[Federal Register Volume 63, Number 38 (Thursday, February 26, 1998)]
[Rules and Regulations]
[Pages 9730-9732]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3799]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-44-AD; Amendment 39-10326; AD 98-04-14]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney PW4164, PW4168, and
PW4168A Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to Pratt & Whitney PW4164, PW4168, and PW4168A series
turbofan engines. This action requires initial and repetitive
inspections for loose or broken front pylon mount bolts, replacement,
if necessary, with new bolts, and establishment of a new cyclic life
limit. This amendment is prompted by new flight test data that indicate
higher than predicted loads. The actions specified in this AD are
intended to prevent front pylon mount bolt failure, which could result
in engine separation from the aircraft.
DATES: Effective March 13, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 13, 1998.
Comments for inclusion in the Rules Docket must be received on or
before April 27, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 97-ANE-44-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9-ad-
[email protected]''. Comments sent via the Internet must contain
the docket number in the subject line.
The service information referenced in this AD 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 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.
FOR FURTHER INFORMATION CONTACT: Tara Goodman, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7130, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received data from flight testing of Pratt & Whitney PW4164 and
PW4168 series turbofan engines installed on Airbus Industrie A330
series aircraft. The flight testing revealed higher than predicted
loads for front pylon mount bolts, resulting in decreased service life.
At this time, there are no U.S. operators of this aircraft/engine
combination. This condition, if not corrected, could result in front
pylon mount bolt failure, which could result in engine separation from
the aircraft.
The FAA has reviewed and approved the technical contents of Pratt &
Whitney Service Bulletin (SB) No. PW4G-100-A71-9, Revision 1, dated
November 24, 1997, that describes procedures for initial and repetitive
inspections for loose or broken front pylon mount bolts, replacement,
if necessary, with new bolts, and removal of bolts from service upon
reaching a prescribed service life limit.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design, this AD is
being issued to prevent front pylon mount bolt failure. This AD
requires initial and repetitive inspections for loose or broken front
pylon mount bolts, replacement, if necessary, with new bolts, and
establishment of a new cyclic life limit of 11,000 cycles in service
(CIS). When parts accumulate 6,000 and 8,000 cycles since new (CSN),
this AD requires different inspection procedures to be followed, but
the manufacturer has informed the FAA that they are developing new
material front pylon mount bolts that may be ready and certified for
installation prior to any parts currently in service accumulating 6,000
CSN. When the new material parts are available, future rulemaking may
be forthcoming that may constitute terminating action to the repetitive
inspections required by this AD. The actions would be required to be
accomplished in accordance with the SB described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD
[[Page 9731]]
action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD 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 9-ANE-44-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, 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 adding the following new
airworthiness directive:
98-04-14 Pratt & Whitney: Amendment 39-10326. Docket 97-ANE-44-AD.
Applicability: Pratt & Whitney PW4164, PW4168, and PW4168A
series turbofan engines, with front pylon mount bolts, Part Number
(P/N) 54T670, installed. These engines are installed on but not
limited to Airbus Industrie A330 series aircraft.
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 (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: Required as indicated, unless accomplished
previously.
To prevent front pylon mount bolt failure, which could result in
engine separation from the aircraft, accomplish the following:
(a) Perform initial and repetitive torque checks of front pylon
mount bolts, and replace, if necessary, with new bolts, in
accordance with the Accomplishment Instructions of Pratt & Whitney
Service Bulletin (SB) No. PW4G-100-A71-9, Revision 1, dated November
24, 1997, as follows:
(1) For front pylon mount bolts with more than 1,000 cycles
since new (CSN) but less than 5,750 CSN on the effective date of
this AD, accomplish the following in accordance with Part (A) of the
Accomplishment Instructions of the SB:
(i) Perform an initial torque check within 250 cycles in service
(CIS) after the effective date of this AD, or prior to the next
engine removal for any cause, whichever occurs first.
(ii) Thereafter, perform torque checks at intervals not less
than 750 or greater than 1,250 CIS since last torque check, not to
exceed 11,000 CSN.
(2) For front pylon mount bolts with 5,750 or more CSN but less
than 8,000 CSN on the effective date of this AD, accomplish the
following in accordance with Part (B) of the Accomplishment
Instructions of the SB:
(i) Perform an initial torque check within 250 CIS after the
effective date of this AD, or prior to the next engine removal for
any cause, whichever occurs first.
(ii) Thereafter, perform torque checks at intervals not less
than 750 or greater than 1,250 CIS since last torque check, not to
exceed 11,000 CSN.
(3) For front pylon mount bolts with 8,000 or more CSN but less
than 11,000 CSN on the effective date of this AD, perform an
inspection in accordance with the schedule and procedures of the
Appendix to the SB.
(4) Prior to further flight, replace all four bolts in
accordance with Part (A), Paragraph 1(D) of the Accomplishment
Instructions of the SB, if any are found loose or broken.
(b) This AD establishes a new life limit of 11,000 CSN for front
pylon mount bolts,
P/N 54T670. Except as provided in paragraph (c) of this AD, no front
pylon mount bolts may exceed this new life limit after the effective
date of this AD.
(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.
Operators shall submit their request 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.
(d) 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 inspection requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance
with the following PW SB:
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Document No. Pages Revision Date
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PW4G-100-A71-9.................... 1................. 1.................... November 24, 1997.
2................. Original............. July 31, 1997.
3................. 1.................... November 24, 1997.
4-7............... Original............. July 31, 1997.
8, 9.............. 1.................... November 24, 1997.
10, 11............ Original............. July 31, 1997.
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Total pages: 11.
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, 400 Main St.,
East Hartford, CT 06108; telephone (860) 565-6600, 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.
(f) This amendment becomes effective on March 13, 1998.
Issued in Burlington, Massachusetts, on February 6, 1998.
James C. Jones,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-3799 Filed 2-25-98; 8:45 am]
BILLING CODE 4910-13-P