[Federal Register Volume 78, Number 18 (Monday, January 28, 2013)]
[Rules and Regulations]
[Pages 5710-5712]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-01552]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1293; Directorate Identifier 2012-NE-45-AD;
Amendment 39-17327; AD 2013-02-06]
RIN 2120-AA64
Airworthiness Directives; Engine Alliance Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Engine Alliance GP7270 and GP7277 turbofan engines. This AD requires
initial and repetitive borescope inspections and removal from service
before further flight if one or more burn holes are detected, in
certain high-pressure turbine (HPT) stage 2 nozzles. This AD also
requires mandatory removal from service of these HPT stage 2 nozzles at
the next engine shop visit. This AD was prompted by a report received
of inadequate cooling of the HPT stage 2 nozzle, leading to damage to
the HPT stage 2 nozzle, burn-through of the turbine case, and engine
shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure,
leading to uncontrolled fire, engine shutdown, and damage to the
airplane.
DATES: This AD is effective February 12, 2013.
We must receive comments on this AD by March 14, 2013.
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; 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: Martin Adler, Aerospace Engineer,
Engine & Propeller Directorate, FAA, 12 New England Executive Park,
Burlington, MA 01803; phone: 781-238-7157; fax: 781-238-7199; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We received a report of an engine shutdown and turbine case burn-
through, preceded by exceedance of the engine exhaust gas temperature
(EGT) limit and loss of engine oil. Investigation revealed that the
event was caused by damage to the HPT stage 2 nozzle due to inadequate
part cooling. HPT stage 2 nozzles, part numbers (P/Ns) 2101M24G01,
2101M24G02, and 2101M24G03, are identified as having
[[Page 5711]]
the inadequate cooling design. This condition, if not corrected, could
result in HPT stage 2 nozzle failure, leading to uncontrolled fire,
engine shutdown, and damage to the airplane.
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 initial and repetitive borescope inspections and
removal from service before further flight if burn holes are detected,
in HPT stage 2 nozzles, P/Ns 2101M24G01, 2101M24G02, and 2101M24G03.
This AD also requires mandatory removal from service of these HPT stage
2 nozzles at the next engine shop visit.
FAA's Justification and Determination of the Effective Date
No domestic operators use this product. Therefore, we find that
notice and opportunity for prior public comment are unnecessary, 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-2012-1293 and
Directorate Identifier 2012-NE-45-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 no engines installed on
airplanes of U.S. registry. We also estimate that it would take about
two hours per engine to perform a borescope inspection of the HPT stage
2 nozzle. The average labor rate is $85 per work hour. Required parts
would cost about $487,312 per engine. Based on these figures, we
estimate the cost of this proposed AD to U.S. operators to be $0.
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):
2013-02-06 Engine Alliance: Amendment 39-17327; Docket No. FAA-2012-
1293; Directorate Identifier 2012-NE-45-AD.
(a) Effective Date
This AD is effective February 12, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Engine Alliance GP7270 and GP7277
turbofan engines with a high-pressure turbine (HPT) stage 2 nozzle,
part number (P/N) 2101M24G01, 2101M24G02, or 2101M24G03, installed.
(d) Unsafe Condition
This AD was prompted by a report received of inadequate cooling
of the HPT stage 2 nozzle, leading to damage to the HPT stage 2
nozzle, burn-through of the turbine case, and engine shutdown.
Investigation revealed that the event was caused by damage to the
HPT stage 2 nozzle due to inadequate part cooling. We are issuing
this AD to prevent HPT stage 2 nozzle failure, leading to
uncontrolled fire, engine shutdown, and damage to the airplane.
(e) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(f) Borescope Inspections of the HPT Stage 2 Nozzle
(1) Initially borescope inspect (360 degrees) the HPT stage 2
nozzle at the following:
(i) Before accumulating 1,500 cycles-since-new (CSN), if the
nozzle has fewer than 1,450 CSN on the effective date of this AD.
(ii) Within the next 50 cycles, if the nozzle has 1,450 or more
CSN on the effective date of this AD.
(2) Thereafter, repetitively borescope inspect (360 degrees) the
HPT stage 2 nozzle within every 100 additional cycles-in-service.
(3) If during any inspection required by this AD, any burn holes
are detected through the surface of the nozzle, remove the nozzle
from service before further flight.
(g) Mandatory Removal From Service of the HPT Stage 2 Nozzles
At the next engine shop visit, remove HPT stage 2 nozzles P/N
2101M24G01, 2101M24G02, and 2101M24G03 from service.
(h) Definition
For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine
[[Page 5712]]
flanges except that the separation of engine flanges solely for the
purposes of transportation without subsequent engine maintenance
does not constitute an engine shop visit.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, Engine Certification Office, may approve AMOCs for
this AD. Use the procedures found in 14 CFR 39.19 to make your
request.
(j) Related Information
For more information about this AD, contact Martin Adler,
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA 01803; phone: 781-238-7157;
fax: 781-238-7199; email: [email protected].
(k) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on January 15, 2013.
Thomas A. Boudreau,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2013-01552 Filed 1-25-13; 8:45 am]
BILLING CODE 4910-13-P