KING AIR MODEL C90/C90A

PILOT S OPERATING HANDBOOK and FAA-Approved Airplane Flight Manual Supplement for the KING AIR MODEL C90/C90A Equipped with Raisbeck Engineering: - STC SA3593NM - STC SA4010NM - 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) Revision B: June 7, 2016

PILOT S OPERATING HANDBOOK AND FAA-APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECHCRAFT KING AIR MODELS C90/C90A Equipped with Raisbeck Engineering: - STC SA3593NM - STC SA4010NM - 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 FAA-Approved: Revision B: June 7, 2016 i

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 B Title, i, ii, 1-1 2-2 2-3, 2-4 5-5 thru 5-14, 5-54 5-53 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. 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 ii FAA-Approved: Revision B: June 7, 2016

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 A: September 17, 2014 iii

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: Propeller Type: Maximum: Minimum: 96 inches 95 inches 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 B: June 7, 2016 1-1

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 N 1 PROP OIL OIL OBSERVED RPM PRESS TEMP FT LBS (1) ITT C RPM % N 2 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 (N 2 ) must be set so at not to exceed power limitation. (2) When gas generator speeds are above 72% N 1 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 N 1 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 N 1 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: Minimum diameter: 96.0 inches 95.0 inches PROPELLER BLADE ANGLES AT 30-INCH STATION Reverse: -10.0 ± 0.5 Feathered: +86.7 ± 0.5 FAA-Approved: Revision A: September 17, 2014 2-1

Section II - Limitations 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 V MCA with one-engine inoperative, thrust lever at idle, and propeller windmilling is 99 KIAS (101 KCAS). AIRSPEED LIMITATIONS Air Minimum Control Speed, V MCA... 94 KCAS (93 KIAS) Maximum Operating Speed, V MO, above 9,650 lbs (LJ-1063 thru LJ-1137, and LJ-1146)... 208 KCAS (208 KIAS) 2-2 FAA-Approved: Revision B: June 7, 2016

Section II - Limitations AIRSPEED INDICATOR MARKINGS C90/C90-1 (LJ-502 thru LJ-1062) Red Radial (Air Minimum Control Speed, V MCA )... 94 KCAS C90A/C90B/C90SE (LJ-1063 thru LJ-1726, LJ-1728 thru LJ-1753, LJ-1755) Red Radial (Air Minimum Control Speed, V MCA )... 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 V MC RED LINE displayed on the airspeed tape. DISREGARD V MC MARKING V MC = 93 KIAS 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. FAA-Approved: Revision B: June 7, 2016 2-3

Section II - Limitations 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 2-4 FAA-Approved: Revision B: June 7, 2016

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. FAA-Approved: Revision A: September 17, 2014 3-1

Section IV Normal Procedures SECTION IV NORMAL PROCEDURES AFTER STARTING ENGINES ICING FLIGHT LANDING 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. 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. 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 V MCA is 99 KIAS (101 KCAS). Dynamic throttle cuts should only be attempted at airspeeds above 104 KIAS (105 KCAS). FAA-Approved: Revision A: September 17, 2014 4-1

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. 4-2 FAA-Approved: Revision B: June 7, 2016

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 FAA-Approved: Revision B: June 7, 2016 5-1

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, acceleratestop, 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). 5-2 FAA-Approved: Revision B: June 7, 2016

FAA-Approved: Revision A: September 17, 2014 5-3

MINIMUM TAKE-OFF POWER AT 2200 RPM (70 KNOTS) NOTE: THE POWER (TORQUE) INDICATED IS THE MINIMUM VALUE FOR WHICH TAKE-OFF PERFORMANCE CAN BE OBTAINED. EXCESS POWER WHICH CAN BE DEVELOPED WITHOUT EXCEEDING ENGINE LIMITATIONS MAY BE UTILIZED. EXAMPLE: OAT AT TAKE-OFF... AIRPORT PRESSURE ALTITUDE... MINIMUM TAKE-OFF POWER... 25 C 3966 FT 1105 FT-LBS TORQUE LIMIT: 1315 FT-LBS 1300 MINIMUM TORQUE SETTING (2200 RPM) ~ FT-LBS 1200 1100 1000 900 10,000 8000 6000 4000 2000 SL PRESSURE ALTITUDE ~ FEET ISA + 37 C 800 700-40 -30-20 -10 0 10 20 30 40 50 60 OUTSIDE AIR TEMPERATURE ~ DEGREES C 5-4 FAA-Approved: Revision A: September 17, 2014

FAA-Approved: Revision B: June 7, 2016 5-5

MAX ALLOWABLE TAKE-OFF GROSS WEIGHT ABOVE 10,350 LBS IN ORDER TO ACHIEVE PART 25 APPROACH CLIMB & LANDING REQUIREMENTS EXAMPLE: OAT... 11 C AIRPORT PRESSURE ALTITUDE... 4,000 FT MAX ALLOWABLE T.O.G.W.... 10,470 LBS 10500 PRESSURE ALTITUDE ~ FEET 8,000 FT 6,000 FT 4,000 FT 2,000 FT SEA LEVEL MAX ALLOWABLE T.O.G.W. ~ LBS 10450 10400 10350-30 -20-10 0 10 20 30 40 OUTSIDE AIR TEMPERATURE ~ DEGREES C 5-6 FAA-Approved: Revision A: September 17, 2014

FAA-Approved: Revision B: June 7, 2016 5-7

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

FAA-Approved: Revision B: June 7, 2016 5-9

5-10 FAA-Approved: Revision B: June 7, 2016

FAA-Approved: Revision B: June 7, 2016 5-11

5-12 FAA-Approved: Revision B: June 7, 2016

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

5-14 Reference Material: Revision B: June 7, 2016

C90 / C90-1 / C90A / C90B / C90SE NORMAL CRUISE POWER SETTINGS (LJ-527 and subsequent with PT6A-21 engines) Reference Material: Revision A: September 17, 2014 5-15

NORMAL CRUISE POWER ISA -30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL -11 12 1180 305 610 208 197 208 197 208 197 2,000-15 5 1209 301 602 208 203 208 203 208 203 4,000-19 -2 1241 299 598 208 208 208 208 208 208 6,000-23 -9 1274 298 596 208 214 208 214 208 214 8,000-26 -15 1308 299 598 207 219 208 220 208 220 10,000-30 -22 1315 298 596 205 224 206 225 208 227 12,000-34 -29 1315 296 592 203 228 204 230 206 231 14,000-38 -36 1315 295 590 201 232 202 234 204 236 1750 16,000-42 -44 1315 276 552 193 230 195 233 197 235 18,000-46 -51 1202 250 500 183 225 185 228 187 231 20,000-50 -58 1083 226 452 172 219 175 223 178 226 22,000-54 -65 973 204 408 161 212 165 217 168 221 24,000-58 -72 870 184 368 150 204 155 211 159 216 26,000-63 -81 772 165 330 137 193 144 202 149 209 28,000-67 -89 682 147 294 120 175 131 191 138 201 29,000-71 -96 635 139 278 101 150 127 182 132 196 5-16 Reference Material: Revision A: September 17, 2014

NORMAL CRUISE POWER ISA -20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL -1 30 1202 310 620 208 201 208 201 208 201 2,000-5 23 1232 306 612 208 206 208 206 208 206 4,000-9 16 1266 305 610 208 212 208 212 208 212 6,000-12 10 1300 305 610 208 218 208 219 208 219 8,000-16 3 1315 304 608 205 222 207 224 208 225 10,000-20 -4 1315 301 602 203 226 205 228 206 230 12,000-24 -11 1315 299 598 201 231 203 233 204 234 14,000-28 -18 1315 297 594 199 235 200 237 202 239 16,000-31 -24 1268 289 578 193 236 196 239 197 241 1750 18,000-36 -33 1245 260 520 183 231 186 234 188 237 20,000-40 -40 1124 236 472 173 225 176 229 179 232 22,000-44 -47 1008 213 426 162 219 166 223 169 227 24,000-48 -54 905 192 384 151 210 156 217 160 222 26,000-52 -62 806 173 346 139 200 145 209 150 216 28,000-57 -71 713 154 308 123 184 133 199 139 208 29,000-59 -75 669 146 292 103 156 126 190 134 203 Reference Material: Revision A: September 17, 2014 5-17

NORMAL CRUISE POWER ISA -10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 9 48 1223 316 632 208 204 208 204 208 204 2,000 5 41 1256 313 626 208 210 208 210 208 210 4,000 1 34 1290 312 624 208 216 208 216 208 216 6,000-2 28 1315 310 620 206 221 208 222 208 223 8,000-6 21 1315 306 612 204 225 205 227 207 228 10,000-10 14 1315 303 606 202 229 203 231 205 232 12,000-14 7 1315 301 602 199 233 201 235 202 237 14,000-17 1 1301 296 592 196 237 198 239 200 241 1750 16,000-21 -6 1315 279 558 189 235 191 238 193 240 18,000-25 -13 1242 262 524 182 234 184 237 186 239 20,000-30 -22 1156 245 490 174 231 176 235 179 238 22,000-34 -29 1043 222 444 163 224 167 229 170 233 24,000-38 -36 938 201 402 152 217 157 223 161 228 26,000-42 -44 835 180 360 140 206 146 215 151 222 28,000-47 -53 741 161 322 125 190 134 205 140 214 29,000-49 -57 696 152 304 104 162 127 197 135 209 5-18 Reference Material: Revision A: September 17, 2014

NORMAL CRUISE POWER ISA NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 19 66 1247 323 646 208 208 208 208 208 208 2,000 15 59 1281 321 642 208 214 208 214 208 214 4,000 12 54 1315 319 638 207 219 208 221 208 220 6,000 8 46 1315 313 626 205 223 206 225 207 226 8,000 4 39 1315 308 616 202 227 204 229 205 231 10,000 0 32 1315 304 608 200 232 202 234 203 235 12,000-4 25 1301 298 596 197 235 199 237 200 239 1750 14,000-8 18 1315 281 562 190 233 192 236 193 238 16,000-12 10 1243 265 530 182 232 185 235 187 237 18,000-16 3 1169 249 498 175 230 178 234 180 237 20,000-20 -4 1097 234 468 168 228 171 232 174 236 22,000-24 -11 1023 220 440 160 225 164 230 167 234 24,000-28 -18 948 204 408 151 220 156 227 160 232 26,000-32 -26 862 187 374 140 211 147 221 151 227 28,000-36 -33 767 168 336 126 196 135 211 141 220 29,000-39 -38 719 159 318 104 167 128 203 135 215 Reference Material: Revision A: September 17, 2014 5-19

