74362 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 

any category, serial numbers 003 through 672 

inclusive, on which Bombardier ModSum 

8Q100813 or Bombardier Service Bulletin 8– 

74–02 is incorporated. 

(1) Model DHC–8–102, –103, and –106 

airplanes. 

(2) Model DHC–8–201 and –202 airplanes. 

(3) Model DHC–8–301, –311, and –315 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 74, Ignition. 

(e) Reason 

This AD was prompted by reports of 

incorrect installation of the auto-ignition 

system due to crossed wires at one of the 

splices in the auto-relight system. We are 

issuing this AD to detect and correct 

incorrect wiring of the auto-ignition system, 

which could result in inability to restart the 

engine in flight and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Actions 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first: Inspect the auto-ignition system 

for correct wiring and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–74–05, Revision B, dated 

April 14, 2014. All applicable corrective 

actions must be done before further flight. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 8–74–05, dated July 12, 

2013; or Revision A, dated January 27, 2014. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–36, dated 

November 19, 2013, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2016–9299. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. You 

may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on October 

14, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–25664 Filed 10–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3343; Directorate 

Identifier 2015–SW–078–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) 2014–12– 

12 for Airbus Helicopters (previously 

Eurocopter France) Model EC130B4 and 

Model EC120B helicopters. AD 2014– 

12–12 currently requires inspecting and, 

if necessary, replacing parts of the 

sliding door star support attachment 

assembly. This proposed AD would 

expand the applicability and provide 

revised instructions for reinforcing the 

sliding door. These proposed actions are 

intended to prevent failure of the sliding 

door star support attachment, which 

could inhibit the operation of the 

sliding door from the inside, delaying 

the evacuation of passengers during an 

emergency. 

DATES: We must receive comments on 

this proposed AD by December 27, 

2016. 

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–2016– 

3343; 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.airbushelicopters.com/techpub. 

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: 

David Hatfield, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5116; 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 


Lhorne on DSK30JT082PROD with PROPOSALS
Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 74363 

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 June 13, 2014, we issued AD 

2014–12–12, Amendment 39–17873 (79 

FR 36638, June 30, 2014) for Airbus 

Helicopters Model EC120B helicopters 

with serial numbers up to and including 

1367 and with a sliding door part 

number (P/N) C526A2370101 installed 

and Model EC130B4 helicopters with 

sliding door P/N C526S1101051 

installed. AD 2014–12–12 does not 

apply to helicopters with modification 

(MOD) 07 3796 or 07 2921 installed. AD 

2014–12–12 requires inspecting the 

upper and lower locking pin control rod 

fittings and the star support pin for a 

crack and reinforcing the sliding door 

star support stringer by installing three 

carbon fabric plies. 

AD 2014–12–12 was prompted by AD 

No. 2013–0093, dated April 15, 2013, 

and corrected on April 17, 2013, issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union. EASA AD No. 2013–0093 was 

issued to correct an unsafe condition for 

Model EC120B and EC130B4 helicopters 

after a case was reported where 

passengers could not open a helicopter’s 

sliding door after landing. EASA advises 

that an investigation revealed a failure 

of the sliding door star axle support. 

Actions Since AD 2014–12–12 Was 

Issued 

Since we issued AD 2014–12–12, 

EASA has issued EASA AD No. 2015– 

0020, dated February 11, 2015, to 

correct an unsafe condition for Model 

EC120B helicopters with sliding door P/ 

N C526A2370101 and Model EC130B4 

helicopters sliding door P/N 

C526S1101051. EASA AD No. 2015– 

0020 does not apply to helicopters with 

MOD A00565, 07 3796, or 07 2921. 

EASA AD No. 2015–0020 supersedes 

EASA AD No. 2013–0093. EASA 

advises that after it issued AD No. 2013– 

0093, it discovered that the doors could 

be installed on all serial-numbered 

EC120B helicopters. Also, Eurocopter 

(now Airbus Helicopters) learned of 

difficulties with installing the angle 

bracket and plate used to reinforce the 

sliding door star support. Because of the 

distance between the star support pin 

and the bottom of the stringer on 

composite sliding doors, installation of 

the angle bracket and plate is not 

possible in a small number of sliding 

doors. Eurocopter subsequently revised 

its repair procedures to provide an 

alternate method for reinforcing the 

sliding door star support. 

EASA advises that it consequently 

issued AD No. 2015–0020 to extend the 

applicability to all serial-numbered 

EC120B helicopters with the affected 

sliding doors. EASA AD No. 2015–0020 

also requires compliance with the 

revised service information. 

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 Eurocopter (now Airbus 

Helicopters) Alert Service Bulletin 

(ASB) No. EC120–52A014, Revision 2, 

dated October 28, 2013, for Model 

EC120B helicopters and ASB No. 130– 

52A009, Revision 1, dated January 25, 

2013, for Model EC130B4 helicopters. 

This service information specifies visual 

and dye penetrant inspections of 

sections of the sliding door attachment 

assembly and reinforcement of the 

sliding door star support. ASB EC120– 

52A014 was changed at Revision 2 to 

expand the applicability for all serialnumbered Model 120B helicopters and 

provides an alternative procedure for 

reinforcing the sliding door star support. 

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. 

Proposed AD Requirements 

This proposed AD would require, 

within 165 hours time-in-service (TIS): 

• Visually inspecting each upper and 

lower locking pin control rod end fitting 

(control end fitting) and replacing it 

before further flight if it is bent, twisted, 

or broken. 

• Cleaning and dye-penetrant 

inspecting the star support pin for a 

crack and replacing it before further 

flight if it is cracked. 

• Reinforcing the sliding door star 

support stringer by installing three 

carbon fabric plies. 

This proposed AD would also 

prohibit installing a sliding door P/N 

C526A2370101 on a Model EC120B 

helicopter, or a sliding door P/N 

C526S1101051 on a Model EC130B4 

helicopter, unless the sliding door star 

support stringer is reinforced as 

required by this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 261 helicopters of U.S. 

Registry and that labor costs average $85 

a work hour. Based on these estimates, 

we expect the following costs: 

• Visually inspecting the control rod 

end fittings would require 1 work-hour 

and a minimal amount for consumable 

materials for an estimated cost of $85 

per helicopter, or $22,185 for the U.S. 

fleet. 

• Replacing the control rod end 

fittings with airworthy fittings would 

require 5 work-hours for a labor cost of 

$425. Parts would cost about $242 for an 

estimated total cost of $667 per 

helicopter. 

• Dye-penetrant inspecting the star 

support pin for a crack would require 2 

work-hours and no parts for an 

estimated cost of $170 per helicopter 

and $44,370 for the U.S. fleet. 

• Replacing the star support pin 

would require 5 work-hours. Parts 

would cost about $200 for an estimated 

total cost of $625 per helicopter. 

• Installing three carbon fabric plies 

to reinforce the sliding door star support 

would require 5 work-hours. Parts 

would cost $200 for an estimated total 

cost of $625 per helicopter and $163,125 

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, 


Lhorne on DSK30JT082PROD with PROPOSALS
74364 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 

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) 

2014–12–12, Amendment 39–17873 (79 

FR 36638, June 30, 2014), and adding 

the following new AD: 

Airbus Helicopters (Previously Eurocopter 

France): Docket No. FAA–2016–3343; 

Directorate Identifier 2015–SW–078–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category, 

except those with modification A00565, 07 

3796, or 07 2921 installed: 

(1) Model EC120B helicopters with a 

sliding door part number (P/N) 

C526A2370101 installed; and 

(2) Model EC130B4 helicopters with a 

sliding door P/N C526S1101051 installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

failure of the sliding door star axle support. 

This condition could prevent operation of a 

sliding door from inside, which could delay 

evacuation of passengers during an 

emergency. 

(c) Affected ADs 

This AD supersedes AD 2014–12–12, 

Amendment 39–17873 (79 FR 36638, June 

30, 2014). 

(d) Comments Due Date 

We must receive comments by December 

27, 2016. 

(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 165 hours time-in-service: 

(i) Visually inspect each upper and lower 

locking pin control rod end fitting (control 

end fitting) for a bend, twist, or breakage. If 

a control end fitting is bent, twisted, or 

broken, before further flight, replace the 

control end fitting with an airworthy control 

end fitting. 

(ii) Clean and dye penetrant inspect the 

star support pin for a crack in the areas 

identified as Zone X and Zone Y in Figure 

3 of Eurocopter Alert Service Bulletin No. 

EC120–52A014, Revision 2, dated October 

28, 2013 (ASB No. EC120–52A014) or 

Eurocopter Alert Service Bulletin No. EC130– 

52A009, Revision 1, dated January 25, 2013 

(ASB No. EC130–52A009), as applicable to 

your model helicopter. If there is a crack in 

the star support pin, before further flight, 

replace the star support pin with an 

airworthy star support pin. 

(iii) Reinforce the sliding door star support 

stringer by installing three carbon fiber plies 

and re-identify the sliding door by following 

the Accomplishment Instructions, paragraphs 

3.B.2.d. and 3.B.2.e of ASB No. EC120– 

52A014, or paragraph 3.B.2.d. and the table 

under paragraph 3.C of ASB No. EC130– 

52A009, whichever is applicable to your 

model helicopter. 

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

not install a sliding door P/N C526A2370101 

on an EC120B helicopter, or a sliding door 

P/N C526S1101051 on an EC130B4 

helicopter, unless the sliding door has been 

reinforced as required by paragraph (f)(1)(iii) 

of this AD. 

(g) Credit for Actions Previously Completed 

Compliance with AD 2014–12–12 (79 FR 

366838, June 30, 2014) before the effective 

date of this AD is considered acceptable for 

compliance with the corresponding actions 

specified in paragraph (f)(1) of this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: David Hatfield, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5116; 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. 

(i) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2015–0020, dated February 11, 2015. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2016–3343. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5220, Emergency Exits. 

Issued in Fort Worth, Texas, on October 18, 

2016. 

James A. Grigg, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–25748 Filed 10–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 2 

[Docket No. FDA–2015–N–1355] 

RIN 0910–AH36 

Use of Ozone-Depleting Substances 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Proposed rule. 

SUMMARY: The Food and Drug 

Administration (FDA, the Agency, or 

we) is proposing to amend its regulation 

on uses of ozone-depleting substances 

(ODSs), including chlorofluorocarbons 

(CFCs), to remove the designation for 

certain products as ‘‘essential uses’’ 

under the Clean Air Act. Essential-use 

products are exempt from the ban by 


Lhorne on DSK30JT082PROD with PROPOSALS