[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
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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
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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
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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