
[Federal Register Volume 82, Number 71 (Friday, April 14, 2017)]
[Rules and Regulations]
[Pages 17933-17936]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07476]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7491; Directorate Identifier 2015-NE-39-AD; 
Amendment 39-18854; AD 2017-08-05]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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[[Page 17934]]

SUMMARY: We are superseding Airworthiness Directive (AD) 2016-13-05 for 
all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-
90B, and GE90-94B turbofan engines. AD 2016-13-05 required eddy current 
inspection (ECI) of the high-pressure compressor (HPC) stage 8-10 spool 
at each shop visit for all affected engines and ECI or ultrasonic 
inspection (USI) for certain affected engines. This new AD requires 
initial and repetitive on-wing USIs of the HPC stage 8-10 spool for 
certain engines prior to shop visit and ECI of all affected engines at 
each shop visit. This AD was prompted by analysis that the risk of the 
failure of an HPC stage 8-10 spool was excessive without repetitive USI 
prior to shop visit. We are issuing this AD to correct the unsafe 
condition on these products.

DATES: This AD is effective May 19, 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; fax: 513-552-3329; email: 
geae.aoc@ge.com. 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-
7491; 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: 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: john.frost@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2016-13-05, Amendment 39-18569 (81 FR 41208, 
June 24, 2016; corrected 81 FR 42475, June 30, 2016), (``AD 2016-13-
05''). AD 2016-13-05 applied to all GE GE90-76B, GE90-77B, GE90-85B, 
GE90-90B, and GE90-94B turbofan engines. The NPRM published in the 
Federal Register on December 19, 2016 (81 FR 91880). The NPRM was 
prompted by an uncontained failure of the HPC stage 8-10 spool, leading 
to an airplane fire. The NPRM proposed to require an ECI or USI of the 
HPC stage 8-10 spool and removing from service those parts that fail 
inspection. We are issuing this AD to prevent failure of the HPC stage 
8-10 spool, uncontained rotor release, damage to the engine, 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 Revise Compliance

    The Boeing Company (Boeing) and GE requested paragraph (f)(1)(i) be 
changed to apply to ECIs performed between January 2016 and July 29, 
2016. Boeing and GE stated that operators who performed an ECI between 
January 2016 and July 29, 2016 are in accordance with GE GE90 Service 
Bulletin (SB) 72-1151, Initial issue or Revision 1.
    We agree. Credit should be given for ECIs performed in accordance 
with GE GE90 SB 72-1151, Initial issue or Revision 1. We added 
paragraph (f)(2)(iii) to the Compliance section.

Request To Revise Compliance Time

    Boeing and GE requested paragraph (f)(1)(ii) be changed to state 
that if it has been more than 400 cycles since the qualified initial 
USI inspection, then, inspect within 100 cycles from the effective date 
of this AD. Boeing and GE stated that this provides the operators with 
a reasonable amount of time to perform the USI.
    We disagree. The date for the initial inspection was based on the 
effective date of AD 2016-13-05. The USI requirement is unchanged, so 
the 500 cycle allowance mandated in AD 2016-13-05 is also mandated by 
this AD. We did not change this AD.

Request To Revise Service Information

    Boeing, GE, and Japan Air Lines (JAL) requested updating the 
Related Information section to reflect the latest version of the GE SB. 
GE SB 72-1151 was revised to Revision 01 on September 13, 2016 and 
includes the most recent details and aligns with this AD.
    We agree. GE GE90 SB 72-1151, Revision 01, dated September 13, 
2016, includes the most recent details, aligns with this AD, and also 
meets the risk analysis performed. We added GE GE90 SB 72-1151, 
Revision 01, dated September 13, 2016 and GE GE90 SB 72-1151, Revision 
0, dated June 10, 2016 to paragraph (i)(2) of this AD.

Request To Revise Service Information

    JAL requested updating paragraph (i)(2) Related Information, to 
perform an ECI in accordance with future revisions of the service 
information. JAL also requested updating paragraph (i)(2) Related 
Information, to add ``and later'' to the revision number relating to 
Chapter 72-31-08; Special Procedure 003 and 72-00-31 Special Procedure 
006 in GE GE90 Engine Manual, GEK100700, Revision 68, dated September 
1, 2016.
    We disagree. We are only authorized to mandate use of service 
information that we have reviewed and which are published. Since future 
revisions of service information are not yet published, we are not 
authorized to mandate their use. We did not change 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 have determined that 
these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM, for correcting the unsafe condition; and
     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 burden on any operator or increase the scope of this AD.

Related Service Information

    We reviewed GE GE90 SB 72-1151, Revision 01, dated September 13, 
2016. The SB describes procedures for an on-wing USI of the stage 8 web 
of the stage 8-10 spool. 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.
    We also reviewed Chapter 72-31-08, Special Procedures 003; and 
Chapter 72-00-31, Special Procedures 006, in the GE GE90 Engine Manual, 
GEK100700, Revision 68, dated

[[Page 17935]]

September 1, 2016. These procedures describe how to perform ECI of the 
stage 8 aft web of the stage 8-10 spool.

Interim Action

    We consider this AD interim action. GE is determining the root 
cause for the unsafe condition identified in this AD. Once a root cause 
is determined, we will consider additional rulemaking.

Costs of Compliance

    We estimate that this AD affects 54 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
        Action                  Labor cost             Parts cost       Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspection............  7 work-hours x $85 per                  $0   $595 per inspection    $32,130 per
                         hour = $595 per                              cycle.                 inspection cycle.
                         inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of engines that might need this 
replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of spool......................  0 work-hours x $85 per hour = $0..        $780,000         $780,000
----------------------------------------------------------------------------------------------------------------

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 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 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) 
2016-13-05, Amendment 39-18569 (81 FR 41208, June 24, 2016; corrected 
81 FR 42475, June 30, 2016), and adding the following new AD:

2017-08-05 General Electric Company: Amendment 39-18854; Docket No. 
FAA-2015-7491; Directorate Identifier 2015-NE-39-AD

(a) Effective Date

    This AD is effective May 19, 2017.

(b) Affected ADs

    This AD replaces AD 2016-13-05, Amendment 39-18569 (81 FR 41208, 
June 24, 2016; corrected June 30, 2016, 81 FR 42475).

(c) Applicability

    This AD applies to General Electric Company (GE) GE90-76B, GE90-
77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with a high-
pressure compressor (HPC) stage 8-10 spool, part numbers (P/Ns) 
1694M80G04, 1844M90G01, or 1844M90G02, installed.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an uncontained failure of the HPC stage 
8-10 spool. We are issuing this AD to prevent failure of the HPC 
stage 8-10 spool, uncontained rotor release, damage to the engine, 
and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For HPC stage 8-10 spool, P/N 1694M80G04, all serial numbers 
(S/Ns), or HPC stage 8-10 spool, P/N 1844M90G01 or 1844M90G02, with 
a S/N listed in Figure 1 to paragraph (f) of this AD; perform an on-
wing ultrasonic inspection (USI) of the stage 8 aft web upper face 
as follows:
    (i) Perform an initial USI after reaching 8,000 cycles since new 
(CSN), but, before exceeding 9,000 CSN, or within 500 cycles in 
service after July 29, 2016, whichever occurs later.
    (ii) Thereafter, perform a USI of the stage 8 aft web upper face 
every 500 cycles since last inspection.

[[Page 17936]]

    (iii) Compliance with paragraph (f)(2)(i) or (f)(2)(iii) of this 
AD is terminating action for the initial and repetitive USIs 
specified by paragraphs (f)(1)(i) and (ii) of this AD.

                                                  Figure 1 to Paragraph (f)--HPC Stage 8-10 Spool S/Ns
--------------------------------------------------------------------------------------------------------------------------------------------------------
 
