[Federal Register Volume 68, Number 57 (Tuesday, March 25, 2003)]
[Proposed Rules]
[Pages 14351-14353]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-6997]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-41-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a 
new airworthiness directive (AD) that is applicable to Pratt & Whitney 
(PW) JT8D-209, -217, -217A, -217C, and -219 series turbofan engines. 
This proposal would require removal and replacement of protective 
coating of the

[[Page 14352]]

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 proposal is 
prompted by reports from operators of cracks observed in JT8D engine 
steel HPC disks. The actions specified by the proposed AD are intended 
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: Comments must be received by May 27, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2002-NE-41-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: [email protected]. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in the proposed rule 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 FAA, New England Region, Office of the 
Regional Counsel, 12 New England Executive Park, Burlington, MA.

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: 

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NE-41-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2002-NE-41-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The FAA has received reports of cracks observed in steel HPC disks 
on PW JT8D-209, -217, -217A, -217C, and -219 series turbofan engines. 
Investigation has revealed that four of these disks cracked as the 
result of corrosion pits originating in the disk dovetail slots and one 
disk cracked as the result of corrosion pits in the tierod hole area.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of PW 
alert service bulletin (ASB) A6435, Revision 1, dated March 7, 2003, 
that describes procedures for initial and repetitive inspections to 
detect corrosion and cracks in 7th and 9th through 12th stage HPC disks 
and 8th stage HPC hubs, and removal from service of those HPC disks and 
hubs corroded beyond serviceable limits or cracked.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Pratt & Whitney JT8D-200 series turbofan 
engines of the same type design, the proposed AD would require 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. The actions would be required to be 
done in accordance with the alert service bulletin described 
previously.

Economic Analysis

    There are approximately 2,200 JT8D-200 series turbofan engines of 
the affected design in the worldwide fleet. The FAA estimates that 
1,470 engines installed on airplanes of U.S. registry would be affected 
by this proposed AD. The FAA also estimates that it would take 
approximately 96 work hours per engine to perform the proposed actions, 
and that the average labor rate is $60 per work hour. The FAA estimates 
that 60% of the inspected disks will require replacement at a prorated 
cost $29,090 per engine. Based on these figures, the total cost of the 
proposed AD to U.S. operators is estimated to be $51,229,500.

Regulatory Analysis

    This proposed 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 proposed rule.
    For the reasons discussed above, I certify that this proposed 
regulation (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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

[[Page 14353]]

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. Section 39.13 is amended by adding the following new 
airworthiness directive:

Pratt & Whitney: Docket No. 2002-NE-41-AD.

    Applicability: This airworthiness directive (AD) is applicable 
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 and 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: Compliance with this AD is required as indicated, 
unless already 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) 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 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 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.

    Issued in Burlington, Massachusetts, on March 18, 2003.
Robert G. Mann,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-6997 Filed 3-24-03; 8:45 am]
BILLING CODE 4910-13-P