Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 36635 

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 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. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2007–10–07, Amendment 39–15048 (72 

FR 26711, May 11, 2007), and adding 

the following new AD: 

2014–12–05 Turbomeca S.A: Amendment 

39–17866; Docket No. FAA–2006–23809; 

Directorate Identifier 2005–NE–52–AD. 

(a) Effective Date 

This AD is effective August 4, 2014. 

(b) Affected ADs 

This AD supersedes AD 2007–10–07, 

Amendment 39–15048 (72 FR 26711, May 11, 

2007). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arriel 2B, 2B1, 2C, 2C1, 2C2, 2S1, and 2S2 

turboshaft engines. 

(d) Unsafe Condition 

This AD was prompted by a report of an 

additional case of wear of the hydromechanical metering unit (HMU) drive gear 

shaft splines on both Turbomeca S.A. Arriel 

2 engines on a twin-engine helicopter. We are 

issuing this AD to prevent failure of the HMU 

drive gear shaft, which could lead to damage 

to the engine and damage to the aircraft. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Arriel 2B and 2B1 Engines 

(i) If on the effective date of this AD the 

HMU has 500 or more operating hours since 

new or since last overhaul, then within 25 

HMU operating hours from the effective date 

of this AD, inspect the high-pressure (HP) 

pump drive gear shaft splines and coupling 

shaft assembly splines. Use paragraph 

2.B.(1)(b) of Turbomeca S.A. Mandatory 

Service Bulletin (MSB) No. 292 73 2812, 

Version G, dated June 24, 2013, to do your 

inspection. 

(ii) If on the effective date of this AD the 

HMU has less than 500 operating hours since 

new or since last overhaul, then inspect the 

HP pump drive gear shaft splines and 

coupling shaft assembly splines between 500 

and 525 operating hours since new or since 

last overhaul. Use paragraph 2.B.(1)(b) of 

Turbomeca S.A. MSB No. 292 73 2812, 

Version G, dated June 24, 2013, to do your 

inspection. 

(2) Arriel 2C, 2C1, 2C2, 2S1, and 2S2 Engines 

(i) If on the effective date of this AD the 

HMU has 500 or more operating hours since 

new, since last overhaul, or if HMU operating 

hours are unknown, then within 200 HMU 

operating hours from the effective date of this 

AD, inspect the HP pump drive gear shaft 

splines and coupling shaft assembly splines. 

Use paragraph 2.B.(1)(b) of Turbomeca S.A. 

MSB No. 292 73 2822, Version F, dated June 

21, 2013, to do your inspection. 

(ii) If on the effective date of this AD the 

HMU has more than 300 but less than 500 

operating hours since new or since last 

overhaul, then within 225 HMU operating 

hours, but no earlier than 500 or later than 

700 HMU operating hours from the effective 

date of this AD, inspect the HP pump drive 

gear shaft splines and coupling shaft 

assembly splines. Use paragraph 2.B.(1)(b) of 

Turbomeca S.A. MSB No. 292 73 2822 

Version F, dated June 21, 2013, to do your 

inspection. 

(iii) If on the effective date of this AD the 

HMU has 300 operating hours or less since 

new or since last overhaul, then inspect the 

HP pump drive gear shaft splines and 

coupling shaft assembly splines between 500 

and 525 HMU operating hours since new or 

since last overhaul. Use paragraph 2.B.(1)(b) 

of Turbomeca S.A. MSB No. 292 73 2822, 

Version F, dated June 21, 2013, to do your 

inspection. 

(f) Credit for Previous Actions 

If, before the effective date of this AD, you 

inspected your HMU after 500 HMU 

operating hours since new or since last 

overhaul using an earlier version of 

Turbomeca S.A. MSB No. 292 73 2822, 

Version F, dated June 21, 2013, for 2C, 2C1, 

2C2, 2S1 and 2S2 engines, or MSB No. 292 

73 2812, Version G, dated June 24, 2013, for 

2B or 2B1 engines, you have met the 

requirements of this AD. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install any HMU onto any engine, nor install 

any engine onto any helicopter with an HMU 

affected by this AD, unless the HMU passed 

the inspection required by paragraph (e)(1) of 

this AD for Arriel 2B and 2B1 engines or 

paragraph (e)(2) of this AD for Arriel 2C, 2C1, 

2C2, 2S1, and 2S2 engines. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Michael Davison, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park; phone: (781) 238– 

7156; fax: (781) 238–7199; email: 

Michael.Davison@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2013–0170, dated July 30, 

2013, for related information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!docketDetail;D=FAA-2006-23809. 

(j) 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) Turbomeca S.A. Mandatory Service 

Bulletin (MSB) No. 292 73 2822, Version F, 

dated June 21, 2013. 

(ii) Turbomeca S.A. MSB No. 292 73 2812, 

Version G, dated June 24, 2013. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca, 

S.A., 40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; telex: 570 042; fax: 33 (0)5 59 74 

45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

June 2, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–14951 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0394; Directorate 

Identifier 2014–SW–015–AD; Amendment 

39–17875; AD 2014–13–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Airbus Helicopters) (Previously 

Eurocopter Deutschland GmbH) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 


wreier-aviles on DSK5TPTVN1PROD with RULES
36636 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model MBB–BK 117 C–2 

helicopters with a certain Goodrich 

rescue hoist damper unit (damper unit) 

installed. This AD requires repairing or 

replacing the damper unit or 

deactivating the rescue hoist. This AD is 

prompted by a report of an 

uncommanded detachment of a damper 

unit from the cable. These actions are 

intended to prevent loss of an external 

load or person from the helicopter hoist 

and injury to persons being lifted by the 

hoist. 

DATES: This AD becomes effective July 

15, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 15, 2014. 

We must receive comments on this 

AD by August 29, 2014. 

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 AD, the European 

Aviation Safety Agency (EASA) AD, any 

incorporated by reference service 

information, 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 AD, contact Airbus Helicopters, 

Inc., 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641– 

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

3775; or at http:// 

www.airbushelicopters.com/techpub. 

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: 

George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, 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 them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued AD No. 2014–0057, 

dated March 6, 2014, and corrected 

March 7, 2014 (AD 2014–0057), to 

correct an unsafe condition for Airbus 

Helicopters Model MBB–BK 117 C–2 

helicopters. EASA advises that a rescue 

hoist damper unit detached from the 

cable when the hoist damper was lifted 

by hand with no load attached. EASA 

further advises that an investigation 

revealed the retaining ring inside the 

damper unit was not located in the 

proper position, and that this 

displacement of the retaining ring may 

have occurred as a maintenance error or 

as a result of interference with the 

bonding strap unit during normal use. 

EASA further states that this condition 

could lead to the detachment of an 

external load or person from the 

helicopter hoist, possibly resulting in 

personal injury or injury to persons on 

the ground. 

To address this unsafe condition, 

EASA issued AD 2014–0057, which 

supersedes AD No. 2014–0046–E, dated 

February 27, 2014, and which requires 

replacing Goodrich rescue hoist damper 

unit/rescue winch damper, part number 

(P/N) 44307–480, P/N 44307–480–1, or 

P/N 44307–480–2, or deactivating the 

rescue hoist. AD 2014–0057 also 

requires modifying the damper unit’s 

bonding strap and replacing the 

retaining ring, which allows reactivation 

of the rescue hoist. Lastly, AD 2014– 

0057 implements a recurring 100 hoistcycle inspection of the retaining ring for 

correct installation. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type design. 

Related Service Information 

Airbus Helicopters has issued 

Emergency Alert Service Bulletin No. 

ASB MBB–BK117 C–2–85A–041, 

Revision 2, dated March 4, 2014, which 

describes procedures for modifying the 

bonding strap unit, installing an 

improved retaining ring, and inspecting 

the retaining ring. 

AD Requirements 

This AD requires, before the next 

hoist operation, either repairing the 

hoist damper unit by following 

specified portions of the service 

information, replacing the hoist damper 

unit with a unit that has been repaired 

by following specified portions of the 

service information, or deactivating the 

rescue hoist. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires a 100 hoistcycle repetitive inspection, while this 

AD does not. We plan to publish a 

notice of proposed rulemaking to give 

the public an opportunity to comment 

on those long-term requirements. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 36637 

Costs of Compliance 

We estimate that this AD will affect 

118 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. At an average labor rate of $85 

per hour, repairing the hoist damper 

unit will require 5 work-hours, and 

required parts will cost $4, for a cost per 

helicopter of $429. Replacing the hoist 

damper unit will require 1 work-hour, 

and required parts will cost $8,715, for 

a cost per helicopter of $8,800. 

Deactivating the rescue hoist will 

require .5 work-hour, for a cost per 

helicopter of $43. 

According to Airbus Helicopters’ 

service information, some of the costs of 

this AD may be covered under warranty, 

thereby reducing the cost impact on 

affected individuals. We do not control 

warranty coverage by Airbus 

Helicopters. Accordingly, we have 

included all costs in our cost estimate. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to adopting this rule 

because the required corrective actions 

must be done before the next hoist 

operation. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

contrary to the public interest and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

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 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, 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): 

2014–13–01 Airbus Helicopters 

Deutschland GmbH (Airbus Helicopters) 

(Previously Eurocopter Deutschland 

GmbH): Amendment 39–17875; Docket 

No. FAA–2014–0394; Directorate 

Identifier 2014–SW–015–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model MBB–BK 117 C–2 helicopters with a 

Goodrich hoist damper unit, part number (P/ 

N) 44307–480, P/N 44307–480–1, or P/N 

44307–480–2, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

uncommanded detachment of the external 

hoist damper unit, which could result in loss 

of an external load or person from the hoist, 

resulting in injury to persons being lifted by 

the hoist. 

