39004 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 

50Proposed revisions to OMB control number 

3133–0191 have been submitted to OMB for 

approval in accordance with 5 CFR 1320.11. 

information collection. The NCUA may 

not conduct or sponsor, and the 

respondent is not required to respond 

to, an information collection unless it 

displays a currently valid Office of 

Management and Budget (OMB) control 

number. 

The proposed changes to part 702 

would increase the asset size of credit 

unions identified as complex from 

greater than $100 million to greater than 

$500 million. This change would reduce 

the number of credit unions who must 

comply with recordkeeping 

requirements prescribed by § 702.101(b). 

Therefore, the burden cleared under 

OMB number 3133–0191 will be revised 

to reflect the reduction in the number of 

respondents.50

Title of Information Collection: 

Prompt Corrective Action—Risk-Based 

Capital. 

OMB Control Number: 3133–0191. 

Affected Public: Private Sector: Notfor-profit institutions—Complex Credit 

Unions. 

Estimated Number of Respondents: 

531. 

Estimated Number of Responses per 

Respondent: 1. 

Estimated Hours per Response: 40. 

Estimated Total Annual Burden 

Hours: 21,240. 

By exempting credit unions with 

assets between $100 million and $500 

million, the NCUA estimates that the 

burden under this proposed rule would 

be 41,040 fewer hours. 

The Board invites comment on (a) 

whether the collections of information 

are necessary for the proper 

performance of the agency’s function, 

including practical utility; (b) the 

accuracy of estimates of the burden of 

the information collections, including 

the validity of the methodology and 

assumptions used; (c) ways to enhance 

the quality, utility, and clarity of the 

information being collected, and (d) 

ways to minimize the burden of the 

information collection on respondents, 

including through the use of automated 

collection techniques or other forms of 

information technology. 

All comments are a matter of public 

record. Comments regarding the 

information collection requirements of 

this rule should be sent to (1) Dawn 

Wolfgang, NCUA PRA Clearance 

Officer, National Credit Union 

Administration, 1775 Duke Street, Suite 

5080, Alexandria, Virginia 22314, or Fax 

No. 703–519–8572, or Email at 

PRAcomments@ncua.gov and the (2) 

Office of Information and Regulatory 

Affairs, Office of Management and 

Budget, Attention: Desk Officer for 

NCUA, New Executive Office Building, 

Room 10235, Washington, DC 20503, or 

email at 

OIRA_Submission,@OMB.EOP.gov. 

Submission of comments. The NCUA 

considers comments by the public on 

this proposed collection of information 

in: 

• Evaluating whether the proposed 

collection of information is necessary 

for the proper performance of the 

functions of the NCUA, including 

whether the information will have a 

practical use; 

• Evaluating the accuracy of the 

NCUA’s estimate of the burden of the 

proposed collection of information, 

including the validity of the 

methodology and assumptions used; 

• Enhancing the quality, usefulness, 

and clarity of the information to be 

collected; and 

• Minimizing the burden of collection 

of information on those who are to 

respond, including through the use of 

appropriate automated, electronic, 

mechanical, or other technological 

collection techniques or other forms of 

information technology; e.g., permitting 

electronic submission of responses. 

Executive Order 13132 

Executive Order 13132 encourages 

independent regulatory agencies to 

consider the impact of their actions on 

state and local interests. The NCUA, an 

independent regulatory agency as 

defined in 44 U.S.C. 3502(5), voluntarily 

complies with the principles of the 

executive order to adhere to 

fundamental federalism principles. This 

proposed rule reduces the number of 

federally insured natural-person credit 

unions, including federally insured, 

state-chartered natural-person credit 

unions that would be subject to the 2015 

Final Rule. It may have, to some degree, 

a 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. It does not, 

however, rise to the level of material 

impact for purposed of Executive Order 

13132. 

Assessment of Federal Regulations and 

Policies on Families 

The NCUA has determined that this 

proposed rule will not affect family 

well-being within the meaning of 

section 654 of the Treasury and General 

Government Appropriations Act, 1999, 

Public Law 105–277, 112 Stat. 2681 

(1998). 

