Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 15149 

Area of Application. Survey area plus: 

North Carolina: 

Alexander 

Anson 

Catawba 

Cleveland 

Iredell 

Lincoln 

Stanly 

Wilkes 

South Carolina: 

Chester 

Chesterfield 

Lancaster 

York 

* * * * * 

SOUTH CAROLINA 

* * * * * 

Columbia 

Survey Area 

South Carolina: 

Darlington 

Florence 

Kershaw 

Lee 

Lexington 

Richland 

Sumter 

Area of Application. Survey area plus: 

South Carolina: 

Abbeville 

Anderson 

Calhoun 

Cherokee 

Clarendon 

Fairfield 

Greenville 

Greenwood 

Laurens 

Newberry 

Oconee 

Orangeburg 

Pickens 

Saluda 

Spartanburg 

Union 

* * * * * 

WISCONSIN 

* * * * * 

Southwestern Wisconsin 

Survey Area 

Wisconsin: 

Chippewa 

Eau Claire 

La Crosse 

Monroe 

Trempealeau 

Area of Application. Survey area plus: 

Minnesota: 

Houston 

Winona 

Wisconsin: 

Barron 

Buffalo 

Clark 

Crawford 

Dunn 

Florence 

Forest 

Jackson 

Juneau 

Langlade 

Lincoln 

Marathon 

Marinette 

Menominee 

Oneida 

Pepin 

Portage 

Price 

Richland 

Rusk 

Shawano 

Taylor 

Vernon 

Vilas 

Waupaca 

Wood 

* * * * * 

[FR Doc. 2015–06410 Filed 3–20–15; 8:45 am] 

BILLING CODE 6325–39–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0752; Directorate 

Identifier 2014–NM–079–AD; Amendment 

39–18110; AD 2015–04–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–06– 

08 for certain Bombardier, Inc. Model 

DHC–8–100, –200, and –300 series 

airplanes. AD 2014–06–08 required 

repetitive functional checks of the nose 

and main landing gear, and corrective 

actions if necessary; and also provided 

optional terminating action 

modification for the repetitive 

functional checks. This new AD 

requires a terminating action 

modification. This AD was prompted by 

a report that the emergency downlock 

indication system (EDIS) had given a 

false landing gear down-and-locked 

indication and a determination that a 

terminating action modification is 

necessary to address the identified 

unsafe condition. We are issuing this 

AD to detect and correct a false downand-locked landing gear indication, 

which, on landing, could result in 

possible collapse of the landing gear. 

DATES: This AD becomes effective April 

27, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of publications listed in this AD as of 

April 14, 2014 (79 FR 17390, March 28, 

2014). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

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

FAA-2014-0752; 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., 

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. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2014–06–08, 

Amendment 39–17812 (79 FR 17390, 

March 28, 2014). AD 2014–06–08 

applied to certain Bombardier, Inc. 

Model DHC–8–100, –200, and –300 

series airplanes. The NPRM published 

in the Federal Register on October 17, 

2014 (79 FR 62363). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–11, 

dated February 13, 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: 

During an in-service event where the 

landing gear control panel indicated an 

unsafe nose landing gear, the flight crew 

observed that all three green lights were 

illuminated on the emergency downlock 

indication system. The nose landing gear was 

not down and locked, and collapsed during 

landing. 

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15150 Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 

Investigation found ambient light and 

wiring shorts can lead to incorrect 

illumination of the green lights on the 

emergency downlock indication system. 

This [Canadian] AD mandates the 

functional check of the nose and main 

landing gear alternate indication 

phototransistors and the modification of the 

emergency downlock indication system 

[incorporation of Modsums 8Q101955, 

8Q101968, and 8Q101969 as applicable]. 

The unsafe condition is a false downand-locked landing gear indication, 

which, on landing, could result in 

possible collapse of the landing gear. 

The modification consists of installing 

certain new electrical components and 

cable assemblies. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2014-0752-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. An 

anonymous commenter supported the 

NPRM (79 FR 62363, October 17, 2014). 

Change Made to This AD 

We have revised paragraphs (h)(1), 

(h)(2), and (h)(3) of this AD to clarify the 

affected airplanes identified in those 

paragraphs. This change does not affect 

the intent of those paragraphs. 

Clarification of Repair Approval 

Required by Paragraph (g) of AD 2014– 

06–08, Amendment 39–17812 (79 FR 

17390, March 28, 2014) 

In paragraph (g) of AD 2014–06–08, 

Amendment 39–17812 (79 FR 17390, 

March 28, 2014), the functional check 

and corrective actions are done in 

accordance with Bombardier Service 

Bulletin 8–32–173, Revision A, dated 

December 17, 2012. That service 

information specifies to contact the 

manufacturer for further instructions if 

certain discrepancies are found. As 

noted in paragraph (j)(2) of AD 2014– 

06–08, ‘‘For any requirement in this AD 

to obtain corrective actions from a 

manufacturer, use these actions if they 

are FAA-approved. . .’’ and ‘‘. . . 

corrective actions are considered FAAapproved if they were approved by the 

State of Design Authority (or its 

delegated agent, or the DAH with a State 

of Design Authority’s design 

organization approval, as applicable).’’ 

