Airworthiness Directives; Honeywell International Inc. TPE331-10 and TPE331-11 Series Turboprop Engines, 6669-6671 [2012-2894]

Download as PDF Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Rules and Regulations 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 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. 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: emcdonald on DSK29S0YB1PROD with RULES ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2012–02–04 Rolls-Royce plc: Amendment 39–16927; Docket No. FAA–2012–0004; Directorate Identifier 2012–NE–01–AD. VerDate Mar<15>2010 15:13 Feb 08, 2012 Jkt 226001 (a) Effective Date This airworthiness directive (AD) becomes effective February 24, 2012. (2) Refer to European Aviation Safety Agency AD 2011–0243, dated December 20, 2011, for related information. (b) Affected ADs None. (h) Material Incorporated by Reference (1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51: (2) Rolls-Royce plc Alert Service Bulletin No. RB.211–73–AG797, dated October 26, 2011. (3) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011–44–1332– 242424; fax: 011–44–1332–245418 or email: https://www.rolls-royce.com/contact/ civil_team.jsp. (4) You may review copies of the service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call (781) 238–7125. (5) You may also review copies of the service information incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (c) Applicability This AD applies to Rolls-Royce plc RB211– Trent 553–61, RB211–Trent 553A2–61, RB211–Trent 556–61, RB211–Trent 556A2– 61, RB211–Trent 556B–61, RB211–Trent 556B2–61, RB211–Trent 560–61, and RB211– Trent 560A2–61 turbofan engines that have not complied with Rolls-Royce plc Service Bulletin No. RB.211–73–G723, and that have any of the following fuel tube part numbers installed: (1) FW57605. (2) FW17689. (3) FW57604. (4) FK30710. (5) FW57578. (6) FK30713. (d) Reason This AD was prompted by reports of wear found between the securing clips and the low-pressure (LP) fuel tube outer surface, which reduces the fuel tube wall thickness, leading to fracture of the fuel tube and consequent fuel leak. We are issuing this AD to prevent engine fuel leaks, which could result in risk to the airplane. (e) Actions and Compliance Unless already done, do the following onetime actions within 1,600 flight hours after the effective date of this AD. (1) Visually inspect the fuel tube clips holding the LP fuel tube run from the LP fuel pump to the fuel-oil-heat exchanger, and the clips holding the LP fuel tube run from the LP filter to the high-pressure (HP) fuel pump, for evidence of damage or wear and replace as necessary. Do this in accordance with paragraphs 3.A(4)(a) through 3.A(4)(c) of Rolls-Royce plc Alert Service Bulletin No. RB.211–73–AG797, dated October 26, 2011. (2) Clean and dry the LP fuel tube run from the LP fuel pump to the fuel-oil-heat exchanger, and the LP fuel tube run from the LP filter to the HP fuel pump. (i) Visually inspect for evidence of damage, wear near the clip locations, and for fuel leakage. (ii) Reject the tube and replace it if evidence of fuel leakage or contact frettage to a depth of greater than 0.1 mm (0.004 in.) on the outer surface of a bend, or 0.2 mm (0.008 in.) in any other area, is evident. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. PART 39—AIRWORTHINESS DIRECTIVES 6669 (g) Related Information (1) For more information about this AD, contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: alan.strom@faa.gov; phone: (781) 238– 7143; fax: (781) 238–7199. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Issued in Burlington, Massachusetts, on January 19, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–2895 Filed 2–8–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0789; Directorate Identifier 2011–NE–04–AD; Amendment 39– 16929; AD 2012–02–06] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. TPE331–10 and TPE331–11 Series Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD was prompted by a report of an uncontained failure of a first stage turbine disk that had a metallurgical defect. This AD requires inspecting certain serial number (S/N) first stage turbine disks, part number (P/N) 3101520–1 and P/N SUMMARY: E:\FR\FM\09FER1.SGM 09FER1 6670 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Rules and Regulations 3107079–1. We are issuing this AD to prevent uncontained failure of the first stage turbine disk and damage to the airplane. DATES: This AD is effective March 15, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 15, 2012. ADDRESSES: For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; phone: (800) 601–3099 (toll free in U.S. or Canada) or (602) 365–3099 (International direct); Web site: https://portal.honeywell.com. 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. emcdonald on DSK29S0YB1PROD with RULES 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: (800) 647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION 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; email: joseph.costa@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on August 9, 2011 (76 FR 48749). That NPRM proposed to require inspecting certain S/N first stage turbine disks, P/N 3101520–1 and P/N 3107079–1. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM. VerDate Mar<15>2010 15:13 Feb 08, 2012 Jkt 226001 Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD affects 90 engines installed on airplanes of U.S. registry. We also estimate that it will take about 20 work-hours per engine to perform these actions, and that the average labor rate is $85 per work-hour. Required parts cost about $19,000 per engine. We estimate that one disk will fail the initial inspection and that repetitive inspections will be performed on 89 engines. We estimate that one engine will fail the repetitive inspections and that further repetitive inspections will be performed on 88 engines. We estimate that an additional one disk will fail those repetitive inspections before retirement. Based on these figures, we estimate the total cost of the 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 This AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (2) Is not a ‘‘significant rule’’ under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): ■ 2012–02–06 Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39–16929; Docket No. FAA–2011–0789; Directorate Identifier 2011–NE–04–AD. (a) Effective Date This AD is effective March 15, 2012. (b) Affected ADs None. (c) Applicability 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. (d) Unsafe Condition 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. (e) Compliance Comply with this AD within the compliance times specified, unless already done. E:\FR\FM\09FER1.SGM 09FER1 Federal Register / Vol. 77, No. 27 / Thursday, February 9, 2012 / Rules and Regulations (f) Initial Inspection (1) 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: (i) For turbine disks with 4,100 or fewer cycles-since-new (CSN) on the effective date of this 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. (ii) For turbine disks with more than 4,100 CSN on the effective date of this 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-inservice (CIS) after the effective date of this AD or at the next access, whichever occurs first. (iii) 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. (2) If you find a crack in the disk, remove the disk from service. (g) Repetitive Inspection (1) 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: (i) 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. (ii) 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. (2) If you find a crack in the disk, remove the disk from service. (2) Contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034–2802; phone: (800) 601–3099 (toll free in U.S. or Canada) or (602) 365–3099 (International direct); Web site: https:// portal.honeywell.com; for a copy of the service information referenced in this AD. (k) Material Incorporated by Reference (1) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51: (i) Honeywell International Inc., Alert Service Bulletin TPE331–72–A2156, December 2, 2008. (2) 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 (U.S./Canada) or (602) 365–3099 (International Direct). (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Burlington, Massachusetts, on January 12, 2012. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–2894 Filed 2–8–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 (i) Alternative Methods of Compliance (AMOCs) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. emcdonald on DSK29S0YB1PROD with RULES (h) Definition 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. RIN 2120–AA64 (j) Related Information (1) 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; email: joseph.costa@faa.gov. VerDate Mar<15>2010 15:13 Feb 08, 2012 Jkt 226001 [Docket No. FAA–2011–0547; Directorate Identifier 2011–NE–13–AD; Amendment 39– 16947; AD 2012–03–06] Airworthiness Directives; Superior Air Parts, Lycoming Engines (Formerly Textron Lycoming), and Continental Motors, Inc., Fuel-Injected Reciprocating Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Superior Air Parts and Lycoming Engines fuel-injected reciprocating engines. That AD currently requires removing AVStar Fuel Systems, Inc. (AFS) fuel servos installed after May 20, 2010, if the servo contained an AFS diaphragm, part number (P/N) AV2541801 or P/N AV2541803, from certain production lots. This AD expands the applicability, and changes the compliance interval for all affected Superior Air Parts, Lycoming Engines, and Continental Motors, Inc., fuelinjected reciprocating engines. This AD was prompted by an accident involving a Piper PA32R–301 airplane, and by the discovery of additional engines being affected by the unsafe condition since we issued the existing AD. We are issuing this AD to prevent an in-flight engine shutdown due to a failed fuel servo diaphragm, and damage to the airplane. This AD is effective February 24, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 16, 2011 (76 FR 45655, August 1, 2011). We must receive any comments on this AD by March 26, 2012. 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: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact AVStar Fuel Systems, Inc., 1365 Park Lane South, Jupiter, FL 33458; phone: (561) 575–1560; Web site: www.avstardirect.com. 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. DATES: Examining the AD Docket We are superseding an existing airworthiness directive (AD) for SUMMARY: 6671 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 E:\FR\FM\09FER1.SGM 09FER1

