# TCDS A20EU: Fokker Services B.V. - Type: Type certificate data sheet - Status: Current - Holder: Fokker Services B.V. - Revision: 15 - Revised: November 25, 2015 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 21 - Data sheet PDF: https://openairdocs.org/files/sha256/73/99/73996f81a55f5871238217f957b65872741d6e485717702b9f061559fff27e46 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/75A4D45744EE450186257F0F0081B15C.0001 - Page: https://openairdocs.org/tcds/A20EU ## Models (6) As the data sheet lists them. - F28 Mark 1000 - F28 Mark 4000 - F28 Mark 2000 - F28 Mark 0070 - F28 Mark 3000 - F28 Mark 0100 ## What the data sheet says Some pages are OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text 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 - Audible stall warning, reference FOKKER Drawing A40265 - Approved Airplane Flight Manual. 15 A20EU, Rev 15 OTHER DATA PERTINENT TO MODELS F28 MARK 1000, 2000, 3000 AND 4000: Datum. Tip of aircraft nose section, Station 0. 87.4 inches forward of front leveling pin. MAC. Mk 1000: 138.03 inches (leading edge of MAC is 425.10 inches aft of datum). Mk 2000: 138.03 inches (leading edge of MAC is 482.10 inches aft of datum). Mk 3000: 135.75 inches (leading edge of MAC is 428.18 inches aft of datum). Mk 4000: 135.75 inches (leading edge of MAC is 485.19 inches aft of datum). Leveling Means. - Two leveling pins mounted on the righthand side of the nosewheel bay at station 2434 and at station 3462. - The forward end of each seat rail (station 4875). - Two brackets mounted behind the rear pressure bulkhead at station 18024 on the Mk 1000 and 3000, and at station 20234 on the Mk 4000/Mk 2000. - For optical leveling two red marked protruding rivets are mounted on both sides of the fuselage on the outer skin; one at station 4960 and one at station 14350 on the Mk 1000 and 3000; one at station 4960 and one at station 16560 on the Mk 4000 and Mk 2000. Control Surface Movements. Surface Travel Elevator Up 25º Down 15º Rudder Left 33º Right 33º Ailerons Up 20º Down 20º Flaps (total) 42º Lift Dumpers 60º Speedbrakes 60º Stabilizer Up 2º30' Down 8º20' Service Information. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by RLD or CAA-NL. Any such documents are accepted by the FAA and are considered FAA approved: Instructions for Continued Airworthiness consisting of: - Structural Repair Manual - Service Bulletins - Structural Inspection Program (SIP) Document - Airworthiness Recommendations Catalog (ARC) - Corrosion Control Program (CCP) Document - Maintenance Schedule, Maintenance Data or Custormer Maintenance Program (ref. NTO 182) Service bulletins, repair instructions (letters, drawings, specifications, forms used for transmitting repair descriptions, etc.), structural repair manuals, airplane flight manuals, vendor manuals, and overhaul and maintenance manuals that are published in the English language and indicate applicability to the U.S. approved type designs included in this Type Certificate and that include a statement “RLD, CAA/NL or EASA Approved” are accepted by the FAA and are considered “FAA Approved.” A20EU, Rev 15 16 Additionally, Fokker Services as a DOA holder has been given authorization by EASA to approve Service Bulletins (SB) that are not associated with Airworthiness Directives. Accordingly, Service Bulletins and repair instructions which contain a statement “The technical content of this document is approved under the authority of DOA ref. EASA.21J.059” are considered EASA approved and are therefore accepted by the FAA and are considered FAA approved. For approvals made before September 28, 2003 the statement “The technical information contained in this document has been approved under the authority of FAA Design Organization Approval no. RLD.JA.001” may have been used and are also considered FAA approved. Certification basis for Models F28, Mark 1000, 2000, 3000 and 4000: FAR 21.29; FAR 25 effective 1 February 1965 including Amendments 25-1 through 25- 11, and 25-14. Special Conditions notified in FAA letter dated 30 November 1967 to the RLD/CAA- NL, Kingdom of the Netherlands. Special retroactive requirements of Amendment 25-15 (Sections 25.2(a) and (b)). The Netherlands Code for Airworthiness of Transport Category Aircraft, dated March 1967, plus FAR 25.473, 25.479, 25.485, and 25.1011 plus the Special Conditions notified in FAA letter to the RLD/CAA-NL dated 30 November 1967, were found to provide a level of safety equivalent to FAR 25 effective 1 February 1965 plus Amendments 25-1 through 25-10, to enable certification under the provisions of FAR 21.29 (a)(1)(ii). Compliance has been shown with: - SFAR 27, Amendments 27-1 through 27-3 (Fuel Venting) by incorporation of Rolls-Royce Modification 5338 for the Mk 4000. - SFAR 27, Amendments 27-1 through 27-4 (Fuel Venting) by incorporation of Rolls-Royce Modification 5338 for the MK 3000 and Mk 2000. - FAR Part 36, Amendment 36-1: Mk 1000 and Mk 2000. - FAR Part 36, Amendment 36-1 through 36-8: Mk 4000 and 3000. - FAR Part 36, Amendment 36-1 through 36-12: Mk 4000 equipped with Rolls-Royce RB 183 Mk. 555-15P engines. Certification with the ditching provisions of FAR 25.801 has not been requested by Fokker, BV. If overwater operation is to be approved, compliance with FAR 25.801 must be demonstrated. Compliance with the optional requirements of FAR 25.1419, Icing Protection has been established. Compliance with the following requirements which were not required based on the effective application date in accordance with FAR 21.17(c)(2) was elected by the manufacturer in accordance with FAR 21.17(d): - FAR 25, Amendments 25-12, 25-13, 25-16 through 25-20 - FAR 25, Powerplant requirements, applicable to the APU installation, including Amendments 25-1 through 25-20. In addition, for the Mk 4000, Mk 3000 and Mk 2000 - FAR 25, Amendment 25-21 and 25-22 - FAR 25, Amendment 25-24 if SFENA horizon 701-15-V4 has been installed - FAR 25, Amendments 25-25, 25-28 through 25-31 - Sections 25.803(e)(1) and (e)(2); 25.811(d)(1), (d)(2), and (d)(3); 25.812(a), (c), (d), (e), (f), (g)(1), (g)(2); and 25.813(c) as amended by Amendments 25-32 - FAR 25, Amendments 25-33, 25-34, and 25-37 - FAR 25, Amemdment 25-35 if Engine Rotor System Unbalance is installed - Section 25.1353 as amended by Amendments 25-41 and 25-42 17 A20EU, Rev 15 Certification basis for Models F28, Mark 1000, 2000, 3000 and 4000: (cont’d) Type Certificate A20EU, issued 24 March 1969 for the Mk 1000 and amended 27 June 1980 for the Mk.4000, 12 November 1982 for the Mk.3000 and 29 October 1986 for the Mk.2000. Effective Date of Application for Type Certificate per FAR 21.17(c)(2): 28 October 1966. Based on 14 CFR § 21.29(a) for new import TCs, (or § 21.101(g) for changes to TCs), applicable provisions of 14 CFR part 26 are