Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34029 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0091; Product 

Identifier 2017–SW–054–AD; Amendment 

39–19334; AD 2018–15–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS350B, AS350B1, 

AS350B2, AS350B3, AS350BA, AS355E, 

AS355F, AS355F1, AS355F2, AS355N, 

and AS355NP helicopters. This AD 

requires inspecting the tail rotor (TR) 

pitch rod. This AD is prompted by a 

report of several cases of damaged TR 

pitch rod ball joints. The actions of this 

AD are intended to correct an unsafe 

condition on these helicopters. 

DATES: This AD becomes effective 

August 3, 2018. 

We must receive comments on this 

AD by September 17, 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– 

0091; 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, 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 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 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 

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 Emergency AD No. 

2017–0020–E, dated February 7, 2017, 

to correct an unsafe condition for Airbus 

Helicopters Model AS 350 B, AS 350 

BA, AS 350 BB, AS 350 B1, AS 350 B2, 

AS 350 B3, AS 355 E, AS 355 F, AS 355 

F1, AS 355 F2, AS 355 N and AS 355 

NP helicopters with modification 

(MOD) 075601 or MOD 076602 

installed. EASA advises of several 

reports of damaged horn-side TR pitch 

rod elastomeric ball joints, and of an ongoing investigation to determine the 

cause of the damage. EASA states that 

this condition could result in loss of 

control of the helicopter. To address this 

unsafe condition, the EASA AD requires 

repetitive inspections of the TR pitch 

rod. While the inspections are contained 

in the Airworthiness Limitations 

Section of the helicopter maintenance 

manual, the EASA AD reduces the 

interval from 50 flight hours to 10 flight 

hours. 

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. 

Related Service Information 

We reviewed Airbus Helicopters 

Emergency Alert Service Bulletin 

(EASB) No. 05.00.86 for Model AS350- 

series helicopters and EASB No. 

05.00.75 for Model AS355-series 

helicopters, both Revision 1 and both 

dated February 6, 2017. This service 

information contains procedures for 

inspecting the TR pitch change rod 

elastomeric ball joint for damage. 

AD Requirements 

This AD requires, for helicopters with 

a TR pitch change rod elastomeric ball 

joint installed, within 10 hours time-inservice (TIS) and thereafter at intervals 

not exceeding 10 hours TIS, inspecting 

each face of the TR pitch rod blade side 

ball joint for debonding, extrusion, and 

a crack. If there is debonding, extrusion, 

or a crack with a circumference of 90 

degrees or more, this AD requires 

replacing the TR pitch rod before further 

flight. Airbus Helicopters identifies the 

installation of a TR pitch change rod 

elastomeric ball joint as MOD 075601 or 

MOD 076602. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to Airbus 

Helicopters Model AS 350 BB 

helicopters. This AD does not as that 

model is not type-certificated in the U.S. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 


sradovich on DSK3GMQ082PROD with RULES
34030 Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 

we might consider further rulemaking 

then. 

Costs of Compliance 

We estimate that this AD affects 896 

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, inspecting the TR pitch 

rod ball joint requires 0.5 hour, for a 

cost of $43 per helicopter and $38,528 

for the U.S. fleet, per inspection cycle. 

If required, replacing a TR pitch rod 

requires one work-hour and required 

parts cost $3,174, for a cost per 

helicopter of $3,259. 

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 because the inspections required by 

this AD must be accomplished within 

10 hours TIS and thereafter every 10 

hours TIS. Therefore, we find good 

cause that notice and opportunity for 

prior public comment are impracticable. 

In addition, for the reason stated above, 

we find 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): 

2018–15–02 Airbus Helicopters: 

Amendment 39–19334; Docket No. 

FAA–2018–0091; Product Identifier 

2017–SW–054–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model AS350B, AS350B1, AS350B2, 

AS350B3, AS350BA, AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and AS355NP 

helicopters, certificated in any category, with 

a tail rotor (TR) pitch change rod elastomeric 

ball joint installed. 

Note 1 to paragraph (a): Airbus Helicopters 

modification (MOD) 075601 and MOD 

076602 consist of replacing the TR pitch 

change rod with an elastomeric ball joint rod. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

damaged elastomeric ball joint on the TR 

pitch change rod. This condition could result 

in failure of the TR pitch change rod and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective August 3, 2018. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 10 hours time-in-service (TIS) and 

thereafter at intervals not exceeding 10 hours 

TIS: 

(1) Manually induce a flapping movement 

in the TR blade until the pitch change rod 

rotates a minimum of 10 degrees. 

(2) Inspect both faces of the blade side of 

the ball joint elastomer for debonding, 

extrusion, and cracks. If there is a crack or 

any debonding or extrusion with a 

circumference of 90 or more degrees, before 

further flight, replace the pitch change rod. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) 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–ASW– 

FTW–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. 

