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2020-12-15 BOMBARDIER, INC.: Amendment 39-19924; Docket No. FAA-2020-0575; Product Identifier 2020-NM-096-AD.
(a) EFFECTIVE DATE

    This AD becomes effective July 24, 2020.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This AD applies to Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11
    airplanes,  certificated in any category,  serial numbers 9810 through
    9838 inclusive, 9840 through 9842 inclusive,  9844 through 9846 inclu-
    sive, 9854 and 9855.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 36, Pneumatic.

(e) REASON

    This AD was  prompted by a  report that certain  safety valves at  the
    left- and right-hand sides of  the cabin pressure control system  were
    not installed correctly and that the trunnion nuts used to fasten  the
    V-band clamp were over torqued. The FAA is issuing this AD to  address
    incorrect installation of the safety valves and over-torqued  trunnion
    nuts,  which could  cause damage to  the safety valve flange and could
    result in pressure leakage or cabin depressurization at altitude.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) MEASUREMENT

    Before August 31, 2020,  measure the trunnion nut torque of the V-band
    clamps at the left-and right-hand sides of the cabin pressure  control
    system  safety  valves,  in  accordance  with  paragraphs  2.B.(1) and
    2.B.(2) of the Accomplishment  Instructions of the applicable  service
    information specified in  figure 1 to  paragraphs (g) and  (h) of this
    AD.

           FIGURE 1 TO PARAGRAPHS (G) AND (H)  SERVICE INFORMATION       
    ______________________________________________________________________
    FOR AIRPLANE MODEL             USE BOMBARDIER SERVICE BULLETIN 
    ______________________________________________________________________
    BD-700-1A10 airplanes           700-21-6009, Revision 02, dated
                                    March 31, 2020

    BD-700-1A11 airplanes           700-21-5009, Revision 02, dated
                                    March 31, 2020
    ______________________________________________________________________

(h) INSPECTION AND CORRECTIVE ACTIONS

    Based on the torque measurement required  by paragraph (g) of this AD,
    do the applicable actions specified in paragraph (h)(1) or (2) of this
    AD.

(1) For safety valves with a V-band clamp trunnion nut torque of less than
    80 lbf-in: Before further flight,  do a general visual inspection  for
    any cracking and deformation, in accordance with paragraph  2.B.(3)(a)
    of  the   Accomplishment  Instructions   of  the   applicable  service
    information specified in  figure 1 to  paragraphs (g) and  (h) of this
    AD.

(i) If no cracking and deformation is found  on the safety valve  and air-
    plane bulkhead  flange: Before  further flight,  re-torque the  V-band
    clamp trunnion  nut, in  accordance with  paragraph 2.B.(3)(b)  of the
    Accomplishment  Instructions  of  the  applicable  service information
    specified in figure 1 to paragraphs (g) and (h) of this AD.

(ii) If any cracking  or  deformation is found on the safety valve: Before
     further  flight,  replace the safety valve,  in accordance with para-
     graph 2.C. of the Accomplishment Instructions of the applicable serv-
     ice information specified  in figure 1 to paragraphs (g)  and  (h) of
     this AD.

(iii) If any cracking or deformation is found  on  the  airplane  bulkhead
      flange: Before further flight, repair 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.

(2) For safety valves with a V-band clamp trunnion nut torque of 80 lbf-in
    or higher: Before  further flight, do  a magnification inspection  for
    any cracking and deformation of the safety valve and airplane bulkhead
    flange area, in accordance  with paragraphs 2.B.(4)(a) and  2.B.(4)(b)
    of  the   Accomplishment  Instructions   of  the   applicable  service
    information specified in  figure 1 to  paragraphs (g) and  (h) of this
    AD.

(i) If no cracking and deformation is found  on the safety valve  and air-
    plane bulkhead flange,  do the actions specified  in paragraphs (h)(2)
    (i)(A) and (B) of this AD.

(A) Before  further  flight, re-install the safety valve and torque the V-
    band clamp trunnion  nut,  in accordance with paragraph 2.B.(4)(c)  of
    the Accomplishment Instructions of the applicable service  information
    specified in figure 1 to paragraphs (g) and (h) of this AD.

(B) Before August 31, 2021,  replace the safety valve,  in accordance with
    paragraph 2.C. of the Accomplishment Instructions  of  the  applicable
    service information specified in figure 1 to paragraphs (g) and (h) of
    this AD.

(ii) If any cracking  or  deformation is found on the safety valve: Before
     further flight,  replace the safety valve,  in accordance  with para-
     graph 2.C. of the Accomplishment Instructions of the applicable serv-
     ice information specified  in figure 1 to paragraphs (g)  and  (h) of
     this AD.

(iii) If any  cracking  or  deformation is found  on the airplane bulkhead
      flange: Before further flight, repair using a method approved by the
      Manager,  New York ACO Branch, FAA;  or TCCA;  or Bombardier, Inc.'s
      TCCA DAO. If approved by the DAO, the approval must include the DAO-
      authorized signature.

(i) CREDIT FOR PREVIOUS ACTIONS

    This paragraph provides credit for actions required  by paragraphs (g)
    and (h) of this AD,  if those actions were performed before the effec-
    tive date of this AD using the following service information.

(1) Bombardier Service Bulletin 700-21-5009,  dated  January 23, 2020; and
    Bombardier Service Bulletin 700-21-5009,  Revision 01, dated March 19,
    2020.

(2) Bombardier Service Bulletin 700-21-6009,  dated January 23, 2020;  and
    Bombardier Service Bulletin 700-21-6009,  Revision 01, dated March 19,
    2020.

(j) 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 District  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
    district office/certificate holding district 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 TCCA; or  Bombardier, Inc.'s TCCA DAO. If  approved by
    the DAO, the approval must include the DAO-authorized signature.

(k) RELATED INFORMATION

(1) Refer   to   Mandatory  Continuing  Airworthiness  Information  (MCAI)
    Canadian AD CF-2020-16,  dated May 15, 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-
    0575.

(2) For more information about this AD, contact Darren Gassetto, Aerospace
    Engineer, Mechanical Systems and Administrative Services Section, FAA,
    New York  ACO Branch,  1600 Stewart Avenue,  Suite  410,  Westbury, NY
    11590; telephone 516-228-7323; fax 516-794-5531; email 9-avs-nyaco-cos
    @faa.gov.

(l) 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 700-21-5009,  Revision 02, dated March 31,
    2020.

(ii) Bombardier Service Bulletin 700-21-6009, Revision 02, dated March 31,
     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
    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
    fedreg.legal@nara.gov,  or  go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on June 18, 2020.Gaetano A Sciortino, Deputy Director for Strategic
Initiatives,  Compliance & Airworthiness Division,  Aircraft Certification
Service.

FOR FURTHER INFORMATION CONTACT:   Darren  Gassetto,  Aerospace  Engineer,
Mechanical Systems and Administrative Services Section, FAA,  New York ACO
Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-
228-7323; 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-2020-0575; Product Identifier 2020-NM-096-AD; Amendment
39-19924; AD 2020-12-15]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes.
This AD was prompted by a report that certain safety valves at the
left- and right-hand sides of the cabin pressure control system were
not installed correctly and that the trunnion nuts used to fasten the
V-band clamp were over torqued. This AD requires a measurement of the
trunnion nut torque of the V-band clamp, an inspection of the safety
valve and airplane bulkhead flange area for any cracking and
deformations, and corrective actions, if necessary. The FAA is issuing
this AD to address the unsafe condition on these products.

DATES: This AD becomes effective July 24, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 24,
2020.
The FAA must receive comments on this AD by August 24, 2020.

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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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 ac.yul@aero.bombardier.com;
internet https://www.bombardier.com. You may view this referenced
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-2020-0575.

