# TCDS 1A16: Allied Ag Cat Productions Inc. - Type: Type certificate data sheet - Status: Current - Holder: Allied Ag Cat Productions Inc. - Revision: 24 - Revised: February 22, 2001 - Product: Aircraft, Small Airplane - Certification basis: Part 11, Part 14, Part 15, Part 23, Part 48, Part 49, Part 68, Part 101, CAR 8 - Registered aircraft: 564, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e7/b5/e7b5095bc29b5e8a790faa493c7b5c4b52a8c7bf4c149877894ee89e3bdea942 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F257E75636F09BA586256A070066912C.0001 - Page: https://openairdocs.org/tcds/1A16 ## Models (10) As the data sheet lists them. - G-164B (with 73 inch wing gap) - G-164D - G-164B - G-164D (with 73 inch wing gap) - G-164C - G-164 - G-164B-20T - G-164A - G-164B-34T - G-164B-15T ## 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 19 20 R e v . N o . 2 41 52 02 32 32 32 32 3 2 3 2 32 3 2 3 2 3 2 3 2 3 2 21 71 71 7 17 P a g e N o . 2 12 22 32 42 52 6 2 7 2 82 9 3 0 3 1 3 2 3 3 3 4 R e v . N o . 1 71 71 71 72 32 3 2 3 2 32 3 2 2 2 2 2 2 2 2 2 2 This revision incorporates the new type certificate holder and adds Model G-164B-20T. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A16 Revision No. 24 Allied Ag Cat Productions, Inc. G-164 G-164A G-164B G-164B with 73” G-164B-15T G-164B-34T G-164B-20T G-164C G-164D G-164D with 73” wing gap February 22, 2001 TYPE CERTIFICATE DATA SHEET NO. 1A16 This data sheet which is a part of type certificate No. 1A16 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 Allied Ag Cat Productions, Inc. 301 West Walnut Street P.O. Box 482 Walnut Ridge, AR 72476 I - Model G-164, 1 POLB or 1 PCLB (Restricted Agricultural Category) approved January 20, 1959. Engine Continental W-670-6N (R-670-4) 479 lb. (+53.5) Continental W-670-16 (R-670-11) 486 lb. (+53.5) Continental W-670-6A (R-670-5) 470 lb. (+53.5) Continental W-670-240 (Gulf Coast) 516 lb. (+53.5) (See G-164 NOTE 3 for operating restrictions) Jacobs R-755-A2M1 503 lb. (+52.5) (See G-164 NOTE 6 for optional Jacobs engine installations) Pratt & Whitney R-985-AN-1, -AN-3, -25, -27, -39, -39A, -AN-14B; Wasp Jr. T1B2, T1B3 (One 4 1/2 and one 9th order crankcase damper) Fuel 80/87 Minimum octane aviation gasoline (R-985 series) 80 Minimum octane aviation gasoline (W-670 Series, R-755 Series) Engine For all operations: Limits: (W-670-6A, -6N or -16 engines) 2075 r.p.m. (220 hp.) (W-670-240 engine) 2075 r.p.m. (225 hp.) with item 1 propeller (W-670-240 engine) 2200 r.p.m. (240 hp.) with item 3 propeller (R-985 series engines) 2300 r.p.m. (450 hp.) with item 4 propeller (R-755-A2M1) 2200 r.p.m. (330 hp.) with item 3 propeller Manifold Pressure: (R-985-AN-14B): 36.5 in. Hg (sea level) 35.5 in. Hg (3500 ft.) Manifold Pressure: (R-985-AN-1, -AN-3, 37.5 in Hg (sea level) -25, -27, -39, -39A, T1B2, T1B3 37.0 in. Hg (1500 ft.) Manifold Pressure: (W-670 series): 28.0 in. Hg (sea level) 26.5 in. Hg (1500 ft.) Manifold Pressure (R-755): 28.0 in. Hg (sea Level) 26.5 in Hg (1500 ft.) Straight line variation between points 1A16 2 of 34 Propeller and Propeller Limits 1. McCauley ground adjustable propeller (with Continental W-670 series and Gulf Coast W-670-240 engines only) (a) Model 41D5926 with hub AAF 41D5926 and blades SS-135-6 79 lb. (+38.5) (b) Model D-1093 with hub D-1093 and blades SS-135-6M (See G-164 Note 2(a)(4) for operating restriction) 82 lb. (+38.5) Diameter: SS-135-6 blades: Max. 102 in. Min. 100 in. SS-135-6M blades: Max. 102-5/8 in. Min. 100 in. Pitch Settings at 42 in. sta. Static r.p.m. at Maximum Permissible W-670-6A, -6N, -16 Engines Throttle Setting (No additional tolerance permitted) 9.0o Not over 2055, not under 1905 9.5o Not over 1965, not under 1815 10.0o Not over 1905, not under 1755 10.5o Not over 1855, not under 1705 11.0o Not over 1815, not under 1665 W-670-240 Engine 9.7o Not over 1975, not under 1825 When