Airworthiness Directive · Amendment 39-14725 · The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes
The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes
Superseded. A later AD replaced this one: AD 2007-08-03. Comply with the one in force.
This AD affects the following airplane models and serial numbers that are certificated in any category:
| 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. |
The FAA is adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from one report of loose fuel hose connections to the fuel injector servo on a Cessna 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.
For Group 1 Airplanes not equipped with the Garmin G1000 System: To address this problem, you must do the following:
| 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:
| 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:
| Hose size | Correct torque in inch-pounds | Minimum | Maximum |
|---|---|---|---|
| 9/16 | −4 | 135 | 150 |
| 11/16 | −6 | 270 | 300 |
| 7/8 | −8 | 450 | 500 |
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
