Tecnam P2010 - Page 438

AFMS N°D07 FOR GARMIN GFC700 AUTOPILOT AND VARIABLE PITCH PROPELLER EQUIPPED
AEROPLANES
Page APV3-32
Section 3 – Emergency procedures
AUTOPILOT EMERGENCY PROCEDURES
12.2 ALTITUDE LOST DURING A PITCH AXIS AUTOPILOT MAL-
FUNCTION AND RECOVERY
Following table addresses the altitude lost during a pitch axis malfunction and re-
covery for each reported flight phase:
Flight phase
Altitude loss
Climb
90 ft
Cruise
200 ft
Descent
170 ft
Maneuvering
210 ft
Approach
70 ft
12.3 ELECTRIC TRIM MALFUNCTION
In case of Electric Trim malfunction (either in AP Autotrim mode or
when manually operated through the Manual Electric Trim Switch),
apply following procedure:
1.
AP DISC/TRIM INTR switch
PRESS and HOLD
2.
TRIM MASTER SWITCH
OFF
3.
TRIM Circuit Breaker
PULL
4.
AP DISC/TRIM INTR switch
RELEASE
When Autopilot is disconnected because of a pitch
trim malfunction, hold the control wheel firmly.
When electric trim is disconnected, it is necessary
operate the pitch trim through the Trim Wheel.
When electric trim is disconnected, Autopilot system can be operated
both in pitch and roll modes; nevertheless, when a pitch mode (ALT
HOLD, VS, GS) is engaged, the Autopilot will provide an annuncia-
tion whenever it is necessary to manually trim the aircraft about the
pitch axis using the Trim Wheel. Make reference to “Garmin G1000
Integrated Avionic System Pilot’s Guide”for Tecnam P2010 (Part No.
190-01830-00 Revision A dated September 25, 2014 or a more updat-
ed version).