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KING AIR C90GTi/C90GTx

PILOT TRAINING MANUAL

• EFIS

• Displays the following information

• Uncorrected Pressure Altitude
• Baro-Corrected Altitude
• Vertical Speed
• Airspeed (KIAS & KCAS)
• Indicated Airspeed Trend Vector
• Mach Number
• Maximum Airspeed (V

MO

/M

MO

)

• True Airspeed
• Ram Air Temperature (RAT)
• Static Air Temperature (SAT)

• ISA Deviation Temperature

• Wind Direction and Speed Vector

• Attitude and Heading Reference

Systems (AHRS)

• Integrated Avionics Processor Sys-

tem (IAPS)

Figure 16-43. ADC

ATTITUDE AND HEADING
REFERENCE SYSTEM
(AHRS)

The Attitude and Heading Reference System
(AHRS) provides pitch, bank, and magnetic
heading data to the onside displays (Figure
16-44). Both Units are installed under the
cabin ﬂoor near the center of the aircraft.

Figure 16-44. AHRS

Magnetic heading information is obtained
from separate magnetic sensors located in
each wing. Compensator units automatically
correct for magnetic interference within the
airplane or due to sensor error.

Attitude information is obtained from two at-
titude and heading computers (AHC). Each
system includes an inertial measurement unit
(IMU) that monitors angular rates and accel-
erations about the airplane axes. The IMU
does not provide self generated navigation po-
sition. The AHC processes IMU data to de-
termine airplane pitch and bank attitude.

Each AHC is provided with a primary and sec-
ondary power supply for redundancy. If the
secondary power supply should fail, the pri-
mary power supply will continue powering the
AHC. After 10 minutes of operation on pri-
mary power only,the primary power supply
will cease operating. The power loss to the
AHC will result in a total failure of that AHC.
There will be no indication, except from a pos-
sible tripped circuit breaker. This indicates a
failure of the secondary power supply. If the
primary power supply should fail, the AHC
will immediately fail. In either case, the cross-
side AHC may then be selected using the
AHRS reversionary switch to regain AHRS
information on the affected side.

The output of each AHRS is supplied to the
integrated avionics processor system (IAPS)

16-22

FOR TRAINING PURPOSES ONLY

16

A

VIONICS

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Summary of Contents for C90GTi

Page 1: ...ia Airport Flushing New York 11371 718 565 4100 www FlightSafety com KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 VOLUME SECOND EDITION The best safety device in any aircraft is a well trained crew KING AIR C90GTi C90GTx PILOT TRAINING MANUAL SECOND EDITION ...

Page 2: ...me of printing it contained then current information In the event of conflict between data provided herein and that in publications issued by the manufacturer or the FAA that of the manufacturer or the FAA shall take precedence We at FlightSafety want you to have the best training possible We welcome any suggestions you might have for improving this manual or any other aspect of our training progr...

Page 3: ...Safety learning centers Wichita Hawker Beechcraft Learning Center 9720 East Central Avenue Wichita Kansas 67206 Phone 316 612 5300 Toll Free 800 488 3747 Fax 316 612 5399 Copyright 2010 by FlightSafety International Inc All rights reserved Printed in the United States of America ...

Page 4: ... 1 3 8 0 4 i 4 iv 0 4 1 4 12 0 5 i 5 iv 0 5 1 5 22 0 6 i 6 ii 0 7 i 7 iv 0 7 1 7 46 0 8 i 8 iv 0 8 1 8 8 0 9 i 9 iv 0 9 1 9 8 0 10 i 10 iv 0 10 1 10 20 0 11 i 11 iv 0 11 1 11 16 0 12 i 12 iv 0 12 1 12 14 0 13 i 13 ii 0 14 i 14 vi 0 14 1 14 26 0 15 i 15 iv 0 15 1 15 8 0 16 i 16 x 0 16 1 16 104 0 16A i 16A vi 0 16A 1 16A 24 0 17 i 17 iv 0 17 1 17 12 0 18 i 18 iv 0 18 1 18 4 0 19 i 19 iv 0 19 1 19 18...

Page 5: ......

Page 6: ...DITIONING Chapter 12 PRESSURIZATION Chapter 13 HYDRAULIC POWER SYSTEMS Chapter 14 LANDING GEAR AND BRAKES Chapter 15 FLIGHT CONTROLS Chapter 16 AVIONICS Chapter 16A WIDE AREA AUGMENTATION SYSTEM WAAS Chapter 17 OXYGEN SYSTEM Chapter 18 MISCELLANEOUS SYSTEMS Chapter 19 MANEUVERS AND PROCEDURES Chapter 20 WEIGHT AND BALANCE Chapter 21 FLIGHT PLANNING AND PERFORMANCE Chapter 22 CREW RESOURCE MANAGEME...

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Page 8: ...RIPTION 1 5 King Air C90GTi and C90GTx Configuration 1 10 Cabin Entry and Exits 1 12 Emergency Exit 1 14 Cabin Compartments 1 15 Flight Deck 1 16 Control Surfaces 1 25 Tiedown and Securing 1 26 Taxiing 1 27 Servicing Data 1 27 Product Support 1 29 Preflight Inspection 1 29 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 AIRCRAFT GENERAL ...

Page 9: ......

Page 10: ...16 1 12 Control Wheels and Fuel Control Panel C90GTi and C90GTx 2 Sheets 1 17 1 13 Instrument Panels 1 19 1 14 Pedestal and Right Side Panel 1 20 1 15 Pilot s and Copilot s Subpanels 1 21 1 16 Annunciators 1 22 1 17 Overhead Light Control Panel C90GTi and C90GTx 2 Sheets 1 23 1 18 Flight Control Surfaces 1 25 1 19 Flight Control Locks 1 25 1 20 Tiedowns 1 26 1 21 Propeller Boots 1 26 1 22 Turning ...

Page 11: ......

Page 12: ...TABLE Table Title Page 1 1 Specifications C90GTi and C90GTx 1 11 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 v FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL ...

Page 13: ......

Page 14: ...ockpit layout In this chapter of the training manual you will find diagrams and data describing the airplane in general and its systems that are not included in the Pilot s Operating Handbook POH Reference material in this training manual covers all of the aircraft systems Each chap ter is complete and independent and can be referred to in any sequence Following are brief descriptions of the sub j...

Page 15: ...arning System Chapter 4 Master Warning System pre sents a description and discussion of the warn ing caution and advisory annunciator panels Each annunciator is described in detail in cluding its purpose and associated cause for illumination Emphasis is on corrective action required by the pilot if an annunciator is il luminated Fuel System Chapter 5 Fuel System presents a de scription and discuss...

Page 16: ...principle of operation controls and emer gency procedures Pressurization System Chapter 12 Pressurization presents a de scription of the pressurization system The function of various major components their physical location and operation of the pres surization system controls are discussed Where necessary references are made to the environmental system as it affects pressur ization Landing Gear an...

Page 17: ...igation and radio tuning while a Flight Guidance System FGS allows the pilot to input attitude heading airspeed and ver tical speed commands for the Flight Director Autopilot Individual audio panels for the pilot and copilot allow each pilot to select audio from any nav com receiver Oxygen Chapter 17 Oxygen presents a summary of the oxygen system and its components General description principle of...

Page 18: ...e is all metal low wing mono plane It has fully cantilevered wings and a conventional tail empennage The wings are an efficient high aspect ratio design with composite winglets for added efficiency on the C90GTx The airfoil section provides an excellent combination of low drag for cruise conditions and easy handling for the low speed terminal conditions or small air port operations A faired oval m...

Page 19: ...or 3 Outboard Flap Section 15 Baggage Area 4 Ground Escape Hatch 16 Airstair Door 5 Inboard Flap Section 17 Aileron Trim Tab 6 Liquid Storage Cabinet 18 Leading Edge Fuel Tanks 7 Lavatory Privacy Curtain 19 Wing Ice Check Light 8 Belted Lavatory 20 Nacelle Fuel Tank 9 Pressurization Safety and Dump Valves 21 PT6 135A Turboprop Engine 10 Oxygen Bottle 22 Heated Pitot Mast 11 Emergency Locator Trans...

Page 20: ...RAFT GENERAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 7 FOR TRAINING PURPOSES ONLY 1 FEET 1 1 2 INCHES 12 FEET 3 INCHES 14 FEET 3 INCHES 35 FEET 6 INCHES 17 FEET 3 INCHES 12 FEET 9 INCHES 7 FEET 6 INCHES 50 FEET 3 INCHES 7 2 Figure 1 3 Three View Diagram C90GTi Sheet 1 of 2 ...

Page 21: ...G PURPOSES ONLY 1 AIRCRAFT GENERAL 1 8 FOR TRAINING PURPOSES ONLY 2 1 FEET 1 1 2 INCHES 12 FEET 3 INCHES 14 FEET 3 INCHES 35 FEET 6 INCHES 17 FEET 3 INCHES 12 FEET 9 INCHES 7 FEET 6 INCHES 53 FEET 8 INCHES 7 Figure 1 3 Three View Diagram C90GTx Sheet 2 of 2 ...

Page 22: ...squared oval not round Figure 1 5 Passengers can sit comfortably without leaning their heads to accommodate sloping walls The floors are flat from side to side for passenger ease in entering and leaving the cabin These air craft are certificated for up to 13 people KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL 1 9 FOR TRAINING PURPOSES ONLY Figure 1 4 E...

Page 23: ... the most maneuverable corporate airplanes in the world Insistence on handling ease in all flight regimes and tough construction tech niques contribute to the following KIAS data calculated at maximum takeoff weight of 10 100 pounds for the C90GTi and 10 485 for the C90GTx Maximum operating speed VMO 226 KIAS Maneuvering speed VA 169 KIAS C90GTi 163 KIAS C90GTx Maximum landing gear operating speed...

Page 24: ...S MAXIMUM ZERO FUEL WEIGHT NO STRUCTUAL LIMITATION 9378 POUNDS MAXIMUM WEIGHT IN BAGGAGE COMPARTMENT REAR BAGGAGE COMPARTMENT 350 POUNDS 350 POUNDS NOSE AVIONICS COMPARTMENT 350 POUNDS 350 POUNDS CABIN AND ENTRY DIMENSIONS CABIN WIDTH MAXIMUM 54 INCHES 54 INCHES CABIN LENGTH PARTITION TO PARTITION 155 INCHES 155 INCHES CABIN LENGTH MAXIMUM BETWEEN PRESSURE BULKHEADS 214 INCHES 214 INCHES CABIN HEI...

Page 25: ...are movable and au tomatically fold flat against the door in the closed position A self storing platform au tomatically folds down over the door sill when the door opens to provide a stepping platform for door seal protection KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 12 FOR TRAINING PURPOSES ONLY Figure...

Page 26: ... Locking Mechanism The door locking mechanism is operated by either of the two vertically staggered han dles one inside and the other outside the door The inside and outside handles are me chanically interconnected When either handle is rotated per placard instructions two latch bolts at each side of the door and two latch hooks at the top of the door lock into the doorframe to secure the airstair...

Page 27: ...lts fas tened After the airplane has made a full stop landing only a crewmember should check the se curity of the airstair door EMERGENCY EXIT The emergency exit door is located at the third cabin window on the right side of the fuselage see Figure 1 7 A placard at the window gives instructions for access to the release mechanism The door is released from the inside with two hooks a trigger button...

Page 28: ...the cabin area is the baggage area This pressurized area is capable of holding 53 5 cubic feet of luggage cargo or cloth ing all accessible in flight The location of the baggage area next to the airstair door makes loading and unloading easy If an operation requires some or all of the seats wall partitions and lavatory can be quickly removed to configure the airplane for cargo transport KING AIR C...

Page 29: ... provided for each seat The general layout of the flight deck shows the location of the instruments and controls Conventional dual controls are installed so that the airplane can be flown by either pilot Figure 1 12 The con trols and instruments are ar ranged for convenient single pilot operation or for a pilot and copilot crew KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONL...

Page 30: ...CE MAP LIGHT SWITCH DETAIL B COPILOT DETAIL C DETAIL A PILOT ELECTRICAL TRIM ROCKER SWITCHES ELECTRICAL TRIM ROCKER SWITCHES AUTOPILOT AND YAW DAMP 1ST LEVEL ELECTRIC TRIM INTERRUPT SWITCH 2ND LEVEL MICROPHONE SWITCH LINE ADVANCE AUTOPILOT AND YAW DAMP 1ST LEVEL ELECTRIC TRIM INTERRUPT SWITCH 2ND LEVEL 8 DAY CLOCK A A B B C C Figure 1 12 Control Wheels and Fuel Control Panel C90GTi Sheet 1 of 2 ...

Page 31: ...ITCH LINE ADVANCE DETAIL B COPILOT DETAIL C DETAIL A PILOT ELECTRICAL TRIM ROCKER SWITCHES ELECTRICAL TRIM ROCKER SWITCHES AUTOPILOT AND YAW DAMP 1ST LEVEL ELECTRIC TRIM INTERRUPT SWITCH 2ND LEVEL MICROPHONE SWITCH LINE ADVANCE AUTOPILOT AND YAW DAMP 1ST LEVEL ELECTRIC TRIM INTERRUPT SWITCH 2ND LEVEL A A B B C C Figure 1 12 Control Wheels and Fuel Control Panel C90GTx Sheet 2 of 2 ...

Page 32: ...d pedestal Figure 1 14 Engine controls flap control handle rudder and aileron trim knobs and pressurization controls are mounted on this pedestal On the right side panel next to the copilot is the main circuit breaker panel Figure 1 14 where the majority of the system circuit breakers are located The static air selector handle is mounted just below the circuit breaker panel Just below the instrume...

Page 33: ...90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 20 FOR TRAINING PURPOSES ONLY A A B B DETAIL A DETAIL B Figure 1 14 Pedestal and Right Side Panel ...

Page 34: ...0GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 21 FOR TRAINING PURPOSES ONLY DETAIL A DETAIL B A A B B Figure 1 15 Pilot s and Copilot s Subpanels ...

Page 35: ... flasher Green annunciators will not trigger a flasher KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 22 FOR TRAINING PURPOSES ONLY DETAIL A A LFUELPRESS LOILPRESS LDC GEN LIGNITION ON R IGNITION ON LAUTOFEATHER RAUTOFEATHER LENGANTI ICE R ENGANTI ICE MAN TIES CLOSE FUELCROSSFEED LNO FUELXFER RVS NOT READY L...

Page 36: ... COPILOT DISPLAYS BRT COPILOT INSTR PNL OFF WINDSHIELD WIPERS OFF PARK SLOW FAST DO NOT OPERATE ON DRY GLASS MASTER PANEL LIGHTS ON OFF ANNUN PUSH BRT CAUTION STALL WARNING IS INOPERATIVE WHEN MASTER SWITCH IS OFF STANDBY COMPASS IS ERRATIC WHEN WINDSHIELD ANTI ICE AND OR AIR CONDITIONER AND OR ELECTRIC HEAT IS ON OPERATION LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE I...

Page 37: ...WHEN WINDSHIELD ANTI ICE AND OR AIR CONDITIONER AND OR ELECTRIC HEAT IS ON OPERATION LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS ARE APPROVED THIS AIRPLANE APPROVED FOR VFR IFR DAY NIGHT OPERATION IN ICING CONDITIONS AIRSPEED KNOTS GEA...

Page 38: ... ing brake handle mounted just under the left corner of the subpanel and the rudder gust lock bar mounted between the pilot s rud der pedals Before towing the airplane the parking brake must be released brake handle pushed in and the rudder gust lock bar must be re moved from between the rudder pedals Serious damage to the tires brakes and steering linkage can result if these items are not release...

Page 39: ... the airplane down with suitable chain or rope Install the control surface lock and be sure the flaps are up Secure the propellers with appropriate tiedown boots one blade up to prevent wind milling Figure 1 21 This airplane has free spinning propellers that could be hazardous if not restrained Windmilling gears and bearings without lu brication is not good practice When there is blowing dust or r...

Page 40: ...ly mea sured reasonable care should be taken to prevent incidents within these danger areas SERVICING DATA The Handling Servicing and Maintenance section of the POH outlines to the Owner and Operator the requirements for main taining the aircraft in a condition equal to that of its original manufacture This infor mation sets time intervals at which the air plane should be taken to a Beechcraft Avi...

Page 41: ...Maintenance Manual Battery Lead acid 24 Volt 42 Ampere Hour Fire Extinguishers Hand Type Halon 1301 Oxygen Supply Cylinder Oxygen Specification MIL 0 27210 Aviators Breathing Oxygen 22 49 or 66 Cu Ft Engine Fire Extinguisher Typical Left Right Extinguishing Agent MIL E 52031 2 5 lbs CF3BR 450 psi Dry Nitrogen Tire Size C90GTi Main Wheels 8 50 x 10 tubeless 8 or 10 ply C90GTx Main Wheels 8 50 x 10 ...

Page 42: ...er controlled parts ser vice that assures rapid shipment of equip ment on a 24 hour basis PREFLIGHT INSPECTION The preflight inspection procedure in the POH has been divided into five areas as shown in Figure 1 25 The inspection be gins in the flight compartment proceeds aft then moves clockwise around the aircraft discussing the left wing landing gear left engine and propeller nose section etc Ex...

Page 43: ... AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 1 30 FOR TRAINING PURPOSES ONLY 1 3 4 5 2 Figure 1 25 Exterior Inspection ...

Page 44: ...er Distribution 2 5 Bus Tie System 2 9 Bus Isolation 2 12 Load Shedding 2 12 Battery 2 12 Starter Generators 2 13 DC Generation 2 14 External Power 2 15 Avionics Master Power 2 16 Circuit Breakers 2 16 QUESTIONS 2 35 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 2 ELECTRICAL POWER SYSTEMS ...

Page 45: ......

Page 46: ... 2 21 2 12 Power Distribution Battery ON Generator Ties Manually Closed 2 22 2 13 Power Distribution Right Engine Start Generator Ties Manually Closed 2 23 2 14 Power Distribution Right Generator ON 2 24 2 15 Power Distribution Left Engine Cross Start Right Engine Running 2 25 2 16 Power Distribution Both Generators ON 2 26 2 17 Power Distribution Both Generators ON Generator Ties Open 2 27 2 18 B...

Page 47: ......

Page 48: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY TABLES Table Title Page 2 1 Electrical System Buses and Feeders 2 6 2 v 2 ELECTRICAL POWER SYSTEMS ...

Page 49: ......

Page 50: ...system with the negative lead of each power source grounded to the main air plane structure DC electrical power is pro vided by one 42 ampere hour sealed lead acid battery and two 250 ampere starter generators connected in parallel Basic electrical symbols are shown in Figure 2 2 FOR TRAINING PURPOSES ONLY 2 1 CHAPTER 2 ELECTRICAL POWER SYSTEMS KING AIR C90GTi C90GTx PILOT TRAINING MANUAL INTRODUC...

Page 51: ...ART RELAY TRIPLE FED BUS Figure 2 1 Electrical System Component Locations FOR TRAINING PURPOSES ONLY 2 2 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 2 ELECTRICAL POWER SYSTEMS GEN CONT GEN CONT HOT BATT BUS CTR BUS BATTERY EPR EXT PWR STR GEN STR GEN B B T R B T R S B L S B L B T R G B U S L G B U S L C S R R C S R R S R R L C L S R L L C B R LEGEND LEFT L R B BT RIGHT BATTERY BUS TIE LINE CONTAC...

Page 52: ...intains the battery at full charge This airplane utilizes a multi bus system The main buses are the left and right gen erator buses center bus triple fed bus and the hot battery bus Switches in the cockpit which receive power from the center or triple fed buses are identified by a white ring on the panel around the switch Electrical loads are divided among the buses as noted on the Electrical Syst...

Page 53: ...r to their respective left and right generator buses The center bus is fed by two generator buses and the battery which automatically con nects those components whenever the bus ties are closed The power distribution schematics Figures 2 9 through 2 23 show how buses are interconnected PILOT S SUBPANEL LJ 1063 THRU LJ 1352 Figure 2 3 Pilot and Copilot Subpanels FOR TRAINING PURPOSES ONLY 2 4 KING ...

Page 54: ...trical system bus arrangement is de signed to provide multiple power sources for all circuits DC POWER DISTRIBUTION The DC power distribution system is com monly called a triple fed system In nor mal operation all buses are automatically tied into a single loop system in which all sources collectively supply power through individual protective devices Three in flight DC power sources are available...

Page 55: ...ional Pilot Instrument Control Pilot PDF DCP FGP MFD RTU CDU 1 CDU 2 PROPELLERS Propeller Sync WEATHER L Fuel Vent Heat Pilot Windshield Heat RIGHT GENERATOR BUS AVIONICS Avionics R Gen Bus MFD Heater DCU 2 EDC 2 ELECTRICAL R Gen Bus Tie Power ENGINE R Fuel Control Heat R Engine Chip Detector R Main Engine Anti ice L Stby Engine Anti Ice Control WARNING ANNUNCIATORS NO SMOKE FSB Signs WEATHER Copi...

Page 56: ...nitor Power L Start Control R Starter Control L Torque Meter R Torque Meter L Oil Press R Oil Press ENVIRONMENTAL Cabin Air Temperature Cabin Pressure Control L Bleed Air Control FLIGHT INSTRUMENTS Outside Air Temperature LANDING GEAR Landing Gear Control LIGHTS Cabin Lights Instruments Indirect Lights Navigation Lights PROPELLERS Propeller Governor Test WARNING ANNUNCIATORS Annunciator Indicator ...

Page 57: ...ri GPS 1 Left IAPS CDU 1 Radar TCAS FGC 1 Servo GPS 2 optional Right IAPS TAWS XMWX optional Com 3 optional RIGHT GEN AVIONICS BUS ADC 2 AHC 2 CDU 2 optional CMU optional Copilot Audio Copilot Audio Control Copilot DCP Copilot PFD Copilot PFD Heater DME 2 optional Com 2 Nav 2 ATC 2 FGC 2 Servo Flt Inst Pnl Cooling IEC TRIPLE FED AVIONICS BUS SFDS BUS Bus Control SFDS Light ADU DISP MHS ADC 1 AHC 1...

Page 58: ... triple fed bus is powered by the battery and each generator bus through 60 amp lim iters and through diodes providing fault iso lation protection between the power sources BUS TIE SYSTEM The electrical system is protected from ex cessively high current flow by the bus tie system Three current sensors consisting of Hall effect devices and solid state circuitry are used to sense current flow throug...

Page 59: ...YSTEM FIRE WALL VALVE BOOST PUMP BUS SFDS SFDS LIGHTS DISP ADU MHS BAT CHG CNTL LTG DBU PILOT INSTR CNTL INSTR CNTL PILOT PFD FGP MFD CNTL CDU2 RTU COPILOT COPILOT PFD PEDESTAL DBU ENG INST EDC1 SEC DCU1 DCU1 SEC EDC2 DCU2 DCU2 TRANS PUMP QTY IND PRESS WARN CROSS FEED PRESS WARN QTY IND TRANS PUMP BOOST PUMP FIRE WALL VALVE BUS TPL FED L GEN R GEN BAT STBY DCP DCP 5 10 5 3 2 5 5 5 5 3 1 2 15 5 5 5...

Page 60: ...rolonged activation of this switch will damage or destroy the sensor modules and should be avoided Momentary activation of the switch to RESET powers the coil of the bus tie relays unlatching the test circuits and permitting the bus ties to energize close Voltage is transferred from the annunciator readouts to the coils closing the bus tie relays Since high current sensing is latched out when the ...

Page 61: ...s LOAD SHEDDING Load shedding is another highly beneficial feature of the triple fed bus electrical sys tem The electrical system will automati cally remove excess loads generator buses when the power source is reduced to bat tery only When both generators are off line the generator bus ties open and the gener ator bus loads are shed Figure 2 19 The battery will continue to power the center triple...

Page 62: ...peration The gen erator shunt field winding is disabled when the series starter winding is activated by the start switch The regulated output of the gen erator is 28 25 0 25 volts with a maximum continuous load of 250 amperes In addition to the starter generators the gen erator system consists of control switches generator control units GCU line con tactors and loadmeters Figure 2 6 Battery Instal...

Page 63: ...40 seconds ON 1 minute off 40 seconds ON then 30 minutes off DC GENERATION The generator phase of operation is con trolled by the generator switches located in the pilot s left subpanel next to the BAT switch under the MASTER SWITCH gang bar Figure 2 3 The switches provide OFF ON and RESET capabilities The generat ing system is self exciting and does not re quire electrical power from the aircraft...

Page 64: ...ralleling circuit averages the output of both generators to equalize load levels The paralleling circuits of both GCUs be come operative when both generators are on the line The paralleling circuits sense the interpole winding voltages of both genera tors to provide an indication of the load on each generator The voltage regulator circuits are then biased up or down as required to increase or decr...

