[Federal Register Volume 62, Number 6 (Thursday, January 9, 1997)]
[Proposed Rules]
[Pages 1299-1301]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-468]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-ANE-35]
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: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to Pratt & Whitney (PW) JT8D-
200 series turbofan engines, that currently requires installation and 
periodic inspection of temperature indicators installed on the No. 4 
and 5 bearing compartment scavenge oil tube and performance of any 
necessary corrective action. This action would require the installation 
and periodic inspection of temperature indicators to all PW JT8D-200 
series engines, including those incorporating the containment hardware 
specified in with AD 93-23-10. This proposal is prompted by report of 
an uncontained turbine failure due to a high pressure turbine (HPT) 
shaft fracture on an engine that had the containment hardware 
installed. The actions specified by the proposed AD are intended to 
prevent fracture of the HPT shaft, which can result in uncontained 
release of engine fragments, engine fire, inflight engine shutdown, or 
possible aircraft damage.

DATE: Comments must be received by March 10, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 96-ANE-35, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location between 8:00 a.m. and 4:30 p.m., Monday through Friday, 
except Federal holidays.

[[Page 1300]]

    The service information referenced in the proposed rule may be 
obtained from Pratt & Whitney, Publication Department, Supervisor 
Technical Publications Distribution, M/S 132-30, 400 Main St., East 
Hartford, CT 06108; telephone (860) 565-7700, fax (860) 565-4503. This 
information may be examined at the FAA, New England Region, Office of 
the Assistant Chief Counsel, 12 New England Executive Park, Burlington, 
MA.

FOR FURTHER INFORMATION CONTACT: Diane Cook, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (617) 238-
7134, fax (617) 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 notice 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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 96-ANE-35.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Assistant Chief Counsel, 
Attention: Rules Docket No. 96-ANE-35, 12 New England Executive Park, 
Burlington, MA 01803-5299.

Discussion

    On November 3, 1994, the Federal Aviation Administration (FAA) 
issued airworthiness directive AD 94-23-03, Amendment 39-9065 (59 FR 
61789, December 2, 1994), applicable to Pratt & Whitney (PW) JT8D-200 
series turbofan engines, to require installation and periodic 
inspection of temperature indicators installed on the No. 4 and 5 
bearing compartment scavenge oil tube and performance of any necessary 
corrective action. That action was prompted by reports of high pressure 
turbine (HPT) shaft fractures caused by oil fires that resulted from 
internal leakage of thirteenth stage compressor discharge air into the 
No. 4 and 5 bearing compartment. That condition, if not corrected, 
could result in fracture of the HPT shaft, which can result in 
uncontained release of engine fragments, engine fire, inflight engine 
shutdown, or possible aircraft damage.
    Airworthiness directive 94-23-03 excluded from the applicability 
engines that had installed HPT containment hardware in accordance with 
AD 93-23-10. Since the issuance of AD 94-23-03, the FAA has received a 
report of an uncontained turbine failure due to an HPT shaft fracture 
on a PW Model JT8D-219 engine that had the containment hardware 
installed.
    The FAA has reviewed and approved the technical contents of PW 
Alert Service Bulletin (ASB) No. 5944, Revision 3, dated December 17, 
1994, and Revison 2, dated June 8, 1992, that describe procedures for 
installation and periodic inspection of temperature indicators 
installed on the No. 4 and 5 bearing compartment scavenge oil tube and 
performance of any necessary corrective action.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 94-23-03 to require installation and 
periodic inspection of temperature indicators to all PW JT8D-200 series 
engines, including those incorporating the containment hardware 
specified in AD 93-23-10. The actions would be required to be 
accomplished in accordance with the SB described previously.
    There are approximately 2,432 engines of the affected design in the 
worldwide fleet. The FAA estimates that 1,044 engines installed on 
aircraft of U.S. registry would be affected by this proposed AD, that 
it would take approximately 1.5 work hours per engine to accomplish the 
proposed actions, and that the average labor rate is $60 per work hour. 
Based on these figures, the total cost impact of the proposed AD on 
U.S. operators is estimated to be $93,960.

    The regulations proposed herein would not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.

    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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9065 (59 FR 
61789, December 2, 1994) and by adding a new airworthiness directive to 
read as follows:

Pratt & Whitney: Docket No. 96-ANE-35. Supersedes AD 94-23-03, 
Amendment 39-9065.

    Applicability: Pratt & Whitney (PW) JT8D-209, -217, -217A, -
217C, and -219 turbofan engines, installed on but not limited to 
McDonnell Douglas MD-80 series and Boeing 727 series aircraft.

