[Federal Register: July 1, 2004 (Volume 69, Number 126)]
[Proposed Rules]
[Page 39875-39877]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01jy04-33]
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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