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PROPOSED AD BOMBARDIER, INC.: Docket No. FAA-2019-0876; Product Identifier 2019-NM-070-AD.
(a) COMMENTS DUE DATE

    The FAA must receive comments by January 30, 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
    already 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, dated October 1,
    9312 inclusive, 9314 through 9380       2018
    inclusive, and 9384 through 9429
    inclusive

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

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

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

(h) CORRECTIVE ACTIONS FOR INSPECTION FINDINGS

    If any cracking is found during the 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 discov-
    ery 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 adja-
    cent 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 be-
    fore 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 9312        700-53-052, dated October 1,
    inclusive, 9314 through 9380            2018
    inclusive, and 9384 through 9429
    inclusive

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

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

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

(j) ALTERNATIVE MODIFICATION

    Airplanes that have been modified  as specified  by  any  modification
    identified in paragraph (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  Canada'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 Airworthiness Directive 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.

(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.  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.

Issued  in  Des Moines, Washington,  on November 21, 2019.  Dorr Anderson,
Acting Director, System Oversight Division, Aircraft Certification Service

DATES: The FAA must receive comments  on this proposed AD  by  January 30,
2020.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0876; Product Identifier 2019-NM-070-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11
airplanes. This proposed 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 proposed AD would require repetitive
inspections of the rudder quadrant box assembly for any cracking, and
modification of the rudder quadrant box assembly. The FAA is proposing
this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by January 30,
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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this NPRM, 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.

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 NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.

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:

Comments Invited

The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include "Docket No. FAA-2019-0876;
Product Identifier 2019-NM-070-AD" at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of 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 NPRM.

Discussion

Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian Airworthiness Directive CF-
2019-11, dated March 22, 2019 (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 in the AD docket on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0876.

This proposed 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 proposing 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.

Related Service Information Under 1 CFR Part 51

Bombardier has issued the following service information.

Bombardier Service Bulletin 700-53-054, dated October 1,
2018.

Bombardier Service Bulletin 700-53-5013, dated October 1,
2018.

Bombardier Service Bulletin 700-53-6012, dated October 1,
2018.

Bombardier Service Bulletin 700-1A11-53-029, 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, dated October 1,
2018.

Bombardier Service Bulletin 700-53-6010, dated October 1,
2018.

Bombardier Service Bulletin 700-1A11-53-027, dated October
1, 2018.

Bombardier Service Bulletin 700-53-5011, 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.

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 a 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 proposing this AD
because the agency evaluated all the relevant information and
determined the unsafe condition described previously is likely to exist
or develop on other products of the same type design.

Proposed Requirements of This NPRM

This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under "Differences Between this Proposed AD and the MCAI or Service
Information."

Differences Between This Proposed AD and the MCAI or Service
Information


Canadian Airworthiness Directive CF-2019-11, dated March 22, 2019,
states that if any cracking is found during the repetitive detailed
visual inspections of the rudder quadrant box assembly, the repair can
be done within 100 flight cycles after the inspection. However, this AD
requires that, for the LH channel, if the length of the crack exceeds
the upper limit, the repair must be done before further flight. In
addition, if the length of the crack for the LH channel is within the
upper limit, the repair must be done within 50 flight cycles. These
differences have been coordinated with TCCA.

Costs of Compliance

The FAA estimates that this proposed AD affects 123 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed 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 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.

This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.

Regulatory Findings

The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would 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 this proposed
regulation:

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.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):