Federal Register / Vol. 87, No. 109 / Tuesday, June 7, 2022 / Proposed Rules 34591 

boom fittings, for at least 12 inches from the 

end of the fittings. It is only necessary to 

remove the topcoat. Primer may be left in 

place and edge and fillet sealant may be left 

in place. If any primer or edge or fillet sealant 

is removed, before further flight, reapply the 

removed primer and sealant. 

Note 1 to paragraph (g)(2)(ii): On some 

models, the baggage compartment floor and 

net must be removed to gain access to the 

lower fuselage attach fittings and cap angles. 

(iii) With an additional person pushing on 

the tail boom at the third vertical rivet line 

aft of the trailing edge of the elevator with 

both hands and gradually applying and 

relieving pressure using body weight a 

minimum of three times in each of the 

following directions: Inboard pushing from 

the left; inboard pushing from the right; and 

upward pushing from the bottom; and using 

a bright light and borescope, inspect each of 

the four tail boom attach structures for 

cracks, bond separation, and loose rivets. On 

the fuselage side, inspect the fittings and the 

cap angles running forward from the fittings, 

paying particular attention to the fitting 

sections near the rivets closest to the attach 

bolts and the cap angle rivets next to the 

fittings. On the tail boom side, inspect the 

fittings and the longerons running aft from 

the fittings, paying particular attention to the 

fitting sections near the rivets closest to the 

attach bolts. Without pushing on the tail 

boom, and using a bright light and borescope, 

inspect each of the four tail boom attach 

structures for scratches, nicks, gouges, tears, 

corrosion, buckling, and distortion, and for 

loose, missing, and smoking rivets. If there 

are any scratches, nicks, gouges, tears, or 

corrosion within allowable limits, before 

further flight, repair the affected components. 

If there are any scratches, nicks, gouges, 

tears, or corrosion that exceed allowable 

limits, or any cracks, buckling, or distortion, 

or loose, missing, or smoking rivets, before 

further flight, remove the affected 

components from service. If there is any bond 

separation, before further flight, re-bond the 

affected components. 

Note 2 to paragraph (g)(2)(iii): It is not 

required to push on the tail boom if it cannot 

be reached from ground level while 

inspecting for cracks, bond separation, and 

loose rivets. 

(iv) Inspect the tail boom attach bolts for 

exposed threads. If there is less than one full 

thread or more than three threads exposed, 

before further flight, remove the bolt and selflocking nut from service and replace with a 

new bolt and new self-locking nut. 

(v) Inspect each of the four tail boom attach 

bolts for movement by either applying the 

required installation torque in the tightening 

direction only, or by inspecting for torque 

stripe misalignment if present and attempting 

to rotate the bolt by hand. If a bolt is undertorqued, a torque stripe is misaligned, or a 

bolt moves, before further flight, remove the 

bolt and self-locking nut from service and 

replace with a new bolt and new self-locking 

nut. 

(vi) After the first flight following any bolt 

replacement as required by paragraph 

(g)(2)(iv) or (v) of this AD, retorque any 

replaced bolt by applying torque in 

accordance with the existing maintenance 

instructions for your helicopter in the 

tightening direction only and then apply a 

torque stripe on the bolt head. 

(3) Within 25 hours TIS after the effective 

date of this AD, and thereafter at intervals not 

to exceed 25 hours TIS, perform the actions 

required by paragraphs (g)(2)(ii) through (vi) 

of this AD at the upper left-hand tail boom 

attach points. 

(4) Within 25 hours TIS after the effective 

date of this AD, and thereafter at intervals not 

to exceed 100 hours TIS, perform the actions 

required by paragraphs (g)(2)(ii) through (vi) 

of this AD at all four tail boom attach points. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, DSCO Branch, 

Compliance & Airworthiness Division, 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 (i) of this AD. You 

may email your request to: 9-ASW-190-COS@

faa.gov@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. 

(i) Related Information 

For more information about this AD, 

contact Ameet Shrotriya, Aviation Safety 

Engineer, DSCO Branch, Compliance & 

Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177– 

1524; phone: (817) 222–5525; email: 

Ameet.Shrotriya@faa.gov. 

