# TCDS H1IN: Airbus Helicopters

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Helicopters
- Revision: 9
- Revised: March 1, 2022
- Product: Aircraft, Rotorcraft
- Certification basis: Part 21, Part 21, Part 21, Part 21, Part 21
- Registered aircraft: 32, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/cc/3d/cc3d495bfd3604beb9f30ccd5f62d8c1a9c7f2c97a67ca867ec7560f9f24a3d2
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2F488B7CE1F3DE70862587F8006FC8A1.0001
- Page: https://openairdocs.org/tcds/H1IN

## Models (5)

As the data sheet lists them.

- SA.316C Alouette III
- SA.316B Alouette III
- SA.315B Alouette III
- SE.3160 Alouette III
- SA.319B Alouette III

## What the data sheet says

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

```text
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
 
TYPE CERTIFICATE DATA SHEET NO. H1IN 
 
This data sheet which is a part of Type Certificate No. H1IN prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations/Federal Aviation 
Regulations. 
 
Type Certificate Holder: Airbus Helicopters Aeroport International 
Marseille Provence 13725 
 Marignane - Cedex 
France 
 
TC Holder Record: Eurocopter France changed name to Airbus Helicopters on January 1, 2014. 
 
I - Model SE.3160 Alouette III, approved 27 March 1962 
 
Engine One - Turbomeca Artouste III B. 
 
Fuel and Engine Oil See data pertinent to all models. 
 
Engine limits Maximum speed: 33,500 r.p.m. true held constant by governor within 
+ 200 r.p.m. (transient variations of + 1000 r.p.m. are permissible). 
 Rating takeoff: 858 hp - 33,500 r.p.m. (5 min.) 
(limited to 562 hp by engine gear box) 
 
Rating maximum continuous: 690 hp - 33,500 r.p.m.) 
(limited to 542 hp by engine gear box) 
) 
) at sea level 
) standard 
) conditions of 
) 59° F., 29.92 in.Hg 
Maximum tailpipe temperature 
Takeoff power (5 min.) : 550°C 
Maximum continuous power : 500°C 
 
Transmission Limits Maximum takeoff power : 542 hp 
Maximum continuous power : 444 hp 
 
Helicopter Limits Maximum takeoff power : 542 hp 
Maximum continuous power : 444 hp 
 
Rotor Limits Maximum speed : 420 r.p.m. 
Minimum speed : 270 r.p.m. 
Constant speed, power-on flight : 353.2 r.p.m. 
 
 
Airspeed Limits For CG location between (109.45) and (121.25) : 113 knots 
For CG location between (121.25) and (124.0) : 103 knots 
See Helicopter Flight Manual for variation of VNE with weight and altitude. 
 
 
 
 
Page No. 1 2 3 4 5 6 7 8 9 
Rev. No. 9 4 4 4 4 4 4 9 8 
H1IN 
Revision 9 
Airbus Helicopters 
SE.3160 Alouette III 
SA.316B Alouette III 
SA.315B Alouette III 
SA.319B Alouette III 
SA.316C Alouette III 
March 1, 2022

Page 2 of 9 H1IN, Rev 9 
 
I - Model SE.3160 Alouette III (cont’d) 
C.G. Range Longitudinal (109.45) to (121.25) 
(121.25) to (124.0) with airspeed restriction per "Airspeed Limits" 
above. 
Lateral LH Limit (5.51) 
RH Limit (4.72) 
 
Maximum Weight 4630 lb. 
 
Number of Seats 7 - Pilot and two front passengers (54.55), plus four rear passengers (86.45) 
Maximum Baggage See Helicopter Flight Manual. 
Fuel Capacity 149 U.S. Gal. (123.2) - Usable 146 U.S. Gal. 
Total tank capacity:  157 U.S. Gal. 
(See NOTE 1 for data on unusable fuel). 
 
Oil Capacity Total capacity 2.6 U.S. Gal. at 143 inches 
(See NOTE 1 for data on undrainable oil). 
 
NOTE A The "Siren" cargo swing, cargo sling and "Air Equipment" rescues hoist to Aerospatiale 
Drawing Nos. 3160-73.06.500 (cargo swing) 3160-73.06.000 (cargo sling) and 3160- 
73.38.000 (rescue hoist) are approved for special-purpose operation in accordance with 
limitations contained in the Helicopter Flight Manual. 
 
II. Model SA.316B Alouette III, approved 25 March 1971 
(SA.316B may be obtained by conversion of SE.3160 in accordance with NOTE B) 
Engine One - Turbomeca Artouste III B. 
Fuel and Engine Oil See data pertinent to all models. 
 
Engine Limits Maximum speed: 33,500 r.p.m. true held constant by governor within 
+ 200 r.p.m. (transient variations of + 1000 r.p.m. are permissible). 
 Rating takeoff: 858 hp - 33,500 r.p.m. (5 min.) 
(limited to 562 hp by engine gear box) 
 
Rating maximum continuous: 690 hp - 33,500 r.p.m. 
(limited to 542 hp by engine gear box) 
) 
) at sea level 
) standard 
) conditions of 
) 59° F., 29.92 in.Hg 
 Maximum tailpipe temperature 
Takeoff power (5 min.) : 550°C 
Maximum continuous power : 500°C 
 
Transmission Limits Maximum takeoff power : 592 hp 
Maximum continuous power : 444 hp 
 
Helicopter Limits Maximum takeoff power : 562 hp 
Maximum continuous power : 444 hp 
 
Rotor Limits Maximum speed : 420 r.p.m. 
Minimum speed : 270 r.p.m. 
Constant speed, power-on flight : 353.2 r.p.m. 
 
 
Airspeed Limits For CG location between (109.45) and (121.25): 113 knots 
For CG location between (121.25) and (124.0): 103 knots 
See Helicopter Flight Manual for variation of VNE with weight and altitude.

Page 3 of 9 H1IN, Rev 9 
 
II. Model SA.316B Alouette III  (cont’d) 
C.G. Range Longitudinal (109.45) to (121.25) 
(121.25) to (124.0) with airspeed restriction per "Airspeed Limits" 
above. 
Lateral LH limit (5.51) 
RH limit (4.72) 
 
Maximum Weight 4850 lb. 
 
Number of Seats 7 - Pilot and two front passengers (54.55), plus four rear passengers (86.45). 
Maximum Baggage See Helicopter Flight Manual. 
Fuel Capacity 149 U.S. Gal. (123.2) - Usable 146 U.S. Gal. 
Total tank capacity: 157 U.S. Gal. 
(See NOTE 1 for data in unusable fuel). 
 
Oil Capacity Total capacity 2.6 U.S. Gal. at 143. 
(See NOTE 1 for data on undrainable oil). 
 
NOTE A  The "Siren" cargo swing, cargo sling and "Air Equipment" rescue hoist to Aerospatiale 
Drawing Nos. 3160-73.06.500 (cargo swing) 3160-73.06.000 (cargo sling) and 3160- 
73.38.000 (rescue hoist) are approved for special-purpose operation in accordance with 
limitations contained in the Helicopter Flight Manual. 
 
NOTE B To convert the Model SE.3160 Alouette III to the Model SA.316B Alouette III the 
following assemblies, or those which bear a higher group number or dot number, must be 
installed. 
(See SGAC-approved Alouette Service Bulletin 01.20). 
- Blade spacing cables reinforced P/N 3160S.14.60.000 
- Main landing gear reinforced P/N 3160S.42.10.000.1 
- Body structure reinforced P/N 3160S.22.11.000.1 
- Improvement of tail boom P/N 3160S.23.11.000.9 
service life 
- Instruction placards (See NOTE 2) 
- Main gear box P/N 3160S.62.00.000.13 or 
P/N 3160S.62.00.000.10 to 12 
embodying modification 
AM.1212 in addition (See log card) 
- Main rotor shaft P/N 3160S.68.10.000.1 
- Main rotor head P/N 3160S.12.20.000.3 
- Freewheel P/N 3160S.60.10.000.1 
- Tube and universal joint assy P/N 3160S.67.11.000 
- Tail rotor gear box P/N 3160S.66.10.000.3 
- Tail rotor head P/N 3160S.33.30.000.6 
- Main rotor blades P/N 3160S.11.10.000.16 to 31 
.42 to 51 
.62 to 71 
- Tail rotor blades P/N 3160S.34.10.000.10

Page 4 of 9 H1IN, Rev 9 
 
III. - Model SA.315B Alouette III, approved 25 February 1972 
 
Engine One - Turbomeca Artouste III B. 
 
Fuel and Engine Oil See data pertinent to all models. 
 
Engine Limits Maximum speed: 33,500 r.p.m. true held constant by governor within 
+ 200 r.p.m. (transient variations of + 1000 r.p.m. are permissible). 
 
 Rating takeoff: 858 hp - 33,500 r.p.m. (5 min.) 
(limited to 562 hp by engine gear box) 
 
Rating maximum continuous: 690 hp - 33,500 r.p.m. 
(limited to 542 hp by engine gear box) 
) 
) at sea level 
) standard 
) conditions of 
) 59° F., 29.92 in.Hg 
Maximum tailpipe temperature 
Takeoff power (5 min.) : 550°C 
Maximum continuous power : 500°C 
 
Transmission Limits Maximum takeoff power : 592 hp 
Maximum continuous power : 494 hp 
 
Helicopter Limits Maximum takeoff power : 562 hp 
Maximum continuous power : 494 hp 
 
Rotor Limits Maximum speed : 420 r.p.m. 
Minimum speed : 270 r.p.m. 
Constant speed, power-on flight : 353.2 r.p.m. 
 
 
Airspeed Limits For CG location between (108.6) and (118.1): 113 knots 
For CG location between (118.1) and (124.0): 108 knots 
See Helicopter Flight Manual for variation of VNE with weight and altitude. 
 
C.G. Range Longitudinal (108.6) to (118.1) 
(118.1) to (124.0) with airspeed restriction per 
"Airspeed Limits" above and for weights below 3860 lb. 
 
Lateral LH limit (5.3) 
RH limit (1.7) 
 
Maximum Weight  4300 lb. with internal load. 
5070 lb. with external load. 
Maximum permissible weight on sling: 2200 lb. 
 
Number of Seats 5 - Pilot and one front passenger (52.80), plus three rear passengers (84.10). 
Maximum Baggage See Helicopter Flight Manual. 
Fuel Capacity 149 U.S. Gal. (120) - Usable 146 U.S. Gal. 
Total tank capacity: 157 U.S. Gal. 
(See NOTE 1 for data on unusable fuel). 
 
Oil Capacity Total capacity 2.6 U.S. Gal. at 141.5. 
(See NOTE 1 for data on undrainable oil). 
 
NOTE A The "Siren" cargo swing and "Air Equipment" rescue hoist to Aerospatiale Drawing 
Nos. 315A73.10.100 (cargo swing) and 315A73-02.100 (rescue hoist) are approved for 
special-purpose operation in accordance with limitations contained in the Helicopter 
Flight Manual.

Page 5 of 9 H1IN, Rev 9 
 
IV. - Model SA319B Alouette III, approved 20 November 1972. 
 
Engine One - Turbomeca Astazou XIVB. 
 
Fuel and Engine Oil See data pertinent to all models. 
 
Engine Limits Maximum speed: 43,000 r.p.m. true held constant by governor within 
+ 200 r.p.m. (transient variation of + 1500 r.p.m. are permissible). 
 Rating takeoff: 858 hp - 43,000 r.p.m. (5 min.) 
(limited to 592 hp by engine gear box) 
 
Rating maximum continuous: 770 hp - 43,000 r.p.m. 
(limited to 542 hp by engine gear box) 
Maximum tailpipe temperature 
Maximum takeoff (5 min.) : 520°C 
Maximum continuous power : 470°C 
) 
) at sea level 
) standard 
) conditions of 
) 59° F., 29.92 in.Hg 
Transmission Limits Maximum takeoff power : 592 hp 
Maximum continuous power : 494 hp 
 
Helicopter Limits 
Rotor Limits 
Maximum takeoff power : 592 hp 
Maximum continuous power : 494 hp 
Maximum speed : 420 r.p.m. 
Minimum speed : 270 r.p.m. 
Constant speed, power on flight : 358 r.p.m. 
 
 
Airspeed Limits  For CG location between (109.4) and (121.2): 118 knots 
For CG location between (121.2) and (124.0): 108 knots 
See Helicopter Flight Manual for variation of VNE with weight and altitude. 
 
C.G. Range Longitudinal (109.4) to (121.2) 
  (121.2) to (124.0) with airspeed restriction 
  (See above "Airspeed Limits") 
 Lateral LH limit (5.5) 
  RH limit (4.7) 
 
Maximum Weight 4,960 lb. 
 
Number of Seats 7 - Pilot and two front passengers (54.5), plus four rear passengers (86.4). 
Maximum Baggage See Helicopter Flight Manual. 
Total Fuel Capacity 149 U.S. Gal. (123.2) - Usable 146 U.S. Gal. 
(See NOTE 1 for data on unusable fuel). 
 
Oil Capacity Total capacity 2.6 U.S. Gal. at 153. 
(See NOTE 1 for data on undrainable oil). 
 
Rotor Blade Movements For rigging information, refer to the Alouette III SA319B Maintenance Manual. 
 
NOTE A The "Siren" cargo swing, cargo sling and "Air Equipment" rescue hoist to 
"Aerospatiale" Drawings. 
319A-73.06.500 and 319A-73.06.510 (cargo swing) 
319A-73.06.000 and 319A-73.06.010 (cargo sling) and 
319A-73.38.005 and 319A-73.38.000 (rescue hoist) are approved for operation in 
accordance with limitations contained in the Helicopter Flight Manual. 
 
NOTE B To convert the Model SA316B Alouette III to the Model SA319B Alouette III the 
appropriate modifications listed in the Aerospatiale Technical Note SA319A.04.00.025 
must be applied.

Page 6 of 9 H1IN, Rev 9 
 
V. - Model SA316C Alouette III, approved 20 November 1972. 
 
Engine One - Turbomeca Artouste IIID. 
 
Fuel and Engine Oil See data pertinent to all models. 
 
Engine Limits Maximum speed: 33,500 r.p.m. true held constant by governor within 
+ 200 r.p.m. (transient variations of + 1000 r.p.m. are permissible). 
Rating takeoff: 858 hp - 33,500 r.p.m. (5 min.) ) 
(limited to 592 hp by engine gear box) ) at sea level 
) standard 
Rating maximum continuous: 690 hp - 33,500 r.p.m. ) conditions of 
(limited to 542 hp by engine gear box) ) 29.92 in.Hg 
 
Maximum tailpipe temperature 
Maximum takeoff (5 min.) : 550°C 
Maximum continuous tsail : 500°C 
 
Transmission Limits Maximum takeoff power : 592 hp 
Maximum continuous power : 494 hp 
 
Helicopter Limits Maximum takeoff power : 592 hp 
Maximum continuous power : 494 hp 
 
Rotor Limits Maximum speed : 420 r.p.m. 
Minimum speed : 270 r.p.m. 
Constant speed, power-on flight : 358 r.p.m. 
 
Airspeed Limits For CG location between (109.4) and (121.2): 118 knots 
For CG location between (121.2) and (124.0): 108 knots 
See Helicopter Flight Manual for variation of VNE with weight and altitude. 
 
C.G. Range Longitudinal (109.4) to (121.2) 
(121.2) to (124.0) with airspeed restriction 
(See above "Airspeed Limits") 
 
Lateral LH limit (5.5) 
RH limit (4.7) 
 
Maximum Weight 4,960 lb. 
 
Number of Seats 7 - Pilot and two passengers (54.5), four rear passengers (86.4). 
Maximum Baggage See Helicopter Flight Manual. 
Total Fuel Capacity 149 U.S. Gal. (123.2) - Usable 146 U.S. Gal. 
(See NOTE 1 for data on unusable fuel) 
 
Oil Capacity Total capacity 2.6 U.S. Gal. at 128. 
(See NOTE 1 for data on undrainable oil). 
 
Rotor Blade Movements For rigging information, refer to the SA316C Alouette III Maintenance Manual. 
 
NOTE A The "Siren" cargo swing, cargo sling and "Air Equipment" rescue hoist to 
"Aerospatiale" Drawings. 
319A-73.06.500 and 319A-73.06.510 (cargo swing) 
319A-73.06.000 and 319A-73.06.010 (cargo sling) and 
319A-73.38.005 and 319A-73.38.010 (rescue hoist) are approved for 
operation in accordance with limitations contained in the Helicopter Flight Manual.

Page 7 of 9 H1IN, Rev 9 
 
NOTE B To convert the Model SA316B Alouette III to the Model SA316C Alouette III the 
appropriate modifications listed in the Aerospatiale Technical Note SA319A.04.00.025 
must be applied. 
 
DATA PERTINENT TO ALL MODELS. 
 
Fuel Normal Fuels, Unrestricted 
SPECIFICATIONS REMARKS 
French U.S.A. British NATO  
Aviation Fuels  D. Eng. RD 2453 F34 
AIR 3405 AVTUR FS II  
(TRO)   
 ASTMJet A   
 ASTMJet A1 D.Eng. RD 2494  
  AVTUR F35 
Aviation Fuels MIL-T-5624 D.Eng. RD 2454  
AIR 3407 (JP.4) AVTAG FS II F40 
(TR4)    
 ASTMJet B D.Eng. RD 2486  
  AVTAG F45 
   F42 
Aviation Fuels    
AIR 3404 MIL-T-5624 D.Eng. RD 2498  
(TR5) (JP.5) AVCAT F44 
Note a: Refer to current issues and amendments. 
Note b: The use of an approved anti-icing additive is recommended, if none is contained in 
the fuel, at OAT below O°C. 
Note c: The following fuel additives are approved for use: 
Anti-icing additive: AIR 3652, NATO.S.748, MIL.I.27686, 
D.Eng. RD 2451 (each is eligible up to .15% in volume, with or without glycerine). 
Anti-static additive: SHELL ASA.3, (up to .0001% in volume). 
 
Fuels Subjected to Restrictions on Use. 
SPECIFICATIONS RESTRICTIONS 
French U.S.A. British NATO  
Maximum operation time on 
gasoline during any period 
between overhauls: 25 hrs. 
 
Add 1 to 2% of lubricating 
oil by volume (mineral oil if 
possible) 
Gasoline 
 
 
 
AIR 3401 
MIL-G-5572 
(Grade 80/87) 
(Grade 100/130) 
 
(Grade 115/145) 
 F12 
D.Eng. RD 2485 F18 
F22 
Automotive 
Gasoline DCEA/2D 
MT 80 
 
MIL-G-3056 
 
DEF 2401 
 
F46 
Automotive Diesel 
Oil DCEA/21 C 
VVF 800 DF2  
TS.10.003 
 
F54 
Not to be used at OAT 
below -5° C 
VVF 800 DF1   Not to be used at OAT 
below - 15°C 
VVF 800 DFA  F56 
Gasoil O 
7120 STM 
MIL-F-16884 DEF 2402 
(47/0 DIESO) 
 
F75 
Not to be used at OAT 
below -5°C 
Gasoil 20 
7120STM 
 DEF 2402 
(47/20 DIESO) 
 
F76 
Not to be used at OAT 
below 0°C 
Illuminating 
Oil DCEA/11C 
VV-K211 DEF 2403 F58 Not to be used at OAT 
below - 15°C

Page 8 of 9 H1IN, Rev 9 
 
Engine Lubricating Oil 
SPECIFICATIONS (Latest Amendment) Remarks 
 
 
Normal 
French NATO U.S.A. British  
Synthetic Oil AIR 3513 0.148 MIL.l.7808  
 
 
AIR 3515 
 
 
0.135 
 
 
 
0.156 
Aeroshell Turbine 
Oil 3 
 
 
D.Eng. RD 
2490 
 
 
Mineral oil 
 
 
 
Synthetic oil 
Esso Aviation 
Utility Oil F 
Caltex jet engine 
oil medium heavy 
MIL.L.23699 
 
CAUTION: The mixing of oils AIR 3513 and 3515 is not permitted. The system should be flushed when changing from 
one type to the other. 
 
Datum Longitudinal: 118.1 in. forward of rotor hub center 
Lateral: Plane of symmetry of rotorcraft. 
 
Leveling Means Four leveling lugs, vertical tubes of body structure, two at the front and two at the rear. 
Rotor Blade Movements For rigging information, refer to the Alouette III Maintenance Manual. 
Serial Nos. Eligible The French Government "Certificat de Navigabilite pour Exportation" endorsed as noted 
under "Import Requirements" must be submitted for each individual helicopter for which 
application for certification is made. For applications for Standard Airworthiness 
Certificates made after May1, 2004, a review of historical records is needed to determine 
if the helicopter was delivered to and operated by the military. If the helicopter has 
military history, the helicopter is not eligible for a Standard Airworthiness Certificate 
unless a copy of a Standard Airworthiness Certificate issued at the time of delivery to the 
military is submitted. 
 
Import Requirements  
The FAA can issue a U.S. airworthiness certificate based on a National Aviation Authority 
(NAA) Export Certificate of Airworthiness (Export C of A) signed by a representative of 
the French Generale de l’Aviation Civile (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 comply with the type design approved 
under U.S. Type Certificate Number H1IN 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 CAR 10 (FAR 21.29) CAR 6, 20 December 1956, plus Amendments 6.1 through 6.4 
and Special Requirements notified to the French Government by the U.S. Government, 
in letters dated 3 May 1960 and 13 September 1961. 
Type Certificate No. H1IN issued 27 March 1962 for the SE.3160 Alouette III. 
Type Certificate No. H1IN amended 25 March 1971 to add the SA.316B 
Alouette III. 
Type Certificate No. H1IN amended 25 February 1972 to add the SA.315B 
Alouette III. 
Type Certificate No. H1IN amended 20 November 1972 to add the SA.319B Alouette III 
and the SA.316C Alouette III. 
Date of Application for Type Certificate: 28 July 1961. 
 
The French Direction Generale de l’Aviation Civile (DGAC) originally type certificated 
this rotorcraft under its type certificate TC 14. The FAA validated this product under U.S. 
Type Certificate Number H1IN. Effective September 28, 2003, the European Aviation 
Safety Agency (EASA) began oversight of this product on behalf of the DGAC.

Page 9 of 9 H1IN, Rev 9 
 
 
Service Information 
Each of the documents listed below must state that it is approved by the European 
Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by 
the French Generale de l’Aviation Civile (DGAC). Any such documents are accepted by 
the FAA and are considered FAA approved. 
 
• Service Bulletin, 
• Structural repair manuals, 
• Vendor manuals, 
• Aircraft flight manuals, and 
• Overhaul and maintenance manuals. 
 
This applies only to the acceptance of the type design data. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations 
(See Certification Basis) must be installed in the aircraft for certification. In addition, the  
following items of equipment are required: 
 
SGAC-approved Helicopter Flight Manual (English language version). 
Ambient air temperature gauge. 
 
NOTES: 
 
NOTE 1 Current weight and balance report, including loading instructions and list of equipment included in the 
certificated empty weight, must be provided for each helicopter at the time of original certification. In order 
to obtain the most consistent weight and balance results, all helicopters should be weighed on jackpoints rather 
than on wheels and floats. When changes are made to the helicopter that affect the weight and balance, refer 
to the Flight Manual for instructions. 
 
The certificated empty weight and corresponding center of gravity locations must include unusable fuel of 18 
lb. (120.8), and undrainable oil of 1.5 lb. (138.6). 
 
NOTE 2 The following placard must be displayed in clear view of the pilot: 
 
"THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE 
OPERATING LIMITATIONS SPECIFIED IN THE APPROVED FLIGHT MANUAL" 
 
The other placards as indicated in the Helicopter Flight Manual must be installed in the appropriate 
location. 
 
NOTE 3 Information essential to the proper maintenance of the helicopter is contained in the Manufacturer's 
Maintenance Manual provided with each helicopter. The retirement times of critical parts are listed in 
Chapter 5, approved by SGAC. 
 
NOTE 4 Revision 8 to the TCDS changed the company name from Eurocopter France to Airbus Helicopters. 
NOTE 5: Effective January 1, 2014, Eurocopter France name was changed to Airbus Helicopters. 
 
 
...END...
```

## ADs (38, in force first)

- [AD 2023-11-07](https://openairdocs.org/ad/2023-11-07): Ground Proximity System · Airbus Helicopters 47, 206, 210 and 237 more. Effective Jun 22, 2023
- [AD 2012-23-03](https://openairdocs.org/ad/2012-23-03): Tail Rotor Drive System · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 5 more. Effective Dec 31, 2012
- [AD 2010-02-07](https://openairdocs.org/ad/2010-02-07): Main rotor blade (blade) · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Feb 12, 2010
- [AD 2007-26-11](https://openairdocs.org/ad/2007-26-11): High-pressure oxygen cylinder · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 45 more. Effective Jan 28, 2008
- [AD 2002-20-03](https://openairdocs.org/ad/2002-20-03): Ferry fuel tank (tank) electrostatic ground connector · Airbus Helicopters AS-365N2, AS-365N3, AS332C and 24 more. Effective Nov 6, 2002
- [AD 2002-01-30](https://openairdocs.org/ad/2002-01-30): Main Gearbox Magnet Plug · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 7 more. Effective Feb 19, 2002
- [AD 2001-18-51](https://openairdocs.org/ad/2001-18-51): Main Gearbox Assembly · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 5 more. Effective Oct 31, 2001
- [AD 2001-04-13](https://openairdocs.org/ad/2001-04-13): Main Rotor Blade Spar · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Apr 16, 2001
- [AD 2000-10-05](https://openairdocs.org/ad/2000-10-05): Flotation Gear Nitrogen Cylinders · Airbus Helicopters SA330F, SA330G, SA330J and 6 more. Effective Jun 29, 2000
- [AD 2000-05-11](https://openairdocs.org/ad/2000-05-11): Tail Rotor Blades · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 7 more. Effective Mar 24, 2000
- [AD 2000-02-32](https://openairdocs.org/ad/2000-02-32): Horizontal Stabilizer Spar Tube · Airbus Helicopters SA.315B Alouette III. Effective Mar 13, 2000
- [AD 99-21-25](https://openairdocs.org/ad/99-21-25): Main Gear Box Magnetic Plug for Metal Particles Inspection · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Oct 29, 1999
- [AD 99-08-06](https://openairdocs.org/ad/99-08-06): Main Rotor Blade Root Reinforcement Strip · Airbus Helicopters SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III and 1 more. Effective Apr 22, 1999
- [AD 99-07-08](https://openairdocs.org/ad/99-07-08): Main Rotor Blade Root Reinforcement Strip · Airbus Helicopters SA.315B Alouette III. Effective Apr 13, 1999
- [AD 99-05-14](https://openairdocs.org/ad/99-05-14): Main Rotor Blade Cuff Attachment Fitting · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Apr 7, 1999
- [AD 98-24-23](https://openairdocs.org/ad/98-24-23): Horizontal Stabilizer · Airbus Helicopters SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III and 1 more. Effective Dec 10, 1998
- [AD 98-16-02](https://openairdocs.org/ad/98-16-02): Tail Rotor Blade · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 7 more. Effective Sep 4, 1998
- [AD 93-23-04](https://openairdocs.org/ad/93-23-04): Install VNE Placard · RMH Development, Inc. Replacement Main Rotor Blades (Phlight of Phancy STC SH778GL). Effective Feb 17, 1994
- [AD 88-12-11](https://openairdocs.org/ad/88-12-11): Main Drive Shaft · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 5 more. Effective May 20, 1988
- [AD 84-01-03 R1](https://openairdocs.org/ad/84-01-03-R1): 'A' Frame Support Assemblies · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Apr 25, 1987
- [AD 85-07-07](https://openairdocs.org/ad/85-07-07): Control Rod · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 3 more. Effective Apr 19, 1985
- [AD 81-21-01](https://openairdocs.org/ad/81-21-01): Erc Cargo Hook Assemblies · Airbus Helicopters SA.315B Alouette III. Effective Nov 4, 1981
- [AD 81-06-04](https://openairdocs.org/ad/81-06-04): Transmission Deck & Bellcrank Support · Airbus Helicopters SA 318B-Alouette Astazou, SA 318C-Alouette Astazou, SA.315B Alouette III and 4 more. Effective Mar 20, 1981
- [AD 81-03-04](https://openairdocs.org/ad/81-03-04): Main Gearshaft · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 1 more. Effective Mar 12, 1981
- [AD 78-23-03](https://openairdocs.org/ad/78-23-03): Helicopter Control · Airbus Helicopters SA.316C Alouette III and SA.319B Alouette III. Effective Dec 4, 1978
- [AD 77-14-03](https://openairdocs.org/ad/77-14-03): Tail Rotor Directional Control · Airbus Helicopters SA.316B Alouette III and SE.3160 Alouette III. Effective Aug 1, 1977
- [AD 76-18-02](https://openairdocs.org/ad/76-18-02): Tail Rotor Controls · Airbus Helicopters SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III and 1 more. Effective Sep 29, 1976
- [AD 75-27-05](https://openairdocs.org/ad/75-27-05): Main Rotor Blades · Airbus Helicopters SA 3180-Alouette Astazou, SA 318C-Alouette Astazou, SA.315B Alouette III and 6 more. Effective Jan 19, 1976
- [AD 75-26-02](https://openairdocs.org/ad/75-26-02): Main Rotor Head · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Dec 23, 1975
- [AD 75-22-21](https://openairdocs.org/ad/75-22-21): Main Gear Boxes · Airbus Helicopters SA.316B Alouette III. Effective Oct 30, 1975
- [AD 75-24-14](https://openairdocs.org/ad/75-24-14): Excessive Vibration · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 7 more. Effective Oct 30, 1975
- [AD 75-21-03](https://openairdocs.org/ad/75-21-03): Tail Boom · Airbus Helicopters SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III and 1 more. Effective Oct 20, 1975
- [AD 75-16-06](https://openairdocs.org/ad/75-16-06): Tail Rotor Gear Box · Airbus Helicopters SA 3180-Alouette Astazou, SA 318B-Alouette Astazou, SA 318C-Alouette Astazou and 6 more. Effective Jul 28, 1975
- [AD 73-09-03](https://openairdocs.org/ad/73-09-03): Main Rotor Gear Box · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 1 more
- [AD 2021-23-13](https://openairdocs.org/ad/2021-23-13) (historical): Ground Proximity System · Airbus Helicopters K-225, K-190A, K-240 and 237 more. Effective Dec 9, 2021
- [AD 2003-15-51](https://openairdocs.org/ad/2003-15-51) (historical): Main rotor blade (blade) · Airbus Helicopters SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Sep 12, 2003
- [AD 98-10-09](https://openairdocs.org/ad/98-10-09) (historical): Blade Spar for Crack Inspection · Eurocopter France SA.315B Alouette III, SA.316B Alouette III, SA.316C Alouette III and 2 more. Effective Sep 15, 1998
- [AD 98-12-21](https://openairdocs.org/ad/98-12-21) (historical): Horizontal Stabilizer Spar Tube · Eurocopter France SA.315B Alouette III. Effective Jul 15, 1998

## Registered aircraft by registry model (OpenAirDocs)

- [Aerospatiale SA315B](https://openairdocs.org/model/aerospatiale-sa315b): 18 aircraft (registry code 8680615)
- [Aerospatiale SA315B ALOUETTE III](https://openairdocs.org/model/aerospatiale-sa315b-alouette-iii): 4 aircraft (registry code 8680516)
- [Aerospatiale SA319B ALOUETTE III](https://openairdocs.org/model/aerospatiale-sa319b-alouette-iii): 3 aircraft (registry code 8680607)
- [Aerospatiale SA316B ALOUETTE III](https://openairdocs.org/model/aerospatiale-sa316b-alouette-iii): 2 aircraft (registry code 8680515)
- [Eurocopter SA315B](https://openairdocs.org/model/eurocopter-sa315b): 2 aircraft (registry code 8680993)
- [Sud SA316B ALOUETTE III](https://openairdocs.org/model/sud-sa316b-alouette-iii): 2 aircraft (registry code 8680207)
- [Sud SA315B LAMA](https://openairdocs.org/model/sud-sa315b-lama): 1 aircraft (registry code 8680208)
- [Aerospatiale SA316C ALOUETTE III](https://openairdocs.org/model/aerospatiale-sa316c-alouette-iii): 0 aircraft (registry code 8680513)
- [Aerospatiale SE3160 ALOUETTE III](https://openairdocs.org/model/aerospatiale-se3160-alouette-iii): 0 aircraft (registry code 8680605)
- [Eurocopter LAMA SA 315B](https://openairdocs.org/model/eurocopter-lama-sa-315b): 0 aircraft (registry code 8680992)
- [Snias SE 3160](https://openairdocs.org/model/snias-se-3160): 0 aircraft (registry code 8680978)
- [Sud SE3160 ALOUETTE III](https://openairdocs.org/model/sud-se3160-alouette-iii): 0 aircraft (registry code 8680209)

## STCs approved under this data sheet (81, first 50)

- [STC SH3319NM](https://openairdocs.org/stc/SH3319NM): Installation of Precise Flight Pulselite Control Unit in the
Landing /Taxi Recognition Visual Control Light system,. Precise Flight Inc
- [STC SH1415NM](https://openairdocs.org/stc/SH1415NM): Installation of a Perkins Plastics part no 3180-20 bubble window in the right hand door. WSH, LLC
- [STC SH4928NM](https://openairdocs.org/stc/SH4928NM): Fabrication of Onboard Systems Model 200-036-00, 200-036-01, 200-038-00, and 200-038-01 Load Weigh Kits. Onboard Systems International
- [STC SR00765SE](https://openairdocs.org/stc/SR00765SE): Fabrication of Onboard Systems Model 200-239-00 (H-frame) or 200-240-00 (frame swing) cargo hook kit. Onboard Systems International
- [STC SR00897SE](https://openairdocs.org/stc/SR00897SE): Fabrication of Onboard Systems Model 200-270-00, 200-270-01, 200-271-00, and 200-271-02 Cargo Hook Kits. Onboard Systems International
- [STC SH1152NW](https://openairdocs.org/stc/SH1152NW): Installation of the Automatic Flagman Model 135 Control Stick Grip. Air Products & Parts LLC
- [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC
- [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SH4671SW](https://openairdocs.org/stc/SH4671SW): Installation of P3180-9/-10 upper sliding window assembly and-11/-12 lower sliding window assembly in the passenger door.. The NORDAM Group LLC
- [STC SR00848SE](https://openairdocs.org/stc/SR00848SE): Replacement of the original landing gear skid tubes with DART Aerospace Model D315-668-011(LH) and 012(RH) skid tubes fabricated in accordance with DART Aerospace Master Drawing List (MDL) No. MDL-D315-668, Revision C , dated July 6, 2000, or later Federal Aviation Administration (FAA) approved revision and installed. Dart Aerospace USA Inc.
- [STC SR00914SE](https://openairdocs.org/stc/SR00914SE): Fabrication and installation of Dart D315-670-011 Bearpaws. Dart Aerospace USA Inc.
- [STC SH1791SW](https://openairdocs.org/stc/SH1791SW): Foxtronics/Tramm BTI-600 nickel cadmium battery temperature.. FoxCart GSE, LLC
- [STC SR02394AK](https://openairdocs.org/stc/SR02394AK): Replacement of existing landing and/or hover light bulbs with Light Emitting Diode (LED) lighting system. Seaplanes North LLC
- [STC SA2693NM](https://openairdocs.org/stc/SA2693NM): Installation of Electronics International digital volt/amp gauges and accessories.. Electronics International Inc.
- [STC SH778GL](https://openairdocs.org/stc/SH778GL): Installation of RMH Development, Inc. Replacement Main Rotor Blades.. Phlight of Phancy Corp.
- [STC SH5889NM](https://openairdocs.org/stc/SH5889NM): Installation of landing gear skid tubes.. Heli-Support Inc.
- [STC SR00122LA-D](https://openairdocs.org/stc/SR00122LA-D): Installation of Heli-Support, Inc.,/Aeroflo Dynamic air filters.. Heli-Support Inc.
- [STC SR00124LA-D](https://openairdocs.org/stc/SR00124LA-D): Installation of horizontal composite stabilizer.. Heli-Support Inc.
- [STC SH1500NM](https://openairdocs.org/stc/SH1500NM): Installation of Airwest 316B skis, P/N 316-S1.. Heli-Support Inc.
- [STC SH5474NM](https://openairdocs.org/stc/SH5474NM): Installation of replacement side panels.. Heli-Support Inc.
- [STC SH5540NM](https://openairdocs.org/stc/SH5540NM): Installation of snow skis.. Heli-Support Inc.
- [STC SH6024NM](https://openairdocs.org/stc/SH6024NM): Installation of mobile radio.. Heli-Support Inc.
- [STC SR00057DE](https://openairdocs.org/stc/SR00057DE): Installation of provisions for structural hardpoints for use in firefighting repelling operations.. Heli-Support Inc.
- [STC SR00120LA-D](https://openairdocs.org/stc/SR00120LA-D): Installation of Engine Air Induction Filters.. Heli-Support Inc.
- [STC SR00121LA-D](https://openairdocs.org/stc/SR00121LA-D): Installation for replacement starter/generator support bracket.. Heli-Support Inc.
- [STC SR00126LA-D](https://openairdocs.org/stc/SR00126LA-D): Installation of Digital Diamond J, Inc. T4 exhaust temperature indicator.. Heli-Support Inc.
- [STC SR00127LA-D](https://openairdocs.org/stc/SR00127LA-D): Installation of OAT Indicator.. Heli-Support Inc.
- [STC SR00739SE](https://openairdocs.org/stc/SR00739SE): Installation of Ag-Air Systems, Inc. hydraulic accessory drive system.. Kawak Aviation Technologies Inc
- [STC SR01573SE](https://openairdocs.org/stc/SR01573SE): Installation of Pulselite and Whelen Landing Light.. Evergreen Helicopters Inc
- [STC SA00680SE](https://openairdocs.org/stc/SA00680SE): Installation of Electronics International model UBG-16 or UBG-16T bar graph engine analyzer.. Electronics International
- [STC SH6039NM](https://openairdocs.org/stc/SH6039NM): Intermixing of main rotor blades of the same part number.. Heli-Support Inc
- [STC SH2716NM](https://openairdocs.org/stc/SH2716NM): Installation of a gyro-stablized television camera pod.. 1592686 Ontario Inc
- [STC SR00811NY](https://openairdocs.org/stc/SR00811NY): Installation of Technisonic Industries Limited TFM-138 series transceiver models.. Technisonic Industries Limited
- [STC SR01834NY](https://openairdocs.org/stc/SR01834NY): Installation of Globalstar Satellite Telephone System.. Atlantic Avionics Inc.
- [STC SA01258SE](https://openairdocs.org/stc/SA01258SE): Installation of the Automatic Flagman Dispenser Models in accordance with Automatic Flagman Master Drawing Lists specified in attached AML, or later FAA approved revision.This STC supercedes several existing STC s as listed in the notes on the attached AML.. R-S Sales Inc.
- [STC SH1243SW-D](https://openairdocs.org/stc/SH1243SW-D): Installation of Eastern Rotorcraft Cargo Hook and Swing.. American Eurocopter Corporation
- [STC SH1307SW-D](https://openairdocs.org/stc/SH1307SW-D): Installation of Eastern Rotorcraft cargo hook and H-Frame.. American Eurocopter Corporation
- [STC SH1318SW-D](https://openairdocs.org/stc/SH1318SW-D): Installation of cabin removable step.. American Eurocopter Corporation
- [STC SH1320SW-D](https://openairdocs.org/stc/SH1320SW-D): Installation of external cargo baskets.. American Eurocopter Corporation
- [STC SH1385SW-D](https://openairdocs.org/stc/SH1385SW-D): Replace existing landing light and anti-collision light.. American Eurocopter Corporation
- [STC SH1471SW-D](https://openairdocs.org/stc/SH1471SW-D): Installation of engine inlet sound suppressors.. American Eurocopter Corporation
- [STC SH1735SW-D](https://openairdocs.org/stc/SH1735SW-D): Installation of Eastern Rotorcraft Cargo Hook and H-Frame.. American Eurocopter Corporation
- [STC SH1909SW-D](https://openairdocs.org/stc/SH1909SW-D): Replacement of existing landing light and/or anti-collision lights.. American Eurocopter Corporation
- [STC SH1913SW-D](https://openairdocs.org/stc/SH1913SW-D): Installation of external cargo carrier.. American Eurocopter Corporation
- [STC SH2215SW-D](https://openairdocs.org/stc/SH2215SW-D): Installation of abrasion resistant tape on main rotor blade leading edge.. American Eurocopter Corporation
- [STC SH2425SW-D](https://openairdocs.org/stc/SH2425SW-D): Installation of low range airspeed indicator and pilot pressure surge chamber.. American Eurocopter Corporation
- [STC SH4266SW-D](https://openairdocs.org/stc/SH4266SW-D): Alternate parts for installation of Modification AMS 2195.. American Eurocopter Corporation
- [STC SR01453NY](https://openairdocs.org/stc/SR01453NY): Installation of Fugro Airborne Surveys SA315B electro-magnetometer boom and geosurvey equipment. Does not include connection or installation of electrical power cables, nor operation of the unit.. Fugro Airborne Surveys
- [STC SR01022SE](https://openairdocs.org/stc/SR01022SE): Fabrication of Eagle Helicopter's Tail Rotor Guard Clamp. Eagle Helicopters Inc
- [STC SH268NW](https://openairdocs.org/stc/SH268NW): Installation of automatic flagman Model #5. R-S Sales Inc.

All 81: https://openairdocs.org/tcds/H1IN/stcs.md

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