King Air C90GTx Memory Items and Limitations
NOTICE
These commodities, technology or software were exported from the United States in accordance
with the Export Administration Regulations. Diversion contrary to U.S. law is prohibited.
Based on Rev. 0.5 of Memory Flash Cards
EMERGENCY ENGINE SHUTDOWN
BOOST PUMP AND AUTO CROSSFEED FAILURE
DUAL GENERATOR FAILURE
OR
OR
AND
1. Crossfeed Switch.................................VERIFY AUTO POSITION
If crossfeed switch is in auto and FUEL PRESS annunciator
remains illuminated:
2. Crossfeed Switch.................................................................OPEN
[FUEL PRESS]—EXTINGUISHED
[CROSSFEED]—ILLUMINATED
1. Instrument Emergency Lights................................................... ON
2. Generators........................................................ RESET, THEN ON
If Either Generator Will Reset:
3. Operating Generator Load Meter.......... DO NOT EXCEED 100%
If Neither Generator Will Reset:
4. Environmental Mode Selector.................................................OFF
5. Vent Blowers.........................................................................AUTO
6. Non-Essential Equipment........................................................OFF
(IF INSTALLED)
1.
2.
3.
4.
Condition Lever..................................................... FUEL CUTOFF
Propeller Lever............................................................... FEATHER
Fuel FW Shutoff Valve........................................................CLOSE
Fire Extinguisher (if installed)
(if Fire Warning persists)................................................ ACTUATE
ELECTRICAL SMOKE OR FIRE
ENGINE FIRE ON GROUND
OR
(IF INSTALLED)
1. Condition Lever..................................................... FUEL CUTOFF
2. Fuel FW Shutoff Valve........................................................CLOSE
3. Ignition and Engine Start.....................................STARTER ONLY
ENGINE FAILURE DURING TAKEOFF
(AT OR BELOW V1)—TAKEOFF ABORTED
1. Power Levers.........................................................GROUND FINE
2. Brakes.......................................................................... MAXIMUM
(or as required to achieve stopping performance)
If Insufficient Runway Remains for Stopping:
3. Condition Levers................................................... FUEL CUTOFF
4. Fuel FW Shutoff Valve........................................................CLOSE
5. Master Switch............................................ OFF (Gang Bar down)
6. Boost Pumps...........................................................................OFF
ENGINE FAILURE DURING TAKEOFF
(AT OR ABOVE V1)—TAKEOFF CONTINUED
V1 Speed.............................. ROTATE TO APPROXIMATELY 10°
Landing Gear (When positive climb established)......................UP
Propeller (Inoperative Engine)......................VERIFY FEATHERED
Power................................................... MAXIMUM ALLOWABLE
Airspeed.....MAINTAIN V2 SPEED OR ABOVE UNTIL 400 FEET
THEN ACCELERATE TO 108 KNOTS
6. Flaps (At 400 feet and 108 knots - minimum)...........................UP
1.
2.
3.
4.
5.
ENGINE FAILURE IN FLIGHT BELOW
AIR MINIMUM CONTROL SPEED (VMCA)
1. Power..............................................................................REDUCE
2. Nose........................... LOWER TO ACCELERATE ABOVE VMCA
2ND ENGINE FLAMEOUT
1.
2.
3.
4.
Power Lever............................................................................IDLE
Propeller......................................................... DO NOT FEATHER
Condition Lever..................................................... FUEL CUTOFF
Conduct Air Start Procedure in ABNORMAL PROCEDURES.
1. Oxygen Mask(s)......................................................................DON
2. Mask Selector Switch........................................... EMER Position
3. Mic Switch(es)........................................................................ OXY
1. Rudder Boost..........................................................................OFF
ENVIRONMENTAL SYSTEM SMOKE OR FUMES
USE OF OXYGEN
1. Oxygen Mask(s)......................................................................DON
2. Mask Selector Switch........................................... EMER Position
3. Mic Switch(es)........................................................................ OXY
1. Oxygen Mask(s)......................................................................DON
2. Mic Switch(es)........................................................................ OXY
UNSCHEDULED RUDDER BOOST ACTIVATION
PRESSURIZATION LOSS
CABIN DOOR UNLOCKED
1. All Occupants.................................. SEATED WITH SEAT BELTS
SECURELY FASTENED
1. Oxygen Mask(s)......................................................................DON
2. Mic Switch(es)........................................................................ OXY
3. Descend................................................................ AS REQUIRED
EMERGENCY DESCENT
1.
2.
3.
4.
5.
Power Levers..........................................................................IDLE
Propeller Levers........................................................... HIGH RPM
Flaps (184 knots maximum)...................................... APPROACH
Landing Gear (182 knots maximum).................................. DOWN
Airspeed..................................................182 KNOTS MAXIMUM
GLIDE
1.
2.
3.
4.
5.
Landing Gear.............................................................................UP
Flaps..........................................................................................UP
Propellers.................................................................. FEATHERED
Airspeed..................................................................... 125 KNOTS
Glide Ratio...........1.8 NAUTICAL MILES FOR EACH 1000 FEET
OF ALTITUDE (decrease by 0.2 nautical miles
for each 10 knots of headwind)
6. ELT Switch................................................................................ ON
(yellow XMT blinking)
HIGH DIFFERENTIAL PRESSURE
Anytime the Differential Pressure goes into the Red Arc:
1. Cabin Altitude Controller...................... SELECT HIGHER CABIN
ALTITUDE SETTING
If Condition Persists:
2. Bleed Air Valves............................................................... CLOSED
3. Cabin Pressure (after cabin is depressurized).....................DUMP
4. Bleed Air Valves....................................................................OPEN
EMERGENCY EXIT
1. Emergency Release Hatch Cover.........................................OPEN
2. Release Button.....................................................................PUSH
3. If release button will not push, PULL hooks to override pressure
lock and then PUSH the release button.
4. PULL handle and PUSH out hatch.
SPINS
UNSCHEDULED ELECTRIC PITCH TRIM ACTIVATION
1. Airplane Attitude........ MAINTAIN USING ELEVATOR CONTROL
2. AP/TRIM Disconnect.....................DEPRESS FULLY AND HOLD
[TRIM]—ILLUMINATES
1.
2.
3.
4.
5.
Control Column...........FULL FORWARD, AILERONS NEUTRAL
Full Rudder...................... OPPOSITE THE DIRECTION OF SPIN
Power Levers..........................................................................IDLE
Rudder.........................NEUTRALIZE WHEN ROTATION STOPS
Execute a smooth pullout.
AUTOPILOT FAILURES
AUTOPILOT MISTRIM [E] OR [A]
1. Flight Controls....................................................... HOLD FIRMLY
(Control forces may exceed 25 pounds)
2. AP..............................................................................DISENGAGE
AUTOPILOT FAILURES
AUTOPILOT TRIM FAIL [TRIM]
1. Flight Controls....................................................... HOLD FIRMLY
2. AP..............................................................................DISENGAGE
AUTOPILOT FAILURES
AUTOPILOT AUTOMATIC DISENGAGEMENT
If An Automatic Disengagement Occurs:
1. Maintain Airplane Control.
2. AP/TRIM Disconnect........................... DEPRESS TO 1ST LEVEL
TO CANCEL HORN
TERRAIN AWARENESS WARNING SYSTEM + (TAWS+)
In IMC or at Night:
1. Autopilot.................................................................DISCONNECT
2. Wings...................................................................................LEVEL
3. Power............................................................. MAX ALLOWABLE
4. Pitch............................................................................. INCREASE
a. Promptly and smoothly increase pitch towards an initial pitch
attitude of 20°.
b. Adjust as required to avoid continuous buffeting and/or stall
warning.
c. Adjust to maintain 101 KIAS.
5. Gear and Flaps..........................................................................UP
LIMITATIONS
AIRSPEED LIMITATIONS
VA Maneuvering Speed
(From Centex Increased Maximum
Operating Weight Supplement).......................... 163 KIAS
Flaps:
VFE/VFO Approach.............................................. 184 KIAS
VFE/VFO Full Down.............................................. 148 KIAS
Landing Gear:
VLO (Extension)................................................... 182 KIAS
VLO (Retraction).................................................. 163 KIAS
VLE .................................................................... 182 KIAS
Air Minimum Control
Speed (VMCA)......................................85 KIAS (Flaps Up)
83 KIAS (Flaps Approach)
VMO/MMO—Maximum Operating Speed........226 KIAS or
0.46 Mach
EMERGENCY AIRSPEEDS
MISCELLANEOUS LIMITATIONS
PROPELLER ROTATIONAL OVERSPEED LIMITS
AVIONICS LIMITS
VXSE—One-Engine-Inoperative
Best Angle-of-Climb........................................... 100 KIAS
VYSE—One-Engine-Inoperative
Best Rate-of-Climb (Blue Line)........................... 108 KIAS
One-Engine-Inoperative Enroute Climb............. 108 KIAS
Emergency Descent........................................... 182 KIAS
Maximum Range Glide....................................... 125 KIAS
Maximum Operating Pressure-Altitude Limit..... 30,000 feet
Yaw Damp System:
Inoperative, Off, or Not Installed............... 24,000 feet
(From BLR Winglet System Supplement)
Maximum Outside Air Temperature Limit......... ISA +33°C
Cabin Pressurization Limit:
Maximum Cabin Differential Pressure.................... 5.1 psi
The maximum propeller overspeed limit is 2090 rpm and
may by used for all power settings during emergency
conditions. Sustained propeller overspeeds faster than
1900 rpm indicate failure of the primary governor. Sustained
propeller overspeeds faster than 1976 rpm indicate failure
of both the primary governor and the overspeed governor.
ENGINE LIMITS
STRUCTURAL LIMITATIONS
PROPELLER LIMITS
1) O
perating in the composite mode is limited to training
and display failure conditions.
2) The pilot’s and copilot’s Air Data Computers must be
operative for takeoff.
3) A
HRS 1 and 2 must be operative for takeoff.
4) The pilot’s PFD and MFD and copilot’s PFD must be
installed and operational in the normal mode for takeoff.
5) The MFD must be operational prior to engine start.
Torque—FT-LB:
Takeoff and Maximum Continuous Power...... 1520 FT-LB
Transient.......................................................... 1626 FT-LB
(From Centex Increased Maximum
Operating Weight Supplement)
Maximum Ramp Weight..................................... 10,545 lb
Maximum Takeoff Weight................................... 10,485 lb
Maximum Landing Weight.................................... 9,832 lb
Maximum Zero Fuel Weight................................. 9,378 lb
The propeller autofeather system must be operable for all flights
and must be armed for takeoff, climb, approach and landing.
AUTOPILOT
N1 Speed:
Takeoff and Maximum Continuous Power............ 101.5%
Transient................................................................ 102.6%
ITT Temp (°C):
Start........................................................................1090°C
Takeoff and Maximum Continuous Power...............805°C
Cruise Climb and Maximum Cruise..........................805°C
Transient...................................................................880°C
Oil (°C/PSI):
Oil Temp for Starting......................................–40°C (MIN)
Oil Press at Idle RPM.................................... 40 PSI (MIN)
Takeoff and Maximum Continuous Power:
Oil Temperature......10°C–99°C (55°C recommended)
Oil Pressure................................................ 85–105 PSI
EXTERNAL POWER LIMITS
Volts....................................................................28.0–28.4
Minimum Amps...................... 1000 Amps (momentarily)
300 Amps (continuous)
GENERATOR LIMITS
In Flight.................................... 100% (minimum 85% N1)
Ground...................................... 85% (minimum 70% N1)
STARTER LIMITS
Duration On/Off.........40 Seconds ON, 60 Seconds OFF,
40 Seconds ON, 60 Seconds OFF,
40 Seconds ON, 30 Minutes OFF
ICING LIMITATIONS
Maximum Rear Baggage Compartment Load........ 350 lb
Maximum Nose Avionics Compartment Load........ 350 lb
FUEL LIMITS
Emergency Engine Fuels........... 80 Red (Formerly 80/87)
100LL Blue
100 Green
Limitations:
• Operation is limited to 150 hours between engine overhauls.
• Operation is limited to 8,000 feet pressure altitude or
below with boost pumps inoperative.
• Crossfeed capability is required for climbs above 8,000
feet pressure altitude.
Approved Engine Fuels (unlimited use):
Commercial Grades........................Jet A, Jet A-1, Jet B,
Chinese Jet Fuel No. 3
Military Grades....................................... JP-4, JP-5, JP-8
Fuel Weights are based on 6.7 lb/gal:
Total Usable Fuel Quantity (lb/gal).......... 2573 lb (384 gal)
Each Side (lb/gal).......................... 1286.5 lb (192 gal)
1) Each Wing Tank (lb/gal).............. 877.5 lb (131 gal)
2) Each Nacelle Tank (lb/gal)............... 409 lb (61 gal)
Maximum Imbalance............................................... 200 lb
Fuel Crossfeed:
Crossfeeding of fuel is permitted only in the event of:
1) Electric boost pump failure, or
2) Engine failure
Minimum Ambient Temperature
for Operation of Deicing Boots.................................–40°C
Minimum Airspeed for Sustained Icing Flight.... 140 KIAS
Minimum Fuel for Takeoff:
Do not take off if fuel quantity gauges indicate in the yellow arc
or if fuel quantity is less than 265 pounds in each wing system.