Issued on May 31, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–12100 Filed 6–6–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0602; Project 

Identifier MCAI–2020–01211–A] 

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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2002–14–28, which applies to all de 

Havilland Inc. (type certificate currently 

held by Viking Air Limited) Model 

DHC–2 Mk. I, DHC–2 Mk. II, and DHC– 

2 Mk. III airplanes. AD 2002–14–28 

establishes a life limit for the front 

fuselage struts and requires repetitively 

replacing the front fuselage struts every 

15 years or repetitively inspecting the 

struts for corrosion or fatigue damage 

and replacing when the damage exceeds 

a certain level. Since the FAA issued 

AD 2002–14–28, Transport Canada 

superseded its mandatory continuing 

airworthiness information (MCAI) to 

correct this unsafe condition on these 

products. This proposed AD would 

require either doing recurring visual 

inspections, borescope inspections, and 

non-destructive inspections (NDIs) of 

the struts and airframe lugs with 

corrective action as necessary or 

replacing the struts every 15 years and 

doing recurring NDIs of the airframe 

lugs with corrective action as necessary. 

The FAA is proposing this AD to 

address the unsafe condition on these 

products. 

DATES: The FAA must receive comments 

on this proposed AD by July 22, 2022. 

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 NPRM, contact Viking Air Limited 

Technical Support, 1959 de Havilland 

Way, Sidney, British Columbia, Canada, 

V8L 5V5; phone: (800) 663–8444; fax: 

(250) 656–0673; email: 

technical.support@vikingair.com; 

website: https://www.vikingair.com/ 

support/service-bulletins. 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 


jspears on DSK121TN23PROD with PROPOSALS1
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searching for and locating Docket No. 

FAA–2022–0602; 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 

NPRM, the MCAI, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aviation Safety Engineer, New 

York ACO Branch, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; phone: (516) 228–7329; email: 

aziz.ahmed@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2022–0602; Project Identifier 

MCAI–2020–01211–A’’ at the beginning 

of your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend the proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this proposed 

AD. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Aziz Ahmed, Aviation 

Safety Engineer, New York ACO Branch, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590. Any commentary 

that the FAA receives which is not 

specifically designated as CBI will be 

placed in the public docket for this 

rulemaking. 

Background 

The FAA issued AD 2002–14–28, 

Amendment 39–12828 (67 FR 47684, 

July 22, 2002) (AD 2002–14–28), for all 

de Havilland Inc. (type certificate 

currently held by Viking Air Limited) 

Model DHC–2 Mk. I, DHC–2 Mk. II, and 

DHC–2 Mk. III airplanes. AD 2002–14– 

28 establishes a life limit for the front 

fuselage struts and requires repetitively 

replacing the front fuselage struts every 

15 years or repetitively inspecting the 

struts for corrosion or fatigue damage 

and replacing when the damage exceeds 

a certain level. The FAA issued AD 

2002–14–28 to prevent structural failure 

of the front fuselage caused by corrosion 

or fatigue damage to the struts that 

develops over time, which could result 

in reduced or loss of airplane control. 

Actions Since AD 2002–14–28 Was 

Issued 

Since the FAA issued AD 2002–14– 

28, the type certificate holder for Model 

DHC–2 Mk. I, DHC–2 Mk. II, and DHC– 

2 Mk. III airplanes changed from de 

Havilland Inc. to Viking Air Limited. 

Transport Canada, which is the 

aviation authority for Canada, 

superseded its prior AD on this unsafe 

condition, AD CF–98–37R1, dated 

August 20, 1999, and issued AD CF– 

2020–22, dated June 5, 2020 (referred to 

after this as ‘‘the MCAI’’), to introduce 

a revised inspection schedule for the 

front fuselage struts from previously 

published schedules to alleviate the 

burden of mandatory replacement every 

15 years or ultrasonic inspections every 

5 years. The MCAI states: 

Operators have reported incidents of 

corrosion of the DHC–2 front fuselage struts 

which are installed on each side of the flight 

compartment windshield. Deterioration of 

the airframe lugs to which the struts are 

attached has also been reported. The actions 

specified by this [Transport Canada] AD are 

intended to prevent structural failure of the 

front fuselage caused by damage to the 

fuselage struts and airframe lugs that 

develops over time, which could result in the 

loss of airframe structural integrity. 

AD CF–98–37 issued 29 September 1998 

mandated a 15-year life limit on the strut. It 

also prohibited installation of part numbers 

(P/Ns) C2FS209 and C2FS210. 

