Airworthiness Directives; Honeywell International Inc. TFE731-2 and -3 Series Turbofan Engines

[Federal Register Volume 70, Number 48 (Monday, March 14, 2005)]
[Rules and Regulations]
[Pages 12404-12406]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-4686]



[[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
----------------------------------------------------------------------------------------------------------------
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

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