AIRPLANE FLIGHT MANUAL SUPPLEMENT

3A-1 ........................................................................................... September 2015 3A-2 ................................................................................................. August 2014 3A-3 ..................................................................................................... June 2015 3A-4 ............................................................................................ December 2014 3A-5 ..................................................................................................... June 2015 3A-6 ........................................................................................... September 2015 4-1 .............................................................................................. September 2015 4-2 ............................................................................................... December 2014 4-3 ........................................................................................................ June 2015 4-4 .............................................................................................. September 2015 4-5 .................................................................................................... August 2014 4-6 ............................................................................................... December 2014 4-7 thru 4-8 ...................................................................................... August 2014 4-9 ........................................................................................................ June 2015 4-10 ............................................................................................ September 2015 5-1 thru 5-2 .......................................................................................... June 2015 5-3 thru 5-5 ...................................................................................... August 2014 5-6 thru 5-9 .......................................................................................... June 2015 5-10 .................................................................................................. August 2014 5-11 ............................................................................................. December 2014 5-12 .................................................................................................. August 2014 5-13 thru 5-14 ...................................................................................... June 2015 5-15 ............................................................................................ September 2015 5-16 thru 5-80 ...................................................................................... June 2015 SECTION 1 CENTEX AEROSPACE 006-4 GENERAL AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 1-6 6-1 thru 6-2 ...................................................................................... August 2014 6-3 ........................................................................................................ June 2015 6-4 thru 6-6 ...................................................................................... August 2014 7-1 .............................................................................................. September 2015 7-2 .................................................................................................... August 2014 7-3 thru 7-4 ................................................................................ September 2015 7-5 ........................................................................................................ June 2015 7-6 .............................................................................................. September 2015 7-7 ........................................................................................................ June 2015 7-8 thru 7-12 .............................................................................. September 2015 8-1 .................................................................................................... August 2014 8-2 ........................................................................................................ June 2015 9-1 thru 9-2 ...................................................................................... August 2014 9-3 thru 9-4 .......................................................................................... June 2015 9-5 .............................................................................................. September 2015 LOG OF REVISIONS Initial Release August 27, 2014 Includes pages dated August 2014 APPROVED BY: S. Frances Cox Revision 1 December 31, 2014 Includes pages