Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66609 

for the purposes of this AD is by modifying 

the servocontrol and marking an ‘‘R’’ after the 

S/N by following Goodrich Service Bulletin 

(SB) No. SC7203–67–31–02, dated May 11, 

2010, for servocontrol, P/N SC7203–1, or 

Goodrich SB No. SC72216739–02, dated May 

11, 2010, for servocontrol, P/N SC7221 1. The 

Goodrich SBs are attached to Eurocopter 

Emergency Alert SB containing two numbers 

(67.00.40 and 67–00.27), dated June 15, 2010 

as Appendix 1 and Appendix 2, respectively. 

None of these three SBs is incorporated by 

reference in this AD. 

(e) Replacing a servocontrol with an 

airworthy servocontrol that is marked with a 

letter ‘‘R’’ by the manufacturer after the S/N 

constitutes terminating action for the 

requirements of this AD. 

(f) 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: Gary Roach, Aviation Safety 

Engineer, FAA, Regulations and Guidance 

Group, 2601 Meacham Blvd, Fort Worth, 

Texas 76137, telephone (817) 222–5130, fax 

(817) 222 5961, for information about 

previously approved alternative methods of 

compliance. 

(g) The Joint Aircraft System/Component 

(JASC) Code is 6730: Rotorcraft Servo 

System. 

(h) This amendment becomes effective on 

November 14, 2011. 

Note 2: The subject of this AD is addressed 

in European Aviation Safety Agency 

Emergency AD No. 2010–0117–E, dated June 

16, 2010. 

Issued in Fort Worth, Texas, on August 23, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27673 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1035; Directorate 

Identifier 2011–SW–038–AD; Amendment 

39–16817; AD 2011–15–51] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) Model 

407 and 427 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting Airworthiness Directive (AD) 

2011–15–51, which was sent previously 

to all known U.S. owners and operators 

of the specified Bell Model 407 and 427 

helicopters by individual letters. This 

AD requires inspecting certain 

hydraulic servo actuators to determine 

whether the shaft turns independently 

of the nut or the clevis assembly. If the 

shaft turns independently, this AD 

requires replacing the servo with an 

airworthy servo. If the shaft does not 

turn independently, the AD requires 

inspecting to determine the condition of 

the lock washers. Based on the 

condition of the lock washers, the AD 

requires either replacing the servo with 

an airworthy servo, or if any tab of the 

lock washer is not flush against a flat 

surface of the nut or clevis assembly, 

bending it flush against a flat surface. 

The AD also requires reidentifying the 

servo by metal-impression stamping or 

by vibro-etching ‘‘67.01’’ onto the 

modification plate. Also, the AD 

requires before installing a servo with a 

part number or serial number identified 

in this AD, not identified by ‘‘67–01’’ on 

the modification plate, inspecting it by 

following the requirements of this AD. 

This AD is prompted by a report that a 

quality escape by a supplier has 

occurred and certain servos may have a 

loose nut, shaft, and clevis assembly 

due to improper lock-washer 

installation. An investigation after an 

accident revealed the clevis nut on the 

servo was loose. The actions specified 

by this AD are intended to prevent a 

malfunction of a servo in the flight 

control system and subsequent loss of 

control of the helicopter. 

DATES: Effective November 14, 2011, to 

all persons except those persons to 

whom it was made immediately 

effective by Emergency AD 2011–15–51, 

issued on July 8, 2011, which contained 

the requirements of this amendment. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

14, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 27, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

You may get the service information 

identified in this AD from Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272, or 

at http://www.bellcustomer.com/files/. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

2601 Meacham Blvd, Fort Worth, Texas 

76137, telephone (817) 222–5051, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: On July 8, 

2011, the FAA issued Emergency AD 

2011–15–51 for the specified model 

helicopters, which requires inspecting 

certain servos to determine whether the 

shaft turns independently of the nut or 

the clevis assembly. If the shaft turns 

independently, the AD requires 

replacing the servo with an airworthy 

servo. If the shaft does not turn 

independently, the AD requires 

inspecting to determine the condition of 

the lock washers. If at least one lock 

washer is not bent flush against a flat 

surface of the nut and at least one tab 

of the lock washer is not bent flush 

against a flat surface of the clevis 

assembly, the AD requires replacing the 

servo with an airworthy servo. If any tab 

of the lock washer is not bent flush 

against either a flat surface of the nut or 

clevis assembly, the AD requires 

bending the tab flush against a flat 

surface. The AD also requires 

reidentifying the servo by metalimpression stamping or by vibro-etching 

‘‘67.01’’ onto the modification plate. 

