[Federal Register Volume 69, Number 115 (Wednesday, June 16, 2004)]
[Proposed Rules]
[Pages 33599-33601]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-13564]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18038; Directorate Identifier 2004-NE-01-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc., (Formerly 
AlliedSignal, Inc., Formerly Textron Lycoming) T5309, T5311, T5313B, 
T5317A, T5317A-1, and T5317B Series, and T53-L-9, T53-L-11, T53-L-13B, 
T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 
Series Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Honeywell International Inc. (formerly AlliedSignal, Inc., formerly 
Textron Lycoming), T5309, T5311, T5313B, T5317A, T5317A-1, and T5317B 
series turboshaft engines, installed on, but not limited to, Bell 205 
and Kaman K-1200 series helicopters, and T53-L-9, T53-L-11, T53-L-13B, 
T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 
series turboshaft engines, installed on, but not limited to, Bell AH-1 
and UH-1 helicopters, certified under Sec.  21.25 or 21.27 of the Code 
of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). This proposed AD 
would require operators to remove from service affected compressor, gas 
producer, and power turbine rotating components at reduced life limits, 
and would require use of replacement drawdown schedules for components 
on certain engine models that exceed the new limits. This proposal 
results from continuous analysis of field-returned hardware indicating 
smaller service life margins than originally expected. We are proposing 
this AD to prevent failure of the compressor, gas producer, and power 
turbine rotating components which could result in an uncontained 
failure of the engine and damage to the helicopter.

DATES: We must receive any comments on this proposed AD by August 16, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this proposed AD 
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.
    You may examine the comments on this proposed AD in the AD docket 
on the Internet at http://dms.dot.gov.

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: 

Docket Management System (DMS)

    We have implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, we posted new AD actions on the DMS 
and assigned a DMS docket number. We track each action and assign a 
corresponding Directorate identifier. The DMS docket No. is in the form 
``Docket No. FAA-200X-XXXXX.'' Each DMS docket also lists the 
Directorate identifier (``Old Docket Number'') as a cross-reference for 
searching purposes.

[[Page 33600]]

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18038; 
Directorate Identifier 2004-NE-01-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of the 
DMS web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the docket that contains the proposal, 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.

Discussion

    Honeywell International Inc. (formerly AlliedSignal Inc., formerly 
Textron Lycoming), has advised us that continuous analysis of field-
returned hardware indicates smaller service life margins than 
originally intended for certain compressor, gas producer, and power 
turbine rotating components installed in T5309, T5311, T5313B, T5317A, 
T5317A-1, and T5317B series turboshaft engines, which are installed on, 
but not limited to, Bell 205 and Kaman K-1200 series helicopters, and 
T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/
SB, T53-L-13B/D, and T53-L-703 series turboshaft engines, installed on, 
but not limited to, Bell AH-1 and UH-1 helicopters, certified under 
Sec.  21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 
or 14 CFR 21.27). This condition, if not corrected, could result in 
uncontained failure of the engine due to fatigue-cracked engine rotor 
disks.