List of Subjects in 12 CFR Part 702 

Credit unions, Reporting and 

recordkeeping requirements. 

By the National Credit Union 

Administration Board on August 2, 2018. 

Gerard Poliquin, 

Secretary of the Board. 

For the reasons discussed above, the 

Board proposes to further amend 12 

CFR part 702, as amended in a final rule 

at 80 FR 66625 (Oct. 29, 2015), effective 

January 1, 2019, as follows: 

PART 702—CAPITAL ADEQUACY 

■ 1. The authority citation for part 702 

continues to read as follows: 

Authority: 12 U.S.C. 1766(a), 1790d. 

§ 702.103 [Amended] 

■ 2. Amend § 702.103 by removing the 

words ‘‘one hundred million dollars 

($100,000,000)’’ and add in their place 

‘‘five hundred million dollars 

($500,000,000).’’ 

[FR Doc. 2018–16888 Filed 8–7–18; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0722; Product 

Identifier 2017–SW–104–AD 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2015–22– 

02 for Bell Helicopter Textron Canada 

Limited (Bell) Model 429 helicopters. 

AD 2015–22–02 requires inspecting the 

tail rotor (TR) pitch link assemblies. 

This proposed AD would retain the 

inspections of AD 2015–22–02 and 

would require replacing certain pitch 

link bearings. Since we issued AD 

2015–22–02, Bell has introduced a new 

design bearing. The actions of this 

proposed AD are intended to prevent an 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 9, 2018. 

ADDRESSES: You may send comments by 

any of the following methods: 


amozie on DSK3GDR082PROD with PROPOSALS
Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 39005 

• 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 by searching for 

and locating Docket No. FAA–2018– 

0722; 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 proposed 

AD, the Transport Canada AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(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 final rule, 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, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. 

FOR FURTHER INFORMATION CONTACT: 

David Hatfield, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

david.hatfield@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 

We issued AD 2015–22–02, 

Amendment 39–18306 (80 FR 65618, 

October 27, 2015) (AD 2015–22–02), for 

Bell Model 429 helicopters with a TR 

pitch link assembly part number (P/N) 

429–112–101 or 429–112–103 installed. 

AD 2015–22–02 requires repetitively 

inspecting each inboard and outboard 

TR pitch link assembly for axial or 

radial bearing play every 50 hours timein-service (TIS), performing a 

dimensional inspection of the TR pitch 

link if there is axial or radial bearing 

play, and replacing the TR pitch link 

before further flight if there is any wear 

beyond allowable limits. AD 2015–22– 

02 was prompted by Emergency AD No. 

CF–2015–16, dated July 2, 2015, and 

Emergency AD No. CF–2015–16R1, 

dated August 6, 2015, issued by 

Transport Canada, to correct an unsafe 

condition for Bell Model 429 

helicopters. Transport Canada advised 

of several occasions where the TR pitch 

link spherical bearings experienced 

early and accelerated wear. 

Actions Since AD 2015–22–02 Was 

Issued 

Since we issued AD 2015–22–02, 

Transport Canada has issued AD No. 

CF–2015–16R2, dated April 17, 2017, 

which supersedes AD CF–2015–16R1. 

According to Transport Canada, Bell has 

reported that the TR pitch link assembly 

can be rotated during the 50-hour 

inspections to extend the serviceability 

life of the bearings. Transport Canada 

AD No. CF–2015–16R2 requires 

modified inspection procedures for the 

spherical bearings and requires 

replacing the TR pitch link bearings (or 

the TR pitch link assembly) with 

spherical bearings manufactured after 

January 12, 2015. Transport Canada AD 

No. CF–2015–16R2 also requires reidentifying TR pitch link assemblies 

with a different P/N after installing the 

new bearings. We propose to issue this 

AD to make similar changes. 

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, Transport 

Canada, its technical representative, has 

notified us of the unsafe condition 

described in the Transport Canada AD. 

