C90ab Pre-course Study Guide R1.1 p2042

King Air C90A/B Initial Pilot Course Pre-Attendance Study Guide

Copyright © 2002 FlightSafety International August, 2005 – Revision 1.1

FOR TRAINING PURPOSES ONLY


TABLE OF CONTENTS TABLE OF CONTENTS .............................................................................................................. 2 INTRODUCTION.......................................................................................................................... 3 DOCUMENTATION REQUIREMENTS .................................................................................... 4 COURSE ATTENDANCE PREREQUISITES ......................................................................... 5 ATP REQUIREMENTS ............................................................................................................... 5 C90A/B EMERGENCY PROCEDURES (Memory Items) ..................................................... 6 EXPANDED CHECKLISTS AND DETAILED SYSTEMS CHECKS (DSCs)....................10 C90A / C90B / C90SE OPERATING LIMITATIONS ............................................................16 TRIPLE-FED ELECTRICAL SYSTEM....................................................................................25 FUEL SYSTEM...........................................................................................................................26 GRADING AND EVALUATION STANDARDS......................................................................28


FOR TRAINING PURPOSES ONLY 2


INTRODUCTION We have sent this short study guide to you to assist in your preparation for attending the King Air C90A/B Initial Pilot Course with FlightSafety International in Wichita, Kansas. Please review this guide prior to attending our course. We know that doing so will give you a head start on learning some of the class material that you will be required to know prior to completing your training. In this guide you will find the following information: Attendance Requirements ATP Requirements (if required) Emergency Procedures (Memory Items) Expanded Procedures and Detailed Systems Checks (DSCs) Selected Operating Limits Initial Pilot Course Syllabus Grading Standards

We look forward to having you as our guest for training and thank you for choosing FlightSafety International for your King Air training needs. Sincerely, Barry Barlow King Air 90/200 Program Manager Steve Olson, Steve Woodbury King Air 90/200 Assistant Program Managers FlightSafety International Raytheon Aircraft Learning Center 9720 E. Central Avenue Wichita, KS 67206 (316) 612-5300 (800) 488-3747 (316) 612-5399 (fax)




DOCUMENTATION REQUIREMENTS Clients attending a King Air C90A/B training course must provide a VALID PILOT CERTIFICATE (with Instrument and Multi-Engine ratings) and MEDICAL CERTIFICATE on the first day of training

NOTE: Non-U.S. citizens seeking the issuance of an Airline Transport Pilot certificate As of August, 2005 there are no United States Transportation Security istration (TSA) requirements that apply for the issuance of the U.S. ATP-MEL rating in the King Air 90/200 program. There are, however, FAA requirements that must be fulfilled prior to training/checking. Non-U.S. citizens seeking the issuance of an ATP-MEL rating must first fill out a Verification of Authenticity of Foreign License, Rating, and Medical. The form can be found at: http://registry.faa.gov/docs/61-75.pdf. Block 10 on the form should state, WICHITA, KS since this is the local FSDO office that will be notified upon approval. After filling out the Verification form you should mail it to: FAA’s Airmen Certification Branch AFS-760, P.O. Box 25082 Oklahoma City, OK 73125 Or fax it to 405-954-4105. If you have any questions or concerns regarding these requirements or any other issues, please Customer at (800) 488-3747 or (316) 612-5300.




COURSE ATTENDANCE PREREQUISITES The prerequisites for attendance of the King Air C90A/B Initial Pilot Training Course are: Ø At least an FAA Private Pilot Certificate, or ICAO recognized equivalent Ø Valid Instrument Rating Ø Valid Multi-Engine Rating

ATP REQUIREMENTS Pilots seeking an Airline Transport Pilot rating in a King Air C90B simulator can receive 100% of that checkride in the simulator provided they comply with the eligibility criteria as specified in 14 CFR § 61.153 and provide documentation for the aeronautical experience as specified in 14 CFR § 61.159. Pilots will be required to provide the following documents prior to the ATP checkride: Ø Original ATP knowledge test result form Ø Logbook(s) to document required 14 CFR § 61.159 requirements Ø All documents required for course attendance § 61.159 Eligibility Requirements: Ø At least 1500 hours of total time as a pilot that includes at least: o 500 hours of cross-country flight time o 100 hours of night flight time o 75 hours of instrument flight time, in actual or simulated instrument conditions §

A maximum of 50 hours of training in a flight simulator or flight training device, as part of a § 142 approved training course, may be credited toward the instrument flight time requirements

o 250 hours of flight time in an airplane as a pilot in command, or as second in command performing the duties of pilot in command while under the supervision of a pilot in command, which includes at least: §

100 hours of cross-country flight time

§

25 hours of night flight time

§

Not more than 100 hours of the total aeronautical experience requirements may be obtained in a flight simulator or flight training device as part of a § 142 approved training course




C90A/B EMERGENCY PROCEDURES (Memory Items)

EMERGENCY ENGINE SHUTDOWN 1. Condition Lever ...........................................................................................FUEL CUT OFF 2. Propeller Lever.......................................................................................................FEATHER 3. Firewall Shutoff Valve ............................................................................................CLOSED 4. Fire Extinguisher (if installed).....................................................ACTUATE (if required)

