[Federal Register Volume 63, Number 126 (Wednesday, July 1, 1998)]
[Rules and Regulations]
[Pages 35794-35796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17415]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-33-AD; Amendment 39-10636; AD 98-14-02]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney Canada PW100 Series
Turboprop Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to Pratt & Whitney Canada (PWC) PW100 series turboprop
engines, that requires removal of the existing fuel manifold tubes,
lock plates, and preformed packing; installation of improved fuel
manifold transfer tubes, improved lock plates, and improved preformed
packing; and, after installation, the performance of a leak check. This
amendment is prompted by reports of engine fuel leaks which resulted in
either inflight engine shutdowns or fire warnings. The actions
specified by this AD are intended to prevent engine fuel leaks, which
can result in inflight engine shutdowns or fire warnings.
DATES: Effective August 31, 1998.
[[Page 35795]]
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 31, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil,
Quebec, Canada J4G 1A1; telephone (514) 677-9411, fax (514) 647-3620.
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; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7747, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to Pratt & Whitney Canada (PWC)
PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A,
PW123, PW123B, PW123C, PW123D, PW123E, PW124B, PW125B, PW126A, PW127,
PW127E, PW127F series turboprop engines was published in the Federal
Register on October 24, 1997 (62 FR 55364). That action proposed to
require removal of the existing fuel manifold tubes, lock plates, and
preformed packing and installation of improved fuel manifold transfer
tubes, lock plates, and preformed packing, at the earliest of the
following: (1) the next time, after the effective date of this AD, that
the engine or module is at a maintenance base that can do the
modifications specified, regardless of the scheduled maintenance action
or reason for engine removal; (2) or at the next fuel nozzle change; or
(3) prior to November 30, 1998. This calendar end-date was determined
based upon risk assessment. After installation, but prior to further
flight, this AD requires performing a leak check.
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 states that the affected part numbers (P/Ns) are not
identified in the proposed rule. The FAA does not concur. The affected
P/Ns have been referenced in the applicable PWC Service Bulletins
(SBs).
One commenter states that the parts to be installed should not be
limited to the part numbers identified in the existing SBs. The AD
should make allowance for installing new parts identified in subsequent
revisions. The FAA does not concur. The FAA cannot approve nonexistent
parts of future designs, hence the reference of subsequent revision of
SB in the AD is not permitted. However, additional parts may be
introduced by an AD revision, or through alternative methods of
compliance requests.
One commenter states that the requirements of PWC SB No. 21549 are
not necessary and should not be required by the proposed rule. The FAA
does not concur. That SB introduced improved drain tubes, that have
been shown to reduce or prevent fires. Drain tube leaks have been
attributed to several inflight engine fires.
One commenter states that the drain tubes should be installed in
accordance with PWC SB No. 21077. The FAA concurs in part with the
comment that PWC SB No. 21077 provides instructions for the part
removal and replacement. However, the installation of fuel manifold
drain tubes may be accomplished in accordance with PWC SB No. 21549 or
PWC SB No. 21077. In addition, fuel manifold transfer tube installed in
accordance with PWC No. 21077 or PWC SB No. 21516 is also acceptable.
Paragraph (a) of the AD compliance section has been modified
accordingly.
Since publication of the NPRM, the manufacturer has issued PWC SB
No. 21077, Revision 8, dated April 4, 1998. This final rule references
this latest revision.
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.
The FAA estimates that 1,216 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will not take any
additional work hours per engine to accomplish the proposed actions, as
the actions may be performed during regularly scheduled maintenance or
overhaul. Required parts will cost approximately $370 per engine. Based
on these figures, the total cost impact of the AD on U.S. operators is
estimated to be $449,920.
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 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 adding the following new
airworthiness directive:
98-14-02 Pratt & Whitney Canada: Amendment 39-10636. Docket 97-ANE-
33-AD.
Applicability: Pratt & Whitney Canada (PWC) PW118, W118A,
PW118B, PW119B, PW119C, PW120, PW120A, PW121, W121A, PW123, PW123B,
PW123C, PW123D, PW123E, PW124B, PW125B, PW126A, PW127, PW127E,
PW127F series engines installed on but not limited to Dornier 328,
Fokker 50, Jetstream ATP, ATR42, ATR42-500, ATR72, Embraer EMB-120,
Canadair CL215T, CL415, and DeHavilland Dash-8-100/-200/-300/-315.
Note 1: This airworthiness directive (AD) applies to each engine
identified in the
[[Page 35796]]
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 engine fuel leaks, which can result in inflight
engine shutdowns or fire warnings, accomplish the following:
(a) Remove the existing fuel manifold transfer tubes, transfer
tube lock plates, and fuel manifold drain tubes in accordance with
PWC Service Bulletin (SB) No. 21077, Revision 8, dated April 4,
1998. Remove the existing preformed packing in accordance with PWC
SB No. 21364, Revision 1, dated April 28, 1995. Replace with fuel
manifold transfer tubes in accordance with the following applicable
PWC Service Bulletins (SBs): No. 21077, Revision 8, dated April 4,
1998, or No. 21516, dated August 14, 1997. Replace fuel manifold
drain tubes in accordance with PWC SB No. 21549, dated September 18,
1997 or SB No. 21077, Revision 8, dated April 4, 1998. The
modification must include installation of the improved lock plates
in accordance with PWC SB No. 21373, Revision 3, dated October 11,
1996, and the preformed packing in accordance with PWC SB No. 21364,
Revision 1, dated April 28, 1995, as follows, whichever occurs first
following the effective date of this AD:
(1) At the next engine removal, regardless of cause; or
(2) At the next fuel nozzle change; or
(3) Prior to November 30, 1998.
(b) After the installation of the improved fuel manifold tubes
and lockplates, but prior to further flight, perform a leak check in
accordance with the applicable maintenance manual.
(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 requests 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 requirements of this AD can be accomplished.
(e) The actions required by 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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21077........................ 1-9 8........... April 4, 1998.
Total Pages: 9
21516........................ 1-5 Original.... August 14, 1997.
Total Pages: 5.
21549........................ 1-4 Original.... September 18,
1997.
Total Pages: 4.
21373........................ 1-11 3........... October 11, 1996.
Total Pages: 11.
21364........................ 1-8 1........... April 28, 1995.
Total Pages: 8.
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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, 1000 Marie-
Victorin, Longueuil, Quebec, Canada J4G 1A1; telephone (514) 677-
9411, fax (514) 647-3620. 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 August 31, 1998.
Issued in Burlington, Massachusetts, on June 23, 1998.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 98-17415 Filed 6-30-98; 8:45 am]
BILLING CODE 4910-13-U
