[Federal Register: August 20, 2004 (Volume 69, Number 161)]
[Rules and Regulations]
[Page 51547-51549]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20au04-1]
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[[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.
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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
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Service bulletin Page number(s) Revision Date
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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.
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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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