AD 2005-05-15 Airworthiness Directives; Honeywell International Inc. TFE731-2 and -3 Series Turbofan Engines

This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan engines, with low pressure turbine (LPT) stage 1 disks, part numbers (P/Ns) 3072070-All, 3072351-All, 3073013-All, 3073113-All, 3073497-All, and 3074103-All, (where All denotes all dash numbers), installed. These engines are installed on, but not limited to, the following airplanes: Avions Marcel Dassault Falcon 10 and Mystere Falcon 50 series Learjet 31, 35, 36, and 55 series Lockheed-Georgia 1329-25 series Israel Aircraft Industries 1124 series and 1125 Westwind series Cessna Model 650, Citations III and VI Raytheon British Aerospace HS-125 series Sabreliner NA-265-65

You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Inspection for TFE731-2 and -2C Series Engines (f) For TFE731-2 and -2C series engines with LPT stage 1 disk, P/N 3072070-All, or 3073013-All, installed, at the next major periodic inspection (MPI) or at next access to the LPT stage 1 nozzle assembly, after the effective date of this AD, whichever occurs first, but not to exceed 2,200 hours time-in-service (TIS) since the last LPT stage 1 nozzle assembly inspection, do the following: (1) Measure throat dimensions, air flow, and determine serviceability of the LPT stage 1 nozzle assembly using paragraphs 2.A.(3) through 2.A.(5) of Honeywell International Inc. Service Bulletin (SB) No. TFE731-72-3369RWK, Revision 6, dated June 26, 2002; and (2) If necessary, adjust the LPT stage 1 nozzle assembly using paragraph 2.B of Honeywell International Inc. SB No. TFE731-72-3369RWK, Revision 6, dated June 26, 2002, or replace with a serviceable LPT stage 1 nozzle assembly. Repetitive Inspections for TFE731-2 and -2C Series Engines (g) Thereafter, for TFE731-2 and -2C series engines, at every MPI, but not to exceed 2,200 hours TIS since the last LPT stage 1 nozzle assembly inspection, do the following: (1) Measure throat dimensions, air flow, and determine serviceability of the LPT stage 1 nozzle assembly using paragraphs 2.A.(3) through 2.A.(5) of Honeywell International Inc. SB No. TFE731-72-3369RWK, Revision 6, dated June 26, 2002; and (2) If necessary, adjust the LPT stage 1 nozzle assembly using paragraph 2.B of Honeywell International Inc. SB No. TFE731-72-3369RWK, Revision 6, dated June 26, 2002, or replace with a serviceable LPT stage 1 nozzle assembly. Disk Replacement for TFE731-3, -3A, -3AR, and -3R Series Engines (h) After the effective date of this AD, for TFE731-3, -3A, -3AR, and -3R series engines with LPT stage 1 disk, P/N 3072351-All, 3073113-All, or 3074103-All, installed, replace the LPT stage 1 disk with a serviceable disk, at next MPI, or at next access to the LPT stage 1 nozzle assembly, or before December 31, 2011, whichever occurs first. Disk Replacement for TFE731-3B and -3BR Series Engines (i) For TFE731-3B and -3BR series engines, do the following: (1) After the effective date of this AD, replace LPT stage 1 disk, P/N 3073497-All, with a serviceable LPT stage 1 disk, at next MPI, or at next access to the LPT stage 1 nozzle assembly, or before December 31, 2011, whichever occurs first. (2) Perform the actions specified in paragraph (i)(1) of this AD, by converting the TFE731-3B and -3BR series engines to a TFE731-3C series engine. This conversion allows the installation of a serviceable LPT stage 1 disk. Optional Terminating Action (j) As optional terminating action to the repetitive inspections required by this AD, replace the applicable LPT stage 1 disk with a more robust serviceable disk. Information on installing a serviceable disk can be found in Honeywell International Inc. SB No. TFE731-72-3704, SB No. TFE731-72-3705, and SB No. TFE731-72-3706, all dated September 15, 2004. Definitions (k) For the purposes of this AD: (1) Next access to the LPT stage 1 nozzle assembly is defined as when the low-pressure tie-shaft is unstretched. (2) A serviceable LPT stage 1 disk is defined as a disk having a part number not listed in this AD. (3) A serviceable LPT stage 1 nozzle assembly is defined as an LPT stage 1 nozzle assembly that passes the acceptance referenced in paragraphs (f)(1) and (g)(1) of this AD. Additional Information (l) For additional information regarding the training and tooling recommended to perform the inspection and adjustment of the LPT stage 1 nozzle assembly, contact Honeywell Engines, Systems & Services, Customer Support Center, M/S 26-06/2102-323, P.O. Box 29003, Phoenix, AZ 85038-9003, Telephone: (Domestic) 1-800-601-3099 (International) 1-602-365-3099, FAX: 1-602-365-3343. Alternative Methods of

This AD results from a report of an uncontained failure of the LPT stage 1 disk installed in a TFE731-3-1H turbofan engine. We are issuing this AD to prevent uncontained failure of the LPT stage 1 disk, and possible damage to the airplane.