TCDS 7A1

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 Rev. No. 20 20 20 20 20 20 20 20 20 20 20 20 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 7A1 Revision 20 FAIRCHILD F-27 F-27A F-27B F-27F F-27G F-27J FH-227 FH-227B FH-227C FH-227D FH-227E F-27M May 13, 1992 TYPE CERTIFICATE DATA SHEET NO. 7A1 This data sheet which is a part of type certificate No. 7A1 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Maryland Air Industries, Inc. 1424 Davis Ford Road Woodbridge, Virginia 22192 I - Model F-27 (Transport Category), Approved July 16, 1958; Model F-27A, Approved December 31, 1958; Model F-27B, Approved October 25, 1958; Model F-27F, Approved February 24, 1961; Model F-27G, Approved May 1, 1963; Model F-27J, Approved August 3, 1965; Model FH-227, Approved June 24, 1966; Model FH-227B, Approved February 27, 1967; Model FH-227C, Approved June 17, 1967; FH-227D and FH-227E, Approved December 21, 1967; Model F-27M, Approved June 12, 1969. F-27A same as F-27 except for engine installation. F-27B same as F-27 except for large forward cargo door. F-27F same as F-27 except for engine installation. F-27G same as F-27F except for large forward cargo door. F-27J same as F-27F except for engine installation. FH-227 same as F-27J except for 70.8 inch extension to fuselage and major structural changes. FH-227B same as FH-227 except for propeller installation, wheels and brakes installation and structural changes. FH-227C same as FH-227 except for propeller installation, wheels and brakes installation. FH-227D same as FH-227B except for engine installation. FH-227E same as FH-227C except for engine installation. F-27M same as F-27J except for propeller and engine installation, elevator trim tab change. Engines F-27, F-27B : 2 Rolls-Royce Dart 511 or Dart 511-7E or Dart 514-7. Reduction gearing 0.086:1. F-27A : 2 Rolls-Royce Dart 528, Dart 528-7E (turboprop). Reduction gearing 0.093:1. F-27F, F-27G : 2 Rolls-Royce Dart 529-7E (turboprop). Reduction gearing 0.093:1. 7A1 2 F-27M : 2 Rolls-Royce Dart 532-7N (turboprop). Reduction gearing 0.093:1. F-27J, FH-227 : 2 Rolls-Royce Dart 532-7 (turboprop). Reduction gearing 0.093:1. FH-227C, FH-227B: 2 Rolls-Royce Dart 532-7 or 532-7P (turboprop). Reduction gearing 0.093:1. FH-227D, FH-227E: 2 Rolls-Royce Dart 532-7L (turboprop). Reduction gearing 0.093:1. Fuel (Fuel shall Aviation Kerosene Specifications. conform to the specifications as United States A.S.T.M. D1655-72 (Jet A or A-1) listed or to United States MIL-T-5624H, Grade JP-5 subsequent revisions Canadian 3-GP-23g thereof) 3-GP-24f British D. Eng. R.D. 2453 Issue 3 2494 Issue 7 2498 Issue 6 U.S.S.R. TS-1 (GOST 10227-62 AM1) I.A.T.A. Nov. 1969, Kerosene Type Fuel Aviation Wide-Cut Specifications. United States A.S.T.M. D1655-72 (Jet B) United States MIL-T-5624H, Grade JP-4 Canadian 3-GP-22g British D. Eng. R.D. 2454 Issue 3 2486 Issue 8 I.A.T.A. Nov. 1969, Wide-Cut Fuel Any mixture of the above type fuels may be used without readjustment of the engine fuel control unit and without loss in engine power of airplane performance. Water/Methanol mixture: to Rolls-Royce Specification AEP-1-W/M (latest issue). Oil (Engine and Gearbox) Refer to limitations section of the applicable Airplane Flight Manual for list of approved engine and gearbox lube oils. 3 7A1 Engine limits Static Sea Level Ratings at ISA DART 511 Shaft Horsepower (shp) Jet Thrust (lb.) Engine Speed (rpm) Max. Permissible Turb. Gas Temp. (°C) Wet