requirement & Appendix).","Short, near-immediate compliance window (within 5 hours TIS and/or before next flight) imposes high operational and scheduling pressure (Compliance).","Technical torque and disassembly/reassembly steps in the appendix require qualified maintenance personnel and appropriate tools; risk of additional repair if fittings rotate during torque (Appendix Steps 3–6).","Multiple hose joints listed (fuel strainer, pump, servo, flow transducer, manifold valve, return) increase inspection scope and parts exposure (Requirement items i–vi).","Potential need to remove, clean, inspect, replace fittings, seals or sealant creates variable cost and parts-sourcing complexity (Appendix Step 6).","Cross-reference to FAA AD history and supersessions (FAA AD 2007‑08‑03 superseding earlier FAA AD) creates regulatory tracing for compliance history and acceptable revisions (Note / Background)."],"plain_english_summary":"This instrument requires immediate inspection and, where necessary, re‑torquing or replacement of flexible fuel‑hose end fittings on specified Cessna 182T and T182T aeroplanes after reports of loose fittings causing engine power loss. Aircraft owners/operators and maintenance providers must follow Cessna Service Bulletin SB07‑71‑01 Rev 1 and the AD appendix; corrective action must be completed before further flight. Compliance costs (labour, parts, downtime) fall on operators; the regulator enforces the requirement to reduce risk of fuel flow loss or fire."},"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":true,"description":"The original AD (effective 4 September 2006) has expanded significantly. Amendment 1 adds additional aircraft serial numbers to the applicability, effectively covering more aircraft than originally intended. It also introduces the appendix with detailed step-by-step inspection instructions that were not in the original issue, and splits compliance requirements into two distinct groups based on avionics configuration (Garmin G1000 presence). The document notes this expansion explicitly in the Background section."},"complexity_factors":["Two distinct compliance groups with different inspection requirements (Group 1 vs Group 2 based on Garmin G1000 installation)","Extensive serial number ranges with multiple non-consecutive blocks requiring careful cross-referencing","Six specific fuel hose connections listed for Group 1, five for Group 2, with variations for turbo models","Mandatory reference to external technical document (Cessna Service Bulletin SB07-71-01) for torque specifications","Nested conditional logic: 'If incorrect torque values found, then establish correct values' with additional conditional in appendix (Step 6: if fittings rotate during torque procedure, disconnect and reinstall)","Dual compliance deadlines with different triggers (5 hours TIS vs before further flight)","Cross-reference to FAA AD 2007-08-03 and its superseded predecessor for international regulatory context"],"plain_english_summary":"This AD requires owners/operators of specified Cessna 182T and T182T serial-numbered aeroplanes (with and without Garmin G1000) to inspect and tighten engine‑compartment fuel hose end fittings within 5 flight hours and correct any loose fittings before further flight. It responds to four incidents—two in‑flight engine failures—where loose fuel lines caused fuel leaks, power loss, or fire, so immediate inspection and correction are mandated to ensure safety."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings","history":"/api/acts/ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings/history","analysis":"/api/acts/ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings/analysis","conflicts":"/api/acts/ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings/conflicts","importantCases":"/api/acts/ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings/important-cases","documents":"/api/acts/ad-cessna-180-88-amdt-1-flexible-fuel-hose-end-fittings/documents"}}