TCDS A20EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A20EU Revision 15 FOKKER F28 Mark 1000 F28 Mark 2000 F28 Mark 3000 F28 Mark 4000 F28 Mark 0100 F28 Mark 0070 November 25, 2015 TYPE CERTIFICATE DATA SHEET No. A20EU This data sheet which is a part of Type Certificate No. A20EU 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. FOKKER SERVICES B.V. P.O. Box 1357 2130 EL, Hoofddorp THE NETHERLANDS I. FOKKER Model F28, Mark 1000 (Transport Aircraft), approved 24 March 1969. Engines. 2 Rolls-Royce Two Shaft Bypass Jet Engines: Spey Mk 555-15. When modified in accordance with approved Fokker F28 Service Bulletin No. 71-9: Spey Mk 555-15N. (See NOTE 7 regarding intermixing of engines). Fuel. Eligible engine fuels are listed in Rolls-Royce Operating Instructions, Document No. F-Sp2-F, Appendix 2. Engine Limits. Thrust RPM % TGT Conditions (lbs) HP LP (ºC) Time Limit Max. Takeoff 9850 101.0 108.5 520 5 minutes Max. Continuous 9470 98.5 108.5 490 Unrestricted Starting and Relight - - 540 2 seconds Max. Overspeed 104.5 115.5 - 20 seconds Max. Overtemp. 540 20 seconds Oil. See relevant Rolls-Royce Operating Instructions Manual. Page 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev 15 15 15 15 15 15 15 15 15 15 15 15 7 15 15 15 15 15 15 15 Page 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 Rev 15 15 15 15 15 15 15 15 15 15 15 15 15 15 15 15 15 A20EU, Rev 15 2 I. FOKKER Model F28, Mark 1000 (cont'd) Oil Temperature Limits. Max. 15 min. 120ºC Max. unrestricted 100ºC Bleed Air. For max. bleed air extraction from the engine refer to FAA Engine Type Certificate Data Sheet E2EU. APU Type. Garrett AiResearch GICP 36-4(A). Fuel. Eligible APU fuels are listed in Garrett AiResearch Document, Model Specification GICP-36-4(A) SC-5754. APU Limits. Conditions Max. RPM (%) Max. TGT (ºC) Start - 705 Transient 10 sec. 110 705 Sustained 105 650 Airspeed Limits (IAS). VMO (Maximum Operating) Sea level 331 kts 10,000 ft 336 kts 20,000 ft 343 kts 20,840 ft 344 kts Straight line variation between points. MMO 20,840 ft M = .75 VA (Maneuvering) See approved Airplane Flight Manual. VFE (Flap Extension) Flap Setting 25º 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft 42º 160 knots IAS up to 20,000 ft For airplane serial numbers 11042 and subsequent or when modified in accordance with approved Fokker F28 Service Bulletin 51-5: 42º 165 knots IAS up to 20,000 ft VLO (Landing Gear Operation) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft VLE (Landing Gear Extended) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft Maximum speed when wheel doors are retracted by means of winch - During Retraction 150 knots IAS 25º flap 140 knots IAS 42º flap Retracted 180 knots IAS 25º flap 155 knots IAS 42º flap Maximum Landing, Taxi and Flare-out Lights Extended Speed: VMO/MMO 3 A20EU, Rev 15 I. FOKKER Model F28, Mark 1000 (cont'd) Center of Gravity (C.G.) Landing Gear Extended: Range. FORWARD AFT Gross Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 56,700 452.71 20.01 470.65 33.00 53,000 451.33 19.00 470.65 33.00 and lower When modified in accordance with approved FOKKER F28 Service Bulletin 57-1: Gross FORWARD AFT Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 62,000 454.60 21.37 470.65 33.00 54,500 451.33 19.00 470.65 33.00 and lower When modified in accordance with approved FOKKER F28 Service Bulletin 55-4: Gross FORWARD AFT Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 63,000 453.90 20.87 473.41 35.00 