ENGINE FIRE ON GROUND 1. Condition Lever ...........................................................................................FUEL CUT OFF 2. Firewall Shutoff Valve ...........................................................................................CLOSED

ENGINE FAILURE DURING GROUND ROLL 1. Power Levers.................................................................................................GROUND FINE 2. Brakes.......................................................................................................................MAXIMUM If Insufficient Runway Remains for Stopping: 3. Condition Levers .........................................................................................FUEL CUT OFF 4. Firewall Shutoff Valves ..........................................................................................CLOSED 5. Master Switch ...................................................................................OFF (Gang bar down) 6. Boost Pumps .....................................................................................................................OFF

ENGINE FAILURE AFTER LIFT-OFF (If Conditions Preclude an Immediate Landing) 1. 2. 3. 4.

Maximum Continuous Power.......................................................................................SET Airspeed.................................................................MAINTAIN (take-off speed or above) Landing Gear ......................................................................................................................UP Propeller Lever (Inoperative engine)..................... FEATHER (or FEATHER if autofeather is Installed) 5. Airspeed..........................108 KNOTS (after obstacle clearance altitude is reached)




ENGINE FAILURE IN FLIGHT BELOW AIR MINIMUM CONTROL AIRPEED (V MCA) 1. Reduce power on operative engine as required to maintain directional control. 2. Lower nose to accelerate above V MCA .

ENGINE FLAMEOUT (2nd Engine) 1. Power Levers....................................................................................................................IDLE 2. Propeller..................................................................................................DO NOT FEATHER 3. Condition Lever ..........................................................................................FUEL CUT OFF 4. Conduct Air Start.

SMOKE AND FUME ELIMINATION ELECTRICAL SMOKE OR FIRE OR ENVIRONMENTAL SYSTEM SMOKE OR FUMES 1. Oxygen a. Oxygen System Control..........................................................................CONFIRM ON b. Crew .............................................................................................................. DON MASKS

CABIN DOOR UNLOCKED (CABIN DOOR Annunciator) If the CABIN DOOR Annunciator Illuminates, or If an Unlocked Cabin Door is Suspected: 1. All Occupants ........................ SEATED WITH SEAT BELTS SECURELY FASTENED

EMERGENCY DESCENT 1. Power Levers....................................................................................................................IDLE 2. Propeller Levers....................................................................................................HIGH RPM 3. Flaps .....................................................................................................................APPROACH 4. Landing Gear ................................................................................................................DOWN 5. Airspeed............................................................................................182 KNOTS MAXIMUM




GLIDE 1. Landing Gear .......................................................................................................................UP 2. Flaps ......................................................................................................................................UP 3. Propellers ..........................................................................................................FEATHERED 4. Airspeed ...............................................................................................................125 KNOTS

INVERTER INOPERATIVE (INVERTER Annunciator) 1. Select Switch ............................................................... SELECT THE OTHER INVERTER

UNSCHEDULED ELECTRIC ELEVATOR TRIM 1. Maintain pitch control with the elevator. 2. Control Wheel Trim Switch ..............ATTEMPT TO TRIM IN OPPOSITE DIRECTION OF RUNAWAY 3. Elevator Trim Switch (Pedestal) ...................................................................................OFF 4. Manual Trim .................................................................................. RETRIM AS REQUIRED

UNSCHEDULED RUDDER BOOST ACTIVATION 1. Rudder Boost Switch ......................................................................................................OFF

HIGH DIFFERENTIAL PRESSURE (Anytime the Differential Pressure goes into the Red Arc) 1. Cabin Altitude Controller.................................... SELECT HIGHER CABIN ALTITUDE If condition persists: 2. Bleed Air Valves.......................................................................................................CLOSED 3. Cabin Pressure Switch (After Cabin is Depressurized).....................................DUMP 4. Bleed Air Valves............................................................................................................ OPEN




LOSS OF PRESSURIZATION (CABIN ALT HI Annunciator) 1. Oxygen System Control................................................................................CONFIRM ON 2. Crew .................................................................................................................... DON MASKS

SPINS If a Spin is Entered Inadvertently: 1. Control Column........................................................................................ FULL FORWARD 2. Full Rudder....................................................................OPPOSITE DIRECTION OF SPIN 3. Power Levers....................................................................................................................IDLE 4. Controls ...........................................................NEUTRALIZE WHEN ROTATION STOPS 5. Execute a smooth pullout.

EMERGENCY EXIT 1. Emergency Release Hatch Cover ............................................................................ OPEN 2. Release Button...............................................................................................................PUSH If release button will not push, PULL hooks to override pressure lock and then PUSH the release button. 3. PULL handle and PUSH out hatch.