Also, the AD requires before installing 

a servo with a part number or serial 

number identified in this AD, not 

identified by ‘‘67–01’’ on the 

modification plate, inspecting and 

reidentifying it by following the 

requirements of this AD. That action 

was prompted by a report that a quality 

escape by a supplier has occurred and 

certain servos may have a loose nut, 

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66610 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

shaft, and clevis assembly due to 

improper lock-washer installation. An 

investigation after an accident revealed 

the clevis nut on the servo was loose. 

This condition, if not corrected, could 

result in a malfunction of a servo in the 

flight control system and subsequent 

loss of control of the helicopter. 

Transport Canada, the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

these helicopter models. Transport 

Canada advises that a quality escape by 

a supplier has occurred, and a number 

of servos may have a loose nut, shaft, 

and clevis assembly. Transport Canada 

states in its AD that the loose 

connection is due to improper lockwasher installation, which is not 

traceable or identifiable except by 

inspection. The authority also states a 

disconnect of the affected parts may 

lead to loss of control of the helicopter. 

Bell has issued Alert Service Bulletin 

(ASB) 407–11–96 and 427–11–35, both 

dated June 29, 2011, which specify the 

part numbers and serial numbers of the 

affected servos and refer to ASB 407– 

05–70, Revision A, dated November 10, 

2005; ASB 427–05–12, Revision A, 

dated November 14, 2005; with HR 

Textron Service Bulletin (SB) 

41011300–67–01, Revision 2, dated 

November 9, 2005; HR Textron SB 

41011400–67–01, Revision 2, dated 

November 9, 2005; and HR Textron SB 

41011700–67–01, Revision 2, dated 

November 9, 2005, attached. The ASBs 

also specify reidentifying the servos 

with a ‘‘67–01’’ on the modification 

plate indicating the inspection 

procedures were followed. 

Transport Canada classified the ASBs 

as mandatory and issued AD No. CF– 

2011–17, dated June 30, 2011, to ensure 

the continued airworthiness of these 

helicopters. 

This helicopter model is 

manufactured in Canada 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, Transport Canada 

has kept us informed of the situation 

described above. We have examined the 

findings of Transport Canada, reviewed 

all available information, and 

determined that AD action is necessary 

for helicopters of this type design that 

are certificated for operation in the 

United States. 

Since the unsafe condition described 

is likely to exist or develop on other Bell 

Model 407 and 427 helicopters of these 

same type designs, the FAA issued 

Emergency AD 2011–15–51 to prevent a 

malfunction of a servo in the flight 

control system and subsequent loss of 

control of the helicopter. The AD 

requires before further flight for certain 

affected servos and within 25 hours 

time-in-service for certain other affected 

servos, identified by a serial number, 

retracting the boot and inspecting the 

servo as follows: 

• Applying only hand pressure, 

determining whether the nut, shaft, or 

clevis assembly turns independently. If 

the shaft turns independently of the nut 

or the clevis assembly, before further 

flight, replacing the servo with an 

airworthy servo. 

• If the shaft does not turn 

independently, inspecting to determine 

whether at least one tab of a lock washer 

is bent flush against a flat surface of the 

nut and at least one tab of the lock 

washer is bent flush against a flat 

surface of the clevis assembly. 

• If at least one lock washer tab is not 

aligned and bent flush with a flat 

surface of the nut and at least one lock 

washer tab is not aligned and bent flush 

with a flat surface of the clevis 

assembly, before further flight, replacing 

the servo with an airworthy servo. 

• If any tab of the lock washer is not 

bent flush against either a flat surface of 

the nut or clevis assembly, bend the tab 

flush against a flat surface. 

