[Federal Register Volume 69, Number 190 (Friday, October 1, 2004)]
[Rules and Regulations]
[Pages 58824-58826]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21913]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19170; Directorate Identifier 2004-NE-18-AD; 
Amendment 39-13809; AD 2004-20-04]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada PT6B-36A and 
PT6B-36B Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Pratt & Whitney Canada (PWC) PT6B-36A and PT6B-36B turboshaft engines 
with compressor rear hubs, part number (P/N) 3018111 installed. This AD 
requires reviewing, and correcting if necessary the critical part 
record for compressor rear hubs, P/N 3018111. This AD also requires 
removing compressor rear hubs from service that exceed the published 
part life limit, before further flight. This AD results from the 
discovery of a compressor rear hub, P/N 3018111, that exceeded the 
published life limit. This occurred because the operator used an 
incorrect life limit calculation contained in a PWC Service Bulletin. 
We are issuing this AD to prevent uncontained failure of the compressor 
rear hub and damage to the airplane.

DATES: Effective October 18, 2004. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of October 18, 2004.
    We must receive any comments on this AD by November 30, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD.

[[Page 58825]]

     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    You can get the service information identified in this AD from 
Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada 
J4G1A1. This information may be examined at the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, SW., 
Nassif Building, Room PL-401, Washington, DC 20590-001, on the internet 
at http://dms.dot.gov; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    You may examine the comments on this AD in the AD docket on the 
Internet at http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: Transport Canada, which is the airworthiness 
authority for Canada, recently notified us that an unsafe condition 
might exist on PWC PT6B-36A and PT6B-36B turboshaft engines. Transport 
Canada advises that a compressor rear hub, P/N 3018111, was discovered 
that exceeded the published life limit. This occurred because the 
operator used an incorrect life limit calculation. PWC investigated and 
confirmed that PWC Service Bulletin (SB) No. 11002, Original issue-
through-Revision 7, incorrectly listed the Flight Count Factor (FCF) of 
1 for compressor rear hubs, P/N 3018111. The correct FCF for that part 
is 3.

Relevant Service Information

    We have reviewed and approved the technical contents of PWC SB No. 
11002, Revision 8, dated June 11, 2003, that provides the service life 
limit and correct FCF for compressor rear hubs P/N 3018111. Transport 
Canada classified this service bulletin as mandatory and issued AD CF-
2003-16, dated June 27, 2003, to ensure the airworthiness of these 
PT6B-36A and PT6B-36B turboshaft engines in Canada.

Bilateral Airworthiness Agreement

    These PWC PT6B-36A and PT6B-36B turboshaft engines are manufactured 
in Canada and are 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. Under this bilateral airworthiness agreement, Transport 
Canada kept the FAA informed of the situation described above. We have 
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.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other PWC PT6B-36A and PT6B-36B turboshaft engines of the 
same type design. We are issuing this AD to prevent uncontained failure 
of the compressor rear hub and damage to the airplane. This AD requires 
reviewing, and correcting if necessary the critical part record for 
compressor rear hubs, P/N 3018111. This AD also requires removing 
compressor rear hubs from service that exceed the published part life 
limit, before further flight. You must use the service information 
described previously to perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Docket Management System (DMS)

    We have implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, we post new AD actions on the DMS 
and assign a DMS docket number. We track each action and assign a 
corresponding Directorate identifier. The DMS docket No. is in the form 
``Docket No. FAA-200X-XXXXX.'' Each DMS docket also lists the 
Directorate identifier (``Old Docket Number'') as a cross-reference for 
searching purposes.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2004-19170; 
Directorate Identifier 2004-NE-18-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You can get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is located on 
the plaza level of the Department of Transportation Nassif Building at 
the street address stated in ADDRESSES. Comments will be available in 
the AD docket shortly after the DMS receives them.

[[Page 58826]]

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the FAA 
amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2004-20-04 Pratt & Whitney Canada: Amendment 39-13809. Docket No. 
FAA-2004-19170; Directorate Identifier 2004-NE-18-AD.

Effective Date

    (a) This AD becomes effective October 18, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Pratt & Whitney Canada (PWC) PT6B-36A and 
PT6B-36B turboshaft engines with compressor rear hubs, part number 
(P/N) 3018111 installed. These engines are installed on, but not 
limited to, Sikorsky S-76B helicopters.

Unsafe Condition

    (d) This AD results from results from the discovery of a 
compressor rear hub, P/N 3018111, that exceeded the published life 
limit. This occurred because the operator used an incorrect life 
limit calculation contained in a PWC Service Bulletin. We are 
issuing this AD to prevent uncontained failure of the compressor 
rear hub and damage to the helicopter.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.
    (f) Within 30 days or at the next engine shop visit, whichever 
occurs first after the effective date of this AD, do the following:
    (1) Using the Flight Count Factor of 3, review and correct the 
critical part record for compressor rear hubs, P/N 3018111. Use 
paragraph 3 of the Accomplishment Instructions of PWC Service 
Bulletin (SB) No. PT6B-72-11002, Revision 8, dated June 11, 2003, to 
do this.
    (2) Remove the compressor rear hub from service before further 
flight, if its life limit is found to be at or higher than the 
published life limit in PWC SB No. PT6B-72-11002, Revision 8, dated 
June 11, 2003.

Alternative Methods of Compliance

    (g) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (h) Under 14 CFR part 39.23, we are limiting the special flight 
permits for this AD by allowing the engine to operate an additional 
25 cycles-in-service or 25 operating hours, whichever occurs first, 
for moving the helicopter to a location where the requirements of 
this AD can be done.

Material Incorporated by Reference

    (i) You must use Pratt & Whitney Canada Service Bulletin No. 
PT6B-72-11002, Revision 8, dated June 11, 2003, to perform the 
reviews and corrections required by this AD. The Director of the 
Federal Register approved the incorporation by reference of this 
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. You can get a copy from Pratt & Whitney Canada, 1000 Marie-
Victorin, Longueuil, Quebec, Canada J4G1A1. You may review copies at 
the Docket Management Facility; U.S. Department of Transportation, 
400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, 
DC 20590-001, on the Internet at http://dms.dot.gov; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Related Information

    (j) Transport Canada airworthiness directive CF-2003-16, dated 
June 27, 2003, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on September 24, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-21913 Filed 9-30-04; 8:45 am]
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