Airworthiness Directives; De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Airplanes, 57030-57033 [2021-22292]
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Federal Register / Vol. 86, No. 196 / Thursday, October 14, 2021 / Rules and Regulations
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229; email
vladimir.ulyanov@faa.gov.
(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.
(3) The following service information was
approved for IBR on November 18, 2021.
(i) European Union Aviation Safety Agency
(EASA) AD 2020–0245, dated November 9,
2020.
(ii) [Reserved]
(4) For EASA AD 2020–0245, contact
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 8999
000; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(5) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195. This material may be found
in the AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2021–0261.
(6) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email
fr.inspection@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on September 22, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
This AD is effective November
18, 2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 18, 2021.
DATES:
For service information
identified in this final rule, contact De
Havilland Aircraft of Canada Limited,
Q-Series Technical Help Desk, 123
Garratt Boulevard, Toronto, Ontario
M3K 1Y5, Canada; telephone 416–375–
4000; fax 416–375–4539; email thd@
dehavilland.com; internet https://
dehavilland.com. You may view this
service information at the FAA,
Airworthiness Products Section,
Operational Safety 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–2021–0312.
ADDRESSES:
[FR Doc. 2021–22293 Filed 10–13–21; 8:45 am]
Examining the AD Docket
BILLING CODE 4910–13–P
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0312; 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,
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0312; Project
Identifier MCAI–2020–01376–T; Amendment
39–21729; AD 2021–19–11]
RIN 2120–AA64
Airworthiness Directives; De Havilland
Aircraft of Canada Limited (Type
Certificate Previously Held by
Bombardier, Inc.) Airplanes
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De Havilland Aircraft of Canada Limited
Model DHC–8–102, –103, and –106
airplanes; Model DHC–8–201 and –202
airplanes; Model DHC–8–301, –311, and
–315 airplanes; and Model DHC–8–400,
–401, and –402 airplanes. This AD was
prompted by reports that mounting nuts
attaching the rudder actuator bracket to
the vertical stabilizer have been found
cracked or missing due to hydrogen
embrittlement. This AD requires a onetime inspection of the rudder actuator
bracket mounting nuts, and corrective
actions if necessary. The FAA is issuing
this AD to address the unsafe condition
on these products.
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
SUMMARY:
VerDate Sep<11>2014
16:23 Oct 13, 2021
Jkt 256001
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
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Background
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued TCCA AD CF–
2020–34, dated October 6, 2020 (TCCA
AD CF–2020–34) (also referred to after
this as the Mandatory Continuing
Airworthiness Information, or the
MCAI), to correct an unsafe condition
for certain De Havilland Aircraft of
Canada Limited Model DHC–8–102,
–103, and –106 airplanes; Model DHC–
8–201 and –202 airplanes; Model DHC–
8–301, –311, –314, and –315 airplanes;
and Model DHC–8–400, –401, and –402
airplanes. Model DHC–8–314 airplanes
are not certificated by the FAA and are
not included on the U.S. type certificate
data sheet; this AD therefore does not
include those airplanes in the
applicability. You may examine the
MCAI in the AD docket at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0312.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain De Havilland Aircraft of
Canada Limited Model DHC–8–102,
–103, and –106 airplanes; Model DHC–
8–201 and –202 airplanes; Model DHC–
8–301, –311, and –315 airplanes; and
Model DHC–8–400, –401, and –402
airplanes. The NPRM published in the
Federal Register on April 20, 2021 (86
FR 20459). The NPRM was prompted by
reports that mounting nuts attaching the
rudder actuator bracket to the vertical
stabilizer have been found cracked or
missing due to hydrogen embrittlement.
The NPRM proposed to require a onetime inspection of the rudder actuator
bracket mounting nuts, and corrective
actions if necessary. The FAA is issuing
this AD to address the possible loss of
the rudder actuator bracket, which
could result in a dormant disconnection
between the rudder actuator and the
vertical stabilizer. This condition, if not
addressed, could result in a loss of
directional control of the aircraft. See
the MCAI for additional background
information.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
Support for the NPRM
The Air Line Pilots Association,
International (ALPA), indicated its
support for the NPRM.
