Cessna Citation Pilot Training Manual

INTRODUCTION ................................................................................................................. 1-1 GENERAL ............................................................................................................................ 1-1 Dimensions ..................................................................................................................... 1-2 Weight Limitations ......................................................................................................... 1-2 STRUCTURES ...................................................................................................................... 1-2 Entrance Door ................................................................................................................ 1-4 Emergency Exit .............................................................................................................. 1-6 Cabin .............................................................................................................................. 1-7 Flight Compartment ....................................................................................................... 1-7 Tailcone Compartment ................................................................................................... 1-7 Wing ............................................................................................................................... 1-7 Empennage ..................................................................................................................... 1-7 Nose Section ................................................................................................................... 1-8 SYSTEMS.............................................................................................................................. 1-8 Electrical System ............................................................................................................ 1-8 Fuel System .................................................................................................................... 1-9 Engines ........................................................................................................................... 1-9 Ice Protection System ..................................................................................................... 1-9 Hydraulic System ........................................................................................................... 1-9 Flight Controls................................................................................................................ 1-9 Environmental System.................................................................................................... 1-9 Avionics ........................................................................................................................ 1-10 CHAPTER 1 AIRCRAFT GENERAL 1-ii FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 PUBLICATIONS ................................................................................................................. 1-10 SINGLE-PILOT OPERATION............................................................................................ 1-10 LIMITATIONS..................................................................................................................... 1-10 EMERGENCY/ABNORMAL............................................................................................. 1-10 QUESTIONS ....................................................................................................................... 1-12 1-iii FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 ILLUSTRATIONS Figure Title Page 1-1. Cessna Citation Mustang ........................................................................................ 1-2 1-2. Citation Mustang Dimensions ................................................................................ 1-3 1-3. Braking Taxi Turning Distance ............................................................................... 1-4 1-4. Engine Hazard Areas .............................................................................................. 1-4 1-5. Entrance Door, Interior Handle, and Latch Release ............................................... 1-5 1-6. Hinged Panel ........................................................................................................... 1-5 1-7. Door Pin Indicator .................................................................................................. 1-6 1-8. Emergency Exit....................................................................................................... 1-6 1-9. Tailcone Baggage Door .......................................................................................... 1-7 1-10. Wing Trailing Edge ................................................................................................. 1-7 1-11. Stall Strips............................................................................................................... 1-8 1-12. Empennage ............................................................................................................. 1-8 1-13. Nose Storage Compartment .................................................................................... 1-8 1-14. Nose Baggage Light ............................................................................................... 1-8 TABLES Table Title Page 1-1. CAS MESSAGES ................................................................................................. 1-11 1-1 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 INTRODUCTION This manual provides a description of the major airframe and engine systems in the Cessna Cita- tion Mustang (Figure 1-1). The information contained herein is intended only as an instructional aid. This material does not supersede, nor is it meant to substitute for, any of the manufacturer’s maintenance or flight manuals. The material presented has been prepared from current design data. Chapter 1 covers the structural makeup of the airplane and gives an overview of the systems. GENERAL CHAPTER 1 AIRCRAFT GENERAL The Citation Mustang is certified in accordance with Title 14 of the Code of Federal Regulations (14 CFR 23) Part 23, including day, night, visual flight rules (VFR), instrument flight rules (IFR), single pilot, and flight into known icing conditions. Takeoff and landing performance and other special condition certification requirements are similar to 14 CFR Part 25. The Mustang meets 14 CFR Part 36 noise standards, and meets 14 CFR Part 34 fuel venting and exhaust emission standards. It combines systems simplicity with ease of access to reduce maintenance requirements. Low takeoff and landing speeds permit operation at small air- ports. Medium bypass turbofan engines contribute to overall operating efficiency and performance. 1-2 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 The Citation Mustang is equipped with a Garmin G-1000 integrated avionics system. This three- panel display system integrates flight instruments, flight guidance, navigation, and communication systems. Also integrated into the avionics system are the master warning and master caution sys- tems and hazard avoidance systems. The engine indication and crew alerting system (EICAS) is a two-column display on the left side of the cen- ter multifunction display (MFD). The crew alert- ing system (CAS) messages are displayed on the lower left of the MFD to alert the crew of system emergencies, abnormal situations, or changes in system operation. EICAS and CAS will be referred to often in the following chapters. DIMENSIONS Figure 1-2 shows a three-view drawing of the Cita- tion Mustang containing the approximate exterior and cabin dimensions. WEIGHT LIMITATIONS • Maximum ramp weight ....... 8,730 pounds • Maximum takeoff weight ...... 8,645 pounds • Maximum landing weight ...... 8,000 pounds STRUCTURES The Citation Mustang (Figure 1-1) is an all-metal, pressurized, low-wing monoplane with a swept T-tail. The interior has provisions for up to four passengers and two crewmembers. It has one cabin entry door and one emergency exit. The aircraft has baggage compartments in the nose and tail cone. Two pylon-mounted Pratt & Whitney PW615F tur- bofan engines are on the rear fuselage. Figure 1-3 shows braking taxi turning distance, and Figure 1-4 is a diagram of engine hazard areas. The aircraft has five doors: • Entrance door • Emergency exit (escape hatch) • Left nose baggage compartment door • Right nose baggage compartment door • Aft (tail cone) compartment door Each door (except the emergency exit) has a mon- itoring system, which provides a specific CAS message for that door if it is not properly closed. However, if the monitoring system for any door fails to pass a test on the ground, stops operating, or does not indicate normal operating condition, the CHECK DOORS CAS message appears. Figure 1-1. Cessna Citation Mustang 1-3 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 Figure 1-2. Citation Mustang Dimensions 43.17 FT (13.0 M) 11.79 FT (3.6 M) 13.10 FT (3.99 M) 14.35 FT (4.37 M) 40.56 FT (12.36 M) BAGGAGE DOORS RUDDER TRIM TAB TAIL CONE ACCESS DOOR (L SIDE ONLY) FS 144.00 IN. (3,658 MM) FS 321.00 IN. (8,153 MM) FS 202.76 IN. (5,150 MM) FORWARD PRESSURE BULKHEAD FORWARD DIVIDER (0.53 IN. THICK) (13 MM THICK) AFT PRESSURE BULKHEAD 24.00 IN. (610 MM) 46.00 IN. (1,168 MM) 54.00 IN. (1,372 MM) 58.76 IN. (1,493 MM) 34.24 IN. (870 MM) 55.00 IN. (1,397 MM) 54.00 IN. (1,372 MM) FLIGHT COMPARTMENT 117.71 IN. (2,990 MM) PASSENGER COMPARTMENT 1-4 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 ENTRANCE DOOR The cabin entrance door is on the forward left side of the fuselage (Figure 1-5). The entrance door opens outboard and forward. It is secured in the closed position with eight locking pins attached to a handle. The door can be opened from inside or outside of the airplane. The exterior handle can be secured with a key. Ensure that the key is removed from the entrance door prior to flight to prevent possible ingestion of the key into an engine. An adjustable stop prevents the door from opening too far. Once the door is fully open, a hook locks the door into position. To unlatch the hook and let the door close, a release button inside the cabin (inside left of door opening) must be pushed (Fig- ure 1-5). This lets the door move freely. CURB TO CURB 27.32 FEET (8.33 M) 11.79 FEET (3.59 M) 15.53 FEET (4.734 M) WING-TIP LIGHT TO WING TIP LIGHT 54.97 FEET (16.75 M) Figure 1-3. Braking Taxi Turning Distance 18 FEET (5.50 M) 27 FEET (8 M) 0 30 60 90 120 150 0 9 18 27 36 45 DISTANCE FEET DISTANCE METERS Figure 1-4. Engine Hazard Areas 1-5 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 CAUTION The locking pins will contact and dam- age the painted surface of the fuselage if an attempt is made to shut the door with the handle in the closed (up) position. The seal system operates passively as the cabin is pressurized. The seal engages and disengages when the door opens and closes. A hinged panel at the main cabin door threshold is used as a water barrier during ditching (Figure 1-6). It hinges up to prevent water from entering the aircraft, and enables the use of the entrance door as an