Airworthiness Directives; Viking Air Limited (Type Certificate Previously Held by Bombardier, Inc.; Canadair Limited) Airplanes, 443-449 [2019-28470]
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Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
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 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 Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
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(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2018–32, dated December 10, 2018,
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–2019–0256.
(2) For more information about this AD,
contact Steven Dzierzynski, Aerospace
Engineer, Avionics and Electrical Systems
Services Section, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–228–
7367; fax 516–794–5531; email 9-avs-nyacocos@faa.gov.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (4) of this AD.
(k) 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) Bombardier CRJ Series Regional Jet
Model CL–600–2B19 Airplane Flight Manual
(AFM), Volume 1, CSP A–012, Revision 70,
dated July 13, 2018.
(A) Subject 2, ‘‘Automatic Flight Control
System (AFCS),’’ of Section 02–08, ‘‘System
Limitations,’’ of Chapter 2, ‘‘LIMITATIONS.’’
(B) Subject 1.C, ‘‘Engine Failure in Climb
During ALTS CAP,’’ and Subject 1.C, ‘‘Engine
Failure in Climb During (V) ALTS CAP,’’ of
Section 05–02, ‘‘In-flight Engine Failures,’’ of
Chapter 5, ‘‘ABNORMAL PROCEDURES.’’
(ii) Bombardier CRJ Series Regional Jet
Model CL–600–2C10 AFM, CSP B–012,
Revision 24, dated May 11, 2018.
(A) Subject 2, ‘‘Automatic Flight Control
System (AFCS),’’ of Section 02–08, ‘‘System
Limitations,’’ of Chapter 2, ‘‘LIMITATIONS.’’
(B) Subject 1.C, ‘‘Engine Failure in Climb
During ALTS CAP,’’ and Subject 1.C, ‘‘Engine
Failure in Climb During (V) ALTS CAP,’’ of
Section 05–02, ‘‘In-flight Engine Failures,’’ of
Chapter 5, ‘‘ABNORMAL PROCEDURES.’’
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(iii) Bombardier CRJ Series Regional Jet
Model CL–600–2D24 and Model CL–600–
2D15 AFM, Volume 1, CSP C–012, Revision
19A, dated August 17, 2018.
(A) Subject 2, ‘‘Automatic Flight Control
System (AFCS),’’ of Section 02–08, ‘‘System
Limitations,’’ of Chapter 2, ‘‘LIMITATIONS.’’
(B) Subject 1.C, ‘‘Engine Failure in Climb
During ALTS CAP,’’ and Subject 1.C, ‘‘Engine
Failure in Climb During (V) ALTS CAP,’’ of
Section 05–02, ‘‘In-flight Engine Failures,’’ of
Chapter 5, ‘‘ABNORMAL PROCEDURES.’’
(iv) Bombardier CRJ Series Regional Jet
Model CL–600–2E25 AFM, CSP D–012,
Revision 20, dated September 28, 2018.
(A) Subject 2, ‘‘Automatic Flight Control
System (AFCS),’’ of Section 02–08, ‘‘System
Limitations,’’ of Chapter 2, ‘‘LIMITATIONS.’’
(B) Subject 1.C, ‘‘Engine Failure in Climb
During ALTS CAP,’’ and Subject 1.C, ‘‘Engine
Failure in Climb During (V) ALTS CAP,’’ of
Section 05–02, ‘‘In-flight Engine Failures,’’ of
Chapter 5, ‘‘ABNORMAL PROCEDURES.’’
(3) For service information identified in
this AD, contact Bombardier, Inc., 400 Coˆte
Vertu Road West, Dorval, Que´bec H4S 1Y9,
Canada; Widebody Customer Response
Center North America toll-free telephone 1–
866–538–1247 or direct-dial telephone 1–
514–855–2999; fax 514–855–7401; email
ac.yul@aero.bombardier.com; internet
https://www.bombardier.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 fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
443
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.
