TCDS A22CE

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 74 44 65 70 44 70 56 65 70 51 44 70 52 56 70 49 Page No. 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Rev. No. 51 70 74 74 74 74 74 74 74 74 74 74 64 65 70 72 Page No. 33 34 35 36 37 38 39 40 Rev. No. 65 74 74 64 71 74 74 74 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A22CE Revision 74 Textron Aviation Inc. 500 550 S550 552 560 560XL December 8, 2025 TYPE CERTIFICATE DATA SHEET NO. A22CE This data sheet which is part of Type Certificate No. A22CE 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 500, Citation and Citation I, (Tra nsport Category), Approved September 9, 1971 The Model 500 Citation and Citation I are defined by Cessna Airplane Assembly Drawing Number 5500000. Engines Two Pratt & Whitney of Canada, Ltd. JT15D-1, JT15D-1A or JT15D-1B turbofans used in any combination (see Note 9 and Note 11). Fuel Jet A, Jet A-1, Jet B, JP-4, JP-5 or JP-8 . For required use of anti-icing additives and emergency use of aviation gasoline, refer to the FAA Approved Airplane Flight Manual. Engine Limits Static thrust, standard day, sea level: Takeoff (5 min.) 2200 lbs. Max. continuous 2090 lbs. Max. permissible engine rotor operational speeds: N 1 (Fan) JT15D-1 99 percent 15,840 r.p.m. N 1 (Fan) JT15D-1A 102.1 percent 16,336 r.p.m. N 1 (Fan) JT15D-1B 103.4 percent 16,540 r.p.m. N 2 (Gas gen.) 95 percent 31,120 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 700° C. Max. continuous 680° C. Starting 500º C. Transient (2 seconds) 720° C. A22CE Page 2 of 40 Rev. 74 I. Model 500 ( cont’d) Airspeed Limits (CAS) V MO (Maximum Operating) Sea level to 14,000 ft. 260 knots 14,000 ft. to 26,000 ft. (S/N 500-0001 thru 500-0349) 287 knots* 14,000 ft. to 28,000 ft. (S/N 500-0350 thru 500-0689) 275 knots* MMO Above 26,000 ft. (S/N 500-0001 thru 500-0349) 0.70 Mach Above 28,000 ft. (S/N 500-0350 thru 500-0689) 0.70 Mach VA (Sea level) 10,850 lbs. 178 knots (S/N 500-0001 thru 500-0070) 11,500 lbs. (S/N 500-0071 thru 500-0302) 182 knots 11,850 lbs. (S/N 500-0303 thru 500-0349) 185 knots (S/N 500-0350 thru 500-0689) 182 knots See AFM for variations with weight and altitude and optional configurations. VB (Speed for maximum gust intensity) 210 knots VFE (Flaps extended) 40° (Landing) 174 knots 15° (Takeoff and approach) 200 knots VMCA (Minimum control speed) Air Below stall speed for all weights VMCG (Minimum control speed) Ground 55 knots VLO (Landing gear operating) 174 knots VLE (Landing gear extended) 174 knots VSB (Speed brakes extended) A ny speed with or without flaps *See NOTE 7 for restricted VMO for optional fuel weight configuration. C.G. Range: (Landing Gear Extended) S/N 500-0001 thru 500-0070 (see NOTE 5). Forward Limits: Linear variation fro m 246.4 in. aft of datum (18% MAC) at 7,500 lbs. or 246.4 in. aft of datum (18% MAC) at 7,500 lbs. or less, to 249.2 in. aft of datum (21.5% MAC) at 10,850 lbs. Aft Limits: 255.9 in. aft of datum (30% MAC) at 10,850 lbs. or less. (Landing Gear Extended) S/N 500-0071 thru 500-0302 (see NOTE 5). Forward Limits: Linear variation fro m 246.4 in aft of datum (18% MAC) at 7,500 lbs. or 246.4 in aft of datum (18% MAC) at 7,500 lbs. or less, to 249.7 in aft of datum (22.6% MAC) at 11,500 lbs. Aft Limits: 255.9 in. aft of datum (30% MAC) at 11,500 lbs. or less. (Landing Gear Extended) S/N 500-0303 thru 500-0689. Forward Limits: Linear variation fro m 246.4 in aft of datum (18% MAC) at 7,500 lbs. or 246.4 in. aft of datum (18% MAC) at 7,500 lbs. or less, to 250.0 in. aft of datum (22.6% MAC) at 11,850 lbs. Aft Limits: 255.9 in. aft of datum (30% MAC) at 11,850 lbs. or less. Rev. 74 Page 3 of 40 A22CE I. Model 500 ( cont’d) Datum 94.0 in. forward of the front face of the forward pressure bulkhead. MAC 79.61 in. (L.E. of MAC at Sta. +232.04) NOTE: This is reference MAC for basic wing without tip. Leveling Means Seat Rails Maximum Weight S/N 500-0001 S/N 500-0071 S/N 500-0303 thru 500-0070 thru 500-0302 thru 500-0689 (see NOTE 5) (see NOTE 5) Takeoff 10,850 lbs. 11,500 lbs. 11,850 lbs. Landing 10,400 lbs. 11,000 lbs. 11,350 lbs. Zero fuel* 8,400 lbs. 8,400 lbs. 8,400 lbs. Ramp 11,000 lbs. 11,650 lbs. 12,000 lbs. *See NOTE 7 for optional zero fuel weights Minimum Crew For all flights: 2 persons (pilot and co-pilot) No. of Seats Up to 9 (2 Pilots, up to 7 Passengers) See NOTE 8 Maximum Baggage Nose compartment 350 lbs. (at Sta. + 74.0) Aft cabin 650 lbs. (at Sta. +286.3) Fuel Capacity (Gal.) Two wing tanks: Total 276 each; usable 268 each (S/N 500-0001 thru 0040) Total 277 each; usable 272 each (S/N 500-0041 thru 0213) Total 287 each; usable 282 each (S/N 500-0214 thru 500-0689) ARM = +256.0 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: JT15D-1 Engine Total 8.9 each; usable 5.0 each JT15D-1A Engine Total 8.6 each; usable 5.0 each ARM - +322.0 in. Maximum Operating 35,000 ft. (S/N 500-0001 thru 0213) (See NOTE 10) Altitude 41,000 ft. (S/N 500-0214 thru 500-0689) Control Surface Elevator Up 20°+1° Down 15° +1° Movements Elevator trim tab Up 7° +1°, -0° Down 18° +1°, -0° (S/N 500-0001 thru 500-0129) Up 10° +1°, -0° Down 19° +1°, -0° (S/N 500-0130 thru 500-0689) Rudder Right 22° +1° Left 22° +1° (perpendicular to hinge) Rudder trim tab Right 10° +1° Left 10° ±1° (perpendicular to hinge) Aileron Up 21° +1° Down 16° +1° Aileron trim tab Up 20° +1° Down 20° +1° Wing flap Down 0° to 40° +1° Speed brake - Upper Up 0° to 58° +2° See Airplane Maintenance Manual for rigging instructions A22CE Page 4 of 40 Rev. 74 I. Model 500 ( cont’d) Certification Basis (1) FAR Part 25 effective February 1, 1965, as amende d by Amendments 25-1 through 25-17, and the following: (a) Additions: FAR §§ 25.934, 25.1091(d)(2) as amended by Amendments 25-1 through 25-23; 25.1387 as amended by Amendments 25-1 through 25-30; 25.1385, 25.1303(a)(2) as amended by Amendments 25-1 through 25-38. (2) FAR Part 36 effect ive December 1, 1969. (3) Special Conditions as follows: (a) 25-25-CE-4, additional requirements for systems, airframe, flight and propulsion (see NOTE 28). (b) 25-674-SC, Non-Rechargeable Lithiu m Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. (4) Equivalent levels of safety as follows: (a) FAR 25.807(d), Emergency exits ditching. (b) FAR 25.1199(b)(c), Fire Bottl e Pressure Relief Valve. (c) FAR 25.1439(b)(2)(ii), Protective Eye Equipment. (d) FAR 25.815, Passenger Cabin Aisle Width. (e) FAR 25.1305(r), Use of N 1 for Power Presentation. (f) FAR 25.773(b)(2), Use of clear vision area of windshield. (g) FAR 25.1331(a)(1), Location of pressure gage