# TCDS A3EU: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 44 - Revised: November 6, 2017 - Product: Aircraft, Large Airplane - Certification basis: Part 25, CAR 10, CAR 4b - Registered aircraft: 642, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b7/71/b771840f4c82b7d83a1ca8c836666a50b46b7c63ab48242c3f9090e46a670dae - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/5871EF1C07FE2CFC862581D300724B70.0001 - Page: https://openairdocs.org/tcds/A3EU ## Models (50) As the data sheet lists them. - Hawker 800 - BAe.125 Series 1000A - BAe.125 Series 800A (C-29A) - HS.125 Series 3B/RB - HS.125 Series 401B - HS.125 Series 600A - HS.125 Series 600B/2 - HS.125 Series 403A(C) - HS.125 Series 600B/1 - Hawker 750 - HS.125 Series 700A - DH.125 Series 1A/R-522 - BH.125 Series 400A - Hawker 850XP - HS.125 Series 700B - HS.125 Series 600B - HS.125 Series 1B/S-522 - HS.125 Series 400A - BH.125 Series 600A - HS.125 Series F3B/RA - DH.125 Series 400A - Hawker 900XP - DH.125 Series 3A/R - HS.125 Series F403B - DH.125 Series 1A - HS.125 Series 403B - DH.125 Series 1A-522 - HS.125 Series 1B-522 - HS.125 Series F3B - DH.125 Series 3A - DH.125 Series 1A/S-522 - BAe.125 Series 1000B - HS.125 Series 400B/1 - BAe.125 Series 800A - HS.125 Series 400B - HS.125 Series 3B - BAe.125 Series 800A (U-125) - BAe.125 Series 800B - Hawker 1000 - HS.125 Series 1B/R-522 - Hawker 800 (U-125A) - Hawker 800XP - DH.125 Series 3A/RA - HS.125 Series 3B/RA - HS.125 Series 3B/R - HS.125 Series 3B/RC - HS.125 Series F400B - HS.125 Series 600B/3 - HS.125 Series F600B - HS.125 Series 1B ## 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. Rev No. 1 44 2 31 3 33 4 25 5 25 6 33 7 31 8 31 9 33 10 31 11 33 12 31 13 31 14 33 15 31 16 33 17 31 18 31 19 33 20 25 21 25 22 31 23 31 24 33 25 31 26 31 27 31 28 31 29 35 30 31 Page No. Rev No. 31 31 32 33 33 31 34 31 35 31 36 33 37 31 38 31 39 33 40 31 41 31 42 31 43 33 44 31 45 31 46 33 47 31 48 31 49 31 50 33 51 31 52 31 53 31 54 35 55 33 56 31 57 31 58 33 59 31 60 31 Page No. Rev No. 61 39 62 35 63 34 64 34 65 41 66 39 67 37 68 44 69 41 70 39 71 38 72 44 73 38 74 40 75 40 76 49 77 39 78 38 79 39 80 38 81 38 82 38 83 38 84 38 85 38 86 38 87 38 88 38 89 38 90 38 Page No. Rev No. 91 42 92 38 93 39 94 44 95 44 96 44 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A3EU Revision 44 Textron Aviation DH.125 Series 1A HS.125 Series F400B HS.125 Series 1B HS.125 Series F403B DH.125 Series 1A-522 BH.125 Series 600A HS.125 Series 1B-522 HS.125 Series 600A DH.125 Series 1A/R-522 HS.125 Series 600B HS.125 Series 1B/R-522 HS.125 Series 600B/1 DH.125 Series 1A/S-522 HS.125 Series 600B/2 HS.125 Series 1B/S-522 HS.125 Series 600B/3 DH.125 Series 3A HS.125 Series F600B HS.125 Series 3B HS.125 Series 700A DH.125 Series 3A/R HS.125 Series 700B HS.125 Series 3B/R BAe.125 Series 800A DH.125 Series 3A/RA BAe.125 Series 800A (C-29A) HS.125 Series 3B/RA BAe.125 Series 800A (U-125) HS.125 Series 3B/RB BAe.125 Series 800B HS.125 Series 3B/RC BAe.125 Series 1000A HS.125 Series F3B BAe.125 Series 1000B HS.125 Series F3B/RA Hawker 800 BH.125 Series 400A Hawker 800 (U-125A) DH.125 Series 400A Hawker 1000 HS.125 Series 400A HS.125 Series 400B Hawker 800XP Hawker 850XP HS.125 Series 400B/1 Hawker 900XP HS.125 Series 401B Hawker 750 HS.125 Series 403A(C) HS.125 Series 403B November 6, 2017 TYPE CERTIFICATE DATA SHEET NO. A3EU This Data Sheet, which is part of Type Certificate No. A3EU prescribes co nditions 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: Textron Aviation Inc. One Cessna Boulevard Wichita, Kansas 67215 Type Certificate Holder Record: Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013. Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016. Type Certificate A3EU was transferred from Raytheon Corporate Jets Inc., 3 Bishop Square, St. Albans Road West, Hatfield, Hertfordshire AL 10 9NE, United Kingdom, to Raytheon Aircraft Company (RAC) on August 1, 1995. Coincident with this transfer, the Federal Aviation Administration (FAA) has accepted the status of State of Design and State of Manufacture as defined A3EU Rev. 44 Page 2 of 105 by Annex 8 to the Convention on International Civil Aviation. Prior to August 1, 1995, products identified under Type Certificate A3EU were approved by the FAA in accordance with the Federal Aviation Regulation appropriate to Imported Products (FAR 21.29). Effective August 1, 1995 and after, these products are to be considered domestic products for the purpose of certification, and Federal Aviation Regulation 21.21 becomes appropriate. Effective May 28, 1999, certain models identified as “B” series that had been previously certified by the UK Civil Aviation Authority were added to Type Certificate A3EU and this Data Sheet. The process for type certification of these aircraft is considered analogous to issuance of export airworthiness approvals, with exceptions, as allowed under 14 CFR 21.325(c). Under that section the requirements that are not met and the differences in configuration, if any, between the product to be exported and the related type certificated product, are listed on the export airworthiness approval as exceptions. The UK certificate d “B” series aircraft can be considered to be the US approved type certificated “A” series with exceptions. The UK approved “B” series are eligible to receive FAA airworthiness certificates and registration for operation in the United States as a US approved “B” series when modified to comply with US standards (i.e. the modification eliminates the exception; see NOTE 50) and when all Airworthiness Directives applicable to the equivalent “A” series have been incorporated. The box in the upper right corner of page 1 ident ifies the FAA Approved Series and Models. The FAA has accepted the responsibility for the promulgation to International Civil Aviation Organization (ICAO) Contracting States of airworthiness information for all such products in accordance with Annex 8. T he Type Certificate Holder designated in this data sheet holds Type Design authority for the production of data associated with all such products. I. Hawker Siddeley Model DH.125 Series 1A (Transport Aircraft), Approved September 25, 1964 (See NOTE 14) Hawker Siddeley Model HS.125 Series 1B (Transport Aircraft), Approved May 28, 1999 (See NOTES 14 & 52) Engines 2 Bristol Siddeley Viper 521 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22 Type 2, ASTM D.1655 Jet B. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (unrestricted) lbs. 3,120 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,120 Maximum permissible engine rotor operating speed 100% (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: Take-off (unrestricted) 695oC Maximum continuous 695oC Maximum for acceleration 695oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 26,800 feet 290 knots MMO (Maximum operating) 26,800 ft. and above 0.735 M A3EU Rev. 44 Page 3 of 105 I. Model DH.125 Series 1A, Model H.S.125 Series 1B (cont’d) Airspeed Limits (IAS) (cont.) VA (Maneuvering) Sea level 181 knots 10,000 ft. 182 knots 20,000 ft. 183 knots 30,000 ft. 195 knots 40,000 ft. 212 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 94 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage lower skin immediately aft of the equipment bay access hatch. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76 in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd of Datum Aft of Datum retracted) In-Flight T.O. & Land Autopilot Autopilot disengaged engaged Wt. Lbs. % SMC In. % SMC In. % SMC In. % SMC In. 21,200 22.40 0.55 23.60 (0.54)* 33.80 9.80 32.60 8.70 20,550 - - - - 34.30 10.20 33.00 9.00 19,000 - - - - 34.10 9.95 32.80 8.82 17,800 18.80 3.78 20.20 2.52 - - - - 16,800 - - - - 33.10 9.10 - - 16,600 - - - - - - 31.60 7.80 13,000 18.00 4.51 20.00 2.71 - - - - 12,350 - - - - 37.50 13.10 35.50 11.30 12,100 18.00 4.51 20.00 2.71 - - - 10,800 - - 26.00 (2.71)* 37.50 13.10 35.50 11.30 *(Aft of Datum) Straight line variation between weights Item (Extending) Moment Change in Lbs. Wing Flaps 15o + 538 25o + 879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear - 1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. A3EU Rev. 44 Page 4 of 105 I. Model DH.125 Series 1A, Model H.S.125 Series 1B (cont’d) Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum Ramp Weight 21,200 lbs. (See NOTE 12) Maximum Brake release weight 21,200 lbs. Maximum Landing Weight 19,550 lbs. Maximum Zero Fuel Weight 13,000 lbs. (See NOTE 12) Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Total 1,231.5 8210 5.79 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible 25013, 25014, 25016 through 25023, 25025 through 25039, 25042, 25043, 25046, 25047, 25051, 25052, 25053, 25057, 25058, 25060, 25063 through 25068, 25070, 25073 through 25075, 25078 through 25080, 25082 through 25110. A3EU Rev. 44 Page 5 of 105 II. Hawker Siddeley Model DH.125 Series 1A-522 (Transport Aircraft), Approved February 3, 1966. (See NOTE 14) Hawker Siddeley Model HS.125 Series 1B-522 (Transport Aircraft), Approved May 28, 1999. (See NOTES 14 & 52) (The DH.125 Series 1A-522 and HS.125 Series 1B-522 aircraft differs from the DH.125 Series 1A and the HS.125 Series 1B aircraft, respectfully, in the following major features: (i) Introduction of Bristol Siddeley Viper 522 engines, (ii) values of MMO increased and VMO decreased.) Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22 Type 2, ASTM D.1655 Jet B. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor 100% Operating speed (5 minutes maximum) (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730oC Maximum continuous 705oC Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 27,800 feet 285 knots MMO (Maximum operating) 27,800 ft. and above 0.750 M VA (Maneuvering) Sea level 181 knots 10,000 ft. 182 knots 20,000 ft. 183 knots 30,000 ft. 195 knots 40,000 ft. 212 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots A3EU Rev. 44 Page 6 of 105 II. Model DH.125 Series 1A-522, Model HS.125 Series 1B-522 (cont’d) Airspeed Limits (IAS) (cont’d) VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage lower skin immediately aft of the equipment bay access hatch. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76 in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd of Datum Aft of Datum retracted) In-Flight T.O. & Land Autopilot Autopilot disengaged engaged Wt. Lbs. % SMC In. % SMC In. % SMC In. % SMC In. 21,200 22.40 0.55 23.60 (0.54)* 33.80 9.80 32.60 8.70 20,550 - - - - 34.30 10.20 33.00 9.00 19,000 - - - - 34.10 9.95 32.80 8.82 17,800 18.80 3.78 20.20 2.52 - - - - 16,800 - - - - 33.10 9.10 - - 16,600 - - - - - - 31.60 7.80 13,000 18.00 4.51 20.00 2.71 - - - - 12,350 - - - - 37.50 13.10 35.50 11.30 12,100 18.00 4.51 20.00 2.71 - - - 10,800 - - 26.00 (2.71)* 37.50 13.10 35.50 11.30 *(Aft of Datum) Straight line variation between weights Item (Extending) Moment Change In. lbs. Wing Flaps 15o + 538 25o + 879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum Ramp Weight 21,200 lbs. (See NOTE 12) Maximum Brake release weight 21,200 lbs. Maximum Landing Weight 19,550 lbs. Maximum Zero Fuel Weight 13,000 lbs. (See NOTE 12) Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance manual. A3EU Rev. 44 Page 7 of 105 II. Model DH.125 Series 1A-522, Model HS.125 Series 1B-522 (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Total 1,231.5 8,210 5.79 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Models DH.125 Series 1A and the HS.125 Series 1B III. Hawker Siddeley Model DH.125 Series 3A (Transport Aircraft), Approved November 7, 1966 Hawker Siddeley Model HS.125 Series 3B (Transport Aircraft), Approved May 28, 1999. (See NOTE 52) (The DH.125 Series 3A aircraft and the HS.125 Series 3B aircraft differs respectively from the DH.125 Series 1A-522 aircraft and the HS.125 Series 1B-522 aircraft in the following major features: (i) increased maximum ramp, brake release, landing and zero fuel weights, (ii) increased Mmo, (iii) Vmo – 285 knots reducing linearly to 273 knots between 27,200 feet and 30,800 feet). Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22f Type 2, ASTM D.1655 Jet B. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes’ maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor 100% Operating speed (5 minutes’ maximum) (13,760 r.p.m.) A3EU Rev. 44 Page 8 of 105 III. Model DH.125 Series 1A-522, Model HS.125 Series 1B-522 (cont’d) Engine Limits (cont’d) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730oC Maximum continuous 705oC Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 27,200 feet and 285 knots decreasing linearly to 273 knots at 30,800 feet MMO (Maximum operating) 30,800 ft. and above (See NOTE 15) 0.765 M VA (Maneuvering) Sea level 185 knots 10,000 ft. 185 knots 20,000 ft. 185 knots 30,000 ft. 195 knots 40,000 ft. 210 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fus elage reference point. The reference point is defined by an eye bolt on the fuselage lower skin immediately aft of the equipment bay access hatch. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for S MC definition, see Approved Flight Manual). A3EU Rev. 44 Page 9 of 105 III. Model DH.125 Series 3A, Model HS.125 Series 3B (cont’d) C.G. Range (Gear and Flaps Fwd of Datum Aft of Datum retracted) In-Flight T.O. & Land Autopilot Autopilot disengaged engaged Wt. Lbs. % SMC In. % SMC In. % SMC In. % SMC In. 21,700 23.64 (0.57)* 24.87 (1.68)* 33.67 9.62 32.44 8.51 21,200 22.40 0.55 23.60 (0.54)* - - - - 20,550 - - - - 34.30 10.20 33.00 9.00 19,000 - - - - 34.10 9.95 32.80 8.82 17,800 18.80 3.78 20.20 2.52 - - - - 16,800 - - - - 33.10 9.10 - - 16,600 - - - - - - 31.60 7.80 13,000 18.00 4.51 20.00 2.71 - - - - 12,350 - - - - 37.50 13.10 35.50 11.30 12,100 18.00 4.51 20.00 2.71 - - - 10,800 - - 26.00 (2.71)* 37.50 13.10 35.50 11.30 *(Aft of Datum) Straight line variation between weights Item (Extending) Moment Change In.Lbs. Wing Flaps 15o + 538 25o + 879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuse lage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum Ramp Weight 21,700 lbs. (See NOTE 12) Maximum Brake Release Weight 21,700 lbs. Maximum Landing Weight 20,000 lbs. Maximum Zero Fuel Weight 13,500 lbs. (See NOTE 12) Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 A3EU Rev. 44 Page 10 of 105 - 10 - III. Model DH.125 Series 3A, Model HS.125 Series 3B (cont’d) Fuel Capacity Usable Fuel Location Volume U.S. Gal Maximum Weight Lbs. Arm In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and Lines 1.5 10 81.00 Total 1,231.5 8,210 5.79 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume U.S. Gal. Maximum Weight Lb. Arm In. Moment In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible 25015, 25062, 25069, 25111 through 25172 IV. Hawker Siddeley Model DH.125 Series 1A/R-522 (Transport Aircraft), Approved August 9, 1967 Hawker Siddeley Model HS.125 Series 1B/R-522 (Transport Aircraft), Approved May 28, 1999. (See NOTE 52) (The DH.125 Series 1A/R-522 aircraft and the HS.125 Series 1B/R-522 aircraft differs respectively from the DH.125 Series 1A-522 aircraft and the HS.125 Series 1B-522 by the incorporation of Modifications No. 251700 and 255640, long-range fuel tank, modified flaps and main landing gear doors.) (See NOTE 10). Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22f Type 2, ASTM D.1655 Jet B. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor 100% Operating speed (5 minutes maximum) (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730oC Maximum continuous 705OC Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% A3EU Rev. 44 Page 11 of 105 - 11 - IV. Model DH.125 Series 1A/R-522, Model HS.125 Series 1B-522 (cont’d) Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 27,800 feet with fuel in long range tank 260 knots from sea level to 27,800 feet with long range tank empty 285 knots MMO (Maximum operating) 27,800 ft. and above 0.750 M VA (Maneuvering) Sea level 189 knots 10,000 ft. 190 knots 20,000 ft. 196 knots 30,000 ft. 202 knots 35,000 ft. 207 knots 40,000 ft. 201 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference p oint is defined by an eye bolt on the fuselage lower skin immediately aft of the equipment bay access hatch. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum retracted) Wt. lbs. % SMC In. % SMC In. 22,200 29.53 (5.89)* 37.87 13.41 22,100 - - 38.00 13.53 21,400 25.53 (2.28)* - - 19,200 - - 37.93 13.47 18,840 - - 34.00 9.92 17,750 22.60 0.37 - - 17,400 - - 33.47 9.44 13,200 23.00 0.00 - - 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. A3EU Rev. 44 Page 12 of 105 - 12 - IV. Model DH.125 Series 1A/R-522, Model HS.125 Series 1B-522 (cont’d) C.G. Range (Gear and Flaps retracted) (cont’d) Item (Extending) Moment Change In. Lbs. Wing Flaps 15o + 538 25o + 879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum Ramp Weight 22,300 lbs. Maximum Brake Release Weight 22,200 lbs. Maximum Landing Weight 19,550 lbs. Maximum Zero Fuel Weight 13,200 lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Long Range Tank 134.5 896 88.70 Total 1,366.0 9,106 13.95 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Volume Maximum Arm Moment Location U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Models DH.125 Series 1A and the HS.125 Series 1B A3EU Rev. 44 Page 13 of 105 - 13 - V. Hawker Siddeley Model DH.125 Series 3A/R (Transport Aircraft), Approved August 9, 1967 Hawker Siddeley Model HS.125 Series 3B/R (Transport Aircraft), Approved May 28, 1999. (See NOTE 52) (The DH.125 Series 3A/R aircraft and the HS.125 Series 3B/R aircraft differs respectively from the DH.125 Series 3A aircraft and the HS.125 Series 3B by the incorporation of Modifications No. 251700 and 255640, long-range fuel tank, modified flaps and main landing gear doors). (See NOTE 10) Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22f Type 2, ASTM D.1655 Jet B. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor 100% Operating speed (5 minutes maximum) (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730oC Maximum continuous 705oC Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 30,800 feet with fuel in long range tank 260 knots from sea level to 27,200 feet with long range tank empty 285 knots decreasing linearly to 273 knots at 30,800 feet. MMO (Maximum operating) 30,800 ft. and above 0.765 M VA (Maneuvering) Sea level 190 knots 10,000 ft. 191 knots 20,000 ft. 197 knots 30,000 ft. 203 knots 35,000 ft. 208 knots 40,000 ft. 201 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots A3EU Rev. 44 Page 14 of 105 - 14 - V. Model DH.125 Series 3A/R, Model HS.125 Series 3B/R (cont’d) Airspeed Limits (IAS) (cont.) VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76 in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 22,700 30.53 (6.79)* 37.20 12.81 22,150 - - 38.00 13.53 21,700 25.80 (2.52)* - - 19,200 - - 37.93 13.47 18,850 - - 34.00 9.92 17,750 22.47 0.48 - - 17,400 - - 33.47 9.44 13,000 23.00 0.00 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. Item (Extending) Moment Change In. Lbs. Wing Flaps 15o + 538 25o + 879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum Ramp Weight 22,800 lbs. Maximum Brake Release Weight 22,700 lbs. Maximum Landing Weight 20,000 lbs. Maximum Zero Fuel Weight 13,700 lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. A3EU Rev. 44 Page 15 of 105 - 15 - V. Model DH.125 Series 3A/R, Model HS.125 Series 3B/R (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Long Range Tank 134.5 896 88.70 Total 1,366.0 9,106 13.95 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lb. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Models DH.125 Series 3A and the HS.125 Series 3B VI. Hawker Siddeley Model DH.125 Series 1A/S-522 (Transport Aircraft), Approved February 15, 1968 Hawker Siddeley Model HS.125 Series 1B/S-522 (Transport Aircraft), Approved May 28, 1999. (See NOTE 52) (The DH.125 Series 1A/S-522 aircraft and the HS.125 Series 1B/S-522 aircraft differs respectively from the DH.125 Series 1A-522 aircraft and the HS.125 Series 1B-522 aircraft by the incorporation of Modification No. 251867 which introduces structural additions enabling the aircraft to be operated to the same limitations as the DH.125 Series 3A or the HS.125 Series 3B aircraft respectively except for the maximum landing weight which remains at 19,550 lbs., and maximum operating altitude). (See NOTE 11). Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP- 22f Type 2, ASTM D.1655 Jet B. (See NOTE 4). A3EU Rev. 44 Page 16 of 105 - 16 - VI. Model DH.125 Series 1A/S-522, Model HS.125 Series 1B/S-522 (cont’d) Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor 100% Operating speed (5 minutes maximum) (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730oC Maximum continuous 705oC Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 27,200 feet and 285 knots decreasing linearly to 273 knots at 30,800 feet MMO (Maximum operating) 30,800 ft. and above (See NOTE 15) 0.765 M VA (Maneuvering) Sea level 185 knots 10,000 ft. 185 knots 20,000 ft. 185 knots 30,000 ft. 195 knots 40,000 ft. 210 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage lower skin immediately aft of the equipment bay access hatch. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 17 of 105 - 17 - VI. Model DH.125 Series 1A/S-522, Model HS.125 Series 1B/S-522 (cont’d) C.G. Range (Gear and Flaps Fwd of Datum Aft of Datum retracted) In-Flight T.O. & Land Autopilot Autopilot disengaged engaged Wt. Lbs. % SMC In. % SMC In. % SMC In. % SMC In. 21,700 23.64 (0.57)* 24.87 (1.68)* 33.67 9.62 32.44 8.51 21,200 22.40 0.55 23.60 (0.54)* - - - - 20,550 - - - - 34.30 10.20 33.00 9.00 19,000 - - - - 34.10 9.95 32.80 8.82 17,800 18.80 3.78 20.20 2.52 - - - - 16,800 - - - - 33.10 9.10 - - 16,600 - - - - - - 31.60 7.80 13,000 18.00 4.51 20.00 2.71 - - - - 12,350 - - - - 37.50 13.10 35.50 11.30 12,100 18.00 4.51 20.00 2.71 - - - 10,800 - - 26.00 (2.71)* 37.50 13.10 35.50 11.30 *(Aft of Datum) Straight line variation between weights Item (Extending) Moment Change In. Lbs. Wing Flaps 15o + 538 25o + 879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum Ramp Weight 21,700 lbs. (See NOTE 12) Maximum Brake Release Weight 21,700 lbs. Maximum Landing Weight 19,550 lbs. Maximum Zero Fuel Weight 13,500 lbs. (See NOTE 12) Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 A3EU Rev. 44 Page 18 of 105 - 18 - VI. Model DH.125 Series 1A/S-522, Model HS.125 Series 1B/S-522 (cont’d) Fuel Capacity Usable Fuel Location Volume Maximum Arm. U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Total 1,231.5 8,210 5.79 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Models DH.125 Series 1A and the HS.125 Series 1B VII. Hawker Siddeley Model DH.125 Series 3A/RA (Transport Aircraft), Approved February 15, 1968 (See NOTE 46) Hawker Siddeley Model HS.125 Series 3B/RA (Transport Aircraft), Approved May 28,1999. (See NOTES 46 & 52) The DH.125 Series 3A/RA aircraft and the HS.125 Series 3B/RA aircraft differs respectively from the DH.125 Series 3A/R aircraft and the HS.125 Series 3B/R by (i) incorporation of Modification No. 251916 which introduces structural additions to permit a maximum zero fuel weight of 14,200 lbs., (ii) a maximum ramp weight of 23,100 lbs. (See NOTE 11) Hawker Siddeley Model HS.125 Series 3B/RB (Transport Aircraft), Approved May 28, 1999. (See NOTE 52) The DH.125 Series 3B/RB aircraft differs respectively from the DH.125 Series 3B/RA aircraft by incorporation of Modification No. 252024 which increases the maximum ramp weight and the maximum take off weight. Hawker Siddeley Model HS.125 Series 3B/RC (Transport Aircraft), Approved May 28, 1999. (See NOTE 52) The DH.125 Series 3B/RC aircraft differs respectively from the DH.125 Series 3B/RA aircraft by incorporation of modifications to enable it to be used for checking navigational aids by (i) installation of a special four seat cabin configuration and (ii) installation of special Avionics and Flight Inspection equipment. Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22f Type 2, ASTM D.1655 Jet B. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor 100% Operating speed (5 minutes maximum) (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730Oc Maximum continuous 705oC Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% A3EU Rev. 44 Page 19 of 105 - 19 - VII. Model DH.125 Series 3A/RA, Model HS.125 Series 3B/RA, Model HS.125 Series 3B/RB, Model HS.125 Series 3B/RC (cont’d) Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 30,800 feet with fuel in long range tank 260 knots from sea level to 27,200 feet with long range tank empty 285 knots decreasing linearly to 273 knots at 30,800 feet. VMO (Maximum operating) (with Mod. 25A767A) from sea level to 30,800 feet with fuel in long range tank 255 knots from sea level to 27,500 feet with long range tank empty 281 knots decreasing linearly to 265 knots at 31,980 feet. MMO (Maximum operating) 30,800 ft. and above 0.765 M MMO (Maximum operating) (3B/RB only) 30,800 ft. and above 0.755 M VA (Maneuvering) Sea level 190 knots 10,000 ft. 191 knots 20,000 ft. 197 knots 30,000 ft. 203 knots 35,000 ft. 208 knots 40,000 ft. 201 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76 in. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 20 of 105 - 20 - VII. Model DH.125 Series 3A/RA, Model HS.125 Series 3B/RA, Model HS.125 Series 3B/RB, Model HS.125 Series 3B/RC (cont’d) C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 22,700 27.20 (3.78)* 38.00 13.53 22,200 25.20 (1.98)* - - 19,200 - - 38.00 13.53 18,950 22.47 0.48 - - 18,850 - - 34.00 9.92 18,400 - - 33.80 9.74 14,200 23.00 0.00 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. C.G. Range (for 3B/RB only) Fwd. of Datum Aft of Datum (Gear and Flaps Retracted) Wt. Lbs. % SMC In. % SMC In. 23,300 29.67 (6.01)* 37.07 12.69 22,400 28.73 (5.17)* - - 22,400 26.00 (2.70)* - - 22,100 - - 38.00 13.53 19,200 - - 38.00 13.53 18,850 - - 34.00 9.92 18,400 22.47 0.48 - - 17,450 - - 33.33 9.32 16,800 22.40 0.55 - - 14,200 - - 36.13 9.57 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. Item (Extending) Moment Change In.Lbs. Wing Flaps 15o +538 25o +879 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights (3B/RB only) Maximum Ramp Weight 23,100 lbs. 23,300 Lbs. Maximum Brake-Release Weight 22,700 lbs. 23,300 Lbs. Maximum Landing Weight 20,000 lbs. 20,000 Lbs. Maximum Zero Fuel Weight 14,200 lbs.* 14,200 Lbs. * (See NOTE 46) Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. A3EU Rev. 44 Page 21 of 105 - 21 - VII. Model DH.125 Series 3A/RA, Model HS.125 Series 3B/RA, Model HS.125 Series 3B/RB, Model HS.125 Series 3B/RC (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Ventral tank 134.5 896 88.70 Total 1,366.0 9,106 13.95 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Models DH.125 Series 3A/R and HS.125 Series 3B/R. (See NOTE 61) VIII. Hawker Siddeley Model DH.125 Series 400A (Transport Aircraft), Approved November 15, 1968 (See NOTE 16) Hawker Siddeley Model HS.125 Series 400B (Transport Aircraft), Approved May 28, 1999. (See NOTES 16 & 53) (The DH.125 Series 400A aircraft and the HS.125 Series 400B aircraft differs respectively from the DH.125 Series 3A/RA aircraft and the HS.125 Series 3B/RA aircraft in the following major features: (i) increased maximum ramp and brake-release weights; (ii) introduction of an outward-opening main entry door) Beechcraft Hawker Model BH.125 Series 400A (Transport Aircraft) Approved 14 July 1970 (See NOTE 16) (The Hawker Siddeley Model DH.125 Series 400A is, from aircraft Serial Number 25230 and subsequent, identified as the Beechcraft Hawker Model BH.125 Series 400A. The BH.125 Series 400A is, in all respects, identical to the DH.125 Series 400A except that the aircraft data plate, the control column central motif and the external nameplate on the fuselage nose have been altered to incorporate the revised identification.) Hawker Siddeley Model HS.125 Series 400B/1 (Transport Aircraft), Approved May 28, 1999. (See NOTES 16 & 53) (The HS.125 Series 400B/1 aircraft were originally manufactured as a HS.125 Series 400A aircraft converted to a HS.125 Series 400B aircraft and then reconverted to the equivalent of a HS.125 Series 400A aircraft.) Hawker Siddeley Model HS.125 Series 401B (Transport Aircraft), Approved May 28, 1999. (See NOTE 53) (The HS.125 Series 401B aircraft differs respectively from the HS.125 Series 400B aircraft in the following major features: (i) increased maximum take off weight and zero fuel weight and (ii) cabin loading altered (See NOTE 8). A3EU Rev. 44 Page 22 of 105 - 22 - VIII. Model DH.125 Series 400A, Model HS.125 Series 400B, Model BH.125 Series 400A, Model HS.125 Series 400B/1, Model HS.125 Series 401B, Model HS.125 Series 403B, Model HS.125 Series 403A(C) (cont’d) Hawker Siddeley Model HS.125 Series 403B (Transport Aircraft), Approved May 28, 1999. (See NOTE 53) Hawker Siddeley Model HS.125 Series 403A(C) (Transport Aircraft), Approved May 28, 1999. (See NOTE 53) (The HS.125 Series 403B and the HS.125 Series 403A(C) aircraft differs respectively from the HS.125 Series 400A aircraft in the following major features: (i) increased maximum take off weight, zero fuel weight, and ramp weight and (ii) cabin loading was altered (See NOTE 8). The HS.125 Series 403A(C) aircraft was for Canadian registry. The following details are applicable to both the Hawker Siddeley Models DH.125 Series 400A, HS.125 Series 400B, Beechcraft Hawker Model BH.125 Series 400A. All other models are the same except as noted. (See NOTE 35) Engines 2 Bristol Siddeley Viper 522 turbine engines. Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22 Type 2, ASTM D.1655 Jet B, Mil-t-5624 JP4 Grade. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,330 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,100 Maximum permissible engine rotor operating speed (5 minutes maximum) 100% (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: (See NOTE 7) Take-off (5 minutes maximum) 730oC Maximum continuous 705°C Maximum for acceleration 705oC Starting maximum gas temperature 800oC Maximum permissible oil inlet temperature: Continuous operation (See NOTE 13) 125oC Maximum permissible air bleed extraction of primary engine airflow 7.5% Airspeed Limits (IAS) VMO (Maximum operating) from sea level to 30,800 feet with fuel in long range tank 260 knots from sea level to 27,200 feet with long range tank empty 285 knots decreasing linearly to 273 knots at 30,800 feet. VMO (Maximum operating) (with Mod. 252243C or 256403D, Series 401B, Series 403A(C) or Series 403B) from sea level to 30,800 feet with fuel in long range tank 257 knots from sea level to 27,500 feet with long range tank empty 282 knots decreasing linearly to 270 knots at 31,350 feet. (See NOTE 16) MMO (maximum operating) (See NOTE 15) 30,800 ft. and above 0.765 M MMO (maximum operating) (Series 401B and Series 403B) 30,800 ft. and above 0.755 M VA (Maneuvering) Sea level 193 knots 10,000 feet 195 knots 20,000 feet 201 knots 30,000 feet 208 knots 35,000 feet 213 knots 40,000 feet 209 knots Straight line variation between points shown. A3EU Rev. 44 Page 23 of 105 - 23 - VIII. Model DH.125 Series 400A, Model HS.125 Series 400B, Model BH.125 Series 400A, Model HS.125 Series 400B/1, Model HS.125 Series 401B, Model HS.125 Series 403B, Model HS.125 Series 403A(C) (cont’d) Airspeed Limits (IAS) (cont.) VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 50o or 45o (See NOTE 23) 145 knots VLO (Landing gear operation) Retract 210 knots Extend 210 knots VLE (Landing gear extended) 210 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 93 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 84 knots Datum The center of gravity datum (station 353.04 inches ) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76 in. forward of t he datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 23,300 29.67 (6.01)* 37.13 12.75 22,400 28.73 (5.17)* - - 22,400 26.00 (2.70)* - - 22,100 - - 38.00 13.53 19,200 - - 38.00 13.53 18,850 - - 34.00 9.92 18,400 22.45 .50 - - 17,400 - - 33.33 9.32 16,800 22.40 .55 - - 14,200 - - 36.00 11.73 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. A3EU Rev. 44 Page 24 of 105 - 24 - VIII. Model DH.125 Series 400A, Model HS.125 Series 400B, Model BH.125 Series 400A, Model HS.125 Ser ies 400B/1, Model HS.125 Series 401B, Model HS.125 Series 403B, Model HS.125 Series 403A(C) (cont’d) C.G. Range (with Mod. 252243C) Fwd. of Datum Aft of Datum (Gear and Flaps Retracted) Wt. Lbs. % SMC In. % SMC In. (See NOTE 16) 23,300 29.40 (5.77)* 37.13 12.75 22,900 - - 38.00 13.53 22,700 29.13 (5.53)* - - 22,700 25.93 (2.64)* - - 19,200 - - 38.00 13.53 18,850 - - 34.00 9.92 18,400 22.45 0.50 - - 17,400 - - 33.33 9.32 16,800 22.40 0.55 - - 14,200 - - 36.00 11.73 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. C.G. Range (with Mod. 256403D) Fwd. of Datum Aft of Datum (Gear and Flaps Retracted) Wt. Lbs. % SMC In. % SMC In. (See NOTE 16) 23,300 29.40 (5.77)* 37.00 12.63 22,900 29.20 (5.59)* - - 22,900 26.07 (2.77)* - - 21,900 - - 38.00 13.53 19,200 - - 38.00 13.53 18,900 - - 34.00 9.92 18,500 22.45 0.50 - - 17,400 - - 33.33 9.32 16,200 22.40 0.55 - - 14,200 - - 36.00 11.73 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. C.G. Range (Series 401B) Fwd. of Datum Aft of Datum (Gear and Flaps Retracted) Wt. Lbs. % SMC In. % SMC In. 23,600 29.73 (6.07)* 34.20 10.10 23,300 - - 37.00 12.63 22,900 29.20 (5.59)* - - 22,900 26.07 (2.77)* - - 21,900 - - 38.00 13.53 19,200 - - 38.00 13.53 18,900 - - 33.93 9.86 18,500 22.45 0.50 - - 17,400 - - 33.33 9.32 16,200 22.40 0.55 - - 14,200 - - 36.00 11.73 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. A3EU Rev. 44 Page 25 of 105 - 25 - VIII. Model DH.125 Series 400A, Model HS.125 Series 400B, Model BH.125 Series 400A, Model HS.125 Series 400B/1, Model HS.125 Series 401B, Model HS.125 Series 403B, Model HS.125 Series 403A(C) (cont’d) C.G. Range (Series 403A(C) Fwd. of Datum Aft of Datum and Series 403B) Wt. Lbs. % SMC In. % SMC In. (Gear and Flaps Retracted) 23,600 29.53 (5.89)* 34.20 10.10 23,300 - - 35.13 10.94 23,300 - - 37.00 12.63 22,900 29.20 (5.59)* - - 22,900 26.07 (2.77)* - - 21,900 - - 38.00 13.53 19,200 - - 38.00 13.53 18,900 - - 33.93 9.86 18,500 22.45 0.50 - - 17,400 - - 33.33 9.32 16,200 22.40 0.55 - - 14,200 - - 36.00 11.73 13,000 - - 37.53 13.11 12,000 23.00 0.00 - - 11,000 28.00 (4.51)* 37.53 13.11 *(Aft of Datum) Straight line variation between weights. C.G. Range (Series 403A(C) Item (extending) Moment Change In.Lbs and Series 403B) Wing flaps 15o +538 (Gear and Flaps Retracted) 25o +879 (cont.) 50o or 45o (See NOTE 23) +1,593 Main Landing Gear -1,800 Nose Landing Gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at st ations 309.35 and 371.55 Maximum Weights (with Mod. (with Mod. 252243C) 256403D) Maximum Ramp Weight 23,300 lbs. 23,600 Lbs. 23,800 Lbs. Maximum Brake-Release Weight 23,300 lbs. 23,300 Lbs. 23,300 Lbs. Maximum Landing Weight 20,000 lbs. 20,000 Lbs. 20,000 Lbs. Maximum Zero Fuel Weight 14,200 lbs. 14,500 Lbs. 14,700 Lbs. (Series 403A(C) (Series 401B) & Series 403B) Maximum Ramp Weight 23,600 lbs. 23,800 lbs. Maximum Brake-Release Weight 23,600 lbs. 23,600 lbs. Maximum Landing Weight 20,000 lbs. 20,000 lbs. Maximum Zero Fuel Weight 14,500 lbs. 14,700 lbs. Minimum Crew For all flights, 2 pilots A3EU Rev. 44 Page 26 of 105 - 26 - VIII. Model DH.125 Series 400A, Model HS.125 Series 400B, Model BH.125 Series 400A, Model HS.125 Series 400B/1, Model HS.125 Series 401B, Model HS.125 Series 403B, Model HS.125 Series 403A(C) (cont’d) Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weigh and balance section, or Weight and Balance section, or Weight and Balance Manual. Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205 to 260 60 210 8 seater 205 to 250 60 160 Forward cabin (a) Side floor 260 to 303.85 50 (b) Center floor 260 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395 50 (b) Center floor 303.85 to 395 60 Aft 395 to 425 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Long Range Tank 134.5 896 88.70 Total 1,366.0 9,106 13.95 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.87 14 82 1153 No. 2 1.87 14 82 1153 Total 3.74 28 82 2306 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible DH.125 Series 400A and HS.125 Series 400B: 25173 through 25229 (See NOTE 61) BH.125 Series 400A: 25230 through 25290 (See NOTE 61) IX. Beechcraft Hawker Model BH.125 Series 600A (Transport Aircraft) Approved August 17, 1972 (See NOTE 17) Hawker Siddeley Model HS.125 Series 600B (Transport Aircraft), Approved May 28, 1999. (See NOTES 17 & 54) The BH.125 Series 600A aircraft and the HS.125 Series 600B differs respectively from the BH.125 Series 400A and the HS.125 Series 400B in the following major features: (i) Introduction of Rolls Royce (1971) Ltd., Bristol Engine Division Viper 601-22 engines, (ii) increased maximum ramp, brake release, landing and zero fuel weights, (iii) increased maximum operating speed (VMO), rough air speed (VRA), flap operating speeds (VFE), and landing gear operating speed (VLE), (iv) increased fuselage length, (v) increased fuel capacity by the addition of an extra fuel tank in the dorsal fairing, (vi) revised aileron tab arrangement and aileron control gearing, (vii) aerodynamic improvements providing better aircraft aerodynamic lines. Hawker Siddeley Model HS.125 Series 600A (Transport Aircraft) Approved January 6, 1976 (See NOTE 17) The Beechcraft Hawker Model BH.125 Series 600A, is, from aircraft Serial No. 256055, identified as the Hawker Siddeley Model HS.125 Series 600A. The Hawker Siddeley Model HS.125 Series 600A is in all respects identical to the Beechcraft Hawker Model BH.125 Series 600A except that the aircraft data plate, the control column central motif and the external nameplate on the fuselage nose have all been altered to reflect the revised identification. A3EU Rev. 44 Page 27 of 105 - 27 - IX. Model BH.125 Series 600A, Model HS.125 Series 600B, Model HS.125 Series 600A, Model HS.125 Series 600B/1, Model HS.125 Series 600B/2, Model HS.125 Series 600B/3 (cont’d) Hawker Siddeley Model HS.125 Series 600B/1 (Transport Aircraft), Approved May 28, 1999 (See NOTES 17, 54 & 55) Hawker Siddeley Model HS.125 Series 600B/2 (Transport Aircraft), Approved May 28, 1999 (See NOTES 17, 54 & 55. Hawker Siddeley Model HS.125 Series 600B/3 (Transport Aircraft), Approved May 28, 1999 (See NOTES 17, 54 & 55) The following details are applicable to both the Beechcraft Hawker Model BH.125 Series 600A and the Hawker Siddeley Models HS.125 Series 600A and Series 600B, 600B/1, 600B/2 and 600B/3 aircraft. (See NOTE 18). Engines 2 Rolls Royce (1971) Ltd., Bristol Engine Division Viper 601-22 turbine engines Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23 Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22 Type 2, ASTM D.1655 Jet B, Mil-T-5624 JP4. (See NOTE 4). Engine Limits Take-off static thrust, standard day, sea level conditions (5 minutes maximum) lbs. 3,675 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,675 Maximum permissible engine rotor operating speed 100% (13,760 r.p.m.) Maximum permissible turbine outlet gas temperature: Take-off (5 minutes maximum) 725oC Maximum continuous 715oC Maximum for acceleration 715oC Starting maximum gas temperature 700oC Maximum permissible oil inlet temperature: Continuous operation 145oC Maximum permissible air bleed extraction of primary engine airflow 5.5% Airspeed Limits (IAS) VMO (Maximum operating) when the dorsal and/or ventral fuel tank contains fuel 280 knots when the dorsal and the ventral fuel tanks are empty 300 knots VMO (Maximum operating) (with Mod. 252320)(See NOTE 17) when the dorsal and/or ventral fuel tank contains fuel 280 knots from sea level to 12,400 feet with dorsal and ventral tanks empty 320 knots decreasing linearly to 292 knots at 29,200 feet. MMO (maximum operating) 30,800 ft. and above 0.755 M MMO (maximum operating) (with Mod. 252320)(See NOTE 17) 29,200 ft. and above 0.78 M VA (Maneuvering) Sea level 190 knots 10,000 feet 193 knots 20,000 feet 196 knots 30,000 feet 201 knots 35,000 feet 205 knots 40,000 feet 212 knots Straight line variation between points shown. A3EU Rev. 44 Page 28 of 105 - 28 - IX. Model BH.125 Series 600A, Model HS.125 Series 600B, Model HS.125 Series 600A, Model HS.125 Series 600B/1, Model HS.125 Series 600B/2, Model HS.125 Series 600B/3 (cont’d) Airspeed Limits (IAS) (cont’d) VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 160 knots VLO (Landing gear operation) Retract 220 knots Extend 220 knots VLE (Landing gear extended) 220 knots VMC (Minimum control speed) VMCA (with flaps at 0o or 15o at sea level for temperatures below 10oC) 96 knots VMCG (with flaps at 0o or 15o at sea level for temperatures below 10oC) 90 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76 in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 25,000 26.40 (3.06)* 34.73 10.58 24,850 - - 35.00 10.82 24,590 26.13 (2.82)* - - 24,590 24.27 (1.14)* - - 23,700 23.67 (0.60)* - - 23,700 20.53 2.23 - - 20,800 - - 35.00 10.82 20,510 - - 30.40 6.67 20,300 17.07 5.36 - - 19,000 - - 29.53 5.89 15,550 16.00 6.32 - - 14,700 - - 32.00 8.12 12,800 16.00 6.32 31.53 7.69 *(Aft of Datum) Straight line variation between weights. A3EU Rev. 44 Page 29 of 105 - 29 - IX. Model BH.125 Series 600A, Model HS.125 Series 600B, Model HS.125 Series 600A, Model HS.125 Series 600B/1, Model HS.125 Series 600B/2, Model HS.125 Series 600B/3 (cont’d) C.G. Range (with Mod. 252320) Fwd. of Datum Aft of Datum (Gear and Flaps Wt. Lbs. % SMC In. % SMC In. Retracted) 25,500 26.87 (3.49)* 33.80 9.74 25,100 26.47 (3.13)* - - 25,100 24.53 (1.38)* - - 24,850 - - 35.00 10.82 24,200 23.93 (0.83)* - - 24,200 21.00 1.81 - - 20,800 - - 35.00 10.82 20,510 - - 30.40 6.67 20,300 17.07 5.36 - - 19,000 - - 29.53 5.89 15,550 16.00 6.32 - - 14,700 - - 32.00 8.12 12,800 16.00 6.32 31.53 7.69 *(Aft of Datum) Straight line variation between weights. C.G. Range (with Mod. 256663) Fwd. of Datum Aft of Datum (Gear and Flaps Wt. Lbs. % SMC In. % SMC In. Retracted) 25,500 26.60 (3.49)* 32.00 9.74 25,100 26.40 (3.13)* - - 25,100 24.53 (1.38)* - - 24,200 23.93 (0.83)* - - 24,200 21.00 1.81 - - 20,650 - - 32.00 10.82 20,500 - - 30.33 10.82 20,300 17.07 5.36 - - 19,150 - - 29.47 10.82 15,550 16.00 6.32 - - 14,700 - - 32.00 8.12 12,800 16.00 6.32 31.40 7.58 *(Aft of Datum) Straight line variation between weights. Item (Extending) Moment Change In.Lbs. Wing Flaps 15o +538 25o +879 45° +1,593 Main landing gear -1,980 Nose landing gear +1,380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights (With Mod 252320) Maximum Ramp Weight 25,000 lbs. 25,500 lbs. Maximum Brake-Release Weight 25,000 lbs. 25,500 lbs. Maximum Landing Weight 22,000 lbs. 22,000 lbs. Maximum Zero Fuel Weight 15,550 lbs. 16,050 lbs. (With Mod. 256663) Maximum Ramp Weight 25,500 lbs. Maximum Brake-Release Weight 25,500 lbs. Maximum Landing Weight 22,000 lbs. Maximum Zero Fuel Weight 16,050 lbs. A3EU Rev. 44 Page 30 of 105 - 30 - IX. Model BH.125 Series 600A, Model HS.125 Series 600B, Model HS.125 Series 600A, Model HS.125 Series 600B/1, Model HS.125 Series 600B/2, Model HS.125 Series 600B/3 (cont’d) Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum - For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 180.25 to 223.11 100 310 Forward cabin (a) Side floor 245.85 to 303.85 50 b) Center floor 245.85 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 397.8 to 422.3 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 611.0 4,070 5.60 Tank 2 611.0 4,070 5.60 Engines and lines 1.5 10 81.00 Long Range (ventral tank) 134.5 896 88.60 Dorsal tank 61.0 406 119.30 Total 1,419.0 9,452 18.43 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Volume Maximum Arm Moment Location U.S. Gal Weight Lbs. In. In. Lbs. No. 1 2.03 15.3 83 1224 No. 2 2.03 15.3 83 1224 Total 4.06 30.6 83 2448 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible BH.125 Series 600A and HS.125 Series 600B: 25256, 25258, 256001 through 256035, and 256037 through 256054. HS.125 Series 600A: 256055 through 256071 A3EU Rev. 44 Page 31 of 105 - 31 - X. Hawker Siddeley Model HS.125 Series 700A (Transport Aircraft), Approved May 20, 1977 Hawker Siddeley Model HS.125 Series 700B (Transport Aircraft), Approved May 28, 1999. (See NOTE 56) The HS.125 Series 700A and HS.125 Series 700B aircraft differs respectively from the BH/HS.125 Series 600A and the HS.125 Series 600B aircraft in the following major respects: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 601-22 engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance, (iv) Provisions for a New Automatic Flight Control System - Collins FCS.80, (v) Addition of a single point pressure refuel/defuel system, (vi) Reduction in certificated taxiing and take-off (brake release) weights, (vii) Reduction of MMO from 0.78 (Post Modification 252320 Part A) to 0.77. The following details are applicable to both the Hawker Siddeley Model HS.125 Series 700A and Series 700B aircraft (See NOTES 20, 24 & 27). Engines 2 Garrett AiResearch TFE 731-3 turbofan engines, or 2 Garrett AiResearch TFE 731-3R turbofan engines (See NOTE 20) Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23h Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22 Type 2, ASTM D.1655 Jet B, Mil-T-5624 JP4. (See NOTE 28). Engine Limits TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 3,700 3,880 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,700 3,700 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 101.5 101.5 (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 100 (29,692 rpm) (29,989 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 907oC 929oC Take-off (10 minutes maximum) 917oC 939oC Take-off (instantaneous) 927oC 949oC Maximum continuous 885oC 885oC Engine starting and relighting (unrestricted) 907oC 907oC Engine starting and relighting (10 seconds) 927oC 927oC Engine starting and relighting (5 seconds) above 927oC above 927oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC A3EU Rev. 44 Page 32 of 105 - 32 - A3EU Rev. 44 Page 33 of 105 - 33 - X. Model HS.125 Series 700A, Model HS.125 Series 700B (cont’d) Engine Limits (cont.) Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (maximum operating) With fuel in the dorsal and/or ventral tank 280 knots With dorsal and ventral tanks empty 320 knots S.L. to 12,400 ft. decreasing linearly 1 kt. per 600 ft. to 292 kts. at 29,200 ft. VMO (maximum operating) (Cont.) With dorsal and ventral tanks empty and with Mod 320 Knots 258825: S.L. to 10,600 ft. decreasing linearly 1 kt. per 600 ft. to 288 kts. at 29,800 ft. MMO (maximum operating) 28,500 ft. and above 0.77 M MMO (maximum operating) (with Mod 252648) 29,200 ft. and above 0.78 M VA (maneuvering) Sea level 192 knots 10,000 ft. 195 knots 20,000 ft. 198 knots 30,000 ft. 203 knots 35,000 ft. 207 knots 38,000 ft. 211 knots 40,000 ft. 214 knots 41,000 ft. 217 knots VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 160 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) APR not operating APR operating VMCA (with flaps 0o or 15o at sea level for temperatures below 22oC 101 knots 104 knots VMCA (with either rudder bias strut inoperative) 110 knots 113 knots VMCG (with flaps 0o or 15o at sea level for temperatures below 22oC 92 knots 95 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 34 of 105 - 34 - X. Model HS.125 Series 700A, Model HS.125 Series 700B (cont’d) C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 24,800 25.00 (1.80)* 35.00 10.82 24,200 24.60 (1.44)* - - 24,200 21.80 1.09 36.80 12.45 22,000 - - 36.80 12.45 20,950 - - 36.27 11.97 20,850 18.60 3.98 33.80 9.74 20,650 - - 33.67 9.62 20,400 - - 30.27 6.56 19,000 - - 29.40 5.77 16,300 18.00 4.52 - - 14,700 - - 31.93 8.05 13,100 18.00 4.52 31.50 7.67 *(Aft of Datum) Straight line variations between weights C.G. Range (with Modification Fwd. of Datum Aft of Datum 258332) Wt. Lbs. % SMC In. % SMC In. (Gear and flaps 25,500 27.40 (3.97)* 33.53 9.50 Retracted) 25,000 25.13 (1.92)* - - 24,200 24.60 (1.44)* - - 24,200 21.80 1.09 36.80 12.45 22,400 - - 36.80 12.45 20,950 - - 36.27 11.97 20,850 18.60 3.98 33.80 9.74 20,600 - - 33.73 9.68 20,400 - - 30.27 6.56 19,000 - - 29.40 5.77 16,300 18.00 4.52 - - 14,700 - - 31.93 8.05 13,100 18.00 4.52 31.50 7.67 *(Aft of Datum) Straight line variations between weights Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1980 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights with Modification 258332 Maximum ramp weight 25,000 Lbs. 25,500 Lbs. (See NOTE 27) Maximum brake release weight 24,800 Lbs. 25,500 Lbs. (See NOTE 27) Maximum landing weight 22,000 Lbs. 22,000 Lbs. Maximum zero fuel weight 16,050 Lbs. 16,300 Lbs. (See NOTES 29 & 34) Minimum zero fuel weight 13,100 Lbs. 13,100 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. A3EU Rev. 44 Page 35 of 105 - 35 - X. Model HS.125 Series 700A, Model HS.125 Series 700B (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 180.25 to 223.11 109 310 Forward cabin (a) Side floor 245.85 to 303.85 50 (b) Center floor 245.85 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 397.8 to 422.3 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 612.5 4,080 5.60 Tank 2 612.5 4,080 5.60 Engines and lines 1.5 10 107.60 Ventral tank 131.0 873 88.60 Dorsal tank 61.0 406 119.30 Total 1,418.5 9,449 18.26 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 93.69 1,059 No. 2 1.5 11.3 93.69 1,059 Total 3.0 22.6 93.90 2,118 Maximum Operating Altitude 41,000 feet Serial Numbers Eligible 257001 through 257215 (See NOTE 61) XI. Hawker Siddeley Model DH.125 Series 1A with Modifications 251867 and 252605 (Transport Aircraft), Approved January 20, 1982 (See NOTE 22) The DH.125 Series 1A with modification 252605 aircraft differs respectively from the DH.125 Series 1A aircraft fitted with modification 251867 in the following major respects: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 521 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance. Hawker Siddeley Model DH.125, Series 1A with Modification 252606 (Transport Aircraft), Approved January 20, 1982 (See NOTE 22) The DH.125 Series 1A with modification 252606 aircraft differs respectively from the DH.125 Series 1A aircraft not fitted with modification 251867 in the following major respects: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 521 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance. Engines 2 Garrett AiResearch TFE 731-3 turbofan engines, or 2 Garrett AiResearch TFE 731-3R turbofan engines (See NOTE 20) Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F -34, Defence Standard 91-91, NATO Code F-35, 3-GP-23h, ASTM D.1655-74 Jet A or Jet A1 Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F -40, ASTM D.1655 Jet B, MIL-T-5624 JP4 Grade, 3 GP-22 (See NOTE 28) A3EU Rev. 44 Page 36 of 105 - 36 - XI. Model DH.125 Series 1A (cont’d) Engine Limits TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 3,700 3,880 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,700 3,700 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 101.5 % 101.5 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 % 101 % (29,692 rpm) (29,989 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 907oC 929oC Take-off (10 minutes maximum) 917oC 939oC Take-off (instantaneous) 927oC 949oC Maximum continuous 885oC 885oC Engine starting and relighting (unrestricted) 907oC 907oC Engine starting and relighting (10 seconds) 927oC 927oC Engine starting and relighting (5 seconds) above 927oC above 927oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (maximum operating) 285 knots S.L. to 27,200 ft. decreasing linearly 1 kt. per 300 ft. to 273 kts. at 30,800 ft. MMO (maximum operating) 0.755 M A3EU Rev. 44 Page 37 of 105 - 37 - XI. Model DH.125 Series 1A (cont’d) Airspeed Limits (IAS) (cont.) VA (Maneuvering) Sea level 185 knots 10,000 ft. 185 knots 20,000 ft. 185 knots 30,000 ft. 195 knots VA (Maneuvering) 40,000 ft. 210 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 45o 145 knots VLO (landing gear operation) Retract 210 knots Extend 210 knots VLE (landing gear extended) 210 knots VMC (minimum control speed) APR not operating APR operating VMCA (with flaps 0o or 15o at sea level for temperatures below 22oC 100 knots 104 knots VMCA (with either rudder bias strut inoperative) 110 knots 113 knots VMCG (with flaps 0o or 15o at sea level for temperatures below 22oC 91 knots 95 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Series 1A with Modifications 251867 and 252605 Retracted) Fwd. of Datum Aft of Datum Wt. Lbs. % SMC In. % SMC In. 21,700 24.60 (1.44)* 33.60 9.56 20,500 - - 34.33 10.22 19,000 - - 34.07 9.98 18,500 21.67 1.20 - - 16,800 - - 33.07 9.08 13,700 22.00 0.91 - - 12,350 - - 37.53 13.11 11,600 22.27 0.66 - - 11,400 23.27 (0.24)* 37.53 13.11 *(Aft of Datum) Straight line variations between weights A3EU Rev. 44 Page 38 of 105 - 38 - XI. Model DH.125 Series 1A (cont’d) C.G. Range (Gear and Flaps Series 1A with Modification 252606 Retracted) Fwd. of Datum Aft of Datum Wt. Lbs. % SMC In. % SMC In. 21,200 24.67 (1.50)* 33.80 9.74 20,500 - - 34.33 10.22 19,000 - - 34.07 9.98 18,000 21.67 1.20 - - 16,800 - - 33.07 9.08 13,700 22.00 0.91 - - 12,350 - - 37.53 13.11 11,600 22.20 0.73 - - 11,400 23.27 (0.24)* 37.53 13.11 *(Aft of Datum) Straight line variations between weights Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1800 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights with Modifications with Modification 251867 & 252605 252606 Maximum ramp weight 21,900 Lbs. 21,400 Lbs. Maximum brake release weight 21,700 Lbs. 21,200 Lbs. Maximum landing weight 19,550 Lbs. 19,550 Lbs. Maximum zero fuel weight 13,700 Lbs. 13,200 Lbs. Minimum zero fuel weight 11,400 Lbs. 11,400 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205.00 to 260.00 60 210 8 seater 205.00 to 260.00 60 160 Forward cabin (a) Side floor 260.00 to 303.85 50 (b) Center floor 260.00 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.30 50 (b) Center floor 303.85 to 395.30 60 Aft 396.00 to 425.00 60 130 A3EU Rev. 44 Page 39 of 105 - 39 - XI. Model DH.125 Series 1A (cont’d) Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Total 1,231.5 8,210 5.79 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 93.69 1,059 No. 2 1.5 11.3 93.69 1,059 Total 3.0 22.6 2,118 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Model DH.125 Series 1A and HS.125 Series 1B XII. Hawker Siddeley Model DH.125 Series 3A with Modification 252603 (Transport Aircraft) Approved January 20, 1982 (See NOTE 26) Hawker Siddeley Model HS.125 Series F3B (Transport Aircraft) Approved May 28, 1999. (See NOTES 26 and 52) (The DH.125 Series 3A aircraft with modification 252603 and the HS.125 Series F3B differs respectively from the DH.125 Series 3A and the HS.125 Series 3B aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance. Engines 2 Garrett AiResearch TFE 731-3 turbofan engines, or 2 Garrett AiResearch TFE 731-3R turbofan engines (See NOTE 20) Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F -34, Defence Standard 91-91, NATO Code F-35, 3-GP-23h, ASTM D.1655-74 Jet A or Jet A1 Aviation Wide-cut to speci fication Defence Standard 91-88, NATO Code F -40, ASTM D.1655 Jet B, MIL-T-5624 JP4 Grade, 3 GP-22 (See NOTE 28) Engine Limits TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 3,700 3,880 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,700 3,700 Maximum permissible engine rotor operating speed: L.P. Shaft (N1) 101.5 % 101.5 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 % 101 % (29,692 rpm) (29,989 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 907oC 929oC Take-off (10 minutes maximum) 917oC 939oC Take-off (instantaneous) 927oC 949oC Maximum continuous 885oC 885oC A3EU Rev. 44 Page 40 of 105 - 40 - XII. Model DH.125 Series 3A, Model HS.125 Series F3B (cont’d) Engine Limits (cont.) TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Engine starting and relighting (unrestricted) 907oC 907oC Engine starting and relighting (10 seconds) 927oC 927oC Engine starting and relighting (5 seconds) above 927oC above 927oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (maximum operating) 285 knots SL to 27,200 ft. decreasing linearly 1 kt. per 300 ft. to 273 kts. at 30,800 ft. MMO (maximum operating) 0.755 M VA (Maneuvering) Sea level 185 knots 10,000 ft. 185 knots 20,000 ft. 185 knots 30,000 ft. 195 knots 40,000 ft. 210 knots Straight line variation between points shown. VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 45o 145 knots VLO (landing gear operation) Retract 210 knots Extend 210 knots VLE (landing gear extended) 210 knots A3EU Rev. 44 Page 41 of 105 - 41 - XII. Model DH.125 Series 3A, Model HS.125 Series F3B (cont’d) Airspeed Limits (IAS) (cont.) VMC (minimum control speed) APR not operating APR operating VMCA (with flaps 0o or 15o at sea level for temperatures below 22oC 100 knots 104 knots VMCA (with either rudder bias strut inoperative) 110 knots 113 knots VMCG (with flaps 0o or 15o at sea level for temperatures below 22oC 91 knots 95 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Retracted) Fwd. of Datum Aft of Datum Wt. Lbs. % SMC In. % SMC In. 21,700 24.60 (1.44)* 33.60 9.56 20,500 - - 34.33 10.22 19,000 - - 34.07 9.98 18,500 21.67 1.20 - - 16,800 - - 33.07 9.08 13,700 22.00 0.91 - - 12,300 - - 37.53 13.11 11,600 22.27 0.66 - - 11,400 23.27 (0.24)* 37.53 13.11 *(Aft of Datum) Straight line variations between weights Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1800 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum ramp weight 21,900 Lbs. Maximum brake release weight 21,700 Lbs. Maximum landing weight 20,000 Lbs. Maximum zero fuel weight 13,700 Lbs. Minimum zero fuel weight 11,400 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. A3EU Rev. 44 Page 42 of 105 - 42 - XII. Model DH.125 Series 3A, Model HS.125 Series F3B (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205.00 to 260.00 60 210 8 seater 205.00 to 260.00 60 160 Forward cabin (a) Side floor 260.00 to 303.85 50 (b) Center floor 260.00 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 395.00 to 425.00 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Total 1,231.5 8,210 5.79 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 93.69 1,059 No. 2 1.5 11.3 93.69 1,059 Total 3.0 22.6 2,118 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Model DH.125 Series 3A and HS.125 Series 3B (See NOTE 61) XIII. Hawker Siddeley Model DH.125, Series 3A/RA with Modification 252600 (Transport Aircraft) Approved February 15, 1968 (See NOTE 25) Hawker Siddeley Model HS.125 Series F3B/RA (Transport Aircraft) Approved May 28, 1999. (See NOTES 25 & 52) (The DH.125 Series 3A/RA aircraft with modification 252600 and the HS.125 Series F3B/RA differs respectively from the DH.125 Series 3A/RA and the HS.125 Series 3B/RA aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance. Engines 2 Garrett AiResearch TFE 731-3 turbofan engines, or 2 Garrett AiResearch TFE 731-3R turbofan engines (See NOTE 20) Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F-34, Defence Standard 91-91, NATO Code F-35, 3-GP-23h, ASTM.D.1655-74 Jet A or Jet A-1 Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, ASTM.D.1655 Jet B, MIL-T-5624 JP4 Grade, 3 GP-22 (See NOTE 28) A3EU Rev. 44 Page 43 of 105 - 43 - XIII. Model DH.125 Series 3A/RA, Model HS.125 Series F3B/RA (cont’d) Engine Limits TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 3,700 3,880 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,700 3,700 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 101.5 % 101.5 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 % 100 % (29,692 rpm) (29,989 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 907oC 929oC Take-off (10 minutes maximum) 917oC 939oC Take-off (instantaneous) 927oC 949oC Maximum continuous 885oC 885oC Engine starting and relighting (unrestricted) 907oC 907oC Engine starting and relighting (10 seconds) 927oC 927oC Engine starting and relighting (5 seconds) above 927oC above 927oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (Maximum operating) with fuel in long range tanks 257 knots from sea level to 27,500 feet with long range tank empty 282 knots decreasing linearly 1 knot per 320 feet to 270 knots at 31,350 feet. MMO (maximum operating) 0.755 M VA (Maneuvering) 193 knots VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots A3EU Rev. 44 Page 44 of 105 - 44 - 45o 145 knots A3EU Rev. 44 Page 45 of 105 - 45 - XIII. Model DH.125 Series 3A/RA, Model HS.125 Series F3B/RA (cont’d) Airspeed Limits (IAS) (cont.) VLO (landing gear operation) Retract 210 knots Extend 210 knots VLE (landing gear extended) 210 knots VMC (minimum control speed) APR not operating APR operating VMCA (with flaps 0o or 15o at sea level for temperatures below 22oC 100 knots 104 knots VMCA (with either rudder bias strut inoperative) 110 knots 113 knots VMCG (with flaps 0o or 15o at sea level for temperatures below 22oC 91 knots 95 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 23,600 30.73 (6.97)* 36.00 11.73 23,300 - - 37.00 12.63 22,900 30.40 (6.67)* - - 22,900 27.40 (3.97)* - - 21,900 - - 38.00 13.53 19,600 - - 38.00 13.53 19,300 - - 34.07 9.98 18,500 23.87 (0.78)* - - 17,400 - - 33.27 9.26 16,100 23.23 (0.20)* - - 14,700 26.20 (2.88)* - - 14,200 - - 36.13 11.84 13,750 25.00 (1.80)* - - 13,000 - - 37.53 13.11 11,600 25.00 (1.80)* - - 11,400 26.00 (2.70)* 37.53 13.11 *(Aft of Datum) Straight line variations between weights Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1800 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum ramp weight 23,800 Lbs. Maximum brake release weight 23,600 Lbs. Maximum landing weight 20,000 Lbs. Maximum zero fuel weight 14,700 Lbs. Minimum zero fuel weight 11,400 Lbs. A3EU Rev. 44 Page 46 of 105 - 46 - XIII. Model DH.125 Series 3A/RA, Model HS.125 Series F3B/RA (cont’d) Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205.00 to 260.00 60 210 8 seater 205.00 to 260.00 60 160 Forward cabin (a) Side floor 260.00 to 303.85 50 (b) Center floor 260.00 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 395.00 to 425.00 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Long Range Tank 134.5 896 88.70 Total 1,366.0 9,106 13.95 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 93.69 1,059 No. 2 1.5 11.3 93.69 1,059 Total 3.0 22.6 2,118 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Model DH.125 Series 3A and HS.125 Series 3B (See NOTE 61) XIV. Hawker Siddeley Model DH.125, Series 400A with Modification 252550 Approved November 15, 1968 (Transport Aircraft) (See NOTE 21) Beechcraft Hawker Model BH.125, Series 400A with Modification 252550 Approved July 14, 1970 (Transport Aircraft) (See NOTE 21) (The DH.125 Series 400A aircraft with modification 252550 and the BH.125 Series 400A aircraft with modification 252550 differs respectively from the DH.125 Series 400A and the BH.125 Series 400A aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance, and (iv) Increase in certificated taxi and take-off weights. Hawker Siddeley Model HS.125 Series F400B (Transport Aircraft) Approved May 28, 1999. (See NOTES 21 & 53) (The HS.125 Series F400B aircraft with modification 252551 differs from the HS.125 Series 400B aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance, and (iv) Increase in certificated taxi and take-off weights. A3EU Rev. 44 Page 47 of 105 - 47 - XIV. Model DH.125 Series 400A, Model BH.125 Series 400A, Model HS.125 Series F400B, Model HS. 125 Series F403B (cont’d) Hawker Siddeley Model HS.125 Series F403B (Transport Aircraft) Approved May 28, 1999 (See NOTES 21 & 53) (The HS.125 Series F403B aircraft with modification 252551 differs from the HS.125 Series 403B aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance, and (iv) Increase in certificated taxi and take-off weights. Engines 2 Garrett AiResearch TFE 731-3 turbofan engines, or 2 Garrett AiResearch TFE 731-3R turbofan engines (See NOTE 20) Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F -34, Defence Standard 91-91, NATO Code F-35, 3-GP-23h, ASTM.D.1655-74 Jet A or Jet A-1 Aviation Wide -cut to specification Defence Standard 91-88, NATO Code F -40, ASTM.D.1655 Jet B, MIL-T-5624 JP4 Grade, 3 GP-22 (See NOTE 28) Engine Limits TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 3,700 3,880 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,700 3,700 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 101.5 % 101.5 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 % 100 % (29,692 rpm) (29,989 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 907oC 929oC Take-off (10 minutes maximum) 917oC 939oC Maximum permissible interstage turbine temperature (ITT): (Cont.) Take-off (instantaneous) 927oC 949oC Maximum continuous 885oC 885oC Engine starting and relighting unrestricted) 907oC 907oC Engine starting and relighting (10 seconds) 927oC 927oC Engine starting and relighting (5 seconds) above 927oC above 927oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC A3EU Rev. 44 Page 48 of 105 - 48 - A3EU Rev. 44 Page 49 of 105 - 49 - XIV. Model DH.125 Series 400A, Model BH.125 Series 400A, Model HS.125 Series F400B, Model HS. 125 Series F403B (cont’d) Engine Limits (continued) TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (Maximum operating) with fuel in long range tanks 257 knots from sea level to 27,500 feet with long range tank empty 282 knots decreasing linearly 1 knot per 320 feet to 270 knots at 31,350 feet. VMO (Maximum operating) (with modification 259273) with fuel in long range tanks 253 knots from sea level to 27,500 feet with long range tank empty 276 knots decreasing linearly 1 knot per 340 feet to 260 knots at 32,940 feet. MMO (maximum operating) 0.755 M VA (Maneuvering) 193 knots VFE (Flap speeds) Deflection 15o 210 knots 25o 160 knots 45o 145 knots VLO (landing gear operation) Retract 210 knots Extend 210 knots VLE (landing gear extended) 210 knots VMC (minimum control speed) APR not operating APR operating VMCA (with flaps 0o or 15o at sea level for temperatures below 22oC 100 knots 104 knots VMCA (with either rudder bias strut inoperative) 110 knots 113 knots VMCG (with flaps 0o or 15o at sea level for temperatures below 22oC 91 knots 95 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 50 of 105 - 50 - XIV. Model DH.125 Series 400A, Model BH.125 Series 400A, Model HS.125 Series F400B, Model HS. 125 Series F4 03B (cont’d) C.G. Range (Gear and Flaps Retracted) Fwd. of Datum Aft of Datum Wt. Lbs. % SMC In. % SMC In. 23,600 30.73 (6.97)* 36.00 11.73 23,300 - - 37.00 12.63 22,900 30.40 (6.67)* - - 22,900 27.40 (3.97)* - - 21,900 - - 38.00 13.53 19,600 - - 38.00 13.53 19,300 - - 34.07 9.98 18,500 23.87 (0.78)* - - 17,400 - - 33.27 9.26 16,100 23.23 (0.20)* - - 14,700 26.20 (2.88)* - - 14,200 - - 36.13 11.84 13,750 25.00 (1.80)* - - 13,000 - - 37.53 13.11 11,600 25.00 (1.80)* - - 11,400 26.00 (2.70)* 37.53 13.11 *(Aft of Datum) Straight line variations between weights Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1800 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are s ituated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights with Modification 259273 Maximum ramp weight 23,800 Lbs. 23,800 Lbs. Maximum brake release weight 23,600 Lbs. 23,600 Lbs. Maximum landing weight 20,000 Lbs. 20,000 Lbs. Maximum zero fuel weight 14,700 Lbs. 15,200 Lbs. Minimum zero fuel weight 11,400 Lbs. 11,400 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 8 – For FAA approved seating configuration, refer to special specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 6 seater 205.00 to 260.00 60 210 8 seater 205.00 to 260.00 60 160 Forward cabin (a) Side floor 260.00 to 303.85 50 (b) Center floor 260.00 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 395.00 to 425.00 60 130 A3EU Rev. 44 Page 51 of 105 - 51 - XIV. Model DH.125 Series 400A, Model BH.125 Series 400A, Model HS.125 Series F400B, Model HS. 125 Series F403B (cont’d) Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 615.0 4,100 5.70 Tank 2 615.0 4,100 5.70 Engines and lines 1.5 10 81.00 Long Range Tank 134.5 896 88.70 Total 1,366.0 9,106 13.95 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 93.69 1,059 No. 2 1.5 11.3 93.69 1,059 Total 3.0 22.6 2,118 Maximum Operating Altitude 40,000 feet (See NOTE 9) Serial Numbers Eligible Same as listed previously for Hawker Siddeley Models DH.125 Series 400A and HS.125 Series 400B and Beechcraft Hawker Model BH.125 Series 400A. (See NOTE 61) XV. Beechcraft Hawker Model BH.125 Series 600A with Modification 252468 (Transport Aircraft) Approved October 15, 1981 (See NOTE 19) Hawker Siddeley Model HS.125 Series 600A with Modification 252468 (Transport Aircraft) Approved October 15, 1981 (See NOTE 19) The BH.125 Series 600A aircraft with modification 252468 and the HS.125 Series 600A aircraft with modification 252468 differs respectively from the BH.125 Series 600A and the HS.125 Series 600A aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance, and (iv) Reduction in take-off weights and increase in maximum zero fuel weight. The BH.125 Series 600A with modification 252468, is, from aircraft Serial No. 256055, identified as the model HS.125 Series 600A with modification 252468. Hawker Siddeley Model HS.125 Series F600B (Transport Aircraft) Approved May 28, 1999. (See NOTES 19 & 54) The HS.125 Series F600B aircraft differs from the HS.125 Series 600B aircraft in the following major features: (i) Garrett AiResearch TFE 731-3 engines replace the Rolls Royce Viper 522 turbine engines, (ii) Modifications to associated aircraft systems consequential to the engine change, (iii) Minor changes to improve aerodynamic efficiency and aircraft appearance, and (iv) Reduction in take-off weights and increase in maximum zero fuel weight. Engines 2 Garrett AiResearch TFE 731-3 turbofan engines, or 2 Garrett AiResearch TFE 731-3R turbofan engines (See NOTE 20) Fuel Aviation Kerosene to specification Defence Standard 91-91, NATO Code F-35, Defence Standard 91-87, NATO Code F-34, 3-GP-23h Type 1, ASTM D.1655 Jet A or Jet A1. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F-40, 3-GP-22 Type 2, ASTM D.1655 Jet B, Mil-T-5624 JP4. (See NOTE 28). Engine Limits TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 3,700 3,880 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 3,700 3,700 A3EU Rev. 44 Page 52 of 105 - 52 - XV. Beechcraft Hawker Model BH.125 Series 600A with Modif ication 252468 (Transport Aircraft) Approved October 15, 1981 (See NOTE 19) (cont’d) Engine Limits (cont.) TFE 731-3 and TFE 731-3R TFE 731-3R with with APR APR not operating operating Maximum permissible engine rotor operating speed L.P. Shaft (N1) 101.5 % 101.5 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 % 100 % (29,692 rpm) (29,989 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 907oC 929oC Take-off (10 minutes maximum) 917oC 939oC Take-off (instantaneous) 927oC 949oC Maximum continuous 885oC 885oC Engine starting and relighting (unrestricted) 907oC 907oC Engine starting and relighting (10 seconds) 927oC 927oC Engine starting and relighting (5 seconds) above 927oC above 927oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Maximum permissible oil temperature: Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (maximum operating) With fuel in the dorsal and/or ventral tank 280 knots With dorsal and ventral tanks empty 320 knots S.L. to 12,400 ft. decreasing linearly 1 kt. per 600 ft. to 292 kts. at 29,200 ft. MMO (maximum operating) 28,500 ft. and above 0.78 M VA (maneuvering) Sea level 192 knots 10,000 ft. 195 knots 20,000 ft. 198 knots 30,000 ft. 203 knots 35,000 ft. 207 knots 38,000 ft. 211 knots A3EU Rev. 44 Page 53 of 105 - 53 - 40,000 ft. 214 knots 41,000 ft. 217 knots A3EU Rev. 44 Page 54 of 105 - 54 - XV. Beechcraft Hawker Model BH.125 Series 600A with Modification 252468 (Transport Aircraft) Approved October 15, 1981 (See NOTE 19) Airspeed Limits (IAS) (cont.) VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 160 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) APR not operating APR operating VMCA (with flaps 0o or 15o at sea level for temperatures below 22oC 101 knots 104 knots VMCA (with either rudder bias strut inoperative) 110 knots 113 knots VMCG (with flaps 0o or 15o at sea level for temperatures below 22oC 92 knots 95 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 90.24 in. The leading edge of the SMC is 20.76. in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 24,800 25.00 (1.80)* 35.00 10.82 24,200 24.60 (1.44)* - - 24,200 21.80 1.09 36.47 12.15 22,500 - - 36.47 12.15 20,950 - - 36.27 11.97 20,850 18.60 3.98 33.80 9.74 20,650 - - 33.67 9.62 20,400 - - 30.27 6.56 19,000 - - 29.40 5.77 16,050 18.00 4.52 - - 14,700 - - 31.93 8.05 13,100 18.00 4.52 31.50 7.66 *(Aft of Datum) Straight line variations between weights C.G. Range (with Modification Fwd. of Datum Aft of Datum 252818) Wt. Lbs. % SMC In. % SMC In. (Gear and flaps 25,500 27.13 (3.72)* 33.53 9.50 Retracted) 25,100 25.00 (1.80)* - - 24,450 24.60 (1.44)* - - 24,450 21.80 1.07 - - 24,200 - - 36.47 12.15 22,400 - - 36.47 12.15 21,100 18.60 3.98 - - 20,950 - - 36.27 11.97 20,875 - - 33.80 9.74 20,600 - - 33.73 9.68 20,400 - - 30.33 6.61 A3EU Rev. 44 Page 55 of 105 - 55 - 19,000 - - 29.40 5.77 A3EU Rev. 44 Page 56 of 105 - 56 - XV. Beechcraft Hawker Model BH.125 Series 600A with Modification 252468 (Transport Aircraft) Approved October 15, 1981 (See NOTE 19) C.G. Range (with Modification Fwd. of Datum Aft of Datum 252818) Wt. Lbs. % SMC In. % SMC In. (Gear and flaps 16,300 18.00 4.52 - - Retracted) 14,700 - - 31.87 8.00 (cont.) 13,100 18.00 4.52 31.50 7.66 *(Aft of Datum) Straight line variations between weights Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1980 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights with Modification 252818 Maximum ramp weight 25,000 Lbs. 25,500 Lbs. (See NOTE 27) Maximum brake release weight 24,800 Lbs. 25,500 Lbs. (See NOTE 27) Maximum landing weight 22,000 Lbs. 22,000 Lbs. Maximum zero fuel weight 16,050 Lbs. 16,050 Lbs. Minimum zero fuel weight 13,100 Lbs. 13,100 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 180.25 to 223.11 100 310 Forward cabin (a) Side floor 245.85 to 303.85 50 (b) Center floor 245.86 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 397.80 to 422.30 60 130 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 612.5 4,080 5.60 Tank 2 612.5 4,080 5.60 Engines and lines 1.5 10 107.60 Ventral tank 131.0 873 88.60 Dorsal tank 61.0 406 119.30 Total 1,418.5 9,449 18.26 A3EU Rev. 44 Page 57 of 105 - 57 - XV. Beechcraft Hawker Model BH.125 Series 600A with Modification 252468 (Transport Aircraft) Approved October 15, 1981 (See NOTE 19) Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 93.69 1,059 No. 2 1.5 11.3 93.69 1,059 Total 3.0 22.6 93.90 2,118 Maximum Operating Altitude. 41,000 feet Serial Numbers Eligible. Same as listed previously for models BH/HS.125 Series 600A and HS.125 Series 600B, 600B/1, 600B/2 and 600B/3 XVI. British Aerospace Model BAe.125 Series 800A (Transport Aircraft) Approved July 12, 1984 (See NOTES 30, 40 & 64) British Aerospace Model BAe.125 Series 800A (C-29A) (Transport Aircraft) Approved December 12, 1989 (See NOTES 30 & 64) The C-29A variant was intended for Airborne Flight Inspection operations. British Aerospace Model BAe.125 Series 800A (U-125)(Transport Aircraft) Approved April 24, 1992 (See NOTE 40 & 64) The U-125 variant was intended for Airborne Flight Inspection operations. British Aerospace Model BAe.125 Series 800B (Transport Aircraft) Approved May 28, 1999. (See NOTE 57) Hawker 800 (name change) (Transport Aircraft) Approved January 28, 1994 (See NOTES 42, 57 & 64) The BAe.125 Series 800A/Hawker 800 and the BAe.125 Series 800B differs respectively from the HS.125 Series 700A and the HS.125 Series 700B aircraft in the following major respects: (i) Garrett Turbine Engine Company TFE 731-5R engines replace the Garrett AiResearch TFE 731-3 engines, (ii) The wing span is increased by 4 ft. 6 ins, (iii) Curved windscreens replace the existing flat panels, (iv) The rear fuselage underfairing is reshaped and the ventral tank is increased in capacity. The ventral fin is deleted, (v) The fin leading edge is extended forward and the dorsal fuel tank deleted, (vi) The nose wheel doors are sequenced to close after the gear is down, (vii) A stall identification (stick pusher) system is fitted, (viii) An Electronic Flight Instrument System (E.F.I.S.) is fitted, (ix) Increase in certificated taxiing, take- off, landing and zero fuel weights, and (x) Increase of MMO from 0.77 to 0.80. (See NOTE 36 & 42). Hawker 800 (U-125A) (Transport Aircraft) Approved December 9, 1994 (See NOTES 49 & 64) The U-125A variant was intended for use by the Japan Air Self Defense Force as a search and rescue aircraft. Engines 2 Garrett Turbine Engine Company TFE 731-5R turbofan engines Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F -34, Defence Standard 91-91, NATO Code F -35, ASTM.D.1655 Jet A or Jet A -1, CAN/CGSB 3.23/, MIL-T-83133 JP8 Grade. Aviation Wide-cut to specification Def ence Standard 91-88, NATO Code F -40, ASTM D.1655 Jet B, MIL-T-5624 JP4 and JP5 Grades, CAN/CGSB 3.22/ Jet B, GOST 10227-86 T-2 (See NOTE 28) Engine Limits TFE 731-5R TFE 731-5R with APR with APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 4,304 4,500 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 4,304 4,304 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 100 % 100 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100 % 100 % (29,692 rpm) (29,989 rpm) A3EU Rev. 44 Page 58 of 105 - 58 - XVI. Model BAe.125 Series 800A, Model BAe.125 Series 800A (C -29A), Model BAe125 Series 800A (U -125), Model BAe.125 Series 800B, Hawker 800 (name change), Hawker 800 (U-125A) (cont’d) Engine Limits (cont.) TFE 731-5R TFE 731-5R with APR with APR not operating operating Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 952oC 974oC Take-off (10 minutes maximum) 984oC 984oC Take-off (instantaneous) 994oC 994oC Maximum continuous 924oC 924oC Engine starting and relighting (unrestricted) 952oC 952oC Engine starting and relighting (10 seconds) 974oC 974oC Engine starting and relighting (5 seconds) above 974oC above 974oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % Airspeed Limits (IAS) VMO (maximum operating) With fuel in the ventral tank 280 knots With ventral tank empty or with the pannier 335 knots fitted to BAe. Mod 259292 (See NOTE 33) S.L. to 12,000 ft. decreasing linearly 1 kt. per 680 ft. to 310 kts. at 29,000 ft. VMO (maximum operating) (with Mod. 25B047A) 335 knots S.L. to 12,000 ft. decreasing linearly 1 kt. per 680 ft. to 313 kts. at 27,300 ft MMO (maximum operating) 0.80 M MMO (maximum operating) (with Mod. 25B047A) 0.78 M VA (maneuvering) Sea level 196 knots 10,000 ft. 202 knots 20,000 ft. 207 knots 30,000 ft. 217 knots 35,000 ft. 225 knots 38,000 ft. 231 knots 40,000 ft. 236 knots A3EU Rev. 44 Page 59 of 105 - 59 - 41,000 ft. 238 knots A3EU Rev. 44 Page 60 of 105 - 60 - XVI. Model BAe.125 Series 800A, Model BAe.125 Series 800A (C -29A), Model BAe125 Seri es 800A (U -125), Model BAe.125 Series 800B, Hawker 800 (name change), Hawker 800 (U-125A) (cont’d) Airspeed Limits (IAS) (cont.) VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 165 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) VMCA (with flaps 0o or 15o at sea level 115 knots for temperatures below 23oC VMCA (with either rudder bias 125 knots strut inoperative) VMCG (with flaps 0o or 15o at sea level 112 knots for temperatures below 23oC Datum The center of gravity datum (st ation 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 87.16 in. The leading edge of the SMC is 15. 70 in. forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 27,400 25.60 (6.61)* 31.80 12.02 26,600 - - 35.00 14.81 26,000 23.70 (4.96)* - - 25,800 19.20 (1.03)* - - 25,000 17.60 0.36 - - 24,000 16.40 1.40 35.00 14.81 23,000 15.60 2.10 - - 22,600 - - 33.20 13.24 22,400 - - 28.00 8.70 22,000 15.20 2.45 - - 21,400 - - 26.20 7.14 21,000 15.00 2.63 - - 20,000 - - 26.60 7.48 19,000 - - 27.30 8.09 18,000 - - 28.20 8.88 17,520 15.70 2.02 24.60 5.74 17,200 - - 29.20 9.75 16,600 - - 29.60 10.10 15,750 15.00 2.63 - - 15,400 15.70 2.02 - - 14,120 19.00 (0.86)* 28.60 9.23 *(Aft of Datum) A3EU Rev. 44 Page 61 of 105 - 61 - XVI. Model BAe.125 Series 800A, Model BAe.125 Seri es 800A (C -29A), Model BAe125 Series 800A (U -125), Model BAe.125 Series 800B, Hawker 800 (name change), Hawker 800 (U-125A) (cont’d) C.G. Range (with Modifications 259550 & Fwd. of Datum Aft of Datum 253169A) (Gear and Wt. Lbs. % SMC In. % SMC In. Flaps Retracted) 28,000 25.60 (6.61)* 32.00 12.19 27,150 - - 35.00 14.81 26,600 23.50 (4.78)* - - 26,500 19.50 (1.30)* - - 26,000 18.00 0.00 - - 25,000 16.80 1.06 - - 24,000 16.10 1.67 35.00 14.81 23,000 15.55 2.15 - - 22,600 - - 33.10 13.15 22,400 - - 28.40 9.05 22,000 15.20 2.45 - - 21,400 15.00 2.63 26.30 7.22 20,300 - - 26.60 7.48 18,000 15.70 2.02 24.60 5.74 17,600 - - 29.20 9.75 17,000 - - 29.60 10.10 15,600 15.00 2.63 - - 15,400 15.70 2.02 - - 14,120 19.00 (0.86)* 28.60 9.23 *(Aft of Datum) Straight line variations between weights. C.G. Range (with Mod. 25B047A) Fwd. of Datum Aft of Datum (Gear and Flaps Wt. Lbs. % SMC In. % SMC In. Retracted) 26,866 19.00 (0.86)* 23.30 .61 25,000 16.20 1.58 24.50 5.65 22,000 15.00 2.63 21.30 2.86 19,500 15.00 2.63 - - 19,200 - - 21.30 2.86 18,450 15.80 1.93 21.50 3.04 17,350 15.80 1.93 - - 17,000 - - 23.00 4.35 16,550 - - 23.00 4.35 *(Aft of Datum) Straight line variations between weights. Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1980 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights with Modifications 259550 & 253169A Maximum ramp weight 27,520 Lbs. 28,100 Lbs. (See NOTE 31) Maximum brake release weight 27,400 Lbs. 28,000 Lbs. (See NOTE 31) Maximum landing weight 23,350 Lbs. 23,350 Lbs. Maximum zero fuel weight 17,520 Lbs. 18,000 Lbs. (See NOTES 32 & 37) Minimum zero fuel weight 14,120 Lbs. 14,120 Lbs. A3EU Rev. 44 Page 62 of 105 - 62 - XVI. Model BAe.125 Series 800A, Model BAe.125 Series 800A (C -29A), Model BAe125 Series 800A (U -125), Model BAe.125 Series 800B, Hawker 800 (name change), Hawker 800 (U-125A) (cont’d) Maximum Weights (cont.) with Modification 25B047A Maximum ramp weight 26,866 Lbs. Maximum brake release weight 26,866 Lbs. Maximum landing weight 23,350 Lbs. Maximum zero fuel weight 18,450 Lbs. Minimum zero fuel weight 16,550 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 180.25 to 223.11 100 310 Forward cabin (a) Side floor 245.85 to 303.85 50 (b) Center floor 245.86 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 397.80 to 422.30 50 60 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 631.75 4208 8.20 Tank 2 631.75 4208 8.20 Ventral tank 231.80 1,544 100.40 Total 1,495.30 9,960 22.49 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.5 11.3 90.84 1,026 No. 2 1.5 11.3 90.84 1,026 Total 3.0 22.6 90.84 2,052 Maximum Operating Altitude. 41,000 feet Serial Numbers Eligible. BAe.125 Series 800A and 800B - 258001 through 258128, 258130, 258132, 258133, 258135 through 258150, 258152, 258153, 258155, 258157, 258160 through 258214, 258216 through 258226, 258228 through 258241, 258243, 258244, 258246, 258248, 258249, 258251 through 258254, (See NOTE 61); C-29A - 258129, 258131, 258134, 258154, 258156 and 258158 U-125 - 258215, 258227 and 258242 Hawker 800 - 258255 through 258265, 258267, 258269 through 258276 U-125A - 258245, 258247, 258250, 258268, 258288, 258305, 258306, 258325, 258333, 258341, 258348, 258360, 258370, 258381, 258407, 258427, 258445, 258469, 258493, 258513, 258533, 258610, 258629, 258685, 258735 and 258797, 258824 and 258843 A3EU Rev. 44 Page 63 of 105 - 63 - XVII. British Aerospace Model BAe.125 Series 1000A (Transport Aircraft) Approved October 31, 1991 (See NOTES 39, 45, 64& 66) British Aerospace Model BAe.125 Series 1000B (Transport Aircraft) Approved May 28, 1999 (See NOTES 45 & 58) Hawker 1000 (name change) Approved January 28, 1994.(See NOTES 41, 45, 64 and 66) The BAe.125 Series 1000A, 1000B and Hawker 1000 differs respectively from the BAe.125 Series 800A, 800B and Hawker 800 aircraft in the following major respects, (i) Pratt and Whitney Canada (P&WC) PW305 engines with Full Authority Digital Engine Control replace the Garrett Turbine Engine Company TFE 731-5R Engines, (ii) Fuselage is lengthened by 33 inches and the addition of a window on each side, (iii) A forward ventral tank is introduced and the aft ventral tank increased in capacity, (iv) An external rear baggage compartment loading door is introduced (See NOTE45), (v) Split pitch and roll control systems are introduced, (vi) A secondary pressure bulkhead is introduced between the toilet and the rear baggage, (vii) An increase in the Maximum Operating Altitude to 43,000 feet is introduced, and (vii) An increase in certificated taxiing, take-off, landing and zero fuel weights are introduced. Engines 2 Pratt & Whitney Canada (P&WC) PW305 turbofan engines, or 2 Pratt & Whitney Canada (P&WC) PW305B turbofan engines (Post Mod. 253650A) (See NOTE 43) Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F-34, Defence Standard 91-91, NATO Code F-35, ASTM.D.1655 (Jet A or Jet A-1), MIL-T-5624 - JP4 and JP5 Grades, MIL-T-83133 JP8 Grade, CAN/CGSB 3.23 (Jet A or A-1), GOST 10227-86 (TS-1 premium and RT.) Engine Limits PW305 engine PW305B engine Normal take-off static thrust (to 15OC OAT) lbs. 5,225 5,204 Maximum take-off static thrust (to 22OC OAT) lbs. 5,225 - Maximum take-off static thrust (to 23.5OC OAT) lbs. - 5,266 Maximum continuous thrust (to 19.4OC OAT) lbs. 4,750 - Maximum continuous thrust (to 27.5OC OAT) lbs. - 4,483 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 102 % 102 % (10,820rpm) (10,820 rpm) H.P. Shaft (N2) 102 % 102 % (27,469rpm) (47,469 rpm) Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 785oC 785oC Take-off (20 seconds maximum) 795oC 795oC Maximum continuous 785oC 785oC Engine starting and relighting (unrestricted) 680oC 680oC Maximum permissible oil temperature: Maximum oil temperature. 135oC 135oC Transient limit ( 20OC) 143oC 143oC A3EU Rev. 44 Page 64 of 105 - 64 - XVII. Model BAe.125 Series 1000A, Model BAe.125 Series 1000B, Hawker 1000 (name change) (cont’d) Engine Limits (cont.) PW305 engine PW305B engine Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +10oC +10oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 7 % 7 % Combined total air source 10 % 10 % Airspeed Limits (IAS) VMO (Maximum operating) with ventral tanks empty, up to 12,900 feet reducing by 1 kt. per 750 ft to 308 knots at 29,400 ft. 330 knots with ventral tanks not empty up to an altitude of 33,730 feet. 280 knots MMO (maximum operating) 0.80 M VA (Maneuvering) 200 knots VFE (Flap speeds) Deflection 15o 220 knots 25o 180 knots 45o 170 knots VLO (Landing gear operation) Retract 220 knots Extend 220 knots VLE (Landing gear extended) 220 knots with Modification VMC (Minimum control speed) 253650A VMCG (with flaps 0o or 15o at sea level 119 knots 119.5 knots for temperatures below 20oC VMCA (with flaps at 0o at sea level for temperatures below 20oC) 124 knots 116.5 knots VMCA (with flaps at 15o at sea level for temperatures below 20oC) 119 knots 111.5 knots Datum The center of gravity datum (station 353.04 inches) is 12.25 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 87.16 in. The leading edge of the SMC is 15.70 in., forward of the datum (for SMC definition, see Approved Flight Manual). C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC In. % SMC In. 31,000 22.00 (3.48)* 31.00 11.32 30,300 - - 33.40 13.41 29,000** 12.50 4.81 19.30 1.12 27,000 - - 34.00 13.93 26,500** 16.00 1.75 - - 24,000** 12.50 4.81 15.40 (2.24)*X 22,500 - - 31.40 11.67 22,000 15.00 2.63 - - 19,800*** 16.18 1.60 28.42 7.66 19,000 15.00 2.63 - - 19,000*** - - 31.00 11.32 A3EU Rev. 44 Page 65 of 105 - 65 - 16,300 16.00 1.75 - - A3EU Rev. 44 Page 66 of 105 - 66 - XVII. Model BAe.125 Series 1000A, Model BAe.125 Series 1000B, Hawker 1000 (name change) (cont’d) C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) (cont.) Wt. Lbs. % SMC In. % SMC In. 16,300*** 16.00 1.75 - - 15,800*** 20.80 (2.43)* 31.00 11.32 15,800 20.80 (2.43)* 33.30 13.32 *(Dimension Aft of Datum) **(Boundary Area for Fuel Transfer In-Flight only) ***(Boundary Area for Zero Fuel Weight) *X(Dimension Fwd of Datum) Straight line variations between weights. C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) (with Wt. Lbs. % SMC In. % SMC In. Modification 253379A) 31,000 22.00 (3.48)* 31.00 11.32 30,300 - - 33.40 13.41 29,000** 12.50 4.81 19.30 1.12 27,000 - - 34.00 13.93 26,500 16.00 1.75 - - 26,500** 16.00 1.75 - - 24,000** 12.50 4.81 15.40 (2.24)*X 22,500 - - 31.40 11.67 22,000 15.00 2.63 - - 20,300*** 16.20 1.58 26.80 7.66 19,000 15.00 2.63 - - 19,000*** - - 31.00 11.32 16,300 16.00 1.75 - - 16,300*** 16.00 1.75 - - 15,800*** 20.80 (2.43)* 31.00 11.32 15,800 20.80 (2.43)* 33.30 13.32 *(Dimension Aft of Datum) **(Boundary Area for Fuel Transfer In-Flight only) ***(Boundary Area for Zero Fuel Weight) *X(Dimension Fwd of Datum) Straight line variations between weights. Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1980 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 with Modification Maximum Weights 253379A Maximum ramp weight 31,100 lbs. 31,100 lbs. Maximum brake release weight 31,000 lbs. 31,000 lbs. Maximum landing weight 25,000 lbs. 25,000 lbs. Maximum zero fuel weight 19,800 lbs. 20,300 lbs. (See NOTES 38 & 44) Minimum zero fuel weight 15,800 lbs. 15,800 lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. A3EU Rev. 44 Page 67 of 105 - 67 - XVII. Model BAe.125 Series 1000A, Model BAe.125 Series 1000B, Hawker 1000 (name change) (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward Stowage Wardrobe 107.35 to 192.25 100 80 Forward Cabin (a) Side Floor 214.75 to 303.85 50 - (b) Center floor 214.75 to 303.85 60 - Aft Cabin (a) Side floor 303.85 to 381.75 50 - (b) Center floor 303.85 to 381.75 60 - Wardrobe 370.81 to 381.56 100 20 Aft Luggage Compartment 410.30 to 445.40 100 500 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 637.0 4243 8.24 Tank 2 637.0 4243 8.24 Fwd Ventral tank 164.0 1092 -87.78 Aft Ventral tank* 270.0 1798 109.07 Total 1,708.0 11,376 15.00 Usable Fuel (pressure refueled) Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 634.6 4227 8.24 Tank 2 634.6 4227 8.24 Fwd Ventral tank 160.4 1068 -87.78 Aft Ventral tank* 266.4 1774 109.07 Total 1,696.0 11,296 15.00 * If external toilet servicing facility is fitted See NOTE 62. Oil Capacity The oil tank has a capacity of 2.0 U.S. gallons of oil, of which 1.25 U.S. gallons may be consumed without adversely affecting the operation of the engine. The engine oil tank in the BAe.125 Series 1000A, 1000B and Hawker 1000 is an integral part of the engine. Maximum Operating Altitude. 43,000 feet Serial Numbers Eligible. BAe.125 Series 1000A and 1000B: 258151, 258159, 259004 through 259042. (See NOTE 61) Hawker 1000: 259003, 259043 through 259052. XVIII. Hawker 800XP (Transport Aircraft) Approved July 28, 1995 (See NOTES 47, 59, 64 and 65). The Hawker 800XP differs respectively from the BAe.125 Series 800A aircraft in the following major respects: (i) Allied Signal Engines TFE 731-5BR turbofan engines replace the Garrett Turbine Engine Company TFE 731-5R turbofan engines, (ii) Dee Howard TR5000BR thrust reversers fitted as standard, (iii) Increase in certificated ramp, take-off and maximum zero fuel weights, (iv) Vortilons replace wing fences and Hawker 1000 aileron servo tab gearing is introduced, (v) Rudder Bias moment arm is reduced to 2.72", (vi) Mach Trim System is fitted, (vii) 3 Wheel ECS is fitted as standard, (viii) 38 liter TKS tank is fitted, and (ix) Introduction of Hawker 800XP designation. Engines 2 Allied Signal Engines TFE 731-5BR turbofan engines. A3EU Rev. 44 Page 68 of 105 - 68 - XVIII. Hawker 800XP (cont’d) Fuel Aviation Kerosene to specification Defence Standard 91-87, NATO Code F-34, Defence Standard 91-91, NATO Code F-35, ASTM.D.1655 (Jet A or Jet A-1), CAN/COGS 3.23/ (Jet A or Jet A-1), Mil-T-83133 JP8 Grade, GOST 10227-86 (TS-1, T-1 or RT.), GB 6537-94/No.3. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F -40, ASTM D.1655 Jet B, MIL-T-5624 JP4 and JP5 Grades, CAN/COGS 3.22/ Jet B, GOST 10227-86 T-2 Engine Limits TFE 731-5BR TFE 731-5BR with APR with APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 4,750 4,750 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 4,634 4,634 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 100 % 100 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100.8 % 100.8 % (30,540 rpm) (30,540 rpm) TFE 731-5BR TFE 731-5BR with APR with APR not operating operating Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 978oC 996oC Take-off (5 second maximum) 1006oC 1006oC Take-off (2 second maximum) 1016oC 1016oC Maximum continuous 968oC 968oC Engine starting and relighting (unrestricted) 978oC 978oC Engine starting and relighting (10 seconds) 996oC 996oC Engine starting and relighting (5 seconds) above 996oC above 996oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent condition only) 5 % 5 % A3EU Rev. 44 Page 69 of 105 - 69 - XVIII. Hawker 800XP (cont’d) Airspeed Limits (IAS) VMO (maximum operating) With fuel in the ventral tank 280 knots With ventral tanks empty, Sea level to 335 knots 12,000 ft. decreasing linearly 1 knot per 680 ft. to 310 kts. at 29,000 ft. MMO (maximum operating) 0.80 M MMO (Mach Trimmer unserviceable/ 0.73 M inoperative) VA (maneuvering) Sea level 196 knots 10,000 ft. 202 knots 20,000 ft. 207 knots 30,000 ft. 217 knots 35,000 ft. 225 knots 38,000 ft. 231 knots 40,000 ft. 236 knots 41,000 ft. 238 knots VFE (Flap speeds) Deflection 15o 20 knots 25o 175 knots 45o 165 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) VMCA (with flaps 0o at sea level 114.0 knots for temperatures below 23o C) VMCA (with flaps 150 at sea level 108.0 knots for temperatures below 230 C) VMCG (with flaps 0o or 15O at sea level 115.5 knots for temperatures below 23oC) VMCL (with flaps 25o at sea level 106.0 knots for temperatures below 23oC) VMCL (with flaps 45o at sea level 105.0 knots for temperatures below 23oC) Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 87.16 in. The leading edge of the SMC is 15.70 in. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 70 of 105 - 70 - XVIII. Hawker 800XP (cont’d) C.G. Range (Gear and Flaps Retracted) Fwd. of Datum Aft of Datum Wt. Lbs. % SMC Ft. % SMC Ft. 28,000 *** 24.80 0.49 * 32.10 1.02 27,100 *** 23.40 0.39 * 35.00 1.23 27,000 *** 25.60 0.55 * - - 26,950 19.40 0.10 * - - 26,000 17.60 -0.03 - - 25,500 *** - - 29.00 0.80 25,000 16.60 -0.10 - - 24,000 *** - - 35.00 1.23 24,000 15.70 -0.17 - - 23,000 15.25 -0.20 - - 22,600 *** - - 33.00 1.09 22,400 *** - - 28.40 0.75 22,000 15.00 -0.22 - - 21,400 - - 26.30 0.60 20,400 - - 26.60 0.62 18,450 ** 15.70 -0.17 24.70 0.49 17,700 - - 29.20 0.81 17,000 ** - - 29.60 0.84 15,750 15.00 -0.22 - - 15,465 ** 15.70 -0.17 - - 14,120 ** 19.00 0.07 * 28.70 0.78 *(Dimension Aft of Datum) **(Boundary Area for Zero Fuel Weight) ***(Boundary Area obtainable with Full Ventral Tank fuel) Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1980 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Maximum ramp weight 28,120 Lbs. Maximum brake release weight 28,000 Lbs. Maximum landing weight 23,350 Lbs. Maximum zero fuel weight 18,450 Lbs. Minimum zero fuel weight 14,120 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. A3EU Rev. 44 Page 71 of 105 - 71 - XVIII. Hawker 800XP (cont’d) Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 180.25 to 234.24 100 225 Forward cabin (a) Side floor 245.85 to 303.85 50 (b) Center floor 245.86 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 397.80 to 422.30 100 210 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 634.00 4,223 8.20 Tank 2 634.00 4,223 8.20 Ventral tank (See NOTE 62) 233.00 1,552 100.40 Total 1,501.00 9,998 22.51 Usable Fuel (Pressure refueled) Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 631.60 4,207 8.20 Tank 2 631.60 4,207 8.20 Ventral tank (See NOTE 62) 229.40 1,528 100.40 Total 1,492.60 9,942 22.61 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.65 12.4 90.84 1,126 No. 2 1.65 12.4 90.84 1,126 Total 3.30 24.8 90.84 2,252 Maximum Operating Altitude 41,000 feet. Serial Numbers Eligible Hawker 800XP equipped with Honeywell SPZ 8000, or optional Collins EFIS 86 258266, 258277, 258279 through 258287, 258289 through 258304, 258307 through 258324, 258326 through 258332, 258334 through 258340, 258342 through 258347, 258349 through 258359, 258361 through 258369, 258371 through 258380, 258382 through 258406, 258408 through 258426, 258428 through 258444, 258446 through 258468,258470 through 258492, 258494 through 258512, 258514 through 258532, 258534 through 258540, 258542 through 258555, 258557 through 258566. Hawker 800XP equipped with Collins Pro Line 21 Serial Number 258278, 258541, 258556, 258567 through 258609, 258611 through 258628, 258630 through 258684, 258686 through 258734, 258736 through 258788, 258795, 258802, 258821, 258825, 258829, 258834, 258840, and 258847. A3EU Rev. 44 Page 72 of 105 - 72 - XIX. Hawker 850XP (Transport Aircraft) Approved February 28, 2006 (See NOTES 1, 2, 3, 8, 64, & 68). The Hawker 850XP differs respectively from the Hawker 800XP aircraft in the following major respects: Addition of winglets on the outboard wings. Engines 2 Allied Signal Engines TFE 731-5BR turbofan engines. Fuel Aviation Kerosene to specification Defence Standard 91-87, NAT O Code F-34, Defence Standard 91-91, NATO Code F -35, ASTM.D.1655 (Jet A or Jet A -1), CAN/COGS 3.23/ (Jet A or Jet A-1), Mil-T-83133 JP8 Grade, GOST 10227-86 (TS-1, T-1 or RT.), GB 6537- 94/No.3. Aviation Wide-cut to specification Defence Standard 91-88, NATO Code F -40, ASTM D.1655 Jet B, MIL-T-5624 JP4 and JP5 Grades, CAN/COGS 3.22/ Jet B, GOST 10227-86 T-2 Engine Limits TFE 731-5BR TFE 731-5BR with APR with APR not operating operating Take-off static thrust standard day, sea level conditions (5 minute limit) lbs. 4,750 4,750 Maximum continuous static thrust, standard day, sea level conditions (unrestricted) lbs. 4,634 4,634 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 100 % 100 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100.8 % 100.8 % (30,540 rpm) (30,540 rpm) TFE 731-5BR TFE 731-5BR with APR with APR not operating operating Maximum permissible interstage turbine temperature (ITT): Take-off (5 minutes maximum) 978oC 996oC Take-off (5 second maximum) 1006oC 1006oC Take-off (2 second maximum) 1016oC 1016oC Maximum continuous 968oC 968oC Engine starting and relighting (unrestricted) 978oC 978oC Engine starting and relighting (10 seconds) 996oC 996oC Engine starting and relighting (5 seconds) above 996oC above 996oC Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % A3EU Rev. 44 Page 73 of 105 - 73 - H.P. air source (descent condition only) 5 % 5 % A3EU Rev. 44 Page 74 of 105 - 74 - XIX. Hawker 850XP (cont’d) Airspeed Limits (IAS) VMO (maximum operating) With fuel in the ventral tank 280 knots With ventral tanks empty, Sea level to 335 knots 12,000 ft. decreasing linearly 1 knot per 680 ft. to 310 kts. at 29,000 ft. MMO (maximum operating) 0.80 M MMO (Mach Trimmer unserviceable/ 0.73 M inoperative) VA (maneuvering) Sea level 196 knots 10,000 ft. 202 knots 20,000 ft. 207 knots 30,000 ft. 217 knots 35,000 ft. 225 knots 38,000 ft. 231 knots 40,000 ft. 236 knots 41,000 ft. 238 knots VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 165 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) VMCA (with flaps 0o at sea level 114.0 knots for temperatures below 23o C) VMCA (with flaps 150 at sea level 108.0 knots for temperatures below 230 C) VMCG (with flaps 0o or 15O at sea level 115.5 knots for temperatures below 23oC) VMCL (with flaps 25o at sea level 106.0 knots for temperatures below 23oC) VMCL (with flaps 45o at sea level 105.0 knots for temperatures below 23oC) Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fusel age reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 87.16 in. The leading edge of the SMC is 15.70 in. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 75 of 105 - 75 - XIX. Hawker 850XP (cont’d) C.G. Range (Gear and Flaps Retracted) Forward Limits Aft Limits with Empty Ventral Tank Aft Limits with Full Ventral Tank Wt. Lbs. % SMC *Ft. % SMC *Ft. % SMC *Ft. 28,000 ** 24.78 +0.49 N/A 32.08 +1.02 27,100 23.40 +0.39 N/A 34.98 +1.23 27,000 20.72 +0.20 25.57 +0.55 34.98 +1.23 26,950 19.37 +0.10 25.68 +0.56 34.98 +1.23 26,000 17.57 -0.03 27.84 +0.72 34.98 +1.23 25,500 17.07 -0.07 28.98 +0.80 34.98 +1.23 25,000 16.57 -0.10 28.88 +0.79 34.98 +1.23 24,000 15.67 -0.17 28.68 +0.78 34.98 +1.23 23,350 15.37 -0.19 28.59 +0.77 N/A 23,000 15.18 -0.20 28.49 +0.76 33.54 +1.13 22,600 15.05 -0.21 28.41 +0.76 32.97 +1.09 22,400 15.09 -0.21 28.37 +0.75 N/A 22,000 14.97 -0.22 27.53 +0.69 N/A 21,400 14.97 -0.22 26.27 +0.60 N/A 20,400 14.97 -0.22 26.57 +0.62 N/A 18,450 *** 15.67 -0.17 24.68 +0.49 N/A 17,700 14.97 -0.22 29.17 +0.81 N/A 17,000 *** 15.67 -0.17 29.57 +0.84 N/A 16,100 14.97 -0.22 29.29 +0.82 N/A 15,750 14.97 -0.22 29.18 +0.81 N/A 15,465 *** 15.67 -0.17 29.09 +0.81 N/A 14,120 *** 18.97 +0.07 28.67 +0.78 N/A * Feet from CG Datum (negative is forward and positive is aft) ** Applicable with Full Ventral Tank Only *** Zero Fuel Weight Limits C.G. Range (Cont.) Item (Extending) Moment Change In. Lb. Wing flaps 15o +538 25o +879 45o +1593 Main landing gear -1980 Nose landing gear +1380 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Minimum Crew For all flights, 2 pilots Maximum ramp weight 28,120 Lbs. Maximum brake release weight 28,000 Lbs. Maximum landing weight 23,350 Lbs. Maximum zero fuel weight 18,450 Lbs. Minimum operating weight 16,100 Lbs. Minimum zero fuel weight 14,120 Lbs. A3EU Rev. 44 Page 76 of 105 - 76 - XIX. Hawker 850XP (cont’d) Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual weight and balance section, or Weight and Balance Manual. Maximum Baggage Compartment Body Maximum Capacity Station Load Pounds Lb/Ft2 (See NOTE 8) Forward 180.25 to 234.24 100 225 Forward cabin (a) Side floor 245.85 to 303.85 50 (b) Center floor 245.86 to 303.85 60 Aft cabin (a) Side floor 303.85 to 395.3 50 (b) Center floor 303.85 to 395.3 60 Aft 397.80 to 422.30 100 210 Fuel Capacity Usable Fuel Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 634.00 4,223 8.20 Tank 2 634.00 4,223 8.20 Ventral tank (See NOTE 62) 233.00 1,552 100.40 Total 1,501.00 9,998 22.51 Usable Fuel (Pressure refueled) Location Volume Maximum Arm U.S. Gal Weight Lbs. In. Tank 1 631.60 4,207 8.20 Tank 2 631.60 4,207 8.20 Ventral tank (See NOTE 62) 229.40 1,528 100.40 Total 1,492.60 9,942 22.61 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. In. In. Lbs. No. 1 1.65 12.4 90.84 1,126 No. 2 1.65 12.4 90.84 1,126 Total 3.30 24.8 90.84 2,252 Maximum Operating Altitude 41,000 feet. Serial Numbers Eligible Serial Number 258789 through 258794, 258796, 258798 through 258801, and 258803 through 258819, 258822, 258823, 258826 through 258828, 258830 through 258833, 258835 through 258838, 258841, 258844, 258845, 258848, 258852, 258855, 258856, 258858, 258859, 258861, 258872, 258874, 258876, 258891, 258893, 258895, 258900, 258901, 258904, 258907, 258909, 258912, 258915, 258921, 258959, 258961, 258963, 258977, 258980, 258982 through 258984. A3EU Rev. 44 Page 77 of 105 - 77 - XX. Hawker 900XP (Transport Aircraft) Approved August 24, 2007 (See NOTES 1, 2, 3, 8, 63, 64 & 69). The Hawker 900XP differs respectively from the Hawker 850XP aircraft in the following major respects: Honeywell Aerospace TFE731-50R turbofan engines replacing the TFE731-5BR engines, and updated Rockwell Collins Pro Line 21 Avionics to integrate with the new engine limitations in the cockpit. Engines 2 Honeywell Aerospace TFE731-50R turbofan engines. Fuel Aviation Kerosene to specification Defense Standard 91-87, NATO Code F-34, Defense Standard 91-91, NATO Code F-35, ASTM.D.1655 (Jet A or Jet A-1), CAN/CGSB 3.23/ (Jet A or Jet A-1), Mil-T-83133 JP8 Grade, GOST 10227-86 (TS-1 or RT.), GB 6537- 94/No.3. Aviation Wide-cut to specification Defense Standard 91-88, NATO Code F-40, ASTM D.1655 Jet B, MIL-T-5624 JP4 and JP5 Grades, CAN/CGSB 3.22/ Jet B, GOST 10227- 86 T-2 Engine Limits TFE 731-50R with APR not operating TFE 731-50R with APR operating Take-off static thrust: standard day, sea level conditions (5 minute limit) lbs. 4,750 4,750 Maximum continuous static thrust: standard day, sea level conditions (unrestricted) lbs. 4,634 4,634 Maximum permissible engine rotor operating speed L.P. Shaft (N1) 100% (21,000 rpm) 100% (21,000 rpm) H.P. Shaft (N2) 100 % (31,485 rpm) 101 % (31,800 rpm) Maximum permissible Interstage Turbine Temperature (ITT): Take-off (5 minutes maximum) 999oC 1022oC Maximum continuous 991oC 991oC Engine starting and relighting (Unrestricted) 994oC 994oC Maximum permissible oil temperature: Sea level to 30,500 ft. 127oC 127oC Above 30,500 ft. 140oC 140oC Transient temperature above maximum at any altitude for a duration of not more than two minutes 149oC 149oC Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5% 5% H.P. air source (climb and cruise condition) 3% 3% H.P. air source (descent condition) 5% 5% A3EU Rev. 44 Page 78 of 105 - 78 - XX. Hawker 900XP (cont’d) Airspeed Limits (IAS) VMO (maximum operating) With fuel in the ventral tank 280 knots With ventral tanks empty, Sea level to 12,000 ft. decreasing linearly 1 knot per 680 ft. to 310 kts. at 29,000 ft. 335 knots MMO (maximum operating) 0.80 M MMO (Mach Trimmer unserviceable/inoperative) 0.73M VA (maneuvering) Sea level 196 knots 10,000 ft. 202 knots 20,000 ft. 207 knots 30,000 ft. 217 knots 35,000 ft. 225 knots 38,000 ft. 231 knots 40,000 ft. 236 knots 41,000 ft. 238 knots VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 165 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) 114.0 knots VMCA (with flaps 0o at sea level for temperatures below 23o C) 114.0 knots (with flaps 150 at sea level for temperatures below 230 C) 108.0 knots VMCG (0 Kt Crosswind) (with flaps 0o or 15O at sea level for temperatures below 23oC) 115.5 knots VMCL (with flaps 25o at sea level for temperatures below 23o C) 106.0 knots (with flaps 450 at sea level for temperatures below 230 C) 105.0 knots Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is a placard-identified screw on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 7.263 ft.. The leading edge of the SMC is 1.308 ft. forward of the c.g. datum. A3EU Rev. 44 Page 79 of 105 - 79 - XX. Hawker 900XP (cont’d) C.G. Range (Gear and Flaps Retracted) Forward Limits Aft Limits with Empty Ventral Tank Aft Limits with Full Ventral Tank Wt. Lbs. % SMC *Ft. % SMC *Ft. % SMC *Ft. 28,000 ** 24.78 +0.49 N/A 32.08 +1.02 27,100 23.40 +0.39 N/A 34.98 +1.23 27,000 20.72 +0.20 25.57 +0.55 34.98 +1.23 26,950 19.37 +0.10 25.68 +0.56 34.98 +1.23 26,000 17.57 -0.03 27.84 +0.72 34.98 +1.23 25,500 17.07 -0.07 28.98 +0.80 34.98 +1.23 25,000 16.57 -0.10 28.88 +0.79 34.98 +1.23 24,000 15.67 -0.17 28.68 +0.78 34.98 +1.23 23,350 15.37 -0.19 28.59 +0.77 N/A 23,000 15.18 -0.20 28.49 +0.76 33.54 +1.13 22,600 15.05 -0.21 28.41 +0.76 32.97 +1.09 22,400 15.09 -0.21 28.37 +0.75 N/A 22,000 14.97 -0.22 27.53 +0.69 N/A 21,400 14.97 -0.22 26.27 +0.60 N/A 20,400 14.97 -0.22 26.57 +0.62 N/A 18,450 *** 15.67 -0.17 24.68 +0.49 N/A 17,700 14.97 -0.22 29.17 +0.81 N/A 17,000 *** 15.67 -0.17 29.57 +0.84 N/A 16,100 14.97 -0.22 29.29 +0.82 N/A 15,750 14.97 -0.22 29.18 +0.81 N/A 15,465 *** 15.67 -0.17 29.09 +0.81 N/A 14,120 *** 18.97 +0.07 28.67 +0.78 N/A * Feet from CG Datum (negative is forward and positive is aft) ** Applicable with Full Ventral Tank Only *** Zero Fuel Weight Limits Item (Extending) Moment Change Lb.-ft. Wing flaps 15o +45 25o +73 45o +133 Main landing gear -165 Nose landing gear +115 The airplane is weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 Maximum Weights Minimum Crew For all flights, 2 pilots Maximum ramp weight 28,120 Lbs. Maximum brake release weight 28,000 Lbs. Maximum landing weight 23,350 Lbs. Maximum zero fuel weight 18,450 Lbs. Minimum operating weight 16,100 Lbs. Minimum zero fuel weight 14,120 Lbs. A3EU Rev. 44 Page 80 of 105 - 80 - Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Airplane Flight Manual. A3EU Rev. 44 Page 81 of 105 - 81 - XX. Hawker 900XP (cont’d) Maximum Baggage Variable – Refer to the serial specific FAA Airplane Flight Manual. Fuel Capacity Usable Fuel (Gravity Refuel) Location Volume Maximum Arm U.S. Gal Weight Lbs. Ft. Tank 1 634.00 4,223 0.68 Tank 2 634.00 4,223 0.68 Ventral tank (See NOTE 62) 233.00 1,552 8.37 Total 1,501.00 9,998 1.87 Usable Fuel (Pressure refueled) Location Volume Maximum Arm U.S. Gal Weight Lbs. Ft. Tank 1 631.60 4,207 0.68 Tank 2 631.60 4,207 0.68 Ventral tank (See NOTE 62) 229.40 1,528 8.37 Total 1,492.60 9,942 1.86 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. Ft. Lb.-Ft. No. 1 3.01 24.09 8.49 204.52 No. 2 3.01 24.09 8.49 204.52 Total 6.02 48.18 8.49 409.05 Maximum Operating Altitude 41,000 feet. Serial Numbers Eligible Serial Number HA-0001 through HA-0108, HA-0110, HA-0112 through HA-0114, HA- 0117, HA-0120, HA-0121, HA-0140, HA-0143, HA-0146 through HA-213. XXI. Hawker 750 (Transport Aircraft) Approved February 08, 2008 (See NOTES 1, 2, 3, 8, 63, 64 & 70). The Hawker 750 differs respectively from the Hawker 800XP, which retains the certification basis and is similar in configuration with the following exceptions: a) External Baggage Unit: The Hawker 750 incorporates as standard equipment, an external baggage unit in place of the aft ventral fuel tank installed on the Hawker 800XP. The standard configuration of the Hawker 750 uses the previously certified external baggage unit with improvements. This baggage unit meets the requirements of 14 CFR 25.857(d)(1)(2)(3)(5) as Amended through 25-32 for Class D baggage compartments. b) MTOW: The range and MTOW of the Hawker 750 is less than that of the Hawker 800XP as a result of the decrease in available fuel. Changes to the weight and center of gravity envelope reflect the alternative loading capabilities provided with the external baggage unit. c) Avionics: Hawker 750 Pro Line 21 avionics installation is revised to include a single FMS-6000/Single GPS in lieu of a dual installation. d) Introduction of Hawker 750 designation. Engines 2 Honeywell Aerospace TFE 731-5BR turbofan engines. Fuel Aviation Kerosene to specification Defense Standard 91-87, NATO Code F-34, Defense Standard 91-91, NATO Code F-35, ASTM.D.1655 (Jet A or Jet A-1), CAN/COGS 3.23/ (Jet A or Jet A-1), Mil-T-83133 JP8 Grade, GOST 10227-86 (TS-1, T-1 or RT.), GB 6537- 94/No.3. Aviation Wide-cut to specification Defense Standard 91-88, NATO Code F-40, ASTM D.1655 Jet B, MIL-T-5624 JP4 and JP5 Grades, CAN/COGS 3.22/ Jet B, GOST 10227-86 T-2 A3EU Rev. 44 Page 82 of 105 - 82 - XXI. Hawker 750 (cont’d) Engine Limits TFE 731-5BR TFE 731-5BR with APR with APR not operating operating Take-off static thrust: standard day, sea level conditions 4,750 4,750 (5 minute limit) lbs. Maximum continuous static thrust: standard day, sea level conditions 4,634 4,634 (unrestricted) lbs. Maximum permissible engine rotor operating speed: L.P. Shaft (N1) 100 % 100 % (21,000 rpm) (21,000 rpm) H.P. Shaft (N2) 100.8 % 100.8 % (30,540 rpm) (30,540 rpm) Maximum permissible Interstage Turbine Temperature (ITT): Take-off (5 minutes maximum) 978oC 996oC Take-off (5 second maximum) 1006oC 1006oC Take-off (2 second maximum) 1016oC 1016oC Maximum continuous 968oC 968oC Engine starting and relighting 978oC 978oC (unrestricted) Engine starting and relighting 996oC 996oC (10 seconds) Engine starting and relighting above 996oC above 996oC (5 seconds) Maximum permissible oil temperature: Sea level to 30,000 ft. 127oC 127oC Above 30,000 ft. 140oC 140oC Transient temperature above maximum 149oC 149oC at any altitude for a duration of not more than two minutes Minimum permissible oil temperature: Engine starting -40oC -40oC Before take-off +30oC +30oC Maximum permissible air bleed extraction: L.P. air source 5 % 5 % H.P. air source (climb and cruise condition) 3 % 3 % H.P. air source (descent only) 5 % 5 % A3EU Rev. 44 Page 83 of 105 - 83 - XXI. Hawker 750 (cont’d) Airspeed Limits (IAS) VMO (maximum operating) Sea level to 12,000 ft. decreasing 335 knots linearly 1 knot per 680 ft. to 310 Kts. at 29,000 ft. MMO (maximum operating) 0.80 M MMO (Mach Trimmer unserviceable/ 0.73 M inoperative) VA (maneuvering) Sea level 196 knots 10,000 ft. 202 knots 20,000 ft. 207 knots 30,000 ft. 217 knots 35,000 ft. 225 knots 38,000 ft. 231 knots 40,000 ft. 236 knots 41,000 ft. 238 knots VFE (Flap speeds) Deflection 15o 220 knots 25o 175 knots 45o 165 knots VLO (landing gear operation) Retract 220 knots Extend 220 knots VLE (landing gear extended) 220 knots VMC (minimum control speed) 114.0 knots VMCA (with flaps 0o at sea level 114.0 knots for temperatures below 23o C) VMCA (with flaps 150 at sea level 108.0 knots for temperatures below 230 C) VMCG (with flaps 0o or 15O at sea level 115.5 knots for temperatures below 23oC) VMCL (with flaps 25o at sea level 106.0 knots for temperatures below 23oC) VMCL (with flaps 45o at sea level 105.0 knots for temperatures below 23oC) Datum The center of gravity datum (station 353.04 inches) is 11 feet forward of the fuselage reference point. The reference point is defined by an eye bolt on the fuselage skin located beneath the starboard engine pod. Standard Mean Chord (SMC) 7.263 ft. The leading edge of the SMC is 1.308 ft. forward of the datum (for SMC definition, see Approved Flight Manual). A3EU Rev. 44 Page 84 of 105 - 84 - XXI. Hawker 750 (cont’d) C.G. Range (Gear and Flaps Fwd. of Datum Aft of Datum Retracted) Wt. Lbs. % SMC *Ft. % SMC *Ft. 27,000 20.7 +0.20 25.6 +0.55 26,950 19.4 +0.10 25.7 +0.56 26,000 17.6 -0.03 27.9 +0.72 25,500 17.1 -0.06 29.0 +0.80 24,000 15.7 -0.17 28.7 +0.78 23,350 15.4 -0.19 28.6 +0.77 23,000 15.3 -0.20 28.5 +0.76 22,400 15.1 -0.21 28.4 +0.76 22,000 15.0 -0.22 27.6 +0.69 21,400 15.0 -0.22 26.3 +0.60 20,400 15.0 -0.22 26.6 +0.62 18,450** 15.7 -0.17 24.7 +0.49 17,700 15.0 -0.22 29.2 +0.81 17,000** 15.7 -0.17 29.6 +0.84 15,750 15.0 -0.22 29.2 +0.81 15,465** 15.7 -0.17 29.1 +0.81 14,120** 19.0 +0.07 28.7 +0.78 *Feet from CG Datum (negative is forward and positive is aft) with straight line variation between points shown. **Zero Fuel Weight Limits Item (Extending) Moment Change Lb-Ft. Wing flaps 15° +45 25° +73 45° +133 Main landing gear -165 Nose landing gear +115 The airplane is normally weighed with wing flaps retracted. Leveling Means Fore and aft alignment bolts are situated in the fuselage seat rails at stations 309.35 and 371.55 inches. Maximum Weights Maximum Ramp Weight (Straight line variation from 27,070 lbs. to 27,120 Lbs. @ 0.20 ft. and 27,120 lbs. thereafter) 27,120 Lbs. Maximum Brake Release Weight (Straight line variation from 26,950 lbs. to 27,000 Lbs. @ 0.20 ft. and 27,000 lbs. thereafter) 27,000 Lbs. Maximum Landing Weight 23,350 Lbs. Maximum Zero Fuel Weight 18,450 Lbs. Minimum Zero Fuel Weight 14,120 Lbs. Minimum Crew For all flights, 2 pilots Maximum Passengers 15 Maximum – For FAA approved seating configuration, refer to serial specific FAA Approved Airplane Flight Manual. A3EU Rev. 44 Page 85 of 105 - 85 - XXI. Hawker 750 (cont’d) Maximum Baggage Compartment Centroid Maximum Capacity Ft. Load Lbs. Lb/Ft2 (See NOTE 8) External Baggage Unit 7.66 100 500 Forward Bay 6.03 100 280 Middle Bay 9.35 100 315 Aft Bay 12.26 100 80 Cabin Variable Refer to the serial specific FAA Approved Airplane Flight Manual, Weight & Balance Section 6, Part 2 – (See Note 8) Fuel Capacity Usable Fuel (Gravity Refuel) Location Volume Maximum Arm U.S. Gal. Weight Lbs. Ft. Tank 1 634.0 4,223 0.68 Tank 2 634.0 4,223 0.68 Total 1,268.0 8,446 0.68 Usable Fuel (Pressure Refuel) Location Volume Maximum Arm U.S. Gal Weight Lbs. Ft. Tank 1 631.6 4,207 0.68 Tank 2 631.6 4,207 0.68 Total 1,263.2 8,414 0.68 Oil Capacity Engine Tank Oil is the oil that is required for circulation in the system. Location Volume Maximum Arm Moment U.S. Gal Weight Lbs. Ft. Lbs. Ft. No. 1 1.65 12.4 7.57 94 No. 2 1.65 12.4 7.57 94 Total 3.30 24.8 7.57 188 Maximum Operating Altitude 41,000 feet. Serial Numbers Eligible Serial Number HB-1 through HB-35, HB-41, HB-43, HB-62, HB-63, HB-65, HB-67 through HA-74. A3EU Rev. 44 Page 86 of 105 - 86 - Data Pertinent to all Models. Required Equipment. The basic required equipment as prescribed in the applicable Airworthiness (See Certification Basis) and Operating Regulations must be installed in the aircraft for certification. The BH/DH/HS/BAe.125 and Hawker Aircraft Maintenance Schedule (MS) publications reference MS.125-1/400 (Series 1A, 1B, 1A-522, 1B-522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA, 3B/RB, 3B/RC, F3B, F3B/RA, 400A, 400B, 401B, 403A(C), 403B, F400B and F403B), MS.125-600 (Series 600A, 600B, F600B, 600B/1, 600B/2 and 600B/3), MS.125-700 (Series 700A and 700B), MS.125-800 (Series 800A, 800B and Hawker 800), MS. Hawker 800 C29A (Hawker 800 C29A), MS U125 (Hawker 800 U-125), MS U125A (Hawker 800 U- 125A), MS.800XP (Hawker 800XP/Hawker 850XP) and MS.125-1000 (Series 1000A, 1000B and Hawker 1000) contain lists of all required inspection schedules pertinent to the model variants specified herein and optional equipment installations approved by the FAA, and identifies all life-limited items (See NOTE 3). Document 25.6PF.61 Fin Tank Refuel instructions is required for HS.125 Series 600A and 600B Certification. Document 25.7PF.83 Single Point Pressure Refuel Instructions is required for HS.125 Series 700A and 700B Certification. Document 25-8PF59-1 Pressure Refueling Instructions is required for BAe.125 Series 800A, BAe.125 Series 800B, Hawker 800, and Hawker 800XP Certification. Document 140-590037-PRF, Pressure Refueling Instructions, is required for Hawker 900XP certification. Document DO1W02102- 0005(/25-8PF-317), Pressure Refueling Instructions, is required for Hawker 750 certification. Document 25-9PF 212, Pressure Refueling Instructions, is required for BAe.125 Series 1000A, 1000B and Hawker 1000 Certification. Control Surface Movements. To ensure proper operation of the airplane the movement of the various control surfaces must be carefully controlled by proper rigging of the flight control systems. The airplane must, therefore, be rigged according to the approved data contained in the Maintenance Manuals (MM or AMM). Publication reference MM.125 (Series 1A, 1B, 1A-522, 1B- 522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA, 3B/RB, 3B/RC, F3B, F3B/RA, 400A, 400B, 400B/1, 401B, 403A(C), 403B, F400B, F403B, 600A, 600B, 600B/1, 600B/2, 600B/3 and F600B) or MM.125-700 (HS.125 Series 700A and 700B), AMM 125-800 Vol. 1-3 (BAe.125 Series 800A, 800B and Hawker 800), AMM C29A Vol. 1-3 (Hawker 800 C29A), AMM U125 Vol. 1-3 (Hawker 800 U-125), AMM U125A Vol. 1-3 (Hawker 800 U-125A), AMM 125-1000A Vol. 1-3 (BAe.125 Series 1000A, 1000B and Hawker 1000), AMM Hawker 800XP Vol. 1-3 (Hawker 800XP) and AMM Supplement (Hawker 850XP), AMM Hawker 900XP Vol. 1- 3 (Hawker 900XP), AMM Hawker 750 Vol. 1-3 (Hawker 750). Certification Basis. Application for Type Certificate to the UK CAA was dated September 28, 1960. CAR.10, British Civil Airworthiness Requirements (1st November 1963), and Special Conditions notified by the United States Government to the Government of the United Kingdom including Validation Arrangements (V.A.) Note 1, Issue 1 dated April 19, 1961. This certification is equivalent to CAR.4b dated December 1953, Amendment 4b- 1 through 4b-11, exclusive of CAR 4b.350 (e) and includes Special Regulation SR.422B. A3EU Rev. 44 Page 87 of 105 - 87 - Certification Basis: (cont.) CAR.10, Type Certificate No. A3EU issued September 25, 1964. The Type Certificate was amended February 3, 1966, to include Model DH.125 Series 1A-522, amended November 7, 1966 to include Model DH.125 Series 3A, amended August 9, 1967 to include Model DH.125 Series 1A/R-522 and Model DH.125 Series 3A/R, amended February 15, 1968, to include Model DH.125 Series 1A/S-522 and Model DH.125 Series 3A/RA, amended November 15, 1968, to include Model DH.125 Series 400A, amended July 14, 1970, to include BH.125 Series 400A, amended August 17, 1972, to include BH.125 Series 600A, amended January 6, 1976, to include HS.125 Series 600A, amended May 20, 1977, to include HS.125 Series 700A, amended July 12, 1984 to include BAe.125 Series 800A, amended October 31, 1991, to include BAe.125 Series 1000A, amended January 28, 1994, to include Hawker 800 and Hawker 1000, amended July 28, 1995, to include Hawker 800XP, amended May 28, 1999 to include HS.125 Series 1B, 1B-522, 1B/R-522, 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB, 3B/RC, F3B, F3B/RA, 400B, 400B/1, 401B, 403A(C), 403B, F400B, F403B, 600B, 600B/1, 600B/2, 600B/3, F600B, 700B, and BAe.125 Series 800B and 1000B. Compliance, over and above, certification basis requirements, has been met with CAR Amendments 4B-12 and 4B-14. Compliance has been established with the following optional requirements: Ice Protection Provision 4b.640. FAA Exemption No. 573 grants exemption from CAR 4b.437, however for DH.125 Series 400A and subsequent models added to this Type Certificate, compliance has been established for Fuel Jettisoning Systems certification weights with FAR 25.1001 of Amendment 25-18. For BH.125 and HS.125 Series 600A models compliance has been established with the special retroactive requirements of FAR 25.2 through FAR Amendment 25-20 and FAR 21 Amendment 21- 27 and (FAR 36(1)(c)(2)). (See NOTE 18). HS.125 Series 1A, 3A, 3A/RA and BH/HS.125 Series 400A and 600A airplanes fitted with Garrett AiResearch TFE 731-3 engines comply with the later requirements of FAR 21.183(e) amendment 21-42 and FAR 36.1(d) amendment 36-1 through 36-5. For HS.125 Series 700A models, compliance has been established with the special retroactive requirements of FAR 25.2 through amendment 25-20; FAR 25.979 of amendment 25-11, FAR 21.183(e) of amendment 21-42, and FAR 36.1(d) for amendment 36-1 through 36-5. For BAe.125 Series 800A models, compliance has been established with the specific additional requirements of FAR Part 25, Amendment 25-1 through 25-54, above and beyond the CAR. 10, British Civil Airworthiness Requirements specified in the second paragraph above under "Certification Basis." The additional FAR requirements are as follows: FAR 25.2 FAR 25.305 (For wing only) FAR 25.571 (For wing and engine mounts only) (See NOTE 3) FAR 25.903 (d) (1) FAR 25.979 (a) through (c) FAR 25.1419 FAR 25.1529 Plus FAR Part 36 as amended by Amendment 36-1 through 36-12. Plus Special Federal Aviation Regulation (SFAR) 27 as amended by Amendments 27-1 through 27-4. Equivalent Safety is established with: FAR 25.773(b)(2) - Pilots Window FAR 25.613(a) - Design Values FAR 25.615(a) - Design Properties A3EU Rev. 44 Page 88 of 105 - 88 - Certification Basis: (cont.) Equivalent Level of Safety (FAA Memo No. TD4610WI-T-SE-2) has been established for CAR 4b.635(c) Aft Position Light on Models HS.125 Series 700A/B, BAe.125 Series 800A/B, BAe.125 Series 800A (U-125), Hawker 800, Hawker 800 (U-125A), BAe.125 Series 1000A/B and Hawker 1000. For Hawker 800XP and 850XP airplanes fitted with Allied Signal TFE 731-5BR engines, for Hawker 750 airplanes fitted with Honeywell Aerospace TFE731-5BR engines, and for Hawker 900XP airplanes fitted with Honeywell Aerospace TFE731-50R engines: The U.S. Certification Basis for BAe.125 Series 800A models (including equivalent safety findings) and, in agreement with the manufacturer, compliance has been established with the following additional FAR requirements: For the Engine Electronic Controls and Mach Trim System: FAR 25.1316 as amended through amendment 25-80 and Special Condition No. 25-ANM-98 High-Intensity Radiated Fields For the thrust reverser installation: FAR 25.933 as amended through amendment 25-40 FAR 25.934 as amended through amendment 25-23 FAR 25.1309 as amended through amendment 25-23 Plus FAR Part 34 basic issue. Plus FAR Part 36 as amended by Amendments 36-1 through 36-20 Plus Equivalent Safety Finding to CAR 4B.635(c), FAA Memo No. TD4610WI-T-SE-1, for Aft Position Light Chromaticity. For the Collins ProLine 21 Avionics install ations the additional 14 CFR Part 25, Amendment 25-1 through 25-97 (with exception noted), requirements are as follows: 25.301(a),(b) 25.843(a) 25.303 25.853(a) 25.305(a),(b) 25.869 25.307(a) 25.1301 25.321 25.1303 25.331 25.1305(a),(c),(d) 25.333 25.1307 (c), (d),(e) 25.337 25.1309(a),(b),(c),(d),(e) 25.341 25.1316 25.345 25.1321(a),(b),(c),(d),(e) 25.349 25.1323(a),(b),(c),(d) 25.351 25. 1325(a),(c)(d),(e) 25.365(a),(b),(d) 25. 1327(a) 25.367 25.1329(a),(c),(e),(f),(h) 25.373 25.1331 25.391(b) 25.1333 25.395(b) 25.1335 25.397(b) 25.1337(b),(c) 25.561 25.1351(a),(b),(d) 25.581(a)(c) 25.1353(a),(b) 25.601 25.1355 25.603 25.1357(a),(c),(d),(e),(g) 25.605(a) 25.1381 25.609(a) 25.1431(a),(c) 25.613(a) 25.1529 25.629(a) 25.1543(b) 25.672 25.1547(a),(d) 25.677(a)(b) 25.1549(a),(b),(c),(d) 25.683 25.1553 25.773(a)(2) 25.1581 25.777(d) 25.1583 amdt (25-105) 25.779 25.1585 amdt (25-105) 25.1587 Certification Basis: (cont.) A3EU Rev. 44 Page 89 of 105 - 89 - Special Condition No. 25-181-SC High Intensity Radiated Fields (HIRF) Equivalent Level of Safety is established with: 14CFR25.1549 – digital presentation of N2, oil temperature, oil pressure and fuel flow For the Universal Avionics CVR-120R installation: 14 CFR 25.1457 as amended through amendment 25-124 For the Hawker 850XP, the Hawker 800XP with Honeywell SPZ-8000 Avionics, or the Hawker 800XP with Rockwell Collins ProLine 21 Avionics airplanes, the addition of the following for the regulations winglets: 14 CFR 25.445(a), as amended through 25-86 14 CFR 25.581(b) as amended through 25-23 14 CFR 25.615(a) as amended through 25-23 14 CFR 25.954(a)(b) as amended through 25-14 For the Hawker 900XP airplanes compliance has also been established with the following additional FAR requirements: 14 CFR 25.901 (b) (1) (i) as amended through 25-46 14 CFR 25.903 (a) (b) (e) (1) (2) as amended through 25-40 14 CFR 25.939 (a) (c) as amended through 25-40 14 CFR 25.943 as amended through 25-40 14 CFR 25.1322 (a) (b) (c) (d) as amended through 25-38 Plus FAR Part 36 as amended by Amendments 36-1 through 36-28 The certification basis for the Hawker 750 is the same as that for the Hawker 800XP with Pro-Line 21 Avionics, including all Special Conditions, and equivalent safety findings, plus the following additional requirements. For the Hawker 750 airplanes, compliance has been established with the special retroactive requirements of 14 CFR 25.2 through Amendment 25-20. 14 CFR 25.855(a)(b)(c)(d)(e)(2)(3) as amended through Amendment 25-32 which apply to the external baggage unit. Equivalent Level of Safety is established with 14 CFR 25.855 (a-1) as amended through Amendment 25-32 for Cargo Compartment Liners; Reference: AT4637WI-T-A-1. 14 CFR 25.857(d)(1)(2)(3)(5) as amended through Amendment 25-32 – Baggage Compartments 14 CFR 25.571 as amended through Amendment 25-54 for Baggage Compartment The Hawker 750 has met the criteria defined in 14 CFR 21.93(b) for “No Acoustical Change”, and therefore maintains compliance with 14 CFR Part 36 as amended by Amendments 36-1 through 36-20. A3EU Rev. 44 Page 90 of 105 - 90 - Certification Basis: (cont.) For BAe.125 Series 1000A models: The U.S. Certification Basis for BAe.125-800A models (including equivalent safety findings) and, in agreement with the manufacturer, compliance has been established with specific additional requirements of Part 25 of the FAR, as amended by amendments 25-1 through 25-70, for areas of significant design change from the Series 800A. The additional FAR requirements are as follows: 25.25 25.1021 25.33 25.1045(d) 25.361(b) 25.109(e) 25.365(a) and (d) 25.1093(b)(1)(i)(ii) 25.511(b)(6) and (b)(2) (Engine only) 25.571(b)(6) 25.1141(f)(2) 25.697(a) 25.1143(d) 25.735(f)(1) 25.1163(a) 25.843(a) 25.1183(b)(1) 25.853(b) and (c) 25.1189(a)(1) and (2) 25.855(a) 25.1303(c)(1) 25.857(d)(6) 25.1305(c)(6) and (7) 25.901(c) 25.1309(a), (b), (c), (d) and (e) 25.903(a) 25.1323(b)(2) 25.904 25.1331(a)(3) 25.905 25.1359 25.939(a) 25.1411(a) 25.961 25.1423 25.963(e) 25.1438(a)(b) and (c) 25.993(c) 25.1457(c) 25.994 25.1459(a)(4) and (e) 25.997 25.1521(b) and (c) 25.1001 25.1549 (Engine only) 25.1013 25.1015 Appendix F 25.1019 Appendix H NOTE: Compliance with the subject paragraphs of FAR 25.1309 has been established for systems which have been significantly redesigned. Plus FAR Part 36 as amended by Amendments 36-1 through 36-18. Plus Special Federal Aviation Regulation (SFAR) 27 as amended by Amendments 27-1 through 27-6. Plus Special Conditions: Special Conditions No. 25-ANM-34 dated June 29, 1990, High Altitude Operation and Protection from Effects of Lightning and High Intensity Radiated Fields. Plus Equivalent Safety Finding to CAR 4B.635(c), FAA Memo No. TD4610WI-T-SE-2, for Aft Position Light Chromaticity. The BH/DH/HS/BAe.125 Series (1B, 1B-522, 1B/R-522, 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB, 3B/RC, F3B, F3B/RA, 400B, 400B/1, 401B, 403A(C), 403B, F400B, F403B, 600B, 600B/1, 600B/2, 600B/3, F600B, 700B, 800B and 1000B) and some Hawker 800 and 1000 models were certified to CAA, United Kingdom, regulations. As of May 28, 1999, these ‘B’ aircraft are eligible to receive FAA Airworthiness Certificates and Registration as a ‘B’ aircraft if shown to meet the requirements to be equivalent to an ‘A’ aircraft. A3EU Rev. 44 Page 91 of 105 - 91 - Production Basis TC only: Serial numbers 258297, 258301, 258304, 258306 and 259003. Prior to Standard Airworthiness, Aircraft must be inspected and flight tested by FAA. Production Certificate, PC-8: Serial numbers 258309, 258311, 258313, 258315, 258317, 258319, 258320, 258322, 258325, 258326, 258331, 258333, 258334, 258336 and 258338 and on. Hawker 900XP: TC only: Serial numbers HA-0001, HA-0002, HA-0003, HA-0004, HA-0005, HA-0006, HA-0007, HA-0008, HA-0009, HA-0010, HA-0011, HA-0012, HA-0013 and HA-0014. Prior to Standard Airworthiness, Aircraft must be inspected and flight tested by FAA. Production Certificate, PC-8: Serial numbers HA-0015 and on. Hawker 750: TC only: Serial numbers HB-1 and HB-2. Prior to Standard Airworthiness, Aircraft must be inspected and flight tested by FAA. Production Certificate, PC-8: Serial numbers HB-3 and on. Service Information. Service bulletins, structural repair manuals, repair drawings, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is C.A.A. approved, or C.A.A. approved through the Manufacturer's C.A.A. Approval Reference, DAI/1103/38, DAI/1011/55 or DAI/2652/55, prior to August 1, 1995, are accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. Effective August 1, 1995 and after, service information pertaining to the type design is to be FAA approved under FAR Part 21 requirements. NOTES. NOTE 1. (a) A current weight and balance report, including list of equipment in certificated empty weight and loading instructions, must be provided for each aircraft at the time of original certification. (b) The airplane must be loaded so that the C.G. is within the specified limits at all times with the effect of fuel use and movement of crew and passengers from their assigned positions being considered. (c) The "drainable unusable fuel" is the amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as defined in CAR 4b.416. This drainable unusable fuel does not include the "tank trapped fuel". The total unusable fuel must be included in the airplane empty weight or be suitably accounted for in the airplane weight and balance report. The total volume of unusable fuel in gallons is as follows: Airplane Total (BH/DH/HS/.125 Series 1A, 1B, 1A-522, 1B-522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA, F3B/RA, 400A, 400B, 400B/1, F400B, 401B, 403A(C), 403B, and F403B) Volume Weight Arm U.S. Gal Lbs. In. Tank trapped 2.4 16 12 Drainable unusable fuel 9.0 60 16.5 Total unusable fuel 11.4 76 15.6 A3EU Rev. 44 Page 92 of 105 - 92 - NOTE 1. (cont.) Airplane Total (BH/HS.125 Series 600A, 600B, 600B/1, 600B/2, 600B/3, F600B and HS.125 Series 700A and 700B). Volume Weight Arm U.S. Gal Lbs. In. Tank trapped 3.4 11.6 -16.6 Drainable (Wing) 11.5 76.6 -14.0 Unusable (Ventral) 0.9 6.0 59.0 Fuel (Dorsal) Nil Nil - Total unusable fuel 15.8 105.2 -9.7 Airplane Total (BAe.125 Series 800A, 800B, Hawker 800, Hawker 800XP and Hawker 850XP) Volume Weight Arm U.S. Gal Lbs. In. Tank trapped 3.3 22.0 -15.6 Drainable (Wing) 8.1 54.0 -14.0 Unusable (Ventral) 0.7 5.0 74.4 Total unusable fuel 12.1 81.0 -9.0 Airplane Total (Hawker 750) Volume U.S. Gal Weight Lbs. Arm Ft. Trapped 3.3 22.0 -1.30 Drainable 8.1 54.0 -1.17 Total unusable 11.4 76.0 -1.21 Airplane Total (Hawker 900XP) Volume U.S. Gal Weight Lbs. Arm Ft. Trapped 3.3 22.0 -1.30 Drainable 8.8 59.0 -0.54 Total unusable 12.1 81.0 -0.75 Airplane Total (BAe.125 Series 1000A and 1000B and Hawker 1000) Volume Weight Arm U.S. Gal Lbs. In. Tank trapped 3.3 22.0 -15.6 Drainable (Wing) 8.1 54.0 -14.0 Unusable forward ventral 4.2 28.0 -57.6 Unusable aft ventral 2.6 17.6 60.0 Total unusable fuel 18.2 121.6 -13.1 A3EU Rev. 44 Page 93 of 105 - 93 - NOTE 1. (cont.) (d) Engine System oil is the total engine oil less than the quantity drainable from the tank. The undrainable oil for the following aircraft fitted with Viper engines is: (BH/DH/HS/.125 Series 1A, 1B, 1A-522, 1B-522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA, 400A, 400B, 400B/1, 401B, 403A(C), 403B, 600A, 600B, 600B/1, 600B/2 and 600B/3 fitted with Viper Engines). Location Volume U.S. Gal. Weight Lb. Arm In. Moment In. Lb. No. 1 0.3 2.3 82.5 190.4 No. 2 0.3 2.3 82.5 190.4 Total 0.6 4.6 82.5 380.8 The undrainable oil for the following aircraft fitted with Garrett TFE 731 engines is: (BH/DH/HS/BAe.125 Series 1A, 1B, 3A, 3B, F3B/RA, 400A, 400B, F400B, F400B, 401B, 403A(C), 403B, F403B, 600A, 600B, 600B/1, 600B/2, 600B/3, F600B, 700A, 700B, 800A, 800B, Hawker 800, Hawker 800XP, Hawker 850XP, and Hawker 750 fitted with Garrett TFE 731 engines). Location Volume U.S. Gal. Weight Lb. Arm In. Moment In. Lb. No. 1 1.5 11.3 106.2 1200 No. 2 1.5 11.3 106.2 1200 Total 3.0 22.6 106.2 2400 (BAe.125 Series 1000A and 1000B and Hawker 1000A and 1000B fitted with Pratt & Whitney PW305B engines.) The total quantity of oil for both engines is 6.02 U.S. gallons. The weight of this is included in the Basic Aircraft Weight. For the Hawker 900XP airplanes fitted with Honeywell Aerospace TFE731-50R engines: The total quantity of oil for both engines is 6.02 gallons. The weight of this is included in the Basic Aircraft Weight. NOTE 2. Any ’A’ and ‘B’(operating as ‘A’ equivalent) aircraft must be operated according to the appropriate FAA Approved Flight Manual: Document No. Model Applicability HS.1.2 DH.125 Series 1A and HS.125 Series 1B HS.1.3 DH.125 Series 1A-522, 1A/R-522, 1A/S-522, 3A, 3A/R and 3A/RA HS.1.3 HS.125 Series 1B-522, 1B/R-522. 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB and 3B/RC HS.1.5 DH/BH.125 Series 400A and HS.125 Series 400B, 401B, 403A(C) and 403B HS.1.7 BH.125 Series 600A and HS.125 Series 600A, 600B, 600B/1, 600B/2 and 600B/3 HS.1.9 BH/HS.125 Series 600A with Modification 252468, HS.125 Series F600B, 700A and 700B HS.1.10 DH.125 Series 3A/RA with Modification 252600, DH/BH.125 Series 400A with Modification 252550, HS.125 Series F3B/RA, F400B and F403B HS.1.11 DH.125 Series 1A with Modifications 251867 and 252605, DH.125 Series 1A with Modification 252606, and DH.125 Series 3A with Modification 252603 and HS.125 Series F3B H.S.1.16 BAe.125 Series 800A and 800B and Hawker 800 HS.1.19 BAe.125 Series 1000A and 1000B and Hawker 1000 HS.1.22 Hawker 800XP A3EU Rev. 44 Page 94 of 105 - 94 - NOTE 2. (cont.) As of August 1, 1995, the FAA accepted responsibility for the maintenance and approval of all Airplane Flight Manuals incorporated by reference within this data sheet and those manuals and amendments thereof previously issued by the United Kingdom Civil Aviation Authority in association with DH/HS/BH/BAe.125 Series 1 through 1000 and Hawker 800, 800XP and 1000 Series products designed and/or manufactured under its authority. All such manuals must incorporate the following amendments which relate to this transfer of responsibility. Particular AFM No. Amendment Model Applicability HS.1.2 P 25 Series 1A/B Models HS.1.3 P 91 Series 1A-522, 1B-522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA, 3B/RB, and 3B/RC Models HS.1.5 P 44 Series 400A, 400B, 400B/1, 401B, 403A(C) and 403BModels HS.1.7 P 37 Series 600A, 600B, 600B/1, 600B/2 and 600B/3 Models HS.1.8 P 47 UK CAA Compliant Series F600B and 700B Models HS.1.9 P 41 US FAA Compliant Series 700A & Garrett converted Series 600A Models HS.1.10 P 17 Garrett converted Series 3A/RA (with Long Range fuel), F3B/RA, 400A, F400B, and F403B Models HS.1.11 P 9 Garrett converted Series 1A and 3A (without Long Range fuel) Models HS.1.15 P 57 UK CAA Compliant Series 800 and Hawker 800 Models HS.1.16 P 70 US FAA Compliant Series 800 and Hawker 800 Models HS.1.18 P 40 UK CAA Compliant Series 1000 and Hawker 1000 Models HS.1.19 P 40 US FAA Compliant Series 1000 and Hawker 1000 Models HS.1.22 * US FAA Compliant Hawker 800XP Models 140-590032-0005 * US FAA Compliant Hawker 800XP Models [see note 67] 140-590035-0005 * US FAA Compliant Hawker 850XP Models 140-590037-0005 * US FAA Compliant Hawker 900XP Models * Original Manual issued in the U.S. 140-590039-0005 * US FAA Compliant Hawker 750 Models * Original Manual issued in the U.S. NOTE 3. Service Life Limits and Airworthiness Structural Inspections: Service Life Limits of Structural Components. The service life for aircraft structural parts which are fatigue critical are listed in Hawker Beechcraft Corporation Airworthiness Limitations Document Reference CJE- HPA-C-GEN-AW1667, latest FAA approved revision. Airworthiness Structural Inspections. For the BAe.125 Series 800/Hawker 800/Hawker 800XP/Hawker 850XP/Hawker 750/Hawker 900XP the structural inspections specified in Part 3 Structural Inspections of the BAe.125 Series 800/Hawker 800/Hawker 800XP/Hawker 850XP/Hawker 750/Hawker 900XP Aircraft Flexible Maintenance Schedule, part number AFMS-800 or AFMS-800XP, are essential to ensure the continued airworthiness of the BAe.125 Series 800/Hawker 800/Hawker 800XP/Hawker 850XP/Hawker 750/Hawker 900XP in operational service. The inspections may be changed only with the mutual agreement between the airworthiness authorities and the aircraft manufacturer. NOTE 4. Kerosene type and wide-cut type fuels conforming to the specifications in the data sheet may be used separately or mixed in any proportions. When the fuel type has been changed, a check must be made at the subsequent take-off to confirm that either the appropriate maximum r.p.m. or maximum ITT is being achieved. Aviation gasoline meeting the following specifications may be used within the limits specified in the appropriate Approved Flight Manual or Supplement: American: Mil-G-5572, JP4 and JP5 Grades; MIL-T-83133 JP8 Grade, ASTM D1655/JET A, JET A-1 and JET B Grades. British Defense Standards: 91-87, 91-90 and 91-91. Canadian: 3-GP-23h; 3-GP-25; CAN/CGSB 3.23/Jet A and Jet A-1; CAN/CGSB 3.22/Jet B Russian: GOST 10227-86/ T-1, T-2, TS-1 premium and RT Grades. Chinese: GB 6537-94/ No. 3 A3EU Rev. 44 Page 95 of 105 - 95 - NOTE 5. Airworthiness Certification for aircraft manufactured in the United Kingdom prior to August 1, 1995, and delivered new to the United States. An acceptable minimum standard of equipment was installed on production DH.125 Series aircraft for factory flyaway (ferrying) on a United Kingdom Certificate of Airworthiness for Export. This standard was in accordance with Parts 2 and 6 (and related Appendices and Addendum) of Airworthiness document DO/AW/125/FAA/TC.1 current issue (DH.125 Series 1A, 1A-522, 3A, 1A/R-522, 3A/R, 1A/S-522, 3A/RA, 400A) or DO/AW/125-600/FAA/TC.1 current issue (BH.125 Series 600A, HS.125 Series 600A) or DO/AW/125-700/FAA/TC.1 current issue (HS.125 Series 700A) or DO/AW/125-800/FAA/TC.1 current issue (BAe.125 Series 800A/Hawker 800) or CJE.HPA.C.258.AW2017 current issue (Hawker 800XP) or Parts 2 and 5 (and related Appendices and Addendum) of Airworthiness document CJE-HPA-C-260-AW1660 current issue (BAe.125 Series 1000A and Hawker 1000). A Standard U.S. Certificate of Airworthiness was issued on proof of satisfactory conformance with Modifications listed in Part 5 (and related Appendices and Addendum) of the above referenced documents except Part 4 of document CJE-HPA-C-260-AW1660 (BAe.125 Series 1000A and Hawker 1000), current issue. Current issues of Documents DO/AW/125/FAA/TC.1, DO/AW/125-600/FAA/TC.1, DO/AW/125-700/FAA/TC.1, DO/AW/125-800/FAA/TC.1, CJE-HPA-C-258-AW2017 and CJE-HPA-C- 260-AW1660 may be obtained upon request to the manufacturer. Each individual aircraft at delivery was further identified as to status of incorporation of factory-installed modifications by the "Modification Statement" appended to the aircraft logbook. NOTE 6. Airworthiness Certification for aircraft manufactured in the United Kingdom after August 1, 1995 FAA Standard Airworthiness Certificates and Export Certificates of Airworthiness may be issued to aircraft manufactured in the UK by Raytheon Corporate Jets, Inc. under license from Raytheon Aircraft Company after August 1, 1995, based on the following: a. Exemption Number 6142 granted to Raytheon Aircraft Company on August 3, 1995, from FAR 21.183(c) and FAR 21.325(b)(1) for Hawker 800, 800XP and 1000 aircraft. b. A certifying statement from the UK CAA stating the aircraft has been examined, tested and found to conform to US Type Certificate A3EU and is in a condition for safe operation. c. The aircraft must be fitted with data plates conforming to FAR 45.13 and stating that Raytheon Corporate Jets, Inc. is the builder under license from Raytheon Aircraft Company. d. The following serial numbered aircraft were manufactured in the UK by Raytheon Corporate Jets, Inc. under license to Raytheon Aircraft Company. Hawker 800 (U-125A) 258268, 258288 and 258305 Hawker 800XP 258266, 258277 through 258287, 258289 through 258296, 258298 through 258300, 258302, 258303, 258307, 258308, 258310, 258312, 258314, 258316, 258318, 258321, 258323, 258324, 258327 through 258330, 258332, 258335, 258337. Hawker 1000 259048 through 259052. NOTE 7. Maximum permissible turbine outlet gas temperatures with Modification 251760 embodied are: Takeoff (5 minutes maximum) 740oC Maximum continuous 715oC Maximum for acceleration 715oC Starting maximum gas temp. 800oC A3EU Rev. 44 Page 96 of 105 - 96 - NOTE 8. Maximum Cabin Loads Forward of Aft of Total Front Spar Front Spar Frame Datum Frame Datum DH/HS/BH.125 Series -1A, 1A with 1950 lbs. 900 lbs. 1350 lbs. modification 252605, 1A with modifications 251867 and 252606, 1B, 1A-522, 1B-522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3A with modification 252603, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA, 400A, 400B, and 400B/1 HS.125 Series 401B 2250 lbs. 1020 lbs. 1350 lbs. Maximum Cabin Loads (continued) Forward of Aft of Total Front Spar Front Spar Frame Datum Frame Datum HS.125 Series 403A(C) and 403B 2300 lbs. 1150 lbs. 1350 lbs. DH.125 Series 3A/RA with modification 252600 DH/BH 125 Series 400A, HS.125 Series F3B/RA, F400B and F403B BH/HS.125-600A and HS.125 Series 600B 2960 lbs. 1515 lbs. 1670 lbs. BH/HS 125 Series 600A and 600B 3050 Lbs. 1550 Lbs. 1680 Lbs. (with modification 252320), BH/HS 125-600A with modification 252468), HS.125 Series F600B, HS.125 Series 700A, and 700B, BAe.125 Series 800A and 800B, Hawker 800 and Hawker 800XP Hawker 850XP, Hawker 750, and Hawker 900XP. BAe.125 Series 1000A, 1000B and Hawker 1000 3070 lbs. 1660 lbs. 1910 lbs. Maximum load forward or aft of front spar frame datum includes loads of passenger seats, their occupants (including supernumerary) and of the appropriate luggage compartments. To ensure that airplane C.G. is within allowable limits it may be necessary to reduce loads to less than maximum stated above. NOTE 9. The maximum permissible altitude is 40,000 feet except that the maximum permissible altitude can be 41,000 feet when equipment installations are incorporated conforming with either: a. U.S. Federal Aviation Administration Supplemental Type Certificates SA858WE, SA859WE, and SA860WE and suitably modified to maintain a cabin pressure equivalent to an altitude of 8,000 ft. or; b. Modifications No. 251600 plus 251601, or 251721, or 252210 plus 252260 and 252261A. NOTE 10. Conversion of DH/HS.125 Series 1A-522, 1B-522, 3A or 3B respectively to 1A/R-522, 1B/R-522, 3A/R or 3B/R, may only be accomplished by incorporation of Approved Service Bulletins corresponding to Modifications No. 251700, 255640 and 255718. NOTE 11. Conversion of DH.125 Series 1A-522 or HS.125 Series 1B-522 respectively to Series 1A/S-522 or Series 1B/S-522 may only be accomplished by incorporation of Approved Service Bulletin corresponding to Modification No. 251867. Conversion of DH.125 Series 3A/R or HS.125 Series 3B/R respectively to Series 3A/RA or Series 3B/RA may only be accomplished by incorporation of Approved Service Bulletin corresponding to Modification No. 251916. NOTE 12. The Maximum Ramp Weight and Maximum Zero Fuel Weight for the Model DH/HS 125 Series 1A, Series 1B, Series 1A/522, Series 1B/522, Series 1A/S-522, Series 1B/S-522, Series 3A and Series 3B may be increased 200 pounds provided the revised limitation placard is installed in accordance with Modification No. 252022 and the relevant Approved Flight Manual revision is used. A3EU Rev. 44 Page 97 of 105 - 97 - NOTE 13. When engine anti-icing is in use the maximum permissible oil inlet temperature for continuous operation is 135oC. This value may only be used, when Modification 252149, introducing a modified oil temperature gauge and engine limitation placard, is embodied or an approved equivalent standard is achieved. NOTE 14. The Model DH.125 Series 1A and HS.125 Series 1B can be converted retrospectively to a Series 1A-522 and Series 1B-522 by the introduction of Modifications 251301, 251665, 251392, 251591, 251642, 251658, 251659, 257104, 255567 and 251760 in accordance with Service Bulletin 71-9-1301. The Approved Flight Manual, Document No. HS.1.2 (DH.125 Series 1A or HS.125 Series 1B) must be returned to RAC and the Approved Flight Manual, Document HS.1.3 (DH.125 Series 1A-522 or HS.125 Series 1B) must be obtained. NOTE 15. The limiting Mach Number is reduced to 0.755 when a Smiths combined ASI/Mach meter Part No. PW 202AMA/4, PW 202AMA/6 or PW 202AMA/8 is fitted. These instruments incorporate a mach scale corrected for position error. NOTE 16. The maximum ramp weight and maximum Zero Fuel Weight for the model DH/HS/BH 125 Series 400A and Series 400B may be increased 300 lbs., or 500 lbs. provided VMO is appropriately reduced. Modification 252243 Part C and the related Approved Flight Manual HS.1.5 and Particular Amendment No. P 14 must be embodied to permit the 300 lb. increase for a maximum zero fuel weight and a maximum ramp weight of 14,500 lbs. and 23,600 lbs. respectively. Modification 256403 Part D and the related Approved Flight Manual HS.1.5 and Particular Amendment No. P 17 must be embodied to permit the 500 lb. increase for a maximum zero fuel weight and a maximum ramp weight of 14,700 lbs. and 23,800 lbs. Respectively. NOTE 17. The maximum operating speeds (VMO/MMO) for the BH.125 Series 600A, HS.125 Series 600A and HS.125 Series 600B may be increased by embodiment of Modification 252320 Part A. Particular Amendment No. P 8 must be incorporated in the Approved Flight Manual Document No. HS.1.7 to permit operation at the increased speeds. The maximum ramp weight and the maximum fuel weight for the BH.125 Series 600A, HS.125 Series 600A and HS.125 Series 600B may be increased by the embodiment of Modification 252320 Part C. Particular Amendment No. P 9 must be incorporated in the Approved Flight Manual Document No. HS.1.7 to permit operation at the increased weights defined in this sub-paragraph. The maximum brake release weight for the BH.125 Series 600A, HS.125 Series 600A and HS.125 Series 600B may be increased by the embodiment of Modification 252320 Part D. Particular Amendment No. P 10 must be incorporated in the Approved Flight Manual Document No. HS 1.7 to permit operation at the increased weights defined in this sub-paragraph. NOTE 18. In addition to the requirements listed under "Certification Basis", a BH.125 Series 600A, HS.125 Series 600A and HS.125 Series 600B airplane which has accumulated no flight time by December 31, 1974, must comply with FAR.21.183 and FAR.36.1(d)(3) Amendment 36-2 in order to qualify for the issue of a U.S. Standard Airworthiness Certificate. Compliance may be accomplished by incorporation of Modification No. 252405 and 252384. Particular Amendment No. P 18 and Supplement No. 12 must be incorporated in the associated Approved Flight Manual Document No. HS.1.7 when the above modifications are fitted. NOTE 19. The Rolls Royce Viper engines originally fitted to BH/HS 125 Series 600A and the HS.125 Series 600B airplanes may be replaced by Garrett AiResearch TFE 731-3 Turbofan engines by embodiment of modification 252468 or equivalent and the complementary modifications listed therein. In addition to the installation of the TFE 731-3 engines, the above modification also introduces changes to systems consequential to the engine change and a reduction in takeoff (brake release) weights and increase in Maximum zero taxi weight. A BH/HS 125 Series 600A airplane modified as specified above is to be operated in accordance with the Approved Flight Manual, Document No. HS.1.9 with Particular Amendment No. P 7. The HS.125 Series F600B aircraft modified as specified herein and meeting the requirements of Note 54 must also be operated in accordance with the Approved Flight Manual Document HS 1.9 with Particular Amendment No. P 7. A3EU Rev. 44 Page 98 of 105 - 98 - NOTE 20. Modifications 252622 (Parts A and B) and 258169 (HS.125 Series 700A and Series 700B) or relevant part of 258469 (All Series except Series 700) introduce an Automatic Performance Reserve (APR) system. When these modifications are embodied, the designation of the Garrett AiResearch TFE 731-3 