We are proposing this AD because we 

evaluated all information provided by 

Transport Canada and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Related Service Information 

Bell has issued Alert Service Bulletin 

No. 429–15–16, Revision B, dated June 

15, 2016. This service information 

contains procedures for repetitively 

inspecting the TR pitch link assembly 

until it is upgraded by replacing the TR 

pitch link bearings. 

AD Requirements 

This proposed AD would require 

performing a dimensional inspection of 

the spherical bearings for axial and 

radial play and inspecting the TR pitch 

link assembly sealant for pin holes, 

voids, and excessive thickness. These 

inspections would be required within 

50 hours TIS and thereafter at intervals 

not exceeding 50 hours TIS. 

This proposed AD would also require 

replacing any spherical bearing 

manufactured before January 13, 2015, 

that has exceeded 250 hours TIS or that 

has an unknown number of hours TIS, 

and re-identifying the P/N of the TR 

pitch link assembly. 

Differences Between This Proposed AD 

and the Transport Canada AD 

The Transport Canada AD requires 

the bearing inspection within 10 hours 

TIS or before exceeding 60 hours TIS 

since new, whichever occurs later. This 

proposed AD would require the bearing 

inspection within 50 hours TIS. The 

Transport Canada AD also requires 

replacing certain bearings within 200 

hours TIS after the initial bearing 

inspection or within 250 hours TIS 

since new, whichever occurs first. This 

proposed AD would require replacing 

the bearing within 200 hours of the 

initial inspection or at the next 50 hour 

TIS inspection if the hours TIS of a 

pitch link assembly exceed 250 hours 

TIS or are unknown. 

Interim Action 

We consider this proposed AD to be 

an interim action. If final action is later 


amozie on DSK3GDR082PROD with PROPOSALS
39006 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 

identified, we might consider further 

rulemaking then. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 85 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this proposed AD. At an 

average labor rate of $85 per hour, 

inspecting the TR pitch link assemblies 

would require 2 work-hours for a cost of 

$170 per helicopter and $14,450 for the 

U.S. fleet per inspection cycle. 

Replacing both spherical bearings in 

each TR pitch link assembly would 

require 3 work-hours, and required parts 

would cost $3,088, for a cost of $3,343 

per helicopter and $284,155 for the U.S. 

fleet. 

According to Bell’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 Bell. 

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 

will not have federalism implications 

under Executive Order 13132. This 

proposed 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 proposed regulation: 

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 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 

removing Airworthiness Directive (AD) 

2015–22–02, Amendment 39–18306 (80 

FR 65618, October 27, 2015), and 

adding the following new AD: 

Bell Helicopter Textron Canada Limited: 

Docket No. FAA–2018–0722; Product 

Identifier 2017–SW–104–AD. 

(a) Applicability 

This AD applies to Model 429 helicopters 

with a pitch link assembly part number 

(P/N) 429–012–112–101, 429–012–112–103, 

429–012–112–101FM, or 429–012–112– 

103FM installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

worn pitch link. This condition, if not 

corrected, could result in pitch link failure 

and subsequent loss of control of the 

helicopter. 

(c) Affected ADs 

This AD replaces AD 2015–22–02, 

Amendment 39–18306 (80 FR 65618, October 

27, 2015). 

(d) Comments Due Date 

We must receive comments by October 9, 

2018. 

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

and thereafter at intervals not to exceed 50 

hours TIS: 

(i) Perform a dimensional inspection of 

each inboard and outboard pitch link 

assembly for axial and radial bearing play. 

With a 10X or higher power magnifying glass, 

inspect the bearing liner for a crack, 

deterioration of the liner, and extrusion of 

the liner from the plane. If there is axial or 

radial play that exceeds allowable limits, or 

if there is a crack, deterioration of the liner, 

or extrusion of the liner, before further flight, 

replace the bearing. 

(ii) Inspect the pitch link assembly sealant 

for pin holes and voids and to determine if 

the sealant thickness is 0.025 inch (0.64 mm) 

or less, extends over the roll staked lip by 

0.030 inch (0.76 mm) or more, and is clear 

of the bearing ball. If there is a pin hole or 

void, or if the sealant exceeds 0.026 inch 

(0.66 mm), does not extend over the roll 

staked lip by 0.030 inch (0.76 mm) or more, 

or is not clear of the bearing ball, before 

further flight, replace the bearing. 

