{"id":"F2007L01110","name":"AD/CESSNA 206/62 Amdt 1 - Flexible Fuel Hose End Fittings","slug":"ad-cessna-206-62-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":65144,"registerId":"commonwealth-F2007L01110-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Cessna 206 Series Aeroplanes","sectionType":"division","heading":"Cessna 206 Series Aeroplanes","content":"### Cessna 206 Series Aeroplanes\n\n| AD/CESSNA 206/62 Amdt 1 | Flexible Fuel Hose End Fittings | 6/2007 DM |\n| ----------------------- | ------------------------------- | --------- |\n\n| Applicability: | Cessna Aircraft Model 206 with the following serial numbers (S/N) - all inclusive:Model 206H S/N 20608231 through 20608285; andModel T206H S/N T20608515 through T20608662, T20608664 through T20608697, T20608699 through T20608714, and T20608717. |\n| -------------- | --------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement: | Group 1 - Cessna 206 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 (except T206H).iii) T206H only: Engine fuel pump to the union at the aft vertical cooling baffle.iv) T206H only: Union at the aft vertical cooling baffle to the fuel injector servo.v) Fuel injector servo to fuel manifold valve (except turbo models).vi) Turbo models only: Fuel injector servo to fuel flow transducer.vii) Turbo models only: Fuel flow transducer to fuel manifold valve.vii) 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 206 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 (except T206H).iii) T206H only: Engine fuel pump to the union at the aft vertical cooling baffle.iv) T206H only: Union at the aft vertical cooling baffle to the fuel injector servo.v) Fuel injector servo to fuel flow transducer.vi) Fuel flow transducer to fuel manifold valve.vii) 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 206H and T206H\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 206/62 Amdt 1","sectionType":"part","heading":"AD/CESSNA 206/62 Amdt 1","content":"## AD/CESSNA 206/62 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":4,"scope_assessment":{"changed":true,"description":"Amendment 1 expanded the AD's applicability by adding additional aircraft serial numbers and introduced further compliance instructions in the appendix. The original AD (effective 4 September 2006) was updated by this amendment (effective 25 April 2007) to cover more aircraft and to clarify inspection/torque procedures."},"complexity_factors":["Safety-critical mechanical work (torqueing fuel line fittings) requires licensed maintenance personnel and access to specified tools.","Short compliance window: actions required within 5 hours TIS or before further flight increases operational disruption and scheduling pressure.","Applicability limited to specific serial-number ranges and two equipment configurations (with/without Garmin G1000), requiring precise aircraft identification.","Dependency on an external service bulletin (Cessna SB07-71-01 Rev 1 or later FAA-approved revisions) for technical torque values and procedures.","Appendix procedures require partial disassembly (removal of upper/side cowlings), cleaning of old torque paint/putty, and potential full disconnection and replacement if fittings rotate.","Multiple hose locations vary by model and equipment (turbo vs non-turbo, T206H exceptions), increasing inspection steps and decision points.","Potential parts replacement and sealant work if fittings fail inspection, adding parts cost and variability in labour time."],"plain_english_summary":"This airworthiness directive requires immediate inspection and correction of torque on flexible fuel hose end fittings on specified Cessna 206 and T206H serial numbers, using Cessna Service Bulletin SB07-71-01 Rev 1 and the AD appendix. Compliance must occur within 5 hours time-in-service or before further flight. It affects aircraft owners/operators and maintenance personnel who must remove cowlings, inspect, retorque or replace fittings, and apply torque paint. CASA (the Delegate) issues the requirement to reduce risk of fuel flow loss and fire."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"This is Amendment 1 to an existing AD originally issued in September 2006. The amendment explicitly expands the scope by adding more aircraft serial numbers to the applicability list and providing additional compliance instructions in the appendix. The original AD likely covered fewer aircraft; this version broadens the safety net to capture more potentially affected planes."},"complexity_factors":["Two distinct compliance groups based on avionics equipment (Garmin G1000 presence)","Seven specific fuel hoses to inspect for Group 1, with variations for turbo vs non-turbo models","Seven specific fuel hoses for Group 2 with slightly different routing (includes fuel flow transducer)","Multiple serial number ranges with gaps (e.g., T20608663 and T20608698 excluded)","Cross-reference to external document: Cessna Service Bulletin SB07-71-01 Revision 1","Conditional logic: 'If incorrect torque values found, then establish correct values'","Appendix contains 6-step mechanical procedure with nested conditional (Step 6: if fitting rotates, stop and perform additional disassembly/replacement)","Reference to FAA AD 2007-08-03 and its supersession of prior FAA AD 2006-17-04","Amendment 1 expands applicability from original September 2006 AD"],"plain_english_summary":"Owners/operators of specific Cessna Model 206H and T206H aircraft must immediately inspect and correct fuel hose end fittings in the engine compartment, following Cessna SB07-71-01 and the AD’s inspection procedure. \n\nThis mandatory CASA Airworthiness Directive requires action within 5 flight hours or before the next flight to prevent fuel leaks, engine power loss, or fire after reported in‑flight failures."},"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"}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-206-62-amdt-1-flexible-fuel-hose-end-fittings","history":"/api/acts/ad-cessna-206-62-amdt-1-flexible-fuel-hose-end-fittings/history","analysis":"/api/acts/ad-cessna-206-62-amdt-1-flexible-fuel-hose-end-fittings/analysis","conflicts":"/api/acts/ad-cessna-206-62-amdt-1-flexible-fuel-hose-end-fittings/conflicts","importantCases":"/api/acts/ad-cessna-206-62-amdt-1-flexible-fuel-hose-end-fittings/important-cases","documents":"/api/acts/ad-cessna-206-62-amdt-1-flexible-fuel-hose-end-fittings/documents"}}