Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26099 

paragraph (f)(1) of this AD or within the next 

12 months after doing the initial visual 

inspection required in paragraph (f)(1) of this 

AD, whichever occurs first, do an ultrasound 

inspection of the main landing gear oleo 

upper attach fittings for cracks as specified in 

Mitsubishi Heavy Industries, Ltd. MU–2 

Service News JCAB T.C.: No. 176, FAA T.C.: 

No. 128/32–013, dated July 18, 2013. This 

ultrasound inspection may also be done in 

place of the visual inspection required in 

paragraph (f)(1) of this AD if done within the 

next 100 hours TIS after June 6, 2016 (the 

effective date of this AD) or within the next 

6 months after June 6, 2016 (the effective date 

of this AD), whichever occurs first. 

Repetitively thereafter ultrasound inspect the 

attach fittings every 600 hours TIS or 36 

months, whichever occurs first, and any time 

a hard landing or overweight landing occurs. 

(4) Before further flight after any inspection 

required in paragraph (f)(3) of this AD, if no 

signs of cracks are found, lubricate the pin 

assembly attached to the main landing gear 

oleo attach fitting as specified in Mitsubishi 

Heavy Industries, Ltd. MU–2 Service News 

JCAB T.C.: No. 171, FAA T.C.: No. 124/32– 

011, dated April 27, 2012, and Mitsubishi 

Heavy Industries, Ltd. MU–2 Service News 

JCAB T.C.: No. 176, FAA T.C.: No. 128/32– 

013, dated July 18, 2013. 

(5) Before further flight after any inspection 

required in paragraph (f)(1) and (f)(3) of this 

AD where cracks are found, replace the main 

landing gear oleo upper attach fittings 

following the INSTRUCTIONS section in 

Mitsubishi Heavy Industries, Ltd. MU–2 

Service Bulletin No. 243, dated June 30, 

2015, and the INSTRUCTIONS sections in 

Mitsubishi Heavy Industries, Ltd. MU–2 

Service Bulletin No. 105/32–017, dated 

September 29, 2015, as applicable. After 

replacement, continue with the repetitive 

ultrasound inspection requirements of 

paragraph (f)(3) and lubrication requirements 

of paragraph (f)(4) of this AD. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Andrew McAnaul, Aerospace 

Engineer, FAA, ASW–143 (c/o San Antonio 

MIDO), 10100 Reunion Place, Suite 650, San 

Antonio, Texas 78216; phone: (210) 308– 

3365; fax: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI Japan Civil Aviation Bureau 

(JCAB) AD No. TCD–8585–2015, dated July 1, 

2015, for related information. You may 

examine the MCAI on the Internet at http:// 

www.regulations.gov/#!docketDetail;D=FAA2016-1363. 

(i) 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 the AD specifies otherwise. 

(i) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service Bulletin No. 105/32–017, dated 

September 29, 2015. 

(ii) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service Bulletin No. 243, dated June 30, 

2015. 

(iii) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service News JCAB T.C.: No. 176, FAA 

T.C.: No. 128/32–013, dated July 18, 2013. 

(iv) Mitsubishi Heavy Industries, Ltd. MU– 

2 Service News JCAB T.C.: No. 171, FAA 

T.C.: No. 124/32–011, dated April 27, 2012. 

(3) For Mitsubishi Heavy Industries, Ltd 

service information identified in this AD, 

contact Mitsubishi Heavy Industries 

America, Inc., c/o Turbine Aircraft Services, 

Inc., 4550 Jimmy Doolittle Drive, Addison, 

Texas 75001; telephone: (972) 248–3108, ext. 

209; fax: (972) 248–3321; Internet: http://mu2aircraft.com. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2016–1363. 

(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 Kansas City, Missouri, on April 

14, 2016. 

Robert P. Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–09239 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0657; Directorate 

Identifier 2014–NM–058–AD; Amendment 

39–18501; AD 2016–09–03] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 2000, 

FALCON 2000EX, MYSTERE–FALCON 

900, and FALCON 900EX airplanes. 

This AD was prompted by reports of a 

co-pilot sliding aft on his seat during 

take-off at rotation. This AD requires 

replacement of certain springs installed 

on the pilot and co-pilot seats. We are 

issuing this AD to prevent fatigue wear, 

which, if not corrected, could cause the 

seat to slide and the pilot or co-pilot to 

lose contact with the controls, leading to 

an inadvertent input on the flight 

control commands during take-off or 

climb, possibly resulting in loss of 

control of the airplane. 

DATES: This AD becomes effective June 

6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.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– 

0657. 

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–2014– 

0657; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

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26100 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is 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 20590. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

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 Dassault Aviation 

Model FALCON 2000, FALCON 

2000EX, MYSTERE–FALCON 900, and 

FALCON 900EX airplanes. The NPRM 

published in the Federal Register on 

November 17, 2014 (79 FR 68392) (‘‘the 

NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0061, dated March 11, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Dassault 

Aviation Model FALCON 2000, 

FALCON 2000EX, MYSTERE–FALCON 

900, and FALCON 900EX airplanes. The 

MCAI states: 

During take-off at rotation, a co-pilot 

reported to slide aft on his seat. 

The results of the investigations concluded 

that one spring of the seat locking system was 

broken and the other was weak. The root 

cause was determined to be fatigue wear. As 

springs accumulate cycles in service, they 

become increasingly exposed to the risk of 

unnoticed degradation or rupture. 

This condition, if not corrected, could 

cause the pilot or the co-pilot to lose contact 

with the controls, leading to an inadvertent 

input on the flight control commands during 

take-off or climb, possibly resulting in loss of 

control of the aeroplane. 

To address this unsafe condition, it was 

decided to require replacement of the 

affected seat springs for older aeroplanes and 

for newer aeroplanes; this task has been 

embodied in the aeroplane maintenance 

manual. 

For the reasons described above, this 

[EASA] AD requires replacement of the 

springs installed on the pilot and co-pilot 

seats with serviceable springs. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0657. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Revise the Compliance 

Times 

Travis Reinhardt requested that if 

paragraph (g) of the proposed AD is 

revised to include other airplanes that 

we consider different replacement 

times. The commenter stated that the 

NPRM is applicable to certain Dassault 

Aviation airplanes equipped with 

SICMA 132-series or 142-series pilot 

and co-pilot seats. The commenter 

noted he has Embraer 120 airplanes 

equipped with SICMA 147-series seats, 

which include part number (P/N) 

132100–19 and/or 147100–19 stop pin 

springs. The commenter stated the 

Embraer 120 heavy checks are due at 

4,000 flight hours versus the stated 

3,750 total flight cycles or 74 months for 

the listed Falcon airplanes. The 

commenter stated that he has only 

changed out one spring, approximately 

twelve years ago, and that currently, his 

installed springs, P/N 132100–19, have 

approximately 34,000 flight hours and 

34,600 flight cycles. 

While we appreciate the information 

Mr. Reinhardt has given, we are not 

revising this final rule to include other 

airplane models (or different 

replacement times) because the 

identified unsafe condition only affects 

the Dassault Aviation airplanes 

identified in the Applicability 

paragraph of this AD that are equipped 

with SICMA 132-series or 142-series 

pilot and co-pilot seats. However, if we 

determine that an unsafe condition 

exists on other airplane models, we 

might consider further rulemaking on 

this issue. We have made no changes to 

this final rule in this regard. 

Request To Add Part Number 

Mr. Reinhardt requested that if the 

NPRM is revised, we consider adding P/ 

N 132100–19 to paragraph (h) of the 

proposed AD, as stated in EASA AD 

2014–0061, dated March 11, 2014. 

For the reasons stated by the 

commenter, we agree to add P/N 

132100–19 to paragraph (h) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Dassault Aviation has issued the 

following service information: 

• Dassault Service Bulletin F900–429, 

Revision 1, dated July 13, 2012. 

• Dassault Service Bulletin F900EX– 

446, Revision 1, dated July 13, 2012. 

• Dassault Service Bulletin F2000– 

401, Revision 1, dated July 13, 2012. 

• Dassault Service Bulletin F2000EX– 

267, Revision 1, dated July 13, 2012. 

The service information describes 

procedures for replacing certain springs 

installed on the pilot and co-pilot seats. 

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. 

Costs of Compliance 

We estimate that this AD affects 528 

airplanes of U.S. registry. 

We also estimate that it will take 

about 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $83 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $133,584, or 

$253 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 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26101 

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. 

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): 

2016–09–03 Dassault Aviation: 

Amendment 39–18501. Docket No. 

FAA–2014–0657; Directorate Identifier 

2014–NM–058–AD. 

(a) Effective Date 

This AD becomes effective June 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) 

of this AD, certificated in any category, 

equipped with SICMA 132-series or 142- 

series pilot and co-pilot seats. 

(1) Dassault Aviation Model FALCON 2000 

airplanes. 

(2) Dassault Aviation Model FALCON 

2000EX airplanes. 

(3) Dassault Aviation Model MYSTERE– 

FALCON 900 airplanes. 

