81_FR_9789 81 FR 9751 - Airworthiness Directives; General Electric Company Turbofan Engines

81 FR 9751 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 38 (February 26, 2016)

Page Range9751-9753
FR Document2016-04031

We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 turbofan engine models. This AD was prompted by reports of two separate, single engine in-flight shutdowns (IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade failure. This AD requires inspection and conditional removal of affected HPT rotor stage 1 blades. 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.

Federal Register, Volume 81 Issue 38 (Friday, February 26, 2016)
[Federal Register Volume 81, Number 38 (Friday, February 26, 2016)]
[Rules and Regulations]
[Pages 9751-9753]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-04031]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2984; Directorate Identifier 2015-NE-21-AD; 
Amendment 39-18405; AD 2016-04-11]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
General Electric Company (GE) GEnx-1B54, -1B58, -1B64, -1B67, and -1B70 
turbofan engine models. This AD was prompted by reports of two 
separate, single engine in-flight shutdowns

[[Page 9752]]

(IFSDs) caused by high-pressure turbine (HPT) rotor stage 1 blade 
failure. This AD requires inspection and conditional removal of 
affected HPT rotor stage 1 blades. 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.

DATES: This AD is effective April 1, 2016.

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 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 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 by adding an AD that would apply to all GE GEnx-1B54, -1B58, -
1B64, -1B67, and -1B70 turbofan engine models. The NPRM published in 
the Federal Register on August 27, 2015 (80 FR 51965). The NPRM was 
prompted by reports of two separate, single engine IFSDs caused by HPT 
rotor stage 1 blade failure. The NPRM proposed to require inspection 
and conditional removal of affected HPT rotor stage 1 blades. We are 
issuing this AD to correct the unsafe condition that 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.

Comments

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

Support for the NPRM

    The National Transportation Safety Board (NTSB) expressed support 
for the NPRM (80 FR 51965).

Request To Change Applicability

    United Airlines (United) requested that the Applicability paragraph 
be changed to more appropriately address engine models. United stated 
that the GEnx-1B54 and GEnx-1B58 be removed and GEnx-1B64G03, 1B64G04, 
1B67G03, 1B67G04, 1B70G03 and 1B70G04 be added to paragraph (c) 
Applicability. United indicated this change would improve clarity and 
accomplishment of the AD.
    We disagree. This AD applies to all GE GEnx-1B54, -1B58, -1B64, -
1B67, and -1B70 turbofan engine models, as listed in the GEnx type 
certificate data sheet. We did not change this AD.

Request To Change Compliance

    United requested that the Compliance paragraph be changed to 
clarify maintenance actions. United requested that in paragraph (e) the 
phrase, `` . . . remove the cracked blade'' be changed to read, `` . . 
. remove the engine containing the cracked blade.'' United reasoned 
that removing the cracked blade is not a maintenance option.
    We partially agree. We agree with changing the compliance language 
to include disposition of a cracked blade. We disagree with using the 
phrase, `` . . . remove the engine containing the cracked blade'' 
because removal of the cracked blade addresses the unsafe condition.
    We revised paragraphs (e)(1)(i) and (e)(1)(ii) of this AD to 
include, `` . . . remove the cracked blade from service. . . .''

Request To Change the Summary and Unsafe Condition

    Boeing and General Electric Company (GE) requested that the Summary 
and Unsafe Condition paragraphs be clarified to reflect that two 
separate, single engine IFSDs occurred, prompting the need for this AD.
    We agree. We changed the Summary and Unsafe Condition paragraphs of 
this AD to read: ``This AD was prompted by reports of two separate, 
single engine in-flight shutdowns, caused by HPT rotor stage 1 blade 
failure. . . .''

Request To Change the Cost of Compliance

    Boeing requested that the Costs of Compliance paragraph 
specifically state that the projected costs are for only the initial 
inspection and not for repetitive inspections. Boeing indicated this is 
needed to clarify the cost of compliance.
    We agree. We changed the Costs of Compliance paragraph of this AD 
to include, ``We also estimate that it will take about 1 hour per 
engine to comply with the initial inspection in this AD.''

