KING AIR MODEL C90/C90A - aso.com · AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS C90/C90A Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers

Revision B: June 7, 2016 Document No. 13-206CGW

PILOT’S OPERATING HANDBOOK and

FAA-Approved Airplane Flight Manual Supplement

for the

KING AIR MODEL C90/C90A

Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers - STC SA3593NM Dual Aft Body Strakes - STC SA4010NM Increased Gross Weight - STC SA3593NM Increased ITT and Cruise Speeds - STC SA3593NM Optional 1,600 Cruise RPM - STC SA3593NM

C90: LJ-527 thru LJ-1062 (including C90,C90-1) C90A: LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753,

LJ-1755 (including C90A,C90B,C90SE)

BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Document No. 13-206CGW Increased Gross Weight

FAA-Approved: Revision B: June 7, 2016 i

PILOT’S OPERATING HANDBOOK AND FAA-APPROVED

AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS

C90/C90A

Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers - STC SA3593NM Dual Aft Body Strakes - STC SA4010NM Increased Gross Weight - STC SA3593NM (for PT6A-21 powered aircraft) Increased ITT and Cruise Speeds - STC SA3593NM (for C90 and C90-1) Optional 1,600 Cruise RPM Minimum Cruise - STC SA3593NM

Reg. No._____________________

Ser. No._____________________

This Supplement must be attached to the Beechcraft Pilot’s Operating Handbook and FAA-approved Airplane Flight Manual when Raisbeck Swept Blade Turbofan Propellers and Raisbeck Dual Aft Body Strakes are installed in accordance with the STCs listed above. The information contained in this document supplements or supersedes the basic manual only in those areas listed. For limitations, procedures, and performance information not contained in this supplement, consult the Beechcraft Pilot’s Operating Handbook and FAA-approved Airplane Flight Manual. The increased gross weight capability applies to aircraft powered by Pratt & Whitney Canada PT6A-21 engines.

I. GENERAL II. LIMITATIONS III. EMERGENCY PROCEDURES IV. NORMAL PROCEDURES V. PERFORMANCE VI. WEIGHT AND BALANCE VII. SYSTEMS DESCRIPTION

FAA-Approved: for Manager, Seattle Aircraft Certification Office Federal Aviation Administration Seattle, Washington

BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Increased Gross Weight

ii FAA-Approved: Revision B: June 7, 2016

Document No. 13-206CGW

BEECHCRAFT KING AIR MODELS

C90/C90A

PILOT’S OPERATING HANDBOOK AND FAA-APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT

Original Issue ................................................................................................................... December 12, 2013

Title Page

Pages i thru iii, 1-1, 2-1 thru 2-4, 3-1, 4-1, 4-2, 5-1 thru 5-55, 6-1, 6-2, and 7-1

LOG OF REVISIONS

REV PAGE(S) DESCRIPTION FAA-APPROVED DATE

IR All Initial Release

A 1-1, 2-1

2-4

2-4, 6-1, 6-2

6-1, 6-2

Changed propeller feather blade angle from 84.5° to 86.7°. Removed redundant reference to SL-08-BC-1. Expanded in-flight aft CG limit. Removed reference propeller weight and moment arm.

B Title, i, ii, 1-1 2-2

2-3, 2-4

5-5 thru 5-14, 5-54

5-53

Corrected title Deleted 10,350 lb from flight load factors. Revised weight limits and removed requirement for wing ballast weight. Calrified tire requirement. Replaced existing charts with revised performance charts Added max Landing Weight chart

BEECHCRAFT King Air C90/C90A Equipped With: Swept Blade Turbofan Propellers Dual Aft Body Strakes Document No. 13-206CGW Increased Gross Weight

FAA-Approved: Revision A: September 17, 2014 iii

TABLE OF DIVISIONS

SECTION I ............................................................................................................... GENERAL

SECTION II ......................................................................................................... LIMITATIONS

SECTION III ............................................................................. EMERGENCY PROCEDURES

SECTION IV ..................................................................................... NORMAL PROCEDURES

SECTION V .................................................................................................... PERFORMANCE

SECTION VI ...................................................................................... WEIGHT AND BALANCE

SECTION VII ................................................................................... SYSTEMS DESCRIPTION


FAA-Approved: Revision B: June 7, 2016 1-1

Document No. 13-206CGW Section I - General

SECTION I — GENERAL

INTRODUCTION Thank you ...

for displaying your confidence in selecting quality products from RAISBECK ENGINEERING INC. Our design engineers, craftsmen, and technicians have utilized their professional skills and years of experience to provide you with state-of-the-art systems to enhance the performance, safety, and productivity of your King Air.

The information contained in this Pilot’s Operating Handbook and FAA-Approved Airplane Flight

Manual Supplement highlights the areas of performance improvement which can be expected from your Raisbeck-equipped King Air C90/C90A.

This Supplement is designed to facilitate maintaining the documents necessary for the efficient

operation of your airplane. It has been prepared in loose-leaf form for ease in maintenance, and incorporates quick reference tabs for each section.

After you have operated your Raisbeck-equipped Beechcraft King Air C90/C90A for a period of time,

we would like to hear your comments regarding our systems in service with your operation. Please feel free to contact us at any time by mail or telephone.

Raisbeck Engineering, Inc. 4411 South Ryan Way

Seattle, Washington 98178 U.S. 800-537-7277

Intl. 1-206-723-2000 FAX (206) 723-2884

For current revision status visit www.raisbeck.com

FAA-Approved information, limitations, performance, and data are on pages marked at the bottom: “FAA-Approved: Revision Level and Date .”

PROPELLERS

No. of Propellers: 2 Propeller Manufacturer: Hartzell Propeller Inc. No. of Blades: 4 Propeller Diameter:

Maximum: 96 inches Minimum: 95 inches

Propeller Type: Constant-speed, Full-feathering, Reversing, Counter-weighted,

Hydraulically Actuated consisting of D9510SK blades and HC-D4N-3C hubs.

Pitch Range (30-inch station):

Reverse: -10.0° ± 0.5° Feathered: +86.7° ± 0.5°


FAA-Approved: Revision A: September 17, 2014 2-1

Document No. 13-206CGW Section II - Limitations

SECTION II — LIMITATIONS

POWER PLANT LIMITATIONS Engine Model ............................................................................................................................... PT6A-21

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

OPERATING CONDITION SHP TORQUE

MAXIMUM GENERATOR RPM N1

PROP OIL OIL

OBSERVED RPM PRESS TEMP

FT‐LBS (1) ITT °C RPM % N2 PSI (2) °C (3)

STARTING ‐‐‐ ‐‐‐ 1090 (4) ‐‐‐ ‐‐‐ ‐‐‐ ‐‐‐ ‐40 (min) LOW IDLE ‐‐‐ ‐‐‐ 660 (5) ‐‐‐ 51(min) 1100(min) 40(min) ‐40 to 99 HIGH IDLE ‐‐‐ ‐‐‐ ‐‐‐ ‐‐‐ 70 (approx) ‐‐‐ ‐‐‐ 0 to 99 TAKE‐OFF & MAX CONT 550 1315 695 38,100 101.5 2200 80 to 100 10 to 99 CRUISE CLIMB AND MAX CRUISE 538 1315 (6) 695 38,100 101.5 2200 80 to 100 0 to 99 MAX REVERSE (7) ‐‐‐ ‐‐‐ 695 ‐‐‐ 88 2100 80 to 100 0 to 99 TRANSIENT ‐‐‐ 1500 (4) 825 (4)(8) 38,500 102.6 2420 ‐‐‐ 0 to 99

(1) Maximum permissible sustained torque is 1315 ft/lbs. Propeller speeds (N2) must be set so at not to exceed power limitation.(2) When gas generator speeds are above 72% N1 and oil temperatures are between 60° C and 70° C, normal oil pressures is between 80 and 100 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 as soon as possible, using the minimum power required to sustain flight. (3) For increased service life of engine oil, an oil temperature of between 74° C and 80° C is recommended. A minimum oil temperature of 55° C is recommended for fuel heater operation at take‐off power. (4) These values are time‐limited to two seconds. (5) High ITT at ground idle may be corrected by reducing accessory load and/or increasing N1 RPM. (6) Cruise torque values vary with altitude and temperature. (7) Reverse power operation is limited to one minute. (8) Higher generator load at low N1 speeds may cause the ITT transient temperature limit to be exceeded. This does not apply during engine start. Observe generator load limits.

PROPELLER BLADE AND HUB NUMBERS

Two full-feathering, constant-speed, reversing, four-bladed propellers consisting of D9510SK blades and HC-D4N-3C hubs.

PROPELLER DIAMETER

Maximum diameter: 96.0 inches Minimum diameter: 95.0 inches

PROPELLER BLADE ANGLES AT 30-INCH STATION

Reverse: -10.0° ± 0.5° Feathered: +86.7° ± 0.5°


2-2 FAA-Approved: Revision B: June 7, 2016


PROPELLER REVERSE SPEED LIMITS

Do not select REVERSE until airspeed is below 95 KIAS.

WARNING PROPELLERS WILL NOT REVERSE AT AIRSPEEDS ABOVE 100 KIAS. BETWEEN 95 KIAS AND 100 KIAS, SIGNIFICANT THRUST ASYMMETRY MAY OCCUR IF REVERSE IS SELECTED.

PROPELLER ROTATIONAL SPEED LIMITS

CAUTION Stabilized ground operation between 400 and 1,100 RPM is prohibited. Operation between 0 and 400 RPM is permissible only with propeller feathered.

WARNING

STABILIZED GROUND OPERATION WITHIN THE PROPELLER RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER STRESSES AND RESULT IN PROPELLER FAILURE AND LOSS OF CONTROL OF THE AIRCRAFT.

The maximum propeller overspeed limit is 2,420 RPM. Propeller speeds above 2,200 RPM indicate failure of the primary governor. Propeller speeds above 2,288 RPM indicate failure of both primary and overspeed governors.

POWERPLANT INSTRUMENT MARKINGS

Propeller Tachometer:

(LJ-527 thru LJ-1360, LJ-1362, and C90SE): Green Arc ................................................................................................. 1,600 to 2,200 RPM Red Radial .............................................................................................................. 2,200 RPM

(LJ-1361, LJ-1363 and After, excluding C90SE):

Green Arc ................................................................................................. 1,100 to 2,200 RPM Red Radial .............................................................................................................. 2,200 RPM

MISCELLANEOUS INSTRUMENT MARKINGS

Propeller De-ice Ammeter: Green Arc ....................................................................................................................... 18 to 24 amps

BEECH PROPELLER AUTOFEATHER SYSTEM INSTALLATION REQUIREMENTS

The optional Beech propeller autofeather system must be installed, operational, and armed prior to takeoff and landing.

CAUTION VMCA with one-engine inoperative, thrust lever at idle, and propeller windmilling is 99 KIAS (101 KCAS).

AIRSPEED LIMITATIONS

Air Minimum Control Speed, VMCA ................................................................................. 94 KCAS (93 KIAS)

Maximum Operating Speed, VMO, above 9,650 lbs (LJ-1063 thru LJ-1137, and LJ-1146) ......................................................................... 208 KCAS (208 KIAS)




AIRSPEED INDICATOR MARKINGS

C90/C90-1 (LJ-502 thru LJ-1062)

Red Radial (Air Minimum Control Speed, VMCA) ................................................................ 94 KCAS

C90A/C90B/C90SE (LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753, LJ-1755)

Red Radial (Air Minimum Control Speed, VMCA) ................................................................. 93 KIAS (LJ-1063 thru LJ-1137, and LJ-1146 only)

Red Line .......................................................................................................................... 208 KIAS*

Red and White Hash-Marked Pointer ............................................................................ 0.46 Mach* *Maximum speed for any operation is 208 KIAS or value equal to 0.46 Mach, whichever is lower.

AIRCRAFT EQUIPPED WITH GARMIN G1000

AIRSPEED INDICATOR DISPLAY (With Placard P/N REI-1001-14 installed)

Two (2) placards have been installed, one above each Primary Flight Display unit, to notify the pilot to disregard the VMC RED LINE displayed on the airspeed tape.

FLIGHT LOAD FACTORS At the design gross weight of 10,500 lbs ............................... Maneuver – positive 3.27G – negative 1.31G

MAXIMUM WEIGHT

Maximum Taxi Weight .................................................................................................................. 10,560 lbs Maximum Takeoff Weight ............................................................................................................. 10,500 lbs Maximum Landing Weight .............................................................................................................. 9,700 lbs Maximum Zero Fuel Weight:

For MTOW below 9,650 lbs .......................................................................................... No limitation For MTOW between 9,650 and 10,500 lbs ....................................................................... 9,000 lbs

NOTE

10-ply rated main tires required for operation above 10,100 lbs.

DISREGARD VMC MARKING VMC = 93 KIAS




CENTER OF GRAVITY LIMITS (LANDING GEAR EXTENDED)

Aft Limit .......................................................................................... 160.0 inches aft of Datum at all weights (LJ-527 thru LJ-1137, and LJ-1146) Forward Limit at:

10,500 lbs ...................................................................................................... 154.8 inches aft of Datum 10,350 lbs ...................................................................................................... 154.5 inches aft of Datum 10,100 lbs ...................................................................................................... 154.0 inches aft of Datum 9,700 lbs ........................................................................................................ 154.0 inches aft of Datum 9,168 lbs ........................................................................................................ 151.4 inches aft of Datum 7,400 lbs or less ............................................................................................ 144.7 inches aft of Datum

(LJ-1138 thru LJ-1145, LJ-1147 and after) Forward Limit at:

10,500 lbs * ................................................................................................... 153.4 inches aft of Datum 10,350 lbs ...................................................................................................... 153.0 inches aft of Datum 10,100 lbs ...................................................................................................... 152.0 inches aft of Datum 7,850 lbs or less ............................................................................................ 144.7 inches aft of Datum

PLACARDS

C90/C90-1 (LJ-502 thru LJ-1062)

On Existing Overhead Panel in Pilot’s Compartment:

MIN SINGLE ENGINE CONTROL 94 KNOTS (108 MPH)

(LJ-1063 thru LJ-1137, and LJ-1146 only)

On Overhead Panel in Pilot’s Compartment:

AIRSPEED LIMITATIONS: MAX OPERATION 208 KIAS (SL TO 20,300 FT) DECREASE BY

4 KNOTS FOR EVERY 1,000 FT ABOVE 20,300 FT



Document No. 13-206CGW Section III – Emergency Procedures

SECTION III — EMERGENCY PROCEDURES

ELECTROTHERMAL PROPELLER DE-ICE Operation in icing conditions with abnormal readings on the de-ice ammeter are not recommended and ice removal cannot be assured. Normal Operation: 18 to 24 amps.

1. Zero Amps:

a. Breaker Switch - CHECK. b. If OFF, reposition to ON after 30 seconds. c. If ON with zero amps, system is inoperative. Position switch to OFF.

2. Zero to 18 Amps:

a. Continue operation. b. If propeller imbalance occurs, increase RPM briefly to aid in ice removal.

3. 24 to 29 Amps:

a. Continue operation. b. If propeller imbalance occurs, increase RPM briefly to aid in ice removal.

4. More than 29 Amps:

a. Avoid icing conditions, since continued operation of the system cannot be assured. b. Do not operate the system, except in emergencies. c. Restrict time of operation to a minimum.



Document No. 13-206CGW Section IV – Normal Procedures

SECTION IV — NORMAL PROCEDURES

AFTER STARTING ENGINES

CAUTION

Stabilized ground operation between 400 and 1,100 RPM is prohibited. Operation between 0 and 400 RPM is permissible only with propeller feathered.

WARNING

STABILIZED GROUND OPERATION WITHIN THE PROPELLER RESTRICTED RPM RANGE CAN GENERATE HIGH PROPELLER STRESSES AND RESULT IN PROPELLER FAILURE AND LOSS OF CONTROL OF THE AIRCRAFT.

ICING FLIGHT

Electrothermal Propeller De-ice:

CAUTION

Do not operate propeller de-ice when propellers are static.

a. Before Takeoff:

(1) Propeller Heat Switch - HEAT. (2) Propeller De-ice Ammeter - CHECK: 18 to 24 AMPERES. Monitor for 2 minutes

to assure automatic timer operation.

b. In Flight:

(1) Propeller Heat Switch - HEAT. The system may be operated continuously in flight and will function automatically until the switch is turned to OFF.

(2) Relieve propeller imbalance due to ice by increasing rpm briefly and returning to the desired setting. Repeat as necessary.

CAUTION

If the de-ice ammeter does not indicate 18 to 24 amperes, refer to the EMERGENCY PROCEDURES section.

LANDING

WARNING

PROPELLERS WILL NOT REVERSE AT AIRSPEEDS ABOVE 100 KIAS. BETWEEN 95 KIAS AND 100 KIAS, SIGNIFICANT THRUST ASYMMETRY MAY OCCUR IF REVERSE IS SELECTED.

SIMULATING ENGINE FAILURES

CAUTION

Using throttle cuts to simulate engine failures will result in the autofeather system being disarmed. In this configuration the VMCA is 99 KIAS (101 KCAS). Dynamic throttle cuts should only be attempted at airspeeds above 104 KIAS (105 KCAS).



Document No. 13-206CGW Section IV – Normal Procedures

NOISE CHARACTERISTICS

Approach to and departure from an airport should be made so as to avoid prolonged flight at low altitude near noise-sensitive areas. Avoidance of noise-sensitive areas, if practical, is preferable to overflight at relatively low altitudes. For VFR operations over outdoor assemblies of persons, recreational and park areas, and other noise-sensitive areas, pilots should make every effort to fly not less than 2,000 feet above the surface, weather permitting, even though flight at a lower level may be consistent with the provisions of government regulations.

NOTE The preceding recommended procedures do not apply where they would conflict with Air Traffic Control clearances or instructions, or where, in the pilot’s judgment, an altitude of less than 2,000 feet is necessary to adequately exercise his duty to see and avoid other airplanes.

The corrected takeoff noise level of this airplane, established in compliance with FAR Part 36, Appendix G (Amdt 36-28) and ICAO Annex 16, Chapter 10, is 84.4 dB as determined by flight tests. No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable for operation at, into, or out of any airport. The above statement notwithstanding, the noise level stated above has been verified by and approved by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR Part 36, Appendix G, Amendment 28, Noise Standards: Airplane Type and Airworthiness Certification. The airplane noise is in compliance with all FAR Part 36 noise standards applicable to this type.



Document No. 13-206CGW Section V – Performance

SECTION V — PERFORMANCE

TABLE OF CONTENTS

INTRODUCTION

Introduction ........................................................................................................................................... 5-2

TAKEOFF AND CLIMB DATA

Stall Speeds - Zero Thrust .................................................................................................................... 5-3 Minimum Takeoff Power at 2200 RPM ................................................................................................. 5-4 Maximum Takeoff Weight to Achieve Positive One Engine Inoperative Climb at Lift-off ..................... 5-5 Maximum Allowable TOGW above 10,350 LBS ................................................................................... 5-6 Takeoff Distance – Flaps Up – Two Engines ....................................................................................... 5-7 Accelerate-Stop Distance – Flaps Up.................................................................................................... 5-8 Accelerate-Go Distance – Flaps Up ..................................................................................................... 5-9 Takeoff Climb Gradient – One-Engine-Inoperative ............................................................................. 5-10 Enroute Climb – All Engines Operating .............................................................................................. 5-11 Enroute Climb – One Engine Inoperative ........................................................................................... 5-12 Service Ceiling – One Engine Inoperative .......................................................................................... 5-13 Time, Fuel and Distance to Cruise Climb ........................................................................................... 5-14

CRUISE DATA

Normal Cruise Power Setting Tables:

ISA -30°C ..................................................................................................................................... 5-16 ISA -20°C ..................................................................................................................................... 5-17 ISA -10°C ..................................................................................................................................... 5-18 ISA ................................................................................................................................................ 5-19 ISA +10°C .................................................................................................................................... 5-20 ISA +20°C .................................................................................................................................... 5-21 ISA +30°C .................................................................................................................................... 5-22 ISA +37°C .................................................................................................................................... 5-23

Normal Cruise Power Setting Graphs: Normal Cruise Speeds ................................................................................................................. 5-24 Normal Cruise Power ................................................................................................................... 5-25 Fuel Flow at Normal Cruise Power .............................................................................................. 5-26

Maximum Cruise Power Setting Tables: ISA -30°C ..................................................................................................................................... 5-28 ISA -20°C ..................................................................................................................................... 5-29 ISA -10°C ..................................................................................................................................... 5-30 ISA ................................................................................................................................................ 5-31 ISA +10°C .................................................................................................................................... 5-32 ISA +20°C .................................................................................................................................... 5-33 ISA +30°C .................................................................................................................................... 5-34 ISA +37°C .................................................................................................................................... 5-35

Maximum Cruise Power Setting Graphs: Maximum Cruise Speeds ............................................................................................................. 5-36 Maximum Cruise Power ............................................................................................................... 5-37 Fuel Flow at Maximum Cruise Power .......................................................................................... 5-38




Maximum Range Power Setting Tables:

ISA -30°C ..................................................................................................................................... 5-40 ISA -20°C ..................................................................................................................................... 5-41 ISA -10°C ..................................................................................................................................... 5-42 ISA ................................................................................................................................................ 5-43 ISA +10°C .................................................................................................................................... 5-44 ISA +20°C .................................................................................................................................... 5-45 ISA +30°C .................................................................................................................................... 5-46 ISA +37°C .................................................................................................................................... 5-47

Range with 384 Gallons Usable Fuel ................................................................................................. 5-48 Endurance with 384 Gallons Usable Fuel .......................................................................................... 5-49

DESCENT AND LANDING DATA

Holding Time ....................................................................................................................................... 5-51 Time, Fuel, and Distance to Descend ................................................................................................ 5-52 Maximum Landing Weight – Flaps Down ........................................................................................... 5-53 Climb – Balked Landing ...................................................................................................................... 5-54 Landing Distance Without Propeller Reversing .................................................................................. 5-55 Landing Distance With Propeller Reversing ....................................................................................... 5-56

INTRODUCTION

The performance of all Beechcraft King Air C90/C90A airplanes equipped with the Raisbeck Increased Gross Weight System will perform to the graphs and charts in this section, up to a maximum takeoff gross weight of 10,500 lbs and a maximum landing weight of 9,700 lbs. Federal Aviation Regulations for this class aircraft require only that the all-engines operating distance over a 50 foot height be presented for take-off distance. We include for your information accelerate-go, accelerate-stop, climb-limited weight, net climb gradient, and other FAR 25 transport category information. For data not shown in this section, refer to Section V of the Beechcraft POH. Cruise performance is divided into three sections: NORMAL CRUISE, MAXIMUM CRUISE, and MAXIMUM RANGE. All sections recommend 1,750 propeller RPM for maximum quietness combined with excellent performance. Propeller RPM reduction in flight to 1,600 RPM is an option, requiring a rigging change to the propeller governors (see applicable Raisbeck Installation and Maintenance Manuals). Cruise at 1,750 RPM does not require this option. MAXIMUM CRUISE power settings reflect an increase in maximum allowable engine ITT to 695° C for C90 and C90-1 airplanes, per Raisbeck Engineering and FAA recertification of Pratt & Whitney Canada certified limits for the PT6A-21 engines. Slight variance in cruise speeds (±4 KTAS) may be evident between pitot inlet airplanes (C90A, C90B, C90SE) and chin inlet airplanes (C90 & C90-1).





5-4 FAA-Approved: Revision A: September 17, 2014


OUTSIDE AIR TEMPERATURE ~ DEGREES C

-40 -30 -20 -10 0 10 20 30 40 50 60

MIN

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M T

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220

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FT

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S

700

800

900

1000

1100

1200

1300

NOTE:THE POWER (TORQUE) INDICATED IS THE MINIMUM VALUEFOR WHICH TAKE-OFF PERFORMANCE CAN BE OBTAINED.EXCESS POWER WHICH CAN BE DEVELOPED WITHOUT EXCEEDING ENGINE LIMITATIONS MAY BE UTILIZED.


-40 -30 -20 -10 0 10 20 30 40 50 60

MINIMUM TAKE-OFF POWER AT 2200 RPM (70 KNOTS)

TORQUE LIMIT: 1315 FT-LBS

PR

ES

SU

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ALTITU

DE

~ FEE

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SL2000

40006000

8000

10,000

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EXAMPLE:OAT AT TAKE-OFF ........................................AIRPORT PRESSURE ALTITUDE ................. MINIMUM TAKE-OFF POWER ......................

25° C3966 FT 1105 FT-LBS







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10400

10450

10500


-30 -20 -10 0 10 20 30 40

MAX ALLOWABLE TAKE-OFF GROSS WEIGHT ABOVE 10,350 LBS

IN ORDER TO ACHIEVE PART 25 APPROACH CLIMB & LANDING REQUIREMENTS

8,00

0 FT

EXAMPLE:OAT ..................................................................AIRPORT PRESSURE ALTITUDE ..................MAX ALLOWABLE T.O.G.W. ..........................

11° C4,000 FT 10,470 LBS

6,0

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5-8 Reference Material: Revision B: June 7, 2016















Reference Material: Revision B: June 7, 2016 5-13






Reference Material: Revision A: September 17, 2014 5-15


C90 / C90-1 / C90A / C90B / C90SE

NORMAL CRUISE POWER SETTINGS

(LJ-527 and subsequent with PT6A-21 engines)


5-16 Reference Material: Revision A: September 17, 2014


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T-L

BS

400

500

600

700

800

900

1000

1100

1200

1300

1400

PRESSURE ALTITUDE ~ FT

29,000

28,000

26,000

24,000

22,000

20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

TORQUE LIMIT ~ 1315 FT-LBS

ISA

-30

° C

ISA

-20

° C

ISA

-10

° C

ISA

ISA

+10

° C

ISA

+20

° C

ISA

+30

° C

ISA

+37

° C




FUEL FLOW AT NORMAL CRUISE POWER


-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

FU

EL

FLO

W ~

LB

S /

HR

/ E

NG

INE

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

PRESSURE ALTITUDE ~ FT29,000

26,000

24,000

22,000

20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

SL

28,000

ISA

+30

° C

ISA

-20

° C

ISA

-30

° C

ISA

ISA

+20

° C

ISA

-10

° C

ISA

+37

° C

ISA

+10

° C




C90 / C90-1 / C90A / C90B / C90SE

MAXIMUM CRUISE POWER SETTINGS





MA

XIM

UM

CR

UIS

E P

OW

ER

ISA

-3

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PR

ES

SU

RE

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AS

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AS

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190

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112

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335

670

218

207

220

208

221

209

2,00

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327

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216

211

218

212

219

213

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320

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214

215

216

216

217

217

6,00

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314

628

212

219

214

220

215

221

8,00

0-2

6-1

513

153

106

202

102

232

112

242

132

25

10,

000

-30

-22

1315

308

616

208

227

209

229

211

230

12,

000

-34

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1315

306

612

206

231

207

233

209

234

14,

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-36

1315

305

610

204

236

205

238

207

239

16,

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306

612

202

241

203

242

204

244

175

01

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122

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641

932

371

952

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256

512

183

232

185

235

187

238

22,

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1065

231

462

172

226

175

230

178

233

24,

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209

418

162

219

165

224

168

228

26,

000

-62

-80

853

188

376

150

211

155

217

158

222

28,

000

-66

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758

168

336

137

200

144

209

149

216

29,

000

-69

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711

159

318

130

193

138

204

143

212

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317

634

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206

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316

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618

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244

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246

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2426

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218

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118

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1106

241

482

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232

176

236

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218

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162

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166

231

169

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196

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217

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481

315

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216

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411

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331

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213

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361

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323

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211

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209

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314

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207

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208

230

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10,

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141

315

313

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205

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206

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12,

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000

1966

112

325

450

817

42

341

7623

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924

0

18,

000

1559

105

423

947

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72

321

7023

617

223

9

20,

000

1050

990

225

450

159

229

163

234

166

238

22,

000

643

926

211

422

152

226

156

232

159

237

24,

000

236

865

198

396

144

221

149

229

153

235

26,

000

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806

185

370

134

215

141

225

146

233

28,

000

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740

172

344

122

203

132

219

138

228

29,

000

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705

165

330

114

193

126

213

133

225

NO

TE

:1

. IO

AT

, T

OR

QU

E A

ND

FU

EL

FL

OW

BA

SE

D O

N 8

50

0 P

OU

ND

S2

. U

SE

19

00

RP

M W

HE

N T

OR

QU

E-L

IMIT

ED

3.

US

E 1

75

0 R

PM

AT

HIG

HE

R A

LT

ITU

DE

4.

