66090 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations 

Issued in Des Moines, Washington, on 

December 13, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–27881 Filed 12–21–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–1039; Product 

Identifier 2018–NE–14–AD; Amendment 39– 

19531; AD 2018–26–01] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International S.A. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2018–18– 

01 for all CFM International S.A. (CFM) 

Model CFM56–7B turbofan engines. AD 

2018–18–01 required initial and 

repetitive inspections of certain fan 

blades and, if they fail the inspection, 

their replacement with parts eligible for 

installation. This AD requires the same 

initial and repetitive inspections but 

revises the compliance time for the 

initial inspections and revises the 

installation prohibition based on the 

updated compliance time. This AD was 

prompted by further analysis by the 

manufacturer that indicated a need to 

reduce the initial fan blade inspection 

interval based on an ongoing root cause 

investigation of an April 2018 engine 

failure. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 10, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 10, 2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 14, 2018 (83 FR 

19176, May 2, 2018). 

We must receive any comments on 

this AD by February 11, 2019. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC, 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this final rule, contact CFM 

International Inc., Aviation Operations 

Center, 1 Neumann Way, M/D Room 

285, Cincinnati, OH, 45125; phone: 

877–432–3272; fax: 877–432–3329; 

email: aviation.fleetsupport@ge.com. 

You may view this service information 

at the FAA, Engine and Propeller 

Standards Branch, 1200 District 

Avenue, Burlington, MA, 01803. For 

information on the availability of this 

material at the FAA, call 781–238–7759. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

1039. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

1039; or in person at Docket Operations 

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

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The street address for 

Docket Operations (phone: 800–647– 

5527) is listed above. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christopher McGuire, Aerospace 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA, 01803; 

phone: 781–238–7120; fax: 781–238– 

7199; email: chris.mcguire@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued AD 2018–18–01, 

Amendment 39–19380 (83 FR 49272, 

October 1, 2018), (‘‘AD 2018–18–01’’), 

for all CFM model CFM56–7B turbofan 

engines. AD 2018–18–01 required initial 

and repetitive ultrasonic inspections 

(USI) or eddy current inspection (ECI) of 

certain fan blades and, if they fail the 

inspection, their replacement with parts 

eligible for installation. AD 2018–18–01 

resulted from analysis by the 

manufacturer that indicated a need to 

reduce the repetitive fan blade 

inspection interval based on ongoing 

root cause investigation of an April 2018 

engine failure. The April 2018 engine 

failure was the result of a fractured fan 

blade leading to the engine inlet cowl 

disintegrating and debris penetrating the 

fuselage, causing a loss of pressurization 

and prompting an emergency descent. 

One passenger fatality occurred as a 

result. We issued AD 2018–18–01 to 

reduce the repetitive inspection interval 

from 3,000 cycles to 1,600 cycles. 

Actions Since AD 2018–18–01 Was 

Issued 

Since we issued AD 2018–18–01, 

CFM gained a better understanding of 

the fan blade failures based on the 

inspections and further analysis of the 

detected cracks and the April 2018 

event. As a result, CFM has published 

CFM International Service Bulletin (SB) 

CFM56–7B S/B 72–1033, Revision 3, 

dated November 6, 2018, to reduce the 

initial inspection requirement from 

20,000 cycles since new (CSN) to 17,000 

CSN. We are issuing this AD to address 

the unsafe condition on these products. 

Related Service Information Under 1 

CFR Part 51 

We reviewed CFM International SB 

CFM56–7B S/B 72–1033, Revision 3, 

dated November 6, 2018, and Subtask 

72–21–01–220–091, of Task 72–21–01– 

200–001, from the CFM56–7B Engine 

Shop Manual (ESM), Revision 57, dated 

January 15, 2018. CFM International SB 

CFM56–7B S/B 72–1033, Revision 3, 

describes procedures for performing a 

USI of the affected fan blades. Subtask 

72–21–01–220–091, of Task 72–21–01– 

200–001, from the CFM56–7B ESM, 

describes procedures for performing an 

ECI of the affected fan blades. 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. 

Other Related Service Information 

We also reviewed CFM SB CFM56–7B 

S/B 72–1019, dated March 24, 2017; 

CFM SB CFM56–7B S/B 72–1019, 

Revision 1, dated June 13, 2017; CFM 

SB CFM56–7B S/B 72–1024, dated July 

26, 2017; CFM International SB CFM56– 

7B S/B 72–1033, Revision 2, dated July 

27, 2018; CFM SB CFM56–7B S/B 72– 

1033, Revision 1, dated May 9, 2018; 

CFM SB CFM56–7B S/B 72–1033, dated 

April 20, 2018; and General Electric 

Field Support Technology (FST) 

Procedure 2370, dated December 9, 

2016. These SBs and the FST provide 

information on performing the USI. 


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Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations 66091 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires initial and repetitive 

USI or ECI of certain fan blades and, if 

they fail the inspection, their 

replacement with parts eligible for 

installation. 

Interim Action 

We consider this AD interim action. 

An investigation to determine the cause 

of the failure is ongoing, and we may 

consider additional rulemaking if final 

action is identified. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies waiving notice 

and comment prior to adoption of this 

rule. Due to the reduction in the initial 

inspection interval, some fan blades 

have reached or exceeded the revised 

initial inspection threshold and will 

require inspection within 1,000 cycles 

after the effective date of this AD. 

Because of this, the compliance time for 

the required action is shorter than the 

time necessary for the public to 

comment and for the FAA to issue the 

final rule to ensure the unsafe condition 

is addressed. Therefore, we find good 

cause that notice and opportunity for 

prior public comment are impracticable. 

In addition, for the reasons stated above, 

we find that good cause exists for 

making this amendment effective in less 

than 30 days. 

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 before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under the ADDRESSES

section. Include the docket number 

FAA–2018–1039 and product identifier 

2018–NE–14–AD at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this final rule. We will 

consider all comments received by the 

closing date and may amend this final 

rule because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this final rule. 

Costs of Compliance 

We estimate that this AD affects 3,716 

engines installed on 1,858 airplanes of 

U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED INSPECTION COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect engine fan blade ................................ 2 work-hours × $85 per hour = $170 ............. $0 $170 $631,720 

We estimate the following costs to 

complete any necessary replacement of 

a single fan blade that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of engines that 

might need fan blades to be replaced. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace fan blade ........................................................ 1 work-hour × $85 per hour = $85 ............................... $51,400 $51,485 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to engines, propellers, and 

associated appliances to the Manager, 

Engine and Propeller Standards Branch, 

Policy and Innovation Division. 

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, and 


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66092 Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations 

(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. 

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) 

2018–18–01, Amendment 39–19380 (83 

FR 49272, October 1, 2018) and adding 

the following new AD: 

2018–26–01 CFM International S.A.: 

Amendment 39–19531; Docket No. 

FAA–2018–1039; Product Identifier 

2018–NE–14–AD. 

(a) Effective Date 

This AD is effective January 10, 2019. 

(b) Affected ADs 

This AD replaces AD 2018–18–01, 

Amendment 39–19380 (83 FR 49272, October 

1, 2018). 

(c) Applicability 

This AD applies to CFM International 

S.A.(CFM) CFM56–7B20, CFM56–7B22, 

CFM56–7B22/B1, CFM56–7B24, CFM56– 

7B24/B1, CFM56–7B26, CFM56–7B26/B2, 

CFM56–7B27, CFM56–7B27A, CFM56–7B26/ 

B1, CFM56–7B27/B1, CFM56–7B27/B3, 

CFM56–7B20/2, CFM56–7B22/2, CFM56– 

7B24/2, CFM56–7B26/2, CFM56–7B27/2, 

CFM56–7B20/3, CFM56–7B22/3, CFM56– 

7B22/3B1, CFM56–7B24/3, CFM56–7B24/ 

3B1, CFM56–7B26/3, CFM56–7B26/3B1, 

CFM56–7B26/3B2, CFM56–7B27/3, CFM56– 

7B27/3B1, CFM56–7B27/3B3, CFM56– 

7B27A/3, CFM56–7B26/3F, CFM56–7B26/ 

3B2F, CFM56–7B27/3F, CFM56–7B27/3B1F, 

CFM56–7B20E, CFM56–7B22E, CFM56– 

7B22E/B1, CFM56–7B24E, CFM56–7B24E/ 

B1, CFM56–7B26E, CFM56–7B26E/B1, 

CFM56–7B26E/B2, CFM56–7B27AE, 

CFM56–7B27E, CFM56–7B27E/B1, CFM56– 

7B27E/B3, CFM56–7B26E/F, CFM56–7B26E/ 

B2F, CFM56–7B27E/F, and CFM56–7B27E/ 

B1F turbofan engine models. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by further analysis 

by the manufacturer that indicated a need to 

reduce the initial fan blade inspection 

requirement based on its ongoing root cause 

investigation of an April 2018 engine failure 

that resulted in one fatality. We are issuing 

this AD to prevent failure of the fan blade. 

