C90AB Pre-Course Study Guide r1.1

7/25/2019 C90AB Pre-Course Study Guide r1.1

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Copyright 2002 FlightSafety International FOR TRAINING PURPOSES ONLYAugust, 2005 Revision 1.1

King Ai r C90A/ B

Initial Pilot Course

Pre-Attendance

Study Guide


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King Air C90A/B Initial Pilot CoursePre-Attendance Study Guide

Copyright 2002 FlightSafety International FOR TRAINING PURPOSES ONLY

August, 2005 Revision 1.1 2

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


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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 giveyou 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 LimitsInitial Pilot Course Syllabus

Grading Standards

We look forward to having you as our guest for training and thank you for choosingFlightSafety International for your King Air training needs.

Sincerely,

Barry BarlowKing 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 AvenueWichita, KS 67206

(316) 612-5300(800) 488-3747(316) 612-5399 (fax)


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DOCUMENTATION REQUIREMENTS

Clients attending a King Air C90A/B training course must provide a VALID PILOT

CERTIFICATE (with Instrument and Multi-Engine ratings) and MEDICALCERTIFICATEon the first day of training

NOTE:

Non -U.S. ci t izens seeking the issu ance of an Air l ine Transpo rt Pi lot cer t i f icate

As of August, 2005 there are no United States Transportation Security Administration(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 ratingmust first fill out a Verification of Authenticity of Foreign License, Rating, and Medical.

The form can be found at: http://registry.faa.gov/docs/verify61-75.pdf. Block 10 on theform 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:

FAAs Airmen Certification Branch

AFS-760, P.O. Box 25082Oklahoma City, OK 73125

Or fax it to 405-954-4105.

If you have any questions or concerns regarding these requirements or any otherissues, please contact Customer Support at (800) 488-3747 or (316) 612-5300.


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COURSE ATTENDANCE PREREQUISITES

The prerequisites for attendance of the King Air C90A/B Initial Pilot Training Course are:

At least an FAA Private Pilot Certificate, or ICAO recognized equivalent Valid Instrument Rating

Valid Multi-Engine Rating

ATP REQUIREMENTS

Pilots seeking an Airline Transport Pilot rating in a King Air C90B simulator can receive100% of that checkride in the simulator provided they comply with the eligibility criteriaas 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: Original ATP knowledge test result form Logbook(s) to document required 14 CFR 61.159 requirements All documents required for course attendance

61.159 Eligibility Requirements:

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 timeo 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 trainingdevice, 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 thesupervision 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 deviceas part of a 142 approved training course


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C90A/B EMERGENCY PROCEDURES(Memory Items)

EMERGENCY ENGINE SHUTDOWN1. 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

I f Insuff ic ient Runway Remains for Stop ping:3. Condition Levers .........................................................................................FUEL CUT OFF

4. Firewall Shutoff Valves ..........................................................................................CLOSED5. Master Switch ...................................................................................OFF (Gang bar down)

6. Boost Pumps .....................................................................................................................OFF

ENGINE FAILURE AFTER LIFT-OFF (If Conditions Preclude an ImmediateLanding)

1. Maximum Continuous Power.......................................................................................SET

2. Airspeed.................................................................MAINTAIN (take-off speed or above)

3. Landing Gear ......................................................................................................................UP

4. Propeller Lever (Inoperative engine)..................... FEATHER (or verify FEATHER if

autofeather is Installed)5. Airspeed..........................108 KNOTS (after obstacle clearance altitude is reached)


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ENGINE FAILURE IN FLIGHT BELOW AIR MINIMUM CONTROL AIRPEED (VMCA)

1. Reduce power on operative engine as required to maintain directional control.

2. Lower nose to accelerate above VMCA.

ENGINE FLAMEOUT (2ndEngine)

1. Power Levers ....................................................................................................................IDLE

2. Propeller..................................................................................................DO NOT FEATHER

3. Condition Lever ..........................................................................................FUEL CUT OFF

4. Conduct Air Start.

SMOKE AND FUME ELIMINATIONELECTRICAL 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)

I f the CAB IN DOOR Annu nciator I l luminates, or If an Unlock ed Cabin Door is

Suspected:

1. All Occupants ........................SEATED WITH SEAT BELTS SECURELY FASTENED

EMERGENCY DESCENT


2. Propeller Levers....................................................................................................HIGH RPM

3. Flaps .....................................................................................................................APPROACH

4. Landing Gear ................................................................................................................DOWN

5. Airspeed............................................................................................182 KNOTS MAXIMUM


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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


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LOSS OF PRESSURIZATION (CABIN ALT HI Annunciator)

1. Oxygen System Control................................................................................CONFIRM ON

2. Crew .................................................................................................................... DON MASKS

SPINS

I f a Spin is Entered Inadvertent ly :

1. Control Column........................................................................................ FULL FORWARD

2. Full Rudder....................................................................OPPOSITE DIRECTION OF SPIN


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.


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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 mannergreatly 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 PANEL CHECK (Before Engine Starting)

1. Fuel Panel 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

ELECTRICAL SYSTEM CHECK (Before Taxi)

1. Gen Ties ..............................................................................................................OPEN

[L GEN TIE OPEN] & [R GEN TIE OPEN] illuminated.

2. 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

3. Gen Ties .............................................................................................................NORM

[L GEN TIE OPEN] & [R GEN TIE OPEN] extinguished.

4. Bus Sense Switch........................................................MOMENTARILLY TO TEST

[L GEN TIE OPEN], [BAT TIE OPEN] & [R GEN TIE OPEN] illuminated.

5. Voltmeter (CTR) ............................................................................................0 VOLTS

6. Bus Sense Switch....................................................MOMENTARILLY TO RESET

[L GEN TIE OPEN], [BAT TIE OPEN] & [R GEN TIE OPEN] extinguished.

7. Voltmeter (CTR) .........................................................................27.5 to 29.0 VOLTS

8. Generator Load ...........................................................PARALLELED WITHIN 10%


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BOOST PUMP/AUTO CROSSFEED TEST (Before Takeoff Runup)

1. Left Boost Pump ....................................................................................................OFF

Verify [L FUEL PRESS] on, then extinguished.

Verify [FUEL CROSSFEED] on.2. Left Boost Pump ......................................................................................................ON

3. Crossfeed ................................................................................CLOSE, THEN AUTO

Verify [FUEL CROSSFEED] extinguished.

4. Right Boost Pump..................................................................................................OFF

Verify [R FUEL PRESS] on, then extinguished.

Verify [FUEL CROSSFEED] on.

5. Right Boost Pump ...................................................................................................ON

6. Crossfeed ................................................................................CLOSE, THEN AUTO

Verify [FUEL CROSSFEED] extinguished.

PRESSURIZATION (Before Takeoff Runup)

1. Bleed Air Valves ................................................................................................OPEN

2. Condition Levers ........................................................................................HIGH IDLE

3. Pressurization Controller......................................................................................SET

Adjust cabin altitude knob to indicate 1,000 feet below field pressure altitude.

Set rate knob to 12-oclock position.

4. Cabin Pressure Switch .......................................HOLD AT THE TEST POSITION

5. Cabin Altimeter and VSI...........................CHECK FOR DESCENT INDICATION

6. Cabin Pressure Switch.....................................RELEASE TO PRESS POSITION7. 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.

8. Condition Levers ...............................................................................AS REQUIRED


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COLLINS APS-65H AUTOPILOT (Before Takeoff Runup)

1. Pitch Trim................................................................................TAKEOFF POSITION

2. Elevator Trim Switch ..............................................................................................ON

3. Autopilot.........................................................................................................ENGAGEVerify [YAW], [A/P], and [ALT ARM] illuminated.

4. Control Wheel ......................................................................FORWARD POSITION

Operate pilots 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

Verify the [YAW DIS] and [AP DIS] annunciators illuminate.

9. DISC TRIM/AP YD Button........................................DEPRESS TO NEXT LEVEL

Verify that the [PITCH TRIM OFF] annunciator illuminates.

10. Elevator Trim Switch........................................................................................RESET

Verify that the [PITCH TRIM OFF] annunciator extinguishes.

11. Repeat items 2 through 10 for copilots side.

12. Yaw Damper .................................................................................................ENGAGE

Verify [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. Verify that controls move in proper direction and no restrictions to free

movement are present.


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ELECTRIC PITCH TRIM (Before Takeoff Runup)

1. Electric Pitch Trim ...................................................................................................ON

2. Pilots and Copilots Switches:

a. Ensure that the electric pitch trim does not operate when only one switchon 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 verify that the electric pitch

trim is disconnected and the [PITCH TRIM OFF] annunciator is illuminate.

d. Cycle the pitch trim switch. Verify 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 RUDDERPEDAL 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


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AUTOFEATHER (Before Takeoff Runup)

1. Power Levers ....................................................... APPROXIMATELY 500 FT-LBS

2. Autofeather Switch..........................................................................HOLD TO TEST

[L AUTOFEATHER] & [R AUTOFEATHER] illuminated.3. 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

4. Left Power Lever ..................................................APPROXIMATELY 500 FT-LBS

5. Repeat Steps 3 and 4 for Right Power Lever.

6. Both Power Levers ............................................................................................... IDLE

[L AUTOFEATHER] & [R AUTOFEATHER] EXTINGUISH AND

NEITHER PROP FEATHERS

ENGINE ANTI-ICE (Before Takeoff Runup)

1. Both ANTI-ICE ACTUATOR Switches ...................................................STANDBY

2. Both ENGINE ANTI-ICE ON-OFF Switches ....................................................OFF

Verify [L ENGINE ANTI-ICE], [R ENGINE ANTI-ICE] extinguished.

3. Both ANTI-ICE ACTUATOR Switches ............................................................MAIN

4. Both ENGINE ANTI-ICE ON-OFF Switches ......................................................ON

Verify [L ENGINE ANTI-ICE], [R ENGINE ANTI-ICE] illuminated.


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ICE PROTECTION (Before Takeoff Runup)

1. Engine Auto-Ignition.

a. Power Levers ..................................................................................................IDLE

b. Engine Auto-ignition Switches .....................................................................ARMc. [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 Loadmeters.

b. Pilot and Copilot Windshield Anti-ice ............................OFF, THEN NORMAL

Observe Loadmeters.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

CAUTIONOperation 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 loadmeter.


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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 limitationsin other words, youd bewise to memorize them, especial ly if you are taking an ATP or 14 CFR 135 checkride!

AIRSPEED LIMITATIONS

VA - Maneuvering Speed.........................................................................................169VFE - Maximum Flap Extension/Extended Speed

Approach Position 35% (White triangle) ...................................................184Full Down Position 100% (White arc) ........................................................148

VLO - Maximum Landing Gear Operating Speed

Extension........................................................................................................... 182Retraction..........................................................................................................163

VLE - Maximum Landing Gear Extended Speed ...................................................182VMCA- Air Minimum Control Speed (Red line)..............................90 (C90A / C90SE)

80 (C90B)

VMO/MMO - 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-o f-Climb .............................................100VYSE- 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 ....................................................................................................182Maximum Range Glide................................................................................................125

Flaps Up Landing .........................................................................................................115

POWER PLANT LIMITATIONS

NUMBER OF ENGINES.............................................................................................TwoENGINE MANUFACTURER.......................................Pratt & Whitney Canada Corp.ENGINE MODEL NUMBER..............................................................................PT6A-21POWER 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, couldresult in a nose-down pitch and a descent rate leading to aircraft damage and

injury to personnel.


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C90B ENGINE OPERATING LIMITATIONS

Operating TORQUE MAXIMUM GAS GENERATOR PROP OIL OIL

Condition SHP FT-LBS OBSERVED RPM N1 RPM PRESS. TEMP

(1) ITT C RPM % N2 PSI (2) C(3)STARTING 1090 (4) -40 (MIN)

LOW IDLE 660 (5) 58 (min) 1100 (min) 40 (MIN) -40 to 99

HIGH IDLE 70 (approx) -40 to 99

TAKEOFF

AND MAX 550 1315 695 38,100 101.5 2200 80 to 100 10 to 99

CONT.

CRUISE CLIMB

AND REC 538 1315 695 38,100 101.5 2200 80 to 100 0 to 99

(NORMAL) (6)

CRUISE

MAX REVERSE (9) 695 88 2100 80 to 100 0 to 99

TRANSIENT 1500 (4) 825 (4) (8) 38,500 102.6 2420 200 0 to 99

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 60C and 70C, normal oil pressure isbetween 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 betolerated only for the completion of the flight, and then only at a reduced power setting. Oil pressure below 40 psi is unsafe; itrequires that either the engine be shut down, or that a landing be made at the nearest suitable airport, using the minimumpower required to sustain flight.

(3) For increased service life of engine oil, an oil temperature of between 74oto 80oC is recommended. A minimum oil temperature

of 55

o

C is recommended for fuel heater operation at take-off power.(4) These values are time-limited to two seconds.

(5) High ITT at ground idle may be corrected by reducing accessory load and/or increasing N1RPM.

(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 loadlimits.


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C90A / C90SE ENGINE OPERATING LIMITATIONS

Operating TORQUE MAXIMUM GAS GENERATOR PROP OIL OIL

Condition SHP FT-LBS OBSERVED RPM N1 RPM PRESS. TEMP

(1) ITT C RPM % N2 PSI (2) C(3)STARTING 1090 (4) -40 (MIN)

LOW IDLE 660 (5) 58 (min) 40 (MIN) -40 to 99

HIGH IDLE 70 (approx) -40 to 99

TAKEOFF

AND MAX 550 1315 695 38,100 101.5 2200 80 to 100 10 to 99

CONT.

CRUISE CLIMB

AND REC 538 1315 695 38,100 101.5 2200 80 to 100 0 to 99

(NORMAL) (6)

CRUISE

MAX REVERSE (9) 695 88 2100 80 to 100 0 to 99

TRANSIENT 1500 (4) 825 (4) (8) 38,500 102.6 2420 200 0 to 99

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 60C and 70C, normal oil pressure isbetween 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 betolerated only for the completion of the flight, and then only at a reduced power setting. Oil pressure below 40 psi is unsafe; itrequires that either the engine be shut down, or that a landing be made at the nearest suitable airport, using the minimumpower required to sustain flight.

(3) For increased service life of engine oil, an oil temperature of between 74oto 80oC is recommended. A minimum oil temperature

of 55

o

C is recommended for fuel heater operation at take-off power.(4) These values are time-limited to two seconds.

(5) High ITT at ground idle may be corrected by reducing accessory load and/or increasing N1RPM.

(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 loadlimits.


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EXTERNAL POWER LIMITS

External power carts will be set to 28.0 28.4 volts and be capable of generating aminimum 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 C90A / C90SE

GENERATORLOAD

MINIMUM N1 GENERATORLOAD

MINIMUM N1

0 to 50% 59% 0 to 50% 51%

50% to 80% 61% 50% to 80% 61%80% to 85% 70% 80% to 85% 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


20/29




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 andC90SE 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 FUELPRESS) 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.


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PROPELLER BLADE ANGLES AT 30-INCH STATION

HARTZELL PROPELLER (LJ-1542 and after)

Feathered +85.8 = 0.2, Reverse 10.0 = 0.2

McCAULEY PROPELLER (Prior to LJ-1542)

Feathered +87, Reverse 11

PROPELLER ROTATIONAL SPEED LIMITS

Transients not exceeding 5 seconds .................................................... .................................... 2420 rpm

Reverse........................................................ ........................................................ ................. 2100 rpm

All other conditions ... ......... ............ ......... ......... ......... ......... ......... ......... ......... ......... ......... ........ 2200 rpm

PROPELLER ROTATIONAL OVERSPEED LIMITSThe maximum propeller overspeed limit is 2420 rpm and is time-limited to five seconds. Sustainedpropeller overspeeds faster than 2200 rpm indicate failure of the primary governor. Sustained propelleroverspeeds 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)


Maximum Landing Weight ..... ...... ..... ..... ...... ..... ...... ..... ...... ...... ..... ...... ..9,600 pounds (LJ-1138 and after)


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 +37C


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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 bya 15 minute cool down period.

ICING LIMITATIONS

Minimum Ambient Temperature for Operation of Deicing Boots ..... ...... ..... ...... ..... ..... ...... ..... ...... ..... .-40C

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 +5C 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 15C)

Octagon Max Flight Type IV


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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 surfacesexceeding the capability of the ice protection system, or may result in ice forming aft of the protected surfac es. This ice may not beshed 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 bedetermined by the following visual cues. If one or more of these visual cues exists, immediatelyrequest 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 collectice.

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 cuesspecified above exist or when unusual lateral trim requirements or autopilot trim warnings areencountered while the airplane is in icing conditions.

3. All icing detection lights must be operative prior to flight into icing conditions at night. [NOTE: Thissupersedes 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 thewindshield.

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 obstructforward vision and may produce small particles or flakes of glass that can break free of the

windshield and interfere with the crews vision. These windshields must be replaced prior to thenext 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 thewipers.

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 BEMAINTAINED 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 flightunless a special flight permit is obtained from the local FAA Flight Standards District Office.


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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 anyside window. These limitations do not apply to minor compression-type chips (Clamshell) which mayoccur 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 requiredequipment, 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


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TRIPLE-FED ELECTRICAL SYSTEM


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FUEL SYSTEM


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

Day Ground School SimulatorDay 1(Monday)

4 Hours Ground SchoolAdministrationFacilities tour

Aircraft GeneralCRMAvionics

Session 1

1 Hour Brief

2 or 4 Hour Simulator

30 Min. Debrief

Day 2(Tuesday)

4 Hours Ground School

PowerplantWeight & Balance / POH/AFMMaster Warning

Electrical System

Session 2

1 Hour Brief


30 Min. Debrief

Day 3(Wednesday) 4 Hours Ground SchoolLightingFuelPropellers

Session 31 Hour Brief


30 Min. DebriefDay 4(Thursday)

4 Hours Ground SchoolPneumatics

EnvironmentalsPressurizationOxygen

Ice and Rain Protection

Session 4

1 Hour Brief


30 Min. Debrief

Day 5(Friday)

4 Hours Ground School

Performance / Flight Planning

Landing Gear & BrakesFlight Controls

Fire Detection and ExtinguishingAircraft GeneralWindshear

End of Course Exam and CritiqueFactory Tour

Session 5

1 Hour Brief2 or 4 Hour Simulator

30 Min. Debrief

Day 6(Saturday)

14 CFR 135 or ATPcheckride (if applicable)

Day 7(Sunday)

Line Oriented Flight Training

(if required for 14 CFR 135operations)


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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 thelevel 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 TRANSPORTPILOT AND AIRCRAFT TYPE RATING Practical Test Standards for AIRPLANE (ATP PTS) tosuccessfully complete the course . For a ProCardto be issued to any pilot, the pilot mustconsistent ly exceedthe standards defined in the ATP PTS throughout the course.

1. Takeoff

a. Heading 5

b. Airspeed

5 KIAS2. Departure, Cruise, Holding, and Arrival

a. Altitude 100 feet

b. Heading 10

c. Airspeed 10 KIAS

3. Steep Turns


b. Rollout Heading 10

c. Bank Angle 5

d. Airspeed 10 KIAS

4. Approach to Stalla. 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 100 feet

(2) Heading 5

(3) Airspeed 10 KIAS

b. Nonprecision(1) Altitude 100 feet

(2) Heading 5

(3) Airspeed 10 KIAS


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Grading and Evaluation Standards (contin ued)

6. IFR Approaches (During Final Approach)

a. Precision Approach

(1) CDI Scale Deflection

(2) GS Scale Deflection

(3) Airspeed 5 KIAS

b. Nonprecision Approach

(1) CDI Scale Deflection

(2) RMI 5Deviation

(3) Bearing Pointer 5Deviation

(4) MDA +50, 0 feet

(5) Airspeed 5 KIAS

c. Circling

(1) MDA + 100, 0 feet

(2) Heading/Track 5

(3) Airspeed 5 KIAS

(4) Bank Should not exceed 30

7. Missed Approach


b. Heading

5

c. Airspeed 5 KIAS

Date post:	26-Feb-2018
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C90AB Pre-Course Study Guide r1.1

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