# TCDS T00008NY: Airbus Canada Limited Partnership

- Type: Type certificate data sheet
- Status: Current
- Holder: Airbus Canada Limited Partnership
- Revision: 16
- Revised: September 9, 2026
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 231, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/7c/a0/7ca0c31c12864812a73c0e7b14233b57794ffe92250ad6622a83b1219eb2b88d
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID196169429020260910140014.0001
- Page: https://openairdocs.org/tcds/T00008NY

## Models (2)

As the data sheet lists them.

- BD-500-1A10
- BD-500-1A11

## What the data sheet says

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

```text
Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15      
Rev. No. 15
16 
13 14 14 13 9 13 8 4 1 10 14 8 
15
16 
14
15 
15      
Page No.                     
Rev. No.                     
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
T00008NY 
Revision No. 16 
                           Airbus Canada Limited Partnership 
                                                         BD-500-1A10 
BD-500-1A11  
September 9, 2026 
    
 
TYPE CERTIFICATE DATA SHEET NO. T00008NY 
 
This data sheet, which is part of Type Certificate No. T00008NY, prescribes conditions and limitations under which 
the product for which the Type Certificate was issued meets the airworthiness requireme nts of the Federal Aviation 
Regulations. 
 
Type Certificate Holder:   Airbus Canada Limited Partnership 
   13100 Henri-Fabre Blvd. 
   Mirabel, Quebec, Canada   
   J7N 3C6 
 
Type Certificate Holder Record: C Series Aircraft Limited Partnership (CSALP) 
   13100 Henri-Fabre Blvd. 
   Montreal, Quebec, Canada   
   J7N 3C6 
 
   Bombardier, Inc. 
   800 Boul. Rene-Levesque Ouest 
   Montreal, Quebec, Canada   
   H3B 1Y8 
 
I - Model BD-500-1A10 (Transport Category), Approved June 15, 2016, by the FAA and December 17, 2015, by 
Transport Canada Civil Aviation type certificate number A-236. 
 
Engines Two Pratt & Whitney PW1519G (Engine Type Certificate No. E00090EN)  
Two Pratt & Whitney PW1521G (Engine Type Certificate No. E00090EN)  
Two Pratt & Whitney PW1521GA (Engine Type Certificate No. E00090EN)  
Two Pratt & Whitney PW1524G (Engine Type Certificate No. E00090EN) 
 
Fuel 
 
 
 
For approved fuel grades, fuel additives, fuel temperature limitations and fuel quantity gauging 
inaccuracy, see applicable AFM as listed in SERVICE INFORMATION – Approved Publications – of 
this TCDS. 
  
Oil 
 
 
Approved engine oils*: 
BP Turbine Oil 2380, Royco/Aeroshell Turbine Oil 500, Royco 500, Mobil Jet Oil II, BP Turbo 
Oil 2197, Royco/Aeroshell Turbine Oil 560, Mobil Jet Oil 254 
*Or additional approved oils as listed in the applicable Aircraft Maintenance Publication (AMP) 
BD500-3AB48-10200-00. 
 
Maximum Engine Oil Volume:  24.4 liters = 25.8 qts 
Minimum Engine Oil Volume:         8.23 liters = 8.7 qts 
 
Maximum APU Oil Volume:  7.32 liters = 7.74 qts 
Minimum APU Oil Volume:  2.59 liters = 2.74 qts

T00008NY Page 2 of 14 
 
  
 
Engine  
Operating Limits Operating Conditions Operating limits 
Thrust Setting Time Limit  Max EGT 
Oil Pressure 
min/max Oil temp[4] N1/N2 
  (minutes) °C (°F) PSIG[2]  °C (°F)   
Max Takeoff 5[1] 
 1054°C 
(1929°F) 50.3 /175.3 
49°C to 
163°C [3]  
(120°F to 
325°F) 100% 
Max 
Continuous[5] Continuous 
 1006°C[5] 
(1842°F) 
 1016°C[6] 
(1861°F) 50.3 /175.3 
49°C to 
163°C [3]  
(120°F to 
325°F) 100% 
Reverse Thrust As Required 
1054°C 
(1929°F) 50.3 /175.3 
49°C to 
163°C [3]  
(120°F to 
325°F) 100% 
Ground idle 
(SLS) Continuous - 50.3 /175.3 
−40°C to 
163°C 
(−40°F to 
325°F) 100% 
Flight Idle Continuous - 50.3 /175.3 
−40°C to 
163°C 
(−40°F to 
325°F) 100% 
Starting - 
1054°C 
(1929°F) - 
−40°C to 
163°C 
(−40°F to 
325°F) 100% 
[1] Time limit may be extended to 10 minutes for One Engine Inoperative 
(OEI) contingency. 
[2] Minimum oil pressure is a function of N2 where the minimum oil pressure  
ranges from 50.3 psig to 97.0 psig. 
[3] Minimum oil temperature for takeoff is 49°C (120°F). 
[4] Maximum oil temperature of 174°C (345°F) for up to 20 minutes. Total 
operation between 163°C (325°F) up to 174°C (345°F) must not exceed  20 minutes. 
[5] Pre-Service Bulletin (SB BD500-732003) 
[6] Post-Service Bulletin (SB BD500-732003) or Mod 500T102160 
 
C.G. Limits See the applicable AFM as listed in SERVICE INFORMATION – Approved Publications - of 
this TCDS. 
 
 
Outside Air 
Temperature 
Limits 
Maximum ambient temperature approved for takeoff and landing is 52.5°C  
(126.5°F). 
