[Federal Register Volume 67, Number 100 (Thursday, May 23, 2002)]
[Rules and Regulations]
[Pages 36092-36093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-12630]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-27-AD; Amendment 39-12753; AD 2002-10-07]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT9D-59A, -70A, -7Q, 
and -7Q3 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 
turbofan engines. This amendment requires fluorescent penetrant 
inspection of the high pressure turbine (HPT) second stage airseal 
knife edges for cracks, each time the airseal is accessible. This 
amendment is prompted by reports of cracks found in the knife edges of 
HPT second stage airseals during HPT disassembly. The actions specified 
by this AD are intended to prevent failure of HPT second stage airseals 
due to cracks in the knife edges, which if not detected could result in 
uncontained engine failure and damage to the airplane.

DATES: Effective June 27, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of June 27, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; 
telephone (860) 565-8770; fax (860) 565-4503. This information may be 
examined, by appointment, at the Federal Aviation Administration (FAA), 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tara Goodman, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7130, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to PW JT9D-59A, -70A, -7Q, and -7Q3 turbofan engines was 
published in the Federal Register on November 23, 2001 (66 FR 58691). 
That action proposed to require fluorescent penetrant inspection of the 
HPT second stage airseal knife edges for cracks, in accordance with PW 
service bulletin (SB) JT9D 6409, dated July 27, 2001, each time the 
airseal is accessible.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Make Removal Wording More Specific

    One commenter suggests changing proposed paragraph (a) to be 
consistent with SB JT9D 6409, dated July 27, 2001. Paragraph (a) 
proposed that airseals found cracked must be removed from service. The 
commenter suggests that paragraph (a) should state that airseals that 
are found cracked must be removed only if the crack is beyond the limit 
defined in the engine manual inspection section. Another commenter 
points out that SB JT9D 6409, dated July 27, 2001, refers to the engine 
manual (EM), but the proposal does not. The EM allows blend repair of 
cracks that are not located in the pedestal area of the airseal, but 
the proposal requires removal from service of airseals with any cracks.
    The FAA agrees that the wording describing the circumstances that 
airseals are to be removed from service needs to be more specific. 
Therefore, the FAA has changed paragraph (a) to reference the return to 
service criteria as well as the procedures for performing the 
inspection contained in the Accomplishment Instructions of PW SB JT9D 
6409, dated July 27, 2001.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 564 engines of the affected design PW JT9D-
59A, -70A, -7Q, and -7Q3 turbofan engines in the worldwide fleet. The 
FAA estimates that 176 engines installed on airplanes of U.S. registry 
would be affected by this AD. The FAA also estimates that it would take 
approximately 1 work hour per engine to perform the fluorescent 
penetrant inspection, and that the average labor rate is $60 per work 
hour. Based on these figures, the total labor cost annually of the AD 
on U.S. operators is estimated to be $10,560.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    For the reasons discussed above, I certify that this action (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) 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. A final evaluation has

[[Page 36093]]

been prepared for this action and it is contained in the Rules Docket. 
A copy of it may be obtained by contacting the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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.


 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

2002-10-07  Pratt & Whitney: Amendment 39-12753. Docket No. 2001-NE-
27-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Pratt & Whitney (PW) JT9D-59A, -70A, -7Q, and -7Q3 turbofan 
engines. These engines are installed on, but not limited to, Airbus 
Indusrie A300 series, Boeing 747 series, and McDonnell Douglas DC-10 
series airplanes.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Compliance with this AD is required as indicated, 
unless already done.
    To prevent failure of high pressure turbine (HPT) second stage 
airseals due to cracks in the knife edges, which if not detected 
could result in uncontained engine failure and damage to the 
airplane, do the following:

Inspections

    (a) Perform a fluorescent penetrant inspection of the HPT second 
stage airseal knife edges for cracks in accordance with procedures 
and return to service criteria contained in Accomplishment 
Instructions, Paragraphs 1 through 3, of PW Service Bulletin (SB) 
JT9D 6409, dated July 27, 2001, each time the HPT stage 1 and stage 
2 rotors are separated. Remove from service those airseals that are 
determined to be unserviceable.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
 21.197 and 21.199 of the Federal Aviation 
Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a 
location where the requirements of this AD can be done.

Documents That Have Been Incorporated By Reference

    (d) The inspection must be done in accordance with Pratt & 
Whitney Service Bulletin JT9D 6409, dated July 27, 2001. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Pratt & Whitney, 400 Main St., East 
Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503. 
Copies may be inspected, by appointment, at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive 
Park, Burlington, MA; or at the Office of the Federal Register, 800 
North Capitol Street, NW, suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on June 27, 2002.


    Issued in Burlington, Massachusetts, on May 10, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-12630 Filed 5-22-02; 8:45 am]
BILLING CODE 4910-13-U