# TCDS T00003NY: Bombardier Inc.

- Type: Type certificate data sheet
- Status: Current
- Holder: Bombardier Inc.
- Revision: 24
- Revised: December 19, 2025
- Product: Aircraft, Large Airplane
- Certification basis: Part 25
- Registered aircraft: 659, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/2e/6c/2e6cd88f2bdcb6228eecb078ba3f9ce9efc309a582709a4d0c2b5abec2965dc5
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID116658665820251219185513.0001
- Page: https://openairdocs.org/tcds/T00003NY

## Models (3)

As the data sheet lists them.

- BD-700-1A10
- BD-700-1A11
- BD-700-2A12

## 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 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:   
  
 Marketing Designation Publication Number Document Identification 
Number 
 Global 7500 BD700-3AB48-11400-01 
Issue 003, or later 
approved revisions 
GL 7500 / 8000 AWL 
 Global 8000 BD700-3AB48-11400-01 
Issue 023, or later 
approved revisions 
GL 7500 /8000 AWL 
  
Type Certification 
Configuration 
The approved type design is defined in the document RAO-BA700-049 Revision 
C or later approved revisions.  
 
The approved type design appropriate for the "as delivered" configuration of a 
particular BD-700-2A12 airplane is defined in RAL-700-XXXXX (XXXXX 
denotes the serial number for the aircraft concerned).

T00003NY Page 14 of 25 
 
 
OIL CAPACITY  Load Weight * 
  U.S. Gal. Liters lb kg 
 2 Engines (Each)  
(Incl. Oil Repl. Lines) 
4.9 18.5 40 18 
 1 Oil Repl. Tank 1.6 6.1 13 6 
 Total 11.4 43.0 92 42 
 *Assuming a fluid density 8.1073 lb/U.S.Gal. (0.971 kg/L).  
 
APU Safran SPU300 [BA] 
  
APU LIMITS See applicable AFM as listed in Approved Publications.  
 
C. G. RANGE See applicable AFM as listed in Approved Publications.   
  
DATUM FS 0.0 is located at 397.5 in. forward of the weighing datum. The weighing datum 
is marked on a plate forward of the wing fairing on the bottom of the fuselage on 
the aircraft center line at FS 397.5.  
  
LEVELING MEANS The aircraft is levelled in the longitudinal and lateral axes by means of a plumb 
bob and target in the aft equipment bay at Fuselage Station (FS) 962.73. 
  
ENGINES Global 7500 
 Two General Electric Passport 20-19BB1A 
  
 Global 8000 
 Two General Electric Passport 20-19BB1B 
  
FUEL See applicable AFM as listed in Approved Publications.  
  
OIL Engine, APU:  Refer to Aircraft Maintenance Publication (AMP), Bombardier 
Publication BD700-3AB48-10200-00, Chapter 51, for the appropriate 
configuration.  
  
ENGINE LIMITS 
CONDITIONS 
See applicable AFM as listed in Approved Publications. 
  
OIL TEMPERATURE See applicable AFM as listed in Approved Publications.  
  
OIL PRESSURE See applicable AFM as listed in Approved Publications.

T00003NY Page 15 of 25 
 
AIRSPEED LIMITS  Knots Mach 
  Vmo and Mmo  
Sea Level to 8,000 ft. 
10,000 ft. to 16,000 ft. 
20,000 ft. to 35,000 ft. 
 @ 35,000 ft. 
- 
300 
335 
320 
- 
- 
- 
- 
- 
0.925 
  37,500 ft. to 51,000 ft - Global 7500: 0.925   Global 8000: 0.95 
  Vfe 
Flap 1 
Flap 2 
Flap 3 
Flap 4 
- 
225 
210 
210 
185 
- 
- 
- 
- 
- 
  Vfc and Mfc 
10,000 ft. to 16,000 ft. 
20,000 ft. to 35,000 ft. 
- 
353 
338 
- 
- 
- 
  @ 51,000 ft. - Global 7500: 0.947   Global 8000: 0.97 
  Vd and Md 
Sea Level to 16,000 ft. 
20,000 ft. to 34,100 ft. 
@ 34,100 ft. 
- 
370 
355 
- 
- 
- 
- 
0.995 
  37,500 ft. to 51,000 ft. - Global 7500: 0.995   Global 8000: 1.02 
  Va (Design Maneuvering) See applicable AFM for variation of Va with 
altitude and aircraft weight. 
  Vmca 
Flap 2 
Flap 3 
- 
100 
98 
- 
- 
- 
  Vmcl 
Flap 2 
Flap 3 
Flap 4 
- 
103 
98 
96 
- 
- 
- 
- 
  Vmcg 
Flap 2 
Flap 3 
- 
105.6 
105.6 
- 
- 
- 
  VLO 200 - 
  VLE 250 - 
 
MEAN AERO-
DYNAMIC CHORD 
179.04 in. (4.5 m) (MAC leading edge at fuselage station 715.32 in.) 
  
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  See applicable AFM as listed in Approved Publications. 
ALTITUDE  
  
CONTROL SURFACE Rudder 37° Left 37° Right  
MOVEMENTS Horizontal Stabilizer 4.5° LE Up 12.5° LE Down 
 Aileron 25° TE Up 24° TE Down 
 Elevator 30° TE Up 19° TE Down 
 Ground spoilers 45° Up -

T00003NY Page 16 of 25 
 Multi-function spoilers  
(Inboard to Outboard) 
40/45/50 ° 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 
RAO-BA700-049 at Revision C 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. 
  
 
CERTIFICATION BASIS Global 7500 
1. Airworthiness Standards: 
Federal Aviation Administration (FAA), Title 14, Code of Federal Regulations (14 CFR), 
Part 25 effective February 1, 1965, including Amendments 25-1 through 25-138 with the 
following exceptions: 
  
§ 25.773 Amendment 25-144 for the Enhanced Flight Vision System (EFVS) only. 
 
