TCDS A49EU

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 Rev No. 18 18 18 18 18 18 18 18 18 19 19 18 18 Page No. 14 15 16 17 18 19 20 21 22 23 24 25 Rev No. 18 18 18 18 18 19 19 18 18 18 18 18 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A49EU Revision 19 BAE SYSTEMS (Operations) Limited BAe 146-Series - 100* -200* -300* Avro 146-RJ Series 70* 85* 100* *See Note 19 April 23, 2018 TYPE CERTIFICATE DATA SHEET NO. A49EU This data sheet which is part of Type Certificate No. A49EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder BAE SYSTEMS (Operations) Limited Prestwick International Airport Ayrshire, Scotland KA9 2WR I. Model BAe 146-100A (Transport Category) Approved June 13, 1983 Engines 4 Avco Lycoming Model ALF 502 R-3 Turbine engines or 4 Avco Lycoming Model ALF 502 R-3A Turbine engines (See NOTE 7) or 4 Avco Lycoming Model ALF 502 R-5 Turbine engines (See NOTE 7) Fuel See Airplane Flight Manual for approved fuels and additives. Engine Limits Model ALF 502 R-3 engine (Standard day Sea Level Conditions) Rating Thrust Engine Engine Turbine Gas lbs. N1 N2 Temperature * _____ % (RPM) % (RPM) °C (°F) Takeoff 6700 96.0 (7300) 98.2 (19640) 882 (1620) (5 minutes) Max Continuous 6300 96.0 (7300) 96.9 (19380) 857 (1574) Model ALF 502 R-5 ALF 502 R-3A engines (See NOTE 9) Rating Thrust Engine Engine Turbine Gas lbs. N1 N2 Temperature* _____ % (RPM) % (RPM) °C (°F) Takeoff 6970 96.7 (7350) 98.2 (19640) 882 (1620) (5 minutes) Max. Continuous 6550 96.7 (7350) 96.9 (19380) 857 (1574) *See Airplane Flight Manual for additional N2 speed, start and relight limits. A49EU, Revision 19 2 I. Model BAe 146-100A (Transport Category) Approved June 13, 1983 (continued) Airspeed Limits MMO (Maximum Operating) 0.70 0.73 with BAe kts. (IAS) Mod HCM40241C VMO (Maximum Operating to 8000 ft) 250 (8,000 to 22,950 ft.) 300 VA (Maneuvering): Flaps Retracted 205 Flaps 18° 165 VFE (Flap Speeds): Flaps Deflected Degrees Enroute/Hold 0 VMO T.O./ Approach 18 200 T.O./Approach 24 170 T.O. 30 160 Landing 33 140 prior to embodiment of BAe Modifications HCM00020P and U. 145 post BAe Modifications HCM00020P and U. VLO (Landing Gear Operation) Operation 205 Extended 205 VLE (Landing Gear) Extended 205 VMC (Minimum Control Speed) VMCA 95 VMCG (up to 65,000 lbs takeoff weight) 87 (above 65,000 lbs takeoff weight) 84 C. G. Range (See Note 8) Landing Gear retraction moment - 8,916 lb. in. (Nose down) Maximum Taxi Weight 76500 lb. FORWARD AFT GROSS WEIGHT LBS Takeoff and Landing Enroute Takeoff and Landing Enroute 76000 43.5 SMC (Arm +0.78 ft.) 44.5% SMC (Arm +0.88 ft.) 76000 to 70000 28.1% SMC All Linear variation between 43.5% and 44% SMC Linear variation between 44.5% and 45% SMC 70000 to 66000 (Arm -0.70 ft.) weights 27% SMC 44% SMC 45% SMC 66000 to 47000 28.0% SMC (Arm (Arm +0.83 ft.) (Arm +0.92 ft.) 47000 to 44000 (Arm -0.71 ft.) -0.81 ft.) Linear variation between 44% and 42.0% SMC Linear variation between 45% and 43% A49EU, Revision 19 3 I. Model BAe 146-100A (Transport Category) Approved June 13, 1983 (continued) C.G. Range (cont’d) Maximum taxi weight 82,750 lb. This is achieved by the fitment of one of the following: i) Modification HCM 60015Q. ii) Modifications HCM 30071A and HCM 40225B or E (Steel brakes). iii) Modifications HCM 30071A and HCM 40225G (carbon brakes). iv) Modifications HCM 40046L and HCM 40225D (low pressure tires, wheels and steel brakes). v) Modifications HCM 40046L and HCM 40225F (low pressure tires, wheels and carbon brakes). Maximum Taxi Weight with BAe Modifications HCM 30071A and HCM 40225B or HCM 40255G; HCM 40046L and HCM 40255D FORWARD AFT Gross Weight lbs. Takeoff and Landing Enroute Takeoff and Landing Enroute Gross Weight lbs. 82250 40.4% SMC (Arm +0.48 ft.) 40.4% SMC (Arm +0.48 ft) 82250 28.1% SMC Linear variation between 40.4% and 40.9% SMC Linear variation between 40.4% and 40.9% SMC 82250 to 82000 to (Arm -0.70 ft.) All weights Linear variation between 40.9% and 44% SMC Linear variation between 40.9% and 42% SMC 82000 to 81350 66000 27% SMC Linear variation between 42% and 45% SMC 81350 to 74000 66000 to 28.0% SMC (Arm -0.81 ft.) 44% SMC (Arm +0.83 ft) 45% SMC (Arm +0.92 ft) 74000 to 47000 44000 (Arm -0.71 ft.) Linear variation between 44% and 42.0% SMC Linear variation between 45% and 43% SMC 47000 to 44000 Maximum taxi weight 84,500 lb with BAe Modification HCM 00020U Gross Weight lbs. Takeoff and Landing Enroute Takeoff and Landing Enroute Gross Weight lbs 84000 43.0% SMC (Arm +0.73 ft.) 44.0% SMC (Arm +0.83 ft) 84000 All Weights 28.0% SMC (Arm -0.71 ft.) All Weights 27.0% SMC (Arm -0.81 ft.) Linear variation between 43.0% and 44.0% SMC Linear variation between 44.0% and 45.0% SMC 84000 to 77500 44.0% SMC (Arm +0.83 ft) 45.0% SMC (Arm +0.92 ft.) 77500 to 47000 Linear variation between 44.0% and 42.0% SMC Linear variation between 45.0% and 43.0% SMC 47000 to 44000 Maximum Weights Maximum Taxi Weight 76500 lb (See NOTE 8) lbs kg Taxi 76,500 34,700 Takeoff Weight 76,000 34,473 Landing Weight 72,350 32,817 Zero Fuel Weight 65,000 29,483 A49EU, Revision 19 4 I. Model BAe 146-100A (Transport Category) Approved June 13, 1983 (continued) Maximum Weights (cont’d) Maximum Taxi Weight 82,750 lb lbs kg Taxi 82,750 37,535 Takeoff Weight 82,250 37,308 Landing Weight 72,350 32,817 Zero Fuel Weight 66,000 29,937 Maximum Taxi Weight 84,500 lb Taxi 84,500 38,328 Takeoff Weight 84,000 38,101 Landing Weight 77,500 35,153 Zero Fuel Weight 68,500 31,070 Maximum Baggage Forward Hold 2580 lbs (Arm -12.7 ft.) Rear Hold 2420 lbs (Arm +11.78 ft.) The maximum floor loading in the baggage compartment is 75 lbs./sq. ft. Control Surface Movements The specific procedures for rigging each of the aircraft movable surfaces are defined in the documents listed below. Correct application of these procedures will ensure movement and travel of each surface is as required. HC271H0001 Aileron Rigging HC272H0001 Rudder Rigging HC273H0001 Elevator Rigging HC275H0001 Flap Rigging HC276H0001 Airbrake and Lift Spoiler Rigging Maximum Passengers 94 maximum, in accordance with approved only setting configuration. BAe modification HCM 60014M provides a 76 seat layout that complies with the Type Certificate Standard. See drawing HC250H0154. Engine Oil Capacity Four oil tanks each 3.02 U.S. gallons capacity. Moment arm - 8.5 ft. See Airplane Flight Manual for Approved Oils. C.G. Datum Fuselage station AX 448.13 inches. This is 4 feet forward of the reference point which is indicated by two plates at the rear end of the landing wheel well. Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the EASA Approved Flight Manual (AFM) Document No. BAE 5.1 dated August 15, 2007 or later approved revisions. AFM BAE 5.1 supersedes CAA Approved Flight Manual Document No. BAe 3.3 dated June 13, 1983, or later approved revisions. When fitted with BAe modifications HCM 00209A, HCM 40046A, HCM 40046L, together with HCM 40046Z or HCM 40046B, HCM 40046D and HCM 40046M, and operated in accordance with the Approved Flight Manual, Document No. BAe 5. 1 Appendix No. 29 the aircraft can be operated on unpaved runways up to a maximum takeoff of 76000 lbs. When fitted with BAe modifications HCM 60014G, HCM 60014H, HCM 60014J, HCM 60014Q, and HCM 60014R, the aircraft may be operated in a mixed passenger/ cargo layout. See BAe report number HTD.R.461-00.DC0097, Issue 3. A49EU, Revision 19 5 II. Model BAe 146 200A (Transport Category) Approved June 13, 1983 (Same as 100A except increased gross weight and passenger seating. ) Engines 4 Avco Lycoming Model ALF 502 R-3 Turbine Engines or 4 Avco Lycoming Model ALF 502 R-3A Turbine Engines (See NOTE 7) or 4 Avco Lycoming Model ALF 502 R-5 Turbine Engines (See NOTE 7) Fuel See Airplane Flight Manual for approved fuels and additives. Engine Limits Model ALF 502 R-3 engine (Standard Day) Rating Thrust Engine Engine Turbine Gas lbs. N1 N2* Temperature* % (RPM) %(RPM) °C (°F) Takeoff 6700 96.0 (7300) 98.2 (19640) 882 (1620) (5 minutes) Max. Continuous 6300 96.0 (7300) 96.1 (19380) 857 (1574) Model ALF 502 R-3A and ALF 502 R-5 engines (See NOTE 9) Rating Thrust Engine Engine Turbine Gas lbs. N1 N2* Temperature* % (RPM) % (RPM) °C (°F) Takeoff 6970 96.7 (7350) 98.2 (19640) 882 (1620) (5 minutes) Max. Continuous 6550 96.7 (7350) 96.9 (19380) 857 (1574) *See Airplane Flight Manual for additional N2 speed, start and relight limits Airspeed Limits MMO (Maximum Operating) 0.70 0.73 with BAe Mod HCM40241D kts. (IAS) VMO (Maximum Operating to 8000 ft) 250 (8000 to 23,900 ft) 295 VA (Maneuvering) Flaps Retracted 225 with BAe Mod. HCM00021B 230 with BAe Mod. HCM00021U Flaps 18° 175 VFE (Flap Speeds) Flaps Deflected Degrees Enroute/Hold 0 VMO T.O./Approach 18 205 prior to embodiment of BAe modifications HCM 00021M and U. 210 post BAe modifications HCM 00021M and U. A49EU, Revision 19 6 II. Model BAe 146 200A (Transport Category) Approved June 13, 1983 (continued) T.O./Approach/Climb 24 180 Approach 30 170 Landing 33 145 VLO (Landing Gear Operation) Operation 205 Extended 205 VLE (Landing Gear) Extended 205 VMC (Minimum Control Speed) VMCA 95 VMCG (up to 65,000 lbs takeoff weight) 86 (above 65,000 lbs takeoff weight) 82 C.G. Range Landing gear retraction moment - 8,916 lb in (Nose down) (See NOTE 8) Maximum Taxi Weight 90,000 lbs. FORWARD AFT Gross Weight lbs Takeoff and Landing Enroute Takeoff and Landing Enroute 89500 44.0% SMC (Arm +0.83 ft) 45.0% SMC (Arm +0.92 ft.) 89500 to 85000 28.1% SMC Linear variation between 44% and 46% SMC Linear variation between 45% and 47% SMC 