NORMAL CRUISE POWER ISA +10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 29 84 1270 330 660 208 212 208 212 208 212 2,000 25 77 1304 327 654 208 217 208 218 208 218 4,000 22 72 1315 321 642 205 221 207 223 208 224 6,000 18 64 1315 315 630 203 226 205 227 206 229 8,000 14 57 1315 309 618 201 2300 203 232 204 233 10,000 10 50 1280 298 596 196 232 198 234 200 236 1750 12,000 6 43 1315 282 564 190 231 192 234 194 236 14,000 2 36 1242 266 532 183 230 185 233 187 235 16,000-2 28 1171 251 502 176 229 179 232 181 235 18,000-6 21 1102 236 472 169 227 172 231 175 234 20,000-10 14 1022 222 444 161 223 165 228 167 232 22,000-14 7 956 208 416 153 220 158 226 161 231 24,000-18 0 895 196 392 145 215 150 223 154 229 26,000-22 -8 832 183 366 136 209 142 219 147 226 28,000-26 -15 765 169 338 123 197 133 212 139 222 29,000-29 -20 730 162 324 104 169 127 206 135 218 5-20 Reference Material: Revision A: September 17, 2014

NORMAL CRUISE POWER ISA +20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 39 102 1290 336 672 208 215 208 215 208 215 2,000 36 97 1315 331 662 206 220 207 221 208 222 4,000 32 90 1315 323 646 204 224 205 225 207 227 6,000 28 82 1308 315 630 201 227 203 229 204 231 8,000 24 75 1250 299 598 195 228 197 230 199 232 1750 10,000 20 68 1285 282 564 189 227 191 230 193 232 12,000 16 61 1216 266 532 182 226 185 229 187 231 14,000 12 54 1150 252 504 176 225 179 228 181 231 16,000 8 46 1086 237 474 169 224 172 228 175 231 18,000 4 39 1024 224 448 162 222 166 226 169 230 20,000 0 32 962 210 420 155 219 159 225 162 229 22,000-4 25 902 198 396 147 215 152 222 156 227 24,000-8 18 834 185 370 137 208 144 217 148 224 26,000-12 10 772 173 346 126 198 135 212 141 221 28,000-17 1 715 161 322 112 182 126 205 133 216 29,000-19 -6 688 155 310 99 164 120 199 129 213 Reference Material: Revision A: September 17, 2014 5-21

NORMAL CRUISE POWER ISA +30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 49 120 1301 339 678 206 217 208 218 208 219 1900 2,000 46 115 1270 325 650 202 219 204 220 205 222 1750 4,000 42 108 1315 312 624 198 221 200 222 201 224 6,000 38 100 1302 298 596 193 222 195 224 197 226 8,000 34 93 1250 283 566 188 222 190 225 192 227 10,000 30 86 1187 268 536 182 222 184 225 186 227 12,000 26 79 1123 252 504 175 221 178 224 180 227 14,000 22 72 1061 238 476 168 219 171 223 174 227 16,000 18 64 1000 224 448 162 218 165 222 168 226 18,000 14 57 942 211 422 154 215 158 221 162 225 20,000 10 50 888 198 396 147 211 152 218 156 224 22,000 6 43 832 186 372 139 207 145 215 149 222 24,000 2 36 780 175 350 129 199 137 211 142 220 26,000-3 27 726 163 326 117 188 128 206 135 216 28,000-7 19 669 152 304 85 142 117 195 127 211 29,000-10 15 635 146 292 107 180 121 205 5-22 Reference Material: Revision A: September 17, 2014

NORMAL CRUISE POWER ISA +37 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1750 SL 56 133 1315 326 652 200 212 201 214 203 216 2,000 52 136 1286 313 626 196 214 198 216 199 218 4,000 48 118 1256 300 600 192 216 194 218 195 220 6,000 45 113 1219 286 572 187 218 189 220 191 222 8,000 41 106 1171 272 544 182 218 184 221 186 223 10,000 37 99 1113 257 514 176 217 178 221 181 223 12,000 33 91 1055 243 486 169 216 172 220 175 223 14,000 29 84 999 229 458 163 215 166 219 169 223 16,000 25 77 943 216 432 156 213 160 218 163 222 18,000 21 70 889 203 406 149 210 153 216 157 221 20,000 17 63 837 190 380 141 205 146 214 151 220 22,000 13 55 784 179 358 132 199 139 210 144 218 24,000 8 46 733 168 338 121 190 131 205 137 215 26,000 6 39 683 157 314 103 168 122 198 130 211 28,000 0 32 633 146 292 85 144 109 185 122 205 29,000-3 26 601 140 280 95 163 117 200 Reference Material: Revision A: September 17, 2014 5-23

NORMAL CRUISE SPEEDS WEIGHT 8500 LBS 30000 ISA 25000 PRESSURE ALTITUDE ~ FEET 20000 15000 10000 ISA -30 C ISA +30 C 5000 0 160 180 200 220 240 260 TRUE AIRSPEED ~ KNOTS 5-24 Reference Material: Revision A: September 17, 2014

NORMAL CRUISE POWER 1400 TORQUE LIMIT ~ 1315 FT-LBS 1300 2,000 4,000 1200 6,000 8,000 1100 10,000 12,000 TORQUE SETTING ~ FT-LBS 1000 900 800 14,000 16,000 18,000 20,000 22,000 PRESSURE ALTITUDE ~ FT 700 600 ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C 24,000 26,000 28,000 29,000 500 400-80 -70-60 -50-40 -30-20 -10 0 10 20 30 40 50 60 INDICATED OUTSIDE AIR TEMPERATURE ~ C Reference Material: Revision A: September 17, 2014 5-25

AT NORMAL CRUISE POWER 350 340 330 ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C 320 SL 310 300 ISA -30 C ISA -20 C ISA -10 C 4,000 2,000 290 280 6,000 270 8,000 ~ LBS / HR / ENGINE 260 250 240 230 220 14,000 12,000 10,000 210 16,000 200 18,000 190 20,000 180 22,000 170 24,000 PRESSURE ALTITUDE ~ FT 160 26,000 150 28,000 140 29,000 130-80 -70-60 -50-40 -30-20 -10 0 10 20 30 40 50 60 INDICATED OUTSIDE AIR TEMPERATURE ~ C 5-26 Reference Material: Revision A: September 17, 2014

C90 / C90-1 / C90A / C90B / C90SE MAXIMUM CRUISE POWER SETTINGS (LJ-527 and subsequent with PT6A-21 engines) Reference Material: Revision A: September 17, 2014 5-27

MAXIMUM CRUISE POWER ISA -30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL -11 12 1315 335 670 218 207 220 208 221 209 2,000-15 5 1315 327 654 216 211 218 212 219 213 4,000-19 -2 1315 320 640 214 215 216 216 217 217 6,000-22 -8 1315 314 628 212 219 214 220 215 221 8,000-26 -15 1315 310 620 210 223 211 224 213 225 10,000-30 -22 1315 308 616 208 227 209 229 211 230 12,000-34 -29 1315 306 612 206 231 207 233 209 234 14,000-38 -36 1315 305 610 204 236 205 238 207 239 16,000-41 -42 1315 306 612 202 241 203 242 204 244 1750 18,000-45 -49 1312 282 564 193 237 195 240 196 242 20,000-50 -58 1185 256 512 183 232 185 235 187 238 22,000-54 -65 1065 231 462 172 226 175 230 178 233 24,000-58 -72 958 209 418 162 219 165 224 168 228 26,000-62 -80 853 188 376 150 211 155 217 158 222 28,000-66 -87 758 168 336 137 200 144 209 149 216 29,000-69 -92 711 159 318 130 193 138 204 143 212 5-28 Reference Material: Revision A: September 17, 2014

MAXIMUM CRUISE POWER ISA -20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL -1 30 1315 337 674 217 209 218 210 219 211 2,000-5 23 1315 328 656 215 213 216 214 217 215 4,000-9 16 1315 322 644 213 217 214 218 215 220 6,000-12 10 1315 317 634 211 221 212 223 213 224 8,000-16 3 1315 313 326 209 226 210 227 211 228 10,000-20 -4 1315 310 320 206 230 208 231 209 233 12,000-24 -11 1315 309 318 204 234 206 236 207 237 14,000-27 -17 1315 308 316 202 239 204 241 205 242 16,000-31 -24 1315 309 618 200 244 201 246 203 247 18,000-35 -31 1248 294 588 193 243 195 246 197 248 1750 20,000-39 -38 1224 266 532 183 238 186 241 188 244 22,000-43 -45 1106 241 482 173 232 176 236 178 239 24,000-48 -54 991 218 436 162 226 166 231 169 234 26,000-52 -62 885 196 392 151 217 156 224 159 229 28,000-56 -69 786 176 352 138 206 145 215 149 222 29,000-58 -72 739 166 332 131 199 139 211 144 219 Reference Material: Revision A: September 17, 2014 5-29

MAXIMUM CRUISE POWER ISA -10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 9 48 1315 339 678 216 212 217 213 218 214 2,000 5 41 1315 331 662 213 216 215 217 216 218 4,000 2 36 1315 323 646 211 220 213 221 214 222 6,000-2 28 1315 317 634 209 224 210 225 212 227 8,000-6 21 1315 314 628 207 228 208 230 210 231 10,000-10 14 1315 313 626 205 233 206 234 207 236 12,000-13 9 1315 311 622 203 237 204 239 205 240 14,000-17 1 1315 311 622 200 242 202 244 203 245 16,000-21 -6 1315 3111 622 198 247 200 249 201 250 1750 18,000-25 -13 1315 292 584 191 245 193 248 194 250 20,000-29 -20 1247 273 546 183 243 185 246 187 249 22,000-33 -27 1135 250 500 173 238 176 242 179 245 24,000-37 -35 1023 227 454 163 231 166 236 169 240 26,000-42 -44 913 204 408 152 223 156 230 160 235 28,000-46 -51 813 183 366 139 212 145 222 150 228 29,000-48 -54 765 173 346 132 205 140 217 145 225 5-30 Reference Material: Revision A: September 17, 2014

MAXIMUM CRUISE POWER ISA NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 19 66 1315 342 684 214 214 215 215 216 216 2,000 15 59 1315 334 668 212 218 213 219 214 220 4,000 12 54 1315 326 652 210 222 211 224 212 225 6,000 8 46 1315 321 642 208 227 209 228 210 229 8,000 4 39 1315 316 632 206 231 207 233 208 234 10,000 0 32 1315 313 626 203 236 205 237 206 239 12,000-3 27 1315 311 622 201 240 203 242 204 243 14,000-7 19 1315 311 622 199 245 200 247 202 248 16,000-11 12 1246 296 592 192 244 194 247 196 249 1750 18,000-15 5 1264 278 556 185 242 187 245 189 248 20,000-19 -2 1181 261 522 177 240 180 244 182 247 22,000-23 -9 1100 245 490 170 238 173 242 175 245 24,000-27 -17 1023 229 458 161 234 165 239 168 243 26,000-31 -24 936 211 422 152 228 156 235 160 240 28,000-36 -33 839 190 380 140 218 146 227 150 234 29,000-38 -36 789 180 360 133 211 140 222 145 230 Reference Material: Revision A: September 17, 2014 5-31

MAXIMUM CRUISE POWER ISA +10 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 29 84 1315 346 692 213 216 214 218 215 219 2,000 26 79 1315 338 676 211 221 212 222 213 223 4,000 22 72 1315 331 662 209 225 210 226 211 227 6,000 18 64 1315 324 648 206 229 208 231 209 232 8,000 14 57 1315 319 638 204 234 206 235 207 237 10,000 11 52 1315 316 632 202 238 203 240 205 241 12,000 7 45 1315 313 626 200 243 201 245 202 246 14,000 3 37 1263 301 602 194 244 196 246 197 248 1750 16,000-1 30 1291 283 566 187 242 189 245 191 247 18,000-5 23 1213 267 534 180 241 182 244 185 247 20,000-9 16 1117 249 498 171 237 174 241 177 244 22,000-13 9 1040 233 466 164 234 167 239 170 243 24,000-17 1 967 218 436 155 230 159 236 163 241 26,000-21 -6 897 204 408 147 225 152 233 155 238 28,000-26 -15 827 189 378 137 218 143 228 148 235 29,000-28 -18 792 182 364 131 213 139 225 144 233 5-32 Reference Material: Revision A: September 17, 2014

MAXIMUM CRUISE POWER ISA +20 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 39 102 1315 349 698 211 219 213 220 214 221 2,000 36 97 1315 341 682 209 223 211 224 212 225 4,000 32 90 1315 333 666 207 227 208 229 210 230 6,000 28 82 1315 327 654 205 232 206 233 208 234 8,000 24 75 1315 322 644 203 236 204 238 205 239 10,000 21 70 1315 318 636 200 241 202 242 203 244 12,000 17 63 1252 302 604 194 240 196 243 198 245 1750 14,000 13 55 1281 285 570 187 240 189 242 191 244 16,000 9 48 1206 268 536 180 238 183 241 185 244 18,000 5 41 1132 252 504 173 237 176 240 178 243 20,000 1 34 1063 237 474 166 235 169 239 172 242 22,000-3 27 996 223 446 159 232 162 237 165 241 24,000-7 19 917 208 416 150 226 162 233 158 238 26,000-12 10 845 194 388 140 220 154 228 150 235 28,000-16 3 780 180 360 130 211 146 223 142 231 29,000-18 0 747 174 348 123 205 133 220 138 229 Reference Material: Revision A: September 17, 2014 5-33

MAXIMUM CRUISE POWER ISA +30 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 50 122 1315 352 704 210 221 211 222 212 223 2,000 46 115 1315 343 686 208 225 209 227 210 228 4,000 42 108 1315 335 670 206 229 207 231 208 232 6,000 38 100 1315 328 656 204 234 205 235 206 237 8,000 34 93 1303 320 640 200 237 202 239 203 241 1750 10,000 30 86 1315 302 604 194 237 196 239 197 241 12,000 27 81 1263 285 570 187 236 189 239 191 241 14,000 23 73 1191 269 538 181 235 183 238 185 241 16,000 19 66 1123 254 508 174 234 176 237 179 240 18,000 15 59 1054 239 478 167 232 170 236 172 239 20,000 10 50 990 225 450 159 229 163 234 166 238 22,000 6 43 926 211 422 152 226 156 232 159 237 24,000 2 36 865 198 396 144 221 149 229 153 235 26,000-2 28 806 185 370 134 215 141 225 146 233 28,000-6 21 740 172 344 122 203 132 219 138 228 29,000-8 18 705 165 330 114 193 126 213 133 225 5-34 Reference Material: Revision A: September 17, 2014

MAXIMUM CRUISE POWER ISA +37 C NOTE: 1. IOAT, TORQUE AND BASED ON 8500 POUNDS 2. USE 1900 RPM WHEN TORQUE-LIMITED 3. USE 1750 RPM AT HIGHER ALTITUDE 4. OBSERVE VMO / M MO LIMITATION WHERE APPLICABLE PROP RPM PRESSURE TORQUE AIRSPEED KNOTS IOAT PER PER ALTITUDE 9500 LBS 8500 LBS 7500 LBS ENGINE ENGINE FEET C F FT-LBS LBS/HR LBS/HR CAS TAS CAS TAS CAS TAS 1900 SL 57 135 1315 353 706 209 222 211 224 212 225 2,000 53 127 1315 344 688 207 227 208 228 210 229 4,000 49 120 1315 336 672 205 231 206 233 207 234 6,000 45 113 1296 326 652 201 234 203 236 204 237 1750 8,000 41 106 1315 309 618 196 234 197 236 199 238 10,000 37 99 1270 291 584 189 234 191 236 193 238 12,000 33 91 1198 275 550 182 233 185 236 186 238 14,000 29 84 1130 259 518 176 232 178 235 180 238 16,000 25 77 1064 244 488 159 230 172 234 174 237 18,000 21 70 1000 229 458 162 228 165 232 168 236 20,000 17 63 939 216 432 154 225 158 231 162 235 22,000 13 55 878 202 404 147 221 151 228 155 234 24,000 9 48 821 190 380 138 216 144 225 148 232 26,000 5 41 763 177 354 128 208 136 220 141 229 28,000 1 34 704 165 330 115 193 127 213 134 224 29,000-1 30 674 159 318 103 176 121 208 129 222 Reference Material: Revision A: September 17, 2014 5-35

MAXIMUM CRUISE SPEEDS 30000 25000 PRESSURE ALTITUDE ~ FEET 20000 15000 10000 5000 ISA ISA -30 C ISA +30 C 0 140 160 180 200 220 240 260 TRUE AIRSPEED ~ KNOTS 5-36 Reference Material: Revision A: September 17, 2014

MAXIMUM CRUISE POWER 1400 TORQUE LIMIT ~ 1315 FT-LBS 1300 10,000 1200 12,000 1100 14,000 16,000 TORQUE SETTING ~ FT-LBS 1000 900 800 20,000 PRESSURE ALTITUDE ~ FT 22,000 24,000 18,000 700 600 ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C ISA +20 C ISA +30 C ISA +37 C 28,000 29,000 26,000 500 400-80 -70-60 -50-40 -30-20 -10 0 10 20 30 40 50 60 INDICATED OUTSIDE AIR TEMPERATURE ~ C Reference Material: Revision A: September 17, 2014 5-37

AT MAXIMUM CRUISE POWER ~ LBS / HR / ENGINE 360 350 340 330 320 310 300 290 280 270 260 250 240 230 220 210 200 190 180 170 160 150 140 ISA -30 C ISA -20 C ISA -10 C ISA ISA +10 C 28,000 29,000 26,000 24,000 ISA -30 C ISA -20 C ISA +20 C ISA -10 C 16,000 18,000 22,000 10,000 12,000 14,000 2,000 4,000 6,000 8,000 PRESSURE ALTITUDE ~ FT 20,000 ISA +30 C ISA ISA +37 C ISA +10 C SL 130-80 -70-60 -50-40 -30-20 -10 0 10 20 30 40 50 60 INDICATED OUTSIDE AIR TEMPERATURE ~ C 5-38 Reference Material: Revision A: September 17, 2014

C90 / C90-1 / C90A / C90B / C90SE MAXIMUM RANGE POWER SETTINGS AT 1750 RPM (LJ-527 and subsequent with PT6A-21 engines) Reference Material: Revision A: September 17, 2014 5-39

MAXIMUM RANGE POWER 1750 RPM ISA -30 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL -12 10 877 253 506 171 814 244 488 167 749 234 468 164 TAS TORQUE TAS 2,000-16 3 841 239 478 170 775 229 458 167 704 218 436 163 4,000-20 -4 801 224 448 170 729 213 426 165 653 201 402 161 6,000-24 -6 767 211 422 169 686 198 396 164 604 186 372 158 8,000-28 -18 750 201 402 170 667 188 376 165 577 174 348 158 10,000-32 -26 739 193 386 172 659 181 362 167 570 167 334 160 12,000-36 -33 732 186 372 174 653 174 348 169 565 160 320 162 14,000-40 -40 719 179 358 176 637 166 332 170 553 152 304 163 16,000-44 -47 706 172 344 177 623 158 316 171 539 144 288 164 18,000-48 -54 694 166 332 178 609 151 302 172 525 137 274 165 20,000-52 -62 686 162 324 180 599 146 292 173 515 131 262 166 22,000-56 -69 684 158 316 182 596 143 286 175 508 127 254 167 24,000-60 -76 687 157 314 185 597 140 280 178 506 124 248 170 26,000-63 -81 700 158 316 190 598 139 278 181 508 122 244 173 28,000-67 -89 701 157 314 192 610 140 280 185 514 121 242 176 29,000-69 -92 697 156 312 192 619 141 282 188 518 121 242 178 5-40 Reference Material: Revision A: September 17, 2014

MAXIMUM RANGE POWER 1750 RPM ISA -20 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL -2 28 905 259 518 175 845 250 500 172 789 241 482 169 TAS TORQUE TAS 2,000-6 21 866 244 488 175 803 234 468 171 746 226 452 168 4,000-10 14 847 233 466 176 777 223 446 172 712 213 426 168 6,000-14 7 823 222 444 177 750 211 422 173 683 201 402 168 8,000-18 0 800 211 422 178 725 200 400 173 655 189 378 168 10,000-22 -8 778 202 404 179 697 189 378 173 620 177 354 167 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 Reference Material: Revision A: September 17, 2014 5-41

MAXIMUM RANGE POWER 1750 RPM ISA -10 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL 8 46 864 255 510 173 801 245 490 170 745 236 472 167 TAS TORQUE TAS 2,000 4 39 869 247 494 177 803 237 474 173 745 228 456 170 4,000 0 32 866 237 474 180 799 227 454 176 736 218 436 172 6,000-4 25 850 227 454 181 774 216 432 177 707 205 410 173 8,000-8 18 833 217 434 183 759 206 412 179 685 195 390 174 10,000-12 10 813 209 418 184 740 198 396 180 666 186 372 175 12,000-16 3 794 200 400 185 724 189 378 181 649 178 356 176 14,000-20 -4 775 192 384 187 709 181 362 183 630 169 338 177 16,000-24 -11 759 185 370 188 697 175 350 185 616 162 324 178 18,000-27 -17 740 178 356 189 687 168 336 187 606 155 310 180 20,000-31 -24 721 171 342 189 674 162 324 188 598 150 300 183 22,000-35 -31 720 168 336 191 658 157 314 189 591 145 290 185 24,000-39 -38 725 167 334 195 641 151 302 189 583 141 282 187 26,000-43 -45 721 165 330 196 636 148 296 191 575 137 274 188 28,000-47 -53 726 165 330 199 645 148 296 195 563 133 266 189 29,000-49 -56 729 166 332 201 644 148 296 196 558 131 262 189 5-42 Reference Material: Revision A: September 17, 2014

MAXIMUM RANGE POWER 1750 RPM ISA WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL 18 64 879 260 520 176 788 246 492 171 717 235 470 166 TAS TORQUE TAS 2,000 14 57 867 249 498 179 776 235 470 173 707 224 448 168 4,000 10 50 859 239 478 181 773 226 452 176 704 215 430 171 6,000 6 43 846 229 458 183 773 218 436 179 706 207 414 175 8,000 2 36 826 218 436 184 767 209 418 181 702 199 398 178 10,000-2 28 805 208 416 185 750 200 400 183 692 191 382 180 12,000-6 21 785 199 398 186 729 190 380 184 669 181 362 180 14,000-10 14 775 193 386 189 709 183 366 185 655 174 348 182 16,000-13 9 772 189 378 191 693 176 352 186 638 167 334 183 18,000-17 1 767 183 366 194 679 169 338 187 621 159 318 185 20,000-21 -6 756 178 356 195 673 164 328 190 608 153 306 186 22,000-25 -13 732 171 342 195 670 160 320 193 594 147 294 187 24,000-29 -20 720 168 336 195 664 156 312 195 580 142 284 188 26,000-33 -27 733 169 338 200 651 152 304 195 569 137 274 189 28,000-37 -35 733 169 338 202 643 150 300 196 571 135 270 192 29,000-39 -38 740 170 340 204 651 151 302 199 574 135 270 194 Reference Material: Revision A: September 17, 2014 5-43

MAXIMUM RANGE POWER 1750 RPM ISA +10 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL 28 82 861 259 518 177 795 249 498 173 734 239 478 170 TAS TORQUE TAS 2,000 24 75 865 251 502 180 793 239 478 176 719 228 456 171 4,000 20 68 871 242 484 184 789 230 460 179 695 216 432 172 6,000 16 61 869 234 468 187 786 221 442 182 689 207 414 175 8,000 12 54 852 224 448 189 777 213 426 185 685 199 398 178 10,000 8 46 835 215 430 191 761 203 406 186 680 191 382 180 12,000 4 39 813 206 412 192 742 194 388 188 669 183 366 183 14,000 1 34 796 198 396 193 724 186 372 189 651 175 350 184 16,000-3 27 778 190 380 194 710 179 358 191 634 167 334 185 18,000-7 19 759 183 366 195 701 173 346 193 618 159 318 186 20,000-11 12 743 178 356 195 687 168 336 194 615 156 312 189 22,000-15 5 746 176 352 198 669 162 324 194 608 151 302 191 24,000-19 -2 744 174 348 201 657 157 314 195 603 147 294 194 26,000-23 -9 734 171 342 201 660 156 312 198 587 142 284 194 28,000-27 -17 758 175 350 208 659 154 308 200 573 137 274 194 29,000-29 -20 --- --- --- --- 654 153 306 200 571 136 272 195 5-44 Reference Material: Revision A: September 17, 2014

MAXIMUM RANGE POWER 1750 RPM ISA +20 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL 38 100 876 264 528 180 772 248 496 173 719 239 478 170 TAS TORQUE TAS 2,000 34 93 864 253 506 182 769 238 476 176 708 228 456 172 4,000 30 86 858 243 486 185 769 229 458 179 700 218 436 174 6,000 26 79 849 234 468 187 774 222 444 183 700 210 420 178 8,000 22 72 836 224 448 189 774 214 428 186 695 202 404 181 10,000 18 64 818 214 428 191 764 206 412 189 697 195 390 184 12,000 15 59 797 205 410 192 745 196 392 190 685 187 374 186 14,000 11 52 783 197 394 193 727 188 376 191 670 179 358 188 16,000 7 45 778 192 384 196 709 180 360 192 656 171 343 190 18,000 3 37 780 187 374 199 693 173 346 193 639 164 328 191 20,000-1 30 772 183 366 201 682 167 334 195 623 157 314 192 22,000-5 23 751 177 354 201 683 164 328 198 609 151 302 193 24,000-9 16 736 174 348 201 680 162 324 200 594 146 292 194 26,000-13 9 764 178 356 208 656 156 312 199 591 144 288 196 28,000-17 1 --- --- --- --- 666 157 314 203 592 142 284 200 29,000-18 0 --- --- --- --- 679 160 320 207 585 140 280 200 Reference Material: Revision A: September 17, 2014 5-45

MAXIMUM RANGE POWER 1750 RPM ISA +30 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL 48 118 872 265 530 181 793 252 504 176 724 241 482 172 TAS TORQUE TAS 2,000 44 111 888 258 516 186 793 244 488 180 702 229 458 173 4,000 40 104 894 250 590 190 793 235 470 183 681 218 436 174 6,000 36 97 884 241 482 192 789 226 452 186 677 209 418 177 8,000 32 90 865 230 460 194 783 218 436 189 679 202 404 181 10,000 29 84 850 221 442 196 767 208 416 191 682 195 390 184 12,000 25 77 833 212 424 198 749 199 398 192 674 187 374 187 14,000 21 70 813 204 408 199 735 191 382 194 659 179 358 189 16,000 17 63 789 195 390 199 726 185 370 196 643 171 342 190 18,000 13 55 767 187 374 199 719 178 356 199 628 164 328 191 20,000 9 48 747 180 360 199 705 172 344 200 619 158 316 193 22,000 5 41 747 178 356 201 685 166 332 200 621 154 308 197 24,000 1 34 769 180 360 208 666 160 320 199 617 150 300 200 26,000-3 27 791 183 366 214 667 158 316 202 601 145 290 200 28,000-6 21 --- --- --- --- 692 163 326 210 583 141 282 199 29,000 --- --- --- --- --- --- --- --- --- --- 581 140 280 200 5-46 Reference Material: Revision A: September 17, 2014

MAXIMUM RANGE POWER 1750 RPM ISA +37 C WEIGHT 9500 POUNDS 8500 POUNDS 7500 POUNDS PRESS ALTITUDE IOAT TORQUE TAS TORQUE FEET C F FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS FT-LBS LBS/HR LBS/HR KNOTS SL 55 131 858 265 530 181 789 253 506 177 726 242 484 174 TAS TORQUE TAS 2,000 51 124 861 256 512 185 782 243 486 180 710 231 462 175 4,000 47 117 873 249 498 189 793 236 472 184 704 222 444 178 6,000 43 109 876 241 482 193 799 229 458 188 700 214 428 181 8,000 40 104 861 231 462 195 793 220 440 191 701 206 412 184 10,000 36 97 843 221 442 196 785 212 424 194 705 200 400 188 12,000 32 90 814 211 422 197 769 203 406 196 691 191 382 190 14,000 28 82 785 201 402 196 751 195 390 197 676 183 366 192 16,000 24 75 768 194 388 197 729 186 372 198 663 176 352 194 18,000 20 68 756 187 374 198 701 177 354 197 651 169 338 196 20,000 16 61 764 185 370 202 680 170 340 197 643 163 326 198 22,000 12 54 776 184 368 207 670 165 330 198 625 156 312 199 24,000 8 46 --- --- --- --- 674 163 326 202 603 149 298 198 26,000 5 41 --- --- --- --- 691 164 328 208 584 143 286 198 28,000 0 32 --- --- --- --- --- --- --- --- 590 143 286 202 29,000-2 28 --- --- --- --- --- --- --- --- 599 144 288 205 Reference Material: Revision A: September 17, 2014 5-47

5-48 Reference Material: Revision A: September 17, 2014

Reference Material: Revision A: September 17, 2014 5-49

C90 / C90-1 / C90A / C90B / C90SE DESCENT AND LANDING DATA (LJ-527 and subsequent with PT6A-21 engines) 5-50 FAA-Approved: Revision A: September 17, 2014

Reference Material: Revision A: September 17, 2014 5-51

TIME,, & DISTANCE TO DESCEND DESCEND SPEED: 169 KNOTS ASSOCIATED CONDITIONS: POWER... LANDING GEAR... FLAPS... PROPELLER SPEED... AS REQUIRED TO DESCEND AT 1500 FT / MIN UP UP 1750 RPM EXAMPLE: INITIAL ALTITUDE... FINAL ALTITUDE... TIME TO DESCEND... TO DESCEND... DISTANCE TO DESCEND... 17,000 FT 5651 FT (11.3-3.8) = 7.5 MIN (47-17) = 30 LBS (37-12) = 25 NM 30000 25000 PRESSURE ALTITUDE ~ FEET 20000 15000 10000 5000 0 0 5 10 15 20 TIME TO DESCEND ~ MINUTES 0 20 40 60 USED TO DESCEND ~ POUNDS 80 0 10 20 30 40 50 60 70 80 DESCENT DISTANCE ~ NAUTICAL MILES 5-52 FAA-Approved: Revision A: September 17, 2014

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

5-54 FAA-Approved: Revision B: June 7, 2016