OB

SE

RV

E V

MO

/ M

MO L

IMIT

AT

ION

WH

ER

E A

PP

LIC

AB

LE

PR

OP

RP

M

AIR

SP

EE

D K

NO

TS

95

00

LB

S8

50

0 L

BS

75

00

LB

SIO

AT




MA

XIM

UM

CR

UIS

E P

OW

ER

ISA

+3

7° C

PR

ES

SU

RE

TO

RQ

UE

FU

EL

F

LO

WT

OT

AL

AL

TIT

UD

EP

ER

E

NG

INE

PE

R

EN

GIN

EF

UE

L

FL

OW

FE

ET

CF

FT

-LB

SL

BS

/HR

LB

S/H

RC

AS

TA

SC

AS

TA

SC

AS

TA

S

190

0S

L5

713

513

1535

370

620

92

2221

122

421

22

25

2,0

005

312

713

1534

468

820

72

2720

822

821

02

29

4,0

004

912

013

1533

667

220

52

3120

623

320

72

34

6,0

004

511

312

9632

665

220

12

3420

323

620

42

37

175

08

,000

41

106

1315

309

618

196

234

197

236

199

238

10,0

00

37

9912

7029

158

418

92

3419

123

619

32

38

12,0

00

33

9111

9827

555

018

22

3318

523

618

62

38

14,0

00

29

8411

3025

951

817

62

3217

823

518

02

38

16,0

00

25

7710

6424

448

815

92

3017

223

417

42

37

18,0

00

21

7010

0022

945

816

22

2816

523

216

82

36

20,0

00

17

639

3921

643

215

42

2515

823

116

22

35

22,0

00

13

558

7820

240

414

72

2115

122

815

52

34

24,0

00

948

821

190

380

138

216

144

225

148

232

26,0

00

541

763

177

354

128

208

136

220

141

229

28,0

00

134

704

165

330

115

193

127

213

134

224

29,0

00

-130

674

159

318

103

176

121

208

129

222

NO

TE

:1

. IO

AT

, T

OR

QU

E A

ND

FU

EL

FL

OW

BA

SE

D O

N 8

50

0 P

OU

ND

S2

. U

SE

19

00

RP

M W

HE

N T

OR

QU

E-L

IMIT

ED

3.

US

E 1

75

0 R

PM

AT

HIG

HE

R A

LT

ITU

DE

4.

OB

SE

RV

E V

MO

/ M

MO L

IMIT

AT

ION

WH

ER

E A

PP

LIC

AB

LE

PR

OP

RP

MIO

AT

AIR

SP

EE

D K

NO

TS

95

00

LB

S8

50

0 L

BS

75

00

LB

S




MAXIMUM CRUISE SPEEDS

TRUE AIRSPEED ~ KNOTS

140 160 180 200 220 240 260

PR

ES

SU

RE

AL

TIT

UD

E ~

FE

ET

0

5000

10000

15000

20000

25000

30000

MAXIMUM CRUISE SPEEDS

ISA

-30°

CIS

AIS

A +

30°

C




MAXIMUM CRUISE POWER


-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

TO

RQ

UE

SE

TT

ING

~ F

T-L

BS

400

500

600

700

800

900

1000

1100

1200

1300

1400


29,000

28,000

26,000

24,000

22,000

20,000

18,000

16,000

14,000

12,000

10,000

TORQUE LIMIT ~ 1315 FT-LBS

ISA

-30

° C

ISA

-20

° C

ISA

-10

° C

ISA

ISA

+10

° C

ISA

+20

° C

ISA

+30

° C

ISA

+37

° C




FUEL FLOW AT MAXIMUM CRUISE POWER


-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

FU

EL

FLO

W ~

LB

S /

HR

/ E

NG

INE

130

140

150

160

170

180

190

200

210

220

230

240

250

260

270

280

290

300

310

320

330

340

350

360


29,000

26,000

24,000

22,000

20,000

18,000

16,000

14,000

12,000

10,000

8,000

6,000

4,000

2,000

SL

28,000

ISA

+30

° C

ISA

-20

° C

ISA

-30

° C

ISA

ISA

+20

° C

ISA

-10

° C

ISA

+37

° C

ISA

+10

° C

ISA

-30

° C

ISA

-20

° C

ISA

-10

° C

ISA

ISA

+10

° C




C90 / C90-1 / C90A / C90B / C90SE

MAXIMUM RANGE POWER SETTINGS AT

1750 RPM





FE

ET

°C°F

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

SL

-12

10

877

253

506

171

814

244

488

167

749

234

468

164

2,00

0-1

63

841

239

478

170

775

229

458

167

704

218

436

163

4,00

0-2

0-4

801

224

448

170

729

213

426

165

653

201

402

161

6,00

0-2

4-6

767

211

422

169

686

198

396

164

604

186

372

158

8,00

0-2

8-1

875

020

140

217

066

71

8837

616

557

717

43

4815

8

10,0

00-3

2-2

673

919

338

617

265

91

8136

216

757

016

73

3416

0

12,0

00-3

6-3

373

218

637

217

465

31

7434

816

956

516

03

2016

2

14,0

00-4

0-4

071

917

935

817

663

71

6633

217

055

315

23

0416

3

16,0

00-4

4-4

770

617

234

417

762

31

5831

617

153

914

42

8816

4

18,0

00-4

8-5

469

416

633

217

860

91

5130

217

252

513

72

7416

5

20,0

00-5

2-6

268

616

232

418

059

91

4629

217

351

513

12

6216

6

22,0

00-5

6-6

968

415

831

618

259

61

4328

617

550

812

72

5416

7

24,0

00-6

0-7

668

715

731

418

559

71

4028

017

850

612

42

4817

0

26,0

00-6

3-8

170

015

831

619

059

81

3927

818

150

812

22

4417

3

28,0

00-6

7-8

970

115

731

419

261

01

4028

018

551

412

12

4217

6

29,0

00-6

9-9

269

715

631

219

261

91

4128

218

851

812

12

4217

8

M

AX

IMU

M R

AN

GE

PO

WE

R

ISA

-30

°C

WE

IGH

T95

00 P

OU

ND

S85

00 P

OU

ND

S75

00 P

OU

ND

S

1750

RP

M

PR

ES

S

AL

TIT

UD

EIO

AT

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

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FU

EL

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W

TO

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L

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EL

FL

OW

P

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EN

G.

TA

SF

UE

L

FL

OW

T

OT

AL

TA

ST

OR

QU

E

PE

R E

NG

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UE

L F

LO

W

PE

R E

NG

.

FU

EL

F

LO

W

TO

TA

LT

AS

TO

RQ

UE

P

ER

EN

G.




FE

ET

°C°F

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

SL

-22

89

0525

951

81

758

4525

050

01

7278

924

14

8216

9

2,0

00-6

21

866

244

488

175

803

234

468

171

746

226

452

168

4,0

00-1

01

48

4723

346

61

767

7722

344

61

7271

221

34

2616

8

6,0

00-1

47

823

222

444

177

750

211

422

173

683

201

402

168

8,0

00-1

80

800

211

422

178

725

200

400

173

655

189

378

168

10,

000

-22

-87

7820

240

41

796

9718

937

81

7362

017

73

5416

7

12,

000

-26

-15

769

194

388

181

682

181

362

174

603

168

336

168

14,

000

-30

-22

760

188

376

183

674

174

348

176

591

161

322

170

16,

000

-34

-29

727

181

362

185

667

168

336

179

583

155

310

172

18,

000

-38

-36

738

175

350

186

658

162

324

181

575

149

298

174

20,

000

-42

-44

730

170

340

188

648

157

314

182

565

143

286

175

22,

000

-45

-49

719

166

332

189

638

152

304

184

556

138

276

177

24,

000

-49

-56

708

162

324

190

633

148

296

186

548

133

266

179

26,

000

-53

-63

711

161

322

193

633

146

292

189

544

130

260

181

28,

000

-57

-71

719

162

324

197

631

145

290

191

543

128

256

183

29,

000

-59

-74

713

161

322

197

632

144

288

192

546

128

256

185

M

AX

IMU

M R

AN

GE

PO

WE

R

ISA

-2

0°C

WE

IGH

T95

00 P

OU

ND

S85

00 P

OU

ND

S7

500

PO

UN

DS

1750

RP

M

PR

ES

S

AL

TIT

UD

EIO

AT

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.

FU

EL

F

LO

W

TO

TA

LT

AS

FU

EL

F

LO

W

TO

TA

LT

AS

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.

FU

EL

F

LO

W

TO

TA

LT

AS

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.




FE

ET

°C°F

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

SL

846

864

255

510

173

801

245

490

170

745

236

472

167

2,00

04

3986

924

749

417

780

323

747

417

374

522

845

617

0

4,00

00

3286

623

747

418

079

922

745

417

673

621

843

617

2

6,00

0-4

2585

022

745

418

177

421

643

217

770

720

541

017

3

8,00

0-8

1883

321

743

418

375

920

641

217

968

519

539

017

4

10,0

00-1

210

813

209

418

184

740

198

396

180

666

186

372

175

12,0

00-1

63

794

200

400

185

724

189

378

181

649

178

356

176

14,0

00-2

0-4

775

192

384

187

709

181

362

183

630

169

338

177

16,0

00-2

4-1

175

918

537

018

869

717

535

018

561

616

232

417

8

18,0

00-2

7-1

774

017

835

618

968

716

833

618

760

615

531

018

0

20,0

00-3

1-2

472

117

134

218

967

416

232

418

859

815

030

018

3

22,0

00-3

5-3

172

016

833

619

165

815

731

418

959

114

529

018

5

24,0

00-3

9-3

872

516

733

419

564

115

130

218

958

314

128

218

7

26,0

00-4

3-4

572

116

533

019

663

614

829

619

157

513

727

418

8

28,0

00-4

7-5

372

616

533

019

964

514

829

619

556

313

326

618

9

29,0

00-4

9-5

672

916

633

220

164

414

829

619

655

813

126

218

9

17

50 R

PM

TA

S

M

AX

IMU

M R

AN

GE

PO

WE

R

ISA

-1

0°C

WE

IGH

T95

00 P

OU

ND

S8

500

PO

UN

DS

7500

PO

UN

DS

PR

ES

S

AL

TIT

UD

EIO

AT

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.

FU

EL

F

LO

W

TO

TA

L

FU

EL

F

LO

W

TO

TA

LT

AS

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.

FU

EL

F

LO

W

TO

TA

LT

AS

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.




FE

ET

°C°F

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

SL

1864

879

260

520

176

788

246

492

171

717

235

470

166

2,00

014

5786

724

949

817

977

623

547

017

370

722

444

816

8

4,00

010

5085

923

947

818

177

322

645

217

670

421

543

017

1

6,00

06

4384

622

945

818

377

321

843

617

970

620

741

417

5

8,00

02

3682

621

843

618

476

720

941

818

170

219

939

817

8

10,0

00-2

2880

520

841

618

575

020

040

018

369

219

138

218

0

12,0

00-6

2178

519

939

818

672

919

038

018

466

918

136

218

0

14,0

00-1

014

775

193

386

189

709

183

366

185

655

174

348

182

16,0

00-1

39

772

189

378

191

693

176

352

186

638

167

334

183

18,0

00-1

71

767

183

366

194

679

169

338

187

621

159

318

185

20,0

00-2

1-6

756

178

356

195

673

164

328

190

608

153

306

186

22,0

00-2

5-1

373

217

134

219

567

016

032

019

359

414

729

418

7

24,0

00-2

9-2

072

016

833

619

566

415

631

219

558

014

228

418

8

26,0

00-3

3-2

773

316

933

820

065

115

230

419

556

913

727

418

9

28,0

00-3

7-3

573

316

933

820

264

315

030

019

657

113

527

019

2

29,0

00-3

9-3

874

017

034

020

465

115

130

219

957

413

527

019

4

17

50 R

PM

TA

S

M

AX

IMU

M R

AN

GE

PO

WE

R

ISA

WE

IGH

T95

00 P

OU

ND

S8

500

PO

UN

DS

7500

PO

UN

DS

PR

ES

S

AL

TIT

UD

EIO

AT

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

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EL

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LO

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TO

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L

FU

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TO

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AS

TO

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UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.

FU

EL

F

LO

W

TO

TA

LT

AS

TO

RQ

UE

P

ER

EN

G.

FU

EL

FL

OW

P

ER

EN

G.




FE

ET

°C°F

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

FT

-LB

SL

BS

/HR

LB

S/H

RK

NO

TS

SL

2882

861

259

518

177

795

249

498

173

734

239

478

170

2,00

024

7586

525

150

218

079

323

947

817

671

922

845

617

1

4,00

020

6887

124

248

418

478

923

046

017

969

521

643

217

2

6,00

016

6186

923

446

818

778

622

144

218

268

920

741

417

5

8,00

012

5485

222

444

818

977

721

342

618

568

519

939

817

8

10,0

008

4683

521

543

019

176

120

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C90 / C90-1 / C90A / C90B / C90SE

DESCENT AND LANDING DATA








TIME, FUEL, & DISTANCE TO DESCENDDESCEND SPEED: 169 KNOTS

TIME TO DESCEND ~ MINUTES

0 5 10 15 20

PR

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FE

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15000

20000

25000

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TIME, FUEL, & DISTANCE TO DESCENDDESCEND SPEED: 169 KNOTS

FUEL USED TO DESCEND ~ POUNDS

DESCENT DISTANCE ~ NAUTICAL MILES

0 20 40 60

0

80

10 20 30 40 50 60 70 80

EXAMPLE:INITIAL ALTITUDE ...................................FINAL ALTITUDE .................................... TIME TO DESCEND .................................FUEL TO DESCEND ................................DISTANCE TO DESCEND .......................

17,000 FT5651 FT (11.3 - 3.8) = 7.5 MIN(47 - 17) = 30 LBS(37 - 12) = 25 NM

ASSOCIATED CONDITIONS:POWER .....................................

LANDING GEAR ........................FLAPS .......................................PROPELLER SPEED ................

AS REQUIRED TO DESCEND AT1500 FT / MINUPUP1750 RPM


Reference Material: Revision B: June 7, 2016 5-53











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FAA Approved: Revision A: September 17, 2014 6-1

Document No. 13-206CGW Section VI – Weight and Balance

SECTION VI — WEIGHT AND BALANCE (LJ-527 thru LJ-1137, and LJ-1146)

CENTER-OF-GRAVITY LIMITS

CENTER OF GRAVITY ~ INCHES AFT OF DATUM

144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161

GR

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BS

7000

7500

8000

8500

9000

9500

10000

10500MAXIMUM TAKEOFF WEIGHT

MAXIMUM LANDING WEIGHT

MAXIMUM ZERO FUEL WEIGHT

NOTE: MAXIMUM RAMP WEIGHT 10,560 LBS


6-2 FAA Approved: Revision A: September 17, 2014

Document No. 13-206CGW Section VI – Weight and Balance

SECTION VI — WEIGHT AND BALANCE (LJ-1138 thru LJ-1145, LJ-1147 and after)

CENTER-OF-GRAVITY LIMITS

CENTER OF GRAVITY ~ INCHES AFT OF DATUM

144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161

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7000

7500

8000

8500

9000

9500

10000

10500MAXIMUM TAKEOFF WEIGHT

MAXIMUM LANDING WEIGHT

MAXIMUM ZERO FUEL WEIGHT

NOTE: MAXIMUM RAMP WEIGHT 10,560 LBS



Document No. 13-206CGW Section VII – Systems Description

SECTION VII — SYSTEMS DESCRIPTION

HARTZELL/RAISBECK SWEPT BLADE TURBOFAN PROPELLER SYSTEM

Each engine is equipped with an advanced technology, lightweight, Hartzell/Raisbeck Swept Blade Turbofan propeller. Each propeller contains four blades, in full feathering, constant speed, counter-weighted, reversing, variable-pitch, and mounted on the output shaft of the reduction gearbox. The propeller pitch and speed are controlled by engine oil pressure, through single action engine-driven propeller governors. Centrifugal counter-weights, assisted by a feathering spring, move the blades toward the low RPM (high pitch) position and into the feathered position. Governor boosted engine oil pressure moves the propeller to the high RPM (low pitch) hydraulic stop and reverse position. The propellers have no low RPM (high pitch) stops; this allows the blades to feather after engine shut-down.

OPTIONAL 1,600 RPM MINIMUM CRUISE

For those wishing the absolute quietest cockpit and cabin in cruise, propeller cruise RPM as low as 1,600 RPM is available as an option. Resetting the propeller governor to Raisbeck specifications per Raisbeck Maintenance Manual (85-120) is required.

DUAL AFT BODY STRAKES The Raisbeck Dual Aft Body Strakes are mounted on the underside of the aft fuselage, and replace the single ventral fin. They are designed and engineered to attach and streamline the airflow over the aft body reducing drag, improving aircraft stability and VMC.

PROPELLER DE-ICE SYSTEM

The Hartzell propeller electric de-ice system includes an electronically heated boot for each propeller blade, brush assemblies, slip rings, an ammeter, a timer for automatic operation, and a manual control circuit for backup. The de-ice ammeter indicates the system amperage (normally 18 to 24 amperes). The timer directs current to the single-element boot on each blade in the following sequence: right propeller all elements; then left propeller all elements. Loss of one heating element circuit on one side does not mean that the entire system must be turned off. The timer switches every 90 seconds resulting in a complete cycle in approximately 3 minutes.

Documents

KING AIR MODEL C90/C90A - aso.com · AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS C90/C90A Equipped with Raisbeck Engineering: Swept Blade Turbofan Propellers