(c) Effective Date 

This AD becomes effective July 15, 2014. 

(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 

Before the next hoist operation, comply 

with paragraph (e)(1), (e)(2), or (e)(3) of this 

AD: 

(1) Repair and re-identify each hoist 

damper unit in accordance with the 

Accomplishment Instructions, paragraph 

3.B.1, of Airbus Helicopters Emergency Alert 

Service Bulletin ASB No. MBB–BK117 C–2– 

85A–041, Revision 2, dated March 4, 2014; 

or 

(2) Replace each hoist damper unit with a 

unit that has been repaired as required by 

paragraph (e)(1) of this AD; or 

(3) Deactivate the rescue hoist system. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: George Schwab, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

george.schwab@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 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0057, dated March 6, 2014, and 

corrected March 7, 2014. You may view the 

EASA AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2014–0394. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2500: Cabin Equipment Furnishings. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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. 


wreier-aviles on DSK5TPTVN1PROD with RULES
36638 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 

(i) Airbus Helicopters Emergency Alert 

Service Bulletin No. ASB MBB–BK117 C–2– 

85A–041, Revision 2, dated March 4, 2014. 

(ii) Reserved. 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

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

641–3775; or at http://

www.airbushelicopters.com/techpub. 

(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 

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 June 13, 

2014. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–14623 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1090; Directorate 

Identifier 2013–SW–017–AD; Amendment 

39–17873; AD 2014–12–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Helicopters Model EC120B and 

EC130B4 helicopters. This AD requires 

replacing parts of the sliding door star 

support attachment assembly, 

depending on the outcome of required 

inspections. This AD is prompted by a 

report that passengers in a helicopter 

were forced to exit through the pilot 

door after landing because they could 

not open the sliding door from the 

inside. The actions of this AD are 

intended to prevent failure of the sliding 

door star support attachment, which 

could inhibit operation of a sliding door 

from inside, delaying the evacuation of 

passengers during an emergency. 

DATES: This AD is effective August 4, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of August 4, 2014. 

ADDRESSES: 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 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, the European 

Aviation Safety Agency (EASA) 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 2, 2014, at 79 FR 74, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

certain Eurocopter France (now Airbus 

Helicopters) Model EC120B and 

EC130B4 helicopters. The NPRM 

proposed to require, within 165 hours 

time-in-service, visually inspecting the 

upper and lower locking pin control rod 

end fittings, and replacing the control 

end fitting before further flight if it is 

bent, twisted, or broken. The NPRM also 

proposed to require cleaning and dye 

penetrant inspecting the star support 

pin for a crack, and replacing the star 

support pin before further flight if there 

is a crack. Lastly, the NPRM proposed 

to require reinforcing the sliding door 

star support stringer by installing three 

carbon fabric plies. The proposed 

requirements were intended to prevent 

failure of the operation of a sliding door 

from inside, which could delay 

evacuation of passengers during an 

emergency. 

The NPRM was prompted by AD No. 

2013–0093, dated April 15, 2013, and 

corrected on April 17, 2013, issued by 

EASA, which is the Technical Agent for 

the Member States of the European 

Union, to correct an unsafe condition 

for Model EC120B and EC130B4 

helicopters after a case was reported 

where passengers could not open a 

helicopter’s sliding door after landing. 

EASA advises that an investigation 

revealed a failure of the sliding door star 

axle support. 

Since we issued the NPRM, 

Eurocopter France changed its name to 

Airbus Helicopters. This AD reflects 

that change and updates the contact 

information to obtain service 

documentation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (79 FR 74, January 2, 2014). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed, except for the name change 

previously described and a minor 

editorial change in referencing the 

service information in paragraph (e)(2) 

of this AD to meet current publishing 

requirements. These changes are 

consistent with the intent of the 

proposals in the NPRM (79 FR 74, 

January 2, 2014) and will not increase 

the economic burden on any operator 

nor increase the scope of the AD. 

Related Service Information 

Eurocopter issued Alert Service 

Bulletin (ASB) No. EC120–52A014 for 

Model EC120B helicopters and ASB No. 

EC130–52A009 for Model EC130B4 

helicopters, both Revision 1, and both 

dated January 25, 2013. The ASBs state 

that the star support pin ruptured on the 


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