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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 land-
    ing 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 al-
    ready 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 Serv-
    ice Bulletin 604-32-030, dated June 30, 2020.

(2) For airplanes having S/N 5701 through 5988 inclusive: Bombardier Serv-
    ice Bulletin 605-32-007, dated June 30, 2020.

(3) For airplanes having S/N 6050 through 6999 inclusive: Bombardier Serv-
    ice 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 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 9-avs-nyaco-cos
    @faa.gov.

(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 Cote-Vertu Road West, Dorval,  Quebec 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.

(4) You may view this service information at the FAA,  Airworthiness Prod-
    ucts 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 refer-
    ence at the National Archives and Records Administration  (NARA).  For
    information on the availability of this material  at  NARA,  email fr.
    inspection@nara.gov,   or   go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on September 21, 2021.  Lance T. Gant,  Director, Compliance & Air-
worthiness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT:Chirayu Gupta, Aerospace Engineer, Mechan-
ical Systems and Administrative Services Section, FAA, New York ACO Branch
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7300
fax 516-794-5531; email 9-avs-nyaco-cos@faa.gov.
PREAMBLE 

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.

-----------------------------------------------------------------------

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 Cote-Vertu Road West, Dorval,
Quebec H4S 2A3, Canada; North America toll-free telephone 1-866-
538-1247 or direct-dial telephone 1-514-855-2999; email
ac.yul@aero.bombardier.com; internet https://www.bombardier.com. You
may view this service information at the FAA, Airworthiness Products
Section, Operational Safety Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call 206-231-3195. It is also available on the internet at https://www.regulations.
gov by 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 9-avs-nyaco-cos@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued TCCA AD CF-2020-54R1, dated December
23, 2020 (TCCA AD CF-2020-54R1) (also referred to after this as the
Mandatory Continuing Airworthiness Information, or the MCAI), to
correct an unsafe condition for certain Bombardier, Inc., Model CL-600-
2B16 (604 Variant) airplanes. You may examine the MCAI in the AD docket
at https://www.regulations.gov by searching for and locating Docket No.
FAA-2021-0462.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Bombardier,
Inc., Model CL-600-2B16 (604 Variant) airplanes. The NPRM published in
the Federal Register on June 14, 2021 (86 FR 31453). The NPRM was
prompted by multiple reports of cracking of the MLG shock strut lower
pin part number (P/N) 19146-3. The subsequent investigation concluded
that the friction torque when the shock strut is under compression
loading, causes the pin anti-rotation tangs to become loaded beyond
their load carrying capability. This overload condition can result in
pin fracture originating at the base of the pin 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:

Estimated Costs for Required Actions

Labor cost
Parts cost
Cost per product
Cost on U.S. 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

Labor cost
Parts cost
Cost per 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 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

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]

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