TCDS T00003NY

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 Rev. No. 24 22 22 22 22 22 16 23 22 22 9 24 24 24 24 24 24 24 24 24 24 24 Page No. 23 24 25 Rev. No. 24 24 24 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00003NY Revision No. 24 Bombardier Inc. BD-700-1A10 BD-700-1A11 BD-700-2A12 December 19, 2025 TYPE CERTIFICATE DATA SHEET NO. T00003NY This data sheet which is part of Type Certificate No. T00003NY, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Bombardier Inc. 800 Boul. Re né-Leves que Ouest Montreal, Quebec, Canada H3B 1Y8 I - Model BD-700-1A10 (Transport Category), Approved November 13, 1998, by the FAA and July 31, 1998, by the Canadian Department of Transport (DOT). MAXIMUM lb kg WEIGHTS Max. Taxi and Ramp 93,750 95,250 (See NOTE 6) 96,250 (See NOTE 7) 98,250 (See NOTE 10) 99,750 (See NOTE 15) 42,525 43,205 (See NOTE 6) 43,659 (See NOTE 7) 44,565 (See NOTE 10) 45,246 (See NOTE 15) Max. Take-off 93,500 95,000 (See NOTE 6) 96,000 (See NOTE 7) 98,000 (See NOTE 10) 99,500 (See NOTE 15) 42,415 43,092 (See NOTE 6) 43,546 (See NOTE 7) 44,452 (See NOTE 10) 45,132 (See NOTE 15) Max. Landing 78,600 35,652 Max. Zero Fuel 58,000 26,308 Min. Flight Weight 48,200 21,865 FUEL CAPACITY Load Weight ** Usable U.S. Gal. Liters lb kg 2 Main Tanks (Each) 2,223 8,415 15,005 6,805 1 Center Tank 1,645 6,227 11,105 5,036 1 Aft Tank 337 1,276 2,275 1,032 Total 6,428 24,333 43,390 19,678 Unusable (Drainable)* 30 114 203 92 Undrainable * 14.8 56.0 100 45.4 * See NOTE 3. ** Assuming a fuel density of 6.75 lb/U.S. Gal. T00003NY Page 2 of 25 For aircraft incorporating Bombardier Service Bulletin 700-28-040 (or Modsum 700T804402): FUEL CAPACITY Load Weight ** Usable U.S. Gal. Liters lb kg 2 Main Tanks (Each) 2,229 8,438 15,045 6,824 1 Center Tank 1,879 7,111 12,683 5,753 1 Aft Tank 337 1,276 2,275 1,032 Total 6,674 25,256 45,050 20,433 Unusable (Drainable)* 10.6 40.1 72 32.4 Undrainable * 14.8 56.0 100 45.4 * See NOTE 3. ** Assuming a fuel density of 6.75 lb/U.S. Gal. TYPE CERTIFICATION APPLICATION DATE 27 January 1994 SERIAL NUMBERS ELIGIBLE Marketing Designation Eligible Serial Numbers Global Express 9002 and Subsequent Global Express XRS 9159 and Subsequent Global 6000 9313, 9381, 9432 and Subsequent excluding 9998, 60001 and Subsequent Global 6500 9861, 9872, 60001 and Subsequent APPROVED PUBLICATIONS Airplane Flight Manual (AFM): Please refer to the table below for the appropriate configuration for approved AFM: Marketing Designation AFM Publication Number AFM Document Identification Number Global Express CSP 700-1 GL 700 AFM-1 Global Express XRS CSP 700-1A GL 700 AFM-1A Global 6000 CSP 700-1V GL 6000 AFM Global 6500 CSP 700-6500-1 GL 6500 AFM Time Limits/Maintenance Checks Manual (TLMC): Please refer to the table below for the appropriate configuration for approved TLMC containing the Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. This information is consistent with Engineering Reports RBR-C700-167 and RAS-C700-990. See NOTE 5: Marketing Designation TLMC Publication Number TLMC Document Identification Number Global Express BD-700 TLMC GL 700 TLMC Global Express XRS BD-700 XRS TLMC GL XRS TLMC Global 6000 GL 6000 TLMC GL 6000 TLMC Global 6500 GL 6500 TLMC GL 6500 TLMC T00003NY Page 3 of 25 Structural Repair Manual (SRM): Please refer to the table below for the appropriate configuration for approved SRM: Marketing Designation SRM Publication Number SRM Document Identification Number Global Express BD-700 SRM GL 700 SRM Global Express XRS BD-700 XRS SRM GL XRS SRM Global 6000 GL 6000 SRM GL 6000 SRM Global 6500 GL 6500 SRM GL 6500 SRM Drawing List: Bombardier Publication RAL-700-0001 at Issue C-4 or later approved revisions. Type Certification Configuration The approved type design is defined in the document RAZ-C700-127 at Issue NC or later approved revisions. The approved type design number appropriate for the "as delivered" configuration of a particular BD-700-1A10 airplane is defined in the document RAL-700-XXXX (XXXX denotes the serial number for the aircraft concerned). C. G. RANGE See applicable AFM as listed in Approved Publications. See NOTE 1. DATUM FS 0.0 is located at 144 in. forward of the aircraft nose. II - Model BD-700-1A11 (Transport Category), Approved September 20, 2004, by the FAA and March 12, 2004, by the Canadian Department of Transport (DOT). MAXIMUM lb kg WEIGHTS Max. Taxi and Ramp 87,950 89,950 * 92,750 ** 39,893 40,801 * 42,071 ** Max. Take-off 87,700 89,700 * 92,500 ** 39,780 40,687 * 41,957 ** Max. Landing 78,600 35,652 Max. Zero Fuel 58,000 26,308 Min. Flight Weight 51,200 23,224 * See NOTE 14. ** See applicable AFM, as listed in Approved Publications, for configuration specific weight limitations and aircraft eligibility. FUEL CAPACITY Load Weight ** Usable U.S. Gal. Liters lb kg 2 Main Tanks (Each) 2,229 8,438 15,046 6,824 1 Center Tank 903 3,418 6,095 2,765 Total 5,361 20,294 36,187 16,413 Unusable (Drainable) * 10 37.9 67.5 30.6 Undrainable * 14.8 56.0 100 45.4 * See NOTE 3. ** Assuming a fuel density of 6.75 lb/U.S. Gal. T00003NY Page 4 of 25 For aircraft incorporating Bombardier Service Bulletin 700-1A11-11-008 or 700-11-5004 or ModSum 700T900764 and 700T900765. Load Weight ** Usable U.S. Gal. Liters lb kg 2 Main Tanks (Each) 2,229 8,438 15,046 6,824 1 Center Tank 1,357 5,136 9,158 4,158 Total 5,815 22,012 39,250 17,806 Unusable (Drainable) * 10 37.9 67.5 30.6 Undrainable * 14.8 56.0 100 45.4 * See NOTE 3. ** Assuming a fuel density of 6.75 lb/U.S. Gal. TYPE CERTIFICATION APPLICATION DATE 15 February 2002 SERIAL NUMBERS ELIGIBLE Marketing Designation Eligible Serial Numbers Global 5000 9127 and Subsequent Global 5000 ft. GVFD 9386, 9401, 9445 and Subsequent excluding 9998, 60001 and Subsequent Global 5500 60001 and Subsequent APPROVED PUBLICATIONS Airplane Flight Manual (AFM): Please refer to the table below for the appropriate configuration for approved AFM: Marketing Designation AFM Publication Number AFM Document Identification Number Global 5000 CSP 700-5000-1 GL 5000 AFM Global 5000 ft. GVFD CSP 700-5000-1V GL 5000 GVFD AFM Global 5500 CSP 700-5500-1 GL 5500 AFM Time Limits/Maintenance Checks Manual (TLMC): Please refer to the table below for the appropriate configuration for approved TLMC containing the Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. This information is consistent with Engineering Reports RBR-C700-167 and RAS-C700-990. See NOTE 5: Marketing Designation TLMC Publication Number TLMC Document Identification Number Global 5000 BD-700 TLMC GL 5000 TLMC Global 5000 ft. GVFD GL 5000 GVFD TLMC GL 5000 GVFD TLMC Global 5500 GL 5500 TLMC GL 5500 TLMC Structural Repair Manual (SRM): Please refer to the table below for the appropriate configuration for approved SRM: Marketing Designation SRM Publication Number SRM Document Identification Number Global 5000 BD-700 SRM GL 5000 SRM Global 5000 ft. GVFD GL 5000 GVFD SRM GL 5000 GVFD SRM Global 5500 GL 5500 SRM GL 5500 SRM T00003NY Page 5 of 25 Drawing List: Bombardier Publication RAL-700-0002 at Issue B or later approved revisions. Type Certification Configuration The approved type design is defined in the document RAZ-C700-127 at Issue A-2 or later approved revisions. The approved type design number appropriate for the "as delivered" configuration of a particular BD-700-1A11 airplane is defined in the document RAL-700-XXXX (XXXX denotes the serial number for the aircraft concerned). C. G. RANGE See applicable AFM as listed in Approved Publications. See NOTE 1. DATUM FS 0.0 is located at 144 in. + 32 in. forward of the aircraft nose. III - Data Pertinent to BD-700-1A10 and BD-700-1A11 except