Proposed Rule2021-12351
Airworthiness Directives; Bombardier, Inc., Airplanes
Primary source
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Published
June 14, 2021
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 86 Issue 112 (Monday, June 14, 2021)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2021-12351]
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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).
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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:
<bullet> Federal eRulemaking Portal: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> 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 <a href="/cdn-cgi/l/email-protection#b9d8da97c0ccd5f9d8dccbd697dbd6d4dbd8cbddd0dccb97dad6d4"><span class="__cf_email__" data-cfemail="3051531e49455c705155425f1e525f5d525142545955421e535f5d">[email protected]</span></a>;
internet <a href="https://www.bombardier.com">https://www.bombardier.com</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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 <a href="/cdn-cgi/l/email-protection#063f2b6770752b687f6765692b6569754660676728616970"><span class="__cf_email__" data-cfemail="99a0b4f8efeab4f7e0f8faf6b4faf6ead9fff8f8b7fef6ef">[email protected]</span></a>.
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
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, 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 <a href="/cdn-cgi/l/email-protection#40796d2136336d2e3921232f6d232f33002621216e272f36"><span class="__cf_email__" data-cfemail="11283c7067623c7f6870727e3c727e62517770703f767e67">[email protected]</span></a>. 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
<a href="https://www.regulations.gov">https://www.regulations.gov</a> 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:
<bullet> Service Bulletin 604-32-030, dated June 30, 2020.
<bullet> Service Bulletin 605-32-007, dated June 30, 2020.
<bullet> 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
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Cost per Cost on U.S.
Labor cost Parts cost product operators
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7 work-hours x $85 per hour = $595........................... $0 $595 $257,635
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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
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Cost per
Labor cost Parts cost product
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6 work-hours x $85 per hour = $510.... $2,435 $2,945
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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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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
<a href="/cdn-cgi/l/email-protection#073e2a6671742a697e6664682a6468744761666629606871"><span class="__cf_email__" data-cfemail="182135796e6b357661797b77357b776b587e7979367f776e">[email protected]</span></a>.
(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
<a href="/cdn-cgi/l/email-protection#9dfcfeb3e4e8f1ddfcf8eff2b3fff2f0fffceff9f4f8efb3fef2f0"><span class="__cf_email__" data-cfemail="660705481f130a26070314094804090b040714020f03144805090b">[email protected]</span></a>; internet <a href="https://www.bombardier.com">https://www.bombardier.com</a>. 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
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