80_FR_52131 80 FR 51965 - Airworthiness Directives; General Electric Company Turbofan Engines

80 FR 51965 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 166 (August 27, 2015)

Page Range51965-51966
FR Document2015-21120

We propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 turbofan engine models. This proposed AD was prompted by reports of two in-flight shutdowns (IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade failure. This proposed AD would require inspection and conditional removal of affected HPT rotor stage 1 blades. We are proposing this AD to prevent failure of the HPT rotor stage 1 blades, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.

Federal Register, Volume 80 Issue 166 (Thursday, August 27, 2015) 
[Federal Register Volume 80, Number 166 (Thursday, August 27, 2015)]
[Proposed Rules]
[Pages 51965-51966]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-21120]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2984; Directorate Identifier 2015-NE-21-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 
turbofan engine models. This proposed AD was prompted by reports of two 
in-flight shutdowns (IFSDs) caused by high-pressure turbine (HPT) rotor 
stage 1 blade failure. This proposed AD would require inspection and 
conditional removal of affected HPT rotor stage 1 blades. We are 
proposing this AD to prevent failure of the HPT rotor stage 1 blades, 
which could lead to failure of one or more engines, loss of thrust 
control, and damage to the airplane.

DATES: We must receive comments on this proposed AD by October 26, 
2015.

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 proposed AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected]. You may view this service information at 
the FAA, Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2984; 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: Christopher McGuire, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
phone: 781-238-7120; 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 NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2015-2984; 
Directorate Identifier 2015-NE-21-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM 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 NPRM.

Discussion

    We propose to adopt a new AD for all GE GEnx-1B54, -1B58, -1B64, -
1B67, and -1B70 turbofan engine models. This proposed AD was prompted 
by reports of two IFSDs caused by HPT rotor stage 1 blade failure. This 
proposed AD would require inspection and conditional removal of 
affected HPT rotor stage 1 blades. This condition, if not corrected, 
could result in failure of the HPT rotor stage 1 blades, which could 
lead to failure of one or more engines, loss of thrust control, and 
damage to the airplane.

Related Service Information

    We reviewed GE GEnx-1B Service Bulletin (SB) No. 72-0267 R00, dated 
April 10, 2015. The SB describes procedures for borescope inspection 
(BSI) of the HPT rotor stage 1 blades.

FAA's Determination

    We are proposing this NPRM 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 NPRM would require initial and repetitive BSI and conditional 
removal of affected HPT rotor stage 1 blades.

Costs of Compliance

    We estimate that this proposed AD will affect 4 engines installed 
on airplanes of U.S. registry. We also estimate that it will take about 
2 hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Based on these figures, we estimate the total 
cost of this proposed AD to U.S. operators to be $680.

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

[[Page 51966]]

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):

General Electric Company: Docket No. FAA-2015-2984; Directorate 
Identifier 2015-NE-21-AD.

(a) Comments Due Date

    We must receive comments by October 26, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all General Electric Company (GE) GEnx-1B54, 
-1B58, -1B64, -1B67, and -1B70 turbofan engines with high-pressure 
turbine (HPT) rotor stage 1 blade, part number 2305M26P06, 
installed.

(d) Unsafe Condition

    This AD was prompted by reports of two in-flight shutdowns 
caused by HPT rotor stage 1 blade failure. We are issuing this AD to 
prevent failure of the HPT rotor stage 1 blades, which could lead to 
failure of one or more engines, loss of thrust control, and damage 
to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) After the effective date of this AD, perform an initial 
borescope inspection (BSI) of the convex surface of the HPT rotor 
stage 1 blades for axial cracks from the platform to 30% span, 
within 1,000 blade cycles since new or 25 cycles in service, 
whichever comes later, and disposition as follows:
    (i) If any axial crack with a length greater than or equal to 
0.3 inch is found, or if any axial crack of any length turning in a 
radial direction is found, or if more than one axial crack of any 
length is found, remove the cracked blade before further flight.
    (ii) If an axial crack is found with a length greater than or 
equal to 0.2 inch and less than 0.3 inch, remove the cracked blade 
within 10 blade cycles in service.
    (iii) If an axial crack is found with a length greater than or 
equal to 0.1 inch and less than 0.2 inch, inspect the cracked blade 
within 50 blade cycles since last inspection (CSLI).
    (iv) If an axial crack is found with a length less than 0.1 
inch, inspect the cracked blade within 100 blade CSLI.
    (v) If no cracks were found, perform a BSI of the blades within 
125 blade CSLI.
    (2) Thereafter, perform a repetitive BSI of the convex surface 
of the HPT rotor stage 1 blades for axial cracks from the platform 
to 30% span within 125 blade CSLI and disposition as specified in 
(e)(1)(i) through (e)(1)(v), or remove the blades from service.

