{"id":"F2007L01108","name":"AD/CESSNA 170/78 Amdt 1 - Flexible Fuel Hose End Fittings","slug":"ad-cessna-170-78-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":65139,"registerId":"commonwealth-F2007L01108-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"Cessna 170, 172, F172, FR172 and 175 Ser","sectionType":"division","heading":"Cessna 170, 172, F172, FR172 and 175 Series Aeroplanes","content":"### Cessna 170, 172, F172, FR172 and 175 Series Aeroplanes\n\n| AD/CESSNA 170/78 Amdt 1 | Flexible Fuel Hose End Fittings | 6/2007 DM |\n| ----------------------- | ------------------------------- | --------- |\n\n| Applicability: | Cessna Aircraft Models 172R and 172S with the following serial numbers - all inclusive:Model 172R Serial Numbers (S/N) 17281244 through 17281364, S/N 17281366 through 17281372, S/N 17281374 through 17281376, and S/N 17281379; andModel 172S Serial Numbers (S/N) 172S9809 through 172S10349,S/N 172S10351 through 172S10374, S/N 172S10376 through 172S10423,S/N 172S10425 through 172S10426, S/N 172S10428 through 172S10430,S/N 172S10432 through 172S10444, S/N 172S10446 through 172S10450, and S/N 172S10452 through 172S10454.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        |\n| -------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Group 1 - Cessna 172 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 172 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 172R & 172S\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 170/78 Amdt 1","sectionType":"part","heading":"AD/CESSNA 170/78 Amdt 1","content":"## AD/CESSNA 170/78 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_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":4,"scope_assessment":{"changed":true,"description":"Yes. Amendment 1 expanded the AD’s applicability by adding aircraft serial numbers for the affected Cessna 172R and 172S models and added more detailed procedural instructions in the appendix for performing the inspection and torque procedures. Mechanically, the core requirement (inspect and correct torque of specific fuel hose end fittings) remains the same, but the amendment broadened the population of aircraft captured and provided additional implementation detail for compliance."},"complexity_factors":["Explicit but long list of affected serial numbers for two model variants (172R and 172S)","Two groups with slightly different hose lists depending on Garmin G1000 equip (Group 1 and Group 2)","Cross‑references to external documents: Cessna Service Bulletin SB07‑71‑01 Revision 1 (or later FAA‑approved revisions) and FAA ADs","Conditional procedural step in appendix: if a non‑hose fitting rotates, the inspector must disconnect, inspect/replace fittings/seals, then repeat torquing","Torque values not stated in the AD itself (dependence on external SB), increasing reliance on another document for compliance","Separate hose routing for turbo vs non‑turbo models (different hose joints listed), adding branching logic","Short, urgent compliance window (5 hours TIS or before further flight) which increases operational pressure but simplifies timing rules"],"plain_english_summary":"**What this instrument does (mechanically)**\n\n- This Airworthiness Directive (AD) requires owners/operators of certain Cessna 172R and 172S aeroplanes to inspect and, if necessary, re-torque or repair specific flexible fuel hose end fittings in the engine compartment. The AD divides affected aircraft into two groups (those with and without the Garmin G1000 system) and lists the specific fuel hose joints to be checked. The detailed torque values and procedures are in Cessna Service Bulletin SB07-71-01 Revision 1 (or any later FAA‑approved revision), and the AD includes an appendix that sets out the step-by-step inspection and torque procedure.\n\n- The on‑aircraft steps required by the AD (summary of the appendix):\n  - Remove upper and side cowlings to access the hoses.\n  - Clean off old torque paint/putty.\n  - Using two tools (one to torque, one to restrain the mating fitting), check and apply the correct torque to each hose end fitting listed.\n  - After torquing, mark the joint with torque paint or putty.\n  - If a non‑hose fitting rotates when torquing, disconnect the joint, remove and inspect/clean or replace the rotating fitting and any seals or sealant, reinstall and torque correctly, then recheck.\n\n- Compliance timing: the inspections must be completed within the next 5 hours time‑in‑service (TIS) after the AD’s effective date (or before further flight in other applicable cases). This creates an immediate, short window for action.\n\n**Who it affects**\n\n- Aircraft owners/operators and maintenance organisations responsible for Cessna 172R and 172S airframes listed by serial number in the AD. The AD gives an explicit serial number range for the affected 172R and 172S aircraft.\n\n- Licensed maintenance personnel or facilities that perform the torque/inspection work and any replacing of fittings or seals.\n\n- Regulators (Civil Aviation Safety Authority delegate) who issued and enforce the AD.\n\n**Why it matters (stated intent and mechanical risk)**\n\n- The AD responds to reports of loose fuel hose fittings that have been associated with in‑flight engine power loss and fuel leaks. Its stated aim is to detect and correct incorrect torque on fuel hose end fittings to prevent loss of fuel flow, engine power loss, or fuel leakage that could lead to fire.