installed on the above engines, the propeller must be indexed in the zero degree position (blades in line with crank throw) and the tachometer shall be placarded: "Avoid continuous operation between 1500 and 1650 RPM." A yellow arc marking must be included on the face of the tachometer between 1500 and 1650 RPM. Note: Blade angle adjustment must be within + or -1/2 o allowable tolerance to result in 2075 r.p.m. in climb at 75 m.p.h. CAS. 2. Hartzell constant speed propeller (with Jacobs R-755-A2M1 engine only) (a) Model HC-B3Z with hub Model HC-B3Z20-1 and blades Model 10160-8 115 lb. (+34.5) Diameter 93 in. only Pitch Settings at 30 in. Sta. Low 12.5o High 28.3o (b) Governor - Hartzell G-1 4.5 lb. (+72) 3. Gulfstream ground adjustable (with Continental W-670 series, Gulf Coast W-670-240 and Jacobs R-755-A2M1 engines only). (a) Model J-5404, SR-5404, SR-5404R/MA-96K-0 86 lb. Continental W-670 series engines (+37.5) Jacobs R-755-A2M1 engine (+35.7) Diameter: 96 in. only (Continental W-670 series engines) Max. 96 in., Min. 94 in. (Jacobs R-755-A2M1 engine) Pitch Settings Static r.p.m. at Maximum at 36 in. Sta. Permissible Throttle Setting (No additional tolerance permitted) W-670-6A, -6N, -16 Engines Not over 2060, not under 1960 14.1o W-670-240 Engine Not over 2095, not under 1945 14.5o R-755-A2M1 Engine Not over 2090, not under 1990 15.0o When installed on the above engines, the propeller must be indexed in the zero degree position, (blades in line with crank throw). Note: Blade angle adjustment must be within + or - 1/2 degree allowable tolerance to result in never exceeding the maximum rated r.p.m. at rated power in a full throttle climb at 75 m.p.h. CAS. 1A16 3 of 34 Model G-164 4. Hamilton Standard: 2D30/6101A-12-13-14 with P&W R-985 Series engines (cont’d) Diameter: 108 in. max., 106 in. min. (No further reduction permitted) 2D30 Hub, Pacific Propeller AG-100-2 blades, diameter 106 in. (2% cutoff permitted) Pitch Setting: 11.75o low, 14o high (2 pos.): 10.0o low, 16.5o high at 42 in. Sta. (constant speed) Governor: 1A2-5, 1A2G-5, or 4A2-1 Static r.p.m. at maximum permissible throttle setting: Not over 2070, not under 1970 (2 position) Airspeed Limits (CAS) V NE (Never Exceed) 131 m.p.h. (114 knots) VA (Maneuvering) 104 m.p.h. (90 knots) C.G. Range (+122.0) to (+124.0) at 3750 lb. (+122.0) to (+125.3) at 2460 lb. Straight line variation between points Empty Weight None C.G. Range Datum +99.1 in. ahead of firewall bulkhead. Leveling Means Longitudinal: Leveling lugs welded on tubular fuselage frame 27 in. below upper longeron and forward lug at station 100, left hand side. Maximum Weight Configuration Engine Prop Pitch Weight With Item 1 or 2 installed Sprayer W-670-6A, -6N or -16 9.5 o 3700 lb. Sprayer W-670-6A, -6N or -16 9 o, 10o, 10.5o, 11o 3550 lb. Duster W-670-6A, - 6N or -16 9.5 o 3600 lb. Duster W-670-6A, -6N or -16 9 o, 10o, 10.5o, 11o 3450 lb. Sprayer or W-670-240 9.7 o 3750 lb. Duster Sprayer or R-755-A2M1 - 3750 lb. Duster Configuration Engine Prop Pitch Weight With Item 3 installed Sprayer W-670-6A, -6N or -16 14.1 o 3600 lb. Sprayer or Duster W-670-240 14.5 o 3750 lb. Sprayer or Duster R-755-A2M1 15.0 o 3750 lb. Configuration Engine Prop Pitch Weight With Item 4 installed Sprayer or Duster R-985 series 16.5 o high, 10o low 3750 lb. No. of Seats 1 (+180) Maximum Hopper Capacity 1200 lb. (+122) S/N 1 through 300 2000 lb. (+122) S/N 301 and up Fuel Capacity 46.3 gal. or 33 gal. (+112.5) (One tank in upper wing center section (See G-164 Note 7)) Oil Capacity 7 gal. (+94) (6.5 gal. usable) (R-985 series) 5 gal. (+94) (4.5 gal. usable) (W-670 series, R-755 series) Serial No. Eligible S/N 1 through 400 Certification Basis CAR 8.10 (a)(1) effective October 11, 1950, and CAM 8, Appendix B as amended March 19, 1957, except CAR 3.241 utilized for Ground Loads. Restricted Type Certificate No. 1A16 issued January 20, 1959. Date of application for Type Certificate June 21, 1957. 