# TCDS T00012WI: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 18
- Revised: September 18, 2025
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 697, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/19/ac/19ac1c2660499133baef866d70f6e045c5d28129845e1d6e7d910b0adc8e9930
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID164335445520250918155951.0001
- Page: https://openairdocs.org/tcds/T00012WI

## Models (2)

As the data sheet lists them.

- 680
- 680A

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 
Rev. No. 18 10 16 9 15 15 18 16 17 14 13 12 18 16 15 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 T00012WI  
 Revision 18  
 Textron Aviation   
 680   
 680A  
 Se ptember 18, 2025  
 
 
TYPE CERTIFICATE DATA SHEET NO. T00012WI 
 
This data sheet, which is part of Type Certificate No. T00012WI, prescribes conditions and limitations under which the product 
for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder Textron Aviation Inc. 
One Cessna Boulevard 
Wichita, Kansas 67215 
 
Type Certificate Holder Record Cessna Aircraft Company transferred to 
Textron Aviation Inc. on July 29, 2015 
 
I. Model 680 Sovereign (Transport Category ) S/N 680-0001 through 680-0500 Approved June 2, 2004; 
 S/N 680-0501 and On Approved December 20, 2013 
 
Engines S/N 680-0001 thru 680-0500 
Two Pratt & Whitney Canada Corp. PW306C turbofans 
 
S/N 680-0501 and On 
Two Pratt & Whitney Canada Corp. PW306D turbofans 
 
Fuel Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5, JP-8, TS-1, RT, and No. 3 Jet. 
 
Engine Limits Static thrust standard day, sea level 
S/N 680-0001 thru 680-0500 
Takeoff 5,770 lb. 
Max. Continuous 5,770 lb. 
 
S/N 680-0501 and On 
Takeoff 5,907 lb. 
Max. Continuous 5,907 lb. 
 
Max. permissible engine rotor operating speeds (Takeoff and Maximum Continuous) 
N1 (fan)  105.0% (100% = 10,608 r.p.m.) 
N2 (Gas Gen.)  105.0% (100% = 26,930 r.p.m.) 
Max. permissible interturbine gas temperatures: 
Takeoff  920 Degrees C 
Max. Continuous  920 Degrees C 
Transient (20 sec.) and starting  950 Degrees C

T00012WI Page 2 of 15 Rev. 18 
I. Model 680 Sovereign (cont’d) 
 
Airspeed limitations (S/N 680-0001 thru 680-0500): 
Vmo (maximum operating) 
 Below 8,000 ft. 270 KIAS (270 KCAS) 
 8,000 ft. to 29,833 ft. 305 KIAS (305 KCAS) 
Mmo above 29,833 ft. 0.80 M I (0.80 MACH calibrated) 
Va (maneuvering sea level) 
 30,300 lb. 169 KIAS (169 KCAS) 
 See AFM for variations with weight and altitude. 
VRA (Rough air speed) 
 Below 38,813 ft. 225 KIAS (225 KCAS) 
 Above 38,813 ft. 0.73 M I (0.73 MACH calibrated) 
Flap extension speeds 
 V FE (0° to 7° extension) 250 KIAS (250 KCAS) 
 V FE (7° to 15° extension) 200 KIAS (200 KCAS) 
 V FE (15° to 35° extension) 175 KIAS (174 KCAS) 
 V MCA (Minimum control speed) Air 7 deg flaps 92 KIAS (93 KCAS) 
VMCA (Minimum control speed) Air 15 deg flaps 90 KIAS (91 KCAS)  
VMCL (Minimum control speed) Landing 15 deg flaps 88 KIAS (89 KCAS)  
VMCL (Minimum control speed) Landing 35 deg flaps 84 KIAS (84 KCAS) 
VMCG (Minimum control speed) Ground 7 deg flaps 96 KIAS (97 KCAS) 
VMCG (Minimum control speed) Ground 15 deg flaps 97 KIAS (98 KCAS) 
 
VLO (landing gear operating) 210 KIAS (207 KCAS) 
VLE (landing gear extended) 210 KIAS (207 KCAS) 
VSB (speed brakes extension) A ny speed with or without flaps 
 
Maximum autopilot operating speed 
Below 8,000 ft. 270 KIAS (270 KCAS) 
8,000 to 29,833 ft. 305 KIAS (305 KCAS) 
Above 29,833 ft. 0.80 M I (0.80 MACH calibrated) 
 
Maximum tire ground speed 182 knots  
 
Airspeed limitations (S/N 680-0501 and On): 
Vmo (maximum operating) 
Below 8,000 ft. 270 KIAS (269 KCAS) 
8,000 ft. to 29,833 ft. 305 KIAS (304 KCAS) 
Mmo above 29,833 ft. 0.80 M I (0.80 MACH calibrated) 
Va (maneuvering sea level) 
30,775 lb. 193 KIAS (193 KCAS) 
(See AFM for variations with weight and altitude) 
VRA (Rough air speed) 
Below 38,813 ft. 225 KIAS (225 KCAS) 
Above 38,813 ft. 0.73 M I (0.73 MACH calibrated) 
Flap extension speeds 
VFE (Up (0°) to 1 (7°) extension) 250 KIAS (249 KCAS) 
VFE (1 (7°) to 2 (15°) extension) 200 KIAS (200 KCAS) 
VFE (2 (15°) to Full (35°) extension) 175 KIAS (175 KCAS) 
VMCA (Minimum control speed) Air 7 deg flaps 88 KIAS (88 KCAS) 
VMCA (Minimum control speed) Air 15 deg flaps 85 KIAS (85 KCAS)  
VMCL (Minimum control speed) Landing 15 deg flaps 84 KIAS (84 KCAS)  
VMCL (Minimum control speed) Landing 35 deg flaps 80 KIAS (80 KCAS) 
VMCG (Minimum control speed) Ground 7 deg flaps 88 KIAS (88 KCAS) 
VMCG (Minimum control speed) Ground 15 deg flaps 88 KIAS (88 KCAS)

Rev. 18 Page 3 of 15 T00012WI 
I. Model 680 Sovereign  (cont’d) 
 
Airspeed limitations (S/N 680-0501 and On) (cont’d): 
VLO (landing gear operating) 210 KIAS (210 KCAS) 
VLE (landing gear extended) 210 KIAS (210 KCAS) 
VSB (speed brakes extension) A ny speed with or without flaps 
 
Maximum autopilot operating speed 
Below 8,000 ft. 270 KIAS (269 KCAS) 
8,000 to 29,833 ft. 305 KIAS (304 KCAS) 
Above 29,833 ft. 0.80 M I (0.80 MACH calibrated) 
 
Maximum tire ground speed 182 knots 
 
C.G. Range (Landing Gear Extended) Design C.G. Limits (S/N 680-0001 thru 680-0500): 
 
Forward: 18.00% MAC at 19,000 lb. to 23,700 lb. 
Linear variation from 18.00% MAC at 23,700 lb. to 21.43% MAC  
at 30,550 lb. 
Takeoff Forward 21.30% at 30,300 lb. 
 
