Appendix C Safety - Lycoming TEO-540-A1A Installation And Operation Manual

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TEO-540-A1A Engine Installation and Operation Manual
Table C-1 shows the safety alert messages.
Ref. ID
WARNING Connection of equipment or devices other than the Lycoming "Field
1
2
WARNING In the event of a NTO indication in flight, the operator should make
3
WARNING After a software installation, the maintainer shall confirm proper and
4
WARNING An ECU reset (re-initialization) shall only be conducted as a last
5
WARNING The NTO indication provides an indication that the ECU along with
6
WARNING The operator must properly conduct a PFT prior to flight.
7
WARNING The operator must allow sufficient time for the PFT to be completely
8
CAUTION
9
CAUTION
10
CAUTION
© 2018 Avco Corporation. All Rights Reserved
October 2018
APPENDIX C
SAFETY
Table C-1.
Safety Alert Messages
Service Tool" to CAN 2 Bus may compromise safe EECS operation.
Connection of non-Lycoming approved equipment or devices to the
CAN 2 bus interface is prohibited. The Field Service Tool must not
be used in flight.
minimum and gentle throttle changes to reduce operability
anomalies.
correct software loading via the Lycoming Field Service Tool.
chance recovery attempt from an EECS anomaly as determined
necessary by the operator. It is possible that an ECU reset may not
be recoverable. The operator must take this into consideration when
deciding to command a reset.
limited conventional engine hardware is acceptably safe for flight
once a proper PFT is conducted. The operator must still interrogate
conventional engine indications to determine that the conventional
engine is also acceptable safe for flight.
executed (as indicated by the PFT active annunciator) prior to
making any throttle changes otherwise the PFT may be inadvertently
canceled with no other indication that the PFT is incomplete.
The PFT is not to be commanded during flight. If the PFT is
commanded during flight, throttle movement will cancel the PFT.
To ensure proper EECS operation, the Lycoming Field Service Tool
shall not be used during flight.
Selection of the IGNITION ON-OFF switch to OFF during ground
operations is a single interlock. To ensure that the engine is not
inadvertently started or the ignition system is not inadvertently
actuated during maintenance, electrical power should be removed
from the ECU during maintenance as a secondary interlock to prevent
injury.
Title
Appendix C
Page 95

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