Request To Change Compliance Time

    Japan Airlines (JAL) and GE suggested that in paragraph (e)(1) 
Compliance, the need to inspect within 1,000 cycles since new (CSN) may 
not be representative of the fleet.
    We disagree. The initial blade inspection compliance time was based 
on the safety evaluation of the known failures. Any person may make a 
request for an Alternative Method of Compliance (AMOC) to the 
compliance times of this AD using the procedures listed herein. We did 
not change this AD.

Request To Change Compliance

    GE requested that the Compliance paragraph be changed to clarify 
that the criteria of multiple cracks should be based on an individual 
blade and not multiple blades, each with a single crack.
    We agree. We changed paragraph (e)(1)(i) of this AD to read: ``. . 
. , or if more than one axial crack of any length is found on one 
blade, remove the cracked blade from service before further flight.''

Revision to Service Information

    We revised the service information in the Related Information 
section of this AD to Revision 01 of GE GEnx-1B Service Bulletin (SB) 
No. 72-0267 R01, dated August 10, 2015. GE made an editorial change to 
this SB that did not affect its contents.

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 (80 FR 51965) for correcting the unsafe condition; and

[[Page 9753]]

     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 51965).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD will affect 4 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 1 
hour per engine to comply with the initial inspection in this AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the total cost of this AD to U.S. operators to be $340.

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 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):

2016-04-11 General Electric Company: Amendment 39-18405; Docket No. 
FAA-2015-2984; Directorate Identifier 2015-NE-21-AD.

(a) Effective Date

    This AD is effective April 1, 2016.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Unsafe Condition

    This AD was prompted by reports of two separate, single engine 
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) 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 after the effective date of this AD, whichever occurs 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 on one blade, remove the cracked blade from service 
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 
from service within 10 blade cycles.
    (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 
paragraphs (e)(1)(i) through (e)(1)(v) of this AD, 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, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7120; fax: 781-238-7199; email: 
[email protected].
    (2) GE GEnx-1B Service Bulletin No. 72-0267 R01, dated August 
10, 2015 can be obtained from GE using the contact information in 
paragraph (h)(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].
    (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.

    Issued in Burlington, Massachusetts, on February, 18, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04031 Filed 2-25-16; 8:45 am]
BILLING CODE 4910-13-P



                                                                   Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations                                              9751