Aft: 31.00% MAC at 17,500 lb. to 23,000 lb. 
30.00% MAC at 26,000 lb. to 27,100 lb. 
31.00% MAC at 28,500 lb. to 30,550 lb. 
With straight line variation between points. 
 
Landing Gear retracting moment -8,095 in-lb. 
 
C.G. Range (Landing Gear Extended) Design C.G. Limits (S/N 680-0501 and On): 
 
Forward:  18.00% MAC at 19,702 lb. to 23,700 lb. 
Linear variation from 18.00% MAC at 23,700 lb. to 21.67% MAC  
at 31,025 lb. 
Takeoff Forward 21.54% at 30,775 lb. 
 
Aft: 31.00% MAC at 18,345 lb. to 23,475 lb. 
30.00% MAC at 26,475 lb. to 27,575 lb. 
31.00% MAC at 28,975 lb. to 31,025 lb. 
With straight line variation between points. 
 
Landing Gear retracting moment -8,370 in-lb. 
 
Empty Wt. C.G. None 
Range 
 
MAC 107.06 in. (L.E. of MAC at +382.68 in. aft of datum) 
 
Maximum Weight S/N 680-0001 thru 680-0500: 
Takeoff 30,300 lb. 
Landing 27,100 lb. 
Ramp 30,550 lb.  
Zero Fuel 20,800 lb. 
 
S/N 680-0501 and On: 
Takeoff 30,775 lb. 
Landing 27,575 lb. 
Ramp 31,025 lb. 
Zero Fuel 21,000 lb.

T00012WI Page 4 of 15 Rev. 18 
I. Model 680 Sovereign  (cont’d) 
 
Minimum Crew  One pilot and one copilot for all flights 
 
Number of Seats Maximum 14 (two crew plus 12 passenger seats) 
 
Maximum Baggage S/N 680-0001 thru 680-0500: 
Aft cabin    295 lb. (+440.82 in. aft of datum) 
Tailcone  1,000 lb. (+522.07 in. aft of datum) 
 
S/N 680-0501 and On: 
Aft cabin    312 lb. (+441.63 in. aft of datum) 
Tailcone  1,000 lb. (+522.09 in. aft of datum) 
 
Fuel Capacity S/N 680-0001 thru 680-0500: 
 (usable) Total usable fuel 11,223 lb. (1,675.2 gal). Two wing tanks with 5,611.5 lb. (837.6 gal) usable each 
(See NOTE 1 for unusable); +412.80 in. aft of datum. 
 
S/N 680-0501 and On: 
Total usable fuel 11,394 lb. (1,700 gal). Two wing tanks with 5,697 lb. (850 gal) usable each  
(See NOTE 1 for unusable); +413.43 in. aft of datum. 
 
Oil Capacity Tank mounted on each engine: 5.28 quarts usable each engine;  
 (usable) +534.17 in. aft of datum (see NOTE 1). 
 
Maximum Operating  47,000 ft. 
 Altitude 
 
Control Surface  Elevator  Up 16.6 +1/-0 degrees 
 Movements Down   9.4 +1/-0 degrees 
 Elevator Trim Tab Down   2.1 +/-0.5 degrees 
Down 11.0 +/-0.5 degrees 
The upper and lower elevator trim tab limits are both  
below the control surface neutral position. 
Rudder Right 30.5 +/-0.5 degrees 
Left 30.5 +/-0.5 degrees 
Rudder Trim Tab Right 3.0 +/-0.5 degrees 
Left 3.0 +/-0.5 degrees 
Horizontal Stabilizer Up 6.9 +/-0.5 degrees 
Down 1.2 +/-0.5 degrees 
Aileron Left Up 18.8 +/-0.5 degrees 
Down 13.4 +/-0.5 degrees 
Aileron Right Up 18.5 +/-0.5 degrees 
Down 13.6 +/-0.5 degrees 
Aileron Trim Tab Up 10.0 +/-0.5 degrees 
Down 10.0 +/-0.5 degrees 
Wing Flap Up       0 +/-0.2 degrees 
T.O.      7 +/-0.5 degrees 
T.O./Appr.    15 +/-1.0 degrees 
(680-0001 thru -0500) 
Land 35 +2.0/-2.0 degrees 
(680-0501 and On) 
 Land 35 +1.0/-2.0 degrees 
Speed Brakes – Panels 5, 6   0-24.0 +/-1.0 degrees 
Speed Brakes – Panels 1, 10    0-35.0 +/-1.0 degrees 
Roll Spoilers – Panels 2, 3, 8, 9   0-35.0 +/-1.0 degrees 
Roll Spoilers – Panels 4, 7   0-24.0 +/-1.0 degrees 
See Airplane Maintenance Manual for rigging instructions.

Rev. 18 Page 5 of 15 T00012WI 
I. Model 680 Sovereign  (cont’d) 
 
Serial Nos. Eligible 680-0001 and On 
 
Datum 140.40 in. forward of the nose jack point.  
 
Leveling Means Longitudinal: Place level on the outboard fl oor panel at BL 13.00 inches, inside of the cabin  
  door. 
 Lateral: Place level across inboard seat trac ks behind crew seats at most aft position. 
 
Certification Basis (S/N 680-0001 thru 680-0500): 
 
1. 14 CFR Part 25 effective February 1, 1965,  as amended by Amendments 25-1 through 25-98.  
 
2. 14 CFR Part 34 effective Se ptember 10, 1990, as amended by Amendments 34-1 through 34-3.  
 
3. 14 CFR Part 36 effective December 1, 1969, as amended by Amendment 36-1 through 36-28. 
 
4. Compliance with the Noise Control Act of 1972.  
 
5. Special Conditions. 
a. No. 25-214-SC, High Intensity Radiated Fields (HIRF). 
b. No. 25-248-SC, Side-Facing  Single-Occupant Seats. 
c. No. 25-680-SC, Non-Rechargeable Lith ium Batteries, effective to design changes applied for after May 26, 2017. 
 
6. Exemptions.   
a. Exemption No. 7625A, from the general occupant protect ion requirements of §25.785(b) for multiple-occupancy, 
side-facing divans 
b. Exemption No. 8280, from the lateral trim requirements of §25.161(d) (see NOTE 11). 
c. Exemption No. 10089, from oxygen dispen sing unit requirements of §25.1447(c)(1). 
 
7. Equivalent Levels  of Safety (ELOS). 
a. TC2548WI-T-AG-1, Ditching Em ergency Exits for Passengers. 
b. TC2548WI-T-AG-2, Door Betw een Passenger Compartments. 
c. TC2548WI-T-AG-3, Width of Aisle. 
d. TC2548WI-T-AG-4, Exit Loca tor and Exit Marking Signs. 
e. TC2548WI-T-AG-5, Placards for Main Entry Door. 
f. TC2548WI-T-AG-6, Gust and Continuous Turbulence Loads. 
g. TC2548WI-T-F-1, Use of 1-G Stall Speeds Instead of Mi nimum Speed in the Stall as a Basis for Determining 
Compliance. 
h. TC2548WI-T-P-1, Digital APU Indi cators (Oil Temperature, Gas Temperature, Tachometer). 
j. TC2548WI-T-P-2, Digital Engi ne Parameter, Fuel Flow. 
k. TC2548WI-T-P-5, Use of Single Fire Suppression Bottl e for Protection of APU and Baggage Compartment. 
l. TC2548WI-T-P-6, Certification of Thrust Reversers. 
m. TC2548WI-T-SE-5, Electric Standby Direction Indicator (Compass). 
n. TC2548WI-T-SG-1, Cabin Pressurization - Hi gh Altitude Takeoff and Landing Operation. 
p. Cessna-066650-SG-5, Operation at High Altitude Ai rports between 14,000 ft. and 15,000 ft. MSL. 
 
8. 14 CFR 25.801 ditching not complied with. 
 
9. Compliance with ice protection has been demonstrated in accordance with §25.1419.

T00012WI Page 6 of 15 Rev. 18 
I. Model 680 Sovereign  (cont’d) 
 
Certification Basis (S/N 680-0501 and On): 
 
1. 14 CFR Part 25 effective February 1, 1965,  as amended by Amendments 25-1 through 25-98.  
 
a. Additions (as shown in table). 
 
Section Title Amendment Level Comments 
25.899 
Electrical bonding and 
protection against static 
electricity 
25-129 Winglet installation and all aircraft installations requiring electrical bonding and p-static protection 
25.1317 High Intensity Radiated Field (HIRF) Protection 25-129 Avionics upgrade, winglet installation,  upgraded interior and autothrottle 
25.1323 Airspeed indicating syste m 25-129 Entire airplane 
25.1325 Static pressure systems 25-129 Entire airplane 
25.1419 Ice protection 25-129 Entire airplane  (see Additional Design Requirement (9)(c)) 
25.1431 Electronic equipment 25-129 Winglet installation, powerplant  improvements, and avionics systems 
25.1459 Fli ght data recorders 25-129 When the o ptional flight data recorder is installed 
25.1001 Fuel jettisoning system 25-129 Entire air plane 
Subpart B Flight 25-115 Entire airplane 
Subpart G Operating Limitations and Information 25-115 Entire airplane  (see Additional Design Requirement (9)(c)) 
25.773 Pilot compartment vi ew 25-108 Entire airplane 
25.1329 Flight guidance system 25-119 Autothrottle only 
25.981 Fuel tank ignition prevention 25-125 Winglet installation 
25.1457(a)(6) Cock pit voice recorders 25-124 When an o ptional data link system is installed 
25.1457(d)(5) Cockpit voice recorders 25-124 When the optional flight data  recorder is also required 
 
2. 14 CFR Part 34 effective Se ptember 10, 1990, as amended by Amendments 34-1 through 34-4.  
 
3. 14 CFR Part 36 effective December 1, 1969, as amended by Amendment 36-1 through 36-28. 
 
4. Compliance with the Noise Control Act of 1972.  
 
5. Special Conditions. 
a. No. 25-248-SC, Side-Facing  Single-Occupant Seats. 
b. No. 25-507-SC, Aircraft Electronic System Securi ty Protection from Unauthorized Internal Access. 
c. No. 25-508-SC, Aircraft Electronic System Securi ty Protection from Unauthorized External Access. 
d. No. 25-680-SC, Non-Rechargeable Lith ium Batteries, effective to design changes applied for after May 26, 2017. 
 
6. Exemptions.   
a. Exemption No. 7625A, from the general occupant protect ion requirements of §25.785(b) for multiple-occupancy, 
side-facing divans. 
b. Exemption No. 10902, §25.901(c) Unc ontrollable High Thrust (see NOTE 12). 
 
7. Equivalent Levels  of Safety (ELOS). 
a. TC2548WI-T-AG-1, Ditching Em ergency Exits for Passengers. 
b. TC2548WI-T-AG-2, Door between Passenger Compartments. 
c. TC2548WI-T-AG-3, Width of Aisle. 
d. TC2548WI-T-AG-4, Exit Loca tor and Exit Marking Signs. 
e. TC2548WI-T-AG-5, Placards for Main Entry Door. 
f. TC2548WI-T-AG-6, Gust and Continuous Turbulence Loads. 
g. TC2548WI-T-P-6, Certification of Thrust Reversers. 
h. TC2548WI-T-SE-5, Electric Standby Direction Indicator (Compass).

Rev. 18 Page 7 of 15 T00012WI 
 
I. Model 680 Sovereign  (cont’d) 
 
Certification Basis (S/N 680-0501 and On) (cont’d): 
 
7. Equivalent Levels of Safety (ELOS)  (cont’d). 
j. AT5438WI-T-P-5, 14 CFR 25.901(c), 25.903(d)(2), 25. 1305, 25.1309(a)(b)(c), 25.1321(c)(2), 25.1322, 25.1549, 
Digital-Only Display of Turbine Engine High Pressure Rotor Speed (N2), Oil Pressure, Oil Temperature and Fuel 
Flow. 
k. AT5438WI-T-P-1, 14 CFR 25.1305(a)(4)(5)(6), 25.1549( a)(b)(c), Digital display of APU Instruments 
l. TC2548WI-T-P-5, 14 CFR 25.857, 25.1195, Use of Singl e Fire Suppression Bottle for Protection of both a  
Class C baggage compartment and APU installation. 
m. TC2548WI-T-SG-1, 14 CFR 25.841(a)(b)(6)(8), Cabin Pressurization - High Altitude Takeoff and Landing 
Operation. 
n. Cessna-072100-P-4, 14 CFR 25.1141(f)(2), Powerplant Valve Indication. 
o. TXTAV-011158-F-1, 14 CFR 25.125(a), Steep Approach Re ference Height of 35 feet instead of 50 feet. 
 