dated December 2014 APPROVED BY: S. Frances Cox Revision 2 June 30, 2015 Includes pages dated June 2015 APPROVED BY: Scott A. Horn Revision 3 September 30, 2015 Includes pages dated September 2015 APPROVED BY: Scott A. Horn CENTEX AEROSPACE 006-4 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS SEPTEMBER 2015 2-9 AIRCRAFT EQUIPPED WITH ROCKWELL COLLINS PRO LINE 21 AVIONICS VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS ELECTRICAL POWER 1. Battery 1 1 1 1 1 2. Standby Battery (ESIS) 1 1 1 1 1 3. Battery Ammeter 1 1 1 1 1 4. DC Generator 2 2 2 2 2 5. L & R DC GEN Annunciators 2 2 2 2 2 6. DC Load Meter 2 2 2 2 2 ENGINE INDICATIONS 1. Multifunctional Display (MFD) 1 1 1 1 1 ENGINE OIL 1. Chip Detector System including L & R CHIP DETECT Annunciators 2 2 2 2 2 2. Oil Pressure Indicator in MFD 2 2 2 2 2 3. Oil Temperature Indicator in MFD 2 2 2 2 2 4. L & R OIL PRESS annunciator 2 2 2 2 2 ENVIRONMENTAL 1. L & R BL AIR FAIL Annunciator 2 2 2 2 2 2. Bleed Air Shutoff Valve 2 2 2 2 2 3. ALT WARN Annunciator (Cabin) 1 1 1 1 1 4. Cabin Rate of Climb Indicator 1 1 1 1 1 5. Outflow Valve/Safety Valve 2 2 2 2 2 6. Pressurization Controller 1 1 1 1 1 7. Differential Pressure/Cabin Altitude Indicator 1 1 1 1 1 8. DUCT OVERTEMP Annunciator 1 1 1 1 1 FIRE PROTECTION 1. Engine Fire Detector System and Annunciators 2 2 2 2 2 2. Engine Fire Extinguisher System & Annunciators 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 System 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 Damp 1 1 1 1 1 7. Elevator Trim Warning System 1 1 1 1 1 AIRCRAFT EQUIPPED WITH ROCKWELL COLLINS PRO LINE FUSION AVIONICS VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS ELECTRICAL POWER 1. Battery 1 1 1 1 1 2. Standby Display Battery 1 1 1 1 1 3. Battery Ammeter 1 1 1 1 1 4. DC Generator 2 2 2 2 2 5. DC Load Meter 2 2 2 2 2 ENGINE INDICATIONS 1. Engine Indication System L & R (Oil Pressure, Oil Temperature, Torque, ITT, 1 1 1 1 1 Prop RPM, N1) ENGINE OIL 1. L & R Chip Detector System 2 2 2 2 2 ENVIRONMENTAL 1. Bleed Air Shutoff Valve 2 2 2 2 2 2. Altitude Warning System (Cabin) 1 1 1 1 1 3. Outflow Valve/Safety Valve 2 2 2 2 2 4. Pressurization Controller 1 1 1 1 1 5. Differential Pressure/Cabin Altitude Indicator 1 1 1 1 1 FIRE PROTECTION 1. Engine Fire Detector System and Annunciators 2 2 2 2 2 2. Engine Fire Extinguisher System & Annunciators 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 System 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 Damp 1 1 1 1 1 7. Elevator Trim Warning System 1 1 1 1 1 SECTION 2 CENTEX AEROSPACE 006-4 LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 2-10 AIRCRAFT EQUIPPED WITH ROCKWELL COLLINS PRO LINE 21 AVIONICS 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 Electric Fuel 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 ICE AND RAIN PROTECTION 1. Alternate Static Air System 0 0 1 1 1 2. Engine Auto Ignition System 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 2 5. Heated Windshield (Left) 0 0 0 0 1 6. Pitot Heat System Including Annunciators 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 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. Landing Gear Hydraulic Power Pack 1 1 1 1 1 5. HYD FLUID LOW Annunciator 1 1 1 1 1 6. Alternate Landing Gear Extension 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 2 0 2 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 AIRCRAFT EQUIPPED WITH ROCKWELL COLLINS PRO LINE FUSION AVIONICS 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 1 1 1 1 1 3. Standby Electric Fuel Pump 2 2 2 2 2 4. Fuel Quantity Indicating System incl. Annunciators 2 2 2 2 2 5. Firewall Fuel Shutoff System 2 2 2 2 2 6. Jet Transfer Pump 2 2 2 2 2 7. Motive Flow Valve 2 2 2 2 2 ICE AND RAIN PROTECTION 1. Alternate Static Air System 0 0 1 1 1 2. Engine Auto Ignition System and Annunciators 2 2 2 2 2 3. Engine Anti-Ice System 2 2 2 2 2 4. Heated Fuel Vent 0 0 0 0 2 5. Heated Windshield (Left) 0 0 0 0 1 6. Pitot Heat System 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 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. Landing Gear Hydraulic Power Pack 1 1 1 1 1 5. Alternate Landing Gear Extension System 1 1 1 1 1 1 1 1 1 1 LIGHTS 1. Cockpit and Instrument Lighting system 0 1 0 1 0 2. Landing Lights 0 2 0 2 0 3. Position Lights 0 3 0 3 0 4. Anti-collision Lights System 0 1 0 1 0 5. Cabin Emergency Lighting System and Escape Path Markings Required when carrying passengers CENTEX AEROSPACE 006-4 SECTION 2 AIRPLANE FLIGHT MANUAL SUPPLEMENT LIMITATIONS SEPTEMBER 2015 2-11 AIRCRAFT EQUIPPED WITH ROCKWELL COLLINS PRO LINE 21 AVIONICS VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS FLIGHT INSTRUMENTS 1. Primary Flight Display (PFD) 2 2 2 2 2 2. Magnetic Compass 1 1 1 1 