Minimum ambient temperature approved for takeoff is −54°C (−65°F). 
Minimum ambient temperature approved for landing is −30°C (−22°F). 
 
 
Maximum Weight  kg lb 
Maximum Ramp Weight (MRW) 64,183 141,500 
Maximum Takeoff Weight (MTOW) 63,730 140,500 
Maximum Landing Weight (MLW) 54,658 120,500 
Maximum Zero Fuel Weight (MZFW) 52,617 116,000 
For additional approved weights, see the applicable AFM as listed in the SERVICE INFORMATION – 
Approved Publications – of this TCDS.

Page 3 of 14 T00008NY 
 
 
Cargo  Max. Loading 
kg lb 
Fwd Cargo Compartment 1697 3742 
Aft Cargo Compartment 2063 4548 
  
 
Airspeed 
Limits (IAS) 
 knots Mach 
VMO and MMO - - 
Sea Level to 2,438 m. (8,000 ft.) 300 - 
3,048 m. (10,000 ft.) to 8,382 m. (27,500 ft.) 330 - 
Above 8,382 m. (27,500 ft.) - 0.82 
For additional approved speeds, see the applicable AFM as listed in the SERVICE  
INFORMATION – Approved Publications – of this TCDS. 
 
    
APU Honeywell 131-9(C) 
For operating limits, see the applicable AFM as listed in the SERVICE INFORMATION – 
Approved Publications – of this TCDS. 
 
 
Reference Datum FS 0.0 is located 640 cm. (252.0 in.) forward of the aircraft nose. 
 
Leveling Means Aircraft is leveled in the longitudinal and lateral axis by means of a plumb bob and target plate in 
the rear fuselage/aft equipment bay at FS 1390.83. 
 
Minimum Flight 
Crew 
2 (Pilot and Co-Pilot) 
 
Maximum 
Occupants 
133 (including 1 Pilot, 1 Co-pilot, 1 Observer, a minimum of 3 Cabin Crew* and a maximum of 
127 Passengers*). See Note 3. 
 
* Maximum 130 cabin occupants when fitted with an approved interior. 
 
3 occupants (1 Pilot, 1 Co-pilot and 1 Observer located in the cockpit) with no Cabin Crew or 
passengers when configured with the Basic Airbus Corporate Jet (ACJ) modifications in 
accordance with RAL-BA500-0005 Rev. - or later approved revisions, unless fitted with an 
approved interior. 
 
 
Flight Load 
Factor 
Flaps up:  -1.0 g to 2.5 g 
Flaps down:  0.0 g to 2.0 g 
 
 
Fuel Capacity See the applicable AFM as listed in the SERVICE  
INFORMATION – Approved Publications – of this TCDS. 
 
 
 
 
Maximum 
Operating Altitude 
Take-off and Landing: 
Enroute: 
3,048 m. (10,000 ft.) 
12,497 m. (41,000 ft.) 
 
Serial Numbers 
Eligible 
50001 to 54999, inclusive. 
 
 
SERVICE Service Bulletins, structural repair manuals, vendor manuals, overhaul and maintenance

T00008NY Page 4 of 14 
 
INFORMATION manuals, and aircraft flight manuals which contain a statement that the document is 
Transport Canada approved or Transport Canada approved through the Manufacturers 
Design Approval Representative are accepted by the FAA and are considered FAA 
approved.  (These approvals pertain to the design data only). 
 
Approved 
Publications 
a) Airplane Flight Manual (AFM), BD500-3AB48-22200-00, Issue 009 or later 
approved revisions.  
 
b)  Maintenance Review Board Report (MRBR), BD500-3AB48-11400-01, Issue 001 or 
later approved revisions. 
 
c)  Aircraft Structural Repair Publication (ASRP), BD500-3AB48-10600-00 Issue 001 or 
later approved revisions. 
  
d) Airworthiness Limitations (AWL), BD500-3AB48-11400-02, Issue 002 or later 
approved revisions. 
 
e)  ETOPS Configuration, Maintenance and Procedures (CMP), BD500-3AB48-11200-
00, Issue 004 or later approved revisions. 
 
Required 
Equipment 
a) The basic required equipment is prescribed in the applicable airworthiness 
requirements (See Certification Basis) must be installed in the aircraft.  
b) Airplane Flight Manual as listed in the SERVICE INFORMATION – Approved 
Publications – of this TCDS. 
 
Type Certification 
Configuration 
Type design definition approved by this TCDS for the BD-500-1A10 is defined in RAZ-BA500-
027 at Rev. H or later approved revisions. 
 
The approved type design appropriate to the “as delivered” configuration of a particular BD -500-
1A10 aircraft is defined in RAZ-BA500-027 Rev. H or later approved revisions, and RAL-
BA500-XXXXX (production sequence number, where XXXXX denotes the aircraft serial 
number). 
 
For particular BD-500-1A10 aircraft configured with the Basic Airbus Corporate Jet (ACJ) 
modifications in accordance with RAL-BA500-0005 Rev. - or later approved revisions, the 
approved type design appropriate to the “as delivered” configuration is defined in RAZ-BA500-
027 Rev. M or later approved revisions, and RAL-BA500-XXXXX (production sequence 
number, where XXXXX denotes the aircraft serial number). 
 
Import 
Requirements 
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.  
