Airworthiness Directives; Honeywell International Inc. Turbofan Engines, 51892-51894 [2012-21010]

Download as PDF 51892 Federal Register / Vol. 77, No. 167 / Tuesday, August 28, 2012 / Rules and Regulations that the prescribed acceptance criteria will not be met—finds that those acceptance criteria will be met, and the Commission or the appropriate director thereafter is able to make the finding that those acceptance criteria are met; and (4) Notwithstanding the pendency of a petition for reconsideration under 10 CFR 2.345, a petition for review under 10 CFR 2.341, or a motion for stay under 10 CFR 2.342, or the filing of a petition under 10 CFR 2.206. * * * * * PART 52—LICENSES, CERTIFICATIONS, AND APPROVALS FOR NUCLEAR POWER PLANTS 3. The authority citation for part 52 continues to read as follows: ■ Authority: Atomic Energy Act secs. 103, 104, 147, 149, 161, 181, 182, 183, 185, 186, 189, 223, 234 (42 U.S.C. 2133, 2201, 2167, 2169, 2232, 2233, 2235, 2236, 2239, 2282); Energy Reorganization Act secs. 201, 202, 206, 211 (42 U.S.C. 5841, 5842, 5846, 5851); Government Paperwork Elimination Act sec. 1704 (44 U.S.C. 3504 note); Energy Policy Act of 2005, Pub. L. 109–58, 119 Stat. 594 (2005). ■ 4. Revise § 52.99 to read as follows: sroberts on DSK5SPTVN1PROD with RULES § 52.99 Inspection during construction; ITAAC schedules and notifications; NRC notices. (a) Licensee schedule for completing inspections, tests, or analyses. The licensee shall submit to the NRC, no later than 1 year after issuance of the combined license or at the start of construction as defined at 10 CFR 50.10(a), whichever is later, its schedule for completing the inspections, tests, or analyses in the ITAAC. The licensee shall submit updates to the ITAAC schedules every 6 months thereafter and, within 1 year of its scheduled date for initial loading of fuel, the licensee shall submit updates to the ITAAC schedule every 30 days until the final notification is provided to the NRC under paragraph (c)(1) of this section. (b) Licensee and applicant conduct of activities subject to ITAAC. With respect to activities subject to an ITAAC, an applicant for a combined license may proceed at its own risk with design and procurement activities, and a licensee may proceed at its own risk with design, procurement, construction, and preoperational activities, even though the NRC may not have found that any one of the prescribed acceptance criteria are met. (c) Licensee notifications—(1) ITAAC closure notification. The licensee shall notify the NRC that prescribed inspections, tests, and analyses have been performed and that the prescribed VerDate Mar<15>2010 16:13 Aug 27, 2012 Jkt 226001 acceptance criteria are met. The notification must contain sufficient information to demonstrate that the prescribed inspections, tests, and analyses have been performed and that the prescribed acceptance criteria are met. (2) ITAAC post-closure notifications. Following the licensee’s ITAAC closure notifications under paragraph (c)(1) of this section until the Commission makes the finding under 10 CFR 52.103(g), the licensee shall notify the NRC, in a timely manner, of new information that materially alters the basis for determining that either inspections, tests, or analyses were performed as required, or that acceptance criteria are met. The notification must contain sufficient information to demonstrate that, notwithstanding the new information, the prescribed inspections, tests, or analyses have been performed as required, and the prescribed acceptance criteria are met. (3) Uncompleted ITAAC notification. If the licensee has not provided, by the date 225 days before the scheduled date for initial loading of fuel, the notification required by paragraph (c)(1) of this section for all ITAAC, then the licensee shall notify the NRC that the prescribed inspections, tests, or analyses for all uncompleted ITAAC will be performed and that the prescribed acceptance criteria will be met prior to operation. The notification must be provided no later than the date 225 days before the scheduled date for initial loading of fuel, and must provide sufficient information to demonstrate that the prescribed inspections, tests, or analyses will be performed and the prescribed acceptance criteria for the uncompleted ITAAC will be met, including, but not limited to, a description of the specific procedures and analytical methods to be used for performing the prescribed inspections, tests, and analyses and determining that the prescribed acceptance criteria are met. (4) All ITAAC complete notification. The licensee shall notify the NRC that all ITAAC are complete. (d) Licensee determination of noncompliance with ITAAC. (1) In the event that an activity is subject to an ITAAC derived from a referenced standard design certification and the licensee has not demonstrated that the prescribed acceptance criteria are met, the licensee may take corrective