AFMS
N°
D07
FOR
GARMIN
GFC700
AUTOPILOT
AND
VARIABLE
PITCH
PROPELLER
EQUIPPED
AEROPLANES
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Page APV3-32
12.2
ALTITUDE
LOST
DURING
A
PITCH
AXIS
AUTOPILOT
MA
L-
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:
I. AP DISCffRIM INTR switch
2.
TRIM MASTER SWITCH
PRESS and HOLD
OFF
3.
TRIM Circuit Breaker PU
LL
4. AP DISCffRIM INTR switch RELEASE
When
Autopilot is disconnected because
of
a pitch
/nm maifunct10n, hold the control wheel firmly.
When
electric
tnm
is disconnected, it
is
necessary
operate the pllch tnm through the Tnm Wheel.
When
electric trim is disconnected, Autopilot system can
be
operated
both
in
pitch and roll modes; nevertheless, when a pitch mode
(A
LT
HOLD, VS, GS)
1s
engaged, the Autopilot
Will
provide an annunc1a-
11on
whenever it is necessary
to
manually tnm the aircraft about the
pllch axis
us
ing the
Tr
im Wheel. Make reference
to
"Garmin
GJOOO
Integrated Avionic System
P1/ot
's
Guide 'for Tecnam P20/0 (Part N
o.
190-01830-00 Revision A dated September 2
5,
2014 or a more updat-
ed version
).
Section
3 -
Emergency
procedures
AUTOPILOT
EMERGENCY
PROCEDURES
Ed
. 2. Rev.O
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