81 FR 19516 - Airworthiness Directives; International Aero Engines AG Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 65 (April 5, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 65 (April 5, 2016)
| Page Range | 19516-19518 | |
| FR Document | 2016-07579 |
[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)] [Proposed Rules] [Pages 19516-19518] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07579] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-4123; Directorate Identifier 2016-NE-06-AD] RIN 2120-AA64 Airworthiness Directives; International Aero Engines AG Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2525- D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines. This proposed AD was prompted by the fracture of the high-pressure turbine (HPT) stage 2 hub during flight, which resulted in an in-flight shutdown (IFSD), undercowl fire, and smoke in the cabin. This proposed AD would require inspecting the HPT stage 1 hub and HPT stage 2 hub, and, if necessary, their replacement with parts that are eligible for installation. We are proposing this AD to prevent failure of the HPT stage 1 or HPT stage 2 hubs, which could result in uncontained HPT blade release, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06118; phone: 860-368-3700; fax: 860-368-4600; email: [email protected]; Internet: https://www.iaeworld.com. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For [[Page 19517]] information on the availability of this material at the FAA, call 781- 238-7125. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 4123 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: Brian Kierstead, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781- 238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-4123; Directorate Identifier 2016-NE-06-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We received a report of an engine IFSD and subsequent undercowl fire on an IAE V2527-A5 turbofan engine during a revenue flight of an Airbus A320 airplane in September 2014. The subsequent investigation of this event determined that it was caused by a manufacturing defect in the HPT stage 2 hub that resulted in fracture and failure of the HPT stage 2 hub. The event involved release of a fir tree lug and two HPT stage 2 blades. IAE also identified a similar manufacturing defect on the HPT stage 1 hub. This condition, if not corrected, could result in uncontained HPT blade release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed IAE Non-Modification Service Bulletin (NMSB) No. V2500- ENG-72-0661, Revision No. 1, dated February 5, 2016. The NMSB describes procedures for inspecting the HPT stage 1 and stage 2 hubs. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. 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 inspecting the engine HPT stage 1 hub and HPT stage 2 hub, and, if necessary, their replacement with parts eligible for installation. Costs of Compliance We estimate that this proposed AD affects 668 engines with 947 hubs installed on airplanes of U.S. registry. Some of the 668 engines have two hubs installed. We estimate that it would take about 8 hours per hub to perform the piece-part inspection. The average labor rate is $85 per hour. We estimate that 568 hubs will require replacement. We estimate the pro-rated cost to replace an HPT stage 1 hub to be $50,271 and the pro-rated cost to replace an HPT stage 2 hub to be $40,063. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $26,298,816. 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 to the extent that it justifies making a regulatory distinction, 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 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): International Aero Engines AG: Docket No. FAA-2016-4123; Directorate Identifier 2016-NE-06-AD. (a) Comments Due Date We must receive comments by June 6, 2016. (b) Affected ADs None. (c) Applicability This AD applies to International Aero Engines AG (IAE) V2522-A5, V2524-A5, [[Page 19518]] V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5, engines with either of the following installed: (1) High-pressure turbine (HPT) stage 1 hub, part number (P/N) 2A5001, with a serial number (S/N) listed in Table 1, Appendix A, of IAE Non-Modification Service Bulletin (NMSB) No. V2500-ENG-72-0661, Revision 1, dated February 5, 2016; or (2) HPT stage 2 hub, P/N 2A4802, with an S/N listed in Table 2, Appendix A, of IAE NMSB No. V2500-ENG-72-0661, Revision 1, dated February 5, 2016. (d) Unsafe Condition This AD was prompted by the fracture of the HPT stage 2 hub during flight, which resulted in an in-flight shutdown, undercowl fire, and smoke in the cabin. We are issuing this AD to prevent failure of the HPT stage 1 or HPT