[Federal Register Volume 69, Number 137 (Monday, July 19, 2004)]
[Rules and Regulations]
[Pages 42855-42858]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-16005]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18585; Directorate Identifier 2004-NE-28-AD; 
Amendment 39-13731; AD 2004-14-22]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada PW206B, PW206C, 
PW206E, PW207D, and PW207E 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) PW206B engines that have incorporated PWC 
Service Bulletin (SB) No. 28119, and PW206C, PW206E, PW207D, and PW207E 
turboshaft engines. This AD requires checking the automatic low-cycle-
fatigue (LCF) counting data made by the engine Data Collection Unit 
(DCU) on installed engines, and validating proper DCU automatic LCF 
counting before an engine is installed. This AD results from two 
reports of irregular LCF counting, observed between engines on the same 
helicopter, during weekly recording of LCF data in the engine log 
books. We are issuing this AD to prevent critical rotating parts from 
exceeding published life limits, which could result in uncontained 
engine failure and possible loss of the helicopter.

DATES: Effective August 3, 2004. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of August 3, 2004.
    We must receive any comments on this AD by September 17, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     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.
    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 (TC), which is the 
airworthiness authority for Canada, recently notified us that an unsafe 
condition may exist on PWC PW206B engines that have incorporated PWC SB 
No. 28119, and PW206C, PW206E, PW207D, and PW207E turboshaft engines. 
Transport Canada advises that two reports of

[[Page 42856]]

irregular LCF counting were observed between engines on the same 
helicopter, during weekly recording of LCF data in the engine log 
books. PWC investigated and confirmed that irregular DCU LCF count 
recordings can occur, registering above and below the LCF count data of 
a paired reference engine. LCF cycle count data is used to track life-
limited critical rotating parts. Pratt & Whitney Canada determined that 
cycle counting history by the DCU becomes corrupted if system 
electrical power is shut off before the completion of data transfer. 
Data transfer occurs after engine shutdown, as the compressor 
revolutions per minute (rpm) decelerates through 20% speed. Operators 
must verify the DCU data each week as described in the maintenance 
manual. However, some operators have not been verifying this data. This 
condition causes potential for some life limited rotating parts to be 
close to or even beyond the currently approved published life limits.

Relevant Service Information

    We have reviewed and approved the technical contents of PWC Alert 
Service Bulletin (ASB) No. PW200-72-A28252, Revision 2, dated March 11, 
2004. That ASB describes procedures to compare the LCF counting data 
recorded by the DCU to the data recorded in the engine log books. We 
have also reviewed and approved the technical contents of PWC service 
bulletin (SB) No. PW200-72-28253, dated February 12, 2004, that 
describes procedures for validating proper DCU automatic LCF counting 
before an engine is installed. Transport Canada classified these SBs as 
mandatory and issued AD No. CF-2004-06, dated March 31, 2004, in order 
to ensure the airworthiness of these PWC engines in Canada.

Bilateral Airworthiness Agreement

    These PWC PW206B, PW206C, PW206E, PW207D, and PW207E 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 has 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 PW206B, PW206C, PW206E, PW207D, and PW207E 
turboshaft engines of the same type design. We are issuing this AD to 
prevent critical rotating parts from exceeding published life limits, 
which could result in uncontained engine failure and possible loss of 
the helicopter. This AD requires a Comparison Check and a Consistency 
Check of the automatic LCF counting data made by the engine DCU on 
installed engines, at the following:
     For engines with impeller and or compressor turbine (CT) 
disks and or power turbine (PT) disks having fewer than 2,000 cycles 
life limit remaining on the effective date of the AD; within the next 
50 engine flight hours or two months, whichever occurs first, after the 
effective date of this AD; and
     For engines with impeller and or CT disks and or PT disks 
having from 2,000 to 5,000 cycles life limit remaining on the effective 
date of the AD; within the next 200 engine flight hours or three 
months, whichever occurs first, after the effective date of this AD; 
and;
     For engines with impeller and or CT disks and or PT disks 
having more than 5,000 cycles life limit remaining on the effective 
date of the AD; within the next 500 engine flight hours or four months, 
whichever occurs first, after the effective date of this AD.
    This AD also requires validating proper DCU automatic LCF counting 
before an engine is installed. 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 posted new AD actions on the DMS 
and assigned 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-2004-18585; 
Directorate Identifier 2004-NE-28-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.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will

[[Page 42857]]

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 Federal 
Aviation Administration 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 FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2004-14-22 Pratt & Whitney Canada: Amendment 39-13731. Docket No. 
FAA-2004-18585; Directorate Identifier 2004-NE-28-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
3, 2004.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Pratt & Whitney Canada (PWC) PW206B 
engines that have incorporated PWC Service Bulletin (SB) No. 28119, 
and PW206C, PW206E, PW207D, and PW207E turboshaft engines. These 
engines are installed on, but not limited to, Augusta 109E, Bell 
427, Eurocopter EC135, and MD Explorer helicopters.

