TCDS 1A17

Page No. 1 2 3 4 5 6 7 Rev No. 19 18 18 15 15 18 18 Reformatted 5/94. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A17 Revision 19 Gulfstream G-159 April 15, 1987 TYPE CERTIFICATE DATA SHEET NO. 1A17 This data sheet, which is a part of Type Certificate No. 1A17, 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: Gulfstream Aerospace Corporation P.O. Box 2206 Savannah, GA 31402-2206 I - Model G-159, Gulfstream I, (Transport Category), Approved May 21, 1959 Engines 2 Rolls-Royce Dart Mark 529-8E, Mark 529-8H, Mark 529-8X, Mark M529-8X (Mod 1814), Mark 529-8Y, or Mark M529-8Z. (Turboprop) (See Note 6 for required modifications and procedures for Engines Mark 529-8X (Mod 1814), Mark 529-8Y and Mark 529-8Z). Reduction Gearing 0.093.1. Fuels (fuels shall conform to Kerosene Type U.S. : ASTM D.1655-74 the specifications as listed) Jet A and A-1 MIL-T-5624-J Grade JP-5 British : D. Eng. R.D. 2498 Issue 6 D. Eng. R.D. 2494 Issue 7 Amendment 1 D. Eng. R.D. 2453 Issue 3 Amendment 1 Canadian : 3-GP-23h 3-GP-24g Wide-Cut Fuels U.S. : ASTM D.1655-74 Jet B MIL-T-5624-J Grade JP-4 British : D. Eng. R.D. 2486 Issue 8 Amendment 1 D. Eng. R.D. 2454 Issue 3 Amendment 1 Canadian: 3-GP-22h 1A17 Page 2 Fuel Specification D. Eng. R.D. 2453 and D. Eng. R.D. 2454 already include HITEC-E515 (formerly Santolene C) and anti-icing additive to Specification E. Eng. R.D. 2451 (Issue 2, or later issue) to approved limitations. Approved deviations Fuels with the following deviations from Specification D. Eng. R.D. 2494 are acceptable: Flash point: Minimum 28 deg. C. (82.4 deg. F.) Mercaptan Maximum 0.005 per cent sulphur content: by weight Mixing of fuels Any mixture of the above type fuels may be used without readjustment of the engine fuel control unit and without loss in engine power or aircraft performance. Wide-Cut Fuel The use of wide-cut fuel, as agreed to by the Operator, Rolls-Royce and appropriate Airworthiness Authority may result in a reduction in H.P. fuel pump life. Fuel conforming to emergency fuel specification ES-2-74 may be used on an exception basis. Refer to Airplane Flight Manual for approved fuel additives. Water/Methanol Refer to Rolls-Royce Specification Mixture: AEP-1-W/M, latest issue. Oil (engine, gearbox and APU) ESSO/EXXON Extra Turbo Oil 274 CASTROL 98 CASTROL UK 98 CASTROL 98 Gas Turbine Oil AEROSHELL Turbine Oil 750 TEXACO Synthetic Aircraft Turbine Oil 35 (T.S.A.T.O. 35) Also marketed as CALTEX Synthetic Turbo Oil 35 And those oils as approved for common usage in the engine, propeller and gearbox by Rolls Royce, Dowty Rotol, and the Civil Aviation Authority (U.K.) in DART OPERATING INSTRUCTIONS (F-DA-7-G), Rolls Royce Service Bulletins and Dowty Rotol Maintenance Manuals No. 865/1 and 865A/1 for G-159 aircraft and for use in APU Model No. GTC 85-37-2 in AiResearch Maintenance Manual 6A-243. Engine Limits Static Sea Level Ratings MK.529 -8E & 8H -8X, -8Y, -8Z Wet Takeoff (5 min.) Shaft Horsepower (Shp.) 1950 1990 Jet Thrust (Lb.) 510 520 Dry Takeoff (Unrestricted) Shaft Horsepower (Shp.) 1910 1910 Jet Thrust (Lb.) 500 500 Max. Continuous (Unrestricted) Shaft Horsepower (Shp.) 1910 1910 Jet Thrust (Lb.) 500 500 Page 3 1A17 Engine Limits (cont'd) Engine Speed Max. Permissible (R.P.M.) Turbine Gas Temp. (GT) °C Mk. 529-8E, -8H, -8X, -8Y, -8Z Wet Takeoff (5 min.) 15,000 860 Dry Takeoff (5 min.) 15,000 825 Max. Continuous 15,000 850 (-8E, -8H, -8X) (Unrestricted) For airplanes incorporating ASC 246; Max. continuous TGT at 15,000 RPM: -8X Engines = 870°C -8Y Engines = 910°C -8Z Engines = 920°C Starting Momentary 930 At low altitude at temperature below ISA, the engines may produce more power at takeoff than the airplane has been certified for. Under these conditions, the placarded torquemeter limitations should not be exceeded. Oil Inlet Temperature: Maximum +120°C Minimum for Starting -30°C Minimum for Opening Power Lever -15°C Propeller and 2 Rotol Model (C) R 184/4-30-4/50, with 4 R.A. 25907 blades each. Propeller Limits Diameter: 11.5 feet (nominal) Minimum allowable for repairs 11' 4". No further reduction permitted. Pitch setting at .7 radius: Ground fine pitch 0 Flight fine pitch +20° Cruise pitch +34° 30' Feathered +85° 30' Maximum governing e. r.p.m. 15,000 Minimum governing e. r.p.m. 11,000 E. r.p.m. limit (max. 20 sec.) 17,000 See NOTE 2(b) for idling e. r.p.m. limitations. Airspeed Limits (IAS) Vmo (max. operating) 290 knots (334 m.p.h.) 12,000 ft. and below Mmo M = .54 above 12,000 ft. is indicated by red & white limit on airspeed indicator. Va (maneuvering) 174 knots (200 m.p.h.) Vfe (flaps down 12.5°) 219 knots (252 m.p.h.) Vfe (flaps down 20°) 162 knots (187 m.p.h.) Vfe (flaps down 33°) 143 knots (165 m.p.h.) Vlo (landing gear operation) 193 knots (222 m.p.h.) Vle (landing gear extended) 193 knots (222 m.p.h.) Vmc (minimum control one engine inoperative) Feathered 101 knots (116 m.p.h.) Gear up. T.O. flaps Feathered 113 knots (130 m.p.h.) Clean Windmilling 127 knots (146 m.p.h.) Gear up. T.O. flaps Windmilling 138 knots (159 m.p.h.) Clean V11 (Landing light extension and operation) 290 knots (334 m.p.h.) Vdb Dive brake extension 310 knots (357 m.p.h.) Dive brake retraction 199 knots (229 m.p.h.) C.G. Range %MAC Sta. %MAC Sta. 1A17 Page 4 Takeoff & Landing (landing gear and flaps down) 20,000 lbs. 14.3 298.0 28.2 311.8 23,700 lbs. 14.3 298.0 - - - 26,100 lbs. 30.4 313.9 33,600 lbs. 20.8 304.4 31.9 315.5 34,285 lbs. 21.2 304.8 32.0 315.6 35,100 lbs. 21.8 305.4 32.2 315.8 36,000 lbs. 22.3 306.0 32.3 315.9 Linear variation of limits between points shown. Landing gear retraction moment is -30,000 in.-lb. Flap retraction moment is -6,600 in.-lb. Datum Station 0 is 8 in. forward of the nose, or 45 in. forward of the jig point at the centerline of the airplane in the nose wheel well. M.A.C. 99.4 in. (L.E. of M.A.C. +283.8) Leveling Means Longitudinal: Lugs at left nose wheel door longeron, Sta. 61.5 and 72.5. Lateral: Lugs on rear face of Bulkhead Sta. 44.5 in nose wheel well. Maximum Weight Takeoff 33,600 lb. on aircraft S/N 1 through S/N 60 including S/N 114. 35,100 lb. on aircraft S/N 61 through S/N 162 (excluding aircraft S/N 114), S/N 322 and 323 on aircraft S/N 1 thru 60 and S/N 114 when modified in accordance with Grumman Service Change No. 69. 36,000 lb. on aircraft S/N 163 through S/N 200 and on aircraft S/N 1 through 162, S/N 322 and 323, when modified in accordance with Grumman Service Change Nos. 69 and 175. Landing 32,000 lb. on aircraft S/N 1 through S/N 60 including S/N 114. 33,600 lb. on aircraft S/N 61 through S/N 162, (excluding aircraft S/N 114), S/N 322 and 323, and on aircraft S/N 1 through 60 and S/N 114 when modified in accordance with Grumman Service Change No. 69. 34,285 lb. on aircraft S/N 163 through S/N 200 and on aircraft S/N 1 through 162, S/N 322 and 323, when modified in accordance with Grumman Service Change Nos. 69 and 175. Zero usable fuel, oil and water/methanol (aircraft with outer wing panel fuel tank installation must include usable W/M). 