beech c90 gti - section 2 limitations

Model C90GTi

2-1May, 2009

SECTION 2LIMTATIONS

TABLE OF CONTENTSSUBJECT PAGE

Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-5

Airspeed Indicator Markings. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6

Power Plant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6Number of Engines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6Engine Manufacturer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6Engine Model Number . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6Power Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-6Engine Operating Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7External Power Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8Generator Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8Starter Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8Fuel Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

Approved Engine Fuels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Commercial Grades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Military Grades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9

Emergency Engine Fuels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Commercial Aviation Gasoline Grades . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Limitations On The Use Of Aviation Gasoline. . . . . . . . . . . . . . . . . . . . 2-9

Approved Fuel Additives. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Anti-Icing Additive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-9Fuel Biocide Additive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-10

Fuel Management . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Usable Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Fuel Imbalance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Fuel Crossfeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Fuel Gages In The Yellow Arc . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Operating With Low Fuel Pressure. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Boost Pumps . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11

Oil Specification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Approved Engine Oils . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11

Number of Propellers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12Propeller Manufacturer. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12Propeller Hub and Blade Model Numbers . . . . . . . . . . . . . . . . . . . . . . . . . 2-12Propeller Diameter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12

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Model C90GTi

2-2 May, 2009

SECTION 2LIMTATIONS

TABLE OF CONTENTS (CONTD)SUBJECT PAGE

Propeller Blade Angles at 30-Inch Station . . . . . . . . . . . . . . . . . . . . . . . . 2-12Propeller Rotational Speed Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12Propeller Rotational Overspeed Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12Propeller Autofeather . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-12Power Plant Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-13

Miscellaneous Instrument Markings . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14Fuel Quantity Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14Cabin Differential Pressure Gage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14Pneumatic Pressure Gage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14Propeller Deice Ammeter . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14Gyro Suction Gage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14

Weight Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-14

Center of Gravity Limits (Landing Gear Extended) . . . . . . . . . . . . . . . . . 2-15Aft Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15Forward Limits. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15Datum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15Mean Aerodynamic Chord (MAC) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15

Maneuver Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15

Flight Load Factor Limits (10,100 Pounds / 4581 Kilograms) . . . . . . . . 2-15

Minimum Flight Crew . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15

Maximum Operating Pressure-Altitude Limit. . . . . . . . . . . . . . . . . . . . . . 2-15

Maximum Outside Air Temperature Limit . . . . . . . . . . . . . . . . . . . . . . . . 2-15

Cabin Pressurization and Structural Limitation. . . . . . . . . . . . . . . . . . . . 2-16

Maximum Occupancy Limit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16

Systems and Equipment List. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16Landing Gear Cycle Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16Aft-Facing Seats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16Ground Communications Electric Power Bus . . . . . . . . . . . . . . . . . . . . . . . 2-16

Limitations When Encountering Severe Icing Conditions(Required By FAA AD 98-04-24) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-16

Icing Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17Approved Airplane Deicing/Anti-Icing Fluids . . . . . . . . . . . . . . . . . . . . . . . . 2-17


Model C90GTi

2-3May, 2009

SECTION 2LIMITATIONS

TABLE OF CONTENTS (CONTD)SUBJECT PAGE

Avionics Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-18Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-19Attitude Heading Reference System (AHRS). . . . . . . . . . . . . . . . . . . . . . . 2-20Flight Management System (FMS). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-20IFIS-5000 Integrated Flight Information System. . . . . . . . . . . . . . . . . . . . . 2-22Terrain Awareness and Warning System+ (TAWS+). . . . . . . . . . . . . . . . . 2-23Traffic Alert and Collision Avoidance System (TCAS I) . . . . . . . . . . . . . . . 2-23VNAV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23Weather Radar. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24

Cracked or Shattered Windshield . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-24

Crack In Any Side Window (Cockpit or Cabin) . . . . . . . . . . . . . . . . . . . . . 2-25

Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-26

Kinds of Operation Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-33

Kinds of Operations Equipment List . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-33


Model C90GTi

2-4

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Section 2 - Limitations

October, 2007


LimitationsSection 2

Model C90GTi

2-5

The limitations included in this section have been approved by the Federal Avia-tion Administration and they must be observed in the operation of the ModelC90GTi.

AIRSPEED LIMITATIONS

SPEED KCAS KIAS REMARKSMaximum Operating Speed

VMOMMO

226.46 Mach

226.46 Mach

Do not exceed this airspeed in any operation.

Maneuvering Speed

VA 169 169

Do not make full or abrupt control movements above this airspeed.

Maximum Flap Extension Speed/Extended Speed

VFE Approach Down

182140

184148

Do not extend flaps or operate with flaps extended above these airspeeds.

Maximum Landing Gear Operating Speed

VLO Extension Retraction

182164

182163

Do not extend or retract the landing gear above these airspeeds.

Maximum Landing Gear Extended Speed

VLE 182 182

Do not exceed this airspeed with the landing gear extended.

Air Minimum Control Speed

VMCA Flaps Up Flaps Approach

8785

8583

These are the lowest airspeeds at which the airplane is directionally controllable when one engine suddenly becomes inoperative with the autofeather armed, and the other engine is at take-off power.

October, 2007

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Section 2Limitations Model C90GTi

2-6

AIRSPEED INDICATOR MARKINGS*

* Impending Stall Speed Low Speed Cue

POWER PLANT LIMITATIONSNUMBER OF ENGINES2

ENGINE MANUFACTURER Pratt & Whitney Canada Corp. (Longueuil, Quebec, Canada)

ENGINE MODEL NUMBER PT6A-135A

POWER LEVERS Do not lift the power levers in flight. Lifting the power levers in flight, or moving thepower levers in flight below the flight idle position, could result in a nose-downpitch and a descent rate leading to aircraft damage and injury to personnel.

DISPLAY KIAS VALUE OR RANGE

SIGNIFICANCE

Red Line 85 Air Minimum Control Speed (VMCA).

Solid Red Bar(at bottom of airspeed scale)

78

83

88

ISS LSC* Marker. The top of the marker changes withflap position to reflect the following stall speeds.Stalling Speed (VSO) at maximum weight with flapsdown and idle power. Stalling Speed (VS1) at maximum weight with flapsapproach and idle power.Stalling speed (VS) at maximum weight with flaps upand idle power.

W DN (white) 148 Maximum speed permissible with flaps extendedbeyond approach.

W APP (white) 184 Maximum Speed permissible with flaps in approachposition.

Blue Line 108 One-Engine-Inoperative Best Rate-of-Climb Speed.

Solid Red Bar (at top of airspeed scale)

226 or value equal to 0.46

Mach, whichever is

lower

VMO Marker. The bottom of the Marker represents theMaximum Operating Speed.These speeds may not be deliberately exceeded inany flight regime.

October, 2007



Model C90GTi

2-7

ENGINE OPERATING LIMITSThe following limitations shall be observed. Each column presents limitations.The limits presented do not necessarily occur simultaneously. Refer to Pratt &Whitney Engine Maintenance Manual for specific actions required if limits areexceeded.

FOOTNOTES:1. Maximum permissible sustained torque is 1520 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 is between 85 and 105 psi.Oil pressures between 40 and 85 psi are undesirable; they should be toler-ated only for the completion of the flight, and then only at a reduced powersetting. Oil pressures below 40 psi are unsafe; they require that either theengine be shut down, or that a landing be made at the nearest suitable air-port, using the minimum power required to sustain flight.

3. For increased service life of engine oil, an oil temperature of between 74to 80C is recommended. A minimum oil temperature of 55C is recom-mended 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.

OPERATING CONDITION

SHP TORQUE FT-LBS

(1)

MAXIMUMOBSERVED

ITTC

GAS GENERATOR

RPM N1

PROP RPMN2

OILPRESSPSI (2)

OILTEMPC (3)

RPM %

STARTING 1090 (4)

-40 (min)

LOW IDLE 685 (5)

1100 (min) (9)

40 (min)

-40 to 99

HIGH IDLE 72 (approx)

0 to 99

TAKEOFF AND MAX CONT

550 1520(13)

805 38,100 101.5 1900(12)

85 to 105 10 to 99

CRUISE CLIMB AND MAX CRUISE

550 1520 (6) (13)

805 38,100 101.5 1900(12)

85 to 105 0 to 99

MAXREVERSE (7)

805 88 1825 85 to 105 0 to 99

TRANSIENT 1626 (10)

880 (4) (8)

38,500 102.6 2090 104(11)

October, 2007



2-8

8. High generator loads at low N1 speeds may cause the ITT transient tem-perature limit to be exceeded. Observe generator load limits.

9. Stabilized propeller operation on the ground between 500 and 1100 rpm isprohibited. Operation in this range can generate high propeller stresses,which can cause propeller damage and result in propeller failure and lossof control of the airplane. The propeller may be operated when feathered ator below 500 rpm.

10. This value is time-limited to 20 seconds.11. This value is time-limited to 10 minutes.12. To account for power setting accuracy and steady state fluctuations, inad-

vertent propeller excursions up to 1938 rpm are time-limited to 7 minutes.13. To account for power setting accuracy and steady state fluctuations, inad-

vertent torque excursions up to 1550 ft-lbs are time-limited to 7 minutes.

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

GENERATOR LIMITS The In-Flight Limits are: 100% GENERATOR LOAD and a MINIMUM N1 of 85%

During ground operation, observe the following limitations:

STARTER LIMITSUse 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.

GENERATOR LOAD MINIMUM N10 to 50% 59%

50 to 80% 61%

80 to 85% 70%

October, 2007


Model C90GTi

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LIMITATIONSFUEL LIMITSAPPROVED ENGINE FUELS

COMMERCIAL GRADES

Jet AJet A-1Jet BChinese No. 3 Jet Fuel

June, 2009

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Model C90GTi

2-9

FUEL LIMITS APPROVED ENGINE FUELS

COMMERCIAL GRADES Jet A Jet A-1 Jet B

MILITARY GRADES JP-4JP-5 JP-8

EMERGENCY ENGINE FUELS

COMMERCIAL AVIATION GASOLINE GRADES 80 Red (Formerly 80/87)100LL Blue 100 Green

LIMITATIONS ON THE USE OF AVIATION GASOLINE1. Operation is limited to 150 hours between engine overhauls. 2. Operation is limited to 8000 feet pressure altitude or below with boost

pumps inoperative. 3. Crossfeed capability is required for climbs above 8000 feet pressure alti-

tude.

APPROVED FUEL ADDITIVES

ANTI-ICING ADDITIVE

Engine oil is used to heat the fuel on entering the fuel control. Since no tempera-ture measurement is available for the fuel at this point, it must be assumed to bethe same as the OAT. The graph below is used to determine the minimum oiltemperature required to maintain the fuel temperature above the freezing point ofwater, and thus prevent ice accumulations in the fuel control unit. Enter the graphat the known or forecast OAT and determine the minimum oil temperaturerequired for each phase of flight. If the anticipated actual oil temperature is notequal to, or above this minimum temperature, anti-icing additive conforming toMIL-I-27686 or MIL-I-85470 must be added to the fuel. Refer to Section 4, NOR-MAL PROCEDURES, for blending procedures.

October, 2007



2-10

Prior to refueling, check with the fuel supplier to determinewhether or not anti-icing additive has already been addedto the fuel. If anti-icing additive is required, it must be prop-erly blended with the fuel to avoid deterioration of the fuelcell sealant. The additive concentration shall be a minimumof 0.10% and a maximum of 0.15% by volume. To assureproper concentration by volume of fuel on board, blendonly enough additive for the unblended fuel.