stage 2 hubs, which could result in uncontained HPT blade release, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Inspect the HPT stage 1 hub, P/N 2A5001, and HPT stage 2 hub, P/N 2A4802, at the next shop visit or as follows, whichever comes first: (i) For hubs with 0 to 7,000 CSN, before accumulating 13,000 CSN; (ii) For hubs with 7,001 to 11,000 CSN, within 6,000 cycles from the effective date of this AD or before accumulating 15,000 CSN, whichever occurs first; (iii) For hubs with 11,001 to 15,500 CSN, within 4,000 cycles from the effective date of this AD or before accumulating 17,000 CSN, whichever occurs first; (iv) For hubs with 15,501 CSN or greater, within 1,500 cycles from the effective date of this AD. (2) Use Accomplishment Instructions, paragraphs 2.A., 2.C., and 2.D., of IAE NMSB No. V2500-ENG-72-0661, Revision 1, dated February 5, 2016, to inspect the HPT stage 1 hub, P/N 2A5001. (3) Use Accomplishment Instructions, paragraphs 2.E., 2.G., and 2H., of IAE NMSB No. V2500-ENG-72-0661, to inspect the HPT stage 2 hub, P/N 2A4802. (4) Remove from service any HPT stage 1 hub, P/N 2A5001, or HPT stage 2 hub, P/N 2A4802, that fail the inspections required by paragraphs (e)(2) and (e)(3) of this AD, and replace with a part that is eligible for installation. (f) Definition For the purpose of this AD, a ``shop visit'' is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (h) Related Information (1) For more information about this AD, contact Brian Kierstead, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781-238-7199; email: [email protected]. (2) For service information identified in this proposed AD, contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06118; phone: 860-368-3700; fax: 860-368-4600; email: [email protected]; Internet: https://www.iaeworld.com. (3) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Issued in Burlington, Massachusetts, on March 24, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-07579 Filed 4-4-16; 8:45 am] BILLING CODE 4910-13-P
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PART 39—AIRWORTHINESS send your request to your principal inspector DEPARTMENT OF TRANSPORTATION
DIRECTIVES or local Flight Standards District Office, as
appropriate. If sending information directly Federal Aviation Administration
■ 1. The authority citation for part 39 to the manager of the ACO, send it to the
continues to read as follows: attention of the person identified in 14 CFR Part 39
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraph (i)(1) of this AD. Information may
[Docket No. FAA–2016–4123; Directorate
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Identifier 2016–NE–06–AD]
§ 39.13 [Amended] Requests@faa.gov.
■ 2. The FAA amends § 39.13 by adding (2) Before using any approved AMOC, RIN 2120–AA64
the following new airworthiness notify your appropriate principal inspector,
or lacking a principal inspector, the manager Airworthiness Directives; International
directive (AD):
of the local flight standards district office/ Aero Engines AG Turbofan Engines
The Boeing Company: Docket No. FAA– certificate holding district office.
2016–5041; Directorate Identifier 2015– AGENCY: Federal Aviation
(3) An AMOC that provides an acceptable Administration (FAA), DOT.
NM–102–AD.
level of safety may be used for any repair,
(a) Comments Due Date ACTION: Notice of proposed rulemaking
modification, or alteration required by this
AD if it is approved by the Boeing (NPRM).
We must receive comments by May 20,
2016. Commercial Airplanes Organization SUMMARY: We propose to adopt a new
Designation Authorization (ODA) that has airworthiness directive (AD) for certain
(b) Affected ADs
been authorized by the Manager, Seattle International Aero Engines AG (IAE)
None. ACO, to make those findings. To be V2522–A5, V2524–A5, V2525–D5,
(c) Applicability approved, the repair method, modification V2527–A5, V2527E–A5, V2527M–A5,
This AD applies to The Boeing Company deviation, or alteration deviation must meet
V2528–D5, V2530–A5, and V2533–A5
Model 747–8 and 747–8F series airplanes, the certification basis of the airplane, and the
turbofan engines. This proposed AD was
certified in any category, as identified in approval must specifically refer to this AD.
prompted by the fracture of the high-
Boeing Alert Service Bulletin 747–57A2348, (4) For service information that contains
pressure turbine (HPT) stage 2 hub
dated June 12, 2015. steps that are labeled as Required for
during flight, which resulted in an in-
Compliance (RC), the provisions of
(d) Subject flight shutdown (IFSD), undercowl fire,
paragraphs (h)(4)(i) and (h)(4)(ii) of this AD
Air Transport Association (ATA) of apply.
and smoke in the cabin. This proposed
America Code 57, Wings.