Global 5500/6500 ENGINES Two Rolls Royce Deutschland Ltd & Co KG BR700-710A2-20 ENGINE LIMITS CONDITIONS SL Static Thrust Fan RPM Core RPM ITT Time Limit lbf kN N1% N2% °C °F Max. Take-off 14,750** 65.6** 102.0 99.6 900 1,652 5 min. Max. Continuous 14,450 64.3 102.0 98.9 860 1,580 - Idle Range - - - 58.0 min. 860 max. 1,580 max. - Max. Overspeed/ Over Temperature - - 102.5 99.8 905 1,661 20 sec. Reverse Thrust - - * - - - - Starting, On Ground - - N/A N/A 700 1,292 - Starting, In Air - - N/A N/A 850 1,562 - * For Reverse Thrust, FADEC controls the Fan RPM (N1) to 70.0 % for 30 seconds. ** For aircraft incorporating SBs 700-72-6002 & 700-72-6003 or aircraft incorporating SB 700-72-5002, increased thrust limits are available for London City Airport (EGLC) AIRSPEED LIMITS Vmo and Mmo Knots Mach Sea Level to 8,000 ft. 300 - 8,000 ft. to 30,267 ft. 340 - 30,267 ft. to 35,000 ft. - 0.89 @ 47,000 ft. - 0.871 @ 47,000 ft. - 0.858 (see NOTE 8) @ 51,000 ft. - 0.855 @ 51,000 ft. - 0.842 (see NOTE 8) Vfe 6° 210 - 16° 210 - 30° 185 - Vfc 369 0.915 Vd 398 0.97 See AFM for variation of Va with altitude and aircraft weight. Vse 225 - Vmca 86 - Vmcg 84 - VLO 200 - VLE 250 - T00003NY Page 6 of 25 OIL CAPACITY Load Weight * U.S. Gal. liters lb kg 2 Engines (Each) 4.8 18.2 39 18 1 Oil Repl. Tank (Including oil repl. lines) 1.6 6.1 13 6 Total 11.2 42.5 91 42 Usable per Engine 1.01 3.83 8.2 3.7 * Assuming an oil density of 8.1073 lb/U.S. Gal. CERTIFICATION BASIS FAR Part 25 dated February 1, 1965, including: Amendments 25-1 through 25-91, Amendment 25-94, Amendment 25-96 and Amendment 25-97. There are no exceptions. Exemptions: (1) (2) No. 6726. FAR 25.1435(b)(1) Hydraulic System Proof Pressure Testing, applicable to BD-700-1A10 only. See Notes 9 and 12 for additional exemptions Additional FAA Requirements: (1) FAR Part 36 dated December 1, 1969, as amended through Amendment 36-28 for both BD-700-1A10 and BD-700-1A11. (2) Applicable portions of FAR 34 dated September 10, 1990, as amended through Amendment 34-1 inclusive. (3) (4) (5) Special Condition No. 25-140-SC dated 24 August 1998, HIRF Special Condition No. 25-288-SC, Enhanced Flight Visibility System, effective date May 12, 2005 Special Condition No. 25-658-SC, Non-Rechargeable Lithium Batteries, See Note 22 Equivalent safety has been established for the following requirements: (1) FAR 25.109 Rejected Take-off and Landing Performance Criteria (2) FAR 25.933 Thrust Reversers (3) FAR 25.1435(b)(1) Hydraulic System Proof Pressure Testing, applicable to BD-700- 1A11 only, documented in Transport Airplane Directorate ELOS Memo AT3532NY-S- 1. This equivalent safety finding is similar to exemption no. 6726 FAR 25.1435(b)(1) Compliance with the following optional requirements has been established: (1) Ditching provisions of FAR 25.801 when the safety equipment requirements of FAR 25.1411 and the ditching equipment requirements of FAR 25.1415 are satisfied. Ditching provisions are applicable to the maximum passenger capacity 22 persons (19 passenger and 3 crew) T00003NY Page 7 of 25 Airplanes incorporating the Global Vision Flight Deck per Bombardier Modsums 700T901900, 700T901901, 700T901258, and 700T901259 (for BD-700-1A10), or Modsums 700T901900, 700T901902, 700T901258, and 700T901259 (for BD-700-1A11) For parts of the airplane not changed or not affected by the modification: Certification basis is unchanged from the basic BD-700-1A10 and BD-700-1A11. For those parts of the airplane that are changed or affected by the modification: FAR Part 25 dated February 1, 1965, including Amendments 25-1 through 25-119, and 14 CFR 25.1317 at Amendment 25-122. FAR 25 Amendments 25-93, 25-95, 25-98 to 25-103, 25-106 to 25-110, 25-112, and 25-116 to 25-118 are not included in the Type Certification Basis. 