King Air C90A/B
Initial Pilot Course
Pre-Attendance
Study Guide
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
2
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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)
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
3
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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 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 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/verify61-75.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 contact Customer Support at (800) 488-3747 or (316) 612-5300.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
4
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
5
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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 verify FEATHER if
autofeather is Installed)
5. Airspeed..........................108 KNOTS (after obstacle clearance altitude is reached)
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
6
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
7
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
8
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
9
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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 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
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%
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
10
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Verify [L FUEL PRESS] on, then extinguished.
Verify [FUEL CROSSFEED] on.
Left Boost Pump ......................................................................................................ON
Crossfeed ................................................................................CLOSE, THEN AUTO
Verify [FUEL CROSSFEED] extinguished.
Right Boost Pump..................................................................................................OFF
Verify [R FUEL PRESS] on, then extinguished.
Verify [FUEL CROSSFEED] on.
Right Boost Pump ...................................................................................................ON
Crossfeed ................................................................................CLOSE, THEN AUTO
Verify [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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
11
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
COLLINS APS-65H AUTOPILOT (Before Takeoff – Runup)
1. Pitch Trim................................................................................ TAKEOFF POSITION
2. Elevator Trim Switch ..............................................................................................ON
3. Autopilot.........................................................................................................ENGAGE
Verify [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
Verify the [YAW D IS] 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 copilot’s 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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
12
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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 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 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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
13
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Verify [L ENGINE ANTI-ICE], [R ENGINE ANTI-ICE] extinguished.
Both ANTI-ICE ACTUATOR Switches ............................................................MAIN
Both ENGINE ANTI-ICE ON-OFF Switches ......................................................ON
Verify [L ENGINE ANTI-ICE], [R ENGINE ANTI-ICE] illuminated.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
14
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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 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
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 loadmeter.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
15
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
16
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
17
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
18
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
19
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
20
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
21
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
22
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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.
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
23
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
24
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
TRIPLE-FED ELECTRICAL SYSTEM
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
25
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
FUEL SYSTEM
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
26
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Administration
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)
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
27
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
FOR TRAINING PURPOSES ONLY
28
King Air C90A/B Initial Pilot Course
Pre-Attendance Study Guide
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
Copyright © 2002 FlightSafety International
August, 2005 – Revision 1.1
± 100 feet
± 5°
± 5 KIAS
FOR TRAINING PURPOSES ONLY
29