                                                   (ii) Either an ultrasonic inspection or a            (j) Post-Modification Inspections and                 Airframe Branch, ANM–120S, FAA, Seattle
                                                surface HFEC inspection for cracks                      Corrective Action                                     ACO, 1601 Lind Avenue SW., Renton, WA
                                                (depending on the location of the scribe                   At the applicable time specified in                98057–3356; phone: 425–917–6412; fax: 425–
                                                line(s)) of any skin panel common to a                  paragraph 1.E., ‘‘Compliance,’’ of Boeing             917–6590; email: Eric.Lin@faa.gov.
                                                stringer S–14 L/R lap splice between fuselage           Alert Service Bulletin 777–53A0052, dated             (m) Material Incorporated by Reference
                                                station 655 and station 1434 that has a scribe          October 10, 2014: Do a post-modification
                                                line 0.001 inch or deeper.                              internal surface HFEC inspection for skin                (1) The Director of the Federal Register
                                                   (iii) An external phased array ultrasonic            cracks in the modified lap splices on both            approved the incorporation by reference
                                                inspection for cracks in the lower/overlapped           sides of the airplane; and do all applicable          (IBR) of the service information listed in this
                                                skin of the stringer S–14 L/R lap splices               corrective actions; in accordance with the            paragraph under 5 U.S.C. 552(a) and 1 CFR
                                                between fuselage station 655 and station                Accomplishment Instructions of Boeing Alert           part 51.
                                                                                                        Service Bulletin 777–53A0052, dated October              (2) You must use this service information
                                                1434.
                                                                                                        10, 2014, except as provided by paragraph             as applicable to do the actions required by
                                                   (iv) An open hole HFEC inspection for skin
                                                                                                        (h)(2) of this AD. Do all applicable corrective       this AD, unless the AD specifies otherwise.
                                                cracks at the upper and lower fastener rows
                                                                                                        actions before further flight. Repeat the                (i) Boeing Alert Service Bulletin 777–
                                                of the stringer S–14 L/R lap splices.                                                                         53A0052, dated October 10, 2014.
                                                   (3) Inspection ‘‘C’’ includes the inspections        inspection of the modified lap splices
                                                                                                        thereafter at the applicable intervals specified         (ii) Reserved.
                                                for scribe lines and cracks specified in                                                                         (3) For Boeing service information
                                                paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of    in paragraph 1.E., ‘‘Compliance,’’ of Boeing
                                                                                                        Alert Service Bulletin 777–53A0052, dated             identified in this AD, contact Boeing
                                                this AD on stringer S–14 L/R lap splice                                                                       Commercial Airplanes, Attention: Data &
                                                                                                        October 10, 2014.
                                                between fuselage station 655 and station                                                                      Services Management, P.O. Box 3707, MC
                                                1434 on both sides of the airplane.                     (k) Alternative Methods of Compliance                 2H–65, Seattle, WA 98124–2207; telephone
                                                   (i) A detailed inspection for scribe lines. If       (AMOCs)                                               206–544–5000, extension 1; fax 206–766–
                                                any scribe line is found during the inspection             (1) The Manager, Seattle Aircraft                  5680; Internet https://
                                                required by this paragraph, the actions                 Certification Office (ACO), FAA, has the              www.myboeingfleet.com.
                                                include the inspections specified in                    authority to approve AMOCs for this AD, if               (4) You may view this service information
                                                paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this        requested using the procedures found in 14            at FAA, Transport Airplane Directorate, 1601
                                                AD.                                                     CFR 39.19. In accordance with 14 CFR 39.19,           Lind Avenue SW., Renton, WA. For
                                                   (A) A detailed inspection for cracks of the          send your request to your principal inspector         information on the availability of this
                                                scribe line area(s).                                    or local Flight Standards District Office, as         material at the FAA, call 425–227–1221.
                                                   (B) Either an ultrasonic inspection or a             appropriate. If sending information directly             (5) You may view this service information
                                                surface HFEC inspection for cracks                      to the manager of the ACO, send it to the             that is incorporated by reference at the
                                                (depending on the location of the scribe                attention of the person identified in                 National Archives and Records
                                                line(s)).                                               paragraph (l) of this AD. Information may be          Administration (NARA). For information on
                                                   (ii) An external phased array ultrasonic             emailed to: 9-ANM-Seattle-ACO-AMOC-                   the availability of this material at NARA, call
                                                inspection for cracks in the lower/overlapped           Requests@faa.gov.                                     202–741–6030, or go to: http://
                                                skin of the stringer S–14 L/R lap splices                  (2) Before using any approved AMOC,                www.archives.gov/federal-register/cfr/ibr-
                                                between fuselage station 655 and station                notify your appropriate principal inspector,          locations.html.
                                                1434.                                                   or lacking a principal inspector, the manager
                                                                                                                                                                Issued in Renton, Washington, on February
                                                   (iii) An open hole HFEC inspection for skin          of the local flight standards district office/
                                                                                                                                                              16, 2016.
                                                cracks at the upper and lower fastener rows             certificate holding district office.
                                                                                                           (3) An AMOC that provides an acceptable            Dionne Palermo,
                                                of the stringer S–14 L/R lap splices.                                                                         Acting Manager,
                                                                                                        level of safety may be used for any repair,
                                                (h) Exceptions to Service Information                   modification, or alteration required by this            Transport Airplane Directorate, Aircraft
                                                Specifications                                          AD if it is approved by the Boeing                    Certification Service.
                                                  (1) Where Paragraph 1.E., ‘‘Compliance,’’ of          Commercial Airplanes Organization                     [FR Doc. 2016–03886 Filed 2–25–16; 8:45 am]
                                                Boeing Alert Service Bulletin 777–53A0052,              Designation Authorization (ODA) that has              BILLING CODE 4910–13–P
                                                dated October 10, 2014, specifies a                     been authorized by the Manager, Seattle
                                                                                                        ACO, to make those findings. To be
                                                compliance time ‘‘after the original issue date
                                                                                                        approved, the repair method, modification
                                                of this service bulletin,’’ this AD requires                                                                  DEPARTMENT OF TRANSPORTATION
                                                                                                        deviation, or alteration deviation must meet
                                                compliance within the specified compliance
                                                                                                        the certification basis of the airplane, and the
                                                time ‘‘after the effective date of this AD.’’                                                                 Federal Aviation Administration
                                                                                                        approval must specifically refer to this AD.
                                                  (2) If, during accomplishment of any
                                                                                                           (4) Except as required by paragraph (h)(2)
                                                inspection required by this AD, any                     of this AD: For service information that              14 CFR Part 39
                                                condition is found for which Boeing Alert               contains steps that are labeled as Required
                                                Service Bulletin 777–53A0052, dated October                                                                   [Docket No. FAA–2015–2984; Directorate
                                                                                                        for Compliance (RC), the provisions of                Identifier 2015–NE–21–AD; Amendment 39–
                                                10, 2014, specifies to contact Boeing for               paragraphs (k)(4)(i) and (k)(4)(ii) apply.
                                                special repair instructions or supplemental                                                                   18405; AD 2016–04–11]
                                                                                                           (i) The steps labeled as RC, including
                                                instructions for the modification, and                  substeps under an RC step and any figures             RIN 2120–AA64
                                                specifies that action as ‘‘RC’’ (Required for           identified in an RC step, must be done to
                                                Compliance): Before further flight, do the              comply with the AD. An AMOC is required               Airworthiness Directives; General
                                                repair or modification using a method                   for any deviations to RC steps, including             Electric Company Turbofan Engines
                                                approved in accordance with the procedures              substeps and identified figures.
                                                specified in paragraph (k) of this AD.                     (ii) Steps not labeled as RC may be                AGENCY:  Federal Aviation
                                                (i) Lap Splice Modification                             deviated from using accepted methods in               Administration (FAA), DOT.
                                                                                                        accordance with the operator’s maintenance            ACTION: Final rule.
                                                  At the applicable time specified in                   or inspection program without obtaining
mstockstill on DSK4VPTVN1PROD with RULES




                                                paragraph 1.E., ‘‘Compliance,’’ of Boeing               approval of an AMOC, provided the RC steps,           SUMMARY:  We are adopting a new
                                                Alert Service Bulletin 777–53A0052, dated               including substeps and identified figures, can
                                                October 10, 2014: Do the left-side and right-
                                                                                                                                                              airworthiness directive (AD) for all
                                                                                                        still be done as specified, and the airplane          General Electric Company (GE) GEnx–
                                                side lap splice modification, in accordance             can be put back in an airworthy condition.
                                                with the Accomplishment Instructions of                                                                       1B54, –1B58, –1B64, –1B67, and –1B70
                                                Boeing Alert Service Bulletin 777–53A0052,              (l) Related Information                               turbofan engine models. This AD was
                                                dated October 10, 2014, except as provided                 For more information about this AD,                prompted by reports of two separate,
                                                by paragraph (h)(2) of this AD.                         contact Eric Lin, Aerospace Engineer,                 single engine in-flight shutdowns


                                           VerDate Sep<11>2014   17:33 Feb 25, 2016   Jkt 238001   PO 00000   Frm 00011   Fmt 4700   Sfmt 4700   E:\FR\FM\26FER1.SGM   26FER1


                                                9752              Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations

                                                (IFSDs) caused by high-pressure turbine                 could result in failure of the HPT rotor              AD to read: ‘‘This AD was prompted by
                                                (HPT) rotor stage 1 blade failure. This                 stage 1 blades, which could lead to                   reports of two separate, single engine in-
                                                AD requires inspection and conditional                  failure of one or more engines, loss of               flight shutdowns, caused by HPT rotor
                                                removal of affected HPT rotor stage 1                   thrust control, and damage to the                     stage 1 blade failure. . . .’’
                                                blades. We are issuing this AD to                       airplane.                                             Request To Change the Cost of
                                                prevent failure of the HPT rotor stage 1
                                                                                                        Comments                                              Compliance
                                                blades, which could lead to failure of
                                                one or more engines, loss of thrust                       We gave the public the opportunity to                 Boeing requested that the Costs of
                                                control, and damage to the airplane.                    participate in developing this AD. The                Compliance paragraph specifically state
                                                DATES: This AD is effective April 1,                    following presents the comments                       that the projected costs are for only the
                                                2016.                                                   received on the proposal and the FAA’s                initial inspection and not for repetitive
                                                                                                        response to each comment.                             inspections. Boeing indicated this is
                                                ADDRESSES: For service information                                                                            needed to clarify the cost of compliance.
                                                identified in this final rule, contact                  Support for the NPRM                                    We agree. We changed the Costs of
                                                General Electric Company, GE Aviation,                    The National Transportation Safety                  Compliance paragraph of this AD to
                                                Room 285, 1 Neumann Way, Cincinnati,                    Board (NTSB) expressed support for the                include, ‘‘We also estimate that it will
                                                OH 45215; phone: 513–552–3272; email:                   NPRM (80 FR 51965).                                   take about 1 hour per engine to comply
                                                aviation.fleetsupport@ge.com. You may                                                                         with the initial inspection in this AD.’’
                                                view this service information at the                    Request To Change Applicability
                                                FAA, Engine & Propeller Directorate,                                                                          Request To Change Compliance Time
                                                                                                           United Airlines (United) requested
                                                1200 District Avenue, Burlington, MA                    that the Applicability paragraph be                      Japan Airlines (JAL) and GE suggested
                                                01803. For information on the                           changed to more appropriately address                 that in paragraph (e)(1) Compliance, the
                                                availability of this material at the FAA,               engine models. United stated that the                 need to inspect within 1,000 cycles
                                                call 781–238–7125.                                      GEnx–1B54 and GEnx–1B58 be removed                    since new (CSN) may not be
                                                                                                        and GEnx–1B64G03, 1B64G04,                            representative of the fleet.
                                                Examining the AD Docket                                                                                          We disagree. The initial blade
                                                                                                        1B67G03, 1B67G04, 1B70G03 and
                                                  You may examine the AD docket on                      1B70G04 be added to paragraph (c)                     inspection compliance time was based