14 CFR 25 design standard amendment levels addressed by the Global Vision Flight Deck modification and surpassing that of the basic aircraft correspond to the following: FAR 25 Section Title Amendment Affected Area of Design 25.105(c) Take-off 25-92 Flight Director 25.111(a)(b)(c)(d) Take-off path 25-115 Flight Director 25.113 Take-off distance and take- off run 25-92 Flight Director 25.677(b) Trim systems 25-115 Trim Control Panel Interface with New Avionics 25.783(e) Fuselage Doors 25-114 Interface with New Avionics 25.856(a) Thermal/Acoustic Insulation materials 25-111 Thermal/Acoustical Insulation Form and Part numbering (no material change) 25.1141(f) Powerplant controls: general 25-115 Interface with New Avionics and Throttle Quadrant Assembly 25.1305(a)(c)(d) Powerplant instruments 25-115 Interface with New Avionics 25.1317 High-intensity Radiated Fields (HIRF) Protection 25-122 New and Modified Electrical Equipment, Controls , and Wiring 25.1329 Flight guidance system 25-119 New Automatic Flight Control System 25.1353(a) Electrical equipment and installations 25-113 New and Modified Electrical Equipment, Controls , and Wiring 25.1431(d) Electronic Equipment 25-113 New and Modified Electronic Equipment 25.1435(b1) Hydraulic systems 25-104 Interface with New Avionic 25.1439(a)(b) Protective breathing equipment 25-115 New Electronic Equipment Interface with Existing Electronic Equipment 25.1527 Maximum operating altitude 25-105 Aircraft Ambient Temperature and Altitude Limits 25.1583 Operating limitations 25-105 New Flight Manual 25.1585 Operating procedures 25-105 New Flight Manual T00003NY Page 8 of 25 Special Condition No. 25-426-SC, dated May 20, 2011, for Synthetic Vision System on Head-Up Display § 25.773(e) Amendment 25-144 for the Enhanced Flight Vision System (EFVS) only. No. 25‐658‐SC, Non‐Rechargeable Lithium Batteries, effective to design changes applied for after May 1, 2017. See the applicability section of this special condition for more information on which design changes must meet it. Equivalent safety has been established for the following requirements: (1) FAR 25.1317(b): High-intensity Radiated Fields (HIRF) Protection documented in Transport Directorate ELOS Memo TD5590NY-S-17, dated December 9, 2009. IV - Data Pertinent to BD-700-1A10 (Global 6500) and BD-700-1A11 (Global 5500) CERTIFICATION BASIS As indicated in Section III – CERTIFICATION BASIS, the certification Basis remains the same with the following additional exemption, updated amendment levels for FAR Parts 34 and 36, and an additional in-flight all-engines restart design requirement and condition: Exemptions: (1) No. 18074. 14 CFR 25.901 (c) single failures that result in uncontrollable high thrust. See NOTE 23. Additional FAA Requirements: (1) FAR Part 36 dated December 1, 1969, as amended through Amendment 36-30. (2) Applicable portions of FAR Part 34 dated September 10, 1990, as amended through Amendment 34-5A inclusive. ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: (1) The following design details or information must be maintained to ensure that an unsafe design condition is not present: In-Flight All-Engines Restart A minimum restart capability after an all-engines-out scenario must be established under the following conditions using procedures provided in the airplane flight manual (AFM): 1. During the take-off and the initial climb-out portion of the flight, the airplane should have the capability for the flightcrew to restore engine power immediately following an all-engine-out scenario and when the fuel source to the engine is restored. 2. During the high altitude portion of the flight at cruise speed and maximum altitude, the airplane should have the capability for the flightcrew to restart engines from a stabilized windmill speed prior to descending below an altitude of 15,000 feet, by showing either or both: a. All but one engine should be restarted and accelerated to produce maximum continuous thrust/power, or b. The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to maintain level flight. T00003NY Page 9 of 25 3. During flight at speeds greater than the minimum flaps-up “holding speed” and at altitudes below 20,000 feet, the airplane should have the capability for the flightcrew to restart engines from a stabilized windmill speed prior to descending 5000 feet from the initiation of the restart procedure and prior to exceeding an airspeed of 300 knots, by showing either or both: a. All but one engine should be restarted and accelerated to produce maximum continuous thrust/power, or b. The engine(s) should be restarted, and the necessary thrust/power achieved, to enable the airplane to maintain level flight. ENGINES Two Rolls-Royce Deutschland Ltd & Co KG BR700-710D5-21 ENGINE LIMITS CONDITIONS SL Static Thrust Fan RPM Core RPM ITT Time Limit lbf kN N1% N2% °C °F Max. Take-off 15,250 67.8 102.1 101.6 890 1,634 5 min AEO 10 min OEI Max. Take-off (Transient 2 min) - - - - 900 1,652 - Max. Continuous 14,250 63.4 102.1 99.9 850 1,562 - Idle Range - - - 58.2 min. 850 max. 1,562 max. - Max. Overspeed / Over- Temperature - - 103.3 102.8 915 1,679 20 sec Reverse Thrust - - 70.4 - - - 30 sec Starting on Ground - - N/A N/A 700 1,292 - Starting in Air - - N/A N/A 850 1,562 - AIRSPEED LIMITS Knots Mach Vmo and Mmo Sea Level to 8,000 ft. 300 - 8,000 ft. to 30,850 ft. 340 - 30,850 ft. to 36,313 ft. - 0.90 ** @ 47,000 ft. - 0.871 (0.858 *) @ 51,000 ft. - 0.855 (0.842 *) Vfe (Flaps Extended) 6o 210 - 16o 210 - 30o 185 - Vfc / Mfc 369 0.915 Vd / Md 398 0.97 Va (Manoeuvring) See AFM for variation of Va with altitude and aircraft weight. Vse (Slats Extended) 225 - Vmca OUT/0 97 - OUT/6 88 - OUT/16 88 - Vmcg OUT/0 96 - OUT/6 86 - T00003NY Page 10 of 25 OUT/16 86 - VLO 200 - VLE 250 - * Refers to BD-700-1A10 aircraft incorporating Bombardier Service Bulletin 700-34-020 (ModSum 700T01613). * Applicable to all BD-700-1A11 aircraft (ModSum 700T01613 is included in the Type Certification Configuration). ** See AFM for procedures to exercise use of 0.90 Mmo. OIL CAPACITY Load Weight * U.S. Gal. Litres lb kg 2 Engines (Each) 2.96 11.2 24.0 10.9 1 Oil Repl. Tank (Including oil repl. lines) 1.51 5.7 12.2 5.53 Total 8.94 33.8 72.5 32.9 Usable per Engine 1.08 4.1 8.76 3.97 * Assuming an oil density of 8.1073 lb/U.S. Gal. V - Data Pertinent to BD-700-1A10 and BD-700-1A11 except as indicated FUEL See applicable AFM as listed in Approved Publications. OIL See applicable Aircraft Maintenance Manual (AMM) as listed below: Marketing Designation AMM Publication Number AMM Document Identification Number Global Express BD-700 AMM GL 700 AMM Global Express XRS BD-700 XRS AMM GL XRS AMM Global 6000 GL 6000 AMM GL 6000 AMM Global 6500 GL 6500 AMM GL 6500 AMM Global 5000 BD-700 AMM GL 5000 AMM Global 5000 ft. GVFD GL 5000 GVFD AMM GL 5000 GVFD AMM Global 5500 GL 5500 AMM GL 5500 AMM OIL TEMPERATURE See applicable AFM as listed in Approved Publications. OIL PRESSURE See applicable AFM as listed in Approved Publications. APU Allied Signal RE 220 (GX) APU LIMITS See applicable AFM as listed in Approved Publications. MEAN AERO- DYNAMIC CHORD 153.6 in. (3.9 m) (MAC leading edge at fuselage station 676.87 in.) LEVELING MEANS Plumb bob and target in the Aft equipment bay at FS 926 MINIMUM CREW Two (Pilot and Co-Pilot) MAXIMUM OCCUPANTS Twenty two (including the crew and no more than 19 passengers) See NOTE 2 MAX. OPERATING Take-off and Landing: 13,700 ft. ALTITUDE Enroute: 51,000 ft. T00003NY Page 11 of 25 CONTROL SURFACE Rudder 37° Left 37° Right MOVEMENTS Horizontal Stabilizer 2° LE Up 12° LE Down Aileron 26.5° TE Up 23° TE Down Elevator 24° TE Up 19° TE Down Ground spoilers 45° Up - Multi-function spoilers (Inboard to Outboard) 40/40/46/46 ° Up - SERVICE INFORMATION Service Bulletins, structural repair manuals, and airplane 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 type design only. IMPORT ELIGIBILITY 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: "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-177 and includes the minimum type design defined in document RAZ-C700-127 at Issue NC or subsequent approved revisions as being required to comply with the basis for the FAA Type Certificate No. T00003NY”, and is in a condition for safe operation. The U.S. airworthiness certification basis for aircraft type certificated under FAR 21.29 and exported by the country of manufacture is FAR 21.183(c) or FAR 21.185(c) The U.S. airworthiness certification basis for aircraft type certificated under FAR 21.29 and exported from countries other than the country of manufacture (e.g. third party country) is FAR 21.183(d) or FAR 21.185(b) The U.S. airworthiness certification basis for the issuance of an airworthiness certificate for aircraft type certificated under FAR 21.21 and manufactured in a foreign country under a licensing arrangement is FAR 21.183(d) or FAR 21.183(b) The U.S. airworthiness certification basis for an aircraft originally type certificated under FAR 21.21 but transferred outside the U.S. is 21.183(d) Additional guidance is contained in FAA AC 21-23A, or subsequent revision, Airworthiness Certification of Civil Aircraft, Engines, Propellers and Related Products Imported into the United States. T00003NY Page 12 of 25 VI - Model BD-700-2A12 (Transport Category), Approved November 07, 2018, by the FAA and September 27 2018, by Transport Canada Civil Aviation MAXIMUM lb kg WEIGHTS Max. Taxi and Ramp 115,100 52,208 Max. Take-off 114,850 52,095 Max. Landing 87,600 39,735 Max. Zero Fuel 67,500 30,617 *See applicable AFM, as listed in Approved Publications, for other weight limitations and aircraft eligibility. FUEL CAPACITY Global 7500 PRESSURE REFUEL (+0/-1%) Load Weight ** Usable U.S. Gal. liters lb. kg 2 Main Tanks (Each) 2,603 9,853 17,550 7,950 1 Center Tank 2,101 7,953 14,200 6,450 Aft Tank 380 1,439 2,550 1,150 Total 7,687 29,098 51,850 23,500 Unusable (Drainable)* 12.4 47.0 83.8 38.0 Undrainable* 14.2 53.9 96.1 43.6 ** Assuming a fuel density of 6.75 lbs/US Gal (0.809 kg / liter), rounded to the nearest 25 kg or 50 lb. Fuel weights are provided for reference only and should not be considered limiting. Global 8000 (see NOTE 26) PRESSURE REFUEL (+0/-1%) Load Weight ** Usable U.S. Gal. liters lb. kg 2 Main Tanks (Each) 2,632 9,963 17,750 8,050 1 Center Tank 2,110 7,987 14,250 6,450 Aft Tank 380 1,438 2,550 1,175 Total 7,754 29,352 52,300 23,725 Unusable (Drainable)* 12.4 47.0 83.8 38.0 Undrainable* 14.2 53.9 96.1 43.6 ** Assuming a fuel density of 6.75 lbs/US Gal (0.809 kg / liter), rounded to the nearest 25 kg or 50 lb. Fuel weights are provided for reference only and should not be considered limiting. TYPE CERTIFICATION APPLICATION DATE Initial: June 13, 2012 Deferred: December 10, 2013 SERIAL NUMBERS ELIGIBLE 70005 and subsequent APPROVED PUBLICATIONS Airplane Flight Manual (AFM): Please refer to the table below for the appropriate configuration for approved AFM: Marketing Designation Publication Number Document Identification Number Global 7500 CSP 700-7000-1 Rev. BASIC or later approved revisions GL 7500 AFM Global 8000 GL 8000 AFM Rev. BASIC or later approved revisions GL 8000 AFM T00003NY Page 13 of 25 Airworthiness Limitations (AWL): Please refer to the table below for the appropriate configuration for approved Airworthiness Limitations containing the mandatory Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. This information is consistent with Engineering Reports RBR-BA700-167 and RAS-BA700-990: