Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules 34335 

servo actuator with servo actuator P/N 222– 

382–001–111 or P/N 222–382–001–111FM. 

(iii) If there is any corrosion that is red or 

orange in color, magnetic particle inspect the 

piston rod for a crack. 

(A) If there is a crack, replace the servo 

actuator with servo actuator, P/N 222–382– 

001–111 or P/N 222–382–001–111FM before 

further flight. 

(B) If there is no crack, comply with 

paragraphs (f)(5) through (f)(7) of this AD. 

Within 2,400 hours TIS or 2 years, whichever 

occurs first, replace the servo actuator with 

servo actuator P/N 222–382–001–111 or P/N 

222–382–001–111FM. 

(iv) If there is no corrosion, visible lack of 

cadmium plate, or damage to the piston rod, 

comply with paragraphs (f)(5) through and 

(f)(7) of this AD. Within 3,000 hours TIS or 

4 years, whichever occurs first, replace the 

servo actuator with servo actuator P/N 222– 

382–001–111 or P/N 222–382–001–111FM. 

(5) Inspect the portion of the piston rod for 

any absence of cadmium plating (bare base 

metal), as shown in Figure 7 of the 

Woodward ASB. If there is any bare base 

metal on the piston rod in this area, apply 

brush cadmium plating to all bare and 

reworked areas using SPS5070 or equivalent 

0.0002 to 0.0005 inch thick and rework the 

piston rod by following the Accomplishment 

Instructions, paragraph C., Part III, C.1.1.1. 

through C.1.1.3., of the Woodward ASB. 

(6) Reassemble the servo actuator by 

following the Accomplishment Instructions, 

paragraph C, Part III, 1.1.4. through 3.3.4. of 

the Woodward ASB. 

(7) Thereafter, overhaul servo actuator P/N 

222–382–001–111 or P/N 222–382–001– 

111FM at intervals not to exceed 10 years or 

10,000 hours TIS, whichever occurs first. 

(g) Credit for Actions Previously Completed 

Compliance with the Woodward ASB or 

with AD 2010–19–51 (75 FR 71540, 

November 24, 2010) before the effective date 

of this AD is considered acceptable for 

compliance with the corresponding 

inspections specified in paragraph (f) of this 

AD. If you replaced the piston rod pursuant 

to the Woodward ASB or paragraph (d)(1) or 

(d)(3) of AD 2010–19–51, apply the 

requirements of paragraph (f)(4)(iv) of this 

AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@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. 

(i) Additional Information 

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

222–11–111 for Model 222 and 222B 

helicopters, ASB No. 222U–11–82 for Model 

222U helicopters, ASB No. 230–11–43 for 

Model 230 helicopters, and ASB No. 430–11– 

46 for Model 430 helicopters, all Revision A 

and all dated June 22, 2012, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

Woodward HRT and Bell 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 

the Transport Canada Civil Aviation (TCCA) 

AD No. CF–2010–29R1, dated July 26, 2012. 

You may view the TCCA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0734. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6730, Rotorcraft Servo System. 

Issued in Fort Worth, Texas, on May 29, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14278 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0105; Directorate 

Identifier 2008–SW–58–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

superseding Airworthiness Directives 

(AD) 2000–05–17 and AD 2001–04–12, 

which apply to Eurocopter France (now 

Airbus Helicopters) Model EC120B 

helicopters. AD 2000–05–17 and AD 

2001–04–12 require repetitive visual 

checks of the engine-to-main gearbox 

(MGB) coupling tube assembly 

(coupling tube) for a crack and replacing 

any cracked tube with an airworthy 

tube. This proposed AD would require 

removing certain engine mount parts 

from service, measuring the height of 

the engine mounting base for certain 

helicopters, replacing the engine mount 

if a certain height is exceeded, 

inspecting the flared coupling on certain 

helicopters for a crack, and replacing 

the coupling if it is cracked. Since we 

issued AD 2000–05–17 and AD 2001– 

04–12, there have been reports of 

additional cracks in coupling tubes. The 

proposed actions are intended to 

prevent coupling tube failure, loss of 

engine drive, and a subsequent forced 

landing of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 17, 2015. 

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 

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 

Direction Generale de L’Aviation Civile 

(DGAC) 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 Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the 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: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 


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76137; telephone (817) 222–5110; email 

james.blyn@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 

On March 6, 2000, we issued AD 

2000–05–17, Amendment 39–11627 (65 

FR 13875, March 15, 2000) for Model 

EC120B helicopters with engine 

coupling tube, part number (P/N) 

C631A1002101, installed. AD 2000–05– 

17 requires recurring inspections of 

each coupling tube for a crack and, if 

there is a crack, replacing any cracked 

coupling tube with an airworthy, 

reinforced coupling tube, P/N 

C631A1101101, and replacing certain 

engine support fitting parts. AD 2000– 

05–17 also requires replacing all 

affected coupling tubes with a 

reinforced coupling tube and replacing 

certain engine support fitting parts by 

March 31, 2000. AD 2000–05–17 was 

prompted by reports of cracks on the 

coupling tubes. 

