23688 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 

the FAA proposes to amend 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): 

Eurocopter France Helicopters: Docket No. 

FAA–2013–0353; Directorate Identifier 

2008–SW–029–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) models AS332C, AS332L, 

AS332L1, AS332L2, and EC225LP 

helicopters, serial numbers (S/N) up to and 

including 2680 and S/N 9000 through 9009, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

interference between the tail gearbox (TGB) 

attachment bolt and the structure fitting. This 

condition could result in insufficient 

tightening of the TGB casing, damage to the 

TGB attachment, cracking under the 

attachment bolt, loss of the TGB and 

consequently, loss of helicopter control. 

(c) 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. 

(d) Required Actions 

Within 50 hours time-in-service (TIS): 

(1) Inspect the TGB aft attachment fitting 

to measure the dimension for a blind hole as 

follows: 

(i) Remove the TGB attachment bolt (c) but 

retain washer (d) as depicted in Detail A, 

Figure 1, of Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 53.01.58 and 

EASB No. 53A012, both Revision 1, and both 

dated January 4, 2008. 

(ii) Use a depth gauge to measure 

dimension ‘‘x’’ between the top face of the 

washer (d) and the bottom of aft fitting (a) as 

depicted in Detail A, Figure 1, of the EASB. 

(2) If the measurement is equal to or greater 

than 81 mm, then the blind hole is present. 

Install the TGB attachment bolt (c) with its 

washer (d) as depicted in Detail A, Figure 1, 

of the EASB. Lock with lockwire. 

(3) If the measurement is less than 81 mm, 

then the blind hole is missing. Inspect the 

end of the threaded section of bolt (c) for 

chafing or a contact mark, as depicted in 

Area 1, Figure 1, of the EASB. 

(i) If there is no chafing and no contact 

marks, install bolt (c) with washer (d) and 

additional washer (2) as depicted in Detail B, 

Figure 1, of the EASB. 

(ii) If there is chafing or a contact mark, 

replace the TGB attachment bolt (c) with an 

airworthy bolt and install with washer (d) 

and additional washer (2) as depicted in 

Detail B, Figure 1, of the EASB. Lock with 

lockwire. 

(iii) Within the next 825 hours TIS, replace 

the TGB aft attachment fitting with an 

airworthy attachment fitting. 

(4) Inspect the right and left attachment 

points of the TGB forward attachment to 

measure the dimension for a blind hole, as 

follows: 

(i) Remove both TGB attachment bolts (c) 

but retain washers (d), as depicted in Detail 

A, Figure 2, of the EASB. 

(ii) Use a depth gauge to measure 

dimension ‘‘x’’ between the top face of 

washer (d) and the bottom of forward fitting 

(b) at the right and left attachment points, as 

depicted in Detail A, Figure 2, of the EASB. 

(5) If both measurements are equal to or 

greater than 81 mm, then the blind hole is 

present. Install TGB attachment bolt (c) with 

its washer (d), as depicted in Detail A, Figure 

2, of the EASB. Lock with lockwire. 

(6) If one or both measurements are less 

than 81 mm, then the blind hole is missing. 

Inspect the end of the threaded section of 

each bolt (c) for chafing or a contact mark, 

as depicted in Area 1, Figure 2 of the EASB. 

(i) If there is no chafing and no contact 

marks, for each attachment point, install bolt 

(c) with washer (d) and additional washer (2), 

as depicted in Detail B, Figure 2, of the 

EASB. 

(ii) If there is chafing or a contact mark, 

replace each the TGB attachment bolt (c) 

with an airworthy bolt and install bolt (1) 

with washer (d) and additional washer (2), as 

depicted in Detail B, Figure 2, of the EASB. 

Lock with lockwire. 

(iii) Within the next 825 hours TIS, replace 

the TGB forward attachment fitting with an 

airworthy attachment fitting. 

(e) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

gary.b.roach@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. 

(f) Additional Information 

The subject of this AD is addressed in the 

Direction Ge ́ne ́rale de L’Aviation Civile 

France AD No F–2007–027, dated January 2, 

2008. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6520, Tail Rotor Gearbox. 

Issued in Fort Worth, Texas, on April 11, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09414 Filed 4–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0349; Directorate 

Identifier 2012–SW–058–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Inc. 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bell Helicopter Textron Canada Inc. 

(BHT) Model 206A, 206B, and 206L 

helicopters. This proposed AD would 

require replacing certain part-numbered 

engine auto-relight kit control boxes. 

This proposed AD is prompted by a 

design review that revealed the control 

box chipset did not meet the required 

temperature range requirements, which 

could cause the control box to 

malfunction, disabling the engine autorelight system. This condition could 

result in increased pilot workload 

during a power loss emergency and 

subsequent loss of control of the aircraft. 

DATES: We must receive comments on 

this proposed AD by June 21, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 23689 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4; telephone (450) 437–2862 or 

(800) 363–8023; fax (450) 433–0272; or 

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

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

Transport Canada (TC), which is the 

aviation authority for Canada, has 

issued TC AD No. CF–2012–19, dated 

June 12, 2012 (CF–2012–19), to correct 

an unsafe condition for certain serial 

numbered BHT Model 206A, 206B, and 

206L helicopters with an engine autorelight kit control box assembly (control 

box assembly) part number 206–375– 

017–101 or 206–375–017–103 installed. 

TC advises that these control box 

assemblies have a manufacturing defect 

which could disable the auto-relight 

system in the event of an engine 

flameout, subsequently requiring the 

pilot to re-start the engine manually. 

