Instruction Manual

G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 7-49
190-00915-01 Revision 9
7.25 Safe Flight Lift Computer Ground Calibration
NOTE
This procedure is required only for aircraft with the optional Electronic Stability
and Protection (ESP) feature with Angle of Attack (AoA) modes and the Safe
Flight Lift Computer p/n C-05606-1.
Prior to removal of the lift computer, it is recommended that Section 7.25.1 be accomplished to record the
existing stall warning points for Pots 0, 1 and 2.
Original C-05606-1 Lift Computer Reinstalled
No ground or flight calibration is required if the removed C-05606-1 Lift Computer is re-installed and the
potentiometers are not adjusted. This does not include units that were returned for repair as their
calibration will need to be completed at installation.
New, Repaired or Exchange C-05606-1 Lift Computer Installed
If a new, repaired or exchange C-05606-1 Lift Computer is installed, the ground and flight calibration will
need to be accomplished. See Section 7.25.2 for the ground calibration and Section 7.25.3 for the flight
calibration of the C-05606-1 Lift Computer.
NOTE
Safe Flight P/N C-05606-1 lift computers are equipped with six adjusta
b
le
potentiometers in the top of the computer. The potentiometers are marked 0, 1,
2, 3, 4, and 5. (Ref. Figure 7-14.)
The potentiometers marked 0, 1, and 2 are used to calibrate the stall warning
points for the three flap positions (full up, approach, and full down.)
The potentiometers marked 3, 4, and 5 are used to calibrate the Low Airspeed
Awareness (LAA) output for the three flap positions (full up, approach, and full
down) which determines Electronic Stability and Protection (ESP) and
Autopilot Underspeed Protection (USP) alpha floor symbol position.
7.25.1 Measuring Lift Computer Stall Warning Points
Prior to removal of the lift computer, it is recommended that the stall warning points from the lift
computer installed in the aircraft be measured. This section is used to measure stall warning points of the
lift computer.
1. Gain access to the stall warning computer.
2. Connect the breakout box (P/N SK100360 or equivalent) between the lift computer and the
airplane wiring harness (see Figure 7-15).
3. Make sure that the stall warning heat system is turned OFF.
4. Remove the potentiometer access cover plate from the lift computer.
5. Simulate an in-flight condition as follows: Bypass the landing gear safety switch by connecting
an electrical ground to TP 7 of the breakout box. This is best accomplished by placing a jumper
between TP 2 and TP 7 of the breakout box.