71532 Federal Register / Vol. 75, No. 226 / Wednesday, November 24, 2010 / Rules and Regulations 

On two occurrences on Myste`re-Falcon 50 

aeroplanes in service, it was detected that 

two pipes of the emergency brake system #2 

located near the nose landing gear bearing 

were swapped. 

The swapping of these two pipes implies 

that when the Left Hand (LH) brake pedal is 

depressed, the Right Hand (RH) brake unit is 

activated, and conversely, when the RH brake 

pedal is depressed, the LH brake unit is 

actuated. This constitutes an unsafe 

condition, which may go unnoticed as the 

condition is latent until the emergency brake 

system #2 is used. This condition, if not 

corrected, 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 7 days after the effective date of 

this AD, do a general visual inspection for 

correct installation (as defined in Dassault 

Service Bulletin F50–515, dated October 12, 

2010) of the emergency brake system number 

2, in accordance with the Accomplishment 

Instructions of Dassault Service Bulletin 

F50–515, dated October 12, 2010, except that 

work required by this AD can only be done 

by persons prescribed in 14 CFR 43.3 and 

43.7. 

(h) If the emergency brake system number 

2 is found installed incorrectly during the 

inspection required by paragraph (g) of this 

AD: Before further flight, install the 

emergency brake system number 2 correctly, 

in accordance with the Accomplishment 

Instructions of Dassault Service Bulletin 

F50–515, dated October 12, 2010. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

(1) European Aviation Safety Agency 

(EASA) AD 2010–0208–E, dated October 12, 

2010, has a compliance time of ‘‘before the 

next flight after the effective date of this AD.’’ 

This AD requires that the actions be done 

within 7 days after the effective date of this 

AD. 

(2) EASA AD 2010–0208–E, dated October 

12, 2010, allows the flightcrew to inspect the 

emergency brake system number 2 specified 

in accordance with Dassault Service Bulletin 

F50–515, dated October 12, 2010. However, 

this AD requires the inspection to be 

performed by certificated maintenance 

personnel. 

(3) EASA AD 2010–0208–E, dated October 

12, 2010, requires painting the pipes end of 

the emergency brake system number 2 and 

related unions within 7 months after the 

effective date of that AD. This AD does not 

require painting the pipes end of the 

emergency brake system number 2 and 

related unions. We might consider additional 

rulemaking to require this action in the 

future. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI EASA AD 2010–0208–E, 

dated October 12, 2010; and Dassault Service 

Bulletin F50–515, dated October 12, 2010; for 

related information. 

Material Incorporated by Reference 

(k) You must use Dassault Service Bulletin 

F50–515, dated October 12, 2010, 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 Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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. 

Issued in Renton, Washington on 

November 15, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–29458 Filed 11–23–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0711; Directorate 

Identifier 2008–SW–25–AD; Amendment 39– 

16521; AD 2010–24–03] 

RIN 2120–AA64 

Airworthiness Directives; Robinson 

Helicopter Company (Robinson) Model 

R22, R22 Alpha, R22 Beta, and R22 

Mariner Helicopters, and Model R44, 

and R44 II Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Robinson Model R22, R22 Alpha, R22 

Beta, and R22 Mariner helicopters, and 

Model R44 and R44 II helicopters. This 

AD requires visually inspecting each tail 

rotor (T/R) control pedal bearing block 

support (support) for a crack, measuring 

the thickness of each support, installing 

support safety tabs on certain supports, 

and replacing supports of a certain 

thickness during the next 2,200 hour 

overhaul. This amendment is prompted 

by two reports of Model R22 helicopters 

experiencing broken supports during 

flight, which resulted in the T/R control 

pedals becoming jammed. The actions 

specified by this AD are intended to 

prevent the supports from breaking, 

which can bind the T/R control pedals, 

resulting in a reduction of yaw control 

and subsequent loss of control of the 

helicopter. 

DATES: Effective December 29, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

29, 2010. 

ADDRESSES: You may get the service 

information identified in this AD from 

Robinson Helicopter Company, 2901 

Airport Drive, Torrance, California 

90505, telephone (310) 539–0508, fax 

(310) 539–5198. 

Examining the Docket: You may 

examine the docket that contains this 

AD, any comments, and other 

information on the Internet at http://


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Federal Register / Vol. 75, No. 226 / Wednesday, November 24, 2010 / Rules and Regulations 71533 

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: Eric 

D. Schrieber, Aviation Safety Engineer, 

telephone (562) 627–5348, fax (562) 

627–5210, regarding Robinson Model 

R22 helicopters, or Fred Guerin, 

Aviation Safety Engineer, telephone 

(562) 627–5232, fax (562) 627–5210, 

regarding Robinson Model R44 

helicopters, at the FAA, Los Angeles 

Aircraft Certification Office, Airframe 

Branch, 3960 Paramount Blvd., 

Lakewood, California 90712. 

SUPPLEMENTARY INFORMATION: We issued 

an NPRM to amend 14 CFR part 39 to 

include an AD that would apply to 

certain serial-numbered helicopters on 

July 06, 2010. That NPRM was 

published in the Federal Register on 

July 15, 2010 (75 FR 41104). That action 

proposed to require for Robinson Model 

R22, R22 Alpha, R22 Beta, and R22 

Mariner helicopters, serial numbers 

(S/N) 0002 through 3325, that have 

more than 2,200 hours total time-inservice (TIS); and for Model R44 and 

R44 II helicopters, S/N 0001 through 

1200, that have more than 2,200 hours 

total TIS, the following within 100 

hours TIS: 

• Visually inspecting both A359–1 

and A359–2 supports for a crack and 

replacing any cracked support before 

further flight; 

• If not cracked, measuring the 

thickness of both supports and if less 

than 0.050-inch thick, installing support 

safety tabs, and at the next 2,200 hour 

TIS overhaul, replacing any support that 

is less than 0.050-inch thick with a 

support that is at least 0.050-inch thick. 