Page 65: ... IN THE AIRPLANE If the battery voltage is less than 20 volts the battery must be recharged or replaced with a battery indicating at least 20 volts before connecting external power Only use an external power source f itted with an AN type plug The auxiliary power unit must be regulated between 28 0 and 28 4 volts DC and be capable of producing 1000 amperes for 5 seconds 500 amperes for two minutes...

Page 66: ... do not reset it Resetting a tripped breaker can cause further damage to the component system or a lead to a electrical fire If an essential system circuit breaker trips however after a 1 minute cooldown time and no electrical or burning smell attempt to reset the circuit breaker If it fails to reset DO NOT attempt to reset it again Take corrective ac tion according to the procedures in the Emerge...

Page 67: ... MASTER POWER C B BATTERY BUS TRIPLE FED ON Off NUMBER 2 AVIONICS BUS NUMBER 1 AVIONICS BUS NUMBER 3 AVIONICS BUS RIGHT GENERATOR BUS Figure 2 8 Avionics Master Power Schematic KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 2 18 FOR TRAINING PURPOSES ONLY 2 ELECTRICAL POWER SYSTEMS ...

Page 68: ... CROSS START RELAY LEFT STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS BATTERY SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL...

Page 69: ...Y RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS BATTERY SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GPU Figure 2 10 Power Distribution Battery OFF 2 20 FOR TRAINING PURPOSES ONLY KING AIR...

Page 70: ...CROSS START RELAY LEFT STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS BATTERY SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL ...

Page 71: ... RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS BATTERY SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GPU Figure 2 12 Power Distribution Battery ON Generator Ties Manually Closed FOR TRAINING PURPOSES ONL...

Page 72: ...TART RELAY LEFT STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GP...

Page 73: ...ARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GPU Figure 2 14 Power Distribution Right Generator ON FOR TRAINING PURPOSES ONLY 2 24 KING...

Page 74: ...S START RELAY LEFT STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL...

Page 75: ...ARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GPU Figure 2 16 Power Distribution Both Generators ON FOR TRAINING PURPOSES ONLY 2 26 KING...

Page 76: ... GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 SFDS SW 275 RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL ED 60 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE GPU CENTER BUS TRIPLE ...

Page 77: ...ELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 SFDS SW 275 RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL ED 60 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE GPU CENTER BUS TRIPLE FED BUS Figure 2 18 Bus Sense Test Both Generators ON FOR TRAINING PURPOSES ONLY 2 28 KING A...

Page 78: ...S START RELAY LEFT STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS BATTERY SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENE...

Page 79: ...S SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE 275 60 GENERATOR CONTROL GPU V RIGHT GENERATOR BUS TO GENERATOR FIELD RIGHT STARTER GENERATOR RIGHT GENERATOR SWITCH LOAD METER RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 250 GENERATOR CONTROL Figure 2 20 Right Generator Bus Short Bus Isolation FOR TRAINING PURPOSES O...

Page 80: ...STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 60 SFDS BATTERY SFDS SW 275 RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 60 GENERATOR CONTROL GENERATOR CONTROL ED 60 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE GPU CENTER...

Page 81: ...TARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GPU Figure 2 22 Triple Fed Bus Short Bus Isolation FOR TRAINING PURPOSES ONLY 2 32 KING A...

Page 82: ...RT RELAY LEFT STARTER GENERATOR RIGHT STARTER GENERATOR LEFT GENERATOR BUS TIE LEFT STARTER RELAY RIGHT STARTER RELAY LEFT GENERATOR SWITCH RIGHT GENERATOR SWITCH LOAD METER LOAD METER 250 60 60 SFDS SW 275 AMMETER BATTERY RELAY BATTERY SWITCH FROM HOT BATTERY BUS BATTERY BUS TIE RIGHT GENERATOR BUS TIE LEFT CROSS START RELAY RIGHT LINE CONTACTOR 275 250 60 GENERATOR CONTROL GENERATOR CONTROL GPU ...

Page 83: ...INTENTIONALLY LEFT BLANK FOR TRAINING PURPOSES ONLY 2 34 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 2 ELECTRICAL POWER SYSTEMS ...

Page 84: ... the switch to ON for one second 6 When an engine is being started in what position should its GEN switch be A RESET B ON C OFF 7 When a generator is off line what indication is present A An amber DC GEN light is on B No indications are present C A green DC GEN light is on D A red DC GEN light is on 8 Where is the external power connector located A Under the left wing B On the left aft fuselage C ...

Page 85: ...FF 40 seconds ON 60 seconds OFF 60 seconds ON 90 seconds OFF C 20 seconds ON 60 seconds OFF 20 seconds ON 60 seconds OFF 20 seconds ON 90 minutes OFF D 15 seconds ON 50 seconds OFF 15 seconds ON 60 seconds OFF 10 seconds ON 5 minutes OFF 15 What electrical bus or buses feed the items on the sub panel with the white rings around them A Center only B Hot Batt Bus only C Triple Fed only D Center or T...

Page 86: ...ONTENTS Page INTRODUCTION 3 1 DESCRIPTION 3 1 Cockpit Lighting 3 1 Cabin Lighting 3 4 Exterior Lighting 3 5 Circuit Breakers 3 6 QUESTIONS 3 7 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 3 LIGHTING ...

Page 87: ......

Page 88: ... Control Panel C90GTi and C90GTx 2 Sheets 3 2 3 2 Cabin Lighting Controls 3 4 3 3 Threshold Light Switch 3 4 3 4 Exterior Light Controls 3 5 3 5 Light System Circuit Breakers 3 6 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 3 LIGHTING ...

Page 89: ......

Page 90: ...s DESCRIPTION The Lighting chapter of the training manual presents a description and discussion of the airplane lighting system and components The location and purpose of switches indicators lights and circuit breakers are described COCKPIT LIGHTING An overhead light control panel easily ac cessible to both pilot and copilot incorpo rates a functional arrangement of all lighting systems in the coc...

Page 91: ...INDSHIELD ANTI ICE AND OR AIR CONDITIONER AND OR ELECTRIC HEAT IS ON OPERATION LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS ARE APPROVED THIS AIRPLANE APPROVED FOR VFR IFR DAY NIGHT OPERATION IN ICING CONDITIONS AIRSPEED KNOTS GEAR EXTE...

Page 92: ...INDSHIELD ANTI ICE AND OR AIR CONDITIONER AND OR ELECTRIC HEAT IS ON OPERATION LIMITATIONS THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS MARKINGS AND MANUALS NO ACROBATIC MANEUVERS INCLUDING SPINS ARE APPROVED THIS AIRPLANE APPROVED FOR VFR IFR DAY NIGHT OPERATION IN ICING CONDITIONS AIRSPEED KNOTS GEAR EXTE...

Page 93: ...he interior light switch activates the cabin NO SMOK ING FASTEN SEAT BELT signs and ac companying chimes This three position switch is placarded NO SMK FSB OFF FSB A hot wired threshold light is mounted on the left side of the entryway at floor level Optional airstair door lights mounted under each step may be installed These lights share the same controls a slide type switch Figure 3 3 mounted ad...

Page 94: ...egardless of the position of the battery master switch This baggage com partment light is connected to the hot bat tery bus EXTERIOR LIGHTING Switches for the landing lights taxi lights wing ice lights navigation lights recogni tion lights rotating beacons and wingtip and tail flood lights are located on the pilot s subpanel Figure 3 4 They are appropri ately placarded as to their function Tail fl...

Page 95: ...CIRCUIT BREAKERS Lighting system circuit breakers are shown in Figure 3 5 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 3 6 FOR TRAINING PURPOSES ONLY 3 LIGHTING Figure 3 5 Light System Circuit Breakers ...

Page 96: ...the door frame B Automatically when the battery switch is turned off C With a switch on the pilot s right subpanel D Automatically when the airstair door is opened and the threshold switch turned on 4 Where is the switch for the strobe lights located A On the overhead panel B On the copilot s side panel C On the pilot s right subpanel D On the pilot s side panel 5 Where are the recognition lights ...

Page 97: ......

Page 98: ...TION 4 1 GENERAL 4 1 ANNUNCIATOR SYSTEM 4 3 Master Warning Flasher 4 3 Dimming 4 5 Testing and Lamp Replacement 4 5 ANNUNCIATOR PANEL DESCRIPTION 4 6 QUESTIONS 4 11 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 4 MASTER WARNING SYSTEM ...

Page 99: ......

Page 100: ...aution Flashers 4 3 4 3 Warning Caution and Advisory Annunciators 4 4 4 4 Lamp Replace 4 5 TABLES Table Title Page 4 1 WARNING Annunciators 4 6 4 2 CAUTION Annunciators 4 7 4 3 ADVISORY Annunciators 4 9 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 4 MASTER WARNING SYSTEM ...

Page 101: ......

Page 102: ...n until a safe landing can be made In the case of an on ground indication the problem should be corrected before flight GENERAL This chapter presents a description and dis cussion of the warning caution and advi sory annunciator panel The annunciator panel is described in detail including each annunciator its purpose and the associated cause for illumination KING AIR C90GTi C90GTx PILOT TRAINING M...

Page 103: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 4 2 FOR TRAINING PURPOSES ONLY 4 MASTER WARNING SYSTEM FAULT WARNING ANNUNCIATORS PRESS TO TEST SWITCH Figure 4 1 Annunciator System ...

Page 104: ...fault condition is corrected at which time it will extinguish An annunciator can be extinguished only by correcting the condi tion indicated on the illuminated lens The illumination of a green annunciator light will not trigger the fault warning system but a red annunciator will actuate the MAS TER WARNING flasher Yellow annuncia tors will actuate the yellow MASTER CAUTION flasher MASTER WARNING F...

Page 105: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 4 4 FOR TRAINING PURPOSES ONLY 4 MASTER WARNING SYSTEM Figure 4 3 Warning Caution and Advisory Annunciators ...

Page 106: ...on Depressing the PRESS TO TEST button located to the right of the annunciator panel in the glareshield illuminates all the an nunciator lights and the MASTER WARN ING flasher Any lamp that fails to illuminate when tested should be replaced The annunciator panel style allows each an nunciator to be removed from the panel Figure 4 4 Each readout annunciator con tains two lamps To replace any annunc...

Page 107: ...R TRAINING PURPOSES ONLY 4 MASTER WARNING SYSTEM NOMENCLATURE CAUSE FOR ILLUMINATION Low fuel pressure on left side check boost pump crossfeed Low oil pressure in left engine Cabin pressure altitude exceeds 12 500 feet Cabin door is open or not secure Low oil pressure in right engine Low fuel pressure on right side check boost pump crossfeed Fire in left engine compartment Fire in right engine com...

Page 108: ... engine anti ice vanes fail in transit or inoperative Right engine anti ice vanes fail in transit or inoperative Left Pitot Heat inoperative or switch is in the OFF position Right Pitot Heat inoperative or switch is in the OFF postition Left generator bus is isolated from the center bus Battery is isolated from the generator buses and center bus Right generator bus is isolated from the center bus ...

Page 109: ...OMENCLATURE CAUSE FOR ILLUMINATION The left bleed air valve switch is in the Closed position The right bleed air valve switch is in the Closed position Right wing tank is empty or transfer pump failed Right generator is off line External power connector is plugged in Table 4 2 CAUTION ANNUNCIATORS Cont ...

Page 110: ...t ignition and engine start switch is ON Left autofeather is armed with power levers advanced above 90 N1 position or autofeather test switch is in test Right autofeather is armed with power levers advanced above 90 N1 position or autofeather test switch is in test Left engine anti ice vanes are in position for icing conditions Right engine anti ice vanes are in position for icing conditions Manua...

Page 111: ...INTENTIONALLY LEFT BLANK KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 4 10 FOR TRAINING PURPOSES ONLY 4 MASTER WARNING SYSTEM ...

Page 112: ...WARNING flasher is pressed C When the RESET button is de pressed D When the TEST button is depressed 5 What action is required to extinguish the RVS NOT READY Annunciator A Put the landing gear handle down B Push the prop levers full forward C Lift the Power Levers into the Reverse Gate D Put the Condition levers into HIGH IDLE 6 After takeoff how are the landing lights extinguished A Automaticall...

Page 113: ......

Page 114: ...EL SYSTEM OPERATION 5 8 Firewall Shutoff Valves 5 10 Crossfeed Operation 5 10 Fuel Drain Purge System 5 12 FUEL GAGING SYSTEM 5 12 Components and Operation 5 13 FUEL DRAINS 5 14 FUEL HANDLING PRACTICES 5 15 Fuel Grades and Additives 5 17 Filling the Tanks 5 18 Draining the Fuel System 5 19 QUESTIONS 5 21 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 5 FUEL SYSTEM ...

Page 115: ......

Page 116: ...Flow Diagram 5 8 5 8 Firewall Shutoff Valve Switches 5 10 5 7 Firewall Shutoff Valve 5 10 5 9 Crossfeed Schematic 5 11 5 11 Fuel Quantity Indication System 5 12 5 10 Fuel Drain Purge System Schematic 5 12 5 12 Fuel Probe 5 13 5 13 Fuel Drains 5 14 5 14 Fuel Drain Locations 5 15 5 15 Fuel Temperature Graph 5 16 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 5 FUEL SYSTEM ...

Page 117: ......

Page 118: ... system The physical layout of the fuel cells and fuel system are described in this section Correct use of the boost pumps transfer pumps crossfeed and firewall shut off valves are discussed Fuel drains their location and type are described with cor rect procedure for taking and inspecting sam ples of fuel Approved fuels and tank filling sequence are included FUEL SYSTEM The Beechcraft King Air fu...

Page 119: ...he fuel system Figure 5 2 in each wing consists of one wing leading edge bladder type tank 40 gallons two outboard wing panel bladder type tanks 23 gallons and 25 gallons one center section bladder type tank 44 gallons and the nacelle tank 61 gallons The total usable fuel capacity of each wing fuel system is 192 gallons The outboard wing tanks supply the center sec tion and nacelle tanks by gravit...

Page 120: ...GE FUEL FILTER FIREWALL AND DRAIN CROSSFEED VALVE TO RIGHT ENGINE NOTE TOTAL USABLE FUEL 384 U S GALLONS 28 OF 44 GALLONS IN THE CENTER TANK WILL NOT GRAVITY FEED TO NACELLE THE TRANSFER PUMP MUST BE USED NOTE A FUEL CAPACITANCE GAUGING SYSTEM UTILIZES A SINGLE FUEL QUANTITY GAUGE FOR EACH WING FUEL SYSTEM THIS GAUGE CAN BE SWITCHED TO DESIGNATE THE AMOUNT OF FUEL IN THE NACELLE TANK OR THE TOTAL ...

Page 121: ...ia tor To identify the failed boost pump mo mentarily place the crossfeed in the CLOSED position The FUEL PRESS annunciator on the side of the failed boost pump will illu minate Place the crossfeed switch in the OPEN position The FUEL PRESS annunci ator will then extinguish In the event of a boost pump failure during any phase of flight the system will begin to crossfeed automatically If the boost...

Page 122: ...10 gallons The nacelle tanks will fill until the fuel reaches the upper trans fer limit and a float switch turns the TRANS FER PUMP off A pressure switch located in the fuel trans fer line will automatically turn off the trans fer pump if a preset pressure is not obtained within approximately 30 seconds after the pump is turned on or if the transfer pump pres sure drops below a preset pressure due...

Page 123: ...ing tanks are empty If the transfer pump fails to operate during flight gravity feed will perform the trans fer When the nacelle tank level drops to ap proximately 150 pounds or approximately 22 gallons the gravity port in the nacelle tank opens and gravity flow from the wing tank starts All wing fuel except 28 gallons from the center section tank will transfer during gravity feed FUEL CAPACITY Th...

Page 124: ...ine from the vent valve in the outboard wing panel fuel tank is routed forward along the leading edge of the wing inboard to the nacelle and aft through a check valve to the heated ram vent Another line tees off from the heated vent line and extends to a recessed or ram scoop vent The heated vent is de scribed in the Anti Ice Section of this man ual A suction relief valve is installed in the line ...

Page 125: ...R C90GTi C90GTx PILOT TRAINING MANUAL 5 8 FOR TRAINING PURPOSES ONLY 5 FUEL SYSTEM FUEL FLOW TRANSMITTER FUEL HEATER TO ENGINE FUEL OUTLET NOZZLES FUEL MANIFOLD DUMP VALVE ENGINE FUEL CONTROL UNIT ENGINE DRIVEN FUEL PUMP FUEL PRESSURE SWITCH FIREWALL SHUTOFF VALVE FUEL PRESSURE ANNUNCIATOR THERMAL RELIEF BYPASS SUBMERGED BOOST PUMP AND DRAIN RAM SCOOP VENT SIPHON BREAK LINE HEATED VENT TRANSFER WA...

Page 126: ... heater which uti lizes heat from the engine oil to warm the fuel The fuel is then routed to the fuel con trol unit that monitors the flow of fuel to the engine fuel nozzles A heater boot is also installed on the governor control line of each engine Each air line heater is protected by a 7 5 ampere push pull circuit breaker mounted in the circuit breaker panel beside the copilot The heaters are co...

Page 127: ...rator bus This source of power is available only when the battery and or generator switches are on The only pilot action nec essary to ensure main fuel system operation is to have the firewall shutoff valves in the OPEN position CROSSFEED OPERATION Crossfeeding fuel is authorized only in the event of engine failure or electric boost pump failure Each nacelle tank is connected to the engine in the ...

Page 128: ... pressure In some instances the pilot may elect to continue the flight with the re maining boost pump and the crossfeed sys tem in operation When the crossfeed switch on the fuel con trol panel is actuated power is drawn from a 5 ampere circuit breaker on the fuel con trol panel to the solenoid that opens the crossfeed valve The crossfeed is also powered through the hot batter y b us through a 5 a...

Page 129: ...d lines through the nozzles and into the combustion cham ber As the fuel is burned a momentary surge in Nl gas generator rpm should be observed The entire operation is automatic and requires no input from the crew FUEL GAGING SYSTEM The airplane is equipped with a capaci tance type fuel quantity indication system Figure 5 11 It automatically compen KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 5 12...

Page 130: ...e center section fuel cell When the fuel selector switch is left in its TOTAL position power is supplied from a 5 ampere circuit breaker on the fuel panel through the fuel quantity indica tor to all of the capacitance probes in the fuel system When the fuel selector switch is placed in the NACELLE position power is then supplied through the fuel quantity indicator to the capacitance probe in the n...

Page 131: ...o not turn the draining tool Turning or twisting of the draining tool will unseat the O ring seal and cause a leak The flush valve attached to the base of the fuel strainer can be opened or closed with a coin a screw driver or a fuel drain tool mak ing it possible to drain fuel from the fuel strainer for preflight check Since jet fuel and water are of similar densities water does not settle out of...

Page 132: ... water cannot be filtered from the fuel by micronic type filters but can be re leased by lowering the fuel temperature which will occur in flight For example a kerosene fuel may contain 65 ppm 8 fluid ounces per 1000 gallons of dissolved water at 80 F When the fuel temperature is low ered to 15 F only about 25 ppm will remain in solution The difference of 40 ppm will have been released as supercoo...

Page 133: ...e required is 38 degrees Celsius If the plot should indicate that oil temperature versus Outside Air Temperature is such that ice formation could occur during takeoff or in flight anti icing additive must be mixed with the fuel The King Air maintains a constant oil tem perature however this temperature varies from one aircraft to another For most air craft the oil temperature will be between 50 an...

Page 134: ... gas is an emergency fuel The 150 hours maximum operation on avi ation gasoline per a Time Between Overhaul should be observed 6 Use only clean fuel servicing equipment 7 After refueling allow a settling period of at least four hours whenever possi ble then drain a small amount of fuel from each drain Remove spilled fuel from the ramp area immediately to prevent the contaminated surface from caus ...

Page 135: ...the corresponding designations established by the American Petroleum Institute APT and the American Society of Testing Material ASTM The brand names are listed for ready reference and are not specifically rec ommended by Beech Aircraft Corporation Any product conforming to the recom mended specification may be used FILLING THE TANKS When filling the aircraft fuel tanks always observe the following...

Page 136: ...e center section trans fer pump drains into suitable containers Fuel may also by pumped out of the tanks utilizing an external pump and suction hoses inserted into the f iller openings For the fastest means of draining the system see the procedures in the Beechcraft King Air 90 Series Maintenance Manual KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 5 19 FOR TRAINING PURPOSES ONLY 5 FUEL SYSTEM ...

Page 137: ...INTENTIONALLY LEFT BLANK KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 5 20 FOR TRAINING PURPOSES ONLY 5 FUEL SYSTEM ...

Page 138: ... D Boost pumps only 6 When is crossfeed use authorized A When a fuel imbalance occurs due to improper fueling B For climbs above 8 000 feet when aviation gas is used C When the transfer pump is inoperative D With one engine inoperative or with a boost pump failure 7 Which of the following limitations applies to operation with aviation gas A A maximum altitude of 8 000 feet with both boost pumps in...

Page 139: ......

Page 140: ...6 AUXILIARY POWER SYSTEM CHAPTER 6 AUXILIARY POWER SYSTEM The information normally contained in this chapter is not applicable to this particular aircraft ...

Page 141: ......

Page 142: ...ine Stations 7 8 Engine Modular Concept 7 8 Compressor Bleed Valve 7 9 Igniters 7 10 Accessory Section 7 10 Lubrication System 7 12 Engine Fuel System 7 16 Fuel Control Unit 7 17 Fuel Pressure Indicators 7 19 Fuel Flow Indicators 7 19 Anti icing Fuel Additive 7 20 Engine Power Control 7 20 ITT and Torquemeters 7 21 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 POWERPLAN...

Page 143: ...er System 7 26 Hartzell Four Blade Propellers 7 28 Blade Angle 7 28 Primary Governor 7 29 Low Pitch Stop 7 33 Ground Fine and Reverse Control 7 35 Overspeed Governor 7 37 Fuel Topping Governor 7 39 Power Levers 7 39 Autofeather System 7 40 Propeller Synchrophaser System 7 42 Propeller Synchroscope 7 44 QUESTIONS 7 45 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 ii FOR TRAINING PURPOSES ONLY 7 PO...

Page 144: ... 9 7 11 Engine Start and Ignition Switches 7 10 7 12 Typical PT6A Engine 7 11 7 13 Engine Lubrications Diagram 7 13 7 14 Engine Oil Dipstick 7 14 7 15 Magnetic Chip Detector 7 15 7 16 Simplified Fuel System Diagram 7 16 7 17 Simplified Fuel Control System 7 18 7 18 Fuel Pressure Annunciators 7 19 7 19 Fuel Flow Indicator 7 19 7 20 Control Levers 7 20 7 21 Engine Indicating System 7 21 7 22 Control...

Page 145: ...32 7 32 Low Pitch Stop Diagram 7 33 7 33 Beta Range and Reverse Diagram 7 36 7 34 Overspeed Governor Diagram 7 38 7 35 Power Levers 7 39 7 36 Propeller Control Levers 7 40 7 37 Autofeather System Diagram Left Engine Failed and Feathering 7 41 7 38 Autofeather System Diagram Armed 7 41 7 39 Autofeather Test Diagram 7 42 7 40 Propeller Synchrophaser 7 43 7 41 Propeller Synchroscope 7 44 KING AIR C90...

Page 146: ...ems extends engine life and ensures safety This chapter also describes the propeller system and its operational limits and preflight checks GENERAL The Engines section of this chapter presents a description and discussion of the Pratt and Whitney PT6A turboprop engines The en gines used on these airplanes will be de scribed in suff icient detail for flight crewmembers to understand normal opera ti...

Page 147: ...r The engines are equipped with conventional four blade full feathering reversing vari able pitch propellers mounted on the out put shaft of the engine reduction gearbox The propeller pitch and speed are controlled by engine oil pressure through single ac tion engine driven propeller governors The propellers will feather automatically when the engines are shut down on the ground and will unfeather...

Page 148: ...nderstand the operation of the PT6A series engines there are several basic terms you should know N1 or NG Gas generator rpm is per cent of turbine speed N2 or Np Propeller rpm NF Power turbine rpm not indicated on engine instruments P3 Air pressure at station three the source of bleed air ITT or T5 Interstage Turbine Tempera ture in degrees of temperature at sta tion 5 Review and remember these te...

Page 149: ...er consisting of a single power turbine which drives the power section and propeller The power turbine section has no physical connection to the compressor turbine at all These tur bines are mounted on separate shafts and are driven in opposite directions by the gas flow across them The term reverse flow refers to airflow through the engine Inlet air enters the compressor at the aft end of the eng...

Page 150: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 5 FOR TRAINING PURPOSES ONLY 7 POWERPLANT Figure 7 5 Engine Stations Figure 7 6 Engine Orientation Figure 7 4 Engine Cutaway ...

Page 151: ...nes to the annulus surrounding the combustion chamber liner The combustion chamber liner has varying size perforations which allow entry of com pressor delivery air Approximately 25 of the air mixes with fuel to support combus tion The remaining 75 centers the flame in the combustion chamber and provides in ternal cooling for the engine As it enters the combustion area and mixes with fuel the flow...

Page 152: ...ases impinge on the turbine blades at the correct angle with minimum loss of energy The expanding gases are then directed forward to drive the power turbine section The single stage power turbine consisting of an inlet guide vane and turbine drives the pro peller shaft through a reduction gearbox The compressor and power turbines are lo cated in the approximate center of the en gine with their res...

Page 153: ...taken off the engine after the centrifu gal compressor stage and prior to entering the combustion chamber This air commonly referred to as P3 air is used for cabin heat pressurization and the pneumatic system ENGINE MODULAR CONCEPT With the modular free turbine design the engine is basically divided into two mod ules a gas generator section and a power sec tion Figure 7 9 The gas generator section...

Page 154: ...10 This pressure relief helps prevent compressor stall of the centrifugal stage The compressor bleed valve is a pneumatic piston which references the pressure dif ferential between the axial and centrifugal stages Looking forward the valve is located at the 6 o clock position The function of this valve is to prevent compressor stalls and surges in the low N1 rpm range 75 to 80 N1 At low N1 rpm the...

Page 155: ...ches should be moved to the ARM position just prior to takeoff If engine torque falls below ap proximately 400 ft lb the igniter will au tomatically energize attempting to restart the engine The IGNITION ON annunciator will be illuminated The spark ignition provides the engine with an ignition system capable of quick light ups over a wide temperature range The system consists of an airframe mounte...

Page 156: ...G PURPOSES ONLY 7 POWERPLANT FUEL PUMP FCU TACHOMETER GENERATOR NG OIL SCAVENGE PUMPS AND FUEL BOOST PUMP OPTIONAL ACCESSORY DRIVES STARTER GENERATOR PROPELLER OVERSPEED GOVERNOR PROPELLER GOVERNOR TACHOMETER GENERATOR NF AFT FRONT Figure 7 12 Typical PT6A Engine ...

Page 157: ...quarts below full when the oil level is normal Do not overfill When adding oil between oil changes do not mix types or brands of oil due to the possibility of chemical incom patibility and loss of lubricating qualities A placard inside the engine cover shows the brand and type of oil used in that particular engine Although the preflight checklist calls for checking the oil level which is re quired...

Page 158: ...90GTx PILOT TRAINING MANUAL 7 13 FOR TRAINING PURPOSES ONLY 7 POWERPLANT LEGEND ENG DIVEN PUMP PRESS HI TEMP SCAVENGE OIL STORAGE OIL INLET AIR BYPASS OIL VENT PRESSURE DRAIN OIL Figure 7 13 Engine Lubrications Diagram ...

Page 159: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 14 FOR TRAINING PURPOSES ONLY 7 POWERPLANT Figure 7 14 Engine Oil Dipstick ...

Page 160: ...ator indicates the presence of ferrous particles in the pro peller gearbox Illumination of the L or R CHIP DETECT annunciator requires the pilot to monitor the engine instruments If abnormal indications are observed the en gine should be secured at the pilots discre tion If left unsecured serious damage to the internal engine components may occur KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 15 F...

Page 161: ...l to maintain a desired fuel temperature at the fuel pump inlet to prevent icing at the pump filter This is done with automatic temperature sensors and re quires no action by the pilot Fuel enters the engine fuel system through the oil to fuel heat exchanger and then flows into the high pressure engine driven fuel pump and on into the fuel control unit FCU The high pressure fuel pump is an engine ...

Page 162: ...ncrease in ITT when the secondary fuel noz zles are activated During engine shutdown any fuel left in the manifold is forced out through the fuel noz zles and into the combustion chamber by purge tank pressure As the fuel is burned a momentary increase in N1 rpm may be ob served The entire operation is automatic and requires no input from the crew FUEL CONTROL UNIT The fuel control unit Figure 7 1...

Page 163: ...OP TO FUEL TOPPING GOVERNOR PURGE VALVE MINIMUM PRESSURIZING VALVE TO GRAVITY FEED LINE FUEL PURGE P 3 FLOW DIVIDER AND DUMP VALVE FUEL CUTOFF VALVE FUEL SUPPLY P 3 INLET N 1 GOVERNOR ENGINE DRIVEN FUEL PUMP LEGEND VENT P 3 AIR PUMP PRESSURE FUEL INSIDE TANK EMPTY Figure 7 17 Simplified Fuel Control System ...

Page 164: ...st pump decreases below about 10 psi If the crossfeed switch is in the AUTO position the automatic crossfeed feature will open the valve extinguishing the annunciator In the event of an engine driven fuel pump high pressure failure the engine will flame out Engine operation with the FUEL PRESS light on is limited to ten hours between overhaul or re placement of the engine driven high pressure fuel...

Page 165: ... mixed with the fuel at refueling to ensure safe operation Refer to the King Air Maintenance Manual for procedures to fol low when blending anti icing additive with the airplane fuel Anti icing additive conforming to Specifi cation MIL 1 27686 is the only approved fuel additive ENGINE POWER CONTROL The propeller lever adjusts the propeller governor to the desired propeller speed Figure 7 20 The pr...

Page 166: ...two seconds The engines will be damaged if lim iting temperatures indicated on the ITT gage are exceeded TORQUEMETER The torquemeter Figure 7 21 which is in dicated in ft lb constantly measures rota tional force applied to the propeller shaft The maximum permissible sustained torque is 1 520 ft lb the red radial on the instru ment A transient torque limit of 1 626 ft lb is time limited to twenty s...

Page 167: ... are lifted over the IDLE detent and pulled back they control engine power through the GROUND FINE and RE VERSE ranges Condition Levers The condition levers have multiple posi tions FUEL CUTOFF and LO IDLE through HI IDLE Figure 7 22 At the FUEL CUTOFF position fuel flow to its re spective engine is cut off At LO IDLE engine gas generator speed N1 is a minimum of 58 at HI IDLE it is 70 The levers ...

Page 168: ...nd C90GTx The Engine Operating Limits chart gives the major operating limits The Power Plant Instrument Markings chart lists the mini mum normal and maximum limits During engine start temperature is the most critical limit The ITT starting limit of 1 090 C represented on the ITT gage by a red line is limited to two seconds During any start if the indicator needle approaches the limit the start sho...

Page 169: ...HE MINIMUM POWER REQURIED TO SUSTAIN FLIGHT 3 FOR INCREASED SERVICE LIFE OF ENGINE OIL AN OIL TEMPERATURE OF BETWEEN 74 TO 80 C IS RECOMMENDED A MINIMUM OIL TEMPERATURE OF 55 C IS RECOMMENDED FOR FUEL HEATER OPERATION AT TAKE OFF POWER 4 THESE VALUES ARE TIME LIMITED TO TWO SECONDS 5 HIGH ITT AT GROUND IDLE MAY BE CORRECTED BY REDUCING ACCESSORY LOAD AND OR INCREASING N1 RPM 6 CRUISE TORQUE VALUES...

Page 170: ...S The engine starters are time limited during the starting cycle if for any reason multiple starts are required in quick sequence The starter is limited to 40 seconds ON then 60 seconds OFF for cooling before the next se quence of 40 seconds ON 60 seconds OFF After the third cycle of 40 seconds ON the starter must stay OFF for 30 minutes If these limits are not observed overheating may damage the ...

Page 171: ...n reversing and feathering are included in this discussion PROPELLER SYSTEM This section on the operation and testing of the propeller system on the Beechcraft King Air C90GTi and C90GTx is directed at in creasing the pilot s understanding of the the ory of operation of a constant speed full feathering reversing propeller and helping him better understand the propeller system checks conducted as o...

Page 172: ...ler governor boosts engine oil pressure to move the propeller to low pitch and reverse The propeller feathers after engine shutdown Propeller tiedown boots Figure 7 26 are provided to prevent windmilling at zero oil pressure when the airplane is parked Low pitch propeller position is determined by the primary low pitch stop which is a me chanically actuated hydraulic stop Blade an gles are control...

Page 173: ...ower tip speeds and thus generate less noise create less air frame vibration and provide generous pro peller tip to ground clearance Dynamic vibration absorbers mounted inside the cock pit and cabin a total of 26 absorbers are used in conjunction with the four blade propellers to reduce noise and vibration even more BLADE ANGLE Blade angle is the angle between the chord of the propeller and the pr...

Page 174: ... sense this overspeed condition and increases blade angle to a higher pitch The higher pitch increases the blade s angle of attack slowing it back to 1 900 rpm or onspeed Likewise if the airplane moves from cruise to climb airspeeds without a power change the propeller rpm tends to decrease but the governor responds to this underspeed con dition by decreasing blade angle to a lower pitch and the r...

Page 175: ...rings and centrifugal coun terweights are trying to send the propeller into the feathered position Propeller con trol is a balancing act of opposing forces A transfer gland is located on the propeller shaft This transfer gland allows the oil to enter and exit the propeller dome area Thus the transfer gland is always replenishing the oils supply to the propeller pitch mech anism with fresh warm oil...

Page 176: ...SSURE TRANSFER GLAND BETA VALVE TO CASE PILOT VALVE PROP LEVER PRIMARY PROP GOVERNOR 1600 TO 1900 RPM Figure 7 29 Propeller Onspeed Diagram OIL GOVERNOR PUMP REVERSE LEVER OVERSPEED GOVERNOR 1976 RPM NORMAL TO CASE LOW PITCH HIGH OIL PRESSURE TRANSFER GLAND BETA VALVE TO CASE PILOT VALVE PROP LEVER PRIMARY PROP GOVERNOR 1600 TO 1900 RPM OVERSPEED AUTOFEATHER SOLENOID N C Figure 7 30 Propeller Over...

Page 177: ... to its equilibrium or onspeed position such as torque interstage turbine tempera ture compressor speed and fuel flow cor recting the held constant by changing the propeller blade angles The cockpit pro peller lever adjusts where the equilibrium or onspeed condition will occur The pilot can select any constant propeller rpm from 1 600 to 1 900 rpm however 1 900 rpm should be used for all operation...

Page 178: ...r the extreme travel in the low pitch direction is past 0 into reverse or negative blade angles Figure 7 32 Consequently the low pitch stop on this propeller must be designed in such a way that it can be repositioned when re versing is desired The low pitch stop is created by mechanical linkage sensing the blade angle The link age causes a valve to close which stops the flow of oil pressure coming...

Page 179: ...prevents the propeller blades from reducing the airflow over the empennage of the aircraft The low pitch stop uses a mechanical link age to hydraulically control propeller blade angle As the propeller blades reduce angle through approximately 20 of pitch the flange mounted on the propeller dome con tacts the nuts located on the rods mounted on the slip ring The propeller dome moves the slip ring f...

Page 180: ...he low pitch stop can be adjusted to allow access to the Ground Fine and Reverse ranges on the ground The hydraulic low pitch stop can be reset to allow the propeller to operate in the Ground Fine and Reverse ranges while the aircraft is on the ground and the engines are operating When the power levers are lifted up and over the idle detent into the Ground Fine range the Beta valve is repositioned...

Page 181: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 36 FOR TRAINING PURPOSES ONLY 7 POWERPLANT Figure 7 33 Beta Range and Reverse Diagram ...

Page 182: ...e reversing system OVERSPEED GOVERNOR The overspeed governor provides protection against excessive propeller speed in the event of primary governor malfunction Since the PT6 s propeller is driven by a free turbine independent of the engine s over speed could occur if the primary governor were to fail The operating point of the overspeed gov ernor is set at 1 976 rpm If an overspeed ing propeller s...

Page 183: ...GOVERNOR PUMP REVERSE LEVER HYDRAULIC OVERSPEED GOVERNOR APPROX 1670 TO 1800 RPM IN TEST MODE 1976 RPM NORMAL TO CASE AUTOFEATHER SOLENOID N C LOW PITCH HIGH OIL PRESSURE TRANSFER GLAND BETA VALVE TO CASE PILOT VALVE PROP LEVER PRIMARY PROP GOVERNOR FAILED Figure 7 34 Overspeed Governor Diagram ...

Page 184: ...e to maximum thrust and in the Ground Fine and Reverse ranges from idle to maximum reverse Two gates in the power lever quadrant aft of the IDLE posi tion prevent inadvertent movement of the power lever into the GROUND FINE or RE VERSE ranges The pilot must lift the power levers up and over the first gate to select GROUND FINE and up and over the sec ond gate to select REVERSE The function of the ...

Page 185: ...hase occurs when both power levers are advanced above 90 N1 at which time a green AFX is displayed in the ITT TORQUE indicators on the MFD and green annunciators placarded L and R AUTOFEATHER on the Caution Advisory annunciator panel will illuminate indicating the system is armed Figure 7 38 The system will remain inoperative as long as either power lever is retarded below 90 N1 position The syste...

Page 186: ...WER LEVER SWITCHES C B RIGHT ARMING RELAY LEGEND NO 1 GENERATOR NO 2 GENERATOR BATTERY Figure 7 37 Autofeather System Diagram Left Engine Failed and Feathering CLOSED AT HIGH N1 OVER 400 FT LBS OVER 200 FT LBS LESS THAN 200 FT LBS TORQUE SWITCHES LESS THAN 400 FT LBS DUMP VALVE AUTOFEATHER LIGHTS N C DUMP VALVE N C ARMING RELAY TEST AUTO FEATHER ARM OFF LEFT POWER LEVER SWITCHES C B RIGHT ARMING R...

Page 187: ...ce rpm of either pro peller below the datum selected by the pro peller control lever Therefore there is no indicating annunciator light associated with the Type II system To prevent either propeller from losing ex cessive rpm if the other propeller is feath ered while the synchrophaser is on the synchrophaser has a limited range of au thority from the manual governor setting In no case will the rp...

Page 188: ...tings selected by the pilot To operate the synchrophaser system synchronize the pro pellers manually or establish a maximum of 10 rpm difference between the engines then turn the synchrophaser on The system may be on for takeoff and landing To change rpm with the system on adjust both propeller controls at the same time If the synchrophaser is on but does not adjust the prop r pm to match the syst...

Page 189: ...de pending on which propeller is spinning faster If the right propeller rpm is greater than the left the boxes slide towards the right With the left propeller rpm greater than the right the boxes slide towards the left This movement however stops when the propellers are synchronized or when an engine has failed KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 7 44 FOR TRAINING PURPOSES ONLY 7 POWERPLA...

Page 190: ...r landing B Reduce torque to 500 foot pounds for the remainder of the flight C Monitor the engine instruments and if normal no action is required D Shut the engine down and land as soon as practical 5 During ground operation at LO IDLE you note that ITT is exceeding 685 C Which of the following actions would you consider best to reduce ITT A Move the propeller control lever to the low rpm position...

Page 191: ...irement is to A Continue to fly the airplane and allow the propeller to feather and stop B Move the power lever to idle C Move the condition lever to cutoff D Reduce electrical loads 9 Which of the following is the most accurate definition of Engine Torque Readout A Power developed by the gas generator B Thrust supplied by the propeller C Ratio of compressor inlet to exhaust outlet D Power deliver...

Page 192: ...ODUCTION 8 1 GENERAL 8 1 FIRE DETECTION SYSTEM 8 1 Fire Detection Test System 8 3 FIRE EXTINGUISHING SYSTEM 8 3 Fire Extinguisher Test System 8 5 QUESTIONS 8 7 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 8 FIRE PROTECTION ...

Page 193: ......

Page 194: ... Figure Title Page 8 1 Fire Detection System 8 2 8 2 Fire Extinguishing System 8 4 8 3 Fire Extinguisher Cylinder Pressure Gage 8 5 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 8 FIRE PROTECTION ...

Page 195: ......

Page 196: ...ussion of the air plane f ire protection system and components The location and purpose of switches and indicators are described FIRE DETECTION SYSTEM The fire detection system Figure 8 1 is designed to provide immediate warning in the event of fire in either engine compart ment The detection system is operable whenever the generator buses are active KING AIR C90GTi C90GTx PILOT TRAINING MANUAL CH...

Page 197: ... ONLY 8 FIRE PROTECTION LOCATION OF ADDITIONAL FLAME DETECTOR FOR CAA MODIFICATION LOCATION OF ADDITIONAL FLAME DETECTOR FOR CAA MODIFICATION FLAME DETECTORS FLAME DETECTORS TEST SWITCH FIRE DET AND FIRE EXT 1 2 3 OFF L ENG FIRE R ENG FIRE Figure 8 1 Fire Detection System ...

Page 198: ...he test switch will include LEFT EXT RIGHT positions The three test positions for the fire detector system are located on the right side of the switch When the switch is rotated from OFF down to any one of these three positions the output voltage of a corresponding flame de tector in each engine compartment is increased to a level sufficient to signal the amplifier that a fire is present The follo...

Page 199: ...Ti C90GTx PILOT TRAINING MANUAL 8 4 FOR TRAINING PURPOSES ONLY 8 FIRE PROTECTION TEST SWITCH FIRE DET AND FIRE EXT 1 2 3 LEFT EXT RIGHT OFF PRESSURE GAGE FIRE EXTINGUSHER BOTTLE Figure 8 2 Fire Extinguishing System ...

Page 200: ...t will illuminate and remain illuminated regardless of battery switch position until the pyrotechnic car tridge has been replaced FIRE EXTINGUISHER TEST SYSTEM The fire extinguisher system test functions incor porated in the rotary TEST SWITCH FIRE DET FIRE EXT test the circuitry of the fire extinguisher system During preflight the pilot should rotate the TEST SWITCH to each of the two positions R...

Page 201: ...INTENTIONALLY LEFT BLANK KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 8 6 FOR TRAINING PURPOSES ONLY 8 FIRE PROTECTION ...

Page 202: ...cal signal simi lar to the one that the detectors send to the warning annunciating system B Heats up an infrared source by each detector C Merely checks the annunciator system operation D Directs a small amount of bleed air to heat the detectors 4 In the testing mode if the TEST SWITCH is in either LEFT or RIGHT EXT position the green OK light fails to illuminate but the amber D does illuminate wh...

Page 203: ......

Page 204: ...ON 9 1 DESCRIPTION 9 1 ENGINE BLEED AIR PNEUMATIC SYSTEM 9 1 Pneumatic Air Source 9 3 Vacuum Air Source 9 3 Cabin Door Seal 9 4 SURFACE DEICE SYSTEM 9 4 QUESTIONS 9 7 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 9 PNEUMATICS ...

Page 205: ......

Page 206: ...iagram 9 2 9 2 Pneumatic Pressure Gage 9 3 9 3 Gyro Suction Gage 9 4 9 4 Surface Deice Boot Installation 9 4 9 5 Surface Deice System Diagram 9 5 9 6 Surface Deice Controls 9 6 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 9 PNEUMATICS ...

Page 207: ......

Page 208: ...stributed and controlled for these various uses This section identifies these systems and covers the pneumatic manifold and controls in detail DESCRIPTION The Pneumatic and Vacuum Systems sec tion of the training manual presents a de scription and discussion of pneumatic and vacuum systems The sources for pneumatic air vacuum and acceptable gage readings are discussed KING AIR C90GTi C90GTx PILOT ...

Page 209: ...ULATOR PRESSURE SWITCH EJECTOR DEICE BOOTS PRESSURIZATION CONTROLLER OUTFLOW SAFETY VALVES RIGHT ENGINE LEFT ENGINE CHECK VALVE CHECK VALVE LANDING GEAR HYDRAULIC FILL CAN AIRSTAIR DOOR SEAL LINE EMERGENCY EXIT SEAL LINE RIGHT SQUAT SWITCH OPEN IN FLIGHT N C 13 PSI PRESSURE REGULATOR VACUUM REGULATOR LEFT SQUAT SWITCH CLOSED ON GROUND N C VALVES N C L SERVO R SERVO RUDDER BOOST SYSTEM 50 PSID DEIC...

Page 210: ...m the manifold the bleed air passes through an 18 psi regulator which incorporates a relief valve set to operate at 21 psi in case of regulator failure This reg ulated bleed air is used to supply pneumatic pressure to inflate the surface deicers escape hatch and door seals and to provide flow and pressure for the vacuum ejector Bleed air is extracted from the P3 tap of the engine at a temperature ...

Page 211: ...open valve that is controlled by the left landing gear safety switch When the airplane lifts off the landing gear switch opens the valve to the door and hatch seals and the seals inflate SURFACE DEICE SYSTEM The leading edges of the wings and horizon tal stabilizer are protected against an accu mulation of ice buildup However the winglets on the C90GTx are not protected Figure 9 4 Inflatable boots...

Page 212: ...ce system removes ice ac cumulations from the leading edges of the wings and stabilizers Ice is removed by al ternately inflating and deflating the deice boots Figure 9 5 Pressure regulated bleed air from the engines supplies pressure to in KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 9 5 FOR TRAINING PURPOSES ONLY 9 PNEUMATICS Figure 9 5 Surface Deice System Diagram ...

Page 213: ...til the switch is released The switch will return to the OFF position when released After the cycle the boots will remain in the vacuum hold down condition until again actuated by the switch Electrical power to the boot system is re quired for the control valve to inflate the boots in either single cycle or manual op eration With a loss of this power the vac uum will hold them tightly against the ...

Page 214: ...erant compressor D Safety dump valve 3 A bleed air leak could result in a de crease in __________ and an increase in __________ A Engine torque N1 B Engine rpm ITT C Engine temperature N1 D Engine torque ITT 4 What is the maximum operating pres sure limit of the pneumatic system A 12 psi B 18 psi C 6 psi D 21 psi 5 From sea level to 15 000 feet MSL what is the normal vacuum range of the vacuum sys...

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Page 216: ... Anti ice System 10 6 Windshield Wipers 10 10 Engine Anti ice System 10 10 Anti ice Controls 10 12 Engine Auto Ignition System 10 13 Engine Air Inlet Lip Heat 10 13 Pitot Mast Heat 10 14 Fuel Heat 10 15 Stall Warning Anti ice 10 16 Wing Ice Lights 10 17 Precautions During Icing Conditions 10 17 QUESTIONS 10 19 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 ICE AND RAIN ...

Page 217: ......

Page 218: ... Diagram High Heat 10 9 10 9 Windshield Wipers 10 10 10 10 Inertial Separator in Retract Position 10 11 10 11 Inertial Separator in Extend Position 10 11 10 12 Anti ice Controls 10 12 10 13 Caution and Advisory Annunciators 10 12 10 14 Engine Auto Ignition Switches 10 13 10 15 Engine Air Inlet Lip Heat 10 13 10 16 Pitot Mast and Heat Controls 10 14 10 17 Fuel System Anti ice 10 15 10 18 Stall Warn...

Page 219: ......

Page 220: ... heavy rain conditions along with their controls Procedures in case of mal function in any system are included This also includes information concerning pre flight deicing and defrosting The Beechcraft King Air C90GTi and C90GTx are FAA approved for flight in known icing conditions when the required equipment is installed and operational Figure 10 1 The Required Equipment for Various Conditions of...

Page 221: ...T ICE AND RAIN PROTECTION 1 ALTERNATE STATIC AIR SYSTEM 0 0 1 1 1 2 ENGINE AUTO IGNITION SYSTEM AND ANNUNCIATOR 2 2 2 2 2 3 ENGINE ANTI ICE SYSTEM AND ANNUNCIATORS 2 2 2 2 2 4 HEATED FUEL VENT 0 0 2 2 2 5 HEATED WINDSHIELD LEFT 0 0 0 0 1 6 PITOT HEAT 0 0 2 2 2 7 PNEUMATIC PRESSURE INDICATOR 0 0 1 1 1 8 STALL WARNING HEATER 0 0 0 0 1 9 SURFACE DEICER SYSTEM 0 0 0 0 1 10 PROPELLER DEICER SYSTEM 0 0 ...

Page 222: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 3 FOR TRAINING PURPOSES ONLY 10 ICE AND RAIN PROTECTION Figure 10 2 Ice and Rain Protection Controls ...

Page 223: ...trothermal boots on each blade that automatically cycle to prevent the formation of ice A heating element in both pitot masts pre vents the pitot openings from becoming clogged with ice The heating elements are connected to the airplane electrical system through two 5 ampere circuit breaker switches SURFACE DEICE SYSTEM The leading edges of the wings and tail stabi lizers are protected against ice...

Page 224: ...eceiving power from the CENTER bus supplies the electrical operation of both boot systems The boots operate most ef fectively when approximately 1 2 to 1 inch of ice has formed Very thin ice cracks and can cling to the boots and or move aft onto unprotected areas When operated manu ally the boots cannot be left inflated longer than necessary to eliminate the ice as a new layer of ice can begin to ...

Page 225: ...ys ical layers Figure 10 4 The inner layer is a thick panel of glass that acts as the struc tural member The middle layer is a polyvinyl sheet which carries the fine wire heating grids The outer layer is a protective layer of glass bonded to the first two layers The out side of the windshield is treated with a static discharge film called a NESA coating The windshields are protected against icing ...

Page 226: ...ch windshield and a temperature controller in each wind shield circuit The temperature controllers operate between 90 and 110ºF to maintain the desired mean temperature of the wind shield heating surfaces KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 7 FOR TRAINING PURPOSES ONLY 10 ICE AND RAIN PROTECTION TEMPERATURE CONTROLLER NORMAL 360 IN2 AT 2 4 WATTS IN2 HIGH 265 IN2 AT 4 5 WATTS IN2 5A HIG...

Page 227: ...at 90 to 110ºF In this mode however the controller will energize the high heat relay switch which applies the electrical heat to a more concentrated but more essential viewing area of the wind shield In high approximately two thirds of the windshield is heated at the outboard por tion Figure 10 8 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 8 FOR TRAINING PURPOSES ONLY 10 ICE AND RAIN PROTECTIO...

Page 228: ... may cause erratic operation of the magnetic compass because of the electrical field created by the heating elements In the event of windshield icing during sustained icing conditions it may be necessary to reduce the airspeed in order to keep the wind shield ice free CAUTION KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 9 FOR TRAINING PURPOSES ONLY 10 ICE AND RAIN PROTECTION TEMPERATURE CONTROL...

Page 229: ...engine inlet screen A movable vane and a bypass door are closed retracted for normal flying conditions Figure 10 10 At temperatures above 5ºC the ice vane and door should be in the retract position as ice formation is unlikely When in icing conditions with the ice vane in the extend position Figure 10 11 the ice vane is positioned to create a venturi ef fect and introduces a sudden turn into the e...

Page 230: ...G AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 11 FOR TRAINING PURPOSES ONLY 10 ICE AND RAIN PROTECTION Figure 10 10 Inertial Separator in Retract Position Figure 10 11 Inertial Separator in Extend Position ...

Page 231: ... selection of either the MAIN or STANDBY actuator motor The main and standby actuators have different circuitry but share the same torque tube drive system The vanes have only two positions there are no intermediate positions The system is monitored by L and R ENG ANTI ICE green and L and R ENG ICE FAIL yellow annunciators Figure 10 13 Illumination of the L and R ENG ANTI ICE annunciators indicate...

Page 232: ... hundred foot pounds electrical power is provided to energize the engine igniters As this happens the green IGNITION ON annunciator on the panel will illuminate in dicating that the ignition system is ener gized During ground operation the system should be turned off to prolong the life of the igniter units ENGINE AIR INLET LIP HEAT The lip around each air inlet is heated by hot exhaust gases to p...

Page 233: ...unciators indicates that pitot mast heat is inoperative The annunciators will also il luminate anytime the PITOT switches are in the OFF position The pitot heat system should not be oper ated on the ground except for testing or for short intervals to remove snow or ice from the mast Pitot heat should be turned on for takeoff and can be left on in flight during icing conditions or whenever icing co...

Page 234: ... in each wing The fuel vent heat is operated by left and right switches located in the ICE PRO TECTION group on the pilot s right subpanel These switches should be turned on when ever ice is anticipated or encountered KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 10 15 FOR TRAINING PURPOSES ONLY 10 ICE AND RAIN PROTECTION PNEUMATIC LINE FUEL CONTROL UNIT TO FUEL TOPPING GOVERNOR OIL OUT VALVE SLEEV...

Page 235: ... to ensure against freeze up during icing conditions The stall warning plate is activated by a two position switch located just to the right of the surface deicer cycle switch on the pilot s right subpanel The down position is OFF and the up position is ON The vane is heated through the battery switch so it is heated when the battery switch is ON A safety switch on the left landing gear lim its th...

Page 236: ...that matters it is the texture A slightly ir regular surface can substantially decrease proper airflow over the wings and stabiliz ers Never underestimate the damaging ef fects of frost All frost should be removed from the leading edges of the wings sta bilons stabilizers and propellers before the airplane is moved Control surfaces hinges the windshield pitot masts fuel tank caps and vents should ...

Page 237: ...taking off During takeoff more runway is needed to achieve necessary take off speed while landing roll is longer be cause of reduced braking effectiveness Only the surface deicers are true deicers The rest are really anti icers and should be used to prevent the formation of ice not melt ice already present Accumulated ice on even the best equipped airplane will de grade its performance and ruin at...

Page 238: ...erheat and deform C Can develop a puncture D Add dangerous drag 5 If the aircraft is flying through icing conditions what is the minimum speed necessary to keep the bottom of the wing leading edges ice free A 100 knots B 120 knots C 140 knots D 160 knots 6 The windshield temperature is regu lated and affected by A Cockpit ambient temperature B Outside ambient temperature C Heat sensors that sense ...

Page 239: ...le cooler 11 Just prior to brake release with the OAT 5 C 41 F or lower and visible moisture encountered what action must be taken A The inertial separator ice vanes must be extended immediately B The inertial separator ice vanes must be extended just after lift off is achieved C The inertial separator ice vanes must be extended only after 500 feet is reached D The inertial separate ice vane must ...

Page 240: ...NTILATION 11 5 BLEED AIR HEATING SYSTEM 11 6 ELECTRIC HEAT 11 9 COOLING SYSTEM 11 10 ENVIRONMENTAL CONTROLS 11 11 Automatic Mode Control 11 12 Manual Mode Control 11 13 Bleed Air Control 11 13 Vent Blower Control 11 14 QUESTIONS 11 15 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 11 AIR CONDITIONING ...

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Page 242: ... Eyeball Outlets 11 5 11 12 Cockpit Eyeball Outlets 11 6 11 13 Ambient and Bleed Air Flow Forward of Firewalls 11 6 11 14 Air Conditioning System Control Diagram 11 7 11 15 Mixing Plenum 11 8 11 16 Electric Heater 11 9 11 17 Grid Heating Elements 11 9 11 18 Elec Heat Switch 11 10 11 19 Cooling System Components in Nose 11 10 11 20 Receiver Dryer Sight Gage 11 11 11 21 Cabin Temp Mode Selector Swit...

Page 243: ......

Page 244: ...RIPTION The Environmental System section of the training manual presents a description and discussion of the air conditioning bleed air heating and fresh air systems Each system includes general description prin ciple of operation controls and emer gency procedures KING AIR C90GTi C90GTx PILOT TRAINING MANUAL CHAPTER 11 AIR CONDITIONING 11 1 FOR TRAINING PURPOSES ONLY 11 AIR CONDITIONING ...

Page 245: ... CEILING OUTLET PEDESTAL DEFROST AIR PULL ON VENT BLOWER RAM AIR SCOOP PRESSURIZATION PRESET SOLENOID AMBIENT AIR UNPRESSURIZED RECIRCULATED AIR PRESSURE AIR CONDITIONER COOL AIR BLEED AIR HEATED AIR PRESSURE VESSEL OUTFLOW VALVE SOLENOID SHUTOFF VALVE DRAIN VALVE AT LOW POINT IN OUTFLOW VALVE LINE CEILING OUTLETS FLOOR OUTLET BLEED AIR BYPASS VALVE CELING OUTLET CHECK VALVES WHEEL WELL AIR TO AIR...

Page 246: ... by the electrical system provides cool air to the airplane cabin The ENVIRONMENTAL control section on the copilot s left subpanel Figure 11 2 pro vides for automatic or manual control of the system This section contains all the major controls of the environmental function Bleed air valve switches Vent blower control switch Manual temperature switch for control of the bypass valves in the air to a...

Page 247: ...ization heating and air condi tioning systems operate in conjunction with each other or as separate systems to maintain the desired cabin pressure altitude and cabin air temperature Occupied compartments are pressurized heated or cooled through a com mon ducting arrangement Ventilation can be obtained on demand during nonpressurized flight through a ram air scoop on the left side of the nose Figur...

Page 248: ... ram air flapper door closed During unpressurized flight ram air enters the evaporator plenum through the ram air door when the electromagnet re leases Recirculated cabin air forced into the evaporator plenum by a blower mixes with ram air from outside is ducted around the electric heater and mixing plenum and into the ceiling outlet duct Air ducted to each individual cabin Figure 11 11 or cockpit...

Page 249: ...nding gear safety switch is in the on the ground position the ambient air valve Figure 11 13 in each flow con trol unit is closed Consequently only bleed air is delivered to the environmental bleed air duct when the airplane is on the ground The exclusion of ambient air allows faster cabin warmup during cold weather opera tion In flight the ambient air valve is open when temperature is above 30 F ...

Page 250: ... on the leading edge of the in board wing brings ram air into the heat ex changer to cool the bleed air Depending upon the position of the cabin temperature control bypass valves a greater or lesser volume of the bleed air mixture will be routed through or around the heat exchanger The temperature of the air flow ing through the heat exchanger is lowered as heat is transferred to cooling fins whic...

Page 251: ... the pilot and copilot A mechanically controlled damper in each outlet permits the volume of air flow to be regulated The pilot s damper is controlled by the PILOT AIR see Figure 11 3 knob on the pilot s left subpanel just outboard of the control column The copi lot s damper is controlled by the COPILOT AIR see Figure 11 6 knob on the copilot s right subpanel just outboard of the con trol column T...

Page 252: ...s combine for GROUND MAX HEAT opera tion The maximum output is available dur ing ground operation and only four elements are available during flight The airplane electrical system is protected against an overload by a lockout circuit that prevents use of the electrical heater during operation of the propeller deicers or windshield heat KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 11 9 FOR TRAINING...

Page 253: ...orator Receiver dryer Expansion valve Cabin heat control valve It is routed Figure 11 19 to the condenser coil receiver dryer expansion valve cabin heat control valve and evaporator which are all in the nose of the airplane The rated output of the standard installation in the fuselage nose is 16 000 BTU The evaporator utilizes a solenoid operated hot gas cabin heat control valve to prevent icing A...

Page 254: ... control switch Manual temperature switch for con trol of the bypass valves in the air to air heat exchangers Cabin temperature level control Cabin temperature mode selector switch for selecting automatic heat ing or cooling manual heating or cool ing or off Electric heat control switch Four additional manual controls on the main instrument subpanels may be utilized for partial regulation of cockp...

Page 255: ...eed air When the automatic control drives the en vironmental system from a heating mode to a cooling mode the bypass valves move to ward the cool position bleed air passes through the air to air heat exchanger When the left valve reaches the full cold position the air conditioning system will begin cool ing When the left bypass valve is moved ap proximately 30 toward the heat position the air cond...

Page 256: ...d if the refrigeration system is operating in the mixing plenum and is then ducted to the floor registers As a result the cabin temperature will vary according to the position of the bypass valves whether or not the air conditioner is operating When the CABIN TEMP MODE selector is in the MAN COOL position the air condi tioning system will operate continuously until the system is turned off or unti...

Page 257: ...cted When the VENT BLOWER switch is in the AUTO position and the CABIN TEMP MODE selector switch is in the OFF posi tion the blower will not operate Anytime the VENT BLOWER switch is in the LO po sition the vent blower will operate at low speed even if the CABIN TEMP MODE se lector switch is OFF Anytime the VENT BLOWER switch is in the HIGH position the vent blower will operate at high speed regar...

Page 258: ...ing heated A PILOT AIR COPILOT AIR DE FROST AIR and CABIN AIR knobs fully pushed in or as required B PILOT AIR COPILOT AIR and DEFROST AIR knobs fully pulled out C Cockpit overhead eyeball outlets closed D CABIN AIR knob pushed in at small increments 6 When the CABIN TEMP MODE selec tor switch is in the MAN COOL posi tion how is the cabin temperature lowered A Momentarily depressing the MANUAL TEM...

Page 259: ......

Page 260: ...TION 12 1 PRESSURIZATION SYSTEM 12 3 AIR DELIVERY SYSTEM 12 4 CABIN PRESSURE CONTROL 12 8 PREFLIGHT CHECK 12 10 IN FLIGHT 12 10 DESCENT 12 10 FLOW CONTROL UNIT 12 11 QUESTIONS 12 13 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 12 PRESSURIZATION ...

Page 261: ......

Page 262: ...ve 12 5 12 6 Pressurization Controls Schematic 12 6 12 7 Bleed Air Control Pressurization and Pneumatics 12 7 12 8 Pressurization Controller 12 8 12 9 Cabin Altimeter 12 8 12 10 Cabin Climb Indicator 12 9 12 11 Cabin Pressure Switch 12 9 12 12 Environmental System Circuit Breakers 12 9 12 13 Pressurization Controller Setting for Landing 12 10 12 14 Flow Control Unit 12 11 FOR TRAINING PURPOSES ONL...

Page 263: ......

Page 264: ...dle malfunctions of the system DESCRIPTION The Pressurization System section of the training manual presents a description of the pressurization system The function of various major components their phys ical location and operation of the pres surization system controls are discussed Where necessary references are made to the environmental system as it affects pressurization KING AIR C90GTi C90GTx...

Page 265: ...KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 12 2 FOR TRAINING PURPOSES ONLY 12 PRESSURIZATION Figure 12 1 Pressurization and Air Conditioning Distribution System ...

Page 266: ...wo pressure differential is a positive number If cabin pressure is less than that of the outside ambient air pressure differential is a negative number Maximum differential is defined as a mea sure of the highest positive differential pres sure the air plane structure can safely withstand for an extended period of time The King Air C90GTi and C90GTx equipped with PT6A 135A engines main tain a 5 0 ...

Page 267: ...lve which is a normally closed solenoid This solenoid is controlled by a switch placarded BLEED AIR VALVES LEFT or RIGHT OPEN CLOSED in the ENVIRONMENTAL controls group Figure 12 3 on the copilot s left subpanel When this switch is in the CLOSED position the solenoid is closed and no bleed air can enter the flow control unit or the cabin When the BLEED AIR VALVE switch is in the OPEN position the ...

Page 268: ...IAPHRAGM UPPER DIAPHRAGM NEGATIVE RELIEF DIAPHRAGM LEGEND CABIN AIR VACUUM SOURCE STATIC AIR CONTROL PRESSURE PLUG Figure 12 4 Cabin Air Outflow Valve SILENCER REAR PRESSURE BULKHEAD SCHRADER TYPE VALVE DUMP SOLENOID MAXIMUM DIFFERENTIAL DIAPHRAGM UPPER DIAPHRAGM CABIN AIR NEGATIVE RELIEF DIAPHRAGM LEGEND CABIN AIR VACUUM SOURCE STATIC AIR CONTROL PRESSURE Figure 12 5 Cabin Air Safety Valve ...

Page 269: ...ch is moved into the DUMP position Keep the pressure vessel unpressur ized while the air plane is on the ground with the left landing gear safety switch compressed A negative pressure relief function is also incorporated into both the outflow and the safety valves This prevents outside atmo spheric pressure from exceeding cabin pres sure by more than 0 l psi during rapid descents even if bleed air...

Page 270: ...er the solenoid in the right flow control unit opens Consequently by increasing the volume of airflow into the pressure vessel in stages excessive pressure bumps dur ing takeoff are avoided KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 12 7 FOR TRAINING PURPOSES ONLY 12 PRESSURIZATION LH GEAR SAFETY SWITCH LH FLOW CONTROL PACKAGE AMBIENT AIR SHUTOFF VALVE CABIN AIR TEMP 5A CABIN AIR TEMP 5A DN UP L...

Page 271: ...the controller to the desired cruising altitude and observing the cabin altitude on the scale The maximum cabin altitude selected may be anywhere from 1 000 to 10 000 feet MSL The rate control selector knob is placarded RATE MIN MAX The rate at which the cabin pressure altitude changes from the current value to the selected value is controlled by rotating the rate control se lector knob The rate o...

Page 272: ...valve is normally closed in flight and the outflow valve is controlled by the pressur ization controller so that the cabin will pressurize When the switch is held in the spring loaded TEST aft position the safety valve is held closed bypassing the landing gear safety switch to facilitate test ing of the pressurization system on the ground Circuit breakers for the system Figure 12 12 are on the cop...

Page 273: ...the selected pressure altitude The system then maintains cabin pressure altitude at the selected value If the airplane climbs to an altitude higher than the value indexed on the ACFT ALT scale of the dial on the face of the controller the pres sure differential will reach the pressure re lief setting of the outflow valve and safety valve Either or both valves will then over ride the cabin pressuri...

Page 274: ... to 500 feet above the landing pressure altitude and maintaining speeds below 180 KIAS in the landing pattern FLOW CONTROL UNIT A flow control unit mounted in each nacelle on the forward side of the firewall controls the bleed air from the engine for use in pres surization heating and ventilation The function of the flow control unit Figure 12 14 is to vary the flow and balance of bleed air and am...

Page 275: ...ally to prevent the simultaneous opening of the modulat ing valves and a sudden pressure surge into the cabin The pneumostat pneumatic thermostat provides temperature input to the flow con trol unit which modulates the amount of ambient air entering the flow unit for blend ing Warmer outside air opens the modu lating valve and allows more ambient air in for blending Cold air closes the valve until...

Page 276: ...ate of climb A Index mark set at MEDIUM B Index mark set between the 2 o clock and 6 o clock positions C Index mark set between the 6 o clock and 9 o clock positions D Index mark set between the 9 o clock and 12 o clock positions 4 The CABIN ALT HI annunciator light illuminates when the cabin pressure al titude reaches A 12 500 feet B 14 000 feet C 10 000 feet D 35 000 feet 5 What is the maximum c...

Page 277: ......

Page 278: ...13 HYDRAULIC POWER SYSTEM CHAPTER 13 HYDRAULIC POWER SYSTEM The information normally contained in this chapter is not applicable to this particular aircraft ...

Page 279: ......

Page 280: ...lic Fluid Level Indication System 14 8 Landing Gear Warning System 14 11 Manual Landing Gear Extension 14 12 Hydraulic Schematics 14 12 Tires 14 16 Shock Struts 14 16 Landing Gear Operating Limits 14 16 KING AIR WHEEL BRAKES 14 19 Series Brake System 14 19 Parking Brake 14 19 Brake Service 14 22 Brake Wear Limits 14 23 Cold Weather Operation 14 23 QUESTIONS 14 25 FOR TRAINING PURPOSES ONLY KING AI...

Page 281: ......

Page 282: ...on Indicator No Illumination 14 10 14 13 Landing Gear Control Switch Handle Red In Transit Indicators 14 10 14 14 Handle Light Test 14 10 14 15 Landing Gear Alternate Extension Placard 14 12 14 16 Landing Gear Relay Circuit Breaker 14 12 14 17 Landing Gear Retraction Schematic 14 14 14 18 Landing Gear Extension Schematic 14 15 14 19 Hand Pump Emergency Extension Schematic 14 17 14 20 Landing Gear ...

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Page 284: ...BLES Table Title Page 14 1 Landing Gear Warning Horn Operation 14 11 14 2 Landing Gear Operating Limits 14 19 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 14 LANDING GEAR AND BRAKES ...

Page 285: ......

Page 286: ...ion to system description operating and servicing procedures are covered GENERAL This chapter presents a description and dis cussion of the landing gear system landing gear controls and limits The indicator sys tem and emergency landing gear extension are also described This chapter also presents a description and discussion of the wheel brake system Correct use of the brakes and parking brakes br...

Page 287: ...charge in the shock struts At touchdown the lower portion of each strut is forced into the upper cylinder this moves fluid through an orifice further compressing the air charge and thus ab sorbing landing shock Orifice action also reduces bounce during landing At takeoff the lower portion of the strut extends until an internal stop engages A torque knee connects the upper and lower portions of the...

Page 288: ...or actuator torque tube assembly with two push pull links Figure 14 3 The torque tube assembly also contains an uplock roller sup port assembly which when contacted by the uplock cam on the main gear shock cylin der rotates the torque tube to pull the doors closed upon gear retraction or push the doors open upon gear extension Roller movement is transmitted through linkage to close the doors Durin...

Page 289: ...ock in place when the gear is fully extended The individual landing gear actuators in corporate internal mechanical downlocks to hold the gear in the fully extended posi tion The landing gear is held in the up po sition by hydraulic pressure KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 14 4 FOR TRAINING PURPOSES ONLY 14 LANDING GEAR AND BRAKES NOSE LEFT RIGHT NO 2 APPROACH LIMIT SWITCH LEFT RIGHT ...

Page 290: ... fluid to the indi vidual gear actuators The selector valve receives electrical power through the land ing gear control switch Accidental retraction of the landing gear is prevented through safety switches located on the main landing gears KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 14 5 FOR TRAINING PURPOSES ONLY 14 LANDING GEAR AND BRAKES LEGEND LANDING GEAR EXTENSION LINE LANDING GEAR EMERGENC...

Page 291: ...each landing gear The power pack Figure 14 7 consists of a hydraulic pump 28 VDC motor two sec tion fluid reservoir filter screens four way gear selector valve fluid level sensor an up selector solenoid and an uplock pressure switch For manual extension the system has a hand lever operated pump The pump han dle is located on the floor between the pilot s seat and the pedestal KING AIR C90GTi C90GT...

Page 292: ...piston faces of the actuators which are attached to folding drag braces resulting in the extension or retraction of the landing gear When the actuator pistons are repositioned to fully extend the landing gear an internal mechanical lock in the nose gear actuator and the over center action of the nose gear drag leg assembly lock the nose gear in the down position In this position the internal locki...

Page 293: ...in the retracted position When the hydraulic pressure reaches approximately 1 850 psi the uplock pressure switch will cause the landing gear relay to open and interrupt the current to the pump motor The same pres sure switch will cause the pump to actuate should the hydraulic pressure drop to ap proximately 1 600 psi The landing gear control circuit is protected by a 2 ampere circuit breaker locat...

Page 294: ...e the squat switches close and a circuit is completed through the solenoid that moves the hook In the event of a malfunction of the down lock solenoid or the squat switch circuit the downlock hook can be overridden by pressing downward on the red DOWN LOCK REL button The release button is located just left of the LDG GEAR CONTROL switch handle The LDG GEAR CONTROL handle should never be moved out ...

Page 295: ... wired indicator lights lo cated in the LDG GEAR CONTROL switch handle Figure 14 13 illuminate to show that the gear is in transit or unlocked Gear UP is indicated when the red lights go out The red lights in the handle also illumi nate when the landing gear warning sys tem is activated The red control handle lights may be checked by pressing the HD LT TEST button Figure 14 14 located adjacent to ...

Page 296: ...of power lever position Thus the function of the landing gear in transit light is to indicate that the landing gear is in transit The up indicator down indicator and warn ing horn systems are essentially indepen dent systems A malfunction in any one system will probably leave the other two systems unaffected LANDING GEAR WARNING SYSTEM The landing gear warning system is provided to warn the pilot ...

Page 297: ...se of an electrical system failure or in the event an actuator is not locked down continue pump ing until sufficient resistance is felt to ensure that the gear is down and locked Do not stow pump handle The landing gear cannot be manually retracted in flight After a manual landing gear ex tension has been made do not move any landing gear controls or reset any switches or circuit breakers until th...

Page 298: ...store needed uplock pressure Consequently when the gear is retracted pressure will be main tained between approximately 1 600 and 1 850 psi to keep the gears in their retracted position An accumulator pre charged to 800 psi located in the left wing inboard of the nacelle is designed to aid in maintain ing the system pressure in the gear up mode Landing Gear Extension For normal gear extension a pi...

Page 299: ...N LOCK SOLENDOID LANDING GEAR REMOTE POWER RELAY PUMP MOTOR PUMP SELECTOR VALVE UP SOLENOID PUMP CHECK VALVE PUMP OVERBOARD VENT CHECK VALVE FILL CAN FILL PORT VENT PORT RETURN FILTER PRIMARY RESERVOIR SYSTEM RELIEF VALVE PUMP MOTOR FILTER RELIEF VALVE SELECTOR VALVE SECONDARY RESERVOIR HAND PUMP SUCTION PORT HAND PUMP HAND PUMP PRESSURE PORT PRESSURE SWITCH HAND PUMP DUMP VALVE PRESSURE CHECK VAL...

Page 300: ...N LOCK SOLENDOID LANDING GEAR REMOTE POWER RELAY PUMP MOTOR PUMP SELECTOR VALVE UP SOLENOID PUMP CHECK VALVE PUMP OVERBOARD VENT CHECK VALVE FILL CAN FILL PORT VENT PORT RETURN FILTER PRIMARY RESERVOIR SYSTEM RELIEF VALVE PUMP MOTOR FILTER RELIEF VALVE SELECTOR VALVE SECONDARY RESERVOIR HAND PUMP SUCTION PORT HAND PUMP HAND PUMP PRESSURE PORT PRESSURE SWITCH HAND PUMP DUMP VALVE PRESSURE CHECK VAL...

Page 301: ...nob located on top of the service valve The hand pump can then be used to raise the gear to the desired position After the re quired maintenance has been performed push the red knob down and use the hand pump to lower the gear The valve is not ac cessible to the pilot If the red knob on the service valve is pushed down while the landing gear is retracted the electrical power on and the landing gea...

Page 302: ...H DOWN LOCK SOLENDOID LANDING GEAR REMOTE POWER RELAY PUMP MOTOR PUMP SELECTOR VALVE UP SOLENOID PUMP CHECK VALVE PUMP OVERBOARD VENT CHECK VALVE FILL CAN FILL PORT VENT PORT RETURN FILTER PRIMARY RESERVOIR SYSTEM RELIEF VALVE PUMP MOTOR FILTER RELIEF VALVE SELECTOR VALVE SECONDARY RESERVOIR HAND PUMP SUCTION PORT HAND PUMP HAND PUMP PRESSURE PORT PRESSURE SWITCH HAND PUMP DUMP VALVE PRESSURE CHEC...

Page 303: ... LANDING GEAR REMOTE POWER RELAY PUMP MOTOR PUMP SELECTOR VALVE UP SOLENOID PUMP CHECK VALVE PUMP OVERBOARD VENT CHECK VALVE FILL CAN FILL PORT VENT PORT RETURN FILTER PRIMARY RESERVOIR SYSTEM RELIEF VALVE PUMP MOTOR FILTER RELIEF VALVE SELECTOR VALVE SECONDARY RESERVOIR HAND PUMP SUCTION PORT HAND PUMP HAND PUMP PRESSURE PORT PRESSURE SWITCH HAND PUMP DUMP VALVE PRESSURE CHECK VALVE GEAR DOWN POR...

Page 304: ...raking action The pilot s and copilot s right rudder pedals control the brake in the right main landing gear Similarly the pilot s and copilot s left rudder pedals control braking in the left main gear This arrangement allows differ ential braking for taxiing and maneuvering on the ground PARKING BRAKE The parking brake utilizes the regular brakes and a set of valves Figure 14 22 Dual parking brak...

Page 305: ...NDING GEAR AND BRAKES ORIFICE PRESSURE VENT OVERLOAD DRAIN RESERVOIR PILOT S MASTER CYLINDERS COPILOT S MASTER CYLINDERS RIGHT PARK BRAKE LEFT PARK BRAKE LEFT WHEEL CYLINDER RIGHT WHEEL CYLINDER LEGEND FLUID UNDER PRESSURE SUPPLY FLUID STATIC FLUID Figure 14 21 Brake System Schematic ...

Page 306: ...NDING GEAR AND BRAKES ORIFICE PRESSURE VENT OVERLOAD DRAIN RESERVOIR PILOT S MASTER CYLINDERS COPILOT S MASTER CYLINDERS RIGHT PARK BRAKE LEFT PARK BRAKE LEFT WHEEL CYLINDER RIGHT WHEEL CYLINDER LEGEND FLUID UNDER PRESSURE SUPPLY FLUID STATIC FLUID Figure 14 22 Parking Brake Schematic ...

Page 307: ... the upper corner of the left side of the nose avionics compartment Figure 14 23 Brake system servicing is limited primar ily to maintaining the hydraulic fluid level in the reservoir A dipstick is provided for measuring the fluid level When the reser voir is low on fluid add a sufficient quan tity of MIL H 5606 hydraulic fluid to fill the reservoir to the full mark on the dip stick Check all hydr...

Page 308: ...solutions may be used on the brakes or tires if freeze up oc curs No anti ice solution which contains a lubricant such as oil should be used on the brakes It will decrease the effectiveness of the brake friction areas When possible taxiing in deep snow or slush should be avoided Under these conditions the snow and slush can be forced into the brake assemblies Keep flaps retracted dur ing taxiing t...

Page 309: ...INTENTIONALLY LEFT BLANK KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 14 24 FOR TRAINING PURPOSES ONLY 14 LANDING GEAR AND BRAKES ...

Page 310: ...ically held in that position C The parking brake valve is actuated to trap pressure from that point to brake assemblies D The parking brake valve is me chanically actuated to build pres sure for brake application 4 The landing gear is held in the retracted position by A Mechanical uplock mechanisms B Continuously applied hydraulic pressure C Internal uplock mechanisms in all three gear actuators D...

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Page 312: ...CTION 15 1 DESCRIPTION 15 1 FLAPS SYSTEM 15 2 Flap Operation 15 3 Landing Gear Warning System 15 4 Flap Airspeed Limits 15 4 RUDDER BOOST SYSTEM 15 4 QUESTIONS 15 7 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 15 FLIGHT CONTROLS ...

Page 313: ......

Page 314: ... Control Lever 15 3 15 3 Flap Position Indicator 15 3 15 4 Flap System Circuit Breaker 15 3 15 5 Airspeed Indicator 15 4 15 6 Rudder Boost System Diagram 15 5 15 7 Rudder Boost Switch 15 6 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 15 FLIGHT CONTROLS ...

Page 315: ......

Page 316: ...hapter also presents familiarization with and operation of the rudder boost system DESCRIPTION This chapter presents a description and discussion of flap system The four seg ment Fowler type system its controls and limits are considered with reference to operation as outlined in the Pilot s Operating Handbook The rudder boost system section of this chapter presents a description and dis cussion of...

Page 317: ...operated by a sliding lever lo cated just below the condition levers on the pedestal Figure 15 2 Flap travel from 0 UP to 100 DOWN is registered at 20 APPROACH 40 60 and 80 and DOWN in percentage of travel on an electric indicator on top of the pedestal Figure 15 3 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 15 2 FOR TRAINING PURPOSES ONLY 15 FLIGHT CONTROLS DETAIL B FLAP POSITION TRANSMITTER DET...

Page 318: ...t hand circuit breaker panel Figure 15 4 A 5 ampere cir cuit breaker placarded FLAP IND CON TROL for the flap control circuit is also located on this panel FLAP OPERATION Flaps are selectable to 3 positions up ap proach 15 and down 43 If a go around is initiated with flaps fully extended re traction to either approach or full up posi tions can be accomplished with a single switch position selectio...

Page 319: ...pproach speed The white DN indicates the maxi mum speed permissible with flaps extended beyond APPROACH Approach speed is 184 KIAS Beyond APPROACH position the maximum speed is 148 KIAS Lowering the flaps will produce these results Attitude Nose up Airspeed Reduced Stall speed Lowered Trim Nose down adjustment required to maintain NOTE All illustration needles may not re flect normal indications R...

Page 320: ...LS P SWITCH 18 PSI PNEUMATIC PRESSURE REGULATOR CHECK VALVE CHECK VALVE N C N C LEFT P3 AIR RIGHT P3 AIR AFT PRESSURE BULKHEAD HIGH PRESSURE P3 AIR REGULATED P3 AIR 13 PSI PRESSURE REGULATOR FILTER LEGEND RIGHT RUDDER SERVO LEFT RUDDER SERVO RIGHT GEN BUS Figure 15 6 Rudder Boost System Diagram ...

Page 321: ...leed air pressure from the right engine will cause the left rudder pedal to move forward Pedal rigging causes the opposite pedal to move in the opposite di rection This system is intended to help com pensate for asymmetrical thrust only Appropriate trimming is to be done with the trim controls The system is controlled by a toggle switch Figure 15 7 placarded RUDDER BOOST OFF located on the pedesta...

Page 322: ...either element of their PITCH TRIM switches in the same direction simultaneously 3 Why should the rudder control lock be removed prior to towing the airplane A So the airplane can be steered with the rudder pedals B So the brakes can be applied C To prevent damage to the steering linkage D It is not necessary to remove the rud der control lock prior to towing 4 How can the rudder boost system be c...

Page 323: ......

Page 324: ...ONARY OPERATIONS 16 23 OUTSIDE AIR TEMPERATURE 16 28 STALL WARNING SYSTEM 16 30 FLIGHT GUIDANCE SYSTEM FGS 16 31 Flight Guidance Computers FGC 16 31 Flight Guidance Panel FGP 16 31 Control Wheel Switches 16 39 CONTROL DISPLAY UNIT CDU 16 41 FLIGHT MANAGEMENT SYSTEM FMS 16 45 Vertical Navigation 16 47 Global Positioning System GPS 16 50 INTEGRATED FLIGHT INFORMATION SYSTEM IFIS 16 51 Cursor Control...

Page 325: ...OICE RECORDER CVR 16 86 EMERGENCY LOCATOR TRANSMITTER ELT 16 86 TERRAIN AWARENESS AND WARNING SYSTEM TAWS 16 87 Basic Ground Proximity Warnings Reactive 16 87 Enhanced Ground Proximity Warnings Predictive 16 89 TRAFFIC COLLISION AND AVOIDANCE SYSTEM TCAS I 16 92 APPENDIx A AVIONICS EQUIPMENT LOCATIONS 16 95 APPENDIx B FLIGHT GUIDANCE MODES 16 97 APPENDIx C AVIONICS ACRONYMS 16 101 FOR TRAINING PUR...

Page 326: ...ration Display 16 6 16 10 Altimeter Display 16 6 16 11 Altitude Negative 16 6 16 12 Vertical Speed Indicator VSI 16 7 16 13 Altitude Preselect Bugs 16 7 16 14 Metric Altitude 16 8 16 15 Heading and Navigation Display 16 8 16 16 DME Hold 16 9 16 17 PFD Compass Rose Format 16 9 16 18 PFD Arc Format 16 9 16 19 PFD Map Format 16 10 16 20 Terrain and Radar Overlay Section 16 10 16 21 PFD Lower Display ...

Page 327: ...dio Altitude Minimum 16 18 16 35 Barometric Minimum 16 18 16 36 Minimums Annunciator 16 18 16 37 PFD REFS Menu Page 2 of 2 16 19 16 38 Metric Altitude 16 19 16 39 Flight Director Formats 16 19 16 40 PFD NAV BRG Menu 16 20 16 41 Bearing Pointer Information 16 20 16 42 IAPS 16 21 16 43 ADC 16 22 16 44 AHRS 16 22 16 45 Heading Slave and Slew 16 23 16 46 AFD Reversions 16 23 16 47 Reversionary Modes 1...

Page 328: ...63 Flight Guidance Couple Arrow 16 32 16 64 Independent Flight Director Operation 16 32 16 65 YD AP Disconnect Bar 16 33 16 66 Heading Vector Line 16 34 16 67 Half Bank Mode 16 34 16 68 APPR Mode Selection 16 35 16 69 Localizer Nav to Nav Capture 16 36 16 70 VNAV Glidepath GP Mode 16 36 16 71 Vertical Speed VS Mode 16 37 16 72 Flight Level Change FLC Mode 16 38 16 73 Left Yoke 16 39 16 74 Pilot s ...

Page 329: ...GPS CONTROL 16 50 16 90 PROGRESS 16 50 16 91 IFIS Block Diagram 16 52 16 92 USB Database Unit DBU 5000 16 53 16 93 MCDU Menu 16 53 16 94 IFIS Dataload Block Diagram 16 54 16 95 CCP 16 54 16 96 MFD Store Complete 16 54 16 97 Geo Politcal Overlay 16 55 16 98 Airspace Overlay 16 55 16 99 Airways Overlay 16 56 16 100 Database Effectivity STAT Key 16 56 16 101 STAT Menu 16 56 16 102 Chart Subscription ...

Page 330: ...al Weather 16 64 16 117 Datalink Weather Selections Universal Weather 16 64 16 118 MFD Plan Map Weather Overlay 16 65 16 119 MFD Dedicated Graphical Weather Format Universal Weather 16 65 16 120 Universal Weather Menu 16 66 16 121 RTU CDU TUNE Switch 16 66 16 122 Emergency Frequency Button 16 67 16 123 Antennas 16 67 16 124 RMT Tune Switch 16 68 16 125 PFD DME Displays 16 69 16 126 DME Hold Select...

Page 331: ...M Button 16 80 16 145 Static Wicks 16 80 16 146 SFDS Display 16 81 16 147 SFDS Power Switch 16 82 16 148 PFD Radar Menu 16 83 16 149 Test Mode 16 83 16 150 Radar Ground Map Mode 16 84 16 151 Radar Display with Path Attenuation Bar 16 84 16 152 Radar Gain Display 16 84 16 153 Radar Ground Clutter Supression 16 85 16 154 Radar Tilt Display 16 86 16 155 CVR Controllers 16 86 16 156 ELT Manual Switch ...

Page 332: ...n Warning 16 90 16 163 Terrain Fail and TERR Annunciations 16 92 16 164 TCAS I TEST 16 93 16 165 Operating Mode Button 16 93 16 166 Overview of Avionics Units 16 95 TABLES Table Title Page 16 1 Basic Cautions and Warnings 16 88 16 2 TAWS Buttons 16 89 16 3 Enhanced Cautions and Warnings 16 91 16 4 Flight Guidance Modes 16 97 16 AVIONICS ...

Page 333: ......

Page 334: ...STRUMENTS ELECTRONIC FLIGHT INSTRUMENT SYSTEM EFIS The Electronic Flight Instrument System EFIS consists of computers and data collectors that when coupled with other subsystems result in the display of ﬂight navigation and engine indi cating on liquid crystal displays LCD these are called Adaptive Flight Displays AFD Compared to conventional instrumentation an EFIS system permits much more inform...

Page 335: ...1 The temperature of LCD displays must stay within appropriate limits to provide normal operation Should these temperature extremes be exceeded each AFD has its own tempera ture monitor Depending on what is needed this monitor has control of integral heaters and cooling fans In the event of a display failure on PFD 1 the MFD can display PFD 1 images in what s called a reversionary or composite mod...

Page 336: ... the LSK Attitude Display The primary function of the PFD is to show airplane attitude The attitude display on the PFD additionally shows the following ﬂight director steering commands ﬂight guidance system status mode annunciations vertical lat eral deviation marker beacon annunciations and radio altitude A rectangular shaped slip skid indicator is lo cated at the base of the sky pointer bank Fig...

Page 337: ...ay This display area can also show current Mach IAS markers bugs IAS trend vector low high speed cues and acceleration rates The trend vector is a magenta line that extends ei ther above or below the pointer to indicate the rate of airspeed increase or decrease The end of the vector indicates expected airspeed in 10 seconds based on current A C pitch power setting and A C conﬁguration A trend vec ...

Page 338: ... disconnect See the Stall Warning section later in this chapter The high speed cue consists of a red bar start ing at the current Vmo or Mmo whichever is appropriate Figure 16 7 Should the aircraft actual airspeed enter this red bar area an over speed warning horn will sound until the speed is reduced to below the red overspeed bar If the autopilot is engaged during the overspeed it will begin to ...

Page 339: ...itude is on a single drum and the hundreds and thousands follow when needed At lower altitudes green striped shutters cover the ap propriate ten thousand and thousand digits Figure 16 10 Should a negative altitude exist a vertically positioned NEG legend will replace the ten thousands position Figure 16 11 Figure 16 10 Altimeter Display The Altimeter setting is displayed below the altitude tape Th...

Page 340: ...rlier by pressing the ALT knob on the ﬂight guidance panel See the Flight Guidance section later in this chapter Should the aircraft go 200 from the altitude an aural tone will sound and the preselected altitude will change to yellow and ﬂash This ﬂashing will continue until the altitude returns to within 200 of selected This ﬂashing can be stopped by pressing the ALT knob on the ﬂight guidance pa...

Page 341: ... always have a yellow FMS needle and the pilot will have a green FMS needle Above the active NAV source label is an area reserved for FMS messages and annunciations Selected messages can appear here However the majority of the messages will be displayed on the Control Display Unit CDU on the pedestal These will be prompted by the label MSG to instruct the pilots to look down at the CDU and retriev...

Page 342: ...imited to 50nm To get a further range the TCAS trafﬁc must be deselected ﬁrst This range is controlled by the DCP and is discussed later Figure 16 17 PFD Compass Rose Format The arc format can display the same items de scribed for the full compass rose but only pres ents a 120 portion of the compass Figure 16 18 In this mode the display of TCAS traf ﬁc does not limit the range to 50nm The dis play...

Page 343: ... indicate that the unit is active Ter rain and Radar must be turned ON from a dif ferent location Below these labels is an area reserved for detail about the selected option For instance if RDR is selected the display will be cyan and the radar operating mode and tilt would be displayed below RDR If TERR is selected the display will be cyan and the ap propriate operating status for the terrain wou...

Page 344: ...edestal simulta neously Each display does not have to be in dividually dimmed or brightened but can be operated together The BRT DIM Rocker Switch will then allow each individual display to be ﬁne tuned to make its brightness com patible with the surrounding displays Line Select Keys Four line select keys LSK are located on each side of the MFD The keys are used in co ordination with the informati...

Page 345: ...ng the UPPER FORMAT LSK described above and choosing CHKLST or by using the checklist ON OFF button on the back of ei ther yoke Figure 16 24 The pages are ad vanced using the Cursor Control Panel CCP Collins BRT DIM FMS DTK 251 6935 TTG 0 8NM 251 W 3 0 24 21 TAS SAT GS ISA 0 0 13 o C 15 o C RDR TERR F 50 WX 0 0 0 ITT 26 TORQ 0 FF PRESS OIL TEMP o C 0 0 46 430 120 73 N I 98 5 PROP 1980 TORQ 2000 IT...

Page 346: ...cle This is controlled by the DCP and will be discussed later This range will always be equal to the range dis played on the left PFD This will limit to the following 50nm if TCAS trafﬁc has been se lected on the left PFD 300nm if TCAS display is OFF and overlays have been selected on the left PFD or MFD or 600nm if no overlays or TCAS are selected on the left PFD or MFD Further display options fo...

Page 347: ...yed on the PPOS format To overlay TCAS on the PPOS format simply press the TFC line select key to turn it cyan A TCAS message only area will be present below this TFC key e g TCAS TEST TA ONLY etc The TCAS only format can be selected by the LOWER FORMAT key or by pressing and holding the trafﬁc TFC key for more than 2 seconds Figure 16 26 The display is a 360 heading up image that only shows trafﬁ...

Page 348: ...e Ground Speed GS indication is derived from the FMS Should the FMS fail the GS indica tion will be removed True Airspeed TAS Static Air Temperature SAT and ISA devia tion ISA are all derived from the ADC Should the ADC fail these indications will be removed Figure 16 28 MFD Lower Dispay Information DISPLAY CONTROL PANELS DCP Display control panels are vertical panels lo cated adjacent to each PFD...

Page 349: ...00 hPa BARO PUSH STD Button When pushed the standard altimeter setting QNE is selected and STD will be displayed in lieu of the pressure setting The cyan prese lect altitude above the altitude display will dis play a ﬂight level FL format when this button is pushed e g 22 000 will be displayed as FL220 8 000 will be FL80 To return the setting to normal units turn the Baro Knob and select the new a...

Page 350: ...lay Figure 16 33 Figure 16 33 PFD V Speeds The right side of the menu contains the num bers used for landing The barometric mini mum BARO MIN value and the radio altimeter minimum RA MIN value will be identical on both pilot s displays Only one pilot needs to set the values Setting RA MIN will create a hollow bar on the altitude tape the length of the value cho sen For instance setting 200 feet wi...

Page 351: ...urn yellow The minimum reference displayed is the last one adjusted e g if RA was set ﬁrst and then BARO the BARO minimums are the only ones displayed Baro min s and RA min s can both be set but only the one that is cyan will be the active minimum reference Figure 16 36 Minimums Annunciator The last option on the right side of the menu is VREF This acts just like the V speeds dis cussed earlier On...

Page 352: ...d to a value other than 18 000 Finally the FLT DIR line will change the ﬂight director image changing it from a v bar pres entation to a cross pointer x PTR presenta tion Figure 16 39 This change will affect both pilots and cannot be set independently Figure 16 38 Metric Altitude Figure 16 39 Flight Director Formats MENU ADV Knob The MENU ADV knob moves the menu cur sor around the displays DATA Kn...

Page 353: ...S installed In this case both needles can be selected to that single FMS Selection is accomplished by pressing the appropriate line select keys or turning the DATA knob These selections are independent for each pilot Once the bearing pointers are chosen an in formation area will appear on the bottom left corner of the PFD Figure 16 41 The follow ing labels are possible V VOR F FMS A ADF Below the ...

Page 354: ...o 2 right section monitors the No 2 systems Each section is powered by a dedicated power supply Fans control the temperature of each unit to eliminate sus tained overheating which would cause an au tomatic shutdown of the respective power supply Additionally the power supply opera tion is inhibited in extreme cold temperatures below 40 C Each IAPS section contains the Flight Guid ance Computers FG...

Page 355: ...ude information is obtained from two at titude and heading computers AHC Each system includes an inertial measurement unit IMU that monitors angular rates and accel erations about the airplane axes The IMU does not provide self generated navigation po sition The AHC processes IMU data to de termine airplane pitch and bank attitude EachAHC is provided with a primary and sec ondary power supply for ...

Page 356: ...ng Slave and Slew REVERSIONARY OPERATIONS AFD Reversion The pilot s PFD and the MFD are designed to provide reversionary support to each other in the event of a single display failure Rever sionary display switching for the pilot s PFD or the MFD is accomplished via the PILOT DISPLAY switch on the reversionary control panel Figure 16 46 Selecting the remaining AFD will display a composite image Wh...

Page 357: ... 0 FF PRESS OIL TEMP o C 0 0 46 430 120 73 N I 98 5 PROP 1980 TORQ 2000 ITT 734 AFX FIRE TFC SAT 15 o C ISA 15 o C ABOVE V2 VR V1 110 93 93 Collins BRT DIM Collins BRT DIM FMS DTK 251 6935 0 8NM ATC1 UTC RAT COM1 COM2 121 800 4336 125 250 14 41 15 o C ET TERM 251 10 10 20 HDG PTCH ALTS 14000 6 60 540 20 400 600 700 1 2 4 4 2 1 140 80 60 6935 ACC 02 0 FMS 30 16IN 0 0 0 ITT 26 TORQ 0 FF PRESS OIL TE...

Page 358: ...0 20 400 600 700 1 2 4 4 2 1 30 16IN 251 W 24 140 80 60 6935 R TERM F ACC 02 T 0 FMS R HDG 010 IAS ALT V2 VR V1 110 93 93 16 25 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS Figure 16 48 ADC1 Failure Collins BRT DIM 10 10 20 PRESET VOR1 FORMAT FMS DTK 251 6935 0 8NM 25 251 W 3 0 24 21 ATC1 UTC RAT COM1 COM2 121 800 4336 125 250 14 41 o C RDR TERR ET TERM F 50 ...

Page 359: ...2 T ADC2 V2 VR V1 110 93 93 FOR TRAINING PURPOSES ONLY 16 26 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS Figure 16 51 AHRS1 Failure Collins BRT DIM 14000 6 60 540 20 400 600 700 1 2 4 4 2 1 30 16IN PRESET VOR1 FORMAT FMS DTK 251 6935 0 8NM 25 W 3 0 24 21 ATC1 UTC RAT COM1 COM2 121 800 4336 125 250 14 41 15 o C 140 80 60 6935 RDR TERR ET TERM F 50 ACC TERRAIN 0 RADAR ON TCAS OFF ATT HD...

Page 360: ...on the forward lower nose sec tion of the airplane Figure 16 53 Pitot Tubes Each heated mast provides ram air pressure to its respective Air Data Computer ADC The pilot s mast also provides ram air pres sure to the Secondary Flight Display System SFDS ADC Dual static ports are located on each side of the aft fuselage in a vertical arrangement Fig ure 16 54 The top port on the left side is con nect...

Page 361: ...ons and the pilot must use appropriate corrections from the perform ance tables Moving the switch back to the Normal position will allow normal pitot sta tic air to return to the standby unit ADC The copilot s ADC only receives normal pitot static air It does not have a connection to the alternate system OUTSIDE AIR TEMPERATURE The digital outside air temperature OAT gage is located on the left si...

Page 362: ...ITOT MAST RAT TEMPERATURE PROBE DRAIN FWD PRESSURE BULKHEAD AFT PRESSURE BULKHEAD PILOT PFD PILOT MFD STANDBY UNIT COPILOT PFD DRAIN DRAIN DRAIN DRAIN ALTERNATE STATIC SOURCE PILOT S STATIC SOURCE SELECTOR RIGHT STATIC PORTS LEFT STATIC PORTS TOP BOTTOM TOP BOTTOM CABIN DIFFERENTIAL PRESSURE GAGE PNEUMATIC PRESSURE GAGE CABIN PRESSURE PNEUMATIC PRESSURE FGC FMC IAPS FGC FMC Optional ADC ...

Page 363: ...ots above stall with ﬂaps in the 40 Approach position and at 8 to 14 knots above stall with the ﬂaps fully ex tended Figure 16 59 Transducer Vane The left main gear squat switch disconnects the stall warning system when the aircraft is on the ground In the ICE group of switches on the pilot s right subpanel a STALL WARN switch con trols electrical heating of the mounting plate Figure 16 60 With th...

Page 364: ...ay FLIGHT GUIDANCE COMPUTERS FGC Each FGC is supplied with input from the AHRS navigation data FGP selections servo and ADC computers The coupled FGC pro duces control signals for yaw damping AP FD and pitch trim functions Each FGC is supplied data from the onside ADC EFIS and AHRS The autopilot and ﬂight director require both attitude portions of the AHRS to be operational Each FGC produces an in...

Page 365: ...und mode full ILS approach mode When GA and full ILS modes are ac tive each Flight Guidance Computer FGC provides independent guidance to the onside PFD ﬂight director When either of these con ditions exist the single pointer arrow adds an other barb to show that the ﬂight directors are now independent Figure 16 64 For this con dition to exist in the full ILS approach mode the same localizer frequ...

Page 366: ...atically activated when the autopilot is en gaged or when a ﬂight director mode is selected Pushing the FD button will initially display both ﬂight directors in the PTCH and ROLL modes but command bars only appear on the side the FD button was pushed If both side command bars are displayed either pilot can independently remove their command bars from view by pressing the respective FD button The c...

Page 367: ...um bank angle to 15 While in this mode a white arc appears bellow the roll scale that spans 15 degrees either side of level Figure 16 67 The half bank mode is automatically selected when climbing through 18 500 feet and dese lected when descending through 18 500 feet This mode is also deselected with the follow ing localizer capture go around mode selec tion or onside FMS navigation capture Figure...

Page 368: ...hange ﬂight guidance modes It is accomplished automatically The APPR button is also used when ﬂying a non localizer based approach to a DA Deci sion Altitude When established on ﬁnal for an appropriate RNAV GPS approach the APPR button will activate the approach mode APPR FMS1 or APPR FMS2 When VNAV is then pressed it will arm the vertical glide path GP mode Figure 16 70 This allows the FMS to fol...

Page 369: ... N 3 6 E 1 2 1 5 S 251 4 1NM SXW RDR TERR TCAS OFF TFC V2 VR V1 110 93 93 Collins BRT DIM 10 10 20 APPR LOC1 GS 14000 6 60 540 20 400 600 700 1 2 4 4 2 1 30 16IN FORMAT LOC1 109 75 CRS 235 IEJC 0 8NM ATC1 UTC RAT COM1 COM2 121 800 4336 125 250 14 41 15 o C 6935 ET V 850 21 24 w 3 0 3 3 N 3 6 E 1 2 1 5 S 251 4 1NM SXW RDR TERR TCAS OFF TFC PRESET FMS1 185 180 160 120 DN 100 141 0 Collins 10 10 20 A...

Page 370: ...ected or when the UP DOWN Pitch Wheel is moved and VS mode is not active Rotating the UP DOWN pitch wheel changes the pitch reference value When the autopilot is not engaged pushing the SYNC button on the control wheel synchronizes the pitch ref erence to the current attitude VS Button The VS button controls selection of the verti cal speed mode When VS is activated the FGC initially maintains the...

Page 371: ...oo high In this situation the aircraft will initially pitch to achieve the selected speed If this results in a speed faster than selected the aircraft will begin to pitch back up until it maintains a de scent of approximately 100 ft min regardless of what speed that generates SPEED Knob The SPEED knob selects the IAS or Mach ref erence value as appropriate to be used by the FLC mode This value dis...

Page 372: ...ﬂash yellow The ﬂashing will stop with an input by the pilot pressing the altitude selector knob or the aircraft re turns to within 200 of selected altitude In ei ther case the number will stop ﬂashing and return cyan in color ALTS shows in yellow if the capture is inhib ited due to invalid data and ALTS CAP shows in yellow if the capture is cleared without a subsequent selection of altitude hold ...

Page 373: ...or further discussion of electric pitch trim and its annunciations GA Button The GA button is located on the outboard side in the center of the left power lever Fig ure 16 75 The G A button selects the go around GA mode of the ﬂight director Selecting GA mode will disengage the autopi lot but not yaw damper and clear all other ﬂight director modes The ﬂight director will display approximately 7 de...

Page 374: ...ound GA Mode CONTROL DISPLAY UNIT CDU The Control Display Unit CDU 3000 serves as a control of the communication and navi gation radios Flight Management System FMS and limited display control for the PFDs and MFD Figure 16 77 The pedestal can contain either one or two CDUs The sec ond CDU is an option If two are installed each CDU will communicate only with the re spective FMS In the optional two...

Page 375: ...er by a line key Brackets identify this line and it is the only place where the operator can input information from the keypad Once input data is displayed on this line it should be veriﬁed before transferring to a selected ﬁeld Should an entry occur that is not compatible with the selected item the scratchpad will mo mentarily display a message to indicate details about the error This message wil...

Page 376: ...o page Navigating backward through these pages will lead to a HISTORY page of all the previous waypoints in the ﬂight plan Figure 16 80 Figure 16 80 Direct to Pages EXEC NEXT PREV MFD DATA MFD ADV CLR DEL BRT DIM DEP ARR PERF LEGS FPLN DIR MSG TUN IDX MFD MENU A B C D F G H I J K L M O P Q R T U V X Y Z SP E N S W 1 2 3 4 5 6 7 8 9 0 ACT LEGS KICT 1 6 SEQUENCE LEG WIND AUTO INHIBIT ICT WUKOL MUGER...

Page 377: ...active PREV Key The PREV previous key is used to display the previous page when the current CDU function has more than one page NEXT Key The NExT key is used to display the next page when the current CDU function has more than one page EXEC Key The ExEC execute key activates modiﬁca tions made to the active ﬂight plan The label ExEC annunciates on the CDU when the ac tive ﬂight plan has been modiﬁ...

Page 378: ...ese receivers The system also provides course tracking signals to the ﬂight guidance system The Flight Management Computers FMCs are housed in the IAPS unit located in the nose avionics bay The FMS uses a blended combination of GPS and VOR DME data to construct a three di mensional position of the aircraft in space To achieve this blend the NAV1 radio and NAV2 radio must be receiving a valid signa...

Page 379: ... ISA 0 0 13 o C 15 o C 0 0 0 ITT 26 TORQ 0 FF PRESS OIL TEMP o C 0 0 46 430 120 73 N I 98 5 PROP 1980 TORQ 2000 ITT 734 WPT DIST ETA FUEL LB KICT 3 6NM 20 07 0 ICT 7 4NM 20 11 2450 MUGER 16 6NM 20 15 2390 WUKOL 19 8NM 20 16 2370 WUKUS 20 4NM 20 16 2370 HUT 29 8NM 20 20 2310 OATHE 218NM 21 32 1170 SELLS 283NM 21 56 760 TFC FMS ACT PROGRESS 1 3 DEST KDEN 415NM 22 47 0 ALTN KAPA 435NM 22 54 0 RESERVE...

Page 380: ...t or the GPS The GPS should be able to update the system quickly unless the aircraft was moved a signiﬁcant distance 40nm with the FMS in operative or the FMS was removed and re placed This step will consist primarily of verifying the known position as opposed to ac tively entering the position PLAN The ﬂight plan will be loaded on the FPLN page ORIGIN DESTination and ﬁxes along the route of ﬂight...

Page 381: ...ed point where this descent will occur The TOD point will indicate when the vertical deviation indicator nears the center position on the vertical deviation scale Figure 16 87 This indicator is sometimes called the snowﬂake or star As with Glideslope op erations these GPS Glidepath operations will only capture VNAV when initially below the projected angle If the aircraft is already passed the desc...

Page 382: ...descent apply here too The initial climb from the airport will be accomplished by any manually chosen vertical mode VS or FLC When VNAV is selected the altitude preselector is then placed at the highest au thorized altitude and the FGS will level off at each intermediate VNAV altitude Once lev eled off at the intermediate altitude FLC will arm indicating there is another climb Passing the altitude...

Page 383: ...dis plays the current navigation sources used by the FMS to determine current position Fig ure 16 90 The PROGRESS page shows a label on the bottom titled NAVIGATION In this example the NAVIGATION area indi cates that the system is using VOR DME and GPS Should the GPS malfunction or lose its Receiver Autonomous Integrity Monitoring RAIM the GPS label would be removed from the NAVIGATION line If the...

Page 384: ...eives inputs from a graphical weather system FMS s database update unit and the pilot s Cursor Control Panel CCP Figure 16 91 The C90GTi uses a Database Unit DBU to update the IFIS information The DBU 5000 uses two USB ports located at the aft end of the pedestal Figure 16 92 Either port is used to update the FMS s E charts E maps graphical weather and or maintenance items Once the databases are l...

Page 385: ...T 1 4 FMC 1 BRT DIM DIRECT PLANT2 452 SEC FPLN COPY ACTIVE VIA ROUTE DIST ORIGIN KICT FPLN ACT FMC 2 MFD ICT KAPA 452 KDEN PERF INIT TO ORIG RWY ALTN DEST DIST 1 4 CDU ETHERNET ETHERNET TS E CHAR FSU 5010 ETHERNET TS FSU 5010 CDU CMU 4000 LOAD A A LOADER T TA DA AT CMU 4000 LOADER GWX E MAPS TS E CHARTS RIU 40X0 CMU 4000 VHF COMMUNICA RIU 40X0 OR CMU 4000 RF LINK ETC HF F ETC F F HF TION SYSTEM IC...

Page 386: ...o the stored settings Enhanced Maps E MAPS The IFIS system contains Collins provided data with certain enhanced map features These include geographic political boundaries airspace and airways high and low The following menu selection may also con tain a MAP SOURCE option This is not re lated to the IFIS installation but is active with a dual FMS conﬁguration Either FMS can be chosen to display the...

Page 387: ...8 DAYS GEO POLITICAL DOWNLOAD AS REQUIRED GRAPHICAL WX DATABASE DOWNLOAD AS REQUIRED FMC 2 DATALOADER MAINTENANCE DIAGNOSTIC COMPUTER MDC HAWKER BEECHCRAFT MFD CHECKLIST DOWNLOAD AS REQUIRED SIMULTANEOUS FLIGHT MANAGEMENT COMPUTER FMC COLLINS FMS NAV DATABASE DOWNLOAD 28 DAYS Figure 16 95 CCP Figure 16 96 MFD Store Complete Collins PUSH S EL EC T MENU ADV DATA MENU ESC STAT MEM 1 MEM 2 MEM 3 CHART...

Page 388: ...Airspace option will allow turning the overlay ON or OFF Figure 16 98 Figure 16 98 Airspace Overlay The airway feature will superimpose all the se lected airways on top of the current MFD map to help orient their positions Only the airway is labeled and not the intersections Once the airway is loaded in the FMS the intersection names will appear for that airway only This overlay is accessed by pre...

Page 389: ...V 3 V140 V 3 5 4 V 7 4 7 V 7 7 V 7 7 V190 V7 7 53 2 V7 7 53 2 V7 7 V12 V12 V350 V350 V354 V354 V12 V77 V77 V12 V 5 3 2 V10 234 V502 V132 V280 V234 V 5 3 2 V 5 3 2 V 7 3 V 7 3 V280 V280 V 7 4 V190 256 V256 V190 V190 V 7 4 V 7 3 2 5 6 V 7 3 V7 7 53 2 TFC MAP MENU MAP SOURCE FMS1 FMS2 GEO POL OFF ON AIRSPACE OFF ON AIRWAYS OFF HI LO GS 0 Collins BRT DIM RDR TERR TFC DATABASE EFFECTIVITY FMS 1 NAV 11 ...

Page 390: ...to choose the desired chart Figure 16 103 MFD Chart Display Choosing the desired chart is accomplished by ﬁrst pressing the CHART key and then the MENU key on the CCP Figure 16 104 The CHART Main index is divided into the fol lowing areas Origin Destination Alternate Other airport Only the OTHER AIRPORT can be changed from this page All other air port identiﬁers are retrieved from the FMS ﬂight pl...

Page 391: ...n the MFD bezel Figure 16 105 MFD Chart Approach Index Charts that have been manually selected will show in cyan To exit out of the menu press the CCP ESC key If the chart is geo referenced the aircraft po sition and orientation will be displayed using a magenta aircraft icon This indicates that the latitude longitude positions on the chart agree with the GPS coordinate system known as WGS 84 When...

Page 392: ...onditions After a chart is displayed it can be changed using the procedures described earlier or using the DATA knob shortcut By rotating the DATA knob clockwise or counterclock wise all the charts linked for the current air port can be viewed without having to navigate to the Chart Main Index For instance if the ILS Rwy 29R for KBJC is in view from Fig ure 16 108 one click counterclockwise will d...

Page 393: ...an be displayed only on the dedicated weather for mat To overlay NExRAD on the PLAN Map format ﬁrst choose the PLAN Map format then press MENU on the CCP Figure 16 109 The USA NExRAD option allows for NExRAD radar overlay to be turned ON or OFF This overlay depicts the FMS course along with NExRAD returns to help antici pate radar returns along the route of ﬂight The age of NExRAD information is d...

Page 394: ...The NATIONAL METerological REPORTS are also text only and are chosen with the PUSH SELECT knob Figure 16 111 MFD XM Weather Menu Figure 16 112 MFD Metar Display Collins TAS SAT GS ISA 0 0 13 o C 15 o C BRT DIM LOWER FORMAT PPOS PLAN GWX FORMAT 0 0 0 ITT 26 TORQ 0 FF PRESS OIL TEMP o C 0 0 46 430 120 73 N I 98 5 PROP 1980 TORQ 2000 ITT 734 AFX FIRE Collins BRT DIM GRAPHICAL WEATHER TAF METAR REPORT...

Page 395: ... SIGMET will choose the display of outlined boxes to display areas of SIGMET weather conditions to include Con vective SIGMETs A C FLIGHT INFO will display the aircraft symbol and FMS gener ated origin and destination airports but will not display the FMS course line LIGHT NING will allow the display of lightning bolt symbols in areas of electrical discharge This last feature is not connected to a...

Page 396: ...M3 VHF transmissions that are requested from the pilot through an additional CDU page The COM3 system is not connected to the audio panels or audio controls in the cockpit Optionally the CMU unit is capable of datalink communica tions e g ACARS or AFIS using an HF SATCOM and or VHF radio The Universal weather provider is a request only system Each weather image or weather data is ﬁrst requested by...

Page 397: ... BRT DIM DEP ARR PERF LEGS FPLN DIR MSG TUN IDX MFD MENU A B C D F G H I J K L M O P Q R T U V X Y Z SP E N S W 1 2 3 4 5 6 7 8 9 0 DL REQ GRAPHICAL WX WEATHER RCVD Figure 16 117 Datalink Weather Selections Universal Weather EXEC NEXT PREV MFD DATA MFD ADV CLR DEL BRT DIM DEP ARR PERF LEGS FPLN DIR MSG TUN IDX MFD MENU A B C D F G H I J K L M O P Q R T U V X Y Z SP E N S W 1 2 3 4 5 6 7 8 9 0 DL W...

Page 398: ...chosen from the LOWER FORMAT line select key on the MFD by choosing the GWx selection Figure 16 119 This format is used for NExRAD and all other Universal weather images The image that appears will be the last viewed weather image To change the selection press the CCP MENU key to display the Universal weather menu page Figure 16 120 The menu is or ganized with the most recently received image at t...

Page 399: ...ay be tuned using either the RTU or the CDU Should the RTU become inoperable tuning the No 1 radios COM1 NAV1 ADF1 etc will not be possible If the CDU should be come inoperable tuning the No 2 radios COM2 NAV2 ADF2 etc will not be possi ble Moving the RTU CDU TUNE switch to the operating unit CDU or RTU will return full tuning capability If the RTU is the only unit still operating selecting RTU wi...

Page 400: ...antenna is mounted on the top of the fuselage while the COM 2 antenna is mounted on the lower fuselage Figure 16 123 VHF Navigation System One NAV 4000 and one NAV 4500 navigation receivers NAV 1 and NAV 2 provide VOR and Localizer navigation capabilities in the frequency range of 108 00 through 117 95 MHz in 25 kHz increments The NAV 4000 also con tains the ADF receiver As an option the air craft...

Page 401: ...eacons NDBs As mentioned in theVHF Navigation section the ADF is part of the NAV 4000 unit and does not have a separate line replaceable unit LRU Magnetic bearing to NDB sta tions is displayed on the PFD and MFD with selectable bearing pointers ADF receivers are tuned using the CDU tune page or the RTU The ADF antenna is mounted on the lower fuselage A second ADF receiver is optional Distance Meas...

Page 402: ...es AUDIO SYSTEM The all digital audio system manages the com munication and navigation systems An audio control panel adjacent to each pilot s PFD en ables individual audio control Figure 16 129 A press to transmit PTT button on the out board horn of each control wheel facilitates communication transmissions A microphone jack on each sidewall allows connection of headset microphones Two speakers i...

Page 403: ...ol the volume of the associated radio Pushing the knob in turns the audio off and pulling it out turns it on These controls are independent of AUTO COMM operation Rotating the knob adjusts the volume COMM 1 Controls the COM 1 audio volume 2 Controls the COM 2 audio volume NAV 1 Controls the NAV 1 audio volume 2 Controls the NAV 2 audio volume DME 1 Controls the DME 1 audio volume 2 Controls the DM...

Page 404: ...ING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS Figure 16 130 Audio System Components Push to Talk Button Hand Mic and Headset Connection Speakers one on each side Figure 16 129 Audio Panels ...

Page 405: ...SPKR Controls the on side cockpit overhead speaker VOICE BOTH IDENT Controls the NAV audio ﬁlter VOICE Removes morse code identiﬁcation and allows only voice communications on the NAV audios BOTH Voice communications and Morse code identiﬁcation are both heard on the NAV audios IDENT Only Morse code identiﬁcations are audible on the NAV audios AUDIO Controls reversionary operation of the on side a...

Page 406: ...e quency in the recall position white color fre quencies and then swapping the active and recall frequencies by pressing the recall line se lect key Preset Tuning Preset tuning i e stored frequencies is en abled when the TUNE MODE on the COM PRESET PAGE is set to PRESET The tuning knobs are then used to select the desired pre set memory number instead of tuning a fre quency Figure 16 133 Line Sele...

Page 407: ...he COM preset page allows for storing known frequencies Once they are entered the RTU preset tuning option can be activated and frequencies are chosen simply by select ing the memory number rather than tuning the frequency In this preset tuning mode however only the active frequency on the RTU top level page can be tuned directly if ATC gives a different frequency to contact NAV Operation The NAV ...

Page 408: ... page provides tuning functions for the ADF radio Other ADF control functions are handled on the ADF main display page and ADF preset page The active frequency can be tuned from the ADF section of the top level page and both the active and the recall frequencies can be tuned from the ADF main display page The ADF or ANT modes BFO feature ADF self test and ADF preset page access are con trolled fro...

Page 409: ...ws the selected transponder code IDENT Line Select Key and Annunciation The IDENT line select key controls the transponder IDENT function The IDENT an nunciation enlarges and changes to cyan during ident functions approximately 18 seconds Altitude Source Annunciator When Mode C is enabled the altitude data source ADC 1 or ADC 2 is shown in cyan below the altitude readout Mode C Control The ALT lin...

Page 410: ...ill then swap the frequencies If a frequency is inserted in the ﬁrst line it will immediately be the active frequency and the previous one will move to the second line For all frequencies the deci mal is assumed and does not need to be in serted e g 123 4 can be entered as 1234 Additionally the active frequencies are always identical between the RTU and CDU Use caution when working with the standb...

Page 411: ...ing is accomplished by insert ing the nav frequency in the scratchpad and then touching the appropriate NAV1 or NAV2 line select key Additionally the nav radio identiﬁer can be typed into the scratch pad and selected by touching the NAV line select key The CDU tuning will search the nearest fre quency associated with that identiﬁer and enter it along with the nav frequency Addi tionally the active...

Page 412: ...ct key the scratchpad must be empty Figure 16 143 From here the ADF can be tuned Beat Frequency Oscillator BFO can be turned ON or OFF the mode selected or the ADF can be tested The BFO selection should only be used for an NDB that cannot produce a typical Morse code identi ﬁer The ANT mode provides only an audio output and does not create bearing to the sta tion signals The bearing pointer will p...

Page 413: ...system is accomplished by pressing the GND COM switch This switch does not have a timer and will remain selected unless turned off or the battery is turned on or the Battery Bus switch is turned off Figure 16 144 GND COMM Button Static Discharging A static electrical charge builds up on the sur face of an airplane while in ﬂight and causes interference in radio and avionics equipment operation The...

Page 414: ...ll prevent its display on the SFDS Adjustment Knob The Adjustment knob on the bezel of the SFDS is used to set the barometric pressure setting or make selections within a menu Pushing the knob selects standard pressure or selects the highlighted item on the menu when the menu is displayed Additionally the HP IN button on the display bezel allows for a quick change between inches and hectopascals S...

Page 415: ...ion the NAV data will be removed to de clutter the display The data will be removed when roll attitude exceeds 65 left or right bank or the pitch attitude exceeds 20 nose down or 30 nose up The SFDS AHRS gener ates this information ROLL Aircraft roll attitude is depicted through the use of a sky pointer type roll pointer and roll scale A rectangular shaped slip skid indicator is located below the ...

Page 416: ...n wheels However once on the ground the radar can be turned ON again by reselecting a desired mode Test Mode TEST The system self test is initiated by selecting the TEST mode of operation A test pattern made up of six rainbow like arcs show on the dis play s when the TEST mode is active Figure 16 149 Figure 16 149 Test Mode Map Mode MAP The MAP mode allows the weather radar to provide the most det...

Page 417: ...2 or 3 Use caution when selecting a setting other than NORM as this will change the purpose of the standard radar colors i e a green area may actually be yellow or red in NORM setting and should be avoided Once the GAIN has been set it will appear next to the RDR label on the PFD or MFD Figure 16 152 Figure 16 152 Radar Gain Display Collins BRT DIM FMS DTK 251 6935 TTG 0 8NM 251 W 3 0 24 21 TAS SA...

Page 418: ...nob selects au tomatic antenna tilt control The letter A ad jacent to the tilt angle indicates that auto tilt is selected The auto tilt function compensates for airplane altitude changes and range changes by adjusting the tilt angle to maintain the selected reference to ground This will cause the tilt number to change when climb ing or descending or changing the range RANGE Knob The RANGE knob con...

Page 419: ...ility of aircraft power The ability of the ELT to transmit on 406 MHz re quires that the ELT be activated with the Na tional Oceanic and Atmospheric Association NOAA as the beacon provides a unique identiﬁer code traceable to a speciﬁc aircraft and operator The registration is free good for two years and can be done on line at www beaconregistration noaa gov The remote switch located on the left h...

Page 420: ...PULL UP PFD message Figure 16 157 Each caution and warning is also accompanied by an aural com mand as shown in the following table This portion of the TAWS system is solely related to the radio altimeter If the radio altimeter were to fail an appropriate TAWS annuncia tor would appear on the PFDs indicating that the basic ground proximity modes are inoper ative Figure 16 158 Figure 16 157 PFD GND...

Page 421: ...d directly in front of the pilot between the pilot s PFD and the MFD Figure 16 159 These push buttons allow the pilot to desensi tize the following listed modes and to remove the enhanced ground proximity feature when necessary FOR TRAINING PURPOSES ONLY 16 88 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS Table 16 1 BASIC CAUTIONS AND WARNINGS Mode Function PFD Caution Message Aural Cau...

Page 422: ... to transport data to the aircraft A series of lights on the unit will indi cate successful or unsuccessful loading Terrain display can be selected manually at any time Areas of terrain sufﬁciently close to the airplane that do not penetrate the terrain caution or warning envelopes are depicted by 16 89 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS Table 16 2 ...

Page 423: ... aural alert will occur when the aircraft position arrives at the TAL arc Figure 16 161 Terrain Advisory Line TAL Another TAWS feature uses a generic per formance model to alert the pilot in situations where the terrain cannot be climbed over In stead of the usual PULL UP PULL UP call outs the aural alert will be AVOID TERRAIN AVOID TERRAIN This indi cates a maneuver other than a straight ahead cl...

