[Federal Register Volume 85, Number 3 (Monday, January 6, 2020)]
[Rules and Regulations]
[Pages 443-449]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-28470]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0710; Product Identifier 2019-NM-060-AD; Amendment 
39-21009; AD 2019-25-11]
RIN 2120-AA64


Airworthiness Directives; Viking Air Limited (Type Certificate 
Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Viking Air Limited Model CL-215-1A10 and CL-215-6B11 (CL-215T 
Variant) airplanes. This AD was prompted by reports of cracks on the 
wing lower skin under the drag angle at a certain wing station (WS). 
This AD requires a one-time inspection of the wing lower skin under the 
drag angle at a certain WS to determine if a certain repair or 
modification has been accomplished; repetitive visual inspections of 
certain fuselage structures; repetitive eddy current inspections of the 
front spar along a certain WS reference line, the drag angle, and all 
fastener holes; repetitive structural gap checks of a certain surface; 
and corrective actions if necessary. This AD also requires replacing 
certain rivets with certain fasteners, and corrective actions if 
necessary. The FAA is issuing this AD to address the unsafe condition 
on these products.

DATES: This AD is effective February 10, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 10, 
2020.

ADDRESSES: For service information identified in this final rule, 
contact Viking Air Limited, 1959 de Havilland Way, Sidney, British 
Columbia V8L 5V5, Canada; telephone +1-250-656-7227; fax +1-250-656-
0673; email [email protected]; internet https://www.vikingair.com. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 206-
231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0710.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0710; 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 regulatory evaluation, 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.

[[Page 444]]


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

SUPPLEMENTARY INFORMATION:

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2019-07, dated March 4, 
2019 (referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for 
certain Viking Air Limited Model CL-215-1A10 and CL-215-6B11 (CL-215T 
Variant) airplanes. You may examine the MCAI in the AD docket on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0710.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain Viking Air 
Limited Model CL-215-1A10 and CL-215-6B11 (CL-215T Variant) airplanes. 
The NPRM published in the Federal Register on October 4, 2019 (84 FR 
53076). The NPRM was prompted by reports of cracks on the wing lower 
skin under the drag angle at a certain WS. The NPRM proposed to require 
a one-time inspection of the wing lower skin under the drag angle at a 
certain WS to determine if a certain repair or modification has been 
accomplished; repetitive visual inspections of certain fuselage 
structures; repetitive eddy current inspections of the front spar along 
a certain WS reference line, the drag angle, and all fastener holes; 
repetitive structural gap checks of a certain surface; and corrective 
actions if necessary. The NPRM also proposed to require replacing 
certain rivets with certain fasteners, and corrective actions if 
necessary. The FAA is issuing this AD to address this condition, which 
if not detected and corrected, may lead to widespread fatigue damage 
and wing structure failure. See the MCAI for additional background 
information.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed, 
except for minor editorial changes. The FAA has determined that these 
minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Viking has issued Alert Service Bulletin 215-A568, Revision 4, 
dated January 22, 2019. This service information describes procedures 
for a one-time inspection of the wing lower skin under the drag angle 
at a certain WS to determine if a certain repair or modification has 
been accomplished; repetitive visual inspections of fastener 
installation for abnormal conditions (missed, sheared, distorted, 
deformed or loose fastener heads/collar/nuts, and corrosion) and 
corrective actions as necessary; repetitive visual inspections of the 
open fastener holes for cracks, burrs, elongation, double or mis-
drilled holes, or corrosion, and corrective actions as necessary; 
repetitive visual inspections of drag angles, wing lower skin, lower 
stringers, spar lower caps/webs, and fuselage structures (internally 
and externally) where fasteners are removed for surface cracks or 
evidence of distortion and surface defects (scratches, gouges, nicks, 
scores, dents, surface pitting/corrosion, or other surface damage), and 
corrective actions as necessary; repetitive bolt hole eddy current 
(BHEC) inspections of all identified fastener holes (except reference 
holes) for cracks, and corrective actions as necessary; repetitive eddy 
current surface scans for surface defects and cracks of the drag angle 
(along the bending radius) and all fastener holes in which crack(s) 
indication is observed, and corrective actions as necessary; repetitive 
structural gap checks of the mating surface between the wing lower skin 
and the drag angles and corrective actions as necessary; and procedures 
for replacing certain rivets with certain fasteners, and corrective 
actions as necessary. Corrective actions include, among other things, 
repair, replacement, and oversizing any affected holes.
    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.

Costs of Compliance

    The FAA estimates that this AD affects 4 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
               Labor cost                   Parts cost         Cost per product         Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 48 work-hours x $85 per hour = Up               $0  Up to $4,080..............  Up to $16,320.
 to $4,080.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    The FAA estimates that it would take about 1 work-hour per product 
to comply with the reporting requirement in this AD. The average labor 
rate is $85 per hour. Based on these figures, the FAA estimates the 
cost of reporting the inspection results on U.S. operators to be $340, 
or $85 per product.
    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the on-condition actions specified 
in this AD.

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 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 current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to 
Information Collection Clearance Officer, Federal Aviation 
Administration, 10101

[[Page 445]]

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.
    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.
    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 transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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.