(2) For pitch link assembly part number 

(P/N) 429–012–112–101, 429–012–112–103, 

429–012–112–101FM, and 429–012–112– 

103FM, within 200 hours TIS following the 

initial inspection required by paragraph (f)(1) 

of this AD, or if the hours TIS of a pitch link 

assembly exceed 250 hours TIS or are 

unknown, at the next 50 hour TIS inspection 

required by paragraph (f)(1) of this AD: 

(i) Replace each bearing P/N 429–312–107– 

103 with a date of manufacture before 

January 13, 2015, with a bearing P/N 429– 

312–107–103 that was manufactured on or 

after January 13, 2015. 

(ii) Using a white permanent fine point 

marker or equivalent, re-identify the pitch 

link assembly: 

(A) Re-identify P/N 429–012–112–101 and 

429–012–112–101FM as 429–012–112– 

111FM. 

(B) Re-identify P/N 429–012–112–103 and 

429–012–112–103FM as 429–012–112– 

113FM. 

(iii) Apply a coating of DEVCON 2–TON 

(C–298) or equivalent over the new P/N. 

(g) Special Flight Permits 

Special flight permits are prohibited. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, Rotorcraft Standards Branch, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: David Hatfield, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@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. 


amozie on DSK3GDR082PROD with PROPOSALS
Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Proposed Rules 39007 

(i) Additional Information 

(1) Bell Alert Service Bulletin No. 429–15– 

16, Revision B, dated June 15, 2016, which 

is not incorporated by reference, contains 

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, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 

(2) The subject of this AD is addressed in 

Transport Canada AD No. CF–2015–16R2, 

dated April 17, 2017. You may view the 

Transport Canada AD on the internet at 

http://www.regulations.gov in the AD Docket. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720 Tail Rotor Control System. 

Issued in Fort Worth, Texas, on July 23, 

2018. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2018–16637 Filed 8–7–18; 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] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2016–25– 

19 for Airbus Helicopters (previously 

Eurocopter France) Model AS350B3 and 

EC130B4 helicopters. AD 2016–25–19 

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

operation. This proposed AD would 

retain the requirements of AD 2016–25– 

19 and add certain model helicopters to 

the applicability. The actions of this 

proposed AD are intended to address 

the unsafe condition on these 

helicopters. 

DATES: We must receive comments on 

this proposed AD by October 9, 2018. 

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 by searching for 

and locating 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 proposed 

AD, the European Aviation Safety 

Agency (EASA) AD, the economic 

evaluation, any comments received and 

other information. The street address for 

Docket Operations (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 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 review service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. 

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: 

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 

We issued AD 2016–25–19, 

Amendment 39–18745 (81 FR 95854, 

December 29, 2016) (AD 2016–25–19), 

for Airbus Helicopters Model AS350B3 

and EC130B4 helicopters with the 

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 requires 

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. AD 2016–25–19 was 

prompted by AD No. 2013–0191–E, 

dated August 22, 2013 (EASA AD 2013– 

0191–E), issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union. EASA advised 

that the switches in the engine ‘‘IDLE’’ 

or ‘‘FLIGHT’’ control system could be 

affected by the corrosive effects of a saltladen atmosphere, which could lead to 

engine power loss. EASA AD 2013– 

0191–E required repetitive inspections 

for corrosion, application of corrosion 

protection on the switches, and testing 

of the insulation and switches of the 

engine idle and flight control system. 

The actions required in AD 2016–25–19 

are 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. 

Actions Since AD 2016–25–19 Was 

Issued 

Since we issued AD 2016–25–19, 

EASA issued AD No. 2017–0052, dated 

March 24, 2017, which superseded 

EASA AD No. 2013–0191–E, dated 

August 22, 2013. EASA advised that 

Airbus Helicopters had added 


amozie on DSK3GDR082PROD with PROPOSALS