[Federal Register Volume 64, Number 209 (Friday, October 29, 1999)]
[Rules and Regulations]
[Pages 58328-58329]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-28075]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 92-ANE-15; Amendment 39-11392; AD 99-22-14]
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 supersedes an existing airworthiness directive
(AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan
engines, that currently requires installation of high pressure turbine
(HPT) containment hardware. This amendment requires removing low
pressure turbine (LPT)-to-exhaust case bolts and nuts and replacement
with improved LPT-to-exhaust case bolts and nuts, and installation of
improved HPT containment hardware. This amendment is prompted by
uncontained HPT events resulting from HPT shaft fractures and LPT
flange separations resulting from LPT blade failures. The actions
specified by this AD are intended to prevent damage to the airplane
resulting from uncontained engine debris following an HPT shaft
fracture or an LPT blade failure.
DATES: Effective December 28, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 28, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Pratt & Whitney, Publications Department, Supervisor
Technical Publications Distribution, M/S 132-30, 400 Main St., East
Hartford, CT 06108; telephone (860) 565-8770, fax (860) 565-4503. This
information may be examined at the Federal Aviation Administration
(FAA), New England Region, Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA 01803-5299; or at the Office of
the Federal Register, 800 North Capitol Street, NW, suite 700,
Washington, DC.
FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7152, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 93-23-10,
Amendment 39-8746 (57 FR 57705, December 17, 1993), which is applicable
to certain Pratt & Whitney (PW) JT8D-200 series turbofan engines, was
published in the Federal Register on March 15, 1999 (64 FR 12770). That
action proposed to require removing low pressure turbine (LPT)-to-
exhaust case bolts and nuts and replacement with improved LPT-to-
exhaust case bolts and nuts, and installation of improved high pressure
turbine (HPT) containment hardware.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter requests Revision 1 of PW Service Bulletin (SB) No.
6149, dated August 27, 1998, be the required SB for performance of the
actions required by paragraph (b) of the proposed rule. The FAA
concurs. Since publication of the NPRM, PW has also issued Revision 1
to PW Alert Service Bulletin (ASB) No. A6346, dated April 23, 1999. The
FAA has added both later revisions to this final rule as references.
Operators who have installed hardware in accordance with the original
versions of the SB and the ASB are not required to apply for an
Alternate Method of Compliance (AMOC) in order to be considered as
having complied with the AD.
One commenter states that the estimated number of domestic JT8D-
217C/219 engines is incorrect in the economic analysis of the proposed
rule, and offers a better estimate. The FAA concurs and has revised the
economic analysis in this final rule.
One commenter has no objection to the rule as proposed.
One commenter agrees with the rule as proposed.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
There are approximately 2,727 engines of the affected design in the
worldwide fleet. The FAA estimates that 1,473 engines installed on
airplanes of U.S. registry will be affected by this AD, and that no
additional work hours per engine to accomplish the required actions are
necessary since they should take place when an engine is already
sufficiently disassembled for normal maintenance on those parts.
Required parts will cost approximately $19,911 per engine for the 1,030
engines requiring improved (over AD 93-23-10) containment hardware, and
$3,275 for 1,473 engines requiring improved bolts and nuts. Based on
these figures, the total cost impact of the AD on U.S. operators is
estimated to be $25,332,405. The manufacturer may be providing parts
free of charge; therefore the actual cost to operators may be reduced.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 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
[[Page 58329]]
of it may be obtained from 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
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
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 removing Amendment 39-8746 (57 FR
57705, December 17, 1993) and by adding a new airworthiness directive,
Amendment 39-11392, to read as follows:
99-22-14 Pratt & Whitney: Amendment 39-11392. Docket 92-ANE-15.
Supersedes AD 93-23-10, Amendment 39-8746.
Applicability: Pratt & Whitney (PW) Model JT8D-209, -217, -217A,
-217C, and -219 turbofan engines, installed on but not limited to
McDonnell Douglas MD-80 series airplanes.
Note 1: This airworthiness directive (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: Required as indicated, unless accomplished
previously.
To prevent damage to the airplane resulting from uncontained
engine debris following a high pressure turbine (HPT) shaft fracture
or a low pressure turbine (LPT) blade failure, accomplish the
following:
(a) For PW Model JT8D-217C and -219 engines, install improved
HPT containment hardware at the next shop visit after the effective
date of this AD, but no later than December 31, 2004, in accordance
with PW JT8D Alert Service Bulletin (ASB) No. A6346, dated September
10, 1998, or Revision 1, dated April 23, 1999.
(b) For PW Model JT8D-209, -217, -217A, -217C and -219 engines,
install improved LPT-to-turbine exhaust case bolts and nuts at the
next shop visit after the effective date of this AD but no later
than December 31, 2004, in accordance with paragraph 2.A.(1) and
2.B.(1) of PW Service Bulletin (SB) No. 6149, January 19, 1994, or
Revision 1, dated August 27, 1998.
(c) For the purpose of this AD, an engine shop visit is defined
as engine maintenance that entails the separation of the J and K
flanges.
(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 shall submit their requests 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 method of compliance with this AD, if any, may be
obtained from the ECO.
(e) 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 airplane to a location where
the requirements of this AD can be accomplished.
(f) The actions required by this AD shall be done in accordance
with the following PW service documents:
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Document No. Pages Revision Date
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ASB No. A6346................. 1,2.................. 1.................... April 23, 1999.
3.................... Original............. September 10, 1998.
4.................... 1.................... April 23, 1999.
5,6.................. Original............. September 10, 1998.
7-25................. 1.................... April 23, 1999.
Total pages: 25.
ASB No. A6346................. 1-23................. Original............. September 10, 1998.
Total pages: 23.
SB No. 6149................... 1-3.................. 1.................... August 27, 1998.
4-10................. Original............. January 19, 1994.
Total pages: 10.
SB No. 6149................... 1-10................. Original............. January 19, 1994.
Total pages: 10.
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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, Publications
Department, Supervisor Technical Publications Distribution, M/S 132-
30, 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.
(g) This amendment becomes effective on December 28, 1999.
Issued in Burlington, Massachusetts, on October 21, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-28075 Filed 10-28-99; 8:45 am]
BILLING CODE 4910-13-U
