[Federal Register Volume 69, Number 161 (Friday, August 20, 2004)]
[Rules and Regulations]
[Pages 51547-51549]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-18998]



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  Federal Register / Vol. 69, No. 161 / Friday, August 20, 2004 / Rules 
and Regulations  

[[Page 51547]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-25-AD; Amendment 39-13775; AD 2004-17-03]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada PW206A and 
PW206E Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Pratt & Whitney Canada (PWC) PW206A and PW206E turboshaft 
engines. That AD currently requires:
     Initial and repetitive borescope inspections of compressor 
turbine and power turbine blades for blade axial shift.
     Replacement of blade retaining rivets and certain rotor 
air seals as terminating action for the repetitive borescope 
inspections.
    This ad requires the same actions as AD 2003-NE-25-AD but the 
extent of engine disassembly that triggers the required part 
replacements needs clarification. This AD results from reports of 
engine shutdowns and emergency landings due to severe vibration, 
resulting in exhaust gases escaping from the engine-to-exhaust nozzle 
interface, thereby 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 loss of the airframe exhaust duct.

DATES: This AD becomes effective September 24, 2004. The Director of 
the Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of August 29, 2003. The 
incorporation by reference of certain other publications, as listed in 
the regulations, was approved previously by the Director of the Federal 
Register as of August 29, 2003 (68 FR 48544; August 14, 2003).

ADDRESSES: You can get the service information identified in this AD 
from Pratt & Whitney Canada, 1000 Marie-Victorin, Longueuil, Quebec, 
Canada J4G 1A1.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA. 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 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.

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: The FAA proposed to amend 14 CFR Part 39 
with a proposed AD. The proposed AD applies to PWC PW206A and PW206E 
turboshaft engines. We published the proposed AD in the Federal 
Register on February 20, 2004 (69 FR 7878). That action proposed to 
require the same actions as AD 2003-16-10, Amendment 39-13263, but 
would change the description of the extent of engine disassembly that 
triggers the required part replacements. Those changes are needed to 
clarify when the parts must be replaced.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Limit the Effectivity of This AD

    One commenter states that the referenced Alert Service Bulletin and 
Service Bulletins only address those engines with between 25 hours 
Total-Time-Since-New (TTSN) or Total-Time-Since-Repair (TTSR) and 600 
hours TTSN or TTSR. Therefore, this AD should address the same group of 
engines.
    We do not agree. The amount of data available is insufficient to 
limit the effectivity to only those engines with between 25 hours TTSN 
or TTSR and 600 hours TTSN or TTSR. We have not changed the AD based on 
this comment.

Request for Earlier Versions of Service Bulletins To Apply

    One commenter states that earlier versions of the Service Bulletins 
should be acceptable for meeting the requirements of this AD.
    We agree. There are no substantial changes between the earliest 
versions of the Service Bulletins and those versions referenced in the 
proposed AD. We have added those service bulletin references to 
paragraph (k) of the AD, which is the Previous Credit paragraph.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the change described previously. 
We have determined that this change will neither increase the economic 
burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 130 PWC PW206A and PW206E turboshaft engines of the 
affected design in the worldwide fleet. We estimate that 15 engines 
installed on airplanes of U.S. registry are affected by this AD. We 
also estimate that it will take about 0.5 work hours per engine to 
perform the required actions, and that the average labor rate is $65 
per work hour. Required parts will cost about $9,077 per engine. Based 
on these figures, we estimate the total cost of this AD to U.S. 
operators to be $136,656. The manufacturer has stated that it may 
provide replacement parts at no cost to operators.

[[Page 51548]]

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 this AD:
    (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.
    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 FAA amends 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 
removing Amendment 39-13263 (68 FR 48544, August 14, 2003) and by 
adding a new airworthiness directive (AD), Amendment 39-13775, to read 
as follows:

2004-17-03 Pratt & Whitney Canada: Amendment 39-13775. Docket No. 
2003-NE-25-AD. Supersedes AD 2003-16-10, Amendment 39-13263.

Effective Date

    (a) This AD becomes effective September 24, 2004.

Affected ADs

    (b) This AD supersedes AD 2003-16-10, Amendment 39-13263.

Applicability

    (c) This AD applies 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, resulting in exhaust 
gases escaping from the engine-to-exhaust nozzle interface, thereby 
triggering in-flight engine fire warnings. The actions specified in 
this AD are intended to prevent turbine blade axial shift, which 
could cause high levels of vibration, loss of engine torque, in-
flight engine shutdown, and loss of the airframe exhaust duct.

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 and determination of blade shift. 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 and determination of blade shift.

Disposition

    (h) If you find any blade shift, remove engine from service 
before further flight and perform rivet and rotor air seal 
replacements, as specified in paragraphs (i)(1) through (i)(3) of 
this AD, to return the engine to service.

Terminating Action

    (i) At the next engine shop visit when access is available to 
subassemblies, such as modules, accessories, and components, or at 
the next engine overhaul, whichever occurs first, but before 
accumulating 1,800 flight hours from the effective date of this AD 
or before December 31, 2009, whichever occurs first, do the 
following:
    (1) Replace the compressor turbine blade retaining rivets with 
new P/N retaining rivets, and the No. 4 bearing rear rotor air seal 
with the new P/N No. 4 bearing rear rotor air seal. Use paragraph 
3., Part A, of Accomplishment Instructions of SB No. PW200-72-28069, 
Revision 5, dated February 10, 2003.
    (2) Replace the No. 3 bearing rotating air seal with the new P/N 
air seal, and the No. 4 bearing front rotor air seal with the new P/
N No. 4 bearing front rotor air seal. Use paragraph 3., Part B, of 
Accomplishment Instructions of SB No. PW200-72-28069, Revision 5, 
dated February 10, 2003.
    (3) Replace the power turbine blade retaining rivets with new P/
N power turbine blade retaining rivets. Use paragraph 3. of 
Accomplishment Instructions of SB No. PW200-72-28239, Revision 2, 
dated February 10, 2003.
    (j) Completing the actions in paragraphs (i)(1) through (i)(3) 
of this AD terminates all inspection requirements of this AD.

Previous Credit

    (k) Previous credit is allowed:
    (1) For performing the initial sequence for borescope 
inspections in paragraph (f) of this AD, that were done using AD 
2003-16-10.
    (2) For terminating action in paragraphs (i)(1) through (i)(3) 
of this AD that was done using the Accomplishment Instructions of 
one of the following, before the effective date of this AD:
    (i) SB No. PW200-72-28069, dated June 10, 1997
    (ii) SB No. PW200-72-28069, Revision 1, dated September 8, 1997
    (iii) SB No. PW200-72-28069, Revision 2, dated December 18, 1997
    (iv) SB No. PW200-72-28069, Revision 3, dated November 30, 1998
    (v) SB No. PW200-72-28069, Revision 4, dated December 27, 2000
    (vi) SB No. PW200-72-28069, Revision 5, dated February 10, 2003
    (vii) SB No. PW200-72-28239, dated September 5, 2002
    (viii) SB No. PW200-72-28239, Revision 1, dated December 5, 2002
    (ix) SB No. PW200-72-28239, Revision 2, dated February 10, 2003

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 Bulletins 
and Alert Service Bulletin listed in Table 1 of this AD to perform 
the inspections and replacement actions required by this AD. The 
incorporation by reference of this publication was approved 
previously by the Director of the Federal Register as of August 29, 
2003 (68 FR 48544; August 14, 2003), 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 
can review copies at the FAA, New England Region, Office of the 
Regional Counsel, 12 New England Executive

[[Page 51549]]

Park, Burlington, MA; 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. Table 1 follows:

                                      Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
           Service bulletin                  Page number(s)       Revision                   Date
----------------------------------------------------------------------------------------------------------------
PW200-72-A28242, Total Pages--7......  All.....................          1  October 2, 2002.
PW200-72-28069, Total Pages--17......  All.....................          5  February 10, 2003.
PW200-72-28239, Total Pages--20......  All.....................          2  February 10, 2003.
----------------------------------------------------------------------------------------------------------------

Related Information

    (n) 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 12, 2004.
Ann Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-18998 Filed 8-19-04; 8:45 am]
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