85000 to 71000 (Arm -0.70 ft.) All Weights 46% SMC 47% SMC 71000 to 48500 28.0% SMC 27% SMC (Arm -0.81 ft.) (Arm +1.02 ft.) (Arm +1.12 ft.) 48500 to 46000 (Arm -0.71 ft) Linear variation between 46% and 44% SMC Linear variation between 47% and 45.2% SMC Maximum taxi weight 90,000 lbs. with Bae modifications HCM 00296A & HCM 45018A FORWARD AFT Gross Weight lb Takeoff and Landing Enroute Takeoff and Landing Enroute 89500 28.0% SMC (Arm -0.71 ft) 26.0% SMC (Arm -0.90 ft.) 42.5% SMC (Arm +0.70 ft.) 44.0% SMC (Arm +0.81 ft.) 89500 to 78000 Linear variation Linear variation Linear variation between 42.5% and 47.0% SMC Linear variation between 44.0% and 48.0% SMC 78000 to 76250 between 28.0% and 27.0% SMC between 26.0% and 25.0% SMC 76250 to 72000 47.0% SMC 48.0% SMC 72000 to 48500 27.0% SMC 25.0% SMC (Arm +1.12 ft.) (Arm +1.22 ft.) 48500 to 46000 (Arm -0.80 ft.) (Arm -1.00 ft.) Linear variation between 47.0% and 45.5% SMC Linear variation between 48.0% and 46.5% SMC A49EU, Revision 19 7 II. Model BAe 146 200A (Transport Category) Approved June 13, 1983 (continued) Maximum taxi weight 93,500 lb with BAe Modification HCM00021U FORWARD AFT Gross Weight lbs Takeoff and Landing Enroute Takeoff and Landing Enroute 93000 28.0% SMC (Arm -0.71 ft.) 26.0% SMC (Arm -0.90 ft.) 42.0% SMC (Arm +0.46 ft.) 42.0% SMC (Arm +0.64 ft.) 93000 to 86000 86000 to 84600 84600 to 73500 73500 to 48500 48500 to 46000 Linear variation between 28.0% and 27.0% SMC 27.0% SMC (Arm 0.80 ft.) Linear variation between 26.0% and 25.0% SMC 25.0% SMC (Arm -1.00 ft.) Linear variation between 42.0% and 47.0% SMC 47.0% SMC (Arm -1.12 ft.) _____________ Linear variation between 47.0% and 45.5% SMC Linear variation between 42.0% and 48.0% SMC _____________ 48.0% SMC (Arm +1.22 ft.) _____________ Linear variation between 48.0% and 46.5% SMC Maximum Weights Maximum Taxi Weight 90,000 lbs. (See NOTE 8) lbs. kg. Taxi 90,000 40,824 Takeoff Weight 89,500 40,597 Landing Weight 77,500 35,154 Zero Fuel Weight 71,000 32,206 Maximum Taxi Weight 93,500 lbs. Taxi 93,500 42,410 Takeoff Weight 93,000 42,184 Landing Weight 81,000 36,740 Zero Fuel Weight 75,000 34,019 Maximum Baggage Forward Hold 3350 lbs. (Arm -14.76 ft.) Reverse Hold 3320 lbs. (Arm +13.68 ft.) The maximum floor loading in the baggage compartment is 75 lbs./sq. ft. Control Surface Movements The specific procedures for rigging each of the aircraft moveable surfaces are defined in the documents listed below. Correct application of these procedures will ensure moment and travel of each surface as required. HC271H0001 Aileron Rigging HC272H0001 Rudder Rigging HC273H0002 Elevator Rigging HC274H0001 Flap Rigging HC275H0001 Airbrake and Lift Spoiler Rigging Engine Oil Capacity Four oil tanks each 3.02 U.S. gallons capacity. Moment arm - 8.5 ft. See Airplane Flight Manual for Approved Oils. A49EU, Revision 19 8 II. Model BAe 146 200A (Transport Category) Approved June 13, 1983 (continued) C.G. Datum Fuselage station AX491.81 inches. This is 4 feet forward of the reference point which is indicated by two plates at the rear end of the landing wheel well pressure floor. Maximum Passengers 108 Maximum. Compliance with FAR 25.803 has been shown by demonstration and analysis with an aircraft having an interior configuration in accordance with British Aerospace document no. HAW.R.460.AW.0506 or any approved seating configuration. Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the EASA Approved Flight Manual Document No. BAE 5.1.dated August 15, 2007 or later approved revisions. AFM BAE 5.1 Supersedes CAA approved Flight Manual Document No. BAe 3.6 dated June 13, 1983 or later approved revisions. III. Model BAe 146 300A (Transport Category) Approved October 28, 1988 (Same as 100A except increased gross weight and passenger seating) Engines 4 Avco Lycoming Model ALF R-3A Turbine Engines (See NOTE 7) or 4 Avco Lycoming Model ALF 502 R-5 Turbine Engines (See NOTE 7) Fuel See Airplane Flight Manual for approved fuels and additives. Engine Limits MODEL ALF 502 R-3A and ALF 502 R-5 engines (See NOTE 9) Engine Engine Turbine Gas Thrust N1 N2 Temperature* Rating lbs. % (RPM) % (RPM) °C (°F) Takeoff 6970 96.7 (7350) 98.2 (19640) 882 (1620) (5 minutes) Max. Continuous 6550 96.7 (7350) 96.9 (19380) 857 (1574) * See Airplane Flight Manual for additional N2 speed, start and relight limits. Airspeed Limits MMO (Maximum Operating) 0.73 Kts. (IAS) VMO (Maximum Operating to 8000 ft.) 250 (8000 to 23,900 ft) 295 305 with BAe Mod. HCM36049A VA (Maneuvering) Flaps Retracted 235 Flaps 18° 180 A49EU, Revision 19 9 III. Model BAe 146 300A (Transport Category) Approved October 28, 1988 (continued) VFE (Flap Speeds) Flaps Deflected Degrees Enroute/Hold 0 VMO T.O./ Approach 18 210 T.O./Approach/Climb 24 180 Approach 30 170 Landing 33 150 VLO (Landing Gear Operation) Operation 205 Extended 205 VLE (Landing Gear) Extended 205 VMC (Minimum Control Speed) VMCA 97 VMCG 82 C.G. Range Landing Gear retraction moment - 8,916 lb. in. (Nose down) (See NOTE 8) Maximum Taxi Weight 95,500 lbs. FORWARD AFT Gross Weight lbs Takeoff and Landing Enroute Takeoff and Landing Enroute 95000 24.5% SMC (Arm -1.05 ft) 22.5% SMC (Arm -1.23 ft.) 44.0% SMC (Arm 0.81 ft.) 45.6% SMC (Arm 0.99 ft.) 95000 to 83000 Linear Linear Linear variation between Linear variation between 83000 to 77500 variation between 24.5% and 22.5% SMC variation between 22.5% and 20.5% SMC 44.6% and 48.5% SMC 45.6% and 50.0% SMC 77500 to 58000 Linear variation 20.5% SMC 48.5% SMC (Arm +1.24 ft.) 50.0% SMC (Arm +1.41 ft.) 58000 to 47000 between 22.5% and 23.0% SMC (Arm -1.42 ft.) Linear variation between 48.5% and 44.0% SMC Linear variation between 50.0% and 45.4% SMC Maximum Weights Maximum Taxi Weight 95500 lb lbs kg Taxi 95,500 43,318 Takeoff Weight 95,000 43.091 Landing Weight 83,000 37,648 Zero Fuel Weight 77,500 35,153 Maximum Baggage Forward Hold 4215 lbs (Arm -16.93 ft.) Rear Hold 4033 lbs.