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 

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 copilot 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 

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 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 http://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 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 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 

http://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 


cprice-sewell on PROD1PC71 with PROPOSALS
Federal Register / Vol. 72, No. 97 / Monday, May 21, 2007 / Proposed Rules 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-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, 

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. 

§ 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. 


cprice-sewell on PROD1PC71 with PROPOSALS
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] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model EC130 B4 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

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 

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 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 http://dms.dot.gov. 

FOR FURTHER INFORMATION CONTACT: 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. 

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–2007–28228, 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 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 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 

http://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 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 


cprice-sewell on PROD1PC71 with PROPOSALS