 
A U.S. Airworthiness Certificate may be issued on the basis of the Canadian Department of 
Transport "Certificate of Airworthiness for Export" signed by the Minister of Transport. This 
form must contain the following statement (in the english language): "This certifies tha t the 
aircraft described below has been manufactured in conformity with data forming the basis for the 
Transport Canada Type Certificate No. A-236 and includes the minimum type design defined in 
document RAZ-BA500-027 Issue H or subsequent approved revisions as being required to 
comply with the basis for the U.S. Type Certificate No. T00008NY, and is in a condition for safe 
operation”. 
 
 
Production Basis The BD-500-1A10, Serial Number 50011 and subsequent, are produced in Canada under C Series 
Aircraft Limited Partnership (CSALP), Manufacturing Certificate No. 24-16.  See Note No. 5 and

Page 5 of 14 T00008NY 
 
Note No. 8. 
 
 
 
II - Model BD-500-1A11 (Transport Category), Approved December 13, 2016, by the FAA and July 8, 2016, by Transport 
Canada Civil Aviation type certificate number A-236. 
 
Engines Two Pratt & Whitney PW1524G-3 (Engine Type Certificate No. E00090EN) 
Two Pratt & Whitney PW1521G-3 (Engine Type Certificate No. E00090EN) 
 
Fuel 
 
For approved fuel grades, fuel additives, fuel temperature limitations and fuel quantity g auging 
inaccuracy, see applicable AFM as listed in SERVICE INFORMATION – Approved Publications – of 
this TCDS. 
 
Oil Approved engine oils*: 
BP Turbine Oil 2380, Royco/Aeroshell Turbine Oil 500, Royco 500, Mobil Jet Oil II, BP Turbo 
Oil 2197, Royco/Aeroshell Turbine Oil 560, Mobil Jet Oil 254 
*Or additional approved oils as listed in the applicable Aircraft Maintenance Publication (AMP) 
BD500-3AB48-10200-00. 
 
Maximum Engine Oil Volume:  24.4 liters = 25.8 qts 
Minimum Engine Oil Volume:         8.23 liters = 8.7 qts 
 
Maximum APU Oil Volume:  7.32 liters = 7.74 qts 
Minimum APU Oil Volume:  2.59 liters = 2.74 qts

T00008NY Page 6 of 14 
 
Engine  
Operating Limits Operating Conditions Operating limits 
Thrust Setting Time Limit  Max EGT 
Oil Pressure 
min/max Oil temp[4] N1/N2 
  (minutes) °C (°F) PSIG[2]  °C (°F)   
Max Takeoff 5[1] 
 1054°C 
(1929°F) 50.3 /175.3 
49°C to 
163°C [3]  
(120°F to 
325°F) 100% 
Max Continuous Continuous 
 1006°C[5] 
(1842°F) 
 1016°C[6] 
(1861°F) 50.3 /175.3 
49°C to 
163°C [3]  
(120°F to 
325°F) 100% 
Reverse Thrust As Required 
1054°C 
(1929°F) 50.3 /175.3 
49°C to 
163°C [3]  
(120°F to 
325°F) 100% 
Ground idle 
(SLS) Continuous - 50.3 /175.3 
−40°C to 
163°C 
(−40°F to 
325°F) 100% 
Flight Idle Continuous - 50.3 /175.3 
−40°C to 
163°C 
(−40°F to 
325°F) 100% 
Starting - 
1054°C 
(1929°F) - 
−40°C to 
163°C 
(−40°F to 
325°F) 100% 
[1] Time limit may be extended to 10 minutes for One Engine Inoperative 
(OEI) contingency. 
[2] Minimum oil pressure is a function of N2 where the minimum oil pressure  
ranges from 50.3 psig to 97.0 psig. 
[3] Minimum oil temperature for takeoff is 49°C (120°F). 
[4] Maximum oil temperature of 174°C (345°F) for up to 20 minutes. Total  
operation between 163°C (325°F) up to 174°C (345°F) must not exceed  20 minutes. 
[5] Pre-Service Bulletin (SB BD500-732003) 
[6] Post-Service Bulletin (SB BD500-732003) or Mod 500T102160 
 
C.G. Limits See the applicable AFM as listed in SERVICE INFORMATION – Approved Publications - of 
this TCDS. 
 
 
 
Outside Air 
Temperature 
Limits 
Maximum ambient temperature approved for takeoff and landing is 52.5°C  
(126.5°F). 
Minimum ambient temperature approved for takeoff is −54°C (−65°F). 
Minimum ambient temperature approved for landing is −54°C (−65°F). 
 
 
Maximum Weight  kg lb 
Maximum Ramp Weight (MRW) 71,214 157,000 
Maximum Takeoff Weight (MTOW) 70,896 156,300 
Maximum Landing Weight (MLW) 58,740 129,500 
Maximum Zero Fuel Weight (MZFW) 55,792 123,000 
For additional approved weights, see the applicable AFM as listed in the SERVICE INFORMATION – 
Approved Publications – of this TCDS.

Page 7 of 14 T00008NY 
 
Cargo  Max. Loading 
kg lb 
Fwd Cargo Compartment 2446 5393 
Aft Cargo Compartment 2606 5746 
  
 
Airspeed Limits 
(IAS) 
 knots Mach 
VMO and MMO - - 
Sea Level to 2,438 m. (8,000 ft.) 300 - 
3,048 m. (10,000 ft.) to 8,382 m. (27,500 ft.) 330 - 
Above 8,382 m. (27,500 ft.) - 0.82 
For additional approved speeds, see the applicable AFM as listed in the SERVICE INFORMATION – 
Approved Publications – of this TCDS. 
 
APU Honeywell 131-9(C) 
For operating limits, see the applicable AFM as listed in the SERVICE INFORMATION – 
Approved Publications – of this TCDS. 
 
 
Reference Datum FS 0.0 is located 427 cm. (168.0 in.) forward of the aircraft nose. 
 
Leveling Means Aircraft is leveled in the longitudinal and lateral axis by means of a plumb bob and target plate in 
the rear fuselage/aft equipment bay at FS 1453.83. 
 
Minimum Flight 
Crew 
2 (Pilot and Co-Pilot) 
 
Maximum 
Occupants 
153 (including 1 Pilot, 1 Co-pilot, 1 Observer, a minimum of 3 Cabin Crew* and a maximum of 
145 Passengers*). See Note 3. 
 
* Maximum 150 cabin occupants when fitted with an approved interior. 
 
 
Flight Load 
Factor 
Flaps up:  -1.0 g to 2.5 g 
Flaps down:  0.0 g to 2.0 g 
 
Fuel Capacity See the applicable AFM as listed in the SERVICE  
INFORMATION – Approved Publications – of this TCDS. 
 
 
 
Maximum 
Operating Altitude 
Take-off and Landing: 
Enroute: 
3,048 m. (10,000 ft.) 
12,497 m. (41,000 ft.) 
 
 
Serial Numbers 
Eligible 
55001 to 59999, inclusive. 
 
 
SERVICE 
INFORMATION 
Service Bulletins, structural repair manuals, vendor manuals, overhaul and maintenance 
manuals, and aircraft flight manuals which contain a statement that the document is 
Transport Canada approved or Transport Canada approved through the Manufacturers 
Design Approval Representative are accepted by the FAA and are considered FAA 
approved.  (These approvals pertain to the design data only). 
 
 
Approved 
Publications 
a) Airplane Flight Manual (AFM), BD500-3AB48-32200-00, Issue 009 or later 
approved revisions.

T00008NY Page 8 of 14 
 
 
b)  Maintenance Review Board Report (MRBR), BD500-3AB48-11400-01, Issue 001 or 
later approved revisions. 
 
c)  Aircraft Structural Repair Publication (ASRP), BD500-3AB48-10600-00 Issue 001 or 
later approved revisions. 
  
d) Airworthiness Limitations (AWL), BD500-3AB48-11400-02, Issue 003 or later 
approved revisions. 
 
e)  ETOPS Configuration, Maintenance and Procedures (CMP), BD500-3AB48-11200-
00, Issue 004 or later approved revisions. 
 
Required 
Equipment 
a) The basic required equipment is prescribed in the applicable airworthiness 
requirements (See Certification Basis) must be installed in the aircraft.  
b) Airplane Flight Manual as listed in SERVICE INFORMATION – Approved 
Publications – of this TCDS. 
 
Type Certification 
Configuration 
Type design definition approved by this TCDS for the BD-500-1A11 is defined in RAZ-BA503-
027 at Rev. D or later approved revisions. 
 
The approved type design appropriate to the “as delivered” configuration of a particular BD-500-
1A11 aircraft is defined in RAZ-BA503-027 Rev. D or later approved revisions, and RAL-
BA503-XXXXX (production sequence number, where XXXXX denotes the aircraft serial 
number). 
 
Import 
Requirements 
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. 
 
A U.S. Airworthiness Certificate may be issued on the basis of the Canadian Department of 
Transport "Certificate of Airworthiness for Export" signed by the Minister of Transport. This 
form must contain the following statement (in the english language): "This certifies that the 
aircraft described below has been manufactured in conformity with data forming the basis for the 
Transport Canada Type Certificate No. A-236 and includes the minimum type design defined in 
document RAZ-BA503-027 at Rev. D or subsequent approved revisions as being required to 
comply with the basis for the U.S. Type Certificate No. T00008NY, and is in a condition for safe 
operation”. 
 
Production Basis The BD-500-1A11, Serial Number 55003 and subsequent, are produced in Canada under C Series 
Aircraft Limited Partnership (CSALP), Manufacturing Certificate No. 24-16.  See Note No. 5 and 
Note No. 8.  
 
 
DATA PERTINENT TO ALL MODELS EXCEPT AS INDICATED 
 
Certification Basis 1. Airworthiness Standards: 
 
Federal Aviation Administration (FAA), Title 14, Code of Federal Reg ulations (14 CFR) Part 
25, effective February 1, 1965, including Amendements 25-1 through 25-134.  
