# TCDS A9NM: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 27
- Revised: June 16, 2015
- Product: Aircraft, Large Airplane
- Certification basis: Part 25, Part 27, Part 34, Part 36, Part 254
- Registered aircraft: 201, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/22/c5/22c5e7a157eede058f73453fe9d40da7ee5314dde36eeaad02be720b88bfe2aa
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/B89D10951D2F3EB286257E6D0053B370.0001
- Page: https://openairdocs.org/tcds/A9NM

## Models (1)

As the data sheet lists them.

- 650 (Citation III, Citation VI)

## 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 
Rev. No. 27 25 25 27 25 25 25 26 25 25 27 27 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A9NM 
Revision 27 
Textron Aviation 
650 
June 16, 2015 
 
 
 
 
 
 
TYPE CERTIFICATE DATA SHEET NO. A9NM 
 
This data sheet which is part of Type Certificate No. A9NM 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 Blvd, W2-2 
 Wichita, KS 67215 
  
Type Certificate Holder Record Cessna Aircraft Company transferred to  
 Textron Aviation Inc. on June 16, 2015 
 
I. Model 650, Citation III and Citation VI, (Transport Category), approved April 30, 1982 
 
 Engines Two Garrett TFE731-3B-100S (Standard) 
  Two Garrett TFE731-3BR-100S (Optional) (See NOTE 11) 
  Two Garrett TFE731-3C-100S (Standard) (See NOTE 18) 
  Two Garrett TFE731-3CR-100S (Optional) (See NOTE 18) 
 
 Fuel Commercial kerosene Jet A, Jet B, Jet A-1, JP-4, JP-5, and JP-8, fuel, conforming to 
  AiResearch Manufacturing Co. fuel specifications, EMS 53111, EMS 53112, or 
  EMS 53116.   
 
 Engine Limits Static thrust standard TFE731-3B-100S TFE731-3BR-100S 
  day, sea level: (Standard) (Optional) 
    Takeoff (5 min.) 3650 lb. 3850 lb. 
    (Emergency Only) 
    Max. continuous 3650 lb. 3650 lb. 
 
  Max. permissible engine rotor operating speed: 
    N1 (Fan) steady state 101.5% r.p.m. 101.5% r.p.m. 
    N2 (Gas gen.) steady state 100% r.p.m. 101% r.p.m. 
    N1 (Fan)  101.5% to 103% r.p.m. 101.5% to 103% r.p.m. 
   limited to 1 min. limited to 1 min. 
    N2 (Gas gen.) 100% to 103% r.p.m. 101% to 103% r.p.m. 
   limited to 1 min. limited to 1 min. 
 
  Max. permissible interturbine gas temperatures: 
    Takeoff (5 minutes) 890° C. 890° C. 
    916° C. (Emergency only) 
    Max. continuous 890° C. 890° C. 
    Starting 890° C. 890° C. 
 
  Static thrust standard TFE731-3C-100S TFE731-3CR-100S 
    day, sea level: (Standard) (Optional) 
      Takeoff (5 min.) 3650 Lb. 3850 Lb. 
    (Emergency Only) 
      Max. continuous 3650 Lb. 3650 Lb.

A9NM                                                                                                   2                                                                                                           Rev. 27 
I. Model 650, Citation III and Citation VI (cont’d) 
  
 Engine Limits (cont’d) Max. permissible engine rotor operating speed: 
    N1 (Fan) steady state 101.5% r.p.m. 101.5% r.p.m. 
    N2 (Gas gen.) steady state 100.0% r.p.m. 101.0% r.p.m. 
    N1 (Fan) 101.5% to 103 % r.p.m. 101.5% to 103% r.p.m. 
   Limited to 1 min. Limited to 1 min. 
    N2 (Gas Gen.) 100% to 103% r.p.m. 101% to 103% r.p.m. 
   Limited to 1 min. Limited to 1 min. 
 
  Max. permissible interturbine gas temperatures: 
    Takeoff (5 minutes) 910o C. 910o C. 
     APR Takeoff (5 minutes)  929o C. (Emergency Only) 
    Max. continuous 910o C. 910o C. 
    Starting 910o C. 910o C. 
 
Airspeed Limits Airplane Serial Numbers (S/N) 
650-0001 through 650–0093 
Airplane Serial Numbers (S/N) 
650-0094 through 650–0241;  and earlier 
Serials incorporating SB650-32-13 
VMO  (Maximum Operating) 
 (Calibrated Altitudes)  
 
305 KIAS below 8000 ft. 
346 KIAS at 8000 ft. with  
linear decrease to 293 KIAS  
(.851 M) at 34,275 feet 
305 KIAS below 8000 ft. 
336 KIAS at 8000 ft. with 
linear decrease to 278 KIAS 
(.851 M) at 36,524 feet 
 See NOTE 8 for VMO with 
Optional Zero Wing Fuel Weight 
 
MMO  (Calibrated Altitude) .851 M above 34,275 feet 851 M above 36,524 feet 
 
  VA  (Sea level) 10,000 lb. 155 KIAS  
   12,000 lb. 164 KIAS 
   15,000 lb. 184 KIAS 
    22,000 lb. 224 KIAS 
  See Airplane Flight Manual (AFM) for variations with weight and altitude and optional  
  configurations. 
 
  VB (Speed for maximum gust intensity) 220 KIAS 
  VFE (Flaps extended) 
   Partial flaps, 7° or 20° 210 KIAS 
   Ldg Position - Full Flaps 170 KIAS 
  VMCA (Minimum control speed) Air   98 KIAS 
  VMCG (Minimum control speed) Ground   99 KIAS 
   (19,000 lb.. and below, see AFM for variation with weight) 
  VLO (Landing gear operating) 210 KIAS 
  VLE  (Landing gear extended) 210 KIAS 
  Landing light extended  250 KIAS 
  Max. tire ground speed 165 knots 
  Speed Brakes Extension Speed Maximum No Limit 
    Panels 2, 3, 6 & 7 Minimum   VREF + 15 KIAS 
 
 (Airplanes S/N 650-0152 through 650–0241; and Airplanes S/N 650-0001 through 650-
0151 incorporating SB650-27-23.)  Extension of the speed brakes with the flaps in any 
position other than the UP position is prohibited below 500 feet AGL.  Above 500 feet 
AGL the speed brakes may be extended with the flaps in any position. 
 (Airplanes S/N 650-0001 through 650-0151 not incorporating SB650-27-23.)  Extension 
of the speed brakes is prohibited in flight with flaps in any position other than the UP 
position. 
 
 Spoiler Extension Speed (In flight restricted to emergency descent) 
Panels 1, 2, 3, 4, 5, 6, 7 & 8 Maximum  VMO/MMO 
 Minimum 150 KIAS

A9NM                                                                                                   3                                                                                                           Rev. 27 
I. Model 650, Citation III and Citation VI (cont’d) 
 
Airspeed Limits  (cont’d) Spoiler extension in flight is restricted to emergency descent use.   
 Extension of the spoilers is prohibited in flight with the flaps in any position other than  
 the up position. 
 
  There is no restriction on roll control spoilers (Panels 1 & 8)  
 
 C.G. Range   Takeoff weights up to 21,000 lb. (Landing Gear Extended)  
   Airplanes S/N 650-0001 through 650-0093 [airplanes not incorporating SB650-32-13 or 
SB650-32-14]  
  Forward limit: Linear variation from 324.29 inches aft of datum (23.89% MAC) at 21,000 lb. to 
316.20 inches aft of datum (14.00% MAC) at 18,000 lb.;  316.20 inches aft of datum 
(14.00% MAC) at 18,000 lb. to 14,500 lb.; Linear variation from 316.20 inches aft 
of datum (14.00% MAC) at 14,500 lb. to 321.10 inches aft of datum (20.00% MAC) 
at 12,000 lb. 
  Aft Limit:  330.1 inches aft of datum (31.00% MAC) at 21,000 lb. or less. 
 
 C.G. Range   Takeoff weights up to 21,000 lb. (Landing Gear Extended)  
   Airplanes S/N 650-0001 through 650-0093 [airplanes incorporating SB650-32-14 but not 
SB650-32-13]  
  Forward limit: Linear variation from 321.66 inches aft of datum (20.67% MAC) at 21,000 lb. to 
316.20 inches aft of datum (14.00% MAC) at 19,000 lb.;  316.20 inches aft of datum 
(14.00% MAC) at 19,000 lb. to 14,500 lb.; Linear variation from 316.20 inches aft 
of datum (14.00% MAC) at 14,500 lb. to 321.10 inches aft of datum (20.00% MAC) 
at 12,000 lb. 
  Aft Limit:  330.10 inches aft of datum (31.00% MAC) at 21,000 lb. or less. 
 
 C.G. Range   Takeoff weights up to 21,500 lb. (Landing Gear Extended)  
   Airplanes S/N 650-0001 through 650-0093 [airplanes incorporating SB650-32-13 or 
SB650-32-14]  
  Forward limit: Linear variation from 323.02 inches aft of datum (22.33% MAC) at 21,500 lb. to 
316.20 inches aft of datum (14.00% MAC) at 19,000 lb.;  316.20 inches aft of datum 
(14.00% MAC) at 19,000 lb. to 14,500 lb.; Linear variation from 316.20 inches aft 
of datum (14.00% MAC) at 14,500 lb. to 321.10 inches aft of datum (20.00% MAC) 
at 12,000 lb. 
  Aft Limit:  330.10 inches aft of datum (31.00% MAC) at 21,500 lb. or less. 
 
 
 C.G. Range   Takeoff weights up to 22,000 lb. (Landing Gear Extended)  
   Airplanes S/N 650-0094 through 650-0241  
  Forward limit: Linear variation from 324.38 inches aft of datum (24.00% MAC) at 22,000 lb. to 
316.20 inches aft of datum (14.00% MAC) at 19,000 lb.;  316.20 inches aft of datum 
(14.00% MAC) at 19,000 lb. to 14,500 lb.; Linear variation from 316.20 inches aft 
of datum (14.00% MAC) at 14,500 lb. to 321.10 inches aft of datum (20.00% MAC) 
at 12,000 lb. 
  Aft Limit:  330.10 inches aft of datum (31.00% MAC) at 22,000 lb. or less. 
 
 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 Water Line 127.25. 
 
 MAC 81.725 in. (L.E. of MAC at Sta. +304.768)

A9NM                                                                                                   4                                                                                                           Rev. 27 
I. Model 650, Citation III and Citation VI (cont’d) 
 
 Leveling Means Seat rails 
 
 Maximum Weight Airplanes S/N 650-0001 through 650-0093 [airplanes not incorporating SB650-32-13]: 
 Ramp 21,200 Pounds 
 Takeoff  21,000 Pounds 
 Landing  17,000 Pounds 
 Zero fuel   14,650 Pounds 
 Design Zero Wing fuel (optional)  16,300 Pounds [See NOTE 8] 
 
 Airplanes S/N 650-0001 through 650-0093 [airplanes incorporating SB650-32-13]: 
 Ramp  21,700 Pounds 
 Takeoff  21,500 Pounds 
 Landing  19,000 Pounds 
 Zero Wing fuel  16,300 Pounds [See NOTE 8] 
 
 Airplanes S/N 650-0094 through 650-0241: 
 Ramp  22,200 Pounds 
 Takeoff  22,000 Pounds 
 Landing  20,000 Pounds 
  Zero Wing fuel  16,300 Pounds [See NOTE 8] 
 
 Minimum Crew For all flights:  2 persons (pilot and co-pilot) 
 
 No. of Seats 15 (2 pilots, up to 13 passengers) 
  See NOTE 5 
 
 Maximum Baggage Tail compartment      700 lb. 
  (500 lb. for A/C with APU) 
 
 Fuel Capacity (Gal.) Two wing tanks:  Usable 480.4 each; Arm 315.46 in. 
  Fuselage tank:  Usable 133.5; Arm 387.5 in. 
  See NOTE 1 for data on unusable fuel 
 
 Oil Capacity (Gal.) Two engine mounted tanks: Total 2.9 each; usable 1.87 each 
     Arm = +411.24 in. 
  See NOTE 1 for data on unusable oil. 
 
 Max. Operating Altitude 51,000 ft. 
 
 Control Surface Movements Stabilizer Range of Stabilizer Setting (Primary Trim) 
    Max. Up  +2° Max Down  -13° 
  Elevator Up 15.5° +0°, -.5° Down 15° +1° 
  Rudder (perpendicular 
    to hinge) Right 25° +1°, -0° Left 25° +1°, -0° 
  Rudder trim tab Right 11.75°, +1° Left 11.75° +1° 
    (Perpendicular to hinge) (Servo Action 11° +1°, -1°) 
  Aileron Up 12.5° +1°, -0° Down 12.5° +1°, -0° 
     from neutral  from neutral

A9NM                                                                                                   5                                                                                                           Rev. 27 
I. Model 650, Citation III and Citation VI (cont’d) 
 
 Control Surface Movements (cont’d) 
 
  Wing flap positions: Up 0° 
   T.O./Appr 20°,  7° 
   Ldg. 37°, 20°* 
  Speed brakes 
   Panels 2, 3, 6 & 7    0° to 47° +3°, -0° 
  Spoiler 
    Outboard (Panels 1 & 8)    0° to 47° +3°, -0° 
    Inboard (Panels 4 & 5)    0° to 30° +1°, -1° 
  (See Instructions for Continued Airworthiness (ICA) for rigging instructions) 
  *See AFM for required Approach flap settings. 
  
 Serial Nos. Eligible Citation III:  S/N 650-0001 through 650-0199, -0203, 0204, -0205, and -0206 
  Citation VI:  S/N 650-0200, -0201, –0202 and S/N 650-0207 through –0241 
  
 Certification Basis  Model 650, Citation III and Citation VI  
 
(1) Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 25-1 
through 25-39;  
 
 (a) Additions: 
  FAR §§ 25.901(c) and 25.1199 as amended by Amendments 25-1 through 25-40; §§ 25.1309 and 
   25.1351(d) as amended by Amendments 25-1 through 25-41; §§ 25.177, 25.255 and 25.703 as amended 
   by Amendments 25-1 through 25-42; § 25.1326 as amended by Amendments 25-1 through 25-43; §  
  25.1413 as amended by Amendments 25-1 through 25-44; §§ 25.1305 and 25.1529 as amended by  
  Amendments 25-1 through 25-54. 
 
 (b) Additions for the Sperry EDZ-601, EDZ-603, EDZ-605, and SPZ-8000 Electronic Flight Instrument  
  Systems only:  FAR §§ 25.1321(a), (b), (d), and (e), 25.1331, 25.1333, and 25.1335 as amended by  
  Amendments 25-1 through 25-41. 
 
 (c) Addition for airplanes incorporating Cessna EC-20600 Auxiliary Power Unit Inflight Operable 
  Installation:  FAR § 25.901(d) as amended by Amendments 25-1 through 25-46. 
 
(2) FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-12. 
 
(3) SFAR Part 27 as amended by Amendments 27-1 through 27-2, Fuel Venting and Exhaust Emission 
Requirements for Turbine Engine Powered Airplanes. 
 
(4) Special Conditions as follows: 
(a) 25-102-NM-7, High Altitude Operations (51,000 feet).  See NOTE 20. 
(b) 25-ANM-6, Automatic Takeoff Thrust Control System (ATTCS). 
 
(5) Exemption as follows: 
 (a) Exemption No. 3436 from compliance with FAR § 25.1305(d)(3), for type certification without an 
engine rotor system unbalance indicator. 
 
(6) Equivalent levels of safety as follows: 
 (a) FAR § 25.807(d), Emergency exits ditching; 
 (b) FAR § 25.773(b)(2), Cockpit Side Window; 
 (c) FAR § 25.1549(a) and (b), Digital Turbine Speed N2 Indicator; 
 (d) FAR § 25.815, Aisle Width; 
 (e) FAR § 25.812(b)(2), Emergency Exit Signs;  
 (f) FAR § 25.813(e), Passenger Compartment Door; 
 (g) FAR § 25.1305(a)(4), Oil Pressure Indicator (See NOTE 12); 
 (h) FAR § 25.1305(a)(6), Oil Temperature Indicator (See NOTE 12); 
 (i) FAR § 25.1305(c)(1), Gas Temperature Indicator (See NOTE 12); and 
 (j) FAR § 25.1305(c)(3), Tachometer (See NOTE 12).

A9NM                                                                                                   6                                                                                                           Rev. 27 
I. Model 650, Citation III and Citation VI (cont’d) 
 
 Certification Basis  (cont’d)  
 
(7) FAR § 25.801 ditching not complied with. 
 
(8) Compliance with ice protection has been demonstrated in accordance with FAR § 25.1419. 
 
 Application for Type Certificate dated April 30, 1977.  Type Certificate No. A9NM issued April 30, 1982. 
 The Model 650, Citation III and VI, are defined by Cessna Airplane Assembly Drawing Number 6200000. 
 
 Production Basis Production Certificate (P.C.) No. 312.  Effective February 15, 1985 and on, P.C. No. 4 is  
  applicable to all spares production.  See NOTE 9 for specific S/N effectivity of P.C.  
  No. 4. 
 
 Equipment   The basic required equipment as prescribed in the applicable airworthiness regulations  
  (see Certification Basis) must be installed in the aircraft for certification. 
 
 
NOTE 1. Current weight and balance 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: 
 
 WEIGHT – lbs. C.G. LOCATION – in. 
Alcohol 3.4 + 92.5 (full) 
Hydraulic Fluid 37.2 + 379.8 (full) 
Unusable Fuel Wing 56.8 + 304.0 
Unusable Fuel Fuselage 3.0 + 387.2 
Engine Unusable Oil 16.0 + 411.2 
Engine Usable Oil 29.0 + 411.1 (full) 
 
NOTE 2. These airplanes must be operated according to the appropriate FAA approved AFM, including latest 
approved revisions.  FAA approved AFM, P/N 65C3FM-01, is applicable to the Citation III.  FAA 
approved AFM, P/N 65C6FM-03, is applicable to the Citation VI.  Required placards are included in 
Chapter Eleven (11) of the ICA. 
 
NOTE 3. See the FAA approved airworthiness limitation section of the ICA for mandatory compliance retirement 
  life or inspection. 
 
NOTE 4. All replacement seats (crew and passenger), although they may comply with TSO C39, must also be 
  demonstrated to comply with FAR 25.785. 
 
NOTE 5. For operation with 10 or more passengers, Cessna Drawing 6211274 must be complied with. 
 
NOTE 6. The following nose wheel tires are approved: 
 
BFG P/N 031-613-2 S/N 650-0001 through 650-0241 
Goodyear P/N 184F13-5 S/N 650-0001 through 650-0241 
   
BFG P/N 031-613-8 S/N 650-0001 through 650-0093 
not incorporating SB650-32-13 or 
SB650-32-14 
Goodyear P/N 184F13-3 S/N 650-0001 through 650-0093 
not incorporating SB650-32-13 or 
SB650-32-14 
 
NOTE 7. Airplanes modified in accordance with Cessna Drawing 6200011 or Service Bulletin SB650-03-01 are 
eligible for Canadian Registration (S/N 650-0001 through 650-0241).

A9NM                                                                                                   7                                                                                                           Rev. 27 
I. Model 650, Citation III and Citation VI (cont’d) 
 
NOTE 8. Airplanes S/N 650-0001 through 650-0083 incorporating SB650-34-10 or airplanes S/N 650-0064 through 
650-0093 incorporating the optional zero wing fuel weight (EC19432) are eligible for operation with zero 
fuel weight of 16,300 lb. with the following VMO/MMO limitations: 
   305 KIAS below 8,000 ft.  
   336 KIAS at 8,000 ft. with linear decrease to 278 KIAS/.851 M at 36,524 ft. 
   .851 M above 36,524 ft. 
  Zero fuel weight plus fuel in the fuselage tank cannot exceed 16,300 lb. 
 
NOTE 9. P. C. No. 4 effective at Serial 650-0079 through 650-0241. 
 
NOTE 10. Deleted at Rev. 25. 
 
NOTE 11. Applicable to those airplanes incorporating EC 19112 or SB650-76-1.  Automatic Performance Reserve  
  Installation. 
 
NOTE 12. Applicable to those airplanes incorporating EC 20600 Auxiliary Power Unit Inflight Operable Installation. 
 
NOTE 13. Airplanes S/N 650-0100 through 650-0178 which are modified in accordance with Cessna Drawing 
  6200019 are eligible for export to France. 
 
NOTE 14. Equipment installations or other modifications to the tailcone area must be coordinated with the Wichita  
  Aircraft Certification Office. 
 
NOTE 15. Airplanes S/N 650-0100 through 650-0178 which are modified in accordance with Cessna Drawing 6200012  
  are eligible for export to the United Kingdom. 
 
NOTE 16. Airplanes S/N 650-0001 through 650–0241 which are modified in accordance with Cessna Drawing 6200017 
are eligible for export to Denmark. 
 
NOTE 17. Airplanes S/N 650-0001 through 650-0241 which are modified in accordance with Cessna Drawing 6200018  
  are eligible for export to Brazil. 
 
NOTE 18. Applicable to airplane S/N 650-0227 through 650-0241, and prior serial numbers that incorporate Service  
  Bulletin SB650-72-01. 
 
NOTE 19. Deleted at Rev. 25.  
 
NOTE 20. Model 650, Citation III and VI, airplanes have been approved for high altitude operations (altitudes above 
41,000 feet), by Special Conditions.  Any modifications to the pressure vessel must be approved in 
accordance with the requirements as shown in the certification basis.  This includes modifications which 
could result in a pressure vessel opening, either through crack-growth or antenna loss, greater than 3.98 sq. 
in. 
 
NOTE 21. Model 650, Citation III, airplanes that incorporate the factory installed Honeywell SPZ-8000 (IFCS) and have 
accomplished Cessna Service Bulletin SB650-34-97, meet the initial airworthiness requirements for operation 
in Reduced Vertical Separation Minimum (RVSM) airspace.  Model 650, Citation III or Citation VI, 
airplanes that incorporate the factory installed Honeywell SPZ-650 (AFCS) and have accomplished Cessna 
Service Bulletin SB650-34-107 or SB650-34-105 respectively, meet the initial airworthiness requirements for 
operation in RVSM airspace.  Each operator must obtain final RVSM operating approval directly from the 
FAA.

A9NM                                                                                                   8                                                                                                           Rev. 27 
II. Model 650, Citation VII, (Transport Category), Approved January 23, 1992 
 
 Engines Two Garrett TFE731-4R-2S 
 
 Fuel Commercial kerosene Jet A, Jet B, Jet A-1, JP-4, JP-5, and JP-8 fuel, conforming to  
  AiResearch Manufacturing Co. Fuel Specifications EMS 53111, EMS 53112, or EMS  
  53116. 
     
 Engine Limits Static thrust standard day, sea level: TFE731-4R-2S 
   Takeoff (5 min.) 4080 lb. 
   Max. continuous 4080 lb.  
   
  Max. permissible engine rotor operating speed: 
   N1 (Fan) steady state 101.5% r.p.m. 
   N2 (Gas gen.) steady state 101% r.p.m. 
   N1 (Fan)  101.5% to 104.5% r.p.m. limited to 5 sec. 
   N2 (Gas gen.) 101% to 103% r.p.m. limited to 5 sec. 
 
  Max. permissible interturbine gas temperatures: 
   Takeoff (5 minutes) 952° C. 
    974° C. (Emergency only) 
   Max. continuous 924° C. 
   Starting 952° C. 
 
 Airspeed Limits VMO  (Maximum Operating) 275 KIAS below 8000 ft. 
     (Calibrated Altitudes) 336 KIAS at 8000 ft. with 
    linear decrease to 278  
    KIAS/.851 M at 36,524 ft. 
    See NOTE 8 for alternate 
    VMO & ZFW 
 
  MMO  (Calibrated Altitude) .851 M above 36,524 ft. 
 
 
  VA  (Sea level) 14,500 lb.  177 KIAS 
    16,500 lb. 191 KIAS 
    19,600 lb. 210 KIAS 
    23,000 lb. 227 KIAS 
  See AFM for variations with weight and altitude and optional configurations. 
 
  VB  (Speed for maximum gust intensity)   220 KIAS 
  VFE (Flaps extended) 
   Partial flaps, 7° or 20°   210 KIAS 
   Ldg Position - Full Flaps   170 KIAS 
  VMCA (Minimum control speed) Air   103 KIAS 
  VMCG (Minimum control speed) Ground   102 KIAS 
   (19,000 lb.. and below, see AFM for variation with weight) 
  VLO (Landing gear operating)   210 KIAS 
  VLE (Landing gear extended)   210 KIAS 
  Landing light extended    250 KIAS 
  Max. Tire Ground Speed   165 knots 
  Speed Brakes Extension Speed Maximum No Limit 
    Panels 2, 3, 6 & 7 Minimum VREF + 15 KIAS 
  Extension of the speed brakes with the flaps in any position other than 
  the UP position is prohibited below 500 feet AGL.  Above 500 feet AGL the 
  speed brakes may be extended with the flaps in any position.

A9NM                                                                                                   9                                                                                                           Rev. 27 
II. Model 650, Citation VII (cont’d) 
 
 Airspeed Limits  (cont’d) Spoiler Extension Speed (In flight restricted to emergency descent) 
  Panels 1, 2, 3, 4, 5, 6, 7 & 8 
   Maximum  VMO/MMO 
   Minimum  150 KIAS 
 
  Spoiler extension in flight is restricted to emergency descent use.  Extension of the  
  spoilers is prohibited in flight with the flaps in  any position other than the up position. 
 
  There is no restriction on roll control spoilers (Panels 1 & 8) 
 
 C.G. Range   (Landing Gear Extended)  
  Forward limit: Linear variation from 324.55 inches aft of datum (24.21% MAC) at 23,000 lb. to 
316.20 inches aft of datum (14.00% MAC) at 19,000 lb.;  316.20 inches aft of datum 
(14.00% MAC) at 19,000 lb. to 16,500 lb.; Linear variation from 316.20 inches aft 
of datum (14.00% MAC) at 16,500 lb. to 321.00 inches aft of datum (19.86% MAC) 
at 14,500 lb. 
  Aft Limit:  Linear variation from 324.55 inches aft of datum (24.21% MAC) at 23,000 lb. to 
330.10 inches aft of datum (31.00 % MAC) at 22,450 lb.; 330.10 inches aft of datum 
(31.00 % MAC) at 22,450 lb. to 13,705 lb. 
 
 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 Water Line 127.25. 
  
 MAC 81.725 in. (L.E. of MAC at Sta. +304.768) 
  
 Leveling Means Seat rails 
 
 Maximum Weight Ramp 23,200 Pounds 
  Takeoff 23,000 Pounds 
  Landing 20,000 Pounds 
  Zero fuel 16,500 Pounds 
  Alternate Zero Fuel (See NOTE 8) 15,350 Pounds 
   
 Minimum Crew For all flights:  2 persons (pilot and co-pilot) 
 
 No. of Seats 15 (2 pilots, 13 passengers)    See NOTE 5 
 
 Maximum Baggage Tail compartment      700 lb. (500 lb. for A/C with APU) 
   
 Fuel Capacity (Gal.) Two wing tanks:  Usable 480.4 each; Arm 315.46 in. 
  Fuselage tank:  Usable 133.5; Arm 387.5 in. 
  See NOTE 1 for data on unusable fuel 
 
 Oil Capacity (Gal.) Two engine mounted tanks: Total 2.9 each; usable 1.87 each 
   Arm = +411.24 in. 
  See NOTE 1 for data on unusable oil 
 
 Max. Operating Altitude 51,000 ft.

A9NM                                                                                                   10                                                                                                           Rev. 27 
II. Model 650, Citation VII (cont’d) 
 
 Control Surface Movements Stabilizer Range of Stabilizer Setting (Primary Trim) 
    Max. Up  +2° Max Down  -13° 
  Elevator Up 15.5° +0°, -.5° Down 15° +1° 
  Rudder (perpendicular 
    to hinge) Right 25° +1°, -0° Left 25° +1°, -0° 
  Rudder trim tab Right 11.75°, +1° Left 11.75° +1° 
    (Perpendicular to hinge) (Servo Action 11° +1°, -1°) 
  Aileron Up 12.5° +1°, -0° Down 12.5° +1°, -0° 
     from neutral  from neutral 
  Wing flap positions: Up 0° 
   T.O./Appr 20°,  7° 
   Ldg 37°, 20°* 
  Speed brakes 
   Panels 2, 3, 6 & 7    0° to 47° +3°, -0° 
  Spoiler 
    Outboard (Panels 1 & 8)    0° to 47° +3°, -0° 
    Inboard (Panels 4 & 5)    0° to 30° +1°, -1° 
  (See Instructions for Continued Airworthiness for rigging instructions) 
  *See AFM for required Approach flap settings. 
 
 Serial Nos. Eligible 650-7001 through 650-7119 
 
 Data Pertinent to Model 650, Citation VII 
 
Certification Basis  
 
(1) Part 25 of the Federal Aviation Regulations effective February 1, 1965, as amended by Amendments 25-1 
through 25-39;  
 
(a) Additions: 
        FAR §§ 25.901(c) and 25.1199 as amended by Amendments 25-1 through 25-40; §§ 25.1309 and 
25.1351(d) as amended by Amendments 25-1 through 25-41; §§ 25.177, 25.255 and 25.703 as amended 
by Amendments 25-1 through 25-42; § 254.1326 as amended by Amendments 25-1 through 25-43; § 
25.1413 as amended by Amendments 25-1 through 25-44; §§ 25.1305 and 25.1529 as amended by 
Amendments 25-1 through 25-54; § 25.904 as amended by Amendments 25-1 through 25-62; § 25.773 
as amended by Amendments 25-1 through 25-72. 
 
(b) Additions for the Sperry SPZ-8000 Digital Integrated Flight Control System only: 
 FAR §§ 25.1321(a), (b), (d), and (e), 25.1331, 25.1333, and 25.1335 as amended by Amendments 
        25-1 through 25-41. 
 
(c) Addition for airplanes equipped with inflight operable Auxiliary Power Unit (APU): 
 FAR § 25.901(d) as amended by Amendments 25-1 through 25-46.  
 
(2) FAR Part 36 effective December 1, 1969, as amended by Amendments 36-1 through 36-18. 
 
(3) FAR Part 34 effective September 10, 1990, Fuel Venting and Exhaust Emission Requirements for Turbine 
Engine Powered Airplanes. 
 
(4) Special Conditions as follows: 
(a) 25-102-NM-7, High Altitude Operations (51,000 feet).  See NOTE 10. 
(b) 25-ANM-54, Protection from the induced effects of lightning and High Intensity Radiated Fields (HIRF) 
due to installation of digital electronic engine controls. 
 
(5) Exemption as follows: 
(a) Exemption No. 3436 from compliance with FAR § 25.1305(d)(3), for type certification without an 
engine rotor system unbalance indicator.

A9NM                                                                                                   11                                                                                                           Rev. 27 
II. Model 650, Citation VII (cont’d) 
 
 Data Pertinent to Model 650, Citation VII (cont’d) 
 
(6) Equivalent levels of safety as follows: 
(a) FAR § 25.807(d), Emergency exits ditching; 
(b) FAR § 25.1549(a) and (b), Digital Turbine Speed N2 Indicator; 
(c) FAR § 25.815, Aisle Width; 
(d) FAR § 25.812(b)(1), Emergency Exit Signs;  
(e) FAR § 25.813(e), Passenger Compartment Door; 
(f) FAR § 25.1305(a)(4), Oil Pressure Indicator (See NOTE 9); 
(g) FAR § 25.1305(a)(6), Oil Temperature Indicator (See NOTE 9); 
(h) FAR § 25.1305(c)(1), Gas Temperature Indicator (See NOTE 9); and 
(i) FAR § 25.1305(c)(3), Tachometer (See NOTE 9). 
 
(7) FAR § 25.801 ditching not complied with. 
 
(8) Compliance with ice protection has been demonstrated in accordance with FAR § 25.1419. 
 
 The Model 650, Citation VII, is defined by Cessna Airplane Assembly Drawing Number 6200000. 
 
 Production Basis Production Certificate No. 4. 
 
 Equipment   The basic required equipment as prescribed in the applicable airworthiness regulations  
  (see Certification Basis) must be installed in the aircraft for certification. 
 
 
NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and  
  loading instructions when necessary must be provided for each airplane at the time of original certification. 
 
  The certified empty weight and corresponding center of gravity location must include: 
   Hydraulic Fluid 37.2 lb.  +  379.8 in. (full) 
   Unusable Fuel Wing 56.8 lb.  +  304.0 in. 
   Unusable Fuel Fuselage   3.0 lb.  +  387.2 in. 
   Engine Unusable Oil 16.0 lb.  +  411.2 in. 
   Engine Usable Oil 29.0 lb.  +  411.1 in. (full) 
 
NOTE 2. The airplane must be operated according to the FAA approved AFM, P/N 65C7FM-09, (or later approved 
revision).  For applications requiring ICAO units, AFM, P/N 65C7EU-00, is equivalent to P/N 65C7FM-
09.  Required placards are included in Chapter Eleven (11) of the ICA. 
 
NOTE 3. See the FAA approved airworthiness limitation section of the ICA [Chapter 4 of Maintenance Manual] for 
mandatory compliance retirement life or inspection. 
 
NOTE 4. All replacement seats (crew and passenger), although they may comply with TSO C39, must also be 
  demonstrated to comply with FAR 25.785. 
 
NOTE 5. For operation with 10 or more passengers, Cessna Drawing 6211274 must be complied with. 
 
NOTE 6. The following nose wheel tires are approved: 
BFG P/N 031-613-2 
Goodyear P/N 184F13-5 
 
NOTE 7. Equipment installations or other modifications to the tailcone area must be coordinated with the Wichita  
  Aircraft Certification Office.