54,200 449.95 18.00 473.41 35.00 and lower When modified in accordance with approved FOKKER F28 Service Bulletin 51-5: Gross FORWARD AFT Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 65,000 451.43 19.07 473.41 35.00 60,800 449.95 18.00 473.41 35.00 and lower Straight line variation between points given. Gear retraction moment is 5833 in-lbs, nose down. Maximum Weight. Takeoff 56,700 lb Landing 54,000 lb Zero fuel 46,650 lb When modified in accordance with approved FOKKER F28 Service Bulletin 57-1: Takeoff 62,000 lb Landing 54,000 lb Zero fuel 47,900 lb A20EU, Rev 15 4 I. FOKKER Model F28, Mark 1000 (cont'd) Maximum Weight (cont'd) When modified in accordance with approved FOKKER F28 Service Bulletin 55-4: Takeoff 63,000 lb Landing 54,000 lb Zero fuel 47,900 lb When modified in accordance with approved FOKKER F28 Service Bulletin 57-9, Revision 1: Takeoff 63,000 lb Landing 54,000 lb Zero fuel 49,900 lb When modified in accordance with approved FOKKER F28 Service Bulletin 51-5: Takeoff 65,000 lb Landing 59,000 lb Zero fuel 54,500 lb When modified in accordance with approved FOKKER F28 Service Bulletin 51-23: Takeoff 65,500 lb Landing 59,000 lb Zero fuel 54,500 lb Minimum Crew. 2 (pilot and copilot). Maximum Passengers. 70 (See NOTE 5). Maximum Baggage Compartment Station (in.) From To Capacity (cu. ft.) Max. Floor Loading Arm (in.) Forward Belly 165.4 369.7 241.0 75 lb/sq ft or 267.6 250 lb/ft Aft Belly 525.4 666.7 136.0 75 lb/sq ft or 594.1 250 lb/ft Rear Cabin 632.5 671.8 80.0 75 lb/sq ft 656.1 450 lb/ft Forward Belly Compartment Aft Belly Compartment Max. structural Comp. 1 1118 Max. structural Comp. 4 810 Capacity (lb) Comp. 2 1394 Capacity (lb) Comp. 5 1230 Comp. 3 1103 TOTAL 3615 TOTAL 2040 Rear Cabin Baggage Compartment Max. Structural Capacity (lb) 1065 Fuel Capacity. Usable fuel (See NOTE 1 for unusable fuel). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Left Wing 1286.5 8491 470.93 Right Wing 1286.5 8491 470.93 Total 2573.0 16982 When modified in accordance with approved FOKKER F28 Service Bulletin 28-12: Center Wing Tank 872.0 5755 429.94 All Tanks Total 3445.0 22737 460.55 Fuel weight based upon fuel density of 6.6. lb/U.S. Gal. 5 A20EU, Rev 15 I. FOKKER Model F28, Mark 1000 (cont'd) Oil Capacity. Usable oil (See NOTE 1 for unusable oil). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Each engine 3.6 27.86 639.8 Total 7.2 55.72 Oil weight based upon oil density of 7.74 lb/U.S. Gal. Maximum Operating Altitude. 25,000 ft. (See NOTE 6). Equipment. The basic required equipment as prescribed in the applicable airworthiness and operating regulations must be installed in the airplane for certification. In addition, the following items of equipment are required: - Stick shaker, pre-stall warning, reference FOKKER Drawing A40265 - Audible stall warning, reference FOKKER Drawing A40265 - Approved Airplane Flight Manual. II. Fokker Model F28, Mark 4000 (Transport Category) approved 27 June 1980. The F28 Mk 4000 is similar to the Mk 1000 except for a wingspan extension of 60 inches, a fuselage stretch of 57 inches in front of and 30 inches aft of the wing, and two overwing emergency exits on both sides. Engines. 2 Rolls-Royce Two Shaft Bypass Jet Engines: Spey Mk 555-15H When modified in accordance with approved FOKKER F28 Service Bulletin No. 71-8: Spey Mk. 555-15P (See NOTE 7 regarding intermixing of engines) Fuel. Eligible engine fuels are listed in Rolls-Royce Operating Instructions, Document No. F-Sp2-F, Appendix 2. Engine Limits. Thrust RPM % TGT Conditions (lbs) HP LP (ºC) Time Limit Max. Takeoff 9900 102.5 109.5 565 5 minutes Max. Continuous 9520 98.5 108.5 520 Unrestricted Starting and Relight - - 570 2 seconds Max. Overspeed 105.5 115.5 - 20 seconds Max. Overtemp. 