[Federal Register: August 8, 2003 (Volume 68, Number 153)]
[Rules and Regulations]
[Page 47207-47208]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08au03-5]
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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]
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