(Arm +14.20 ft.) The maximum floor loading in the baggage compartment is 75 lbs/sq. ft. A49EU, Revision 19 10 III. Model BAe 146 300A (Transport Category) Approved October 28, 1988 (continued) Control Surface Movements The specific procedures for rigging each of the aircraft moveable surfaces are defined in the documents listed below. Correct application of these procedures will ensure movement and travel of each surface is as required. HC271H0001 Aileron Rigging HC272H0001 Rudder Rigging HC273H0567 Elevator Rigging HC274H0001 Flap Rigging HC275H0002 Airbrake and Lift Spoiler Rigging Engine Oil Capacity Four oil tanks each 3.02 U.S. gallons capacity. Movement arm -8.5 ft. See Airplane Flight Manual for Approved Oils. C.G. Datum Fuselage station AX 544.81 inches. This is 4 feet forward of the reference point which is indicated by two plates at the rear end of the landing wheel well pressure floor. Maximum Passengers 108 maximum. Compliance with FAR 25.803 has been shown by demonstration and analysis with an aircraft having an interior configuration in accordance with any British Aerospace approved seating configuration. Other Operating Limitations Aircraft shall be operated in compliance with the operating limitations specified in the EASA Approved Flight Manual Document No. BAE 5.1 dated August 15, 2007 or later approved revisions. AFM BAE 5.1 supersedes CAA approved Flight Manual Document No. BAe 3.11 dated June 1988 or later approved revisions. DATA PERTINENT TO ALL MODELS Auxiliary Power Unit 1 AiResearch GTCP 36-100 (M) or 1 AiResearch GTCP 36-150(M) or 1 Sundstrand APS1000 T-62T-46C ** Limits *GTCP 36-100(M) GTCP 36-150(M) APS1000 T-62T-46C Rated shp, maximum for Standard Day, Sea Level conditions 45 shp 50 shp 53.5 shp Shaft Speed: Maximum (at rated power) 100.5% (59034 RPM) 103% (60499 RPM) 108% (69286 RPM) Maximum Exhaust Temperature: Continuous Operation: Starting: (Up to 10 seconds) 732oC 974oC 870oC 746oC 974oC 870oC 718oC -oC 1032oC *See Note 5 **See Airplane Flight Manual for additional limitations and Approved Oils. Minimum Crew 2 - Pilot and Co-Pilot Maximum Operating Altitude 30,000 ft. (See NOTE 12) Usable Fuel Capacity 100A 200A 300A Wing Tanks (Right & Left) 16,240 lbs (Arm +0.008 ft) Center Tank 4,400 lbs (Arm -3.243 ft) Auxiliary Tanks (Right & Left) 2,064 lbs (Arm +4.230 ft) Fuel must be loaded symmetrically into the wing tanks. The maximum allowable wing tank fuel asymmetry is 1,500 lbs. See NOTE 1 for information on unusable and undrainable fuel. Standard Mean Chord (SMC) The Standard Mean Chord is 9.62 ft. The leading edge of the Standard Mean Chord is 3.405 ft. forward of the C.G. datum. A49EU, Revision 19 11 Leveling Means Clinometer on cabin seat rails. Certification Basis for the 100A & 200A FAR 21.29, FAR 25, effective February 1, 1965, including Amendment 25-1 through 25-43. In addition the applicant voluntarily complied with the following later requirements. FAR Section Amdt. FAR Section Amdt. 25.305 (d) 54 25.809 (f) (iii, iv, v) 47 25.345 (d) 46 25.851 (a) (5) 54 25.351 (a) 46 25.853 (c), (d), (e) 51 25.365 (e)(1), (e)(2) 54 25.1103(a), (b)(2), (d), (e), (f) 46 25.571 45 25.1142 46 25.605 (a), (b) 46 25.1207(d) 46 25.629 (d)(1), (d)(4) (v & vi) 46 25.1305 (d) 54 25.697 (b) 46 25.1329 (h) 46 25.701 (a) 46 25.1522 46 25.733 (a), (b), (c) 49 25.1561 (c) 46 25.735 (b), (f)(2), (g) 48 25.773(b)(2)(ii) 72 25.793 51 25.775(e) 72 25.803 (c), (d) 46 Certification Basis (cont'd) Compliance with FAR 25.803 and 25.1419 has been established. Compliance with FAR 25.801 has been established for the structure of the aircraft fitted