Revision 1, CF–98–37R1, introduced 

repetitive inspection as an alternative to 

replacement of the strut. Detailed visual 

inspection was required to begin within 12 

months from the effective date of the 

[Transport Canada] AD and be repeated every 

12 months regardless of the age of the strut. 

Ultrasonic thickness measurements were 

required to begin within 24 months from the 

effective date of the [Transport Canada] AD 

and be repeated every 5 years regardless of 

the age of the strut. 

After AD CF–98–37R1 was issued, it was 

determined that the repetitive inspections are 

not required to be started until the strut has 

accumulated 15 years since installation. As a 

result, Transport Canada (TC) approved 

several AMOCs [alternative methods of 

compliance] to authorize starting the 

inspections at that time. 

Since the issuance of AD CF–98–37R1, TC 

has received several Service Difficulty 

Reports (SDRs) indicating that the corrective 

actions of that [Transport Canada] AD have 

not been effective at controlling damage of 

the fuselage struts to an acceptable level. 

Viking Air Ltd. (Viking) has determined 

that a modified program of recurring visual 

inspection, borescope inspection and nondestructive inspection (NDI) of the struts and 

airframe lugs would be more effective than 

the existing inspection program. This 

program modifies affected parts by 

introducing a hole to permit a borescope 

inspection if that hole does not already exist 

in the parts. 

To implement the modified inspection 

program, Viking has published Service 

Bulletin (SB) V2/0010 and Technical Bulletin 

(TB) V2/00002 that provide specific 

instructions for performing the modification, 

inspections and measurements required by 

this [Transport Canada] AD. The SB and TB 

also define the follow-on actions associated 

with those inspections and measurements. 

Viking has also developed a version of the 

front fuselage strut with improved resistance 

to corrosion and with provisions for 

borescope inspection. The improved struts 

have been assigned P/Ns C2FS3281A–9 (left 

strut) and C2FS3282A–9 (right strut). 

The corrective actions of this [Transport 

Canada] AD differ from those of AD CF–98– 

37R1 in the following ways: 

• AD CF–98–37R1 included the details for 

all of the corrective actions, it did not require 

reference to other documents. For this 

[Transport Canada] AD, the details of the 

corrective actions are now specified in a SB 

and a TB. 

• AD CF–98–37R1 required repetitive 

detailed visual inspection (DVI) of the 

airframe lugs. This [Transport Canada] AD 

requires repetitive DVI and NDI of the 

airframe lugs. 

• AD CF–98–37R1 only permitted 

installation of P/Ns C2FS3281A and 

C2FS3282A. This [Transport Canada] AD 

permits installation of those parts, the 

superseding Viking P/Ns, parts installed by 

TC-issued or -accepted Supplemental Type 

Certificate (STC) or Part Manufacturing 

Approval (PMA) and Part Design Approval 

(PDA) parts that are approved for installation 

in DHC–2 as replacements for P/Ns 

C2FS3281A and C2FS3282A. Those are all 

approved parts. 

• AD CF–98–37R1 did not specify to 

remove parts from the aeroplane to perform 

inspections. This [Transport Canada] AD 

requires repetitive removal of the struts from 

the aeroplane followed by a NDI of the 

airframe lugs. This requirement applies to 


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DHC–2 where the struts are being replaced 

when they reach 15 years since installation. 

It also applies to DHC–2 where the struts are 

kept in service and inspected as required by 

the SB and TB. 

• AD CF–98–37R1 required the visual 

inspection to start within 12 months from the 

[Transport Canada] AD effective date and the 

NDI to start within 24 months from the 

[Transport Canada] AD effective date. This 

[Transport Canada] AD requires the repetitive 

inspections to start no later than when the 

struts have accumulated 15 years since initial 

installation. 

• AD CF–98–37R1 required repetitive 

ultrasonic thickness measurement for all 

parts. This [Transport Canada] AD only 

requires that measurement if corrosion is 

detected during an inspection. 

• AD CF–98–37R1 required visual 

inspection of the exterior surfaces of the strut 

with the strut installed in the aeroplane. For 

struts that have accumulated more than 15 

years since first installation, this [Transport 

Canada] AD continues to require visual 

inspection of the accessible exterior surfaces 

of the strut with the strut installed. This 

[Transport Canada] AD also includes 

repetitive requirements for: 

Æ Inspection of the fillet sealant; 

Æ Borescope inspection of the interior of 

the strut; and 

Æ Removal of the strut from the aeroplane 

followed by visual inspection of the entire 

strut and NDI of the strut end fittings. 

