Airworthiness Directives; Honeywell International Inc. TPE331-10 and TPE331-11 Series Turboprop Engines, 48749-48751 [2011-20170]

Download as PDF Federal Register / Vol. 76, No. 153 / Tuesday, August 9, 2011 / Proposed Rules value of a panel) starting on October 12, 2011. Manufacturers shall use this paragraph (c) for the purposes of certifying compliance with the applicable energy conservation standards and for all representations of energy efficiency/energy use starting on January 1, 2015. * * * * * (5) * * * Testing must be performed on a completed panel; foam may not be used for the test sample. * * * * * International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; Web site: https://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. [FR Doc. 2011–20114 Filed 8–8–11; 8:45 am] Examining the AD Docket BILLING CODE 6450–01–P You may examine the AD docket on the Internet at https:// 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: joseph.costa@faa.gov. 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 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 https://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 jlentini on DSK4TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:11 Aug 08, 2011 Jkt 223001 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 https:// 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 48749 turboprop engine. That disk, which has a 20,000-cycle life, failed after accumulating 8,314 cycles-in-service. The fracture revealed a large meltrelated 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. E:\FR\FM\09AUP1.SGM 09AUP1 48750 Federal Register / Vol. 76, No. 153 / Tuesday, August 9, 2011 / Proposed Rules 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. jlentini on DSK4TPTVN1PROD with PROPOSALS 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), VerDate Mar<15>2010 16:11 Aug 08, 2011 Jkt 223001 (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. § 39.13 [Amended] 2. The FAA amends § 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 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: joseph.costa@faa.gov. (m) For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802; Web site: https://portal.honeywell.com; or call Honeywell toll free at (800) 601–3099 E:\FR\FM\09AUP1.SGM 09AUP1 Federal Register / Vol. 76, No. 153 / Tuesday, August 9, 2011 / Proposed Rules (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 DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 573 [Docket No. FDA–2011–F–0549] Lanxess Corp.; Filing of Food Additive Petition (Animal Use); Calcium Formate AGENCY: Food and Drug Administration, HHS. ACTION: Notice of petition. The Food and Drug Administration (FDA) is announcing that Lanxess Corp. has filed a petition proposing that the food additive regulations be amended to provide for the safe use of calcium formate in poultry and swine feed as a nutrient and digestive aid. DATES: Submit either electronic or written comments on the petitioner’s environmental assessment by September 8, 2011. ADDRESSES: Submit electronic comments to: https:// www.regulations.gov. Submit written comments to the Division of Dockets Management (HFA–305), Food and Drug Administration, 5630 Fishers Lane, rm. 1061, Rockville, MD 20852. FOR FURTHER INFORMATION CONTACT: Isabel W. Pocurull, Center for Veterinary Medicine, Food and Drug Administration, 7519 Standish Pl., Rockville, MD 20855, 240–453–6853, email: isabel.pocurull@fda.hhs.gov. SUPPLEMENTARY INFORMATION: Under the Federal Food, Drug, and Cosmetic Act (section 409(b)(5) (21 U.S.C. 348(b)(5)), notice is given that a food additive petition (FAP 2261) has been filed by Lanxess Corp. (Lanxess), 111 RIDC Park West Dr., Pittsburgh, PA 15275–1112. The petition proposes to amend the food additive regulations in part 573 Food Additives Permitted in Feed and Drinking Water of Animals (21 CFR part jlentini on DSK4TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:11 Aug 08, 2011 Jkt 223001 573) to provide for the safe use of calcium formate in poultry and swine feed as a nutrient and digestive aid. The potential environmental impact of this action is being reviewed. To encourage public participation consistent with regulations issued under the National Environmental Policy Act (40 CFR 1501.4(b)), the Agency is placing the environmental assessment submitted with the petition that is the subject of this notice on public display at the Division of Dockets Management (see DATES and ADDRESSES) for public review and comment. Interested persons may submit to the Division of Dockets Management (see ADDRESSES) either electronic or written comments regarding this document. It is only necessary to send one set of comments. It is no longer necessary to send two copies of mailed comments. Identify comments with the docket number found in brackets in the heading of this document. Received comments may be seen in the Division of Dockets Management between 9 a.m. and 4 p.m., Monday through Friday. FDA will also place on public display any amendments to, or comments on, the petitioner’s environmental assessment without further announcement in the Federal Register. If, based on its review, the Agency finds that an environmental impact statement is not required, and this petition results in a regulation, the notice of availability of the Agency’s finding of no significant impact and the evidence supporting that finding will be published with the regulation in the Federal Register in accordance with 21 CFR 25.51(b). Dated: August 3, 2011. Bernadette Dunham, Director, Center for Veterinary Medicine. [FR Doc. 2011–20126 Filed 8–8–11; 8:45 am] BILLING CODE 4160–01–P 48751 Captain of the Port Sector Lake Michigan has determined that to better protect such infrastructure, while also mitigating burdens on waterway users, it is necessary to amend these security zones in our regulations. Specifically, the Coast Guard proposes to reduce the size of an existing security zone, disestablish another security zone, and create three new security zones. DATES: Comments and related materials must reach the Coast Guard on or before September 8, 2011. ADDRESSES: You may submit comments identified by Coast Guard docket number USCG–2011–0489 to the Docket Management Facility at the U.S. Department of Transportation. To avoid duplication, please use only one of the following methods: (1) Online: https:// www.regulations.gov. (2) Mail: Docket Management Facility (M–30), U.S. Department of Transportation, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590– 0001. (3) Hand delivery: Room W12–140 on the Ground Floor of the West Building, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The telephone number is 202–366–9329. (4) Fax: 202–493–2251. FOR FURTHER INFORMATION CONTACT: If you have questions on this proposed rule, call MST1 Brenden Otjen Coast Guard Marine Safety Unit, Willowbrook, IL at (630) 986–2155. If you have questions on viewing or submitting material to the docket, call Renee V. Wright, Program Manager, Docket Operations, telephone 202–366–9826. SUPPLEMENTARY INFORMATION: Public Participation and Request for Comments DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 165 [Docket No. USCG–2011–0489] RIN 1625–AA87 Security Zones; Captain of the Port Lake Michigan Zone We encourage you to participate in this rulemaking by submitting comments and related materials. All comments received will be posted, without change, to https:// www.regulations.gov and will include any personal information you have provided. We have an agreement with the Department of Transportation (DOT) to use the Docket Management Facility. Please see ‘‘Privacy Act’’ paragraph below. AGENCY: Submitting Comments Based on a review of safety and security zones around critical infrastructure in the Chicago area, the If you submit a comment, please include the docket number for this rulemaking (USCG–2011–0489), indicate the specific section of this document to which each comment Coast Guard, DHS. ACTION: Notice of proposed rulemaking. SUMMARY: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\09AUP1.SGM 09AUP1

Agencies

[Federal Register Volume 76, Number 153 (Tuesday, August 9, 2011)]
[Proposed Rules]
[Pages 48749-48751]
From the Federal Register Online via the Government Printing 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).

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

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 https://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: https://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 https://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: joseph.costa@faa.gov.

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 https://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: 
joseph.costa@faa.gov.
    (m) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Web site: https://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