Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations 16097 

(c) Applicability 

This AD applies to all Airbus SAS 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) through (4) of 

this AD. 

(1) Model A318–111 and –112 airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/furnishings. 

(e) Reason 

This AD was prompted by reports of 

damaged lower lateral fittings of the 80VU 

rack, and reports of new damage on airplanes 

on which certain optional service 

information had been accomplished. The 

FAA is issuing this AD to address damage or 

cracking of the 80VU fittings and supports, 

which could lead to possible disconnection 

of the cable harnesses to one or more 

computers, and if occurring during a critical 

phase of flight, could result in reduced 

control of the airplane. 

(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, European Union Aviation 

Safety Agency (EASA) AD 2021–0172, dated 

July 20, 2021 (EASA AD 2021–0172). 

(h) Exceptions to EASA AD 2021–0172 

(1) Where EASA AD 2021–0172 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The remarks section of EASA AD 2021– 

0172 does not apply to this AD. 

(3) Where paragraph (3) of EASA AD 2021– 

0172 specifies ‘‘any discrepancy,’’ for this AD 

‘‘any discrepancy’’ includes broken fittings, 

missing bolts, an electronics rack FIN 80VU 

that is in contact with structure, any bush 

that has migrated, burred material, and 

cracks. 

(i) Method of Compliance for Paragraphs (1), 

(2), and (3) of EASA AD 2021–0172 

Accomplishing inspections and correctives 

actions in accordance with the 

Accomplishment Instruction of Airbus 

Service Bulletin A320–25–1BKJ, Revision 02, 

dated April 9, 2020, with corrections 

referenced in the Airbus Technical 

Adaptation 80827186/024/2020, Issue 1, 

dated September 18, 2020, is an acceptable 

method of compliance for the inspections 

and corrective actions specified in 

paragraphs (1), (2), and (3) of EASA AD 

2021–0172. 

(j) Additional 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 (k) 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 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (j)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email sanjay.ralhan@

faa.gov. 

(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. 

(i) Airbus Service Bulletin A320–25–1BKJ, 

Revision 02, dated April 9, 2020. 

(ii) Airbus Technical Adaptation 

80827186/024/2020, Issue 1, dated 

September 18, 2020. 

(iii) European Union Aviation Safety 

Agency (EASA) AD 2021–0172, dated July 

20, 2021. 

(3) For EASA AD 2021–0172, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

EASA AD on the EASA website at https://

ad.easa.europa.eu. For Airbus service 

information identified in this AD, contact 

Airbus SAS, Airworthiness Office—EIAS, 

Rond-Point Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 61 

93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; internet 

https://www.airbus.com. 

(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. 

(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 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on March 8, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–05617 Filed 3–21–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1178; Project 

Identifier MCAI–2021–00986–R; Amendment 

39–21986; AD 2022–06–20] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited (Type Certificate 

Previously Held by Bell Helicopter 

Textron Canada Limited) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–20– 

06, which applied to certain Bell 

Helicopter Textron Canada Limited 

(now Bell Textron Canada Limited) 

Model 429 helicopters. AD 2020–20–06 

required repetitive inspections of 

certain cyclic and collective assembly 

bearings. This AD was prompted by new 

bellcrank assemblies, which have been 

upgraded with corrosion resistant steel 

bearings. This AD retains certain 

requirements of AD 2020–20–06, and 

depending on the inspection results, 

requires removing certain parts from 

service and installing the upgraded 

cyclic and collective bellcrank 


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16098 Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations 

assemblies. This AD also requires 

installing the upgraded collective and 

cyclic bellcrank assemblies on certain 

helicopters if not already installed, and 

prohibits installing certain bellcrank 

assemblies. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective April 26, 

2022. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J 1R4, 

Canada; telephone 1–450–437–2862 or 

1–800–363–8023; fax 1–450–433–0272; 

email productsupport@bellflight.com; or 

at https://www.bellflight.com/support/ 

contact-support. You may view this 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy, Room 

6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222– 

5110. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1178; 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 Transport Canada AD, 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: 

Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 1600 

Stewart Ave., Suite 410, Westbury, NY 

11590; telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–20–06, 

Amendment 39–21262 (85 FR 60356, 

September 25, 2020) (AD 2020–20–06). 