29,707 lb. when takeoff weight is not more than 35,100 lbs. 27,303 lb. when takeoff weight is 36,000 lb. with linear variation between gross weights of 35,100 lb. and 36,000 lb. Minimum Crew 2 - Pilot and Copilot Maximum Number of Occupants The total number of occupants shall not exceed 23. The total number of passengers shall not exceed 19 as determined by emergency exit requirements. When Aircraft Service Change 153A is incorporated the total number of occupants shall not exceed 28. The total number of passengers shall not exceed 24 as determined by emergency exit requirements. (See Review Case Number 6.) Page 5 1A17 Maximum Baggage Compartment Forward Aft Aft-Shelved Station Boundary 133-193 525-571 525-586 525-586 Capacity (lb.) 400 736 1700* 800* Max. Floor Loading 50 64 64 64 (#/sq. ft.) Shelf Loading None None Variable Variable C.G. 163.0 543.0 Variable Variable *1700 lb. is the capacity at a Zero usable fuel, oil and W/M weight of 26,103 lb. This decreases linearly to 800 lb. at a Zero usable fuel, oil and W/M weight of 29,707 lbs. Fuel Capacity 1550 gal. total usable fuel in 2 wing tanks of 775 gal. each (F.S. 321). For aircraft with outer wing panel fuel tank installation, 1793.6 gal. total usable fuel (left tank 893.9 gallon, right tank 899.7 gallon) (F.S. 321). See NOTE 1(b) for system fuel. Water/Methanol Aircraft S/N 1 through 106 and 114 - 84 gal. Total usable in two parts of wing bladder tanks of 42 gallons each pair (F.S. 321). For aircraft with outer wing panel fuel tank installation (Gulfstream Aircraft service Change No. 125), the total usable water/methanol is 47.4 gal. in two wing fillet tanks of 23.7 gal. each (F.S. 384.1). For aircraft S/N 107 and subsequent and airplanes incorporating Gulfstream Airport Service Change No. 165, the total usable water/methanol is 46 gal. in two wing bladder tanks of 23 gal. each (F.S. 321). See NOTE 1(b) for system W/M. Oil Capacity 8.4 gal. total "Usable" 67.2 lb. located in integral engine tanks of 4.2 gal. each (F.S. 200.5). See NOTE 1(c) for system oil. Maximum Operating Altitude 30,000 ft. with APU or ASC 126 installed 25,000 ft. with Auxiliary Power Unit inoperative or not installed. Control Surface Movements Elevator Up 25° + 1/2° -1½° Down 14° + 0° -2° Elevator trim tab Up 3° ± ½° Down 20° ± 2°* Up 2° ± ½° Down 20° ± 2°** Rudder Right 22° + 0° -1° Left 22° + C° -1° Rudder tab Right 10° ± 1° Left 10° ± 1° (spring or trim) Aileron Up 16° ± 1° Down 12° ± 1° Aileron tab (trim) Up 20° ± 2° Down 20° ± 2° Aileron tab (spring) Up 15° ± 1 Down 15° ± 1° Flaps Down 33° ± 1° *For S/N 26 and subsequent excluding aircraft S/N 114. **For S/N 1 through 25 and S/N 114. Serial Nos. Eligible 1 and up. 1A17 Page 6 Certification Basis CAR 4b dated December 31, 1953, including Amendments 4b-1 to 4b-5 inclusive, Amendment 4b-6 Items 7, 8, 12, 16, 17, 19, 22, 23, 24, 25, 26, 28, 31, 32, 34, 35, 38, 39, 42 and 44, 4b-7 all Items, 4b-8 Items 2, 5, 6, 12, 17, 20, 21, 22, and 23, Special Regulation SR 422A, and Special Conditions in Attachment A of CAA letter to Grumman dated December 2, 1957, and exemption No. 689, CAR 4b.437, "Fuel Jettisoning System." Type Certificate 1A17 issued May 21, 1959. Date of Application for Type Certificate May 14, 1957. FAR 25.771, Amendment 4. A lockable door is not required between the pilot and passenger compartments. Compliance with the following optional requirements has been established: Ice Protection CAR 4b.640. Data covering ditching requirements of 4b.361 including 4b.362(d) and 4b.742(e) (but excluding 4b.645 and 4b.646) are approved. When the operating rules require emergency ditching equipment, compliance with 4b.645 and 4b.646 must be demonstrated. Grumman Report 1159-GER-7, revised July 25, 1977, entitled "Outfitting Requirements for FAA Certification for Ditching," provides an acceptable means for showing compliance with 4b.645 and 4b.646. Airplane Flight Manual Interim Revision 22.3, or later FAA approved revision must be incorporated. Production Basis None. Prior to original certification of aircraft manufactured subsequent to serial numbers 1 through 12, 14 through 112, 114 through 200, plus 322 and 323, an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved data, and a check of the flight characteristics (see NOTE 5.) Equipment The basic required 