Systems and Equipment Limits:
Flight with Flaps Extended:
Sustained flight in icing conditions with flaps extended is
prohibited except for approach and landings.
Engine Anti-Ice:
Temperature Requiring Engine Anti-Ice,
If Conditions Free of Visible Moisture
Cannot Be Assured...............................+5°C OR LOWER
Operating With Low Fuel Pressure:
Operation of either engine with its corresponding fuel
pressure annunciator (L FUEL PRESS or R FUEL PRESS)
illuminated is limited to 10 hours before overhaul or
replacement of the engine-driven fuel pump. Windmilling
time need not be charged against this time limit.
Boost Pumps:
Both boost pumps must be operational prior to takeoff.
PROPELLER SPEED LIMITS
Transients...........................................................2090 rpm
Reverse..............................................................1825 rpm
Minimum Idle Speed..........................................1100 rpm
Ground Operation
Prohibited Range................................ >500 to <1100 rpm
Ground Operations in Feather......... At or below 500 rpm
All Other Conditions...........................................1900 rpm
SYSTEMS AND EQUIPMENT LIMITS
Landing Gear Cycle Limits:
Landing gear cycles (1 up – 1 down) are limited to 1 every
3 minutes for a total of 10 cycles, followed by a 15 minute
cool down period.
Aft-Facing Seats:
The seatback of each occupied aft-facing seat must be
in the upright position and the headrest fully extended for
takeoff and landing.
FLIGHT MANAGEMENT SYSTEM (FMS)
1) IFR enroute and terminal navigation is prohibited unless
the pilot verifies either the currency of the database or
the accuracy of each selected waypoint and navaid by
reference to current approved data.
2) The FMS position must be checked for accuracy prior to
use as a means of navigation.
3) FMS based instrument approaches must be accomplished
in accordance with approved instrument approach
procedures that are retrieved from the FMS-3000 database.
• GPS instrument approaches must be conducted with
GPS integrity monitoring (RAIM) and must be available
by the Final Approach Fix.
• During FMS instrument approaches, the FMS
annunciator APPR (green) or the FMS annunciator GPS
APPR (green) must be displayed on the PFD at the FAF
to indicate that the FMS is in the Approach Mode.
• Use of FMS guidance for conducting instrument approach
procedures is prohibited with the FMS annunciator NO
APPR (white or amber) displayed on the PFD.
4) Fuel management parameters are advisory only and must
not replace the primary fuel quantity indications.
1) A
n autopilot preflight check must be conducted and found
satisfactory prior to each flight on which the autopilot is
to be used.
2) The autopilot minimum engage height after takeoff is 400
feet AGL.
3) The autopilot minimum use height during cruise is 1000
feet AGL.
4) The autopilot minimum use height during precision
approach is 100 feet AGL.
5) The autopilot minimum use height during non-precision
approach is 200 feet AGL.
6) T
he maximum coupled intercept angles are:
Nav and Localizer—Less than 90°
Back Course—70°
IFIS-5000 INTEGRATED FLIGHT INFORMATION SYSTEM
1) T
he use of the airplane symbol on the Electronic Charts
is prohibited for navigation.
2) The database utilized for the Electronic Charts must
incorporate the current update cycle.
3) When using the Electronic Charts, a paper equivalent (or
electronic flight bag) must be on board and accessible to
the pilot.
TERRAIN AWARENESS WARNING SYSTEM (TAWS+)
The Terrain Awareness and Display (TAD) must be inhibited
by selecting the TERR INHIB switch/annunciator when
within 15 nm of takeoff, approach, or landing at an airport
not contained in the TAWS+ Airport Database.
VNAV
1) W
hen using the VNAV system, the barometric altimeters
must be used as the primary altitude reference for all
operations.
2) VNAV altitudes must be displayed on the MFD map page
or CDU legs page when utilizing VNAV for flight guidance.
3) VNAV approach guidance to a DA is not authorized if
the reported surface temperature is below the BaroVNAV minimum temperature limitation specified on the
applicable RNAV approach procedure chart.