Airworthiness Directive · Amendment 39-11942 · CFE Company CFE738-1-1B Turbofan Engines
CFE Company CFE738-1-1B Turbofan Engines
This AD is applicable to CFE Company CFE738-1-1B turbofan engines with support assembly, part numbers (P/N's) 3050860-2, -3, and -5 through -9 inclusive, installed. These engines are installed on, but not limited to, Dassault Aviation Falcon 2000 series airplanes.
Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD) that is applicable to CFE Company CFE738-1-1B turbofan engines. This action requires removing certain support assemblies and replacing them with support assemblies that have a new design. This amendment is prompted by a report of the loss of seal retention that resulted in contact between the seal face and the stage 2 high pressure turbine (HPT) rotor disk, and subsequent wear of the stage 2 HPT rotor disk. That condition resulted in separation of the stage 2 HPT wheel rim, and an uncontained failure of the stage 2 HPT rotor wheel. The actions specified in this AD are intended to prevent the static seal from moving forward, which could result in contact between the seal face and stage 2 HPT rotor, wear, and the possibility of an uncontained failure of the stage 2 HPT rotor.
To prevent the static seal from moving forward, which could result in contact between the seal face and stage 2 HPT rotor, wear, and the possibility of an uncontained failure of the stage 2 HPT rotor, do the following:
(a) Remove support assembly, P/N 3050860-2, -3, -5 through -9, and replace it with a serviceable seal assembly in accordance with the Accomplishment instructions 2.A.(3) through 2.A.(8)(d) and 2.B.(1) through 2.B.(3) of ASB CFE738 A72-8042, Revision 1, dated September 25, 2000, as follows:
(1) For engines that have been inspected using CFE Company alert service bulletin (ASB) ASB CFE738 A72-8041, dated August 21, 2000, replace the support assembly as follows:
| Operating hours time-since new (TSN) on the effective date of this AD | Replace by the earlier of— |
|---|---|
| Fewer than 500 hours TSN | 150 hours time-in-service (TIS) or 90 days after the effective date of this AD. |
| 500 hours to 1,000 hours TSN | 250 hours TIS or 150 days after the effective date of this AD. |
| More than 1,000 hours TSN | 400 hours TIS or 240 days after the effective date of this AD. |
(2) For engines that have not been inspected using CFE Company alert service bulletin (ASB) ASB CFE738 A72-8041, dated August 21, 2000, do EITHER of the following within the earlier of 50 hours TIS or 30 days after the effective date of this AD:
(i) Replace the support assembly with a serviceable support assembly in accordance with the Accomplishment instructions 2.A.(3) through 2.A.(8)(d) and 2.B.(1) through 2.B.(3) of ASB CFE738 A72-8042, and 2.A. or 2.B. of SB CFE738-72-8043, Revision 1, dated October 2, 2000;
(ii) Inspect the engine in accordance with the Accomplishment Instructions 2.A. through 2.B.(6) of ASB CFE738-A72-8041, dated August 21, 2000, and then replace the support assembly in accordance with the replacement schedule in paragraph (a)(1) of this AD.
(b) After the seal has been replaced, do the support assembly seal break-in procedure in accordance 2.A. (test cell) or 2.B. (on wing) of SB CFE738-72-8043, Revision 1, dated October 2, 2000.
(c) For the purposes of this AD, a serviceable support assembly is defined as a support assembly with P/N 3050860-10, or -11, P/N 3057005-1 through -5 inclusive, or P/N 3057006-1, or -2.