exit during ditching. WARNING Water barrier must be raised and latched into position prior to ditching. NOTE The water barrier is installed at the main cabin door threshold. Crew members should be familiar with its location and operation; and passengers should be briefed prior to flights over water. Figure 1-5. Entrance Door, Interior Handle, and Latch Release Figure 1-6. Hinged Panel 1-6 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 A monitoring system checks for safe condition of the door (closed, pins secure, door latched). There are eight view ports on the inside panel of the entry door to verify that the eight locking pins are in the closed position. With the door closed and handle latched, the pilot should be able to see the white and black indicators in each port. (Figure 1-7). Three proximity switches verify that the door is closed, pins secure, and door latched by sensing the posi- tion of targets on the closing mechanism of the door and signals the condition to the CAS: • The proximity switch on the doorway sur- round structure senses the door after it is closed. • When the door handle is latched, this moves a bracket on the left and right side of the door outward pushing the eight locking pins into position. A proximity switch senses that this locking bracket has moved into the locked position (pilot must inspect the eight door pin indicators) (Figure 1-7). • As the handle catch is engaged, a proximity switch on the inner handle assembly senses a flag. If one of the proximity switches does not sense its target, the CABIN DOOR CAS message appears. EMERGENCY EXIT A plug-type emergency exit (escape hatch) is on the aft right side of the cabin, above the wing. It opens inboard. The emergency exit door can be opened from outside or inside the airplane (Figure 1-8). The D-shaped inner door handle is recessed behind a magnetic cover. The flush-mounted outer handle is located at the top of the door. The outer handle is not directly connected to the inner handle. The outer handle has a black indicator to show when the door is latched. Because no other provisions are provided for secur- ing the escape hatch when the airplane is unat- tended, a safety pin with a REMOVE BEFORE FLIGHT streamer is placed on the inside of the hatch. The pilot must ensure this pin is removed prior to flight. The emergency exit hatch is not con- nected to the door warning circuit. Figure 1-7. Door Pin Indicator EXTERIOR INTERIOR EXTERIOR Figure 1-8. Emergency Exit 1-7 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 CABIN The cabin extends from the forward pressure bulk- head to the aft pressure bulkhead and measures approximately 14 feet in length, 4.7 feet in width, and 4.5 feet in height. Figure 1-2 shows the interior arrangements and dimensions. The standard interior arrangement consists of two aft-facing and two forward-facing passenger seats. There is a toilet on the right side of the fuse- lage, abeam the cabin entry door. The toilet is not equipped with a safety belt and cannot be occupied during taxi, takeoff, or landing. The cabin area has dropout, constant-flow oxygen masks for emergency use. The cabin overhead panels contain individual air vent outlets and seat lighting for passenger comfort. FLIGHT COMPARTMENT The airplane is equipped with dual controls, includ- ing control yokes, brakes, and rudder pedals at each crew seat. There are two adjustable seats with seat belts and shoulder harnesses. TAILCONE COMPARTMENT The tailcone compartment is an unpressurized area and contains major components of the envi- ronmental, electrical distribution, flight controls, and engine fire extinguishing systems. Access is through the tail cone baggage door on the left side of the fuselage below the engine. This door opens the tail cone baggage compartment (Figure 1-9), which holds 300 pounds. The tailcone compartment door is secured at the aft side by mechanical latches and a key lock and is hinged at the left forward edge. The door is secured by a key lock, which is monitored by the CAS. The AFT DOOR CAS message appears if the door is unlocked. A light switch on the right side of the door opening is powered from the battery bus and provides illu- mination of the tail cone area for preflight inspec- tion purposes. If the manual switch is left on, a microswitch in the door track extinguishes the light when the door is closed. WING The wing assembly attaches to the bottom of the fuselage and is constructed of aluminum. Each wing is also a fuel tank. Electromechanical speed- brakes and flaps, and hydraulically actuated main landing gear are attached to each wing (Figure 1-10). An aileron fence is attached to the inboard side of each aileron. The wing leading edges are deiced by inflatable deice boots, which are inflated by regulated engine bleed-air. Vortex generators and stall strips are attached to the leading edge boots (Figure 1-11). EMPENNAGE The empennage consists of a vertical stabilizer with T-tail mounted horizontal stabilizers (Figure 1-12). The leading edges of the horizontal and ver- tical stabilizers are deiced by inflatable deice boots. Figure 1-9. Tailcone Baggage Door Figure 1-10. Wing Trailing Edge 1-8 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 NOSE SECTION The nose section is an unpressurized storage area. Various hydraulics components, pneumatic bottles, oxygen bottle, fresh-air duct, and radar antenna are located in this compartment (Figure 1-13). The nose storage compartment holds up to 20-cubic feet (320-pounds) of baggage. It has two swing-up doors (left and right). Each door has a mechanical lock. Each door has a key-operated cam lock, for- ward pin latch, and two independent paddle latches. The pin latch shows orange when not latched. Each latch has a switch and indicates the latch position with the NOSE DOOR L-R CAS message. A manual light switch is in the compartment (Fig- ure 1-14). If the manual light switch is left on, a microswitch at the left and right storage door assembly extinguishes the storage compartment light when the doors are closed. An over-center gas spring on each door holds the door in the full open position until the door is closed manually. Ensure that the keys are removed from both nose compartment doors prior to flight to prevent pos- sible ingestion of a key into an engine. SYSTEMS ELECTRICAL SYSTEM The Mustang is an all-DC aircraft. The 28-VDC electrical power is supplied by two starter-genera- tors and one 24-volt, 28 amp-hour sealed lead acid battery. An optional battery is a 24-volt, 28 amp- hour NiCad battery. An external power receptacle is below the right engine pylon. Figure 1-11. Stall Strips Figure 1-12. Empennage Figure 1-13. Nose Storage Compartment Figure 1-14. Nose Baggage Light 1-9 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 For convenience of pilot and passengers, two DC power outlets are provided in the cabin, powered by the DC system through a converter. One DC outlet is in the cabinet behind the copilot seat and the other is in the aft center console. FUEL SYSTEM The fuel system has two distinct, identical halves. Each wing tank stores and supplies the fuel to its respective engine. Fuel transfer capability is pro- vided. Fuel is heated through an oil-to-fuel heat exchanger (PRIST is not required). ENGINES Two pylon-mounted Pratt & Whitney PW615F tur- bofan engines are on the rear fuselage, and each produces approximately 1,460 pounds of thrust (sea level ISA + 0°C). To improve automation and efficiency, the engines are controlled by dual-channel full authority digi- tal engine controls (FADECs). Engines are started with electrical starter-generators, which are pow- ered by the onboard battery or a ground power unit (GPU). Ice-protection, fire-detection, and fire-extinguish- ing systems are provided for each engine. The engine pylons have ram-air inlets and exhausts to provide cooling airflow through the cabin air heat exchangers. ICE PROTECTION SYSTEM Anti-ice protection is provided to the engine inlets, and deice protection is provided to the wings, and empennage by engine bleed air. Engine bleed air directly heats the engine inlets and generator cool- ing inlets. The wings, vertical tail, and horizontal stabilizers are deiced by boots inflated by engine bleed air regulated to 20 psig (service air). The windshields are electrically anti-iced and defogged. Electric heat also anti-ices the pitot-static systems, stall-warning vane, and engine inlet-mounted T2 sensors. Ice detection lights on the glareshield help the pilot detect icing on the windshield. A light on the outside left fuselage helps the pilot detect icing on the wings. HYDRAULIC SYSTEM A single electrically driven hydraulic pump sup- plies pressure for operation of the landing gear and wheel brakes through a closed center system. The main gear are equipped with hydraulically oper- ated antiskid-controlled wheel brakes. Pneumatic backup is available for emergency landing gear extension and braking. FLIGHT CONTROLS Primary flight control is accomplished through conventional cable-operated surfaces. An aileron- rudder interconnect provides improved lateral sta- bility. Trimming is provided by aileron, elevator, and rudder tabs. The elevator trim is both mechani- cally and electrically actuated. Aileron and rudder trim are electrically activated. The flaps are electri- cally actuated and are on the trailing edges of the wing. Electrically powered speedbrakes are on the upper and lower wing surfaces. Nosewheel steer- ing is mechanically controlled by the rudder pedals through steering bungees. ENVIRONMENTAL SYSTEM The aircraft has a two-zone automatic temperature control system that is divided into cabin and cock- pit. An independent vapor cycle air-conditioning system provides cooling to the cabin and cockpit. Conditioned engine bleed air is used for cabin pressurization and temperature control. Cabin pressurization is controlled by an autoscheduling pressurization system. The crew need only to adjust destination elevation any time prior to or during flight and the controller automatically con- trols cabin pressure for operation at the highest practical differential pressure with minimum rates and changes. A 22-cubic-foot oxygen bottle (40-cubic-foot optional) supplies oxygen to the quick-donning masks for the crew and automatic dropout masks for each passenger. If cabin altitude becomes exces- sive, passenger oxygen masks deploy automatically (utilizing an electrically actuated solenoid) and can be deployed manually upon pilot command. 