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_register/code_of_federal_

regulations/ibr_locations.html. 

(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 wing 

center 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 


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

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 also 

estimate 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, 


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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_register/ 

code_of_federal_regulations/ 

ibr_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, replacing 

the 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 


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