Airworthiness Directives; Eurocopter France Model EC130 B4 Helicopters, 33598-33600 [06-5241]

Download as PDF 33598 Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules and Regulations (4) AMOCs approved previously in accordance with AD 2001–14–22, are approved as AMOCs for the corresponding provisions of paragraphs (f) and (j) of this AD. Material Incorporated by Reference (m) You must use Boeing Alert Service Bulletin 747–53A2451, including Appendix A, dated October 5, 2000; or Boeing Alert Service Bulletin 747–53A2451, Revision 1, dated November 10, 2005; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2451, Revision 1, dated November 10, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On August 30, 2001 (66 FR 38891, July 26, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2451, including Appendix A, dated October 5, 2000. (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on May 31, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–5207 Filed 6–9–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Examining the Docket 14 CFR Part 39 [Docket No. FAA–2006–24807; Directorate Identifier 2005–SW–41–AD; Amendment 39– 14603; AD 2006–10–19] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model EC130 B4 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC130 B4 helicopters. This action VerDate Aug<31>2005 18:28 Jun 09, 2006 Jkt 208001 requires inspecting the throttle twist grip (twist grip) assembly for any foreign body (chip or debris), any rotating micro-switch, and any micro-switch roller that does not move freely. If any unairworthy condition is found, this action requires that it be corrected before further flight. This amendment is prompted by two reports of a twist grip assembly jamming in the ‘‘IDLE’’ position. The actions specified in this AD are intended to detect and prevent jamming of the twist grip assembly, which, if present, could keep the engine from operating above idle speed and result in subsequent loss of control of the engine power of the helicopter. DATES: Effective July 27, 2006. Comments for inclusion in the Rules Docket must be received on or before August 11, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: (202) 493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, 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, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. You may examine the docket that contains the AD, any comments, and other information on the Internet at http://dms.dot.gov, or in person at the Docket Management System (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Management Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for Eurocopter Model EC130 B4 helicopters. This action requires, within 30 hours time-in-service (TIS), unless accomplished during the previous 100hour TIS or annual inspection, inspecting the twist grip assembly for any foreign body (chip or debris), any rotating micro-switch, and any microswitch roller that does not move freely. If any unairworthy condition is found, this action requires that it be corrected before further flight. This amendment is prompted by reports of two incidents in which a twist grip assembly jammed in the ‘‘IDLE’’ position. Analyses conducted by the manufacturer revealed that a chip was caught between the roller of the ‘‘FLIGHT’’ micro-switch and the cam in one of the reported incidents, and marks on the cam indicated that debris had been present in the second incident. This condition, if not detected, could result in jamming of the twist grip assembly, which, if present, could keep the engine from operating above idle speed and result in subsequent loss of control of the engine power of the helicopter. The Direction Generale de L’Aviation Civile (DGAC), the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Eurocopter Model EC130 B4 helicopters before embodiment of MOD 073773 fitted with a twist grip assembly, part number (P/N) 350A27–5209–00, P/N 350A27–5209–01, or P/N 350A27– 5209–02, installed. The DGAC advises of two reports of twist grip assembly jamming in the ‘‘IDLE’’ position. Eurocopter has issued Alert Telex No. 05A003, dated June 30, 2005, which specifies an initial and repetitive functional checks of the twist grip assembly on Model EC130 B4 helicopters. The DGAC classified this alert telex as mandatory and issued AD No. F–2005–145, dated August 17, 2005, to ensure the continued airworthiness of these helicopters in France. This helicopter model is manufactured in France and is type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are E:\FR\FM\12JNR1.SGM 12JNR1 Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules and Regulations sroberts on PROD1PC70 with RULES certificated for operation in the United States. This AD requires an ‘‘inspection’’ rather than a ‘‘functional check’’ required by the DGAC AD and does not allow this inspection to be performed by a pilot. Further, the DGAC AD requires repetitive inspections at intervals of 110 hours TIS. This AD does not require those repetitive inspections because a functional check of the twist grip assembly is now a part of the annual or 100-hour TIS helicopter inspection made effective by an amendment to the maintenance instructions in the maintenance manual at AMM Task 76–12–00, 6–1. This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to detect and prevent jamming of the twist grip assembly, which, if present, could keep the engine from operating above idle speed and result in subsequent loss of control of the engine power of the helicopter. This AD requires, within 30 hours TIS, unless accomplished during the previous 100-hour TIS or 12-month inspection, inspecting the twist grip assembly for any foreign body (chip or debris), any rotating micro-switch, and any micro-switch roller that does not move freely. If any unairworthy condition is found, this action requires that it be corrected before further flight. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability of the helicopter. Therefore, the actions described previously are required in a very short time interval and this AD must be issued immediately. Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. We estimate that this AD will affect 46 helicopters and, assuming that no micro-switches will need to be replaced, inspecting the twist grip assembly and removing any chip, if present, will take approximately 0.25 work hours to accomplish at an average labor rate of $80 per work hour. Based on these figures, the total estimated cost impact of the AD on U.S. operators is $920. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments VerDate Aug<31>2005 18:28 Jun 09, 2006 Jkt 208001 to an address listed under ADDRESSES. Include ‘‘Docket No. FAA–2006–24807; Directorate Identifier 2005–SW–41–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to http:// dms.dot.