EXPANDED CHECKLISTS AND DETAILED SYSTEMS CHECKS (DSCs) The Expanded Checklists and Detailed Systems Checks (DSCs) are an integral part of the BEFORE ENGINE START, BEFORE TAXI, and BEFORE TAKEOFF (RUNUP) checklists. Learning, understanding, and memorizing these checks in a timely manner greatly decreases the amount of time required to get the airplane ready for takeoff. Doing so will allow for more simulator time to be devoted to flying. FUEL CHECK (Before Engine Starting) 1. Fuel CBs..........................................................................................................IN 2. Battery Switch..........................................................................................................ON 3. Fuel Firewall Valves........................................................................................CLOSE 4. Battery Switch........................................................................................................OFF 5. Crossfeed Switch ...............................................................................................OPEN (Crossfeed Annunciator Illuminated –Then Closed) 6. Boost Pumps............................................................................................................ON 7. Battery Switch..........................................................................................................ON (Fuel Pressure Lights Illuminated). 8. Fuel Firewall Valves...........................................................................................OPEN (Fuel Pressure Lights Extinguish). 9. Fuel Quantity....................................................................................................CHECK 10. Transfer Pumps .............................................................................TEST, THEN OFF

1. 2.

3. 4. 5. 6. 7. 8.

ELECTRICAL SYSTEM CHECK (Before Taxi) Gen Ties ..............................................................................................................OPEN [L GEN TIE OPEN] & [R GEN TIE OPEN] illuminated. Voltmeter .............................................................................................................Check TPL FED......................................................................................26.5 to 28.0 VOLTS R GEN and L GEN.....................................................................27.5 to 29.0 VOLTS (within 1.0 volt of each other) CTR ........................................................................................... 23 VOLTS MINIMUM Gen Ties .............................................................................................................NORM [L GEN TIE OPEN] & [R GEN TIE OPEN] extinguished. Bus Sense Switch........................................................MOMENTARILLY TO TEST [L GEN TIE OPEN], [BAT TIE OPEN] & [R GEN TIE OPEN] illuminated. Voltmeter (CTR) ............................................................................................0 VOLTS Bus Sense Switch.................................................... MOMENTARILLY TO RESET [L GEN TIE OPEN], [BAT TIE OPEN] & [R GEN TIE OPEN] extinguished. Voltmeter (CTR) .........................................................................27.5 to 29.0 VOLTS Generator Load ...........................................................PARALLELED WITHIN 10%




1.

2. 3. 4.

5. 6.

1. 2. 3.

4. 5. 6. 7.

8.

BOOST PUMP/AUTO CROSSFEED TEST (Before Takeoff – Runup) Left Boost Pump ....................................................................................................OFF [L FUEL PRESS] on, then extinguished. [FUEL CROSSFEED] on. Left Boost Pump ......................................................................................................ON Crossfeed ................................................................................CLOSE, THEN AUTO [FUEL CROSSFEED] extinguished. Right Boost Pump..................................................................................................OFF [R FUEL PRESS] on, then extinguished. [FUEL CROSSFEED] on. Right Boost Pump ...................................................................................................ON Crossfeed ................................................................................CLOSE, THEN AUTO [FUEL CROSSFEED] extinguished.

PRESSURIZATION (Before Takeoff – Runup) Bleed Air Valves ................................................................................................OPEN Condition Levers ........................................................................................HIGH IDLE Pressurization Controller......................................................................................SET Adjust cabin altitude knob to indicate 1,000 feet below field pressure altitude. Set rate knob to 12-o’clock position. Cabin Pressure Switch .......................................HOLD AT THE TEST POSITION Cabin Altimeter and VSI...........................CHECK FOR DESCENT INDICATION Cabin Pressure Switch.....................................RELEASE TO PRESS POSITION Pressurization Controller......................................................................................SET The inner scale (ACFT ALT) should indicate planned cruise altitude plus 1,000 feet. This setting must no result in an outerscale (CABIN ALT) indication of less than 500 feet above departure field pressure altitude. Condition Levers ............................................................................... AS REQUIRED




COLLINS APS-65H AUTOPILOT (Before Takeoff – Runup) 1. Pitch Trim................................................................................ TAKEOFF POSITION 2. Elevator Trim Switch ..............................................................................................ON 3. Autopilot.........................................................................................................ENGAGE [YAW], [A/P], and [ALT ARM] illuminated. 4. Control Wheel ......................................................................FORWARD POSITION Operate pilot’s pitch trim switches in both directions to ensure that the autopilot disengages and that the yaw damper remains engaged. 5. Control Wheel .........................................................................................CENTERED 6. Autopilot.........................................................................................................ENGAGE a. Apply forward pressure on the control wheel, and note that the pitch trim travels nose up and that the amber TRIM light comes on. b. Apply rearward pressure on the control wheel, and note that the pitch trim travels nose down and that the amber TRIM light comes on. 7. Control Wheel ..............................................................................HOLD CENTERED 8. DISC TRIM/AP YD Button.......................................DEPRESS TO FIRST LEVEL the [YAW D IS] and [AP DIS] annunciators illuminate. 9. DISC TRIM/AP YD Button........................................DEPRESS TO NEXT LEVEL that the [PITCH TRIM OFF] annunciator illuminates. 10. Elevator Trim Switch........................................................................................RESET that the [PITCH TRIM OFF] annunciator extinguishes. 11. Repeat items 2 through 10 for copilot’s side. 12. Yaw Damper .................................................................................................ENGAGE [YAW] annunciator is illuminated. Check for additional resistance to movement of rudder pedals. 13. Yaw Damper ..........................................................................................DISENGAGE 14. Pitch Trim ............................................................................ RESET FOR TAKEOFF 15. Primary Flight Controls ...................................................................... FULL TRAVEL a. Move all primary flight controls through their full travel in both directions. b. that controls move in proper direction and no restrictions to free movement are present.




ELECTRIC PITCH TRIM (Before Takeoff – Runup) 1. Electric Pitch Trim ...................................................................................................ON 2. Pilot’s and Copilot’s Switches: a. Ensure that the electric pitch trim does not operate when only one switch on a side is moved fore or aft. b. Check electric pitch trim operation for nose-up and nose-down travel. c. Depress the DISC TRIM/AP YD button, and that the electric pitch trim is disconnected and the [PITCH TRIM OFF] annunciator is illuminate. d. Cycle the pitch trim switch. that the [PITCH TRIM OFF] annunciator is extinguished, and repeat for the other side.

PRIMARY GOVERNORS/OVERSPEED GOVERNORS/RUDDER BOOST (Before Takeoff – Runup) 1. Rudder Boost ..........................................................................................................ON 2. Prop Levers ................................................................................... FULL FORWARD 3. Prop Gov Test Switch .....................................................................HOLD TO TEST 4. Left Power Lever ............................................................ INCREASE UNTIL PROP STABILIZES AT 1980-2060 RPM 5. Left Prop Lever .....................................................................RETARD TO DETENT THEN FULL FORWARD [RVS NOT READY] illuminated as prop lever retarded. 6. Vacuum and Pneumatic Pressure Gages ..................................................CHECK 7. Left Power Lever .................................ADVANCE UNTIL SAME SIDE RUDDER PEDAL MOVES FORWARD OBSERVE ENGINE LIMITATIONS 8. Left Power Lever .................................................................................................IDLE 9. Repeat steps 4 through 8 for Right Engine. 10. Prop Governor Test Switch......................................................................RELEASE




1. 2. 3.

4. 5. 6.

1. 2. 3. 4.

AUTOFEATHER (Before Takeoff – Runup) Power Levers ....................................................... APPROXIMATELY 500 FT-LBS Autofeather Switch..........................................................................HOLD TO TEST [L AUTOFEATHER] & [R AUTOFEATHER] illuminated. Left Power Lever ..........................................................................................RETARD a. At Approximately 400 ft-lbs..................................OPPOSITE ANNUNCIATOR EXTINGUISHED b. At Approximately 260 ft-lbs .................................SAME SIDE ANNUNCIATOR FLASHING AND PROP FEATHERS Left Power Lever .................................................. APPROXIMATELY 500 FT-LBS Repeat Steps 3 and 4 for Right Power Lever. Both Power Levers...............................................................................................IDLE [L AUTOFEATHER] & [R AUTOFEATHER] EXTINGUISH AND NEITHER PROP FEATHERS

ENGINE ANTI-ICE (Before Takeoff – Runup) Both ANTI-ICE ACTUATOR Switches ...................................................STANDBY Both ENGINE ANTI-ICE ON-OFF Switches ....................................................OFF [L ENGINE ANTI-ICE], [R ENGINE ANTI-ICE] extinguished. Both ANTI-ICE ACTUATOR Switches ............................................................MAIN Both ENGINE ANTI-ICE ON-OFF Switches ......................................................ON [L ENGINE ANTI-ICE], [R ENGINE ANTI-ICE] illuminated.




ICE PROTECTION (Before Takeoff – Runup) 1. Engine Auto -Ignition. a. Power Levers ..................................................................................................IDLE b. Engine Auto -ignition Switches .....................................................................ARM c. [L IGNITION ON], [R IGNITION ON]......................................... ILLUMINATED d. Power Levers .........................ADVANCE TO ABOVE 400 FT-LBS TORQUE e. [L IGNITION ON], [R IGNITION ON]......................................EXTINGUISHED f. Engine Auto -ignition Switches ......................................................................OFF g. Power Levers ..................................................................................................IDLE 2. Windshield Anti-ice. a. Pilot and Copilot Windshield Anti-ice ...............................................................HI Observe Increase on Loeters. b. Pilot and Copilot Windshield Anti-ice ............................OFF, THEN NORMAL Observe Loeters. c. Pilot and Copilot Windshield Anti-ice ...........................................................OFF 3. Electrothermal Propeller Deice. CAUTION Do not operate propeller deice when the propellers are static. a. Prop Deice..........................................................................................................ON b. Deice Ammeter..........................................................................18-24AMPERES Monitor for 90 seconds to ensure automatic timer operation. c. Prop Deice........................................................................................................OFF 4. Surface Deice System. a. Condition Levers .................................................................................HIGH IDLE b. Pneumatic Pressure .................................................................................CHECK c. Surface Deice .........................................................CHECK BOTH POSITIONS Single Cycle ................................................................................................. UP Manual................................................................................................... DOWN Check the boots visually for inflation and hold -down. Single cycle inflation is six seconds for the wings, then four seconds for the horizontal stabilizer. d. Condition Levers ..............................................LOW IDLE OR AS REQUIRED CAUTION Operation of the surface deice system in ambient temperatures below –40oC can cause permanent damage to the boots. 5. Pitot Heat..........................................................................................................CHECK Observe slight increase in loeter.