SUMMARY:
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.
DATES:
DEPARTMENT OF TRANSPORTATION
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 acstechnical.publications@vikingair.com;
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.
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
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.
Issued in Des Moines, Washington, on
November 18, 2019.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2019–28463 Filed 1–3–20; 8:45 am]
BILLING CODE 4910–13–P
[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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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ADDRESSES:
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Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
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 9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
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
Up to 48 work-hours × $85 per hour = Up to $4,080 ..............
Cost per product
$0
Cost on U.S. operators
Up to $4,080 ...........................
Up to $16,320.
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* 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 oncondition actions specified in this AD.
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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
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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
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Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
Adoption of the Amendment
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.
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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.
VerDate Sep<11>2014
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Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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
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445
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 technical.support@
vikingair.com 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.
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Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
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
(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
Accomplishment Instructions of Viking Alert
Service Bulletin 215–A568, Revision 4, dated
January 22, 2019.
Figure 1 to paragraphs (i), (1), and (m) -Initial compliance times
Description
Total Flight Hours
as of the Effective
Date of this AD
Total Water Drops
as of the Effective
Date of this AD
Total Operation Cycles
as of the Effective Date
of this AD
Initial
Inspection
Threshold
7,500
10,000
12,000
Figure 2 to paragraphs (i) and (m) - Repetitive compliance times
Description
Flight Hours
Water Drops
Total Operation Cycles
Repetitive
Inspection
3,750
5,000
6,000
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(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
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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 DAOauthorized 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.
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(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.
Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
447
Figure 3 to paragraph (m)(l) - Initial compliance times 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
Total
Flight
Hours as
ofthe
Effective
Date of
this AD
Total Water
Drops as of
the Effective
Date of this
AD
Total Operation
Cycles as of the
Effective Date of
this AD
Compliance Time
7,500 or
more
Or 22,001 or
more
Or 26,401 or more
Within 4 months after the effective
date of this AD
7,500 or
more
Or 20,001 to
22,000
Or 24,001 to
26,400
Within 8 months after the effective
date of this AD
7,500 or
more
Or 10,000 to
20,000
Or 12,000 to
24,000
Within 18 months after the effective
date of this AD
Less than
7,500
And less than
10,000
And less than
12,000
At or before the initial inspection
time in figure 1 to paragraphs (i), (1),
and (m) of this AD, or within 18
months after the effective date of this
AD, whichever occurs later
VerDate Sep<11>2014
17:31 Jan 03, 2020
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(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
PO 00000
Frm 00029
Fmt 4700
Sfmt 4700
compliance time applies if the accumulated
airplane flight times (flight hours, water
drops, or total operation cycles) meet
multiple criteria.
E:\FR\FM\06JAR1.SGM
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lotter on DSKBCFDHB2PROD with RULES
(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
448
Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
Figure 4 to paragraph (m)(2) -Initial compliance times 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
Total
Flight
Hours as
ofthe
Effective
Date of
this AD
Total Water
Drops as of
the Effective
Date of this
AD
Total Operation
Cycles as of the
Effective Date of
this AD
Compliance Time
7,500 or
more
Or 20,001 or
more
Or 24,001 or more
Within 12 months after the effective
date of this AD
7,500 or
more
Or 10,000 to
20,000
Or 12,000 to
24,000
Within 18 months after the effective
date of this AD
Less than
7,500
And less than
10,000
And less than
12,000
At or before the initial inspection
time in figure 1 to paragraphs (i), (1),
and (m) of this AD, or within 18
months after the effective date of this
AD, whichever occurs later
(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.
VerDate Sep<11>2014
17:31 Jan 03, 2020
Jkt 250001
(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
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
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 9avs-nyaco-cos@faa.gov.
(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 acstechnical.publications@vikingair.com;
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 fedreg.legal@nara.gov, or go to: https://
E:\FR\FM\06JAR1.SGM
06JAR1
ER06JA20.004</GPH>
lotter on DSKBCFDHB2PROD with RULES
(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 technicalsupport@vikingair.com 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.
Federal Register / Vol. 85, No. 3 / Monday, January 6, 2020 / Rules and Regulations
www.archives.gov/federal-register/cfr/ibrlocations.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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0983; Product
Identifier 2019–NM–171–AD; Amendment
39–21010; AD 2019–25–12]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2016–18–
02, which applied to certain The Boeing
Company Model 777–200 and –300ER
series airplanes. AD 2016–18–02
required replacing the low-pressure
oxygen flex hoses with new nonconductive low-pressure oxygen flex
hoses in the gaseous passenger oxygen
system in airplanes equipped with
therapeutic oxygen. This AD retains
those actions and adds actions for
certain airplanes. AD 2016–18–02 was
prompted by the determination that the
low-pressure oxygen flex hoses in the
gaseous passenger oxygen system can
potentially be conductive. This AD was
further prompted by the determination
that the associated service information
is inadequate for certain airplanes. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 21,
2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 21, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of September 15, 2016 (81 FR
59834, August 31, 2016).
The FAA must receive any comments
on this AD by February 20, 2020.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
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SUMMARY:
VerDate Sep<11>2014
17:31 Jan 03, 2020
Jkt 250001
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110–SK57,
Seal Beach, CA 90740–5600; telephone
562–797–1717; internet https://
www.myboeingfleet.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–2019–0983.
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–
0983; 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 street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Susan L. Monroe, Aerospace Engineer,
Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3570; email: susan.l.monroe@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued AD 2016–18–02,
Amendment 39–18632 (81 FR 59834,
August 31, 2016) (‘‘AD 2016–18–02’’),
for certain The Boeing Company Model
777–200 and –300ER series airplanes.
AD 2016–18–02 required replacing the
low-pressure oxygen flex hoses with
new non-conductive low-pressure
oxygen flex hoses in the gaseous
passenger oxygen system in airplanes
equipped with therapeutic oxygen. AD
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
449
2016–18–02 resulted from a
determination that the low-pressure
oxygen flex hoses in the gaseous
passenger oxygen system can potentially
be conductive. The FAA issued AD
2016–18–02 to address the potential for
electrical current to pass through the
low-pressure oxygen flex hoses in the
gaseous passenger oxygen system,
which can cause the flex hoses to melt
or burn and result in an oxygen-fed fire
in the passenger cabin.
Actions Since AD 2016–18–02 Was
Issued
Since AD 2016–18–02 was issued, the
FAA has been advised that the required
service information omitted certain
instructions for Group 4 airplanes.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Special
Attention Service Bulletin 777–35–
0041, Revision 1, dated August 14,
2019. This service information describes
procedures for replacing the lowpressure oxygen flex hoses with new
non-conductive low-pressure oxygen
flex hoses in the gaseous passenger
oxygen system in airplanes equipped
with therapeutic oxygen. This service
information adds instructions (i.e.,
Figures 6 and 10) that had previously
been omitted for certain airplanes (i.e.,
Group 4).
This AD requires Boeing Special
Attention Service Bulletin 777–35–
0041, dated April 8, 2016, which the
Director of the Federal Register
approved for incorporation by reference
as of September 15, 2016 (81 FR 59834,
August 31, 2016).
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.
FAA’s Determination
The FAA is issuing this AD because
the agency evaluated all the relevant
information and determined the unsafe
condition described previously is likely
to exist or develop in other products of
the same type design.
AD Requirements
Although this AD does not explicitly
restate the requirements of AD 2016–
18–02, this AD retains the requirements
of AD 2016–18–02. Those requirements
are referenced in the service information
identified previously, which, in turn, is
referenced in paragraph (g) of this AD.
For certain airplanes, this AD adds
actions that were omitted from the
previous service information. This AD
requires accomplishment of the actions
E:\FR\FM\06JAR1.SGM
06JAR1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
