[Federal Register Volume 67, Number 90 (Thursday, May 9, 2002)]
[Rules and Regulations]
[Pages 31111-31113]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-11216]



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 Rules and Regulations
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  Federal Register / Vol. 67, No. 90 / Thursday, May 9, 2002 / Rules 
and Regulations  

[[Page 31111]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-50-AD; Amendment 39-12742; AD 2002-09-09]
RIN 2120-AA64


Airworthiness Directives; Honeywell International, Inc., 
(Formerly AlliedSignal, Inc., Textron Lycoming, Avco Lycoming, and 
Lycoming) Former Military T53 Series Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Honeywell International, Inc., (formerly AlliedSignal, 
Inc., Textron Lycoming, Avco Lycoming, and Lycoming) former military 
T53 series turboshaft engines. This amendment requires conducting a 
revised operating cycle count (prorate) and initial and repetitive 
inspections for cracks of centrifugal compressor impellers. This 
amendment is prompted by a report of a military surplus helicopter that 
experienced low-cycle fatigue failure of the centrifugal compressor 
impeller, resulting in an uncontained engine failure. The actions 
specified by this AD are intended to prevent centrifugal compressor 
impeller failure, which can result in an uncontained engine failure, 
in-flight engine shutdown, or damage to the helicopter.

DATES: Effective date June 13, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of June 13, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Honeywell International, Inc., Attn: Data Distribution, 
M/S 64-3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone: 
(602) 365-2493; fax: (602) 365-5577. This information may be examined, 
by appointment, at the Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone: 
(562) 627-5245, fax: (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Honeywell International, Inc., (formerly AlliedSignal, 
Inc., Textron Lycoming, Avco Lycoming, and Lycoming) former military 
T53 series turboshaft engines was published in the Federal Register on 
August 16, 2001(66 FR 42970). That action proposed to require 
conducting a revised operating cycle count (prorate) and initial and 
repetitive inspections for cracks of centrifugal compressor impellers 
in accordance with AlliedSignal, Inc. SB's T53-L-13B-0108, Revision 1, 
dated November 22, 1999; T53-L-13B/D-0108, Revision 1, dated November 
22, 1999; T53-L-703-0108, Revision 1, dated November 22, 1999 and 
Honeywell International Inc. SB's T53-L-13B-0020, Revision 2, dated 
April 25, 2001; T53-L-13B/D-0020, Revision 1, dated April 25, 2001; and 
T53-L-703-0020, Revision 1, dated April 25, 2001.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.
    One commenter believes that the AD is unnecessary. The FAA does not 
agree. The AD was prompted by a report of a military surplus helicopter 
that experienced low-cycle fatigue of the centrifugal compressor 
impeller, resulting in an uncontained engine failure.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Economic Analysis

    The FAA estimates that there are approximately 300 Lycoming former 
military T53 series turboshaft engines installed on helicopters of U.S. 
registry, that would be affected by this AD. The FAA also estimates 
that it would take approximately 8 work hours per engine to accomplish 
an initial or repetitive inspection of the centrifugal compressor 
impeller, and that the average labor rate is $60 per work hour. No 
additional work hour cost would be incurred if the centrifugal 
compressor impeller is replaced during normal engine disassembly. Based 
on these figures, the total labor cost impact of the AD on U.S. 
operators for an inspection is estimated to be $144,000. The FAA 
estimates that operators will perform two inspections annually, and 
that the total annual labor cost for inspections is estimated to be 
$288,000. The cost of a replacement centrifugal compressor impeller is 
estimated to be $22,037. Assuming a loss of 50% of the life of each 
disk by the prorate, the total annual cost of the proposed AD on U.S. 
operators is estimated to be $3,593,550.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    For the reasons discussed above, I certify that this action (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) if promulgated, 
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. A final evaluation has been prepared for 
this action and it is contained in the Rules Docket. A copy of it may 
be obtained by contacting the

[[Page 31112]]

Rules Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

2002-09-09  Honeywell International, Inc.: Amendment 39-12742. 
Docket No. 2000-NE-50-AD.

Applicability

    This airworthiness directive (AD) is applicable to Honeywell 
International, Inc. (formerly AlliedSignal, Inc., Textron Lycoming, 
Avco Lycoming, and Lycoming) former military T53 series turboshaft 
engines with centrifugal compressor impellers part numbers (P/N's) 
1-100-078-07 or 1-100-078-08 installed. These engines are installed 
on, but not limited to, Bell Helicopter Textron manufactured AH-1, 
UH-1, and SW-204/205 (UH-1) series surplus military helicopters that 
have been certified in accordance with Secs. 21.25 or 21.27 of the 
Federal Aviation regulations (14 CFR 21.25 or 21.27).

