[Federal Register: June 16, 2004 (Volume 69, Number 115)]
[Proposed Rules]
[Page 33590-33592]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16jn04-26]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18019; Directorate Identifier 2003-NE-65-AD]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. 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 number (P/N) low pressure turbine (LPT) stage 1 disks
installed. This proposed AD would require for TFE731-2 and -2C series
engines, initial and repetitive measurements and calculations to
determine acceptance, and adjustment or replacement if necessary, of
the LPT stage 1 nozzle assembly. This proposed AD would also require
for TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series engines, replacement
of LPT stage 1 disks with serviceable disks. This proposed AD also
allows replacement of the LPT stage 1 disk with a disk having a part
number not listed in the proposed AD as optional terminating action to
the repetitive actions. This proposal results from a report of an
uncontained failure of the LPT stage 1 disk installed in a TFE731-3-1H
turbofan engine. We are proposing this AD to prevent additional
uncontained failure of the LPT stage 1 disk, and possible damage to the
airplane.
DATES: We must receive any comments on this proposed AD by August 16,
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 20590-0001.
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-2004-18019;
Directorate Identifier 2003-NE-65-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 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
In June of 2003, we became aware of a report of a TFE731-3-1H
turbofan engine that experienced an uncontained failure of LPT stage 1
disk, P/N 3072351-5. Analysis by the manufacturer revealed that the
disk, which only had 107 hours of operation accumulated since new,
failed due to vibration-induced high-cycle-fatigue (HCF) cracking in
the web area of the disk. Analysis and testing of these vibrations have
revealed that the disk design is sensitive to significant nozzle
throat-area variations such as those caused by inappropriate
maintenance of the vanes of the LPT stage 1 nozzle assembly. Two other
uncontained disk failures involving TFE731-3 series
[[Page 33591]]
engines occurred over the past 16 years and were considered at the time
to have been caused by inappropriate maintenance practices performed on
the LPT stage 1 nozzle assembly. We have determined that similarly
designed LPT stage 1 disks, P/Ns 3072070-All, 3072351-All, 3073013-All,
3073113-All, 3073497-All, and 3074103-All, (where All denotes all dash
numbers), are sensitive for the same reasons described for disk P/N
3072351-5. This condition, if not corrected, could result in
uncontained failure of the LPT stage 1 disk, and possible damage to the
airplane.
Relevant Service Information
We have reviewed and approved the technical contents of Honeywell
International Inc. Service Bulletin No. TFE731-72-3369RWK, Revision 6,
dated June 26, 2002, that describes procedures for inspection,
measurement and adjustment, or replacement if necessary, of the LPT
stage 1 nozzle assembly. These procedures reduce the potential for
vibration-induced HCF cracking in the web area of the disk.
Differences Between the Proposed AD and the Manufacturer's Service
Information
Although Honeywell International Inc. SB No. TFE731-72-3369RWK,
Revision 6, dated June 26, 2002, requires the inspections, measurements
and adjustments, and replacements of the LPT stage 1 nozzle assembly to
be done by certain approved repair stations, this proposed AD allows
the actions to be done by any repair station certificated to perform
the repair work.
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. Therefore, we are proposing this AD, which
would require:
For TFE731-2 and -2C series engines with LPT stage 1
disk, P/Ns 3072070-All, or 3073013-All, (where All denotes all dash
numbers) installed, initial and repetitive measurements and
calculations to determine the acceptance, and adjustment or
replacement if necessary of the LPT stage 1 nozzle assembly. These
actions are to be done at the next major periodic inspection (MPI)
or at next access to the LPT stage 1 nozzle assembly, whichever
occurs first, but not to exceed 2,200 hours time-in-service (TIS)
since the last LPT stage 1 nozzle assembly inspection.
For TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series
engines with LPT stage 1 disk, P/N 3072351-All, 3073113-All,
3073497-All, or 3074103-All, installed, replacement of the LPT stage
1 disk with a serviceable disk, at next major periodic inspection or
at next access to the LPT stage 1 nozzle assembly, but not to exceed
1,500 hours time-in-service since last inspection, or before
December 31, 2011, or at disk life limit, whichever occurs first.
As optional terminating action to the repetitive
actions of the proposed AD, replacement of the LPT stage 1 disk with
a serviceable disk.
For the purposes of this proposed AD, a serviceable LPT
stage 1 disk is a disk having a part number not listed in this
proposed AD.
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 TFE731-2 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 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:
Honeywell International Inc.: Docket No. FAA-2004-18019; Directorate
Identifier 2003-NE-65-AD.
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.) TFE731-2 and -2C
series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan
engines, with low pressure turbine (LPT) stage 1 disks, part numbers
(P/Ns) 3072070-All, 3072351-All, 3073013-All, 3073113-All, 3073497-
All, and 3074103-All, (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
Lockheed-Georgia 1329-25 series
Israel Aircraft Industries 1124 series and 1125 Westwind series
Cessna Model 650, Citations III and VI
Raytheon British Aerospace HS-125 series
Sabreliner NA-265-65
Unsafe Condition
(d) This AD results from a report of an uncontained failure of
the LPT stage 1 disk installed in a TFE731-3-1H 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 TFE731-2 and -2C Series Engines
(f) For TFE731-2 and -2C series engines with LPT stage 1 disk,
P/N 3072070-All, or
[[Page 33592]]
3073013-All, 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 time-in-service (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. TFE731-72-
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. TFE731-72-
3369RWK, Revision 6, dated June 26, 2002 or replace with a
serviceable LPT stage 1 nozzle assembly.
Repetitive Inspections for TFE731-2 and -2C Series Engines
(g) Thereafter, for TFE731-2 and -2C series engines, at every
MPI, but not to exceed 2,200 hours time-in-service 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. TFE731-72-3369RWK, 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. TFE731-72-
3369RWK, Revision 6, dated June 26, 2002 or replace with a
serviceable LPT stage 1 nozzle assembly.
Disk Replacement for TFE731-3, -3A, -3AR, -3B, -3BR, and -3R Series
Engines
(h) For TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series engines
with LPT stage 1 disk, P/N 3072351-All, 3073113-All, 3073497-All, or
3074103-All, 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.
TFE731-3B and -3BR Series Engines
(i) For TFE731-3B and -3BR series engines, no replacement LPT
stage 1 disk is available for disk P/N 3073497-All. Conversion from
the TFE731-3B and -3BR series engines to the TFE731-3C 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 low-pressure tie-shaft 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 26-06/2102-323, P.O. Box
29003, Phoenix, AZ 85038-9003, Telephone: (Domestic) 1-800-601-3099
(International) 1-602-365-3099, FAX: 1-602-365-3343.
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. 04-13563 Filed 6-15-04; 8:45 am]
BILLING CODE 4910-13-U