# TCDS T00007WI: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 19
- Revised: October 20, 2020
- Product: Aircraft, Large Airplane
- Certification basis: Part 21, Part 25, Part 26, Part 34, Part 36
- Registered aircraft: 288, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/d9/58/d95853131746006e5476d15917b8b3c99226dd8cb987483a4dcdaa9193fc4895
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4849020E23BA20458625860900457098.0001
- Page: https://openairdocs.org/tcds/T00007WI

## Models (1)

As the data sheet lists them.

- 750

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
P a g e  N o .  1  2  3  4  5  6  7  8  9  1 0  1 1  1 2  
Rev. No. 19 14 14 14 14 14 19 14 19 14 14 18 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 T00007WI 
Revision 19 
  Textron Aviation Inc.  
750 
October 20, 2020 
 
TYPE CERTIFICATE DATA SHEET NO. T00007WI 
 
This data sheet which is part of Type Certificate No. T00007WI 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 Avation Inc. 
 One Cessna Boulevard 
 Wichita, KS  67215 
 
Type Certificate Holder Record: Cessna Aircraft Company transfe rred to 
 Textron Aviation Inc. on July 29, 2015. 
 
I. Model 750 (Transport Cate gory) S/N 750-0001 through 750-0500 Approved May 31, 1996; S/N 750-0501 and On 
Approved June 25, 2014  
 
The Model 750 is defined by Cessna Airplane Assembly Drawing Number 6700000. 
 
 Engines For airplane seria l numbers 750-0001 through 750-0172 not incorporating Cessna 
Service Bulletin SB 750-71-10: 
 
Two Rolls-Royce Model AE 3007C engines, part number 23057202.   
 
 For airplane serial numbe rs 750-0173 through 750-0500 and aircraft incorporating 
Cessna Service Bulletin SB 750-71-10: 
 
Two Rolls-Royce Model AE 3007C1 engines, part number 23074408.   
 
 For airplane serial numbers 750-0501 and on: 
 
Two Rolls-Royce Model AE 3007C2 engines, part number 23090589.   
 
 Fuel Jet A, Jet A-1, and Jet B , per ASTM D1655, Jet Fuel No. 3 (GB6537-94), RT and TS-1 
per GOST 10227, RT per GSTU 320.00149943.007, TS-1 per GSTU 320.00149943.011, 
JP-4 and JP-5 per MIL-T-5624, JP-8 per MIL-T-83133, NATO F34, F35, F40, F43 and 
F44. EGME (ATSM D4171, Class 1, or MIL-T-27686) or DIEGME (ASTM D4171, 
Class 3, or MILT- 85470) anti-icing additive may be blended into the aircraft fuel in 
concentrations of not more that 0.15 percent by volume.  Mixtures of EGME and 
DIEGME are permissible if combined concentrations are within limits.  JP-4, JP-8, F43 
and F44 fuels may have antiicing additive preblended.  Hammonds Biodor JF additive is 
permitted up to maximum concentration of 270 parts per million.  See the Airplane Flight 
Manual (AFM) for fueling procedures.

Rev. 19 Page 2 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
 Engine Limits  
 
 Airspeed Limits  
(For airplane serial numbers 750-0001 through 750-0172 not incorporating Cessna Service Bulletin SB 750-71-10) 
    V MO (Maximum Operating)   
     Below 8000 ft.  270 KIAS (270 KCAS) 
    8000 ft. to 30,650 ft. 350 KIAS (350 KCAS)  
    M MO  (Maximum Operating)  
    Above 30,650 ft.  0.92 Mach i ndicated (0.92 Mach calibrated) 
   V A (Maneuvering Sea Level)  
       35,700 lbs. 221 KIAS (221 KCAS)  
    See AFM for variations with  weight and altitude and optional configurations. 
    V B (Speed for maximum gust intensity)  
     Below 37,575 ft. 300 KIAS (300 KCAS) 
     Above 37,575 ft. 0.92 Mach i ndicated (0.92 Mach calibrated) 
    V RA  (Rough air speed)  
     Below 36,480 ft.  300 KIAS (300 KCAS)  
     Above 36,480 ft.  0.90 Mach  indicated (0.90 Mach calibrated)  
    V FE (Flaps extended) 
     F l a p s  5  250 KIAS (251 KCAS) 
     F l a p s  1 5   210 KIAS (210 KCAS) 
      Flaps Full 180 KIAS (178 KCAS) 
Maximum Slats Extended Speed 250 KIAS (251 KCAS) 
VMCA (Minimum control speed) Air    
  Flaps 5º 118 KIAS (118 KCAS)  
  Flaps 15º 110 KIAS (109 KCAS)  
   V MCL (Minimum control speed) Landing  
     Flaps 15º 113 KIAS (112 KCAS)  
     Flaps Full 106 KIAS (105 KCAS) 
   V MCG (Minimum control speed) Ground  
     Flaps 5º 109 KIAS (108 KCAS)  
     Flaps 15º 109 KIAS (108 KCAS)  
 AE3007C2 AE3007C13 AE3007C2 
Static thrust standard day, sea level:    
Takeoff  6442 lbs. 6764 lbs. 7042 lbs. 
Max. continuous  6442 lbs.  6764 lbs. 7042 lbs. 
Max. permissible engine rotor operating speed:    
N1  (Fan)   steady state  100%  r.p .m. 100%  r.p.m. 93.2%  r.p.m.  
N2  (Gas gen.)   steady state  101.6%  r.p.m. 101.6%  r.p.m. 102. 6%  r.p.m. 
Max. permissible interturbine gas temperatures:    
Takeoff (5 minute limit)   888 C 1850 C 907 C 899° C 
Max. continuous    850 C 857  C 867° C 
Starting:     
Starter assisted    800 C 800  C 800° C4 
Windmill   888 C 1850 C 888 C 800° C4 
1  For airplane serial numbers 750-0003 through 750-0022 not inc orporating Cessna Service Bulletin SB 750-34-04 
2 For airplane serial numbers 750-0001 through 750-0172 not inco rporating Cessna Service Bulletin SB 750-71-10 
3  For airplane serial numbers 750-0173 through 750-0500 and air craft incorporating Cessna Service Bulletin SB 750-71-10 
4  Engine temperature can exceed  800°C up to 850°C for a total accumulated time of up to 5 seconds. An exceedance of this limit 
will be annunciated by the EIS.

Rev. 19 Page 3 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
 Airspeed Limits (cont’d) 
   V LO (Landing gear operati ng) 210 KIAS (208 KCAS) 
   V LE   (Landing gear extended) 210 KIAS (208 KCAS) 
   Max. tire ground speeds:  182 Knots 
   Speed Brakes Extension Speed No Limit 
   There is no restriction on ro ll control spoilers (Panel #1, #2, #9, & #10). 
 
(For airplane serial numbers 750-0173 through 750-0500 and aircraft incorporating Cessna Service Bulletin SB 750-71-10) 
    V MO (Maximum Operating)   
     Below 8000 ft.  270 KIAS (270 KCAS) 
    8000 ft. to 30,650 ft. 350 KIAS (350 KCAS)  
    M MO  (Maximum Operating)  
    Above 30,650 ft.  0.92 Mach i ndicated (0.92 Mach calibrated) 
   V A (Maneuvering Sea Level)  
     36,100 lbs. 223 KIAS (223 KCAS)    
    See AFM for variations with  weight and altitude and optional configurations. 
    V B (Speed for maximum gust intensity)  
     Below 37,575 ft. 300 KIAS  (300 KCAS) 
     Above 37,575 ft. 0.92 Mach i ndicated (0.92 Mach calibrated) 
    V RA  (Rough air speed)  
     Below 36,480 ft.  300 KIAS (300 KCAS)  
     Above 36,480 ft.  0.90 Mach  indicated (0.90 Mach calibrated)  
    V FE (Flaps extended) 
     F l a p s  5  250 KIAS (251 KCAS) 
     F l a p s  1 5   210 KIAS (210 KCAS) 
      Flaps Full 180 KIAS (178 KCAS) 
Maximum Slats Extended Speed 250 KIAS (251 KCAS) 
VMCA (Minimum control speed) Air    
  Flaps 5º 120 KIAS (120 KCAS)  
  Flaps 15º 112 KIAS (112 KCAS)  
   V MCL (Minimum control speed) Landing  
     Flaps 15º 116 KIAS (115 KCAS)  
     Flaps Full 108 KIAS (107 KCAS) 
   V MCG (Minimum control speed) Ground  
     Flaps 5º 110 KIAS (111 KCAS) 
     Flaps 15º 110 KIAS (111 KCAS)  
   V LO (Landing gear operati ng) 210 KIAS (208 KCAS) 
   V LE   (Landing gear extended) 210 KIAS (208 KCAS) 
   Max. tire ground speeds:  182 Knots 
   Speed Brakes Extension Speed No Limit 
   There is no restriction on ro ll control spoilers (Panel #1, #2, #9, & #10). 
(For airplane serial numbers 750-0501 and on) 
    V MO (Maximum Operating)   
     Below 8000 ft.  270 KIAS (270 KCAS) 
    8000 ft. to 31,500 ft. 350 KIAS (350 KCAS)  
    M MO  (Maximum Operating)  
    Above 31,500 ft.  0.935 Mach i ndicated (0.935 Mach calibrated) 
   V A (Maneuvering Sea Level)  
     36,600 lbs. 220 KIAS (220 KCAS)    
    See AFM for variations with  weight and altitude and optional configurations. 
    V B (Speed for maximum gust intensity)  
     Below 8,000 ft.   225 KIAS (225 KCAS)  
     8,000 ft. – 38,393 ft.  300 KIAS (300 KCAS)  
     Above 38,393 ft.   0.935 Mach  indicated (0.935 Mach calibrated)

Rev. 19 Page 4 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
 Airspeed Limits (cont’d) 
    V RA  (Rough air speed)  
     Below 8,000 ft.   225 KIAS (225 KCAS)  
     8,000 ft. – 34,800 ft.  300 KIAS (300 KCAS)  
     Above 34,800 ft.   0.87 Mach  indicated (0.87 Mach calibrated)  
    V FE (Flaps extended) 
     Flaps 1 250 KIAS (250 KCAS) 
     Flaps 2  210 KIAS (210 KCAS) 
      Flaps Full 180 KIAS (181 KCAS) 
Maximum Slats Extended Speed 250 KIAS (250 KCAS) 
VMCA (Minimum control speed) Air    
  Flaps 1 121 KIAS (123 KCAS)  
  Flaps 2 114 KIAS (116 KCAS)  
   V MCL (Minimum control speed) Landing  
     Flaps 2 124 KIAS (125 KCAS)  
     Flaps Full 116 KIAS (116 KCAS) 
   V MCG (Minimum control speed) Ground  
     Flaps 1 122 KIAS (120 KCAS)  
     Flaps 2 118 KIAS (116 KCAS)  
   V LO (Landing gear operati ng) 210 KIAS (208 KCAS) 
   V LE   (Landing gear extended) 210 KIAS (208 KCAS) 
   Max. tire ground speeds:  182 Knots 
   Speed Brakes Extension Speed No Limit 
   There is no restriction on ro ll control spoilers (Panel #1, #2, #9, & #10). 
 
 C.G. Range  
      (Landing Gear Extended) Maximum Design C.G. Limits 
 
 (1) Aft Limits (For airplane  serial numbers 750-0001 through 750-0172 not incorporating Cessna 
Service Bulletin SB 750-71-10) 
20.50% MAC from 35,700 lbs. to 35,100 lbs.; linear variation from 20.50% MAC at  
   35,100 lbs. to 33.00% MAC at 29,400 lbs.; 33.00% MAC at 29,400 lbs. to 26,754 lbs.;  
   linear variation from 33.00% M AC at 26,754 lbs. to 34.42% MAC at 25,700 lbs.; linear  
   variation from 34.42% MAC at 25,700 lbs. to 35.00%  MAC at 25,269 lbs.; 
   35.00% MAC at 25,269 lbs. to 21,310 lbs. 
   (For airplane serial numbers 750-0173 through 750-0500 and aircraft incorporating 
Cessna Service Bulletin SB 750-71-10) 
20.50% MAC from 36,100 lbs. to 35,100 lbs.; linear variation from 20.50% MAC at 
35,100 lbs. to 33.00% MAC at 29,400 lbs.; 33.00% MAC at 29,400 lbs. to 26,754 lbs.; 
linear variation from 33.00% MAC at 26,754 lbs. to 34.42% MAC at 25,700 lbs.; linear 
variation from 34.42% MAC at 25,700 lbs. to 35.00% MAC at 25,269 lbs.; 35.00% MAC 
at 25,269 lbs. to 21,310 lbs. 
 (For airplane serial numbers 750-0501 and on) 
35.00% MAC at 21,310 lbs to 25,269 lbs; 33.00% MAC at 26,754 lbs to 29,600 lbs.; 
20.50% MAC at 35,400 lbs to 36,900 lbs. 
With straight line variation between points. 
 
 (2) Forward Limits  (For airplane serial numbers 750-0001 through 750-0172 not incorporating Cessna 
Service Bulletin SB 750-71-10) 
Linear variation from 15.84% MAC at 35,700 lbs. to 15.00% MAC at 35,100 lbs.; 
15.00% MAC from 35,100 lbs. to 32,500 lbs.; linear variation from 15.00% MAC at 
32,500 lbs. to 21.00% MAC at 29,500 lbs.; 21.00% MAC at 29,500 lbs. to 28,000 lbs.; 
linear variation from 21.00% MAC at 28,000 lbs. to 26.16% MAC at 22,374 lbs.; linear 
variation from 26.16% MAC at 22,374 lbs. to 35.00% MAC at 21,310 lbs. 
(For airplane serial numbers 750-0173 through 750-0500 and aircraft incorporating 
Cessna Service Bulletin SB 750-71-10)

Rev. 19 Page 5 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
Linear variation from 16.40% MAC at 36,100 lbs. to 15.00% MAC at 35,100 lbs.; 
15.00% MAC from 35,100 lbs. to 32,500 lbs.; linear variation from 15.00% MAC at 
32,500 lbs. to 21.00% MAC at 29,500 lbs.; 21.00% MAC at 29,500 lbs. to 28,000 lbs.; 
linear variation from 21.00% MAC at 28,000 lbs. to 26.16% MAC at 22,374 lbs.; linear 
variation from 26.16% MAC at 22,374 lbs. to 35.00% MAC at 21,310 lbs. 
(For airplane serial numbers 750-0501 and on) 
17.11% MAC at 36,900 lbs; to 15.00% MAC 35,400 lbs; to 15.00% MAC at 33,500 lbs; 
to 21.00% MAC at 30,500 lbs; to 21.00% MAC at 28,000 lbs; to 26.16% MAC at 22,374 
lbs; to 35.00% MAC at 21,310 lbs. 
With straight line variation between points. 
 
 Empty Weight C.G. Range None 
 
 Datum Zero reference datum is 184.5 inches forward of the leveling screw located 2.50 inches  
  forward of the cabin door frame on Water Line 127.25. 
 
 MAC 118.60 in. (L.E. of MAC at F.S. 387.60) 
 
 Leveling Means Outboard floor p anel inside of door parallel to B.L. 13.00 
 
 Maximum Weight Ramp   ….…… 36,000 pounds (For airplane serial n umbers 750-0001 through 750-
0172 not incorporating Cessna Service Bulletins SB 750-71-10 and 
SB750-32-50) 
Ramp  ….…… 36,400 pounds (For airp lane serial numbers 750-0173 through 750-
0500 or aircraft incorporating Cessna Service Bulletins SB 750-71-
10 and SB750-32-50) 
Ramp  ….…… 36,900 pounds (For airp lane serial numbers 750-0501 and on) 
Takeoff  ….…. 35,700 pounds (For ai rplane serial numbers 750-0001 through 750-
0172 not incorporating Cessna Service Bulletins SB 750-71-10 and 
SB750-32-50) 
Takeoff  .…….. 36,100 pounds (For ai rplane serial numbers 750-0173 through 750-
0500 or aircraft incorporating Cessna Service Bulletins SB 750-71-
10 and SB750-32-50) 
Takeoff    ….…… 36,600 pounds (For airplane serial numbers 750-0501 and on) 
   Landing   ….…… 31,800 pounds (For airplane serial numbers 750-0001 through  
    750-0500) 
   Landing   ….… 32,000 pounds (For airplane serial numbers 750-0501 and on) 
   Zero Fuel   ….… 24,400 pounds (Fo r airplane serial numbers 750-0001 through  
    750-0500) 
   Zero Fuel   ….… 24,978 pounds (Fo r airplane serial numbers 750-0501 and on) 
 
 Minimum Crew For all flights:  Two persons (pilot and co-pilot ) 
 
 No. of Seats Two pilots , 12 passengers maximum 
 
 Maximum Baggage Tail compar tment:  700 pounds at F.S. 490.0 
  Floor loading density: 170 pounds per square foot 
 
 Fuel Capacity (Gal.) Two wing tanks: Usable  521 gals. each; A rm  410.07 inches 
  Center tank: Usable  888 gals.;  Arm  335.32 inches 
  See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity  S/N 750-0001 through 750-0500  
Total 12.1 qts each; (usable) 11.8 qts each; Arm 544.30 inches 
 
S/N 750-0501 and on  
Total 13.0 qts each; Arm 546.12 inches  
 
See NOTE 1 for data on unusable oil.

Rev. 19 Page 6 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
 Max. Operating Altitude 51,000 ft. 
 
 Control Surface Movements To ins ure proper operation of the airplane, the movement of the various control surfaces 
  must be carefully controlled by  proper rigging of the flight control systems.  The airplane 
  must, therefore, be rigged in accordance with the appropriate  FAA approved rigging 
  specification or Cessna drawing.  Specific rigging instructio ns may also be found in the 
  Model 750 Maintenance Manual (In structions for Continued Airworthiness), part  
  number 75MM00 (or late r approved revision). 
 (For airplane serial numbers  750-0001 through 750-0500) 
 
  Stabilizer  Range of Stabilizer  Setting (Leading Edge Position) 
   Cessna Drawing No. 6700750 
   Primary Trim Max. L.E. Up 1.2º ± 0.3  Max. L.E. Down 12 ± 0.6 
   Secondary Trim Max. L.E. Up 1.2º ± 0.3  Max. L.E. Down 12 ± 0.6 
  Elevator Rigging Spec No. 6760335 Up 18.5  + 0.5/-0 Down 14.0   1 . 0 
  Rudder Rigging Spec. No. 6760405 
   Lower  (perpendicular to H.L.)  Right 29.5° ± 0.5° Left 29.5  ± 0.5 
   Upper  (perpendicular to H.L.) Right 17   +1.5/-1.0º  Left 17  + 1.5º/-1.0 
  Rudder trim  Right 11  1 Left 11  1 
  Aileron Rigging Spec. No. 6760115 
    (from droop position) Up 15º  0.5 Down 15º  0.5 
  Droop position      1.5º    0.5º down from faired 
  Aileron Trim  Up   8º  1 Down   8º  1 
    
  Flaps Cessna Drawing No. 6700750 and Rigging Spec. No. 6762715 
 
 F l a p  
Position 
Nominal 
Outboard 
Nominal  
Center 
Nominal 
Inboard 
Allowable 
Tolerance 
 Up 0° 0° 0° ±0.2° 
 5° 5.9° 5.6° 5.2° ±0.5° 
 15° 17.4° 16.5° 15.0° ±1.0° 
 Full 39.0° 37.8° 36.3° ±2.0° 
 
  Speed brakes Rigging Spec.  No. 6760275 
   Panels 3, 4, 5, 6, 7, & 8 Up:  40°  -  43° 
      Maximum 1.0° betw een corresponding panels 
 
 Roll Spoilers Rigging Spec. No. 6760205  
   Panels 1, 2, 9, & 10  Up:  40°  -  43° 
(For airplane serial numbers 750-0501 and on) 
 
  Stabilizer  Range of Stabilizer  Setting (Leading Edge Position) 
   Cessna Drawing No. 6700751 
   Primary Trim Max. L.E. Up 1.2º ± 0.3  Max. L.E. Down 12 ± 0.6 
   Secondary Trim Max. L.E. Up 1.2º ± 0.3  Max. L.E. Down 12 ± 0.6 
  Elevator Rigging Spec. No. 6760647 Up 18.5  + 0.5/-0 Down 14.0   1 . 0 
  Rudder Rigging Spec. No. 6760657 
   Lower  (perpendicular to H.L.)  Right 29.5° ± 0.5° Left 29.5  ± 0.5 
   Upper  (perpendicular to H.L.) Right 17   +1.5/-1.0º  Left 17  + 1.5º/-1.0 
  Rudder trim  Right 11  1 Left 11  1 
  Aileron Rigging Spec. No. 6760617 
    (from droop position) Up 15º  1° Down 15º  1° 
  Droop pos ition                                                             1.5º    0.5º down from faired 
  Aileron Trim  Up  1 5° Down 15° 
    With one hydraulic system Up   8º  1 Down   8º  1

Rev. 19 Page 7 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
  Flaps Cessna Drawing No. 6700751 and Rigging Spec. No. 6762757 
 
 F l a p  
Position 
Nominal 
Outboard 
Nominal  
Center 
Nominal 
Inboard 
Allowable 
Tolerance 
 Up 0° 0° 0° ±0.2° 
 1 (5°) 5.9° 5.6° 5.2° ±0.5° 
 2 (15°) 17.4° 16.5° 15.0° ±1.0° 
 Full 39.0° 37.8° 36.3° ±2.0° 
 
  Speed brakes Rigging Spec.  No. 6760637 
   Panels 3, 4, 5, 6, 7 & 8 Up:  40°  -  43° 
      Maximum 1.0° delta b etween corresponding panels 
 
 Roll Spoilers Rigging Spec. No. 6760617  
   Panels 1, 2, 9 & 10  Up:  40°  -  43° 
 
 Serial Nos. Eligible 750-0001 and on 
 
 Certification Basis (S /N 750-0001 through 750-0500) 
 
(1) 14 CFR Part 25 effective Fe bruary 1, 1965, as amended by Amendments 25-1 through 25-74: 
 (a) Additions:  14 CFR § 25.729( e) as amended by Amendment 25-75; and § 25.1316, as amended by  
   Amendment 25-80 
 
(2) 14 CFR Part 36 effective D ecember 1, 1969 as amended by Amendment 36-1 through 36-21. 
 
(3) Noise Control Act of 1972. 
 
(4) 14 CFR Part 34 of the Feder al Aviation Regulations effective September 10, 1990. 
 
(5) Special Conditions as follows: 
(a) No. 25-ANM-80, additional re quirements for High Altitude Operation (See NOTE 7) 
(b) No. 25-ANM-99, additional requi rements for protection of Electrical and Electronic Systems from High 
Intensity Radiated Fields (HIRF) 
(c) No. 25-ANM-113, additional re quirements for operation with Fly-by-Wire Rudder. 
(d) No. 25-686-SC, Non-rechargeab le Lithium Batteries, effective to design changes applied for after  
May 31, 2017. 
 
(6) Equivalent levels of safety as follows: 
 (a) 14 CFR § 25.335(d) and 25.341 , Design Discrete Gust Criteria; 
 (b) 14 CFR § 25.811(e)(4), Red A rrow Marking for the Main Passenger Door Handle; 
 (c) 14 CFR § 25.807(e), Ditching Emergency Exits for Passengers;  
 (d) 14 CFR § 25.841(b)(6), Cab in Pressurization - High Altitude Takeoff and Landing Operations; 
 (e) 14 CFR § 25.1549(a)(c), Digital Turbine Speed; 
 (f) 14 CFR § 25.1305, Digital APU Indicators (Oil Pressure, Oil Temperature, Gas Temperature, Tachometer); 
 (g) 14 CFR § 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, and 25.1587, Accelerate-Stop Distance;  
 (h) 14 CFR § 25.811(d)(1) and 25.812(b)(1)(i), Emergency Exit Locator Signs; and 
 (i) 14 CFR § 25.201, 25.203 and 25.207, Stall Warning System for flight conditions above 34,500 feet. 
 (j) 14 CFR § 25.813(e), Emergency Exit Access 
 (k) T00002WI-T-AG-12, 14 CFR 25.815, Width of aisle.

Rev. 19 Page 8 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
 Certification Basis (S/N 750-0001 through 750-0500) (cont’d) 
 
(7) Exemptions:   
 (a) No. 6179, exemption from bird  impact requirements of § 25.571(e)(1); 
 (b) No. 6431, exemption from Engi ne-out lateral trim requirements of § 25.161(d); and 
 (c) No. 6432, exemption from the emergency landing dynamic conditions of § 25.562 for multiple-occupancy, 
side-facing divans.  Expires November 30, 1996. 
   o r  
 No. 7922, partial grant of exemp tion from the general occupant protection requirements of 25.785(b) for 
multiple-occupancy, side-facing divans, restricted to airplanes manufactured prior to January 1, 2004. 
or 
 No. 7922A, grant of exemption fro m the general occupant protection requirements of 25.785(b) for multiple-
occupancy, side-facing divans, (no restriction). 
 (d) No. 8767, exemption from door installation prohibition of interior doors between passenger compartments of 
§ 25.813(e). 
 
(8) 14 CFR § 25.801 ditchi ng not complied with. 
 
(9) Compliance with ice protection has been demonstrated in acc ordance with 14 CFR § 25.1419. 
 
 Date of Application for Type C ertificate was October 15, 1991. 
 Type Certificate No. T00007WI was issued May 31, 1996. 
 
Certification Basis (S/N 750-0501 and on) 
 
(1) 14 CFR Part 25 effective Fe bruary 1, 1965, as amended by Amendments 25-1 through 25-74: 
 (a) Additions:   
 
For all components 
14 CFR § 25.677 as amended by Amendment 25-115 
14 CFR § 25.735 as amended by Amendment 25-92 
14 CFR § 25.729(e) as amended by Amendment 25-75 
14 CFR § 25.1316, as amended by Amendment 25-80 
14 CFR § 25.1317(a)(b)(c)(d) as amended by Amendment 25-122 
 
Winglet related changes 
14 CFR 25.305, 25.335, 25.341, 25.345, 25.349, 25.427, 25.445, 25.571, 25.629, 25.899, 25.1001, 25.1419, 
25.1431 through Amendment 25-129 
 
Part 25, Subpart B, through Amendment 25-115 
Part 25, Subpart G, through Amendment 25-115 
 
14 CFR 25.981 through Amendment 25-125 except for lightning protection of fuel tank structural fasteners.  
14 CFR 25.981 through Amendment 25-11 for lightning protection of fuel tank structural fasteners 
 
Flight Envelope Expansion (MMO Increase) related changes 
14 CFR 25.335, 25.629 through Amendment 25-129 
 
Part 25, Subpart B, through Amendment 25-115 
Part 25, Subpart G, through Amendment 25-115 
 
Fuselage Stretch (15”) related changes 
14 CFR 25.335, 25.427, 25.445, 25.519, 25.562, 25.629,  25.803, 25.856, 25.1323, 25.1325, and 25.1419 
through Amendment 25-129 apply to all areas of the airplane. 
 
14 CFR 25.899 applies to all aircraft installations requiring electrical bonding and p-static protection 
 
14 CFR 25.773 through Amendment 25-108 applies to all areas of the airplane.

Rev. 19 Page 9 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
Certification Basis (S/N 750-0501 and on) (cont’d) 
 
Part 25, Subpart B, through Amendment 25-115 
Part 25, Subpart G, through Amendment 25-115 
 
Autothrottle only changes 
14 CFR 25.1329 as amended at Amendment 25-119  
 
Optional CVR only changes 
14 CFR 25.1457 as amended at Amendment 25-124*** 
 
***Standard CVR will remain at original amendment level 
 
Pitot System related changes 
14 CFR 25.1323 as amended at Amendment 25-109 
14 CFR 25.1325 as amended at Amendment 25-108 
 
(2) 14 CFR Part 36 effective D ecember 1, 1969 as amended by Amendment 36-1 through 36-28. 
 
(3) Noise Control Act of 1972. 
 
(4) 14 CFR Part 34 of the Feder al Aviation Regulations effective September 10, 1990, as amended by amendments 
34-1 through 34-5. 
 
(5) Special Conditions as follows: 
(a) No. 25-ANM-80, additional re quirements for High Altitude Operation (See NOTE 7) 
(b) No. 25-ANM-113, additional re quirements for operation with Fly-by-Wire Rudder. 
(c)  No. 25-509-SC, Aircraft Elect ronic System Security Isolation or Protection from Internal Access 
(d) No. 25-510-SC, Aircraft Elect ronic System Security Isolation or Protection from Unauthorized External 
Access 
(e) No. 25-686-SC, Non-rechargeab le Lithium Batteries, effective to design changes applied for after  
May 31, 2017. 
 
(6) Equivalent levels of safety as follows: 
(a) 14 CFR § 25.811(e)(4), Red Arro w Marking for the Main Passenger Door Handle;  
(b) 14 CFR § 25.841(b)(6), Cabin  Pressurization - High Altitude Takeoff and Landing Operations; 
(c) 14 CFR § 25.811(d)(1) and 25. 812(b)(1)(i), Emergency Exit Locator Signs; 
(d) 14 CFR § 25.201, 25.203 and 25.207, Stall Warning System for flight conditions above 34,500 feet. 
(e) 14 CFR § 25.813(e), Emergency Exit Access 
(f) T00002WI-T-AG-12, 14 CFR 25.815, Width of aisle. 
(g) AT5435WI-T-P-1, § 25.1305(a)(4 )(5)(6); 25.1549(a)(b)(c), Digital Display of APU Instruments 
(h) AT5435WI-T-P-5, § 25.901(c) , 25.903(d)(2), 25.1305, 25.1309(a)(b)(c), 25.1321(c)(2), 25.1322 and 25.1549, 
Digital-Only Display of Turbine Engine High Pressure Rotor Speed (N2), Oil Pressure, Oil Temperature, and 
Fuel Flow)  
(i) AT5435WI-T-SE-2, § 25.1301(a )(d), 25.1303(a)(3), 25.1309(a)(b)(d)(e), 25.1316, 25.1321, 25.1327, 25.1331, 
25.1333, 25.1353(a)(c), 25.1459(e), 25.1547, Electric Standby Direction Indication (Compass) 
(j) AT5435WI-T-SE-4, § 25.1397(c) E xterior Lighting Chromaticity  
 
(7) Exemptions:   
 (a) No. 6431, exemption from Engi ne-out lateral trim requirements of 25.161(d); and 
 (b) No. 7922A, grant of exempti on from the general occupant protection requirements of 25.785(b) for multiple-
occupancy, side-facing divans, (no restriction). 
 (c) No. 8767, exemption from door installation prohibition of interior doors between passenger compartments of 
25.813(e). 
 