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (e) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent centrifugal compressor impeller failure, which can 
result in an uncontained engine failure, in-flight engine shutdown, 
or damage to the helicopter, do the following:

Centrifugal Compressor Impeller Revised Operating Cycle Count

    (a) Within 25 operating cycles or 7 calendar days, whichever 
occurs first, after the effective date of this AD, do a revised 
centrifugal compressor impeller operating cycle count (prorate) in 
accordance with the accomplishment instructions of Honeywell 
International, Inc. Service Bulletin (SB) No. T53-L-13B-0020, 
Revision 3, dated October 25, 2001, for T53-L-13B Lycoming engines, 
SB No. T53-L-13B/D-0020, Revision 1, dated April 25, 2001 for T53-L-
13B/D Lycoming engines, and SB No. T53-L-703-0020, Revision 1, dated 
April 25, 2001 for T53-L-703 Lycoming engines.
    (b) Following the revised operating cycle count required by 
paragraph (a) of this AD, remove from service installed centrifugal 
compressor impellers that exceed their life limit or whose life 
cannot be determined, within 50 hours time-in-service (TIS), or 25 
operating cycles, whichever occurs first and replace with a 
serviceable part that does not exceed the life limit.
    (c) Installation of uninstalled centrifugal compressor impellers 
that exceed their life limit, which is revised in accordance with 
paragraph (a) of this AD is prohibited.

Centrifugal Compressor Impeller Inspections

    (d) Following the revised operating cycle count required by 
paragraph (a) of this AD, inspect centrifugal compressor impellers, 
part numbers (P/N's) 1-100-078-07 and 1-100-078-08, in accordance 
with the accomplishment instructions of AlliedSignal, Inc. SB No. 
T53-L-13B-0108, Revision 1, dated November 22, 1999, for T53-L-13B 
Lycoming engines; SB No. T53-L-13B/D-0108, Revision 1, dated 
November 22, 1999 for T53-L-13B/D Lycoming engines; or SB No. T53-L-
703-0108, Revision 1, dated November 22, 1999 for T53-L-703 Lycoming 
engines, as follows:
    (1) For centrifugal compressor impellers with equal to or 
greater than 4,600 cycles-in-service (CIS), initially inspect within 
200 CIS after the effective date of this AD.
    (2) For those centrifugal compressor impellers with less than 
4,600 CIS, initially inspect no later than 4,800 CIS.
    (3) Centrifugal compressor impellers found cracked must be 
removed from service prior to further flight and replaced with a 
serviceable part.
    (4) If no cracks are detected, perform repetitive inspections of 
the centrifugal compressor impellers at intervals not to exceed 500 
CIS since last inspection.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (ACO). Operators must submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (f) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated By Reference

    (g) The inspection must be done in accordance with the following 
Honeywell International Inc. (HII) and AlliedSignal, Inc. (ASI) 
service bulletins:

----------------------------------------------------------------------------------------------------------------
           Document No.                   Pages                 Revision                       Date
----------------------------------------------------------------------------------------------------------------
HII, SB No. T53-L-13B-0020.......  All...............  3........................  Oct. 25, 2001.
    Total pages 13
HII, SB No. T53-L-13B/D-0020.....  All...............  1........................  April 25, 2001.
    Total pages 12
HII, SB No. T53-L-703-0020.......  All...............  1........................  April 25, 2001.
    Total pages 12
ASI..............................  1.................  Original.................  July 22, 1999.
SB No. T53-L-13B-0108............  2.................  1........................  Nov. 22, 1999.
                                   3-12..............  Original.................  July 22, 1999.
    Total pages 12
ASI..............................  1.................  Original.................  July 22, 1999.
SB No. T53-L-13B/D-0108..........  2.................  1........................  Nov. 22, 1999.
                                   3-12..............  Original.................  July 22, 1999.
    Total pages 12
ASI..............................  1.................  Original.................  July 22, 1999.
SB No. T53-L-703-0108............  2.................  1........................  Nov. 22, 1999.

[[Page 31113]]

 
                                   3-12..............  Original.................  July 22, 1999.
    Total pages 12
----------------------------------------------------------------------------------------------------------------

    This incorporation by reference was approved by the Director of 
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Honeywell International, Inc., 
Attn: Data Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix, 
AZ 85038-9003; telephone: (602) 365-2493; fax: (602) 365-5577. 
Copies may be inspected, by appointment, at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive 
Park, Burlington, MA; or at the Office of the Federal Register, 800 
North Capitol Street, NW, suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on June 13, 2002.

    Issued in Burlington, Massachusetts, on April 29, 2002.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-11216 Filed 5-8-02; 8:45 am]
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