(f) Definition

    For the purpose of this AD, a ``blade cycle'' is defined as the 
number of engine cycles that a set of rotor blades has accrued, 
regardless of the engine(s) in which they have operated.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to 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 Christopher 
McGuire, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: 
[email protected].
    (2) GE GEnx-1B Service Bulletin No. 72-0267 R00, dated April 10, 
2015 can be obtained from GE using the contact information in 
paragraph (h)(3) of this proposed AD.
    (3) For service information identified in this proposed AD, 
contact General Electric Company, GE Aviation, Room 285, 1 Neumann 
Way, Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected].
    (4) 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.

    Issued in Burlington, Massachusetts, on August 21, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-21120 Filed 8-26-15; 8:45 am]
 BILLING CODE 4910-13-P

Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 51965 10 CFR part 61’’). The public comment • Hand Delivery: Deliver to Mail Discussion periods for the proposed rule and draft address above between 9 a.m. and 5 We propose to adopt a new AD for all guidance closed on July 24, 2015. The p.m., Monday through Friday, except GE GEnx–1B54, –1B58, –1B64, –1B67, NRC has decided to reopen the public Federal holidays. and –1B70 turbofan engine models. This comment periods for the proposed rule For service information identified in proposed AD was prompted by reports and draft guidance until September 21, this proposed AD, contact General of two IFSDs caused by HPT rotor stage 2015, to allow more time for members Electric Company, GE Aviation, Room 1 blade failure. This proposed AD of the public to develop and submit 285, 1 Neumann Way, Cincinnati, OH would require inspection and their comments. 45215; phone: 513–552–3272; email: conditional removal of affected HPT Dated at Rockville, Maryland, this 19th day aviation.fleetsupport@ge.com. You may rotor stage 1 blades. This condition, if of August, 2015. view this service information at the not corrected, could result in failure of For the Nuclear Regulatory Commission. FAA, Engine & Propeller Directorate, 12 the HPT rotor stage 1 blades, which Annette L. Vietti-Cook, New England Executive Park, could lead to failure of one or more Secretary of the Commission. Burlington, MA 01803. For information engines, loss of thrust control, and [FR Doc. 2015–21169 Filed 8–26–15; 8:45 am] on the availability of this material at the damage to the airplane. BILLING CODE 7590–01–P FAA, call 781–238–7125. Related Service Information Examining the AD Docket We reviewed GE GEnx–1B Service Bulletin (SB) No. 72–0267 R00, dated DEPARTMENT OF TRANSPORTATION You may examine the AD docket on April 10, 2015. The SB describes the Internet at http:// procedures for borescope inspection Federal Aviation Administration www.regulations.gov by searching for (BSI) of the HPT rotor stage 1 blades. and locating Docket No. FAA–2015– 14 CFR Part 39 2984; or in person at the Docket FAA’s Determination Management Facility between 9 a.m. We are proposing this NPRM because [Docket No. FAA–2015–2984; Directorate Identifier 2015–NE–21–AD] and 5 p.m., Monday through Friday, we evaluated all the relevant except Federal holidays. The AD docket information and determined the unsafe RIN 2120–AA64 contains this proposed AD, the condition described previously is likely regulatory evaluation, any comments to exist or develop in other products of Airworthiness Directives; General received, and other information. The Electric Company Turbofan Engines the same type design. street address for the Docket Office AGENCY: Federal Aviation (phone: 800–647–5527) is in the Proposed AD Requirements Administration (FAA), DOT. ADDRESSES section. Comments will be This NPRM would require initial and ACTION: Notice of proposed rulemaking available in the AD docket shortly after repetitive BSI and conditional removal (NPRM). receipt. of affected HPT rotor stage 1 blades. FOR FURTHER INFORMATION CONTACT: Costs of Compliance SUMMARY: We propose to adopt a new Christopher McGuire, Aerospace airworthiness directive (AD) for all We estimate that this proposed AD Engineer, Engine Certification Office, will affect 4 engines installed on General Electric Company (GE) GEnx– FAA, Engine & Propeller Directorate, 12 1B54, –1B58, –1B64, –1B67, and –1B70 airplanes of U.S. registry. We also New England Executive Park, estimate that it will take about 2 hours turbofan engine models. This proposed Burlington, MA 01803; phone: 781– AD was prompted by reports of two in- per engine to comply with this proposed 238–7120; fax: 781–238–7199; email: AD. The average labor rate is $85 per flight shutdowns (IFSDs) caused by chris.mcguire@faa.gov. high-pressure turbine (HPT) rotor stage hour. Based on these figures, we 1 blade failure. This proposed AD SUPPLEMENTARY INFORMATION: estimate the total cost of this proposed would require inspection and AD to U.S. operators to be $680. Comments Invited conditional removal of affected HPT Authority for This Rulemaking rotor stage 1 blades. We are proposing We invite you to send any written this AD to prevent failure of the HPT Title 49 of the United States Code relevant data, views, or arguments about specifies the FAA’s authority to issue rotor stage 1 blades, which could lead this NPRM. Send your comments to an to failure of one or more engines, loss rules on aviation safety. Subtitle I, address listed under the ADDRESSES section 106, describes the authority of of thrust control, and damage to the section. Include ‘‘Docket No. FAA– airplane. the FAA Administrator. Subtitle VII: 2015–2984; Directorate Identifier 2015– Aviation Programs, describes in more DATES: We must receive comments on NE–21–AD’’ at the beginning of your detail the scope of the Agency’s this proposed AD by October 26, 2015. comments. We specifically invite authority. ADDRESSES: You may send comments, comments on the overall regulatory, We are issuing this rulemaking under using the procedures found in 14 CFR economic, environmental, and energy the authority described in Subtitle VII, 11.43 and 11.45, by any of the following aspects of this NPRM. We will consider Part A, Subpart III, Section 44701: methods: all comments received by the closing ‘‘General requirements.’’ Under that • Federal eRulemaking Portal: Go to date and may amend this NPRM section, Congress charges the FAA with rmajette on DSK2VPTVN1PROD with PROPOSALS http://www.regulations.gov. Follow the because of those comments. promoting safe flight of civil aircraft in instructions for submitting comments. We will post all comments we air commerce by prescribing regulations • Fax: 202–493–2251. receive, without change, to http:// for practices, methods, and procedures • Mail: U.S. Department of www.regulations.gov, including any the Administrator finds necessary for Transportation, Docket Operations, M– personal information you provide. We safety in air commerce. This regulation 30, West Building Ground Floor, Room will also post a report summarizing each is within the scope of that authority W12–140, 1200 New Jersey Avenue SE., substantive verbal contact we receive because it addresses an unsafe condition Washington, DC 20590. about this NPRM. that is likely to exist or develop on VerDate Sep<11>2014 14:07 Aug 26, 2015 Jkt 235001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\27AUP1.SGM 27AUP1