On February 20, 2001, we issued AD 

2001–04–12, Amendment 39–12131 (66 

FR 13232, March 5, 2001), for Model 

EC120B helicopters with engine 

coupling tube, P/N C631A1101101, 

installed. AD 2001–04–12 requires a 

visual check on each coupling tube for 

a crack at specified intervals. AD 2001– 

04–12 was prompted by several reports 

of cracks on the reinforced coupling 

tube. 

AD 2000–05–17 and AD 2001–04–12 

were intended to prevent coupling tube 

failure, loss of engine drive, and a 

subsequent forced landing. 

Actions Since AD 2000–05–17 and AD 

2001–04–12 Were Issued 

Since we issued AD 2000–05–17 (65 

FR 13875, March 15, 2000) and AD 

2001–04–12 (66 FR 13232, March 5, 

2001), there have been reports of 

additional cracks in coupling tubes. 

Eurocopter France (now Airbus 

Helicopters) has conducted tests and 

determined that the washer-type engine 

mount may, in certain cases, induce 

excessive loading on the coupling tube 

since the design does not allow the 

operators to ensure that all of the parts 

are correctly assembled. Eurocopter 

France (now Airbus Helicopters) has 

also determined that excessive loading 

results in binding that increases 

component wear of the inner diameter 

of the mounting base. 

The DGAC, on behalf of the European 

Aviation Safety Agency, issued AD No. 

F–2003–325 R1, dated May 12, 2004, to 

correct an unsafe condition for Model 

EC120B helicopters with engine 

coupling tube, P/N C631A1101101, and 

with an engine mount containing 

certain parts listed in Eurocopter Alert 

Service Bulletin (ASB) No. 04A005, 

dated July 16, 2003. DGAC AD No. F– 

2003–325 R1 requires certain 

inspections for helicopters with an 

engine mount block modified in 

accordance with Eurocopter Service 

Bulletin (SB) No. 71–003, Revision 1, 

dated July 18, 2002, replacing any 

coupling tube that has a crack, and 

increasing the life limit of the coupling 

tube from 1,000 flight hours to 20,000 

flight hours. Also, DGAC AD No. F– 

2003–325 R1 requires, for helicopters 

with a new spring-loaded engine 

suspension modification in accordance 

with Eurocopter SB No. 71–005, 

Revision 0, dated May 14, 2004, 

increasing the life limit of the coupling 

tube to 20,000 flight hours and 

canceling the repetitive inspections of 

the coupling tube. The DGAC advises 

that a crack was detected on a 

reinforced coupling tube, which may 

lead to coupling tube failure and 

subsequent autorotation. 

This action is intended to prevent 

coupling tube failure, loss of engine 

drive, and a subsequent forced landing 

of the helicopter. 

FAA’s Determination 

This helicopter has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, the DGAC has 

kept the FAA informed of the situation 

described above. We are proposing this 

AD because we evaluated all 

information provided by the DGAC and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

helicopters of these same type designs. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following 

Eurocopter service information: 

• ASB No. 04A005, Revision 0, dated 

July 16, 2003, prohibits, after June 30, 

2004, operating an engine mount made 

up of the following parts: support arm, 

P/N C714A1107201; swaged support 

arm, P/N C714A1106201; left-hand 

support bracket, P/N C714A1101102; 

and right-hand support bracket, P/N 

C714A1101103. SB No. 04A005 also 

specifies measuring the height of the 

engine mounting base and, if the height 

is more than 10.5 millimeters, replacing 

the engine mount with an engine mount 

that does not have the specified P/N. 

ASB No. 04A005 does not apply to 

helicopters modified with an improved 

engine mount in accordance with SB 

No. 71–003. ASB No. 04A005 also does 

not apply to helicopters with a serial 

number 1170 or larger, as the specified 

engine mounts are not installed on those 

helicopters. 

• SB No. 71–005, Revision 0, dated 

May 14, 2004, contains procedures to 

modify the spring-type engine 

suspension system and dye-penetrant 

inspect the flared coupling assembly. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this NPRM. 

The DGAC classified the service 

information contained in ASB No. 

