### 70102 Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 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. FAA amends § 39.13 by adding the following new AD:
2010–23–24 Sikorsky Aircraft Corp.: Amendment 39–16514; Docket No. FAA–2010–0490; Directorate Identifier 2010–SW–037–AD. Applicability: Model S–70A and S–70C helicopters with a tail gearbox output bevel gear (gear), part number 70358–06620, certificated in any category.

Compliance: Required as indicated. To prevent a tail rotor separating, loss of tail rotor control, and subsequent loss of control of the helicopter, do the following:

(a) Within 500 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 500 hours TIS, remove the tail rotor servo control and pitch beam shaft, and using a Level II Ultrasonic Testing Technician or equivalent, ultransonic inspect the gear for a crack. Ultrasonic inspect the gear by following paragraphs A.(5)a. through A(5)n. of Special Service Instructions No. 70–121A, Revision A, dated May 21, 2009. If you find a crack, before further flight, replace the gear with an airworthy gear.

(b) 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, Boston Aircraft Certification Office, FAA, Attn: 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, for information about previously approved alternative methods of compliance.

(c) The Joint Aircraft System/Component (JASC) Code is 6520: Tail rotor gearbox.

(d) The inspections shall be done in accordance with the specified portions of Sikorsky Special Service Instructions No. 70– 121A, Revision A, dated May 21, 2009. 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 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. 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

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(e) This amendment becomes effective on December 22, 2010. Issued in Fort Worth, Texas, on November 1, 2010. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010–28458 Filed 11–16–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0376; Directorate Identifier 2009–NM–267–AD; Amendment**  **39–16504; AD 2010–23–15]**

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Model 777–200, –200LR,**  **–300, and –300ER Series Airplanes**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Model 777–200, –200LR, –300, and –300ER series airplanes. This AD requires removing and repairing the sealant at the four lower corners of the wing center section and the four lower t-chord segment gaps on each side of the wing center section. This AD results from reports of fuel leakage from the center tank. We are issuing this AD to detect and correct improperly applied sealant, which could result in the disbonding and displacing of sealant, and consequent fuel leaks. On the ground, uncontained fuel leakage could result in pooling, and pooling combined with an ignition source could result in a fire.

**DATES :**  This AD is effective December 22, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 22, 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. 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 (telephone 800–647–5527) is the 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 :**  Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6501; fax (425) 917–6590.

**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 certain Model 777–200, –200LR, –300, and –300ER series airplanes. That NPRM was published in the Federal Register on April 8, 2010 (75 FR 17889). That NPRM proposed to require removing and repairing the sealant at the four lower corners of the wingcenter section and the four lower tchord segment gaps on each side of the wing center section.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comments received from the two commenters. Support for the NPRM

Continental Airlines (CAL) stated that it concurs with intent of the NRPM to ensure a high level of safety for the Model 777 airplane fleet. Request to Include Revised Inspection Criteria in Revised Service Information

Boeing requested that we revise the NPRM to refer to Revision 2 of Boeing Special Attention Service Bulletin 777– 57–0063. Boeing stated that this revision includes an alternative inspection, and, depending on the inspection findings, it may be unnecessary to remove and replace the sealant. Furthermore, Boeing requested that we provide credit for actions accomplished in accordance with Boeing Special Attention Service Bulletin 777–57–0063, Revision 1, dated May 14, 2009.

CAL also requested a provision to allow the inspection of the sealant condition in the affected areas before the sealant repair that is specified by Boeing Special Attention Service Bulletin 777–57–0063, Revision 1, dated


### 70103 Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations

May 14, 2009. CAL stated it believes that the additional inspection of the sealant is required to prevent unnecessary corrective actions on the affected airplanes that do not have the fuel leakage problems. CAL based its recommendation on its two affected airplanes that have not had any abnormal fuel leakage. CAL stated that Boeing has agreed that such a provision is acceptable to ensure an adequate level of safety. CAL asked that we revise the proposed AD to include the additional inspection criteria.

We infer that Boeing is asking us to revise the NPRM to add an additional inspection for sealant that Boeing plans to include in the next revision of the service information. We agree that an alternative inspection may prevent unnecessarily removing the sealant. However, we do not agree to delay this AD action until after Boeing revises the service bulletin, since sufficient methods specified in Boeing Special Attention Service Bulletin 777–57– 0063, Revision 1, dated May 14, 2009, address the unsafe condition within the compliance time. However, after reviewing the next revision of this service bulletin, we might consider approving it as an alternative method of compliance (AMOC), if requested. In addition, any operator may request approval of an AMOC under the provisions of paragraph (i) of the final rule if data are submitted to substantiate that such a request would provide an acceptable level of safety. We have not changed this final rule in regard to this issue.

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 8 airplanes of U.S. registry. We alsoestimate that it will take about 10 workhours 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 this AD to the U.S. operators to be $6,800, or $850 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), 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.

