63052 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. The FAA amends § 39.13 by adding 

the following new AD: 

2010–21–01 Eurocopter France: 

Amendment 39–16461. Docket No. 

FAA–2010–0969; Directorate Identifier 

2009–SW–62–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on October 29, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Eurocopter France 

Model AS350B, BA, B1, B2, B3, D, AS355E, 

F, F1, F2, and N helicopters, certificated in 

any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

that AD is issued following one report of a 

crack discovered in the area of the center 

cross-member at station X 2325, at the 

attachment point of the yaw channel balltype control sheath stop of an AS355N 

helicopter with the collective-to-yaw control 

coupling. Investigations revealed that the 

helicopter did not have the structural 

doublers installed, which are combined with 

the collective-to-yaw control coupling 

installation. Repetitive loads on the nonmodified cross-member may cause it to crack. 

A crack can reduce the yaw control travel. 

The AD requires actions that are intended to 

prevent reduced yaw control and subsequent 

loss of control of the helicopter. 

Actions and Compliance 

(e) Within 10 hours time-in-service (TIS) or 

within 1 month, whichever occurs first, 

unless already done, determine whether the 

cross-member (numbered ‘‘1’’) at station X 

2165 and the two doublers (numbered ‘‘2’’ 

and ‘‘3’’) at stations X 2325 and Y 269 are 

installed as shown in Figure 1 of Eurocoper 

Emergency Alert Service Bulletin (EASB) No. 

53.00.37, dated April 11, 2007 (EASB 

53.00.37), for the Model AS350 helicopters 

and EASB No. 53.00.23, dated April 11, 2007 

(EASB 53.00.23), for the Model AS355 

helicopters. 

Note: The one Eurocopter EASB contains 3 

different numbers (Nos. 53.00.37, 53.00.11, 

and 53.00.23) for 4 different Eurocopter 

model helicopters. EASB 53.00.37 relates to 

2 Model 350 (350 BB and 350 L1) helicopters 

that are not type-certificated in the United 

States; and EASB No. 53.00.11 relates to 4 

Model 550 and 6 Model 555 military 

helicopters that are not type-certificated in 

the United States. 

(f) If the cross-member (numbered ‘‘1’’) and 

doublers (numbered ‘‘2’’ and ‘‘3’’) are not 

installed, before further flight, inspect for a 

crack in the center cross-member (numbered 

‘‘4’’) in the area around the attachment point 

of the tail rotor directional ball-type control 

as shown in Figure 1 of EASB 53.00.37 for 

the Model AS350 helicopters or EASB 

53.00.23 for the Model AS355 helicopters. 

(1) If you find a crack, before further flight, 

replace the unairworthy center cross-member 

(Numbered ‘‘4’’) with an airworthy center 

cross-member and comply with paragraph (g) 

of this AD. 

(2) If you do not find a crack, before further 

flight, inspect the tail rotor control rigging. 

(g) Within 55 hours TIS, install the crossmember (Numbered ‘‘1’’) at station X 2165 

and the 2 doublers (Numbered ‘‘2’’ and ‘‘3’’) 

at stations X 2325 and Y 269 by following the 

Appendix and the referenced Figures 2 and 

3 of EASB 53.00.37 for the Model AS350 

helicopters and EASB 53.00.23 for the Model 

AS355 helicopters. 

Differences Between the FAA AD and the 

MCAI AD 

(h) This AD differs from the MCAI AD as 

follows: 

(1) We use the word ‘‘inspect’’ to describe 

the actions required by an inspector versus 

the word ‘‘check,’’ which is how we describe 

the actions allowed by a pilot. 

(2) We refer to the compliance time as 

hours TIS rather than flying hours. 

(3) We do not include the military model 

helicopters. 

Other Information 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, ATTN: 

Gary Roach, Aviation Safety Engineer, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

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

5961, has the authority to approve AMOCs 

for this AD, if requested, using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) EASA Emergency AD No. 2007–0139–E, 

dated May 15, 2007 (corrected May 23, 2007), 

contains related information. 

Joint Aircraft System/Component (JASC) 

Code 

(k) The JASC Code is 5320—Fuselage Misc. 

Structure. 

Material Incorporated by Reference 

(l) You must use the specified portions of 

Eurocoper Emergency Alert Service Bulletin 

No. 53.00.37 for the AS350 model helicopters 

and No. 53.00.23 for the AS355 model 

helicopters, both dated April 11, 2007, to do 

the actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (800) 

232–0323, fax (972) 641–3510. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, DOT/FAA 

Southwest Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; 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/ 

cfr/ibr-locations.html. 

Issued in Fort Worth, Texas, on September 

23, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25273 Filed 10–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0779; Directorate 

Identifier 2009–SW–84–AD; Amendment 39– 

16467; AD 2010–21–07] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (ECF) Model AS350B3 and 

EC130 B4 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Eurocopter France Model AS350B3 and 

EC130 B4 helicopters. This amendment 

is prompted by a mandatory continuing 

airworthiness information (MCAI) AD 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community. The MCAI AD 

states that a dormant failure of one of 

the two contactors 53Ka or 53Kb can 

occur following certain modifications. 

Failure of a contactor can prevent 

switching from ‘‘IDLE’’ mode to 

‘‘FLIGHT’’ mode during autorotation 

training making it impossible to execute 

a power recovery and compelling the 

pilot to continue the autorotation to the 

ground. This condition, if not corrected, 

can lead to an unintended touchdown to 

the ground during a practice 

autorotation at a flight-idle power 

setting, damage to the helicopter, and 

injury to the occupants. 

DATES: Effective November 18, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

18, 2010. 


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Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 63053 

ADDRESSES: You may get the service 

information identified in this AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (800) 232–0323, 

fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

Examining the Docket: You may 

examine the docket that contains this 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov or at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Rotorcraft 

Directorate, Safety Management Group, 

ASW–112, Ed Cuevas, Aviation Safety 

Engineer, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone: 817– 

222–5135; fax: 817–222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a Notice of Proposed 

Rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to ECF Model AS350B3 and 

EC130 B4 helicopters on August 3, 

2010. That NPRM was published in the 

Federal Register on August 11, 2010 (75 

FR 48615). That NPRM proposed to 

require inspecting the pilot’s and copilot’s throttle twist for proper operation 

of the contactors, which provide for 

changes between the ‘‘IDLE’’ and 

‘‘FLIGHT’’ positions of the throttle twist 

grip control. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No. 

2009–0256, dated December 2, 2009, to 

correct an unsafe condition for the ECF 

Model AS350B3 and EC130 B4 

helicopters. EASA advises that analysis 

shows a dormant failure of one of the 

two contactors 53Ka or 53Kb can occur 

following the modification of the Model 

AS350B3 by MOD 073254 and 

modification of the Model EC130 B4 by 

MOD 073773. Failure of a contactor can 

prevent switching from ‘‘IDLE’’ mode to 

‘‘FLIGHT’’ mode during autorotation 

training making it impossible to execute 

a power recovery and compelling the 

pilot to continue the autorotation to the 

ground. This condition, if not corrected, 

can lead to an unintended touchdown to 

the ground during a practice 

autorotation at a flight-idle power 

setting, damage to the helicopter, and 

injury to the occupants. 

Related Service Information 

ECF has issued Alert Service Bulletin 

(ASB) No. 05.00.61 for the Model 

AS350B3 helicopters and ASB No. 

05A009 for the EC130 B4 helicopters. 

Both ASBs are dated November 16, 

2009. Both ASBs specify a functional 

check of the two contactors 53Ka and 

53Kb, which are used to switch from 

‘‘IDLE’’ to ‘‘FLIGHT’’ mode or vice versa. 

The ASBs also specify repetitive 

checking of the contactors for correct 

opening and closing to detect this 

dormant failure. ECF states that it will 

be preparing a modification, which will 

cancel the ASBs, in the very near future. 

Once the manufacturer develops 

corrective terminating actions, we 

anticipate further rulemaking. 

FAA’s Evaluation and Unsafe Condition 

Determination 

These products have been approved 

by the aviation authority of France and 

are 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 products of 

these same type designs. 

Differences Between this AD and the 

MCAI AD 

We refer to flying hours as hours timein-service (TIS). Also, we refer to 

maintenance actions as inspections 

rather than checks. 

Comments 

By publishing the NPRM, we gave the 

public an opportunity to participate in 

developing this AD. However, we 

received no comments on the NPRM or 

on our determination of the cost to the 

public. Therefore, based on our review 

and evaluation of the available data, we 

have determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

about 116 of the Model EC130 B4 

helicopters and 231 of the Model 

AS350B3 helicopters for a total of 347 

helicopters of U.S. registry. We also 

estimate that it will take about 0.5 workhour per helicopter to inspect and about 

0.5 work-hour per helicopter to replace 

a micro-switch. The average labor rate is 

$85 per work-hour. Required parts cost 

about $538 for the T3933–3 

microswitch. Based on these figures, we 

estimate that the cost of this AD on U.S. 

operators is $21,714, assuming 4 

microswitches are replaced on the 

Model EC130 B4 helicopters and 8 

microswitches are replaced on the 

Model AS350B3 helicopters. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. We prepared an 

economic evaluation of the estimated 

costs to comply with this AD. See the 

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: 


emcdonald on DSK2BSOYB1PROD with RULES
63054 Federal Register / Vol. 75, No. 198 / Thursday, October 14, 2010 / Rules and Regulations 

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: 

2010–21–07 Eurocopter France: 

Amendment 39–16467; Docket No. 

FAA–2010–0779; Directorate Identifier 

2009–SW–84–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on November 18, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model AS350B3 and 

EC130 B4 helicopters, certificated in any 

category, with the ARRIEL 2B1 engine with 

the two-channel Full Authority Digital 

Engine Control (FADEC), and with new twist 

grip modification (MOD) 073254 for the 

Model AS350B3 helicopter or MOD 073773 

for the Model EC130 B4 helicopter, installed. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

that analysis shows a ‘‘dormant failure’’ of 

one of the two contactors, 53Ka or 53Kb, can 

occur following the introduction of MOD 

073254 or MOD 073773. Failure of a 

contactor can prevent switching from ‘‘IDLE’’ 

mode to ‘‘FLIGHT’’ mode during autorotation 

training making it impossible to recover from 

the practice autorotation and compelling the 

pilot to continue the autorotation to the 

ground. This condition, if not corrected, can 

lead to an unintended touchdown to the 

ground at a flight-idle power setting during 

a practice autorotation, damage to the 

helicopter, and injury to the occupants. 

Actions and Compliance 

(e) Before the next practice autorotation or 

on or before 100 hours time-in-service (TIS), 

whichever occurs first, unless accomplished 

previously, and thereafter at intervals not to 

exceed 600 hours TIS: 

(1) Inspect for the proper operation of 

contactors 53Ka and 53Kb by rotating the 

pilot and co-pilot throttle twist grip controls 

between the ‘‘IDLE’’ and ‘‘FLIGHT’’ position in 

accordance with the Accomplishment 

Instructions, paragraph 2.B.2, of Eurocopter 

Alert Service Bulletin (ASB) No. 05.00.61, 

dated November 16, 2009, for the Model 

AS350B3 helicopters or ASB No. 05A009, 

dated November 16, 2009, for the Model 

EC130 B4 helicopters, as appropriate for your 

model helicopter. 

(2) Test the pilot and co-pilot throttle twist 

grip controls for proper functioning. If the 

throttle twist grip controls are not 

functioning properly, repair the controls. 

Differences Between This AD and the MCAI 

AD 

(f) We refer to flight hours as hours TIS. 

Also, we refer to maintenance actions as 

inspections rather than checks. Finally, 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, ATTN: DOT/FAA Southwest Region, 

Ed Cuevas, ASW–112, Aviation Safety 

Engineer, Rotorcraft Directorate, Safety 

Management Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5355, fax (817) 222–5961, has the 

authority to approve AMOCs for this AD, if 

requested, using the procedures found in 14 

CFR 39.19. 

Related Information 

(h) MCAI AD No. 2009–0256, dated 

December 2, 2009, contains related 

information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) The JASC Code is 7697: Engine Control 

System Wiring. 

Material Incorporated by Reference 

(j) You must use Eurocopter Alert Service 

Bulletin ASB No. 05.00.61 or 05A009, both 

dated November 16, 2009, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, Texas 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

(3) You may review copies 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/ 

cfr/ibr-locations.html. 

Issued in Fort Worth, Texas, on September 

29, 2010. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service 

[FR Doc. 2010–25270 Filed 10–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1229; Directorate 

Identifier 2009–NM–106–AD; Amendment 

39–16471; AD 2010–21–11] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A specific batch of nose landing gear (NLG) 

and NLG door selector valves, part number 

(P/N) 601R75146–1 (Kaiser Fluid 

Technologies P/N 750006000), may have had 

their end caps incorrectly lock-wired and/or 

incorrectly torqued during assembly. This 

condition can lead to the end cap backing off, 

with consequent damage to a seal and 

internal leakage within the valve. 

Subsequently, if electrical power is 

transferred or removed from the aircraft 

before the NLG safety pin is installed, any 

pressure, including residual pressure, in the 

No. 3 hydraulic system can result in an 

uncommanded NLG retraction and/or 

uncommanded opening of the NLG doors. 

There have been six cases reported on 

CL[-]600–2B19 aircraft, one of which resulted 

in the collapse of the NLG at the departure 

gate. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 18, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 18, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 


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