[Federal Register Volume 75, Number 195 (Friday, October 8, 2010)]
[Rules and Regulations]
[Pages 62319-62320]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-25391]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 75, No. 195 / Friday, October 8, 2010 / Rules
and Regulations
[[Page 62319]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0514; Directorate Identifier 2010-NE-02-AD;
Amendment 39-16477; AD 2010-21-17]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney JT8D-9, -9A, -11, -15,
-17, and -17R Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Pratt & Whitney (PW) JT8D-9, -9A, -11, -15, -17, and -17R turbofan
engines. This AD requires overhauling fan blade leading edges at the
first shop visit after 4,000 cycles-in-service (CIS) since the last
total fan blade overhaul was performed. This AD results from reports of
failed fan blades. We are issuing this AD to prevent high-cycle fatigue
cracking at the blade root, which could result in uncontained failures
of first stage fan blades and damage to the airplane.
DATES: This AD becomes effective November 12, 2010.
ADDRESSES: You can get the service information identified in this AD
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone
(860) 565-7700; fax (860) 565-1605.
The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: James Gray, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7742; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to PW JT8D-9, -9A, -11, -
15, -17, and -17R turbofan engines. We published the proposed AD in the
Federal Register on May 19, 2010 (75 FR 27972). That action proposed to
require overhauling fan blade leading edges at the first shop visit
after 4,000 CIS since the last total fan blade overhaul was performed.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
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 Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Extend the Proposed AD Comment Period
Two commenters, Delta Airlines, Inc. and the National
Transportation Safety Board, request that we extend the proposed AD
comment period. The extension would allow time to determine the root
cause of a fan blade failure on a Delta DC-9 airplane, occurring on
June 14, 2010.
We do not agree. Extending the comment period would delay the
rulemaking process. The root cause investigation can continue after the
AD is issued. We did not change the AD.
Request for Clarification of Shop Visit
Delta Airlines, Inc. requests clarification of the shop visit
definition in paragraph (i) of the proposed AD. Specifically, clarify
whether a gearbox removal or gearbox change would fit into the shop
visit definition. Also, that we clarify that a nose cowl removal or a
thrust reverser removal not be included in the shop visit definition.
These actions involve components that mate to engine flanges.
We partially agree. We revised the definition of shop visit in the
AD to include a clarification of ``lettered flanges'' after ``pairs of
major mating engine flanges.'' The procedures referenced by the
commenter are shop visits according to the definition in paragraph (i)
of the AD. Since the nose cowl and thrust reverser are not engine
components, they would involve the separation of an engine flange with
a non-engine flange. A gearbox removal would not involve a lettered
flange. You can find further information on what is a lettered flange
in the engine manual.
Clarification Requirements
Since we issued the proposed AD, we discovered that paragraphs (f)
and (g) require clarification. We clarified those paragraphs in the AD,
to state that the cycles-in-service apply to the fan blades.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
Costs of Compliance
We estimate that this AD will affect 1,527 engines installed on
airplanes of U.S. registry. We also estimate that it will take about 63
work-hours per engine to perform the actions, and that the average
labor rate is $85 per work-hour. No additional parts are required.
Based on these figures, we estimate the total cost of the AD to U.S.
operators to be $8,177,085.
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
[[Page 62320]]
the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses
an unsafe condition that is likely to exist or develop on products
identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration 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:
2010-21-17 Pratt & Whitney: Amendment 39-16477. Docket No. FAA-2010-
0514; Directorate Identifier 2010-NE-02-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
12, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney (PW) JT8D-9, -9A, -11, -
15, -17, and -17R turbofan engines. These engines are installed on,
but not limited to, Boeing 727 series, Boeing 737-200 series and
McDonnell Douglas DC-9 airplanes.
Unsafe Condition
(d) This AD results from reports of failed fan blades. We are
issuing this AD to prevent high-cycle fatigue cracking at the blade
root, which could result in uncontained failures of first stage fan
blades and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Initial Overhaul
(f) For engines where the cycles-in-service (CIS) since the last
overhaul of the fan blades are known, overhaul the total set of
stage 1 fan blades at the first shop visit after 4,000 CIS since the
last total stage 1 fan blade overhaul, or the next shop visit after
the effective date of this AD, whichever occurs later. Guidance on
performing a fan blade overhaul can be found in Pratt & Whitney JT8D
Maintenance Advisory Notice No. MAN-JT8D-2-06, and the Engine Manual
Chapter/Section 72-33-21, Inspection 00.
(g) For engines where the CIS since the last overhaul of the fan
blades are unknown, overhaul the total set of stage 1 fan blades at
the next shop visit after the effective date of this AD. Guidance on
performing a fan blade overhaul can be found in Pratt & Whitney JT8D
Maintenance Advisory Notice No. MAN-JT8D-2-06, and the Engine Manual
Chapter/Section 72-33-21, Inspection 00.
Repetitive Overhaul
(h) Thereafter, overhaul the total set of stage 1 fan blades at
the first shop visit after 4,000 CIS since the last total stage 1
fan blade overhaul. Guidance on performing a fan blade overhaul can
be found in Pratt & Whitney JT8D Maintenance Advisory Notice No.
MAN-JT8D-2-06, and the Engine Manual Chapter/Section 72-33-21,
Inspection 00.
Definitions
(i) For the purpose of this AD, a shop visit is the induction of
an engine into the shop for maintenance involving the separation of
pairs of major mating engine flanges (lettered flanges), except that
the separation of engine flanges solely for the purposes of
transporting the engine without subsequent engine maintenance does
not constitute an engine shop visit.
Alternative Methods of Compliance
(j) The Manager, Engine Certification Office, FAA, has the
authority to approve alternative methods of compliance for this AD
if requested using the procedures found in 14 CFR 39.19.
Related Information
(k) Contact James Gray, Aerospace Engineer, Engine Certification
Office, FAA, Engine & Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: [email protected];
telephone (781) 238-7742; fax (781) 238-7199, for more information
about this AD.
(l) Pratt & Whitney JT8D Maintenance Advisory Notice No. MAN-
JT8D-2-06, dated November 20, 2006, pertains to the subject of this
AD. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108;
telephone (860) 565-7700; fax (860) 565-1605, for a copy of this
service information.
Material Incorporated by Reference
(m) None.
Issued in Burlington, Massachusetts, on October 1, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-25391 Filed 10-7-10; 8:45 am]
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