TCDS A-817

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