takeoff (5 min.) 1570 310 14,500 595 Dry takeoff 1535 310 14,500 580 Max continuous 1535 310 14,500 580 Starting (momentary) — — — 640 DART 511-7E Wet takeoff (5 min.) 1570 310 14,500 595 Dry takeoff 1535 310 14,500 625 Max continuous 1535 310 14,500 625 Starting (momentary) — — — 640 DART 514-7 Wet takeoff (5 min.) 1670 332 14,500 600 Dry takeoff 1535 310 14,500 625 Max continuous 1535 310 14,500 625 Starting (momentary) — — — 640 DART 528 Wet takeoff (5 min.) 1870 495 15,000 810 Dry takeoff 1835 485 15,000 780 Max continuous 1835 485 15,000 780 Starting (momentary) — — — 930 DART 528-7E Wet takeoff (5 min.) 1870 495 15,000 860 Dry takeoff 1835 485 15,000 850 Max continuous 1835 485 15,000 850 Starting (momentary) — — — 930 DART 529-7E Wet takeoff (5 min.) 1950 510 15,000 860 Dry takeoff 1910 500 15,000 850 Max continuous 1910 500 15,000 850 Starting (momentary) — — — 930 DART 532-7 -7 -7P Wet takeoff (5 min.) 1990 520 15,000 860 860 Dry takeoff 1835 485 15,000 850 850 Max continuous 1835 485 15,000 850 850 Starting (momentary) — — — 930 930 DART 532-7L Wet takeoff (5 min.) 2040 520 15,000 905 Dry takeoff 1835 485 15,000 885 Max continuous 1835 485 15,000 885 Starting (momentary) — — — 930 DART 532-7N Wet takeoff (5 min.) 1990 520 15,000 905 Dry takeoff 1835 485 15,000 885 Max continuous 1835 485 15,000 885 Starting (momentary) — — — 930 7A1 4 Oil Inlet Temperature Dart 511, 511-7E, 514-7 Dart 528, 532-7L, 532-7N, 528-7E, 529-7E, 532-7 Maximum 110° C 120° C Minimum for starting -30° C -30° C Minimum for opening power lever -15° C -15°C Propeller and Dart 511, 511-7E, 514-7 2 Rotol Model (c) R 175/4-30-4/13E, with 4 R.A. 25899 blades each propeller limits (F-27, F-27B) Diameter 12.0 ft. (nominal). Minimum allowable for repairs 11' 9.75". No further reduction permitted. Pitch settings at .7 radius Ground fine pitch 0° Flight fine pitch +28° 48' Feathered +83° R.P.M. Limit (Max. 20 sec.) 17,000 Avoid all continuous operation below 7,000 r.p.m. Dart 528, 528-7E, 2 Rotol Model (c) R 193/4-30-4/50, with 4 R.A. 25907 blades each. 529-7E, 532-7 Diameter 11.5 ft. (nominal). (F-27A, F-27F, F-27G, Minimum allowable for repairs 11' 4.35". F-27J, FH-227) Pitch settings at .7 radius Ground fine pitch 0° Flight fine pitch 20° Cruise pitch 32° Feathered 87° R.P.M. Limit (Max. 20 sec.) 16,500 Avoid all continuous operation below 7,000 r.p.m. Dart 532-7, 532-7L, 2 Rotol Model (c) R 257/4-30-4/60, with 4 R.A. 25941 blades each. 532-7N, Diameter 12.5 ft. (nominal). (FH-227B, FH-227C, Minimum allowable for repairs 12' 3.2". FH-227D, FH-227E Pitch settings at 0.7 radius F-27M) Ground fine pitch 0° Flight fine pitch 16° Cruise pitch 28° Feathered 83° R.P.M. Limit (Max. 20 sec.) 16,500 r.p.m. Avoid all continuous operation between 8,500 and 9,500 r.p.m. Airspeed limits Vne (Never exceed) 298 m.p.h. (259 kt.) (CAS) Vmo (Maximum Operating) SL - 19,000 ft. 262 m.p.h. (227 kt.) at 20,000 ft. (226.5 kt.) above 20,000 ft., Vmo decreases 4.5 kt./1000 ft. Vmo (Maximum Operating) for FH-227B and FH-227D aircraft when modified in accordance with Fairchild Service Bulletin FH-227-53-2 SL-14800 ft. 287 m.p.h. (249 kt.) above 14,800 ft. 0.493 MACH. Va (Maneuvering and rough-air speed) 177 m.p.h. (154 kt.) Va (Maneuvering and rough-air speed) for FH-227, FH-227B, FH-227C, FH-227D, and FH-227E 196 m.p.h. (170 kt.) Vfe (Flaps down to 27°/18°) 161 m.p.h. (140 kt.) Vfe (Flaps down 27°/18° to full down at 40°/26° 145 m.p.h. (126 kt.) Vlo (Landing