This condition could result in increased 

pilot workload during a power loss 

emergency in-flight and subsequent loss 

of control of the helicopter. CF–2012–19 

specifies replacing the affected control 

boxes within 4 months to correct the 

unsafe condition. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TC, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

BHT has issued Alert Service Bulletin 

(ASB) No. 206–11–127 for Model 206A 

and 206B helicopters and ASB No. 

206L–11–167 for Model 206L 

helicopters, both dated May 2, 2011. 

Both ASBs specify replacing the affected 

control box assembly with an upgraded 

control box assembly. 

Proposed AD Requirements 

This proposed AD would require 

replacing the control box assembly 

within 4 months. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 1,357 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this AD. If installed, 

replacing the control box assembly 

would require about 2 work-hours at an 

average labor rate of $85 per hour and 

required parts would cost about 

$18,974, for a cost per helicopter of 

$19,144. 

According to BHT’s service 

information, some of the costs of this 

proposed AD may be covered under 

warranty, thereby reducing the cost 

impact on affected individuals. We do 

not control warranty coverage by BHT. 

Accordingly, we have included all costs 

in our cost estimate. 

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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed 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); 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
23690 Federal Register / Vol. 78, No. 77 / Monday, April 22, 2013 / Proposed Rules 

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): 

Bell Helicopter Textron Canada Inc (BHT): 

Docket No. FAA–2013–0349; Directorate 

Identifier 2012–SW–058–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: 

(1) BHT Model 206A and 206B helicopters, 

all serial numbers (S/N) except S/Ns 1, 2, and 

3, with an engine auto-relight kit control box 

assembly (control box assembly) part number 

(P/N) 206–375–017–101 installed; and 

(2) BHT Model 206L helicopters, S/N 

45001 through 45153 and 46601 through 

46617, with a control box assembly P/N 206– 

375–017–103 installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

inoperative control box assembly. This 

condition could result in a disabled autorelight system, failure of the engine to relight 

after a flame-out, increased pilot workload 

during a power loss emergency, and 

subsequent loss of control of the helicopter. 

(c) Reserved 

(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 4 months, replace the control box 

assembly: 

(1) For Model 206A and 206B helicopters, 

replace control box assembly P/N 206–375– 

017–101 with a control box assembly P/N 

206–375–017–105. 

(2) For Model 206L helicopters, replace 

control box assembly P/N 206–375–017–103 

with a control box assembly P/N 206–375– 

017–107. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Rao Edupuganti, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

rao.edupuganti@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) Additional Information 

(1) BHT Alert Service Bulletin (ASB) No. 

206–11–127 for Model 206A and 206B 

helicopters and ASB No. 206L–11–167 for 

Model 206L helicopters, both dated May 2, 

2011, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Bell Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4; telephone (450) 437–2862 or (800) 

363–8023; fax (450) 433–0272; or at http:// 

www.bellcustomer.com/files/. You may 

review a copy of the service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada AD CF–2012–19, dated 

June 12, 2012. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7410: Ignition Power Supply. 

Issued in Fort Worth, Texas, on April 11, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09415 Filed 4–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0034; Directorate 

Identifier 2010–NM–021–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Proposed rule; withdrawal. 

SUMMARY: The FAA withdraws a notice 

of proposed rulemaking (NPRM) that 

proposed a new airworthiness directive 

(AD) for certain The Boeing Company 

Model 777–200 series airplanes. The 

proposed AD would have required 

installing a new circuit breaker, relays, 

and wiring to allow the flightcrew to 

turn off electrical power to the in-flight 

entertainment (IFE) systems and other 

non-essential electrical systems through 

a switch in the flight compartment, and 

doing other specified actions. This 

proposed AD would also have required 

installing a new cabin system control 

panel (CSCP); installing a new cabin 

management system (CMS) 

configuration database; and installing 

new operational program software (OPS) 

for the CSCP, zone management unit 

(ZMU), passenger address controller, 

cabin interphone controller, cabin area 

control panel (CACP), speaker drive 

module, overhead electronics units, and 

seat electronics unit. Since the proposed 

AD was issued, we have received new 

data that indicates the unsafe condition 

would not be adequately addressed by 

the proposed action. Subsequently, we 

are considering issuing new rulemaking 

that positively addresses the unsafe 

condition identified in the NPRM and 

eliminates the need for the actions 

proposed in the NPRM. Accordingly, 

the proposed AD is withdrawn. 

ADDRESSES: 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 action, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 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: Ray 

Mei, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6467; fax: 

425–917–6590; email: 

raymont.mei@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with a notice of proposed 

rulemaking (NPRM) for a new AD for 

certain Model 777–200 series airplanes. 

That NPRM published in the Federal 

Register on February 1, 2011 (76 FR 

5505). The NPRM would have required 

installing a new circuit breaker, relays, 

and wiring to allow the flightcrew to 

turn off electrical power to the IFE 

systems and other non-essential 

electrical systems through a switch in 

the flight compartment, and doing other 

specified actions. The actions included 

removing the CSCP core partition 

software, the CACP OPS, the ZMU OPS, 

and the cabin system management unit 

(CSMU) OPS; installing OPS for the 

CSCP, CACP, ZMU, and CSMU; and 

installing the new configuration 

database (CDB). That NPRM would also 

have required installing a new CSCP; 

installing a new CMS CDB, installing 

passenger address controller, cabin 


tkelley on DSK3SPTVN1PROD with PROPOSALS