with BAe modifications HCM 00100A or HCM 00166A, plus HCM 00100B for BAe 146-100A or HCM 00100C for BAe 146-200A. Full compliance will be achieved when survival equipment is installed in accordance with FAR’s 25.1411 through 25.1415 and the appropriate operating equipment. FAR 36, effective December 1, 1969, including Amendments 36-1 through 36-13. SFAR 27, 27-1 through 27-4 (see NOTE 4). For the 300A In addition to the 100A and 200A certification requirements, the following later requirements apply to the 300A certification: FAR 25 Subpart C, Amendments 44 to 54 inclusive. FAR Section Amdt. FAR Section Amdt. 25.629 46 25.811 46 25.783 54 25.812 46 25.787 51 25.853 51 25.789 46 25.858 54 25.803 46 25.863 46 FAR Part 36 effective December 1, 1969, including Amendments 36-1 through 36-15. Special Federal Aviation Regulation No. 27 effective February 1, 1974, including amendments 27-1 through 27-5. For All Bae 146 Equivalent Safety FAR 25.613 (a) - Design Values FAR 25.615 (a) - Design Properties FAR 25.773 (b)(2) - Pilot’s Window(see note 18) FAR 25.1091 (e) - Foreign Object Ingestion Exemption No. 3639 regarding FAR 25.807(c)(1) Type Certificate No. A49EU, issued June 13, 1983. Effective Date of Application for Type Certificate August 4, 1978. The applicable later requirements for the installation of the LF507 -1H engine are defined within FAA issue paper G-1 dated January 26, 1993 detailing: FAR 25.903 (a) Amendment 57 FAR 25.1091 (e) Amendment 57 A49EU, Revision 19 12 FAR 25.1093 (b) (2) Amendment 57 FAR 25.1163 (a) (3) Amendment 57 FAR 25.1305 (d) (1) Amendment 54 Historical Transition The United Kingdom Civil Aviation Authority originally type certificated this aircraft under its type certificate Number BA16. The FAA validated this product under U.S. Type Certificate Number A49EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom. Serial Nos. Eligible The United Kingdom Certificate of Airworthiness for Export endorsed as noted under “Import Requirements” must be submitted for each individual aircraft for which application of certification is made. Import Requirements The FAA can issue a U.S. airworthiness certificate based on an NAA Export Certificate of Airworthiness (Export C of A) signed by a representative of United Kingdom Civil Aviation Authority on behalf of the European Community. The Export C of A should contain the following statement: ‘The aircraft covered by this certificate has been examined, tested, and found to conform with Type Design approved under U.S. Type Certificate No. A49EU and to be in a condition for safe operation.’ Service Information Each of the documents listed below that contain a statement that it is approved by the European Aviation Safety Agency (EASA) - or for approvals made before September 28, 2003 - by the United Kingdom Civil Aviation Authority, are accepted by the FAA and are considered FAA approved. Additionally, approvals issued by BAE Systems (Operations) Limited under the authority of EASA approved Design Organization EASA.21J.047 - or for approvals made before September 28, 2003 under the authority of JAA Design Organization Approval No. CAA.JA.02034 or Manufacturers CAA