1A16 4 of 34 Model G-164 (cont’d) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis and CAM 8, Appendix B, subparagraph .51) must be installed in aircraft for certification. In addition, the following items of equipment are required: (a) For aircraft with no electrical system: Pre-stall warning indicator, Safe Flight Instrument Corporation Kit No. 164-R, 6 volt. (Dry batteries powering this unit must be dated and replaced every six months.) (b) For aircraft incorporating an electrical system: Pre-stall warning indicator, (Safe Flight Instrument Corporation 12V or 24V P/N C-35407 or P/N 164-3) Installation per Drawing No. A1011. (c) Winter front installation per Gulfstream Drawing A1605. For all aircraft with Continental W-670 series Gulf Coast W-670-240 engines if operated when the OAT is below 35oF. (d) Nose Ballast installation per Gulfstream Drawing A1073A on aircraft equipped with Continental W-670 series engines or Gulf Coast W-670-240 engines. Required only when aircraft C.G. would otherwise be outside the specific aft limits. (e) Tail Ballast installation per Gulfstream Drawing A1072B. Required only when aircraft C.G. would otherwise be outside the specified forward limit. Maximum permissible weight. (Use actual weight). (f) Cylinder head Temperature Gage and Manifold Pressure Gage required on aircraft equipped with R985 series powerplant. Agricultural Dispersal The following Agricultural Dispersal Equipment may be installed: Equipment (a) Sprayer dispensing installation per Gulfstream Drawings A1011, S/N 1 and up, A1921, S/N 1 and up, A1960, S/N 1 through 300, A1480, S/N 301 through 400. (b) Dust dispensing installation per Gulfstream Drawing (1) A1970C Sheet 3 applicable S/N 1 through 100 (2) A1970D Sheet 4 applicable S/N 101 through 300 (3) A1970F Sheet 5 applicable S/N 301 through 400 (R-755 series and R985 series) II - Model G-164A 1 PCLB (Restricted Agricultural Category) approved March 4, 1966. Engines (See G-164A Pratt and Whitney R-985-AN-1, -AN-3, -25, -27, -39, -39A NOTE 1) -AN-14B, Wasp Jr. T1B2, T1B3 (One 4 1/2 and one 9th order crankshaft damper) Pratt and Whitney R-1340-AN-1, S1H1, S3H1 (eligible S/N 526 and up only) (One 4 1/2 and one 9th order crankshaft damper) Fuel 80/87 minimum octane aviation gasoline Engine Limits R-985 2300 r.p.m. (450 hp.) all operations Manifold Pressure: (R-985-AN-14B) 36.5 in. Hg (sea level) 35.5 in. Hg (3500 ft.) Manifold Pressure: (All others) 37.5 in. Hg (sea level) 37.0 in. Hg (1500 ft.) Straight line variation between points. 1A16 5 of 34 Model G-164A (cont’d) Engine Limits (cont’d) R-1340 2250 r.p.m. (600 hp.) Takeoff (5 minutes) 2200 r.p.m. (550 hp.) Max Continuous Manifold Pressure: (R-1340-AN-1, S3H1) 600 hp. 2250 r.p.m. 36.0 in. Hg (Sea Level) 550 hp. 2200 r.p.m. 34.0 in. Hg (Sea Level) to 32.5 in. Hg (5000 ft.) Manifold Pressure: (R-1340-S1H1) 600 hp. 2250 r.p.m. 36.5 in. Hg (Sea Level) 550 hp. 2200 r.p.m. 35.0 in. Hg (Sea Level) to 33.0 in. Hg (8000 ft.) Straight line variation between points Propeller and Propeller Limits R-985: Hamilton Standard 2D30 hub, 6101A-12, -13, -14 blades Diameter: 108 in. max., 106 in. min: (No further reduction permitted) Pitch Setting: 11.75o low, 14o high (2 pos.) At 42 in. station: 10o low, 16.5o high (constant speed) Governor: 1A2G-5, 1A2-5 or 4A2-1 Hamilton Standard 2D30 hub, Pacific Propeller AG-100-2 blades Diameter 106 in. (2% cutoff permitted) Pitch Setting: 11.75o low, 14o high (2 pos.) At 42 in. station: 10o low, 16.5o high (2 pos.) Governor: 1A2G-5, 1A2-5 or 4A2-1 Static r.p.m. at maximum permissible throttle setting: not over 2070, not under 1970 (2 position) R-1340: Hamilton Standard 12D40 hub, 6101A-12 blades Diameter: 108 in. (2% cutoff permitted) Pitch Setting: 11o low, 20o high Governor: 1M12 Hamilton Standard 12D40 hub, Pacific Propeller AG-100-2 blades Diameter: 106 in. (2% cutoff permitted) Pitch Setting: 11o low, 20o high Governor: 1M12 or EDO-AIRE 34-828-021 Airspeed Limits V ne (Never exceed) 147 m.p.h. (128 knots) (CAS) V a (Maneuvering) 117 m.p.h. (102 knots) C.G. Range Aircraft S/N 1571, 1583, 1616 up (401 through 1570, 1572 through 1582 R-985 and 1584 through 1615 retroactive) (+122.0) to (+125.4) at 4500 lb. C.G. Range Aircraft S/N 526 and Up R-1340 (+122.0) to (+124.0) at 4500 lb. (+120.3) to (+125.3) at 3525 lb. Empty Weight Aircraft S/N 401 and Up C.G. Range None R-985 Empty Weight Aircraft S/N 526 and Up C.G. Range None R-1340 Datum +99.1 in. ahead of firewall bulkhead. 1A16 6 of 34 Model G-164A (cont’d) Leveling Means Longitudinal: Level lugs welded on tubular fuselage frame 27 in. below upper longeron and forward lug at station 100, left hand side. No. of Seats 1 (+180) Maximum Hopper 2000 lb. (+126.2) Capacity Fuel Capacity 46.3 gal. (+112.5) (One Tank in wing center section) (See G-164A NOTE 3) Oil Capacity 7 gal. (+94.0) (6.5 gal. usable) (See G-164A NOTE 6) 8.7 gal. (+94.0) (8.2 gal. usable) (See G-164A NOTE 6) Serial No. Eligible S/N 401 and Up Certification Basis CAR 8.10 (a)(1) effective October 11, 1950, and CAM 8, Appendix B, as amended March 19, 1957. Amended Restricted Type Certificate No. 1A16 issued March 1966. Date of Application for Type Certificate Amendment November 12, 1964. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis and CAM 8, Appendix B, subparagraph .51) must be installed in aircraft for certification. In addition, the following items of equipment are required: (a) For aircraft with no electrical system: Pre-stall warning indicator, Safe Flight Instrument Corp. Kit No. 164-R, 6 volt. (Dry batteries powering this unit must be dated and replaced every six months) (b) For aircraft incorporating an electrical system: Pre-stall warning indicator, Safe Flight Instrument Corp. 12V or 24V P/N C-35407 or P/N 164-3. Installation per A1011, Sheet 2 (c) Cylinder head temperature gage and manifold pressure gage required on aircraft equipped with R-985 and R1340 series powerplants. (d) Tail ballast per Gulfstream Drawing A1074 required on all R-1340 series engine installations only when aircraft C.G. would otherwise be outside the specified forward limit. Agricultural Dispersal The following Agricultural Dispersal Equipment may be installed: Equipment (a) Sprayer Dispensing Installation per Gulfstream Drawings (1) A1480 (Leading Edge Booms), through S/N 750 (2) A2930 (Leading Edge Booms), S/N 751 through 1725 (3) A2901 (Trailing Edge Booms), S/N 751 through 1726 and up (4) A5740 (Trailing Edge Booms), S/N 1726 and up (b) Dust dispensing installation per Gulfstream Drawing (1) A1970F Sheet 5, Dust System Installation (2) A1398, Spreader Installation (R-985 and R-1340 Only) (Alternate) (3) A1490, Spreader Installation (R-985 and R-1340 Only) 1A16 7 of 34 III - Model G-164B 1 PCLB (Restricted Agricultural Category) approved November 18, 1975. Model G-164B (with 73" wing gap) - 1 PCLB (Restricted Agricultural Category) approved November 18, 1982 Model G-164B-15T and G-164B-34T 1 PCLB (Restricted Agricultural Category) approved December 23, 1985 Model G-164B-20T, 1 PCLB (Restricted Agricultural Category) approved April 1991 Engine Pratt and Whitney R-985-AN-1, AN-3, -25, -27, -39, -39A, -AN-14B; T1B2, T1B3 (One 4 1/2 and one 9th order crankshaft damper) Continental/Page R-975-46/A2 Pratt & Whitney R-1340-AN-1, S1H1, S3H1 (One 4 1/2 and one 9th order crankshaft damper) Pratt & Whitney of Canada Ltd. PT6A-15AG - G-164B-15T only. Pratt & Whitney of Canada Ltd. PT6A-34AG - G-164B-34T only. Pratt & Whitney of Canada LTD. PT6A-20B - G-164B-20T only. Fuel R-985 & R-1340 80/87 minimum octane aviation gasoline R-975 100 minimum octane aviation gasoline PT6A-15AG & PT6A-34AG, and PT6A-20B Jet A/Jet A-1/Jet B Automotive Diesel Fuel permitted for agricultural operations when free air temperature is above +5oC (+41oF) for grade DF-2 -4oC (+25oF) for grade DF-1 Engine Limits R-985 2300 r.p.m. (450 hp.) all operations Manifold Pressure (R-985-AN-14B) 36.5 in. Hg (sea level) 35.5 in. Hg (3500 ft.) Manifold Pressure (all others) 37.5 in. Hg (sea level) 37.0 in. Hg (1500 ft.) Straight line variation between points. R-975-46/PA2 2300 r.p.m. (525 hp.) Takeoff (5 minutes) 2300 r.p.m. (500 hp.) Max. Continuous Manifold Pressure: 525 hp. 42.1 in. Hg (Sea Level) 500 hp. 40.7 in. Hg (Sea Level) R-1340 2250 r.p.m. (600 hp.) Takeoff (5 minutes) 2200 r.p.m. (550 hp.) Max. Continuous Manifold Pressure: (R-1340-AN-1, S3H1) 600 hp. 2250 r.p.m. 36.0 in. Hg (Sea Level) 550 hp. 2200 r.p.m. 34.0 in. Hg (Sea Level) to 32.5 in. Hg (5000 ft.) Straight line variation between points Manifold Pressure: Wasp S1H1 600 hp. 2250 r.p.m. 36.5 in. Hg (Sea Level) 550 hp. 2200 r.p.m. 35.0 in. Hg (Sea Level) to 33.0 in. Hg (8000 ft.) Straight line variation between points 1A16 8 of 34 Model G-164B (cont’d) PT6A-15AG Operating Conditions OPERATING LIMITS POWER SETTING SHP TORQUE PSI MAXIMUM ITT oC Ng RPM % Np RMP % OIL PRESSURE PSIG OIL TEMP oC TAKEOFF (5 MINUTES) 680 53.3 725 38100 101.5 2200 100 80-100 10-99 MAXIMUM CONTINUOUS 600 47 695 -- -- 2200 100 80-100 10-99 MAX. CLIMB/ MAX CRUISE 600 47 695 -- -- -- -- 80-100 0-99 IDLE GROUND IDLE FLIGHT -- -- 660 660 19000 52 25500 68 -- -- 40 (MIN) 40 (MIN) -40-99 -40-99 STARTING -- -- 1090 -- -- -- -- -- -40 (MIN) ACCELERATION -- 68.8 825 38500 102.6 2420 110 -- 0-99 MAX. REVERSE 600 49.2 725 38100 101.5 2100 95.5 80-100 0-99 PT6A-34AG Operating Conditions OPERATING LIMITS POWER SETTING SHP TORQUE PSI MAXIMUM ITT oC Ng RPM % Np RMP % OIL PRESSURE PSIG OIL TEMP oC TAKEOFF (5 MINUTES) 750 58.7 790 38100 101.5 2200 100 85-105 10-99 MAXIMUM CONTINUOUS 600 47 740 -- -- 2200 100 85-105 10-99 MAX. CLIMB/ MAX CRUISE 600 47 740 -- -- -- -- 85-105 0-99 IDLE GROUND IDLE FLIGHT -- -- 685 685 19000 52 25500 68 -- -- 40 (MIN) 40 (MIN) -40-99 -40-99 STARTING -- -- 1090 -- -- -- -- -- -40 (MIN) ACCELERATION -- 68.4 850 38500 102.6 2420 110 -- 0-99 MAX. REVERSE 600 49.2 780 38100 101.5 2100 95.5 85-105 0-99 PT6A-20B Operating Conditions OPERATING LIMITS POWER SETTING SHP TORQUE PSI MAXIMUM ITT Ng RPM % Np RMP % Oil Press PSIG Oil Temp oC Take-off* Max. Cont.** 550 42.5 750 38100 101.5 2200 100 65-85 10-99 Max. Climb 538 ISA 42.5 725 -- -- 2200 100 65-85 0-99 Max. Cruise 495 ISA 42.5 705 -- -- 2200 100 65-85 0-99 Idle - Grnd Idle - Flight -- -- 685 685 19000 52 25500 68 -- -- 40 (MIN) 40 (MIN) -40-99 -40-99 Starting -- -- 1090 -- -- -- -- -- -40 (MIN) Acceleration -- 48.5 850 38500 102.6 2420 110 -- 0-99 Max Reverse 500 40.5 750 38100 101.5 2100 95.5 65-85 0-99 *Takeoff -5 mintes **Maximum Continuous - enroute emergency 1A16 9 of 34 Model G-154B (cont’d) Propeller and Propeller R-985: Limits Hamilton Standard 2D30 hub, 6101A-12, -13, -14 blades Diameter: 108 in. max., 106 in. min: (No further reduction permitted) Pitch Setting: 11.75o low, 14o high (2 pos.) At 42 in. station: 10o low, 16.5o high (constant speed) Governor: 1A2G-5, 1A2-5 or 4A2-1 Hamilton Standard 2D30 Hub, Pacific Propeller AG-100-2 blades Diameter: 106 in. (2% cutoff permitted) Pitch Setting: 11.75o low, 14o high (2 pos.) At 42 in. station: 10o low, 16.5o high (constant speed) Governor: 1A2G-5, 1A2-5 or 4A2-1 Static r.p.m. at maximum permissible throttle setting: not over 2070, not under 1970 (2 position) Hamilton Standard 2D30 hub, Pacific Propeller AG-100-48 blades Diameter: 104 in. max., 102 in. min. Pitch Settings at 42 in. station 9.5o low, 16.5o high (Constant Speed) R-975-46/PA2: Hamilton Standard 2D30 Hub, Pacific Propeller AG-100-48 blades Diameter: 104 in. max., 102 in. min. Pitch Settings at 42 in. station 9.5o low, 16.5o high (Constant Speed) Avoid