1 3. Electronic Standby Instrument System (ESIS) 1 1 1 1 1 4. AHRS 2 2 2 2 2 5. Air Data Computer (ADC) 2 2 2 2 2 6. Outside Air Temperature 1 1 1 1 1 OXYGEN 1. Oxygen System 1 1 1 1 1 PROPELLER 1. Autofeather System including Annunciators 1 1 1 1 1 2. Propeller Reversing System including Annunciators 2 2 2 2 2 3. Propeller Governor Test Switch 1 1 1 1 1 4. Propeller Over-speed Governor 2 2 2 2 2 5. Propeller Low-Pitch Stop 2 2 2 2 2 VACUUM SYSTEM 1. Vacuum Gage 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. AIRCRAFT EQUIPPED WITH ROCKWELL COLLINS PRO LINE FUSION AVIONICS VFR DAY VFR NIGHT SYSTEM and/or COMPONENT IFR DAY IFR NIGHT ICING CONDITIONS FLIGHT INSTRUMENTS 1. Crew Alerting System (CAS) 1 1 1 1 1 2. Primary Flight Display (PFD) 2 2 2 2 2 3. Multifunction Display (MFD) 1 1 1 1 1 4. Magnetic Compass 1 1 1 1 1 5. Standby Flight Display System (SFDS) 1 1 1 1 1 6. Attitude Heading System (AHS) 2 2 2 2 2 7. Air Data System (ADS) 2 2 2 2 2 8. Outside Air Temperature (Pilot’s Side Console) 1 1 1 1 1 OXYGEN 1. Oxygen System 1 1 1 1 1 PROPELLER 1. Autofeather System including Annunciators 1 1 1 1 1 2. Propeller Reversing System 2 2 2 2 2 3. Propeller Governor Test Switch 1 1 1 1 1 4. Propeller Over-speed Governor 2 2 2 2 2 5. Propeller Low-Pitch Stop 2 2 2 2 2 VACUUM SYSTEM 1. Vacuum Gage 1 1 1 1 1 SECTION 2 CENTEX AEROSPACE 006-4 LIMITATIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 2-12 THIS PAGE IS INTENTIONALLY BLANK CENTEX AEROSPACE 006-4 SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES SEPTEMBER 2015 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 STALL FAIL ..................................................................................................... 3A-6 NOTE See BLR Aerospace AFMS-B250-1 AFM Supplement and Beechcraft B200GT Pilot Operating Handbook for other Abnormal Procedures. SECTION 3A CENTEX AEROSPACE 006-4 ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT AUGUST 2014 3A-2 FLAPS UP LANDING Refer to Section 5 of Supplement AFM 006-4 for Flaps Up Landing Distance. WEIGHT POUNDS VREF (FLAPS UP) KNOTS 13,420 124 13,000 121 12,500 119 12,000 115 11,000 111 10,000 106 9,000 101 1. Approach Speed, VREF (Flaps Up) ....................................................... CONFIRM 2. Autofeather ..............................................................................................ARM 3. Pressurization......................................................................................... CHECK 4. Cabin Sign............................................................................. NO SMOKE & FSB 5. Flaps ............................................................................................................. UP Do not silence the landing gear warning horn, since the flap actuated portion of the landing gear warning system will not be actuated during a flap up landing. 6. Flap Override......................................................................................... 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 006-4 CAUTION CENTEX AEROSPACE 006-4 SECTION 3A AIRPLANE FLIGHT MANUAL SUPPLEMENT ABNORMAL PROCEDURES JUNE 2015 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 13,420 105 13,000 104 12,500 103 When Landing Is Assured: 1. Flaps ...................................................................................................... DOWN 2. Airspeed ..................................................................................................... VREF 3. Yaw Damp .................................................................................................. OFF 4. Power Levers............................................................................................. IDLE 5. Propeller Levers ...................................................................... FULL FORWARD 6. Sink Rate .......................... TOUCHDOWN WITH NOMINAL OR LESS SINK RATE After Touchdown: 7. Power Levers.................................................. LIFT AND SELECT GROUND FINE 8. Brakes ......................................................................................... AS REQUIRED NOTE An overweight landing is defined as any landing made when the airplane gross weight is greater than 12,500 pounds, which is the maximum landing weight limitation. When the airplane is landed at a gross weight above 12,500 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. Also, an overweight landing where the touchdown sink rate is nominal will not result in damage to the landing gear or airframe structure. SECTION 3A CENTEX AEROSPACE 006-4 ABNORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 3A-6 Only For Aircraft with Rockwell Collins Pro Line Fusion: STALL FAIL This CAS message indicates that the stall computer has failed. Maintain airspeed appropriate for phase of flight. NOTE Halo 250 equipped aircraft have two stall computer modes, Normal Mode and Icing Mode. The Stall Fail CAS message applies to the mode in use at the time of failure. Stall Fail CENTEX AEROSPACE 006-4 SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES SEPTEMBER 2015 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) .................................................................. 4-4 TAKEOFF ............................................................................................... 4-4 CLIMB ICING CONDITIONS ....................................................................... 4-4 CRUISE ICING CONDITIONS ....................................................................... 4-5 BEFORE LANDING ................................................................................. 4-6 NORMAL LANDING................................................................................ 4-6 MAXIMUM REVERSE THRUST LANDING................................................ 4-7 BALKED LANDING ................................................................................. 4-7 SHUT DOWN AND SECURING ............................................................... 4-7 OTHER PROCEDURES ICING FLIGHT ........................................................................................ 4-7 TAKEOFF TRIM WARNING TEST ............................................................ 4-7 STALL WARNING SYSTEM OPERATION .................................................. 4-8 CABIN EMERGENCY LIGHTING SYSTEM OPERATION ............................ 4-8 CHARGING EMERGENCY ESCAPE PATH MARKINGS ............................. 4-9 OVERWEIGHT LANDING ........................................................................ 4-9 NOISE CHARACTERISTICS ..................................................................... 4-9 OPERATIONS AT AIRPORTS ABOVE 10,000 FEET PRESSURE ALTITUDE BEFORE ENGINE STARTING ................................................................... 4-10 BEFORE TAKEOFF (FINAL ITEMS) ........................................................... 4-10 CLIMB .................................................................................................... 4-10 DESCENT ............................................................................................... 4-10 SECTION 4 CENTEX AEROSPACE 006-4 NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT DECEMBER 2014 4-2 All airspeeds quoted in this section 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......................................................................................... 16 Knots Tailwind............................................................................................ 10 Knots 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 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), Flaps Up ................................ 92 Knots Flaps Approach ..................... 87 Knots CAUTION See Section 5 Performance for Takeoff Speeds CENTEX AEROSPACE 006-4 SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES JUNE 2015 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 250 Commuter Category STC. 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 LEFT WING AND NACELLE Change the following: Propeller .......................... CHECK PROPELLER AND DEICE BOOT CONDITION RIGHT WING AND NACELLE Change the following: Propeller .......................... CHECK PROPELLER AND DEICE BOOT CONDITION 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 SECTION 4 CENTEX AEROSPACE 006-4 NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 4-4 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. TAKEOFF 1. Brakes ..................................................................................................... HOLD 2. Power ................................. SET (ensure minimum takeoff power is available) 3. Rockwell Collins Pro Line 21 Annunciators: [L AFX] and [R AFX] or ................................................................ ILLUMINATED [L AUTOFEATHER] and [R AUTOFEATHER] ................................. ILLUMINATED Rockwell Collins Pro Line Fusion CAS Messages: Left and Right .................... CONFIRM DISPLAYED ON EICAS 4. Brakes .............................................................................................. RELEASED 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 Rockwell Collins Pro Line 21 Annunciators: [L ENG ANTI-ICE] and [R ENG ANTI-ICE] ILLUMINATED Rockwell Collins Pro Line Fusion CAS Message: CAS MESSAGE DISPLAYED 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 ................................................. 145 KNOTS MINIMUM AIRSPEED L-R ENG ANTI-ICE AFX AFX CENTEX AEROSPACE 006-4 SECTION 4 AIRPLANE FLIGHT MANUAL SUPPLEMENT NORMAL PROCEDURES JUNE 2015 4-9 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 greater than 12,500 pounds, which is the maximum landing weight limitation. If it becomes necessary to land the airplane at a gross weight above 12,500 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. Note that components in the standard landing gear have less overall strength margin than the corresponding components in the high flotation landing gear. Also, an overweight landing where the touchdown sink rate is nominal will not result in damage to the landing gear or airframe structure. NOISE CHARACTERISTICS The takeoff noise level of King Air 200 series airplanes modified in accordance with the CenTex Aerospace Halo 250 Commuter Category STC established in compliance with 14 CFR Part 36, Appendix G and ICOA 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. SECTION 4 CENTEX AEROSPACE 006-4 NORMAL PROCEDURES AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 4-10 OPERATIONS AT AIRPORTS ABOVE 10,000 FEET PRESSURE ALTITUDE BEFORE ENGINE STARTING Prior to turning battery on: Oxygen Controls ................................................................... DO NOT PULL ON With the Oxygen Controls not pulled on, crew oxygen and automatic deployment of the passenger oxygen masks is not available. After turning battery on: Rockwell Collins Pro Line 21 Annunciator: [ALT WARN] ............ ILLUMINATED (above approximately 12,000 feet) Rockwell Collins Pro Line Fusion CAS Message: CAS MESSAGE DISPLAYED BEFORE TAKEOFF (FINAL ITEMS) Envir Bleed Air ...........................................................................................LOW CLIMB 1. Envir Bleed Air ................................................................................. AUTO 2. Cabin Controller ................................................ SET AT PLANNED CRUISE ALTITUDE PLUS 500 FEET (if desired) 3. Pressurization................................................................................. CHECK 4. Oxygen Controls (after cabin altitude descends through 11,000 feet) ........................................ PULL ON SYSTEM READY DESCENT When landing at field elevations above 11,000 feet pressure altitude: 1. Oxygen Controls (prior to cabin altitude climbing through 11,000 feet) ............................................................... PUSH OFF 2. Envir Bleed Air ...................................................................................LOW 3. Rockwell Collins Pro Line 21 Annunciator: [ALT WARN] .... ILLUMINATED (above approximately 12,000 feet) Rockwell Collins Pro Line Fusion CAS Message: CAS MESSAGE DISPLAYED (above approximately 12,000 feet) With the Oxygen Controls not pulled on, crew oxygen and automatic deployment of the passenger oxygen masks is not available. WARNING Cabin Alt High Cabin Alt High WARNING CENTEX AEROSPACE 006-4 SECTION 5 AIRPLANE FLIGHT MANUAL SUPPLEMENT PERFORMANCE SEPTEMBER 2015 5-15 SECTION 5 CENTEX AEROSPACE 006-4 PERFORMANCE AIRPLANE FLIGHT MANUAL SUPPLEMENT JUNE 2015 5-16 MAXIMUM ALLOWED TAKEOFF WEIGHT – FLAPS UP TO MEET FIRST, SECOND, AND FINAL SEGMENT CLIMB REQUIREMENTS NOTES: 1. The gross weight of the airplane at takeoff 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 requirement for a minimum climb gradient in the event of an engine failure. For temperatures below 0°C and pressure altitudes up to 14,000 feet, the Maximum Allowed Takeoff Weight is 13,420 ponds. 2. For operations with ice vanes extended, add 6°C to the actual Outside Air Temperature and use this adjusted temperature in the table. 3. Blue background indicates under the respective conditions the Maximum Allowed Takeoff Weight is less than 13,420 pounds. Pressure Altitude -Feet- Outside Air Temperature Maximum Allowed Takeoff Weight - Pounds 14,000 0°C 5°C 10°C 15°C 20°C 24°C 13,420 13,217 12,594 11,937 11,239 10,679 13,000 0°C 5°C 10°C 15°C 20°C 25°C 26°C 13,420 13,420 13,202 12,569 11,903 11,187 11,037 12,000 0°C 5°C 10°C 15°C 20°C 25°C 28°C 13,420 13,420 13,420 13,177 12,536 11,852 11,430 11,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 13,420 13,420 13,420 13,420 13,058 12,425 11,753 10,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 32°C 13,420 13,420 13,420 13,420 13,420 12,956 12,327 12,059 9,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 34°C 13,420 13,420 13,420 13,420 13,420 13,420 12,847 12,331 8,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 36°C 13,420 13,420 13,420 13,420 13,420 13,420 13,368 12,719 12,589 7,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 38°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,275 12,878 6,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,172 5,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 42°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,370 4,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 44°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 3,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 45°C 46°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 2,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 45°C 48°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 1,000 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 45°C 50°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 Sea Level 0°C 5°C 10°C 15°C 20°C 25°C 30°C 35°C 40°C 45°C 50°C 52°C 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 13,420 CENTEX AEROSPACE 006-4 SECTION 7 AIRPLANE FLIGHT MANUAL SUPPLEMENT SYSTEMS DESCRIPTION SEPTEMBER 2015 7-1 SECTION 7 SYSTEMS DESCRIPTION TABLE OF CONTENTS SUBJECT PAGE INTRODUCTION............................................................................................. 7-2 TAKEOFF TRIM WARNING ............................................................................. 7-3 OVER-SPEED WARNING ................................................................................ 7-4 SEATING ARRANGEMENT ............................................................................. 7-4 EMERGENCY ESCAPE PATH MARKINGS ........................................................ 7-4 ENGINE FIRE EXTINGUISHER ......................................................................... 7-5 STALL WARNING ICE MODE .......................................................................... 7-5 CABIN EMERGENCY LIGHTING ...................................................................... 7-6 CREW ALERTING SYSTEM (CAS) ...................................................................... 7-8 RIGHT CIRCUIT BREAKER PANEL (PRO LINE 21) .............................................. 7-9 AVIONICS/ELECTRICAL BUS CONNECTION (PRO LINE 21) ............................. 7-10 RIGHT CIRCUIT BREAKER PANEL (PRO LINE FUSION) .................................... 7-11 AVIONICS/ELECTRICAL BUS CONNECTION (PRO LINE FUSION)..................... 7-12 SECTION 7 CENTEX AEROSPACE 006-4 SYSTEMS DESCRIPTION AIRPLANE FLIGHT MANUAL SUPPLEMENT AUGUST 2014 7-2 INTRODUCTION New safety systems are installed under the Halo 250 conversion. These systems provide safety functions that are required for airplanes certificated in the Commuter category. Also, the stall warning system has been modified and will now provide accurate and reliable warning when the airplane is operated in icing conditions. The result is a King Air 200 series airplane that operates at a higher level of safety. Below is a list of the added functions:  Takeoff Trim Warning  (Omitted)  Engine Fire Extinguisher  Stall Warning Ice Mode  Emergency Cabin Lighting  Escape Path Markings This section describes the functionality of these systems and the pertinent design details. It is imperative that the pilot be knowledgeable of this information so he/she can fully utilize these new features and thereby realize the added safety they provide. For information on systems other than those described in this section see the BLR Aerospace AFMS-B250-1 AFM Supplement and the basic Pilot Operating Handbook. ---------------------------- CENTEX AEROSPACE 006-4 SECTION 7 AIRPLANE FLIGHT MANUAL SUPPLEMENT SYSTEMS DESCRIPTION SEPTEMBER 2015 7-3 TAKEOFF TRIM WARNING The Halo 250 conversion adds a takeoff trim warning system. The system detects if the elevator trim tab has not been properly set before takeoff and sounds a warning when the pilot initiates a takeoff. The pilot should respond to the warning by immediately aborting the takeoff run. The trim warning system utilizes the existing elevator tab position indicator to determine tab position. A micro switch actuated by the tab position indicator activates the warning horn when the tab position is outside of the approved range for takeoff. The horn emits a constant, mid-frequency tone. It is located beneath the lower edge of the pilot’s instrument panel next to the console. The micro switch is mounted to the console beneath the elevator trim wheel. The Autofeather/takeoff trim warning system is powered from Dual Fed Bus No. 2 (See FIGURE 7-6 and FIGURE 7-8). Power to the elevator trim warning system comes through the Autofeather system switch when it is in the ARMED position. Power must also pass through the weight-on-wheels switch and the 90% N1 switch associated with the left engine power lever. The system becomes fully operational once the Autofeather system is ARMED and the left power lever is advance to the 90% N1, or higher, position. The takeoff trim warning system is deactivated through the weight-on-wheels