Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations 31599 

(v) Any additional information as 

found in the annual Federal Register 

notice. 

§§ 4284.1121—4284.1130 [Reserved] 

§ 4284.1131 OMB control number. 

The information collection 

requirements in this subpart are 

approved by the Office of Management 

and Budget (OMB) and assigned OMB 

control number 0570–0075. 

Mark Brodziski, 

Acting Administrator, Rural BusinessCooperative Service. 

[FR Doc. 2021–12334 Filed 6–14–21; 8:45 am] 

BILLING CODE 3410–XY–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0183; Project 

Identifier MCAI–2020–01408–T; Amendment 

39–21589; AD 2021–12–02] 

RIN 2120–AA64 

Airworthiness Directives; De Havilland 

Aircraft of Canada Limited (Type 

Certificate Previously Held by 

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 

De Havilland Aircraft of Canada Limited 

Model DHC–8–400 series airplanes. 

This AD was prompted by a report that 

a number of nacelle A-frames were not 

manufactured in accordance with 

engineering drawings. This AD requires, 

depending on airplane configuration, 

removing the fasteners on the nacelle Aframe side brace sub-assemblies, doing 

an eddy current inspection for cracking, 

cold-working the holes, installing 

oversize fasteners, re-identifying the 

reworked side brace fitting and A-frame, 

and repair if necessary. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective July 20, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publication listed in this AD 

as of July 20, 2021. 

ADDRESSES: For service information 

identified in this final rule, contact De 

Havilland Aircraft of Canada Limited, 

Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.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–2021–0183. 

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–2021– 

0183; 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: 

Antariksh Shetty, Aerospace Engineer, 

Airframe and Propulsion Section, FAA, 

New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7300; fax 

516–794–5531; email 9-avs-nyaco-cos@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued TCCA AD CF– 

2020–39, dated October 14, 2020 (TCCA 

AD CF–2020–39) (also referred to as the 

Mandatory Continuing Airworthiness 

Information, or the MCAI), to correct an 

unsafe condition for certain De 

Havilland Aircraft of Canada Limited 

Model DHC–8–400 series 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–2021– 

0183. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain De Havilland Aircraft of 

Canada Limited Model DHC–8–400 

series airplanes. The NPRM published 

in the Federal Register on March 22, 

2021 (86 FR 15149). The NPRM was 

prompted by a report that a number of 

nacelle A-frames were not manufactured 

in accordance with engineering 

drawings. The holes in the side brace 

sub-assemblies were not cold-worked as 

required. As a result the side brace 

fitting might not meet its fatigue life, 

and cracking of the A-frame bottom 

flange may result. The NPRM proposed 

to require, depending on airplane 

configuration, removing the fasteners on 

the nacelle A-frame side brace subassemblies, doing an eddy current 

inspection for cracking, cold-working 

the holes, installing oversize fasteners, 

re-identifying the reworked side brace 

fitting and A-frame, and repair if 

necessary. The FAA is issuing this AD 

to address possible cracking of the Aframe. This condition, if not addressed, 

may lead to collapse of the main landing 

gear (MLG). See the MCAI for additional 

background information. 

Comments 

The FAA gave the public the 

opportunity to participate in developing 

this final rule. The FAA has considered 

the comment received. The Air Line 

Pilots Association, International 

(ALPA), stated that it supports the 

NPRM. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule as proposed, except for minor 

editorial changes. The FAA has 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing 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 

De Havilland Aircraft of Canada 

Limited has issued Service Bulletin 84– 

54–32, dated October 10, 2019. This 

service information describes 

procedures, depending on airplane 

configuration, for removing the fasteners 

on the nacelle A-frame side brace subassemblies, doing an eddy current 

inspection for cracking, cold-working 

the holes, installing oversize fasteners, 

and re-identifying the reworked side 

brace fitting and A-frame. 

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 

The FAA estimates that this AD 

affects 41 airplanes of U.S. registry. The 


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31600 Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

15 work-hours × $85 per hour = $1,275 ..................................................................................... $254 $1,529 $62,689 

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. 

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: 

2021–12–02 De Havilland Aircraft of 

Canada Limited (Type Certificate 

Previously Held by Bombardier, Inc.): 

Amendment 39–21589; Docket No. 

FAA–2021–0183; Project Identifier 

MCAI–2020–01408–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 20, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to De Havilland Aircraft 

of Canada Limited (type certificate 

previously held by Bombardier, Inc.) Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4081 through 4591 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Reason 

This AD was prompted by a report that a 

number of nacelle A-frames were not 

manufactured in accordance with 

engineering drawings. The holes in the side 

brace sub-assemblies were not cold-worked 

as required. As a result the side brace fitting 

might not meet its fatigue life, and cracking 

of the A-frame bottom flange may result. The 

FAA is issuing this AD to address possible 

cracking of the A-frame. This condition, if 

not addressed, may lead to collapse of the 

main landing gear (MLG). 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within the compliance time specified 

in paragraph (g)(2) of this AD, do the 

applicable actions specified in paragraphs 

(g)(1)(i) and (ii) of this AD. 

(i) For airplanes having serial numbers 

4081 through 4582 inclusive: Remove the 

fasteners on the nacelle A-frame side brace 

sub-assemblies, do an eddy current 

inspection for cracking on airplanes having 

30,000 total flight cycles or more, cold-work 

the holes, and install oversize fasteners, in 

accordance with Part A of paragraph 3.B. of 

the Accomplishment Instructions of De 

Havilland Aircraft of Canada Limited Service 

Bulletin 84–54–32, dated October 10, 2019. If 

any cracking is found, before further flight, 

repair the cracking using a method approved 

by the Manager, New York ACO Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or De Havilland Aircraft of Canada 

Limited’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(ii) For all airplanes: Re-identify the 

reworked side brace fitting and A-frame, in 

accordance with Part B of paragraph 3.B. of 

the Accomplishment Instructions of De 

Havilland Aircraft of Canada Limited Service 

Bulletin 84–54–32, dated October 10, 2019. 

(2) At the earlier of the times specified in 

paragraphs (g)(2)(i) and (ii) of this AD, do the 

applicable actions specified in paragraph 

(g)(1) of this AD. 

(i) Within 48 months or 8,000 flight hours 

after the effective date of this AD, whichever 

occurs first. 

(ii) At the later of the times specified in 

paragraphs (g)(2)(ii)(A) and (B) of this AD. 

(A) Before accumulating 40,000 total flight 

cycles. 

(B) Within 12 months or 1,290 flight cycles 

after the effective date of this AD, whichever 

occurs first. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO 

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 manager of the certification office, 

send it to ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 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 

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 


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Federal Register / Vol. 86, No. 113 / Tuesday, June 15, 2021 / Rules and Regulations 31601 

by the Manager, New York ACO Branch, 

FAA; or TCCA; or De Havilland Aircraft of 

Canada Limited’s TCCA DAO. If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) TCCA AD 

CF–2020–39, dated October 14, 2020, for 

related information. This MCAI may be 

found in the AD docket on the internet at 

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

and locating Docket No. FAA–2021–0183. 

(2) For more information about this AD, 

contact Antariksh Shetty, Aerospace 

Engineer, Airframe and Propulsion Section, 

FAA, New York ACO Branch, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531; 

email 9-avs-nyaco-cos@faa.gov. 

(j) 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) De Havilland Aircraft of Canada Limited 

Service Bulletin 84–54–32, dated October 10, 

2019. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact De Havilland Aircraft of 

Canada Limited, Q-Series Technical Help 

Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.com. 

(4) 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. 

(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/ibrlocations.html. 

Issued on May 25, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–12435 Filed 6–14–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0499; Project 

Identifier MCAI–2021–00571–E; Amendment 

39–21612; AD 2021–13–07] 

RIN 2120–AA64 

Airworthiness Directives; GE Aviation 

Czech s.r.o. (Type Certificate 

Previously Held by WALTER Engines 

a.s., Walter a.s., and MOTORLET a.s.) 

Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all GE 

Aviation Czech s.r.o. (GEAC) M601D– 

11, M601E–11, M601E–11A, M601E– 

11AS, M601E–11S, and M601F model 

turboprop engines. This AD was 

prompted by the manufacturer finding 

errors in the Airworthiness Limitation 

Section (ALS) of the Engine 

Maintenance Manual (EMM), including 

errors in the formula to determine the 

equivalent flight cycles (FCs) of critical 

parts and errors with certain part 

numbers (P/Ns). The manufacturer also 

determined that the life limit of a 

certain compressor case is not listed in 

the ALS section of the applicable EMM. 

This AD requires recalculating the life 

of critical parts and, depending on the 

results of the recalculation, replacement 

of these critical parts. This AD also 

requires replacement of a certain 

compressor case. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective June 30, 

2021. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 30, 2021. 

The FAA must receive comments on 

this AD by July 30, 2021. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this final rule, contact GE Aviation 

Czech s.r.o., Beranovy ́ch 65, 199 00 

Praha 18, Letnany, Czech Republic; 

phone: +420 222 538 111; fax: +420 222 

538 222. You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 1200 District Avenue, 

Burlington, MA 01803. For information 

on the availability of this material at the 

FAA, call (781) 238–7759. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0499. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0499; 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 street address for 

the Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7146; fax: (781) 238– 

7199; email: barbara.caufield@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Community, has issued EASA 

Emergency AD 2021–0125–E, dated May 

7, 2021 (referred to after this as ‘‘the 

MCAI’’), to address an unsafe condition 

for the specified products. The MCAI 

states: 

Errors have been identified in the ALS 

section of the EMM [Engine Maintenance 

Manual], including errors in the formula to 

determine the equivalent flight cycles of 

critical parts, and certain part numbers. It 

was also determined that, inadvertently, 

certain M601E engines have a compressor 

case P/N M601–154.61 installed, the life 

limit of which is not listed in the ALS section 

of the applicable EMM. 

These conditions, if not corrected, may 

lead to operation of an engine beyond the life 

limit of one or more critical parts, possibly 

resulting in failure of the engine and 

consequent reduced control of the aeroplane. 

To address this potential unsafe 

conditions, GEAC issued [GEAC Alert 

Service Bulletin (ASB) ASB–M601D–72–00– 

00–0075, ASB–M601E–72–00–00–0106, 

ASB–M601F–72–00–00–0057 and ASB– 

M601Z–72–00–00–0057 (issued as a single 

document)], providing instructions to 

recalculate the consumed life of certain 


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