2007-08-03: Flexible fuel hoses

2007-08-03 Cessna Aircraft Company: Amendment 39-15020; Docket No. FAA-2007-27709; Directorate Identifier 2007-CE-028-AD. Effective Date (a) This AD becomes effective on May 2, 2007. Affected ADs (b) This AD supersedes AD 2006-17-04; Amendment 39-14725. Applicability (c) This AD applies to the following airplane models and serial numbers that are certificated in any category: Table 1.--Applicability Model Serial Numbers (i) 172R 17281244 through 17281364, 17281366 through 17281372, 17281374 through 17281376, and 17281379 (ii) 172S 172S9809 through 172S10349, 172S10351 through 172S10374, 172S10376 through 172S10423, 172S10425 through 172S10426, 172S10428 through 172S10430, 172S10432 through 172S10444, 172S10446 through 172S10450, and 172S10452 through 172S10454 (iii) 182T 18281527 through 18281889, 18281892, 18281895, 18281897, 18281899, 18281901, and 18281904 (iv) T182T T18208381 through T18208659, T18208661, T18208663 through T18208678, T18208680 through T18208686, T18208689, and T18208690 (v) 206H 20608231 through 20608285 (vi) T206H T20608515 through T20608662, T20608664 through T20608697, T20608699 through T20608714, and T20608717 Unsafe Condition (d) This AD is the result of 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. We are issuing this AD to detect and correct potential loss of fuel flow, which may result in partial or complete loss of engine power and/or uncontrolled engine compartment fire due to fuel leakage forward of the firewall. Compliance (e) To address this problem, you must do the following, unless already done: Table 2.--Actions, Compliance, and Procedures Actions Compliance Procedures (1) For all airplanes not equipped with the Garmin G1000 System: Establish the correct torque values of the end fittings on each of the following hoses in the engine compartment: (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. (viii) Fuel injector servo fuel return to firewall fitting. Within the next 5 hours time-in-service (TIS) after May 2, 2007 (the effective date of this AD). Follow Cessna Service Bulletin No. SB07-71-01, Revision 1, dated March 16, 2007; the procedures of the appendix to this AD; and the torque values from the tableTorque Values for Hose End Fittings in the appendix to this AD. (2) For all airplanes equipped with the Garmin G1000 System: Establish the correct torque values of the end fittings on each of the following hoses in the engine compartment: (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. Within the next 5 hours TIS after May 2, 2007 (the effective date of this AD). Follow Cessna Service Bulletin No. SB07-71-01, Revision 1, dated March 16, 2007; the procedures of the appendix to this AD; and the torque values from the table Torque Values for Hose End Fittings in the appendix to this AD. Special Flight Permit (f) Under 14 CFR 39.23, we are allowing special flight permits for the purpose of compliance with this AD under the following conditions: Only operate under day visual flight rules (VFR). Alternative Methods of Compliance (AMOCs) (g) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Trenton Shepherd, Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946- 4143; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (h) AMOCs approved for AD 2006-17-04 are not approved for this AD. Material Incorporated by Reference (i) You must use Cessna Service Bulletin No. SB07-71-01, Revision 1, dated March 16, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942- 9006. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202- 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Appendix to AD 2007-08-03--Inspection Instructions--Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes 1. Remove upper and sidecowlings to perform torque procedure. 2. Remove all signs of old torque putty or paint. 3. 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. 4. Using the applicable fitting torque from the table Torque Values for Hose End Fittings of this appendix to AD 2007-08-03, 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. 5. After proper torque has been applied to the hose end fitting, apply the applicable torque paint or putty to the hose end fitting joint. 6. 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 andtorque it to the applicable requirement. Then reconnect the hose end fitting and repeat Step 4. of this appendix to AD 2007-08-03. 7. Use the table below Torque Values for Hose End Fittings for the correct torque values to tighten the hose end fittings as required in paragraphs (e)(1) and (e)(2) of this AD: Torque Values for Hose End Fittings Correct torque in inch-pounds Flare Hex sizes in fractions of an inch Hose size Minimum Maximum 9/16 -4 135 150 11/16 -6 270 300 7/8 -8 450 500