 
2. Special Conditions are as follow:

Page 9 of 14 T00008NY 
 
Certification Basis 
(Cont’d) Special Condition No. Title 
 25-477-SC Limit Pilot Forces for Sidestick Controllers 
 25-499-SC Interactions of Systems and Structures 
 25-500-SC Design Roll Maneuver Condition 
 25-512-SC Seats With Non-Traditional, Large, Non-Metallic Panels 
 
25-513-SC 
Side Stick Controllers: Pilot Strength, Pilot Control Authority, 
and Pilot Control 
 25-515-SC Autobraking System Loads 
 25-518-SC Fuselage Post-Crash Fire Survivability 
 25-519-SC Fuselage In-Flight Fire Safety and Flammability Resistance 
 
25-544-SC 
Composite Wing and Fuel Tank Structure Post-Crash Fire 
Survivability 
 
25-546-SC 
Electronic Flight Control System: Control Surface Awareness 
and Mode Annunciation 
 25-547-SC Flight Envelope Protection: Normal Load Factor (g) Limiting 
 25-548-SC Flight Envelope Protection: General Limiting Requirements 
 25-549-SC Flight Envelope Protection: High-Speed Limiting 
 25-555-SC Limit Engine Torque Loads 
 25-560-SC Tire Failure – Tire Debris Impacts to Fuel Tanks 
 25-565-SC Automatic Speed Protection for Design Dive Speed 
 
25-566-SC 
Isolation or Airplane Electronic System Security Protection 
From Unauthorized Internal Access 
 
25-567-SC 
Airplane Electronic System Security Protection From 
Unauthorized External Access 
 
25-576-SC 
Electronic Flight-Control System (EFCS): Pitch-and Roll- 
Limiting Functions 
 
25-578-SC 
Alternate Fuel Tank Structural Lightning Protection 
Requirements 
 25-583-SC Operation Without Normal Electrical Power 
 
25-584-SC 
Electronic Flight Control System: Lateral-Directional and 
Longitudinal Stability and Low-Energy Awareness 
 25-591-SC Installed Rechargeable Lithium Batteries and Battery Systems 
 25-597-SC Flight-Envelope Protection, High Incidence Protection Function 
 25-657-SC Non-Rechargeable Lithium Batteries 
 25-731-SC Seats with Inflatable Lap Belt System (Note 6)

T00008NY Page 10 of 14 
 
DATA PERTINENT TO ALL MODELS EXCEPT AS INDICATED) (CONT’D) 
 
 3. Equivalent Safety Findings: 
 
Certification 
Basis (Cont’d) 
 
ELOS Memo Requirement Title 
 
 
TC4948NY-T-ES-
19 25.856(b) 
Penetrations in Fire Barrier of Cargo Compartment and WTBF 
 
TC4948NY-T-ES-
20 25.1441(c) Oxygen Quantity Indication 
  25.721 
Emergency Landing Conditions  TC4948NY-T-A-25 25.963(d) 
  25.994 
 
 
TC4948NY-T-ES-
18 25.1443(c)  
Minimum Mass Flow of Supplemental Oxygen 
   
Lack of On/Off Switch for ATTCS System 
   
   
  25.904 
 
TC4948NY-T-P-06 Part 25 
Appendix I 
   
   
   
  25.811(g) 
Symbolic Exit Signs 
 
TC4948NY-T-CS-
10 25.812(b)(1) 
 
 
TC4948NY-T-ES-
16 
25.856(b) Burn Through Protection at Aft Pressure Bulkhead 
   Engine Ignition Switches 
 TC4948NY-T-P-41 25.1145(a) 
 TC4948NY-T-P-16 25.1193(e)(3) Engine and APU Fire Protection 
   
Flight Critical Thrust Reverser  TC4948NY-T-P-20 25.933(a)(1) 
   
 
TC4948NY-T-ES-
17 25.813(c)(1)(i) Type III Exit Passageway Width 
 
TC4948NY-T-P-15 25.1549 (a) to 
(c) Digital Only Display of the Turbine Engine Required Parameters 
 
TC4948NY-T-P-08 
14CFR part 25 
subpart E, F, 
and G, APU Certification Requirements 
  25.1103(e)(1) 
  25.1105 
  25.1305 
 
 
 
TC4948NY-T-ES-
25.831(g) 
Finding FOR Ventilation System Failures - Cabin Temperature 
and Humidity

Page 11 of 14 T00008NY 
 
Certification 
Basis (Cont’d) 
 
ELOS Memo Requirement Title 
17 
  25.1301 ARAC Recommendation Revision 
 TC4948NY-T-S-13 25.1309 
   
Flight Control System Failure Criteria  TC4948NY-T-S-3 25.671 
   
  25.904 
Performance Credit for use of Automatic Power Reserve (APR) 
During Reduced Thrust Takeoffs(Automatic Takeoff Thrust 
Control System (ATTCS) 
   
 
TC4948NY-T-P-7 Part 25 
Appendix I 
   
   
 TC4948NY-T-F-28 25.161(c )(1) Longitudinal Trim  
 TC4948NY-T-EE-9 
25.1535 
Part 25 
Appendix K 
K25.2.2(d)  
Extended Operations (ETOPS) Propulsion System Validation Test 
 AT09445NY-T-ES-21 25.841(a) 25.841(b)(6) High Altitude Airport Operations

T00008NY Page 12 of 14 
 
DATA PERTINENT TO ALL MODELS EXCEPT AS INDICATED) (CONT’D) 
 
Certification Basis 
(Cont’d) 
4. Exemptions from 14 CFR Part 25 are as follows: 
 
Exemption No. 10944 dated February 2, 2015, High Altitude Decompression caused by a 
failure of one of the engines, 14 CFR 25.841(a)(2)(i) and (ii); 
 
Exemption No. 10840 dated August 8, 2013, Emergency Exit Viewing Means, 14 CFR 
25.809(a); 
 
Time Limited Exemption No.16779 dated June 10, 2016, Fuel Tank Ignition Prevention, 14 
CFR 25.981(a)(3) See Note 7; 
 
Time Limited Exemption No.16779A dated July 15, 2019, Fuel Tank Ignition Prevention, 
14 CFR 25.981(a)(3);  
 
Time Limited Exemption No. 16779B dated December 13, 2024, Fuel Tank Ignition 
Prevention 14 CFR 25.901 (c) and 25.981(a)(3) See Note 7. 
 
Exemption No. 16780 dated June 10, 2016, Throttle Quadrant Assembly, 14 CFR 25.901(c) 
See Note 4. 
 
5. Optional Design Regulations: 
 
a) Ditching §§ 25.801, 25.1411 and 25.1415* 
b) Ice Protection 25.1419 
c) Automatic Takeoff Thrust Control System (ATTCS) 25.904 and Appendix I to Part 25 
d) Extended Operations (ETOPS) approval 25.1535. See Note 1. 
 
*The BD-500-1A10 Model configured with the Basic Airbus Corporate Jet (ACJ) 
modifications as defined in RAL-BA500-0005 Rev. - or later approved revisions, is not 
approved for ditching, unless fitted with the required ditching equipment. 
 
6. 14 CFR Part 26: 
December 10, 2007 including Amendments 26-1 through 26-6. See Note 10. 
 
7. 14 CFR Part 36: 
BD-500-1A10 
Effective December 1, 1969, and including all amendments through Amendme nt 36-31. 
BD-500-1A11 
Effective December 1, 1969, and including all amendments through Amendment 36 -29.   
 
8. 14 CFR Part 34: 
Effective September 10, 1990, and including all amendments through Amendment 34 -5A, 
in effect on the date of type certification. 
 
9. A finding of regulatory adequacy pursuant to the “Noise Control Act of 1972” (49 
USC Section 44715). 
 
10.   Aircraft equipped with the Installed Physical Secondary Barrier (IPSB) complies with  
         14 CFR 25.795(a)(4), Amendment 25-150. 
 
Placards 
 
 
 
 
 
BD-500-1A10: 
All placards must be installed in accordance with Bombardier drawings: C04471003 Rev. D, 
C04473003 Rev. C, C04475003 Rev. A, C04477003 Rev. D, and C05200003 Rev. A.  
 
Drawings noted above are for basic type certification only.  For “as-delivered” aircraft 
configurations, refer to RAL-BA500-XXXXX (XXXXX denotes aircraft serial number).

Page 13 of 14 T00008NY 
 
 
 
 
 
 
Placards (Cont’d) 
 
BD-500-1A11: 
All placards must be installed in accordance with Bombardier drawings : C04471302 Rev. A, 
C04473302 Rev. B, C04475302 Rev. B, C04477302 Rev. B, and C05200008 Rev. A. 
 
Drawings noted above are for basic type certification only.  For “as-delivered” aircraft 
configurations, refer to RAL-BA503-XXXXX (XXXXX denotes aircraft serial number). 
 
Application Date 
 
Initial Date February 25, 2010 
Deferred Date December 31, 2011 
  
 
NOTE  1 The type-design reliability and performance of the Models BD-500-1A10 and BD-500-1A11 have 
been evaluated under 14 CFR §25.1535 and found suitable for up to and including 180 minutes 
extended operations (ETOPS) when the configuration, maintenance, and procedures standards 
contained in Airbus Canada Document BD500-3AB48-11200-00, Issue 004 "ETOPS 
CONFIGURATION, MAINTENANCE AND PROCEDURES (CMP)" are met. This finding does 
not constitute operational approval to conduct ETOPS. 
 
NOTE  2 The A220-100 (previously known as the CS100) is a marketing designation of the CSALP aircraft 
model BD-500-1A10. 
The A220-300 (previously known as the CS300) is a marketing designation of the CSALP aircraft 
model BD-500-1A11. 
 
NOTE  3 
 
 
 
 
 
 
 
NOTE  4 
 
 
 
 
 
 
 
 
 
Other Operating Limitations: 
a) Removed. 
b) Removed. 
c) Removed. 
The FAA has concluded that the occurrence of any uncontrollable high -thrust failure 
condition, or any of the associated causal failures listed within Bombardier Aerospace 
Document Aircraft Maintenance Publication (AMP) BD500-3AB48-10200-00 Section 
BD500-A-J05-51-00-01AAA-096A-A, may endanger the safe operation of an airplane.  
Consequently, the FAA recommends that operators be encouraged to report any such 
failures in accordance with Title 14, Code of Federal Regulations 121.703(c), 125.409(c), 
and 135.415(c). 
NOTE  5 
 
NOTE  6 
 
NOTE  7 
 
 
 
 
 
NOTE  8  
 
 
 
 
 
Removed. 
 
Applicable to CSALP aircraft model BD-500-1A10. 
 
Since the grant of time-limited exemption (Exemption No. 16779) was issued, the FAA has found that 
the BD-500-1A10 and BD-500-1A11 fuel pump installation design complies with the requirements of 
14 CFR 25.901(c) and 25.981(a)(3) without the incorporation of GFI. The conditions in Exemption  
No. 16779 relating to the incorporation of a GFI are no longer relevant and have been replaced by 
conditions in Exemption No. 16779B. 
 
Airbus Canada Limited Partnership, Manufacturing Certificate No. 24-16, is authorized by Transport 
Canada to use the facility located at 320 Airbus Way, Mobile, Alabama, 36615, (USA) to manufacture 
and obtain Airworthiness Certificates for aircraft models in this Type Certificate Data Sheet.

T00008NY Page 14 of 14 
 
 
 
 
NOTE  9 
 
 
 
 
RAZ-BA500-027 Appendix A, Revision M or later revisions, provides guidance  to completion 
centers when installing an interior regarding compliance with the certification basis for the BD500-
1A10 (A220-100) configured with the Basic ACJ modifications in accordance with RAL-BA500-
0005 Rev. - or later approved revisions. This guidance notes general applicable conditions, or 
considerations regarding: 
• How compliance has been demonstrated for the Basic ACJ aircraft. 
• If compliance with some requirement(s) is partial for the Basic ACJ aircraft with the 
remainder to be addressed by the completion center. 
• Specific items for which compliance must be addressed by the completion center (N/A to the 
Basic ACJ aircraft). 