engine must be changed to TFE 731-3R. Limitations and procedures associated with the APR system are provided in the Approved Flight Manuals, Document H.S.1.9 Particular Amendment No. P11 (BH/HS 125 Series 600A with modification 252468, HS.125 Series F600B, 700A, and 700B.), Document H.S.1.10 with Particular Amendment No. P 2 (DH 125 Series 3A/RA with modification 252600, HS.125 Series F3B/RA, BH/DH 125 Series 400A with modification 252550 and HS.125 series F400B) and Document H.S.1.11 with Particular Amendment No. P 4 (DH.125 Series 1A with modifications 251867 and 252605, DH.125 Series 1A with modification 252606, DH.125 Series 3A with modification 252603 and HS.125 Series F3B). NOTE 21. The Rolls-Royce Viper engines originally fitted to DH/BH.125 Series 400A airplanes, may be replaced by Garrett AiResearch TFE 731-3 turbofan engines by embodiment of Modification 252550 and the complementary modifications listed therein. The HS.125 Series 400B airplanes may replace the Garrett AiResearch TFE 731-3 turbofan engines by embodiment of Modification 252551 and the complementary modifications listed therein. In addition to the installation of the TFE 731-3 engines, the above modifications also introduce changes to systems consequential to the engine change and an increase in certificated taxi and take-off (brake release) weights. The DH/BH.125 Series 400A aircraft modified as specified herein must be operated in accordance with the Approved Flight Manual Document HS.1.10. The HS.125 Series F400B or F403B aircraft modified as specified herein and meeting the requirements of Note 53 must also be operated in accordance with the Approved Flight Manual Document HS 1.10. NOTE 22. The Rolls-Royce Viper engines originally fitted to DH.125 Series 1A and HS.125 Series 1B airplanes may be replaced by Garrett AiResearch TFE 731-3 turbofan engines embodiment of Modification 252605 (aircraft fitted with Modification 251867) or 252606 (aircraft not fitted with Modification 251867) and the complementary modifications listed therein. In addition to the installation of the TFE 731-3 engines, the above modifications also introduce changes to systems consequential to the engine change. A DH.125 Series 1A or Series 1B aircraft modified with Modifications 251867 and 252605 as specified herein must be operated in accordance with the Approved Flight Manual Document H.S.1.11 basic. A DH.125 Series 1A or Series 1B aircraft modified with Modification 252606 as specified herein must be operated in accordance with the Approved Flight Manual Document H.S.1.11 and Particular Amendment No. P 2. A DH.125 Series 1B aircraft with either modifications seeking U.S. FAA Airworthiness Certificates and registration must also meet the requirements of Note 52. NOTE 23. Modification 252672 introduces a revised landing flap setting of 45 degrees to Series 400A and earlier Viper powered airplanes. Embodiment of this modification gives a noise reduction which meets the noise requirements of I.C.A.O. Annex 16. The limitations and procedures associated with this modification are provided in the Approved Flight Manual Documents: H.S.1.2 with Particular Amendment No. P 22 (Series 1A and 1B); H.S.1.3 with Particular Amendment No. P 87 (Series 1A-522, 1B-522, 1A/R-522, 1B/R-522, 1A/S-522, 1B/S-522, 3A, 3B, 3A/R, 3B/R, 3A/RA, 3B/RA and 3B/RB); H.S.1.5 with Particular Amendment No. P 37 (Series 400A and 400B) NOTE 24. Modification 256991 introduces an Aeronca Thrust Reverser system to the HS.125 Series 700A and Series 700B aircraft. The limitations and procedures associated with the thrust reverser system are provided in the Approved Flight Manual Document H.S.1.9, by Particular Amendment No. P 12. NOTE 25. The Rolls-Royce Viper engines originally fitted to DH.125 Series 3A/RA and HS.125 Series 3B/RA airplanes may be replaced by Garrett TFE 731-3 turbofan engines by embodiment of Modification 252600 or equivalent and the complementary modifications listed therein. In addition to the installation of the TFE 731-3 engines, the above modifications also introduce changes to systems consequential to the engine change and an increase in certificated taxi and take-off (brake release) weights. A DH.125 Series 3A/RA aircraft modified as specified herein must be operated in accordance with the Approved Flight Manual Document. H.S.1.10. A HS.125 Series F3B/RA aircraft modified as specified herein and meeting the requirements of Note 52 must also be operated in accordance with the Approved Flight Manual Document HS.1.10. NOTE 26. The Rolls-Royce Viper engines originally fitted to DH.125 Series 3A and HS.125 Series 3B aircraft may be replaced by Garrett TFE 731-3 turbofan engines by embodiment of Modification 252603 on the DH.125 Series 3A and Modification 252604 on the HS.125 Series 3B and the complementary modifications listed A3EU Rev. 44 Page 99 of 105 - 99 - therein. In addition to the installation of the TFE 731-3 engines, the modifications also introduce changes to systems consequential to the engine change. A DH.125 Series 3A aircraft modified as specified herein, must be operated in accordance with the Approved Flight Manual Document HS 1.11 with Particular Amendment No. P 3. A HS.125 Series F3B aircraft modified as specified herein and meeting the requirements of Note 52 must also be operated in accordance with the Approved Flight Manual Document HS 1.11 with Particular Amendment No. P 3. NOTE 27. The maximum ramp weight may be increased by 500 lbs. to 25,500 lbs. and the take-off weight by 700 lbs. to 25,500 lbs. for the BH/HS.125 Series 600A with modification 252468, HS.125 Series F600B, HS.125 Series 700A and Series 700B aircraft providing that a revised limitations label is installed in accordance with Modification 252818 (Series 600A) or 258332, (Series 700) and the Approved Flight Manual document HS.1.9 containing Particular Amendment No. P 13. NOTE 28. Aviation Wide-cut fuel may only be used with TFE 731 engined aircraft when both engines have Modification 252738 embodied. NOTE 29. The maximum zero fuel weight may be increased with reductions in VMO on a HS.125 Series 700A and Series 700B aircraft with modifications 252648 and 258332 by embodiment of modification 258825 Part D and by inclusion in the Approved Flight Manual Document H.S.1.9 of Particular Amendment No. P 26. NOTE 30. Modification 259550A introduces the BAe.125 Series 800A (C-29A C-FIN aircraft) intended for operation by the United States Air Force. Document HAW.D.258.AW0159 Issue 4 outlines the changes made to the standard BAe.125 Series 800A aircraft to achieve the delivery standard exported from the manufacturer. These aircraft embody features which would not normally be found on civil aircraft, including various provisions to enable the aircraft to be completed to the USAF requirements in the U.S. (Where provisions have been made for the fitment of equipment by the U.S. customer, these have been shown to comply with the associated installation requirements and be of no hazard to the aircraft, but have not been investigated for their intended function.) A BAe.125 Series 800A aircraft modified as specified above must be operated in accordance with the Approved Manual Document No. HS 1.16 containing Particular Amendment No. P 40 and any other applicable approved amendments. NOTE 31. The maximum taxiing (ramp) weight and the maximum take-off (brake release) weight for the BAe.125 Series 800A, 800B and Hawker 800 aircraft may be increased to 28,100 lbs. (12,746 kg) and 28,000 lbs. (12,701 kg) respectively, by the embodiment of either Modification 259550 Part B or 259952 Part A. An aircraft modified as specified above must be operated in accordance with the Approved Flight Manual Document No. HS.1.16 containing Particular Amendment No. P 45. NOTE 32. The maximum zero fuel weight for the BAe.125 Series 800A, 800B and Hawker 800 aircraft may be increased to 18,000 lbs. when Modification 253169A is embodied. NOTE 33. When a baggage pannier (Mod. 259292 or 259500) is embodied in lieu of the ventral tank, VMO is: 335 knots up to 12,000 feet, less 1 knot per 680 feet, to 310 knots at 29,000 feet. NOTE 34. The maximum zero fuel weight may be increased to 16,300 Lbs. for HS.125 Series 700A and Series 700B with Modification 258825 embodied. NOTE 35. The Maximum Zero Fuel Weight may be increased to 15,200 lbs. but with a reduction in VMO on a DH/BH.125 Series 400A or HS.125 Series 400B with Modification 259273 embodied. NOTE 36. Modification 259283 introduces Dee Howard TR5000BR Thrust Reversers to the BAe.125 Series 800A, 800B and Hawker 800. The limitations and procedures associated with the thrust reverser are provided in the Approved Flight Manual Document HS.1.16 containing Particular Amendment No. P 32. NOTE 37. The maximum zero fuel weight for the BAe.125 Series 800A, 800B and Hawker 800 aircraft may be increased to 17,750 lbs. when Modification 259579A is embodied. NOTE 38. The maximum zero fuel weight on the BAe.125 Series 1000A, 1000B and the Hawker 1000 may be increased to 20,300 lbs. provided that a revised limitations label is installed in accordance with Modification 253379A and the Approved Flight Manual contains General Amendment No. G1. The Approved Flight Manuals are document HS.1.19 for FAA certified aircraft and document HS.1.18 for UK CAA certified aircraft. A3EU Rev. 44 Page 100 of 105 - 100 - NOTE 39. Modification 253410A introduces aerodynamic improvements to the tailplane/elevator configuration. BAe.125 Series 1000 and Hawker 1000 aircraft modified as specified above are to be operated in accordance with the Approved Flight Manual Document No. HS.1.19 containing General Amendment No. G6. NOTE 40. Modification 259976 Part A introduces the BAe.125 Series 800A (U-125) aircraft intended for Airborne Flight Inspection Operations. These aircraft embody features which would not normally be found on Civil Transport Aircraft including various provisions to enable the aircraft to be modified under STC action in the U.S. Where these provisions have been made for installations of equipment under STC action, these have been shown to comply with the associated installation requirements and be of no hazard to the aircraft, but have not been investigated for their intended function with installation of any STC. A BAe.125 Series 800A aircraft modified as specified above must be operated in accordance with the Approved Flight Manual Document No. HS 1.16 containing Particular Amendment No. P 60. NOTE 41. Modification 253686A introduces the Hawker 1000 designation and makes the requisite changes to identification plates and the limitations placard. This change is reflected in the Approved Flight Manual Document No. HS.1.19 containing Particular Amendment No. P 34. The Hawker 1000 is only a name change from the former BAe.125 Series 1000A. All Service Information published for the BAe.125 Series 1000A is equally applicable to the Hawker 1000. NOTE 42 . Modification 253558A introduces the Hawker 800 designation and makes the requisite changes to identification plates and the limitations placard. This change is reflected in the Approved Flight Manual Document. No. HS 1.16 containing Particular Amendment P 63. The Hawker 800 is only a name change from the former BAe.125 Series 800A. All Service Information published for the BAe.125 Series 800A is equally applicable to the Hawker 800. NOTE 43. Modification 253650A introduces the PW305B engine. Embodiment of this modification changes the VMC (Minimum Control Speed) limits. A BAe.125 Series 1000A, 1000B or Hawker 1000 aircraft modified as specified above is to be operated in accordance with the Approved Flight Manual Document No. HS.1.19 containing Particular Amendment No. P 17. NOTE 44. The maximum zero fuel weight on the BAe.125 Series 1000A, 1000B and the Hawker 1000 may be increased to 20,400 lbs. provided that a revised label is installed in accordance with Modification 25A714A and the Approved Flight Manual HS.1.19 containing Particular Amendment No. P 33. NOTE 45. An optional Modification Number 253608A deletes the external baggage door on the BAe.125 Series 1000A, 1000B and Hawker 1000 aircraft. NOTE 46. The maximum Zero Fuel Weight for the Models DH.125 Series 3A/RA and the HS.125 Series 3B/RA may be increased to 14,700 lbs. provided that Modification 25A767A is embodied and the Approved Flight Manual HS.1.3. contains Particular Amendment No. P 89. VMO is also reduced. NOTE 47. Modification 253564A with associated changes introduces the model Hawker 800XP. The Garrett AiResearch TFE 731-5R Turbofan engines originally fitted to the Hawker 800 airplanes are replaced by Allied Signal Engines TFE 731-5BR. In addition to the installation of the TFE 731 -5BR engines, the above modification also introduces the following changes: i) Dee Howard TR5000BR thrust reversers fitted as standard. ii) Increase in certificated ramp, take-off and maximum zero fuel weights. iii) Vortilons replace wing fences and Hawker 1000 aileron servo tab gearing is introduced. iv) Rudder Bias moment arm is reduced to 2.72". A3EU Rev. 44 Page 101 of 105 - 101 - NOTE 47. (cont) v) Mach Trim System is fitted. vi) 3 Wheel ECS is fitted as standard. vii) 38 liter TKS tank is fitted. viii) A Hawker 800XP airplane is to be operated in accordance with the Approved Flight Manual, Document No. HS.1.22. with appropriate Particular Amendments. NOTE 48 UK CAA has made an assessment that all mandatory actions are contained in the instructions for Continued Airworthiness as well as embodied during the production of the Hawker model airplanes. This is documented in UK CAA letter reference 9/33/3956/A 24890 dated July 26, 1995. NOTE 49. Modification 25B047A introduces the Hawker 800 intended for operation by the Japan Air Self Defense Force as a U-125A aircraft. Document CJE.CPD.D.272.001381 Issue 1, outlines the changes made to a standard Hawker 800 aircraft to achieve the delivery standard exported from the manufacturer. This modification was approved by the UK CAA on December 7, 1994 and is accepted by FAA as having demonstrated compliance with the particular requirement of the customer. Where provisions have been made for the fitment of equipment by the Japanese customer, these have been shown to comply with the associated installation requirements and be of no hazard to the aircraft, but have not been investigated for their intended function. A Hawker 800 aircraft modified as specified above must be operated in accordance with the Approved Flight Manual Document. No. HS.1.16 containing Particular Amendment No. P 64 and any other applicable approved amendments. NOTE 50. Some aircraft delivered new from the UK to international customers may not necessarily comply in full with the defined certification basis on which this TC has been granted due to overriding Foreign Authority requirements which have been satisfied for aircraft delivered into their country. There are two basic certification standards for the DH/HS/BH/BAe.125/Hawker series of airplanes. One is the US FAA Type Certificate standard. Aircraft certified to this standard are identified with an “A” in the Model suffix. The other certification standard is based on requirements established by the UK Civil Aviation Authority (CAA). Aircraft certified to the UK CAA standards are identified as “B” versions and include the following Models, Series: 1B, 1B-522, 1B/S-522, 1B/R-522, 3B, 3B/R, 3B/RA, 3B/RB, 3B/RC, F3B, F3B/RA, 400B, 400B/1, 401B, 403A(C), 403B, F400B, F403B, 600B, 600B/1, 600B/2, 600B/3, F600B, 700B, 800B, and 1000B. The ‘B’ models are equivalent to the ‘A’ models and meet U.S. certification requirements with the exception of the overriding UK CAA requirements and customer requested optional modifications approved by the UK CAA. While most countries outside of the UK and U.S. accept either “A”, “B”, or both versions of the aircraft, modifications of these aircraft are sometimes required to satisfy national variations in the certification standards established by the importing countries. Due to the wide range of potential configurations, specific instructions for modifying an airplane from one country standard to another are not available in a pre-published format. In those cases, where it does become necessary to convert an aircraft from one certification standard to another, or to show the equivalency to the U. S. standard, the document used will be a serial number specific Service Bulletin issued by the Type Certificate Holder. This Service Bulletin will be FAA Approved. NOTE 51. Raytheon Aircraft Company Service Bulletin No. 00-11 titled "General-Record of UK Airworthiness Directives (AD) at the Time of Transfer of ICAO Annex 8 Responsibilities from UK CAA to US FAA" will be used to document the AD’s issued by the UK CAA prior to August 1, 1995. NOTE 52. Regulatory requirements applicable to HS.125 Series 1B, 1B-522, 1B/R-522, 1B/S-522, 3B, 3B/R, 3B/RA, 3B/RB, 3B/RC, F3B and F3B/RA United Kingdom certified aircraft (“B” aircraft) to be eligible for U.S. FAA Transport category airworthiness certificates and registration as equivalent to an “A” aircraft are: (i) UK Air Registration Board V. A. Note 1, Issue 1, dated 19 April, 1961, (ii) Modification 251265 or equivalent for stall warning when the throttles are opened while lift dump or air brakes are extended, (iii) Modification 255051 or equivalent for passenger oxygen systems, (iv) Modification 251266 or equivalent for a speed warning device set in accordance with the requirements of FAA S.R. 450A, (v) FAA Exemption Number 573 grants exemption from CAR 4 b.437 Fuel Jettisoning System, and (vi) See Requirements of NOTE 50. A3EU Rev. 44 Page 102 of 105 - 102 - NOTE 53. Regulatory requirements applicable to HS.125 Series 400B, 400B/1, 401B, 403B, 403A(C), F400B and F403B United Kingdom certified aircraft (“B” aircraft) to be eligible for U. S. FAA Transport category airworthiness certificates and registration as equivalent to an “A” aircraft are: (i) UK Air Registration Board V. A. Note 1, Issue 1, dated 19 April, 1961, (ii) Modification 251265 or equivalent for stall warning, (iii) Modification 255051 or equivalent for passenger oxygen systems, (iv) Modification 251266 or equivalent for a speed warning horn set in accordance with the requirements of FAA S.R. 450A, and (v) See requirements of NOTE 50. NOTE 54. Regulatory requirements applicable to HS.125 Series 600B, 600B/1, 600B/2, 600B/3 and F600B United Kingdom certified aircraft (“B” aircraft) to be eligible for U. S. FAA Transport category airworthiness certificates and registration as equivalent to an “A” aircraft are: (i) UK Air Registration Board V. A. Note 1, Issue 1, dated 19 April, 1961, (ii) Modification 251721 or equivalent for stall warning, (iii) Modification 256263A or equivalent for passenger oxygen systems, (iv) Modification 252261A or equivalent for a speed warning horn to meet compliance with FAR 25.1303 (c) (1) , (v) If applicable meet NOTE 18, and (vi) See requirements of NOTE 50. NOTE 55. The models HS.125 Series 600B/1, 600B/2 and 600B/3 were aircraft that had been exported to various countries and modified to operate within that countries Certification Agencies rules. These aircraft were later exported to the United Kingdom and inspected and modified to operate equivalent to a HS.125 Series 600B aircraft. To be eligible for U.S. FAA Transport category airworthiness certificate and registration these aircraft will be considered a model HS.125 Series 600B and shall meet the requirements of NOTE 54. NOTE 56. Regulatory requirements applicable to HS.125 Series 700B United Kingdom certified aircraft (“B” aircraft) to be eligible for U.S. FAA Transport category airworthiness certificates and registration as equivalent to an “A” aircraft are: (i) UK Air Registration Board V. A. Note 1, Issue 1, dated 19 April, 1961, (ii) Modification 252509 or equivalent for stall warning, (iii) Modification 252036A or equivalent for passenger oxygen systems, (iv) Modification 252523 or equivalent for a speed warning horn to meet compliance with FAR 25.1303 (c) (1), (v) Aircraft must be operated using Approved Flight Manual Document HS.1.9 with the appropriate Particular Amendments, and (vi) See requirements of NOTE 50. NOTE 57. Regulatory requirements applicable to BAe.125 Series 800B and some Hawker 800 that were United Kingdom certified aircraft (“B” aircraft) to be eligible for U. S. FAA Transport category airworthiness certificates and registration as equivalent to an “A” aircraft are: (i) UK Air Registration Board V. A. Note 1, Issue 1, dated 19 April, 1961, (ii) Modification 252509 or equivalent for stall warning, (iii) Modification 252036A or equivalent for passenger oxygen systems, (iv) Modification 252523 or equivalent for a speed warning horn to meet compliance with FAR 25.1303 (c) (1), (v) Aircraft must be operated using Approved Flight Manual Document HS.1.16 with the appropriate Particular Amendments, and (vi) See requirements of NOTE 50. NOTE 58. Regulatory requirements applicable to BAe.125 Series 1000B and some Hawker 1000 that were United Kingdom certified aircraft (“B” aircraft) to be eligible for U.S. FAA Transport category airworthiness certificates and registration as equivalent to an “A” aircraft are: (i) UK Air Registration Board V. A. Note 1, Issue 1, dated 19 April, 1961, (ii) Modification 252509 or equivalent for stall warning, (iii) Modification 252036A or equivalent for passenger oxygen systems, (iv) Modification 252523 or equivalent for a speed warning horn to meet compliance with FAR 25.1303 (c)(1), (v) Aircraft must be operated using Approved Flight Manual Document HS.1.19 with the appropriate Particular Amendments, and (vi) See requirements of NOTE 50. NOTE 59. The Hawker 800XP aircraft was designed to meet this Type Certificate standard and receive the U. S. FAA Transport Category Airworthiness Certificates. Some individual aircraft may not necessarily comply in full with the defined certification basis on which this TC has been granted due to overriding Foreign Authority requirements which have been satisfied to deliver in their country. Airplanes requesting a U.S. FAA airworthiness certificate should contact the Type Certificate Holder for information regarding the FAA approval status of modifications installed by the Type Certificate Holder to meet foreign registry requirements. Aircraft with Honeywell SPZ-8000 avionics, or Collins EFIS 86 avionics, must be operated using Approved Flight Manual Document HS.1.22 with the appropriate Particular Amendments and Supplements. Aircraft equipped with Collins Pro line 21 avionics must be operated using Airplane Flight Manual 140-590032-0005. [see note 67]. See requirements of NOTE 50. A3EU Rev. 44 Page 103 of 105 - 103 - NOTE 60. The following serial numbered aircraft were manufactured in the UK by Raytheon Corporate Jets, Inc. Hawker 800 (U-125A) 258245, 258247 and 258250 Hawker 800 258255 through 258265, 258267, 258269 through 258276 Hawker 1000 259043 through 259047. Aircraft manufactured in the UK by Raytheon Corporate Jets, Inc. under license to Raytheon Aircraft Company can be identified in NOTE 6 (d). NOTE 61. Some aircraft were manufactured and delivered to the United States using only a North American (NA) reference number on the aircraft data plate. Service Bulletin SB.00-12 provides a cross reference listing of the North American (NA) reference numbers against serial numbers (25XXX or 25XXXX). NOTE 62. The contents of the ventral fuel tank are reduced by 4.8 gallons for aircraft which have fitted an external toilet servicing facility. NOTE 63. The following serial numbered Hawker 800 (U-125A), Hawker 800XP, Hawker 850XP, and Hawker 1000 aircraft were manufactured by Raytheon Aircraft Company in the USA.: Hawker 800 (U-125A) and Hawker 800XP and Hawker 850XP: 258297, 258301, 258304, 258306, 258309, 258311, 258313, 258315, 258317, 258319, 258320, 258322, 258325, 258326, 258331, 2583 33, 258334, 258336 and 258338 thru 258819, 258821 thru 258835. Hawker 1000: 259003 The following serial numbered Hawker 800 (U-125A), Hawker 800XP, Hawker 850XP, Hawker 750, and Hawker 900XP aircraft were manufactured by Hawker Beechcraft Corporation in the USA.: Hawker 800 (U-125A): 258843 Hawker 800XP: 258840 and 258847 Hawker 850XP: 258836, 258838, 258841, 258844,258845, 258848, 258852, 258855,258856, 258858,258859, 258861, 258872, 258874, 258876, 258891, 258893, 258895, 258900, 258901, 258904, 258907, 258909, 258912, 258915, 258921, 258959, 258961, 258963, 258977, 258980, 258982, 258983, 258984. Hawker 750: HB-1 through HB-35, HB-41, HB-43, HB-62, HB-63, HB-65, and HB-67 through HB-74. Hawker 900XP: HA -1 through HA -108, HA-110, HA-112, HA-113, HA-114, HA-117, HA-120, HA-121, HA-140, HA-143 and HA-146 through HA-213. NOTE 64. The BAe.125 Series 800A, BAe.125 Series 800B, BAe 125 Series 1000A, Bae.125 Series 1000B, Hawker 800, Hawker 1000, Hawker 800XP, Hawker 850XP, Hawker 750, and Hawker 900XP have been approved for Reduced Vertical Separation Minimum (RVSM) flight provided one of the following criteria are met: • For