Airworthiness Directives; Eurocopter France Model EC130 B4 Helicopters, 28456-28458 [E7-9708]

Download as PDF 28456 Federal Register / Vol. 72, No. 97 / Monday, May 21, 2007 / Proposed Rules Authority: Secs. 23, 161, 68 Stat. 925, 948, as amended (42 U.S.C. 2033, 2201); sec. 29, Pub. L. 85–256, 71 Stat. 579, Pub. L. 95–209, 91 Stat. 1483 (42 U.S.C. 2039); sec. 191, Pub. L. 87–615, 76 Stat. 409 (42 U.S.C. 2241); secs. 201, 203, 204, 205, 209, 88 Stat. 1242, 1244, 1245, 1246, 1248, as amended (42 U.S.C. 5841, 5843, 5844, 5845, 5849); 5 U.S.C. 552, 553; Reorganization Plan No. 1 of 1980, 45 FR 40561, June 16, 1980. 2. In § 1.46, paragraph (c) is revised to read as follows: § 1.46 Office of Nuclear Security and Incident Response. * * * * * (c) Develops emergency preparedness policies, regulations, programs, and guidelines for nuclear facilities; * * * * * Dated at Rockville, Maryland, this 8th day of May, 2007. For the Nuclear Regulatory Commission. Martin J. Virgilio, Acting Executive Director for Operations. [FR Doc. E7–9713 Filed 5–18–07; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28229; Directorate Identifier 2006–SW–23–AD] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model EC130 B4 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). cprice-sewell on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 130 B4 helicopters, with certain twist grip assemblies installed. This proposal would require inspecting the pilot and co-pilot collective levers for proper bonding between the twist grip drive tubes and the control pinions and if debonding is present, replacing the collective levers before further flight. This proposal is prompted by one incident in which the engine remained at idle speed although the twist grip had been turned to the flight position. The actions specified by this proposed AD are intended to detect debonding between the twist grip drive tubes and the control pinions on the pilot and copilot collective levers to prevent loss of cockpit throttle control of the engine, and subsequent loss of control of the helicopter. VerDate Aug<31>2005 15:31 May 18, 2007 Jkt 211001 Comments must be received on or before July 20, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://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 proposed 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 comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. 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: DATES: 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–2007–28229, Directorate Identifier 2006–SW–23–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:// 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 proposed rulemaking. 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 or signed the PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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 https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5227) is located at the plaza level of the Department of Transportation Nassif Building in Room PL–401 at 400 Seventh Street, SW., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. Discussion The European Aviation Safety Agency (EASA) notified us that an unsafe condition may exist on Eurocopter Model EC 130 B4 helicopters, with a twist grip assembly, part number (P/N) 350A27520900, 350A27520901, 350A27520902, or 350A27520903, with a serial number below 64, installed on the pilot’s side, and a twist grip assembly, P/N 350A27521201, with a serial number below 67, installed on the co-pilot’s side. EASA advises that analysis of an incident that occurred during autorotation training revealed a failure of the twist grip drive tube and control pinion bonded attachment. The engine remained at idle rating although the twist grip had been turned back to the flight position. The manufacturer states that the autorotation procedure continued without damage to the helicopter, which landed safely. The failure has been attributed to noncompliant surface preparation during manufacture. Eurocopter, an EADS Company, has issued Alert Service Bulletin EC130 No. 76A001, dated February 10, 2006, which specifies a check by use of a twist grip adjusting gauge of the bonding between the twist grip drive tube and the control pinion on both the pilot and co-pilot collective levers. If the twist grip twists under a load on the adjusting gauge of 35N, the collective lever must be replaced. EASA classified this service bulletin as mandatory and issued AD No. 2006–0079, dated April 3, 2006, 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 section 21.29 of the Federal Aviation E:\FR\FM\21MYP1.SGM 21MYP1 cprice-sewell on PROD1PC71 with PROPOSALS Federal Register / Vol. 72, No. 97 / Monday, May 21, 2007 / Proposed Rules Regulations (14 CFR 21.29) and the applicable bilateral agreement. Under this agreement, EASA has kept the FAA informed of the situation described above. We have examined EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Therefore, the proposed AD would require, within 110 hours time-inservice (TIS) or 4 months, whichever occurs first, or before the installation of a collective lever with an affected twist grip assembly on a helicopter, inspecting the bonding between the twist grip drive tube and the control pinion on both the pilot and co-pilot collective levers. If debonding is present, replacing the collective lever with an airworthy collective lever that has been inspected in accordance with paragraph (a) of this proposed AD, or a collective lever with a twist grip assembly that is not listed in the Applicability of this proposed AD is required before further flight. The actions would be required to be accomplished by following the specified portions of the alert service bulletin described previously. We estimate that this proposed AD would affect 73 helicopters of U.S. registry. The debonding inspection would take approximately 0.25 work hour per helicopter and replacing a collective lever would take approximately 2 work hours, at an average labor rate of $80 per work hour. If replacement is necessary, required parts would cost approximately: • $8,651 for a co-pilot twist grip assembly, P/N 350A27521201; • $12,542 for a pilot twist grip assembly, P/N 350A27520903; • $5 for a clamp, P/N ASNA0021; • $2 for a bolt, P/N 22125BC050014L; and • $1 for a nut, P/N 22431BC050L. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $10,271, assuming one co-pilot twist grip assembly is replaced in one helicopter, that the twist grip adjusting gage (tool) and spring scale needed are on-site and available, that the co-pilot twist grip assembly is not covered by warranty, and no pilot twist grip assembly will need to be replaced. The manufacturer has indicated that parts are covered by warranty up to 1,000 hours or 2 years after the purchase of a new helicopter, VerDate Aug<31>2005 15:31 May 18, 2007 Jkt 211001 however it was indicated that labor is not covered by a warranty. 