1-10 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 AVIONICS The Mustang uses a Garmin G1000 three-display “glass cockpit” to present most indications for flight instrumentation, navigation, avionics, and aircraft systems. The displays include two 10.4- inch primary flight displays (for pilot and copilot) and a 15-inch multifunction display. The standard factory-installed avionics package includes the fully integrated flight instruments, flight guidance, communications, and navigation systems. The navigation system includes GPS, ground-based navigation, and is WAAS-capable. An integrated engine indicating and crew alerting system (EICAS) is included. The Garmin G1000 system manages the instrument and engine dis- plays, the autopilot, flight guidance systems, and the flight director. Terrain and traffic avoidance systems and color radar are standard equipment. Data link weather capability is available with subscription. PUBLICATIONS The following publications must be immediately available to the flight crew: • FAA-approved AFM contains the limita- tions, data pertinent to takeoffs and landings, and weight and balance data. Information in the AFM always takes precedence over any other publication. • FAA-approved Citation Mustang Abbreviat- ed Checklist—Normal Procedures contains abbreviated normal operating procedures and abbreviated performance data. If any doubt exists or if the conditions are not covered by the checklist, the AFM must be consulted. • FAA-approved Citation Mustang Abbre- viated Checklist—Emergency/Abnormal Procedures contains emergency and abnor- mal procedures. If any doubt exists or if the conditions are not covered by the checklist, the AFM must be consulted. • Garmin G1000 Cockpit Reference Guide for the Citation Mustang Other publications that are not required to be in the aircraft include: • Operating Manual • Garmin G1000 Pilot’s Guide for the Cessna Citation Mustang • FAA-approved Weight and Balance Manual SINGLE-PILOT OPERATION The following are required when the airplane is operated with a crew of one pilot, per applicable operating rules: 1. Operable GFC-700 Autopilot 2. Headset with microphone (must be worn) 3. FAA-approved Pilots’ Abbreviated Normal Procedures Checklist (as revised) 4. FAA-approved Pilots’ Abbreviated Emergen- cy and Abnormal Procedures Checklist (as revised) 5. Provisions for storage and retention of navi- gation charts, accessible to the pilot from the pilot station LIMITATIONS For specific information on limitations, refer to the FAA-approved AFM. EMERGENCY/ ABNORMAL For specific information on Emergency/Abnormal procedures, refer to the FAA-approved AFM. 1-11 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 AFT DOOR DESCRIPTION Tailcone baggage door is not fully secured. INHIBITS EMER CABIN DOOR DESCRIPTION Indicates the cabin door is not fully secured. INHIBITS EMER CHECK DOORS DESCRIPTION Indicates a door monitor has not been properly tested or has failed. INHIBITS EMER, IN AIR, LOPI, TOPI Table 1-1. CAS MESSAGES NOSE DOOR L-R DESCRIPTION One or both of the nose baggage doors are not fully secured. INHIBITS EMER 1-12 FOR TRAINING PURPOSES ONLY 1 AIRCRAFT GENERAL CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 1. The maximum weight allowed in the nose bag- gage compartment is: A. 320 pounds B. 200 pounds C. 150 pounds D. 500 pounds 2. The maximum takeoff weight for the Citation Mustang is: A. 8,730 pounds B. 8,645 pounds C. 8,000 pounds D. 6,854 pounds 3. During single-pilot operation, the maximum number of passenger seats, excluding the pilot seat, is: A. 7 B. 6 C. 5 D. 4 4. Regarding the emergency exit escape hatch: A. The hatch is pushed outside the aircraft after the D handle is pulled. B. After the D handle is unlatched, rotate the hatch down into the cabin. C. If the hatch is not properly latched and locked, an amber CAS message will display. D. The hatch cannot be opened from the outside. 5. The amber AFT DOOR CAS message is acti- vated by: A. Aft door in the full open position B. Aft door unlocked C. Aft baggage compartment light being left on D. Key left in the aft door 6. Minimum equipment to operate the Citation Mustang as a single pilot: A. Operable autopilot B. Headset with microphone C. Approved checklist and navigation charts D. All the above 7. The following flight controls are electrically actuated: A. Nosewheel steering, aileron, brakes B. Elevator, aileron, flaps, speedbrakes C. Elevator trim, flaps, rudder D. Aileron trim, rudder trim, speedbrakes, flaps QUESTIONS 2-i 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL CONTENTS INTRODUCTION ................................................................................................................. 2-1 GENERAL ...............................................................................................................................2-1 DESCRIPTION...................................................................................................................... 2-3 COMPONENTS .................................................................................................................... 2-3 Battery ............................................................................................................................ 2-3 Standby Battery .............................................................................................................. 2-4 Starter-Generators .......................................................................................................... 2-4 Ground Power Unit ......................................................................................................... 2-5 Distribution..................................................................................................................... 2-5 System Protection ........................................................................................................... 2-7 CONTROLS AND INDICATIONS ....................................................................................... 2-9 Battery Switch ................................................................................................................ 2-9 Battery Disconnect switch ............................................................................................ 2-10 Interior Disconnect Switch ........................................................................................... 2-10 Avionics Standby Instrument Switch ........................................................................... 2-10 Generator Switches ...................................................................................................... 2-11 Engine Start Buttons .................................................................................................... 2-11 Indications .................................................................................................................... 2-11 OPERATION ....................................................................................................................... 2-12 Preflight ........................................................................................................................ 2-12 Starting (First Engine) .................................................................................................. 2-12 Starting (Second Engine) ............................................................................................. 2-13 CHAPTER 2 ELECTRICAL POWER SYSTEM 2-ii 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY Starting (In Flight)........................................................................................................ 2-13 Starting (Assisted by External Power Unit).................................................................. 2-13 LIMITATIONS..................................................................................................................... 2-13 EMERGENCY/ABNORMAL............................................................................................. 2-13 QUESTIONS ....................................................................................................................... 2-15 2-iii 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL ILLUSTRATIONS Figure Title Page 2-1. Electrical System Schematic................................................................................... 2-2 2-2. Battery .................................................................................................................... 2-4 2-3. GPU Receptacle ...................................................................................................... 2-5 2-4. Aft J-Box ................................................................................................................ 2-6 2-5. CB Panels................................................................................................................ 2-8 2-7. BATT Switch ........................................................................................................ 2-10 2-6. BATTERY DISCONNECT Switch....................................................................... 2-10 2-8. INTERIOR DISCONNECT Switch ..................................................................... 2-10 2-9. AVIONICS Standby Instrument Switch ............................................................... 2-11 2-10. Generator Switches ............................................................................................... 2-11 2-11. ENGINE START Buttons ..................................................................................... 2-11 2-12. Electric Display (Normal)..................................................................................... 2-12 TABLES Table Title Page 2-1. EMERGENCY BUS ITEMS .................................................................................. 2-7 2-2. CAS MESSAGES ................................................................................................. 2-14 2-1 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL Direct current provides the principal electrical power for the Citation Mustang. Normal aircraft system voltage is 28.5 VDC. Two generators are the primary power sources (one generator is capable of supplying all standard requirements). Second- ary sources (battery or external power) may also be used. Normal distribution of DC power is via a left and right feed bus connected by a crossfeed bus. This arrangement allows either generator to power the entire system or, working in parallel, to share the system load. The battery and emergency buses normally tie to the main system, but they may isolate to only the battery or external power sources. When the air- craft is on the ground, an external DC power unit may supply electrical power to all buses. INTRODUCTION This chapter provides a description of the electrical power system on Citation Mustang aircraft (Figure 2-1). The DC system consists of storage, generation, distribution, and system monitoring. Provision is also made for a limited supply of power during emergency conditions in flight and connection of a ground power unit (GPU) while on the ground. GENERAL CHAPTER 2 ELECTRICAL POWER SYSTEMS 2-2 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY Figure 2-1. Electrical System Schematic R S H U N T B U S R S T A R T # 1 R S T A R T # 2 E M E R G P W R C B B U S R AVN EMERG R FEED BUS #1 R ELE #1 R ELE #2 R FEED BUS #2 R SSR #1 BUS BAR R ELE EMERG MASTER INTERIOR SSR R AVN #1 SSR L AVN SSR R AVN #2 SSR L BOOST SSR R BOOST SSR INTERIOR BUS R AVIONICS #1 R AVIONICS #2 BATTERY BATTERY BUS L FEED BUS #1 L FEED BUS #2 L ELE #1 L ELE #2 AVN EMER SSR LEFT L SSR #1 BUS BAR L AVIONICS L AVN EMERG L ELE EMERG L S H U N T B U S L S T A R T # 1 R SSR #2 BUS BAR CROSSFEED BUS STANDBY BATTERY PACK L S T A R T # 2 T A A A V V V L GEN RELAY R GEN RELAY L DC AMPS R DC AMPS 100 AMP A/C COMP 100 AMP W/S DEICE 50 AMP FLAPS 50 AMP HYD PUMP 100 AMP W/S DEICE START RELAY START RELAY AFT J-BOX CIRCUIT BREAKERS EXT PWR RELAY EXT PWR CONNECTOR L STARTER- GENERATOR R STARTER- GENERATOR INT DISC NORM STANDBY INST SWITCH BATT DISC RELAY BATT AMPS BATT VOLTS R GEN VOLTS L GEN