[Federal Register Volume 83, Number 186 (Tuesday, September 25, 2018)]
[Rules and Regulations]
[Pages 48363-48366]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20802]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0867; Product Identifier 2017-CE-021-AD; Amendment 
39-19411; AD 2018-19-11]
RIN 2120-AA64


Airworthiness Directives; Viking Air Limited Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III 
airplanes. This AD results from mandatory continuing airworthiness 
information (MCAI) issued by an aviation authority of another country 
to identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as cracking found in the wing rear 
spar web at the wing station where the flap outboard hinge is attached. 
We are issuing this AD to require actions to address the unsafe 
condition on these products.

DATES: This AD is effective October 30, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 30, 
2018.

ADDRESSES: You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0867; or in person at Document

[[Page 48364]]

Management Facility, 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 service information identified in this AD, contact Viking Air 
Limited Technical Support, 1959 De Havilland Way, Sidney, British 
Columbia, Canada, V8L 5V5; telephone: (North America) (800) 663-8444; 
fax: (250) 656-0673; email: [email protected]; internet: 
http://www.vikingair.com/support/service-bulletins. You may view this 
referenced service information at the FAA, Policy and Innovation 
Division, 901 Locust, Kansas City, Missouri 64106. For information on 
the availability of this material at the FAA, call (816) 329-4148. It 
is also available on the internet at http://www.regulations.gov by 
searching for Docket No. FAA-2017-0867.

FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, FAA, 
New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 
11590; telephone: (516) 228-7329; fax: (516) 794-5531; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 by adding an AD that would apply to all Viking Air 
Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes. 
The SNPRM published in the Federal Register on May 7, 2018 (83 FR 
19983). We preceded the SNPRM with a notice of proposed rulemaking 
(NPRM) that published in the Federal Register on September 8, 2017 (82 
FR 42489). The NPRM proposed to require inspecting the wing rear spar 
and flap/aileron support brackets within 400 hours time-in-service 
(TIS) and reporting the results to the manufacturer. The NPRM was based 
on mandatory continuing airworthiness information (MCAI) originated by 
Transport Canada, the aviation authority for Canada. The MCAI states:

    It was reported that a crack was found in the wing rear spar 
web, part number C2W1007, at wing station 123.5 where the flap 
outboard hinge is attached. An aileron hinge bracket has also been 
found cracked. Viking Air Ltd. analysis shows that similar cracks 
may develop on the wing rear spar web and flap/aileron hinge arm 
support brackets at the other flap/aileron hinge attachment 
locations.
    Undetected cracking of the wing rear spar or flap/aileron hinge 
bracket may lead to the failure of the component with consequent 
loss of aeroplane control.

    The MCAI requires inspecting the left-hand and right-hand wing rear 
spar and the flap/aileron hinge air support brackets for cracks, 
damage, or discrepancies and repairing or replacing any parts with 
cracks, damage, or discrepancies. The MCAI can be found in the AD 
docket on the internet at https://www.regulations.gov/document?D=FAA-2017-0867-0002.
    The SNPRM proposed to revise the compliance times to require the 
inspections within 400 hours TIS or 6 months, whichever occurs first, 
to match the compliance times in the MCAI.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     [Agr]re consistent with the intent that was proposed in 
the SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Viking Air Limited has issued Viking DHC-2 Beaver Service Bulletin 
Number: V2/0009, Revision A, dated February 10, 2017. The service 
information describes procedures for inspecting the left-hand and 
right-hand wing rear spars, the flap/aileron hinge brackets, and the 
exterior store support bracket for cracks, damage, and discrepancies. 
The service information also specifies repairing or replacing any parts 
that have cracks, damage, or discrepancies. 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.

Interim Action

    We consider this AD interim action. The inspection report required 
by this AD allows us to obtain better information into the nature, 
cause, and extent of the damage to the wing rear spars and flap/aileron 
hinge arm support brackets and to develop final action to address the 
unsafe condition. After evaluating the inspection results, we may 
consider further rulemaking.

Costs of Compliance

    We estimate that this AD will affect 140 products of U.S. registry. 
We also estimate that it will take about 11 work-hours per product to 
comply with the basic inspection requirements of this AD. The average 
labor rate is $85 per work-hour.
    Based on these figures, we estimate the basic cost of this AD on 
U.S. operators to be $130,900, or $935 per product.
    Reporting the inspection findings would require about 5 minutes, 
for a cost of $7 per airplane and $980 for the U.S. operator fleet.
    In addition, the following is an estimate of possible necessary 
follow-on replacement actions. We have no way of determining the number 
of products that may need these actions.

--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                                          Number of work-
                 Part No.                    Left-hand (LH) or right-              Description              Number per      Parts cost       hours to
                                                  hand (RH) wing                                             airplane                         replace
--------------------------------------------------------------------------------------------------------------------------------------------------------
C2W123A..................................  Both (one per wing)........  Hinge bracket LH inboard (flap)/               2         \2\ 288          \2\ 12
                                                                         RH outboard (aileron).
C2W124A..................................  Both (one per wing)........  Hinge bracket RH inboard (flap)/               2         \2\ 288          \2\ 12
                                                                         LH outboard (aileron).
C2W143...................................  Both (four per wing).......  Hinge bracket, flap and aileron                8         \3\ 271          \3\ 12
                                                                         (common part--multiple wing
                                                                         stations (WS)).
C2W143A (Agricultural Option)............  Both (one per wing)........  Agricultural (optional                     \1\ 2         \2\ 271          \2\ 12
                                                                         configuration)--hinge bracket,
                                                                         support arm (IPC PSM 1-2-4
                                                                         Figure 128, Item 15).
C2W63....................................  LH.........................  Inboard spar, rear spar.........  ..............             277              60

[[Page 48365]]

 
C2W64....................................  RH.........................  Inboard spar, rear spar.........  ..............             277              60
C2W155...................................  Both (one per wing)........  Intermediate spar...............               2         \2\ 563          \2\ 60
C2W65A...................................  LH.........................  Spar WS 89.16 to WS 170.16......             * 1             835              60
C2W66A...................................  RH.........................  Spar WS 89.16 to WS 170.16......             * 1             835              60
C2W67A...................................  LH.........................  Outboard spar, WS 170.16 to WS               * 1             835              60
                                                                         245.75.
C2W68A...................................  RH.........................  Outboard spar, WS 170.16 to WS               * 1             835              60
                                                                         245.75.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* To replace any wing spar section takes 60 work-hours. To replace all four wing spar sections per wing takes 240 work-hours.
\1\ (If applies).
\2\ For both.
\3\ For all eight.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a currently valid OMB Control Number. The OMB 
Control Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to be 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 
76177-1524.

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.
    We are 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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to small airplanes, gliders, 
balloons, airships, domestic business jet transport airplanes, and 
associated appliances to the Director of the Policy and Innovation 
Division.

Regulatory Findings

    We 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0867; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
the NPRM, the SNPRM, the regulatory evaluation, any comments received, 
and other information. The street address for Docket Operations 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of 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 adding the following new airworthiness 
directive (AD):

2018-19-11 Viking Air Limited: Amendment 39-19411; Docket No. FAA-
2017-0867; Product Identifier 2017-CE-021-AD.

(a) Effective Date

    This AD becomes effective October 30, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Viking Air Limited Models DHC-2 Mk. I, DHC-2 
Mk. II, and DHC-2 Mk. III airplanes, all serial numbers, 
certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 57: Wings.

(e) Reason

    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

[[Page 48366]]

describes the unsafe condition as cracking found in the wing rear 
spar web at the wing station (WS) where the flap outboard hinge is 
attached. We are issuing this AD to detect and correct cracks in the 
wing rear spars and the flap/aileron hinge arm support brackets. 
This condition, if not corrected, could result in structural failure 
with consequent loss of control of the airplane.

(f) Actions and Compliance

    Unless already done, do the actions in paragraphs (f)(1) through 
(5) of this AD:

    (1) Within 400 hours time-in-service (TIS) after October 30, 
2018 (the effective date of this AD) or within 6 months after 
October 30, 2018 (the effective date of this AD), whichever occurs 
first, visually inspect the left-hand and right-hand wing rear spar 
and flap/aileron hinge arm support brackets by following the 
Accomplishment Instructions of Viking DHC-2 Beaver Service Bulletin 
Number: V2/0009, Revision A, dated February 10, 2017 (SB V2/0009, 
Revision A).
    (2) For airplanes with an agricultural configuration installed 
(SOO Mod 2/984), within 400 hours TIS after October 30, 2018 (the 
effective date of this AD) or within 6 months after October 30, 2018 
(the effective date of this AD), whichever occurs first, inspect the 
exterior store support arm bracket at WS 101.24 by following the 
Accomplishment Instructions of SB V2/0009, Revision A.
    (3) If any discrepancies are found during the inspections 
required in paragraphs (f)(1) and (2) of this AD, before further 
flight, repair or replace 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.
    (4) Within 30 days after completing the inspections required in 
paragraphs (f)(1) and (2) of this AD, using the Operator Reply Form 
on page 7 of SB V2/0009, Revision A, report the inspection results 
to Viking Air Limited at the address specified in paragraph (i)(3) 
of this AD.
    (5) As of October 30, 2018 (the effective date of this AD), do 
not install a wing on any airplane affected by this AD unless it has 
been inspected as specified in paragraphs (f)(1) of this AD and 
paragraph (f)(2) of this AD, if applicable, and is found free of any 
discrepancies.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): 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. Send 
information to ATTN: Aziz Ahmed, Aerospace Engineer, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, New York 
11590; telephone: (516) 228-7329; fax: (516) 794-5531; email: 
[email protected]. Before using any approved AMOC on any airplane 
to which the AMOC applies, notify your appropriate principal 
inspector (PI) in the FAA Flight Standards District Office (FSDO), 
or lacking a PI, your local FSDO.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York ACO 
Branch, FAA; or Transport Canada; or Viking Air Limited's Transport 
Canada DOA. If approved by the DOA, the approval must include the 
DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a currently valid OMB Control Number. The OMB Control 
Number for this information collection is 2120-0056. Public 
reporting for this collection of information is estimated to be 
approximately 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, completing and reviewing the collection 
of information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, 
TX 76177-1524.

(h) Related Information

    Refer to MCAI Transport Canada AD Number CF-2017-17, dated May 
18, 2017, for related information. You may examine the MCAI on the 
internet at https://www.regulations.gov/document?D=FAA-2017-0867-0002.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Viking DHC-2 Beaver Service Bulletin Number: V2/0009, 
Revision A, dated February 10, 2017.
    (ii) Reserved.
    (3) For Viking DHC-2 Beaver service information identified in 
this AD, contact Viking Air Limited Technical Support, 1959 De 
Havilland Way, Sidney, British Columbia, Canada, V8L 5V5; telephone: 
(North America) (800) 663-8444; fax: (250) 656-0673; email: 
[email protected]; internet: http://www.vikingair.com/
support/service-Bulletins.
    (4) You may view this service information at the FAA, Policy and 
Innovation Division, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
(816) 329-4148. In addition, you can access this service information 
on the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2017-0867.
    (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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on September 7, 2018
Melvin J. Johnson,
Aircraft Certification Service, Deputy Director, Policy and Innovation 
Division, AIR-601.
[FR Doc. 2018-20802 Filed 9-24-18; 8:45 am]
 BILLING CODE 4910-13-P