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Federal Register / Vol. 86, No. 196 / Thursday, October 14, 2021 / Rules and Regulations
Request To Require Procedure Only
Horizon Air requested that paragraph
(g) of the proposed AD be changed to
require only paragraph 3.B. (Procedure)
of the Accomplishment Instructions of
the applicable service information.
Horizon stated that requiring paragraph
3.A. (Job Set-up) and paragraph 3.C.
(Close-Out) restricts an operator’s ability
to perform other maintenance in
conjunction with the required actions.
The FAA agrees with the request.
Paragraph (g) of this AD has been
changed to require only paragraph 3.B.
(Procedure) of the Accomplishment
Instructions of De Havilland Service
Bulletin 8–27–123, Revision A, dated
September 8, 2020; or Service Bulletin
84–27–74, Revision B, dated September
8, 2020; as applicable.
Request To Remove and Replace All
Suspect Hardware
A commenter suggested removal and
replacement of ‘‘all suspect hardware.’’
The commenter asserted that hydrogen
embrittlement would not be evident by
way of visual inspection. The FAA
infers a request to change the
requirements of the proposed AD to
replace all affected rudder actuator
bracket mounting nuts instead of relying
on an inspection to determine which
mounting nuts need replacement.
The FAA disagrees with the request.
The FAA notes that the rudder actuator
bracket mounting nuts were installed as
required by AD 2012–04–08,
Amendment 39–16964 (77 FR 13193,
March 6, 2012), which has a compliance
time of within 6,000 flight hours or 3
years after April 10, 2012, whichever
occurs first. Viking confirmed that
mounting nuts with hydrogen
embrittlement can show cracking as
soon as one week after being torqued.
However, these airplanes have been
flying for several years with the
mounting nuts installed and without
reports of loss of directional control of
the airplane caused by the mounting
nuts. TCCA and Viking therefore
determined, and the FAA agrees, that a
one-time visual inspection and
replacement if necessary is sufficient to
address the unsafe condition. This AD
has not been changed with regard to this
request.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the change described
previously and 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
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• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
The FAA also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
De Havilland has issued Service
Bulletin 8–27–123, Revision A, dated
September 8, 2020; and Service Bulletin
84–27–74, Revision B, dated September
8, 2020. This service information
specifies procedures for doing a detailed
visual inspection of the nuts attaching
the rudder actuator brackets to the rear
spar. If the nuts are corroded, cracked,
or otherwise damaged, or if they are
missing, they are replaced. These
documents are distinct since they apply
to different airplane models. 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
would affect 69 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
3 work-hours × $85 per hour = $255 ..........................................................................................
$0
$255
$17,595
The FAA estimates the following
costs to do any necessary replacement
that would be required based on the
results of the inspection. The agency has
no way of determining the number of
aircraft that might need this
replacement:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Nut replacement ..........................................
2 work-hours × $85 per hour = $170 ............................................
Minimal ..........
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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
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16:23 Oct 13, 2021
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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.
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Cost per
product
$170
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:
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Federal Register / Vol. 86, No. 196 / Thursday, October 14, 2021 / Rules and Regulations
(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
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:
■
2021–19–11 De Havilland Aircraft of
Canada Limited (Type Certificate
Previously Held by Bombardier, Inc.):
Amendment 39–21729; Docket No.
FAA–2021–0312; Project Identifier
MCAI–2020–01376–T.
(a) Effective Date
This airworthiness directive (AD) is
effective November 18, 2021.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to De Havilland Aircraft
of Canada Limited (type certificate
previously held by Bombardier, Inc.)
airplanes, certificated in any category, and
identified in paragraphs (c)(1) through (4) of
this AD.
(1) Model DHC–8–102, –103, and –106
airplanes, as identified in De Havilland
Service Bulletin 8–27–123, Revision A, dated
September 8, 2020.
(2) Model DHC–8–201 and –202 airplanes,
as identified in De Havilland Service Bulletin
8–27–123, Revision A, dated September 8,
2020.
(3) Model DHC–8–301, –311, and –315
airplanes, as identified in De Havilland
Service Bulletin 8–27–123, Revision A, dated
September 8, 2020.
