[Federal Register Volume 66, Number 159 (Thursday, August 16, 2001)]
[Proposed Rules]
[Pages 42970-42972]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-20591]


 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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  Federal Register / Vol. 66, No. 159 / Thursday, August 16, 2001 / 
Proposed Rules  

[[Page 42970]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-50-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt 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 (herein referred to as Lycoming) having certain part numbers of 
centrifugal compressor impellers installed. This proposal would require 
conducting a revised operating cycle count (prorate) and initial and 
repetitive inspections for cracks of those compressor impellers. This 
proposal 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 the proposed 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: Comments must be received by October 15, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-50-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: [email protected]''. Comments sent via the Internet must contain the 
docket number in the subject line. Comments may be inspected at this 
location between 8:00 a.m. and 4:30 p.m., Monday through Friday, except 
Federal holidays. The service information referenced in the proposed 
rule 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 at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-50-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2000-NE-50-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The FAA has become aware of a Lycoming former military T53 series 
turboshaft engine, installed on a Bell Helicopter Textron manufactured 
UH-1L military surplus helicopter, that experienced low-cycle fatigue 
failure of the centrifugal compressor impeller, resulting in an 
uncontained engine failure. In May 1995, the FAA published AD 95-10-04, 
dated May 25, 1995, to revise operating cycle counts (prorate) and 
require initial and repetitive inspections for cracks, for centrifugal 
compressor impellers, part numbers (P/N's) 1-100-78-07 and 1-100-078-
08, installed on Lycoming former military T5313B and T5317 series 
turboshaft engines. Because centrifugal compressor impellers P/N's 1-
100-78-07 and 1-100-078-08 are also installed on Lycoming former 
military T53 series engines, this proposal would require revising 
operating cycle counts (prorate) and require initial and repetitive 
inspections for cracks for centrifugal compressor impellers P/N's 1-
100-078-07 and 1-100-078-08, installed on Lycoming former military T53 
series turboshaft engines. This proposal 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. These impellers, if not inspected for cracks using a 
revised cycle count could experience low-cycle fatigue failure, 
resulting in an uncontained engine failure, in-flight shutdown, or 
damage to the helicopter.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of 
Honeywell International, Inc. Service Bulletins (SB's) T53-L-13B-0020, 
Revision 2, dated April 25, 2001; T53-L-13B/D-0020, Revision 1, dated 
April 25, 2001;

[[Page 42971]]

and T53-L-703-0020, Revision 1, dated April 25, 2001; that describe 
procedures for conducting a revised centrifugal compressor impeller 
operating cycle count (prorate) of impellers P/N's 1-100-078-07 and 1-
100-078-08. The FAA has also reviewed and approved the technical 
contents of 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; and T53-L-703-0108, Revision 1, dated November 22, 1999; that 
describe procedures for special visual and fluorescent-penetrant 
inspections of centrifugal compressor impellers P/N's 1-100-078-07 and 
1-100-078-08.

Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design, the proposed 
AD would require initial and repetitive inspections of centrifugal 
compressor impellers, using a revised cycle count. The actions would be 
required to be done in accordance with the service bulletins described 
previously.

Economic Impact

    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 proposed 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 proposed 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 Impact

    This proposal 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 proposal.
    For the reasons discussed above, I certify that this 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) 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 copy of the draft 
regulatory evaluation prepared for this action 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 the following new 
airworthiness directive:

Honeywell International, Inc. Docket 2000-NE-50-AD.

Applicability

    This airworthiness directive (AD) is applicable to Honeywell 
International, Inc., (formerly AlliedSignal, Inc., Textron Lycoming, 
Avco Lycoming, and Lycoming) (herein referred to as Lycoming) former 
military T53-L-13B series, T53-L-13B/D series, and T53-L-703 series 
turboshaft engines with centrifugal compressor impellers part 
numbers (P/N's) 1-100-078-07 or 1-100-078-08 installed. These 
Lycoming 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 
accomplished previously.
    To prevent centrifugal compressor impeller failure, which can 
result in an uncontained engine failure, in-flight engine shutdown, 
or damage to the helicopter, accomplish 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 2, dated April 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

[[Page 42972]]

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 3: 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 
sections 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 accomplished.

    Issued in Burlington, Massachusetts, on August 7, 2001.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-20591 Filed 8-15-01; 8:45 am]
BILLING CODE 4910-13-U