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            Part Nos.                                                                   Serial Nos.
--------------------------------------------------------------------------------------------------------------------------------------------------------
1844M90G01......................  GWN005MF                GWNBK753                GWNBS077                GWNBS497                GWNBS724
                                  GWN005MG                GWNBK754                GWNBS078                GWNBS499                GWNBS794
                                  GWN0087M                GWNBK841                GWNBS079                GWNBS500                GWNBS810
                                  GWN0087N                GWNBK842                GWNBS080                GWNBS501                GWNBS811
                                  GWN00DGK                GWNBK843                GWNBS081                GWNBS502                GWNBS812
                                  GWN00DGL                GWNBK844                GWNBS157                GWNBS609                GWNBS813
                                  GWNBJ992                GWNBK952                GWNBS158                GWNBS610                GWNBS814
                                  GWNBK667                GWNBK953                GWNBS159                GWNBS611                GWNBS910
                                  GWNBK674                GWNBK954                GWNBS160                GWNBS612                GWNBS911
                                  GWNBK675                GWNBK955                GWNBS266                GWNBS613                GWNBS912
                                  GWNBK743                GWNBK956                GWNBS267                GWNBS614                GWNBS914
                                  GWNBK744                GWNBK957                GWNBS268                GWNBS721                GWNBS915
                                  GWNBK751                GWNBK958                GWNBS269                GWNBS722                GWNBS982
                                  GWNBK752                GWNBK959                GWNBS270                GWNBS723                GWNBS983
1844M90G02......................  GWN00C2T                GWN01C5N                GWN02N8D                GWN03RTM                GWN04E21
                                  GWN00C2V                GWN01GE2                GWN02T3R                GWN03RTP                GWN04GHT
                                  GWN00G2N                GWN01GE3                GWN02WGM                GWN040RL                GWN04GHW
                                  GWN00G2P                GWN01GE4                GWN0311K                GWN040RM                GWN04GJ0
                                  GWN00PFP                GWN01GE6                GWN035PP                GWN040RN                GWN04JW6
                                  GWN00PFR                GWN01WH1                GWN038TD                GWN040RP                GWN04JW7
                                  GWN00T2N                GWN02688                GWN039TG                GWN04202                GWN04JW8
                                  GWN00YHV                GWN02689                GWN03G2R                GWN0435W                GWN04L7K
                                  GWN0125G                GWN0268A                GWN03G2W                GWN04360                GWN04L7L
                                  GWN0125H                GWN02DP2                GWN03G30                GWN04361                GWN04MT7
                                  GWN0166K                GWN02DP3                GWN03JPC                GWN04362                GWN04MT8
                                  GWN01C5K                GWN02F9F                GWN03JPD                GWN04ATG                GWNBS984
                                  GWN01C5L                GWN02F9G                GWN03N8P                GWN04ATH
                                  GWN01C5M                GWN02L9T                GWN03N8R                GWN04E20
--------------------------------------------------------------------------------------------------------------------------------------------------------

    (2) For all HPC stage 8-10 spools, P/N 1694M80G04, 1844M90G01, 
or 1844M90G02, perform an eddy current inspection (ECI) of the stage 
8 aft upper face as follows:
    (i) Perform an initial ECI of the stage 8 aft web upper face at 
the next shop visit after the effective date of this AD.
    (ii) Thereafter, perform an ECI of the stage 8 aft web upper 
face at each subsequent shop visit.
    (iii) If you performed an ECI of the stage 8 aft web upper 
surface before the effective date of the AD, you met the 
requirements of paragraph (f)(2)(i) of this AD.
    (3) Remove from service any HPC stage 8-10 spool that fails the 
inspection required by paragraphs (f)(1) or (2) of this AD, and 
replace with a spool 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 during which 
the compressor discharge pressure seal face is exposed.

(h) 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: ANE-AD-AMOC@faa.gov.

(i) Related Information

    (1) For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine Certification Office, FAA, 1200 District 
Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-
7199; email: john.frost@faa.gov.
    (2) GE GE90 Service Bulletin (SB) 72-1151, Revision 01, dated 
September 13, 2016; GE GE90 SB 72-1151, Revision 0, dated June 10, 
2016; Chapter 72-31-08, Special Procedures 003; and Chapter 72-00-
31, Special Procedures 006, in GE GE90 Engine Manual, GEK100700, 
Revision 68, dated September 1, 2016, can be obtained from GE using 
the contact information in paragraph (i)(3) of this AD. These SBs 
describe procedures for an on-wing USI of the stage 8 web of the 
stage 8-10 spool. These engine manual procedures describe how to 
perform ECI of the stage 8 aft web of the stage 8-10 spool.
    (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; fax: 513-552-3329; email: 
geae.aoc@ge.com.
    (4) 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.

(j) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on April 5, 2017.
Carlos A. Pestana,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-07476 Filed 4-13-17; 8:45 am]
BILLING CODE 4910-13-P