to i ndicate adequate power to bank and pitch indicator. (5) Exemption Number 1435 granted. Model 500 exempt from requirements of FAR 25.1378(a) for location of position light on vertical tail. This exemption was deleted from certification basis by addition of 25.1387 as amended by Amendments 25-1 through 25-30. (6) FAR 25.801 ditching not complied with. (7) Compliance with ice protection has been de monstrated in accordance with FAR 25.1419. Serial No. Eligible 500-0001 and On II. Model 550, Citation II (Transport Category), Approved March 24, 1978 The Model 550 Citation II is defined by Ce ssna Airplane Assembly Drawing Number 6500000. Engines Two Pratt and Whitney Aircraft of Cana da, Ltd. (formerly United Aircraft of Canada, Ltd.) JT15D-4 turbofans or Pratt and Whitney Aircraft JT15D-4 turbofans. Fuel Jet A, Jet A-1, Jet B, JP-4, JP-5 or JP-8 . For required use of anti-icing additives and emergency use of aviation gasoline, refer to the FAA Approved Airplane Flight Manual. Engine Limits Static thrust, standard day, sea level: Takeoff (5 min.) 2500 lb. Max. continuous 2375 lb. Max. permissible engine rotor operating speeds: N 1 (Fan) JT15D-4 104 percent 16,540 r.p.m. N 2 (Gas Gen.) 96 percent 31,450 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 700° C. Max. continuous 680° C. Starting 500° C. Transient (2 seconds) 720° C. Rev. 74 Page 5 of 40 A22CE II. Model 550 (cont’d) Airspeed Limits (CAS) V MO (Maximum operating) Sea level to 14,000 ft. 260 knots 14,000 ft. to 28,000 ft. 275 knots Sea level to 30,500 ft. 260 knots MMO Above 30,500 ft. 0.70 Mach (S/N 550-0550 thru 550-0800) VA (Sea level) 13,300 ft. 186 knots See AFM for variations with weight and altitude and optional configurations VB (Speed for max. gust intensity) 210 knots VFE (Flaps extended) 40° (Landing) 174 knots 15° (Takeoff and approach) 200 knots VMCA (Minimum control speed) Air 75 knots VMCG (Minimum control speed) Ground 62 knots VLO (Landing gear operating) 174 knots (S/N 550-0001 thru 550-0626) VLO (Landing gear operating extend) 248 knots (S/N 550-0627 thru 550-0800) VLO (Landing gear operating retract) 198 knots (S/N 550-0627 thru 550-0800) VLE (Landing gear extended) 174 knots (S/N 550-0001 thru 550-0626) VLE (Landing gear extended) 260 knots (S/N 550-0627 thru 550-0800) VSB (Speed brakes extended Any speed with or without flaps See NOTE 7 for restricted VMO for optional fuel weight configuration, (S/N 550-0001 thru 550-0549) See NOTE 21 for increased VLO and VLE for S/N 550-0001 thru 550-0626. C.G. Range: (Landing Gear Extended) S/N 550-0001 thru 550-0626 Forward Limits: Linear variation fro m 276.1 in. aft of datum (18% MAC) at 8,540 lbs. or 276.1 in. aft of datum (18% MAC) at 8,540 lbs. or less, to 279.8 in. aft of datum (21.6% MAC) at 13,300 lbs. Aft Limits: 285.8 in. aft of datum (30% MAC) at 13,300 lbs. or less. (Landing Gear Extended) S/N 550-0627 thru 550-0800 Forward Limits: Linear variation fro m 276.1 in. aft of datum (18% MAC) at 8,540 lbs. or 276.1 in. aft of datum (18% MAC) at 8,540 lbs. or less, to 280.4 in. aft of datum (23.3% MAC) at 14.100 lbs. Aft Limits: 285.8 in. aft of datum (30% MAC) at 14,100 lbs. or less. Empty Wt. C.G. Range None Datum 94.0 in. forward of the front face of the forward pressure bulkhead. MAC 80.98 