8. 14 CFR 25.801 ditching not complied with. 
 
9. Additional Design Requirements. 
 
a. Flight in Icing Conditions.  The design complies with 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 may be 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 after 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 has 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 portion of the flight at cr uise speed and maximum altitude, the airplane has the 
capability for the flight crew to restart engines from a stabilized windmill speed prior to descending below an 
altitude of 15,000 ft., by showing either or both: 
 
a) All but one engine s hould be restarted and accelerated to produce maximum continuous thrust/power,  
or 
b) The engine(s) should be restarted, and the necessary  thrust/power achieved, to enable the airplane to 
maintain level flight. 
 
3) During flight at speeds greater than the minimum fl aps-up “holding speed” and at altitudes below 20,000 ft, 
the airplane has the capability for the flight crew to restart engines from a stabilized windmill speed prior to 
descending 5,000 ft., 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 produce maximum continuous thrust/power,  
 or 
b) The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to 
maintain level flight. 
c) AFM: The AFM text associated with the design maneuvering speed (V A) meets the requirements of 14 
CFR 25.1583, Amendment 25-130. 
 
10. 14 CFR Part 26 is not applicable.

T00012WI Page 8 of 15 Rev. 18 
I. Model 680 Sovereign  (cont’d) 
 
Production Basis Production Certificate No. 4 amended to ad d Model 680, effective September 1, 2004.  See NOTE 
10 for airplane serial number effectivity of Production Certificate No. 4 on new airplane serial 
numbers. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see 
Certification Basis) must be installed in the airplane for certification. 
 
 
NOTE  1. Current weight and ba lance information, including list of equipment included in certificated empty weight, and 
loading instructions are provided for each airplane at the time of original certification. 
 
The certificated empty weight and corresponding center of gravity location must include: 
 
 S/N 680-0001 thru 680-0500 
Unusable fuel 82.90 lb. at +405.86 in. 
Full oil 33.50 lb. at +534.17 in. 
Hydraulic Fluid 46.83 lb. at +505.53 in. 
 
 S/N 680-0501 and On 
Unusable fuel 86.85 lb. at +410.66 in. 
Full oil 33.50 lb. at +534.17 in. 
Hydraulic Fluid 46.83 lb. at +505.53 in. 
 
NOTE  2. S/N 680-0001 thru 680-0500: Airplanes must be operated according to the FAA Approved AFM, part number 
68FM-00 (or later FAA approved revision).  All placards required by either the FAA Approved AFM, the 
applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via 
Parts List 6900000, Airplane Assembly.  A useful placarding reference is the Textron Aviation Illustrated Parts 
Catalogue (IPC).  Any discrepancies identified between the IPC and an aircraft under inspection need to be 
reconciled using the previously stated parts list. 
 
S/N 680-0501 and On: Airplanes must be operated according to the FAA Approved AFM, part number 
68FMA-00 (or later FAA approved revision).  All placards required by either the FAA Approved AFM, the 
applicable operating rules, or the certification basis, must be installed as specified for this Type Certificate via 
Parts List 6900000, Airplane Assembly.  A useful placarding reference is the Textron Aviation Illustrated Parts 
Catalogue (IPC).  Any discrepancies identified between the IPC and an aircraft under inspection need to be 
reconciled using the previously stated parts list. 
 
NOTE  3. See Maintenance Manual, Chapter 4 Airworthine ss Limitations, for inspections, mandatory retirement life 
information, and other requirements for continued airworthiness. 
 
NOTE  4. Aircraft definition for Type Certif icate is Parts List 6900000, Airplane Assembly. 
 
NOTE  5. Certification Maintenance Requirements (CMR) are found in the Maintenance Manual, Chapter 4.  Engineering 
approval of the CMR’s is documented in the Cessna System Safety Assessment reports.  
 
NOTE 6. Deleted. 
 
NOTE 7. Model 680 has been approved for high altitude oper ations (altitudes above 41,000 ft) by compliance with 
certain Part 25 sections.  To ensure the compliance is maintained, any modifications to the pressure vessel must 
be approved in accordance with the requirements as shown in the appropriate certification basis.  To ensure 
pressurization compliance is not affected, this includes modifications which could result in a pressure vessel 
opening, either through crack-growth or antenna loss, greater than 3.98 sq. in.

Rev. 18 Page 9 of 15 T00012WI 
I. Model 680 Sovereign  (cont’d) 
 
NOTE 8. Model 680 received a Provisional Type Certificat e (TC) on December 24, 2003, that was subsequently 
cancelled when TC T00012WI was issued on June 2, 2004. 
 
NOTE 9.   Model 680 has been shown to meet the airworth iness requirements for operations in Reduced Vertical 
Separation Minimum (RVSM) airspace.  No Service Bulletin is associated with this requirement.  All serial 
numbers are eligible.  Each operator must obtain RVSM operating approval directly from the FAA. 
 
NOTE 10. The following serial number will be certified TC only: S/N 680-0501.  Production Certificate No. 4 applies to 
the following Model 680 S/N: 680-0005 and On. 
 
NOTE 11. Exemption No. 8280, from the lateral trim requirem ents of 14 CFR 25.161(d), is only applicable to  
S/N 680-0001 thru 680-0049.  
 
NOTE 12. The FAA has concluded that the occurrence of any uncontrollable high-thrust failure condition, or any of the 
associated causal failures listed within Cessna Document (Maintenance Manual, Chapter 4 Airworthiness 
Limitations), may endanger the safe operation of an airplane. Consequently, the FAA recommends that 
operators be encouraged to report any such failures in accordance with Title 14, CFR Part 121.703(c), 
125.409(c), and 135.415(c). 
 
NOTE 13. The following serial numbers are manufactu red under the name Cessna Aircraft Company:   
 S/N 680-0001 thru 680-0547. 
 
NOTE 14. Company name change effect ive 7/29/2015. The following serial numbers are manufactured under the name 
Textron Aviation Inc.: S/N 680-0548 and On. 
 
NOTE 15. Required Equipment: The basic requi red equipment prescribed in the applicable airworthiness requirements (see 
certification basis) must be installed in the aircraft.  Only hand fire extinguishers that use water and  
U.S. – UL 5B:C – Halotron BrX (2-BTP), C3H2BrF3, CAS Number 1514 82 5 OR U.S. – UL 2A:10B:C – 
Halotron (HCFC Blend-B), C2HCI2BrF3, CAS Number 306-83-2 are approved for use.  No airplanes may have 
a combination of Halotron BrX AND Halotron I hand fire extinguishers installed. 
 