The unsafe condition, if not addressed, could 

result in failure of the fan blade, the engine 

inlet cowl disintegrating and debris 

penetrating the fuselage, causing a loss of 

pressurization, and prompting an emergency 

descent. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Perform an ultrasonic inspection (USI) 

or eddy current inspection (ECI) of the 

concave and convex sides of the fan blade 

dovetail as follows: 

(i) For a fan blade with less than or equal 

to 16,000 cycles since new (CSN), inspect 

prior to accumulating 17,000 CSN. 

(ii) For a fan blade with more than 16,000 

and less than 20,000 CSN, inspect within 

1,000 cycles but no later than 20,000 CSN. 

(iii) For a fan blade with 20,000 or more 

CSN, inspect before further flight. 

(iv) Thereafter, repeat this inspection no 

later than 1,600 cycles since the last 

inspection, or within 450 cycles after October 

16, 2018, the effective date of AD 2018–18– 

01, whichever occurs later. 

(v) Use the Accomplishment Instructions, 

paragraphs 3.A.(3)(a) through (i), of CFM 

International Service Bulletin (SB) CFM56– 

7B S/B 72–1033, Revision 3, dated November 

6, 2018, to perform a USI or use the 

instructions in subtask 72–21–01–220–091, 

of task 72–21–01–200–001, from CFM 

CFM56–7B Engine Shop Manual, Revision 

57, dated January 15, 2018, to perform an 

ECI. 

(2) If any unserviceable indication, as 

specified in the applicable service 

information in paragraph (g)(1)(v) of this AD, 

is found during the inspections required by 

paragraph (g) of this AD, replace the fan 

blade before further flight with a part eligible 

for installation. 

(h) Installation Prohibition 

Do not install any replacement fan blade 

unless it meets one of the following criteria: 

(1) The replacement fan blade has fewer 

than 17,000 CSN, or; 

(2) The replacement fan blade has been 

inspected, per paragraph (g)(1) of this AD, 

within the last 1,600 cycles before 

installation. 

(i) Definition 

For the purpose of this AD, a ‘‘replacement 

fan blade’’ is a fan blade that is being 

installed into an engine from which it was 

not previously removed. Removing and 

reinstalling a fan blade for the purpose of 

relubrication is not subject to the Installation 

Prohibition of this AD. 

(j) Credit for Previous Actions 

You may take credit for the actions that are 

required by paragraph (g) of this AD, if you 

performed those actions before the effective 

date of this AD using CFM SB CFM56–7B S/ 

B 72–1019, dated March 24, 2017; CFM SB 

CFM56–7B S/B 72–1019, Revision 1, dated 

June 13, 2017; CFM SB CFM56–7B S/B 72– 

1024, dated July 26, 2017; CFM SB CFM56– 

7B S/B 72–1033 dated April 20, 2018; CFM 

SB CFM56–7B S/B 72–1033, Revision 1, 

dated May 9, 2018; or CFM International SB 

CFM56–7B S/B 72–1033, Revision 2, dated 

July 27, 2018; or performed an ECI using the 

instructions in task 72–21–01–200–001, 

subtask 72–21–01–220–091 of CFM56–7B 

Engine Shop Manual, earlier than Revision 

57, dated January 15, 2018. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the certification office, 

send it to the attention of the person 

identified in paragraph (l) of this AD. You 

may email your request to: ANE-AD-AMOC@

faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (k)(3)(i) and (k)(3)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(4) AMOCs approved previously for AD 

2018–10–11 (83 FR 22836, May 17, 2018) and 

AD 2018–18–01 (83 FR 49272, October 1, 

2018) are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

For more information about this AD, 

contact Christopher McGuire, Aerospace 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7120; fax: 781–238–7199; email: 

chris.mcguire@faa.gov. 

(m) 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. 


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Federal Register / Vol. 83, No. 246 / Wednesday, December 26, 2018 / Rules and Regulations 66093 

(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 January 10, 2019. 

(i) CFM International (CFM) Service 

Bulletin CFM56–7B S/B 72–1033, Revision 3, 

dated November 6, 2018. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on May 14, 2018 (83 FR 

19176, May 2, 2018). 

(i) Subtask 72–21–01–220–091, of Task 72– 

21–01–200–001, from the CFM CFM56–7B 

Engine Shop Manual, Revision 57, dated 

January 15, 2018. 

(ii) [Reserved] 

(5) For CFM service information identified 

in this AD, contact CFM International Inc., 

Aviation Operations Center, 1 Neumann 

Way, M/D Room 285, Cincinnati, OH 45125; 

phone: 877–432–3272; fax: 877–432–3329; 

email: aviation.fleetsupport@ge.com. 

(6) You may view this service information 

at the FAA, Engine and Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7759. 

(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 Burlington, Massachusetts, on 

December 18, 2018. 

Robert J. Ganley, 

Manager, Engine & Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–27920 Filed 12–21–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0669; Product 

Identifier 2017–SW–041–AD; Amendment 

39–19532; AD 2018–26–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2016–25– 

19 for Airbus Helicopters (previously 

Eurocopter France) Model AS350B3 and 

EC130B4 helicopters. AD 2016–25–19 

required inspecting the pilot’s and copilot’s throttle twist for proper 

operation. This new AD retains the 

requirements of AD 2016–25–19 and 

adds certain model helicopters to the 

applicability. The actions of this AD are 

intended to address an unsafe condition 

on these products. 

DATES: This AD is effective January 30, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 30, 2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of February 2, 2017 (81 FR 

95854, December 29, 2016). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.helicopters.airbus.com/website/ 

en/ref/Technical-Support_73.html. You 

may the review service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. It is also available on the internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2018–0669. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at http://

www.regulations.gov in Docket No. 

FAA–2018–0669; or in person at Docket 

Operations 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 incorporatedby-reference service information, the 

economic evaluation, any comments 

received, and other information. The 

address for Docket Operations (phone: 

800–647–5527) is Docket Operations, 

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: 

George Schwab, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2016–25–19, 

Amendment 39–18745 (81 FR 95854, 

December 29, 2016) (AD 2016–25–19) 

and add a new AD. AD 2016–25–19 

applied to Airbus Helicopters Model 

AS350B3 and EC130B4 helicopters with 

an ARRIEL 2B1 engine with the twochannel Full Authority Digital Engine 

Control (FADEC) and with new twist 

grip modification (MOD) 073254 (for the 

Model AS350B3 helicopter) or MOD 

073773 (for the Model EC130B4 

helicopter). AD 2016–25–19 required 

repetitively inspecting the wiring, 

performing an insulation test, inspecting 

the pilot and copilot throttle twist grip 

controls, and testing the pilot and 

copilot throttle twist grip controls for 

proper functioning. The actions 

required in AD 2016–25–19 were 

intended to prevent unintended 

touchdown to the ground at a flight-idle 

power setting during a practice 

autorotation, damage to the helicopter, 

and injury to occupants. 

The NPRM published in the Federal 

Register on August 8, 2018 (83 FR 

39007). The NPRM proposed to retain 

the requirements of AD 2016–25–19 and 

expand the applicability by adding 

Model AS350B3 helicopters with an 

ARRIEL 2D engine installed and Model 

EC130T2 helicopters with an ARRIEL 

2D engine installed. 

The NPRM was prompted by AD No. 

2017–0059, dated April 6, 2017 (EASA 

AD 2017–0059), issued by EASA, which 

is the Technical Agent for the Member 

States of the European Union, for Airbus 

Helicopters Model AS 350 B3, EC 130 

B4, and EC 130 T2 helicopters. EASA 

advises that Airbus Helicopters added 

clarifications to the operational 

procedure, introduced a modification to 

apply water-tight protection to the 

microswitch connectors, and extended 

the applicability to helicopters with a 

Turbomeca ARRIEL 2D engine installed. 

Accordingly, EASA AD 2017–0059 

retains the required actions and corrects 

the applicability of the previous EASA 

AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

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 its 

AD. We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 


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