# TCDS A43EU: Airbus Defense and Space S.A.

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Defense and Space S.A.
- Revision: 12
- Revised: July 23, 2021
- Product: Aircraft, Large Airplane
- Certification basis: Part 25, Part 36, Part 25, Part 36, Part 25, Part 36, Part 25, Part 36, Part 25, Part 36, Part 25, Part 36, Part 25, Part 36
- Registered aircraft: 18, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/1a/1b/1a1b1f0ba29049e77e43a299882a8d4cb9096b39af6c238867ccdd049179ce7e
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DF17CB5C3D339EAB8625871B005C6A75.0001
- Page: https://openairdocs.org/tcds/A43EU

## Models (7)

As the data sheet lists them.

- C-212-DE
- C-212-CB
- C-212-CE
- C-212-CC
- C-212-CF
- C-212-DF
- C-212-CD

## 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 16 17 
Rev. No. 11 8 8 8 8 8 8 8 8 8 8 8 8 8 12 9 8 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A43EU 
Revision  12 
Airbus Defense and 
Space S.A. 
Model:     C-212-CB 
C-212-CC 
C-212-CD 
C-212-CE 
C-212-CF 
C-212-DF 
C-212-DE 
July 23, 2021 
 
TYPE CERTIFICATE DATA SHEET NO. A43EU 
 
This data sheet, which is a part of  Type Certificate No. A43EU, 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 Airbus Defense and Space S.A. 
 (formerly known as Construcciones Aeronauticas, S.A.) 
 Apartado 193 
 Madrid, Spain 
 
I  - Model C-212-CB (Transport Category Airplane) approved February 22,  1977 
 
Engines 2- Garrett Turbine Engine Co. Model TPE331-5-251C Turboprop engines. 
 
Fuel Prop.  Shaft/Eng. Rotor Ratio:   1/26.2287.  
 
 See Airplane Flight Manual for approved fuels, alternate fuels and approved fuel 
 additives. 
 
Oil Oils conforming to Garrett Turbine Engine Co.  Specification EMS 53110 (Type I and 
 Type II).  See approved AFM for a list of approved engine lubricating oils. 
  
Engine Limits 
Conditions SHP ESHP RPM (%) ITT (°C) 
Takeoff (5 minutes) 750 808 100 923 
Max. Continuous 715 776 100 923 
  
 Transient temperature (ITT) limit (1 sec.)  1149°C. 
 Transient overspeed limits:     105.5% for 30 sec.;  106% for 5 sec. 
 100% RPM is defined as 41,730 engine rotor speed, 1591 propeller shaft speed.  
  
 See INTA-approved Airplane Flight Manual, Document D.T. 76-2501, for additional 
 information. 
 
Propeller and Propeller Limits 2 Hartzell Model HC-B4TN-5CL, constant speed hydraulic full feathering reversible  
 propellers. 
 Blades: 4, Model LT 10282 HB + 4 
 Diameter: 107.5 in. 
 
 Hard and soft alloy blades of the same model designation may not be intermixed. 
 For % R. P.M. at windmilling see INTA-approved Airplane Flight Manual  
 Document D.T. 76-2501.

A 43EU 2 
I  - Model C-212-CB   (cont’d) 
 Blade angle measured at 30-in. radius station: 
 Feathered 89.0°  ±  1.0° 
 Flight Idle 13.5°  ±  0.2° 
 Start Locks   2.5°   +  0° 
              -  0.5° 
 Full Reverse -6.5°   ±  0.5° 
 
   Speed Knots IAS 
Airspeed Limits VMO  (Max. Operating) (S.L.  -25000 ft)  200 
 VA    (Maneuvering)   146 
 VFE   (Flaps Extended) Takeoff 25%  125 
  Approach 50%  120 
  Landing 100%  100 
 VMC  (Min. control speed)      78 
C.G. Range 
Weight   
(lb) 
FWD 
%  MAC 
AFT 
%  MAC 
   
14332 17.4 30.0 
13781 16.9 30.0 
12678 16.0 30.0 
 
 Straight line variation between points given. 
 
Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of  
 the fuselage.  The C.G. reference datum is situated 43.90 in. forward of the jig point. 
 
M.A.C. Length is 86.22 in. 
 The leading edge of M.A.C. is 215.04 in. aft of datum. 
 
Leveling Means Plumb-bob provision on aft face of aft cockpit compartment bulkhead. 
 
Maximum Weights Takeoff: 14332 lb. 
 Landing: 13781 lb. 
 MZFW: 13230 lb. 
 
Minimum Crew The minimum flight crew is two pilots. 
  
Maximum Passengers 19 - limited by Emergency Exit Requirements of FAR 25.807 (c) 
 
Maximum Baggage Aft baggage comp:  662 lb. total - maximum floor loading:  120 lb/sq. ft 
     470 lb/linear ft. 
 
 Baggage and/or cargo load must comply with loading limitations of approved Airplane  
 Flight Manual, and must be loaded in accordance with loading instructions of Weight  
 and Balance Supplement to the INTA-approved Airplane Flight Manual. 
 
Fuel Capacity Total Capacity: 548.00 U.S. gal. in two wing tanks 
 Usable fuel: 528.00 U.S. gal. 
 Unusable fuel:   20.00 U.S. gal. 
 
 (See NOTE I (b) and I (c) for data on system fuel and oil) 
Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank 
 Unusable oil: (NONE) 
 
Maximum Approved Operating 
Altitude 25,000 ft.

A43EU 3 
I  - Model C-212-CB   (cont’d) 
Control Surface Movement Elevator 30° Up 20° Down 
 Elevator trim tab 15.5° Up 21° Down 
 Rudder 25° Right 25° Left 
 Rudder trim tab 17.5° Right 19° Left 
 Aileron 20° Up 20° Down 
 Aileron trim tab 15° Up 15°  Down 
 Flaps, Inner and Outer 10° Down - takeoff 
  20° Down - approach 
  40° Down - landing 
 
 All measurements taken at trailing edge from neutral position.  For details of tolerance 
 on control surface movement refer to document D.T. 77.2101. 
 
II.  Model C-212-CC  (Transport Category Airplane) approved May 16,  1980 
 
The C-212-CC Model is similar to the C-212-CB Model except for powerplant installation, gross weight and seating capacity. 
 
Engines 2 - Garrett Turbine Engine Co. Model TPE331-10-501C or TPE331-10R -501C 
 Turboprop engines, or 2 - Model TPE331-10-511c or TPE311-10R -511C Turboprop 
 engine. 
 
 Prop. Shaft/Eng. Rotor Ratio:   1/26.2287 
 
Fuel  See AFM for approved fuels, alternate fuels and approved fuel additives. 
  
Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and  
 Type II).  See approved AFM for a list of approved engine lubricating oils. 
 
Engine Limits  
Conditions SHP ESH
P 
% 
RPM 
EGT 
(°C) 
Takeoff (initial) (5 minutes) 900 944 100 650 
Takeoff (APR on) (5 minutes) 900 944 100 650 
Max. Continuous 900 944 100 650 
 
 Transient overspeed limits:   105.5% for 30 sec.;  106% for 5 sec. 
 100% RPM is defined as 41,730 rpm engine rotor speed, 1591 rpm propeller shaft speed.  
 Transient temperature (EGT) limit (1 sec.):   770°C 
 See INTA-approved Airplane Flight Manual, Document D.T. 78-2501, for additional 
 information. 
 
Propeller and Propeller Limits 2 Hartzell Model HC-B4MN-5AL, constant speed hydraulic full feathering, reversible  
 propellers. 
  
 Blades: 4, Model LM 10585 B + 4 
 Diameter: 110 in. 
 
