[Federal Register Volume 87, Number 165 (Friday, August 26, 2022)]
[Rules and Regulations]
[Pages 52434-52437]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-18383]
[[Page 52434]]
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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;
Amendment 39-22143; AD 2022-17-05]
RIN 2120-AA64
Airworthiness Directives; Viking Air Limited (Type Certificate
Previously Held by Bombardier Inc. and de Havilland Inc.) Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2002-14-
28, which applied 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 established a life limit for the front
fuselage struts and required repetitively replacing the front fuselage
struts every 15 years or repetitively inspecting the struts for
corrosion or fatigue damage and replacing when the damage exceeded 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superseded its mandatory continuing airworthiness information (MCAI) to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 AD requires
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 issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective September 30, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of September
30, 2022.
ADDRESSES: For service information identified in this final rule,
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:
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. It
is also available at www.regulations.gov under Docket No. FAA-2022-
0602.
Examining the AD Docket
You may examine the AD docket at www.regulations.gov under 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 final rule, the MCAI, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2002-14-28, Amendment 39-12828 (67 FR
47684, July 22, 2002) (AD 2002-14-28). AD 2002-14-28 applied 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 established a life limit for the front fuselage struts and
required repetitively replacing the front fuselage struts every 15
years or repetitively inspecting the struts for corrosion or fatigue
damage and replacing when the damage exceeded 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.
The NPRM published in the Federal Register on June 7, 2022 (87 FR
34591). The NPRM was prompted by AD CF-2020-22, dated June 5, 2020
(referred to after this as ``the MCAI''), issued by Transport Canada,
which is the aviation authority for Canada, which superseded its prior
AD on this unsafe condition, AD CF-98-37R1, dated August 20, 1999.
Transport Canada issued 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.
[[Page 52435]]
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
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 with the requirements of this [Transport
Canada] AD.
You may examine the MCAI in the AD docket at www.regulations.gov
under Docket No. FAA-2022-0602.
In the NPRM, the FAA proposed to require either doing recurring
visual inspections, borescope inspections, and 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 issuing this AD to
address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the NPRM or on the determination of
the costs.
Conclusion
These products have been approved by the aviation authority of
another country and are approved for operation in the United States.
Pursuant to the FAA's bilateral agreement with this State of Design
Authority, it has notified the FAA of the unsafe condition described in
the MCAI referenced above. The FAA reviewed the relevant data and
determined that air safety requires adopting this AD as proposed.
Accordingly, the FAA is issuing this AD to address the unsafe condition
on these products. This AD is adopted as proposed in the NPRM.
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 (NDT) 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, 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.
Costs of Compliance
The FAA estimates that this AD affects 143 airplanes of U.S.
registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost per Cost on U.S.
Action Labor cost Parts cost airplane operators
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Visual, borescope, and NDT 80 work-hours x $85 Not applicable.......... $6,800 per $972,400 per
inspections of the front per hour = $6,800 inspection inspection
fuselage struts and airframe per inspection cycle. cycle. cycle.
lugs.
Detailed visual inspection... 4 work-hours x $85 Not applicable.......... $340 per $48,620 per
per hour = $340 per inspection inspection
inspection cycle. cycle. cycle.
Borescope and detailed visual 6 work-hours x $85 Not applicable.......... $510 per $72,930 per
inspection. per hour = $510 per inspection inspection
inspection cycle. cycle. cycle.
Replace left-hand fuselage 54 work-hours x $85 $2,331.40............... $6,921.40...... $989,760.20.
strut. per hour = $4,590.
Replace right-hand fuselage 54 work-hours x $85 $2,331.40............... $6,921.40...... $989,760.20.
strut. per hour = $4,590.
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The extent of damage found during the required 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.
[[Page 52436]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA has determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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:
2022-17-05 Viking Air Limited (type certificate previously held by
Bombardier Inc. and de Havilland Inc.): Amendment 39-22143; Docket
No. FAA-2022-0602; Project Identifier MCAI-2020-01211-A.
(a) Effective Date
This airworthiness directive (AD) is effective September 30,
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
[[Page 52437]]
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 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 www.regulations.gov by searching for and locating
Docket No. FAA-2022-0602.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Viking DHC-2 Beaver Technical Bulletin No. V2/00002,
Revision `A,' dated June 20, 2019.
(ii) [Reserved]
(3) For Viking Air Ltd 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: www.vikingair.com/support/service-bulletins.
(4) You may view this service information at FAA, Airworthiness
Products Section, Operational Safety Branch, 901 Locust, Kansas
City, MO 64106. For information on the availability of this material
at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on August 4, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-18383 Filed 8-25-22; 8:45 am]
BILLING CODE 4910-13-P