Including optional design requirements: 
a) Ditching (limited to structural provisions): § 25.801(b)(c)(e) 
b) Icing: § 25.1419

T00003NY Page 17 of 25 
 2. Special Conditions 
25-581-SC Design Roll-Maneuver Condition. 
25-587-SC Electronic Flight Control System: Control Surface Awareness and Mode 
Annunciation 
25-588-SC Side Stick Controllers: Pilot Strength, Pilot Control Authority, and Pilot 
Control 
25-593-SC Flight Envelope Protection, High-Speed Limiting 
25-615-SC Airplane Electronic System Security Protection From Unauthorized 
External Access 
25-631-SC Automatic Speed Protection for Design Dive Speed 
25-633-SC Airplane Electronic-System Security Protection From Authorized Internal 
Access 
25-635-SC Interactions of Systems and Structures 
25-636-SC Sidestick Controllers 
25-637-SC Hydrophobic Coatings in Lieu of Windshield Wipers 
25-647-SC Electronic Flight Control System: Lateral- Directional and Longitudinal 
Stability, and Low-Energy Awareness 
25-653-SC Operation Without Normal Electrical Power. 
25-656-SC Fuselage In-Flight Fire Safety and Flammability Resistance of 
Aluminum-Lithium Material 
25-658-SC Non-Rechargeable Lithium Batteries (See Note 22) 
25-670-SC Limit Engine Torque Loads 
25-695-SC Fuselage Post-Crash Fire Survivability 
25-717A-
SC 
Flight Envelope Protection: Pitch and Roll Limiting 
25-718-SC Synthetic Vision System on Head-Up Display 
25-719-SC Flight-Envelope Protection: General Limiting Requirements 
25-720-SC Flight Envelope Protection: Normal Load Factor (g) Limiting 
25-725-SC Flight Envelope Protection: High Incidence Protection System 
25-727-SC Autobrake System Structural Loads 
25-734-SC Multiple-Place Side-Facing Seats with Active Leg Flail Restraint Device 
and Shoulder-Belt Airbags 
25-735-SC Enhanced Flight Vision System (EFVS)

T00003NY Page 18 of 25 
 3. Equivalent Safety Findings 
ELOS Memo Requirement Title 
AT7180NY-T-GA-ES-06 25.831(g) Acceptable High Temperature Physiological 
Environment During Failure Conditions - 
Equivalent Safety Finding (Cabin Temperature - 
Humidity Limits) 
AT7180NY-T-GA-P-06 25.901(d), 
and 14 CFR 
part 25 
subpart E, F, 
and G 
applicable to 
APU 
installations 
Part 25 Subparts E, F, and G (Added as Subpart J) 
APU Certification Requirements 
AT7180NY-T-IP-P-21 14 CFR 
25.901, 
25.903, 
25.1305, 
25.1309, 
25.1321, 
25.1322 and 
25.1549 
Digital Only Display of the Turbine Engine 
Required Parameters 
AT7180NY-T-GA-SA-05 25.901, 
25.130l and 
25.1309 
25.1309(a)(b)(c)(d)(e)   Equipment, Systems, & 
Installations Requirements - ESF Using ARAC 
901, 1301, & 1309 
AT7180NY-T-CL-SM-02 25.671   Flight Control System Failure Criteria 
AT7180NY-T-GA-A-02 25.391 
25.395(b) 
25.415 
25.391, 25.395(b), 25.415   Ground Gust Condition 
AT7180NY-T-GA-A-03 25.341(a)(5)
(i)(b) 
25.343(b)(1)
(ii) 
25.345(c)(2) 
25.371 
25.373(a) 
25.391  
25.1517    
Gust and Continuous Turbulence Loads 
AT7180NY-T-GA-A-04 25.721 
25.963(d) 
25.994  
Emergency Landing Conditions 
AT7180NY-T-GA-ES-05 25.841(a) 
25.841(b)(6) 
Cabin Pressurization – High Altitude Airports 
AT7180NY-T\ 
AT7285NY-T-GA-F-06 
25.331(c)(2)  Checked Pitch Maneuver 
AT7180NY-T-GA-P-01 25.933(a)(1) Flight Critical Thrust Reverser 
AT7180NY-T-GA-SA-02 25.1303(a)(3
) 
25.1327(a)(b
) 
25.1547    
Use of an Electric-Only Direction Indicator 
Standby Instrumentation 
AT7180NY-T-GA-SE-01 25.1317(b) High-Intensity Radiated Fields 
AT7180NY-T-GA-SE-05 25.1389(b)(3
) 25.1395    
Maximum Allowable Overlapping Intensities on 
Position Lights 
AT7180NY-T-GA-F-25 25.1322 
(c)(2) 
25.1322 
(e)(1) 
Flight Crew Alerting 
AT7180NY-T-CL-F-24 25.161(c)(1) Longitudinal Trim

T00003NY Page 19 of 25 
 ST08054NY-T- 
GA-CS-02 
25.811, 25.812 Emergency Exit and Exit Locator Sign 
ST08054NY-T-
GA-CS-04 
25.785 Occupant Retention - Lap Belt Rebound Position 
Assessment for Injury 
ST08054NY-T-
GA-CS-06 
25.1443 Passenger Cabin Minimum Mass Flow of Supplemental 
Oxygen 
ST08054NY-T-
GA-P-08 
21.21, 25.851, 
25.857, 25.1195, 
25.1309 
Powerplant Fire Extinguishing System Bottle 
ST08054NY-T-
GA-ES-02 
25.851 (b), 
25.857 (b) (1) 
Shared Fire Extinguisher Bottle for the Class B 
Baggage Compartment Fire Protection System 
ST08054NY-T-
GA-ES-01 
25.851  Built-In Fire Extinguishing System in place of Hand Fire 
Extinguisher for a Class B Baggage Compartment 
 
  
4. Exemptions: 
No. 11162A 14 CFR 25.809 (a) Relief from the requirement to view the likely area of 
evacuee ground contact for the flight crew emergency exit in addition to 
the overwing exit. 
No. 17817 14 CFR 25.981(a) (3) Use of the provisions of FAA Policy Statement 
PS-ANM-25.981-02, Policy on Issuance of Special Conditions and 
Exemptions Related to Lightning Protection of Fuel Tank Structure and 
Systems, for fuel tank lightning protection as an alternative to full 
compliance to § 25.981(a)(3). 
No. 17895 14 CFR 25.901 (c) single failures that result in uncontrollable high thrust. 
See Note 21. 
No. 18049 14 CFR 25.1322(a)(2) L(R) ENG Flameout Caution Messages Inhibited 
No. 17716 
 
14 CFR 25.1447(c)(1) Relief from the requirement for passenger oxygen 
masks to be automatically presented before the cabin pressure altitude 
exceeds 15,000 feet 
No. 18007 
 
14 CFR 25.813(e) Allow for the installation of doors between passenger 
seats and passenger emergency exits 
 
  
5. Noise Standards: 
14 CFR Part 36, effective December 1, 1969, including Amendments 36-1 through 36-29. 
  
6. Fuel Venting and Exhaust Emission Standards: 
14 CFR Part 34, effective September 10, 1990, as amended by Amendments 34-1 through 
34-5A inclusive. 
  
7. A finding of regulatory adequacy pursuant to the “Noise Control Act of 1972” (49 USC 
Section 44715 
  
ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: 
1) Engine Damage From Wing Ice Caused by Cold Soaked Fuel.   
The potential hazards associated with ice that may form on the wings due to cold soaked 
fuel have been addressed through an analysis of the basic aircraft design, plus an airplane 
flight manual (AFM) limitation specific to this concern.  The AFM limitation references the 
Flight Crew Operating Manual (FCOM).  The FCOM has inspection criteria based on fuel 
temperature and observed ambient weather conditions, and includes the requirement for a 
tactile inspection.  This information must be retained such that any ice accumulation on the 
upper wing surface after refueling will be detected and addressed. 
 
