Document ID: FAA-2009-1185-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Honeywell International LTS101-600A Series and LTS101-700D-2 Turboshaft Engines and LTP101-600A-1A, and LTP101-700A-1A Turboprop Engines
Posted Date: 2009-12-21T05:00Z

[Federal Register: December 21, 2009 (Volume 74, Number 243)]
[Proposed Rules]               
[Page 67829-67830]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21de09-13]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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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[[Page 67829]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1185; Directorate Identifier 2009-NE-24-AD]
RIN 2120-AA64

 
Airworthiness Directives; Honeywell International LTS101-600A 
Series and LTS101-700D-2 Turboshaft Engines and LTP101-600A-1A, and 
LTP101-700A-1A Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Honeywell International LTS101-600A series and LTS101-700D-2 
turboshaft engines and LTP101-600A-1A, and LTP101-700A-1A turboprop 
engines with power turbine blades, part number (P/N) 4-141-084-06, 
installed. This proposed AD would require removing power turbine 
blades, P/N 4-141-084-06 from service, using a drawdown schedule 
specified in this proposed AD. This proposed AD results from reports of 
fatigue cracks in the airfoil of the power turbine blade. We are 
proposing this AD to prevent fracture of the power turbine blade 
airfoil, which could result in sudden loss of engine power.

DATES: We must receive any comments on this proposed AD by February 19, 
2010.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 
85072-2181; telephone (800) 601-3099 (U.S.A.) or (602) 365-3099 
(International); or go to: https://portal.honeywell.com/wps/portal/
aero, for a copy of the service information identified in this proposed 
AD.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2009-1185; Directorate 
Identifier 2009-NE-24-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://
www.regulations.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 Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, 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).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    We have received reports of two power turbine blades, P/N 4-141-
084-06, that had fractures at the mid span of the airfoil. Honeywell's 
analysis of the fractured blades and field returned blades identified a 
manufacturing processing issue, with some blades, which may result in 
crack development between the platinum core pins and the blade 
material. This condition, if not corrected, could result in fracture of 
the power turbine blade airfoil, which could result in sudden loss of 
engine power.

Differences Between the Proposed AD and the Manufacturer's Service 
Information

    Honeywell International Inc. Service Bulletin (SB) LT 101-71-00-
0252, dated December 12, 2008, describes procedures and a drawdown 
schedule for removing power turbine rotors, P/Ns 4-141-290-01, -03, -
05, -06, -11, -12, -13, and -14. This proposed AD would limit the 
actions to removing power turbine blades, P/N 4-141-084-06, from 
service using the same drawdown schedule specified in the SB for the 
power turbine rotors.

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. We are proposing this AD, which would require 
removing power turbine blades, P/N 4-141-084-06, from service using a 
specific drawdown schedule.

Costs of Compliance

    We estimate that this proposed AD would affect 25 engines installed 
on aircraft of U.S. registry. We also estimate that it would take about 
30 work-hours per engine to perform the proposed actions, and that the 
average labor rate

[[Page 67830]]

is $80 per work-hour. Required parts would cost about $70,000 per 
engine. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $1,810,000.

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 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 AD:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. 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, 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, Textron 
Lycoming): Docket No. FAA-2009-1185; Directorate Identifier 2009-NE-
24-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by February 19, 
2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International LTS101-600A-2, -
3, -3A, and LTS101-700D-2 turboshaft engines; and LTP101-600A-1A and 
LTP101-700A-1A turboprop engines with power turbine blades, part 
number (P/N) 4-141-084-06, installed. These engines are installed 
on, but not limited to, Eurocopter AS350 series helicopters and Page 
Thrush, Air Tractor AT-302, and Pacific Aero 08-600 airplanes.

Unsafe Condition

    (d) This AD results from reports of fatigue cracks in the 
airfoil of the power turbine blade. We are issuing this AD to 
prevent fracture of the power turbine blade airfoil, which could 
result in sudden loss of engine power.

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.
    (f) For engines with power turbine rotors, P/Ns 4-141-290-11, -
12, -13, and -14, marked with ``ORI T41881,'' on the aft hub in the 
vicinity of the P/N, no further action is required.

Removing Power Turbine Blades, P/N 4-141-084-06

    (g) Remove power turbine blades, P/N 4-141-084-06, using the 
cycles specified in Table 1 of this AD:

   Table 1--Drawdown Times for Power Turbine Blades, P/N 4-141-084-06
------------------------------------------------------------------------
   If power turbine rotor time on the    Then remove the blades from the
   effective date of this AD is * * *       power turbine rotor * * *
------------------------------------------------------------------------
(1) Fewer than 5,000 cycles-since-new    Before exceeding 5,500 CSN.
 (CSN).
(2) 5,000 to 7,499 CSN.................  Within 500 cycles-in-service
                                          (CIS) after the effective date
                                          of this AD or before exceeding
                                          8,000 CSN, whichever occurs
                                          first.
(3) 7,500 to 9,999 CSN.................  Within 100 CIS after the
                                          effective date of this AD or
                                          before exceeding 10,050 CSN,
                                          whichever occurs first.
(4) 10,000 or more CSN.................  Within 50 CIS after the
                                          effective date of this AD.
------------------------------------------------------------------------

Alternative Methods of Compliance

    (h) The Manager, Los Angles 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.

Related Information

    (i) Contact Robert Baitoo, Aerospace Engineer, Los Angeles 
Aircraft Certification Office, FAA, Transport Airplane Directorate, 
3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail: 
robert.baitoo@faa.gov; telephone (562) 627-5245; fax (562) 627-5210, 
for more information about this AD.
    (j) Honeywell International Inc. Service Bulletin LT 101-71-00-
0252, dated December 12, 2008, pertains to the subject of this AD. 
Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 
85072-2181; telephone (800) 601-3099 (U.S.A.) or (602) 365-3099 
(International); or go to: https://portal.honeywell.com/wps/portal/
aero, for a copy of this service information.

    Issued in Burlington, MA, on December 11, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-30220 Filed 12-18-09; 8:45 am]

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