AIRPLANE FLIGHT MANUAL SUPPLEMENT

The terminology used in this supplement matches the terminology used in the basic AFM and POH. This includes the definitions of warnings, cautions, and notes. Also, you will find the format of limitations, procedures, and checklists herein match the AFM and POH format for 200 series airplanes. DESCRIPTIVE DATA MAXIMUM CERTIFICATED WEIGHTS Maximum Ramp Weight .........................................................14,090 pounds Maximum Take-off Weight .....................................................14,000 pounds Maximum Zero Fuel Weight: Model B200/B200GT series with Serials BB-1439, BB-1444 & after, BL-139 & after, BY-1 thru BY-116, BY-118...........................11,500 pounds Maximum Landing Weight ......................................................13,500 pounds SPECIFIC LOADINGS Wing Loading: 46.2 pounds per square foot Power Loading: 8.2 pounds per shaft horsepower COMPATIBLE MODIFICATIONS The following STC-approved modifications have been found to be compatible with the Halo 275 Commuter category conversion: 1. SA2698NM-S, Raisbeck Eng. Hartzell HC-D4N-3A/D9383K propeller. 2. SA02130SE, BLR Hartzell HC-E4N-3A/NC9208K propellers 3. SA3366NM, Raisbeck Ram Air Recovery System 4. SA3831NM, Raisbeck Inboard Leading Edges 5. SA3519NM, Raisbeck Aft Body Strakes 6. SA4175NM, Raisbeck MLG Doors 7. SA3857NM, Raisbeck Storage Lockers 8. SA3683NM, Raisbeck Exhaust Stack Fairings 9. SA00433AT, Blackhawk Modifications PWC PT6A-42 Engine Conversion 10. SA10824SC, Blackhawk Modifications PWC PT6A-52 Engine ConversionREFERENCE ONLY SECTION 1 CENTEX AEROSPACE 006-2A HW GENERAL AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 1-4 11. SA10842SC, Enhanced Aero PWC PT6A-52 Engine Conversion 12. SA02715CH-D, Standard Aero PWC PT6A-52 Engine Conversion 13. SA10737SC, Blackhawk Modifications PWC PT6A-61 Engine Conversion 14. SA01615SE, BLR Winglets 15. SA01535WI-D, Garmin G1000 Avionics (GDC 7400 ADC required) 16. SA02738CH, L-3 Comm ESI-1000 standby instrument 17. SA1036GL, McCauley 4HFR34C7 (54,55,71)/94LA-0 Propellers 18. SA01157CH, McCauley 5HFR34C1008/96LTA-0 Propellers 19. SA757GL, Parker Cleveland wheels and brakes 20. SA2451CE, Commuter Air Technology Super 60 (Cargo) Pod (requires AFM Supplement no. 006-3 HW additionally) 21. SA2300CE, Avcon Industries Aeropak Cargo Pod (requires AFM Supplement no. 006-3A HW additionally) 22. SA03209NY, MT-Propeller MTV-27-1-E-C-F-R(P)/CFR225-55f 5-blade propeller 23. SA03289CH, Elliott Aviation Mid-Continent MD302 Electronic Standby Indicator 24. SA2633CE, Aviation Fabricators 4-place side facing divan seat. NOTE: Only airplanes manufactured prior to 12/12/86 with passenger seating configurations of 9 or less are compatible. 25. SA2671CE, Aviation Fabricators stretcher installation. 26. SA4157SW, Aviation Fabricators 2-place attendant divan seat. 27. SA02468LA, Aviation Fabricators aft toilet cabinet seat. 28. SA00635WI, Aviation Fabricators jump seat. NOTE: Seating configuration may not exceed 9 passenger seats. 29. SA10478SC, Hawker Beechcraft Services flight data recorder/cockpit voice recorder 30. SA00273WI, LifePort stretcher, patient loading, and support system 31. SA02235LA, LifePort Patient Loading and Utility System (PLUS) and ServiPlex 32. SA00882CH, Spectrum Aeromed air ambulance conversion 33. SA01213CH, Spectrum Aeromed air ambulance conversion It is up to the installer to determine whether any other STC-approved modifications are compatible with the Halo 275 Commuter category conversion. When determining compatibility regulatory requirements applicable to Commuter category airplanes must be considered. Note, other modifications affecting the display of flight attitude, airspeed, and altitude; and autopilot functionality must meet the design assurance levels required for Commuter category airplanes. - Continued on next page - REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 1 AIRPLANE FLIGHT MANUAL SUPPLEMENT GENERAL MAY 2017 1-5 LIST OF EFFECTIVE PAGES The list of effective pages shown below contains all current pages with the page version date. This list should be used to verify this supplement contains all of the applicable and required pages. When inserting revised pages into this supplement the List of Effective Pages should be updated, as well, to the corresponding new list. Title Page ............................................................................................. May 2017 iii thru iv ............................................................................................... May 2017 1-1 thru 1-6 .......................................................................................... May 2017 2-1 thru 2-12 ........................................................................................ May 2017 3-1 thru 3-4 .......................................................................................... May 2017 3A-1 thru 3A-6 ..................................................................................... May 2017 4-1 thru 4-10 ........................................................................................ May 2017 5-1 thru 5-89 ........................................................................................ May 2017 6-1 thru 6-6 .......................................................................................... May 2017 7-1 thru 7-8 .......................................................................................... May 2017 8-1 thru 8-2 .......................................................................................... May 2017 9-1 thru 9-4 .......................................................................................... May 2017 REFERENCE ONLY SECTION 1 CENTEX AEROSPACE 006-2A HW GENERAL AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 1-6 LOG OF REVISIONS Initial Release Date: June 29, 2017 Includes pages dated May 2017 APPROVED BY: James A. Grigg REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS MAY 2017 2-1 SECTION 2 LIMITATIONS TABLE OF CONTENTS SUBJECT PAGE AIRSPEED LIMITATIONS ............................................................................... 2-2 POWER PLANT LIMITATIONS ........................................................................ 2-4 FUEL IMBALANCE .......................................................................................... 2-4 WEIGHT LIMITS ............................................................................................. 2-4 CENTER-OF-GRAVITY LIMITS Aft Limits ............................................................................................... 2-5 Forward Limits ...................................................................................... 2-5 MANEUVER LIMITS ....................................................................................... 2-5 FLIGHT LOAD FACTOR LIMITS ....................................................................... 2-5 MINIMUM FLIGHT CREW .............................................................................. 2-5 ICING LIMITATIONS ....................................................................................... 2-5 OTHER LIMITATIONS Structural Limitations............................................................................ 2-7 Maximum Tailwind Component Limitation .......................................... 2-7 Maximum Headwind Component Limitation ........................................ 2-7 PLACARDS ..................................................................................................... 2-7 KINDS OF OPERATIONS ................................................................................. 2-8 KINDS OF OPERATIONS EQUIPMENT LIST ..................................................... 2-8REFERENCE ONLY SECTION 2 CENTEX AEROSPACE 006-2A HW LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 2-2 The limitations shown in this section are approved by the Federal Aviation Administration and must be observed while operating Beechcraft King Air 200 series airplanes that have been modified by the CenTex Aerospace Halo 275 Conversion. This conversion provides the following changes:  Increases maximum ramp weight limitation to 14,090 pounds.  Increases maximum takeoff weight limitation to 14,000 pounds.  Increases maximum landing weight limitation to 13,500 pounds.  Increases maximum zero fuel weight limitation to 11,500 pounds for B200 airplanes manufactured in 1993 and after.  Creates option to change from Normal category to Commuter category. Refer to the Beechcraft 200 series Airplane Flight Manual / Pilot Operating Handbook for limitations not contained in this section. It is noted that not all of the information presented in this Supplement is changed from the basic Airplane Flight Manual or Pilot Operating Handbook information. In this section, the changed information or value is identified either by a note or by simple underline. AIRSPEED LIMITATIONS SPEED KCAS KIAS REMARKS Operating Maneuvering Speed, VO 182 181 Do not make full or abrupt control movements above this speed. Maximum Flap Extension/ Extended Speed, VFE Approach Position – 40% Full Down Position – 100% NC NC NC NC Do not extend flaps or operate with flaps in prescribed position above these speeds. Maximum Landing Gear Operating Speed, VLO Extension Retraction NC NC NC NC Do not exceed or retract landing gear above the speeds given. Maximum Landing Gear Extended Speed, VLE NC NC Do not exceed this speed with landing gear extended. Air Minimum Control Speed VMCA Hartzell Propellers ................. McCauley Propellers.............. 1STC SA2698NM….Flaps Up ... Flaps Approach… 2STC SA02130SE…Flaps Up .... Flaps Approach… NC NC NC NC NC NC NC NC NC NC NC NC This is the lowest airspeed at which the airplane is directionally controllable when one engine suddenly becomes inoperative and the other engine is at takeoff power. (See definition in Section I of the basic AFM or POH) Maximum Operating Speed VMO NC NC Do not exceed this airspeed or Mach number in any operation. MMO 0.58 Mach NC-No change to original airspeed limitation. See basic AFM / POH. 1-Hartzell HC-D4N-3A/D9383K prop installed per Raisbeck Engineering STC SA2698NM-S. 2-Hartzell HC-E4N-3A/NC9208K prop installed per BLR Hartzell STC SA02130SE. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS MAY 2017 2-3 THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY SECTION 2 CENTEX AEROSPACE 006-2A HW LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 2-4 POWER PLANT LIMITATIONS Engine Model(s) .............................. PT6A-41 or PT6A-42 or PT6A-52 or PT6A-61 Engine Operating Limits: Takeoff & Max Continuous Power 850 SHP 2230 FT-LBS 2000 RPM Propeller Limitation: Autofeather must be in operation during takeoff. FUEL IMBALANCE The maximum allowable fuel imbalance between wing fuel systems is 300 pounds, except for one engine inoperative operations. The maximum allowable fuel imbalance between wing fuel systems is 1,000 pounds when operating with one engine inoperative. WEIGHT LIMITS Maximum Ramp Weight ...............................................................14,090 pounds Maximum Take-off Weight is 14,000 pounds or as limited by (see Section 5):  Maximum Allowed Takeoff Weight tables  Maximum Allowed Takeoff Weight Limited By Brake Energy  Maximum Tire Speed During Takeoff  Takeoff Speeds and Field Length tables For 14 CFR Part 135 Operations:  Service Ceiling - One Engine inoperative chart Maximum Landing Weight is 13,500 pounds or as limited by (see Section 5)  Maximum Allowed Landing Weight tables  Landing Distance charts Maximum Zero Fuel Weight: Model B200/B200GT series with Serials BB-1439, BB-1444 & after, BL-139 & after, BY-1 thru BY-116, BY-118...............................11,500 pounds REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS MAY 2017 2-5 CENTER OF GRAVITY LIMITS Aft Limits 195.4 inches aft of datum at 14,000 pounds gross weight with straight line variation to 196.4 inches aft of datum at 12,500 pounds gross weight. 196.4 inches aft of datum at gross weights less than 12,500 pounds. Forward Limits 188.3 inches aft of datum at gross weights between 14,000 pounds and 13,500 pounds with straight line variation to 181.0 inches aft of datum at 11,279 pounds gross weight. 181.0 inches aft of datum at gross weights less than 11,279 pounds. MANEUVER LIMITS The Beechcraft King Air B200/B200GT series airplanes modified with the HALO 275 conversion are Commuter category airplanes. Acrobatic maneuvers, including spins, are prohibited. FLIGHT LOAD FACTOR LIMITS FLAPS UP FLAPS DOWN 3.10 positive g’s 2.00 positive g’s 1.24 negative g’s 0.00 g MINIMUM FLIGHT CREW ......................................................................One Pilot MAXIMUM OCCUPANCY LIMIT Flight Crew ......................................................................Two (Pilot and Co-pilot) Passengers ...............................................................................................Nine (9) ICING LIMITATIONS The limitations and information presented in this subsection have been changed from the basic Airplane Flight Manual and Pilot Operation Handbook. The changes are considered by the FAA to be essential in ensuring the safe operation of the airplane in icing conditions. Minimum Ambient Temperature for Operation of Deicing Boots ............... -40oC Minimum Airspeed for Sustained Icing Flight ...................................... 148 Knots Sustained flight in icing conditions with flaps extended is prohibited except for approach and landing. ENGINE ANTI-ICE shall be ON for operations in ambient temperatures of +5oC or below when flight free of visible moisture cannot be assured. ENGINE ANTI-ICE shall be OFF for all takeoff and flight operations in ambient temperatures above + 15oC. REFERENCE ONLY SECTION 2 CENTEX AEROSPACE 006-2A HW LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 2-6 Takeoff is prohibited with any frost, ice, snow, or slush adhering to the wings, horizontal stabilizer, control surfaces, propeller blades, or engine inlet. In icing conditions the airplane must be operated and its ice protection system used as described in the operating procedures section of this AFM Supplement. Where specific operational speeds and performance information have been established for such conditions, this information must be used. WARNING Severe icing may result from environment conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capacity of the ice protection system, or may result in ice forming aft of the protected surfaces. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane and an unsafe situation will likely result. It is the responsibility of the pilot to identify severe icing conditions and to exit such condition to ensure safe flight operations. 1. Severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions.  Extensive ice accumulation on the airframe and windshield in areas not observed to collect ice during light or moderate icing conditions.  Accumulation of ice on the upper surface of the wing, aft of the protected area (i.e., leading-edge boot).  Accumulation of ice on the engine nacelles and propeller spinners farther aft than observed during light or moderate icing conditions. 2. DO NOT USE THE AUTOPILOT in severe icing conditions or whenever:  Visual cues specified above exist.  Unusual aileron trim settings are required.  Autopilot trim warnings occur. Note: an unsafe condition exists when the autopilot is engaged and the airplane handling characteristics are degrading due to ice accumulating on the airplane. The pilot will not be aware of this unsafe condition, which requires an immediate exit from icing conditions, if he/she is not manually flying the airplane. 3. All icing detection lights must be operative prior to flight into known or forecast icing conditions at night. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS MAY 2017 2-7 OTHER LIMITATIONS STRUCTURAL LIMITATIONS Refer to Chapter Four of the Super King Air 200 Series Maintenance Manual and to the CenTex Aerospace Halo 250 Commuter Category Conversion Instructions for Continued Airworthiness for structural limitations. MAXIMUM TAILWIND COMPONENT LIMITATION Do not take-off with a tailwind component greater than 10 knots. Do not land with a tailwind component greater than 10 knots. MAXIMUM HEADWIND COMPONENT LIMITATION Do not extrapolate for a headwind component that exceeds 30 knots. Assume a 30 knot headwind component when correcting takeoff field length whenever there is a 30 knot or greater headwind. PLACARDS On Overhead Panels in Pilot’s Compartment: OPERATION LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A COMMUTER CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS ARE APPROVED. THIS AIRPLANE APPROVED FOR VFR, IFR, & DAY & NIGHT OPERATION & IN ICING CONDITIONS. CAUTION STALL WARNING IS INOPERATIVE WHEN MASTER SWITCH IS OFF STANDBY COMPASS IS ERRATIC WHEN WINDSHIELD ANTI-ICE AND/OR AIR CONDITIONING IS ON. Inside Non-Cargo Airstair Door Behind Handle: CAUTION DO NOT OPEN DOOR WHEN CABIN IS PRESSURIZED PUSH BUTTON & TURN HANDLE TO OPEN DOOR CAUTION DO NOT ATTEMPT TO CHECK SECURITY OF CABIN DOOR BY MOVING DOOR HANDLE UNLESS CABIN IS DEPRESSURIZED AND AIRCRAFT IS ON THE GROUND LATCH LOCK REFERENCE ONLY SECTION 2 CENTEX AEROSPACE 006-2A HW LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 2-8 Inside Cargo Airstair Door Behind Handle: KINDS OF OPERATIONS The Beechcraft King Air 200 series airplanes are approved for the following type of operations when the required equipment is installed and operational as defined within the KINDS OF OPERATIONS EQUIPMENT LIST. VFR Day VFR Night IFR Day IFR Night Known Icing Conditions KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR, or day and night IFR, when the appropriate equipment is 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 items of equipment listed must be installed and operable unless: 1. The airplane is operated in accordance with a current Minimum Equipment List (MEL) issued by the FAA. or; 2. An alternate procedure is provided in the Pilot Operating Handbook and FAA Approved Airplane Flight Manual for the inoperative state of the listed equipment. Numbers on the Kinds of Operations Equipment List refer to quantities required to be operative for a specified condition. NOTE The following systems and equipment list does not include all equipment required by the 14 CFR Part 91 and 135 operating requirements. It also does not include components obviously required for the airplane to be airworthy, such as wings, empennage, engine, etc. LOCK PUSH BUTTON & TURN HANDLE TO OPEN DOOR CAUTION DO NOT OPEN OR CHECK SECURITY BY MOVING DOOR HANDLE WHILE AIRCRAFT IS PRESSURIZED AND/OR IN FLIGHT OPEN REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS MAY 2017 2-9 VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS ELECTRICAL POWER 1. AC Volts/Frequency Meter 1 1 1 1 1 2. Battery 1 1 1 1 1 3. DC Generator 2 2 2 2 2 4. DC GEN Annunciator 2 2 2 2 2 5. DC Load Meter 2 2 2 2 2 ENGINE INDICATIONS 1. Multifunctional Display 1 1 1 1 1 ENGINE OIL 1. Chip Detector System including Annunciators 2 2 2 2 2 2. Oil Pressure Indicator 2 2 2 2 2 3. Oil Temperature Indicator 2 2 2 2 2 4. OIL PRESS annunciator 2 2 2 2 2 ENVIRONMENTAL 1. BL AIR FAIL Annunciator 2 2 2 2 2 2. ALT WARN Annunciator (Cabin) 1 1 1 1 1 3. Cabin Rate of Climb Indicator 1 1 1 1 1 4. Differential Pressure/Cabin Altitude Indicator 1 1 1 1 1 5. DUCT OVERTEMP Annunciator 1 1 1 1 1 6. Outflow Valve 1 1 1 1 1 7. Pressurization Controller 1 1 1 1 1 8. Safety Valve 1 1 1 1 1 9. Bleed Air Shutoff Valve 2 2 2 2 2 FIRE PROTECTION 1. Engine Fire Detector System and Annunciator 2 2 2 2 2 2. Engine Fire Extinguisher Sys & Annunciator 2 2 2 2 2 FLIGHT CONTROLS 1. Flap Position Indicator 1 1 1 1 1 2. Flap System 1 1 1 1 1 3. Stall Warning Horn 1 1 1 1 1 4. Stall Warning System Ice Mode 0 0 0 0 1 5. Trim Tab Position Indicator 3 3 3 3 3 (Rudder, Aileron, and Elevator) 6. Yaw Damper System 1 1 1 1 1 7. Elevator Trim Warning System 1 1 1 1 1 REFERENCE ONLY SECTION 2 CENTEX AEROSPACE 006-2A HW LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 2-10 VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS FUEL 1. Engine Driven Boost Pump 2 2 2 2 2 2. Fuel Crossfeed System including Annunciator 1 1 1 1 1 3. Standby Fuel Boost Pump 2 2 2 2 2 4. FUEL PRESS Annunciator 2 2 2 2 2 5. Fuel Quantity Indicating System incl. Annunciators 2 2 2 2 2 6. Firewall Fuel Shutoff System incl. Annunciators 2 2 2 2 2 7. Jet Transfer Pump 2 2 2 2 2 8. Motive Flow Valve 2 2 2 2 2 9. Fuel Flow Indicator 2 2 2 2 2 ICE AND RAIN PROTECTION 1. Alternate Static Air Source 0 0 1 1 1 2. Engine Auto Ignition and Annunciators 2 2 2 2 2 3. Engine Anti-Ice System and Annunciators 2 2 2 2 2 4. Heated Fuel Vent 0 0 0 0 1 5. Heated Windshield (Left) 0 0 0 0 1 6. Pitot Heat 0 0 2 2 2 7. Pneumatic Pressure Indicator 0 0 1 1 1 8. Propeller Deicer System 0 0 0 0 1 9. Stall Warning Heat (Lift Transducer and Mounting Plate) 0 0 0 0 1 10. Surface Deicer System 0 0 0 0 1 11. Wing Ice Light (Left) 0 0 0 0 1 LANDING GEAR 1. Landing Gear Position Indicator Lights 3 3 3 3 3 2. Landing Gear Handle Light 1 1 1 1 1 3. Landing Gear Aural Warning 1 1 1 1 1 4. Alternate Landing Gear Extension System 1 1 1 1 1 5. HYD FLUID LOW Annunciator 1 1 1 1 1 6. Landing Gear Actuation System 1 1 1 1 1 LIGHTS 1. Cockpit and Instrument Lighting system 0 1 0 1 0 2. DOOR UNLOCKED Annunciator 1 1 1 1 1 3. Landing Lights 0 1 0 1 0 4. Position Lights 0 3 0 3 0 5. Anti-collision Lights System 0 1 0 1 0 6. Cabin Emergency Lighting System and Escape Path Markings Required when carrying passengers REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS MAY 2017 2-11 VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS NAVIGATION INSTRUMENTS 1. Over-speed Warning System 1 1 1 1 1 2. Left side Primary Flight Display 1 1 1 1 1 3. Right side Primary Flight Display 1 1 1 1 1 4. AHRS 2 2 2 2 2 5. Electronic Standby Instrument System (ESIS) 1 1 1 1 1 6. Magnetic Compass 1 1 1 1 1 7. Outside Air Temperature 1 1 1 1 1 OXYGEN 1. Oxygen System 1 1 1 1 1 PROPELLER 1. Prop Reversing System including Annunciators 2 2 2 2 2 2. Prop Governor Test Switch 1 1 1 1 1 3. Prop Over-speed Governor 2 2 2 2 2 4. Prop Low-Pitch Stop 2 2 2 2 2 5. Autofeather System including Annunciators 1 1 1 1 1 VACUUM SYSTEM 1. Instrument Air system 1 1 1 1 1 2. Vacuum Indicator 1 1 1 1 1 NOTE The above Kinds of Operations Equipment List does not include all specific flight instruments and communication/navigation equipment required by 14 CFR Part 91 and 135 Operating Requirements. REFERENCE ONLY SECTION 2 CENTEX AEROSPACE 006-2A HW LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 2-12 THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 3 AIRPLANE FLIGHT MANUAL SUPPLEMENT EMERGENCY PROCEDURES MAY 2017 3-1 SECTION 3 EMERGENCY PROCEDURES TABLE OF CONTENTS SUBJECT PAGE EMERGENCY AIRSPEEDS ................................................................................. 3-2 ENGINE FAILURE DURING TAKEOFF (AT OR BELOW V1).................................. 3-2 TAKEOFF ABORTED ENGINE FAILURE DURING TAKEOFF (AT OR ABOVE V1) .................................. 3-3 TAKEOFF CONTINUED CABIN EMERGENCY LIGHTING ACTIVATION ................................................... 3-3 EMERGENCY ESCAPE PATH ............................................................................. 3-3 NOTE See Beechcraft B200GT or B200 Pilot Operating Handbook for other Emergency Procedures as applicable. REFERENCE ONLY SECTION 3 CENTEX AEROSPACE 006-2A HW EMERGENCY PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 3-2 All airspeeds quoted in this section are indicated airspeeds (IAS) and assume zero instrument error. EMERGENCY AIRSPEEDS One-Engine Inoperative Best Angle-of-Climb (VXSE) ............................. 115 Knots One-Engine Inoperative Best Rate-of-Climb (VYSE) ............................... 124 Knots One-Engine-Inoperative Enroute Climb (VENR): 14,000 pounds ...................... 126 Knots 13,000 pounds ...................... 123 Knots 12,000 pounds ...................... 120 Knots 11,000 pounds ...................... 115 Knots 10,000 pounds ...................... 111 Knots 9,500 pounds ...................... 110 Knots Air Minimum Control Speed (VMCA) ........................................................ 86 Knots Raisbeck Engineering STC Prop Installation (VMCA)......................... 91 Knots BLR Aerospace STC Prop Installation (VMCA) ................................... 92 Knots Emergency Descent ............................................................................. 181 Knots Maximum Range Glide ......................................................................... 136 Knots ENGINE FAILURE DURING TAKEOFF (AT OR BELOW V1) – TAKEOFF ABORTED 1. Power Levers ........................................................................ GROUND FINE 2. Brakes ...............................AS REQUIRED TO ACHIEVE STOPPING DISTANCE 3. Operative Engine .............................. MAXIMUM REVERSE or AS REQUIRED WARNING Extreme care must be exercised when using single- engine reversing on surfaces with reduced traction. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 3 AIRPLANE FLIGHT MANUAL SUPPLEMENT EMERGENCY PROCEDURES MAY 2017 3-3 ENGINE FAILURE DURING TAKEOFF (AT OR ABOVE V1) – TAKEOFF CONTINUED 1. VR Speed ................................ ROTATE TO APPROX 8° NOSE UP ATTITUDE 2. Landing Gear (when positive climb established) ..................................... UP 3. Airspeed ................................................... V2 (MAINTAIN TO 400 FEET AGL) 4. Propeller Inoperative Engine ........................................ VERIFY FEATHERED 5. Airspeed at 400 Feet AGL ...................................................................... VENR 6. Flaps (if extended) ........................................................ UP AT V2 + 5 KNOTS 7. Climb to 1,500 Feet AGL WARNING 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. 8. Clean up (Inoperative engine) a. Condition Lever - FUEL CUT OFF b. Propeller Lever - FEATHER c. Firewall Shutoff Valve - CLOSED d. Auto Ignition - OFF e. Autofeather - OFF f. Generator - OFF g. Prop Sync - OFF 9. Electrical Load .................................................................................. MONITOR CABIN EMERGENCY LIGHTING ACTIVATION An emergency lighting system has been added to provide lighting in key areas of the passenger cabin in case there is an emergency situation, such as a loss of electrical power or when an evacuation of the aircraft is required. To manually activate the system, place the control switch located on the copilot instrument panel in the ON position. The emergency cabin flood lamps will illuminate the cabin areas near the emergency exit and door. Also, the system will automatically activate the emergency cabin flood lamps whenever the control switch is in the ARM position, and the aircraft experiences a horizontal deceleration of 2g’s, or more. EMERGENCY ESCAPE PATH Photoluminescent markings have been installed on the cabin floor outlining the aisle and the location of the emergency exit door and cabin door. Under conditions of reduced visibility, such as a cabin filled with smoke, occupants can follow this marked escape path to the exit from the aircraft. REFERENCE ONLY SECTION 3 CENTEX AEROSPACE 006-2A HW EMERGENCY PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 3-4 THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES MAY 2017 3A-1 SECTION 3A ABNORMAL PROCEDURES TABLE OF CONTENTS SUBJECT PAGE FLAPS UP LANDING ...................................................................................... 3A-2 ONE-ENGINE-INOPERATIVE APPROACH AND LANDING ............................... 3A-3 ONE-ENGINE-INOPERATIVE GO-AROUND..................................................... 3A-5 OVERWEIGHT LANDING ................................................................................ 3A-5 NOTE See Beechcraft B200GT or B200 Pilot Operating Handbook as applicable for other abnormal procedures. REFERENCE ONLY SECTION 3A CENTEX AEROSPACE 006-2A HW ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 3A-2 FLAPS UP LANDING Refer to Section 5 of Supplement AFM 006-2A HW for Flaps Up Landing Distance. WEIGHT POUNDS VREF (FLAPS UP) KNOTS 14,000 128 13,500 126 13,000 124 12,000 121 11,000 118 10,000 115 9,000 111 1. Approach Speed, VREF (Flaps Up) ....................................................... CONFIRM 2. Autofeather ..............................................................................................ARM 3. Pressurization......................................................................................... CHECK 4. Cabin Sign............................................................................. NO SMOKE & FSB 5. Flaps ............................................................................................................. UP CAUTION 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 flap up landing. 6. Flap Override (If installed)..................................................................... SELECT 7. Landing Gear ......................................................................................... DOWN 8. 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. Surface Deice .................................................................. CYCLE (as required) If wings are free of ice: 11. Stall Warning Ice Mode Switch  PRESS (to select Normal Mode) If residual ice remains on wing boots: 12. Surface Deice ........................................................................................CYCLE 13. Stall Warning Ice Mode Annunciator ....................................... ILLUMINATED 14. Approach Speed and Landing Distance ...... INCREASE VREF BY 15 KNOTS AND INCREASE LANDING DISTANCE BY 25 PER CENT. See LANDING DISTANCE chart in Section 5 of Supplement AFM 006-2A HWREFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES MAY 2017 3A-3 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. NOTE If crosswind landing is anticipated, determine Crosswind Component from Section 5, PERFORMANCE. 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. Use propeller reverse as desired. When Landing Is Assured: 15. Approach Speed .............. VREF  ESTABLISHED (With ice on wings, VREF + 15) 16. Yaw Damp ................................................................................................ OFF 17. Power Levers........................................................................................... IDLE 18. Propeller Levers .................................................................... FULL FORWARD After Touchdown: 14. Power Levers...... LIFT AND SELECT GROUND FINE OR REVERSE (as required) 15. Brakes ....................................................................................... AS REQUIRED ONE-ENGINE-INOPERATIVE APPROACH AND LANDING WEIGHT POUNDS Flaps DOWN VREF Speeds, KNOTS 14,000 106 13,500 105 13,000 104 12,000 102 11,000 99 10,000 96 9,000 93 1. Approach Speed, VREF ........................................................................ CONFIRM 2. Fuel Balance ........................................................................................... CHECK 3. Pressurization ........................................................................................ CHECK 4. Cabin Sign ............................................................................ NO SMOKE & FSB When It Is Certain that the Field Can Be Reached: 5. Flaps ............................................................................................... APPROACH 6. Landing Gear ......................................................................................... DOWN 7. Propeller Lever (operating engine) ......................................... FULL FORWARD 8. Airspeed ..............................................................................................VREF + 10 REFERENCE ONLY SECTION 3A CENTEX AEROSPACE 006-2A HW ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 3A-4 9. Interior and Exterior lights ..........................................................AS REQUIRED 10. Radar .........................................................................................AS REQUIRED 11. Surface Deice .................................................................. CYCLE (as required) If wings are free of ice: 12. Stall Warning Ice Mode Switch .................... PRESS (to select Normal Mode) If residual ice remains on wing boots: 13. Surface Deice ........................................................................................CYCLE 14. Stall Warning Ice Mode Annunciator ....................................... ILLUMINATED 15. Approach Speed and Landing Distance INCREASE VREF BY 15 KNOTS AND INCREASE LANDING DISTANCE BY 25 PERCENT See LANDING DISTANCE chart in Section 5 of Supplement AFM 006-2A HW. 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. NOTE If crosswind landing is anticipated, determine Crosswind Component from Section 5, PERFORMANCE. 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. When it is Certain There is No Possibility of a Go-Around 16. Flaps .......................................................................................................... DN 17. Airspeed .................................................... VREF (With ice on wings, VREF + 15) 19. Perform normal landing. NOTE Single-engine reverse thrust may be used with caution after touchdown on smooth, dry, paved surfaces. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES MAY 2017 3A-5 ONE-ENGINE-INOPERATIVE GO-AROUND 1. Power ......................................................................... MAXIMUM ALLOWABLE 2. Landing Gear ................................................................................................ UP 3. Flaps ............................................................................. UP AT VREF + 10 KNOTS 4. Airspeed .................................................................................. VREF + 20 KNOTS OVERWEIGHT LANDING WEIGHT POUNDS VREF KNOTS 14,000 106 13,500 105 When Landing Is Assured: 1. Flaps ...................................................................................................... DOWN 2. Airspeed ..................................................................................................... VREF 3. Yaw Damp .................................................................................................. OFF 4. Power Levers............................................................................................. IDLE 5. Propeller Levers ...................................................................... FULL FORWARD CAUTION To ensure constant reversing characteristics, the propeller levers must be in the high rpm position. 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 13,500 pounds, which is the maximum landing weight limitation. When the airplane is landed at a gross weight above 13,500 pounds the pilot should request that an inspection in accordance with the King Air 200 Series Maintenance Manual Section 5-50-00, Inspection After Hard Landing be performed before the next flight. REFERENCE ONLY SECTION 3A CENTEX AEROSPACE 006-2A HW ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 3A-6 THIS PAGE IS INTENTIONALLY BLANK REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES MAY 2017 4-1 SECTION 4 NORMAL PROCEDURES TABLE OF CONTENTS SUBJECT PAGE AIRSPEEDS FOR SAFE OPERATION ................................................................ 4-2 PROCEDURES BY FLIGHT PHASE PREFLIGHT INSPECTION .......................................................................... 4-3 BEFORE ENGINE STARTING .................................................................. 4-3 BEFORE TAKEOFF (RUNUP) .................................................................. 4-3 TAKEOFF ............................................................................................... 4-4 ENROUTE CLIMB ICING CONDITIONS ....................................................................... 4-4 CRUISE ICING CONDITIONS ....................................................................... 4-5 BEFORE LANDING ................................................................................. 4-6 NORMAL LANDING.................................................................................. 4-7 MAXIMUM REVERSE THRUST LANDING.................................................. 4-7 BALKED LANDING ................................................................................. 4-7 SHUT DOWN AND SECURING ............................................................... 4-7 OTHER PROCEDURES ICING FLIGHT ........................................................................................ 4-8 TAKEOFF TRIM WARNING TEST ............................................................ 4-8 STALL WARNING SYSTEM OPERATION .................................................. 4-9 CABIN EMERGENCY LIGHTING SYSTEM OPERATION ............................ 4-9 CHARGING EMERGENCY ESCAPE PATH MARKINGS ........................... 4-10 OVERWEIGHT LANDING ...................................................................... 4-10 NOISE CHARACTERISTICS ................................................................... 4-10 REFERENCE ONLY SECTION 4 CENTEX AEROSPACE 006-2A HW NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 4-2 All airspeeds are indicated airspeeds (IAS) and assume zero instrument error. AIRSPEEDS FOR SAFE OPERATION Maximum Demonstrated Crosswind Component ................................. 25 Knots Maximum Demonstrated Wind Components for Coupled Approaches Crosswind...................................................................... See basic AFM / POH Tailwind......................................................................... See basic AFM / POH Takeoff (Flaps UP) Decision Speed, V1 ......................................................................................... Rotation, VR .................................................................................................... Safety Speed, V2 ............................................................................................. Enroute Climb, VENR ........................................................................................ Takeoff (Flaps Approach) Decision Speed, V1 ......................................................................................... Rotation, VR .................................................................................................... Safety Speed, V2 ............................................................................................. Enroute Climb, VENR ........................................................................................ Two-Engine Best Angle-of-Climb (VX)................................................... 100 Knots Two-Engine Best Rate-of-Climb (VY) .................................................... 125 Knots Cruise Climb: Sea level to 10,000 feet ................................................................. 160 Knots 10,000 feet to 20,000 feet ............................................................. 140 Knots 20,000 feet to 25,000 feet ............................................................. 130 Knots 25,000 feet to 35,000 feet ............................................................. 120 Knots Maximum Airspeed for Effective Windshield Anti-icing ...................... 226 Knots Operating Maneuvering Speed (VO) ..................................................... 181 Knots Turbulent Air Penetration .................................................................... 170 Knots CAUTION 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. Landing Approach: Flaps Down.................................................. VREF, see Section 5 Performance Balked Landing Climb ........................................ VREF, see Section 5 Performance Intentional One-Engine-Inoperative Speed (VSSE) ................................ 104 Knots Air Minimum Control Speed (VMCA) Hartzell & McCauley propellers ....................................................... 86 Knots Raisbeck Engineering STC SA2698NM-S, Flaps Up .......................... 91 Knots Flaps Approach ............... 88 Knots BLR Hartzell STC SA02130SE, Flaps Up .......................................... 92 Knots Flaps Approach ............................... 87 Knots See Section 5 Performance for Takeoff Speeds REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES MAY 2017 4-3 PROCEDURES BY FLIGHT PHASE NOTE Refer to all applicable Supplements for flight phase procedures for optional equipment installed in the airplane. The procedures listed below are required for airplanes modified by the installation of the CenTex Aerospace Halo 275 Conversion. PREFLIGHT INSPECTION CABIN/COCKPIT Add the following steps while Battery Switch is OFF. Emergency Lighting Cabin Switch ............................................................. ON Emerg Cabin Lt Control Switch................................................................ARM Emergency Cabin Flood Lamps ...................................... CHECK (illuminated) Add the following step when Battery Switch is ON Emergency Cabin Flood Lamps ................................ CHECK (not illuminated) Add the following step after the Battery Switch is turned OFF. Emergency Lighting Cabin Switch ............................................................ OFF Emergency Escape Path Markings ............. MUST BE UNCOVERED & VISIBLE BEFORE ENGINE STARTING Add the following step after airstair door is LOCKED. Emergency Lighting Cabin Switch ............................................................. ON Add the following steps after the Battery Switch is ON. Left Power Lever ............................... ADVANCE TO AT LEAST 80% POSITION Autofeather Switch .................................................................................ARM Elevator Trim Warning System ............................................................... TEST Elevator Trim Control......................................................... SET FOR TAKEOFF Autofeather Switch .................................................................................. OFF Left and Right Power Levers ................................................................... IDLE BEFORE TAKEOFF (RUNUP) Add the following steps after the Surface Deice System check. Stall Warning Ice Mode Annunciator ....................................... ILLUMINATED Stall Warning........................................................................................... TEST Stall Warning Ice Mode Annunciator ........... PRESS (to select Normal Mode) NOTE The stall warning system must be in the Normal Mode during takeoff and initial climb-out. If a takeoff is conducting 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 006-2A HW NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 4-4 TAKEOFF 1. Brakes ..................................................................................................... HOLD 2. Power ................................. SET (ensure minimum takeoff power is available) 3. [L AFX] and [R AFX] or ................................................................ ILLUMINATED [L AUTOFEATHER] and [R AUTOFEATHER] ................................. ILLUMINATED 4. Brakes .................................................................................................RELEASE NOTE Increasing airspeed will cause torque and ITT to increase. 5. VR ................................................ ROTATE TO APPROX. 8° NOSE UP ATTITUDE 6. Landing Gear (when positive climb established) ......................................... UP 7. Airspeed ........................................ MAINTAIN V2 UNTIL CLEAR OF OBSTACLES 8. Flaps (at V2 + 5 Knots) .................................................................................. UP CLIMB Add the following after normal climb checklist. CLIMB IN ICING CONDITIONS 1. Engine Anti-Ice ........................................................................................ ON [L ENG ANTI-ICE] & [R ENG ANTI-ICE] ILLUMINATED 2. Auto Ignition .........................................................................................ARM 3. Prop Deice ........................................................................................... AUTO 4. Stall Warning Heat .................................................................. CONFIRM ON 5. Left and Right Fuel Vent Heat ................................................. CONFIRM ON 6. Left and Right Pitot Heat ........................................................ CONFIRM ON 7. Windshield Anti-Ice ............................................. CONFIRM NORMAL OR HI At first sign of ice accretion on aircraft. 8. Surface Deice Switch ................. SINGLE AND RELEASE (repeat as required) 9. Stall Warning Ice Mode Annunciator .................................... ILLUMINATED 10. Climb Power ........................... SET MAX CONT POWER (to expedite climb) 11. Airspeed ................................................. 148 KNOTS MINIMUM AIRSPEED REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES MAY 2017 4-5 CRUISE Add the following after normal cruise checklist. CRUISE IN ICING CONDITIONS At first sign of ice accretion on aircraft. 1. Airspeed – 148 KNOTS MINIMUM 2. Surface Deice Switch  SINGLE AND RELEASE 3. Stall Warning Ice Mode Annunciator – VERIFY ILLUMINATED OUTSIDE OF ICING CONDITIONS AND WINGS FREE OF ICE 1. Stall Warning Ice Mode Annunciator  PRESS (to select Normal Mode) 2. Stall Warning Ice Mode Annunciator – EXTINGUISHED ICING CONDITIONS Replace the warning statement with the following: Due to distortion of the wing airfoil, ice accumulation on the leading edges can cause a significant loss in rate of climb and in cruise speed, as well as increases in stall speed. Even after cycling deicing boots, the ice accumulation remaining on the boots plus ice accumulations on unprotected areas can cause large performance losses. In order to minimize ice accumulation on unprotected surfaces of the wing, maintain a minimum of 148 knots during operations in sustained icing conditions. 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. The stall warning system will sound the aural warning at 15 to 20 knots above the normal warning speed when it is in the ice mode, which is appropriate when there is ice on the wings. Add the following after Surface Deice. At first sign of ice accretion on aircraft. a. Airspeed – 148 KNOTS MINIMUM b. Surface Deice Switch – SINGLE AND RELEASE c. Stall Warning Ice Mode Annunciator – VERIFY ILLUMINATED d. Repeat as required If Single Position of the Surface Deice Switch Fails: e. Surface Deice Switch – MANUAL AND HOLD FOR A MINIMUM OF 6 SECONDS, THEN RELEASE f. Stall Warning Ice Mode Annunciator – VERIFY ILLUMINATED g. Repeat as required. Add the following. OUTSIDE OF ICING CONDITIONS AND WINGS FREE OF ICE a. Stall Warning Ice Mode Annunciator – PRESS (to select Normal Mode) b. Stall Warning Ice Mode Annunciator – EXTINGUISHED WARNING REFERENCE ONLY SECTION 4 CENTEX AEROSPACE 006-2A HW NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 4-6 BEFORE LANDING 1. Approach Speed ................................................................... CONFIRM VREF 2. Autofeather .........................................................................................ARM 3. Pressurization................................................................................... CHECK 4. Cabin Sign ....................................................................... NO SMOKE & FSB 5. Flaps ......................................................................................... APPROACH 6. Landing Gear ......................................................................................... DN 7. Lights .....................................................................................AS REQUIRED NOTE Under low visibility conditions, landing and taxi lights should be left off due to light reflections. 8. Radar .....................................................................................AS REQUIRED 9. Surface Deice ............................................................. CYCLE AS REQUIRED If wings are free of ice: 10. Stall Warning Ice Mode Switch ................ PRESS (to select Normal Mode) If residual ice remains on wing boots: 11. Surface Deice ....................................................................................CYCLE 12. Stall Warning Ice Mode Annunciator ................................... ILLUMINATED 13. Approach Speed and Landing Distance .......... INCREASE VREF BY 15 KNOTS AND INCREASE EXPECTED LANDING DISTANCE BY 25 PERCENT In the NOTE replace last sentence with “Stall speeds can be expected to increase as much as 15 knots if ice is present on the wings and/or horizontal tail surfaces.” REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES MAY 2017 4-7 NORMAL LANDING When Landing Is Assured 1. Flaps ................................................................................................ DOWN 3. Airspeed ................................................ VREF (With ice on wings, VREF + 15) 4. Yaw Damper ......................................................................................... OFF 5. Power Levers....................................................................................... IDLE 6. Prop Levers ....................................................................... FULL FORWARD After Touchdown: 7. Power Levers............................................ LIFT AND SELECT GROUND FINE 8. Brakes ................................................................................... AS REQUIRED MAXIMUM REVERSE THRUST LANDING Replace step 2: 2. Airspeed .............................................. VREF (With ice on wings, VREF + 15) BALKED LANDING 1. Power ................................................................... MAXIMUM ALLOWABLE 2. Airspeed ............................................................................ MAINTAIN VREF When clear of obstacles or 400 feet AGL, establish a normal climb. 3. Flaps (at VREF + 10) .................................................................... APPROACH 4. Landing Gear ......................................................................................... UP 5. Flaps (at 125 knots) ................................................................................ UP SHUT DOWN AND SECURING Add the following steps. 16. Emerg Cabin Lt Switch ......................................................................... OFF 20. Emergency Cabin Light Power Switch .................................................. OFF REFERENCE ONLY SECTION 4 CENTEX AEROSPACE 006-2A HW NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 4-8 OTHER PROCEDURES ICING FLIGHT Refer to Section 2 Limitations of this Supplement for limitations relating to icing flight. See Section 3A for abnormal procedures associated with icing equipment malfunctions and procedures required for severe icing conditions. See the BEFORE TAKEOFF (RUNUP) and CRUISE checklists in this section for normal ground and in-flight procedures pertaining to flight in icing conditions. At first sign of ice accretion on aircraft: a. Airspeed ................................................................. 148 KNOTS MINIMUM b. Surface Deice Switch ................................................ SINGLE AND RELEASE c. Stall Warning Ice Mode Annunciator ....................... VERIFY ILLUMINATED d. Repeat as required TAKEOFF TRIM WARNING TEST A warning system has been added that provides a constant tone aural alert in the cockpit when the elevator trim tab is not set within the acceptable range for takeoff and engine power is increased above approximately 80% N1. The system should be tested for proper operation before the first flight of each day while conducting the BEFORE ENGINE STARTING procedure. To perform this test the trim warning system must first be activated by placing the Autofeather switch to ARM. Then the left power lever must be advanced past the 80% N1 position. The system should now be tested by adjusting the elevator trim tab to a position outside of the takeoff range marked on the tab position indicator in both the nose up and the nose down directions. The aural alert should sound just as the tab position indicator moves outside of the takeoff range. The aural alert should be silent when the tab position is inside of the takeoff range. When the power levers are advanced to initiate a takeoff and the aural alert sounds, immediately reduce power to idle and abort the takeoff. Do not takeoff when the elevator trim tab position is not set within the takeoff range. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES MAY 2017 4-9 STALL WARNING SYSTEM OPERATION An ICE MODE feature has been added to the stall warning system. The ice mode is automatically activated when the Surface Deice system is selected by the pilot. Illumination of the STALL WARNING ICE MODE annunciator indicates the stall warning system is operating in the ice mode. After exiting icing conditions and when the aircraft is free of ice, transfer the stall warning system to the normal mode by pressing and releasing the STALL WARNING ICE MODE annunciator. CABIN EMERGENCY LIGHTING SYSTEM OPERATION An emergency lighting system has been added to provide supplemental lighting in the passenger cabin around the emergency exit door and cabin door. Two switches – a cabin switch located in the ceiling and a control switch located in the copilot instrument panel – control operation of the system. When entering the cabin during the preflight inspection the charge level of the emergency lighting system battery pack should be verified. To do this, place the cabin switch to ON with the aircraft battery switch OFF. The emergency cabin flood lamps should illuminate. If the lamps do not illuminate, the emergency lighting system batteries have been discharged or there is a malfunction in the system. Discharged batteries must be removed and recharged or replaced. The Instructions for Continued Airworthiness manual describes the proper procedures for removing and recharging or replacing the cabin emergency lighting system batteries. Before taxiing, place the cabin switch to ON and the control switch to ARMED. This is the switch configuration for normal taxiing and flight operations. When shutting down and exiting the airplane, place both the control switch and the cabin switch to OFF. It is acceptable to utilize the flood lamps to illuminate the cabin whenever needed, such as for boarding or to charge the photoluminescent escape path markings. Limit the time the flood lamps are being powered by the emergency lighting system battery to no more than 20 minutes to ensure the battery will have remaining capacity in case of an emergency. REFERENCE ONLY SECTION 4 CENTEX AEROSPACE 006-2A HW NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 4-10 CHARGING EMERGENCY ESCAPE PATH MARKINGS Photoluminescent markings have been installed on the cabin floor outlining the aisle and the paths to the emergency exit door and cabin door. The markings must be charged during preflight operations by illuminating the cabin with either or a combination of sunlight through the cabin windows, the cabin lights, or the emergency cabin flood lamps when any part of that flight will be conducted in darkness. The table below lists the minimum charging time to ensure the markings will perform as intended throughout the respective flight. Required Charging of Emergency Escape Path Markings Charging Time Duration of Acceptable Luminance 5 minutes 1.5 hours 10 minutes 2.5 hours 20 minutes 4 hours 30 minutes 5 hours OVERWEIGHT LANDING An overweight landing is defined as any landing made when the airplane gross weight is heavier than 13,500 pounds, which is the maximum landing weight limitation. If it becomes necessary to land the airplane at a gross weight heavier than 13,500 pounds the pilot should request that an inspection in accordance with the King Air 200 Series Maintenance Manual Section 5-50-00 Inspection After Hard Landing be performed before the next flight. NOISE CHARACTERISTICS The takeoff noise level of King Air 200 series airplanes modified in accordance with the CenTex Aerospace Halo 275 Conversion established in compliance with 14 CFR Part 36, Appendix G and ICAO Annex 16, Chapter 10 is 85.3 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 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-1 SECTION 5 PERFORMANCE TABLE OF CONTENTS SUBJECT PAGE Introduction to Commuter Category Performance and Flight Planning ......... 5-2 Takeoff Path Profile ........................................................................................ 5-5 Maximum Allowed Takeoff Weight ................................................................ 5-6 Maximum Allowed Landing Weight ................................................................ 5-6 Performance Example ..................................................................................... 5-6 Airspeed Calibration – Normal System, Take-Off Ground Roll ..................... 5-12 Stall Speeds – Zero Thrust............................................................................. 5-13 Maximum Allowed Takeoff Weight (LBS) – Flaps Up .................................... 5-14 Maximum Takeoff Weight – Flaps Up, Limited By Brake Energy .................. 5-15 Maximum Tire Speed During Takeoff – Flaps Up .......................................... 5-16 Maximum Allowed Takeoff Weight (LBS) – Flaps Approach ......................... 5-17 Maximum Takeoff Weight – Flaps Approach, Limited By Brake Energy ....... 5-18 Maximum Tire Speed During Takeoff – Flaps Approach ............................... 5-19 Service Ceiling - One Engine Inoperative ...................................................... 5-20 Using Takeoff Speeds & Field Length Tables................................................. 5-21 Takeoff Speeds & Field Lengths – Flaps Approach........................................ 5-23 Takeoff Field Length Correction – Flaps Approach ....................................... 5-45 Accelerate Stop Distance – Flaps Approach .................................................. 5-46 Net Gradient of Climb – Flaps Approach....................................................... 5-47 Takeoff Speeds & Field Lengths – Flaps UP ................................................... 5-49 Takeoff Field Length Correction – Flaps UP .................................................. 5-71 Accelerate Stop Distance – Flaps UP............................................................. 5-72 Net Gradient of Climb – Flaps UP ................................................................. 5-73 Climb – One Engine Inoperative ................................................................... 5-74 Climb – Two Engines – Flaps Up.................................................................... 5-75 Time, Fuel, and Distance to Climb ................................................................ 5-76 Close-In Takeoff Flight Path .......................................................................... 5-77 Distant Takeoff Flight Path............................................................................ 5-78 Total Height Required - Pressure Altitude Conversion ................................. 5-79 Maximum Cruise Power, ISA ......................................................................... 5-80 Maximum Range Power, ISA ......................................................................... 5-81 One Engine Inoperative Maximum Cruise Power ......................................... 5-82 Time, Fuel, Distance to Descend ................................................................... 5-83 Maximum Allowed Landing Weight – To Achieve Landing Climb Req .......... 5-84 Maximum Allowed Landing Weight – To Achieve Landing Climb Req (Ice) .. 5-85 Discontinued Approach Climb Gradient ....................................................... 5-86 Climb – Balked Landing ................................................................................. 5-87 Landing Distance Without Propeller Reversing ............................................ 5-88 Landing Distance With Propeller Reversing .................................................. 5-89 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-2 INTRODUCTION TO COMMUTER CATEGORY PERFORMANCE AND FLIGHT PLANNING REGULATORY COMPLIANCE Information in this section is provided for the purpose of maintaining compliance with the applicable certification requirements of 14 CFR Part 23, which imposes specific performance based limitations. The airplane will not meet these performance limitations under all atmospheric conditions for which it is approved at the maximum takeoff weight of 14,000 pounds and at the maximum landing weight of 13,500 pounds. Therefore, the operating weight must be reduced under some atmospheric conditions. The maximum operating weights are limited by the following performance data and compliance therewith is mandatory. For all 14 CFR Part 91 and Part 135 operations: 1. Maximum Allowed Takeoff Weight (to achieve takeoff climb requirements and limited by brake energy) 2. Maximum Tire Speed During Takeoff (to not exceed maximum tire speed rating) 3. Takeoff Field Length 4. Maximum Allowed Landing Weight (to achieve landing climb requirements) 5. Landing Distance For 14 CFR Part 135 operations only: 6. Service Ceiling - One Engine Inoperative FLIGHT TEST PERFORMANCE CONDITIONS All performance data presented in this section is based on FAA-approved performance data taken from applicable King Air 200 series Airplane Flight Manual(s) and verified by FAA flight testing. 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 paved, dry runway. 4. Runway or takeoff and landing performance was obtained using the following procedures and conditions: REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-3 ONE ENGINE INOPERATIVE TAKEOFF (ACCELERATE-GO)  Static takeoff power was set.  The critical engine was shutdown with the condition lever just prior to V1. The Autofeather system was allowed to feather the inoperative engine propeller.  The acceleration was continued to VR and the airplane was rotated to an attitude of approximately 8° nose up.  The landing gear was retracted when a positive rate of climb was established.  V2 was attained by 35 feet AGL and maintained until 400 feet AGL. REJECTED TAKEOFF (ACCELERATE STOP)  Static takeoff power was set.  The critical engine was shut down with the condition lever just prior to V1.  Both power levers were rapidly moved to the idle position in one continuous motion at V1.  Maximum braking was immediately initiated and maintained until the airplane came to a complete stop. ALL ENGINES TAKEOFF  Static takeoff power was set.  The airplane was accelerated to VR and the airplane was rotated to an attitude of approximately 8° nose up.  The landing gear was retracted when a positive rate of climb was established.  V2 was attained by 35 feet AGL and maintained until 400 feet AGL. LANDING  Power was set to maintain a 3° approach angle with the airspeed stabilized at VREF.  Both power levers were moved to the idle position when the airplane reached 50 feet AGL.  Maximum braking was immediately initiated and maintained until the airplane came to a complete stop. REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-4 PERFORMANCE CONFIGURATIONS No. of Oper- ating 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 Enroute Climb 1 Max Continuous Up Up Approach Climb 1 Max Continuous Approach Up Balked Landing Climb 2 Takeoff Landing Down FLIGHT PLANNING Flight planning is an essential part of operating this airplane. Proper flight planning ensures that the pilot is complying with the applicable 14 CFR Part 23 regulatory requirements, which are intended to increase the level of safety. The regulations applicable to Commuter category airplanes impose performance minimums that must be met in order for the airplane to takeoff and land using a specified departure and destination runway. These additional performance minimums make sure, in the event there is an engine failure during takeoff, the airplane can be stopped on the available runway or the airplane’s climb performance is adequate to clear obstacles within the takeoff flight path. It is the pilot’s responsibility to do the proper flight planning and thereby make certain the airplane’s performance will meet the required minimums under the actual conditions. When the actual conditions are such that the performance minimums cannot be met, the pilot must elect to lower the gross weight of the airplane, select a longer runway, or wait until outside air temperatures cool sufficiently so the performance minimums will be met. Furthermore, the takeoff flight path profile that the pilot must fly is defined in this section. The subsequent paragraph TAKEOFF PATH PROFILE shows and explains the new takeoff flight path profile, which is typical for commuter and transport category airplanes. The profile has multiple segments where the takeoff speeds and airplane configurations are applicable from the beginning of the takeoff run until the airplane reaches 1,500 feet above ground level. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-5 The performance data in this section are presented in a familiar format, similar to the Beechcraft performance charts, tables, and graphs in the basic AFM/POH. However, the tabular presentations of takeoff field lengths and of maximum allowed takeoff and landing weight to meet minimum climb requirements are new to the operators and pilots of the King Air 200 series airplanes. These tables should prove to be straightforward and easy to use. It is noted interpolation of the tabulated data can be utilized when needed. The following example shows how to properly plan for a typical flight. The departure airport and destination airport were selected for the following example so that there is similarity with the flight planning example found in the Beechcraft King Air B200/B200GT series AFM/POH. Please note the airport, weather, and route information presented in this example are not to be considered accurate or reliable and should not be used for any actual flight plan. It is presented here only as an example of how to properly plan a flight and how to correctly utilize the performance data in this section. TAKEOFF PATH PROFILE For the King Air B200/B200GT series airplanes with the Halo 275 Commuter category conversion, the takeoff path is defined as shown below. The performance data presented in this section provide the parameters that are needed to construct such a takeoff path for a given departure runway and location. The variable the pilot must consider and restrict, if necessary, is the takeoff weight. This is required to ensure the takeoff path of the airplane will not require more runway than is available and will clear all obstacles. REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-6 MAXIMUM ALLOWED TAKEOFF WEIGHT The maximum takeoff weight limit from Section 2 Limitations is 14,000 pounds. However, the maximum allowed takeoff weight may be less than the maximum takeoff weight limit depending on the available runway length and any obstacles in the takeoff path, the engine inoperative climb performance of the airplane, the braking energy that would be needed to abort a takeoff at decision speed (V1), and the tire speed rating. Below is a list of the performance data tables and charts contained in this section that establish the maximum allowed takeoff weight.  MAXIMUM ALLOWED TAKEOFF WEIGHT – FLAPS UP / APPROACH TO MEET TAKEOFF CLIMB REQUIREMENTS  MAXIMUM ALLOWED TAKEOFF WEIGHT LIMITED BY BRAKE ENERGY – FLAPS UP / APPROACH  MAXIMUM TIRE SPEED DURING TAKEOFF - FLAPS UP / APPROACH  SERVICE CEILING - ONE ENGINE INOPERATIVE (14 CFR PART 135 OPERATIONS)  TAKEOFF SPEEDS & FIELD LENGTHS – FLAPS UP / APPROACH MAXIMUM ALLOWED LANDING WEIGHT The maximum landing weight limit from Section 2 Limitations is 13,500 pounds. However, the maximum allowed landing weight may be less if a reduction in weight is required so that the engine inoperative climb performance during a discontinued/missed approach meets the minimum requirement. The following chart(s) should be used to determine the maximum allowed landing weight:  MAXIMUM ALLOWED LANDING WEIGHT - TO ACHIEVE LANDING CLIMB REQUIREMENTS  MAXIMUM ALLOWED LANDING WEIGHT - TO ACHIEVE LANDING CLIMB REQUIREMENT WITH ICE ACCUMULATIONS PRESENT  LANDING DISTANCE (WITHOUT/WITH) PROPELLER REVERSE  CLIMB -BALKED LANDING (Note-requirement met at all weights) PERFORMANCE EXAMPLE CONDITIONS At Departure: Outside Air Temperature .............................................................................. 28°C Field Elevation ...................................................................................... 5,333 feet Altimeter Setting ......................................................................... 29.82 Inches Hg Wind .......................................................................................... 330° at 10 knots Runway 35L length ............................................................................. 11,500 feet Runway 35L gradient ......................................................................... 0.4% Down Pressure Altitude ........................5,333 ft + (29.92-29.82) x 1,000 ft = 5,433 feet Temperature Relative to ISA ......... 28°C - (ISA @ 5,333 ft) = 28° - 4° => ISA+24°C REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-7 Route Segment Course Dist. NM Wind, Temp. at FL 260 Temp. FL 180 LEG A 265° M 252° T 143 350°/40ks, -10°C -6°C LEG B 321° M 255° T 192 350°/40ks, -10°C -6°C LEG C 270° M 233° T 81 340°/35ks, -20°C 0°C LEG D 250° M 234° T 145 340°/35ks, -20°C 0°C LEG E 227° M 210° T 146 290°/45ks, -20°C -4°C At Destination: Outside Air Temperature .............................................................................. 32°C Field Elevation...................................................................................... 4,412 feet Altimeter Setting......................................................................... 29.60 Inches Hg Wind ............................................................................................ 270° at 5 knots Runway 25 length ................................................................................ 6,101 feet Pressure Altitude ........................4,412 ft + (29.92-29.60) x 1,000 ft = 4,732 feet MAXIMUM ALLOWED TAKEOFF WEIGHT TABLES TO MEET TAKEOFF CLIMB REQUIREMENTS The maximum allowed takeoff weight must be established for the takeoff configuration (i.e, flaps up or flaps approach) and the departure conditions (i.e., pressure altitude and outside air temperature). These two tables list the maximum allowed takeoff weight for the corresponding configuration at which the airplane will meet the first, second, and final segment climb requirements. A computation using interpolation shows the MATOW to be 13,252 pounds for flaps up and 11,797 pounds for flaps approach. NOTE: Similarly, the maximum allowed landing weight should be established for the arrival conditions during preflight planning. The landing weight (i.e., takeoff weight minus the fuel consumed enroute to the destination) must not be greater than the maximum allowed landing weight. MAXIMUM ALLOWED TAKEOFF WEIGHT LIMITED BY BRAKE ENERGY CHART Determine with the applicable chart whether a reduction in takeoff weight is necessary to not exceed the brake energy rating during a rejected/aborted takeoff run. For this example, no reduction in takeoff weight is required. REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-8 MAXIMUM TIRE SPEED DURING TAKEOFF CHARTS Determine with the applcable chart whether the takeoff conditions will cause the tire speed rating(s) to be exceeded. The lowest tire speed rating approved for airplanes with this conversion is 160 MPH. Do not attempt a takeoff if the tire speed rating will be exceeded. Change runway to reduce a tail wind or increase a headwind component, or wait until conditions are acceptable. Also, tires with a speed rating of 170 MPH or greater can be installed. For this example, the maximum tire speed will be less than 160 mph. SERVICE CEILING – ONE ENGINE INOPERATIVE CHART This chart establishes the maximum weight at which the airplane will climb at least 50 feet per minute with one engine inoperative and the associated propeller feathered. It also serves to provide the altitudes necessary to comply with 14 CFR Section 135.181 or 135.391 performance requirements for operations under Part 135 regulations. A check of the example shown on the Service Ceiling – One Engine Inoperative chart shows for an outside temperature of -6°C and a Minimum Enroute Altitude of 18,000 Feet the maximum gross weight at the MEA is 12,200 pounds. Note, to determine the maximum takeoff weight that results in a service ceiling equal to the highest Maximum Enroute Altitude (MEA), add the weight of the fuel used to reach a MEA to the weight from this chart that provides the required service ceiling. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-9 TAKEOFF SPEEDS & FIELD LENGTHS TABLES There are two sets of takeoff speeds and field length tables - one set for flaps up and the other set for flaps approach. The pilot can choose either of these two flap settings for takeoff, but the corresponding maximum allowed takeoff weight, accelerate stop distance, and net gradient of climb data must be applied. Takeoff speeds are the takeoff decision speed (V1), rotation speed (VR), safety speed (V2), and final segment climb speed (VENR) that apply to the takeoff condition. The field lengths presented in these charts allow the airplane to be stopped within the distance shown when an engine fails at a speed below V1 and the pilot immediately aborts the takeoff with maximum braking. Also, the field lengths are sufficient to allow a takeoff to be continued and to reach a height of 35 feet above the point of liftoff within the distance shown when an engine failure occurs at V1, the airplane is rotated at VR, and V2 is obtained and maintained before or upon reaching the 35 feet height. A preliminary look at the takeoff field length required for a flaps-up takeoff at the performance example departure conditions and at a gross weight of 13,252 pounds shows the required field length to be very close to the available runway length of 11,500 feet. As you can see, interpolation is required to determine whether the takeoff field length is greater than the available runway. Also, if pressure altitude is between table values, select the next higher pressure altitude. Below is an example of how to interpolate takeoff field length for temperatures that are between values shown in the table. For Flaps Up: TOW of 13,252 lbs, Pressure Altitude 5,500 ft, and, OAT of 28°C. A computation using interpolation shows the uncorrected TFL to be 11,636 feet. The corresponding V1, Vr, V2, and VENR takeoff speeds are 115, 115, 125, 125 knots, respectively. TAKEOFF FIELD LENGTH CORRECTION CHART Use these charts to correct the takeoff field length for runway slope/gradient and for headwind and tail wind components. When the runway surface is not flat, the takeoff field length should be corrected to account for the effect of a sloping takeoff surface. A downward slope will aid in accelerating the airplane and thus reduces the field length. However, if the accelerate-stop distance is the deciding field length, a downward slope will result in a longer field length. This effect can be seen for field lengths less than approximately 4,000 feet. REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-10 The uncorrected TFL distance of 11,636 feet can now be corrected for the runway 35 downward gradient of 0.4% and effect of wind (330° at 10 knots) using this chart. For determining headwind or tail wind component see the WIND COMPONENTS graph in the basic AFM/POH. The example on the chart shows the corrected TFL to be 10,930 feet, which is less than the available length of runway 35 at the departure airport. CLEARWAYS If the runway to be used for takeoff has a clearway, up to 20% of the field length required for takeoff can be over the clearway. Check the runway declared distance information, which is published in the Airport/Facility Directory, to determine whether the runway has a clearway. This information will include the following lengths if a clearway exists:  TORA (takeoff run available)  TODA (takeoff distance available)  ASDA (accelerate-stop distance available) Note - The length of a clearway is TODA minus TORA. To utilize a clearway all of the following conditions must be met: 1. The TORA must be at least 80% of the required field length. 2. The TODA must be at least equal to the required field length. 3. The ASDA must be equal to or greater than the required accelerate-stop distance (see the ACCELERATE-STOP DISTANCE chart in this section). CLOSE IN and DISTANT TAKEOFF FLIGHT PATH CHARTS The Close-In Takeoff Flight Path and Distant Takeoff Flight Path charts are used to determine the minimum climb gradient required from the zero reference point in the takeoff path to clear any obstacles in the takeoff path. To demonstrate how to use the charts assume there is a 150 feet high ridge located 9,430 feet from the end of departure runway 35 in the performance example. The corrected takeoff field length from the example is 10,930 feet. Since the departure runway is 11,500 feet long, from reference zero to the end of the runway is 570 feet. This distance is added to 9,430 feet to place the 150 feet high ridge 10,000 feet from reference zero. A check of the Close-In Takeoff Flight Path chart example shows the minimum climb gradient must be 1.2%. Next, check the Net Gradient of Climb chart to see whether the climb gradient produced by the airplane will meet the minimum climb gradient. The example on this chart shows the airplane will deliver a climb gradient of 1.5%, which will allow the airplane to clear the ridge. REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-11 Note, when a takeoff is made with flaps set to approach there is a period upon reaching 400 feet AGL where the pilot momentarily levels off and accelerates to V2 + 5, and then retracts the flaps before climbing again at VENR. The airplane travels approximately 6,000 feet horizontally during this period. This 6,000 feet should be subtracted from the distance to the obstacle when determining the minimum climb gradient. The reduction in the distance to the obstacle is a means to account for the distance the aircraft travels while it is accelerating and not climbing. MAXIMUM ALLOWED LANDING WEIGHT TABLES The maximum landing weight limitation from Section 2 Limitations is 13,500 pounds. However, the maximum allowed landing weight may be less than the maximum landing weight limit depending on the airplane’s climb performance. Following the data in the maximum allowed landing weight table ensures the airplane will be at a weight allowing the climb requirements to be met. The fuel required to reach the destination should be subtracted from the takeoff weight to determine the predicted landing weight. If the predicted landing weight is greater than the maximum allowed landing weight, then the takeoff weight must be reduced so that the maximum allowed landing weight is not exceeded at the destination. The following charts contained in this section are provided to aid in determining the fuel required to reach the destination. See the basic AFM/POH for more detailed information regarding cruise performance and the associated fuel consumption.  TIME, FUEL, AND DISTANCE TO CLIMB  MAXIMUM CRUISE POWER 1700 RPM (ISA and ISA+20°C tables)  MAXIMUM RANGE POWER 1700 RPM (ISA and ISA+20°C tables)  TIME, FUEL, AND DISTANCE TO DESCEND Note that when icing is expected during the landing approach, the MAXIMUM ALLOWED LANDING WEIGHT - TO ACHIEVE LANDING CLIMB REQUIREMENTS WITH ICE ACCUMULATIONS PRESENT table must be used to determine the maximum allowed landing weight. The data presented in this table takes into account the increased drag and loss of propeller efficiency caused by ice accumulations on the airplane. LANDING INFORMATION The example on the Climb - Balked Landing chart shows how to determine the rate of climb and the associated gradient of climb for a given set of conditions. The example on the Landing Distance without and with Propeller Reversing charts show how to determine flaps down landing distance and flaps up landing distance, if needed. REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-12 REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-13 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-14 MAXIMUM ALLOWED TAKEOFF WEIGHT – FLAPS UP TO ACHIEVE TAKEOFF CLIMB REQUIREMENTS NOTES: 1. For operations with ice vanes extended, add 6°C to the actual Outside Air Temperature and use this adjusted Outside Air Temperature in the table. 2. For takeoff, the gross weight of the airplane must not exceed the maximum allowed takeoff weight at the corresponding pressure altitude and temperature shown in this table. This ensures compliance to the regulatory requirements for first, second, and enroute climb segments with one engine inoperative. 3. Blue background indicates under the respective conditions the maximum allowed takeoff weight is less than 14,000 pounds. Pressure Altitude -Feet- Outside Air Temperature Maximum Allowed Takeoff Weight - Pounds -25°C -20°C -15°C -10°C -5°C 0°C 5°C 10°C 15°C 20°C 25°C 30°C 10,000 14,000 13,823 13,558 13,274 12,969 12,685 12,396 12,110 11,818 11,516 11,192 10,863 32°C 10,735 9,000 14,000 14,000 14,000 13,876 13,551 13,236 12,923 12,623 12,324 12,021 11,717 11,393 34°C 11,117 8,000 14,000 14,000 14,000 14,000 14,000 13,804 13,467 13,142 12,826 12,511 12,207 11,892 35°C 11,570 36°C 11,503 7,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,686 13,343 13,000 12,682 12,360 12,036 38°C 11,842 6,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,877 13,513 13,163 12,821 12,481 40°C 12,151 5,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,704 13,324 12,950 12,594 42°C 12,450 4,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,885 13,469 13,064 44°C 12,678 3,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,963 13,522 45°C 13,091 46°C 13,002 2,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,950 13,487 48°C 13,218 1,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,945 50°C 13,464 Sea Level 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,954 52°C 13,757 REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-15 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-16 REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-17 MAXIMUM ALLOWED TAKEOFF WEIGHT – FLAPS APPROACH TO ACHIEVE TAKEOFF CLIMB REQUIREMENTS NOTES: 1. For operations with ice vanes extended, add 6°C to the actual Outside Air Temperature and use this adjusted Outside Air Temperature in the table. 2. For takeoff, the gross weight of the airplane must not exceed the maximum allowed takeoff weight at the corresponding pressure altitude and temperature shown in this table. This ensures compliance to the regulatory requirements for first, second, and enroute climb segments with one engine inoperative. 3. Blue background indicates under the respective conditions the maximum allowed takeoff weight is less than 14,000 pounds. Pressure Altitude Feet Outside Air Temperature Maximum Allowed Takeoff Weight - Pounds -35°C -30°C -25°C -20°C -15°C -10°C -5°C 0°C 5°C 10°C 15°C 20°C 25°C 30°C 10,000 12,657 12,445 12,246 12,038 11,837 11,623 11,390 11,165 10,927 10,663 10,414 10,154 9,861 9,551 32°C 9,500 9,000 13,157 12,945 12,733 12,516 12,313 12,102 11,882 11,651 11,413 11,177 10,920 10,626 10,326 10,029 34°C 9,779 8,000 13,567 13,373 13,179 12,974 12,769 12,545 12,335 12,111 11,882 11,640 11,360 11,085 10,768 10,443 35°C 10,147 36°C 10,086 7,000 13,899 13,717 13,535 13,353 13,172 12,967 12,763 12,542 12,321 12,083 11,808 11,506 11,209 10,881 10,519 38°C 10,330 6,000 14,000 14,000 13,850 13,667 13,481 13,321 13,151 12,965 12,743 12,503 12,235 11,947 11,649 11,292 10,929 40°C 10,520 5,000 14,000 14,000 14,000 13,954 13,802 13,644 13,473 13,325 13,136 12,931 12,663 12,362 12,064 11,719 11,346 10,978 42°C 10,811 4,000 14,000 14,000 14,000 14,000 14,000 13,947 13,808 13,636 13,460 13,299 13,123 12,786 12,451 12,124 11,782 11,423 44°C 11,078 3,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,929 13,776 13,616 13,459 13,229 12,873 12,513 12,177 11,836 45°C 11,478 46°C 11,412 2,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,908 13,777 13,632 13,301 12,934 12,563 12,212 11,857 48°C 11,639 1,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,930 13,731 13,377 12,994 12,606 12,234 50°C 11,861 Sea Level 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 14,000 13,888 13,445 13,046 12,633 12,236 52°C 12,075 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-18 REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-19 REFERENCE ONLY SECTION 5 CENTEX AEROSPACE 006-2A HW PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT MAY 2017 5-20 REFERENCE ONLY CENTEX AEROSPACE 006-2A HW SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE MAY 2017 5-21 USING TAKEOFF SPEEDS & FIELD LENGTHS TABLES The first group of tables applies to aircraft operating with flaps set at the approach setting for takeoff and the second group for takeoff with flaps up. In each group, tables are provided for each 500 foot increment in pressure altitude starting with sea level pressure up through 10,000 feet. Each chart is arranged by aircraft weight and ambient outside air temperature. Starting with the maximum takeoff weight of 14,000 pounds in the top row, subsequent rows provide takeoff data for aircraft from 13,500 pound to 9,500 pound weights at 500 pound increments. For each row, the takeoff speeds in knots indicated airspeed (KIAS) and takeoff field length (TOFL) in feet are listed for each temperature. Outside air temperatures in degrees Celsius are given in 10oC increments, starting with 30oC below standard atmospheric (ISA) conditions and ending with 37oC above ISA, which equates to the maximum operating temperature limit of the aircraft. In the tables, the ambient temperatures are organized as follows: Pres. Alt. Feet OUTSIDE AIR TEMPERATURE (OC) ISA-30 ISA-20 ISA-10 ISA ISA+10 ISA+20 ISA+30 ISA+37 Sea level -15 -5 5 15 25 35 45 52 500 -16 -6 4 14 24 34 44 51 1,000 -17 -7 3 13 23 33 43 50 1,500 -18 -8 2 12 22 32 42 49 2,000 -19 -9 1 11 21 31 41 48 2,500 -20 -10 0 10 20 30 40 47 3,000 -21 -11 -1 9 19 29 39 46 3,500 -22 -12 -2 8 18 28 38 45 4,000 -23 -13 -3 7 17 27 37 44 4,500 -24 -14 -4 6 16 26 36 43 5,000 -25 -15 -5 5 15 25 35 42 5,500