[Federal Register: November 9, 2007 (Volume 72, Number 217)]
[Proposed Rules]
[Page 63510-63512]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09no07-21]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23742; Directorate Identifier 2005-NE-53-AD]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney (PW) JT9D-7R4 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for PW JT9D-7R4 series turbofan engines. That AD
currently requires removing certain reduced cooling flow 2nd stage high
pressure turbine (HPT) vane assemblies installed in certain 2nd stage
HPT vane cluster assemblies. It also requires a visual and a
fluorescent penetrant inspection (FPI) of the 2nd stage HPT air seal
assembly, P/N 815097. This proposed AD would require a visual and
fluorescent penetrant inspection (FPI) of all part number (P/N) 2nd
stage HPT air seal assemblies that were used with reduced cooling flow
2nd stage HPT vane assemblies. This proposed AD results from the
manufacturer identifying additional P/N air seal assemblies that are
affected by the unsafe condition. We are proposing this AD to prevent
uncontained failure of the 2nd stage HPT air seal assembly, leading to
engine in-flight shutdown and damage to the airplane.
DATES: We must receive any comments on this proposed AD by January 8,
2008.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108;
telephone (860) 565-8770; fax (860) 565-4503, for the service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
mark.riley@faa.gov; telephone (781) 238-7758, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-23742;
Directorate Identifier 2005-NE-53-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light 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
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
[[Page 63511]]
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
Discussion
The FAA proposes to amend 14 CFR part 39 by superseding AD 2007-17-
21, Amendment 39-15180 (72 FR 48549, August 24, 2007). That AD requires
removing reduced cooling flow 2nd stage HPT vane assemblies. It also
requires a visual and an FPI of the 2nd stage HPT air seal assembly.
That AD resulted from a report of an uncontained failure of the 2nd
stage HPT air seal assembly, caused by the air seal assembly brace
disengaging from the air seal, due to insufficient cooling air flow.
That condition, if not corrected, could result in uncontained failure
of the 2nd stage HPT air seal assembly, leading to engine in-flight
shutdown and damage to the airplane.
Actions Since AD 2007-17-21 Was Issued
Since we issued that AD, we determined that we need to expand the
applicability of the AD to include all 2nd stage HPT air seal
assemblies that were used with reduced cooling flow 2nd stage HPT vane
assemblies, P/Ns 797282, 796972, 800082, 800072, 803182, 803282, and
822582, installed in 2nd stage HPT vane cluster assemblies P/Ns 797592,
797372, 799872, 799782, and 822572.
Relevant Service Information
We have reviewed and approved the technical contents of Pratt &
Whitney Alert Service Bulletin JT9D-7R4-A72-596, dated September 15,
2005, that describes procedures for modifying the reduced cooling flow
2nd stage HPT vane assemblies.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. For that reason, we are proposing this AD,
which would require at the next HPT module exposure:
Removing the reduced cooling flow 2nd stage HPT vane
assemblies.
Visual and fluorescent penetrant inspections of the 2nd
stage HPT air seal assemblies that have operated in an engine with
reduced cooling flow 2nd stage HPT vane assemblies.
Costs of Compliance
Because this proposed AD is superseding an existing AD to remove
the seal assembly P/N, this proposed AD would not add any additional
costs beyond the costs included in the original AD.
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
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 14 CFR part 39 as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by removing Amendment 39-15180 (72 FR
48549, August 24, 2007), and by adding a new airworthiness directive to
read as follows:
Pratt & Whitney (PW): Docket No. FAA-2006-23742; Directorate
Identifier 2005-NE-53-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by January 8,
2008.
Affected ADs
(b) This AD supersedes AD 2007-17-21, Amendment 39-15180.
Applicability
(c) This AD applies to Pratt & Whitney (PW) JT9D-7R4G2, -7R4E1,
-7R4E4, and -7R4H1 series turbofan engines. These engines are
installed on, but not limited to, Boeing 747-200, -300, 767-200, and
Airbus A300-600 and A310-300 series airplanes.
Unsafe Condition
(d) This AD results from the manufacturer identifying additional
part numbers (P/N) air seal assemblies that are affected by the
unsafe condition. We are issuing this AD to prevent uncontained
failure of the 2nd stage high pressure turbine (HPT) air seal
assembly, leading to engine in-flight shutdown and damage to the
airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed at the next HPT module exposure after the effective
date of this AD, unless the actions have already been done.
(f) At the next HPT module exposure, remove reduced cooling flow
2nd stage HPT vane assemblies P/Ns: 797282, 796972, 800082, 800072,
803182, 803282, and 822582, installed in 2nd stage HPT vane cluster
assemblies: P/Ns 797592, 797372, 799872, 799782, and 822572.
(g) For 2nd stage HPT air seals that have operated in an engine
with reduced cooling flow HPT vane assemblies, at the next HPT
module exposure do the following:
(1) Perform a onetime visual inspection of the 2nd stage HPT air
seal assembly. The
[[Page 63512]]
JT9D-7R4 engine manual, Section 72-51-22, Inspection/Check-01,
paragraphs 1.D.(1), 1.D.(4), and 1.D.(6) contains instructions for
the visual inspection.
(2) Perform a fluorescent penetrant inspection (FPI) of the 2nd
stage HPT air seal assembly for cracks. The JT9D-7R4 engine manual,
Section 72-51-00, Inspection/Check-03, contains instructions for the
FPI.
Definition
(h) For the purpose of this AD, we define an HPT module exposure
as removing the 1st stage HPT rotor or the 2nd stage HPT rotor from
the HPT case.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, 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
(j) Pratt & Whitney Alert Service Bulletin JT9D-7R4-A72-596,
dated September 15, 2005, contains information for modifying the
reduced cooling flow 2nd stage HPT vane assemblies.
(k) Contact Mark Riley, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; e-mail: mark.riley@faa.gov;
telephone (781) 238-7758, fax (781) 238-7199, for more information
about this AD.
Issued in Burlington, Massachusetts, on November 2, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-22005 Filed 11-8-07; 8:45 am]
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