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-
0575; or in person at the Docket Operations office between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, any comments received, and other information. The
street address for the Docket Operations office is listed above.
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Darren Gassetto, Aerospace Engineer,
Mechanical Systems and Administrative Services Section, FAA, New York
ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7323; 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-2020-16, dated May 15,
2020 (referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for
certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes.
You may examine the MCAI on the internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2020-0575.
This AD was prompted by a report that certain safety valves at the
left- and right-hand sides of the cabin pressure control system were
not installed correctly and that the trunnion nuts used to fasten the
V-band clamp were over torqued. The FAA is issuing this AD to address
incorrect installation of the safety valves and over-torqued trunnion
nuts, which could cause damage to the safety valve flange and could
result in pressure leakage or cabin depressurization at altitude. See
the MCAI for additional background information.

Related Service Information Under 1 CFR Part 51

Bombardier has issued Service Bulletin 700-21-5009, Revision 02,
dated March 31, 2020; and Service Bulletin 700-21-6009, Revision 02,
dated March 31, 2020. This service information describes procedures for
a measurement of the trunnion nut torque of the V-band clamp at the
left- and right-hand sides of the cabin pressure control system safety
valves, a general visual or magnification inspection of the safety
valve and airplane bulkhead flange area for any cracking and
deformation, and corrective actions. The corrective actions include
replacement of the safety valve and repair of cracks on the airplane
bulkhead flange. These documents are distinct since they apply to
different airplane models.
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 our bilateral agreement with the State of Design Authority, the FAA
has been notified of the unsafe condition described in the MCAI and
service information referenced above. The FAA is issuing this AD
because the FAA evaluated all pertinent information and determined the
unsafe condition exists and is likely to exist or develop on other
products of the same type design.

Requirements of This AD

This AD requires accomplishing the actions specified in the service
information described previously.

Explanation of Compliance Time

In most ADs, we adopt a compliance time relative to the AD's
effective date. In this case, however, TCCA has already issued
regulations that require operators to measure the trunnion nut torque
of the V-band clamp to address the identified unsafe condition by a
certain date. Per the safety assessment of the design approval holder
and TCCA, the initial measurement of the trunnion nut torque of the V-
band clamp must be completed before August 31, 2020. In addition, TCCA
also requires operators to replace certain safety valves by that date.
To provide for coordinated implementation of TCCA's regulations and
this AD, we are using the same compliance date in this AD.

Differences Between This AD and the MCAI

Canadian AD CF-2020-16, dated May 15, 2020, requires an inspection
of the bulkhead flange but does not provide a corrective action. This
AD includes a corrective action as specified in paragraphs (h)(1)(iii)
and (h)(2)(B)(iii) of this AD.

FAA's Justification and Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of
this AD without providing an opportunity for public comments prior to
adoption. The FAA has found that the risk to the flying public
justifies waiving notice and comment prior to adoption of this rule
because incorrectly installed safety valves and over-torqued trunnion
nuts could cause damage to the safety valve flange and could result in
pressure leakage or cabin depressurization at altitude. Therefore, the
FAA finds good cause that notice and opportunity for prior public
comment are impracticable. In addition, for the reasons stated above,
the FAA finds that good cause exists for making this amendment
effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety, and the FAA did not precede it by notice and opportunity for
public comment. The FAA invites you to send any written relevant data,
views, or arguments about this AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2020-0575;
Product Identifier 2020-NM-096-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. The FAA will
consider all comments received by the closing date and may amend this
AD based on those comments.
The FAA will post all comments received, without change, to https://www.regulations.
gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact received about this AD.

Regulatory Flexibility Act (RFA)

The requirements of the RFA do not apply when an agency finds good
cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and
comment. Because the FAA has determined that it has good cause to adopt
this rule without notice and comment, RFA analysis is not required.

Costs of Compliance

The FAA estimates that this AD affects 17 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
2 work-hours x $85 per hour = $170
$0
$170
$2,890

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
3 work-hours x $85 per hour = $255
$5,070
$5,325

* The table does not include costs for the corrective action for the
bulkhead flange. The FAA has received no definitive data for the cost
of this corrective action.

According to the manufacturer, some or all of the parts costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected individuals. The FAA does not control warranty coverage for
affected individuals. As a result, the FAA has included all known costs
in our cost estimate.

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 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, and
(2) Will not affect intrastate aviation in Alaska.

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 (AD):