# TCDS H88EU: Airbus Helicopters Deutschland GmbH (AHD)

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Helicopters Deutschland GmbH (AHD)
- Revision: 17
- Revised: May 8, 2026
- Product: Aircraft, Rotorcraft
- Certification basis: Part 27, Part 29, Part 21
- Registered aircraft: 399, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/e5/c2/e5c2e91762787e174db0beda6d51b50cb928ffed9913cb4120d8785cbaedc73e
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID173953594420260508145313.0001
- Page: https://openairdocs.org/tcds/H88EU

## Models (9)

As the data sheet lists them.

- EC135P1
- EC135T1
- EC135P2
- EC135T2
- EC135P2+
- EC135P3
- EC135T3
- EC135T2+
- EC635T2+

## 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. H88EU 
 
This data sheet, which is part of Type Certificate No. H88EU prescribes conditions and limitations under which the product for 
which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. 
 
Type Certificate Holder AIRBUS HELICOPTERS DEUTSCHLAND GmbH (AHD) 
D-86609 Donauwoerth 
Germany 
 
I. Model EC135P1 (Normal Category) Helicopter, Approved July 31, 1996 
 
Engines. 2 Pratt &Whitney Canada PW 206 B  
Fuel. See Rotorcraft Flight Manual 
Installed Engine Limits. Gas Generator 
Output Shaft Speed N-1 
Torque % % (RPM) 
Output Shaft 
Speed N-2 
 % (RPM) 
Measured Gas 
Temperature 
oC ( oF) 
Normal Operation 
Takeoff power (5 min.) 
 
75 
 
98.7 (57250) 
 
104 (6134) 
 
 
854 (1569) 
Max Continuous 69  97.4 (56500) 104 (6134) 820 (1508) 
 One Engine Inoperative 
2.5 min. power 
 
100 
 
102.4 (59400) 
 
104 (6134) 
 
930 (1706) 
Max. Continuous 86 100.4 (58250) 104 (6134) 885 (1625) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits. 
 
Min. Continuous 
Max. Continuous 
 
Power On % 
95 
 
104 
 
Power Off % 
80 for gross mass up to 1900 kg (4189 lb) 
85 for gross mass above 1900 kg (4189 lb) 
106 
 
Airspeed Limits (IAS). Max. v NE = 155 kts. See Rotorcraft Flight Manual for airspeed limit decrease 
with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum 
at 2720 kg (5996 lb): 4219 mm (166.1 in.) aft of datum 
at 2835 kg (6250 lb): 4224 mm (166.3 in.) aft of datum 
 
Max. rearward range: at 1500 kg (3307 lb): 4570 mm (179.90 in.) aft of datum 
at 2720 kg (5996 lb): 4387 mm (172.72 in.) aft of datum 
at 2835 kg (6250 lb): 4369 mm (172.0 in.) aft of datum 
Straight-line variation between points given. 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 
Rev. No. 17 17 8 8 17 8 17 14 15 17 17 14 17 17 
H88EU 
Revision 17 
AIRBUS HELICOPTERS DEUTSCHLAND  
GmbH 
EC135P1 
EC135T1 
EC135P2 
EC135T2 
EC135P2+ 
                  EC135T2+ 
                   EC635T2+ 
EC135P3 
EC135T3 
                                                                May 8, 2026

Page 2 H88EU  
 
 
 
Lateral C.G. Limits 
Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range. None 
 
Max. Weight. 2720 kg (5996 lb) (Max GW 2835 kg (6250 lb) with S/B EC135-11-003 incorporated. 
See FMS 9.1-3) 
 
Min. Crew. One Pilot 
 
Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb) 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank) 
usable: 670.5 liters (177.1 US gal.) (standard fuel tank) 
 
Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank) 
usable: 664 liters (175.4 US gal.) (self-sealing fuel tank) 
 
Oil Capacity. Engine oil capacity: 4.5 liter (1.19 US gal.) included in minimum gross weight 
 
Max. Operating Altitude. 6096 m (20000 ft.) 
 
Rotor blade and Control Movements.   For rigging information, refer to the EC135 Maintenance Manual. 
 
II. Model EC135T1 (Normal Category) Helicopter, Approved September 17, 1996 
 
Engines. 2 Safran Helicopter Engines ARRIUS 2B1/2B1A/2B1A1 
 
Fuel. See Rotorcraft Flight Manual 
 
Installed Engine Limits (ARRIUS 2B1) – See NOTE 1 
 
Output Shaft 
Torque %  
Gas Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
 % (RPM) 
Measured Gas 
Temperature 
oC ( oF) 
Normal Operation 
Takeoff power (5 min.) 
 
75 
 
101.1 (54706) 
 
104 (6134) 
 
 
895 (1643) 
Max Continuous 69 98.7 (53406) 104 (6134) 855 (1571)  
 One Engine Inoperative 
2.5 min. power 
 
100 
 
103.7 (56113) 
 
104 (6134) 
 
945 (1733) 
Max. Continuous 86 101.1 (54706) 104 (6134) 895 (1643) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
Installed Engine Limits (ARRIUS 2B1A) – (After SB EC135-71-008. See FMS 9.2-57). 
Output Shaft 
Torque %  
Gas Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
 % (RPM) 
Measured Gas 
Temperature 
oC ( oF) 
Normal Operation 
Takeoff power (5 min.) 
 
75 
 
101.1 (54706) 
 
104 (6134) 
 
 
895 (1643) 
Max Continuous 69 98.7 (53406) 104 (6134) 855 (1571)  
 One Engine Inoperative 
2.5 min. power 
 
119.8 
 
103.7 (56113) 
 
104 (6134) 
 
945 (1733) 
Max. Continuous 86 101.1 (54706) 104 (6134) 895 (1643) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients

Page 3 H88EU  
 
 
 
II. Model EC135T1 (Normal Category) Helicopter, Approved September 17, 1996 – (Cont’d) 
 
Installed Engine Limits (ARRIUS 2B1A_1) – (S/N 0188 and Subsequent or After SB EC135-71-015. See FMS 9.2-62). 
 
Output Shaft 
Torque %  
Gas Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
 % (RPM) 
Measured Gas 
Temperature 
oC ( oF) 
Normal Operation 
Takeoff power (5 min.) 
 
75 
 
101.1 (54706) 
 
104 (6134) 
 
 
895 (1643) 
Max Continuous 69 98.7 (53406) 104 (6134) 855 (1571)  
 One Engine Inoperative 
2.5 min. power 
 
128 
 
103.7 (56113) 
 
104 (6134) 
 
945 (1733) 
Max. Continuous 86 101.1 (54706) 104 (6134) 895 (1643) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 95 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 104 106 
 
Airspeed Limits (IAS). Max. v NE = 155 kts. See Rotorcraft Flight Manual for airspeed limit  
decrease with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum 
at 2720 kg (5996 lb): 4219 mm (166.1 in.) aft of datum 
at 2835 kg (6250 lb): 4224 mm (166.3 in.) aft of datum 
 
Max. rearward range: at 1500 kg (3307 lb): 4570 mm (179.90 in.) aft of datum 
at 2720 kg (5996 lb): 4387 mm (172.72 in.) aft of datum 
at 2835 kg (6250 lb): 4369 mm (172.0 in.) aft of datum 
Straight-line variation between points given. 
Lateral C.G. Limits 
Max. deviation 100mm (3.94 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range None 
 
Maximum Weight. 2720 kg (5996 lb) (Max GW 2835 kg (6250 lb) with S/B EC135-11-003 R01 or higher 
incorporated. See FMS 9.1-3) 
 
Minimum Crew. One Pilot 
 
Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb) 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank) 
Usable: 670.5 liters (177.1 US gal.) (standard fuel tank) 
 
Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank)  
Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank) 
 
Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight 
 
Maximum Operating Altitude. 6096 m (20000 ft) 
 
Rotorblade and Control Movements.   For rigging information refer to the EC135 Maintenance Manual.

Page 4 H88EU  
 
 
 
III. Model EC135P2 (Normal Category) Helicopter, Approved September 6, 2001 
 
The Model EC 135 P2 is the same as the EC 135P1 except for the installation of the Pratt & Whitney PW206B2 engine 
which includes new OEI power ratings. 
 
Engines. 2 Pratt & Whitney Canada PW 206 B2  
Fuel. See Rotorcraft Flight Manual 
Installed Engine Limits. Gas Generator 
Output Shaft Speed N-1 
Torque % % (RPM) 
Output Shaft 
Speed N-2 
 % (RPM) 
Measured Gas 
Temperature 
oC ( oF) 
Normal Operation 
Takeoff power (5 min.) 
 
75 
 
98.7 (57250) 
 
104 (6165) 
 
 
869 (1596) 
Max Continuous 69 97.4 (56500) 104 (6165) 835 (1535)  
 One Engine Inoperative 
30 sec. power 
 
128 
 
104.3 (60500) 
 
104 (6165) 
 
990 (1814) 
2 min. power 125 102.6 (59500) 104 (6165) 950 (1742) 
Max. Continuous 86 100.4 (58250) 104 (6165) 900 (1652) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 104 106 
 
Airspeed Limits (IAS). Max. v NE = 155 kts. See Rotorcraft Flight Manual for airspeed limit decrease 
with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum 
at 2835 kg (6250lb): 4224 mm (166.3 in.) aft of datum 
 
Max. rearward range: at 1500kg (3307 lb): 4570mm (179.9 in.) aft of datum 
at 2835kg (6250lb): 4369mm (172.0 in.) aft of datum 
Straight-line variation between points given. 
Lateral C.G. Limits 
Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range. None 
 
Max. Weight. 2835 kg (6250 lb) 
 
Min. Crew. One Pilot 
 
Passengers. Six (or seven if the kit described in FMS 9.2-31 is installed and operated) 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb) 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) 
Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) 
 
Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) 
Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) 
 
Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) 
Usable: 700.5 liters (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) 
Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent)

Page 5 H88EU  
 
 
Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
 
Oil Capacity. Engine oil capacity: 4.5 liters (1.19 US gal.) included in minimum gross weight 
 
Max. Operating Altitude. 6096 m (20000 ft.) 
 
Rotor blade and Control Movements.   For rigging information, refer to the EC135 Maintenance Manual. 
 
IV. Model EC135T2 (Normal Category) Helicopter, Approved November 25, 2002 
 
The Model EC 135 T2 is the same as the EC 135 T1 except for the installation of Safran Helicopter Engines Arrius 2B2 
engines, which  includes new OEI power ratings. 
 
Engines. 2 Safran Helicopter Engines ARRIUS 2B2 
 
Fuel. See Rotorcraft Flight Manual 
 
Installed Engine Limits (ARRIUS 2B2). 
Output Shaft 
Gas Generator 
Speed N-1 
Output Shaft 
Speed N-2 
Measured Gas 
Temperature 
Torque % 
Normal Operation 
% (RPM) % (RPM) oC (oF) 
Takeoff power (5 min.) 75 100 (54117) 104 (6134) 897 (1647) 
Max Continuous 69 99 (53576) 104 (6134) 879 (1614) 
One Engine Inoperative 
30 second power 
 
128 
 
105 (56823) 
 
104 (6134) 
 
1024 (1875) 
2.0 min. power 125 103.5 (56011) 104 (6134) 994 (1821) 
Max. Continuous 86 101.3 (54821) 104 (6134) 942 (1728) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 104 106 
 
Airspeed Limits (IAS). Max. v NE = 155 kts. See Rotorcraft Flight Manual for airspeed limit  
decrease with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 1840 kg (4057 lb): 4180 mm (164.6 in.) aft of datum 
at 2835 kg (6250 lb): 4224 mm (166.3 in.) aft of datum 
Max. rearward range: at 1500 kg (3307 lb): 4570 mm (179.9 in.) aft of datum 
at 2835 kg (6250 lb): 4369 mm (172.0 in.) aft of datum 
Straight line variation between points given. 
Lateral C.G. Limits 
Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range None 
 
Maximum Weight. 2835 kg (6250 lb) 
 
Minimum Crew. One Pilot 
 
Passengers. Six (or seven if the kit described in FMS 9.2-31 is installed and operated) 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb)

Page 6 H88EU  
 
 
IV. Model EC135T2 (Normal Category) Helicopter, Approved November 25, 2002 – (Cont’d) 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) 
Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) 
 
Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) 
Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) 
 
Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) 
Usable: 700.5 liters (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) 
 
Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
 
Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight 
 
Maximum Operating Altitude. 6096 m (20000) ft. 
 
Rotor blade and Control Movements.   For rigging information refer to the EC135 Maintenance Manual. 
 
V. Model EC135P2+ (Normal Category) Helicopter, Approved October 19, 2006 
 
The Model EC135P2+ is the same as the EC135P2 except for maximum takeoff mass of 2910 kg / 2950 kg, and new 
power ratings AEO TOP & OEI MCP). See NOTE 5 
 
Engines. 2 Pratt & Whitney Canada PW 206 B2  
Fuel. See Rotorcraft Flight Manual 
Installed Engine Limits. Gas Generator 
Output Shaft Speed N-1 
Output Shaft 
Speed N-2 
Measured Gas 
Temperature 
Torque %  % (RPM)  % (RPM) oC (oF) 
Normal Operation 
Takeoff power (5 min.) 
 
78 
 
98.7 (57250) 
 
104 (6165) 
 
 
869 (1596) 
Max Continuous 69 97.4 (56500) 104 (6165) 835 (1535)  
 One Engine Inoperative 
30 sec. power 
 
128 
 
104.3 (60500) 
 
104 (6165) 
 
990 (1814) 
2 min. power 125 102.6 (59500) 104 (6165) 950 (1742) 
Max. Continuous 89.5 100.4 (58250) 104 (6165) 900 (1652) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 104 106 
 
Airspeed Limits (IAS). Max. v NE = 155 kts. See Rotorcraft Flight Manual for airspeed limit decrease 
with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 1840 kg (4057 lb): 4180.0 mm (164.6 in.) aft of datum 
at 2910 kg (6415 lb): 4227.3 mm (166.43 in.) aft of datum 
at 2950 kg (6504 lb): 4229.3 mm (166.51 in.) aft of datum 
 
Max. rearward range: at 1500 kg (3307 lb): 4570.0 mm (179.9 in.) aft of datum 
at 2910 kg (5996 lb): 4369.0 mm (172.0 in.) aft of datum 
at 2950 kg (6504 lb): 4362.6 mm (171.75 in.) aft of datum 
Straight line variation between points given. 
Lateral C.G. Limits 
Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane.

Page 7 H88EU  
 
 
 
Empty Weight C.G. Range. None 
 
Maximum Weight. 2910 kg (6415 lb) / 2950 kg (6504 lb) 
 
Note: Operation of the aircraft with MTOW up to 2950 kg is only permitted in accordance 
with FMS 9.1-5, FMS 9.1-6 and FMS 9.1-7 from S/N 1055 and subsequent, or after SB 
EC135-62-028. 
 
Minimum Crew. One Pilot 
 
Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb) 
 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) 
Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) 
 
Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) 
Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) 
 
Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) 
Usable: 700.5 liter (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) 
 
Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
 
Oil Capacity. Engine oil capacity: 4.5 liters (1.19 US gal.) included in minimum gross weight 
 
Max. Operating Altitude. 6096 m (20000 ft) 
 
Rotor blade and Control Movements.   For rigging information, refer to the EC135 Maintenance Manual. 
 
VI. Models EC135T2+ and EC635T2+ (Normal Category) Helicopter, EC135T2+ Approved October 19, 2006 and 
EC635T2+ Approved October 30, 2019 
 
Data pertinent to both models. The Models EC135T2+ and EC635T2+ are the same as the EC135T2 except for maximum 
takeoff mass of 2910 kg / 2950 kg, and new power ratings AEO TOP & OEI MCP). See NOTE 5 
 
Engines. 2 Safran Helicopter Engines ARRIUS 2B2 
 
Fuel. See Rotorcraft Flight Manual 
Installed Engine Limits (ARRIUS 2B2). Gas Generator Output Shaft Measured Gas 
Output Shaft 
Torque % 
Normal Operation 
Speed N-1 
% (RPM) 
Speed N-2 
% (RPM) 
Temperature 
oC ( oF) 
Takeoff power (5 min.) 78 100 (54117) 104 (6134) 897 (1647) 
Max Continuous 69 99 (53576) 104 (6134) 879 (1614) 
One Engine Inoperative     
30 second power 128 105.0 (56823) 104 (6134) 1024 (1875) 
2.0 min. power 125 103.5 (56011) 104 (6134) 994 (1821) 
Max. Continuous 89.5 101.3 (54821) 104 (6134) 942 (1728) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 104 106

Page 8 H88EU  
 
 
Airspeed Limits (IAS). Max. v NE = 155 kts. See Rotorcraft Flight Manual for airspeed limit  
decrease with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 1840 kg (4057 lb): 4180.0 mm (164.6 in.) aft of datum 
at 2910 kg (6415 lb): 4227.3 mm (166.43 in.) aft of datum 
at 2950 kg (6504 lb): 4229.3 mm (166.51 in.) aft of datum 
 
Max. rearward range: at 1500 kg (3307 lb): 4570.0 mm (179.9 in.) aft of datum 
at 2910 kg (5996 lb): 4369.0 mm (172.0 in.) aft of datum 
at 2950 kg (6504 lb): 4362.6 mm (171.75 in.) aft of datum 
Straight-line variation between points given. 
Lateral C.G. Limits 
Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range None 
 
Maximum Weight. 2910 kg (6415 lb) / 2950 kg (6504 lb) 
 
Note: Operation of the aircraft with MTOW up to 2950 kg is only permitted in accordance 
with FMS 9.1-5, FMS 9.1-6 and FMS 9.1-7 from S/N 1055 and subsequent, or after SB 
EC135-62-028. 
 
Minimum Crew. One Pilot 
 
Passengers. Six (or 7 if the kit described in FMS 9.2-31 is installed and operated) 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb) 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) (standard fuel tank, up to S/N 249) 
Usable: 670.5 liters (177.1 US gal.) (standard fuel tank, up to S/N 249) 
 
Total: 673.4 liters (177.9 US gal.) (self-sealing fuel tank, up to S/N 249) 
Usable: 664 liters (175.4 US gal.) (self-sealing fuel tank, up to S/N 249) 
 
Total: 710 liters (187.6 US gal.) (standard fuel tank, S/N 250 and subsequent) 
Usable: 700.5 liter (185.1 US gal.) (standard fuel tank, S/N 250 and subsequent) 
 
Total: 701 liters (185.2 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
Usable: 691.6 liters (182.7 US gal.) (self-sealing fuel tank, S/N 250 and subsequent) 
 
Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight 
 
Maximum Operating Altitude. 6096 m (20000 ft.) 
 
Rotor blade and Control Movements.   For rigging information, refer to the EC135 Maintenance Manual. 
 
Additional Information. 
SN 0858 was converted from an EC635T2+ to an EC135T2+ with the application of major modification E6065 via Airbus 
Helicopters SB-EC135-00-002. The aircraft has two data plates identifying it as a converted EC635T2+ and carries the same 
certification basis and same continued airworthiness requirements as an EC135T2+. See NOTE 7. 
 
VII. Model EC135P3 (Normal Category) Helicopter, Approved September 3, 2015, Revised March 6, 2023 
For Models EC135P3 equipped with avionics configuration HELIONIX (Mod E-2698), see Note 5. 
 
Engines. 2 Pratt & Whitney Canada PW 206 B3  
Fuel. See Rotorcraft Flight Manual   
Installed Engine Limits. Gas Generator 
Output Shaft Speed N-1 
Output Shaft 
Speed N-2 
Measured Gas 
Temperature (TOT)

Page 9 H88EU  
 
 
Torque % %  %  oC ( oF) 
 
Normal Operation 
Takeoff power (5 min.) 
 
78 
 
99.8 
 
105.5 
 
900 (1652) 
Max Continuous 69 97.4 105.5 835 (1535) 
 One Engine Inoperative 
30 sec. power 
 
128 
 
104.3 
 
104.5 
 
990 (1814) 
2 min. power 125 102.6 104.5 950 (1742) 
Max. Continuous 89.5 99.8 104.5 900 (1652) 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 105.5 106 
 
Airspeed Limits (IAS). Max. v NE = 150 kts. See Rotorcraft Flight Manual for airspeed limit decrease 
with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 2039 kg (4495 lb): 4152 mm (163.5 in.) aft of datum 
at 2980 kg (6569 lb): 4201 mm (165.4 in.) aft of datum 
 
Max. rearward range: at 1600 kg (3527 lb): 4555 mm (179.3 in.) aft of datum 
at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum 
For Models EC135P3 equipped with avionics configuration HELIONIX (Mod E-2698) 
Max. forward range:         at 2150 kg (4740 lb): 4121 mm (162.2 in.) aft of datum 
            at 2980 kg (6569 lb): 4171 mm (164.2 in.) aft of datum 
                                          at 3100 kg (6834 lb): 4178 mm (164.5 in.) aft of datum 
 
Max. rearward range:       at 1700 kg (3748 lb): 4541 mm (178.8 in.) aft of datum 
            at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum 
            at 3100 kg (6834 lb): 4353 mm (171.4 in.) aft of datum 
 
   Straight-line variation between points given. 
 
Lateral C.G. Limits 
Max. deviation: 100 mm (3.94 in.) left or right of the fuselage median plane. 
 
For Models EC135P3 equipped with avionics configuration HELIONIX (Mod E-2698) 
Max. deviation 50 mm (1.97 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range. None 
 
Maximum Weight. 2980 kg (6569 lb) 
 Flight with increased gross weight above 2980 kg (6569 lb) up to 3100 kg (6834 lb) is 
 permitted only in accordance with FMA 11-11. 
 
Minimum Crew. One Pilot 
 
Passengers. Seven 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb) 
 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.) 
Usable: 670.5 liters (177.1 US gal.) 
 
Total: 710 liters (187.6 US gal.) 
Usable: 700.5 liters (185.1 US gal.) 
 
Oil Capacity. Engine oil capacity: 4.5 liters (1.19 US gal.) included in minimum gross weight 
 
Max. Operating Altitude. 6096 m (20000 ft.)

Page 10 H88EU  
 
 
Rotor blade and Control Movements.   For rigging information, refer to the EC135 Maintenance Manual. 
 
VIII. Model EC135T3 (Normal Category) Helicopter, Approved September 3, 2015, Revised March 6, 2023 
For Models EC135T3 equipped with avionics configuration HELIONIX (Mod E-2698), see Note 5. 
 
Engines. 2 Safran Helicopter Engines ARRIUS 2B2 
 
Fuel. See Rotorcraft Flight Manual 
 
Installed Engine Limits (ARRIUS 2B2). 
Output Shaft 
Gas Generator 
Speed N-1 
Output Shaft 
Speed N-2 
Measured Gas 
Temperature (TOT) 
Torque % 
Normal Operation 
%  %   oC (oF) 
Takeoff power (5 min.) 78 86.1-100 106  897 (1647) 
Max Continuous 69 85.3-99 106  879 (1614) 
One Engine Inoperative 
30 second power 
 
128 
 
91.7-104.8 
  
106 
 
1024 (1875) 
2.0 min. power 125 91.7-103.5  106 994 (1821) 
Max. Continuous 89.5 87.4-101.25  106 942 (1728) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients 
 
Rotor Limits.  Power On % Power Off % 
 Min. Continuous 97 80 for gross mass up to 1900 kg (4189 lb) 
   85 for gross mass above 1900 kg (4189 lb) 
 Max. Continuous 105.5 106 
 
Airspeed Limits (IAS). Max. v NE = 150 kts. See Rotorcraft Flight Manual for airspeed limit  
decrease with outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits 
Max. forward range: at 2039 kg (4495 lb): 4152 mm (163.5 in.) aft of datum 
at 2980 kg (6569 lb): 4201 mm (165.4 in.) aft of datum 
 
Max. rearward range: at 1600 kg (3527 lb): 4555 mm (179.3 in.) aft of datum 
at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum 
For Models EC135T3 equipped with avionics configuration HELIONIX (Mod E-2698) 
Max. forward range:         at 2150 kg (4740 lb): 4121 mm (162.2 in.) aft of datum 
            at 2980 kg (6569 lb): 4171 mm (164.2 in.) aft of datum 
                                          at 3100 kg (6834 lb): 4178 mm (164.5 in.) aft of datum 
 
Max. rearward range:       at 1700 kg (3748 lb): 4541 mm (178.8 in.) aft of datum 
            at 2980 kg (6569 lb): 4369 mm (172 in.) aft of datum 
            at 3100 kg (6834 lb): 4353 mm (171.4 in.) aft of datum 
 
                                                                                                                             Straight-line variation between points given. 
Lateral C.G. Limits 
Max. deviation 100 mm (3.94 in.) left or right of the fuselage median plane. 
 
For Models EC135T3 equipped with avionics configuration HELIONIX (Mod E-2698) 
Max. deviation 50 mm (1.97 in.) left or right of the fuselage median plane. 
 
Empty Weight C.G. Range None 
 
Maximum Weight. 2980 kg (6569 lb) 
Flight with increased gross weight above 2980 kg (6569 lb) up to 3100 kg (6834 lb) is 
permitted only in accordance with FMA 11-11. 
 
Minimum Crew. One Pilot 
 
Passengers. Seven 
 
Max. Baggage. Max. permissible floor loading: 600 kg/m 2 (123 lb/sq. ft.) 
Max. loading: 1130 kg (2491 lb.)

Page 11 H88EU  
 
 
Fuel Capacity. Total: 680 liters (179.6 US gal.)            
Usable: 670.5 liters (177.1 US gal.) 
 
Total: 710 liters (187.6 US gal.) 
Usable: 700.5 liters (185.1 US gal.) 
 
 
Oil Capacity. Engine oil capacity: 4.85 liters (1.28 US gal.) included in minimum gross weight 
 
Maximum Operating Altitude. 6096 m (20000 ft.) 
 
Rotor blade and Control Movements.   For rigging information, refer to the EC135Maintenance Manual. 
 
DATA PERTINENT TO ALL MODELS 
 
Datum. 2160 mm (85.04 in.) in front of alignment point in the frame of the front doors. 
 
Leveling Means. Alignment points are given in the EC135 Maintenance Manual 
 
Series Nos. Eligible. A German (Luftfahrt-Bundesamt, LBA) Certificate of Airworthiness endorsed as noted 
below under “Import Requirements” must be submitted for each individual rotorcraft for 
which application for FAA certification is made. For the Model EC135P1 serial numbers 
0006 and subsequent. For the Model EC135T1 serial numbers 0005 and subsequent. 
 
Production Basis.  The Model Aircraft listed in this Type Certificate Data Sheet are manufactured by Airbus   
Helicopters Deutschland GmbH in Germany. 
 
Certification Basis. - FAR 21.29 
- FAR 27, incl. Amdt. 31 
- FAR 29, incl. Amdt. 37, for engine isolation requirements 
- FAR 36 
- Special Condition defined in Issue Paper G-1 
- 14 CFR § 29.1557(d) Miscellaneous markings and placards (documented in ELOS 
Memo AT04289RD-R-C-1) 
 
For the model EC135T3/P3: 
Type Certificate No. H88EU amended September 3, 2015. 
Date of application for amended Type Certificate: November 12, 2012 
 
FAR 21.29, FAR 27 effective February 1, 1965, with Amendments 27-1 through    
27-31 
 
 For IFR certification: FAR 27 Appendix B through Amdt 27-44 requirements 
For Category A Certification: FAR 27 Appendix C through Amdt 27-33 
 
For all the changed areas compared to EC135T2+/P2+, FAR 27 through Amdt 27-44 
for the following requirements: 
 
27.21 27.303 27.610 27.1091 27.1529 
27.25 27.305 27.611 27.1093 27.1541 
27.27 27.307 27.613 27.1141 27.1545 
27.29 27.309 27.629 27.1143 27.1549 
27.31 27.321 27.653 27.1187 27.1559 
27.33 27.337 27.659 27.1193 27.1581 
27.45 27.339 27.661 27.1301 27.1583 
27.49 27.341 27.663 27.1305  
27.51 27.351 27.671 27.1309  
27.65 27.361 27.672 27.1317  
27.67 27.391 27.681 27.1321  
27.75 27.427 27.683 27.1323  
27.79 27.471 27.691 27.1329  
27.141 27.473 27.695 27.1351  
27.143 27.501 27.771 27.1365  
27.151 27.521 27.853 27.1381  
27.161 27.547 27.865 27.1435  
27.171 27.549 27.901 27.1501  
27.173 27.561 27.903 27.1503

Page 12 H88EU  
 
 
27.175 27.571 27.907 27.1505  
27.177 27.601 27.931 27.1509  
27.231 27.602 27.939 27.1519  
27.241 27.603 27.1041 27.1521  
27.251 27.607 27.1043 27.1525  
27.301 27.609 27.1045 27.1527  
 
Environmental Standards: 
14 CFR Part 36, Appendix H, Amendment 36-31 
 
The main differences between the EC135T2+/P2+ and the EC135T3/P3 are as 
follows: 
a. Increase of the maximum Take-off Weight from 2950kg to 2980kg 
b. Increase of main rotor blade geometry and length to improve the rotor blade 
efficiency 
c. Introduction of Lateral Engine Air Inlet to reduce the engine air intake losses 
d. Increase of engine performance through FADEC software change. 
e. MEGHAS software adaptation for the new dynamics of the helicopter and 
adaptation of 3-Axis autopilot software resulting from these changes. 
 
For Models EC135P3/T3 equipped with avionics configuration Helionix (Mod E-2698): 
EASA variant: EC 135 P3H / T3H 
Type Certificate Data Sheet H88EU amended November 30, 2017 
 
The certification basis as established in Type Certificate Data Sheet (TCDS) H88EU for 
the EC135T3/P3 for areas unaffected by this change. 
 
For IFR certification: FAR 27 Appendix B through Amdt 27-46 requirements 
 
For all the changed areas compared to EC135T3/P3, FAR 27 through Amdt 27-47 for the 
following requirements: 
 
27.610 27.1309 27.1316 27.1457 27.1459 
 
Equivalent Safety Findings: 
a. 14 CFR § 27.1305 Powerplant instruments (documented in ELOS Memo 
AT04292RD-R-P-1) 
b. 14 CFR § 27.1549 Powerplant instruments (documented in ELOS Memo 
AT04292RD-R-P-1) 
c. 14 CFR § 27.1305 Powerplant Instruments; 27.1321(a) Arrangement and 
Visibility; 27.1351(d)(1) Electrical Systems and Equipment, General; and 
Section C27.2 for 29.1305(a)(6) and (b)(1) Powerplant Instruments 
(documented in ELOS Memo AT04292RD-R-S-1) 
d. 14 CFR § 27.1545(b)(4) Airspeed indicator, and 27.1549(b) Powerplant 
instruments (documented in ELOS Memo AT04292RD-R-F-1) 
 
Main differences of the HELIONIX configuration to the basic configuration EC135P3/T3: 
a. 3 Liquid Crystal Displays for a Single Pilot / Dual Pilot Operational Capability 
b. 2 Aircraft Management Computers 
c. Primary flight and navigation sensors: 2 Attitude Heading Reference Unit, 2 
Magnetic Aircraft Sensor and 2 Air Data Computers 
d. 1 Multi-Purpose Control Panel including directional Gyro Mode control to activate 
the free steering mode 
e. 1 Data Transfer Device for uploading/downloading operations and to provide ground 
data communication 
f. 1 Integrated Standby Instrument System including backup SAS functionality 
g. 1 four-axis Automatic Flight Control System 
h. Autopilot Control Panel 
 
The German Authority Luftfahrt-Bundesamt (LBA) originally type certificated this under 
its type certificate number (LBA 3061). The FAA validated this product under U.S. Type 
Certificate Number (H88EU). Effective September 28, 2003, the European Aviation 
Safety Agency (EASA) began oversight of this product on behalf of the German LBA 
(EASA TC R.009). 
 
Import Requirements. To be considered eligible for operation in the United States, each aircraft manufactured under 
this type certificate must be accompanied by a certificate of airworthiness for export or 
certifying statement endorsed by the exporting foreign civil airworthiness authority which

Page 13 H88EU  
 
 
states (in the English language): “The aircraft covered by this certificate has been examined, 
test, and found to comply with the German LBA TC Number 3061 (or EASA TC Number 
R.009) approved under the U.S. Type Certificate Number H88EU 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. 
 
 
The EC135 P3H or EC135 T3H is an EASA variant that corresponds to the FAA validated 
EC135P3 or EC135T3 model equipped with HELIONIX for SN 2001 and up. FAA 
documentation does not identify or distinguish between these variants. 
 
Equipment. The minimum required equipment as prescribed in the applicable airworthiness regulations (see 
Certification Basis) must be installed in the respective helicopter for certification. 
 
For model EC135P1, LBA-approved EC135P1 Rotorcraft Flight Manual, dated 
14.06.1996 Revision 0, or later approved revision, as required. LBA-approved EC135P1 
(CPDS) Rotorcraft Flight Manual (for helicopters with Central Panel Display System 
installed), dated November 6, 1998, Revision 0, or later approved revision. 
 
For model EC135T1, LBA-approved EC135T1 Rotorcraft Flight Manual, 
dated 14.06.1996 Revision 0, or later approved revision, as required. LBA-approved 
EC135T1 (CPDS) Rotorcraft Flight Manual (for helicopters with Central Panel Display 
System installed), dated May 26, 1999, Revision 0, or later approved revision. 
 
For model EC135P2, LBA-approved EC135P2(CPDS) Rotorcraft Flight Manual, 
dated July 10, 2001, Revision 0, or later approved revision, as required. 
 
For model EC135T2, LBA-approved EC135T2(CPDS) Rotorcraft Flight Manual, 
dated August 9, 2002, Revision 0, or later approved revision, as required. 
 
For model EC135P2+, EASA-approved EC135P2+ Rotorcraft Flight Manual, 
dated February 21, 2006, Revision 0, or later approved revision, as required. 
 
For model EC135T2+, EASA-approved EC135T2+ Rotorcraft Flight Manual, 
dated February 21, 2006, Revision 0, or later approved revision, as required. 
 
For model EC135P3, EASA-approved EC135P3(CPDS) Rotorcraft Flight Manual, dated 
March 18, 2015, Revision 0, or later approved revision, as required. For rotorcraft  
equipped with avionics configuration HELIONIX (Mod E-2698), EASA-approved  
EC135P3H Rotorcraft Flight Manual, dated October 4, 2017, Revision 4, or later  
approved revision, as required. 
 
For model EC135T3, EASA-approved EC135T3(CPDS) Rotorcraft Flight Manual, dated  
October 17, 2014, Revision 0, or later approved revision, as required. For rotorcraft  
equipped with avionics configuration HELIONIX (Mod E-2698), EASA-approved  
EC135T3H Rotorcraft Flight Manual, dated October 4, 2017, Revision 4, or later  
approved revision, as required. 
 
For Category A special operation, the configuration requirements as defined in section 
A.2.2 of the applicable 9.1-1 Rotorcraft Flight Manual Supplement must be met. 
 
Service Information. Service bulletins, repair manuals, vendor manuals, rotorcraft flight manuals and 
maintenance manuals, which contain a statement that the document is approved by the 
European Aviation Safety Agency (EASA) or, for approvals made before September 28, 
2003, by the German LBA, are accepted by the FAA and are considered FAA approved. 
These approvals pertain to the type design only. 
 
NOTES 
 
NOTE 1. Safran Helicopter Engines ARRIUS 2B1 engines installed in EC135T1 serial numbers 
0036 and subsequent. ARRIUS 2B1 engine installation limitations apply if ECD Service 
Bulletin EC135-71-001 is incorporated on EC135T1 serial numbers 0035 and prior.

Page 14 H88EU  
 
 
NOTE 2. The model EC-135 rotorcraft employs electronic engine controls, commonly named Full 
Authority Digital Engine Controls (FADEC) and is recognized to be more susceptible to 
Electromagnetic Interference (EMI) than rotorcraft that have only manual (non-electronic) 
controls. (EMI may be the result of radiated or conducted interference.) For this reason 
modifications that add or change systems that have the potential for EMI, must either be 
qualified to a standard acceptable to the FAA or tested at the time of installation for 
interference to the FADEC. This type of testing must employ the particular FADEC’s 
diagnostic techniques and external diagnostic techniques. The test procedure must be FAA 
approved. 
 
NOTE 3. Life limitations for the EC135 P1, P2 , P3, T1, T2, and T3 are provided in the Chapter 4 
Airworthiness Limitations Section. 
 
