[Federal Register Volume 69, Number 126 (Thursday, July 1, 2004)]
[Proposed Rules]
[Pages 39875-39877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-14946]


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DEPARTMENT OF TRANSPORTATION (DOT)

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18496; Directorate Identifier 2004-NE-04-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. (Formerly 
AlliedSignal Inc. and Garrett Turbine Engine Co.). TFE731-2 and -3 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt 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 
as new parts before April 1, 1991. This proposed AD would require 
replacement of those LP 1st and 2nd stage turbine rotor discs. This 
proposed AD results from a report of an uncontained failure of an LP 
2nd stage turbine rotor disc that caused an in-flight engine shutdown. 
We are proposing this AD to prevent LP turbine rotor disk separation, 
which could result in an uncontained engine failure and damage to the 
airplane.

DATES: We must receive any comments on this proposed AD by August 30, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this proposed AD 
from Honeywell Engines and Systems (formerly AlliedSignal Inc. and 
Garrett Turbine Engine Co.) 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).
    You may examine the comments on this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood CA 90712-4137; telephone: 
(562) 627-5246; fax: (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    We have implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, we posted new AD actions on the DMS 
and assigned a DMS docket number. We track each action and assign a 
corresponding Directorate identifier. The DMS docket No. is in the form 
``Docket No. FAA-200X-XXXXX.'' Each DMS docket also lists the 
Directorate identifier (``Old Docket Number'') as a cross-reference for 
searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18496; 
Directorate Identifier 2004-NE-04-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of the 
DMS Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register

[[Page 39876]]

published on April 11, 2000 (65 FR 19477-78) or you may visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, 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 Docket Office (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.

Discussion

    Honeywell International Inc. has made the FAA aware that a problem 
may exist with LP 1st and 2nd stage turbine rotor discs manufactured 
from 1981 through 1984 that were heat treated in an oil fired furnace. 
This heat treat process might have resulted in turbine rotor disc 
material with nonuniform microstructure, which is susceptible to 
cracking and/or separation. On March 22, 1995, we issued AD 95-07-02 
(60 FR 19343, April 18, 1995) that requires removing suspect LP turbine 
rotor discs due to their suspect heat treatment and susceptibility to 
creep fatigue. At that time, a total of five LP 2nd stage turbine rotor 
discs had failed.
    Since AD 95-07-02 was issued, a sixth LP 2nd stage turbine rotor 
disc failed, causing an in-flight engine shutdown. Analysis revealed 
that the disc was from a manufacturing lot that was originally not 
suspect for defects, and revealed that the disc had nonuniform 
microstructure similar to the LP turbine rotor disc lots identified by 
AD 95-07-02. This condition, if not corrected, could result in LP 
turbine rotor disk separation, which may result in an uncontained 
engine failure and damage to the airplane.

Relevant Service Information

    We have reviewed and approved the technical contents of Honeywell 
International Inc. Service Bulletin (SB) No. TFE731-72-3682, dated 
November 26, 2002, that describes procedures for replacement of 
specific serial numbered LP 1st and 2nd stage turbine rotor discs 
manufactured before April 1, 1991.

Differences Between the Proposed AD and the Manufacturer's Service 
Information

    There are differences between this proposed AD and SB No. TFE731-
72-3682, dated November 26, 2002, in identifying the suspect serial 
numbers with respect to the engine model number. These differences 
result from LP 1st and 2nd stage turbine rotor discs previously 
identified in AD 95-07-02.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. We are proposing this AD, which would require 
the following for Honeywell International Inc. TFE731-2 and -3 series 
turbofan engines:
     The following actions are applicable to the P/Ns of LP 1st 
and 2nd stage turbine rotor discs listed in the applicability section 
of the proposed AD that were initially installed as new parts before 
April 1, 1991, and that have SNs listed in Tables 1, 2, and 3 of 
Honeywell International Inc. Service Bulletin (SB) No. TFE731-72-3682, 
dated November 26, 2002.
     For TFE731-2-2J, TFE731-2-2N, TFE731-2A-2A, and TFE731-3-
1J engines, within 100 hours time-in-service (TIS) after the effective 
date of this proposed AD, replace discs that are listed by SN in Tables 
1 and 3 of Honeywell International Inc. SB No. TFE731-72-3682, dated 
November 26, 2002.
     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 Honeywell International Inc. 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.
     For TFE731-3 series engines except TFE731-3-1J, replace 
discs that are listed by SN in Table 3 of Honeywell International Inc. 
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.
     After the effective date of this proposed 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.

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 
would be affected by this proposed AD. We also estimate that it would 
take about 4 work hours per engine to perform the proposed actions, and 
that the average labor rate is $65 per work hour. Required parts would 
cost about $30,000 per engine. Based on these figures, we estimate the 
total cost of the proposed AD to U.S. operators to be $726,240.

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 by 
sending a request to us 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 39--AIRWORTHINESS DIRECTIVES

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

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

[[Page 39877]]

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

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

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by August 30, 
2004.

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:

3072069-All
3072070-All
3072351-All
3072542-All
3073013-All
3073014-All
3073113-All
3073114-All
3074103-All
3074105-All

    (All denotes all dash numbers installed)
    These engines are installed 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 caused 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) None.

Related Information

    (n) None.

    Issued in Burlington, Massachusetts, on June 24, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 04-14946 Filed 6-30-04; 8:45 am]
BILLING CODE 4910-13-U