switch after liftoff so no misleading warnings occur during flight. Note the Halo 250 STC conversion requires the Autofeather system to be operative for takeoff. The warning system should be tested before the first flight of each day, as specified in Section 4 Normal Procedures. ------------------------------ SECTION 7 CENTEX AEROSPACE 006-4 SYSTEMS DESCRIPTION AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 7-4 OVER-SPEED WARNING The Rockwell Collins Pro Line 21 or Rockwell Collins Pro Line Fusion integrated avionics provides an aural over-speed warning, which is required for commuter category airplanes. The aural warning automatically alerts the pilot whenever airspeed is greater than VMO or Mach number is greater than MMO. This system provides a backup to the function provided by the airspeed tape on the Primary Flight Displays. The pilot should respond to a warning by immediately taking the necessary action to reduce airspeed. SEATING ARRANGEMENTS Various configurations of passenger chairs and one-place couch installations may be installed on the continuous tracks mounted to the cabin floor. Seating for up to nine (9) persons, excluding crew, may be installed. This is a new limitation imposed by the Commuter category requirements. EMERGENCY ESCAPE PATH MARKINGS The Halo 250 conversion adds photoluminescent markings that highlight the escape path along the floor to the emergency exit door and cabin door. The photoluminescent markings must be visible (not covered by floor mats or any other coverings) and adequately charged before conducting any part of a flight in darkness. Charging can be accomplished with sunlight or with the interior lights or with the emergency flood lamps. See Section 4 Normal Procedures for the required charging time CENTEX AEROSPACE 006-4 SECTION 7 AIRPLANE FLIGHT MANUAL SUPPLEMENT SYSTEMS DESCRIPTION JUNE 2015 7-5 ENGINE FIRE EXTINGUISHER The Halo 250 conversion requires installation of the optional engine fire extinguisher system. Information regarding this system is contained in the basic Airplane Flight Manual or Pilot Operating Handbook. STALL WARNING ICE MODE The King Air 200 series stall warning system does not have the capability to adjust for the effect that icing has on stall speed. Ice accretion causes the wing to stall at a lower angle-of-attack and can result in a 15% to 20% increase in stall speed. The Halo 250 conversion adds additional capability so a reliable and accurate stall warning is available in icing conditions. This new stall warning functionality is called the “ice mode”. The stall warning system will activate the warning horn when the output of the lift transducer reaches a preset voltage. The system has three different voltage settings, one for each flap position; which enables it to provide accurate warning at each flap setting. The Halo 250 conversion adds components to the stall warning system that allow three different preset voltages to become active when it is in the ice mode. These voltage settings are uniquely selected so that the effect of ice on the wings is considered. With wing flaps up, the stall warning activates at approximately 20 knots higher airspeed in the ice mode. The pilot should respond to the warning by pitching the aircraft nose down until the warning ceases, leveling the wings to orient lift vector for recovery, and adding power to assist in the recovery. The pilot’s failure to respond to a stall warning can result in a stall and subsequent loss of control of the airplane. Switching to the ice mode occurs automatically when the pilot selects either SINGLE or MANUAL on the Surface Deice switch. The STALL WARNING ICE MODE annunciator, which is located in the glareshield in front of the pilot, will illuminate whenever the ice mode is active (See FIGURE 7-2). The ice mode will stay active until it is manually deactivated by the pilot pressing the illuminated annunciator. This should be done when the airplane is outside of icing conditions and is free of ice. Pressing the annunciator when it is extinguished has no effect. Note the stall warning heat must be operating when flying in icing conditions to keep the lift transducer free of ice. When testing the stall warning system, the mode in operation when the test is performed is the mode that is tested. A constant tone will be heard if the system is functioning properly. The new system components are located inside the aft end of the console. SECTION 7 CENTEX AEROSPACE 006-4 SYSTEMS DESCRIPTION AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 7-6 FIGURE 7-2 STALL WARNING ICE MODE ANNUNCIATOR CABIN EMERGENCY LIGHTING The Halo 250 conversion adds a cabin emergency lighting system. It provides supplemental lighting in the cabin around the emergency exit door and cabin door. The system has two LED flood lamps located in the cabin ceiling that are powered by a dedicated battery pack, which contains two 12-volt, sealed lead- acid batteries connected in series, installed under the cabin floor. The system automatically turns on the flood lamps in the event of a 2-g, or greater, deceleration or a loss of power on the main electrical bus. This keeps the cabin from becoming unlighted during such critical events. Additionally, the lamps can be used for lighting the cabin when boarding or to charge the photoluminescent escape path markings. Two switches operate the system and provide required functionality. A cabin switch located next to the aft flood lamp connects the battery pack to the system (See FIGURE 7-3). A control switch located in the pilot’s sub-panel arms automatic operation or provides manual operation of the flood lamps from the cockpit (See FIGURE 7-4). Power to charge the battery pack is fed from the main electrical bus through a five (5) amp circuit breaker labeled EMERG LIGHT in the copilot circuit breaker panel (See FIGURE 7-5 thru FIGURE 7-8). Two amber indicator lights located adjacent to the control switch (See FIGURE 7-4) warn the pilot when the system switches are not set as required for taxi and takeoff operations. The amber indicator lights will be extinguished when the cockpit control switch is ARMED and the cabin switch is ON. Note these are the required positions for taxi and flight operations. CENTEX AEROSPACE 006-4 SECTION 7 AIRPLANE FLIGHT MANUAL SUPPLEMENT SYSTEMS DESCRIPTION JUNE 2015 7-7 When exiting the airplane both the control switch and the cabin switch should be placed in the OFF position. If left on, a timer prevents the battery from becoming totally discharged by disconnecting the battery pack from the system after 10 minutes. Selecting OFF on the cabin switch reconnects the battery pack and resets the timer. Note recharging of the battery pack occurs automatically whenever the airplane battery switch is ON and the main electrical bus is powered by either the generators or an external power source. The level of charge of the emergency lighting system battery pack should be checked before the first flight of each day as described in Section 4 NORMAL PROCEDURES. The system must be operational when carrying passengers. If the lamps do not illuminate, the emergency lighting system batteries have been discharged or there is a malfunction in the system. A discharged battery pack must be removed and the batteries recharged or replaced. The Halo 250 Instructions for Continued Airworthiness, Manual no. 006-30 describes the proper procedures for removing and recharging or replacing the cabin emergency lighting system battery pack. The battery pack and relays are located beneath the cabin floor at either Fuselage Station 207 or Fuselage Station 270. Also, the battery pack should be inspected at each maintenance Phase Inspection interval for general condition and the time-in-service for the batteries. The batteries must be replaced after 36 calendar months from the time they were installed. FIGURE 7-3 EMERGENCY CABIN LIGHTING SYSTEM CABIN SWITCH & FLOOD LAMP SECTION 7 CENTEX AEROSPACE 006-4 SYSTEMS DESCRIPTION AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 7-8 FIGURE 7-4 EMERGENCY CABIN LIGHTING SYSTEM COCKPIT CONTROL SWITCH and WARNING LIGHTS CREW ALERTING SYSTEM (CAS) Only For Aircraft with Rockwell Collins Pro Line Fusion: CAUTION (AMBER) CAS MESSAGES CAS Message Description Stall Fail The stall computer has failed. NOTE Halo 250 equipped aircraft have two stall computer modes, Normal Mode and Icing Mode. The Stall Fail CAS message applies to the mode in use at the time of failure. CENTEX AEROSPACE 006-4 SECTION 7 AIRPLANE FLIGHT MANUAL SUPPLEMENT SYSTEMS DESCRIPTION SEPTEMBER 2015 7-9 FIGURE 7-5 RIGHT CIRCUIT BREAKER PANEL (PRO LINE 21) EMERGENCY LIGHTING SYSTEM CIRCUIT BREAKER EMERG LIGHT SECTION 7 CENTEX AEROSPACE 006-4 SYSTEMS DESCRIPTION AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 7-10 FIGURE 7-6 AVIONICS/ELECTRICAL EQUIPMENT BUS CONNECTION (PRO LINE 21) EMERG LIGHTING SYSTEM TRIM WARN SYSTEM CENTEX AEROSPACE 006-4 SECTION 7 AIRPLANE FLIGHT MANUAL SUPPLEMENT SYSTEMS DESCRIPTION SEPTEMBER 2015 7-11 FIGURE 7-7 RIGHT CIRCUIT BREAKER PANEL (PRO LINE FUSION) EMERGENCY LIGHTING SYSTEM CIRCUIT BREAKER SECTION 7 CENTEX AEROSPACE 006-4 SYSTEMS DESCRIPTIONS AIRPLANE FLIGHT MANUAL SUPPLEMENT SEPTEMBER 2015 7-12 FIGURE 7-8 AVIONICS/ELECTRICAL EQUIPMENT BUS CONNECTION (PRO LINE FUSION) EMERG LIGHTING SYSTEM TRIM WARN SYSTEM CENTEX AEROSPACE 006-4 SECTION 9 AIRPLANE FLIGHT MANUAL SUPPLEMENT SUPPLEMENTS SEPTEMBER 2015 9-5 THIS PAGE IS INTENTIONALLY BLANK