Unsafe Condition

    (d) This AD results from two reports of irregular LCF counting 
observed between engines on the same helicopter, during weekly 
recording of LCF data in the engine log books. We are issuing this 
AD to prevent critical rotating parts from exceeding published life 
limits, which could result in uncontained engine failure and 
possible loss of 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.

Confirmation of Data Collection Unit (DCU) Properly Collecting Engine 
Low-Cycle-Fatigue (LCF) Data, and Confirmation of Engine LCF Count 
Values

    (f) To confirm that the data stored in the DCU is correct and 
that the data recorded in the engine log books is correct, do a 
Comparison Check and a Consistency Check as specified in paragraphs 
(g) and (h) of this AD, within the following compliance 
requirements:
    (1) For engines with impeller and or compressor turbine (CT) 
disks and or power turbine (PT) disks having fewer than 2,000 cycles 
life limit remaining on the effective date of this AD, do a 
Comparison Check and a Consistency Check within the next 50 engine 
flight hours or two months, whichever occurs first, after the 
effective date of this AD; and
    (2) For engines with impeller and or CT disks and or PT disks 
having from 2,000 to 5,000 cycles life limit remaining on the 
effective date of this AD; do a Comparison Check and a Consistency 
Check within the next 200 engine flight hours or three months, 
whichever occurs first, after the effective date of this AD; and
    (3) For engines with impeller and or CT disks and or PT disks 
having more than 5,000 cycles life limit remaining on the effective 
date of this AD; do a Comparison Check and a Consistency Check 
within the next 500 engine flight hours or four months, whichever 
occurs first, after the effective date of this AD.

Comparison Check

    (g) Do a Comparison Check of the data stored by the DCU using 
paragraph 3.C of PWC Alert Service Bulletin (ASB) No. PW200-72-
28252, Revision 2, dated March 11, 2004. Interpret the results of 
the Comparison Check using paragraphs 3.C.9.a. and 3.C.9.b. of PWC 
ASB No. PW200-72-28252, Revision 2, dated March 11, 2004. If 
necessary, restore baseline LCF life of components using manual 
counting using paragraph 3.E of PWC ASB No. PW200-72-28252, Revision 
2, dated March 11, 2004.

Consistency Check

    (h) Do a Consistency Check by reviewing the engine log books to 
confirm the impeller, CT, and PT disks LCF counts are correct using 
paragraph 3.D. of PWC ASB No. PW200-72-28252, Revision 2, dated 
March 11, 2004.
    (1) Interpret the results using paragraphs 3.D.5 and 3.D.6 of 
PWC ASB No. PW200-72-28252, Revision 2, dated March 11, 2004.
    (2) If necessary, restore the baseline LCF life of components 
using manual counting as indicated in paragraph 3.E. of PWC ASB No. 
PW200-72-28252, Revision 2, dated March 11, 2004.

Components Exceeding Published Life Limit

    (i) Before further flight, replace any impeller, CT, or PT disk 
that exceeds its published life limit.

Validating Proper DCU Automatic LCF Counting Before an Engine Is 
Installed

    (j) Before an engine is installed, validate the proper DCU 
automatic LCF counting using the checks in paragraphs (g) and (h) of 
this AD and using paragraphs 3A. through 3.A.(21)(a)15 of PWC 
Service Bulletin (SB) No. PW200-72-28253, dated February 12, 2004.

Previous Credit

    (k) Previous credit is allowed for Comparison Checks and 
Consistency Checks that were done in accordance with the Original, 
Revision 1, or Revision 2 of PW ASB No. PW200-72-A28252, before the 
effective date of this AD.

Alternative Methods of Compliance

    (l) 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.

Material Incorporated by Reference

    (m) You must use the Pratt & Whitney Canada service information 
specified in Table 1 to perform the checks required by this AD. The 
Director of the Federal Register approved the incorporation by 
reference of the documents listed in Table 1 of this AD 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; 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.

[[Page 42858]]



                                      Table 1.--Incorporation by Reference
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       Service bulletin No.                  Page                Revision                      Date
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PW200-72-A28252...................  ALL..................  2...................  March 11, 2004.
Total Pages: 11
PW200-72-28253....................  ALL..................  Original............  February 12, 2004.
Total Pages: 10
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Related Information

    (n) Transport Canada airworthiness directive No. CF-2004-06, 
dated March 31, 2004, also addresses the subject of this AD.

    Issued in Burlington, Massachusetts, on July 7, 2004.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-16005 Filed 7-16-04; 8:45 am]
BILLING CODE 4910-13-P