BAe.125 Series 800A, BAe125 Series 800B, Hawker 800 and 800XP aircraft equipped with Honeywell SPZ-8000 avionics, either Mod 25F731A or Raytheon Aircraft Company Service Bulletin 34-3110 must be embodied. • For BAe.125 Series 800A, BAe125 Series 800B, Hawker 800 and 800XP aircraft equipped with Rockwell Collins EFIS-86 avionics (with Collins ADC-86), either Modification 25F731B or Raytheon Aircraft Company Service Bulletin 34-3166 must be embodied. • For BAe.125 Series 800A, BAe.125 Series 800B, and BAe.125 – Series 800A Major Variant C- 29A, equipped with Rockwell Collins EFIS-85 avionics (with Collins ADC-82A), Raytheon Aircraft Company Bulletin 34-3381 must be embodied. (See Section XVI, Serial Number Eligible, for model effectivity) • For Hawker 800XP aircraft equipped with Collins ProLine 21 avionics: Aircraft 258541, 258556, 258567 through 258586, require embodiment of Raytheon Aircraft Company Service Bulletin 34-3517 Aircraft 258587 through 258609, 258611 through 258628, 258630 through 258684, 258686 through 258734, 258736 through 258788, 258795, 258802, 258821, 258825, 258829, 258834, 258840, and 258847 are RVSM-capable by type design as delivered new from Raytheon Aircraft Company. A3EU Rev. 44 Page 104 of 105 - 104 - NOTE 64. (cont.) • For Hawker 850XP aircraft equipped with Collins ProLine 21 avionics: Serial Number 258789 through 258794, 258796, 258798 through 258801, and 258803 through 258820, 258822, 258823, 258826 through 258828, 258830 through 258833, 258835 through 258839, 258841, 258842, 258844 through 258846, 258848 and subsequent; are RVSM-capable by type design as delivered new from Raytheon Aircraft Company; (Serial Number 258750 through 258788, 258795, and 258802, when Service Bulletin 01-3776, To Introduce the Conversion of Model 800XP Aircraft to Model 850XP Aircraft, which installs manufacturer kit 140-1702, are RVSM-capable by their original Hawker 800XP type design, Pro Line 21 avionics suite equipped, as delivered new from Raytheon Aircraft Company.) • For Hawker 750 aircraft equipped with Collins ProLine 21 avionics: Serial Number HB-1 and subsequent; are RVSM-capable by type design as delivered new from Hawker Beechcraft Corporation. • For Hawker 900XP aircraft equipped with Collins ProLine 21 avionics: Serial Number HA-0001 and subsequent; are RVSM-capable by type design as delivered new from Hawker Beechcraft Corporation. • For BAe.125 Series 1000A, BAe.125 Series 1000B and the Hawker 1000 equipped with Honeywell SPZ-8000 avionics, either Modification 25F856A or Raytheon Aircraft Company Service Bulletin 34-3216 must be embodied. (See Section XVII, Serial Number Eligible, for model effectivity) Final approval for RVSM operations must be obtained by the operator from the local FAA Flight Standards District Office (FSDO) or equivalent. NOTE 65. Master Drawing List 800E0165 introduces the FAA approved modifications for the Hawker 800XP aircraft for operation by the Brazilian Air Force for Airborne Flight Inspection Operations. A Hawker 800XP aircraft modified as specified above must be operated in accordance with the Approved Flight Manual Document No. HS 1.22 containing Supplement 9, Issue 2. The following serial numbered aircraft were modified per the above master drawing list 258401, 258421, 258434 and 258447. NOTE 66. Airplane models 125-1000A and Hawker 1000 are the subject of Special Condition related to operation at high altitude. This special condition includes pressurization system requirements, as well as damage tolerance requirements on the pressure vessel. Therefore, any changes to the pressurization system or modifications or repairs to the pressure vessel must be approved in accordance with the requirements defined in the special condition. The damage tolerance requirements in the special condition are specified in terms of cabin altitude time history, which is a function of the cabin leak rate. For models 125-1000A and Hawker 1000 the specified cabin altitude time history requirement can be met with a pressure vessel opening of 3.0 square inches, (assuming an emergency descent). The determination of an equivalent crack length will depend upon the particular location of the crack, the pressure vessel configuration in that location, and the direction of the crack, etc. The approval of modifications and/or repairs must take into account the requirements of the special condition and how they apply to the particular location and configuration being modified or repaired. The resulting inspection program must also consider other applicable structural criteria. NOTE 67. Collins Pro Line 21 Avionics are embodied in the Hawker 800XP effective serial number: Serial Number 258278, 258541, 258556, 258567 through 258609, 258611 through 258628, 258630 through 258684, 258686 through 258734, 258736 through 258788, 258795, and 258802, 258821, 258825, 258829, 258834, 258840, and 258847. A Collins Pro Line 21 Avionics equipped aircraft is required to operate in accordance with the Airplane Flight Manual 140-590032-0005. NOTE 68. Hawker 800XP equipped with Collins Pro Line 21 Serial Number 258750 through 258788, 258795, and 258802, are eligible to be re-designated as a Model Hawker 850XP when modified by Service Bulletin 01- 3776, To Introduce the Conversion of Model 800XP Aircraft to Model 850XP Aircraft, which installs manufacturer kit 140-1702. Original Hawker 800XP data plate (14 CFR 21.182 and 14 CFR 45.11) shall not be removed when incorporating Service Bulletin 01-3776. NOTE 69. Master Data List 900E301900 defines the introduction of the Hawker 900XP airplanes equipped with Collins Pro Line 21 Avionics in conjunction with Honeywell Aerospace TFE731-50R engines. Serial Number HA- A3EU Rev. 44 Page 105 of 105 - 105 - 0001 and subsequent are required to operate in accordance with the Airplane Flight Manual 140-590037- 0005. NOTE 70. Master Data List 750E314272 defines the introduction of the Hawker 750 airplanes equipped with Collins Pro Line 21 Avionics in conjunction with Honeywell Aerospace TFE731-5BR engines. Serial Number HB-1 and subsequent are required to operate in accordance with the FAA Approved Airplane Flight Manual 140- 590039-0005. --END-- ``` ## ADs (200, first 50, in force first) - [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 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 2016-13-13](https://openairdocs.org/ad/2016-13-13): Engine Exhaust · Textron BAe.125 Series 1000A, BAe.125 Series 1000B and Hawker 1000. Effective Aug 12, 2016 - [AD 2014-15-08](https://openairdocs.org/ad/2014-15-08): Fuel · Textron Hawker 800XP, Hawker 850XP and Hawker 900XP. Effective Sep 5, 2014 - [AD 2013-11-16](https://openairdocs.org/ad/2013-11-16): Flight Controls and Wings · Winglets (Aviation Partners STC ST01411SE). 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Effective Sep 10, 2001 - [AD 2001-13-05](https://openairdocs.org/ad/2001-13-05): Turbine Air Discharge Duct and Water Separator Outlet Duct · Textron BAe.125 Series 1000A, BAe.125 Series 1000B, BAe.125 Series 800A and 6 more. Effective Aug 1, 2001 - [AD 2001-12-17](https://openairdocs.org/ad/2001-12-17): Rivets at Fuselage Stations · Textron Hawker 800XP. Effective Jul 25, 2001 - [AD 2000-24-25](https://openairdocs.org/ad/2000-24-25): Nose Landing Gear Drag Stay Roller Clearance Inspection · Textron Hawker 800 (U-125A) and Hawker 800XP. Effective Jan 16, 2001 - [AD 2000-22-22](https://openairdocs.org/ad/2000-22-22): Wire Bundle Exiting Panel · Textron Hawker 800 (U-125A) and Hawker 800XP. Effective Dec 19, 2000 - [AD 2000-22-03](https://openairdocs.org/ad/2000-22-03): Pitot/Static and Stall Vent Drain Valves · Textron BAe.125 Series 1000A, BAe.125 Series 1000B, BAe.125 Series 800A and 43 more. Effective Dec 4, 2000 - [AD 2000-21-11](https://openairdocs.org/ad/2000-21-11): Cockpit Canopy Blister Interface · Textron BH.125 Series 400A, BH.125 Series 600A, DH.125 Series 1A and 33 more. Effective Nov 29, 2000 - [AD 2000-08-07](https://openairdocs.org/ad/2000-08-07): Tooling Holes · Textron BAe.125 Series 800A, BAe.125 Series 800B, Hawker 800 and 1 more. Effective May 31, 2000 - [AD 2000-02-35](https://openairdocs.org/ad/2000-02-35): Oxygen System Plumbing · Textron BAe.125 Series 1000A, BAe.125 Series 1000B, BAe.125 Series 800A and 36 more. Effective Mar 13, 2000 - [AD 2000-01-02](https://openairdocs.org/ad/2000-01-02): Turbine Air Discharge Duct in the Air Conditioning System · Textron BAe.125 Series 1000A, BAe.125 Series 1000B and Hawker 1000. Effective Feb 15, 2000 - [AD 99-25-01](https://openairdocs.org/ad/99-25-01): P1 Pitot Pipes · Textron BAe.125 Series 1000A, BAe.125 Series 1000B and Hawker 1000. Effective Jan 4, 2000 - [AD 99-23-10](https://openairdocs.org/ad/99-23-10): PS Wire Bundle · Textron Hawker 1000. Effective Dec 17, 1999 - [AD 97-05-03 R1](https://openairdocs.org/ad/97-05-03-R1): Global Positioning Systems · BAE Systems Avro 146-RJ100A, BAe 146-200A, Jetstream Model 4101 and 27 more. Effective Apr 20, 1999 - [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 89-18-07 R1](https://openairdocs.org/ad/89-18-07-R1): Elevator Balance Spigot · Textron BAe.125 Series 1000A, BAe.125 Series 1000B, BAe.125 Series 800A and 34 more. Effective Dec 18, 1998 - [AD 98-23-15](https://openairdocs.org/ad/98-23-15): Fuel Feed Hose Assemblies · Textron Hawker 800XP. Effective Dec 18, 1998 - [AD 98-11-13](https://openairdocs.org/ad/98-11-13): Fire Extinguisher Assemblies · Textron Hawker 800 (U-125A) and Hawker 800XP. Effective Jun 8, 1998 - [AD 98-05-16](https://openairdocs.org/ad/98-05-16): Main Entry Door/Frame Pressing · Textron DH.125 Series 1A, DH.125 Series 1A-522, DH.125 Series 1A/R-522 and 4 more. Effective Apr 10, 1998 - [AD 97-26-10](https://openairdocs.org/ad/97-26-10): Aft Core Cowl Nozzles Of Engine Nacelles · Textron Hawker 1000. Effective Jan 23, 1998 - [AD 97-21-05](https://openairdocs.org/ad/97-21-05): High Pressure Oxygen Hose Assemblies · Textron BAe.125 Series 800A, BAe.125 Series 800A (C-29A), BAe.125 Series 800A (U-125) and 8 more. Effective Nov 24, 1997 All 200: https://openairdocs.org/tcds/A3EU/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Raytheon HAWKER 800XP](https://openairdocs.org/model/raytheon-hawker-800xp): 251 aircraft (registry code 7150012) - [Hawker Beechcraft HAWKER 900XP](https://openairdocs.org/model/hawker-beechcraft-hawker-900xp): 129 aircraft (registry code 4220011) - [British Aerospace BAE 125 SERIES 800A](https://openairdocs.org/model/british-aerospace-bae-125-series-800a): 61 aircraft (registry codes 1500285, 1500286) - [Raytheon HAWKER 850XP](https://openairdocs.org/model/raytheon-hawker-850xp): 40 aircraft (registry code 7150016) - [Hawker Beechcraft HAWKER 750](https://openairdocs.org/model/hawker-beechcraft-hawker-750): 28 aircraft (registry code 4220010) - [Raytheon Corporate Jets HAWKER 800XP](https://openairdocs.org/model/raytheon-corporate-jets-hawker-800xp): 23 aircraft (registry code 7450006) - [Hawker Beechcraft HAWKER 850XP](https://openairdocs.org/model/hawker-beechcraft-hawker-850xp): 19 aircraft (registry code 4220007) - [British Aerospace HS 125-700A](https://openairdocs.org/model/british-aerospace-hs-125-700a): 14 aircraft (registry code 1500204) - [British Aerospace BAE 125 SERIES 1000A](https://openairdocs.org/model/british-aerospace-bae-125-series-1000a): 9 aircraft (registry code 1500287) - [Corporate Jets BAE 125-1000A](https://openairdocs.org/model/corporate-jets-bae-125-1000a): 9 aircraft (registry codes 1500104, 1500109) - [Raytheon Corporate Jets HAWKER 800](https://openairdocs.org/model/raytheon-corporate-jets-hawker-800): 9 aircraft (registry code 7450004) - [Corporate Jets BAE 125-800A](https://openairdocs.org/model/corporate-jets-bae-125-800a): 8 aircraft (registry code 1500103) - [Raytheon Corporate Jets BAE 125-800A](https://openairdocs.org/model/raytheon-corporate-jets-bae-125-800a): 8 aircraft (registry code 7450002) - [Raytheon Corporate Jets HAWKER 1000](https://openairdocs.org/model/raytheon-corporate-jets-hawker-1000): 8 aircraft (registry code 7450005) - [Hawker Siddeley HS.125 SERIES 700A](https://openairdocs.org/model/hawker-siddeley-hs-125-series-700a): 7 aircraft (registry code 4230170) - [British Aerospace BAE 125-800A](https://openairdocs.org/model/british-aerospace-bae-125-800a): 5 aircraft (registry code 1500119) - [Raytheon Corporate Jets BAE 125-1000A](https://openairdocs.org/model/raytheon-corporate-jets-bae-125-1000a): 4 aircraft (registry code 7450001) - [Hawker Siddeley BH.125-400A](https://openairdocs.org/model/hawker-siddeley-bh-125-400a): 2 aircraft (registry code 4230138) - [Hawker Siddeley DH.125-3A/RA](https://openairdocs.org/model/hawker-siddeley-dh-125-3a-ra): 2 aircraft (registry code 423013P) - [Raytheon BAE 125-800A](https://openairdocs.org/model/raytheon-bae-125-800a): 2 aircraft (registry code 7150040) - [Hawker Beechcraft BAE 125-800B](https://openairdocs.org/model/hawker-beechcraft-bae-125-800b): 1 aircraft (registry code 422000B) - [Hawker Beechcraft HAWKER 800XP](https://openairdocs.org/model/hawker-beechcraft-hawker-800xp): 1 aircraft (registry code 4220000) - [Raytheon HAWKER 1000](https://openairdocs.org/model/raytheon-hawker-1000): 1 aircraft (registry code 1500290) - [Raytheon HS 125-700A](https://openairdocs.org/model/raytheon-hs-125-700a): 1 aircraft (registry code 7150019) - [Beechcraft-Hawker BH-125-400A](https://openairdocs.org/model/beechcraft-hawker-bh-125-400a): 0 aircraft (registry code 4210112) - [Beechcraft-Hawker BH-125-600A](https://openairdocs.org/model/beechcraft-hawker-bh-125-600a): 0 aircraft (registry code 4210101) - [British Aerospace BAE 125-1000B](https://openairdocs.org/model/british-aerospace-bae-125-1000b): 0 aircraft (registry code 1500289) - [British Aerospace BAE 125-800B](https://openairdocs.org/model/british-aerospace-bae-125-800b): 0 aircraft (registry code 1500120) - [British Aerospace BAE.125 SERIES 800B](https://openairdocs.org/model/british-aerospace-bae-125-series-800b): 0 aircraft (registry code 1500118) - [British Aerospace DH 125-1A/R-522](https://openairdocs.org/model/british-aerospace-dh-125-1a-r-522): 0 aircraft (registry code 1500105) - [British Aerospace DH 125-1A/S-522](https://openairdocs.org/model/british-aerospace-dh-125-1a-s-522): 0 aircraft (registry code 1500106) - [British Aerospace DH-125-3ARA](https://openairdocs.org/model/british-aerospace-dh-125-3ara): 0 aircraft (registry code 1500100) - [British Aerospace DH.125-400A](https://openairdocs.org/model/british-aerospace-dh-125-400a): 0 aircraft (registry code 1500102) - [British Aerospace HS 125 SERIES 600A](https://openairdocs.org/model/british-aerospace-hs-125-series-600a): 0 aircraft (registry code 1500206) - [Dehavilland DH-125-1A](https://openairdocs.org/model/dehavilland-dh-125-1a): 0 aircraft (registry code 2800550) - [Hawker Beechcraft HAWKER 800](https://openairdocs.org/model/hawker-beechcraft-hawker-800): 0 aircraft (registry code 422000A) - [Hawker Siddeley DH.125-1A](https://openairdocs.org/model/hawker-siddeley-dh-125-1a): 0 aircraft (registry code 4230106) - [Hawker Siddeley DH.125-1A/522](https://openairdocs.org/model/hawker-siddeley-dh-125-1a-522): 0 aircraft (registry code 4230110) - [Hawker Siddeley DH.125-3A](https://openairdocs.org/model/hawker-siddeley-dh-125-3a): 0 aircraft (registry code 4230126) - [Hawker Siddeley DH.125-3A/R](https://openairdocs.org/model/hawker-siddeley-dh-125-3a-r): 0 aircraft (registry code 423013M) - [Hawker Siddeley DH.125-400A](https://openairdocs.org/model/hawker-siddeley-dh-125-400a): 0 aircraft (registry code 4230140) - [Hawker Siddeley HS 125 600B](https://openairdocs.org/model/hawker-siddeley-hs-125-600b): 0 aircraft (registry code 4230160) - [Hawker Siddeley HS 125 SERIES F3B/RA](https://openairdocs.org/model/hawker-siddeley-hs-125-series-f3b-ra): 0 aircraft (registry code 4230137) - [Hawker Siddeley HS 125-F400B](https://openairdocs.org/model/hawker-siddeley-hs-125-f400b): 0 aircraft (registry code 4230157) - [Hawker Siddeley HS-125-600A](https://openairdocs.org/model/hawker-siddeley-hs-125-600a): 0 aircraft (registry code 4230158) - [Hawker Siddeley HS-125-F600B](https://openairdocs.org/model/hawker-siddeley-hs-125-f600b): 0 aircraft (registry code 4230159) - [Hawker Siddeley HS.125 SERIES 700B](https://openairdocs.org/model/hawker-siddeley-hs-125-series-700b): 0 aircraft (registry code 4210171) - [Hawker Siddeley HS.125-1B/522](https://openairdocs.org/model/hawker-siddeley-hs-125-1b-522): 0 aircraft (registry code 4230112) - [Hawker Siddeley HS125 SERIES 3B](https://openairdocs.org/model/hawker-siddeley-hs125-series-3b): 0 aircraft (registry code 4230136) - [Hawker Siddeley HS125 SERIES 400A](https://openairdocs.org/model/hawker-siddeley-hs125-series-400a): 0 aircraft (registry code 4230145) All 56: https://openairdocs.org/tcds/A3EU/aircraft.md ## STCs approved under this data sheet (1,032, first 50) - [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC ST12360WI](https://openairdocs.org/stc/ST12360WI): Installation of the Gogo Wi-Fi System, AVANCE L3 or AVANCE L5,. Yingling Aviation, Inc. - [STC ST12294SE](https://openairdocs.org/stc/ST12294SE): Installation of Starlink Aviation System. AeroMech Incorporated - [STC ST00197IB](https://openairdocs.org/stc/ST00197IB): Installation of the Universal Quick Access Recorder (uQAR). Flight Data Technologies Inc. - [STC ST04570CH](https://openairdocs.org/stc/ST04570CH): Installation of the following systems: Universal lnSight Electronic Flight Instrument System (EFIS), Dual Universal UNS 1FW WAAS FMS, Universal Datacom for CPDLC and FANS 1/A, Universal Kapture CVR with RIPS, Mid Continent Instruments MD 302 electronic standby instrument, Dual Garmin GTX 3000 ADS-B Transponders, Honeywell RDR-2100 weather radar, PS Engineering PAC 45 cockpit audio system. Southeast Aerospace, Incorporated - [STC ST12344IB](https://openairdocs.org/stc/ST12344IB): Replacement of the Halon Type 1211 portable fire extinguisher with Halotron BrX portable fire extinguisher with Halotron BrX portable fire extinguisher. Cessna Duesseldorf Citation Service Center GmbH - [STC ST00892LA](https://openairdocs.org/stc/ST00892LA): Installation of Emergency Vision Assurance System (EVAS).. VisionSafe LLC - [STC ST11216DS](https://openairdocs.org/stc/ST11216DS): Installation of automatic dependent surveillance-broadcast (ADS-B) out on Part 25 aircraft. BHE & Associates Ltd. - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST02718LA](https://openairdocs.org/stc/ST02718LA): Modification to replace the existing standby instrument. Acron Aviation Inc. - [STC ST03292CH](https://openairdocs.org/stc/ST03292CH): Activation of an 802.11 a/b/g/n WiFi System. Elliott Aviation Technical Products Development, Inc. - [STC ST02410CH-D](https://openairdocs.org/stc/ST02410CH-D): Installation of Rockwell Collins Pro Line 21 IDS (Integrated Display System) with IFIS-5000 (Integrated Flight Information System) and Engine Instrument Display. BHE & Associates LTD - [STC ST11145SC](https://openairdocs.org/stc/ST11145SC): Installation of Rockwell Collins dual AHC-3000 Attitude Heading Reference System (AHRS). BHE & Associates Ltd. - [STC ST12091DE](https://openairdocs.org/stc/ST12091DE): Installation of Nine Passenger or Less Limitation. International Jet Aviation Service Inc. - [STC ST00749WI-D](https://openairdocs.org/stc/ST00749WI-D): Installation of AlliedSignal Digital Flight Data Recorder System.. KGB Aviation Solutions LLC - [STC ST00029LB](https://openairdocs.org/stc/ST00029LB): Installation of BFGoodrich traffic alert and collision avoidance system(TCAS I).. Acron Aviation Inc. - [STC ST126CH](https://openairdocs.org/stc/ST126CH): Installation of Traffic Alert and Collision Avoidance System I (TCAS I) system.. Acron Aviation Inc. - [STC ST316CH](https://openairdocs.org/stc/ST316CH): Installation of a TCAS791/791A Traffic alert and collision avoidance system I (TCAS I).. Acron Aviation 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 ST01117DE](https://openairdocs.org/stc/ST01117DE): Installation of the Gogo ATG C1.. Peregrine - [STC ST01833WI](https://openairdocs.org/stc/ST01833WI): Modification of a Rockwell Collins Global Positioning System (GPS) installation. Rockwell Collins Inc. - [STC ST04654CH](https://openairdocs.org/stc/ST04654CH): Installation of Gogo Antennas. StandardAero Business Aviation Services LLC - [STC ST11169SC](https://openairdocs.org/stc/ST11169SC): Installation of a Rockwell Collins Pro Line 21 update to include optional Terrain Awareness and Warning System (TAWS) mode 5 warning during Localizer Performance with Vertical Guidance (LPV) approaches, optional Automatic Dependent Surveillance Broadcast (ADS-B) Out, optional Synthetic Vision System (SVS), optional 3rd VHF datalink to support Controller Pilot Datalink Communication (CPDLC), optional SATCOM, optional handsets, optional FAA Privacy ICAO address (PIA) program. BHE & Associates LTD - [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 ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC - [STC ST04575AT](https://openairdocs.org/stc/ST04575AT): Installation of the Rockwell Collins ALT-1000+/ -4000+ with 5G Filtering. Chippewa Aerospace Inc. - [STC ST02346AT-D](https://openairdocs.org/stc/ST02346AT-D): Installation of Composite Stang Fairings. Summit Aviation Inc. - [STC ST01070DE](https://openairdocs.org/stc/ST01070DE): Installation of the Curtiss-Wright Fortress Flight Data Recorder (with Cockpit Voice Recorder). Peregrine - [STC ST01985WI](https://openairdocs.org/stc/ST01985WI): Installation of the Garmin GI-275 I Electronic Standby Instrument (ESI). Peregrine - [STC ST02004WI](https://openairdocs.org/stc/ST02004WI): Installation of the Garmin GI-275 Instantaneous Vertical Speed Indicators (IVSI). Peregrine - [STC ST11285DS](https://openairdocs.org/stc/ST11285DS): An update to the existing Collins Aerospace Integrated Flight Information System (IFIS) FSU-5010 and upgrade the existing XMWR-1000 to a XMWR-1000S (Sirius XM) in Part 25.. BHE & Associates Ltd. - [STC ST04773NY](https://openairdocs.org/stc/ST04773NY): Interior Refurbishment. Exacaire Inc A Division of IMP Group Ltd. - [STC ST04281AT](https://openairdocs.org/stc/ST04281AT): Installation for the Upgrade of the NZ-2000 FMS computer for software version NZ6.. Chippewa Aerospace Inc - [STC ST01086DE](https://openairdocs.org/stc/ST01086DE): Installation of the True Blue Power TS60 Lithium-ion Nanophosphate batteries as an alternate to existing Grimes Emergency Exit Lighting (EEL) Power Supply. Peregrine - [STC ST04470CH](https://openairdocs.org/stc/ST04470CH): Installation of a Honeywell RDR-7000 Weather Radar System. Honeywell International Inc - [STC ST04704NY](https://openairdocs.org/stc/ST04704NY): Cabin Reconfiguration. Exacaire IMP Group Ltd - [STC SA7634SW](https://openairdocs.org/stc/SA7634SW): Installation of Mark V ground proximity warning system.. Honeywell International Inc - [STC ST04536CH](https://openairdocs.org/stc/ST04536CH): 1. Installation of Aviation Clean Air Ionizer System in accordance with Pentastar Aviation Master Data List, Document No. A-18028-210, Revision E, dated September 23, 2021 or later FAA approved revision. 2. The aircraft must be maintained in accordance with the Instructions for Continuted Airworthiness listed in Pentastar Aviation Master Data List, Document No. A-18028-210, Revision E, dated September 23, 2021 or later FAA approved revision is a required part of this modification.. Pentastar Aviation LLC - [STC ST04210NY](https://openairdocs.org/stc/ST04210NY): Installation of LAI Windshield Panel A. Lee Aerospace Inc. - [STC ST10001SC-D](https://openairdocs.org/stc/ST10001SC-D): Installation of the Honeywell Solid State Flight Data Recorder with interface to Collins Proline 21. Duncan Aviation Inc - [STC ST00818DE](https://openairdocs.org/stc/ST00818DE): Installation of Honeywell Control Display Unit (CDU) model CD-830. Premier Air Center LLC d/b/a West Star Aviation - [STC ST01930LA](https://openairdocs.org/stc/ST01930LA): Installation of Sandel Avionics SN4500 Electronic Horizontal Situation Indicator (EHSI). Sandel Avionics LLC - [STC ST01084WI](https://openairdocs.org/stc/ST01084WI): Installation of Collins TCAS-4000 TCAS II System (with or without optional Avidyne Flight Max 800 MDF).. Blackhawk Aerospace Technologies Inc. - [STC ST01085WI](https://openairdocs.org/stc/ST01085WI): Installation of Honeywell MK VIII Enhanced Ground Proximity Warning System (EGPWS) (with/without optional Avidyne Flight Max 800 MFD).. Blackhawk Aerospace Technologies Inc. - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST10137SC](https://openairdocs.org/stc/ST10137SC): Installation of leather handgrip covers on control yoke.. Textron Aviation Inc - [STC ST04202NY](https://openairdocs.org/stc/ST04202NY): Installation of Lee Aerospace Inc. Window Panel B. Lee Aerospace Inc. - [STC ST04567NY](https://openairdocs.org/stc/ST04567NY): The Rockwell Collins TDR-94D Transponder Upgrade - ADS-B Out. MidCanada Mod Center All 1,032: https://openairdocs.org/tcds/A3EU/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.