(8) 14 CFR § 25.801 ditchi ng not complied with.

Rev. 19 Page 10 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
Certification Basis (S/N 750-0501 and on) (cont’d) 
 
(9) Additional Desi gn Requirements: 
 (a) Flight in Icing Conditions: 
 The design  complies with 14 CFR 25.21(g), 25.103, 25.105, 25.107, 25.111, 25.119, 25.121, 25.123, 25.125, 
25.143, 25.207, 25.237, and 25.253 at amendment 25-129, except that compliance shown using ice 
accretions based on the atmospheric icing conditions defined in appendix C at amendment 25-0.   
 (b) In-flight Engine Restart: 
  A minimum restart capability aft er an all-engines-out scenario must be established under the following 
conditions using procedures provided in the Airplane Flight Manual (AFM): 
 
1. During the take-off and the initial climb-out portion of the flight, the airplane should have the capability 
for the flight crew to restore engine power immediately following an all-engine-out scenario and when 
the fuel source to the engine is restored. 
 
2. During the high altitude porti on of the flight at cruise speed and maximum altitude, the airplane should 
have the capability for the flight crew to restart engines from a stabilized windmill speed prior to 
descending below an altitude of 15,000 feet, by showing either or both: 
 
a)   All but one engine should be restarted and accelerated to produce maximum continuous 
thrust/power, or 
b)  The engine(s) should be res tarted, and the necessary thrust/power achieved, to enable the airplane 
to maintain level flight. 
 
3. During flight at speeds great er than the minimum flaps-up “holding speed” and at altitudes below 
20,000 feet, the airplane should have the capability for the flight crew to restart engines from a 
stabilized windmill speed prior to descending 5000 feet from the initiation of the restart procedure and 
prior to exceeding an airspeed of 300 knots, by showing either or both: 
 
a) All but one engine should be restarted and accelerated to pr oduce maximum continuous 
thrust/power, or  
b) The engine(s) should be resta rted, and the necessary thrust/power achieved, to enable the airplane 
to maintain level flight. 
 
 (c) Lightning Protection of Fue l Tank Structural Fasteners 
 Sealant on all fasteners (exis ting and new) within the surge tank area is required.  This design feature was 
established as a condition for setting the certification basis for lighting protection of fuel tank structural 
fasteners at § 25.981 through Amendment 25-11. 
 
 (d) Airplane Flight Manual (AFM) 
 The AFM text associated with t he design maneuvering speed (VA) must meet the requirements of 14 CFR 
25.1583, Amendment 25-130. 
 
(10) 14 CFR Part 26 through Amendment 26-6 is not applicable. 
 
 Date of Application, for S/N 750-0501 and on, was September 10, 2010.   
 Approval was issued June 25, 2014. 
 
 Production Basis Production Cer tificate No. 4 amended to add Model 750 effective October 4, 1996.  See NOTE 6 
     for airplane serial effectivity of Production Certificate No. 4 on new airplane serials. 
 
 Equipment The basic required equi pment as prescribed in the applicable airworthiness regulations (see  
    Certification Basis) must be  installed in the airplane for certification.

Rev. 19 Page 11 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
 
NOTE 1. FAA Approved Weight and Balance Manual:  part number 75WB-01 (or later approved revision) is 
applicable to the Model 750 serial numbers 750-0001 through 750-0172 not incorporating Cessna Service 
Bulletin SB 750-71-10.   
 
FAA Approved Weight and Balance Manual:  part number 75WBA-00 (or later approved revision) is 
applicable to the Model 750 serial numbers 750-0173 through 750-0500 and aircraft incorporating Cessna 
Service Bulletin SB 750-71-10.   
 
Weight and balance for 750-0501 and on will be included in the AFM. 
 
The airplane must be loaded according to the appropriate FAA Approved Weight and Balance Manual.  The 
list of equipment included in certificated empty weight must be provided for each airplane at the time of 
original certification. 
 
  The certified empty weight a nd corresponding center of gravity location must include: 
 
S/N 750-0001 through 750-0500  
   Weight – lbs. 
Drainable Unusable Fuel  79.40 
Undrainable Unusable Fuel  22.19 
Full Oil  46.80 
S/N 750-0501 and on  
   Weight – lbs. 
Drainable Unusable Fuel  78.93 
Undrainable Unusable Fuel  22.19 
Full Oil  52.88 
  
NOTE 2. FAA Approved AFM:  part number 75FM-02 (or later approved revision) is applicable to the Model 750 
serial numbers 750-0001 through 750-0172 not incorporating Cessna Service Bulletin SB 750-71-10.   
 
FAA Approved AFM:  part number 75FMA-00 (or later approved revision) is applicable to the Model 750 
serial numbers 750-0173 through 750-0500 and aircraft incorporating Cessna Service Bulletin  
SB 750-71-10.   
 
FAA Approved AFM:  part number 75FMC-00 (or later approved revision) is applicable to the Model 750 
serial numbers 750-0501 and on.   
 
The airplane must be operated according to the appropriate FAA Approved AFM.    
 
Required placards are included in the Maintenance Manual (Instructions for Continued Airworthiness), part 
number 75MM00 (or later approved revision), Chapter 11, Placards and Markings. 
 
NOTE 3. FAA approved Airworthine ss Limitations for mandatory compliance retirement life or inspection are 
included in the Maintenance Manual (Instructions for Continued Airworthiness), part numbers 75MM00 (for 
S/N 750-0001 thru 0500) and 75MMC-00 (for S/N 750-0501 and on) (or later approved revision), Chapter 4, 
Airworthiness Limitations.

Rev. 19 Page 12 of 12 T00007WI 
 
I. Model 750  (cont’d) 
 
NOTE 4. All replacement seats (crew and passenger), although they may comply with TSO C127, must also be
 demonstrated to comply with re quirements of 14 CFR §§ 25.333, 25.561, 25.562, and 25.785. 
 The foam cushion buildup of all seats (crew and passenger) may not be altered unless deviations in the
 foam construction are demonstrat ed by tests to comply with the listed 14 CFR 25 paragraphs. 
 The LH side facing seat lap be lt shall have a buckle which opens from the left to right to prevent the
 buckle’s own inertia from causing it to open.  Any other confi guration must be verified by dynamic 
 requirements. 
 