in. (L.E. of MAC at Sta. +261.56) NOTE: This is reference MAC for basic wing without tip. Leveling Means Seat Rails Maximum Weight S/N 550-0001 S/N 550-0627 thru 550-0626 thru 550-0800 Takeoff 13,300 lbs. 14,100 lbs. Landing 12,700 lbs. 13,500 lbs. Zero fuel* 9,500 lbs. 11,000 lbs. Ramp 13,500 lbs. 14,300 lbs. *See NOTE 7 for optional zero fuel weight (S/N 550-0001 thru 550-0549) A22CE Page 6 of 40 Rev. 74 II. Model 550 (cont’d) Minimum Crew For all flights: 2 persons (pilot and co-pilot) No. of Seats Up to 13 (2 Pilots, up to 11 Passengers) See NOTE 12 Maximum Baggage Nose compartment 350 lbs. at Sta. + 74.0 Aft cabin 400 lbs. at Sta. + 321.0 200 lbs. at Sta. + 338.0 Tailcone 200 lbs. at Sta. + 442.0 (S/N 550-0001 thru 550-0626) 200 lbs. at Sta. + 431.0 and 300 lbs. at Sta. + 462.0 (S/N 550-0627 thru 550-0800) Fuel Capacity (Gal.) Two wing ta nks: Total 376 each; usable 371 each ARM = +285.9 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: Total 9.0 each; usable 5.7 each ARM = +367.0 in. Maximum Operating 43,000 ft. Altitude Control Surface Elevator Up 20° +1° Down 15° +1° Movements Elevator trim tab - S/N 550-0001 thru S/N 550-0576 Up 15° +1°, -0° Down 17° +1°, -0° Elevator trim tab - S/N 550-0577 thru 550-0800 Up 17° +1°, -0° Down 15° +1°, -0° Rudder Right 22° +1° Left 22° +1° (perpendicular to hinge) Rudder trim tab Right 10° +1° Left 10° +1° (perpendicular to hinge) Aileron Up 19° +1° Down 15° +1° Aileron trim tab Up 20° +1° Down 20° +1° Wing flap Down 0° to 40° +1° Speed brake - Upper Up 0° to 57° +3° See Airplane Maintenance Manual for rigging instructions Certification Basis (S/N 550-001 thru 550-0505 and 550-0550 thru 550-0800) (1) FAR Part 25 effective February 1, 1965, as amende d by Amendments 25-1 through 25-17, and the following: (a) Additions: FAR §§ 25.934 and 25.1091(d)(2) as amended by Ame ndments 25-1 through 25-23; 25.1401 as amended by Amendments 25-1 through 25-27; 25.1387 as amended by Amendments 25-1 through 25-30; 25.1303(a)(2) and 25.1385(c) as amended by Amendments 25-1 through 25-38. (b) Addition for the Bendix EFS-10, Sperry EDZ-600, Sp erry EDZ-601, and Sperry EDZ-603 Electronic Flight Instrument Systems only: FAR §§ 25.1301, 25.1303(b), 25.1322 as amended by Amendments 25-1 through 25-38; 25.1309, 25.1321(a)(b)(d)(e), 25.1331, 25.1333, 25.1335 as amended by Amendments 25-1 through 25-41. (2) FAR Part 36 effect ive December 1, 1969. (3) SFAR 27, as amended by Amendmen ts 27-1 and 27-2, fuel venting. (4) Special Conditions as follows: (a) 25-25-CE-4, additional requirements for systems, airframe, flight and propulsion (see NOTE 28). (b) 25-674-SC, Non-Rechargeable Lithiu m Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Rev. 74 Page 7 of 40 A22CE II. Model 550 (cont’d) Certification Basis (S/N 550-001 thru 550-0505 and 550-0550 thru 550-0800) (cont’d) (5) Equivalent levels of safety as follows: (a) FAR 25.807(d), Emergency exits ditching. (b) FAR 25.1199(b)(c), Fire Bottl e Pressure Relief Valve. (c) FAR 25.1439(b)(2)(ii), Protective Eye Equipment. (d) FAR 25.815, Passenger Cabin Aisle Width. (e) FAR 25.1305(r), Use of N 1 for Power Presentation. (f) FAR 25.773(b)(2), Use of clear vision area of windshield. (g) FAR 25.1331(a)(1), Location of pressure gage to i ndicate adequate power