Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 68055 

(3) Fokker Report, SE–623, Fokker 70/100 

Airworthiness Limitation Items and Safe Life 

Items, Issue 8, dated December 20, 2010. 

(4) Goodrich Service Bulletin 41000–32– 

29, dated November 10, 2010. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 20, 2012. 

(i) Fokker Service Bulletin SBF100–32– 

161, dated April 7, 2011. 

(ii) Fokker Report, SE–623, Fokker 70/100 

Airworthiness Limitation Items and Safe Life 

Items, Issue 8, dated December 20, 2010. 

(iii) Goodrich Service Bulletin 41000–32– 

29, dated November 10, 2010. 

(4) The following service information was 

approved for IBR on March 22, 2011 (76 FR 

8618, February 15, 2011). 

(i) Fokker Service Bulletin SBF100–32– 

158, dated October 2, 2009. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. For 

Goodrich Corporation service information 

identified in this AD, contact Goodrich, 1400 

South Service Road, West Oakville, L6L 5Y7, 

Ontario, Canada, telephone +1–905–827– 

7777; fax +1–905–825–1583; Internet http:// 

www.goodrich.com/TechPubs. 

(6) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(7) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26781 Filed 11–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0530; Directorate 

Identifier 2011–SW–075–AD; Amendment 

39–17247; AD 2012–22–11] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron (BHT) Model 412, 

412EP, and 412CF helicopters. This AD 

requires a repetitive inspection of the 

collective lever for a crack, and if there 

is a crack, before further flight, replacing 

the collective lever with an airworthy 

collective lever. This AD was prompted 

by a reported failure of a collective 

lever. The actions are intended to detect 

a crack in the collective lever, which 

could lead to failure of the collective 

lever and subsequent loss of control of 

the helicopter. 

DATES: This AD is effective December 

20, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 20, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, Texas 76101; telephone 

(817) 280–3391; fax (817) 280–6466; or 

at http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket: You may 

examine the AD docket 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 AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Martin Crane, Aerospace Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5170; email 

martin.r.crane@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 22, 2012, at 77 FR 30232, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

certain serial-numbered BHT Model 

412, 412EP, and 412CF helicopters with 

a collective lever, part number (P/N) 

412–010–408–101. That NPRM 

proposed to require within 25 hours 

time-in-service (TIS) or 30 days, 

whichever occurs first, and thereafter at 

intervals not to exceed 100 hours TIS, 

cleaning the collective lever and 

inspecting it for cracks with a 10X or 

higher power magnifying glass. If there 

is a crack in the collective lever paint 

finish, the NPRM proposed to require 

removing the collective lever from the 

swashplate and performing a fluorescent 

penetrant inspection, and if there is a 

crack in the collective lever, before 

further flight, replacing the collective 

lever with an airworthy collective lever. 

The proposed requirements were 

intended to detect a crack in the 

collective lever, which could lead to 

failure of the collective lever and 

subsequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 30232, May 22, 2012). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

We reviewed Bell Helicopter Alert 

Service Bulletin (ASB) No. 412–11–148 

and ASB No. 412CF–11–47, both 

Revision A, and both dated December 

12, 2011, which describe procedures for 

repetitively inspecting the collective 

lever with a magnifying glass and a 

strong light source and, if necessary, a 

fluorescent penetrant inspection. If 

there is a crack, the ASBs require 

replacing the collective lever. 


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68056 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 

Differences Between This AD and the 

Service Information 

The BHT ASBs require compliance 

within 100 hours of flight time for the 

initial inspection; this AD requires 

compliance within 25 hours TIS or 30 

days, whichever occurs first. If there is 

a crack, the BHT ASBs require reporting 

the defect to Bell Product Support 

Engineering; this AD does not. The BHT 

ASBs allow a portion of the collective 

lever to be inspected by a mirror and 

light only without a magnifying glass; 

this AD requires using a 10X or higher 

power magnifying glass for the entire 

inspection. 

Costs of Compliance 

We estimate that this AD will affect 

83 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. Inspecting the collective lever 

requires one work-hour at an average 

labor rate of $85 per work-hour, for a 

cost per helicopter of $85 and a total 

cost to the U.S. operator fleet of $7,055 

per inspection cycle. Replacing a 

cracked collective lever requires 10 

work-hours at an average labor rate of 

$85 per work-hour and required parts 

will cost $12,883, for a total cost of 

$13,733 per helicopter. 

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); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; and 

(4) 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 and placed it 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 airworthiness 

directive (AD): 

2012–22–11 Bell Helicopter Textron: 

Amendment 39–17247; Docket No. 

FAA–2012–0530; Directorate Identifier 

2011–SW–075–AD. 

(a) Applicability 

This AD applies to Model 412 and 412EP 

helicopters, serial numbers (S/N) 33001 

through 33213, 34001 through 34036, and 

36001 and higher; and Model 412CF 

helicopters, S/N 46400 and higher; with a 

collective lever part number (P/N) 412–010– 

408–101 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

cracked collective lever, which could result 

in failure of the collective lever and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective December 20, 

2012. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 25 hours time-in-service (TIS) or 30 

days, whichever occurs first, and thereafter at 

intervals not to exceed 100 hours TIS: 

(1) Using cleaning compound (C–318) or 

equivalent, thoroughly clean the collective 

lever. 

(2) Using a 10X or higher power 

magnifying glass, inspect the collective lever 

in the areas shown in Figure 1 of Bell 

Helicopter Textron Alert Service Bulletin 

(ASB) 412–11–148, Revision A, dated 

December 12, 2011 or Bell Helicopter 

Textron ASB 412CF–11–47, Revision A, 

dated December 12, 2011, as appropriate for 

your model helicopter. 

(3) If there is a crack in the paint, remove 

the collective lever from the swashplate 

assembly. 

(i) Remove paint and primer from the area 

around the crack. 

(ii) Fluorescent penetrant inspect the area 

of the crack. 

(4) If there is a crack in the collective lever, 

before further flight, replace the collective 

lever with an airworthy collective lever. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin Crane, 

Aerospace Engineer, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5170, email 

martin.r.crane@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6230, Main Rotor. 

(h) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bell Helicopter Textron Alert Service 

Bulletin No. 412–11–148, Revision A, dated 

December 12, 2011. 

(ii) Bell Helicopter Textron Alert Service 

Bulletin No. 412CF–11–47, Revision A, dated 

December 12, 2011. 

(3) For Bell Helicopter service information 

identified in this AD, contact Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, 

Texas 76101, telephone (817) 280–3391, fax 

(817) 280–6466, or at http:// 

www.bellcustomer.com/files/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations 68057 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on October 26, 

2012. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27059 Filed 11–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0340; Directorate 

Identifier 2011–SW–073–AD; Amendment 

39–17250; AD 2012–22–13] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Sikorsky Aircraft Corporation (Sikorsky) 

Model S–76C helicopters. This AD 

requires installing an improved throttle 

stop and a wider trigger on the engine 

control levers (ECL). This AD was 

prompted by a bird-strike to the 

windshield that resulted in unintended 

movement of the engine control levers 

from the forward position and towards 

the flight-idle position, which reduced 

power on both engines. These actions 

are intended to prevent unintended 

movement of the ECLs, resulting in 

main rotor speed decay and subsequent 

loss of control of the aircraft. 

DATES: This AD is effective December 

20, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of December 20, 2012. 

ADDRESSES: For service information 

identified in this AD, contact 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. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining The AD Docket: You may 

examine the AD docket 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 AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Kirk 

Gustafson, Aerospace Engineer, FAA, 

Boston Aircraft Certification Office, 

Engine and Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; telephone (781) 

238–7190; email kirk.gustafson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 29, 2012, at 77 FR 18969, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 to include an AD that would apply 

to Sikorsky Model S–76C helicopters 

with serial numbers 760506 and 760607 

through 760812. That NPRM proposed 

to require within 6 months after the 

effective date of the AD, installing an 

improved throttle stop and a wider 

trigger on each ECL as specified in 

Sikorsky Alert Service Bulletin (ASB) 

No. 76–76–6A, Revision A, dated May 

18, 2011. 

The proposed requirements were 

intended to prevent unintended in-flight 

movement of the ECLs from the normal 

‘‘FLY’’ position towards the ‘‘IDLE’’ 

position, which significantly reduces 

engine power, resulting in an 

unrecoverable loss of main rotor speed 

and subsequent loss of control of the 

helicopter. 

Comments 

Two commenters, one anonymous 

and one from the National 

Transportation Safety Board, 

commented that they support the NPRM 

(77 FR 18969, March 29, 2012). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design and that air safety and 

the public interest require adopting the 

AD requirements as proposed. 

Related Service Information 

We reviewed ASB 76–76–6A, which 

describes procedures for partially 

disassembling the engine control 

quadrant assembly, removing the 

existing throttle stop, and installing a 

new airworthy throttle stop. The ASB 

also describes procedures to remove the 

existing trigger assembly from each ECL 

and install a new airworthy wide trigger 

assembly. 

Costs of Compliance 

We estimate that this AD will affect 

52 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. To replace the engine control 

lever stop and trigger assemblies will 

require 2 work-hours at an average labor 

cost of $85 per hour. Required parts will 

cost about $939. Based upon these costs, 

we estimate a total cost of $1,109 per 

helicopter and a total cost of $57,668 for 

the entire U.S. operator fleet. 

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; 


wreier-aviles on DSK5TPTVN1PROD with