AD 2017-07-04

[Federal Register Volume 82, Number 65 (Thursday, April 6, 2017)]
[Rules and Regulations]
[Pages 16728-16730]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-06715]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0879; Directorate Identifier 2013-NE-30-AD; 
Amendment 39-18842; AD 2017-07-04]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-24-17 for 
General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines 
with certain high-pressure compressor (HPC) rotor stage 2-5 spools 
installed. AD 2013-24-17 required removing these spools from service at 
times determined by a drawdown plan. This AD retains the same 
requirements as AD 2013-24-17. This AD also adds additional part number 
(P/N) HPC spools to the applicability. This AD was prompted by reports 
of cracking on these additional spools. We are issuing this AD to 
correct the unsafe condition on these products.

DATES: This AD is effective April 21, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 21, 
2017.
    We must receive any comments on this AD by May 22, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact General 
Electric Company, One Neumann Way, Room 285, Cincinnati, OH; phone: 
513-552-3272; email: <a href="/cdn-cgi/l/email-protection#5c3b393d39723d333f1c3b39723f3331"><span class="__cf_email__" data-cfemail="3e595b5f5b105f515d7e595b105d5153">[email&#160;protected]</span></a>. 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. It is also available on the 
internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating 
Docket No. FAA-2013-0879.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2013-
0879; 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 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: John Frost, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-
238-7199; email: <a href="/cdn-cgi/l/email-protection#1c76737472327a6e736f685c7a7d7d327b736a"><span class="__cf_email__" data-cfemail="4b21242325652d3924383f0b2d2a2a652c243d">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    On November 27, 2013, we issued AD 2013-24-17, Amendment 39-17694 
(78 FR 76045, December 16, 2013), (``AD 2013-24-17''), for GE GE90-
110B1 and GE90-115B turbofan engines with certain HPC rotor stage 2-5 
spools installed. AD 2013-24-17 required removing these spools from 
service at times determined by a drawdown plan. AD 2013-24-17 resulted 
from reports of cracks in HPC rotor stage 2-5 spool aft

[[Page 16729]]

spacer arms. We issued AD 2013-24-17 to prevent failure of a critical 
life-limited rotating engine part, which could result in an uncontained 
engine failure and damage to the airplane.

Actions Since AD 2013-24-17 Was Issued

    Since we issued AD 2013-24-17, GE found cracking on additional P/N 
HPC spools. These spools had not previously been thought to be affected 
by cracking because they had a revised coating applied in the seal 
teeth area. We also reviewed the risk assessment and determined that an 
installation prohibition was not needed, therefore, we eliminated that 
paragraph from this AD. In addition, GE revised its service material by 
issuing GE Service Bulletin (SB) GE90-100 SB 72-0659 R01, dated 
February 18, 2016, which we reference in the compliance section of this 
AD. We are issuing this AD to prevent failure of the HPC rotor stage 2-
5 spools, uncontained spool release, damage to the engine, and damage 
to the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed GE Service Bulletin (SB) GE90-100 SB 72-0659 R01, dated 
February 18, 2016. The SB describes procedures for identification and 
removal from service of the affected HPC 2-5 spools. The part numbers 
that are listed in Appendix A of GE SB GE90-100 SB 72-0659 R01 are the 
original P/Ns. Spools that have been reworked may have a P/N other than 
that listed in Appendix A. 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 issuing 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.

AD Requirements

    This AD requires removing certain HPC rotor stage 2-5 spools from 
service at times determined by a drawdown plan specified in the 
compliance section.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because it 
requires compliance before further flight. Therefore, we find that 
notice and opportunity for prior public comment are impracticable and 
that good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
the Docket No. FAA-2013-0879 and Directorate Identifier 2013-NE-30-AD 
at the beginning of your comments. We specifically invite comments on 
the overall regulatory, economic, environmental, and energy aspects of 
this AD. We will consider all comments received by the closing date and 
may amend this AD because of those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 22 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                Parts     Cost per  Cost on U.S.
                   Action                               Labor cost               cost     product     operators
----------------------------------------------------------------------------------------------------------------
Replacement of HPC rotor stage 2-5 spool....  0 work-hours x $85 per hour =    $229,737   $229,737    $5,054,214
                                               $0.
----------------------------------------------------------------------------------------------------------------

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 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:


[[Page 16730]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-24-17, Amendment 39-17694 (78 FR 76045, December 16, 2013), and 
adding the following new AD:

2017-07-04 General Electric Company: Amendment 39-18842; Docket No. 
FAA-2013-0879; Directorate Identifier 2013-NE-30-AD.

(a) Effective Date

    This AD is effective April 21, 2017.

(b) Affected ADs

    This AD replaces AD 2013-24-17, Amendment 39-17694 (78 FR 76045, 
December 16, 2013) (``AD 2013-24-17'').

(c) Applicability

    All GE90-110B1 and GE90-115B engines with high-pressure 
compressor (HPC) stage 2-5 spools, with:
    (1) a part number (P/N) 351-103-106-0, 351-103-107-0, 351-103-
108-0, 351-103-141-0, 351-103-142-0, 351-103-143-0, 351-103-144-0, 
351-103-145-0, 351-103-146-0, 351-103-148-0, 351-103-149-0, 351-103-
150-0, or 351-103-151-0; and
    (2) a serial number listed in paragraph 4, Appendix A, of GE 
Service Bulletin (SB) GE90-100 SB 72-0659 R01, dated February 18, 
2016.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

(e) Unsafe Condition

    This AD was prompted by reports of cracks in HPC rotor stage 2-5 
spool aft spacer arms since AD 2013-24-17.We are issuing this AD to 
prevent failure of the HPC rotor stage 2-5 spools, uncontained spool 
release, damage to the engine, and damage to the airplane.

(f) Compliance

    (1) Comply with this AD within the compliance times specified, 
unless already done.
    (2) Remove from service HPC rotor stage 2-5 spools listed in 
paragraph 4, Appendix A, of GE SB GE90-100 SB 72-0659 R01, dated 
February 18, 2016, as follows:
    (i) For spools that have fewer than 4,500 flight cycles since 
new (CSN) on the effective date of this AD, remove before exceeding 
5,000 CSN.
    (ii) For spools that have 4,500 CSN or more but fewer than 5,200 
CSN on the effective date of this AD, remove within 500 cycles in 
service (CIS) but not to exceed 5,500 CSN.
    (iii) For spools that have 5,200 CSN or more but fewer than 
5,600 CSN on the effective date of this AD, remove within 300 CIS 
but not to exceed 5,800 CSN.
    (iv) For spools that have 5,600 CSN or more but fewer than 5,800 
CSN on the effective date of this AD, remove within 200 CIS but not 
to exceed 5,850 CSN.
    (v) For spools that have 5,800 CSN or more but fewer than 6,000 
CSN on the effective date of this AD, remove within 50 CIS but not 
to exceed 6,000 CSN.
    (vi) For spools that have 6,000 CSN or more on the effective 
date of this AD, remove before the next flight.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for 
this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: <a href="/cdn-cgi/l/email-protection#a4e5eae189e5e089e5e9ebe7e4c2c5c58ac3cbd2"><span class="__cf_email__" data-cfemail="7e3f303b533f3a533f33313d3e181f1f50191108">[email&#160;protected]</span></a>.

(h) Related Information

    For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7756; fax: 781-238-7199; email: <a href="/cdn-cgi/l/email-protection#771d181f195911051804033711161659101801"><span class="__cf_email__" data-cfemail="600a0f080e4e06120f1314200601014e070f16">[email&#160;protected]</span></a>.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) General Electric Company (GE) Service Bulletin GE90-100 SB 
72-0659 R01, dated February 18, 2016.
    (ii) Reserved.
    (3) For GE service information identified in this AD, contact 
General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; email: 
<a href="/cdn-cgi/l/email-protection#63040602064d020c002304064d000c0e"><span class="__cf_email__" data-cfemail="12757773773c737d715275773c717d7f">[email&#160;protected]</span></a>.
    (4) You may view this service information at FAA, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.
    (5) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
<a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.


    Issued in Burlington, Massachusetts, on March 24, 2017.

Carlos A. Pestana,
Acting Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2017-06715 Filed 4-5-17; 8:45 am]
BILLING CODE 4910-13-P