AD 2020–20–06 applied to Bell 

Helicopter Textron Canada Limited 

Model 429 helicopters with a bellcrank 

assembly part number (P/N) 429–001– 

523–101, 429–001–523–103, 429–001– 

532–101, or 429–001–532–103 installed. 

The NPRM published in the Federal 

Register on January 14, 2022 (87 FR 

2362). In the NPRM, the FAA proposed 

to retain some of the requirements of AD 

2020–20–06, and proposed to require, 

for certain serial-numbered helicopters, 

within 12 months after the helicopter 

was manufactured or 30 days, 

whichever occurs later, and thereafter at 

intervals not to exceed 6 months, 

disconnecting certain parts, stowing 

certain parts to prevent binding, and 

moving the cyclic stick and the 

collective stick to inspect for roughness 

in the flight control system and binding 

in the collective, lateral, and 

longitudinal arm assemblies. If any of 

these conditions exist, the NPRM 

proposed to require, before further 

flight, removing certain parts from 

service and installing upgraded 

bellcrank assemblies. 

Additionally, the NPRM proposed to 

require, for certain serial-numbered 

helicopters that do not have the 

upgraded bellcrank assemblies installed, 

within 24 months, installing the 

upgraded bellcrank assemblies, which 

would provide a terminating action for 

the recurring inspections. Finally, the 

NPRM proposed to prohibit installing 

any affected bellcrank assembly on any 

helicopter. 

The NPRM was prompted by 

Transport Canada AD CF–2016–11R3, 

dated August 30, 2021 (Transport 

Canada AD CF–2016–11R3), issued by 

Transport Canada, which is the aviation 

authority for Canada, to correct an 

unsafe condition for Bell Textron 

Canada Limited Model 429 helicopters, 

all serial numbers. Transport Canada 

advises of new collective and cyclic 

bellcrank assemblies which have been 

upgraded with corrosion resistant steel 

bearings. This condition, if not 

addressed, could result in restrictions in 

the collective, directional, or pitch 

control systems, and subsequent loss of 

helicopter control. 

Accordingly, Transport Canada AD 

CF–2016–11R3 requires for certain 

serial-numbered helicopters, within 12 

months from the helicopter manufacture 

date, or for helicopters that have 

exceeded the age threshold of 12 

months from the helicopter 

manufacturer date, within 30 days, and 

thereafter at intervals not to exceed 6 

months, performing a functional check 

of the flight controls to detect roughness 

in the pivot bearings and binding of the 

collective, lateral, or longitudinal arm 

end bearings of the bellcrank 

assemblies. If any roughness or binding 

is detected, Transport Canada AD CF– 

2016–11R3 requires replacement of each 

affected bellcrank assembly before 

further flight. Transport Canada AD CF– 

2016–11R3 also requires, within 24 

months, installing the upgraded 

collective and cyclic bellcrank 

assemblies and considers this action a 

terminating action to the recurring 

inspections. Finally, Transport Canada 

AD CF–2016–11R3 prohibits an affected 

bellcrank assembly from being installed 

on any helicopter. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified the FAA of the unsafe condition 

described in its AD. The FAA reviewed 

the relevant data, 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 helicopters. This AD 

is adopted as proposed in the NPRM. 

Related Service Information 

The FAA reviewed Bell Technical 

Bulletin 429–18–58, Revision B, dated 

August 23, 2021 (TB 429–18–58 Rev B), 

which specifies procedures to upgrade 

certain part-numbered bellcrank 

assemblies to the bellcrank assemblies 

that utilize the corrosion resistant steel 

bearings. 

The FAA also reviewed Bell 

Helicopter Alert Service Bulletin 429– 

15–21, Revision C, dated August 23, 

2021 (ASB 429–15–21 Rev C), which 

specifies moving the cyclic stick fore, 

aft, and laterally, and the collective stick 

up and down from stop to stop to detect 

deteriorated pivot bearings. ASB 429– 

15–21 Rev C also specifies inspecting to 

determine whether the bearings in the 

collective, lateral, and longitudinal arm 

assemblies rotate freely. If discrepant 

arm bearings are found, ASB 429–15–21 

Rev C specifies contacting Bell Product 

Support Engineering to report the 

findings and replacing the discrepant 

parts with serviceable parts. 

Differences Between This AD and 

Transport Canada AD CF–2016–11R3 

Transport Canada AD CF–2016–11R3 

provides requirements if the most recent 

functional check was performed using a 

hydraulic test stand as an alternate 

procedure. This AD provides no such 

alternate procedure. Transport Canada 

AD CF–2016–11R3 provides 

requirements for helicopters that have 

exceeded the age threshold of 12 

months from the helicopter 


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Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations 16099 

manufacturer date to complete the 

initial functional check within 30 days 

from the effective date of its AD. This 

AD requires the initial inspection 

within 12 months after the helicopter 

was manufactured or 30 days after the 

effective date of this AD, whichever 

occurs later. Transport Canada AD CF– 

2016–11R3 allows credit for the 

corrective actions of Part I if the initial 

functional check was accomplished 

prior to the effective date of Transport 

Canada AD CF–2016–11R3, whereas 

this AD does not. 

Costs of Compliance 

The FAA estimates that this AD 

affects 64 helicopters of U.S. Registry. 

Labor rates are estimated at $85 per 

work-hour. Based on these numbers, the 

FAA estimates the following costs to 

comply with this AD. 

Inspecting the cyclic and the 

collective bellcrank assemblies for 

roughness in the pivot bearings and 

binding in the collective, lateral, and 

longitudinal arm end bearings takes 

about 3 work-hours for an estimated 

cost of $255 per inspection cycle. 

Installing the upgraded collective and 

cyclic bellcrank assemblies takes about 

18 work-hours and parts cost about 

$1,750 for an estimated cost of $3,280 

per upgrade installation. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, 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: 

■ a. Removing Airworthiness Directive 

2020–20–06, Amendment 39–21262 (85 

FR 60356, September 25, 2020); and 

■ b. Adding the following new 

airworthiness directive: 

AD 2022–06–20 Bell Textron Canada 

Limited (Type Certificate Previously 

Held by Bell Helicopter Textron Canada 

Limited): Amendment 39–21986; Docket 

No. FAA–2021–1178; Project Identifier 

MCAI–2021–00986–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 26, 2022. 

(b) Affected ADs 

This AD replaces AD 2020–20–06, 

Amendment 39–21262 (85 FR 60356, 

September 25, 2020) (AD 2020–20–06). 

(c) Applicability 

This AD applies to Bell Textron Canada 

Limited (type certificate previously held by 

Bell Helicopter Textron Canada Limited) 

Model 429 helicopters, certificated in any 

category, with a bellcrank assembly part 

number (P/N) 429–001–523–101, 429–001– 

523–103, 429–001–532–101, or 429–001– 

532–103 installed. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2700, Flight Control System. 

(e) Unsafe Condition 

This AD was prompted by new bellcrank 

assemblies, which have been upgraded with 

corrosion resistant steel bearings. The FAA is 

issuing this AD to prevent corrosion of the 

bearings due to pooling at the bellcrank 

assembly from precipitation in the forward 

portion of the roof structure. The unsafe 

condition, if not addressed, could result in 

restrictions in the collective, directional, or 

pitch control systems, and subsequent loss of 

helicopter control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For Model 429 helicopters serial 

number (S/N) 57001 through 57296 

inclusive, within 12 months after the 

helicopter was manufactured or 30 days after 

the effective date of this AD, whichever 

occurs later, and thereafter at intervals not to 

exceed 6 months: 

(i) Disconnect the forward ends of the 

collective control tube, longitudinal stability 

and control augmentation system (SCAS) 

actuator, and lateral SCAS actuator. Stow the 

collective control tube and each SCAS 

actuator to prevent binding. 

(ii) Move the cyclic stick fore, aft, and 

laterally, and the collective stick up and 

down from stop to stop to determine if there 

is any roughness. If there is any roughness in 

the flight control system, before further flight, 

remove each pivot bearing P/N MS27646–41, 

each arm assembly bearing P/N MS27643–4, 

and each sleeve P/N 120–13–4A from service 

and install bellcrank assemblies P/N 429– 

001–523–101FM and 429–001–532–101FM; 

or 429–001–523–107FM and 429–001–532– 

107FM; or 429–001–523–107 and 429–001– 

532–107. 

(iii) Inspect the collective arm assembly P/ 

N 429–001–525–101, the lateral arm 

assembly P/N 429–001–527–101, and the 

longitudinal arm assembly P/N 429–001– 

530–101, by rotating each bearing and 

determining whether each bearing rotates 

freely. If there is any binding in any arm end 

bearing or on the longitudinal bellcrank 

assembly, before further flight, remove each 

pivot bearing P/N MS27646–41, each arm 

assembly bearing P/N MS27643–4, and each 

sleeve P/N 120–13–4A from service and 

install bellcrank assemblies P/N 429–001– 

523–101FM and 429–001–532–101FM; or 

429–001–523–107FM and 429–001–532– 

107FM; or 429–001–523–107 and 429–001– 

532–107. 

(2) For Model 429 helicopters S/N 57001 

through 57296 inclusive, unless already 

accomplished by following paragraphs 

(g)(1)(ii) or (iii) of this AD, within 24 months 

after the effective date of this AD, install 

bellcrank assemblies P/N 429–001–523– 

101FM and 429–001–532–101FM; or 429– 

001–523–107FM and 429–001–532–107FM; 

or 429–001–523–107 and 429–001–532–107. 

(3) As of the effective date of this AD, 

installing bellcrank assemblies P/N 429–001– 

523–101FM and 429–001–532–101FM; or 

429–001–523–107FM and 429–001–532– 

107FM; or 429–001–523–107 and 429–001– 


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16100 Federal Register / Vol. 87, No. 55 / Tuesday, March 22, 2022 / Rules and Regulations 

532–107, constitutes a terminating action for 

the recurring inspections required by 

paragraph (g)(1) of this AD. 

(4) As of the effective date of this AD, do 

not install any bellcrank assembly P/N 429– 

001–523–101, 429–001–523–103, 429–001– 

532–101, or 429–001–532–103 on any 

helicopter. 

(h) Special Flight Permits 

Special flight permits are prohibited. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) 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. 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 manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (j)(1) of this AD. 

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

(2) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

(2) For service information identified in 

this AD, contact Bell Textron Canada 

Limited, 12,800 Rue de l’Avenir, Mirabel, 

Quebec J7J 1R4, Canada; telephone 1–450– 

437–2862 or 1–800–363–8023; fax 1–450– 

433–0272; email productsupport@

bellflight.com; or at https://

www.bellflight.com/support/contact-support. 

You may view this referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. For information on the availability 

of this material at the FAA, call (817) 222– 

5110. 

(3) The subject of this AD is addressed in 

Transport Canada AD CF–2016–11R3, dated 

August 30, 2021. You may view the 

Transport Canada AD on the internet at 

https://www.regulations.gov in Docket No. 

FAA–2021–1178. 

(k) Material Incorporated by Reference 

None. 

Issued on March 10, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–05664 Filed 3–21–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2021–0816; Airspace 

Docket No. 21–ANM–27] 

RIN 2120–AA66 

Modification of Class D and Class E 

Airspace, and Establishment of Class 

E Airspace; Southwest Oregon 

Regional Airport, OR; Correction 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting a final 

rule that appeared in the Federal 

Register on March 3, 2022. The rule 

modified the Class D and Class E surface 

airspace, established Class E airspace 

designated as an extension to Class D & 

E surface areas, Class E airspace 

beginning at 700 feet above the surface, 

removed navigational aids (NAVAIDs) 

from text headers, and made 

administrative changes to the legal 

descriptions at Southwest Oregon 

Regional Airport, North Bend, OR. The 

Final Rule did not explain the 

purposeful removal of Class E airspace 

beginning at 1,200 feet above the 

surface, nor did it properly exclude the 

Sunnyhill Airport cut-out. This action 

adds verbiage explaining the removal of 

Class E airspace beginning at 1,200 feet 

above the surface, and corrects the legal 

description for the newly established 

Class E airspace designated as an 

extension to Class D & E surface areas 

to properly exclude Sunnyhill Airport, 

OR. 

DATES: Effective 0901 UTC, May 19, 

2022. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.11 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Nathan A. Chaffman, Federal Aviation 

Administration, Western Service Center, 

Operations Support Group, 2200 S 

216th Street, Des Moines, WA 98198; 

telephone (206) 231–3460. 

SUPPLEMENTARY INFORMATION: 

History 

The FAA published a final rule in the 

Federal Register (87 FR 11955; March 3, 

2022) for Docket FAA–2021–0816, 

which modified the Class D and Class 

E surface airspace, established Class E 

airspace designated as an extension to 

Class D & E surface areas, modified the 

Class E airspace beginning at 700 feet 

above the surface, removed navigational 

aids (NAVAIDs) from text headers, and 

made administrative changes to the 

legal descriptions at Southwest Oregon 

Regional Airport, North Bend, OR. 

Subsequent to publication, the FAA 

identified that the removal of Class E 

airspace beginning at 1,200 feet above 

the surface at the airport was not 

disclosed. This airspace was removed as 

it is not needed at Southwest Oregon 

Regional Airport. The Bend E6 en route 

domestic airspace area beginning at 

1,200 feet above the surface provides 

sufficient containment to accommodate 

arriving instrument flight rules (IFR) 

operations at 1,500 feet and higher 

above the surface and departing IFR 

operations from the point they reach 

1,200 feet above the surface. 

Additionally, it was discovered after 

publication of the Final Rule that the 

legal description for the Class E airspace 

designated as an extension to Class D & 

E surface areas did not properly exclude 

the Sunnyhill Airport, OR cut-out. This 

action corrects those errors. 

Class D, Class E2, Class E4, and Class 

E5 airspace designations are published 

in paragraphs 5000, 6002, 6004, and 

6005, respectively, of FAA Order JO 

7400.11F, dated August 10, 2021, and 

effective September 15, 2021, which is 

incorporated by reference in 14 CFR 

71.1. The Class D and Class E airspace 

designations listed in this document 

will be published subsequently in FAA 

Order JO 7400.11. 

Correction to Final Rule 

Accordingly, pursuant to the 

authority delegated to me, Amendment 

of Class D and Class E airspace, and 

Establishment of Class E airspace; 

Southwest Oregon Regional Airport, 

North Bend, OR, published in the 

Federal Register of March 3, 2022 (87 

FR 11955), FR Doc. 2022–04326, is 

corrected as follows: 

§ 71.1 [Corrected] 

■ 1. On page 11957, in the first column, 

beginning on line 8, the legal 

description for ANM OR E4 is corrected 

to read: 

ANM OR E4 North Bend, OR [New] 

Southwest Oregon Regional Airport, OR 

(Lat. 43°25′01′′ N, long. 124°14′49′′ W) 

Sunnyhill Airport, OR 

(Lat. 43°28′59′′ N, long. 124°12′10′′ W) 

That airspace extending upward from the 

surface within 3.6 miles north and 3.5 miles 

south of the 092° bearing from the airport, 

extending from the Southwest Oregon 

Regional Airport Class D 4.2-mile radius to 

11.7 miles east of the airport, excluding that 

airspace within a 0.9-mile radius of 

Sunnyhill Airport, and within 2.0 miles 

southeast and 2.1 miles northwest of the 242° 


lotter on DSK11XQN23PROD with RULES1