C90A / C90B / C90SE OPERATING LIMITATIONS NOTE TO THE CLIENT: We at FlightSafety strongly recommend that you arrive for your King Air C90A/B initial course familiar with these limitations…in other words, you’d be wise to memorize them, especially if you are taking an ATP or 14 CFR § 135 checkride!

AIRSPEED LIMITATIONS VA - Maneuvering Speed.........................................................................................169 VFE - Maximum Flap Extension/Extended Speed Approach Position – 35% (White triangle) ...................................................184 Full Down Position – 100% (White arc) ........................................................148 VLO - Maximum Landing Gear Operating Speed Extension...........................................................................................................182 Retraction ..........................................................................................................163 VLE - Maximum Landing Gear Extended Speed ...................................................182 VMCA - Air Minimum Control Speed (Red line)..............................90 (C90A / C90SE) 80 (C90B) VMO/M MO - Maximum Operating Speed (Red & White hash-marked pointer) 226 or .46 Mach (whichever is less) EMERGENCY AIRSPEEDS (10,100 LBS) VXSE - One-Engine Inoperative Best Angle-of-Climb .............................................100 VYSE - One-Engine-Inoperative Best Rate-of Climb (Blue line) ............................108 VMCA - Air Minimum Control Speed (Red line ) ..............................90 (C90A / C90SE) 80 (C90B) One-Engine-Inoperative Enroute Climb ..................................................................108 Emergency Descent ....................................................................................................182 Maximum Range Glide................................................................................................125 Flaps Up Landing .........................................................................................................115 POWER PLANT LIMITATIONS NUMBER OF ENGINES.............................................................................................Two ENGINE MANUFACTURER....................................... Pratt & Whitney Canada Corp. ENGINE MODEL NUMBER..............................................................................PT6A-21 POWER LEVERS - Do not lift power levers in flight. Lifting the power levers in flight, or moving the power levers in flight below the flight idle position, could result in a nose-down pitch and a descent rate leading to aircraft damage and injury to personnel.




C90B ENGINE OPERATING LIMITATIONS Operating Condition STARTING LOW IDLE HIGH IDLE TAKEOFF AND MAX CONT. CRUISE CLIMB AND REC (NORMAL) CRUISE MAX REVERSE (9) TRANSIENT

SHP

TORQUE MAXIMUM FT-LBS OBSERVED (1) ITT ºC 1090 (4) 660 (5)

GAS GENERATOR RPM N1 RPM %

PROP RPM N2

58 (min) 1100 (min) 70 (approx)

OIL PRESS. PSI (2) 40 (MIN)

OIL TEMP ºC (3) -40 (MIN) -40 to 99 -40 to 99

550

1315

695

38,100

101.5

2200

80 to 100

10 to 99

538

1315 (6)

695

38,100

101.5

2200

80 to 100

0 to 99

88

2100

80 to 100

0 to 99

102.6

2420

200

0 to 99

695 1500 (4)

825 (4) (8)

38,500

FOOTNOTES: (1) Maximum permissible sustained torque is 1315 ft-lbs. Propeller speeds (N2) must be set so as not to exceed power limitation. (2) When gas generator speeds are above 72% N1 and oil temperatures are between 60ºC and 70ºC, normal oil pressure is between 80 and 100 psi. During extremely cold starts, oil pressure may reach 200 psi. Oil pressure between 40 and 80 psi is undesirable; it should be tolerated only for the completion of the flight, and then only at a reduced power setting. Oil pressure below 40 psi is unsafe; it requires that either the engine be shut down, or that a landing be made at the nearest suitable airport, using the minimum power required to sustain flight. (3) For increased service life of engine oil, an oil temperature of between 74o to 80oC is recommended. A minimum oil temperature of 55oC is recommended for fuel heater operation at take-off power. (4) These values are time-limited to two seconds. (5) High ITT at ground idle may be corrected by reducing accessory load and/or increasing N1 RPM. (6) Cruise torque values vary with altitude and temperature. (7) Reverse power operation is limited to one minute. (8) High generator loads at low N1 speeds may cause the ITT transient temperature limit to be exceeded. Observe generator load limits.




C90A / C90SE ENGINE OPERATING LIMITATIONS Operating Condition STARTING LOW IDLE HIGH IDLE TAKEOFF AND MAX CONT. CRUISE CLIMB AND REC (NORMAL) CRUISE MAX REVERSE (9) TRANSIENT

SHP

TORQUE MAXIMUM FT-LBS OBSERVED (1) ITT ºC 1090 (4) 660 (5)

GAS GENERATOR RPM N1 RPM %

PROP RPM N2

58 (min) 70 (approx)

OIL PRESS. PSI (2) 40 (MIN)

OIL TEMP ºC (3) -40 (MIN) -40 to 99 -40 to 99

550

1315

695

38,100

101.5

2200

80 to 100

10 to 99

538

1315 (6)

695

38,100

101.5

2200

80 to 100

0 to 99

88

2100

80 to 100

0 to 99

102.6

2420

200

0 to 99

695 1500 (4)

825 (4) (8)

38,500

FOOTNOTES: (1) Maximum permissible sustained torque is 1315 ft-lbs. Propeller speeds (N2) must be set so as not to exceed power limitation. (2) When gas generator speeds are above 72% N1 and oil temperatures are between 60ºC and 70ºC, normal oil pressure is between 80 and 100 psi. During extremely cold starts, oil pressure may reach 200 psi. Oil pressure between 40 and 80 psi is undesirable; it should be tolerated only for the completion of the flight, and then only at a reduced power setting. Oil pressure below 40 psi is unsafe; it requires that either the engine be shut down, or that a landing be made at the nearest suitable airport, using the minimum power required to sustain flight. (3) For increased service life of engine oil, an oil temperature of between 74o to 80oC is recommended. A minimum oil temperature of 55oC is recommended for fuel heater operation at take-off power. (4) These values are time-limited to two seconds. (5) High ITT at ground idle may be corrected by reducing accessory load and/or increasing N1 RPM. (6) Cruise torque values vary with altitude and temperature. (7) Reverse power operation is limited to one minute. (8) High generator loads at low N1 speeds may cause the ITT transient temperature limit to be exceeded. Observe generator load limits.




EXTERNAL POWER LIMITS External power carts will be set to 28.0 – 28.4 volts and be capable of generating a minimum of 1000 amps momentarily and 300 amps continuously.

GENERATOR LIMITS Maximum sustained generator load is limited as follows: In flight: 100% During ground operation, observe the following limitations: C90B GENERATOR LOAD 0 to 50% 50% to 80% 80% to 85%

C90A / C90SE MINIMUM N 1

GENERATOR LOAD 0 to 50% 50% to 80% 80% to 85%

59% 61% 70%

MINIMUM N 1 51% 61% 70%

STARTER LIMITS Use of the starter is limited to 40 seconds ON, 60 seconds OFF, 40 seconds ON, 60 seconds OFF, 40 seconds ON, then 30 minutes OFF. FUEL LIIMITS APPROVED ENGINE FUELS COMMERCIAL GRADES Jet A, Jet A-1, Jet B MILITARY GRADES JP-4, JP-5, JP -8

EMERGENCY ENGINE FUELS COMMERCIAL AVIATION GASOLINE GRADES 80 Red (Formerly 80/87) 100LL Blue* 100 Green (Formerly 100/130) * In some countries, this fuel is colored Green and designated “100L”. MILITARY AVIATION GASOLINE GRADES 80/87 Red 100/130 Green 115/145 Purple




LIMITATIONS ON THE USE OF AVIATION GASOLINE 1.

Operation is limited to 150 hours between engine overhauls.

2.

Operation is limited to 8,000 feet pressure altitude or below with boost pumps inoperative.

3.

Crossfeed capability is required for climbs above 8,000 feet pressure altitude.

FUEL MANAGEMENT USABLE FUEL (GALLONS X 6.7 = POUNDS) Total Usable Fuel Quantity....................................................................384 gallons (2573 pounds) Useable Fuel, Each Side.............................................................. 192 gallons (1286.5 pounds) Useable Fuel, Each Wing Tank ......................................................132 gallons (884.5 pounds) Useable Fuel, Each Nacelle Tank ....................................................... 60 gallons (402 pounds)

FUEL IMBALANCE Maximum allowable fuel imbalance between wing fuel systems is 200 pounds (C90B and C90SE only).

FUEL CROSSFEED Crossfeeding of fuel of fuel is permitted only in the event of: 1.

Electric boost pump failure, or

2.

Engine Failure

FUEL GAGES IN THE YELLOW ARC Do not take off if fuel quantity gages indicate in the yellow arc or indicate less than 265 pounds of fuel in each wing system.

OPERATING WITH LOW FUEL PRESSURE Operation of either engine with its corresponding fuel pressure annunciator (L FUEL PRESS or R FUEL PRESS) illuminated is limited to 10 hours before overhaul or replacement of the engine-driven fuel pump. Windmilling time need not be charged against this time limit.

BOOST PUMPS Both boost pumps must be operational prior to takeoff.




PROPELLER BLADE ANGLES AT 30-INCH STATION HARTZELL PROPELLER (LJ-1542 and after) Feathered +85.8º = 0.2º, Reverse –10.0º = 0.2º

McCAULEY PROPELLER (Prior to LJ-1542) Feathered +87º, Reverse –11º

PROPELLER ROTATIONAL SPEED LIMITS Transients not exceeding 5 seconds ........................................................................................ 2420 rpm Reverse................................................................................................................................. 2100 rpm All other conditions ................................................................................................................. 2200 rpm

PROPELLER ROTATIONAL OVERSPEED LIMITS The maximum propeller overspeed limit is 2420 rpm and is time-limited to five seconds. Sustained propeller overspeeds faster than 2200 rpm indicate failure of the primary governor. Sustained propeller overspeeds faster than 2288 rpm indicate failure of both the primary governor and overspeed governor.

