[Federal Register: July 10, 2002 (Volume 67, Number 132)]
[Proposed Rules]               
[Page 45680-45682]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10jy02-24]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-11-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 certain Pratt & 
Whitney (PW) JT8D-200 series turbofan engines. This proposal would 
require the installation of stops on the fan exit guide vane case. This 
proposal is prompted by reports of the flange between the fan duct case 
and the fan exit guide vane case separating due to a fan blade fracture 
event. The actions specified by the proposed AD are intended to prevent 
the flange between the fan duct case and the fan exit guide vane case 
from separating due to a fan blade failure. Separations of that flange 
could result in damage to the airplane.

DATES: Comments must be received by September 9, 2002.

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-11-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: ``9-ane-adcomment@faa.gov''. 
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) 565-6600, 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-11-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

[[Page 45681]]

FAA, New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2002-NE-11-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    The FAA has received reports of the flange between the fan duct 
case and the fan exit guide vane case separating due to fan blade 
fracture events on PW JT8D-209, -217, -217A, -217C, and ``219 series 
turbofan engines. This proposal would require a one-time installation 
of stops on engines that do not incorporate a fan exit guide vane case 
and fan duct assembly with improved durability and impact resistance, 
part number 805919 or 815377. This proposal is prompted by a number of 
reports of fan case flange separation, one of which occurred in July 
2001 when a JT8D powered MD-80 was required to make an emergency 
landing after experiencing a fan blade fracture, resulting in fan case 
flange separation and high aircraft vibrations. The actions specified 
by the proposed AD are intended to prevent the flange between the fan 
duct case and the fan exit guide vane case from separating due to a fan 
blade failure. This condition, if not corrected, could result in damage 
to the airplane.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of PW 
JT8D-200 Series Service Bulletin No. 6100, Revision 2 dated December 9, 
1998. That SB describes the procedures for installing stops on the fan 
exit guide vane case, to restrict axial separation of the case in the 
event of a case fracture.

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 PW JT8D-209, -217, -217A, -217C, and ``219 
series turbofan engines, the proposed AD would require installation of 
stops on the fan exit guide vane case at the next shop visit in 
accordance with PW SB No. 6100, Revision 2, dated December 9, 1998.

Economic Analysis

    There are approximately 1,346 PW JT8D-200 series engines of the 
affected design in the worldwide fleet. The FAA estimates that 821 
engines installed on airplanes of U.S. registry would be affected by 
this proposed AD. The FAA also estimates that it would take 
approximately 1.5 work hours per engine to perform the proposed 
actions, and that the average labor rate is $60 per work hour. Required 
parts would cost approximately $5,200 per engine. Based on these 
figures, the total cost of the proposed AD to U.S. operators is 
estimated to be $4,343,090.

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:

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-11-AD.

Applicability

    This airworthiness directive (AD) is applicable to Pratt & 
Whitney (PW) JT8D-209, -217, -217A, -217C, and -219 series turbofan 
engines that do not incorporate the fan exit guide vane case and fan 
duct assembly with improved durability and impact resistance, part 
numbers 805919 or 815377. 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 (c) 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, unless already done.
    To prevent the flange between the fan duct and the fan exit 
guide vane from separating due to a fan blade failure, which could 
result in damage to the airplane, do the following:

Installation of Hardware

    (a) At the next shop visit after the effective date of this AD, 
install stops on the fan exit guide vane case in accordance with 
paragraphs 2.A. through 2.C.(1) of the Accomplishment Instructions 
of PW JT8D-200 Series SB No. 6100, Revision 2, dated December 9, 
1998.

Definitions

    (b) For the purposes of this AD, a shop visit is defined as an 
engine removal, where engine maintenance entails separation of pairs 
of major mating engine flanges or the removal of a disk, hub, or 
spool at a maintenance facility that is capable of compliance with 
the instructions of this AD, regardless of other planned 
maintenance.

Alternative Methods of Compliance

    (c) 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

    (d) Special flight permits may be issued in accordance with 
Secs. 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.


[[Page 45682]]


    Issued in Burlington, Massachusetts, on July 1, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-17296 Filed 7-9-02; 8:45 am]
BILLING CODE 4910-13-P