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TYPE CERTIFICATE DATA SHEET Nº EA-9001

Type Certificate Holder:

TEXTRON AVIATION INC. P.O. Box 7704 Wichita, KA - 67277 USA

EA-9001-07 Sheet 01

TEXTRON

560 , 550 ,560XL

20 June 2017

This data sheet, which is part of Type Certificate No. 9001 prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the airworthiness requirements of the Brazilian Aeronautical Regulations.

I - Model 560 Citation V (Transport Category), approved 12 April 1990. Model 560 Citation Ultra (Transport Category), approved 20 November 1995.

ENGINE S/N 560-0001

through 560-0259 Two Pratt & Whitney of Canada Inc. JT15D-5A turbofans.

S/N 560-0260 through 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 and fueling procedures, refer to the Brazilian Approved Airplane Flight Manual.

ENGINE LIMITS Static thrust, standard day, sea level – daN (lb): JT15D-5A JT15D-5D Takeoff (5min.) 1 290 (2 900) 1 354 (3 045) Max. continuous 1 290 (2 900) 1 354 (3 045) Max. permissible engine rotor operating speeds - % (rpm): JT15D-5A JT15D-5D N1 (Fan) 104 (16 540) 100 (16 860) N2 (Gás Gen.) 96 (31 450) 97 (31 777) Max. permissible interturbine gas temperatures - C: JT15D-5A JT15D-5D Takeoff 700 720 Max. continuous 680 700 Transient (20 seconds) 720 740 Starting 550 550 OIL According to CPW spec. 521 and listed in PWA S.B.700.

TEXTRON 20 June 2017 EA-9001-07 Sheet 2/30

AIRSPEED LIMITS (CAS) Maximum operating (VMO): - Sea level to 2 438 m (8 000 ft) 260 kcas (261 kias) - 2 438m (8 000 ft) to 8 811m (28 907 ft) 290 kcas (292 kias)* Maximum operating (MMO): - Above 8 811m (28 907 ft) 0.75 Mach (0.755

Mias) Maneuvering (VA) - sea level: - 7 212 kg (15 900 lb) 201 kcas (202 kias) - See AFM for variations with weight and altitude. Flaps extended (VFE): - 35° (landing) 174 kcas (173 kias) - 15° (takeoff and approach) 199 kcas (200 kias) - 7° (takeoff) 199 kcas (200 kias) *See note 6 for restricted VMO for optional fuel weight

configuration. Minimum control speed - Air (VMCA) 84 kcas (85 kias) Minimum control speed - Ground (VMCG) 85.5 kcas (86 kias) L. G. operation - extend (VLO) 249 kcas (250 kias) L. G. operation - retract (VLO) 199 kcas (200 kias) L. G. extended (VLE) 290 kcas (292 kias) See note 9 for VLO and VLE for 5 534 kg (12 200 lb) ZFW option

and gravel kit. Speed Brakes extended (VSG): any speed with or without flaps TIRE LIMIT Maximum ground speed 165 knots CG RANGE For S/N 560-0001 through 560-0259 (Landing Gear Extended) Forward Limits: Linear variation from 751.91 cm (296.03 in) aft of

datum (17.87% MAC) at 7 212 kg (15 900 lb) to 746.02 cm (293.71 in) aft of datum (15.0 % MAC) at 5 216 kg (11 500 lb); 746.02 cm (293.71 in) aft of datum (15.0% MAC) at 5 216 kg (11 500 lb) or less.

Aft limits: 772.74 cm (304.23 in) aft of datum (28.0% MAC) at 7 212 kg (15 900 lb) or less.

For S/N 560-0260 through 560-0538 ** Forward limits: Linear variation from 752.45 cm (296.24 in) aft of

datum (18.13% MAC) at 7 394 kg (16 300 lb) to 746.02 cm (293.71 in) aft of datum (15.0% MAC) at 5 216 kg (11 500 lb); 746.02 cm (293.71 in) aft of datum (15.0% MAC) at 5 216 kg (11 500 lb) or less.

Aft limits: 772.74 cm (304.23 in) aft of datum (28.0% MAC) at 7 394 kg (16 300 lb) or less.

** See NOTE 16 EMPTY WEIGHT CG RANGE None. DATUM 238.7 cm (94.0 in) forward of the front face of the forward

pressure bulkhead. LEVELING MEANS Seat rails. MEAN AERODYNAMIC CHORD 205.7 cm (80.98 in) - L.E. of MAC at sta. +715,2 cm (281.56 in)

Note: This is reference MAC for basic wing without leading edge cuff and tip.


MAXIMUM WEIGHT S/N 560-0001 through 560-0259

S/N 560-0260 through 560-0538**

Takeoff: 7 212 kg (15 900 lb) 7 394 kg(16 300 lb) Landing: 6 895 kg (15 200 lb) 6 895 kg(15 200 lb) Zero Fuel: 5 080 kg (11 200 lb)* 5 534 kg(12 200 lb) Ramp: 7 303 kg (16 100 lb) 7 484 kg(16 500 lb) * See note 6 for optional zero fuel weight.

** See Note 16 MINIMUM CREW For all flights: 2 persons (pilot and co-pilot) MAXIMUM PASSENGERS 13 (2 pilots, 11 passengers) MAXIMUM BAGGAGE Nose compartment

S/N 560-0001 through 560-0259

158.8 kg (350 lb) at Sta 188.0 cm (74.0 in)

Nose compartment S/N 560-0260 through 560-0538

140.6 kg (350 lb) at Sta 188.0 cm (74.0 in)

Aft Cabin: 272.2 kg (600 lb) at Sta 883.9 cm (348.0 in) Tailcone 136.1 kg (300 lb) at Sta 1102.4 cm (434.0 in)

90.7 kg (200 lb) at Sta 1173.5 cm (462.0 in) FUEL CAPACITY Two wing tanks: 1634.7 liters (431.9 US Gal) total each tank 1629.4 liters (430.5 US Gal) usable each tank Arm: +768.9 cm (302.7 in) See note 1 for data on unusable fuel. OIL CAPACITY S/N 560-0001

through 560-0259 Two engine-mounted tanks. 7.67 liters (8.1 US Quarts) total each tank. 4.54 liters (4.8 US Quarts) usable each tank. Arm = +983.0 cm (+387.0 in)

S/N 560-0260 through 560-0538

Two engine-mounted tanks. 7.95 liters (8.4 US Quarts) total each tank. 4.45 liters (4.7 US Quarts) usable each tank. Arm = +983.0 cm (+387.0 in)

WINDSHIELD ANTI-ICE FLUID Capacity: 1.5 kg (3.4 lb)

Arm = +232.2 cm (91.4 in) Approved Anti-Ice Fluids: TT-I-735 Isopropyl Alcohol

MAXIMUM OPERATING ALTITUDE 13 700 m (45 000 ft) CONTROL SURFACE Elevator: Up 22 +1/2, -1 Down 15 1 MOVEMENTS Elevator trim tab: Up 4.5 +1, -0 Down 16 +1/2, -0 Rudder: (perpendicular to

hinge) Right 22 +1, -0 Left 22 +1, -0

Rudder trim tab: (perpendicular to

hinge) Right 10 1 Left 10 1

Aileron: Up 19 1 Down 15 1 Aileron trim tab: Up 20 1 Down 20 1 Wing flaps: Down 0º to 35º 1 Speed break: Up 0º to 58º +2, -0


See Airplane Maintenance Manual for rigging instructions. CERTIFICATION BASIS For S/N 560-0001 through 560-0259

RBAC 25, which endorses the 14 CFR Part 25 as amended by 25-1 through 25-17, except the following paragraphs which are in the specified amendments: - RBAC/14 CFR part 25 §§ 25.251(e), 25.934 and 25.1091(d) (2)

as amended through 25-23; § 25.1401 as amended through 25-27; § 25.1387 as amended through 25-30; §§ 25.787; 25.789; 25.791, 25.853, 25.855, 25.857, and 25.1359 as amended through amendment through 25-38;

- for the Honeywell (Sperry) EDZ-603 and EDZ-605 Electronic Flight Instrument Systems only: RBAC/14 CFR part 25 §§ 25.1301, 25.1303(b), 25.1322 as amended through 25-38; §§ 25.1309, 25.1321(a), (b), (d) and (e), 25.1331, 25.1333, and 25.1335 as amended through 25-41; and

RBAC 36, which adopts 14 CFR Part 36 effective 01 December 1969 as amended by 36.1 thru 36-15.

Special condition:

- 25-25-CE-4 relative to systems, airframe, flight and propulsion requirements accepted by CTA. See note 13.

- 25-ANM-21 relative to the aircraft operation at altitude up to 13 720 m (45 000ft) accepted by CTA. See note 11. Equivalent safety items: (1) Emergency exits ditching: RBAC/14 CFR 25.807 (d); (2) Fire Bottle Pressure Relief Valve: RBAC/14 CFR 25.1199(b) and (c); (3) Passenger Cabin Aisle Width: RBAC/14 CFR 25.815; (4) Use of N1 for Power Presentation: RBAC/14 CFR 25.1305(r);

(5)Use of Clear Vision Area of Windshield: RBAC/14 CFR 25.773(b)(2); (6) N

2 Indicator Markings: RBAC/14 CFR 25.1549(a) and (b); and

(7) Frangible Door: RBAC/14 CFR 25.813(e). RBAC/14 CFR 25.801 ditching not complied with. Compliance with ice protection has been demonstrated in accordance with RBAC/14 CFR 25.1419. SFAR 27, as amended by 27-1 through 27-6, fuel venting. Special condition established on ANAC report H-10.1050 issued originally in 23 June 1989.

For Citation Ultra, S/N 560-0260 through 560-0583 only: RBAC 25, which endorses the 14 CFR part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 25-1 through 25-17; (a) Additions: RBAC / 14 CFR part 25 §§ 25.251(e), 25.934 and 25.1091(d)(2) as amended 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, and 25.1359 as amended by Amendments 25-1 through 25-32; §§ 25.1303(a)(2) and 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 Electronic Flight Instrument Systems only: RBAC / 14 CFR part 25 §§ 25.1301, 25.1303(b), 25.1322 as amended by Amendments 25-1 through 25-38; §§ 25.1309, 25.1321(a), (b), (d), and (e), 25.1331, 25.1333, and 25.1335 as amended by Amendments 25-1 through 25-41. RBAC 36, which adopts 14 CFR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-15. RBAC 34, which adopts 14 CFR Part 34 effective September 10, 1990, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes. 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). Equivalent levels of safety as follows:

(a) RBAC / 14 CFR part 25 § 25.807(d), Emergency exits ditching; (b) RBAC / 14 CFR part 25 § 25.1199(b) and (c), Fire Bottle Pressure Relief Valve; (c) RBAC / 14 CFR part 25 § 25.815, Passenger Cabin Aisle Width; (d) RBAC / 14 CFR part 25 § 25.1305(r), Use of N1 for Power Presentation; (e) RBAC / 14 CFR part 25 § 25.773(b)(2), Use of clear vision area of windshield; (f) RBAC / 14 CFR part 25 § 25.1549(a) and (b), N2 Digital Indicator Markings. (g) RBAC / 14 CFR part 25 § 25.813(e), Frangible door. RBAC / 14 CFR part 25 § 25.801 ditching not complied with.

Compliance with ice protection has been demonstrated in accordance with RBAC / 14 CFR part 25 § 25.1419. Special Condition 25-ANM-79 relative to Lightning and High-Intensity Radiated Fields (HIRF) accepted by CTA.

REQUIRED EQUIPMENT The basic required equipment, as prescribed in the applicable

airworthiness regulations (see Certification Basis) must be installed in the airplane.


II - Model 550 Bravo (Transport Category), approved 08 January 1997.

ENGINE Two Pratt & Whitney of Canada Inc. PW530A Turbofans FUEL Jet A, Jet A-1, Jet B, JP-5, or JP-8. For use of anti-icing additives,

refer to the ANAC Approved Flight Manual. ENGINE LIMITS Static thrust, standard day, sea level – daN (lb): Takeoff (5min.) 1 284 (2 887) Max. Continuous 1 265 (2 843) Max. permissible engine rotor operating speeds - % (rpm):

N1(Fan) 100 (15 750) N2(Gas Gen.) 100 (32 150)

Max. permissible interturbine gas temperatures - C: Takeoff 700 Max. Continuous 700 Starting 690 Transient (starting 20 sec.) 740 AIRSPEED LIMITS (CAS) Maximum operating (VMO): Sea level to 2 438 m (8 000 ft) 260 kcas (260 kias) 2 438m (8 000 ft) to 8 504m (27 900 ft) 275 kcas (275 kias) Maximum operating (MMO):

above 8 504m (27 900 ft) 0.70 mach (0.70 mias)

Design Maneuvering (VA): Sea level – 6 713 kg (14 800 lb) 190 kcas(190 kias) See AFM for variations with weight and

altitude and optional configurations

VB (speed for max. gust intensity) 210 Kcas (210 Kias) Flaps extended (VFE) 40° (landing): 174 kcas (174 kias) 15° (takeoff and approach): 200 kcas (200 kias) Minimum control speed - Air (VMCA): 79 kcas (78 kias) Minimum control speed - Ground (VMCG): 92 kcas (89 kias) L. G. operation - extend (VLO): 250 kcas (250 kias) L. G. operation - retract (VLO): 200 kcas (200 kias) L. G. extended (VLE): 260 kcas (260 kias) VSB (Speed brake extend or retract) Any speed with or

without flaps TIRE LIMITS Maximum ground speed 165 knots C. G. RANGE (Landing Gear Extended)

Forward Limits: Linear variation from 713.66 cm (280.97 in) aft of datum (23.99% MAC) at 6 713 kg (14 800 lb) to 702.5 cm (276.57 in) aft of datum (18.54 % MAC) at 4 149 kg (9 147 lb).

Aft Limits: 725.93 cm (285.8 in) aft datum (30.0% MAC) from 6 713 kg (14 800 lb) through 3 933 kg (8 670 lb).

EMPTY WEIGHT CG RANGE None. DATUM Zero reference datum is 238 cm (93.7 in) forward of the nose jack

point. LEVELING MEANS Lower seat rail RBL 22.86 cm (9.0 in) starting at 523.24 cm (206.0

in) aft datum.


MEAN AERODYNAMIC CHORD 205.7 cm (80.98 in). Leading Edge of MAC 664.36 cm (261.56 in) MAXIMUM WEIGHT Takeoff: 6 713 kg (14 800 lb) Landing: 6 123 kg (13 500 lb) Zero Fuel: 5 125 kg (11 300 lb) Ramp: 6 804 kg (15 000 lb) MINIMUM WEIGHT Inflight - Forward C.G limit: 4 149 kg (9 147 lb)

Aft. C. G. limit 3 933 kg (8 670 lb) Note: Linear variation between forward and aft limits.

MINIMUM CREW For all flights: 2 persons (pilot and co-pilot) MAXIMUM PASSENGERS 13 (2 pilots, 11 passengers) MAXIMUM BAGGAGE Nose compartment: 158 kg (350 lb) at Sta 188 cm (74.0 in) Aft Cabin: 273 kg (600 lb) at Sta 815.34 cm (321.0 in) Tailcone 136 kg (300 lb) at Sta 1051.56 cm (414.0 in)

91 kg (200 lb) at Sta 1122.68 cm (442.0 in) FUEL CAPACITY Two wing tanks: 1 376 liters (363.5 US Gal) total each tank 1 362.8 liters (360.0 US Gal) usable each tank Arm: +728.98 cm (287.0 in) See note 1 for data on unusable fuel. OIL CAPACITY Two engine-mounted tanks

4.73 liters (5.0 US quarts) total each tank 1.80 liters (1.9 US quarts) usable each tank Arm = +931.80 cm (+366.85 in)

MAXIMUM OPERATING ALTITUDE

13 106 m (43 000 ft) (S/N 550-0801 through 550-0820) (S/N 550-0822 through 550-0823) 13 716 m (45 000 ft) (S/N 550-0821, 550-0824 and on) See NOTE 10 for S/N 550-0801 through 550-0820 & 550-0822 through 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 Rudder trim: Right 10 1 Left 10 1 Aileron: Up 19 1 Down 15 1 Aileron trim tab: Up 20 1 Down 20 1 Wing flaps: Down 0 to 40 1 Speed break: 0 to 58 2 See Airplane Maintenance Manual for rigging instructions


CERTIFICATION BASIS RBAC 25 Brazilian Requirements for Aeronautical Certification, which endorses the 14 CFR Part 25 effective 01 February 1965, as amended by 25-1 through 25-17; except the following paragraph which are in the specified amendments: - RBAC/14 CFR 25.305, as amended by Amdts. 25-1 through

25-54. - RBAC/14 CFR 25.1401, as amended by Amdts. 25-1 through 25-27. - RBAC/14 CFR 25.1387, as amended by Amdts. 25-1 through

25-30. - RBAC/14 CFR 25.1303 (a) (2) and 25.1385 (c), as amended by

Amdts. 25-1 through 25-38. - RBAC/14 CFR 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 and 25.1551, as amended by Amdts. 25-1 through 25-82.

- For Electronic Flight Instrument Systems only, compliance must be demonstrated for the additional regulations: RBAC/14 CFR 25.1301, and 25.1303(b), as amended by Amendments 25-1 through 25-38, 25.1309, 25.1321(a),(b),(d) and (e), 25.1331, 25.1333 and 25.1335, as amended by Amendments 25-1 through 25-41.

- Additions for airplanes approved for High Altitude Operation ( 45,000 feet) only:

1. RBAC / 14 CFR part 25 §§ 25.571(b)(5) and 25.1529 as amended by Amendments 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. RBAC / 14 CFR part 25 §§ 25.365, 25.831, 25.841, and 25.1447 as amended by Amendments 25-1 through 25-87.

RBAC 34, which adopts 14 CFR Part 34 effective September 10, 1990, as amended by Amendment 34-1, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes.

RBAC 36, which adopts 14 CFR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-21.

Special Condition 25-ANM-120, additional requirements for High Intensity Radiated Fields (HIRF).

Equivalent safety items:

(1) Emergency exits ditching: RBAC/14 CFR Part 25.807 (d) (2) Passenger Cabin Aisle width: RBAC/14 CFR Part 25.815 (3) Clear Vision: RBAC/14 CFR Part 25.773 (b) (2) (4) N2 Indicator Markings: RBAC/14 CFR Part 25.1549 (a) and (b) (5) Frangible door: RBAC/14 CFR part 25.813(e).

RBAC/14 CFR part 25 § 25.801 ditching not complied with.

Compliance with ice protection has been demonstrated in accordance with RBAC/14 CFR Part 25.1419.


III - Model 560 XL Excel (Transport Category), approved 22 April 1998.

ENGINES S/N 560-5001 through 560-5500

Two Pratt & Whitney of Canada, Inc. PW545A Turbofans

S/N 560-5501 through 560-6000 Two Pratt & Whitney of Canada, Inc. PW545B Turbofans

S/N 560-6001 and on Two Pratt & Whitney of Canada, Inc. PW545C Turbofans

FUEL Jet A, Jet A-1, Jet B, Jet 3, JP-4, JP-5 or JP-8. For S/N 560-5001

through 560-6000. Jet A, Jet A-1, Jet 3, JP-5 or JP-8. For S/N 560-6001 and on. For use of anti-icing additives, refer to the ANAC Approved Airplane Flight Manual.

ENGINE LIMITS S/N 560-5001 through 560-5500 (PW545A Turbofans) Static thrust standard day, sea level – daN (lb): Takeoff (5min.) 1 758 (3 952) Max. continuous 1 500 (3 372) Max. permissible engine rotor operating speeds - % (rpm): N1 (Fan) 100 (13 034) N2 (Gas Gen.) 100 (32 700) (S/N 560-5002 only) N2 (Gas Gen.) 101.8 (33 289) (S/N 560-5001, 560-5003 thru

560-5500)

Max. permissible interturbine gas temperatures - C: Takeoff 720 Max. continuous 720 Starting 720 Transient (20 seconds) 760 S/N 560-5501 through 560-6000 (PW545B Turbofans) Static thrust standard day, sea level – daN (lb): Takeoff (5min.) 1 832 (4 119) Max. continuous 1 500 (3 372) Max. permissible engine rotor operating speeds - % (rpm): N1 (Fan) 100 (13 034) N2 (Gas Gen.) 102.8 (33 622) Max. permissible interturbine gas temperatures - C: Takeoff 740 Max. continuous 720 Starting 740 Transient (20 seconds) 780 S/N 560-6001 and on (PW545C Turbofans) Static thrust standard day, sea level – daN (lb): Takeoff (5min.) 1 832 (4 119) Max. continuous 1 500 (3 372)


Max. permissible engine rotor operating speeds - % (rpm): N1 (Fan) 100 (13 034) N2 (Gas Gen.) 102.8 (33 622) Max. permissible interturbine gas temperatures - C: Takeoff 740 Max. continuous 720 Starting 740 Transient (20 seconds) 780 AIRSPEED LIMITS (CAS) Maximum operating (VMO): - Sea level to 2 438 m (8 000 ft) 261 kcas (260 kias) - 2 438 m (8 000 ft) to 8 081 m (26 515 ft) 306 kcas (305 kias) Maximum operating (MMO): - Above 8 081 m (26 515 ft) 0.752 Mach

(0.750 Mach IAS) Maneuvering (VA) - sea level: - 9 072 kg (20 000 lb) 196 kcas (195 kias) - See AFM for variations with weight and altitude and optional

configurations. Max. Gust Intensity (VB): 211 kcas (210 kias) Flaps extended (VFE): - 35° (landing) 175 kcas (174 kias) - 15° (takeoff and approach) 201 kcas (200 kias) - 7° (takeoff and approach) 201 Kcas (200 Kias) Minimum control speed - Air/Takeoff (VMCA) 90 kcas (90 kias ) Minimum control speed - Air/Landing (VMCL) 92 kcas (92 kias ) Minimum control speed - Ground (VMCG) 98 kcas (98 kias ) L. G. operation - extend (VLO) 251 kcas (250 kias) TIRE LIMIT Maximum ground speed 165 knots C. G. RANGE Forward Limits: *(Landing Gear Extended) S/N 560-5001 through 560-5500

Linear variation from 823.4 cm (324.18 in) aft of datum (21.39% MAC) at 9 163 kg (20 200 lb) to 810.1 cm (318.92 in) aft of datum (15.00% MAC) at 5 216 kg (11 500 lb).

Aft Limits: 841.4 cm (331.26 in) aft of datum (30.0% MAC) from 6 804 kg (15

000 lb) through 5 216 kg (11 500 lb). Linear variation from 840.0 cm (330.74 in) aft of datum (29.37% MAC) at 8 074 kg (17 800 lb) to 841.4 cm (331.26 in) aft of datum (30.0% MAC) at 6 804 kg (15 000 lb). 840.1 cm (330.74 in) aft of datum (29.37% MAC) from 8 074 kg (17 800 lb) through 9 163 kg (20 200 lb).

* See Note 17 (Landing Gear Extended) S/N 560-5501 through 560-6000

Forward Limits:


Aft Limits:


841.4 cm (331.26 in) aft of datum (30.0% MAC) from 6 804 kg (15 000 lb) through 5 216 kg (11 500 lb).


840.1 cm (330.74 in) aft of datum (29.37% MAC) from 8 074 kg (17 800 lb) through 9253 kg (20 400 lb).

(Landing Gear Extended) S/N 560-6001 and on

Forward Limits:


Aft Limits: 841.4 cm (331.26 in) aft of datum (30.0% MAC) from

6 804 kg (15 000 lb) through 5 216 kg (11 500 lb). Linear variation from 841.4 cm (331.26 in) aft of datum (30.00%

MAC) at 6 804 kg (15 000 lb) to 840.0 cm (330.74 in) aft of datum (29.37% MAC) at 8 074 kg (17 800 lb).

840.1 cm (330.74 in) aft of datum (29.37% MAC) from 8 074 kg (17 800 lb) through 9253 kg (20 400 lb).

EMPTY WEIGHT CG RANGE None DATUM Zero reference datum is 561.3 cm (221.0 in) forward of the leveling

screw just aft of the cabin door on W. L. 127.25. LEVELING MEANS Outboard floor panel inside of door parallel to B. L. 13.00. MEAN AERODYNAMIC CHORD 208.9 cm (82.231 in) (Leading edge of MAC is 778.7 cm (306.593

in) aft of datum). Note: This is reference MAC for basic wing without tip.

