Federal Register / Vol. 75, No. 221 / Wednesday, November 17, 2010 / Rules and Regulations 70101 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on 

November 1, 2010. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–27980 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–2010–0490; Directorate 

Identifier 2010–SW–037–AD; Amendment 

39–16514; AD 2010–23–24] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S–70A and S–70C Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Sikorsky Model S–70A and S–70C 

helicopters. This AD requires an 

ultrasonic test (UT) inspection of the tail 

gearbox output bevel gear (gear) for a 

crack. If you find a crack, replacing the 

gear with an airworthy gear is required 

before further flight. This AD is 

prompted by three gear cracking 

incidents, one of which resulted in the 

tail rotor separating from the helicopter. 

The actions specified by this AD are 

intended to detect a crack in the gear to 

prevent a tail rotor separating, loss of 

tail rotor control, and subsequent loss of 

control of the helicopter. 

DATES: Effective 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 get the service 

information identified in this AD 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. 

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: 

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. 

SUPPLEMENTARY INFORMATION: A 

proposal to amend 14 CFR part 39 to 

include an AD for the specified model 

helicopters was published in the 

Federal Register on May 13, 2010 (75 

FR 26888). That action proposed to 

require a UT inspection of the gear for 

a crack and replacing any cracked gear 

before further flight. The proposal was 

prompted by three gear crack incidents, 

one of which resulted in the tail rotor 

separating from the helicopter. The tail 

gearbox on the helicopter where the tail 

rotor separated from the helicopter 

experienced a fracture of the output 

shaft spline that drives the tail rotor 

blades. An investigation into the cause 

of the cracks is ongoing. The unsafe 

condition described previously, if not 

corrected, could result in a tail rotor 

separating, loss of tail rotor control, and 

subsequent loss of control of the 

helicopter. 

We have reviewed Sikorsky Alert 

Service Bulletin No. 70–06–28A, 

Revision A, dated May 21, 2009 (ASB), 

which refers to procedures for a UT 

inspection of the gear in accordance 

with Special Service Instructions (SSI) 

No. 70–121A or latest revision. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD 

requires a UT inspection of the gear, 

part number 70358–06620, for a crack. 

If a crack is found, this AD requires 

replacing the gear with an airworthy 

gear before further flight. The actions 

are required to be to be done by 

following the SSI described previously. 

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 action as proposed with 

only minor non-substantive changes. 

We estimate that this AD affects 5 

helicopters in the U.S. registry. The 

actions will take about 4 work hours per 

helicopter at an average labor rate of $85 

per work hour. Required parts cost 

about $20,000 for each gear. Based on 

these figures, we estimate the total cost 

impact of this AD on U.S. operators to 

be $101,700, assuming the gear is 

replaced on the entire fleet. 

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: 


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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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