# TCDS A-817: Fokker Services B.V. - Type: Type certificate data sheet - Status: Current - Holder: Fokker Services B.V. - Revision: 22 - Revised: June 26, 2017 - Product: Aircraft, Large Airplane - Certification basis: Part 25, CAR 10, CAR 4b - Data sheet PDF: https://openairdocs.org/files/sha256/5f/c7/5fc7bc638f07a7a685cc3d9c67746b2746fe49642e296a3c1550d089bb8a3921 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/FCCB210206CD6E688625814D00791AC5.0001 - Page: https://openairdocs.org/tcds/A-817 ## Models (8) As the data sheet lists them. - F27 Mark 500 - F27 Mark 100 - F27 Mark 700 - F27 Mark 200 - F27 Mark 400 - F27 Mark 600 - F27 Mark 050 - F27 Mark 300 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 Rev. No. 22 12 17 22 22 17 22 22 13 22 22 22 22 22 20 22 22 22 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-817 Revision 22 FOKKER F27 Mark 100 F27 Mark 200 F27 Mark 300 F27 Mark 400 F27 Mark 500 F27 Mark 600 F27 Mark 700 F27 Mark 050 June 26, 2017 TYPE CERTIFICATE DATA SHEET NO. A-817 This data sheet which is a part of Type Certificate No. A-817 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. Model F27 Mark 100, approved October 29, 1957, Mark 200, 300, 400, 600, and 700 approved May 25, 1965. F27 Mark 200 same as F-27 Mark 100 except for engine installation. F27 Mark 300 same as F-27 Mark 100 except for large forward cargo door and all-metal cargo floor in cabin. F27 Mark 400 same as F-27 Mark 200 except for large forward cargo door and all-metal cargo floor in cabin. F27 Mark 600 same as F-27 Mark 200 except for large forward cargo door. F27 Mark 700 same as F-27 Mark 100 except for large forward cargo door. Engines. F27 Mark 100, 300, and 700: 2 Rolls Royce Dart 511 or Dart 511-7E or Dart 514-7. Reduction gearing 0.086:1 F27 Mark 200, 400, and 600: 2 Rolls Royce Dart 528-7E, Dart 532-7, Dart 532-7R, Dart 535-7R, Dart 551-7R or Dart 552-7R, (See Note 3(b)). Reduction gearing 0.093:1 Engine Limits. Static Sea Level Ratings at ISA Shaft Horsepower (shp.) Jet Thrust (lb.) Engine Speed (rpm) Max. Permissible JPT/TGT (°C) Dart 511 Wet Takeoff (5 min.) 1570 365 14,500 595 Dry Takeoff 1535 355 14,500 580 Max. Continuous 1535 355 14,500 580 Starting (Momentary) - - - - - - - - - - - - 640 Dart 511-7E Wet Takeoff (5 min.) 1570 365 14,500 595 Dry Takeoff 1535 355 14,500 595 Max. Continuous 1535 355 14,500 625 Starting (Momentary) - - - - - - - - - - - - 640 A-817, Rev 22 2 Engine Limits (cont'd) Shaft Horsepower (shp.) Jet Thrust (lb.) Engine Speed (rpm) Max. Permissible JPT/TGT (°C) Dart 514-7 Wet Takeoff (5 min.) 1670 385 14,500 600 Dry Takeoff 1535 355 14,500 595 Max. Continuous 1535 355 14,500 650 Starting (Momentary) - - - - - - - - - - - - 640 Dart 528-7E Wet Takeoff (5 min.) 1870 495 15,000 860 Dry Takeoff 1835 485 15,000 810 Max. Continuous 1835 485 15,000 850 Starting (Momentary) - - - - - - - - - - - - 930 Dart 532-7 Wet Takeoff (5 min.) 1990 520 15,000 860 Dry Takeoff 1835 485 15,000 810 Max. Continuous 1835 485 15,000 850 Starting (Momentary) - - - - - - - - - - - - 930 Dart 532-7R Wet Takeoff (5 min.) 2080 520 15,000 905 Dry Takeoff 1835 485 15,000 810 Max. Continuous 1835 485 15,000 885 Starting (Momentary) - - - - - - - - - - - - 930 Dart 535-7R Wet Takeoff (5 min.) 2080 520 15,000 920 Dry Takeoff 1835 485 15,000 810 Max. Continuous 2030 495 15,000 920 Starting (Momentary) - - - - - - - - - - - - 930 Dart 551-7R Wet Takeoff (5 min.) 2136 457 15,000 940 Dry Takeoff 2164 455 15,000 910 Max. Continuous 2164 455 15,000 930 Starting (Momentary) - - - - - - - - - - - - 930 Dart 552-7R Wet Takeoff (5 min.) 2180 511 15,000 930 Dry Takeoff 2167 508 15,000 900 Max. Continuous 2167 508 15,000 920 Starting (Momentary) - - - - - - - - - - - - 930 NOTE: Dart 511/511-7E/514 temperatures are expressed in JPT, Dart 7 (520, 530 and 550 Series) in TGT. Oil Inlet Temperature Dart 511, Dart 532-7R 511-7E, 528-7E 535-7R 514-7 532-7 551-7R 552-7R Maximum 110oC 120oC 120oC Minimum for starting -30oC -30oC -30oC Minimum for opening-up -15oC -15oC -15oC Dart 514-7 Minimum for WET Take-off 40oC 40oC 50oC A-817, Rev 22 3 Propeller and Propeller Limits. Dart 511, 511-7E, 514-7: 2 Rotol Model (c) R 175/4-30-4/13E, with 4 RA.25899 blades each. Diameter 12.0 ft. (nominal) Minimum allowable for repairs 11'9.75". No further reduction permitted. Pitch setting at .7 radius Ground fine pitch 0o Flight fine pitch +20o48' Feathered +83o R.P.M. limit (max. 20 sec.) 17,000 Avoid all continuous operation below 7,000 r.p.m. Dart 528-7E, 532-7, 532-7R, 535-7R: 2 Dowty Rotol Model (c) R193/4-30-4/50 or 4/61 with 4 RA.25907 blades each or 4/63 with 4 RA.660208304 blades each or 4/65 with 4 RA.601023450 blades each. Diameter 11.5 ft. (nominal) Minimum allowable for repairs 11'4.35" Pitch setting at .7 radius Ground fine pitch 0o Flight fine pitch 20o Cruise pitch 32o Feathered 87o R.P.M. limit (max. 20 sec.) 17,000 Avoid all continuous operation below 7,000 r.p.m. Dart 551-7R, 552-7R: 2 Dowty Rotol Model (c) R193/4-30-4/65 with 4 RA.601023450 blades each. Diameter 11.5 ft (nominal) Minimum allowable for repairs 11'4.35" Pitch setting at 0.7 radius Ground fine pitch 0o Flight fine pitch 20o Cruise pitch 32o Feathered 87o R.P.M. limit (max. 20 sec.) 17,000 Avoid all continuous operation below 7,000 rpm. For the 551-7R engine all continuous operation between 13,000 and 13,400 rpm. should be avoided. A-817, Rev 22 4 C.G. Range. FWD AFT Weight (lb) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.) Takeoff and Landing 31,300 20.0 (360.28) 38.0 (378.52) (gear down) and below 35,700 25.0 (365.35) 38.0 (378.52) 37,500 25.6 (365.95) 38.0 (378.52) 39,500 26.2 (366.57) 38.0 (378.52) 40,500 26.5 (366.87) 38.0 (378.52) 42,000 27.0 (367.37) 38.0 (378.52) 43,500 27.3 (367.68) 38.0 (378.52) 45,000 27.7 (368.03) 38.0 (378.52) Enroute (gear up) 31,300 18.7 (358.95) 40.7 (381.26) and below 35,700 23.7 (364.03) 40.7 (381.26) 37,500 24.3 (364.64) 40.7 (381.26) 39,500 24.9 (365.24) 40.7 (381.26) 40,500 25.2 (365.55) 40.7 (381.26) 42,000 25.7 (366.05) 40.7 (381.26) 43,500 26.0 (366.36) 40.7 (381.26) 45,000 26.4 (366.76) 40.7 (381.26) The forward c.g. limit for weights between points shown shall be interpolated linearly except when modified in accordance with approved Fokker F27 Service Bulletin B-159 or in accordance with approved Fokker F27 Service Bulletin 51-30. The forward c.g. limit for weights between 31,300 lbs and 37,500 lbs, and between 31,300 lbs and 39,500 lbs, shall be interpreted linearly. Gear retraction moment is + 30,000 in. lb. Datum. The fuselage datum (Station Zero) is: for Mk 100, 200, 600 and 700 aircraft: 228.5 in. forward of the front leveling pin. For Mk 300 and 400 aircraft: 268.5 in. forward of the front leveling pin. M.A.C. 101.38 in. (L.E. of M.A.C. + 340.0 in.) Maximum Weights. Takeoff: 35,700 lb. 37,500 lb. When modified in accordance with approved Fokker F27 Service Bulletin D-16 and D-17. 