63420 Federal Register / Vol. 80, No. 202 / Tuesday, October 20, 2015 / Rules and Regulations 

other goods or services that relate to a 

licensee’s, certificate holder’s, quality 

assurance program approval holder’s or 

applicant’s activities subject to this part, 

that they may be individually subject to 

NRC enforcement action for violation of 

§§ 30.10, 40.10, 61.9b, 70.10, and 71.8. 

Dated at Rockville, Maryland, this 13th day 

of October, 2015. 

For the Nuclear Regulatory Commission. 

Annette L. Vietti-Cook, 

Secretary of the Commission. 

[FR Doc. 2015–26590 Filed 10–19–15; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1985; Directorate 

Identifier 2014–NM–214–AD; Amendment 

39–18294; AD 2015–21–02] 

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–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This AD was prompted 

by reports of un-annunciated failures of 

the direct current (DC) starter generator, 

which caused caution indicators of the 

affected systems to illuminate and 

prompted emergency descents and 

landings. This AD requires replacing the 

DC generator control units (GCUs) with 

new GCUs and replacing the GCU label. 

We are issuing this AD to prevent a low 

voltage condition on the left main DC 

bus, which, during critical phases of 

flight, could result in the loss of flight 

management, navigation, and 

transponder systems, and could affect 

continued safe flight. 

DATES: This AD becomes effective 

November 24, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 24, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/#!docket

Detail;D=FAA-2015-1985; 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 service information identified in 

this AD, contact Bombardier, Inc., QSeries 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1985. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Services Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office (ACO), 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7301; 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–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

NPRM published in the Federal 

Register on June 25, 2015 (80 FR 36493). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–31R2, 

dated November 11, 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–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

MCAI states: 

Four occurrences of un-annunciated failure 

of the No. 1 Direct Current (DC) Starter 

Generator prompted emergency descents and 

landings resulting from the illumination of 

numerous caution indications of the affected 

systems. The functionality of the affected 

systems such as Flight Management System, 

Navigation, and transponder systems, were 

reportedly reduced or lost. Investigation 

determined the failure was a result of a low 

voltage condition of the Left Main DC Bus. 

During critical phases of flight, the loss of 

these systems could affect continued safe 

flight. 

The original issue of this [Canadian] AD 

mandated the modification [replacing certain 

DC GCUs with new GCUs and replacing 

labels] which introduces generator control 

unit (GCU) undervoltage protection. 

Revision 1 of this [Canadian] AD added a 

GCU part number to the applicability of Part 

III of this [Canadian] AD, in order to ensure 

that all units are fitted with a warning label. 

Revision 2 of this [Canadian] AD corrects 

the GCU part number in the applicability of 

Part III of this [Canadian] AD. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/#!document

Detail;D=FAA-2015-1985-0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 36493, June 25, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available 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 (80 FR 

36493, June 25, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 36493, 

June 25, 2015). 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued the following 

service information. 

• Service Bulletin 8–24–84, Revision 

D, dated April 10, 2014, describes 

incorporating Bombardier Modification 

Summary (ModSum) 8Q101710 by 

replacing the GCU with a new GCU, and 

replacing the GCU label for airplanes 

having certain Phoenix DC power GCU 

part numbers. 

• Service Bulletin 8–24–89, Revision 

C, dated November 4, 2014, describes 

incorporating Bombardier ModSum 

8Q101925 by replacing the GCU with a 

new GCU, and replacing the GCU label 

for airplanes having certain Goodrich 

DC power GCU part numbers. 

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 92 

airplanes of U.S. registry. 

We also estimate that it takes about 3 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

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Federal Register / Vol. 80, No. 202 / Tuesday, October 20, 2015 / Rules and Regulations 63421 

Required parts will cost up to $12,098 

per product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be up to $1,136,476, or up 

to $12,353 per product. 

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-2015-1985; 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): 

2015–21–02 Bombardier, Inc.: Amendment 

39–18294. Docket No. FAA–2015–1985; 

Directorate Identifier 2014–NM–214–AD. 

(a) Effective Date 

This AD becomes effective November 24, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category, serial numbers 003 through 672 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by reports of unannunciated failures of the direct current 

(DC) starter generator, which caused caution 

indicators of the affected systems to 

illuminate and prompted emergency descents 

and landings. We are issuing this AD to 

prevent a low voltage condition on the left 

main DC bus which, during critical phases of 

flight, could result in the loss of flight 

management, navigation, and transponder 

systems, and could affect continued safe 

flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) For Airplanes Having Certain Generator 

Control Units (GCUs) Installed: Replacement 

of DC GCUs and GCU Labels 

Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first, accomplish the actions specified 

in paragraphs (g)(1) and (g)(2) of this AD, as 

applicable. 

(1) For airplanes having Goodrich DC GCU 

part number 51539–008B, 51539–008C, or 

51539–008D installed: Incorporate 

Bombardier Modification Summary 

(ModSum) 8Q101925 by replacing the GCU 

with a new GCU, and replacing the GCU 

label, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–24–89, Revision C, dated 

November 4, 2014. 

(2) For airplanes having Phoenix DC GCU 

part number GC–1010–24–5DIII or GC–1010– 

24–5DII installed: Incorporate Bombardier 

ModSum 8Q101710 by replacing the GCU 

with a new GCU, and replacing the GCU 

label, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–24–84, Revision D, dated 

April 10, 2014. 

