Federal Register / Vol. 80, No. 10 / Thursday, January 15, 2015 / Rules and Regulations 1999 

(e) Required Actions 

Before further flight, insert a copy of this 

AD in the Rotorcraft Flight Manual or make 

the following pen-and-ink changes: 

(1) In the Eurocopter EC 155B1 Flight 

Manual, under Limitations (Prohibited 

Maneuvers) add: ‘‘Coupled LOC/VOR 

approaches.’’ 

(2) In the Airbus Helicopters Flight Manual 

EC155B1: 

(i) Under Limitations, add: ‘‘Autopilot 

coupled with a LOC/ILS or VOR approach is 

prohibited.’’ 

(ii) Under Normal Procedures, remove 

paragraphs 4.2 (Power-on GPS on Ground or 

In Flight) and 4.3 (Pre-taxiing checklist) in 

their entirety. Performing the procedures in 

Paragraphs 4.2 and 4.3 is prohibited. 

(3) In the Eurocopter Flight Manual AS 365 

N3, under Limitations, add: ‘‘Autopilot 

coupled with a LOC/ILS or VOR approach is 

prohibited.’’ 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: George Schwab, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

george.schwab@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. 

(g) Additional Information 

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; or at http://

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2210, Autopilot System. 

Issued in Fort Worth, Texas, on December 

4, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00543 Filed 1–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0582; Directorate 

Identifier 2014–NM–065–AD; Amendment 

39–18060; AD 2014–26–09] 

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) 2014–03– 

05, for certain Bombardier, Inc. Model 

BD–700–1A10 airplanes. AD 2014–03– 

05 required modification of the air data 

probes and sensors. This new AD 

continues to require modification of the 

air data probes and sensors. This new 

AD also adds airplanes to the 

applicability. This AD was prompted by 

a report that the manufacturer has 

determined that some completion 

centers used the heater current/brake 

temperature monitor unit (HBMU) logic 

circuit to control the line voltage of the 

drain mast heaters. We are issuing this 

AD to detect and correct an 

unannunciated failure of two pitot static 

probe heaters, which could affect 

controllability of the airplane in icing 

conditions. 

DATES: This AD becomes effective 

February 19, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 1, 2014 (79 FR 10331, 

February 25, 2014). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0582; 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., 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 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: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office, 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 to supersede AD 2014–03–05, 

Amendment 39–17742 (79 FR 10331, 

February 25, 2014). 

AD 2014–03–05 applied to certain 

Bombardier, Inc. Model BD–700–1A10 

airplanes. The NPRM published in the 

Federal Register on August 26, 2014 (79 

FR 50880). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–32, 

dated December 13, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model BD– 

700–1A10 airplanes. The MCAI states: 

The aeroplane manufacturer has 

determined that some completion centers 

used the Heater/Brake Monitoring Unit 

(HBMU) logic circuit to control the line 

voltage of the drain mast heaters. This same 

logic circuit is also used to control the line 

voltage of the number 2 pitot static (PS) 

probe heater. Since the drain mast heaters are 

connected in parallel with the number 2 PS 

probe heater circuit, a number 2 PS probe 

heater failure may not be detected by the 

fault monitoring capabilities of the HBMU. 

The unannunciated failure of two PS probe 

heaters could adversely affect the aeroplane’s 

flight characteristics in icing conditions. 

This [Canadian] AD mandates a 

modification to the existing drain mast heater 

wiring to correct the fault-monitoring 

capabilities of the HBMU and eliminate the 

potential dormant failure of the number 2 PS 

probe heater. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0582- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 50880, August 26, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 


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2000 Federal Register / Vol. 80, No. 10 / Thursday, January 15, 2015 / Rules and Regulations 

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 

50880, August 26, 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 50880, 

August 26, 2014). 

Costs of Compliance 

We estimate that this AD affects 79 

airplanes of U.S. registry. 

The actions required by AD 2014–03– 

05, Amendment 39–17742 (79 FR 

10331, February 25, 2014), and retained 

in this AD take about 35 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that were required by AD 2014–03–05 is 

$2,975 per product. 

We also estimate that it will take 

about 35 work-hours per product to 

comply with the new basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $235,025, or $2,975 per 

product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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-2014-0582; 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 

removing Airworthiness Directive (AD) 

2014–03–05, Amendment 39–17742 (79 

FR 10331, February 25, 2014), and 

adding the following new AD: 

2014–26–09 Bombardier, Inc.: Amendment 

39–18060. Docket No. FAA–2014–0582; 

Directorate Identifier 2014–NM–065–AD. 

(a) Effective Date 

This AD becomes effective February 19, 

2015. 

(b) Affected ADs 

This AD replaces AD 2014–03–05, 

Amendment 39–17742 (79 FR 10331, 

February 25, 2014). 

(c) Applicability 

(1) This AD applies to Bombardier, Inc. 

Model BD–700–1A10 airplanes, certificated 

in any category, equipped with any electrical 

wiring heater current/brake temperature 

monitor unit (HBMU) installed in accordance 

with any FAA supplemental type certificate 

specified in table 1 and table 2 of paragraph 

1.A., ‘‘Effectivity,’’ of Bombardier Service 

Bulletin 700–30–021, Revision 01, dated 

November 21, 2012. 