We have reviewed Robinson Service 

Bulletins SB–63 and SB–97, both dated 

February 22, 2008, which describe 

procedures for inspecting both supports 

for a crack, and if no crack is found, 

measuring each support and installing 

safety tabs on supports that are less than 

0.050-inch thick, and at the next 2,200 

hour TIS overhaul, replacing certain 

supports. 

We provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the proposal or on the determination of 

the cost to the public. Therefore, we are 

adopting the actions as proposed. 

This AD affects 4,524 helicopters of 

U.S. registry. It will take approximately 

0.5 work hour to inspect and measure 

the supports. We estimate that 2,050 

helicopters will require an additional 1 

work hour to install both safety tabs; 6 

work hours to replace both supports if 

cracked or broken or before overhaul, or 

3 work hours to replace both supports 

as part of a 2,200 hours TIS overhaul, 

at an average labor rate of $85 per work 

hour. Required parts will cost 

approximately $20 per support if 

replacement is required. Based on these 

figures, we estimate that the total cost 

impact of this AD on U.S. operators is 

$1,101,830, assuming 1,538 

(approximately 75% of the 2,050 

helicopters) have both supports 

replaced during overhaul, and 512 

helicopters (approximately 25% of the 

2,050 helicopters) have both supports 

replaced before the next 2,200 hours TIS 

overhaul. 

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 AD. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under 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. The FAA amends § 39.13 by adding 

the following new AD: 

2010–24–03 Robinson Helicopter Company: 

Amendment 39–16521; Docket No. 

FAA–2010–0711; Directorate Identifier 

2008–SW–25–AD. 

Applicability: Model R22, R22 Alpha, R22 

Beta, and R22 Mariner helicopters, serial 

numbers (S/N) 0002 through 3325, that have 

more than 2,200 hours total time-in-service 

(TIS); and Model R44, and R44 II helicopters, 

S/N 0001 through 1200, that have more than 

2,200 hours total TIS, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent the tail rotor (T/R) control 

pedal bearing block support (support) from 

breaking, which can bind the T/R control 

pedals, resulting in a reduction of yaw 

control and subsequent loss of control of the 

helicopter, accomplish the following: 

(a) Within 100 hours TIS, visually inspect 

each A359–1 (left) and A359–2 (right) pedal 

support for a crack by referring to the figure 

in Robinson Helicopter Company (Robinson) 

Service Bulletin SB–97, dated February 22, 

2008 (SB–97) for all Model R22 helicopters, 

and Robinson Service Bulletin SB–63, dated 

February 22, 2008 (SB–63) for all Model R44 

helicopters. 

(1) If you find a crack in a support, before 

further flight, replace the cracked support 

with an airworthy support that is at least 

0.050-inch thick. 

(2) For each uncracked support, measure 

the thickness of the support. If the support 

is less than 0.050-inch thick, before further 

flight, install a safety tab on the support in 

accordance with steps 4 and 5 of the 

Compliance Procedures section in SB–97 or 

SB–63, as appropriate for your model 

helicopter. 

(b) At the next 2,200 hours TIS overhaul, 

replace any support that is less than 0.050- 

inch thick, with an airworthy support that is 

at least 0.050-inch thick. 

(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, Los Angeles 

Aircraft Certification Office, FAA, ATTN: 

Eric D. Schrieber, Aviation Safety Engineer, 


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71534 Federal Register / Vol. 75, No. 226 / Wednesday, November 24, 2010 / Rules and Regulations 

3960 Paramount Blvd., Lakewood, California 

90712, telephone (562) 627–5348, fax (562) 

627–5210 (regarding Model R22 helicopters); 

or ATTN: Fred Guerin, Aviation Safety 

Engineer, telephone (562) 627–5232, fax 

(562) 627–5210 (regarding Model R44 

helicopters) for information about previously 

approved alternative methods of compliance. 

(d) The Joint Aircraft System/Component 

(JASC) Code is 6720: Tail Rotor Control 

System. 

(e) The inspection and modification shall 

be done in accordance with the specified 

portions of Robinson Helicopter Company 

Service Bulletin SB–97 or SB–63, both dated 

February 22, 2008. 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 Robinson Helicopter 

Company, 2901 Airport Drive, Torrance, 

California 90505, telephone (310) 539–0508, 

fax (310) 539–5198. 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 

December 29, 2010. 

Issued in Fort Worth, Texas, on November 

10, 2010. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–29203 Filed 11–23–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0764; Directorate 

Identifier 2009–NM–260–AD; Amendment 

39–16519; AD 2010–24–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–900ER Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

doing a one-time general visual 

inspection for a keyway in two fuel tank 

access door cutouts, and related 

investigative and corrective actions if 

necessary. This AD was prompted by 

reports of cracks emanating from the 

keyway of the fuel tank access hole. We 

are issuing this AD to detect and correct 

such cracking, which could result in the 

loss of the lower wing skin load path 

and consequent structural failure of the 

wing. 

DATES: This AD is effective December 

29, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 29, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590; 

e-mail: nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

August 10, 2010 (75 FR 48281). That 

NPRM proposed to require a general 

visual inspection for a keyway in the 

fuel tank access door cutout on the left 

and right wings, and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

The Boeing Company supports the 

NPRM. Continental Airlines submitted 

information to make a comment, but no 

specific comment on the NPRM or 

request to change it. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 30 

airplanes of U.S. registry. We estimate 

that it will take 3 work-hours per 

product to comply with this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of the AD to the U.S. operators to 

be $7,650, or $255 per product. 

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. 

Regulatory Findings 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 


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