[Federal Register Volume 81, Number 7 (Tuesday, January 12, 2016)]
[Rules and Regulations]
[Pages 1291-1292]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-33075]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 81, No. 7 / Tuesday, January 12, 2016 / Rules
and Regulations
[[Page 1291]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-6823; Directorate Identifier 2015-NE-38-AD;
Amendment 39-18360; AD 2015-27-01]
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 all
General Electric Company (GE) GE90-76B, -77B, -85B, -90B, and -94B
turbofan engines. This AD requires performing an eddy current
inspection (ECI) or ultrasonic inspection (USI) of the high-pressure
compressor (HPC) stage 8-10 spool and removing from service those parts
that fail inspection. This AD was prompted by an uncontained failure of
the HPC stage 8-10 spool, leading to an airplane fire. 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.
DATES: This AD is effective January 27, 2016.
We must receive comments on this AD by February 26, 2016.
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.
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-
6823; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax:
781-238-7199; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We received a report of an HPC stage 8-10 spool uncontained failure
resulting in an airplane fire. Ongoing investigations have determined
that a crack initiated in the stage 8 aft web upper face of the HPC 8-
10 spool and propagated until spool rupture. The root cause of the
crack initiation is not yet known. This condition, if not corrected,
could result in failure of the HPC stage 8-10 spool, uncontained rotor
release, damage to the engine, and damage to the airplane. We are
issuing this AD to correct the unsafe condition on these products.
Related Service Information
We reviewed GE Service Bulletin (SB) No. GE90 S/B 72-1145, dated
November 24, 2015. The SB describes procedures for one-time on-wing USI
of the stage 8 web of the stage 8-10 spool. We also reviewed the
following chapters of GE GE90 Engine Manual, GEK100700, Revision 66,
dated September 1, 2015:
Chapter 72-31-08, Special Procedure 003, piece-part level
ECI,
Chapter 72-00-31, Special Procedure 006, rotor assembly
and module level ECI and,
Chapter 72-00-31, Special Procedure 007, rotor assembly
level USI.
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 an ECI or USI of the stage 8 aft web
upper face of the HPC stage 8-10 spool and removing from service those
parts that fail inspection.
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 identified, we might consider additional rulemaking.
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. 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 ``Docket No. FAA-2015-6823; Directorate
Identifier 2015-NE-38-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.
[[Page 1292]]
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 affects 1 engine installed on an airplane
of U.S. registry. We also estimate that it will take about 7 hours per
engine to comply with this AD. The average labor rate is $85 per hour.
Required parts cost about $780,000 per engine. Based on these figures,
we estimate the total cost of the AD to U.S. operators to be $780,595.
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):
2015-27-01 General Electric Company: Amendment 39-18360; Docket No.
FAA-2015-6823; Directorate Identifier 2015-NE-38-AD.
(a) Effective Date
This AD is effective January 27, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) GE90-76B, -77B,
-85B, -90B, and -94B turbofan engines with high-pressure compressor
(HPC) stage 8-10 spool, part number 1694M80G04, installed.
(d) Unsafe Condition
This AD was prompted by an uncontained failure of the HPC stage
8-10 spool, leading to an airplane fire. 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.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) Perform an eddy current inspection or ultrasonic inspection
of the stage 8 aft web upper face of the HPC stage 8-10 spool for
cracks as follows:
(i) For HPC stage 8-10 spools with serial number (S/N) GWNHC086
or GWNHB875, inspect within 150 cycles-in-service (CIS), after the
effective date of this AD.
(ii) For HPC stage 8-10 spools with S/N GWNHC154, GWNHA455,
GWNHC153, or GWNHB516, inspect within 300 CIS, after the effective
date of this AD.
(2) Remove from service any HPC stage 8-10 spool that fails the
inspection required by paragraph (e)(1) of this AD and replace the
spool with a spool eligible for installation.
(f) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, FAA, may approve AMOCs
for this AD. Use the procedures found in 14 CFR 39.19 to make your
request. You may email your request to: [email protected].
(g) Related Information
For more information about this AD, contact John Frost,
Aerospace Engineer, Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England Executive Park, Burlington, MA
01803; phone: 781-238-7756; fax: 781-238-7199; email:
[email protected].
(h) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on December 21, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2015-33075 Filed 1-11-16; 8:45 am]
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