 
II. Model 680A Latitude (Transport Catego ry) S/N 680A0001 and On Approved June 5, 2015 
 
Engines Two Pratt & Whitney Canada Corp. PW306D1 turbofans 
 
Fuel Commercial kerosene Jet A, Jet A-1, Jet B, JP-4, JP-5, JP-8, TS-1, RT, and No. 3 Jet 
 
Engine Limits Static thrust standard day, sea level 
Takeoff 5,907 lb. 
Max. Continuous 5,907 lb. 
 
Max. permissible engine rotor operating speeds (Takeoff and Maximum Continuous) 
N1 (fan)     105.0% (100% = 10,608 r.p.m.) 
N2 (Gas Gen.)  105.0% (100% = 26,930 r.p.m.) 
Max. permissible interturbine gas temperatures: 
Takeoff  920 Degrees C 
Max. continuous 920 Degrees C 
Transient (20 sec.) and starting 950 Degrees C 
 
Airspeed limitations  
VMO (maximum operating) 
Below 8,000 ft. 270 KIAS (270 KCAS) 
8,000 ft. to 29,833 ft. 305 KIAS (305 KCAS) 
MMO above 29,833 ft. 0.80 M I (0.80 MACH calibrated) 
VA (maneuvering sea level)  
30,800 lb. 191 KIAS (191 KCAS) 
See AFM for variations with weight and altitude.

T00012WI Page 10 of 15 Rev. 18 
II. Model 680A Latitude (cont’d) 
 
Airspeed limitations (cont’d) 
 
VRA (Rough air speed) 
Below 38,813 ft. 225 KIAS (225 KCAS) 
Above 38,813 ft. 0.73 M I (0.73 MACH calibrated) 
Flap extension speeds 
VFE (Position UP to 1) 250 KIAS (250 KCAS) 
VFE (Position 1 to 2) 200 KIAS (200 KCAS) 
VFE (Position 2 to FULL) 175 KIAS (175 KCAS) 
VMCA (Minimum Control Speed) Air Flaps 1 88 KIAS (88 KCAS) 
VMCA (Minimum Control Speed) Air Flaps 2 83 KIAS (83 KCAS)  
VMCL (Minimum Control Speed) Landing Flaps 2   83 KIAS (83 KCAS)  
VMCL (Minimum Control Speed) Landing Flaps FULL  78 KIAS (78 KCAS) 
VMCG (Minimum Control Speed) Ground Flaps 1  88 KIAS (88 KCAS) 
VMCG (Minimum Control Speed) Ground Flaps 2  91 KIAS (91 KCAS) 
VLO (Landing Gear Operating) 210 KIAS (211 KCAS) 
VLE (Landing Gear Extended) 210 KIAS (211 KCAS) 
VSB (Speed Brakes Extension) A ny speed with or without flaps 
Maximum autopilot operating speed 
Below 8,000 ft. 270 KIAS (270 KCAS) 
8,000 to 29,833 ft. 305 KIAS (305 KCAS) 
Above 29,833 ft. 0.80 M I (0.80 MACH calibrated) 
Maximum tire ground speed 182 knots  
 
C.G. Range (Landing Gear Extended) Design C.G. Limits:  
 
Forward: 18.00% MAC at 19,700 lb. to 23,700 lb. 
Linear variation from 18.00% MAC at 23,700 lb. to 21.68% MAC  
at 31,050 lbs. 
Takeoff Forward 21.56% MAC at 30,800 lb. 
 
Aft: 31.00% MAC at 17,500 lb. to 31,050 lb. 
Landing Gear retracting moment -7,954 in-lb. 
 
Empty Wt. None 
 C.G. Range 
 
MAC 107.06 in. (L.E. of MAC at +368.24 in. aft of datum) 
 
Maximum Weight Takeoff 30,800 lb. 
Landing 27,575 lb. 
Ramp 31,050 lb.  
Zero Fuel 21,430 lb. 
 
Minimum Crew One pilot and one copilot 
 for all Flights 
 
Number of Seats Maximum 11 (two crew plus nine passenger seats) 
 
Maximum Baggage Tailcone  1,000 lb. (+500.09 in. aft of datum) 
 
Fuel Capacity Total usable fuel 11,394 lb. (1,700 gal). Two wing tanks with 5,697 lb. (850 gal) usable each  
(usable) (see NOTE 1 for unusable); +399.03 in. aft of datum. 
 
Oil Capacity  Tank mounted on each engine: 5.28 quarts usable each engine; +519.73 in. aft of datum  
 (usable)  (see NOTE 1).

Rev. 18 Page 11 of 15 T00012WI 
II. Model 680A Latitude (cont’d) 
 
Maximum Operating 45,000 ft. 
 Altitude  
 
Control Surface  Elevator   Up 16.6 +1/-0 degrees 
 Movements  Down   9.4 +1/-0 degrees 
Elevator Trim Tab Down   2.1 +0.0/-0.5 degrees 
 Down 12.5 +/-0.5 degrees 
The upper and lower elevator trim tab limits are both  
below the control surface neutral position. 
Rudder Right 30.5 +/-0.5 degrees 
   Left 30.5 +/-0.5 degrees 
Rudder Trim Tab Right  3.0 +/-0.5 degrees 
  Left  3.0 +/-0.5 degrees 
Horizontal Stabilizer Up  7.4 +/-0.5 degrees 
  Down 1.2 +0.2/-0.0 degrees 
Aileron Left Up 18.8 +/-0.5 degrees 
  Down  13.4 +/-0.5 degrees 
Aileron Right Up 18.5 +/-0.5 degrees 
  Down 13.6 +/-0.5 degrees 
Aileron Trim Tab Up 10.0 +/-0.5 degrees 
  Down 10.0 +/-0.5 degrees 
Wing Flap UP       0 +/-0.2 degrees 
1   7.1 +/-0.5 degrees 
2 15.1 +/-1.0 degrees 
FULL 35.1 +1.0/-2.0 degrees 
Speed Brakes – Panels 5, 6 0-24 +/-1.0 degrees 
Speed Brakes – Panels 1, 10 0-35 +/-1.0 degrees 
Roll Spoilers – Panels 2, 3, 8, 9 0-35 +/-1.0 degrees 
Roll Spoilers – Panels 4, 7 0-24 +/-1.0 degrees 
 See Airplane Maintenance Manu al for rigging instructions. 
 
Serial Nos. Eligible 680A0001 and On 
 
Datum 135.52 in. forward of the nose jack point.  
 
Leveling Means Longitudinal: Put the leveling bar on the center of the floorboard panel at approximately BL 
0.00 inches, directly in front of the cabin entry door. 
Lateral:  Put the leveling bar be hind the inboard crew seat rails and flush against the rear  
of the seat rails.

T00012WI Page 12 of 15 Rev. 18 
II. Model 680A Latitude  (cont’d) 
 
Certification Basis:  
 
1. 14 CFR Part 25 effective February 1, 1965,  as amended by Amendments 25-1 through 25-98.  
 
a. Additions (see table below). 
 
Section Title Amendment Level Comments 
25.571 Damage-Tolerance and Fatigue Evaluation of Structure 25-134 Fuselage, Engine Support 
25.773 Pilot compartment vi ew 25-134 Entire airplane 
25.783 Fuselage Doors 25-134 Entire airplane 
25.807 Emergency exits 25-134 Fuselage 
25.809 Emer gency exit arrangement 25-134 Fusela ge 
25.810 Emergency egress assist means  and escape routes 25-114 Entire airplane 
25.820 Lavatory doors 25-114 Entire airplane 
25.899 Electrical bonding and protection against static electricity 25-134 Entire airplane 
25.903 Engines 25-134 Entire airplane 
25.981 Fuel tank ex plosion prevention 25-125 Win glet installation 
25.981(a)(d) Fuel tank ex plosion prevention 25-134 Fusela ge 
25.1001 Fuel jettisoning system 25-134 Entire air plane 
25.1316 Electrical and electronic system lightning projection 25-134 Entire airplane 
25.1317 High Intensity Radiated  Fields (HIRF) Protection 25-134 Entire airplane 
25.1323 Airspeed indicating syste m 25-129 Entire airplane 
25.1325 Static pressure systems 25-129 Entire air plane 
25.1329 Fli ght guidance system 25-119 Autothrottle onl y 
25.1419 Ice protection 25-129 Entire air plane 
25.1431 Electronic equipment 25-129 Winglet installation, powerplant improvements, and avionics systems 
25.1457(a)(6) Cockpit voice recorders 25-124 When an optional data link  system is installed 
25.1459 Flight recorders 25-129 When the optional flight data recorder is installed 
Subpart B Flight 25-129 Entire airplane 
Subpart G Operating Limitations  and Information 25-115 Entire airplane 
Subpart G Operating Limitations  and Information 25-130 
The AFM text associated with the 
design maneuvering speed (VA) 
must meet the requirements of 14 
CFR 25.1583, Amendment 25-130 
Appendix C Ice Shapes 25-0 
Original ice shapes can be used to 
show compliance, based on the 
atmospheric icing conditions 
defined at Amendment 25-0 
 
2. 14 CFR Part 34 effective Se ptember 10, 1990, as amended by Amendments 34-1 through 34-5.  
 
3. 14 CFR Part 36 effective December 1, 1969, as amended by Amendment 36-1 through 36-28. 
 
4. Compliance with the Noise Control Act of 1972.

Rev. 18 Page 13 of 15 T00012WI 
II. Model 680A Latitude  (cont’d) 
 
Certification Basis (cont’d):  
 
5. Special Conditions. 
a. No. 25-248-SC, Side-Facing  Single-Occupant Seats. 
b. No. 25-507-SC, Aircraft Electronic System Securi ty Protection from Unauthorized Internal Access. 
c. No. 25-508-SC, Aircraft Electronic System Securi ty Protection from Unauthorized External Access. 
d. No. 25-579-SC, Pilot Compartmen t View - Hydrophobic Coatings in Lieu of Windshield Wipers. 
e. No. 25-680-SC, Non-Rechargeable Lith ium Batteries, effective to design changes applied for after May 26, 2017. 
 
6. Exemption.   
a. Exemption No. 7625B, from the general occupant prot ection requirements of 14 CFR 25.785(b) for multiple-
occupancy, side-facing divans. 
b. Exemption No. 11350, 14 CFR 25.809(a) fo r view out of emergency door exits. 
 
7. Equivalent Level of Safety (ELOS). 
a. TC2548WI-T-AG-2, 14 CFR 25.813(e),  Door between Passenger Compartments. 
b. TC2548WI-T-AG-4, 14 CFR 25.811(d)(1), 25.812(b )(1), Exit Locator and Exit Marking Signs. 
c. TC2548WI-T-AG-6, 14 CFR 25.341(b), Gust and Continuous Turbulence Loads. 
d. TC2548WI-T-P-6, 14 CFR 25.933(a)(1)(ii) , Flight Critical Thrust Reverser. 
e. TC2548WI-T-SE-5, 14 CFR 25.1303(a)(3), 25.1547, Electric Standby Direction Indicator (Compass). 
f. AT5438WI-T-P-5, 14 CFR 25.1549(a)(b)(c), Digital-Only Display of Turbine Engine High Pressure Rotor Speed 
(N2), Oil Pressure, Oil Temperature, and Fuel Flow. 
g. AT5438WI-T-P-1, 14 CFR 25.1305(a)(4)(5)(6), 25 .1549(a)(b)(c), ELOS for APU Instrumentation. 
h. TC2548WI-T-P-5, 14 CFR 25.857(c)(2), 25.1195(a)(b), Us e of Single Fire Suppression Bottle for Protection of 
both a Class C Baggage Compartment and APU Installation. 
j. Cessna-072100-AG-1, 14 CFR 25.807(i), Emergency Exit – Use of Water Barrier. 
k. Cessna-072100-S-3, 14 CFR 25.831(g), Acceptable High Te mperature Physiological Environment During Failure 
Conditions. 
l. Cessna-072100-P-4, 14 CFR 25.1141(f)(2),  Powerplant Valve Indication. 
m. Cessna-072100-S-5, 14 CFR 25.783(d)(2), Cabin Entry Door – Independence of Latch Securing Means and 
Locking System. 
n. Cessna-072100-S-6, 14 CFR 25.783(d)(2), Unpressurized Doors – Independence of Latch Securing Means and 
Locking Systems. 
o. Cessna-072100-S-2, 14 CFR 25.841(a)(b)(6), Cabin Pre ssurization – High Elevation Takeoff and Landing 
Operations Systems. 
p. TXTAV-014008-F-1, 14 CFR 25.125(a), Steep Approach re ference height of 35 feet instead of 50 feet. 
 
8. 14 CFR 25.801 ditching not complied with. 
 
9. Compliance with ice protection has been de monstrated in accordance with 14 CFR 25.1419. 
 
10. Additional Design Requirements: 
 
a. In-Flight Engine Restart.  A minimum restart capability after 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 has 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 portion of the flight at cr uise speed and maximum altitude, the airplane has the 
capability for the flight crew to restart engines from a stabilized windmill speed prior to descending below an 
altitude of 15,000 ft, by showing either or both: 
 
a) All but one engine restarted and accelerated to produce maximum continuous thrust/power,  
 or 
b) The engine(s) restarted, and the n ecessary thrust/power achieved, to enable the airplane to maintain level 
flight.

