[Federal Register Volume 77, Number 184 (Friday, September 21, 2012)]
[Rules and Regulations]
[Pages 58471-58473]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-23443]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1017; Directorate Identifier 2012-NE-30-AD;
Amendment 39-17203; AD 2012-19-08]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Turbofan
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for General
Electric Company GEnx-1B54, GEnx-1B58, GEnx-1B64, GEnx-1B67, GEnx-1B70,
GEnx-1B54/P1, GEnx-1B58/P1, GEnx-1B64/P1, GEnx-1B67/P1, GEnx-1B70/P1,
GEnx-1B70/72/P1, GEnx-1B70/75/P1, GEnx-1B74/75/P1, GEnx-1B75/P1, GEnx-
2B67, and GEnx-2B67B turbofan engines. This AD requires initial and
repetitive ultrasonic inspections (UI) of certain part number (P/N) fan
mid shafts (FMS) for cracks. This AD was prompted by a report of an FMS
failure and a report of a crack found in another FMS. We are issuing
this AD to prevent failure of the FMS resulting in one or more engine
failure(s) and possible loss of the airplane.
DATES: This AD is effective September 21, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of September 21,
2012.
We must receive comments on this AD by October 22, 2012.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact General
Electric Company, 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, 12 New
England Executive Park, 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; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: James Gray, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7742; fax:
781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On July 28, 2012, we received a report of a GEnx-1B engine failure
installed on a Boeing 787 (B787) airplane. Boeing was conducting
routine ground testing of the B787, before aircraft delivery. During a
taxi test, one engine's FMS fractured just aft of the coupling nut. The
low-pressure turbine (LPT) rotor shifted axially backwards, resulting
in LPT blade and vane clashing. The LPT case contained the failure and
debris was released out the tailpipe. There was no engine overspeed as
the LPT rotor remained coupled to the fan rotor at the FMS spline. On
August 14, 2012, we received a second report concerning the GEnx
engine, this time about an FMS, installed in a GEnx-1B engine, that was
found cracked during an on-wing UI. This condition, if not corrected,
could result in failure of the FMS resulting in one or more engine
failure(s) and possible loss of the airplane.
Relevant Service Information
We reviewed GE Service Bulletin (SB) No. GEnx-1B S/B 72-0107,
Revision 2, dated September 14, 2012, and SB No. GEnx-2B S/B 72-0091,
Revision 1, dated September 14, 2012. The SBs describe procedures for
performing UI inspections of FMS P/N 2331M20G02, P/N 2332M81G01, and P/
N 2332M33G01.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the AD and the Service Information.''
Differences Between the AD and the Service Information
The SBs require an initial FMS inspection within 30 days of the SB
date. This AD requires an initial FMS inspection before further flight.
Interim Action
We consider this AD interim action. Root cause is still under
investigation, but the failure of the FMS is likely due to
environmentally assisted cracking; a type of corrosive cracking that is
time-dependent.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule based on the
reported engine failure, the crack find, and that the root
[[Page 58472]]
cause is still somewhat unknown. We therefore determined that a
repetitive inspection interval needed to be established. The repetitive
inspection interval is less than the time it would take to process a
proposed AD. Therefore, we find that notice and opportunity for prior
public comment are impracticable and that good cause exists for making
this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2012-1017 and
Directorate Identifier 2012-NE-30-AD at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD will affect 11 GE GEnx turbofan engines
installed on airplanes of U.S. registry. We also estimate that it will
take about 9 work-hours per engine to perform the UI of the FMS, and
that the average labor rate is $85 per work-hour. The estimated cost of
one set of inspection tooling is $105,000. Based on these figures, we
estimate the total cost of this AD to U.S. operators to be $113,415.
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, 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):
2012-19-08 General Electric Company: Amendment 39-17203; Docket No.
FAA-2012-1017; Directorate Identifier 2012-NE-30-AD.
(a) Effective Date
This AD is effective September 21, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to:
(1) General Electric Company (GE) GEnx-1B54, GEnx-1B58, GEnx-
1B64, GEnx-1B67, GEnx-1B70, GEnx-1B54/P1, GEnx-1B58/P1, GEnx-1B64/
P1, GEnx-1B67/P1, GEnx-1B70/P1, GEnx-1B70/72/P1, GEnx-1B70/75/P1,
GEnx-1B74/75/P1, and GEnx-1B75/P1 turbofan engines with fan mid
shaft (FMS) part number (P/N) 2331M20G02 or P/N 2332M81G01,
installed; and
(2) GE GEnx-2B67 and GEnx-2B67B turbofan engines with FMS P/N
2332M33G01, installed.
(d) Unsafe Condition
This AD was prompted by a report of an FMS failure and a report
of a crack found in another FMS. We are issuing this AD to prevent
failure of the FMS resulting in one or more engine failure(s) and
possible loss of the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(f) Ultrasonic Inspections (UIs)
(1) Perform an initial UI for cracks in the FMS before further
flight.
(2) Thereafter, perform repetitive UIs for cracks in the FMS
within every 90 days since-last-inspection.
(3) Remove any cracked FMS from service before further flight.
(4) For engines listed in paragraph (c)(1) of this AD, use
paragraphs 3.A and 3.B.(1) through 3.B.(9) of the Accomplishment
Instructions of GE Service Bulletin (SB) No. GEnx-1B S/B 72-0107,
Revision 2, dated September 14, 2012, to do the inspections.
(5) For engines listed in paragraph (c)(2) of this AD, use
paragraphs 3.A and 3.B.(1) through 3.B.(9) of the Accomplishment
Instructions of GEnx-2B S/B 72-0091, Revision 1, dated September 14,
2012, to do the inspections.
(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.
(h) Credit for Actions Accomplished in Accordance With Previous Service
Information
(1) For engines listed in paragraph (c)(1) of this AD, if you
performed the initial inspection before the effective date of this
AD using GE SB No. GEnx-1B S/B 72-0107, dated August 17, 2012, or
Revision 1, dated August 24, 2012, you met the requirement of
paragraph (f)(1) of this AD.
(2) For engines listed in paragraph (c)(2) of this AD, if you
performed the initial inspection before the effective date of this
AD using GE SB No. GEnx-2B S/B 72-0091, dated August 22, 2012, you
met the requirement of paragraph (f)(1) of this AD.
(3) For engines listed in paragraphs (c)(1) or (c)(2) of this
AD, if an initial inspection was performed before the effective date
of this AD using GE Field Engineering Instruction (FEI) GEnx-1B No.
2012-014 Fan Mid Shaft Inspection, or FEI GEnx-2B No. 2012-017 Fan
Mid Shaft Inspection, you met the requirement of paragraph (f)(1) of
this AD.
[[Page 58473]]
(i) Related Information
For more information about this AD, contact James Gray,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7742; fax: 781-238-7199; email:
[email protected].
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) General Electric Company Service Bulletin No. GEnx-1B S/B
72-0107, Revision 2, dated September 14, 2012.
(ii) General Electric Company Service Bulletin No. GEnx-2B S/B
72-0091, Revision 1, dated September 14, 2012.
(3) For General Electric Company 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, 12 New England Executive Park, Burlington,
MA. For information on the availability of this material at the FAA,
call 781-238-7125.
(5) You may view this service information at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on September 17, 2012.
Diane M. Cook,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2012-23443 Filed 9-20-12; 8:45 am]
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