                                                the Internet at http://                                 Applicability. United indicated this                  on the safety evaluation of the known
                                                www.regulations.gov by searching for                    change would improve clarity and                      failures. Any person may make a request
                                                and locating Docket No. FAA–2015–                       accomplishment of the AD.                             for an Alternative Method of
                                                2984; or in person at the Docket                           We disagree. This AD applies to all                Compliance (AMOC) to the compliance
                                                Management Facility between 9 a.m.                      GE GEnx–1B54, –1B58, –1B64, –1B67,                    times of this AD using the procedures
                                                and 5 p.m., Monday through Friday,                      and –1B70 turbofan engine models, as                  listed herein. We did not change this
                                                except Federal holidays. The AD docket                  listed in the GEnx type certificate data              AD.
                                                contains this AD, the regulatory                        sheet. We did not change this AD.                     Request To Change Compliance
                                                evaluation, any comments received, and
                                                other information. The address for the                  Request To Change Compliance                             GE requested that the Compliance
                                                Docket Office (phone: 800–647–5527) is                     United requested that the Compliance               paragraph be changed to clarify that the
                                                Document Management Facility, U.S.                                                                            criteria of multiple cracks should be
                                                                                                        paragraph be changed to clarify
                                                Department of Transportation, Docket                                                                          based on an individual blade and not
                                                                                                        maintenance actions. United requested
                                                Operations, M–30, West Building                                                                               multiple blades, each with a single
                                                                                                        that in paragraph (e) the phrase, ‘‘ . . .
                                                Ground Floor, Room W12–140, 1200                                                                              crack.
                                                                                                        remove the cracked blade’’ be changed                    We agree. We changed paragraph
                                                New Jersey Avenue SE., Washington,                      to read, ‘‘ . . . remove the engine
                                                DC 20590.                                                                                                     (e)(1)(i) of this AD to read: ‘‘. . . , or if
                                                                                                        containing the cracked blade.’’ United                more than one axial crack of any length
                                                FOR FURTHER INFORMATION CONTACT:                        reasoned that removing the cracked                    is found on one blade, remove the
                                                Christopher McGuire, Aerospace                          blade is not a maintenance option.                    cracked blade from service before
                                                Engineer, Engine Certification Office,                     We partially agree. We agree with                  further flight.’’
                                                FAA, Engine & Propeller Directorate,                    changing the compliance language to
                                                1200 District Avenue, Burlington, MA                    include disposition of a cracked blade.               Revision to Service Information
                                                01803; phone: 781–238–7120; fax: 781–                   We disagree with using the phrase, ‘‘                    We revised the service information in
                                                238–7199; email: chris.mcguire@faa.gov.                 . . . remove the engine containing the                the Related Information section of this
                                                SUPPLEMENTARY INFORMATION:                              cracked blade’’ because removal of the                AD to Revision 01 of GE GEnx–1B
                                                                                                        cracked blade addresses the unsafe                    Service Bulletin (SB) No. 72–0267 R01,
                                                Discussion
                                                                                                        condition.                                            dated August 10, 2015. GE made an
                                                  We issued a notice of proposed                           We revised paragraphs (e)(1)(i) and                editorial change to this SB that did not
                                                rulemaking (NPRM) to amend 14 CFR                       (e)(1)(ii) of this AD to include, ‘‘ . . .            affect its contents.
                                                part 39 by adding an AD that would                      remove the cracked blade from
                                                apply to all GE GEnx–1B54, –1B58,                       service. . . .’’                                      Conclusion
                                                –1B64, –1B67, and –1B70 turbofan                                                                                We reviewed the relevant data,
                                                engine models. The NPRM published in                    Request To Change the Summary and
                                                                                                                                                              considered the comments received, and
                                                the Federal Register on August 27, 2015                 Unsafe Condition
                                                                                                                                                              determined that air safety and the
                                                (80 FR 51965). The NPRM was                               Boeing and General Electric Company                 public interest require adopting this AD
mstockstill on DSK4VPTVN1PROD with RULES




                                                prompted by reports of two separate,                    (GE) requested that the Summary and                   with the changes described previously.
                                                single engine IFSDs caused by HPT                       Unsafe Condition paragraphs be                        We have determined that these minor
                                                rotor stage 1 blade failure. The NPRM                   clarified to reflect that two separate,               changes:
                                                proposed to require inspection and                      single engine IFSDs occurred,                           • Are consistent with the intent that
                                                conditional removal of affected HPT                     prompting the need for this AD.                       was proposed in the NPRM (80 FR
                                                rotor stage 1 blades. We are issuing this                 We agree. We changed the Summary                    51965) for correcting the unsafe
                                                AD to correct the unsafe condition that                 and Unsafe Condition paragraphs of this               condition; and


                                           VerDate Sep<11>2014   17:33 Feb 25, 2016   Jkt 238001   PO 00000   Frm 00012   Fmt 4700   Sfmt 4700   E:\FR\FM\26FER1.SGM   26FER1


                                                                  Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations                                               9753

                                                  • Do not add any additional burden                    List of Subjects in 14 CFR Part 39                    0.2 inch, inspect the cracked blade within 50
                                                upon the public than was already                                                                              blade cycles since last inspection (CSLI).
                                                                                                          Air transportation, Aircraft, Aviation                 (iv) If an axial crack is found with a length
                                                proposed in the NPRM (80 FR 51965).                     safety, Incorporation by reference,
                                                  We also determined that these                                                                               less than 0.1 inch, inspect the cracked blade
                                                                                                        Safety.                                               within 100 blade CSLI.
                                                changes will not increase the economic
                                                burden on any operator or increase the                  Adoption of the Amendment                                (v) If no cracks were found, perform a BSI
                                                scope of this AD.                                                                                             of the blades within 125 blade CSLI.
                                                                                                          Accordingly, under the authority                       (2) Thereafter, perform a repetitive BSI of
                                                Costs of Compliance                                     delegated to me by the Administrator,                 the convex surface of the HPT rotor stage 1
                                                  We estimate that this AD will affect 4                the FAA amends 14 CFR part 39 as                      blades for axial cracks from the platform to
                                                engines installed on airplanes of U.S.                  follows:                                              30% span within 125 blade CSLI and
                                                registry. We also estimate that it will                                                                       disposition as specified in paragraphs
                                                                                                        PART 39—AIRWORTHINESS
                                                take about 1 hour per engine to comply                                                                        (e)(1)(i) through (e)(1)(v) of this AD, or
                                                                                                        DIRECTIVES                                            remove the blades from service.
                                                with the initial inspection in this AD.
                                                The average labor rate is $85 per hour.                 ■ 1. The authority citation for part 39               (f) Definition
                                                Based on these figures, we estimate the                 continues to read as follows:
                                                total cost of this AD to U.S. operators to                                                                       For the purpose of this AD, a ‘‘blade cycle’’
                                                                                                            Authority: 49 U.S.C. 106(g), 40113, 44701.        is defined as the number of engine cycles that
                                                be $340.
                                                                                                                                                              a set of rotor blades has accrued, regardless
                                                Authority for This Rulemaking                           § 39.13   [Amended]                                   of the engine(s) in which they have operated.
                                                   Title 49 of the United States Code                   ■ 2. The FAA amends § 39.13 by adding                 (g) Alternative Methods of Compliance
                                                specifies the FAA’s authority to issue                  the following new airworthiness                       (AMOCs)
                                                rules on aviation safety. Subtitle I,                   directive (AD):
                                                                                                                                                                The Manager, Engine Certification Office,
                                                section 106, describes the authority of                 2016–04–11 General Electric Company:                  FAA, may approve AMOCs to this AD. Use
                                                the FAA Administrator. Subtitle VII:                        Amendment 39–18405; Docket No.
                                                                                                                                                              the procedures found in 14 CFR 39.19 to
                                                Aviation Programs, describes in more                        FAA–2015–2984; Directorate Identifier
                                                                                                                                                              make your request. You may email your
                                                detail the scope of the Agency’s                            2015–NE–21–AD.
                                                                                                                                                              request to: ANE-AD-AMOC@faa.gov.
                                                authority.                                              (a) Effective Date
                                                   We are issuing this rulemaking under                                                                       (h) Related Information
                                                                                                          This AD is effective April 1, 2016.
                                                the authority described in Subtitle VII,                                                                         (1) For more information about this AD,
                                                Part A, Subpart III, Section 44701:                     (b) Affected ADs                                      contact Christopher McGuire, Aerospace
