Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32449 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2012–0195–E, dated September 24, 2012, 

and corrected September 25, 2012. You may 

view the EASA AD on the Internet at 

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

FAA–2015–1937. 

(k) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400 Tail Rotor System. 

Issued in Fort Worth, Texas, on May 26, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13845 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0754; Directorate 

Identifier 2014–NM–136–AD; Amendment 

39–18156; AD 2015–10–01] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This AD was prompted 

by reports of hydraulic fluid loss from 

the reservoir of the main landing gear 

(MLG) alternate extension system. This 

AD requires inspection for correct 

assembly of the MLG alternate extension 

system reservoir lid, and corrective 

action if necessary. We are issuing this 

AD to, in the event of a failure of the 

primary MLG extension system, prevent 

failure of the alternate MLG extension 

system to fully extend the MLG into a 

down-and-locked position, which could 

result in collapse of both left-hand and 

right-hand MLG sides during 

touchdown. 

DATES: This AD becomes effective July 

14, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 14, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0754; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For Bombardier 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. For Parker 

service information identified in this 

AD, contact Parker Aerospace, 14300 

Alton Parkway, Irvine, CA 92618; 

phone: 949–833–3000; Internet: http://

www.parker.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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0754. 

FOR FURTHER INFORMATION CONTACT: 

Fabio Buttitta, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7303; fax 

516–794–5531. 

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 certain Bombardier, Inc. Model 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

October 23, 2014 (79 FR 63341). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–15, 

dated June 6, 2014 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–400 series airplanes. The MCAI 

states: 

Several cases have been reported of hydraulic 

fluid loss from the main landing gear (MLG) 

alternate extension system reservoir and in 

one case, the reservoir was found empty. The 

cause was determined to be an incorrectly 

assembled reservoir lid. In the event of a 

failed primary MLG extension system, an 

alternate MLG extension system with an 

empty reservoir may not be able to fully 

extend the MLG into the down and locked 

position, resulting in an unsafe landing 

configuration. 

This [Canadian] AD mandates the [general 

visual] inspection of the MLG alternate 

extension system reservoir lid for correct 

assembly and the required rectification [i.e., 

corrective action which consists of repairing 

the lid assembly]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0754- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 63341, October 23, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

63341, October 23, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 63341, 

October 23, 2014). 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Service 

Bulletin 84–29–34, dated May 9, 2013, 

with the attached Parker Service 

Bulletin 82910012–29–431, dated 

October 22, 2012. This service 

information describes procedures to 

inspect the lid assembly of the MLG 

alternate extension system reservoir for 

correct assembly and corrective actions. 

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 of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 173 

airplanes of U.S. registry. 

We also estimate that it will take 

about 4 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $58,820, or $340 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 


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32450 Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 

about 2 work-hours and require parts 

costing $0, for a cost of $170 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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 above, I 

certify that this AD: 

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; 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docketDetail;D=

FAA-2014-0754; 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 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. 

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): 

2015–10–01 Bombardier, Inc.: Amendment 

39–18156. Docket No. FAA–2014–0754; 

Directorate Identifier 2014–NM–136–AD. 

(a) Effective Date 

This AD becomes effective July 14, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–401, –402, and –403 airplanes, 

certificated in any category, serial numbers 

4001 through 4424 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 29, Hydraulic Power. 

(e) Reason 

This AD was prompted by reports of 

hydraulic fluid loss from the reservoir of the 

main landing gear (MLG) alternate extension 

system. We are issuing this AD to, in the 

event of a failure of the primary MLG 

extension system, prevent failure of the 

alternate MLG extension system to fully 

extend the MLG into a down-and-locked 

position, which could result in collapse of 

both left-hand and right-hand MLG sides 

during touchdown. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first: Do a general visual inspection of 

the MLG alternate extension system reservoir 

lid for correct assembly, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–29–34, dated May 9, 

2013, and with the attached Parker Service 

Bulletin 82910012–29–431, dated October 22, 

2012, as referenced in Bombardier Service 

Bulletin 84–29–34, dated May 9, 2013. Do all 

applicable corrective actions within 2,000 

flight hours or 12 months after the effective 

date of this AD, whichever occurs first. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier All 

Operator Message 543, dated October 17, 

2012, which is not incorporated by reference 

in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (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. The AMOC 

approval letter must specifically reference 

this AD. 

(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–2014–15, dated 

June 6, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0754-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (k)(5) of this AD. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 84–29–34, 

dated May 9, 2013. 

(ii) Parker Service Bulletin 82910012–29– 

431, dated October 22, 2012. 


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Federal Register / Vol. 80, No. 110 / Tuesday, June 9, 2015 / Rules and Regulations 32451 

(3) For Bombardier 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. 

(4) For Parker service information 

identified in this AD, contact Parker 

Aerospace, 14300 Alton Parkway, Irvine, CA, 

92618; phone: 949–833–3000; Internet: 

http://www.parker.com. 

(5) 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. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 1, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11389 Filed 6–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1936; Directorate 

Identifier 2014–SW–005–AD; Amendment 

39–18170; AD 2015–11–07] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. 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 certain 

Agusta S.p.A. Model AB412 and AB412 

EP helicopters. This AD requires 

inspecting the tail rotor (T/R) drive shaft 

flanged adapter (adapter) for a crack and 

removing the adapter from service if 

there is a crack. This AD is prompted by 

a report of a crack found in an adapter. 

These actions are intended to detect a 

crack in the adapter and prevent failure 

of the T/R drive shaft, which could 

result in reduced control of the 

helicopter. 

DATES: This AD becomes effective June 

24, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of June 24, 2015. 

We must receive comments on this 

AD by August 10, 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 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 AD, the European 

Aviation Safety Agency (EASA) 

Emergency AD (EAD), any incorporated 

by reference service information, 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 AD, contact AgustaWestland, 

Product Support Engineering, Via del 

Gregge, 100, 21015 Lonate Pozzolo (VA) 

Italy, ATTN: Maurizio D’Angelo; 

telephone 39–0331–664757; fax 39– 

0331–664680; or at http://

www.agustawestland.com/technicalbulletins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. It is also available on the Internet 

at http://www.regulations.gov in Docket 

No. FAA–2015–1936. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@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 

This AD action was prompted by EAD 

No. 2014–0040–E, dated February 19, 

2014, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for certain 

AgustaWestland S.p.A. Model AB 412 

and AB 412 EP helicopters. EASA 

advises that a crack was found in an 

adapter, part number (P/N) 412–040– 

622–101, installed on a Model AB 412 

EP helicopter. EASA further advises that 

the condition, if not detected and 

corrected, could lead to T/R drive shaft 

failure, possibly resulting in reduced 

control of the helicopter. To address this 

unsafe condition, the EASA EAD 

requires repetitive inspections of 

adapters, P/N 412–040–622–101 and P/ 

N 412–040–623–101, for a crack and 

replacing a cracked adapter. EASA also 

requires reporting and sending the 

cracked adapter to AgustaWestland for 

investigation. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, the 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 the EASA and determined 

the unsafe condition exists and is likely 

to exist or develop on other helicopters 

of these same type designs. 


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