to bank and pitch indicator. (h) FAR 25.1549(a)(b), N 2 Digital Indicator Markings. (i) FAR 25.813(e), Frangible door for S/N 550-0550 thru 550-0800. (6) FAR 25.801 ditching not complied with. (7) Compliance with ice protection has been de monstrated in accordance with FAR 25.1419. Serial No. Eligible 550-0001 thru 550- 0505 and 550-0550 thru 550-0800 (See NOTE 19) III. Model S550, Citation S/II (Transpo rt Category), Approved August 15, 1984 The Model S550 Citation S/II is defined by Ce ssna Airplane Assembly Drawing Number 6500000. Engines Two Pratt and Whitney Canada, Inc. (formerly United Aircraft of Canada Ltd.) JT15D-4B turbofans. Fuel Jet A, Jet A-1, Jet B, JP-4, JP-5 or JP-8 . For required use of anti-icing additives and emergency use of aviation gasoline, refer to the FAA Approved Airplane Flight Manual. Engine Limits Static thrust, standard day, sea level: Takeoff (5 min.) 2500 lbs. Max. continuous 2375 lbs. Max. permissible engine rotor operating speeds: N 1 (Fan) 106 percent 16,854 r.p.m. N 2 (Gas Gen.) 97 percent 31,777 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 710° C. Max. continuous 690° C. Starting 500° C. Transient (2 seconds) 730° C. Airspeed Limits V MO (Maximum operating) Sea level to 8,000 ft. 260 KCAS (261 KIAS) 8,000 ft. to 29,315 ft. 275 KCAS (276 KIAS) MMO Above 29,315 ft. 0.72 Mach (0.72 MIAS) VA (Sea level) 14,700 lb. 192 KCAS (192 KIAS) See AFM for variations with weight and altitude VFE (Flaps extended) 35° (Landing) 174 KCAS (172 KIAS) 20° (Takeoff and approach) 200 KCAS (200 KIAS) VMCA (Minimum control speed) Air 84 KCAS (83 KIAS) VMCG (Minimum control speed) Ground 75 KCAS (73 KIAS) A22CE Page 8 of 40 Rev. 74 III. Model S550 ( cont’d) Airspeed Limits (cont’d) VLO (Landing gear operating) 174 KCAS (172 KIAS) VLE (Landing gear extended) 174 KCAS (172 KIAS) VSB (Speed brakes extended Any speed with or without flaps See NOTE 21 for increased VLO and VLE. Tire Limit Maximum ground speed 165 knots C.G. Range: (Landing Gear Extended) S/N S550-0001 thru S550-0085 Forward Limits: Linear variation fro m 273.7 in. aft of datum (15% MAC) at 9,600 lbs. or 273.1 in. aft of datum (15% MAC) at 9,600 lbs. or less, to 277.7 in. aft of datum (19.9% MAC) at 14,700 lbs. Aft Limits: 284.2 in. aft of datum (28% MAC) at 14,700 lbs. or less. (Landing Gear Extended) S/N S550-0086 thru S550-0160 Forward Limits: Linear variation fro m 273.7 in. aft of datum (15% MAC) at 9,600 lbs. or 273.1 in. aft of datum (15% MAC) at 9,600 lbs. or less, to 278.0 in. aft of datum (20.3% MAC) at 15,100 lbs. Aft Limits: 284.2 in. aft of datum (28% MAC) at 15,100 lbs. or less. Empty Wt. C.G. Range None Datum 94.0 in. forward of the front face of the forward pressure bulkhead. MAC 80.98 in. (L.E. of MAC at Sta. +261.56) NOTE: This is reference MAC for basic wing without tip. Leveling Means Seat Rails Maximum Weight S/N S550-0001 S/N S550-0086 thru S550-0085 thru S550-0160 Takeoff 14,700 lbs. 15,100 lbs. Landing 14,000 lbs. 14,400 lbs. Zero fuel 11,000 lbs. 11,200 lbs. Ramp 14,900 lbs. 15,300 lbs. Minimum Crew For all flights: 2 persons (pilot and co-pilot) No. of Seats Up to 13 (2 Pilots, up to 11 Passengers) Maximum Baggage Nose Compartme nt 350 lbs. (at Sta. + 74.0) Aft Cabin 400 lbs. (at Sta. +321.0) 200 lbs. (at Sta. +338.0) Tailcone 200 lbs. (at Sta. +442.0) 300 lbs. (at Sta. +414.0) Fuel Capacity (Gal.) Two wing tanks: Total 437 each; usable 431.5 each ARM = +282.7 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: Total 9.0 each; usable 5.7 each ARM = +367.0 in. Surface Anti-Ice Fluid Capacity: 65.5 lb., ARM = +62.9 in. Surface anti-ice fluids must meet British Deicing Fluid Specification DTD 406B (NATO Symbol S-745). Fluids meeting this specification as follows: Canyon Industries AL-5, Aero Shell Compound 07, and BP Aero Deicing 2. Rev. 74 Page 9 of 40 A22CE III. Model S550 ( cont’d) Windshield Anti-Ice Fluid Capacity: 3.4 lbs., AR M = +91.4 in.; TT-I-735 Isopropyl Alcohol Approved Maximum Operating 43,000 ft. Altitude Control Surface Elevator Up 20° +1° Down 15° +1° Movements Elevator trim tab Up 5° +1°, -0° Down 17° +1°, -0° Rudder Right 22° +1° Left 22° +1° (perpendicular to hinge) Rudder trim tab Right 10° +1° Left 10° +1° (perpendicular to hinge) Aileron Up 19° +1° Down 15° +1° Aileron trim tab Up 20° +1° Down 20° +1° Wing flap Down 0° to 35° +1° Speed brake - Upper Up 0° to 58° +2° See Airplane Maintenance Manual for rigging instructions Certification Basis (1) FAR Part 25 effective February 1, 1965, as amende d by Amendments 25-1 through 25-17, and the following. (a) Additions: FAR §§ 25.251(e), 25.934, 25.1091(d)(2) as ame nded by Amendments 25-1 through 25-23; 25.1401 as amended by Amendments 25-1 through 25-27; 25.1387 as amended by Amendments 25-1 through 25-30; 25.787, 25.789, 25.791, 25.853, 25.855, 25.857, 25.1359 as amended by Amendments 25-1 through 25-32; 25.1303(a)(2), 25.1385(c) as amended by Amendments 25-1 through 25-38. (b) Addition for the Bendix EFS-10, Sperry EDZ-600, Sperry EDZ-601, and Sperry EDZ-603 Electronic Flight Instrument Systems only: FAR §§ 25.1301, 25.1303(b), 25.1322 as amended by Amendments 25-1 through 25-38; 25.1309, 25.1321(a)(b)(d)(e), 25.1331, 25.1333, 25.1335 as amended by Amendments 25-1 through 25-41. (2) FAR Part 36 effective Dece mber 1, 1969, as amended by Amendments 36-1 through 36-12. (3) SFAR 27, as amended by Amendmen ts 27-1 and 27-2, fuel venting. (4) Special Conditions as follows: (a) 25-25-CE-4, additional requirements for systems, airframe, flight and propulsion (see NOTE 28). (b) 25-674-SC, Non-Rechargeable Lithiu m Batteries, effective to design changes applied for after May 16, 2017. See the applicability section of this special condition for more information on which design changes must meet it. (5) Equivalent levels of safety as follows: (a) FAR 25.807(d), Emergency exits ditching. (b) FAR 25.1199(b)(c), Fire Bottl e Pressure Relief Valve. (c) FAR 25.1439(b)(2)(ii), Protective Eye Equipment. (d) FAR 25.815, Passenger Cabin Aisle Width. (e) FAR 25.1305(r), Use of N 1 for Power Presentation. (f) FAR 25.773(b)(2), Use of clear vision area of windshield. (g) FAR 25.1331(a)(1), Location of pressure gage to i ndicate adequate power to bank and pitch indicator. (h) FAR 25.1549(a)(b), N 2 Digital Indicator Markings. (i) FAR 25.813(e), Frangible door. (6) FAR 25.801 ditching not complied with. (7) Compliance with ice protection has been de monstrated in accordance with FAR 25.1419. Serial No. Eligible S550-0001 thru S550-0160 A22CE Page 10 of 40 Rev. 74 IV. Model 552, Navy T-47A (Transport Category), Approved November 21, 1984 Model 552 (Navy T-47A) is defined by Cessna Airplane Assembly Drawing Number 6400001. Engines Two Pratt and Whitney Canada, Inc. (formerly United Aircraft of Canada, Ltd.) JT15D-5 turbofans. Fuel Jet A, Jet A-1, Jet B, JP-4, JP-5 or JP-8. For required use of anti-icing additives, refer to the FAA Approved Airplane Flight Manual. Engine Limits Static thrust, standard day, sea level: Takeoff (5 min.) 2900 lbs. Max. continuous 2900 lbs. Max. permissible engine rotor operating speeds: N 1 (Fan) 104 percent 16,540 r.p.m. N 2 (Gas Gen.) 96 percent 31,450 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 700° C. Max. continuous 680° C. Starting 550° C. Transient (2 seconds) 720° C. Airspeed Limits V MO (Maximum operating) Sea level 355 KCAS (358 KIAS) 27,425 ft. 299 KCAS (300 KIAS) Linear variation between altitudes MMO Above 27,425 ft. 0.75 Mach (0.755 MIAS) VA (Sea level) 15,500 lb. 215 KCAS (216 KIAS) See AFM for variations with weight and altitude and optional configurations. VFE (Flaps extended) 35° (Landing) 174 KCAS (173 KIAS) 20° (Takeoff and approach) 200 KCAS (201 KIAS) VMCA (Minimum control speed) Air 85 KCAS ( 84 KIAS) VMCG (Minimum control speed) Ground 82 KCAS ( 78 KIAS) VLO (Landing gear operating) 174 KCAS (173 KIAS) VLE (Landing gear extended) 174 KCAS (173 KIAS) VSB (Speed brakes extended Any speed with or without flaps Tire Limit Maximum ground speed 165 knots C.G. Range (Landing Gear Extended) Forward Limits: Linear variation fro m 274.4 in. aft of datum (15.82% MAC) at 9,400 lbs. or 274.4 in. aft of datum (15.82% MAC) at 9,400 lbs. or less, to 279.1 in. aft of datum (21.69% MAC) at 15,500 lbs. Aft Limits: 282.6 in. aft of datum (26% MAC) at 15,500 lbs. or less. Empty Wt. C.G. Range None Datum 94.0 in. forward of the front face of the forward pressure bulkhead. MAC 80.98 in. (L.E. of MAC at Sta. +261.56) NOTE: This is reference MAC for basic wing without cuff Leveling Means Seat Rails Rev. 74 Page 11 of 40 A22CE IV. Model 552 (cont’d) Maximum Weight Takeoff 15,500 lbs. Landing 14,300 lbs. Zero fuel 10,500 lbs. Ramp 15,679 lbs. Minimum Crew For all flights: 2 Pilots No. of Seats Up to 6 (2 Pilots, up to 4 Passengers) Maximum Baggage None Fuel Capacity (Gal.) Two wing ta nks: Total 414 each; usable 412 each ARM = +282.7 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: Total 8.1 each; usable 4.8 each ARM +367.0 in. Fluid Anti-Ice System Capacity : 65.5 lbs. ARM 86.3 in. (Airframe) Surface anti-ice fluids must meet British Deicing Fluid Specification DTD 406B (NATO Symbol S-745). Fluids meeting this specification as follows: Canyon Industries AL-5, Aero Shell Compound 07, and BP Aero Deicing 2 Windshield Anti-Ice Capacity : 3.4 lbs. ARM 91.4 in. Fluid Approved Anti-Ice Fluid: TT-I-735 Isopropyl Alcohol Maximum Operating 43,000 ft. Altitude Control Surface Elevator Up 20° +1° Down 15° +1° Movements Elevator trim tab Up 5° +1°, -0° Down 17° +1°, -0° Rudder Right 22° +1° Left 22° +1° (perpendicular to hinge) Rudder trim tab Right 10° +1° Left 10° +1° (perpendicular to hinge) Aileron Up 16° +2°, -0° Down 14° +2°, -0° Wing flap Down 0° to 35° +1° Speed brake - Upper Up 0° to 58° +2° See Airplane Maintenance Manual for rigging instructions Certification Basis