You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. 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 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:
2010–23–15 The Boeing Company: Amendment 39–16504. Docket No. FAA–2010–0376; Directorate Identifier 2009–NM–267–AD. Effective Date (a) This airworthiness directive (AD) is effective December 22, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to The Boeing Company Model 777–200, –200LR, –300, and –300ER series airplanes, certificated in any category; as identified in Boeing Special Attention Service Bulletin 777–57–0063, Revision 1, dated May 14, 2009.
Subject

(d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

(e) This AD results from reports of fuel leakage from the center tank. We are issuing this AD to detect and correct improperly applied sealant, which could result in the disbonding and displacing of sealant, and consequent fuel leaks. On the ground, uncontained fuel leakage could result in pooling, and pooling combined with an ignition source could result in a fire.
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.
Removal and Repair of Sealant

(g) Within 36 months or 6,000 flight cycles after the effective date of this AD, whichever occurs first: Remove and repair the sealant at the four lower corners of the wing center section and the four lower t-chord segment gaps on each side of the wing center section, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–57–0063, Revision 1, dated May 14, 2009.
Credit for Actions Accomplished According to Previous Issue of Service Bulletin

(h) Actions accomplished before the effective date of this AD in accordance with Boeing Special Attention Service Bulletin 777–57–0063, dated November 20, 2008, are considered acceptable for compliance with the corresponding action specified in this AD. Alternative Methods of Compliance (AMOCs)

(i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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: Kevin Nguyen, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6501; fax (425) 917–6590. Information may be e-mailed to: 9- ANM-Seattle-ACO-AMOC-Requests@faa.gov.

(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies,


### 70104 Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations

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.
Material Incorporated by Reference

(j) You must use Boeing Special Attention Service Bulletin 777–57–0063, Revision 1, dated May 14, 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 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.

(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

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_locations.html. Issued in Renton, Washington, on October 22, 2010. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–28176 Filed 11–16–10; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0670; Directorate Identifier 2009–SW–42–AD; Amendment 39–**  **16513; AD 2010–23–23]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France (ECF) Model SA330F, G, and J;**  **and AS332C, L, L1, and L2 Helicopters**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  This amendment adopts a new airworthiness directive (AD) for the specified ECF model helicopters. This AD results from 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 EASA received a report of a rear hinged door on a Model AS332L1 helicopter opening in flight without loss of the door. Examinations revealed incorrect positioning of a door catch that resulted in incorrect locking and uncontrolled opening of the door. This condition, if not detected and corrected, can lead to the loss of the hinged door in flight, damage to the main or tail rotor blades, and subsequent loss of control of the helicopter.

**DATES :**  This AD becomes effective on December 22, 2010.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of December 22, 2010.

**ADDRESSES :**  You may examine the AD docket on the Internet at http:// regulations.gov or in person at the Docket Operations office, U.S. Department of Transportation, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 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 the AD Docket: The AD docket contains the Notice of proposed rulemaking (NPRM), the economic evaluation, any comments received, and other information. The street address and operating hours for the Docket Operations office (telephone (800) 647– 5527) are in the **ADDRESSES** section of this AD. Comments will be available in the AD docket shortly after they are received.

**FOR FURTHER INFORMATION CONTACT :**  DOT/FAA Southwest Region, Gary Roach, ASW–111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd, Fort Worth, Texas 76137, telephone (817) 222–5130, fax (817) 222–5961.

**SUPPLEMENTARY INFORMATION :** 

Discussion

We issued an NPRM to amend 14 CFR part 39 to include an AD that would apply to the specified ECF model helicopters on June 11, 2010. That NPRM was published in the Federal Register on July 7, 2010 (75 FR 38956). That NPRM proposed to require:

• Within the next 220 hours time-inservice (TIS) or 6 months, whichever occurs first, inspecting the positioning of each lower and upper door catch; and

• If any door catch is improperly installed, before further flight, replacingthe affected catch, adjusting the microswitches, and doing a functional test of the hinged door indicating system.

Comments

By publishing the NPRM, we gave the public an opportunity to participate in developing this AD. However, we received no comment 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.

Related Service Information

ECF has issued Alert Service Bulletin (ASB) No. 52.13 for the SA330F, G, and J helicopters, and 52.00.38 for the AS332C, C1, L, L1, and L2 helicopters, both ASBs dated December 1, 2008. The ASBs specify inspecting the upper and lower catches of the hinged doors to ensure the catches are correctly positioned. The actions described in the MCAI AD are intended to correct the unsafe condition identified in the service information. The AS332C1 is not type certificated in the United States.

FAA’s Evaluation and Unsafe Condition Determination

These helicopters 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 Agent, has notified us of the unsafe condition described in the MCAI 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 these same type designs.

Differences Between This AD and the MCAI AD

We refer to flight hours as hours TIS. This AD does not apply to the Model AS332C1 because that model is not FAA type certificated. Costs of Compliance

We estimate that this AD will affect about 10 helicopters of U.S. registry. We also estimate that it will take about 2 work-hours per helicopter to inspect each door catch for correct position of the door hinges, replace an affected