    Note 1: This airworthiness directive (AD) applies to each engine 
identified in the preceding applicability provision, regardless

[[Page 1301]]

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 (f) 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: Required as indicated, unless accomplished 
previously.
    To prevent fracture of the high pressure turbine (HPT) shaft, 
which can result in uncontained release of engine fragments, engine 
fire, inflight engine shutdown, or possible aircraft damage, 
accomplish the following:
    (a) Install and inspect one or two temperature indicators, part 
number (P/N) 810486, or a single or double set of P/N 809129 and P/N 
809130 temperature indicators, on the No. 4 and 5 bearing 
compartment scavenge oil tube, as follows:
    (1) Install temperature indicators on the No. 4 and 5 bearing 
compartment scavenge oil tube in accordance with Section 2.A.(1) of 
the Accomplishment Instructions of PW Alert Service Bulletin (ASB) 
No. 5944, Revision 3, dated December 16, 1994, or Revision 2, dated 
June 8, 1992, within 90 days after the effective date of this 
airworthiness directive (AD).
    (2) Visually inspect temperature indicators within 65 hours TIS 
of installation. Thereafter, inspect at intervals not to exceed 65 
hours TIS since last inspection.
    (3) If upon inspection, the color of any temperature indicator 
window(s) has turned completely black, perform troubleshooting and 
diagnostic testing and corrective action as required, in accordance 
with Section 2.A.(2) (c) and (d) or (f) and (g), as applicable, of 
the Accomplishment Instructions of PW ASB No. 5944, Revision 3, 
dated December 16, 1994, or Revision 2, dated June 8, 1992. Prior to 
returning the engine to service, replace any temperature indicator 
that has turned black and inspect in accordance with paragraphs 
(a)(2) and (a)(3) of this AD.
    (b) For aircraft installations utilizing one P/N 810486 
indicator or one set of P/N 809129 and 809130 indicators, and 
inspection reveals a missing indicator, inspect the remaining 
temperature indicator, if applicable, to determine if the indicator 
window has turned completely black. If the indicator window has 
turned completely black, perform troubleshooting and diagnostic 
testing, and corrective action as required, in accordance with 
paragraph (a)(3) of this AD. If the indicator window has not turned 
completely black or if there are no additional indicators installed, 
then install a new indicator in accordance with Section 2.A.(1) of 
the Accomplishment Instruction of PW ASB No. 5944, Revision No. 3, 
dated December 16, 1994, or Revision 2, dated June 8, 1992, prior to 
return to service, and visually inspect the temperature indicator 
within 65 hours TIS since installation. Thereafter, inspect at 
intervals not to exceed 65 hours TIS since last inspection in 
accordance with paragraphs (a)(2) and (a)(3) of this AD.
    (c) For aircraft installations utilizing two P/N 810486 
indicators or two sets of P/N 809129 and 809130 indicators, and 
inspection reveals a missing indicator(s), inspect the remaining 
temperature indicator(s), if applicable, to determine if the 
indicator window has turned completely black. If the indicator 
window has turned completely black, perform troubleshooting and 
diagnostic testing, and corrective action as required, in accordance 
with paragraph (a)(3) of this AD. If the indicator window has not 
turned completely black, install a new indicator(s) in accordance 
with Section 2.A.(1) of the Accomplishment Instructions of PW ASB 
No. 5944, Revision 3, dated December 16, 1994, or Revision 2, dated 
June 8, 1992, prior to return to service, and visually inspect the 
temperature indicator within 65 hours TIS since installation. 
Thereafter, inspect at intervals not to exceed 65 hours TIS since 
last inspection in accordance with paragraphs (a)(2) and (a)(3) of 
this AD.
    (d) Report the data elements identified in Appendix E of the 
Accomplishment Instructions of PW ASB No. 5944, Revision 3, dated 
December 16, 1994, or Revision 2, dated June 8, 1992, whenever an 
overtemperature condition is observed on any color temperature 
indicator which is the result of an internal engine problem only and 
not resulting from an external cause corrected by the published 
troubleshooting procedures. Data elements should be reported within 
30 days of determining that the overtemperature condition is the 
result of an internal engine problem, to Diane Cook, Aerospace 
Engineer, Engine Certification Office, Engine and Propeller 
Directorate, Aircraft Certification Service, FAA, 12 New England 
Executive Park, Burlington, MA 01803-05299; telephone (617) 238-
7134, fax (617) 238-7199; Internet: Diane.C[email protected]. The 
reporting requirements of this AD terminate six months from the 
effective date of the AD.
    (e) Information collection requirements contained in this 
regulation have been approved by the Office of Management and Budget 
under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 
96-511) and have been assigned OMB control number 2120-0056.
    (f) 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. The 
request should be forwarded through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Engine Certification Office.

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

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

    Issued in Burlington, Massachusetts, on January 2, 1997.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 97-468 Filed 1-8-97; 8:45 am]
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