# TCDS A37CE: Textron Aviation Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Textron Aviation Inc.
- Revision: 25
- Revised: August 1, 2025
- Product: Aircraft, Small Airplane
- Certification basis: Part 23
- Registered aircraft: 1,019, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/4d/31/4d31562f875b4b2d18a1d6f98404ffd7b2520a39f2f90783c8054dece06dd862
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID139525973020250804161345.0001
- Page: https://openairdocs.org/tcds/A37CE

## Models (2)

As the data sheet lists them.

- 208B
- 208

## 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 
Rev. No. 25 23 17 16 13 20 23 20 21 24 22 25 25 
 
DEPARTMENT OF TRANSPORTATION 
 FEDERAL AVIATION ADMINISTRATION 
 
 
A37CE  
Revision 25  
 
Textron Aviation  
208 
208B  
August 1, 2025  
 
 
 TYPE CERTIFICATE DATA SHEET NO. A37CE 
 
This data sheet, which is part of Type Certificate No. A37CE, 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 208, Caravan, 11 PCLM (Normal Category), Approved October 23, 1984; 
Model 208, Caravan, 11 PCSM (Normal Category), Approved March 26, 1986  
 
 Engine [Applicable to S/N 20800001 thru 20800276] (600 SHP) 
Pratt & Whitney of Canada Ltd., PT6A-114 Turbo Prop 
Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop 
(When operated to PT6A-114 operating limitations) 
 
 Engine [Applicable to S/N 20800277 and On] (675 SHP) 
Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop 
 
 Fuel Aviation turbine fuel Jet A, Jet A-1, Jet B,  JP-1, JP-4, JP-5 or JP-8.  For required use of 
anti-icing additives and emergency use of aviation gasoline, refer to the Pilot’s Operating 
Handbook (POH) and FAA Approved Airplane Flight Manual (AFM). 
 
 Engine Limits [Applicable to S/N 20800001 thru 20800276] 
  P&W PT6A-114 or PT6A-114A when operated to PT6A-114 operating limits 
  
 
Shaft 
Horsepower 
NG Gas 
Generator 
Speed 
(% rpm) 
 
Indicator 
Torque 
(ft.-lb.) 
 
Prop Shaft 
Speed 
(rpm) 
Maximum 
Permissible 
Interturbine 
Temp. (C) 
Takeoff static & 
  max. continuous 
 
600 (1) 
 
101.6 
 
1658 
 
1900 
 
     805 
Maximum climb 600 (1) 101.6 1658/1970 (2) 1900      765 
Maximum cruise 600 (1) 101.6 1658/1970 (2) 1900      740 
Idle   - 52 min.       -    -      685 
Starting (2 sec.)   -     -       -    -    1090 
Max. reverse (1 min.) 600 (1) 101.6 1658 1825      805 
Transient (2 sec.)   - 102.6 2200 2090      850

A37CE 2 Rev. 25  
I.  Model 208, Caravan (cont’d) 
 
 Engine Limits [Applicable to S/N 20800277 and On] 
 
  P&W PT6A-114A 
  
 
Shaft 
Horsepower 
NG Gas 
Generator 
Speed 
(% rpm) 
 
Indicator 
Torque 
(ft.-lb.) 
 
Prop Shaft 
Speed 
(rpm) 
Maximum 
Permissible 
Interturbine 
Temp. (C) 
Takeoff static & 
  max. continuous 
 
675 (1) 
 
101.6 
 
1865 
 
1900 
 
805 
Maximum climb 675 (1) 101.6 1865/1970 (2) 1900 765 
Maximum cruise 675 (1) 101.6 1865/1970 (2) 1900 740 
Idle   - 52 min.       -    - 685 
Starting (2 sec.)   -     -       -    - 1090 
Max. reverse (1 min.) 675 (1) 101.6 1865 1825   805 
Transient (2 sec.)   - 102.6 2200 2090   850 
 
(1) Flat Rated: 
The engines may produce more power than that for which the airplane has been 
certificated.  Under these conditions, the stated torque, ITT, or Ng limitations shall 
not be exceeded. 
(2) If maximum torque is used, propeller r.p.m.  must be set so as not to exceed power 
limitations. 
 
 Propeller and Propeller L imits [Applicable to S/N 20800001 through 20800276] (600 SHP) 
 
Hartzell composite three-bladed, constant speed, full-feathering, reversible  
Model: HC-B3MN3/M10083 
Diameter: Maximum 100 inches, minimum 100 inches, no cutoff approved 
Pitch at 42-inch station: 
 Low pitch (Beta pickup) 9° 
 Feathered  78.4° 
 Maximum Reverse -18°  
 
 Propeller and Propeller Limits [A pplicable to S/N 20800001 and On and all TKS equipped aircraft] (675 SHP) 
 
McCauley aluminum three-bladed, constant speed, full-feathering, reversible  
Model: 3GFR34C703/106GA-0 
Diameter: Maximum 106 inches, minimum 104 inches  
 (2-inch cutoff on diameter allowed) 
Pitch at 30-inch station: 
 Low pitch (Beta pickup) +15.6° 
 Feathered +88° 
 Maximum Reverse -14° 
 
 *Airspeed Limits V MO (Max Operating) 175 KIAS 
S/N 20800001 V A  (Maneuvering) at 7300 lb. 148 KIAS 
thru 20800060 See POH/AFM for variati ons with weight and altitude. 
VFE (Flaps extended) 
 To 10°  175 KIAS 
 10° to 20° 150 KIAS 
 20° to 30°  125 KIAS 
 
 *Airspeed Limits V MO (Max Operating) 175 KIAS 
S/N 20800061 and On V A (Maneuvering) at 8000 lb. 150 KIAS 
See POH/AFM for variations with weight and altitude. 
VFE (Flaps extended) 
 To 10°  175 KIAS 
 10° to 20°  150 KIAS 
 20° to 30°  125 KIAS

A37CE 3 Rev. 25  
I.  Model 208, Caravan (cont’d) 
 *Airspeed Limits (cont’d) 
 
S/N 20800014 and On V MO (Max Operating) 175 KIAS 
Amphibian V A (Maneuvering) at 7600 lb. 141 KIAS 
 See POH/AFM for variations with weight and altitude. 
VFE (Flaps extended) 
 To 10°  175 KIAS 
 10° to 20° 150 KIAS 
 20° to 30°  125 KIAS 
 