2) Inflight Engine Restart 
Compliance shown by test. Any modifications to the associated AFM procedures require 
evaluation to ensure an unsafe condition is not introduced. Changes in the engine design 
affecting engine restart require aircraft-level evaluation.

T00003NY Page 20 of 25 
 Global 8000 
1. Airworthiness Standards: 
For parts of the airplane not changed or not affected by the change: Certification basis is 
unchanged from the original certification basis for the Model BD-700-2A12 (Global 7500). 
 
For the areas affected by the change:  14 CFR Part 25 effective February 1, 1965, including 
amendments 25-1 through 25-150, with the exceptions per 14 CFR 21.101. 
 
14 CFR Part 25 design standard amendment levels addressed by the Global 8000 
modifications and surpassing that of the basic aircraft correspond to the following: 
  
 14 CFR Amendment 
Level 
Applicable Area Notes 
 Section Title 
 25.307 Proof of 
structure. 
25-139 Winglet, 
Aileron, Flaps, 
Cockpit 
MMO increase 
affects static loads 
on localized areas 
of the structure. 
 25.353 Rudder control 
reversal 
conditions. 
25-147 Aeroelastic and 
Aeroservoelastic 
analyses 
MD increase 
affects aeroelastic 
and 
aeroservoelastic 
analyses. 
  
 2. Special Conditions: 
Same as Global 7500. 
  
 3. Equivalent Safety Findings: 
Same as Global 7500. 
  
 4. Exemptions: 
Same as Global 7500. 
  
 5. Noise Standards: 
No Acoustical Change per § 21.93(b) compared to Global 7500, however Global 8000 has 
been shown to comply with Stage 5 noise requirement in 14 CFR Part 36 effective 
December 1, 1969, including amendments 36-1 through 36-32. 
  
 6. Fuel Venting and Exhaust Emission Standards: 
No Emissions Change per § 21.93(c) compared to Global 7500. 
  
 ADDITIONAL DESIGN REQUIREMENTS AND CONDITIONS: 
Same as Global 7500. 
  
 
VII. Data Pertinent to all Models except as indicated 
  
EQUIPMENT The basic equipment as prescribed in the applicable requirements (See certification basis) 
must be installed in the aircraft.  
 
NOTE 1 A current weight and balance report must be provided for each aircraft at the time of 
the original airworthiness certification and at all times thereafter except in case of an 
operator having an FAA approved loading system for weight and balance control. 
  
NOTE 2 The green aircraft type design configuration does not include passenger provisions.  
Carriage of persons in the cabin is permitted when an approved seating arrangement 
and related required passenger provisions are incorporated in accordance with the 
Type Certificate Basis.

T00003NY Page 21 of 25 
  
NOTE 3 System fuel, which must be included in the empty weight, is the amount of fuel 
required to fill the system plumbing and tanks to the undrainable level plus unusable 
fuel in the fuel tanks.  The weight of undrainable and unusable fuel defined in the 
Fuel Capacity section must be included in the empty weight of the airplane. 
  
NOTE 4 BD-700-1A10 & BD-700-1A11 
Placards must be installed in accordance with Bombardier Drawings:   
GC 789-0001, GD 972-0001, GM 972-0010, GS 782-0001 (for BD-700-1A10 only), 
and GS 782-5001 (for BD-700-1A11 only). 
 
BD-700-1A10 & BD-700-1A11 – Global 6000/6500 and Global 5000 ft. 
GVFD/5500 
Placards must be installed in accordance with Bombardier Drawings GC 789-7000, 
GC 789-7001, GD 972-0001, GM 972-0010, GS 782-0001 (BD-700-1A10 only), GS 
782-5001 (BD-700-1A11 only) and GC 789-7500 (BD-700-1A11 only). 
 
BD-700-2A12  
Placards must be installed in accordance with Bombardier Drawings:   
G05318400, G01100006, G05378400, G05387700, G05387900, G05700014, 
G05313290, G05217000, G05290700, G00693181, G05290800, G00611121 and 
G00611122. 
  
NOTE 5 The airplane life limits and repetitive inspections for components and equipment and 
information essential for proper maintenance, are listed in the following respective 
Bombardier Publications. These limitations may not be changed without FAA 
Engineering approval. 
 
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 
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 
 
  
NOTE 6 Refers to aircraft which incorporate Bombardier Service Bulletin SB 700-11-007. 
  
NOTE 7 Refers to aircraft which incorporate Bombardier Service Bulletin SB 700-11-011. 
  
NOTE 8 Refers to BD-700-1A10 aircraft which incorporate Bombardier Service Bulletin 
SB 700-34-020, or have modification 700T01613 incorporated during production. 
All BD-700-1A11 aircraft have modification 700T01613 incorporated during 
production.

T00003NY Page 22 of 25 
NOTE 9 FAA Exemption No. 7120C (Regulatory Docket No. FAA-2002-13385) was issued 
to Bombardier Aerospace, on September 2, 2003 which granted an exemption from 
the requirements of 25.785(b) for the general occupant protection requirements for 
occupants of multiplace side-facing seats that are occupied during take off and 
landing for Bombardier Global Express BD-700-1A10 airplanes.  
 
FAA Exemption No. 7120D (Regulatory Docket No. FAA-2002-13385) was issued 
to Bombardier Aerospace, on June 13, 2005 which granted an exemption from the 
requirements of 25.785(b) for the general occupant protection requirements for 
occupants of multiplace side-facing seats that are occupied during take off and 
landing for Bombardier Global Express BD-700-1A11 airplanes. 
  
NOTE 10 Refers to aircraft which incorporate Bombardier Service Bulletin SB 700-11-016. 
  
NOTE 11 The certification basis for airplane model BD-700-1A10 and BD-700-1A11 includes 
FAR 25.831 at Amendment 25-89 and FAR 25.841 at Amendment 25-87.  These 
regulations address operation at high altitude and include pressurization system 
requirements, as well as structural requirements on the pressure vessel.  In addition, a 
high altitude special condition, which contains similar requirements, was applied by 
the Canadian authorities.  Therefore, any changes to the pressurization system or 
modifications or repairs to the pressure vessel must be approved in accordance with 
these and other applicable requirements. 
 
NOTE 12 FAA Exemption No. 7259 (Regulatory Docket No. 29819) and 7891 (Regulatory 
Docket No. FAA-2002-12350) were issued to Bombardier Aerospace, on June 29, 
2000 which granted exemption from the requirements of FAR 25.813(e) for the 
installation of doors in partitions between passenger compartments for the BD-700-
1A10 aircraft. 
 
FAA Exemption No. 7259A (Regulatory Docket No. FAA-2005-21272) was issued 
to Bombardier Aerospace, on June 13, 2005 which granted exemption from the 
requirements of FAR 25.813(e) for the installation of doors in partitions between 
passenger compartments for the BD-700-1A11 aircraft. 
  
NOTE 13 Global Express is a marketing designation for the Model BD-700-1A10 aircraft and 
Global 5000 is a marketing designation for the Model BD-700-1A11 aircraft.  FAA 
Airworthiness Directives will be issued against the Model numbers (BD-700-1A10, 
or BD-700-1A11) 
 
NOTE 14 The higher weights are applicable to aircraft that are either post modification 
Bombardier Service Bulletin SB 700-1A11-11-002 or post modification Bombardier 
Modsum 700T97079C. 
  
NOTE 15 Refers to aircraft which incorporate Bombardier Service Bulletin SB 700-11-020.

T00003NY Page 23 of 25 
NOTE 16 BD-700-1A10 and BD-700-1A11 “Global Vision Flight Deck” Definition  
The Global Vision Flight Deck designation for the BD-700-1A10 and BD-700-1A11 
does not correspond to a model designation.  This is only a commercial designation 
for airplanes on which Modsums 700T001900, 700T901901, 700T901258, and 
700T901259 (for BD-700-1A10), and Modsums 700T901900, 700T901902, 
700T901258, and 700T901259 (BD-700-1A11) have been embodied. 
 
Major Change Modification numbers 700T001900, 700T901901, 700T901258, and 
700T901259 (for BD-700-1A10), and 700T901900, 700T901902, 700T901258, and 
700T901259 (for BD-700-1A11) install the Rockwell Collins ProLine Fusion 
avionics suite.  This system architecture is mainly built around 4 Integrated 
Processing Cabinets (IPC), 2 Data Concentration Unit Module Cabinets (DMC), 2 
Radio Interface Units (RIU), 2 Audio Control Panels (ACP), 2 Reversion Switch 
Panels (RSP) and 4 14.1 inch Liquid Crystal Displays.  The pilots have access to the 
system using the 2 Cursor Control Devices (CCDs) and 2 Control Tuning Panels 
(CTP). 
  
ModSums 700T901900 and 700T901901 are baseline on all BD-700-1A10 aircraft, 
serial number 9313, 9381, 9432 and subsequent, excluding 9998. 
 
ModSums 700T901900 and 700T901902 are baseline on all BD-700-1A11 aircraft, 
serial number 9386, 9401, 9445 and subsequent, excluding 9998. 
 
The LCD HUD is separately installed via Modsums 700T97369 (BD-700-1A10) and 
700T97578 (BD-700-1A11). 
 
All parameters listed in the preceding sections I and II for the basic BD-700-1A10 
and BD-700-1A11 remain valid for airplanes which incorporate Modsums 
700T901900 and 700T901901 (for BD-700-1A10), or Modsums 700T901900 and 
700T901902 (for BD-700-1A11).  
 
Refer to document RAZ-C700-127 at Issue A-10 or later approved revision for 
additional Modsums required to comply with the FAA basis of certification. 
 
NOTE 17 Global 6000 is a marketing designation for BD-700-1A10 equipped with the Global 
Vision Flight Deck, corresponding to aircraft with either following combinations of 
modifications installed: 
With 
700T901901 
and 
Without 
700T03185 
OR 
With 
700T901901 
700T03185 
700T101134 
  
Global 5000 featuring the Global Vision Flight Deck (Global 5000 ft. GVFD) is a 
marketing designation for BD-700-1A11 equipped with the Global Vision Flight 
Deck, corresponding to aircraft with either following combinations of modifications 
installed: 
With 
700T901902 
and 
Without 
700T03185 
OR 
With 
700T901902 
700T03185 
700T101134 
 
  
NOTE 18 All variants of the BD-700-1A10, BD-700-1A11 and BD-700-2A12 are compliant 
with RVSM airworthiness requirements through basic equipment.  Each operator 
must obtain RVSM operating approval directly from the FAA.

T00003NY Page 24 of 25 
  
NOTE 19 BD-700-1A10 and BD-700-1A11 – Equipped with the “Global Vision Flight Deck” 
BD-700-1A10 and BD-700-1A11 equipped with the "Global Vision Flight Deck" are 
compliant with RNP RNAV, down to RNP 0.3 RNAV through basic equipment. 
 
NOTE 20 Global 7500 (previously known as Global 7000) is a marketing designation for BD-
700-2A12.  
  
NOTE 21 For BD-700-2A12, The FAA has concluded that the occurrence of any 
uncontrollable high-thrust failure condition, or any of the associated causal failures 
listed within Global 7500 / 8000 Aircraft Maintenance Publication (BD700-3AB48-
10200-00), may endanger the safe operation of an airplane. Consequently, the FAA 
recommends that operators be encouraged to report any such failures in accordance 
with 14 CFR 121.703(c), 125.409(c), 135.415(c) 
  
NOTE 22 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. 
  
NOTE 23 FAA Exemption No. 18074 (Regulatory Docket No. FAA-2018-0530) was issued to 
Bombardier Aerospace, on December 4, 2018 which granted exemption from the 
requirements of FAR § 25.901(c) for the relief from full compliance with the 
regulation as it relates to single failures that result in uncontrolled high thrust (UHT) 
for Model BD-700-1A10 and BD-700-1A11 airplane models equipped with BR700 
Next-Gen Engines (BR700-710D5-21). 
 
For BD-700-1A10 and BD-700-1A11 equipped with BR700 Next-Gen Engines 
(BR700-710D5-21), the FAA has concluded that the occurrence of any uncontrolled 
high-thrust failure condition, or any of the associated causal failures listed within 
Bombardier Aerospace Publication Number GL 5500 AMM and GL 6500 AMM, 
may endanger the safe operation of an airplane. Consequently, the FAA recommends 
that operators report any such failures in accordance with title 14, Code of Federal 
Regulations 121.703(c), 125.409(c), and 135.415(c). 
 