585 20 seconds Oil. (See relevant Rolls-Royce Operating Instructions Manual). Oil Temperature Limits. Max. 15 min. 120ºC Max. unrestricted 100ºC Bleed Air. For max. bleed air extraction from the engine refer to FAA Engine Type Certificate Data Sheet E2EU. APU Type. Garrett AiResearch GTCP 36-4(A). Fuel. Eligible APU fuels are listed in Garrett AiResearch Document, Model Specification GTCP-36-4(A) SC-5754. A20EU, Rev 15 6 II. Fokker Model F28, Mark 4000 (cont'd) APU Limits. Conditions Max. RPM (%) Max. TGT (ºC) Start - 705 Transient 10 sec. 110 705 Sustained 105 650 Airspeed Limits (IAS). VMO (Maximum Operating) Sea level 331 kts 10,000 ft 336 kts 20,000 ft 343 kts 20,840 ft 344 kts Straight line variation between points. MMO 20,840 ft and above M = .75 VA (Maneuvering) See approved Airplane Flight Manual. VFE (Flap Extension) Flap Setting 25º 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft 42º 165 knots IAS up to 20,000 ft VLO (Landing Gear Operation) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft VLE (Landing Gear Extended) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft Maximum speed when wheel doors are retracted by means of winch - During Retraction 155 knots IAS 25º flap 140 knots IAS 42º flap Retracted 180 knots IAS 25º flap 155 knots IAS 42º flap Maximum Landing, Taxi and Flare-out Lights Extended Speed: VMO/MMO 7 A20EU, Rev 15 II. Fokker Model F28, Mark 4000 (cont'd) Center of Gravity (C.G.) Landing Gear Extended: Range. Gross FORWARD AFT Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 73,000 506.30 15.54 519.13 25.00 71,000 68,000 64,000 62,350 57,500 & 505.16 502.16 501.50 14.70 12.50 12.00 523.46 525.91 525.91 28.20 30.00 30.00 and lower 501.50 12.00 530.00 33.00 When modified in accordance with approved FOKKER F28 Service Bulletin 51-18: Gross FORWARD AFT Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 73,000 503.81 13.71 519.13 25.00 71,000 69,500 68,000 66,870 62,000 502.36 501.50 501.50 12.66 12.00 12.00 523.46 524.69 525.91 530.00 28.20 29.10 30.00 33.00 and lower Straight line variation between points. Gear retraction moment is 5833 in-lb., nose down. Maximum Weight. Takeoff 71,000 lb Landing 64,000 lb Zero fuel 57,500 lb When modified in accordance with approved FOKKER F28 Service Bulletin 51-15: Takeoff 73,000 lb Landing 64,000 lb Zero fuel 57,500 lb When modified in accordance with approved FOKKER F28 Service Bulletin 51-17: Takeoff 73,000 lb Landing 65,800 lb Zero fuel 57,500 lb When modified in accordance with approved FOKKER F28 Service Bulletin 51-18: Takeoff 73,000 lb Landing 69,500 lb Zero fuel 62,000 lb A20EU, Rev 15 8 II. Fokker Model F28, Mark 4000 (cont'd) Minimum Crew. 2 (pilot and copilot). Maximum Passengers. 85 (See NOTE 5). Maximum Baggage Compartment Station (in.) From To Capacity (cu. ft.) Max. Floor Loading Arm (in.) Forward Belly 165.4 426.7 308.0 75 lb/sq ft or 295.9 250 lb/ft Aft Belly 582.4 753.7 171.3 75 lb/sq ft or 665.1 250 lb/ft Rear Cabin 719.5 758.9 80.0 75 lb/sq ft 743.1 450 lb/ft Forward Belly Compartment Aft Belly Compartment Max. structural Comp. 1 1118 Max. structural Comp. 5 1340 Capacity (lb) Comp. 2 1394 Capacity (lb) Comp. 6 1230 Comp. 3 1394 TOTAL 2570 Comp. 4 714 TOTAL 4620 Rear Cabin Baggage Compartment Max. Structural Capacity (lb) 1065 Fuel Capacity. Usable fuel (See NOTE 1 for unusable fuel). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Left Wing 1286.5 8491 527.93 Right Wing 1286.5 8491 527.93 TOTAL 2573.0 16982 Total usable fuel by pressure fueling is 2546.7 U.S. Gal. When modified in accordance with approved FOKKER F28 Service Bulletin 28-12: Center Wing Tank 872.0 5755 486.94 All Tanks Total 3445.0 22737 517.55 Fuel weight based upon fuel density of 6.6. lb/U.S. Gal. Oil Capacity. Usable oil (See NOTE 1 for unusable oil). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Each engine 3.6 27.86 726.8 Total 7.2 55.72 Oil weight based upon oil density of 7.74 lb/U.S. Gal. Maximum Operating Altitude. 25,000 ft. (See NOTE 6). Equipment. The basic required equipment as prescribed in the applicable airworthiness and operating regulations must be installed in the airplane for certification. In addition, the following items of equipment are required: - Stick shaker, pre-stall warning, reference FOKKER Drawing A40265 - Audible stall warning, reference FOKKER Drawing A40265 - Two nickel cadmium batteries, reference FOKKER Drawing A43250 - Approved Airplane Flight Manual. 9 A20EU, Rev 15 III. FOKKER Model F28 Mark 3000 (Transport Category) Approved 12 November 1982. The F28 Mk 3000 is similar to the Mk 1000 except for a wingspan extension of 60 inches. Engines. 2 Rolls-Royce Two Shaft Bypass Jet Engines: Spey Mk 555-15H. Fuel. Eligible engine fuels are listed in Rolls-Royce Operating Instructions, Document No. F-Sp2-F, Appendix 2. Engine Limits. Thrust RPM % TGT Conditions (lbs) HP LP (ºC) Time Limit Max. Takeoff 9900 102.5 109.5 565 5 minutes Max. Continuous 9520 98.5 108.5 520 Unrestricted Starting and - - 570 2 seconds Relight Max. Overspeed 105.5 115.5 - 20 seconds Max. Overtemp. 585 20 seconds Oil. See relevant Rolls-Royce Operating Instructions Manual. Oil Temperature Limits. Max. 15 min. 120ºC Max. unrestricted 100ºC Bleed Air. For max. bleed air extract from the engine refer to FAA Engine Type Certificate Data Sheet E2EU. APU Type. Garret AiResearch GTCP 36-4(A). Fuel. Eligible APU fuels are listed in Garrett AiResearch Document, Model Specification GTCP-36-4(A) SC-5754. APU Limits. Conditions Max. RPM (%) Max. TGT (ºC) Start - 705 Transient 10 sec. 110 705 Sustained 105 650 Airspeed Limits (APU). VMO (Maximum Operating) Sea level 331 kts 10,000 ft 336 kts 20,000 ft 343 kts 20,840 ft 344 kts Straight line variation between points. MMO 20,840 ft and above M = .75 VA (Maneuvering) See approved Airplane Flight Manual. VFE (Flap Extension) Flap Setting 25º 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft 42º 165 knots IAS up to 20,000 ft A20EU, Rev 15 10 III. FOKKER Model F28 Mark 3000 (cont'd) Airspeed Limits (APU). (cont'd) VLO (Landing Gear Operation) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft VLE (Landing Gear Extended) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft Maximum speed when wheel doors are retracted by means of winch - During Retraction 150 knots IAS 25º flap 140 knots IAS 42º flap Retracted 180 knots IAS 25º flap 155 knots IAS 42º flap Maximum Landing, Taxi and Flare-out Lights Extended Speed: VMO/MMO Center of Gravity (C.G.) Landing Gear Extended: Range. FORWARD AFT Gross Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 73,000 452.95 18.26 466.85 28.50 71,000 68,500 64,000 61,650 56,000 451.33 448.38 447.59 447.59 17.20 14.88 14.30 14.30 470.94 474.34 474.34 475.69 31.50 34.00 34.00 35.00 and lower Straight line variation between points. Gear retraction moment is 5833 in-lb, nose down. Maximum Weight. Takeoff 73,000 lb Landing 64,000 lb Zero fuel 56,000 lb Minimum Crew. 2 (pilot and copilot). Maximum Passengers. 70 (See NOTE 5). Maximum Baggage. Compartment Station (in.) Capacity Max. Floor C.G. Location From To (Cu. ft) Loading (in) Forward Belly 165.4 369.7 241.0 75 lb/sq ft 267.6 and Aft Belly 525.4 666.7 136.0 250 lb/ft 594.1 Rear Cabin 632.5 671.9 80.0 75 lb/sq ft 656.1 Baggage Compt. & 450 lb/ft 11 A20EU, Rev 15 III. FOKKER Model F28 Mark 3000 (cont'd) Maximum Baggage Forward Belly Compartment Aft Belly Compartment Max. structural Comp. 1 1118 Max. structural Comp. 4 810 Capacity (lb) Comp. 2 1394 Capacity (lb) Comp. 5 1230 Comp. 3 1103 TOTAL 2040 TOTAL 3615 Rear Cabin Baggage Compartment Max. Structural Capacity (lb) 1065 Fuel Capacity. Usable fuel (See NOTE 1 for unusable fuel). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Left Wing 1286.5 8491 470.93 Right Wing 1286.5 8491 470.93 Total 2573.0 16982 Total usable fuel by pressure fueling is 2546.7 U.S. Gal. When modified in accordance with approved FOKKER F28 Service Bulletin 28-12: Center Wing Tank 872.0 5755 429.94 All Tanks Total 3445.0 22737 460.55 Fuel weight based upon fuel density of 6.6. lb/U.S. Gal. Oil Capacity. Usable oil (See NOTE 1 for unusable oil). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Each engine 3.6 27.86 639.8 Total 7.2 55.72 Oil weight based upon oil density of 7.74 lb/U.S. Gal. Maximum Operating Altitude. 25,000 ft. (See NOTE 6). Equipment. The basic required equipment as prescribed in the applicable airworthiness and operating regulations must be installed in the airplane for certification. In addition, the following items of equipment are required: - Stick shaker, pre-stall warning, reference FOKKER Drawing A40265 - Audible stall warning, reference FOKKER Drawing A40265 - Two nickel cadmium batteries, reference FOKKER Drawing A43250 - Approved Airplane Flight Manual. IV. FOKKER Model F28 Mark 2000 (Transport Category) approved 29 October 1986. The Mk 2000 is basically a Mk 1000, with a fuselage stretch of 57 inch in front of and 30 inch aft of the wing. Engines. 2 Rolls-Royce Two Shaft Bypass Jet Engines: Spey Mk 555-15. When modified in accordance with approved Fokker F28 Service Bulletin No. 71-9: Spey Mk 555-15N. (See NOTE 7 regarding intermixing of engines). Fuel. Eligible engine fuels are listed in Rolls-Royce Operating Instructions, Document No. F-Sp2-F, Appendix 2. A20EU, Rev 15 12 IV. FOKKER Model F28 Mark 2000 (cont'd) Engine Limits. Thrust RPM % TGT Time Limit (lbs) (ºC) Conditions HP LP Max. Takeoff 9850 101.0 108.5 520 5 minutes Max. Continuous 9470 98.5 108.5 490 Unrestricted Starting and - - 540 2 seconds Relight Max. Overspeed 104.5 115.5 - 20 seconds Max. Overtemp. 540 20 seconds Oil. See relevant Rolls-Royce Operating Instructions Manual. Oil Temperature Limits. Max. 15 min. 120ºC Max. unrestricted 100ºC Bleed Air. For max. bleed air extraction from the engine refer to FAA Engine Type Certificate Data Sheet E2EU. APU Type. Garrett AiResearch GTCP 36-4(A). Fuel. Eligible APU fuels are listed in Garrett AiResearch Document, Model Specification GTCP-36-4(A) SC-5754. APU Limits. Conditions Max. RPM (%) Max. TGT (ºC) Start - 705 Transient 10 sec. 110 705 Sustained 105 650 Airspeed Limits (IAS). VMO (Maximum Operating) Sea level 331 kts 10,000 ft 336 kts 20,000 ft 343 kts 20,840 ft 344 kts Straight line variation between points. MMO 20,840 ft and above M = .75 VA (Maneuvering) See approved Airplane Flight Manual. VFE (Flap Extension) Flap Setting 25º 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft 42º 165 knots IAS up to 20,000 ft For airplane serial numbers 11042 and subsequent or when modified in accordance with approved Fokker F28 Service Bulletin 51-5: 42º 165 knots IAS up to 20,000 ft VLO (Landing Gear Operation) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft 13 A20EU, Rev 15 IV. FOKKER Model F28 Mark 2000 (cont'd) VLE (Landing Gear Extended) 200 knots IAS up to 15,000 ft 180 knots IAS up to 20,000 ft Maximum speed when wheel doors are retracted by means of winch - During Retraction 150 knots IAS 25º flap 140 knots IAS 42º flap Retracted 180 knots IAS 25º flap 155 knots IAS 42º flap Maximum Landing, Taxi and Flare-out Lights Extended Speed: VMO/MMO Center of Gravity (C.G.) Landing Gear Extended: Range. FORWARD AFT Gross Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 65,000 504.95 16.55 523.51 30.00 64,000 59,400 502.81 15.00 530.41 530.41 35.00 35.00 and lower 502.81 15.00 530.41 35.00 The FORWARD C.G. limits for weights between 65,000 lb and 59,500 lb shall be interpolated linearly. The AFT C.G. limits for weights between 65,000 lb and 64,000 lb shall be interpolated linearly. LANDING GEAR EXTENDED FORWARD AFT Gross Weight Inches aft Inches aft Lbs. of datum % MAC of datum % MAC 65,000 503.77 15.70 533.17 37.00 59,400 501.42 14.00 533.17 37.00 and lower 501.42 14.00 533.17 37.00 The C.G. limits for weights between 65,000 lb and 59,400 lb. shall be interpolated linearly. Gear retraction moment is 5833 in. lb. nose down. Maximum Weight. Takeoff 65,000 lb Landing 59,000 lb Zero fuel 54,500 lb Minimum Crew. 2 (pilot and copilot). Maximum Passengers. 79 (See NOTE 5). A20EU, Rev 15 14 IV. FOKKER Model F28 Mark 2000 (cont'd) Maximum Baggage. Compartment Station (in.) Capacity Max. Floor C.G. Lo- From To (Cu. ft) Loading cation (in) Forward Belly 165.4 426.7 308.0 75 lb/sq ft 259.9 and Aft Belly 582.4 753.7 171.3 250 lb/ft 665.1 Rear Cabin 719.5 758.9 80.0 75 lb/sq ft and 743.1 Baggage Compt. 450 lb/ft Maximum Baggage Forward Belly Compartment Aft Belly Compartment Max. structural Comp. 1 1118 Max. structural Comp. 5 1340 Capacity (lb) Comp. 2 1394 Capacity (lb) Comp. 6 1230 Comp. 3 1394 TOTAL 2570 Comp. 4 714 TOTAL 4620 Rear Cabin Baggage Compartment Max. Structural Capacity (lb) 1065 Fuel Capacity. Usable fuel (See NOTE 1 for unusable fuel). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Left Wing 1286.5 8491 470.93 Right Wing 1286.5 8491 470.93 Total 2573.0 16982 When modified in accordance with approved FOKKER F28 Service Bulletin 28-12: Center Wing Tank 872.0 5755 429.94 All Tanks Total 3445.0 22737 460.55 Fuel weight based upon fuel density of 6.6. lb/U.S. Gal. Oil Capacity. Usable oil (See NOTE 1 for unusable oil). Location Volume (U.S. Gal.) Weight (lb) Arm (in.) Each engine 3.6 27.86 726.8 Total 7.2 55.72 Oil weight based upon oil density of 7.74 lb/U.S. Gal. Maximum Operating Altitude. 25,000 ft. (See NOTE 6). Equipment. The basic required equipment as prescribed in the applicable airworthiness and operating regulations must be installed in the airplane for certification. In addition, the following items of equipment are required: - Stick shaker, pre-stall warning, reference FOKKER Drawing A40265