*S/N 560-5001 through

560-5500 * See Note 17

S/N 560-5501 through 560-6000

MAXIMUM WEIGHT Takeoff: 9 072 kg (20 000 lb) 9 163 kg (20 200 lb) Landing: 8 482 kg (18 700 lb) 8 482 kg (18 700 lb) Zero Fuel: 6 804 kg (15 000 lb) 6 849 kg (15 100 lb) Ramp: 9 163 kg (20 200 lb) 9 253 kg (20 400 lb) MINIMUM WEIGHT Inflight: 5 626 kg(12 400 lb) 5 626 kg (12 400 lb) S/N 560-6000 and on MAXIMUM WEIGHT Takeoff: 9 163 kg (20 200 lb) Landing: 8 482 kg (18 700 lb) Zero Fuel: 6 849 kg (15 100 lb) Ramp: 9 253 kg (20 400 lb) MINIMUM WEIGHT Inflight: 5 626 kg (12 400 lb) MINIMUM CREW For all flights: 2 persons (pilot and co-pilot)


MAXIMUM PASSENGERS 14 (2 crew, 12 passengers) see Note 14 MAXIMUM BAGGAGE Tailcone: 317.5 kg (700 lb) at 1 095 cm (431.0 in) aft of datum FUEL CAPACITY Two wing tanks: total 1 915 liters (505.8 US Gal) each; usable

1 904 liters (503.0 US Gal) each Arm 835.1 cm (328.8 in) aft of datum See note 1 for data on unusable fuel. OIL CAPACITY Two engine mounted tanks.

Total 7.0 liters (7.5 quarts) each; usable 0.6 liters (0.6 quarts) each tank. Arm 1 102 cm (433.9 in) of datum.

MAXIMUM OPERATING ALTITUDE

13 700 m (45 000 ft)

CONTROL SURFACE Elevator: MOVEMENTS (with stabilizer at + 1º) Up 19 +1, -0 Down 15 1 Elevator trim tab: (with stabilizer at + 1º) 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 +0.5, -0°

Left 28 +0.5, -0

Rudder trim: (perpendicular to hinge

with rudder centered) Right 11.5 0.5 Left 11.5 0.5

Aileron: Up 19 1 Down 15 1 Aileron trim tab: Up 20 2 Down 20 2 Wing flaps: 0º, and extend 7º, 15, 35º, 1 Speed break: Upper Up 60 2 Lower Up 65º 2º 2-position horizontal stabilizer - Takeoff & Landing -2º +0º, -0.1º - Cruise +1º +0.1º, -0º See Airplane Maintenance Manual for rigging instructions. CERTIFICATION BASIS (S/N 560-5001 through 560-6000)

RBAC 25, which endorses the 14 CFR Part 25 effective 01 Feb. 65, as amended by 25-1 through 25-82; except the following paragraphs which are in the specified amendments:

RBAC/14 CFR 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 and 25.1517 all these requirements as amended by Amdt 25-86;

RBAC/14 CFR 25.351 as amended by Amendment 25-91; and


CERTIFICATION BASIS Exceptions (as show in table): (Cont.) Section

No. Title

Effective Amendment

Exemptions

25.562 Emergency landing dynamic conditions

25-82 applicable 25-562(c)(5) and (c)(6)

25.571 Damage-tolerance and fatigue evaluation of structure

25-82 applicable 25.571(e)(1)

25.631 Bird strike damage None. This section is not part of the

certif. basis.

25.631 not applicable

25.671 Control Systems-General - Applicable to the 2-position

horizontal stabilizer -All other airplane control

systems

25-82

Original issue

applicable

None

25.671 as amended by Amdt. 25-23 and later,

not applicable 25.677 Trim systems

- Applicable to the 2-position horizontal stabilizer

- All other airplane trim systems, including the elevator trim

25-82

Original issue

applicable

None


not applicable

25.1309 Equipment, systems and installations - Applicable to Electronic

Flight Instrument systems (Honeywell Primus 1000 Cockpit Display), Flight Guidance, hydraulic, electrical, pressurization system, and 2-position horizontal stabilizer only.

-All other airplane systems

25.82

Original issue applicable

None

25.1309 as amended by Amdt. 25-23 and later, not applicable

RBAC 36 Brazilian corresponding to 14 CFR Part 36 effective 01 Dec. 69, as amended by Amendments 36-1 through 36-21.

RBAC 34 Brazilian corresponding to 14 CFR Part 34 effective 10 Sep. 90, as amended by Amendment 34-1. Special Conditions as follows:

25-ANM-79 Effects of High Intensity Radiated Fields (HIRF). The portions associated with System Lightning Protection do not apply.

25-ANM-21 High Altitude Operation (45 000ft). See note 11. Exemption: (a) Exemption number 6706 granted. Model 560XL exempt from requirements of RBAC / 14 CFR part 25 § 25.677 (b) for horizontal stabilizer position indicator. (b) Exemption 8621 granted. Model 560XL exempt from requirements of RBAC / 14 CFR part 25 § 25.813 (e) for


installation of interior doors between passenger compartments.

CERTIFICATION BASIS (Cont.)

Equivalent levels of safety, accepted by CTA, relative to the following requirements:

RBAC/14 CFR 25.807(e), emergency exits ditching (involves water barrier);

RBAC/14 CFR 25.815, passenger cabin aisle width;

RBAC/14 CFR 25.813(e), lavatory door installation between passenger compartments;

RBAC/14 CFR 25.811(d)(1); 25.812(b)(1)(i), emergency exit markings and locator signs;

RBAC/14CFR 25.841(b)(6), takeoff and landing operations at high elevation airports;

RBAC/14 CFR 25.1549(a) and (b), digital only display of turbine engine N2; and

RBAC/14 CFR 1.1, 1.2; 25.101; 25.105; 25.109; 25.113; 25.115; 25.735; and 25.1587, rejected takeoff distance and landing performance criteria (includes worn brake criteria).

RBAC/14 CFR 25.1305(a)(4), (a)(5), (a)(6), (c)(1) and (c)(3),

and 25.1549(a) through (d), Digital only display of APU engine rotor speed, exhaust gas temperature and no indication of oil pressure or oil temperature.

RBAC/14 CFR 25.1301(a)(d), 25.1303(a)(3), 25.1309(a)(b) (d)(e), 25.1316, 25.1327, 25.1331, 25.1333, 25.1547, 25.1351(d), 25.1353(a)(c), and 25.1459(e), Electric Standby Direction Indicator (Compass) (Applies to XLS)

RBAC / 14 CFR 25.815, Passenger Cabin Aisle Width, ELOS #SP2095WI-T-AG-8, dated August 23, 2002.

RBAC/14 CFR 25.801 ditching not complied with. Compliance with ice protection has been demonstrated in accordance with RBAC/14 CFR 25.1419.

(S/N 560-6001 and on) RBAC 25, which endorses the 14 CFR Part 25 effective 01 Feb. 65, as amended by 25-1 through 25-82; except the following paragraphs which are in the specified amendments:

RBAC/14 CFR 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, and 25.1517 as amended by Amendment 25-86; and, RBAC/14 CFR 25.351 as amended by Amendment 25-91.

RBAC/14 CFR 25.901, 25.903, 25.933, 25.934, 25.939, and 25.943 as amended by Amendments 25-1 through 25-117; and


CERTIFICATION BASIS Exceptions (as show in table):

(Cont.) Section No.

Title Effective

Amendment Exemptions

25.562 Emergency landing dynamic conditions

25-82 applicable 25-562(c)(5) and (c)(6)

25.571 Damage-tolerance and fatigue evaluation of structure

25-82 applicable 25.571(e)(1)

25.631 Bird strike damage None. This section is not part of the

certif. basis.

25.631 not applicable

25.671 Control Systems-General - Applicable to the 2-position

horizontal stabilizer -All other airplane control

systems

25-82

Original issue

applicable

None


not applicable 25.677 Trim systems

- Applicable to the 2-position horizontal stabilizer

- All other airplane trim systems, including the elevator trim

25-82

Original issue

applicable

None


not applicable

25.1309 Equipment, systems and installations - Applicable to Electronic

Flight Instrument systems (Honeywell Primus 1000 Cockpit Display), Flight Guidance, hydraulic, electrical, pressurization system, and 2-position horizontal stabilizer only.

- All other airplane systems -FADEC Installation

25.82

Original issue applicable

25-117

None

25.1309 as amended by Amdt. 25-23 and later, not applicable

RBAC 36 Brazilian corresponding to 14 CFR Part 36 effective

01 Dec. 69, as amended by Amendments 36-1 through 36-21. RBAC 34 Brazilian corresponding to 14 CFR Part 34 effective 10 Sep. 90, as amended by Amendment 34-1. Special Conditions as follows:

25-ANM-79 Effects of High Intensity Radiated Fields (HIRF). The portions associated with System Lightning Protection do not apply.

25-ANM-21 High Altitude Operation (45 000ft). See note 11. Exemption number 6706, accepted by CTA, from the requirements of RBAC/14 CFR 25.677(b) for horizontal stabilizer position indicator. (b) Exemption 8621 granted. Model 560XL exempt from requirements of RBAC / 14 CFR part 25 § 25.813 (e) for


installation of interior doors between passenger compartments. CERTIFICATION BASIS (Cont.)

Equivalent levels of safety, accepted by CTA, relative to the following requirements:

RBAC/14 CFR 25.807(e), emergency exits ditching (involves water barrier);

RBAC/14 CFR 25.815, passenger cabin aisle width;

RBAC/14 CFR 25.813(e), lavatory door installation between passenger compartments;

RBAC/14 CFR 25.811(d)(1); 25.812(b)(1)(i), emergency exit markings and locator signs;

RBAC/14 CFR 25.841(b)(6), takeoff and landing operations at high elevation airports;

RBAC/14 CFR 25.1549(a) and (b), digital only display of turbine engine N2; and

RBAC/14 CFR 1.1, 1.2; 25.101; 25.105; 25.109; 25.113; 25.115; 25.735; and 25.1587, rejected takeoff distance and landing performance criteria (includes worn brake criteria).

RBAC/14 CFR 25.1305(a)(4), (a)(5), (a)(6), (c)(1) and (c)(3), and 25.1549(a) through (d), Digital only display of APU engine rotor speed, exhaust gas temperature and no indication of oil pressure or oil temperature.

RBAC/14 CFR 25.1301(a)(d), 25.1303(a)(3), 25.1309(a)(b) (d)(e), 25.1316, 25.1327, 25.1331, 25.1333, 25.1547, 25.1351(d), 25.1353(a)(c), and 25.1459(e), Electric Standby Direction Indicator (Compass)

RBAC/14 CFR 21.21(b)(1), 25.1549, Use of Numeric Digital Only Display for Engine High-Pressure Turbine Speed (N2) and Engine Fuel Flow (Wf), and Standby N1, N2, and ITT.

RBAC/14 CFR 25.1397(c), 25.1401(d), Exterior Lighting Chromaticity Requirements

RBAC / 14 CFR 25.815, Passenger Cabin Aisle Width, ELOS #SP2095WI-T-AG-8, dated August 23, 2002.

RBAC/14 CFR 25.801 ditching not complied with. Compliance with ice protection has been demonstrated in accordance with RBAC/14 CFR 25.1419.

IV - Model 560 Encore (Transport Category), approved 30 January 2002.

ENGINE Two Pratt & Whitney of Canada Inc. PW535A Turbofans FUEL Jet A, Jet A-1, Jet B, JP4, JP8 or JP-5. For required use of anti-

icing additives and emergency use of aviation gasoline, refer to the Approved Airplane Flight Manual.

ENGINE LIMITS Static thrust, standard day, sea level – daN (lb): Takeoff (5min, normal all engines operating): 1 512 (3 400) Takeoff (10min, one engine inoperative) 1 512 (3 400) Max. Continuous 1 512 (3 400) Max. permissible engine rotor operating speeds - % (rpm):

N1(Fan) 100 (15 850) N2(Gas Gen.) 100 (33 970)


ENGINE LIMITS (Cont.) Max. permissible interturbine gas temperatures - C: Takeoff 700 Max. Continuous 700 Starting 740 Transient (starting 2 sec.) 740 AIRSPEED LIMITS (CAS) Maximum operating (VMO): Sea level to 2 438 m (8 000 ft) 260 kcas (262 kias) 2 438m (8 000 ft) to 8 810m (28 907 ft) 290 kcas (292 kias) Maximum operating (MMO): Above 8 810m (28 907 ft) 0.75 mcas (0.755 mias) Design Maneuvering (VA) - sea level: 7 543 kg (16 630 lb) 193 kcas(194 kias) See AFM for variations with weight and


Flaps extended (VFE) 35° (landing): 173 kcas (173 kias) 15° (takeoff and approach): 199 kcas (200 kias) 7° (takeoff and approach): 199 kcas (200 kias) Minimum control speed - Air (VMCA): 84 kcas (86 kias) Minimum control speed - Ground (VMCG): 15 (Takeoff) 95 kcas (92 kias)

7 (Takeoff) 99 kcas (96 kias) L. G. operation - extend (VLO): 249 kcas (250 kias) L. G. operation - retract (VLO): 199 kcas (200 kias) L. G. extended (VLE): 249 kcas (250 kias) Speed brakes extended (VSB): Any speed with or

without flaps TIRE LIMIT Maximum ground speed 165 knots CG RANGE (Landing Gear Extended)

Forward Limits: - Linear variation from 760.19 cm (299.29 in) aft of datum

(21.89% MAC) at 7 633 kg (16 830 lb) to 752.19 cm (296.14 in) aft of datum (18.0% MAC) at 5 624 kg (12 400 lb); 752.19 cm (296.14 in) aft of datum (18.0% MAC) at 5 624 kg (12 400 lb) or less.

Aft Limits: - 772.74 cm (304.23 in) aft of datum (28.0% MAC) at 7 634 kg

(16 830 lb) or less.

EMPTY WEIGHT C. G. RANGE None DATUM 238.7 cm (94.0 in) forward of the front face of the forward pressure

bulkhead. LEVELING MEANS Crew seat rails (lateral level); cabin door step hinge brackets

(longitudinal level). MEAN AERODYNAMIC CHORD 205.7 cm (80.98 in). Leading Edge of MAC at Sta. +715,16 cm

(281.56 in). Note: This is reference MAC for basic wing without leading edge

cuff and tip.


MAXIMUM WEIGHT Takeoff: 7 543 kg (16 630 lb) Landing: 6 894 kg (15 200 lb) Zero Fuel: 5 715 kg (12 600 lb) Ramp: 7 633 kg (16 830 lb) MINIMUM CREW For all flights: 2 persons (pilot and co-pilot) MAXIMUM PASSENGERS 13 (2 pilots, 11 passengers) MAXIMUM BAGGAGE Nose

compartment: 140 kg (310 lb) at Sta +188 cm (74.0 in)

Aft Cabin: 273 kg (600 lb) at Sta +884 cm (348.0 in) Tailcone 136 kg (300 lb) at Sta +1102 cm (434.0 in)

91 kg (200 lb) at Sta +1173 cm (462.0 in) FUEL CAPACITY Two wing tanks: 1538.39 liters (406.4 US Gal) total each tank; 1525.52 liters (403 US Gal) usable each tank. Arm: +771 cm (+303.5 in). See note 1 for data on unusable fuel. OIL CAPACITY Two engine-mounted tanks.

8.14 liters (8.6 quarts) total each tank. 0.6 liters (0.6 quarts) usable each tank. Arm = +982.98 cm (+387.0 in).

WINDSHIELD ANTI-ICE 1.89 liters (2 quarts)

Arm: +232,43 cm (+91.5 in) FLUID Approved anti-ice fluids: TT-I-735 Isopropyl alcohol. MAXIMUM OPERATING ALTITUDE

13 716 m (45 000 ft)

CONTROL SURFACE Elevator: Up 18 + 1, -½ Down 15 1 MOVEMENTS: Elevator trim tab: Up 4 ½ +0, -½ Down 11 +½, -0

Rudder: (perpendicular to

hinge) Right 22 +1, -0 Left 22 + 1, -0

Rudder trim: 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 flaps: Down 0 to 35 1 Speed break: 0to 58 + 2, -0 See Airplane Maintenance Manual for rigging instructions


CERTIFICATION BASIS (Cont.) RBAC 25 corresponding to 14 CFR Part 25, effective 01 Feb.

1965, including amendments 25-1 through 25-17, and the following:

– Additions:

- RBAC/14 CFR 25.625 as amended by Amendments 25-1 through 25-17;


- RBAC/14 CFR 25.787, 25.789, 25.791, 25.853, 25.855, 25.857, and 25.1359 as amended by Amendments 25-1 through 25-32;

- RBAC/14 CFR 25.1303(a)(2) as amended by Amendments 25-1 through 25-38;


- RBAC/14 CFR 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, and 25.1551 as amended by Amendments 25-1 through 25-91;

– Additions for the Honeywell Primus 1000 Electronic Flight

Instrument Systems only: - RBAC/14 CFR 25.1301, 25.1303(b), 25.1322 as amended by

Amendments 25-1 through 25-38; - RBAC/14 CFR 25.1309, 25.1321(a), (b), (d), and (e),

25.1331, 25.1333, and 25.1335 as amended by Amendments 25-1 through 25-41.

– Addition limited ONLY to: - Pressurization System; Digital Controller and Outflow

System; - Anti-skid System; Individual Wheel Digital Anti-skid

Controller; - Anti-ice System; Electronic Tail Boot Control and Monitoring

and Outboard Wing Leading Edge Bleed Air Control and Fault Annunciation; and

- Integrated Warning, Caution, and Advisory Annunciation System limited to the Internal Control Logic and Display Functions only;


CERTIFICATION BASIS (Cont.) - RBAC/14 CFR 25.1309 as amended by Amendments 25-1 through 25-91.

RBAC 36 corresponding to 14 CFR Part 36, effective 01 Dec. 1969, Noise Standards, as amended by Amendments 36-1 through 36-21.

RBAC 34 corresponding to 14 CFR Part 34, effective 10 Sep. 1990, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, as amended by Amendments 34-1 through 34-3.

FAA Special Conditions as follows:

- 25-ANM-21, additional requirements for High Altitude Operation (45 000 feet).

- 25-ANM-79, additional requirements for High Intensity Radiated Fields (HIRF) only.

- 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.

FAA Equivalent Levels of Safety as follows:

- RBAC/14 CFR 25.815, Passenger Cabin Aisle Width; - RBAC/14 CFR 25.773(b)(2), Use of clear vision of windshield; - RBAC/14 CFR 25.1549(a) and (b), N2 Digital indicator

Markings; - RBAC/14 CFR 25.813(e), Frangible door; - RBAC/14 CFR 25.807(d), Emergency exits ditching; - RBAC/14 CFR 25.841 (b)(6), Cabin Pressurization – High

Altitude Takeoff and Landing.

RBAC/14 CFR 25.801,ditching not complied with.

Compliance with ice protection has been demonstrated in accordance with RBAC/14 CFR 25.1419.

V - Model 560 Encore Plus (Transport Category), approved 16 May 2007.

ENGINE 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 – daN (lb): Takeoff (5min, normal all engines operating): 1 512 (3 400) Takeoff (10min, one engine ioperative) 1 512 (3 400) Max. Continuous 1 512 (3 400) Max. permissible engine rotor operating speeds - % (rpm):

N1(Fan) 100 (15 850) N2(Gas Gen.) 100 (33 970)

Max. permissible interturbine gas temperatures - C: Takeoff 700 Max. Continuous 700 Starting 740 Transient (starting 2 sec.) 740


OIL See Pratt and Whitney Canada Engine Maintenance Manual. AIRSPEED LIMITS (CAS) Maximum operating (VMO): Sea level to 2 438 m (8 000 ft) 260 kcas (262 kias) 2 438m (8 000 ft) to 8 810m (28 907 ft) 290 kcas (292 kias)

Maximum operating (MMO):

Above 8 810m (28 907 ft) 0.75 mcas (0.755 mias) Design Maneuvering (VA) - sea level: 7 634 kg (16 830 lb) 193 kcas(194 kias) See AFM for variations with weight and


Flaps extended (VFE) 35° (landing): 173 kcas (173kias) 15° (takeoff and approach): 199 kcas (200 kias) 7° (takeoff) 199 kcas (200 kias) Minimum control speed - Air (VMCA): 84 kcas (86 kias) Minimum control speed - Ground (VMCG): 15 (Takeoff) 95 kcas (92 kias)

7 (Takeoff) 99 kcas (96 kias)

L. G. operation - extend (VLO): 249 kcas (250 kias) L. G. operation - retract (VLO): 199 kcas (200 kias) L. G. extended (VLE): 249 kcas (250 kias) Speed brakes extended (VSB): Any speed with or

without flaps TIRE LIMIT Maximum ground speed 165 knots CG RANGE (Landing Gear Extended)

Forward Limits: - Linear variation from 760.55 cm (299.43 in) aft of datum (22.07%

MAC) at 7 725 kg (17 030 lb) to 752.19 cm (296.14 in) aft of datum (18.0% MAC) at 5 624 kg (12 400 lb); 752.19 cm (296.14 in) aft of datum (18.0% MAC) at 5 624 kg (12 400 lb) or less.

Aft Limits: - 772.74 cm (304.23 in) aft of datum (28.0% MAC) at 7 725 kg

(17 030 lb) or less.

EMPTY WEIGHT CG RANGE None DATUM 238.7 cm (94.0 in) forward of the front face of the forward pressure

bulkhead which station is 238.7 cm (94.0 in). LEVELING MEANS Crew seat rails (lateral level) and cabin door step hinge brackets

(longitudinal level). MEAN AERODYNAMIC CHORD 205.7 cm (80.98 in). Leading edge of MAC at sta. +715,16 cm

(281.56 in). Note: This is reference MAC for basic wing without leading edge

cuff and tip. MAXIMUM WEIGHT Takeoff: 7 634 kg (16 830 lb) Landing: 6 894 kg (15 200 lb) Zero Fuel: 5 829 kg (12 850 lb) Ramp: 7 725 kg (17 030 lb)


MINIMUM CREW For all flights: 2 persons (pilot and copilot) MAXIMUM PASSENGERS 11 passengers (up to 13 seats, 2 pilots, 11 passengers) MAXIMUM BAGGAGE Nose

compartment: 140 kg (310 lb) at Sta +188 cm (74.0 in)

Aft Cabin: 273 kg (600 lb) at Sta +884 cm (348.0 in) Tailcone 136 kg (300 lb) at Sta +1102 cm (434.0 in)

91 kg (200 lb) at Sta +1173 cm (462.0 in) FUEL CAPACITY Two wing tanks: 1 538.39 liters (406.4 US Gal) total each tank; 1 525.52 liters (403 US Gal) usable each tank. Arm: +771 cm (+303.5 in). See note 1 for data on unusable fuel. OIL CAPACITY Two engine-mounted tanks.

8.14 liters (8.6 quarts) total each tank, 0.6 liters (0.6 quarts) usable each tank, Arm = +982.98 cm (+ 387.0 in).

WINDSHIELD ANTI-ICE 1.89 liters (2 quarts)

Arm: +232,43 cm (91.5 in) FLUID Approved anti-ice fluids: TT-I-735 Isopropyl alcohol. MAXIMUM OPERATING ALTITUDE

13 716 m (45 000 ft)

TEMPERATURE OPERATING See AFM section II - Operating Limitations. LIMITS CONTROL SURFACE Elevator: Up 18 + 1, -½ Down 15 1 MOVEMENTS Elevator trim tab: Up 4 ½ +0, -½ Down 11 +½, -0

Rudder: Right 22 +1, -0 Left 22 + 1, -0 (perpendicular to

hinge)

Rudder trim: 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 flaps: Down 0 to 35 1 Speed break: 0to 58 + 2, -0 See Airplane Maintenance Manual for rigging instructions. CERTIFICATION BASIS RBAC 25 corresponding to 14 CFR Part 25, effective 01 Feb.

1965, including amendments 25-1 through 25-17, except for the paragraphs applicable for engines and FADEC and the following:


CERTIFICATION BASIS (Cont.) – Additions: - RBAC/14 CFR 25.625 as amended by Amendments 25-1

through 25-17; and - RBAC/14 CFR 25.1401 as amended by Amendments 25-1

through 25-27; - RBAC/14 CFR 25.787, 25.789, 25.791, 25.853, 25.855, 25.857,

and 25.1359 as amended by Amendments 25-1 through 25-32; - RBAC/14 CFR 25.1303(a)(2) as amended by Amendments

25-1 through 25-38; - RBAC/14 CFR 25.305 as amended by Amendments 25-1

through 25-54; - RBAC/14 CFR 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, and 25.1551 as amended by Amendments 25-1 through 25-91; and 25.901, 25.903(a)(b)(c)(e) and (f), 25.933, 25.934, 25.939, 25.943 as amended by Amendments 25-1 through 25-117.

– Additions for Electronic Flight Instrument Systems only: - RBAC/14 CFR 25.1301, 25.1303(b), 25.1322 as amended by

Amendments 25-1 through 25-38; - RBAC/14 CFR 25.1309, 25.1321(a), (b), (d), and (e),

25.1331, 25.1333, and 25.1335 as amended by Amendments 25-1 through 25-41.

– Addition limited ONLY to: - Pressurization System; Digital Controller and Outflow

System; - Anti-skid System; Individual Wheel Digital Anti-skid

Controller; - Anti-ice System; Electronic Tail Boot Control and Monitoring

and Outboard Wing Leading Edge Bleed Air Control and Fault Annunciation; and

- Integrated Warning, Caution, and Advisory Annunciation System limited to the Internal Control Logic and Display Functions only;

- RBAC/14 CFR 25.1309 as amended by Amendments 25-1 through 25-91.

-Addition limited ONLY to: - FADEC engine control system: 25.1309 as amended by Amendments 25-1 through 25-117

RBAC 36 corresponding to 14 CFR Part 36, effective 01 Dec. 1969, Noise Standards, as amended by Amendments 36-1 through 36-21.


CERTIFICATION BASIS (Cont.) RBAC 34 corresponding to 14 CFR Part 34, effective 10 Sep. 1990,

Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, as amended by Amendments 34-1 through 34-3. FAA Special Conditions as follows:

- 25-ANM-21, additional requirements for High Altitude Operation (45 000 feet).

- 25-ANM-79, additional requirements for High Intensity Radiated Fields (HIRF) only.

- 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.

FAA Equivalent Levels of Safety as follows: - RBAC/14 CFR 25.815, Passenger Cabin Aisle Width; - RBAC/14 CFR 25.773(b)(2), Use of clear vision of windshield; - RBAC/14 CFR 25.1549(a) and (b), N2 Digital indicator

Markings; - RBAC/14 CFR 25.813(e), Frangible door; - RBAC/14 CFR 25.807(d), Emergency exits ditching; and - RBAC/14 CFR 25.841 (b)(6), Cabin Pressurization – High

Altitude Takeoff and Landing. - RBAC/14 CFR 25.1303(a)(9) and 25.1547 electronic standby

direction indicator. ELOS memo #ST4383WI-T-SE-1. - RBAC/14 CFR 25.801, ditching not complied with. Compliance with ice protection has been demonstrated in

accordance with RBAC/14 CFR 25.1419. DATA PERTINENT TO ALL MODELS: A Certificate of Airworthiness for Export endorsed as noted under

"Import Requirements" must be submitted for each individual aircraft for which application for a Brazilian Certificate of Airworthiness is made. 560-0001 through 560-0259 (Citation V) 560-0260 through 560-0538 (Citation Ultra) 550-0801 and on (Bravo) 560-5001 through 560-5500 (Citation Excel) 560-5501 through 560-6000 (Citation XLS) 560-6001 and on (Citation XLS+) 560-0539 through 560-0750 (560 Encore) 560-0751 through 560-5000 (560 Encore+)

IMPORT ELEGIBILITY A Brazilian Certificate of Airworthiness may be issued on the basis

of on an FAA Export Certificate on Airworthiness (or a third country Export Certificate on Airworthiness, in case of used aircraft imported from such country), including the following statement:

“The aircraft covered by this certificate has been inspected, tested and found to be in conformity with the Brazilian approved type design as defined by the Brazilian Type Certificate No. 9001 and in condition of safe operation”.


REQUIRED EQUIPMENT The basic required equipment, as prescribed in the applicable

airworthiness regulations (see Certification Basis) must be installed in the airplane.

NOTES: NOTE 1 Weight and balance. Current weight and balance report including list of equipment in

certificated empty weight, and loading instructions when necessary must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include:

Unusable fuel 9.1 kg (20.0 lb) at +782.3 cm (308.0 in) - Citation V and Ultra, S/N 560-0001 through 560-0538

21.4 kg (47.2 lb) at +715.5 cm (281.7 in) - Citation Bravo, S/N 550-0801 and on

17.1 kg (37.8 lb) at +847.1 cm (333.5 in) - Citation Excel, S/N 560-5001 and on

21.82 kg (48.1 lb) at + 762.8 cm (300.3 in)

- (560 Encore, S/N 560-0539 through 560-0750)

21.59 kg (47.6 lb) at + 762.3 cm (300.1 in)

- (560 Encore+, S/N 560-0751 through 560-5000)

Full Oil 14.2 kg (31.3 lb) at +983.0 cm (387.0 in) - Citation V, S/N 560-0001 through 560-0259

14.6 kg (32.2 lb) at +983.0 cm (387.0 in) - Citation Ultra, S/N 560-0260 through 560-0538


10.8 kg (23.7 lb) at +1102 cm (433.9 in) - Citation Excel, S/N 560-5001 and on

15.5 kg (34.1 lb) at + 983 cm (387.0 in) - (560 Encore, S/N 560-0539 through 560-0750)

15.5 kg (34.1 lb) at + 983 cm (387.0 in) - (560 Encore+, S/N 560-0751 through 560-5000)

Hydraulic fluid 14.3 kg (31.5 lb) at +813.5 cm (320.3 in) - Citation V and Ultra, S/N 560-0001 through 560-0538


15.5 kg (34.2 lb) at +899.2 cm (354.0 in) - Citation Excel, S/N 560-5001 and on

9.7 kg (21.7 lb) at +721.6 cm (284.0 in) - (560 Encore, S/N 560-0539 through 560-0750)

7.0 kg (15.4 lb) at +579.2 cm (228.02 in) - (560 Encore+, S/N 560-0751 through 560-5000)

Anti-Ice fluid 1.5 kg (3.4 lb) at +232.2 cm (91.4 in) - Citation V and Ultra, S/N 560-0001 through 560-0538

(windshield) 1.5 kg (3.4 lb) at +232.2 cm (91.4 in) - (560 Encore, S/N 560-0539 through 560-0750)

1.5 kg (3.4 lb) at +232.2 cm (91.4 in) - (560 Encore+, S/N 560-0751 through 560-5000)

NOTE 2 Markings and placards. The airplane must be operated according to the appropriate FAA

approved Brazilian Airplane Flight Manual and in the chapter XI of the Airplane Maintenance Manual.

NOTE 3 Continuing Airworthiness. See Maintenance Manual, Chapter 4, “Airworthiness

Limitations” for inspections, mandatory retirement life information, and other requirements for continued airworthiness


NOTE 4 The differences of the Brazilian airplanes in relation to the basic FAA type design are

summarized below: For Citation V:

1) The FAA approved Brazilian Airplane Flight Manual No. 560BR-00 original dated 02 March 1990 and further revision is the AFM approved for the model 560 Citation V Brazilian airplanes.

2) Markings and placards.

For Citation Ultra: 1) The FAA approved Brazilian Airplane Flight Manual No. 56BRA-00 original dated

26 July 1995 and further revision is the AFM approved for the model 560 Citation Ultra Brazilian airplanes.

2) Markings and placards.

For Bravo: 1) The Brazilian Airplane Flight Manual nr. 55BBR-02 revision 2 dated March 1998 and

further revision is the AFM approved by CTA. 2) Markings and placards.

For Excel: 1) The FAA approved Brazilian Airplane Flight Manual No. 56XBR-00 original dated Dec.

1998 and further revision is the AFM approved by CTA for the S/N 560-5001 through 560-5500. The Brazilian AFM No. 56XBR-00 includes the supplement 15 “Airplanes Certified to Brazilian Configuration”. The FAA approved Brazilian Airplane Flight Manual No. 56XBRA-01 revision 1, dated 23 July 2004 or later revisions and the Supplement 21 (Airplanes Certified to Brazilian Configuration) are the Brazilian AFM approved for the S/N 560XL 560-5501 through 560-6000. The FAA approved Brazilian Airplane Flight Manual No. 56XBRB-00, dated 30 May 2008 or later revisions and the Supplement 12 (Airplanes Certified to Brazilian Configuration) are the Brazilian AFM approved for the S/N 560XL 560-6001 and on.

2) Markings and placards. For 560 Encore:

1) The FAA approved Brazilian Airplane Flight Manual No. 56FMB-01 revision 1, dated 27 June 2000, and further revisions is the AFM approved for the model 560 Encore Brazilian airplanes.

