# TCDS A22CE: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 74 - Revised: December 8, 2025 - Product: Aircraft, Large Airplane - Certification basis: Part 25 - Registered aircraft: 1,979, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/00/6d/006dc82b5d0c0be00ed8888b0cda08de5f1874ed5f9b3e496ff480e843476de9 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID132119292720251209201014.0001 - Page: https://openairdocs.org/tcds/A22CE ## Models (6) As the data sheet lists them. - S550 (Citation S/II) - 550 (Bravo; Citation II) - 552 ((Navy T-47A)) - 500 (Citation 500; Citation; Citation I) - 560XL (Excel) - 560 (Citation V; Ultra) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text 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 (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; 25.1303, 25.1385(c) as amended by Amendments 25-1 through 25-38; 25.255 as amended by Amendments 25-1 through 25-42; 25.1001 as amended by Amendments 25-1 thru 25-57. (b) Addition for ailer on boost system only: FAR 25.671 and 25.672 as amended by Amendments 25-1 through 25-23. (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. A22CE Page 12 of 40 Rev. 74 IV. Model 552 (cont’d) Certification Basis (cont’d) (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 25.1549(a)(b), N 2 Digital Indicator Markings. (6) Exemption Number NM-105 granted. Model 552 exempt from requirements of FAR 25.1303 and 25.1321 for required instruments, instrument panel arrangement and visibility of instruments. (7) FAR 25.801 ditching not complied with. (8) Compliance with ice protection has been de monstrated in accordance with FAR 25.1419. Serial No. Eligible 552-0001 thru 552-0015 (See NOTE 23) V. Model 560, Citation V and Citation Ultra (Transport Category), Approved December 9, 1988 Model 560 Citation V and Citation U ltra are defined by Cessna Airplane Assembly Drawing Number 6500560. Engines S/N 560-0001 thru 560-0259 Two Pratt & Whitney of Canada, Inc. JT15D-5A turbofans S/N 560-0260 thru 560-0538 Two Pratt & Whitney of Canada, Inc. JT15D-5D 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: JT15D-5A JT15D-5D Takeoff (5 min.) 2900 3045 Max. continuous 2900 3045 Max. permissible engine rotor operating speeds: JT15D-5A JT15D-5D N 1 (Fan) 104% 100% 16540 r.p.m. 16860 rpm N 2 (Gas Gen.) 96% 97% 31450 rpm 31777 rpm Max. permissible interturbine gas temperatures: JT15D-5A JT15D-5D Takeoff 700° C 720 o C Max. continuous 680° C 700 o C Starting 550º C 550º C Transient (2 seconds) 720° C 740° C Rev. 74 Page 13 of 40 A22CE V. Model 560 (cont’d) Airspeed Limits V MO (Maximum operating) Sea level to 8000 ft. 260 KCAS (261 KIAS) 8000 ft. to 28,907 ft. 290 KCAS (292 KIAS)* MMO Above 28,907 ft. 0.75 Mach (0.755 MIAS) VA (Sea level) 15,900 lbs. 201 KCAS (202 KIAS) See AFM for variations with weight and altitude VFE (Flaps extended) 35° (Landing) 174 KCAS (173 KIAS) 15° (Takeoff and approach) 199 KCAS (200 KIAS) 7° (Takeoff) 199 KCAS (200 KIAS) *See NOTE 7 for restricted VMO for optional fuel weight configuration VMCA (Minimum control speed) Air 84 KCAS ( 85 KIAS) VMCG (Minimum control speed) Ground 85.5 KCAS ( 86 KIAS) VLO (Landing gear operating extend) 249 KCAS (250 KIAS) VLO (Landing gear operating retract) 199 KCAS (200 KIAS) VLE (Landing gear extended) 290 KCAS (292 KIAS) VSB (Speed brakes extended Any speed with or without flaps See NOTE 22 for VLO and VLE for 12,200 lb. ZFW option and gravel kit. Tire Limit Maximum ground speed 165 knots C.G. Range (Landing Gear Extended) S/N 560-0001 thru 560-0259 Forward Limits: Linear variation fro m 293.71 in. aft of datum (15% MAC) at 11,500 lbs. or 293.71 in. aft of datum (15% MAC) at 11,500 lbs. or less, to 296.03 in. aft of datum (17.87% MAC) at 15,900 lbs. Aft Limits: 304.23 in. aft of datum (28% MAC) at 15,900 lbs. or less. (Landing Gear Extended) S/N 560-0260 thru 560-0538** Forward Limits: Linear variation fro m 293.71 in. aft of datum (15% MAC) at 11,500 lbs. or 293.71 in. aft of datum (15% MAC) at 11,500 lbs. or less, to 296.24 in. aft of datum (18.13% MAC) at 16,300 lbs. Aft Limits: 304.23 in. aft of datum (28% MAC) at 16,300 lbs. or less. **See NOTE 31 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. +281.56) NOTE: This is reference MAC for basic wing without leading edge cuff and tip Leveling Means Seat Rails Maximum Weight S/N 560-0001 S/N 560-0260 ** thru 560-0259 thru 560-0538 Takeoff 15,900 lbs. 16,300 lbs. Landing 15,200 lbs. 15,200 lbs. Zero fuel 11,200 lbs.* 12,200 lbs. Ramp 16,100 lbs. 16,500 lbs. *See NOTE 7 for optional zero fuel weight ** See NOTE 31 A22CE Page 14 of 40 Rev. 74 V. Model 560 (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) Maximum Baggage Nose Compartment S/N 560- 0001 thru 560-0259 350 lbs. (at Sta. + 74.0) Nose Compartment S/N 560-0260 thru 560-0538 310 lbs. (at Sta. + 74.0) Aft Cabin 600 lbs. (at Sta. +348.0) Tailcone 300 lbs. (at Sta. +434.0) 200 lbs. (at Sta. +462.0) Fuel Capacity (Gal.) Two wing tanks : Total 431.9 each; usable 430.5 each ARM = 302.7 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) S/N 560-0001 thru 560-0259 Two engine-mounted tanks: Total 8.1 each; usable 4.8 each ARM = +387.0 in. S/N 560-0260 thru 560-0538 Two engine mounted tanks: Total 8.4 each; usable 4.7 each ARM: +387.0 in. Windshield Anti-Ice Capacity : 3.4 lb., ARM = +91.4 in. Fluid Approved Anti-Ice Fluids: TT-I-735 Isopropyl alcohol Maximum Operating 45,000 ft. Altitude Control Surface Elevator Up 22° +1/2°, -1° Down 15° +1° Movements Elevator trim tab Up 4-1/2° +1°, -0° Down 16° +1/2°, -0° Rudder Right 22° +1°, -0 ° Left 22° +1°, -0° (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 0° to 58° +2°, -0° See Airplane Maintenance Manual for rigging instructions Certification Basis - Citation V (S/N 560-0001 through 560-0259) (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 amende d 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) Additions for the Honeywell (S perry) EDZ-603 and EDZ-605 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, and 25.1335 as amended by Amendments 25-1 through 25-41. Rev. 74 Page 15 of 40 A22CE V. Model 560 (cont’d) Certification Basis - Citation V (S/N 560-0001 through 560-0259) (cont’d) (2) FAR Part 36 effective Dece mber 1, 1969, as amended by Amendments 36-1 through 36-15. (3) SFAR 27, as amended by Amendmen ts 27-1 and 27-6, 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-ANM-21, additional requirements for High Altitude Operation (45,000 feet) (see NOTE 26). (c) 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 25.815, Passenger Cabin Aisle Width. (d) FAR 25.1305(r), Use of N 1 for Power Presentation. (e) FAR 25.773(b)(2), Use of clear vision area of windshield. (f) FAR 25.1549(a)(b), N 2 Digital Indicator Markings. (g) 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. Certification Basis - Citation Ultra (S/N 560-0260 thru 560-0538) (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; 25.305 as amended by Amendments 25-1 through 25-54; 25.1001 as amended by Amendments 25-1 through 25-57. (b) Additions for the Honeywell Primus 1000 El ectronic 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 36-15. (3) FAR Part 34 effective September 10, 1990, Fuel Venti ng and Exhaust Emission Requirements for Turbine Engine Powered Airplanes. (4) Special Conditions as follows: (a) 25-25-CE-4, additional requirements for systems, airframe, flight and propulsion (see NOTE 28). (b) 25-ANM-21, additional requirements for High Altitude Operation (45,000 feet) (see NOTE 26). (c) 25-ANM-79, additional requirements for Lighting and High Intensity Radiated Fields (HIRF). (d) 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. A22CE Page 16 of 40 Rev. 74 V. Model 560 (cont’d) Certification Basis - Citation Ultra (S/N 560-0260 thru 560-0538) (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 25.815, Passenger Cabin Aisle Width. (d) FAR 25.1305(r), Use of N 1 for Power Presentation. (e) FAR 25.773(b)(2), Use of clear vision area of windshield. (f) FAR 25.1549(a)(b), N 2 Digital Indicator Markings. (g) 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 560-0001 thru 560-0259 (Citation V) 560-0260 thru 560-0538 (Citation Ultra) VI. Model 550 (Bravo) (Transport Category), Approved January 8, 1997 Model 550 Bravo is defined by Cessna Airplane Assembly Drawing Number 6500000. Engines Two Pratt & Whitney of Canada, Inc. PW530A Turbofans Fuel Jet A, Jet A-1, Jet B, JP-5, or JP-8. Fo r use of anti-icing additives, refer to the FAA Approved Airplane Flight Manual. Engine Limits Static thrust, standard day, sea level: Takeoff (5 min.) 2887 lbs. Max. continuous 2843 lbs. Max. permissible engine rotor operating speeds: N 1 (Fan) PW530A 100 percent 15,750 r.p.m. N 2 (Gas Gen.) 100 percent 32,150 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 700° C. Max. continuous 700° C. Starting 690° C. Transient (20 seconds) 740° C. Airspeed Limits V MO (Maximum operating) Sea level to 8,000 ft. 260 KCAS (260 KIAS) 8,000 ft. to 27,900 ft. 275 KCAS (275 KIAS) MMO Above 27,900 ft. 0.70 Mach (0.70 MIAS) VA (Sea level) 14,800 lbs. 190 KCAS (190 KIAS) See AFM for variations with weight, altitude and optional configurations. VB (Speed for max. gust intensity) 210 KCAS (210 KIAS) VFE (Flaps extended) 40° (Landing) 174 KCAS (174 KIAS) 15° (Takeoff and Approach) 200 KCAS (200 KIAS) VMCA (Minimum control speed) Air 79 KCAS ( 78 KIAS) VMCG (Minimum control speed) Ground 92 KCAS ( 89 KIAS) VLO (Landing gear operating extend) 250 KCAS (250 KIAS) VLO (Landing gear operating retract) 200 KCAS (200 KIAS) VLE (Landing gear extended) 260 KCAS (260 KIAS) VSB (Speed brakes extend or retract) Any speed with or without flaps Rev. 74 Page 17 of 40 A22CE VI. Model 550 (cont’d) Tire Limit Maximum ground speed 165 knots C.G. Range (Landing Gear Extended) Forward Limits: Linear variation fro m 276.57 in. aft of datum (18.54% MAC) at 9,147 lbs. to 280.97 in. aft of datum (23.99% MAC) at 14,800 lbs. Aft Limits: 285.8 in. aft of datum (30% MAC) from 14,800 lbs. thru 8,670 lbs. Empty Wt. C.G. Range None Datum Zero reference datum is 93.7 in ches forward of the nose jack point. MAC 80.98 in. (Leading edge of MAC 261.56 in. aft of datum) Leveling Means Lower seat rail RBL 9.0 in. starting at 206.0 in aft of datum. Maximum Weight Takeoff 14,800 lbs. Landing 13,500 lbs. Zero fuel 11,300 lbs. Ramp 15,000 lbs. Minimum Weight In-flight: Forward C.G. Limit: 9,147 lbs. Aft C.G. Limit: 8,670 lbs. NOTE: Linear variation between forward and aft limits. 