All TC-issued or -accepted AMOCs with 

AD CF–98–37R1 are cancelled on the 

effective date of this [Transport Canada] AD. 

Parts in service must be replaced or 

modified, inspected and maintained in 

accordance with the requirements of this 

[Transport Canada] AD unless TC approves 

AMOCs [alternative methods of compliance] 

with the requirements of this [Transport 

Canada] AD. 

You may examine the MCAI in the 

AD docket at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0602. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Viking DHC–2 

Beaver Technical Bulletin No. V2/ 

00002, Revision ‘A,’ dated June 20, 

2019. The service information specifies 

procedures for a detailed visual, 

borescope, and non-destructive testing 

inspection of the front fuselage struts 

and airframe lugs. 

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. 

Other Related Service Information 

The FAA reviewed Viking DHC–2 

Beaver Service Bulletin No. V2/0010, 

Revision ‘NC,’ dated April 3, 2020. The 

service information contains a detailed 

and revised schedule for a detailed 

visual inspection of the forward-lower 

and aft-upper strut attachment points on 

the fuselage (mating airframe lugs) every 

12 months, borescope inspection of the 

strut interior surfaces every 5 years, 

non-destructive testing (NDT) 

inspection of the fuselage strut fork ends 

and lugs every 15 years, replacement of 

each fuselage strut every 15 years, and 

replacement of the 5-year ultrasonic 

thickness measurement as an option to 

the 15-year life limit. 

FAA’s Determination 

This product has been approved by 

the aviation authority of another 

country, and is 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 and service 

information referenced above. The FAA 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

on other products of the same type 

design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. This proposed AD does not 

retain any of the requirements from AD 

2002–14–28. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 143 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per airplane Cost on U.S. 

operators 

Visual, borescope, and NDT inspections of 

the front fuselage struts and airframe 

lugs.

80 work-hours × $85 per 

hour = $6,800 per inspection cycle.

Not applicable ..................... $6,800 per inspection cycle $972,400 per inspection 

cycle. 

Detailed visual inspection .......................... 4 work-hours × $85 per 

hour = $340 per inspection cycle.

Not applicable ..................... $340 per inspection cycle ... $48,620 per inspection 

cycle. 

Borescope and detailed visual inspection 6 work-hours × $85 per 

hour = $510 per inspection cycle.

Not applicable ..................... $510 per inspection cycle ... $72,930 per inspection 

cycle. 

Replace left-hand fuselage strut ................ 54 work-hours × $85 per 

hour = $4,590.

$2,331.40 ............................ $6,921.40 ............................ $989,760.20. 

Replace right-hand fuselage strut .............. 54 work-hours × $85 per 

hour = $4,590.

$2,331.40 ............................ $6,921.40 ............................ $989,760.20. 

The extent of damage found during 

the proposed inspections could vary 

significantly from airplane to airplane. 

The FAA has no way of determining 

how much damage may be found on 

each airplane, the cost to repair 

damaged parts on each airplane, or the 

number of airplanes that may require 

repair. 

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, and 

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 

proposed AD would not have federalism 

implications under Executive Order 


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34594 Federal Register / Vol. 87, No. 109 / Tuesday, June 7, 2022 / Proposed Rules 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

2002–14–28, Amendment 39–12828 (67 

FR 47684, July 22, 2002); and 

■ b. Adding the following new 

airworthiness directive: 

Viking Air Limited (type certificate 

previously held by Bombardier Inc. and 

de Havilland Inc.): Docket No. FAA– 

2022–0602; Project Identifier MCAI– 

2020–01211–A. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by July 22, 2022. 

(b) Affected ADs 

This AD replaces AD 2002–14–28, 

Amendment 39–12828 (67 FR 47684, July 22, 

2002) (AD–2002–14–28). 

(c) Applicability 

This AD applies to Viking Air Limited 

(type certificate previously held by 

Bombardier Inc. and de Havilland Inc.) 

Model DHC–2 Mk. I, DHC–2 Mk. II, and 

DHC–2 Mk. III airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5300, Fuselage Structure (General). 

(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 

identifies the unsafe condition as the 

development of damage to the front fuselage 

struts and airframe lugs over time. The FAA 

is issuing this AD to address this condition. 

