[Federal Register Volume 87, Number 109 (Tuesday, June 7, 2022)]
[Proposed Rules]
[Pages 34591-34595]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-12157]


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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).

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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superseded its mandatory continuing airworthiness information (MCAI) to 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: [email protected]; 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

[[Page 34592]]

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: [email protected].

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 non-
destructive 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

[[Page 34593]]

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:
    [cir] Inspection of the fillet sealant;
    [cir] Borescope inspection of the interior of the strut; and
    [cir] 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
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per airplane       operators
----------------------------------------------------------------------------------------------------------------
Visual, borescope, and NDT        80 work-hours x     Not applicable....  $6,800 per          $972,400 per
 inspections of the front          $85 per hour =                          inspection cycle.   inspection cycle.
 fuselage struts and airframe      $6,800 per
 lugs.                             inspection cycle.
Detailed visual inspection......  4 work-hours x $85  Not applicable....  $340 per            $48,620 per
                                   per hour = $340                         inspection cycle.   inspection cycle.
                                   per inspection
                                   cycle.
Borescope and detailed visual     6 work-hours x $85  Not applicable....  $510 per            $72,930 per
 inspection.                       per hour = $510                         inspection cycle.   inspection cycle.
                                   per inspection
                                   cycle.
Replace left-hand fuselage strut  54 work-hours x     $2,331.40.........  $6,921.40.........  $989,760.20.
                                   $85 per hour =
                                   $4,590.
Replace right-hand fuselage       54 work-hours x     $2,331.40.........  $6,921.40.........  $989,760.20.
 strut.                            $85 per hour =
                                   $4,590.
----------------------------------------------------------------------------------------------------------------

    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

[[Page 34594]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2002-14-28, Amendment 39-12828 (67 
FR 47684, July 22, 2002); and
0
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 DOA-authorized 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

[[Page 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: 
[email protected].
    (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: [email protected]; 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