 C.G. Range  Takeoff and Flight 
S/N 20800001 and On (+174.06) to (+184.35) at 8000 lb.  
(+162.41) to (+184.35) at 4200 lb. 
Straight line variation between points given 
 
Landing 
(+173.44) to (+184.35) at 7800 lb. 
(+162.41) to (+184.35) at 4200 lb. 
Straight line variation between points given 
 
S/N 20800014 and On Takeoff and Flight 
Amphibian (+172.83) to (+182.68) at 7600 lb.  
 (+165.47) to (+182.68) at 5200 lb. 
Straight line variation between points given 
 
Landing 
(+171.91) to (+182.68) at 7300 lb. 
(+165.47) to (+182.68) at 5200 lb. 
Straight line variation between points given 
 
 Empty Wt. C.G. Range None 
 
 Maximum Weight 8000 lb. takeoff and flight 
S/N 20800001 and On 7800 lb. landing 
8035 lb. ramp 
 
S/N 20800014 and On 7600 lb. takeoff and flight 
Amphibian 7300 lb. landing 
 7635 lb. ramp 
 
 No. of Seats 1 and 2 (at +133.5 to +146.5) Pilot Seat Locations. 
3 through 11 refer to current POH and FAA Approved AFM for passenger seating 
arrangements. 
 
 Maximum Baggage Reference weight and balance data 
 
 Fuel Capacity 335 gal. (332 gal. usable),  two 167.5 gal. tanks in wings at +183.8 
See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 3.5 gal. total, 2.37 gal.  usable in engine mounted tank at +69.2 
 
 Maximum Operating 30,000 ft. - Landplane 600 SHP  
Altitude 25,000 ft. - Landplane 675 SHP 
20,000 ft. - Amphibian and Landplane Flight into Known Icing

A37CE 4 Rev. 25  
I.  Model 208, Caravan (cont’d) 
 
 Control Surface Wing flaps 0° +1° Up, 10° +1° -2° Down, 20° +2° Down, 
Movements   30° +1° -2° Down 
LH & RH Flap Extension to be symmetric within 1/2° at all positions 
Main surfaces 
Ailerons Up 25° +4° -0° Down 16° +1° -0°  
Spoiler Up 40° +5° Down   0° +0° -5° 
Elevator Up 25° +2° Down 20° +2° 
Elevator (w/TKS fairing) Up 18° +1° Down 20° +2° 
Rudder (Landplane) Right 25° +2° Left 25° +2° 
 (Amphibian) Right 23° +2°,  -0° Left 23° +2°, -0° 
(Measured perpendicular to hinge line) 
Tabs (main surfaces in neutral) 
Aileron (RH) Up 15° +2° Down 15° +2° 
Elevator Up 15° +2° Down 15° +2° 
Tabs servo actions 
Aileron (RH): 50% of aileron travel +1° Up and Down 
 (tab adjusted to neutral) 
Aileron (LH): 50% of aileron travel +1° Up and Down  
 
 Serial No. Eligible 20800001 and On - Landplane 
20800014 and On - Amphibian with Wipline Model 8000 Amphibious/Seaplane Floats. 
 
 
II. Model 208B, Caravan, 2 PCLM (Norma l Category), Approved October 9, 1986 
 Model 208B, Caravan, 11 PCLM (Norma l Category), Approved December 13, 1989 
 
 Engine Pratt & Whitney of Cana da Ltd., PT6A-114 Turbo Prop:  
1. S/N 208B0001 thru 208B0178 and 208B0180 thru 208B0229, and as modified by 
SK208-84 (600 SHP). 
 
Pratt & Whitney of Canada Ltd., PT6A-114A Turbo Prop:  
1. S/N 208B0001 thru 208B0178 and 208B0180 thru 208B0229, as modified by 
SK208-84 when operated to PT6A-114 operating limits (600 SHP). 
2. S/N 208B0179, 208B0230 thru 208B4999, as modified by SK208-80 (675 SHP). 
 
 Fuel Aviation turbine fuel Jet A, Jet A-1, Jet B,  JP-1, JP-4, JP-5 or JP-8.  For required use of  
anti-icing additives and emergency use of aviation gasoline, refer to the POH and FAA 
Approved AFM. 
 
 Engine Limits P&W PT6A-114 or PT6A-114A  when operating to PT6A-114 operating limits: 
  
 
Shaft 
Horsepower 
NG Gas 
Generator 
Speed 
(% rpm) 
 
Indicator 
Torque 
(ft.-lb.) 
 
Prop Shaft 
Speed 
(rpm) 
Maximum 
Permissible 
Interturbine 
Temp. (C) 
Takeoff static & 
  max. continuous 
 
600 (1) 
 
101.6 
 
1658 
 
1900 
 
805 
Maximum climb 600 (1) 101.6 1658/1970 (2) 1900 765 
Maximum cruise 600 (1) 101.6 1658/1970 (2) 1900 740 
Idle   - 52 min.       -    - 685 
Starting (2 sec.)   -     -       -    - 1090 
Max. reverse (1 min.) 600 (1) 101.6 1658 1825   805 
Transient (2 sec.)   - 102.6 2200 2090   850

A37CE 5 Rev. 25  
II. Model 208B, Caravan (cont’d) 
 Engine Limits (cont’d) 
 
  PT6A-114A (675 hp) 
  
 
Shaft 
Horsepower 
NG Gas 
Generator 
Speed 
(% rpm) 
 
Indicator 
Torque 
(ft.-lb.) 
 
Prop Shaft 
Speed 
(rpm) 
Maximum 
Permissible 
Interturbine 
Temp. (C) 
Takeoff static & 
  max. continuous 
 
675 (1) 
 
101.6 
 
1865 
 
1900 
 
805 
Maximum climb 675 (1) 101.6 1865/1970 (2) 1900 765 
Maximum cruise 675 (1) 101.6 1865/1970 (2) 1900 740 
Idle   - 52 min.       -    - 685 
Starting (2 sec.)   -     -       -    - 1090 
Max. reverse (1 min.) 675 (1) 101.6 1865 1825   805 
Transient (2 sec.)   - 102.6 2200 2090   850 
 
(1) Flat Rated: 
The engines may produce more power than that for which the airplane has been 
certificated.  Under these conditions, the stated torque, ITT, or Ng limitations shall 
not be exceeded. 
(2) If maximum torque is used, propeller r.p.m.  must be set so as not to exceed power 
limitations. 
 
