Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63145 

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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency Airworthiness Directive CF– 

2014–27R1, dated August 29, 2014, 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–2015–3988. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514 

855–7401; email 

thd.crj@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 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26222 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4112; Directorate 

Identifier 2014–SW–043–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) 2010–23– 

02 for Eurocopter France (now Airbus 

Helicopters) Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. AD 2010–23–02 currently 

requires amending the Limitations 

section of the Rotorcraft Flight Manual 

(RFM) to limit the never-exceed velocity 

(VNE) to 150 Knots Indicated Air Speed 

(KIAS) and to add a 1,500 ft/minute rate 

of descent (R/D) limitation beyond 140 

KIAS. Since we issued AD 2010–23–02, 

a design change designated as 

modification (MOD) 0755B28 improved 

the dynamic behavior of the horizontal 

stabilizer such that AD actions are not 

required. This proposed AD would 

retain the requirements of AD 2010–23– 

01 and revise the applicability to 

exclude helicopters with MOD 0755B28. 

These proposed actions are intended to 

exclude certain helicopters from the 

applicability and restrict the VNE on 

other helicopters to prevent failure of 

the horizontal stabilizer and subsequent 

loss of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by December 18, 

2015. 

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 in Docket No. 

FAA–2015–4112; 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 AD, contact Airbus 

Helicopters, Inc., 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, 

Texas 76177. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy., Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

robert.grant@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 October 15, 2010, we issued AD 

2010–23–02, Amendment 39–16491 (75 

FR 68169, November 5, 2010) for 

Eurocopter France (now Airbus 

Helicopters) Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. AD 2010–23–02 requires 

amending the Limitations section of the 

RFM to limit the VNE to 150 KIAS and 

to add a 1,500 ft/minute R/D limitation 

beyond 140 KIAS and installing one or 

more placards on the cockpit instrument 

panel in full view of the pilot and 

copilot. AD 2010–23–01 was prompted 

by failures of the horizontal stabilizers 

on then-recently delivered Model AS 

365 N3 helicopters due to a vibration 

phenomenon that may arise during the 

descent flight phases at high speed 

regardless of the stabilizer installed. 

Those actions were intended to prevent 

failure of the horizontal stabilizer and 

subsequent loss of control of the 

helicopter. 

Actions Since AD 2010–23–02 Was 

Issued 

Since we issued AD 2010–23–01 (75 

FR 68169, November 5, 2010), 

Eurocopter France changed its name to 

Airbus Helicopters. EASA, which is the 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
63146 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 

Technical Agent for the Member States 

of the European Union, issued EASA 

AD No. 2008–0204R1, Revision 1, dated 

May 21, 2014, to correct an unsafe 

condition for Airbus Helicopters Model 

SA–365N, SA–365N1, SA–365N2 and 

AS 365 N3 helicopters, all serial 

numbers, except those that have 

‘‘embodied’’ MOD 07 55B28. EASA 

advises that Airbus Helicopters 

developed MOD 07 55B28 to improve 

the dynamic behavior of the horizontal 

stabilizer and thus reduce the vibration 

levels during high speed descent. EASA 

revised a prior AD and issued AD No. 

2008–0204R1 to exclude helicopters 

with MOD 07 55B28 from the 

applicability. 

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 these same 

type designs. 

Related Service Information 

We reviewed a Eurocopter Emergency 

Alert Service Bulletin (EASB) with three 

numbers (01.00.60, 01.00.16, and 01.28), 

Revision 1, dated December 2, 2008. 

EASB No. 01.00.60 applies to U.S. typecertificated Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters and also to military Model 

AS365F, Fs, Fi, and K helicopters that 

are not certificated in the United States. 

EASB 01.00.16 applies to military 

Model AS565AA, MA, MB, SA, SB, and 

UB helicopters that are not type 

certificated in the United States. EASB 

01.28 applies to the Model SA–366G1 

helicopter. The EASB specifies bonding 

one or more locally-produced labels to 

the instrument panel stating that the 

VNE is limited to 150 KIAS and the R/ 

D must not exceed 1,500 ft/min beyond 

140 KIAS. Eurocopter states in the 

EASB that it is working on an enhanced 

definition that will be proposed as soon 

as possible. EASA classified this EASB 

as mandatory and issued AD No. 2008– 

0204–E, dated December 4, 2008, and 

revised with Revision 1, dated May 21, 

2014, to ensure the continued 

airworthiness of these helicopters. 

We also reviewed Airbus Helicopters 

Service Bulletin (SB) No. AS365– 

55.00.06, Revision 0, dated November 

14, 2014, which Airbus Helicopters 

identifies as MOD 0755B28. The SB 

specifies repairing the stabilizer for 

suppression of the flutter phenomenon. 

