10744 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 

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) Will not affect intrastate aviation 

in Alaska, and 

(3) 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: 

2021–04–09 Yabora ̃ Indu ́ stria Aerona ́utica 

S.A. (Type Certificate Previously Held 

by Embraer S.A.): Amendment 39– 

21430; Docket No. FAA–2020–1035; 

Project Identifier MCAI–2020–01017–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 30, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Yabora ̃ Indu ́ stria 

Aerona ́utica S.A. Model EMB–135BJ, 

–135ER, –135KE, –135KL, and –135LR 

airplanes; and Model EMB–145, –145EP, 

–145ER, –145LR, –145MP, –145MR, and 

–145XR airplanes; certificated in any 

category; as identified in Ageˆncia Nacional 

de Aviac ̧a ̃o Civil (ANAC) AD 2020–07–02, 

effective July 21, 2020 (ANAC AD 2020–07– 

02). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 73, Engine fuel and control. 

(e) Reason 

This AD was prompted by reports that 

calculations provided by the automatic 

takeoff thrust control system (ATTCS) are 

incorrect under certain conditions. The FAA 

is issuing this AD to address the risk of overprediction of the operational margins, 

without the necessary alert being provided to 

the flightcrew in some situations. This 

condition, if not corrected, could lead to a 

performance reduction during takeoff, in 

which case the airplane may not be able to 

take off safely. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, ANAC AD 2020–07–02. 

(h) Exceptions to ANAC AD 2020–07–02 

(1) Where ANAC AD 2020–07–02 refers to 

its effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Alternative method of compliance 

(AMOC)’’ section of ANAC AD 2020–07–02 

does not apply to this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation Branch, 

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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (j) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

ANAC; or ANAC’s authorized Designee. If 

approved by the ANAC Designee, the 

approval must include the Designee’s 

authorized signature. 

(j) Related Information 

For more information about this AD, 

contact Kathleen Arrigotti, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3218; email 

kathleen.arrigotti@faa.gov. 

(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) Ageˆncia Nacional de Aviac ̧a ̃o Civil 

(ANAC) AD 2020–07–02, effective July 21, 

2020. 

(ii) [Reserved] 

(3) For ANAC AD 2020–07–02, contact 

National Civil Aviation Agency (ANAC), 

Aeronautical Products Certification Branch 

(GGCP), Rua Dr. Orlando Feirabend Filho, 

230—Centro Empresarial Aquarius—Torre 

B—Andares 14 a 18, Parque Residencial 

Aquarius, CEP 12.246–190—Sa ̃o Jose ́ dos 

Campos—SP, BRAZIL, Tel: 55 (12) 3203– 

6600; Email: pac@anac.gov.br; internet 

www.anac.gov.br/en/. You may find this IBR 

material on the ANAC website at https://

sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. This material may be found 

in the AD docket on the internet at https:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2020–1035. 

(5) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email fedreg.legal@

nara.gov, or go to: https://www.archives.gov/ 

federal-register/cfr/ibr-locations.html. 

Issued on February 5, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–03586 Filed 2–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0813; Product 

Identifier 2019–CE–040–AD; Amendment 

39–21387; AD 2021–02–04] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Pilatus 

Aircraft Ltd. (Pilatus) Model PC–12/47E 

airplanes. This AD was prompted by 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as 

Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 10745 

inboard flap fairings aft (IFFAs) having 

an incorrect shape, which may result in 

chafing between the IFFA and the 

associated front inboard tension rod. 

This AD requires an inspection of the 

IFFAs for the correct shape and chafing 

between the IFFA and the associated 

front inboard tension rod, with 

corrective action as necessary. This 

condition could lead to failure of the 

inboard flap drive arm with consequent 

asymmetric flap extension, resulting in 

reduced control of the airplane. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective March 30, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 30, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact 

Pilatus Aircraft, Ltd., Customer Support 

PC–12, CH–6371 Stans, Switzerland; 

phone: +41 41 619 33 33; fax: +41 41 

619 73 11; email: supportPC12@pilatusaircraft.com; website: https://

www.pilatus-aircraft.com. You may 

review this referenced service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. It is also available 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0813. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0813; or in person at Docket 

Operations between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

final rule, the MCAI, any comments 

received, and other information. The 

address for Docket Operations is 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: 

