[Federal Register Volume 63, Number 193 (Tuesday, October 6, 1998)]
[Rules and Regulations]
[Pages 53560-53562]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-26528]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-58-AD; Amendment 39-10817; AD 98-17-10]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Canada PW530A Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule, request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 98-17-10 that was sent previously
to all known U.S. owners and operators of Pratt & Whitney Canada (PWC)
PW530A series turbofan engines by individual letters. This AD requires
recording engine surge events in the aircraft maintenance records. If
an engine surge event is experienced, this AD requires, prior to the
next flight, inspecting that engine for evidence of second stage stator
vanes rubbing on the compressor rotor. In addition, this AD requires
reworking all affected engines to increase the clearance between the
second stage stator vanes and the compressor rotor. This amendment is
prompted by reports of 4 inflight engine shutdowns and 2 additional
unscheduled engine removals for significant compressor rotor damage.
The actions specified by this AD are intended to prevent an inflight
engine shutdown due to rubbing of the second stage stator vanes on the
compressor rotor.
DATES: Effective October 21, 1998, to all persons except those persons
to whom it was made immediately effective by priority letter AD 98-17-
10, issued on August 7, 1998, which contained the requirements of this
amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 21, 1998.
Comments for inclusion in the Rules Docket must be received on or
before December 7, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-58-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.dot.gov''. Comments sent via the Internet must contain
the docket number in the subject line.
The applicable service information may be obtained from Pratt &
Whitney Canada, Inc., 1000 Marie-Victorin, Longueuil, Quebec, Canada
J4G 1A1; Attn: Supervisor, Publications Customer Service (01CA4);
telephone (514) 647-2705, fax (514) 647-2702. 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: Richard Woldan, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7136, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: Transport Canada, which is the airworthiness
authority for Canada, recently notified the Federal Aviation
Administration (FAA) that an unsafe condition may exist on certain
Pratt & Whitney Canada (PWC) PW530A series turbofan engines. Transport
Canada advises that they have received reports of 4 inflight engine
shutdowns and 2 additional unscheduled engine removals for significant
compressor rotor damage. The investigation revealed that compressor
rotor damage and a high rate of inflight engine shutdowns result from
rubbing of the second stage stator vanes on the compressor rotor. The
original type design second stage stator clearance was insufficient to
prevent rubbing of the stator vanes on the compressor rotor during all
phases of engine operation. This condition, if not corrected, can
result in an inflight engine shutdown due to rubbing of the second
stage stator vanes on the compressor rotor.
PWC has issued Service Bulletin (SB) No. PW500-72-30063, Revision
2, dated July 10, 1998, that specifies inspection procedures for
rubbing of the second stage stator vanes on the compressor rotor, and
SB No. PW500-72-30044, Revision 2, dated July 10, 1998, that specifies
procedures for reworking the engine to increase the clearance between
the second stage stator vanes and the compressor rotor. Transport
Canada classified these SBs as mandatory and issued airworthiness
directive (AD) CF-98-18, dated July 16, 1998, in order to assure the
airworthiness of these engines in Canada.
This engine model is manufactured in Canada and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to
[[Page 53561]]
this bilateral airworthiness agreement, Transport Canada has kept the
FAA informed of the situation described above. The FAA has examined the
findings of Transport Canada, reviewed all available information, and
determined that AD action is necessary for products of this type design
that are certificated for operation in the United States.
On August 7, 1998, the Federal Aviation Administration (FAA) issued
priority letter airworthiness directive (AD) 98-17-10, applicable to
PWC PW530A series turbofan engines.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
requires, for aircraft with one or more affected engines identified by
serial numbers (S/Ns) in the applicability section of this AD,
recording engine surge events in the aircraft maintenance records. If
an engine surge event is experienced, this AD requires, prior to the
next flight, inspecting that engine for evidence of second stage stator
vanes rubbing on the compressor rotor. If evidence of rubbing is
discovered, this AD requires, prior to further flight, removal from
service of the engine that experienced rubbing and replacement with a
serviceable engine. In addition, this AD requires, within 200 hours
time in service (TIS) after the effective date of this AD, or prior to
December 31, 1998, whichever occurs first, reworking all affected
engines to increase the clearance between the second stage stator vanes
and the compressor rotor. The calendar end-date was determined based
upon risk analysis. The actions are required to be accomplished in
accordance with the SBs described previously.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on August 7, 1998, to all known U.S. owners and operators of PWC
PW530A series turbofan engines. These conditions still exist, and the
AD is hereby published in the Federal Register as an amendment to
Section 39.13 of part 39 of the Federal Aviation Regulations (14 CFR
part 39) to make it effective to all persons.
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 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 98-ANE-58-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:
98-17-10 Pratt & Whitney Canada: Amendment 39-10817 Docket 98-ANE-
58-AD.
Applicability: Pratt & Whitney Canada (PWC) PW530A series
turbofan engines, with serial numbers (S/Ns) PCE-DA0001 through PCE-
DA0059, and S/Ns PCE-DA0061 through PCE-DA0064 (S/N PCE-DA0060 is
not affected, as it was shipped with the increased type design
clearance). These engines are installed on but not limited to Cessna
Citation Model 550 Bravo 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 (e) 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 inflight engine shutdown due to rubbing of the second
stage stator vanes on the compressor rotor, accomplish the
following:
(a) In the event of an engine surge, make a record of the engine
which surged and the date and approximate time of the event in the
aircraft maintenance records. For this purpose, an engine surge is
defined as unstable engine operation which is accompanied by unusual
sounds which could be described as bangs, pops, growls, or rumbles
and which may also be accompanied by increased engine vibration
levels.
[[Page 53562]]
(b) If an engine surge event is experienced, prior to the next
flight, inspect that engine for evidence of rubbing of the second
stage stator vanes on the compressor rotor in accordance with PWC
Service Bulletin (SB) No. PW500-72-30063, Revision 2, dated July 10,
1998.
(c) If evidence of rubbing is discovered, prior to further
flight, remove from service the engine that experienced rubbing and
replace with a serviceable engine.
(d) Within 200 hours time in service (TIS) after the effective
date of this AD, or prior to December 31, 1998, whichever occurs
first, rework all affected engines identified by S/N in the
applicability of this AD to increase the clearance between the
second stage stator vanes and the compressor rotor, in accordance
with PWC SB No. PW500-72-30044, Revision 2, dated July 10, 1998.
Completion of this rework constitutes terminating action to the
inspection requirements of this AD.
(e) 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 requests through an appropriate FAA
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.
(f) The requirements of this AD shall be done in accordance with
the following PWC SBs:
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Document No. Pages Revision Date
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PW500-72-30063.................................. 1-5 2 July 10, 1998.
Total pages: 5.
PW500-72-30044.................................. 1-6 2 July 10, 1998.
Total pages: 6.
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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 Canada, Inc., 1000
Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1; Attn: Supervisor,
Publications Customer Service (01CA4); telephone (514) 647-2705, fax
(514) 647-2702. 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 October 21, 1998, to all
persons except those persons to whom it was made immediately
effective by priority letter AD 98-17-10, issued August 7, 1998,
which contained the requirements of this amendment.
Issued in Burlington, Massachusetts, on September 28, 1998.
Diane Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-26528 Filed 10-5-98; 8:45 am]
BILLING CODE 4910-13-P
