REFERENCE ONLY - CenTex Aerospace

checklists herein match the basic POH/AFM format for Super King Air 350 and 360 series airplanes. DESCRIPTIVE DATA MAXIMUM CERTIFICATED WEIGHTS Maximum Ramp Weight .......................................................................... 16,050 pounds Maximum Takeoff Weight ....................................................................... 15,950 pounds Maximum Landing Weight ....................................................................... 15,000 pounds SPECIFIC LOADINGS Wing Loading: 51.5 pounds per square foot (251.3 kg per square meter) Power Loading: 7.60 pounds per shaft horsepower REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 1 AIRPLANE FLIGHT MANUAL SUPPLEMENT GENERAL FAA APPROVED APRIL 2023 1-3 COMPATIBLE MODIFICATIONS The following STC-approved modifications have been found to be compatible with the Halo 350 Increased Gross Weight conversion: 1. SA11142SC, CenTex Aerospace Saddle Tanks 2. SA5151NM, Raisbeck Engineering Dual Aft Body Strakes 3. SA4175NM, Raisbeck Engineering MLG Doors 4. SA5152NM, Raisbeck Engineering Nacelle Wing Lockers 5. SA3683NM, Raisbeck Engineering Exhaust Stack Fairings 6. SA380CH, Parker Cleveland Nose Wheel 7. SA03275CH, Advent Aircraft Systems Antiskid Brake System 8. SA2671CE, Aviation Fabricators Stretcher on Seat Rails 9. SA4745NM, LifePort Patient Loading and Support System 10. SA00273WI, LifePort Stretcher, Patient Loading and Support System 11. SA00882CH, Spectrum Aeromed Air Ambulance Conversion 12. SA1129GL, Aero Medical Products Air Ambulance Stretcher 13. SA01496CH, Med-Pac Air Ambulance Conversion 14. SA01177WI-D, Hawker Beechcraft Installation of Pro Line 21 Avionics 15. SA01267WI-D, Rockwell Collins Installation of Pro Line 21 Avionics 16. SA01784WI, Rockwell Collins Installation of Pro Line Fusion Avionics 17. SA01535WI-D, Garmin International Installation of G1000 Avionics 18. SA10478SC, Hawker Beechcraft Services Flight Data Recorder 19. SA02658LA, Blackhawk Modifications PT6A-67A Engines 20. SA03525NY, MT-Propeller Composite 5-Blade Propellers 21. SA00400BO, IS&S Autothrottle System It is up to the installer to determine whether any other STC-approved modifications are compatible with the Halo 350 Increased Gross Weight conversion. REFERENCE ONLY SECTION 1 CENTEX AEROSPACE AFM 051-1 GENERAL AIRPLANE FLIGHT MANUAL SUPPLEMENT 1-4 APRIL 2023 FAA APPROVED THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS FAA APPROVED APRIL 2023 2-1 SECTION 2 LIMITATIONS TABLE OF CONTENTS SUBJECT PAGE AIRSPEED LIMITATIONS .................................................................................. 2-3 AIRSPEED INDICATOR DISPLAY - PRO LINE 21/FUSION ................................... 2-4 AIRSPEED INDICATOR MARKINGS (NON-PRO LINE) ........................................ 2-5 POWER PLANT LIMITATIONS .......................................................................... 2-6 WEIGHT LIMITS ............................................................................................... 2-6 CENTER-OF-GRAVITY LIMITS AFT LIMITS .............................................................................................. 2-6 FORWARD LIMITS ................................................................................... 2-6 FLIGHT LOAD FACTOR LIMITS ......................................................................... 2-7 ICING LIMITATIONS ......................................................................................... 2-7 STRUCTURAL LIMITATIONS ............................................................................. 2-7 PLACARDS ....................................................................................................... 2-7 KINDS OF OPERATIONS ................................................................................... 2-8 KINDS OF OPERATIONS EQUIPMENT LIST ....................................................... 2-8 NOTE See the basic POH/AFM for other Limitations.REFERENCE ONLY SECTION 2 CENTEX AEROSPACE AFM 051-1 LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT 2-2 APRIL 2023 FAA APPROVED The limitations shown in this section are approved by the Federal Aviation Administration and must be observed while operating Super King Air 350, 350C, 360, and 360C airplanes modified by the CenTex Aerospace Halo 350 Increased Gross Weight conversion. The Halo 350 conversion approves an increase in the maximum takeoff weight from 15,000 pounds to 15,950 pounds. Refer to the basic POH/AFM for limitations not contained in this section. REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS FAA APPROVED APRIL 2023 2-3 AIRSPEED LIMITATIONS SPEED KCAS KIAS REMARKS Maneuvering Speed (VA) 179 179 Do not make full or abrupt control movements above this speed. Maximum Flap Extension/Extended Speed (VFE) Approach Full Down 200 155 202 158 Do not extend flaps or operate with flaps extended above these speeds. Maximum Landing Gear Operating Speed (VLO ) Extension Retraction 182 164 182 164 Do not extend or retract landing gear above these speeds. Maximum Landing Gear Extended Speed (VLE) 182 182 Do not exceed this speed with landing gear extended. Air Minimum Control Speed (VMCA) Propeller Feathered Flaps Up Flaps Approach 103 99 101 98 These are the lowest airspeeds at which the airplane is directionally controllable when one engine suddenly becomes inoperative with autofeather armed and the other engine at takeoff power. Maximum Operating Speed (VMO) Sea Level to 24,000 feet 24,000 to 35,000 feet 245 245-192* 245 245-192* These speeds may not be deliberately exceeded in any flight regime. *0.58 Mach * The indicated airspeed decreases with altitude to maintain a constant Mach number of 0.58. REFERENCE ONLY REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS FAA APPROVED APRIL 2023 2-5 AIRSPEED INDICATOR MARKINGS (NON-PRO LINE) MARKING OR RANGE KIAS VALUE OR RANGE SIGNIFICANCE Red Line 101 Air Minimum Control Speed (VMCA) White Arc 82 to 158 Full-flap Operating Range Wide White Arc 82 to 99 Lower Limit is the Stalling Speed (VSO) at maximum weight with Flaps Down and idle power. Narrow White Arc 99 to 158 Lower Limit is Stalling Speed (VS) at maximum weight with Flaps Up and idle power. Upper Limit is the maximum speed permissible with flaps extended beyond Approach. White Triangle 202 Maximum Speed with Approach Flaps. Blue Line 135 One-Engine-Inoperative Best Rate-of- Climb Speed Red Pointer (VMO) Sea Level 24,000 feet 24,000 35,000 feet 245 245 - 192* Maximum Operating Speed These speeds may not be deliberately exceeded in any flight regime. * The indicated airspeed decreases with altitude to maintain a constant Mach number of 0.58. REFERENCE ONLY SECTION 2 CENTEX AEROSPACE AFM 051-1 LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT 2-6 APRIL 2023 FAA APPROVED POWER PLANT LIMITATIONS ENGINE MODEL NUMBER PT6A-60A or PT6A-67A ENGINE OPERATING LIMITS Takeoff & Max Continuous Power 1050 SHP 100% Torque (3244 LB-FT) 1700 RPM WEIGHT LIMITS Maximum Ramp Weight ...........................................................16,050 pounds (7280 kg) Maximum Take-off Weight .......................................................15,950 pounds (7235 kg) or as limited by the following Maximum Takeoff Weight graph Maximum Allowed Takeoff Weight - Limited by Brake Energy graph Maximum Tire Speed During Takeoff graph Takeoff Speeds and Field Lengths table For 14 CFR Part 135 Operations: Take-off Flight Path requirements to 1500 feet AGL. Service Ceiling - One Engine Inoperative graph Maximum Landing Weight ........................................................15,000 pounds (6804 kg) or as limited by the following Maximum Landing Weight graph Landing Distance graph NOTE See Section 5, PERFORMANCE for the above tables and graphs. Maximum Zero Fuel Weight .....................................................12,500 pounds (5670 kg) CENTER OF GRAVITY LIMITS AFT LIMITS 208.0 inches (5283 mm) aft of datum at 15,000 pounds (6804 kg) or less, with a straight- line variation to 207.6 inches (5273 mm) aft of datum at 15,950 pounds (7235 kg). FORWARD LIMITS 191.4 inches (4861 mm) aft of datum at 11,800 pounds (5352 kg) or less, with a straight- line variation to 201.8 inches (5126 mm) aft of datum at 15,950 pounds (7235 kg). REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS FAA APPROVED APRIL 2023 2-7 FLIGHT LOAD FACTOR LIMITS FLAPS UP FLAPS DOWN 0.0 g ICING LIMITATIONS Minimum Airspeed for Sustained Icing Flight Weight greater than 15,000 pounds .............................................................150 knots Weight 15,000 pounds or less ......................................................................140 knots Sustained flight in icing conditions with flaps extended is prohibited except for approach and landings. STRUCTURAL LIMITATIONS Refer to the Beechcraft Super King Air B300/B300C Airworthiness Limitations Manual and the CenTex Aerospace Halo 350 Instructions for Continued Airworthiness Manual. PLACARDS On overhead panel in : MAXIMUM IAS KNOTS GR EXTENSION 182 GR RETRACT 164 GR EXTENDED 182 APPROACH FLAP 202 FULL DN FLAP 158 MANEUVERING 179 REFERENCE ONLY SECTION 2 CENTEX AEROSPACE AFM 051-1 LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT 2-8 APRIL 2023 FAA APPROVED KINDS OF OPERATIONS The Models B300 and B300C modified with the Halo 350 conversion are approved for the following types of operations when the required equipment, as shown in the KINDS OF OPERATIONS EQUIPMENT LIST, is installed and operational. 1. VFR Day 2. VFR Night 3. IFR Day 4. IFR Night 5. Icing Conditions KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR, day or night IFR, and icing conditions when the required systems and equipment are installed and operable. The following equipment list identifies the systems and equipment upon which type certification for each kind of operation was predicated. The systems and equipment listed must be installed and operable for the particular kind of operation indicated unless: 1. The airplane is approved to be operated in accordance with a current Minimum Equipment List (MEL) approved by the FAA. or; 2. Approved Airplane Flight Manual for the inoperative state of the listed system or equipment and all limitations are complied with. Numbers in the Kinds of Operations Equipment List refer to quantities required to be operative for the specified condition. The list does not include all equipment that may be required by specific operating rules. It also does not include components obviously required for the airplane to be airworthy, such as wings, empennage, engine, etc. Refer to the basic POH/AFM for the basic equipment list. The following equipment list identifies equipment installed as part of the Halo 350 conversion. REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS FAA APPROVED APRIL 2023 2-9 VFR DAY VFR NIGHT SYSTEM and/or EQUIPMENT IFR DAY IFR NIGHT ICING CONDITIONS REMARKS FLIGHT CONTROLS (Add the following systems) 7. Stall Warning - Ice Mode 0 0 0 0 0 Note 1 8. Takeoff Trim Warning (for elevator trim) 0 0 0 0 0 Note 2 NOTES: 1. Stall Warning - Ice Mode equipment is not required equipment. 2. Takeoff Trim Warning equipment is not required equipment. REFERENCE ONLY SECTION 2 CENTEX AEROSPACE AFM 051-1 LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT 2-10 APRIL 2023 FAA APPROVED THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 3 AIRPLANE FLIGHT MANUAL SUPPLEMENT EMERGENCY PROCEDURES FAA APPROVED APRIL 2023 3-1 SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS SUBJECT PAGE EMERGENCY AIRSPEEDS ................................................................................. 3-2 ENGINE FAILURE DURING TAKEOFF (AT OR ABOVE V1) TAKEOFF CONTINUED ................................................................................. 3-2 EMERGENCY DESCENT .................................................................................... 3-3 ELECTRICAL DUAL GENERATOR FAILURE [L DC GEN] & [R DC GEN] OR [L-R DC Generator] ........................................................................ 3-3 LOAD MANAGEMENT TABLE ................................................................... 3-3 ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) (IF INSTALLED).............................................................................. 3-3 TERRAIN AWARENESS AND WARNING SYSTEM PLUS (TAWS+) (IF INSTALLED) .............................................................................. 3-3 NOTE See the basic POH/AFM for other Emergency Procedures. REFERENCE ONLY SECTION 3 CENTEX AEROSPACE AFM 051-1 EMERGENCY PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 3-2 APRIL 2023 FAA APPROVED All airspeeds quoted in this section are indicated airspeeds (IAS) and assume zero instrument error. EMERGENCY AIRSPEEDS (15,950 LBS (7235 KG)) One-Engine Inoperative Best Angle-of-Climb (VXSE) ................................... *135 Knots One-Engine Inoperative Best Rate-of-Climb (VYSE) ..................................... *135 Knots One-Engine-Inoperative Enroute Climb (VENR) ........................................... *135 Knots Air Minimum Control Speed (VMCA): Flaps Up ............................................................................................... 101 Knots Flaps Approach ...................................................................................... 98 Knots Emergency Descent ..................................................................................... 182 Knots Maximum Range Glide ................................................................................. 135 Knots NOTE *125 Knots when the basic POH/AFM performance data is being followed. ENGINE FAILURE DURING TAKEOFF (AT OR ABOVE V1) - TAKEOFF CONTINUED 1. VR Speed ...................................................... ROTATE TO APPROXIMATELY 10° PITCH ATTITUDE 2. Landing Gear (when positive climb established) .....................................UP 3. Airspeed ................................................... V2 (MAINTAIN TO 400 FEET AGL) 4. Propeller Inoperative Engine ......................................... VERIFY FEATHERED Do not retard the failed engine power lever until the Autofeather system has completely feathered the propeller and propeller rotation has stopped. To do so will deactivate the autofeather circuit and prevent automatic feathering. 5. Airspeed (at 400 Feet AGL minimum) .................... INCREASE TO *135 KNOTS *125 KNOTS when the basic POH/AFM performance data is being followed. 6. Flaps ............................................................................................................. UP 7. Climb to 1,500 Feet AGL, then accomplish the following cleanup procedures on the inoperative engine: a. Condition Lever .................................................................. FUEL CUT OFF b. Propeller Lever ........................................................................... FEATHER c. Firewall Fuel Valve ......................................................................... CLOSE [EXTINGUISHER PUSH] & [CLOSED] - ILLUMINATED d. Generator ........................................................................................... OFF e. Engine Auto Ignition ........................................................................... OFF 8. Autofeather................................................................................................ OFF 9. Brake Deice (if installed) ............................................................................ OFF 10. Electrical Load .................................................................................. MONITOR WARNING REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 3 AIRPLANE FLIGHT MANUAL SUPPLEMENT EMERGENCY PROCEDURES FAA APPROVED APRIL 2023 3-3 EMERGENCY DESCENT 1. Power Levers ....................................................................................... IDLE 2. Prop Levers .........................................................................FULL FORWARD 3. Flaps (202 knots maximum) ....................................................... APPROACH 4. Landing Gear (182 knots maximum) ..................................................DOWN 5. Airspeed ..................................................................182 KNOTS MAXIMUM ELECTRICAL DUAL GENERATOR FAILURE [L DC GEN] & [R DC GEN] OR [L-R DC Generator] Replace step 13 or 15: VREF + 25 ........................................................................................ DETERMINE Replace step 19 or 21: Airspeed ..................................................................................VREF + 25 KNOTS LOAD MANAGEMENT TABLE Add the following equipment: EQUIPMENT OPERATING TIME (Minutes) REDUCTION IN MAIN BATTERY DURATION (Minutes) Stall Warning Ice Mode Continuous* 2.2 *Only if Surface Deice is activated. Press Stall Warning Ice Mode annunciator switch to deactivate. No reduction in main battery duration when not in operation. ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) (IF INSTALLED) Replace step 3: 3. Pitch ............................................................................................ INCREASE Promptly and smoothly increase pitch towards an initial pitch attitude of 20° to 25°. Adjust as required to avoid continuous buffeting and/or stall warning. Adjust to maintain 135 KIAS. Replace step 5: 5. Continue climb at 135 KIAS until all visual and voice warnings cease and safe terrain clearance is assured. TERRAIN AWARENESS AND WARNING SYSTEM PLUS (TAWS+) (IF INSTALLED) Replace step 4: 4. Pitch ............................................................................................ INCREASE Promtly and smoothly increase pitch towards an initial pitch attitude of 20° to 25°. Adjust as required to avoid continuous buffeting and/or stall warning. Adjust to maintain 135 KIAS. Replace step 6: 6. Continue climb at 135 KIAS until all visual and voice warnings cease. REFERENCE ONLY SECTION 3 CENTEX AEROSPACE AFM 051-1 EMERGENCY PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 3-4 APRIL 2023 FAA APPROVED THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES FAA APPROVED APRIL 2023 3A-1 SECTION 3A ABNORMAL PROCEDURES TABLE OF CONTENTS SUBJECT PAGE LANDING FLAPS UP LANDING ............................................................................... 3A-2 ONE-ENGINE-INOPERATIVE APPROACH AND LANDING ........................ 3A-3 ONE-ENGINE-INOPERATIVE GO-AROUND ............................................. 3A-4 OVERWEIGHT LANDING ........................................................................ 3A-5 SYSTEMS STALL WARNING SYSTEM - ICE MODE .................................................. 3A-5 NOTE See the basic POH/AFM for other Abnormal Procedures. REFERENCE ONLY SECTION 3A CENTEX AEROSPACE AFM 051-1 ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 3A-2 APRIL 2023 FAA APPROVED LANDING FLAPS UP LANDING Refer to Section 5 of this supplement for Flaps Up Landing Distance and VREF. 1. Approach Speed (VREF + 25) ...............................................................CONFIRM 2. Pressurization ........................................................................................CHECK 3. Cabin Sign a. Standard Configuration ....................................................... NO SMK/FSB b. No Smoking Configuration ................................................................. FSB 4. Autofeather.............................................................................................. ARM 5. Flaps ............................................................................................................. UP Do not silence the landing gear warning horn, since the flap actuated portion of the landing gear warning system will not be actuated during a flaps up landing. 6. Flap Override (if equipped) ...................................................................SELECT NOTE On airplanes with TAWS+, if the FLAP OVRD switch/annunciator is deselected below 500 feet AGL, the ACTIVE annunciator will rearm after the airplane has landed or has climbed back to an altitude higher than 500 feet AGL. 7. Landing Gear ......................................................................................... DOWN 8. Exterior and Interior Lights .........................................................AS REQUIRED NOTE Under low visibility conditions, landing and taxi lights should be left off due to light reflections. 9. Radar ...........................................................................................AS REQUIRED 10. Environmental Bleed Air .......................................................................... LOW 11. Surface Deice ...................................................................CYCLE AS REQUIRED NOTE Prior to the landing approach, cycle the wing deice boots to shed as much residual ice as possible, regardless of the amount of ice remaining on the boots. Stall speeds can be expected to increase if ice is not shed from the deice boots. CAUTION REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES FAA APPROVED APRIL 2023 3A-3 NOTE If crosswind landing is anticipated, determine Crosswind Component from Section 5 in the basic POH/AFM. Immediately prior to touchdown, lower upwind wing and align the fuselage with the runway by use of rudder. During rollout, hold aileron control into the wind and maintain directional control with rudder and brakes. Use propeller reverse as desired. When Landing Assured: 12. Airspeed ..................................................................................VREF + 25 KNOTS 13. Yaw Damp .................................................................................................. OFF 14. Power Levers............................................................................................. IDLE 15. Propeller Levers ...................................................................... FULL FORWARD After Touchdown: 16. Power Levers.................................................. LIFT AND SELECT GROUND FINE 17. Brakes .........................................................................................AS REQUIRED ONE-ENGINE-INOPERATIVE APPROACH AND LANDING WEIGHT POUNDS VREF KNOTS 15,950 108 15,500 107 15,000 105 14,000 or less 104 1. Approach Speed, VREF ........................................................................ CONFIRM 2. Pressurization ........................................................................................ CHECK 3. Cabin Sign a. Standard Configuration ....................................................... NO SMK/FSB b. No Smoking Configuration ..................................................................FSB 4. Fuel Balance ........................................................................................... CHECK 5. Radar ...........................................................................................AS REQUIRED 6. Environmental Bleed Air ...........................................................................LOW If residual ice remains on wing boots: 7. Surface Deice ..........................................................................................CYCLE Approach Speed and Landing Distance ................ INCREASE VREF BY 15 KNOTS INCREASE LANDING DISTANCE BY 27 PERCENT (Refer to Section 5, Landing Distance - One Engine Inoperative - Flaps Down graph) NOTE Prior to the landing approach, cycle the wing deice boots to shed as much residual ice as possible, regardless of the amount of ice REFERENCE ONLY SECTION 3A CENTEX AEROSPACE AFM 051-1 ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 3A-4 APRIL 2023 FAA APPROVED remaining on the boots. Stall speeds can be expected to increase if ice is not shed from the deice boots. NOTE If crosswind landing is anticipated, determine Crosswind Component from Section 5 in the basic POH/AFM. Immediately prior to touchdown, lower upwind wing and align the fuselage with the runway. During rollout, hold aileron control into the wind and maintain directional control with rudder and brakes. 8. Flaps ............................................................................................... APPROACH 9. Landing Gear ......................................................................................... DOWN 10. Exterior and Interior Lights .........................................................AS REQUIRED 11. Prop Lever ............................................................................... FULL FORWARD 12. Airspeed ..................................................................................VREF + 10 KNOTS When it is Certain There is No Possibility of Go-Around: 13. Flaps ...................................................................................................... DOWN 14. Airspeed ..................................................................................................... VREF VREF + 15 KNOTS with ice on wing 15. Execute normal landing. Care must be exercised when using single-engine ground fine on surfaces with reduced traction. Do not use reverse thrust with one engine inoperative. NOTE Single engine landing distances may be greater than normal landing distance. Refer to Section 5, Landing Distance - One-Engine Inoperative - Flaps Down graph for single-engine landing distances. ONE-ENGINE-INOPERATIVE GO-AROUND 1. Power .........................................................................MAXIMUM ALLOWABLE 2. Landing Gear ................................................................................................ UP 3. Airspeed ................................................................. INCREASE TO *135 KNOTS 4. Flaps ............................................................................................................. UP NOTE *125 KNOTS when the basic POH/AFM performance data is being followed. --------------------- WARNING REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES FAA APPROVED APRIL 2023 3A-5 OVERWEIGHT LANDING WEIGHT POUNDS VREF KNOTS 15,950 108 15,500 107 15,000 105 When Landing Is Assured: 1. Flaps ...................................................................................................... DOWN 2. Airspeed ..................................................................................................... VREF 3. Yaw Damp .................................................................................................. OFF 4. Power Levers............................................................................................. IDLE 5. Propeller Levers ...................................................................... FULL FORWARD 6. Sink Rate .......................... TOUCHDOWN WITH NOMINAL OR LESS SINK RATE After Touchdown: 7. Power Levers.................................................. LIFT AND SELECT GROUND FINE 8. Brakes .........................................................................................AS REQUIRED NOTE An overweight landing is defined as any landing made when the airplane gross weight is greater than 15,000 pounds, which is the maximum landing weight limitation. When the airplane is landed at a gross weight above 15,000 pounds, before the next flight, the pilot should request that an inspection be performed in accordance with the Super King Air B300/B300C Maintenance Manual, Chapter 5-50- 00, Inspection After Hard or Overweight Landing. An overweight landing where the touchdown sink rate is nominal should not result in damage to the landing gear or airframe structure. SYSTEMS STALL WARNING SYSTEM - ICE MODE ICE MODE FAILS TO ACTIVATE IN FLIGHT 1. 2. Correct fault prior to next flight. ICE MODE FAILS TO DEACTIVATE IN FLIGHT 1. [STALL WARNING ICE MODE] Annunciator ................................................. ON 2. STALL WARN Circuit Breaker ...................................................................CYCLE 3. [STALL WARNING ICE MODE] Annunciator ................................................ OFF --------------------- REFERENCE ONLY SECTION 3A CENTEX AEROSPACE AFM 051-1 ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 3A-6 APRIL 2023 FAA APPROVED THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES FAA APPROVED APRIL 2023 4-1 SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS SUBJECT PAGE AIRSPEEDS FOR SAFE OPERATION .................................................................. 4-2 PROCEDURES BY FLIGHT PHASE BEFORE ENGINE STARTING ..................................................................... 4-3 BEFORE TAKEOFF (RUNUP) ..................................................................... 4-3 TAKEOFF.................................................................................................. 4-4 ROLLING TAKEOFF................................................................................... 4-4 CRUISE..................................................................................................... 4-4 BALKED LANDING .................................................................................... 4-5 OTHER PROCEDURES TAKEOFF TRIM WARNING TEST .............................................................. 4-5 ICING FLIGHT ........................................................................................... 4-5 PRACTICE LANDING GEAR MANUAL EXTENSION .................................... 4-6 OVERWEIGHT LANDING .......................................................................... 4-6 NOISE CHARACTERISTICS ........................................................................ 4-6 NOTE See the basic POH/AFM for other Normal Procedures. REFERENCE ONLY SECTION 4 CENTEX AEROSPACE AFM 051-1 NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 4-2 APRIL 2023 FAA APPROVED All airspeeds quoted in this section are indicated airspeeds (IAS) and assume zero instrument error. AIRSPEEDS FOR SAFE OPERATION Maximum Demonstrated Crosswind Component ......................................... 20 Knots Maximum Demonstrated Wind Components for Coupled Approaches Crosswind............................................................................................... 32 Knots Tailwind.................................................................................................. 14 Knots Two-Engine Best Angle-of-Climb (VX)........................................................... 135 Knots Two-Engine Best Rate-of-Climb (VY) ............................................................ 135 Knots Cruise Climb: Sea level to 35,000 feet ....................................................................... 135 Knots NOTE When the basic POH/AFM performance data is being followed, see the AIRSPEEDS FOR SAFE OPERATION in Section IV of the basic POH/AFM for Two Engine Best Angle of Climb (VX), Two Engine Best Rate of Climb (VY), and the Cruise Climb airspeeds. Maneuvering Speed (VA) .............................................................................. 179 Knots Turbulent Air Penetration ............................................................................ 170 Knots For turbulent air penetration, use an airspeed of 170 knots. Avoid over-action on power levers. Turn off autopilot altitude hold. Keep wings level, maintain attitude and avoid use of trim. Do not chase airspeed and altitude. Penetration should be at an altitude which provides adequate maneuvering margins when severe turbulence is encountered. Maximum Airspeed for Effective Windshield Anti-icing .............................. 226 Knots Intentional One-Engine-Inoperative Speed (VSSE) ........................................ 110 Knots Air Minimum Control Speed (VMCA): Flaps Up ............................................................................................... 101 Knots Flaps Approach ...................................................................................... 98 Knots CAUTION REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES FAA APPROVED APRIL 2023 4-3 PROCEDURES BY FLIGHT PHASE NOTE Refer to applicable Supplements for flight phase procedures for optional equipment installed in the airplane. The procedures below are required for airplanes modified by the Halo 350 conversion with Stall Warning Ice Mode equipment and Takeoff Trim Warning equipment. BEFORE ENGINE STARTING Add the following steps after the Battery Switch is ON for the Takeoff Trim Warning system. 1. Left Power Lever .....................ADVANCE TO AT LEAST 50% OF LEVER TRAVEL 2. Autofeather Switch ...................................................................................ARM 3. Pitch Trim Control .................................. MOVE OUTSIDE OF TAKEOFF RANGE NOTE: Warning should activate when trim is outside of takeoff range. 4. Pitch Trim Control ................................................................ SET FOR TAKEOFF 5. Autofeather Switch .................................................................................... OFF 6. Left and Right Power Levers ..................................................................... IDLE NOTE See the Takeoff Trim Warning Test procedure below in Other Procedures. Takeoff Trim Warning is not a required function for the continued operation and safe flight of the airplane. Should the system fail to activate, the continuation of the flight is at t discretion. BEFORE TAKEOFF (RUNUP) Add the following steps after the Surface Deice System check for the Stall Warning Ice Mode system. 1. [STALL WARNING ICE MODE] Annunciator ................................ ILLUMINATED 2. Stall Warning............................................................................................. TEST 3. [STALL WARNING ICE MODE] Annunciator .... PRESS (to select Normal Mode) NOTE Ice Mode is not a required function for the continued operation and safe flight of the airplane. Should the system fail to activate, the NOTE The stall warning system must be in the Normal Mode during takeoff and initial climb-out. If a takeoff is conducted with the stall warning system in the Ice Mode, a misleading stall warning following lift-off will likely occur. REFERENCE ONLY SECTION 4 CENTEX AEROSPACE AFM 051-1 NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 4-4 APRIL 2023 FAA APPROVED TAKEOFF Add the following information for the Takeoff Trim Warning system. Abort takeoff if the Takeoff Trim Warning horn sounds. ROLLING TAKEOFF Add the following information for the Takeoff Trim Warning system. Abort takeoff if the Takeoff Trim Warning horn sounds. CRUISE ICING CONDITIONS Replace WARNING: Due to distortion of the wing airfoil, an accumulation of one inch of ice on the leading edges can cause a loss in rate of climb of 500 FPM, a cruise speed reduction of up to 75 knots TAS, as well as a significant buffet and stall speed increase (up to 15 knots IAS). Even after cycling the deicing boots, the ice accumulation remaining on the boots and unprotected areas of the airplane can cause large performance losses. The aural stall warning system is equipped with an Ice Mode function to provide an accurate stall warning in icing conditions. If Ice Mode is inactive, the normal stall warning may not be accurate and should not be relied upon. However, with ice accumulations on the airplane, significant aerodynamic buffet will occur in advance of the stall. Maintain a comfortable margin of airspeed above the normal stall airspeed. In order to minimize ice accumulation on unprotected surfaces of the wing, maintain the following minimum airspeeds during operations in sustained icing conditions: Weight 15,000 pounds or less: maintain a minimum of 140 knots. Weight greater than 15,000 pounds: maintain a minimum of 150 knots. In the event of windshield icing, reduce airspeed to 226 knots or below. Prior to a landing approach, cycle the deicing boots to shed any accumulated ice. Add the following steps after Surface Deice is activated for the Stall Warning Ice Mode system: 11. [STALL WARNING ICE MODE] Annunciator ................................ ILLUMINATED When the wing is free of ice: 12. [STALL WARNING ICE MODE] Annunciator .... PRESS (to select Normal Mode) WARNING REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES FAA APPROVED APRIL 2023 4-5 BALKED LANDING 1. Power ......................................................................... MAXIMUM ALLOWABLE 2. Airspeed ................................................................................... MAINTAIN VREF (when clear of obstacles, establish a normal climb) 3. Flaps (at VREF + 10 knots) ................................................................ APPROACH 4. Landing Gear (when a positive climb is established) ................................... UP 5. Flaps (at *135 knots, minimum) .................................................................. UP *125 knots when the basic POH/AFM performance data is being followed. OTHER PROCEDURES TAKEOFF TRIM WARNING SYSTEM TEST Test the Takeoff Trim Warning system as part of the Before Starting Engine procedure. Place the AUTOFEATHER switch to ARM and advance the left power lever beyond the 87% to 89% N1 switch, which is typically set at approximately 40% of the power lever travel. Select a pitch trim setting that is outside of the takeoff range marked on the pitch trim position indicator in the nose up and the nose down directions. The warning should activate whenever the pitch trim is outside of the takeoff range. Should the system fail Refer to Section 7, SYSTEMS DESCRIPTION for more information. ICING FLIGHT Add the following information for the Stall Warning Ice Mode system: The aircraft stall warning system switches to Ice Mode whenever the surface deice system is activated. The illuminated [STALL WARNING ICE MODE] annunciator indicates the ICE MODE is selected and operating. Ice Mode remains active until the pilot presses the annunciator switch and the light extinguishes. The Ice Mode lift computer provides an elevated stall warning for flight in icing conditions. Refer to Section 7, SYSTEMS DESCRIPTION. The pilot response to a stall warning in Ice Mode should be the same as a stall warning in normal (non-icing) flight. Ice Mode is not a required function for the continued operation and safe flight of the airplane. Should the system fail to activate, the ABNORMAL PROCEDURES. REFERENCE ONLY SECTION 4 CENTEX AEROSPACE AFM 051-1 NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT 4-6 APRIL 2023 FAA APPROVED PRACTICE LANDING GEAR MANUAL EXTENSION 1. Airspeed .............................................................................BELOW 182 KNOTS 2. L ..................... PULL 3. Landing Gear Control ............................................................................ DOWN 4. Alternate Extension Handle .............................................................. UNSTOW 5. Alternate Extension Handle .......................................... PUMP UP AND DOWN (until [L], [R] & [NOSE] illuminate and further resistance is felt) 6. Alternate Extension Handle ................................................................... STOW NOTE Ensure the Extension Handle is in the full down position prior to placing the Extension Handle in the securing clip. OVERWEIGHT LANDING An overweight landing is defined as any landing made when the airplane gross weight is greater than 15,000 pounds, which is the maximum landing weight limitation. Refer to Section 3A, ABNORMAL PROCEDURES. If it becomes necessary to land the airplane at a gross weight above 15,000 pounds the pilot should request that an inspection be performed before the next flight in accordance with the Super King Air B300/B300C Maintenance Manual, Chapter 5-50-00, Inspection After Hard or Overweight Landing. An overweight landing where the touchdown sink rate is nominal should not result in damage to the landing gear or airframe structure. NOISE CHARACTERISTICS Approach to and departure from an airport should be made so as to avoid prolonged flight at low altitude near noise-sensitive areas. Avoidance of noise sensitive areas, if practical, is preferable to overflight at relatively low altitudes. For VFR operations over outdoor assemblies of persons, recreational and park areas, and other noise-sensitive areas, pilots should make every effort to fly not less than 2000 feet above the surface, weather permitting, even though flight at lower level may be consistent with the provisions of government regulations. NOTE The preceding recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions, or necessary to adequately exercise his duty to see and avoid other airplanes. The takeoff noise level established in compliance with 14 CFR Part 36, Appendix G and ICAO Annex 16, Chapter 10 is 81.45 dB(A). The limit is 88.0 dB(A). No determination has been made by the Federal Aviation Administration that the noise level of this airplane is, or should be, acceptable or unacceptable for operation at, into, or out of any airport. REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-1 SECTION 5 PERFORMANCE TABLE OF CONTENTS SUBJECT PAGE Introduction to Performance .......................................................................... 5-3 Airspeed Calibration - Normal System Takeoff Ground Roll ........................... 5-9 Airspeed Calibration - Normal System .......................................................... 5-10 Total Height Required - Pressure Altitude Conversion ................................. 5-11 Static Takeoff Power At 1700 RPM ............................................................... 5-12 Stall Speeds - Power Idle ............................................................................... 5-13 Maximum Takeoff Weight - Flaps Up ........................................................... 5-14 Maximum Tire Speed During Takeoff - Flaps Up........................................... 5-15 Maximum Allowed Takeoff Weight - Flaps Up Limited by Brake Energy ...... 5-16 Takeoff Speeds & Field Lengths - Flaps Up ................................................... 5-17 Takeoff Field Length Correction - Flaps Up ................................................... 5-33 Takeoff Decision Speed (V1) - Flaps Up ......................................................... 5-34 Net Takeoff Flight Path - First Segment - Flaps Up ....................................... 5-35 Net Takeoff Flight Path - Second Segment - Flaps Up ................................... 5-36 Horizontal Dist. From Ref. Zero to Third Segment Climb - Flaps Up ............. 5-37 Close-In Takeoff Flight Path - Flaps Up ......................................................... 5-38 Distant Takeoff Flight Path - Flaps Up ........................................................... 5-39 Net Takeoff Flight Path - Third Segment - Flaps Up ...................................... 5-40 Maximum Takeoff Weight - Flaps Approach................................................. 5-41 Maximum Tire Speed During Takeoff - Flaps Approach ................................ 5-42 Maximum Allowed Takeoff Weight - Flaps Appr. Limited by Brake Energy .. 5-43 Takeoff Speeds & Field Lengths - Flaps Approach ........................................ 5-45 Takeoff Field Length Correction - Flaps Approach ........................................ 5-59 Takeoff Decision Speed (V1) - Flaps Approach .............................................. 5-60 Net Takeoff Flight Path - First Segment - Flaps Approach............................. 5-61 Net Takeoff Flight Path - Second Segment - Flaps Approach ........................ 5-62 Horizontal Dist. From Ref. Zero to Third Seg. Climb - Flaps Approach .......... 5-63 Close-In Takeoff Flight Path - Flaps Approach .............................................. 5-64 Distant Takeoff Flight Path - Flaps Approach ................................................ 5-65 Net Takeoff Flight Path - Third Segment - Flaps Up ...................................... 5-66 Climb - One Engine Inoperative .................................................................... 5-67 Climb - Two Engines ...................................................................................... 5-68 Service Ceiling - One Engine Inoperative ...................................................... 5-69 Time, Fuel, and Distance to Climb ................................................................ 5-70 Maximum Cruise Power ................................................................................ 5-71 Normal Cruise Power .................................................................................... 5-72 Maximum Range Power ................................................................................ 5-73 One Engine Inoperative Maximum Cruise Power ......................................... 5-74 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-2 APRIL 2023 FAA APPROVED SECTION 5 PERFORMANCE TABLE OF CONTENTS (CONTINUED) SUBJECT PAGE Holding Time ................................................................................................. 5-75 Maximum Landing Weight - To Achieve Climb Requirements ...................... 5-76 Maximum Landing Weight - To Achieve Climb Requirements with Ice Accumulations Present ........................................................................ 5-77 Approach Climb Gradient.............................................................................. 5-78 Climb - Balked Landing .................................................................................. 5-79 Normal Landing Distance - Flaps Down ........................................................ 5-80 Landing Distance - Flaps Up .......................................................................... 5-81 Landing Distance - One Engine Inoperative - Flaps Down ............................. 5-82 NOTE See the basic POH/AFM for other Performance information. REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-3 INTRODUCTION TO PERFORMANCE REGULATORY COMPLIANCE Information in this section is presented for the purpose of compliance with the appropriate performance criteria and certification requirements of 14 CFR Part 23 when operating Super King Air 350, 350C, 360, and 360C airplanes modified by the CenTex Aerospace Halo 350 conversion at 15,950 pounds gross weight and below. Note that the Halo 350 conversion does nothing to affect the performance of the airplane except allow it to operate at a heavier takeoff weight, therefore, the performance data contained in the basic POH/AFM is still applicable for takeoff weights at and below 15,000 pounds gross weight. PERFORMANCE LIMITATIONS The maximum operating weights are limited by the following performance graphs or criteria, and compliance therewith is mandatory. FOR ALL 14 CFR PART 91 AND 14 CFR PART 135 OPERATIONS 1. Maximum Takeoff Weight to Achieve Takeoff Climb Requirements 2. Maximum Tire Speed During Takeoff 3. Maximum Allowed Takeoff Weight - Limited by Brake Energy 4. Takeoff Speeds & Field Lengths 5. Maximum Landing Weight to Achieve Climb Requirements 6. Normal Landing Distance - Flaps Down FOR 14 CFR PART 135 OPERATIONS ONLY 7. Service Ceiling - One Engine Inoperative 8. Takeoff Flight Path Requirements to 1500 feet AGL FLIGHT TEST PERFORMANCE CONDITIONS All performance in this manual is based on flight test data and the following conditions: 1. Power ratings include the installation, bleed air, and accessory losses. 2. Full temperature accountability within the operational limits for which the airplane is certified. NOTE Should ambient air temperature or altitude be below the lowest temperature or altitude shown on the performance charts, use the performance at the lowest value shown. 3. All takeoff and landing performance is based on a paved, dry runway.REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-4 APRIL 2023 FAA APPROVED 4. Runway or takeoff and landing performance was obtained using the following procedures and conditions: a. ONE-ENGINE-INOPERATIVE TAKEOFF (ACCELERATE-GO) 1) Static takeoff power was set. 2) The critical engine was shut down with the condition lever just prior to V1. The autofeather system was allowed to feather the inoperative engine propeller. 3) The acceleration was continued to VR and the airplane was rotated to an attitude of approximately 10° nose up. 4) The landing gear was retracted when a positive rate of climb was established. 5) V2 was attained by 35 feet AGL and maintained until 400 feet AGL. b. REJECTED TAKEOFF (ACCELERATE-STOP) 1) Static takeoff power was set. 2) The critical engine was shut down with the condition lever just prior to V1. 3) Both power levers were rapidly moved to the ground fine position in one continuous motion at V1. 4) Maximum braking was immediately initiated and maintained until the airplane came to a complete stop. c. ALL-ENGINES TAKEOFF 1) Static takeoff power was set. 2) The airplane was accelerated to VR and a positive rotation to approximately 1o nose up was made. 3) V35 was attained by 35 feet AGL and maintained until 400 feet AGL. 4) The landing gear was retracted when a positive rate of climb was established. d. LANDING 1) Power was set to maintain a 3° approach with the airspeed stabilized at VREF. 2) Both power levers were moved to the idle position when the airplane reached 50 feet AGL. 3) Ground fine was selected immediately upon touchdown. 4) Maximum braking was immediately initiated and maintained until the airplane came to a complete stop.REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-5 CONFIGURATIONS No. of Operating Engines Power Flap Setting Landing Gear 1st Segment Takeoff Climb 1 Takeoff Up or Approach Down 2nd Segment Takeoff Climb 1 Takeoff Up or Approach Up Horizontal Acceleration 1 Takeoff Up Up 3rd Segment Climb 1 Maximum Continuous Up Up Approach Climb 1 Takeoff Approach Up Balked Landing Climb 2 Takeoff Landing Down VARIABLE FACTORS AFFECTING PERFORMANCE Details of variables affecting performance are given with tables to which they apply. Assumptions which relate to all performance calculations, unless otherwise stated, are: 1. Cabin pressurized. 2. Humidity corrections to power have been applied according to the applicable regulations. 3. Winds, for which graphical correction information is presented on the charts, are to be taken as the tower winds (30 feet above runway surface). Factors have been applied as prescribed in the applicable regulations. In the tables, negative represents tailwind and positive represents headwind. ICING FLIGHT Degradations in performance were determined for selected conditions. This performance is shown for reference only and was determined under controlled conditions with the simulated ice shapes listed below attached to the airplane. These accumulations are 1. Leading edges of boots to simulate the ice that may accumulate up to the time the boots are activated by the pilot (i.e., one inch). 2. On the following unprotected surfaces to simulate the ice that may accumulate during a 45-minute holding condition in icing conditions defined by 14 CFR Part 25, Appendix C: a. Nose Radome b. Wing Center Sections Not Protected by Boots c. Wing Outer Panels Not Protected by Boots d. Vertical Stabilizer and Bullet e. Horizontal Stabilizer Not Protected by Boots REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-6 APRIL 2023 FAA APPROVED Actual performance degradations may be more or less than the values quoted herein, depending on the type and duration of the icing encounter. Refer to the icing notes on the following graphs and tables: 1. Stall Speeds - Power Idle 2. Maximum Cruise Power 3. Normal Cruise Power 4. Maximum Range Power 5. One Engine Inoperative Maximum Cruise Power 6. Holding Time 7. Maximum Landing Weight 8. Approach Climb Gradient 9. Climb - Balked Landing 10. Normal Landing Distance - Flaps Down 11. Landing Distance - Flaps Up 12. Landing Distance One Engine Inoperative - Flaps Down HOW TO USE GRAPHS 1. In addition to presenting the answer for a particular set of conditions, the example on a graph also presents the order in which the various scales on that graph should be used. For instance, if the first item in the example is OAT, then enter the graph at the existing OAT. 2. The reference lines indicate where to begin following the guidelines. Always project to the reference line first, then follow the guidelines to the next item by maintaining the same PROPORTIONAL DISTANCE between the guideline above and the guideline below the projected line. For instance, if the projected line intersects the reference line in the ratio of 30% down/70% up between the guidelines, then maintain this same 30%/ 70% relationship between the guidelines all the way to the next item. 3. The associated conditions define the specified conditions from which performance parameters have been determined. They are not intended to be used as instructions; however, performance values determined from charts can only be achieved if the specified conditions exist. 4. All airspeeds presented in this section are indicated airspeeds (IAS) unless otherwise noted, assume zero instrument error, and, with the exception of the stall speeds presented, were derived from calibrated airspeeds corrected per either the AIRSPEED CALIBRATION - NORMAL SYSTEM TAKEOFF GROUND ROLL graph or AIRSPEED CALIBRATION - NORMAL SYSTEM graph. REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-7 5. The full amount of usable fuel is available for all approved flight conditions. 6. Notes have been provided on various graphs and tables to approximate performance when using Engine Anti-ice-ON power. The effect will vary, depending upon airspeed and ambient conditions. At lower altitudes, where operation at or near the torque limit is possible, the effect of using Engine Anti-ice will be less, depending upon how much power can be recovered after the Engine Anti-ice has been turned ON. While in flight, if the power set before Engine Anti-ice activation can be achieved after activation without exceeding engine limitations, anti-ice effects will be negated. For all takeoff charts, during operation requiring Engine Anti-ice ON, the results read from the graphs will remain the same if the power per the STATIC TAKEOFF POWER At 1700 RPM graph can be set without exceeding engine limitations. 7. The MAXIMUM TAKEOFF WEIGHT TO ACHIEVE TAKEOFF CLIMB REQUIREMENTS graph presents the most restrictive maximum takeoff weight with: a. The airplane in the takeoff configuration, with the most critical center of gravity, the critical engine inoperative and its propeller feathered, and the remaining engine at maximum takeoff power, which: 1) With landing gear extended, will result in a steady gradient of climb, between lift-off and the point where the landing gear is retracted, that is measurably positive; and 2) With landing gear retracted, will result in a steady gradient of climb of 2 percent. b. The airplane in the enroute configuration at an altitude 1500 feet above the takeoff surface, with the critical engine inoperative, the remaining engine at maximum continuous power, and the most critical CG, which will result in a steady gradient of climb of 1.2 percent. 8. The MAXIMUM LANDING WEIGHT graph presents the most restrictive maximum landing weight which: a. With the airplane in the discontinued approach configuration (i.e., gear up and flaps approach) at normal approach speed, the critical engine inoperative, and the other engine at available takeoff power, will result in a steady gradient of climb of 2.1 percent; and b. With the landing gear extended, flaps extended, and both engines operating at takeoff power, will result in a steady gradient of climb of 3.3 percent at the most critical CG and the normal approach speed.REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-8 APRIL 2023 FAA APPROVED EXAMPLE CALCULATIONS The example calculations found in the basic POH/AFM can and should be followed as an example and guide to preflight planning. The performance graphs and tables present in this supplement are intended and therefore designed to display the applicable data in a similar manner as the corresponding graphs and tables contained in the basic POH/AFM. ------------------ REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-9 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-10 APRIL 2023 FAA APPROVED REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-11 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-12 APRIL 2023 FAA APPROVED REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-13 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-14 APRIL 2023 FAA APPROVED REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-15 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-16 APRIL 2023 FAA APPROVED REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-17 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP (AIR CONDITIONING AND BLEED AIR ON) ASSOCIATED CONDITIONS Power.............................. STATIC TAKEOFF POWER SET BEFORE BRAKE RELEASE Autofeather ............................................................................................. ARMED V1, VR, V2, V35 ..................................................................................................................... AS TABULATED Runway ..............................................................................PAVED, DRY SURFACE Landing Gear ............................................................ RETRACTED AFTER LIFT-OFF Obstacle Height ....................................................................................... 35 FEET If Accelerate-Stop: Power Lever ...................................................GROUND FINE AT OR BELOW V1 Braking ................................................... MAXIMUM WITHOUT SLIDING TIRES NOTES: Red shaded areas exceed operating limitations and are presented as interpolation aids only. For operation with engine anti-ice ON: 1. Increase the scheduled V1 speed obtained from the table by 2 knots. 2. Increase the takeoff field length obtained from the table by 10%. Refer to the following graphs for the runway gradient and headwind/tailwind component correction as applicable. TAKEOFF FIELD LENGTH CORRECTION FLAPS UP FOR RUNWAY GRADIENT AND WIND COMPONENT. TAKEOFF DECISION SPEED (V1) CORRECTION FLAPS UP FOR RUNWAY GRADIENT AND WIND COMPONENT. REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-18 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP SEA LEVEL PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -15 -5 5 15 25 35 45 52 15,950 LB 7235 KG V1 109 109 109 110 110 112 114 114 VR 113 113 113 113 113 114 114 114 V2 120 120 120 120 120 120 120 120 V35 130 130 130 129 129 127 126 126 TOFL-FT 4247 4485 4726 4992 5358 6034 6787 7333 15,500 LB 7031 KG V1 106 107 107 107 108 110 112 113 VR 111 111 111 112 112 112 113 113 V2 119 119 119 119 119 119 119 119 V35 129 129 128 128 128 126 125 124 TOFL-FT 4010 4241 4466 4705 5056 5683 6390 6914 15,000 LB 6804 KG V1 104 105 105 105 106 108 110 111 VR 109 110 110 110 110 111 111 111 V2 117 117 117 117 117 117 117 117 V35 128 127 127 127 126 125 124 123 TOFL-FT 3772 3988 4209 4440 4768 5353 6009 6513 14,500 LB 6577 KG V1 102 102 103 103 104 106 108 109 VR 108 108 108 108 109 109 109 110 V2 116 116 116 116 116 116 116 116 V35 127 126 126 126 125 124 123 122 TOFL-FT 3550 3752 3960 4175 4502 5039 5653 6113 14,000 LB 6350 KG V1 99 100 100 101 102 104 106 107 VR 106 106 106 106 107 107 108 108 V2 114 114 114 114 114 114 114 114 V35 125 125 125 125 124 123 122 121 TOFL-FT 3341 3529 3724 3925 4228 4740 5312 5749 13,500 LB 6123 KG V1 97 98 98 98 100 102 104 105 VR 104 104 104 105 105 106 106 107 V2 113 113 113 113 113 113 113 113 V35 124 124 124 124 123 122 121 120 TOFL-FT 3141 3317 3498 3687 3970 4458 4987 5385 12,500 LB 5670 KG V1 96 96 96 96 97 100 102 103 VR 104 104 104 104 104 105 106 106 V2 113 113 113 112 112 112 112 112 V35 125 125 124 124 123 122 121 120 TOFL-FT 2960 3110 3265 3423 3672 4117 4619 4984 11,500 LB 5216 KG V1 95 95 95 95 96 98 100 102 VR 104 104 104 104 104 104 105 106 V2 114 114 113 113 112 112 112 112 V35 127 126 126 125 124 123 122 121 TOFL-FT 2795 2936 3080 3229 3421 3818 4291 4642 10,500 LB 4763 KG V1 93 93 94 94 94 96 98 100 VR 104 104 104 104 104 104 104 105 V2 115 115 114 114 113 112 112 112 V35 128 128 127 127 125 123 122 122 TOFL-FT 2630 2761 2895 3034 3211 3536 3953 4286 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-19 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 1,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -15 -5 5 15 25 35 45 52 15,950 LB 7235 KG V1 109 109 110 110 111 113 114 115 VR 113 113 113 113 114 114 114 115 V2 120 120 120 120 120 120 120 120 V35 130 130 129 129 128 127 126 125 TOFL-FT 4471 4720 4996 5257 5756 6482 7314 7565 15,500 LB 7031 KG V1 107 107 107 108 109 111 113 113 VR 111 111 112 112 112 112 113 113 V2 119 119 119 119 119 119 119 119 V35 129 128 128 128 127 126 125 124 TOFL-FT 4227 4461 4708 4956 5429 6112 6891 7446 15,000 LB 6804 KG V1 105 105 105 106 107 109 111 111 VR 110 110 110 110 110 111 111 111 V2 117 117 117 117 117 117 117 117 V35 127 127 127 127 126 125 123 123 TOFL-FT 3975 4204 4443 4678 5115 5747 6480 6996 14,500 LB 6577 KG V1 102 103 103 103 105 107 109 110 VR 108 108 108 108 109 109 110 110 V2 116 116 116 116 116 116 116 116 V35 126 126 126 126 125 124 122 122 TOFL-FT 3741 3956 4178 4405 4822 5413 6092 6591 14,000 LB 6350 KG V1 100 100 101 101 103 105 106 108 VR 106 106 106 107 107 108 108 108 V2 114 114 114 114 114 114 114 114 V35 125 125 125 125 124 122 121 121 TOFL-FT 3518 3719 3928 4140 4547 5088 5722 6176 13,500 LB 6123 KG V1 98 98 98 99 100 103 104 106 VR 104 104 105 105 105 106 106 107 V2 113 113 113 113 113 113 113 113 V35 124 124 124 123 123 121 120 120 TOFL-FT 3307 3494 3690 3888 4263 4777 5368 5797 12,500 LB 5670 KG V1 96 96 96 97 98 101 103 104 VR 104 104 104 104 104 105 106 106 V2 113 113 112 112 112 112 112 112 V35 125 124 124 124 123 122 121 120 TOFL-FT 3102 3261 3426 3593 3934 4426 4970 5366 11,500 LB 5216 KG V1 95 95 95 96 97 99 101 103 VR 104 104 104 104 104 105 105 106 V2 114 113 113 113 112 112 112 112 V35 126 126 125 125 123 122 121 121 TOFL-FT 2928 3078 3231 3387 3660 4097 4636 4992 10,500 LB 4763 KG V1 93 94 94 94 95 97 10 101 VR 104 104 104 104 104 104 105 105 V2 115 114 114 114 113 112 112 112 V35 128 127 127 126 124 123 122 121 TOFL-FT 2754 2893 3036 3181 3410 3788 4265 4625 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-20 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 2,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -15 -5 5 15 25 35 45 52 15,950 LB 7235 KG V1 109 110 110 110 112 114 115 VR 113 113 113 113 114 114 115 V2 120 120 120 120 120 120 120 V35 130 129 129 129 128 126 125 TOFL-FT 4706 4991 5263 5551 6186 6990 7860 15,500 LB 7031 KG V1 107 107 108 108 110 112 113 113 VR 111 112 112 112 112 113 113 113 V2 119 119 119 119 119 119 119 119 V35 128 128 128 128 126 125 124 124 TOFL-FT 4448 4704 4961 5242 5831 6579 7421 8009 15,000 LB 6804 KG V1 105 105 106 106 108 110 111 112 VR 110 110 110 110 111 111 111 112 V2 117 117 117 117 117 117 117 117 V35 127 127 127 126 125 124 123 122 TOFL-FT 4192 4439 4683 4936 5492 6198 6980 7537 14,500 LB 6577 KG V1 103 103 103 104 106 108 109 110 VR 108 108 108 109 109 109 110 110 V2 116 116 116 116 116 116 116 116 V35 126 126 126 125 124 123 122 121 TOFL-FT 3944 4175 4410 4656 5174 5823 6564 7075 14,000 LB 6350 KG V1 100 101 101 102 104 105 107 108 VR 106 106 107 107 107 108 108 108 V2 114 114 114 114 114 114 114 114 V35 125 125 125 124 123 122 121 120 TOFL-FT 3709 3925 4144 4372 4871 5477 6162 6661 13,500 LB 6123 KG V1 98 98 99 99 101 103 105 106 VR 104 105 105 105 106 106 107 107 V2 113 113 113 113 113 113 113 113 V35 124 124 123 123 122 121 120 119 TOFL-FT 3485 3687 3893 4104 4584 5139 5779 6232 12,500 LB 5670 KG V1 96 96 97 97 99 102 103 105 VR 104 104 104 104 105 106 106 106 V2 113 112 112 112 112 112 112 112 V35 125 124 124 123 122 121 120 119 TOFL-FT 3253 3423 3597 3797 4224 4761 5338 5763 11,500 LB 5216 KG V1 95 95 96 96 97 100 102 103 VR 104 104 104 104 104 105 106 106 V2 113 113 113 112 112 112 112 112 V35 126 125 125 124 123 122 121 120 TOFL-FT 3070 3229 3390 3544 3920 4416 4969 5362 10,500 LB 4763 KG V1 94 94 94 94 96 98 101 102 VR 104 104 104 104 104 104 105 106 V2 114 114 114 113 112 112 112 112 V35 127 127 126 125 123 122 121 121 TOFL-FT 2886 3034 3184 3326 3625 4071 4605 4970 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-21 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 3,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -15 -5 5 15 25 35 45 52 15,950 LB 7235 KG V1 110 110 110 111 113 114 115 VR 113 113 113 114 114 114 115 V2 120 120 120 120 120 120 120 V35 129 129 129 128 127 126 125 TOFL-FT 4977 5261 5559 5960 6661 7516 8405 15,500 LB 7031 KG V1 107 108 108 109 111 112 113 VR 111 112 112 112 112 113 113 V2 119 119 119 119 119 119 119 V35 128 128 128 127 126 125 124 TOFL-FT 4692 4958 5250 5616 6277 7090 7962 15,000 LB 6804 KG V1 105 106 106 107 108 110 111 112 VR 110 110 110 110 111 111 111 112 V2 117 117 117 117 117 117 117 117 V35 127 127 126 126 125 124 123 122 TOFL-FT 4428 4680 4943 5298 5909 6659 7498 8086 14,500 LB 6577 KG V1 103 103 104 105 106 108 110 110 VR 108 108 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 116 V35 126 126 125 125 124 123 121 121 TOFL-FT 4164 4408 4663 4991 5564 6274 7058 7624 14,000 LB 6350 KG V1 101 101 102 102 104 106 108 109 VR 106 107 107 107 108 108 108 109 V2 114 114 114 114 114 114 114 114 V35 125 125 124 124 123 121 120 120 TOFL-FT 3915 4142 4378 4702 5234 5885 6627 7186 13,500 LB 6123 KG V1 98 99 99 100 102 104 106 107 VR 105 105 105 105 106 106 107 107 V2 113 113 113 113 113 113 113 113 V35 124 123 123 123 122 120 119 119 TOFL-FT 3678 3891 4110 4411 4920 5525 6212 6743 12,500 LB 5670 KG V1 96 97 97 98 100 102 104 105 VR 104 104 104 104 105 106 106 106 V2 112 112 112 112 112 112 112 112 V35 124 124 123 123 122 121 120 119 TOFL-FT 3416 3595 3796 4071 4549 5114 5745 6232 11,500 LB 5216 KG V1 95 96 96 96 98 101 103 104 VR 104 104 104 104 104 105 106 106 V2 113 113 113 112 112 112 112 112 V35 125 125 124 124 122 122 120 120 TOFL-FT 3222 3389 3561 3789 4212 4759 5346 5797 10,500 LB 4763 KG V1 94 94 94 95 97 99 102 103 VR 104 104 104 104 104 105 106 106 V2 114 114 114 113 112 112 112 112 V35 127 126 126 124 123 122 121 120 TOFL-FT 3027 3183 3343 3536 3896 4380 4954 5372 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-22 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 4,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -25 -15 -5 5 15 25 35 45 15,950 LB 7235 KG V1 110 110 110 111 112 113 114 115 VR 113 113 113 113 114 114 114 115 V2 120 120 120 120 120 120 120 120 V35 129 129 129 128 128 127 126 125 TOFL-FT 4954 5248 5558 5868 6407 7177 8064 8954 15,500 LB 7031 KG V1 107 108 108 108 110 111 113 113 VR 111 112 112 112 112 112 113 113 V2 119 119 119 119 119 119 119 119 V35 128 128 128 127 127 125 124 123 TOFL-FT 4671 4946 5248 5542 6053 6761 7620 8485 15,000 LB 6804 KG V1 105 106 106 106 107 109 111 112 VR 110 110 110 110 111 111 111 112 V2 117 117 117 117 117 117 117 117 V35 127 127 126 126 125 124 123 122 TOFL-FT 4407 4670 4942 5216 5692 6363 7181 8051 14,500 LB 6577 KG V1 103 103 104 104 105 107 109 110 VR 108 108 109 109 109 109 110 110 V2 116 116 116 116 116 116 116 116 V35 126 126 125 125 124 123 122 121 TOFL-FT 4146 4398 4662 4924 5370 5989 6742 7600 14,000 LB 6350 KG V1 101 101 102 102 103 105 107 108 VR 106 107 107 107 107 108 108 109 V2 114 114 114 114 114 114 114 114 V35 125 125 124 124 123 122 121 120 TOFL-FT 3897 4133 4377 4631 5050 5631 6341 7146 13,500 LB 6123 KG V1 98 99 99 100 101 103 105 106 VR 105 105 105 105 106 106 107 107 V2 113 113 113 113 113 113 113 113 V35 124 123 123 123 122 121 120 119 TOFL-FT 3661 3882 4109 4345 4750 5289 5940 6699 12,500 LB 5670 KG V1 96 97 97 98 99 101 103 105 VR 104 104 104 104 105 105 106 106 V2 112 112 112 112 112 112 112 112 V35 124 124 123 123 122 121 120 119 TOFL-FT 3402 3588 3796 4011 4379 4906 5496 6189 11,500 LB 5216 KG V1 95 95 96 96 97 99 102 104 VR 104 104 104 104 104 105 106 106 V2 113 113 113 112 112 112 112 112 V35 125 125 124 124 123 122 121 120 TOFL-FT 3209 3382 3561 3746 4064 4538 5115 5761 10,500 LB 4763 KG V1 94 94 94 95 95 98 100 102 VR 104 104 104 104 104 104 105 106 V2 114 114 114 113 112 112 112 112 V35 127 126 126 125 124 123 122 121 TOFL-FT 3016 3177 3343 3515 3765 4185 4722 5334 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-23 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 5,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -25 -15 -5 5 15 25 35 45 15,950 LB 7235 KG V1 110 110 111 111 112 114 115 VR 113 113 113 114 114 114 115 V2 120 120 120 120 120 120 120 V35 129 129 128 128 127 126 125 TOFL-FT 5226 5546 5868 6224 6901 7742 8622 15,500 LB 7031 KG V1 108 108 108 109 110 112 113 113 VR 112 112 112 112 112 113 113 113 V2 119 119 119 119 119 119 119 119 V35 128 128 127 127 126 125 124 123 TOFL-FT 4925 5238 5543 5865 6504 7290 8187 9087 15,000 LB 6804 KG V1 106 106 106 107 108 110 111 112 VR 110 110 110 110 111 111 111 112 V2 117 117 117 117 117 117 117 117 V35 127 126 126 126 125 124 123 122 TOFL-FT 4651 4932 5217 5534 6125 6856 7723 8612 14,500 LB 6577 KG V1 103 104 104 105 106 108 109 110 VR 108 109 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 116 V35 126 125 125 125 124 123 122 121 TOFL-FT 4379 4652 4925 5214 5770 6452 7281 8167 14,000 LB 6350 KG V1 101 102 102 102 104 106 107 109 VR 107 107 107 107 108 108 108 109 V2 114 114 114 114 114 114 114 114 V35 125 124 124 124 123 122 120 119 TOFL-FT 4116 4368 4632 4912 5435 6063 6823 7707 13,500 LB 6123 KG V1 99 99 100 100 102 104 105 107 VR 105 105 105 105 106 106 107 107 V2 113 113 113 113 113 113 113 113 V35 123 123 123 123 122 121 119 118 TOFL-FT 3866 4101 4346 4609 5104 5693 6407 7243 12,500 LB 5670 KG V1 97 97 98 98 100 102 104 105 VR 104 104 104 104 105 106 106 107 V2 112 112 112 112 112 112 112 112 V35 124 123 123 123 122 121 120 119 TOFL-FT 3575 3789 4012 4254 4715 5270 5928 6695 11,500 LB 5216 KG V1 95 96 96 96 98 100 103 105 VR 104 104 104 104 104 105 106 106 V2 113 113 112 112 112 112 112 112 V35 125 124 124 124 123 122 120 119 TOFL-FT 3370 3555 3746 3956 4367 4896 5513 6226 10,500 LB 4763 KG V1 94 94 95 95 96 99 101 103 VR 104 104 104 104 104 105 105 106 V2 114 114 113 113 112 112 112 112 V35 126 126 125 124 123 122 121 120 TOFL-FT 3165 3337 3516 3694 4039 4507 5103 5768 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-24 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 6,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -25 -15 -5 5 15 25 35 45 15,950 LB 7235 KG V1 110 110 111 112 113 114 VR 113 113 114 114 114 114 V2 120 120 120 120 120 120 V35 129 128 128 128 127 126 TOFL-FT 5524 5857 6227 6686 7443 8314 15,500 LB 7031 KG V1 108 108 109 110 111 113 113 VR 112 112 112 112 112 113 113 V2 119 119 119 119 119 119 119 V35 128 127 127 127 126 125 124 TOFL-FT 5216 5533 5866 6315 7011 7865 8773 15,000 LB 6804 KG V1 106 106 107 107 109 110 112 112 VR 110 110 110 111 111 111 112 112 V2 117 117 117 117 117 117 117 117 V35 127 126 126 125 124 123 122 121 TOFL-FT 4913 5207 5532 5943 6599 7395 8289 9179 14,500 LB 6577 KG V1 104 104 105 105 107 108 110 110 VR 109 109 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 116 V35 126 125 125 124 123 122 121 120 TOFL-FT 4633 4917 5211 5606 6213 6953 7840 8707 14,000 LB 6350 KG V1 101 102 102 103 105 106 108 109 VR 107 107 107 107 108 108 109 109 V2 114 114 114 114 114 114 114 114 V35 124 124 124 123 122 121 120 119 TOFL-FT 4351 4624 4906 5275 5843 6523 7367 8293 13,500 LB 6123 KG V1 99 100 100 101 103 104 106 107 VR 105 105 105 106 106 107 107 107 V2 113 113 113 113 113 113 113 113 V35 123 123 123 122 121 120 119 118 TOFL-FT 4085 4339 4602 4961 5496 6130 6904 7808 12,500 LB 5670 KG V1 97 98 98 99 101 103 105 106 VR 104 104 104 105 105 106 106 107 V2 112 112 112 112 112 112 112 112 V35 123 123 123 122 122 120 119 118 TOFL-FT 3774 4005 4247 4574 5087 5672 6382 7244 11,500 LB 5216 KG V1 96 96 96 97 99 101 103 105 VR 104 104 104 104 105 106 106 106 V2 113 112 112 112 112 112 112 112 V35 124 124 124 123 122 121 120 119 TOFL-FT 3543 3741 3947 4706 5279 5936 6735 10,500 LB 4763 KG V1 94 95 95 95 97 100 102 104 VR 104 104 104 104 104 105 106 106 V2 114 113 113 112 112 112 112 112 V35 126 125 125 124 123 122 121 119 TOFL-FT 3326 3511 3702 3932 4340 4865 5499 6237 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-25 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 7,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -25 -15 -5 5 15 25 35 45 15,950 LB 7235 KG V1 110 111 111 112 114 115 VR 113 114 114 114 114 115 V2 120 120 120 120 120 120 V35 128 128 128 127 126 125 TOFL-FT 5835 6217 6588 7208 8037 8902 15,500 LB 7031 KG V1 108 109 109 110 112 113 VR 112 112 112 112 113 113 V2 119 119 119 119 119 119 V35 127 127 127 126 125 124 TOFL-FT 5513 5858 6205 6793 7565 8451 15,000 LB 6804 KG V1 106 107 107 108 110 111 112 VR 110 110 110 111 111 111 112 V2 117 117 117 117 117 117 117 V35 126 126 126 125 124 123 122 TOFL-FT 5187 5524 5855 6409 7116 7987 8916 14,500 LB 6577 KG V1 104 105 105 106 108 109 110 VR 109 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 V35 125 125 125 124 123 122 121 TOFL-FT 4899 5204 5510 6028 6696 7511 8438 14,000 LB 6350 KG V1 102 102 103 104 105 107 109 109 VR 107 107 107 108 108 108 109 109 V2 114 114 114 114 114 114 114 114 V35 124 124 124 123 122 121 120 119 TOFL-FT 4607 4900 5207 5678 6295 7050 7959 8871 13,500 LB 6123 KG V1 100 100 100 102 103 105 107 107 VR 105 105 106 106 106 107 107 107 V2 113 113 113 113 113 113 113 113 V35 123 123 122 122 121 120 118 117 TOFL-FT 4323 4596 4879 5334 5911 6604 7466 8386 12,500 LB 5670 KG V1 97 98 98 100 102 103 105 107 VR 104 104 105 105 106 106 106 107 V2 112 112 112 112 112 112 112 112 V35 123 123 123 122 121 120 119 118 TOFL-FT 3991 4241 4500 4927 5472 6111 6898 7851 11,500 LB 5216 KG V1 96 96 97 98 100 102 104 106 VR 104 104 104 104 105 106 106 107 V2 112 112 112 112 112 112 112 112 V35 124 124 123 123 122 121 119 118 TOFL-FT 3729 3943 4174 4563 5078 5684 6413 7303 10,500 LB 4763 KG V1 95 95 95 96 98 101 103 105 VR 104 104 104 104 105 105 106 106 V2 113 113 113 112 112 112 112 112 V35 125 125 124 123 122 121 120 119 TOFL-FT 3500 3698 3897 4218 4676 5263 5939 6774 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-26 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 8,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -25 -15 -5 5 15 25 35 45 15,950 LB 7235 KG V1 111 111 112 113 114 VR 114 114 114 114 114 V2 120 120 120 120 120 V35 128 128 128 127 126 TOFL-FT 6195 6582 7037 7780 8664 15,500 LB 7031 KG V1 109 109 110 111 112 113 VR 112 112 112 112 113 113 V2 119 119 119 119 119 119 V35 127 127 126 126 125 124 TOFL-FT 5839 6198 6636 7330 8173 9083 15,000 LB 6804 KG V1 107 107 107 109 110 112 VR 110 110 111 111 111 112 V2 117 117 117 117 117 117 V35 126 126 125 124 123 122 TOFL-FT 5505 5850 6254 6898 7685 8583 14,500 LB 6577 KG V1 105 105 105 107 108 110 110 VR 109 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 V35 125 125 124 123 122 121 120 TOFL-FT 5187 5504 5906 6495 7226 8118 8889 14,000 LB 6350 KG V1 102 103 103 105 106 108 109 VR 107 107 107 108 108 108 109 V2 114 114 114 114 114 114 114 V35 124 124 123 122 121 120 119 TOFL-FT 4883 5201 5552 6110 6789 7620 8573 13,500 LB 6123 KG V1 100 100 101 103 104 106 107 108 VR 105 106 106 106 107 107 107 108 V2 113 113 113 113 113 113 113 113 V35 123 123 122 121 120 119 118 117 TOFL-FT 4581 4874 5227 5746 6372 7146 8074 9024 12,500 LB 5670 KG V1 98 98 99 101 103 104 106 107 VR 104 105 105 105 106 106 107 107 V2 112 112 112 112 112 112 112 112 V35 123 123 122 122 120 119 118 117 TOFL-FT 4228 4496 4815 5318 5896 6605 7475 8490 11,500 LB 5216 KG V1 96 97 97 99 101 103 105 107 VR 104 104 104 105 106 106 106 107 V2 112 112 112 112 112 112 112 112 V35 124 123 123 122 121 120 119 118 TOFL-FT 3932 4169 4463 4920 5491 6142 6952 7952 10,500 LB 4763 KG V1 95 95 96 97 99 102 104 106 VR 104 104 104 104 105 106 106 107 V2 113 113 112 112 112 112 112 112 V35 125 124 123 123 122 121 120 118 TOFL-FT 3688 3900 4129 4534 5051 5689 6437 7369 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-27 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 9,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -35 -25 -15 -5 5 15 25 35 15,950 LB 7235 KG V1 111 111 111 112 114 115 VR 114 114 114 114 114 115 V2 120 120 120 120 120 120 V35 128 128 128 127 126 125 TOFL-FT 6160 6562 6987 7588 8407 9306 15,500 LB 7031 KG V1 109 109 109 110 111 113 VR 112 112 112 112 113 113 V2 119 119 119 119 119 119 V35 127 127 127 126 125 124 TOFL-FT 5807 6190 6594 7151 7915 8808 15,000 LB 6804 KG V1 107 107 107 108 110 111 112 VR 110 110 111 111 111 111 112 V2 117 117 117 117 117 117 117 V35 126 126 125 125 124 123 122 TOFL-FT 5475 5833 6206 6734 7446 8311 9088 14,500 LB 6577 KG V1 104 105 105 106 107 109 110 VR 109 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 V35 125 125 124 124 123 122 121 TOFL-FT 5160 5498 5852 6345 7006 7815 8756 14,000 LB 6350 KG V1 102 103 103 104 105 107 109 VR 107 107 107 108 108 108 109 V2 114 114 114 114 114 114 114 V35 124 124 123 123 122 121 120 TOFL-FT 4857 5186 5508 5982 6586 7337 8254 13,500 LB 6123 KG V1 100 100 101 102 103 105 106 107 VR 105 106 106 106 106 107 107 107 V2 113 113 113 113 113 113 113 113 V35 123 123 122 122 121 120 119 118 TOFL-FT 4557 4860 5179 5616 6186 6882 7742 8701 12,500 LB 5670 KG V1 98 98 99 100 102 103 105 107 VR 104 105 105 105 106 106 106 107 V2 112 112 112 112 112 112 112 112 V35 123 123 122 122 121 120 119 118 TOFL-FT 4205 4483 4773 5189 5726 6363 7150 8115 11,500 LB 5216 KG V1 96 97 97 98 100 102 104 106 VR 104 104 104 105 105 106 106 107 V2 112 112 112 112 112 112 112 112 V35 124 123 123 122 122 121 120 118 TOFL-FT 3913 4157 4424 4804 5312 5918 6646 7547 10,500 LB 4763 KG V1 95 95 95 96 98 100 103 105 VR 104 104 104 104 105 105 106 106 V2 113 113 112 112 112 112 112 112 V35 125 124 124 123 122 121 120 119 TOFL-FT 3670 3890 4111 4436 4891 5468 6161 6987 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-28 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 10,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -35 -25 -15 -5 5 15 25 35 15,950 LB 7235 KG V1 111 111 112 113 114 115 VR 114 114 114 114 114 115 V2 120 120 120 120 120 120 V35 128 128 127 127 126 125 TOFL-FT 6529 6968 7465 8192 9056 9911 15,500 LB 7031 KG V1 109 109 110 111 112 113 VR 112 112 112 112 113 113 V2 119 119 119 119 119 119 V35 127 127 126 125 125 124 TOFL-FT 6158 6576 7041 7718 8557 9433 15,000 LB 6804 KG V1 107 107 108 109 110 112 VR 110 111 111 111 111 112 V2 117 117 117 117 117 117 V35 126 125 125 124 123 122 TOFL-FT 5803 6191 6631 7264 8046 8969 14,500 LB 6577 KG V1 105 105 106 107 108 110 110 VR 109 109 109 109 110 110 110 V2 116 116 116 116 116 116 116 V35 125 124 124 123 122 121 120 TOFL-FT 5470 5837 6251 6839 7567 8464 9414 14,000 LB 6350 KG V1 103 103 104 105 106 108 109 VR 107 107 108 108 108 108 109 V2 114 114 114 114 114 114 114 V35 124 123 123 122 121 120 119 TOFL-FT 5159 5495 5882 6433 7110 7948 8880 13,500 LB 6123 KG V1 100 101 102 103 104 106 107 108 VR 106 106 106 106 107 107 107 108 V2 113 113 113 113 113 113 113 113 V35 123 122 122 121 120 119 118 117 TOFL-FT 4835 5166 5538 6055 6673 7450 8389 9366 12,500 LB 5670 KG V1 98 99 100 101 103 104 106 107 VR 104 105 105 105 106 106 107 107 V2 112 112 112 112 112 112 112 112 V35 123 122 122 121 120 119 118 117 TOFL-FT 4461 4761 5111 5603 6182 6884 7757 8787 11,500 LB 5216 KG V1 96 97 98 99 101 103 105 106 VR 104 104 104 105 106 106 106 107 V2 112 112 112 112 112 112 112 112 V35 123 123 123 122 121 120 119 118 TOFL-FT 4136 4413 4734 5181 5746 6399 7198 8226 10,500 LB 4763 KG V1 95 95 96 97 99 101 103 105 VR 104 104 104 104 105 106 106 107 V2 113 113 112 112 112 112 112 112 V35 125 124 123 122 122 121 120 119 TOFL-FT 3873 4106 4375 4774 5285 5925 6663 7617 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-29 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 11,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -35 -25 -15 -5 5 15 25 30 15,950 LB 7235 KG V1 111 112 113 114 115 VR 114 114 114 114 115 V2 120 120 120 120 120 V35 128 127 127 126 125 TOFL-FT 7023 7500 8145 8969 9817 15,500 LB 7031 KG V1 109 110 111 112 113 113 VR 112 112 112 113 113 113 V2 119 119 119 119 119 119 V35 127 126 126 125 124 123 TOFL-FT 6625 7069 7675 8448 9316 10184 15,000 LB 6804 KG V1 107 107 108 110 111 112 VR 111 111 111 111 111 112 V2 117 117 117 117 117 117 V35 125 125 125 124 123 122 TOFL-FT 6240 6647 7228 7947 8817 9743 14,500 LB 6577 KG V1 105 105 106 108 109 110 VR 109 109 109 110 110 110 V2 116 116 116 116 116 116 V35 124 124 123 123 122 121 TOFL-FT 5882 6274 6805 7479 8290 9273 14,000 LB 6350 KG V1 103 103 104 105 107 109 109 VR 107 107 108 108 108 109 109 V2 114 114 114 114 114 114 114 V35 123 123 122 122 121 120 119 TOFL-FT 5539 5907 6407 7030 7785 8729 9699 13,500 LB 6123 KG V1 101 101 102 103 105 106 107 108 VR 106 106 106 106 107 107 107 108 V2 113 113 113 113 113 113 113 113 V35 122 122 121 121 120 119 118 117 TOFL-FT 5206 5564 6017 6603 7303 8177 9161 9651 12,500 LB 5670 KG V1 99 99 100 102 103 105 106 107 VR 105 105 105 106 106 106 107 107 V2 112 112 112 112 112 112 112 112 V35 122 122 122 121 120 119 118 117 TOFL-FT 4799 5124 5572 6110 6751 7567 8540 9114 11,500 LB 5216 KG V1 97 98 99 100 102 104 105 106 VR 104 104 105 105 106 106 107 107 V2 112 112 112 112 112 112 112 112 V35 123 123 122 122 121 120 118 118 TOFL-FT 4448 4747 5157 5670 6277 7034 7936 8492 10,500 LB 4763 KG V1 95 96 97 98 100 102 104 105 VR 104 104 104 105 105 106 106 106 V2 113 112 112 112 112 112 112 112 V35 124 123 123 122 121 120 119 119 TOFL-FT 4141 4390 4755 5220 5798 6504 7343 7861 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE AFM 051-1 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT 5-30 APRIL 2023 FAA APPROVED TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 12,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -35 -25 -15 -5 0 5 15 25 15,950 LB 7235 KG V1 112 112 113 114 115 115 VR 114 114 114 114 115 115 V2 120 120 120 120 120 120 V35 127 127 126 126 125 125 TOFL-FT 7612 8169 8970 9861 10301 10741 15,500 LB 7031 KG V1 110 110 111 113 113 113 113 VR 112 112 113 113 113 113 113 V2 119 119 119 119 119 119 119 V35 126 126 125 124 124 124 123 TOFL-FT 7175 7701 8458 9314 9748 10183 11053 15,000 LB 6804 KG V1 108 108 109 110 111 112 112 VR 111 111 111 111 111 112 112 V2 117 117 117 117 117 117 117 V35 125 125 124 123 123 122 122 TOFL-FT 6758 7254 7963 8763 9215 9668 10578 14,500 LB 6577 KG V1 105 106 107 108 109 110 110 VR 109 109 109 110 110 110 110 V2 116 116 116 116 116 116 116 V35 124 124 123 122 122 121 120 TOFL-FT 6369 6836 7494 8242 8668 9170 10177 14,000 LB 6350 KG V1 103 104 105 106 107 107 109 VR 107 108 108 108 108 108 109 V2 114 114 114 114 114 114 114 V35 123 123 122 121 121 120 119 TOFL-FT 5997 6442 7046 7745 8140 8613 9623 13,500 LB 6123 KG V1 101 102 103 104 105 105 107 108 VR 106 106 106 107 107 107 107 108 V2 113 113 113 113 113 113 113 113 V35 122 122 121 120 120 119 118 117 TOFL-FT 5648 6054 6623 7269 7638 8074 9051 10029 12,500 LB 5670 KG V1 99 100 101 103 103 104 105 107 VR 105 105 106 106 106 106 107 107 V2 112 112 112 112 112 112 112 112 V35 122 122 121 120 120 119 118 117 TOFL-FT 5201 5592 6130 6722 7059 7460 8368 9480 11,500 LB 5216 KG V1 97 98 100 101 102 103 104 106 VR 104 105 105 106 106 106 106 107 V2 112 112 112 112 112 112 112 112 V35 123 122 122 121 121 120 119 118 TOFL-FT 4818 5179 5679 6261 6562 6932 7774 8828 10,500 LB 4763 KG V1 96 96 98 99 100 101 103 105 VR 104 104 104 105 105 106 106 106 V2 112 112 112 112 112 112 112 112 V35 123 123 122 122 121 121 120 119 TOFL-FT 4462 4779 5230 5757 6061 6416 7192 8168 REFERENCE ONLY CENTEX AEROSPACE AFM 051-1 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE FAA APPROVED APRIL 2023 5-31 TAKEOFF SPEEDS & FIELD LENGTHS - FLAPS UP 13,000 FEET PRESSURE ALTITUDE T.O. WEIGHT ITEM OUTSIDE AIR TEMPERATURE (OC) -35 -25 -15 -5 0 5 15 20 15,950 LB 7235 KG V1 112 113 114 115 VR 114 114 114 115 V2 120 120 120 120 V35 127 127 126 125 TOFL-FT 8264 9012 9903 10813 15,500 LB 7031 KG V1 110 111 112 113 113 VR 112 112 113 113 113 V2 119 119 119 119 119 V35 126 125 125 124 124 TOFL-FT 7780 8494 9340 10239 10689 15,000 LB 6804 KG V1 108 109 110 111 112 112 VR 111 111 111 111 112 112 V2 117 117 117 117 117 117 V35 125 124 124 123 122 122 TOFL-FT 7333 7997 8784 9679 10136 10596 14,500 LB 6577 KG V1 106 107 108 109 110 110 111 VR 109 109 110 110 110 110 111 V2 116 116 116 116 116 116 116 V35 124 123 122 122 121 121 120 TOFL-FT 6902 7531 8274 9108 9593 10079 11059 14,000 LB 6350 KG V1 104 105 106 107 107 109 109 VR 108 108 108 108 108 109 109 V2 114 114 114 114 114 114 114 V35 123 122 121 121 120 120 119 TOFL-FT 6496 7085 7770 8553 9011 9520 10539 13,500 LB 6123 KG V1 102 103 104 105 105 106 107 108 VR 106 106 106 107 107 107 107 108 V2 113 113 113 113 113 113 113 113 V35 122 121 120 119 119 119 118 117 TOFL-FT 6111 6668 7295 80