Operating Manual MODEL 560 560-0539 THRU -5000 Member of GAMA COPYRIGHT ” 2000 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA 56OMB-01 28 SEPTEMBER 2000 REVISION 1 3 NOVEMBER 2005
LOG OF EFFECTIVE PAGES MODEL 560 LOG OF EFFECTIVE PAGES Use this page to determine the currency and applicability of your Operating Manual. Pages affected by the current revision are indicated by an asterisk (*) preceding the pages listed under the Page column. Determine which pages are applicable to your airplane by checking effectivity of each page, which is listed after each page entry where an airplane serialization is required.
MODEL 560 INTRODUCTION CONTENTS SECTION INTRODUCTION .................................. DESCRIPTION AND SPECIFICATIONS AIRPLANE AND SYSTEMS INTRODUCTION-1 ............................... ........................................ INSTRUMENTATION AND AVIONICS 2 ................................ 3 OPERATING INFORMATION ....................................... 4 ABNORMAL PROCEDURES ....................................... 5 ......................................
INTRODUCTION MODEL 560 INTRODUCTION UNIT AND SERIAL NUMBER On all Model 560 Citation Encore airplanes, the serial and unit number are stamped into the airplane identification nameplate. This manual uses serial numbers to describe airplane effectivities.
INTRODUCTION MODEL 560 AIRPLANE CONFIGURATION CODES (Continued) Configuration Code I Introduction-4 Effectivity by Serial Number AH Airplanes 560-0626 thru -0644 not incorporating SB560-77-06. AI Airplanes 560-0645 thru -0677 not incorporating SB560-77-06. AJ Airplanes 560-0626 thru -0651 incorporating SB56077-05, and Airplanes 560-0652 thru -5000. AK Airplanes 560-0626 thru -0651 not incorporating SB560-77-05. AL Airplanes 560-0539 thru -0648 not incorporating SB560-28-11.
INTRODUCTION MODEL 560 COVERAGE This manual is intended to provide an information source for familiarization, review and suggested technique to achieve maximum safety, passenger comfort and utility, and is based on experience gained in the typical transport category jet operating environment. While the Operating Manual covers and expands upon the basic FAA Approved Airplane Flight Manual information, the FAA approved document shall take precedence should a difference be noted.
INTRODUCTION MODEL 560 DEFINITIONS AND ABBREVIATIONS AC: Alternating Current Accelerate-Stop Distance: The distance required to accelerate the aircraft and then abort the takeoff due to a failed engine, or other emergency, occurring just prior to V1 with brake application commencing at V1 ADF: Automatic Direction Finding ADI: Attitude Director Indicator AIA: Anti-icing Additive Altitude: All altitudes used in this manual are pressure altitudes unless otherwise stated.
INTRODUCTION MODEL 560 Demonstrated Crosswind: The demonstrated crosswind velocity of 30 knots (measured at 30 feet above the runway surface) is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. This is not limiting. The demonstrated crosswind velocity for an airplane using thrust reversers is 30 knots.
INTRODUCTION MODEL 560 ISA: International Standard Atmosphere in which: a. The air is a dry perfect gas; b. The temperature at sea level is 15°C (59°F); c. The pressure at sea level (standard datum plane) is 29.92 inches Hg. (1013.2 Mb); d. The temperature gradient from sea level to the altitude at which the temperature is -56.6°C will be -1.98°C per 1000 feet. ITT: Interstage Turbine Temperature. Engine operating temperature taken between the high and low pressure turbine sections.
INTRODUCTION MODEL 560 MHz: Megahertz Multiengine Normal Climb Thrust Setting Maximum power setting recommended for normal multiengine climb. N1: Low pressure turbine speed. pressure turbine. N 2: High pressure turbine speed. Net Climb Gradient: The gross climb gradient reduced by 0.8 percent during the takeoff phase and 1.1 percent during enroute. This conservatism is required by FAR Part 25 for terrain clearance determination to account for variables encountered in service.
INTRODUCTION MODEL 560 Residual Ice: That ice which is not completely removed from the leading edge of the wing and horizontal stabilizer by the surface anti-ice/deice system during operation in icing conditions. Refer to Sections II and IV of the airplane flight manual for applicable procedures. Reverse Thrust: The thrust produced when the thrust reverser deflectors are deployed into the engine exhaust stream.
INTRODUCTION MODEL 560 True Airspeed (KTAS): The airspeed (knots) of an airplane relative to undisturbed air. UHF: Ultra High Frequency Unusable Fuel: Fuel remaining after fuel runout tests have been completed in accordance with governmental regulations. U.S.: United States Usable Fuel: Fuel available for flight planning. USB: Upper Side Band V1: Takeoff decision speed.
INTRODUCTION MODEL 560 VR: The rotation speed is the speed at which rotation is initiated during takeoff to attain the V2 climb speed at or before a height of 35 feet above runway surface has been reached. VREF: The landing approach airspeed at the 50-foot point with flaps in landing position and landing gear extended (1.3 VSO). VSO: The stalling speed in the landing configuration. VS1: The stalling speed obtained in a specified configuration. V Y: Best Rate-of-Climb Speed.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 SECTION 1 DESCRIPTION AND SPECIFICATIONS General Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Fuselage . . . . . . .
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 DESCRIPTION AND SPECIFICATIONS Page Operating Limitations (Continued) Oxygen Mask . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Supplemental Oxygen System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Airplane Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 GENERAL DESCRIPTION The Cessna Citation Encore is certified in accordance with FAR Part 25 airworthiness standards and utilizes the fail-safe construction concept. It combines systems simplicity with ease of access to reduce maintenance requirements. Low takeoff and landing speeds permit operation at small and unimproved airports. Front fan type turbofan engines contribute to overall operating efficiency and performance.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 ENVIRONMENTAL CONTROL Cabin pressurization utilizes bleed air from the engines which is routed through precoolers before being conditioned by an air cycle machine. Temperature is controllable over a wide range and the system provides sufficient pressure to maintain an 8000-foot cabin at a cruise altitude of 45,000 feet.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 Figure 1-1.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 SPECIFICATIONS DIMENSIONS Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Wingspan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Horizontal Stabilizer Span . . . . . .
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 OPERATING LIMITATIONS WEIGHT Maximum Design Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum Design Takeoff Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Maximum Zero Fuel Weight (Standard) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION I DESCRIPTION AND SPECIFICATIONS Pressure Altitude - 25,000 FEET Weight - 16,630 POUNDS Maximum Maneuvering Speed - 236 KNOTS Figure 1-2.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 NOTE: Ambient Air Temperature Limit is indicated Ram Air Temperature (RAT) adjusted for Ram rise (refer to Figure 4-3 in Section IV of the FAA Approved Airplane Flight Manual. Figure 1-3.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 APPROACH AND LANDING IN ICING CONDITIONS When any residual ice is present or can be expected during approach and landing, VREF and VAPP must be increased. VREF and VAPP, the landing distance, and the maximum landing weight permitted by brake energy limits must be corrected per the appropriate tables in the Airplane Flight Manual Section IV, Performance - Approach and Landing.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 AREA AREA A B AREA C - NO ACTION REQUIRED. - RECORD IN ENGINE LOG BOOK. - REFER TO MAINTENANCE MANUAL. Figure 1-5.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 Figure 1-6.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 BATTERY AND STARTER CYCLE LIMITATIONS Three engine starts per 30 minutes. Two cycles of operation with a 90-second rest period between cycles is permitted. Battery Limitation. Three engine starts per hour. Refer to Notes 2 and 3.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 HYDRAULIC FLUID Approved Fluids: Use Skydrol 500A, B, B-4, C or LD-4; or Hyjet, Hyjet W, III, IV, IVA, or IVA Plus only. OIL The following oils are approved for use: MOBIL JET OIL II MOBIL JET OIL 254 BP TURBO OIL 2380 EXXON TURBO OIL 2380 CASTROL 5000 ROYCO TURBINE OIL 500 AEROSHELL TURBINE OIL 500 AEROSHELL TURBINE OIL 560 ROYCO TURBINE OIL 560 In addition, oils listed for the engine in the latest revision to Pratt & Whitney Canada Inc.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 1. 2.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 FUEL LIMITATIONS Anti-icing must be added to all approved fuels not presently containing additive. FUEL BOOST Pumps - ON; when low fuel lights illuminate or at 180 ± 20 pounds or less indicated fuel. The following fuels are approved for use in accordance with Figure 1-8. COMMERCIAL KEROSENE JET A, JET A-1, JET B, JP-4,JP-5, and JP-8.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 LOAD FACTOR In Flight: Flaps - UP Position (0°) . . . . . . . . . . . . . . . . . . . . . . . . . . Flaps - T.O., T.O. & APPR and LAND Position (7° to 35°) .. $1.44 to +3.6G at 16,630 Pounds 0.0 to +2.0G at 16,630 Pounds NOTE These accelerations limit the angle-of-bank in turns and limit the severity of pull-up/push-over maneuvers. Landing : Flaps LAND Position (35°) ............................. +3.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 MANEUVERS No acrobatic maneuvers, including spins, are approved. 25,000 feet. No intentional stalls are permitted above MINIMUM CREW Minimum Flight Crew for all Operations: 1 Pilot and 1 Copilot. The pilot in command must have a C-500 type rating and meet the requirements of FAR 61.58 for two pilot operation. The copilot shall possess a multi-engine rating and meet the requirements of FAR 61.55.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 INSTRUMENT MARKINGS Left and Right Oil Pressure Indicators .................. Left and Right Turbine RPM Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Left and Right Oil Temperature Indicators Flashing Red Light: Normal Operating: >100% RPM 45 to 100% RPM Red Line: Green Band: Red Triangle: 132.2°C 10 to 132.2°C 140.5°C ............... Airspeed Indicator (PFD and Standby Flight Display) . . . . . . . .
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 HONEYWELL PRIMUS-1000 FLIGHT GUIDANCE SYSTEM The Honeywell Primus 1000 Display and Flight Guidance System is a comprehensive flight management system that provides three axis airplane attitude stabilization and path control.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 STANDBY FLIGHT INSTRUMENTS 1. 2. A satisfactory preflight test must be accomplished on the standby gyro system. The standby flight display and standby HSI must be functioning prior to takeoff. HIGH FREQUENCY (HF) / AUTOMATIC DIRECTION FINDER (ADF) SYSTEMS The ADF bearing information may be erratic when keying the HF transmitter. disregard the ADF bearing during periods of transmission.
SECTION I DESCRIPTION AND SPECIFICATIONS MODEL 560 ANGLE-OF-ATTACK / STICK SHAKER SYSTEM The angle-of-attack and stall warning system must be operable and a satisfactory preflight must be performed in accordance with Section IV, Operating Information. The angle-of-attack indicating system may be used as a reference system but does not replace the airspeed display in the PFD as a primary instrument. The angle-of-attack system can be used as a reference for approach speed (1.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 SECTION II AIRPLANE AND SYSTEMS CONTENTS Page ENGINE .................................................................. 2-3 THRUST REVERSERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-4 OIL SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5 FIRE PROTECTION . . . . . . . . . . . . . . . . . . . . . . . .
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ENGINE GENERAL Jet engines produce thrust by accelerating air. It is the product of the mass of the air times the increase in velocity that determines thrust output. To generate a given amount of thrust, a small volume of air can be accelerated to a very high velocity, or a relatively large amount can be accelerated to a lower velocity. In a turbojet engine, incoming air is compressed, mixed with fuel, combusted and exhausted at a high velocity.
MODEL 560 SECTION II AIRPLANE AND SYSTEMS Figure 2-1 Engine Airflow and Cross Section NOTES • When practicing touch and go landings, the GND IDLE switch must be placed to HIGH for maximum engine acceleration capability. • When operating on the ground with engine anti-ice bleed ON, the GND IDLE switch must be in the HIGH position. ENGINE SYNCHRONIZER The synchronizer utilizes a master engine (left) and a slave engine (right).
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ENGINE SYNCHRONIZER (Continued) Alternating current from the fan and turbine monopoles is routed into the control box. When any difference in frequency is detected, a signal is sent from the control box to the actuator, which trims the speed of the slave engine to match the master engine. Normal fuel control operation is not affected. The Synchronizer will continuously monitor engine speeds and resets the slave engine speed setting as required.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 THRUST REVERSER SYSTEM DESCRIPTION AND OPERATION The thrust reversers are of the external target type employing two vertically oriented doors or buckets, which, when deployed, direct exhaust gases forward to provide a deceleration force for ground braking. When stowed, the reversers fair into external airplane contours to form the aft portion of the nacelle.
MODEL 560 SECTION II AIRPLANE AND SYSTEMS Control of the individual thrust reverser is through the reverse thrust lever mounted on each of the engine throttles. The reversers can only be deployed when the primary throttle levers are in the idle thrust position and the airplane is on the ground as sensed by that side's respective main gear squat switches. The reverse thrust lever also controls engine thrust during reverse thrust operation.
MODEL 560 SECTION II AIRPLANE AND SYSTEMS During thrust reverser deployment, the initial movement of the actuators activates the stow switches. Either switch will cause the amber UNLOCK light to illuminate. Further movement of the actuator unlocks the reverser through the overcenter linkage. The remaining travel of the actuators deploys the reverser doors.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 After deployment, power may be increased by moving the thrust reverser throttle levers aft for maximum reverse thrust. For convenience, STOPS have been installed on the thrust reverser levers and are set to provide 71.4% (N1) on a -18°C day at sea level. These stops will allow the pilot to keep his attention on the landing rollout instead of diverting his attention to the reverser power settings.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 I 56OMB-01 Figure 2-6.
SECTION II AIRPLANE AND SYSTEMS I MODEL 560 Figure 2-6.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-6.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 FIRE PROTECTION Engine fire detection consists of a closed-loop sensing system and detector control unit which illuminates the respective red ENG FIRE warning light on the cockpit glare shield if a fire or overheat condition is present. The warning light, under a transparent, spring-loaded guard, also serves as a firewall shutoff switch.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 FUEL GENERAL The Citation Encore fuel system is made up of two distinct, but essentially identical halves. Normal operation supplies fuel to the engine from its respective integral wing tank. Each half of the system holds approximately 403 U.S. gallons for a total airplane capacity of 806 gallons of usable fuel (approximately 5440 pounds). Crossfeed capability is incorporated, and when selected, enables both engines to receive fuel from a single tank.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 EJECTOR PUMPS Four ejector pumps in each fuel cell utilize existing fuel pressure in conjunction with a venturi to produce a high-volume flow. As high pressure fuel is forced through the ejector orifice, a low pressure area is created at the pump inlet drawing in a comparatively large volume of fuel and pushing it out at low pressure.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ENGINE FUEL SYSTEM The two-stage, engine-driven pump mounted on the accessory gearbox supplies high pressure flow to the fuel control unit. Fuel enters the pump at 20-30 PSI from the primary ejector pump. The engine-driven pump increases this pressure to 500-1250 PSI. Part of the pump output is bypassed through the motive flow valve to drive the primary ejector pump and the remainder is directed downstream to the fuel control.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-10 (Sheet 1 of 2) Fuel System Schematic I 2-18 Configuration AA 56OMB-01
SECTION II AIRPLANE AND SYSTEMS MODEL 560 I 56OMB-01 Figure 2-10 (Sheet 2 of 2) Fuel System Schematic Configuration AA 2-19
SECTION II AIRPLANE AND SYSTEMS MODEL 560 HYDRAULIC GENERAL The Main hydraulic system is an open-center type system. Two engine-driven pumps (one on each engine) supply a continuous flow of hydraulic fluid as long as engine(s) is operating. A reservoir stores fluid for the various hydraulically operated components. The reservoir is a boot-strap type and performs similar to a hydraulic accumulator by maintaining potential pressure on system.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 PUMPS Hydraulic pressure is provided by two positive displacement engine-driven pumps, each mounted on the engine accessory case. Either pump is capable of supplying enough pressure to operate the gear, flaps, speedbrakes, two-position horizontal stabilizer and reversers. From each pump, hydraulic fluid is routed through filters and flow switch check valve assemblies to the bypass valve and relief valve.
Figure 2-12.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 LANDING GEAR AND BRAKES GENERAL The landing gear is electrically controlled and hydraulically actuated. Each main landing gear assembly uses a single wheel assembly and an air over oil strut. The two main gear are articulated with a trailing link arrangement which improves the smoothness of landings. The nose gear has a straight oil over air strut and a chined tire for water and slush deflection.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-13 (Sheet 1 of 2) Landing Gear Extension and Retraction Flow Diagram I 2-24 Configuration AA 56OMB-01
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-13 (Sheet 2 of 2) Landing Gear Extension and Retraction Flow Diagram I 56OMB-01 Configuration AA 2-25
SECTION II AIRPLANE AND SYSTEMS MODEL 560 POSITION AND WARNING SYSTEM The landing gear position and warning system provides visual and audible indication of landing gear position. Three green safe lights and a red GEAR UNLOCK light are located in a group adjacent to the gear control handle. Each green light corresponds to one gear, NOSE, LH or RH and indicates that it is in the down and locked position. The red light indicates an unsafe gear position (in transit or not locked).
SECTION II AIRPLANE AND SYSTEMS MODEL 560 WHEEL BRAKES Toe-actuated multiple disc brakes are installed on the main gear wheels. Braking can be accomplished by either of two independent systems: the power brake hydraulic system or the back-up pneumatic system. Normal braking can be applied from either cockpit seat. The emergency brake control handle is installed under the left instrument panel only. DIGITAL ANTISKID/POWER BRAKE The antiskid system provides power assisted braking with skid protection.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 A switch on the instrument panel allows the pilot to select antiskid ON or OFF. When the switch is in the ON position, the antiskid function is operational. With the control switch in the OFF position, the ANTISKID INOP light on the annunciator panel will illuminate and the pilot will have power braking available without the antiskid function. If the power system should fail, braking will only be available through the back-up pneumatic system.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 PNEUMATIC GENERAL An air bottle which provides for emergency extension of the landing gear and/or emergency braking is located on the right side of the forward pressure bulkhead. The bottle is properly serviced at 1800-2050 PSI and can be checked on preflight by a gauge visible in the right forward baggage compartment. A relief valve on the bottle will rupture at 4000 PSI if the bottle becomes overpressurized.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-16 (Sheet 1 of 2) Wheel Brake Hydraulic System Schematic I 2-30 Configuration AA 56OMB-01
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-16 (Sheet 2 of 2) Wheel Brake Hydraulic System I 56OMB-01 Configuration AA 2-31
SECTION II AIRPLANE AND SYSTEMS MODEL 560 FLIGHT CONTROLS GENERAL All aerodynamic controls, with the exception of the flaps and speed brakes, are mechanically actuated by cables. The ailerons, elevator and rudder have trimmed control surfaces and cockpit trim position indicators. Flaps are hydraulically powered and can be operated to 15° at 200 KIAS or below and 35° (full travel) at 173 KIAS or below.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-17. Flight Controls RUDDER Rudder control is effective at all flight speeds. Full rudder deflection is 22°, ±1° either side of center. The rudder trim is mechanically operated by the rudder trim wheel on the center pedestal. With the rudder in the trail position, the trim tab will deflect 10° , ±1° left and right. In addition to mechanical actuation, the rudder trim is servo-connected to assist in rudder movement.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 When the speed brakes are fully retracted, the control valve closes, the hydraulic system bypass valve opens and open center operation resumes. Microswitches in the tailcone prevent speed brakes extension at engine power settings above approximately 85% N2. If the speed brakes are extended at lower power settings and either throttle is subsequently advanced above 85%, the speed brakes will retract and the switch will return to the RETRACT position.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ELECTRICAL GENERAL Electrical power is normally supplied by two 28.5-volt direct current (DC), 300-ampere, engine-driven starter/generators. A 24-volt, 40 or 44 ampere-hour, nickel-cadmium battery is located in the tailcone compartment to supply power for starting and emergency requirements. A receptacle below the left engine pylon is provided for connection of an external power unit.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 DIRECT CURRENT (DC) POWER The direct current (DC) power generation system consists of two starter/generators, two generator control units, one battery, two DC ammeters, one aft power junction box (divided into left and right side electrical circuits), one DC voltmeter, and control switches. Normally, the left generator powers the left main DC bus and the right main DC bus receives power from the right generator.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 CIRCUIT BREAKERS Push-to-reset, pull-off type circuit breakers, with the amperage rating marked on each breaker, are installed in panels located on both sides of the cockpit, under the side windows. Each panel incorporates various electrical system circuit breakers with the majority of the avionics circuit breakers located in the right circuit breaker panel. The AC BUS circuit breaker panel is located adjacent to the right circuit breaker panel.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 EMERGENCY BATTERY Placing the battery switch in the EMER position opens the battery relay. The emergency bus relay will remain closed. This disconnects the main direct current (DC) buses and the battery bus from the battery and connects the battery directly to the emergency bus.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ENGINE STARTING Depressing either engine start button closes the respective start relay and provides DC power to the engine starter. Power to close the solenoid start relays and energize ignition comes from the battery bus requiring the battery switch to be in the BATT position. Automatic ignition sequencing takes place with both engine ignition switches in the NORM position and throttles out of cutoff.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-18.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 5674T1001 Figure 2-18.
MODEL 560 SECTION II AIRPLANE AND SYSTEMS Figure 2-19.
MODEL 560 SECTION II AIRPLANE AND SYSTEMS Figure 2-19.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-20.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ANTI-ICE/DEICE SYSTEMS The anti-ice systems consist of bleed air heated engine inlets, wing leading edges, fan spinner and stators, and electrically heated pitot tubes, static ports and angle-of-attack probe. The horizontal stabilizer is deiced by pneumatic boots. Windshield anti-ice is provided by bleed air with alcohol backup.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 NOTE f Icing conditions exist when the indicated RAT on the ground and for takeoff is +10°C (+50°F) or below; the indicated RAT inflight is +10°C (+50°F) or below; and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet or ice crystals).
SECTION II AIRPLANE AND SYSTEMS MODEL 560 TAIL DEICE The horizontal tail is deiced by pneumatic boots controlled by the tail deice AUTO/OFF MANUAL switch. Selecting the switch to AUTO will activate a controller which will inflate the boots one side at a time and then repeat this cycle after 3 minutes, continuously, providing automatic deice of the stablizer. Selecting the momentary MANUAL position will inflate both boots as long as the pilot holds the switch in the MANUAL position.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 An additional temperature sensor is located in the bleed air line, which automatically actuates the electrical shutoff valve and illuminates the WS AIR O'HEAT annunciator light should the bleed air temperature exceed the normal control value. This condition should not occur unless a sustained high power, low airspeed condition is maintained or a system malfunction occurs.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-22.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-23.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 ENVIRONMENTAL The pressurization and air conditioning systems utilize engine bleed air to pressurize and air condition the cabin and defog the cabin and cockpit windows. During normal operation, most functions are automatic. The only manual adjustments required are for individual comfort, such as cabin rate-of-climb and temperature. Ram air for cabin ventilation is available when the pressurization system is not in use.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 During descent, the pilot can view the selected landing field altitude by pressing the FL button on the controller. The display will show cabin altitude, allowing the pilot to set the desired cabin altitude prior to landing. The controller then controls the cabin pressure rate of change to maintain the displayed cabin altitude.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-24.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 AIR CONDITIONING Air conditioning for the cabin is provided by routing engine bleed air through precoolers and in turn through the air cycle machine which conditions the air prior to distribution to the cabin. Cabin overhead and underfloor ducting is used to distribute the conditioned air. A standard R134A vapor cycle air conditioning system is also available for additional cooling up to 18,000 feet.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 An air cycle machine overheat sensor is installed between the compressor and turbine section of the air cycle machine to prevent excessively hot air from causing damage to the air cycle machine due to overheating. If this sensor indicates that the compressor section is producing air that is too hot (approximately 435°F), it will close all shutoff valves in the bleed air ducts and open the emergency pressurization valve when airplane is in flight.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 VAPOR CYCLE AIR CONDITIONING A standard vapor cycle air conditioner using R134A refrigerant is available. It discharges conditioned air from floor mounted evaporator/blowers in the forward and aft ends of the dropped isle, to provide rapid cabin cooling. The air conditioner is controlled by a switch panel on the copilot’s instrument panel, and can be used on the ground or in flight up to 18,000 feet.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-27 Oxygen System Schematic I 2-58 Configuration AA 56OMB-01
SECTION II AIRPLANE AND SYSTEMS MODEL 560 Figure 2-28. Pilot's Side Console Oxygen Control and Outlets WARNING • NO SMOKING WHEN OXYGEN IS BEING USED OR FOLLOWING USE OF PASSENGER OXYGEN UNTIL LANYARDS HAVE BEEN REINSTALLED. • DUE TO HUMAN PHYSIOLOGICAL LIMITATIONS, THE PASSENGER OXYGEN SYSTEM IS NOT SATISFACTORY FOR CONTINUOUS OPERATION ABOVE 25,000 FEET CABIN ALTITUDE AND THE CREW OXYGEN SYSTEM IS NOT SATISFACTORY FOR CONTINUOUS OPERATION ABOVE 40,000 FEET CABIN ALTITUDE.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 CREW OXYGEN MASKS The EROS crew mask is a quick donning diluter-demand/pressure breathing mask with integral microphone and oxygen regulator. It is certified to a maximum cabin altitude of 40,000 feet. A red rocker lever on the bottom of the mask labeled "N" and "100%" selects either NORMAL or 100% oxygen scheduling to the mask. In NORMAL mode the regulator increases the proportion of oxygen mixing with the cabin air as cabin altitude increases.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 LIGHTING INTERIOR LIGHTING Interior lighting is provided for the flight compartment, cabin and tailcone area. Electroluminescent panels, instrument floodlights and white background lighting illuminate all cockpit instruments and switches. Two overhead floodlights, controlled by a single rheostat switch, are available for additional cockpit lighting. The overhead floodlights operate off the emergency bus in the event of a double generator failure.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 EXTERIOR LIGHTING Exterior lighting consists of wing and tail mounted navigation lights, anti-collision lights (strobe), wing inspection lights, landing lights, combination wing recognition/taxi lights, rotating beacon, and optional tail flood lights. All exterior lights are controlled by switches located on the instrument panel. The navigation lights are installed in the wing tips and in the tailcone cap.
MODEL 560 SECTION II AIRPLANE AND SYSTEMS Figure 2-29. Annunciator Panel 1. BATT O’TEMP The red battery overtemperature light will illuminate with a steady light at temperatures over 145°F and will flash at temperatures over 160°F. Illumination of the light also triggers the master warning system and which will illuminate the master warning light.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 7. F/W SHUTOFF L R The amber firewall shutoff light advises that the left and/or right fuel and hydraulic shutoff valves are closed 8. FUEL GAUGE L R The amber fuel gauge light advises that the fuel gauging system has detected an error. 9. FUEL BOOST L R The amber fuel boost ON light advises that electrical power has been applied to the left and/or right boost pump. 10.
SECTION II AIRPLANE AND SYSTEMS MODEL 560 TEST SYSTEM The test selector is located in the upper left corner of the pilot’s switch panel and offers several positions of test. It will function only when the BATT switch is ON. A red light above the test selector switch illuminates whenever the test selector switch is in any position but OFF. Figure 2-30. Test Selector Switch OFF The red light will be off and the test system inoperative.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 SECTION III INSTRUMENTATION AND AVIONICS CONTENTS Page Instrumentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Pitot-Static Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Altimeter And Airspeed Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 Figure 3-1 Instrument Panel (Typical) I 56OMB-01 Configuration AA 3-3
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 INSTRUMENTATION The Citation Encore is equipped with a Primus 1000 Integrated Avionics System which includes display, flight director guidance, autopilot, yaw damper and pitch trim functions.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 ALTIMETER AND AIRSPEED INDICATIONS Altitude and airspeed data to the primary flight displays (PFD) are provided by information generated by the AZ-850 micro air data computers which is transmitted in digital form through the IC-600 Display Guidance Computers to the pilots’ primary flight displays. The altitude and airspeed are then presented in color on the display in the PFDs.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 LOW AIRSPEED AWARENESS A red, amber, and white thermometer type display located on the inside of the airspeed scale gives indication of low airspeed. The white extends from 1.3 VS1 to 1.2 VS1, the amber band extends from 1.2 VS1 to 1.1 VS1 (approximately stick shaker speed), and the red extends from stick shaker speed to the smaller airspeeds on the tape.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 An altitude trend vector is displayed on the left edge of the altitude tape and provides an indication of the rate of altitude change. The trend vector extends vertically from the apex of the current altitude display window. The vector extends up for positive vertical trends and down for negative values. The vector represents a prediction of what the altitude will be in six seconds if the current vertical speed is maintained.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 INCLINOMETERS Conventional inclinometers (slip indicators) are fixed to the bezel of each primary flight display. In addition, the primary flight displays also show split sky pointers.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 AMLCD INDICATING INSTRUMENT Each engine is equipped with the following instruments displayed on the center instrument panel (See Figure 3-5): Fan RPM (N1) Inter-Turbine Temperature (ITT) Turbine RPM (N2) Oil Pressure Oil Temperature Fuel Flow Also shown in addition to the engine instruments are: Ram Air Temperature (RAT) Fuel Temperature Fuel Quantity The engine instruments are displayed on a two screen active matrix liquid crystal display (AMLCD).
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 Figure 3-5 AMLCD Indicating Instrument I 56OMB-01 Configuration AA 3-11
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The ITT gage is calibrated from 0 - 7500C. The temperature displayed is a synthetic inter-turbine temperature which is computed by measuring the exhaust gas temperature and adding to it three times the temperature rise across the bypass duct. During normal engine operation, if the 7410C redline is exceeded, the ITT vertical indicator will turn red and red digits will be displayed.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 STANDBY FLIGHT DISPLAY A Meggitt Avionics Standby Flight Display (SFD) System indicator is located on the left side of the center instrument panel. This DC-powered cathode ray tube indicator combines standby attitude indicator, and altimeter, and airspeed indications into one composite instrument. A Mach indication is also included in the instrument.
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The area at the lower part of the scale (0.57 to 0.1) represents the normal operating range of the airplane, except for approach and landing. The narrow white arc (0.57 to 0.63) covers the approach and landing range and the middle of the white arc, 0.6, represents the optimum landing approach (VAPP or VREF). The yellow range (0.63 to 0.85) represents a caution area where the airplane is approaching a critical angle-of-attack. The red arc (0.85 to 1.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 DIGITAL CLOCK One model M877 digital clock is mounted on the left side of the pilot’s instrument panel and one on the right side of the copilot’s panel. The clock can be made to display four time functions: local time, GMT, flight time and elapsed time. Two versions of the elapsed time function may be selected: count up or count down. The clock has two control buttons: SEL (select) and CTL (control).
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 AVIONICS The standard avionics package includes dual audio control panels, dual VHF COMM transceivers, dual NAVs, dual RMUs, dual DMEs, dual transponders, ADF, automatic flight guidance system, pilot’s electronic flight instrument system (EFIS, which is part of the flight guidance system), a GNS-XL flight management system with GPS capability, a standby horizontal situation indicator, a secondary flight display and weather radar.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 CONTROLS AND INDICATORS Tuning of the COM radios is accomplished by three methods. The first method, discussed below, also provides methods to store frequencies in the memory locations. This is considered the "normal" method. Storing of the frequencies while tuning is not required, however, and is discussed there only because it may be convenient to store the frequencies as they are used for possible later use.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 A TX annunciation at the top of the COM frequency window will annunciate whenever the transmitter is active. When the second (first memory location) page of the display is selected, a "NARROW BANDWIDTH SELECT" annunciation will appear in the upper right corner of the display. Narrow bandwidth is the normal selection, however, a wider bandwidth may be selected for use in areas where slightly off-channel transmitters are used.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The SQ push button toggles the COM squelch open and closed. When the squelch is open, SQ is annunciated in the right center port of the display. When the EMER button is selected on the audio panel, the NAV AUDIO push button toggles the NAV AUDIO off and on. When NAV AUDIO is on, it is summed in with the COM audio. NAV AUDIO will be annunciated at the center left of the display.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 A comparator annunciator displays a flashing ACT to the left of the active frequency display when the selected control radio frequency is not identical to that of the radio receiver-transmitter unit. An OFF/ON/SQ OFF function switch is concentric with a volume control. The ON position provides power to the system and SQ OFF position disables the automatic squelch circuits which compensate for varying noise levels during normal operation.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The STO button is used to perform three separate functions. (1) When in the channel mode (NOT in program mode - program mode is annunciated by the flashing dash adjacent to the channel number), pressing and holding the STO button causes the control to display the letters "TX" and the tuned transmit frequency while the receiver monitors the transmit frequency. This enables the pilot to listen for signals on the transmit frequency of duplex channels.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 HONEYWELL PRIMUS II REMOTE RADIO SYSTEM - AUDIO CONTROL UNIT Two Honeywell Primus II digital audio control units (AV-850A) are supplied with the Honeywell Primus II remote radio system. Digital transmission of audio from remote units to the audio panels differs from conventional audio systems in that it requires one twisted pair of wires rather than many twisted pairs to achieve the same performance.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 An ID/VOICE selector is located on the right center of the audio panel. It is not a latching switch, but is active whenever NAV 1 or 2 and/or ADF 1 or 2 (if installed) is selected. If BOTH is selected, both ID and voice will be heard; if ID is selected, voice signals will be filtered out and coded identification signals will be heard. If VOICE is selected, coded signals will be filtered out and voice will be heard.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 NOTE • With passenger speaker mode selected and microphone selector switch selected to oxygen mask, the same side cockpit speaker will not receive voice interphone communications from the oxygen mask microphone of the opposite side pilot. • Headset audio is not affected when (PASS SPKR) mode is selected. A side tone control knob, which is concentric to the passenger speaker volume control knob, is located on the lower left side of the audio control panel.
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 Outer, middle, and inner marker receivers are incorporated in the VIR-432 receivers. The visual marker beacon annunciators are located in the PFD display, on the center-right side. Refer to the Electronic Flight Instrument System (EFIS) discussion in this section. The copilot’s system is a duplicate of the pilot’s, except for the fact that there is no autopilot guidance capability internal to the copilot’s IC-600 display Guidance Computer (DGC).
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 STANDBY HORIZONTAL SITUATION INDICATOR (HSI) The standby horizontal situation indicator is a three-inch instrument located on the left side of the center instrument panel. It provides navigational guidance in case of PFD/flight director failure.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 HONEYWELL PRIMUS II REMOTE RADIO SYSTEM - ADF
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 AUTOMATIC DIRECTION FINDER - COLLINS ADF-462 (Optional) The Collins ADF-462 is controlled by a CTL-62 electronic control head mounted on the right side of the center instrument panel. The automatic direction finder system operates in the frequency range of 190 to 1749.5 KHz. The CTL-62 control panel uses two digital readouts to display the controlling (active) frequency and a pilot-selected preset frequency.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The ADF bearing information may be selected on the "O" bearing needle of the pilot's electronic primary flight display (PFD). If dual ADFs are installed, the " ~ " bearing pointer will display ADF 2, when selected. Selection is accomplished by means of the bearing knobs (O and ~) on the respective DC-550. On the PFDs the single bar needle displays ADF 1 (when ADF is selected) and the double bar needle displays ADF 2 (when selected, if installed).
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The marker beacon receivers are in operation whenever the NAV receivers are ON. They operate on a frequency of 75.00 MHz. The annunciators in the pilots’ primary flight displays are part time displays. A white box. located in the center right of the display, identifies the location of the marker beacon annunciator when a localizer frequency is tuned.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 EMERGENCY LOCATOR BEACON The emergency locator beacon (ELT) system is an emergency transmitter designed to assist in locating a downed airplane. The transmitter has a self-contained battery pack which must be changed every three years or after a cumulative total of one hour of operation. The system is activated automatically by an impact of 5.0 G,+2 or -0 G along the flight axis of the airplane.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 MODE ANNUNCIATION Flight director mode annunciations are integral to the primary flight displays. The vertical and lateral modes are annunciated along the top of the display. Armed vertical and lateral modes are annunciated in white and appear slightly to the left of the position of the captured vertical and lateral mode annunciations, which are presented in green.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 MISCELLANEOUS ANNUNCIATIONS : AP FAIL Illuminates in amber to indicate automatic flight control system (AFCS) failure. MAG1 (MAG2) (DG1 (DG2) Heading Source, in mid left-center of PFD. MAG annunciation if AUTO selected on gyro slave switch; DG if MAN selected. Annunciation is in amber. No annunciation if normal selections are made. SG1 (SG2) Amber, in upper left side of primary flight display (PFD) (annunciated only in case of reversion selection).
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The selection of NAV 1, NAV 2 or FMS on the DC-550 display controller push-buttons controls the source of navigation information to the flight director, as well as selects the source of navigation information displayed on the EFIS course deviation indicator of the PFD.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 When the bank limit mode is engaged, the autopilot maximum bank angle is limited to 14 degrees. When the mode is engaged, LOW will annunciate in the pushbutton. Low bank mode will be automatically selected when climbing through 34,000 feet altitude, and will automatically cancel when descending through 33,750 feet.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 PRIMUS 1000 SYSTEM OPERATION The Primus 1000 system incorporates a wide variety of capabilities that produces one of the most precise, flexible and easy to use systems in airplanes today. The flight director and autopilot can be used independently or together.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 VNAV MODE
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 PROGRAMMING Programming is possible when a VOR station is tuned, lock-on of azimuth and DME occurs, and the waypoint desired is within selectable parameters, or when FMS navigation is in use and the next waypoint is used to define the VNAV problem. Arming of the VNAV to any waypoint consists of selection of the desired waypoint, and selection of waypoint data which will enable the flight director computer to compute a viable VNAV problem.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 TOUCH CONTROL STEERING Touch control steering (TCS) enables the airplane to be maneuvered manually during autopilot operation without cancellation of any selected flight director modes. To use touch control steering, press the TCS button, maneuver the airplane and release the TCS button. TCS is operable with all autopilot modes. During TCS operation the yaw damper will remain engaged.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 For a VOR approach (VAPP mode), the desired VOR frequency is selected on the NAV receiver, the course bearing set on the EHSI, and the APR mode is selected on the flight director mode selector. The green light will illuminate in the APR button and, if outside the capture limits, VAPP will illuminate in white on the top left side of the EADI. HDG will annunciate in green in the top right side of the EADI..
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 ALTITUDE HOLD (ALT) AND ALTITUDE PRESELECT (ASEL) Selecting altitude hold (ALT) provides steering commands to maintain the altitude at the moment of engagement. An altitude preselect (ASEL) mode is also incorporated which provides a preprogramming capability. To use altitude preselect, the desired altitude is set into the ALT window at the lower right corner of the multifunction display (MFD) by means of the knob on the bottom right of the MFD bezel.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 GO-AROUND MODE A go-around mode (GA) is available through buttons on the left and right throttles. Depressing one of the buttons will drop all other FD modes and disconnect the autopilot except, for the yaw damper. The FD command bars will command a wings level and a ten-degree nose up climb attitude. GA will illuminate in green on the EADI.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 DISPLAY CONTROLLER The display controllers, located on the left and right of the instrument panels, allows selection of the different formats and provides for selection of required navigation sources and bearing data. The individual controls are: SC/CP: Selects flight director command mode. Alternate action toggling between single cue and cross pointer flight director display. Power up state is single cue.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 Decision Height (Inner Concentric “DH”) Rotation of the "DH" knob adjusts the decision height display on the EADI. Rotating the knob fully counterclockwise removes decision height information from the display. Test Function (TEST) Pressing and holding the RA/TEST button causes the displays to enter the test mode. Flags, cautions, and all flight director and mode annunciations are tested and presented on the display.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 MULTIFUNCTION DISPLAY SYSTEM The Multifunction Display (MFD), the central DU-870 cathode ray tube, serves as the weather radar indicator. It can be used to display the horizontal navigation situation, either short range (VORTAC) or long range (FMS), and to display electronic checklists. It also provides backup capability to the EFIS systems, with a major sub-function.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The MAP format is always oriented to the airplane heading and the airplane symbol is located at the center of the display. When coupled to the FMS, the NAV route, with up to ten waypoints, can be displayed to the range limit. When weather returns are selected, range control defaults to the WC-650 Weather Radar Controller.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 MFD CONTROLS Dim This knob controls overall MFD CRT dimming in addition to the automatic dimming feature accomplished by CRT mounted photodiodes. Counterclockwise dims display. The WX display is dimmed at the same time. Joystick The function of the joystick depends upon the type of MFD display: MAP or PLAN: Moves the designator in the directions shown. TEXT: a. Vertical actuations - act as a cursor control by changing the active line.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 MFD CONTROLS SKP The function of this button depends upon the type of MFD display: MAP or PLAN: Skips the designator to the next waypoint. If the designator is not at the home position, the displacement line will be moved to the next waypoint. TEXT: Actuation skips the active line in a checklist or index and advances the active selection to the subsequent line.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 ELECTRONIC ATTITUDE DIRECTOR INDICATOR (EADI) Certain displays form a permanent part of the electronic attitude director indicator (EADI) portion of the Primary Flight Display (PFD). The displays are: the blue and brown sphere, the pitch and roll attitude reference marks, the airplane symbol, and the inclinometer which is fixed to the lower part of the PFD.
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 NOTE When the back course (BC) mode is selected on the flight director (the selected course is more than 90 degrees from the airplane heading) the glide slope indication will not be present. Vertical Track Alert - A vertical track alert message (VTA) will be displayed in amber above the glideslope/vertical path annunciation when VNAV function of FMS is selected for display. A white FMS will also be annunciated above the vertical deviation scale.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 ELECTRONIC HORIZONTAL SITUATION INDICATOR (EHSI) The displays in the EHSI portion of the PFD are discussed below in three categories: FULL TIME which are always present, PART TIME which are sometimes present, and the arc mode. FULL TIME DISPLAYS Certain displays are always present on the EHSI or are always present when certain navigation equipment is in operation.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 PART TIME DISPLAYS Part time displays are present when selected on the display controller or the flight director mode selector panel. The mode and bearing pointers available depend upon optional equipment installed and may not be present in all installations. Some annunciations also concern other systems, which will be discussed under headings pertaining to those systems.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 ARC MODE (PARTIAL COMPASS FORMAT) During operation in the arc (WX) mode, additional presentations are available which enhance navigation and safety of flight. Pressing the FULL/WX button on the display controller toggles the display between the full and partial compass display. Selecting Additional features presented in partial display are: Range Rings - Display of the range rings aids in the use of radar returns when (WX) mode is selected.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 DISPLAY REVERSION In the event of failure of one of the display units, turning off the failed display DIM knob of the display controller will cause that display to be presented on the multifunction display (MFD). Control of the display will still be through the respective display controller. EFIS EQUIPMENT FAILURE CHECKLIST Failure of equipment feeding information to EFIS will be annunciated by flags or dashes. effects of EFIS equipment are listed below.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 COMPARISON MONITOR Selected pilot and copilot input data are compared in the symbol generator. If the difference between the data exceeds predetermined levels, the out-of-tolerance symbol will be displayed in amber. A list of the compared signals and the displayed cautionary symbols is given below. When the compared pitch and roll attitude or glideslope and localizer signals are out of tolerance, a combined level (ATT or ILS) will be displayed.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 PULSE EQUIPMENT HONEYWELL PRIMUS II REMOTE RADIO SYSTEM - ATC The ATC (transponder) function of the optional SRZ-850 Integrated Radio System is provided by the XS-850 transponder module, which is a sub-unit of the RCZ-850 Integrated Communication Unit. It functions as a 4096 code mode A transponder, as well as providing mode C (altitude) and mode S (collision avoidance) information.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 Only one transponder is in operation at one time; the opposite one is held in STANDBY for instantaneous operation, if required. The system in operation is controlled by the mode select line key. Pressing the mode select line key (once the cursor is moved to that line) cycles the transponders as follows: STANDBY - Both units in STANDBY. SYSTEM No. 1 in operation. STANDBY - Both units in STANDBY. SYSTEM No. 2 in operation.
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The radio altimeter system interfaces with the data acquisition units (DAUs) and the optional ground proximity warning system. The DAUs provide information to the integrated avionics computers (IACs) which, in turn, provide the digital absolute altitude display In the PFDs, in the lower part of both attitude director (ADI) displays.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 The Primus 660 ColoRadar System is an X-band alphanumeric digital radar with display designed for weather location and analysis and for ground mapping. The radar system can also be operated in conjunction with Electronic Flight Instrument Systems (EFIS) and the Multifunction Display (MFD) to provide radar video to the EFIS EHSI display and the MFD.
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 RCT Alternate action pushbutton enables the Rain Echo Attenuation Compensation Technique (REACT) blue background field to indicate ranges at which the receiver calibration has been exceeded. The REACT OFF condition is annunciated above the button. STAB Alternate action pushbutton permits disabling the antenna stabilization causing the display to vary with airplane attitude. When disabled, the OFF condition is annunciated above the pushbutton.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEMS (TCAS) (OPTIONAL) TCAS 1
SECTION III INSTRUMENTATION AND AVIONICS
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 maneuvers. The following information is generated and considered by the TCAS II in making a decision as to whether an aircraft which returns a signal constitutes a threat or not: range between your airplane and the intruder, relative bearing of the intruder, altitude and vertical speed of the intruder( if it is reporting altitude), and the closing rate between your aircraft and the intruder.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560 AREA NAVIGATION GNS-XL FLIGHT MANAGEMENT SYSTEM The GNS-XL Flight Management System is a comprehensive navigation management system which integrates multiple systems and sensors into an integrated whole, which is capable of precise navigation and aircraft performance computations.
SECTION III INSTRUMENTATION AND AVIONICS MODEL 560
SECTION IV OPERATING INFORMATION MODEL 560 OPERATING INFORMATION TABLE OF CONTENTS Page NORMAL PROCEDURES ..................................................... 4-3 Preflight Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Preliminary Cockpit Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Exterior Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION IV OPERATING INFORMATION MODEL 560 NORMAL PROCEDURES TABLE OF CONTENTS Page NORMAL PROCEDURES ..................................................... 4-3 Preflight Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Preliminary Cockpit Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Exterior Inspection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION IV OPERATING INFORMATION MODEL 560 NORMAL PROCEDURES PREFLIGHT INSPECTION 1. 2. 3. Battery - CONNECTED. Engine Covers (2) - REMOVED. Pitot Covers (3) - REMOVED. NOTE Refer to Normal Procedures, Cold Weather Operations, if the airplane has been exposed to ambient temperatures below -10°C (+14°F) for a prolonged period. PRELIMINARY COCKPIT INSPECTION 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. Documents - CHECK ABOARD. a.
SECTION IV OPERATING INFORMATION MODEL 560 EXTERIOR INSPECTION During inspection, make a general check for security, condition and cleanliness of the airplane and components. Check particularly for damage; fuel, oil and hydraulic fluid leakage; security of access panels; and removal of keys from locks. NOTE f Expedite all checks with electrical power on and ensure that the air conditioner switch is OFF, if external power is not used.
SECTION IV OPERATING INFORMATION MODEL 560 NORMAL PROCEDURES PREFLIGHT INSPECTION 1. 2. 3. Battery - CONNECTED. Engine Covers (2) - REMOVED. Pitot Covers (3) - REMOVED. NOTE Refer to Normal Procedures, Cold Weather Operations, if the airplane has been exposed to ambient temperatures below -10°C (+14°F) for a prolonged period. PRELIMINARY COCKPIT INSPECTION 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. Documents - CHECK ABOARD. a.
SECTION IV OPERATING INFORMATION MODEL 560 EXTERIOR INSPECTION During inspection, make a general check for security, condition and cleanliness of the airplane and components. Check particularly for damage; fuel, oil and hydraulic fluid leakage; security of access panels; and removal of keys from locks. NOTE f Expedite all checks with electrical power on and ensure that the air conditioner switch is OFF, if external power is not used.
SECTION IV OPERATING INFORMATION MODEL 560 EXTERIOR INSPECTION (Continued) e. f. g. h. i. j. k. l. m. n. 5. 6. 7. 8. Anti-Ice Bleed Air Cooling Air Inlet - CLEAR. Heated Leading Edge - CONDITION and VENTS CLEAR. Fuel Quick Drains (5) - DRAIN and CHECK for contamination. Main Gear Door, Wheel, Tire and Brake - CONDITION and SECURE. Boundary Layer Energizers (16) - CHECK (none may be missing). Fuel Filler Cap - SECURE. Fuel Tank Vent - CLEAR.
SECTION IV OPERATING INFORMATION MODEL 560 EXTERIOR INSPECTION (Continued) 9. 10. 11. Left Nacelle - CHECK. a. Precooler Exhaust - CLEAR. b. Thrust Reverser Buckets - CONDITION AND STOWED. c. Engine Exhaust and Bypass Ducts - CONDITION and CLEAR. d. Engine Fluid Drain Mast - CLEAR. e. Generator Cooling Air Exhaust - CLEAR. f. Oil Level - CHECK. g. Chip Detector - TEST. h. Oil Filler Cap and Access Door - SECURE. Left Wing - CHECK. a. Flap, Speed Brakes, Aileron and Trim Tab - CONDITION and SECURE. b.
SECTION IV OPERATING INFORMATION MODEL 560 COCKPIT PREPARATION (Continued) 5. 6. 7. 8. 9. 10. 11. 12. f. IGNITION Switch - NORM. g. Fuel CROSSFEED Switch - OFF. h. Anti-Ice/Deice - OFF. i. BATTERY DISCONNECT Switch - NORM (cover down). j. Left VERT GYRO - NORM. k. LEFT GYRO - AUTO. l. Exterior Lights - OFF or AS REQUIRED. m. PANEL LIGHTS - AS REQUIRED. n. PANEL LIGHT CONTROLS - SET. o. STBY GYRO - TEST, verify green light, then ON (Amber light on). p. BEACON Light - AS DESIRED. q. LANDING LIGHTS - OFF.
SECTION IV OPERATING INFORMATION MODEL 560 COCKPIT PREPARATION (Continued) 13. Warning Systems - TEST/OFF. NOTE The W/S TEMP annunciator may not test after cold soak at extremely cold temperatures. If this occurs, repeat the test after the cabin has warmed up. The test must be completed prior to each flight. 14. 15. AVIONIC POWER Switch - OFF. Windshield Ice Detection Lights - CHECK FOR ILLUMINATION. DELAY BEFORE FLIGHT W/O GPU 1. 2. STBY GYRO - OFF. Battery Switch - OFF. BEFORE STARTING ENGINES 1.
SECTION IV OPERATING INFORMATION MODEL 560 COCKPIT PREPARATION (Continued) 5. 6. 7. 8. 9. 10. 11. 12. f. IGNITION Switch - NORM. g. Fuel CROSSFEED Switch - OFF. h. Anti-Ice/Deice - OFF. i. BATTERY DISCONNECT Switch - NORM (cover down). j. Left VERT GYRO - NORM. k. LEFT GYRO - AUTO. l. Exterior Lights - OFF or AS REQUIRED. m. PANEL LIGHTS - AS REQUIRED. n. PANEL LIGHT CONTROLS - SET. o. STBY GYRO - TEST, verify green light, then ON (Amber light on). p. BEACON Light - AS DESIRED. q. LANDING LIGHTS - OFF.
SECTION IV OPERATING INFORMATION MODEL 560 COCKPIT PREPARATION (Continued) 13. Warning Systems - TEST/OFF. NOTE The W/S TEMP annunciator may not test after cold soak at extremely cold temperatures. If this occurs, repeat the test after the cabin has warmed up. The test must be completed prior to each flight. 14. 15. AVIONIC POWER Switch - OFF. Windshield Ice Detection Lights - CHECK FOR ILLUMINATION. DELAY BEFORE FLIGHT W/O GPU 1. 2. STBY GYRO Switch - OFF. Battery Switch - OFF.
SECTION IV OPERATING INFORMATION MODEL 560 STARTING ENGINES (Continued) 2. 3. g. Fuel, Oil, Generator and Hydraulic Annunciators - EXTINGUISHED (respective engine). GND IDLE Switch - HIGH. Other Engine - START. a. Repeat procedures in item 1. NOTE The operating engine should be set to GND IDLE-HIGH for a cross generator start to provide additional amperage. Load on operating generator should be 200 AMPS or less prior to starting other engine. 4. 5. 6. 7. GND IDLE Switch - NORM.
SECTION IV OPERATING INFORMATION MODEL 560 BEFORE TAXI (Continued) 2. Flight Controls/Speed Brakes/Flaps - CHECKED/SET. NOTE Verify flaps trim interconnect operation is between 15 and 25 degrees. 3. Pitch Trim - CHECK/SET for Takeoff. a. b. c. d. e. f. g. h. i. 4. LH - Push both trim switches down and verify elevator trim movement, and push AP DISC, verify no elevator trim movement. Release AP TRIM DISC.
SECTION IV OPERATING INFORMATION MODEL 560 BEFORE TAXI (Continued) b. c. d. e. f. g. h. 9. 10. 11. Radio Altimeter - SET. Altimeters - SET and CROSS CHECK. Heading - CROSS CHECK. Communication Frequencies - SET. Navigation Frequencies - SET. Course - SET. Autopilot (at pilot’s discretion) - ENGAGE, PUSH left AP TRIM DISC switch, verify autopilot disconnects and chime sounds. Repeat using right AP TRIM DISC switch. AC Inverter Switch - CHECK INV 1 and INV 2.
SECTION IV OPERATING INFORMATION MODEL 560 BEFORE TAKEOFF 1. 2. 3. 4. Flaps - SET. Speed Brakes - RETRACTED. Trims - (3) SET FOR TAKEOFF. Anti-ice/Deice - AS REQUIRED. Check anti-ice and deice systems when icing conditions are anticipated. CAUTION f IF ANTI-ICE SYSTEMS ARE TO BE USED FOR TAKEOFF AND GROUND AMBIENT TEMPERATURE IS BETWEEN 0°C AND 10°C, CLOSE THE R WINDSHIELD BLEED AIR MANUAL VALVE FOR TAKEOFF. THIS WILL ENSURE ADEQUATE BLEED AIR TEMPERATURE REGULATION TO THE PYLON PRECOOLERS.
SECTION IV OPERATING INFORMATION MODEL 560 BEFORE TAXI (Continued) b. c. d. e. f. g. h. 9. 10. 11. Radio Altimeter - SET. Altimeters - SET and CROSS CHECK. Heading - CROSS CHECK. Communication Frequencies - SET. Navigation Frequencies - SET. Course - SET. Autopilot (at pilot’s discretion) - ENGAGE, PUSH left AP TRIM DISC switch, verify autopilot disconnects and chime sounds. Repeat using right AP TRIM DISC switch. AC Inverter Switch - CHECK INV 1 and INV 2.
SECTION IV OPERATING INFORMATION MODEL 560 BEFORE TAKEOFF 1. 2. 3. 4. Flaps - SET. Speed Brakes - RETRACTED. Trims - (3) SET FOR TAKEOFF. Anti-ice/Deice - AS REQUIRED. Check anti-ice and deice systems when icing conditions are anticipated. CAUTION f IF ANTI-ICE SYSTEMS ARE TO BE USED FOR TAKEOFF AND GROUND AMBIENT TEMPERATURE IS BETWEEN 0°C AND 10°C, CLOSE THE R WINDSHIELD BLEED AIR MANUAL VALVE FOR TAKEOFF. THIS WILL ENSURE ADEQUATE BLEED AIR TEMPERATURE REGULATION TO THE PYLON PRECOOLERS.
SECTION IV OPERATING INFORMATION MODEL 560 AFTER TAKEOFF - CLIMB 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. Landing Gear - UP. Flaps - UP. Throttles - SET CLIMB N1. ENGINE SYNC Knob - ON. Yaw Damper - ENGAGE. IGNITION Switch - NORMAL. (ON when flying in heavy rain). Passenger Advisory Lights - AS REQUIRED. Pressurization - CHECK. Altimeters- SET and CROSS CHECK (transition altitude). REC/TAXI Lights - OFF (transition altitude). A/C COMPRESSOR - OFF or FAN (above 18,000 feet). Anti-Ice/Deice - AS REQUIRED.
SECTION IV OPERATING INFORMATION MODEL 560 DESCENT 1. 2. 3. 4. 5. 6. DEFOG Fan - HI or LOW (minimum of 15 minutes prior to descent). Pilot and Copilot Foot Warmers - CLOSE (Up). AIR FLOW DISTR - CKPT. WINDSHIELD BLEED AIR Knobs - AS REQUIRED. W/S BLEED Switch - AS REQUIRED. Anti-ice/Deice - AS REQUIRED. CAUTION DO NOT OPERATE DEICE BOOTS UNDER ANY OF THE FOLLOWING CONDITIONS BECAUSE BOOT CRACKING MAY RESULT: AIRSPEEDS AT OR ABOVE 150 KIAS AND THE RAT IS LESS THAN OR EQUAL TO -35°C (-31°F).
SECTION IV OPERATING INFORMATION MODEL 560 APPROACH (Continued) 12. Landing at airports above 11,500 feet: a. PRESS SOURCE Select Knob - OFF (below 15,000 feet). b. OXYGEN CONTROL VALVE - CREW ONLY. WARNING WHEN HOLDING OR OTHERWISE OPERATING AT ALTITUDES BELOW 25,000 FEET FOR PERIODS GREATER THAN 30 MINUTES WITH THE CABIN ALTITUDE WARNING SHIFTED FROM 10,000 FEET TO 14,500 FEET (SLA BETWEEN 8000 AND 14,500 FEET), REFER TO APPROPRIATE OPERATING REQUIREMENTS FOR USE OF SUPPLEMENTAL OXYGEN.
SECTION IV OPERATING INFORMATION MODEL 560 LANDING 1. Throttles - IDLE. NOTE Eight seconds after touchdown, engines will spool down from flight idle to ground idle if the GND IDLE switch is in NORM. 2. Brakes - APPLY (after touchdown). CAUTION f IF, DURING LANDING, A NORMAL BRAKE PEDAL - NO BRAKING CONDITION IS ENCOUNTERED, OPERATE THE EMERGENCY BRAKE SYSTEM. CORRECT PRIOR TO NEXT FLIGHT. f ANTISKID SYSTEM DOES NOT FUNCTION DURING EMERGENCY BRAKING.
SECTION IV OPERATING INFORMATION MODEL 560 AFTER LANDING 1. Thrust Reversers - STOW. CAUTION DO NOT ADVANCE THROTTLES UNTIL THE THRUST REVERSER UNLOCK LIGHTS ARE OUT. 2. 3. 4. 5. 6. 7. 8. 9. Speed Brakes - RETRACT. Flaps - UP. IGNITION Switch - NORMAL. Transponder/TCAS - STBY. PITOT & STATIC Heat - OFF. Anti-Ice/Deice - WING and TAIL OFF, ENGINE As Required. Exterior Lights - AS REQUIRED. a. Anti-collision lights - OFF. b. REC/TAXI lights - AS REQUIRED. Radar - STBY or OFF. SHUTDOWN 1.
SECTION IV OPERATING INFORMATION MODEL 560 DRY MOTORING 1. 2. 3. 4. 5. 6. Throttle - OFF. IGNITION Switch - OFF. FUEL BOOST Pump - ON. ENGINE START Button - PRESS momentarily. Motor engine for the desired duration. Observe starter and battery limitations. ENGINE START DISENGAGE Button - PRESS. FUEL BOOST Pump - OFF. QUICK TURN 1. 2. Warning Systems - TEST/OFF. Return to BEFORE STARTING ENGINES checklist. TURBULENT AIR PENETRATION Flight through severe turbulence should be avoided if possible.
SECTION IV OPERATING INFORMATION MODEL 560 SPECIAL PROCEDURES SHORT FIELD OPERATION For takeoff, taxi into position as close to the approach end as possible and apply takeoff thrust while holding the brakes. FAA Approved Airplane Flight Manual takeoff field length data assumes a static run-up and use of all available runway. When specified thrust is set, release the brakes. Rotate smoothly right at VR as a delay will result in degradation of takeoff performance.
SECTION IV OPERATING INFORMATION MODEL 560 ADVERSE FIELD CONDITIONS All flight manual field length data assumes a dry, hard surface runway except where otherwise noted. Precipitation-covered runway conditions will degrade braking effectiveness and will require significantly greater actual takeoff and landing field lengths. Considerations for landing on a precipitation-covered runway are similar to those for short field operations where speed is minimized and maximum roll out distance is made available.
SECTION IV OPERATING INFORMATION MODEL 560 BIRD INGESTION PRECAUTIONS Studies have indicated that bird strikes are most likely from the surface to approximately 4000 feet AGL. As a precaution against engine flameout due to bird ingestion, it is recommended that the engine igniters be ON when flying at or below 4000 feet AGL, or anytime the crew has reason to suspect that the potential for a bird strike exists.
SECTION IV OPERATING INFORMATION MODEL 560 The abbreviated checklist is designed to enable the crew to perform all prestart functions in advance. This permits items such as the Warning Test to be complete before passenger boarding and accelerates the ramp departure without compromising safety or thoroughness. Leaving the chocks, brake checks can be done lightly and smoothly.
SECTION IV OPERATING INFORMATION MODEL 560 WHEEL FUSIBLE PLUG CONSIDERATIONS Brake application reduces the speed of an airplane by means of friction between the brake stack components. The friction generates heat, which increases the temperature of the brake and wheel assembly, resulting in an increased tire pressure. Each main wheel incorporates fuse plugs, which melt at a predetermined temperature, to prevent a possible tire explosion due to excessively high tire pressure.
SECTION IV OPERATING INFORMATION MODEL 560 FLIGHT INTO ICING Flight into known icing is the intentional flight into icing conditions that are known to exist by either visual observation or pilot weather report information. Icing conditions exist any time the indicated RAT is +10°C (+50°F) and below, and visible moisture in any form is present.
SECTION IV OPERATING INFORMATION MODEL 560 PROCEDURE FOR ADDING DIETHYLENE GLYCOL MONOMETHYL ETHER (DIEGME) FUEL ADDITIVE NOTE Service experience has shown that DIEGME has provided acceptable protection from bacterial growth in fuel systems. Use the following procedure to blend anti-icing additive as the airplane is being refueled through the wing filler caps: 1. Attach MIL-I-85470 additive to refuel nozzle, making sure blender tube discharges in the refueling stream. 2.
SECTION IV OPERATING INFORMATION MODEL 560 COLD WEATHER OPERATIONS COLD SOAK Operation of the airplane has been demonstrated after prolonged exposure to ground ambient temperature of -40°C (-40°F). This was the minimum temperature achieved in cold weather testing. The following operational procedures are recommended or required for operations where prolonged exposure to ground ambient temperatures below -10°C (+14°F) is anticipated or has occurred: 1. Preflight: a.
SECTION IV OPERATING INFORMATION MODEL 560 COLD WEATHER OPERATIONS 2. Engine Start Preparation: a. Engine preheat should not be required for engine oil temperatures down to -20°C (-4°F). However, minor engine oil leaks may occur after start at extremely cold temperatures if the engines have not been preheated. Any leak should stop once the oil seals have warmed up. Any visible oil leak must stop prior to flight. For AMLCD equipped aircraft, include step b. b.
SECTION IV OPERATING INFORMATION MODEL 560 GROUND DEICE/ANTI-ICE OPERATIONS During cold weather operations, flight crews are responsible for ensuring the aircraft is free of ice contaminants. Ground icing may occur whenever there is high humidity with temperatures of +10°C (+50°F) or colder. Type I deice, and Type II or Type IV anti-ice fluids may be used sequentially to ensure compliance with FAA regulations (clean wing concept) requiring critical component airframe deicing and anti-icing.
SECTION IV OPERATING INFORMATION MODEL 560 NOTE • Tables do not apply to other than SAE or ISO Type I, Type II, or Type IV FPD fluids. • The responsibility for the application of this data remains with the user. • The Freezing Point of Type I, Type II, and Type IV fluid mixture must be at least 10°C (18°F) below the current OAT. SPRAYING TECHNIQUE TYPE I FLUID Type I fluid should be sprayed on the aircraft (with engines off) in a manner which minimizes heat loss to the air.
NOTE: Figure 4-2 Airplane Deicing I 56OMB-01 Configuration AA
SECTION IV OPERATING INFORMATION MODEL 560 SERVICING FUEL A variety of fuels can be used in the airplane, but each must have anti-icing additive incorporated or added to the fuel during refueling. Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5, and JP-8 are approved fuels and aviation gasoline in specified amounts is approved.
SECTION IV OPERATING INFORMATION MODEL 560 OIL Each engine oil tank has an oil filler neck with a cap assembly. Oil is added to each engine directly through the filler neck and quantity is measured on the sight gage in U.S. quarts. An accurate check of oil quantity can only be made when the engine is hot, within approximately 10 minutes after engine shutdown. CAUTION PERSONS WHO HANDLE ENGINE OIL ARE ADVISED TO MINIMIZE SKIN CONTACT WITH USED OIL, AND PROMPTLY REMOVE ANY USED OIL FROM THEIR SKIN.
SECTION IV OPERATING INFORMATION MODEL 560 ALCOHOL An alcohol reservoir is located next to the brake reservoir behind the right baggage compartment aft liner. The liner must be removed for servicing. The filler plug on the reservoir should be removed and alcohol added to bring the fluid level up to the neck of the filler plug. Filling to above the sight gage provides a reserve supply of alcohol to perform preflight or operational checks without replenishing the reservoir.
SECTION IV OPERATING INFORMATION MODEL 560 AIRPLANE CLEANING AND CARE PAINTED SURFACES The exterior of a new airplane is painted with a polyurethane two-component topcoat which, unlike early coatings, does not require exposure to air for complete cure to occur. The care required by the finish will not change as the paint ages. The finish should be cleaned only by washing with clean water and mild soap, followed by rinse water and drying with a soft cloth or chamois.
SECTION IV OPERATING INFORMATION MODEL 560 The application of both AGE MASTER Number 1 and ICEX should be in accordance with the manufacturer's recommended directions as outlined on the containers. CAUTION • PROTECT ADJACENT AREAS, CLOTHING, AND USE PLASTIC OR RUBBER GLOVES DURING APPLICATIONS, AS AGE MASTER NUMBER 1 STAINS AND ICEX CONTAINS SILICONE WHICH MAKES PAINT TOUCHUP ALMOST IMPOSSIBLE. • ENSURE THAT THE MANUFACTURER’S WARNINGS AND CAUTIONS ARE ADHERED TO WHEN USING AGE MASTER NUMBER 1 AND ICEX.
SECTION V ABNORMAL PROCEDURES MODEL 560 ABNORMAL PROCEDURES TABLE OF CONTENTS ABNORMAL PROCEDURES ................................................... PAGE 5-5 ENGINE/FUEL Engine Failure/Precautionary Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inflight Restart - One Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Airstart Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION V ABNORMAL PROCEDURES MODEL 560 FLIGHT CONTROLS Electric Elevator Runaway Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Trim Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jammed Elevator Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION V ABNORMAL PROCEDURES MODEL 560 ABNORMAL PROCEDURES TABLE OF CONTENTS ABNORMAL PROCEDURES ................................................... PAGE 5-5 ENGINE/FUEL Engine Failure/Precautionary Shutdown . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Inflight Restart - One Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Airstart Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION V ABNORMAL PROCEDURES MODEL 560 FLIGHT CONTROLS Electric Elevator Runaway Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Electric Trim Inoperative . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Jammed Elevator Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION V ABNORMAL PROCEDURES MODEL 560 ABNORMAL LANDING Single-Engine Approach and Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Single-Engine Reversing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Single-Engine Go-Around . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flaps Inoperative Approach and Landing (Not In Landing Position) . . . . . . .
SECTION V ABNORMAL PROCEDURES MODEL 560 ABNORMAL PROCEDURES ENGINE FAILURE/PRECAUTIONARY SHUTDOWN 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. AP TRIM DISC Button - PRESS and RELEASE. Rudder and Aileron Trim - Trim toward operating engine as required. Throttle (affected engine) - OFF. Autopilot/Yaw Damper - ON as desired. IGNITION Switch (affected engine) - NORM. ENGINE SYNC Knob - OFF. GEN Switch (affected engine) - OFF. Electrical Load - REDUCE as required.
SECTION V ABNORMAL PROCEDURES MODEL 560 AIRSTART ENVELOPE Figure 3-3 I 5-6 Configuration AA 56OMB-01
SECTION V ABNORMAL PROCEDURES MODEL 560 ABNORMAL PROCEDURES ENGINE FAILURE/PRECAUTIONARY SHUTDOWN 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. AP TRIM DISC Button - PRESS and RELEASE. Rudder and Aileron Trim - Trim toward operating engine as required. Throttle (affected engine) - OFF. Autopilot/Yaw Damper - ON as desired. IGNITION Switch (affected engine) - NORM. ENGINE SYNC Knob - OFF. GEN Switch (affected engine) - OFF. Electrical Load - REDUCE as required.
SECTION V ABNORMAL PROCEDURES MODEL 560 AIRSTART ENVELOPE Figure 3-3 I 5-6 Configuration AA 56OMB-01
SECTION V ABNORMAL PROCEDURES MODEL 560 ENGINE START MALFUNCTION (ENGINE DOES NOT START ON GROUND) 1. 2. Throttle - OFF. ENGINE START DISENGAGE Button - PRESS 15 seconds after throttle OFF. NOTE Observe starter duty cycle limits. ENGINE STARTER WILL NOT DISENGAGE (L OR R ENGINE START BUTTON LIGHT ON AFTER ENGINE START) 1. ENGINE START DISENGAGE Button - PRESS. IF STARTER DOES NOT DISENGAGE AND ENGINE START BUTTON LIGHT REMAINS ILLUMINATED (START RELAY STUCK) 2. 3. GEN Switches - OFF.
SECTION V ABNORMAL PROCEDURES MODEL 560 LOW FUEL PRESSURE (LO FUEL PRESS L OR R CAUTION LIGHT ON) 1. 2. 3. 4. FUEL BOOST Pump Switch- ON. L or R BOOST and L or R FUEL CONTROL Circuit Breakers (LH panel) - CHECK IN. Fuel Quantity - CHECK. Fuel CROSSFEED Switch - AS REQUIRED. LOW FUEL QUANTITY (LO FUEL LEVEL L OR R CAUTION LIGHT ON) The illumination of this light serves notice to the pilot that a minimum of 180 ±20 pounds of fuel remains in the respective tank. 1. Land as soon as possible.
SECTION V ABNORMAL PROCEDURES MODEL 560 ENGINE START MALFUNCTION (ENGINE DOES NOT START ON GROUND) 1. 2. Throttle - OFF. ENGINE START DISENGAGE Button - PRESS 15 seconds after throttle OFF. NOTE Observe starter duty cycle limits. ENGINE STARTER WILL NOT DISENGAGE (L OR R ENGINE START BUTTON LIGHT ON AFTER ENGINE START) 1. ENGINE START DISENGAGE Button - PRESS. IF STARTER DOES NOT DISENGAGE AND ENGINE START BUTTON LIGHT REMAINS ILLUMINATED (START RELAY STUCK) 2. 3. GEN Switches - OFF.
SECTION V ABNORMAL PROCEDURES MODEL 560 LOW FUEL PRESSURE (LO FUEL PRESS L OR R CAUTION LIGHT ON) 1. 2. 3. 4. FUEL BOOST Pump Switch- ON. L or R BOOST and L or R FUEL CONTROL Circuit Breakers (LH panel) - CHECK IN. Fuel Quantity - CHECK. Fuel CROSSFEED Switch - AS REQUIRED. LOW FUEL QUANTITY (LO FUEL LEVEL L OR R CAUTION LIGHT ON) The illumination of this light serves notice to the pilot that a minimum of 180 ±20 pounds of fuel remains in the respective tank. 1. Land as soon as possible.
SECTION V ABNORMAL PROCEDURES MODEL 560 ENGINE DISPLAY FAILURE (BLANK DISPLAY CHANNEL) 1. Engine Display Reversion Switch - L or R. (Switch to operating side.) NOTE Depending on the failure, leaving the engine manual reversion mode switch in the AUTO position will achieve the same results as step 1 above. ENGINE DISPLAY PARAMETER FAILURE NOTE f Fuel Quantity will display amber dashes "---" and an amber "FAIL" message with sensor failure or DC power interruption to the sensor.
SECTION V ABNORMAL PROCEDURES MODEL 560 FIREWALL SHUTOFF VALVE CLOSED (F/W SHUTOFF L OR R CAUTION LIGHT ON) Indicates the fuel and hydraulic firewall shutoff valves have closed and the generator field relay has been activated by their respective ENGINE FIRE switch. ENGINE FIRE DETECTION SYSTEM FAILURE (FIRE DET SYS L OR R CAUTION LIGHT ON) Indicates failure of the affected engine fire detection system. ON GROUND 1. Correct prior to flight. IN FLIGHT 1. 2. 3.
SECTION V ABNORMAL PROCEDURES MODEL 560 ENGINE VIBRATION (ENG VIB L OR R ADVISORY LIGHT ON) (Continued) IF VIBRATION EXISTS ON GROUND 2. Correct prior to flight. IN FLIGHT 2. 3. 4. 5. Engine - MONITOR for other evidence of malfunction. Consider reducing RPM. ENGINE SYNC Knob - OFF. Throttle (affected engine) - REDUCE THRUST (as required). Land as soon as practical. IF VIBRATION INCREASES OR OTHER EVIDENCE OF ENGINE MALFUNCTION IS PRESENT 6. Consider the possibility of shutting down the engine.
SECTION V ABNORMAL PROCEDURES MODEL 560 FIREWALL SHUTOFF VALVE CLOSED (F/W SHUTOFF L OR R CAUTION LIGHT ON) Indicates the fuel and hydraulic firewall shutoff valves have closed and the generator field relay has been activated by their respective ENGINE FIRE switch. ENGINE FIRE DETECTION SYSTEM FAILURE (FIRE DET SYS L OR R CAUTION LIGHT ON) Indicates failure of the affected engine fire detection system. ON GROUND 1. Correct prior to flight. IN FLIGHT 1. 2. 3.
SECTION V ABNORMAL PROCEDURES MODEL 560 ENGINE VIBRATION (ENG VIB L OR R ADVISORY LIGHT ON) (Continued) IF VIBRATION EXISTS ON GROUND 2. Correct prior to flight. IN FLIGHT 2. 3. 4. 5. Engine - MONITOR for other evidence of malfunction. Consider reducing RPM. ENGINE SYNC Knob - OFF. Throttle (affected engine) - REDUCE THRUST (as required). Land as soon as practical. IF VIBRATION INCREASES OR OTHER EVIDENCE OF ENGINE MALFUNCTION IS PRESENT 6. Consider the possibility of shutting down the engine.
SECTION V ABNORMAL PROCEDURES MODEL 560 AFT J-BOX CURRENT LIMITER OR CIRCUIT BREAKER (AFT J BOX LMT OR CB CAUTION LIGHT ON) Indicates either an open current limiter or circuit breaker in the aft junction box. ON GROUND 1. Correct prior to flight. IN FLIGHT 1. Electrical System - MONITOR (generator voltages may vary from 25 to 33 volts). CAUTION DO NOT TURN OFF THE GENERATORS BECAUSE PARTIAL ELECTRICAL SYSTEM FAILURE MAY OCCUR ON THE BUS ASSOCIATED WITH A GENERATOR WHICH IS TURNED OFF.
SECTION V ABNORMAL PROCEDURES MODEL 560 ENVIRONMENTAL SYSTEM AIR DUCT OVERHEAT (AIR DUCT O'HEAT CAUTION LIGHT ON) 1. 2. 3. TEMP Circuit Breaker (LH Panel) - CHECK IN. Temperature Select Knob - MANUAL. MANUAL HOT/COLD Switch - COLD; hold in this position until overheat light goes out (30 seconds maximum). NOTE Operation above 31,000 feet in MANUAL full cold mode may result in the cycle machine overtemp and shutdown. Refer to Abnormal Procedures, AUTOMATIC TEMPERATURE CONTROLLER INOPERATIVE.
SECTION V ABNORMAL PROCEDURES MODEL 560 EMERGENCY PRESSURIZATION ON (AUTOMATIC ACTUATION) (EMER PRESS CAUTION LIGHT ON) AND CABIN ALTITUDE (CAB ALT WARNING LIGHT NOT ON) (Continued) IF EMER PRESS CAUTION LIGHT REMAINS ON 4. PRESS SOURCE Select Knob - EMER, then R, L or NORM. IF EMER PRESS CAUTION LIGHT STILL REMAINS ON 5. 6. 7. 8. 9. PRESS SOURCE Select Knob - EMER. Control cabin temperature with left throttle. Overhead Wemacs - OPEN. OVHD Fan Switch - HI. ENGINE SYNC Knob - OFF.
SECTION V ABNORMAL PROCEDURES MODEL 560 CABIN PRESSURIZATION CONTROLLER FAILURE (AMBER LED ILLUMINATED) NOTE Detection of auxiliary control will be indicated by the SET ALT display showing the icon and illumination of an amber LED in the upper left corner of the controller face. FL Indicates probable loss of air data sensor (copilot's) input; therefore, the controller autoschedule function will be inoperative. 1. 2. 3. Pressurization Controller Knob - SELECT CA or FL (cabin altitude or flight level).
SECTION V ABNORMAL PROCEDURES MODEL 560 ELECTRIC TRIM INOPERATIVE 1. PITCH TRIM Circuit Breaker (LH panel) - CHECK IN. IF STILL INOPERATIVE 2. Manual Elevator Trim - AS REQUIRED. NOTE Do not attempt to use the autopilot if the electric trim is inoperative. The autopilot will not be able to trim out servo torque, and disengaging the autopilot could result in a significant pitch upset. JAMMED ELEVATOR TRIM TRIM JAMMED AT CRUISE SETTING 1. 2. 3. AP TRIM DISC Button - PRESS and RELEASE.
SECTION V ABNORMAL PROCEDURES MODEL 560 AUTOPILOT OUT OF TRIM (AP ROLL MISTRIM OR AP PITCH MISTRIM CAUTION LIGHT ON) (Continued) NOTE Be prepared for minor control wheel force required to maintain desired flight path 3. 4. 5. 6. Elevator, Rudder or Aileron Trim - CHECK, ADJUST as required. Thrust - CHECK balanced. Fuel Quantity - CHECK balanced. Autopilot Button - ENGAGE as desired. LANDING WITH FAILED PRIMARY FLIGHT CONTROL CABLE RUDDER 1. 2. 3. 4. Utilize rudder trim. Yaw Damper - OFF.
SECTION V ABNORMAL PROCEDURES MODEL 560 WING ANTI-ICE FAILURE (WING ANTI-ICE L OR R CAUTION LIGHT ON AND MASTER CAUTION) 1. Throttle (affected side) - INCREASE THRUST (as required above 70% N2). IF WING ANTI-ICE LIGHT REMAINS ON 2. 3. WING XFLOW Switch - ON. Throttle (opposite side) - INCREASE THRUST (as required above 70% N2). IF WING ANTI-ICE LIGHT STILL REMAINS ON 4. L/R WING/ENG Anti-ice Circuit Breaker (affected side) (LH panel) - PULL.
SECTION V ABNORMAL PROCEDURES MODEL 560 WING ANTI-ICE FAILURE (WING ANTI-ICE L OR R CAUTION LIGHT ON AND MASTER CAUTION) (Continued) BEFORE LANDING (with ice on wing leading edges) WARNING f APPROXIMATELY 15 KNOTS INCREASE IN STALL SPEEDS CAN BE EXPECTED. f DO NOT USE AUTOPILOT FOR APPROACH AND LANDING. f USE FLAPS T.O. AND APPR (15°) FOR LANDING. f USE VAPP + 15 KNOTS FOR APPROACH AND LANDING.
SECTION V ABNORMAL PROCEDURES MODEL 560 WING BLEED AIR OVERHEAT (WING O'HEAT L OR R CAUTION LIGHT ON) IF ANTI-ICE SWITCH IS WING/ENG ON CONTINUOUS ILLUMINATION 1. 2. AFFECTED WING - DECREASE THRUST (affected engine). ENGINE SYNC Knob - OFF. IF LIGHT DOES NOT EXTINGUISH 3. 4. 5. AFFECTED WING ANTI-ICE Switch - ENGINE ON. WING XFLOW Switch - ON. LEAVE ICING ENVIRONMENT AS SOON AS POSSIBLE. TAIL DEICE FAILURE (TL DEICE FAIL L OR R CAUTION LIGHT ON) 1. 2.
SECTION V ABNORMAL PROCEDURES MODEL 560 TAIL DEICE FAILURE (TL DEICE FAIL L OR R CAUTION LIGHT ON) (Continued) 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. Passenger Advisory Lights - PASS SAFETY. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. Flaps - T.O. & APPR (15°). Flap Override Switch - GPWS FLAP OVRD ON (amber). IGNITION Switch - ON. Exterior Lights - AS REQUIRED.
SECTION V ABNORMAL PROCEDURES MODEL 560 TAIL DEICE TIMER FAILURE (TL DEICE PRESS L OR R ADVISORY LIGHT FAILS TO ILLUMINATE OR CONTINUES TO CYCLE OR TL DEICE PRESS REMAINS ILLUMINATED WITH SWITCH IN AUTO OR OFF) (Continued) 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. Avionics/Flight Instruments - CHECK /SET. Crew Briefing - COMPLETE. a. Landing Speeds and Distance - SET. b. Go-Around N1 - SET. Passenger Advisory Lights - PASS SAFETY.
SECTION V ABNORMAL PROCEDURES MODEL 560 WINDSHIELD AIR OVERHEAT (WS AIR O'HEAT CAUTION LIGHT ON) (Continued) WS AIR O'HEAT CONTINUOUS ILLUMINATION 1. W/S BLEED Switch - OFF. 2. WINDSHIELD BLEED AIR Knobs - OFF. 3. W/S ALCOHOL Switch - AS REQUIRED. NOTE 10 minutes alcohol available to pilot’s windshield only. 4. Leave icing environment as soon as possible. IF W/S BLEED SWITCH OFF WS AIR O'HEAT MOMENTARY OR CONTINUOUS ILLUMINATION Indicates probable solenoid valve failure or leak.
SECTION V ABNORMAL PROCEDURES MODEL 560 WINDSHIELD BLEED AIR FAILURE LOSS OF HOT AIR SUPPLY (VALVE WILL NOT OPEN OR POSSIBLE LINE FAILURE) 1. 2. 3. W/S BLEED Switch - OFF. WINDSHIELD BLEED AIR Knobs - OFF. W/S ALCOHOL Switch - AS REQUIRED. NOTE 10 minutes alcohol available to pilot’s windshield only. 4. Leave icing environment as soon as possible. PITOT-STATIC HEATER FAILURE (P/S HTR L OR R, OR STBY P/S HTR CAUTION LIGHT ON) 1. 2. 3. 4. 5. PITOT & STATIC Heat Switch - CHECK ON.
SECTION V ABNORMAL PROCEDURES MODEL 560 ANGLE-OF-ATTACK PROBE HEATER FAILURE (AOA HTR FAIL CAUTION LIGHT ON) Indicates that the angle of attack probe heating element has failed. 1. 2. 3. 4. PITOT & STATIC Heat Switch - CHECK ON. AOA HEATER Circuit Breaker (LH panel) - CHECK IN. Leave icing environment as soon as practical.
PFD ANNUNCIATOR (AMBER) PIT ROL HDG LOC ATT GS ILS IAS ALT RA* * 1. 2. 3. 4. 5. 1. 2.
SECTION V ABNORMAL PROCEDURES MODEL 560 LOSS OF TAS INPUT TO FLIGHT GUIDANCE SYSTEM 1. Failure Side - DETERMINE. NOTE • Failure of TAS input to the pilot’s side will generate a ’TAS FAIL’ message from FMS as well as blanking the displayed value of TAS on the MFD. Failure of TAS input to the co-pilot’s side will not result in any message annunciation. • Autopilot performance when coupled to the side with a failed TAS input will be significantly degraded in other than approach phases of flight.
SECTION V ABNORMAL PROCEDURES MODEL 560 DISPLAY GUIDANCE COMPUTER COOLING FAN FAILURE (IC-1 OR IC-2 FAN MESSAGE ON MFD) ON GROUND Indicates failure of the display guidance computer cooling fan. 1. Ground Operating Time - DO NOT EXCEED 10 MINUTES. IF GROUND OPERATING TIME EXCEEDS 10 MINUTES 2. DISPLAY GUID 1, DISPLAY GUID 2, and/or MFD Circuit Breakers (RH panel) - PULL as appropriate. CAUTION ELECTRICAL POWER MUST BE REMOVED FROM EFIS SYSTEM TO PREVENT OVERHEATING DURING GROUND OPERATIONS. 3.
SECTION V ABNORMAL PROCEDURES MODEL 560 NOSE AVIONIC FAN FAILURE (NOSE AVN FAN CAUTION LIGHT ON) ON GROUND 1. Ground Operating Time - LIMIT TO 30 MINUTES. IN FLIGHT 1. Flight may be continued in a normal manner. AUTOPILOT FAIL/DISCONNECT (AP OFF ANNUNCIATOR ON AND AP FAIL MESSAGE ON PFD) ON GROUND 1. DISPLAY GUID 1 Circuit Breaker - PULL and RESET. IN FLIGHT 1. 2. AP TRIM DISC Button - PRESS and RELEASE. Yaw Damper Switch - As desired.
SECTION V ABNORMAL PROCEDURES MODEL 560 LANDING GEAR WILL NOT EXTEND (Continued) IF GEAR EXTENDS INTO THE LOCKED POSITION 5. EMERGENCY GEAR RELEASE - PULL KNOB TO BLOW DOWN (for positive lock). NOTE Pneumatic pressure should be used to assure positive locking of all three gear actuators. 6. EMERGENCY GEAR RELEASE - RESET KNOB AND T-HANDLE (after gear down and locked). LOW HYDRAULIC FLOW (LO HYD FLOW L OR R CAUTION LIGHT ON) Indicates inoperative left or right hydraulic pump.
SECTION V ABNORMAL PROCEDURES MODEL 560 WHEEL BRAKE FAILURE 1. 2. Brake Pedals - REMOVE FEET from BRAKE PEDALS. EMER BRAKE Handle - PULL as required. CAUTION f ANTISKID SYSTEM DOES NOT FUNCTION DURING EMERGENCY BRAKING. EXCESSIVE PRESSURE ON EMER BRAKE HANDLE CAN CAUSE BOTH WHEEL BRAKES TO LOCK, RESULTING IN BLOWOUT OF BOTH TIRES.
SECTION V ABNORMAL PROCEDURES MODEL 560 LANDING GEAR WILL NOT EXTEND (Continued) IF GEAR EXTENDS INTO THE LOCKED POSITION 5. EMERGENCY GEAR RELEASE - PULL KNOB TO BLOW DOWN (for positive lock). NOTE Pneumatic pressure should be used to assure positive locking of all three gear actuators. 6. EMERGENCY GEAR RELEASE - RESET KNOB AND T-HANDLE (after gear down and locked). LOW HYDRAULIC FLOW (LO HYD FLOW L OR R CAUTION LIGHT ON) Indicates inoperative left or right hydraulic pump.
SECTION V ABNORMAL PROCEDURES MODEL 560 WHEEL BRAKE FAILURE 1. 2. Brake Pedals - REMOVE FEET from BRAKE PEDALS. EMER BRAKE Handle - PULL as required. CAUTION f ANTISKID SYSTEM DOES NOT FUNCTION DURING EMERGENCY BRAKING. EXCESSIVE PRESSURE ON EMER BRAKE HANDLE CAN CAUSE BOTH WHEEL BRAKES TO LOCK, RESULTING IN BLOWOUT OF BOTH TIRES.
SECTION V ABNORMAL PROCEDURES MODEL 560 ANTISKID SYSTEM FAILURE (ANTISKID INOP CAUTION LIGHT ON AND LO BRK PRESS CAUTION LIGHT EXTINGUISHED) (Continued) IF LIGHT REMAINS ILLUMINATED 3. ANTISKID Switch - OFF. NOTE Multiply landing distance by 1.6. 4. 5. Thrust Reverser - Maximum Reverse Thrust. Wheel Brakes - Lightly apply. CAUTION DIFFERENTIAL POWER BRAKING IS AVAILABLE.
SECTION V ABNORMAL PROCEDURES MODEL 560 SINGLE-ENGINE APPROACH AND LANDING (Continued) 12. 13. 14. 15. 16. 17. 18. 19. 20. 21. Pressurization - CHECK ZERO DIFFERENTIAL PRIOR TO LANDING. Landing Gear - DOWN. ANTI-SKID Switch - CHECK ON. Landing Lights - AS DESIRED. Airspeed - VAPP. Speed Brakes - RETRACT (50 feet AGL and below). Flaps - LAND (35°). Airspeed - VREF. Autopilot and Yaw Damper - OFF (400 feet AGL and below). Refer to Abnormal Procedures, SINGLE ENGINE REVERSING and SINGLE ENGINE GOAROUND.
SECTION V ABNORMAL PROCEDURES MODEL 560 FLAPS INOPERATIVE APPROACH AND LANDING (NOT IN LANDING POSITION) 1. Flap Override Switch - GPWS FLAP OVRD ON (amber). 2. Avionics/Flight Instruments - CHECK/SET. 3. Crew Briefing - COMPLETE. a. Landing Speeds and Distance - SET. b. Go-Around N1 - SET. 4. Passenger Advisory Lights - PASS SAFETY. 5. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure. 6.
SECTION V ABNORMAL PROCEDURES MODEL 560 CABIN DOOR PRESSURE SEAL FAILURE (DOOR SEAL CAUTION LIGHT ON) ON GROUND 1. Correct prior to flight. IN FLIGHT 1. 2. 3. 4. 5. 6. Altitude - DESCEND to 41,000 feet or lower altitude. Altitude. OXYGEN MASKS - DON AND 100%. Microphone Switches - MIC OXY MASK. Passenger Advisory Lights - PASS SAFETY. Monitor cabin pressure. Land as soon as practical. Do not descend below Minimum Safe NOTE f Secondary door seal will maintain cabin pressurization.
SECTION V ABNORMAL PROCEDURES MODEL 560 USE OF SUPPLEMENTAL OXYGEN (UNPRESSURIZED) 1. Oxygen Masks - NORMAL below 25,000 feet cabin altitude. - 100% at or above 25,000 feet cabin altitude. - EMER for SMOKE OR FIRE. - Ensure crew and passengers are receiving oxygen. NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. 2. 3. 4. 5. Cabin Altitude - MAX 25,000 feet with passengers. - MAX 40,000 feet crew only. Microphone Switches - MIC OXY MASK.
SECTION V ABNORMAL PROCEDURES MODEL 560 INADVERTENT ICING ENCOUNTER 1. 2. 3. 4. I 5-36 WING/ENGINE Anti-Ice L and R Switches - ON. W/S BLEED Switch - LOW or HI. TAIL DEICE Switch - AUTO. Airspeed - Maintain 160 KIAS minimum (except for approach and landing).
SECTION VI EMERGENCY PROCEDURES MODEL 560 EMERGENCY PROCEDURES TABLE OF CONTENTS PAGE EMERGENCY PROCEDURES .................................................. 6-3 ENGINE Engine Failure or Fire, or Master Warning During Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Fire (LH or RH Engine Fire Warning Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Failure/Fire During Final Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION VI EMERGENCY PROCEDURES MODEL 560 EMERGENCY PROCEDURES TABLE OF CONTENTS PAGE EMERGENCY PROCEDURES .................................................. 6-3 ENGINE Engine Failure or Fire, or Master Warning During Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Fire (LH or RH Engine Fire Warning Light On) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Engine Failure/Fire During Final Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION VI EMERGENCY PROCEDURES MODEL 560 EMERGENCY PROCEDURES ENGINE FAILURE OR FIRE, OR MASTER WARNING DURING TAKEOFF SPEED BELOW V1 - TAKEOFF SHOULD BE ABORTED. 1. 2. 3. 4. Brakes - AS REQUIRED. Throttles - IDLE. Speed Brakes - EXTEND. Thrust Reverser - DEPLOY ON UNAFFECTED ENGINE. 5. Thrust Reverser Indicator Lights - CHECK ILLUMINATION of ARM, UNLOCK AND DEPLOY LIGHTS. Thrust Reverser - REVERSE THRUST ON THE UNAFFECTED ENGINE. Thrust Reverser - REVERSE LEVER TO IDLE REVERSE AT 60 KIAS. 6. 7.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ENGINE FIRE (LH OR RH ENGINE FIRE WARNING LIGHT ON) 1. Throttle (affected engine) - IDLE. IF LIGHT REMAINS ON 2. 3. ENGINE FIRE Switch (affected engine) - LIFT COVER and PUSH. Either Illuminated BOTTLE ARMED Light - PUSH. 4. 5. 6. 7. 8. IGNITION Switch (affected engine) - NORM. Throttle (affected engine) - OFF. Electrical Load - REDUCE as required. Affected ENGINE Anti-ice - CHECK OFF. WING XFLOW Switch - ON as required.
SECTION VI EMERGENCY PROCEDURES MODEL 560 EMERGENCY RESTART - TWO ENGINES 1. 2. 3. IGNITION Switches - BOTH ON. FUEL BOOST Pumps - BOTH ON. Throttles - IDLE. 4. 5. 6. 7. If altitude allows - INCREASE AIRSPEED to 200 KIAS. ENGINE FIRE Switches - CHECK OPEN (F/W SHUTOFF Caution Light L or R extinguished). All Anti-Ice Switches - OFF. If no start in ten seconds: Either ENGINE START Button - PRESS momentarily. IF ENGINE DOES NOT START 8. 9. ENGINE START DISENGAGE Button - PRESS momentarily.
SECTION VI EMERGENCY PROCEDURES MODEL 560 AIRSTART ENVELOPE Figure 3-1 I 6-6 Configuration AA 56OMB-01
SECTION VI EMERGENCY PROCEDURES MODEL 560 MAXIMUM GLIDE - EMERGENCY LANDING (Continued) 7. 8. 9. 10. Passenger Advisory Lights - PASS SAFETY. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure, and stow loose items securely. Shoulder Harnesses - SECURE. Landing Gear - AS DESIRED prior to touchdown. LOW OIL PRESSURE (LO OIL PRESS L OR R WARNING LIGHT ON) BETWEEN 20 AND 45 PSI 1. 2.
SECTION VI EMERGENCY PROCEDURES MODEL 560 THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued) SPEED ABOVE V1 - TAKEOFF SHOULD NORMALLY BE CONTINUED. 1. 2. 3. 4. Emergency STOW Switch (affected engine) - EMER. Throttle (affected engine) - CHECK IDLE. Rotate - VR. Landing Gear - UP (after positive rate-of-climb). Do not exceed 150 KIAS until thrust reverser stows. 5. Climb Airspeed - V2. IF THRUST REVERSER WILL NOT STOW 6. 7. 8. 9. 10. 11. 12. 13. 14. 15.
SECTION VI EMERGENCY PROCEDURES MODEL 560 MAXIMUM GLIDE - EMERGENCY LANDING (Continued) 7. 8. 9. 10. Passenger Advisory Lights - PASS SAFETY. Passenger Briefing - CHECK passenger seats full upright, outboard and positioned aft or forward to clear all exit doors, seat belts and shoulder harnesses secure, and stow loose items securely. Shoulder Harnesses - SECURE. Landing Gear - AS DESIRED prior to touchdown. LOW OIL PRESSURE (LO OIL PRESS L OR R WARNING LIGHT ON) BETWEEN 20 AND 45 PSI 1. 2.
SECTION VI EMERGENCY PROCEDURES MODEL 560 THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued) SPEED ABOVE V1 - TAKEOFF SHOULD NORMALLY BE CONTINUED. 1. 2. 3. 4. Emergency STOW Switch (affected engine) - EMER. Throttle (affected engine) - CHECK IDLE. Rotate - VR. Landing Gear - UP (after positive rate-of-climb). Do not exceed 150 KIAS until thrust reverser stows. 5. Climb Airspeed - V2. IF THRUST REVERSER WILL NOT STOW 6. 7. 8. 9. 10. 11. 12. 13. 14. 15.
SECTION VI EMERGENCY PROCEDURES MODEL 560 THRUST REVERSER INADVERTENT DEPLOYMENT DURING TAKEOFF (Continued) 18. Speed Brakes - RETRACT (50 feet AGL and below). WARNING DO NOT INITIATE GO-AROUND BELOW 600 FEET AGL WITH A THRUST REVERSER DEPLOYED. NOTE Multiply landing distance by 1.4 for flaps 15°. GO-AROUND (WITH THRUST REVERSER DEPLOYED) 1. 2. 3. 4. 5. 6. Throttle (operating engine) - SET TAKEOFF N1. Airplane Pitch Attitude - +5°. Climb Airspeed - VAPP +10 KIAS. Flaps - 0° (when VAPP +10 KIAS).
SECTION VI EMERGENCY PROCEDURES MODEL 560 THRUST REVERSER INADVERTENT INFLIGHT DEPLOYMENT (Continued) NOTE If possible, the runway used for landing should have a minimum crosswind. BEFORE LANDING (WITH THRUST REVERSER DEPLOYED) 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. Avionics and Flight Instruments - CHECK and SET. Crew Briefing - COMPLETE. a. Landing Speeds and Distance - SET. b. Go-Around N1 - SET. Passenger Advisory Lights - PASS SAFETY.
SECTION VI EMERGENCY PROCEDURES MODEL 560 THRUST REVERSER UNLOCK LIGHT ON IN FLIGHT 1. 2. Emergency STOW Switch (affected engine) - EMER. Thrust Reverser Levers - CHECK THRUST REVERSER LEVERS AT STOWED (FULL FORWARD) POSITION. IF LIGHT WILL NOT EXTINGUISH 3. 4. 5. 6. L/R THRUST REVERSER Circuit Breakers (LH panel) - CHECK IN. Airspeed - MAINTAIN 200 KIAS or below. Altitude - FL310 or below. Land as soon as practical (affected thrust reverser will be inoperative).
SECTION VI EMERGENCY PROCEDURES MODEL 560 OVERPRESSURIZATION (Continued) 8. 9. PRESS SOURCE Select Knob - OFF. Descend to 15,000 feet MSL or Minimum Safe Altitude, whichever is higher. IF STILL OVERPRESSURIZED 10. 11. EMER DUMP Switch - ON. Refer to Emergency Procedures, EMERGENCY DESCENT and Abnormal Procedures, USE OF SUPPLEMENTAL OXYGEN. CABIN DECOMPRESSION (CAB ALT WARNING LIGHT ON) 1. 2. 3. Oxygen Masks - DON and 100% Oxygen. Microphone Switches - MIC OXY MASK. Emergency Descent - AS REQUIRED.
SECTION VI EMERGENCY PROCEDURES MODEL 560 EMERGENCY DESCENT 1. 2. 3. 4. AP TRIM DISC Button - PRESS and RELEASE. Throttles - IDLE. Speed Brakes - EXTEND. Airplane Pitch Attitude - INITIALLY TARGET 20 DEGREES NOSE DOWN ATTITUDE. 5. 6. 7. 8. 9. Airspeed - MMO/VMO (use reduced speed if structural damage has occurred). Transponder - EMERGENCY. Passenger Advisory Lights - PASS SAFETY. ATC - ADVISE and obtain local altimeter setting. Altitude - 10,000 feet MSL or Minimum Safe Altitude, whichever is higher.
SECTION VI EMERGENCY PROCEDURES MODEL 560 SMOKE REMOVAL NOTE No action is normally required; however, if smoke is intense: 1. 2. Oxygen Masks - DON and EMER. Microphone Switches - MIC OXY MASK. NOTE Headsets or hats worn by the crew should be removed prior to donning the oxygen masks. 3. 4. 5. 6. 7. 8. Smoke Goggles - DON (if required). OXYGEN CONTROL Valve - MANUAL DROP. Cockpit Divider - OPEN. Passenger Oxygen - ENSURE passengers are receiving oxygen. Passenger Advisory Light - PASS SAFETY.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) KNOWN SOURCE 5. 6. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. Land as soon as practical. UNKNOWN SOURCE 5. 6. 7. 8. INTERIOR MASTER Switch - OFF. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) 9. 10. WINDSHIELD BLEED AIR Knobs - OFF UNLESS REQUIRED FOR ANTI-ICING. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. 12. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. Land as soon as possible. COCKPIT FIRE 13. 14. 15. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). Fire - LOCATE and EXTINGUISH. Land as soon as possible. CABIN FIRE 13.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) KNOWN SOURCE 5. 6. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. Land as soon as practical. UNKNOWN SOURCE 5. 6. 7. 8. INTERIOR MASTER Switch - OFF. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) 9. 10. WINDSHIELD BLEED AIR Knobs - OFF UNLESS REQUIRED FOR ANTI-ICING. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. 12. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. Land as soon as possible. COCKPIT FIRE 13. 14. 15. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). Fire - LOCATE and EXTINGUISH. Land as soon as possible. CABIN FIRE 13.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) KNOWN SOURCE 5. 6. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. Land as soon as practical. UNKNOWN SOURCE 5. 6. 7. 8. INTERIOR MASTER Switch - OFF. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) 9. 10. WINDSHIELD BLEED AIR Knobs - OFF. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. 12. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. Land as soon as possible. COCKPIT FIRE 13. 14. 15. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). Fire - LOCATE and EXTINGUISH. Land as soon as possible. CABIN FIRE 13. 14. 15.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) KNOWN SOURCE 5. 6. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. Land as soon as practical. UNKNOWN SOURCE 5. 6. 7. 8. INTERIOR MASTER Switch - OFF. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) 9. 10. WINDSHIELD BLEED AIR Knobs - OFF. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. 12. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. Land as soon as possible. COCKPIT FIRE 13. 14. 15. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). Fire - LOCATE and EXTINGUISH. Land as soon as possible. CABIN FIRE 13. 14. 15.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE KNOWN SOURCE 5. 6. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. Land as soon as practical. UNKNOWN SOURCE 5. 6. 7. 8. INTERIOR MASTER Switch - OFF. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) 9. 10. WINDSHIELD BLEED AIR Knobs - OFF. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. 12. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. Land as soon as possible. COCKPIT FIRE 13. 14. 15. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). Fire - LOCATE and EXTINGUISH. Land as soon as possible. CABIN FIRE 13. 14. 15.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) KNOWN SOURCE 5. 6. Faulty Circuit(s) - PULL CIRCUIT BREAKER(s) to isolate. Land as soon as practical. UNKNOWN SOURCE 5. 6. 7. 8. INTERIOR MASTER Switch - OFF. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 ELECTRICAL FIRE OR SMOKE (Continued) 9. 10. WINDSHIELD BLEED AIR Knobs - OFF. Land as soon as practical (within 30 minutes). IF SEVERITY OF SMOKE WARRANTS 11. 12. Initiate Emergency Procedures, SMOKE REMOVAL and/or EMERGENCY DESCENT. Land as soon as possible. COCKPIT FIRE 13. 14. 15. Fire Extinguisher - UNSTOW and REMOVE SAFETY PIN (under copilot’s seat). Fire - LOCATE and EXTINGUISH. Land as soon as possible. CABIN FIRE 13. 14. 15.
SECTION VI EMERGENCY PROCEDURES MODEL 560 BATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON) 1. 2. 3. Amperage - NOTE. BATT Switch - EMER. Amperage - NOTE DECREASE. NOTE If current decreases and battery voltage is 1 volt less than generator voltage in 30 seconds to 2 minutes, monitor battery overheat annunciator for possible change. IF NO VOLT/AMP DECREASE (Battery Relay Stuck) 4. 5. 6. BATT Switch - BATT. BATTERY DISCONNECT Switch (LH panel) - LIFT GUARD AND DISC. Amperage - NOTE DECREASE.
SECTION VI EMERGENCY PROCEDURES MODEL 560 LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) 1. L/R GEN Switches - RESET THEN GEN. IF NEITHER GENERATOR COMES ON 2. 3. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 BATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON) 1. 2. 3. Amperage - NOTE. BATT Switch - EMER. Amperage - NOTE DECREASE. NOTE If current decreases and battery voltage is 1 volt less than generator voltage in 30 seconds to 2 minutes, monitor battery overheat annunciator for possible change. IF NO VOLT/AMP DECREASE (Battery Relay Stuck) 4. 5. 6. BATT Switch - BATT. BATTERY DISCONNECT Switch (LH panel) - LIFT GUARD AND DISC. Amperage - NOTE DECREASE.
SECTION VI EMERGENCY PROCEDURES MODEL 560 LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) 1. L/R GEN Switches - RESET THEN GEN. IF NEITHER GENERATOR COMES ON 2. 3. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 BATTERY OVERTEMPERATURE (BATT O’TEMP WARNING LIGHT ON) 1. 2. 3. Amperage - NOTE. BATT Switch - EMER. Amperage - NOTE DECREASE. NOTE If current decreases and battery voltage is 1 volt less than generator voltage in 30 seconds to 2 minutes, monitor battery overheat annunciator for possible change. IF NO VOLT/AMP DECREASE (Battery Relay Stuck) 4. 5. 6. BATT Switch - BATT. BATTERY DISCONNECT Switch (LH panel) - LIFT GUARD AND DISC. Amperage - NOTE DECREASE.
SECTION VI EMERGENCY PROCEDURES MODEL 560 LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) 1. L/R GEN Switches - RESET THEN GEN. IF NEITHER GENERATOR COMES ON 2. 3. Overhead FLOOD LTS - FULL BRIGHT. BATT Switch - EMER.
SECTION VI EMERGENCY PROCEDURES MODEL 560 LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) (Continued) NOTE When flaps are at approach (15°) and the landing gear is down for the approach to landing, maintain VAPP +10 KIAS minimum. WHEN LANDING ASSURED 6. 7. 8. 9. 10. Pressurization - ZERO DIFFERENTIAL PRIOR TO LANDING (use manual toggle switch to depressurize cabin). Landing Gear - DOWN. Flaps - LAND (35°). Airspeed - VREF +5 KIAS. Landing - Use emergency brake system.
SECTION VI EMERGENCY PROCEDURES MODEL 560 AC POWER FAILURE (AC FAIL AND MASTER WARNING LIGHTS ON) AND DUAL INVERTER FAILURE (MASTER CAUTION AND INVTR FAIL 1 AND 2 CAUTION LIGHTS ON) (Continued) IF INVTR FAIL 2 ANNUNCIATOR REMAINS ILLUMINATED 7. 8. 9. AC INVERTER NO. 2 Circuit Breaker (RH panel) - PULL. AC INVERTER NO. 1 Circuit Breaker (LH panel) - RESET. INVTR FAIL 1 Annunciator - CHECK (No annunciation indicates recovery of Inverter 1). Refer to IF INVERTER 1 OR 2 RECOVERS. NOTE If Inverter NO.
SECTION VI EMERGENCY PROCEDURES MODEL 560 LOSS OF BOTH GENERATORS (GEN OFF L AND R CAUTION LIGHTS ON AND MASTER WARNING) (Continued) WHEN LANDING ASSURED 6. 7. 8. 9. 10. Pressurization - ZERO DIFFERENTIAL PRIOR TO LANDING (use manual toggle switch to depressurize cabin). Landing Gear - DOWN. Flaps - LAND (35°). Airspeed - VREF. Landing - Use emergency brake system. Refer to Abnormal Procedures, WHEEL BRAKE FAILURE. NOTE For emergency braking, multiply landing distance by 1.6.
SECTION VI EMERGENCY PROCEDURES MODEL 560 AC POWER FAILURE (AC FAIL AND MASTER WARNING LIGHTS ON) AND DUAL INVERTER FAILURE (MASTER CAUTION AND INVTR FAIL 1 AND 2 CAUTION LIGHTS ON) (Continued) IF INVTR FAIL 2 ANNUNCIATOR REMAINS ILLUMINATED 7. 8. 9. AC INVERTER NO. 2 Circuit Breaker (RH panel) - PULL. AC INVERTER NO. 1 Circuit Breaker (LH panel) - RESET. INVTR FAIL 1 Annunciator - CHECK (No annunciation indicates recovery of Inverter 1).Refer to IF INVERTER 1 OR 2 RECOVERS. NOTE If Inverter NO.