A9NM                                                                                                   12                                                                                                           Rev. 27 
II. Model 650, Citation VII (cont’d) 
 
NOTE 8. The following alternate VMO/MMO limitations apply when airplanes are loaded to the alternate zero fuel  
  weight of 15,350 pounds: 
   275 KIAS below 8000 ft. 
   346 KIAS at 8000 ft. with linear decrease to 293 KIAS/.851 M at 34,275 ft.  
   .851 M above 34,275 ft. 
 
NOTE 9. Applicable to those airplanes incorporating Auxiliary Power Unit Inflight Operable Installation. 
 
NOTE 10. Model 650, Citation VII, airplanes has been approved for high altitude operations (altitudes above 41,000 
feet), by Special Conditions.  Any modifications to the pressure vessel must be approved in accordance 
with the requirements as shown in the certification basis.  This includes modifications which could result 
in a pressure vessel opening, either through crack-growth or antenna loss, greater than 3.98 sq. in. 
 
NOTE 11. Model 650, Citation VII, S/N 650-7001 through 650-7075, airplanes that have accomplished Cessna Service 
Bulletin SB650-34-97, and Model 650, Citation VII, S/N 650-7076 through 650-7119, airplanes meet the 
initial airworthiness requirements for operation in Reduced Vertical Separation Minimum (RVSM) airspace.  
Each operator must obtain final RVSM operating approval directly from the FAA. 
 
