preamble attached >>>
ADs updated daily at www.Tdata.com
PROPOSED AD BOMBARDIER, INC.: Docket No. FAA-2019-0189; Product Identifier 2019-NM-001-AD.
(a) COMMENTS DUE DATE

    We must receive comments by May 20, 2019.

(b) AFFECTED ADS

    None.

(c) APPLICABILITY

    This  AD  applies  to  Bombardier, Inc.,  Model DHC-8-102, -103, -106,
    -201, -202, -301, -311, and -315 airplanes,  certificated in any cate-
    gory, serial numbers 003 through 672 inclusive.

(d) SUBJECT

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) REASON

    This AD was prompted  by the reported loss  of an elevator spring  tab
    balance weight  prior to  takeoff. We  are issuing  this AD to address
    tolerance stack-up between the balance  weight and the hinge arm  that
    can allow the attachment bolts to  fret with the hinge arm and  result
    in wear, fracture, and loss of the spring tab balance weight. Loss  of
    the spring tab balance weight can lead to unacceptable flutter margins
    and loss of the airplane.

(f) COMPLIANCE

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

(g) INSPECTION AND CORRECTIVE ACTIONS

    Within 600 flight hours after the effective date of this AD, perform a
    detailed  inspection  of  the  two  balance  weights  and  a  detailed
    inspection of  the two  hinge arms  on each  elevator spring tab (left
    hand and right hand), in accordance  with Section 3.B, Part A, of  the
    Accomplishment Instructions  of Bombardier  Service Bulletin  8-55-27,
    Revision A, dated August 15, 2018.

(1) If any of the balance weight attachment locknuts,  part  number  (P/N)
    MS21042-4,  is  found  fractured, loose,  or  missing:  Before further
    flight conduct the rectification in accordance with Section 3.B,  Part
    B, of the Accomplishment  Instructions of Bombardier Service  Bulletin
    8-55-27, Revision A, dated August 15, 2018.

(2) If  the  balance  weight  is  found not secure: Within 60 flight hours
    after the inspection required by paragraph (g) of this AD, repair  any
    damage to the  hinge arm and  permanently secure the  mass balance, in
    accordance  with   Section  3.B,   Part  B,   of  the   Accomplishment
    Instructions of Bombardier Service Bulletin 8-55-27, Revision A, dated
    August 15, 2018.

(3) If the balance weight is found secure: Within 5,000 flight hours after
    the inspection required by paragraph (g) of this AD, repair any damage
    to  the  hinge  arm  and  permanently  secure  the  mass  balance,  in
    accordance  with   Section  3.B,   Part  B,   of  the   Accomplishment
    Instructions of Bombardier Service Bulletin 8-55-27, Revision A, dated
    August 15, 2018.

(4) Where Bombardier Service Bulletin 8-55-27 Revision A, dated August 15,
    2018, specifies to contact  Bombardier for appropriate action:  Before
    further flight, accomplish corrective  actions in accordance with  the
    procedures specified in paragraph (i)(2) of this AD.

(h) CREDIT FOR PREVIOUS ACTIONS

    This paragraph provides credit for actions required by paragraphs (g),
    (g)(2), (g)(3), and (g)(4) of this AD, if those actions were performed
    before  the  effective  date  of this  AD  using  Section  3.B of  the
    Accomplishment Instructions  of Bombardier  Service Bulletin  8-55-27,
    dated April 17, 2018, provided that within 600 flight hours after  the
    effective date of this AD, a detailed visual inspection of the balance
    weight  locknuts,  P/N  MS21042-4,  is  performed  in  accordance with
    Section 3.B, Part C, of the Accomplishment Instructions of  Bombardier
    Service Bulletin 8-55-27, Revision A,  dated August 15, 2018, and  the
    rectification is  performed before  further flight  for any fractured,
    loose, or missing balance  weight attachment locknuts, P/N  MS21042-4,
    in accordance with Section 3.B, Part B, of Bombardier Service Bulletin
    8-55-27, Revision A dated August 15, 2018.

(i) 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.

