# TCDS H13EU: Airbus Helicopters Deutschland GmbH (AHD)

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Helicopters Deutschland GmbH (AHD)
- Revision: 26
- Revised: March 5, 2026
- Product: Aircraft, Rotorcraft
- Certification basis: Part 29, Part 21
- Registered aircraft: 304, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/90/2b/902b831d13bd7892efb28511817c6fc0d28e1749edf9a94fbce8c127d72b00ea
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID162364927620260305154641.0001
- Page: https://openairdocs.org/tcds/H13EU

## Models (9)

As the data sheet lists them.

- MBB-BK 117 C-2
- MBB-BK 117 B-2
- MBB-BK 117 A-3
- MBB-BK 117 B-1
- MBB-BK 117 A-4
- MBB-BK 117 A-1
- MBB-BK 117 C-1
- MBB-BK 117 D-2
- MBB-BK 117 D-3

## 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. H13EU 
This data sheet, which is part of Type Certificate No. H13EU 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 Donauwörth 
Germany 
Type Certificate Holder Record: Eurocopter Deutschland GmbH changed name to Airbus Helicopters Deutschland GmbH 
on January 7, 2014. 
 
I. Model MBB-BK 117 A-1 (Transport Category A&B) Helicopter, Approved March 29, 1983. 
Engines. 2 Lycoming LTS 101-650 B-1 
 
Fuel. See Rotorcraft Flight Manual. 
Installed Engine Limits 
 
 
 
Normal Operation 
Output Shaft 
Torque % 
(Ft-Lbs.) 
Gas 
Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
% (RPM) 
Measured 
Gas 
Temperature 
°C (°F) 
    
Takeoff power (5 min.) 71 (368) 102.7 (49159) 102 (6120) 782 (1440) 
Max. continuous 71 (368) 102.7 (49159) 102 (6120) 763 (1405) 
One Engine Inoperative     
2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 832 (1528) 
30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 796 (1463) 
Max. continuous 83 (431) 102.7 (49159) 102 (6120) 763 (1404) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
 
Rotor Limits.  
Min. Continuous 
Power On, % (RPM) Power Off, %(RPM) 
gross weight up to 4409 lbs. 98 (376) 80 (307) 
gross weight 4409 - 6283 lbs. 98 (376) 85 (326) 
 
Max. Continuous 102 (391) 104 (399) 
Max. Transient 106 (406) 110 (422) 
Min. Transient 85 (326) --- 
 
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 
Rev. No. 26 6 13 13 13 6 13 13 19 26 26 26 26 17 24 20 25 18 25 25 
H13EU 
Revision 26 
AIRBUS HELICOPTERS 
DEUTSCHLAND GmbH 
MBB-BK 117 A-1 
MBB-BK 117 A-3 
MBB-BK 117 A-4 
 MBB-BK 117 B-1 
 MBB-BK 117 B-2 
 MBB-BK 117 C-1 
 MBB-BK 117 C-2 
 MBB-BK 117 D-2 
 MBB-BK 117 D-3 
               March 5, 2026

2 H13EU 
 
 
I. Model MBB-BK 117 A-1 (Transport Category A&B) Helicopter, Approved March 29, 1983. (cont'd) 
Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with 
outside air temperature and altitude. 
C.G. Range. Longitudinal C.G. Limits 
 
Max. forward range: up to 3747.8 lb: 172.2 in. aft of datum 
up to 4409.2 lb: 170.7 in. aft of datum 
up to 6283.1 lb: 173.8 in. aft of datum 
Max. rearward range: up to 3747.8 lb: 183.9 in. aft of datum 
up to 6283.1 lb: 179.7 in. aft of datum 
Straight line variation between points given. 
Lateral C.G. Limits. 
Max. deviation 3.9 in right or left of the fuselage median plane. 
Empty Weight C.G. Range. None 
 
Max. Weight. 6283 lbs. 
Min. Crew. 1 (right-hand seat only). 
 
Passengers. 7 (See NOTE 1A). 
Max. Baggage. Max. permissible floor loading: 123 lb/sq. ft. 
Max. loading: 2645 lb 
Aft of rear seat bank: 551 lb 
Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total; 158.0 US gal. (1054.9 lb.) usable: 
132.5 US gal. (884.5 lb., 179.88 in.) in main tank, and 25.5 US gal. (170.4 lb., 187.36 in.) 
in supply tank. 
(See NOTE 1B) 
Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight 
2 x 1.14 US gal. (176.77 in.). 
Main transmission oil has been included with the minimum gross weight 
3.3 US gal. (176.38 in.) 
 
Max. Operating Altitude. See Rotorcraft Flight Manual, Model MBB-BK 117 A-1. 
Rotor Blade and Control For rigging information refer to the MBB Model MBB-BK 117 Maintenance Manual. 
Movements

3 H13EU 
 
 
II. Model MBB-BK 117 A-3 (Transport Category A&B) Helicopter, Approved September 10, 1985. 
Engines. 2 Lycoming LTS 101-650B-1 
 
Fuel. See Rotorcraft Flight Manual. 
 
Installed Engine Limits 
 
 
 
Normal Operation 
Output Shaft 
Torque % 
(Ft-Lbs.) 
Gas 
Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
% (RPM) 
Measured 
Gas 
Temperature 
°C (°F) 
    
Takeoff power (5 min.) 71 (368) 102.7 (49159) 102 (6120) 782 (1440) 
Max. continuous 71 (368) 102.7 (49159) 102 (6120) 763 (1405) 
One Engine Inoperative     
2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 832 (1528) 
30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 796 (1463) 
Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 763 (1404) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
 
Rotor Limits.  
Min. Continuous 
Power On, % (RPM) Power Off, %(RPM) 
gross weight up to 4409 lbs. 98 (376) 80 (307) 
gross weight 4409 - 6283 lbs. 98 (376) 85 (326) 
 
Max. Continuous 102 (391) 104 (399) 
Max. Transient 106 (406) 110 (422) 
Min. Transient 85 (326) --- 
 
Airspeed Limits (IAS). Max. V NE = 150 Kt. 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 3748 lb: 172.2 in. aft of datum 
at 4409 lb: 170.7 in. aft of datum 
at 7055 lb: 175.1 in. aft of datum 
Max. rearward range: at 3748 lb: 183.9 in. aft of datum 
at 7055 lb: 178.5 in. aft of datum 
Straight-line variation between points given. 
        Lateral C.G. Limits.         Up to 6283 lb.: Max. deviation 3.94 in. right or left of the fuselage median plane. 
        Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. 
Empty Weight C.G. Range. None. 
 
Max. Weight. 7055 lb. 
Min. Crew. 1 (right-hand seat only). 
 
Passengers. 7 (See NOTE 1A). 
Max. Baggage. Max. permissible floor loading: 123 lb/sq. ft. 
Max. loading: 2645 lb. 
Aft of rear seat bank: 551 lb.

4 H13EU 
 
 
II. Model MBB-BK 117 A-3 (Transport Category A&B) Helicopter, Approved September 10, 1985. (cont'd) 
Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total; 158.0 US gal. (1054.9 lb.) usable: 
132.5 US gal. (884.5 lb., 179.88 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) 
in supply tank. (See NOTE 1B) 
Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight 
2 x 1.4 US gal. (176.77 in.). 
Main transmission oil has been included with the minimum gross weight 
3.3 US gal. (176.77 in.). 
 
Max. Operating Altitude. See Rotorcraft Flight Manual, MBB BK-117 A-3. 
Rotor Blade and Control For rigging information refer to the MBB Model BK 117 Maintenance Manual. 
Movement 
 
 
III. Model MBB-BK 117 A-4 (Transport Category A&B) Helicopter, Approved April 24, 1987. 
Engine. 2 Lycoming LTS 101-650B-1 
Fuel. See Rotorcraft Flight Manual. 
 
Installed Engine Limits 
 
 
 
Normal Operation 
Output Shaft 
Torque % 
(Ft-Lbs.) 
Gas 
Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
% (RPM) 
Measured 
Gas 
Temperature 
°C (°F) 
    
Takeoff power 83 (430) 102.7 (49159) 102 (6120) 782 (1440) 
Max. continuous 71 (368) 102.7 (49159) 102 (6120) 763 (1405) 
One Engine Inoperative     
2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 832 (1528) 
30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 796 (1463) 
Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 763 (1404) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
 
Rotor Limits.  
Min. Continuous 
Power On, % (RPM) Power Off, %(RPM) 
gross weight up to 4409 lbs. 98 (376) 80 (307) 
gross weight 4409 - 6283 lbs. 98 (376) 85 (326) 
 
Max. Continuous 102 (391) 104 (399) 
Max. Transient 106 (406) 110 (422) 
Min. Transient 85 (326) --- 
 
Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with 
outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits (Straight-line variation between points given.) 
Max. forward range: at 3748 lb: 172.2 in. aft of datum 
at 4409 lb: 170.7 in. aft of datum 
at 7055 lb: 175.1 in. aft of datum 
 
Max. rearward range: at 3748 lb: 183.9 in. aft of datum 
at 7055 lb: 178.5 in. aft of datum

5 H13EU 
 
 
III. Model MBB-BK 117 A-4 (Transport Category A&B) Helicopter, Approved April 24, 1987. (cont'd) 
        Lateral C.G. Limits.         Up to 6283 lb.: Max. deviation 3.84 in. right or left of the fuselage median plane. 
        Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. 
 
Empty Weight C.G. Range. None. 
 
Max. Weight. 7055 lb. 
Min. Crew. 1 (right-hand seat only). 
 
Passengers. 7 (See NOTE 1A). 
Max. Baggage. Max. permissible floor loading: 123 lb/sq. ft. 
Max. loading: 2645 lb. 
Aft of rear seat bank: 551 lb. 
 
Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total: 158.0 US gal (1054.8 lb.) usable: 
132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) 
in supply tank. 
(See NOTE 1B) 
Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 
2 x 1.14 US gal. (176.77 in.). 
Main transmission oil has been included with the minimum gross weight. 
3.3 US gal. (176.77 in.). 
 
Max. Operating Altitude. See Rotorcraft Flight Manual, MBB BK-117 A-4. 
 
Rotor Blade and Control For rigging information refer to the MBB Model BK 117 Maintenance Manual. 
Movement 
 
 
IV. Model MBB-BK 117 B-1 (Transport Category A & B) Helicopter, Approved December 11, 1987. 
Engines. 2 Lycoming LTS 101-750B-1 
 
Fuel. See Rotorcraft Flight Manual. 
 
Installed Engine Limits 
 
 
 
Normal Operation 
Output Shaft 
Torque % 
(Ft-Lbs.) 
Gas 
Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
% (RPM) 
Measured 
Gas 
Temperature 
°C (°F) 
    
Takeoff power (5 min.) 83 (430) 102.7 (49159) 102 (6120) 786 (1447) 
Max. continuous 71 (368) 102.7 (49159) 102 (6120) 765 (1408) 
One Engine Inoperative     
2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 836 (1536) 
30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 800 (1471) 
Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 765 (1408) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients.

6 H13EU 
 
 
IV. Model MBB-BK 117 B-1 (Transport Category A & B) Helicopter, Approved December 11, 1987. (cont'd) 
 
Rotor Limits. 
Min. Continuous 
Power On, % (RPM) Power Off, %(RPM) 
gross weight up to 4409 lbs. 98 (376) 80 (307) 
gross weight 4409 - 6283 lbs. 98 (376) 85 (326) 
 
Max. Continuous 102 (391) 104 (399) 
Max. Transient 106 (406) 110 (422) 
Min. Transient 85 (326) --- 
 
Airspeed Limits (IAS). Max. V NE = 150 Kt. 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 3748 lb: 172.2 in. aft of datum 
at 4409 lb: 170.7 in. aft of datum 
at 7055 lb: 175.1 in. aft of datum 
Max. rearward range: at 3748 lb: 183.9 in. aft of datum 
at 7055 lb: 178.5 in. aft of datum 
Straight line variation between points given. 
        Lateral C.G. Limits.         Up to 6283 lb.: Max. deviation 3.84 in. right or left of the fuselage median plane. 
        Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. 
Empty Weight C.G. Range. None. 
 
Max. Weight. 7055 lb. 
Min. Crew. 1 (right-hand seat only) 
 
Passengers. 7 (See NOTE 1A) 
Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. 
Max. loading: 2645 lb. 
Aft of rear seat bank: 551 lb. 
Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total: 158.0 US gal (1054.8 lb.) usable: 
132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) 
in supply tank. 
(See NOTE 1B) 
Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 
2 x 1.14 US gal. (176.77 in.). 
Main transmission oil has been included with the minimum gross weight. 
3.3 US gal. (176.77 in.) 
 
Max. Operating Altitude. See Rotorcraft Flight Manual, MBB BK-117 B-1. 
Rotor Blade and Control For rigging information refer to the MBB BK 117 Maintenance Manual. 
Movement

7 H13EU 
 
 
V. Model MBB-BK 117 B-2 (Transport Category A & B) Helicopter, Approved December 7, 1992. 
Engines. 2 Lycoming LTS 101-750B-1 
 
Fuel. See Rotorcraft Flight Manual. 
 
Installed Engine Limits 
 
 
 
Normal Operation 
Output Shaft 
Torque % 
(Ft-Lbs.) 
Gas 
Generator 
Speed N-1 
% (RPM) 
Output Shaft 
Speed N-2 
% (RPM) 
Measured 
Gas 
Temperature 
°C (°F) 
    
Takeoff power (5 min.) 83 (430) 102.7 (49159) 102 (6120) 786 (1447) 
Max. continuous 71 (368) 102.7 (49159) 102 (6120) 765 (1408) 
One Engine Inoperative     
2.5 minutes power 100 (519) 105.6 (50548) 102 (6120) 836 (1536) 
30 minutes power 91.5 (475) 104.8 (50469) 102 (6120) 800 (1471) 
Max. continuous (See Note 6.) 83 (431) 102.7 (49159) 102 (6120) 765 (1408) 
 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
 
Rotor Limits.  
Min. Continuous 
Power On, % (RPM) Power Off, %(RPM) 
gross weight up to 4409 lbs. 98 (376) 80 (307) 
gross weight 4409 - 7385 lbs. 98 (376) 85 (326) 
 
Max. Continuous 102 (391) 104 (399) 
Max. Transient (max 12 sec.) 106 (406) 110 (422) 
Min. Transient 85 (326) --- 
 
Airspeed Limits (IAS). Max. V NE = 150 Kt. 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 3748 lb: 172.2 in. aft of datum 
at 4409 lb: 170.7 in. aft of datum 
at 7385 lb: 173.2 in. aft of datum 
Max. rearward range: at 3748 lb: 183.9 in. aft of datum 
at 7385 lb: 178.0 in. aft of datum 
Straight line variation between points given. 
        Lateral C.G. Limits.         Up to 6283 lb.: Max. deviation 3.94 in. right or left of the fuselage median plane. 
                                                                     Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. 
Empty Weight C.G. Range. None. 
 
Max. Weight. 7385 lb. 
Min. Crew. 1 (right-hand seat only) 
 
Passengers. 7 (See NOTE 1A) 
Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. 
Max. loading: 2645 lb. 
Aft of rear seat bank: 551 lb.

8 H13EU 
 
 
 
V. Model MBB-BK 117 B-2 (Transport Category A & B) Helicopter, Approved December 7, 1992. (cont'd) 
 
Fuel Capacity. 160.5 US gal. (1071.6 lb., 179.6 in.) total: 158.0 US gal (1054.8 lb) usable: 
132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 25.5 US gal (170.4 lb., 187.36 in.) 
in supply tank. 
(See NOTE 1B) 
Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 
2 x 1.14 US gal. (176.77 in.). 
Main transmission oil has been included with the minimum gross weight. 
3.3 US gal. (176.77 in.) 
 
Max. Operating Altitude. See Rotorcraft Flight Manual, BK-117 B-2. 
 
Rotor Blade and Control For rigging information refer to the MBB BK 117 Maintenance Manual. 
Movements. 
 
 
VI. Model MBB-BK 117 C-1 (Transport Category A&B) Helicopter, Approved December 7, 1992. 
Engines 2 Turbomeca Arriel 1E2 
 
Fuel See Rotorcraft Flight Manual. 
 
Installed Engine Limits 
 
 
 
Normal Operation 
 
Torque Limits 
% 
Gas 
Generator 
Speed N-1 
% (RPM) °C 
Temperature 
TOT 
°C 
Power 
RPM 
% 
Takeoff power (5 min.) 83 100.6 (52111) 845 102*  
Max. continuous 71 100.0 (51800) 845 102*  
One Engine Inoperative     
2.5 minutes power 125 103.3 (53509) 885 102 
Max. continuous 91.5 100.3 (51955) 845 102 
 
*Max PA > 8000 ft and V < 55 KIAS 104%. 
 
Rotor Limits. Power On, % (RPM) Power Off, %(RPM) 
Min. continuous 98 80 (<2000 kg) 
 
Max. continuous 
 
102 
85 (>2000 kg) 
104 
PA > 8000 ft + V <55 KIAS 
 
For all serial numbers 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
Airspeed Limits (IAS). Max. V NE = 150 Kt. 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 3748 lb: 172.2 in. aft of datum 
at 4409 lb: 170.7 in. aft of datum 
at 7385 lb: 173.2 in. aft of datum 
Max. rearward range: at 3748 lb: 183.9 in. aft of datum 
at 7385 lb: 178.0 in. aft of datum

9 H13EU 
 
 
 
 
VI. Model MBB-BK 117 C-1 (Transport Category A&B) Helicopter, Approved December 7, 1992. (cont'd) 
 
Straight line variation between points given. 
        Lateral C.G. Limits.         Up to 6283 lb.: Max. deviation 3.94 in. right or left of the fuselage median plane. 
        Above 6283 lb.: Max. deviation 3.15 in. right or left of the fuselage median plane. 
Empty Weight C.G. Range. None. 
 
Max. Weight. 7385 lb. 
Min. Crew. 1 (right-hand seat only) 
 
Passengers. 7 (See NOTE 1A) 
Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. 
Max. loading: 2645 lb. 
Aft of rear seat bank: 551 lb. 
 
Fuel Capacity. 187 US gal. (1248 lb., 173.6 in.) total: 184.2 US gal (1230.2 lb.) usable: 
132.5 US gal. (884.5 lb., 179.6 in.) in main tank, and 26.2 US gal 175.3 
lb., 134.6 in.) in auxiliary fuel tank, and 25.5 US gal (170.4 lb., 
187.36 in.) in supply tank. 
 
Oil Capacity. Engine oil (each tank) has been included with the minimum gross weight. 
2 x 1.14 US gal. (176.77 in.) 
Main transmission oil has been included with the minimum gross weight. 
3.3 US gal. (176.77 in.). 
 
Max. Operating Altitude. See Rotorcraft Flight Manual, MBB-BK 117 C-1. 
 
Rotor Blade and Control For rigging information refer to the MBB BK 117 C Maintenance Manual. 
Movements. 
 
VII. Model MBB-BK 117 C-2 (Transport Category A&B) Helicopter, Approved January 17, 2002. 
For Serial Numbers 9004 through 19999 
 
Engines. 2 Turbomeca ARRIEL 1E2 engines 
 
Fuel. See Rotorcraft Flight Manual. 
Installed Engine Limits 
 
 
 
Normal Operation 
 
Torque Limits 
% 
Gas 
Generator 
Speed N-1 
% (RPM) 
Temperature 
TOT 
°C 
Power 
RPM 
% 
Takeoff power (5 min.) 88 101.9 (52835) 845 102*  
Max. continuous 71 100.0 (51995) 845 102*  
One Engine Inoperative     
2.5 minute power 125 103.3 (53509) 885 102 
Max. continuous 91.5 101.9 (52835) 845 102 
 
*Max PA > 8000 ft and V < 55 KIAS 104%.

10 H13EU 
 
 
VII. Model MBB-BK 117 C-2 (Transport Category A&B) Helicopter, Approved January 17, 2002. (cont'd) 
 
Rotor Limits. Power On, % (RPM) Power Off, %(RPM) 
Min. continuous 96 80 (<2000 kg) 
 
Max. continuous 
 
104 
85 (>2000 kg) 
104 
 
For all serial numbers 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
Airspeed Limits (IAS). Max. V NE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with 
outside air temperature and altitude. 
 
C.G. Range. Longitudinal C.G. Limits (Straight line variation between points given.) 
Max. forward range: at 7900 lb: 172.2 in. aft of datum 
at 4409 lb: 170.7 in. aft of datum 
 
Max. rearward range: at 3858 lb: 183.7 in. aft of datum 
at 7900 lb: 179.0 in. aft of datum 
Lateral C.G. Limits. Up to 6614 lbs (3000 kg): Max. deviation 3.94 in. (100 mm) right or left of the fuselage 
median plane. 
Above 6614 lbs (3000 kg): Max. deviation 3.15 in. (80 mm) right or left of the fuselage 
median plane. 
Empty Weight C.G. Range. None. 
 
Max. Weight. 3585 (kg) (7900 lbs) 
Min. Crew. 1 (right-hand seat only) 
 
Passengers. standard: 9, when equipped and operated in accordance with FMS 9.2-27: ten 
Max. Baggage. Max. permissible floor loading 123 lb/sq. ft. 
 
Fuel Capacity. with standard fuel tank total fuel: 879.1 l 
usable fuel: 867.5 l 
with self-sealing fuel tank total fuel: 861.6 l 
useable fuel: 850.0 l 
 
Oil Capacity. Refer to Rotorcraft Flight Manual 
Max. Operating Altitude. 18000 ft. 
 
Rotor Blade and Control For rigging information refer to the MBB BK 117 C-2 Maintenance Manual. 
Movements. 
Production Basis: Production Certificate No. 343CE. The manufacturer Airbus Helicopters Inc.,                 
located in Columbus, Mississippi, is licensed by Airbus Helicopters Deutschland GmbH                
to manufacture the MBB-BK117 C-2 and C-2(e).  S/N 9004 through 19999 may be                       
produced by Airbus Helicopters Inc. in Columbus, Mississippi, Airbus Helicopters in France,             
or Airbus Helicopters Deutschland GmbH in Germany.  The manufacturer can be confirmed             
by the aircraft data plate. 
Information Pertinent to the MBB-BK117 C-2(e) 
Effective from Serial Number 9601 if Garmin G500H cockpit is installed. 
 
Type design changes to the MBB-BK117 C-2 that install Garmin 500H avionics equipment and limit operations to VFR only 
have been approved. These type design changes result in a helicopter that AHD has named MBB-BK117 C-2e. EASA issued an 
amended type certificate (EASA.R.010 dated April 17, 2015) that identifies the MBB-BK117 C-2e. In accordance with FAR 
21.19, the FAA determined that the type design changes involved did not rise to the level that required an FAA amended type 
certificate. However, the FAA does wish to recognize that helicopters with these type design changes exist; therefore, the 
designation MBB-BK117 C-2(e) will be used. See Note 12 for more information on the type design changes for MBB-BK117 C-
2(e).

11 H13EU 
VIII. Model MBB-BK 117 D-2 (Transport Category A&B) Helicopter, Approved October 9, 2014.
Production Basis. Production Certificate No. 005 (JCAB approved Production Organization). The  
manufacturer Kawasaki Heavy Industries, Ltd., located in Gifu Prefecture, Japan, 
is licensed by Airbus Helicopters Deutschland GmbH to manufacture the      
MBB-BK117 D-2, S/N 20293 only. 
For Serial Numbers 20003 through 20999 
Engines. 2 Turbomeca ARRIEL 2E engines 
Fuel. See Rotorcraft Flight Manual. 
Installed Engine Limits* 
Normal Operation 
Torque Limits 
% 
Gas 
Generator 
Speed N-1 
% 
Temperature 
TOT 
°C 
Power 
RPM 
% 
Takeoff power (5 min.) 95 100.6 933 108.3 
Max. continuous 74 98.5 916 108.3 
Extended Power (30 min.) 95 100.6 933 108.3 
One Engine Inoperative 
30 seconds power 150 105.7 1021 108.3 
2 minutes power 130 104.3 1002 108.3 
Max. continuous 100 101.7 960 108.3 
* See Rotorcraft Flight Manual for AEO transient limits
Rotor Limits. Power On, % (RPM) Power Off, %(RPM) 
Min. continuous 94 80 (<2200 kg) 
Max. continuous 108.3 
85 (>2200 kg) 
109 
For all serial numbers 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
Airspeed Limits (IAS). Max. VNE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with 
outside air temperature and altitude. 
C.G. Range. Longitudinal C.G. Limits (Straight line variation between points given.) 
Max. forward range: at 5289 lbs (2400 kg): 171.3 in. (4347 mm) aft of datum 
at 8157 lbs (3700 kg): 172.5 in. (4379 mm) aft of datum 
at 8377 lbs (3800 kg): 172.6 in (4383 mm) aft of datum 
Max. rearward range: at 4407 lbs (2000 kg): 185.2 in. (4700 mm) aft of datum 
at 8157 lbs (3700 kg): 178.9 in. (4540 mm) aft of datum 
at 8377 lbs (3800 kg): 178.1 in (4525 mm) aft of datum 
Lateral C.G. Limits. Up to 6614 lbs (3000 kg): Max. deviation 3.94 in. (100 mm) right or left of the fuselage 
median plane. 
Above 6614 lbs (3000 kg): Max. deviation 3.15 in. (80 mm) right or left of the fuselage 
median plane. 
Empty Weight C.G. Range. None. 
Max. Weight. 8157 lbs (3700kg) 
Alternate max weight: 8377 lbs (3800 kg) only in accordance with FMA 11-19 
Min. Crew. 1 (right-hand seat only) 
Passengers. 9 (standard configuration) 
Max. Baggage. Max. permissible floor loading 123 lb/sq. ft.

12 H13EU 
VIII. Model MBB-BK 117 D-2 (Transport Category A&B) Helicopter, Approved October 9, 2014. (cont'd)
Fuel Capacity. with standard fuel tank total fuel : 915.8 liter 
usable fuel : 903.8 liter 
Oil Capacity. Refer to Rotorcraft Flight Manual 
Max. Operating Altitude. 20000 ft. 
16000 ft (PA/DA whichever is less) for hover in ground effect, takeoff and landing 
Rotor Blade and Control For rigging information refer to the MBB BK 117 D-2 Maintenance Manual. 
Movements. 
IX. Model MBB-BK 117 D-3 (Transport Category A&B) Helicopter, Approved November 25, 2020.
For Serial Numbers 21001 and subsequent 
Production Basis: Production Certificate No. 005 (JCAB approved Production Organization). The    
manufacturer Kawasaki Heavy Industries, Ltd., located in Gifu Prefecture, Japan, is      
licensed by Airbus Helicopters Deutschland GmbH to manufacture the MBB-BK117 D-3. 
Production Certificate No. 343CE. The manufacturer Airbus Helicopters Inc.,      
located in Columbus, Mississippi, is licensed by Airbus Helicopters Deutschland GmbH 
to manufacture the MBB-BK117 D-3. 
S/N 21001 and subsequent may be produced by Kawasaki Heavy Industries, Ltd. in Japan, 
Airbus Helicopters Inc. in Columbus, Mississippi, Airbus Helicopters in France, or Airbus  
Helicopters Deutschland GmbH in Germany.  The manufacturer can be confirmed by the      
aircraft data plate. 
Engines. 2 Safran Helicopter Engines (former Turbomeca) ARRIEL 2E engines 
Fuel. See Rotorcraft Flight Manual. 
Installed Engine Limits* 
Normal Operation 
Torque Limits 
% 
Gas 
Generator 
Speed N-1 
% 
Temperature 
TOT 
°C 
Power 
RPM 
% 
Max. continuous 74 98.5 916 108.3 
Extended Power (30 min.) 95 100.6 933 108.3 
One Engine Inoperative 
30 seconds power 150 105.7 1021 108.3 
2 minutes power 143 104.3 1002 108.3 
Max. continuous 100 101.7 960 108.3 
* See Rotorcraft Flight Manual for AEO transient limits
Rotor Limits. Power On, % (RPM) Power Off, %(RPM) 
Min. continuous 94 80 (<2250 kg) 
Max. continuous 107.5 
85 (>2250 kg) 
109 
For all serial numbers 
See Rotorcraft Flight Manual for other limitations including speed and temperature transients. 
Airspeed Limits (IAS). Max. VNE = 150 Kt. See Rotorcraft Flight Manual for airspeed limit decrease with 
outside air temperature and altitude. 
C.G. Range. Longitudinal C.G. Limits (Straight-line variation between points given.) 
Max. forward range: at 5289 lbs (2400 kg): 171.3 in. (4347 mm) aft of datum 
at 8377 lbs (3800 kg): 172.6 in. (4383 mm) aft of datum 
Max. rearward range: at 4407 lbs (2000 kg): 185.2 in. (4700 mm) aft of datum 
at 8377 lbs (3800 kg): 179.1 in. (4550 mm) aft of datum

13 H13EU 
Lateral C.G. Limits. Up to 6614 lbs (3000 kg): Max. deviation 3.94 in. (100 mm) right or left of the fuselage 
median plane. 
Above 6614 lbs (3000 kg): Max. deviation 3.15 in. (80 mm) right or left of the fuselage 
median plane. 
Empty Weight C.G. Range. None. 
IX. Model MBB-BK 117 D-3 (Transport Category A&B) Helicopter, Approved November 25, 2020. (cont'd)
Max. Weight. 8377 lbs (3800kg) 
Min. Crew. 1 (right-hand seat only) 
Passengers. 9 (refer to the RFM for approved seat configurations) 
Max. Baggage. Max. permissible floor loading 123 lb/ft² (Loading 600 kg/m²). 
Fuel Capacity. With standard fuel tank total fuel : 915.8 liter 
usable fuel : 903.8 liter 
Oil Capacity. Refer to Rotorcraft Flight Manual 
Max. Operating Altitude. 20000 ft. 
20000 ft (PA/DA whichever is less) for hover in ground effect, takeoff, and landing 
Rotor Blade and Control For rigging information refer to the MBB BK 117 D-3 Maintenance Manual. 
Movements. 
DATA PERTINENT TO ALL MODELS. 
Datum. Refer to the appropriate BK117 RFM or MM. 
Leveling Means. Alignment Points are given in the Maintenance Manual. 
Serial 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. 
Production Basis: The manufacturer Airbus Helicopters located in Marignane, France, is licensed by Airbus 
Helicopters Deutschland GmbH to manufacture the Model Aircraft listed in this Type      
Certificate Data Sheet. The aircraft may be produced by either Airbus Helicopters in France 
or Airbus Helicopters Deutschland GmbH in Germany. The manufacturer can be confirmed  
by the aircraft data plate.  
Certification Basis. FAR 21.29 and FAR 29 effective Feb. 1, 1965, plus Amendments 29-1 through 29-16. 
Equivalent Safety Findings and Special Conditions in NOTE 4. 
The Airworthiness criteria for Helicopter Instrument Flight, dated December 15, 1978, for 
IFR certification. 
For the Model MBB-BK 117 A-1: 
Type Certificate No. H13EU issued March 29, 1983. 
Date of application for Type Certificate: February 19, 1979. 
For the Model MBB-BK 117 A-3: 
Type Certificate No. H13EU amended September 10, 1985. 
Date of application for amended Type Certificate: April 2, 1985. 
For the Model MBB-BK 117 A-4: 
Type Certificate No. H13EU amended April 24, 1987. 
Date of application for amended Type Certificate: August 14, 1986. 
For the Model MBB-BK 117 B-1: 
Type Certificate No. H13EU amended December 11, 1987. 
Date of application for amended Type Certificate: June 22, 1987.

14 H13EU 
For the Model MBB-BK 117 B-2: 
Type Certificate No. H13EU amended December 7, 1992. 
Date of application for amended Type Certificate: January 23, 1991. 
For the Model MBB-BK 117 C-1: 
Type Certificate No. H13EU amended December 7, 1992. 
Date of application for amended Type Certificate: March 8, 1991. 
For S/N up to and including 7509 with modification per SB-MBB-BK117-60,112 and 
S/N greater than or equal to 7510. 
FAR Part 29 dated. Feb. 1, 1965, 
including Amendments 29-1 to 29-16 
FAR 29.927, 29.1091, 29.1103, 29.1195 Amend. 17 
FAR 29.1, 29.1517, 29.1587 Amend. 21 
FAR 29.143 Amend. 24 
FAR 29.901, 29.903, 29.908, 29.955, 29.961, 29.1041, 29.1043, 29.1045, 29.1047, 
29.1093 Amend. 26 
FAR 29.2 Amend. 32 
JAR 29 (First Issue): 29.45 to 29.87 
For the Model MBB-BK 117 C-2: 
Type Certificate No. H13EU amended January 17, 2002. 
Date of application for amended Type Certificate: October 18, 2000. 
FAR 21.29 and FAR 29 effective Feb. 1, 1965, plus Amendments 29-1 through 29-40 
with the following exceptions. 
FAR 29.631 at Amendment 29-40 for roof cover, overhead panel, and center beam only 
FAR 29.903 at Amendment 29-26 
FAR 29.923 at Amendment 29-26 
FAR 29.927 at Amendment 29-17 
FAR 29.547 at Amendment 29-16 
FAR 29.571 at Amendment 29-16 
FAR 29.863 at Amendment 29-16 
FAR 29.901(c) at Amendment 29-16 
FAR 29.917 at Amendment 29-16 
FAR 29.1011 at Amendment 29-16 
FAR 29.1019(a) at Amendment 29-16 
FAR 29.1021 at Amendment 29-16 
FAR 29.1163 at Amendment 29-16 
FAR 29.1181 at Amendment 29-16 
FAR 29.1183 at Amendment 29-16 
FAR 29.1189 at Amendment 29-16 
FAR 29.1309(b),(d),(e) at Amendment 29-16 
FAR 29.1521 at Amendment 29-16 
and the following FAR’s that revert to the original Amendment 29-16 certification basis 
and were not codified at that time 
FAR 29.610(d)(4) 
FAR 29.1027 
FAR 29.1305(a)(21) and (23) 
FAR 29.1337(e) 
FAR Part 36 Appendix H at Amendment 36-22 
For the Model MBB-BK 117 D-2: 
Type Certificate No. H13EU amended: October 9, 2014. 
Date of application for amended Type Certificate: December 21, 2009. 
14 CFR 21.29 and 14 CFR 29 effective Feb. 1, 1965, plus Amendments 29-1 through 29-
40 for the new or changed parts with respect to the MBB-BK117 C-2, identified in the 
document ETYC 1183/09-MHa, supplemented with requirements from other amendments 
listed below: 
14 CFR 29 requirements with amendment through 29-51 for: 
29.25, 29.59, 29.62, 29.67, 29.77, 29.81, 29.85, 29.143, 29.173, 29.175, 29.177, 29.351, 
29.397, 29.562, 29.602, 29.865, 29.923, 29.1317, 29.1323, 29.1329, 29.1351, 29.1359, 
29.1457, 29.1459, 29.1521, 29.1587, B29.5, B29.7

15 H13EU 
 
14 CFR 29.631 at Amendment 29-40 for the entire tail section only  
 
14 CFR 36 Appendix H at Amendment 36-25 
The main differences between the MBB-BK117 C-2 and the MBB-BK117 D-2 are as 
follows: 
a) Installation of Turbomeca Arriel 2E engines with FADEC control. 
b) New tail section including composite structure and fanned tail rotor 
(FENESTRON) with composite blades. 
c) New cockpit indication system using integrated modular avionics. 
d) Auto Flight System as a standard configuration of the MBB-BK117 D-2. 
e) Main gearbox modifications to support 30-minute run-dry capability. 
f) Maximum take-off weight increased to 3650 kg. 
The German Authority Luftfahrt-Bundesamt (LBA) originally type certificated this under 
its type certificate number (LBA 3049). The FAA validated this product under U.S. Type 
Certificate Number (H13EU). Effective September 28, 2003, the European Aviation 
Safety Agency (EASA) began oversight of this product on behalf of the German LBA 
(EASA TC R.010). 
 
For the Model MBB-BK 117 D-3: 
Type Certificate No. H13EU amended: November 25, 2020. 
Date of application for amended Type Certificate: March 23, 2018. 
 
For significantly affected areas with respect to MBB-BK 117 D-2 as identified in 
CRD D0000M505304, Revision C, dated June 19, 2020, 14 CFR § 29 effective February 
1, 1965, plus Amendments 29-1 through 29-55 for the following requirements: 
29.571, 29.573 
For the remaining areas, systems, parts, or appliances, 14 CFR § 29 effective 
February 1, 1965, plus Amendments 29-1 through 29-55 for the following requirements: 
29.610, 29.631, 29.1501, A29.4 
 
For the remaining areas, systems, parts, or appliances, 14 CFR § 29 effective 
February 1, 1965h, plus Amendments 29-1 through 29-51 for the following requirements: 
29.1, 29.25, 29.59, 29.62, 29.67, 29.77, 29.81, 29.85, 29.143, 29.173, 29.175, 29.177, 
29.351, 29.397, 29.602, 29.923, 29.1323, 29.1329, 29.1351, 29.1359, 29.1457, 29.1459, 
29.1521, 29.1587, B29.5, B29.7 
14 CFR § 29 effective February 1, 1965, plus Amendments 29-1 through 29-40 for all the 
other applicable requirements with the following exceptions: 
29.631 at Amendment 29-16 (for cockpit windscreens only), 
29.863 at Amendment 29-16 (for unaffected parts from BK 117 C-1), 
29.865 at Amendment 29-43 for External Loads applicable to Common 
Cargo Hook Beam and Hoist installation. 
29.1011 (b),(e) at Amendment 29-16, 
29.1019 at Amendment 29-16, 
29.1021 (for Main Gearbox only) at Amendment 29-16 
See Note 4 for updated ELOS finding for Alternative Category “A” Continued Take-Off 
and Balked Landing Procedures on the Model D-3 helicopter 
The main differences between the MBB-BK 117 D-2 and the MBB-BK 117 D-3 are as 
follows: 
a) New five bladed main rotor with bearingless design 
b) Elongated rotor mast with integrated flanges for blade attachment 
c) Redesigned upper controls with five arm swashplate and adapted kinematics 
d) Enlarged hub cap 
e) Adaption of rigging procedure and tooling for main rotor controls 
f) Removal of mechanic stick centering device 
g) Integration of an electric hydraulic pump into one hydraulic system to allow 
full range pre-flight check of flight controls 
h) Adaption of IMA SW HELIONIX to V8.0 according to Technical Note Major 
change TN X460C1555E01 for the common part shared with EC175 and TN 
D460M0520E03 for the MBB BK 117 specific part. 
i) Adaption of Automatic Flight Control System software to new rotor dynamics

16 H13EU 
 
j) Removal of anti-vibration systems (improved) Light Active Vibration Control 
System (LAVCS(+)) and 3Hz Landing Gear dampers 
k) Adaption of stiffness of forward cross tube and LG skids 
l) Adaption of stiffness of horizontal stabilizer 
m) Adaption of stiffness of tail rotor Smart Electro-Mechanical Actuator rod 
n) Relocation of roof mounted Emergency Locator Transmitter antenna and 
addition of alternative ARTEX ELT-4000. 
o) Shortening of the deflector from optional upper (roof mounted) cable cutter 
p) Removal of structural reinforcements for LAVCS and LG dampers 
q) Adaption of stiffness of pilot and co-pilot collective control sticks 
r) Replacement of DTD by wireless Airborne Communication Server 
s) Redesign of optional main rotor blade folding kit (provisions only) 
t) Maximum weight limit will be extended to 3,800 Kg (no longer considered an 
alternative MTOW). 
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 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 3049 
(or EASA TC Number R.010) approved under the U.S. Type Certificate Number H13EU 
and to be in a condition for safe operation.” 
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 
21.29 and exported by the country of manufacture is FAR Sections 21.183(c) or 
21.185(c). 
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 
21.29 exported from countries other than the country of manufacture (e.g., third party 
country) is FAR Sections 21.183(d) or 21.183(b). 
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. 
 
Model MBB-BK 117 A-1 is ineligible for a U.S. certificate of airworthiness. See Note 9. 
 
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 the Model MBB-BK 117 A-1, LBA-approved MBB-BK 117 A-1 Rotorcraft Flight 
Manual dated December 9, 1982, Revision 0, or later approved revision, is required. 
 
For the Model MBB-BK 117 A-3, LBA-approved MBB-BK 117 A-3 Rotorcraft Flight 
Manual dated March 15, 1985, or later as required. 
For the Model MBB-BK 117 A-4, LBA-approved MBB-BK 117 A-4 Rotorcraft Flight 
Manual Revision 1 dated April 8, 1987, or later as required. 
For the Model MBB-BK 117 B-1, LBA-approved MBB-BK 117 B-1 Rotorcraft Flight 
Manual Revision 0, dated December 10, 1987, or later as required. 
 
For the Model MBB-BK 117 B-2, LBA-approved MBB-BK 117 B-2 Rotorcraft Flight 
Manual Revision 2 dated November 20, 1992, or later as required. 
For the Model MBB-BK 117 C-1, LBA-approved MBB-BK 117 C-1 Rotorcraft Flight 
Manual Revision 0 dated October 2, 1992, or later as required. 
For the Model MBB-BK 117 C-2, LBA-approved MBB-BK 117 C-2 Rotorcraft Flight 
Manual Revision 0 dated December 20, 2000, or later as required. 
 
For the MBB-BK 117 C-2(e), EASA-approved MBB-BK 117 C-2e Rotorcraft 
Flight Manual Revision 1 dated June 17, 2015, or later as required. See Note 12.

17 H13EU 
 
For the Model MBB-BK 117 D-2, EASA-approved MBB-BK 117 D-2 Rotorcraft Flight 
Manual Revision 0 dated April 16, 2014, or later as required. 
For the Model MBB-BK 117 D-3, EASA-approved MBB-BK 117 D-3 Rotorcraft Flight 
Manual Revision 4.1 dated March 29, 2021, or later as required. 
For the Model MBB-BK 117 D-3 Helionix V10, FAA dedicated-approved MBB-BK 117 
D-3 HLX V10 Rotorcraft Flight Manual Revision 0 or later is required. 
 
 
Service Information. Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and 
overhaul maintenance manuals, which contain a statement that the document is LBA 
approved, are accepted by the FAA, and are considered FAA approved. These approvals 
pertain to the type design only. 
“Each of the documents listed below must state that it is approved by the EASA or – for 
approvals made before September 28, 2003 – by the German LBA. 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.” 
 
NOTES: 
 
NOTE 1. Current weight and balance report including list of required equipment and list of equipment 
included in certified empty weight and loading instructions when necessary, must be provided for 
each helicopter at the time of original certification: the certificated empty weight and 
corresponding center of gravity location must include unusable fuel of (16.7 lb. at 176.77 in.) and 
engine oil (2 x 9.64 lb. at 176.77 in.) and transmission oil of (27.8 lb. at 176.38 in.). 
 
NOTE 1A. Ten (10) passengers are permitted with MBB Kit Number 117-86099 or, -86100 installed. 
NOTE 1B. With 80 Kg auxiliary fuel tank installed (P/N 117-891011) 187 US gal. (1248 lbs, 173.6 in.) total; 
184.2 US gal. (1230.2 lbs, 173.5 in) usable. 
 
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 
LBA-approved Rotorcraft Flight Manual. The "Airworthiness Limitations" section of the 
Rotorcraft Maintenance Manual must be complied with". 
 
In addition, all placards required in the LBA-approved Rotorcraft Flight Manual must be installed 
in the appropriate locations. 
 
NOTE 3. For Model MBB-BK 117 A-1: Refer to the MBB-BK 117 Maintenance Manual Appendix A; 
Chapter 9, "AIRWORTHINESS LIMITATIONS", Preliminary Revision 4, dated 20 February 
1983, or a later LBA-approved issue, for the retirement life limitations of the helicopter parts which 
are critical from a fatigue standpoint. These values of retirement on service life cannot be 
increased without FAA Engineering approval. 
For Model MBB-BK 117 A-3 and Model MBB-BK 117 A-4: Refer to the MBB-BK 117 
Maintenance Manual Appendix A; Chapter 9, "AIRWORTHINESS LIMITATIONS", Temporary 
Revision 6, dated 5 March 1983, or a later LBA-approved issue, for the retirement life limitations 
of the helicopter parts which are critical from a fatigue standpoint. These values of retirement on 
service life cannot be increased without FAA Engineering approval. 
 
For Model MBB-BK 117 A-4: Refer to the MBB-BK 117 Maintenance Manual Appendix A;

18 H13EU 
 
Chapter 9, "AIRWORTHINESS LIMITATIONS", Revision 4, dated July 1, 1986, or later LBA-
approved issue, for the retirement life limitations of the helicopter parts which are critical from a 
fatigue standpoint. These values of retirement on service life cannot be increased without FAA 
Engineering approval. 
 
For Model MBB-BK 117 B-1; Refer to the MBB-BK 117 Maintenance Manual Appendix A; 
Chapter 9, "AIRWORTHINESS LIMITATIONS", Revision 8, dated December 15, 1987, or later 
LBA-approved issue, for the retirement life limitations of the helicopter parts which are critical 
from a fatigue standpoint. These values of retirement on service life cannot be increased without 
FAA Engineering approval. 
For Model MBB-BK 117 B-2; Refer to the MBB-BK 117 Maintenance Manual Appendix A; 
Chapter 9, "AIRWORTHINESS LIMITATIONS", Revision 18, dated January 17, 1992, or later 
LBA-approved issue, for the retirement life limitations of the helicopter parts which are critical 
from a fatigue standpoint. These values of retirement on service life cannot be increased without 
FAA Engineering approval. 
 
For Model MBB-BK 117 C-1; Refer to the MBB-BK 117 C Maintenance Manual Appendix A; 
Chapter 9, "AIRWORTHINESS LIMITATIONS", Revision 0, dated October 2, 1992, or later 
LBA-approved issue, for the retirement life limitations of the helicopter parts which are critical 
from a fatigue standpoint. These values of retirement on service life cannot be increased without 
FAA Engineering approval. 
 
For Model MBB-BK 117 C-2; Refer to the MBB-BK 117 C-2 Maintenance Manual; 
Chapter 4, "AIRWORTHINESS LIMITATIONS", Revision 0, or later LBA/EASA-approved issue, 
for the retirement life limitations of the helicopter parts which are critical from a fatigue standpoint. 
These values of retirement on service life cannot be increased without FAA Engineering approval. 
For Model MBB-BK 117 D-2: Refer to the MBB-BK 117 D-2 Maintenance Manual; 
Chapter 4, "AIRWORTHINESS LIMITATIONS", Revision 0, or later EASA-approved issue, for the 
retirement life limitations of the helicopter parts which are critical from a fatigue standpoint. These 
values of retirement on service life cannot be increased without FAA Engineering approval. 
For Model MBB-BK 117 D-3; Refer to the MBB-BK 117 D-3 Maintenance Manual; 
Chapter 4, "AIRWORTHINESS LIMITATIONS", Revision 0, dated September 25, 2020, or later 
EASA-approved issue, for the retirement life limitations of the helicopter parts which are critical 
from a fatigue standpoint. These values of retirement on service life cannot be increased without 
FAA Engineering approval. 
 
Additional information essential for proper maintenance of the helicopter is contained in the MBB-
BK 117 Maintenance and Repair Manual. 
 
NOTE 4. Equivalent Safety Findings 
For Models MBB-BK 117 A-1 up to B-1; 
FAR 29.175(b) Demonstration of Static Longitudinal Stability (See NOTE 8) 
 
For Models MBB-BK 117 A-1 up to C-1: 
FAR 29.811(h)(1) Exterior Markings 
FAR 29.1151(b) Rotor Brake Controls 
For Model MBB-BK 117 C-2: 
FAR 29.807 (a)(4) Emergency exits 
FAR 29.1151(b) Rotor Brake Controls 
FAR 29.1303 (a),(j) VNE indication 
FAR 29.1549 (b) Powerplant Instruments 
FAR 29.1457(d)(5) Amdt 52, FAR 135.151(g)(1)(i), ELOS No: SP4261RD-R 
FAR 29.1457(c) Cockpit voice recorders, with Airbus modification E-2711 
For Model MBB-BK 117 D-2: 
14 CFR 29.807 (a)(4) Emergency exits 
14 CFR 29.1545(b)(4), 29.1549(b) Airspeed & Powerplant indication green marking 
14 CFR 29.1305, 29.1351(b)(6), 29.1435(a)(3) Part Time Display of Vehicle Parameters 
14 CFR 29.1397 and 29.1401 Dual Color Anti Collision light 
For Model MBB-BK 117 D-3 
14 CFR 29.807 (a)(4) Emergency exits 
14 CFR 29.1305, 29.1351(b)(6), 29.1435(a)(3) Part Time Display of Vehicle Parameters 
14 CFR 29.1397 and 29.1401 Dual Color Anti Collision light

19 H13EU 
 
14 CFR § 29.59(d) Takeoff Path: Category A and 29.1587(a)(6)(ii) Performance information. The ELOS 
finding is documented in ELOS Memorandum AT11546IB-R-F-01. 
 
Special Conditions 
For Models MBB-BK 117 D-2 and MBB-BK 117 D-3: 
14 CFR 29.1049, 29.1305, 29.1521 for 30 min Extended Power Rating 
NOTE 5. The engine limits shown are installed limits. For computation purposes 100 percent engine output 
shaft torque is 519 ft.-lb. and, 100 per cent engine output shaft (N2) speed is 6000 rpm. Also 100% 
Gas Generator speed is 47,870 rpm. 
 
NOTE 6. This emergency rating can be used for demonstration/training purposes. 
 
NOTE 7. All modifications or alterations of the powerplant installation type design approved under H13EU 
must be reviewed by the type certificating office before approval of changes in type design are 
granted. This includes the engine air intake system, the transmission compartment, engine model, 
and fuel changes. 
NOTE 8. Airspeed limitations must comply with MBB Service Bulletin BK-117-40-4 (Reference U.S. AD 
85-02-04) and minimum ambient air temperature must be limited to -35oC unless MBB Service 
Bulletin BK-117-40-7 has been accomplished or the MBB stick Position Augmentation System 
(SPAS) kit has been installed as basic equipment). 
 
NOTE 9. Model MBB-BK 117 A-1 S/N 7001 to S/N 7054 may be converted to Model BK 117 A-3 in 
accordance with MBB Service Bulletin SB-MBB-BK 117-10-4 dated April 15, 1985, or later 
revision. In addition, these serial number helicopters may be further converted to model BK117 
A-4 in accordance with MBB Service Bulletin SB-MBB-BK117-80-105 dated November 26, 1987, 
or later revision. Model MBB-BK 117 A-1 helicopters are ineligible for U.S. certificate of 
airworthiness due to Airbus Helicopter Deutschland discontinued maintenance of the approved 
flight manuals for this model; reference Airbus Helicopter Deutschland Technical Information 
Letter, No. BK117 006-2005. 
Model MBB-BK 117 A-3 S/N 7055 to S/N 7121 may be converted to Model BK 117 A-4 in 
accordance with MBB Service Bulletin SB-MBB-BK 117-80-105 dated November 26, 1987, or 
later revision. 
Model MBB-BK 117-B1 S/N 7140 to S/N 7243 may be converted to Model BK 117 B-2 in 
accordance with ECD Drawing No. 117-800121 (refer to BK 117 Service Information SI-MBB-
BK117-36). 
Model MBB-BK-117 A-4, any eligible serial number, may be converted to Model MBB-BK-117 
B-1 in accordance with MBB Service Bulletin SB-MBB-BK 117-80-126, revision 1, dated May 16, 
1995. 
 
Model MBB-BK117 D-2, any eligible serial number, may be converted to Model MBB-BK117 D-
3 in accordance with Airbus Service Bulletin MBB-BK117 D-2-00-003/xx, where the “xx” refers 
to the customer specific configuration. Once modified according to the design change approved 
under EASA Major Change Approval 10076247, any MBB-BK117 D-2 helicopter shall be re-
identified as MBB-BK117 D-3 and all the related data from this data sheet will apply. 
The validation approval of EASA Major Change Approval 10077593 (“Population 2” Hoist System) for 
the MBB-BK117 D-3 is also valid for the model MBB BK117 D-2 helicopter converted into a model 
MBB BK117 D-3. 
 
Model MBB-BK 117 B-2 S/N 7203 is ineligible for U.S. registration. 
 
NOTE 10. Any changes to the type design of this helicopter by means of a amended type certificate (TC), 
supplemental type certificate (STC), or amended STC, requiring instructions for continued 
airworthiness (ICA's) must be submitted thru the project aircraft certification office (ACO) for 
review and acceptance by the Fort Worth -Aircraft Evaluation Group (FTW-AEG) Flight Standards 
District Office (FSDO) prior to the aircraft delivery, or upon issuance of the first standard 
airworthiness certificate for the affected aircraft, whichever occurs later as prescribed by Title 14 
CFR 21.50. Type design changes (major repairs or alterations) by means of a FAA Form 337 (field 
approval) that require ICA's must have those ICA's reviewed by the field approving FSDO. 
NOTE 11. Effective January 1, 2018, Airbus Helicopters Deutschland GmbH (Production Organization 
Approval holder) was changed to Airbus Helicopters.

20 H13EU 
 
NOTE 12. Type design changes to the MBB-BK117 C-2 were approved June 30, 2015. These type design 
changes resulted in the MBB-BK117 C-2(e), starting from Serial Number 9601. The MBB-BK117 
C-2(e) is a VFR only configuration of the MBB-BK117 C-2 utilizing a Garmin 500H flight display 
system. See Rotorcraft Flight Manual under the Equipment section of this TCDS. 
NOTE 13. This MBB-BK117 D-3 Common Cargo Hook Beam installation (EASA Major Change Approval 
10081993) deals only with the detachable parts of the common cargo hook beam system (cargo 
hook beam, onboard systems cargo hook, detachable electrical part, landing gear provisions). The 
common cargo hook beam system will be used for HEC and NHEC operations. The fixed 
provisions have been approved under AH DOA privileges and are a pre-requisite for CCHB 
installation. 
A service bulletin (SB BK117-25-98-0002) will be released for the model MBB-BK117 D-3 helicopters 
already delivered with the common cargo hook beam fixed provisions. The same fuel tank protection 
mitigations also need to be implemented on the MBB-BK117 D-2 delivered with common cargo hook 
beam or fixed provisions only. The in-service fleet of the MBB-BK117 D-2 with common cargo hook 
beam installed is addressed by the airworthiness follow-up sheet, reference ETJA-2021-174 
 
Limitations applicable to the MBB-BK117 D-3 Common Cargo Hook Beam installation: 
The following modifications are a pre-requisite for the embodiment of this design change: 
-K-8113: change of fuel system and airframe parts in the framework of CCHB validation 
-K-8272: fuel pump modification due to fuel tank drop tests results 
-K-6355: mechanical fixed provisions and electrical integration 
-K-6829: placards for the CCHB system 
-K-6583: bore holes and bushings in the FWD and AFT cross tubes 
 
Airworthiness Limitations: approved by validation of EASA Major Change Approval E-6722 (TFSAC 
23.117.0001.A), dated May 25, 2023. 
NOTE 14: For the validation approval of EASA Major Change Approval 10077593 applicable to the model 
MBB-BK117 D-3, Installation of the COLLINS AEROSPACE “Population 2” Hoist System (P/N 
44301-12-XXX), the following Technical Documents are applicable: 
- BK117 D-3 FMS 9.2-4 Rev. 3, External Hoist System 
- MBB-BK117 D-3 (Helionix V10 excluded) FMA 11-69 Rev 0 or later approved, Appendix 
for FAA-registered helicopters, which lists specific Limitations, Procedures, and Performance 
Data applicable only to FAA-registered helicopters, as well as a list of the EASA Basic 
Rotorcraft Flight Manual (RFM), Flight Manual Supplements (FMS) and Flight Manual 
Appendices (FMA) approved by the FAA as part of the Type Certificate 
Airworthiness Limitations: 
- approved by validation of EASA Major Change Approval E-6506 (TFSAC 21.BK117.0001.A and 
21.BK117.0007.A), dated November 3, 2021. 
NOTE 15: Ditching note for MBB-BK117 C-2, MBB-BK117 D-2, MBB-BK117 D-3: 
 
The emergency flotation system is approved as a ditching provision according to FAR 29.801 Amdt.40 
(Ref. Rotorcraft Flight Manual Supplement 9.2-9). 
In order for the helicopter to be fully approved for ditching the following additional equipment must be 
installed in accordance with FAR 29.801, 29.1411 and 29.1415: 
-approved survival type emergency locator transmitter, 
-approved life rafts along with survival equipment, 
-approved life preserver for each occupant. 
it is the operator’s responsibility to ensure that the equipment not covered under ditching certification 
meets all the applicable airworthiness and operational requirements. 
 
 
.....END.....
```

## ADs (119, first 50, in force first)

- [AD 2026-21-02](https://openairdocs.org/ad/2026-21-02): Air conditioning system · Airbus Helicopters Deutschland MBB-BK 117 C-1. Effective Oct 26, 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 2026-10-20](https://openairdocs.org/ad/2026-10-20): Main Rotor Mast/Swashplate · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Jul 9, 2026
- [AD 2026-09-08](https://openairdocs.org/ad/2026-09-08): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland MBB-BK 117 C-2 and MBB-BK 117 D-2. Effective Jun 17, 2026
- [AD 2026-08-51](https://openairdocs.org/ad/2026-08-51): Main rotor drive system · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective May 14, 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 2026-06-04](https://openairdocs.org/ad/2026-06-04): Rotorcraft flight control · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Apr 30, 2026
- [AD 2026-05-04](https://openairdocs.org/ad/2026-05-04): Main Rotor Head · Airbus Helicopters Deutschland MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4 and 3 more. Effective Apr 17, 2026
- [AD 2026-02-12](https://openairdocs.org/ad/2026-02-12): Main Rotor Mast/Swashplate · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Feb 17, 2026
- [AD 2025-25-11](https://openairdocs.org/ad/2025-25-11): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland MBB-BK 117 C-2, MBB-BK 117 D-2 and MBB-BK 117 D-3. Effective Feb 6, 2026
- [AD 2025-16-02](https://openairdocs.org/ad/2025-16-02): Main Rotor Mast/Swashplate · Airbus Helicopters Deutschland MBB-BK 117 C-2 and MBB-BK 117 D-2. Effective Jan 12, 2026
- [AD 2025-25-05](https://openairdocs.org/ad/2025-25-05): Rotorcraft Flight Control · Airbus Helicopters Deutschland BO-105A, BO-105C, BO-105S and 6 more. Effective Dec 31, 2025
- [AD 2025-20-06](https://openairdocs.org/ad/2025-20-06): Air Conditioning System · Airbus Helicopters Deutschland MBB-BK 117 D-2 and MBB-BK 117 D-3. Effective Dec 23, 2025
- [AD 2025-18-12](https://openairdocs.org/ad/2025-18-12): Battery/Charger System · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Oct 29, 2025
- [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 2025-14-04](https://openairdocs.org/ad/2025-14-04): Main Rotor Mast/Swashplate · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Jul 30, 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 2024-25-51](https://openairdocs.org/ad/2024-25-51): Rotorcraft Flight Control · Airbus Helicopters Deutschland MBB-BK 117 C-2. Effective Jan 17, 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 2024-04-01](https://openairdocs.org/ad/2024-04-01): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland EC135P1, EC135P2, EC135P2+ and 8 more. Effective Apr 19, 2024
- [AD 2023-22-15](https://openairdocs.org/ad/2023-22-15): Main Rotor Control · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Jan 16, 2024
- [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 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 2023-03-01](https://openairdocs.org/ad/2023-03-01): Main Rotor System · ECD Superlifter Conversion Kit 105-800331 (Eurocopter Deutschland STC SR00043RD). Effective Feb 21, 2023
- [AD 2022-20-01](https://openairdocs.org/ad/2022-20-01): Tail Rotor Control System · Airbus Helicopters Deutschland MBB-BK 117 C-2. Effective Nov 14, 2022
- [AD 2022-11-07](https://openairdocs.org/ad/2022-11-07): Main Rotor System · Airbus Helicopters Deutschland MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4 and 5 more. Effective Jul 8, 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 2022-08-15](https://openairdocs.org/ad/2022-08-15): Flight Compartment Equipment · Airbus Helicopters Deutschland MBB-BK 117 C-2. Effective May 26, 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 2022-06-01](https://openairdocs.org/ad/2022-06-01): Main Rotor System · Airbus Helicopters Deutschland MBB-BK 117 D-3. Effective Apr 20, 2022
- [AD 2022-06-13](https://openairdocs.org/ad/2022-06-13): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland MBB-BK 117 C-2 and MBB-BK 117 D-2 with STC SR03130NY or SR03703NY. Effective Mar 30, 2022
- [AD 2022-02-20](https://openairdocs.org/ad/2022-02-20): Main Rotor Mast/Swashplate · Airbus Helicopters Deutschland MBB-BK 117 C-2 and MBB-BK 117 D-2. 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 2022-02-17](https://openairdocs.org/ad/2022-02-17): Engine Air Intake System · Airbus Helicopters Deutschland MBB-BK 117 C-2, MBB-BK 117 D-2 and MBB-BK 117 D-3. Effective Feb 10, 2022
- [AD 2021-23-18](https://openairdocs.org/ad/2021-23-18): Equip/Furnishing System Wiring · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective Jan 11, 2022
- [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 2021-16-17](https://openairdocs.org/ad/2021-16-17): Main gearbox · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective Oct 13, 2021
- [AD 2021-14-05](https://openairdocs.org/ad/2021-14-05): Main Rotor Blades · Airbus Helicopters Deutschland MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4 and 3 more. Effective Aug 18, 2021
- [AD 2021-12-16](https://openairdocs.org/ad/2021-12-16): Main Rotor Control · Airbus Helicopters Deutschland MBB-BK 117 C-2 and MBB-BK 117 D-2. Effective Aug 3, 2021
- [AD 2021-12-08](https://openairdocs.org/ad/2021-12-08): Miscellaneous Wiring · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective Jul 29, 2021
- [AD 2021-12-09](https://openairdocs.org/ad/2021-12-09): Flight Control System · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective Jul 29, 2021
- [AD 2021-11-09](https://openairdocs.org/ad/2021-11-09): Main Rotor System · Airbus Helicopters Deutschland MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4 and 3 more. Effective Jul 12, 2021
- [AD 2021-10-21](https://openairdocs.org/ad/2021-10-21): Main Rotor System · Airbus Helicopters Deutschland BO-105A, BO-105C, BO-105LS A-3 and 9 more. Effective Jul 7, 2021
- [AD 2021-10-18](https://openairdocs.org/ad/2021-10-18): Flight Control System · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective Jul 6, 2021
- [AD 2021-10-23](https://openairdocs.org/ad/2021-10-23): Fasteners, Tail Rotor Control System · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective Jul 6, 2021
- [AD 2021-10-15](https://openairdocs.org/ad/2021-10-15): Cabin Equipment/Furnishings · Airbus Helicopters Deutschland MBB-BK 117 C-2 and MBB-BK 117 D-2. Effective Jul 1, 2021
- [AD 2021-06-05](https://openairdocs.org/ad/2021-06-05): Engine (Turbine, Turboprop) · Airbus Helicopters Deutschland MBB-BK 117 D-2. Effective May 7, 2021
- [AD 2021-05-07](https://openairdocs.org/ad/2021-05-07): Electrical Power System Wiring · Airbus Helicopters Deutschland BO-105A, BO-105C, BO-105S and 6 more. Effective Apr 16, 2021
- [AD 2021-02-11](https://openairdocs.org/ad/2021-02-11): Tail Rotor Gearbox · Airbus Helicopters Deutschland MBB-BK 117 A-1, MBB-BK 117 A-3, MBB-BK 117 A-4 and 4 more. Effective Apr 15, 2021

All 119: https://openairdocs.org/tcds/H13EU/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Eurocopter Deutschland MBB-BK 117 C-2](https://openairdocs.org/model/eurocopter-deutschland-mbb-bk-117-c-2): 109 aircraft (registry code 5626002)
- [Airbus Helicopters MBB-BK117 D-3](https://openairdocs.org/model/airbus-helicopters-mbb-bk117-d-3): 53 aircraft (registry codes 5620037, 3940080)
- [Airbus Helicopters Deutschland MBB-BK117 D-3](https://openairdocs.org/model/airbus-helicopters-deutschland-mbb-bk117-d-3): 40 aircraft (registry code 5620025)
- [Airbus Helicopters MBB-BK 117 C-2](https://openairdocs.org/model/airbus-helicopters-mbb-bk-117-c-2): 35 aircraft (registry code 1145009)
- [Airbus Helicopters Deutschland MBB-BK 117 D-2](https://openairdocs.org/model/airbus-helicopters-deutschland-mbb-bk-117-d-2): 21 aircraft (registry code 5620034)
- [Airbus Helicopters Deutschland MBB-BK 117 C-2](https://openairdocs.org/model/airbus-helicopters-deutschland-mbb-bk-117-c-2): 13 aircraft (registry code 5620036)
- [Messerschmitt-Bolkow-Blohm BK 117 B-2](https://openairdocs.org/model/messerschmitt-bolkow-blohm-bk-117-b-2): 11 aircraft (registry code 5626013)
- [Eurocopter Deutschland MBB-BK 117 C-1](https://openairdocs.org/model/eurocopter-deutschland-mbb-bk-117-c-1): 9 aircraft (registry code 5626025)
- [Eurocopter Deutschland MBB-BK 117-B2](https://openairdocs.org/model/eurocopter-deutschland-mbb-bk-117-b2): 3 aircraft (registry code 5626027)
- [MBB BK 117 A-3](https://openairdocs.org/model/mbb-bk-117-a-3): 3 aircraft (registry code 5626015)
- [Messerschmitt BK 117 B-1](https://openairdocs.org/model/messerschmitt-bk-117-b-1): 3 aircraft (registry code 5626012)
- [Airbus Helicopters Deutschland MBB-BK 117 C-2E](https://openairdocs.org/model/airbus-helicopters-deutschland-mbb-bk-117-c-2e): 1 aircraft (registry code 5620035)
- [American Eurocopter MBB-BK 117 C-2](https://openairdocs.org/model/american-eurocopter-mbb-bk-117-c-2): 1 aircraft (registry codes 1145003, 1145001)
- [Messerschmitt-Bolkow-Blohm BK 117 A-4](https://openairdocs.org/model/messerschmitt-bolkow-blohm-bk-117-a-4): 1 aircraft (registry code 5626017)
- [Messerschmitt-Bolkow-Blohm MBB-BK 117 B-2](https://openairdocs.org/model/messerschmitt-bolkow-blohm-mbb-bk-117-b-2): 1 aircraft (registry code 5626041)
- [Eurocopter Deutschland MBB BK-117 A4](https://openairdocs.org/model/eurocopter-deutschland-mbb-bk-117-a4): 0 aircraft (registry code 5626035)
- [Eurocopter DTCHLND GMBH BK117C1](https://openairdocs.org/model/eurocopter-dtchlnd-gmbh-bk117c1): 0 aircraft (registry code 8680975)
- [Messerschmitt BK 117](https://openairdocs.org/model/messerschmitt-bk-117): 0 aircraft (registry code 5626010)
- [Messerschmitt Bolkow Blohm BK117 B-1](https://openairdocs.org/model/messerschmitt-bolkow-blohm-bk117-b-1): 0 aircraft (registry code 5626033)
- [Messerschmitt-Boelkow-Blohn MBB-BK117 A-4](https://openairdocs.org/model/messerschmitt-boelkow-blohn-mbb-bk117-a-4): 0 aircraft (registry code 5626032)

## STCs approved under this data sheet (260, first 50)

- [STC SR12508IB](https://openairdocs.org/stc/SR12508IB): Installation of Personnel Carrying Devices (PCDs) for Human External Cargo (HEC). Ascent Aerospace Ltd.
- [STC SR11409DS](https://openairdocs.org/stc/SR11409DS): Installation of a TDFM Communication System. Airbus Helicopters 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 SR11849NY](https://openairdocs.org/stc/SR11849NY): Installation of an IRIS system made by Outerlink. Outerlink Corporation
- [STC SR01099DE](https://openairdocs.org/stc/SR01099DE): Installation of the GPMS Foresight MX Condition Monitoring System. GPMS International Inc.
- [STC SR00006RD](https://openairdocs.org/stc/SR00006RD): nstallation of Emergency Medical System (EMS) equipment part number 145121-501 or 145121-502. Aerolite AG
- [STC SR00601DE](https://openairdocs.org/stc/SR00601DE): Installation of a cabin air conditioning system.. Air Comm Corporation
- [STC SR12398DE](https://openairdocs.org/stc/SR12398DE): Installation of Improved Heater Ejector. Air Comm Corporation
- [STC SR02290LA](https://openairdocs.org/stc/SR02290LA): Installation of Apical Industries, Inc. Cable Cutters Kit .. Dart Aerospace
- [STC SR02270SE](https://openairdocs.org/stc/SR02270SE): Fabrication and installation of Geneva Aviation Audio System. AEM USA Inc.
- [STC SR02444SE](https://openairdocs.org/stc/SR02444SE): Installation of P178 Failsafe Audio Mixer. AEM USA Inc.
- [STC SR00638DE](https://openairdocs.org/stc/SR00638DE): Installation of a Floor Mounted Litter System (FMLS). Air Methods LLC
- [STC SR11354DS](https://openairdocs.org/stc/SR11354DS): Incorporation of IBF HOGE Performance with Extra EPC Margin. Airbus Helicopters Inc.
- [STC SR12207IB](https://openairdocs.org/stc/SR12207IB): Installation of the Bear Paw Kit. Alpine Aerotech LP
- [STC SR04465NY](https://openairdocs.org/stc/SR04465NY): Installation of the iPad Mount. Avio Design Group Inc
- [STC SR12072IB](https://openairdocs.org/stc/SR12072IB): Manufacturing and Installation of Cargo Hold Nets; 
Maintenance must be in accordance with ICARUS Aero Inc. Instructions for Continued Airworthiness as shown on
the attached FAA AML No. SR12072IB.. Icarus Aero Inc.
- [STC SH8975SW](https://openairdocs.org/stc/SH8975SW): Installation of an Isolair Eliminator II Fire Fighting System. Isolair Inc.
- [STC SR00171DE](https://openairdocs.org/stc/SR00171DE): Installation of a Versa TRAC Patient Loading System. Air Methods LLC
- [STC SR00126DE-D](https://openairdocs.org/stc/SR00126DE-D): Installation of enlarged aft cargo door windows.. Air Methods LLC
- [STC SR03703NY](https://openairdocs.org/stc/SR03703NY): Installation of Mecaer Aviation Group S.p.A.'s H145 VIP MB Interiors P/N 6EC10000X002001. Mecaer Aviation Group S.p.A.
- [STC SR04484NY](https://openairdocs.org/stc/SR04484NY): SkyTrac ISAT-200A Flight Following/Satcom System Installation. SkyTrac Systems Ltd.
- [STC SR00096DE-D](https://openairdocs.org/stc/SR00096DE-D): Installation of a search and landing light.. Air Methods LLC
- [STC SR00110RD](https://openairdocs.org/stc/SR00110RD): Installation of Luggage Net. HELIBRAS - Helicópteros do Brasil S. A.
- [STC SR00596DE](https://openairdocs.org/stc/SR00596DE): Installation of NVG Compatible Filters. Air Methods LLC
- [STC SR01853SE](https://openairdocs.org/stc/SR01853SE): Installation of skid tubes. Dart Aerospace USA Inc.
- [STC SR00234MC](https://openairdocs.org/stc/SR00234MC): Installation of one each SAL-7000 Interface Panel and two each AA-34 Universal Radio Interface units as
provisions for a Portable Hand Held Radio (PHHR). United States Government Light Utility Helicopter Product Office
- [STC SH4310NM](https://openairdocs.org/stc/SH4310NM): Installation of the Model 2110 Vibration Isolation Mount with a FLIR 2000 Series Infrared Imager or a Spectrolab SX-16 Nightsun. RSG Aviation Inc.
- [STC SR00187IB](https://openairdocs.org/stc/SR00187IB): Installation of Crew Bubble Window. VH Aerospace
- [STC SR11194DS](https://openairdocs.org/stc/SR11194DS): Installation of a Garmin GTX 345R. Airbus Helicopters Inc.
- [STC SR11190DS](https://openairdocs.org/stc/SR11190DS): Installation of a Garmin GTN 650. Airbus Helicopters Inc.
- [STC SR02137LA](https://openairdocs.org/stc/SR02137LA): Installation of Utility Mount. Airfilm Camera Systems
- [STC SR02514SE](https://openairdocs.org/stc/SR02514SE): Installation of a Model 311 GII Fire Attack System. Simplex Manufacturing Company
- [STC SR02508SE](https://openairdocs.org/stc/SR02508SE): Installation of Bearpaw kit. Dart Aerospace USA Inc.
- [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 SR00181BO](https://openairdocs.org/stc/SR00181BO): Installation of Outerlink Corporation CP-2 Satcom System in accordance with Outerlink Corporation Master Document List No. D000-1002, Revision IR, dated December 23, 2003, or later FAA-approved revision.. Outerlink Corporation
- [STC SR00374BO](https://openairdocs.org/stc/SR00374BO): The STC installs a Satcom and Flight Data Monitoring System KIT 145-SAT-100. Outerlink Corporation
- [STC SR04358CH](https://openairdocs.org/stc/SR04358CH): Installation of an Ultra Electronics - Flightline Systems, Inc. Health Usage Monitoring System (HUMS). Ultra Electronics ICE Inc.
- [STC SR02867AT](https://openairdocs.org/stc/SR02867AT): Installation of windows. TECH-TOOL PLASTICS INC
- [STC SR03779NY](https://openairdocs.org/stc/SR03779NY): Installation of Air Ambulance Equipment and VIP Interior. Air Ambulance Technology GmbH
- [STC SR11341DS](https://openairdocs.org/stc/SR11341DS): Installation of NVIS/NVG Cockpit Lighting System Compatible Modifications. Airbus Helicopters Inc.
- [STC SR00592DE](https://openairdocs.org/stc/SR00592DE): Installation of an Emergency Medical System (EMS) interior.. Air Methods Corporation
- [STC SR01611SE](https://openairdocs.org/stc/SR01611SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SR01074DE](https://openairdocs.org/stc/SR01074DE): Installation of Stryker 6086 Performance-PRO XT Gurney system and Performance Pro MX Locking System. Metro Aviation Inc
- [STC SR02244LA](https://openairdocs.org/stc/SR02244LA): Installation of Emergency Float Kits.. Dart Aerospace ULC
- [STC SR04694NY](https://openairdocs.org/stc/SR04694NY): Installation of the Emergency Float System. Dart Aerospace Limited
- [STC SR09528RC](https://openairdocs.org/stc/SR09528RC): Installation of Night Vision Imaging System (NVIS) / Night Vision Goggle (NVG) Compatible Lighting System. Aero Dynamix Inc.
- [STC SR00123MC](https://openairdocs.org/stc/SR00123MC): Installation of alternate cabin seating configurations. Airbus Helicopters Inc.
- [STC SR09403RC](https://openairdocs.org/stc/SR09403RC): Installation of Emergency Medical System. Metro Aviation Inc
- [STC SR09405RC](https://openairdocs.org/stc/SR09405RC): Installation of Optional Equipment. Metro Aviation Inc
- [STC SR00200MC](https://openairdocs.org/stc/SR00200MC): Installation of a AN/ARC-231 Communications system. Airbus Helicopters Inc.

All 260: https://openairdocs.org/tcds/H13EU/stcs.md

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