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 our 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), or you may visit http://dms.dot.gov. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD. See the DMS 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 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 33599 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, 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: I 2006–10–19 Eurocopter France: Amendment 39–14603. Docket No. FAA–2006–24807; Directorate Identifier 2005–SW–41–AD. Applicability: Model EC130 B4 helicopters, with a throttle twist grip (twist grip) assembly, part number (P/N) 350A27–5209– 00, P/N 350A27–5209–01, or P/N 350A27– 5209–02, installed, certificated in any category. Compliance: Required as indicated, unless accomplished during the previous 100 hour time-in-service (TIS) or annual inspection. To detect jamming of the twist grip assembly, which could keep the engine from operating above idle speed and result in subsequent loss of control of the engine power of the helicopter, accomplish the following: (a) Within 30 hours TIS, access the twist grip assembly and inspect the cam and micro-switch body and rollers for: (1) Any foreign chip or debris; (2) Any friction point while turning the twist grip assembly from ‘‘Flight’’ to ‘‘Idle’’ position; (3) Any rotating micro-switch body; and (4) Any micro-switch roller that does not turn freely. (b) If you find any chip or debris, remove it; if you find a friction point, a rotating micro-switch body, a binding micro-switch roller or any other unairworthy part, repair or replace the part before further flight. Note 1: Eurocopter Alert Telex No. 05A003, dated June 30, 2005, pertains to the subject of this AD. AMM Task 76–12–00, 6–1, dealing with a repetitive functional check of the twist grip assembly, has been E:\FR\FM\12JNR1.SGM 12JNR1 33600 Federal Register / Vol. 71, No. 112 / Monday, June 12, 2006 / Rules and Regulations inserted into the current maintenance instructions and is now part of the annual or 100-hour inspection. (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, Rotorcraft Directorate, FAA, ATTN: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5355, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (d) This amendment becomes effective on June 27, 2006. Note 2: The subject of this AD is addressed in Direction Generale de L’Aviation Civile (France) AD No. F–2005–145, dated August 17, 2005. Issued in Fort Worth, Texas, on June 1, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–5241 Filed 6–9–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24103; Directorate Identifier 2005–NM–241–AD; Amendment 39–14625; AD 2006–12–01] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600R Series Airplanes, A300 C4–605R Variant F Airplanes, A300 F4– 600R Series Airplanes; and Model A310–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus transport category airplanes. This AD requires replacing the existing vent float valve with a new, improved vent float valve. This AD results from reports of failure of the vent float valve in the left-hand outboard section of the trimmable horizontal stabilizer. We are issuing this AD to prevent, in the event of a lightning strike to the horizontal stabilizer, sparking of metal parts and debris from detached and damaged float valves, or a buildup of static electricity, which could result in ignition of fuel vapors and consequent fire or explosion. DATES: This AD becomes effective July 17, 2006. VerDate Aug<31>2005 18:28 Jun 09, 2006 Jkt 208001 The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of July 17, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus transport category airplanes. That NPRM was published in the Federal Register on March 8, 2006 (71 FR 11555). That NPRM proposed to require replacing the existing vent float valve with a new, improved vent float valve. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Add Revised Service Information The manufacturer, Airbus, advises that both of the service bulletins (Airbus Service Bulletins A300–28–6081 and A310–28–2155, both dated February 16, 2005) specified in the NPRM have been revised. Airbus notes that Airbus Service Bulletins A300–28–6081, Revision 01, dated October 11, 2005; and A310–28–2155, Revision 01, dated October 17, 2005, contain minor changes and that no additional work is required. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 We agree with Airbus and have revised paragraph (f) of the AD to reflect the revised service bulletins. In addition, we have added a new paragraph (g) of this AD specifying that accomplishment of the actions specified in paragraph (f) of the AD in accordance with the original issuance of the service bulletins, as applicable, is considered to be an acceptable method of compliance. Subsequent paragraphs of the AD have been re-identified accordingly. Request To Add a Phrase One commenter, Modification and Replacement Parts Association (MARPA), states that the requirement to install a certain part number to the exclusion of any other part nullifies part 21 of the Federal Aviation Regulations (14 CFR part 21) by preventing the development and/or use of alternative parts. MARPA submits that this can be averted by adding the common phrase ‘‘or FAA-approved equivalent part number’’ as a suffix to the part number mandated to be installed. Additionally, MARPA referenced an existing AD that contains the phrase MARPA suggests. In response to MARPA’s request to add the phrase ‘‘or FAA-approved equivalent part number,’’ we do not agree. Whether an alternative part is ‘‘equivalent’’ in adequately resolving the unsafe condition can be determined only on a case-by-case basis based on a complete understanding of the unsafe condition. Our policy is that, in order for operators to replace a part with one that is not specified in the AD, they must request and receive approval of an Alternative Method of Compliance (AMOC). This is necessary so that we can make a specific determination that an alternative part is or is not susceptible to the same unsafe condition. In response to the commenter’s statement that the requirement to install a certain part number part to the exclusion of any other part nullifies part 21 of the FARs (14 CFR part 21) under which the FAA issues parts manufacturer approvals (PMAs), this statement appears to reflect a misunderstanding of the relationship between ADs and the certification procedural regulations of part 21 of the Federal Aviation Regulations (14 CFR part 21). Those regulations, including section 21.303 of the Federal Aviation Regulations (14 CFR 21.303), are intended to ensure that aeronautical products and parts are safe. But ADs are issued when, notwithstanding those procedures, we become aware of unsafe conditions in these products or parts. Therefore, an AD takes precedence over other ‘‘approvals’’ when we identify an E:\FR\FM\12JNR1.SGM 12JNR1

