Division Cessna 180, 182 and Wren 460 Series Aero - AD/CESSNA 180/88 Amdt 1 - Flexible Fuel Hose End Fittings - Cessna 180, 182 and Wren 460 Series Aeroplanes

Cessna 180, 182 and Wren 460 Series AeroCessna 180, 182 and Wren 460 Series Aeroplanes

Start here

Get a plain-English read of Cessna 180, 182 and Wren 460 Series Aero

Turn the raw legal text into a practical explanation grounded in AD/CESSNA 180/88 Amdt 1 - Flexible Fuel Hose End Fittings.

Cessna 180, 182 and Wren 460 Series Aeroplanes

AD/CESSNA 180/88 Amdt 1	Flexible Fuel Hose End Fittings	6/2007 DM

Applicability:	Cessna Aircraft Models 182T and T182T with the following serial numbers (S/N) - all inclusive:Model 182T S/N 18281527 through 18281889, 18281892, 18281895, 18281897, 18281899, 18281901, and 18281904; andModel T182T S/N T18208381 through T18208659, T18208661, T18208663 through T18208678, T18208680 through T18208686, T18208689, and T18208690.
Requirement:	Group 1 - Cessna 182 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.

Applicability:

Cessna Aircraft Models 182T and T182T with the following serial numbers (S/N) - all inclusive:Model 182T S/N 18281527 through 18281889, 18281892, 18281895, 18281897, 18281899, 18281901, and 18281904; andModel T182T S/N T18208381 through T18208659, T18208661, T18208663 through T18208678, T18208680 through T18208686, T18208689, and T18208690.

Requirement:

Group 1 - Cessna 182 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.

Group 2 - Cessna 182 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.

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.