04A005 and SB No. 71–005 as 

mandatory and issued AD No. F–2003– 

325 R1, dated May 12, 2004, to ensure 

the continued airworthiness of these 

helicopters. 

Other Related Service Information 

We also reviewed the following 

Eurocopter service information: 

• SB No. 71–003, Revision 1, dated 

July 18, 2002, contains procedures to 

improve the engine mount. 

• ASB No. 05A003, Revision 2, dated 

July 16, 2003, for helicopters that have 

not been modified with an improved 

engine mount in accordance with SB 

No. 71–003, specifies inspecting the 

coupling tube for a crack every 5 hours 

and establishing a coupling tube life 

limit of 1,000 hours. For helicopters that 

have been modified with an improved 

engine mount, ASB No. 05A003 


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specifies inspecting the coupling tube 

for a crack every 25 hours and 

increasing the coupling tube life limit to 

20,000 hours. ASB No. 05A003 was 

revised to Revision 3, dated May 11, 

2004, to specify an optional spring-type 

engine suspension modification and 

cancel the repetitive inspection for this 

modified configuration. 

The DGAC also classified the service 

information contained in SB No. 71–003 

and ASB No. 05A003 as mandatory and 

issued AD No. F–2003–325 R1, dated 

May 12, 2004, to ensure the continued 

airworthiness of these helicopters. 

Proposed AD Requirements 

This proposed AD would require: 

• Before further flight, for certain 

helicopters, removing from service 

certain engine mount parts: support 

arm, P/N C714A1107201; swaged 

support arm, P/N C714A1106201; lefthand support bracket, P/N 

C714A1101102; and right-hand support 

bracket, P/N C714A1101103. Measuring 

the height of the engine mounting base 

and, if the height is more than 10.5 

millimeters, replacing the engine mount 

with an engine mount that does not 

have the affected parts. 

• Within 25 hours time-in-service 

(TIS), for certain other helicopters that 

do not have the specified engine mount 

parts due to modifications, replacing the 

spring-type engine suspension system 

and dye-penetrant inspecting the flared 

coupling for a crack. If there is a crack 

in the flared coupling, before further 

flight, replacing the coupling with an 

airworthy coupling. 

• Before further flight, removing 

coupling tube, P/N C631A1002101 from 

service. This proposed AD would 

prohibit installing coupling tube, P/N 

C631A1002101 on any helicopter. 

Differences Between This Proposed AD 

and the DGAC AD 

This proposed AD would require the 

installation of the spring-type engine 

suspension modification specified in 

Eurocopter SB No. 71–005 and would 

not require the repetitive inspection of 

the coupling tube and the engine mount 

base. This proposed AD would not 

require you to contact the manufacturer. 

Costs of Compliance 

We estimate out of 115 helicopters on 

the U.S. registry about 23 helicopters 

would be affected by this proposed AD. 

At an average labor rate of $85 per work 

hour, we estimate the following: 

• Installing new mounting arms and 

brackets would require about 12 work 

hours and required parts would cost 

$9,194, for a total cost per helicopter of 

$10,214 and $234,922 for the fleet. 

• Installing the mounting spring kit 

would require about 14 work hours and 

required parts would cost $14,621, for a 

total cost per helicopter of $15,811 and 

$363,653 for the fleet. 

• Dye-penetrant inspecting the 

coupling tube would require about 1 

work hour for a cost per helicopter of 

$85 and $1,955 for the 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 

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: 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2000–05–17, Amendment 39– 

11627 (65 FR 13875, March 15, 2000); 

and AD 2001–04–12, Amendment 39– 

12131 (66 FR 13232, March 5, 2001); 

and 

■ b. Adding the following new AD: 

Airbus Helicopters (Previously Eurocopter 

France): Docket No. FAA–2014–0105; 

Directorate Identifier 2008–SW–58–AD. 

(a) Applicability 

This AD applies to Model EC120B 

helicopters with an engine-to-main gearbox 

coupling tube assembly (coupling tube), part 

number (P/N) C631A1101101 or P/N 

C631A1002101, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a coupling tube. This condition 

could result in coupling tube failure, loss of 

engine drive, and a subsequent forced 

landing of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2000–05–17, 

Amendment 39–11627 (65 FR 13875, March 

15, 2000) and AD 2001–04–12, Amendment 

39–12131 (66 FR 13232, March 5, 2001). 

(d) Comments Due Date 

We must receive comments by August 17, 

2015. 

(e) 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. 

(f) Required Actions 

(1) For helicopters with a serial number up 

to and including 1169, not modified with an 

improvement of the engine mount in 

accordance with Eurocopter Service Bulletin 

(SB) No. 71–003, Revision 1, dated July 18, 

2002 (SB 71–003), or not modified by 

installing a spring-type engine suspension 

system in accordance with Eurocopter SB No. 

71–005, Revision 0, dated May 14, 2004 (SB 

71–005), before further flight: 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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(i) Remove from service the following 

engine mount parts: 

(A) Support arm, P/N C714A1107201; 

(B) Swaged support arm, P/N 

C714A1106201; 

(C) Left-hand support bracket, P/N 

C714A1101102; and 

(D) Right-hand support bracket, P/N 

C714A1101103. 

(ii) Measure the height of the engine 

mounting base as depicted in Figure 1 of 

Eurocopter Alert SB No. 04A005, Revision 0, 

dated July 16, 2003. If the height is more than 

10.5 millimeters, replace the engine mount 

with an engine mount that does not have the 

parts identified in paragraph (f)(1)(i) of this 

AD. 

(2) For helicopters with a serial number 

1170 and larger or helicopters modified with 

an improvement of the engine mount in 

accordance with SB 71–003: 

(i) Within 25 hours TIS, replace the springtype engine suspension system and perform 

a dye-penetrant inspection of the flared 

coupling for a crack by following the 

Accomplishment Instructions, paragraphs 

2.B.2.a through 2.B.2.c of SB 71–005. 

(ii) If there is a crack in the flared coupling, 

before further flight, replace the coupling 

with an airworthy coupling. 

(3) For helicopters with coupling tube, P/ 

N C631A1002101, installed, before further 

flight, remove coupling tube, P/N 

C631A1002101, from service. Do not install 

coupling tube, P/N C631A1002101, on any 

helicopter. 

(g) Special Flight Permits 

Special flight permits may be issued 

provided there are no cracks in the coupling 

tube attachment fitting. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: James Blyn, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@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. 

(i) Additional Information 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. 05A003, Revision 2, dated July 16, 2003, 

Eurocopter ASB No. 05A003, Revision 3, 

dated May 11, 2004, and Eurocopter Service 

Bulletin No. 71–003, Revision 1, dated July 

18, 2002, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, Texas 75052, telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://

www.airbushelicopters.com/techpub. 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 

Direction Generale de L’Aviation Civile 

(DGAC) AD No. F–2003–325 R1, Revision A, 

dated May 12, 2004. You may view the 

DGAC AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2014–0105. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6310 Engine/Transmission Coupling— 

Coupling Tube, Engine Mount, and Engine 

Mount Base. 

Issued in Fort Worth, Texas, on May 29, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14282 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 61 and 141 

[Docket No.: FAA–2015–1846; Notice No. 

15–03] 

RIN 2120–AK71 

Aviation Training Device Credit for 

Pilot Certification 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: This rulemaking proposes to 

relieve burdens on pilots seeking to 

obtain aeronautical experience, training, 

and certification by increasing the 

allowed use of aviation training devices. 

These actions are necessary to bring the 

regulations in line with current needs 

and activities of the general aviation 

training community and pilots. 

DATES: Send comments on or before July 

16, 2015. 

ADDRESSES: Send comments identified 

by docket number FAA–2015–1846 

using any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30; U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: In accordance with 5 U.S.C. 

553(c), DOT solicits comments from the 

public to better inform its rulemaking 

process. DOT posts these comments, 

without edit, including any personal 

information the commenter provides, to 

http://www.regulations.gov, as 

described in the system of records 

notice (DOT/ALL–14 FDMS), which can 

be reviewed at http://www.dot.gov/

privacy. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov at any time. 

Follow the online instructions for 

accessing the docket or go to the Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Marcel Bernard, Airmen 

Certification and Training Branch, 

Flight Standards Service, AFS–810, 

Federal Aviation Administration, 898 

Airport Park Road, Suite 204, Glen 

Burnie, MD 21061; telephone: (410) 

590–5364 x235 email marcel.bernard@

faa.gov. 

For legal questions concerning this 

action, contact Anne Moore, Regulations 

Division, Office of the Chief Counsel, 

AGC–200, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone (202) 267–3073; email 

anne.moore@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules on 

aviation safety is found in Title 49 of the 

United States Code (49 U.S.C.). 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. 

This rulemaking is promulgated 

under the authority described in 49 

U.S.C. 106(f), which establishes the 

authority of the Administrator to 

promulgate regulations and rules; 49 

U.S.C. 44701(a)(5), which requires the 

Administrator to promote safe flight of 

civil aircraft in air commerce by 

prescribing regulations and setting 

minimum standards for other practices, 

methods, and procedures necessary for 

safety in air commerce and national 

security; and 49 U.S.C. 44703(a), which 


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