                                                ‘‘General requirements.’’ Under that                      None.                                               Engineer, Engine Certification Office, FAA,
                                                section, Congress charges the FAA with                  (c) Applicability                                     Engine & Propeller Directorate, 1200 District
                                                promoting safe flight of civil aircraft in                                                                    Avenue, Burlington, MA 01803; phone: 781–
                                                air commerce by prescribing regulations                    This AD applies to all General Electric
                                                                                                                                                              238–7120; fax: 781–238–7199; email:
                                                                                                        Company (GE) GEnx–1B54, –1B58, –1B64,
                                                for practices, methods, and procedures                  –1B67, and –1B70 turbofan engine models               chris.mcguire@faa.gov.
                                                the Administrator finds necessary for                   with high-pressure turbine (HPT) rotor stage             (2) GE GEnx–1B Service Bulletin No. 72–
                                                safety in air commerce. This regulation                 1 blade, part number 2305M26P06, installed.           0267 R01, dated August 10, 2015 can be
                                                is within the scope of that authority                                                                         obtained from GE using the contact
                                                because it addresses an unsafe condition                (d) Unsafe Condition                                  information in paragraph (h)(3) of this AD.
                                                that is likely to exist or develop on                     This AD was prompted by reports of two                 (3) For service information identified in
                                                products identified in this rulemaking                  separate, single engine in-flight shutdowns,          this AD, contact General Electric Company,
                                                action.                                                 caused by HPT rotor stage 1 blade failure. We         GE Aviation, Room 285, 1 Neumann Way,
                                                                                                        are issuing this AD to prevent failure of the         Cincinnati, OH 45215; phone: 513–552–3272;
                                                Regulatory Findings                                     HPT rotor stage 1 blades, which could lead
                                                                                                                                                              email: aviation.fleetsupport@ge.com.
                                                                                                        to failure of one or more engines, loss of
                                                  This AD will not have federalism                      thrust control, and damage to the airplane.              (4) You may view this service information
                                                implications under Executive Order                                                                            at the FAA, Engine & Propeller Directorate,
                                                13132. This AD will not have a                          (e) Compliance                                        1200 District Avenue, Burlington, MA. For
                                                substantial direct effect on the States, on                Comply with this AD within the                     information on the availability of this
                                                the relationship between the national                   compliance times specified, unless already            material at the FAA, call 781–238–7125.
                                                government and the States, or on the                    done.
                                                                                                           (1) Perform an initial borescope inspection          Issued in Burlington, Massachusetts, on
                                                distribution of power and                                                                                     February, 18, 2016.
                                                                                                        (BSI) of the convex surface of the HPT rotor
                                                responsibilities among the various                                                                            Ann C. Mollica,
                                                                                                        stage 1 blades for axial cracks from the
                                                levels of government.                                   platform to 30% span, within 1,000 blade
                                                  For the reasons discussed above, I                                                                          Acting Manager, Engine & Propeller
                                                                                                        cycles since new or 25 cycles after the               Directorate, Aircraft Certification Service.
                                                certify that this AD:                                   effective date of this AD, whichever occurs
                                                  (1) Is not a ‘‘significant regulatory                                                                       [FR Doc. 2016–04031 Filed 2–25–16; 8:45 am]
                                                                                                        later, and disposition as follows:
                                                action’’ under Executive Order 12866,                      (i) If any axial crack with a length greater       BILLING CODE 4910–13–P
                                                  (2) Is not a ‘‘significant rule’’ under               than or equal to 0.3 inch is found, or if any
                                                DOT Regulatory Policies and Procedures                  axial crack of any length turning in a radial
                                                (44 FR 11034, February 26, 1979),                       direction is found, or if more than one axial
                                                  (3) Will not affect intrastate aviation               crack of any length is found on one blade,
mstockstill on DSK4VPTVN1PROD with RULES




                                                in Alaska to the extent that it justifies               remove the cracked blade from service before
                                                                                                        further flight.
                                                making a regulatory distinction, and
                                                                                                           (ii) If an axial crack is found with a length
                                                  (4) Will not have a significant                       greater than or equal to 0.2 inch and less than
                                                economic impact, positive or negative,                  0.3 inch, remove the cracked blade from
                                                on a substantial number of small entities               service within 10 blade cycles.
                                                under the criteria of the Regulatory                       (iii) If an axial crack is found with a length
                                                Flexibility Act.                                        greater than or equal to 0.1 inch and less than



                                           VerDate Sep<11>2014   17:33 Feb 25, 2016   Jkt 238001   PO 00000   Frm 00013   Fmt 4700   Sfmt 9990   E:\FR\FM\26FER1.SGM   26FER1



Document Created: 2018-02-02 14:37:14
Document Modified: 2018-02-02 14:37:14
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD is effective April 1, 2016.
ContactChristopher 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]
FR Citation81 FR 9751 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR