Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6 Airplanes, 32497-32499 [E8-12816]

Download as PDF Federal Register / Vol. 73, No. 111 / Monday, June 9, 2008 / Proposed Rules responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 removing Amendment 39–15520 (73 FR 26318; May 9, 2008), and adding the following new AD: EADS SOCATA: Docket No. FAA–2008– 0627; Directorate Identifier 2008–CE– 033–AD. Comments Due Date (a) We must receive comments by July 9, 2008. Affected ADs (b) This AD supersedes AD 2008–10–13, Amendment 39–15520. Applicability (c) This AD applies to Models TBM 700 airplanes, serial numbers 434 through 455, certificated in any category. jlentini on PROD1PC65 with PROPOSALS Subject (d) Air Transport Association of America (ATA) Code 24: Electric Power. Reason (e) The mandatory continuing airworthiness information (MCAI) states: A rupture of the alternator and vapour cycle cooling system pulley drive assembly has reportedly been found. Such a failure could lead to the loss of the alternator and vapour cycle cooling systems and could also cause mechanical damage inside the powerplant compartment. VerDate Aug<31>2005 18:31 Jun 06, 2008 Jkt 214001 To address this condition, AD 2008–0063– E had been published to require a check of the pulley drive assembly for leakage and, as an interim action, removal of the compressor drive belt from the assembly, and adoption of a new operational procedure to keep the air-conditioning system deactivated. This AD retains the requirements of AD 2008–0063–E which is superseded, introduces a mandatory terminating action which consists in replacing the original pulley drive assembly by a new one of an improved design—corresponding to the EADS SOCATA modification MOD 70–0231– 21—that permits reinstallation of the compressor drive belt. Actions and Compliance (f) Unless already done, do the following before further flight after May 9, 2008 (the compliance date retained from AD 2008–10– 13): (1) Position to ‘‘OFF’’ the air-conditioning ‘‘AIR COND’’ switch. (2) Inspect for oil leakage in the pulley drive assembly by following EADS SOCATA Service Bulletin (SB) No. 70–156 Amendment 1, dated March 2008. (i) If any leak is found, before further flight after the inspection, replace the pulley drive assembly part number (P/N) T700G215504900000 with P/N T700G215505710000 following EADS SOCATA Service Bulletin (SB) No. 70–156 Amendment 1, dated March 2008. (ii) If no leak is found, before further flight, remove the compressor drive belt from the pulley drive assembly following either EADS SOCATA Service Bulletin (SB) No. 70–156, original issue; or EADS SOCATA Service Bulletin (SB) No. 70–156, Amendment 1; both dated March 2008. (3) The air-conditioning ‘‘AIR COND’’ switch must be in the ‘‘OFF’’ position and the compressor drive belt must remain removed until the pulley drive assembly part number (P/N) T700G215504900000 is replaced with P/N T700G215505710000 following EADS SOCATA Service Bulletin (SB) No. 70–156 Amendment 1, dated March 2008. This replacement must be done before further flight if any leak is found and may be done at any time as terminating action to this AD. (g) Within the next 12 months after the effective date of this AD, unless already done, replace the pulley drive assembly P/N T700G215504900000 with P/N T700G215505710000 and reinstall the compressor drive belt, following EADS SOCATA Service Bulletin (SB) No. 70–156 Amendment 1, dated March 2008. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 32497 ATTN: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; fax: (816) 329– 4090. 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. (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 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Special Flight Permit (i) Under 14 CFR 39.23, we are limiting the special flight permits for the check of equipment of this AD under the following condition: The air-conditioning ‘‘AIR-COND’’ switch is set to the ‘‘OFF’’ position. Related Information (j) Refer to MCAI European Aviation Safety Agency (EASA) Emergency AD No.: 2008– 0067–E, dated April 3, 2008, and EADS SOCATA Service Bulletin (SB) No. 70–156 Amendment 1, dated March 2008, for related information. Issued in Kansas City, Missouri, on June 2, 2008. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–12818 Filed 6–6–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0626; Directorate Identifier 2008–CE–035–AD] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Model PC–6 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing E:\FR\FM\09JNP1.SGM 09JNP1 32498 Federal Register / Vol. 73, No. 111 / Monday, June 9, 2008 / Proposed Rules airworthiness information (MCAI) originated 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: This Airworthiness Directive (AD) is prompted due to the discovery of loose selflocking stop nuts Part Number (P/N) 938.07.65.105 in the tail landing gear fastener assemblies of some PC–6 aircraft. It is believed that this occurrence could also exist in other fastener assemblies using nuts P/N 938.07.65.105 at various identified locations in the aircraft. If left uncorrected, the identified assemblies may become loose and not function as designed and could lead to hazardous situations. jlentini on PROD1PC65 with PROPOSALS The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by July 9, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about VerDate Aug<31>2005 18:31 Jun 06, 2008 Jkt 214001 this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–0626; Directorate Identifier 2008–CE–035–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No.: 2008–0083, dated May 5, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: This Airworthiness Directive (AD) is prompted due to the discovery of loose selflocking stop nuts Part Number (P/N) 938.07.65.105 in the tail landing gear fastener assemblies of some PC–6 aircraft. It is believed that this occurrence could also exist in other fastener assemblies using nuts P/N 938.07.65.105 at various identified locations in the aircraft. If left uncorrected, the identified assemblies may become loose and not function as designed and could lead to hazardous situations. In order to prevent those conditions, the present AD requires you replace self-locking stop nuts P/N 938.07.65.105 from the Tail Landing Gear Assembly, the Parachute Cable Assembly, the Water Tank Assembly, the Cable Tensioner Assembly, the Fuel Filter Assembly, the Hydraulic Pump Assembly and the Engine Mounts Assembly in accordance with Pilatus PC–6 Service Bulletin No. 53–002 Revision 2. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Pilatus Aircraft Ltd. has issued Pilatus PC–6 Service Bulletin Number 53–002, Revision No. 2, dated September 24, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance We estimate that this proposed AD will affect 50 products of U.S. registry. We also estimate that it would take about 7 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $310 per product. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $43,500, or $870 per product. 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 E:\FR\FM\09JNP1.SGM 09JNP1 Federal Register / Vol. 73, No. 111 / Monday, June 9, 2008 / Proposed Rules that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: Pilatus Aircraft Ltd.: Docket No. FAA–2008– 0626; Directorate Identifier 2008–CE– 035–AD. Comments Due Date (a) We must receive comments by July 9, 2008. jlentini on PROD1PC65 with PROPOSALS Affected ADs (b) None. Applicability (c) This AD applies to PC–6, PC–6–H1, PC– 6–H2, PC–6/350, PC–6/350–H1, PC–6/350– H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/ B–H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/B2– H4, PC–6/C–H2, and PC–6/C1–H2 airplanes, manufacturer serial numbers (MSN) MSN 101 through MSN 949 and MSN 2001 VerDate Aug<31>2005 18:31 Jun 06, 2008 Jkt 214001 through MSN 2092, certificated in any category. Note 1: These airplanes may also be identified as Fairchild Republic Company PC–6 airplanes, Fairchild Heli Porter PC–6 airplanes, or Fairchild-Hiller Corporation PC–6 airplanes. Subject (d) Air Transport Association of America (ATA) Code 53: Fuselage. Reason (e) The mandatory continuing airworthiness information (MCAI) states: This Airworthiness Directive (AD) is prompted due to the discovery of loose selflocking stop nuts Part Number (P/N) 938.07.65.105 in the tail landing gear fastener assemblies of some PC–6 aircraft. It is believed that this occurrence could also exist in other fastener assemblies using nuts P/N 938.07.65.105 at various identified locations in the aircraft. If left uncorrected, the identified assemblies may become loose and not function as designed and could lead to hazardous situations. In order to prevent those conditions, the present AD requires you replace self-locking stop nuts P/N 938.07.65.105 from the Tail Landing Gear Assembly, the Parachute Cable Assembly, the Water Tank Assembly, the Cable Tensioner Assembly, the Fuel Filter Assembly, the Hydraulic Pump Assembly and the Engine Mounts Assembly in accordance with Pilatus PC–6 Service Bulletin No. 53–002 Revision 2. Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 12 months after the effective date of this AD, inspect and modify the fastener assemblies as instructed in paragraph 3 of Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin Number 53–002, Revision No. 2, dated September 24, 2007. (2) After the effective date of this AD, no person shall install on any PC–6 series aircraft, water tank assemblies and hydraulic pump assemblies, unless they have been previously modified following paragraph 4 of Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin Number 53–002, Revision No. 2, dated September 24, 2007. FAA AD Differences Note 2: 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, Standards Office, 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: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090. Before using any approved AMOC on any airplane to which the AMOC applies, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 32499 notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency EASA AD No.: 2008–0083, dated May 5, 2008; and Pilatus Aircraft Ltd. Pilatus PC–6 Service Bulletin Number 53– 002, Revision No. 2, dated September 24, 2007, for related information. Issued in Kansas City, Missouri, on June 3, 2008. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–12816 Filed 6–6–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 [REG–124590–07] RIN 1545–BG11 Guidance Regarding Foreign Base Company Sales Income; Hearing Internal Revenue Service (IRS), Treasury. ACTION: Notice of public hearing on proposed rulemaking. AGENCY: SUMMARY: This document provides notice of public hearing on proposed regulations that provide guidance relating to foreign base company sales income, as defined in section 954(d), in cases in which personal property sold by a controlled foreign corporation (CFC) is manufactured, produced, or constructed pursuant to a contract manufacturing arrangement or by one or more branches of the CFC. DATES: The public hearing is being held on Tuesday, July 29, 2008, at 10 a.m. The IRS must receive outlines of the topics to be discussed at the public hearing by Tuesday, July 8, 2008. E:\FR\FM\09JNP1.SGM 09JNP1

Agencies

[Federal Register Volume 73, Number 111 (Monday, June 9, 2008)]
[Proposed Rules]
[Pages 32497-32499]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-12816]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0626; Directorate Identifier 2008-CE-035-AD]
RIN 2120-AA64


Airworthiness Directives; Pilatus Aircraft Ltd. Model PC-6 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing

[[Page 32498]]

airworthiness information (MCAI) originated 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:

    This Airworthiness Directive (AD) is prompted due to the 
discovery of loose self-locking stop nuts Part Number (P/N) 
938.07.65.105 in the tail landing gear fastener assemblies of some 
PC-6 aircraft.
    It is believed that this occurrence could also exist in other 
fastener assemblies using nuts P/N 938.07.65.105 at various 
identified locations in the aircraft.
    If left uncorrected, the identified assemblies may become loose 
and not function as designed and could lead to hazardous situations.

    The proposed AD would require actions that are intended to address 
the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by July 9, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0626; 
Directorate Identifier 2008-CE-035-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No.: 2008-0083, dated May 5, 2008 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    This Airworthiness Directive (AD) is prompted due to the 
discovery of loose self-locking stop nuts Part Number (P/N) 
938.07.65.105 in the tail landing gear fastener assemblies of some 
PC-6 aircraft.
    It is believed that this occurrence could also exist in other 
fastener assemblies using nuts P/N 938.07.65.105 at various 
identified locations in the aircraft.
    If left uncorrected, the identified assemblies may become loose 
and not function as designed and could lead to hazardous situations.
    In order to prevent those conditions, the present AD requires 
you replace self-locking stop nuts P/N 938.07.65.105 from the Tail 
Landing Gear Assembly, the Parachute Cable Assembly, the Water Tank 
Assembly, the Cable Tensioner Assembly, the Fuel Filter Assembly, 
the Hydraulic Pump Assembly and the Engine Mounts Assembly in 
accordance with Pilatus PC-6 Service Bulletin No. 53-002 Revision 2.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Pilatus Aircraft Ltd. has issued Pilatus PC-6 Service Bulletin 
Number 53-002, Revision No. 2, dated September 24, 2007. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all information and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 50 products of U.S. 
registry. We also estimate that it would take about 7 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $80 per work-hour. Required parts would cost 
about $310 per product.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $43,500, or $870 per product.

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

[[Page 32499]]

that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

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

Pilatus Aircraft Ltd.: Docket No. FAA-2008-0626; Directorate 
Identifier 2008-CE-035-AD.

Comments Due Date

    (a) We must receive comments by July 9, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/
350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/
B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes, 
manufacturer serial numbers (MSN) MSN 101 through MSN 949 and MSN 
2001 through MSN 2092, certificated in any category.

    Note 1: These airplanes may also be identified as Fairchild 
Republic Company PC-6 airplanes, Fairchild Heli Porter PC-6 
airplanes, or Fairchild-Hiller Corporation PC-6 airplanes.

Subject

    (d) Air Transport Association of America (ATA) Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    This Airworthiness Directive (AD) is prompted due to the 
discovery of loose self-locking stop nuts Part Number (P/N) 
938.07.65.105 in the tail landing gear fastener assemblies of some 
PC-6 aircraft.
    It is believed that this occurrence could also exist in other 
fastener assemblies using nuts P/N 938.07.65.105 at various 
identified locations in the aircraft.
    If left uncorrected, the identified assemblies may become loose 
and not function as designed and could lead to hazardous situations.
    In order to prevent those conditions, the present AD requires 
you replace self-locking stop nuts P/N 938.07.65.105 from the Tail 
Landing Gear Assembly, the Parachute Cable Assembly, the Water Tank 
Assembly, the Cable Tensioner Assembly, the Fuel Filter Assembly, 
the Hydraulic Pump Assembly and the Engine Mounts Assembly in 
accordance with Pilatus PC-6 Service Bulletin No. 53-002 Revision 2.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) Within the next 12 months after the effective date of this 
AD, inspect and modify the fastener assemblies as instructed in 
paragraph 3 of Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin 
Number 53-002, Revision No. 2, dated September 24, 2007.
    (2) After the effective date of this AD, no person shall install 
on any PC-6 series aircraft, water tank assemblies and hydraulic 
pump assemblies, unless they have been previously modified following 
paragraph 4 of Pilatus Aircraft Ltd. Pilatus PC-6 Service Bulletin 
Number 53-002, Revision No. 2, dated September 24, 2007.

FAA AD Differences

    Note 2: 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, 
Standards Office, 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: Doug Rudolph, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090. 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.
    (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 (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency EASA AD No.: 
2008-0083, dated May 5, 2008; and Pilatus Aircraft Ltd. Pilatus PC-6 
Service Bulletin Number 53-002, Revision No. 2, dated September 24, 
2007, for related information.

    Issued in Kansas City, Missouri, on June 3, 2008.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-12816 Filed 6-6-08; 8:45 am]
BILLING CODE 4910-13-P

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