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 compartment (w/s td equip.) 350 lbs. at Sta. + 74.0 Aft cabin 600 lbs. at Sta. +321.0 Tailcone 300 lbs. at Sta. +414.0 and 200 lbs. at Sta. +442.0 Fuel Capacity (Gal.) Two wing tanks : Total 363.5 each; usable 360 each ARM 287.0 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: Total 5.0 each; usable 1.9 each ARM 366.85 in Maximum Operating 43,000 ft. (S/N 550-0801 thru 550-0820) Altitude (S/N 550-0822 thru 550-0823) 45,000 ft. (S/N 550-0821, 550-0824 and On) See NOTE 25 for S/N 550-0801 thru 550-0820 & 550-0822 thru 550-0823 Control Surface Elevator Up 20° +1° Down 15° +1° Movements Elevator trim tab Up 7° +1°, -1° Down 8° +1°, -1° 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 58° +2° See Airplane Maintenance Manual for rigging instructions A22CE Page 18 of 40 Rev. 74 VI. Model 550 ( cont’d) Certification Basis (S/N 550-0801 and on) (1) FAR Part 25 effective February 1, 1965, as amende d by Amendments 25-1 through 25-17, and the following: (a) Additions: FAR §§ 25.1401, as amended by Amendments 25-1 th ru 25-27; § 25.1387, as amended by Amendments 25-1 through 25-30; 25.1303(a)(2), 25.1385(c), as amended by Amendments 25-1 through 25-38; 25.305, as amended by Amendments 25-1 through 25-54; 25.125, 25.251, 25.337, 25.493, 25.731, 25.733, 25.735, 25.867, 25.869, 25.901, 25.903, 25.933, 25.934, 25.939, 25.943, 25.951, 25.952, 25.1001, 25.1041, 25.1043, 25.1045, 25.1091, 25.1093, 25.1103, 25.1121, 25.1123, 25.1143, 25.1163, 25.1165, 25.1181, 25.1183, 25.1185, 25.1189, 25.1195, 25.1197, 25.1203, 25.1205 (revoked), 25.1207, 25.1305, 25.1316, 25.1322, 25.1326, 25.1337, 25.1351, 25.1438, 25.1521, 25.1549, 25.1551, as amended by 25-1 through 25-82. (b) Additions for the Electronic Flight Instrument Systems only: FAR §§ 25.1301, 25.1303(b) as amended by Amendmen ts 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. (c) Additions for airplanes approved for Hi gh Altitude Operation (45,000 feet) only: 1. FAR §§ 25.571(b)(5), 25.1529 as amended by Ame ndments 25-1 through 25-82. Compliance with the requirements of 25.571(b)(5) is limited to the fuselage. The inspection intervals for compliance with 25.1529 are to address a crack growth propagating for a period encompassing four normal inspection intervals (see NOTE 26). 2. FAR §§ 25.365, 25.831, 25.841, 25.1447 as am ended by Amendments 25-1 through 25-87. (2) FAR Part 36 effective Dece mber 1, 1969, as amended by Amendments 36-1 through 36-21. (3) FAR Part 34 effective September 10, 1990, as amended by Amendment 34-1, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes. (4) Special Conditions. (a) 25-ANM-120, additional requirements for High Intensity Radiated Fields (HIRF). (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 25.815, Passenge r Cabin Aisle Width. (c) FAR 25.773(b)(2), Use of clear vision area of windshield. (d) FAR 25.1549(a) and (b), N 2 Digital Indicator Markings. (e) 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 550-0801 and On Rev. 74 Page 19 of 40 A22CE VII. Model 560XL (Excel) Approved April 22, 1998; (XLS) Approved March 22, 2004; (XLS+) Approved May 30, 2008; (XLS GEN 2) Approved April 22, 2022; (Ascend) Approved November 5, 2025 (Transport Category) Model 560XL is defined by Cessna Airplane Assembly Drawing No. 6600000. Serial No. Eligible: 560-5001 thru 560-5500 (Excel) Serial No. Eligible: 560-5501 thru 560-6000 (XLS) Serial No. Eligible: 560-6001 thru 560-6317, 560-6319 thru 560-6321 (XLS+) Serial No. Eligible: 560-6318 and 560-6322 thru 560-6500 (XLS GEN 2) Serial No Eligible: 560-6501 and On (Ascend) Engines S/N 560-5001 thru 560-5500 Two Pratt & Whitney of Canada, Inc. PW545A Turbofans S/N 560-5501 thru 560-6000 Two Pratt & Whitney of Canada, Inc. PW545B Turbofans S/N 560-6001 thru 560-6500 Two Pratt & Whitney of Canada, Inc. PW545C Turbofans S/N 560-6501 and On Two Pratt & Whitney of Canada, Inc. PW545D Turbofans Fuel For use of anti-icing additives, refer to the FAA Approved Airplane Flight Manual. 560-5001 thru 560-6000 Fuel Type Specification Jet A ASTM D1655 Jet A-1 ASTM D1655 Jet B ASTM D6615 Chinese Jet #3 GB6537 JP-4 MIL-DTL-5624 JP-5 MIL-DTL-5624 JP-8 MIL-DTL-83133 560-6001 and On Fuel Type Specification Jet A ASTM D1655 Jet A-1 ASTM D1655 Chinese Jet #3 GB6537 JP-5 MIL-DTL-5624 JP-8 MIL-DTL-83133 Russian TS-1 GOST 10227 Russian RT GOST 10227 Ukrainian TS-1 GSTU 320-00149943.011 Ukrainian RT GSTU 320-00149943.007 A22CE Page 20 of 40 Rev. 74 VII. Model 560XL (cont’d) Engine Limits S/N 560-5001 thru 560-5500 PW545A Turbofans Static thrust standard day, sea level: Takeoff (5 min.) 3952 lb. Max. continuous 3372 lb. Max. permissible engine rotor operating speeds (PW 545A): N 1 (Fan) 100 percent 13,034 r.p.m. N 2 (Gas Gen.) 101.8 percent 33,289 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 720° C. Max. continuous 720° C. Starting 720° C. Transient (20 seconds) 760° C. S/N 560-5501 thru 560-6000 PW545B Turbofans Static thrust standard day, sea level: Takeoff (5 min.) 4119 lb. Max. continuous 3372 lb. Max. permissible engine rotor operating speeds (PW 545B): N1 (Fan) 100 percent 13,034 r.p.m. N2 (Gas Gen.) 102.8 percent 33,622 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 740° C. Max. continuous 720° C. Starting 740° C. Transient (20 seconds) 780° C. S/N 560-6001 thru 560-6500 PW545C Turbofans Static thrust standard day, sea level: Takeoff (5 min.) 4119 lb. Max. continuous 3372 lb. Max. permissible engine rotor operating speeds (PW 545C): N1 (Fan) 100 percent 13,034 r.p.m. N2 (Gas Gen.) 102.8 percent 33,622 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 740° C. Max. continuous 720° C. Starting 740° C. Transient (20 seconds) 780° C. S/N 560-6501 and on PW545D Turbofans Static thrust standard day, sea level: Takeoff (5 min.) 4218 lb. Max. continuous 3453 lb. Max. permissible engine rotor operating speeds (PW 545D): N1 (Fan) 100 percent 13,034 r.p.m. N2 (Gas Gen.) 102.8 percent 33,622 r.p.m. Max. permissible interturbine gas temperatures: Takeoff 740° C. Max. continuous 720° C. Starting 740° C. Transient (20 seconds) 780° C. Rev. 74 Page 21 of 40 A22CE VII. Model 560XL (cont’d) Airspeed Limits V MO (Maximum operating) Sea level to 8,000 ft. 261 KCAS (260 KIAS) 8,000 ft. to 26,515 ft. 306 KCAS (305 KIAS) MMO Above 26,515 ft. 0.752 Mach (0.750 MIAS) VA (Sea level) 20,000 lb. 196 KCAS (195 KIAS) See AFM for variations with weight and altitude and optional configurations. VB (Speed for max. gust intensity) 211 KCAS (210 KIAS) VFE (Flaps extended) S/N 560-6001 thru 560-6500: 35° (Landing) 175 KCAS (174 KIAS) 15° (Takeoff and approach) 201 KCAS (200 KIAS) 7  (Takeoff and approach) 201 KCAS (200 KIAS) VFE (Flaps extended) S/N 560-6501 and On: FULL (35° - Landing) 176 KCAS (175 KIAS) 2 (15° - Takeoff and Approach) 201 KCAS (200 KIAS) 1 (7° - Takeoff and Approach) 201 KCAS (200 KIAS) VMCA Air (Takeoff) [Min control speed] 90 KCAS (90 KIAS) VMCL Air (Landing) [Min control speed] 92 KCAS (92 KIAS) VMCG (Minimum control speed) Ground 98 KCAS (98 KIAS) VLO (Landing gear operating extend) 251 KCAS (250 KIAS) Tire Limit Maximum ground speed 165 knots *C.G. Range (Landing Gear Extended) S/N 560-5001 thru 560-5500 Forward Limits: Linear variation from 318.92 in. aft of datum (15% MAC) at 11,500 lbs. to 324.18 in. aft of datum (21.39% MAC) at 20,200 lbs. Aft Limits: 331.26 in. aft of datum (30% MAC) from 11,500 lbs. thru 15,000 lbs. Linear variation from 331.26 in. aft of datum (30% MAC) at 15,000 lbs. to 330.74 in. aft of datum (29.37% MAC) at 17,800 lbs. 330.74 in. aft of datum (29.37% MAC) from 17,800 lbs. thru 20,200 lbs. *See NOTE 32. (Landing Gear Extended) S/N 560-5501 thru 560-6000 Forward Limits: Linear variation fro m 318.92 in. aft of datum (15% MAC) at 11,500 lbs. to 324.29 in. aft of datum (21.52% MAC) at 20,400 lbs. Aft Limits: 331.26 in. aft of datum (30% MAC) from 11,500 lbs. thru 15,000 lbs. Linear variation from 331.26 in. aft of datum (30% MAC) at 15,000 lbs. to 330.74 in. aft of datum (29.37% MAC) at 17,800 lbs. 330.74 in. aft of datum (29.37% MAC) from 17,800 lbs. thru 20,400 lbs. (Landing Gear Extended) S/N 560-6001 thru 560-6317, 560-6319 thru 560-6321 Forward Limits: Linear variation fro m 318.92 in. aft of datum (15% MAC) at 11,500 lbs. to 324.29 in. aft of datum (21.52% MAC) at 20,400 lbs. Aft Limits: 331.26 in. aft of datum (30% MAC) from 11,500 lbs. thru 15,000 lbs. Linear variation from 331.26 in. aft of datum (30% MAC) at 15,000 lbs. to 330.74 in. aft of datum (29.37% MAC) at 17,800 lbs. 330.74 in. aft of datum (29.37% MAC) from 17,800 lbs. thru 20,400 lbs. (Landing Gear Extended) S/N 560-6318, and 560-6322 thru 560-6500 Forward Limits: Linear variation fro m 318.92 in. aft of datum (15% MAC) at 11,500 lbs. to 324.37 in. aft of datum (21.62% MAC) at 20,530 lbs. Aft Limits: 331.26 in. aft of datum (30% MAC) from 11,500 lbs. thru 15,000 lbs. Linear variation from 331.26 in. aft of datum (30% MAC) at 15,000 lbs. to 330.74 in. aft of datum (29.37% MAC) at 17,800 lbs. 330.74 in. aft of datum (29.37% MAC) from 17,800 lbs. thru 20,530 lbs. A22CE Page 22 of 40 Rev. 74 VII. Model 560XL (cont’d) C.G. Range (cont’d) (Landing Gear Extended) S/N 560-6501 and On Forward Limits: Linear variation fro m 320.57 in. aft of datum (17% MAC) at 14,000 lbs. to 324.47 in. aft of datum (21.74% MAC) at 20,700 lbs. Aft Limits: 331.26 in. aft of datum (30% MAC) from 11,500 lbs. thru 15,000 lbs. Linear variation from 331.26 in. aft of datum (30% MAC) at 15,000 lbs. to 330.74 in. aft of datum (29.37% MAC) at 17,800 lbs. 330.74 in. aft of datum (29.37% MAC) from 17,800 lbs. thru 20,700 lbs. Empty Wt. C.G. Range None Datum Zero reference datum is 221.0 inches forward of the leveling screw just aft of the cabin door on W.L. 127.25. MAC 82.231 in. (Leading edge of MAC 306.593 in. aft of datum) NOTE: This is reference MAC for basic wing without tip. Leveling Means Outboard floor panel insi de of door parallel to B.L. 13.00. *S/N 560-5001 thru 560-5500 S/N 560-5501 thru 560-6000 Maximum Weight Takeoff 20, 000 lbs. Takeoff 20,200 lbs. Landing 18,700 lbs. Landing 18,700 lbs. Zero fuel 15,000 lbs. Zero fuel 15,100 lbs. Ramp 20,200 lbs. Ramp 20,400 lbs. *See NOTE 32. Minimum Weight In-flight 12, 400 lbs. In-flight 12,400 lbs. S/N 560-6001 thru 560-6317 and S/N 560-6318 and 560-6322 560-6319 thru 560-6321 thru 560-6500 Maximum Weight Takeoff 20,200 lbs. Takeoff 20,330 lbs. Landing 18,700 lbs. Landing 18,700 lbs. Zero fuel 15,100 lbs. Zero fuel 15,360 lbs. Ramp 20,400 lbs. Ramp 20,530 lbs. S/N 560-6501 and On Maximum Weight Takeoff 20,500 lbs. Landing 18,700 lbs. Zero fuel 15,800 lbs. Ramp 20,700 lbs. Minimum Weight In-flight 12,800 lbs. Minimum Crew For all flights: 2 persons (pilot and co-pilot) No. of Seats 2 to 14 (2 crew, 0 to 12 passengers) See NOTE 29 Maximum Baggage Tailcone: 700 lbs. at 431.0 in. aft of datum Fuel Capacity (Gal.) Two wing tanks: Total 505.8 each; usable 503.0 each ARM 328.8 in. aft of datum See NOTE 1 for data on unusable fuel. Oil Capacity (Quarts) Two engine mo unted tanks: Max Level LH=6.0, RH=5.56 Unusable Min Level LH=0.85, RH=0.84 ARM 433.9 in. aft of datum Maximum Operating 45,000 ft. Altitude Rev. 74 Page 23 of 40 A22CE VII. Model 560XL (cont’d) Control Surface Elevator (with stabilizer at  1°) Up 19°  1°,  0 Down 15°  1° Movements Elevator trim tab (with stabilizer at  1°) Up 5°  1° Down 15°  1° Rudder (perpendicular to hinge) Right 22° + 1°, 0 Left 22°  1°,  0 For Aircraft with rudder bias system installed Rudder (perpendicular to hinge) Right 28.5° + 0.5°, -0° Left 28.5° + 0.5°, -0° Rudder trim tab Right 11.5°  0.5° Left 11.5°  0.5° (perpendicular to hinge with Rudder centered) Aileron Up 19°  1° Down 15°  1° Aileron trim tab Up 20°  2º Down 20°  2° Wing flap 0°, and extend 7°, 15°, 35°  1° Speed brake - Upper Up 60°  2° - Lower Up 65°  2° 2-position Horizont al stabilizer T/O & Landing  2  0°,  0.1 Cruise  1°  0.1°,  0 See Airplane Maintenance Manual for rigging instructions. Certification Basis (Excel and XLS) (1) FAR Part 25 effective February 1, 1965, as amende d by Amendments 25-1 thru 25-82, with additions and exceptions as follows. (a) Additions: FAR §§ 25.305, 25.321, 25.331, 25.333, 25.335, 25. 341, 25.343, 25.345, 25.349, 25.371, 25.373, 25.391, 25.427, 25.1517 as amended by Amendment 25-86; 25.351 as amended by Amendment 25-91. (b) Exceptions (as shown in table): SECTION NO. TITLE EFFECTIVE AMENDMENT COMMENTS 25.562(c)(5)(6) Emergency landi ng dynamic conditions. N/A N/A 25.571(e)(1) Damage-tolerance and fatigue evaluation of structure. N/A N/A 25.631 Bird strike damage. N/A N/A 25.671 Control Systems – General.  Applicable to the 2-position horizontal stabilizer.  All other airplane control systems. 25-0 Initial Issue 2-position horizontal stabilizer not included in the exception 25.677 Trim Systems.  Applicable to the 2-position horizontal stabilizer.  All other airplane trim systems, including the elevator trim. 25-0 Initial Issue 2-position horizontal stabilizer not included in the exception 25.1309 (Excel, XLS) Equipment, systems, and installations.  All airplane systems. 25-0 Initial Issue Electronic Flight Instrument systems (Honeywell Primus 1000 Cockpit Display), Flight Guidance, hydraulic, electrical, pressurization system, and 2- position horizontal stabilizer not included in the exception. A22CE Page 24 of 40 Rev. 74 VII. Model 560XL (cont’d) Certification Basis (Excel and XLS) (cont’d) (2) For EXCEL: FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-21. For XLS: FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-28 (3) FAR Part 34 effective September 10, 1990 as amended by Amendment 34-1. (4) Special Conditions as follows: (a) 25-ANM-79, effects of High Intens ity Radiated Fields (HIRF). The portions associated with System Lightning Protection do not apply. (b) 25-ANM-21, High Altitude Operation (45,000 feet). See NOTE 26. (c) 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) Exemption: (a) Exemption Number 6706 granted. Model 560XL exempt from requirements of FAR 25.677(b) for horizontal stabilizer position indicator. (b) Exemption Number 8621 granted. Model 560XL exempt from requirements of FAR 25.813(e) for installation of interior doors between passenger compartments. (6) Equivalent levels of safety as follows: (a) FAR 25.807(e), Emergency exits ditching (involves water barrier). (b) FAR 25.815, Passenger Cabin Aisle Width; (See NOTE 29). (c) FAR 25.813(e), Lavatory door insta llation between passenger compartments. (d) FAR 25.811(d)(1); 25.812(b)(1)(i), Emer gency exit markings and locator signs. (e) FAR 25.841(b)(6), Takeoff and landing op erations at high elevation airports. (f) FAR 25.1549(a)(b), Digital only di splay of turbine engine N2. (g) FAR 1.1; 1.2; 25.101, 25.105, 25.109, 25.113, 25. 115, 25.735, 25.1587, Rejected takeoff distance and landing performance criteria (includes worn brake criteria). (h) FAR 25.1305(a)(4)(5)(6)(c)(1)(3), 25.1549(a) thru (d), Digital only display of APU engine rotor speed, exhaust gas temperature and no indication of oil pressure or oil temperature. (i) ELOS #SP2095WI-T-AG-8, dated August 23, 2002, FAR 25.815, Passenger Cabin Aisle Width. (j) FAR 25.1301(a)(d), 25.1303(a)(3), 25.1309(a)(b)(d )(e), 25.1316, 25.1327, 25.1331, 25.1333, 25.1547, 25.1351(d), 25.1353(a)(c), 25.1459(e), Electric Standby Direction Indicator (Compass) (Applies to XLS) (7) FAR 25.801 ditching not complied with. (8) Compliance with ice protection has been de monstrated in accordance with FAR 25.1419. Certification Basis (XLS+ and XLS GEN 2) (1) FAR Part 25 effective February 1, 1965, as amende d by Amendments 25-1 thru 25-82, with additions and exceptions as follows. (a) Additions: FAR §§25.305, 25.321, 25.331, 25.333, 25.335, 25.341, 25.343, 25.345, 25.349, 25.371, 25.373, 25.391, 25.427, 25.1517 as amended by Amendment 25-86; 25.351 as amended by Amendment 25-91. FAR §§25.901, 25.903, 25.933, 25.934, 25.939, 25.943 as amended by Amendments 25-1 through 25-117 for main engine installations. FAR §§25.1317(b) as amended by Amendment 25-1 through 25-122, is applicable to Global Positioning System Sensor for S/N 560-6247 and On. FAR §§25.1457(a)(6) as amended by Amendment 25-1 through 25-124, is applicable to the Cockpit Voice Recorder Installation when the optional ATN-B1 Datalink Installation is installed. Rev. 74 Page 25 of 40 A22CE VII. Model 560XL ( cont’d) Certification Basis (XLS+ and XLS GEN 2) (b) Exceptions (as shown in table): Section No. Title Amendment Level Comments 25.562(c)(5)(6) Emergency landi ng dynamic conditions. N/A N/A 25.571(e)(1) Damage-tolerance and fatigue evaluation of structure. N/A N/A 25.631 Bird strike damage. N/A N/A 25.671 Control Systems: All airplane control systems. 25-0 (initial issue) 2-position horizontal stabilizer not included in the exception. 25.677 Trim Systems: All airplane control systems, including elevator trim. 25-0 (initial issue) 2-position horizontal stabilizer not included in the exception. 25.1309 (XLS+) Equipment, systems, and installations: All airplane systems. 25-0 (initial issue) Electronic Flight Instrument systems, (Rockwell Collins Pro Line 21), Flight Guidance, hydraulic, electrical, pressurization system, FADEC, and 2-position horizontal stabilizer, not included in the exception. (2) FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-28 for S/N 560-6001 to 560-6317 and 560-6319 to 560-6321. FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-31 for S/N 560-6318 and 560-6322 and on. (3) FAR Part 34 effective September 10, 1990, as amended by Amendment 34-1. (4) Special Conditions as follows: (a) 25-ANM-79, effects of High Intens ity Radiated Fields (HIRF). The portions associated with System Lightning Protection do not apply. (b) 25-ANM-21, High Altitude Operation (45,000 feet). See NOTE 26. (c) 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) Exemption: (a) Exemption Number 6706 granted. Model 560XL exempt from requirements of FAR 25.677(b) for horizontal stabilizer position indicator. (b) Exemption Number 8621 granted. Model 560XL exempt from requirements of FAR 25.813(e) for installation of interior doors between passenger compartments. (6) Equivalent Levels of Safety (ELOS) as follows: (a) FAR 25.807(e), Emergency exits ditching (involves water barrier). (b) FAR 25.815, Passenger Cabin Aisle Width; (See NOTE 29). (c) FAR 25.813(e), Lavatory door insta llation between passenger compartments. (d) FAR 25.811(d)(1), 25.812(b)(1)(i), Emer gency exit markings and locator signs. (e) FAR 25.841(b)(6), Takeoff and landing operations at high elevation airports. (f) FAR 25.1549(a)(b), Digital only di splay of turbine engine N2. (g) FAR 1.1; 1.2; 25.101, 25.105, 25.109, 25.113, 25. 115, 25.735, 25.1587, Rejected takeoff distance and landing performance criteria (includes worn brake criteria). (h) FAR 25.1305(a)(4)(5)(6)(c)(1)(3), 25.1549(a)(b)(c)(d), Digital only display of APU engine rotor speed, exhaust gas temperature and no indication of oil pressure or oil temperature. (i) ELOS #SP2095WI-T-AG-8, dated August 23, 2 002, FAR 25.815, Passenger Cabin Aisle Width (j) ELOS #AT4531WI-T-SE-1, FAR §§ 25.1301(a)(d), 25.1303(a)(3), 25.1309(a)(b)(d)(e), 25.1316, 25.1327, 25.1331, 25.1333, 25.1547, 25.1351(d), 25.1353(a)(c), 25.1459(e), Electric Standby Direction Indicator (Compass). (k) ELOS #AT4531WI-T-P-1, dated March 20, 2008, 21.21(b)(1), 25.1549, Use of Numeric Digital Only Display for Engine High-Pressure Turbine Speed (N2), Engine Fuel Flow (Wf), Standby N1, N2, and ITT. (l) ELOS #AT4531WI-T-SE-2, dated May 30, 2008, 25. 