 
The guidance in Appendix A should not be understood as an exhaustive list of  all the certification 
requirements to be addressed by the completion center during the process of obtaining a cabin 
completion Supplemental Type Certificate. 
 
RAZ-BA500-027 Appendix B, Revision M or later revisions also includes references to installation, 
interface data with associated limitations, and relevant data to support completion centers’ 
understanding of the scope of the compliance activities. 
 
 
NOTE  10                        EWIS requirement 14 CFR Part 26 Subpart B, “Enhanced Airworthiness Program for   
                                         Airplane systems (EAPAS)” is not applicable due to the Certification Basis of the Model 
                                         BD-500-1A10 and BD-500-1A11 including 14 CFR Part 25 Amendment Number 25-1 
                                        Through 25-134, which include Subpart H- Electrical Wiring Interconnection Systems  
                                        (EWIS), requirements section 25.1701 to 25.1733, introduced at Amendment Number  
             25-123, Effective date December 10, 2007, which satisfies part 26.1(c).                           
– END –
```

## ADs (82, first 50, in force first)

- [AD 2026-15-14](https://openairdocs.org/ad/2026-15-14): Engine fuel and control · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Sep 3, 2026
- [AD 2026-13-52](https://openairdocs.org/ad/2026-13-52): Pneumatic · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jul 7, 2026
- [AD 2026-10-07](https://openairdocs.org/ad/2026-10-07): Wings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jul 1, 2026
- [AD 2026-10-10](https://openairdocs.org/ad/2026-10-10): Equipment/furnishings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jul 1, 2026
- [AD 2026-10-12](https://openairdocs.org/ad/2026-10-12): Fuel · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jul 1, 2026
- [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026
- [AD 2026-07-04](https://openairdocs.org/ad/2026-07-04): Equipment/Furnishings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective May 11, 2026
- [AD 2026-06-06](https://openairdocs.org/ad/2026-06-06): Electrical system installation · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective May 1, 2026
- [AD 2026-07-07](https://openairdocs.org/ad/2026-07-07): Air conditioning system · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Apr 17, 2026
- [AD 2026-04-04](https://openairdocs.org/ad/2026-04-04): Fuel · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Apr 8, 2026
- [AD 2025-20-08](https://openairdocs.org/ad/2025-20-08): Fire protection · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Dec 30, 2025
- [AD 2025-19-07](https://openairdocs.org/ad/2025-19-07): Electrical system installation · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Nov 6, 2025
- [AD 2025-19-01](https://openairdocs.org/ad/2025-19-01): Autoflight · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Oct 23, 2025
- [AD 2025-17-01](https://openairdocs.org/ad/2025-17-01): Flight controls · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Sep 29, 2025
- [AD 2025-16-01](https://openairdocs.org/ad/2025-16-01): Fuel · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Sep 18, 2025
- [AD 2025-12-04](https://openairdocs.org/ad/2025-12-04): Hydraulic Power · Airbus Canada Limited Partnership BD-500-1A11. Effective Jul 25, 2025
- [AD 2025-09-02](https://openairdocs.org/ad/2025-09-02): Landing Gear · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jun 18, 2025
- [AD 2025-11-06](https://openairdocs.org/ad/2025-11-06): Standard practices/structures · Airbus Canada Limited Partnership BD-500-1A11. Effective Jun 16, 2025
- [AD 2025-07-04](https://openairdocs.org/ad/2025-07-04): Standard practices/structures · Airbus Canada Limited Partnership BD-500-1A11. Effective May 27, 2025
- [AD 2025-06-06](https://openairdocs.org/ad/2025-06-06): Fuselage · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective May 2, 2025
- [AD 2025-05-07](https://openairdocs.org/ad/2025-05-07): Standard practices/structures · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Apr 15, 2025
- [AD 2025-02-06](https://openairdocs.org/ad/2025-02-06): Fuselage · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Apr 9, 2025
- [AD 2025-03-05](https://openairdocs.org/ad/2025-03-05): Stabilizers · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Mar 21, 2025
- [AD 2024-24-08](https://openairdocs.org/ad/2024-24-08): Equipment/Furnishings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jan 13, 2025
- [AD 2024-23-05](https://openairdocs.org/ad/2024-23-05): Fuel · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jan 6, 2025
- [AD 2024-22-01](https://openairdocs.org/ad/2024-22-01): Time Limits/Maintenance Checks · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Dec 31, 2024
- [AD 2024-22-04](https://openairdocs.org/ad/2024-22-04): Fuselage · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Dec 17, 2024
- [AD 2024-22-03](https://openairdocs.org/ad/2024-22-03): Electrical Power · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Nov 14, 2024
- [AD 2024-15-06](https://openairdocs.org/ad/2024-15-06): Equipment/furnishings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Oct 15, 2024
- [AD 2024-17-04](https://openairdocs.org/ad/2024-17-04): Landing Gear · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Sep 20, 2024
- [AD 2024-12-02](https://openairdocs.org/ad/2024-12-02): Portable Oxygen System · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Aug 13, 2024
- [AD 2024-09-01](https://openairdocs.org/ad/2024-09-01): Equipment/Furnishings · Airbus Canada Limited Partnership BD-500-1A11. Effective Jul 2, 2024
- [AD 2024-10-11](https://openairdocs.org/ad/2024-10-11): Doors · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jul 1, 2024
- [AD 2024-10-03](https://openairdocs.org/ad/2024-10-03): Flight Controls · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jun 28, 2024
- [AD 2024-07-11](https://openairdocs.org/ad/2024-07-11): Equipment/furnishings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jun 6, 2024
- [AD 2024-05-08](https://openairdocs.org/ad/2024-05-08): Flight Controls · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective May 22, 2024
- [AD 2024-05-10](https://openairdocs.org/ad/2024-05-10): Electrical Power · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective May 22, 2024
- [AD 2024-04-08](https://openairdocs.org/ad/2024-04-08): Electrical power · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Apr 23, 2024
- [AD 2024-03-09](https://openairdocs.org/ad/2024-03-09): Equipment/furnishings · Airbus Canada Limited Partnership BD-500-1A11. Effective Apr 16, 2024
- [AD 2023-24-01](https://openairdocs.org/ad/2023-24-01): Fuel · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jan 2, 2024
- [AD 2023-20-01](https://openairdocs.org/ad/2023-20-01): Fire protection · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Nov 9, 2023
- [AD 2023-16-03](https://openairdocs.org/ad/2023-16-03): Pneumatic · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Sep 25, 2023
- [AD 2023-16-02](https://openairdocs.org/ad/2023-16-02): Fuel · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Sep 22, 2023
- [AD 2023-12-09](https://openairdocs.org/ad/2023-12-09): Flight control system · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Aug 7, 2023
- [AD 2023-14-02](https://openairdocs.org/ad/2023-14-02): Navigation · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jul 27, 2023
- [AD 2023-07-05](https://openairdocs.org/ad/2023-07-05): Equipment/furnishings · Airbus Canada Limited Partnership BD-500-1A10. Effective May 30, 2023
- [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023
- [AD 2023-07-01](https://openairdocs.org/ad/2023-07-01): Turbine/turboprop engine · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Apr 19, 2023
- [AD 2022-26-06](https://openairdocs.org/ad/2022-26-06): Placards and markings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Feb 2, 2023
- [AD 2022-25-05](https://openairdocs.org/ad/2022-25-05): Wings · Airbus Canada Limited Partnership BD-500-1A10 and BD-500-1A11. Effective Jan 23, 2023

All 82: https://openairdocs.org/tcds/T00008NY/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Airbus Canada LP BD-500-1A11](https://openairdocs.org/model/airbus-canada-lp-bd-500-1a11): 186 aircraft (registry code 1400015)
- [Airbus Canada Ltd Ptnrsp BD-500-1A10](https://openairdocs.org/model/airbus-canada-ltd-ptnrsp-bd-500-1a10): 31 aircraft (registry code 1400010)
- [C Series Aircraft Ltd Ptnrsp BD-500-1A10](https://openairdocs.org/model/c-series-aircraft-ltd-ptnrsp-bd-500-1a10): 14 aircraft (registry code 1400012)

## STCs approved under this data sheet (17)

- [STC ST04254NY](https://openairdocs.org/stc/ST04254NY): Installation of Viasat Satcom Software. ALOFT AeroArchitects
- [STC ST04818NY](https://openairdocs.org/stc/ST04818NY): Installation of a Passenger Seat Re-Pitch. ALOFT AeroArchitects
- [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF
- [STC ST02570LA](https://openairdocs.org/stc/ST02570LA): Interior Installations and Modifications. Safran Cabin Inc.
- [STC ST11389DS](https://openairdocs.org/stc/ST11389DS): Installation of Delta Comfort Passenger Seating Section. Aircraft Systems and Manufacturing Inc.
- [STC ST04803NY](https://openairdocs.org/stc/ST04803NY): Installation of a Panasonic Avionics In-Flight Entertainment System. Delta Engineering Coporation
- [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH
- [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH
- [STC ST04792NY](https://openairdocs.org/stc/ST04792NY): Update of Intelsat 2Ku. Delta Engineering Corporation
- [STC ST04562NY](https://openairdocs.org/stc/ST04562NY): Installation of saf-Tglo® SuperSeal UltraLite-X (SSUL-X) Photoluminescent Floor Proximity Emergency Escape Path Marking Systems. STG AEROSPACE GERMANY GmbH
- [STC ST03422NY](https://openairdocs.org/stc/ST03422NY): Update of Intelsat components. Delta Engineering Corporation
- [STC ST04483AT](https://openairdocs.org/stc/ST04483AT): Installation of the Avionics Support Group Constant Friction Mount (cfMount) with Cradle. Avionics Support Group Inc.
- [STC ST04425CH](https://openairdocs.org/stc/ST04425CH): Installation of a Honeywell One Aero Edge Node (1AEN) in accordance with StandardAero Master Data List 1037081, Revision (B), dated June 9, 2020 or later FAA approved revision.. StandardAero Business Aviation Services LLC
- [STC ST04424CH](https://openairdocs.org/stc/ST04424CH): TPED Compatibility Test in accordance with StandardAero Master Data List 1037140, Revision (B), dated June 1, 2020 or later FAA approved revision.. Standard Aero Business Aviation Services LLC
- [STC ST03972NY](https://openairdocs.org/stc/ST03972NY): Installation of Honeywell Satcom SBB Upgrade and WiFi Network Activation. UMLAUT ENGINEERING GMBH
- [STC ST04073NY](https://openairdocs.org/stc/ST04073NY): Installation of navAero Electronic Flight Bag provisions. Delta Engineering Corporation
- [STC ST00149IB](https://openairdocs.org/stc/ST00149IB) (historical): Installation of a Cabin air exhaust muffler, to reduce this noise to a more comfortable level by installing a valve cap and sound damping system. DOA21 LIMITED

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