Airworthiness Directives; Pratt & Whitney Canada PW206A, PW206B, PW206B2, PW206C, PW206E, PW207C, PW207D, and PW207E Turboshaft Engines, 7794-7796 [E9-3046]

Download as PDF 7794 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations Applicability (c) This AD applies to all Airbus Model A300–600 airplanes, certificated in any category; all certified models, all serial numbers. Subject (d) Air Transport Association (ATA) of America Code 28: Fuel. Reason (e) The mandatory continuing airworthiness information (MCAI) states: One operator experienced failures of four Fuel Level Sensor-Amplifier (FLSA) and Multi Tank Indicators (MTI) units. FLSA and MTI failures have been identified as having been caused by incorrect connector sleeves material fitted to the MTI units. Degradation of the electrical insulation sleeves of the Low-level indication lamps on the MTI on the flight deck can cause a short circuit that might result in high voltage being conveyed to the high and low level sensors in the outer tanks. This might cause the level sensor to heat above acceptable limits. For the reasons stated above, this Airworthiness Directive (AD) requires the accomplishment of wiring modifications to protect the FLSA and the Flight Warning Computers from 115V AC and 28V DC short circuits within the MTI. This action is necessary to prevent overheating of the fuel level sensors, which could result in a fuel tank explosion and consequent loss of the airplane. Actions and Compliance (f) Unless already done, within 3 months after the effective date of this AD: Modify the wiring in the right-hand electronics rack in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–28A6096, Revision 02, dated July 4, 2008. Previous accomplishment of the modification before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A300–28A6096, dated October 19, 2007; or Revision 01, dated April 16, 2008; meets the requirements in this paragraph. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. DEPARTMENT OF TRANSPORTATION Related Information AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008– 0055, dated March 5, 2008, and Airbus Mandatory Service Bulletin A300–28A6096, Revision 02, dated July 4, 2008, for related information. Material Incorporated by Reference (i) You must use Airbus Mandatory Service Bulletin A300–28A6096, Revision 02, dated July 4, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// www.airbus.com. (3) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information 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. Issued in Renton, Washington, on December 28, 2008. Linda Navarro, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3277 Filed 2–19–09; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00018 Fmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0219; Directorate Identifier 2007–NE–46–AD; Amendment 39– 15806; AD 2009–03–05] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada PW206A, PW206B, PW206B2, PW206C, PW206E, PW207C, PW207D, and PW207E Turboshaft Engines SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: PW206 and PW207 compressor turbine (CT) disc bore areas may experience impact damage resulting from bending or fracture of the CT disc retaining nut. Damage of the CT disc bore area can reduce LCF capabilities of the CT disc, resulting in disc fracture. We are issuing this AD to prevent damage to the CT disc bore area, which could result in possible uncontained failure of the engine and damage to the helicopter. DATES: This AD becomes effective March 27, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 27, 2009. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park; Burlington, MA 01803; e-mail: ian.dargin@faa.gov; telephone (781) 238–7178; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That Sfmt 4700 E:\FR\FM\20FER1.SGM 20FER1 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations 7795 Authority for This Rulemaking List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Under high centrifugal loads, the CT disk retaining nut castellations might bend outward, then contact and mark the CT disk internal bore. Worldwide, a total of five events of CT nut damage and associated damage to the CT disk bore have been reported. A total of 195 out of 402 engines in the U.S. fleet have been inspected with two cases of CT nut damage and no findings of disk damage, to date. You may obtain further information by examining the MCAI in the AD docket. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Comments Regulatory Findings We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Although the MCAI allows use of future revisions of PWC ASB PW200– 72–A28280, we require the use of Revision 4 of that ASB. Although the MCAI has a March 21, 2008 compliance date, we have changed the final rule from a December 21, 2008 compliance date to within 30 days after the effective date of the AD. This is based on a review of the risk assessment and the fleet inspection results to date. We 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 this AD: 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Costs of Compliance Examining the AD Docket We estimate that this AD will affect 402 engines of U.S. registry. We also estimate that it will take 8 work-hours per product to comply with this AD. The average labor rate is $80 per workhour. Required parts will cost about $500 per product. We expect that 1 disk on the remaining 207 engines will be replaced, at an estimated cost of $20,000. Based on these figures, we estimate the cost of the AD to U.S. operators to be $478,280. Our cost estimate is exclusive of possible warranty coverage. You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. NPRM was published in the Federal Register on June 25, 2008, (73 FR 35982). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: PW206 and PW207 compressor turbine (CT) disc bore areas may experience impact damage resulting from bending or fracture of the CT disc retaining nut. Damage of the CT disc bore area can reduce LCF capabilities of the CT disc, resulting in disc fracture. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–03–05 Pratt Whitney Canada: Amendment 39–15806. Docket No. FAA–2007–0219; Directorate Identifier 2007–NE–46–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 27, 2009. Affected ADs (b) None. Applicability (c) This airworthiness directive (AD) applies to Pratt & Whitney Canada (PWC) PW206A, PW206B, PW206B2, PW206C, PW206E, PW207C, PW207D, and PW207E turboshaft engines. (d) These engines are installed on, but not limited to, MD Explorer, Agusta S.p.A. A109, A109E, A109S, Bell Helicopter Textron Canada Limited 427, Bell 429, and Eurocopter Deutschland GmbH EC135 P1, and EC135 P2 helicopters. (e) For engines that have been converted from one model to another, see Effectivity paragraph 1.A. of PWC Alert Service Bulletin (ASB) PW200–72–A28280, Revision 4, dated August 28, 2007. Reason (f) Transport Canada AD CF–2007–24R1, dated December 21, 2007, states: PW206 and PW207 compressor turbine (CT) disc bore areas may experience impact damage resulting from bending or fracture of the CT disc retaining nut. Damage of the CT disc bore area can reduce LCF capabilities of the CT disc, resulting in disc fracture. We are issuing this AD to prevent damage to the CT disc bore area, which could result in possible uncontained failure of the disc and damage to the helicopter. Actions and Compliance (g) Unless already done, do the following actions: (1) For engines that have never had a shop visit and have accumulated 4,000 CT cycles or more since new; or for engines that accumulated 2,700 CT cycles or more since last shop visit, last CT disc inspection, or E:\FR\FM\20FER1.SGM 20FER1 7796 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Rules and Regulations incorporation of PWC SB PW200–72–28287; within 1,150 hours of engine operating time since April 28, 2006 (original issue date of Alert Service Bulletin (ASB) PW200–72– A28280), but not later than 30 days after the effective date of this AD, whichever occurs first, accomplish the following in accordance with PWC ASB PW200–72–A28280, Revision 4, dated August 28, 2007: (i) Inspect the CT disc bore area for damage and if any damage is noticed, replace the CT disc before further flight. (ii) Replace the existing CT disc retaining nut and associated hardware. (2) For engines that have never had a shop visit and have accumulated less than 4,000 CT cycles since new, before the engine reaches 4,000 CT cycles or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with PWC ASB PW200–72– A28280, Revision 4, dated August 28, 2007: (i) Inspect the CT disc bore area for damage and if any damage is noticed, replace the CT disc before further flight. (ii) Replace the existing CT disc retaining nut and associated hardware. (3) For engines that have accumulated fewer than 2,700 CT cycles since last shop visit, last CT disc inspection, or incorporation of PWC SB PW200–72–28287; before the engine reaches 2,700 CT cycles or within 30 days after the effective date of this AD, whichever occurs later, accomplish the following in accordance with PWC ASB PW200–72–A28280, Revision 4, dated August 28, 2007: (i) Inspect the CT disc bore area for damage and if any damage is noticed, replace the CT disc before further flight. (ii) Replace the existing CT disc retaining nut and associated hardware. Previous Credit (h) Inspection of the CT disc bore and replacement of the CT disc retaining nut using PWC ASB PW200–72–A28280, dated April 28, 2006, or Revision 1, dated May 11, 2006, or Revision 2, dated September 29, 2006, or Revision 3, dated December 11, 2006, before the effective date of this AD, meets the requirements of this AD. Other FAA AD Provisions (i) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (j) Refer to Transport Canada Airworthiness Directive 2007–24R1, dated December 21, 2007, for related information. (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park; Burlington, MA 01803; e-mail: ian.dargin@faa.gov; telephone (781) 238–7178; fax (781) 238–7199. Material Incorporated by Reference (l) You must use Pratt & Whitney Canada Alert Service Bulletin (ASB) PW200–72– A28280, Revision 4, dated August 28, 2007 to do the actions required by this AD, unless the AD specifies otherwise. VerDate Nov<24>2008 16:40 Feb 19, 2009 Jkt 217001 (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Pratt & Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1, telephone: (800) 268–8000. (3) You may review copies at the FAA, New England Region, 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/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on January 29, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–3046 Filed 2–19–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0681; Directorate Identifier 2008–NE–13–AD; Amendment 39– 15805; AD 2009–03–04] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Models Arriel 1E2, 1S, and 1S1 Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Turbomeca S.A. has informed EASA of a case of a ‘‘red disk’’ plug that has been actually installed on an engine which has been subsequently released for service operation. This engine experienced an inservice high pressure leak event (at the fuel pump outlet) due to cracking of this ‘‘red disk’’ plug. This leak could lead to in-flight flame-out and/or possibly a fire. We are issuing this AD to prevent fuel leaks, which could result in a fire and damage to the helicopter. DATES: This AD becomes effective March 27, 2009. The Director of the PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 27, 2009. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on June 25, 2008 (73 FR 35981). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: A plug adapted for engine bench testing (called ‘‘red disk’’ plug) and not approved for service operation, could inadvertently be installed on the engine Fuel Control Unit 3way union, instead of the sealed plug approved for service operation. Turbomeca S.A. has informed EASA of a case of a ‘‘red disk’’ plug that has been actually installed on an engine which has been subsequently released for service operation. This engine experienced an inservice high pressure leak event (at the fuel pump outlet) due to cracking of this ‘‘red disk’’ plug. This leak could lead to in-flight flame-out and/or possibly a fire. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance Based on the service information, we estimate that this AD will affect about 179 products installed on helicopters of U.S. registry. We also estimate that it will take about 0.5 work-hour per product to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $14 per product. Based on these figures, we E:\FR\FM\20FER1.SGM 20FER1

Agencies

[Federal Register Volume 74, Number 33 (Friday, February 20, 2009)]
[Rules and Regulations]
[Pages 7794-7796]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3046]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0219; Directorate Identifier 2007-NE-46-AD; 
Amendment 39-15806; AD 2009-03-05]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada PW206A, PW206B, 
PW206B2, PW206C, PW206E, PW207C, PW207D, and PW207E Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    PW206 and PW207 compressor turbine (CT) disc bore areas may 
experience impact damage resulting from bending or fracture of the 
CT disc retaining nut. Damage of the CT disc bore area can reduce 
LCF capabilities of the CT disc, resulting in disc fracture.

We are issuing this AD to prevent damage to the CT disc bore area, 
which could result in possible uncontained failure of the engine and 
damage to the helicopter.

DATES: This AD becomes effective March 27, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of March 27, 2009.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park; Burlington, MA 01803; e-mail: 
ian.dargin@faa.gov; telephone (781) 238-7178; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That

[[Page 7795]]

NPRM was published in the Federal Register on June 25, 2008, (73 FR 
35982). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    PW206 and PW207 compressor turbine (CT) disc bore areas may 
experience impact damage resulting from bending or fracture of the 
CT disc retaining nut. Damage of the CT disc bore area can reduce 
LCF capabilities of the CT disc, resulting in disc fracture.

Under high centrifugal loads, the CT disk retaining nut castellations 
might bend outward, then contact and mark the CT disk internal bore. 
Worldwide, a total of five events of CT nut damage and associated 
damage to the CT disk bore have been reported. A total of 195 out of 
402 engines in the U.S. fleet have been inspected with two cases of CT 
nut damage and no findings of disk damage, to date. You may obtain 
further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI

    Although the MCAI allows use of future revisions of PWC ASB PW200-
72-A28280, we require the use of Revision 4 of that ASB.
    Although the MCAI has a March 21, 2008 compliance date, we have 
changed the final rule from a December 21, 2008 compliance date to 
within 30 days after the effective date of the AD. This is based on a 
review of the risk assessment and the fleet inspection results to date.

Costs of Compliance

    We estimate that this AD will affect 402 engines of U.S. registry. 
We also estimate that it will take 8 work-hours per product to comply 
with this AD. The average labor rate is $80 per work-hour. Required 
parts will cost about $500 per product. We expect that 1 disk on the 
remaining 207 engines will be replaced, at an estimated cost of 
$20,000. Based on these figures, we estimate the cost of the AD to U.S. 
operators to be $478,280. Our cost estimate is exclusive of possible 
warranty coverage.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We 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 this AD:
    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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

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 FAA amends Sec.  39.13 by adding the following new AD:

2009-03-05 Pratt Whitney Canada: Amendment 39-15806. Docket No. FAA-
2007-0219; Directorate Identifier 2007-NE-46-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
27, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This airworthiness directive (AD) applies to Pratt & Whitney 
Canada (PWC) PW206A, PW206B, PW206B2, PW206C, PW206E, PW207C, 
PW207D, and PW207E turboshaft engines.
    (d) These engines are installed on, but not limited to, MD 
Explorer, Agusta S.p.A. A109, A109E, A109S, Bell Helicopter Textron 
Canada Limited 427, Bell 429, and Eurocopter Deutschland GmbH EC135 
P1, and EC135 P2 helicopters.
    (e) For engines that have been converted from one model to 
another, see Effectivity paragraph 1.A. of PWC Alert Service 
Bulletin (ASB) PW200-72-A28280, Revision 4, dated August 28, 2007.

Reason

    (f) Transport Canada AD CF-2007-24R1, dated December 21, 2007, 
states:

    PW206 and PW207 compressor turbine (CT) disc bore areas may 
experience impact damage resulting from bending or fracture of the 
CT disc retaining nut. Damage of the CT disc bore area can reduce 
LCF capabilities of the CT disc, resulting in disc fracture.

    We are issuing this AD to prevent damage to the CT disc bore 
area, which could result in possible uncontained failure of the disc 
and damage to the helicopter.

Actions and Compliance

    (g) Unless already done, do the following actions:
    (1) For engines that have never had a shop visit and have 
accumulated 4,000 CT cycles or more since new; or for engines that 
accumulated 2,700 CT cycles or more since last shop visit, last CT 
disc inspection, or

[[Page 7796]]

incorporation of PWC SB PW200-72-28287; within 1,150 hours of engine 
operating time since April 28, 2006 (original issue date of Alert 
Service Bulletin (ASB) PW200-72-A28280), but not later than 30 days 
after the effective date of this AD, whichever occurs first, 
accomplish the following in accordance with PWC ASB PW200-72-A28280, 
Revision 4, dated August 28, 2007:
    (i) Inspect the CT disc bore area for damage and if any damage 
is noticed, replace the CT disc before further flight.
    (ii) Replace the existing CT disc retaining nut and associated 
hardware.
    (2) For engines that have never had a shop visit and have 
accumulated less than 4,000 CT cycles since new, before the engine 
reaches 4,000 CT cycles or within 30 days after the effective date 
of this AD, whichever occurs later, accomplish the following in 
accordance with PWC ASB PW200-72-A28280, Revision 4, dated August 
28, 2007:
    (i) Inspect the CT disc bore area for damage and if any damage 
is noticed, replace the CT disc before further flight.
    (ii) Replace the existing CT disc retaining nut and associated 
hardware.
    (3) For engines that have accumulated fewer than 2,700 CT cycles 
since last shop visit, last CT disc inspection, or incorporation of 
PWC SB PW200-72-28287; before the engine reaches 2,700 CT cycles or 
within 30 days after the effective date of this AD, whichever occurs 
later, accomplish the following in accordance with PWC ASB PW200-72-
A28280, Revision 4, dated August 28, 2007:
    (i) Inspect the CT disc bore area for damage and if any damage 
is noticed, replace the CT disc before further flight.
    (ii) Replace the existing CT disc retaining nut and associated 
hardware.

Previous Credit

    (h) Inspection of the CT disc bore and replacement of the CT 
disc retaining nut using PWC ASB PW200-72-A28280, dated April 28, 
2006, or Revision 1, dated May 11, 2006, or Revision 2, dated 
September 29, 2006, or Revision 3, dated December 11, 2006, before 
the effective date of this AD, meets the requirements of this AD.

Other FAA AD Provisions

    (i) Alternative Methods of Compliance (AMOCs): The Manager, 
Engine Certification Office, FAA, may approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (j) Refer to Transport Canada Airworthiness Directive 2007-24R1, 
dated December 21, 2007, for related information.
    (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park; Burlington, MA 01803; e-mail: ian.dargin@faa.gov; 
telephone (781) 238-7178; fax (781) 238-7199.

Material Incorporated by Reference

    (l) You must use Pratt & Whitney Canada Alert Service Bulletin 
(ASB) PW200-72-A28280, Revision 4, dated August 28, 2007 to do the 
actions required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact Pratt 
& Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, 
Canada J4G 1A1, telephone: (800) 268-8000.
    (3) You may review copies at the FAA, New England Region, 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/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on January 29, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3046 Filed 2-19-09; 8:45 am]
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