1397(c), 25.1401(d), Exterior Lighting Chromaticity Requirements. A22CE Page 26 of 40 Rev. 74 VII. Model 560XL ( cont’d) Certification Basis (XLS+ and XLS GEN 2) (cont’d) (7) FAR 25.801 ditching not complied with. (8) Compliance with ice protection has been de monstrated in accordance with FAR 25.1419. Certification Basis (Ascend) 1) 14 CFR Part 25, effective February 1, 1965, as amended by Amendments 25-1 through 25-82, with additions and exceptions as follows. a) Additions (as shown in table): Section No. Title Amendment Level Comments 25.305 Strength and Deformation 25-86 For entire airplane 25.321 General 25-86 For entire airplane 25.331 Symmetric Maneuvering Conditions 25-86 For entire airplane 25.333 Flight (Maneuvering) Enve lope 25-86 For entire airplane 25.335 Design Airspeeds 25-86 For entire airplane 25.341 Gust and Turbulence Loads 25-86 For entire airplane 25.343 Design Fuel and Oil Loads 25-86 For entire airplane 25.345 High Lift Devices 25-86 For entire airplane 25.349 Rolling Conditions 25-86 For entire airplane 25.351 [Yaw Maneuver] Conditions 25-91 For entire airplane 25.371 Gyroscopic Loads 25-86 For entire airplane 25.373 Speed Control Devices 25-86 For entire airplane 25.391 Control Surface Loads: Gene ral 25-86 For entire airplane 25.427 Unsymmetrical Loads 25-86 For entire airplane 25.613 Material Strength Properties and Material Design Values 25-112 For entire airplane 25.773 Pilot Compartment View 25-136 Cockpit side window configuration, hydrophobic coating for rain removal 25.856 Thermal/Acoustic Insulation materials 25-111 For entire airplane 25.903 Engines 25-100 Main engine installations 25.981 Fuel Tank Ignition Prevention 25-102 New HW wiring for fuel temperature and low fuel quantity altering interfaces, new HW for fuel quantity indicating system Rev. 74 Page 27 of 40 A22CE VII. Model 560XL ( cont’d) Certification Basis Ascend ( cont’d) Section No. Title Amendment Level Comments 25.1141(f) Powerplant Controls: General 25-115 New Run/Stop and Engine Fire switches, FADEC control of the HMU 25.1316 System Lightning Protection 25-134 Changes in avionics, powerplant, airframe, and systems 25.1317 High-Intensity Radiated Fields (HIRF) Protection 25-122 Changes in avionics, powerplant, airframe, and systems 25.1323(a)(f)(g)(h) Airspeed Indicating System 25-109 Changes in avionics systems 25.1329 Flight Guidance System 25-119 Addition of autothrottle for Autothrottle Only 25.1360 Precautions Against Injury 25- 123 Changes in avionics systems 25.1457 Cockpit Voice Recorders 25-124 Recording datalink communications, specifically FANS 1/A+ with ADS-C and ATN B1 25.1517 Rough Air Speed, VRA 25-86 For entire airplane (b) Exceptions (as shown in table): Section No. Title Amendment Level Comments 25.562(c)(5)(6) Emergency landing dynamic conditions. N/A N/A 25.571(e)(1) Damage-tolerance and fatigue evaluation of structure. N/A N/A 25.631 Bird strike damage. N/A N/A 25.671 Control Systems: All airplane control systems. 25-0 (initial issue) 2-position horizontal stabilizer not included in the exception. 25.677 Trim Systems: All airplane control systems, including elevator trim. 25-0 (initial issue) 2-position horizontal stabilizer not included in the exception. 25.1309 (Ascend) Equipment, systems, and installations: All airplane systems. 25-0 (initial issue) Flight Instrument systems (Garmin G5000 Cockpit Display), Flight Guidance, hydraulic, electrical, pressurization system, FADEC, UHT, APU changes, and 2-position horizontal stabilizer, not included in the exception. (2) 14 CFR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-32. (3) 14 CFR Part 34 effective September 10, 1990, as amended by Amendments 34-1 through 34-5A. (4) Special Conditions as follows: (a) 25-ANM-21, High Altitude Operation (45,000 feet) (b) 25-674-SC, Non-Rechargeable Lithiu m Batteries, effective to design changes applied for after May 16, 2017. (c) 25-838-SC Aircraft Electronic System Secur ity Protection from Unauthorized External Access (d) 25-839-SC Aircraft Electronic System Secur ity Protection from Unauthorized Internal Access (e) 25-867-SC Hydrophobic Coating in Lieu of Windshield Wipers (5) Exemption: (a) Exemption Number 6706 granted. Model 560XL ex empt from requirements of 14 CFR 25.677(b) for horizontal stabilizer position indicator. (b) Exemption Number 8621 granted. Model 560XL ex empt from requirements of 14 CFR 25.813(e) for installation of interior doors between passenger compartments. A22CE Page 28 of 40 Rev. 74 VII. Model 560XL ( cont’d) Certification Basis Ascend ( cont’d) (6) Equivalent Levels of Safety (ELOS) as follows: (a) 14 CFR 25.773(b)(1)(i) Pilot Compartment View. (b) 14 CFR 25.807(e) Emergency exit markings and locator signs. (c) 14 CFR 25.811(d)(1), 25.812(b)(1)(i) Emer gency exit markings and locator signs. (d) 14 CFR 25.813(e) Lavatory door insta llation between passenger compartments. (e) 14 CFR 25.815 Passenge r Cabin Aisle Width. (f) 14 CFR 25.841(a)(b)(6) Amdt 25-38; 25.1447(c)(1) Amdt 25-41, 91.1211(a)(1), 121.329(b)(1)(2), 135.89(b) Cabin Pressurization High Elevation Takeoff and Landing Operations. (g) 14 CFR 25.901, 25.903, 25.1305, 25.1309, 25.1321, 25.1322, 25.1549 Powerplant Digital Displays. (h) 14 CFR 25.1141(f)(2) Powerplant Valve Indications. (i) 14 CFR 25.1301(a)(d), 25.1303(a)(3), 25.1309(a)(b)(d )(e), 25.1316, 25.1327, 25.1331, 25.1333, 25.1351, 25.1353(a)(c), 25.1459(e), 25.1547 Electric Standby Indicator (Compass). (j) 14 CFR 1.1, 1.2, 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, 25.1587 Rejected takeoff distance and landing. (k) 14 CFR Part 25 subparts E, F, an d G APU 25 Certification Requirements. (7) 14 CFR 25.801 ditching not complied with. (8) Compliance with ice protection has been de monstrated in accordance with 14 CFR 25.1419. VIII. Model 560 (Encore) (Transport Category), Approved April 26, 2000 The Model 560 Encore is defined by Cessn a Airplane Assembly Drawing Number 6500560. Engines Two Pratt & Whitney of Canada, Inc. PW535A turbofans Fuel Jet A, Jet A-1, Jet B, JP-4, JP-5, JP-8. Engine Limits Static thrust, standard day, sea level: Takeoff (5 min., Normal All Engines Operating) 3,400 lbs. Takeoff (10 min., One Engi ne Inoperative) 3,400 lbs. Maximum continuous 3,400 lbs. Max. permissible engine rotor operating speeds: N 1 (Fan) 100% 15,850 rpm N 2 (Gas Gen.) 100% 33,970 rpm Max. permissible interturbine gas temperatures: Takeoff 700° C Max. continuous 700° C Starting 740º C Transient (20 seconds) 740° C Airspeed Limits V MO (Maximum operating) Sea level to 8,000 ft. 260 KCAS (262 KIAS) 8,000 ft. to 28,907 ft. 290 KCAS (292 KIAS) M MO Above 28,907 ft. 0.75 Mach (0.755 MIAS) VA (Sea level) 16,630 lbs. 193 KCAS (194 KIAS) See AFM for variations with weight and altitude VFE (Flaps extended) 35° (Landing) 173 KCAS (173 KIAS) 15° (Takeoff and approach) 199 KCAS (200 KIAS) 7° (Takeoff) 199 KCAS (200 KIAS) Rev. 74 Page 29 of 40 A22CE VIII. Model 560 (cont’d) Airspeed Limits (cont’d) V MCA (Minimum control speed Air) 84 KCAS (86 KIAS) VMCG (Minimum control speed Ground) 15° (Takeoff) 95 KCAS (92 KIAS) 7° (Takeoff) 99 KCAS (96 KIAS) VLO (Landing gear operating extend) 249 KCAS (250 KIAS) VLO (Landing gear operating retract) 199 KCAS (200 KIAS) VLE (Landing gear extended) 249 KCAS (250 KIAS) VLSB (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 296.14 in. aft of datum (18% MAC) at 12,400 lbs. or 296.14 in. aft of datum (18% MAC) at 12,400 lbs. or less, to 299.29 in. aft of datum (21.89% MAC) at 16,830 lbs. Aft Limits: 304.23 in. aft of datum (28% MAC) at 16,830 lbs. or less. *See NOTE 33 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. +281.56) NOTE: This is reference MAC for basic wing without leading edge cuff and tip Leveling Means Crew Seat Rails (Lateral level); Cabin Door Step Hinge Brackets (Longitudinal level) Maximum Weight* Takeoff 16,630 lbs. Landing 15,200 lbs. Zero fuel 12,600 lbs . Ramp 16,830 lbs. *See NOTE 33 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 Compartment 310 lbs. (at Sta. + 74.0) Aft Cabin 600 lbs. (at Sta. +348.0) Tailcone 300 lbs. (a t Sta. +434.0) and 200 lbs. (at Sta. +462.0) Fuel Capacity (Gal.) Two wing tanks : Total 406.4 each; usable 403 each ARM: +303.5 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: Total 8.6 each; usable 0.6 each ARM: +387.0 in. Windshield Anti-Ice Ca pacity: 2.0 quarts Fluid ARM: +91.5 in. Approved Anti-Ice Fluids: TT-I-735 Isopropyl alcohol Maximum Operating 45,000 ft. Altitude A22CE Page 30 of 40 Rev. 74 VIII. Model 560 (cont’d) Control Surfaces Elevator Up 18° +1°, -½° Down 15° +1° Movements Elevator trim tab Up 4½° +0°, -½° Down 11° +½°, -0° Rudder Right 22° +1°, -0 ° Left 22° +1°, -0° (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 0° to 58° +2°, -0° See Airplane Maintenance Manual for rigging instructions. Certification Basis (1) FAR Part 25 effective February 1, 1965, as amended by Amendments 25-1 through 25-17, and the following. (a) Additions: FAR §§ 25.625 as amended by Amendments 25-1 th ru 25-17; 25.1401 as amended by Amendments 25-1 through 25-27; 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) as amended by Amendments 25-1 through 25-38; 25.305 as amended by Amendments 25-1 thru 25-54; 25.119, 25.121, 25.125, 25.143, 25.145, 25.149, 25.201, 25.203, 25.251, 25.253, 25.337, 25.361, 25.363, 25.371, 25.471, 25.473, 25.479, 25.481, 25,483, 25.485, 25.489, 25.491, 25.493, 25.509, 25.611, 25.721, 25.723, 25.725, 25.727, 25.731, 25.733, 25.735, 25.863, 25.865, 25.867, 25.869, 25.901, 25.933, 25.934, 25.939, 25.943, 25.951, 25.952, 25.959, 25.961, 25.965, 25.977, 25.979, 25.994, 25.995, 25.997, 25.999, 25.1001, 25.1041, 25.1043, 25.1045, 25.1091, 25.1093, 25.1103, 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1163, 25.1165, 25.1181, 25.1183, 25.1185, 25.1189, 25.1195, 25.1197, 25.1199; 25.1203, 25.1205(revoked), 25.1207, 25.1305, 25.1316, 25.1322, 25.1326, 25.1337, 25.1351, 25.1385(c), 25.1387, 25.1419, 25.1438, 25.1521, 25.1529, 25.1549, 25.1551 as amended by Amendments 25-1 through 25-91. (b) Additions for the Honeywell Primus 1000 El ectronic 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. (c) Addition limited ONLY to: (i) Pressurization System; Digital Controller and Outflow System. (ii) Anti-skid System; Individual Wheel Digital Anti-skid Controller. (iii) Anti-ice System; Electronic Tail Boot Control an d Monitoring and Outboard Wing Leading Edge Bleed Air Control and Fault Annunciation. (iv) Integrated Warning, Caution, and Advisory Annunc iation System limited to the Internal Control Logic and Display Functions Only. FAR 25.1309 as amended by Amendments 25-1 through 25-91. (2) FAR Part 36 effective December 1, 1969, Noise Standards, as amended by Amendments 36-1 through 36-21. (3) FAR Part 34 effective September 10, 1990, Fuel Venti ng and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, as amended by Amendments 34-1 through 34-3. (4) Special Conditions as follows: (a) 25-ANM-21, additional requirements for High Altitude Operation (45,000 feet). (b) 25-ANM-79, additional requirements for High Intensity Radiated Fields (HIRF) only. (c) 25-25-CE-4, additional requirements for Turbine engine powerplant installation [Paragraphs 3, Inflight restart capability; 6, Turbine engine powerplant installation; and 7, Engine ignition system only]. (d) 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 31 of 40 A22CE VIII. Model 560 (cont’d) Certification Basis (cont’d) (5) Equivalent levels of safety as follows: (a) FAR 25.815, Passenger Cabin Aisle Width. (b) FAR 25.773(b)(2), Use of clear vision area of windshield. (c) FAR 25.1549(a)(b), N 2 Digital Indicator Markings. (d) FAR 25.813(e), Frangible door. (e) FAR 25.807(d), Emergency exits ditching. (f) FAR 25.841(b)(6), Cabin Pressurization – High Altitude Takeoff and Landing. (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 560-0539 thru 560-0750. IX. Model 560 (Encore+) (Transport Category), Approved December 14, 2006 Model 560 Citation Encore+ is defined by Ce ssna Airplane Assembly Drawing No. 6500560. Engines Two Pratt & Whitney of Canada, Inc. PW535B turbofans Fuel Jet A, Jet A-1, JP-5 or JP-8 Engine Limits Static thrust, standard day, sea level: Takeoff (5 min., Normal All Engines Operating) 3,400 lbs. Takeoff (10 min., One Engine Inoperative) 3,400 lbs. Maximum continuous 3,400 lbs. Max. permissible engine rotor operating speeds: N 1 (Fan) 100% 15,850 rpm N 2 (Gas Gen.) 100% 33,970 rpm Max. permissible interturbine gas temperatures: Takeoff 700° C Max. continuous 700° C Starting 740º C Transient (20 seconds) 740° C Airspeed Limits V MO (Maximum operating) Sea level to 8,000 ft. 260 KCAS (262 KIAS) 8,000 ft. to 28,907 ft. 290 KCAS (292 KIAS) M MO Above 28,907 ft. 0.75 Mach (0.755 MIAS) VA (Sea level) 16,830 lbs. 193 KCAS (194 KIAS) See AFM for variations with weight and altitude VFE (Flaps extended) 35° (Landing) 173 KCAS (173 KIAS) 15° (Takeoff and approach) 199 KCAS (200 KIAS) 7° (Takeoff) 199 KCAS (200 KIAS) A22CE Page 32 of 40 Rev. 74 IX. Model 560 (Encore+) (cont’d) Airspeed Limits (cont’d) V MCA (Minimum control speed Air) 84 KCAS (86 KIAS) VMCG (Minimum control speed Ground) 15° (Takeoff) 95 KCAS (92 KIAS) 7° (Takeoff) 99 KCAS (96 KIAS) VLO (Landing gear operating extend) 249 KCAS (250 KIAS) VLO (Landing gear operating retract) 199 KCAS (200 KIAS) VLE (Landing gear extended) 249 KCAS (250 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 296.14 in. aft of datum (18% MAC) at 12,400 lbs. or 296.14 in. aft of datum (18% MAC) at 12,400 lbs. or less, to 299.43 in. aft of datum (22.07% MAC) at 17,030 lbs. Aft Limits: 304.23 in. aft of datum (28% MAC) at 17,030 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. +281.56) NOTE: This is reference MAC for basic wing without leading edge cuff and tip Leveling Means Crew Seat Rails (Lateral level); Ca bin Door Step Hinge Brackets (Longitudinal level) Maximum Weight Takeoff 16,830 lbs. Landing 15,200 lbs. Zero fuel 12,850 lbs. Ramp 17,030 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 310 lbs. (at Sta. + 74.0) Aft Cabin 600 lb s. (at Sta. +348.0) Tailcone 300 lbs. (at Sta. + 434.0) and 200 lbs. (at Sta. +462.0) Fuel Capacity (Gal.) Two wing tanks : Total 406.4 each; usable 403 each ARM: +303.5 in. See NOTE 1 for data on unusable fuel Oil Capacity (Quarts) Two engine mounted tanks: Total 8.6 each; usable 0.6 each ARM: +387.0 in. Windshield Anti-Ice Ca pacity: 2.0 quarts Fluid ARM: +91.5 in. Approved Anti-Ice Fluids: TT-I-735 Isopropyl Alcohol Maximum Operating 45,000 ft. Altitude Rev. 74 Page 33 of 40 A22CE IX. Model 560 (Encore+) (cont’d) Control Surfaces Elevator Up 18° +1°, -½° Down 15° +1° Movements Elevator trim tab Up 4½° +0°, -½° Down 11° +½°, -0° Rudder Right 22° +1°, -0 ° Left 22° +1°, -0° (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 0° to 58° +2°, -0° See Airplane Maintenance Manual for rigging instructions. Certification Basis (1) 14 CFR Part 25 effective February 1, 1965, as amended by Amendments 25-1 through 25-17, except for paragraphs applicable for engines and FADEC and the following. (a) Additions: FAR 25.625 as amended by Amendments 25-1 through 25-17; 25.1401 as amended by Amendments 25-1 through 25-27; 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) as amended by Amendments 25-1 through 25-38; 25.305 as amended by Amendments 25-1 through 25-54; 25.119, 25.121, 25.125, 25.143, 25.145, 25.149, 25.201, 25.203, 25.251, 25.253, 25.337, 25.361, 25.363, 25.371, 25.471, 25.473, 25.479, 25.481, 25,483, 25.485, 25.489, 25.491, 25.493, 25.509, 25.611, 25.721, 25.723, 25.725, 25.727, 25.731, 25.733, 25.735, 25.863, 25.865, 25.867, 25.869, 25.901, 25.933, 25.934, 25.939, 25.943, 25.951, 25.952, 25.959, 25.961, 25.965, 25.977, 25.979, 25.994, 25.995, 25.997, 25.999, 25.1001, 25.1041, 25.1043, 25.1045, 25.1091, 25.1093, 25.1103, 25.1121, 25.1123, 25.1141, 25.1143, 25.1145, 25.1163, 25.1165, 25.1181, 25.1183, 25.1185, 25.1189, 25.1195, 25.1197, 25.1199; 25.1203, 25.1205(revoked), 25.1207, 25.1305, 25.1316, 25.1322, 25.1326, 25.1337, 25.1351, 25.1385(c), 25.1387, 25.1419, 25.1438, 25.1521, 25.1529, 25.1549, 25.1551 as amended by Amendments 25-1 through 25-91; 25.901, 25.903(a)(b)(c)(e)(f), 25.933, 25.934, 25.939, 25.943 as amended by Amendments 25-1 through 25-117 (b) Additions for the Electronic Flight Instrument Systems only: 14 CFR 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. (c) Addition limited ONLY to: (i) Pressurization System; Digital Controller and Outflow System. (ii) Anti-skid System; Individual Wheel Digital Anti-skid Controller. (iii) Anti-ice System; Electronic Tail Boot Control an d Monitoring and Outboard Wing Leading Edge Bleed Air Control and Fault Annunciation. (iv) Integrated Warning, Caution, and Advisory Annunc iation System limited to the Internal Control Logic and Display Functions Only. 14 CFR 25.1309 as amended by Amendments 25-1 through 25-91. (d) Addition limited only to FADEC engine control syst em: 25.1309 as amended by Amendments 25-1 through 25-117 (2) 14 CFR Part 36 effective December 1, 1969, Noise St andards, as amended by Amendments 36-1 through 36-21. (3) 14 CFR Part 34 effective September 10, 1990, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, as amended by Amendments 34-1 through 34-3. A22CE Page 34 of 40 Rev. 74 IX. Model 560 (Encore+) (cont’d) Certification Basis (cont’d) (4) Special Conditions as follows: (a) 25-ANM-21, additional requirements for High Altitude Operation (45,000 feet). (b) 25-ANM-79, additional requirements for High Intensity Radiated Fields (HIRF) only. (c) 25-25-CE-4, additional requirements for Turbine engine powerplant installation [Paragraphs 3, Inflight restart capability; 6, Turbine engine powerplant installation; and 7, Engine ignition system only]. (d) 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) 14 CFR 25.815, Passenge r Cabin Aisle Width. (b) 14 CFR 25.773(b)(2), Use of clear vision area of windshield. ELOS Memo # AT4267WI-T-P-1, 14 CFR 25.1549(a) thru (c) digital only displays N2, engine fuel flow (Wf), and Standby N1, N2, and ITT. (b) 14 CFR 25.813(e), Frangible door. (d) 14 CFR 25.807(d), Emergency exits ditching. (e) 14 CFR 25.841 (b)(6), Cabin Pressurization – High Altitude Takeoff and Landing Operation, through Amendment 25-87. ELOS Memo #ST4383WI-T-SE-1, 14 CFR 25.1303(a)(9), 25.1547 electronic standby direction indicator. (6) 14 CFR 25.801 ditching not complied with. (7) Compliance with ice protection has been de monstrated in accordance with 14 CFR 25.1419. Application for Type Certificate dated July 16, 1968. Type Certificate No. A22CE issued September 9, 1971. Production Basis Production Certificate No . PC-4 effective June 1, 1985, or later issue. Production Certificate No. PC-312 effective September 9, 1971, through May 31, 1985. Effective February 15, 1985, and on, Production Certificate No. PC-4 is applicable to all spares production. See NOTE 14 for latest issue date of PC-4 and specific effectivity on airplane models and serial numbers. Equipment The basic required equipment as prescrib ed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. Serial No. Eligible 560-0751 thru 560-0815 (Encore +) Data Pertinent to all Models NOTE 1. Current weight and ba lance report including 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: Unusable Fuel 96.0 lbs. at +247.0 in. 500, S/N 500-0001 thru 500-0040 200.5 lbs. at +247.0 in. 500, S/N 500-0001 thru 500-0040 incorporating SB500-28-10 58.0 lbs. at +247.0 in. 500, S/N 500-0041 thru 500-0689 138.4 lbs. at +247.0 in 500, S/N 500-0041 thru 500-0689 incorporating SB500-28-10 52.8 lbs. at +298.4 in. 550, S/N 550-0001 thru 550-0800 47.2 lbs. at +281.7 in. 550, S/N 550-0801 and on 60.0 lbs. at +285.5 in. S550, S/N S550-0001 thru S550-0160 20.0 lbs. at +288.0 in. 552 20.0 lbs. at +308.0 in. 560 Citation V and Ultra, S/N 560-0001 thru 560-0538 37.8 lbs. at +335.6 in. 560XL, S/N 560-5001 to 560-6000 37.5 lbs. at +335.6 in. 560XL, S/N 560-6001 and On 48.1 lbs. at +300.3 in. 560 Encore, S/N 560-0539 thru 560-0750 47.6 lbs. at +300.1 in. 560 Encore+, S/N 560-0751 thru 560-5000 Rev. 74 Page 35 of 40 A22CE Data Pertinent to all Models (cont’d) NOTE 1. (cont’d) Full oil 34.3 lbs. at +322.0 in. 500 with JT15D-1 en gine 33.1 lbs. at +322.0 in. 500 with JT15D-1A en gine 34.7 lbs. at +367.0 in. 550, S/N 550-0001 thru 550-0800 34.7 lbs. at +367.0 in. S550 31.2 lbs. at +367.0 in. 552 31.3 lbs. at +387.0 in. 560 Citation V, S/N 560-0001 thru 560-0259 32.2 lbs. at +387.0 in. 560 Ultra, S/N 560-0260 thru 560-0538 19.3 lbs. at +366.9 in. 550 Bravo, 550-0801 and On 23.7 lbs. at +433.9 in. 560XL S/N 560-5001 to 560-5500 33.3 lbs. at +438.8 in. 560XL, S/N 560-5501 and On 34.1 lbs. at +387.0 in. 560 Encore and Encore+, S/N 560-0539 thru 560-5000 Hydraulic Fluid 27.5 lbs. at +284.0 in. 500 16.3 lbs. at +341.8 in. 550, S/N 550-0001 thru 550-0733 31.5 lbs. at +300.3 in. S550 and 552 31.5 lbs. at +320.3 in. 560, Citation V and Ultra, S/N 560-0001 thru 560-0538 17.8 lbs. at +342.7 in. 550, S/N 550-0801 and On 34.2 lbs. at +354.0 in. 560XL, S/N 560-5001 to 560-5500 36.1 lbs. at +407.2 in. 560XL, S/N 560-5501 and On 21.7 lbs. at +284.0 in. 560 Encore, S/N 560-0539 thru 560-0750 15.4 lbs. at 228.02 in. 560 Encore+, S/N 560-0571 thru 560-5000 Anti-Ice fluid 15.2 lbs. at +82.3 in. S550 (Airframe) 65.5 lbs. at +86.3 in. 552 Anti-Ice fluid (Windshield) 3.4 lbs. at +91.4 in. 500, 550, S550, 552, and 560 Citation V and Ultra S/N 560-0001 thru 560-0538 3.4 lbs. at +91.5 in. 560 Encore and Encore+, S/N 560-0539 thru 560-5000 NOTE 2. Airplanes must be operated according to the FAA Approved AFM, Part Number as listed in the table below (or later FAA approved revision). All placards required by either the FAA Approved AFM, the applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via Parts List xxxxxxx, Airplane Assembly. A useful placarding reference is the Textron Aviation Illustrated Parts Catalogue (IPC). Any discrepancies identified between the IPC and an aircraft under inspection need to be reconciled using the previously stated parts list. Model AFM P/N (or later FAA approved revision) Airplane Assembly 500 500FM057 5500000 550 (0002-0505) 55FM-41 6500000 550 (0550-0626) 55FMA-02 6500000 550 (0627-0733) 55FMB-05 6500000 550 Bravo 55BFM-06 6500000 S550 S55FM-43 6500000 552 552FM08 6400001 560 Citation V 56FM-11 6500560 560 Ultra 56FMA-08 6500560 560XL(Excel) 56XFM-03 6600000 560XL(XLS) 56XFMA-00 6600000 560XL(XLS+) 56XFMB-00 6600000 560XL(Ascend) 56XFMC-00 (Volume 1) 56XNPC-00 (Volume 2) 56XEAPC-00 (Volume 3) 6600000 560 Encore 56FMB-01 6500560 560 Encore+ 56FMC-00 6500560 NOTE 3. See Maintenance Manua l, Chapter 4, "Airworthiness Limitations" for inspections, mandatory retirement life information, and other requirements for continued airworthiness. A22CE Page 36 of 40 Rev. 74 Data Pertinent to all Models (cont’d) NOTE 4. All Model 500, 550, 552, S 550 and 560 replacement seats (crew and passenger), although they may comply with TSO C39, must also be demonstrated to comply with the installation requirements of Part 25 paragraphs as shown in the certification basis. All Model 560XL replacement seats (crew and passenger), although they may comply with TSO C127, must also be demonstrated to comply with the installation requirements of Part 25 paragraphs as shown in the certification basis. For Model 560XL, the seat cushion foam buildup of all seats (crew and passenger) may not be altered unless the deviations in the foam construction or stiffness are shown to comply with the requirements of Part 25 paragraphs as shown in the certification basis. NOTE 5. Model 500, S/N 500-0001 thru 500-0070, are elig ible for the Maximum Weights and C.G. Range applicable to S/N 500-0071 and on when modified in accordance with Cessna Service Bulletin SB32-1. Model 500, S/N 500-0001 thru 500-0302, are eligible for Maximum Weights and C.G. Range applicable to S/N 500-0303 and on when modified in accordance with the following Cessna Service Bulletins: S/N 500-0001 thru 500-0040, SB 30-1, SB32-1, SB32-23 S/N 500-0041 thru 500-0070, SB32-1, SB32-23 S/N 500-0071 thru 500-0302, SB32-23 Model S550, S/N S550-0001 thru S550-0085, are eligible for the Maximum Weights and C.G. Range applicable to S/N S550-0086 and on when modified in accordance with Cessna Service Bulletin SBS550-11-1. NOTE 6. Airplanes in compliance with ECR EC00002 and ECR EC07682, Model 500 and 550, respectively, comply with French Certification requirements of the DIRECTION GENERALE DE L'AVIATION CIVILE of France. Such aircraft are identified by a prefix letter "F" at the beginning of the manufacturer's serial number. Examples: F500-XXXX(500) or F550-XXXX(550). NOTE 7. Model 500, S/N 500-0001 thru 500-0349, conforming to ECR 500-1048 or SB34-15 are eligible for 9,500 lbs. zero fuel weight with VMO reduced to 275 KCAS from 14,000 ft. to 28,000 ft. Aircraft conforming to ECR EC01164 or SB34-23 are eligible for 10,500 lb. zero fuel weight with VMO reduced to 260 KCAS from 14,000 ft. to 30,500 ft. Model 500, S/N 500-0350 and on, conforming to ECR EC04139 or SB34-15 are eligible for 9,500 lb. zero fuel weight with VMO reduced to 260 KCAS from 14,000 ft. to 30,500 ft. Model 550, S/N 550-0001 thru 550-0549, conforming to ECR EC04574 or SB550-34-4 are eligible for 11,000 lbs. zero fuel weight with VMO reduced to 260 KCAS from 14,000 ft. to 30,500 ft. 11,000 lbs. zero fuel weight provision is standard at S/N 550-0550 thru 550-0800. Model 560, S/N 560-0001 thru 560- 0259, conforming to ECR 26053 are eligible for 12,200 lbs. zero fuel weight with VMO reduced to 275 KCAS from 8,000 ft. to 31,400 ft. NOTE 8. Model 500, S/N 500-0275 and on, conforming to ECR EC02446 and aircraft. S/N 500-0001 and on modified in accordance with Cessna Service Bulletin SB25-17 are eligible to carry a maximum of 9 people. NOTE 9. Per Cessna Service Bulletin SB72-2, a JT15D-1A or JT15D-1B used in combination with at JT15D-1, is required to be operated to JT15D-1 engine limitations. NOTE 10. Model 500, S/N 500-0001 thru 500-0213, are eligible for operation at 41,000 ft. when modified in accordance with Cessna Service Bulletin SB21-9. NOTE 11. Per Cessna Service Bulletin SB72- 2, a JT15D-1B used in combination with a JT15D-1A, is required to be operated to JT15D-1A engine limitations. NOTE 12. Model 550, S/N 550-0021 thru 550-0505 and S/N 550-0550 thru 550-0800, conforming to ECR EC08691 are eligible to carry a maximum of 13 people. NOTE 13. Approved nose gear tires are limited to those listed in the Limitations Section of the FAA Approved Airplane Flight Manual (AFM). Rev. 74 Page 37 of 40 A22CE Data Pertinent to all Models (cont’d) NOTE 14. Production Certificate No. PC-4 issued May 7, 19 98. Applies to the following airplanes and serial numbers: Model 500 beginning at S/N 500-0687 thru 500-0689; Model 550 beginning at S/N 550-0550 thru 550-0800; Model S550 beginning at S/N S550-0034 thru S550-0160; Model 552 beginning at S/N 552-0012 thru 552-0015; Model 560 (Citation V and Citation Ultra) S/N 560-0001 thru 560-0538; Model 550 (Bravo) S/N 550-0801 and on; Model 560XL beginning at S/N 560-5001 and on; Model 560 Encore beginning at S/N 560-0539 thru 560-0750 and Encore+ S/N 560-0751 thru 560-5000. NOTE 15. The Model 552 is approved with a five-inch removable nose plug assembly installed between the radome and nose fuselage structure, as defined by Cessna ECR EC21789. No Flight Manual changes are required. NOTE 16. Model S550, S/N S550-0121 thru S550-0160, are eligible for German configuration and meet the certification requirements of Luftfahrt-Bundesamt of the Federal Republic of Germany when modified in accordance with Cessna ECR EC20308 and CR00206. NOTE 17. Deleted. NOTE 18. For the Model 500, the first 349 airplanes are identified by serial number only, i.e., S/N 500-0001 thru 500-0349. Contact Cessna Customer Service regarding Model 500 unit number and airplane serial number effectivity. NOTE 19. For the Model 550, the unit number and the airpla ne serial number may not coincide until unit number 439 (S/N 550-0439). Contact Cessna Customer Service regarding Model 550 unit number and airplane serial number effectivity. NOTE 20. Model S550 airplanes conforming to Cessna Dr awing 6590002-2 and Model 560 airplanes conforming to Cessna Drawing 6590561-1 or -2 (for public transport or private category operation, respectively) comply with the certification requirements of the DIRECTION GENERALE DE L'AVIATION CIVILE OF FRANCE. Airplanes so modified or so constructed retain their original unit/serial number identification. NOTE 21. Model 550, S/N 550-0001 thru 550-0505 and S/N 550- 0550 thru 550-0626, when modified in accordance with Cessna Service Bulletin SB550-32-14 and Model S550, S/N S550-0001 thru S550-0160, when modified in accordance with Cessna Service Bulletin SBS550-32-08 are eligible to operate at the following VLO and VLE: Model 550 - SB550-32-14 Model S550 – SBS550-32-08 11,000 9,500 lbs. ZFW lbs. ZFW Gravel Kit Std. Acft. Gravel Kit VLO (Landing gear operating extend) 248 KCAS 248 KCAS 198 KCAS 250 KCAS 200 KCAS VLO (Landing gear operating retract) 198 KCAS 198 KCAS 198 KCAS 202 KCAS 200 KCAS VLE (Landing gear extended) 260 KCAS 275 KCAS 198 KCAS 278 KCAS 202 KCAS NOTE 22. Model 560 Citation V and Ultra, S/N 560-0001 thru 560-0538, airplanes conforming to ECR 26053, 12,200 ZFW Option and conforming to ECR 26155, Gravel Kit, the following VLO's and VLE's apply: Model 560 (Citation V and Ultra) 12,200 lbs. ZFW Gravel Kit ECR 26053, Rev. D ECR 26155, Rev. C VLO (Landing gear operating extend) 249 KCAS 199 KCAS VLO (Landing gear operating retract) 199 KCAS 199 KCAS VLE (Landing gear extended) 275 KCAS 199 KCAS ECR 26053, 12,200 ZFW Option is applicable to S/N 560-0001 through 560-0259. NOTE 23. Model 552, S/N 552-0001 thru S/N 552-0011, S/N 552-0013, and S/N 552-0015, destroyed. S/N 552-0012 and S/N 552-0014 are permanently out of service. NOTE 24. Deleted. A22CE Page 38 of 40 Rev. 74 Data Pertinent to all Models (cont’d) NOTE 25. Model 550 (Bravo) increase the ma ximum operating altitude from 41,000 feet to 45,000 feet when modified in accordance with the following Cessna Service Bulletins: S/N 550-0801 thru 550-0808, Cessna Service Bulletin SB550-03-03. S/N 550-0809 thru 550-0820 and S/N 550-0822 thru 550-0823, Cessna Service Bulletin SB550-34-64. NOTE 26. Certain models have been approved for high alti tude operations (altitudes above 41,000 feet), either by Special Conditions or compliance with certain Part 25 sections. Any modifications to the pressure vessel must be approved in accordance with the requirements as shown in the appropriate certification basis. This includes modifications which could result in a pressure vessel opening, either through crack-growth or antenna loss, greater than the specified areas as follows: Model 550 (Bravo) S/N 550-0801 and on 4.00 s q. in. Model 560 (Citation V and Ultra) S/N 560-0001 thru 560-0538 4.00 s q. in. Model 560XL 3.98 s q. in. Model 560 (Encore and Encore+) S/N 560-0539 thru 560-5000 4.00 s q. in. NOTE 27. Model 560XL, S/N 560–5001 thru 560-5500. Left divide r assembly (part no. 6679017-1) or equivalent must always be installed when the LH aft toilet or LH aft side-facing seat installed and approved for occupancy during takeoff and landing. The structural divider is an integral part of the seat restraint system. Model 560XL, S/N 560–5501 thru 560-6000. Left divider assembly (part no. 4589029-1) or equivalent must always be installed when the LH aft toilet or LH aft side-facing seat installed and approved for occupancy during takeoff and landing. The structural divider is an integral part of the seat restraint system. Model 560XL, S/N 560–6001 and on. Left divider assembly (part no. 4569035-1) or equivalent must always be installed when the LH aft toilet or LH aft side-facing seat is installed and approved for occupancy during takeoff and landing. The structural divider is an integral part of the seat restraint system. Model 560XL, S/N 560–6501 and on. Lefthand aft divider assembly (part no. 4569623) or equivalent must always be installed when the LH aft side-facing seat is installed and approved for occupancy during takeoff and landing. This structural divider is an integral part of the seat restraint system and may not be structurally altered, unless the changes are shown to comply with the requirements of 14 CFR Part 25 paragraphs as shown in the certification basis. NOTE 28. Models 500, 550 (S/N 550-0001 thru 550-0505 and 550-0550 thru 550-0800), S550, 552, and 560 (S/N 560- 0001 thru 560-0259 and 560-0260 thru 560-0538). Special Condition #applies to the following: a. Operation without normal electrical power. b. Limit Maneuvering load fa ctor, in lieu of 25.337(b). c. Turbulence criteria. d. Vibration and buffeting, in lieu of 25.251(c). e. Engine exhaust system drains. f. Engine bleed air system. g. Engine inflight restart capability. h. Engine thrust control. i. Powerplant installation fault analysis. j. Turbine engine powerplant installation, in lieu of 25.903(d). k. Engine ignition system. l. Powerplant shutoff means, in addition to 25.1189. NOTE 29. Model 560XL (effective for all va riants) Equivalent Level of Safety (ELOS) for 14 CFR 25.815, Passenger Cabin Aisle Width, allows a minimum aisle width of 13 inches from 25 inches to 27.5 inches measured from the floor and 15 inches above 27.5 inches measured from the floor for passenger configurations up to and including 12 passengers Rev. 74 Page 39 of 40 A22CE NOTE 30. Certain Models meet the initial airworthiness re quirements for operation in Reduced Vertical Separation Minimum (RVSM) airspace. Model 500 Citation/Citation I S/N 500-0275 thru 500-0689 that have accomplished Cessna Service Bulletin SB500-34-65. Model 550 Citation II S/N 550-0002 thru 550-0800 that have accomplished Cessna Service Bulletin SB550-34-79. Model S550 Citation SII S/N S550-0001 thru S550-0160 that have accomplished Cessna Service Bulletin SBS550-34-36. Model 560 Citation V S/N 560-0001 thru 560-0259 that have accomplished Cessna Service Bulletin SB 560-34-97. Model 560 Ultra S/N 560-0260 thru 560-0525 that have accomplished Cessna Service Bulletin SB560-34-79, and S/N 560-0526 thru 560-0538. Model 550 Bravo S/N 550-0801 thru 550-0872 that have accomplished Cessna Service Bulletin SB550-34-70, and S/N 550-0873 and On. Model 560XL S/N 560-5001 and On. Model 560 Encore Model 560 Encore+ S/N 560-0539 thru 560-0750 S/N 560-0751 thru 560-5000. Each operator must obtain RVSM operating approval directly from the FAA. NOTE 31. Model 560 aircraft S/N 560-0387, -0392, -0404, -0410, -0415, -0420, -0426, -0452, -0456, -0462, -0468, -0472, -0495, -0501, -0505, -0508, -0513, -0524, -0529, -0532, -0534, and -0538 modified per EC 46497 are eligible to operate at the following C.G. range and increased weights. C.G. Range: Forward Limits: Linear variation fro m 293.71 in. aft of datum (15% MAC) at 11,500 lbs. or 293.71 in. aft of datum (15% MAC) at 11,500 lbs. or less, to 296.35 in aft of datum (18.26 % MAC) at 16,500 lbs. or 296.95 in. aft of datum (19% MAC) at 16,850 lbs. Aft Limits: 304.23 in. aft of datum (28% MAC) at 16,850 lbs. or less Maximum Weight Takeoff 16,650 lbs. Ramp 16,850 lbs. Landing 15,200 lbs. Zero fuel 12,200 lbs. NOTE 32. Model 560XL, S/N 560-5001 thru 560-5500, modified per SB560XL-32-28: C.G. Range (Landing Gear Extended): Forward Limits: Linear variation from 319.47 in. aft of datum (15.81% MAC) at 12,400 lbs. to 324.30 in. aft of datum (21.54% MAC) at 20,400 lbs. Aft Limits: 331.26 in. aft of datum (30% MAC) from 12,400 lbs. thru 15,000 lbs. Linear variation from 330.74 in. aft of datum (30% MAC) at 15,000 lbs. to 331.26 in. aft of datum (29.37% MAC) at 17,800 lbs. 330.74 in. aft of datum (29.37% MAC) from 17,800 lbs. thru 20,400 lbs. Maximum Weight Takeoff 20,200 lbs. Landing 18,700 lbs. Zero fuel 15,100 lbs. Ramp 20,400 lbs. Minimum Weight Inflight 12,400 lbs. A22CE Page 40 of 40 Rev. 74 Data Pertinent to all Models (cont’d) NOTE 33. Model 560, S/N 560-0539 thru 560-0750, modified per SB560-32-40: C.G Range (Landing Gear Extended) Forward Limits: Linear variation from 296.14 in. aft of datum (18.0% MAC) at 12,400 lbs.; 296.14 in. aft of datum (18.0% MAC) at 12,400 lbs. or less, to 299.43 in. aft of datum (22.07% MAC) at 17,030 lbs. Aft Limits: 304.23 in. aft of datum (28.0% MAC) at 17,030 lb. or less. Maximum Weight Takeoff 16,830 lbs. Landing 15,200 lbs. Zero Fuel 12,850 lbs. Ramp 17,030 lbs. NOTE 34. The following serials are manufacture d under the name Cessna Aircraft Company: 560XL: 560-5001 thru 560-6191. NOTE 35. Company name change effect ive 7/29/15. The following serials are manufactured under the name Textron Aviation Inc.: 560XL: 560-6192 and On. NOTE 36. Handheld Fire Extinguishers Required Equipment (all models and variants, except 560XL Ascend): The basic required equipment prescribed in the applicable airworthiness requirements (see certification basis) must be installed in the aircraft. Only handheld fire extinguishers containing Halon 1211 (BCF, CBrCIF2), Halotron BrX (2-BTP, C3H2BrF3), or Halotron I (HCFC Blend-B, C2HCI2BrF3) are approved for use. No airplanes may have any combination of dissimilar agents installed on a particular unit. Required Equipment (560XL Ascend): Halotron BrX (2-BTP, C3H2BrF3) -------- END ------- ``` ## ADs (52, first 50, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2025-11-09](https://openairdocs.org/ad/2025-11-09): Fire Protection · Textron 560 and 560XL. Effective Jul 11, 2025 - [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2020-26-05](https://openairdocs.org/ad/2020-26-05): POWER LEVER · Textron 560XL. Effective Dec 17, 2020 - [AD 2017-04-14](https://openairdocs.org/ad/2017-04-14): Electrical power · Textron 560XL. Effective Mar 9, 2017 - [AD 2015-17-12](https://openairdocs.org/ad/2015-17-12): Air conditioning · Freon air conditioning system (Textron STC SA3849SW or 3 others). Effective Sep 29, 2015 - [AD 2012-26-15 R1](https://openairdocs.org/ad/2012-26-15-R1): Navigation · Agusta AW139, A318-111, A318-112 and 70 more. Effective Dec 3, 2014 - [AD 2014-18-01](https://openairdocs.org/ad/2014-18-01): Navigation · Bombardier ATR42-200, ATR42-300, ATR42-320 and 23 more. Effective Oct 14, 2014 - [AD 2013-09-11](https://openairdocs.org/ad/2013-09-11): Air Conditioning · Cessna 500, 501, 550 and 5 more. Effective Jul 5, 2013 - [AD 2012-09-01](https://openairdocs.org/ad/2012-09-01): Landing Gear · Cessna 560XL. Effective Jun 7, 2012 - [AD 2012-06-01](https://openairdocs.org/ad/2012-06-01): Fuselage · Cessna 560XL. Effective Apr 25, 2012 - [AD 2010-07-02](https://openairdocs.org/ad/2010-07-02): Integrated navigation units (INUs) · 328 Support Services 328-100, 328-300, Jetstream Model 4101 and 26 more. Effective May 3, 2010 - [AD 2008-26-04](https://openairdocs.org/ad/2008-26-04): Airspeed placards · Cessna 560. Effective Jan 28, 2009 - [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008 - [AD 2007-11-17](https://openairdocs.org/ad/2007-11-17): Wires for the positive and negative terminal studs of the engine and/or auxiliary power unit (APU) fire extinguishing bottles. · Cessna 500, 501, 550 and 5 more. Effective Jul 6, 2007 - [AD 2006-19-04](https://openairdocs.org/ad/2006-19-04): Honeywell COM unit and Mode S transponder · Bombardier BD-700-1A10, BD-700-1A11, 550 and 26 more. Effective Oct 17, 2006 - [AD 2006-06-03](https://openairdocs.org/ad/2006-06-03): Airplane flight manual (AFM) · Cessna 500, 501, 550 and 3 more. Effective Apr 20, 2006 - [AD 2004-08-15](https://openairdocs.org/ad/2004-08-15): TAWS8000 terrain awareness warning systems (TAWS) · Cessna 421, 500, 501 and 18 more. Effective Jun 7, 2004 - [AD 2004-09-05](https://openairdocs.org/ad/2004-09-05): Brake Stator Disks · Cessna 500, 501, 550 and 1 more. Effective Jun 2, 2004 - [AD 2003-23-02](https://openairdocs.org/ad/2003-23-02): Ptich trim and autopilot servo · Cessna 560. Effective Nov 28, 2003 - [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001 - [AD 2001-22-14](https://openairdocs.org/ad/2001-22-14): Fire Extinguishing System Bottle Cartridges · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 105 more. Effective Dec 10, 2001 - [AD 2001-14-09](https://openairdocs.org/ad/2001-14-09): Wiring of the Landing Light Switch and theJ-Box Fairing Light Relays · Cessna 560XL. Effective Jul 26, 2001 - [AD 2000-15-51](https://openairdocs.org/ad/2000-15-51): Aileron Cable Fairlead Tube and Aileron Cable Sector · Cessna 560XL. Effective Aug 14, 2000 - [AD 2000-03-09](https://openairdocs.org/ad/2000-03-09): Residual Ice · Cessna 560 and 560XL. Effective Apr 3, 2000 - [AD 97-05-03 R1](https://openairdocs.org/ad/97-05-03-R1): Global Positioning Systems · BAE Systems Avro 146-RJ100A, BAe 146-200A, Jetstream Model 4101 and 27 more. Effective Apr 20, 1999 - [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 98-04-38](https://openairdocs.org/ad/98-04-38): AFM - Limitations Section - Icing · Cessna 500, 501, 550 and 2 more. Effective Mar 25, 1998 - [AD 95-25-10](https://openairdocs.org/ad/95-25-10): Outflow/Safety Valve · Cessna 441, 500, 550 and 1 more. Effective Jan 22, 1996 - [AD 95-22-01](https://openairdocs.org/ad/95-22-01): Fluorescent Lighting System · Aerospace Lighting Fluorescent lighting systems, A310-203, A310-204 and 74 more. Effective Dec 4, 1995 - [AD 94-19-06](https://openairdocs.org/ad/94-19-06): Crew Oxygen Masks · 328 Support Services 328-100, 328-300, 500 and 17 more. Effective Oct 6, 1994 - [AD 94-01-04](https://openairdocs.org/ad/94-01-04): Traffic Alert and Collision Avoidance System · Airbus A300 B4-601, A300 B4-603, A300 B4-605R and 136 more. Effective Feb 4, 1994 - [AD 93-05-15](https://openairdocs.org/ad/93-05-15): Thrust Reverser Throttle Load Limiter · Cessna 500, 501, 550 and 4 more. Effective Apr 23, 1993 - [AD 90-07-10 R1](https://openairdocs.org/ad/90-07-10-R1): Air Conditioning System · Cessna 550, 551 and S550 with STC