(4) Dassault Aviation Model FALCON 

900EX airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of a copilot sliding aft on his seat during take-off at 

rotation. We are issuing this AD to prevent 

fatigue wear, which, if not corrected, could 

cause the seat to slide and the pilot or copilot to lose contact with the controls, 

leading to an inadvertent input on the flight 

control commands during take-off or climb, 

possibly resulting in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

For airplanes that have accumulated more 

than 3,750 total flight cycles or have 

exceeded 74 months since the airplane’s first 

flight as of the effective date of this AD: 

Within 9 months after the effective date of 

this AD, replace each spring having part 

number (P/N) 132100–19 and P/N 147100–19 

installed on the pilot and co-pilot seats with 

a spring as specified in, and in accordance 

with, the Accomplishment Instructions of the 

service information identified in paragraph 

(g)(1), (g)(2), (g)(3), or (g)(4) of this AD, as 

applicable. Repeat the replacement thereafter 

at intervals not to exceed 78 months or 3,750 

flight cycles, whichever occurs first. 

(1) Dassault Service Bulletin F900–429, 

Revision 1, dated July 13, 2012. 

(2) Dassault Service Bulletin F900EX–446, 

Revision 1, dated July 13, 2012. 

(3) Dassault Service Bulletin F2000–401, 

Revision 1, dated July 13, 2012. 

(4) Dassault Service Bulletin F2000EX–267, 

Revision 1, dated July 13, 2012. 

(h) Parts Installation Limitation 

As of the effective date of this AD, 

installation of a spring having P/N 147100– 

19 or P/N 132100–19 on any airplane is 

allowed, provided that the spring is new. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0061, dated March 11, 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–2014–0657. 

(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) Dassault Service Bulletin F900–429, 

Revision 1, dated July 13, 2012. 

(ii) Dassault Service Bulletin F900EX–446, 

Revision 1, dated July 13, 2012. 

(iii) Dassault Service Bulletin F2000–401, 

Revision 1, dated July 13, 2012. 

(iv) Dassault Service Bulletin F2000EX– 

267, Revision 1, dated July 13, 2012. 

(3) For service information identified in 

this AD, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.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. 

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26102 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

Issued in Renton, Washington, on April 20, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–09800 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4814; Directorate 

Identifier 2015–NM–105–AD; Amendment 

39–18502; AD 2016–09–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by the 

discovery of a number of incorrectly 

calibrated angle of attack (AOA) 

transducers installed in the stall 

protection system. This AD requires 

replacement of incorrectly calibrated 

AOA transducers. We are issuing this 

AD to detect and replace incorrectly 

calibrated AOA transducers; incorrect 

calibration of the transducers could 

result in late activation of the stick 

pusher. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 6, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. It is also available 

on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4814. 

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– 

4814; 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 address for the 

Docket Office (phone: 800–647–5527) is 

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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, 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 516–228–7318; 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 

CL–600–2B19 (Regional Jet Series 

100&440) airplanes. The NPRM 

published in the Federal Register on 

November 17, 2015 (80 FR 71749) (‘‘the 

NPRM’’). The NPRM was prompted by 

the discovery of a number of incorrectly 

calibrated AOA transducers installed in 

the stall protection system. The NPRM 

proposed to require replacement of 

incorrectly calibrated AOA transducers. 

We are issuing this AD to detect and 

replace incorrectly calibrated AOA 

transducers; incorrect calibration of the 

transducers could result in late 

activation of the stick pusher. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 

CF–2015–17, effective July 16, 2015 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Bombardier, Inc. 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) airplanes. The MCAI 

states: 

It was discovered that a number of [angle 

of attack] AOA transducers installed on 

Bombardier CL–600–2B19 aeroplanes were 

incorrectly calibrated due to a quality control 

problem at both the production and repair 

facilities. Incorrect calibration of the AOA 

transducer could result in a late activation of 

the stick pusher. 

This [Canadian] AD mandates the 

replacement of the incorrectly calibrated 

AOA transducer. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4814. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Bombardier Service 

Bulletin 601R–27–164, dated March 30, 

2015. The service information describes 

procedures for replacement of 

incorrectly calibrated AOA transducers. 

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. 

Costs of Compliance 

We estimate that this AD affects 575 

airplanes of U.S. registry. 

We also estimate that it would 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. Required parts would 

cost about $10,000 per product. Based 

on these figures, we estimate the cost of 

this AD on U.S. operators to be 

$5,945,500, or $10,340 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 

mstockstill on DSK3G9T082PROD with RULES