[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.Cook@faa.dot.gov. 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]
BILLING CODE 4910-13-U