(i) The steps labeled as RC, including
AD would require inspecting the HPT
(e) Unsafe Condition substeps under an RC step and any figures
stage 1 hub and HPT stage 2 hub, and,
identified in an RC step, must be done to if necessary, their replacement with
This AD was prompted by a report that parts that are eligible for installation.
static strength analysis has shown that the comply with the AD. An AMOC is required
aluminum transmission aft bearing plate for any deviations to RC steps, including We are proposing this AD to prevent
assemblies have inadequate structural substeps and identified figures. failure of the HPT stage 1 or HPT stage
strength for one or more of the required load (ii) Steps not labeled as RC may be 2 hubs, which could result in
cases, including cases for drive system jam, deviated from using accepted methods in uncontained HPT blade release, damage
flap skew, and structural damage tolerance. accordance with the operator’s maintenance to the engine, and damage to the
Inadequate structural strength can result in or inspection program without obtaining airplane.
damage to the transmission aft bearing plate
approval of an AMOC, provided the RC steps, DATES: We must receive comments on
assemblies. We are issuing this AD to prevent
including substeps and identified figures, can this proposed AD by June 6, 2016.
inadequate structural strength of
transmission aft bearing plate assemblies. still be done as specified, and the airplane ADDRESSES: You may send comments,
This condition could result in damaged can be put back in an airworthy condition. using the procedures found in 14 CFR
transmission aft bearing plate assemblies, (i) Related Information 11.43 and 11.45, by any of the following
which could result in incorrect operation and methods:
departure of the flap from the airplane and (1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
• Federal eRulemaking Portal: Go to
consequent loss of controllability of the
airplane. Airframe Branch, ANM–120S, FAA, Seattle
http://www.regulations.gov. Follow the
ACO, 1601 Lind Avenue SW., Renton, WA instructions for submitting comments.
(f) Compliance
98057–3356; phone: 425–917–6432; fax: 425– • Fax: 202–493–2251.
Comply with this AD within the 917–6590; email: bill.ashforth@faa.gov.
• Mail: U.S. Department of
compliance times specified, unless already (2) For service information identified in Transportation, Docket Operations, M–
done. 30, West Building Ground Floor, Room
this AD, contact Boeing Commercial
(g) Replacement Airplanes, Attention: Data & Services W12–140, 1200 New Jersey Avenue SE.,
Management, P.O. Box 3707, MC 2H–65, Washington, DC 20590.
Within 48 months after the effective date
Seattle, WA 98124–2207; telephone 206– • Hand Delivery: Deliver to Mail
of this AD: Remove aluminum transmission
aft bearing plate assemblies from the flap 544–5000, extension 1; fax 206–766–5680; address above between 9 a.m. and 5
track and install new titanium transmission Internet https://www.myboeingfleet.com. For p.m., Monday through Friday, except
aft bearing plate assemblies to the flap track, information on the availability of this Federal holidays.
in accordance with the Accomplishment material at the FAA, call 425–227–1221. For service information identified in
Instructions of Boeing Alert Service Bulletin this NPRM, contact International Aero
Issued in Renton, Washington, on March
Lhorne on DSK5TPTVN1PROD with PROPOSALS
747–57A2348, dated June 12, 2015. Engines AG, 400 Main Street, East
24, 2016. Hartford, CT 06118; phone: 860–368–
(h) Alternative Methods of Compliance
(AMOCs) Michael Kaszycki, 3700; fax: 860–368–4600; email:
(1) The Manager, Seattle Aircraft Acting Manager, Transport Airplane iaeinfo@iaev2500.com; Internet: https://
Certification Office (ACO), FAA, has the Directorate, Aircraft Certification Service. www.iaeworld.com. You may view this
authority to approve AMOCs for this AD, if [FR Doc. 2016–07578 Filed 4–4–16; 8:45 am] service information at the FAA, Engine
requested using the procedures found in 14 BILLING CODE 4910–13–P & Propeller Directorate, 1200 District
CFR 39.19. In accordance with 14 CFR 39.19, Avenue, Burlington, MA. For
VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1](https://thefederalregister.org/doc/81_FR_19581/page/1.svg)
![Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 19517
information on the availability of this in uncontained HPT blade release, safety in air commerce. This regulation
material at the FAA, call 781–238–7125. damage to the engine, and damage to the is within the scope of that authority
airplane. because it addresses an unsafe condition
Examining the AD Docket
that is likely to exist or develop on
You may examine the AD docket on Related Service Information Under 1
products identified in this rulemaking
the Internet at http:// CFR Part 51
action.
www.regulations.gov by searching for We reviewed IAE Non-Modification
and locating Docket No. FAA–2016– Service Bulletin (NMSB) No. V2500– Regulatory Findings
4123 or in person at the Docket ENG–72–0661, Revision No. 1, dated We determined that this proposed AD
Management Facility between 9 a.m. February 5, 2016. The NMSB describes would not have federalism implications
and 5 p.m., Monday through Friday, procedures for inspecting the HPT stage under Executive Order 13132. This
except Federal holidays. The AD docket 1 and stage 2 hubs. This service proposed AD would not have a
contains this proposed AD, the information is reasonably available substantial direct effect on the States, on
regulatory evaluation, any comments because the interested parties have the relationship between the national
received, and other information. The access to it through their normal course Government and the States, or on the
street address for the Docket Office of business or by the means identified distribution of power and
(phone: 800–647–5527) is in the in the ADDRESSES section. responsibilities among the various
ADDRESSES section. Comments will be levels of government.
available in the AD docket shortly after FAA’s Determination For the reasons discussed above, I
receipt. We are proposing this AD because we certify this proposed regulation:
FOR FURTHER INFORMATION CONTACT: evaluated all the relevant information (1) Is not a ‘‘significant regulatory
Brian Kierstead, Aerospace Engineer, and determined the unsafe condition action’’ under Executive Order 12866,
Engine Certification Office, FAA, Engine described previously is likely to exist or (2) Is not a ‘‘significant rule’’ under
& Propeller Directorate, 1200 District develop in other products of the same the DOT Regulatory Policies and
Avenue, Burlington, MA 01803; phone: type design. Procedures (44 FR 11034, February 26,
781–238–7772; fax: 781–238–7199; 1979),
Proposed AD Requirements (3) Will not affect intrastate aviation
email: brian.kierstead@faa.gov.
SUPPLEMENTARY INFORMATION: This proposed AD would require in Alaska to the extent that it justifies
inspecting the engine HPT stage 1 hub making a regulatory distinction, and
Comments Invited and HPT stage 2 hub, and, if necessary, (4) Will not have a significant
We invite you to send any written their replacement with parts eligible for economic impact, positive or negative,
relevant data, views, or arguments about installation. on a substantial number of small entities
this proposal. Send your comments to under the criteria of the Regulatory
Costs of Compliance Flexibility Act.
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA– We estimate that this proposed AD
List of Subjects in 14 CFR Part 39
2016–4123; Directorate Identifier 2016– affects 668 engines with 947 hubs
NE–06–AD’’ at the beginning of your installed on airplanes of U.S. registry. Air transportation, Aircraft, Aviation
comments. We specifically invite Some of the 668 engines have two hubs safety, Incorporation by reference,
comments on the overall regulatory, installed. We estimate that it would take Safety.
economic, environmental, and energy about 8 hours per hub to perform the The Proposed Amendment
aspects of this proposed AD. We will piece-part inspection. The average labor
rate is $85 per hour. We estimate that Accordingly, under the authority
consider all comments received by the
568 hubs will require replacement. We delegated to me by the Administrator,
closing date and may amend this
estimate the pro-rated cost to replace an the FAA proposes to amend 14 CFR part
proposed AD because of those
HPT stage 1 hub to be $50,271 and the 39 as follows:
comments.
We will post all comments we pro-rated cost to replace an HPT stage PART 39—AIRWORTHINESS
receive, without change, to http:// 2 hub to be $40,063. Based on these DIRECTIVES
www.regulations.gov, including any figures, we estimate the cost of this
personal information you provide. We proposed AD on U.S. operators to be ■ 1. The authority citation for part 39
will also post a report summarizing each $26,298,816. continues to read as follows:
substantive verbal contact we receive
Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701.
about this proposed AD.
Title 49 of the United States Code § 39.13 [Amended]
Discussion specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by adding
We received a report of an engine rules on aviation safety. Subtitle I, the following new airworthiness
IFSD and subsequent undercowl fire on section 106, describes the authority of directive (AD):
an IAE V2527–A5 turbofan engine the FAA Administrator. Subtitle VII:
during a revenue flight of an Airbus International Aero Engines AG: Docket No.
Aviation Programs, describes in more
FAA–2016–4123; Directorate Identifier
A320 airplane in September 2014. The detail the scope of the Agency’s 2016–NE–06–AD.
subsequent investigation of this event authority.
determined that it was caused by a We are issuing this rulemaking under (a) Comments Due Date
Lhorne on DSK5TPTVN1PROD with PROPOSALS
manufacturing defect in the HPT stage the authority described in Subtitle VII, We must receive comments by June 6,
2 hub that resulted in fracture and Part A, Subpart III, Section 44701: 2016.
failure of the HPT stage 2 hub. The ‘‘General requirements.’’ Under that (b) Affected ADs
event involved release of a fir tree lug section, Congress charges the FAA with
None.
and two HPT stage 2 blades. IAE also promoting safe flight of civil aircraft in
identified a similar manufacturing air commerce by prescribing regulations (c) Applicability
defect on the HPT stage 1 hub. This for practices, methods, and procedures This AD applies to International Aero
condition, if not corrected, could result the Administrator finds necessary for Engines AG (IAE) V2522–A5, V2524–A5,
VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1](https://thefederalregister.org/doc/81_FR_19581/page/2.svg)
![19518 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules
V2525–D5, V2527–A5, V2527E–A5, make your request. You may email your 72296) and extended at 81 FR 2787
V2527M–A5, V2528–D5, V2530–A5, and request to: ANE-AD-AMOC@faa.gov. (January 19, 2016) is reopened. The
V2533–A5, engines with either of the Department will accept written
following installed: (h) Related Information
(1) For more information about this AD,
comments on the notice of proposed
(1) High-pressure turbine (HPT) stage 1
hub, part number (P/N) 2A5001, with a serial contact Brian Kierstead, Aerospace Engineer, rulemaking from interested parties that
number (S/N) listed in Table 1, Appendix A, Engine Certification Office, FAA, Engine & are submitted from April 5, 2016
of IAE Non-Modification Service Bulletin Propeller Directorate, 1200 District Avenue, through May 9, 2016.
(NMSB) No. V2500–ENG–72–0661, Revision Burlington, MA 01803; phone: 781–238– ADDRESSES: Parties may submit
1, dated February 5, 2016; or 7772; fax: 781–238–7199; email: comments on the regulations in the
(2) HPT stage 2 hub, P/N 2A4802, with an brian.kierstead@faa.gov. proposed rule, identified by Regulatory
S/N listed in Table 2, Appendix A, of IAE (2) For service information identified in
Information Number (RIN) 1240–AA08,
NMSB No. V2500–ENG–72–0661, Revision 1, this proposed AD, contact International Aero
dated February 5, 2016. Engines AG, 400 Main Street, East Hartford, by any ONE of the following methods:
CT 06118; phone: 860–368–3700; fax: 860– Federal e-Rulemaking Portal: The
(d) Unsafe Condition Internet address to submit comments on
368–4600; email: iaeinfo@iaev2500.com;
This AD was prompted by the fracture of Internet: https://www.iaeworld.com. the regulations in the proposed rule is
the HPT stage 2 hub during flight, which (3) You may view this service information www.regulations.gov. Follow the Web
resulted in an in-flight shutdown, undercowl at the FAA, Engine & Propeller Directorate, site instructions for submitting
fire, and smoke in the cabin. We are issuing 1200 District Avenue, Burlington, MA. For comments. Comments will also be
this AD to prevent failure of the HPT stage information on the availability of this available for public inspection on the
1 or HPT stage 2 hubs, which could result in material at the FAA, call 781–238–7125.
uncontained HPT blade release, damage to Web site.
the engine, and damage to the airplane. Issued in Burlington, Massachusetts, on Mail or Hand Delivery: Submit written
March 24, 2016. comments by mail to Rachel P. Leiton,
(e) Compliance Colleen M. D’Alessandro, Director, Division of Energy Employees
Comply with this AD within the Manager, Engine & Propeller Directorate, Occupational Illness Compensation,
compliance times specified, unless already Aircraft Certification Service. Office of Workers’ Compensation
done. Programs, U.S. Department of Labor,
[FR Doc. 2016–07579 Filed 4–4–16; 8:45 am]
(1) Inspect the HPT stage 1 hub, P/N Room C–3321, 200 Constitution Avenue
2A5001, and HPT stage 2 hub, P/N 2A4802, BILLING CODE 4910–13–P
at the next shop visit or as follows, NW., Washington, DC 20210. The
whichever comes first: Department will only consider mailed
(i) For hubs with 0 to 7,000 CSN, before DEPARTMENT OF LABOR comments that have been postmarked
accumulating 13,000 CSN; by the U.S. Postal Service or other
(ii) For hubs with 7,001 to 11,000 CSN, Office of Workers’ Compensation delivery service on or before the
within 6,000 cycles from the effective date of deadline for comments.