actions to successfully complete that ITAAC or request an exemption from the standard design certification ITAAC, as applicable. A request for an exemption must also be accompanied by a request for a PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 license amendment under 10 CFR 52.98(f). (2) In the event that an activity is subject to an ITAAC not derived from a referenced standard design certification and the licensee has not demonstrated that the prescribed acceptance criteria are met, the licensee may take corrective actions to successfully complete that ITAAC or request a license amendment under 10 CFR 52.98(f). (e) NRC inspection, publication of notices, and availability of licensee notifications. The NRC shall ensure that the prescribed inspections, tests, and analyses in the ITAAC are performed. (1) At appropriate intervals until the last date for submission of requests for hearing under 10 CFR 52.103(a), the NRC shall publish notices in the Federal Register of the NRC staff’s determination of the successful completion of inspections, tests, and analyses. (2) The NRC shall make publicly available the licensee notifications under paragraph (c) of this section. The NRC shall, no later than the date of publication of the notice of intended operation required by 10 CFR 52.103(a), make publicly available those licensee notifications under paragraph (c) of this section that have been submitted to the NRC at least seven (7) days before that notice. Dated at Rockville, Maryland, this 22nd day of August, 2012. For the Nuclear Regulatory Commission. Annette L. Vietti-Cook, Secretary of the Commission. [FR Doc. 2012–21207 Filed 8–27–12; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1045; Directorate Identifier 2011–NE–32–AD; Amendment 39– 17168; AD 2012–17–05] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. models TFE731–4, –4R, –5, –5R, –5AR, and –5BR series turbofan engines. This AD was prompted by a report of a rim/web separation of a first stage low-pressure SUMMARY: E:\FR\FM\28AUR1.SGM 28AUR1 Federal Register / Vol. 77, No. 167 / Tuesday, August 28, 2012 / Rules and Regulations turbine (LPT1) rotor assembly. This AD requires replacing affected LPT1 rotor assemblies with assemblies eligible for installation. We are issuing this AD to prevent uncontained disk separation, engine failure, and damage to the airplane. DATES: This AD is effective October 2, 2012. 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 phone: 800–601– 3099 (U.S./Canada) or 602–365–3099 (International Direct). You may view this 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. ADDRESSES: 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: sroberts on DSK5SPTVN1PROD with RULES 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 February 21, 2012 (77 FR 9868). That NPRM proposed to require replacing affected LPT1 rotor assemblies with LPT1 rotor assemblies eligible for installation. Comments We gave the public the opportunity to participate in developing this AD. The following presents the one comment VerDate Mar<15>2010 16:13 Aug 27, 2012 Jkt 226001 received on the proposal and the FAA’s response to the comment. Request To Clarify Definition Paragraph One commenter requested we change a term in paragraph (h) of the proposed AD. The commenter requested that ‘‘tie rod’’ be changed to ‘‘tie shaft.’’ The commenter said that making this change would allow a level of disassembly to access the inlet total temperature harness and other hardware without affecting the low-pressure turbine (LPT) module. We do not agree. Mandating access to the LPT module in the AD and suspect disks when the tie rod is unstretched is consistent in achieving AD compliance sooner for the Falcon 20 and CASA 101 airplanes. LPT disk separations in these airplanes have been determined to be higher risk than for engines in other applications. We did not change the AD. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 9868, February 21, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 9868, February 21, 2012). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 1,550 engines installed on airplanes of U.S. registry. We also estimate that it will take about 1 work-hour per engine to perform the actions at next access and 165 work-hours per unscheduled engine disassembly, and that the average labor rate is $85 per work-hour. Replacement parts will cost about $175,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $35,195,488 per year. 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. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 51893 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 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): ■ 2012–17–05 Honeywell International Inc. (formerly AlliedSignal Inc., formerly Garret Turbine Engine Company): Amendment 39–17168; Docket No. FAA–2011–1045; Directorate Identifier 2011–NE–32–AD. E:\FR\FM\28AUR1.SGM 28AUR1 51894 Federal Register / Vol. 77, No. 167 / Tuesday, August 28, 2012 / Rules and Regulations (a) Effective Date This AD is effective October 2, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Honeywell International Inc.: (1) Model TFE731–5 series turbofan engines, with a first stage low-pressure turbine (LPT1) rotor assembly, part number (P/N) 3075184–2, 3075184–3, or 3075184–4, installed, and (2) Models TFE731–5AR and –5BR series turbofan engines, with a first stage LPT1 rotor assembly, P/N 3075447–1, 3075447–2, 3075447–4, 3075713–1, 3075713–2, 3075713–3, or 3074748–5, installed, and (3) Models TFE731–4, –4R, –5AR, –5BR, and –5R series turbofan engines, with an LPT1 rotor assembly, P/N 3074748–4, 3074748–5, 3075447–1, 3075447–2, 3075447–4, 3075713–1, 3075713–2, or 3075713–3, installed. (d) Unsafe Condition This AD was prompted by a report of a rim/web separation of an LPT1 rotor assembly. We are issuing this AD to prevent uncontained disk separation, engine failure, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (f) Engines Installed in Dassault-Aviation Falcon 20 and Construcciones Aeronauticas, S.A. (CASA) 101 Airplanes (1) Remove the LPT1 rotor assembly at the next access to the LPT1 rotor assembly or at the next major periodic inspection, not to exceed 2,600 hours-in-service since last major periodic inspection, or 8 years after the effective date of this AD, whichever occurs first. (2) Install an LPT1 rotor assembly that is eligible for installation. sroberts on DSK5SPTVN1PROD with RULES (g) Engines Not Installed in DassaultAviation Falcon 20 or CASA 101 Airplanes (1) Remove the LPT1 rotor assembly at the next core zone inspection, not to exceed 5,100 hours-in-service since last core zone inspection, or at the next time the LPT1 rotor disc is removed for cause, or 8 years after the effective date of this AD, whichever occurs first. (2) Install an LPT1 rotor assembly that is eligible for installation. (h) Definitions (1) For the purpose of this AD, ‘‘next access’’ is when the low-pressure tie rod is unstretched. (2) For the purpose of this AD, an LPT1 rotor assembly ‘‘eligible for installation’’ is an LPT1 rotor assembly not having a P/N listed in this AD. (i) Installation Prohibition After the effective date of this AD, do not install any LPT1 rotor assembly listed by P/ N in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, into any engine. VerDate Mar<15>2010 16:13 Aug 27, 2012 Jkt 226001 (j) Alternative Methods of Compliance (AMOCs) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to request an AMOC. (k) 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) Honeywell International Inc. Service Bulletin (SB) No. TFE731–72–3768; SB No. TFE731–72–3769; and SB No. TFE731–72– 3770, pertain to the subject of this AD. (3) 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 phone: 800– 601–3099 (U.S./Canada) or 602–365–3099 (International Direct). (l) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on August 14, 2012. Robert G. Mann, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–21010 Filed 8–27–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30857; Amdt. No. 3492] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 This rule is effective August 28, 2012. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 28, 2012. ADDRESSES: Availability of matters incorporated by reference in the amendment is as follows: For Examination— 1. FAA Rules Docket, FAA Headquarters Building, 800 Independence Avenue SW., Washington, DC 20591; 2. The FAA Regional Office of the region in which the affected airport is located; 3. The National Flight Procedures Office, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 or, 4. 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/ code_of_federal_regulations/ ibr_locations.html. Availability—All SIAPs and Takeoff Minimums and ODPs are available online free of charge. Visit https:// www.nfdc.faa.gov to register. Additionally, individual SIAP and Takeoff Minimums and ODP copies may be obtained from: 1. FAA Public Inquiry Center (APA– 200), FAA Headquarters Building, 800 Independence Avenue SW., Washington, DC 20591; or 2. The FAA Regional Office of the region in which the affected airport is located. DATES: FOR FURTHER INFORMATION CONTACT: This rule establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under SUMMARY: instrument flight rules at the affected airports. Richard A. Dunham III, Flight Procedure Standards Branch (AFS–420), Flight Technologies and Programs Divisions, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082, Oklahoma City, OK 73125) Telephone: (405) 954–4164. SUPPLEMENTARY INFORMATION: This rule amends Title 14 of the Code of Federal Regulations, Part 97 (14 CFR part 97), by establishing, amending, suspending, or revoking SIAPS, Takeoff Minimums and/or ODPS. The complete regulators description of each SIAP and its associated Takeoff Minimums or ODP E:\FR\FM\28AUR1.SGM 28AUR1