• Reidentifying the servo by metalimpression stamping or by vibro-etching 

‘‘67.01’’ onto the modification plate. 

• Before installing a servo with a P/ 

N and S/N identified in this AD, not 

identified by ‘‘67–01’’ on the 

modification plate, inspecting it by 

following the requirements of this AD. 

This AD differs from the Transport 

Canada AD in that we do not require 

that the servo be returned to the 

manufacturer. Also, we do not limit the 

applicability to specific serial-numbered 

helicopters. We have specified the 

inspection requirements rather than 

referring to the applicable service 

bulletins. The AD requires that the servo 

be replaced before further flight, and the 

Transport Canada AD refers to the ASB, 

which requires that the servo be 

replaced within 300 hours time-inservice. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the controllability of the 

helicopter. Therefore, inspecting the 

servos for specified conditions and 

replacing any affected servo, as 

necessary, are required before further 

flight, and this AD must be issued 

immediately. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

letters issued on July 8, 2011, to all 

known U.S. owners and operators of 

Bell Model 407 and 427 helicopters. 

These conditions still exist, and the AD 

is hereby published in the Federal 

Register as an amendment to 14 CFR 

39.13 to make it effective to all persons. 

We estimate that this AD will affect 

582 helicopters of U.S. registry, and 

inspecting or replacing an affected servo 

will take about 2 work hours to inspect 

and 2 work hours to replace per 

helicopter at an average labor rate of $85 

per work hour. Required parts will cost 

about $33,000 per helicopter. Based on 

these figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $164,940, assuming 2 servos are 

replaced on the entire fleet. 

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–2011–1035; 

Directorate Identifier 2011–SW–038– 

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://www.

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of 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). 

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: 

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Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66611 

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 AD docket to examine 

the economic evaluation. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2011–15–51 Bell Helicopter Textron, Inc. 

(Bell): Amendment 39–16817; Docket 

No. FAA–2011–1035; Directorate 

Identifier 2011–SW–038–AD. 

Applicability: Model 407 helicopters with 

a hydraulic servo actuator assembly (servo), 

part number (P/N) 206–076–062–105, or –107 

and Model 427 helicopters, with servo, P/N 

206–076–062–109 or –111, installed, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect loose or misaligned parts of the 

servo that could lead to failure of the servo 

and subsequent loss of control of the 

helicopter, do the following: 

(a) Before further flight, for those 

helicopters with a servo serial number (S/N) 

on the modification plate listed in Table 1 of 

Bell Alert Service Bulletin (ASB) No. 407– 

11–96, dated June 29, 2011, for the Model 

407 helicopters or Table 1 of ASB 427–11– 

35, dated June 29, 2011, for the Model 427 

helicopters, do the following: 

(1) Retract the boot depicted as ‘‘230’’ in 

Figure 1 of this AD: 

Note 1: Bell ASB 427–05–12, Revision A, 

dated November 14, 2005; HR Textron SBs 

41011300–67–01, 41011400–67–01, and 

41011700–67–01, all Revision 2, all dated 

November 9, 2005, which are not 

incorporated by reference, contain 

information pertaining to the subject of this 

AD. 

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66612 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

(2) Applying only hand pressure, 

determine whether the nut, shaft, or clevis 

assembly, depicted as ‘‘225,’’ ‘‘215,’’ and 

‘‘205,’’ respectively, in Figure 1 of this AD, 

turns independently. If the shaft turns 

independently of the nut or the clevis 

assembly, before further flight, replace the 

servo with an airworthy servo. 

(3) If the shaft does not turn 

independently, inspect to determine whether 

at least one tab of the lock washer is bent 

flush against a flat surface of the nut and at 

least one tab of the lock washer is bent flush 

against a flat surface of the clevis assembly. 

(i) If at least one lock washer tab is not 

aligned and bent flush with a nut flat surface 

and at least one lock washer tab is not 

aligned and bent flush with a flat surface of 

the clevis assembly, before further flight, 

replace the servo with an airworthy servo. 

(ii) If any tab of the lock washer is not bent 

flush against either a flat surface of the nut 

or clevis assembly, bend the tab flush against 

a flat surface. 

(4) After accomplishing paragraph (a)(1) 

through (a)(3) of this AD, reidentify the servo 

by metal-impression stamping or by vibroetching ‘‘67–01’’ onto the modification plate. 

(b) For those servo P/Ns with a S/N less 

than the S/Ns listed in the following Table 

A of this AD but NOT specifically included 

in the list of S/Ns in Table 1 referenced in 

paragraph (a) of this AD, within 25 hours 


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Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66613 

time-in-service, inspect the nut, shaft, and 

clevis assembly and accomplish the 

requirements of paragraphs (a)(1) through 

(a)(4) of this AD. 

TABLE A 

Helicopter model Servo P/N Servo prefix ‘‘HR,’’ S/N 

407 .......................... 41011300–101 (BHT 206–076–062–105) ................................................................................. Less than 807. 

41011400–101 (BHT 206–076–062–107) ................................................................................. Less than 2248. 

427 .......................... 41011300–101 (BHT 206–076–062–111) ................................................................................. Less than 807. 

41011700–101 (BHT 206–076–062–109) ................................................................................. Less than 230. 

(c) Before installing a servo with a P/N and 

S/N identified in paragraphs (a) or (b) of this 

AD, not identified by ‘‘67–01’’ on the 

modification plate, inspect the servo by 

following the requirements of this AD. 

(d) 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: Matt 

Wilbanks, Aviation Safety Engineer, 2601 

Meacham Blvd, Fort Worth, Texas 76137, 

telephone (817) 222–5051, fax (817) 222– 

5961, for information about previously 

approved alternative methods of compliance. 

(e) The Joint Aircraft System/Component 

(JASC) Code is: 6730: Rotorcraft Servo 

System. 

(f) The affected servo serial numbers are 

listed in Table 1 of Bell Alert Service Bulletin 

(ASB) No. 407–11–96, dated June 29, 2011, 

for the Model 407 helicopters or Table 1 of 

ASB 427–11–35, dated June 29, 2011, for the 

Model 427 helicopters. The Director of the 

Federal Register approved this incorporation 

by reference in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4, telephone (450) 

437–2862 or (800) 363–8023, fax (450) 433– 

0272, or at http://www.bellcustomer.com/ 

files/. Copies may be inspected at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ibr_

locations.html. 

(g) This amendment becomes effective on 

November 14, 2011, to all persons except 

those persons to whom it was made 

immediately effective by Emergency AD 

2011–15–51, issued July 8, 2011, which 

contained the requirements of this 

amendment. 

Note 2: The subject of this AD is addressed 

in Transport Canada AD CF–2011–17, dated 

June 30, 2011. 

Issued in Fort Worth, Texas, on September 

19, 2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27687 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1074; Directorate 

Identifier 2010–SW–028–AD; Amendment 

39–16834; AD 2011–21–11] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Model EC225LP 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Eurocopter Model EC225LP helicopters. 

This AD requires inspecting the side 

mount of the pilot and copilot seats to 

determine if any floor attachment screw, 

nut, or washer is missing. If a screw, 

nut, or washer is missing, this AD also 

requires installing airworthy parts. This 

AD is prompted by a report that some 

of the floor attachment screws and nuts 

under the pilot and co-pilot seats were 

missing. Further investigation has 

shown that some of the cup washers 

that need to be used in installing 

countersunk head screws that attach the 

pilot and co-pilot seat frame to the floor 

were missing. A missing floor 

attachment screw, washer, or nut, if not 

detected, could reduce the strength of 

the seat attachment. The actions 

specified in this AD are intended to 

detect a missing floor attachment screw, 

washer, or nut and help prevent 

detachment of the seat from the floor 

during an emergency landing. 

DATES: Effective November 14, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

14, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 27, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

You may get the service information 

identified in this AD from American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, TX 75053–4005, 

telephone (800) 232–0323, fax (972) 

641–3710, or at http:// 

www.eurocopter.com. 

Examining te Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Guidance Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5130, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2010– 

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