NOTE 24 Global 6500 is a marketing designation for BD-700-1A10 equipped with the Global 
Vision Flight Deck and Rolls-Royce Deutschland Ltd & Co KG BR700-710D5-21 
engines, corresponding to aircraft following combination of modifications installed: 
With 
700T901901 
700T03185 
700T63572 
and 
Without 
700T101134 
 
  
NOTE 25 Global 5500 is a marketing designation for BD-700-1A11 equipped with the Global 
Vision Flight Deck and Rolls-Royce Deutschland Ltd & Co KG BR700-710D5-21 
engines, corresponding to aircraft following combination of modifications installed: 
With 
700T901902 
700T03185 
700T63572 
and 
Without 
700T101134

T00003NY Page 25 of 25 
NOTE 26 Global 8000 is a marketing designation for BD-700-2A12 equipped with the General 
Electric Passport 20-19BB1B engines, and the following combination of 
modifications installed: 
 
With 
700T7095076 
700T7095110 
700T7095078 
or With 
SB 700-34-7528 
 
 
 
…..END…..
```

## ADs (89, first 50, in force first)

- [AD 2026-20-09](https://openairdocs.org/ad/2026-20-09): Wings · Bombardier BD-700-2A12. Effective Nov 18, 2026
- [AD 2026-15-09](https://openairdocs.org/ad/2026-15-09): Landing Gear · Bombardier BD-700-1A10 and BD-700-1A11. Effective Sep 3, 2026
- [AD 2026-14-01](https://openairdocs.org/ad/2026-14-01): Wings · Bombardier BD-700-2A12. Effective Aug 14, 2026
- [AD 2026-11-07](https://openairdocs.org/ad/2026-11-07): Equipment/furnishings · Bombardier BD-700-1A10, BD-700-1A11 and BD-700-2A12. Effective Jul 20, 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 2026-09-18](https://openairdocs.org/ad/2026-09-18): Doors · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jun 26, 2026
- [AD 2026-08-04](https://openairdocs.org/ad/2026-08-04): Flight Controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective May 29, 2026
- [AD 2025-14-51](https://openairdocs.org/ad/2025-14-51): Indicating/Recording System · Bombardier BD-700-1A10 and BD-700-1A11. Effective Mar 4, 2026
- [AD 2025-16-07](https://openairdocs.org/ad/2025-16-07): Oxygen · Bombardier BD-700-1A10. Effective Sep 18, 2025
- [AD 2025-12-01](https://openairdocs.org/ad/2025-12-01): Flight Controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jul 17, 2025
- [AD 2025-07-11](https://openairdocs.org/ad/2025-07-11): Hydraulic Power · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jul 2, 2025
- [AD 2025-09-04](https://openairdocs.org/ad/2025-09-04): Time Limits/Maintenance Checks · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jun 6, 2025
- [AD 2025-04-11](https://openairdocs.org/ad/2025-04-11): Navigation · Bombardier BD-700-2A12. Effective Apr 8, 2025
- [AD 2024-26-09](https://openairdocs.org/ad/2024-26-09): Time Limits/Maintenance Checks; Flight Controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective Mar 11, 2025
- [AD 2024-18-06](https://openairdocs.org/ad/2024-18-06): Engine exhaust · Bombardier BD-700-2A12. Effective Jan 23, 2025
- [AD 2024-23-02](https://openairdocs.org/ad/2024-23-02): Landing Gear · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jan 15, 2025
- [AD 2024-23-08](https://openairdocs.org/ad/2024-23-08): Wings · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jan 6, 2025
- [AD 2024-14-05](https://openairdocs.org/ad/2024-14-05): Fire protection · Bombardier BD-700-2A12. Effective Dec 17, 2024
- [AD 2024-18-04](https://openairdocs.org/ad/2024-18-04): Electrical power · Bombardier BD-700-2A12. Effective Nov 12, 2024
- [AD 2024-07-09](https://openairdocs.org/ad/2024-07-09): Doors · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jun 17, 2024
- [AD 2024-06-08](https://openairdocs.org/ad/2024-06-08): Pneumatic · Bombardier BD-700-2A12. Effective Jun 5, 2024
- [AD 2024-03-08](https://openairdocs.org/ad/2024-03-08): Pneumatic · Bombardier BD-700-1A10 and BD-700-1A11. Effective May 3, 2024
- [AD 2024-02-05](https://openairdocs.org/ad/2024-02-05): Wings · Bombardier BD-700-1A10 and BD-700-1A11. Effective Apr 9, 2024
- [AD 2023-24-08](https://openairdocs.org/ad/2023-24-08): Landing gear · Bombardier BD-700-1A10 and BD-700-1A11. Effective Feb 6, 2024
- [AD 2023-20-10](https://openairdocs.org/ad/2023-20-10): Flight controls · Bombardier BD-700-2A12. Effective Nov 21, 2023
- [AD 2023-12-02](https://openairdocs.org/ad/2023-12-02): Time Limits/Maintenance Checks · Bombardier BD-700-1A10 and BD-700-1A11. Effective Aug 7, 2023
- [AD 2023-13-15](https://openairdocs.org/ad/2023-13-15): Navigation · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jul 27, 2023
- [AD 2023-14-01](https://openairdocs.org/ad/2023-14-01): Navigation · Bombardier BD-700-2A12. Effective Jul 27, 2023
- [AD 2023-09-08](https://openairdocs.org/ad/2023-09-08): Pneumatic · Bombardier BD-700-2A12. Effective Jul 10, 2023
- [AD 2023-08-01](https://openairdocs.org/ad/2023-08-01): Flight controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jun 20, 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 2023-05-11](https://openairdocs.org/ad/2023-05-11): Flight controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective May 12, 2023
- [AD 2023-04-01](https://openairdocs.org/ad/2023-04-01): Doors · Bombardier BD-700-2A12. Effective Apr 7, 2023
- [AD 2023-03-08](https://openairdocs.org/ad/2023-03-08): Fuselage · Bombardier BD-700-2A12. Effective Apr 3, 2023
- [AD 2022-27-02](https://openairdocs.org/ad/2022-27-02): Navigation · Bombardier BD-700-2A12. Effective Mar 17, 2023
- [AD 2022-24-01](https://openairdocs.org/ad/2022-24-01): Flight controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective Mar 9, 2023
- [AD 2022-25-13](https://openairdocs.org/ad/2022-25-13): Doors · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jan 13, 2023
- [AD 2022-23-03](https://openairdocs.org/ad/2022-23-03): Navigation · Bombardier BD-700-2A12. Effective Jan 9, 2023
- [AD 2022-23-04](https://openairdocs.org/ad/2022-23-04): Oxygen · Bombardier BD-700-2A12. Effective Dec 30, 2022
- [AD 2022-20-09](https://openairdocs.org/ad/2022-20-09): Pneumatic · Bombardier BD-700-2A12. Effective Nov 25, 2022
- [AD 2022-17-11](https://openairdocs.org/ad/2022-17-11): Oxygen · Bombardier BD-700-2A12. Effective Oct 27, 2022
- [AD 2022-18-10](https://openairdocs.org/ad/2022-18-10): Fire protection · Bombardier BD-700-2A12. Effective Oct 20, 2022
- [AD 2022-14-07](https://openairdocs.org/ad/2022-14-07): Oxygen · Bombardier BD-700-1A10 and BD-700-1A11. Effective Aug 19, 2022
- [AD 2022-13-05](https://openairdocs.org/ad/2022-13-05): Navigation · Bombardier BD-700-1A10 and BD-700-1A11. Effective Aug 11, 2022
- [AD 2022-11-17](https://openairdocs.org/ad/2022-11-17): Time Limits/Maintenance Checks · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jul 22, 2022
- [AD 2022-12-01](https://openairdocs.org/ad/2022-12-01): Oxygen · Bombardier BD-700-1A10 and BD-700-1A11. Effective Jul 19, 2022