(j) RELATED INFORMATION

(1) Refer   to   Mandatory  Continuing  Airworthiness  Information  (MCAI)
    Canadian AD CF-2018-30,  dated November 7, 2018,  for related informa-
    tion. This MCAI may be found in the AD docket on the internet at http:
    //www.regulations.gov by searching for  and  locating  Docket No. FAA-
    2019-0189.

(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.,  Q-Series Technical Help Desk,  123 Garratt Boulevard,  Toronto,
    Ontario M3K 1Y5, Canada;  telephone 416-375-4000; fax 416-375-4539; e-
    mail thd.qseries@aero.bombardier.com;  internet http://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  March 28, 2019.  Michael Kaszycki,
Acting  Director,  System   Oversight  Division,  Aircraft   Certification
Service.

DATES: We must receive comments on this proposed AD by May 20, 2019.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0189; Product Identifier 2019-NM-001-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc., Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes;
DHC-8-200 series airplanes; and DHC-8-300 series airplanes. This
proposed AD was prompted by the reported loss of an elevator spring tab
balance weight prior to takeoff. This proposed AD would require
inspecting the two balance weights and the two hinge arms on each
elevator spring tab, and corrective actions if necessary. We are
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by May 20, 2019.

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 http://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., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; internet http://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 http://www.regulations.
gov by searching for and locating Docket No. FAA-2019-
0189; 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 (phone: 800-647-
5527) is in the ADDRESSES section. 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

We invite 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-2019-0189;
Product Identifier 2019-NM-001-AD" at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM because
of those comments.

We will post all comments we receive, without change, to http://www.
regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact
we receive about this NPRM.

Discussion

Transport Canada Civil Aviation (TCCA), which is the aviation
authority for Canada, has issued Canadian AD CF-2018-30, dated November
7, 2018 (referred to after this as the Mandatory Continuing
Airworthiness Information, or "the MCAI"), to correct an unsafe
condition for certain Bombardier, Inc., Model DHC-8-102, -103, and -106
airplanes; DHC-8-200 series airplanes; and DHC-8-300 series airplanes.
The MCAI states:

One operator has reported the loss of an elevator spring tab
balance weight prior to takeoff. An investigation found that
clearances, due to tolerance stack-up between balance weight and
hinge arm, allow the attachment bolts to fret with the hinge arm
causing wear and potentially progressing to fracture and loss of the
spring tab balance weight. The loss of a spring tab balance weight
could result in unacceptable flutter margins and loss of the
aeroplane.

This [Canadian] AD mandates a one-time [detailed] inspection to
verify the spring tab balance weights are securely attached on both
the left hand and right hand spring tab assemblies. If any of the
balance weights are found loose, instructions are given to repair
any damage to the hinge arm, and to add a solid shim between balance
weight and hinge arm to eliminate any potential gap, and to specify
balance weight attachment hardware that has low susceptibility to
hydrogen embrittlement.

You may examine the MCAI in the AD docket on the internet at http://
www.regulations.gov by searching for and locating Docket No. FAA-2019-
0189.

Related Service Information Under 1 CFR Part 51

Bombardier has issued Service Bulletin 8-55-27, Revision A, dated
August 15, 2018. This service information describes procedures for
inspecting the two balance weights and the two hinge arms on each
elevator spring tab, and corrective actions including inspecting the
holes in the hinge arm, inspecting the hinge arm for corrosion and
chafing, installing bushings and a solid shim, replacing the hinge arm,
repairing damage to the hinge arm, and permanently securing the mass
balance.

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, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
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.

Costs of Compliance

We estimate that this proposed AD affects 47 airplanes of U.S.
registry. We estimate 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
$0
$170
$7,990

We estimate the following costs to do any necessary on-condition
actions that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need these on-condition actions:

Estimated Costs for On-Condition Actions

Labor cost
Parts cost
Cost per product
Up to 18 work-hours x $85 per hour = $1,530
$0
Up to $1,530

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.

We are 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

We 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. Is not a "significant rule" under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);

3. Will not affect intrastate aviation in Alaska; and

4. 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):