continuous operation 1300-1450 r.p.m. Governor: 1A4-R-975 (Pacific Propeller) R-1340: Hamilton Standard 12D40 hub, 6101A-12 blades Diameter: 108 in. (2% cutoff permitted) Pitch Setting: 11o low, 20o high Governor: 1M12 Hamilton Standard 2D40 Hub, Pacific Propeller AG-100-48 blades Diameter: 104 in. max., 102 in. min. Pitch Settings at 42 in. station 10.5o low, 20 high (Constant Speed) Governor: 1M12 Hamilton Standard 2D40 Hub, Pacific Propeller AG-100-48 blades Diameter: 104 in. max., 102 in. min. Pitch Settings at 42 in. station 10.5o low, 20 high (Constant Speed) Governor: 1M12 Hamilton Standard 22D40 Hub, Pacific Propeller AG-100-48 blades 549B & up Diameter: 104 in. (2% cutoff permitted) Pitch Settings 11.o low, 20o high Governor: 4G10-21 PT6A-15AG, PT6A-34AG, and PT6A-20B Hartzell HC-B3TN-3D hub, T10282 + 4 blades Diameter: 106 in. max., 100 in. min. Pitch Setting: at 30 in. station low 18o, reverse 8o, feather 90o Airspeed Limits V ne (Never exceed) 147 m.p.h. (128 knots) Through S/N 548B (CAS) V a (Maneuvering) 117 m.p.h. (102 knots) S/N 549B and Up Vne (Never exceed) 145 m.p.h. I.A.S. (126 knots) Va (Maneuvering) 116 m.p.h. I.A.S. (101 knots) 1A16 10 of 34 Model G-164B (cont’d) G-164B-15T, G-164B-34T, and G-164B-20T Vne (Never exceed) 157 m.p.h. I.A.S. (136 knots) Va (Maneuvering) 125 m.p.h. I.A.S. (109 knots) C.G. Range G-164B (through S/N 708B) R-985 (+122.0) to (+125.0) at 4500 lb. R-975-46/PA2 (+122.0) to (+124.8) at 4500 lb. R-1340 (+122.0) to (+124.0) at 4500 lb. G-164B with 73" Wing Gap (S/N 709B and Up) R-1340 (+122.0) to (+125.5) at 5200 lb. (S/N 709B and up) R-985 (+122.0) to (+126.0) at 5200 lb. (S/N 752B and up) PT6A-15AG & (+122.0) to (+125.5) at 5200 lb. PT6A-34AG (+122.0) to (+125.5) at 5200 lb. PT6A-20B (+122.0) to (+125.5) at 5200 lb. Empty Weight G-164B (through S/N 708B) and G-164B with 73" Wing Gap (S/N 709B and Up) C.G. Range None Datum +99.1 in. ahead of firewall bulkhead. Leveling Means Longitudinal: Leveling lugs welded on tubular fuselage frame 27 in. below upper longeron and forward lug at station 100, left hand side. No. of Seats 1 (+180) Maximum Hopper 2000 lb. (+126.2) Capacity Fuel Capacity 46.3 gal. (+112.5) (One tank in wing center section) (See G-164B NOTE 3) 80 gal. (+112.5) (S/N 660B through 708B) 80 gal. (+112.6) (S/N 709B and up with 73" in. wing gap) (see G-164B Note 6). Oil Capacity 8.7 gal. (+94.0) (8.2 gal. usable) 2.8 gal. (+72.0) (PT6A-15AG & PT6A-34AG), and PT6A-20B Serial No. Eligible Model G-164B 1B and up Model G-164B-15T, -34T, & -20T 709B & up Certification Basis G-164B and G-164B with 73" wing gap: CAR 8.10(a)(1) effective October 11, 1950, and CAM 8, Appendix B, as amended March 19, 1957. Amended Restricted Type Certificate No. 1A16 issued November 18, 1975. Date of application for Type Certificate Amendment March 11, 1975. G-164B-15T and G-164B-34T CAR 8.10(a)(1) effective October 11, 1950 and CAM 8, Appendix B, as amended March 19, 1957, and applicable FAR paragraphs. Amended Restricted Type Certificate No. 1A16 issued December 23, 1985. Date of application for Type Certificate Amendment, January 23, 1983. G-164B-20T CAR 8.10(a)(1) effective October 11, 1950 and CAM 8, Appendix B, as amended March 19, 1957, and applicable FAR paragraphs. Amended Restricted Type Certificate No. 1A16 issued April 23, 1991. Date of application for Type Certificate Amendment, March, 1991. 