The unsafe condition, if not addressed, could 

result in failure of the front fuselage struts, 

which could lead to failure of the airframe 

and loss of airplane control. 

(f) Definition of Serviceable Part 

For purposes of this AD, a ‘‘serviceable 

part’’ is a front fuselage strut that has a part 

number (P/N) other than P/N C2FS209 and 

C2FS210 and meets the conditions in either 

paragraph (f)(1) or (2) of this AD: 

(1) Has accumulated less than 15 years 

since first installation on an airplane; or 

(2) Has accumulated 15 or more years since 

first installation on an airplane and has been 

inspected in accordance with the 

requirements of this AD. 

(g) Compliance 

Comply with the initial actions in 

paragraph (h) of this AD at the applicable 

compliance time in paragraph (g)(1), (2), or 

(3) of this AD, unless already done. 

(1) For airplanes with a front fuselage strut 

that has been installed for less than 15 years 

as of the effective date of this AD: Before 

each front fuselage strut accumulates 15 

years since first installation on an airplane. 

(2) For airplanes with a front fuselage strut 

that has been installed for more than 15 years 

as of the effective date of this AD or with a 

front fuselage strut where the date of first 

installation on an airplane is unknown and 

the ultrasonic inspection required by 

paragraph (d)(2) of AD 2002–14–28 has not 

been done within the last 5 years: Before 

further flight. 

(3) For airplanes with a front fuselage strut 

that has been installed for more than 15 years 

as of the effective date of this AD or with a 

front fuselage strut where the date of first 

installation on an airplane is unknown and 

the ultrasonic inspection required by 

paragraph (d)(2) of AD 2002–14–28 has been 

done within the last 5 years: Within 5 years 

from the date of the last ultrasonic inspection 

done in accordance with paragraph (d)(2) of 

AD 2002–14–28. 

(h) Initial Actions 

(1) Do the actions in paragraph (h)(1)(i) or 

(ii) of this AD. 

(i) Remove the front fuselage struts from 

service and install and seal serviceable parts 

in accordance with steps w. and y. through 

ii. of Section II.B.1. or II.B.2., as applicable 

to your airplane, of Viking DHC–2 Beaver 

Technical Bulletin No. V2/00002, Revision 

A, dated June 20, 2019 (Viking TB V2/00002); 

or 

(ii) Do visual and borescope inspections of 

the front fuselage struts and non-destructive 

testing (NDT) inspections of the fuselage strut 

fork ends for corrosion and cracks in 

accordance with steps m. through p. of 

Section II.B.1. or II.B.2., as applicable to your 

airplane, of Viking TB V2/00002, except you 

are not required to contact the manufacturer. 

Instead, do the actions in paragraph (h)(3) of 

this AD. 

(2) Do visual and NDT inspections of the 

mating airframe lug surfaces and bolt holes 

for corrosion and cracks and replace if 

necessary in accordance with steps q., r., t., 

and u. of Section II.B.1. or II.B.2., as 

applicable to your airplane, of Viking TB V2/ 

00002, except you are not required to contact 

the manufacturer. 

(3) If, during any inspection required by 

paragraph (h)(1)(ii) of this AD, any crack or 

corrosion is found, before further flight, do 

one of the following: 

(i) Remove the part from service and install 

and seal a serviceable part in accordance 

with steps w. and y. through ii. of Section 

II.B.1. or II.B.2., as applicable to your 

airplane, of Viking TB V2/00002; or 

(ii) If the wall thickness of the part is 0.030 

inch or more, repair in accordance with step 

s(2) of Section II.B.1. or II.B.2., as applicable 

to your airplane, of Viking TB V2/00002; or 

(iii) Repair using a method approved by the 

Manager, New York ACO Branch, FAA; 

Transport Canada; or Viking Air Limited’s 

Transport Canada Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(i) Repetitive Actions 

(1) After completing the actions in 

paragraphs (h)(1)(ii) and (2) of this AD, 

unless already done, do the following: 

(i) At intervals not to exceed 12 months, 

except when complying with paragraph 

(i)(1)(ii) or (2) of this AD, clean and visually 

inspect the front fuselage struts and airframe 

lugs for corrosion and cracking in accordance 

with steps n., p., and q. of Section II.B.1. or 

II.B.2., as applicable to your airplane, of 

Viking TB V2/00002. If there is a crack or any 

corrosion, before further flight, comply with 

the actions in paragraph (h)(3)(i), (ii), or (iii) 

of this AD. 

(ii) At intervals not to exceed 5 years, 

except when complying with paragraph (i)(2) 

of this AD, do visual and borescope 

inspections of the front fuselage struts and a 

visual inspection of the airframe lugs for 

corrosion and cracking in accordance with 

steps m. through q. and t. of Section II.B.1. 

or II.B.2., as applicable to your airplane, of 

Viking TB V2/00002, except you are not 

required to contact the manufacturer. If there 

is a crack or any corrosion, before further 

flight, comply with the actions in paragraph 

(h)(3)(i), (ii), or (iii) of this AD. 

(2) At intervals not to exceed 15 years, 

repeat the actions required by paragraph (h) 

of this AD. 

(j) 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 


jspears on DSK121TN23PROD with PROPOSALS1
Federal Register / Vol. 87, No. 109 / Tuesday, June 7, 2022 / Proposed Rules 34595 

the person identified in paragraph (k)(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Aziz Ahmed, Aviation Safety 

Engineer, New York ACO Branch, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, NY 

11590; phone: (516) 228–7329; email: 

aziz.ahmed@faa.gov. 

(2) Refer to Transport Canada AD CF– 

2020–22, dated June 5, 2020, for more 

information. You may examine the Transport 

Canada AD in the AD docket at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2022–0602. 

(3) For service information identified in 

this AD, contact Viking Air Limited 

Technical Support, 1959 de Havilland Way, 

Sidney, British Columbia, Canada, V8L 5V5; 

phone: (800) 663–8444; fax: (250) 656–0673; 

email: technical.support@vikingair.com; 

website: https://www.vikingair.com/support/ 

service-bulletins. You may view this 

referenced 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. 

Issued on June 1, 2022. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–12157 Filed 6–6–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2021–0244; Airspace 

Docket No. 20–AWP–9] 

RIN 2120–AA66 

Proposed Modification of Class D and 

Class E Airspace and Establishment of 

Class E Airspace; Camarillo, CA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

modify the Class E airspace, designated 

as an extension to a Class D or Class E 

surface area, at Camarillo Airport, 

Camarillo, CA. This action also 

proposes to remove the Camarillo VOR/ 

DME from the airspace’s legal 

description. Additionally, this action 

proposes to establish Class E airspace 

extending upward from 700 feet above 

the surface. Lastly, this action proposes 

administrative updates to the Class D 

and Class E legal descriptions. This 

action would ensure the safety and 

management of instrument flight rules 

(IFR) operations at the airport. 

DATES: Comments must be received on 

or before July 22, 2022. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue SE, West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590; telephone: 1– 

800–647–5527, or (202) 366–9826. You 

must identify FAA Docket No. FAA– 

2021–0244; Airspace Docket No. 20– 

AWP–9, at the beginning of your 

comments. You may also submit 

comments through the internet at 

https://www.regulations.gov. 

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. 

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: 

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 

modify the Class D and Class E airspace, 

and establish new Class E airspace at 

Camarillo Airport, Camarillo, CA, to 

support IFR operations at the airport. 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers and be submitted in 

triplicate to the address listed above. 

Persons wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket No. FAA–2021–0244; Airspace 

Docket No. 20–AWP–9’’. The postcard 

will be date/time stamped and returned 

to the commenter. 

All communications received before 

the specified closing date for comments 

will be considered before taking action 

on the proposed rule. The proposal 

contained in this notice may be changed 

in light of the comments received. A 

report summarizing each substantive 

public contact with FAA personnel 

concerned with this rulemaking will be 

filed in the docket. 

Availability of NPRMs 

An electronic copy of this document 

may be downloaded through the 

internet at https://www.regulations.gov. 

Recently published rulemaking 

documents can also be accessed through 

the FAA’s web page at https://

www.faa.gov/air_traffic/publications/ 

airspace_amendments. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office (see the 

ADDRESSES section for the address and 

phone number) between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except federal holidays. An informal 

docket may also be examined during 

normal business hours at the Northwest 

Mountain Regional Office of the Federal 

Aviation Administration, Air Traffic 

Organization, Western Service Center, 

Operations Support Group, 2200 S 

216th Street, Des Moines, WA 98198. 

Availability and Summary of 

Documents for Incorporation by 

Reference 

This document proposes to amend 

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, 


jspears on DSK121TN23PROD with PROPOSALS1