Airworthiness Directives; Pratt & Whitney Canada PW100 Series Turboprop Engines

[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:

------------------------------------------------------------------------
         Document No            Pages     Revision           Date       
------------------------------------------------------------------------
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

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