Document ID: FAA-2021-0462-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier, Inc., Airplanes
Posted Date: 2021-10-14T04:00Z

[Federal Register Volume 86, Number 196 (Thursday, October 14, 2021)]
[Rules and Regulations]
[Pages 57033-57035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-22295]

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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; 
Amendment 39-21751; AD 2021-20-13]
RIN 2120-AA64

Airworthiness Directives; 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 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 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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0462.

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 [email protected].

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 anti-rotation tang. 
Inadequate lubrication 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:

[[Page 57034]]

                                      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
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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 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2021-20-13 Bombardier, Inc.: Amendment 39-21751; Docket No. FAA-
2021-0462; Project Identifier MCAI-2020-01714-T.

(a) Effective Date

    This airworthiness directive (AD) is effective November 18, 
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.
    (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.

[[Page 57035]]

    (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 inspection 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].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Bombardier Service Bulletin 604-32-030, dated June 30, 2020.
    (ii) Bombardier Service Bulletin 605-32-007, dated June 30, 
2020.
    (iii) Bombardier Service Bulletin 650-32-004, dated June 30, 
2020.
    (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.
    (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.

    Issued on September 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-22295 Filed 10-13-21; 8:45 am]
BILLING CODE 4910-13-P