gear operation) 196 m.p.h. (170 kt.) Vle (Landing gear extended) 196 m.p.h. (170 kt.) 5 7A1 Vmc (Minimum control) for F-27, F-27A and F-27B with 0° takeoff flaps at sea level standard conditions 96 m.p.h. ( 83 kt.) Vmc (Minimum control) for F-27, F-27A and F-27B with 16.5° takeoff flaps at sea level standard conditions 90 m.p.h. ( 78 kt.) Vmc (Minimum control) for F-27F, F-27J and F-27M with 0° takeoff flaps at sea level standard conditions 99 m.p.h. ( 86 kt.) Vmc (Minimum control) for F-27F, F-27J and F-27M with 16.5° takeoff flaps at sea level standard conditions 93 m.p.h. ( 81 kt.) Vmc (Minimum control) for FH-227, FH-227B, FH-227C, FH-227D, and FH-227E with 16.5° flaps at sea level standard conditions 98 m.p.h. ( 85 kt.) Vmc (Minimum control) for FH-227, FH-227B, FH-227C, FH-227D, and FH-227E with 0° flaps at sea level standard conditions 104 m.p.h. ( 90 kt.) Vmc (Minimum control) for FH-227D and FH-227E with 9° flaps at sea level standard conditions 101 m.p.h. ( 87.5 kt.) Maximum speed for extending retractable type landing light and for operation with light extended 196 m.p.h. (170 kt.) Vdb (Drag Brake) 262 m.p.h. (227 kt.) C.G. range For Models F-27, F-27A, F-27B, F-27FF, F-27G, F-27J and F-27M : Weight Fwd. Aft (lb.) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.) (For aircraft with pneumatic nose gear steering system) Takeoff & landing (gear down) 22,000 21.0 (361.29) 38.0 (378.52) 25,400 to 30,200 20.0 (360.28) 38.0 (378.52) 34,000 24.0 (364.33) 38.0 (378.52) 34,500 24.4 (364.74) 38.0 (378.52) 35,700 25.6 (365.95) 38.0 (378.52) 36,000 25.8 (366.16) 38.0 (378.52) 36,300 26.0 (366.36) 38.0 (378.52) 36,500 26.2 (366.56) 38.0 (378.52) 36,700 26.3 (366.66) 38.0 (378.52) 37,500 27.0 (367.37) 38.0 (378.52) 38,500 27.8 (368.18) 38.0 (378.52) *39,400 28.4 (368.79) 38.0 (378.52) *42,000 30.0 (371.41) 38.0 (378.52) Enroute (gear up) 22,000 Same as Takeoff 40.7 (381.26) to and Landing 30,200 31,300 20.0 (360.28) 40.7 (381.26) 34,000 23.0 (363.32) 40.7 (381.26) 37,500 25.8 (366.16) 40.7 (381.26) 38,500 26.6 (366.97) 40.7 (381.26) 39,400 27.3 (367.68) 40.7 (381.26) 42,000 29.4 (369.81) 40.7 (381.26) 7A1 6 C.G. range For Models F-27, F-27A, F-27B, F-27FF, F-27G, F-27J and F-27M : (cont'd) Weight Fwd. Aft (lb.) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.) (For aircraft with hydraulic or pneumatic spur gear steering system.) Takeoff & landing (gear down) 22,000 21.0 (361.29) 38.0 (378.52) 25,400 to 31,300 20.0 (360.28) 38.0 (378.52) 34,000 23.0 (363.32) 38.0 (378.52) 34,500 23.5 (363.72) 38.0 (378.52) 36,000 24.6 (364.94) 38.0 (378.52) 36,300 24.8 (365.14) 38.0 (378.52) 36,500 25.0 (365.35) 38.0 (378.52) 36,700 25.2 (365.55) 38.0 (378.52) 37,500 25.8 (366.16) 38.0 (378.52) 38,500 26.6 (366.97) 38.0 (378.52) *39,400 27.3 (367.68) 38.0 (378.52) 40,000 27.8 (368.19) 38.0 (378.52) *42,000 29.4 (369.81) 38.0 (378.52) *Takeoff only. Enroute (gear up) 22,000 21.0 (361.29) 40.7 (381.26) 25,400 to 31,300 20.0 (360.28) 40.7 (381.26) 34,000 23.0 (363.32) 40.7 (381.26) 34,500 23.5 (363.72) 40.7 (381.26) 36,000 24.6 (364.94) 40.7 (381.26) 36,500 25.0 (365.35) 40.7 (381.26) 37,500 25.8 (366.16) 40.7 (381.26) 38,500 26.6 (366.97) 40.7 (381.26) 39,400 27.3 (367.68) 40.7 (381.26) 42,000 29.4 (369.81) 40.7 (381.26) For Model FH-227: Takeoff & landing (gear down) 26,000 18.0 (358.25) 35.0 (375.48) 39,000 18.0 (358.25) 35.0 (375.48) 43,500 20.0 (360.28) 35.0 (375.48) Enroute (gear up) 26,000 18.0 (358.25) 38.0 (378.52) 43,500 18.0 (358.25) 38.0 (378.52) For Models FH-227B and FH-227D: Takeoff & landing (gear down) 26,000 25.8 (366.18) 35.0 (375.48) 33,400 18.0 (358.25) 35.0 (375.48) 41,000 18.0 (358.25) 35.0 (375.48) 45,500 20.0 (360.28) 35.0 (375.48) Enroute (gear up) 26,000 25.8 (366.18) 38.0 (378.52) 33,400 18.0 (358.25) 38.0 (378.52) 41,000 18.0 (358.25) 38.0 (378.52) 45,000 20.0 (360.28) 38.0 (378.52) For Models FH-227C and FH-227E: Takeoff & landing (gear down) 26,000 25.8 (366.18) 35.0 (375.48) 33,400 18.0 (358.25) 35.0 (375.48) 41,000 18.0 (358.25) 35.0 (375.48) 43,500 19.1 (359.38) 35.0 (375.48) 7 7A1 For Models FH-227C and FH-227E: (cont'd) Weight Fwd. Aft (lb.) % M.A.C. Sta. (in.) % M.A.C. Sta. (in.) Enroute (gear up) 26,000 25.8 (366.18) 38.0 (378.52) 33,400 18.0 (358.25) 38.0 (378.52) 41,000 18.0 (358.25) 38.0 (378.52) 43,500 19.1 (359.38) 38.0 (378.52) F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M: Linear variation of forward C.G. limit between points shown. Gear retraction moment change is +27,000 in.-lb. FH-227: Linear variation of forward C.G. limit between points shown. Gear retraction moment change is +29,000 in.-lb. FH-227B, FH-227C, FH-227D, and FH-227E: Linear variation of forward C.G. limit between points shown. Gear retraction moment change is +36,174 in.-lb. Datum The datum location is variable. The airplane Weight and Balance report provides the datum location for that particular airplane. M.A.C. 101.4 in. (L.E. of M.A.C. +340.0) Leveling means The leveling means are variable. The Airplane Weight and Balance report provides means for that particular airplane. Maximum weights For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M: Takeoff 36,225 lb. 36,500 lb. when modified in accordance with Fairchild Service Bulletin 51-5. 37,500 lb. when modified in accordance with Fairchild Service Bulletin 51-6. 38,500 lb. when modified in accordance with Fairchild Service Bulletin 51-7. 39,400 lb. when modified in accordance with Fairchild ECP-233. 40,500 lb. when modified in accordance with Fairchild ECP-268 or Service Bulletin 51-13. 42,000 lb. when modified in accordance with Fairchild ECP-247. Landing 34,000 lb. 34,500 lb. when Dowty 9027, Y.4 main landing gear drag link attachment bolt incorporated. 36,000 lb. when modified in accordance with Fairchild Service Bulletin 51-5. 36,700 lb. when modified in accordance with Fairchild Service Bulletin 51-7. 37,500 lb. when modified in accordance with Fairchild ECP-233. 38,500 lb. when modified in accordance with Fairchild ECP-268 or Service Bulletin 51-13. 40,000 lb. when modified in accordance with Fairchild ECP-269 or Service Bulletin 51-15 or 51-16. Zero Fuel, 34,000 lb. oil and 36,300 lb. when modified in accordance with Fairchild Service W/M fluid Bulletin 51-7. 7A1 8 Maximum weights (cont'd For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E: Takeoff 43,500 lb. 45,500 lb. (FH-227B and FH-227D when modified per Fairchild Service Bulletin FH-227-32-8). Landing 43,000 lb. 45,000 lb. (FH-227B and FH-227D when modified per Fairchild Service Bulletin FH-227-32-8). Zero fuel, 39,000 lb. oil and 41,000 lb. (FH-227B and FH-227D when modified per W/M fluid Fairchild Service Bulletin FH-227-32-8). Minimum crew 2. (Pilot and copilot) Maximum passengers 48 ). See Note 1 (d) regarding approved interior arrangements). Maximum baggage For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M: Maximum Floor Capacity Loading Compartment Station (lb.) (#/ft.2) Fwd. Left 187-230 1200 150 Fwd. Right 154-230 2055 150 Fwd. Left 187-263(1) 2145 150 Fwd. Right 154-263(1) 3000 150 Fwd. Left 187-208 570 150 Fwd. Right 154-208 1444 150 Fwd. Right 136-208 1890 150 Fwd. Right 136-230 2494 150 Fwd. Left 205-230 705 150 Aft 600-681 790(2) 100 (1) Floor reinforcement required in accordance with Fairchild floor assembly Dwg. No. 27-313131, and installed per Fairchild Dwg. 27-310319. (2) Maximum capacity for aircraft with heater, air cycle and vapor cycle systems installed. REmoval of vapor cycle system increases capacity to 850 lb.; removal of both the vapor cycle system and the heater increases limit to 1040 lb. For Model FH-227, FH-227B, FH-227C, FH-227D, and FH-227E: Serial Nos. 501-512 Maximum Floor Capacity Loading Compartment Station (lb.) (#/ft.2) Fwd. Left (1) 187-230 1200 150 Fwd. Right (1) 154-230 2055 150 Aft 600-691 2200 100 Serial Nos. 513 and up Fwd. Left (1) 187-230 1200 150 230-265 665 105 Fwd. Left (2) 187-265 1560 105 Fwd. Right (1) 154-230 2055 150 230-265 689 105 Fwd. Right (2) 154-265 2150 105 Aft 600-691 2200 100 (1) Sum of Fwd. Left and Right compartments must not exceed 2200 lb (2) Sum of Fwd. Left and Right compartments must not exceed 3554 lb 9 7A1 Fuel capacity For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M: 2 outboard tanks of 668 gal. usable fuel each or 2 outboard tanks (ECP 246/256) of 741.5 gal. usable fuel each. 2 inboard tanks (optional) of 182 gal. usable fuel each in accordance with Fairchild ECP-29, or 2 inboard tanks (optional) of 286 gal. usable fuel each in accordance with Fairchild ECP-234, or 2 inboard tanks (optional) of 428.5 gal. usable fuel each in accordance with Fairchild ECP-245/256. 2 collector tanks of 14 gal. usable fuel each. See NOTE 1(b) for system fuel. For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E: 2 outboard tanks of 668 gal. usable fuel each. 2 collector tanks of 14 gal. usable fuel each. See NOTE 1(e) for system fuel. Water-Methanol capacity For Models F-27, F-27A, F-27B, F-27F and F-27G: 80 gal. (total) in two nacelle tanks of 40 gal. each (467.0). For Models F-27J and F-27M: 120 gal. (total) in two center section tanks of 60 gal. each (378.0) For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E: Optional for Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M 146 gal. (total) in two center section tanks of 73 gal. each (378.0). Oil capacity 8 gal. (total) in two engine tanks of 4 gal. each (267.5). See NOTE 1(c) for system oil. Maximum approved 25,000 ft. operating altitude Other operating The aircraft must be operated in accordance with the FAA Approved Airplane limitations Flight Manual. Control surface movements Elevator Up 25° Down 22° Elevator Trim Tab (left) Up 12.5° Down 32.5° "tab trails 3 1/2° down when cockpit indicator reads zero." Rudder Right 20° Left 20° Rudder (FH-227, FH-227B, FH-227C, FH-227D, and FH-227E) Right 17.5° Left 17.5° Rudder Balance Tab Right 6° Left 6° Rudder Trim Tab Right 14° Left 14° Rudder Trim Tab (FH-227, FH-227B, FH-227C, FH-227D, and FH-227E) Right 18° Left 18° Aileron (with spring tab neutral) Up 33° Down 22° Aileron Spring Tab (inner) Up 13° Down 13° Aileron Balance Tab (outer) Up 11° Down 16.5° Aileron Trim Tab (right outer) Up 15° Down 15° Flaps Down 40°/26° Serial Nos. eligible For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M: 1 through 500. For Models FH-227, FH-227C, and FH-227E: 501 and up. For Models FH-227B and FH-227D: 513 and up. 7A1 10 Certification basis For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M : CAR 4 b dated December 31, 1953, including Amendment 4b-1, Amendment 4b-3 (Item 21 thru 33 plus Item 39), Amendment 4b-7 and Amendment 4b-8 (Item 17); Special Regulations SR-422 effective August 27, 1957; and F-27 Special Condition dated January 28, 1957, as amended. Type Certificate No. 7A1 issued November 13, 1957; reissued to Fairchild July 16, 1958. Date of Application for Type Certificate November 9, 1954. Complies with the following optional requirements: Ice Protection CAR 4b.640 Ditching CAR 4b.361 (F-27, F-27A, F-27F, F-27J, and F-27M eligible for ditching certification when modified in accordance with Fairchild Engineering Report No. R27-207 revised April 17, 1959, when incorporating 44 passenger interior arrangement per Dwg. 27-771164 and related drawings). Airplane Flight Manual Supplements Required: F-27 (with MK-511-7E engines), Supplement I dated September 22, 1959 F-27 (with MK-514-7 engines), Supplement 19 dated February 18, 1963 For Models FH-227, FH-227B, FH-227C, FH-227D, and FH-227E: CAR 4b dated December 31, 1953, including Amendment 4b-1, Amendment 4b-3, (Items 21 thru 33 plus Item 39), Amendment 4b-7 and Amendment 4b-8 (Item 17); Special Regulation SR-422B and SR-450A and F-27 Special Conditions dated January 28, 1957, as amended. Complies with the following optional requirements: Ice Protection CAR 4b.640 Production basis Production Certificate No. 1. Equipment The basic equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: (a) Stall warning system, Fairchild Dwgs. 27-710050/1, 27-721010, 27-740064 (Safe flight speed control indicator P/N C-30205, included in above Dwgs., is not required equipment). (b) FAA Approved Airplane Flight Manual (1) Model F-27 and F-27B, dated July 18, 1958 reissued April 10, 1959. Supplement "0" (dated August 5, 1959) required for 36,500 lb. takeoff weight and 36,000 lb. landing weight. Supplement "T" (dated April 1, 1960) required for 37,500 lb. takeoff weight with Dart 511 engine installation. Supplements "T" (dated April 1, 1960), "AC" (dated December 9, 1960) and "AF" (dated November 9, 1961), required for 37,500 lb. takeoff weight with Dart 511-7E engine installation. Supplements "AC" (dated December 9, 1960), "AD" (dated February 20, 1961) and "AF" (dated November 9, 1961), required for 38,500 lb. takeoff, 36,700 lb. landing, and 36,300 lb. zero fuel weights with Dart 511-7E engine installation. 38,500 lb. takeoff, 36,700 lb. landing, and 36,300 lb. zero fuel weights not applicable to aircraft with Dart 511 engine installation. 11 7A1 (2) Model F-27 and F-27B with MK-514-7 engines, dated February 18, 1963. Supplement No. 13 (Rev. 1, dated June 1, 1964) required for 39,400 lb. takeoff and 37,500 lb. landing gross weights. Supplement No. 22 (dated June 1, 1964) required for 40,500 lb. takeoff and 38,500 lb. landing gross weights. Supplement No. 24 (dated August 3, 1965) required for 40,000 lb. landing gross weight. (3) Model F-27A dated December 31, 1958 reissued June 14, 1962. supplement No. 13 (dated June 14, 1962) required for 39,400 lb. takeoff and 37,500 lb. landing gross weights. supplement No. 15 (dated November 7, 1962) required for 42,000 lb. takeoff gross weight. Supplement No. 17 (dated June 1, 1964) required for 40,500 lb. takeoff gross weight. Supplement No. 18 (dated June 1, 1964) required for 38,500 lb. landing gross weight. Supplement No. 21 (dated August 3, 1965) required for 40,000 lb. landing gross weight. (4) Model F-27F/F-27G dated February 24, 1961, reissued August 11, 1964. Supplement No. 13 (dated August 11, 1964) required for 39,400 lb. takeoff, 37,500 lb. landing gross weight. Supplement No. 17 (dated August 11, 1964) required for 40,500 lb. takeoff gross weight. Supplement No. 18 (dated August 11, 1964) required for 38,500 lb. landing gross weight. Supplement No. 19 (dated August 11, 1964) required for 42,000 lb. takeoff gross weight. Supplement No. 16 (dated August 11, 1964) required for F-27G model only for convertible passenger - cargo version with large cargo door. Supplement No. 23 dated August 3, 1965 required for 40,000 lb. landing gross weight. (5) Model F-27J dated August 3, 1965. (6) Model FH-227 dated June 24, 1966. (7) Model FH-227B (Model FH-227 dated June 24, 1966 and Supplement No. 6 dated February 27, 1967) or FH-227B dated June 17, 1967. (8) Model FH-227C dated June 17, 1967. (9) Model FH-227D dated December 21, 1967. (10) Model FH-227E dated December 21, 1967. (11) Model F-27M dated June 12, 1969. Service information Service Bulletins and other service information when FAA approved will carry a statement to that effect. NOTE 1. (a) Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions, when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of operators having an approved weight control system). (b) System fuel, which must be included in the empty weight, is the amount of fuel required to fill both systems, including the cross-feed, up to the level of the boost pump inlets in the collector tanks (3.3 gal. total), plus the unusable fuel of the main tanks (12.1 gal. total). The total amount of "System Fuel" is as follows: 15.4 gal. total, 101 lb. (365). (c) System oil which must be included in empty weight, is the amount of oil normally trapped in the propellers, plus the amount normally trapped in the engines after oil drainage. The total amount of "System Oil" is as follows: 2.4 gal. (total) contained in engines, 19 lb. (282) 2.0 gal. (total) contained in propellers, 16 lb. (243) (d) Fairchild Engineering Reports "Weight and Balance Serial No. " contain interior arrangement, equipment list, weight and balance and loading schedule for each airplane. (e) System fuel, which must be included in the empty weight, is the amount of fuel required to fill both systems, including the cross-feed, up to the level of the boost pump inlets in the collector tanks (12.0 gal. total), plus the unusable fuel of the main tanks (12.1 gal. total). The total amount of the "System Fuel" is as follows: 24.1 gal. total, 161.1 lb. (370.9). 7A1 12 NOTE 2 The following placards must be displayed in the locations indicated: For Models F-27, F-27A, F-27B, F-27F, F-27G, F-27J and F-27M: (a) Deleted June 13, 1960. (b) On the lavatory door (on aircraft with the emergency exit located in the lavatory): (1) "This door must be open during take-off and landing" (2) "Emergency exit inside" (c) On the forward face of the lavatory wall (on aircraft with the emergency exit located in the lavatory): "Emergency exit thru lavatory" (d) Deleted June 1, 1963. (e) On the forward side of the passenger compartment forward door: "This Door Should be UNLOCKED for Take-off and Landing" (this applies to aircraft with life raft stored forward of door). (f) In the immediate vicinity of swivel seats that do not have the proper back height (36 1/2 in.) in