(h) For Airplanes Having Certain Other 

GCUs Installed: Replacement of DC GCU 

Label 

For airplanes having Phoenix DC GCU part 

number GC–1010–24–5DIV or GC–1010–24– 

5DV installed: Within 6,000 flight hours or 

36 months after the effective date of this AD, 

whichever occurs first, replace the DC GCU 

label with a new GCU label, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–24–84, 

Revision D, dated April 10, 2014. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

information specified in paragraphs (i)(1)(i) 

through (i)(1)(iii) of this AD, as applicable. 

This service information is not incorporated 

by reference in this AD. 

(i) Bombardier Service Bulletin 8–24–89, 

dated November 12, 2011. 

(ii) Bombardier Service Bulletin 8–24–89, 

Revision A, dated August 8, 2012. 

(iii) Bombardier Service Bulletin 8–24–89, 

Revision B, dated April 9, 2014. 

(2) This paragraph provides credit for 

actions required by paragraphs (g)(2) and (h) 

of this AD, if those actions were performed 

before the effective date of this AD using the 

service information specified in paragraphs 

(i)(2)(i) through (i)(2)(iv) of this AD, as 

applicable. This service information is not 

incorporated by reference in this AD. 

(i) Bombardier Service Bulletin 8–24–84, 

dated August 22, 2008. 

(ii) Bombardier Service Bulletin 8–24–84, 

Revision A, dated August 23, 2008. 

(iii) Bombardier Service Bulletin 8–24–84, 

Revision B, dated October 15, 2008. 

(iv) Bombardier Service Bulletin 8–24–84, 

Revision C, dated July 7, 2009. 

(j) 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 

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63422 Federal Register / Vol. 80, No. 202 / Tuesday, October 20, 2015 / Rules and Regulations 

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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–31R2, 

dated November 14, 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–2015–1985–0003. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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 8–24–84, 

Revision D, dated April 10, 2014. 

(ii) Bombardier Service Bulletin 8–24–89, 

Revision C, dated November 4, 2014. 

(3) 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. 

(4) 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. 

(5) 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 October 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26218 Filed 10–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0442; Directorate 

Identifier 2007–SW–24–AD; Amendment 39– 

18291; AD 2015–20–12] 

RIN 2120–AA64 

Airworthiness Directives; Various 

Sikorsky-Manufactured Transport and 

Restricted Category Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 98–26–02 

for certain Sikorsky Aircraft Corporation 

(Sikorsky) Model S–61A, D, E, L, N, 

NM, R, and V helicopters. AD 98–26–02 

required determining whether the main 

rotor shaft (MRS) was used in repetitive 

external lift (REL) operations, 

performing a nondestructive inspection 

(NDI) for cracks, replacing any 

unairworthy MRS, and establishing 

retirement lives for each REL MRS. This 

new AD retains some of the 

requirements of AD 98–26–02 but 

determines a new retirement life for 

each MRS, expands the applicability to 

include additional helicopters, and 

requires removing from service any 

MRS with oversized dowel pin bores. 

This AD was prompted by the 

manufacturer’s reevaluation of the 

retirement life for the MRS based on 

torque, ground-air-ground (GAG) cycle, 

and fatigue testing. We are issuing this 

AD to prevent MRS structural failure, 

loss of power to the main rotor, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective November 

24, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 24, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, Connecticut, telephone (203) 

383–4866, email tsslibrary@

sikorsky.com, or at http://

www.sikorsky.com. You may view this 

referenced service information at the 

FAA, Office of the Regional Counsel, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2008–0442; 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, any 

incorporated-by-reference information, 

the economic evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Tracy Murphy, Aviation Safety 

Engineer, Boston Aircraft Certification 

Office, Engine & Propeller Directorate, 

FAA, 12 New England Executive Park, 

Burlington, Massachusetts 01803; 

telephone (781) 238–7172; email 

tracy.murphy@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 10, 2008, we issued a notice 

of proposed rulemaking (NPRM) (73 FR 

21556, April 22, 2008) proposing to 

amend 14 CFR part 39 by adding an AD 

for Sikorsky Aircraft Corporation Model 

S–61A, D, E, L, N, NM, R, and V; 

Croman Corporation Model SH–3H; 

Carson Helicopters, Inc., Model S–61L; 

Glacier Helicopters, Inc., Model CH–3E; 

Robinson Air Crane, Inc., Model CH–3E, 

CH–3C, HH–3C and HH–3E; and Siller 

Helicopters Model CH–3E and SH–3A 

helicopters. The NPRM proposed 

superseding AD 98–26–02 (63 FR 69177, 

December 16, 1998), which required 

determining whether the MRS was used 

in REL operations, performing an NDI 

for cracks, replacing any unairworthy 

MRS, and establishing retirement lives 

for each REL MRS. The NPRM proposed 

to retain some of the requirements of AD 

98–26–02 but also proposed a new 

retirement life determination for each 

MRS, removing from service any MRS 

with oversized dowel pin bores, and 

expanding the applicability to include 

certain restricted category models. The 

NPRM was prompted by the 

manufacturer’s reevaluation of the 

retirement life for the MRS based on 

torque, GAG cycle, and fatigue testing. 

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