NOTE 4. For the EC 135(CPDS) to be eligible for SPIFR-Cockpit with AFCS and AN 
Flight Displays the following RFM supplements are required; FMS 9.2-48, Revision 4, 
Automatic 
Flight Control System, LBA approved December 22, 2000, FMS 9.2-53, Revision 2, Single 
Flight Control Display System, LBA approved September 7, 2000, and FMS 9.2-56, 
Revision 3, SP/DPIFR Operation Kit, LBA approved August 17, 2000. 
 
NOTE 5. EC135P2+ starts with S/N 505 or upgraded EC135P2 model according to Service Bulletin 
EC135-71-033. 
 
EC135T2+ starts with S/N 506 or upgraded EC135T2 model according to Service 
Bulletin EC135-71-033. 
 
EC135P3 starts with S/N 1178 or upgraded EC135P2+ model according to Service 
Bulletin EC135-71T-045. 
 
EC135P3 rotorcraft equipped with avionics configuration HELIONIX (Mod E-2698) 
starts with S/N 2006. 
 
EC135T3 starts with S/N 1155 or upgraded EC135T2+ model according to Service 
Bulletin EC135-71T-045. 
 
EC135T3 rotorcraft equipped with avionics configuration HELIONIX (Mod E-2698) 
starts with S/N 2001. 
 
NOTE 6. EC135P3/T3 rotorcraft equipped with avionics configuration HELIONIX (Mod E-2698) 
must comply with Type Design Definition as defined in AH document, EC135 Type 
Design Definition for United States of America, E0000M2698USA. 
 
NOTE 7 The EC635T2+ mandatory continued operational safety requirements issued by EASA 
have not been addressed by the FAA; therefore, import of EC635T2+ models is limited to 
SN 0858. This aircraft was converted from an EC635T2+ to an EC135T2+ and has 
maintained its continued airworthiness by meeting regulatory requirements defined for 
the EC135T2+. No other serial numbers are eligible for conversion and import. 
 
 
-- END --
```

## ADs (75, first 50, in force first)

- [AD 2026-20-06](https://openairdocs.org/ad/2026-20-06): Main rotor gearbox · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 6 more. Effective Oct 13, 2026
- [AD 2026-17-05](https://openairdocs.org/ad/2026-17-05): Cabin Equipment/Furnishings · Airbus Helicopters H160-B, EC225LP, AS 365 N3 and 18 more. Effective Oct 2, 2026
- [AD 2026-08-10](https://openairdocs.org/ad/2026-08-10): Passenger compartment equipment · B/E Aerospace Fischer Medical Seat 230/305, EC135P1, EC135T1 and 19 more. Effective May 11, 2026
- [AD 2026-02-01](https://openairdocs.org/ad/2026-02-01): Tail Rotor Drive Shaft · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 6 more. Effective Feb 26, 2026
- [AD 2026-03-02](https://openairdocs.org/ad/2026-03-02): Rotorcraft Tail Boom · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 6 more. Effective Feb 17, 2026
- [AD 2025-18-04](https://openairdocs.org/ad/2025-18-04): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 9 more. Effective Oct 21, 2025
- [AD 2025-13-06](https://openairdocs.org/ad/2025-13-06): Tail Rotor Control System · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 6 more. Effective Jul 18, 2025
- [AD 2025-07-01](https://openairdocs.org/ad/2025-07-01): Air Data Computer · Synthetic Vision Electronic Flight Information System (Arrow STC SR09595RC or ST01523WI). Effective May 15, 2025
- [AD 2025-04-10](https://openairdocs.org/ad/2025-04-10): Emergency equipment · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 10 more. Effective Mar 24, 2025
- [AD 2024-20-07](https://openairdocs.org/ad/2024-20-07): Emergency Equipment; Emergency Flotation Section · Apical Emergency Float Kit, P/N 20498 (STC SR00780LA or 12 others). Effective Dec 5, 2024
- [AD 2024-17-01](https://openairdocs.org/ad/2024-17-01): Main Rotor Control · Airbus EC135P1, EC135P2, EC135P2+ and 6 more. Effective Nov 4, 2024
- [AD 2024-04-01](https://openairdocs.org/ad/2024-04-01): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 8 more. Effective Apr 19, 2024
- [AD 2024-04-10](https://openairdocs.org/ad/2024-04-10): Tail Rotor Blades · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 6 more. Effective Mar 19, 2024
- [AD 2023-05-09](https://openairdocs.org/ad/2023-05-09): Instrument System Wiring · Airbus Helicopters Deutschland EC135P3, EC135T3, MBB-BK 117 D-2 and 1 more. Effective Mar 31, 2023
- [AD 2022-17-01](https://openairdocs.org/ad/2022-17-01): Air Conditioning System · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 5 more. Effective Sep 27, 2022
- [AD 2022-10-51](https://openairdocs.org/ad/2022-10-51): Flight Control System · Airbus Helicopters AS350B, AS350B1, AS350B2 and 22 more. Effective Jun 7, 2022
- [AD 2022-05-10](https://openairdocs.org/ad/2022-05-10): Cabin Equipment/Furnishings · Airbus Helicopters AS332L, AS332L1, AS332L2 and 57 more. Effective Apr 20, 2022
- [AD 2022-02-19](https://openairdocs.org/ad/2022-02-19): Flight Compartment Equipment · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 5 more. Effective Mar 17, 2022
- [AD 2022-01-03](https://openairdocs.org/ad/2022-01-03): Fire Bottle, Portable · Airbus Helicopters AS332C, AS332C1, AS332L and 35 more. Effective Mar 7, 2022
- [AD 2021-24-17](https://openairdocs.org/ad/2021-24-17): Tail rotor blades · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 5 more. Effective Jan 18, 2022
- [AD 2021-24-05](https://openairdocs.org/ad/2021-24-05): Cargo Compartments · Airbus Helicopters Deutschland EC135P2+, EC135P3, EC135T2+/EC635T2+ and 1 more. Effective Jan 14, 2022
- [AD 2021-21-01](https://openairdocs.org/ad/2021-21-01): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 5 more. Effective Dec 10, 2021
- [AD 2021-17-17](https://openairdocs.org/ad/2021-17-17): Cabin Equipment/Furnishings · Airbus Helicopters EC135P3, EC135T3, MBB-BK 117 C-2 and 32 more. Effective Nov 22, 2021
- [AD 2021-22-07](https://openairdocs.org/ad/2021-22-07): Fire Bottle, Portable · Airbus A319-111, A319-112, A319-113 and 127 more. Effective Nov 18, 2021
- [AD 2021-16-10](https://openairdocs.org/ad/2021-16-10): Tail Rotor Blades · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective Oct 13, 2021
- [AD 2021-13-05](https://openairdocs.org/ad/2021-13-05): Tail Rotor Control System · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective Aug 11, 2021
- [AD 2021-07-12](https://openairdocs.org/ad/2021-07-12): Rotorcraft Flight Control · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective May 11, 2021
- [AD 2021-09-07](https://openairdocs.org/ad/2021-09-07): Rotorcraft Flight Control · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective May 10, 2021
- [AD 2021-03-04](https://openairdocs.org/ad/2021-03-04): Fasteners, Tail Rotor Drive Shaft · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective Mar 29, 2021
- [AD 2020-26-03](https://openairdocs.org/ad/2020-26-03): Rotorcraft Flight Control · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective Jan 22, 2021
- [AD 2020-22-04](https://openairdocs.org/ad/2020-22-04): Tail Rotor Drive · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective Nov 18, 2020
- [AD 2014-05-06 R2](https://openairdocs.org/ad/2014-05-06-R2): Main Rotor Control · Airbus Helicopters Deutschland MBB-BK 117 C-2, EC135P1, EC135P2 and 4 more. Effective Feb 19, 2019
- [AD 2013-21-05 R1](https://openairdocs.org/ad/2013-21-05-R1): Tail Rotor Control System · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Dec 21, 2018
- [AD 2018-07-01](https://openairdocs.org/ad/2018-07-01): Main Rotor Gearbox · Airbus Helicopters Deutschland EC135P3, EC135T3, EC135P1 and 5 more. Effective May 3, 2018
- [AD 2017-03-01](https://openairdocs.org/ad/2017-03-01): Main Rotor Control · Airbus Helicopters Deutschland MBB-BK 117 C-2, EC135P1, EC135P2 and 4 more. Effective Mar 31, 2017
- [AD 2015-12-09 R1](https://openairdocs.org/ad/2015-12-09-R1): Flight Controller · Airbus Helicopters Deutschland MBB-BK 117 C-2, EC135P1, EC135P2 and 4 more. Effective Feb 25, 2016
- [AD 2014-16-24](https://openairdocs.org/ad/2014-16-24): Main Rotor Head · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Sep 25, 2014
- [AD 2014-05-01](https://openairdocs.org/ad/2014-05-01): Main Rotor Gearbox · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Apr 14, 2014
- [AD 2014-01-02](https://openairdocs.org/ad/2014-01-02): Air conditioning system · Airbus Helicopters Deutschland EC135P2+ and EC135T2+/EC635T2+. Effective Mar 3, 2014
- [AD 2013-21-06](https://openairdocs.org/ad/2013-21-06): Fuselage, Equipment Attach Fittings · Airbus Helicopters Deutschland MBB-BK 117 C-2, EC135P1, EC135P2 and 4 more. Effective Jan 31, 2014
- [AD 2013-18-05](https://openairdocs.org/ad/2013-18-05): Extinguishing System · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Oct 18, 2013
- [AD 2013-11-15](https://openairdocs.org/ad/2013-11-15): Main Rotor Control · Airbus Helicopters Deutschland BO-105A, BO-105C, BO-105LS A-1 and 14 more. Effective Jul 26, 2013
- [AD 2013-06-51](https://openairdocs.org/ad/2013-06-51): Equipment/Furnishings · Agusta A109, A109A, A109A II and 43 more. Effective Jul 15, 2013
- [AD 2013-10-01](https://openairdocs.org/ad/2013-10-01): Exterior lighting · Agusta AB139, AW139, MBB-BK 117 C-2 and 7 more. Effective Jun 20, 2013
- [AD 2012-23-07](https://openairdocs.org/ad/2012-23-07): Main Rotor Mast/Swashplate · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135T1 and 1 more. Effective Jan 11, 2013
- [AD 2012-11-02](https://openairdocs.org/ad/2012-11-02): Crack · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Jul 10, 2012
- [AD 2012-03-01](https://openairdocs.org/ad/2012-03-01): Engine Controls · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Mar 21, 2012
- [AD 2011-25-01](https://openairdocs.org/ad/2011-25-01): Liferafts · Agusta AB412, AB412 EP, 206A and 23 more. Effective Jan 17, 2012
- [AD 2009-11-10](https://openairdocs.org/ad/2009-11-10): Main rotor drive · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Jun 12, 2009
- [AD 2008-04-05](https://openairdocs.org/ad/2008-04-05): Wiring harness · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 3 more. Effective Mar 6, 2008

All 75: https://openairdocs.org/tcds/H88EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Eurocopter Deutschland EC 135 P2+](https://openairdocs.org/model/eurocopter-deutschland-ec-135-p2-plus): 166 aircraft (registry code 5620030)
- [Eurocopter Deutschland EC 135 T2+](https://openairdocs.org/model/eurocopter-deutschland-ec-135-t2-plus): 45 aircraft (registry code 5620031)
- [Airbus Helicopters Deutschland EC135 P3](https://openairdocs.org/model/airbus-helicopters-deutschland-ec135-p3): 34 aircraft (registry code 5620040)
- [Eurocopter Deutschland EC 135 P2](https://openairdocs.org/model/eurocopter-deutschland-ec-135-p2): 31 aircraft (registry code 5620027)
- [Airbus Helicopters Deutschland EC135T3](https://openairdocs.org/model/airbus-helicopters-deutschland-ec135t3): 27 aircraft (registry code 5620038)
- [Airbus Helicopters EC135 P3](https://openairdocs.org/model/airbus-helicopters-ec135-p3): 16 aircraft (registry code 8680151)
- [Eurocopter Deutschland EC135T2](https://openairdocs.org/model/eurocopter-deutschland-ec135t2): 16 aircraft (registry code 5620032)
- [Eurocopter Deutschland EC135P1](https://openairdocs.org/model/eurocopter-deutschland-ec135p1): 14 aircraft (registry code 8680990)
- [Eurocopter Deutschland EC135T1](https://openairdocs.org/model/eurocopter-deutschland-ec135t1): 14 aircraft (registry code 5620026)
- [Airbus Helicopters Deutschland EC135 P2+](https://openairdocs.org/model/airbus-helicopters-deutschland-ec135-p2-plus): 13 aircraft (registry code 5620010)
- [Airbus Helicopters EC135T3](https://openairdocs.org/model/airbus-helicopters-ec135t3): 13 aircraft (registry code 5620028)
- [Airbus Helicopters Deutschland EC135T2+](https://openairdocs.org/model/airbus-helicopters-deutschland-ec135t2-plus): 5 aircraft (registry code 5620033)
- [Eurocopter Deutschland EC-135](https://openairdocs.org/model/eurocopter-deutschland-ec-135): 2 aircraft (registry code 5620029)
- [Eurocopter Espana EC135 T2+](https://openairdocs.org/model/eurocopter-espana-ec135-t2-plus): 2 aircraft (registry code 8681010)
- [Eurocopter Deutschland EC135 P3](https://openairdocs.org/model/eurocopter-deutschland-ec135-p3): 1 aircraft (registry code 5620039)

## STCs approved under this data sheet (125, first 50)

- [STC SR12474NY](https://openairdocs.org/stc/SR12474NY): Installation of replacement windows. Tech-Tool Plastics, Inc.
- [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems
- [STC SR11844CH](https://openairdocs.org/stc/SR11844CH): Installation of Heli-Preheat Kit, p/n TA3391-1 for 115 volt application. Hartzell Propeller LLC
- [STC SR04464NY](https://openairdocs.org/stc/SR04464NY): Installation of the iPad Mount. Avio Design Group Inc.
- [STC SR00521SE](https://openairdocs.org/stc/SR00521SE): Installation of Geneva Aviation Audio System. AEM USA Inc.
- [STC SR02301SE](https://openairdocs.org/stc/SR02301SE): Installation of Geneva Aviation 28 - 14 VDC Power Converter. AEM USA Inc.
- [STC SR02445SE](https://openairdocs.org/stc/SR02445SE): Installation of P178 Failsafe Audio Mixer. AEM USA Inc.
- [STC SR00202IB](https://openairdocs.org/stc/SR00202IB): Installation of Emergency Medical Services (EMS) Equipment, either P/N 135-0238317-501 or P/N
135-0238317-502. AEROLITE AG
- [STC SR00440DE-D](https://openairdocs.org/stc/SR00440DE-D): Installation of exterior lighting system. Air Methods LLC
- [STC SR12092IB](https://openairdocs.org/stc/SR12092IB): Manufacturing and Installation of Cargo Hold Nets. ICARUS AERO INC.
- [STC SR12065DE](https://openairdocs.org/stc/SR12065DE): Installation of Honeywell 5G Bandpass Filter into existing KRA 405B Radar Altimeter Systems. QAI Aviation Inc.
- [STC SR04842NY](https://openairdocs.org/stc/SR04842NY): Installation of RMCI Inc. Expandable Rotorcraft Diagnostic System (XRDS). Sterling Helicopter
- [STC SR04711NY](https://openairdocs.org/stc/SR04711NY): Replacement of Luminator LS400 LED searchlight (steerable landing light). Sterling Helicopter
- [STC SR11343DS](https://openairdocs.org/stc/SR11343DS): Installation of TDFM-9000 Communication System. Airbus Helicopters Inc.
- [STC SR11857IB](https://openairdocs.org/stc/SR11857IB): Installation of SkyTrac ISAT-200A Flight Following / Satcom System. SkyTrac Systems Ltd.
- [STC SR01790SE](https://openairdocs.org/stc/SR01790SE): Installation of Skidtube and Skidtube extension. Dart Aerospace USA Inc.
- [STC SR09947AC](https://openairdocs.org/stc/SR09947AC): Replacement of the original N2 tachometer with a corresponding Ahlers tachometer. Ahlers Aerospace Inc.
- [STC SR00182IB](https://openairdocs.org/stc/SR00182IB): Installation of the Avidyne Integrated Flight Display (IFD) Navigator(s). Horizon Design Services Ltd.
- [STC SR03704NY](https://openairdocs.org/stc/SR03704NY): Installation of Air Ambulance Technology GmbH's P/N 135-25-20-5000-600 Series Air Ambulance Equipment (EMS config)
or P/N 135-25-20-5000-900 Series VIP Interior (VIP config). Air Ambulance Technology GmbH
- [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 SR00368BO](https://openairdocs.org/stc/SR00368BO): Installation of an Outerlink SATCOM Communications and Flight Data Monitoring System KIT 135-SAT-100. Outerlink Corporation
- [STC SR02217SE](https://openairdocs.org/stc/SR02217SE): Fabrication of Onboard Systems Single-Hook and Double-Hook Cargo Hook Kit. Onboard Systems
- [STC SR09559RC](https://openairdocs.org/stc/SR09559RC): Installation of Night Vision Goggle Compatible Interior Lighting System. REB Technologies Inc.
- [STC SR09102RC-D](https://openairdocs.org/stc/SR09102RC-D): Installation of windows in crew, cabin, and cargo doors. Tech-Tool Plastics Inc
- [STC SR09116RC-D](https://openairdocs.org/stc/SR09116RC-D): Installation of a sliding window in the rear sliding door.. Tech-Tool Plastics Inc
- [STC SR09105RC-D](https://openairdocs.org/stc/SR09105RC-D): Installation of a Concorde RG-390E or RG-380E/44 Lead Acid Battery. Airbus Helicopters Inc.
- [STC SR09919AC](https://openairdocs.org/stc/SR09919AC): Installation of a Luminator search light LS-400, LS-400M, or LS-400T. Luminator Holdings L.P.
- [STC SR02138LA](https://openairdocs.org/stc/SR02138LA): Installation of Utility Step Mount. Airfilm Camera Systems
- [STC SR00666DE](https://openairdocs.org/stc/SR00666DE): Installation of Angled Scene Lights. Air Methods Corporation
- [STC SR02704SE](https://openairdocs.org/stc/SR02704SE): Installation and maintenance of the Sunspot 36 and 46 series lights. AeroLED's Holdings LLC
- [STC SR02114NY-D](https://openairdocs.org/stc/SR02114NY-D): Installation of a Honeywell Chadwick Model 15175 VXP System. Diagnostic Solution International LLC
- [STC SR01052DE](https://openairdocs.org/stc/SR01052DE): Installation of Non-Aviation Band FM Radio Systems. Cert Works LLC
- [STC SR00565DE](https://openairdocs.org/stc/SR00565DE): Installation of Cabin Air Conditioning System.. Air Comm Corporation
- [STC SR09583RC](https://openairdocs.org/stc/SR09583RC): Installation of the Sky Connect Forte Iridium Satellite Phone and/or automated position reporting system including the installation of an Iridium Satellite antenna, Transceiver, aircraft GPS interface to obtain position, SOP and/or MMU dialer panels, and optional GPS antenna. Honeywell International Inc
- [STC SR02124SE](https://openairdocs.org/stc/SR02124SE): Installation functionality. of Data Garmin Required: transponders: (1) Garmin GTX Master 345/345R Drawing with List ADS-B (MDL), Out and In 005-00734-A4, functionality;. Garmin International Inc
- [STC SR02677SE](https://openairdocs.org/stc/SR02677SE): Installation of Heavy Duty Wearplates. Dart Aerospace USA Inc.
- [STC SR09164RC](https://openairdocs.org/stc/SR09164RC): Installation of an Airborne Emergency Medical Systems.. Metro Aviation Inc
- [STC SR09354RC](https://openairdocs.org/stc/SR09354RC): Installation of Metro Aviation optional equipment.. Metro Aviation Inc
- [STC SR00359BO](https://openairdocs.org/stc/SR00359BO): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies
- [STC SR09193RC](https://openairdocs.org/stc/SR09193RC): Installation of a window in the aft clamshell doors. Metro Aviation Inc
- [STC SR00814DE](https://openairdocs.org/stc/SR00814DE): Installation of Garmin Helicopter Terrain Awareness and Warning System (HTAWS). Cert Works LLC
- [STC SA00339BO](https://openairdocs.org/stc/SA00339BO): Installation of Single pilot IFR KIT135M-GTN-150 with Garmin GTN 650-750 WAAS Navigators. Metro Aviation Inc
- [STC SR00821DE](https://openairdocs.org/stc/SR00821DE): Installation of Automatic Dependent Surveillance - Broadcast (ADS-B) Out and in functionality using the BendixKing KT74 Transponder and qualified position sensor and ADS-B In Receiver. Peregrine
- [STC SR00828DE](https://openairdocs.org/stc/SR00828DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the Garmin G330ES or G33H ES Transponder and qualified position sensor. Peregrine
- [STC SR04276NY](https://openairdocs.org/stc/SR04276NY): Installation of the Crosstubes. Dart Aerospace Limited
- [STC SR01042SE](https://openairdocs.org/stc/SR01042SE): Fabrication of Dart D135-692-011 Bearpaws. Dart Aerospace USA, Inc.
- [STC SR01709SE](https://openairdocs.org/stc/SR01709SE): Installation of Skidtube and Skidtube extension. Dart Aerospace USA Inc.
- [STC SR04235NY](https://openairdocs.org/stc/SR04235NY): Installation of Garmin GTS Traffic System. Maxcraft Avionics Ltd.
- [STC SR04228NY](https://openairdocs.org/stc/SR04228NY): Installation of Garmin HTAWS (Helicopter Terrain Awareness Warning System). Maxcraft Avionics Ltd.
- [STC SR00812DE](https://openairdocs.org/stc/SR00812DE): Installation of Honeywell Sky Connect Tracker III system. Cert Works LLC

All 125: https://openairdocs.org/tcds/H88EU/stcs.md

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.