Agencies

[Federal Register Volume 77, Number 27 (Thursday, February 9, 2012)]
[Rules and Regulations]
[Pages 6669-6671]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-2894]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0789; Directorate Identifier 2011-NE-04-AD; 
Amendment 39-16929; AD 2012-02-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD was prompted by a report of an 
uncontained failure of a first stage turbine disk that had a 
metallurgical defect. This AD requires inspecting certain serial number 
(S/N) first stage turbine disks, part number (P/N) 3101520-1 and P/N

[[Page 6670]]

3107079-1. We are issuing this AD to prevent uncontained failure of the 
first stage turbine disk and damage to the airplane.

DATES: This AD is effective March 15, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 15, 
2012.

ADDRESSES: For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; phone: (800) 601-3099 (toll free in U.S. or Canada) or (602) 365-
3099 (International direct); Web site: https://portal.honeywell.com. 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: (800) 647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION 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; email: joseph.costa@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on August 9, 2011 (76 FR 
48749). That NPRM proposed to require inspecting certain S/N first 
stage turbine disks, P/N 3101520-1 and P/N 3107079-1.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2012-02-06 Honeywell International Inc. (formerly AlliedSignal Inc., 
Garrett Engine Division; Garrett Turbine Engine Company; and 
AiResearch Manufacturing Company of Arizona): Amendment 39-16929; 
Docket No. FAA-2011-0789; Directorate Identifier 2011-NE-04-AD.

(a) Effective Date

    This AD is effective March 15, 2012.

(b) Affected ADs

    None.

(c) Applicability

    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.

(d) Unsafe Condition

    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.

(e) Compliance

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

[[Page 6671]]

(f) Initial Inspection

    (1) 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:
    (i) For turbine disks with 4,100 or fewer cycles-since-new (CSN) 
on the effective date of this 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.
    (ii) For turbine disks with more than 4,100 CSN on the effective 
date of this 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 AD or at the next access, whichever occurs 
first.
    (iii) 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.
    (2) If you find a crack in the disk, remove the disk from 
service.

(g) Repetitive Inspection

    (1) 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:
    (i) 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.
    (ii) 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.
    (2) If you find a crack in the disk, remove the disk from 
service.

(h) Definition

    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.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Los Angeles Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 
to make your request.

(j) Related Information

    (1) 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; email: 
joseph.costa@faa.gov.
    (2) Contact Honeywell International Inc., 111 S. 34th Street, 
Phoenix, AZ 85034-2802; phone: (800) 601-3099 (toll free in U.S. or 
Canada) or (602) 365-3099 (International direct); Web site: https://portal.honeywell.com; for a copy of the service information 
referenced in this AD.

(k) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) of the following service information under 5 U.S.C. 
552(a) and 1 CFR part 51:
    (i) Honeywell International Inc., Alert Service Bulletin TPE331-
72-A2156, December 2, 2008.
    (2) 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 (U.S./Canada) or (602) 365-3099 
(International Direct).
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call (202) 741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Burlington, Massachusetts, on January 12, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-2894 Filed 2-8-12; 8:45 am]
BILLING CODE 4910-13-P

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