 Propeller and Hartzell composite three-bladed, constant speed, full-feathering, reversible. 
Propeller Limits Model: HC-B3MN3/M10083 
Diameter: Maximum 100 inches, minimum 100 inches, no cutoff approved 
Pitch at 42-inch station: 
Low pitch (Beta pickup) 9° 
Feathered 78.4° 
Maximum Reverse -18° 
 
McCauley aluminum three-bladed, constant speed, full-feathering, reversible. 
NOTE:  All aircraft equipped with TKS anti-ice system must use this prop. 
Model: 3GFR34C703/106GA-0 
Diameter: Maximum 106 inches, minimum 104 inches (2-inch cutoff on diameter 
allowed) 
Pitch at 30-inch station: 
Low pitch (Beta pickup) +15.6° 
Feathered +88° 
Maximum Reverse -14° 
 
 *Airspeed Limits V MO (Max Operating) 175 KIAS 
VA (Maneuvering) at 8750 lb. 148 KIAS 
See POH/AFM for variations with weight and altitude. 
VFE (Flaps extended) 
To 10°  175 KIAS 
10° to 20° 150 KIAS 
20° to 30°  125 KIAS 
 
 C.G. Range  Takeoff and Flight 
(+199.15) to (+204.35) at 8750 lb.  
(+193.37) to (+204.35) at 8000 lb. 
(+179.60) to (+204.35) at 5500 lb. 
Straight line variation between points given 
 
Landing 
(+197.22) to (+204.35) at 8500 lb. 
(+193.37) to (+204.35) at 8000 lb. 
(+179.60) to (+204.35) at 5500 lb. 
Straight line variation between points given 
 
 Empty Wt. C.G. Range None

A37CE 6 Rev. 25  
II. Model 208B, Caravan (cont’d) 
 
 Maximum Weight 8750 lb. takeoff and flight 
8500 lb. landing 
8785 lb. ramp 
 
For Flight into Known Icing: 
 
With PT6A-114 engine and PT6A-114A when operated to PT6A-114 operating limits 
8000 lb. takeoff and flight - cargo pod installed 
8450 lb. takeoff and flight - cargo pod removed 
 
With PT6A-114A (675 hp.) engine 
8550 lb. takeoff and flight - cargo pod installed 
8750 lb. takeoff and flight - cargo pod removed 
 
With PT6A-114A (675 hp.) engine and TKS Anti-ice System installed 
8750 lb. takeoff and flight 
 
 No. of Seats 1 and 2 (at +133.5 to +146.5) Pilot Seat Locations for Cargo and Passenger Versions.   
3 thru 11 refer to POH for passenger seat locations Passenger Version only. 
 
 Maximum Baggage Reference weight and balance data 
 
 Fuel Capacity 335 gal. (332 gal. usable),  two 167.5 gal. tanks in wings at +203.8 
(See NOTE 1 for data on unusable fuel). 
 
 Oil Capacity 3.5 gal. total, 2.37 gal.  usable in engine mounted tank at +69.2 
 
 Maximum Operating 25,000 ft. 
Altitude 20,000 ft. for Flight into Known Icing 
 
 Control Surface Wing flaps 0° +1° Up, 10° +1° -2° Down, 20° +2° Down, 
Movements  30° +1° -2° Down 
LH & RH Flap Extension to be symmetric within 1/2° at all positions 
Main surfaces 
Ailerons Up 25° +4° -0° Down 16° +1° -0°  
Spoiler Up 40° +5° Down   0° +0° -5° 
Elevator Up 25° +2° Down 20° +2° 
Elevator (w/TKS fairing) Up 22° +1° -0 ˚ Down 20° +2° 
Rudder  Right 25° +2° Left 25° +2° 
 (Measured perpendicular to hinge line) 
Tabs (main surfaces in neutral) 
Aileron (RH) Up 15° +2° Down 15° +2° 
Elevator Up 15° +2° Down 15° +2° 
Tabs servo actions 
Aileron (RH): 50% of aileron travel +1° Up and Down 
 (tab adjusted to neutral) 
Aileron (LH):  50% of aileron travel +1° Up and Down  
 
 Serial No. Eligible 208B0001 thru 208B2196 and 208B2198 thru 208B4999

A37CE 7 Rev. 25  
III. Model 208B, Caravan, 2 PCLM or 11 PCLM (Normal Ca tegory), Approved December 21, 2012, for S/N 208B2197 
and 208B5000 and On (This series differs from the basic Model 208B (Item II) by installation of a PT6A-140 engine, 
 increase in gross weight, and other changes)  
 
 Engine Pratt & Whitney of Canada Ltd. , PT6A-140 Turbo Prop, S/N 208B2197 and 208B5000 
and On (867 SHP) 
 
 Fuel Refer to the POH and FAA Approved AFM for approved aviation turbine fuels. 
 
 Engine Limits P&WC PT6A-140: 
  
 
Shaft 
Horsepower 
NG Gas 
Generator 
Speed 
(% rpm) 
 
Indicator 
Torque 
(ft.-lb.) 
 
Prop Shaft 
Speed 
(rpm) 
Maximum 
Permissible 
Interturbine 
Temp. (C) 
Takeoff static & 
  max. continuous 
 
867 (1) 
 
103.7 
 
2397 
 
1900 
 
850 
Maximum climb 867 (1) 103.7 2397 1900 825 
Maximum cruise 867 (1) 103.7 2397 1900 805 
Idle   - 55 min.       -    - 700 
Starting (2 sec.)   -     -       -    - 1090 
Max. reverse (1 min.) 867 (1) 103.7 2500 1825   850 
Transient (20 sec.)   - 105.4 2600    2090 (2)   905 
 
(1) Flat Rated: 
The engines may produce more power than that for which the airplane has been 
certificated.  Under these conditions, the stated torque, ITT, or Ng limitations 
shall not be exceeded. 
(2) 2090 RPM NP may be employed in an emergency condition to complete a flight 
and may be employed at all ratings.  Not limited to 20 seconds. 
 
 Propeller and Hartzell Aluminum three-bladed, constant speed, full-feathering, reversible 
Propeller Limits Model:  HC-B3TN-3AF/T10890CN-2 or HC-B3TN-3AF/T10890CN(B)-2 
Diameter: Maximum 106 inches, minimum 104 inches, no cutoff approved 
Pitch at 42-inch station: 
Low pitch (Beta pickup) 8.5° 
Feathered 78.4° 
Maximum Reverse -21°  
 
 *Airspeed Limits V MO (Max Operating) 175 KIAS 
VA (Maneuvering) at 8807 lb. 148 KIAS 
See POH/AFM for variations with weight and altitude. 
VFE (Flaps extended) 
 UP – TO/APR 150 KIAS 
 TO/APR – LAND   125 KIAS 
 
 C.G. Range  Takeoff and Flight 
(With/without  (+199.15) to (+204.35) at 8807 lb.  
 Cargo pod) (+193.37) to (+204.35) at 8000 lb. 
(+185.00) to (+204.35) at 6500 lb. 
Straight line variation between points given 
 
Landing 
(+197.22) to (+204.35) at 8500 lb. 
(+193.37) to (+204.35) at 8000 lb. 
(+185.00) to (+204.35) at 5500 lb. 
Straight line variation between points given

A37CE 8 Rev. 25  
III. Model 208B, Caravan, S/N 208B2197 and 208B5000 and On (cont’d) 
 
 C.G. Range  Takeoff and flight 
(With TKS Fairing) (+199.15) to (+204.35) at 8750 lb.  
(+193.37) to (+204.35) at 8000 lb. 
(+185.00) to (+204.35) at 5500 lb. 
Straight line variation between points given 
 
Landing 
(+197.22) to (+204.35) at 8500 lb. 
(+193.37) to (+204.35) at 8000 lb. 
(+185.00) to (+204.35) at 5500 lb. 
Straight line variation between points given 
 
 Empty Wt. C.G. Range None 
 
 Maximum Weight 8807 lb. takeoff and flight (with or without cargo pod) 
8750 lb. takeoff and flight (TKS fairing) 
8500 lb. landing 
8842 lb. ramp 
8785 lb. ramp (TKS fairing) 
 
For Flight into Known Icing (w/TKS): 
208B with cargo pod; 8807 lbs. takeoff and flight 
208B with fairing; 8750 lbs. takeoff and flight 
 
 No. of Seats 1 and 2 (at +133.5 to +146.5) Pilot Seat Locations for Cargo and Passenger Versions.   
3 through 11 refer to POH for passenger seat locations Passenger Version only. 
 
 Maximum Baggage Reference weight and balance data 
 
 Fuel Capacity 339.1 gal. (335.3 gal. usable ), two 167.5 gal. tanks in wings at +203.8 
See NOTE 1 for data on unusable fuel. 
 
 Oil Capacity 2.36 gal. total, 0.98 gal. usable in engine mounted tank at +69.2 
 
 Maximum Operating 25,000 ft. 
Altitude 20,000 ft. for Flight into Known Icing 
 
 Control Surface Wing flaps 0° +1° Up, 15°  +1° -2° for TO/APR, 30° +1° -2° Land, 
Movements  
LH & RH Flap Extension to be symmetric within 1/2° at all positions 
Main surfaces 
Ailerons Up 25° +4° -0° Down 16° +1° -0°  
Spoiler Up 40° +5° Down   0° +0° -5° 
Elevator Up 24° +0° -1° Down 20° +2° 
Elevator (w/TKS fairing) Up 22° +1° -0° Down 20° +2° 
Rudder  Right 25° +2° Left 25° +2° 
 (Measured perpendicular to hinge line) 
Tabs (main surfaces in neutral) 
Aileron (RH) Up 15° +2° Down 15° +2° 
Elevator Up 15° +2° Down 15° +2° 
Tabs servo actions 
Aileron (RH):  50% of aileron travel +1° Up and Down 
 (tab adjusted to neutral) 
Aileron (LH):  50% of aileron travel +1° Up and Down  
 
 Serial No. Eligible 208B2197 and 208B5000 and On

A37CE 9 Rev. 25  
 
Data Pertinent to All Models 
 
Datum Landplane:  100.00 in. forward of  center of nose gear jack point. 
Amphibian:  100.00 in. forward of front face of firewall. 
 
Leveling Means Two jig located nutplates  and screws installed on left side of fuselage below side windows and 
 forward of cargo door. 
 
Certification Basis Applies to Models 208 and 208B wh en equipped with PW PT6A-114 engine and Hartzell 
propeller: 
1. FAR Part 36 as amended by Amendments 36-1 through 36-12. 
2. FAR Part 23 as amended by Amendments 23-1 through 23-28. 
3. SFAR 27 as amended by Am endments 27-1 through 27-4. 
4. Equivalent Level of Safety (ELOS) applicable to Models 208 and 208B, not equipped with the 
Garmin G1000 Integrated Cockpit System: FAR 23.955(f)(2), Fuel System. 
5. Special Conditions: 23-AC E-3, Dynamic Evaluation, Engine Installation.   
 
Applies to the following: 
1. Models 208 and 208B when equipped with  P&WC PT6A-114 engine and McCauley 
propeller; and  
2. Model 208B when equipped with P&WC PT6A-114A  engine and either McCauley or Hartzell 
propeller; and  
3. Model 208 when equipped with P&WC PT 6A-114A engine and McCauley propeller: 
a. FAR Part 36 as amended by Amendments 36-1 through 36-18. 
b. FAR Part 23 as amended by Amendments 23-1 through 23-28. 
c. SFAR 27 as amended by Am endments 27-1 through 27-4. 
d. ELOS applicable to Models 208 and 208B, not equipped with the Garmin G1000 
Integrated Cockpit System: FAR 23.955(f)(2), Fuel System. 
e. Special Conditions: 23-ACE-3; Dynamic Evaluation, Engine Installation.   
f. Addition of CFR 23.1459 for FDR and 23.1457 for CVR, Amendment 23-25.   
Effective for S/N 2080356 and On and 208B0932 and On. 
 
Applies to G1000 Model 208B S/N 208B2197, 208B5000 and On equipped with P&WC  
PT6A-140 (867 SHP) engine and Hartzell propeller: 
1. FAR Part 36 (Acoustic s) as amended by Amendments 36-1 through 36-28. 
2. FAR Part 23 as amended by Amendments 23-1 through 23-28 with additions for the Garmin 
G1000 and P&WC PT6A-140 engine. 
3. FAR Part 34 (Emissions) original. 
4. Special Conditions: 23-AC E-3, Dynamic Evaluation, Engine Installation.   
 
Additions for the Garmin G1000 Integrated Cockpit System (ICS) applicable to the following  
Serial Numbers (S/N): 
1. 2080416, 2080500 and On  
2. 208B1190, 208B1216, 208B2000 thru 208B2196, and 208B2198 thru 208B4999  
3. 208B2197 and 208B5000 and On, equipped with P&WC PT6A-140 (867 SHP) Engine.   
 