- [AD 2021-21-04](https://openairdocs.org/ad/2021-21-04): Powerplant · Bombardier BD-700-1A10 and BD-700-1A11. Effective Dec 8, 2021
- [AD 2021-10-22](https://openairdocs.org/ad/2021-10-22): Fuel · Bombardier BD-700-1A10. Effective Jul 6, 2021
- [AD 2021-08-11](https://openairdocs.org/ad/2021-08-11): Flight controls · Bombardier BD-700-1A10 and BD-700-1A11. Effective Apr 27, 2021
- [AD 2021-03-17](https://openairdocs.org/ad/2021-03-17): Lights · Bombardier BD-700-1A10. Effective Mar 30, 2021

All 89: https://openairdocs.org/tcds/T00003NY/ads.md

## Registered aircraft by registry model (OpenAirDocs)

- [Bombardier BD-700-1A10](https://openairdocs.org/model/bombardier-bd-700-1a10): 372 aircraft (registry code 1390006)
- [Bombardier BD-700-1A11](https://openairdocs.org/model/bombardier-bd-700-1a11): 149 aircraft (registry code 1390022)
- [Bombardier BD-700-2A12](https://openairdocs.org/model/bombardier-bd-700-2a12): 137 aircraft (registry code 1390052)
- [Bombardier Aerospace BD-700-1A10](https://openairdocs.org/model/bombardier-aerospace-bd-700-1a10): 1 aircraft (registry code 1390085)

## STCs approved under this data sheet (462, first 50)

- [STC ST12509WI](https://openairdocs.org/stc/ST12509WI): Change to Layout of Passenger Accommodations. Duncan Aviation, Inc.
- [STC ST04766NY](https://openairdocs.org/stc/ST04766NY): Installation of LAI Cabin Windows on Bombardier Inc.. Lee Aerospace, Inc.
- [STC ST04612CH](https://openairdocs.org/stc/ST04612CH): Installation of a SpaceX Starlink Aviation System. Nextant Aerospace
- [STC ST12507IB](https://openairdocs.org/stc/ST12507IB): Iridium Antenna relocation. Q.C.M. DESIGN GmbH
- [STC ST01418NY](https://openairdocs.org/stc/ST01418NY): Interior Completion Modification IAW Aero Consulting Services Modification Data Summary C88100, Rev B dated 11/30/01. Approved for serial number 9068 ONLY.. Bombardier Inc.
- [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc.
- [STC ST00952LA](https://openairdocs.org/stc/ST00952LA): Installation of Mass Systems fire extinguisher cartridges as replacements for Kidde fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON LLC d/b/a MASS Systems
- [STC ST12362IB](https://openairdocs.org/stc/ST12362IB): Ferry Kit Lift Raft installation equipment must be installed in accordance with Transport Canada Civil Aviation (TCCA) approved Bombardier Inc. Modification Data Summary RAZ-BM700-323 Rev--, dated July 16, 2024, or later TCCA approved revision.. Bombardier Inc.
- [STC ST12269WI](https://openairdocs.org/stc/ST12269WI): Installation of a supplemental cooling system. Learjet Inc.
- [STC ST12183WI](https://openairdocs.org/stc/ST12183WI): Installation of Outer Mold Line modifications, MZFW increase and related avionics updates. Learjet Inc.
- [STC ST12188WI](https://openairdocs.org/stc/ST12188WI): Relocation of the DME 1, DME 2 (and transceiver), ATC 2, and lower directional TCAS antennas. Learjet Inc.
- [STC ST12189WI](https://openairdocs.org/stc/ST12189WI): Relocation of the lower anti-collision light and installation of an additional beacon light. Learjet Inc.
- [STC ST03199NY](https://openairdocs.org/stc/ST03199NY): Installation of ABC Completions Electronic Flight Bag Display Mounts and DAC International GDC-64. Delta Engineering Corporation
- [STC ST12270IB](https://openairdocs.org/stc/ST12270IB): Installation of Gogo Galileo Satcom System. Q.C.M. DESIGN GmbH
- [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc.
- [STC ST04754NY](https://openairdocs.org/stc/ST04754NY): Installation of LAI Windshields. Lee Aerospace Inc.
- [STC ST12078IB](https://openairdocs.org/stc/ST12078IB): Installation of wiring provisions for a subsequent interior completion. Bombardier Inc.
- [STC ST12029CH](https://openairdocs.org/stc/ST12029CH): Installation of Gogo MB13 antennas. Premier Air Center, LLC d/b/a West Star Aviation
- [STC ST00240MC](https://openairdocs.org/stc/ST00240MC): The installation of wing internal hardpoints on the Bombardier BD-700-1A10. Learjet Inc.
- [STC ST12022IB](https://openairdocs.org/stc/ST12022IB): Installation of Interior Completion, Cabin Reconfiguration. Bombardier Inc.
- [STC ST00941LA](https://openairdocs.org/stc/ST00941LA): Installation of floor proximity emergency escape path marking system.. Bruce Aerospace Inc.
- [STC ST02472AT](https://openairdocs.org/stc/ST02472AT): Installation of a mini Quick Access Recorder (QAR) model MKI, MKII, or MKIII. Aircraft Systems and Manufacturing Inc.
- [STC ST04677NY](https://openairdocs.org/stc/ST04677NY): Installation of Demonstration of Transmitting Personal Electronic Device (TPED) Tolerance. Bombardier Inc.
- [STC ST09931AC](https://openairdocs.org/stc/ST09931AC): Installation of an Aspire 400 Satcom System. L2 Aviation
- [STC ST11916IB](https://openairdocs.org/stc/ST11916IB): Modification of the Miscellaneous Cabin Installations and Entertainment System Upgrade. Bombardier Inc.
- [STC ST03759NY](https://openairdocs.org/stc/ST03759NY): Installation of INGENIO Cockpit Tripod Electronic Flight Bag (EFB) Mount. INGENIO Aerospace Inc.
- [STC ST02032WI](https://openairdocs.org/stc/ST02032WI): Installation of Gogo Business Aviation AVANCE L5/X3 System or Optional AVANCE L5 System with MB13 antennas. Duncan Aviation Inc.
- [STC ST04591NY](https://openairdocs.org/stc/ST04591NY): Structural integration and installation of Iridium Satcom Antenna. ALAMO Engineering GmbH
- [STC ST11840WI](https://openairdocs.org/stc/ST11840WI): Change to Layout of Passenger Accommodations (LOPA). Duncan Aviation Inc.
- [STC ST00079IB](https://openairdocs.org/stc/ST00079IB): Integration of Halon-free Portable Fire Extinguisher HAFEX. UMLAUT ENGINEERING GMBH
- [STC ST04561CH](https://openairdocs.org/stc/ST04561CH): Installation of a Latitude Technologies Corporation DL-150 Satellite Data Unit (SDU) and Iridium Antenna. West Star Aviation
- [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH
- [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC
- [STC ST02022WI](https://openairdocs.org/stc/ST02022WI): Installation of a Bombardier Smart Router. Learjet Inc.
- [STC ST00046MC-D](https://openairdocs.org/stc/ST00046MC-D): Installation of structural and electrical provisions for communications equipment. Learjet Inc.
- [STC ST00187MC](https://openairdocs.org/stc/ST00187MC): Installation of a Raytheon APX-119 Transponder System with/without a Honeywell H-764 EGI. Learjet Inc.
- [STC ST00208IB](https://openairdocs.org/stc/ST00208IB): Installation of Fuel Recirculation System Modification. Bombardier Aerospace
- [STC ST04159CH](https://openairdocs.org/stc/ST04159CH): Upgrade of Honeywell Primus II Communications Units RCZ-8XX Transponders to support Certification of Automatic Dependent Surveillance -Broadcast (ADS-B) Out. CMD Flight Solutions LLC
- [STC ST01057WI](https://openairdocs.org/stc/ST01057WI): Installation of a Vision Safe Emergency Vision Assurance System (EVAS).. VisionSafe LLC
- [STC ST00190IB](https://openairdocs.org/stc/ST00190IB): Installation of a Satcom Iridium Datalink Unit with FANS 1/A+ capability and removal of the installed
Inmarsat Swift 64 satcom system. ALAMO ENGINEERING GmbH
- [STC ST00180IB](https://openairdocs.org/stc/ST00180IB): Installation of Go-Go 4G to 5G Upgrade. Flying Colours Corp.
- [STC ST04268NY](https://openairdocs.org/stc/ST04268NY): Replacement of Honeywell DU-870 display units with DU-875 Elite display units with basic functions. ALAMO ENGINEERING GmbH
- [STC ST00175IB](https://openairdocs.org/stc/ST00175IB): Installation of Interior Modifications. Innotech Aviation a Division of IMP Group Limited
- [STC ST00167IB](https://openairdocs.org/stc/ST00167IB): Installation of Ku-Band Satcom with TMA. ALAMO ENGINEERING GmbH
- [STC ST04575AT](https://openairdocs.org/stc/ST04575AT): Installation of the Rockwell Collins ALT-1000+/ -4000+ with 5G Filtering. Chippewa Aerospace Inc.
- [STC ST00126IB](https://openairdocs.org/stc/ST00126IB): Replacement of Halon agent with alternate Halon-free Portable Fire Extinguisher agent. AMAC Aerospace Switzerland AG
- [STC ST02302CH](https://openairdocs.org/stc/ST02302CH): Install ERDA model 7004 HI-LO table with slide top. Collins Aerospace
- [STC ST01970WI](https://openairdocs.org/stc/ST01970WI): Installation of an Aircraft Health Management System (AHMS). Learjet Inc.
- [STC ST00122IB](https://openairdocs.org/stc/ST00122IB): Installation of Satellite Communications (SATCOM). Bombardier Inc.
- [STC ST02012WI](https://openairdocs.org/stc/ST02012WI): Upgrade of Gogo Business Aviation AVANCE L5 to AVANCE L5/X3 System with MB13 Antennas. Duncan Aviation Inc.

All 462: https://openairdocs.org/tcds/T00003NY/stcs.md

## PMA parts (OpenAirDocs) (1,613, newest 50)

Current parts manufacturer approvals (PMA): parts the FAA has approved companies to make as replacements or modifications. Each record lists its models as free text; OpenAirDocs matched them to this data sheet's models, so check the FAA record before relying on it. Newest first.

- [NT0079-KDL0-0500](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID172121873520261026180300.0001): Kit Data List (Block 3.0 & 5.0). Flexjet LLC · PMA PQ04311CE · Modification part · For BD-700-1A11 · Oct 26, 2026
- [9143FR-0325](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID194868012120260909221038.0001): Corrosion Prevention Sealing Tape. 3M Aerospace · PMA PQ04414CE · Modification part · For BD-700-1A10, BD-700-1A11, BD-700-2A12 · Jul 7, 2026
- [No part number](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID180824568520260909221037.0001): 3M Aerospace · PMA PQ04414CE · For BD-700-2A12 · Jul 7, 2026
- [No part number](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID145730438120260909221034.0001): 3M Aerospace · PMA PQ04414CE · For BD-700-2A12 · Jul 7, 2026
- [9143FR-0315](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID109435775720260909221037.0001): Corrosion Prevention Sealing Tape. 3M Aerospace · PMA PQ04414CE · Modification part · For BD-700-1A10, BD-700-1A11, BD-700-2A12 · Jul 7, 2026
- [9143FR-0200](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID100760361520260909221037.0001): Corrosion Prevention Sealing Tape. 3M Aerospace · PMA PQ04414CE · Modification part · For BD-700-1A10, BD-700-1A11, BD-700-2A12 · Jul 7, 2026
- [800-0043-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID116491177420260826223157.0001): COMBI OVEN DOOR BACK ASSY. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0043-01 · For BD-700-1A10, BD-700-2A12 · Jun 25, 2026
- [800-3003-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID110019921620260826223157.0001): BEZEL HMI PAINTED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-3003-01 · For BD-700-2A12 · Jun 25, 2026
- [L305610-20629](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID176937879420260705233751.0001): Cup. Timken Corporation · PMA PQ4105CE · Replaces L305610-20629 · For BD-700-1A10 · Jun 4, 2026
- [L305649-20629](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID163372519620260705233751.0001): Cone. Timken Corporation · PMA PQ4105CE · Replaces L305649-20629 · For BD-700-1A10 · Jun 4, 2026
- [68-216-OAA](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID108049960920260729141225.0001): O-Ring. Omega Aircraft Articles LLC · PMA PQ4191CE · Replaces 68-216 · For BD-700-1A10, BD-700-1A11, BD-700-2A12 · Jun 1, 2026
- [243020K-1](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID192065634920260826222249.0001): Installation Kit, aviONS Panel Assembly. Aircraft Systems and Manufacturing · PMA PQ0601SW · Modification part · For BD-700-1A10, BD-700-1A11, BD-700-2A12 · May 28, 2026
- [LSM-500-111](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID169772913220260909145846.0001): Boom Beam Instl Global Express, Wing Mount Ldg/ Taxi Lights. Whelen Aerospace Technologies · PMA PQ1372CE · Modification part · For BD-700-1A10, BD-700-1A11 · May 22, 2026
- [800-0335-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID195000949020260705232924.0001): FRONT FACE COVER. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0335-01 · For BD-700-2A12 · Apr 29, 2026
- [400-1795-02](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID182665460720260705232919.0001): TANK ASSEMBLY 1603 TOP - FILL COFFEE BREWER. Safran Cabin Inc. · PMA PQ1176NM · Replaces 400-1795-02 · For BD-700-1A10 · Apr 29, 2026
- [800-1481-02](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID165835912120260705232925.0001): DOOR WATER TANK ACCESS. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-1481-02 · For BD-700-1A10, BD-700-2A12 · Apr 29, 2026
- [800-2272-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID159081896220260705232925.0001): PLATE ADAPTER CHASSIS. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2272-01 · For BD-700-2A12 · Apr 29, 2026
- [800-2661-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID159019491720260705232926.0001): CARAFE LID PAINTED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2661-01 · For BD-700-2A12 · Apr 29, 2026
- [300-1776-02](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID151191597720260705232915.0001): CARAFE ASSEMBLY. Safran Cabin Inc. · PMA PQ1176NM · Replaces 300-1776-02 · For BD-700-1A10 · Apr 29, 2026
- [800-0484-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID145184908720260705232924.0001): DRIP STOP VALVE PLUNGER. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0484-01 · For BD-700-2A12 · Apr 29, 2026
- [800-2698-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID139939810820260705232927.0001): SPRING CLIP SEAL RETAINER. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2698-01 · For BD-700-1A10, BD-700-2A12 · Apr 29, 2026
- [800-3298-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID120761534620260705232928.0001): OVEN TRAY. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-3298-01 · For BD-700-1A10, BD-700-2A12 · Apr 29, 2026
- [400-1798-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID110255373120260705232920.0001): HEATER CASTING ASSEMBLY 1603 TOP FILL COFFEE BREWER. Safran Cabin Inc. · PMA PQ1176NM · Replaces 400-1798-01 · For BD-700-1A10 · Apr 29, 2026
- [800-0511-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID107471730320260705232924.0001): RESERVOIR TANK LID. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0511-01 · For BD-700-2A12 · Apr 29, 2026
- [400-2641-04](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID101574153020260705232923.0001): BASE COVER. Safran Cabin Inc. · PMA PQ1176NM · Replaces 400-2641-04 · For BD-700-1A10 · Apr 29, 2026
- [N2402](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID115032308220260423175245.0001): AC Dimmer. Aircraft Lighting International · PMA PQ2043NE · Replaces AL-2402, AL-2502 · For BD-700-1A10 · Mar 27, 2026
- [2940026-201](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID128348324620260608185749.0001): Valve, Shutoff, Motor Op. Parker Hannifin Corporation · PMA PQ1268NM · Replaces GP422-1404-13 · For BD-700-1A10, BD-700-1A11 · Jan 13, 2026
- [RFS170-584-1](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID106420382320251124155007.0001): Insert. Rapco Fleet Support Inc · PMA PQ2386CE · Replaces 170-584-1 · For BD-700-1A10, BD-700-1A11 · Nov 17, 2025
- [AAP-3502129-1](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID190104461620251125143635.0001): Bearing. Approved Air Parts, LLC · PMA PQ4173NE · Replaces Honeywell 3502129-1 · For BD-700-1A10, BD-700-1A11 · Nov 6, 2025
- [00020-2710-0004](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID157518565520251114175729.0001): Computer, Stall Protection. Rosemount Aerospace Inc · PMA PQ2034CE · Replaces GH582-3001-19 · For BD-700-1A11 · Oct 29, 2025
- [LAGC331-0001-015](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID113750214120250827133055.0001): Windshield Assy, LH. Lee Aerospace, Inc. · PMA PQ3766CE · Modification part · For BD-700-1A10, BD-700-1A11 · Aug 26, 2025
- [LAGC331-0001-016](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID109251676220250827133056.0001): Windshield Assy, RH. Lee Aerospace, Inc. · PMA PQ3766CE · Modification part · For BD-700-1A10, BD-700-1A11 · Aug 26, 2025
- [800-0542-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID197175986820260113213037.0001): PANEL TOP. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0542-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2803-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID197147269020260113213040.0001): SUPPORT DOOR COVER LHH. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2803-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2696-05](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID189177744420260113213039.0001): OVEN DOOR COVER TEXTURED R7159. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2696-05 · For BD-700-2A12 · Aug 13, 2025
- [800-3232-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID187724026020260113211654.0001): BREW HEAD BOTTOM PLATE. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-3232-01 · For BD-700-2A12 · Aug 13, 2025
- [800-1481-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID185335666720260113213037.0001): DOOR WATER TANK ACCESS SATIN NICKEL BRUSHED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-1481-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2970-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID184264001920260113213041.0001): LINER COMBI OVEN LHH (LEFT HAND HINGE). Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2970-01 · For BD-700-2A12 · Aug 13, 2025
- [800-0336-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID181842135120260113213037.0001): FRONT FACE BOTTOM LIP SATIN NICKEL BRUSHED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0336-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2282-04](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID180001913820260113213039.0001): DOOR FRONT ASSY BLACK ANODIZE TEXTURED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2282-04 · For BD-700-2A12 · Aug 13, 2025
- [800-0248-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID177541919320260113213035.0001): FASCIA PANEL SATIN NICKEL         BRUSHED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0248-01 · For BD-700-2A12 · Aug 13, 2025
- [800-0252-02](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID177034628520260113213036.0001): FACIAL PANEL BLACK BRUSHED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0252-02 · For BD-700-2A12 · Aug 13, 2025
- [800-0074-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID174700075620260113213034.0001): PANEL SIDE  LEFT. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0074-01 · For BD-700-2A12 · Aug 13, 2025
- [800-0247-02](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID174627807720260113213035.0001): FASCIA BAR BLACK BRUSHED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0247-02 · For BD-700-2A12 · Aug 13, 2025
- [800-0247-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID172537289420260113213035.0001): FASCIA BAR SATIN NICKEL BRUSHED. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0247-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2879-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID172021720220260113213041.0001): OVEN TRAY. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2879-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2461-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID170605527920260113213039.0001): BOTTOM PANEL ASSY. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2461-01 · For BD-700-2A12 · Aug 13, 2025
- [800-2169-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID170498249020260113213038.0001): LINER CUP HOUSE. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-2169-01 · For BD-700-2A12 · Aug 13, 2025
- [800-0074-02](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID167600490220260113213034.0001): PANEL SIDE RIGHT. Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0074-02 · For BD-700-2A12 · Aug 13, 2025
- [800-0045-01](https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID167545923720260113211652.0001): COMBI DOOR WELDMENT LHH (LEFT HAND HINGE). Safran Cabin Inc. · PMA PQ1176NM · Replaces 800-0045-01 · For BD-700-2A12 · Aug 13, 2025

All 1,613: https://openairdocs.org/tcds/T00003NY/pma.md

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