
[Federal Register Volume 82, Number 169 (Friday, September 1, 2017)]
[Proposed Rules]
[Pages 41577-41579]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-18571]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0660; Product Identifier 2017-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 
certain General Electric Company (GE) GEnx-1B64/P2, -1B67/P2, -1B70/P2, 
-1B70/75/P2, -1B70C/P2, and -1B74/75/P2 turbofan engines. This proposed 
AD was prompted by a report of the failure of the high-pressure turbine 
(HPT) stage 1 blade retainer and subsequent in-flight shutdown of the 
engine. This proposed AD would require inspection of the HPT stage 1 
blade retainer. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by October 16, 
2017.

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 General 
Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 
45215, phone: 513-552-3272; fax: 513-552-3329; email: geae.aoc@ge.com. 
You may view this service information at the FAA, Engine and Propeller 
Standards Branch, Policy and Innovation Division,

[[Page 41578]]

1200 District Avenue, 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0660; 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 NPRM, 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, FAA, ECO Branch, Compliance and Airworthiness Division, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7120; fax: 781-
238-7199; email: Chris.mcguire@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0660; 
Directorate Identifier 2017-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 learned of the failure of an HPT stage 1 blade retainer that 
resulted in an in-flight shutdown of the engine. This condition, if not 
corrected, could result in failure of one or more engines, loss of 
thrust control, and damage to the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed GE Service Bulletin (SB) GEnx-1B SB 72-0326 R02, dated 
August 16, 2017. The SB describes procedures for piece-part inspection 
of the HPT stage 1 blade retainer. 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 inspection of the HPT stage 1 blade 
retainer.

Costs of Compliance

    We estimate that this proposed AD affects 11 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of the HPT stage 1 blade  1 work-hour x $85 per hour               $0             $85            $935
 retainer.                            = $85.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
appliances to the Manager, Engine and Propeller Standards Branch, 
Policy and Innovation Division.

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:

[[Page 41579]]

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-2017-0660; Product 
Identifier 2017-NE-21-AD.

(a) Comments Due Date

    We must receive comments by October 16, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) GEnx-1B64/P2, -
1B67/P2, -1B70/P2, -1B70/75/P2, -1B70C/P2, and -1B74/75/P2 turbofan 
engines, with a high-pressure turbine (HPT) stage 1 blade retainer, 
part number (P/N) 2445M91P01 or 2383M99P02, with a serial number 
listed in Planning Information, paragraph 1.A., of GE GEnx-1B 
Service Bulletin (SB) 72-0326 R02, dated August 16, 2017.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by a report of the failure of the high-
pressure turbine (HPT) stage 1 blade retainer and subsequent in-
flight shutdown of the engine. We are issuing this AD to prevent 
failure of the HPT stage 1 blade retainer. The unsafe condition, if 
not corrected, could result in failure of one or more engines, loss 
of thrust control, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) At the next engine shop visit after the effective date of 
this AD, perform a one-time inspection of the HPT stage 1 blade 
retainer. Use the Accomplishment Instructions, paragraph 3.A.(1), in 
GE GEnx-1B SB 72-0326 R02, dated August 16, 2017, to do the 
inspection.
    (2) If any cracks are found in the HPT stage 1 blade retainer, 
or the retainer does not meet the dimensional criteria found in the 
Accomplishment Instructions, paragraph 3.A.(1), in GEnx-1B SB 72-
0326 R02, dated August 16, 2017, replace with a part eligible for 
installation.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine case flanges, except 
separation of engine flanges solely for the purposes of 
transportation or for replacing the fan or propulsor, without 
subsequent maintenance, does not constitute an engine shop visit.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, FAA, ECO Branch, Compliance and Airworthiness 
Division, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ECO Branch, send it to 
the attention of the person identified in paragraph (i)(1) of this 
AD. You may email your request to: ANE-AD-AMOC@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    (1) For more information about this AD, contact Christopher 
McGuire, Aerospace Engineer, FAA, ECO Branch, Compliance and 
Airworthiness Division, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7120; fax: 781-238-7199; email: 
Christopher.mcguire@faa.gov.
    (2) GE GEnx-1B SB 72-0326 R02, dated August 16, 2017, can be 
obtained from GE using the contact information in paragraph (i)(3) 
of this 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; fax: 513-552-3329; 
email: geae.aoc@ge.com.
    (4) You may view this service information at the FAA, Engine and 
Propeller Standards Branch, Policy and Innovation Division, 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 August 29, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-18571 Filed 8-31-17; 8:45 am]
BILLING CODE 4910-13-P