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. FAA approved Airplane Flight Manual, dated May 21, 1959. Reissued July 1, 1960. b. Crew oxygen system installation. When an aircraft is outfitted to carry passengers, an FAA approved passenger oxygen system must be installed. Service Information Service bulletins and other service information, when FAA approved, will carry a statement to that effect. See NOTE 4 regarding Grumman Gulfstream Service Change Number 147. NOTE 1. (a) Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. (b) System or unusable fuel, which must be included in the empty weight, is the amount of fuel required to fill the system plumbing and tank to the undrainable level (2.4 gal. total), plus unavailable fuel in the fuel tanks (8.3 gal. total). The total amount of "system fuel" 10.7 gal. total, 72 lb. (325). System or unusable and undrainable water/methanol are in identical quantity (3.4 gal. or 27 lb. total) and also must be included in the empty weight (325). For aircraft with outer wing panel fuel tank installation (Service Change No. 125), system water/methanol equals 1.8 gal. or 14 lb. total (346). (c) System oil, which must be included in empty weight, is the amount of oil necessary for engine lubrication and propeller operation. The total amount of "system oil" is as follows: 5.7 gal. (total) contained in engines, 45.8 lb. (200.5). NOTE 2. The following placards must be displayed in the locations indicated: (a) On the forward side of the passenger compartment forward door: (if installed) "This door must be OPEN during take-off and landing." Page 7 1A17 (b) On the instrument panel below r.p.m. indicators: "Avoid all continuous operation below 7000 RPM." (c) On aircraft serial numbers 3 and 114 adjacent to each swivel seat: "This seat must be forward facing during take-off and landing." (d) On aircraft serial numbers 2, 3, and 114 on the back rest of the jump seat: "Not to be used during take-off and landing." (e) On the forward side of the passenger compartment rear door: (This placard is required for 24 passenger aircraft and recommended for others.) "This door must be OPEN during take-off and landing." NOTE 3. Retirement Times: The retirement times of fatigue critical life limited components are listed in Section IV, Part 1 of the Gulfstream Aerospace Model 159 (Gulfstream I) Inspection Schedule Manual. The retirement times of these life limited components cannot be increased/changed without FAA Engineering approval. NOTE 4. Grumman Gulfstream Service Change No. 147 regarding large cargo door may be incorporated when the structural inspections specified in Service Change No. 147 are complied with. Grumman Flight Manual Supplement dated 31 August 1962 is also required for this modification. NOTE 5. Spare parts and aircraft may be manufactured at Grumman, Bethpage, Long Island, New York, facility under their production Certificate No. 23. Spare parts may be manufactured at Gulfstream Aerospace Corporation, Savannah, Georgia, under Production Certificate No. 507. NOTE 6. When Aircraft Service Change No. 246, "Nacelle Modification to Operate Dart Mark 529-8X, -8Y, and -8Z engines at Higher Maximum Continuous Power Settings" is installed, one of the following Airplane Flight Manual (AFM) Supplements is required. Engine Supplement No. -529-8X G1-82-002 -529-8Y G1-82-003 -529-8Z G1-82-004 The higher maximum continuous power settings below can be used where maximum continuous power setting follows use of wet takeoff power. *Engine Rolls Royce Mod RPM TGT (°C) Time Limit -529-8X 1814 15,000 870 Unrestricted -529-8Y 1806 15,000 910 Unrestricted -529-8Z 1810 15,000 920 Unrestricted *These engines must incorporate listed Rolls Royce modifications in order to use above higher maximum continuous power settings. ...END...