Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12665 

TABLE 1—INSTALLED ON AIRPLANES BY MANUFACTURER—Continued 

Manufacturer Model 

Raytheon Corporate Jets (formerly British Aerospace and Hawker 

Beechcraft Corporation).

DH.125 Series 1A, 3A, and 3A/RA, HS.125 Series F3B and F3B/RA, 

BH.125 and DH.125 Series 400A, HS.125 Series 403B, F400B, and 

F403B, HS.125 Series 600A, BH.125 Series 600A, HS.125 Series 

F600B, 700A, and 700B, BAe.125 Series 800 and 1000, and Hawker 

800 and 850XP series. 

Unsafe Condition 

(d) This AD results from a report of cracks 

found during a fluorescent penetrant 

inspection (FPI) of the disc bore. We are 

issuing this AD to prevent an uncontained 

failure of a second stage LPCR disc and/or a 

third stage LPCR disc due to cracks in the 

bore, which could result in damage to the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Removing LPCR Discs From Service 

(f) For engines with any of the serial 

number (S/N) LPCR discs listed in Table 5 of 

Honeywell International Inc. Alert Service 

Bulletins (ASBs) TFE731–72–A3748, dated 

August 21, 2008, and/or Table 5 of TFE731– 

72–A3749, dated August 21, 2008, remove 

those LPCR discs from service within 100 

cycles-in-service (CIS) after the effective date 

of this AD. 

(g) For engines with any of the S/N LPCR 

discs listed in Table 6 of Honeywell 

International Inc. ASBs TFE731–72–A3748, 

dated August 21, 2008, and/or Table 6 of 

TFE731–72–A3749, dated August 21, 2008, 

do the earlier of the following: 

(1) Remove the LPCR disc from service 

within 2,000 CIS after the effective date of 

this AD, or 

(2) Remove the LPCR disc from service the 

next time the intermediate case is removed 

from the low-pressure compressor case. 

Installation Prohibition 

(h) After the effective date of this AD, do 

not install any of the S/Ns of LPCR discs 

listed in Table 5 of Honeywell International 

Inc. ASBs TFE731–72–A3748, dated August 

21, 2008, and the discs listed in Table 5 of 

TFE731–72–A3749, dated August 21, 2008, 

into any engine. Also, do not install any of 

the S/Ns of LPCR discs listed in Table 6 of 

Honeywell International Inc. ASBs TFE731– 

72–A3748, dated August 21, 2008, and the 

discs listed in Table 6 of TFE731–72–A3749, 

dated August 21, 2008, into any engine. 

Alternative Methods of Compliance 

(i) The Manager, Los Angeles Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) Contact Joseph Costa, Aerospace 

Engineer, Los Angeles Aircraft Certification 

Office, FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: joseph.costa@faa.gov; 

telephone: (562) 627–5246; fax: (562) 627– 

5210, for more information about this AD. 

Material Incorporated by Reference 

(k) You must use the service information 

specified in the following Table 2 to identify 

the affected discs requiring removal. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in the following Table 2 in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Honeywell Engines and Systems 

Technical Publications and Distribution, M/ 

S 2101–201, P.O. Box 52170, Phoenix, AZ 

85072–2170, telephone: Global Customer 

Care toll free (800) 601–3099; International 

callers (602) 365–3099, for a copy of this 

service information. You may review copies 

at the FAA, New England Region, 12 New 

England Executive Park, Burlington, MA; 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/cfr/ibrlocations.html. 

TABLE 2—INCORPORATION BY REFERENCE

Honeywell International Inc. Alert Service Bulletin No. Page Revision Date 

TFE731–72–A3748; Total Pages: 18 ............................... All ........................................ Original ................................ August 21, 2008. 

TFE731–72–A3749; Total Pages: 14 ............................... All ........................................ Original ................................ August 21, 2008. 

Issued in Burlington, Massachusetts, on 

March 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–5507 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0242; Directorate 

Identifier 2009–SW–27–AD; Amendment 39– 

16232; AD 2010–06–08] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–76C 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Sikorsky Aircraft Corporation 

(Sikorsky) Model S–76C helicopters. 

This action requires inspecting the 

emergency flotation system squib 

connector (flotation system connector) 

to determine if a metallic foil shunt is 

installed. This amendment is prompted 

by a discovery that a metallic foil shunt 

meant to prevent inadvertent activation 

of a flotation system during installation 

was still installed in the left-hand 

flotation system connector of a Model 

S–76C helicopter. The actions specified 

in this AD are intended to determine if 

a metallic foil shunt is installed in the 

flotation system, which could prevent 

the flotation system from deploying and 

could prevent the helicopter from 

staying afloat long enough to enable 


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12666 Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 

emergency evacuation after a water 

landing. 

DATES: Effective April 1, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of April 1, 

2010. 

