### 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://


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

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 havemore 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,


### 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),