VOLTS BATT TEMP SENSOR STBY INST OFF BATT TEST EMER BUS RELAY BATT POWER RELAY 200 A MP 200 A MP LEGEND BATTERY POWER GROUND 2-3 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL DESCRIPTION The Mustang electrical system primarily pro- vides 28-VDC power to operate electrical devices throughout the aircraft. A starter-generator is used to start its respec- tive engine, with starting power coming from the battery or from a GPU. Additionally, the starter- generator of a functioning engine (with battery assistance) can be used to start the opposite side engine. One generator is capable of supplying all standard electrical requirements if a generator fails. DC power is routed from each J-box feed bus through individual circuit breakers to each of the circuit-breaker buses in the cockpit CB panels. Cockpit circuit breakers control power to individual systems. Battery power is supplied to a hot battery bus and then through the battery relay to the cross- feed bus and the left and right feed buses. When the BATT switch is in the EMER position, emergency DC power is supplied from the bat- tery bus through the emergency power relay to the emergency bus circuit breakers on each cockpit CB panel. If the battery switch is in the BATT position, generator power is supplied through the battery relay to the hot battery bus to charge the battery and from the crossfeed bus through the emergency relay to the emergency power buses. The external power receptacle is underneath the right engine nacelle. First engine start is performed from the battery unless using external power. The second engine start may be powered three different ways: • With external power (if the first generator switch is OFF) • From the battery (if the first generator switch is OFF and external power is not connected) • From the battery with assistance from the first generator (ground only) if the first gen- erator is online Normally, when both engines are operating, the starter-generator in each engine provides 28-VDC power to the main bus system in the tail cone. This bus system and its associated relays provide connections and power management for the bat- tery and provide for connection to a GPU. This bus system also allows either starter-generator to assist the other during starting and allows the two starter-generators to operate “in parallel” to share the electrical load evenly. From the main bus system in the tail cone, power is distributed through circuit breakers in the tail cone directly to a few electrical devices in or near the tail cone. More power is routed forward from the main buses through feeder cables to the cockpit buses. Buses on each side of the cockpit (behind the CB panels) supply power through the cockpit circuit breakers and panel controls to most of the aircraft electrical devices. Cockpit indicators monitor electrical system status and performance. Cockpit panel controls allow the crew to directly manage the generation and distri- bution of electrical power. Relays, solid state relays (SSRs), circuit breakers, current limiters, and gen- erator control units (GCUs) protect the electrical system, and assist the crew in managing the supply and flow of electrical power. COMPONENTS BATTERY A standard lead acid battery provides 24 volts rated at 28 amp hours. An optional NiCad battery pro- vides 24 volts rated at 28 amp hours. The battery is in the tail cone compartment (Figure 2-2). It has a manual quick-disconnect, and is accessible through the tail cone door. The battery connects to the battery bus. A battery disconnect relay between the battery and its ground provides an electrical disconnect during certain conditions. A BATTERY disconnect switch (Fig- ure 2-7) is in the cockpit on the left side console panel. This switch opens the battery disconnect relay. Use this switch in case of a battery overheat or stuck start relay. 2-4 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY NOTE The optional NiCad battery is suscep- tible to, and must be protected from, overheat due to excessive charging or discharging. During an external power start cycle, to prevent battery discharge, the battery disconnect relay auto- matically disconnects the battery from its ground. A GPU start is not a battery start. Starting the engines with an external power source is recommended practice to prolong the life of the batteries and conserve battery power for times when battery starts must be accomplished. When it is anticipated the aircraft will be idle for more than 2 days, it is advisable to disconnect the bat- tery to prevent frequency memory circuits, or other equipment that may be powered by the battery bus, from draining the batteries. A battery in good condition supplies power to all buses for a minimum of 10 minutes with maxi- mum load. If powering only the battery and emer- gency buses, battery life should be a minimum of 30 minutes. An INTERIOR DISCONNECT switch is on the pilot side console panel (Figure 2-7). When the switch is selected to the up position, the master interior relay opens, shutting off all electrical power in the cabin. When the switch is in the NORM position, the master interior relay closes, and elec- trical power flows to the cabin normally (when DC power is available and the other electrical controls are in the appropriate positions). STANDBY BATTERY The standby instrument battery is a 24 V, 1.2 amp hour NiCad battery. The standby battery is con- trolled with the AVIONICS STBY INST switch. The standby instrument battery is in the radome on the avionics shelf assembly. The battery auto- matically supplies electrical power to the standby airspeed, attitude, and altitude instruments and the lighting for the magnetic compass when normal electrical power is not available. STARTER-GENERATORS Two engine-driven DC starter-generators (one on each engine accessory gearbox) are the primary source of aircraft electrical power and supply power to all DC buses. Each generator is air cooled, rated at 29 VDC, and regulated to 28.5 volts. The generators are engine-starting motors that revert to generators at the completion of the start cycle. Each generator system operates indepen- dently, but power distributes evenly through bus systems that are in parallel except during fault conditions. DC power from the engine-driven generators dis- tributes to two feed buses (see Figure 2-1). Each feed bus connects through a 200-amp current lim- iter to the crossfeed bus, allowing each feed bus to parallel the other. During normal operation, the generators share loads equally (within ±10% of the total load) via the crossfeed bus. Each starter-generator is regu- lated by its own generator control unit (GCU). Generator power routes from the crossfeed bus through the battery relay (when it is closed) to the battery bus. This provides power to charge the battery, and during generator operation powers the items on the battery bus. Normally (with the battery switch set to BATT), generator power routes from the crossfeed bus through the emergency relay to power the cockpit emergency buses and through the battery relay to power the emergency bus in the J-box. The bat- tery and emergency relays are operated with the battery switch. Figure 2-2. Battery 2-5 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL GROUND POWER UNIT A GPU can be connected to the aircraft DC sys- tem through a receptacle in the fuselage below the right engine nacelle (Figure 2-4). External power is routed through the external power relay to the battery bus. The battery charges from the GPU, regardless of the battery switch position. A GPU providing a maximum voltage of 29 VDC may be used. The left and right start controllers monitor GPU voltage and open the external power relay to disconnect the GPU from the aircraft if voltage exceeds approximately 32.5 VDC. Before connecting a GPU, ensure that the voltage of the GPU is regulated to 28–29 volts the amper- age output between 800 and 1,100 amps. When using external power for prolonged ground opera- tion (over 30 minutes), disconnect the battery to preclude overheating the battery. Do not use the battery disconnect switch. CAUTION Some GPUs do not have reverse-current protection. If the GPU is powered off while connected to the aircraft, the bat- tery may be rapidly discharged and/or damaged. Always disconnect the GPU from the aircraft when not in use. Connecting the external power source energizes the external power relay, which connects the external power source to the battery bus. Setting the battery switch to the BATT position energizes the battery relay, which allows the con- nection of external (or battery) power from the battery bus to the emergency buses, and through the crossfeed bus to the left and right feed buses. When either the left or right generator power relay closes, the external power relay deenergizes to remove external power from the battery bus. This prevents the aircraft generators and the GPU from simultaneously applying power to the aircraft buses. CAUTION If the battery is charged using the GPU, it must be monitored. Current from most GPUs is not regulated and a battery overheat may occur. DISTRIBUTION DC power is distributed throughout the aircraft though several buses (see Figure 2-1) via the main junction box (aft J-box) and cockpit buses (behind CB panels). Main Junction Box (Aft J-Box) The main junction box (aft J-box) (Figure 2-5) in the tail cone compartment contains: • Two feed buses: ° Left feed bus No. 1 ° Right feed bus No. 1 • Two start buses: ° Left start bus No. 1 ° Right start bus No. 1 • Two shunt buses: ° Left shunt bus ° Right shunt bus • Crossfeed bus ° Battery bus Figure 2-3. GPU Receptacle 2-6 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY Main Feed Buses Each generator (left and right) normally supplies power through its respective generator relay to its respective main feed bus (left feed bus No. 1 and right feed bus No. 1). These buses are tied together through the crossfeed bus. Start Buses The left and right start buses provide power to the left and right start No. 2 buses and those provide power to the controllers and related systems. In order for the start relay to close, the battery switch must be in the BATT position. When the respective start relay closes, the start bus is connected to the battery bus, which supplies power from the battery or a GPU. Shunt Buses The left and right shunt buses connect the starter- generators to the electrical system. The GCUs and starter-generators manage the con- nection of the start buses through the left and right start relay and the left and right generator relay. With the exception of a cross-generator start, nor- mally only one relay at a time (either start relay or generator relay) is closed on each side to connect the corresponding start bus to the electrical system. Crossfeed Bus The crossfeed bus functions solely as a bus tie con- necting the battery bus, the emergency buses, and the two main feed buses into one integral system. If the battery switch is selected to BATT, the bat- tery power relay closes, which connects the battery bus to the crossfeed bus. Power extends from the crossfeed bus through 200-amp current limiters to each main feed bus. Power also extends from the crossfeed bus to the cockpit emergency power cir- cuit-breaker buses and (through the avionics power switch) to the avionics buses. Battery Bus The battery bus is connected directly to the bat- tery. It may receive power from a GPU and during normal operation, receives its power from either or both generators. Cockpit Distribution and CB Panels Various feed-extension buses, avionics buses, emergency buses, and the interior buses are in the cockpit. Feed Extension Buses From each main feed bus (left feed No. 1 and right feed No. 1) in the tail cone, various extension feed buses distribute power to components through con- trols and circuit breakers in the cockpit. The main left and right feed-extension buses are behind the pilot and copilot CB panels respectively (Figure 2-6). Other feed-extension buses are also behind the corresponding CB panels and are powered through 25-amp circuit breakers. Avionics Buses Avionics buses (left and right) are powered from the respective main feed buses through solid-state relays (SSRs) when the AVN MASTER switch is selected ON. These buses provide power to the air- craft avionics, except the avionics that are on the emergency buses. Figure 2-4. Aft J-Box 2-7 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL Emergency Buses Emergency bus items are listed in Table 2-1. The aircraft has five emergency buses: • Emergency power circuit-breaker bus • Left electrical emergency bus • Right electrical emergency bus • Left avionics emergency bus • Right avionics emergency bus (with standby battery) The emergency power circuit-breaker bus is direct- ly connected to the battery bus at all times. Other buses are powered from either the crossfeed bus, the battery bus, or the standby battery. With the battery switch in the BATT position, power to the emergency buses is from the cross- feed bus. Because the crossfeed bus normally feeds the emer- gency buses, the pilot must use the battery switch to energize the emergency power relay to the EMER position, which switches all emergency buses from the disabled crossfeed bus to the battery bus. With the battery switch in the EMER position, the following aural warnings are available: • Terrain awareness and warning system (TAWS) alert • Autopilot disconnect • Check altitude • Barometric minimum descent altitude/deci- sion height • Vertical track • Marker beacon CAUTION With the battery switch in the EMER position, some aural warnings are NOT available, including: • Stall warning • Landing gear • Overspeed • Traffic alerts TIS, TAS, TCAS SYSTEM PROTECTION Generator Control Units Two GCUs regulate, parallel, and protect the gen- erators. The GCUs are in the tail cone, with one unit dedicated to each starter-generator. Each GCU controls a field and generator relay. Each genera- tor relay connects the generator to its feed bus. The GCU permits the generator relay to close when the cockpit generator switch is in GEN and the gen- erator output is within 0.5 volts of normal system voltage (28.5 VDC). When the GCU senses an internal feeder fault (short circuit) or an overvoltage, the respective side generator and field relays open. These relays also open when the ENGINE FIRE switchlight is selected. • PFD 1 - Reversion mode • COM 1 • NAV 1 (including marker beacon) • GPS 1 • ADC 1 • AHRS 1 • Pilot and copilot audio panel • L and R N1, N2, and ITT indications • L Oil Temperature • L Fuel flow • Fuel Temperature • Magnetic compass light • Battery voltage indication • AFCS panel (except auto- pilot and yaw damper) • Cabin altitude and differential pressure indications • Cabin dump system • Cockpit flood light • Pilot pitot-static heat • Landing gear indicator lights • Avionics audio warnings • Standby instruments (airspeed, altitude, attitude) • ELT GPS position interface Table 2-1. EMERGENCY BUS ITEMS 2-8 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY A reverse current (10% of total load) or under- voltage opens only the generator relay, removing the generator from the system but leaving the field relay closed. The GCU utilizes software and solid-state circuitry to perform the following operations: • Control voltage regulation • Load sharing • Overvoltage/overexcitation protection • Automatic generator line contactor control • Reverse current protection • Overload protection • Overspeed protection • Open ground protection • Open shunt protection • Open point of regulation (POR) protection • Starter cutoff • Field weakening • Ground fault protection Figure 2-5. CB Panels 2-9 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL Circuit Breakers and Current Limiters Parallel feeder cables (between each DC feed bus in the tail cone and the corresponding feed-extension buses in the cockpit) receive protection from cir- cuit breakers. Various other circuit breakers on the feed buses in the tail cone protect against overload. Current limiters, also known as fuse limiters, are provided to protect against major electrical over- load. A list of the protected buses and components is provided below: • Left feed bus No. 1—200 amps • Right feed bus No. 1—200 amps • Air-conditioner compressor—100 amps • Windshield heat (left)—100 amps • Windshield heat (right)—100 amps • Flaps—50 amps • Hydraulic powerpack—50 amps • HF radio (optional)—50 amps Solid-State Relays Solid-state relays (SSRs) serve as a combination circuit breaker and relay for numerous compo- nents. SSRs are individually controlled by cockpit system switches or, in some instances, by remotely mounted printed circuit boards (PCBs). SSRs are installed in either a 25- or 10-amp size; however, they are resistor-adjustable for lower amperage trip points. The following buses and components are SSR-protected and controlled: • Left avionics bus • Right avionics bus (No. 1) • Right avionics bus (No. 2) • Left avionics emergency bus • Master interior bus • Cockpit fan • Cabin fan • Condenser fan • Left fuel boost pump • Right fuel boost pump • Left ignitor No. 1 • Right ignitor No. 1 • Left ignitor No. 2 • Right ignitor No. 2 Relays and Engine Starting For generator-assisted second engine starts, the battery power relay opens to prevent high-current flow from the crossfeed bus to the battery bus and protects the 200-amp current limiters. This causes starting current from the online generator and bat- tery to flow through the two starter relays and bat- tery bus to the starter. A blown 200-amp current limiter splits the feed buses, preventing generator paralleling. Pressing the starter button for GPU starts, first opens the battery disconnect relay to prevent the battery cycles, then closes the start relay. If GPU voltage is excessive, an overvoltage sen- sor opens the external power relay and breaks the circuit to the battery bus. External power disable relays also disconnect the GPU from the battery bus whenever a generator relay closes, bringing a generator online. CONTROLS AND INDICATIONS Control of DC power is maintained with a battery switch and two generator switches (Figure 2-6). BATTERY SWITCH The battery switch is on the pilot DC POWER subpanel and has three positions: BATT, OFF, and EMER. If the battery switch is in the OFF position, the bat- tery bus isolates from all other buses in the system with the exception of the emergency power circuit- breaker bus. 2-10 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY When the battery switch is in the BATT position, the battery power relay closes, completing a circuit to the crossfeed bus. The emergency relay deener- gizes while the battery relay is in the BATT posi- tion and completes a circuit to the emergency buses from the crossfeed bus. In the EMER position, only the emergency power relay energizes, which connects the emergency buses to the battery bus. These buses receive power from the battery or external power. When external power is not applied to the aircraft and the gen- erators are online, placing the battery switch in EMER or OFF isolates the battery from any charg- ing source. BATTERY DISCONNECT SWITCH A guarded battery disconnect switch (see Figure 2-7) is above the pilot armrest on the left side con- sole panel. The switch has two positions: BAT- TERY (disconnect) and NORM. It disconnects the battery and is used only for abnormal operations involving stuck start relay or battery overtempera- ture. Activating this switch uses battery power to open the battery disconnect relay on the ground side of the battery. NOTE The battery switch on the DC POWER subpanel must be in the BATT posi- tion for the battery disconnect switch to operate. If the battery ground is open, the battery cannot supply electrical power to the aircraft or receive a charge from the generators. CAUTION Do not use the battery disconnect switch for an extended time. The battery dis- connect relay will continue to draw a small current from the battery until the battery is discharged. The battery dis- connect relay will then close, resulting in a very high charge rate and probable overheat. INTERIOR DISCONNECT SWITCH The interior disconnect switch is above the pilots armrest on the left console panel by the battery dis- connect switch. The interior disconnect switch dis- connects the cabin lights (except for the emergency exit lights operated by the pax safety switch), the cabin DC-DC converters, and the cabin XM radio. AVIONICS STANDBY INSTRUMENT SWITCH The avionics standby instrument switch is on the AVIONICS pilot switch panel in the cockpit. The switch can be set to the STBY INST, OFF, or BATT TEST position. The switch supplies power to the right avionics emergency bus. Figure 2-6. BATT Switch Figure 2-7. BATTERY DISCONNECT Switch Figure 2-8. INTERIOR DISCONNECT Switch 2-11 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL When the standby battery is powering the standby instruments, the amber light adjacent to the switch illuminates. Selecting BATT TEST performs a capacity check on the standby battery. A success- ful test is indicated by a green light adjacent to the switch. GENERATOR SWITCHES Two generator switches (L GEN and R GEN) are on the pilot DC POWER subpanel (see Figure 2-10). The generator switches have three positions: L (or R) GEN, OFF, and RESET. Setting the switch to L GEN or R GEN allows the GCU to close the generator relay and connects the generator to its feed bus. The ammeter indicates the generator output to the feed buses. With the switch in the OFF position, the generator relay opens and the ammeter shows no generator load to the feed buses. Placing the switch in the spring-loaded RESET position rebuilds field voltage to provide a means of resetting a generator that has tripped as a result of a fault condition. ENGINE START BUTTONS Two engine start buttons (L and R) (see Figure 2-7) on the pilot ENGINE START subpanel activate a circuit to close the associated start relay and allow starting current to flow from the battery bus to the starter. A starter disengage (DISENG) button between the starter buttons opens the start circuit if manual termination of the start sequence is desired (see Figure 2-11). Pushing the engine start button illuminates a white light in the starter button as a direct indication that the start relay is closed. INDICATIONS The DC electrical system is monitored by: • Crew alerting system (CAS) messages • Engine indicating and crew alerting system (EICAS) display window ° DC AMPS display ° DC VOLTS display ° BATTERY AMPS display ° BATTERY VOLTS display • ENGINE START button lights Figure 2-9. AVIONICS Standby Instrument Switch Figure 2-10. Generator Switches Figure 2-11. ENGINE START Buttons 2-12 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY EICAS Display Window The DC window of the EICAS display provides dual generator indications (left and right) for both voltage (VOLTS) and current (AMPS), and also BATTERY voltage and current. VOLTS Display The left and right generator VOLTS displays are on the upper-left area of the DC window (Figure 2-12). Each VOLTS display indicates voltage at its respective generator. In reversionary mode, only the digits are displayed. AMPS Display The left and right generator AMPS displays are on the upper-right area of the DC window (Figure 2-12). Each display indicates current flow from its respective generator to its respective DC feed bus. During normal operation, the indication should be parallel within ±10% of total load. Amperage between the starter-generator and the battery bus is not reflected on the AMPS displays. In reversion- ary mode, only the digits are displayed. BATTERY–VOLTS Display The BATTERY–VOLTS display is a digital display on the bottom-center area of the DC window. The display indicates voltage on the battery bus. BATTERY–AMPS Display The BATTERY–AMPS display is a digital display on the bottom of the DC window (Figure 2-12). The display indicates current into or from the bat- tery. Positive amperage indicates battery charging. Negative amperage indicates battery discharge. OPERATION PREFLIGHT During the exterior preflight, visually check the battery for signs of deterioration or corrosion. Do not connect external power until completing these checks. During the interior preflight, place the generator switches to GEN if the intention is a bat- tery start or to the OFF position if external power is desired. Place the battery switch to BATT and verify the voltage display is at or above 24 volts minimum (22 volts minimum for a NiCad). After checking lights and pitot heat, turn the battery switch to the OFF position. STARTING (FIRST ENGINE) Before starting the engines, recheck the genera- tor switches for proper position and verify battery voltage. Ensure that the battery switch is in the BATT position. Depressing the L or R ENGINE START button: • Closes the respective start relay • Activates the electric fuel boost pump Closure of the start relay (indicated by illumination of the start button white light) connects battery bus power to the starter for engine rotation. At approximately 8% turbine rpm (N 2): • FADEC commands fuel flow to the start nozzles • Ignition is activated by the full-authority digital engine control (FADEC) • A green IGN appears on the multifunction display (MFD) at the upper interturbine tem- perature (ITT) scale and indicates current to one or both exciter boxes Within 10 seconds, combustion should occur as evidenced by rising ITT. Figure 2-12. Electric Display (Normal) 2-13 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL As the engine accelerates through 48.6% N 2: • The GCU starter overspeed sensor automati- cally terminates the start sequence. • The start relay opens. • The electric boost pump is deenergized. • The GEN OFF message disappears from the CAS window(GEN switch ON). • The green IGN indication extinguishes. • N2 digits change from white to green. STARTING (SECOND ENGINE) Before starting the second engine, the operating engine must be INCREASED to 10% above ground idle N2. CAUTION If the operating generator drops off-line during a cross-generator start (GEN OFF L-R), an ENG CTRL SYS L or R CAS message posts, of ITT indica- tion is lost at any time during the start sequence, abort the start immediately by bringing the throttle to CUTOFF to reduce the possibility of a hot or hung engine start. For a second engine start on the ground, the operat- ing generator assists the battery in providing cur- rent to the starter. When the remaining start button activates, both start relays close and the white light in each starter button illuminates. When one generator relay closes and the other ener- gizes as a starter, the battery disable relay causes the battery relay to open the circuit between the crossfeed bus and the battery bus in order to pro- tect the 200-amp current limiter. STARTING (IN FLIGHT) An engine start in flight using the start button is a battery start only. The squat switch disables gen- erator-assist capability when airborne. Only the associated start relay closes and the boost pump on that side activates. The only difference between an in-flight start and a ground start with one generator online, is that the start relay on the same side as the operating gen- erator does not close and the battery power relay opens. This isolation of the start circuit from the operating generator and buses in flight is through left squat switch logic and is required by certifica- tion regulations. The protection circuit for the 200-amp current lim- iter is the same as previously described. Refer to the “Airstart Envelope” graph in “Limitations” of the Airplane Flight Manual (AFM). STARTING (ASSISTED BY EXTERNAL POWER UNIT) A GPU can be used for engine starts. Check for voltage regulation to a maximum of 29 VDC and 800/1,100 amps. When external power starts are planned, the gen- erator switches remain in the OFF position until the removal of external power from the aircraft. Otherwise, when the first generator comes online, the external power relay opens and the GPU auto- matically disconnects from the battery bus. The second engine start becomes a generator-assist battery start. LIMITATIONS For specific limitations, refer to the FAA-approved AFM. EMERGENCY/ ABNORMAL For specific information on emergency/abnormal procedures, refer to the appropriate checklist or FAA-approved AFM. 2-14 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL FOR TRAINING PURPOSES ONLY Revision 1.3 Table 2-2. CAS MESSAGES BATTERY O’TEMP DESCRIPTION With the optional NiCad battery installed, a battery overtemperature warning sys- tem warns the pilot of abnormally high battery temperatures. If the tempera- ture reaches 71°C (160°F) a red BATT O’TEMP message displays and the MASTER WARNING lights flash. INHIBITS NONE BATTERY O’TEMP DESCRIPTION With the optional NiCad battery installed, a battery overtemperature warning sys- tem warns the pilot of abnormally high battery temperatures. An internal tem- perature of 63–70°C (145–156°F) dis- plays an amber BATT O’TEMP message and steady MASTER CAUTION lights. INHIBITS NONE BATT TEMP FAIL DESCRIPTION The battery temperature sensor has failed. INHIBITS LOPI, TOPI GEN OFF L-R DESCRIPTION Both electrical generators have gone offline. INHIBITS NONE GEN OFF L-R DESCRIPTION One electrical generator has gone offline. INHIBITS NONE AFT JBOX CB L-R DESCRIPTION Start control circuit breaker (located in the aft j-box) is tripped. INHIBITS EMER AFT JBOX LMT L-R DESCRIPTION This message occurs when both cur- rent limiters are blown. With no other faults, the aircraft will have normal power available to both buses. In the event of a generator failure, the cross-feed bus will not supply power from the battery or opposite generator. INHIBITS EMER 2-15 2 ELECTRICAL POWER SYSTEMS Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL 1. What action should be taken if the engine starter fails to disengage? A. E N G I N E S T A R T D I S E N G switch—PRESS B. FADEC RESET switch—Select affected side and release C. IGNITION switch—NORM D. AP/TRIM DISC button—PRESS 2. What is indicated by illumination of the light in the start buttons? A. Engine has not reached a stabilized idle B. Start relay is closed C. Engine has been started and the generator is online D. Generator relay is closed 3. If the AFT JBOX LMT L CAS message is displayed in the CAS window, what bus or busses would be lost if the L generator fails? A. L FEED BUS and L SHUNT BUS B. R START BUS C. L AVIONICS EMER BUS D. R EXTENSION BUS 4. With the battery disconnect switch in the bat- tery disconnect position: A. Do not use the switch for an extended period of time B. The aircraft battery is connected to the airframe C. The standby battery is connected to the airframe D. The keep alive for the avionics is discon- nected from the airframe 5. With the battery switch in EMER and the gen- erators OFF, battery life should be a minimum of: A. 5 minutes B. 30 minutes C. 60 minutes D. 90 minutes 6. With the battery switch in the EMER position and the generators OFF, there is no: A. Cockpit floodlight B. Landing gear indication lights C. Exterior lights D. EICAS messages 7. The wing and tail deice systems are inopera- tive with the battery switch in the: A. EMER position B. NORM position C. ON position D. INTERIOR DISCONNECT position 8. For engine start with a sealed lead-acid battery, minimum battery voltage is: A. 18 VDC B. 20 VDC C. 24 VDC D. 28 VDC 9. The maximum electrical load per generator on the ground at idle is limited to: A. 50 amps B. 100 amps C. 150 amps D. 200 amps 10. Battery starts are limited to: A. One engine start per hour B. Two engine starts per hour C. Three engine starts per hour D. Four engine starts per hour 11. If a ground power unit is being used to start the engines, the generator switches should be in which position? A. ON B. OFF C. Reset D. Manual QUESTIONS 2-16 2 ELECTRICAL POWER SYSTEMS CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY 12. With the STBY INST switch in the BATT TEST position, the pilot should see the fol- lowing indication: A. A green STBY INST message in the CAS window B. The green test light illuminated C. An amber BATT TEST message in the CAS window D. The red LED test light illuminated 3-i 3 LIGHTING Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL CONTENTS INTRODUCTION ................................................................................................................. 3-1 GENERAL ...............................................................................................................................3-1 INTERIOR LIGHTING ......................................................................................................... 3-2 Flight Compartment Lighting ........................................................................................ 3-2 Magnetic Compass Light ............................................................................................... 3-3 Entry/Exit Lighting and Entry Light Switch .................................................................. 3-3 Cabin Lighting................................................................................................................ 3-3 Passenger Safety Light System ...................................................................................... 3-4 Baggage Compartment Lighting .................................................................................... 3-5 EXTERIOR LIGHTING ........................................................................................................ 3-5 Landing/Recognition/Taxi Lights ................................................................................... 3-5 Beacon ............................................................................................................................ 3-6 Anticollision Lights ........................................................................................................ 3-6 Navigation Lights ........................................................................................................... 3-6 Wing Inspection Light .................................................................................................... 3-6 LIMITATIONS....................................................................................................................... 3-6 EMERGENCY/ABNORMAL............................................................................................... 3-6 QUESTIONS ......................................................................................................................... 3-7 CHAPTER 3 LIGHTING 3-iii 3 LIGHTING Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL ILLUSTRATIONS Figure Title Page 3-1. Flight Compartment Lighting Controls .................................................................. 3-2 3-2. Cockpit Overheat Lights and Controls ................................................................... 3-3 3-3. Compass Light ........................................................................................................ 3-3 3-4. Entry Lights Switch ................................................................................................ 3-3 3-5. Cabin Lighting ........................................................................................................ 3-4 3-6. Cabin Lighting Controls ......................................................................................... 3-4 3-7. Emergency Exit Light ............................................................................................. 3-4 3-8. No Smoking/Fasten Seat Belt Sign ......................................................................... 3-4 3-9. Nose Baggage Light and Switch............................................................................. 3-5 3-10. Aft Baggage Light Switch ...................................................................................... 3-5 3-11. Landing Lights ........................................................................................................ 3-6 3-12. Beacon Light........................................................................................................... 3-6 3-13. Position Lights ........................................................................................................ 3-6 3-1 3 LIGHTING Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL Interior lighting is provided for the flight compart - ment, cabin, windshield ice detection, and passen- ger safety. Most instruments are internally lighted. For general illumination, map lights, and a floodlight are above the pilot and copilot. There are standard passenger advisory lights in the cabin area, and emergency exit lights that consist of a light over the main cabin entry door and a table light over the emergency exit door. Reading and table lights are also available in the cabin area. The exterior lighting consists of wingtip lights (navigation/anticollision lights), landing/ recogni- tion lights, wing inspection light, and beacon light. INTRODUCTION This chapter provides information on lighting for the Citation Mustang. Interior lighting illumi- nates the flight compartment area, all flight instruments, and the passenger cabin. Exterior lighting provides necessary illumination for day or night operation. GENERAL CHAPTER 3 LIGHTING 3-2 3 LIGHTING CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY INTERIOR LIGHTING The aircraft interior lights are DC powered. Inte- rior light circuit breakers are on the right CB panel. The breakers are grouped within the LIGHTS cat- egory. Panel back lighting is provided by light emit- ting diodes (LEDs). Overhead lights are halogen and the displays are liquid crystal displays (LCDs). FLIGHT COMPARTMENT LIGHTING Flight compartment panel lighting is provided by LED panels (Table 3-1). Light intensity is controlled by a PANEL dimmer knob (Figure 3-1). The panel dimmer knob controls: • Switchlights • Oxygen gauge lighting • Magnetic compass light • Three standby instruments • Landing gear position lights • Audio panels and display bezels A DISPLAYS dimmer knob controls the dimming of the Garmin avionics. The dimmer knob is on the LIGHTING panel (Figure 3-1). Rotating the DISPLAYS dimmer knob clockwise increases the intensity of the Garmin displays. Rotating it counterclockwise dims the displays; rotating the knob fully counterclockwise (to the DAY position) causes the intensity to be set auto- matically in response to photocell sensors. Figure 3-1. Flight Compartment Lighting Controls PANEL DIMMER KNOB POSITION LIGHT DAY JUST OUT OF DAY FULL CW VARIABLE? BATTERY EMER. POSITION PANEL LIGHT DIM CB-HF021 LED PANELS X 19 OFF VERY DIM BRIGHT YES OFF ICE DETECT LIGHTS ON ON ON NO OFF OXYGEN GAUGE OFF VERY DIM BRIGHT YES OFF STANDBY AIRSPEED OFF VERY DIM BRIGHT YES OFF STANDBY ATTITUDE OFF VERY DIM BRIGHT YES OFF STANDBY ALTITUDE OFF VERY DIM BRIGHT YES OFF MAGNETIC COMPASS OFF VERY DIM BRIGHT YES OFF GEAR LIGHTS BRIGHT VERY DIM VERY DIM NO VERY DIM DUMP SWITCH BRIGHT VERY DIM DIM YES OFF M A S T E R W A R N I N G / CAUTION BRIGHT DIM DIM NO DIM R ENGINE FIRE/ L ENGINE FIRE BRIGHT DIM DIM NO DIM BOTTLE ARMED PUSH BRIGHT BRIGHT BRIGHT NO NO EFFECT STANDBY PLACARD LIGHT ON ON ON NO ON Table 3-1. COCKPIT LIGHTING 3-3 3 LIGHTING Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL The DISPLAYS dimmer knob can only control a Garmin display if AUTO brightness mode is select- ed. This mode is the default lighting mode but can be changed. Refer to the Garmin Mustang G-1000 Cockpit Reference Guide. A cockpit floodlight and two map lights are over- head near the center of the aircraft (Figure 3-2). A center rheostat controls the floodlight and separate rheostats to the left and right of the floodlight rheo- stat control each of the two map lights. MAGNETIC COMPASS LIGHT The magnetic compass is on the windshield center post (Figure 3-3). LED backlighting is provided for night operation when the PANEL dimmer knob is in any position other than DAY. ENTRY/EXIT LIGHTING AND ENTRY LIGHT SWITCH To activate the entry/exit lighting, use the entry light pushbutton switch on the aft side of the left divider cabinet (Figure 3-4). When the entry door is opened, a green backlight illuminates a symbol on the entry light switch. After a 10-minute delay, the entry lights (if turned on) and the switch backlighting extinguish. The entry light switch turns on the fixed light above the entry door and the fixed light above the toilet. CABIN LIGHTING Cabin lighting consists of (Figure 3-5): • Two table lights • Four reading lights • Two entry lights • Passenger safety light There are oval-shaped light assemblies above the passenger seats on the cabin headliner. Each assem- bly consists of (Figure 3-6): • Controllable air duct outlet • Inboard button that controls the respective table light • Outboard button that controls the respective cabin light • Light assembly Figure 3-2. Cockpit Overheat Lights and Controls Figure 3-3. Compass Light Figure 3-4. Entry Lights Switch 3-4 3 LIGHTING CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY PASSENGER SAFETY LIGHT SYSTEM The Mustang is equipped with a passenger safety light system. The pilot can activate the light above the entry door and the right table light over the emergency exit (Figure 3-7) with the PAX SAFE- TY light switch on the light switch grouping below the multifunction display (MFD) (see Figure 3-1). These same two lights can also be activated by a 5-G switch. Anytime 5-G is exceeded (such as in an emergency landing), the exit lights illuminate. These two safety lights are powered from the emer- gency power CB bus. NOTE The passenger safety lights illuminate for emergency lighting when the G- switch is tripped or when the passenger safety switch on the cockpit LIGHTS switch panel is in the PAX SAFETY position. NOTE If activated by the G-switch, these lights remain on until deactivated by mainte- nance, regardless of battery switch or cabin door status. The interior disconnect switch (above the pilot armrest on the left side con- sole panel) does not disable the passen- ger safety lights controlled by the PAX SAFETY switch. The cabin lights are powered through the CABIN LIGHTS circuit breaker on the aft J-box. No Smoking/Fasten Seat Belt Sign and Switches A no smoking/fasten seat belt sign is above the table on the left side of the cabin (Figure 3-8). The no smoking placard is always visible. The PAX SAFETY–SEAT BELT switch (on the LIGHTING panel under the MFD) controls the fasten-seat-belt light. The light illuminates when the switch is set to SEAT BELT or PAX SAFETY. Figure 3-5. Cabin Lighting Figure 3-6. Cabin Lighting Controls Figure 3-7. Emergency Exit Light Figure 3-8. No Smoking/Fasten Seat Belt Sign 3-5 3 LIGHTING Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL BAGGAGE COMPARTMENT LIGHTING Baggage compartment lighting includes the nose baggage compartment light and the tail cone com- partment light. They are wired directly to the emer- gency power bus and do not require the battery switch to be in the BATT or EMER position for operation. Nose Baggage Compartment The manual switch assembly of the baggage light system is an illuminated two-position rocker switch. The switch is in the baggage compartment overhead and adjacent to the light assembly (Fig- ure 3-9). The manual switch applies DC power to the light. During daylight hours or when the light is not desired, turn the manual switch OFF, which disconnects power from the light. When the switch is OFF, it illuminates so it is easy to locate at night. When both nose baggage doors are closed, a micro- switch on each nose baggage door hinge turns the light off regardless of rocker switch position. Aft Baggage Compartment The toggle switch for the aft baggage light system is on the right side door opening. The baggage light is aft of the baggage door on the upper right side. When the switch is in the ON position, DC power is applied to the light. When the aft baggage door is closed, a micro- switch on the door turns the light off regardless of the manual toggle switch position (Figure 3-10). EXTERIOR LIGHTING LANDING/RECOGNITION/ TAXI LIGHTS The aircraft is equipped with two lamps that illu- minate for landing and taxi purposes. The landing lights consist of two 50-watt sealed high intensity discharge (HID) lamps in the belly fairing, forward of the forward wing spar. These lamps are protected behind tempered glass cov- ers. They are situated so the flight compartment is shielded from glare (Figure 3-11). A LANDING–RECOG TAXI switch on the LIGHTING panel controls the landing lights. The LANDING position provides the brightest illumi- nation for landing. The RECOG TAXI position dims the lights to a lower intensity. The landing lights receive power through the respective LAND/REC LIGHTS circuit breakers on the aft J-box. Figure 3-9. Nose Baggage Light and Switch BAGGAGE LIGHT SWITCH LIGHT Figure 3-10. Aft Baggage Light Switch 3-6 3 LIGHTING CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY BEACON The aircraft is equipped with a beacon. The bea- con assembly is on the top of the vertical stabilizer for optimum line of sight visibility (Figure 3-12). The beacon consists of a red LED assembly with a