Page 424: ...er functioning of the en hanced features of the TAWS system 1 TAWS Warning Computer 2 Heading from the No 1 Compass System 3 GPS position 4 Terrain and Airport Data Base 16 91 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS Table 16 3 ENHANCED CAUTIONS AND WARNINGS Mode Function PFD Caution Message Aural Caution PFD Warning Message Aural Warning Terrain Alerting...

Page 425: ...in a 35 nm radius in the same way ground based radar interrogates air craft transponders When the SKY899 receives replies to its interrogations it computes the re sponding aircraft s range relative bearing rel ative altitude and closure rate The SKY899 then predicts collision threats and plots the eight most threatening aircraft locations The display of trafﬁc can be selected on the MFD by pressin...

Page 426: ...t This is accompanied by the aural alert TRAFFIC TRAFFIC Addition ally the PFD will annunciate a ﬂashingTRAF FIC below the attitude indicator Collins BRT DIM 10 10 20 HDG PTCH ALTS 14000 6 60 540 20 400 600 700 1 2 4 4 2 1 30 16IN PRESET VOR1 FORMAT FMS1 DTK 251 6935 0 8NM 25 251 W 3 0 24 21 ATC1 UTC RAT COM1 COM2 121 800 4336 125 250 14 41 15 o C 140 80 60 6935 RDR TERR ET TERM F 50 ACC 02 TERRAI...

Page 427: ...titude as your aircraft 00 is displayed above the trafﬁc symbol Four altitude display modes are available Look up Mode ABOVE Displays trafﬁc detected within 9 000 feet to 2 700 feet of your airplane Normal Mode blank Displays trafﬁc detected within 2 700 feet of your airplane Look down Mode BELOW Displays trafﬁc detected within 2 700 feet to 9 000 feet of your airplane Unrestricted Mode ABOVE BELO...

Page 428: ...ENDIX A AVIONICS EQUIPMENT LOCATIONS Figure 16 166 Overview of Avionics Units Aft Avionics Air Cell Satellite Phone CVR ELT FSU TCAS I Transponder 1 2 Universal Weather COMM 3 and CMU XM Weather Nose Avionics ADC 1 2 COMM NAV DME 1 2 GPS 1 2 IAPS Standby Battery Weather Radar Mid Avionics AHRS ...

Page 429: ...16 96 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS INTENTIONALLY LEFT BLANK ...

Page 430: ... Tracks the selected VOR course from the selected NAV radio with a VOR frequency tuned Annunciates VOR1 or VOR2 as appropriate to the selected radio Localizer Lateral Naviga tion NAV LOC1 LOC2 LOC1 LOC2 Tracks the selected Localizer course from the selected NAV radio with a localizer frequency tuned Annunciates LOC1 or LOC2 as appropriate to the selected radio FMS Approach APPR APPR FMS APPR FMS1 ...

Page 431: ...l speed is annunciated adjacent to VS Flight Level Change FLC FMS FMS1 FMS2 FLC 160 Maintains the Indicated Airspeed at the time the mode is se lected Can be adjusted with the SPEED Knob or the SYNC button Selected speed is annunciated adjacent to FLC Altitude Hold ALT VOR1 VOR2 ALT Maintaining an altitude other than the Preselected or VNAV alti tude Maintains the altitude present at the time the ...

Page 432: ...cent to VFLC Can be adjusted with the SPEED Knob or the SYNC button VNAV Altitude Hold ALT VNAV N A VALT Maintaining an altitude other than the Preselected or VNAV altitude Maintains the altitude present at the time the mode is selected Can be adjusted with the SYNC button VNAV Preselected Altitude Hold VNAV ALTS VALTS Preselected altitude is being maintained or will be maintained if armed with VN...

Page 433: ...16 100 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS INTENTIONALLY LEFT BLANK ...

Page 434: ...t Unit CPL Couple CVR Cockpit Voice Recorder CW Clockwise D DBU Database Unit DCP Display Control Panel DCU Data Concentrator Unit E E Chart Electronic Charts E Maps Enhanced Maps EDC Engine Data Concentrator EFIS Electronic Flight Instrument System EGPWS Enhanced Ground Proximity Warning System EIS Engine Indicating System F FD Flight Director FGC Flight Guidance Computer FGP Flight Guidance Pane...

Page 435: ...oice M MCDU Maintenance Control Display Unit MDC Maintenance Diagnostic Computer MFD 1 Multifunction Display MFD 2 Multi Function Display MFD 3 Multifunctional Flight Display N NDB Non Directional Beacon O P PA Passenger Address PFD Primary Flight Display PTT Press to Talk Q R RA Resolution Advisory RAT Ram Air Temperature RIU Radio Interface Unit RSS Radio Sensor System RTU Radio Tuning Unit S SA...

Page 436: ...FOR TRAINING PURPOSES ONLY 16 103 U USTB Unstabilized Weather Radar UV Upper Sideband Voice V W X Y Z KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 16 AVIONICS ...

Page 437: ......

Page 438: ... ROCKWELL COLLINS WAAS FMS Version 4 0 16A 12 Select SBAS Provider 16A 13 Load LPV Approach 16A 13 Failure of SBAS During LPV Approach 16A 15 Load LNAV VNAV or LNAV Approach 16A 17 Failure of SBAS During LNAV VNAV Approach 16A 18 Load LNAV VNAV Approach with WAAS Rare 16A 19 Load Non GPS Approach 16A 20 Navigation Integrity 16A 21 RAIM Prediction 16A 22 ROCKWELL COLLINS FMS DIFFERENCES 16A 23 16A ...

Page 439: ......

Page 440: ... 16A 12 VNAV Flag 16A 9 16A 13 Changing VNAV Guidance 16A 10 16A 14 PFD Annunciations Non SBAS 16A 11 16A 15 Loss of Nonprecision Approach RAIM 16A 11 16A 16 Select SBAS Provider 16A 13 16A 17 LPV Approach 16A 13 16A 18 Failure of SBAS During LPV Approach 16A 15 16A 19 Load LNAV VNAV or LNAV Approach 16A 17 16A 20 RAIM Failure after SBAS Failure 16A 18 16A 21 LNAV VNAV Approach with WAAS 16A 19 16...

Page 441: ......

Page 442: ...TABLE Table Title Page 16A 1 Loss of Integrity 16A 3 16A v FOR TRAINING PURPOSES ONLY KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM ...

Page 443: ......

Page 444: ... CHAPTER 16A WIDE AREA AUGMENTATION SYSTEM WAAS GENERAL Two forms of correction have been imple mented to achieve this goal Ground based Augmentation Systems GBAS and Satellite based Augmentation Systems SBAS GBAS uses towers in the vicinity of an airport that correct the GPS signal locally and send the cor rection message back to the aircraft using VHF radios The special equipment require ments f...

Page 445: ...se the SBAS system in Collins equipped aircraft This FMS is used with a SBAS capable receiver labeled GPS 4000S The FMS uses the corrected signal to create appropriate vertical and lateral navigation dis plays during all phases of flight to include WAAS approaches SBAS and other software equipment upgrades are included with FMS v4 0 and this addendum will highlight the most critical Refer to the a...

Page 446: ... SBAS units after SBAS has failed The aircraft position will not be as accurate but is still well within the boundaries of standard RNAV operations If the RAIM error gets too large the FMS will post the LOSS OF IN TEGRITY message as previously discussed DEPARTURES During RNAV departures CDI deflection val ues will match the navigational performance requirements of the procedure US RNAV de partures...

Page 447: ... the CDI will be 1nm for the en tire procedure This will be annunciated as TERM on the PFD Navigational integrity and messages on the CDU PFD and MFD are the same as dis cussed in the Departures section APPROACHES The most significant changes for the Collins FMS v4 0 will be in the approach phase of flight The FMS is now capable of flying RNAV GPS or RNAV GNSS approaches to the Localizer Performan...

Page 448: ...or LNAV minimums since these do not require SBAS The SBAS Service Providers page does not have a default selection and once the appro priate SBAS is enabled it will remain that way for every flight Loading The Approach The DEP ARR key is used to load a SBAS ap proach The instrument approach listing is la beled APPROACHES and the visuals are labeled RUNWAYS Figure 16A 4 The FMS is able to load mult...

Page 449: ...uidance It must be un derstood that this label does not indicate the actual navigation integrity available but is only database information Pressing the Execute key will load the ap proach into the active flight plan Colors for the selected approach are the same before and after the execute key is pressed Arrival Data Page The ARR DATA line select key is a shortcut to the Active Arrival Data page ...

Page 450: ...d from the FMS database and indicates which SBAS provider must be enabled as discussed earlier in this section Approach VNAV Selection Before discussing approaches it is necessary to review Collins vertical navigation Non SBAS FMS units accomplish VNAV by using barometric inputs baro VNAV from the altimeter system This is used during enroute and terminal operations It is also used on LNAV VNAV app...

Page 451: ...cator snowflake may appear to move suddenly when transitioning from baro VNAV to LPV VNAV and more time is needed to be established on glidepath before crossing the Final Approach Fix FAF If VNAV is already selected on the flight guid ance panel the aircraft will smoothly increase or decrease the rate of descent as required to center the new LPV glidepath Once LPV APPR is annunciated lateral and v...

Page 452: ...xecuting a missed approach USE LNAV MINIMUM will appear only if the approach has an LNAV minimum published For approaches that do not have LNAV mini mums published an APPR NOTAVAILABLE message will appear and a missed approach must be flown If the label LPVAPPR was already present on the PFD this label will remain even though the integrity is degraded The amber messages must be acknowledged and th...

Page 453: ...6A 14 Additionally LPV NOT AVAILABLE and USE LNAV MINIMUM messages will be removed from the displays and the CDU message page After the FAF If SBAS guidance fails after the FAF the descent may be continued to the LNAV minimum or a missed approach can be flown If a descent is continued it can only be done using VS FLC or PTCH mode since baro VNAV is not selec table at this point and VNAV deviation ...

Page 454: ...area with an approach loaded NPA NonprecisionApproach The FMS must not be used as primary navigation with this message ac tive Figure 16A 15 Additionally if a LOSS OF INTEGRITY message posts at any time be fore or during an approach the approach must be abandoned and the FMS must no longer be used as primary navigation KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM 16A ...

Page 455: ...KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM 16A 12 FOR TRAINING PURPOSES ONLY QUICK REFERENCE ROCKWELL COLLINS WAAS FMS VERSION 4 0 ...

Page 456: ...propriate provider is not chosen a CHK SBAS SVC PRVDR message will appear on the CDU message line when loading an LPV approach If no SBAS providers are chosen the FMS will not use augmented signals LOAD LPV APPROACH Procedures for loading an LPV approach are the same as loading a non LPV approach Figure 16A 17 Sheet 1 of 2 1 Confirm desired airport is in ORIGIN or DESTination on the active flight ...

Page 457: ...7 sheet 2 of 2 The PFD will display LPV APPR in green after passing the Final Approach Course Fix FACF if the SBAS system is operational Baro VNAV is used up until LPV APPR is an nunciated at which time GPS corrected VNAV LPV VNAV will be used for the remainder of the approach A slight jump in the vertical deviation indicator may be noticeable during this transition Baro VNAV temperature restricti...

Page 458: ...s will appear on the CDU a LPV NOT AVAILABLE b Also if LNAV minimums are pub lished USE LNAV MINIMUM 2 If LNAV minimums are published this message will appear on the MFD a USE LNAV MINIMUM 3 An amber MSG will flash on the PFD 4 The VNAV deviation will have a red VNV flag with the deviation indicator removed KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM 16A 15 FOR TRAIN...

Page 459: ...l appear on the CDU a LPV NOT AVAILABLE b Also if LNAV minimums are pub lished USE LNAV MINIMUM 2 If LNAV minimums are published this message will appear on the MFD a USE LNAV MINIMUM 3 An amber MSG will flash on the PFD Figure 16A 18 Sheet 3 of 3 4 The VNAV deviation will have a red VNV flag with the deviation indicator removed 5 Depending on aircraft altitude aircraft may be descended with non V...

Page 460: ...P to en sure proper information 5 EXECute after confirmation The PFD will display TERM in white when within 31nm of the desired airport The PFD will display GPS APPR in green when within 2nm of the FAF Baro VNAV is used for the entire procedure Baro VNAV temperature restrictions apply to LNAV VNAV minimums KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM 16A 17 FOR TRAINI...

Page 461: ...airport Figure 16A 20 1 If RAIM is insufficient for the approach this message will appear on the CDU a NO NPA RAIM 2 An amber MSG will flash on the PFD 3 Accomplish a non GPS approach as per AFM or AFM supplement NOTES KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM 16A 18 FOR TRAINING PURPOSES ONLY EXEC MSG ACT LEGS KICT 1 6 SEQUENCE LEG WIND AUTO INHIBIT ICT WUKOL MUGE...

Page 462: ... capability 4 Verify LEGS page or MFD MAP to en sure proper information 5 EXECute after confirmation The FMS will use any available SBAS provider for lateral navigation The PFD will display L V TERM in white when within 31nm of the desired airport The PFD will display L V APPR in green when within 2nm of the FAF The FMS will use baro VNAV until the FACF and then transition to SBAS VNAV just like L...

Page 463: ...will be using baro VNAV It is NOT real time display of system capability 4 Verify LEGS page or MFD MAP to en sure proper information 5 EXECute after confirmation A NO APPR label will appear on the PFD An APPR FOR REF ONLY will appear on the CDU Verify AFM or AFM supplement limitations for navigation guidance requirements NOTES KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYS...

Page 464: ...ty message and will appear whether SBAS is being received or not Figure 16A 23 1 A LOSS OF INTEGRITY message will appear on the CDU 2 A LOI or LOI TERM will appear on the PFD depending on the 31nm distance from the airport 3 Use another source of navigation NOTES KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATION SYSTEM 16A 21 FOR TRAINING PURPOSES ONLY Figure 16A 23 Navigation In...

Page 465: ...ght plan destination airport 4 Enter satellites that have been NOTAM d out of service in the dese lect option in L3 5 The ETA will automatically be filled when inflight or it can be manually en tered in R2 i e when still on the ground These are the possible outcomes of approach RAIM prediction AVAILABLE UNAVAILABLE REQ PENDING NOTES KING AIR 90 SERIES PILOT TRAINING MANUAL 16A WIDE AREA AUGMENTATI...

Page 466: ...e EGNOS Japan MSAS India GAGAN VNAV Enroute Terminal Uses Baro VNAV only 500 FT Approaches LPV minimums WAAS only Angular LNAV VNAV minimums Baro VNAV 250 FT WAAS when FAA certified Angular LNAV minimums Baro VNAV only 250 FT RNAV SID RNAV STAR 1nm CDI for entire procedure TERM 1nm CDI when off procedure within 31nm of ARPT 2nm CDI when off procedure outside 31nm of ARPT RAIM prediction only when ...

Page 467: ......

Page 468: ...n Duration 17 6 Oxygen Duration Computation 17 6 Time of Useful Consciousness 17 7 PHYSIOLOGICAL TRAINING 17 8 What Is It 17 8 Who Needs It 17 8 Where Can You Get It 17 8 How Long is the Course 17 8 What Is Contained in the Course 17 8 What Are the Prerequisites for Training 17 9 How Do You Apply For Training 17 9 How Can You Get Further Information 17 9 FOR TRAINING PURPOSES ONLY KING AIR C90GTi ...

Page 469: ...OXYGEN SYSTEM 17 9 Filling the Oxygen System 17 10 Oxygen Capacity 17 10 Oxygen Cylinder Retesting 17 10 QUESTIONS 17 11 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 17 ii FOR TRAINING PURPOSES ONLY 17 OXYGEN SYSTEM ...

Page 470: ...7 4 17 5 Oxygen System Control Handle 17 4 17 6 Oxygen Pressure Gage 17 4 17 7 Oxygen Fill Valve and Gage 17 5 17 8 Percent of Usable Oxygen Capacity 17 6 17 9 FAA Altitude Chamber 17 8 TABLES Table Title Page 17 1 Oxygen Duration Minutes 17 7 17 2 Time of Useful Consciousness 17 7 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 17 OXYGEN SYSTEM ...

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Page 472: ...en duration chart involves working simulated problems under vari ous flight conditions FAR requirements for crew and passenger needs are part of the discussion as well as the types and availability of oxygen masks Local servicing procedures referenced in the Pilot s Operating Handbook are also included OXYGEN SYSTEM Current FARs require that anytime an air craft flies above 25 000 feet oxygen must...

Page 473: ... OXYGEN SYSTEM LEGEND HIGH PRESSURE LINES LOW PRESSURE LINES PRESSURE GAGE CREW MASKS OUTLET FOR COPILOT DILUTER DEMAND MASK INSTALLATION CABIN OUTLETS PUSH PULL CONTROL FILLER VALVE SUPPLY PRESSURE GAGE NOTES AVIATORS BREATHING OXYGEN KEEP FILL AREA CLEAN DRY FREE FROM OIL PRESSURIZED TO ___ PSI 14 7 PSI 70OF 1800 WHEN 22 CU FT CYLINDER IS USED 1850 WHEN 49 OR 66 CU FT CYLINDER IS USED PRESSURE R...

Page 474: ...ad and one hangs from a bracket behind the copi lot s head Passenger masks are kept in seatback pock ets except in the couch installation in which case they are stored under the couch The cabin outlets are located at both the forward and aft ends of the cabin All masks are easily plugged in by pushing the orif ice in f irmly and turning clockwise approximately one quarter turn Unplug ging is easil...

Page 475: ...gen supply is available anywhere in the airplane When this control is pulled out the oxygen system is charged with oxy gen ready for use provided the oxygen sup ply cylinder is not empty The oxygen supply pressure gage is located in the copi lot s right subpanel Figure 17 6 KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 17 4 FOR TRAINING PURPOSES ONLY 17 OXYGEN SYSTEM OXYGEN GAGE OXYGEN CYLINDER OXY...

Page 476: ...o hold the mask firmly in place Insert the fitting in one of the oxygen outlets in the overhead cavity push in firmly and turn clockwise approximately one quarter turn to lock it in place If oxygen is available the system is turned on and the oxygen cylinder charged the red flow indicator will move and the green portion will come into view The mix ing bag will inflate with breathing Breath normall...

Page 477: ...tion is for a Puritan Zep oxygen system which must use the red color coded plug in mask rated at 3 7 standard liters per minute normal temperature pressure SLPM NTPD flow Both aircraft are ap proved for altitudes up to 30 000 feet OXYGEN DURATION COMPUTATION In this sample computation oxygen dura tion is computed for a Puritan Zep oxygen system which utilizes the red color coded plug in mask rated...

Page 478: ...ess available at various alti tudes This is the time from the onset of hypoxia until loss of effective performance Individuals may differ from that shown in the table Using the Emergency Descent pro cedure in the Emergency Procedures sec tion of the POH a very rapid descent can minimize the exposure to hypoxia KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 17 7 FOR TRAINING PURPOSES ONLY 17 OXYGEN S...

Page 479: ...scussed so that the trainee will understand why a pilot cannot fly safely at altitudes in excess of 12 500 feet for a prolonged period without some aid either supplemental oxygen or a pressurized air craft Both oxygen equipment and pressur ization are discussed When humans are confronted with certain stressful situations there is a tendency to breathe too rapidly This topic hyperventilation and me...

Page 480: ...and one ad jacent to the filler valve for checking sys tem pressure during filling A shutoff valve and regulator on the cylinder control the flow of oxygen to the crew and passenger outlets The shutoff valve is actuated by a push pull control located aft of the over head light control panel in the cockpit The regulator is a constant flow type which sup plies low pressure oxygen through system plum...

Page 481: ...ic foot cylinders may be charged to a pres sure of 1 850 50 psi at a temper ature of 70 F When the system is properly charged disconnect the filler hose from the filler valve and replace the protective cap on the filler valve OXYGEN CAPACITY Oxygen for unpressurized high altitude flight is supplied by a cylinder in the com partment immediately aft of the pressure bulkhead see Figure 17 4 A 22 49 o...

Page 482: ... B At altitudes below 20 000 ft C At altitudes above 20 000 ft D Anytime there is smoke in the cock pit 3 The passenger masks are deployed A Automatically when the cabin alti tude exceeds 12 500 ft B By pulling the PASSENGER MAN UAL DROPOUT handle C Manually by the passengers D Automatically when the Oxygen sys tem is armed KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 17 11 FOR TRAINING PURPOSES O...

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Page 484: ...ISCELLANEOUS SYSTEMS CONTENTS Page INTRODUCTION 18 1 TOILET 18 2 RELIEF TUBES 18 2 EMERGENCY ABNORMAL 18 2 QUESTIONS 18 3 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 18 MISCELLANEOUS SYSTEMS ...

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Page 486: ...18 iii ILLUSTRATIONS Figure Title Page 18 1 Toilet 18 2 18 2 Relief Tube 18 2 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 18 MISCELLANEOUS SYSTEMS ...

Page 487: ......

Page 488: ...miscellaneous systems in the King Air C90GTi and C90GTx aircraft which include the toilet and relief tubes KING AIR C90GTi C90GTx PILOT TRAINING MANUAL CHAPTER 18 MISCELLANEOUS SYSTEMS 18 1 FOR TRAINING PURPOSES ONLY 18 MISCELLANEOUS SYSTEMS ...

Page 489: ...BES An optional relief tube is located in the cabin sidewall just forward of the toilet when in stalled Figure 18 2 A relief tube is also installed in the cockpit and stowed under the pilot seat The hose on the cockpit relief tube is long enough for use by either the pilot or copilot A valve lever is on the side of the relief tube horn The lever must be pressed at all times while the relief tube i...

Page 490: ...A At all times except when servicing the unit B At all times including when servicing the unit C Only when servicing the unit D Only when in actual use KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 18 3 FOR TRAINING PURPOSES ONLY 18 MISCELLANEOUS SYSTEMS QUESTIONS ...

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Page 492: ...19 1 LANDING 19 17 Flaps Up Approach and Landing 19 17 Single Engine Approach and Landing 19 17 Crosswind Approach And Landing 19 17 WINDSHEAR 19 17 General 19 17 Microbursts 19 18 Acceptable Performance Guidelines 19 18 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 19 MANEUVERS AND PROCEDURES ...

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Page 494: ...uration 19 8 19 8 Approach to Stall Approach Configuration 19 9 19 9 Emergency Descent 19 10 19 10 Visual Approach and Landing Normal 19 11 19 11 Visual Approach and Landing No Flap 19 12 19 12 Visual Approach and Landing One Engine Inoperative 19 13 19 13 ILS Approach Landing in Sequence from an ILS 19 14 19 14 Non Precision Approach Procedure Turn 19 15 19 15 Circling Approach and Landing 19 16 ...

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Page 496: ...procedures for normal takeoff except Transition to flight instruments at or before 100 feet AGL Obstacle Clearance Takeoff Follow procedures for normal takeoff except Maintain V2 until clear of obstacle FLIGHT PROFILES Specific flight profiles are graphically de picted on the following pages CHAPTER 19 MANUEVERS AND PROCEDURES 19 1 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING M...

Page 497: ...E ITT 2 ANNUNCIATORS CHECK 1 ROTATE AT VR TO APPROX 10 NOSE UP 2 ESTABLISH POSITIVE RATE OF CLIMB 3 LANDING GEAR UP 1 YAW DAMP ON 2 CLIMB 400 AGL 3 ACCELERATE TO 108 KIAS 4 FLAPS UP IF USED 5 CLIMB POWER SET 1 ACCELERATE TO 150 KIAS 2 LANDING TAXI LIGHTS OUT 3 COMPLETE CLIMB CHECKLIST AREA DEPARTURE CLIMB PROFILE 1 150 KIAS TO 10 000 FT 2 130 KIAS 10 000 20 000 FT 3 120 KIAS 20 000 25 000 FT 4 110...

Page 498: ... ALTITUDE 400 AGL OR HIGHER 2 AIRSPEED VYSE 3 FLAPS UP IF USED 4 YAW DAMP ON NOTE IT MAY BE NECESSARY TO BANK AS MUCH AS 5 INTO THE GOOD ENGINE TO MAINTAIN RUNWAY HEADING IT WILL TAKE ALMOST FULL RUDDER ON THE SIDE OF THE GOOD ENGINE TO KEEP THE BALL SLIGHTLY OFF CENTER NOTE DO NOT RETARD FAILED ENGINE POWER LEVER UNTIL THE AUTOFEATHER SYSTEM HAS COMPLETELY STOPPED PROPELLER ROTATION 1 POWER MAXIM...

Page 499: ...LLOW NORMAL TAKEOFF PROCEDURES UNTIL INITIATING ABORT AT OR BELOW VR 1 RECOGNIZE REASON FOR REJECTING TAKEOFF 2 POWER LEVERS GROUND FINE 3 BRAKING MAXIMUM OR AS REQUIRED 4 REVERSE AS NECESSARY 5 MAINTAIN RUNWAY HEADING 1 COMPLETE AFTER LANDING CHECKLIST NOTE IF REJECTED TAKEOFF IS DUE TO REASONS OTHER THAN ONE ENGINE POWER LOSS REVERSE IS MOST EFFECTIVE AT HIGH SPEEDS BRAKING IS MOST EFFECTIVE AT ...

Page 500: ...EFERENCE ROLL INTO TURN 1 MAINTAIN INITIAL ALTITUDE THROUGH 30 BANK 1 ADD APPROX 100 LBS TORQUE 2 ONE UNIT NOSE UP TRIM 3 SMALL PITCH INCREASE HOLD 45 BANK 1 SMALL PITCH CORRECTIONS 2 MAINTAIN AIRSPEED ROLL OUT OF TURN 1 REDUCE TORQUE 100 LBS 2 REDUCE PITCH 3 TAKE OUT TRIM 1 START ROLLOUT 25 PRIOR TO ROLLOUT HEADING 1 RETURN TO AND HOLD ENTRY PARAMETERS Figure 19 4 Steep Turns 19 MANEUVERS AND PRO...

Page 501: ...ITIAL ALTITUDE 5 PITCH ATTITUDE PRIOR TO HORN OR BUFFET MAY REACH 10 15 DEPENDING ON TECHNIQUE 6 HORN WILL SOUND APPROX 10 KNOTS ABOVE BUFFET AT HORN OR BUFFET RECOVER 1 SIMULTANEOUSLY ADVANCE THE POWER LEVERS TOWARD MAX TORQUE REDUCE THE PITCH ATTITUDE AS NECESSARY TO STOP THE STALL WARNING AND ROLL THE WINGS LEVEL 2 ESTABLISH POSITIVE RATE OF CLIMB COMPLETION 1 LEVEL OFF AT NEW ALTITUDE AND HEAD...

Page 502: ...ION 1 TORQUE 200 LBS 2 PROPELLERS 1 900 RPM 3 MAINTAIN INTITIAL HEADING 4 MAINTAIN INTITIAL ALTITUDE 5 FLAPS APPROACH BELOW TRIANGLE 6 AT 110 KIAS OR LESS SIMULTANEOUSLY SET THE TORQUE TO 700 LBS SIMULATED 100 TORQUE ESTABLISH A BANK ANGLE OF 20 NO MORE THAN 30 RAISE THE NOSE AND CLIMB 7 PILOT MAY BE REQUIRED TO PERFORM THIS MANEUVER WHILE MAINTAINING 15 30 ANGLE OF BANK OR WHILE MAINTAINING HEADI...

Page 503: ...ED FOR THE C90GTx WITH THE CENTEX SUPPLEMENT 1 SIMULTANEOUSLY ADVANCE THE POWER LEVERS TOWARD MAX TORQUE REDUCE THE PITCH ATTITUDE AS NECESSARY TO STOP THE STALL WARNING AND ROLL THE WINGS LEVEL 2 ESTABLISH POSITIVE RATE OF CLIMB 3 FLAPS APPROACH AT OR ABOVE 102 KIAS 4 GEAR UP 5 FLAPS UP 6 MINIMIZE LOSS OF ALTITUDE VYSE INITIAL CONDITION 1 TORQUE 600 LBS 2 PROPELLERS 1 900 RPM 3 MAINTAIN INTITIAL ...

Page 504: ...POSITIVE RATE OF CLIMB 3 FLAPS UP AT OR ABOVE VYSE BLUE LINE 4 GEAR UP COMPLETION 1 LEVEL OFF AT NEW ALTITUDE AND HEADING 2 RESET POWER AS REQUIRED VYSE INITIAL CONDITION 1 TORQUE 600 LBS 2 PROPELLERS 1 900 RPM 3 MAINTAIN INTITIAL HEADING 4 MAINTAIN INTITIAL ALTITUDE 5 FLAPS APPROACH BELOW TRIANGLE 6 GEAR DOWN BELOW VLE 7 FLAPS DOWN 100 BELOW TOP OF WHITE ARC 8 SLOWLY REDUCE TORQUE TO 200 LBS 9 PI...

Page 505: ... VLE MAINTAIN THE INITIAL ALTITUDE UNTIL THE IAS IS AT OR BELOW VLE 1 INITIAL PITCH ATTITUDE 14 NOSE DOWN 2 MAXIMUM IAS SHOULD BE VLE 3 ADVISE ATC 4 RESET ALTIMETER AND ALTITUDE ALERTER TO LEVEL OFF ALTITUDE 1 APPROXIMATELY 500 FT BEFORE LEVEL OFF ALTITUDE SMOOTHLY REDUCE RATE OF DESCENT 2 FLAPS UP 3 GEAR UP BELOW VLO RETRACTION 4 ADD POWER AS REQUIRED 5 REMOVE MASK 6 SET PROP RPM 7 COMPLETE DESCE...

Page 506: ...HECK DOWN 2 AIRSPEED VREF 3 POWER IDLE 4 PROPS FULL FORWARD REJECTED BALKED LANDING 1 POWER MAXIMUM ALLOWABLE 2 AIRSPEED 101 KIAS 3 FLAPS UP 4 GEAR UP 5 AIRSPEED CLEAR OF OBSTACLES NORMAL CLIMB CAUTION TO ENSURE CONSTANT REVERSING CHARACTERISTICS THE PROPELLER CONTROL MUST BE IN FULL INCREASE RPM POSITION NOTE REVERSE IS MOST EFFECTIVE AT HIGHER SPEEDS BRAKING IS MOST EFFECTIVE AT LOWER SPEEDS CAU...

Page 507: ... CONTROL MUST BE IN FULL INCREASE RPM POSITION NOTE REVERSE IS MOST EFFECTIVE AT HIGHER SPEEDS BRAKING IS MOST EFFECTIVE AT LOWER SPEEDS CAUTION IF POSSIBLE PROPELLERS SHOULD BE MOVED OUT OF REVERSE AT APPROXIMATELY 40 KNOTS TO MINIMIZE BLADE EROSION CARE MUST BE EXERCISED WHEN REVERSING ON RUNWAYS WITH LOOSE SAND DUST OR SNOW ON THE SURFACE FLYING GRAVEL WILL DAMAGE PROPELLER BLADES AND DUST OR S...

Page 508: ... FINAL 1 AIRSPEED 120 KIAS WHEN IT IS CERTAIN THERE IS NO POSSIBILITY OF A GO AROUND 2 FLAPS DOWN 3 TRANSITION TO VREF 4 YAW DAMP OFF 5 ONE ENGINE INOPERATIVE LANDING CHECKLIST COMPLETE 1 GROUND FINE OR REVERSE 2 BRAKES AS REQUIRED THRESHOLD 1 GEAR RECHECK DOWN 2 AIRSPEED VREF 3 POWER IDLE ONE ENGINE INOPERATIVE GO AROUND 1 POWER MAXIMUM ALLOWABLE 2 GEAR UP 3 FLAPS UP 4 AIRSPEED 108 KIAS LANDING N...

Page 509: ...AR RECHECK DOWN 2 AIRSPEED VREF 3 POWER IDLE 4 PROPS FULL FORWARD LANDING 1 GROUND FINE OR REVERSE 2 BRAKES AS REQUIRED DH MISSED APPROACH 1 POWER MAXIMUM ALLOWABLE 2 PITCH 10 NOSE UP 3 GEAR UP 4 FLAPS UP 5 AIRSPEED NORMAL CLIMB 6 COMPLETE MISSED APPROACH PROCEDURE GLIDE SLOPE INTERCEPT 1 TORQUE APPROX 600 LBS 2 120 KIAS VYSE MIN CAUTION TO ENSURE CONSTANT REVERSING CHARACTERISTICS THE PROPELLER C...

Page 510: ...LOWABLE 2 PITCH 10 NOSE UP 3 GEAR UP 4 FLAPS UP 5 AIRSPEED NORMAL CLIMB 6 COMPLETE MISSED APPROACH PROCEDURE MAP LANDING ASSURED 1 FLAPS DOWN 2 TRANSITION TO VREF 3 YAW DAMP OFF 4 NORMAL LANDING CHECKLIST COMPLETE THRESHOLD 1 GEAR RECHECK DOWN 2 AIRSPEED VREF 3 POWER IDLE 4 PROPS FULL FORWARD LANDING 1 GROUND FINE OR REVERSE 2 BRAKES AS REQUIRED CAUTION TO ENSURE CONSTANT REVERSING CHARACTERISTICS...

Page 511: ...ACH PROCEDURES TO MDA MINIMUM DESCENT ALTITUDE MDA 1 LEVEL OFF AT MDA AT LEAST 1 MILE PRIOR TO MAP IF POSSIBLE 2 TORQUE 800 1 000 LBS 3 120 KIAS VYSE 10 KT MIN 4 MANEUVER WITHIN VISIBILITY CRITERIA 5 MAINTAIN MDA MAP AND DURING CIRCLING MANEUVER 1 DETERMINE THAT VISUAL CONTACT WITH THE RUNWAY ENVIRONMENT CAN BE MAINTAINED AND A NORMAL LANDING CAN BE MADE FROM A CIRCLING APPROACH OR INITIATE A MISS...

Page 512: ...h the gear down CROSSWIND APPROACH AND LANDING Follow normal approach and landing proce dures except Crab into the wind to maintain the desired track across the ground Immediately prior to touchdown lower the upwind wing by use of the aileron and align the fuselage with the run way by use of the rudder During the rollout hold the aileron control into the wind and maintain directional con trol with...

Page 513: ...h sufficiently to depart the stall warning regime 4 When positively climbing at a safe altitude complete the rejected land ing maneuver NOTE The positive rate of climb should be verified on at least two 2 in struments Leave the gear down until you have this climb indica tion as it will absorb some energy on impact should the microburst exceed your capability to climb If a decision is made to rotat...

Page 514: ...20 WEIGHT AND BALANCE CHAPTER 20 WEIGHT AND BALANCE Please refer to the OEM Manual applicable to this particular aircraft ...

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Page 516: ...21 FLIGHT PLANNING AND PERFORMANCE CHAPTER 21 FLIGHT PLANNING AND PERFORMANCE Please refer to the OEM Manual applicable to this particular aircraft ...

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Page 518: ... Common Terms 22 3 Pretakeoff Briefing IFR VFR 22 3 Crew Coordination Approach Sequence 22 5 ALTITUDE CALLOUTS 22 8 Enroute 22 8 Approach Precision 22 8 Approach Nonprecision 22 9 Significant Deviation Callout 22 9 22 i KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 22 CREW RESOURCE MANAGEMENT ...

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Page 520: ... 22 2 22 2 Command and Leadership 22 2 22 3 Error Management 22 4 22 4 Communication Process 22 4 22 5 Decision Making Process 22 4 22 6 Crew Performance Standards 22 6 22 iii KING AIR C90GTi C90GTx PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY 22 CREW RESOURCE MANAGEMENT ...

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Page 522: ...TRAINING PURPOSES ONLY INTRODUCTION This chapter describes the crew resource management program Information is pro vided on the crew concept briefing guide and altitude callouts between pilots CHAPTER 22 CREW RESOURCE MANAGEMENT 22 CREW RESOURCE MANAGEMENT ...

Page 523: ...TRACTION 10 CONFUSION OR EMPTY FEELING 11 NEED TO HURRY LAST MINUTE CHANGES 12 FATIGUE PILOT MONITORING PM Events that may happen Events that have happened Events that are happening now PILOT FLYING PF COLLECTIVE S A SA SITUATIONAL AWARENESS IN THE COCKPIT Figure 22 1 Situational Awareness in the Cockpit LEADERSHIP STYLES VARY WITH SITUATION PARTICIPATION H G I H W O L Command Designated by Organi...

Page 524: ...ot flying and pilot not flying duties PF Pilot Flying Controls the airplane with respect to assigned runway course altitude airspeed etc during normal and emergency conditions Accomplishes other tasks as directed by the PIC PM Pilot Monitoring Maintains ATC communications copies clearances accomplishes checklists and other tasks as directed by the PIC B Both PRETAKEOFF BRIEFING IFR VFR NOTE The fo...

Page 525: ... achieved Be aware of barriers to communication COMMUNICATION PROCESS Figure 22 4 Communication Process HINTS Identify the problem Communicate it Achieve agreement Obtain commitment Consider appropriate SOP s Think beyond the obvious alternatives Make decisions as a result of the process Resist the temptation to make an immediate decision and then support it with facts EVALUATE RESULT ACCELERATED ...

Page 526: ...e approach setup PM Accomplishes the approach setup and advises of frequency tuned identified and course set PF Transfers control of the airplane to the PM advising You have control heading_____ altitude_____ and special instructions Communications duties should be transferred back to the PM at this point PM Responds I have control heading_____ altitude _____ PF Advises Approach Briefing PF At the...

Page 527: ... advocacy inquiry to maintain regain situational awareness g Recognizes error chain clues and takes actions to break links in the chain h Communicates objectives and gains agreement when appropriate i Uses effective listening techniques to maintain regain situational awareness a Establishes open environment for interactive communication b Conducts adequate briefings to convey required information ...

Page 528: ...g decisions and adjusts accordingly i Avoids making a decision and then going in search of facts that support it DECISION MAKING a Follows automation related SOPs b Specifies pilot and copilot duties and responsibilities with regard to automation c Verbalizes and acknowledges entries and changes in flight operation d Verifies status and programming of automation e Selects appropriate levels of aut...

Page 529: ...OGER level off altitude 200 above below LEVELING APPROACH PRECISION PM PF At 1 000 ft above minimums 1 000 feet above minimums DH ______ At 500 ft above minimums 500 above minimums CROSS CHECK NO FLAGS At 100 ft above minimums 100 feet above minimums outside At decision height Minimums Lights at ______ CONTINUE At 100 ft AGL Runway in sight VISUAL OR LANDING Speed Rate OR GO AROUND Minimums not in...

Page 530: ...ent altitude MDA Minimums CONTINUE At missed approach point MAP Missed Approach Point Lights at ______ CONTINUE VISUAL LANDING Speed Rate Missed Approach Point OR Runway not in sight GO AROUND SIGNIFICANT DEVIATION CALLOUT CHALLENGE RESPONSE PM PF IAS 10 KIAS VREF ______ CORRECTING TO ______ Heading 10 5 on approach Heading ______ degrees left right CORRECTING TO ______ Altitude 100 ft enroute 50 ...

Page 531: ...PURPOSES ONLY 22 CREW RESOURCE MANAGEMENT PM PF RMI course left or right 5 Left right of course ______ degrees CORRECTING Vertical descent speed greater than 1 000 fpm on final approach Sink rate ______ CORRECTING Bank in Excess of 30 Bank ______ degrees CORRECTING ...

Page 532: ...NUAL WALKAROUND NOTES The following section is a pictorial walkaround Each item listed in the exterior power off preflight inspection is displayed The foldout pages contain photographs that depict the specific area to be inspected The general photographs contain circled numbers that correspond to specific steps displayed on the subsequent pages ...

Page 533: ...R C90GTi C90GTx PILOT TRAINING MANUAL LEFT WING AND NACELLE 1 CABIN DOOR SEAL STEP EXTENSION CABLE LIGHT WIRE DAMPER AND HANDRAILS CHECK 2 CABIN WINDOWS CHECK 3 FLAPS CHECK 4 AILERON AND TAB CHECK 5 WING TIP AND LIGHTS CHECK 6 STALL WARNING CHECK 7 8 9 10 6 1 16 11 18 17 14 13 12 2 3 4 5 15 LEFT WING AND NACELLE ...

Page 534: ...FIRE EXTINGUISHER IF INSTALLED CHECK 16 ENGINE AIR INTAKES CLEAR 17 ENGINE OIL CHECK QUANTITY CAP SECURE LEFT WING AND NACELLE 10 OUTBOARD WING SUMP CHECK 9 WING FUEL TANK CHECK QUANTITY CAP SECURE 11 WHEEL WELL SUMP DRAIN 12 LANDING GEAR STRUT BRAKE WHEEL WELL AND LANDING GEAR DOORS CHECK 8 TIE DOWN AND CHOCKS REMOVE 7 DEICE BOOT CHECK LEFT WING AND NACELLE 18 FUEL STRAINER FIREWALL DRAIN ...

Page 535: ...NG AIR C90GTi C90GTx PILOT TRAINING MANUAL LEFT WING AND NACELLE LEFT WING AND NACELLE 23 22 20 21 19 19 COWLING DOORS AND PANELS SECURE 19 COWLING DOORS AND PANELS CONT SECURE 20 NACELLE FUEL TANK CHECK CAP SECURE 21 HEAT EXCHANGER INLET CLEAR 22 TRANSFER PUMP SUMP DRAIN 23 LOWER ANTENNAS AND BEACON CHECK ...

Page 536: ...RAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 2 BRAKE RESERVOIR VENT CLEAR 3 RAM AIR INLET CLEAR 1 OAT PROBE CHECK 4 LEFT AVIONICS ACCESS PANEL BAGGAGE DOOR SECURE 6 WINDSHIELD AND WIPERS CHECK 5 AIR CONDITIONER CONDENSER EXHAUST DUCT CLEAR NOSE NOSE 1 2 3 4 5 6 ...

Page 537: ...MANUAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 8 PITOT MASTS CLEAR 7 RADOME CHECK 10 NOSE GEAR SHIMMY DAMPER STOP BLOCK TORQUE KNEE STRUT TIRE CHECK 10 NOSE GEAR SHIMMY DAMPER STOP BLOCK TORQUE KNEE STRUT TIRE CONT CHECK 9 LANDING AND TAXI LIGHTS CHECK 11 CHOCKS REMOVE NOSE NOSE 7 8 8 9 10 11 ...

Page 538: ...0GTx PILOT TRAINING MANUAL WA 7 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 14 RIGHT AVIONICS ACCESS PANEL SECURE 13 AIR CONDITIONER CONDENSER INTAKE DUCT CLEAR NOSE 12 NOSE GEAR DOORS AND WHEEL WELL CHECK NOSE 13 14 12 ...

Page 539: ... KING AIR C90GTi C90GTx PILOT TRAINING MANUAL RIGHT WING AND NACELLE RIGHT WING AND NACELLE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 2 HEAT EXCHANGER INLET CLEAR 1 TRANSFER PUMP SUMP DRAIN 4 PROP CHECK 3 NACELLE FUEL TANK CHECK CAP SECURE 6 ENGINE OIL CHECK QUANTITY CAP SECURE 5 ENGINE AIR INTAKES CLEAR ...

Page 540: ...CURE 7 FUEL STRAINER FIREWALL DRAIN 10 BOOST PUMP SUMP DRAIN 9 FIRE EXTINGUISHER IF INSTALLED CHECK PRESSURE 11 LANDING GEAR STRUT BRAKE WHEEL WELL AND LANDING GEAR DOORS CONT CHECK 11 LANDING GEAR STRUT BRAKE WHEEL WELL AND LANDING GEAR DOORS CHECK 13 OUTBOARD WING SUMP DRAIN 12 WHEEL WELL SUMP DRAIN 15 TIE DOWN AND CHOCKS REMOVE 14 WING FUEL TANK CHECK QUANTITY CAP SECURE 17 WING TIP AND LIGHTS ...

Page 541: ...NLY FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL RIGHT WING AND NACELLE RIGHT WING AND NACELLE 18 19 20 19 FLAPS CHECK 18 AILERON CHECK 20 CABIN WINDOWS CHECK ...

Page 542: ...Ti C90GTx PILOT TRAINING MANUAL WA 11 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL 2 STATIC PORTS CLEAR 3 ACCESS PANELS SECURE 3 ACCESS PANELS SECURE 1 OXYGEN DOOR SECURE RIGHT AFT FUSELAGE RIGHT AFT FUSELAGE 1 2 3 ...

Page 543: ...GTi C90GTx PILOT TRAINING MANUAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL TAIL 1 2 3 4 5 6 TAIL 2 DEICE BOOTS CHECK 1 TIE DOWN REMOVE 3 CONTROL SURFACES AND TABS CHECK 2 DEICE BOOTS CONT CHECK 3 CONTROL SURFACES AND TABS CONT CHECK 3 CONTROL SURFACES AND TABS CONT CHECK ...

Page 544: ...90GTx PILOT TRAINING MANUAL WA 13 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL NOTES 5 TOP ANTENNAS AND BEACON CHECK 5 TOP ANTENNAS AND BEACON CONT CHECK 4 LIGHTS CHECK 6 ELEVATOR TRIM TAB VERIFY 0 NEUTRAL POSITION TAIL ...

Page 545: ...NG PURPOSES ONLY FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL LEFT AFT FUSELAGE LEFT AFT FUSELAGE 2 STATIC PORTS CLEAR 1 ACCESS PANELS SECURE 1 2 ...

Page 546: ...FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL WA 15 FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL NOTES NOTES ...

Page 547: ......

Page 548: ... Approach APU Auxiliary power unit ARPS Alternate rudder power system ASCB Avionics standard communica tions bus serial ASR Airport surveillance radar ASYM Asymmetry ATA Antenna train angle ATC Air traffic control ATTD Attitude ATTN Attention AUX Auxiliary BAT Battery BBPU Bus bar protection unit BIT Built in test BITE Built in test equipment BLE Boundary layer energizer BOV Bleedoff valve BOW Bas...

Page 549: ...ectronic fuel control unit EFIS Electronic flight instrument system EGPWS Enhanced ground proximity warning system EGT Exhaust gas temperature EHSI Electronic horizontal situation indicator EHSV Electrohydraulic servo valves EIS Engine indicating system EL Electroluminescent ELT Emergency locator transmitter EMED Elect romagnetic expulsive deicing EMER Emergency ENG Engine EPR Engine pressure rati...

Page 550: ...r glide slope GWT Gross weight HDLC High level data link control HF High frequency HMU Hydromechanical fuel control unit HP High pressure HSCM Hydraulic spoiler control module HSI Horizontal situation indicator IAC Integrated avionics computers IAF Initial approach fix IAP Instrument approach procedures IAPS Integrated avionics processing system IAS Indicated airspeed ICAO International Civil Avia...

Page 551: ...MI Indicated mach number MSL Mean sea level MSP Mode select panel flight director MSU Mode selector unit NACA National Advisory Committee for Aeronautics NDB Nondirectional beacon NAV Navigation radio or mode N1 Low pressure rotor speed N2 High pressure rotor speed OAT Outside air temperature OXY Oxygen pressure PAST Pilot activates self test PBCV Power brake anti skid control valve PCB Printed ci...

Page 552: ...AS True airspeed TAT Total air temperature TAWS Terrain alert and warning system TCA Terminal control area TCAS Traffic alert and collision avoidance system TCWS Takeoff configuration warning system TCS Touch control steering TDC Top dead center TERR Terrain TFC Traffic TIS Traffic information system TIT Turbine inlet temperature T O Takeoff TOPI Takeoff operational phase inhibit TLA Throttle leve...

Page 553: ...d WAAS Wide area augmentation system GPS signal enhancment ground based WAC World aeronautical charts WATCH Weather attenuated color highlight WOW Weight on wheels WX Weather radar XFMR Transformer XFR Transfer XM External master satellite XMSN Transmission XPDR Transponder YD Yaw damper ZFW Zero fuel weight KING AIR C90GTi C90GTx PILOT TRAINING MANUAL APP A 6 FOR TRAINING PURPOSES ONLY APPENDIX A...

Page 554: ...A 7 D 8 B 9 A 10 D Chapter 8 1 A 2 B 3 A 4 D Chapter 9 1 C 2 B 3 D 4 D 5 C Chapter 10 1 A 2 B 3 D 4 A 5 C 6 C 7 C 8 B 9 B 10 D 11 A 12 B Chapter 11 1 A 2 D 3 B 4 A 5 A 6 B 7 D Chapter 12 1 B 2 B 3 D 4 A 5 A Chapter 14 1 D 2 B 3 C 4 B 5 C 6 B Chapter 15 1 C 2 C 3 C 4 A Chapter 17 1 D 2 B 3 C Chapter 18 1 A KING AIR C90GTi C90GTx PILOT TRAINING MANUAL APP B 1 FOR TRAINING PURPOSES ONLY APPENDIX B AP...

Page 555: ......

Page 556: ...FOR TRAINING PURPOSES ONLY KING AIR C90GTi C90GTx PILOT TRAINING MANUAL KING AIR C90GTi C90GTx PILOT TRAINING MANUAL ANN 1 FOR TRAINING PURPOSES ONLY L PITOT HEAT R PITOT HEAT Figure ANN 1 Annunciators ...

Page 557: ......

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