\n\n**Who pays and who decides**\n\n- Aircraft owners/operators pay for the inspection, labour and any replacement parts or seals identified as necessary. If inspection reveals fittings that have rotated or are otherwise defective, parts and additional labour will be required.\n\n- The regulator (delegate of the Civil Aviation Safety Authority) decides compliance is mandatory by issuing the AD; the AD also directs technicians to follow the Cessna Service Bulletin (SB07-71-01 Rev 1 or later FAA‑approved revisions) for the technical torque values and similar details.\n\n**Implementation, costs and operational effects (practical testing of the AD’s claims)**\n\n- Immediate operational cost: aircraft must be taken into maintenance quickly (within 5 hours TIS). That imposes urgent downtime and a short‑term scheduling cost for owners/operators and maintenance providers.\n\n- Technical dependency: the AD does not state torque values directly. It requires use of the Cessna service bulletin or later FAA‑approved revision for the numeric torque settings, so compliance requires access to that external technical document.\n\n- Potential additional costs: if torquing causes any fittings to rotate, the AD requires disconnecting and removing the rotating fitting, cleaning, inspecting and/ or replacing the fitting, seals or sealant, then reinstalling and re‑torquing. That can increase parts/labour and downtime beyond a simple torque check.\n\n- Burden distribution: costs are concentrated on the affected aircraft owners/operators and on maintenance providers who must perform the work quickly. The regulator sets the rules and enforces them via the AD.\n\n**Trade‑offs, risks and implementation issues**\n\n- Compliance is straightforward in concept (inspect and torque), but relies on accurate execution: correct tools, a second person or tool to restrain fittings, and correct torque values from the service bulletin.\n\n- There is some operational risk if owners attempt to defer or perform incomplete checks: the short compliance window is meant to reduce that risk.\n\n- The AD cross‑references the manufacturer service bulletin and FAA ADs (FAA AD 2007‑08‑03 and earlier FAA AD 2006‑17‑04). This external referencing centralises the technical details outside the AD itself, which concentrates technical discretion in the approved service bulletin language.\n\n**Source statements vs consequences**\n\n- The AD’s stated purpose (preventing loss of engine power and fuel leaks) is grounded in four reported incidents described in the background. The AD’s prescribed mechanical remedy (inspect and correct torque; replace/repair fittings that move) logically addresses loose fittings as the proximate cause of those incidents.\n\n- The text does not quantify expected costs, nor does it mandate a specific repair beyond reinstalling or replacing rotating fittings and seals; therefore, the scope of possible expense depends on inspection findings and parts required. The AD does expand applicability from the original issue by adding serial numbers and provides the detailed appendix for compliance (see “Amendment 1” note)."},"kimi_summary":{"content_quality":"ok","complexity_score":4,"scope_assessment":{"changed":true,"description":"The original AD (effective September 2006) was amended in April 2007 to expand applicability to additional aircraft serial numbers and to add detailed inspection instructions in an appendix. The scope grew from a narrower initial fleet to cover more 172R and 172S models, and shifted from general directive to specific procedural guidance."},"complexity_factors":["Multiple serial number ranges with gaps and exclusions (e.g., '17281366 through 17281372, S/N 17281374' — skipping 17281373)","Two distinct compliance groups based on avionics configuration (Garmin G1000 vs. standard)","Turbo vs. non-turbo engine variations requiring different hose inspection lists","Cross-reference to external technical document (Cessna Service Bulletin SB07-71-01) for torque specifications","Nested conditional logic: 'If incorrect torque found, then...' and 'If fitting rotates during procedure, then disconnect, clean, examine, replace, reinstall, and repeat'","Appendix with 6-step mechanical procedure including conditional loop (Step 6 references repeating Steps 4–6)","Reference to FAA AD 2007-08-03 and its supersession of earlier FAA AD 2006-17-04, creating international regulatory layering"],"plain_english_summary":"This CASA Airworthiness Directive orders owners/operators of certain Cessna 172R/172S (circa 2006–2007 serials) to inspect and, if needed, torque specific engine‑compartment fuel hose fittings (six or five depending on equipment) and mark the work. Action is mandatory within 5 flight hours or before the next flight to prevent fuel leaks, engine failures, or fire after multiple in‑flight incidents."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cessna-170-78-amdt-1-flexible-fuel-hose-end-fittings","history":"/api/acts/ad-cessna-170-78-amdt-1-flexible-fuel-hose-end-fittings/history","analysis":"/api/acts/ad-cessna-170-78-amdt-1-flexible-fuel-hose-end-fittings/analysis","conflicts":"/api/acts/ad-cessna-170-78-amdt-1-flexible-fuel-hose-end-fittings/conflicts","importantCases":"/api/acts/ad-cessna-170-78-amdt-1-flexible-fuel-hose-end-fittings/important-cases","documents":"/api/acts/ad-cessna-170-78-amdt-1-flexible-fuel-hose-end-fittings/documents"}}