Agencies

[Federal Register Volume 77, Number 167 (Tuesday, August 28, 2012)]
[Rules and Regulations]
[Pages 51892-51894]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-21010]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1045; Directorate Identifier 2011-NE-32-AD; 
Amendment 39-17168; AD 2012-17-05]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honeywell International Inc. models TFE731-4, -4R, -5, -5R, -5AR, and -
5BR series turbofan engines. This AD was prompted by a report of a rim/
web separation of a first stage low-pressure

[[Page 51893]]

turbine (LPT1) rotor assembly. This AD requires replacing affected LPT1 
rotor assemblies with assemblies eligible for installation. We are 
issuing this AD to prevent uncontained disk separation, engine failure, 
and damage to the airplane.

DATES: This AD is effective October 2, 2012.

ADDRESSES: 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 phone: 800-601-3099 (U.S./Canada) or 602-365-3099 
(International Direct). You may view this 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.

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 February 21, 2012 (77 FR 
9868). That NPRM proposed to require replacing affected LPT1 rotor 
assemblies with LPT1 rotor assemblies eligible for installation.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the one comment received on the 
proposal and the FAA's response to the comment.

Request To Clarify Definition Paragraph

    One commenter requested we change a term in paragraph (h) of the 
proposed AD. The commenter requested that ``tie rod'' be changed to 
``tie shaft.'' The commenter said that making this change would allow a 
level of disassembly to access the inlet total temperature harness and 
other hardware without affecting the low-pressure turbine (LPT) module.
    We do not agree. Mandating access to the LPT module in the AD and 
suspect disks when the tie rod is unstretched is consistent in 
achieving AD compliance sooner for the Falcon 20 and CASA 101 
airplanes. LPT disk separations in these airplanes have been determined 
to be higher risk than for engines in other applications. We did not 
change the AD.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed except for minor editorial changes. We have determined 
that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 9868, February 21, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 9868, February 21, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 1,550 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
work-hour per engine to perform the actions at next access and 165 
work-hours per unscheduled engine disassembly, and that the average 
labor rate is $85 per work-hour. Replacement parts will cost about 
$175,000 per engine. Based on these figures, we estimate the total cost 
of the AD to U.S. operators to be $35,195,488 per year.

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):

2012-17-05 Honeywell International Inc. (formerly AlliedSignal Inc., 
formerly Garret Turbine Engine Company): Amendment 39-17168; Docket 
No. FAA-2011-1045; Directorate Identifier 2011-NE-32-AD.

[[Page 51894]]

(a) Effective Date

    This AD is effective October 2, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc.:
    (1) Model TFE731-5 series turbofan engines, with a first stage 
low-pressure turbine (LPT1) rotor assembly, part number (P/N) 
3075184-2, 3075184-3, or 3075184-4, installed, and
    (2) Models TFE731-5AR and -5BR series turbofan engines, with a 
first stage LPT1 rotor assembly, P/N 3075447-1, 3075447-2, 3075447-
4, 3075713-1, 3075713-2, 3075713-3, or 3074748-5, installed, and
    (3) Models TFE731-4, -4R, -5AR, -5BR, and -5R series turbofan 
engines, with an LPT1 rotor assembly, P/N 3074748-4, 3074748-5, 
3075447-1, 3075447-2, 3075447-4, 3075713-1, 3075713-2, or 3075713-3, 
installed.

(d) Unsafe Condition

    This AD was prompted by a report of a rim/web separation of an 
LPT1 rotor assembly. We are issuing this AD to prevent uncontained 
disk separation, engine failure, and damage to the airplane.

(e) Compliance

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

(f) Engines Installed in Dassault-Aviation Falcon 20 and Construcciones 
Aeronauticas, S.A. (CASA) 101 Airplanes

    (1) Remove the LPT1 rotor assembly at the next access to the 
LPT1 rotor assembly or at the next major periodic inspection, not to 
exceed 2,600 hours-in-service since last major periodic inspection, 
or 8 years after the effective date of this AD, whichever occurs 
first.
    (2) Install an LPT1 rotor assembly that is eligible for 
installation.

(g) Engines Not Installed in Dassault-Aviation Falcon 20 or CASA 101 
Airplanes

    (1) Remove the LPT1 rotor assembly at the next core zone 
inspection, not to exceed 5,100 hours-in-service since last core 
zone inspection, or at the next time the LPT1 rotor disc is removed 
for cause, or 8 years after the effective date of this AD, whichever 
occurs first.
    (2) Install an LPT1 rotor assembly that is eligible for 
installation.

(h) Definitions

    (1) For the purpose of this AD, ``next access'' is when the low-
pressure tie rod is unstretched.
    (2) For the purpose of this AD, an LPT1 rotor assembly 
``eligible for installation'' is an LPT1 rotor assembly not having a 
P/N listed in this AD.

(i) Installation Prohibition

    After the effective date of this AD, do not install any LPT1 
rotor assembly listed by P/N in paragraphs (c)(1), (c)(2), and 
(c)(3) of this AD, into any engine.

(j) Alternative Methods of Compliance (AMOCs)

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

(k) 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) Honeywell International Inc. Service Bulletin (SB) No. 
TFE731-72-3768; SB No. TFE731-72-3769; and SB No. TFE731-72-3770, 
pertain to the subject of this AD.
    (3) 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 phone: 800-601-3099 (U.S./Canada) or 602-365-3099 
(International Direct).

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on August 14, 2012.
Robert G. Mann,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-21010 Filed 8-27-12; 8:45 am]
BILLING CODE 4910-13-P

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