39,000 lb. For Mk 100, 300 and 700 aircraft equipped with Dart 511 and 511-7E engines, when modified in accordance with approved Fokker F27 Service Bulletin D-16, D-17 and D-40. 40,500 lb. For Mk 100, 300 and 700 aircraft equipped with Dart 514-7 engines and modified in accordance with approved Fokker F27 Service Bulletins D-16, D-17, D-40 and D-64. 42,000 lb. For Mk 200, 400 and 600 aircraft when modified in accordance with approved Fokker F27 Service Bulletins D- 16, D-17 and D-41. 43,500 lb. For Mk 200, 400 and 600 aircraft equipped with Dart 532-7 engines and modified in accordance with approved Fokker F27 Service Bulletins B-158 and D-71. 45,000 lb. For Mk 200, 400 and 600 aircraft equipped with Dart 532-7, 532-7R and 535-7R, 551-7R and 552-7R engines and modified in accordance with approved Fokker F27 Service Bulletin 51-26. A-817, Rev 22 5 Maximum Weights (Cont'd). Landing: 34,000 lb. 37,500 lb. When modified in accordance with approved Fokker F27 Service Bulletins D-16 and D-17. 40,000 lb. When modified in accordance with approved Fokker F27 Service Bulletins D-16, D-17 and, D-41 (Mk 200, 400 and 600) or D-40 plus D-64 (Mk 100, 300 and 700), D-65 and B-148. 41,000 lb. For the Mk 200, 400 and 600 aircraft when modified in accordance with approved Fokker F27 Service Bulletin 54-32. 43,500 lb. For Mk 400 and 600 aircraft when modified in accordance with approved Fokker F27 Service Bulletins 51-31. Zero Fuel, Oil and Water/Methanol: 32,400 lb. 34,900 lb. For Mk 100, 300 and 700 aircraft with original small fuel tanks when modified in accordance with approved Fokker F27 Service Bulletins D-16 and D-17. 35,200 lb. For Mk 100, 300 and 700 aircraft with enlarged fuel tanks when modified in accordance with approved Fokker F27 Service Bulletins D-16 and D-17. 35,700 lb. For Mk 200, 400 and 600 aircraft, when modified in accordance with approved Fokker F27 Service Bulletins D- 16 and D-17. 37,500 lb. For Mk 100, 300, 700, 200, 400, and 600 aircraft, when modified in accordance with approved Fokker F27 Service Bulletin B-159. 39,500 lb. For Mk 200, 400 and 600 aircraft, when modified in accordance with approved Fokker F27 Service Bulletin 51-30. Maximum Baggage. Compartment Station (in.) Capacity (lb.) Max. Floor Loadng (Lb./ft2) C.G. (in.) Mk. 100, 200, Forward 161-230 2,620 135 199.1 Mk. 600, 700, (20" gangway) 161-263 4,000 135 217.6 without Mallison Aft. 647-691 1,120 100 669.3 floors Mk. 300, 400 (no gangway) 161-304 100 Mk. 600 & 700 304-446 15,980 140 406.4 with Mallison floors 446-691 Maximum Passengers. 48 (CAR 4b-362(c)) (see NOTE 4 regarding approved interior arrangements). II. Model F27 Mark 500 approved 21 May 1970. F27 Mark 500 same as Mark 200 or Mark 600 except for stretched fuselage. Engines. 2 Rolls Royce Dart 532-7, 532-7R, 535-7R, 551-7R or 552-7R. Reduction gearing 0.093:1 A-817, Rev 22 6 Engine Limits. Static Sea Level at ISA Shaft Horsepower (shp.) Jet Thrust (lb.) Engine Speed (rpm) Max. Permissible JPT/TGT (°C) Dart 532-7 Wet Takeoff (5 min.) 1990 520 15,000 835 Dry Takeoff 1835 485 15,000 795 Max. Continuous 1835 485 15,000 835 Starting (Momentary) - - - - - - - - - - - - 930 Dart 532-7R Wet Takeoff (5 min.) 2080 520 15,000 905 Dry Takeoff 1835 485 15,000 810 Max. Continuous 1835 485 15,000 885 Starting (Momentary) - - - - - - - - - - - - 930 Dart 535-7R Wet Takeoff (5 min.) 2080 520 15,000 920 Dry Takeoff 1835 485 15,000 810 Max. Continuous 2030 495 15,000 920 Starting (Momentary) - - - - - - - - - - - - 930 Dart 551-7R Wet Takeoff (5 min.) 2136 457 15,000 940 Dry Takeoff 2164 455 15,000 910 Max. Continuous 2164 455 15,000 930 Starting (Momentary) - - - - - - - - - - - - 930 Dart 552-7R Wet Takeoff (5 min.) 2180 511 15,000 930 Dry Takeoff 2167 508 15,000 900 Max. Continuous 2167 508 15,000 920 Starting (Momentary) - - - - - - - - - - - - 930 Oil Inlet Temperature Dart 532-7 Dart 532-7R, 535-7R, 551-7R, 552-7R Maximum 120° C 120° C Minimum for starting -30° C -30° C Minimum for opening up -15° C -15° C Minimum for WET takeoff 40° C 50° C Propeller and Propeller Limits. DART 532-7, DART 532-7R and DART 535-7R: 2 Dowty Rotol Model (c) R193/4/30-4/50 or 4/61 with 4 RA.25907 blades each or 4/63 with 4RA660208304 or 4/65 with 4RA601023450 blades each. Diameter 11.5 ft. (nominal) Minimum allowable for repairs 11'4.35". Pitch settings at .7 radius Ground fine pitch 0o Flight fine pitch 20o Cruise pitch 32o Feathered 87o R.P.M. Limit (max. 20 sec.) 17,000 Avoid all continuous operation below 7,000 r.p.m. A-817, Rev 22 7 Propeller and Propeller Limits. (cont'd) DART 551-7R, 552-7R: 2 Dowty Rotol Model (c) R193/4-30-4/65 with 4 RA.601023450 blades each. Diameter 11.5 ft. (nominal) Minimum allowable for repairs 11'4.35" Pitch setting at 0.7 radius Ground fine pitch 0o Flight fine pitch 20o Cruise pitch 32o Feathered 87o R.P.M. limit (max. 20 sec.) 17,000 Avoid all continuous operation below 7,000 r.p.m. For the 551-7R engine all continuous operation between 13,000 and 13,400 rpm. should be avoided. C.G. Range. FWD AFT Weight (lb) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.) Takeoff and Landing 31,000 20.0 395.68 (gear down) and below 38,500 25.9 401.64 38.0 431.92 41,000 26.5 402.47 43,500 27.2 402.88 45,000 27.5 403.31 45,900 27.7 403.48 35.0 410.88 Enroute (gear up) 31,000 18.7 394.36 and below 38,500 24.6 400.34 40.7 416.66 41,000 25.4 401.15 43,500 25.8 401.56 45,000 26.2 402.00 Linear variation of forward C.G. limit between points shown except when modified in accordance with RLD/CAA-NL-approved Fokker F27 Service Bulletin 51-25; linear variation between 31,300 lb. and 39,500 lb. Gear retraction moment change: +30,000 in.lb. Datum. Fuselage datum (Station Zero): 340.4 in. forward of front leveling pin for versions with enlarged cargo door; 269.4 in. for versions with small cargo door. M.A.C. 101.38 in. (L.E. of M.A.C. + 375.4 in.) Maximum Weights. Takeoff: 43,500 lb. 45,000 lb. When modified in accordance with approved Fokker F27 Service Bulletin 53-89. 45,900 lb. When modified in accordance with approved Fokker F27 Service Bulletin 51-35. Landing: 41,000 lb. 42,000 lb. When modified in accordance with approved Fokker F27 Service Bulletin 51-25. 43,500 lb. When modified in accordance with approved Fokker F27 Service Bulletin 51-32. A-817, Rev 22 8 Maximum Weights (Cont'd). Zero Fuel, Oil and Water/Methanol: 38,500 lb. 39,500 lb. When modified in accordance with approved Fokker F27 Service Bulletin 51-25. 