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the DMS to examine the draft 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. 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: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 28457 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Eurocopter France: Docket No. FAA–2007– 28229; Directorate Identifier 2006–SW– 23–AD. Applicability: Model EC130 B4 helicopters, with a twist grip assembly, part number (P/ N) 350A27520900, 350A27520901, 350A27520902, or 350A27520903, with a serial number below 64, installed on the pilot’s side, and a twist grip assembly, P/N 350A27521201, with a serial number below 67, installed on the co-pilot’s side, certificated in any category. Compliance: Required within 110 hours time-in-service (TIS) or 4 months, whichever occurs first, and before installing a replacement collective lever with an affected twist grip assembly, unless accomplished previously. To detect a reduced bonding strength of the control pinion on the pilot and co-pilot collective lever drive tubes, which could lead to failure of a twist grip drive tube and control pinion bonded attachment, resulting in loss of engine throttle control and subsequent loss of control of the helicopter, accomplish the following: (a) Inspect the pilot and co-pilot collective levers for proper bonding between the twist grip drive tubes and the control pinions in accordance with paragraphs 2.B.1. and 2.B.2. of the Accomplishment Instructions, in Eurocopter, an EADS Company, Alert Service Bulletin EC130 No. 76A001, dated February 10, 2006, except you are neither required to contact the manufacturer nor return a noncompliant collective lever. (b) If a twist grip turns when applying the 35N load to the twist grip, before further flight, replace the collective lever with an airworthy collective lever that has been inspected in accordance with paragraph (a) of this AD, or a collective lever with a twist grip assembly that is not listed in the Applicability 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: 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. Note: The subject of this AD is addressed in EASA (France) AD 2006–0079, dated April 3, 2006. E:\FR\FM\21MYP1.SGM 21MYP1 28458 Federal Register / Vol. 72, No. 97 / Monday, May 21, 2007 / Proposed Rules Issued in Fort Worth, Texas, on May 7, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–9708 Filed 5–18–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28228; Directorate Identifier 2006–SW–08–AD] You may get the service information identified in this proposed 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 comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. Gary Middleton, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5197, fax (817) 222–5961. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Comments Invited Airworthiness Directives; Eurocopter France Model EC130 B4 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). cprice-sewell on PROD1PC71 with PROPOSALS AGENCY: SUMMARY: This amendment proposes adopting a new airworthiness directive (AD) for Eurocopter France (ECF) Model EC130 B4 helicopters. This proposal would require, within 100 hours timein-service (TIS), modifying and testing the wiring of the battery overheat sensing circuit. This proposal is prompted by a malfunction in the battery overheat sensing circuit found during a scheduled inspection. The actions specified by this proposed AD are intended to correct the connection of the thermal switch to the cockpit indicator light, to notify the flight crew of an overheated battery, and to prevent a thermal runaway of the battery, an inflight fire, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before July 20, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://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. VerDate Aug<31>2005 15:31 May 18, 2007 Jkt 211001 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–2007–28228, Directorate Identifier 2006–SW–08–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:// 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 proposed rulemaking. 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 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), or you may visit https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5227) is located at the plaza level of the Department of Transportation Nassif Building in Room PL–401 at 400 Seventh Street, SW., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Discussion The Direction Generale De L’Aviation Civile (DGAC), the airworthiness authority for France, notified the FAA that an unsafe condition may exist on ECF Model EC130 B4 helicopters. The DGAC advises that a malfunction of the battery overheat sensing function, due to incorrect wiring of the battery overheat sensing circuit, was found during a scheduled maintenance. The DGAC also advises that failure of the battery overheat sensing function to operate could give rise to a fire in the event of thermal runaway of the battery. ECF has issued Alert Telex No. 24A001, dated December 20, 2005 (AT). The AT specifies modifying and testing the battery overheat sensing circuit (MOD 073572) for batteries located in the right-hand side baggage compartment (not modified per OP– 3685 or 073739) and for batteries in the tailboom (modified per OP–3685 or 073739). The DGAC classified this AT as mandatory and issued AD No. F– 2006–010, dated January 4, 2006, 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 us informed of the situation described above. We have 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 certificated for operation in the United States. This previously described unsafe condition is likely to exist or develop on other helicopters of the same type design registered in the United States. Therefore, the proposed AD would require, within 100 hours TIS, modifying and testing the wiring of the battery overheat sensing circuit. The actions of this AD would be required to be accomplished by following the specified portions of the alert telex described previously. We estimate that this proposed AD would affect 68 helicopters of U.S. registry. Modifying and testing the overheat sensing circuit wiring would take about 1 work hour per helicopter at an average labor rate of $80 per work hour. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $5440. Regulatory Findings We have determined that this proposed AD would not have federalism E:\FR\FM\21MYP1.SGM 21MYP1

