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2021-01-01 MHI RJ AVIATION ULC (TYPE CERTIFICATE PREVIOUSLY HELD BY BOMBARDIER, INC.): Amendment 39-21377; Docket No. FAA-2020-0691; Product Identifier 2020-NM-064-AD.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective March 30, 2021.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies  to MHI RJ  Aviation ULC (type  certificate previously
    held by Bombardier, Inc.) Model CL-600-2B19 (Regional Jet Series 100 &
    440)  airplanes, certificated  in any  category, serial  numbers  7003
    through 8999 inclusive.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 32, Landing gear.

(e) REASON

    This AD was prompted by evidence that a revised structural life  limit
    of some components of the nose landing gear (NLG) and/or main  landing
    gear (MLG) was not implemented during repair. The FAA is issuing  this
    AD to  address structural  life limits  that are  lower than  the life
    limits published in the Maintenance Requirements Manual (MRM), Part 2.
    This condition, if  not corrected, could  lead to the  collapse of the
    affected NLG  and/or MLG,  possibly resulting  in airplane  damage and
    injury to the occupants.

(f) COMPLIANCE

    Comply  with this  AD within  the compliance  times  specified, unless
    already done.

(g) VERIFICATION OF AIRPLANE OR TECHNICAL RECORDS

    Within  6  months from  the  effective date  of  this AD:  Verify  the
    airplane or technical records to determine if an NLG or MLG  component
    listed in Table  1 or Table  2 of Bombardier  Service Bulletin 601R-32
    -112, dated November 11, 2019,  is installed on the airplane.  If this
    verification determines that an  affected component listed in  Table 1
    or Table 2 of Bombardier Service Bulletin 601R-32-112, dated  November
    11, 2019, is installed on the airplane, perform the actions  specified
    in paragraph (h) or (i) of this AD, as applicable.

(h) INCORPORATION  OF  THE  STRUCTURAL  DEVIATION INSPECTION  REQUIREMENTS
    (SDIR) LIFE LIMIT INTO THE EXISTING SDIR AIRPLANE DOCUMENT

    If the total flight cycles of  the component is less than the  revised
    SDIR life limit  identified in figure  1 to paragraph  (h) of this  AD
    minus  2,000  flight cycles:  Within  12 months  after  completing the
    actions  specified  in  paragraph  (g)  of  this  AD,  incorporate the
    applicable  revised  life limit  of  the affected  component  into the
    existing SDIR airplane document as specified in figure 1 to  paragraph
    (h) of this AD.

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 1 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 2 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 3 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 4 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 5 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 6 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 7 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 8 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 9 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 10 OF 11)

                                ILLUSTRATION
      FIGURE 1 TO PARAGRAPH (h)  REVISED SDIR LIFE LIMITS (SHEET 11 OF 11)

(i) REPLACEMENT OF REPAIRED NLG AND/OR MLG COMPONENT

    If the total flight cycles of  the component is equal to or  more than
    the  applicable  revised SDIR  life  limit specified  in  figure 1  to
    paragraph (h) of this AD  minus 2,000 flight cycles: Within  12 months
    or 2,000 flight cycles,  whichever occurs first, after  completing the
    actions specified in  paragraph (g) of  this AD, replace  the affected
    component with a serviceable component.

(j) PARTS INSTALLATION PROHIBITION

    As  of  the effective  date  of this  AD,  no person  may  install any
    component listed in Table 1 or Table 2 of Bombardier Service  Bulletin
    601R-32-112, dated November  11, 2019, on  any airplane without  first
    incorporating the actions  specified in paragraph  (h) or (i)  of this
    AD, as applicable.

(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
    local 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 local 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 MHI  RJ
    Aviation ULC'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) Canad-
    ian AD CF-2020-09, dated April 7, 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-2020-0691.

(2) For more information about this AD, contact Andrea Jimenez,  Aerospace
    Engineer, Airframe and Propulsion  Section, FAA, New York  ACO Branch,
    1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone  516-228
    -7330; 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 601R-32-112, dated November 11, 2019.