51966 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules products identified in this rulemaking (d) Unsafe Condition Neumann Way, Cincinnati, OH 45215; action. This AD was prompted by reports of two phone: 513–552–3272; email: in-flight shutdowns caused by HPT rotor aviation.fleetsupport@ge.com. Regulatory Findings stage 1 blade failure. We are issuing this AD (4) You may view this service information to prevent failure of the HPT rotor stage 1 at the FAA, Engine & Propeller Directorate, We determined that this proposed AD blades, which could lead to failure of one or 12 New England Executive Park, Burlington, would not have federalism implications MA. For information on the availability of more engines, loss of thrust control, and under Executive Order 13132. This this material at the FAA, call 781–238–7125. damage to the airplane. proposed AD would not have a (e) Compliance Issued in Burlington, Massachusetts, on substantial direct effect on the States, on August 21, 2015. the relationship between the national Comply with this AD within the Colleen M. D’Alessandro, Government and the States, or on the compliance times specified, unless already distribution of power and done. Directorate Manager, Engine & Propeller (1) After the effective date of this AD, Directorate, Aircraft Certification Service. responsibilities among the various levels of government. perform an initial borescope inspection (BSI) [FR Doc. 2015–21120 Filed 8–26–15; 8:45 am] of the convex surface of the HPT rotor stage BILLING CODE 4910–13–P For the reasons discussed above, I 1 blades for axial cracks from the platform to certify this proposed regulation: 30% span, within 1,000 blade cycles since (1) Is not a ‘‘significant regulatory new or 25 cycles in service, whichever comes DEPARTMENT OF TRANSPORTATION action’’ under Executive Order 12866, later, and disposition as follows: (2) Is not a ‘‘significant rule’’ under (i) If any axial crack with a length greater Federal Aviation Administration the DOT Regulatory Policies and than or equal to 0.3 inch is found, or if any Procedures (44 FR 11034, February 26, axial crack of any length turning in a radial direction is found, or if more than one axial 14 CFR Part 39 1979), crack of any length is found, remove the [Docket No. FAA–2015–3620; Directorate (3) Will not affect intrastate aviation cracked blade before further flight. in Alaska to the extent that it justifies Identifier 2015–CE–029–AD] (ii) If an axial crack is found with a length making a regulatory distinction, and greater than or equal to 0.2 inch and less than RIN 2120–AA64 (4) Will not have a significant 0.3 inch, remove the cracked blade within 10 economic impact, positive or negative, blade cycles in service. Airworthiness Directives; Pacific on a substantial number of small entities (iii) If an axial crack is found with a length Aerospace Limited Airplanes under the criteria of the Regulatory greater than or equal to 0.1 inch and less than 0.2 inch, inspect the cracked blade within 50 AGENCY: Federal Aviation Flexibility Act. blade cycles since last inspection (CSLI). Administration (FAA), Department of List of Subjects in 14 CFR Part 39 (iv) If an axial crack is found with a length Transportation (DOT). less than 0.1 inch, inspect the cracked blade ACTION: Notice of proposed rulemaking Air transportation, Aircraft, Aviation within 100 blade CSLI. safety, Incorporation by reference, (v) If no cracks were found, perform a BSI (NPRM). Safety. of the blades within 125 blade CSLI. SUMMARY: We propose to adopt a new (2) Thereafter, perform a repetitive BSI of The Proposed Amendment the convex surface of