NOTE 5. Model 750 serial numbers  0001 thru 0500, two (2) Honeywell AZ-840 or AZ-940 Micro Air Data Computers 
(MADC) are required equipment.  Approved part numbers are listed in the following table: 
 
MADC Part Number Model 750-xxxx Se rial Range Service Bulletin 
7014700-904 -0003 through -0041 N/A 
7014700-604 -0001, 0002,  -0042 through -0105, SB750-34-05 Rev 0,1 
7014700-607 -0106 through -0240 SB750-34-05 Rev 2 
7030700-70706 -0241 through -0500 N/A 
 
Aircraft with part number 7014700-607 or 7030700-70706 MADCs meet airworthiness requirements for 
operation in Reduced Vertical Separation Minimum (RVSM) airspace.  Each operator must obtain RVSM 
operating approval directly from the FAA. 
  
Model 750 serial numbers 0526 and on and aircraft incorporating Textron Aviation Service Bulletin SB 750-
34-60 meet airworthiness requirements for operation in Reduced Vertical Separation Minimum (RVSM) 
airspace.  Each operator must obtain RVSM operating approval directly from the FAA. 
 
NOTE 6. Production Certificate No. 4 applies to Model 750 serial numbers 750-0001, 750-0002, 750-0004, 
 750-0006 and on (*except serial number 750-0501). 
 
 * Serial number 750-0501 was manuf actured under Type Certificate T00007WI and authorized to issue 
airworthiness certificate after the FAA inspection and flight test with the provision of 14 CFR 21.183(b). 
 
NOTE 7. Model 750 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 includ es modifications which could result in a 
 pressure vessel opening, either  through crack-growth or antenna loss, greater than 3.98 sq. in. 
 
NOTE 8. The airplane (S/N 750-0001 through 750-0500) is approved for Category II operation using the flight-
director with autopilot-coupled or not coupled.  This does not constitute operational approval.   Minimum 
approved integrated computer (IC-800) software is Phase IV (P/N 7017300-31201). 
 
NOTE 9. Certification Maintenan ce Requirements (CMR) are found in Maintenance Manual, Chapter 4.  Engineering 
approval of the CMR’s is documented in the Cessna System Safety Assessment reports. 
 
NOTE 10. The following serials ar e manufactured under the name Cessna Aircraft Company: 750-0001 thru 750-0502, 
750-0504 thru 750-0517, and 750-0519. 
 
NOTE 11. Company name change eff ective 7/29/15. The following serials are manufactured under the name Textron 
Aviation Inc.: 750-0503, 750-0518, 750-0520 and On.  
 
 
 
--- END ---
```

## ADs (16, 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 2013-04-03](https://openairdocs.org/ad/2013-04-03): Pitot/Static Anti-Ice System · Cessna 750. Effective Apr 11, 2013
- [AD 2012-18-16](https://openairdocs.org/ad/2012-18-16): Electrical power · Cessna 750. Effective Oct 24, 2012
- [AD 2011-03-16](https://openairdocs.org/ad/2011-03-16): Electrical power · Cessna 750. Effective Mar 22, 2011
- [AD 2010-20-10](https://openairdocs.org/ad/2010-20-10): Flight Controls · Cessna 750. Effective Nov 1, 2010
- [AD 2007-11-17](https://openairdocs.org/ad/2007-11-17): Wires for the positive and negative terminal studs of the engine and/or auxiliary power unit (APU) fire extinguishing bottles. · Cessna 500, 501, 550 and 5 more. Effective Jul 6, 2007
- [AD 2006-24-01](https://openairdocs.org/ad/2006-24-01): Auxiliary power unit (APU) fuel tube assembly · Cessna 750. Effective Dec 6, 2006
- [AD 98-16-17 R1](https://openairdocs.org/ad/98-16-17-R1): Secondary horizontal stabilizer · Textron 750. Effective Oct 23, 2003
- [AD 2002-23-05](https://openairdocs.org/ad/2002-23-05): Circuit Breakers for the Auxiliary Hydraulic Pump System and the King KHF 950 High Frequency Communication System(s) · Cessna 750. Effective Dec 26, 2002
- [AD 2001-07-04](https://openairdocs.org/ad/2001-07-04): Roll Control System · Cessna 750. Effective May 15, 2001
- [AD 98-05-02](https://openairdocs.org/ad/98-05-02): Aileron Feel Cartridge Assembly Shaft · Cessna 750. Effective Mar 16, 1998
- [AD 2006-23-05](https://openairdocs.org/ad/2006-23-05) (historical): Inboard- hinge brackets · Cessna 750. Effective Nov 22, 2006
- [AD 2006-04-10](https://openairdocs.org/ad/2006-04-10) (historical): Identification sleeves · Cessna Aircraft Company, The 500, 550, 560 and 3 more. Effective Mar 24, 2006
- [AD 2005-09-01](https://openairdocs.org/ad/2005-09-01) (historical): Auxiliary power unit (APU) fuel tube assembly · Cessna Aircraft Company, The 750. Effective May 10, 2005
- [AD 98-16-17](https://openairdocs.org/ad/98-16-17) (historical): Secondary Horizontal Stabilizer Trim Actuator · Cessna Aircraft Company, The 750. Effective Aug 24, 1998

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna 750](https://openairdocs.org/model/cessna-750): 273 aircraft (registry codes 2076810, 2076809)
- [Textron 750](https://openairdocs.org/model/textron-750): 15 aircraft (registry code 2076820)

## STCs approved under this data sheet (73, 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 ST04578CH](https://openairdocs.org/stc/ST04578CH): Installation of SmartSky system. Apcela ATG
- [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 ST04269AT](https://openairdocs.org/stc/ST04269AT): Installation of Send Solutions, LLC Airtext  Messaging System which connects the passengers  phones and portable electronic devices via Bluetooth to provide the passengers with in-flight messaging service via the Iridium Satellite Communication Network. Send Solutions LLC
- [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC
- [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC ST11873SE](https://openairdocs.org/stc/ST11873SE): Installation of Starlink Aviation System. AeroMech Incorporated
- [STC ST12016IB](https://openairdocs.org/stc/ST12016IB): Installation of Gogo AVANCE L5/LX5. Sky Service F.B.O 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 ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine
- [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 ST00011WI](https://openairdocs.org/stc/ST00011WI): Installation of Concorde RG380E/40 and 40B battery.. Aero-Mach Wilco LLC
- [STC ST04519CH](https://openairdocs.org/stc/ST04519CH): Installation of a Honeywell FANS-1/A+ Datalink Communications System in accordance with West Star Aviation Master Data List, Doc. No. A21311L-658, Revision A, dated November 3, 2021, or later FAA-approved revision.. West Star Aviation
- [STC SA04518CH](https://openairdocs.org/stc/SA04518CH): Installation of a Honeywell Flight Management System Software Update to version NZ 6.2.1 in accordance with West Star Aviation Master Data List, Doc. No. A21312L-652, Revision I/R, dated October 4, 2021, or later FAA-approved revision.. West Star Aviation
- [STC ST02715SE](https://openairdocs.org/stc/ST02715SE): Installation of the Honeywell RDR-7000 Volumetric Buffer Weather Radar System. Honeywell International 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 ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC ST03595NY](https://openairdocs.org/stc/ST03595NY): Installation of Honeywell Laseref IV Upgrade. Dassault Aircraft Services (DAS)
- [STC ST01950WI](https://openairdocs.org/stc/ST01950WI): Installation of Gogo Business Aviation AVANCE L5 Broadband. Duncan Aviation Inc
- [STC ST01942WI](https://openairdocs.org/stc/ST01942WI): Installation of Garmin G5000 System Release v4.5. Wichita Citation Center
- [STC SA01452CH](https://openairdocs.org/stc/SA01452CH): Installation of an air ambulance conversion kit.. Med-Pac Inc.
- [STC ST00954DE](https://openairdocs.org/stc/ST00954DE): Demonstration of Aircraft Compatibility to Wireless Fidelity (WiFi) Data Transmissions (Ground & Flight). West Star Aviation
- [STC ST01859WI](https://openairdocs.org/stc/ST01859WI): Installation of Gogo Business Aviation's Gogo Biz 4G Air-to-Ground System. Textron Aviation Inc
Wichita Citation Service Center
- [STC ST00934DE](https://openairdocs.org/stc/ST00934DE): Installation of Becker Avionics BXT6553 transponder. Peregrine
- [STC ST02119LA](https://openairdocs.org/stc/ST02119LA): Installation of a Patient Loading and Utility System (PLUS). LifePort LLC
- [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 ST00347BO](https://openairdocs.org/stc/ST00347BO): Modification to upgrade a BendixKing CAS 67A TCAS II system to CAS 67B TCAS II Change 7.1. Pro Star Aviation, LLC
- [STC ST00361BO](https://openairdocs.org/stc/ST00361BO): Installation of a Honeywell Primus II (XS-852) ADS-B Out System. Pro Star Aviation, LLC
- [STC ST00135BO](https://openairdocs.org/stc/ST00135BO): Modification of Honeywell TCAS II system installation with R/T 910 and software Version 6.4a to R/T 910 with Change 7.0 software; or TCAS 2000 system with R/T 950, 951 and software Version 6.4a to R/T 950, 951 with Change 7.0 software.. Pro Star Aviation, LLC
- [STC ST04146NY](https://openairdocs.org/stc/ST04146NY): Upgrade for ADS-B Out capability on aircraft equipped with Primus II Radio Suites. 328 Support Services GmbH
- [STC ST01720WI](https://openairdocs.org/stc/ST01720WI): Installation of a Safe Flight Instrument Corporation Auto Throttle System.. Textron Aviation Inc.
- [STC ST03271CH](https://openairdocs.org/stc/ST03271CH): Upgrade existing Honeywell Mark V Enhanced Ground Proximity Warning System software level and activate the Runway Awareness Advisory System (including enhanced features known as SmartRunway  SmartLanding). Textron Aviation Inc.
- [STC ST11071SC](https://openairdocs.org/stc/ST11071SC): Demonstration of aircraft critical equipment and antenna systems tolerance of radio frequency interference (RFI) from intentional or spurious transmissions from certain Portable Electronic Devices (PEDs). Liberty Partners Inc
- [STC ST04194CH](https://openairdocs.org/stc/ST04194CH): Install Honeywell Liquid Crystal Display (LCD) Flight Displays. Pentastar Aviation LLC
- [STC ST03957AT](https://openairdocs.org/stc/ST03957AT): Activation of Aircell Axxess Cabin Telecommunications Router (CTR) Wireless Local Area Network (WLAN) in accordance with Constant Aviation LLC, Master Drawing List DB1107001, Revision IR, dated December 9, 2011, or later FAA approved revision.. Nextant Aerospace
- [STC ST03776NY](https://openairdocs.org/stc/ST03776NY): Modification to upgrade existing Rockwell Collins TCAS (Model: TTR-920, TTR-921, and TTR-4000) at VERSION 7.0 to Rockwell Collins TCAS (Model: TTR-921, TTR-4000, and TTR-4100) at VERSION 7.1 (ACAS II). Scandinavian Avionics Design ApS
- [STC ST01545WI](https://openairdocs.org/stc/ST01545WI): Installation of winglets, wing structural reinforcement, and related system changes. Winglet Technology LLC
- [STC ST00881WI-D](https://openairdocs.org/stc/ST00881WI-D): Modification of a TCAS II system installation to Change 7.0 or Change 7.1. Rockwell Collins Inc
- [STC ST00796DE](https://openairdocs.org/stc/ST00796DE): Installation of Teledyne Battery Products P/N 7638-44T Lead-Acid Battery. Teledyne Battery Products
- [STC ST01399WI](https://openairdocs.org/stc/ST01399WI): Installation of Honeywell DL-950 Data Loader.. Textron Aviation Inc
- [STC SA04006CH](https://openairdocs.org/stc/SA04006CH): Installation of Fuel Vent Scoop. Textron Aviation Inc
- [STC ST02127LA](https://openairdocs.org/stc/ST02127LA): Installation of a Crane Aerospace & Electronics Tire Sensor Assembly. ELDEC Corporation
- [STC ST00673WI-D](https://openairdocs.org/stc/ST00673WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System installation.. Rockwell Collins Inc

All 73: https://openairdocs.org/tcds/T00007WI/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.