The proposed AD would require you to use the service information described previously to perform these actions.

Costs of Compliance

There are about 5,462 TFE7312 and 3 series turbofan engines of the affected design in the worldwide fleet. We estimate that 3,572 engines installed on airplanes of U.S. registry would be affected by this proposed AD. We also estimate that it would take about 8 work hours per engine to perform the proposed measurements and calculations during MPI, and about 2 work hours per engine to replace the disk during MPI. The average labor rate is $65 per work hour. Required replacement parts would cost about $30,000 per engine. We expect about 1,900 engines to have the LPT stage 1 disk replaced. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $58,151,000.

Regulatory Findings

We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that the proposed regulation:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a summary of the costs to comply with this proposal and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment

Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows:

PART 39AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive:
Honeywell International Inc.: Docket No. FAA200418019; Directorate Identifier 2003NE65AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by August 16, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE7312 and 2C series, and TFE7313, 3A, 3AR, 3B, 3BR, and 3R series turbofan engines, with low pressure turbine (LPT) stage 1 disks, part numbers (P/Ns) 3072070All, 3072351All, 3073013All, 3073113All, 3073497 All, and 3074103All, (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
LockheedGeorgia 132925 series
Israel Aircraft Industries 1124 series and 1125 Westwind series Cessna Model 650, Citations III and VI
Raytheon British Aerospace HS125 series
Sabreliner NA26565
Unsafe Condition
(d) This AD results from a report of an uncontained failure of the LPT stage 1 disk installed in a TFE73131H turbofan engine. We are issuing this AD to prevent uncontained failure of the LPT stage 1 disk, and possible damage to the airplane.
Compliance
(e) 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 TFE7312 and 2C Series Engines
(f) For TFE7312 and 2C series engines with LPT stage 1 disk, P/N 3072070All, or
[[Page 33592]]
3073013All, 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 timeinservice (TIS) since the last LPT stage 1 nozzle assembly inspection, do the following:
(1) Measure and determine the acceptance of the LPT stage 1 nozzle assembly using paragraphs 2.A.(3) through 2.A.(5) of Honeywell International Inc. Service Bulletin (SB) No. TFE73172 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. TFE73172 3369RWK, Revision 6, dated June 26, 2002 or replace with a serviceable LPT stage 1 nozzle assembly.
Repetitive Inspections for TFE7312 and 2C Series Engines
(g) Thereafter, for TFE7312 and 2C series engines, at every MPI, but not to exceed 2,200 hours timeinservice since the last LPT stage 1 nozzle assembly inspection, do the following:
(1) Measure and determine the acceptance of the LPT stage 1 nozzle assembly using paragraph 2.A.(3) through 2.A.(5) of Honeywell International Inc. SB No. TFE731723369RWK, 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. TFE73172 3369RWK, Revision 6, dated June 26, 2002 or replace with a serviceable LPT stage 1 nozzle assembly.
Disk Replacement for TFE7313, 3A, 3AR, 3B, 3BR, and 3R Series Engines
(h) For TFE7313, 3A, 3AR, 3B, 3BR, and 3R series engines with LPT stage 1 disk, P/N 3072351All, 3073113All, 3073497All, or 3074103All, 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, after the effective date of this AD, or before December 31, 2011, or at disk life limit, whichever occurs first. TFE7313B and 3BR Series Engines
(i) For TFE7313B and 3BR series engines, no replacement LPT stage 1 disk is available for disk P/N 3073497All. Conversion from the TFE7313B and 3BR series engines to the TFE7313C series engine changes the turbine rotor configuration to allow 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 serviceable LPT stage 1 disk.
Definitions
(k) For the purposes of this AD:
(1) Next access to the LPT stage 1 nozzle assembly is defined as when the lowpressure tieshaft 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 paragraph (f)(1) or (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 2606/2102323, P.O. Box 29003, Phoenix, AZ 850389003, Telephone: (Domestic) 18006013099 (International) 16023653099, FAX: 16023653343.
Alternative Methods of Compliance
(m) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference
(n) None.
Related Information

(o) None.

Issued in Burlington, Massachusetts, on June 4, 2004. Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 0413563 Filed 61504; 8:45 am]
BILLING CODE 491013U

FOR FURTHER INFORMATION CONTACT Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 907124137; telephone: (562) 6275246; fax: (562) 6275210.