[Federal Register Volume 84, Number 65 (Thursday, April 4, 2019)]
[Proposed Rules]
[Pages 13148-13150]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-06458]


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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).

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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 [email protected]; 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 [email protected].

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

[[Page 13149]]

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

[[Page 13150]]

    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

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (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 
category, 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 
information. 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 [email protected].
    (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; email [email protected]; 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.
[FR Doc. 2019-06458 Filed 4-3-19; 8:45 am]
BILLING CODE 4910-13-P


