TCDS T00008NY

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