included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this TC must demonstrate compliance with the applicable sections. Exemption No. 9804 has been issued for the Fokker F.28 Mk 1000 through 4000 to the requirements of 14 CFR Part 26 Sections 26.11, 26.43, 26.45 and 26.49. This exemption grants relief to Fokker Services B.V., from having to meet the requirements of § 26.11 for development of EWIS ICA and of §§ 26.43, 26.45, and 26.49 for development of damage tolerance data for repairs and alterations. See NOTE (10) “CAA-NL (formerly RLD) originally type certificated these aircraft under its type certificate Number A23F. The FAA validated this product under U.S. Type Certificate Number A20EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of CAA-NL.” V. Fokker Model F.28 Mark 0100 (Transport Category) approved April 21, 1989. The F.28 Mk0100 (based on the Mk4000) will have two high by-pass ratio engines with thrust reversers; extensive use of composites; increased fuselage length by 18.83 feet with plugs foward and aft of the wing; increased wing span by 9.8 feet; increased wing chord and improved aerodynamics with extended leading and trailing edges; increased horizontal stabilizer span by 4.6 feet; new flaps; larger ailerons; strengthened landing gear with new wheels and brakes; increased passenger count from 85 to 109 in the basic version; increased maximum weights; advanced digital electronic flight deck with integrated flight management system; autopilot/flight director, including CAT III autoland capability, and thrust management system; electronic flight instrument displays and full ARINC avionics. Engine. Two Rolls-Royce Two Shaft High Bypass Ratio Jet Engines with Thrust Reversers: TAY 620-15 or TAY 650-15. Fuel Specification. Eligible engine fuels are listed in the approved Airplane Flight Manual. Fuel Capacity. Usable fuel (See NOTE 1 for unusable fuel) Configuration with center wing bag tanks (Standard). LOCATION Volume (US Gal) Weight (lb) Arm (in) Wing tanks 2557 17073 672.0 Center tanks 830 5540 631.2 Total 3387 22611 662.0 Total usable fuel by pressure fueling is 3345 US gal. Fuel weight based upon fuel density of 6.6 lb/US Gal. (0.8 kg/1) Above mentioned table is applicable to an aircraft with the standard bag tank configuration. From a/c s/n 11442 and up an integral center wing was introduced. For this configuration the following table is applicable: A20EU, Rev 15 18 LOCATION Volume (US Gal) Weight (lb) Arm (in) Wing tanks 2547 17002 671.7 Center tanks 984 6570 630.4 Total 3531 23572 660.2 Total Usable Fuel by pressure fueling is 3547 U.S. Gal. Fuel weight is based upon fuel density of 6.6 lb/U.S. Gal (0.8 kg/1) Oil Specifications. Refer to the approved Airplane Flight Manual. Oil Capacity. Usable oil (See NOTE 1 for unusable oil) Location Volume (US Gal) Weight (lb) Arm (in) Each engine 1.3 11.0 945.5 Total 2.6 22.0 945.5 Oil weight based upon oil density of 7.74 lb/US gal. Oil Pressure Limits. Minimum acceptance for flight: Takeoff 30 psi Minimum to complete flight: Low idle to 78% N2 : 16 psi rising to 25 psi at Max Continuous following a straight line relationship. Oil Temperature Limits. Minimum for starting : minus 50º C Minimum before increasing power : minus 30º C Maximum (unrestricted) : plus 105º C Maximum (15 minutes) transient : plus 120º C Fuel Temperature Limits. The limits for the Tay 650-15 engine are: Maximum (unrestricted) : plus 95º C Maximum (15 minutes) transient : plus 130º C The limits for the Tay 620-15 engine are: Maximum (unrestricted) : plus 90º C Maximum (15 minutes) transient : plus 120º C Bleed Air. For maximum bleed air extraction from the engine refer to FAA Engine Type Certificate Data Sheet No. E25NE. Engine Limits. Condition N1% N2% MAX TGT Time Limit TAY 620-15 ºC During starts - - 700 Momentary (not exceeding During relights - - 780 2 seconds) _______________________________________________________________ Max Take-off 96.5 103.5 800 5 minutes Max Continuous 96.5 100.5 735 Unrestricted Max Overspeed 99.3 106.6 - 20 seconds Max Overtemperature - - 820 20 seconds Low Idle (Min) - 47.9 - Unrestricted Note: This is a minimum below which N2% should not fall. 19 A20EU, Rev 15 V. Fokker Model F28 Mark 0100 (Transport Category) (cont'd) Engine Limits. Condition N1% N2% MAX TGT Time Limit TAY 650-15 ºC During starts - - 740 Momentary (not exceeding during relights - - 780 2 seconds) Max Take-off 95.5 103.5 850 5 minutes Max Continuous 95.5 100.5 795 Unrestricted Max Overspeed 98.3 106.6 - 20 seconds Max Overtemperature - - 870 20 seconds Low Idle (Min) - 47.9 - Unrestricted Note: This is a minimum below which N2% should not fall. _______________________________________________________________ NOTE 1.: 100 per cent N1 = 8.393 rpm 100 per cent N2 = 12.136 rpm NOTE 2.: To avoid high fan blade stresses, stabilized ground operation in the N1 rpm range of 62 to 80 per cent is not permitted with a static airplane and wind velocities in excess of 15 kts. Thrust Reverser Limits. See the approved Airplane Flight Manual. APU Type. Garrett GTCP 36-150 (R) and GTCP 36-150 (RR) APU Fuels. Eligible APU fuels are listed in the approved Airplane Flight Manual. Airspeed Limits (IAS). Vmo/Mmo Maximum operating limit speed 320 kts / M 0.75 For S/N 11276 and up MMO increased to: M 0.77 VA Maximum design maneuvering speed: Airspeed Limits (VA -F28 Mk0100) 95,000 lb: A20EU, Rev 15 20 V. Fokker Model F28 Mark 0100 (Transport Category) (cont'd) When modified in accordance with approved Service Bulletin F100-51-001: 98,000 lb. 140 0 10,000 20,000 30,000 160 180 200 220 240 260 ALTITUDE (ft) 44,450 kg 98,000 lb 24,837 kg 54,756 lb SPEED (kt IAS) When modified in accordance with approved Fokker modification ECR 91408: 101,000 lb. Full application of rudder and aileron controls, as well as maneuvers that involve angle of attack near the stall, should be confined to speeds below VA VRA/MRA Rough air speed: 250 kts/ M 0.65 VFE Maximum flap extended speed: flaps at 8º : 250 kts/ M 0.50 15º and 25º : 220 kts/ M 0.45 42º : 180 kts/ M 0.36 Maximum flap extended altitude: 20,000 ft VLO/VLE Maximum Landing gear extended and operating speed: 200 kts. Maximum Landing gear extended altitude: 25,000 ft. Maximum Lift dumper extension speed: 170 kts. Maximum Operating Altitude. 