(4) Model DHC–8–400, –401, and –402
airplanes, as identified in De Havilland
Service Bulletin 84–27–74, Revision B, dated
September 8, 2020.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
VerDate Sep<11>2014
16:23 Oct 13, 2021
Jkt 256001
(e) Unsafe Condition
This AD was prompted by reports that
mounting nuts attaching the rudder actuator
bracket to the vertical stabilizer have been
found cracked or missing due to hydrogen
embrittlement. The FAA is issuing this AD to
address the possible loss of the rudder
actuator bracket, which could result in a
dormant disconnection between the rudder
actuator and the vertical stabilizer. This
condition, if not addressed, could result in a
loss of directional control of the aircraft.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
Within 8,000 flight hours or 4 years,
whichever is earlier, after the effective date
of this AD: Do a detailed visual inspection of
the rudder actuator bracket mounting nuts for
missing nuts or corrosion, cracking, or other
damage, in accordance with paragraph 3.B. of
the Accomplishment Instructions of De
Havilland Service Bulletin 8–27–123,
Revision A, dated September 8, 2020; or De
Havilland Service Bulletin 84–27–74,
Revision B, dated September 8, 2020; as
applicable. If any missing nuts or corrosion,
cracking, or other damage is found, replace
the nuts before further flight, in accordance
with paragraph 3.B. of the Accomplishment
Instructions of De Havilland Service Bulletin
8–27–123, Revision A, dated September 8,
2020; or De Havilland Service Bulletin 84–
27–74, Revision B, dated September 8, 2020;
as applicable.
(h) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using De Havilland Service
Bulletin 8–27–123, dated December 20, 2019;
De Havilland Service Bulletin 84–27–74,
dated December 20, 2019; or De Havilland
Service Bulletin 84–27–74, Revision A, dated
January 20, 2020; as applicable.
(i) No Reporting Requirement
Although De Havilland Service Bulletin 8–
27–123, Revision A, dated September 8,
2020; and De Havilland Service Bulletin 84–
27–74, Revision B, dated September 8, 2020,
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) 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
responsible Flight Standards 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,
PO 00000
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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
responsible Flight Standards 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 Transport Canada Civil Aviation
(TCCA); or De Havilland Aircraft of Canada
Limited’s TCCA Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) TCCA AD
CF–2020–34, dated October 6, 2020, 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–2021–0312.
(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.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (l)(3) and (4) of this AD.
(l) 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) De Havilland Service Bulletin 8–27–123,
Revision A, dated September 8, 2020.
(ii) De Havilland Service Bulletin 84–27–
74, Revision B, dated September 8, 2020.
(3) For service information identified in
this AD, contact De Havilland Aircraft of
Canada Limited, Q-Series Technical Help
Desk, 123 Garratt Boulevard, Toronto,
Ontario M3K 1Y5, Canada; telephone 416–
375–4000; fax 416–375–4539; email thd@
dehavilland.com; internet https://
dehavilland.com.
(4) You may view this service information
at the FAA, Airworthiness Products Section,
Operational Safety 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 fr.inspection@nara.gov, or go to:
https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
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Federal Register / Vol. 86, No. 196 / Thursday, October 14, 2021 / Rules and Regulations
Issued on September 7, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
searching for and locating Docket No.
FAA–2021–0462.
[FR Doc. 2021–22292 Filed 10–13–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0462; Project
Identifier MCAI–2020–01714–T; Amendment
39–21751; AD 2021–20–13]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model CL–600–2B16
(604 Variant) airplanes. This AD was
prompted by multiple reports of
cracking of the main landing gear (MLG)
shock strut lower pin. This AD requires
repetitive lubrication and repetitive
detailed visual inspections (DVI) and
non-destructive test (NDT) inspections
of the MLG shock strut lower pins, and
replacement if necessary. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective November
18, 2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 18, 2021.