T00012WI Page 14 of 15 Rev. 18 
II. Model 680A Latitude  (cont’d) 
 
3) During flight at speeds greater than the minimum fl aps-up “holding speed” and at altitudes below 20,000 ft, 
the airplane has the capability for the flight crew to restart engines from a stabilized windmill speed prior to 
descending 5,000 ft 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 restarted and accelerated to produce maximum continuous thrust/power,  
 or  
b) The engine(s) restarted, and the necessary thrust/power  achieved, to enable the airplane to maintain level 
flight. 
 
11. 14 CFR Part 26 is not applicable. 
 
The application to amend Type Certificate (TC) T00012WI was dated January 25, 2012.  TC T00012WI was amended to 
add the Model 680A and it was obtained by the manufacturer using the Organization Designation Authorization (ODA) 
Procedures. 
 
Production Basis Production Certificate No. 4 amended to ad d Model 680A, effective June 5, 2015.  See NOTE 9  
for airplane serial number effectivity of Production Certificate No. 4 on new airplane serial  
numbers. 
Equipment  The basic required equipment as prescribed in the applicable airworthiness regulations (see  
Certification Basis) must be installed in the airplane for certification. 
 
 
NOTE 1. Current weight and ba lance information, including list of equipment included in certificated empty weight, and 
loading instructions are provided for each airplane at the time of original certification. 
 
The certificated empty weight and corresponding center of gravity location must include: 
 
Unusable fuel 86.85 lb. at +395.22 in. 
Full oil 33.50 lb. at +519.73 in. 
Hydraulic Fluid 56.97 lb. at +415.52 in.  
 
NOTE 2. Airplanes must be operated according to the FAA Approved AFM, Part Number 68AFM-00 (or later FAA 
approved revision).  All placards required by either the FAA Approved AFM, the applicable operating rules, or 
the certification basis, must be installed as specified for this Type Certificate via Parts List 7400000, Airplane 
Assembly.  A useful placarding reference is the Textron Aviation Illustrated Parts Catalogue (IPC).  Any 
discrepancies identified between the IPC and an aircraft under inspection need to be reconciled using the 
previously stated parts list. 
 
NOTE 3. See Maintenance Manual, Chapter 4 Airworthine ss Limitations, for inspections, mandatory retirement life 
information, and other requirements for continued airworthiness. 
 
NOTE 4. Aircraft definition for TC is  Parts List 7400000, Airplane Assembly. 
 
NOTE 5. Certification Maintenance Requirements (CMR) are f ound in the Maintenance Manual, Chapter 4.  Engineering 
approval of the CMR’s is documented in the Cessna System Safety Assessment reports.  
 
NOTE 6. Model 680A has been approved for high altitude operations (altitudes above 41,000 ft) by compliance with 
certain Part 25 sections.  To ensure the compliance is maintained, any modifications to the pressure vessel must 
be approved in accordance with the requirements as shown in the appropriate certification basis.  To ensure 
pressurization compliance is not affected, this includes modifications which could result in a pressure vessel 
opening, either through crack-growth or antenna loss, greater than 5.00 sq. in. 
 
NOTE 7.  Model 680A has been shown to meet the airworth iness requirements for operations in RVSM airspace.  All 
serial numbers are eligible.  Each operator must obtain RVSM operating approval directly from the FAA.    
 
NOTE 8. The following serial number is  certified TC only, under the name Cessna Aircraft Company: S/N 680A0005.

Rev. 18 Page 15 of 15 T00012WI 
 
NOTE 9. Company name change effect ive 7/29/2015. The following serial numbers are manufactured under the name 
Textron Aviation Inc.: S/N 680A0001 thru 680A0004, 680A0006 and On. 
 
NOTE 10. Flight crew use of the alerting system during high el evation airport takeoff and landing operations may result in 
non-compliance with 14 CFR 91.211(a)(1), 121.329(b)(1)(2), and 135.89(b) requirements for flight crew use of 
supplemental oxygen.  
 
NOTE 11. Required Equipment: The basic requi red equipment prescribed in the applicable airworthiness requirements (see 
certification basis) must be installed in the aircraft.  Only hand fire extinguishers that use water and  
U.S. – UL 5B:C – Halotron BrX (2-BTP), C3H2BrF3, CAS Number 1514 82 5 OR U.S. – UL 2A:10B:C – 
Halotron (HCFC Blend-B), C2HCI2BrF3, CAS Number 306-83-2 are approved for use.  No airplanes may have 
a combination of Halotron BrX AND Halotron I hand fire extinguishers installed. 
 
 
-------- END -------
```

## ADs (7, 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 2018-07-13](https://openairdocs.org/ad/2018-07-13): Landing Gear · Textron 510, 680 and 680A. Effective May 15, 2018
- [AD 2017-06-13](https://openairdocs.org/ad/2017-06-13): Fuselage · Textron 680. Effective May 2, 2017
- [AD 2012-07-04](https://openairdocs.org/ad/2012-07-04): Electrical Power · Cessna 680. Effective May 15, 2012
- [AD 2007-26-16](https://openairdocs.org/ad/2007-26-16): Aft fairing wire bundle assembly · Cessna 680. Effective Jan 18, 2008
- [AD 2005-08-03](https://openairdocs.org/ad/2005-08-03): Cockpit display units · Cessna 680. Effective Apr 29, 2005

## Registered aircraft by registry model (OpenAirDocs)

- [Textron 680A](https://openairdocs.org/model/textron-680a): 402 aircraft (registry code 2076814)
- [Cessna 680](https://openairdocs.org/model/cessna-680): 253 aircraft (registry codes 2076811, 2076821)
- [Textron 680](https://openairdocs.org/model/textron-680): 40 aircraft (registry code 2076815)
- [Cessna 680A](https://openairdocs.org/model/cessna-680a): 2 aircraft (registry codes 2076816, 2076813, 2076817)

## STCs approved under this data sheet (56, first 50)

- [STC ST04765NY](https://openairdocs.org/stc/ST04765NY): Unprepared (Grass/Sod) Runway Operations. Textron Aviation Inc.
- [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center
- [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems
- [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 ST122244IB](https://openairdocs.org/stc/ST122244IB): Installation of Gogo Galileo system, including HDX Antenna. Alamo Engineering GmbH
- [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 ST11983SE](https://openairdocs.org/stc/ST11983SE): Installation of Starlink Aviation System. AeroMech Incorporated
- [STC ST12082WI](https://openairdocs.org/stc/ST12082WI): Upgrade of AirCell High Speed Internet System to Gogo Business Aviation C1 System. Duncan Aviation Inc.
- [STC ST11984SE](https://openairdocs.org/stc/ST11984SE): Installation of Starlink Aviation System. AeroMech Incorporated
- [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 ST02037WI](https://openairdocs.org/stc/ST02037WI): Installation of Gogo Business  Aviation AVANCE L5 System with MB 13 Antennas. Duncan Aviation Inc.
- [STC ST01141DE](https://openairdocs.org/stc/ST01141DE): Installation of the LifePort Medical Interior. LifePort LLC
- [STC ST04736NY](https://openairdocs.org/stc/ST04736NY): True Blue TS28 Emergency Battery Power Supply Replacement. Aerospace Design and Compliance LLC
- [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC
- [STC 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 ST04575AT](https://openairdocs.org/stc/ST04575AT): Installation of the Rockwell Collins ALT-1000+/ -4000+ with 5G Filtering. Chippewa Aerospace Inc.
- [STC ST04367CH](https://openairdocs.org/stc/ST04367CH): Installation of a Medical Interior in accordance with LifePort Master Data List EGR-887-000-001, Revision (B), dated April 18, 2019 or later FAA approved revision and LifePort Master Drawing List MDL-887-00, Revision (D), dated April 11, 2019 or later FAA approved revision.". LifePort LLC
- [STC ST04477CH](https://openairdocs.org/stc/ST04477CH): Installation of a Honeywell RDR-7000 Weather Radar System in accordance with AeroTec STC Master Data List, Doc. # ATEC-077-241-1200, Revision F, dated June 4. 2021, or later FAA-approved revisions.. AeroTEC Inc
- [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC ST04573NY](https://openairdocs.org/stc/ST04573NY): AVIATOR 300 Installation. Amtech Aeronautical Limited
- [STC ST01941WI](https://openairdocs.org/stc/ST01941WI): Installation of Gogo Business Aviation AVANCE L5 Broadband System. Duncan Aviation Inc
- [STC ST01403WI-D](https://openairdocs.org/stc/ST01403WI-D): Installation of alternate part number DU-1080 Display Unit.. Honeywell International Inc
- [STC ST01410WI-D](https://openairdocs.org/stc/ST01410WI-D): Installation of alternate part number NI-900 Network Interface Module.. Honeywell International Inc
- [STC ST01440WI-D](https://openairdocs.org/stc/ST01440WI-D): Installation of alternate part number EPIC MC-850-2 Multi-Function Control Display Unit.. Honeywell International Inc
- [STC ST01448WI-D](https://openairdocs.org/stc/ST01448WI-D): Installation of EPIC Phase 4.1 Software.. Honeywell International Inc
- [STC ST01482WI-D](https://openairdocs.org/stc/ST01482WI-D): Installation of EPIC Phase 4.2 Software, alternate part number AGM-200 AFGS and alternate part number TR-865B CMF VDR. Honeywell International Inc
- [STC ST01530WI-D](https://openairdocs.org/stc/ST01530WI-D): Installation of EPIC NIC/PROC, AIOP, AND CMC modules and Pentium M software. Honeywell International Inc
- [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 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 ST01840WI](https://openairdocs.org/stc/ST01840WI): Installation of winglets, wing structural reinforcement, and related system changes. Winglet Technology LLC
- [STC ST00934DE](https://openairdocs.org/stc/ST00934DE): Installation of Becker Avionics BXT6553 transponder. Peregrine
- [STC ST02240LA-D](https://openairdocs.org/stc/ST02240LA-D): Installation of a Patient Loading and Utility System (PLUS).. LifePort LLC
- [STC ST02286LA](https://openairdocs.org/stc/ST02286LA): 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 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 ST04366AT](https://openairdocs.org/stc/ST04366AT): This STC is a replacement of the original equipment nickel cadmium main batteries manufactured by Saft or Marathon with Concorde valve regulated lead acid main batteries. Concorde Battery Corporation
- [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 ST01399WI](https://openairdocs.org/stc/ST01399WI): Installation of Honeywell DL-950 Data Loader.. Textron Aviation Inc
- [STC ST11168SC](https://openairdocs.org/stc/ST11168SC): Installation of a Pratt & Whitney Flight Data Acquisition, Storage, and Transmission System (FAST). Pratt & Whitney Engine Services Inc.
- [STC ST02127LA](https://openairdocs.org/stc/ST02127LA): Installation of a Crane Aerospace & Electronics Tire Sensor Assembly. ELDEC Corporation
- [STC ST00717DE](https://openairdocs.org/stc/ST00717DE): Installation of a camera portal as a provision to accommodate a future camera. Sierra Nevada Corporation
- [STC ST01655WI-D](https://openairdocs.org/stc/ST01655WI-D): Installation of a Tenfine Chinese Flight Inspection System.. Duncan Aviation Inc
- [STC ST00715DE-D](https://openairdocs.org/stc/ST00715DE-D): Installation of Nose Boom Provisions, Pylons and Antennas. Sierra Nevada Corporation
- [STC ST00718DE](https://openairdocs.org/stc/ST00718DE): Interior installation of, operator seats, equipment racks, power distribution panel, signal junction boxes, inoperative cockpit video display, cabin Inter-Communication System (ICS), ballast boxes and provisions to mount antennas, and baggage compartment installation of, power inverters, alternating current/direct current junction boxes, and a lead-acid mission battery in accordance with Sierra Nevada Corporation Drawing List, Report No. MDL- 0142-25-9309 Revision A, dated June 15, 2011, FAA approved July 25, 2011, or later FAA approved revision.. Sierra Nevada Corporation
- [STC ST00720DE](https://openairdocs.org/stc/ST00720DE): Installation of sensors and provisions for future capability to monitor aircraft control surface deflections, existing pilot control input signals, and other aircraft systems in accordance with Sierra Nevada Corporation Drawing List, Report Number MDL-0142-25-9315, Revision B, dated February 24, 2011, FAA approved July 25, 2011, or later FAA approved revision.. Sierra Nevada Corporation
- [STC ST00719DE](https://openairdocs.org/stc/ST00719DE): Installation of structural fittings in the wing as provisions to accommodate future external stores in accordance with Sierra Nevada Corporation Drawing List, Report No  MDL-0142-25-9316, Revision A, dated February 15, 2011, FAA approved March 29, 2011, or later FAA approved revision.. Sierra Nevada Corporation
- [STC ST01608WI-D](https://openairdocs.org/stc/ST01608WI-D): Installation of Aircell High Speed Internet System with Wireless LAN System. Duncan Aviation Inc

All 56: https://openairdocs.org/tcds/T00012WI/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.