40,200 lb. When modified in accordance with approved Fokker F27 Service Bulletin 51-35. Maximum Passengers. 59 (CAR 4B.362(c)) (See NOTE 4 regarding approved interior arrangements). Maximum Baggage. Compartment Station (in.) Capacity (lb.) Maximum Floor Loading (lb/ft2) C.G. (in.) Forward 161-230 2,620 135 199.1 (20" gangway) 161-263 3,400 135 217.6 Aft 647-691 1,120 100 728.4 III. Model F27 Mark 050 approved February 8, 1989. The F27 Mark 050 same as Mark 500 except for the installation of two new technology Pratt & Whitney Canada PW125B engines, Dowty Rotol (c) R 352/6-123F/1 composite 6-bladed propellers, state of the art systems and cockpit instrumentation, electronic engine and propeller controls, increased use of composite structure, four type I doors i.l.o. two type I doors and two type IV exists, double the number of windows, switch from pneumatic systems to hydraulic systems, an electronic flight instrument system (EFIS) and integrated warning system. Engine. Two (2) Pratt and Whitney PW125B turboprop engines. Reduction gearing 0.060: 1. (Ref. U.S. T.C. No. E20NE) Fuel Specification. Eligible engine fuels and additives are listed in the approved Airplane Flight Manual. Oil Specification. Eligible engine oils as listed in the approved Airplane Flight Manual. (Engine and gearbox) Engine and Propeller Limits CONDITION TIME TORQUE (%) ITT (deg C) RPM (%) NH NL NP MAX TO 5 min. 102 800 102 103 100 MAX TO* 5 min. 96 800 102 103 106 NORMAL TO 5 min. 92 765 102 103 100 MAX CONT unl 87.5 800 102 103 100 MAX CONT* unl 82.5 800 102 103 106 MIN GND IDLE - - - 66 - 60 STARTING 5 sec - 950 - - - 20 sec - 840 - - - TRANSIENT 15 sec - - - - 115 20 sec 115 840 102 103 - 5 min 105 - - - - * Operation on overspeed governor A-817, Rev 22 9 Propeller. o Type no. 2 Dowty Rotol propellers, Model: (c) R352/6-123-F/1 or (c) R352/6-123-F/2 (Ref. U.S. TC No. P16NE). o Diameter 3.65 m (144 inch). o No. of blades 6 - clock wise rotation (viewed from rear of propeller). o Spinner type (c) SB 20/6/1. o Blades Composite glass and carbon reinforced plastic construction, polyrethane coated and fitted with nickel leading edge sheets for erosion protection and, with electric de-icing overshoe. o Pitch Settings Pitch setting at .7 radius. (Nominal) Feathered pitch +82.6o Flight fine pitch +15o Low pitch (pure beta) +10o Ground fine pitch -2o Max reverse pitch -17o To avoid high propeller stresses, stabilized ground operation in the propeller rpm of 65 percent to 90 percent NP is not permitted with the airplane static. Excluded from this limitation is the use of reverse during ground maneuvering in engine EC operating mode. APU (Optional). Sundstrand, SPS T62T-46-C1 (ground use only). Airspeed Limits. ` All speeds mentioned in this section are indicated airspeeds (IAS) Vmo Maximum operation list speed. Up to 21,000 ft altitude : 224 kts. Above 21,000 ft altitude : Vmo decreases linearly to 206 kts at 25,000 ft altitude. VA Maximum design maneuvering speed : 175 kts. Full application of rudder and aileron controls, as well as maneuver that involve angle of attack near the stall, should be confined to speeds below VA. VRA Rough air speed : 165 kts. VFE Maximum flap extend speed : Flap Position 5 : 180 kts 10 : 180 " 15 : 180 " 20 : 160 " 25 : 160 " 35 : 140 " VLO = VLE Maximum Landing gear extended and operating speed : 170 kts. C.G. Range. WEIGHT FWD AFT (lb) (kg) % MAC Sta (in) % MAC Sta (in) gear down 45900 20820 25.5 401.25 38.0 413.92 45590 20680 - - 40.0 415.95 37480 17000 - - 40.0 415.95 31970 14500 - - 38.0 413.92 31000 14200 20.0 395.68 38.0 413.92 and lower gear up 45900 20820 24.4 400.14 40.7 416.66 31310 14200 18.9 394.56 40.7 416.66 and lower The C. G. limits for weights between the given figures shall be interpolated linearly. Gear retraction moment change: 243.4 kgm (21129.3 inch pounds). A-817, Rev 22 10 When modified in accordance with Fokker Modification ECR 78547: Landing Gear Extended Landing Gear Retracted Weight Forward Aft Forward Aft lb kg (% MAC) (% MAC) (% MAC) (% MAC) 45,900 20.820 25.5 40.0 24.0 43.2 42,900 19.500 - 40.0 19.8 43.2 37,480 17.000 - 40.0 - 43.2 31,970 14.500 - 38.0 - - 31,300 14.200 20.0 38.0 13.0 - 27,118 12.300 20.0 38.0 13.0 41.2 and lower The C of G limits for weights between the given figures shall be interpolated linearly. Gear retraction moment change: 243.4 kgm (21129.3 inch pounds). When modified in accordance with Fokker Modifications ECR 78547 and 50203: Landing Gear Extended Landing Gear Retracted Weight Forward Aft Forward Aft lb kg (% MAC) (% MAC) (% MAC) (% MAC) 45,900 20.820 25.5 40.0 24.0 43.2 43,500 19.730 24.6 40.0 - 43.2 42,990 19.500 - 40.0 19.8 43.2 41,000 18.600 20.7 40.0 - 43.2 39,680 18.000 - 40.0 16.0 43.2 37,480 17.000 17.0 40.0 - 43.2 33,290 15.100 14.0 - - - 31,970 14.500 14.0 38.0 - - 30,865 14.000 14.0 38.0 10.0 - 27,118 12.300 14.0 38.0 10.0 41.2 and lower For C of G limits for weights between the given figures shall be interpolated linearly. Gear retraction moment change: 243.4 kgm (21129.3 inch pounds). Datum. The datum referred to is defined as the Fuselage Datum (Station Zero), which is 7535 mm (296.7 inch) forward of the front leveling pin. M.A.C. The Mean Aerodynamic Chord is 2575 mm (101.38 inch) aft of datum. Leveling Means. Leveling holes are provided to accommodate leveling equipment. They are located on the left hand side of the fuselage. Maximum Weights. Maximum Taxi Weight : 20,865 kg (45,000 lbs) Maximum Take-off Weight : 20,820 kg (45,900 lbs) Maximum Landing Weight : 19,730 kg (43,500 lbs) Maximum Zero Fuel Weight : 18,600 kg (41,000 lbs) Maximum Passengers. 62 (See note 4(c) regarding approved interior arrangement). A-817, Rev 22 11 Maximum Baggage. Compartment Station (in.) Capacity (lb) C.G. (in.) forw. RH 179.1 - 242.3 1157 210.7 179.1 - 264.8 1642 222.0 aft. 689.0 - aft 2205 719.3* press bulkhead (inc. max galley weight) * Freight only, based on 1598 lb freight. Note: As the cargo holds configuration is dependent on customer requirements reference is made to the report "basic weight and balance information," specific to each separate aeroplane. Fuel Capacity. Total 5136 Liter (1357 U.S. Gallon) of usable fuel in two wing tanks of 2518 Liter (665 U.S. Gallon) each and in two collector tanks of 50 Liter (13 U.S. Gallon) each. See NOTE 1 for data on system fuel and oil. Oil Capacity. See FAA engine TC Data Sheet No. E20NE (exl. oil cooling system) Liter U.S. Gallon Usable 8.0 2.0 Total 19.3 5.72 Control Surface Movements Elevator Up 25° Down 22° Elevator trim tab Up 19° Down 27° Rudder Left 20° Right 20° Rudder trim tab Left 17° Right 17° Aileron (with spring tab Up 33° Right 22° neutral) Aileron spring tabs Up 13° Down 13° Aileron balance tabs 19° tab t.e. down 11° tab t.e. up Aileron trim tab 17° Down 17° (right outer tab) 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. - Safe Life Items (SLI), Airworthiness Limitation Items (ALI) and Certification Maintenance Requirements (CMR) , all approved, as referenced in Section 06, Appendix 1 of the MRB document - Structural Repair Manual - MRB document - Maintenance Planning Document - Service Bulletins - Airworthiness Recommendations Catalog (ARC) Service bulletins, 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 the 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. A-817, Rev 22 12 For approvals made before September 28, 2003 the statement “The technical information contained in this document has been approved under the authority of JAA Design Organization Approval no. RLD.JA.001” may have been used and are also considered FAA approved. DATA PERTINENT TO ALL MODELS F27 Mark 100, 200, 300, 400, 500, 600 and 700. Fuel. Eligible engine fuels and additives are listed in Rolls Royce Operating Instructions, Document F-Da6-FoF or F-Da7-FoF. Fuel Capacity. 972 U.S. gal. (total) of usable fuel in two wing tanks of 472.5 U.S. gal. each and in two collector tanks of 13.4 U.S. gal. each. 1357 U.S. gal. (total) of usable fuel in two wing tanks of 665 U.S. gal. each and two collector tanks of 13.4 U.S. gal. each, when modified in accordance with F27 Modification Bulletin 2. See NOTE 1 (b) for unusable fuel. For aircraft equipped with inboard fuel tanks: 605 U.S. gal. (total) of usable fuel in two inboard tanks. Water/Methanol Capacity. Water/Methanol Mixture: Rolls-Royce Specification AEP-1-W/M latest issue. 80 U.S. Gal. (total) in two nacelle tanks of 40 gal. each. Oil (Engine and Gearbox). Eligible engine oils are listed in Rolls Royce Operating Instructions, Document F-Da6- Fof or F-Da7-FoF. Oil Capacity. 8 U.S. Gal. (total) in two engine tanks of 4 gal. each. (See NOTE 1 (b) for system oil). Airspeed Limits. Knots (IAS) (IAS) VNE (Never Exceed) 0-20,000 ft. 254 259 20,000-25,000 ft. 234 238 VMO (Max. Operation) 0-20,000 ft. 223 238 above 20,000 ft. MO decreases 4.5 ft. per 1,000 ft. 25,000 ft. 204.5 204 VA (Maneuvering) MTOW 42,000 166 169 MTOW 43,500 169 172 MTOW 45,000 172 175 MTOW 45,900 174 176 VFE (Flap extended) 0 - 16.5° 138 140 16.5° - 40.0° 125 126 VFE (Flap extended), when modified in accordance with RLD/CAA-NL-approved Fokker F27 Service Bulletin B182. 0 - 40.0° 144 145 VFE (Flap extended), when modified in accordance with RLD/CAA-NL-approved Fokker F27 Service Bulletin 11-4: 0 - 16.5° 177 180 16.5° - 26.5° 157 160 26.5° - 40.5° 144 145 VLO (Landing gear operation) 168 170 VLE (Landing gear extended) 168 170 VMC (Minimum control) with 16°.5 takeoff flaps at S.L. Stand Cond. RR Dart Mk 528-7E 78 78 RR Dart Mk 532-/535- engines 80 80 RR Dart Mk 551-7R/552-7R 81 81 Maximum airspeed for extending retractable type landing lights 168 170 A-817, Rev 22 13 Leveling Means. Pins for installing leveling instrument are located on the left hand side of the fuselage. Control Surface Elevator Up 25o Down 22o Movements. Elevator Trim Tab (Left) Up 22.5o Down 22.5o Rudder Right 20o Left 20o Rudder Balance Tab Right 3o Left 3o Rudder Trim Tab Right 10o Left 10o Aileron (with spring tab neutral) Up 33o Down 22o Aileron Spring Tabs (inner tabs) Up 13o Down 13o Aileron Balance Tabs (outer tabs) Up 11o Down 16.5o Aileron Trim Tab (right outer tab) Up 15o Down 15o 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: (a) Maintenance Manual (b) Overhaul Manual (c) Structural Repair Manual (d) Structural Inspection Program (SIP) Document (e) Airworthiness Recommendations Catalog (ARC) (f) Corrosion Control Program (CCP) Document (g) Service Bulletins (g) Inspection Guide, Maintenance Schedule, Maintenance Data or Customer Maintenance Program as applicable to the specific aircraft serial number, as published and specified by the TC-Holder (ref. Service Letter 330). 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 the 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 JAA Design Organization Approval no. RLD.JA.001” may have been used and are also considered FAA approved. DATA PERTINENT TO ALL MODELS Certification Basis for Models F27 Mark 100, 200, 300, 400, 500, 600 and 700 CAR 10, dated March 1955, CAA (Import) Type Certificate no. 817 issued 19 October 1957, for Fokker F27 Friendship. Original Type Certificate superseded and replaced by FAA Type Certificate no. 817 dated 25 May 1965 to re-identify basic F27 as F27 Mark 100 and add F27 Marks 200, 300, 400, 600 and 700. Type Certificate no. 817 issued 25 May 1965 superseded and replaced by FAA Type Certificate no. 817, dated 21 May 1970 to add F27 Mark 500. Date of application for Type Certificate; 9 November 1954. A-817, Rev 22 14 Type approval basis for all Marks, certified by Netherlands Government Rijksluchtvaartdienst (RLD/CAA-NL) is: U.S. CAR Part 4b effective 31 December 1953, including Amendment 4b-1, Amendment 46-2 items 1 and 48, Amendment 46-3 items 21 through 33 and 39, Amendment 4b-7, Amendment 4b-8 Items 9, 21 and 22, SR- 422B effective 9 July 1959, Section 4T.110 through 4T.123 and 4T.743, and SR 450A effective 31 August 1962 including Amendments 1 and 2, and with the Special Conditions notified to the Government of the Netherlands by Government of the United States of America. Compliance has been shown with FAR Part 25, Amendments 25-15, 25-17 and 25-20 for the F27 Mark 500. Compliance has been shown with the following optional requirements: Ice Protection CAR 4b.640. In addition compliance has been shown with: • FAR Part 25, Amendments 25-15, 25-17 and 25-20 for the F27 Mark 200 and 600, Serial Nos. 10446 and up, with the incorporation of approved Fokker Service Bulletin 25-27. • FAR 25.1001 Amendment 25-18 for F27 airplanes equipped with Dart 528-7E, 532-7, 532-7R, 535-7R, 551-7R and 552-7R engines. • FAR 25 Section 812(e) as amended by Amendment 25-46, according to approved Fokker F27 Service Bulletin 33-28. • FAR 25 Section 785(g) and (h) as amended by Amendment 25-51, according to approved Fokker F27 Service Bulletins 25-49, 25-50, 25-51, 25-54 and 25-56. • FAR 25 Amendments 25-22 and 25-24 if third attitude instrument SFENA type 705-15V9, or type 705-15V10 is installed. Compliance has been shown with FAR 36 • Amendment 36-1 for: RR Dart 532-7 Mk's All MTOW 45,000 lbs MLW 42,000 lbs or 43,500 lbs RR Dart 532-7R Mk's All MTOW 45,000 lbs MLW 42,000 lbs RR Dart 535-7R Mk's All MTOW 45,000 lbs MLW 42,000 lbs • Up to and including Amendment 36-7 for: RR Dart 532-7R Mk's All MTOW 45,000 lbs MLW 43,500 lbs RR Dart 535-7R Mk's All MTOW 45,000 lbs MLW 43,500 lbs • Up to and including Amendment 36-12: When modified in accordance with Fokker Service Bulletin F27/71-28: RR Dart 532-7R Mk's All MTOW 45,000 lbs 535-7R MLW 41,000, 42,000 or 43,500 lbs. 551-7R 552-7R RR Dart 532-7R Mk's All MTOW 45,900 lbs 535-7R MLW 41,000 or 43,500 lbs 551-7R 552-7R A-817, Rev 22 15 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. 14 CFR part 26 is not applicable to the Mk 100. Exemption No. 9804 has been issued for the Fokker F27 Mk 200 through 700 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 (6) “CAA-NL (formerly RLD) originally type certificated this aircraft under its type certificate Number A22F. The FAA validated this product under U.S. Type Certificate Number A-817. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of CAA-NL.” Certification Basis for Model F27 Mark 050 1. Part 25 of the FAR dated February 1, 1965, as amended by Amendments 25-1 through 25-56, 25-58, 25-29, 25-60, §25.904 as amended by Amendment 25-62 except for the following paragraphs which will be certified to earlier amendments as noted: §25.109 25-41 25.631 Not applicable, §25.631 added to Amendment 25-23 25.671(c)(3) 25-22 25.701(d) 25-22 25.1309 25-22 All systems comply with §25.1309 as amended by Amendment 25-56 except for the following which comply with Amendment 25-22: - Communication Systems - Flight Control Systems - Fuel and Fuel Shut-Off System - Stall Warning System 25.571(e)(2) Not applicable, 25.571(e)(2) added at Amendment 25-45 25.1305(e)(3) Not applicable, 25.1305(e)(3) added at Amendment 25-23 2. Part 36 as amended by Amendment 36-16. 3. SFAR 27 as amended by Amendment 27-6. 4. Special Conditions No. 25-ANM-11 issued for the Automatic Takeoff Power Control System (ATPCS), i.e., §25.904 as amended by Amendment 25-62. 5. Special Conditions No. 25-ANM-13 issued on October 19, 1987, for Lightning Protection Requirements for Electronic Devices/Engine and Prop Controls. 6. Findings of Equivalent Safety. §25.729(e)(2) Landing Gear Warning System Throttles 25.807(d) Ditching Emergency Exits 25.1416(c) Pneumatic De-Icer System Indication 7. Exemptions: None 8. Certification with the ditching provisions of FAR 25.801 has not been requested by Fokker Aircraft, BV. If extende d overwater operation is to be approved, compliance with FAR 25.801 must be demonstrated. 9. Compliance with the optional requirements of FAR 25.1419, Icing Protection has been established. In addition it has been shown that: a) The optional APU complies with FAR 25 Amdt. 25-56. b) The aircraft complies with FAR 25.791(d) and (c) as amended by Amdt. 25-72. 10. 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 applicable sections. A-817, Rev 22 16 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. “CAA-NL (formerly RLD) originally type certificated this aircraft under its type certificate Number T-050-87. The FAA validated this product under U.S. Type Certificate Number A-817. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of CAA-NL.” Maximum Operating Altitude. 25,000 ft. Minimum Flight Crew. 2 (pilot and co-pilot) Serial Nos. Eligible. The Netherlands Certificate of Airworthiness endorsed as noted under Import Requirements 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 CAA-NL 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. A-817 and to be in a condition for safe operation.” In order for the FAA to determine that a Fokker F27 Mark 050 aircraft is in a condition for safe operation under the provisions of 14 CFR 21.183, the FAA certificating inspector or other authorized person must contact the Manager, International Branch, ANM-116, FAA Transport Airplane Directorate; 1601 Lind Avenue Southwest; Renton, Washington 98055; telephone (425) 227-1263; fax (425) 227-1149, prior to issuance of the U.S. airworthiness certificate to obtain the FAA Required Airworthiness Action List (RAAL) for the F27 Mark 050. After the first airplane is imported to the U.S. the RAAL will be finalized and published in the TCDS. When the TCDS is amended to include the RAAL, a notice will be published in the Federal Register, to inform the public of thi s amendment. The RAAL contains a list of type design modifications and inspections that have been determined by the European Aviation Safety Agency (EASA), which is the state of design authority for the Fokker F27 Mark 050, to be required to correct unsafe conditions discovered on the original type design of the F27 Mark 050. EASA has issued Airworthiness Directives that require the accomplishment of these modifications and inspections to correct the identified unsafe conditions, and has advised the FA A of this mandatory continuing airworthiness information (MCAI). Based on this MCAI the FAA has determined that the airworthiness actions identified in the EASA ADs listed in Model F27 Mark 050 RAAL are required in the interest of safety and are necessary for this airplane to be in a condition for safe operation. Prior to issuance of a Standard Airworthiness Certificate on any Fokker F27 Mark 050 model aircraft, all airworthiness actions listed in the Model F27 Mark 050 RAAL must be accomplished in accordance with the compliance times listed in each MCAI, except as noted in the RAAL. The MCAI listed in the RAAL are airworthiness limitations in addition to those listed in note 3 of this TCDS, and must be included in the operator’s airplane maintenance or inspection program. All inspections or modifications, required by the EASA MCAI, that have surpassed the initial compliance time, must be accomplished prior to issuance of the Standard Airworthiness Certificate. Any deviation from the requirements of the MCAIs, listed in the RAAL, must be approved by the Manager, International Branch, ANM-116, FAA Transport Airplane Directorate. A Notice of Policy Statement announcing the FAA’s policy with respect to foreign MCAI, when no aircraft of the affected design are currently registered in the U.S. was published in the Federal Register on May 1, 1998, docket 98-11648. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States. Equipment. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The approved Airplane Flight Manual version issued for the applicable airplane serial number. A-817, Rev 22 17 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 original certification. (b) For F27 Marks 100 thru 700, System Fuel which must be included in the empty weight, is the amount of fuel required to fill both system, including the cross-feed, up to the level of the booster pump inlets in collector tanks unusable but drainable fuel in the main tanks (6.5 U.S. gal. total). The total amount of "System fuel" is 9.95 U.S. gal. For aircraft equipped with inboard fuel tanks the following amount of fuel must be added to the "System Fuel" mentioned above: 0.79 U.S. gal. trapped fuel plus 11.9 U.S. gal. unusable but drainable fuel in the inboard tanks. Therefore, for aircraft equipped with inboard fuel tanks the total amount of "System Fuel" is 22.64 U.S. gal. Systems oil is that amount of oil normally trapped in the propellers plus the amount normally trapped in the engines after oil drainage. The amount of system oil is as follows: 2.4 U.S. gal. (total) contained in engines 2.0 U.S. gal. (total) contained in propellers (c) For the F27 Mark 050 System Fuel, which must be included in the empty weight, is the amount of fuel required to fill both systems including the crossfeed, up to the level of the booster pump inlets in the collector tanks (20.2 liters, 5.34 U.S. gal.) plus the trapped fuel in the main tanks (24.0 liters, 6.34 U.S. gal.). The total amount of "System Fuel" is 44.2 liters, 11.68 U.S. gal.). NOTE 2. For F27 Mark 100 through 700 the following placard must be displayed in the location indicated: On the lavatory door leading to a floor level exit: "During take-off and landing this door must be open". For Fokker F27 Mark 050, airplane operation must be in accordance with the approved AFM. All placards required in either the approved AFM or the Certification Basis must be installed in the airplane. NOTE 3. (a) Eligibility for Alternate Engine Installation: F27 Mark 100, 300, and 700 (basic with Dart 511 engines) are eligible for the: Dart 511-7E Installation only when modified in accordance with approved Fokker F27 Service Bulletin N5. and for the Dart 514-7 installation when further modified in accordance with approved Fokker F27 Service Bulletin E23, N21 and H29. F27 Mark 200, 400 and 600 are eligible for the: Dart 528-7E installation only when modified in accordance with approved Fokker F27 Service Bulletin N11. and for the Dart 532-7 Installation when further modified in accordance with approved Fokker F27 Service Bulletin E29 and 1129. and for the Dart 532-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-23. and for the Dart 535-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-30. A-817, Rev 22 18 and for the Dart 551-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-34. F27 Mark 500 (basic with Dart 532-7 engine) is eligible for the: Dart 532-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-23, and for the Dart 532-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-30, and for the Dart 551-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-34, and for the Dart 552-7R installation when further modified in accordance with approved Fokker F27 Service Bulletin 71-42. (b) The RR Dart 528 engine is no longer in service and was deleted from TCDS E-297 on September 9, 1980. (c) F27 Mk050 (basic with PW125B engine) is eligible for the PW127B installation. NOTE 4. (a) For the F27 Mark 100 thru 700 approved interior lay-out and maximum passenger capacity reference Fokker Drawing 27.1-9000. (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. (c) For the F27 Mark 050 approved interior lay-out and maximum passenger capacity reference Fokker Drawing F9004-000. NOTE 5. For the F27 Mark 050 systems and powerplant certification maintenance requirements are included in the approved Chapter 05-10 of the Maintenance Manual. Any changes to these requirements must be shown to meet FAR 25 and must be approved by EASA and FAA. NOTE 6 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 (128, first 50, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2022-15-08](https://openairdocs.org/ad/2022-15-08): Information systems · Airbus A318-111, A318-112, A319-111 and 49 more. Effective Aug 12, 2022 - [AD 2019-03-16](https://openairdocs.org/ad/2019-03-16): Main landing gear · Fokker Services B.V. F27 Mark 100, F27 Mark 200, F27 Mark 300 and 4 more. Effective Apr 8, 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 2017-24-04](https://openairdocs.org/ad/2017-24-04): Placards and markings · Fokker Services B.V. F27 Mark 050, F27 Mark 100, F27 Mark 200 and 5 more. Effective Dec 12, 2017 - [AD 2016-12-12](https://openairdocs.org/ad/2016-12-12): Fuel · Fokker Services B.V. F27 Mark 050, F27 Mark 200, F27 Mark 300 and 4 more. Effective Jul 22, 2016 - [AD 2016-04-22](https://openairdocs.org/ad/2016-04-22): Fuel · Fokker Services B.V. F27 Mark 200, F27 Mark 300, F27 Mark 400 and 3 more. Effective Apr 4, 2016 - [AD 2015-21-05](https://openairdocs.org/ad/2015-21-05): Fuel · Fokker Services B.V. F27 Mark 200, F27 Mark 300, F27 Mark 400 and 3 more. Effective Nov 30, 2015 - [AD 2015-16-04](https://openairdocs.org/ad/2015-16-04): Fire Protection · Airbus Defense and Space C-212-CB, C-212-CC, C-212-CD and 23 more. Effective Sep 15, 2015 - [AD 2013-17-06](https://openairdocs.org/ad/2013-17-06): Electric power · Fokker Services B.V. F.28 Mark 0070, F.28 Mark 0100 and F27 Mark 050. Effective Oct 18, 2013 - [AD 2012-07-05](https://openairdocs.org/ad/2012-07-05): Fuselage · Fokker Services F27 Mark 050. Effective Apr 25, 2012 - [AD 2012-03-03](https://openairdocs.org/ad/2012-03-03): Lights · Fokker Services F.28 Mark 0070, F.28 Mark 0100 and F27 Mark 050. Effective Apr 4, 2012 - [AD 2011-21-08](https://openairdocs.org/ad/2011-21-08): Equipment/Furnishings · ATR - GIE Avions de Transport Régional ATR42-200, ATR42-300, ATR42-320 and 202 more. Effective Nov 23, 2011 - [AD 2011-21-01](https://openairdocs.org/ad/2011-21-01): Fuel · Fokker Services F.28 Mark 0070, F.28 Mark 0100, F.28 Mark 1000 and 10 more. Effective Nov 16, 2011 - [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011 - [AD 2011-07-12](https://openairdocs.org/ad/2011-07-12): Fuel · Fokker Services F27 Mark 050. Effective Apr 28, 2011 - [AD 2011-08-02](https://openairdocs.org/ad/2011-08-02): Fuel · Fokker Services F27 Mark 050. Effective Apr 28, 2011 - [AD 2011-01-09](https://openairdocs.org/ad/2011-01-09): Oxygen · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 290 more. Effective Feb 9, 2011 - [AD 2010-13-02](https://openairdocs.org/ad/2010-13-02): Landing gear · Fokker Services F27 Mark 500 and F27 Mark 600. Effective Jul 8, 2010 - [AD 2009-18-05](https://openairdocs.org/ad/2009-18-05): Electrical power · Fokker Services F27 Mark 050 and F.28 Mark 0100. Effective Oct 1, 2009 - [AD 2009-16-05](https://openairdocs.org/ad/2009-16-05): Flight Controls. · Fokker Services F27 Mark 050. Effective Aug 20, 2009 - [AD 2009-06-15](https://openairdocs.org/ad/2009-06-15): Engine cowling · Fokker Services F27 Mark 050. Effective Apr 8, 2009 - [AD 2009-06-14](https://openairdocs.org/ad/2009-06-14): Lockwire on the two lockbolts that hold the sliding member end stop · Fokker Services F27 Mark 050. Effective Mar 31, 2009 - [AD 2008-13-01](https://openairdocs.org/ad/2008-13-01): Engine mounting frames · Fokker Services F27 Mark 050. Effective Aug 1, 2008 - [AD 2008-08-05](https://openairdocs.org/ad/2008-08-05): Passenger Serivce Units (PSU) · Fokker Services F27 Mark 050 and F.28 Mark 0100. Effective May 19, 2008 - [AD 2008-03-21](https://openairdocs.org/ad/2008-03-21): Non-destructive testing manual · Fokker Services F27 Mark 050. Effective Feb 26, 2008 - [AD 2007-25-04](https://openairdocs.org/ad/2007-25-04): Engine mount frames · Fokker Services F27 Mark 050. Effective Dec 18, 2007 - [AD 2007-16-11](https://openairdocs.org/ad/2007-16-11): Minnesota Mining and Manufacture Co. (3M) 1300L adhesive · Fokker Services F27 Mark 050. Effective Aug 24, 2007 - [AD 2007-02-20](https://openairdocs.org/ad/2007-02-20): Rope assemblies in the flight compartment · Fokker Services F27 Mark 050, F.28 Mark 0070 and F.28 Mark 0100. Effective Mar 2, 2007 - [AD 2006-26-05](https://openairdocs.org/ad/2006-26-05): Use of continuous ignition, fuel filter heating, and resetting circuit breakers · Fokker Services F27 Mark 100, F27 Mark 200, F27 Mark 300 and 4 more. Effective Jan 31, 2007 - [AD 2006-25-06](https://openairdocs.org/ad/2006-25-06): Main landing gear (MLG) drag stay units (DSUs) · Fokker Services F27 Mark 500. Effective Jan 16, 2007 - [AD 2006-17-09](https://openairdocs.org/ad/2006-17-09): Leading edge sections of the elevators to detect loose leading edges · Fokker Services F27 Mark 050. Effective Sep 6, 2006 - [AD 2005-25-06](https://openairdocs.org/ad/2005-25-06): Leading edges of the elevators, rudder, and ailerons · Fokker Services F27 Mark 050. Effective Dec 27, 2005 - [AD 2005-23-11](https://openairdocs.org/ad/2005-23-11): Compressor impeller assemblies · BAE Systems Avro 146-RJ100A, Avro 146-RJ70A, Avro 146-RJ85A and 5 more. Effective Dec 14, 2005 - [AD 2005-23-18](https://openairdocs.org/ad/2005-23-18): Bleed air supply ducts · Fokker Services F27 Mark 050. Effective Dec 1, 2005 - [AD 2005-20-26](https://openairdocs.org/ad/2005-20-26): Seat attachments. · Aviointeriors Seats, F27 Mark 050, F27 Mark 500 and 1 more. Effective Nov 16, 2005 - [AD 2005-18-19](https://openairdocs.org/ad/2005-18-19): Fuel tank isolation valves · Fokker Services F27 Mark 200, F27 Mark 400, F27 Mark 500 and 1 more. Effective Oct 14, 2005 - [AD 2005-07-27](https://openairdocs.org/ad/2005-07-27): Seat central crossmember · Aviointeriors Seats, F27 Mark 050, F27 Mark 500 and 1 more. Effective May 16, 2005 - [AD 2004-22-09](https://openairdocs.org/ad/2004-22-09): Aileron spring tab balance unit · Fokker Services F27 Mark 100, F27 Mark 200, F27 Mark 300 and 4 more. Effective Dec 7, 2004 - [AD 2004-22-01](https://openairdocs.org/ad/2004-22-01): Cargo restraint strap assemblies · Cargo restraint straps (Airline Container Manufacturing STC ST01004NY). Effective Dec 1, 2004 - [AD 2004-15-17](https://openairdocs.org/ad/2004-15-17): Engine Mounting Frames, Brace Struts, and Attachment Fittings · Fokker Services F27 Mark 100, F27 Mark 200, F27 Mark 300 and 4 more. Effective Sep 3, 2004 - [AD 2004-09-23](https://openairdocs.org/ad/2004-09-23): Control Panel of Direct Current (DC) Generator · Fokker Services F27 Mark 100, F27 Mark 200, F27 Mark 300 and 4 more. Effective Jun 9, 2004 - [AD 2002-04-03](https://openairdocs.org/ad/2002-04-03): Structural Provisions for the Global Positioning System (GPS) Antenna · Fokker Services F27 Mark 050. Effective Mar 8, 2002 - [AD 2001-18-03](https://openairdocs.org/ad/2001-18-03): Fuel Differential Pressure Switches · Fokker Services F27 Mark 100, F27 Mark 200, F27 Mark 300 and 4 more. Effective Oct 11, 2001 - [AD 2001-16-04](https://openairdocs.org/ad/2001-16-04): Wiring Harness · Fokker Services F27 Mark 050. Effective Aug 22, 2001 - [AD 2001-15-32](https://openairdocs.org/ad/2001-15-32): Traffic Collision Avoidance System (TCAS) · Fokker Services F27 Mark 050. Effective Aug 21, 2001 - [AD 2000-11-29](https://openairdocs.org/ad/2000-11-29): Shoulder Harnesses · Fokker Services F27 Mark 050, F27 Mark 100, F27 Mark 200 and 11 more. Effective Jul 19, 2000 - [AD 2000-07-28](https://openairdocs.org/ad/2000-07-28): High Pressure Cock (HPC) Levers · Fokker Services F27 Mark 050, F27 Mark 100, F27 Mark 200 and 5 more. Effective Apr 18, 2000 - [AD 2000-05-02](https://openairdocs.org/ad/2000-05-02): Horizontal and Vertical Stabilizer De-Icing System · Fokker Services F27 Mark 050, F27 Mark 200, F27 Mark 500 and 1 more. Effective Apr 12, 2000 All 128: https://openairdocs.org/tcds/A-817/ads.md ## STCs approved under this data sheet (78, first 50) - [STC ST01305WI-D](https://openairdocs.org/stc/ST01305WI-D): Modification of a Collins ALT-50A or ALT-55B Radio Altimeter system installation to a Collins ALT-1000 or ALT-4000 Radio Altimeter system installation in accordance with Collins Drawing Index as listed on AML No. ST01305WI-D, Revision -, or later FAA approved revision.. Rockwell Collins Inc - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC ST00885LA](https://openairdocs.org/stc/ST00885LA): Installation of fire extinguisher cartridges as replacements for Pacific Scientific fire extinguisher cartridges in fire extinguisher bottles.. AMETEK AMERON, LLC d/b/a MASS Systems - [STC 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 ST03885AT](https://openairdocs.org/stc/ST03885AT): Installation of an Avionica, Inc. avCM Cellular Module. Aircraft Systems and Manufacturing Inc. - [STC ST00264LA](https://openairdocs.org/stc/ST00264LA): Installation of floor proximity emergency escape path marking.. Bruce Industries Inc. - [STC ST00265LA](https://openairdocs.org/stc/ST00265LA): Installation of Interior Cabin Lighting.. Bruce Aerospace 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 ST01114DE](https://openairdocs.org/stc/ST01114DE): Installation of a Universal Avionics Navigation Management System with WAAS GPS. Peregrine - [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 ST03424CH](https://openairdocs.org/stc/ST03424CH): Certification of Automatic Dependent Surveillance - Broadcast (ADS-B) Out System with Rockwell Collins TDR-94/-94D Transponders. CMD Flight Solutions LLC - [STC 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 ST02120AT](https://openairdocs.org/stc/ST02120AT): Installation of an AlliedSignal CAS 67A traffic alert and collision avoidance system, along with a Single Mode S Transponder.. Woven Electronics LLC - [STC ST02592AT](https://openairdocs.org/stc/ST02592AT): This installation of an ACSS Dual Mode S Transponder System, along with Traffic Alert and Collision Avoidance System and provisions for Terrain Awareness and Warning System. Woven Electronics, LLC - [STC SA9086SC-D](https://openairdocs.org/stc/SA9086SC-D): Recore of Hamilton Standard Heat Exchangers 778683-2 for Installation on deHavilland DHC-8 Series Aircraft and 778683-2 for Installation on Fokker F27 Mark 050 Aircraft, in accordance with Honeywell LORI Sealed Drawing List SDL3545-1, Revision C, dated 11 October 2005 or later FAA approved revision.. Honeywell International Inc. - [STC ST00892AT](https://openairdocs.org/stc/ST00892AT): Installation of Hygolet lavatory seat to replace an existing aircraft toilet seat.. GDC Technics LLC - [STC ST04177AT](https://openairdocs.org/stc/ST04177AT): Installation of a Talon Aerospace LED Replacement General Purpose Lamps. Aaxico Technical Services Inc. - [STC ST10223SC](https://openairdocs.org/stc/ST10223SC): Installation of a Universal Avionics Terrain Awareness and Warning System (TAWS).. DAC International Inc - [STC ST09441SC](https://openairdocs.org/stc/ST09441SC): Installation of a single Universal Avionics Flight Management System with integrated GPS in accordance with New Systems Master Drawing List 228-00-0001, Rev. H, dated August 6, 2004, or later FAA approved revision. Airplane Flight Manual Supplement No. 228-00-0011, Rev. A, dated August 12, 2004, or later FAA approved revision is required.. DAC 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 ST00813DE](https://openairdocs.org/stc/ST00813DE): Replacement of Honeywell (formerly Sperry) ED-800 cathode ray tube (CRT) display, part number 7003110-90 I or 7003110-902, with Esterline CMC Electronics CMA-6800 multi-purpose liquid crystal display (LCD),. Peregrine - [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 ST04360CH](https://openairdocs.org/stc/ST04360CH): Reduction of payload to 7500 lbs. Installation of placard per Rezich & Rezich drawing RR006, Revision NONE, dated November 14, 2018, or later FAA approved revision.. Rezich and Rezich Aviation Consulting Inc. - [STC ST04229NY](https://openairdocs.org/stc/ST04229NY): Introduction of a 16G New Generation Stretcher XL P/N 1120030-Series. Bucher Leichtbau AG - [STC ST00384WI](https://openairdocs.org/stc/ST00384WI): Installation of Keddeg Company P/N 21BC116 Coalescer Assembly. 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 ST02479AK](https://openairdocs.org/stc/ST02479AK): ST02479AK. ADS-B Technologies, LLC - [STC ST00260DE](https://openairdocs.org/stc/ST00260DE): Installation of class e cargo interior, configuration 24E301-211.. Fokker 50 Freighter STC Corporation - [STC ST02530LA](https://openairdocs.org/stc/ST02530LA): Installation of T2CAS with TCAS version 7.1. Aircraft Communication & Surveillance Systems - [STC ST01916LA](https://openairdocs.org/stc/ST01916LA): Installation of a large cargo door.. Fokker50Freighter STC Corporation - [STC SA4995NM](https://openairdocs.org/stc/SA4995NM): Installation of model 1500 head up guidance system.. Rockwell Collins Aerospace & Electronics Inc. Flight Dynmics Division - [STC SA302WE](https://openairdocs.org/stc/SA302WE): Incorporate a de-icing system (as manufactured by applicant) externally on Rotol propeller spinner as an alternate to Dowty Rotol internal elements. If applied to original spinner, Montgomery Systems Tech., Inc. P/N 72196-2 will apply. If applied to a new aluminum nose spinner P/N 72196-1 will apply. Dowty Rotol Service Bulletin Section 61-170 pages 1 and 2 outlines a revised spinner de-icing system. This is a Napier external system. Approval of the A.R.B. is indicated. (Continued on page 3). ROBERT W. MURRAY - [STC SA4574NM](https://openairdocs.org/stc/SA4574NM): Installation of a de-icing system on the Rolls Royce P/N RK29954A or P/N RK48279A (MO) 1800 engine inlet cowl.. ROBERT W. MURRAY - [STC SA3693SW](https://openairdocs.org/stc/SA3693SW): : Installation of Floor Proximity Lighting System in accordance with Vista Manufacturing, Inc., Drawing Number FF27-1000, Revision C, Dated December 02, 1986 or later FAA approved revision. BF Goodrich Aerospace - [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 ST00673WI-D](https://openairdocs.org/stc/ST00673WI-D): Modification of Collins VHF-22A/VHF-22B VHF COMM Receiver Transmitter with CTL-22 Control Pro Line II System Installation to a Collins VHF-22C/VHF-22D VHF COMM Receiver Transmitter with CTL-22C Control 8.33 kHz Pro Line II System installation.. Rockwell Collins Inc - [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing - [STC ST00564NY](https://openairdocs.org/stc/ST00564NY): Installation of a King-KLN900 GPS Navigation System.. Cascade Aerospace Inc. - [STC ST00752NY](https://openairdocs.org/stc/ST00752NY): Installation of a Bendix King/KLN900 GPS navigation system.. Cascade Aerospace Inc. - [STC SA2394SO](https://openairdocs.org/stc/SA2394SO): Installation of a class E cargo compartment.. Mountain Air Cargo Inc - [STC ST00665DE](https://openairdocs.org/stc/ST00665DE): Fokker 50 Freighter list of drawings and documents, Drawing No. 24A343, Revision NC, dated February 18, 2008 or later FAA approved revision.. Fokker50Freighter STC Corporation - [STC SA1092GL](https://openairdocs.org/stc/SA1092GL): Installation of Grimes Floor Proximity lighting system, P/N 10-1309-43, P/N 10-1039-81, or P/N 10-1309-83 in Fokker 27 MARK 200 airplanes and P/N10-1309-41 or P/N 10-1309-59 in Fokker F.27 Mark 500 airplanes and P/N 10-1309-149 in F.27 Mark 600 airplanes.. Honeywell International Inc. - [STC ST177CH](https://openairdocs.org/stc/ST177CH): Installation of AlliedSignal expanded parameter flight data recorders and associated sensors.. Canard Aerospace Corporation - [STC ST178CH](https://openairdocs.org/stc/ST178CH): Installation of a BFGoodrich Aerospace Jet Electronics and Technology, standby attitude indicator and power supply.. Canard Aerospace Corporation - [STC ST01142WI-D](https://openairdocs.org/stc/ST01142WI-D): Modification of a single or dual Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92 control head to a Flight ID capable Collins TDR-94 or TDR-94D Mode S Transponder System installation with CTL-92E control head.. Rockwell Collins Inc - [STC ST00525WI-D](https://openairdocs.org/stc/ST00525WI-D): Modification of Collins 618M-4 VHF COMM Receiver Transmitter Installation to a 618M-5 VHF COMM Receiver Transmitter installation with either a Gables G7406-02 or Avtech 7522-1-2 VHF COMM Receiver Transmitter Control Series using with Collins Installation Instructions as listed on AML No. ST00525WI-D, or later FAA approved revisions.. Rockwell Collins Inc - [STC SA5810NM](https://openairdocs.org/stc/SA5810NM): Installation of Flite-Tronics static inverter model No. PC-3Y-500.. WECO Aerospace Systems Inc. All 78: https://openairdocs.org/tcds/A-817/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.