Relevant Service Information

    We have reviewed and approved the technical contents of the 
following service bulletins (SBs) that describe reduced limits for 
removal from service of affected compressor, gas producer, and power 
turbine rotating components:
     Lycoming SB No. 0002, Revision 2, dated March 6, 1989.
     Honeywell International Inc. SB No. T5313B/17-0020, 
Revision 7, dated November 21, 2002.
     Honeywell International Inc. SB No. T53-L-13B-0020, 
Revision 3, dated October 25, 2001.
     Honeywell International Inc. SB No. T53-L-13B/D-0020, 
Revision 2, dated November 25, 2002.
     Honeywell International Inc. SB No. T53-L-703-0020, 
Revision 2, dated November 25, 2002.
    We have also reviewed and approved the technical contents of the 
following SBs that describe replacement drawdown schedules for 
components that exceed new limits listed in the SBs.
     Honeywell International Inc. SB No. T5313B-0125, dated 
March 15, 2001.
     Honeywell International Inc. SB No. T5317-0125, dated 
March 15, 2001.
     Honeywell International Inc. SB No. T53-L-13B-0125, dated 
April 5, 2001.
     Honeywell International Inc. SB No. T53-L-13B/D-0125, 
dated April 5, 2001.
     Honeywell International Inc. SB No. T53-L-703-0125, dated 
April 5, 2001.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing this AD, which 
would:
     Require operators to remove from service affected 
compressor, gas producer, and power turbine rotating components at 
reduced life limits; and
     Require use of replacement drawdown schedules for affected 
components that exceed the new limits.
    The FAA Engine & Propeller Directorate has coordinated the reduced 
life limits for engines installed on surplus military aircraft 
certified under Sec.  21.25 or 21.27 of the Code of Federal Regulations 
(14 CFR 21.25 or 14 CFR 21.27), with the FAA Rotorcraft Directorate. 
The proposed AD would require you to use the service information 
described previously to perform these actions.

Costs of Compliance

    There are about 4,500 Honeywell International Inc. (formerly 
AlliedSignal, Inc., formerly Textron Lycoming), T5309, T5311, T5313B, 
T5317A, T5317A-1, and T5317B series turboshaft engines, installed on, 
but not limited to, Bell 205 and Kaman K-1200 series helicopters, and 
T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/
SB, T53-L-13B/D, and T53-L-703 series turboshaft engines, installed on, 
but not limited to, Bell AH-1 and UH-1 helicopters, certified under 
Sec.  21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 
or 14 CFR 21.27), of the affected design in the worldwide fleet. We 
estimate that 300 engines installed on helicopters of U.S. registry 
would be affected by this proposed AD, and that the prorated cost of 
the life reduction per engine would be about $250,000. Based on these 
figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $75,000,000.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. Would 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 proposal and 
placed it in the AD Docket. You may get a copy

[[Page 33601]]

of this summary at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

Honeywell International Inc. (formerly AlliedSignal, Inc., formerly 
Textron Lycoming): Docket No. FAA-2004-18038; Directorate Identifier 
2004-NE-01-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by August 16, 
2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International Inc., (formerly 
AlliedSignal, Inc., formerly Textron Lycoming) T5309, T5311, T5313B, 
T5317A, T5317A-1, and T5317B series turboshaft engines, installed 
on, but not limited to, Bell 205 and Kaman K-1200 series 
helicopters, and T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B 
S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 series turboshaft 
engines, installed on, but not limited to, Bell AH-1 and UH-1 
helicopters, certified under Sec.  21.25 or 21.27 of the Code of 
Federal Regulations (14 CFR 21.25 or 14 CFR 21.27).

Unsafe Condition

    (d) This AD results from continuous analysis of field-returned 
hardware indicating smaller service life margins than originally 
expected. We are issuing this AD to prevent failure of compressor, 
gas producer, and power turbine rotating components, which could 
result in an uncontained failure of the engine and damage to the 
helicopter.

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.

T5309, T5311, T53-L-9, and T53-L-11 Series Turboshaft Engines

    (f) For T5309, T5311, T53-L-9, and T53-L-11 series turboshaft 
engines, within 100 operating hours after the effective date of this 
AD, compute the total operating hours and cycles and replace 
rotating components before they exceed the service life limits. Use 
2.a. through 2.f. and Component Service Life Limits Table 1 of 
Accomplishment Instructions of Lycoming Service Bulletin (SB) No. 
0002, Revision 2, dated March 6, 1989.

