Appendix A Figure A-17 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
GO AROUND - REJECTED LANDING
AFTER GEAR IS FULLY RETRACTED, A/S ACCELERATE TO 130 KCAS, IF FLAPS 20°, RETRACT TO DESIRED CLIMB SPEED FLAPS 5°, INCREASE PITCH TO 10° COMPLETE AFTER T/O
AND CLIMB CHECKLIST A/S 140 KCAS, WHEN LANDING REJECTED, FLAPS UP.
APPLY MAX POWER, PITCH 8° UP AND SELECT FLAPS 20° IF 40°
PREVIOUSLY SELECTED
POSITIVE RATE,,
GEAR UP, IF FLAPS APPROACH, NORMAL 20°, 113 KCAS MIN., 120 KCAS MIN. IF FLAPS 5°,
STABILIZED AND
CONFIGURED FOR
LANDING A-50
Appendix A Figure A-18 CAUTION MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
DO NOT SELECT REVERSE UNTIL NO FLAP OR 5° FLAP LANDING (ABNORMAL PROCEDURE) BELOW 90 KCAS
WITH NOSE WHEEL ON CHECK BOTH PROPS BETA. BRAKES AND NOTE GROUND REVERSE AS REQUIRED. NOTE: BETA MAY LANDING DISTANCE NOT BE AVAILABLE UNTIL BELOW 90 KCAS WILL INCREASE
APPROXIMATELY APPROXIMATELY 1500 FT AGL LEVERS SLOWLY RETARD TOUCHDOWN - POWER 30%
TO FLIGHT IDLE STOP THRESHOLD (10%-20% TORQUE) NO FLAP Vref 1.25 VS1, BUT NOT COMPLETE DESCENT AND PARALLEL TO RUNWAY MAINTAIN TRACK BELOW 115 KCAS (SEE CHART) FINAL CHECK. A/S
APPROACH CHECKLISTS
SLOWING TO NO FLAP Vref. 115 KCAS MIN.
(25%-30% TORQUE) A/S 150 KCAS MIN. APPROACH BY STABILIZED 500 agl
1.5 MILES M NO FLAP Vref 1.25 Vs1 BUT NOT BELOW 115KCAS (USE FOR FLAPS UP OR 5°) CHECK 7,500 UP / 115* 5° / 115* LANDING ASSURED, GEAR DOWN A/S 140 KCAS MIN, SINK RATE 8,000 / 115* / 115* COMPLETE LANDING CHECKLIST 8,500 / 116* / 115* 9,000 116 / 120* 115 / 115* FLAPS 0° OR 5°.
9,500 9,995 119 / 123* / 126* 115 / 117* / 120* 500-600 FPM SINK RATE. A/S 140 KCAS MIN.
10,000 123 / 115 / (APPROX 25%-30% TORQUE) 10,500 127 / 118 / 11,025 129 / 121 / "SOL. P A-51
Appendix A Figure A-19 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
CAUTION ONE ENGINE INOPERATIVE LANDING
ANTICIPATE
SWERVE TOWARD WHILE MAINTAINING TRACK WITH
OPERATING RUDDER, MOVE OPERATING CAUTION WARNING
ENGINE WHEN ENGINE POWER LEVER GROUND ENTERING BETA IDLE, CHECK PROP BETA., DO NOT USE SINGLE DO NOT ATTEMPT A
REVERSE AND BRAKES AS TOUCHDOWN, ENGINE REVERSE GO-AROUND WITH REQUIRED. OPERATING ENGINE THRUST WITH THE GEAR DOWN BELOW APPROXIMATELY POWER LEVER SLOWLY SIMULATED FAILED 400' AGL OR AFTER 1500 FT AGL RETARD TO FLIGHT IDLE ENGINE POWER 20° FLAPS ARE STOP LEVER ABOVE FLIGHT SELECTED.
IDLE.
THRESHOLD, (10%-20% TORQUE). Vref.
PARALLEL TO RUNWAY MAINTAIN TRACK A/S 110 KCAS (MARQ, N). 105 KCAS (SOL, P). CHECK SINK RATE. 300-600 FPM FINAL CHECK. FLAPS 20°.
A/S Vxse MIN. (SEE CHART)
COMPLETE DESCENT AND COMPLETE LANDING CHECKLIST,
APPROACH CHECKLISTS AND RUDDER TRIM CENTERED, HOLD REVIEW SINGLE ENGINE LANDING BALL IN CENTER WITH RUDDER.
CHECKLIST 140 KCAS (MARQ, N) MIN, 135 KCAS (SOL, P) MIN (APPROX 50%-55% TORQUE) A/S 150 KCAS _ AS REQUIRED APPROACH BY STABILIZED 500 agi
N, MARQ/P,SOL FLAP SETTING Vxse (KCAS) Vyse (KCAS) FLAPS 5° A/S 140 KCAS CHECK UP 140 / 135 * 150 / 150 * (130 KCAS MIN) SINK RATE 50 130 / 130 * 140 / 140 * 500 - 600 20° 125 / 125 * 135 / 130 * FEET PER MINUTE *P, SOL
LANDING ASSURED CHECK GLIDE PATH, GEAR DOWN.
(APPROX 40% TORQUE) A-52
Appendix A Figure A-20 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
CROSSWIND LANDING
DEMONSTRATED
CROSSWIND
ALL MODELS TAKEOFF 22 KCAS LANDING 18 KCAS
• WIND • WIND
AIRCRAFT WILL BE FLOWN DOWN AN EXTENSION OF
THE RUNWAY CENTER LINE WITH DRIFT CORRECTION
ESTABLISHED SUFFICIENTLY IN ADVANCE TO PERMIT
CENTER LINE TO BE FLOWN WITH ONLY MINOR
COORDINATED CORRECTIONS INCREASE VrefFOR CROSSWIND LANDING BY ONE-
HALF THE STEADY WIND SPEED PLUS ONE-HALF THE GUST SPEED NOT TO EXCEED Vref PLUS 10 KCAS.
• WIND
PRIOR TO TOUCHDOWN, THE UPWIND WING IS LOWERED AND SMOOTHLY MODULATED. OPPOSITE
RUDDER IS APPLIED SO THAT AIRCRAFT PATH CONTINUES DOWN RUNWAY CENTERLINE. THE
AIRCRAFT SHOULD NOT BE ALLOWED TO DEVELOP ANY TENDENCY TO DRIFT DOWNWIND.
NOTE: RUDDERS CENTERED BEFORE NOSE WHEEL TOUCHDOWN. SPOILERS INTO WIND AS NECESSARY
TO KEEP WINGS LEVEL
• WIND A-53
Appendix A Figure A-21 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
ILS, LPV, RNP, LNAV/NAV APPROACH COMPLETE DESCENT AND APPROACH A/S 140 KCAS MIN. (20%-25% TORQUE), CHECKLISTS. A/S 150 KCAS (140 KCAS MIN) DESCEND 500 FPM TO PROCEDURE REVIEW APPROACH PLATE. RADIOS: TUNE & TURN OR OTHER APPROACH SEGMENT IDENTIFY. CHECK FINAL APPROACH FIX ALTITUDE ALTITUDE, MARKER BEACON RECENER *ON® FLAPS 5°, 140 KCAS MIN.
(25%-30% TORQUE) LANDING APPROACH SPEEDS - Vref
1.3 Vs1 1.5 Vs1 WEIGHT FLAPS 20° FLAPS 40° 7,500 LBS / 96 * / 99 * 8,000 LBS / 99 * /102 * A/S 140 KCAS MIN.
8,500 LBS 99 / 102 * 105/106: (25%-30% TORQUE) 9,000 LBS 100 / 105 * 108/109 * 9,500 LBS 102 / 108 * 111/112* MISSED APPROACH:
9,955 LBS / 111 * /115 * CONTINUE WITH LANDING ASSURED, CHECK GEAR 10,000 LBS 105 / 114 / MISSED APPROACH DOWN, FLAPS 20° APPROACHING 10,500 LBS 108 / 116 / PROFILE GLIDE SLOPE (ONE DOT BELOW G/S), 11,025 LBS 110 / 119 / A/S 120 KCAS MIN.
+ P. BOL
COMPLETE LANDING CHECKLIST (APPROX 25% TORQUE) FINAL CHECK. FLAPS 20° (OR 40*) DH IF DESIRED, BELOW 120 KCAS TOUCHDOWN: POWER LEVERS RETARD TO FLIGHT IDLE STOP. POWER LEVERS RETARD TO GROUND IDLE, CHECK BOTH PROPS BETA. REVERSE AND BRAKES AS REQUIRED.
A-54
Appendix A Figure A-22 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
TWO ENGINE MISSED APPROACH
COMPLETE AFTER
TAKEOFF CHECKLIST
ACCELERATE TO
DESIRED CLIMB SPEED A/S 140 KCAS.
FLAPS UP AFTER GEAR IS FULLY RETRACTED, A/S 130 KCAS, IF FLAPS 20°, RETRACT TO FLAPS 5°, INCREASE PITCH TO 10°
MISSED APPROACH GO- AROUND. MAX POWER. POSITIVE RATE. GEAR UP, PITCH UP 8° AND SELECT IF FLAPS 20°, 113 KCAS MIN, FLAPS 20° IF 40° IF FLAPS 5°, 120 KCAS MIN.
PREVIOUSLY SELECTED MAP A-55
Appendix A Figure A-23 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
ONE ENGINE INOPERATIVE ILS, LPV, RNP, LNAV/NAV APPROACH A/S 140 KCAS (130 KCAS MIN.), (50%-60% TORQUE), FLAPS 5°. DESCEND 500 FPM TO PROCEDURE TURN OR OTHER APPROACH SEGMENT ALTITUDE.
COMPLETE DESCENT AND APPROACH CHECKLISTS. A/S 150 KCAS 140 KCAS (MARQ, N) MIN, 135 KCAS (SOL, P) MIN. REVIEW APPROACH PLATE. RADIOS: FLAPS 5°, 140 KCAS (130KCAS MIN) TUNE & IDENTIFY. CHECK FINAL (50%-60% TORQUE)
APPROACH FIX ALTITUDE, MARKER RECEIVER "ON" WARNING A/S 140 KCAS (130 KCAS MIN.)
(50%-60% TORQUE), FLAPS 5°
DO NOT ATTEMPT A
GO-AROUND WITH GEAR DOWN BELOW MISSED APPROACH:
400' AGL OR AFTER CONTINUE WITH ENGINE OUT 20° FLAPS ARE MISSED APPROACH PROFILE LANDING ASSURED, CHECK GEAR SELECTED. DOWN APPROACHING GLIDE
SLOPE (ONE DOT BELOW G/S), A/S 140 KCAS (130 KCAS MIN)
CAUTION
DO NOT USE SINGLE LANDING CHECK ENGINE REVERSE (50%-55% TORQUE)
THRUST WITH THE SIMULATED FAILED ENGINE POWER RUNWAY IN SIGHT, FINAL CHECK. FLAPS 20°, SLOWING TO CROSS THRESHOLD AT LEVER ABOVE FLIGHT 110 KCAS (MARQ, N), 105 KCAS (SOL, P), IDLE. COMPLETE LANDING CHECKLIST. RUDDER TRIM CENTERED, HOLD BALL IN CENTER WITH RUDDER.
CHECK FINAL LANDING CONFIGURATION.
TOUCHDOWN, OPERATING
OPERATING ENGINE ENGINE POWER LEVER
POWER LEVER GROUND SLOWLY RETARD TO FLIGHT IDLE, CHECK PROP IDLE STOP.
BETA. REVERSE AND BRAKES AS REQUIRED.
A-56
Appendix A Figure A-24 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
ONE ENGINE INOPERATIVE MISSED APPROACH
N, MARQ/P, SOL FLAP SETTING Vxse (KCAS) Vyse (KCAS) AFTER TAKEOFF CHECKLIST A/S 150 KCAS, COMPLETE 0ª 140 / 135* 150 / 150 * 5° 130 / 130 * 140 / 140 * 20° 125 / 125 * 135 / 130 * A/S 140 KCAS.
*P, BOL MINIMUM, FLAPS UP
AFTER GEAR IS FULLY RETRACTED AND OBSTRUCTIONS CLEARED, IF FLAPS 20° ADJUST PITCH TO ACCELERATE TO Vyse A/S 130KCAS (P,SOL), 135KCAS (N,MARQ), FLAPS TO 5°, PITCHAPPROX. 10° PITCH TO MAINTAIN Vse MINIMUM, APPROX 8° PITCH, FLAPS 209, APPROX 10-12° PITCH, FLAPS 5°.
IF 20° FLAPS 113 KCAS MIN. IF 5° FLAPS 120 KCAS (MARQ, N) MIN.
OR 125 KCAS (SOL, P) MIN.
COMMENCING MISSED APPROACH, SET MAX POWER. MAINTAIN DIRECTIONAL
CONTROL, RUDDER AND SPOILER AS NECESSARY, GEAR UP.
MAP
WARNING
UNDER CERTAIN COMBINATIONS OF WEIGHT, *IF TRANSITIONING FROM A DESCENT, TEMPERATURE, AND PRESSURE ALTITUDES, WITH LANDING MAINTAIN PITCH TO MAINTAIN 140 KCAS, GEAR DOWN AND FLAPS 20°, SINGLE ENGINE GO RAISE GEAR, THEN 10° PITCH. SOME AROUND MAY NOT BE POSSIBLE AT ALTITUDES OF LESS ALTITUDE LOSS IS TO BE EXPECTED. THAN 400 FEET AGL. (SEE PAGE A-24a) A-57
Appendix A Figure A-25 NOTE MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
NONPRECISION STRAIGHT-IN APPROACH
EITHER THIS PROCEDURE, OR ALTERNATELY PROFILE A-25a MUST BE DEMONSTRATED. A/S 140 KCAS (130 KCAS MIN).
(20%-25% TORQUE), DESCEND 500 COMPLETE DESCENT AND APPROACH CHECKLISTS. FPM TO PROCEDURE TURN OR A/S 150 KCAS (140 KCAS MIN). REVIEW APPROACH OTHER APPROACH SEGMENT PLATE. RADIOS: TUNE & IDENTIFY. CHECK FINAL ALTITUDE
APPROACH FIX CROSSING ALTITUDE, MARKER RECEIVER "ON" IF REQUIRED.
FLAPS 5°, A/S 140 KCAS MIN.
LANDING APPROACH SPEEDS - Vref (25%-30% TORQUE)
1.3 Vs1 1.5 Vs1 WEIGHT FLAPS 20° FLAPS 40° 7,500 LBS / 96* / 99* 8,000 LBS / 00 * / 102 * 8,500 LBS 99 / 102* 105 / 106 * 9,000 LBS 100 / 105 * 108 / 109 * A/S 140 KCAS MIN.
9,500 LBS 102 / 108 * 111 / 112* (25%-30% TORQUE) 9,955 LBS / 111 * / 115* 10,000 LBS 105 / 114 /
10.500 LBS 108 / 116 / LANDING ASSURED CHECK GEAR 11,025 LBS 110 / 119 / DOWN, FLAPS 20° APPROACHING
FIX INBOUND, LANDING CHECKLIST * P. BOL COMPLETE A/S 120 KCAS MIN.
MAP MISSED APPROACH: NDA A/S 120 KCAS MIN, (25%-30% TORQUE). 800-1000 FPM DESCENT POWER, PITCH TO 8°. GO-AROUND, MAX *VDP A/S 120 KCAS MIN.
CONTINUE WITH TWO (APPROX 50% TORQUE)
ENGINE MISSED *VDP APPROACH PROFILE VISUAL DESCENT POINT FINAL CHECK. FLAPS 40° IF DESIRED, BELOW 120 KCAS
AN APPROACH CONSTRUCTED WITH A TOUCHDOWN: POWER LEVERS RETARD TO FLIGHT IDLE STOP,
VDP SHOULD HAVE THE THEN POWER LEVERS RETARD TO GROUND IDLE, CHECK BOTH AIRCRAFT CROSS THE PROPS BETA. REVERSE AND BRAKES AS REQUIRED.
MDA AT OR BEYOND THE VDP.
A-58
Appendix A Figure A-25a NOTE MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
NONPRECISION STRAIGHT-IN APPROACH OR ALTERNATELY PROFILE EITHER THIS PROCEDURE, **OPTIONAL USE OF CONTINUOUS DESCENT FINAL APPROACH (CDFA) DEMONSTRATED. A-25 MUST BE COMPLETE DESCENT AND APPROACH CHECKLISTS. (20%-25% TORQUE), DESCEND 500 FPM TO PROCEDURE TURN OR A/S 140 KCAS (130 KCAS MIN).
A/S 150 KCAS (140 KCAS MIN). REVIEW APPROACH OTHER APPROACH SEGMENT PLATE. RADIOS: TUNE & IDENTIFY. CHECK FINAL ALTITUDE
APPROACH FIX CROSSING ALTITUDE, MARKER RECEIVER "ON" IF REQUIRED, *CALCULATE VDA FLAPS 5°, A/S 140 KCAS MIN.
LANDING APPROACH SPEEDS - Vref (25%-30% TORQUE)
1.3 VS1 1.5 Vs1 WEIGHT FLAPS 20° FLAPS 40° 7,500 LBS / 96 * / 99 * 8,000 LBS / 99 * /102 * 8,500 LBS 99 / 102 * 105 /106 * 9,000 LBS 100 / 105 * 108 /109 * CAUTION - STEPDOWN FIXES A/S 140 KCAS MIN.
9,500 LBS 102 / 108 * 111/112 * (25%-30% TORQUE) 9,955 LBS / 111* 1115 * **DURING ALLAPPROACHES, 10,000 LBS 105 / 114 / USE CDFA THAT MEETS ALL
10.500 LBS 108 / 116 / ALTITUDE CONSTRAINTS LANDING ASSURED, CHECK GEAR 11,025 LBS 110 / 119 / DOWN, FLAPS 20° APPROACHING
FIX INBOUND, LANDING CHECKLIST * P, #OL COMPLETE A/S 120 KCAS MIN.
**DERIVED DECISION ALTITUDE (DDA) "CAUTION MDA A/S 120 KCAS MIN, (25%-30% TORQUE), WHEN USING CDFA METHOD, MISSED APPROACH MUST BE DDA. DESCENT BELOW MDA EXECUTED UPON REACHING POWER, PITCH TO 8°. MISSED APPROACH: GO-AROUND, MAX *VDP BEGIN CALCULATED DESCENT RATE A/S 120 KCAS MIN.
DURING MISSED APPROACH CONTINUE WITH TWO (APPROX 50% TORQUE)
NOT AUTHORIZED APPROACH PROFILE ENGINE MISSED
FINAL CHECK *VDP CHECK FINAL LANDING CONFIGURATION
VISUAL DESCENT POINT CONSTRUCTED WITH A AN APPROACH THEN POWER LEVERS RETARD TO GROUND IDLE, CHECK BOTH TOUCHDOWN: POWER LEVERS RETARD TO FLIGHT IDLE STOP, PROPS BETA. REVERSE AND BRAKES AS REQUIRED.
VDP SHOULD HAVE THE
AIRCRAFT CROSS THE
MDA AT OR BEYOND THE VDP.
A-59
Appendix A Figure A-26 NOTE MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
ONE ENGINE INOPERATIVE STRAIGHT-IN NONPRECISION APPROACH
EITHER THIS
PROCEDURE, OR ALTERNATELY PROFILE A/S 140KCAS (130 KCAS MIN), (50%-60% TORQUE), A-26a MUST BE FLAPS 5°. DESCEND 500 FPM TO PROCEDURE DEMONSTRATED. TURN ALTITUDE OR OTHER APPROACH SEGMENT
ALTITUDE COMPLETE DESCENT AND APPROACH FLAPS 5°, 140 KCAS CHECKLISTS. A/S 150 KCAS (140 KCAS (130 KCAS MIN), (MARQ, N) MIN. 135 KCAS (SOL, P) MIN). (50%-60% TORQUE) REVIEW APPROACH PLATE. RADIOS:
TUNE & IDENTIFY. CHECK FINAL
APPROACH FIX ALTITUDE, MARKER RECEIVER "ON" IF REQUIRED.
*VDP (130 KCAS MIN), A/S 140 KCAS VISUAL DESCENT POINT (50%-60% TORQUE).
AN APPROACH MISSED APPROACH: FLAPS 50
CONSTRUCTED WITH A CONTINUE WITH ENGINE
VDP SHOULD HAVE THE OUT MISSED APPROACH
AIRCRAFT CROSS THE PROFILE MDA ATOR BEYOND THE VDP. *VDP (20%-30% TORQUE), 800-1000 FPM DESCENT A/S140 KCAS (130 KCAS MIN), WARNING MAP A/S140 KCAS (130 KCAS MIN), (50%-60% TORQUE)
DO NOT ATTEMPT A
GO-AROUND WITH
GEAR DOWN BELOW WHEN RUNWAY IN SIGHT, LANDING ASSURED, GEAR DOWN, FLAPS 400' AGL OR AFTER 20P, SLOWING TO CROSS THRESHOLD AT 20° FLAPS ARE 110 KCAS (MARQ, N), 105 KCAS (SOL, P).
SELECTED. BEFORE LANDING CHECKLIST COMPLETE
CAUTION
CAUTION FINAL CHECK DO NOT USE SINGLE CHECK FINAL LANDING CONFIGURATION GEAR EXTENSION TIME. APPROXIMATELY ENGINE REVERSE 17 SECONDS MARQ, N, THRUST WITH THE 15 SECONDS SOL, P.
LEVER ABOVE FLIGHT SIMULATED FAILED ENGINE POWER IDLE. TOUCHDOWN, OPERATING ENGINE POWER LEVER SLOWLY RETARD TO FLIGHT IDLE STOP. THEN POWER LEVER GROUND IDLE, CHECK PROP BETA. REVERSE AND BRAKES AS REQUIRED.
A-60
Appendix A Figure A-26a MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
ONE ENGINE INOPERATIVE STRAIGHT-IN NONPRECISION APPROACH **OPTIONAL USE OF CONTINUOUS DESCENT FINAL APPROACH (CDFA) NOTE A/S 140 KCAS (130 KCAS MIN), (50%-60% TORQUE), EITHER THIS PROCEDURE, OR FLAPS 5°. DESCEND 500 FPM TO PROCEDURE ALTERNATELY PROFILE A-26 TURN ALTITUDE OR OTHER APPROACH SEGMENT MUST BE DEMONSTRATED. ALTITUDE FLAPS 5°, 140 KCAS (130 KCAS MIN), COMPLETE DESCENT AND APPROACH (50%-60% TORQUE) CHECKLISTS. A/S 150 KCAS (140 KCAS (MARQ, N) MIN. 135 KCAS (SOL) MIN).
REVIEW APPROACH PLATE. RADIOS: TUNE & IDENTIFY. CHECK FINAL APPROACH FIX CROSSING ALTITUDE, MARKER RECEIVER "ON IF REQUIRED,. **CALCULATE VDA A/S 140 KCAS (130 KCAS MIN.)
*VDP CAUTION - STEPDOWN FIXES (50%-60% TORQUE), FLAPS 5°.
CONSTRUCTED WITH A VDP AIRCRAFT CROSS THE MDA VISUAL DESCENT POINT SHOULD HAVE THE AN APPROACH **DURING ALL APPROACHES, USE CDFA THAT MEETS ALL ALTITUDE CONSTRAINTS LANDING ASSURED, CHECK GEAR INBOUND, LANDING CHECKLIST COMPLETE A/S 120 KCAS MIN. DOWN, APPROACHING FIX AT OR BEYOND THE VDP. **DERIVED DECISION ALTITUDE (DDA) A/S140 KCAS (130 KCAS MIN) (20%-30% TORQUE),
MDA BEGIN CALCULATED DESCENT RATE AT FAF
WARNING DO NOT ATTEMPT A MISSED APPROACH: *VDP
GO-AROUND WITH CONTINUE WITH GEAR DOWN BELOW 400' AGL OR AFTER 20° FLAPS ARE MISSED APPROACH ENGINE OUT PROFILE FINAL CHECK. FLAPS 20°, CHECK FINAL LANDING CONFIGURATION. SLOWING TO CROSS THRESHOLD AT 110 KCAS (MARQ, N), 105 SELECTED BEFORE LANDING CHECKLIST COMPLETE KCAS (SOL, P).
CAUTION TOUCHDOWN, OPERATING ENGINE POWER LEVER SLOWLY RETARD TO FLIGHT IDLE STOP. THEN POWER LEVER GROUND IDLE, CHECK DO NOT USE SINGLE PROP BETA. REVERSE AND BRAKES AS REQUIRED.
ENGINE REVERSE THRUST WITH THE *CAUTION