AD 2006-17-04 Airworthiness Directives; The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes

Makes named: cessna. Read the applicability below — it usually turns on serial or part numbers too.

This AD affects the following airplane models and serial numbers that are certificated in any category: Table 1.—Applicability and Airplane Groups Group Model Serial Nos. (1) Group 1 Airplanes: All models not equipped with the Garmin G1000 System (i) 172R (ii) 172S 17281244 through 17281334. 172S9809 through 172S10219.   (iii) 182T 18281527 through 18281832.   (iv) T182T T18208381 through T18208583.   (v) 206H 20608231 through 20608265.   (vi) T206H T20608515 through T20608635. (2) Group 2 Airplanes: All models equipped with the Garmin G1000 System (i) 172R (ii) 172S 17281244 through 17281334. 172S9809 through 172S10219.   (iii) 182T 18281527 through 18281832.   (iv) T182T T18208381 through T18208583.   (v) 206H 20608231 through 20608265.   (vi) T206H T20608515 through T20608635.

For Group 1 Airplanes not equipped with the Garmin G1000 System: To address this problem, you must do the following: Table 2.—Actions, Compliance, and Procedures for Group 1 Airplanes Actions Compliance Procedures (1) Inspect the two end fittings on each of the following hoses in the engine compartment for the correct torque values (i) Fuel strainer to engine fuel pump. (ii) Engine fuel pump to fuel injector server (except T206). (iii) T206 only: Engine fuel pump to the union at the aft vertical cooling baffle. (iv) T206 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 return to firewall fitting. Within the next 5 hours time-in-service (TIS) after September 1, 2006 (the effective date of this AD), on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittings Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. (2) If any incorrect torque values are found during the inspection required by paragraph (e)(1) of this AD, clean and dry the threads of all fittings, and tighten the hose end fittings to the correct torque values as defined in Table 4 Before further flight after the inspection required by paragraph (e)(1) of this AD, in which any incorrect torque values are found Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. (f) For Group 2 Airplanes equipped with the Garmin G1000 System: To address this problem, you must do the following: Table 3.—Actions, Compliance, and Procedures for Group 2 Airplanes Actions Compliance Procedures (1) Inspect the two end fittings on each of the following hoses in the engine compartment for the correct torque values (i) Fuel strainer to engine fuel pump. (ii) Engine fuel pump to fuel injector servo (except T206). (iii) T206 only: Engine fuel pump to the union at the aft vertical cooling baffle. Within the next 5 hours TIS after September 1, 2006 (the effective date of this AD), on airplanes that have not had a 100-hour or annual inspection of the engine installation fuel hoses for security and tightness of the end fittings Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. (iv) T206 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 return to firewall fitting. (2) If any incorrect torque values are found during the inspection required by paragraph (f)(1) of this AD, clean and dry the threads of all fittings, and tighten the hose end fittings to the correct torque values as defined in Table 4 Before further flight after the inspection required by paragraph (f)(1) of this AD, in which any incorrect torque values are found Follow Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. (g) Use the following table for the correct torque values to tighten the hose end fittings as required in paragraphs (e)(2) and (f)(2) of this AD: Table 4.—Torque Values for Hose End Fittings Flare hex sizes in fractions of an inch Hose size Correct torque in inch-pounds Minimum Maximum 9/16 −4 135 150 11/16 −6 270 300 7/8 −8 450 500 Alternative Methods of Compliance (AMOCs) (h) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Jeff Janusz, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4148; facsimile: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (i) You must do the actions required by this AD following the instructions in Cessna Service Bulletin No. SB06-71-02, dated June 19, 2006. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277-7706; telephone: (316) 517-5800; facsimile: (316) 942-9006. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2006-25262; Directorate Identifier 2006-CE-39-AD. Issued in Kansas City, Missouri, on August 9, 2006. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13442 Filed 8-17-06; 8:45 am] BILLING CODE 4910-13-P

This AD is the result of one report of loose fuel hose connections to the fuel injector servo on a Cessna Aircraft Company Model 172S airplane. We are issuing this AD to detect and correct any incorrect torque values of the end fittings of flexible fuel hoses in the engine compartment, which could result in the loss of fuel flow and fuel leakage. Loss of fuel flow could result in partial or complete loss of engine power and fuel leakage could result in an engine compartment fire.