Agencies

[Federal Register Volume 71, Number 112 (Monday, June 12, 2006)]
[Rules and Regulations]
[Pages 33598-33600]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5241]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24807; Directorate Identifier 2005-SW-41-AD; 
Amendment 39-14603; AD 2006-10-19]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC130 B4 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
Eurocopter France (Eurocopter) Model EC130 B4 helicopters. This action 
requires inspecting the throttle twist grip (twist grip) assembly for 
any foreign body (chip or debris), any rotating micro-switch, and any 
micro-switch roller that does not move freely. If any unairworthy 
condition is found, this action requires that it be corrected before 
further flight. This amendment is prompted by two reports of a twist 
grip assembly jamming in the ``IDLE'' position. The actions specified 
in this AD are intended to detect and prevent jamming of the twist grip 
assembly, which, if present, could keep the engine from operating above 
idle speed and result in subsequent loss of control of the engine power 
of the helicopter.

DATES: Effective July 27, 2006.
    Comments for inclusion in the Rules Docket must be received on or 
before August 11, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically;
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590;
     Fax: (202) 493-2251; or
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, 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, Texas 
75053-4005, telephone (972) 641-3460, fax (972) 641-3527.

Examining the Docket

    You may examine the docket that contains the AD, any comments, and 
other information on the Internet at http://dms.dot.gov, or in person 
at the Docket Management System (DMS) Docket Offices between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The Docket 
Office (telephone (800) 647-5227) is located on the plaza level of the 
Department of Transportation Nassif Building at the street address 
stated in the ADDRESSES section. Comments will be available in the AD 
docket shortly after the DMS receives them.

FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer, 
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: This amendment adopts a new AD for 
Eurocopter Model EC130 B4 helicopters. This action requires, within 30 
hours time-in-service (TIS), unless accomplished during the previous 
100-hour TIS or annual inspection, inspecting the twist grip assembly 
for any foreign body (chip or debris), any rotating micro-switch, and 
any micro-switch roller that does not move freely. If any unairworthy 
condition is found, this action requires that it be corrected before 
further flight. This amendment is prompted by reports of two incidents 
in which a twist grip assembly jammed in the ``IDLE'' position. 
Analyses conducted by the manufacturer revealed that a chip was caught 
between the roller of the ``FLIGHT'' micro-switch and the cam in one of 
the reported incidents, and marks on the cam indicated that debris had 
been present in the second incident. This condition, if not detected, 
could result in jamming of the twist grip assembly, which, if present, 
could keep the engine from operating above idle speed and result in 
subsequent loss of control of the engine power of the helicopter.
    The Direction Generale de L'Aviation Civile (DGAC), the 
airworthiness authority for France, notified the FAA that an unsafe 
condition may exist on Eurocopter Model EC130 B4 helicopters before 
embodiment of MOD 073773 fitted with a twist grip assembly, part number 
(P/N) 350A27-5209-00, P/N 350A27-5209-01, or P/N 350A27-5209-02, 
installed. The DGAC advises of two reports of twist grip assembly 
jamming in the ``IDLE'' position.
    Eurocopter has issued Alert Telex No. 05A003, dated June 30, 2005, 
which specifies an initial and repetitive functional checks of the 
twist grip assembly on Model EC130 B4 helicopters. The DGAC classified 
this alert telex as mandatory and issued AD No. F-2005-145, dated 
August 17, 2005, to ensure the continued airworthiness of these 
helicopters in France.
    This helicopter model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the 
applicable bilateral agreement, the DGAC has kept the FAA informed of 
the situation described above. The FAA has examined the findings of the 
DGAC, reviewed all available information, and determined that AD action 
is necessary for products of this type design that are

[[Page 33599]]

certificated for operation in the United States. This AD requires an 
``inspection'' rather than a ``functional check'' required by the DGAC 
AD and does not allow this inspection to be performed by a pilot. 
Further, the DGAC AD requires repetitive inspections at intervals of 
110 hours TIS. This AD does not require those repetitive inspections 
because a functional check of the twist grip assembly is now a part of 
the annual or 100-hour TIS helicopter inspection made effective by an 
amendment to the maintenance instructions in the maintenance manual at 
AMM Task 76-12-00, 6-1.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect and prevent jamming of the twist grip assembly, which, if 
present, could keep the engine from operating above idle speed and 
result in subsequent loss of control of the engine power of the 
helicopter. This AD requires, within 30 hours TIS, unless accomplished 
during the previous 100-hour TIS or 12-month inspection, inspecting the 
twist grip assembly for any foreign body (chip or debris), any rotating 
micro-switch, and any micro-switch roller that does not move freely. If 
any unairworthy condition is found, this action requires that it be 
corrected before further flight. The short compliance time involved is 
required because the previously described critical unsafe condition can 
adversely affect the controllability of the helicopter. Therefore, the 
actions described previously are required in a very short time interval 
and this AD must be issued immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.
    We estimate that this AD will affect 46 helicopters and, assuming 
that no micro-switches will need to be replaced, inspecting the twist 
grip assembly and removing any chip, if present, will take 
approximately 0.25 work hours to accomplish at an average labor rate of 
$80 per work hour. Based on these figures, the total estimated cost 
impact of the AD on U.S. operators is $920.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2006-24807; 
Directorate Identifier 2005-SW-41-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the AD in light 
of those comments.
    We will post all comments we receive, without change, to http://
dms.dot.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 our 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), or you may visit http://
dms.dot.gov.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the DMS 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, Safety.

Adoption of the Amendment

0
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:

2006-10-19 Eurocopter France: Amendment 39-14603. Docket No. FAA-
2006-24807; Directorate Identifier 2005-SW-41-AD.

    Applicability: Model EC130 B4 helicopters, with a throttle twist 
grip (twist grip) assembly, part number (P/N) 350A27-5209-00, P/N 
350A27-5209-01, or P/N 350A27-5209-02, installed, certificated in 
any category.
    Compliance: Required as indicated, unless accomplished during 
the previous 100 hour time-in-service (TIS) or annual inspection.
    To detect jamming of the twist grip assembly, which could keep 
the engine from operating above idle speed and result in subsequent 
loss of control of the engine power of the helicopter, accomplish 
the following:
    (a) Within 30 hours TIS, access the twist grip assembly and 
inspect the cam and micro-switch body and rollers for:
    (1) Any foreign chip or debris;
    (2) Any friction point while turning the twist grip assembly 
from ``Flight'' to ``Idle'' position;
    (3) Any rotating micro-switch body; and
    (4) Any micro-switch roller that does not turn freely.
    (b) If you find any chip or debris, remove it; if you find a 
friction point, a rotating micro-switch body, a binding micro-switch 
roller or any other unairworthy part, repair or replace the part 
before further flight.

    Note 1: Eurocopter Alert Telex No. 05A003, dated June 30, 2005, 
pertains to the subject of this AD. AMM Task 76-12-00, 6-1, dealing 
with a repetitive functional check of the twist grip assembly, has 
been

[[Page 33600]]

inserted into the current maintenance instructions and is now part 
of the annual or 100-hour inspection.

    (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, Rotorcraft 
Directorate, FAA, ATTN: Ed Cuevas, Aviation Safety Engineer, FAA, 
Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 
76193-0111, telephone (817) 222-5355, fax (817) 222-5961, for 
information about previously approved alternative methods of 
compliance.
    (d) This amendment becomes effective on June 27, 2006.

    Note 2: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (France) AD No. F-2005-145, dated 
August 17, 2005.


    Issued in Fort Worth, Texas, on June 1, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-5241 Filed 6-9-06; 8:45 am]
BILLING CODE 4910-13-P