35,000 ft. Maximum Weights. Max Taxi weight: 41,225 kg (90,875 lbs) Max Take-off weight: 40,995 kg (90,375 lbs) Max Landing weight: 39,915 kg (88,000 lbs) Max Zero Fuel weight: 36,740 kg (81,000 lbs) or Max Taxi weight: 42,230 kg (93,100 lbs) Max Take-off weight: 41,995 kg (92,590 lbs) Max Landing weight: 39,915 kg (88,000 lbs) Max Zero Fuel weight: 36,740 kg (81,000 lbs) or 21 A20EU, Rev 15 Maximum Weights. (cont’d) Max Taxi weight: 43,320 kg (95,500 lbs) Max Take-off weight: 43,090 kg (95,000 lbs) Max Landing weight: 38,780 kg (85,500 lbs) Max Zero Fuel weight: 35,835 kg (79,000 lbs) When modified in accordance with approved Service Bulletin No. F100 51-001: Max Taxi weight: 44,680 kg (98,500 lbs) Max Take-off weight: 44,450 kg (98,000 lbs) Max Landing weight: 39,915 kg (88,000 lbs) Max Zero Fuel weight: 36,740 kg (81,000 lbs) When modified in accordance with approved Service Bulletin No. F100 51-010: Max Taxi weight: 46,040 kg (101,500 lbs) Max Takeoff weight: 45,810 kg (101,000 lbs) Max Landing weight: 39,915 kg ( 88,000 lbs) Max Zero Fuel weight: 36,740 kg ( 81,000 lbs) When modified in accordance with approved Service Bulletin No. F100 51-012: Max Taxi weight: 44,225 kg (97,500 lbs) Max Takeoff weight: 43,995 kg (97,000 lbs) Max Landing weight: 39,915 kg (88,000 lbs) Max Zero Fuel weight: 36,740 kg (81,000 lbs) C.G. Range 95,000 lbs. 66000 68000 70000 72000 74000 76000 78000 80000 82000 84000 86000 88000 90000 92000 94000 96000 98000 30000 31000 32000 33000 34000 35000 36000 37000 38000 39000 40000 41000 42000 43000 44000 kg lb 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 AIRCRAFT WEIGHT 43090 kg 95000 lbs MTOW MLW MZFW 38780 kg 85500 lbs 35835 kg 79000 lbs CENTER OF GRAVITY (% MAC) MTW 43320 kg 95500 lbs TAKE-OFF & LANDING EN ROUTE TAXI A20EU, Rev 15 22 Fokker Model F28 Mark 0100 (Transport Category) (cont'd) When modified in accordance with approved Service Bulletin No. F100 51-001: 98,000 1b. Center of Gravity - F28 Mk0100 AIRCRAFT WEIGHT kr 1b 45000 100000 98000 44000 96000 HOW 43000 94000 44680 kr 42000 92000 98500 1bs 41000 90000 40000 88000 39000 86000 38000 84000 135915 k 82000 37000 80000 36000 35000 34000 06740 Fr 74000 1000 1 33000 32000 31000 68000 30000 66000 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 CENTER OF GRAVITY (% MAC) 23 A20EU, Rev 15 V. Fokker Model F28 Mark 0100 (Transport Category) (cont d) C.G. Range When modified in accordance with approved Fokker Service Bulletin No. F100 51-010: 101,000 lb Center of Gravity -F.28 Mk0100 AIRCRAFT WEIGHT kg 46000- - 102000 47 000 - - 100 000 - 104 000 • MTOW MTW 45 000 - 98 000 44 000 - 96 000 46 040 kg 101 500 lb 43 000 - 94 000 42 000 - 92 000 45 810 kg 101 000 lb 41 000 - 90 000 MLW 40 000 - 88 000 39 000 - 86 000 38 000 - 84 000 39 915 kg 88 000 lb 82 000 MZFW 37 000 - 80 000 36 000 78 000 35 000 76 000 36 740 kg 34 000 81 000 lb 74 000 33 000 000 32 000 70 000 31 000 68 000 30 000 66 000 29 000 64 000 28 000 - 62 2 000 27 000 60 000 58 000 26 000 25 000 56 000 TAXI 54 000 TAKE-OFF & LANDING 24 000 EN ROUTE 52 000 23 000 50 000 22 000 - 48 000 21 000 46 000 20 000 - 44 000 35 37 16 18 20 22 24 26 28 30 32 34 36 38 CENTER OF GRAVITY (% MAC) Datum. The datum referred to is defined as the Fuselage Datum (Station Zero), which is 2434 mm (95.8 inch) forward aft of the front leveling pin. (Tip of the aircraft nose section). M.A.C. The Mean Aerodynamic Cord is 3832.6 mm (12 ft 6.9 inch). Leveling Means. Two leveling pins are installed on RH side of the nose gear bay for checking the longitudinal level of the aircraft. Two brackets are installed on the aft wall of the APU compartment for checking the lateral level of the aircraft. Minimum Flight Crew. 2 (Pilot and Co-pilot) Maximum Passengers Seating See Note 5. Maximum Baggage. Refer to the appropriate document "Basic Weight and Balance Information". A20EU, Rev 15 24 V. Fokker Model F28 Mark 0100 (Transport Category) (cont'd) Control Surface Movements (Max). Elevator Up 25º Down 15º Rudder Left 33º Right 33º Aileron Up 20º Down 20º Control Surface Movements (Max). (cont’d) Flap: single slotted 18º double slotted 42º Liftdumpers 60º Horz. Stabilizers + 3º (A/C nose down) -9º (A/C nose up) Speed brakes 60º Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. - The approved Airplane Flight Manual issued for the applicable aircraft serial number. Service Information. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by RLD or CAA-NL. Any such documents are accepted by the FAA and are considered FAA approved.: - Structural Repair Manual - MRB document - Maintenance Planning Document - Service Bulletins - Airworthiness Recommendations Catalog (ARC) - Certification Maintenance Requirements (CMR), Airworthiness Limitation Items (ALI), - Safe Life Items (SLI) Service bulletins, repair instructions (letters, drawings, specifications, forms used for transmitting repair descriptions, etc.), structural repair manuals, airplane flight manuals, vendor manuals, and overhaul and maintenance manuals that are published in the English language and indicate applicability to the U.S. approved type designs included in this Type Certificate and that include a statement “RLD, CAA/NL, or EASA Approved” are accepted by the FAA and are considered “FAA Approved.” Additionally, Fokker Services as a DOA holder has been given authorization by EASA to approve Service Bulletins (SB) that are not associated with Airworthiness Directives. Accordingly, Service Bulletins and repair instructions which contain a statement “The technical content of this document is approved under the authority of DOA ref. EASA.21J.059” are considered EASA approved and are therefore accepted by the FAA and are considered FAA approved. For approvals made before September 28, 2003 the statement “The technical information contained in this document has been approved under the authority of FAA Design Organization Approval no. RLD.JA.001” may have been used and are also considered FAA approved. Certification Basis for F.28 Mark 0100 1. FAR Part 25 dated February 1, 1965 as amended by Amendments 25-1 through 25-60 effective June 16, 1986, except paragraph 25.631, and those paragraphs affected by Am 25-57 effective March 26, 1984, and except the paragraphs amended as follows: Am 25-22 effective May 2, 1970 - 25.1309 (for modified systems only) Am 25-41 effective September 1, 1977 - 25.109 Am 25-54 effective October 14, 1980 - 25.783 (see Note 9) Am 25-72 effective August 20, 1990 - 25.791(d) and (e) Compliance has been demonstrated to the following optional requirement: 25 A20EU, Rev 15 • Ditching, FAR § 25.801 2. FAR Part 36 effective December 1, 1969, as amended through Am 36-16 effective November 22, 1988. 3. SFAR 27 as amended through Am 27-6 effective March 28, 1986. 4. Special condition 25-ANM-14 issued on October 19, 1987 (Lightning Protection for Electronic Devices). 5. Equivalent Level of Safety Findings: 25.729(e)(2) and (e)(3) Landing Gear Warning System 25.811(e)(3) Emergency Exit Markings 25.901(d) APU Installation - Instruments 25.1307(d) Total loss of all cockpit communication 6. Exemptions: none Based on § 21.17(a) for new TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the certification basis. For any future part 26 amendments, the holder of this TC must demonstrate compliance w ith the applicable sections VI. Fokker model F28 Mk0070 (Transport Category) approved, October 14, 1994 The F28 Mk0070 model is derived from the F.28 Mk0100 and differs only in the fuselage length being reduced by 4.623 metres (182 inches). Engine. Two Rolls-Royce Two Shaft High Bypass Ratio Jet Engines with Thrust Reversers: TAY 620-15. Fuel Specification. Eligible engine fuels are listed in approved Airplane Flight Manual. Fuel Capacity. Usable fuel (See NOTE 1 for unusable fuel) Standard two tank configuration: LOCATION Volume (US Gal) Weight (lb) Arm (in) Wing tanks 2547 17002 575.1 Configuration with optional Integral Center Wing Tank: LOCATION Volume (US Gal) Weight (lb) Arm (in) Wing tanks 2547 17002 575.1 Center tanks 984 6570 534.3 Total 3531 23572 565.1 Total usable fuel by pressure fueling for the two tank configuration is 2493 US Gal. Include. ICWT the total usable fuel by pressure fueling is 3547 US Gal. Fuel weight is based upon fuel density of 6.6lb/US Gal. (0.8 kg/1). Oil Specifications. Refer to approved Airplane Flight Manual. Oil Capacity. Usable oil (See NOTE 1 for unusable oil) Location Volume (US Gal) Weight (lb) Arm (in) Each engine 1.4 10.9 763.5 Total 2.8 21.8 763.5 Oil weight based upon oil density of 7.74 lb/US gal. Oil Pressure Limits. Minimum acceptance for flight: Take-off 30 psi Minimum to complete flight: Low idle to 78% N2 : 16 psi rising to 25 psi at Max Continuous A20EU, Rev 15 26 following a straight line relationship. VI. Fokker model F.28 Mk0070 (Transport Category) (cont'd) Oil Temperature Limits. Minimum for starting : minus 50º C Minimum before increasing power : minus 30º C Maximum (unrestricted) : plus 105º C Maximum (15 minutes) transient : plus 120º C Fuel Temperature Limits. TAY 620-15 Maximum (unrestricted) : plus 90º C Maximum (15 minutes) transient : plus 120º C Bleed Air. For maximum bleed air extraction from the engine refer to FAA Engine Type Certificate Data Sheet No. E25NE. _______________________________________________________________ Engine Limits. Condition N1% N2% MAX TGT Time Limit TAY 620-15 ºC During starts - - 700 Momentary (not exceeding during relights - - 780 2 seconds) Max Take-off 96.5 103.5 800 5 minutes Max Continuous 96.5 100.5 795 Unrestricted _______________________________________________________________ Max Overspeed 99.3 106.6 - 20 seconds _______________________________________________________________ Max Overtemperature - - 870 20 seconds _______________________________________________________________ Low Idle (Min) - 47.9 - Unrestricted Note: This is a minimum below which N2% should not fall. NOTE 1.: 100 per cent N1 = 8.393 rpm 100 per cent N2 = 12.136 rpm NOTE 2.: To avoid high fan blade stresses, stabilized ground operation in the N1 rpm range of 62 to 80 per cent is not permitted with a static airplane and wind velocities in excess of 15 kts. Thrust Reverser Limits. See approved Airplane Flight Manual. APU Type. Only Garrett GTCP 36-150 (RR) is applicable APU Fuels. Eligible APU fuels are listed in the approved Airplane Flight Manual. 27 A20EU, Rev 15 VI. Fokker model F28 Mk0070 (Transport Category) (cont'd) Airspeed Limits (IAS). Vmo Mmo Maximum operating limit speed 320 kts / M 0.77 VA Maximum design maneuvering speed: 81,000 lb. 230 36 740 kg 220 481 000 ฿ 210 200 SPEED 190 (kt. IAS) 180 1 70 22 610 kg 160 49 850 Ib 150 140 10000 20000 30000 ALTITUDE (ft) 83,760 lb. 230 37 995 kg 220 83 760 6 210 200 SPEED 190 (kt. IAS) 180 170 22 608 kg 160 49 850 b 150 140 10000 20000 30000 ALTITUDE (f) 84,000 1bs. 230 38 100 kg 220 1 84 000 b 210 200 SPEED 190 (kt. IAS) 180 170 22 608 kg 160 1 49 850 1b 150 140 10000 20000 30000 ALTITUDE (ft) A20EU, Rev 15 28 VI. Fokker model F28 Mk0070 (Transport Category) (cont'd) Airspeed Limits (VA) - F.28 Mk0070 88,000 lbs. 92,000 lbs. 140 150 160 170 180 190 200 10000 20000 30000 SPEED (kts. IAS) ALTITUDE (ft) 210 220 230 4 1 7 3 0 k g 9 2 0 0 0 lb 2 2 6 1 0 k g 4 9 8 5 0 lb Full application of rudder and aileron controls, as well as maneuvers that involve angle of attack near the stall, should be confined to speeds below VA VRA/MRA Rough air speed: 250 kts/ M 0.65 VFE Maximum flap extended speed: flaps at 8º : 250 kts/ M 0.50 15º and 25º : 220 kts/ M 0.45 42º : 180 kts/ M 0.36 Maximum flap extended altitude: 20,000 ft VLO/VLE Maximum Landing gear extended and operating speed: 200 kts. Maximum Landing gear extended altitude: 25,000 ft. Maximum Liftdumper extension speed: 170 kts. Maximum Operating Altitude. 35,000 ft. 29 A20EU, Rev 15 VI. Fokker model F28 Mk0070 (Transport Category) (cont'd) Maximum Weights. Max Taxi weight: 36,965 kg (81,500 lbs) Max Take-off weight: 36,740 kg (81,000 lbs) Max Landing weight: 34,020 kg (75,000 lbs) Max Zero Fuel weight: 31,975 kg (70,500 lbs) Max Taxi weight: 38,325 kg (84,500 lbs) Max Take-off weight: 37,995 kg (83,760 lbs) Max Landing weight: 34,020 kg (75,000 lbs) Max Zero Fuel weight: 32,655 kg (72,000 lbs) Max Taxi weight: 38,325 kg (84,500 lbs) Max Take-off weight: 37,995 kg (83,760 lbs) Max Landing weight: 36,740 kg (81,000 lbs) Max Zero Fuel weight: 32,655 kg (72,000 lbs) When modified in accordance with approved Service Bulletin No. F100-51-015: Max Taxi weight: 38,325 kg (84,500 lbs) Max Take-off weight: 38,100 kg (84,000 lbs) Max Landing weight: 36,740 kg (81,000 lbs) Max Zero Fuel weight: 32,655 kg (72,000 lbs) When modified in accordance with approved Service Bulletin No. F100-51-014: Max Taxi weight: 40,140 kg (88,500 lbs) Max Take-off weight: 39,915 kg (88,000 lbs) Max Landing weight: 36,740 kg (81,000 lbs) Max Zero Fuel weight: 33,565 kg (74,000 lbs) When modified in accordance with approved Service Bulletin No. F100-51-011: Max Taxi weight: 41,960 kg (92,500 lbs) Max Take-off weight: 41,730 kg (92,000 lbs) Max Landing weight: 36,740 kg (81,000 lbs) Max Zero Fuel weight: 33,565 kg (74,000 lbs) When modified in accordance with approved Service Bulletin No. F100-51-013: Max Taxi weight: 38,325 kg (84,500 lbs) Max Take-off weight: 38,100 kg (84,000 lbs) Max Landing weight: 35,830 kg (79,000 lbs) Max Zero Fuel weight: 32,655 kg (72,000 lbs) When modified in accordance with approved Service Bulletin No. F100-51-024: Max Taxi weight: 38,325 kg (84,500 lbs) Max Take-off weight: 36,740 kg (81,000 lbs) Max Landing weight: 36,740 kg (81,000 lbs) Max Zero Fuel weight: 33,565 kg (74,000 lbs) C.G Range. To obtain paper copies of Center of Gravity charts for 81,000 lbs., 83,760 lbs., 83,760 lbs. (with higher MLW), 84,000 lbs., and 88,000 lbs., contact Fokker or FAA, AFS-610 (phone 405/954-6628). A20EU, Rev 15 30 VI. Fokker model F28 Mk0070 (Transport Category) (cont'd) 92,000 lb 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 54,000 56,000 58,000 60,000 62,000 64,000 66,000 68,000 70,000 72,000 74,000 76,000 78,000 80,000 82,000 84,000 86,000 88,000 90,000 92,000 94,000 96,000 2 5 , 0 0 0 26,000 43,000 42,000 41,000 40,000 39,000 38,000 37,000 36,000 35,000 34,000 33,000 32,000 31,000 30,000 29,000 28,000 27,000 kg lb AIRCRAFT WEIGHT MZFW MLW MTW MTOW 41,955 kg 92,500 lb 41,730 kg 92,000 lb 36,740 kg 81,000 lb 33,565 kg 74,000 lb CENTER OF GRAVITY (% MAC) TA K E-O FF & LA N D IN G EN RO U TE TA X I Datum. The datum referred to is defined as the Fuselage Datum (Station Zero), which is 2434 mm (95.8 inch) forward aft of the front leveling pin. (Tip of the aircraft nose section). M.A.C. The Mean Aerodynamic Cord is 3832.6 mm (12 ft 6.9 inch). Leveling Means. Two leveling pins are installed on RH side of the nose gear bay for checking the longitudinal level of the aircraft. Two brackets are installed on the aft wall of the APU compartment for checking the lateral level of the aircraft. Minimum Flight Crew. 2 (Pilot and Co-pilot) Maximum Passengers. See note 5. Maximum Baggage. Refer to the appropriate document "Basic Weight and Balance Information". 