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
SIMULATED FAILED
ENGINE POWER WHEN USING CDFA METHOD, MISSED
LEVER ABOVE FLIGHT APPROACH MUST BE EXECUTED UPON IDLE REACHING DDA. DESCENT BELOW MDA
DURING MISSED APPROACH NOT
AUTHORIZED A-01
Appendix A Figure A-27 MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A)
CIRCLING APPROACH AT WEATHER MINIMUMS COMPLETE DESCENT AND APPROACH CHECKLISTS. A/S 150 KCAS (140 KCAS (MARQ, N), MIN. (135 KCAS SOL, P) MIN). PREVIEW APPROACH PLATE. RADIOS: TUNE & IDENTIFY. CHECK FINAL APPROACH FIX CROSSING ALTITUDE, MARKER RECEVER "ON IF REQUIRED CAT C 121 - 140 KCAS 1.7NM CATD 141 - 165 KCAS 2.3NM FROM APPROACH:
GEAR DOWN, FLAPS 5°, A/S 140 KCAS
TOUCHDOWN, RETARD POWER LEVERS TO FLIGHT MISSED APPROACH: IDLE STOP, THEN POWER LEVERS RETARD TO GO-AROUND, MAX GROUND IDLE, CHECK BOTH PROPS BETA.
POWER, PITCH TO 8°. REVERSE AND BRAKES AS REQUIRED.
CONTINUE WITH TWO NDA
ENGINE MISSED APPROACH PROFILE THRESHOLD:
(20% TORQUE), Vref A/S 140 KCAS (130 KCAS MIN). AS REQUIRED TO MAINTAIN CAT CORD CHECK SINK RATE 500-600 FPM (APPROX 50% TORQUE), NOT
BELOW CIRCLING MINIMUM DESCENT ALTITUDE FINAL CHECK. FLAPS 20P OR 40° CHECK
FINAL LANDING CONFIGURATION.
LANDING APPROACH SPEEDS - Vref 1.3 Vs1 1.5 Vs1 CAT C OR D TO MAINTAIN AS REQUIRED *MAX BANK 30° SLOWING TO Vref WEIGHT FLAPS 20° FLAPS 40° A/S 120 KCAS MIN, 7,500 LBS / 96 * / 99 * (20%-25% TORQUE), 8,000 LBS / 99 * /102 * 500-600 FPM 8,500 LBS 99 / 102 * 105 /106 * DESCENT 9,000 LBS 100 / 105 * 108 /109 * 9,500 LBS 102 / 108* 111/112 * 9,955 LBS / 111* /115 * 10,000 LBS 105 / 114 / LANDING ASSURED, DO NOT DESCEND 10,500 LBS 108 / 116 / CHECK GEAR DOWN, UNTIL WITHIN 30° OF 11,025 LBS 110 / 119 / FLAPS 20° COMPLETE RUNWAY CENTERLINE + P. BOL LANDING CHECKLIST A-62
Appendix A Figure A-28
WARNING MU-2B MARQUISE (-60), SOLITAIRE (-40), N (-36A), P (-26A) DO NOT USE CDFA APPROACH
ONE ENGINE INOPERATIVE CIRCLING APPROACH AT WEATHER MINIMUMS PROCEDURES DURING ENGINE
OUT CIRCLING APPROACH
COMPLETE DESCENT AND PROCEDURES CAT C 121 - 140 KCAS 1.7NM APPROACH CHECKLISTS.
CAT D 141 - 165 KCAS 2.3NM ** NOTE: ENGINE OUT CIRCLING
APPROACH SHOULD BE FLOWN WITH 5° FLAPS AND GEAR UP. WHEN MISSED APPROACH: FROM APPROACH: LANDING ASSURED, GEAR DOWN, CONTINUE WITH ENGINE OUT GEAR UP, FLAPS 5°, A/S 140 KCAS A/S 110 KCAS (MARQ, N). FLAPS 20°, SLOWING TO MISSED APPROACH A/S 105 KCAS (SOL, P).
PROFILE TOUCHDOWN. OPERATING ENGINE POWER LEVER SLOWLY RETARD TO CAUTION FLIGHT IDLE STOP, THEN POWER LEVER TO GROUND IDLE. CHECK PROP BETA. REVERSE AND BRAKES AS REQUIRED
ANTICIPATE SWERVE
TOWARD OPERATING ENGINE WHEN ENTERING BETA THRESHOLD FLAPS 20°, AS RAN TAN A/S 110 KCAS (MARQ, N). 105 KCAS (SOL, P).
A/S 140 KCAS (130 KCAS MIN). CAT C OR D CHECK SINK RATE (APPROX 70% TORQUE), 500-600 FPM
MINIMUM DESCENT ALTITUDE FINAL CHECK. FLAPS 20°,
CHECK FINAL LANDING
CONFIGURATION CAT C OR D TO MAINTAIN AS REQUIRED • MAX BANK 30° COMPLETE LANDING A/S 125 KCAS MIN. CHECKLIST
CAUTION WARNING
DO NOT USE SINGLE DO NOT ATTEMPT A CHECK DESCENT ENGINE POWER LEVER ABOVE FLIGHT IDLE.. SIMULATED FAILED THRUST WITH THE ENGINE REVERSE GEAR DOWN BELOW 400' AGL OR AFTER GO-AROUND WITH 20° FLAPS ARE SELECTED. CHECK FLAPS 5°, DONOT DESCEND UNTIL WITHIN 30° OF RUNWAY CENTERLINE DOWN, CHECK SINK PROFILE, LANDING RATE 500-600 FPM ASSURED, GEAR A-63
Appendix A Figure B-1 PRIOR TO TAKEOFF, CONSULT THE "WEIGHT FOR POSITIVE GRADIENT AFTER LIFTOFF® AND "SINGLE ENGINE RATE OF CLIMB® CHARTS FOR THE TAKEOFF FLAP SETTING SELECTED.
MU-2B J (-35), K (-25), L (-36), M(-26) NORMAL TAKE-OFF, 5° OR 20° FLAPS A/S 155 KCAS (J, L), 150 KCAS (K, M), MIN
TAKE OFF SPEEDS
AFTER GEAR IS FULLY RETRACTED, IF FOR ROTATE SPEEDS SEE FLAPS 20° ADJUST PITCH TO TABULAR CHART ON ACCELERATE. 130 KCAS (K, MOD S/R10)(K, COMPLETE AFTER T/O REVERSE SIDE OF NOT MOD S/R10), 140 KCAS (J, L, M) AND CLIMB CHECKLIST PROFILE. RETRACT FLAPS TO 5°. INCREASE PITCH TO APPROX. 10°, THEN FLAPS UP.
NORMAL PITCH.
APPROX 8°- FLAPS 20° ACCELERATE TO APPROX 10-12° -FLAPS 5° DESIRED CLIMB SPEED
POS RATE, NO RUNWAY REMAINING FOR LANDING, GEAR UP. IF 20° FLAPS 113 KCAS MIN. IF 5° FLAPS 120 KCAS (J, L) 125 KCAS (K, M) MIN * TORQUE 90% OR 600° EGT / 875° ITT,
WHICHEVER OCCURS FIRST. BETA LIGHTS VR - ROTATE 13° OUT. RELEASE BRAKES. RAM RISE WILL CAUSE MAX NOSE UP PITCH
TORQUE OR TEMP TO
RISE TO MAXIMUM
TAKEOFF POWER DURING TAKEOFF ROLL. * NOTE: IF RUNWAY LENGTH OR OBSTACLE CLEARANCE IS
CRITICAL, SET POWER TO
TORQUE OR TEMP MAXIMUM,
WHICHEVER OCCURS FIRST
RETARD POWER LEVERS AS
REQUIRED TO MAINTAIN
MAXIMUM ALLOWABLE TORQUE OR TEMP.
A-64
Appendix А Figure B-1a
TAKE OFF SPEEDS ROTATE FLAPS 5° K 11,575 LBS 11,000 LBS 10,800 LBS 10,470 LBS 10,000 LBS 9,920 LBS 108 9,500 LBS 107 9,000 LBS 106 8,000 LBS 104 7,500 LBS 102 FLAPS 20° K M 11,575 LBS 105 11,000 LBS 103 10,800 LBS 105 10,470 LBS 103 10,000 LBS 102 102 100 9,920 LBS 102 9,500 LBS 101 101 101 100 9,000 LBS 100 100 100 100
8.000 LBS 99 99 100 7 500 L RS 98 A-65
Appendix A Figure B-2 MU-2B J (-35), K (-25), L (-36), M(-26) TAKE-OFF ENGINE FAILURE - FLAPS 5° OR 20° PRIOR TO TAKEOFF, CONSULT THE "WEIGHT
FOR POSITIVE GRADIENT AFTER LIFTOFF AND *SINGLE ENGINE RATE OF CLIMB® CHARTS FOR THE TAKEOFF FLAP SETTING SELECTED.
J, K, L, M APPROX 300-400 FEET (OBSTRUCTION CLEARANCE). IF FLAPS 20° ADJUST PITCH TO ACCELERATE. 130 KCAS (K, MOD S/R10) (K, NOT MOD S/R10), 140 KCAS (J, L, M), FLAPS 5° FLAP SETTING UP 20° 5° Vxse KCAS) 140 / 135 * 130 / 130 * 125 / 125 * Vvse (KCAS) 150 / 150 * 135 / 130 * 140 / 140 * COMPLETE AFTER TAKE-OFF AND A/S 150 KCAS.
ENGINE SHUTDOWN *K, M CHECKLIST PITCH TO MAINTAIN Vxse MIN, APPROX 8° PITCH, A/S 150 KCAS MIN FLAPS 20°, APPROX 10-12° PITCH, FLAPS 5° FLAPS UP
MAINTAIN DIRECTIONAL CONTROL WITH RUDDER AND MINIMUM SPOILER. FAILED ENGINE - CONDITION LEVER. EMERGENCY STOP: POWER LEVER, TAKE OFF **, TRIM AIRCRAFT
POSITIVE RATE, NO RUNWAY REMAINING FOR LANDING, GEAR UP. IF 20° FLAPS 113 KCAS MIN. IF 5° FLAPS 120 KCAS (J, L) MIN, 125 KCAS (K, M) MIN
MAKE NORMAL T/O ** IF SUFFICIENT RUNWAY CAUTION REMAINS, OR UNABLE TO CLIMB:
GEAR DOWN, REDUCE POWER TO FAILURE (NOT LESS SIMULATED ENGINE THAN 200FT AGL) A/S APPROPRIATE FOR WEIGHT, 105KCAS (J, L), 100KCAS (K, M). LAND STRAIGHT AHEAD USING A-66