TCDS R.011
Issue 01, 10 July 2009
Page 1 of 24
European Aviation Safety Agency
EASA
TYPE CERTIFICATE
DATA SHEET
R.011
BO105
Type Certificate Holder:
EUROCOPTER DEUTSCHLAND GmbH
D-86607 Donauwörth
Germany
Manufacturer:
EUROCOPTER DEUTSCHLAND GmbH
D-86607 Donauwörth
Germany
Issue 01: 10 July 2009
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TCDS R.011
Issue 01, 10 July 2009
Page 2 of 24
TABLE OF CONTENTS
Sections for different 5 models [variants]
Page
BO105 A .....................................................................................................................................................................................................3
I.
II.
III.
IV.
V.
GENERAL ...................................................................................................................................................................................3
CERTIFICATION BASIS .................................................................................................................................................................3
TECHNICAL CHARACTERISTICS AND OPERATIONAL LIMITATIONS .....................................................................................................3
OPERATING AND SERVICE INSTRUCTIONS .....................................................................................................................................5
NOTES.......................................................................................................................................................................................5
BO105 C [C23, CB, CB-4, CB-5]................................................................................................................................................................6
I.
II.
III.
IV.
V.
GENERAL ...................................................................................................................................................................................6
CERTIFICATION BASIS .................................................................................................................................................................6
TECHNICAL CHARACTERISTICS AND OPERATIONAL LIMITATIONS .....................................................................................................6
OPERATING AND SERVICE INSTRUCTIONS .....................................................................................................................................9
NOTES.......................................................................................................................................................................................9
BO105 S [CS, CBS, CBS-4, CBS-5].........................................................................................................................................................10
I.
II.
III.
IV.
V.
GENERAL .................................................................................................................................................................................10
CERTIFICATION BASIS ...............................................................................................................................................................10
TECHNICAL CHARACTERISTICS AND OPERATIONAL LIMITATIONS ...................................................................................................10
OPERATING AND SERVICE INSTRUCTIONS ...................................................................................................................................13
NOTES.....................................................................................................................................................................................13
BO105 LS A-1 ..........................................................................................................................................................................................15
I.
II.
III.
IV.
V.
GENERAL .................................................................................................................................................................................15
CERTIFICATION BASIS ...............................................................................................................................................................15
TECHNICAL CHARACTERISTICS AND OPERATIONAL LIMITATIONS ...................................................................................................15
OPERATING AND SERVICE INSTRUCTIONS ...................................................................................................................................17
NOTES.....................................................................................................................................................................................17
BO105 LS A-3 ..........................................................................................................................................................................................18
VI.
VII.
VIII.
IX.
X.
GENERAL .................................................................................................................................................................................18
CERTIFICATION BASIS ...............................................................................................................................................................18
TECHNICAL CHARACTERISTICS AND OPERATIONAL LIMITATIONS ...................................................................................................18
OPERATING AND SERVICE INSTRUCTIONS ...................................................................................................................................20
NOTES.....................................................................................................................................................................................20
BO105 D [D, DS, DB, DB-4, DBS, DBS-4, DBS-5]...................................................................................................................................21
I.
II.
III.
IV.
V.
GENERAL .................................................................................................................................................................................21
CERTIFICATION BASIS ...............................................................................................................................................................21
TECHNICAL CHARACTERISTICS AND OPERATIONAL LIMITATIONS ...................................................................................................21
OPERATING AND SERVICE INSTRUCTIONS ...................................................................................................................................23
NOTES.....................................................................................................................................................................................23
TCDS R.011
Issue 01, 10 July
Page 3 of 24
BO105 A
BO105 A
I.
General
1. Data Sheet No:
EASA.R.011
based on LBA TCDS No. 3025 Issue No. 25 on 15.03.2004
2. Type / Variant or Model:
(a)
Type:
BO105
(b)
Variant or Model:
Model BO105 A
3. Airworthiness Category:
Normal Category Rotorcraft
4. Type Certificate Holder:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
5. Manufacturer:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
6. National Certification Date:
13 October 1970
7. LBA Application Date:
-
8. LBA Recommendation Date:
N/A
9. EASA Type Certification Date:
N/A
II. Certification Basis
1. Reference Date for determining the applicable requirements:
2. LBA Certification Date:
13 October 1970
3. LBA Type Certificate Data Sheet No:
3025
4. LBA Certification Basis:
(see the following points 5 to 9)
5. Airworthiness Requirements:
FAR 27 (first issue February 1, 1965 including amendments 27-1 through 27-3)
6. Special Conditions:
N/A
7. Reversion and Exemptions:
N/A
8. Equivalent Safety Findings:
N/A
9. Environmental Standards including Noise:
Complies with the essential requirements by virtue of early TC date
III. Technical Characteristics and Operational Limitations
1. Type Design Definition:
105-A1.11
2. Description:
Hingeless four-bladed main rotor, two-bladed tail rotor, rotor blades made of reinforced
fibreglass plastics, airframe of semi-monocoque design partly using honeycomb
components, horizontal stabilizer with end plates, propulsion by two freewheel turbines,
five-seat interior, skid landing gear.
3. Equipment:
Basic equipment must be installed and operational prior to registration of the helicopter.
4. Dimensions:
Fuselage:
Main Rotor:
Tail Rotor:
5. Engines:
Length
Width
Height
4 blades, diameter
2 blades, diameter
Manufacturer:
Type:
Number of engines
State of design engine TCDS No:
LBA data sheet no.:
4,30 m
1,58 m
3,00 m
9,84 m
1,90 m
Rolls-Royce Corporation
250-C18 freewheel turbines
Two
FAA E4CE
7007
TCDS R.011
Issue 01, 10 July
Page 4 of 24
BO105 A
5. 1 Installed Engine and Transmission Torque Limits:
(Engine limits at standard atmosphere and sea level)
Power/Torque Limits
kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
AEO-TOP (5 min)
2 x 317 [100]
51600 [101]
6000 [100]
749
AEO-MCP
2 x 270 [85]
49760 [97]
6000 [100]
Engine: 250-C18
All Engine Operation
693
Transients (6 sec):
843
Start-up (10 sec):
927
One Engine Inoperative
OEI-TOP (30 min)
1 x 317 [100]
51600 [101]
6000 [100]
749
OEI-MCP
1 x 270 [85]
49760 [97]
6000 [100]
693
6. Fluids (Fuel/Oil/Additives):
6.1
Fuel
(see EASA approved RFM, section 2)
6.2
Oil
(see EASA approved RFM, section 2)
7. Fluid capacities:
7.1
7.2
Fuel:
fuel tank capacity:
useable fuel:
Engine oil reservoir capacity (per engine):
580 l
570 l
4.5 l
8. Airspeed limits:
VNE = 135 knots
(see EASA approved RFM for reduction in VNE with altitude and other speed limitations)
9. Rotor Speed Limits:
Power on:
maximum
minimum
102 %
95 %
(433 rpm)
(403 rpm)
Power off:
maximum
minimum
110 %
85 %
(467 rpm)
(361 rpm)
10. Maximum Operating Altitude and Temp.:
17000 ft (for variation see EASA approved RFM)
11. Operating Limitations:
11.1 General:
VFR, No flight into known icing condition
11.2 Additional limitations for take-off and landing:
(see EASA approved RFM)
12. Maximum Certified Mass:
2100 kg
13. Centre of Gravity Range:
Longitudinal C.G Limits,
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3102 mm aft of DP at 2100 kg
maximum rearward limit:………………… 3395 mm aft of DP at 2100 kg
Lateral C.G Limits,
maximum deviation on right / left:………..100 mm
14. Datum Plane:
Longitudinal:
Lateral:
3000 mm in front of levelling point, frame 7
fuselage median plane
15. Levelling Means:
(see Maintenance Manual BO105, Chapter 103)
16. Minimum Flight Crew:
one (on right side)
17. Maximum Passenger Seating Capacity:
four
18. Passenger Emergency Exit:
two (one on each side of the passengers cabin)
19. Maximum Baggage/Cargo Loads:
Maximum loading of 600 kg/m2. Small baggage compartment: 20 kg
20. Rotor blade and control movement:
(For rigging information refer to the Maintenance Manual BO105)
21. Auxiliary Power Unit (APU):
N/A
22. Life-limited parts:
The periods specified in the latest EASA approved revision of the Airworthiness
Limitations section in Chapter 101 of the Maintenance Manual BO105 must not be
exceeded.
23. Wheels and Tires:
Skid type landing gear
TCDS R.011
Issue 01, 10 July
Page 5 of 24
BO105 A
IV. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No:
1. BO105 A Flughandbuch, Drittausgabe, firstly LBA approved on 01.11.1978 and
subsequent approved revisions.
2. BO105 A, Flight manual 3rd Issue, firstly approved on 01.11.1978, and subsequent
approved revisions.
2. Maintenance Manual, Document No:
a. Maintenance Manual BO105, second issue of 01.12.1990 (Wartung- und
Überholhandbuch, Hubschrauber BO105, Zweitausgabe vom 01.12.1990)
b. Repair Manual BO105
c. Illustrated Parts Catalogue BO105
d. Wiring Diagram Manual BO105
e. Engine documents as per LBA Engine TCDS No. 7007
3. Service Letters and Service Bulletins:
safety information notice (from October 2008 onwards, before: Alert Service
Information), information notice (from October 2008 onwards, before: Service
Information), Alert Service Bulletin, Service Bulletin
4. Required Equipment:
Special equipment and kits necessary for intended kind of operations as defined in the
approved Flight Manual are required.
V. Notes
1. Eligible serial numbers:
S/N 05, 06; 18; 19; 22; 24; 30 ; 53; 54
2. Applicability:
The serial numbers of rotorcraft delivered firstly for civil registration are listed in the ECD
document No: ECD-TN-ETYAC-001/2006.
3. Record of Type Certificate Holder:
The Type Certificate was originally issued to Messerschmitt-Bölkow-Blohm GmbH,
Postfach 801140, 8000 München 80.
4. Record of Manufacturer:
Company name until December 1991: Messerschmitt-Bölkow-Blohm GmbH,
Unternehmensbereich Drehflügler und Verkehr bzw. Unternehmensgruppe
Hubschrauber und Flugzeuge, Postfach 1350, W-8850 Donauwörth 80. Until May 1992
the manufacturer name was Eurocopter Hubschrauber GmbH, Postfach 1353, W-8850
Donauwörth. From May 1992 the manufacturer name has been changed to: Eurocopter
Deutschland GmbH, Postfach 1353, W-8850 Donauwörth or 86603 Donauwörth or
86607 Donauwörth.
TCDS R.011
Issue 01, 10 July 2009
Page 6 of 24
BO105 C
BO105 C [C23, CB, CB-4, CB-5]
I.
General
1. Data Sheet No:
EASA.R.011
based on LBA TCDS No. 3025 Issue No. 25 on 15.03.2004
2. Type / Variant or Model:
(a)
Type:
BO105
(b)
Variant or Model:
Model BO105 C (Variants: C23, CB, CB-4, CB-5)
3. Airworthiness Category:
Normal Category Rotorcraft
4. Type Certificate Holder:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
5. Manufacturer:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
6. National Certification Date:
31 August 1971
7. LBA Application Date:
-
8. LBA Recommendation Date:
N/A
9. EASA Type Certification Date:
N/A
II. Certification Basis
1. Reference Date for determining the applicable requirements:
2. LBA Certification Date:
31 August 1971
3. LBA Type Certificate Data Sheet No:
3025
4. LBA Certification Basis:
(see the following points 5 to 9)
5. Airworthiness Requirements:
FAR 27 (first issue February 1, 1965 including amendments 27-1 through 27-3)
FAR 29.45 to 29.79 including amendments 29-1 to 29-17 (for VTOL operation)
additionally for the variants CB-4 and CB-5:
FAR 27.1501 and 27.1581 including amendments 27-1 to 27-8
JAR 29.45 to 29.87 first issue – 06 September 1993
6. Special Conditions:
N/A
7. Reversion and Exemptions:
N/A
8. Equivalent Safety Findings:
N/A
9. Environmental Standards including Noise:
Complies with the essential requirements by virtue of early TC date
III. Technical Characteristics and Operational Limitations
1. Type Design Definition:
105-C1.01
2. Description:
Hingeless four-bladed main rotor, two-bladed tail rotor, rotor blades made of reinforced
fibreglass plastics, airframe of semi-monocoque design partly using honeycomb
components, horizontal stabilizer with end plates, propulsion by two freewheel turbines,
five-seat interior, skid landing gear. The BO105 C differs from the BO105 A in having
more powerful engines, higher all-up (take-off) weight and extended operating limits.
3. Equipment:
Basic equipment must be installed and operational prior to registration of the helicopter.
4. Dimensions:
Fuselage:
Main Rotor:
Tail Rotor:
5. Engines:
Length
Width
Height
4 blades, diameter
2 blades, diameter
4,30 m
1,58 m
3,00 m
9,84 m
1,90 m
Manufacturer:
Allison (Rolls-Royce Corporation)
Type (for variant C23)
250-C20 or 250-C20B freewheel turbines
Type (for variants CB, CB-3,CB-4, CB-5) 250-C20B freewheel turbines
Number of engines
Two
State of design engine TCDS No:
FAA E4CE
LBA data sheet no.:
7007
TCDS R.011
Issue 01, 10 July 2009
5.1
Page 7 of 24
BO105 C
Installed Engine and Transmission Torque Limits:
(Engine limits are at standard atmosphere and sea level, for temperature and RPM transients refer to the RFM)
Power/Torque Limits
kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
AEO-TOP (5 min)
2x235 [79]
52000 [102]
6016 [100]
793
AEO-MCP
2x235 [79]
51490 [101]
6016 [100]
777
1x277 [93]
52000 [102]
6016 [100]
793
Torque Transmission
Limits kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
AEO-TOP (5 min)
- Variants C23a)
- Variants CB b), CB-4 c), CB-5
2x235 [79]
2x257 [86]
53000 [104]
6016 [100]
810
AEO-MCP,
- Variants C23a)
- Variants CB b), CB-4 c), CB-5
2x235 [79]
2x257 [86]
52220 [102]
6016 [100]
779
1x277 [93]
1x283 [95]
53000 [104]
6016 [100]
810
Engine: 250-C20
All Engine Operation
One Engine Inoperative
Emergency Power
Engine: 250-C20B
All Engine Operation
One Engine Inoperative
Emergency Power
- Variants C23a)
- Variants CB b), CB-4 c), CB-5
One Engine Inoperative
d)
Max. Continuous Power
1x313 [105]
53510 [105]
6016[100]
810
2,5 min Power
1x328 [110]
53510 [105]
6016 [100]
810
a)
b)
c)
d)
Helicopters equipped with ZF FS72B main transmission and modified in accordance with. MBB Service Bulletin No. 60-44 are subject to the same operating limits as
Variant CB.
Applicable to helicopters with equipment cited in the Service Bulletin No. 60-33 or according to drawings 105-80020 and 105-80019 or 105-80021 and 105-80019
(valid for helicopters S/N S 1 to S 320). This is also applicable for series configuration starting from S/N S 321 onward.
Applicable to helicopters that fulfil the requirements of the Variant CB and is additionally fitted with optional equipment according to the MBB Service Bulletin No. 8077 or with Kit 105-80026 by the manufacturer (valid for helicopters S/N S 1 to S 750). The CB-4 is also valid for S/Ns S 751 and higher.
Applicable for the power transmission of the BO105 CB, CB-4 and CB-5 variants with ZF FS72E main transmission and other equipment according to SB-BO-105-80110 or to MBB/ED engineering drawing 105-84521.
6. Fluids (Fuel/Oil/Additives):
6.1
Fuel
(see EASA approved RFM, section 2)
6.2
Oil
(see EASA approved RFM, section 2)
7. Fluid capacities:
7.1
7.2
Fuel:
fuel tank capacity:
useable fuel:
Engine oil reservoir capacity (per engine):
8. Airspeed limits:
580 l
570 l
4.5 l
VNE = 145 knots up to 2400 kg
VNE = 130 knots above 2400 kg
Variant CB-5:
VNE = 145 knots up to 2300 kg
VNE = 130 knots above 2300 kg
(see EASA approved RFM for reduction in VNE with altitude and other speed limitations)
9. Rotor Speed Limits:
Power on:
maximum
minimum
102 %
98 %
(433 rpm)
(416 rpm)
Power off:
maximum
minimum
110 %
85 %
(467 rpm)
(361 rpm)
Transient:
(see EASA approved RFM)
(Note: For helicopters with a maximum certified mass of up to 2.400 kg a minimum
power on rotor rpm of 95% is permissible at airspeeds of less than VNE - 20 kts if the
triple tachometer indicator is marked accordingly)
10. Maximum Operating Altitude and Temp.:
17000 ft (for variation see EASA approved RFM)
TCDS R.011
Issue 01, 10 July 2009
Page 8 of 24
BO105 C
11. Operating Limitations:
11.1 General:
VFR, IFR (when equipped and operated in accordance with FMS 11-2), Category A
(equivalent) Operation (when equipped and operated in accordance with FMS 11-4),
No flight into known icing condition
11.2 Additional limitations for take-off and landing:
(see EASA approved RFM)
12. Maximum Certified Mass:
2300 kg (for Variants C23)
2400 kg (for Variant CB)
2500 kg (for Variants CB-4, CB-5)
2500 kg (for Variant CB, if the helicopter has been converted per SB No. 80-77 and is
operated in accordance with OPT 49)
13. Centre of Gravity Range:
Longitudinal C.G Limits,
Variants C23:
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3102 mm aft of DP at 2100 kg
3125 mm aft of DP at 2300 kg
maximum rearward limit………………… 3395 mm aft of DP at 2100 kg
3295 mm aft of DP at 2300 kg
other values on a straight line between the points given.
Variant CB:
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3125 mm aft of DP at 2400 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3295 mm aft of DP at 2400 kg
other values on a straight line between the points given.
Variant CB (for extended centre of gravity range according to Flight Manual OPT 48):
maximum forward limit………………….. 3081 mm aft of DP at 1140 kg
3038 mm aft of DP at 1900 kg
3075 mm aft of DP at 2400 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3295 mm aft of DP at 2400 kg
other values on a straight line between the points given.
Variant CB (for take-off mass between 2400 kg and 2500 kg according to Flight Manual
OPT 49), Variants CB-4 and CB-5:
maximum forward limit………………….. 3081 mm aft of DP at 1140 kg
3038 mm aft of DP at 1900 kg
3082 mm aft of DP at 2500 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3270 mm aft of DP at 2500 kg
other values on a straight line between the points given.
Lateral C.G Limits,
maximum deviation on right / left:………..100 mm up to 2400 kg
80 mm above 2400 kg
14. Datum Plane:
Longitudinal:
Lateral:
3000 mm in front of levelling point, frame 7
fuselage median plane
15. Levelling Means:
(see Maintenance Manual BO105, Chapter 103)
16. Minimum Flight Crew:
one (on right side)
17. Maximum Passenger Seating Capacity:
four
18. Passenger Emergency Exit:
two (one on each side of the passengers cabin)
19. Maximum Baggage/Cargo Loads:
Maximum loading of 600 kg/m2. Baggage compartment: 20 kg
20. Rotor blade and control movement:
(For rigging information refer to the Maintenance Manual BO105)
21. Auxiliary Power Unit (APU):
N/A
22. Life-limited parts:
The periods specified in the latest EASA approved revision of the Airworthiness
Limitations section in Chapter 101 of the Maintenance Manual BO105 must not be
exceeded.
23. Wheels and Tires:
Skid type landing gear
TCDS R.011
Issue 01, 10 July 2009
Page 9 of 24
BO105 C
IV. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No:
Variants C23:
BO105 C Flight Manual Variant C23, 3rd Issue, firstly approved on 01.11.1978, and
subsequent approved revisions
BO105 S Flughandbuch Variante C23, Drittausgabe, firstly approved on 01.11.1978,
and subsequent approved revisions
Variants CB, CB-4:
BO105 CB/CBS, 4th Issue, firstly approved on 23.11.1993, and subsequent approved
revisions.
BO105 C Flight Manual Variant CB, 3rd Issue including Rev. 2, firstly approved on
08.02.1980, and subsequent approved revisions
BO105 C Flughandbuch Variante CB, Drittausgabe including Rev. 2, firstly approved on
08.02.1980, and subsequent approved revisions
Variants CB-5:
BO105 CB-5/CBS-5, 2nd Issue, firstly approved on 10.04.1995, and subsequent
approved revisions..
Variants CB-4/ CB-5 for CAT A-Equivalent:
Flight Manual Supplement FMS 11-4, Rev. 5 (CB-4), Rev. 3 (CB-5) firstly LBA approved
12.07.2002 and subsequent approved revisions.
2. Maintenance Manual, Document No:
a. Maintenance Manual BO105, second issue of 01.12.1990 (Wartung- und
Überholhandbuch, Hubschrauber BO105, Zweitausgabe vom 01.12.1990)
b. Repair Manual BO105
c. Illustrated Parts Catalogue BO105
d. Wiring Diagram Manual BO105
e. Engine documents as per LBA Engine TCDS No. 7007
3. Service Letters and Service Bulletins:
safety information notice (from October 2008 onwards, before: Alert Service
Information), information notice (from October 2008 onwards, before: Service
Information), Alert Service Bulletin, Service Bulletin
4. Required Equipment:
Special equipment and kits necessary for intended kind of operations as defined in the
approved Flight Manual are required.
V. Notes
1. Eligible serial numbers:
S/N 01 to 929 (except S/Ns for the BO105 A and LS A-1)
2. Applicability:
The serial numbers of rotorcraft delivered firstly for civil registration are listed in the ECD
document No: ECD-TN-ETYAC-001/2006.
3. Record of Type Certificate Holder:
The Type Certificate was originally issued to Messerschmitt-Bölkow-Blohm GmbH,
Postfach 801140, 8000 München 80.
4. Record of Manufacturer:
Company name until December 1991: Messerschmitt-Bölkow-Blohm GmbH,
Unternehmensbereich Drehflügler und Verkehr bzw. Unternehmensgruppe
Hubschrauber und Flugzeuge, Postfach 1350, W-8850 Donauwörth 80. Until May 1992
the manufacturer name was Eurocopter Hubschrauber GmbH, Postfach 1353, W-8850
Donauwörth. From May 1992 the manufacturer name has been changed to: Eurocopter
Deutschland GmbH, Postfach 1353, W-8850 Donauwörth or 86603 Donauwörth or
86607 Donauwörth.
5. Convertibility:
Helicopters of the model BO 105 C, variant CB-4, may be converted into variant CB-5
according to the ECD drawings 105-80081/105-80082.
TCDS R.011
Issue 01, 10 July 2009
Page 10 of 24
BO105 S
BO105 S [CS, CBS, CBS-4, CBS-5]
I.
General
1. Data Sheet No:
EASA.R.011
based on LBA TCDS No. 3025 Issue No. 25 on 15.03.2004
2. Type / Variant or Model:
(a)
Type:
BO105
(b)
Variant or Model:
Model BO105 S (Variants: CS, CBS, CBS-4, CBS-5)
3. Airworthiness Category:
Normal Category Rotorcraft
4. Type Certificate Holder:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
5. Manufacturer:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
6. National Certification Date:
25 May 1977
7. LBA Application Date:
-
8. LBA Recommendation Date:
N/A
9. EASA Type Certification Date:
N/A
II. Certification Basis
1. Reference Date for determining the applicable requirements:
2. LBA Certification Date:
25 May 1977
3. LBA Type Certificate Data Sheet No:
3025
4. LBA Certification Basis:
(see the following points 5 to 9)
5. Airworthiness Requirements:
FAR 27 (first issue February 1, 1965 including amendments 27-1 through 27-3)
additionally for the variant CBS:
FAR 29.45 to 29.79 including amendments 29-1 to 29-17 (for VTOL operation)
additionally for the variants CBS-4 and CBS-5:
FAR 27.1501 and 27.1581 including amendments 27-1 to 27-8
JAR 29.45 to 29.87 (Draft version dated March 19, 1993)
additionally for the sub-variants CBS-5 KLH:
FAR 27.1501 and 27.1581 including amendments 27-1 to 27-8
6. Special Conditions:
N/A
7. Reversion and Exemptions:
N/A
8. Equivalent Safety Findings:
N/A
9. Environmental Standards including Noise:
Complies with the essential requirements by virtue of early TC date
III. Technical Characteristics and Operational Limitations
1. Type Design Definition:
105-CBS
2. Description:
Hingeless four-bladed main rotor, two-bladed tail rotor, rotor blades made of reinforced
fibreglass plastics, airframe of semi-monocoque design partly using honeycomb
components, horizontal stabilizer with end plates, propulsion by two free wheel turbines,
five-seat interior, skid landing gear. The BO105 S differs from the BO105 C in having a
stretched cabin.
3. Equipment:
Basic equipment must be installed and operational prior to registration of the helicopter.
4. Dimensions:
Fuselage:
Main Rotor:
Tail Rotor:
5. Engines:
Length
Width
Height
4 blades, diameter
2 blades, diameter
Manufacturer:
Type (for variant CS):
4,55 m
1,58 m
3,00 m
9,84 m (9,80 m for variant CBS-5)
1,90 m
Allison (Rolls-Royce Corporation)
250-C20 or 250-C20B freewheel turbines
TCDS R.011
Issue 01, 10 July 2009
Page 11 of 24
BO105 S
Type (for variants CBS, CBS-4, CBS-5):
Number of engines
State of design engine TCDS No:
LBA data sheet no.:
250-C20B freewheel turbines
Two
FAA E4CE
7007
5. 1 Installed Engine and Transmission Torque Limits:
(Engine limits are at standard atmosphere and sea level, for temperature and RPM transients refer to the RFM)
Engine: 250-C20
Power/Torque Limits
kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
All Engine Operation
AEO-TOP (5 min), Variant CSa)
2x235 [79]
52000 [102]
6016 [100]
793
AEO-MCP, Variant CSa)
2x235 [79]
51490 [101]
6016 [100]
777
1x277 [93]
52000 [102]
6016 [100]
793
Torque Transmission
Limits kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
AEO-TOP (5 min)
- Variant CSa)
- Variant CBS b), CBS-4 c), CBS-5
2x235 [79]
2x257 [86]
53000 [104]
6016 [100]
810
AEO-MCP,
a)
- Variant CS
b)
c)
- Variant CBS , CBS-4 , CBS-5
2x235 [79]
2x257 [86]
52220 [102]
6016 [100]
779
1x277 [93]
2x283 [95]
53000 [104]
6016 [100]
810
One Engine Inoperative
30’ Emergency Power, Variant
CSa)
Engine: 250-C20B
All Engine Operation
One Engine Inoperative
30’ Emergency Power
- Variant CSa)
- Variant CBS b), CBS-4 c), CBS-5
One Engine Inoperative d)
Max. Continuous Power
1x313 [105]
53510 [105]
6016[100]
810
2,5 min Power
1x328 [110]
53510 [105]
6016 [100]
810
a)
b)
c)
d)
Helicopters equipped with ZF FS72B main transmission and modified in accordance with. MBB Service Bulletin No. 60-44 are subject to the same operating limits as
Variant CBS.
Applicable to helicopters with equipment cited in the Service Bulletin No. 60-33 or according to drawings 105-80020 and 105-80019 or 105-80021 and 105-80019
(valid for helicopters S/N S 1 to S 320). This is also applicable for series configuration starting from S/N S 321 onward.
Applicable to helicopters that fulfil the requirements of the Variant CBS and is additionally fitted with optional equipment according to the MBB Service Bulletin No. 8077 or with Kit 105-80026 by the manufacturer (valid for helicopters S/N S 1 to S 750). The CBS-4 is also valid for S/Ns S 751 and higher.
Applicable for the power transmission of the BO105 CBS, CBS-4 and CBS-5 variants with main rotor transmissions ZF FS 72E and other equipment to SB-BO-10580-110 or to MBB/ED engineering drawing 105-84521.
6. Fluids (Fuel/Oil/Additives):
6.1
Fuel
(see EASA approved RFM, section 2)
6.2
Oil
(see EASA approved RFM, section 2)
7. Fluid capacities:
7.1
7.2
Fuel:
fuel tank capacity:
useable fuel:
Engine oil reservoir capacity (per engine):
8. Airspeed limits:
580 l
570 l
4.5 l
VNE = 145 knots up to 2400 kg
VNE = 130 knots above 2400 kg
Variant CBS-5:
VNE = 145 knots up to 2300 kg
VNE = 130 knots above 2300 kg
(see EASA approved RFM for reduction in VNE with altitude and other speed limitations)
TCDS R.011
Issue 01, 10 July 2009
9. Rotor Speed Limits:
Page 12 of 24
BO105 S
Power on:
maximum
minimum
102 %
98 %
(433 rpm)
(416 rpm)
Power off:
maximum
minimum
104 %
85 %
(442 rpm)
(361 rpm)
Transient:
(see EASA approved RFM)
(Note: For helicopters with a maximum certified mass of up to 2.400 kg a minimum
power on rotor rpm of 95% is permissible at airspeeds of less than VNE - 20 kts if the
triple tachometer indicator is marked accordingly)
10. Maximum Operating Altitude and Temp.:
17000 ft (for variation see EASA approved RFM)
11. Operating Limitations:
11.1 General:
VFR, IFR (when equipped and operated in accordance with FMS 11-2),
Category A (equivalent) Operation (when equipped and operated in accordance with
FMS 11-4), No flight into known icing condition
11.2 Additional limitations for take-off and landing:
(see EASA approved RFM)
12. Maximum Certified Mass:
2300 kg (for Variant CS)
2400 kg (for Variant CBS)
2500 kg (for Variants CBS-4, CBS-5)
2500 kg (for Variant CBS, if the helicopter has been converted per SB No. 80-77 and is
operated in accordance with OPT 49)
13. Centre of Gravity Range:
Longitudinal C.G Limits,
Variants CS:
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3102 mm aft of DP at 2100 kg
3125 mm aft of DP at 2300 kg
maximum rearward limit………………… 3395 mm aft of DP at 2100 kg
3295 mm aft of DP at 2300 kg
other values on a straight line between the points given.
Variant CBS:
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3125 mm aft of DP at 2400 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3295 mm aft of DP at 2400 kg
other values on a straight line between the points given.
Variant CBS (for extended centre of gravity range according to Flight Manual OPT 48):
maximum forward limit………………….. 3081 mm aft of DP at 1140 kg
3038 mm aft of DP at 1900 kg
3075 mm aft of DP at 2400 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3295 mm aft of DP at 2400 kg
other values on a straight line between the points given.
Variant CBS (for take-off mass between 2400 kg and 2500 kg according to Flight
Manual OPT 49), Variants CBS-4 and CBS-5:
maximum forward limit………………….. 3081 mm aft of DP at 1140 kg
3038 mm aft of DP at 1900 kg
3082 mm aft of DP at 2500 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3270 mm aft of DP at 2500 kg
other values on a straight line between the points given.
Lateral C.G Limits,
maximum deviation on right / left:………..100 mm up to 2400 kg
80 mm above 2400 kg
14. Datum Plane:
Longitudinal:
Lateral:
3000 mm in front of levelling point, frame 7
fuselage median plane
15. Levelling Means:
(see Maintenance Manual BO105, Chapter 103)
16. Minimum Flight Crew:
one (on right side)
17. Maximum Passenger Seating Capacity:
four (or five if the optional equipment “4-seater bench” MBB 105S-82660 is installed and
operated)
18. Passenger Emergency Exit:
two (one on each side of the passengers cabin)
19. Maximum Baggage/Cargo Loads:
Maximum loading of 600 kg/m2. Baggage compartment: 20 kg
TCDS R.011
Issue 01, 10 July 2009
Page 13 of 24
BO105 S
20. Rotor blade and control movement:
(For rigging information refer to the Maintenance Manual BO105)
21. Auxiliary Power Unit (APU):
N/A
22. Life-limited parts:
The periods specified in the latest revision of the Airworthiness Limitations section in
Chapter 101 of the Maintenance Manual BO105 must not be exceeded.
23. Wheels and Tires:
Skid type landing gear
IV. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No:
Variants CS:
BO105 S Flight Manual Variant CS, 3rd Issue, firstly approved on 01.11.1978, and
subsequent approved revisions
BO105 S Flughandbuch Variante CS, Drittausgabe, firstly approved on 01.11.1978, and
subsequent approved revisions
Variants CBS, CBS-4:
BO105 S Flight Manual Variant CBS, 3rd Issue and including Rev. 2, firstly approved on
08.02.1980, and subsequent approved revisions
BO105 S Flughandbuch Variante CBS, Drittausgabe and including Rev. 2, firstly
approved on 01.11.1978, and subsequent approved revisions
Variants CBS-5:
BO105 CB-5/CBS-5, 2nd Issue, firstly approved on 10.04.1995, and subsequent
approved revisions
Variants CBS-4/ CBS-5 for CAT A-Equivalent:
Flight Manual Supplement FMS 11-4, Rev. 5 (CB-4), Rev. 3 (CB-5) firstly LBA approved
12.07.2002 and subsequent approved revisions.
2. Maintenance Manual, Document No:
a. Maintenance Manual BO105, second issue of 01.12.1990 (Wartung- und
Überholhandbuch, Hubschrauber BO105, Zweitausgabe vom 01.12.1990)
b. Repair Manual BO105
c. Illustrated Parts Catalogue BO105
d. Wiring Diagram Manual BO105
e. Engine documents as per LBA Engine TCDS No. 7007
3. Service Letters and Service Bulletins:
safety information notice (from October 2008 onwards, before: Alert Service
Information), information notice (from October 2008 onwards, before: Service
Information), Alert Service Bulletin, Service Bulletin
4. Required Equipment:
Special equipment and kits necessary for intended kind of operations as defined in the
approved Flight Manual are required.
V. Notes
1. Eligible serial numbers:
S/N 01 to 929 (except S/Ns for the BO105 A and BO105 LS A-1)
2. Applicability:
The serial numbers of rotorcraft delivered firstly for civil registration are listed in the ECD
document No: ECD-TN-ETYAC-001/2006.
3. Record of Type Certificate Holder:
The Type Certificate was originally issued to Messerschmitt-Bölkow-Blohm GmbH,
Postfach 801140, 8000 München 80.
4. Record of Manufacturer:
Company name until December 1991: Messerschmitt-Bölkow-Blohm GmbH,
Unternehmensbereich Drehflügler und Verkehr bzw. Unternehmensgruppe
Hubschrauber und Flugzeuge, Postfach 1350, W-8850 Donauwörth 80. Until May 1992
the manufacturer name was Eurocopter Hubschrauber GmbH, Postfach 1353, W-8850
Donauwörth. From May 1992 the manufacturer name has been changed to: Eurocopter
Deutschland GmbH, Postfach 1353, W-8850 Donauwörth or 86603 Donauwörth or
86607 Donauwörth..
5. Convertibility:
The models BO105 C may be converted into the model BO105 S configuration
according to the drawings No. 105 S-000001 or:
- No. 105 S-000002
(S/N S 161 to 300) or
- No. 105 S-000003
(S/N S 301 to 550) or
- No. 105 S-000005
(S/N S 551 to 740) or
- No. 105 S-000006
(S/N S 741 to 780)
The models BO105 C (S/N S 9 to S 160) may be converted in accordance with the
drawing No. 105-80036 into the BO105 S variant CBS-4 configuration or into variant
CBS, if Kit 105-80026 is not installed.
The BO105 S variant CBS-4 (S/N up to and including 901) may be converted into the
variant CBS-5 in accordance with the drawings No. 105-80038/105-80033.
The BO105 S variant CBS-4, S/N from 902 and upwards, may be converted into the
TCDS R.011
Issue 01, 10 July 2009
Page 14 of 24
BO105 S
variant CBS-5 in accordance with the drawings No. 105-80838/105-80833.
The BO105 S sub-variant CBS-5-KLH is fitted with various equipment items according to
P/N 105-CBS-KLH. Only helicopters S/N 932 and 933 are of the variant CBS-5-KLH.
These helicopters do not qualify for a civil registration.
TCDS R.011
Issue 01, 10 July 2009
Page 15 of 24
BO105 LS A-1
BO105 LS A-1
I.
General
1. Data Sheet No:
EASA.R.011
based on LBA TCDS No. 3025 Issue No. 25 on 15.03.2004
2. Type / Variant or Model:
(a)
Type:
BO105
(b)
Variant or Model:
BO105 LS A-1
3. Airworthiness Category:
Normal Category Rotorcraft
4. Type Certificate Holder:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
5. Manufacturer:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
6. National Certification Date:
19 July 1984
7. LBA Application Date:
-
8. LBA Recommendation Date:
N/A
9. EASA Type Certification Date:
N/A
II. Certification Basis
1. Reference Date for determining the applicable requirements:
2. LBA Certification Date:
19 July 1984
3. LBA Type Certificate Data Sheet No:
3025
4. LBA Certification Basis:
(see the following points 5 to 9)
5. Airworthiness Requirements:
FAR 27 (first issue February 1, 1965 including amendments 27-1 through 27-3)
FAR 27.67 and FAR 27.75 amendments 27-14
FAR 27.923 and FAR 27.927 amendments 27-12
FAR 27.939 amendments 27-11
FAR 27.1195 amendments 27-5
6. Special Conditions:
N/A
7. Reversion and Exemptions:
N/A
8. Equivalent Safety Findings:
N/A
9. Environmental Standards including Noise:
Complies with the essential requirements by virtue of early TC date
III. Technical Characteristics and Operational Limitations
1. Type Design Definition:
105-LS-A1.01
2. Description:
Hingeless four-bladed main rotor, two-bladed tail rotor, rotor blades made of reinforced
fibreglass plastics, airframe of semi-monocoque design partly using honeycomb
components, horizontal stabilizer with end plates, propulsion by two free wheel turbines,
five-seat interior, skid landing gear. The BO105 LS A-1 differs from the BO105 S in
having a more powerful engine and reinforced transmission, improvements in the engine
oil cooler and in the onboard electrical system.
3. Equipment:
Basic equipment must be installed and operational prior to registration of the helicopter.
4. Dimensions:
Fuselage:
Main Rotor:
Tail Rotor:
5. Engines:
Length
Width
Height
4 blades, diameter
2 blades, diameter
Manufacturer:
Type:
Number of engines
State of design engine TCDS No:
4,55 m
1,58 m
3,00 m
9,84 m
1,90 m
Allison (Rolls-Royce Corporation)
250-C28C freewheel turbines
Two
FAA E1GL
TCDS R.011
Issue 01, 10 July 2009
Page 16 of 24
BO105 LS A-1
LBA data sheet no.:
EASA engine TCDS No:
7014
-
5. 1 Installed Engine and Transmission Torque Limits:
(Engine limits are at standard atmosphere and sea level, for temperature and RPM transients refer to the RFM)
Power/Torque Limits
kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
AEO-TOP (5 min)
2x283 [54]
52980 [104]
6016 [100]
791
AEO-MCP
2x258 [49]
52980 [104]
6016 [100]
741
52980 [104]
6016 [100]
791
Engine: 250-C28C
All Engine Operation
One Engine Inoperative
2,5 min OEI-TOP
1x410[78]
30 min OEI-MCP
2x368 [70]
6. Fluids (Fuel/Oil/Additives):
6.1
Fuel
(see EASA approved RFM, section 2)
6.2
Oil
(see EASA approved RFM, section 2)
7. Fluid capacities:
7.1
7.2
Fuel:
fuel tank capacity:
useable fuel:
Engine Oil reservoir capacity (per engine):
580 l
570 l
4.5 l
8. Airspeed limits:
VNE = 145 knots
(see EASA approved RFM for reduction in VNE with altitude and other speed limitations)
9. Rotor Speed Limits:
Power on:
maximum
minimum
minimum
102 %
98 %
100 %
(433 rpm)
(416 rpm) below 12000 ft
(424 rpm) above 12000 ft
Power off:
maximum
minimum
104 %
85 %
(442 rpm)
(361 rpm)
Transient:
(see EASA approved RFM)
10. Maximum Operating Altitude and Temp.:
17000 ft (for variation see EASA approved RFM)
11. Operating Limitations:
11.1 General:
VFR, No flight into known icing condition
11.2 Additional limitations for take-off and landing:
(see EASA approved RFM)
12. Maximum Certified Mass:
2400 kg
13. Centre of Gravity Range:
Longitudinal C.G Limits,
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3125 mm aft of DP at 2400 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3295 mm aft of DP at 2400 kg
Other values on a straight line between the points given.
Lateral C.G Limits,
maximum deviation on right / left:………..100 mm up to 2400 kg
14. Datum Plane:
Longitudinal:
Lateral:
3000 mm in front of levelling point, frame 7
fuselage median plane
15. Levelling Means:
(see Maintenance Manual BO105 LS, Chapter 103)
16. Minimum Flight Crew:
one (on right side)
17. Maximum Passenger Seating Capacity:
four (or five if the optional equipment “4-seater bench” MBB 105S-82660 is installed and
operated)
18. Passenger Emergency Exit:
two (one on each side of the passengers cabin)
19. Maximum Baggage/Cargo Loads:
Maximum loading of 600 kg/m . Baggage compartment: 20 kg
20. Rotor blade and control movement:
(For rigging information refer to the Maintenance Manual BO105)
2
TCDS R.011
Issue 01, 10 July 2009
Page 17 of 24
BO105 LS A-1
21. Auxiliary Power Unit (APU):
N/A
22. Life-limited parts:
The periods specified in the latest revision annex A, section 9 of the BO105 LS A-1
Maintenance Manual must not be exceeded.
23. Wheels and Tires:
Skid type landing gear
IV. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No:
BO105 LS A-1, firstly LBA approved on 19.07.1984
2. Maintenance Manual, Document No:
a.
b.
c.
d.
3. Service Letters and Service Bulletins:
safety information notice (from October 2008 onwards, before: Alert Service
Information), information notice (from October 2008 onwards, before: Service
Information), Alert Service Bulletin, Service Bulletin
4. Required Equipment:
Special equipment and kits necessary for intended kind of operations as defined in the
approved Flight Manual are required.
Maintenance Manual BO105 LS A-1
Repair Manual BO105
Wiring Diagram Manual BO105
Engine documents as per LBA Engine TCDS No. 7014
V. Notes
1. Eligible serial numbers:
S/N 459, 651, 652, 653, 654, 655.
These serial numbers were retrofitted to BO105 LS A-1 in accordance with the drawing
No. 105 LSA 1.01.
2. Applicability:
The serial numbers of rotorcraft delivered firstly for civil registration are listed in the ECD
document No: ECD-TN-ETYAC-001/2006.
3. Record of Type Certificate Holder:
The Type Certificate was originally issued to Messerschmitt-Bölkow-Blohm GmbH,
Postfach 801140, 8000 München 80.
4. Record of Manufacturer:
Company name until December 1991: Messerschmitt-Bölkow-Blohm GmbH,
Unternehmensbereich Drehflügler und Verkehr bzw. Unternehmensgruppe
Hubschrauber und Flugzeuge, Postfach 1350, W-8850 Donauwörth 80. Until May 1992
the manufacturer name was Eurocopter Hubschrauber GmbH, Postfach 1353, W-8850
Donauwörth. From May 1992 the manufacturer name has been changed to: Eurocopter
Deutschland GmbH, Postfach 1353, W-8850 Donauwörth or 86603 Donauwörth or
86607 Donauwörth.
TCDS R.011
Issue 01, 10 July 2009
Page 18 of 24
BO105 LS A-3
BO105 LS A-3
VI. General
1. Data Sheet No:
EASA.R.011
based on TCCA TCDS No. H-94 Issue No. 3 on July 31, 1994
and on LBA TCDS No. 3058 Issue 1 on 25 February 1991
2. Type / Variant or Model:
(a)
Type:
BO105
(b)
Variant or Model:
BO105 LS A-3
3. Airworthiness Category:
Normal Category Rotorcraft
4. Type Certificate Holder:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
5. Manufacturer:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
6. National Certification Date:
based on LBA TCDS No. 3025 first Issue on 07 July 1986 (see section X. Notes 1.)
7. LBA Application Date:
12. June 1985
8. LBA Recommendation Date:
N/A
9. EASA Type Certification Date:
N/A
VII. Certification Basis
1. Reference Date for determining the applicable requirements:
2. LBA Certification Date:
07 June 1986 (see notes)
3. LBA Type Certificate Data Sheet No:
3058
4. LBA Certification Basis:
(see the following points 5 to 9)
5. Airworthiness Requirements:
FAR 27 effective February 1, 1965, including Amendments 27-1 through 27-3.
FAA Special Conditions 27-31 EU-6 issued November 8, 1970.
The following amendments have been incorporated into the approval basis: FAR
27.1195 Amendment 27-5, 27.939 Amendment 27-11, 27.923 and 27.927
Amendment 27-12, 27.67 and 27.75 Amendment 27-14.
6. Special Conditions:
N/A
7. Reversion and Exemptions:
N/A
8. Equivalent Safety Findings:
for Static Longitudinal Stability FAR 27.175(b) as detailed in MBB Opinion Sheet LHE3261/87.
9. Environmental Standards including Noise:
German Noise Prevention Requirement for Aircraft (Lärmschutzforderungen für
Luftfahrzeuge LSL) Chapter 8 dated August 1st, 1985 (equivalent to ICAO Annex 16
Chapter 8
VIII. Technical Characteristics and Operational Limitations
1. Type Design Definition:
105-A3.01
2. Description:
Hingeless four-bladed main rotor, two-bladed tail rotor, rotor blades made of reinforced
fibreglass plastics, airframe of semi-monocoque design partly using honeycomb
components, horizontal stabilizer with end plates, propulsion by two free wheel turbines,
five-seat interior, skid landing gear.
3. Equipment:
Basic equipment must be installed and operational prior to registration of the helicopter.
4. Dimensions:
Fuselage:
Main Rotor:
Tail Rotor:
5. Engines:
Length
Width
Height
4 blades, diameter
2 blades, diameter
Manufacturer:
Type:
Number of engines
State of design engine TCDS No:
4,55 m
1,58 m
3,00 m
9,84 m
1,90 m
Rolls-Royce Corporation
250-C28C freewheel turbines
Two
FAA E1GL
TCDS R.011
Issue 01, 10 July 2009
Page 19 of 24
BO105 LS A-3
LBA data sheet no.:
7014
5. 1 Installed Engine and Transmission Torque Limits:
(Engine limits are at standard atmosphere and sea level, for temperature and RPM transients refer to the RFM)
Engine: 250-C28C
KW (SHP)
Take-off (5 min)
Maximum Continuous
373 (500)
368 (494)
Power turbine rpm
min-1 [%]
6036 (102)
6030 (102)
kW (SHP)
Torque
310 (416)
294 (395)
75%
72%
410 (550)
368 (494)
100%
90%
Transmission Limits:
Take-off (5 min.)
Maximum Continuous
One Engine inoperative:
Gas generator rpm Temperature TOT
min-1 [%]
°C
52980 (104)
791
52980 (104)
741
6. Fluids (Fuel/Oil/Additives):
6.1
Fuel
(see EASA approved RFM, section 2)
6.2
Oil
(see EASA approved RFM, section 2)
7. Fluid capacities:
7.1
7.2
Fuel:
fuel tank capacity:
useable fuel:
Engine Oil reservoir capacity (per engine):
580 l (127.6 Imp. gallons)
570 l (125.4 Imp: gallons)
5.0 l (1.1 Imp. gallons)
8. Airspeed limits:
VNE = 145 knots (268.5 km/h)
(see EASA approved RFM for reduction in VNE with altitude and other speed limitations)
9. Rotor Speed Limits:
Power on:
max. Transient
105 % (446 rpm)
max. Continuous
102 % (433 rpm)
min. Transient
95 %
(413 rpm)
min. Continuous
98 %
(416 rpm)
below 8000 ft 100% (424 rpm) above 8000 ft
Power off:
max. Transient
max. Continuous
min. Transient
min. Continuous
10. Maximum Operating Altitude and Temp.:
110 %
104 %
85 %
85 %
(467 rpm)
(442 rpm)
(361 rpm)
(361 rpm)
20,000 ft (for variation see EASA approved RFM)
11. Operating Limitations:
11.1 General:
VFR, No flight into known icing condition
11.2 Additional limitations for take-off and landing:
(see EASA approved RFM)
12. Maximum Certified Mass:
2600 kg (5733lb)
13. Centre of Gravity Range:
Longitudinal C.G Limits,
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3137 mm aft of DP at 2600 kg
maximum rearward limit………………… 3247 mm aft of DP at 2600 kg
3395 mm aft of DP at 2000 kg
other values on a straight line between the points given.
Lateral C.G Limits,
Up to 2400 kg 100mm left or right of Lateral Reference Datum.
2400-2600 kg 80mm left or right of Lateral Reference Datum.
14. Datum Plane:
Longitudinal:
Lateral:
3000 mm in front of levelling point, frame 7
Longitudinal plane of symmetry
15. Levelling Means:
(see Maintenance Manual BO105 LS, Chapter 103)
16. Minimum Flight Crew:
one (on right side)
TCDS R.011
Issue 01, 10 July 2009
Page 20 of 24
BO105 LS A-3
17. Maximum Passenger Seating Capacity:
four (or five if the optional equipment “4-seater bench” MBB 105S-82660 is installed and
operated)
18. Passenger Emergency Exit:
two (one on each side of the passengers cabin)
19. Maximum Baggage/Cargo Loads:
Maximum loading of 600 kg/m2. Baggage compartment: 20 kg
20. Rotor blade and control movement:
(For rigging information refer to the Maintenance Manual BO105)
21. Auxiliary Power Unit (APU):
N/A
22. Life-limited parts:
The periods specified in the latest revision annex A, section 9 of the BO105 LS A-3
Maintenance Manual must not be exceeded.
23. Wheels and Tires:
Skid type landing gear
IX. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No:
BO105 LS A-3, Issue 3 Rev. 3, firstly EASA approved on 30.06.2009
2. Maintenance Manual, Document No:
a.
b.
c.
d.
3. Service Letters and Service Bulletins:
safety information notice from October, 2008 (Alert Service Information), information
notice from October, 2008 (Service Information), Alert Service Bulletin, Service Bulletin
4. Required Equipment:
Special equipment and kits necessary for intended kind of operations as defined in the
approved Flight Manual are required.
Maintenance Manual BO105 LS A-3
Repair Manual BO105
Wiring Diagram Manual BO105
Engine documents as per LBA Engine TCDS No. 7014
X. Notes
1. Eligible serial numbers:
2001 through 2058
2. Applicability:
The serial numbers of rotorcraft delivered firstly for civil registration are listed in the ECD
document No: ECD-TN-ETYAC-001/2006.
3. Record of Type Certificate Holder:
The Type Certificate was originally issued to Messerschmitt-Bölkow-Blohm GmbH,
Postfach 801140, 8000 München 80.
On 25.02.1991 the TC was transferred to MCL, Fort Erie/Ontario.
Effective March 20, 1992 MBB Helicopter Canada name was changed to Eurocopter
Canada Limited.
4. Record of Manufacturer:
serial numbers 2001-2016 were manufactured by Messerschmitt-Bölkow-Blohm GmbH,
Unternehmensbereich Drehflügler und Verkehr, Postfach 1350, W-8850 Donauwörth 80,
under Luftfahrt Bundesamt Type Certificate 3025.
Model LS A-3, serial numbers 2017-2032 were manufactured by MBB Helicopter
Canada Limited, Fort Erie, Ontario, under Transport Canada Type Approval H-79,
serial numbers 2033-2058 were manufactured by MBB Helicopter Canada Limited, Fort
Erie, Ontario, under Transport Canada Type Approval H-94.
5. Responsibility Transfer:
Initial certification of BO105 LS A-3 by LBA on 07 July 1986 under TC No. 3025.
As per 25.02.1991, the development responsibility for all BO105 LS A-3 models was
transferred from MBB, D-8000 München 80, and the Civil Aviation Authority of Germany
(LBA) to Messerschmitt-Bölkow-Blohm Helicopter Canada Limited (MCL), Fort Erie,
Canada and Transport Canada.
As per 30.06.2009, the development responsibility for all BO105 LS A-3 models was
transferred from Eurocopter Canada Limited, Fort Erie, Canada, and Transport Canada
to Eurocopter Deutschland GmbH and European Aviation Safety Agency.
6. Airworthiness Directives:
a) The TCCA Airworthiness Directive that are applied at the time of design transfer (See
NOTE 5) are
CF-88-07R2
CF-91-41
CF-2005-17R1
CF-88-18
CF-93-06
CF-2008-17R1
CF-97-18
CF-2009-12
TCDS R.011
Issue 01, 10 July 2009
Page 21 of 24
BO105 D
BO105 D [D, DS, DB, DB-4, DBS, DBS-4, DBS-5]
I.
General
1. Data Sheet No:
EASA.R.011
based on LBA TCDS No. 3025 Issue No. 25 on 15.03.2004
and CAA UK TCDS FR.3 Issue No. 4 on August 1996)
2. Type / Variant or Model:
(a)
Type:
BO105
(b)
Variant or Model:
Model BO105 D (Variants: D, DS, DB, DBS, DB-4, DBS-4, DBS-5)
3. Airworthiness Category:
Normal Category Rotorcraft
4. Type Certificate Holder:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
5. Manufacturer:
Eurocopter Deutschland GmbH, Industriestrasse 4, D-86607 Donauwörth, Germany
6. National Certification Date:
15 August 1985
7. LBA Application Date:
-
8. LBA Recommendation Date:
N/A
9. EASA Type Certification Date:
N/A
II. Certification Basis
1. Reference Date for determining the applicable requirements:
2. NAA Certification Dates:
CAA UK 05 July 1973
LBA 15 August 1985
3. NAA Type Certificate Data Sheet No:
LBA: 3025
CAA: UK FR.3
4. LBA Certification Basis:
(see the following points 5 to 9)
5. Airworthiness Requirements:
FAR 27 (first issue February 1, 1965 including amendments 27-1 through 27-3)
6. Special Conditions:
N/A
7. Reversion and Exemptions:
N/A
8. Equivalent Safety Findings:
N/A
9. Environmental Standards including Noise:
Complies with the essential requirements by virtue of early TC date
III. Technical Characteristics and Operational Limitations
1. Type Design Definition:
105-800086
2. Description:
Hingeless four-bladed main rotor, two-bladed tail rotor, rotor blades made of reinforced
fibreglass plastics, airframe of semi-monocoque design partly using honeycomb
components, horizontal stabilizer with end plates, propulsion by two freewheel turbines,
five-seat interior, skid landing gear.
The BO105 D differs from the BO105 C by changes to the electrical system and detailed
changes to the engine and hydraulic installations. These changes have been defined for
the purpose of export to Great Britain and are contained in Kit 105-80082.
The technical characteristics and differences of the variants are provided in the following
subparagraphs.
3. Equipment:
Basic equipment must be installed and operational prior to registration of the helicopter.
4. Dimensions:
Fuselage:
Main Rotor:
Tail Rotor:
5. Engines:
Length
Width
Height
4 blades, diameter
2 blades, diameter
4,30 m
1,58 m
3,00 m
9,84 m (9,80 m for variant DBS-5)
1,90 m
Manufacturer:
Allison (Rolls-Royce Corporation)
Type (for variants D, DS):
250-C20 or 250-C20B freewheel turbines
Type (for variants DB, DBS, DB-4, DBS-4, DBS-5): 250-C20B freewheel turbines
Number of engines
two
State of design engine TCDS No:
FAA E4CE
TCDS R.011
Issue 01, 10 July 2009
Page 22 of 24
BO105 D
LBA data sheet no.:
EASA engine TCDS No:
7007
-
5. 1 Installed Engine and Transmission Torque Limits:
(Engine limits are at standard atmosphere and sea level, for temperature and RPM transients refer to the RFM)
Engine: 250-C20
(Variants D, DS)
Power/Torque Limits
kW [%]
Gas generator rpm
min-1 [%]
Power turbine rpm
min-1 [%]
Temperature TOT
°C
All Engine Operation
AEO-TOP (5 min)
2x235 [79]
52000 [102]
6016 [100]
793
AEO-MCP
2x235 [79]
51490 [101]
6016 [100]
777
1x277 [93]
52000 [102]
6016 [100]
793
Power turbine rpm
min-1 [%]
Temperature TOT
°C
One Engine Inoperative
OEI-MCP
Engine: 250-C20B
(Variants D, DS)
Torque Transmission Gas generator rpm
Limits kW [%]
min-1 [%]
All Engine Operation
AEO-TOP (5 min)
2x235 [79]
53000 [104]
6016 [100]
810
AEO-MCP
2x235 [79]
52220 [102]
6016 [100]
779
1x277 [93]
53000 [104]
6016 [100]
810
Power turbine rpm
min-1 [%]
Temperature TOT
°C
One Engine Inoperative
OEI-MCP
Engine: 250-C20B
(DB, DB-4, DBS, DBS-4, DBS-5)
Torque Transmission Gas generator rpm
Limits kW [%]
min-1 [%]
All Engine Operation
AEO-TOP (5 min)
2x257 [86]
105
102
810
AEO-MCP
2x257 [86]
105
102
779
1x313 [105]
1x328 [110]
53510 [105]
53510 [105]
6016[100]
6016 [100]
810
810
One Engine Inoperative
Max. Continuous Power
2,5 min Power
6. Fluids (Fuel/Oil/Additives):
6.1
Fuel
(see EASA approved RFM, section 2)
6.2
Oil
(see EASA approved RFM, section 2)
7. Fluid capacities:
7.1
7.2
Fuel:
fuel tank capacity:
useable fuel:
Engine oil reservoir capacity (per engine):
580 l
570 l
4.5 l
8. Airspeed limits:
VNE = 145 knots
(see EASA approved RFM for reduction in VNE with altitude and other speed limitations)
9. Rotor Speed Limits:
Power on:
maximum
minimum
102 %
98 %
(433 rpm)
(416 rpm)
Power off:
maximum
minimum
110 %
85 %
(467 rpm)
(361 rpm)
Transient:
(see EASA approved RFM)
10. Maximum Operating Altitude and Temp.:
17000 ft (for variation see EASA approved RFM)
11. Operating Limitations:
11.1 General:
VFR, No flight into known icing condition
11.2 Additional limitations for take-off and landing:
(see EASA approved RFM)
12. Maximum Certified Mass:
2300 kg (for Variants D, DS)
2400 kg (for Variants DB, DBS)
2500 kg (for Variants DB-4, DBS-4, DBS-5)
13. Centre of Gravity Range:
Longitudinal C.G Limits,
Variants D, DS:
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3102 mm aft of DP at 2100 kg
3125 mm aft of DP at 2300 kg
TCDS R.011
Issue 01, 10 July 2009
Page 23 of 24
BO105 D
maximum rearward limit………………… 3395 mm aft of DP at 2100 kg
3295 mm aft of DP at 2300 kg
other values on a straight line between the points given.
Variants DB, DBS:
maximum forward limit………………….. 3081 mm aft of DP at 1800 kg
3125 mm aft of DP at 2400 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3295 mm aft of DP at 2400 kg
other values on a straight line between the points given.
Variants DB-4, DBS-4, DBS-5:
maximum forward limit………………….. 3081 mm aft of DP at 1140 kg
3038 mm aft of DP at 1900 kg
3082 mm aft of DP at 2500 kg
maximum rearward limit………………… 3395 mm aft of DP at 2000 kg
3270 mm aft of DP at 2500 kg
other values on a straight line between the points given.
Lateral C.G Limits,
maximum deviation on right / left:………..100 mm up to 2400 kg
80 mm above 2400 kg
14. Datum Plane:
Longitudinal:
Lateral:
3000 mm in front of levelling point, frame 7
fuselage median plane
15. Levelling Means:
(see Maintenance Manual BO105, Chapter 103)
16. Minimum Flight Crew:
one (on right side)
17. Maximum Passenger Seating Capacity:
four
18. Passenger Emergency Exit:
two (one on each side of the passengers cabin)
19. Maximum Baggage/Cargo Loads:
Maximum loading of 600 kg/m2. Baggage compartment: 20 kg
20. Rotor blade and control movement:
(For rigging information refer to the Maintenance Manual BO105)
21. Auxiliary Power Unit (APU):
N/A
22. Life-limited parts:
The periods specified in the latest revision of the Chapter 11 of the Maintenance Manual
BO105 must not be exceeded.
23. Wheels and Tires:
Skid type landing gear
IV. Operating and Service Instructions
1. Rotorcraft Flight Manual, Document No:
Variants D, DS:
BO105 D and BO105 DS, 2nd Issue, firstly approved on 01.09.1982, and subsequent
revisions
Variants DB, DB-4, DBS, DBS-4:
BO105 DB/DBS, 3rd Issue, firstly approved on 10.02.1995 (by CAA-UK), and
subsequent revisions.
Variants DBS-5:
BO105 DBS-5, 1st Issue, firstly approved on 22.11.1994 (by CAA-UK), and subsequent
revisions.
2. Maintenance Manual, Document No:
a.
b.
c.
d.
e.
Maintenance and Manual BO105, issued on 13.10.1970. Plus Chapter 8+9 of MOM D
Repair Manual BO105
Illustrated Parts Catalogue BO105
Wiring Diagram Manual BO105
Engine documents as per LBA Engine TCDS No. 7007
3. Service Letters and Service Bulletins:
safety information notice (from October 2008 onwards, before: Alert Service
Information), information notice (from October 2008 onwards, before: Service
Information), Alert Service Bulletin, Service Bulletin
4. Required Equipment:
Special equipment and kits necessary for intended kind of operations as defined in the
approved Flight Manual are required.
V. Notes
1. Eligible serial numbers:
S/N 01 to 929 (except S/N for the BO105 A and BO105 LS A-1)
2. Applicability:
The serial numbers of rotorcraft delivered firstly for civil registration are listed in the ECD
document No: ECD-TN-ETYAC-001/2006.
TCDS R.011
Issue 01, 10 July 2009
Page 24 of 24
BO105 D
3. Record of Type Certificate Holder:
The Type Certificate was originally issued to Messerschmitt-Bölkow-Blohm GmbH,
Postfach 801140, 8000 München 80.
4. Record of Manufacturer:
Company name until December 1991: Messerschmitt-Bölkow-Blohm GmbH,
Unternehmensbereich Drehflügler und Verkehr bzw. Unternehmensgruppe
Hubschrauber und Flugzeuge, Postfach 1350, W-8850 Donauwörth 80. Until May 1992
the manufacturer name was Eurocopter Hubschrauber GmbH, Postfach 1353, W-8850
Donauwörth. From May 1992 the manufacturer name has been changed to: Eurocopter
Deutschland GmbH, Postfach 1353, W-8850 Donauwörth or 86603 Donauwörth or
86607 Donauwörth.
5. Data Plate:
The helicopter model/variant designation provided on the helicopter data plate under
‘Code’ or ‘Model’ or ‘Baumuster’, as applicable, refers to the model/variant as listed in
this TCDS.