Airworthiness Directives; Eurocopter France (Eurocopter) Model EC225LP Helicopters, 66618-66620 [2011-27771]

Download as PDF 66618 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 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 have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES 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 airworthiness directive (AD): mstockstill on DSK4VPTVN1PROD with RULES ■ 2011–21–12 Erickson Air-Crane Incorporated: Amendment 39–16835; Docket No. FAA–2010–0909; Directorate Identifier 2010–SW–026–AD. Applicability: Model S–64F helicopters, with rotating swashplate assembly (swashplate), part number (P/N) 65104– 11001–051, installed, certificated in any category. Compliance: Required as indicated. To prevent loss of a swashplate due to a fatigue crack, loss of control of the main rotor system, and subsequent loss of control of the helicopter, do the following: VerDate Mar<15>2010 17:05 Oct 26, 2011 Jkt 226001 (a) Within 15 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 15 hours TIS, clean and visually inspect the swashplate for a crack in areas A through F as depicted in Figure 1 of Erickson Air-Crane Service Bulletin 64B10–10, Revision 2, dated April 1, 2008 (SB). (b) Within 150 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 150 hours TIS, clean the swashplate and, using a 10-power or higher magnifying glass, visually inspect for a crack in areas A through F as depicted in Figure 1 of the SB. (c) Within 1,000 hours TIS since the last fluorescent-penetrant inspection (FPI) and thereafter at intervals not to exceed 1,000 hours TIS, remove the swashplate from the rotor head, disassemble and remove the paint from the swashplate, and FPI the swashplate for a crack in accordance with ATSM E1417, Type I, Methods A or C. (d) If a crack is found in the swashplate, before further flight, replace the swashplate with an airworthy swashplate. (e) 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, Rotorcraft Certification Office, Rotorcraft Directorate, ATTN: DOT/FAA Southwest Region, Michael Kohner, ASW–170, Aviation Safety Engineer, Fort Worth, Texas 76137, telephone (817) 222–5170, fax (817) 222–5783, for information about previously approved alternative methods of compliance. (f) The Joint Aircraft System/Component (JASC) Code is 6230: Main Rotor Mast/ Swashplate. (g) The inspections shall be done in accordance with the specified portions of Erickson Air-Crane Service Bulletin 64B10– 10, Revision 2, dated April 1, 2008. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Erickson AirCrane Incorporated, 3100 Willow Springs Road, P. O. Box 3247, Central Point, OR 97502, telephone (541) 664–5544, fax (541) 664–2312. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives. gov/federal_register/code_of_federal_ regulations/ibr_locations.html. (h) This amendment becomes effective on December 1, 2011. Issued in Fort Worth, Texas, on September 29, 2011. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2011–27775 Filed 10–26–11; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1033; Directorate Identifier 2009–SW–43–AD; Amendment 39– 16815; AD 2011–20–05] RIN 2120–AA64 Airworthiness Directives; Eurocopter France (Eurocopter) Model EC225LP Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. AGENCY: This amendment adopts a new airworthiness directive (AD) for the Eurocopter Model EC225LP helicopters. This AD requires inspecting the dome fairing support for a crack at the dome fairing attachment point. If a crack is found, this AD requires replacing the dome fairing support and the associated coning stop support assembly before further flight. If no crack is found, this AD requires repetitive inspections and retorquing the screws at specified intervals. This AD is prompted by the discovery of two fatigue cracks in the dome fairing attachment on the dome fairing support. This condition, if not corrected, could lead to the loss of the dome fairing in flight, causing damage to the helicopter and injury to people on the ground. DATES: Effective November 14, 2011. Comments for inclusion in the Rules Docket must be received on or before December 27, 2011. ADDRESSES: Use one of the following addresses to submit comments on this AD: • Federal eRulemaking Portal: Go to http://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 AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http:// www.eurocopter.com. SUMMARY: E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations Examining the Docket: You may examine the docket that contains the AD, any comments, and other information 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 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. FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222–5130; fax: 817–222–5961. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2009–0023, dated February 20, 2009, to correct an unsafe condition for the Eurocopter Model EC225LP helicopters. EASA advises that two fatigue cracks were discovered in the dome fairing attachment on the dome fairing support due to the loss of the tightening torque of the screws which secure the assembly. Since then, Eurocopter has developed a modification (MOD) which includes installation of redesigned parts with ‘‘modified geometrics’’ in the main rotor hub area. and improves the dome fairing support attachment on the coning stop support. The EASA classified this service information as mandatory and issued EASA AD No. 2009–0023, dated February 20, 2009, to ensure the continued airworthiness of these helicopters. FAA’s Evaluation and Unsafe Condition Determination This helicopter model has been approved by the aviation authority of France and is approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, their technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined an unsafe condition exists and is likely to exist or develop on other helicopters of the same type design. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these products are placed on the U.S. Registry in the future. Differences Between This AD and the EASA AD This AD differs from the EASA AD in that we: • Use ‘‘hours time-in-service’’ rather than ‘‘flight hours.’’ • Do not impose a calendar date compliance time. • Use the term ‘‘inspect’’ rather than ‘‘check.’’ mstockstill on DSK4VPTVN1PROD with RULES Related Service Information Costs of Compliance Eurocopter has issued Emergency Alert Service Bulletin No. 05A005, Revision 1, dated February 3, 2009 (EASB 05A005), which applies to FAA type-certificated Model EC225LP helicopters and non-FAA type certificated Model EC725AP military helicopters. Eurocopter also issued Service Bulletin No. 62–007, Revision 1, dated July 10, 2009, which applies to FAA type-certificated Model EC225LP helicopters, and specifies reinforcing the cone restrainer support, MOD 0743718. EASB 05A005 specifies checking the dome fairing support for a crack and readjusting the tightening torque of the dome fairing-to-dome fairing support attachment screws. If a crack is found, the EASB specifies complying with MOD 0743718 before resuming flight. Eurocopter states that installing this MOD exempts the operator from the monitoring requirements. They also state that this MOD reinforces the coning stop support There are no costs of compliance since there are no helicopters of this type design on the U.S. Registry. VerDate Mar<15>2010 17:05 Oct 26, 2011 Jkt 226001 FAA’s Determination of the Effective Date Since there are currently no affected U.S. registered helicopters, we have determined that notice and opportunity for prior public comment before issuing this AD are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Requirements of This AD This unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Therefore, this AD is being issued to prevent loss of the dome fairing in flight, causing damage to the helicopter and injury to people on the ground. This AD requires inspecting for a crack in the dome fairing support at the dome fairing attachment points. If a PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 66619 crack is found, this AD requires replacing the dome fairing support and the associated coning stop support assembly before further flight. If no crack is found, this AD requires repetitive inspections and retorquing the screws securing the dome fairing support to the dome fairing at specified intervals. This AD is prompted by the discovery of two fatigue cracks in the dome fairing attachment on the dome fairing support. Accomplishing Eurocopter MOD 0743718 constitutes terminating action for the requirements of this AD. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES. Include ‘‘Docket No. FAA–2011–1033; Directorate Identifier 2009–SW–43–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// 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 AD. 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 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). Regulatory Findings We have determined that notice and prior public comment are unnecessary in promulgating this regulation; therefore, it can be issued immediately to correct an unsafe condition in aircraft since none of these model helicopters are registered in the United States. We have also determined that this regulation is not a ‘‘significant regulatory action’’ under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be E:\FR\FM\27OCR1.SGM 27OCR1 66620 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the AD docket. 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. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: Issued in Fort Worth, Texas, on September 13, 2011. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. PART 39—AIRWORTHINESS DIRECTIVES [FR Doc. 2011–27771 Filed 10–26–11; 8:45 am] BILLING CODE 4910–13–P 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: mstockstill on DSK4VPTVN1PROD with RULES ■ 2011–20–05 Eurocopter France (Eurocopter): Amendment 39–16815; Docket No. FAA–2011–1033; Directorate Identifier 2009–SW–43–AD. Applicability: Model EC225LP helicopters, certificated in any category, that have not been modified in accordance with Eurocopter Modification (MOD) 0743718. Compliance: Required as indicated. To prevent loss of the dome fairing in flight, damage to the helicopter, and injury to people on the ground, accomplish the following: (a) Within 15 hours time-in-service (TIS), unless accomplished previously, inspect for 17:05 Oct 26, 2011 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Amended] VerDate Mar<15>2010 a crack in the dome fairing support at the dome fairing attachment points. (1) If a crack is found in the dome fairing support or at a dome fairing attachment point, before further flight, replace the dome fairing support and the associated coning stop support assembly. (2) If no crack is found, thereafter at intervals not exceeding 165 hours TIS, inspect for a crack in the dome fairing support, and re-torque the screws securing the dome fairing support to the dome fairing. Note 1: Eurocopter Emergency Alert Service Bulletin No. 05A005, Revision 1, dated February 3, 2009, and Service Bulletin No. 62–007, Revision 1, dated July 10, 2009, which are not incorporated by reference, contain additional information about the subject of this AD. (b) Accomplishing Eurocopter MOD 0743718 constitutes terminating action for the requirements of this AD. (c) 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, FAA, Attn: Gary Roach, Aviation Safety Engineer, FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222– 5130; fax: 817–222–5961, for information about previously approved alternative methods of compliance. (d) A special flight permit will not be issued. (e) The Joint Aircraft System/Component (JASC) Code is 6300: Main Rotor Drive System. (f) This amendment becomes effective on November 14, 2011. Note 2: The subject of this AD is addressed in European Aviation Safety Agency AD No. 2009–0023, dated February 20, 2009. Jkt 226001 We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–215–1A10, CL–215–6B11 (CL–215T Variant), and CL–215–6B11 (CL–415 Variant) airplanes. This AD results from mandatory continuing 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: SUMMARY: Multiple cracks were reported on the Main Landing Gear (MLG) upper member forward lug, part numbers 160–714–3 (L/H) and 160– 714–4 (R/H). An investigation determined the cause to be fatigue cracks at the base of the step radius with multiple initiation sites. The fatigue cracking may compromise the structural integrity of the MLG during takeoff or landing, leading to failure. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 14, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 14, 2011. We must receive comments on this AD by December 12, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2011–1096; Directorate Identifier 2011–NM–185–AD; Amendment 39–16848; AD 2011–22–06] 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 in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Model CL–215–1A10, CL–215– 6B11 (CL–215T Variant), and CL–215– 6B11 (CL–415 Variant) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 76, Number 208 (Thursday, October 27, 2011)]
[Rules and Regulations]
[Pages 66618-66620]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27771]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1033; Directorate Identifier 2009-SW-43-AD; 
Amendment 39-16815; AD 2011-20-05]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France (Eurocopter) Model 
EC225LP Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the Eurocopter Model EC225LP helicopters. This AD requires inspecting 
the dome fairing support for a crack at the dome fairing attachment 
point. If a crack is found, this AD requires replacing the dome fairing 
support and the associated coning stop support assembly before further 
flight. If no crack is found, this AD requires repetitive inspections 
and retorquing the screws at specified intervals. This AD is prompted 
by the discovery of two fatigue cracks in the dome fairing attachment 
on the dome fairing support. This condition, if not corrected, could 
lead to the loss of the dome fairing in flight, causing damage to the 
helicopter and injury to people on the ground.

DATES: Effective November 14, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before December 27, 2011.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     Federal eRulemaking Portal: Go to http://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 AD from 
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 
75053-4005, telephone (800) 232-0323, fax (972) 641-3710, or at http://www.eurocopter.com.

[[Page 66619]]

    Examining the Docket:
    You may examine the docket that contains the AD, any comments, and 
other information 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 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.

FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer, 
FAA, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone: (817) 222-5130; fax: 817-222-5961.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2009-0023, dated February 20, 2009, to correct an unsafe condition for 
the Eurocopter Model EC225LP helicopters. EASA advises that two fatigue 
cracks were discovered in the dome fairing attachment on the dome 
fairing support due to the loss of the tightening torque of the screws 
which secure the assembly. Since then, Eurocopter has developed a 
modification (MOD) which includes installation of redesigned parts with 
``modified geometrics'' in the main rotor hub area.

Related Service Information

    Eurocopter has issued Emergency Alert Service Bulletin No. 05A005, 
Revision 1, dated February 3, 2009 (EASB 05A005), which applies to FAA 
type-certificated Model EC225LP helicopters and non-FAA type 
certificated Model EC725AP military helicopters. Eurocopter also issued 
Service Bulletin No. 62-007, Revision 1, dated July 10, 2009, which 
applies to FAA type-certificated Model EC225LP helicopters, and 
specifies reinforcing the cone restrainer support, MOD 0743718. EASB 
05A005 specifies checking the dome fairing support for a crack and 
readjusting the tightening torque of the dome fairing-to-dome fairing 
support attachment screws. If a crack is found, the EASB specifies 
complying with MOD 0743718 before resuming flight. Eurocopter states 
that installing this MOD exempts the operator from the monitoring 
requirements. They also state that this MOD reinforces the coning stop 
support and improves the dome fairing support attachment on the coning 
stop support. The EASA classified this service information as mandatory 
and issued EASA AD No. 2009-0023, dated February 20, 2009, to ensure 
the continued airworthiness of these helicopters.