Original paragraphs amended by 23-1 through 23-28 and addressed during the G1000 certification  
are included (14CFR): 
1. Part 23 as amended by Amendment N/C: 
23.303, 23.305(a)(b), 23.307(a), 23.601, 23.609, 23.671(a), 23.1367, 23.1381. 
2. Part 23 as amended by Amendment 23-7: 23.561(e), 23.611, 23.689(a), 23.867(a)(b). 
3. Part 23 as amended by Amendment 23-13: 23.1589. 
4. Part 23 as amended by Amendment 23-14: 
Electrical aspects of 23.1365(a)(b), 23.1419(b)(c), 23.771(a). 
5. Part 23 as amended by Amendment 23-17: 
23.607, 23.685(a), and electrical aspects of 23.1309(a)(1)(2)(c), 23.1165(b)(c). 
6. Part 23 as amended by Amendment 23-20: 
23.1301, 23.1327, 23.1335, 23.1547(b)(e), electrical aspects of 23.1351(a)(b)(c)(d)(e),  
and electrical aspects of 23.1361(a)(b)(c).

A37CE 10 Rev. 25  
 
Data Pertinent to All Models  
Certification Basis (cont’d) 
 
7. Part 23 as amended by Amendment 23-21:  
23.1501, 23.1541(a)(1)(2)(b)(1)(2), 23.1353(g). 
8. Part 23 as amended by Amendm ent 23-23: 23.603(a)(b), 23.605. 
9. Part 23 as amended by Amendment 23-26: 23.1529. 
10. Part 23 as amended by Am endment 23-28: 23.301(a)(d). 
11. Part 23 as amended by Amendment 23-34: 
23.853(e), 23.1523, 23.1581(a)(b)(d), 23.1583(a)(1)(b)(h), 23.1585(a).  
12. Part 23 as amended by Ame ndment 23-35: 23.1459, 23.1457. 
13. Part 23 as amended by Amendment 23-43:   
23.1322, 23.1331, and 23.1357(a)(b)(c)(d)(e).  
14. Part 23 as amended by Amendment 23- 45: 23.773(a)(1)(2), 23.1525, 23.1549. 
15. Part 23 as amended by Amendment 23-49: 
23.677(d), 23.1303(a)(b)(c)(d)(e)(1)(f), avionic aspects of 23.1309(a)(1)(2)(b)(1)(2)(3)(4)  
(c)(1)(2)(iii)(3)(d)(e)(f)(1), 23.1311, 23.1321(a)(c)(d)(e), 23.1323(a)(b)(1)(2)(c), 23.1329,  
23.1351(c)(4)(d)(1), 23.1361(c), 23.1365(a)(b)(d)(e), 23.1431(a)(b)(d)(e).  
16. Part 23 as amended by Amendment 23-50: 
23.1325(a)(b)(1)(i)(ii)(iii)(b)(2)(i)(3)(c)(1)(2)(d)(e), 23.1543(b)(c), 23.1553, 
23.1545(a)(b)(4)(d), 23.1555(a)(b), 23.1567(a). 
17. Part 23 as amended by Amendment 23-51: 
23.777(a)(b), 23.955(a)(1)(2)(f), 23.959, 23.1337(a)(1)(2)(b)(1)(4)(c)(d), 23.1183,  
23.1203(b)(c)(d)(e). 
18. Part 23 as amended by Amendment 23-52: 23.1305(a)(1)(2)(3)(5)(c)(1-10)(e) 
19. Part 23 as amended by Amendment 23-53: 23.901(a)(b) 
20. Part 23 as amended by Amendment 23-57: 23.1308  
 
Additions for Model 208B equipped with Garmin G1000 and P&WC PT6A-140 Engine (14CFR): 
1. Part 23 as amended by Amendment 23-51: 23 .955(a)(4)(b), 23.1203(a)(1), 23.1337(a)(3). 
2. Part 23 as amended by Amendment 23-52: 23.1305(a)(4) 
 
Additions for new or changed lithium battery installations: 
1. 14 CFR Part 23 as amended by Amendment 23-64 (see NOTE 9): 
23.2000, 23.2005, 23.2010, 23.2325(g), 23.2510 
 
Additions for new or changed installations affecting aeronautical security (cybersecurity): 
1. 14 CFR Part 23 as amended by Amendment 23-64 (see NOTE 9): 
23.2000, 23.2005, 23.2010, 23.2500, 23.2505, 23.2510 
 
ELOS: 
1. Applicable to Model 208 and 208B equipp ed with the Garmin G1000 Integrated Cockpit 
System: 
a. 23.1305(c)(2)(5), Amendment 52; Powerplant instruments. 
b. 23.1549(a)(b)(c), Amendment 45; Powerplant  and auxiliary power unit instruments.  
Additionally, with guidance from AC 23.1311-1B, Installation of Electronic Display 
(Section 9 – Powerplant Displays), Section 9.4 Direct-Reading Alphanumeric-Only 
Displays. 
2. Applicable to Model 208 with Garmin G 1000 and Model 208B with or without Garmin G1000 
and equipped with the optional TKS ice protection system: 23.207(c) Amendment 7; Stall 
Warning. 
3. Applicable to Model 208B equipped with P&WC PT6A-140 Engine: 23.145, Amendment 17; 
Longitudinal Control. 
 
Compliance with ice protection has been demonstrated in accordance with 23.1419 when ice 
protection equipment is installed in accordance with the airplane equipment list and is operated per 
the POH and FAA Approved AFM.  
 
Application for type certificate dated June 2, 1982.  Type Certificate No. A37CE issued October 
23, 1984, obtained by the manufacturer under delegation option provisions of FAR Part 21.

A37CE 11 Rev. 25  
 
Data Pertinent to All Models  
 
Production Basis Production Certificate No. 4. 
Delegation Option Manufacturer No. CE-1 (2080001 through 20800246, 208B0001 through 
208B0501) and CE-3 (20800247 and On, 208B0502 and On, *except the S/N listed below), 
authorized to issue airworthiness certificates under delegation option provisions of FAR Part 21. 
 
*S/N 208B5230, 208B5247, 208B5267 and 208B5270 were manufactured under Type Certificate 
A37CE and authorized to issue airworthiness certificate after the FAA inspection and flight test 
with the provision of 14 CFR 21.183(b). 
 
Equipment  The basic required equipment as prescribed in the applicable airworthiness regulations (see 
Certification Basis) must be installed in the aircraft for certification.  This equipment must include 
a current POH and FAA Approved AFM. 
 
NOTE 1. Current weight and ba lance report including list of equipment included in certificated empty weight and 
loading instructions, when necessary, must be provided for each aircraft at the time of original certification. 
Verify from aircraft records whether SK 208-52 “Wing Take External Sump Installation” has been installed.  
The certified empty weight and corresponding center of gravity location must include full oil of 29 lbs. (at 
+69.2), and unusable fuel as follows: 
 
Model Serial Effectivity Modification Unusable Fuels lb.    @     c. g. 
208 20800001 through 20800130  NOT modified with SK208-52 20.1  @  +185.7 
208 20800001 through 20800130  modified with SK208-52 24.1  @   +186.4 
208 20800131 and On 24.1  @   +186.4 
208B 208B0001 through 208B0089  NOT modified with SK208-52 20.1  @   +205.7 
208B 208B0001 through 208B0089  modified with SK208-52 24.1  @   +206.4 
208B 20800090 and On 24.1  @   +206.4 
 
 
NOTE 2. Airplanes must be operated according to the FAA Approved AFM Part Number as listed in the table below 
(or later FAA approved revision). All placards required by either the AFM, the applicable operating rules, or 
the certification basis, must be installed as specified for this Type Certificate via Parts List xxxxxxx, 
Airplane Assembly. A useful placarding reference is the Textron Aviation Illustrated Parts Catalogue (IPC). 
Any discrepancies identified between the IPC and an aircraft under inspection need to be reconciled using 
the previously stated parts list.

A37CE 12 Rev. 25  
NOTE 2 (cont’d): 
 
Model Cessna AFM/POH  Part Numbers Airplane Assembly  
208 [600 SHP] 
(00001 – 00276) 
00001 – 00060 modified by SK208-12 or SK208-85 
D1307-34-13PH* 2600000 
 
208 [675 SHP] 
20800277 – 20800415, 20800417 - 20800499 D1352-7-13PH* 2600000  
208 [675 SHP] 
20800416, 20800500 – On 208PHBUS-04** 2600000  
208B [600 SHP] 
208B0001 – 208B0178 and 
208B0180 – 208B0229 not modified by SK208-80 
208B0179, 208B0230 and On modified by SK208-84 
D1309-29-13PH* 2600000 
 
208B [675 SHP] 
208B0179, 208B0230 and On and 
208B0001 - 208B0178 and 
208B0180 - 208B0229 modified by SK208-80 
D1329-23-13PH* 2600000 
 
208B [675 SHP] 
208B01190, 208B01216, 208B02000 and On 208BPHBUS-02** 2600000  
208B [867 SHP] 
208B2197, 2085000 and On 208BPHDUS-03** 2600867  
208B [867 SHP] 
208B2197, 2085000 and On 208BPHCUS-03** 2600867  
 
Model 208 airplanes modified in accordance with SK-208-12 should use Cessna P/N D1307-34-13PH (or 
later FAA Approved revision). 
 
*The revision level is incorporated into the number (e.g. D1307-XX-13PH where XX is the revision level) 
**The revision level is incorporated into the number (e.g. 208PHBUS-XX where XX is the revision level) 
 
NOTE 3. Airplanes S/N 20800001 thru 20800060 are eligible for operation at the same weight and C.G. as approved 
for S/N 20800061 and On when modified in accordance with SK-208-12 or SK-208-85A “208A to 208 
Caravan I Cargo Configuration Conversion”. 
 
NOTE 4. Mandatory inspection times for all wings and wing carry-through structural components are contained in the 
Model 208 Series Maintenance Manual. 
 
NOTE 5. In addition to the placards required by NOTE 2 above, the prescribed operating limitations indicated by an 
asterisk (*) must also be displayed as permanent markings. 
 
NOTE 6. Special Ferry Flight Authorization.  Flight Standards District Offices (FSDO) are authorized to issue special 
overweight ferry flight authorizations.  These airplanes are structurally satisfactory for ferry flights if 
maintained within the following limits:  
1. Takeoff weight must not exceed  the maximum certified takeoff weight multiplied by a gross weight 
increase factor up to 1.3 (e.g. 8,000 x 1.3 = 10,400 lb.).  
2. The Maximum Operating Airspeed (V MO) must be divided by the same gross weight increase factor 
(e.g. VMO = 175 ÷ 1.3 = 135 KIAS).   
3. Forward and aft center of gravity limits may not be exceeded. 
4. Structural load factors of +2.5 g. to -1.0 g. may not be exceeded.   
This determination is based upon the production configuration of the airplane and does not account for 
modifications, such as STCs, that may have affected the gross weight of the airplane.  The excess weight 
authorized is limited to the additional fuel, fuel-carrying tanks, and navigational equipment necessary for the 
flight.  Requirements for any additional engine oil should be established in accordance with Advisory 
Circular AC 23-16A.  Increased stall speeds and reduced climb performances should be expected for the 
increased weights.  Flight characteristics and performance at the increase weights have not been evaluated.  
Procedures for issuing a Flight Permit for operations of overweight aircraft may be found in Advisory 
Circular AC 21-4.

A37CE 13 Rev. 25  
 
NOTE 7. The following S/N are manufactured under the name Cessna Aircraft Company:  
Model 208: 20800001 thru 20800572  
Model 208B: 208B0001 thru 208B5208 and 208B5210 thru 208B5223. 
 
NOTE 8. Company name change, effec tive 7/29/2015. The following S/N are manufactured under the name Textron 
Aviation Inc.:  
Model 208: 20800573 and On  
Model 208B: 208B5209, 208B5224 and On. 
 
NOTE 9. 14 CFR 23.2005 Certific ation and Performance Level: 
1. Model 208B:  Cargo Vers ion Level 1, Low Speed 
2. Models 208, 208B: Passenger Version Level 3, Low Speed 
 
The Detailed Design Standard (DDS) Means of Compliance for 23.2325(g), 23.2500, 23.2505, 23.2510, 
as amended through Amendment 23-64: 
1. 23.2325(g): CPP 23.2525-2 (signed 5/24/2023) 
2. 23.2500:  ASTM F3532-22 
3. 23.2505:  ASTM F3532-22 
4. 23.2510:  CPP 23.2525-1 (signed 4/17/2023)  
CPP 23.2525-2 (signed 5/24/2023)  
ASTM F3061-20, F3309-20, F3532-22 
 
NOTE 10. Required Equipment.  The basic required equipment prescribed in the applicable airworthiness requirements 
(see certification basis) must be installed in the aircraft.  Only handheld fire extinguishers containing Halon 
1211 (BCF, CBrC1F2), Halotron I (HCFC Blend-B, C2HC12F3) OR Halotron BrX (2-BTP, C3H2BrF3) are 
approved for use.  No airplanes may have any combination of dissimilar agents installed on a particular unit. 
 
