Proposed Rule2022-12157
Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier Inc. and de Havilland Inc.) Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
June 7, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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 Since the FAA issued AD 2002-14-28, Transport Canada superseded its mandatory continuing airworthiness information (MCAI) to correct this unsafe condition on these products.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.
Full Text
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<title>Federal Register, Volume 87 Issue 109 (Tuesday, June 7, 2022)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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:
<bullet> Federal eRulemaking Portal: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> 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.
<bullet> 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: <a href="/cdn-cgi/l/email-protection#8cf8e9efe4e2e5efede0a2fff9fcfce3fef8ccfae5e7e5e2ebede5fea2efe3e1"><span class="__cf_email__" data-cfemail="621607010a0c0b01030e4c111712120d101622140b090b0c05030b104c010d0f">[email protected]</span></a>; website: <a href="https://www.vikingair.com/support/service-bulletins">https://www.vikingair.com/support/service-bulletins</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#3a5b405340145b52575f5e7a5c5b5b145d554c"><span class="__cf_email__" data-cfemail="c4a5beadbeeaa5aca9a1a084a2a5a5eaa3abb2">[email protected]</span></a>.
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
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, 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:
<bullet> 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.
<bullet> 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.
<bullet> 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.
<bullet> 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.
<bullet> 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.
<bullet> 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.
<bullet> 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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:
<a href="/cdn-cgi/l/email-protection#24455e4d5e0a454c494140644245450a434b52"><span class="__cf_email__" data-cfemail="e283988b98cc838a8f8786a2848383cc858d94">[email protected]</span></a>.
(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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#f28697919a9c9b91939edc818782829d8086b2849b999b9c95939b80dc919d9f"><span class="__cf_email__" data-cfemail="9ce8f9fff4f2f5fffdf0b2efe9ececf3eee8dceaf5f7f5f2fbfdf5eeb2fff3f1">[email protected]</span></a>; website: <a href="https://www.vikingair.com/support/service-bulletins">https://www.vikingair.com/support/service-bulletins</a>. 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
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on June 7, 2022.
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