4800 Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Rules and Regulations 

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) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2020–0013, dated January 29, 

2020. You may view the EASA AD at https:// 

www.regulations.gov in Docket No. FAA– 

2021–0843. 

(j) 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 this AD specifies otherwise. 

(i) Umlaut Vendor Service Bulletin Doc. 

No. P3VSB000001, Issue C, dated December 

13, 2019. 

(ii) Umlaut Vendor Service Bulletin Doc. 

No. P3VSB000001, Issue D, dated September 

9, 2020. 

(3) For Umlaut service information 

identified in this AD, contact Umlaut 

Engineering, Blohmstrasse 12, Hamburg, 

Germany 21079, Phone: 49 0 40 75 25 779 

0, email: hafex@umlaut.com, or web: https:// 

www.umlaut.com/hafex. 

(4) 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. 

(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 December 21, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01859 Filed 1–28–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0947; Project 

Identifier MCAI–2021–00195–R; Amendment 

39–21889; AD 2022–01–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Helicopters Model AS350B, 

AS350BA, AS350B1, AS350B2, 

AS350B3, AS350D, EC130B4, and 

EC130T2 helicopters; AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and 

AS355NP helicopters; and Model SA– 

365C1, SA–365C2, SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. This AD was prompted a 

report of increased vibration during 

flight. This AD requires the application 

of alignment markings on, and repetitive 

inspections of, the main rotor (MR) 

pitch rod upper links and, depending on 

findings, the accomplishment of 

applicable corrective actions, as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective March 7, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 7, 2022. 

ADDRESSES: For EASA material 

incorporated by reference (IBR) in this 

AD, contact EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; 

telephone +49 221 8999 000; email 

ADs@easa.europa.eu; internet 

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

material on the EASA website at https:// 

ad.easa.europa.eu. You may view this 

material 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. It is also 

available in the AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0947. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0947; 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 EASA 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 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0048, 

dated February 16, 2021 (EASA AD 

2021–0048), to correct an unsafe 

condition for Airbus Helicopters 

(formerly Eurocopter, Eurocopter 

France, Ae ́rospatiale) Model AS 350 B, 

AS 350 BA, AS 350 BB, AS 350 B1, AS 

350 B2, AS 350 B3, AS 350 D, EC 130 

B4, and EC 130 T2 helicopters; Model 

AS 355 E, AS 355 F, AS 355 F1, AS 355 

F2, AS 355 N, and AS 355 NP 

helicopters; and Model SA 365 C1, SA 

365 C2, SA 365 C3, SA 365 N, SA 365 

N1, AS 365 N2, and AS 365 N3 

helicopters; all serial numbers. Model 

AS 350 BB and SA 365 C3 helicopters 

are not certificated by the FAA and are 

not included on the U.S. type certificate 

data sheet; this AD therefore does not 

include those helicopters in the 

applicability. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Helicopters Model 

AS350B, AS350BA, AS350B1, 

AS350B2, AS350B3, AS350D, EC130B4, 

and EC130T2 helicopters; Model 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, and AS355NP helicopters; and 

Model SA–365C1, SA–365C2, SA–365N, 

SA–365N1, AS–365N2, and AS 365 N3 

helicopters. The NPRM published in the 

Federal Register on October 29, 2021 

(86 FR 59892). The NPRM was 

prompted by a report of increased 

vibration during flight. The NPRM 

proposed to require the application of 

alignment markings on, and repetitive 

inspections of, the MR pitch rod upper 

links and, depending on findings, the 

accomplishment of applicable corrective 

actions, as specified in EASA AD 2021– 

0048. 

The FAA is issuing this AD to address 

loss of tightening torque of the screws 

connecting the MR pitch rods to the 

horns of the upper links. This condition, 

if not addressed, could result in loss of 

one or more MR pitch rod upper links, 

possibly resulting in loss of control of 

the helicopter. See EASA AD 2021–0048 

for additional background information. 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Rules and Regulations 4801 

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 EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about 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. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0048 requires the 

application of alignment markings on 

the screw, washer, nut, and horn on 

both sides of each MR pitch rod upper 

link, and repetitive visual inspections of 

the two alignment markings to 

determine if the markings are aligned on 

both sides. If, during any inspection the 

markings on one or both sides of an MR 

pitch rod upper link are found 

misaligned, the additional actions and 

corrective actions include the following. 

• Measuring the tightening torque 

value of the nut of the pitch rod upper 

link and adjusting the nut if it does not 

meet the specified criteria. 

• Inspecting the pitch rod upper link 

to determine the condition of the bush 

(bushing) and spherical bearing and to 

determine if the cups are tight (paint 

mark in place), and measuring the play. 

If there is seizing, carbide chips, or the 

cups are loose (paint mark not in place), 

the corrective actions include replacing 

the spherical bearing. If the play 

measurement is greater than the 

specified measurement the corrective 

action is replacing the rod end fitting. 

Additional actions include checking the 

bonding and condition of the retaining 

ring and inspecting the pitch rod bodies 

for evidence of any impact, scratch, 

strike, or corrosion. 

• Inspecting the pitch rods for 

chipped finish paint, scratches, impacts, 

and cracking, and measuring the play. If 

paint is chipped the corrective action is 

repair (sanding the affected area and 

applying touch-up primer and paint). If 

there is any scratch, an impact with a 

depth equal to or greater than the 

specified measurement, or any crack, 

the corrective action is replacing the 

pitch rod. If the play measurement is 

greater than 0.25 mm or there is 

cracking, the corrective action is 

replacing the spherical bearing. An 

additional action, if a helicopter was 

involved in an incident, is inspecting 

the straightness of the rod body ‘‘R’’ and 

replacing the pitch rod if the 

straightness of the rod body is greater 

than 0.5 mm. 

• Inspecting the pitch horn for any 

evidence of impact, scratch, corrosion, 

chipped paint, cracking, and any 

elongated attachment hole; and 

inspecting the bonding of the retaining 

ring and measuring dimension ‘‘X’’ of 

the retaining ring. If there is any 

evidence of impact, scratch, or 

corrosion, and the depth meets the 

specified criteria, the corrective actions 

include touching up the affected area 

with an abrasive cloth and applying a 

protective coating and a coat of primer. 

If there is any cracking, elongated 

attachment hole, or the impact, scratch, 

or corrosion depth exceeds the specified 

criteria, the corrective action is 

replacing the pitch horn. If paint is 

chipped the corrective actions include 

sanding the affected area and applying 

touch-up primer and paint. If the 

retaining ring has debonded the 

corrective action is to rebond the 

retaining ring. If dimension ‘‘X’’ of the 

retaining ring exceeds the specified 

criteria, the corrective action is 

replacing the retaining ring. 

• Measuring the geometry of ‘‘G’’ of 

the pitch horn and replacing the pitch 

horn if the dimension is not within the 

specified range. 

• Installing new split pins, nuts, 

washers, and a screw on the pitch rod 

upper link. 

This material 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 1,266 helicopters of U.S. 

Registry. The FAA estimates the 

following costs to comply with this AD. 

ESTIMATED COSTS * 

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ......... 0.50 work-hour × $85 per hour = $42.50 per 

inspection cycle..

$0 $42.50 per inspection cycle. $53,805 per inspection 

cycle. 

* The FAA has determined that application of alignment markings would take a minimal amount of time at a nominal cost. 

The FAA estimates the following 

costs to do any necessary actions that 

would be required based on the results 

of the inspection. The agency has no 

way of determining the number of 

aircraft that might need these actions: 

ON-CONDITION COSTS * 

Action Labor cost Parts cost Cost per 

product 

Screw, Washer, Nut, and Split Pin Replacement ........ 1 work-hour × $85 per hour = $85 ............................... $40 $125 

Spherical Bearing Replacement ................................... 4 work hours × $85 per hour = $340 ........................... 500 840 

Pitch Rod Replacement ................................................ 4 work hours × $85 per hour = $340 ........................... 3,000 3,340 

Pitch Horn Replacement .............................................. 16 work hours × $85 per hour = $1360 ....................... 4,000 5,360 

* The FAA has determined that ‘‘repair’’ of chipped paint would take a minimal amount of time at a nominal cost. 

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. 


khammond on DSKJM1Z7X2PROD with RULES
4802 Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Rules and Regulations 

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: 

2022–01–01 Airbus Helicopters: 

Amendment 39–21889; Docket No. 

FAA–2021–0947; Project Identifier 

MCAI–2021–00195–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 7, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus Helicopters 

helicopters, certificated in any category, 

identified in paragraphs (c)(1) through (3) of 

this AD, all serial numbers. 

(1) Model AS350B, AS350BA, AS350B1, 

AS350B2, AS350B3, AS350D, EC130B4, and 

EC130T2 helicopters. 

(2) Model AS355E, AS355F, AS355F1, 

AS355F2, AS355N, and AS355NP 

helicopters. 

(3) Model SA–365C1, SA–365C2, SA– 

365N, SA–365N1, AS–365N2, and AS 365 N3 

helicopters. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, Main Rotor System. 

(e) Unsafe Condition 

This AD was prompted by a report of 

increased vibration during flight on an 

Airbus Helicopters Model AS 365 helicopter. 

Subsequent investigation found a total loss of 

tightening torque of one screw connecting the 

main rotor (MR) pitch rod to the horn of its 

upper link, which led to abnormal wear of 

the screw and consequently increased the 

vibrations coming from the MR control chain 

to the pilot’s flight controls. The FAA is 

issuing this AD to address loss of tightening 

torque of the screws connecting the MR pitch 

rods to the horns of the upper links. The 

unsafe condition, if not addressed, could 

result in loss of one or more MR pitch rod 

upper links, possibly resulting in loss of 

control of the helicopter. 

(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 2021–0048, dated 

February 16, 2021 (EASA AD 2021–0048). 

(h) Exceptions to EASA AD 2021–0048 

(1) Where EASA AD 2021–0048 requires 

compliance in terms of flight hours, this AD 

requires using hours time-in-service. 

(2) Where EASA AD 2021–0048 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where the service information 

referenced in EASA AD 2021–0048 specifies 

discarding parts, this AD requires removing 

those parts from service. 

(4) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0048. 

(5) Where a work card in the service 

information referenced in EASA AD 2021– 

0048 specifies returning a part to the 

manufacturer, this AD does not include that 

requirement. 

(6) For Model AS350 helicopters: For the 

visual inspection of the pitch rod upper link, 

where a work card in the service information 

referenced in EASA AD 2021–0048 specifies 

to do an inspection of a pitch rod body for 

any dent, impact, scratch, or corrosion, and 

any dent, impact, scratch, or corrosion is 

found, this AD requires replacing the pitch 

rod before further flight. 

(7) For Model AS355 helicopters: For the 

visual inspection of the pitch rod upper link, 

where a work card in the service information 

referenced in EASA AD 2021–0048 specifies 

to do an inspection of a pitch rod body for 

any impact, scratch, strike, or corrosion, and 

any impact, scratch, strike, or corrosion is 

found, this AD requires replacing the pitch 

rod before further flight. 

(8) For Model SA365 helicopters: For the 

visual inspection of the pitch rod upper link, 

where a work card in the service information 

referenced in EASA AD 2021–0048 specifies 

to ‘‘check bonding and state retaining ring on 

the pitch rods,’’ and any discrepancy (e.g., 

disbonding) is found and no corrective action 

is specified, before further flight, contact the 

Manager, General Aviation & Rotorcraft 

Section, International Validation Branch 

FAA; or EASA; or Airbus Helicopters’ EASA 

Design Organization Approval (DOA); for 

approved corrective actions, and accomplish 

those actions before further flight. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(9) For Model SA365 helicopters: For the 

visual inspection of the pitch horn, if any 

discrepancy (corrosion, scratch, impact, 

crack, or debonded retaining ring) is found 

during the inspection of the pitch horn and 

there is no corrective action specified in the 

work card in the service information 

referenced in EASA AD 2021–0048, before 

further flight, contact the Manager, General 

Aviation & Rotorcraft Section, International 

Validation Branch, FAA; or EASA; or Airbus 

Helicopters’ EASA DOA; for approved 

corrective actions, and accomplish those 

actions before further flight. If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(10) For Model AS365 helicopters: For the 

visual inspection of the pitch horn, where a 

work card in the service information 

referenced in EASA AD 2021–0048 specifies 

to do a dye penetrant inspection ‘‘if in 

doubt,’’ this AD requires doing a dye 

penetrant inspection. 

(11) For Model AS350 and EC130 

helicopters: Where a work card in the service 

information referenced in EASA AD 2021– 

0048 refers to ‘‘the pitch change lever,’’ for 

this AD, that term is equivalent to ‘‘pitch 

horn.’’ 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0048 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, are prohibited. 

(k) 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 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 87, No. 20 / Monday, January 31, 2022 / Rules and Regulations 4803 

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 (l) 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. 

(l) Related Information 

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. 

(m) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0048, dated February 16, 

2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0048, 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 the 

EASA material on the EASA website at 

https://ad.easa.europa.eu. 

(4) 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. 

This material may be found in the AD docket 

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

for and locating Docket No. FAA–2021–0947. 

(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 December 21, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01864 Filed 1–28–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2021–0925; Airspace 

Docket No. 21–ANM–49] 

RIN 2120–AA66 

Establishment of Class E Airspace; 

Joseph State Airport, OR 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E airspace extending upward from 700 

feet above the surface of the earth at 

Joseph State Airport, Joseph, OR. The 

establishment of airspace supports the 

airport’s transition from visual flight 

rules to instrument flight rule (IFR) 

operations and ensures the safety and 

management of IFR operations within 

the National Airspace System. 

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 JO 7400.11 and publication of 

conforming amendments. 

ADDRESSES: FAA Order JO 7400.11F, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed online at https://

www.faa.gov/air_traffic/publications/. 

For further information, you can contact 

the Airspace Policy Group, Federal 

Aviation Administration, 800 

Independence Avenue SW, Washington, 

DC 20591; telephone: (202) 267–8783. 

FAA Order JO 7400.11F is also available 

for inspection at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

FAA Order JO 7400.11F at NARA, email 

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

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

ibr-locations.html. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Chaffman, Federal Aviation 

Administration, Western Service Center, 

Operations Support Group, 2200 S. 

216th Street, Des Moines, WA 98198; 

telephone (206) 231–3460. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority, as it would 

establish Class E airspace extending 

upward from 700 feet above ground 

level to support IFR operations at Joseph 

State Airport, Joseph, OR. 

History 

The FAA published a notice of 

proposed rulemaking in the Federal 

Register (86 FR 60783; November 4, 

2021) for Docket No. FAA–2021–0925 to 

establish Class E airspace at Joseph State 

Airport, Joseph, OR. Interested parties 

were invited to participate in this 

rulemaking effort by submitting written 

comments on the proposal to the FAA. 

No comments were received. 

Class E5 airspace designations are 

published in paragraph 6005 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 E airspace 

designations listed in this document 

will be published subsequently in FAA 

Order JO 7400.11. 

Availability and Summary of 

Documents for Incorporation by 

Reference 

This document amends FAA Order JO 

7400.11F, Airspace Designations and 

Reporting Points, dated August 10, 

2021, and effective September 15, 2021. 

FAA Order JO 7400.11F is publicly 

available as listed in the ADDRESSES

section of this document. FAA Order JO 

7400.11F lists Class A, B, C, D, and E 

airspace areas, air traffic service routes, 

and reporting points. 

The Rule 

The FAA is amending 14 CFR part 71 

by establishing Class E airspace 

extending upward from 700 feet above 

the surface of the earth at Joseph State 

Airport, Joseph, OR. 

The Class E airspace is established 

extending upward from 700 feet above 

ground level within a 6.5-mile radius of 

the airport, beginning at the 316° 

bearing from the airport clockwise to the 

170° bearing from the airport, then to 

the point of beginning 6.5 miles 

northwest of the airport. This airspace is 

designed to contain the new Area 

Navigation (RNAV) approaches into the 

airport and instrument departures from 

the airport. The airspace supports the 

airport’s transition from visual flight 

rules to IFR operations. 


khammond on DSKJM1Z7X2PROD with RULES