DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0189; Product Identifier 2019-NM-001-AD; Amendment
39-19672; AD 2019-12-17]
Airworthiness Directives; Bombardier, Inc., Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
ACTION: Final rule.
SUMMARY: The FAA is adopting a new airworthiness directive (AD)
certain Bombardier, Inc., Model DHC-8-102, -103, and -106 airplanes;
Model DHC-8-200 series airplanes; and Model DHC-8-300 series airplanes.
This AD was prompted by the reported loss of an elevator spring tab
balance weight prior to takeoff. This AD requires inspecting the two
balance weights and the two hinge arms on each elevator spring tab, and
corrective actions if necessary. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective August 12, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 12,
ADDRESSES: For service information identified in this final rule,
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@example.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. It is also available on the internet at http://www.regulations.gov
by searching for and locating Docket No. FAA-2019-0189.
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 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 firstname.lastname@example.org.
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 DHC-8-102, -103, and -106 airplanes; Model DHC-8-200 series
airplanes; and Model DHC-8-300 series airplanes. The NPRM published in
the Federal Register on April 4, 2019 (84 FR 13148). The NPRM was
prompted by the reported loss of an elevator spring tab balance weight
prior to takeoff. The NPRM proposed to require inspecting the two
balance weights and the two hinge arms on each elevator spring tab, and
corrective actions if necessary.
The FAA is 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.
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; Model DHC-8-200 series airplanes; and Model 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
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
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.
The FAA gave the public the opportunity to participate in
developing this final rule. The FAA has considered the comment
received. The Air Line Pilots Association, International stated that it
agrees with the intent of the NPRM.
The FAA reviewed the relevant data, considered the comment
received, 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 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
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 47 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
|2 work-hours x $85 per hour =
The FAA estimates the following costs
to do any necessary on-
condition actions 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 these on-condition actions:
Estimated Costs of On-Condition Actions
|Up to 18 work-hours x $85 per
hour = $1,530
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.
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
This 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.
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
(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
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