# TCDS 7A6: Sud Aviation

- Type: Type certificate data sheet
- Status: Current
- Holder: Sud Aviation
- Revision: 8
- Revised: November 24, 2009
- Product: Aircraft, Large Airplane
- Certification basis: Part 21, CAR 10
- Data sheet PDF: https://openairdocs.org/files/sha256/d0/68/d068054f25e2140ceb9bc93d18ae13a9dd1320a0f103fb08039a3617891b756e
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/4F2A2D0C1A2BE1C5862576800063D22A.0001
- Page: https://openairdocs.org/tcds/7A6

## Models (3)

As the data sheet lists them.

- Caravelle SE 210 Model VIR
- Caravelle SE 210 Model III
- Caravelle SE 210 Model I

## 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 
Rev. 
No. 
7 - - - - - 7 
 
Surrendered October 27, 2009 
 
FEDERAL AVIATION AGENCY 
 
7A6 
Revision 8 
SUD AVIATION 
Caravelle SE 210 
Model I 
Model III 
Model VIR 
 
November 24, 2009 
 
TYPE CERTIFICATE DATA SHEET NO. 7A6 
 
This data sheet which is a part of type certificate No. 7A 6 prescribes conditions and limita tions under which the product for 
which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. 
 
Type Certificate Holder SUD AVIATION 
 
 
  (1)  This TC was surrendered for cancellation on October 27, 2009.  Only standard airworthiness 
certificates issued prior to October 27, 2009 are valid. 
(2)  Future unsafe conditions existing in the aircraft may result in the revocation of the 
airworthiness certificates of the aircraft if there is no entity to comply with 14 CFR 
§ 21.99(a), “Required design changes.” 
(3)  Replacement parts may not be available in the future. 
   
I - SUD AVIATION Caravelle SE 210 Model I (T ransport Category), approved April 8, 1959 
 Engines 2   Rolls-Royce Avon 522 turbojets 
 
 Fuel French: TRO (AIR 3405) 
  British: Aviation Kerose ne D.Eng. RD 2482 (AVTUR) 
      or D.Eng. RD 2494 (AVTUR/50) 
  American: JP-1 (MIL-F-5616) 
  Canadian: 3-GP-23B 
 
 Oil British: D.Eng. RD 2487 
  American: ESSO Aviation Turbo oil 35  
 
 Engine limits Static Sea Level Ratings  
 
 
Rating 
Minimum 
Thrust 
(lb.) 
 
Maximum 
R.P.M. 
Max. Turbine 
Gas Temp., 
°C 
Maximum takeoff (5 min.) 10,500 8,050 625 
Maximum continuous   9,125 7,650 575 
 
 Airspeed limits (CAS)   Knots  
  Vne (Never exceed) 325 or Mach 0.81 whichever is the lesser 
  Vno (Normal operation) 300 or M ach 0.77 whichever is the lesser 
  Va (Maneuvering) 174 
  Vfe (Flaps down 0° to 10°) 258 
  Vfe (Flaps down 10° to 20°) 202 
  Vfe (Flaps down 20° to 35°) 190 
  Vlo (Landing gear operation) 180 
  Vle (Landing gear extended) 218 
  Vllo (Landing light extension 215

Air brake operation 306 or Mach 0.81 
   Air brake extended 306 or Mach 0.81 
  Vmc (Minimum control) Less than the stalling speed 
 
 C.G. range (Landing Landing gear  retraction moment -79,860 in.-lb. (moves the C.G. forward) 
   gear extended)  
Weight Forward Aft 
(Pounds) % S.M.C. Aft of datum (in. ) % S.M.C. Aft of datum (in.) 
Up to 81,600 25 623.18 39.0 648.54 
95,900 25 623.18 35.8 642.75 
  Straight line variation between weights. 
 
 Maximum weights Taxi  96,500 lb. 
  Takeoff 95,900 lb. 
  Landing 91,335 lb. 
  Zero fuel 77,160 lb. 
 
 Minimum crew 3.  Pilot and copilot at (77), flight engineer at (102). 
 
 Maximum passengers 90.  (See a pproved weight and balance report for actual number and location) 
 
 Maximum luggage   Volume  Maximum floor Capacity 
    (Cu.ft.)   loading (p.s.f.)   (lb.)  
  Upper aft hold 212 82 2,120 (948) 
  Lower forward hold 194 62 1,940 (372) 
  Lower aft hold 88 62 880 (800) 
 
 Fuel capacity (See NOTE 1(b) for data on system fuel and oil) 
    Total Usable 
    (U.S. gal.)   (U.S. gal.)  
  2 inboard wing tanks 2,141.0 each 2,140 each (621) 
  2 outboard wing tanks 372.5 each 370 each (729) 
 
 Oil capacity (See NOTE 1(b) for data on system fuel and oil) 
  1.05 U.S. gal. per engine    Total oil 2.1 U.S. gal. (886) 
 
II - SUD AVIATION Caravelle SE 210 Model III (Transport Category), approved July 12, 1960 
Same as SE 210 Model I except for maximum weights, stabilizer se tting 1° up, engine installation,  engine silencer and wheels 
and brakes. 
 
 Engines 2 Rolls-Royce Avon 527 turbojets 
 
 Fuel French: TRO (AIR 3405) 
  British: Aviation Kerose ne D.Eng. RD 2482 (AVTUR) 
      or D.Eng. RD 2494 (AVTUR) 50 
  American: JP-1 (MIL-F-5616) 
  Canadian: 3-GP-23B 
    or 
  For aircraft on which modifi cation No. 227 has been applied: 
  French: (AIR 3407) 
  British: D.Eng. RD 2486 
  American: JP-4 (MIL-F-5624/C) 
  Canadian: 3-GP-22B 
 
 Oil British: D.Eng. RD 2487 
  American: ESSO Aviation Turbo oil 35 
 
 Engine limits Static Sea Level Ratings 
 
 
Rating 
Minimum 
Thrust 
(lb.) 
 
Maximum 
R.P.M. 
Max. Turbine 
Gas Temp., 
°C 
Maximum takeoff (5 min.) 11,400 8,050 675 
Maximum continuous   9,500 7,750 580

3 7A6 
 
 Airspeed limits (CAS)   Knots  
  Vne (Never exceed) 325 or Mach 0.81 whichever is the lesser 
  Vno (Normal operation) 300 or M ach 0.77 whichever is the lesser 
  Va (Maneuvering) 174 
  Vfe (Flaps down 0° to 10°) 258 
  Vfe (Flaps down 10° to 20°) 202 
  Vfe (Flaps down 20° to 35°) 190 
  Vlo (Landing gear operation) 180 
  Vle (Landing gear extended) 218 
  Vllo (Landing light extension) 215 
   Brake parachute 
     (Normal operation) 115 
     (Never exceed) 130 
   Air brake operation 325 or Mach 0.81 
   Air brake extended 325 or Mach 0.81 
  Vmc (Minimum control) Less than the stalling speed  
 
 C.G. range (Landing Landing gear  retraction moment -79,860 in.-lb. (moves the C.G. forward) 
   gear extended)  
Weight Forward Aft 
(Pounds) % S.M.C. Aft of datum (in. ) % S.M.C. Aft of datum (in.) 
Up to 81,600 25 623.18 39 648.54 
101,400 25 623.18 35 641.29 
  Straight line variation between weights. 
 
 Maximum weights Taxi  102,500 lb. 
  Takeoff 101,400 lb. 
  Landing   96,570 lb. 
  Zero fuel   78,260 lb. 
 
 Minimum crew 3.  Pilot and copilot at (77), flight engineer at (102). 
 
 Maximum passengers 90.  (See a pproved weight and balance report for actual number and location) 
 
 Maximum luggage   Volume  Maximum floor Capacity 
    (Cu.ft.)   loading (p.s.f.)   (lb.)  
  Upper aft hold 212 82 2,120 (948) 
  Lower forward hold 194 62 1,940 (372) 
  Lower aft hold 88 62 880 (800) 
 
 Fuel capacity (See NOTE 1(b) for data on system fuel and oil) 
    Total Usable 
    (U.S. gal.)   (U.S. gal.)  
  2 inboard wing tanks 2,141.0 each 2,140 each (621) 
  2 outboard wing tanks 372.5 each 370 each (729) 
 
 Oil capacity (See NOTE 1(b) for data on system fuel and oil) 
  1.05 U.S. gal. per engine    Total oil 2.1 U.S. gal. (886) 
 
III - SUD AVIATION Caravelle SE 210 Model VIR (Transport Category), approved June 5, 1961 
Same as SE 210 Model III except for maximum weights, engine installation, reversers, spoilers, windshield and cockpit, artificial 
feel (elevator and rudder control systems).  Vortex generators, and wheels and brakes. 
 
 Engines 2 Rolls-Royce Avon 532R or Avon 533R turbojets

Fuel American: JP-1 (MIL-F-5616) 
    JP-4 (MIL-F-5624C) 
  Canadian: 3-CP-23B, 3-CP-22B  
  British: D.Eng. RD 2482, 2494, 2486 
  French: TRO AIR 3405, AIR 3407 
 
 Oil ESSO Aviation Turbo Oil 35 
  ESSO Turbo Oil 35 (Also known as Penola Turbo Oil 35  or Humble Turbo Oil 35) 
  Castrol 98 Gas Turbine Oil 
  Texaco Synthetic Aircraft Turbo Oil 15 
 
 Engine limits Static Sea Level Ratings 
 
 
Rating 
 
MinimumThrust (lb.) 
Maximum 
R.P.M. 
Max. Turbine 
Gas Temp.,°C 
 532R 533R 532R 533R 532R 533R 
Maximum takeoff (5 min.) 12,080 12,600 8,050 8,150 670 685 
Maximum continuous 10, 710 10,710 7,900 7,900 595 595 
     EXCEPT WHEN: 
   Knots Mod. 1122 Mod. 1042 
    installed installed 
 
 Airspeed limits (CAS) 
  Vne (Never exceed) 350 325 345 or Mach .81 whichever is the lesser 
  Vno (Normal operation) 325 300 320 or Mach .77 whichever is the lesser  
  Va (Maneuvering) 190   (Sea Level) 
    213   (H = 39,300 ft.) 
  Vfe (Flaps down  0° to  5°) 270 
   (Flaps down  5° to 10°) 258 
   (Flaps down 10° to 20°) 202 
   (Flaps down 20° to 35°) 190 
  Vlo (Landing gear operation) 180 
  Vle (Landing gear extended) 245 
  Vllo (Landing light extension 215 
   Airbrake operation 350 325 345 or Mach .81 
   Airbrake extended 350 325 345 or Mach .81 
  Vmc (Minimum control) Less than the stalling speed 
 
 C.G. range (Landing Landing gear  retraction moment -85,930 in.-lb. (moves the C.G. forward) 
   gear extended)  
Weight Forward Aft 
(Pounds) % S.M.C. Aft of datum (in. ) % S.M.C. Aft of datum (in.) 
  Up to      
110,200 25 623.18 39 648.54 
 
 Maximum weights Taxi  111,300 lb. 
  Takeoff 110,200 lb. 
  Landing 105,000 lb. 
  Zero fuel   79,400 lb. 
      81,570 lb. (Mod. 1042 installed) 
 
 Minimum crew (See NOTE 4) 
  All operations except training, test and ferry flights  
  3.  Pilot and copilot at (77), flight engineer at (102). 
 
  Training, test and ferry flights  
  2.  Pilot and copilot at (77) 
 
 Maximum passengers 90.  (See a pproved weight and balance report for actual number and location)

5 7A6 
 
 
 Maximum luggage UAL Version  
  Mod. 712 installed  
 Maximum luggage   Volume  Maximum floor Capacity 
    (Cu.ft.)   loading (p.s.f.)   (lb.)  
  Left upper aft hold 120 122 1,200 (954) 
  Right upper aft hold 81 122 810 (950) 
  Lower forward hold 194 61 1,940 (372) 
  Lower aft hold 88 61 880 (800) 
 
  Mod. 998, 1188  
  Installed  
  Lower forward hold 222.5 61 3,065 (374) 
  Lower aft hold 116.5 61 1,575 (798) 
 
 Fuel capacity (See NOTE 1(b) for data on system fuel and oil) 
    Total Usable 
    (U.S. gal.)   (U.S. gal.)  
  2 inboard wing tanks 2,141.0 each 2,140 each (621) 
  2 outboard wing tanks 372.5 each 370 each (729) 
 
 Oil capacity (See NOTE 1(b) for data on system fuel and oil) 
  1.05 U.S. gal. per engine    Total oil 2.1 U.S. gal. (886) 
 
Data Pertinent to All Models 
 
 Datum Zero moment datum is located on the center lin e of the aircraft at the vertical line tangent  
  to the aircraft theoretical nose, i.e., 82.8 inch es forward of frame No. 7.  Horizontal arms  
  to the rear of the datum are positive (+). 
 
 Standard Mean chord 181.42 inches  The leading e dge of the standard mean chord is at+577.8 in. 
   (S.M.C.)  
 
 Leveling means Leveling plates in fo rward lower hold at Frames 22 and 25. 
 
 Control surface movements Elevator Up 30° Down 12° 
  Rudder Right 25° Left 25° 
  Aileron Up 21° Down 21° 
  Flaps  35° Total angle of travel 
  Upper airbrake Up 70° 
  Lower airbrake Down 75° 
  Spoilers Up 60° (for Model VIR only) 
 
 Maximum operating altitude 39,300 ft. 
 
 Other operating Aircraft shall be operated in compliance with the operating limitations specified 
   limitations in the S.G.A.C. approved Airplane Flight Manual. 
 
 Serial Nos. eligible The French Government Certifi cate of Airworthiness for export endorsed as noted under  
  "Certification basis" must be submitted for each individual aircraft for which application  
  for certification is made. 
 
 Certification basis CAR 10.  Type Ce rtificate No. 7A6 dated April 18, 1959. 
  Date of application for Type  Certificate September 30, 1955. 
 
  Each aircraft and any replacement part manuf actured in France must be clearly identified  
  as imported.

A U.S. Airworthiness Certificate may be  issued on the basis of Certificate of  
  Airworthiness for Export signed by a repr esentative of the Secretariat General a  
  l'Aviation Civile (S.G.A.C.) containing the following statement: 
 
   "The aeroplane covered by this certificat e has been examined and found to comply  
   with U.S. Civil Air Regulation Part  4b, effective December 31, 1953, including  
   amendments 4b1, 4b2, 4b4, 4b7, 4b9 a nd SR 422 A (Models I and III), SR 422 B  
   (Model VIR) and with the Special Require ments notified by the U.S. Government to  
   the French Government and conforms to T.C. 7A6." 
 
  Compliance with the ditching re quirements has been demonstrated. 
 
  Compliance with the ice protection require ments of CAR 4b.640 has been demonstrated. 
 
 Equipment The basic required equipm ent as prescribed in the applicable airworthiness regulations  
  (see Certification Basis) must be installed in the aircraft for certification.   
 
  The following additional equipment is required: 
    Weight  (lb.)  
  (a) Stall warning, 1 horn SANOR Model TR 2 2 (59) 
  (b) High speed warning according to SR 450A 
   1 horn SANOR Model J8 AV or 1 cling bell 2 (59) 
   BONVOISIN 4003/AF/G - (Mod. 1132 installed) 1 (59) 
  (c) Artificial feel device, Elevator Control System 
   SUD AVIATION drawing No. 27 06 003 51 (932) 
   (Models I and III) 
   SUD AVIATION drawing No. 27 06 801 (Model VIR) 69 (932) 
   Aileron Control System 
   SUD AVIATION drawing No. 17 50 425 17 (772) 
   Rudder Control System 
   SUD AVIATION drawing No. 27 07 003 44 (932) 
   (Models I and III) 
   SUD AVIATION drawing No. 27 07 295 (Model VIR) 60 (932) 
  (d) Control surface positions 
   Elevator: 
   1 transmitter AIR EQUIPEMENT Model 11501 1 (1145) 
   1 indicator AIR EQUIPEMENT Model 12504.01 1 (49) 
   Aileron: 
   1 transmitter AIR EQUIPEMENT Model 11501 1 (739) 
   1 indicator AIR EQUIPEMENT Model 12504.02 1 (49) 
   Rudder: 
   1 transmitter AIR EQUIPEMENT Model 11501 1 (1160) 
   1 indicator AIR EQUIPEMENT Model 12504.03 1 (49) 
 
NOTE 1. (a) Current weight and balance report including list of equipment included in the certificated empty 
weight, and loading instructions when necessary, must be provided for each aircraft at the time of 
original certification. 
 
  (b) "Unusable Fuel and System Oil " and all hydraulic fluid must be included in the certificated empty  
   weight. 
 
   "Unusable Fuel  is that quantity of fuel in the system and in the tanks which is unavailable to the 
engine under critical flight conditions as defined in CAR 4b.416. This unusable fuel includes "system 
fuel" which is defined as the quantity required to fill the system and tanks to the tank outlet level 
when the airplane is on the ground level attitude.  The fuel gauges are calibrated with the unusable 
fuel as the zero datum.

7 7A6 
 
 
   The total amount of  fuel is as follows: 
    Usable fuel   Unusable fuel  
    5020 U.S. gal. 7 U.S. gal. 
 
   System oil  is that amount of oil required to fill the oil system and tanks and is completely contained  
   within the engine. 
   System oil weight is 31 lb. 
   The oil tank capacity shown in the da ta sheet includes only the usable oil. 
   A sight glass allows to check the oil level. 
 
NOTE 2. The following is a list of aircraft parts which are critical from the fatigue standpoint and must be  
  replaced at the times specified: 
   2 Pressure regulators, LOCKH EED-ENGLAND Model AIR 43444    6,000 hours 
 
NOTE 3. All aircraft must be maintained and repaired in  accordance with the French Government approved Maintenance 
and Structural Repair Manuals. 
 
NOTE 4. Aircraft incorporating SUD Mod. 1126 may be flown with a minimu m crew as shown on page I.4.1 of 
S.G.A.C. approved Airplane Flight Manual SE 210 655. 
 
NOTE 5. Sud/Lear Autoland Installation - SE 210 Model VI R.  
 
If Sud Modifications Nos. 1186, 1357 and 1358 have been incorporated in accordance with Caravelle Service 
Bulletin No. 22.33, operation of the autopilot is author ized down to 50 feet.  (The above equipment complies 
with FAA Advisory Circular A.C. 20-31). 
 
 
 
 
 
.....END.....
```

## ADs (20, in force first)

- [AD 91-06-19](https://openairdocs.org/ad/91-06-19): Main Landing Gear · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Apr 1, 1991
- [AD 90-25-13](https://openairdocs.org/ad/90-25-13): Rear Spar · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Jan 7, 1991
- [AD 90-14-03](https://openairdocs.org/ad/90-14-03): Wing Spar · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Aug 3, 1990
- [AD 90-11-03](https://openairdocs.org/ad/90-11-03): Main Landing Gear Struts · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Jun 19, 1990
- [AD 90-11-07](https://openairdocs.org/ad/90-11-07): Wing Ribs · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Jun 19, 1990
- [AD 90-10-01](https://openairdocs.org/ad/90-10-01): Wing-To-Fuselage Junction Fittings · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Jun 1, 1990
- [AD 90-08-02](https://openairdocs.org/ad/90-08-02): Nose Landing Gear Well · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective May 4, 1990
- [AD 90-07-09](https://openairdocs.org/ad/90-07-09): Passenger Door · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective May 1, 1990
- [AD 88-06-05](https://openairdocs.org/ad/88-06-05): Wing Ribs · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Apr 22, 1988
- [AD 88-04-08](https://openairdocs.org/ad/88-04-08): Main Landing Gear Shafts · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Apr 5, 1988
- [AD 85-14-07](https://openairdocs.org/ad/85-14-07): Wing Rib · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Aug 16, 1985
- [AD 83-05-06](https://openairdocs.org/ad/83-05-06): Structural Inspection · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Apr 11, 1983
- [AD 71-20-03](https://openairdocs.org/ad/71-20-03): Relay In Elevator Servodyne Circuit · Sud Caravelle SE 210 Model VIR. Effective Oct 18, 1971
- [AD 71-19-02](https://openairdocs.org/ad/71-19-02): Hydraulic System · Sud Caravelle SE 210 Model VIR. Effective Sep 27, 1971
- [AD 64-27-03](https://openairdocs.org/ad/64-27-03): Main Landing Gear Beams · Sud Caravelle SE 210 Model VIR. Effective Jan 1, 1965
- [AD 64-20-02](https://openairdocs.org/ad/64-20-02): Main Landing Gear · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Sep 21, 1964
- [AD 63-27-04](https://openairdocs.org/ad/63-27-04): Nose Wheel Tires · Sud Caravelle SE 210 Model I, Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Jan 27, 1964
- [AD 63-17-07](https://openairdocs.org/ad/63-17-07): Horizontal Stabilizer Attach Structure · Sud Caravelle SE 210 Model VIR. Effective Sep 13, 1963
- [AD 63-08-05](https://openairdocs.org/ad/63-08-05): Flight Control System · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective May 20, 1963
- [AD 63-04-03](https://openairdocs.org/ad/63-04-03): Trim Controls · Sud Caravelle SE 210 Model III and Caravelle SE 210 Model VIR. Effective Mar 12, 1963

## STCs approved under this data sheet (8)

- [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc.
- [STC SA863EA](https://openairdocs.org/stc/SA863EA): Incorporation of DME Corporation emergency evacuation slide lighting system. Astronics Luminescent Systems Inc
- [STC SA1121WE](https://openairdocs.org/stc/SA1121WE): Installation of Cockpit Voice Recorder, United Data Controls, per United Air Lines Report F-1031 dated June 16, 1965, Revision, dated August 24, 1965, or later FAA approved revision.. United Airlines Inc
- [STC SA2139WE](https://openairdocs.org/stc/SA2139WE): :   Installation of Automatically Deployed (two step) Inflatable Emergency Evacuation Slides in accordance with FAA Approved United Air Lines Drawing List No. COA 1-1013.. United Airlines Inc
- [STC SA835WE](https://openairdocs.org/stc/SA835WE): Temporary installation of closed-circuit television and auto-land display board per United Air Lines Change Order Authorization No. 1-812 and Report No. F-972.. United Airlines Inc
- [STC SA2728WE](https://openairdocs.org/stc/SA2728WE): Incorporation of Holcombe Industries HI-LITE SYSTEM P/N 50-1001 for emergency evacuation slide lighting. (707 AIRPLANES EQUIPPED WITH BOEING P/N 65-11685 AND 65-68862 FORWARD THRUST REVERSER DOORS). Maravia Corp of Idaho
- [STC SA36NW](https://openairdocs.org/stc/SA36NW): Installation of Sundstrand Ground Proximity Warning System. Sundstrand Data Control Inc
- [STC SA1583WE](https://openairdocs.org/stc/SA1583WE): Installation of Fairchild Model13920-301 or 15830-601 flight data recorder and Honeywell P/N 180 VI central air data computer.. United Air Lines Inc

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