[Federal Register: March 14, 2005 (Volume 70, Number 48)]
[Rules and Regulations]
[Page 12404-12406]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14mr05-3]
[[Page 12404]]
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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;
Amendment 39-14004; AD 2005-05-15]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. TFE731-2
and -3 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: 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 number (P/N) low pressure turbine (LPT) stage 1 disks
installed. This AD requires 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 AD also requires for TFE731-3, -3A, -3AR,
-3B, -3BR, and -3R series engines, replacement of LPT stage 1 disks
with serviceable disks. This AD also allows replacement of the LPT
stage 1 disk with a disk having a part number not listed in the AD as
optional terminating action to the repetitive actions. 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 additional uncontained failure of the LPT stage 1 disk, and
possible damage to the airplane.
DATES: This AD becomes effective April 18, 2005. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of April 18, 2005.
ADDRESSES: Contact 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) for the service information identified
in this AD.
You may examine the AD docket on the Internet at http://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
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: We 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/N LPT stage 1 disks
installed. We published the proposed AD in the Federal Register on June
16, 2004 (69 FR 33590). That action proposed to 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. That action also
proposed to require for TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series
engines, replacement of LPT stage 1 disks with serviceable disks. Also,
that action proposed to allow replacement of the LPT stage 1 disk with
a disk having a part number not listed in the AD as optional
terminating action to the repetitive actions.
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 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.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Question About Which Service Bulletin Is Correct
One commenter states that the service bulletin (SB) referenced in
the proposed AD seems to be incorrect. The commenter was able to find
references to the subject matter of the proposed AD in Honeywell
International Inc. SB No. TFE731-72-3367, instead of Honeywell
International Inc. SB No. TFE-72-3369RWK, which is referenced in the
proposed AD. The commenter asks which SB is correct.
Honeywell International Inc. SB No. TFE731-72-3369RWK, Revision 6,
dated June 26, 2002, is the correct SB. It was initially distributed
only to Honeywell-authorized service centers. We believe Honeywell
corrected the distribution of this SB and it is now available to anyone
that wants a copy, through Honeywell Engines and Systems at the address
listed under ADDRESSES in this AD.
We reviewed the information in SB No. TFE731-72-3367 that the
commenter thought pertains to this AD, and found that it does not
pertain to this AD.
Clarification of the Compliance for the Initial and Repetitive
Inspections
For clarification of the compliance for the initial and repetitive
inspections, paragraphs (f)(1) and (g)(1), we have reworded the first
half of the sentences from ``Measure and determine the acceptance of
the LPT stage 1 nozzle assembly ``to Measure throat dimensions,
airflow, and determine serviceability, of the LPT stage 1 nozzle
assembly''.
Clarification of the Compliance for TFE731-3B and -3BR Series Engines
For clarification of the compliance for TFE731-3B and -3BR series
engines, we have moved references to TFE731-3B and -3BR series engines
disk replacement, from paragraph (h) to paragraph (i). Also, for
clarification, we have moved the phrase ``after the effective date of
this AD'' to the beginning of paragraph (h) and paragraph (i) and
deleted the phrase ``or at disk life limit'' because it was redundant
with the ``next access'' compliance time. We have also changed
paragraph (i) of the AD from stating ``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'', to stating:
``(i) For TFE731-3B and -3BR series engines, do the following:
(i)(1) After the effective date of this AD, replace LPT stage 1
disk, P/N 3073497-All, with a serviceable LPT stage 1 disk, at next
MPI, or at next access to the LPT stage 1 nozzle assembly, or before
December 31, 2011, whichever occurs first.
(i)(2) Perform the actions specified in paragraph (i)(1) of this
AD, by converting the TFE731-3B and -3BR
[[Page 12405]]
series engines to a TFE731-3C series engine. This conversion allows the
installation of a serviceable LPT stage 1 disk.''
Service Bulletin References Added to the Optional Terminating Action
We added three service bulletin references to Optional Terminating
Action paragraph (j), of the AD. Paragraph (j) now states ``Information
on installing a serviceable disk can be found in Honeywell
International Inc. SB No. TFE731-72-3704, SB No. TFE731-72-3705, and SB
No. TFE731-72-3706, all dated September 15, 2004.''
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
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 will be affected by
this AD. We also estimate that it will take about 8 work hours per
engine to perform the measurements and calculations during major
periodic inspection (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 will 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 AD to U.S.
operators to be $58,151,000.
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 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
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
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2005-05-15 Honeywell International Inc.: Amendment 39-14004. Docket
No. FAA-2004-18019; Directorate Identifier 2003-NE-65-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective April
18, 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 -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 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 throat dimensions, air flow, and determine
serviceability 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 TIS since the last LPT stage 1
nozzle assembly inspection, do the following:
(1) Measure throat dimensions, air flow, and determine
serviceability of the LPT stage 1 nozzle assembly using paragraphs
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.
[[Page 12406]]
Disk Replacement for TFE731-3, -3A, -3AR, and -3R Series Engines
(h) After the effective date of this AD, for TFE731-3, -3A, -
3AR, and -3R series engines with LPT stage 1 disk, P/N 3072351-All,
3073113-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, or before December 31, 2011, whichever
occurs first.
Disk Replacement for TFE731-3B and -3BR Series Engines
(i) For TFE731-3B and -3BR series engines, do the following:
(1) After the effective date of this AD, replace LPT stage 1
disk, P/N 3073497-All, with a serviceable LPT stage 1 disk, at next
MPI, or at next access to the LPT stage 1 nozzle assembly, or before
December 31, 2011, whichever occurs first.
(2) Perform the actions specified in paragraph (i)(1) of this
AD, by converting the TFE731-3B and -3BR series engines to a TFE731-
3C series engine. This conversion allows the 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
more robust serviceable disk. Information on installing a
serviceable disk can be found in Honeywell International Inc. SB No.
TFE731-72-3704, SB No. TFE731-72-3705, and SB No. TFE731-72-3706,
all dated September 15, 2004.
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
paragraphs (f)(1) and (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) You must use the Honeywell Engines and Systems service
information specified in Table 1 of this AD to perform the
measurements, adjustments, calculations, and replacements required
by this AD. The Director of the Federal Register approved the
incorporation by reference of the document in Table 1 of this AD 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 20590-001, 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.
Table 1
follows:
Table 1.--Incorporation by Reference
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Honeywell Service Bulletin No. Page Revision Date
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TFE731-72-3369RWK.......................... 1-2 6 June 26, 2002.
3 5 August 9, 2001.
4-5 6 June 26, 2002.
6-14 5 August 9, 2001.
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Related Information
(o) None.
Issued in Burlington, Massachusetts, on March 3, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-4686 Filed 3-11-05; 8:45 am]
BILLING CODE 4910-13-P