[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]


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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:
     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
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                                                                                    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
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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