[Federal Register Volume 67, Number 31 (Thursday, February 14, 2002)]
[Rules and Regulations]
[Pages 6857-6859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3310]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-34-AD; Amendment 39-12642; AD 2002-03-01]
RIN 2120-AA64


Airworthiness Directives; Honeywell International, Inc., 
(Formerly AlliedSignal, Inc., and Textron Lycoming) T5311A, T5311B, 
T5313B, T5317A, T5317B, T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-
L-11D, T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and 
T53-L-703 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., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and 
former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, 
T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-
703 series turboshaft engines. This amendment requires initial and 
repetitive special vibration tests of the engine, and if necessary 
replacement with a serviceable reduction gearbox assembly, or a 
serviceable engine before further flight. This amendment is prompted by 
reports of tachometer drive spur gear failure, resulting in potential 
engine overspeed, loss of power turbine speed (N2) instrument panel 
indication, and hard landings. The actions specified in this AD are 
intended to prevent excessive vibrations produced by the reduction 
gearbox assembly that could cause failure of the tachometer drive spur 
gear.

DATES: Effective date March 21, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of March 21, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Honeywell International, Inc., (formerly AlliedSignal, 
Inc., and Textron Lycoming), 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., and Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and 
former military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, 
T53-L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-
703 series turboshaft engines was published in the Federal Register on 
June 15, 2001 (66 FR 32591). That action proposed to require initial 
and repetitive special vibration tests of the engine, and if necessary 
replacement with a serviceable reduction gearbox assembly, or a 
serviceable engine before further flight, in accordance with 
AlliedSignal, Inc., Service Bulletin (SB) No.''s T5311A/B-0100, dated 
January 20, 2000; T5313B/17-0100, dated November 19, 1999; T53-L-11-
0100, dated January 20, 2000; T53-L-13B-0100, Revision 2, dated May 11, 
1999; and T53-L-703-0100, Revision 2, dated May 11, 1999.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the one comment received.
    The commenter stated that further investigation into the root 
problem causing the spur gear failures needs to be addressed. The 
problem may be a manufacturing problem from one U.S. Government 
contract supplier.
    The FAA does not agree. The commenter did not supply sufficient 
evidence substantiating a design nonconformity.
    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

    There are about 4,500 engines of the affected design in the 
worldwide fleet. The FAA estimates that 300 engines

[[Page 6858]]

installed on aircraft of U.S. registry would be affected by this AD, 
and that it would take about four work hours per engine to accomplish 
each special vibration test, and that the average labor rate is $60 per 
work hour. Based on these figures, for each special vibration test, the 
total labor cost effect on U.S. operators is estimated to be $240 per 
engine. The FAA estimates that operators, on average, will perform ten 
special vibration tests per year, resulting in a total annual cost on 
U.S. operators of $720,000.

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 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:

2002-03-01  Honeywell International, Inc.: Amendment 39-12642. 
Docket No. 2000-NE-34-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Honeywell International, Inc., (formerly AlliedSignal, Inc., and 
Textron Lycoming) T5311A, T5311B, T5313B, T5317A, T5317B, and former 
military T53-L-11, T53-L-11A, T53-L-11B, T53-L-11C, T53-L-11D, T53-
L-11A S/SA, T53-L-13B, T53-L-13B S/SA, T53-L-13B S/SB, and T53-L-703 
turboshaft engines. These engines are installed on, but not limited 
to Bell Helicopter Textron 204, 205, and 209 series, and Kaman K-
1200 series helicopters, and the following surplus military 
helicopters that have been certified in accordance with sections 
21.25 or 21.27 of the Federal Aviation Regulations (14 CFR 21.25 or 
21.27): Bell Helicopter Textron manufactured AH-1, HH-43, TH-1, UH-1 
and SW-204/205 (UH-1) series.

    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 (d) 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 excessive vibrations produced by the reduction 
gearbox assembly that could cause failure of the tachometer drive 
spur gear, do the following:

Initial and Repetitive Special Vibration Tests

    (a) Perform an initial special vibration test of the engine in 
accordance with the applicable service bulletin (SB) listed in the 
following Table 1, within 100 flight hours after the effective date 
of this AD:

         Table 1. AlliedSignal SB's for Special Vibration Tests.
------------------------------------------------------------------------
               Engine                                SB's
------------------------------------------------------------------------
(1) T5311A and T5311B..............  T5311A/B-0100, dated January 20,
                                      2000.
(2) T5313B, T5317A, and T5317B.....  T5313B/17-0100, dated November 19,
                                      1999.
(3) T53-L-11, -11A, -11B, -11C, -    T53-L-11-0100, Revision 2, dated
 11D, and 11A S/SA.                   January 20, 2000.
(4) T53-L-13B, -13B S/SA, and -13B   T53-L-13B-0100, Revision 2, dated
 S/SB.                                May 11, 1999.
(5) T53-L-703......................  T53-L-703-0100, Revision 2, dated
                                      May 11, 1999.
------------------------------------------------------------------------

    (b) Perform repetitive special vibration tests of the engine in 
accordance with the applicable SB listed in Table 1 of this AD, as 
follows:
    (1) For engines that have tachometer drive spur gear part number 
(P/N) 1-070-062-04 installed, perform repetitive special vibration 
tests within 500 flight hours since the last special vibration test.
    (2) For engines that have tachometer drive spur gear P/N 1-070-
062-06 installed, perform repetitive special vibration tests within 
1,000 flight hours since the last special vibration test.

Engines That Fail Special Vibration Tests

    (c) For engines that fail a special vibration test performed in 
accordance with paragraph (a) or (b) of this AD, do either of the 
following:
    (1) Replace the gearbox assembly with a serviceable reduction 
gearbox assembly, and before further flight perform an initial 
special vibration test as specified in paragraph (a) of this AD; or
    (2) Replace the engine with a serviceable engine, and before 
further flight perform an initial special vibration test as 
specified in paragraph (a) of this AD.

Alternative Methods of Compliance

    (d) 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 airworthiness directive, 
if any, may be obtained from the Los Angeles ACO.

Special Flight Permits

    (e) 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 aircraft to a location where the 
special vibration tests and engine replacement requirements of this 
AD can be done.

[[Page 6859]]

Documents That Have Been Incorporated By Reference

    (f) The inspection must be done in accordance with the following 
AlliedSignal, Inc. Service Bulletins (SB's):

----------------------------------------------------------------------------------------------------------------
          Document No.                  Pages                Revision                        Date
----------------------------------------------------------------------------------------------------------------
SB T5311A/B-0100................  All..............  Original...............  January 20, 2000.
    Total pages: 5                                                            ..................................
SB T5313B/17-0100...............  All..............  Original...............  November 19, 1999.
    Total pages: 5                                                            ..................................
SB T53-L-11-0100................  All..............  Revision 2.............  January 20, 2000.
    Total pages: 5                                                            ..................................
SB T53-L-13B-0100...............  All..............  Revision 2.............  May 11, 1999.
    Total pages: 5                                                            ..................................
SB T53-L-703-0100...............  All..............  Revision 2.............  May 11, 1999.
    Total pages: 5                                                            ..................................
----------------------------------------------------------------------------------------------------------------

    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. 
(formerly AlliedSignal, Inc. and Textron Lycoming), 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

    (g) This amendment becomes effective on March 21, 2002.

    Issued in Burlington, Massachusetts, on February 4, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-3310 Filed 2-13-02; 8:45 am]
BILLING CODE 4910-13-U