Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 30405 

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: 

2022–11–03 Airbus SAS: Amendment 39– 

22053; Docket No. FAA–2022–0585; 

Project Identifier MCAI–2022–00603–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 3, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A350–941 and –1041 airplanes, certificated 

in any category, as identified in European 

Union Aviation Safety Agency (EASA) 

Emergency AD 2022–0079–E, dated May 5, 

2022 (EASA Emergency AD 2022–0079–E). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Unsafe Condition 

This AD was prompted by an indication 

that both elevator actuators of the PRIMary 

flight control computers (PRIMs) were 

considered faulty due to incorrect 

instructions with a new PRIM standard. The 

FAA is issuing this AD to address the faulty 

standard, which could lead to loss of control 

of the elevator surfaces, possibly resulting in 

loss of 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, EASA Emergency AD 

2022–0079–E. 

(h) Exceptions to EASA Emergency AD 2022– 

0079–E 

(1) Where EASA Emergency AD 2022– 

0079–E refers to its effective date, this AD 

requires using the effective date of this AD. 

(2) Where paragraph (1) of EASA 

Emergency AD 2022–0079–E specifies to 

‘‘inform all flight crews, and, thereafter, 

operate the aeroplane accordingly,’’ this AD 

does not require those actions as those 

actions are already required by existing FAA 

operating regulations. 

(3) Where paragraph (3) of EASA 

Emergency AD 2022–0079–E specifies to 

‘‘implement the instructions of the MER, as 

defined in [the EASA Emergency] AD,’’ for 

this AD replace that phrase with ‘‘revise the 

operator’s existing FAA-approved minimum 

equipment list (MEL) to incorporate the 

instructions of the MER.’’ 

(4) Where paragraph (4) of EASA 

Emergency AD 2022–0079–E specifies 

‘‘operating the aeroplane accordingly,’’ this 

AD does not require that action as that action 

is already required by existing FAA operating 

regulations. 

(5) The ‘‘Remarks’’ section of EASA 

Emergency AD 2022–0079–E does not apply 

to this AD. 

(i) 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 (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 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; phone 206–231– 

3225; email Dan.Rodina@faa.gov. 

(k) 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) Emergency AD 2022–0079–E, dated 

May 5, 2022. 

(ii) [Reserved] 

(3) For EASA Emergency AD 2022–0079– 

E, 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. 

(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 May 13, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–10865 Filed 5–17–22; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0099; Project 

Identifier 2019–CE–019–AD; Amendment 

39–22045; AD 2022–10–07] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate Previously 

Held by Bombardier, Inc. and de 

Havilland, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 89–24–06 

R1, which applied to all Boeing of 

Canada, Ltd. and de Havilland (now 

Viking Air Limited) Model DHC–6–1, 

DHC–6–100, DHC–6–200, and DHC–6– 

300 airplanes. AD 89–24–06 R1 required 

repetitively inspecting the elevator 

quadrant for damage and taking 

corrective action as necessary. Since the 

FAA issued AD 89–24–06 R1, Transport 

Canada, the aviation authority for 

Canada, revised its mandatory 

continuing airworthiness information 

(MCAI) to correct this unsafe condition 

on these products. This AD retains the 

actions required by AD 89–24–06 R1, 

extends the compliance time intervals 

for the repetitive inspections, adds 

Model DHC–6–400 airplanes to the 

applicability, and adds a fluorescent 

penetrant inspection requirement. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective June 23, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 23, 2022. 


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30406 Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 

ADDRESSES: For service information 

identified in this final rule, contact 

Viking Air Ltd., 1959 de Havilland Way, 

Sidney British Columbia, Canada V8L 

5V5; phone: (800) 663–8444; email: 

continuing.airworthiness@

vikingair.com; website: https://

www.vikingair.com. You may view this 

service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information 

on the availability of this material at the 

FAA, call (817) 222–5110. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0099. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0099; 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: 

Darren Gassetto, Aviation Safety 

Engineer, New York ACO Branch, FAA, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (516) 228– 

7323; email: 9-avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 89–24–06 R1, 

Amendment 39–6670 (Docket No. 89– 

CE–29–AD; 55 FR 29347, July 19, 1990) 

(AD 89–24–06 R1). AD 89–24–06 R1 

applied to all Boeing of Canada, Ltd. 

and de Havilland (type certificate 

currently held by Viking Air Limited) 

Model DHC–6–1, DHC–6–100, DHC–6– 

200, and DHC–6–300 airplanes. AD 89– 

24–06 R1 required repetitively 

inspecting the elevator quadrant, part 

number (P/N) C6CFM 1138–27 (Pre Mod 

6/1394), P/N C6CFM 1450–27 (Post Mod 

6/1394 or production cut-in (PCI) serial 

number (S/N) 331, Pre Mod 6/1678), or 

P/N C6CFM 1450–29 (Post Mod 6/1678 

or PCI S/N 602), for distortion (warping, 

buckling, and score marks on the 

quadrant topside face caused by rubbing 

against the side of the cable guard) and 

replacing if distortion is found. AD 89– 

24–06 R1 also required inspecting the 

elevator quadrant mounting support 

bracket, P/N C6CFM 1142–1, for cracks 

if distortion in the elevator quadrant is 

found and replacing any cracked P/N 

C6CFM 1142–1. The FAA issued AD 

89–24–06 R1 to prevent failure of the 

flight control system, which could result 

in loss of control of the airplane. 

The NPRM published in the Federal 

Register on February 11, 2022 (87 FR 

7965). The NPRM was prompted by 

Transport Canada AD CF–1972–06R5, 

dated June 22, 2018 (referred to after 

this as ‘‘the MCAI’’), issued by 

Transport Canada, which is the aviation 

authority for Canada. The MCAI states: 

Damage to the flight control system of 

DHC–6 aeroplanes was found during 

inspection. The damage has been attributed 

to ground gusts. The damage included cracks 

in the base of the lower control column, 

cracks and buckles in the elevator/rudder 

pulley bracket, and distortion of the elevator 

quadrant. Damage to the elevator quadrant 

may produce abnormal loads on the quadrant 

support bracket that damage the bracket. 

Damaged flight control components may 

fail when subjected to service loads, resulting 

in loss of control of the aeroplane. 

This revision of the [Transport Canada] AD 

clarifies the applicability of the corrective 

actions and endorses Service Bulletin (SB) 6/ 

511 as a means of accomplishing some of the 

required inspections. In corrective action Part 

III, dye penetrant inspection has been 

replaced by fluorescent penetrant inspection. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0099. 

In the NPRM, the FAA proposed to 

retain the actions of AD 89–24–06 R1, 

extend the compliance time intervals for 

the repetitive inspections, add Model 

DHC–6–400 airplanes to the 

applicability, and add a fluorescent 

penetrant inspection requirement. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

the Airline Pilots Association, 

International, which supported the 

NPRM without change. 

Conclusion 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with this 

State of Design Authority, it has notified 

the FAA of the unsafe condition 

described in the MCAI referenced 

above. The FAA reviewed the relevant 

data, considered the comment received, 

and determined that air safety requires 

adopting the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. This AD is adopted as 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Viking DHC–6 

(Twin Otter) Service Bulletin 6–511, 

Revision A, dated June 22, 1990. This 

service bulletin specifies procedures for 

repetitively inspecting the elevator 

quadrant for distortion (warping, 

buckling, and score marks), performing 

a one-time dye penetrant inspection of 

the elevator quadrant support bracket 

for cracks, and taking corrective actions. 

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. 

Differences Between This AD and the 

MCAI 

The MCAI addresses actions on the 

control column lower assembly, the 

elevator pulley bracket system, and the 

elevator quadrant. This AD only 

requires actions on the elevator 

quadrant and elevator quadrant support 

bracket. The FAA is not requiring the 

repetitive inspections of the control 

column lower sub-assembly, lower 

horizontal torque tube, and top and 

bottom channels of the pulley bracket 

assembly, and the modifications that 

terminate those inspections, because 

those actions are addressed by AD 69– 

05–01 R2, Amendment 39–3824 (Docket 

No. 79–EA–63; 45 FR 45258, July 3, 

1980); and AD 69–8–12 R1, Amendment 

39–867 (Docket No. 69–EA–133; 34 FR 

18226, November 14, 1969). 

Costs of Compliance 

The FAA estimates that this AD 

affects 133 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 


jspears on DSK121TN23PROD with RULES1
Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 30407 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

airplane 

Cost on U.S. 

operators 

Elevator quadrant and support bracket visual inspection.0.5 work-hour × $85 

per hour = $42.50.

Not Applicable .. $42.50 per inspection 

cycle.

$5,652.50 (for the affected 133 airplanes) per inspection cycle. 

Fluorescent penetrant inspection of 

the elevator quadrant support 

bracket.

1 work-hour × $85 per 

hour = $85.

Not Applicable .. $85 ............................ $10,795 (for the affected 127 airplanes). 

The FAA estimates the following 

costs to do any repairs or replacements 

that would be required based on the 

results of the inspections. The FAA has 

no way of determining the number of 

airplanes that might need these repairs/ 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

airplane 

Replacement of elevator quadrant ............................... 1.5 work-hours × $85 per hour = $127.50 ................... $825 $952.50 

Fluorescent penetrant inspection of the elevator quadrant support bracket.1 work-hour × $85 per hour = $85 ............................... Not Applicable 85 

Replacement of elevator quadrant support bracket ..... 2 work-hours × $85 per hour = $170 ........................... 485 655 

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 

The FAA has determined that this AD 

will not have federalism implications 

under Executive Order 13132. This AD 

will not have a substantial direct effect 

on the States, on the relationship 

between the national government and 

the States, or on the distribution of 

power and responsibilities among the 

various levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) 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 

89–24–06 R1, Amendment 39–6670 

(Docket No. 89–CE–29–AD; 55 FR 

29347, July 19, 1990); and 

■ b. Adding the following new 

airworthiness directive: 

2022–10–07 Viking Air Limited (Type 

Certificate Previously Held by 

Bombardier, Inc. and de Havilland, 

Inc.): Amendment 39–22045; Docket No. 

FAA–2022–0099; Project Identifier 

2019–CE–019–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 23, 2022. 

(b) Affected ADs 

This AD replaces AD 89–24–06 R1, 

Amendment 39–6670 (Docket No. 89–CE–29– 

AD; 55 FR 29347, July 19, 1990) (AD 89–24– 

06 R1). 

(c) Applicability 

This AD applies to Viking Air Limited 

(Type Certificate previously held by 

Bombardier, Inc. and de Havilland, Inc.) 

Model DHC–6–1, DHC–6–100, DHC–6–200, 

DHC–6–300, and DHC–6–400 airplanes, all 

serial numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2700, Flight Control System. 

(e) Unsafe Condition 

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 damage to 

the flight control system. The FAA is issuing 

this AD to prevent failure of the flight control 

system. The unsafe condition, if not 

addressed, could result in loss of control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Elevator Quadrant and Support Brackets: 

Inspections, Replacements, and 

Modifications 

(1) Visually inspect the elevator quadrant 

for indications of distortion (warping, 

buckling, or score marks) by following 

paragraphs III.A.2.(a) and III.A.2.(b) of the 

Accomplishment Instructions in Viking 

DHC–6 (Twin Otter) Service Bulletin 6–511, 

Revision A, dated June 22, 1990 (DHC–6 SB 

6–511, Revision A) at the following 

applicable compliance times: 

(i) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes, 

before further flight after the effective date of 


jspears on DSK121TN23PROD with RULES1
30408 Federal Register / Vol. 87, No. 97 / Thursday, May 19, 2022 / Rules and Regulations 

this AD or within 400 hours time-in-service 

(TIS) after the last inspection required by AD 

89–24–06 R1, whichever occurs later, and 

thereafter at intervals not to exceed 400 hours 

TIS; or 

(ii) For Model DHC–6–400 airplanes, 

before further flight after the effective date of 

this AD and thereafter at intervals not to 

exceed 400 hours TIS. 

Note 1 to paragraph (g)(1): The elevator 

quadrant may be identified as part number 

(P/N) C6CFM1138–27 (Pre Mod 6/1394), P/N 

C6CFM1450–27 (Post Mod 6/1394 or 

production cut-in (PCI) serial number (S/N) 

331, Pre Mod 6/1678), or P/N C6CFM1450– 

29 (Post Mod 6/1678 or PCI S/N 602), and is 

referred to as assembly P/N C6CF1137–1, –3, 

–5, or –7. 

(2) If any indication of distortion is found 

on the elevator quadrant during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, replace the 

elevator quadrant with a serviceable part and 

inspect the elevator quadrant support bracket 

assembly for cracks by following paragraphs 

III.B.1. through III.B.4.(b) of the 

Accomplishment Instructions in DHC–6 SB 

6–511, Revision A. This AD requires that you 

do a fluorescent penetrant inspection as the 

type of required dye penetrant inspection. If 

a crack is found in the elevator quadrant 

support bracket, before further flight, replace 

with a serviceable part by following 

paragraphs III.B.5 through III.B.12 of the 

Accomplishment Instructions in DHC–6 SB 

6–511, Revision A. 

(3) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes: 

Within 400 hours TIS after the effective date 

of this AD, unless already done within the 

preceding 12 months before the effective date 

of this AD, inspect the elevator quadrant 

support bracket assembly for cracks by 

following paragraphs III.B.1. through 

III.B.4.(b) of the Accomplishment 

Instructions in DHC–6 SB 6–511, Revision A. 

This AD requires that you do a fluorescent 

penetrant inspection as the type of required 

dye penetrant inspection. If a crack is found 

in the elevator quadrant support bracket, 

before further flight, replace with a 

serviceable part by following paragraphs 

III.B.5 through III.B.12 of the 

Accomplishment Instructions in DHC–6 SB 

6–511, Revision A. 

(h) Credit for Previous Actions 

(1) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes: This 

paragraph provides credit for the inspection 

required by paragraph (g)(1) of this AD if you 

performed the inspection before the effective 

date of this AD using paragraph (a)(1) of AD 

89–24–06 R1. 

(2) For Model DHC–6–1, DHC–6–100, 

DHC–6–200, and DHC–6–300 airplanes: This 

paragraph provides credit for the fluorescent 

penetrant inspection and subsequent 

replacement of the elevator quadrant support 

bracket due to a crack found from the 

fluorescent penetrant inspection required by 

paragraph (g)(2) of this AD if performed 

before the effective date of this AD using 

paragraphs (a)(3) and (4) of AD 89–24–06 R1. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) 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 local Flight Standards 

District Office, as appropriate. If sending 

information directly to the manager of the 

certification office, send it to the attention of 

the person identified in paragraph (j)(1) of 

this AD. 

(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 Darren Gassetto, Aviation Safety 

Engineer, New York ACO Branch, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, NY 

11590; phone: (516) 228–7323; email: 9-avsnyaco-cos@faa.gov. 

(2) Refer to Transport Canada AD CF– 

1972–06R5, dated June 22, 2018, for more 

information. You may examine the Transport 

Canada AD at https://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2022–0099. 

(k) 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) Viking DHC–6 (Twin Otter) Service 

Bulletin 6–511, Revision A, dated June 22, 

1990. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Viking Air Ltd., 1959 de 

Havilland Way, Sidney British Columbia, 

Canada V8L 5V5; phone: (800) 663–8444; 

email: continuing.airworthiness@

vikingair.com; website: https://

www.vikingair.com. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

(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: fr.inspection@nara.gov, or go to: 

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

ibr-locations.html. 

Issued on May 5, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–10758 Filed 5–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0217; Project 

Identifier MCAI–2020–01486–A; Amendment 

39–22041; AD 2022–10–03] 

RIN 2120–AA64 

Airworthiness Directives; Viking Air 

Limited (Type Certificate Previously 

Held by Bombardier, Inc. and de 

Havilland, Inc.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Viking Air Limited (type certificate 

previously held by Bombardier, Inc. and 

de Havilland, Inc.) Model DHC–6–1, 

DHC–6–100, DHC–6–200, DHC–6–300, 

and DHC–6–400 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 identifies the unsafe 

condition as loose quadrants on the 

rudder pedal torque tube and signs of 

loose rivets or rivet joint wear due to 

inadequate manufacturing tolerances. 

This AD requires inspecting the rudder 

pedal torque tube quadrant for looseness 

and taking corrective action as 

necessary. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective June 23, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 23, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Viking Air Ltd., 1959 de Havilland Way, 

Sidney British Columbia, Canada V8L 

5V5; phone: (800) 663–8444; email: 

continuing.airworthiness@

vikingair.com; website: https://

www.vikingair.com. You may view this 

service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information 

on the availability of this material at the 

FAA, call (817) 222–5110. It is also 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0217. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 


jspears on DSK121TN23PROD with RULES1