[Federal Register: August 14, 2003 (Volume 68, Number 157)]
[Rules and Regulations]
[Page 48544-48546]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14au03-4]
[[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: 9-ane-adcomment@faa.gov. 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