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):

2019-25-11 Viking Air Limited (Type Certificate previously held by 
Bombardier, Inc.; Canadair Limited): Amendment 39-21009; Docket No. 
FAA-2019-0710; Product Identifier 2019-NM-060-AD.

(a) Effective Date

    This AD is effective February 10, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Viking Air Limited (Type Certificate 
previously held by Bombardier, Inc.; Canadair Limited) airplanes, 
certificated in any category, identified in paragraphs (c)(1) and 
(2) of this AD.
    (1) Model CL-215-1A10 airplanes, serial numbers 1001 through 
1125 inclusive.
    (2) Model CL-215-6B11 (CL-215T Variant) airplanes, serial 
numbers 1001 through 1125 inclusive.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracks on the wing lower skin 
under the drag angle at a certain wing station (WS). The FAA is 
issuing this AD to address this condition, which if not detected and 
corrected, may lead to widespread fatigue damage and wing structure 
failure.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Reporting of Existing Repairs

    (1) Within 10 months after the effective date of this AD: 
Perform a one-time inspection to identify existing standard 
structural repair manual (SRM) repairs and non-standard repairs on 
the wing box between WS 355L and WS 355R in accordance with the 
Accomplishment Instructions of Viking Alert Service Bulletin 215-
A568, Revision 4, dated January 22, 2019. A review of airplane 
maintenance records is acceptable in lieu of this inspection if 
accomplishment of the repair or modification can be conclusively 
determined from that review. For the purposes of this AD, 
replacement of damaged wing box primary structural member is 
considered a ``repair.''
    (2) If, during the inspection required by paragraph (g)(1) of 
this AD, a repair or modification of the wing box between WS 355L 
and WS 355R is found: Within 11 months after the effective date of 
this AD: Submit an Inspection Reply Form with details of the repair 
or modification to Viking Air Limited via email at 
[email protected] or via fax at 1-403-295-8888, and 
request inspection instructions for the repaired or modified 
structure in accordance with the procedures specified in paragraph 
(o)(2) of this AD.

(h) Record Keeping

    Beginning no later than 30 days after the effective date of this 
AD: Record all water landings, land landings, and water drops, and 
use this data to determine compliance times for the inspections 
required by paragraph (i) of this AD. For the purposes of this AD, 
total operation cycles equals water drops plus water landings (non-
water scooping/dropping operations) plus land landings. If there are 
no records of water landings, determine total operation cycles using 
only land landings and water drops.

(i) Repetitive Actions

    Except as specified in paragraph (m) of this AD, at the earliest 
of the times specified in figure 1 to paragraphs (i), (l), and (m) 
of this AD: Do the actions specified in paragraphs (i)(1) through 
(6) of this AD. Repeat the actions thereafter at intervals not to 
exceed the earliest of the times specified in figure 2 to paragraphs 
(i) and (m) of this AD.
    (1) Perform a visual inspection of the fastener installation for 
abnormal conditions (missed, sheared, distorted, deformed or loose 
fastener heads/collar/nuts, and corrosion) in accordance with 
Section II.A.1. of the Accomplishment Instructions of Viking Alert 
Service Bulletin 215-A568, Revision 4, dated January 22, 2019.
    (2) Perform a visual inspection of the open fastener holes for 
cracks, burrs, elongation, double or mis-drilled holes, and 
corrosion in accordance with Section II.A.1. of the Accomplishment 
Instructions of Viking Alert Service Bulletin 215-A568, Revision 4, 
dated January 22, 2019.
    (3) Perform a visual inspection of the drag angles, wing lower 
skin, lower stringers, spar lower caps/webs, and fuselage structures 
(internally and externally) where fasteners are removed for surface 
cracks or evidence of distortion and surface defects in accordance 
with Section II.A.2. of the Accomplishment Instructions of Viking 
Alert Service Bulletin 215-A568, Revision 4, dated January 22, 2019.
    (4) Perform a bolt hole eddy current (BHEC) inspection of all 
identified fastener holes (except reference holes) specified in 
Figure 1 of Viking Alert Service Bulletin 215-A568, Revision 4, 
dated January 22, 2019, for any cracks in accordance with Section 
II.A.3. of the Accomplishment Instructions of Viking Alert Service 
Bulletin 215-A568, Revision 4, dated January 22, 2019.

[[Page 446]]

    (5) Perform an eddy current surface scan for surface defects and 
cracks of the drag angle (along the bending radius) and all fastener 
holes in which crack(s) indication have been observed in accordance 
with Section II.A.4. of the Accomplishment Instructions of Viking 
Alert Service Bulletin 215-A568, Revision 4, dated January 22, 2019.
    (6) Perform a structural gap check between the drag angles and 
the wing lower skin in accordance with Section II.A.5. of the 
Accomplishment Instructions of Viking Alert Service Bulletin 215-
A568, Revision 4, dated January 22, 2019.
[GRAPHIC] [TIFF OMITTED] TR06JA20.002

(j) Corrective Actions

    If any of the findings identified in paragraphs (j)(1) through 
(6) of this AD are found, before further flight, repair using a 
method approved by the Manager, New York ACO Branch, FAA; or 
Transport Canada Civil Aviation (TCCA); or Viking Air Limited's TCCA 
Design Approval Organization (DAO). If approved by the DAO, the 
approval must include the DAO-authorized signature.
    (1) If, during any inspection required by paragraph (i)(1) of 
this AD, any abnormal condition is found.
    (2) If, during any inspection required by paragraph (i)(2) of 
this AD, any cracks, burrs, elongation, double or mis-drilled holes, 
or corrosion are found.
    (3) If, during any inspection required by paragraph (i)(3) of 
this AD, any surface cracks or evidence of distortion or surface 
defects are found.
    (4) If, during any inspection required by paragraph (i)(4) of 
this AD, any cracks are found.
    (5) If, during any inspection required by paragraph (i)(5) of 
this AD, any surface defects or cracks are found.
    (6) If, during any structural gap check required by paragraph 
(i)(6) of this AD, any gaps are found.

(k) Exception to Service Information

    Where Viking Alert Service Bulletin 215-A568, Revision 4, dated 
January 22, 2019, specifies that preventative Repair Engineering 
Order (REO) 215-57-V022 may be installed and certain inspections may 
be done as specified in that REO, this AD does not allow the use of 
that REO for compliance with this AD.

(l) Replace Rivets

    For airplanes on which the actions specified in Viking Alert 
Service Bulletin 215-A568, Revision 3, dated June 15, 2016, or 
earlier, have been accomplished: At the earliest of the times 
specified in figure 1 to paragraphs (i), (l), and (m) of this AD, 
perform a one-time replacement of installed NAS1242AD rivets with 
Titanium Hi-Lite fasteners and do a BHEC inspection of the open 
holes for cracks in accordance with the Accomplishment Instructions 
of Viking Alert Service Bulletin 215-A568, Revision 4, dated January 
22, 2019. If any crack is found, before further flight, repair using 
a method approved by the Manager, New York ACO Branch, FAA; or TCCA; 
or Viking Air Limited's TCCA DAO. If approved by the DAO, the 
approval must include the DAO-authorized signature.

(m) Initial Compliance Time for Certain Airplanes

    (1) For airplanes on which the actions specified in Viking Alert 
Service Bulletin 215-A568, Revision 3, dated June 15, 2016, or 
earlier, have not been accomplished: At the times specified in 
figure 3 to paragraph (m)(1) of this AD, accomplish the actions 
required by paragraph (i) of this AD. Repeat the actions thereafter 
at the times specified in figure 2 to paragraphs (i) and (m) of this 
AD. For the purposes of this AD, the earliest compliance time 
applies if the accumulated airplane flight times (flight hours, 
water drops, or total operation cycles) meet multiple criteria.

[[Page 447]]

[GRAPHIC] [TIFF OMITTED] TR06JA20.003

    (2) For airplanes on which the actions specified in Viking Alert 
Service Bulletin 215-A568, Revision 3, dated June 15, 2016, or 
earlier, have been accomplished: At the times specified in figure 4 
to paragraph (m)(2) of this AD, accomplish the actions required by 
paragraph (i) of this AD. Repeat the actions thereafter at the times 
specified in figure 2 to paragraphs (i) and (m) of this AD. For the 
purposes of this AD, the earliest compliance time applies if the 
accumulated airplane flight times (flight hours, water drops, or 
total operation cycles) meet multiple criteria.

[[Page 448]]

[GRAPHIC] [TIFF OMITTED] TR06JA20.004

(n) Reporting

    At the applicable time specified in paragraph (n)(1) or (2) of 
this AD: Report the results of the actions required by paragraph (i) 
of this AD to Viking Air Limited via email at 
[email protected] or fax at +1-403-295-8888 in 
accordance with the instructions of Viking Alert Service Bulletin 
215-A568, Revision 4, dated January 22, 2019.
    (1) If the action was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the action was done before the effective date of this AD: 
Submit the report within 30 days after the effective date of this 
AD.

(o) 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. 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 ATTN: Program Manager, Continuing Operational 
Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, 
Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, New York ACO 
Branch, FAA; or TCCA; or Viking Air Limited's TCCA DAO. If approved 
by the DAO, the approval must include the DAO-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 current 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, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory as 
required by this AD. 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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian AD CF-2019-07, dated March 4, 2019, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2019-0710.
    (2) For more information about this AD, contact Aziz Ahmed, 
Aerospace Engineer, Airframe and Propulsion Section, FAA, New York 
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone 516-228-7329; fax 516-794-5531; email [email protected].

(q) 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 Alert Service Bulletin 215-A568, Revision 4, dated 
January 22, 2019.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Viking Air Limited, 1959 de Havilland Way, Sidney, British Columbia 
V8L 5V5, Canada; telephone +1-250-656-7227; fax +1-250-656-0673; 
email [email protected]; internet https://www.vikingair.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (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: https://

[[Page 449]]

www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on December 12, 2019.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2019-28470 Filed 1-3-20; 8:45 am]
BILLING CODE 4910-13-P