SA2698SW. Effective May 29, 1990 - [AD 90-06-13](https://openairdocs.org/ad/90-06-13): Vertical Gyro · Bombardier DHC-8-101, DHC-8-102, DHC-8-103 and 14 more. Effective Mar 30, 1990 - [AD 89-16-10](https://openairdocs.org/ad/89-16-10): Fuel Flow Transmitter · Cessna 550 and 551. Effective Sep 7, 1989 - [AD 88-13-03 R1](https://openairdocs.org/ad/88-13-03-R1): Cotter Pins - Main Landing Gear · Cessna S550. Effective Mar 15, 1989 - [AD 88-24-16](https://openairdocs.org/ad/88-24-16): Cabin Electrical Power · Cessna 650 and S550. Effective Dec 12, 1988 - [AD 88-11-07](https://openairdocs.org/ad/88-11-07): Flap Panels · Cessna 552 and S550. Effective Jul 21, 1988 - [AD 88-06-02](https://openairdocs.org/ad/88-06-02): Electrical Power · Cessna 550 and S550. Effective May 10, 1988 - [AD 85-24-04](https://openairdocs.org/ad/85-24-04): AFM Revised Placard - Icing · Cessna S550. Effective Feb 24, 1986 - [AD 85-25-10](https://openairdocs.org/ad/85-25-10): Placard - Icing Conditions · Cessna 552 and S550. Effective Feb 11, 1986 - [AD 85-03-51](https://openairdocs.org/ad/85-03-51): Aircraft Battery Inspection · Cessna 552 and 650. Effective Apr 11, 1985 - [AD 80-09-09](https://openairdocs.org/ad/80-09-09): Dual Flight Director Installation · Cessna 500, 501, 550 and 1 more. Effective May 12, 1980 - [AD 79-12-06](https://openairdocs.org/ad/79-12-06): Upper & Lower Spar Cap Stems · Cessna 500, 501, 550 and 1 more. Effective Apr 10, 1980 - [AD 73-26-09](https://openairdocs.org/ad/73-26-09): Flight Compartment Side Windows · Cessna 500. Effective Oct 9, 1974 - [AD 2012-26-15](https://openairdocs.org/ad/2012-26-15) (historical): Navigation · Agusta AW139, A318-111, A318-112 and 71 more. Effective Jan 24, 2013 - [AD 2007-23-13](https://openairdocs.org/ad/2007-23-13) (historical): Installing new minimum airspeed placards · Cessna 560. Effective Nov 30, 2007 - [AD 2006-22-05](https://openairdocs.org/ad/2006-22-05) (historical): Integrated navigation units (INUs) · 328 Support Services 328-100, 328-300, Jetstream Model 4101 and 27 more. Effective Dec 1, 2006 All 52: https://openairdocs.org/tcds/A22CE/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Cessna 560](https://openairdocs.org/model/cessna-560): 596 aircraft (registry code 2076750) - [Cessna 560XL](https://openairdocs.org/model/cessna-560xl): 585 aircraft (registry codes 2076702, 2076704) - [Cessna 550](https://openairdocs.org/model/cessna-550): 500 aircraft (registry code 2076604) - [Textron 560XL](https://openairdocs.org/model/textron-560xl): 141 aircraft (registry code 2076710) - [Cessna S550](https://openairdocs.org/model/cessna-s550): 94 aircraft (registry codes 2076607, 2076610) - [Cessna 500](https://openairdocs.org/model/cessna-500): 62 aircraft (registry code 2076602) - [Textron 560](https://openairdocs.org/model/textron-560): 1 aircraft (registry code 2076708) - [Cessna 552](https://openairdocs.org/model/cessna-552): 0 aircraft (registry code 2076606) - [Textron 560XLS+](https://openairdocs.org/model/textron-560xls-plus): 0 aircraft (registry code 2076712) ## STCs approved under this data sheet (566, first 50) - [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST01823WI](https://openairdocs.org/stc/ST01823WI): Installation of Garmin GTS Traffic Sensor with Garmin GTX 3000 Mode S Transponders with ADS-B Out.. Blackhawk Aerospace Technologies Inc. - [STC ST04201NY](https://openairdocs.org/stc/ST04201NY): Installation of ENode Engine Data Acquisition Unit & IONode Digital Data Recorder. TBO Extension, LLC - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST12344IB](https://openairdocs.org/stc/ST12344IB): Replacement of the Halon Type 1211 portable fire extinguisher with Halotron BrX portable fire extinguisher with Halotron BrX portable fire extinguisher. Cessna Duesseldorf Citation Service Center GmbH - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC ST04805NY](https://openairdocs.org/stc/ST04805NY): Installation Gogo Connectivity System. Delta Engineering Corporation - [STC ST02016WI](https://openairdocs.org/stc/ST02016WI): Installation of the Meggitt Wireless Tire Pressure Sensor. 3S Certification LLC - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST00390BO](https://openairdocs.org/stc/ST00390BO): Installation of a SmartSky Networks Air to Ground Data Link System. Apcela IFC JV, LLC dba Apcela ATG - [STC ST04604CH](https://openairdocs.org/stc/ST04604CH): INSTALL SMARTSKY FLAGSHIP SYSTEM. Apcela IFC JV, LLC dba Apcela ATG - [STC ST11216DS](https://openairdocs.org/stc/ST11216DS): Installation of automatic dependent surveillance-broadcast (ADS-B) out on Part 25 aircraft. BHE & Associates Ltd. - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST02718LA](https://openairdocs.org/stc/ST02718LA): Modification to replace the existing standby instrument. Acron Aviation Inc. - [STC ST03292CH](https://openairdocs.org/stc/ST03292CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development, Inc. - [STC ST12042WI](https://openairdocs.org/stc/ST12042WI): Upgrade of AirCell High Speed Internet System to Gogo Business Aviation C1 System. Duncan Aviation Inc. - [STC ST09854AC](https://openairdocs.org/stc/ST09854AC): Installation of a Lumin Media Server. L2 Aviation - [STC ST155CH](https://openairdocs.org/stc/ST155CH): Installation of BF Goodrich Avionics systems TCAS791 traffic alert and collison avoidance system I (TCASI).. Acron Aviation Inc. - [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc. - [STC ST04730NY](https://openairdocs.org/stc/ST04730NY): Installation of Battery Temperature Indicator. Aero-Mach Labs Inc. - [STC ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine - [STC ST02804SE](https://openairdocs.org/stc/ST02804SE): Installation of Starlink Aviation System. AeroMech Incorporated - [STC ST01979WI](https://openairdocs.org/stc/ST01979WI): Installation of Gogo Business Aviation AVANCE L5/X3 System or optional AVANCE LX5 System. Gogo Business Aviation LLC - [STC ST04742NY](https://openairdocs.org/stc/ST04742NY): Installation of SkyVue 1000 Cockpit Upgrade including dual Avidyne IFD540 FMS with LPV i. Aerospace Design & Compliance LLC - [STC ST01833WI](https://openairdocs.org/stc/ST01833WI): Modification of a Rockwell Collins Global Positioning System (GPS) installation. Rockwell Collins Inc. - [STC ST01918WI](https://openairdocs.org/stc/ST01918WI): Installation of Garmin G5000 Integrated Flight Deck. Garmin International Inc. - [STC ST04736NY](https://openairdocs.org/stc/ST04736NY): True Blue TS28 Emergency Battery Power Supply Replacement. Aerospace Design and Compliance LLC - [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC - [STC ST01083DE](https://openairdocs.org/stc/ST01083DE): Installation of the Aviation Clean Air Airborne Air & Surface Purification System. Lee Aerospace, Inc. - [STC ST04159CH](https://openairdocs.org/stc/ST04159CH): Upgrade of Honeywell Primus II Communications Units RCZ-8XX Transponders to support Certification of Automatic Dependent Surveillance -Broadcast (ADS-B) Out. CMD Flight Solutions LLC - [STC ST02427LA](https://openairdocs.org/stc/ST02427LA): Installation of Dual Garmin GTN 6XX/7XX Series Global Navigation System with Structural Antenna and WAAS approval; Garmin GMA 35 Audio Panel; and Dual Garmin GTX 33 Mode S Transponders, Weather Radar, and ADS-B Link. JETTECH LLC - [STC ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC - [STC ST04575AT](https://openairdocs.org/stc/ST04575AT): Installation of the Rockwell Collins ALT-1000+/ -4000+ with 5G Filtering. Chippewa Aerospace Inc. - [STC ST02029WI](https://openairdocs.org/stc/ST02029WI): Installation of Garmin GI 275 Standby Instrument and GSB 15 USB Port. Blackhawk Aerospace Technologies - [STC SA1773SO](https://openairdocs.org/stc/SA1773SO): Installation of a third stand-by attitude gyro and dedicated power supply AIM P/N PE 24-1RM. Summit Aviation Inc - [STC ST02444AT-D](https://openairdocs.org/stc/ST02444AT-D): Installation of a Honeywell Mark VIII EGPWS System.. Summit Aviation Inc. - [STC ST00116MC](https://openairdocs.org/stc/ST00116MC): Installation of an Avionics Upgrade consisting of a Data-Link System, a High Frequency Radio System, and a Tactical Air Navigation System. L3Harris Technologies Integrated Systems L.P. - [STC ST00129MC](https://openairdocs.org/stc/ST00129MC): Installation of a Cabin Communication System consisting of a Satellite Communications System and an In-Flight Internet System. L3Harris Technologies Integrated Systems L.P. - [STC ST11217DS](https://openairdocs.org/stc/ST11217DS): Installation of search and rescue upgrade to the factory installed Rockwell Collins Pro Line 21 Flight Management System (FMS-3000). Textron Aviation Inc. - [STC ST01070DE](https://openairdocs.org/stc/ST01070DE): Installation of the Curtiss-Wright Fortress Flight Data Recorder (with Cockpit Voice Recorder). Peregrine - [STC SA7408SW](https://openairdocs.org/stc/SA7408SW): Installation of Heads Up checklist(electronic verbal checklist).. Heads Up Technologies Inc. - [STC ST00098IB](https://openairdocs.org/stc/ST00098IB): Introduction of ADS-B Out. STC Twenty One Limited - [STC ST01985WI](https://openairdocs.org/stc/ST01985WI): Installation of the Garmin GI-275 I Electronic Standby Instrument (ESI). Peregrine - [STC ST02004WI](https://openairdocs.org/stc/ST02004WI): Installation of the Garmin GI-275 Instantaneous Vertical Speed Indicators (IVSI). Peregrine - [STC ST00011WI](https://openairdocs.org/stc/ST00011WI): Installation of Concorde RG380E/40 and 40B battery.. Aero-Mach Wilco LLC - [STC SA1297GL](https://openairdocs.org/stc/SA1297GL): Installation of Cleveland main wheels and brakes.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA1441GL](https://openairdocs.org/stc/SA1441GL): Installation of Cleveland Main Wheels and Brakes.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA882GL](https://openairdocs.org/stc/SA882GL): Install aircraft wheel and brake conversion kit 199-137.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC ST01994WI](https://openairdocs.org/stc/ST01994WI): Installation of Honeywell Primus Elite Enhanced Functionality Modification and Honeywell Primus Elite Drop-in Modification.. TurboJet Engineering Pty Ltd All 566: https://openairdocs.org/tcds/A22CE/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.