the HPT rotor stage 1 airworthiness directive (AD) for certain Accordingly, under the authority blades for axial cracks from the platform to Pacific Aerospace Limited Model 750XL delegated to me by the Administrator, 30% span within 125 blade CSLI and airplanes that would supersede AD the FAA proposes to amend 14 CFR part disposition as specified in (e)(1)(i) through 2014–20–13. This proposed AD results 39 as follows: (e)(1)(v), or remove the blades from service. from mandatory continuing (f) Definition airworthiness information (MCAI) PART 39—AIRWORTHINESS originated by an aviation authority of For the purpose of this AD, a ‘‘blade cycle’’ DIRECTIVES another country to identify and correct is defined as the number of engine cycles that a set of rotor blades has accrued, regardless an unsafe condition on an aviation ■ 1. The authority citation for part 39 of the engine(s) in which they have operated. product. The MCAI describes the unsafe continues to read as follows: condition as fatigue cracks on the fin (g) Alternative Methods of Compliance forward pickup plates, which could Authority: 49 U.S.C. 106(g), 40113, 44701. (AMOCs) cause it to fail. We are issuing this § 39.13 [Amended] The Manager, Engine Certification Office, proposed AD to require actions to FAA, may approve AMOCs to this AD. Use address the unsafe condition on these ■ 2. The FAA amends § 39.13 by adding the procedures found in 14 CFR 39.19 to the following new airworthiness products. make your request. You may email your directive (AD): request to: ANE-AD-AMOC@faa.gov. DATES: We must receive comments on General Electric Company: Docket No. FAA– (h) Related Information this proposed AD by October 13, 2015. 2015–2984; Directorate Identifier 2015– ADDRESSES: You may send comments by NE–21–AD. (1) For more information about this AD, contact Christopher McGuire, Aerospace any of the following methods: (a) Comments Due Date Engineer, Engine Certification Office, FAA, • Federal eRulemaking Portal: Go to We must receive comments by October 26, Engine & Propeller Directorate, 12 New http://www.regulations.gov. Follow the 2015. England Executive Park, Burlington, MA instructions for submitting comments. 01803; phone: 781–238–7120; fax: 781–238– • Fax: (202) 493–2251. rmajette on DSK2VPTVN1PROD with PROPOSALS (b) Affected ADs 7199; email: chris.mcguire@faa.gov. • Mail: U.S. Department of None. (2) GE GEnx-1B Service Bulletin No. 72– Transportation, Docket Operations, M– 0267 R00, dated April 10, 2015 can be (c) Applicability 30, West Building Ground Floor, Room obtained from GE using the contact This AD applies to all General Electric information in paragraph (h)(3) of this W12–140, 1200 New Jersey Avenue SE., Company (GE) GEnx–1B54, –1B58, –1B64, proposed AD. Washington, DC 20590. –1B67, and –1B70 turbofan engines with (3) For service information identified in • Hand Delivery: U.S. Department of high-pressure turbine (HPT) rotor stage 1 this proposed AD, contact General Electric Transportation, Docket Operations, M– blade, part number 2305M26P06, installed. Company, GE Aviation, Room 285, 1 30, West Building Ground Floor, Room VerDate Sep<11>2014 14:07 Aug 26, 2015 Jkt 235001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 E:\FR\FM\27AUP1.SGM 27AUP1


Document Created: 2015-12-15 10:52:55
Document Modified: 2015-12-15 10:52:55
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by October 26, 2015.
ContactChristopher McGuire, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: [email protected]
FR Citation80 FR 51965 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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