Programs
this AD or before accumulating 15,000 CSN, Instructions: All comments must cite
whichever occurs first; RIN 1240–AA08 that has been assigned
(iii) For hubs with 11,001 to 15,500 CSN, 20 CFR Part 30
to this rulemaking. Receipt of any
within 4,000 cycles from the effective date of RIN 1240–AA08
this AD or before accumulating 17,000 CSN, comments, whether by Internet, mail or
whichever occurs first; hand delivery, will not be
Claims for Compensation Under the acknowledged.
(iv) For hubs with 15,501 CSN or greater,
within 1,500 cycles from the effective date of Energy Employees Occupational
Illness Compensation Program Act FOR FURTHER INFORMATION CONTACT:
this AD.
Rachel P. Leiton, Director, Division of
(2) Use Accomplishment Instructions,
AGENCY: Office of Workers’ Energy Employees Occupational Illness
paragraphs 2.A., 2.C., and 2.D., of IAE NMSB
No. V2500–ENG–72–0661, Revision 1, dated Compensation Programs, Department of Compensation, Office of Workers’
February 5, 2016, to inspect the HPT stage 1 Labor. Compensation Programs, U.S.
hub, P/N 2A5001. ACTION: Notice of proposed rulemaking; Department of Labor, Room C–3321, 200
(3) Use Accomplishment Instructions, reopening of comment period. Constitution Avenue NW., Washington,
paragraphs 2.E., 2.G., and 2H., of IAE NMSB DC 20210, Telephone: 202–693–0081
No. V2500–ENG–72–0661, to inspect the SUMMARY: The Department of Labor is (this is not a toll-free number).
HPT stage 2 hub, P/N 2A4802. reopening and extending the comment Individuals with hearing or speech
(4) Remove from service any HPT stage 1 period for the notice of proposed impairments may access this telephone
hub, P/N 2A5001, or HPT stage 2 hub, P/N
2A4802, that fail the inspections required by
rulemaking it published on November number via TTY by calling the toll-free
paragraphs (e)(2) and (e)(3) of this AD, and 18, 2015 (80 FR 72296). The Department Federal Information Relay Service at 1–
replace with a part that is eligible for originally allowed a 60-day comment 800–877–8339.
installation. period that was scheduled to close on SUPPLEMENTARY INFORMATION: In
January 19, 2016, but on that date response to requests from members of
(f) Definition
extended the comment period another the public, the Department has decided
For the purpose of this AD, a ‘‘shop visit’’ 30 days through February 18, 2016 (81
is the induction of an engine into the shop to reopen the public comment period for
FR 2787). This notice indicates that the the notice of proposed rulemaking it
for maintenance involving the separation of
pairs of major mating engine flanges, except comment period is being reopened as of published on November 18, 2015 (80 FR
that the separation of engine flanges solely April 5, 2016 and extended for an 72296). The Department originally
additional period. The comment period
Lhorne on DSK5TPTVN1PROD with PROPOSALS
for the purposes of transportation without allowed a 60-day comment period that
subsequent engine maintenance does not for the information collection was scheduled to close on January 19,
constitute an engine shop visit. requirements in the proposed rule 2016, but on that date extended the
(g) Alternative Methods of Compliance ended on December 18, 2015, and that comment period another 30 days
(AMOCs) period is not being reopened. through February 18, 2016 (81 FR 2787).
The Manager, Engine Certification Office, DATES: The comment period for the The comment period is being reopened
FAA, may approve AMOCs for this AD. Use notice of proposed rulemaking as of April 5, 2016 and extended
the procedures found in 14 CFR 39.19 to published on November 18, 2015 (80 FR through May 9, 2016. The comment
VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\05APP1.SGM 05APP1](https://thefederalregister.org/doc/81_FR_19581/page/3.svg)
Document Created: 2018-02-07 13:53:25
Document Modified: 2018-02-07 13:53:25
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 6, 2016. | |
| Contact | Brian Kierstead, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 81 FR 19516 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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