Agencies

[Federal Register Volume 72, Number 97 (Monday, May 21, 2007)]
[Proposed Rules]
[Pages 28456-28458]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-9708]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28229; Directorate Identifier 2006-SW-23-AD]
RIN 2120-AA64


Airworthiness Directives; Eurocopter France Model EC130 B4 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for Eurocopter France (Eurocopter) Model EC 130 B4 helicopters, 
with certain twist grip assemblies installed. This proposal would 
require inspecting the pilot and co-pilot collective levers for proper 
bonding between the twist grip drive tubes and the control pinions and 
if debonding is present, replacing the collective levers before further 
flight. This proposal is prompted by one incident in which the engine 
remained at idle speed although the twist grip had been turned to the 
flight position. The actions specified by this proposed AD are intended 
to detect debonding between the twist grip drive tubes and the control 
pinions on the pilot and co-pilot collective levers to prevent loss of 
cockpit throttle control of the engine, and subsequent loss of control 
of the helicopter.

DATES: Comments must be received on or before July 20, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically;
     Government-wide rulemaking Web site: Go to https://
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 proposed 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 comments to this proposed AD in the AD docket 
on the Internet at https://dms.dot.gov.

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:

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-2007-
28229, Directorate Identifier 2006-SW-23-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://
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 proposed rulemaking. 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 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), or you may visit https://dms.dot.gov.

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Management 
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of 
Transportation Nassif Building in Room PL-401 at 400 Seventh Street, 
SW., Washington, DC. Comments will be available in the AD docket 
shortly after the DMS receives them.

Discussion

    The European Aviation Safety Agency (EASA) notified us that an 
unsafe condition may exist on Eurocopter Model EC 130 B4 helicopters, 
with a twist grip assembly, part number (P/N) 350A27520900, 
350A27520901, 350A27520902, or 350A27520903, with a serial number below 
64, installed on the pilot's side, and a twist grip assembly, P/N 
350A27521201, with a serial number below 67, installed on the co-
pilot's side. EASA advises that analysis of an incident that occurred 
during autorotation training revealed a failure of the twist grip drive 
tube and control pinion bonded attachment. The engine remained at idle 
rating although the twist grip had been turned back to the flight 
position. The manufacturer states that the autorotation procedure 
continued without damage to the helicopter, which landed safely. The 
failure has been attributed to non-compliant surface preparation during 
manufacture.
    Eurocopter, an EADS Company, has issued Alert Service Bulletin 
EC130 No. 76A001, dated February 10, 2006, which specifies a check by 
use of a twist grip adjusting gauge of the bonding between the twist 
grip drive tube and the control pinion on both the pilot and co-pilot 
collective levers. If the twist grip twists under a load on the 
adjusting gauge of 35N, the collective lever must be replaced. EASA 
classified this service bulletin as mandatory and issued AD No. 2006-
0079, dated April 3, 2006, 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 
section 21.29 of the Federal Aviation

[[Page 28457]]

Regulations (14 CFR 21.29) and the applicable bilateral agreement. 
Under this agreement, EASA has kept the FAA informed of the situation 
described above. We have examined EASA's findings, evaluated all 
pertinent information, and determined that AD action is necessary for 
products of this type design that are certificated for operation in the 
United States.
    This previously described unsafe condition is likely to exist or 
develop on other helicopters of the same type design registered in the 
United States. Therefore, the proposed AD would require, within 110 
hours time-in-service (TIS) or 4 months, whichever occurs first, or 
before the installation of a collective lever with an affected twist 
grip assembly on a helicopter, inspecting the bonding between the twist 
grip drive tube and the control pinion on both the pilot and co-pilot 
collective levers. If debonding is present, replacing the collective 
lever with an airworthy collective lever that has been inspected in 
accordance with paragraph (a) of this proposed AD, or a collective 
lever with a twist grip assembly that is not listed in the 
Applicability of this proposed AD is required before further flight. 
The actions would be required to be accomplished by following the 
specified portions of the alert service bulletin described previously.
    We estimate that this proposed AD would affect 73 helicopters of 
U.S. registry. The debonding inspection would take approximately 0.25 
work hour per helicopter and replacing a collective lever would take 
approximately 2 work hours, at an average labor rate of $80 per work 
hour. If replacement is necessary, required parts would cost 
approximately:
     $8,651 for a co-pilot twist grip assembly, P/N 
350A27521201;
     $12,542 for a pilot twist grip assembly, P/N 350A27520903;
     $5 for a clamp, P/N ASNA0021;
     $2 for a bolt, P/N 22125BC050014L; and
     $1 for a nut, P/N 22431BC050L.

    Based on these figures, we estimate the total cost impact of the 
proposed AD on U.S. operators to be $10,271, assuming one co-pilot 
twist grip assembly is replaced in one helicopter, that the twist grip 
adjusting gage (tool) and spring scale needed are on-site and 
available, that the co-pilot twist grip assembly is not covered by 
warranty, and no pilot twist grip assembly will need to be replaced. 
The manufacturer has indicated that parts are covered by warranty up to 
1,000 hours or 2 years after the purchase of a new helicopter, however 
it was indicated that labor is not covered by a warranty.

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 a draft economic evaluation of the estimated costs to 
comply with this proposed AD. See the DMS to examine the draft 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.

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-2007-28229; Directorate Identifier 
2006-SW-23-AD.

    Applicability: Model EC130 B4 helicopters, with a twist grip 
assembly, part number (P/N) 350A27520900, 350A27520901, 
350A27520902, or 350A27520903, with a serial number below 64, 
installed on the pilot's side, and a twist grip assembly, P/N 
350A27521201, with a serial number below 67, installed on the co-
pilot's side, certificated in any category.
    Compliance: Required within 110 hours time-in-service (TIS) or 4 
months, whichever occurs first, and before installing a replacement 
collective lever with an affected twist grip assembly, unless 
accomplished previously.
    To detect a reduced bonding strength of the control pinion on 
the pilot and co-pilot collective lever drive tubes, which could 
lead to failure of a twist grip drive tube and control pinion bonded 
attachment, resulting in loss of engine throttle control and 
subsequent loss of control of the helicopter, accomplish the 
following:
    (a) Inspect the pilot and co-pilot collective levers for proper 
bonding between the twist grip drive tubes and the control pinions 
in accordance with paragraphs 2.B.1. and 2.B.2. of the 
Accomplishment Instructions, in Eurocopter, an EADS Company, Alert 
Service Bulletin EC130 No. 76A001, dated February 10, 2006, except 
you are neither required to contact the manufacturer nor return a 
non-compliant collective lever.
    (b) If a twist grip turns when applying the 35N load to the 
twist grip, before further flight, replace the collective lever with 
an airworthy collective lever that has been inspected in accordance 
with paragraph (a) of this AD, or a collective lever with a twist 
grip assembly that is not listed in the Applicability 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: 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.

    Note: The subject of this AD is addressed in EASA (France) AD 
2006-0079, dated April 3, 2006.



[[Page 28458]]


    Issued in Fort Worth, Texas, on May 7, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-9708 Filed 5-18-07; 8:45 am]
BILLING CODE 4910-13-P
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