strobe rate of 50 flashes per minute. The beacon is controlled by the BEACON switch on the LIGHT- ING panel. ANTICOLLISION LIGHTS In addition to the navigation lights, each wingtip assembly contains an anticollision strobe light. The anticollision lights flash at a rate of 50 flashes per minute. The lights are controlled by the ANTI COLL switch on the LIGHTING panel. The anti- collision lights are powered through the L and R ANTI-COLLISION LT circuit breakers on the aft J-box. NAVIGATION LIGHTS Navigation lights are in assemblies behind clear tempered glass covers. The lights are located as follows (Figure 3-13): • Red forward light—Left wingtip • Green forward light—Right wingtip • White rear light—Both wingtips The navigation lights are controlled by a NAV switch on the LIGHTING panel. The lights are powered by the circuit breakers in the aft J-box. WING INSPECTION LIGHT A wing inspection light is on the left side of the fuselage, above and forward of the wing leading edge. The inspection light assembly includes a halogen bulb that illuminates the outboard leading edge of the left wing. Aircraft crew utilize the light to detect wing ice accumulation during nighttime flight in icing conditions. A WING INSP switch on the LIGHTING panel supplies power to the lamp. The WING INSP light circuit breaker is on the left CB panel. LIMITATIONS For specific limitations, refer to the FAA-approved AFM. EMERGENCY/ ABNORMAL For specific information on emergency/abnormal procedures, refer to the appropriate checklist or FAA-approved AFM. Figure 3-11. Landing Lights Figure 3-12. Beacon Light LEFT (RED) NAVIGATION LIGHT ANTICOLLISION LIGHT AFT (WHITE) NAVIGATION LIGHT Figure 3-13. Position Lights 3-7 3 LIGHTING Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL 1. When the LANDING–RECOG TAXI switch is in the LANDING position, it provides: A. The dimmest lighting available for taxiing B. Significantly more lamp life C. The brightest lighting available for landing D. The best lighting available for deplaning 2. When the nose baggage compartment doors are closed, the: A. Compartment light extinguishes regard- less of the rocker switch position B. Compartment light remains illuminated C. White CAS message remains in the steady ON state D. White CAS message flashes in reverse video 3. In the event of activation, the 5-G switch sends power to: A. The light above the cabin door B. The right table light above the emergency exit door C. The cockpit floodlight D. Both A and B 4. If left illuminated, the cabin entry light: A. Remains illuminated B. Should extinguish after 10 minutes C. Begins to flash D. Changes its shading to red QUESTIONS 4-i 4 MASTER WARNING SYSTEM Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL CONTENTS INTRODUCTION ................................................................................................................. 4-1 GENERAL ...............................................................................................................................4-1 DESCRIPTION...................................................................................................................... 4-2 CONTROLS AND INDICATIONS ....................................................................................... 4-2 CAS Messages................................................................................................................ 4-2 Master Indicator Lights .................................................................................................. 4-5 Rotary TEST Knob ......................................................................................................... 4-6 LIMITATIONS....................................................................................................................... 4-7 EMERGENCY/ABNORMAL............................................................................................... 4-7 QUESTIONS ......................................................................................................................... 4-9 CHAPTER 4 MASTER WARNING SYSTEM ILLUSTRATIONS Figure Title Page 4-1. CAS Window on MFD in Normal Display Mode .................................................. 4-3 4-2. CAS Window on PFD in Reversionary Display Mode ........................................... 4-3 4-3. CAS Scroll Buttons................................................................................................. 4-4 4-4. Master Indicator Lights........................................................................................... 4-6 4-5. Rotary TEST Knob ................................................................................................. 4-6 TABLES Table Title Page 4-1. ROTARY TEST INDICATIONS (AIRCRAFT CONFIGURATION AG) ............. 4-8 4-1 4 MASTER WARNING SYSTEM Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL The master warning system includes a pair of MAS- TER WARNING and MASTER CAUTION lights, and the crew alerting system (CAS) messages. CAS messages are displayed by the G1000 engine indicating and crew alerting system (EICAS). These lights and messages provide a visual indica- tion to the pilots of certain faults, functions, and/or conditions of selected systems. Each CAS message indicates an individual system situation, or simulta- neous situations on both sides (left and right) of a dual system. Additionally, an audio warning system provides indication of some situations. CAS messages appear on the EICAS, which is on the left side of the multifunction display (MFD). In the event of a PFD or MFD failure, the pilot can press the red DISPLAY BACKUP button on each audio panel. INTRODUCTION This chapter describes the master warning systems on the Citation Mustang aircraft. The master warning systems provide a warning of aircraft system malfunctions, indications of unsafe operat- ing conditions requiring immediate attention, and indications that some specific systems are in operation. Audio warnings provide further indications. GENERAL CHAPTER 4 MASTER WARNING SYSTEM 4-2 4 MASTER WARNING SYSTEM CITATION MUSTANG PILOT TRAINING MANUAL Revision 1.2 FOR TRAINING PURPOSES ONLY This selects reversionary mode which combines displays from the PFD and MFD (including CAS messages). The combined displays appear on both the select- ed PFD and the MFD. When the MFD and a PFD are in reversionary mode, the EICAS displays the CAS messages on the upper-right section of both display panels. NOTE Crew alerts associated with the autopi- lot, avionics, and engine fire warning/ suppression are displayed elsewhere in the displays or cockpit. The crew alerts are described in the corresponding chap- ters in this manual. The abnormal and emergency procedures in this section are keyed, where applicable, to the appro- priate CAS messages. The rotary TEST knob pro- vides testing for the master warning system. DESCRIPTION The Mustang master warning system uses cockpit indications (visual and aural) to advise the crew of important warnings, cautions, and advisory infor- mation about the aircraft and its systems. Pressure sensors, temperature sensors, switches, and other devices detect conditions in the aircraft and its systems. This information is provided as analog signals or discrete digital signals to the G1000 system. These signals are received at the left and right Garmin integrated avionics unit (GIAs), and at the left and right Garmin engine/airframe interface units (GEAs). A detailed description of G1000 system architecture is provided in Chapter 16—“Avionics.” With the battery switch selected to EMER, only the left GIA and left GEA are powered; CAS messages requiring input from the right GIA or right GEA are inhibited and do not appear, regardless of aircraft or system condition. CONTROLS AND INDICATIONS The Mustang master warning system includes: • CAS messages • Master indicators: • MASTER WARNING lights • MASTER CAUTION lights • Aural warnings—Various audio warn- ings are incorporated into aircraft sys- tems that warn of specific conditions and malfunctions. Control of the system is provided by: • CAS scroll softkeys (up and/or down) • Rotary TEST knob CAS MESSAGES The Mustang master warning system is primar- ily a function of the G1000 avionics system. The CAS displays warning, caution, and advisory mes- sages in response to data from aircraft sensors and FADECs. CAS Message Window All CAS messages are displayed in the CAS mes- sage window. The window is on either the MFD, or on one or both of the PFDs: • Normal display mode—CAS message window is in the bottom left corner of the EICAS display, which appears on the left side of the MFD (Figure 4-1). • Reversionary display mode—CAS mes- sage window is on the right side of the PFD display (Figure 4-2). CAS Message Types CAS messages are in one of three colors: red, amber, or white. Red (Warning) Message Red indicates a warning (hazardous situation that requires immediate pilot corrective action). 4-3 4 MASTER WARNING SYSTEM Revision 1.2 FOR TRAINING PURPOSES ONLY CITATION MUSTANG PILOT TRAINING MANUAL When a red CAS message displays, it flashes in reverse video and the MASTER WARNING light flashes. Pressing the MASTER WARNING light acknowledges the message, extinguishes the MAS- TER WARNING light, and changes the CAS mes- sage to a steady ON state. Red CAS messages are displayed until the situation is corrected. All red CAS messages are grouped together at the top of the CAS display window. Any new red CAS mes- sage displays at the top of the red CAS group. NOTE If a red CAS message is displayed and is not acknowledged by the crew, the mes- sage DOES NOT extinguish even if the problem is corrected by the system itself or by the crew. Red CAS messages must be acknowledged. Amber (Caution) Message Amber indicates a caution (abnormal or special situation that includes a possible need for future pilot corrective action). When an amber CAS mes- sage displays, it flashes in reverse video and the MASTER CAUTION light illuminates steady. Pressing the MASTER CAUTION light acknowl- edges the message, extinguishes the MASTER CAUTION light, and changes the CAS message to a steady ON state. Amber CAS messages are displayed until the situation is corrected. All amber CAS messages are grouped together below any red CAS messages in the CAS display window. Any new amber CAS message displays at the top of the amber CAS group. NOTE If an amber CAS message is displayed, the CAS message extinguishes once the problem is corrected by the system or by the crew (regardless if the crew acknowledges the CAS by pressing the MASTER CAUTION light). White (Advisory) Message White indicates an advisory (advisory in nature and denote items which are considered normal during operation of the aircraft or do not normally require any pilot action). When a white CAS mes- sage displays, it appears in a steady ON state. All white CAS messages are grouped together below any red or amber CAS messages in the CAS display window. Any new white CAS messages display at the top of the white CAS group. CAS Message Type Priority Some CAS messages may appear in different colors at different times, indicating different conditions or levels of severity (warning, caution, or advisory). Figure 4-1. CAS Window on MFD in Normal Display Mode Figure 4-2. CAS Window on PFD in Reversionary Display Mode 4-4 4 MASTER WARNING