 For %RPM as windmilling see INTA-approved Airplane Flight Manual, Document D.T. 
 78-2501. 
 
 Blade angle measured at 42- in. radius station: 
 Feathered 83.0°  ±  1.0° 
 Flight Idle   7.0°  ±  0.3° 
 Start Locks  -1.5°  ±  0.2°   
 Full Reverse -10°    ±  0.5°

A 43EU 4 
II.  Model C-212-CC    (cont’d) 
   Speed Knots IAS 
Airspeed Limits VMO   (Max. Operating) (S.L.  -25.000 ft)  200 
 VA     (Maneuvering)   146 
 VFE    (Flaps extended) Takeoff 25%  135 
  Approach 37.5%  130 
  Landing 100%  115 
 VMC   (Min. Control)     85 
 
C.G. Range  
Weight 
    (lb) 
     FWD 
%  MAC 
   AFT 
% MAC 
16,976     16.00    30.00 
16,424     15.90    30.00 
11,051     15.00    30.00 
  9,481     15.00    30.00 
 
 Straight line variation between points given. 
 
Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of  
 the fuselage.  The C.G. reference datum is situated 43.90 in. forward of the jig point. 
 
M.A.C. Length is 86.22 in. 
 
 The leading edge of M.A.C. is 215.04 in. aft of datum. 
 
Leveling Means Plumb-bob provisions on aft fact of aft cockpit compartment bulkhead. 
 
Maximum Weights Ramp: 17,086 lb. 
 Takeoff: 16,976 lb. 
 Landing: 16,424 lb. 
 MZFW: 15,653 lb. 
 
Minimum Crew The minimum flight crew is two pilots 
 
Maximum Baggage Aft baggage comp.:  882 lb. Total - maximum floor loading: 120 lb/sq. ft. 
   470 lb/linear ft. 
 
 Baggage and/or cargo load must comply with loading limitations of approved Airplane  
 Flight Manual, and must be loaded in accordance with loading instructions of Weight  
 and Balance Supplement to the INTA-approved Airplane Flight Manual. 
 
Fuel Capacity Total capacity: 548.00 U.S. gal. in two wing tanks 
 Usable fuel: 528.00 U.S. gal. 
 Unusable fuel:   20.00 U.S. gal. 
 
 (See NOTES 1 (b) and  1 (c) for data on system fuel and oil). 
 
Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank 
 Unusable oil: (NONE) 
 
Maximum Approved Operating 
Altitude 25,000 ft.

A43EU 5 
II.  Model C-212-CC    (cont’d) 
Control Surface Movements Elevator 30° Up 20° Down 
 Elevator Trim Tab 15.5° Up 21° Down 
 Rudder 27.5° Right 27.5° Left 
 Ruddeer Trim Tab 12.5° Right 19° Left 
 Aileron   20°      Up 15°      Down 
       Aileron Trim Tab 15° Up 15° Down 
 Flaps, Inner and Outer 10° Down - Takeoff 
  15° Down - Approach 
  40° Down - Landing 
 
 All measurements taken at trailing edge from neutral position.  For details of tolerances      
  on control surface movement refer to document D.T. 77-2101. 
 
Maximum Passengers 28 - limited by space available for accommodation. 
 
III.   Model  C-212-CD  (Transport Category Airplane)  approved September 6, 1985 
 
The C-212-CD model is similar to the C-212-CC Model except for powerplant installation. 
 
Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-502C or TPE331-10R-512C 
(See NOTES 5 & 6) Turboprop engines. 
  
 Prop. Shaft/Eng. Rotor Ratio:   1/26.2287 
 
Fuel See AFM for approved fuels, alternate fuels and approved fuel additives. 
 
Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and  
 Type II).  See approved AFM for a list of approved engine lubricating oils. 
 
Engine Limits  
Conditions SHP ESHP %  RPM EGT (°C) 
Takeoff (initial) (5 minutes) 900 944 100 650 
Takeoff (APR on) (5 
minutes) 
900 944 100 650 
Max. Continuous 900 944 100 650 
 
 Transient overspeed limits:   105.5% for 30 sec.;  106% for 5 sec. 
 100% RPM is defined as 41.730 rpm engine rotor speed, 1591 rpm propeller shaft speed.  
 Transient temperature (EGT) limit (1 sec.):   770°C. 
 
 See INTA-approved Airplane Flight Manual, Document D.T. 83-2501, for additional 
 information. 
 
Propeller and Propeller Limits 2 Dowty Rotol Model (c) R.334/4-82-F/13 hydraulic full feathering, constant speed  
 reversible propellers. 
  
 Blades: 4, serial number 660709314 
 Diameter: 110 in. 
 
 For % RPM at windmilling see INTA-approved Airplane Flight Manual, Document D.T. 
 83-2501. 
 
 Blade angle measured at 35.333 in radius station: 
 
 Feathered 82°30’  ±   20’ 
 Flight Idle   9°       ±   20’ 
 Start Locks -1°45’  ±   0°30’ 
 Full Reverse -13°     ±   1°

A 43EU 6 
III.   Model  C-212-CD   (cont’d)   Speed Knots IAS 
Airspeed Limits VMO   (Max. Operating) (S.L.  -25,000 ft.)  200 
 VA     (Maneuvering)   146 
 VFE    (Flaps Extended) Takeoff 25%  135 
  Approach 37.5%  130 
  Landing 100%  115 
VMC   (Min. Control)     85 
C.G. Range  
Weight 
    (lb) 
FWD 
%  MAC 
 AFT 
%  MAC 
16,976 16.0 30.0 
16,424 15.9 30.0 
11,051 15.0 30.0 
  9,481 15.0 30.0 
 Straight line variation between points given. 
 
Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of  
 the fuselage.  The C.G. reference datum is situated 43.90 in. forward of the jig point. 
 
M.A.C. Length is 86.22 in. 
 The leading edge of M.A.C. is 215.04 in. aft of datum. 
 
Leveling Means Plumb-bob provisions on aft face cockpit compartment bulkhead. 
 
Maximum Weights Ramp: 17,086 lb. 
 Takeoff: 16,976 lb. 
 Landing: 16,424 lb. 
 MZFW: 15,653 lb. 
 
Minimum Crew The minimum flight crew is two pilots. 
 
Maximum Baggage Aft baggage comp.:   882 lb. Total - maximum floor loading: 120 lb/sq. ft. 
   470 lb/linear ft. 
 Baggage and/or cargo load must comply with loading limitations of approved  Airplane 
 Flight Manual, and must be loaded in accordance with loading instructions of Weight  
 and Balance Supplement to the INTA-approved Airplane Flight Manual. 
 
Fuel Capacity Total capacity: 548.00 U.S. Gal. in two wing tanks 
 Usable fuel: 528.00 U.S. Gal. 
 Unusable fuel:   20.00 U.S. Gal. 
 (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). 
 
Oil Capacity Usable Oil: 5.25 U.S. quarts in each engine tank 
 Unusable Oil: None 
 
Maximum Approved Movement 25,000 ft. 
 
Control Surface Movement Elevator 30° Up 20° Down 
 Elevator Trim Tab 15.5° Up 31° Down 
 Rudder 27.5° Right 27.5° Left 
 Rudder Trim Tab 12.5° Right 19° Left 
 Aileron 20° Up 20° Down 
 Aileron Trim Tab 15° Up 15° Down 
 Flaps,  Inner and Outer 10° Down - Takeoff 
  15° Down - Approach 
  40° Down - Landing 
 All measurements taken at trailing edge from neutral position.  For details of tolerances  
 on control surface movement refer to document D.T. 77-2101. 
 
Maximum Passengers 28 - limited by space available for accommodation.

A43EU 7 
IV.    Model C-212-CE  (Transport Category Airplane)  approved September 9,  1985 
 
The C-212-CE model is similar to the C-212-CD model except for incorporation of CASA Modification No. PP0956 or PP1012 
which enables engine operation at a higher Takeoff (APR on) rating. 
 
Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-502C or TPE331-10R-512C  
(See NOTES 5 & 6) Turboprop engines. 
 
 Prop. Shaft/Eng. Rotor Ratio:    1/26.2287 
 
Fuel See AFM for approved fuels, alternate fuels and approved fuel additives 
 
Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and  
 Type II).  See approved AFM for a list of approved engine lubricating oils. 
 
Engine Limits  
Conditions SHP ESHP %  RPM EGT (°C) 
Takeoff (initial) (5 minutes) 900 944 100 650 
Takeoff (APR on) (5 
minutes) 
925 970 100 650 
Max. Continuous 900 944 100 650 
 
 Transient overspeed limits:   105.5% for 30 sec.;  106% for 5 sec. 
 100% is defined as 41,730 rpm engine rotor speed, 1591 rpm propeller shaft speed.  
 Transient temperature (EGT) limit (1 sec.):   770°C. 
 
 See INTA-approved Airplane Flight Manual, Document D.T. 84-2501, for additional 
 information. 
 
Propeller and Propeller Limits 2 Dowty Rotol Model (c) R.334/4-82-F/13 hydraulic full feathering, constant speed  
 reversible propellers. 
  Blades: 4, serial number 660709314 
  Diameter: 110 in. 
 For % RPM at windmilling see INTA-approved Airplane Flight Manual, Document D.T. 
 84-2501. 
 
 Blade angle measured at 35.333 in radius station: 
 Feathered 82°30’   ±       20’ 
 Flight Idle   9°         ±      20’ 
 Start Locks -1°45’     to 0°30’ 
 Full Reverse -13°        ±  1° 
   Speed Knots IAS 
Airspeed Limits VMO   (Max. Operating)  (S.L.  -25.000 ft)  200 
 VA     (Maneuvering)   146 
 VFE    (Flaps extended) Takeoff 25%  135 
  Approach 37.5%  130 
  Landing 100%  115 
 VMC   (Min. Control)     88 
 
C.G. Range 
Weight 
     (lb) 
     FWD 
%  MAC 
     AFT 
%  MAC 
16,976       16.0       30.0 
16,424       15.9       30.0 
11,051       15.0       30.0 
  9,481       15.0       30.0 
  
 Straight line variation between points given.

A 43EU 8 
IV.    Model C-212-CE    (cont’d) 
Datum A jig point is located in forward fuselage Frame No. 3 and marked on the  
 underside of the fuselage.  The C.G. reference datum is situated 43.90 in. forward of the 
 jig point. 
 
M.A.C. Length is 86.22 in. 
 
 The leading edge of M.A.C. is 215.04 in. aft of datum. 
 
Leveling Means Plumb-bob provisions on aft fact of aft cockpit compartment bulkhead. 
 
Maximum Weights Ramp: 17,086 lb. 
 Takeoff: 16,976 lb. 
 Landing: 16,424 lb. 
 MZFW: 15,653 lb. 
 
Minimum Crew The minimum flight crew is two pilots. 
 
Maximum Baggage Aft baggage comp.:  882 lb. Total - Maximum floor loading: 120 lb/sq. ft. 
   470 lb/linear ft. 
 
 Baggage and/or cargo load must comply with loading limitations of approved Airplane  
 Flight Manual, and must be loaded in accordance with loading instructions of Weight  
 and Balance Supplement to the INTA-approved Airplane Flight Manual. 
 
Fuel Capacity Total capacity: 548.00 U.S. Gal. in two wing tanks 
 Usable fuel: 528.00 U.S. Gal. 
 Unusable fuel:   20.00 U.S. Gal. 
 (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). 
 
Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank 
 Unusable oil: None 
 
Maximum Approved Operating 
Altitude 25,000 ft. 
 
Control Surface Movements Elevator 30° Up 20° Down 
 Elevator Trim Tab 15.5° Up 31° Down 
 Rudder 27.5° Right 27.5° Left 
 Rudder Trim Tab 12.5° Right 19° Left 
 Aileron 20° Up 20° Down 
 Aileron Trim Tab 15° Up 15° Down 
 Flaps, Inner and Outer 10° Down - Takeoff 
  15° Down - Approach 
  40° Down - Landing 
 
 All measurements taken at trailing edge from nuetral position.  For details of tolerance on  
 control surface movement refer to document D.T. 77-2101. 
 
Maximum Passengers 28 - limited by space available for accommodation.

A43EU 9 
V.    Model C-212-CF  (Transport Category Airplane)  approved December 6,  1985 
 
The C-212-CF model is similar to the C-212-CC model with the same engine except for incorporation of CASA Modification 
No. PP0956 or PP1012 which enables engine operation at a higher Takeoff (APR on) rating.  
 
Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-501C or TPE331-10R-511C 
 Turboprop engines. 
 
 Prop.  Shaft/Eng. Rotor Ratio:   1/26.2287 
 
Fuel See AFM for approved fuels, alternate fuels and approved fuel additives. 
 
Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and 
 Type II).  See approved AFM for a list of approved engine lubricating oils. 
 
Engine Limits  
Conditions SHP ESHP % RPM EGT (°C) 
Takeoff (initial) (5 minutes) 900 944 100 650 
Takeoff (ARP on) (5 
minutes) 
925 970 100 650 
Max. Continuous 900 944 100 650 
 
 Transient overspeed limits:   105.5% for 30 sec.;  106% for 5 sec. 
 100% is defined as 41,730 rpm engine rotor speed, 1591 rpm propeller shaft speed.  
 Transient temperature (EGT) limit (1 sec.):   770°C. 
 
 See INTA-approved Airplane Flight Manual, Document D.T. 84-2502, for additional  
 information. 
 
Propeller and Propeller Limits 2 - Hartzell Model HC-B4MN-5AL, constant speed, hydraulic, full feathering, reversible 
 propellers. 
 
 Blades: 4, Model LM10585B + 4 
 Diameter: 110 in. 
 
 For % RPM at windmilling see INTA-approved Airplane Flight Manual, Document D.T. 
 84-2502. 
 
 Blade angle measured at 42 in. radius station: 
 Feathered 83.0°    ±   1.0° 
 Flight Idle   7.0°    ±   0.3° 
 Start Locks -1.5°     ±   0.2° 
 Full Reverse -10°      ±   0.5° 
   Speed Knots IAS 
Airspeed Limits VMO   (Max. Operating) (S.L.  -25,000 ft.)  200 
 VA     (Maneuvering)   146 
 VFE    (Flaps Extended) Takeoff 25%  135 
  Approach 37.5%  130 
  Landing 100%  115 
 VMC   (Min. Control Speed)     88 
 
C.G. Range 
Weight 
     (lb) 
     FWD 
%  MAC 
     AFT 
%  MAC 
16,976      16.0      30.0 
16,424      15.9      30.0  
11,051      15.0      30.0  
  9,481      15.0      30.0 
 Straight line variation between points given.

A 43EU 10 
V.    Model C-212-CF    (cont’d) 
Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside 
 of the fuselage.  The C.G. reference datum is situated 43.90 in. forward of the jig point. 
 
M.A.C. Length is 86.22 in. 
 
 The leading edge of M.A.C. is 215.04 in aft of datum. 
 
Leveling Means Plumb-bob provisions on aft face of act cockpit compartment bulkhead. 
 
 Ramp: 17,086 lb. 
 Takeoff: 16,976 lb. 
 Landing: 16,424 lb. 
 MZFW: 15,653 lb. 
 
Minimum Crew The minimum flight crew is two pilots 
 
Maximum Baggage Aft baggage comp.:  882 lb. Total - Maximum floor loading: 120lb/sq. ft. 
   470 lb/linear ft. 
 
 Baggage and/or cargo load must comply with loading limitations of approved Airplane 
 Flight Manual, and must be loaded in accordance with loading instructions of Weight  
 and Balance Supplement to the INTA-approved Airplane Flight Manual. 
 
Fuel Capacity Total capacity: 548.00 U.S. Gal in two wing tanks 
 Usable fuel: 528.00 U.S. Gal. 
 Unusable fuel:  20.00 U.S. Gal. 
 (See NOTE 1 (b) and 1 (c) for data on system fuel oil). 
 
Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank. 
 Unusable oil: None 
 
Maximum Approved Operating 
Altitude 25,000 ft. 
 
Control Surface Movements Elevator 30° Up 20° Down 
 Elevator Trim Tab 15.5° Up 31° Down 
 Rudder 27.5° Right 27.5° Left 
 Rudder Trim Tab 12.5° Right 19° Left 
 Aileron 20° Up 20° Down 
 Aileron Trim Tab 15° Up 15° Down 
 Flaps, Inner and Outer 10° Down - Takeoff 
  15° Down - Approach 
  40° Down - Landing 
 
 All measurements taken at trailing edge from neutral position.  For details of tolerance on  
 control surface movement refer to document D.T. 77-2101. 
 
Maximum Passengers 28 - limited by space available for accommodation. 
 
VI.     Model C-212-DF  (Transport Category Airplane)  approved March 30,  1989 
 
The C-212-DF model is similar to the C-212-CE except by the modification in the nose, wingtips and vertical tail. 
 
Engines 2 - Garrett Turbine Engine Co. Model TPE331-10R-502C or TPE331-10R-512C or  
(See NOTE 7 & 8) TPE331-10R-513C. 
 
 Prop. Shaft/Eng Rotor Ratio:   1/26.2287.

A43EU 11 
VI.     Model C-212-DF   (cont’d) 
Fuel See AFM for approved fuels, alternate fuels and approve fuel additives. 
 
Oil Oils conforming to Garrett Turbine Engine Co. Specification EMS 53110 (Type I and 
 Type II).  See approved AFM for a list of approved engine lubricating oils. 
 
Engine Limits 
Conditions SHP ESHP %  RPM EGT (°C) 
Takeoff (initial)(5 minutes) 900 944 100 650 
Takeoff (APR on) (5 
minutes) 
925 970 100 650 
Max. Continuous 900 944 100 650 
 
 Transient overspeed limits:  105.5% for 30 sec.;  106% for 5 sec. 
 100% RPM is defined as 41,730 rpm engine rotor speed, 1591 rpm propell er shaft speed. 
 Transient temperature (EGT) limit (1 sec.):   770°C. 
 
 See DGAC-approved Airplane Flight Manual, Document D.T. 88-2509 for additional 
 information. 
 
Propeller and Propeller Limits 2 Dowty Rotol Ltd, Model (c) R.334/4-82-F/13, hydraulic full feathering, constant  
 speed, reversible propellers. 
 Blades: 4, serial number 660709314 
 Diameter: 110 in. 
 
 For % RPM at windmilling see DGAC-approved Airplane Flight Manual, Document  
 D.T. 88-2509. 
 
 Blade angle measured at 35.333-in. radius station: 
 Feathered  82°32’    ±      20’ 
 Flight Idle    9°        ±      20’ 
 Start Locks -1°45’     ±  0°30’ 
 Full Reverse -13°         ± 1° 
 
   Speed Knots IAS 
Airspeed Limits VMO (Max. Operating) (S.L. -25,000 ft.) 200 
 VA (Maneuvering)  146 
 VFE (Flaps Extended) Takeoff 25% 135 
  Approach 25% 135 
  Landing 100% 115 
 VMC (Min. Control)    76 
 
C.G. Range 
Weight 
    (lb) 
     FWD 
%  MAC 
     AFT 
%  MAC 
16,976      16.0     30.0 
16,424      15.9     30.0 
11,051      15.0     30.0 
  9,481      15.0     30.0 
 
 Straight line variation between points given. 
 
Datum A jig point is located in forward fuselage Frame No. 3 and marked on the underside of  
 the fuselage.  The C.G. reference datum is situated 43.90 in. forward of the jig point. 
 
M.A.C. Length is 86.22 in. 
 
 The leading edge of M.A.C. is 215.04 in. aft of datum

A 43EU 12 
VI.     Model C-212-DF    (cont’d) 
Leveling Means Plumb-bob provisions on aft face of aft cockpit compartment bulkhead. 
 
Maximum Weight Ramp: 17,086 lb. 
 Takeoff: 16,976 lb. 
 Landing: 16,424 lb. 
 MZFW : 15,653 lb. 
 
Minimum Crew The minimum crew is two pilots. 
 
Maximum Baggage Aft baggage comp.:  882 lb. Total - maximum floor loading: 120 lb/sq. ft. 
   470 lb/linear ft, 
 
 Fwd baggage comp.:  309 lb. total 
 
 Baggage and/or cargo load must comply with loading limitations of approved Airplane 
 Flight Manual, and must be loaded in accordance with loading instructions of Weight 
 and Balance Supplement to the DGAC-approved Airplane Flight Manual. 
 
Fuel Capacity Total Capacity: 548.00 U.S. Gal. in two wing tanks 
 Usable Fuel: 528.00 U.S. Gal. 
 Unusable Fuel:   20.00 U.S. Gal. 
 
 (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). 
 
Oil Capacity Usable oil: 5.25 U.S. quarts in each engine tank 
 Unusable oil: None 
 
Maximum Approved Operating 
Altitude 25,000 ft. 
  
Control Surface Movements Elevator 30° Up 20° Down 
 Elevator Trim Tab 15.5° Up 31° Down 
 Rudder 20° Right 24° Left 
 Rudder Trim Tab 14° Right 14° Left 
 Aileron 20° Up 20° Down 
 Aileron Trim Tab 15° Up 15° Down 
 Flaps, Inner and Outer 10° Down - Takeoff 
  10° Down - Approach 
    40° Down - Landing 
 All measurements taken at trailing edge from neutral position.  For details of tolerances  
 on control surface movement refer to document D.T. 77-2101. 
 
Maximum Passengers 28 - Limited by space available for accommodation. 
 
 
VII.   Model C-212-DE   (Transport Category Airplane)  approved October 1,  1991 
 
Engines 2 - Pratt and Whitney Canada, Model PT6A-65B turboprop engines 
  
 Propeller Shaft Gear Ratio:   0.0568:1 
 
Fuel Refer to Engine Service Bulletin No. 3032845-72-44  (PWC SB 13044) for listing of  
 approved fuels 
 
Oil Refer to Engine Service Bulletin No. 3032845-72-1  (PWC SB 13001) for listing of  
 approved oils.

A43EU 13 
VII.   Model C-212-DE    (cont’d) 
Engine Limits 
Conditions SHP ESHP PROP 
% RPM 
ITT 
(°C) 
Takeoff (initial) (5 minutes) 1000 1069 100 820 
Max. Continuous 1000 1069 100 810 
 
 100% NG is defined as 37,468 rpm. 
 100% NP is defined as 1,700 rpm (which means a Power Turbine Speed of 29,894 rpm  
 (NF)). 
  
 Transient temperature (ITT) limit:   1000°C for 5 seconds. 
 See DGAC-approved Airplane Flight Manual, Document D.T. 88-2518, for additional 
 information. 
 
Propeller and Propeller Limits 2 McCauley Model 4HFR34C756/106LM, constant speed, hydraulic full feathering,  
 reversible, propellers. 
 
 Blades: 4, Model 106LM 
 Diameter: 106 in. 
 
 Blade angle measured at 30 in. radius station: 
 Feathered 86.7°   ±   0.5° 
 Beta pick-up 19.5°   ±   0.2° 
 Flight Idle 15°      ±   0.2° 
 Start Locks   7°      ±   0.5° 
 Full Reverse -10°     ±   0.5° 
   Speed Knots IAS 
Airspeed Limits VMO   (Max. Operating) (S.L.  -25,000 ft.)  200 
 VA     (Maneuvering)   146 
 VFE    (Flaps Extended) Takeoff 25%  135 
  Approach 25%  130 
  Landing 100%  115 
 VMC   (Min. Control)     76 
 
C.G. Range 
Weight 
    (lb) 
     FWD 
%  MAC 
     AFT 
%  MAC 
16,976      16.0     30.0 
16,424      15.9     30.0 
11,051      15.0     30.0 
  9,481      15.0     30.0 
 Straight line variation between point given. 
 
Datum A jig point is located in forward fuselage Frame. No. 3 and marked on the underside of 
 the fuselage.  The C.G. reference datum is situated 43.9 in. forward to the jig point. 
 
M.A.C. Length is 86.22 in. 
  
 The leading edge of M.A.C. is 215.04 in. aft of datum 
 
Leveling Means Plumb-bob provisions on aft face of aft cockpit compartment bulkhead. 
 
Maximum Weights Ramp: 17,086 lb. 
 Takeoff: 16,976 lb. 
 Landing: 16,424 lb. 
 MZFW: 15,653 lb.

A 43EU 14 
VII.   Model C-212-DE    (cont’d) 
Minimum Crew The minimum flight crew is two pilots. 
 
Maximum Baggage Aft baggage compartment: 882 lb total 
 Fwd baggage compartment: 309 lb. total 
 Maximum floor loading: 120 lb/sq. ft. 
                                           470 lb/linear ft. 
 
 Baggage and/or cargo load must comply with loading limitations of approved Airplane 
 Flight Manual, and must be loaded in accordance with loading instructions of Weight  
 and Balance Supplement to the approved Airplane Flight Manual. 
 
Fuel Capacity Total capacity: 548.00 U.S. Gal. in two wing tanks 
 Usable fuel: 528.00 U.S. Gal. 
 Unusable fuel:   20.00 U.S. Gal. 
 
Oil Capacity Usable oil: 1.5 U.S. gallons in each engine tank 
 Unusable oil: 1 U.S. gallon 
 
 (See NOTES 1 (b) and 1 (c) for data on system fuel and oil). 
 
Maximum Approved Operating 
Altitude 25,000 ft. 
 
Control Surface Movement Elevator 30° Up 20° Down 
 Elevator Trim Tab   3° Up   8.6° Down 
 Rudder 24.5° Right 21° Left 
 Rudder Trim Tab 14° Right 14° Left 
 Aileron 20° Up 20° Down 
 Aileron Trim Tab 15° Up 15° Down 
 Flaps, Inner and Outer 10° Down - Takeoff 
  10° Down - Approach 
  40° Down - Landing 
 All measurements taken at trailing edge from neutral position.  For details of tolerance on  
 control surface movement refer to document D.T. 87-2104. 
 
Maximum Passengers 28 - Limited by space available for accommodation. 
 
 
DATA PERTINENT TO ALL MODELS 
 
Serial Nos. Eligible The Spanish Export Airworthiness Certificate endorsed as noted below under Import  
 Requirements must be submitted for each individual aircraft for which application for  
 FAA Airworthiness Certification is made except for S/N 64N and 73N. 
 
 The Indonesian Export Airworthiness Certificate endorsed as noted below under Import 
 Requirements must be submitted for Airplanes S/N 64N and 73N produced by IPTN in 
 Indonesia and validated by the Spanish Direccion General de Aviacion Civil (DGAC)  
 (by letter dated December 23,  1986) for which application for FAA Airworthiness 
 Certification is made. 
 
Import Requirements The U.S. Airworthiness certification basis for aircraft type certificated under FAR 
 Section 21.29 and exported by the country of manufacture is FAR Sections 21.183 (c) or  
 21.185 (c).  
 
 The U. S. Airworthiness certification basis for aircraft type certificated under FAR  
 Section 21.29 exported from countries other than the country of manufacture (e.g.,  
 third party country) is FAR Section 21.183 (d) or 21.183 (b).

A43EU 15 
The FA A  can i ssue a U.S. ai rworthi ness certi f i cate based on an Export Certi f i cate of  
Airworthiness (Export C of A) signed by a representative of the Spanish DGAC on behalf 
of the European Community.  The Export C of A should contain the following statement: 
‘ The aircraft covered by this certificate has been examined, tested, and found to conform 
with the Type Design approved under U.S. Type Certificate No. A43EU and to be in a 
condition for safe operation.’     
 
Refer to the applicable bilateral agreement to verify eligibility for import into the 
United States of both new and used aircraft based on the scope of the agreement, to 
identify any required statements by the exporting authority on the export certificate 
of airworthiness (or equivalent document), and for procedures for coordinating 
exceptions to conformity statements on these documents. Refer to FAA 
Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance 
of an airworthiness certificate for imported aircraft. 
 
Certification Basis FAR Part 25 effective February 1,  1965, including Amendments 25-1 through 25-35. 
 
 FAR Part 36 effective December 1,  1969, including Amendments 36-1 through 36-17. 
 
 CASA has elected to comply with the requirements of FAR 25.855 and 25.857 as 
 amended by Amendment 25-60 for the forward cargo compartment of the C-212-DF and 
 C-212-DE Models. 
 
 FAA Special Condition 25-100-NW-6, dated May 18,  1981, applicable to Models -CC,  
 -CD, -CE, -CF and -DF. 
 
 SFAR 27 effective February 1,   1974, including amendments 27-1 through 27-6 as it 
 applies to the fuel venting emissions requirements.  Compliance has been demonstrated  
 for Model -DF with the installation of CASA modification 212.510251 and for Model 
 -DE with the installation of CASA drawing 212-54515. 
  
 Date of application for Type Certificate:   September 7,   1974. 
 
 Type Certificate No. A43EU, issued February 22,   1977. 
 
The Spanish DGAC  originally type certificated these Construcciones Aeronauticas, S.A  
C-212 aircraft under its type certificate Number 01-82.  The FAA validated these  
products under U.S. Type Certificate number A43EU.  Effective September 28, 2003, the 
European Aviation Safety Agency (EASA) began oversight of this product on behalf of 
the Spanish DGAC . 
 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
 (see Certification Basis) and listed in document Equipment List Report D.T. 77-2301, 
 (Models -CC through -CF), D.T. 87-2523 (Model -DF) and D.T. 88-2315 (Model -DE)  
 must be installed in the aircraft for certification. 
 
In addition, the following is required: 
 
 - INTA-approved Airplane Flight Manual, Document No. D.T. 76-2501, applicable to C-212-CB Model. 
 
 - INTA-approved Airplane Flight Manual, Document No. D.T. 78-2501, applicable to C-212-CC Model,  
  Revision 3 or later approved revisions. 
 
 - INTA-approved Airplane Flight Manual, Document No. D.T. 83-2501, applicable to C-212-DC Model. 
 
 - INTA-approved Airplane Flight Manual, Document No. D.T. 84-2501, applicable to C-212-CE Model. 
 
 - INTA-approved Airplane Flight Manual, Document No. D.T. 84-2502, applicable to C-212-CF Model. 
 
 - DGAC-approved Airplane Flight Manual, Document No. D.T. 88-2509, applicable to C-212-DF Model.

A 43EU 16 
 - DGAC-approved Airplane Flight Manual, Document No. D.T. 88-2518, applicable to C-212-DE  
  Model. 
 
 
Service Information  Each of the documents listed below must state that it is approved by EASA – or for 
approvals made before September 28, 2003 – by the Spanish DGAC. Any such 
documents  are accepted by the FAA and are considered FAA approved.  Additionally, 
approvals issued by Construcciones Aeronauticas, S.A.under the authority of EASA 
approved Design Organization EASA.21J.032 -  or for approvals made before 
September 28, 2003 - under the authority of  Spanish DGAC Design 
Organization Approval No. 1 are considered FAA approved.  These approvals 
pertain to the type design only. 
 
 TC holder Service Bulletins, except as noted below, 
 Structural repair manuals 
 Vendor manuals referenced in TC holder Service Bulletins 
 Airplane flight manuals 
 Repair instructions. 
 
    
 Note: Design changes that are contained in TC holder Service Bulletins and that are 
classified as Level 1 Major in accordance with either the US/Spain or US/EASA Bilateral 
Aviation Safety Agreement – Implementation Procedures for Airworthiness, must be 
approved by the FAA. 
 
 
NOTES 
NOTE 1 (a) Current weight and balance report, including list of equipment included in certificated empty weight, - 
  and loading instructions must be in each aircraft at the time of original certification. 
 
 (b) Unusable fuel and system oil and all hydraulic fluid must be included in the certified weight. 
  Unusable fuel is that quantity of fuel remaining in the system and in the tanks when the fuel quantity 
  indicators read zero.  The approved unusable fuel of 20.0 U.S. gal. (130.0 lbs.) is comprised of  
  system and tank fuel determined under FAR 25.959. 
 
 (c) System oil is the amount of oil required to fill the oil system and tanks up to its normal level. 
 
NOTE 2 All placards presented in the limitations section of the approved Airplane Flight Manual must be installed in  
 the appropriate location on the aircraft. 
 
NOTE 3 (a) The service life limits for aircraft structural parts which are fatigue critical are listed in the approved  
  Airframe Maintenance Manual, Chapter 5. 
 
 (b) Life limited parts for the Model TPE331-5-501C engine are listed in FAA-Approved Garrett Service 
  Bulletin TPE331-72-0019 dated December 4,   1972, or later FAA-Approved revisions. 
  
 (c) Life limited parts for the Model TPE331-10 and -10R series engines are listed in FAA-Approved 
  Garrett Service Bulletins TPE331-72-0180, dated February 15,   1978, or later FAA-Approved  
  revisions. 
 (d) Life limited parts for the Model PT6A-65B engine are listed in DOT of Canada approved Service 
  Bulletin 3032845-72-2 (PEC SB 13002) dated October 14,  1986, or later DOT -approved 
  revisions.  
 
NOTE 4 For the C-212-CC Model with the TPE331-10R-501C or -501C engines installed the INTA-approved 
 Airplane Flight Manual, Document 78-25-1 Revision 7, dated January 8,   1982, or later approved 
 revision is required. 
 
NOTE 5 Engine Models TPE331-10-511C, TPE331-10R -511C and TPE331-10R-512C are the same as Models 
 TPE331-10-501C, TPE331-10R-501C and TPE331-10R-502C with Garrett Service Bulletin No. 
 TPE331-72-0395, effective April 1,  1983, Revision 1, dated November 10,  1983, or later revision  
 incorporated and are eligible when CASA Service Bulletin 212-80-22 and 212-80-23 are incorporated 
 upon installation of the later model engine.

A43EU 17 
 
NOTE 6 Operation of the C-212-CC and -CF Models with a TPE331-10-501C or TPE331-10R -501C engine on  
 one side and a TPE331-10-511C or TPE331-10R -511C engine on the other side is authorized for a  
 maximum of 300 hours after the later model engine is installed.  Operation of the C-212-CD and -CE 
 Models with a TPE331-10R-502C engine on one side and a TPE331-10R-512C engine on the other side 
 is authorized for a maximum of 300 hours after the later model engine is installed.  C-212-CC, -CD, -CE and 
 -CE airplane performance is unaffected with mixed engine installed. 
 
NOTE 7 Engine Model TPE-331-10R-513C is the same as Model TPE331-10R-512C with Garrett Service Bulletin 
 TPE331-72-0509, dated August 21,  1985, or later approved revision incorporated.  
 
NOTE 8 Operation of the C-212-DF Model with a TPE331-10R-512C engine on one side and TPE331-10R-513C 
 engine on the other side is authorized for an unlimited time.  Operation of the C-212-DF Model with a  
 TPE331-10R-512C or TPE331-10R-513C engine on one side, and TPE331-10R-502C engine on the 
 other side is authorized for a maximum of 300 hours after the later model engine is installed.  C-212-DF 
 airplane performance is unaffected with mixed engines installed. 
 
 
 
 
.....END.....
```

## ADs (49, in force first)

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- [AD 2020-03-18](https://openairdocs.org/ad/2020-03-18): Flight Controls · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 2 more. Effective Apr 2, 2020
- [AD 2018-19-02](https://openairdocs.org/ad/2018-19-02): Flight controls · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 2 more. Effective Oct 22, 2018
- [AD 2017-01-10](https://openairdocs.org/ad/2017-01-10): Flight controls · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Feb 22, 2017
- [AD 2015-16-04](https://openairdocs.org/ad/2015-16-04): Fire Protection · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 23 more. Effective Sep 15, 2015
- [AD 2013-24-09](https://openairdocs.org/ad/2013-24-09): Engine Controls · EADS CASA C-212-CB, C-212-CC, C-212-CD and 2 more. Effective Jan 21, 2014
- [AD 2009-20-10](https://openairdocs.org/ad/2009-20-10): Auto Flight · EADS CASA C-212-CB, C-212-CC, C-212-CD and 1 more. Effective Nov 17, 2009
- [AD 2009-12-04](https://openairdocs.org/ad/2009-12-04): Navigation · EADS CASA C-212-CB, C-212-CC, C-212-CD and 3 more. Effective Jul 16, 2009
- [AD 2009-02-01](https://openairdocs.org/ad/2009-02-01): Center wing attachment fittings · EADS CASA C-212-DF. Effective Mar 9, 2009
- [AD 2008-06-13](https://openairdocs.org/ad/2008-06-13): Centre wing lower skin · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Apr 17, 2008
- [AD 2006-15-11](https://openairdocs.org/ad/2006-15-11): Protective liner between the passengers and the cargo. · EADS CASA C-212-CC with STC ST02177AK. Effective Aug 29, 2006
- [AD 2006-15-12](https://openairdocs.org/ad/2006-15-12): Protective liner between the passengers and the cargo. · EADS CASA C-212-CC with STC ST02129AK. Effective Aug 29, 2006
- [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005
- [AD 2004-07-17](https://openairdocs.org/ad/2004-07-17): Nose landing gear (NLG) · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective May 11, 2004
- [AD 99-19-15](https://openairdocs.org/ad/99-19-15): AFM - Limitations Section - Ice Protection Systems · EADS CASA C-212-CB, C-212-CC, C-212-CD and 8 more. Effective Dec 27, 1999
- [AD 99-04-02](https://openairdocs.org/ad/99-04-02): Inspect Fuel Pump Cover Plates For Spark Marks · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 17, 1999
- [AD 98-22-04](https://openairdocs.org/ad/98-22-04): Power Quadrant Cover · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Nov 27, 1998
- [AD 98-18-21](https://openairdocs.org/ad/98-18-21): Corrosion Inspection · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Oct 20, 1998
- [AD 98-12-28](https://openairdocs.org/ad/98-12-28): Inspect False Spar Of Wing For Cracking · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Jul 15, 1998
- [AD 98-10-08](https://openairdocs.org/ad/98-10-08): Lower Shaft & Support Structure Of Rudder · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Jun 17, 1998
- [AD 98-06-02](https://openairdocs.org/ad/98-06-02): Inspect Spherical Bearings Of Aileron Control Rod · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Apr 15, 1998
- [AD 97-21-14](https://openairdocs.org/ad/97-21-14): Inspect Restrictor Pistons · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Nov 24, 1997
- [AD 97-03-13](https://openairdocs.org/ad/97-03-13): Rudder Pedal Setting Mechanisms · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 14, 1997
- [AD 96-09-22](https://openairdocs.org/ad/96-09-22): AFM - Icing · EADS CASA C-212-CB, C-212-CC, C-212-CD and 7 more. Effective Jun 11, 1996
- [AD 96-07-14](https://openairdocs.org/ad/96-07-14): Reduced Structural Integrity · EADS CASA C-212-CB, C-212-CC, C-212-CD and 2 more. Effective May 15, 1996
- [AD 92-13-51](https://openairdocs.org/ad/92-13-51): Backup Blocking Device · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Jul 31, 1992
- [AD 91-03-10](https://openairdocs.org/ad/91-03-10): Propeller Speed & Pitch Control System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 11, 1991
- [AD 89-23-16](https://openairdocs.org/ad/89-23-16): Power Reserve System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Dec 12, 1989
- [AD 89-22-09](https://openairdocs.org/ad/89-22-09): Passenger Door Evacuation · Step and handrails (Fischer Brothers Avn STC SA906GL). Effective Nov 20, 1989
- [AD 89-19-05](https://openairdocs.org/ad/89-19-05): Rear Passenger Seats · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Oct 14, 1989
- [AD 89-21-08](https://openairdocs.org/ad/89-21-08): Trim Control System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Oct 5, 1989
- [AD 89-02-08 R1](https://openairdocs.org/ad/89-02-08-R1): Wing Flap Control System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Sep 5, 1989
- [AD 89-05-01](https://openairdocs.org/ad/89-05-01): Wing Flap Control System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Apr 3, 1989
- [AD 88-09-02](https://openairdocs.org/ad/88-09-02): Fuel Shut-Off Valves · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Jun 1, 1988
- [AD 87-16-04](https://openairdocs.org/ad/87-16-04): Stall Warning System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Aug 31, 1987
- [AD 87-10-08](https://openairdocs.org/ad/87-10-08): Crew Door Handle Cover · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Jun 19, 1987
- [AD 87-05-06](https://openairdocs.org/ad/87-05-06): Propeller Feathering Control · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 25, 1987
- [AD 87-05-07](https://openairdocs.org/ad/87-05-07): Attendant's Seat · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 25, 1987
- [AD 87-04-10](https://openairdocs.org/ad/87-04-10): Smoke Detector System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 9, 1987
- [AD 87-04-02](https://openairdocs.org/ad/87-04-02): Nose Landing Gear · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 2, 1987
- [AD 87-03-04](https://openairdocs.org/ad/87-03-04): Trim Control Markings & Placards · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Feb 19, 1987
- [AD 86-19-05](https://openairdocs.org/ad/86-19-05): Electrical System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Oct 2, 1986
- [AD 84-12-03](https://openairdocs.org/ad/84-12-03): Structural Flight Controls and Fuel System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Jul 23, 1984
- [AD 84-02-03](https://openairdocs.org/ad/84-02-03): Exit Doors Modification · EADS CASA C-212-CB and C-212-CC. Effective Feb 27, 1984
- [AD 83-02-06](https://openairdocs.org/ad/83-02-06): Fuel Filter System · EADS CASA C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Feb 7, 1983
- [AD 2021-16-07](https://openairdocs.org/ad/2021-16-07) (historical): Fuselage · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Sep 28, 2021
- [AD 2017-19-08](https://openairdocs.org/ad/2017-19-08) (historical): Flight controls · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 2 more. Effective Oct 25, 2017
- [AD 2007-05-01](https://openairdocs.org/ad/2007-05-01) (historical): Cracks had been found in the centre wing lower skin. · Construcciones Aeronauticas C-212-CB, C-212-CC, C-212-CD and 4 more. Effective Mar 14, 2007
- [AD 74-08-09 R2](https://openairdocs.org/ad/74-08-09-R2) (historical): Waste Receptacles · Aero Spacelines 377, 377MG, 377SGT and 268 more. Effective Jul 29, 1996

## Registered aircraft by registry model (OpenAirDocs)

- [Construcciones Aeronauticas C-212-CC](https://openairdocs.org/model/construcciones-aeronauticas-c-212-cc): 12 aircraft (registry code 2410204)
- [C A S A C-212-DF](https://openairdocs.org/model/c-a-s-a-c-212-df): 3 aircraft (registry code 2410205)
- [C A S A C-212-CD](https://openairdocs.org/model/c-a-s-a-c-212-cd): 1 aircraft (registry code 2410201)
- [Construcciones Aeronauticas C-212-CB](https://openairdocs.org/model/construcciones-aeronauticas-c-212-cb): 1 aircraft (registry code 2410202)
- [Construcciones Aeronauticas C-212-CD](https://openairdocs.org/model/construcciones-aeronauticas-c-212-cd): 1 aircraft (registry code 2410209)
- [Construcciones Aeronauticas C-212-CE](https://openairdocs.org/model/construcciones-aeronauticas-c-212-ce): 0 aircraft (registry code 2410206)
- [Construcciones Aeronauticas C-212-CF](https://openairdocs.org/model/construcciones-aeronauticas-c-212-cf): 0 aircraft (registry code 2410207)

## STCs approved under this data sheet (77, first 50)

- [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc
- [STC ST04105NY](https://openairdocs.org/stc/ST04105NY): Installation of Flight Data Recorder, Flight Data Acquisition Unit, Traffic Advisory Altering System and Navigation Suite. CASA Flight Tech LLC
- [STC ST04109NY](https://openairdocs.org/stc/ST04109NY): Update of COMBI. CASA Flight Tech LLC
- [STC ST02257AK](https://openairdocs.org/stc/ST02257AK): Modify the aircraft configuration from 23 passenger seats to a combined cargo and passenger configuration.. CASA Flight Tech LLC
- [STC ST02046AK](https://openairdocs.org/stc/ST02046AK): nstallation of Allied Signal (Sundstrand) Mark VI Ground Proximity Warning System. Erickson Incorporated
- [STC ST02047AK](https://openairdocs.org/stc/ST02047AK): Installation of Trimble TNL 2101 I/O global positioning system.. Erickson Incorporated
- [STC ST02048AK](https://openairdocs.org/stc/ST02048AK): Installation of Trimble TNL 2100T global positioning system.. Erickson Incorporated
- [STC ST02083AK](https://openairdocs.org/stc/ST02083AK): Installation of a BFGoodrich Aerospace Traffic alert and collision avoidance system I, Model TCAS 791.. Erickson Incorporated
- [STC ST02129AK](https://openairdocs.org/stc/ST02129AK): Reduction/limitation of passenger seats to 19 or fewer.. Erickson Incorporated
- [STC ST02414AK](https://openairdocs.org/stc/ST02414AK): Reduction/limitation of passenger seats to 19 or fewer. Erickson Incorporated
- [STC ST00065MC](https://openairdocs.org/stc/ST00065MC): Installation of a Ballistic Protection System (BPS). Erickson Incorporated
- [STC ST09907AC](https://openairdocs.org/stc/ST09907AC): Installation of Hartzell 5-blade carbon composite propellers.. BS Designs Inc.
- [STC ST03558AT](https://openairdocs.org/stc/ST03558AT): Installation of a Collins TCAS-4000 (TCAS II) System (Version 7.0) with dual Collins TVI-920D VSI/TA/RA Indicators and associated hardware.. Woven Electronics, LLC
- [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc.
- [STC ST02548AK](https://openairdocs.org/stc/ST02548AK): Installation of Main Gear Gravel Deflectors. Aero Twin Inc
- [STC ST04200NY](https://openairdocs.org/stc/ST04200NY): Installation of 19 Martin Baker Aircraft Company Inc. Seat. Carson Helicopters Inc
- [STC ST02540AK](https://openairdocs.org/stc/ST02540AK): Fabrication and installation of Aero Twin, Inc., Rudder Gust Lock Kit No. 4111-212. Aero Twin Inc
- [STC ST04248AT](https://openairdocs.org/stc/ST04248AT): Replacement of OEM metric flight control cables assemblies for the ailerion, elevator, rudder, ailerion trim tab, elevator trim tab, and rudder trim tab with MIL-SPEC standard cables assemblies. Bighorn Airways Inc
- [STC ST02433LA](https://openairdocs.org/stc/ST02433LA): Installation of LifePort Triple Litter Stacking System (TLSS). LifePort LLC
- [STC ST02099SE](https://openairdocs.org/stc/ST02099SE): Installation of a Supplemental Lighting System; manufactured and installed. Aviation Specialties Unlimited Inc.
- [STC ST03993AT](https://openairdocs.org/stc/ST03993AT): Installation of a Universal Avionics EFI-890R Electronic Flight Instruments System (EFIS).. Air Data Consulting Group, Inc.
- [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 ST04157AT](https://openairdocs.org/stc/ST04157AT): Installation of Concorde lead acid batteries to replace nickel-cadmium (NiCd) batteries along with associated hardware. AAR Airlift Group
- [STC ST04178AT](https://openairdocs.org/stc/ST04178AT): Replace original equipment Nickel-Cadmium (NiCd) main and auxiliary batteries with Concorde Lead-Acid, main and auxiliary batteries along with associated hardware. Concorde Battery Corporation
- [STC ST02434AK](https://openairdocs.org/stc/ST02434AK): Limit passenger seating to nineteen (19) or less. Samaritan Purse
- [STC ST02401AK](https://openairdocs.org/stc/ST02401AK): Installation of a Nose Gear Gravel Deflector. Aero Twin Inc
- [STC SA3686SW](https://openairdocs.org/stc/SA3686SW): Installation of floor proximity lighting system.. BF Goodrich Aerospace
- [STC ST02382AK](https://openairdocs.org/stc/ST02382AK): Reduction / Limitation of passenger seats to nine (9), in accordance with Bighorn Airways, Inc., Document Number BIG-C-212-AFMS, Revision IR, dated June 15, 2011, or later FAA approved revisions.. Bighorn Airways Inc
- [STC ST02251AK](https://openairdocs.org/stc/ST02251AK): Reduction / Limitation of passenger seats to nine (9). Bighorn Airways Inc
- [STC ST00673WI-D](https://openairdocs.org/stc/ST00673WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System installation.. Rockwell Collins Inc
- [STC ST00682WI-D](https://openairdocs.org/stc/ST00682WI-D): Modification of Collins VHF-20/VHF-20A/VHF-20B VHF COMM Receiver Transmitter with CTL-20 Control Pro Line I System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System Installation in accordance with Collins Installation Instructions as listed on AML No. ST00682WI-D, Revision -, or later FAA approved revisions.. Rockwell Collins Inc
- [STC ST02559AK](https://openairdocs.org/stc/ST02559AK): Installation of Aero Twin, Inc. CASA 212 Exhaust Deflector, part number AT-CASA-EXDF-1001. Aero Twin Inc
- [STC SA1315SO](https://openairdocs.org/stc/SA1315SO): Installation of refreshment center.. Aeronautical Engineers, Inc
- [STC ST00335NY](https://openairdocs.org/stc/ST00335NY): Remove existing starter-generator and install Aircraft Parts Corporation (APC) starter generator P/N. Shurka Aerospace Inc
- [STC ST02346AK](https://openairdocs.org/stc/ST02346AK): Restricted category installation of a Forward Looking Infrared (FLIR) system. ConocoPhillips Company
- [STC ST02317AK](https://openairdocs.org/stc/ST02317AK): Reduction/limitation of passenger seats to nineteen (19) or fewer. Samaritan Purse
- [STC ST03274AT](https://openairdocs.org/stc/ST03274AT): Passenger seating reconfiguration to 9 seats.. Fayad Enterprises, LLC
- [STC ST01142WI-D](https://openairdocs.org/stc/ST01142WI-D): Modification of a single or dual Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92 control head to a Flight ID capable Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92E control head.. Rockwell Collins Inc
- [STC ST511CH](https://openairdocs.org/stc/ST511CH): Eliminate 27,000 landing cycle life limit of the landing gear by placing aircraft on an inspection program described by the Murray Aviation document titled CASA C212-200 Series Aircraft Landing Gear Continued Airworthiness Limitations , no revision, dated January 23, 1996, or later FAA Approved Revision. Presidential Airways Inc
- [STC ST03305AT](https://openairdocs.org/stc/ST03305AT): Installation of a SINGLE Class-A Sandel ST3400 Terrain Awareness Warning System (TAWS), pilot and co-pilot annunciator panels, and Air Data Computer (ADC) .. Presidential Airways Inc
- [STC ST01468CH](https://openairdocs.org/stc/ST01468CH): Installation of various SMR Technologies electrical propeller deicer models.. SMR Technologies
- [STC ST01394WI-D](https://openairdocs.org/stc/ST01394WI-D): Modification of a Collins CTL-23 or CTL-23C VHF COMM/NAV Control Panel System installation.. Rockwell Collins Inc
- [STC ST01398NY](https://openairdocs.org/stc/ST01398NY): Installation of Universal Avionics Systems Corporation CVR-120 cockpit voice recorder (CVR). Approved for serial number 405 ONLY.. Sierra Nevada Corporation/Integrated Mission Systems
- [STC ST01307WI-D](https://openairdocs.org/stc/ST01307WI-D): Modification of a Collins TVI-920/TVI-920D Vertical Speed/TCAS Indicator installation. Rockwell Collins Inc
- [STC ST02243AK](https://openairdocs.org/stc/ST02243AK): Installation of a Honeywell MK-VI EGPWS (TAWS). Jim Air Inc
- [STC ST10215SC](https://openairdocs.org/stc/ST10215SC): Installation of Honeywell Mark VI Enhanced Ground Proximity Warning System (EGPWS) equipped with a HOneywell KMD 850 Multi-Function Display (MFD).. Bighorn Airways Inc
- [STC SA00823CH](https://openairdocs.org/stc/SA00823CH): Installation of various de-icer wire harnesses.. SMR Technologies
- [STC ST00609NY-D](https://openairdocs.org/stc/ST00609NY-D): Installation of replacement Lead Acid Batteries.. Bering Air, Inc
- [STC SA5603NM-D](https://openairdocs.org/stc/SA5603NM-D): Installation of a Fairchild A100/A100A cockpit voice recorder.. Learjet Inc
- [STC SA1670NM](https://openairdocs.org/stc/SA1670NM): Two (2) 400 gallon bulk liquid cargo tanks.. F. S. Air Service

All 77: https://openairdocs.org/tcds/A43EU/stcs.md

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