FAA's Evaluation and Unsafe Condition Determination

    This helicopter model has been approved by the aviation authority 
of France and is approved for operation in the United States. Pursuant 
to our bilateral agreement with France, EASA, their technical 
representative, has notified us of the unsafe condition described in 
the EASA AD. We are issuing this AD because we evaluated all 
information provided by EASA and determined an unsafe condition exists 
and is likely to exist or develop on other helicopters of the same type 
design.
    There are no products of this type currently registered in the 
United States. However, this rule is necessary to ensure that the 
described unsafe condition is addressed if any of these products are 
placed on the U.S. Registry in the future.

Differences Between This AD and the EASA AD

    This AD differs from the EASA AD in that we:
     Use ``hours time-in-service'' rather than ``flight 
hours.''
     Do not impose a calendar date compliance time.
     Use the term ``inspect'' rather than ``check.''

Costs of Compliance

    There are no costs of compliance since there are no helicopters of 
this type design on the U.S. Registry.

FAA's Determination of the Effective Date

    Since there are currently no affected U.S. registered helicopters, 
we have determined that notice and opportunity for prior public comment 
before issuing this AD are unnecessary and that good cause exists for 
making this amendment effective in less than 30 days.

Requirements of This AD

    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design registered in the United States. 
Therefore, this AD is being issued to prevent loss of the dome fairing 
in flight, causing damage to the helicopter and injury to people on the 
ground. This AD requires inspecting for a crack in the dome fairing 
support at the dome fairing attachment points. If a crack is found, 
this AD requires replacing the dome fairing support and the associated 
coning stop support assembly before further flight. If no crack is 
found, this AD requires repetitive inspections and retorquing the 
screws securing the dome fairing support to the dome fairing at 
specified intervals. This AD is prompted by the discovery of two 
fatigue cracks in the dome fairing attachment on the dome fairing 
support. Accomplishing Eurocopter MOD 0743718 constitutes terminating 
action for the requirements of this AD.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES. Include ``Docket No. FAA-2011-1033; Directorate 
Identifier 2009-SW-43-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://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 AD. 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 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).

Regulatory Findings

    We have determined that notice and prior public comment are 
unnecessary in promulgating this regulation; therefore, it can be 
issued immediately to correct an unsafe condition in aircraft since 
none of these model helicopters are registered in the United States. We 
have also determined that this regulation is not a ``significant 
regulatory action'' under Executive Order 12866. It has been determined 
further that this action involves an emergency regulation under DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If 
it is determined that this emergency regulation otherwise would be

[[Page 66620]]

significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the AD docket.

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.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2011-20-05 Eurocopter France (Eurocopter): Amendment 39-16815; 
Docket No. FAA-2011-1033; Directorate Identifier 2009-SW-43-AD.

    Applicability: Model EC225LP helicopters, certificated in any 
category, that have not been modified in accordance with Eurocopter 
Modification (MOD) 0743718.
    Compliance: Required as indicated.
    To prevent loss of the dome fairing in flight, damage to the 
helicopter, and injury to people on the ground, accomplish the 
following:
    (a) Within 15 hours time-in-service (TIS), unless accomplished 
previously, inspect for a crack in the dome fairing support at the 
dome fairing attachment points.
    (1) If a crack is found in the dome fairing support or at a dome 
fairing attachment point, before further flight, replace the dome 
fairing support and the associated coning stop support assembly.
    (2) If no crack is found, thereafter at intervals not exceeding 
165 hours TIS, inspect for a crack in the dome fairing support, and 
re-torque the screws securing the dome fairing support to the dome 
fairing.

    Note 1:  Eurocopter Emergency Alert Service Bulletin No. 05A005, 
Revision 1, dated February 3, 2009, and Service Bulletin No. 62-007, 
Revision 1, dated July 10, 2009, which are not incorporated by 
reference, contain additional information about the subject of this 
AD.

    (b) Accomplishing Eurocopter MOD 0743718 constitutes terminating 
action for the requirements of this AD.
    (c) 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, FAA, Attn: Gary Roach, 
Aviation Safety Engineer, FAA, Regulations and Policy Group, 2601 
Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-5130; 
fax: 817-222-5961, for information about previously approved 
alternative methods of compliance.
    (d) A special flight permit will not be issued.
    (e) The Joint Aircraft System/Component (JASC) Code is 6300: 
Main Rotor Drive System.
    (f) This amendment becomes effective on November 14, 2011.

    Note 2:  The subject of this AD is addressed in European 
Aviation Safety Agency AD No. 2009-0023, dated February 20, 2009.


    Issued in Fort Worth, Texas, on September 13, 2011.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27771 Filed 10-26-11; 8:45 am]
BILLING CODE 4910-13-P