WEIGHT LIMITS Maximum Ramp Weight ..................................................................... 10,160 pounds (LJ-1138 and after) 9,710 pounds (Prior to LJ-1138) Maximum Take-off Weight ................................................................. 10,100 pounds (LJ-1138 and after) 9,650 pounds (Prior to LJ-1138) Maximum Landing Weight ....................................................................9,600 pounds (LJ-1138 and after) 9,168 pounds (Prior to LJ-1138) Maximum Zero Fuel Weight ...............................................................................................No Limitation Maximum Weight in Rear Baggage Compartment...................... 350 pounds (incl. lavatory seat occupant) Maximum Weight in Avionics Compartment ...........................................................................350 pounds

MINIMUM FLIGHT CREW One pilot.

MAXIMUM OPERATING PRESSURE-ALTITUDE LIMIT 30,000 feet

MAXIMUM OUTSIDE AIR TEMPERATURE LIMITS ISA +37ºC




CABIN PRESSURIZATION LIMIT Maximum Cabin Pressure Differential .......................................................................................... 5.1 psi

MAXIMUM OCCUUPANCY LIMIT Thirteen (13) including crew

LANDING GEAR CYCLE LIMITS Landing gear cycles (1 up – 1 down) are limited to one every 3 minutes for a total of 10 cycles followed by a 15 minute cool down period.

ICING LIMITATIONS Minimum Ambient Temperature for Operation of Deicing Boots .......................................................-40ºC Minimum Airspeed for Sustained Icing Flight ........................................................................... 140 Knots Sustained Flight in icing conditions with flaps extended is prohibited except for approach and landings. ENGINE ANTI-ICE shall be ON for operation in ambient temperature of +5ºC when flight free of visible moisture cannot be assured.

APPROVED AIRPLANE DEICING/ANTI-ICING FLUIDS SAE AMS 1424 Type I ISO 11075 Type I SAE AMS 1428 Type II ISO 11078 Type II SAE AMS 1428 Type IV. Only the following type IV fluids are approved: Clariant Safewing MP IV 1957 Clariant Safewing MP IV 2001 UCAR ULTRA+ (Approved for use down to –15ºC) Octagon Max Flight Type IV




LIMITATIONS WHEN ENCOUNTERING SEVERE ICING CONDITIONS (Required By FAA AD 98-04-24) WARNING Severe icing may result from environmental conditions outside of those for which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfac es. This ice may not be shed using the ice protection systems, and may seriously degrade the performance and controllability of the airplane.

1.

During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following visual cues. If one or more of these visual cues exists, immediately request priority handling from Air Traffic Control to facilitate a route or an altitude change to exit the icing conditions. a.

Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice.

b.

Accumulation of ice on the upper surface of the wing aft of the protected area.

c.

Accumulation of ice on the propeller spinner 14 further aft than normally observed.

2.

Since the autopilot, when installed and operating, may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when any of the visual cues specified above exist or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions.

3.

All icing detection lights must be operative prior to flight into icing conditions at night. [NOTE: This supersedes any relief provided by the Master Minimum Equipment List (MMEL).]

CRACKED OR SHATTERED WINDSHIELD The following limitations apply when continued flight is required with a cracked outer or inner ply of the windshield. 1.

Continued flight with a cracked windshield is limited to 25 flight hours.

2.

Windshields which have a shattered inner ply will have numerous cracks which will obstruct forward vision and may produce small particles or flakes of glass that can break free of the windshield and interfere with the crew’s vision. These windshields must be replaced prior to the next flight unless a special flight permit is obtained from the local FAA Flight Standards Office.

3.

Crack(s) must not impair visibility.

4.

Crack(s) must not interfere with the use of windshield wipers for flights requiring the use of the wipers.

5.

Windshield Anti-ice must be operational for flights in icing conditions.

6.

The following placard must be installed in plain view of the pilot: MAXIMUM AIRPLANE ALTITUDE IS LIMITED TO 25,000 FEET. CABIN ?P MUST BE MAINTAINED BETWEEN 2.0 AND 4.6 PSI DURING FLIGHT

Windshields that have cracks in both the inner and outer plies must be replaced prior to the next flight unless a special flight permit is obtained from the local FAA Flight Standards District Office.




CRACK IN ANY SIDE WINDOW (COCKPIT OR CABIN) The following limitations apply when continued flight is required with a cracked outer or inner ply in any side window. These limitations do not apply to minor compression-type chips (Clamshell) which may occur on the milled edge of cockpit side windows. Refer to the maintenance manual for the disposition of such chips. 1.

Continued flight is limited to 25 flight hours.

2.

Flights must be conducted with the cabin depressurized. The following placard must be installed in clear view of the pilot: PRESSURIZED FLIGHT IS PROHIBITED DUE TO A CRACKED SIDE WINDOW. CONDUCT FLIGHT WITH THE CABIN PRESSURE SWITCH IN THE DUMP POSITION

KINDS OF OPERATIONS The Beech King Air C90A and C90B are approved for the following types of operations when the required equipment, as shown in the KINDS OF OPERATIONS EQUPMENT LIST, is installed and operable. 1.

VFR Day

2.

VFR Night

3.

IFR Day

4.

IFR Night

5.

Icing Conditions




TRIPLE-FED ELECTRICAL SYSTEM




FUEL SYSTEM




KING AIR C90A/B INITIAL PILOT COURSE SYLLABUS (Typical) Day Day 1 (Monday)

Day 2 (Tuesday)

Day 3 (Wednesday)

Day 4 (Thursday)

Day 5 (Friday)

Ground School 4 Hours Ground School istration Facilities tour Aircraft General CRM Avionics 4 Hours Ground School Powerplant Weight & Balance / POH/AFM Master Warning Electrical System 4 Hours Ground School Lighting Fuel Propellers

Simulator Session 1 1 Hour Brief 2 or 4 Hour Simulator 30 Min. Debrief Session 2 1 Hour Brief 2 or 4 Hour Simulator 30 Min. Debrief Session 3 1 Hour Brief 2 or 4 Hour Simulator

4 Hours Ground School Pneumatics Environmentals Pressurization Oxygen Ice and Rain Protection 4 Hours Ground School Performance / Flight Planning Landing Gear & Brakes Flight Controls Fire Detection and Extinguishing Aircraft General Windshear End of Course Exam and Critique Factory Tour

30 Min. Debrief Session 4 1 Hour Brief 2 or 4 Hour Simulator 30 Min. Debrief Session 5 1 Hour Brief 2 or 4 Hour Simulator 30 Min. Debrief

Day 6 (Saturday)

14 CFR § 135 or ATP checkride (if applicable)

Day 7 (Sunday)

Line Oriented Flight Training (if required for 14 CFR § 135 operations)




GRADING AND EVALUATION STANDARDS (Applicable for ATP and 14 CFR § 135 Clients) NOTE: For § 91 clients, not accomplishing an ATP check, the appropriate PTS for the level of certificate held would apply. ATP or FlightSafety Proficiency Card (“ProCard”) Completion Standards: The pilot must perform all procedures and maneuvers to the tolerances listed in the AIRLINE TRANSPORT PILOT AND AIRCRAFT TYPE RATING Practical Test Standards for AIRPLANE (ATP PTS) to successfully complete the course . For a ProCard to be issued to any pilot, the pilot must consistently exceed the standards defined in the ATP PTS throughout the course. 1. Takeoff a. Heading b. Airspeed

± 5° ± 5 KIAS

2. Departure, Cruise, Holding, and Arrival a. Altitude b. Heading c. Airspeed

± 100 feet ± 10° ± 10 KIAS

3. Steep Turns a. Altitude b. Rollout Heading c. Bank Angle d. Airspeed

± 100 feet ± 10° ± 5° ± 10 KIAS

4. Approach to Stall a. Recognize Perceptible Stall or Stall Warning b. Recover at First Indication of Stall c. Strive for Minimum Altitude Loss 5. IFR Approaches (Prior to Final Approach) a. Precision (1) Altitude (2) Heading (3) Airspeed

± 100 feet ± 5° ± 10 KIAS

b. Nonprecision (1) Altitude (2) Heading (3) Airspeed

± 100 feet ± 5° ± 10 KIAS




Grading and Evaluation Standards (continued) 6. IFR Approaches (During Final Approach) a. Precision Approach (1) CDI (2) GS (3) Airspeed

± ¼ Scale Deflection ± ¼ Scale Deflection ± 5 KIAS

b. Nonprecision Approach (1) CDI (2) RMI (3) Bearing Pointer (4) MDA (5) Airspeed

± ¼ Scale Deflection ± 5° Deviation ± 5° Deviation +50, – 0 feet ± 5 KIAS

c. Circling (1) MDA (2) Heading/Track (3) Airspeed (4) Bank

+ 100, – 0 feet ± 5° ± 5 KIAS Should not exceed 30°

7. Missed Approach a. Altitude b. Heading c. Airspeed


± 100 feet ± 5° ± 5 KIAS


C90ab Pre-course Study Guide R1.1 p2042

Overview 4q3b3c

More details 26j3b

Related Documents 171j1w

C90ab Pre-course Study Guide R1.1 p2042

Celta Precourse Task 6n4b3c

Manual Acer Aspire R11 6521v

Study Guide 5v19

Study Guide 5v19

Study Guide 5v19

More Documents from "Preston Bakic" 6g1y71

C90ab Pre-course Study Guide R1.1 p2042

Sr22t G3 Poh - Cirrus Perspective 135h3j

1.1 Essence Of Hospitality Industry 604s6x

2004_polaris_sportsman_600_700_atv_s.pdf 6x68c

2c82t

07 Reglas De La Natacion 252h5q