 
------------ END ------------
```

## ADs (31, in force first)

- [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 2021-04-10](https://openairdocs.org/ad/2021-04-10): Elevator Structure · Textron 208 and 208B. Effective Apr 12, 2021
- [AD 2009-15-05](https://openairdocs.org/ad/2009-15-05): Yaw bridle cable tension · Cessna 208 and 208B. Effective Jul 27, 2009
- [AD 2009-05-12](https://openairdocs.org/ad/2009-05-12): Aileron control system · Cessna 208 and 208B. Effective Apr 15, 2009
- [AD 2008-26-10](https://openairdocs.org/ad/2008-26-10): Alternate static air source selector valve · Cessna 172, 172A, 172B and 179 more. Effective Jan 5, 2009
- [AD 2008-13-06](https://openairdocs.org/ad/2008-13-06): Right wing wire bundles · Cessna 208 and 208B. Effective Jul 30, 2008
- [AD 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008
- [AD 2008-10-02](https://openairdocs.org/ad/2008-10-02): Part number identification placard · Cessna 172, 172R, 172RG and 64 more. Effective May 12, 2008
- [AD 2007-10-15](https://openairdocs.org/ad/2007-10-15): S1 Known Icing Equipment AFM supplements · Cessna 208 and 208B. Effective Jun 21, 2007
- [AD 2006-01-11 R1](https://openairdocs.org/ad/2006-01-11-R1): Cargo pod and landing gear fairings · Cessna 208 and 208B. Effective Feb 22, 2006
- [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 2006
- [AD 2004-25-16 R1](https://openairdocs.org/ad/2004-25-16-R1): Fuel regulator shutoff valve · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 64 more. Effective Jun 20, 2005
- [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005
- [AD 2004-21-05](https://openairdocs.org/ad/2004-21-05): B-Seires Combustion Heaters · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 41 more. Effective Nov 19, 2004
- [AD 2004-17-01](https://openairdocs.org/ad/2004-17-01): Flap bellcranks · Cessna 208 and 208B. Effective Sep 26, 2004
- [AD 2004-08-17](https://openairdocs.org/ad/2004-08-17): Upper and Lower Wing Strut Attach Fitting Nut · Cessna 208 and 208B. Effective May 17, 2004
- [AD 2001-23-17](https://openairdocs.org/ad/2001-23-17): GNS 430 units · Cessna 172, 182, 206 and 209 more. Effective Dec 28, 2001
- [AD 2001-10-09](https://openairdocs.org/ad/2001-10-09): Automatic Flight Control Systems · Aerostar PA-60-700P (Aerostar 700P), 208, 208B and 15 more. Effective Jun 15, 2001
- [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998
- [AD 97-25-04](https://openairdocs.org/ad/97-25-04): Airplane Flight Manual (AFM) - Limitations - Power Levers · Cessna 208, 208A, 208B and 2 more. Effective Jan 21, 1998
- [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997
- [AD 96-09-15](https://openairdocs.org/ad/96-09-15): Airplane Flight Manual - Icing Conditions · Cessna 208 and 208B. Effective Jun 11, 1996
- [AD 90-05-04](https://openairdocs.org/ad/90-05-04): Engine Mount Ring · Cessna 208, 208A and 208B. Effective Mar 23, 1990
- [AD 90-05-01](https://openairdocs.org/ad/90-05-01): Bellcrank Assembly · Cessna 208, 208A and 208B. Effective Mar 5, 1990
- [AD 88-19-06](https://openairdocs.org/ad/88-19-06): Elevators · Cessna 208B. Effective Sep 30, 1988
- [AD 86-22-06](https://openairdocs.org/ad/86-22-06): Wing Fuel Tank Selectors · Cessna 208 and 208A. Effective Nov 7, 1986
- [AD 2006-06-06](https://openairdocs.org/ad/2006-06-06) (historical): Airplane Flight Manual (AFM) · Cessna Aircraft Company, The 208 and 208B. Effective Mar 24, 2006
- [AD 2006-01-11](https://openairdocs.org/ad/2006-01-11) (historical): Pilot assist handle and deicing boots on the cargo pod · Cessna Aircraft Company, The 208 and 208B. Effective Feb 22, 2006
- [AD 2005-07-01](https://openairdocs.org/ad/2005-07-01) (historical): Airplane Flight Manual (AFM) · Cessna Aircraft Company, The 208 and 208B. Effective Mar 29, 2005
- [AD 2003-21-04](https://openairdocs.org/ad/2003-21-04) (historical): Right inboard forward flap bell crank · Cessna 208 and 208B. Effective Oct 21, 2003
- [AD 2002-22-17](https://openairdocs.org/ad/2002-22-17) (historical): Inboard forward flap bellcranks · Cessna 208 and 208B. Effective Dec 31, 2002

## Registered aircraft by registry model (OpenAirDocs)

- [Cessna 208B](https://openairdocs.org/model/cessna-208b): 645 aircraft (registry codes 2073701, 2073700, 2073705)
- [Textron 208B](https://openairdocs.org/model/textron-208b): 211 aircraft (registry code 2073712)
- [Cessna 208](https://openairdocs.org/model/cessna-208): 118 aircraft (registry code 2073702)
- [Textron 208](https://openairdocs.org/model/textron-208): 44 aircraft (registry code 207371A)
- [Cessna 208A](https://openairdocs.org/model/cessna-208a): 1 aircraft (registry code 2073703)

## STCs approved under this data sheet (333, first 50)

- [STC SA12517WI](https://openairdocs.org/stc/SA12517WI): Installation of a Single Point Pressure Refueling System. AO Aviation LLC
- [STC SA12388AK](https://openairdocs.org/stc/SA12388AK): Removal of engine fire detection system. Randigo LLC
- [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of  existing instrument panel lights dimmer control.. TCW Technologies, LLC
- [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC
- [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc.
- [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies
- [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC
- [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA02741SE](https://openairdocs.org/stc/SA02741SE): Installation of Raisbeck Engineering Drag Reduction System. Raisbeck Engineering Inc.
- [STC SA01975WI](https://openairdocs.org/stc/SA01975WI): Installation of Fuselage Camera Ports with or without Mission Power System. Avcon Industries Inc.
- [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA8954SW](https://openairdocs.org/stc/SA8954SW): Installation of Hartzell HC-B3TN-3Z/ T10282N(K)+4 or HC-B3TN-3Z/ T10282N+4 propeller.. John Wentzell Downs Jr.
- [STC SA11158SC](https://openairdocs.org/stc/SA11158SC): Demonstration of aircraft tolerance to potential electromagnetic interference from certain Transmitting Potable Electronic Devices (T-PEDS). Liberty Partners Inc.
- [STC SA02812SE](https://openairdocs.org/stc/SA02812SE): Installation of Starlink Aviation System. AeroMech Incorporated
- [STC SA04804NY](https://openairdocs.org/stc/SA04804NY): Installation of Avionics. Delta Engineering Corporation
- [STC SA12011DE](https://openairdocs.org/stc/SA12011DE): Installation of Mission Equipment, including consoles and turret mounts. Southeast Aerospace
- [STC SA09625AC](https://openairdocs.org/stc/SA09625AC): Installation of Dual Camera Ports and Navigation Sight Ports.. Metrea Special Aerospace ISR Inc.
- [STC SA01516WI](https://openairdocs.org/stc/SA01516WI): Installation of the L-3 Communications Avionics Systems Infrared Imaging System (IRIS). Acron Aviation Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA11933IB](https://openairdocs.org/stc/SA11933IB): Manufacturing and Installation of the Camera Mount. Icarus Aero Inc.
- [STC SA00892WI](https://openairdocs.org/stc/SA00892WI): TKS Ice Protection System Installation approving aircraft for flight into known icing conditions. CAV Ice Protection Limited
- [STC SA02549SE](https://openairdocs.org/stc/SA02549SE): Installation of new structural components in certain fuselage bulkheads. Metal Innovations Inc. dba MII Aero
- [STC SA02763SE](https://openairdocs.org/stc/SA02763SE): Installation of Metal Innovations Inc. C-208B Cargo Pod Alteration. Metal Innovations Inc. dba MII Aero
- [STC SA01657CH](https://openairdocs.org/stc/SA01657CH): Installation of Honeywell Bendix/King KGP 560 Enhanced Ground Proximity Warning System, KMD 850 Multi-Function Display, and KLN 94 GPS Navigator.. Amphenol Cable and Interconnect Technologies Inc.
- [STC SA04746NY](https://openairdocs.org/stc/SA04746NY): Installation of Outlook Aero LLC ISR Payload Mount System. Outlook Aero LLC
- [STC SA01330LA](https://openairdocs.org/stc/SA01330LA): Installation of alternate avionics support assembly.. Radiorax Aviation Systems LLC
- [STC SA04744NY](https://openairdocs.org/stc/SA04744NY): Installation of New External Radar Pod with Retractable EO/IR Sensor Lift Mechanism. AVCON Industries Inc.
- [STC SA04741NY](https://openairdocs.org/stc/SA04741NY): Installation of a Soot Shield. Raisbeck Engineering Inc.
- [STC SA01871NY](https://openairdocs.org/stc/SA01871NY): Installation of Hawker Sealed Lead-Acid Battery.. Securaplane Technologies Inc.
- [STC SA04648CH](https://openairdocs.org/stc/SA04648CH): Installation of a Universal Adapter Plate (UAP) and Radome for Electronically Steered Antenna (ESA). StandardAero Business Aviation Services LLC
- [STC SA39CH](https://openairdocs.org/stc/SA39CH): Installation of an Amphibian Landing Gear Position Advisory System/Laser Gear Advisory System. Wipaire Inc.
- [STC SA09948AC](https://openairdocs.org/stc/SA09948AC): Incorporation of engine indications, fuel quantity indications, and electrical system indications into the display units
of the Garmin G600 TXi system. Xtreme Avonics LLC.
- [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC
- [STC SA00301BO](https://openairdocs.org/stc/SA00301BO): Installation of Light Emitting Diode (LED) based Position, Anticollision, Taxi, and Landing Light Systems with Single Mode (visible) or Dual Mode (visible plus infrared) options. ATI Engineering Services LLC
- [STC SA00341BO](https://openairdocs.org/stc/SA00341BO): Installation of an NVIS / NVG Compatible Lighting System. ATI Engineering Services LLC
- [STC SA00419BO](https://openairdocs.org/stc/SA00419BO): Installation of an Airborne Operator Workstation. ATI Engineering Services LLC
- [STC SA00421BO](https://openairdocs.org/stc/SA00421BO): Installation of Interior Sidewall Blanket. ATI Engineering Services LLC
- [STC SA04646CH](https://openairdocs.org/stc/SA04646CH): Installation of Hartzell Model HC-E4N-3KTV( )/GC11114( )-2 propeller. Wipaire Inc.
- [STC SA04639CH](https://openairdocs.org/stc/SA04639CH): Incorporation of an Avcon External Belly Mounted Radar Pod in accordance with FAA approved Master 
Data List 07801000 Revision (IR), dated 06/26/2024, or later FAA or ODA Approved Revision.. AVCON INDUSTRIES INC
- [STC SA00236MC](https://openairdocs.org/stc/SA00236MC): Operational Approval of an L3Harris WESCAM MX-15DR Sensor System. ATI Engineering Services LLC
- [STC SA00199MC](https://openairdocs.org/stc/SA00199MC): Installation of an L3 Harris (Harris Global Communications, Inc.) tactical radio system consisting of an RF-7800H-MP radio, an RF-7850A-MR radio, an RF-7850A/7800H radio control unit (RCU), and associated antennas. ATI Engineering Services LLC
- [STC SA7687SW](https://openairdocs.org/stc/SA7687SW): Modification of the lower fuselage skin to include provisions for a scanner or camera and navigation sight port. Randingo LLC
- [STC SA03817NY](https://openairdocs.org/stc/SA03817NY): Installation of the Parachute Kit. airplus engineering GmbH
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02917NY-D](https://openairdocs.org/stc/SA02917NY-D): Installation of Camera Ports. MAG Aerospace
- [STC SA01105DE](https://openairdocs.org/stc/SA01105DE): Installation of the Persistent Systems MPU5 Wave Radio System. Persistent Systems
- [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc.
- [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc.
- [STC SA02027WI](https://openairdocs.org/stc/SA02027WI): Installation of Garmin GI 275 Indicator. Yingling Aviation Inc.

All 333: https://openairdocs.org/tcds/A37CE/stcs.md

---
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