T5313B, T5317A, T5317A-1, and T5317B Turboshaft Engines

    (g) For T5313B, T5317A, T5317A-1, and T5317B turboshaft engines, 
within 100 operating hours after the effective date of this AD, 
compute the total operating hours and cycles and replace the 
rotating components before they exceed the service life limits. Use 
2.A. through 2.K. and Component Service Life Limits Table 1 of 
Accomplishment Instructions of Honeywell International Inc. SB No. 
T5313B/17-0020, Revision 7, dated November 21, 2002.
    (h) For T513B, T5317A, T5317A-1, and T5317B turboshaft engines 
that have one or more rotating components that exceed the limits 
specified in Component Service Life Limits Table 1 of Honeywell 
International Inc. SB No. T5313B/17-0020, Revision 7, dated November 
21, 2002, replace the components using the applicable drawdown 
schedule in Table 1 of Honeywell International Inc. SB No. T5313B-
0125, dated March 15, 2001 or Honey well International Inc. SB No. 
T5317-0125, dated March 15, 2001.

T53-L-13B, T53-L-13BA, T53-L-13B S/SA, and T53-L-13B S/SB Turboshaft 
Engines

    (i) For T53-L-13B, T53-L-13BA, T53-L-13B S/SA, and T53-L-13B S/
SB turboshaft engines, within 100 operating hours after the 
effective date of this AD, compute the total operating hours and 
cycles and replace the rotating components before they exceed the 
service life limits. Use 2.A. through 2.J. and Component Service 
Life Limits Table 1 of Accomplishment Instructions of Honeywell 
International Inc. SB No. T53-L-13B-0020, Revision 3, dated October 
25, 2001.
    (j) For T53-L-13B, T53-L-13BA, T53-L-13B S/SA, and T53-L-13B S/
SB turboshaft engines that have one or more rotating components that 
exceed the limits in Component Service Life Limits Table 1 of 
Honeywell SB No. T53-L-13B-0020, Revision 3, dated October 25, 2001, 
replace the components using the applicable drawdown schedule in 
Table 1 of Honeywell International Inc. SB No. T53-L-13B-0125, dated 
April 5, 2001.

T53-L-13B/D Turboshaft Engines

    (k) For T53-L-13B/D turboshaft engines, within 100 operating 
hours after the effective date of this AD, compute the total 
operating hours and cycles and replace the rotating components 
before they exceed the service life limits. Use 2.A. through 2.J. 
and Component Service Life Limits Table 1 of Accomplishment 
Instructions of Honeywell International Inc. SB No. T53-L-13B/D-
0020, Revision 2, dated November 25, 2002.
    (l) For T53-L-13B/D turboshaft engines that have one or more 
rotating components that exceed the limits in Component Service Life 
Limits Table 1 of Honeywell International Inc. SB No. T53-L-13B/D-
0020, Revision 2, dated November 25, 2002, replace the components 
using the applicable drawdown schedule in Table 1 of Honeywell 
International Inc. SB No. T53-L-13B/D-0125, dated April 5, 2001.

T53-L-703 Turboshaft Engines

    (m) For T53-L-703 turboshaft engines, within 100 operating hours 
after the effective date of this AD, compute the total operating 
hours and cycles and replace the rotating components before they 
exceed the service life limits. Use 2.A. through 2.K. and Component 
Service Life Limits Table 1 of Accomplishment Instructions of 
Honeywell International Inc. SB No. T53-L-703-0020, Revision 2, 
dated November 25, 2002.
    (n) For T53-L-703 turboshaft engines that have one or more 
rotating components that have exceeded the limits in Component 
Service Life Limits Table 1 of Honeywell International Inc. SB No. 
T53-L-703-0020, Revision 2, dated November 25, 2002, replace the 
components using the applicable drawdown schedule in Table 1 of 
Honeywell International Inc. SB No. T53-L-703-0125, dated April 5, 
2001.

Computing Compliance Intervals

    (o) For the purposes of this AD, use the effective date of this 
AD for computing compliance intervals whenever the SBs refer to the 
release date of the SB.

Prohibition of Removed Rotating Components

    (p) Do not reinstall any rotating component that is replaced as 
specified in paragraphs (f) through (n) of this AD, into any engine.

Alternative Methods of Compliance

    (q) 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

    (r) None.

Related Information

    (s) None.

    Issued in Burlington, Massachusetts, on June 3, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 04-13564 Filed 6-15-04; 8:45 am]
BILLING CODE 4910-13-P