Comments for inclusion in the Rules 

Docket must be received on or before 

May 17, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, 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 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 the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Terry Fahr, Aviation Safety Engineer, 

Boston Aircraft Certification Office, 12 

New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7155, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for the 

specified Sikorsky Model S–76C 

helicopters. This action requires a onetime inspection of the flotation system 

connector to determine if a metallic foil 

shunt is installed, and if one is found, 

removing it. This amendment is 

prompted by a discovery during an 

inspection that a metallic foil shunt was 

still installed in the left-hand flotation 

system squib connector of a Model S– 

76C helicopter. The metallic foil shunt 

is intended to prevent inadvertent 

activation of the flotation system during 

installation. The actions specified in 

this AD are intended to determine if a 

metallic foil shunt is installed in the 

flotation system, which could prevent 

the flotation system from deploying and 

could prevent the helicopter from 

staying afloat long enough to enable 

emergency evacuation after a water 

landing. 

We have reviewed Sikorsky Alert 

Service Bulletin No. 76–32–30, dated 

April 8, 2009, which describes 

procedures for a one-time inspection of 

a flotation system connector, installed 

by Keystone Helicopter Corporation on 

Sikorsky Model S–76C helicopters, 

serial numbers 760501 and 760506 

through 760761, to determine if a 

metallic foil shunt is installed, and if so, 

removing it. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to require inspecting the 

flotation system connector to determine 

if a metallic foil shunt is installed, 

which could prevent the flotation 

system from deploying and could 

prevent the helicopter from staying 

afloat long enough to enable emergency 

evacuation after a water landing. This 

AD requires, before the next flight over 

water, or on or before 30 days after the 

effective date of this AD, whichever 

occurs first, accomplishing the actions 

by following specified portions of the 

alert service bulletin described 

previously. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition 

could adversely affect the ability of the 

helicopter to stay afloat after an 

emergency water landing. Therefore, 

inspecting the flotation system 

connector and removing any metallic 

foil shunt that is found is required 

before the next flight over water, or on 

or before 30 days after the effective date 

of this AD, whichever occurs first, and 

this AD must be issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

76 helicopters, and inspection and 

removal, if necessary, will take 

approximately 1 work hour to 

accomplish at an average labor rate of 

$85 per work hour. Based on these 

figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $6,460. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0242; 

Directorate Identifier 2009–SW–27–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 51 / Wednesday, March 17, 2010 / Rules and Regulations 12667 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to 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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2010–06–08 Sikorsky Aircraft Corporation: 

Amendment 39–16232. Docket No. 

FAA–2010–0242; Directorate Identifier 

2009–SW–27–AD. 

Applicability: Sikorsky Aircraft 

Corporation Model S–76C helicopters, serial 

numbers 760501 and 760506 through 760761, 

with Option Code 88051 Flotation System 

installed by Keystone Helicopter 

Corporation, certificated in any category. 

Compliance: Before the next flight over 

water, or within 30 days, whichever occurs 

first, unless accomplished previously. 

To determine if a metallic foil shunt is 

installed in the flotation system, which could 

prevent the flotation system from deploying 

and could prevent the helicopter from 

staying afloat long enough to enable 

emergency evacuation after a water landing, 

accomplish the following: 

(a) Inspect the flotation system connector 

and if a metallic foil shunt is found, remove 

it in accordance with the Accomplishment 

Instructions, paragraphs 3.A.(1) through 

3.A.(9), in Sikorsky Alert Service Bulletin 

No. 76–32–30, dated April 8, 2009. 

(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: Terry Fahr, 

12 New England Executive Park, Burlington, 

MA 01803, telephone (781) 238–7155, fax 

(781) 238–7170. 

(c) The inspection shall be done in 

accordance with the specified portions of 

Sikorsky Alert Service Bulletin No. 76–32– 

30, dated April 8, 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, email 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. 

Joint Aircraft System/Component (JASC) 

Code 

(d) JASC Code 3212: Emergency Flotation 

Systems. 

(e) This amendment becomes effective on 

April 1, 2010. 

Issued in Fort Worth, Texas, on February 

3, 2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–5294 Filed 3–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0226; Directorate 

Identifier 2010–NM–034–AD; Amendment 

39–16238; AD 2010–06–13] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Model 45 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 45 airplanes. This AD requires a 

general visual inspection for cracked 

and missing ballscrew assembly sleeves 

of the flap actuator, repetitive nondestructive liquid penetrant inspections 

of each sleeve or flap actuator for cracks, 

and replacement or modification of the 

flap actuator if necessary. This AD 

results from reports of cracked and 

missing ballscrew assembly sleeves of 

the flap actuators. We are issuing this 

AD to detect and correct cracked and 

missing sleeves, which could cause loss 

of the load-carrying ball bearings on 

both actuators on one flap, resulting in 

flap asymmetry and loss of control of 

the airplane. 

DATES: This AD is effective April 1, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 1, 2010. 

We must receive comments on this 

AD by May 3, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Learjet, Inc., One 

Learjet Way, Wichita, Kansas 67209– 

2942; telephone 316–946–2000; fax 

316–946–2220; e-mail 

ac.ict@aero.bombardier.com; Internet 

http://www.bombardier.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 street address for 

the Docket Office (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

William Griffith, Aerospace Engineer, 

Airframe Branch, ACE–118W, FAA, 

Wichita Aircraft Certification Office, 

1801 Airport Road, Room 100, MidVerDate Nov<24>2008 14:47 Mar 16, 2010 Jkt 220001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\17MRR1.SGM 17MRR1

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