SECTION VI EMERGENCY PROCEDURES MODEL 560 PFD/MFD RED GUN FAILURE The failure of a red gun in an electronic display indicator results in the following presentations: PFD - Sky turns from dark blue to a dull dark blue. Ground turns from brown to green hue Compass rose turns from white to blue. 1. Use display with caution - MONITOR remaining displays for any red annunciators. WARNING FOLLOWING A FAILURE OF A RED GUN IN A DISPLAY UNIT, THE RED WARNING ANNUNCIATORS WILL NOT BE VISIBLE. 2.
SECTION VI EMERGENCY PROCEDURES MODEL 560 AUTOPILOT GLIDESLOPE DEVIATION PROFILE CONDITIONS: Airspeed Flaps Gear Delay - VREF - Land - Down - One second from fault recognition. Pilot’s hands on control wheel and throttles during the approach.
SECTION VI EMERGENCY PROCEDURES MODEL 560 EMERGENCY EVACUATION 1. 2. 3. 4. 5. 6. Parking Brake - SET. Throttles - BOTH OFF. LH/RH ENGINE FIRE Switches - BOTH PRESS. LH/RH Fire Bottle Armed Switches - BOTH PRESS (if fire suspected). Passenger Advisory Lights - PASS SAFETY. BATT Switch - OFF. 7. Airplane and Immediate Area - CHECK for BEST ESCAPE ROUTE. IF THRU CABIN DOOR 8. 9. Cabin Door - OPEN. Move away from airplane. IF THRU EMERGENCY EXIT 8. 9. Emergency Exit - REMOVE and THROW OUT of airplane.
SECTION VI EMERGENCY PROCEDURES MODEL 560 DITCHING (Continued) WATER CONTACT 1. 2. 3. Aircraft Pitch Attitude - Slightly higher than Normal Landing Attitude. Reduce airspeed and rate of descent to a minimum, but do not stall the airplane. Throttles - OFF just prior to water contact and contact water on a crest of a swell, parallel to the major swell. AFTER WATER CONTACT Depending on sea conditions, multiple impacts can be expected.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 SECTION VII FLIGHT PLANNING AND PERFORMANCE CONTENTS Page WEIGHT AND BALANCE FLIGHT PLANNING ...................................................... ......................................................... 7-3 7-14 PERFORMANCE Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-57 Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 WEIGHT AND BALANCE The center-of-gravity (CG) of an airplane can be defined as the point on the longitudinal axis about which the airplane would balance. The force of weight always acts through the center-of-gravity. The forces of lift attempt to rotate the airplane about the center-of-gravity. In flight, the forces of gravity and lift from the wing and horizontal stabilizer must balance about the center-of-gravity so that stability is achieved.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 AIRPLANE WEIGHING INFORMATION
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 SAMPLE LOADING PROBLEM Standard Airplane Basic Empty Weight - 10,176 pounds.* Crew of 170 and 170 pounds in Seats 1 and 2. One 170-pound Passenger in Seat 3. One 170-pound Passenger in Seat 4. One 170-pound Passenger in Seat 5. One 170-pound Passenger in Seat 6. One 170-pound Passenger in Seat 7. One 170-pound Passenger in Seat 8. 100 pounds of baggage at station 74 in nose. 300 pounds of baggage at station 434 in tailcone baggage compartment.
SECTION VII FLIGHT PLANNING AND PERFORMANCE 10. MODEL 560 Subtract the fuel and moment used for taxi. A standard 200-pound burnoff is assumed. The moment for the taxi fuel is determined by the difference in moments of the fuel loaded and the fuel remaining on board after taxi. Check takeoff weight and moment for approved limits. NOTE To check approved limits, divide moment by weight and multiply by 100 and obtain center-of-gravity.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-3.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 FUEL LOADING WEIGHT AND MOMENT TABLE WING TANK FUEL (CONTINUED) WING TANK FUEL WEIGHT (POUNDS) MOMENT/100 ARM VARIE
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 CENTER-OF-GRAVITY LIMITS ENVELOPE Figure 7-5.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 MULTIENGINE NORMAL CLIMB ANTI-ICE SYSTEMS - OFF Figure 7-6.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 MULTIENGINE NORMAL CLIMB ANTI-ICE SYSTEMS - ON Figure 7-7.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 MAXIMUM CRUISE THRUST SETTING ANTI-ICE SYSTEMS - OFF Figure 7-8.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 MAXIMUM CRUISE THRUST SETTING ANTI-ICE SYSTEMS - ON Figure 7-9.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 FLIGHT PLANNING Thorough flight planning suggests establishing a preflight goal such as maximum range, minimum time enroute, or maximum fuel reserve within the parameters defined by the Airplane Flight Manual takeoff, climb and landing requirements. Tables for Maximum Cruise Thrust, .65 Mach, and Long Range Cruise are presented in this chapter to aid the crew in determining how best to achieve that goal.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 The following criteria are used: 1. 2. 3. 4. 5. 6. 7. 200 pounds of taxi fuel. 247 Knot /.62 Mach climb schedule for all tables. 60 percent of the cruise wind factor applied to climb; 40 percent to descent. Descent to 10,000 feet from cruise altitude using normal descent profile. Thirty nautical miles from destination at 10,000 feet and long range cruise airspeed. Ten minutes approach fuel at 856 pounds per hour total fuel flow. No reserve fuel.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-16 MODEL 560 Figure 7-10.
MODEL 560 I 56OMB-01 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-18 MODEL 560 Figure 7-10.
MODEL 560 I 56OMB-01 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
MODEL 560 I 56OMB-01 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
MODEL 560 I 56OMB-01 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-10.
MODEL 560 I 56OMB-01 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-10.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-11.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-11.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-32 MODEL 560 Figure 7-11.
MODEL 560 I 56OMB-01 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-11.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-34 MODEL 560 Figure 7-11.
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-11 Normal Cruise Thrust (Sheet 6) Configuration AA 7-35
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-36 MODEL 560 Figure 7-11 Normal Cruise Thrust (Sheet 7) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-11 Normal Cruise Thrust (Sheet 8) Configuration AA 7-37
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-38 MODEL 560 Figure 7-11 Normal Cruise Thrust (Sheet 9) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-11 Normal Cruise Thrust (Sheet 10) I 56OMB-01 Configuration AA 7-39
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-40 MODEL 560 Figure 7-12 Long Range Cruise (Sheet 1 of 16) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-001 Figure 7-12 Long Range Cruise (Sheet 2) Configuration AA 7-41
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-42 MODEL 560 Figure 7-12 Long Range Cruise (Sheet 3) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 4) I 56OMB-001 Configuration AA 7-43
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 5) I 7-44 Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 6) I 56OMB-001 Configuration AA 7-45
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 7) I 7-46 Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 8) I 56OMB-001 Configuration AA 7-47
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 9) I 7-48 Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 560OMB-01 Figure 7-12 Long Range Cruise (Sheet 10) Configuration AA 7-49
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-50 MODEL 560 Figure 7-12 Long Range Cruise (Sheet 11) Configuration AA 560OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 12 ) I 560OMB-01 Configuration AA 7-51
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 13) I 7-52 Configuration AA 560OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 14) I 560OMB-01 Configuration AA 7-53
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-12 Long Range Cruise (Sheet 15) I 7-54 Configuration AA 560OMB-01
MODEL 560 SECTION VII FLIGHT PLANNING AND PERFORMANCE Figure 7-12 Long Range Cruise (Sheet 16) I 56OMB-01 7-55/7-56(Blank)
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 CLIMB Multiengine climb performance is presented in tabulated form on the following pages. presented is based on 247 KIAS/0.62 INDICATED MACH. The climb This performance is based on maximum continuous thrust setting on both engines (refer to the Multiengine Normal Climb thrust setting chart, Figure 7-6), gear and flaps up, speedbrakes retracted and anti-ice systems OFF. The performance is also presented for anti-ice systems ON.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-58 MODEL 560 Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Configuration AA 7-59
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-60 MODEL 560 Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 CRUISE Specific performance data are presented on the following pages for various combinations of fan speeds, weights, temperature, altitudes and winds to enable the calculation of the cruise portion of a range profile. The various fan speeds presented provide the specific ranges between maximum cruise thrust (maximum TAS) and the approximate maximum range thrust.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-62 MODEL 560 Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-14 Cruise (Sheet 2) I 56OMB-01 Configuration AA 7-63
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-64 MODEL 560 Figure 7-14 Cruise (Sheet 3) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 4) Configuration AA 7-65
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-66 MODEL 560 Figure 7-14 Cruise (Sheet 5) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 6) Configuration AA 7-67
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-68 MODEL 560 Figure 7-14 Cruise (Sheet 7) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 8) Configuration AA 7-69
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-70 MODEL 560 Figure 7-14 Cruise (Sheet 9) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-14 Cruise (Sheet 10) I 56OMB-01 Configuration AA 7-71
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-72 MODEL 560 Figure 7-14 Cruise (Sheet 11) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 12) Configuration AA 7-73
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-74 MODEL 560 Figure 7-14 Cruise (Sheet 13) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 14) Configuration AA 7-75
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-76 MODEL 560 Figure 7-14 Cruise (Sheet 15) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 16) Configuration AA 7-77
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-78 MODEL 560 Figure 7-14 Cruise (Sheet 17) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-14 Cruise (Sheet 18) I 56MB-01 Configuration AA 7-79
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-80 MODEL 560 Figure 7-14 Cruise (Sheet 19) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56MB-01 Figure 7-14 Cruise (Sheet 20) Configuration AA 7-81
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-82 MODEL 560 Figure 7-14 Cruise (Sheet 21) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56MB-01 Figure 7-14 Cruise (Sheet 22) Configuration AA 7-83
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-84 MODEL 560 Figure 7-14 Cruise (Sheet 23) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56MB-01 Figure 7-14 Cruise (Sheet 24) Configuration AA 7-85
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-86 MODEL 560 Figure 7-14 Cruise (Sheet 25) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-14 Cruise (Sheet 26) I 56OMB-01 Configuration AA 7-87
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-88 MODEL 560 Figure 7-14 Cruise (Sheet 27) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 28) Configuration AA 7-89
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-90 MODEL 560 Figure 7-14 Cruise (Sheet 29) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 30) Configuration AA 7-91
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-92 MODEL 560 Figure 7-14 Cruise (Sheet 31) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-14 Cruise (Sheet 32) Configuration AA 7-93
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-94 MODEL 560 Figure 7-14 Cruise (Sheet 33) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-14 Cruise (Sheet 34) I 56OMB-01 Configuration AA 7-95
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-96 MODEL 560 Figure 7-14 Cruise (Sheet 35) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-15 Cruise (Sheet 1 of 10) Configuration AA 7-97
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-98 MODEL 560 Figure 7-15 Cruise (Sheet 2) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-15 Cruise (Sheet 3) Configuration AA 7-99
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-100 MODEL 560 Figure 7-15 Cruise (Sheet 4) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-15 Cruise (Sheet 5) Configuration AA 7-101
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-102 MODEL 560 Figure 7-15 Cruise (Sheet 6) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 Figure 7-15 Cruise (Sheet 7) I 56OMB-01 Configuration AA 7-103
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-104 MODEL 560 Figure 7-15 Cruise (Sheet 8) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-15 Cruise (Sheet 9) Configuration AA 7-105
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-106 MODEL 560 Figure 7-15 Cruise (Sheet 10) Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 DESCENT Performance for two types of descent is presented on the following pages. Time, distance and fuel information are provided for a normal descent of 2000 feet per minute, and a high speed descent of 3000 feet per minute. This performance is based on controlling the fan speed to obtain the fuel flows, airspeed and rates of descent presented with gear and flaps up, speed brakes retracted and anti-ice systems OFF or ON.
SECTION VII FLIGHT PLANNING AND PERFORMANCE I 7-108 MODEL 560 Figure 7-16 Normal Descent Configuration AA 56OMB-01
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 I 56OMB-01 Figure 7-17 High Speed Descent Configuration AA 7-109/7-110(Blank)
SECTION VII FLIGHT PLANNING AND PERFORMANCE MODEL 560 HOLDING Holding fuel in total pounds per hour is presented for various weights at several altitudes. These data are based on a nominal holding speed with gear and flaps up and speed brakes retracted.
INDEX MODEL 560 INDEX A Abbreviations . . . . . . . . . . . . . . . Introduction-6 Abnormal Procedures . . . . . . . . . . . . . . . . . 5-1 Aborted Takeoff . . . . . . . . . . . . . . . . . . . . . 6-3 AC Power . . . . . . . . . . . . . . . . . . . . . . . . 2-35 AC Power Failure . . . . . . . . . . . . . . . . . . . 6-22 AC Power System Electrical Schematic . . . . . . . . . . . . . . . 2-40, 2-41 Accessory Gearbox . . . . . . . . . . . . . . . . . . 2-5 Adverse Field Conditions . . . . . . . . . . . .
INDEX MODEL 560 INDEX Center-of-Gravity Limitations . . . . . . . . . . . . 1-7 Center-of-Gravity Limits Envelope . . . . . . . . . . . . . . . . . . . . . 7-9 Circuit Breakers . . . . . . . . . . . . . . . . 2-42, 2-43 Cleaning and Care, Airplane . . . . . . . . . . . 4-39 CDU ........................... 3-19 Climb Performance . . . . . . . . . . . . . . . . . . 7-57 Clock . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-16 Cockpit Inspection . . . . . . . . . . . . . . . . . . .
INDEX MODEL 560 INDEX F Filters, Fuel . . . . . . . . . . . . . . . . . . . . . . . 2-17 Fire Bottles . . . . . . . . . . . . . . . . . . . . . . . 4-38 Fire Extinguishing System, Engine . . . . . . . . . . . . . . . . . . . . . . 2-14 Fire Protection . . . . . . . . . . . . . . . . . . . . . 2-14 Flaps . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-34 Flight Controls . . . . . . . . . . . . . . . . . 1-3, 2-32 Flight Controls, Abnormal Procedures . . . . . . . . . . . . . . . . . . .
INDEX MODEL 560 INDEX Lighting, Exterior . . . . . . . . . . . . . . . . . . . 2-62 Lighting, Interior . . . . . . . . . . . . . . . . . . . . 2-61 Lighting, Nose Compartment . . . . . . . . . . . 2-61 Lighting, Tailcone Compartment . . . . . . . . . . . . . . . . . 2-61 Limitations, Operating . . . . . . . . . . . . . . . . . 1-7 Limitations, Airspeed . . . . . . . . . . . . . . . . . . 1-7 Limitations, Alcohol . . . . . . . . . . . . . . . . . . 1-16 Limitations, Altitude . . . . . . . . . . . . . .
INDEX MODEL 560 INDEX Performance, Airplane . . . . . . . . . . . . . . 7-1/7-2 Climb . . . . . . . . . . . . . . . . . . . . . . . 7-57 Cruise . . . . . . . . . . . . . . . . . . . . . . 7-61 Descent . . . . . . . . . . . . . . . . . . . . 7-107 Holding . . . . . . . . . . . . . . . . . . . . 7-111 Pitot-Static and Angle-of-Attack Anti-ice . . . . . . . . . . . . . . . . . . . . . 2-48 Pitot-Static Systems . . . . . . . . . . . . . . . . . . 3-4 Pneumatic System Servicing . . . . . . . . . .
INDEX MODEL 560 INDEX Tire Pressure . . . . . . . . . . . . . . . . . . . . . . Touch Control Steering . . . . . . . . . . . . . . . To/From Bias . . . . . . . . . . . . . . . . . . . . . . Toilet Servicing . . . . . . . . . . . . . . . . . . . . Traffic and Collision Avoidance System (TCAS) . . . . . . . . . . . . . . . Transponder . . . . . . . . . . . . . . . . . . . . . . True Airspeed Probe . . . . . . . . . . . . . . . . . . Turbulent Air Penetration . . . . . . . . . . . . . .