FUEL BIOCIDE ADDITIVE

Fuel biocide-fungicide BIOBOR JF in concentrations of 135 ppm or 270 ppmmay be used in the fuel. BIOBOR JF may be used as the only fuel additive or itmay be used with the anti-icing additive conforming to MIL-I-27686 or MIL-I-85470 specification. Used together the additives have no detrimental effect onthe fuel system components.

Refer to the King Air 90 Series Maintenance Manual and the latest revision ofPratt & Whitney Service Bulletin No. 1244 for concentrations to use and for pro-cedures, recommendations and limitations pertaining to the use of biocidal/fungi-cidal additives in turbine fuels.

October, 2007



Model C90GTi

2-11

FUEL MANAGEMENT USABLE FUEL

(GALLONS x 6.7 = POUNDS) Total Usable Fuel Quantity . . . . . . . . . . . . . . 384 gal. (1453 liters), 2573 lbs

Each Side . . . . . . . . . . . . . . . . . . . . . . . 192 gal. (727 liters), 1286.5 lbs1) Each Wing Tank System . . . . . . . . . . 131 gal. (496 liters), 877.5 lbs2) Each Nacelle Tank . . . . . . . . . . . . . . . . . . 61 gal. (231 liters), 409 lbs

FUEL IMBALANCE

Maximum allowable fuel imbalance between fuel systems is 200 pounds.

FUEL CROSSFEED

Crossfeeding 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 if fuel quantity isless than 265 pounds in each wing system.

OPERATING WITH LOW FUEL PRESSURE

Operation of either engine with its corresponding fuel pressure annunciator (LFUEL PRESS or R FUEL PRESS) illuminated is limited to 10 hours before over-haul or replacement of the engine-driven fuel pump. Windmilling time need notbe charged against this time limit.

BOOST PUMPS

Both boost pumps must be operational prior to takeoff.

OIL SPECIFICATION Any oil called out by brand name in the latest revision of Pratt & Whitney ServiceBulletin Number 1001 is approved for use in the PT6A-135A engine.

APPROVED ENGINE OILS 7.5 Centistoke Turbine Engine Oils5 Centistoke Turbine Engine Oils

October, 2007



2-12

NUMBER OF PROPELLERS 2

PROPELLER MANUFACTURER Hartzell Propeller Inc. (Piqua, Ohio)

PROPELLER HUB AND BLADE MODEL NUMBERS Two full-feathering, constant-speed, reversing, four-bladed propellers consistingof D8990SK blades and HC-E4N-3N hubs.

PROPELLER DIAMETER Maximum Diameter. . . . . . . . . . . . . . . . . . . . . . . 90.0 inches (228.5 centimeters)Minimum Diameter . . . . . . . . . . . . . . . . . . . . . . . . . 89.0 inches (226 centimeters)

PROPELLER BLADE ANGLES AT 30-INCH STATION Reverse: -10.0 0.2 Feathered: 85.8 0.5

PROPELLER ROTATIONAL SPEED LIMITS Transients . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2090 rpmReverse . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1825 rpmMinimum Idle Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1100 rpmGround Operation Prohibited Range . . . . . . . . . . . . . . . . . . . >500 to


Model C90GTi

2-13

POWER PLANT INSTRUMENT MARKINGSINSTRUMENTPARAMETER

GREEN/NORMALOPERATING RANGE

YELLOW/CAUTION /TRANSIENT RANGE

RED/MAXIMUM/MINIMUMRANGE

ITT(starting) C

805or

> 805 925 10 sec

or> 925 1090

2 sec(White)

- - - > 805 925> 10 sec

or> 925 1090

> 2 secor

> 1090

ITT(running) C

805(White)

> 805 880 2 sec

> 805 880> 2 sec

or> 880

Torque Ft-Lbs(Prop RPM greater

than 0)

1520or

> 1520 1550for

5 min

> 1550 1630 10 sec

or> 1520 1550 for> 5 min 7 min

> 1550 1630> 10 sec

or> 1520 1550

> 7 minor

> 1630

PROP RPM(starting on ground)

500or

> 1900 1930 5 min

or> 1100 1900

> 500 < 1100 15 sec

or> 1900 1930 for> 5 min 7 min

> 500 < 1100> 15 sec

or> 1900 1930

> 7 minor

> 1930

PROP RPM(starting in air)

1900or

> 1900 1930 5 min

> 1900 1930 for> 5 min 7 min

> 1900 1930> 7 min

or> 1930

PROP RPM(engine running on

ground)

500or

1100 1900or

> 1900 1930 5 min

> 500 < 1100 15 sec

or> 1900 1930 for> 5 min 7 min

> 500 < 1100> 15 sec

or> 1900 1930

> 7 minor

> 1930

PROP RPM(engine running in air)

1900or

> 1900 1930 5 min

> 1900 1930 for> 5 min 7 min

> 1900 1930> 7 min

or> 1930

% N1(starting)

101.5(White)

> 101.5 102.6 2 sec

> 101.5 102.6> 2 sec

or> 102.6

% N1(running)

58 101.5(White)

> 101.5 102.6 2 sec

or< 58

> 101.5 102.6> 2 sec

or> 102.6

FUEL FLOW 0 800 - - - - - -OIL TEMP

(starting) C -40 99 > 99 110

10 min> 99 104> 10 min

or< -40

or> 104

October, 2007



2-14

The Pilot is responsible for monitoring all engine limits, including transient limitsnot accounted for by the EIS as defined in the existing airplane flight manualengine operating limitations.

MISCELLANEOUS INSTRUMENT MARKINGS FUEL QUANTITY INDICATORS Yellow Arc (No-takeoff Range) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 to 265 lbs

CABIN DIFFERENTIAL PRESSURE GAGE Green Arc (Approved Operating Range) . . . . . . . . . . . . . . . . . . . . . . 0 to 5.0 psiRed Arc (Unapproved Operating Range) . . . . . . . . above 5.0 psi to end of scale

PNEUMATIC PRESSURE GAGE Green Arc (Normal Operating Range) . . . . . . . . . . . . . . . . . . . . . . . . 12 to 20 psiRed Line (Maximum Operating Limit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .20 psi

PROPELLER DEICE AMMETER Green Arc (Operating Range). . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 to 24 amps

GYRO SUCTION GAGE Narrow Green Arc (Normal from 35,000 to 15,000 feet). . . . . . . 2.8 to 4.3 in. HgWide Green Arc (Normal from 15,000 feet to Sea Level) . . . . . . 4.3 to 5.9 in. Hg35K marked on the face of gage at. . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.0 in. Hg15K marked on the face of gage at. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.3 in. Hg

WEIGHT LIMITS Maximum Ramp Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10,160 lbs (4608 kg)Maximum Take-off Weight . . . . . . . . . . . . . . . . . . . . . . . . . . 10,100 lbs (4581 kg)Maximum Landing Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . .9600 lbs (4354 kg)Maximum Zero Fuel Weight . . . . . . . . . . . . . . . . . . . . . . .No Structural LimitationMaximum Rear Baggage Compartment Load . . . . . . . . . . . . . . .350 lbs (159 kg)Maximum Nose Avionics Compartment Load. . . . . . . . . . . . . . . .350 lbs (159 kg)

INSTRUMENTPARAMETER

GREEN/NORMALOPERATING RANGE

YELLOW/CAUTION /TRANSIENT RANGE

RED/MAXIMUM/MINIMUMRANGE

OIL TEMP(running) C

0 99 > 99 104 10 min

or< 0

> 99 104> 10 min

or> 104

OIL PRESS(psig)

85 105 40 < 85 < 40or

> 105

October, 2007



Model C90GTi

2-15

CENTER OF GRAVITY LIMITS (LANDING GEAREXTENDED) AFT LIMIT 160.0 inches aft of datum at all weights.

FORWARD LIMITS 152.0 inches aft of datum at 10,100 lbs (4581 kg) 150.7 inches aft of datum at 9600 lbs (4354 kg) 144.7 inches aft of datum at 7850 lbs (3560 kg) or less

DATUM The reference datum is located 83.5 inches (212 centimeters) forward of the cen-ter of the nose jack point.

MEAN AERODYNAMIC CHORD (MAC) The leading edge of the MAC is 135.9 inches (345.2 centimeters) aft of datum. The MAC length is 75.9 inches (193 centimeters).

MANEUVER LIMITSThis is a normal category airplane. Acrobatic maneuvers, including spins, are pro-hibited.

FLIGHT LOAD FACTOR LIMITS (10,100 POUNDS / 4581KILOGRAMS)

MINIMUM FLIGHT CREWOne Pilot

MAXIMUM OPERATING PRESSURE-ALTITUDE LIMIT30,000 feet

MAXIMUM OUTSIDE AIR TEMPERATURE LIMITISA + 33C

FLAPS UP FLAPS DOWN

3.29 positive gs 2.00 positive gs

1.33 negative gs 0.00 g

October, 2007



2-16

CABIN PRESSURIZATION AND STRUCTURAL LIMITATIONMaximum Cabin Differential Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.1 psiFuselage Pressure Vessel Structure . . . Inspections in Chapters 5 and 53-10-00of the King Air 90 Series Maintenance Manual are required for continued airwor-thiness.

MAXIMUM OCCUPANCY LIMIT 13 including crew

SYSTEMS AND EQUIPMENT LIMITSLANDING GEAR CYCLE LIMITSLanding gear cycles (1 up - 1 down) are limited to one every 3 minutes for a totalof 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 andthe headrest fully extended for takeoff and landing.

GROUND COMMUNICATIONS ELECTRIC POWER BUSOperation of the ground communications electric power bus is restricted toground operation only. No authorization is extended to operate this system in anyflight configuration.

The ground communications electric power bus must not be used when refuelingthe airplane.

LIMITATIONS WHEN ENCOUNTERING SEVERE ICINGCONDITIONS (REQUIRED BY FAA AD 98-04-24)

Severe icing may result from environmental conditions outside ofthose for which the airplane is certificated. Flight in freezing rain,freezing drizzle, or mixed icing conditions (supercooled liquid waterand ice crystals) may result in ice build-up on protected surfaces ex-ceeding the capability of the ice protection system, or may result inice forming aft of the protected surfaces. This ice may not be shedusing the ice protection systems, and may seriously degrade theperformance and controllability of the airplane.

1. During flight, severe icing conditions that exceed those for which the air-plane is certificated shall be determined by the following visual cues. If oneor more of these visual cues exists, immediately request priority handling

October, 2007

sec02.fm Page 16 Thursday, November 15, 2007 8:25 AM


Model C90GTi

2-17

from Air Traffic Control to facilitate a route or an altitude change to exit theicing conditions. a. Unusually extensive ice accumulation on the airframe and windshield in

areas not normally observed to collect ice. b. Accumulation of ice on the upper surface of the wing, aft of the pro-

tected area. c. Accumulation of ice on the engine nacelles and propeller spinners far-

ther 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 auto-pilot is prohibited when any of the visual cues specified above exist, orwhen unusual lateral trim requirements or autopilot trim warnings areencountered while the airplane is in icing conditions.

3. All wing icing inspection lights must be operative prior to flight into known orforecast icing conditions at night. [NOTE: This supersedes any reliefprovided by the Master Minimum Equipment List (MMEL).]

ICING LIMITATIONS Minimum Airspeed (KIAS) for Sustained Icing Flight . . . . . . . . . . . . . . . 140 knotsMinimum Temperature for Operation of Deicing Boots . . . . . . . . . . . . . . . . -40CTemperature requiring Engine Anti-ice, if conditions free of visible moisture cannot be assured . . . . . . . . . . . . . . . . . . . . . . + 5C or lowerSustained flight in icing conditions with flaps extended is prohibited except for ap-proach and landings.

APPROVED AIRPLANE DEICING/ANTI-ICING FLUIDSISO 11075 Type IISO 11078 Type IISAE AMS 1424 Type ISAE AMS 1428 Type II

SAE AMS 1428 Type IV

October, 2007

sec02.fm Page 17 Friday, May 15, 2009 3:10 PM


2-18

AVIONICS LIMITSGENERAL

1. The following guides must be immediately available to the pilot at all times: Operators Guide, Collins Pro Line 21 Avionics System with IFIS for the

Beechcraft King Air, P/N 523-0808535, dated June 1, 2007, or later revi-sion.

Operators Guide, Collins FMS-3000 Flight Management System for theHawker Beechcraft Corporation C90GTi, P/N 523-0790066, dated June 6,2007, or later revision.

ACSS TAWS+ Pilots Guide Publication Number 8006772-001, RevisionNo. 3 dated December 31, 2008, or later revision.

Pilots Guide for the L3 Skywatch HP Traffic Alert/Advisory System, ModelSKY899, Publication No. 009-11901-001, Revision B, dated February 3,2004, or later revision.

The Meggitt Hawker Beechcraft Corporation C90/460XP SFD MK2, SILNo. 59, Issue 1, or later revision.

The Operators Guide, Collins Corporate Data Link System CMU-4000/RIU-40X0, Publication No. 523-0790499-001117, dated July 14, 2003, orlater revision.

The Operators Guide, IFIS-5000 integrated Flight Information System,Publication No. 523-0806347, dated April 4, 2007, or later.

2. This POH/AFM is approved for use with Collins FMS-3000 software ver-sion SCID 832-4120-011 or later.

3. Operating in the composite mode is limited to training and display failureconditions.

4. The pilots and copilots Air Data Computers must be operative for takeoff.5. AHRS 1 and 2 must be operative for takeoff.6. The pilots PFD and MFD and copilots PFD must be installed and opera-

tional in the normal mode for takeoff.7. The MFD must be operational prior to engine start.

May, 2009



Model C90GTi

2-19

AUTOPILOT1. During autopilot operations, a pilot must be seated at the controls with the

seat belt and shoulder harness fastened.2. An autopilot preflight check must be conducted and found satisfactory prior

to each flight on which the autopilot is to be used.3. The autopilot minimum engage height after takeoff is 400 feet AGL.4. The autopilot minimum use height during cruise is 1000 feet AGL.5. The autopilot minimum use height during precision approach is 100 feet

AGL.6. The autopilot minimum use height during non-precision approach is 200

feet AGL.7. Maximum airspeed for autopilot operation is unchanged from the airplane

maximum airspeed (VMO/MMO).8. The autopilot and yaw damper must not be used for takeoff and landing.9. Operation of the autopilot system with a pitch trim malfunction is prohibited.

10. Do not manually override the autopilot during normal flight.

Overriding the autopilot in pitch does not cancel the autopi-lot automatic trim. If a force is applied to the control columnwith the autopilot engaged, then automatic trim will run tooppose the applied force. This can lead to a severe out-of-trim condition during any phase of flight.

11. The maximum coupled intercept angles are:Nav and Localizer - Less than 90Back Course - 70

12. The minimum airspeed for autopilot operation must not be less than Vref,based on the airplanes configuration.

13. Once established on a Localizer, Localizer Backcourse and ILSApproaches, with the inbound course set, do not turn or adjust the courseknob. Flight Director and autopilot will temporarily steer the airplane to thechange.

14. VOR approaches conducted without DME must be intercepted greaterthan 6 NM from the VOR.

October, 2007



2-20

ATTITUDE HEADING REFERENCE SYSTEM (AHRS)Operations based on magnetic heading data are limited to within the U.S.National Airspace and latitude bounded by:

Operations to 60 North latitude and 60 South latitude and any longitude. Operations to 70 North latitude is acceptable East of 75 West longitude

and West of 120 West longitude. Operations to 80 North latitude is acceptable East of 50 West longitude

and West of 70 East longitude. Operations to 70 South latitude is acceptable except for the 45 between

120 East and 165 East longitude.

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 way-point and navaid by reference to current approved data.

2. The FMS position must be checked for accuracy prior to use as a means ofnavigation.

3. During periods of dead reckoning, the FMS shall not be used for naviga-tion.

4. All FMS navigation operations are approved within the U.S. National Air-space System and latitudes bounded by 60 North latitude and 60 Southlatitude at any longitude.

Operation to 70 North latitude is acceptable East of 75 West longitudeand West of 120 West longitude.

Operation to 80 North latitude is acceptable East of 50 West longitudeand West of 70 East longitude.

Operation to 70 South latitude is acceptable except for the 45 between120 East and 165 East longitude.

The WGS-84 coordinate reference datum in accordance with the criteria ofAC 20-130A, AC 91-49 CHG 1, and AC 20-138 must be used. Satellitenavigation data is based upon use of only the Global Positioning System(GPS) operated by the United States.

5. FMS based instrument approaches must be accomplished in accordancewith approved instrument approach procedures that are retrieved from theFMS-3000 database.

GPS instrument approaches must be conducted with GPS integrity moni-toring (RAIM) and must be available by the Final Approach Fix.

During FMS instrument approaches, the FMS annunciator APPR (green) orthe FMS annunciator GPS APPR (green) must be displayed on the PFD atthe FAF to indicate that the FMS is in the Approach Mode.

Use of FMS guidance for conducting instrument approach procedures isprohibited with the FMS annunciator NO APPR (white or amber) displayedon the PFD.

October, 2007



Model C90GTi

2-21

Accomplishment of ILS, LOC, LOC-BC, LDA and SDF approaches are notauthorized utilizing the FMS from the FAF to the MAP.

When an alternate airport is required by the applicable rules, it must beserved by an approach based on other than GPS navigation, the airplanemust have operational equipment capable of using that navigation aid, andthe required navigation aid must be operational.

FMS based approaches that are retrieved from the navigation databasewith an approach name of RNVxxx or VORxxx may be flown provided theVHF navigation receiver is tuned to the reference facility.

IFR Non-Precision Approach is limited to published approaches within theUS National Airspace System. Approaches to airports in other airspace arenot approved unless authorized by the appropriate governing authority.

6. Provided the FMS is receiving adequate usable sensor inputs, it has beendemonstrated capable of, and has been shown to meet the accuracy spec-ifications for:a. VFR/IFR enroute RNAV operation in accordance with the criteria of AC

20-130A.b. VFR/IFR enroute, terminal, and approach operations.c. VFR/IFR operations on U.S. Area Navigation (RNAV) Routes (Q

Routes), Standard Instrument Departures (SIDs) (Type A and B), andStandard Instrument Arrivals (STARs) (Type A and B) in accordancewith AC 90-100 when the FMS is receiving usable GPS signals and theroute/airport has been checked and verified for RAIM availability.

d. GPS primary means of navigation in oceanic and remote airspace inaccordance with AC 20-130A and FAA Notice 8110.60 if the followingconditions are met.1) Dual FMS-3000 Flight Management Systems and dual GPS-4000A

receivers are installed and operable.Or-

2) A single FMS-3000 Flight Management System and a single GPS-4000A receiver are installed and operable when operating alongroutes approved for single GPS navigation.And, in either case-The Collins Prediction Program, Predeparture GPS Coverage Pre-dictor (FDE Tool), P/N 832-3443-005, or equivalent, has been runwith satisfactory results.

Compliance with the above does not constitute operational approval tooperate in oceanic and remote airspace.

e. Operation in European B-RNAV airspace in accordance with AC 90-96,AC 20-130A, and JAA Temporary Guidance Material, Leaflet No. 2,Rev. 1. This does not constitute an operational approval to operate insuch airspace.

f. Minimum Navigation Performance Specification (MNPS) airspace foreach of the following configurations.1) When dual FMS-3000 Flight Management Systems and dual GPS-

4000A GPS receivers are installed and operable.

October, 2007



2-22

2) When a single FMS-3000 Flight Management System and a singleGPS-4000A receiver are installed and operable when operatingalong routes approved for single GPS navigation.

Availability of the above equipment does not constitute operationalapproval to operate in MNPS airspace.

7. Use of FMS to capture and track a DME arc outside the published endpoints is prohibited.

8. Fuel management parameters are advisory only and must not replace theprimary fuel quantity indications.

IFIS-5000 INTEGRATED FLIGHT INFORMATION SYSTEM1. The IFIS-5000 system provides supplemental airplane situational aware-

ness information. Its use as a means for navigational or weather avoidanceis not approved.

2. Display ranges less than 50 miles must not be used when the GEO-POLdata is selected for display. At shorter ranges, the situational picture pro-vided by this data (i.e. rivers, lakes, oceans and political boundaries) mayappear erroneous.

3. The use of the airplane symbol on the Electronic Charts is prohibited fornavigation.

4. The database utilized for the Electronic Charts must incorporate the cur-rent update cycle.

5. When using the Electronic Charts, a paper equivalent (or electronic flightbag) must be on board and accessible to the pilot.

6. Data-linked graphical weather (either XM Radio or Universal Weather) isfor informational purposes and should not be used for tactical decisionmaking. By its nature, graphical weather is delayed from real time weatherconditions. Use the aircrafts primary weather radar for all tactical decisionsabout weather avoidance.

7. Digital Automatic Terminal Information Service (available only when Uni--versal Weather is installed):

The flight crew shall verify that the D-ATIS numeric and alpha altimeter setting values are identical, e.g., ...ALTIMETER SETTING 29.95 (TWONINER NINER FIVE)...

If the D-ATIS numeric and alpha altimeter setting values are different,the flight crew must not accept the D-ATIS Altimeter Setting nor rely on anyother D-ATIS information.

May, 2009



Model C90GTi

2-23

TERRAIN AWARENESS AND WARNING SYSTEM+ (TAWS+)1. Navigation must not be predicated upon use of the Terrain Awareness Dis-

play. The terrain display is intended to serve as a situational awarenesstool only, and may not provide the accuracy and/or fidelity on which tosolely base terrain avoidance maneuvering.

2. The Terrain Awareness and Display (TAD) must be inhibited by selectingthe TERR INHIB switch/annunciator when within 15 nm of takeoff,approach, or landing at an airport not contained in the TAWS+ AirportDatabase. Refer to ACSS document 8006417 for airports contained in thedatabase. (See www.acsscustomerservices.com.)

3. When the FMS is operating in the DR mode, the Terrain Awareness alert-ing must be inhibited by selecting the TERR INHIB switch/annunciator.

NOTEThe terrain database, displays and alerting algorithms cur-rently account for limited cataloged human-made obstruc-tions in North America and Europe. If obstacle data is notin the database for a particular obstacle the ObstacleAwareness alerting is not available for the obstacle.

4. The current local QNH altimeter setting must be entered in the pilots altim-eter for proper terrain alerting. In particular, the TERR INHIB switch/annun-ciator must be selected when operating in QFE mode.

5. The terrain database part number displayed on the MFD by MDC diagnos-tics must be 9000280-023 or latest.

6. The obstacle database part number displayed on the MFD by MDC diag-nostics must be 9000380-001 or latest.

TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM(TCAS I)

1. The pilot must not maneuver the airplane based only on the traffic display.The traffic display is intended to assist in visually locating traffic and lacksthe resolution necessary for use in evasive maneuvering.

2. If the pilot is advised by Air Traffic Control to disable the altitude reportingfunction of the transponder, the Traffic Advisory System must be turned off.

3. The traffic advisory system can only detect aircraft that are transponderequipped.

VNAV1. When using the VNAV system, the barometric altimeters must be used as

the primary altitude reference for all operations.2. Use of VNAV guidance for a V-MDA approach that includes a step-down

fix between the final approach fix and missed approach point is prohibited.

May, 2009



2-24

3. VNAV altitudes must be displayed on the MFD map page or CDU legspage when utilizing VNAV for flight guidance.

4. Use of VNAV while conducting a missed approach procedure is prohibited.5. Provided the FMS is receiving adequate usable sensor inputs, it has been

demonstrated capable of and has been shown to meet the accuracy speci-fications of VNAV operation in accordance with AC 20-129. Such VNAVapproaches must be flown utilizing either the flight director or autopilot.

6. VNAV approach guidance to a DA is not authorized if the reported surfacetemperature is below the Baro-VNAV minimum temperature limitationspecified on the applicable RNAV approach procedure chart.

NOTEBarometric VNAV guidance during approach including theapproach transition, final approach segment and themissed approach procedure is not temperature compen-sated. Operating at uncompensated minimum IFR altitudeswill not provide expected terrain and obstacle clearance fortemperature below ISA.

WEATHER RADAR

The area within the scan arc and within 2 feet (0.65meters) of an operating TWR-852 system can be a hazard-ous area. Do not operate the systems in any mode otherthan standby (STBY) or test (TEST) when the antennamight scan over personnel within that range. Turning thetransmitter on while inside the hangar is not advisable.

CRACKED OR SHATTERED WINDSHIELDThe following limitations apply when continued flight is required with a crackedouter 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 flakesof glass that can break free of the windshield and interfere with the crewsvision. These windshields must be replaced prior to the next flight unless aspecial flight permit is obtained from the local FAA Flight Standards DistrictOffice.

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.

October, 2007



Model C90GTi

2-25

6. The following placard must be installed in plain view of the pilot:MAXIMUM AIRPLANE ALTITUDE IS LIMITED TO25,000 FEET. CABIN P MUST BE MAINTAINEDBETWEEN 2.0 AND 4.6 PSI DURING FLIGHT

Windshields that have cracks in both the inner and outer plies must be replacedprior to the next flight unless a specials flight permit is obtained from the localFAA Flight Standards District Office.

CRACK IN ANY SIDE WINDOW (COCKPIT OR CABIN)The following limitations apply when continued flight is required with a crack inany side window. These limitations do not apply to minor compression-type chips(Clamshell) which may occur on the milled edge of cockpit side windows. Referto 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 ACRACKED SIDE WINDOW. CONDUCT FLIGHT WITH

THE CABIN PRESSURE SWITCH IN THE DUMP POSITION.

October, 2007



2-26

PLACARDS On Overhead Panel in Pilots Compartment:

On Overhead Panel in Pilots Compartment:

Aft of Overhead Light Panel:

October, 2007



Model C90GTi

2-27

On Pilots and Copilots Window Sills:

On Pilots Side Window Sill When Strobe Lights Are Installed:

On Curved Pedestal Adjacent to Power Levers:

October, 2007



2-28

On Pedestal Adjacent to Cabin Pressurization Controller:

On Floor Between Pilots Seats:

On Right Sidepanel:

October, 2007



Model C90GTi

2-29

On Outside of Each Oxygen Access Door:

On Inside Surface of Each Oxygen Access Door:

Adjacent to the Baggage Compartment Dome Light, When Optional Aft Compart-ment Oxygen Outlet is Installed:

October, 2007



2-30

On Shoulder Harness Assemblies for All Cabin Chairs:

On Cup holders and Tables When Installed:

Located on Right Forward and Aft Partitions:

On Emergency Exit Hatch Release Cover:

October, 2007



Model C90GTi

2-31

On Aft Wall of Baggage Compartment:

On Left Hand Aft Compartment Sidewall:

October, 2007



2-32

Inside Airstair Door Behind Handle:

Inside Airstair Door On Folding Step:

Inside Airstair Door Between Folding Steps:

October, 2007



Model C90GTi

2-33

KINDS OF OPERATION LIMITS The Model C90GTi is approved for the following types of operations when the re-quired equipment, as shown in the KINDS OF OPERATIONS EQUIPMENT LIST,is installed and operable.

VFR DayVFR Night IFR Day IFR Night Icing Conditions

KINDS OF OPERATIONS EQUIPMENT LIST This airplane may be operated in day or night VFR, day or night IFR, and icingconditions when the required systems and equipment are installed and operable.

The following equipment list identifies the systems and equipment upon whichtype certification for each kind of operation was predicated. The systems andequipment listed must be installed and operable for the particular kind of operationindicated unless:

1. The airplane is approved to be operated in accordance with a current Mini-mum Equipment List (MEL) issued by the FAA.

Or:

2. An alternate procedure is provided in the Pilots Operating Handbook andFAA Approved Flight Manual for the inoperative state of the listed systemor equipment and all limitations are complied with.

Numbers in the Kinds of Operations Equipment List refer to quantities required tobe operative for the specified condition. The list does not include all equipmentthat may be required by specific operating rules. It also does not include compo-nents obviously required for the airplane to be airworthy such as wings, empen-nage, engines, etc.

October, 2007



2-34

VFR DAYVFR NIGHT

SYSTEM and/or EQUIPMENT IFR DAYIFR NIGHT

ICING CONDITIONSREMARKS and/or EXCEPTIONS

ELECTRICAL POWER1. Battery 1 1 1 1 1

2. Standby Battery (SFDS) 1 1 1 1 13. BAT TIE OPEN Annunciator 1 1 1 1 14. DC Generator 2 2 2 2 25. L & R DC GEN Annunciators 2 2 2 2 26. DC Load Meter 2 2 2 2 27. DC Voltmeter/Battery Ammeter and Select Switch 1 1 1 1 18. GEN TIE OPEN Annunciator 2 2 2 2 2ENGINE INDICATIONS1. Multifunctional Display (MFD) 1 1 1 1 1ENGINE OIL1. Chip Detector System Including L & R CHIP

DETECT Annunciators2 2 2 2 2

2. Oil Pressure Indicator in MFD 2 2 2 2 23. Oil Temperature Indicator in MFD 2 2 2 2 2

4. L & R OIL PRESS Annunciator 2 2 2 2 2

ENVIRONMENTAL1. Bleed Air Shutoff/Flow Control Valve 2 2 2 2 22. L & R BL AIR OFF Annunciators 2 2 2 2 23. CABIN ALT HI Annunciator (Cabin) 2 2 2 2 24. Cabin Rate of Climb Indicator 1 1 1 1 15. Outflow Valve 1 1 1 1 16. Pressurization Controller 1 1 1 1 17. Differential Pressure/Cabin Altitude Indicator 1 1 1 1 18. Safety Valve 1 1 1 1 1FLIGHT CONTROLS1. Flap Position Indicator 1 1 1 1 12. Flap System 1 1 1 1 13. Trim Tab Position Indicator (Rudder, Aileron, Elevator) 3 3 3 3 34. Stall Warning System 1 1 1 1 1

May, 2009



Model C90GTi

2-35

VFR DAYVFR NIGHT



FLIGHT INSTRUMENTS1. AHRS 2 2 2 2 22. Air Data Computer (ADC) 2 2 2 2 23. Clock 1 1 1 1 14. Magnetic Compass 1 1 1 1 15. Outside Air Temperature 1 1 1 1 16. Overspeed Aural Warn 1 1 1 1 1

7. Primary Flight Display (PFD) 2 2 2 2 2

8. Secondary Flight Display System (SFDS) 1 1 1 1 1

FUEL1. Fuel Crossfeed System and FUEL

CROSSFEED Annunciator1 1 1 1 1

2. L & R FUEL PRESS Annunciators 2 2 2 2 23. Fuel Quantity Indicating System 2 2 2 2 24. Firewall Fuel Shutoff Valve 2 2 2 2 25. Electric Boost Pump 2 2 2 2 26. Electric Transfer Pump 2 2 2 2 27. L & R NO FUEL XFR Annunciators 2 2 2 2 2ICE AND RAIN PROTECTION1. Alternate Static Air System 0 0 1 1 12. Engine Auto-Ignition System and Annunciator 2 2 2 2 23. Engine Anti-Ice System and Annunciators 2 2 2 2 24. Heated Fuel Vent 0 0 2 2 25. Heated Windshield (Left) 0 0 0 0 16. Pitot Heat 0 0 2 2 27. Pneumatic Pressure Indicator 0 0 1 1 18. Stall Warning Heater 0 0 0 0 19. Surface Deicer System 0 0 0 0 110. Propeller Deicer System 0 0 0 0 111. Wing Ice Light (Left) 0 0 0 0 1LANDING GEAR1. Landing Gear Position Annunciators 3 3 3 3 32. Landing Gear Handle Light 1 1 1 1 13. Landing Gear Aural Warning 1 1 1 1 14. Landing Gear Hydraulic Power Pack 1 1 1 1 15. Emergency Extension Hand Pump 1 1 1 1 16. HYD FLUID LO Annunciator 1 1 1 1 1

October, 2007



2-36

VFR DAYVFR NIGHT



LIGHTS1. Cockpit and Instrument Lighting

System0 1 0 1 0

2. CABIN DOOR Annunciator 1 1 1 1 13. Landing Lights 0 1 0 1 04. Position Lights 0 3 0 3 05. Anticollision Lights System 0 1 0 1 0OXYGEN1. Oxygen System 1 1 1 1 1PROPELLER1. Autofeather System Including

Annunciators1 1 1 1 1

2. Prop Ground Fine System 2 2 2 2 23. Prop Reversing System Including

Annunciator2 2 2 2 2

4. Prop Governor Test Switch 1 1 1 1 15. Prop Overspeed Governor 2 2 2 2 2

VACUUM SYSTEM

1. Vacuum Gage 1 1 1 1 1

October, 2007


MANUAL - MAIN MENUSection 2 - LimitationsTable of ContentsAirspeed LimitationsAirspeed Indicator MarkingsPower Plant LimitationsNumber of EnginesEngines ManufacturerEngine Model NumberPower LeversEngine Operating LimitsExternal Power LimitsGenerator LimitsStarter LimitsTemporary Change - TC 2Fuel LimitsFuel ManagementOil SpecificationsNumber of PropellersPropeller ManufacturerPropeller Hub and Blade Model NumbersPropeller DiameterPropeller Blade Angles at 30-Inch StationPropeller Rotational Speed LimitsPropeller Rotational Overspeed LimitsPropeller AutofeatherPower Plant Instrument Markings

Miscellaneous Instrument MarkingsFuel Quantity IndicatorsCabin Differential Pressure GagePneumatic Pressure GagePropeller Deice AmmeterGyro Suction Gage

Weight LimitsCenter of Gravitity Limits (Landing Gear Extended)Aft LimitForward LimitsDatumMean Aerodynamic Chord (MAC)

Maneuver Limits Flight Load Factor Limits (10,000 Pounds / 4581 Kilograms)Minimum Flight CrewMaximum Operating Pressure-Altitude LimitMaximum Outside Air Temperature LimitCabin Pressurization and Structural LimitationMaximum Occupancy LimitSystems and Equipment LimitsLanding Gear Cycle LimitsAft-Facing SeatsGround Communications Electric Power Bus

Limitations When Encountering Severe Icing Conditions (Required by FAA AD 98-04-24)Icing LimitationsApproved Airplane Deicing/Anti-Icing FluidsAvionics LimitsGeneralAutopilotAttitude Heading Reference System (AHRS)Flight Management System (FMS)IFIS-5000 Integrated Flight Information SystemTerrain Aweareness and Warning System (TAWS+)Traffic Alert and Collision Avoidance System (TCAS I)VNAVWeather Radar

Cracked or Shattered WindshieldCrack In Any Side Window (Cockpit or Cabin)PlacardsKinds of Operation LimitsKinds of Operations Equipment List

beech c90 gti - section 2 limitations

Documents

engine operating limits

generator limits

starter limits

weight limits

forward limits

maneuver limits

fuel limits2

external power limits