Airworthiness Directives; Bombardier, Inc., Airplanes, 31453-31456 [2021-12351]
Download as PDF
<![CDATA[
Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules
§ 39.13
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(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.
lotter on DSK11XQN23PROD with PROPOSALS1
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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.
VerDate Sep<11>2014
16:49 Jun 11, 2021
Jkt 253001
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
Leonardo S.p.a.: Docket No. FAA–2021–
0461; Project Identifier MCAI–2021–
00156–R.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by July 29, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Leonardo S.p.a.
Model AB139 and AW139 helicopters,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
Code 2400, Electrical Power System.
(e) Unsafe Condition
This AD was prompted by a report of a
short circuit caused by chafing of the
electrical wiring in the overhead panel. The
FAA is issuing this AD to address a short
circuit caused by chafing of the electrical
wiring in the overhead panel, which could
cause damaged electrical wiring, possible fire
in the overhead panel, and loss of control of
the helicopter.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2021–0044, dated
February 5, 2021 (EASA AD 2021–0044).
(h) Exceptions to EASA AD 2021–0044
(1) Where EASA AD 2021–0044 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2021–0044 does not apply to this AD.
(3) Where EASA AD 2021–0044 refers to
flight hours (FH), this AD requires using
hours time-in-service.
(4) Where paragraphs (3) and (5) of EASA
AD 2021–0044 refer to ‘‘any discrepancy,’’
for this AD, discrepancies include chafing of
the cable harnesses or incorrect clearance
between the anchor nuts/screws and the
cable harnesses, incorrect length of the
screws, inadequately bonded supports, and
poor condition of the white protective tape.
(i) No Reporting Requirement
Although EASA AD 2021–0044 and the
service information referenced in EASA AD
2021–0044 specify to submit certain
information to the manufacturer, this AD
does not include that requirement.
(j) Special Flight Permit
Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
31453
to operate the helicopter to a location where
the helicopter can be modified (if the
operator elects to do so), provided the flight
is straight, level, and avoids areas of known
turbulence.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
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 International Validation
Branch, send it to the attention of the person
identified in paragraph (l)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(l) Related Information
(1) For EASA AD 2021–0044, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone: +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. You may view this
material at the FAA, Office of the Regional
Counsel, Southwest Region, 10101 Hillwood
Pkwy., Room 6N–321, Fort Worth, TX 76177.
For information on the availability of this
material at the FAA, call 817–222–5110. This
material may be found in the AD docket at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2021–0461.
(2) For more information about this AD,
contact Jacob Fitch, Aerospace Engineer, COS
Program Management Section, Operational
Safety Branch, Compliance & Airworthiness
Division, FAA, 10101 Hillwood Pkwy., Fort
Worth, TX 76177; phone: (817) 222–4130;
email: jacob.fitch@faa.gov.
Issued on June 7, 2021.
Ross Landes,
Deputy Director for Regulatory Operations,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–12359 Filed 6–11–21; 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]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
E:\FR\FM\14JNP1.SGM
14JNP1
31454
Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules
Notice of proposed rulemaking
(NPRM).
ACTION:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bombardier, Inc., CL–600–2B16
(604 Variant) airplanes. This proposed
AD was prompted by multiple reports of
cracking of the main landing gear (MLG)
shock strut lower pin. This proposed
AD would require 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 proposing this
AD to address the unsafe condition on
these products.
DATES: The FAA must receive comments
on this proposed AD by July 29, 2021.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• 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 NPRM, 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.
SUMMARY:
lotter on DSK11XQN23PROD with PROPOSALS1
Examining the AD Docket
You may examine the AD docket 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
NPRM, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT:
Chirayu Gupta, Aerospace Engineer,
Mechanical Systems and Administrative
Services Section, FAA, New York ACO
VerDate Sep<11>2014
16:49 Jun 11, 2021
Jkt 253001
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:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–0462; Project Identifier
MCAI–2020–01714–T’’ at the beginning
of your comments. The most helpful
comments reference a specific portion of
the proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend the proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to 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 9avs-nyaco-cos@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
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.,
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.
This proposed AD 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
aggravates the condition. The FAA is
proposing 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.
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.
FAA’s Determination
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to the
FAA’s bilateral agreement with the State
of Design Authority, the FAA has been
notified of the unsafe condition
E:\FR\FM\14JNP1.SGM
14JNP1
Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules
described in the MCAI and service
information referenced above. The FAA
is proposing this AD because the FAA
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Proposed AD Requirements in This
NPRM
This proposed AD would require
accomplishing the actions specified in
the service information already
described.
31455
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 433
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
7 work-hours × $85 per hour = $595 ..........................................................................................
$0
$595
$257,635
The FAA estimates the following
costs to do any necessary on-condition
actions that would be required based on
the results of any required actions. The
FAA has no way of determining the
number of aircraft that might need these
on-condition actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Cost per
product
6 work-hours × $85 per hour = $510 ......................................................................................................................
$2,435
$2,945
The FAA has included all known
costs in its cost estimate. According to
the manufacturer, however, some or all
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
operators.
lotter on DSK11XQN23PROD with PROPOSALS1
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
VerDate Sep<11>2014
16:49 Jun 11, 2021
Jkt 253001
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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:
■
Bombardier, Inc.: Docket No. FAA–2021–
0462; Project Identifier MCAI–2020–
01714–T.
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by July 29, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc.,
Model CL–600–2B16 (604 Variant) airplanes,
serial numbers (S/N) 5301 through 5665
inclusive, 5701 through 5988 inclusive, and
6050 through 6999 inclusive, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Unsafe Condition
This AD was prompted by multiple reports
of cracking of the main landing gear (MLG)
shock strut lower pin. 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.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Lubrication
Within 200 flight hours (FH) or 12 months
after the effective date of this AD, whichever
occurs first, lubricate the left-hand (LH) and
right-hand (RH) MLG shock strut lower pins
having part number (P/N) 19146–3, in
accordance with paragraph 2.B., ‘‘Part A,’’ of
the Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (g)(1) through (3) of this AD.
Repeat thereafter at intervals not to exceed
200 FH or 12 months, whichever occurs first.
E:\FR\FM\14JNP1.SGM
14JNP1
31456
Federal Register / Vol. 86, No. 112 / Monday, June 14, 2021 / Proposed Rules
(1) For airplanes having S/N 5301 through
5665 inclusive: Bombardier Service Bulletin
604–32–030, dated June 30, 2020.
(2) For airplanes having S/N 5701 through
5988 inclusive: Bombardier Service Bulletin
605–32–007, dated June 30, 2020.
(3) For airplanes having S/N 6050 through
6999 inclusive: Bombardier Service Bulletin
650–32–004, dated June 30, 2020.
lotter on DSK11XQN23PROD with PROPOSALS1
(h) Repetitive Detailed Visual Inspections
(DVI)
At the applicable compliance time
specified in paragraphs (h)(1) through (3) of
this AD, perform the DVI for cracking and
damage of the LH and RH MLG shock strut
lower pins having part number (P/N) 19146–
3, in accordance with paragraph 2.C., ‘‘Part
B,’’ of the Accomplishment Instructions of
the applicable service bulletin, as specified
in paragraphs (g)(1) through (3) of this AD.
Repeat thereafter at intervals not to exceed
400 FH or 24 months, whichever occurs first.
If the DVI coincides with a non-destructive
testing (NDT) inspection required by
paragraph (i) of this AD, the NDT inspection
supersedes the DVI for that interval only. If
the accumulated flight cycles (FC) of the
MLG shock strut lower pin are not known,
use the related MLG assembly accumulated
FC to determine when to accomplish the
actions required by this paragraph.
(1) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD and on
which an MLG shock strut lower pin has
accumulated fewer than 600 total FC on the
pin as of the effective date of this AD: Before
the accumulation of 750 total FC on the pin.
(2) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD and on
which an MLG shock strut lower pin has
accumulated 600 total FC or more on the pin
as of the effective date of this AD: Within 150
FC after the effective date of this AD.
(3) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued after the
effective date of this AD: Before the
accumulation of 750 total FC.
(i) Repetitive NDT Inspection
At the applicable compliance time
specified in paragraphs (i)(1) through (4) of
this AD: Perform the NDT for cracking and
damage of the LH and RH MLG shock strut
lower pins having P/N 19146–3, in
accordance with paragraph 2.D., ‘‘Part C,’’ of
the Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (g)(1) through (3) of this AD.
Repeat thereafter at intervals not to exceed
900 FC. If the accumulated FC of the MLG
shock strut lower pin is not known, use the
related MLG assembly accumulated FC to
determine when to accomplish the actions
required by this paragraph.
(1) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD and on
which an MLG shock strut lower pin has
accumulated fewer than 1,200 total FC on the
VerDate Sep<11>2014
16:49 Jun 11, 2021
Jkt 253001
pin as of the effective date of this AD: Before
the accumulation of 1,500 total FC on the
pin.
(2) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD and on
which an MLG shock strut lower pin has
accumulated 1,200 total FC or more but fewer
than 2,000 total FC on the pin as of the
effective date of this AD: Within 300 FC after
the effective date of this AD, or before the
accumulation of 2,200 total FC on the pin,
whichever occurs first.
(3) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued on or
before the effective date of this AD and on
which an MLG shock strut lower pin that has
accumulated 2,000 total FC or more on the
pin as of the effective date of this AD: Within
200 FC after the effective date of this AD.
(4) For airplanes with an original
airworthiness certificate or original export
certificate of airworthiness issued after the
effective date of this AD: Before the
accumulation of 1,500 total FC.
(j) Replacement
If, during any inspection required by this
AD, any crack or damage of the MLG shock
strut lower pin is detected, before further
flight, replace the affected MLG shock strut
lower pin with a new part in accordance with
paragraph 2.E., ‘‘Part D,’’ of the
Accomplishment Instructions of the
applicable service bulletin, as specified in
paragraphs (g)(1) through (3) of this AD.
(k) 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 Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) TCCA AD
CF–2020–54R1, dated December 23, 2020, for
related information. This MCAI may be
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
found in the AD docket on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2021–0462.
(2) For more information about this AD,
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-nyacocos@faa.gov.
(3) For service information identified in
this AD, contact Bombardier, Inc., 200 CoˆteVertu 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.
Issued on June 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–12351 Filed 6–11–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
33 CFR Part 165
[Docket Number USCG–2021–0135]
RIN 1625–AA00
Safety Zones; Fireworks Displays, Air
Shows and Swim Events in Captain of
the Port Long Island Sound Zone
Coast Guard, DHS.
Notice of proposed rulemaking.
AGENCY:
ACTION:
The Coast Guard is proposing
to add one safety zone for the Dolan
Family Labor Day Fireworks event on
Oyster Bay, NY, and remove six other
annual recurring marine events in Coast
Guard Sector Long Island Sound’s
Captain of the Port Zone. This proposed
rule is intended to expedite public
information and to ensure the protection
of the maritime public and event
participants from the hazards associated
with certain marine events. When
enforced, the safety zones would restrict
vessels from transiting the regulated
area during annually recurring events.
We invite your comments on this
proposed rulemaking.
DATES: Comments and related material
must be received by the Coast Guard on
or before July 14, 2021.
SUMMARY:
E:\FR\FM\14JNP1.SGM
14JNP1
]]>Agencies
[Federal Register Volume 86, Number 112 (Monday, June 14, 2021)]
[Proposed Rules]
[Pages 31453-31456]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-12351]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0462; Project Identifier MCAI-2020-01714-T]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 31454]]
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier, Inc., CL-600-2B16 (604 Variant) airplanes. This
proposed AD was prompted by multiple reports of cracking of the main
landing gear (MLG) shock strut lower pin. This proposed AD would
require 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
proposing this AD to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by July 29,
2021.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
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 NPRM, contact
Bombardier, Inc., 200 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec
H4S 2A3, Canada; North America toll-free telephone 1-866-538-1247 or
direct-dial telephone 1-514-855-2999; email [email protected];
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.
Examining the AD Docket
You may examine the AD docket 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 NPRM, any comments
received, and other information. The street address for Docket
Operations is listed above.
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 [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-0462; Project Identifier
MCAI-2020-01714-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
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 [email protected]. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
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., 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.
This proposed AD 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
anti-rotation tang. Inadequate lubrication aggravates the condition.
The FAA is proposing 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.
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.
FAA's Determination
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to the FAA's bilateral agreement with the State of Design Authority,
the FAA has been notified of the unsafe condition
[[Page 31455]]
described in the MCAI and service information referenced above. The FAA
is proposing this AD because the FAA evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop on other products of the same type design.
Proposed AD Requirements in This NPRM
This proposed AD would require accomplishing the actions specified
in the service information already described.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 433 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
7 work-hours x $85 per hour = $595........................... $0 $595 $257,635
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated costs of on-condition actions
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510.... $2,435 $2,945
------------------------------------------------------------------------
The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some or all of the costs of
this proposed AD may be covered under warranty, thereby reducing the
cost impact on affected operators.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
Bombardier, Inc.: Docket No. FAA-2021-0462; Project Identifier MCAI-
2020-01714-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by July 29, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Bombardier, Inc., Model CL-600-2B16 (604
Variant) airplanes, serial numbers (S/N) 5301 through 5665
inclusive, 5701 through 5988 inclusive, and 6050 through 6999
inclusive, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Unsafe Condition
This AD was prompted by multiple reports of cracking of the main
landing gear (MLG) shock strut lower pin. 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.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Lubrication
Within 200 flight hours (FH) or 12 months after the effective
date of this AD, whichever occurs first, lubricate the left-hand
(LH) and right-hand (RH) MLG shock strut lower pins having part
number (P/N) 19146-3, in accordance with paragraph 2.B., ``Part A,''
of the Accomplishment Instructions of the applicable service
bulletin, as specified in paragraphs (g)(1) through (3) of this AD.
Repeat thereafter at intervals not to exceed 200 FH or 12 months,
whichever occurs first.
[[Page 31456]]
(1) For airplanes having S/N 5301 through 5665 inclusive:
Bombardier Service Bulletin 604-32-030, dated June 30, 2020.
(2) For airplanes having S/N 5701 through 5988 inclusive:
Bombardier Service Bulletin 605-32-007, dated June 30, 2020.
(3) For airplanes having S/N 6050 through 6999 inclusive:
Bombardier Service Bulletin 650-32-004, dated June 30, 2020.
(h) Repetitive Detailed Visual Inspections (DVI)
At the applicable compliance time specified in paragraphs (h)(1)
through (3) of this AD, perform the DVI for cracking and damage of
the LH and RH MLG shock strut lower pins having part number (P/N)
19146-3, in accordance with paragraph 2.C., ``Part B,'' of the
Accomplishment Instructions of the applicable service bulletin, as
specified in paragraphs (g)(1) through (3) of this AD. Repeat
thereafter at intervals not to exceed 400 FH or 24 months, whichever
occurs first. If the DVI coincides with a non-destructive testing
(NDT) inspection required by paragraph (i) of this AD, the NDT
inspection supersedes the DVI for that interval only. If the
accumulated flight cycles (FC) of the MLG shock strut lower pin are
not known, use the related MLG assembly accumulated FC to determine
when to accomplish the actions required by this paragraph.
(1) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before the
effective date of this AD and on which an MLG shock strut lower pin
has accumulated fewer than 600 total FC on the pin as of the
effective date of this AD: Before the accumulation of 750 total FC
on the pin.
(2) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before the
effective date of this AD and on which an MLG shock strut lower pin
has accumulated 600 total FC or more on the pin as of the effective
date of this AD: Within 150 FC after the effective date of this AD.
(3) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued after the
effective date of this AD: Before the accumulation of 750 total FC.
(i) Repetitive NDT Inspection
At the applicable compliance time specified in paragraphs (i)(1)
through (4) of this AD: Perform the NDT for cracking and damage of
the LH and RH MLG shock strut lower pins having P/N 19146-3, in
accordance with paragraph 2.D., ``Part C,'' of the Accomplishment
Instructions of the applicable service bulletin, as specified in
paragraphs (g)(1) through (3) of this AD. Repeat thereafter at
intervals not to exceed 900 FC. If the accumulated FC of the MLG
shock strut lower pin is not known, use the related MLG assembly
accumulated FC to determine when to accomplish the actions required
by this paragraph.
(1) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before the
effective date of this AD and on which an MLG shock strut lower pin
has accumulated fewer than 1,200 total FC on the pin as of the
effective date of this AD: Before the accumulation of 1,500 total FC
on the pin.
(2) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before the
effective date of this AD and on which an MLG shock strut lower pin
has accumulated 1,200 total FC or more but fewer than 2,000 total FC
on the pin as of the effective date of this AD: Within 300 FC after
the effective date of this AD, or before the accumulation of 2,200
total FC on the pin, whichever occurs first.
(3) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued on or before the
effective date of this AD and on which an MLG shock strut lower pin
that has accumulated 2,000 total FC or more on the pin as of the
effective date of this AD: Within 200 FC after the effective date of
this AD.
(4) For airplanes with an original airworthiness certificate or
original export certificate of airworthiness issued after the
effective date of this AD: Before the accumulation of 1,500 total
FC.
(j) Replacement
If, during any inspection required by this AD, any crack or
damage of the MLG shock strut lower pin is detected, before further
flight, replace the affected MLG shock strut lower pin with a new
part in accordance with paragraph 2.E., ``Part D,'' of the
Accomplishment Instructions of the applicable service bulletin, as
specified in paragraphs (g)(1) through (3) of this AD.
(k) 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
Bombardier, Inc.'s TCCA Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) TCCA AD CF-2020-54R1, dated December 23, 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-2021-0462.
(2) For more information about this AD, 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
[email protected].
(3) For service information identified in this AD, contact
Bombardier, Inc., 200 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 2A3, Canada; North America toll-free telephone 1-
866-538-1247 or direct-dial telephone 1-514-855-2999; email
[email protected]; 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.
Issued on June 8, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-12351 Filed 6-11-21; 8:45 am]
BILLING CODE 4910-13-P
