Operation; General; Starting Procedures; I N-Flight Procedures - Mid-Continent Instruments 4300 Series Installation Manual And Operating Instructions

Section 3: Operation
3.1

General

This section describes the Model 4300-XXX Electric Attitude I ndicator operating procedures. The
indicator is required to be installed in an aircraft with the specified inputs applied. Figure 1.2
provides an illustration of a typical Model 4300 display and a table describing indicator functions.
3.2

Starting Procedures

The following operational procedures are recommended when preparing the indicator for use:
THE I NDI CATOR MAY BE DAMAGED I F THE "PULL TO CAGE"
KNOB I S RELEASED WI TH A "SNAP." SLOWLY RELEASE "PULL
TO CAGE" KNOB AVOI DI NG A "SNAP" RELEASE.
NOTE: I ndicator may be momentarily caged by pulling "PULL TO CAGE"
knob to the fully extended position, holding knob until the
display stabilizes, and then allow ing the knob to return to the
normal position.
A. Apply power to the indicator. Note that the Gyro Warning flag (red) will pull out-of-
view. Allow three minutes for presentation stabilization.
B. On models with trim adjustment, rotate the symbolic airplane adjustment knob for
the desired pitch attitude presentation, i.e. aligning the symbolic airplane with the
horizon.
C. I f caging is required, caging should be accomplished when the aircraft is in a wings
level, normal cruise attitude, as indicated by other instruments or the earth's horizon.
I f the gyro is caged when the aircraft is not in this attitude, the resulting attitude
presentation immediately after caging will be in error by the difference between true
vertical and actual aircraft attitude. Small errors in caging erection will be corrected
by the indicator to true vertical in pitch and roll at 2.5
nominal).
3.3

I n-Flight Procedures

A. Adjust the symbolic airplane to obtain desired pitch attitude presentation after take-
off.
B. I n the event of errors in excess of 10
acceleration, the indicator should be momentarily caged after the aircraft is returned
to level flight.
3.4

Dynamic Errors

A. Turn I nduced Errors
Pitch indication errors resulting from a standard coordinated turn (180 degrees in
one minute at a true airspeed of 156 knots) will not exceed 3
developed under non-standard conditions may be greater. Errors that develop will be
self corrected by the internal erection system or manually corrected by the actuation
of the caging system.
Rev J, September 1, 2009
Mid-Continent I nstruments, Wichita, KS
* * * * CAUTI ON* * * *
°
Manual Number 9015762
°
per minute minimum (5
caused by extended bank or fore-aft
°
. Dynamic errors
°
/ min.
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