(ii) [Reserved]

(3) For service information identified in this AD, contact MHI RJ Aviation
    ULC,  12655  Henri-Fabre  Blvd.,  Mirabel,  Quebec,  J7N  1E1  Canada;
    Widebody Customer  Response Center  North America  toll-free telephone
    +1-844-272-2720 or direct-dial  telephone +1-514-855-8500; fax  +1-514
    -855-8501; email thd.crj@mhirj.com; internet https://mhirj.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 refer-
    ence at the National  Archives and Records Administration  (NARA). For
    information  on  the  availability of  this  material  at NARA,  email
    fedreg.legal@nara.gov,  or  go  to:   https://www.archives.gov/federal
    -register/cfr/ibr-locations.html.

Issued  on  December  28,  2020. Lance  T.  Gant,  Director,  Compliance &
Airworthiness Division, Aircraft Certification Service.

FOR  FURTHER  INFORMATION  CONTACT:  Andrea  Jimenez,  Aerospace Engineer,
Airframe and Propulsion  Section, FAA, New  York ACO Branch,  1600 Stewart
Avenue, Suite 410, Westbury,  NY 11590; telephone  516-228-7330; 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-2020-0691; Product Identifier 2020-NM-064-AD; Amendment
39-21377; AD 2021-01-01]
RIN 2120-AA64

Airworthiness Directives; MHI RJ Aviation ULC (Type Certificate
Previously Held by 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 MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100
& 440) airplanes. This AD was prompted by evidence that a revised
structural life limit of some components of the nose landing gear (NLG)
and/or main landing gear (MLG) was not implemented during repair. This
AD requires verifying that the affected components are installed on the
airplane, revising the structural life limits in the existing
structural deviation inspection requirements (SDIR) airplane document,
and replacing affected components if necessary. The FAA is issuing this
AD to address the unsafe condition on these products.

DATES: This AD is effective March 30, 2021.

The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 30, 2021.

ADDRESSES: For service information identified in this final rule,
contact MHI RJ Aviation ULC, 12655 Henri-Fabre Blvd., Mirabel, Quebec J7N
1E1, Canada; Widebody Customer Response Center North America toll-free
telephone +1-844-272-2720 or direct-dial telephone +1-514-855-8500; fax
+1-514-855-8501; email thd.crj@mhirj.com; internet https://mhirj.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-2020-0691.

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-2020-
0691; 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: Andrea Jimenez, Aerospace Engineer,
Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7330; fax 516-
794-5531; email 9-avs-nyaco-cos@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion


Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2020-09, dated April 7,
2020 (also referred to as the Mandatory Continuing Airworthiness
Information, or the MCAI), to correct an unsafe condition for certain
MHI RJ Aviation ULC Model CL-600-2B19 (Regional Jet Series 100 & 440)
airplanes. You may examine the MCAI in the AD docket on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2020-0691.

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain MHI RJ Aviation
ULC Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The
NPRM published in the Federal Register on October 5, 2020 (85 FR
62626). The NPRM was prompted by evidence that a revised structural
life limit of some components of the NLG and/or MLG was not implemented
during repair. The NPRM proposed to require verifying that the affected
components are installed on the airplane, revising the structural life
limits in the existing SDIR airplane document, and replacing affected
components if necessary. The FAA is issuing this AD to address
structural life limits that are lower than the life limit published in
the Maintenance Requirements Manual (MRM), Part 2. This condition, if
not corrected, could lead to the collapse of the affected NLG and/or
MLG, possibly resulting in airplane damage and injury to the occupants.
See the MCAI for additional background information.

Comments


The FAA gave the public the opportunity to participate in
developing this final rule. The FAA has considered the comment
received. Air Line Pilots Association, International (ALPA) stated that
it supports the NPRM.

Additional Change Made to This AD


This AD has been revised to provide the revised structural life
limits in figure 1 to paragraph (h) of this AD instead of referencing
the individual repair engineering orders (REOs) in paragraph (h) of
this AD. The REOs did not meet the Office of the Federal Register's
criteria for incorporation by reference.

Conclusion


The FAA reviewed the relevant data, considered the comment
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and 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.

The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final rule.

Related Service Information Under 1 CFR Part 51


Bombardier has issued Service Bulletin 601R-32-112, dated November
11, 2019. This service information describes procedures for verifying
that affected components are installed on the airplane, revising the
structural life limits in the existing SDIR airplane document, and
replacing affected parts if necessary. 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 456 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
Up to 143 work-hours x $85 per hour = Up to $12,155. Up to $103,114 Up to $115,269 Up to $52,562,664.

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: