This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

42487 

Vol. 82, No. 173 

Friday, September 8, 2017 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0826; Product 

Identifier 2016–SW–084–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2015–22– 

53 for Airbus Helicopters (Airbus) 

Model AS350B3 helicopters. AD 2015– 

22–53 requires revising the rotorcraft 

flight manual (RFM) to perform the yaw 

load compensator check after rotor shutdown and to state that the yaw servo 

hydraulic switch must be in the ‘‘ON’’ 

position before taking off. Since we 

issued AD 2015–22–53, Airbus 

developed a modification of the ACCU 

TST switch. This proposed AD would 

retain the requirements of AD 2015–22– 

53 and require modifying the yaw servo 

hydraulic switch (collective switch) and 

replacing the ACCU TST button. The 

actions of this proposed AD are 

intended to address an unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by November 7, 2017. 

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–2017– 

0826; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed 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: 

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 

On November 13, 2015, we issued AD 

2015–22–53, Amendment 39–18331 (80 

FR 74982, December 1, 2015), which 

was sent previously as an emergency 

AD to all known U.S. owners and 

operators of Airbus Helicopters Model 

AS350B3 helicopters. AD 2015–22–53 

requires revising the pre-flight and postflight procedures in the RFM to perform 

the yaw load compensator check (ACCU 

TST switch) after rotor shut-down 

instead of during preflight procedures 

and to state that the yaw servo hydraulic 

switch (collective switch) must be in the 

‘‘ON’’ (forward) position before taking 

off. AD 2015–22–53 was prompted by 

two accidents and one incident of 

Model AS350B3 helicopters with a dual 

hydraulic system installed, and which 

also prompted EASA, which is the 

Technical Agent for the Member States 

of the European Union, to issue EASA 

AD No. 2015–0178, dated August 26, 

2015. EASA advised these occurrences 

may have resulted from improperly 

performing the T/R hydraulic preflight 

check (a pilot forgetting to put the yaw 

servo hydraulic switch (collective 

switch) in the ‘‘ON’’ position or put the 

ACCU TST switch in the ‘‘OFF’’ 

position before flight)—and not from 

equipment failure. According to EASA, 

these conditions significantly increase 

the control load necessary to generate 

sufficient tail rotor thrust for take-off. 

Actions Since AD 2015–22–53 Was 

Issued 

Since we issued AD 2015–22–53, 

Airbus Helicopters issued SB No. 

AS350–67.00.65, Revision 0, dated 

August 25, 2016, which specifies 

procedures to alter the ACCU TST 

switch. Subsequently, EASA issued AD 

No. 2016–0220, dated November 4, 

2016. EASA advises that further 


sradovich on DSK3GMQ082PROD with PROPOSALS
42488 Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Proposed Rules 

analysis of the incidents resulted in the 

recognition that a pilot could forget to 

activate a switch despite the RFM 

changes and that the modifications 

developed by Airbus Helicopters are 

necessary. Accordingly, EASA AD No. 

2016–0220 requires installing a caution 

indication to the pilot when the yaw 

servo hydraulic switch (collective 

switch) is in the ‘‘OFF’’ position, 

installing an additional indicator light 

on the caution and warning panel, and 

replacing the bistable push button 

(push-on, push-off) ACCU TST switch 

with a monostable push button (pushon, timer-off) switch. 

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 are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Helicopters SB 

No. AS350–67.00.64, Revision 0, dated 

February 25, 2015, which specifies 

procedures to install a timer relay and 

an additional indicator light on the 

caution and warning panel. This 

modification provides an ‘‘OFF’’ status 

indication of the yaw servo hydraulic 

switch (collective switch) by flashing a 

newly installed ‘‘HYD2’’ indicator light 

on the caution and warning panel. 

Airbus Helicopters identifies 

performance of this SB as modification 

074622. This modification was available 

when AD 2015–22–53 was issued; 

however, it was determined 

unnecessary to address the unsafe 

condition at that time. 

We also reviewed Airbus Helicopters 

SB No. AS350–67.00.65, Revision 0, 

dated August 25, 2016, which specifies 

procedures to replace the bistable push 

button ACCU TST switch with a 

monostable push button switch. Airbus 

Helicopters identifies performance of 

this SB as modification 074719. 

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 reviewed Airbus SB No. AS350– 

67.00.66, Revision 1, dated October 22, 

2015, which specifies inserting specific 

pages of the SB into the rotorcraft flight 

manual. These pages revise the preflight 

and post-flight hydraulic checks by 

moving the tail rotor yaw load 

compensator check from preflight to 

post-flight. These pages also revise 

terminology within the flight manuals 

for the different engine configurations. 

Proposed AD Requirements 

This proposed AD would retain the 

RFM revision that moves the yaw load 

compensator check (ACCU TST switch) 

from preflight procedures to post-flight 

procedures after rotor shut-down. This 

proposed AD would also retain the RFM 

revision that requires the yaw servo 

hydraulic switch (collective switch) to 

be in the ‘‘ON’’ (forward) position before 

taking off. 

Additionally, this proposed AD 

would require, within 350 hours timein-service, installing a timer relay for 

the yaw servo hydraulic switch 

(collective switch) and installing an 

additional light on the caution and 

warning panel. This proposed AD 

would also require replacing the 

bistable ACCU TST button with a 

monostable button. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 86 helicopters of U.S. 

Registry. We estimate that operators 

may incur the following costs in order 

to comply with this AD. Labor costs are 

estimated at $85 per work-hour. 

Revising an RFM would take about 

0.5 work-hour for a cost of $43 per 

helicopter and $3,698 for the U.S. fleet. 

Installing a timer relay for the yaw servo 

hydraulic switch (collective switch) and 

an indicator light would take about 9 

work-hours and parts would cost about 

$2,224. Replacing the ACCU TST button 

would take about 1 work-hour and parts 

would cost about $2,244. 

Based on these figures, we estimate a 

total cost of $5,361 per helicopter and 

$461,046 for the U.S. fleet. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2015–22–53, Amendment 39–18331 (80 

FR 74982, December 1, 2015), and 

adding the following new AD: 

Airbus Helicopters: Docket No. FAA–2017– 

0826; Product Identifier 2016–SW–084– 

AD. 


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Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Proposed Rules 42489 

(a) Applicability 

This AD applies to Model AS350B3 

helicopters with a dual hydraulic system 

installed, certificated in any category. 

Note 1 to paragraph (a) of this AD: The 

dual hydraulic system for Model AS350B3 

helicopters is referred to as Airbus 

modification OP 3082 or OP 3346. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

lack of hydraulic pressure in a tail rotor 

(T/R) hydraulic system. This condition could 

result in loss of T/R flight control and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2015–22–53, 

Amendment 39–18331 (80 FR 74982, 

December 1, 2015). 

(d) Comments Due Date 

We must receive comments by November 

7, 2017. 

(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) Before further flight, insert a copy of 

this AD into the rotorcraft flight manual, 

Section 4 Normal Operating Procedures, or 

make pen and ink changes to the preflight 

and post-flight procedures as follows: 

(i) Stop performing the yaw load 

compensator check (ACCU TST switch) 

during preflight procedures, and instead 

perform the yaw load compensator check 

during post-flight procedures after rotor shutdown. 

(ii) The yaw servo hydraulic switch 

(collective switch) must be in the ‘‘ON’’ 

(forward) position before takeoff. 

Note 2 to paragraph (f)(1)(ii) of this AD: 

The yaw servo hydraulic switch is also called 

the hydraulic pressure switch or hydraulic 

cut off switch in various Airbus Helicopters 

rotorcraft flight manuals. 

(2) Within 350 hours time-in-service: 

(i) Install a timer relay for the yaw servo 

hydraulic switch (collective switch) by 

following the Accomplishment Instructions, 

paragraph 3.B.2.b.1, 3.B.2.b.2, 3.B.2.b.3, 

3.B.2.b.4, 3.B.2.b.5, or 3.B.2.b.6, as applicable 

to the configuration of your helicopter, of 

Airbus Helicopters Service Bulletin (SB) No. 

AS350–67.00.64, Revision 0, dated February 

25, 2015 (AS350–67.00.64). If your helicopter 

has an automatic pilot system, also comply 

with paragraph 3.B.2.b.7 of AS350–67.00.64. 

(ii) Install an indicator light on the caution 

and warning panel by following the 

Accomplishment Instructions, paragraph 

3.B.2.c.1 or 3.B.2.c.2, as applicable to the 

configuration of your helicopter, of AS350– 

67.00.64. 

(iii) Replace the bistable ACCU TST button 

on the control panel with a monostable 

button as depicted in Figure 1 or Figure 3, 

as applicable to the configuration of your 

helicopter, of Airbus Helicopters SB No. 

AS350–67.00.65, Revision 0, dated August 

25, 2016. 

(3) After the effective date of this AD, do 

not install a bistable ACCU TST button on 

any helicopter. 

(g) Special Flight Permits 

A special flight permit may be issued for 

paragraph (f)(2) of this AD only. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Section, FAA, may approve AMOCs for this 

AD. Send your proposal to: George Schwab, 

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. 

(i) Additional Information 

(1) Airbus Helicopters SB No. AS350– 

67.00.66, Revision 1, dated October 22, 2015, 

which is not incorporated by reference, 

contains 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 the referenced 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) AD 

No. 2016–0220, dated November 4, 2016. 

You may view the EASA AD on the Internet 

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

Docket. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2910, Main Hydraulic System. 

Issued in Fort Worth, Texas, on August 29, 

2017. 

Scott A. Horn, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2017–18973 Filed 9–7–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0867; Product 

Identifier 2017–CE–021–AD] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Viking Air Limited Models DHC–2 Mk. 

I, DHC–2 Mk. II, and DHC–2 Mk. III 

airplanes. This proposed AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as cracking found in the wing 

rear spar web at the wing station where 

the flap outboard hinge is attached. We 

are issuing this proposed AD to require 

actions to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by October 23, 2017. 

ADDRESSES: You may send comments 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 proposed AD, contact Viking Air 

Limited Technical Support, 1959 De 

Havilland Way, Sidney, British 

Columbia, Canada, V8L 5V5; telephone: 

(North America) (800) 663–8444; fax: 

(250) 656–0673; email: 

technical.support@vikingair.com; 

Internet: http://www.vikingair.com/ 

support/service-bulletins. You may 

review this referenced service 

information at the FAA, Policy and 

Innovation Division, 901 Locust, Kansas 


sradovich on DSK3GMQ082PROD with PROPOSALS