To clarify the repair approval for the 

action specified in paragraph (g) of this 

AD, we have added an exception to 

paragraph (g) of this AD, including 

specific delegation approval language. 

The exception clarifies that where the 

service information specifies to contact 

the manufacturer for further 

instructions, this AD requires repairing 

using a method approved by the 

Manager, New York Aircraft 

Certification Office, ANE–170, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA 

Design Approval Organization. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

62363, October 17, 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 62363, 

October 17, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 85 

airplanes of U.S. registry. 

The actions that are required by AD 

2014–06–08, Amendment 39–17812 (79 

FR 17390, March 28, 2014), and retained 

in this AD take about 3 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that 

were required by AD 2014–06–08 is 

$21,675, or $255 per product, per 

inspection cycle. 

We also estimate that it will take up 

to 40 work-hours per product to comply 

with the basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost up to 

$19,436 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be up to $1,941,060, 

or $22,836 per product. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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-2014-0752; 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. 

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Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations 15151 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2014–06–08, Amendment 39–17812 (79 

FR 17390, March 28, 2014), and adding 

the following new AD: 

2015–04–08 Bombardier, Inc.: Amendment 

39–18110. Docket No. FAA–2014–0752; 

Directorate Identifier 2014–NM–079–AD. 

(a) Effective Date 

This AD becomes effective April 27, 2015. 

(b) Affected ADs 

This AD replaces AD 2014–06–08, 

Amendment 39–17812 (79 FR 17390, March 

28, 2014). 

(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 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report that the 

emergency downlock indication system 

(EDIS) had given a false landing gear downand-locked indication and a determination 

that a terminating action modification is 

necessary to address the identified unsafe 

condition. We are issuing this AD to detect 

and correct a false down-and-locked landing 

gear indication, which, on landing, could 

result in possible collapse of the landing 

gear. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Functional Check With Repair 

Approval Clarification 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–06–08, 

Amendment 39–17812 (79 FR 17390, March 

28, 2014), with specific delegation approval 

language. Within 600 flight hours or 100 

days, whichever occurs first, after April 14, 

2014 (the effective date of AD 2014–06–08): 

Perform a functional check of the alternate 

indication phototransistors of the nose and 

main landing gear; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–173, Revision A, dated 

December 17, 2012; except where 

Bombardier Service Bulletin 8–32–173, 

Revision A, dated December 17, 2012, 

specifies to contact the manufacturer for 

further instructions, before further, flight, 

repair using a method approved by the 

Manager, New York Aircraft Certification 

Office, ANE–170, FAA; or Transport Canada 

Civil Aviation (TCCA); or Bombardier, Inc.’s 

TCCA Design Approval Organization (DAO). 

Do all applicable corrective actions before 

further flight. Repeat the functional check 

thereafter at intervals not to exceed 600 flight 

hours or 100 days, whichever occurs first, 

until accomplishment of the applicable 

actions specified in paragraph (h) of this AD. 

(h) New Requirement of This AD: 

Terminating Action 

Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first: Do the applicable actions 

specified in paragraphs (h)(1) through (h)(3) 

of this AD. Accomplishment of the 

applicable actions specified in paragraphs 

(h)(1) through (h)(3) of this AD terminates the 

requirements of paragraph (g) of this AD. 

(1) For airplanes on which Bombardier 

ModSum 8/1519 is installed: Incorporate 

Modsum 8Q101968, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–33–56, Revision A, dated 

February 22, 2013. 

(2) For airplanes on which Bombardier 

Modsums 8/0235, 8/0461, and 8/0534 are 

installed: Incorporate Modsum 8Q101955, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–32–176, Revision A, dated February 22, 

2013. 

(3) For airplanes on which Bombardier 

Modsum 8/0534 is not installed: Incorporate 

Modsum 8Q101969, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–177, dated October 9, 

2013. 

(i) Credit for Previous Actions 

(1) 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 

Service Bulletin 8–32–173, dated October 28, 

2011, which is not incorporated by reference 

in this AD. 

(2) This paragraph provides credit for 

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

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–33–56, dated 

February 11, 2013, which is not incorporated 

by reference in this AD. 

(3) This paragraph provides credit for 

actions required by paragraph (h)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–32–176, dated 

February 11, 2013, which is not incorporated 

by reference in this AD. 

(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 

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: As of the 

effective date of this AD, 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 Aircraft Certification 

Office, ANE–170, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. If approved 

by the DAO, the approval must include the 

DAO-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–11, dated 

February 13, 2014, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http:// 

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

FAA-2014-0752-0002. 

(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. 

(3) The following service information was 

approved for IBR on April 14, 2014 (79 FR 

17390, March 28, 2014). 

(i) Bombardier Service Bulletin 8–32–173, 

Revision A, dated December 17, 2012. 

(ii) Bombardier Service Bulletin 8–32–176, 

Revision A, dated February 22, 2013. 

(iii) Bombardier Service Bulletin 8–32–177, 

dated October 9, 2013. 

(iv) Bombardier Service Bulletin 8–33–56, 

Revision A, dated February 22, 2013. 

(4) 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. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on February 

19, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05033 Filed 3–20–15; 8:45 am] 

BILLING CODE 4910–13–P 

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