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O IF IT CANNOT BE VERIFIED THERE IS NO ICE ON THE
HORIZONTAL STABILIZER
ENROUTE / DESCENT
6. Minimum Speed (once out of icing conditions) . . . . . . . . . . . . . . . . . . 130 KIAS
APPROACH AND LANDING
7. Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO/APR
8. Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF +10
9. Landing Distance/Weight:
(a) MULTIPLY normal Flap TO/APR landing distance by 1.22.
(b) REDUCE maximum landing weight by 40 lbs.
CAUTION
Avoid landing with a tailwind.
PROCEDURE COMPLETED
O IF NO ICE ON THE HORIZONTAL STABILIZER
PROCEDURE COMPLETED
IF TAIL DE-ICE FAIL MESSAGE REMAINS OFF
PROCEDURE COMPLETED
• IF WING/STAB DEICE SWITCH OFF
1. Do not fly into icing conditions.
PROCEDURE COMPLETED
3-88 AA 510FM-07
MODEL 510 SECTION III - OPERATING PROCEDURES
ABNORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
W/S A/I FAIL L-R - AMBER (WINDSHIELD ANTI-ICE FAILURE)
Indicates a loss of power to the windshield anti-ice system or insufficient heat is being provided to
the windshield.
1. WINDSHIELD ANTI-ICE Switch (affected side) . . . . . . . . . . . . . . . . . . . . . . . OFF then ON
2. L or R WSHLD TEMP Circuit Breaker . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
• IF W/S A/I FAIL MESSAGE REMAINS DISPLAYED
3. Exit icing environment.
4. Windshield . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR FOG MANUALLY as required
5. Refer to Abnormal Procedures, WINDSHIELD A/I INOPERATIVE APPROACH AND
LANDING.
PROCEDURE COMPLETED
• IF W/S A/I FAIL MESSAGE EXTINGUISHED
PROCEDURE COMPLETED
W/S O'HEAT L-R - AMBER (WINDSHIELD OVERHEAT)
Indicates the windshield has been overheated for more than 5 seconds. The white W/S O’HEAT
message turns amber if it is on for 5 seconds. If the windshield temperature controller is working
properly, it will shut off power to the windshield heater to allow the windshield to cool then turn
heat back on.
• IF MESSAGE IS ON STEADY
1. WINDSHIELD ANTI-ICE Switch (affected side) . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
2. Exit icing environment.
3. Refer to Abnormal Procedures, WINDSHIELD A/I INOPERATIVE APPROACH AND
LANDING.
PROCEDURE COMPLETED
• IF MESSAGE IS CYCLING ON AND OFF
1. W/S O’HEAT L-R message. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
PROCEDURE COMPLETED
510FM-07 AA 3-89
SECTION III - OPERATING PROCEDURES MODEL 510
ABNORMAL PROCEDURES
FAA APPROVED
U.S. Configuration
WING DE-ICE FAIL
Indicates that one or more segments of the wing deice boot system did not reach the required
pressure when commanded or that pressure is present when not commanded.
• IF WING/STAB DEICE SWITCH AUTO OR MANUAL
1. Throttles . . . . . . . . . . . . . . . . . . . . . . INCREASE POWER (as required above 70% N2)
2. WING/STAB Deice Switch . . . . . . . . OFF (Verify WING DE-ICE FAIL message clears)
3. WING/STAB Deice Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD IN MANUAL
(SURFACE DE-ICE message should display within 6 seconds)
4. WING/STAB Deice Switch . . . . . . . . . . . . . . . . . . . . . . . . . AUTO for at least 2 minutes
IF WING DE-ICE FAIL MESSAGE REMAINS DISPLAYED OR
DISPLAYS AGAIN
5. WING/STAB Deice Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
6. Exit icing environment.
O IF IT CANNOT BE VERIFIED THERE IS NO ICE ON THE WING
7. Refer to Abnormal Procedures, LANDING WITH ICE ON WING LEADING
EDGE.
PROCEDURE COMPLETED
O IF NO ICE ON THE WING
PROCEDURE COMPLETED
IF WING DE-ICE FAIL MESSAGE REMAINS OFF
PROCEDURE COMPLETED
• IF WING/STAB DEICE SWITCH OFF
1. Do not fly into icing conditions.
2. WING/STAB Deice Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO then OFF
(Verify white STALL WARN HI message is displayed)
3. Use STALL WARNING-HIGH performance data for landing.
PROCEDURE COMPLETED
3-90 AA 510FM-07
MODEL 510 SECTION III - OPERATING PROCEDURES
ABNORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
UNCOMMANDED REDUCTION IN ENGINE POWER DURING
ICING CONDITIONS
In some icing encounters at high altitude, the heater on the engine T2 probe cannot keep the
probe clear of ice. This can cause a false high RAT temperature indication to the FADEC. The
result is the FADEC will command a lower N1 until the T2 probe is de-iced, or the engine Anti-Ice
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Citation Mustang airplane flight manual 1(69)
