Division Cessna 206 Series Aeroplanes - AD/CESSNA 206/62 Amdt 1 - Flexible Fuel Hose End Fittings - Cessna 206 Series Aeroplanes

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Cessna 206 Series Aeroplanes

AD/CESSNA 206/62 Amdt 1	Flexible Fuel Hose End Fittings	6/2007 DM

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.
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.

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.

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.

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.

Compliance:	1. Within the next 5 hours time-in-service (TIS) after the effective date of this AD.2. Before further flight.
	This Amendment becomes effective on 25 April 2007.
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.