AD 2005-13-07

The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with certain part numbers (P/Ns) and serial numbers (SNs) of low pressure (LP) 1st and 2nd stage turbine rotor discs initially installed. This AD requires replacement of those LP 1st and 2nd stage turbine rotor discs. This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, which could result in an uncontained engine failure and damage to the airplane.

Final rule.

2005-13-07 Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.): Amendment 39-14143. Docket No. FAA- 2004-18496; Directorate Identifier. 2004-NE-04-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective July 27, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with the following low pressure (LP) 1st and 2nd stage turbine rotor disc part numbers (P/Ns), with serial numbers (SNs) listed in Tables 1, 2, and 3 of Honeywell International Inc. SB No. TFE731-72-3682, dated November 26, 2002, initially installed as new parts before April 1, 1991:

Part Numbers

3072069-All
3073014-All
3072070-All
3073113-All
3072351-All
3071114-All
3072542-All
3074103-All
3073013-All
3074105-All
(All denotes all dash numbers installed)

These engines areinstalled on, but not limited to, the following airplanes:

Avions Marcel Dassault Mystere-Falcon 10 and 50 series

Cessna Model 650, Citation III, and Citation VI

Gulfstream Aerospace LP (formerly IAI) 1125 Westwind Astra series

Israel Aircraft Industries (IAI) 1124 series

Learjet 31, 35, 36, and 55 series

Lockheed-Georgia 1329-25 series (731 Jetstar, Jetstar II)

Raytheon Corporate Jets (formerly British Aerospace) DH/HS/BH-125 series;

Sabreliner NA-265-65 (Sabreliner 65)

Unsafe Condition

(d) This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, which could result in an uncontained engine failure and 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.

Removal From Service of LP 1st and 2nd Stage Turbine Rotor Discs

(f) For TFE731-2-2J, TFE731-2-2N, TFE731-2A-2A, and TFE731-3-1J engines, replace discs that are listed by SN in Tables 1 and 3 of SB No. TFE731-72-3682, dated November 26, 2002, within 100 hours time- in-service (TIS) after the effective date of this AD.

(g) For TFE731-2 series engines except TFE731-2-2J, TFE731-2-2N, and TFE731-2A-2A engines, replace discs that are listed by SN in Tables 1 and 2 of SB No. TFE731-72-3682, dated November 26, 2002, at the next Major Periodic Inspection (MPI) or next access to the turbine discs after the effective date of this AD, but within 2,200 hours TIS since the last disc inspection, whichever occurs first.

(h) For TFE731-3 series engines except TFE731-3-1J, replace discs that are listed by SN in Table 3 of SB No. TFE731-72-3682, dated November 26, 2002, at the next MPI or next access to the turbine discs after the effective date of this AD, but within 1,500 hours TIS since the last disc inspection, whichever occurs first.

(i) Information on replacing affected discs can be found in Honeywell International Inc. SB No. TFE731-72-3682, dated November 26, 2002.

(j) After the effective date of this AD, do not install any LP 1st and 2nd stage turbine rotor disc that has a SN listed in Table 1, 2, or 3 of SB No. TFE731-72-3682, dated November 26, 2002, and determined to be manufactured before April 1, 1991.

Definitions

(k) For the purposes of this AD, access to the turbine discs is the level of disassembly that has removed the tie-shaft nut.

Alternative Methods of Compliance

(l) 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

(m) You must use Honeywell International, Inc. Service Bulletin No. TFE731-72-3682, dated November 26, 2002, to perform the replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell Engines and Systems Technical Publications and Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General Aviation), (602) 365-5535 (Commercial Aviation), fax: (602) 365-5577 (General Aviation), (602) 365-2832 (Commercial Aviation) for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001, on the internet at http://dms.dot.gov, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .

Related Information

(n) None.

The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with certain P/Ns and SNs of LP 1st and 2nd stage turbine rotor discs initially installed as new parts before April 1, 1991. These discs were heat treated with a process that may have resulted in disk material with a non-uniform microstructure that is susceptible to creep fatigue, which may lead to cracking or separation. We published the proposed AD in the Federal Register on July 1, 2004 (69 FR 39875). That action proposed to require replacement of those LP 1st and 2nd stage turbine rotor discs.

Examining the AD Docket

You may examine the docket that contains the AD, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The DocketOffice (telephone (800) 647-5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them.

Comments

We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public.

Conclusion

We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

There are about 56 Honeywell International Inc. TFE731-2 and -3 series turbofan engines of the affected design in the worldwide fleet. We estimate that 24 engines installed on airplanes of U.S. registry will be affected by this AD. We also estimate that it will take about 4 work hours per engine to perform these actions, and that the average labor rate is $65 per work hour. Required parts cost about $30,000 per engine. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $726,240.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, "General requirements." Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD:

(1) Is not a "significant regulatory action" under Executive Order 12866;

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

(3) 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.

We prepared a summary of the costs to comply with this AD 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 39Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS 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: