AD 2002-03-01

Effective date March 21, 2002. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 21, 2002.

The service information referenced in this AD may be obtained from Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming), Attn: Data Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone: (602) 365-2493; fax: (602) 365-5577. This information may be examined, by appointment, at the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone: (562) 627-5245; fax: (562) 627-5210.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-703 series turboshaft engines was published in the Federal Register on June 15, 2001 (66 FR 32591). That action proposed to require initial and repetitive special vibration tests of the engine, and if necessary replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight, in accordance with AlliedSignal, Inc., Service Bulletin (SB) No.”s T5311A/B-0100, dated January 20, 2000; T5313B/17-0100, dated November 19, 1999; T53-L-11-0100, dated January 20, 2000; T53-L-13B-0100, Revision 2, dated May 11, 1999; and T53-L-703-0100, Revision 2, dated May 11, 1999.

Interested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the one comment received.

The commenter stated that further investigation into the root problem causing the spur gear failures needs to be addressed. The problem may be a manufacturing problem from one U.S. Government contract supplier.

The FAA does not agree. The commenter did not supply sufficient evidence substantiating a design nonconformity.

After careful review of the available data, including the comment noted above, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

There are about 4,500 engines of the affected design in the worldwide fleet. The FAA estimates that 300 engines installed on aircraft of U.S. registry would be affected by this AD, and that it would take about four work hours per engine to accomplish each special vibration test, and that the average labor rate is $60 per work hour. Based on these figures, for each special vibration test, the total labor cost effect on U.S. operators is estimated to be $240 per engine. The FAA estimates that operators, on average, will perform ten special vibration tests per year, resulting in a total annual cost on U.S. operators of $720,000.

This final rule does not have federalism implications, as defined in Executive Order 13132, because it 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. Accordingly, the FAA has not consulted with state authorities prior to publication of this final rule.

For the reasons discussed above, I certify that this action (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) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:

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

2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: