TCDS A28CE

Page No. 1 2 3 4 Rev. No. 14 11 10 14 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A28CE Revision 14 Textron Aviation 441 April 19, 2024 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 Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 441, Conquest (Normal Ca tegory), 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, MI L-T-2768E, or Phillips PFA 55MB must be blended into the aircraft fuel in concen trations not less than 0.060% by volume. For emergency use of aviation gasoline and fueling procedures, refer to FAA Approved Airplane Flight Manual (AFM). 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. A28CE 2 Rev. 14 I. Model 441 (cont’d) Propeller and Two three-bladed fu ll-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: Mc Cauley 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 V MO (Maximum operating) 245 knots (IAS) Sea level to 21,300 ft. M MO Above 21,300 ft. .55 mach V A (Maneuvering) 167 knots V FE (Flaps extended) 30° (Landing) 180 knots 20° (Approach) 200 knots 10° (Takeoff) 200 knots V MCA (Minimum control speed) Air 91 knots V LO (Landing gear operating) 180 knots V LE (Landing gear extended) 180 knots C.G. Range (Landing (+167.63 in.) to (+178.07 in.) at 6,800 lbs. (12% to 28.5% MAC) Gear Extended) (+173.35 in.) to (+178.07 in.) at 9,850 lbs. (21% to 28.5% MAC) Variation is linear between points Landing gear retracting moment (+1113 in.-lbs.) 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 lbs. Landing 9,360 lbs. Zero fuel 8,500 lbs. Ramp 9,925 lbs. 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 Li st for other seating arrangements Rev. 14 3 A28CE I. Model 441 (cont’d) Maximum Baggage Nose compartment: 250 lbs. Sta. + 32.0 350 lbs. Sta. + 71.0 Aft cabin: 400 lbs. Sta. +281.0 400 lbs. Sta. +301.0 100 lbs. Sta. +317.0 Fuel Quantity 3227 lbs. (481. 5 gal.) total in two wing tanks 1613.5 lbs. (240.75 gal.) each 3183 lbs. (475 gal.) usable total, 1591.5 lbs. (237.5 gal.) in each tank at sta. +181.9. Fuel weight based on 6.70 lbs./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 698 and 441-0001 through 441-0362 Certification Basis: Part 23 of the Federal Aviation Regulations (FAR) 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 FAR effective December 1, 1969, as amended by 36-1 through 36-6; SFAR 27, fuel venting. Findings of Equivalent Level of Safety (ELOS) 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 FAR. 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. A28CE 4 Rev. 14 Equipment: Pilot’s Operating Handbook (POH) and FAA Approved AFM required as follows: *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 as modified by CBQ-34-01, or Angle-of-Attack Indicator System - Cessna Dwg. 0800302 NOTE 1. Current weight and ba lance 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) Fuel 44.0 lbs. (6.5 gal.) at (sta.+186.7) (b) Oil 0.0 lbs. NOTE 2. The placards specified in the FAA Approved AFM 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: 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 S/N 441-0347 and On. --- END --- Airplane S/N Effectivity POH/AFM Part Numbe r* 441-0001 through 441-0172 D1561-14-13PH 441-0173 and On D1586-11-13PH Part Numbers Hours Air plane S/N Aileron Hinge Bracket 5824400-3 5824400-4 5824400-5 5824400-6 5824400-7 10,000 441-0001 through 441-0362