(2) For airplanes on which the applicable 

service request for product support action 

(SRPSA) specified in table 3 and table 4 of 

paragraph 1.A., ‘‘Effectivity,’’ of Bombardier 

Service Bulletin 700–30–021, Revision 01, 

dated November 21, 2012, has been 

incorporated, the requirements of this AD 

have been met. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 30, Ice and Rain Protection. 

(e) Reason 

This AD was prompted by a report that the 

manufacturer has determined that some 

completion centers used the heater current/ 

brake temperature monitor unit (HBMU) 

logic circuit to control the line voltage of the 

drain mast heaters. We are issuing this AD 

to detect and correct an unannunciated 

failure of two pitot static probe heaters, 

which could affect controllability of the 

airplane in icing conditions. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–03–05, 

Amendment 39–17742 (79 FR 10331, 

February 25, 2014). For airplanes equipped 

with any electrical wiring HBMU installed in 

accordance with any FAA supplemental type 

certificate specified in table 1 of paragraph 

1.A., ‘‘Effectivity,’’ of Bombardier Service 

Bulletin 700–30–021, Revision 01, dated 

November 21, 2012: Within 800 flight hours 

or 15 months after April 1, 2014 (the effective 

date of AD 2014–03–05), whichever occurs 

first, modify the air data probes and sensors, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

700–30–021, Revision 01, dated November 

21, 2012. 

(h) New Modification 

For airplanes equipped with any electrical 

wiring HBMU installed in accordance with 

any FAA supplemental type certificate 

specified in table 2 of paragraph 1.A., 

‘‘Effectivity,’’ of Bombardier Service Bulletin 

700–30–021, Revision 01, dated November 

21, 2012: Within 800 flight hours or 15 


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Federal Register / Vol. 80, No. 10 / Thursday, January 15, 2015 / Rules and Regulations 2001 

months after the effective date of this AD, 

whichever occurs first, modify the air data 

probes and sensors, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 700–30–021, Revision 01, 

dated November 21, 2012. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) or (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 700–30–021, dated August 

28, 2012, 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 ACO, ANE–170, 

Engine and Propeller Directorate, 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 DAOauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–32, dated 

December 13, 2012, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0582-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(4) and (l)(5) 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. 

(3) The following service information was 

approved for IBR on April 1, 2014 (79 FR 

10331, February 25, 2014). 

(i) Bombardier Service Bulletin 700–30– 

021, Revision 01, dated November 21, 2012. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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. 

(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 

December 22, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30919 Filed 1–14–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Parts 61 and 141 

[Docket No. FAA–2014–0987; Amdt. Nos. 

61–133, 141–18] 

RIN 2120–AK62 

Aviation Training Device Credit for 

Pilot Certification; Withdrawal 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Direct final rule; withdrawal. 

SUMMARY: The FAA is withdrawing a 

direct final rule regarding aviation 

training devices published December 3, 

2014. That rule would have relieved 

burdens on pilots seeking to obtain 

aeronautical experience for an 

instrument rating by increasing the 

allowed use of aviation training devices. 

The FAA received adverse comments to 

the direct final rule and, thus, is 

withdrawing the direct final rule. 

DATES: The direct final rule published 

on December 3, 2014 at 79 FR 71634 is 

withdrawn, effective January 15, 2015. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Marcel Bernard, Airmen 

Certification and Training Branch, 

Flight Standards Service, AFS–810, 

Federal Aviation Administration, 55 M 

Street SE., 8th floor, Washington, DC 

20003–3522; telephone (202) 385–9616; 

email marcel.bernard@faa.gov. 

For legal questions concerning this 

action, contact Anne Moore, 

International Law, Legislation, and 

Regulations Division, Office of the Chief 

Counsel, AGC–200, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone (202) 267–8018; email 

anne.moore@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On December 3, 2014, the FAA 

published a direct final rule regarding 

use of aviation training devices (ATDs). 

The direct final rule would have 

increased the maximum time that may 

be credited in an ATD toward the 

instrument time requirements for an 

instrument rating under § 61.65(i). The 

direct final rule would have permitted 

a person to credit a maximum of 20 

hours of instrument time in an approved 

ATD toward the requirements for an 

instrument rating under that section. 

The direct final rule would have also 

amended appendix C to part 141 to 

increase the limit on the amount of 

training hours that may be 

accomplished in an ATD in an approved 

course for an instrument rating. With 

this direct final rule, an ATD would 

have been permitted to be used for no 

more than 40 percent of the total flight 

training hour requirements for an 

instrument rating. 

Finally, the direct final rule would 

have revised § 61.65(i)(4) to eliminate 

the requirement that pilots 

accomplishing instrument time in an 

ATD wear a view-limiting device. 

Withdrawal of Direct Final Rule 

The FAA is withdrawing the direct 

final rule because the agency received 

adverse comments to the rule. The 

agency is obligated by § 11.13 to 

withdraw a direct final rule if the 

agency receives any adverse comments. 

One commenter raised concerns 

regarding the effectiveness of ATDs for 

training, suggesting that these devices 

do not provide appropriate sensory cues 

or provide a realistic environment. 

Another commenter believed that the 

increases in time/percentage of training 

contained in the direct final rule were 

too great. 

As a result of this withdrawal, the 

current regulations remain in effect, 

which provides that no applicant for an 

instrument rating under part 61 may 

credit more than 10 hours of instrument 

time in an ATD toward the minimum 

aeronautical experience requirements 


rljohnson on DSK3VPTVN1PROD with RULES