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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66614 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

0030, dated February 26, 2010, to 

correct an unsafe condition for the 

Eurocopter Model EC225LP helicopters. 

EASA reports that on several newlyproduced helicopters, some screws and 

nuts that attach the frames of the pilot’s 

and co-pilot’s seats to the floor were 

missing. Further investigation has 

shown that some of the cup washers 

that need to be used in installing the 

countersunk head screws, which attach 

the pilot’s and co-pilot’s seat frames to 

the floor, were missing. EASA states 

that this condition, if not corrected, 

reduces the seat attachments strength, 

and it could result in no longer retaining 

the seats in place in the event of an 

emergency or hard landing. 

Differences Between This AD and the 

EASA AD 

We refer to flight hours as hours timein-service. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin No. 53A020, Revision 0, dated 

February 17, 2010 (ASB), which 

specifies checking for the presence of 

screws and nuts on each side of the 

pilot’s and co-pilot’s seat mount. If one 

screw or one nut is missing, the ASB 

specifies removing the affected seat, 

checking for cup washers, and 

performing the specified corrective 

action to return the seat to conformity. 

FAA’s Evaluation and Unsafe Condition 

Determination 

This helicopter has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, their 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

this same type designs. 

There are no helicopters of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

helicopters are placed on the U.S. 

Registry in the future. 

Costs of Compliance 

There are no costs of compliance 

since there are no helicopters of this 

type design on the U.S. Registry. 

FAA’s Determination of the Effective 

Date 

Since there are currently no affected 

U.S. registered helicopters, we have 

determined that notice and opportunity 

for prior public comment before issuing 

this AD are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Requirements of This AD 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design that may become 

registered in the United States. 

Therefore, this AD is being issued to 

require, within 85 hours time-in-service 

(TIS), unless accomplished previously, 

inspecting for the presence of 4 screws 

and 4 nuts on each side of the copilot’s 

seat mount and 1 screw and 1 nut on 

each side of the pilot’s seat mount. If 

any screw, nut, or cup washer is 

missing, this AD requires removing the 

seat and mount and, before further 

flight, counter sinking the hole and 

installing airworthy parts and replacing 

the mount and seat. The actions must be 

done by following specified portions of 

the ASB described previously. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES. Include 

‘‘Docket No. FAA–2011–1074; 

Directorate Identifier 2010 SW 028 AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the docket web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477 78). 

Regulatory Findings 

We have determined that notice and 

prior public comment are unnecessary 

in promulgating this regulation; 

therefore, it can be issued immediately 

to correct an unsafe condition in aircraft 

since none of these model helicopters 

are registered in the United States. We 

have also determined that this 

regulation is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If it is 

determined that this emergency 

regulation otherwise would be 

significant under DOT Regulatory 

Policies and Procedures, a final 

regulatory evaluation will be prepared 

and placed in the AD docket. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration amends part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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 (AD) to 

read as follows: 

2011–21–11 Eurocopter France: 

Amendment 39–16834; Docket No. 

FAA–2011–1074; Directorate Identifier 

2010–SW–028–AD. 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66615 

Applicability: Model EC225LP helicopters, 

with an airworthiness certificate issued 

before December 15, 2009, with FISHER 

H140 pilot and co-pilot seats, part number 

(P/N) 052010032000D61091, Eurocopter P/N 

704A41120116, or with Eurocopter co-pilot 

seat, P/N 332V08–0180–00, installed, 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect a missing floor attachment screw, 

nut, or washer to help prevent detachment of 

the seat from the floor during an emergency 

landing, do the following: 

(a) Within 85 hours time-in-service (TIS), 

inspect for the presence of 4 screws and 4 

nuts on each side of the copilot’s seat mount 

and 1 screw and 1 nut on each side of the 

pilot’s seat mount by reference to Figures 1 

through 4 of Eurocopter Alert Service 

Bulletin No. 53A020, Revision 0, dated 

February 17, 2010 (ASB). 

(b) If any screw, nut, or cup washer is 

missing, remove the seat and mount and 

before further flight, countersink the hole and 

install airworthy parts and replace the mount 

and seat by following the Accomplishment 

Instructions, paragraph 2.b.2.b., of the ASB. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, FAA, Attn: Gary Roach, 

Aviation Safety Engineer, Rotorcraft 

Directorate, 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. 

(d) The Joint Aircraft System/Component 

Code is 2500: Cabin Equipment/Furnishings. 

(e) The inspection and repair of the pilot 

and co-pilot seats shall be done by following 

the specified portions of Eurocopter Alert 

Service Bulletin No. 53A020, Revision 0, 

dated February 17, 2010. 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 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. 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. 

(f) This amendment becomes effective on 

November 14, 2011. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2010–0030, dated February 26, 2010. 

Issued in Fort Worth, Texas, on September 

29, 2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27680 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–2011–0792; Directorate 

Identifier 2009–SW–19–AD; Amendment 39– 

16762; AD 2011–16–04] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S–92A Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Sikorsky Model S–92A helicopters. This 

action requires making pen and ink 

changes, inserting a copy of this AD, or 

inserting specified temporary revisions 

into the Limitations section of the 

Rotorcraft Flight Manual (RFM) limiting 

the maximum rolling groundspeed for a 

normal landing or takeoff from 65 knots 

to 50 knots for helicopters with a certain 

serial-numbered landing gear retract 

actuator (actuator). Instead of limiting 

the groundspeed, replacing the affected 

actuator with a modified actuator is 

terminating action for the requirements 

of this AD. This amendment is 

prompted by a report of a main landing 

gear that would not retract. The 

manufacturer reports that certain 

actuators were manufactured with 

down-lock keys that did not meet the 

specified minimum hardness 

requirements. This condition, if not 

corrected, could lead to a landing gear 

collapse following a roll-on landing that 

exceeds 50 knots groundspeed. These 

actions are intended to prevent collapse 

of a landing gear and subsequent loss of 

control of the helicopter. 

DATES: Effective November 14, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 27, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

You may get the service information 

identified in this AD from Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (203) 383–4866, 

e-mail address tsslibrary@sikorsky.com, 

or at http://www.sikorsky.com. 

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: 

Michael Schwetz, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, 12 New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7761, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for 

Sikorsky Model S–92A helicopters. This 

action requires making pen and ink 

changes, inserting a copy of this AD, or 

inserting certain temporary revisions 

into the Limitations section of the RFM 

limiting the maximum groundspeed for 

a normal landing or takeoff to 50 knots 

for helicopters with a certain serialnumbered actuator installed. The 

temporary revisions to the Limitations 

section of the RFM also require 

replacing the actuators if the landing 

exceeds the 50 knot rolling groundspeed 

before further flight or before towing the 

helicopter; rolling ground taxi 

operations are permitted. Replacing the 

affected actuator with a modified 

actuator is terminating action for the 

requirements of this AD. The 

manufacturer states that it anticipates 

retrofitting the fleet with a modified 

actuator within 3 years. This 

amendment is prompted by a report that 

certain actuators were manufactured 

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