Airworthiness Directives; General Electric Company Turbofan Engines

[Federal Register Volume 82, Number 86 (Friday, May 5, 2017)]
[Rules and Regulations]
[Pages 21111-21114]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-09039]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0165; Directorate Identifier 2015-NE-02-AD; 
Amendment 39-18868; AD 2017-09-06]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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[[Page 21112]]

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-15-03 for 
all General Electric Company (GE) GEnx turbofan engine models. AD 2015-
15-03 precluded the use of certain electronic engine control (EEC) full 
authority digital engine control (FADEC) software on GEnx turbofan 
engines. This AD requires removing a specific part and replacing it 
with a part eligible for installation and specifying the EEC FADEC 
software version for the affected GEnx turbofan engines. This AD was 
prompted by GE implementing final design changes that remove the unsafe 
condition. We are issuing this AD to correct the unsafe condition on 
these products.

DATES: This AD is effective June 9, 2017.

ADDRESSES: For service information identified in this final rule, 
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, 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-2015-
0165; 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: Christopher McGuire, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7120; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2015-15-03, Amendment 39-18212 (80 FR 42707, 
July 20, 2015), (``AD 2015-15-03''). AD 2015-15-03 applied to all GE 
GEnx turbofan engine models. The NPRM published in the Federal Register 
on November 3, 2016 (81 FR 76540). The NPRM was prompted by GE 
implementing final design changes that remove the unsafe condition. The 
NPRM proposed to remove a specific part and replace it with a part 
eligible for installation and specify the EEC FADEC software version 
for the affected GEnx turbofan engines. We are issuing this AD to 
prevent engine failure, loss of thrust control, and damage to the 
airplane.

Comments

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

Request To Change Compliance

    The Boeing Company and GE requested that we amend paragraph (f) to 
clarify which software versions are prohibited from being installed. 
They stated that the listed software versions do not contain the 
highest level of ice crystal icing (ICI) accommodation.
    We agree. We revised this AD because the listed software versions 
do not contain the highest level of ICI accommodation features. Also, 
the change requested makes the prohibition statement consistent with 
the AD removal requirements.

Request To Add Terminating Action

    The Boeing Company requested that we add compliance to this AD as a 
terminating action to AD 2013-24-01, Amendment 39-17675 (78 FR 70851, 
November 27, 2013), (``AD 2013-24-01'') since it removes the unsafe 
condition.
    We partially agree. We agree that complying with this AD is 
terminating action for certain requirements of AD 2013-24-01. 
Therefore, we added a new terminating action paragraph (h) of this AD. 
Since complying with this AD is terminating action to certain 
requirements of AD 2013-24-01, we disagree that complying with this AD 
is terminating action for all requirements of AD 2013-24-01.

Request To Add Terminating Action

    The Boeing Company requests that 747-8 and 747-8F aircraft with 
GEnx-2B engines that are operating with software, version C075, be 
granted a relaxation of the requirements in paragraphs (g) and (h) of 
AD 2013-24-01. They stated that an alternative method of compliance 
(AMOC) exists that grants a relaxation of the requirements of 
paragraphs (g) and (h) of AD 2013-24-01 as long as the aircraft engines 
have the required software versions.
    We disagree. Although Transport Airplane Directorate issued 
aircraft level AD 2013-24-01 and granted an AMOC, those are interim 
actions. Complying with this AD is required to remove the unsafe 
condition and is terminating action to certain requirements of AD 2013-
24-01. We did not change this AD.

Request To Revise a Definition

    GE requested that we revise the definition of an engine shop visit. 
They suggested that we add ``Workscopes involving only externals, 
including transfer gearbox (TGB) and accessory gearbox (AGB) do not 
constitute an engine shop visit for the purpose of this AD.''
    We disagree. The definition of a shop visit as ``the induction of 
an engine into the shop for maintenance involving the separation of 
pairs of major mating engine case flanges'' is a standard industry 
definition. Workscopes involving the TGB/AGB, or externals, do not 
separate major mating engine case flanges and do not constitute an 
engine shop visit for the purpose of this AD. We did not change this 
AD.

Request To Change Compliance Time

    Cathay Pacific Airways Limited requested that we clarify which 
parts may be installed into the engine.
    We disagree. The FAA does not intend to specify which parts may be 
installed into the engine, only those parts that may not be installed 
into the engine. Specifying which parts are eligible for installation 
may inadvertently prohibit new parts that are introduced from being 
installed into the engine. We did not change this AD.

Agreement With the Proposed AD

    The Air Line Pilots Association expressed agreement with this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously. We determined that the 
changes we made as the result of the comments we received:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic

[[Page 21113]]

burden on any operator or increase the scope of this AD.

Related Service Information

    We reviewed GE GEnx-2B Service Bulletin (SB) 72-0241 R00, dated 
March 16, 2016 that describes removal and installation procedures of 
fan hub stator assembly booster outlet guide vane; GE GEnx-2B SB 73-
0041 R00, dated July 2, 2015 that describes reprogramming procedures 
for EEC FADEC software, version C075; and GE GEnx-1B SB 73-0044 R00, 
dated July 1, 2015 that describes reprograming procedures for EEC FADEC 
software, version B185.

Costs of Compliance

    We estimate that this AD affects 130 engines installed on airplanes 
of U.S. registry. We estimate that it would take about 1 hour per 
engine to comply with the software installation required by this AD. We 
also estimate that 32 engines would require hardware replacement, which 
would take about 60 hours per engine. Required parts cost about 
$390,000 per engine. The average labor rate is $85 per hour. Based on 
these figures, we estimate the cost of this AD on U.S. operators to be 
$12,654,250.

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 have determined that 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 removing Airworthiness Directive (AD) 
2015-15-03, Amendment 39-18212 (80 FR 42707, July 20, 2015), and adding 
the following new AD:

2017-09-06: General Electric Company: Amendment 39-18868; Docket No. 
FAA-2015-0165; Directorate Identifier 2015-NE-02-AD.

(a) Effective Date

    This AD is effective June 9, 2017.

(b) Affected ADs

    This AD replaces AD 2015-15-03, Amendment 39-18212 (80 FR 42707, 
July 20, 2015). This AD also affects AD 2013-24-01, Amendment 39-
17675 (78 FR 70851, November 27, 2013).

(c) Applicability

    This AD applies to all General Electric Company (GE) GEnx-1B and 
GEnx-2B turbofan engines.

(d) Unsafe Condition

    This AD was prompted by GE implementing final design changes 
that remove the unsafe condition. We are issuing this AD to prevent 
engine failure, loss of thrust control, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Thirty days after the effective date of this AD, do not 
operate any GE GEnx-1B engine with electronic engine control (EEC) 
full authority digital engine control (FADEC) software, version B180 
or earlier, installed.
    (2) Thirty days after the effective date of this AD, do not 
operate any GE GEnx-2B engine with EEC FADEC software, version C068 
or earlier, installed.
    (3) At the next shop visit after the effective date of this AD, 
remove from service all GE GEnx-2B67, -2B67B, and -2B67/P fan hub 
stator assembly booster outlet guide vanes, part number B1316-00720, 
and replace with a part eligible for installation.

(f) Installation Prohibition

    After removing any software, version B180 or earlier, for the GE 
GEnx-1B engines; or software, version C068 or earlier, for the GE 
GEnx-2B engines, do not operate those engines with any software, 
version B180 or C068, or earlier.

(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 for 
the following situations which do not constitute an engine shop 
visit:
    (1) Separation of engine flanges solely for the purposes of 
transportation without subsequent maintenance does not constitute an 
engine shop visit.
    (2) Separation of engine flanges solely for the purpose of 
replacing the fan or propulsor without subsequent maintenance does 
not constitute an engine shop visit.

(h) Terminating Action

    Compliance with this AD, for all engines installed on a specific 
airplane, is a terminating action to AD 2013-24-01 for that specific 
airplane, since it removes the unsafe condition on that specific 
airplane.
    (1) For GEnx-1B engines:
    (i) Compliance with paragraphs (e)(1) and (f) of this AD, for 
all engines on an airplane, is an approved terminating action for 
that airplane for paragraphs (g) and (i) of AD 2013-24-01.
    (ii) Note that paragraph (j) of AD 2013-24-01, which contains 
post-event inspection requirements, remains in force.
    (2) For GEnx-2B engines:
    (i) Compliance with paragraphs (e)(2), (e)(3), and (f) of this 
AD, for all engines on an airplane, is an approved terminating 
action for that airplane for paragraphs (g) and (h) of AD 2013-24-
01.
    (ii) Note that paragraph (j) of AD 2013-24-01, which contains 
post-event inspection requirements, remains in force.

(i) 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].

(j) Related Information

    (1) For more information about this AD, contact Christopher 
McGuire, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7120; fax: 781-238-7199; email: 
[email protected].

[[Page 21114]]

    (2) GE GEnx-2B Service Bulletin (SB) 72-0241 R00, dated March 
16, 2016; GE GEnx-2B SB 73-0041 R00, dated July 2, 2015; and GE 
GEnx-1B SB 73-0044 R00, dated July 1, 2015 can be obtained from GE, 
using the contact information in paragraph (j)(3) of this AD.
    (3) For service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: [email protected].

    Issued in Burlington, Massachusetts, on April 27, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-09039 Filed 5-4-17; 8:45 am]
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