Airworthiness Directives; Eurocopter France Model AS-365N2, AS 365 N3, and SA-365N1 Helicopters, 48618-48620 [2010-19823]

Download as PDF 48618 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules 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 product(s) identified in this rulemaking action. Other Affected ADs 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. Therefore, I certify this proposed 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 an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. (d) The mandatory continued airworthiness information (MCAI) AD states: ‘‘EASA was informed by the manufacturer of an in-flight incident in which a dynamic weight broke off the control lever subsequently leading to considerable vibrations. A visual inspection revealed that the threaded bolt of the control lever had broken off.’’ This AD requires actions that are intended to prevent separation of dynamic weights, severe vibration, and subsequent loss of control of the helicopter. Related Information (k) MCAI EASA Airworthiness Directive No. 2006–0237, dated August 31, 2007, which supersedes EASA Emergency AD 2007–0189–E, dated July 12, 2007, contains related information. Actions and Compliance Issued in Fort Worth, Texas, on August 3, 2010. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. Applicability (c) This AD applies to Model MBB–BK 117 C–2 helicopters with a tail rotor control lever B642M1009103, installed, certificated in any category. Reason 2. The FAA amends § 39.13 by removing Amendment 39–14961 (72 FR 13679, dated March 23, 2007) and adding the following new AD: (e) Before further flight, unless already done, mark the position of the weights, remove the split pins, remove the weights, and visually inspect the tail rotor control lever in the area around the split pin bore for score marks, notching, scratching, or a crack. Inspect by following the Accomplishment Instructions, paragraph 3.A.(1) through 3.A.(3) and Figure 1, of Eurocopter Alert Service Bulletin MBB BK 117 C–2–64A–002, Revision 2, dated August 6, 2007 (ASB). (1) If done previously, within the next 8 hours time-in-service (TIS) or before reaching 25 hours TIS after the last inspection, and thereafter at intervals not to exceed 8 hours TIS, repeat the visual inspection of the tail rotor control lever as required by paragraph (e) of this AD. (2) If you find a score mark, a notch, or a scratch that exceeds the maintenance manual limits, or find a crack, before further flight: (i) Replace the tail rotor control lever with an airworthy tail rotor control lever; and (ii) Reidentify the tail rotor head, head assembly, and drive system with the new part numbers by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB. (f) Within 100 hours TIS, unless already done, replace the control levers and reidentify the tail rotor head, head assembly, and drive system with the new part numbers by following the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(8) and 3.C.(1) through 3.C.(2), of the ASB. (g) Replacing the control levers and reidentifying the part numbers is terminating action for the requirements of this AD. Eurocopter Deutschland GmbH: Docket No. FAA–2010–0780; Directorate Identifier 2009–SW–68–AD. Differences Between the FAA AD and the MCAI AD List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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 jlentini on DSKJ8SOYB1PROD with PROPOSALS (b) This AD supersedes AD 2006–26–51, Amendment 39–14961, Docket No. FAA 2006–26721, Directorate Identifier 2006–SW– 28–AD. [Amended] Comments Due Date (a) We must receive your comments by September 10, 2010. VerDate Mar<15>2010 16:23 Aug 10, 2010 Jkt 220001 (h) We refer to flight hours as hours TIS. We do not refer to a date of October 31, 2007, for replacing the levers because the date has passed. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Other Information (i) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, Sharon Miles, ASW–111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5122, fax (817) 222–5961, has the authority to approve AMOCs for this AD, if requested, using the procedures found in 14 CFR 39.19. (j) Special flight permits are prohibited. Joint Aircraft System/Component (JASC) Code (l) The JASC Code is 6400: Tail rotor system-control lever. [FR Doc. 2010–19817 Filed 8–10–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0781; Directorate Identifier 2007–SW–49–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model AS–365N2, AS 365 N3, and SA–365N1 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the specified Eurocopter France model helicopters. This proposed AD would require replacing the aluminum tail rotor (T/R) blade pitch control shaft with a steel T/R blade pitch control shaft. This proposed AD is prompted by an incident involving a Eurocopter France Model AS–365N2 helicopter on which there was a loss of control of the T/R due to a broken shaft. The actions specified by this proposed AD are intended to prevent failure of the T/R blade pitch control shaft, loss of T/R control, and subsequent loss of control of the helicopter. SUMMARY: E:\FR\FM\11AUP1.SGM 11AUP1 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules Comments must be received on or before October 12, 2010. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • 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. You may get the service information identified in this proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053– 4005, telephone (800) 232–0323, fax (972) 641–3710, or at https:// www.eurocopter.com. You may examine the comments to this proposed AD in the AD docket on the Internet at https:// www.regulations.gov. DATES: Jim Grigg, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5126, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: jlentini on DSKJ8SOYB1PROD with PROPOSALS Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2010–0781, Directorate Identifier 2007–SW–49–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed rulemaking. Using the search function of the docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the VerDate Mar<15>2010 16:23 Aug 10, 2010 Jkt 220001 comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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. 2007–0220, dated August 13, 2007, to correct an unsafe condition for Eurocopter AS 365 N2, AS 365 N3, and SA 365 N1 helicopters, all serial numbers, equipped with an aluminum T/R blade pitch control shaft, part number (P/N) 365A33.6161.20 or P/N 365A33.6161.21. The EASA advises of an incident in which the pilot of a Model AS 365 N2 helicopter encountered a loss of control of the T/ R, but executed an uneventful run-on landing. A subsequent investigation revealed that the T/R blade pitch control shaft, P/N 365A33.6161.21, had broken in the main section of the shaft sliding area, which appeared to be damaged by peening. The origin of the crack, which developed under fatigue loading, could not be determined. However, accidental damage (i.e., shock impact), is believed to have caused the initiation of a crack. Related Service Information Eurocopter has issued Alert Service Bulletin No. 01.00.59, dated June 21, 2007, which specifies removing any T/ R blade pitch control shaft, P/N 365A33.6161.20 or P/N 365A33.6161.21, and replacing it with a steel T/R blade pitch control shaft, P/N 365A33.6214.20. The EASA classified this alert service bulletin as mandatory and issued EASA AD No. 2007–0220, dated August 13, 2007, to ensure the continued airworthiness of these helicopters. FAA’s Evaluation and Unsafe Condition Determination These products have been approved by the aviation authority of France, and are approved for operation in the United States. Pursuant to our bilateral PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 48619 agreement with France, the EASA, their technical representative, has notified us of the unsafe condition described in the EASA AD. We are proposing this AD because we evaluated all information provided by the EASA and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. This proposed AD would require, within 100 hours time-in-service, removing any aluminum T/R blade pitch control shaft, P/N 365A33.6161.20 or P/N 365A33.6161.21, and replacing it with a steel T/R blade pitch control shaft, P/N 365A33.6214.20. The actions would be required to be accomplished by following specified portions of the alert service bulletin described previously. Differences Between This Proposed AD and the EASA AD Our proposed AD differs from the EASA AD in that we require compliance within 100 hours time-in-service instead of no later than December 31, 2007, since that date has passed. Costs of Compliance We estimate that this proposed AD would affect 36 helicopters of U.S. registry and the proposed actions would take approximately 12 work hours per helicopter to accomplish at an average labor rate of $85 per work hour. Required parts would cost approximately $3,525. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $163,620 to replace the aluminum T/R blade pitch control shaft on the entire fleet, or $4,545 per helicopter. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, 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 that the 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 an economic evaluation of the estimated costs to comply with E:\FR\FM\11AUP1.SGM 11AUP1 48620 Federal Register / Vol. 75, No. 154 / Wednesday, August 11, 2010 / Proposed Rules this proposed AD. See the AD docket to examine the economic evaluation. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] jlentini on DSKJ8SOYB1PROD with PROPOSALS 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Eurocopter France: Docket No. FAA–2010– 0781; Directorate Identifier 2007–SW– 49–AD. Applicability: Model AS–365N2, AS 365 N3, and SA–365N1 helicopters, with an aluminum tail rotor (T/R) blade pitch control shaft, part number (P/N) 365A33.6161.20 or P/N 365A33.6161.21, installed, certificated in any category. Compliance: Required within 100 hours time-in-service, unless accomplished previously. To prevent failure of the T/R blade pitch control shaft, loss of T/R control, and subsequent loss of control of the helicopter, accomplish the following: (a) Remove the aluminum T/R blade pitch control shaft, P/N 365A33.6161.20 or P/N 365A33.6161.21, and replace it with a steel VerDate Mar<15>2010 16:23 Aug 10, 2010 Jkt 220001 Note: The subject of this AD is addressed in European Aviation Safety Agency AD No. 2007–0220, dated August 13, 2007. Issued in Fort Worth, Texas, on August 2, 2010. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2010–19823 Filed 8–10–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0761; Directorate Identifier 2010–NM–069–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 1. The authority citation for part 39 continues to read as follows: § 39.13 T/R blade pitch control shaft, P/N 365A33.6214.20, in accordance with the Accomplishment Instructions, Operational Procedure, paragraphs 2.B.1. through 2.B.3., of Eurocopter Alert Service Bulletin No. 01.00.59, dated June 21, 2007. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Jim Grigg, Aviation Safety Engineer, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5126, fax (817) 222–5961. (c) The Joint Aircraft System/Component (JASC) Code is 6500: Tail Rotor Drive System. We propose to adopt a new airworthiness directive (AD) for certain Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD would require installing two warning level indicator lights on the P2–2 center instrument panel in the flight compartment for certain airplanes. For a certain other airplane, this proposed AD would require activating the cabin altitude warning and takeoff configuration warning lights. For all airplanes, this proposed AD also would require revising the airplane flight manual to remove certain requirements included by previous AD actions, to require new pressure altitude limitations for certain airplanes, and to advise the flightcrew of the following changes: revised emergency procedures to use when a cabin altitude warning or SUMMARY: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 rapid depressurization occurs, and revised cabin pressurization procedures for normal operations. This proposed AD results from a design change in the cabin altitude warning system that would address the identified unsafe condition. We are proposing this AD to prevent failure of the flightcrew to recognize and react to a valid cabin altitude warning horn, which could result in incapacitation of the flightcrew due to hypoxia (lack of oxygen in body), and consequent loss of control of the airplane. DATES: We must receive comments on this proposed AD by September 27, 2010. 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. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information 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. ADDRESSES: 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. E:\FR\FM\11AUP1.SGM 11AUP1

Agencies

[Federal Register Volume 75, Number 154 (Wednesday, August 11, 2010)]
[Proposed Rules]
[Pages 48618-48620]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-19823]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0781; Directorate Identifier 2007-SW-49-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model AS-365N2, AS 
365 N3, and SA-365N1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
specified Eurocopter France model helicopters. This proposed AD would 
require replacing the aluminum tail rotor (T/R) blade pitch control 
shaft with a steel T/R blade pitch control shaft. This proposed AD is 
prompted by an incident involving a Eurocopter France Model AS-365N2 
helicopter on which there was a loss of control of the T/R due to a 
broken shaft. The actions specified by this proposed AD are intended to 
prevent failure of the T/R blade pitch control shaft, loss of T/R 
control, and subsequent loss of control of the helicopter.

[[Page 48619]]


DATES: Comments must be received on or before October 12, 2010.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     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.
    You may get the service information identified in this proposed AD 
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, 
TX 75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at 
https://www.eurocopter.com.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at https://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: Jim Grigg, Aviation Safety Engineer, 
Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham 
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5126, fax (817) 
222-5961.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2010-0781, 
Directorate Identifier 2007-SW-49-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light 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 
with FAA personnel concerning this proposed rulemaking. Using the 
search function of the docket Web site, you can find and read the 
comments to any of our dockets, including the name of the individual 
who sent or signed the comment. You may review the DOT's complete 
Privacy Act Statement in the Federal Register published on April 11, 
2000 (65 FR 19477-78).

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Operations 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

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. 2007-0220, dated August 13, 2007, to correct an unsafe condition 
for Eurocopter AS 365 N2, AS 365 N3, and SA 365 N1 helicopters, all 
serial numbers, equipped with an aluminum T/R blade pitch control 
shaft, part number (P/N) 365A33.6161.20 or P/N 365A33.6161.21. The EASA 
advises of an incident in which the pilot of a Model AS 365 N2 
helicopter encountered a loss of control of the T/R, but executed an 
uneventful run-on landing. A subsequent investigation revealed that the 
T/R blade pitch control shaft, P/N 365A33.6161.21, had broken in the 
main section of the shaft sliding area, which appeared to be damaged by 
peening. The origin of the crack, which developed under fatigue 
loading, could not be determined. However, accidental damage (i.e., 
shock impact), is believed to have caused the initiation of a crack.

Related Service Information

    Eurocopter has issued Alert Service Bulletin No. 01.00.59, dated 
June 21, 2007, which specifies removing any T/R blade pitch control 
shaft, P/N 365A33.6161.20 or P/N 365A33.6161.21, and replacing it with 
a steel T/R blade pitch control shaft, P/N 365A33.6214.20. The EASA 
classified this alert service bulletin as mandatory and issued EASA AD 
No. 2007-0220, dated August 13, 2007, to ensure the continued 
airworthiness of these helicopters.

FAA's Evaluation and Unsafe Condition Determination

    These products have been approved by the aviation authority of 
France, and are approved for operation in the United States. Pursuant 
to our bilateral agreement with France, the EASA, their technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are proposing this AD because we evaluated all 
information provided by the EASA and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs. This proposed AD would require, within 100 hours 
time-in-service, removing any aluminum T/R blade pitch control shaft, 
P/N 365A33.6161.20 or P/N 365A33.6161.21, and replacing it with a steel 
T/R blade pitch control shaft, P/N 365A33.6214.20. The actions would be 
required to be accomplished by following specified portions of the 
alert service bulletin described previously.

Differences Between This Proposed AD and the EASA AD

    Our proposed AD differs from the EASA AD in that we require 
compliance within 100 hours time-in-service instead of no later than 
December 31, 2007, since that date has passed.

Costs of Compliance

    We estimate that this proposed AD would affect 36 helicopters of 
U.S. registry and the proposed actions would take approximately 12 work 
hours per helicopter to accomplish at an average labor rate of $85 per 
work hour. Required parts would cost approximately $3,525. Based on 
these figures, we estimate the total cost impact of the proposed AD on 
U.S. operators to be $163,620 to replace the aluminum T/R blade pitch 
control shaft on the entire fleet, or $4,545 per helicopter.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. Additionally, 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 that the 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 an economic evaluation of the estimated costs to comply 
with

[[Page 48620]]

this proposed AD. See the AD docket to examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Eurocopter France: Docket No. FAA-2010-0781; Directorate Identifier 
2007-SW-49-AD.

    Applicability: Model AS-365N2, AS 365 N3, and SA-365N1 
helicopters, with an aluminum tail rotor (T/R) blade pitch control 
shaft, part number (P/N) 365A33.6161.20 or P/N 365A33.6161.21, 
installed, certificated in any category.
    Compliance: Required within 100 hours time-in-service, unless 
accomplished previously.
    To prevent failure of the T/R blade pitch control shaft, loss of 
T/R control, and subsequent loss of control of the helicopter, 
accomplish the following:
    (a) Remove the aluminum T/R blade pitch control shaft, P/N 
365A33.6161.20 or P/N 365A33.6161.21, and replace it with a steel T/
R blade pitch control shaft, P/N 365A33.6214.20, in accordance with 
the Accomplishment Instructions, Operational Procedure, paragraphs 
2.B.1. through 2.B.3., of Eurocopter Alert Service Bulletin No. 
01.00.59, dated June 21, 2007.
    (b) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, Rotorcraft 
Directorate, FAA, ATTN: Jim Grigg, Aviation Safety Engineer, 2601 
Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5126, 
fax (817) 222-5961.
    (c) The Joint Aircraft System/Component (JASC) Code is 6500: 
Tail Rotor Drive System.

    Note:  The subject of this AD is addressed in European Aviation 
Safety Agency AD No. 2007-0220, dated August 13, 2007.


    Issued in Fort Worth, Texas, on August 2, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-19823 Filed 8-10-10; 8:45 am]
BILLING CODE 4910-13-P
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