# TCDS A15EU: De Havilland Aircraft of Canada Limited

- Type: Type certificate data sheet
- Status: Current
- Holder: De Havilland Aircraft of Canada Limited
- Revision: 12
- Revised: October 19, 2026
- Product: Aircraft, Small Airplane
- Certification basis: Part 21, Part 23
- Data sheet PDF: https://openairdocs.org/files/sha256/9d/a8/9da8f09520538bfce051115d411644565225261677c079aeee5422265555192c
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID111901207320261019140512.0001
- Page: https://openairdocs.org/tcds/A15EU

## Models (2)

As the data sheet lists them.

- SC-7 Skyvan Series 3
- SC-7 Skyvan Series 2

## What the data sheet says

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

```text
A15EU 
Revision 12 
De Havilland 
SC-7 Series 2 
SC-7 Series 3 
 
October 19, 2026 
I - Model SC-7 Skyvan Series 2, Variant 200, 20 PCLM (Normal Category), Approved 1 June 1967 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET NO. A15EU 
This Data Sheet, which is a part of Type Certificate No. A15EU, 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 De Havilland Aircraft of Canada Limited 
4100 Westwinds Drive NE 
 Calgary, Alberta 
 Canada T3J 4L2 
Type Certificate Holder Record Shorts Brothers & Harland Ltd. transferred TC A15EU to Viking Air Limited on June 28, 
2019. (See Note 14) 
 Viking Air Limited transferred TC  A15EU to De Havilland Aircraft of Canada Limited on August 1, 
2024 
 
Engine 2 Turbomeca Astazou XII Model H-1 (Propeller Turbine) 
 
Fuel Specifications, latest issue, (See NOTE 6) 
American British 
 
 
 
 
To prevent icing of fuel system components, all fuel in the tanks before takeoff must 
contain anti-icing additives in accordance with the limitations of NOTE 6, when route 
forecast air temperatures are less than 6°C. 
 
Engine limits Static Ratings 
The static ratings for the Astazou XII H-1 engine are specified under the following test 
conditions: 
International Standard Atmospheric Conditions at Sea Level. 
All optional air bleeds closed. 
Aircraft service accessory drives unloaded. 
100% = 42574 rpm 
 
  Jet Thermic  Jet Pipe 
Conditions 
SHP 
(Min.) 
Thrust 
(lb.) 
Load 
(Power) 
RPM 
(Max.) % 
Temp. (JPT) 
(C) 
Takeoff and      
Maximum Cont. 630 97 100% 101.0 520 
 
See ARB-Approved Flight Manual, Document SBH.2.4 for additional engine operating 
limitations.  
 
 
Page No. 1 2 3 4 5 6 7 8 9 
Rev. No. 12 10 10 10 10 10 10 10 11 
JP-1 (MIL-F-5616) o r D.Eng.RD.2482 an d 2494 
JP-4 (MIL-J-5624) o r D.Eng.RD.2486 
JP-5 (MIL-J-5524) o r D.Eng. RD.2488 
JP-5 (MIL-J-5624) o r D.Eng.RD.2498

Page 2 of 9 A15EU 
 
 
 
Propeller and 2 Ratier-Forest Type FH 76-2-07 B reversible propellers. 
propeller limits 
Blades : 3 Type 207 
Diameter : 8 ft. - 2.4 ins. 
 
Pitch setting at 0.7 radius stations: 
Ground fine - 5° 
Flight fine + 7 1/2° 
Feathered 84° 
Full Reverse - 11° 
 
Airspeed limits (IAS)  Vne (Never exceed) 200 Kt. 
Max. Structural Cruising 178 Kt. 
Va (Maneuvering) 144 Kt. 
Vfo (Flap Operation) 
Takeoff 130 Kt. 
Landing 100 Kt. 
Vfe (Flaps Extended) 
Takeoff 130 Kt. 
Landing 115 Kt. 
Vmc (Min. Control Speed) 67 Kt. 
(See NOTE 8(a)) 
 
Maximum weights Takeoff 12,300 lbs. 
Landing 12,300 lbs. 
(See NOTE 7 for short range fuel tanks) 
 
Maximum baggage Baggage and/or cargo must be loaded in accordance with the Weight and Balance 
Supplement of the ARB-approved Flight Manual. 
 
Fuel capacity 283 U.S. Gals total in 2 tanks 
276 U.S. Gals usable 
(See Note 1 (b) for data on system fuel) (See Note 7 for short range fuel tanks). 
 
Oil capacity 2.25 U.S. Gals/tank on each engine. 
0.8 U.S. Gals/tank usable 
Total capacity 4.5 U.S. Gals 
Total usable = 1.6 U.S. Gals (5.3 pints/Engine) 
(See NOTE 1 (b) for data on system oil) 
Other operating Aircraft shall be operated in compliance with the Operating limitations 
Limitations specified in the ARB-Approved Aircraft Flight Manual Doc. No. SBH/2.4. 
 
Control surface movements 
 
 
 
 
 
 
 
 
I - Model SC-7 Skyvan Series 2, Variant 200  (cont'd) 
Elevator Up 35° Down 12° 
Elevator Trim Tab Up 11-3/4° Down 16° 
Rudder Right 30° Left 30° 
Rudder Trim Tab Right 21° Left 24 1/4° 
Aileron Up 30° Down 15° 
Aileron Trim Tab Up 44-3/4° Down 28-3/4° 
Flaps Inner and Outer   Down Landing 45° 
   Down Take Off 18° 
(See NOTE 8 (b))

Page 3 of 9 A15EU 
 
 
 
(The Series 3 is similar to the Series 2 except for powerplant installation and increased fuel capacity.) 
Engine 2 Garrett AiResearch Model TPE 331-2-201A (Propeller Turbine) 
Fuel Specifications, latest issue, (See NOTE 6) 
 
American British Canadian  
MIL-F-5616-1, Grade JP-1 D.Eng.RD.2482 Arctic Diesel 
MIL-T-5624G-1, Grade JP-4 D.Eng.RD.2486 CPW-46 Rev. A 
MIL-T-5624G-1, Grade JP-5 D.Eng.RD.2494 (equivalent to 
MIL-F-46005A (MR)-1,  AiResearch Mfg. Co., 
Types I and II  of Arizona-Spec. 
ASTM D1655-68T, Types Jet A  EMS 53100) 
and Jet A-1 
ASTM D1655-68T, Type Jet B 
 
Engine limits Static Ratings 
The static ratings for the Garrett TPE 331-2-201A engine are specified under the following 
test conditions: 
U.S. Standard Atmospheric Conditions at Sea-Level. 
All optional air bleeds closed. 
Aircraft service accessory drives unloaded. 
100% = 41730 rpm 
Compensated 
 
ESHP SHP Net Thrust 
Prop 
Shaft 
Measured 
Exhaust Gas 
Conditions (Min.) (Min .) lb. (Min.) RPM Temp.C (Max) 
Takeoff (5 min.)      
and Max. Cont. 755 715 102 2000 578 
 
See ARB-Approved Flight Manual, Document SBH.2.5 for additional engine operating 
limitations. 
 
Propeller and 2 Hartzell HC-B3TN-5C reversible propellers 
propeller limits 
Blades : 3 Type T 10282 HB 
Diameter  : 8 ft. - 6 ins. 
 
Pitch setting at 30 in. radius stations: 
Ground fine - 2 1/2° 
Flight fine + 9 1/4° 
Feathered 85° 
Full Reverse - 6° 
 
Airspeed limits (IAS) Vne (Never exceed) 200 Kt. (Pre.Mod.1019 only) 
Vno (Normal Operating) 173 Kt. (Pre.Mod.1019 only) 
Vmo (Maximum Operating) 173 Kt . (Post Mod.1019, See NOTE 12) 
Va (Maneuvering) 140 Kt. 
Vfo (Flap Operation) 
Takeoff 128 Kt. 
Landing 98 Kt. 
Vfe (Flaps Extended) 
Takeoff 128 Kt. 
Landing 110 Kt. 
Vmc (Min. Control Speed) 65 Kt. 
 
Maximum weights Takeoff 12,500 
Landing 12,500 lbs. 
 
II - Model SC-7 Skyvan Series 3, Variant 200, 20 PCLM (Normal Category), Approved June 7, 1968

Page 4 of 9 A15EU 
 
 
 
Maximum baggage Baggage and/or cargo must be loaded in accordance with the Weight and Balance 
Supplement of the ARB-approved Flight Manual. 
Fuel capacity 354 U.S. Gals total in 2 tanks 
348 U.S. Gals usable 
(See NOTE 1 (b) for data on system fuel) 
 
Oil capacity 1.75 U.S. Gals/tank on each engine. 
0.3 U.S. Gals/tank usable 
Total capacity 3.5 U.S. Gals 
Total usable 0.6 U.S. Gals 
(See NOTE 1 (b) for data on system oil) 
 
Other operating Aircraft shall be operated in compliance with the Operating Limitations specified 
limitations in the ARB-Approved Aircraft Flight Manual Document No. SBH/2.5. 
 
Control surface movements Elevato r Up 35° Down 12° 
 Elevator Trim Tab Up 4° Down 5° 
 Rudder Right 30° Left 30° 
 Rudder Trim Tab Right 17° Left 21° 
 Aileron Up 30° Down 15° 
 Aileron Trim Tab Up 44-3/4° Down 28-3/4° 
 Flaps Inne r and Outer Down Landing 50° 
  Down Take Off 18° 
 
DATA PERTINENT TO ALL MODELS 
 
C.G. Limits 
(See NOTE 10.) 
 
 
 
Datum Located on center line of aircraft vertical ly below leading edge of wing, which is at 
Sta. 152. Horizontal moment arms to the rear of the datum are positive. 
 
Standard mean chord (SMC)  70.0 ins. Leading edge of SM C is coincident with wing leading edge. Standard Mean 
Chord is defined by the wing area divided by wing span, where the wing area includes that 
area of the fuselage enclosed by the leading and trailing edges of the wing projected to the 
center line of the airplane. 
 
Leveling means Internal datum plates are fitted, 2 on front spar frame and 1 on rear spar frame. 
Minimum crew 1 pilot unless otherw ise specified by operating rules. 
Maximum passengers 20 
Maximum operating 20,000 ft. when supplemental oxygen is provided for the crew and 
altitude passengers in accordance with the applicable operating rules. 
Serial Nos. eligible The United King dom Certificate of Airworthiness for Export, endorsed as noted below 
under Import Requirements, must be submitted for each individual aircraft for which 
application for FAA Airworthiness Certification is made. 
II - Model SC-7 Skyvan Series 3, Variant 200  (cont'd) 
Forward Limit 
Aft of Datum 
(In.) 
 
% SMC 
10 14.30 
Aft Limit 
Aft of Datum 
(In.) 
 
% SMC 
22.4 32.0

Page 5 of 9 A15EU 
 
Certification basis FAR 21.29. FAR Pa rt 23 effective February 1, 1965 including Amendments 23-1, 23-2, 
23-3, plus Special Conditions notified by the U.S. Government to the Government of the 
United Kingdom and Northern Ireland in FAA letters of April 1, 1966 and October 19, 1966. 
 
Type Certificate A15EU issued June 1, 1967. 
Date of Application for Type Certificate: February 17, 1966. 
 
The Series 3 airplane type design with the following modifications incorporated was 
approved in accordance with Special Federal Aviation Regulation No. 23 on 26 June 1970. 
1. Mod. 970 or 971 : Addition of Rear Passenger Doors (2). 
2. Mod. 1019 : Revised A.S.I. marking for Vmo. 
3. Mod. 1042 : Alternate Static Source in S2 Static System. 
4. ARB Approved Flight Manual Doc. No. SBH.2.5, Amdts. G/5, G/6, and G/7. 
 
The United Kingdom Civil Aviation Authority originally type certificated this aircraft 
under its type certificate. The FAA validated this product under U.S. Type Certificate 
Number A15EU. Effective September 28, 2003, the European Aviation Safety Agency 
(EASA) began oversight of this product on behalf of the United Kingdom. Currently there 
is not an EASA TCDS number for this airplane. 
 
 
 
 
Import requirements The FAA can issue a U.S. airworthin ess certificate based on an NAA Export Certificate of 
Airworthiness (Export C of A) signed by a representative of the United Kingdom Civil 
Aviation Authority 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 comply with U.S. airworthiness regulations 14 CFR Federal 
Aviation Regulations Part 23, effective February 1, 1965 including Amendments 23-1, 23- 
2 and 23-3 plus Special Conditions notified by the U.S. Government to the Government of 
the United Kingdom and Northern Ireland in their letters April 1, 1966 and October 19, 
1966 under U.S. Type Certificate No. A15EU and to be in a condition for safe operation.’ 
 
 
Service Information  Each of the documents listed below mu st state that it is approved by the European Aviation 
Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the Air 
Registration Board Through the manufacturers ARB Approval, Ref: AD/1023/45, or the 
United Kingdom Civil Aviation Authority. 
 
• Service bulletins, 
• Structural repair manuals, 
• Vendor manuals, 
• Aircraft flight manuals, and 
• Overhaul and maintenance manuals. 
 
The FAA accepts such documents and considers them FAA-approved for type design data 
only unless one of the following conditions exists: 
 
• The documents change the limitations, performance, or procedures of the FAA 
approved manuals; or 
 
• The documents make an acoustical or emissions changes to this product’s U.S. type 
certificate as defined in 14 CFR § 21.93. 
 
The FAA uses the post type validation proce dures to approve these documents. The FAA 
may delegate on case-by-case to EASA to approve on behalf of the FAA for the U.S. type 
certificate. If this is the case it will be noted on the document.

Page 6 of 9 A15EU 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see 
Certification Basis) must be installed in the aircraft for certification. 
 
For Series 2 aircraft: See SBH pub lication reference SC/-SVE-1 details. 
 
For Series 3 aircraft: See SBH pub lication reference SC7-EAS/1 details. 
 
In addition the following items of equipment are required:- 
(a) Stall Warning Indicator (Safe Flight Ltd. Type No. 165). 
(b) ARB Approved Flight Manual Doc. No. SBH.2.4 (for Series 2 aircraft). 
(c) ARB Approved Flight Manual Doc. No. SBH.2.5 (for Series 3 aircraft). 
 
NOTES: 
 
NOTE 1. (a)  Current weight and balance report including list of equipment included in certified empty weight, and loading 
instructions when necessary, must be in each aircraft at the time of original certification and at all times 
thereafter (except in the case of operators having an approved weight control system). 
 
(b) "Unusable Fuel and System Oil" and all hydraulic fluid must be included in the certified 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 FAR. 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 in the ground level 
altitude. The fuel gauges are calibrated with the unusable fuel level as the zero datum. Th e total amount of 
fuel is as follows: 
Usable Fuel Unusable Fuel 
(@ 6.5 lb./U.S. Gal.) (@ 6.5 lb/U.S. Gal.) 
 
Series 2 aircraft: 
1794 lb 24 lb (This excludes 14 lb undrainable fuel plus 6 lb. for 
1359 lb (with short range fuel  zeroing fuel gauges. 
tanks Mod. 136) 
Series 3 aircraft: 
2262 lb 20 lb (This excludes 14 lb undrainable fuel plus 6 lb for 
zeroing fuel gauges) 
 
System Oil is that amount of oil required to fill the oil systems and engine sumps up to the sump outlet to 
the engines. The oil capacities shown in this specification include only usable oil. Dipstick readings 
indicate the amount of usable oil. 
 
NOTE 2. All placards required in the Limitations Section of ARB-approved Airplane Flight Manual must be installed in the 
appropriate location. 
 
NOTE 3. The service life limits for aircraft structural parts wh ich are fatigue critical are listed in the Approved Airplane 
Maintenance Manuals S.B. & H. Publication SC-7-AMM-1 for Series 2 aircraft and S.B. & H. Publication 
SC-7-AMM-3 for Series 3 aircraft. 
 
NOTE 4. Each individual Airplane must be fitted with a placar d which specifies approved types of operation (such as VFR, 
IFR, Day or Night) to which the airplane is limited by the equipment installed. 
NOTE 5. No load shall be placed on the rear door. 
NOTE 6. Fuel Additives 
Only the following additives may be used with the specified fuels: 
Series 2 aircraft:- 
Anti-icing additives to MIL-L-2768D (or D.Eng. R.D.2451) provided that the concentration does not exceed 
0.15% by volume. 
 
Anti-static additive Shell ASA 3 in concentrations not exceeding 0.75 ppm in kerosene or 0.60 ppm in wide 
cut fuel. 
 
The following anti-icing additives comply with approved specifications:

Page 7 of 9 A15EU 
 
Phillips PFA 55MB 
Hoffman - Taff Inc. PRIST fuel additive. 
Shell - Max and BP Limited fuel additive MG 98/2A 
 
Concentration by volume of fuel in aircraft tanks will be within the following limits: 
Minimum 0.035% Maximum 0.15% 
 
Series 3 aircraft:- 
The following additives may be used with the specified fuels: 
a) Anti-static additive Shell ASA 3 in concentrations not exceeding 1.0 ppm. 
b) MIL-I-27686D Inhibitor Fuel System Icing in amounts not to exceed 0.15% by volume. 
 
NOTE 7. For Series 2 aircraft with M odification 136 "Introduction of short range fuel tank" embodied, the following apply:- 
 
Maximum Weights: Take-off 12,020 lb 
Landing 12,020 lb 
 
Fuel Capacity: 216 U.S. Gals. total in 2 tanks 
209 U.S. Gals. usable 
NOTE 8. For Series 2 aircraft with incorporation of: 
Modification 196 - Introduction of drooped leading edge inboard of engine nacelle 
 
Modification 251 & Introduction of airframe fluid de-icing system 
252 
Modification 336 Increase maximum flap angle to 50° the following apply: 
 
(a) Airspeed Limits Vfo (Flap Operation) Landing 99 kt. 
Vfe (Flap extended) Landing 112 kt. 
Vmc (Minimum Control Speed)  71 kt. 
(b) Control Surface Movement Flaps inner and outer 50° down landing. 
 
NOTE 9. Compliance has been demonstrated for operation into known or predicted icing conditions for airplanes that have 
Goodrich de-icing boots or T.K.S. fluid de-icing system installed on the leading edges of the wing, stabilizer 
and fin. 
 
NOTE 10. For Series 3 aircraft with M odification No. 837 incorporated, which alters the elevator trim tab movement, the 
following apply: 
 
Control Surface Movement Elevator trim tab 7° up 5° down 
C.G. Limits (+10 in) to (+25 in) 
 
NOTE 11. For series 3 aircraft with incorporation of:- 
Modification 269 : Strengthened rear fuselage longerons 
Modification 295 : Alteration to door locking structure 
Modification 1012 : Flight Limitations Pla card/Rear freight door open or removed. 
 
These aircraft are cleared for flight with the rear freight door opened or removed in accordance with the Limitations 
and Procedures contained in the relevant Flight Manual supplement No. 2 Issue 4, to Doc. No. SBH. 2.5. 
 
NOTE 12. For Series 3 aircraft  with incorporation of:- 
Modification 1019 : Revised A.S.I. Color Markings the following applies: 
Airspeed Limits. 
Vne (Never Exceed Speed) and the Maximum Structural Cruising Speed are replaced by 
Vmo (Maximum Operating Limit Speed) which is established as 173 kts.

Page 8 of 9 A15EU 
 
NOTE 13. SKYVAN 3 Series 
VARIANT 100 (U.K.) CONVERSION TO VARIANT 200 (U.S.A.) 
The following lists additions, deletions, and changes required to convert a Variant 100 Skyvan, to a 
Variant 200 Skyvan. 
 
1) Flight Deck Entrance Door Barrier 
Barriers to be fitted to Port and Starboard Flight Deck Doors, in accordance with 
DRG SC7-10-1743/4. (No serv ice bulletin available.) 
2) Mod 1638 Ditching Hatch 
Ditching Hatch required in roof of flight deck. (No service bulletin available but Mod Covers 
Instructions for Retro-Fit). 
3) Mod 993 A.S.I. Limitation Placard 
Existing A.S.I. Limitation Placard on ID Panel to be replaced with A.S.I. Limitation Placard 
SC7-18-5409. (Service Bulletin 31-51 applies.) 
 
4) Mod 1114 Operations Placard 
Existing Operations Placard SC7-18-410 on ID panel to be replaced with Placard SC7-18-5771. 
(Service Bulletin 11-58 applies.) 
 
5) Mod 1514 Engine Fuel Purge System 
To conform with U.S.A. environmental protection agency fuel venting requirements (if 
applicable) embody Shorts Service Bulletin 73-50, also Airsearch Bulletin TPE 331-73-0035 will 
be required to be embodied concurrently. 
 
6) Altimeter 
Replace milibar scale with inches hg in accordance with one of the following modifications. 
Mod 848 - Weston Type 22-374A-01-2 
Mod 1439 - EDO Aire Type 22-374A-2 
Mod 1671 - Aerosonic Type 10173-01467 (dual scale) 
 
NOTE. Altimeter panel cutouts and pipe ends may require alterations, refer to Drawing called 
for on Respective Modifications. (N o Service Bulletins available.) 
 
7) 30 Flap Position (Mod 972) 
Delete 30 flap position as follows: 
 
Refer to Drawing SC7-45-3549 
Remove flap gate SC7-45-5079 (Item 2) 
Remove label SC7-18-5434 (Item 13) 
 
SC7-18-5433 (Item 14) 
Removel label or 
SC7-18-5642 (Item 15) 
 
Fit flap gate SC7-45-3507 (Item 1) 
Fit label SC7-45-3523 (Item 11) 
Fit label SC7-45-3522 (Item 12) 
 
Refer to DRG SC7-80-5000 (Installation of IP Panel) 
Delete 30 flap position mark introduced by Drg SC7-80-5298 (Item 26) from the flap 
indicator gauge. 
Gauge now meets the requirements of DRG SC7-80-5298 (Item 22). 
Flap Detent (18  Position) 
It is not a requirement to reinstate the detent at the 18 flap position, which was deleted 
as part of Mod 972.

Page 9 of 9 A15EU 
 
8) Registration Plate 
Existing manufacturers plate SC7-18-5363 (B.C.A.R.) to be removed and replaced with plate 
conforming to the requirements of Drawing SC7-18-5354 (FAA). 
9) Flight Manual 
Existing flight manual to be returned when actions 1 to 8 are completed. 
CAA to issue new flight manual (Doc SBH 2.5). 
 
NOTE 14. The TC transfer from Shorts Brothers & Harland Limited (Shorts Brothers) to Viking Air Limited is also 
a state of design change from the European Aviation Safety Agency (EASA) to Transport Canada 
(TCCA). 
 
 
 
.....END.....
```

## ADs (22, 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 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 2015-04-01](https://openairdocs.org/ad/2015-04-01): Landing Gear · Short Brothers & Harland SC-7 Skyvan Series 3. Effective Mar 30, 2015
- [AD 2003-17-05 R1](https://openairdocs.org/ad/2003-17-05-R1): Replacement os certain life limited items · Short Brothers SC-7 Skyvan Series 2 and SC-7 Skyvan Series 3. Effective Mar 23, 2007
- [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 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 2003-13-07](https://openairdocs.org/ad/2003-13-07): Flight Control System Rods · Short Brothers SC-7 Skyvan Series 2 and SC-7 Skyvan Series 3. Effective Aug 11, 2003
- [AD 2000-02-16](https://openairdocs.org/ad/2000-02-16): Wing Attachment Bushes · Short Brothers SC-7 Skyvan Series 2 and SC-7 Skyvan Series 3. Effective Mar 20, 2000
- [AD 83-14-01](https://openairdocs.org/ad/83-14-01): Flap Attachments · Short Brothers SC-7 Skyvan Series 3. Effective Aug 19, 1983
- [AD 83-07-04 R1](https://openairdocs.org/ad/83-07-04-R1): Flight Control System · Short Brothers SC-7 Skyvan Series 3. Effective Jun 23, 1983
- [AD 83-07-16](https://openairdocs.org/ad/83-07-16): Vertical Fin · Short Brothers SC-7 Skyvan Series 3. Effective Apr 14, 1983
- [AD 83-07-21](https://openairdocs.org/ad/83-07-21): Cargo Door Locking Pin · Short Brothers SC-7 Skyvan Series 3. Effective Apr 14, 1983
- [AD 83-07-08](https://openairdocs.org/ad/83-07-08): Ground/Air Lever Mechanism · Short Brothers SC-7 Skyvan Series 3. Effective Apr 11, 1983
- [AD 83-06-08](https://openairdocs.org/ad/83-06-08): MLG Brake Flange · Short Brothers SC-7 Skyvan Series 3. Effective Apr 4, 1983
- [AD 81-06-03](https://openairdocs.org/ad/81-06-03): Aileron Servo Control Cable · Short Brothers SC-7 Skyvan Series 3. Effective Mar 19, 1981
- [AD 77-24-02](https://openairdocs.org/ad/77-24-02): Flap Support Structure · Short Brothers SC-7 Skyvan Series 3. Effective Nov 28, 1977
- [AD 70-15-12](https://openairdocs.org/ad/70-15-12): Engine Drain Line · Short Brothers SC-7 Skyvan Series 3. Effective Jul 23, 1970
- [AD 70-15-05](https://openairdocs.org/ad/70-15-05): Altimeter Stand-By Correction Label · Short Brothers SC-7 Skyvan Series 3. Effective Jul 20, 1970
- [AD 69-26-01](https://openairdocs.org/ad/69-26-01): Flap Shroud Attachment Lugs · Short Brothers SC-7 Skyvan Series 2 and SC-7 Skyvan Series 3. Effective Dec 16, 1969
- [AD 67-23-05](https://openairdocs.org/ad/67-23-05): Automatic Fire Extinguishers · Airbus BAC 1-11 200 Series, BAC 1-11 400 Series, DH.125 Series 1A and 10 more
- [AD 2003-17-05](https://openairdocs.org/ad/2003-17-05) (historical): Life limited items · Short Brothers SC-7 Skyvan Series 2 and SC-7 Skyvan Series 3. Effective Sep 29, 2003
- [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

## STCs approved under this data sheet (54, first 50)

- [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 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 SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA02254AK](https://openairdocs.org/stc/SA02254AK): Installation of "Single Screen", "2 or 3 Screen", "Dual Screen", or "4 or 6 screen". Genesys Aerosystems Inc.
- [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC
- [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King)
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc
- [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA02153LA-D PAGE 2](https://openairdocs.org/stc/SA02153LA-D%20PAGE%202): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 2](https://openairdocs.org/stc/SA00352BO%20PAGE%202): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA02119SE PAGE 2](https://openairdocs.org/stc/SA02119SE%20PAGE%202): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA01229SE PAGE 2](https://openairdocs.org/stc/SA01229SE%20PAGE%202): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA02442AK PAGE 2](https://openairdocs.org/stc/SA02442AK%20PAGE%202): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01933LA-D PAGE 2](https://openairdocs.org/stc/SA01933LA-D%20PAGE%202): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc
- [STC SA02149AK](https://openairdocs.org/stc/SA02149AK): Installation of GX50/60 GPS Navigator, Capstone configured MX20 Multi-Function Display and UAT transceiver.. Garmin International Inc
- [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc
- [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation
- [STC SA02016SE-D](https://openairdocs.org/stc/SA02016SE-D): Installation of Garmin GTS 800, GTS 820 or GTS 850 Traffic System. Garmin International Inc
- [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc
- [STC SA00243BO](https://openairdocs.org/stc/SA00243BO): Installation of Centurion Consulting, Inc. GPS Steering Assist Module (SAM) with roll steering (p/n 0025-5100), or without roll steering (p/n 0025-5200).. Icarus Avionics, LLC
- [STC SA00681WI-D](https://openairdocs.org/stc/SA00681WI-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. Rockwell Collins Inc
- [STC SA02018SE-D](https://openairdocs.org/stc/SA02018SE-D): Provisions installation of Garmin GPS/XM Antennas in accordance with FAA Approved Model List (AML) SA02018SE-D, dated January 4, 2011, or later FAA approved revision, and FAA Approved GPS/XM Antenna STC Master Drawing List, Document No.: 005-00638-01, Revision 1 , approved on January 4, 2011, or later FAA approved revision.. Garmin International Inc
- [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc.
- [STC SA03228AT](https://openairdocs.org/stc/SA03228AT): Replacement of existing propeller with Mt-Propeller Model MTV-27-1-E-C-F-R(G)/R235-55 and Spinner.. MT-Propeller USA Inc.
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc.
- [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies
- [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA02154AK](https://openairdocs.org/stc/SA02154AK): Installation of the UPS Aviation Technologies Inc. Apollo MX20 multi-function display, P/N 430-0270-500.. Garmin AT Inc.
- [STC SA02217AK](https://openairdocs.org/stc/SA02217AK): Installation of Garmin AT Model GDL90 UAT Data Link System, in accordance with Garmin AT, Inc., GDL 90 UAT Master Data List, P/N 560-0278-01, Revision A, dated November 12, 2004, or later FAA approved revision.. Garmin AT Inc.
- [STC SA00823CH](https://openairdocs.org/stc/SA00823CH): Installation of various de-icer wire harnesses.. SMR Technologies
- [STC SA02168AK](https://openairdocs.org/stc/SA02168AK): Installation of hourmeter airspeed switch. For unpressurized aircraft only. Pressurized aircraft must have pressurization system deactivated.. Avalaska Inc
- [STC SA812NE](https://openairdocs.org/stc/SA812NE): Installation of BF Goodrich Model 6975-1 De-Icer kit or BF Goodrich Model 6975-10 De-Icer kit.. BF Goodrich Aerospace
- [STC SA02059AK](https://openairdocs.org/stc/SA02059AK): Installation and Maintenance of Garrett(AirResearch) TPE 331-6-252T engines. FS Air Service, Inc
- [STC SA488CH](https://openairdocs.org/stc/SA488CH): Installation of AiResearch (Garrett) TPE331-2-201A engines.. National Flight Services, Inc
- [STC SA4612NM](https://openairdocs.org/stc/SA4612NM): Limitation of passenger seating to 5 seats maximum, including co-pilot seat. Arctic Circle Air Service Inc
- [STC SA3638NM](https://openairdocs.org/stc/SA3638NM): Reduce/limit passenger seating to4 seats, including co-pilot seat. (SC-7 SERIES 3 Variant 200). North Star Air Cargo, Inc
- [STC SA2230NM](https://openairdocs.org/stc/SA2230NM): Removal of passenger seats. Union Flights
- [STC SA00765DE PAGE 1](https://openairdocs.org/stc/SA00765DE%20PAGE%201) (historical): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine

All 54: https://openairdocs.org/tcds/A15EU/stcs.md

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