Doug Rudolph, Aviation Safety 

Engineer, General Aviation & Rotorcraft 

Section, International Validation 

Branch, FAA, 901 Locust, Room 301, 

Kansas City, Missouri 64106; phone: 

(816) 329–4059; fax: (816) 329–4090; 

email: doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Pilatus Model PC–12/47E 

airplanes. The NPRM published in the 

Federal Register on September 16, 2020 

(85 FR 57804). In the NPRM, the FAA 

proposed to require an inspection of the 

IFFAs for the correct shape and chafing 

between the IFFA and the associated 

front inboard tension rod, with 

corrective action as necessary. 

The NPRM was based on MCAI from 

the European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union. EASA issued AD No.: 

2019–0231, dated September 13, 2019 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for Pilatus 

Model PC–12/47E airplanes. The MCAI 

states: 

On the final assembly line of PC–12/47E 

aeroplanes, IFFAs were detected having an 

incorrect shape. As a consequence, chafing 

between the IFFA and the associated front 

inboard tension rod could occur, may cause 

corrosion of the bare rod aluminium tube and 

reduce aluminium thickness. 

This condition, if not detected and 

corrected, could lead to failure of the inboard 

flap drive arm with consequent asymmetric 

flap extension, possibly resulting in reduced 

control of the aeroplane. 

To address this potential unsafe condition, 

Pilatus issued the [service bulletin] SB to 

provide inspection and modification 

instructions. 

For the reason described above, this 

[EASA] AD requires a one-time inspection of 

both IFFA and, depending on findings, a 

follow-on inspection of the associated front 

inboard tension rod for chafing, and 

modification or replacement of affected parts. 

You may examine the MCAI at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0813. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received two comments 

from Pilatus. The following presents the 

comments received on the NPRM and 

the FAA’s response to each comment. 

Pilatus requested the FAA reduce the 

applicability of the proposed AD from 

all Model PC–12/47E airplanes to Model 

PC–12/47E airplanes with serial number 

(S/N) 1576 and higher. Pilatus stated 

that due to an engineering change in 

2014, the left-hand (LH) IFFA, part 

number (P/N) 557.52.12.223, and the 

right-hand (RH) IFFA, P/N 

557.52.12.224, introduced on airplanes 

with S/N 1576 and higher, have 

different attachment hole positions and 

a maximum hole position difference of 

more than 12mm. As a result, it is not 

physically possible to install P/Ns 

557.52.12.223 and 557.52.12.224 on 

airplanes with an S/N lower than 1576. 

The FAA partially agrees. The 

commenter is correct that the affected 

IFFAs cannot be installed on Model PC– 

12/47E airplanes with an S/N lower 

than 1576. The FAA has revised 

paragraph (f) of this AD to limit the 

inspection of the IFFAs to airplanes 

with an S/N 1576 and higher. 

Pilatus acknowledged that tension rod 

P/N 527.52.12.135 can be installed on 

all Model PC–12/47E airplanes but 

requested the FAA limit the tension rod 

inspection for airplanes with an S/N 

lower than 1576 to only those with 

maintenance records showing that the 

tension rod had been installed. 

The FAA partially agrees. The FAA 

has revised the tension rod inspection to 

limit its scope for airplanes with an S/ 

N lower than 1576. Because the tension 

rods are not life-limited parts, there is 

no regulatory requirement for them to be 

serialized or for operators to record or 

retain information about the part’s 

traceability. Therefore, operators would 

be unable to comply with, and the FAA 

would be unable to enforce, the change 

requested by the commenter, as 

maintenance records may not identify if 

a tension rod was removed from an 

airplane with an S/N 1576 or higher. 

Instead, the FAA has changed the AD so 

that the inspection of the tension rod is 

required for all airplanes with a S/N 

1576 or higher and for airplanes with a 

S/N 1001 through 1575 if tension rod P/ 

N 527.52.12.135 is installed. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 

determined that air safety requires 

adopting this AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for the changes 

described previously, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Pilatus PC–12 

Service Bulletin No: 27–026, dated July 

10, 2019 (Pilatus SB No. 27–026). The 

service information specifies procedures 

for inspecting and correcting chafing 

between the left and right IFFAs and the 

associated front inboard tension rods. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

10746 Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 

course of business or by the means 

identified in ADDRESSES. 

Differences Between This AD and the 

MCAI 

The MCAI only requires inspection of 

the tension rods if the IFFAs are 

modified because they have been found 

to have the incorrect shape. Due to the 

length of time between manufacture and 

the issuance of this AD, operators could 

have installed an affected tension rod 

onto an airplane that was not 

manufactured with the defective part. 

Therefore, this AD requires inspection 

for chafing damage on the tension rods 

on all Model PC–12/47E airplanes that 

have an affected tension rod installed. 

Costs of Compliance 

The FAA estimates that this AD will 

affect 18 products of U.S. registry. The 

FAA also estimates that it will take 

about 2.5 work-hours per product to 

comply with the requirements of this 

AD. The average labor rate is $85 per 

work-hour. Required parts will cost 

about $1,600 per product. 

Based on these figures, the FAA 

estimates the cost of this AD on U.S. 

operators will be $32,634 or $1,813 per 

product. 

The FAA has included all costs in this 

cost estimate. According to the 

manufacturer, however, all or some of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected operators. 

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. 

The FAA is 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 

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) Will not affect intrastate aviation 

in Alaska, and 

(3) 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. 

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: 

2021–02–04 Pilatus Aircraft Ltd.: 

Amendment 39–21387; Docket No. 

FAA–2020–0813; Product Identifier 

2019–CE–040–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 30, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pilatus Aircraft Ltd. 

Model PC–12/47E airplanes, all serial 

numbers (S/Ns), certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2700: Flight Controls. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as inboard 

flap fairings aft (IFFAs) having an incorrect 

shape. The FAA is issuing this AD to prevent 

chafing between the IFFA and the front 

inboard tension rod, and consequent 

corrosion of the bare rod aluminum tube and 

reduced aluminum thickness. This condition, 

if not corrected, could lead to failure of the 

inboard flap drive arm, asymmetric flap 

extension, and reduced control of the 

airplane. 

(f) Actions and Compliance 

(1) For airplanes with a S/N 1576 and 

higher, unless already done, within 100 

hours time-in-service (TIS) after the effective 

date of this AD or within 6 months after the 

effective date of this AD, whichever occurs 

first, inspect the left-hand (LH) and righthand (RH) IFFAs for correct shape and 

clearance with the LH and RH tension rods 

by following step 3.B.(1) and Figures 2 and 

3 of the Accomplishment Instructions— 

Aircraft in Pilatus PC–12 Service Bulletin No: 

27–026, dated July 10, 2019 (Pilatus SB 27– 

026). 

(i) If the shape of the LH or RH IFFA is 

incorrect or if the clearance between the 

IFFA and the tension rod is less than 5 mm 

(0.2 inch), before further flight, modify the 

IFFA and inspect the tension rods for chafing 

by following section 3.C. of the 

Accomplishment Instructions—Aircraft in 

Pilatus SB 27–026. 

(ii) If the shape of the LH and RH IFFAs 

is correct and the clearance between the IFFA 

and the tension rod is at least 5 mm (0.2 

inch), before further flight, inspect the front 

inboard LH and RH tension rods for chafing 

by following step 3.C.(12)(a) of the 

Accomplishment Instructions—Aircraft in 

Pilatus SB 27–026. If the LH or RH tension 

rod has any chafing, before further flight, 

replace the tension rod by following step 

3.C.(12)(b) of the Accomplishment 

Instructions—Aircraft in Pilatus SB 27–026. 

(2) For airplanes with a S/N 1001 through 

S/N 1575, inclusive, that have a tension rod 

part number (P/N) 527.52.12.135 installed, 

unless already done, within 100 hours TIS 

after the effective date of this AD or within 

6 months after the effective date of this AD, 

whichever occurs first, inspect the front 

inboard LH and RH tension rods for chafing 

by following step 3.C.(12)(a) of the 

Accomplishment Instructions—Aircraft in 

Pilatus SB 27–026. If the LH or RH tension 

rod has any chafing, before further flight, 

replace the tension rod by following step 

3.C.(12)(b) of the Accomplishment 

Instructions—Aircraft in Pilatus SB 27–026. 

(3) For all Model PC–12/47E airplanes, as 

of the effective date of this AD, do not install 

on any airplane an LH IFFA P/N 

557.52.12.223, RH IFFA P/N 557.52.12.224, 

or tension rod P/N 527.52.12.135 unless the 

part has been inspected and all corrective 

actions have been taken as required by this 

AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

Federal Register / Vol. 86, No. 34 / Tuesday, February 23, 2021 / Rules and Regulations 10747 

The Manager, International Validation 

Branch, FAA, has the authority to approve 

AMOCs for this AD if requested using the 

procedures found in 14 CFR 39.19. Send 

information to Doug Rudolph, Aviation 

Safety Engineer, General Aviation & 

Rotorcraft Section, International Validation 

Branch, FAA, 901 Locust, Room 301, Kansas 

City, Missouri 64106; phone: (816) 329–4059; 

fax: (816) 329–4090; email: 

doug.rudolph@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. 

(h) Related Information 

(1) Refer to MCAI European Union 

Aviation Safety Agency AD No. 2019–0231, 

dated September 13, 2019, for related 

information. You may examine the MCAI at 

https://www.regulations.gov by searching for 

and locating Docket No. FAA–2020–0813. 

(2) For service information related to this 

AD, contact Pilatus Aircraft, Ltd., Customer 

Support PC–12, CH–6371 Stans, Switzerland; 

phone: +41 41 619 33 33; fax: +41 41 619 73 

11; email: supportPC12@pilatus-aircraft.com; 

website: https://www.pilatus-aircraft.com. 

You may review this referenced service 

information at the FAA, Airworthiness 

Products Section, Operational Safety Branch, 

901 Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

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

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Pilatus Service Bulletin No: 27–026, 

dated July 10, 2019. 

(ii) [Reserved] 

(3) For Pilatus Aircraft Ltd. service 

information identified in this AD, contact 

Pilatus Aircraft, Ltd., Customer Support PC– 

12, CH–6371 Stans, Switzerland; phone: +41 

41 619 33 33; fax: +41 41 619 73 11; email: 

supportPC12@pilatus-aircraft.com; website: 

https://www.pilatus-aircraft.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(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, 

email: fedreg.legal@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on January 6, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–03476 Filed 2–22–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0843; Product 

Identifier 2020–NM–073–AD; Amendment 

39–21420; AD 2021–03–17] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc., Model BD–700–1A10 

airplanes. This AD was prompted by a 

report of smoke and signs of an 

overheating condition from the 

emergency light battery (ELB) due to 

excessive corrosion surrounding the 

internal lead acid batteries, which 

caused an electrical short circuit that 

led to the smoke and overheating 

condition. This AD requires an 

inspection to determine the last 

replacement date of the ELB, and 

replacement if necessary. This AD also 

requires the incorporation of a new 

maintenance task into the existing 

maintenance or inspection program. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective March 30, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 30, 2021. 

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 ac.yul@

aero.bombardier.com; internet https://

www.bombardier.com. You may view 

this service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2020–0843. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

0843; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

any comments received, and other 

information. The address for Docket 

Operations is 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: 

Thomas Niczky, Aerospace Engineer, 

Avionics and Electrical Systems 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7347; fax 516–794–5531; email 9- 

avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 

CF–2020–07, dated March 17, 2020 (also 

referred to as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for certain Bombardier, Inc., Model BD– 

700–1A10 airplanes. You may examine 

the MCAI in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2020–0843. 

The FAA 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 

BD–700–1A10 airplanes. The NPRM 

published in the Federal Register on 

September 17, 2020 (85 FR 58010). The 

NPRM was prompted by a report of 

smoke and signs of an overheating 

condition from the ELB due to excessive 

corrosion surrounding the internal lead 

acid batteries, which caused an 

electrical short circuit that led to the 

smoke and overheating condition. The 

NPRM proposed to require an 

inspection to determine the last 

replacement date of the ELB, and 

replacement if necessary. The NPRM 

also proposed to require the 

incorporation of a new maintenance 

task into the existing maintenance or 

inspection program. The FAA is issuing 

this AD to address smoke and an 

overheating condition of the ELB due to 

corrosion, which could cause fire 

onboard the airplane. See the MCAI for 

additional background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The following presents 

the comment received on the NPRM and 

the FAA’s response to that comment.