TYPE CERTIFICATE DATA SHEET NO. A28CE
CESSNA CONQUEST II · Weight And Balance
Overview
This document is the Type Certificate Data Sheet for the Cessna 441 Conquest, issued by the Federal Aviation Administration. It outlines the conditions and limitations under which the Cessna 441 meets airworthiness requirements. The document provides essential information for pilots and maintenance personnel, including engine specifications, weight and balance data, airspeed limits, and control surface movements. It serves as a reference for understanding the operational capabilities and limitations of the aircraft, ensuring safe and efficient flight operations.
- Maximum takeoff weight: 9,850 lb
- Maximum landing weight: 9,360 lb
- Total fuel capacity: 3,227 lb (481.5 gal)
- VMO: 245 knots up to 21,300 ft
- C.G. range for landing gear extended: +173.35 in. to +178.07 in.
Document
Source
Originally published by www.conquestowners.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Weight And Balance
- Year
- 2003
- Pages
- 4
- File size
- 145 KB
- Publisher
- www.conquestowners.org
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 635.5
- Propeller
- Hartzell
- Engine model
- TPE331-8-401S
- Max speed (kt)
- 245
- Fuel capacity (gal)
- 481.5
- Service ceiling (ft)
- 35,000
- Max takeoff weight (lb)
- 9,850
V-speeds
- VA
- 167
- VFE
- 200
Weight & balance
- Max ramp weight (lb)
- 9,925
- Baggage allowance (lb)
- 250
- Max landing weight (lb)
- 9,360
- Max takeoff weight (lb)
- 9,850
Most owners only have the POH. Here's the essential set for the CESSNA CONQUEST II.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
More CESSNA CONQUEST IImanuals & documents
See all 13 →- Emergency Procedures for the CESSNA CONQUEST IIEmergency Procedures
- General Aviation Engine Mount Application GuideAvionics Manual
- Conquest SERVICE BULLETIN CQB-34-01Maintenance Manual
- ATSB Transport Safety Report: Loss of control and collision with terrain involving Cessna 441, VH-XMJOther Documents
- ATSB Transport Safety Report: Loss of control and collision with terrain involving Cessna 441, VH-XMJOther Documents
- AAIB Bulletin: 1/2020 EI-DMG EW/G2019/06/19Other Documents
- CASA Ruling 1/2014Maintenance Manual
- STC INDEXSystems Description
- Airworthiness Directive Schedule Aeroplanes Cessna 441 SeriesAirworthiness Directives
- Integrated Flight Deck & RVSM Retrofit for Cessna 441 Conquest II AircraftSystems Description
- Customer Case StudyOther Documents
- Type Acceptance Report TAR 1/21B/17 - Cessna 441Type Certificate
In this document
Engine Specifications
The Cessna 441 is powered by two Garrett TPE331-8 series turboprop engines. The static sea level ratings for takeoff and maximum continuous power are both 635.5 shaft horsepower at 100% gas generator speed, with a maximum exhaust gas temperature of 450°C. The engines can be interchanged in any combination.
Weight and Balance
The maximum takeoff weight for the Cessna 441 is 9,850 lb, with a maximum landing weight of 9,360 lb and a zero fuel weight of 8,500 lb. The center of gravity (C.G.) range for landing gear extended is from +173.35 inches to +178.07 inches at 9,850 lb. The aircraft has a certified empty weight that includes undrainable oil and unusable fuel.
Fuel Capacity
The total fuel capacity of the Cessna 441 is 3,227 lb (481.5 gallons) distributed in two wing tanks, with 1,613.5 lb (240.75 gallons) in each tank. The usable fuel is 3,183 lb (475 gallons), with 1,591.5 lb (237.5 gallons) available in each tank at the specified station.
Airspeed Limits
The maximum operating airspeed (VMO) is 245 knots from sea level to 21,300 feet, and the maximum Mach operating speed (MMO) above 21,300 feet is .55 Mach. Other important airspeed limits include a maneuvering speed (VA) of 167 knots and a landing gear operating speed (VLO) of 180 knots.
Control Surface Movements
The Cessna 441 features specific control surface movement limits: the elevator can move up to 25° and down to 15°, while the ailerons have the same limits. The rudder can deflect up to 32° in either direction. These limits are crucial for understanding the aircraft's handling characteristics.
Safety notes
- Ensure the current weight and balance report is available for each flight.
- Follow the specified fuel and oil capacities to maintain safe operations.
Full document text
DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A28CE Revision 12 | CESSNA 441 September 22, 2003 | TYPE CERTIFICATE DATA SHEET NO. A28CE This data sheet which is part of Type Certificate No. A28CE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Cessna Aircraft Company P. O. Box 7704 Wichita, Kansas 67277 I - Model 441, Conquest, (Normal Category), Approved August 19, 1977 Engines Two Garrett Turbine Engine Company TPE331-8 Series Turboprops: S/N 441-0001 through 441-0339 TPE331-8-401S TPE331-8-402S TPE331-8-403S TPE331-8-404S Engines may be interchanged in any combination. S/N 441-0340 and on TPE331-8-406S Fuel Aviation turbine fuel ASTM D-1655, Jet A, Jet A-1 or Jet B; MIL-T-5624, JP-4 or Jp-5. Anti-icing additive per MIL-I-27686D, MIL-T-2768E, or Phillips PFA 55MB must be blended into the aircraft fuel in concentrations not less than 0.060% by volume. For emergency use of aviation gasoline and fueling procedures, refer to FAA Approved Airplane Flight Manual. Engine Limits Static sea level ratings Shaft Horse Power Gas Gen. Speed (% R.P.M.) Indicated Torque (Ft.-lbs.) Prop Shaft Speed (R.P.M.) Exhaust Gas Temp. (Deg. C) Takeoff (5 min) Static 635.5 100 1669 2000 450° Max. Continuous 635.5 100 1669 2000 450° Starting Limit -- -- -- -- 770° Note: During manual mode operation, refer to OAT gage and AFM for EGT limits. Page No. 1 2 3 4 Rev. No. 12 11 10 12 A28CE Page 2 of 4 Rev. 12 Propeller and Two three-bladed full-feathering, reversible propellers: Propeller Limits 1. Manufacturer: Hartzell Compatible Engines: TPE331-8-401S or 402S Hub: Hartzell HC-B3TN-5 Blade: Hartzell T10178B-11 Diameter: not over 90.0 inches, not under 88.5 inches; no further reduction permitted Pitch at 30-inch station: Start locks + 2.0° Flight idle +10.0° Feathered +87.4° Reverse - 8.0° 2. Manufacturer: McCauley Accessory Division Compatible Engines: TPE331-8-403S, 404S, or 406S Hub: McCauley 3GFR34C601 Blade: McCauley 93JA-3 Diameter: Not over 90.0 inches, not under 88.5 inches; no further reduction permitted Pitch at 30-inch station: Start locks + 2.0° Flight idle + 8.5° Feathered +85.3° Reverse - 8.0° Note: Either two McCauley or two Hartzell Propellers are required. Airspeed Limits VMO (Maximum operating) 245 knots (IAS) Sea level to 21,300 ft. MMO Above 21,300 ft. .55 mach VA (Maneuvering) 167 knots VFE (Flaps extended) 30° (Landing) 180 knots 20° (Approach) 200 knots 10° (Takeoff) 200 knots VMCA (Minimum control speed) Air 91 knots VLO (Landing gear operating) 180 knots VLE (Landing gear extended) 180 knots C.G. Range (Landing (+167.63 in.) to (+178.07 in.) at 6,800 lb. (12% to 28.5% MAC) Gear Extended) (+173.35 in.) to (+178.07 in.) at 9,850 lb. (21% to 28.5% MAC) Variation is linear between points Landing gear retracting moment (+1113 in.-lb.) Empty Wt. C.G. Range None Datum 100.0 in. forward of the front face of the forward pressure bulkhead which is sta. +100.0 Leveling Means Seat rails over main spar (lateral) Leveling screws, R.H. fuselage (longitudinal) Maximum Weight Takeoff 9,850 lb. Landing 9,360 lb. Zero fuel 8,500 lb. Ramp 9,925 lb. No. of Seats 1 through 11 (2 at +137.0, 2 at +178.0, 2 at +209.0, 2 at +249.0, 1 at +285.0, 2 at +296.0) See Manufacturer's Equipment List for other seating arrangements Rev. 12 Page 3 of 4 A28CE Maximum Baggage Nose compartment: 250 lb. Sta. + 32.0 350 lb. Sta. + 71.0 Aft cabin: 400 lb. Sta. +281.0 400 lb. Sta. +301.0 100 lb. Sta. +317.0 Fuel Quantity 3227 lb. (481.5 gal.) total in two wing tanks 1613.5 lb. (240.75 gal.) each 3183 lb. (475 gal.) usable total, 1591.5 lb. (237.5 gal.) in each tank at sta. +181.9. Fuel weight based on 6.70 lb./gal. See NOTE 1 for data on unusable fuel Oil Capacity 3.75 gal. total, 3.75 gal. usable (1.88 gal. in ea. engine mounted tank at sta. +116.0) See NOTE 1 for undrainable oil Maximum Operating 33,000 ft. S/N 441-0001 through -0172 (See NOTE 4) Altitude 35,000 ft. S/N 441-0173 and on Control Surface Elevator (horn faired) Up 25° Down 15° Movements Elevator trim tabs Up 4° Down 9° Rudder (perpendicular to Right 32° Left 32° hinge 0° faired with fin) Rudder trim tab Right 11° Left 16° (perpendicular to hinge) Aileron Up 25° Down 15° Aileron trim tab Up 19° from Down 19° from neutral neutral Wing flap (inboard) Down 0° to 30° Wing flap (outboard) Down 0° to 20° Serial Nos. Eligible Serial 698 and 441-0001 through 441-0362 Certification Basis Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 through 23-14 except FAR 23.1385(c) as amended through 23-21; plus Special Conditions 23-74-CE-9; Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by 36-1 through 36-6; SFAR 27, fuel venting. Findings of equivalent level of safety were made for FAR 23.1189(a), 23.1545, and 23.1583(a). In addition to the above certification basis, compliance with ice protection has been demonstrated in accordance with FAR 23.1419 of Amendment 23-14 effective December 20, 1973. S/N 441-0173 and on In addition to the above, certification basis compliance with FAR 25.1447(c)(2) as amended through 25-41 effective September 1, 1977, is required. Application for Type Certificate dated October 30, 1974. Type Certificate No. A28CE issued August 19, 1977, obtained by the manufacturer under Delegation Option Procedures. Production Basis Production Certificate No. 312 issued and Delegation Option Manufacturer No. CE-3 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Effective February 15, 1985, and on, Production Certificate No. 4 is applicable to all spares production. See NOTE 6 for specific effectivity of P.C. 4 on new airplane serials.
Show full textShow less
A28CE Page 4 of 4 Rev. 12 Equipment Pilot’s Operating Handbook and FAA Approved Airplane Flight Manual required as follows: Airplane S/N Effectivity *POH/AFM Part Number 441-0001 through 441-0172 D1561-14-13PH 441-0173 and On D1586-11-13PH *Note: Or later approved revisions. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following item of equipment is required: Stall Warning Indicator - Cessna Dwg. 5818008, or Angle-of-Attack Indicator System - Cessna Dwg. 0800302 NOTE 1. Current weight and balance report together with list of equipment included in certificated empty weight and loading instructions when necessary must be provided for each aircraft at the time of original certification. The certified empty weight and corresponding center of gravity location must include undrainable oil (not included in oil capacity) and unusable fuel as follows: (a) Unusable fuel 44.0 lb. (6.5 gal.) at (sta.+186.7). (b) Oil 0.0 NOTE 2. The placards specified in the FAA Approved Airplane Flight Manual must be displayed. NOTE 3. Service information: The airplane maintenance manual contains structural retirement lives, which may not be changed without FAA Engineering approval for the following components: Part Numbers Hours Airplane S/N Aileron Hinge Bracket 5824400-3 5824400-4 5824400-5 5824400-6 5824400-7 10,000 441-0001 through 441-0362 NOTE 4. 35,000 ft. S/N 441-0001 through -0172 when modified by SK441-36. NOTE 5. Model 441 aircraft in compliance with Cessna Drawing 5700018 are eligible for certification in the Netherlands. NOTE 6. Production Certificate No. 4 effective at Serial 441-0347 and on. ...END...