Airworthiness Directives; Pratt & Whitney JT8D-200 Series Turbofan Engines

[Federal Register Volume 68, Number 153 (Friday, August 8, 2003)]
[Rules and Regulations]
[Pages 47207-47208]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-19828]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-41-AD; Amendment 39-13258; AD 2003-16-05]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-200 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 
series turbofan engines. This amendment requires removal and 
replacement of protective coating of the 7th and 9th through 12th stage 
high pressure compressor (HPC) disks and the 8th stage HPC hub, initial 
and repetitive inspections for corrosion pits and cracks, and removal 
from service as required. This amendment is prompted by reports from 
operators of cracks observed in JT8D engine steel HPC disks. We are 
issuing this AD to prevent fracture of the 7th and 9th through 12th 
stage HPC disks and 8th stage HPC hub, resulting in uncontained engine 
failure and damage to the airplane.

DATES: Effective September 12, 2003. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of September 12, 2003.

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: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7175; 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 JT8D-209, -217, -217A, -217C, and -219 series turbofan 
engines was published in the Federal Register on March 25, 2003 (68 FR 
14351). That action proposed to require removal and replacement of 
protective coating of the 7th and 9th through 12th stage HPC disks and 
the 8th stage HPC hub, initial and repetitive inspections for corrosion 
pits and cracks, and removal from service as required in accordance 
with PW alert service bulletin (ASB) JT8D A6435, Revision 1, dated 
March 7, 2003.

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.

Disk Tracking

    One commenter requests that the disks inspected using PW ASB JT8D 
6435, Revision 1, dated March 7, 2003, as well as all new disks, be 
tracked by the engine release date recorded on FAA 337 form or 
equivalent rather than per individual disk inspection dates. The 
commenter feels that this would significantly reduce the burden on 
airline records departments, especially for large operators, because 
the time between the disk inspection and the engine release date is 
typically not more than a few weeks.
    The FAA does not agree. There is no way to ensure that the time 
between the disk inspection and the engine release date will always be 
a short or controlled amount of time. Some operators or repair 
facilities may elect to store disks in their inventory for long periods 
of time. Unless these disks are preserved using instructions in the 
ASB, the time in storage must be counted in the accumulation of time to 
the next inspection because the corrosion protective coatings begin to 
degrade while in storage without proper preservation. However, if an 
operator can show that their particular operation will always result in 
short controlled times between inspection and installation and can 
demonstrate that an acceptable level of safety is maintained, they may 
apply for relief in accordance with paragraph (d) of this AD.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

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

[[Page 47208]]

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 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

0
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

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

2003-16-05 Pratt & Whitney: Amendment 39-13258. Docket No. 2002-NE-
41-AD.

    Applicability: This airworthiness directive (AD) applies to 
Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series 
turbofan engines. These engines are installed on, but not limited to 
McDonnell Douglas MD-80 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 (d) 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: You are responsible for having the actions required 
by this AD performed within the compliance times specified unless 
the actions have already been done.
    To prevent fracture of the 7th and 9th through 12th stage high 
pressure compressor (HPC) disks and 8th stage HPC hub, resulting in 
uncontained engine failure and damage to the airplane, do the 
following:
    (a) Perform initial and repetitive inspections of 7th and 9th 
through 12th stage HPC disks and 8th stage HPC hubs for corrosion 
pits and cracks after stripping the protective coating in accordance 
with the intervals specified in the compliance section and 
procedures specified in the accomplishment instructions of PW alert 
service bulletin (ASB) JT8D A6435, Revision 1, dated March 7, 2003.
    (b) Before further flight, replace 7th and 9th through 12th 
stage HPC disks and 8th stage HPC hubs found with corrosion pits or 
cracks beyond serviceable limits as defined by PW ASB JT8D A6435, 
Revision 1, dated March 7, 2003.
    (c) For the purposes of this AD, use the effective date of this 
AD for computing compliance intervals whenever PW ASB JT8D A6435, 
Revision 1, dated March 7, 2003, refers to the release date of the 
ASB.

Alternative Methods of Compliance

    (d) 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

    (e) Special flight permits may be issued in accordance with 
Sec. Sec.  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

    (f) The actions must be done in accordance with Pratt & Whitney 
alert service bulletin JT8D A6435, Revision 1, dated March 7, 2003. 
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 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

    (g) This amendment becomes effective on September 12, 2003.

    Issued in Burlington, Massachusetts, on July 30, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-19828 Filed 8-7-03; 8:45 am]
BILLING CODE 4910-13-P

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