ADDRESSES: For service information
identified in this final rule, contact
Bombardier, Inc., 200 Coˆte-Vertu Road
West, Dorval, Que´bec H4S 2A3, Canada;
North America toll-free telephone 1–
866–538–1247 or direct-dial telephone
1–514–855–2999; email ac.yul@
aero.bombardier.com; internet https://
www.bombardier.com. You may view
this service information at the FAA,
Airworthiness Products Section,
Operational Safety 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
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SUMMARY:
VerDate Sep<11>2014
16:23 Oct 13, 2021
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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–2021–
0462; 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,
any comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Chirayu Gupta, Aerospace Engineer,
Mechanical Systems and Administrative
Services Section, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531; email
9-avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued TCCA AD CF–
2020–54R1, dated December 23, 2020
(TCCA AD CF–2020–54R1) (also
referred to after this as the Mandatory
Continuing Airworthiness Information,
or the MCAI), to correct an unsafe
condition for certain Bombardier, Inc.,
Model CL–600–2B16 (604 Variant)
airplanes. You may examine the MCAI
in the AD docket at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
0462.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Bombardier, Inc., Model
CL–600–2B16 (604 Variant) airplanes.
The NPRM published in the Federal
Register on June 14, 2021 (86 FR 31453).
The NPRM was prompted by multiple
reports of cracking of the MLG shock
strut lower pin part number (P/N)
19146–3. The subsequent investigation
concluded that the friction torque when
the shock strut is under compression
loading, causes the pin anti-rotation
tangs to become loaded beyond their
load carrying capability. This overload
condition can result in pin fracture
originating at the base of the pin antirotation tang. Inadequate lubrication
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57033
aggravates the condition. The NPRM
proposed to require repetitive
lubrication and repetitive DVI and NDT
inspections of the MLG shock strut
lower pins, and replacement if
necessary. The FAA is issuing this AD
to address cracking of the MLG shock
strut lower pin. If not addressed, this
condition could result in structural
failure of one or both MLG. 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
Bombardier, Inc., has issued the
following service information:
• Service Bulletin 604–32–030, dated
June 30, 2020.
• Service Bulletin 605–32–007, dated
June 30, 2020.
• Service Bulletin 650–32–004, dated
June 30, 2020.
This service information describes
procedures for lubricating, inspecting
(DVI and NDT inspections for cracking
and damage, including fracture of the
MLG shock strut lower pin at the pin
rotation tang location), and replacing
the MLG shock strut lower pin. These
documents are distinct since they apply
to different airplane configurations. 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 433 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
E:\FR\FM\14OCR1.SGM
14OCR1
]]>Agencies
[Federal Register Volume 86, Number 196 (Thursday, October 14, 2021)]
[Rules and Regulations]
[Pages 57030-57033]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-22292]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0312; Project Identifier MCAI-2020-01376-T;
Amendment 39-21729; AD 2021-19-11]
RIN 2120-AA64
Airworthiness Directives; De Havilland Aircraft of Canada Limited
(Type Certificate Previously Held by Bombardier, Inc.) 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 De Havilland Aircraft of Canada Limited Model DHC-8-102, -103,
and -106 airplanes; Model DHC-8-201 and -202 airplanes; Model DHC-8-
301, -311, and -315 airplanes; and Model DHC-8-400, -401, and -402
airplanes. This AD was prompted by reports that mounting nuts attaching
the rudder actuator bracket to the vertical stabilizer have been found
cracked or missing due to hydrogen embrittlement. This AD requires a
one-time inspection of the rudder actuator bracket mounting nuts, and
corrective actions if necessary. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective November 18, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of November 18,
2021.
ADDRESSES: For service information identified in this final rule,
contact De Havilland Aircraft of Canada Limited, Q-Series Technical
Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada;
telephone 416-375-4000; fax 416-375-4539; email [email protected];
internet https://dehavilland.com. You may view this service information
at the FAA, Airworthiness Products Section, Operational Safety 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-2021-0312.
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-2021-
0312; 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, any comments received, and other information. The
address for Docket Operations is U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, 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:
Background
Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued TCCA AD CF-2020-34, dated October 6,
2020 (TCCA AD CF-2020-34) (also referred to after this as the Mandatory
Continuing Airworthiness Information, or the MCAI), to correct an
unsafe condition for certain De Havilland Aircraft of Canada Limited
Model DHC-8-102, -103, and -106 airplanes; Model DHC-8-201 and -202
airplanes; Model DHC-8-301, -311, -314, and -315 airplanes; and Model
DHC-8-400, -401, and -402 airplanes. Model DHC-8-314 airplanes are not
certificated by the FAA and are not included on the U.S. type
certificate data sheet; this AD therefore does not include those
airplanes in the applicability. You may examine the MCAI in the AD
docket at https://www.regulations.gov by searching for and locating
Docket No. FAA-2021-0312.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain De Havilland
Aircraft of Canada Limited Model DHC-8-102, -103, and -106 airplanes;
Model DHC-8-201 and -202 airplanes; Model DHC-8-301, -311, and -315
airplanes; and Model DHC-8-400, -401, and -402 airplanes. The NPRM
published in the Federal Register on April 20, 2021 (86 FR 20459). The
NPRM was prompted by reports that mounting nuts attaching the rudder
actuator bracket to the vertical stabilizer have been found cracked or
missing due to hydrogen embrittlement. The NPRM proposed to require a
one-time inspection of the rudder actuator bracket mounting nuts, and
corrective actions if necessary. The FAA is issuing this AD to address
the possible loss of the rudder actuator bracket, which could result in
a dormant disconnection between the rudder actuator and the vertical
stabilizer. This condition, if not addressed, could result in a loss of
directional control of the aircraft. See the MCAI for additional
background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Support for the NPRM
The Air Line Pilots Association, International (ALPA), indicated
its support for the NPRM.
[[Page 57031]]
Request To Require Procedure Only
Horizon Air requested that paragraph (g) of the proposed AD be
changed to require only paragraph 3.B. (Procedure) of the
Accomplishment Instructions of the applicable service information.
Horizon stated that requiring paragraph 3.A. (Job Set-up) and paragraph
3.C. (Close-Out) restricts an operator's ability to perform other
maintenance in conjunction with the required actions.
The FAA agrees with the request. Paragraph (g) of this AD has been
changed to require only paragraph 3.B. (Procedure) of the
Accomplishment Instructions of De Havilland Service Bulletin 8-27-123,
Revision A, dated September 8, 2020; or Service Bulletin 84-27-74,
Revision B, dated September 8, 2020; as applicable.
Request To Remove and Replace All Suspect Hardware
A commenter suggested removal and replacement of ``all suspect
hardware.'' The commenter asserted that hydrogen embrittlement would
not be evident by way of visual inspection. The FAA infers a request to
change the requirements of the proposed AD to replace all affected
rudder actuator bracket mounting nuts instead of relying on an
inspection to determine which mounting nuts need replacement.
The FAA disagrees with the request. The FAA notes that the rudder
actuator bracket mounting nuts were installed as required by AD 2012-
04-08, Amendment 39-16964 (77 FR 13193, March 6, 2012), which has a
compliance time of within 6,000 flight hours or 3 years after April 10,
2012, whichever occurs first. Viking confirmed that mounting nuts with
hydrogen embrittlement can show cracking as soon as one week after
being torqued. However, these airplanes have been flying for several
years with the mounting nuts installed and without reports of loss of
directional control of the airplane caused by the mounting nuts. TCCA
and Viking therefore determined, and the FAA agrees, that a one-time
visual inspection and replacement if necessary is sufficient to address
the unsafe condition. This AD has not been changed with regard to this
request.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the change described previously
and 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.
The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
De Havilland has issued Service Bulletin 8-27-123, Revision A,
dated September 8, 2020; and Service Bulletin 84-27-74, Revision B,
dated September 8, 2020. This service information specifies procedures
for doing a detailed visual inspection of the nuts attaching the rudder
actuator brackets to the rear spar. If the nuts are corroded, cracked,
or otherwise damaged, or if they are missing, they are replaced. These
documents are distinct since they apply to different airplane models.
