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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-1081; Product Identifier 2018-NE-39-AD; Amendment
39-19676; AD 2019-13-03]
RIN 2120-AA64
Airworthiness Directives; Trig Avionics Limited Transponders
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD)
for
certain Trig Avionics Limited TT31, Avidyne Corporation AXP340, and
BendixKing/Honeywell International KT74 Mode S transponders. This AD
was prompted by the discovery that the retaining cam that engages in
the mounting tray may not withstand g-forces experienced during an
emergency landing. This AD requires one-time inspection of the
transponder installation and, depending on the findings, removal of the
affected transponder for modification. The FAA is issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective August 27, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 27,
2019.
ADDRESSES: For service information identified in this final rule,
contact Trig Avionics Limited, Heriot Watt Research Park, Riccarton,
Edinburgh EH14 4AP, United Kingdom; phone: +44 131 449 8810; fax: +44
131 449 8811; email: support@trig-avionics.com; internet: https://trig-
avionics.com. You may view this service information at the FAA, Engine
and Propeller Standards Branch, 1200 District Avenue, Burlington, MA,
01803. For information on the availability of this material at the FAA,
call 781-238-7759. It is also available on the internet at http://www.
regulations.gov by searching for and locating Docket No. FAA-2018-
1081.
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-2018-
1081; 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 mandatory continuing airworthiness information
(MCAI), 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: Min Zhang, Aerospace Engineer,
Boston
ACO Branch, FAA, 1200 District Avenue, Burlington, MA, 01803; phone:
781-238-7161; fax: 781-238-7199; email: min.zhang@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Trig Avionics
Limited TT31, Avidyne Corporation AXP340, and BendixKing/Honeywell
International KT74 Mode S transponders. The NPRM published in the
Federal Register on March 22, 2019 (84 FR 10735). The NPRM was prompted
by the discovery that the retaining cam that engages in the mounting
tray may not withstand g-forces experienced during an emergency
landing. The NPRM proposed to require one-time inspection of the
transponder installation to determine if it is a conventional aft-
facing installation, and depending on the findings, removal of the
affected transponder for modification. The FAA is issuing this AD to
address the unsafe condition on these products.
The European Union Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA AD 2018-0247, dated November 13, 2018 (referred to after
this as ``the MCAI''), to address the unsafe condition on these
products. The MCAI states:
While testing a new model of transponder, it was detected that
the retaining cam was not meeting the approved design criteria for
crash safety shock in the aft direction (20g sustained). This was
due to an uncontrolled deviation in the manufacturing process of the
retaining cam by the part manufacturer. The retaining cam is a small
nylon part that engages in the mounting tray when the transponder is
installed into the aircraft. Additional tests using affected
retaining cam showed that the transponders meet RTCA/DO-106G Section
7.0 operational shocks and crash safety impulse tests, as well as
RTCA/DO-160G Section 7.0 crash safety sustained tests for all
directions, except the aft direction. As a consequence, units which
have been installed with a control panel orientation that is not
opposite to the direction of flight may not withstand g-forces
experienced during an emergency landing. This condition, if not
detected and corrected, could lead to detachment of the transponder,
possibly resulting in damage to fuel systems or emergency evacuation
equipment, and/or injury to aircraft occupants.
To address this potential unsafe condition, Trig Avionics
published the applicable SB to provide instructions to inspect the
installation and the transponder, and how to arrange for
modification.
For the reason described above, this [EASA] AD requires a one-
time inspection of the transponder installation to determine whether
this is a conventional installation, as defined in this [EASA] AD,
and, depending on findings, removal from service of the affected
transponder for modification.
You may obtain further information by examining the MCAI in the AD
docket on the internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2018-1081.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Request To Clarify Compliance
An individual commenter commented that paragraph (g)(1) of the NPRM
does not state clearly that no further action is required if the
transponder is installed in a conventional rear facing installation.
The FAA agrees. The FAA added a new paragraph (g)(2) to this AD to
indicate that no further action is required if the transponder is
installed in a conventional aft-facing avionics rack. Because of this
change,
paragraph (g)(2) in the NPRM becomes paragraph (g)(3) and paragraph
(g)(3) in the NPRM becomes paragraph (g)(4) in this AD.
Support for the AD
An individual commenter supported the AD because it is cost-
effective and the manufacturer may cover some of the costs under
warranty.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the change described previously
and minor editorial changes. The FAA has determined that these minor
changes:
[Agr]re 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.
The FAA has also determined that these changes will not increase
the economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Trig Avionics Limited Service Bulletin (SB) SUP/
TT31/027, Issue 1.0, dated October 1, 2018; Trig Avionics Limited SB
SUP/AXP340/002, Issue 1.0, dated October 1, 2018; and Trig Avionics
Limited SB SUP/KT74/005, Issue 1.0, dated October 1, 2018.
Trig Avionics Limited SB SUP/TT31/027, Issue 1.0, dated October 1,
2018, describes procedures for determining the direction of the Trig
Avionics Limited TT31 Mode S transponder installation and removal of
these affected transponders for replacement or repair. Trig Avionics
Limited SB SUP/AXP340/002, Issue 1.0, dated October 1, 2018, describes
procedures for determining the direction of the Avidyne Corporation
AXP340 Mode S transponder installation and removal of these affected
transponders for replacement or repair. Trig Avionics Limited SB SUP/
KT74/005, Issue 1.0, dated October 1, 2018, describes procedures for
determining the direction of the BendixKing/Honeywell International
KT74 Mode S transponder installation and removal of these affected
transponders for replacement or repair.
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 2,390 transponders installed
on airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
Cost on
U.S. operators
|
| Inspect the transponder installation |
0.5 work-hours x $85 per hour
= $42.50 |
$0
|
$42.50
|
$101,575
|
The FAA estimates the following costs
to do any necessary repairs
that are required based on the results of the inspection. The FAA has
no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
|
Action
|
Labor cost
|
Parts cost
|
Cost per
product
|
|
Replace the
transponder
|
1 work-hour x $85 per hour =
$85 |
$2,872
|
$2,957
|
According to the manufacturer, some
of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. The FAA does not control warranty coverage for affected
individuals. As a result, the FAA has included all costs in our cost
estimate.
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 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 engines, propellers, and
associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
Regulatory Findings
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 this AD:
(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.
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
directive (AD):
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