31 A20EU, Rev 15 VI. Fokker model F28 Mk0070 (Transport Category) (cont'd) Control Surface Movements (Max). Elevator Up 25º Down 15º Rudder Left 33º Right 33º Aileron Up 20º Down 20º Flap: single slotted 18º double slotted 42º Liftdumpers 60º Horz. Stabilizers + 3º (A/C nose down) -10º (A/C nose up) Speed brakes 60º Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. - The approved Airplane Flight Manual issued for the applicable aircraft serial number. Service Information. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by RLD or CAA-NL. Any such documents are accepted by the FAA and are considered FAA approved: Instructions for Continued Airworthiness consisting of: - Structural Repair Manual - MRB document - Maintenance Planning Document - Service Bulletins - Airworthiness Recommendations Catalog (ARC) - Certification Maintenance Requirements (CMR), Airworthiness Limitation Items (ALI), - Safe Life Items (SLI) Repair instructions (letters, drawings, specifications, forms used for transmitting repair descriptions, etc.), airplane flight manuals, vendor manuals, and overhaul and maintenance manuals that are published in the English language and indicate applicability to the U.S. approved type designs included in this Type Certificate and that include a statement “RLD, CAA/NL or EASA Approved” are accepted by the FAA and are considered “FAA Approved.” Additionally, Fokker Services as a DOA holder has been given authorization by EASA to approve Service Bulletins (SB) that are not associated with Airworthiness Directives. Accordingly, Service Bulletins and repair instructions which contain a statement “The technical content of this document is approved under the authority of DOA ref. EASA.21J.059” are considered EASA approved and are therefore accepted by the FAA and are considered FAA approved. For approvals made before September 28, 2003 the statement “The technical information contained in this document has been approved under the authority of FAA Design Organization Approval no. RLD.JA.001” may have been used and are also considered FAA approved. Certification Basis for F28 Mark 0070 1. FAR Part 25 dated February 1, 1965, as amended by Amendments 25-1 through 25-60, except June 16, 1986, except paragraph 25.631, and those paragraphs affected by Am 25-27 effective March 26, 1984, and except the paragraphs amended as follows: Am 25-64 effective June 16, 1988 - 25.562(b),(c)(4), (c)(7) and (c)(8) (Passenger seats only and not applicable to floor structure and seat tracks.) Am 25-66 effective September 26, 1988 - 25.20, 25.21, 25.23, 25.25, 25.27, 25.29, 25.31, 25.101 through 25.125, 25.143 through 25.255, and 25.1581 through 25.1587 (see paragraph 6). Am 25-72 effective August 20, 1990 - 25.365(e), (f), and (g) (For flight deck internal door). 25.561 (For passenger-flight deck-cargo compartment, and engine mounting), 25.772, 25.783 (see paragraph 6), 25.785, 25.787, 25.789, 25.791, 25.793, 25.803, 25.807, 25.809, A20EU, Rev 15 32 25.810, 25.811 (see paragraph 6), 25.812, 25.813, 25.815, 25.817, 25.851, 25.853, 25.855, 25.857, and 25.869(a) Am 25-74 effective May 16, 1991 - 25,854 Am 25-79 effective September 27, 1993 - 25.811(e)(2) Am 25-80 effective May 3, 1994 - 25.1316 Compliance has been demonstrated to the following optional requirement: • Ditching, FAR § 25.801 2. FAR Part 36 effective December 1, 1969, as amended through Am 36-20 effective September 16, 1992. 3. FAR Part 34 effective September 10, 1990. 4. Special Condition 25-ANM-89 issued October 6, 1994 (High Intensity Radiated Fields (HIRF) Protection - electrical systems. 5. Exemptions: None. 6. Equivalent Level of Safety Findings: 25.101 through 25.125 and 25.1581 through 25.1587 - Takeoff and Landing Performance 25.143 through 25.255 - 1 G Stall Speed § 25.729(e)(2)&(3) - Landing Gear Warning System § 25.783(e) - Cargo Door Mechanism-Inspection § 25.811(e)(3) - Emergency Exit Markings § 25.901(d) - APU Installation Instruments § 25.1307(d) - Total Loss of Cockpit Communications Based on § 21.17(a) for new TCs, or § 21.101(g) for changes to TCs, applicable provisions of part 26 are included in the certification basis. For any future part 26 amendments, the holder of this TC must demonstrate compliance with the applicabl e sections “CAA-NL (formerly RLD) originally type certificated the Mk0100 and Mk0070 aircraft under its type certificate Number T- 100-87. The FAA validated this product under U.S. Type Certificate Number A20EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of CAA-NL.” DATA PERTINENT TO ALL MODELS. Serial Numbers Eligible. The Netherlands Certificate of Airworthiness endorsed as noted under "Import Requirements" below must be submitted for each individual aircraft for which application for 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 the EASA 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 comply with the Fokker Type Design approved under U.S. Type Certificate No. A20EU and to be in a condition for safe operation.” NOTES Note 1. (a) Current Weight and Balance Report, including List of Equipment included in the certificated empty weight, interior arrangement and loading instructions must be provided for each aircraft at the time of the original certification. (b) The undrainable fuel is that amount of fuel after drainage in accordance with the procedures described in the AFM. The total amount and distribution of unusable fuel is listed in the following table. The highest level of the unusable fuel is the level prescribed by the critical flight conditions as defined in FAR 25.959 and must be included in the aircraft empty weight. The total unusable fuel is distributed as follows: A. Mk 1000 and 3000: Unusable Undrainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 8.97 59.2 Collector tanks 0.80 5.3 Main tanks 1.86 12.3 33 A20EU, Rev 15 TOTAL 11.63 76.8 512.2 If Center Wing Tank is installed: Fuel lines 9.45 62.4 Collector tanks 0.80 5.3 Main tanks 1.86 12.3 Center wing tanks 5.02 33.1 TOTAL 17.13 113.1 486.7 Fuel lines 0.71 4.7 Collector tanks 7.68 50.7 Main tanks 0.74 4.9 TOTAL 9.13 60.3 426.4 If Center Wing Tank is installed: Unusable Undrainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 1.33 8.8 Collector tanks 7.68 50.7 Main tanks 0.74 4.9 Center wing tanks 6.62 43.7 TOTAL 16.37 108.1 425.9 If Center Wing Tank is installed: The total amount of undrainable fuel is 113.1 lb The total amount of drainable unusable is 108.0 lb TOTAL unusable fuel 221.2 lb This weight must be included in the aircraft empty weight. B. Mk 4000 and Mk 2000 Unusable Undrainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 9.31 61.4 Collector tanks 0.80 5.3 Main tanks 1.86 12.3 TOTAL 11.97 79.0 577.2 Unusable Undrainable Fuel Volume (U.S. Gal.) Weight (lb) Arm (in.) If Center Wing Tank is installed: Fuel lines 9.79 64.6 Collector tanks 0.80 5.3 Main tanks 1.86 12.3 Center wing tanks 5.02 33.1 TOTAL 17.47 115.3 549.6 Unusable Drainable Fuel Fuel lines 0.71 4.7 Collector tanks 7.68 50.7 Main tanks 0.74 4.9 TOTAL 9.13 60.3 483.4 If Center Wing Tank is installed: Unusable drainable Fuel Volume (U.S. Gal.) Weight (lb) Arm (in.) Fuel lines 1.33 8.8 Collector tanks 7.68 50.7 Main tanks 0.74 4.9 A20EU, Rev 15 34 Center wing tanks 6.62 43.7 TOTAL 16.37 108.1 482.9 Note 1 (cont’d) B. Mk 4000 and Mk 2000 (cont’d) If Center Wing Tank is installed: The total amount of undrainable fuel is 115.3 lb The total amount of drainable fuel is 108.1 lb TOTAL unusable fuel 223.4 lb This weight must be included in the aircraft empty weight. C. Mk 0100: Unusable Undrainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 9.7 63.9 Collector tanks 0.7 4.5 Main tanks 1.6 10,5 Center wing tanks 3.7 24.4 TOTAL 15.7 103.3 700.8 Unusable drainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 1.4 8.8 Collector tanks 10.3 68.8 Main tanks negl. negl. Center wing tanks 1.6 10.5 TOTAL 13.2 87.3 637.8 For a/c with Integral Center Wing Tank Unusable Undrainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 9.7 63.9 Collector tanks 0.7 4.5 Main tanks 1.6 10.5 Center wing tank 1.1 7.0 TOTAL 13.0 85.9 716.0 Unusable drainable Fuel Volume (U.S. Gal.) Weight (lb) (Arm (in.) Fuel lines 1.4 8.8 Collector tanks 10.3 68.8 Main tanks negl. negl Center wing tanks 0.3 1.7 TOTAL 11.9 78.6 639.7 D. Mk 1000, 2000, 3000 and 4000. Engine system oil is the total engine oil less the quantity drainable from the tank, which is 29 lb. and must be included in the aircraft empty weight. The undrainable oil is distributed as follows: Arm (in.) Mk 1000 Mk 2000 Volume (U.S. Gal.) Weight (lb) Mk 3000 Mk 4000 Each engine 1.8 14.5 646.5 733.5 TOTAL 3.6 29 Mk 0100 Engine system oil is the total engine oil less the quantity drainable from the tank which is 9.7 lb. and must be included in the aircraft empty weight. 35 A20EU, Rev 15 Note 1 (cont’d) D. Mk 1000, 2000, 3000 and 4000. (cont’d) The total undrainable oil is distributed as follows: Volume (U.S. Gal.) Weight (lb) Arm (in.) Each engine 1.2 9.7 945.5 TOTAL 2.4 19.4 945.5 E. Mk0070 with standard fuel system Unusable Undrainable Fuel Volume (U.S.Gal.) Weight (lb.) Arm (in.) Fuel lines 8.7 57.5 Collector tanks 0.7 4.5 Main tanks 1.6 10.5 TOTAL 11.0 72.5 601.1 Unusable Drainable Fuel Fuel lines 1.4 8.8 Collector tanks 10.3 68.8 Main tanks negl. negl. TOTAL 11.7 76.8 542.3 Mk0070 with integral center wing tank (optional) Unusable Undrainable Fuel Volume (U.S.Gal.) Weight (lb.) Arm (in.) Fuel lines 8.9 58.7 Collector tanks 0.7 4.5 Main tanks 1.6 10.5 Integral center wing tank 1.1 7.0 TOTAL 12.2 80.6 596.9 Unusable Drainable Fuel Fuel lines 1.4 8.8 Collector tanks 10.3 68.8 Main tanks negl. negl. Integral center wing tank 0.3 1.7 TOTAL 11.9 78.6 542.7 (Undrainable oil): No change except for the arm: Each engine: 763.5 (in) Total : 763.5 (in) Note 2. (a) Mk 1000, 2000, 3000 and 4000 All placards required in the approved Airplane Flight Manual must be installed in the appropriate locations. (b) Mk 0100 Airplane operation must be in accordance with the approved Airplane Flight Manual. All placards required in either the approved Airplane Flight Manual or the Certification Basis must be installed in the airplane in accordance with the applicable Fokker drawings, as follows: - Interior placards: drawings D93200 thru D93399 - Exterior placards: drawings D85500 thru D85699 - Cockpit placards: T.N. F.28 -61-037 (c) The Mk0070 drawing numbers are: Interior placards: D932**- (C) Exterior placards: D855**-(C) Cockpit placards: T.N F.28-61-037 A20EU, Rev 15 36 Note 3. A. Mk 1000, 2000, 3000 and 4000 (a) Required inspections items related to fatigue and the service life limits for aircraft structural parts, which are fatigue critical, are listed in the approved Fokker F28 Structural Integrity Program Document No. 28438. (b) The required Maintenance and Inspection to maintain airworthiness based on/involving reliability are presented in approved Chapter 05-10 of the Fokker Maintenance Manual. (c) Inspection items and service life limits for engine parts are listed in Rolls-Royce NTO No. 50, Spey Maintenance Manual Chapter 5 and Rolls-Royce SB SP.70-1. B. Mk 0100, Mk070 (a) For the F28 Mk0100 and the F28 Mk070 the required structural inspections for damage-tolerant structure and the retirement times for safe-life parts are referenced in the approved Airworthiness Limitations Section in Section 06, Appendix 1 of the MRB document. The Airworthiness Limitations Section includes the Certification Maintenance Requirements (CMR's). Mk0100 only (b) Until service bulletin F100-49-007 has been incorporated, inspect and verify operation of the APU flapper check valve and APU inlet temperature sensor at 250 hours intervals. Note 4. Mk 1000, 2000, 3000 and 4000 only If the airplane is operated from unpaved runways, the applicable certified performance information should be incorporated for: (a) Mk 1000 and Mk.2000 Approved Flight Handbook Volume II, Section 11, paragraph 8. (b) Mk 3000 and Mk 4000 Approved Flight Handbook Volume II, Section 9, paragraph 5. Note 5. A. For the approved interior lay-out and maximum passenger, capacity reference Fokker Master Drawings: (a) Mk 1000, 2000, 3000 and 4000 For the approved interior layout refer to Fokker drawings A85001 and A85002 applicable for each aircraft when delivered. For the Mark 1000 and 3000 with 70 passengers refer to F28 Service Bulletin No. 25-96. (b) For the F.28 Mk.0100 the maximum number of passenger seating capacity demonstrated for emergency evacuation is 109. For the approved interior layout refer to Fokker drawings D85001 thru D85157, W85031, W85032 and W98251 applicable for each aircraft when delivered. (c) For the F.28 Mk.0070 the maximum number of passenger seating capacity demonstrated for emergency evacuation is 79. For the approved interior layout refer to Fokker drawings D85060 thru D85157 approved for each aircraft when delivered. B. All replacement seats (crew, passenger, lounge), although they may comply with TSO C39, must also be demonstrated to comply with FAR 25.785 and FAR 25.561. Other installations such as berths, buffets, compartments, or items of mass which could create a hazard to the safety of passengers and crew must also be demonstrated to meet the same requirements. (a) Mk 1000, 2000, 3000 and 4000 37 A20EU, Rev 15 Passenger seats meeting the structural criteria of Fokker Technical Specification TS-28-138 will meet these requirements. (b) Mk 0100 Passenger seats meeting the structural criteria of Fokker Technical Specification TS-100-003 will meet these requirements. (c) Mk 070 Passenger seats meeting the structural criteria of Fokker Technical Specification TS-070-001 will meet these requirements. Note 6. Mk 1000, 2000, 3000 and 4000 only (a) When modified in accordance with approved FOKKER F.28 Service Bulletin 21-12; 30,000 feet. (b) When modified in accordance with approved FOKKER F.28 Service Bulletin 21-16; 35,000 feet. Note 7. Mk 1000, 2000, 3000 and 4000 only Combinations of engines which can be intermixed and their applicable limitations are covered in the approved Flight Manual, which is a part of the F.28 Flight Handbook. Note 8. The documents which are approved by the Airworthiness Authority (RLD/CAA-NL/EASA) include a statement to that effect. The statement may be interpreted as "FAA approved". This also applies to the documents listed herein under "Service Information" and Note 3. Note 9. F.28 Mark 0100 For the passenger door with integral stair, compliance has been shown with FAR 25.783, Amdt 25-54, when modified in accordance with approved Service Bulletin F100-52-044 (standard incorporated from a/c s/n 11442 onwards) and approved Service Bulletin F100-53-080 (standard incorporated in a/c s/n 11461, 11462, 11470, 11472, 11473, 11496, 11497, 11500, 11503, 11505, 11509, 11511, 11516 and 11518). Note 10. This exemption does not grant relief from the related operational requirements. Should a person choose to operate one of the airplane models covered by this exemption under 14 CFR Part 121 or 129 beyond the operational compliance deadlines as stated in § 121.1111 or § 129.111 (EWIS ICA) or in § 121.1109(c) or § 129.109(b) (damage tolerance data for repairs and alterations), that person will be required to comply with those operational requirements. .....END..... ``` ## ADs (308, 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 2023-14-04](https://openairdocs.org/ad/2023-14-04): Time Limits/Maintenance Checks · Fokker Services B.V. F28 Mark 0070 and F28 Mark 0100. Effective Aug 15, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. 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Effective Jan 18, 2019 - [AD 2018-25-03](https://openairdocs.org/ad/2018-25-03): Landing gear · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Jan 14, 2019 - [AD 2018-24-05](https://openairdocs.org/ad/2018-24-05): Landing gear · Fokker Services B.V. F.28 Mark 0070, F.28 Mark 0100, F.28 Mark 1000 and 3 more. Effective Jan 2, 2019 - [AD 2018-23-12](https://openairdocs.org/ad/2018-23-12): Equipment/furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 180 more. Effective Dec 28, 2018 - [AD 2018-17-06](https://openairdocs.org/ad/2018-17-06): Landing gear · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Sep 21, 2018 - [AD 2018-07-21](https://openairdocs.org/ad/2018-07-21): Equipment/furnishings · Fokker Services B.V. F.28 Mark 0100. Effective May 21, 2018 - [AD 2018-07-11](https://openairdocs.org/ad/2018-07-11): Equipment/furnishings · Fokker Services B.V. F.28 Mark 0100. Effective Apr 23, 2018 - [AD 2018-04-03](https://openairdocs.org/ad/2018-04-03): Landing gear · Fokker Services B.V. F.28 Mark 0100. Effective Mar 30, 2018 - [AD 2018-02-03](https://openairdocs.org/ad/2018-02-03): Navigation · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Feb 15, 2018 - [AD 2018-02-09](https://openairdocs.org/ad/2018-02-09): Fuel · Fokker Services B.V. F.28 Mark 1000, F.28 Mark 2000, F.28 Mark 3000 and 1 more. Effective Feb 6, 2018 - [AD 2018-01-09](https://openairdocs.org/ad/2018-01-09): Doors · Fokker Services B.V. F.28 Mark 0100. Effective Jan 29, 2018 - [AD 2018-01-05](https://openairdocs.org/ad/2018-01-05): Fuselage · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Jan 22, 2018 - [AD 2018-01-06](https://openairdocs.org/ad/2018-01-06): Engine controls · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Jan 22, 2018 - [AD 2017-25-14](https://openairdocs.org/ad/2017-25-14): Engine Controls · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Dec 29, 2017 - [AD 2017-25-02](https://openairdocs.org/ad/2017-25-02): Placards and markings · Fokker Services B.V. F.28 Mark 1000, F.28 Mark 2000, F.28 Mark 3000 and 1 more. Effective Dec 21, 2017 - [AD 2017-25-03](https://openairdocs.org/ad/2017-25-03): Ice and rain protection · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. Effective Dec 21, 2017 - [AD 2017-14-09](https://openairdocs.org/ad/2017-14-09): Wings · Fokker Services B.V. F.28 Mark 0100. Effective Aug 23, 2017 - [AD 2017-06-02](https://openairdocs.org/ad/2017-06-02): Placards and Markings · Fokker Services B.V. F.28 Mark 0100. Effective Apr 26, 2017 - [AD 2017-01-04](https://openairdocs.org/ad/2017-01-04): Fuselage · Fokker Services B.V. F.28 Mark 0100. Effective Feb 22, 2017 - [AD 2016-25-04](https://openairdocs.org/ad/2016-25-04): Wings · Fokker Services B.V. F.28 Mark 0070 and F.28 Mark 0100. 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AMETEK AMERON, LLC d/b/a MASS Systems - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC ST00030IB](https://openairdocs.org/stc/ST00030IB): Installation of Test Tech ELT. APTOZ EHF - [STC ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC SA5869NM](https://openairdocs.org/stc/SA5869NM): Installation of class divider.. Safran Cabin Inc. - [STC ST01306LA](https://openairdocs.org/stc/ST01306LA): Installation of bin, LH and RH closet with doghouse, curtain header, sidewall, PSU, decompression grille, ceiling panel.. Safran Cabin Inc. - [STC SA3958NM](https://openairdocs.org/stc/SA3958NM): Installation of Floor Proximity Emergency Escape Path Marking System.. Bruce Aerospace Inc. - [STC ST02111AT](https://openairdocs.org/stc/ST02111AT): This installation adds three new parameter outputs (Control Column, Control Wheel, and Rudder Pedals) to the existing Digital Flight Data Recorder (DFDR) to meet the requirements of 14 CFR 121.344(c)(d).. 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 ST02236NY](https://openairdocs.org/stc/ST02236NY): Reconfiguration of passenger cabin interior.. Aero Technik Inc. - [STC ST00215IB](https://openairdocs.org/stc/ST00215IB): Installation of saf-Tglo ECO Photoluminescent Aisle Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST01936WI](https://openairdocs.org/stc/ST01936WI): Installation of LED lights. AeroLED's Holdings LLC - [STC ST02406AT](https://openairdocs.org/stc/ST02406AT): Installation of SafTGlo Inc. photoluminescent floor proximity emergency escape path marketing system (FPEEPMS).. STG Aerospace Inc. - [STC ST04562NY](https://openairdocs.org/stc/ST04562NY): Installation of saf-Tglo® SuperSeal UltraLite-X (SSUL-X) Photoluminescent Floor Proximity Emergency Escape Path Marking Systems. STG AEROSPACE GERMANY GmbH - [STC ST02896AT](https://openairdocs.org/stc/ST02896AT): Installation of a Kannad Model 406-AF Emergency Locator Transmittter (ELT).. Woven Electronics LLC - [STC ST09976SC](https://openairdocs.org/stc/ST09976SC): Installation of Emergency Escape Path Marker System.. Astronics Luminescent Systems Inc - [STC SA1220NW](https://openairdocs.org/stc/SA1220NW): Installation of Universal flight data recorder.. Honeywell International Inc - [STC SA3170SO](https://openairdocs.org/stc/SA3170SO): Installation of the CAS-81 TCAS II system and dual TRA-67 Mode S transponders.. Honeywell International Inc - [STC ST00476SE](https://openairdocs.org/stc/ST00476SE): Installation of Honeywell enhanced ground proximity warning system.. Honeywell International Inc - [STC ST00575AT](https://openairdocs.org/stc/ST00575AT): Installation of a CAS-81 TCAS II.. Honeywell International Inc - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC SA6057NM](https://openairdocs.org/stc/SA6057NM): Installation of standard windshear systems.. Honeywell International Inc - [STC ST02635LA](https://openairdocs.org/stc/ST02635LA): Modification to replace the existing Mode S Transponder system with the ACSS NXT-600 Mode S Transponder with ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC - [STC ST04399NY](https://openairdocs.org/stc/ST04399NY): Installation of saf-Tglo® Photoluminescent Aisle Path Marking System. STG Aerospace Ltd - [STC ST04340NY](https://openairdocs.org/stc/ST04340NY): Installation of TCAS 7.1 (ACAS II) upgrade of Prior Existing TCAS 7.0. Scandinavian Avionics Design ApS - [STC ST09269SC](https://openairdocs.org/stc/ST09269SC): Installation of X Band Radomes.. The NORDAM Group LLC - [STC ST02636LA](https://openairdocs.org/stc/ST02636LA): Modification to upgrade the existing XS-950 Mode S Transponder system to add ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC - [STC ST00034AT](https://openairdocs.org/stc/ST00034AT): Installation of a replacement coalescer filter.. Purolator Facet, Inc - [STC ST02632LA](https://openairdocs.org/stc/ST02632LA): Modification to replace the existing Mode S Transponder system with ACSS NXT-700 Mode S Transponder with ADS-B Out and optionally install ACSS NXG-900 GPS as a position source for ADS-B Out. Aviation Communications and Surveillance Systems - [STC ST02609LA](https://openairdocs.org/stc/ST02609LA): Modification to replace the existing Mode S Transponder system with ACSS NXT-700 Mode S Transponder with ADS-B Out. Aviation Communication and Surveillance Systems (ACSS) LLC - [STC SA2256SO](https://openairdocs.org/stc/SA2256SO): Installation of Jepson Burns Airest 5 tourist seats.. American Airlines Inc - [STC ST00393NY](https://openairdocs.org/stc/ST00393NY): Installation of NNAL 527 Stretcher System. Avmax Aviation Services Inc - [STC SA1882SO](https://openairdocs.org/stc/SA1882SO): Installation of a closet.. American Airlines Inc - [STC SA1925SO](https://openairdocs.org/stc/SA1925SO): Installation of a dry galley.. American Airlines Inc - [STC SA1933SO](https://openairdocs.org/stc/SA1933SO): Installation of emergency escape path lighting system.. American Airlines Inc - [STC SA1951SO](https://openairdocs.org/stc/SA1951SO): Installation of standardized equipment.. American Airlines Inc - [STC SA2087SO](https://openairdocs.org/stc/SA2087SO): Reconfiguration of passenger seating to an 4F/64Y mixed class configuration. American Airlines Inc - [STC SA2095SO](https://openairdocs.org/stc/SA2095SO): Reconfiguration of passenger seating to a 4F/59Y Mixed Class configuration. American Airlines Inc - [STC ST00061NY](https://openairdocs.org/stc/ST00061NY): Remove Flight Data Recorder Fairchild P/N 17M900-274 and install Fairchild Solid State Digital Flight Recorder, P/N S703-1000-00,. American Airlines Inc - [STC ST00102NY-D](https://openairdocs.org/stc/ST00102NY-D): Installation of Honeywell HG1050AC Series IRU. US Airways, Inc - [STC ST00118NY-D](https://openairdocs.org/stc/ST00118NY-D): All coach passenger seating and interior accommodations layout/installation (69Y, 70Y, and 72Y options). American Airlines Inc - [STC ST00120NY-D](https://openairdocs.org/stc/ST00120NY-D): To install a GTE Airfone System. American Airlines Inc - [STC ST00122NY-D](https://openairdocs.org/stc/ST00122NY-D): Installation and certification of a Collins VHF Series 900 PN 822-0323-002 VHF Communication System. American Airlines Inc - [STC ST00123NY-D](https://openairdocs.org/stc/ST00123NY-D): Installation of a forward cargo bay avionics rack and shroud enclosure. American Airlines Inc - [STC ST00125NY-D](https://openairdocs.org/stc/ST00125NY-D): This modification directs a change in the cabin seats and the cabin seating layout from a 62 tourist class seating configuration to a 65 tourist class seating configuration.. American Airlines Inc - [STC ST03001AT](https://openairdocs.org/stc/ST03001AT): Installation of an AAE, Ltd smoke detection and Halon fire suppression system into the lower baggage compartments of the aircraft to establish a Class C cargo compartment classification. The installation includes a control head installed in the aircraft cockpit for monitoring and operation of the system.. Advanced Aircraft Extinguishers (AAE) Ltd - [STC ST00526WI-D](https://openairdocs.org/stc/ST00526WI-D): Modification of Collins VHF COMM Receiver Installation. Rockwell Collins Inc - [STC ST02705AT](https://openairdocs.org/stc/ST02705AT): Installation of Goodrich Hella Aerospace Fixed Wingtip Navigation Lighting System in accordance with Goodrich Hella Aerospace Master Drawing List R-356-00 Rev. -, dated 28 November 2001 or later FAA approved revision.. BF Goodrich Aerospace - [STC ST01202WI-D](https://openairdocs.org/stc/ST01202WI-D): Modification of an existing FAA approved Collins TPR-720, TPR-900 or TPR-901 Mode S transponder installation in Part 25 Aircraft using Collins Drawing Index as listed on AML No. ST01202WI-D, latest FAA approved revision.. Rockwell Collins Inc All 104: https://openairdocs.org/tcds/A20EU/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.