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 would affect 69 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Labor cost Parts cost product operators
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3 work-hours x $85 per hour = $255........................... $0 $255 $17,595
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The FAA estimates the following costs to do any necessary
replacement that would be required based on the results of the
inspection. The agency has no way of determining the number of aircraft
that might need this replacement:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Nut replacement........................ 2 work-hours x $85 per Minimal..................... $170
hour = $170.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
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:
[[Page 57032]]
(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:
2021-19-11 De Havilland Aircraft of Canada Limited (Type Certificate
Previously Held by Bombardier, Inc.): Amendment 39-21729; Docket No.
FAA-2021-0312; Project Identifier MCAI-2020-01376-T.
(a) Effective Date
This airworthiness directive (AD) is effective November 18,
2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to De Havilland Aircraft of Canada Limited (type
certificate previously held by Bombardier, Inc.) airplanes,
certificated in any category, and identified in paragraphs (c)(1)
through (4) of this AD.
(1) Model DHC-8-102, -103, and -106 airplanes, as identified in
De Havilland Service Bulletin 8-27-123, Revision A, dated September
8, 2020.
(2) Model DHC-8-201 and -202 airplanes, as identified in De
Havilland Service Bulletin 8-27-123, Revision A, dated September 8,
2020.
(3) Model DHC-8-301, -311, and -315 airplanes, as identified in
De Havilland Service Bulletin 8-27-123, Revision A, dated September
8, 2020.
(4) Model DHC-8-400, -401, and -402 airplanes, as identified in
De Havilland Service Bulletin 84-27-74, Revision B, dated September
8, 2020.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Unsafe Condition
This AD was prompted by reports that mounting nuts attaching the
rudder actuator bracket to the vertical stabilizer have been found
cracked or missing due to hydrogen embrittlement. The FAA is issuing
this AD to address the possible loss of the rudder actuator bracket,
which could result in a dormant disconnection between the rudder
actuator and the vertical stabilizer. This condition, if not
addressed, could result in a loss of directional control of the
aircraft.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Within 8,000 flight hours or 4 years, whichever is earlier,
after the effective date of this AD: Do a detailed visual inspection
of the rudder actuator bracket mounting nuts for missing nuts or
corrosion, cracking, or other damage, in accordance with paragraph
3.B. of the Accomplishment Instructions of De Havilland Service
Bulletin 8-27-123, Revision A, dated September 8, 2020; or De
Havilland Service Bulletin 84-27-74, Revision B, dated September 8,
2020; as applicable. If any missing nuts or corrosion, cracking, or
other damage is found, replace the nuts before further flight, in
accordance with paragraph 3.B. of the Accomplishment Instructions of
De Havilland Service Bulletin 8-27-123, Revision A, dated September
8, 2020; or De Havilland Service Bulletin 84-27-74, Revision B,
dated September 8, 2020; as applicable.
(h) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using De Havilland Service Bulletin 8-27-123, dated
December 20, 2019; De Havilland Service Bulletin 84-27-74, dated
December 20, 2019; or De Havilland Service Bulletin 84-27-74,
Revision A, dated January 20, 2020; as applicable.
(i) No Reporting Requirement
Although De Havilland Service Bulletin 8-27-123, Revision A,
dated September 8, 2020; and De Havilland Service Bulletin 84-27-74,
Revision B, dated September 8, 2020, specify to submit certain
information to the manufacturer, this AD does not include that
requirement.
(j) 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 responsible Flight Standards 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
responsible Flight Standards 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 Transport Canada Civil Aviation (TCCA); or De
Havilland Aircraft of Canada Limited's TCCA Design Approval
Organization (DAO). If approved by the DAO, the approval must
include the DAO-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) TCCA AD CF-2020-34, dated October 6, 2020, 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-2021-0312.
(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].
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (l)(3) and (4) of this AD.
(l) 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) De Havilland Service Bulletin 8-27-123, Revision A, dated
September 8, 2020.
(ii) De Havilland Service Bulletin 84-27-74, Revision B, dated
September 8, 2020.
(3) For service information identified in this AD, contact De
Havilland Aircraft of Canada Limited, Q-Series Technical Help Desk,
123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone
416-375-4000; fax 416-375-4539; email [email protected]; internet
https://dehavilland.com.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety 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://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 57033]]
Issued on September 7, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-22292 Filed 10-13-21; 8:45 am]
BILLING CODE 4910-13-P