2) Markings and placards. 3) An HF Communication System must be installed in accordance with the drawing #

9610646. 4) An Emergency Locator Transmitter (ELT) must be installed in accordance with the

drawing # 9602022. 5) A Cockpit Voice Recorder (CVR) must be installed in accordance with the drawing #

9622661. For 560 Encore+:

1) The FAA approved Brazilian Airplane Flight Manual No. 56FMC-00, dated 21 December 2006, and further revisions is the AFM approved for the model 560 Encore+ Brazilian airplanes.

2) Markings and placards. 4) An HF Communication System must be installed in accordance with the drawing

# 9610950 and 9610951. 5) An Emergency Locator Transmitter (ELT) must be installed in accordance with the

drawing # 9602950. 6) A Cockpit Voice Recorder (CVR) must be installed in accordance with the drawing

# 9622950.


NOTE 5 All Model 560 Citation V and Ultra, Model 560XL Excel, Model 550 Bravo and 560

Encore and Encore+ replacement seats (crew and passenger), although they may comply with TSO C39, must also comply with 25.785. All Model 560XL replacement seats must comply with 25.562, Emergency landing dynamic conditions, as shown in the certification basis.

NOTE 6 Model 560 s/n 560-0001 through 0259 aircraft, conforming to ECR-26053, are eligible for

5 534 kg (12 200 lb), zero fuel weight with VMO reduced to 275 kcas from 2 440 m (8 000 ft) to 9 300 m (31 400 ft).

NOTE 7 Approved nose gear tires are limited to those listed in the Limitations Section of the

Brazilian Approved Airplane Flight Manual. NOTE 8 Reserved NOTE 9 For aircraft models 560 coming to ECR 26053 - 5 534 kg (12 200 lb) ZFW Option, and

conforming to ECR 26155 Gravel kit, the following VLO and VLE apply: ECR 26053 Rev. D Gravel kit ECR 26155 5 534 kg (12 200 lb) Rev. C - VLO (landing gear operating extended) 249 kcas 199 kcas - VLO (landing operating retract) 199 kcas 199 kcas - VLE (landing gear extended) 275 kcas 199 kcas ECR 26053 - 5 534 kg (12 200 lb) ZFW Option is applicable to s/n 560-0001 through 560-0259.

NOTE 10 Model 550 (Bravo) increase the maximum operating altitude from 12 497 m (41 000 ft) to

13 716 m (45 000 ft) modified in accordance with the following Cessna Service Bulletins: S/N 550-0801 through 550-0808, Cessna Service Bulletin SB550-03-03; S/N 550-0809 through 550-0820, and S/N 550-0822 through 550-0823, Cessna Service Bulletin SB550-34-64.

NOTE 11 Certain models have been approved for high altitude 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: 25.8 cm2 (4.00 sq. in) - Model 560 (Citation V and Ultra) s/n 560-001 through 560-0538:25.8cm2(4.00sq. in) - Model 560 XL (Excel): 25.67 cm2 (3.98 sq. in) - Model 560 (Encore) S/N 560-0539 through 560-5000: 25.8 cm2 (4.00 sq. in)


NOTE 12 Model 560XL. (s/n 560-5001 thru 560-5500) Left divider assembly (part No. 6679017-1) or equivalent must always be installed when the LH aft toilet is installed and approved for occupancy during takeoff and landing. The structure divider is an integral part of the seat restraint system. Model 560XL. (s/n 560-5501 through 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 installed and approved for occupancy during takeoff and landing. The structural divider is an integral part of the seat restraint system.

NOTE 13 Models 560 (S/N 560-0001 thru 560-0538). Special condition number 25-25-CE-4

applies to the following: 1) Operation without normal electrical power; 2) Limit maneuvering load factor, in lieu of §25.337(b); 3) Turbulence criteria; 4) Vibration and buffeting, in lieu of §25.251(c); 5) Engine exhaust system drains; 6) Engine bleed air system; 7) Engine in-flight restart capability; 8) Engine thrust control; 9) Powerplant installation fault analysis; 10) Turbine engine powerplant installation, in lieu of §25.903(d); 11) Engine ignition system; and 12) Powerplant shutoff means, in addition to §25.1189.


NOTE 14 Model 560XL width of aisle equivalent level of safety allows a minimum aisle width of 13 inches when measured from 25 inches to 27.5 inches from the dropped aisle floor. Any further reduction in aisle width requires further ANAC evaluation and is not included in the accepted equivalent level of safety.

NOTE 15 Certain models meet the initial airworthiness requirements for operation in Reduced

Vertical Separation Minimum (RVSM) airspace.

Model 560 Citation V S/N 560-0001 through 560-0259 that have accomplished Cessna Service Bulletin SB 560-34-97.

Model 560 Ultra S/N 560-0260 through 560-0525 that have accomplished Cessna Service Bulletin Sb560-34-79, and S/N 560-0526 through 560-0583.

Model 550 Bravo S/N 550-0801 through 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 and Model 560 encore +

S/N 560-0539 through 560-5000.

Each operator must obtain RVSM operating approval directly from the ANAC.

NOTE 16 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.

CG Range Forward Limits: Linear variation from 754.25 cm (296.95 in) aft of datum (19% MAC) at 7 643 kg (16 850 lbs) to 752.73 cm (296.35 in) aft of datum (18.26% MAC) at 7 484 kg (16 500 lb) to 746.02 cm (293.71 in) aft of datum (15% MAC) at 5 216 kg (11 500 lb); 746.02 cm (293.71 in) aft datum (15% MAC) at 5 216 kg (11 500 in) or less. Aft Limits: 772.74 cm (304.23 in) aft of datum (28% MAC) at 7 643 kg (16 850 lb) or less.

Maximum Weight Takeoff 7 552 kg (16 650 lb) Ramp 7 643 kg (16 850 lb) Landing 6 895 kg (15 200 lb) Zero fuel 5 534 kg (12 200 lb)

TEXTRON 20 June 201 7 EA-9001 -07 Sheet 30/30

NOTE 17Model 560XL aircraft S/N 560-5001 through 560-5500, modified per SB560XL-32-28

CG RangeForward Limits Linear variation from 823.72 cm (324.30 in) aft of datum (21.54%

MAC) at 9 253 kg (20 400 lbs) to 81 1.45 cm (319.47 in) aft of datum(15.81% MAC) at 5 625 kg(12400 lb).841 .40 cm(331.26 in) aft of datum(30% MAC) from 6 840 kg(15 000lb) through 5 625 (1 2 400 lb).Linear variation from 841.40 cm (331.26 in) aft of datum (29.37%MAC) at 8 074 kg (17 800 lb) to 840.68 cm (330.74 in) aft of datum(30.0o%o MAC) at 6 804 kg (1 5 000 1b).840.68 cm (330.74 in) aft of datum (29.37% MAC) from 8 074 kg (17800 lb) through 9 253 kg (20 400 lb).

Aft Limita

Maximum WeiahtTakeoffRampLandingZero fuel

9 1 63 kg (20 200 1b)9 253 kg (20 400 1b)8 482 kg (1 8 700 1b)6 849 kg (15 100 lb)

Mir!!mum WeiahtIn flight 5 625 kg (1 2 400 lb)

NOTA 18 Modem 560 aircraft S/N 560-0539 through 560-0750, modified per SB560-32-40

C:G Range (Landina Gear Extended)Forward Limits: Linear variatíon from 760.55 cm (299.43 in.) aft of datum (22.07% MAC)

at 7 725 kg (17 030 lb.) t0 752,20 cm (296.14 in.) aft of datum (18.0%MAC) at 5 625 kg (12 400 lb.)l 752.20 cm (296.14 in.) aft of datum(1 8.0% MAC) at 5 625 kg (1 2 400 lb.) or less.772.74 cm (304.23 in.) aft of datum (28.0% MAC) at 7 725 kg (17,030lb.) or less.

Aft Limita:

Maximum WeiqhtTakeoff 7 634 kg (16,830 lb.)Landing 6 895 kg (15 200 lb.)Zero Fuel 5 829 kg (12 850 lb.)Ramp 7 725 kg (17,030 lb.)

NOTE 19 The following serials are manufactured under the name of Cessna Aircraft Company560XL: 560-5001 thru 560-61 91 .

NOTA 20 Company name change effective 29 September 2015. The followingmanufactured under the name Textron Aviation Inc.: 560-61 92 and On.

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