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2020-05-27 BOMBARDIER, INC.: Amendment 39-19877; Docket No. FAA-2019-0876; Product Identifier 2019-NM-070-AD.
(a) EFFECTIVE DATE

    This AD is effective May 7, 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 9001 through
    9844 inclusive, and 9998.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) REASON

    This AD was  prompted by a  report that cracking  was discovered in  a
    channel within a  structural support member  for the rudder  quadrant,
    rudder feel  unit assembly,  and environmental  control system  due to
    fatigue. The FAA is issuing this AD to address cracking in the  rudder
    quadrant   support   structure,   which   can   lead   to  progressive
    deterioration in the performance of the systems it supports, and could
    eventually lead to uncommanded rudder movement and bleed air leakage.

(f) COMPLIANCE

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

(g) INITIAL AND REPETITIVE INSPECTIONS

    For  airplanes that  have accumulated  fewer than  2,900 total  flight
    cycles as of  the effective date  of this AD,  and that have  not been
    modified as specified in paragraph  (i) of this AD: At  the applicable
    time specified in paragraph  (g)(1) or (2) of  this AD, do a  detailed
    visual inspection for cracking of the rudder quadrant box assembly, in
    accordance with paragraph 2.B.  of the Accomplishment Instructions  of
    the applicable service bulletin specified in figure 1 to paragraph (g)
    of  this AD.  Repeat  the  inspection thereafter  at intervals  not to
    exceed 1,000 flight cycles.

(1) For airplanes  that  have  accumulated  fewer  than 2,000 total flight
    cycles  as of  the effective  date of  this AD:  Inspect within  1,000
    flight cycles after the effective date of this AD.

(2) For airplanes that have accumulated 2,000 total flight cycles or more,
    but fewer than 2,900 total flight cycles,  as of the effective date of
    this AD:  Inspect within 100 flight cycles after the effective date of
    this AD.

        FIGURE 1 TO PARAGRAPH (G)  INSPECTION SERVICE INFORMATION        
    ______________________________________________________________________
         AIRPLANE MODEL                      SERVICE INFORMATION
    ______________________________________________________________________
    BD-700-1A10 airplanes having        Bombardier Service Bulletin
    serial numbers 9002 through         700-53-054, Basic Issue, dated
    9312 inclusive, 9314 through        October 1, 2018
    9380 inclusive, and 9384
    through 9429 inclusive

    BD-700-1A10 airplanes having        Bombardier Service Bulletin
    serial numbers 9313, 9381, and      700-53-6012, Basic Issue, dated
    9432 through 9844 inclusive         October 1, 2018

    BD-700-1A11 airplanes having        Bombardier Service Bulletin
    serial numbers 9127 through         700-1A11-53-029, Basic Issue,
    9383 inclusive, 9389 through        dated October 1, 2018
    9400 inclusive, 9404 through
    9431 inclusive, and 9998

    BD-700-1A11 airplanes having        Bombardier Service Bulletin
    serial numbers 9386, 9401, and      700-53-5013, Basic Issue, dated
    9445 through 9840 inclusive         October 1, 2018
    ______________________________________________________________________

(h) CORRECTIVE ACTIONS FOR INSPECTION FINDINGS

    If any cracking is found  during any inspection specified in paragraph
    (g) of this AD,  do the actions specified  in paragraph (i) of this AD
    at the applicable time specified  in paragraphs (h)(1) through (4)  of
    this AD.

(1) If any crack of 1.20 inch (30.48 mm) or longer is found on the forward
    (FWD) upper half rib:  Do the actions  within 100 flight cycles  after
    discovery of the crack.

(2) If any crack of 0.40 inch (10.16 mm)  or  longer  is  found on the AFT
    lower half rib,  do  the  actions  within 100 flight cycles after dis-
    covery of the crack.

(3) If any crack is found  on the left-hand (LH) channel  that  has  grown
    from  the  air  system's  support fitting  aft  fastener  hole  to the
    adjacent air  systems support  fitting fastener  hole (which  is 0.625
    inch (15.88 mm) from hole edge to hole edge) or longer, do the actions
    before further flight.

(4) If any crack is found  on the LH channel  that is less than 0.625 inch
    (15.88 mm) from hole edge to hole edge (which is the distance from the
    air system's  support fitting  aft fastener  hole to  the adjacent air
    system's  support fitting  fastener hole),  do the  actions within  50
    flight cycles after discovery of the crack.

(i) MODIFICATION OF THE RUDDER QUADRANT BOX ASSEMBLY

    At the applicable  time specified in  paragraph (i)(1) or  (2) of this
    AD, except as required by paragraph (h) of this AD: Modify the  rudder
    quadrant box assembly. The modification includes surface and bolt-hole
    eddy  current inspections  for cracking  of the  left-hand channel;  a
    detailed visual inspection  for cracking of  the forward and  aft half
    ribs  and  bottom  and  top  skins;  applicable  corrective   actions;
    replacement of the rudder quadrant box half ribs, air systems  support
    fitting, and LH channel; and  installation of new rudder quadrant  box
    back-up  fittings.  Do  the  modification  and  associated  actions in
    accordance with paragraph 2.B., 2.C., and 2.D., of the  Accomplishment
    Instructions of the applicable service bulletin specified in figure  2
    to paragraph  (i) of  this AD;  except, where  the applicable  service
    bulletin  specifies  to  contact  Bombardier  for  appropriate action,
    corrective actions must  be done before  further flight in  accordance
    with the procedures specified in paragraph (l)(2) of this AD.

(1) For airplanes that have accumulated 2,900 total flight cycles or fewer
    as of the effective  date of this AD,  do the required actions  before
    the accumulation  of 3,000  total flight  cycles, or  within 60 months
    after the effective date of this AD, whichever occurs first.

(2) For  airplanes  that  have  accumulated  more  than 2,900 total flight
    cycles as of the  effective date of this  AD, do the required  actions
    within 100 flight cycles or  12 months, whichever occurs first,  after
    the effective date of this AD.

        FIGURE 2 TO PARAGRAPH (I)  MODIFICATION SERVICE INFORMATION      
    ______________________________________________________________________
         AIRPLANE MODEL                      SERVICE INFORMATION
    ______________________________________________________________________
    BD-700-1A10 airplanes having        Bombardier Service Bulletin
    serial numbers 9002 through         700-53-052, Basic Issue, dated
    9312 inclusive, 9314 through        October 1, 2018
    9380 inclusive, and 9384
    through 9429 inclusive

    BD-700-1A10 airplanes having        Bombardier Service Bulletin
    serial numbers 9313, 9381, and      700-53-6010, Basic Issue, dated
    9432 through 9844 inclusive         October 1, 2018.

    BD-700-1A11 airplanes having        Bombardier Service Bulletin
    serial numbers 9127 through         700-1A11-53-027, Basic Issue,
    9383 inclusive, 9389 through        dated October 1, 2018
    9400 inclusive, 9404 through
    9431 inclusive, and 9998

    BD-700-1A11 airplanes having        Bombardier Service Bulletin
    serial numbers 9386, 9401, and      700-53-5011, Basic Issue, dated
    9445 through 9840 inclusive         October 1, 2018
    ______________________________________________________________________

(j) ALTERNATIVE MODIFICATION

    Airplanes that  have been  modified as  specified by  any modification
    identified in paragraphs (j)(1) through (4) of this AD (which are  not
    required by this AD), meet the requirements specified in paragraph (i)
    of this AD.

(1) Bombardier Repair Modification R700T400669, Revision C,  dated January
    19, 2018,  or Bombardier Repair Modification R700T400669,  Revision G,
    dated May 30, 2018.

(2) Bombardier In-Service Modification IS700-53-0024,  Revision  A,  dated
    July 24, 2018.

(3) Bombardier Service Request for Product Support Action(SRPSA) 000220372

(4) Bombardier Service Request for Product Support Action(SRPSA) 000271526

(k) TERMINATING ACTION FOR REPETITIVE INSPECTIONS

    Accomplishing the actions in paragraph (i) or (j)  of  this  AD termi-
    nates all of the requirements in paragraph (g) of this AD.

(l) 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
    corrective  actions   from  a   manufacturer,  the   action  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.

(m) RELATED INFORMATION

(1) Refer   to   Mandatory  Continuing  Airworthiness  Information  (MCAI)
    Canadian AD CF-2019-11, dated March 22, 2019, 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-2019-
    0876.

(2) For more information about this AD,  contact Andrea Jimenez, Aerospace
    Engineer,  Airframe and Mechanical Systems 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.

(n) 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 700-53-052, Basic Issue,  dated October 1,
    2018.

(ii) Bombardier Service Bulletin 700-53-054, Basic Issue, dated October 1,
     2018.

(iii) Bombardier Service Bulletin 700-53-5011,  Basic Issue, dated October
      1, 2018

(iv) Bombardier Service Bulletin 700-53-5013,  Basic Issue,  dated October
     1, 2018.

(v) Bombardier Service Bulletin 700-53-6010, Basic Issue, dated October 1,
    2018.

(vi) Bombardier Service Bulletin 700-53-6012,  Basic Issue,  dated October
     1, 2018.

(vii) Bombardier  Service Bulletin  700-1A11-53-027,  Basic  Issue,  dated
      October 1, 2018.

(viii) Bombardier  Service Bulletin 700-1A11-53-029,  Basic  Issue,  dated
       October 1, 2018.

(3) For  service information identified  in this AD,  contact  Bombardier,
    Inc.,  400 Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; tele-
    phone 514-855-5000;  fax 514-855-7401;  email thd.crj@aero.bombardier.
    com; internet https://www.bombardier.com.

(4) You may view this service information at the FAA,  Transport Standards
    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 March 10, 2020. Lance T. Gant, Director, Compliance & Airworthi-
ness Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Andrea Jimenez,  Aerospace Engineer, Air-
frame and Mechanical Systems 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-2019-0876; Product Identifier 2019-NM-070-AD; Amendment
39-19877; AD 2020-05-27]
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 BD-700-1A10 and BD-700-1A11 airplanes.
This AD was prompted by a report that cracking was discovered in a
channel within a structural support member for the rudder quadrant,
rudder feel unit assembly, and environmental control system due to
fatigue. This AD requires repetitive inspections of the rudder quadrant
box assembly for any cracking, and modification of the rudder quadrant
box assembly. The FAA issuing this AD to address the unsafe condition
on these products.

DATES: This AD is effective May 7, 2020.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 7, 2020.

ADDRESSES: For service information identified in this final rule,
contact Bombardier, Inc., 400 Cote-Vertu Road West, Dorval,
Quebec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; internet https://www.bombardier.
com. You may view this service information at the FAA,
Transport Standards 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-2019-0876.

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-2019-
0876; 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, the regulatory evaluation, 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 Mechanical Systems 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-2019-11, dated March
22, 2019 (also referred to 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 in the AD docket on the internet at https://www.
regulations.gov by searching for and locating Docket No. FAA-2019-0876.
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 BD-700-1A10 and BD-700-1A11 airplanes. The NPRM published
in the Federal Register on December 16, 2019 (84 FR 68370). The NPRM
was prompted by a report that cracking was discovered in a channel
within a structural support member for the rudder quadrant, rudder feel
unit assembly, and environmental control system due to fatigue. The
NPRM proposed to require repetitive inspections of the rudder quadrant
box assembly for any cracking, and modification of the rudder quadrant
box assembly. The FAA is issuing this AD to address cracking in the
rudder quadrant support structure, which can lead to progressive
deterioration in the performance of the systems it supports, and could
eventually lead to uncommanded rudder movement and bleed air leakage.
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 has issued the following service information.
Bombardier Service Bulletin 700-53-054, Basic Issue, dated
October 1, 2018.
Bombardier Service Bulletin 700-53-5013, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-53-6012, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-1A11-53-029, Basic Issue,
dated October 1, 2018.
This service information describes procedures for repetitive
detailed visual inspections of the rudder quadrant box assembly for any
cracking. These documents are distinct since they apply to different
airplane models.
Bombardier also issued the following service information:
Bombardier Service Bulletin 700-53-052, Basic Issue, dated
October 1, 2018.
Bombardier Service Bulletin 700-53-6010, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-1A11-53-027, Basic Issue,
dated October 1, 2018.
Bombardier Service Bulletin 700-53-5011, Basic Issue,
dated October 1, 2018.
This service information describes procedures for modification of
the rudder quadrant box assembly. The modification includes surface and
bolt-hole eddy current inspections for cracking of the left-hand (LH)
channel; a detailed visual inspection for cracking of the forward and
aft half ribs and bottom and top skins; replacement of the rudder
quadrant box half ribs, air systems support fitting, and LH channel;
and installation of new rudder quadrant box back-up fittings. 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.

Costs of Compliance

The FAA estimates that this AD affects 123 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 per inspection cycle $0 $170 per inspection cycle $20,910 per inspection cycle

The FAA estimates the following costs to do any necessary on-
condition action 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 this on-condition action:

Estimated Costs of On-Condition Action

Labor cost
Parts cost
Cost per product
46 work-hours x $85 per hour = $3,910
$355
$4,265

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 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 (AD):