Proposed AD Requirements 

This proposed AD would retain the 

requirements of AD 2010–23–02, 

Amendment 39–16491 (75 FR 68169, 

November 5, 2010) to amend the 

Limitations section of the RFM to limit 

the VNE to 150 KIAS and to add a 1,500 

ft/minute R/D limitation for airspeeds 

beyond 140 KIAS and installing one or 

more placards on the cockpit instrument 

panel in full view of the pilot and 

copilot stating the limitations. This 

proposed AD would also revise the 

applicability to exclude those 

helicopters with MOD 0755B28 

installed. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 33 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 hour. We estimate about 1⁄2

work-hour per helicopter to make copies 

to include in the RFM and to make and 

install the placards. The parts costs are 

minimal. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators would be $1,403 for the 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) 

2010–23–02, Amendment 39–16491 (75 

FR 68169, November 5, 2010), and 

adding the following new AD: 

Airbus Helicopters (previously Eurocopter 

France): Docket No. FAA–2015–4112; 

Directorate Identifier 2014–SW–043–AD. 

(a) Applicability 

This AD applies to Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters, with a horizontal stabilizer, part 

number 365A13–3030–1901, –1902, –1903, 

–1904, –1905, –1906, –1908, –1909; 365A13– 

3036–00, –0001, –0002, –0003; or 365A13– 

3038–00, installed, except those with 

modification 0755B28 installed, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

vibration during descent at high speed. This 

condition could result in failure of the 

horizontal stabilizer and subsequent loss of 

control of the helicopter. 

(c) Affected ADs 

This AD replaces AD 2010–23–02, 

Amendment 39–16491 (75 FR 68169, 

November 5, 2010). 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63147 

(d) Comments Due Date 

We must receive comments by December 

18, 2015. 

(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 

Before further flight: 

(1) Revise the airspeed operating limitation 

in the Limitations section of the Rotorcraft 

Flight Manual (RFM) by making pen and ink 

changes or by inserting a copy of this AD into 

the RFM stating: ‘‘The never-exceed speed 

(VNE) is limited to 150 knots indicated 

airspeed (KIAS)’’ and ‘‘The rate-of-descent 

(R/D) must not exceed 1,500 ft/min when the 

airspeed is beyond 140 KIAS.’’ 

(2) Install one or more self-adhesive 

placards, with 6 millimeter red letters on 

white background, on the cockpit instrument 

panel in full view of the pilot and co-pilot 

to read as follows: ‘‘VNE LIMITED TO 150 

KIAS’’ and ‘‘R/D MUST NOT EXCEED 1,500 

ft/min when airspeed is beyond 140 KIAS’’ 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy, Fort Worth, Texas 76177; 

telephone (817) 222–5110; email 9-asw-ftwamoc-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) Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 01.00.60, 01.00.16, and 

01.28, Revision 1, dated December 2, 2008, 

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, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775. 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, 

Texas 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2008–0204R1, dated May 21, 2014. You 

may view the EASA AD on the Internet at 

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

FAA–2015–4112. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code 5310: Horizontal Stabilizer Structure. 

Issued in Fort Worth, Texas, on October 1, 

2015. 

Lance T. Gant, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–26229 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3986; Directorate 

Identifier 2015–NM–057–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400, 

–401, and –402 airplanes. This proposed 

AD was prompted by reports of chafing 

damage due to insufficient clearance on 

the main landing gear (MLG) stabilizer 

brace, the nacelle A-frame structure, and 

the adjacent electrical wiring harnesses. 

An insufficient fillet radius may also 

exist on certain airplanes. This 

proposed AD would require, depending 

on airplane configuration, an inspection 

of the nacelle A-frame structure for 

insufficient fillet radius; an inspection 

for cracking of affected structure, and 

rework or repair if necessary, and 

rework of the nacelle A-frame structure; 

repetitive inspections of the nacelle Aframe structure and the MLG stabilizer 

brace for insufficient clearance and 

damage, and repair if necessary, and 

rework of the nacelle A-frame structure, 

which would terminate the repetitive 

inspections; installation of new stop 

brackets and a shim on each MLG 

stabilizer brace assembly; and rework of 

the electrical wiring harnesses in the 

nacelle area. We are proposing this AD 

to detect and correct chafing damage 

and subsequent premature cracking and 

fracture of the nacelle A-frame structure, 

which could result in failure of the MLG 

stabilizer brace and loss of the MLG 

down-lock indication, which could 

adversely affect the safe landing of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 3, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 referenced 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. 

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–2015– 

3986; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory 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 FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aerospace Engineer, Airframe 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7329; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–3986; Directorate Identifier 

2015–NM–057–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS