TCDS T00005NY

Page No. 1 2 3 4 5 6 7 8 9 10 Rev No. 11 12 7 7 11 9 11 12 7 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION T00005NY Revision No. 12 Bombardier Inc. BD-100-1A10 July 2, 2019 TYPE CERTIFICATE DATA SHEET NO. T00005NY This data sheet which is part of Type Certificate No. T00005NY, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations (FAR). Type Certificate Holder: Bombardier Inc. 800 boul. René Lévesque West Montreal, Quebec, Canada H3B1Y8 I - Model BD-100-1A10, (Transport Category), Approved June 4, 2003 by the FAA and May 30, 2003, by Transport Canada Civil Aviation with Canadian type certificate number A-234 ENGINES Two Honeywell AS907-1-1A for S/N 20002 to 20500, or two Honeywell AS907-2-1A for S/N 20501 and subsequent, engine type certificate number E00010LA FUEL Type Specifications Canada U.S.A. U.K. Jet A CAN2-3.23 ASTM D1655 D. Eng RD2494 Jet A-1 CAN2-3.23 ASTM D1655 D. Eng RD2494 OIL Engine, APU: Refer to Aircraft Maintenance Manual, Bombardier Publication BD 100 AMM, Chapter 12. AS907-1-1A ENGINE LIMITS CONDITIONS Refer to Limits Table in the AFM (CH 300 AFM) AS907-2-1A ENGINE LIMITS CONDITIONS Refer to Limits Table in the AFM (CH 350 AFM) OIL TEMPERATURE °C °F Minimum for Starting (ground) -40 -40 Minimum before accelerating above idle N/A N/A Maximum Continuous 138 280 Maximum Permissible (transient, 2 minutes) 154 309 Page 2 of 11 T00005NY OIL PRESSURE Take-off Power (minimum) * Steady State Idle (minimum) 28 psi * Oil pressure is not regulated and pressure limits varies with N 2 speeds APU Honeywell 36-150[BD] APU LIMITS Maximum RPM: 110% Maximum EGT: °C °F Starting 512-1024 954-1875 Running 594-714 1101-1317 AIRSPEED LIMITS (IAS) S/N 20002 - 20500 S/N above 20501 S/N 20813 and subsequent & 20501 to 20812, incorporating SB 350−27−008, Rudder Travel Increase (See Flight Manual Supplement 11, SFO, for additional limitations) VMO and MMO (Maximum Operating): m.p.h. knots Mach m.p.h. knots Mach m.p.h. knots Mach Sea Level to 8000 ft. 345 300 - 345 300 - 345 300 - 8001 ft. to 29475 ft. 368 320 - 368 320 - 368 320 - Above 29475 ft. - - 0.83 - - 0.83 - - 0.83 VFE 10° 242 210 - 242 210 - 242 210 - 20° 242 210 - 242 210 - 242 210 - 30° 201 175 - 201 175 - 201 175 - VD and MD Sea Level to 25525 ft. 437 380 - 437 380 - 437 380 - Above 25525 ft. - - 0.90 - - 0.90 - - 0.90 See Flight Manual for variation of Va with altitude and aircraft weight VMCA Flap 10° 122 106 - 127 110 - 127 110 - Flap 20° 117 102 - 125 109 - 125 109 - VMCG Flap 10° 128 111 - 132 115 - 132 115 - Flap 20° 128 111 - 131 114 - 125 109 - VLO (EXT) 288 250 - 288 250 - 288 250 - VLO (RET) 230 200 - 230 200 - 230 200 - VLE 288 250 - 288 250 - 288 250 - C. G. RANGE See Figure 1.0, Longitudinal C.G. Envelope MRW=Maximum Ramp Weight MTOW= Maximum Takeoff Weight MLW=Maximum Landing Weight MZFW=Maximum Zero Fuel Weight MFW=Minimum Fuel Weight DATUM FS 0.0 located at 195 in. Fwd of the aircraft nose Page 3 of 11 T00005NY MEAN AERO- DYNAMIC CHORD 112.2 in (MAC leading edge at fuselage station 556.67 in.) LEVELING MEANS Plumb bob and target in the aft equipment bay at FS 755.5 and RBL 1.0 MAXIMUM WEIGHTS (S/Ns up to 20500) (See Figure 1) (See Note 1) lb. kg. Max. Taxi and Ramp 38 650 17 530 Max. Takeoff 38 500 17 460 Max. Landing 33 750 15 310 Max. Zero Fuel 26 100 11 840 INCREASED MAXIMUM WEIGHT WITH M.S.100T010126 BB100T010126 & S.B. 100-11-01 (See Figure 2)(See Note 1) lb. Kg. Max. Taxi and Ramp 39 000 17 690 Max. Takeoff 38 850 17 622 Max. Landing 33 750 15 310 Max. Zero Fuel 27 000 12 247 MAXIMUM WEIGHTS (S/N 20501 and subs) (See Figure 3) (See Note 1) lb. Kg. Max. Taxi and Ramp 40 750 18 484 Max. Takeoff 40 600 18 416 Max. Landing 34 150 15 490 Max. Zero Fuel 28 200 12 791 MINIMUM CREW Two (Pilot and Co-pilot) MAXIMUM OCCUPANTS 19 (including the crew and no more than 16 passengers) See Note 4 FUEL CAPACITY Load Weight** Usable U.S. Gal. liters lb. kg 2 main tanks (each) 1 048 3 967 7 074 3 209 Total 2 096 7 934 14 150 6 418 * Total Unusable (drainable) 7.5 28.2 50.4 22.8 * Total Undrainable 6.4 24.3 43.4 19.7 * See NOTE 3 ** Assuming a fuel density of 6.75 lbs/U.S. Gal. OIL CAPACITY Load Weight U.S. Qts. liters lb. kg. Left Engine 6.0 5.7 12.6 5.7 Right Engine 5.0 4.7 10.4 4.7 Total 11.0 10.4 23.0 10.4 Usable per Engine 1.7 1.6 3.5 1.6 MAX. OPERATING Take off and landing: 10 000 ft Page 4 of 11 T00005NY ALTITUDE En route: 45 000 ft CONTROL SURFACE Rudder 30° Left 30° Right MOVEMENTS Horizontal Stabilizer 2° LE Up 12° LE Down Aileron 18° TE Up 18° TE Down Elevator 24° TE Up 18° TE Down Ground spoilers 60° Up - Multi-function spoilers (Inboard to Outboard) 45 ° Up - TYPE CERTIFICATION APPLICATION DATE 28 June 1999 SERIAL NUMBERS ELIGIBLE 20002 and subsequent SERVICE INFORMATION Service Bulletins, structural repair manuals, vendor manuals, overhaul and maintenance manuals, and aircraft flight manuals which contain a statement that the document is Transport Canada approved or Transport Canada approved through the Manufacturers Design Approval Representative are accepted by the FAA and are considered FAA approved. (These approvals pertain to the design data only). APPROVED PUBLICATIONS S/N 20002 to 20500 (a) Airplane Flight Manual (AFM), Bombardier Publication CSP 100 -1, dated May 30, 2003 and subsequent approved revisions. (b) Drawing List, Bombardier Publication RAL-100-0001, Issue A and subsequent approved revisions. (c) Time Limits/Maintenance Checks Manual, Bombardier Publication CH 300 TLMC and subsequent approved revisions contains the Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. See NOTE 3 (d) Structural Repair Manual (SRM), Bombardier Publication CH 300 SRM and subsequent approved revisions. See NOTE 3 S/N 20501 and subs (a) Airplane Flight Manual (AFM), Bombardier Publication CH 350 AFM, dated June 24, 2014 and subsequent approved revisions. (b) Drawing List, Bombardier Publication RAL-100-0001, Issue A and subsequent approved revisions. (c) Time Limits/Maintenance Checks Manual, Bombardier Publication CH 350 TLMC and subsequent approved revisions contains the Certification Maintenance Tasks, Life Limited Parts and Damage Tolerant Inspections. See NOTE 3 (d) Structural Repair Manual (SRM), Bombardier Publication CH 350 SRM and subsequent approved revisions. See NOTE 3 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: Page 5 of 11 T00005NY "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-234 and includes the minimum type design defined in document RAZ-BA100-124 Issue A or subsequent approved revisions and RAL-100-0001 Issue A or subsequent approved revisions as being required to comply with the basis for the U.S. Type Certificate No. T00005NY, and is in a condition for safe operation. " The approved type design appropriate to the "as delivered" configuration of a particular BD-100-1A10 airplane is defined in the document RAL-100- XXXX. (XXXX represents the Serial Number for the airplane concerned). 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. CERTIFICATION BASIS FAR Part 25, including: Amendments 25-1 through 25-101, Amendment 25-103 and Amendment 25-105. There are no exceptions. Exemptions: (1) Static testing requirements of FAR 25.1435(b)(1), Hydraulic System Proof Pressure Testing, Exemption No. 7508, Regulatory Docket No. FAA-2001-9034, issued April 18, 2001. (2) (3) General Occupant Protection of FAR 25.785(b), Multi-Place Side Facing Divans, Exemption No. 7884A, Regulatory Docket No. FAA-2002- 11998, issued September 2, 2003. Exemption No. 11013 , FAR 25.901(c) Uncontrollable High Thrust (See Note 8 and Note 9) Additional FAA Requirements: (1) FAR Part 36 dated February 3, 2006, as amended through Amendment 36 -28 inclusive. (2) Applicable portions of FAR 34 dated November 5, 2002, as amended through Amendment 34 -3 inclusive. Page 6 of 11 T00005NY (3) Special Conditions: High Intensity Radiated Fields (HIRF), Docket No. NM243, Special Condition No. 25-226-SC, effective date 1/9/2003. Approach and Go-around use of Automatic Power Reserve, Docket No. NM255, Special Conditon No. 25-03-04-SC, effective date May 28, 2003 Limit Engine Torque Loads for Sudden Engine Stoppage, Docket No. NM245, Special Condition No. 25-229-SC, effective date March 6, 2003 Side Facing Single Occupancy Seats, Docket No. NM259, Special Condition No. 25-249-SC, effective October 6, 2003 No. 25-659-SC, Non-Rechargeable Lithium Batteries, effective to design changes applied for after May 12, 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 25.103 and several other FAR’s for the use of 1-g stall speed and reduced reference speeds (documented in Transport Airplane Directorate Equivalent Level of Safety (ELOS) Memo No. TC2500NY-T-F-1) (2) FAR 25.933(a)(1)(ii) Capability of Continued Safe Flight and Landing under any possible position of the Thrust Reverser System (documented in Transport Airplane Directorate ELOS Memo No. TC2500NY -T-P-1) (3) FAR 25.1203, FAR 25.1207 Engine Thrust Reverser Zone Fire Detection (documented in Transport Airplane Directorate ELOS Memo No. TC2500NY-T-P-3) (4) FAR 25.177(c) Static lateral-directional stability, (documented in Transport Airplane Directorate (TAD) ELOS Memo No. TC2500NY-T- F-2) (5) FAR 25.811(d)(1) and 25.812(b)(1)(i) Emergency Exit Marking and Locator Signs (documented in Transport Airplane Directorate Equivalent Level of Safety (ELOS) Memo No. ANM-113-04-01) (6) FAR 25.813(e) Lavatory Door (documented in Transport Airplane Directorate Equivalent Level of Safety (ELOS) Memo No. ST4805NY- SE-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. EQUIPMENT The basic equipment as prescribed in the applicable airworthiness requirements (see Certification Basis) must be installed in the aircraft for certification. NOTE 1 (a) A current weight and balance report including the list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. Page 7 of 11 T00005NY (b) 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 unsuable fuel defined in the Fuel Capacity section must be included in the empty weight of the airplane. NOTE 2 All placards must be installed in accordance with Bombardier Drawings: 1001100001, 1001100002, 1001100003 and 1001100004. NOTE 3 The airplane life limits and repetitive inspections for components and equipment and information essential for proper maintenance, ar e listed in Bombardier Publication BD 100 TLMC. These limitations may not be changed without FAA Engineering approval. Instructions for Continued Airworthiness consist of the following Publications: a) BD 100 AMM, Aircraft Maintenance Manual (Publication s No. CH300 AMM and CH350 AMM) b) BD100 TLMC, Time Limits/Maintenance Checks Manual (Publications No. CH300 TLMC and CH350 TLMC) c) BD 100 SRM, Structural Repair Manual (Publications No. CH300 SRM and CH350 SRM) d) BD 100 NDT, Non-Destructive Testing Manual (Publications No. CH300 NDTM and CH350 NDTM) NOTE 4 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 provisio ns are incorporated in accordance with the Type Certificate Basis. NOTE 5 Bombardier Aerospace report RAZ-BA-100 provides guidance to completion centers regarding compliance with the basis of certification for the BD-100- 1A10 Challenger 300 with a completed interior. NOTE 6 Compliance with FAR 25.105(c)(1) and 25.125(b), associated with Takeoff and Landing Performance on Unpaved Runways, has not been demonstrated. NOTE 7 “Challenger 300” is a marketing designation for the BD -100-1A10 up to aircraft S/N 20500. “Challenger 350” is a marketing designation for the BD - 100-1A10 starting at aircraft S/N 20501. NOTE 8 The FAA has concluded that the occurrence of any uncontrollable high -thrust failure conditions, or any of the associated causal failures listed in Section 05- 10-00 of the CH350 TLMC, Time Limits/Maintenance Checks Manual may endanger the safe operation of an airplane , and hence are reportable under FAR 121.703(c), 125.409(c), and 135.415(c). Page 8 of 11 T00005NY NOTE 9 Bombardier has complied with the conditions in TLE 11013 with the incorporation of Modification Summary 100T010874. TLE 11013 permanently exempts the Model BD-100-1A10 airplane from single failures within the Airplane Throttle System (ATS) and single failures on approach below 400 feet from full compliance with 25.901(c) as it pertains to UHT. No retrofit is required. The FAA has concluded that the occurrence of any uncontrollable high-thrust failure conditions, or any of the associated causal failures listed in Section 05- 10-00 of the CH350 TLMC, Time Limits/Maintenance Checks Manual 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 Regulation 121.703(c), 125.409(c), and 135.415(c). Page 9 of 11 T00005NY Figure 1.0 LONGITUDINAL C.G. ENVELOPE 40000 - 17980 MRW 38 650 lb (17 530 kg) MTOW 38 500 Ib (17 465 kg) 38000 - 16980 36000 - 15980 34000 MLW 33 750 Ib (15 310 kg) 14980 Aircraft Weight (Ib) 32000 Aircraft Weight (kg) 13980 30000 - 12980 28000 MZFW 26 100 lb (11 840 kg) - 11980 26000 - 10980 24000 MFW 23 100 lb (10 480 kg) 22000 + + 9980 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 % MAC Page 10 of 11 T00005NY Figure 2.0 LONGITUDINAL C.G. ENVELOPE (A/Cs with M.S.100T010126, BB100T010126 & S.B. 100-11-01) 22000 24000 26000 28000 30000 32000 34000 36000 38000 40000 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 % MAC Aircraft Weight (lb) 10000 11000 12000 13000 14000 15000 16000 17000 18000 Aircraft Weight (kg) MRW 39 000 lb (17 690 kg) MTOW 38 850 lb (17 622 kg) MLW 33 750 lb (15 309 kg) MZFW 27 000 lb (12 247 kg) MFW 23 100 lb (10 478 kg) Page 11 of 11 T00005NY Figure 3.0 LONGITUDINAL C.G. ENVELOPE (S/N 20501 and subsequents) 42000 19000 MRW 40 750 Ib (18 484 kg) MTOW 40 600 Ib (18 416 kg) 40000 - 18000 38000 - 17000 36000 16000 MLW 34 150 lb (15 490 kg) 34000 Aircraft Weight (Ib) 32000 - 15000 Aircraft Weight (kg) 14000 30000 MZFW 28 200 Ib (12 791 kg) - 13000 28000 - 12000 00092 MFW 24 800 lb (11 249 kg) - 11000 0O0+Z 0002Z 00001 + 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 % MAC