[Federal Register Volume 68, Number 157 (Thursday, August 14, 2003)]
[Rules and Regulations]
[Pages 48544-48546]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-20484]



[[Page 48544]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-25-AD; Amendment 39-13263; AD 2003-16-10]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada PW206A and 
PW206E 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) PW206A and PW206E turboshaft engines. This 
AD requires initial and repetitive borescope inspections of compressor 
turbine and power turbine blades for blade axial shift, and replacement 
of blade retaining rivets and certain rotor air seals as terminating 
action for the repetitive borescope inspections.
    This AD is prompted by reports of engine shutdowns and emergency 
landings due to severe vibration and drops in engine torque, and an 
increase in internal engine temperature, triggering in-flight engine 
fire warnings. We are issuing this AD to prevent turbine blade axial 
shift, which could cause high levels of vibration, loss of engine 
torque, in-flight engine shutdown, and possible uncontained engine 
failure.

DATES: Effective August 29, 2003. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of August 29, 2003.
    We must receive any comments on this AD by October 14, 2003.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
    [sbull] By mail: The Federal Aviation Administration (FAA), New 
England Region, Office of the Regional Counsel, Attention: Rules Docket 
No. 2003-NE-25-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
    [sbull] By fax: (781) 238-7055.
    [sbull] By e-mail: [email protected].
    You may get the service information referenced in this AD from 
Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, Canada 
J4G1A1. You may examine the service information 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.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

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 the FAA that an unsafe 
condition may exist on PWC PW206A and PW206E turboshaft engines. 
Transport Canada advises that there have been several reports of PW206-
powered helicopters where axial shifting of compressor turbine blades 
and power turbine blades resulted in heavy blade rubs, causing an 
increase in internal engine temperature, triggering in-flight engine 
fire warnings and subsequent emergency landings.

Relevant Service Information

    We have reviewed and approved the technical contents of the 
following Pratt & Whitney Canada service documents:
    [sbull] Alert Service Bulletin (ASB) No. PW200-72-A28242, Revision 
1, dated October 2, 2002, that describes procedures for borescope 
inspecting of compressor turbine blades and power turbine blades for 
axial shift within the disks.
    [sbull] Service Bulletin (SB) No. PW200-72-28069, Revision 5, dated 
February 10, 2003, that describes procedures for replacing compressor 
turbine blade retaining rivets, the No. 3 bearing rotor air seal, and 
the No. 4 bearing front rotor air seal.
    [sbull] SB No. PW200-72-28239, Revision 2, dated February 10, 2003, 
that describes procedures for replacing power turbine blade retaining 
rivets.
    Transport Canada classified these service bulletins as mandatory 
and issued AD CF-2003-06, dated February 4, 2003, in order to assure 
the airworthiness of these PWC PW206A and PW206E turboshaft engines in 
Canada.

Bilateral Airworthiness Agreement

    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. 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 PW206A and PW206E turboshaft engines of the same 
type design. We are issuing this AD to prevent turbine blade axial 
shift, leading to high levels of vibration, loss of engine torque, in-
flight engine shutdown, and possible uncontained engine failure. This 
AD requires:
    [sbull] Initial and repetitive borescope inspections of compressor 
turbine blades and power turbine blades for blade axial shift within 
the turbine disks, and
    [sbull] Replacement of blade retaining rivets, the No. 3 bearing 
rotor air seal, and the No. 4 bearing front rotor air seal as mandatory 
terminating action for the repetitive borescope inspections.
    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.

Changes to 14 CFR Part 39--Effect on the AD

    On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 
47997, July 22, 2002), which governs our AD system. This regulation now 
includes material that relates to special flight permits, alternative 
methods of compliance, and altered products. This material previously 
was included in each individual AD. Since this material is included in 
14 CFR part 39, we will not include it in future AD actions.

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

[[Page 48545]]

ADDRESSES. Include ``AD Docket No. 2003-NE-25-AD'' in the subject line 
of your comments. If you want us to acknowledge receipt of your mailed 
comments, send us a self-addressed, stamped postcard with the docket 
number written on it; we will date-stamp your postcard and mail it back 
to you. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it. If a person contacts us verbally, and that 
contact relates to a substantive part of this AD, we will summarize the 
contact and place the summary in the docket. We will consider all 
comments received by the closing date and may amend the AD in light of 
those comments.
    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 may get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

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. Include 
``AD Docket No. 2003-NE-25-AD'' in your request.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, 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:

2003-16-10 Pratt & Whitney Canada: Amendment 39-13263. Docket No. 
2003-NE-25-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
29, 2003.

Affected ADs

    (b) None.

Applicability

    (c) This AD is applicable to Pratt & Whitney Canada (PWC) PW206A 
and PW206E turboshaft engines. These engines are installed on, but 
not limited to MD Helicopters Inc. Model MD-900 helicopters.

Unsafe Condition

    (d) This AD is prompted by reports of engine shutdowns and 
emergency landings due to severe vibration and drops in engine 
torque, and an increase in internal engine temperature, triggering 
in-flight engine fire warnings. We are issuing this AD to prevent 
turbine blade axial shift, leading to high levels of vibration, loss 
of engine torque, in-flight engine shutdown, and possible 
uncontained engine failure.

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.

Initial Sequence of Borescope Inspections

    (f) Perform an initial sequence of borescope inspections of 
compressor turbine blades and power turbine blades for blade axial 
shift within the turbine disks. Use paragraph 3. of Accomplishment 
Instructions of PWC Alert Service Bulletin (ASB) No. PW200-72-
A28242, Revision 1, dated October 2, 2002, for the borescope 
inspection. Do the inspections at the following times:
    (1) Within 25 flight hours accumulated or 30 days after the 
effective date of this AD, whichever occurs earlier.
    (2) After 30 flight hours, but before 50 flight hours 
accumulated since inspection of paragraph (f)(1) of this AD.
    (3) After 80 flight hours, but before 100 flight hours 
accumulated since inspection of paragraph (f)(1) of this AD.
    (4) After 180 flight hours, but before 200 flight hours 
accumulated since inspection of paragraph (f)(1) of this AD.

Repetitive Borescope Inspections

    (g) Thereafter, perform repetitive borescope inspections at 
intervals of not less than 280 nor more than 300 flight hours since-
last-inspection. Use paragraph 3. of Accomplishment Instructions of 
PWC ASB No. PW200-72-A28242, Revision 1, dated October 2, 2002, for 
the borescope inspections.

Disposition

    (h) If any blade shift is found, remove engine from service 
before further flight and perform rivet and rotor air seal 
replacements, as specified in paragraphs (j)(1) and (j)(2) of this 
AD, to return the engine to service.
    (i) If blade shift is suspected, confirm the blade shift with 
the appropriate engine manufacturer service representative before 
further flight. Remove engine from service if shift is confirmed, 
and perform rivet and rotor air seal replacements, as specified in 
paragraphs (j)(1) and (j)(2) of this AD, to return the engine to 
service.

Terminating Action

    (j) At the next engine shop visit for any reason, or at the next 
engine overhaul, whichever occurs first, but before December 31, 
2009, do the following:
    (1) Replace the compressor turbine blade retaining rivets, the 
No. 3 bearing rotor air seal, and the No. 4 bearing front rotor air 
seal. Use paragraph 3. Accomplishment Instructions of Service 
Bulletin (SB) No. PW200-72-28069, Revision 5, dated February 10, 
2003.
    (2) Replace the power turbine blade retaining rivets. Use 
paragraph 3. Accomplishment Instructions of SB No. PW200-72-28239, 
Revision 2, dated February 10, 2003.

Previous Credit

    (k) Previous credit is allowed for terminating action in 
paragraph (j)(1) and (j)(2) of this AD that was done in accordance 
with Accomplishment Instructions of SB No. PW200-72-28069, Revision 
4, dated December 27, 2000, and Accomplishment Instructions of SB 
No. PW200-72-28239, dated September 5, 2002, or Revision 1, dated 
December 5, 2002, before the effective date of this AD.
    (l) Completing the actions in paragraphs (j)(1) and (j)(2) of 
this AD terminates all inspection requirements of this AD.

Alternative Methods of Compliance (AMOCs)

    (m) You must request AMOCs as specified in 14 CFR part 39.19. 
All AMOCs must be approved by the Manager, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803-5299.

Material Incorporated by Reference

    (n) You must use the following Pratt & Whitney Canada Service 
Bulletins and Alert Service Bulletin to perform the inspections and 
replacement actions 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

[[Page 48546]]

part 51. You may get a copy from Pratt & Whitney Canada, 1000 Marie-
Victorin, Longueuil, Quebec, Canada J4G1A1. You may review copies at 
Federal Aviation Administration (FAA), New England Region, Office of 
the Regional Counsel, Attention: Rules Docket No. 2003-NE-25-AD, 12 
New England Executive Park, Burlington, MA 01803-5299; or at the 
Office of the Federal Register, 800 North Capitol Street, NW, suite 
700, Washington, DC. Table 1 follows:

                                      Table 1.--Incorporation by Reference
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          Service bulletin                  Page No.(s)          Revision                   Date
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PW200-72-A28242.....................  All....................            1  October 2, 2002.
Total Pages--7......................
PW200-72-28069......................  All....................            5  February 10, 2003.
Total Pages--17.....................
PW200-72-28239......................  All....................            2  February 10, 2003.
Total Pages--20.....................
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Related Information

    (o) Transport Canada issued airworthiness directive CF-2003-06, 
dated February 4, 2003, which pertains to the subject of this AD, in 
order to assure the airworthiness of these PWC PW206A and PW206E 
turboshaft engines in Canada.

    Issued in Burlington, Massachusetts, on August 4, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-20484 Filed 8-13-03; 8:45 am]
BILLING CODE 4910-13-P