(h) Additional Information 

(1) Airbus Helicopters Emergency Alert 

Service Bulletin (EASB) No. 05.00.86 and 

EASB No. 05.00.75, both Revision 1 and both 

dated February 6, 2017, 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, 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 

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 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2017–0020–E, dated 

February 7, 2017. You may view the EASA 

Emergency AD on the internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2018–0091. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720 Tail Rotor Control System. 


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Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations 34031 

Issued in Fort Worth, Texas, on July 6, 

2018. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2018–15303 Filed 7–18–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0166; Product 

Identifier 2017–NM–169–AD; Amendment 

39–19331; AD 2018–14–11] 

RIN 2120–AA64 

Airworthiness Directives; ATR–GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

ATR–GIE Avions de Transport Re ́gional 

Model ATR72 airplanes. This AD was 

prompted by a determination that more 

restrictive maintenance instructions and 

airworthiness limitations are necessary. 

This AD requires revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised maintenance instructions and 

airworthiness limitations. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 23, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 23, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

ATR–GIE Avions de Transport Re ́gional, 

1, Alle ́e Pierre Nadot, 31712 Blagnac 

Cedex, France; telephone +33 (0) 5 62 

21 62 21; fax +33 (0) 5 62 21 67 18; 

email continued.airworthiness@atraircraft.com. You may view this service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0166. 

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– 

0166; 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 address for Docket 

Operations (phone: 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Section, 

Transport Standards Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3220. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all ATR–GIE Avions de 

Transport Re ́gional Model ATR72 

airplanes. The NPRM published in the 

Federal Register on March 22, 2018 (83 

FR 12508). The NPRM was prompted by 

a determination that more restrictive 

maintenance instructions and 

airworthiness limitations are necessary. 

The NPRM proposed to require revising 

the maintenance or inspection program, 

as applicable, to incorporate new or 

revised maintenance instructions and 

airworthiness limitations. We are 

issuing this AD to address fatigue 

cracking, damage, and corrosion in 

principal structural elements, which 

could result in reduced structural 

integrity of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017– 

0223R1, dated December 15, 2017 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all ATR–GIE Avions de 

Transport Re ́gional Model ATR72 

airplanes. The MCAI states: 

The airworthiness limitations and 

certification maintenance requirements 

(CMR) for ATR aeroplanes, which are 

approved by EASA, are currently defined and 

published in the ATR72–101/–201/–102/– 

202/–211/–212/–212A Time Limits (TL) 

document. These instructions have been 

identified as mandatory actions for continued 

airworthiness. 

Failure to accomplish these instructions 

could result in an unsafe condition. 

Consequently, ATR published Revision 15 

of the ATR72–101/–201/–102/–202/–211/– 

212/–212A TL document, which contains 

new and/or more restrictive CMRs and 

airworthiness limitation tasks. 

For the reasons described above, this 

[EASA] AD requires accomplishment of the 

actions specified in the ATR72–101/–201/– 

102/–202/–211/–212/–212A TL document 

Revision 15, hereafter referred to as ‘the TLD’ 

in this [EASA] AD. 

This [EASA] AD, in conjunction with two 

other [EASA] ADs related to ATR42–200/– 

300/–320 (EASA AD 2017–0221) and 

ATR42–400/–500 (EASA AD 2017–0222) 

aeroplanes, retains the requirements of EASA 

AD 2009–0241 and EASA AD 2012–0193. 

Once all these three ADs are effective, EASA 

will cancel EASA AD 2009–0242 and EASA 

AD 2012–0193. 

This [EASA] AD is revised to provide the 

correct issue date (02 May 2017) of the TLD. 

The original [EASA] AD inadvertently 

referenced the EASA approval date for that 

document. 

This AD requires revising the 

maintenance or inspection program to 

incorporate certain maintenance 

instructions and airworthiness 

limitations. The unsafe condition is 

fatigue cracking, damage, and corrosion 

in principal structural elements, which 

could result in reduced structural 

integrity of the airplane. You may 

examine the MCAI in the AD docket on 

the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0166. 

Comment 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comment 

received on the NPRM and the FAA’s 

response. 

Request To Correct Typographical 

Error 

Empire Airlines asked that 

airworthiness limitations (AWL) task 

number 572401–1, identified in table 1 

to paragraph (h) of this AD, be changed 

to AWL task number 572402–1. Empire 

Airlines stated that AWL task number 

572401–1 corresponds to maintenance 

review board report (MRBR) task 

numbers ZL–500–01–1 and ZL–600–01– 

1; and the MRBR task numbers ZL–520– 

01–1 and ZL–620–01–1, identified in 

table 1 to paragraph (h) of this AD, 

correspond with AWL task number 

572402–1. Empire Airlines provided 

substantiation data to this effect. 

We agree with the commenter that a 

typographical error was made in the 

AWL task number 572401–1, identified 

in table 1 to paragraph (h) of this AD. 

We have corrected this error 

accordingly. 


sradovich on DSK3GMQ082PROD with RULES