 
.....END......
```

## ADs (28, 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 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 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 2013-09-11](https://openairdocs.org/ad/2013-09-11): Air Conditioning · Cessna 500, 501, 550 and 5 more. Effective Jul 5, 2013
- [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 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 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 2005-13-21](https://openairdocs.org/ad/2005-13-21): Actuator control unit (ACU) · Cessna 650. Effective Jul 29, 2005
- [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 2002-22-12](https://openairdocs.org/ad/2002-22-12): Titeflex hoses · BAE Systems ATP, Avro 146-RJ100A, Avro 146-RJ70A and 122 more. Effective Dec 13, 2002
- [AD 2002-14-24](https://openairdocs.org/ad/2002-14-24): Side Brace Mechanism Assembly of Main Landing Gear · Cessna 650. Effective Aug 26, 2002
- [AD 97-12-01](https://openairdocs.org/ad/97-12-01): Wire Bundle Assembly · Cessna 650. Effective Jun 19, 1997
- [AD 96-25-12](https://openairdocs.org/ad/96-25-12): Auxiliary Power Units · BAE Systems HS 748 Series 2A, HS 748 Series 2B, 707-100 Long Body and 74 more. Effective Jan 13, 1997
- [AD 95-24-10](https://openairdocs.org/ad/95-24-10): Tires · Cessna 650 and Tires. Effective Feb 21, 1996
- [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 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 92-27-08](https://openairdocs.org/ad/92-27-08): Elevator Control · Cessna 650. Effective Jan 4, 1993
- [AD 90-25-06](https://openairdocs.org/ad/90-25-06): DME Antenna Cable Connectors · Cessna 650. Effective Dec 11, 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 90-01-03](https://openairdocs.org/ad/90-01-03): Attitude and Heading Reference System · Bombardier ATR42-300, DHC-8-101, DHC-8-102 and 16 more. Effective Feb 5, 1990
- [AD 89-03-16](https://openairdocs.org/ad/89-03-16): Avionics Bus Relays · Cessna 650. Effective Apr 5, 1989
- [AD 88-23-04](https://openairdocs.org/ad/88-23-04): AFM Changes -- Elevator · Cessna 650. Effective Feb 21, 1989
- [AD 88-24-16](https://openairdocs.org/ad/88-24-16): Cabin Electrical Power · Cessna 650 and S550. Effective Dec 12, 1988
- [AD 87-06-02](https://openairdocs.org/ad/87-06-02): Electronic Flight Instrument Systems Symbol Generators · ATR - GIE Avions de Transport R gional ATR42-200, ATR42-300, ATR42-320 and 19 more. Effective May 11, 1987
- [AD 86-14-01](https://openairdocs.org/ad/86-14-01): Attitude Heading Reference System · ATR - GIE Avions de Transport R gional ATR42-200, ATR42-300, ATR42-320 and 19 more. Effective Jul 14, 1986
- [AD 85-03-51](https://openairdocs.org/ad/85-03-51): Aircraft Battery Inspection · Cessna 552 and 650. Effective Apr 11, 1985
- [AD 84-08-02 R1](https://openairdocs.org/ad/84-08-02-R1): Placard-Usable Fuel · Cessna 650. Effective Jan 28, 1985
- [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

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna 650](https://openairdocs.org/model/cessna-650): 201 aircraft (registry code 2076802)

## STCs approved under this data sheet (225, 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 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 ST00452WI](https://openairdocs.org/stc/ST00452WI): Installation of an AlliedSignal Avionics Inc, CAS 67A traffic Alert and Collison Avoidance system (TCAS II).. Duncan Aviation Inc.
- [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC
- [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 ST03292CH](https://openairdocs.org/stc/ST03292CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development, Inc.
- [STC ST00296WI](https://openairdocs.org/stc/ST00296WI): Installation of a TCAS-791 traffic alert and collision avoidance system (TCAS I).. 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 ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC
- [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 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 ST01070DE](https://openairdocs.org/stc/ST01070DE): Installation of the Curtiss-Wright Fortress Flight Data Recorder (with Cockpit Voice Recorder). Peregrine
- [STC ST10167SC](https://openairdocs.org/stc/ST10167SC): Installation of interior lighting system.. Heads Up Technologies Inc.
- [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 ST00029IB](https://openairdocs.org/stc/ST00029IB): Installation of Deviations to FAA STC ST02654LA. Mid Canada Mod Center
- [STC ST04281AT](https://openairdocs.org/stc/ST04281AT): Installation for the Upgrade of the NZ-2000 FMS computer for software version NZ6.. Chippewa Aerospace Inc
- [STC ST00818DE](https://openairdocs.org/stc/ST00818DE): Installation of Honeywell Control Display Unit (CDU) model CD-830. Premier Air Center LLC
d/b/a West Star Aviation
- [STC ST04503CH](https://openairdocs.org/stc/ST04503CH): Upgrade Dual Honeywell FMZ-2000 / NZ 6.1 With WAAS-LPV in accordance with StandardAero Master Data List 1039558, Revision (C), Dated May 20, 2021 or later FAA approved revision.. StandardAero Business Aviation Services LLC
- [STC ST04638NY](https://openairdocs.org/stc/ST04638NY): Installation of the GOGO Avance L3 System. MidCanada Mod Center
- [STC ST01015WI](https://openairdocs.org/stc/ST01015WI): Installation of the Collins FDS-2000 EFIS.. Blackhawk Aerospace Technologies Inc.
- [STC ST01016WI](https://openairdocs.org/stc/ST01016WI): Installation of a dual Collins AHS-3000A AHRS.. Blackhawk Aerospace Technologies Inc.
- [STC ST01227WI](https://openairdocs.org/stc/ST01227WI): Installation of IS&S Air Data System. Data required: (1) Columbia Avionics, Inc. Master Document List No. 30141324, Revision 3, dated January 21, 2004; and (2) FAA Approved Flight Manual Supplement 30141339, dated January 28, 2004, or later FAA Approved Revisions to (1) or (2).. Blackhawk Aerospace Technologies Inc.
- [STC ST01257WI](https://openairdocs.org/stc/ST01257WI): Reduced Vertical Separation Minimum (RVSM) group airworthiness approval of Cessna Model 650 Citation III Aircraft.. Blackhawk Aerospace Technologies Inc.
- [STC ST01309WI](https://openairdocs.org/stc/ST01309WI): Installation of a Honeywell MK-VIII EGPWS system.  Data required: (1) Columbia Avionics, Inc. Master Document List No. 30141108, Revision 2, dated February 21, 2005; and (2) FAA Approved Flight Manual Supplement 30141123, dated February 25, 2005, or later FAA Approved Revisions to (1) or (2).. Blackhawk Aerospace Technologies Inc.
- [STC ST01446WI](https://openairdocs.org/stc/ST01446WI): Installation of Universal Avionics EFI-890R Flat Panel EFIS System .. Blackhawk Aerospace Technologies Inc.
- [STC ST01683WI](https://openairdocs.org/stc/ST01683WI): Installation of Garmin GTN Series GPS/Comm/Nav Systems with optional Garmin GDL-69/A XM Weather Data Link, GTX-33 series Transponders and optional Bendix/King KMR-675 Marker Beacon Receiver. Blackhawk Aerospace Technologies Inc.
- [STC ST01853WI](https://openairdocs.org/stc/ST01853WI): Installation of Garmin GTS Traffic Sensor with Garmin GTX 3000 Mode S Transponders and ADS-B Out. Blackhawk Aerospace Technologies Inc.
- [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC ST00963LA](https://openairdocs.org/stc/ST00963LA): ONE ONLY STC, SN 650-0005: Installation of Honeywell Total Aircraft Information system (TAIS).. Honeywell International Inc
- [STC ST00691LA](https://openairdocs.org/stc/ST00691LA): Installation of Honeywell/Racal Intermediate gain satellite communication system.. Honeywell International Inc
- [STC SA3461NM](https://openairdocs.org/stc/SA3461NM): Installation of a Honeywell, Inc. FMZ-800 Flight Management System (FMS). Honeywell International Inc
- [STC SA3451NM](https://openairdocs.org/stc/SA3451NM): Installation of Sperry SPZ-8000 Digital Integrated Flight Control System.. Honeywell International Inc
- [STC SA5030NM](https://openairdocs.org/stc/SA5030NM): Addition of Honeywell GPS sensor unit to FAA approved Honeywell FMS installation.. Honeywell International Inc
- [STC SA2269NM](https://openairdocs.org/stc/SA2269NM): ONE ONLY STC, SN 650-0005; Installation of dual Sperry EDZ-601 Electronic Flight Instrument Systems (EFIS) and a Global GNS-500A VLF/Omega Navigation System with a NDB-2 Data Base. Honeywell International Inc
- [STC SA6046NM](https://openairdocs.org/stc/SA6046NM): Installation of Primus 2000 integrated avionics system.. Honeywell International Inc
- [STC ST02635LA](https://openairdocs.org/stc/ST02635LA): Modification to replace the existing Mode S Transponder system with the ACSS NXT-600 Mode S Transponder with ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC
- [STC ST00882DE](https://openairdocs.org/stc/ST00882DE): Installation of Becker Avionics BXT6553 transponder. Peregrine
- [STC ST01027DE](https://openairdocs.org/stc/ST01027DE): Installation of MarathonNorco Aerospace Inc Nickel Cadmium battery in place of existing Nickel Cadmium main aircraft battery/batteries. MarathonNorco Aerospace Inc
- [STC ST04359NY](https://openairdocs.org/stc/ST04359NY): Installation of Interior Modifications. Ramm Aerospace Inc.
- [STC ST00934DE](https://openairdocs.org/stc/ST00934DE): Installation of Becker Avionics BXT6553 transponder. Peregrine
- [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS
- [STC ST00835DE](https://openairdocs.org/stc/ST00835DE): Installation of Automatic Dependent Surveillance - Broadcast (ADS-B) Out and In functionality using the Garmin GTX 335R and GTX 345R Transponders plus qualified position sensor. Peregrine
- [STC ST02654LA](https://openairdocs.org/stc/ST02654LA): Installation of lnSight® Display System, EIU, TAWS Class A, and UNS-1Fw SBAS FMS (with ADS-B Out function). Universal Avionics Systems Incorporated

All 225: https://openairdocs.org/tcds/A9NM/stcs.md

---
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