[Federal Register Volume 76, Number 153 (Tuesday, August 9, 2011)]
[Proposed Rules]
[Pages 48749-48751]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-20170]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0789; Directorate Identifier 2011-NE-04-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. TPE331-10 
and TPE331-11 Series Turboprop Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD would require inspecting 
certain serial number (S/N) first stage turbine disks, part number (P/
N) 3101520-1 and P/N 3107079-1. This proposed AD was prompted by a 
report of an uncontained failure of a first stage turbine disk that had 
a metallurgical defect. We are proposing this AD to prevent uncontained 
failure of the first stage turbine disk and damage to the airplane.

DATES: We must receive comments on this proposed AD by September 23, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Web site: http://portal.honeywell.com; or call Honeywell toll 
free at (800) 601-3099 (U.S./Canada) or (602) 365-3099 (International 
Direct). You may review copies of the referenced service information at 
the FAA, Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call (781) 238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
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 Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los 
Angles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 
(562) 627-5246; fax: (562) 627-5210; e-mail: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-0789; 
Directorate Identifier 2011-NE-04-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because 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 we 
receive about this proposed AD.

Discussion

    In May 2008, we received a report of an uncontained separation of a 
first stage turbine disk, P/N 3107079-1. The disk was installed in a 
TPE331-11U turboprop engine. That disk, which has a 20,000-cycle life, 
failed after accumulating 8,314 cycles-in-service. The fracture 
revealed a large melt-related oxide cluster inclusion in the web area 
of the disk, which occurred during the forging alloy melting process. 
The disk was produced from Waspaloy material, from Heat Lot 9-7121, 
which was melted by Special Metals in 1980. We have determined that 
approximately 360 turbine disks were produced from the same heat lot as 
the failed forged turbine disk and therefore may have similar 
inclusions. This condition, if not corrected, could result in 
uncontained failure of the first stage turbine disks made from these 
billets and damage to the airplane.

Relevant Service Information

    We reviewed Honeywell International Inc. Alert Service Bulletin 
(ASB) TPE331-72-A2156, dated December 2, 2008. The Honeywell ASB 
TPE331-72-A2156, dated December 2, 2008, provides S/Ns of the affected 
turbine disks and describes procedures for initial and repetitive 
fluorescent penetrant inspection (FPI) and eddy current inspection 
(ECI) of the first stage turbine disk.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require:
     For turbine disks that have an S/N listed in Table 1 of 
this proposed AD with 4,100 or fewer cycles-since-new (CSN) on the 
effective date of this proposed AD, performing an initial FPI and ECI 
within 4,500 CSN or at the next access, whichever occurs first.
     For turbine disks that have an S/N listed in Table 1 of 
this proposed AD with more than 4,100 CSN on the effective date of this 
proposed AD, performing an initial FPI and ECI within 400 cycles-in-
service after the effective date of this proposed AD or at the next 
access, whichever occurs first.
     Thereafter, for turbine disks that have an S/N listed in 
Table 1 of this proposed AD, perform a repetitive FPI and ECI at each 
scheduled hot section inspection, but not to exceed 3,600 hours-since-
last inspection.
    The proposed AD would require that you do these actions using the 
service information described previously.

[[Page 48750]]

Costs of Compliance

    We estimate that this proposed AD would affect 90 engines installed 
on airplanes of U.S. registry. We also estimate that it would take 
about 20 work-hours per engine to perform the proposed actions, and 
that the average labor rate is $85 per work-hour. Required parts would 
cost about $19,000 per engine. We estimate that one disk would fail the 
initial inspection and that repetitive inspections would be performed 
on 89 engines. We estimate that one engine would fail the repetitive 
inspections and that further repetitive inspections would be performed 
on 88 engines. We estimate that an additional one disk would fail those 
repetitive inspections before retirement. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$511,155.

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 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 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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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 (AD):

Honeywell International Inc. (Formerly AlliedSignal Inc., Garrett 
Engine Division; Garrett Turbine Engine Company; and AiResearch 
Manufacturing Company of Arizona): Docket No. FAA-2011-0789; 
Directorate Identifier 2011-NE-04-AD.

Comments Due Date

    (a) We must receive comments by September 23, 2011.

Affected ADs

    (b) None.

Applicability

    (c) Honeywell International Inc. TPE331-10, -10AV, -10GP, -10GT, 
-10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, 
and TPE331-11U model turboprop engines with a first stage turbine 
disk, part number (P/N) 3101520-1 or 3107079-1, with a serial number 
(S/N) listed in Table 2 of Honeywell International Inc. Alert 
Service Bulletin (ASB) TPE331-72-A2156, dated December 2, 2008, 
installed.

Unsafe Condition

    (d) This AD was prompted by a report of an uncontained failure 
of a first stage turbine disk that had a metallurgical defect. We 
are issuing this AD to prevent uncontained failure of the first 
stage turbine disk and damage to the airplane.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Initial Inspection

    (f) For first stage turbine disks, P/N 3101520-1 or 3107079-1, 
that have an S/N listed in Table 2 of Honeywell International Inc. 
ASB TPE331-72-A2156, dated December 2, 2008, inspect the disks as 
follows:
    (1) For turbine disks with 4,100 or fewer cycles-since-new (CSN) 
on the effective date of this proposed AD, perform an initial 
fluorescent penetrant inspection (FPI) by using paragraph 3.B.(2) 
through 3.B.(5) of Honeywell International Inc. ASB TPE331-72-A2156, 
dated December 2, 2008, within 4,500 CSN or at the next access, 
whichever occurs first.
    (2) For turbine disks with more than 4,100 CSN on the effective 
date of this proposed AD, perform an initial FPI by using paragraph 
3.B.(2) through 3.B.(5) of Honeywell International Inc. ASB TPE331-
72-A2156, dated December 2, 2008, within 400 cycles-in-service (CIS) 
after the effective date of this proposed AD or at the next access, 
whichever occurs first.
    (3) If the disk passes the FPI inspection, perform a special 
eddy current inspection (ECI) by using paragraph 3.B.(6) of 
Honeywell International Inc. ASB TPE331-72-A2156, dated December 2, 
2008, before returning the disk to service.
    (g) If you find a crack in the disk, remove the disk from 
service.

Repetitive Inspection

    (h) Thereafter, for first stage turbine disks, P/N 3101520-1 or 
3107079-1, that have an S/N listed in Table 2 of Honeywell 
International Inc. ASB TPE331-72-A2156, dated December 2, 2008, 
inspect the disks as follows:
    (1) Perform a repetitive inspection at each scheduled hot 
section inspection, but not to exceed 3,600 hours-since-last 
inspection. Use paragraph 3.B.(2) through 3.B.(5) of Honeywell 
International Inc. ASB TPE331-72-A2156, dated December 2, 2008.
    (2) If the disk passes the FPI inspection, perform a special ECI 
by using paragraph 3.B.(6) of Honeywell International Inc. ASB 
TPE331-72-A2156, dated December 2, 2008, before returning the disk 
to service.
    (i) If you find a crack in the disk, remove the disk from 
service.

Definition

    (j) For the purpose of this AD, ``next access to the first stage 
turbine disk'' is defined as the removal of the second stage turbine 
nozzle from the turbine stator housing.

Alternative Methods of Compliance (AMOCs)

    (k) The Manager, Los Angles Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19.

Related Information

    (l) For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, 
Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 
90712-4137; phone: (562) 627-5246; fax: (562) 627-5210; e-mail: 
[email protected].
    (m) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Web site: http://portal.honeywell.com; or call Honeywell toll 
free at (800) 601-3099

[[Page 48751]]

(U.S./Canada) or (602) 365-3099 (International Direct). You may 
review copies of the referenced service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call (781) 238-7125.

    Issued in Burlington, Massachusetts, on August 1, 2011.
Peter A. White,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-20170 Filed 8-8-11; 8:45 am]
BILLING CODE 4910-13-P