[Federal Register Volume 74, Number 60 (Tuesday, March 31, 2009)]
[Rules and Regulations]
[Pages 14458-14460]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-6749]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0759; Directorate Identifier 2008-NE-02-AD; 
Amendment 39-15824; AD 2009-04-18]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney (PW) JT9D-7 Series 
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 PW 
models JT9D-7, -7A, -7AH, -7H, -7F, and -7J turbofan engines. This AD 
requires initial and repetitive borescope inspections of the 2nd stage 
high-pressure turbine (HPT) rotor and stator assembly. This AD results 
from an uncontained failure of a 2nd stage HPT rotor disk that caused 
the engine to separate from the airplane. We are issuing this AD to 
prevent failure of the 2nd stage HPT rotor disk, which could result in 
uncontained engine failure, damage to the airplane, and the engine 
separating from the airplane.

DATES: This AD becomes effective May 5, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of May 5, 2009.

ADDRESSES: You can get the service information identified in this AD 
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503.
    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: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
<a href="/cdn-cgi/l/email-protection#d9b2bcafb0b7f7bdb0bab2bcabad99bfb8b8f7beb6af"><span class="__cf_email__" data-cfemail="bbd0decdd2d595dfd2d8d0dec9cffbdddada95dcd4cd">[email protected]</span></a>; telephone (781) 238-7117, 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 models JT9D-7, -7A, -
7AH, -7H, -7F, and -7J turbofan engines. We published the proposed AD 
in the Federal Register on July 10, 2008 (73 FR 39627). That action 
proposed to require an initial and repetitive borescope inspection of 
the 2nd stage HPT vane assembly.

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.
    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.
    One commenter asks us to change the compliance time from ``cycles-
since-overhaul'' to ``cycles-since-last installation of the second 
stage HPT vanes.'' The commenter states that second stage HPT vanes 
might be removed and replaced at times other than module overhaul, such 
as for module repair.
    We agree. We changed paragraph (f) of the proposed AD from ``Within 
100 cycles-in-service (CIS) after the effective date of this AD, or 
within 1,000 CIS after the last HPT module overhaul * * *'' to ``Within 
100 cycles-in-service (CIS) after the effective date of this AD, or 
within 1,000 CIS after the last installation of the second stage HPT 
vanes * * *''

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 240 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 5 
work-hours per engine to perform the proposed actions, that each engine 
might require two inspections, and that the average labor rate is $80 
per work-hour. Based on these figures, we estimate the total cost of 
the AD to U.S. operators to be $192,000.

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 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:

[[Page 14459]]

    (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, Incorporation by 
reference, 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:

2009-04-18 Pratt & Whitney: Amendment 39-15824. Docket No. FAA-2008-
0759; Directorate Identifier 2008-NE-02-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 5, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) JT9D-7, -7A, -7AH, -
7H, -7F, and -7J turbofan engines. These engines are installed on, 
but not limited to, Boeing 747 series airplanes.

Unsafe Condition

    (d) This AD results from an uncontained failure of a 2nd stage 
high-pressure turbine (HPT) rotor disk that caused the engine to 
separate from the airplane. We are issuing this AD to prevent 
failure of the 2nd stage HPT rotor disk, which could result in 
uncontained engine failure, damage to the airplane, and the engine 
separating from 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 Borescope Inspection

    (f) Within 100 cycles-in-service (CIS) after the effective date 
of this AD, or within 1,000 CIS after the last installation of the 
second stage HPT vanes, whichever occurs later, do the following:
    (1) Use the Accomplishment Instructions of PW Alert Service 
Bulletin (ASB) JT9D A6488, Revision 1, dated April 18, 2008, to 
borescope-inspect the 2nd stage HPT rotor and stator assembly either 
on-wing or in the shop.
    (2) If you see any damage or contact between the 2nd stage HPT 
vanes and the 2nd stage HPT rotor, remove the engine from service.

Repetitive Borescope Inspection

    (g) Thereafter, within 1,000 cycles-since-last inspection, do 
the following:
    (1) Use the Accomplishment Instructions of PW ASB JT9D A6488 
Revision 1, dated April 18, 2008, to borescope-inspect the 2nd stage 
HPT rotor and stator assembly either on-wing or in the shop.
    (2) If you see any damage or contact between the 2nd stage HPT 
vanes and the 2nd stage HPT rotor, remove the engine from service.

Optional Terminating Action

    (h) Installing the 2nd stage HPT vanes as specified in 
paragraphs 1.B.(1) through 1.B.(32) of the JT9D-7 Engine Manual 
Revision 122, dated February 15, 2008, terminates the repetitive 
inspection requirement specified in paragraph (g) of this AD.

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) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
<a href="/cdn-cgi/l/email-protection#0b606e7d6265256f6268606e797f4b6d6a6a256c647d"><span class="__cf_email__" data-cfemail="1e757b687770307a777d757b6c6a5e787f7f30797168">[email protected]</span></a>; telephone (781) 238-7117, fax (781) 238-7199, 
for more information about this AD.

Material Incorporated by Reference

    (k) You must use the service information specified in the 
following Table 1 to perform the actions required by this AD. The 
Director of the Federal Register approved the incorporation by 
reference of the documents listed in the following Table 1 in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Contact 
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503, for a copy of this service 
information. You may review copies at the FAA, New England Region, 
12 New England Executive Park, Burlington, MA; or 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.

                                       Table 1--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
       Service information No.                  Page              Revision                    Date
----------------------------------------------------------------------------------------------------------------
Pratt & Whitney JT9D Engine           1001 through 1036......             122  February 15, 2008.
 Maintenance Manual PN 770408.
Total Pages--36
Pratt & Whitney PW ASB JT9D A6488,    All....................               1  April 18, 2008.
 Revision 1, dated April 18, 2008.
Total Pages--21
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[[Page 14460]]

    Issued in Burlington, Massachusetts, on March 17, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-6749 Filed 3-30-09; 8:45 am]
BILLING CODE 4910-13-P


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