1A16 11 of 34 Model G-164B (cont’d) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis and CAM 8, Appendix B, subparagraph .51) and applicable FAR 23 paragraphs for the models G-164B-15T, G-164B-34T, and G-164B-20T must be installed in aircraft for certification. In addition, the following items of equipment are required: (a) For aircraft with no electrical system: Pre-Stall warning indicator, Safe Flight Instrument Corporation Kit No. 164-R, 6 volt. (Dry batteries powering this unit must be dated and replaced every six months). (b) For aircraft incorporating an electrical system: Pre-stall warning indicator, (Safe Flight Instrument Corporation 12v or 24v P/N C-35407) or P/N 164-3 Installation per drawing A3011. (c) Cylinder head temperature gage and manifold pressure gage. (R975, R985, R1340 only). (d) Fixed Ballast Inst. STA 46.5 (G-164B-15T & G-164B-34T) or sta 45.8 (G- 164B-20T) per drawing A7534. Agricultural Dispersal The following Agricultural Equipment may be installed: Equipment Equipment (a) Sprayer dispensing installation per Gulfstream Drawing: (1) A2901 (Trailing Edge Booms) through A/C 334B. (2) A3740 (Trailing Edge Booms) 335B through 659B (3) A3740 (Trailing Edge Booms) 660B and up. (R-1340 Eng.) (4) A3723 (Trailing Edge Booms) 752B and up. (R-985 Eng.) (b) Dust Dispensing Installation per Gulfstream Drawing: A1970A Sheet 6, Dust System Installation (S/N 1B through 659B). (1) A1398 Spreader Installation. (2) A1490 Spreader Installation. A3709 Dust Spreader Installation (660B and up). (R-1340 and PT6A Engine). A7740 Dust Spreader and Emergency Dump Installation - (R-985 Eng.) S/N 752B and up. IV - Model G-164C 1 PCLB (Restricted Agricultural Category) approved November 23, 1977 Engine Pratt and Whitney R-1340-AN-1, S1H1, S3H1 (One 4 1/2 and one 9th order crankshaft damper) Fuel 80/87 minimum octane aviation gasoline Engine Limits R-1340 2250 r.p.m. (600 hp.) Take off (5 minutes) 2200 r.p.m. (550 hp.) Max. Continuous Manifold Pressure: (R-1340-AN-1, S3H1) 600 hp. 2250 r.p.m. 36.0 in. Hg (Sea Level) 550 hp. 2200 r.p.m. 34.0 in. Hg (Sea Level) to 32.5 in. Hg (5000 ft.) Manifold Pressure: (R-1340-S1H1) 600 hp. 2250 r.p.m. 36.5 in. Hg (Sea Level) 550 hp. 2200 r.p.m. 35.0 in. Hg (Sea Level) to 33.0 in. Hg (8000 ft.) Straight line variation between points Propeller and Propeller R-1340: Limits Hamilton Standard 12D40 hub, 6101A-12 blades Diameter: 108 in. (2% cutoff permitted) Pitch Setting: 11o low, 20o high Governor: 1M12 1A16 12 of 34 Model G-164C (cont’d) Propeller and Propeller Hamilton Standard 12D40 hub, Pacific Propeller AG-100-2 blades Limits (cont’d) Diameter: 106 in. (2% cutoff permitted) Pitch Setting: 11o low, 20o high Governor: 1M12 or EDO-AIRE 34-828-021 Airspeed Limits (CAS) Through S/N 42C Vne (Never exceed) 147 m.p.h. (128 knots) Va (Maneuvering) 117 m.p.h. (102 knots) Aircraft S/N 43C and Up Vne (Never exceed) 139 m.p.h. I.A.S. (121 knots) Va (Maneuvering) 112 m.p.h. I.A.S. (97 knots) C.G. Range (+121.0) to (+125.2) at 6300 lb. (+121.0) to (+125.2) at 4400 lb. Empty Weight None C.G. Range Datum +81.1 in. ahead of firewall bulkhead. Leveling Means Longitudinal: Level lugs welded on tubular fuselage frame 27 in. below upper longeron and forward lug at station 82.0, left hand side. No. of Seats 1 (+206) Maximum Hopper 4000 lb. (See Weight and Balance Data) Capacity Fuel Capacity 80 gal. (+112.5) Oil Capacity 8.7 gal. (+94.0) (8.2 gal. usable) Serial No. Eligible S/N 1C and up Certification Basis CAR 8.10 (a)(1) effective October 11, 1950, and CAM 8, Appendix B, as amended March 19, 1957. Amended Restricted Type Certificate No. 1A16 issued November 23, 1977. Date of Application for Type Certificate Amendment July 21, 1976. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis and CAM 8, Appendix B, subparagraph .51) must be installed in aircraft for certification. In addition, the following equipment is required: (a) For aircraft with no electrical system: Pre-stall warning indicator, Safe Flight Instrument Corp. Kit No. 164-R, 6 volt. (Dry batteries powering this unit must be dated and replaced every six months) (b) For aircraft incorporating an electrical system: Prestall warning indicator, Safe Flight Instrument Corp. 12V or 24V P/N C-35407 or P/N 164-3) installation per drawing A3011 Agricultural Dispersal The following Agricultural Dispersal Equipment may be installed: Equipment (a) Sprayer Dispensing Installation per Gulfstream Drawings A5740. (b) Dust dispensing installation per Gulfstream Drawing A5760. 1A16 13 of 34 V - Model G-164D 1 PCLB (Restricted Agricultural Category) Approved March 26, 1979. Model G-164D (with 73" wing gap) - 1 PCLB (Restricted Agricultural Category) Approved June 15, 1981. Engine Pratt and Whitney of Canada Ltd. PT6A-15AG Pratt & Whitney of Canada Ltd. PT6A-34AG Fuel Jet A/Jet A-1/Jet B Automotive Diesel Fuel permitted for agricultural operations when free air temperature is above +5oC (+41oF) for grade DF-2 -4oC (+25oF) for grade DF-1 ENGINE LIMITS PT6A-15AG Operating Conditions OPERATING LIMITS POWER SETTING SHP TORQUE PSI MAXIMUM ITT oC Ng RPM % Np RMP % OIL PRESSURE PSIG OIL TEMP oC TAKEOFF (5 MINUTES) 680 53.3 725 38100 101.5 2200 100 80-100 10-99 MAXIMUM CONTINUOUS 600 47 695 -- -- 2200 100 80-100 10-99 MAX. CLIMB/ MAX CRUISE 600 47 695 -- -- -- -- 80-100 0-99 IDLE GROUND IDLE FLIGHT -- -- 660 660 19000 52 27400 73 -- -- 40 (MIN) 40 (MIN) -40-99 -40-99 STARTING -- -- 1090 -- -- -- -- -- -40 (MIN) ACCELERATION -- 68.8 825 38500 102.6 2420 110 -- 0-99 MAX. REVERSE 600 49.2 725 38100 101.5 2100 95.5 80-100 0-99 ENGINE LIMITS PT6A-34AG Operating Conditions OPERATING LIMITS POWER SETTING SHP TORQUE PSI MAXIMUM ITT oC Ng RPM % Np RMP % OIL PRESSURE PSIG OIL TEMP oC TAKEOFF (5 MINUTES) 750 58.7 790 38100 101.5 2200 100 85-105 10-99 MAXIMUM CONTINUOUS 600 47 740 -- -- 2200 100 85-105 10-99 MAX. CLIMB/ MAX CRUISE 600 47 740 -- -- 2200 100 85-105 0-99 IDLE GROUND IDLE FLIGHT -- -- -- -- 685 685 19000 52 27400 73 -- -- 40 (MIN) 40 (MIN) -40-99 -40-99 STARTING -- -- 1090 -- -- -- -- -- -40 (MIN) ACCELERATION -- 68.4 850 38500 102.6 2420 110 -- 0-99 MAX. REVERSE 600 49.2 780 38100 101.5 2100 95.5 85-105 0-99 Propeller and Propeller Hartzell HC-B3TN-3D hub, T10282 + 4 blades Limits Diameter: Max. 106 in. Min. 100 in. Pitch Setting: Low 18 o Reverse 8 o Feather 90o at 30 in. Station Airspeed Limits V ne (Never exceed) 164 m.p.h. I.A.S. (142 knots) VA (Maneuvering) 131 m.p.h. I.A.S. (114 knots) 1A16 14 of 34 Model 164D (cont’d) C.G. Range G-164D (+120.5) to (+123.6) at 6300 lb. (+120.5) to (+125.0) at 4000 lb. Straight line variation between points G-164D (with 73" GAP) (+120.8) to (+122.8) at 6300 lb. (+120.8) to (+123.6) at 4000 lb Straight line variation between points Empty weight C.G. Range None. Datum +81.1 in. ahead of firewall bulkhead. Leveling Means Longitudinal: Leveling lugs welded on tubular fuselage frame 27 in. below upper longeron and forward lug at station 82.0, left hand side. No. of Seats 1 (+206) Maximum Hopper 4000 lb. (See Weight and Balance Data) Capacity Fuel Capacity 80 gal. (+112.5) With 73" Wing Gap 80 gal. (+112.7) Oil Capacity 2.8 gal. (+36.0) Serial No. Eligible S/N 1D and up Certification Basis CAR 8.10(a)(1) effective October 11, 1950, and CAM 8, Appendix B, as amended March 19, 1957 and applicable FAR 23 paragraphs. Amended Restricted Type Certificate No. 1A16 issued March 26, 1979. Date of application for Type Certificate Amendment May 23, 1977. Reissued to Schweizer Aircraft Corporation May 12, 1981. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see certification basis and CAM 8, Appendix B, subparagraph .51 and applicable FAR 23 paragraphs) must be installed in aircraft for certification. In addition, the following items of equipment are required: (a) Pre-stall warning indicator, (Safe Flight Instrument Corporation 24v P/N C-35407 or P/N 164-3) Installation per drawing A3011. (b) Fixed ballast installed at fuselage Sta 60.4 per drawing A5173 (Model G-164D with 73" wing gap) 1A16 15 of 34 DATA PERTINENT TO ALL MODELS Control Surface G- 164A, G-164B (through 708B), G-164C Movements (See G-164D Note 3) Ailerons 27 o (+3.5o -2o) Up 13 1/2 o (+ or -2o) Down Elevator 25 o (+ or -2o) Up 15 o (+ or -2o) Down Rudder 33 o (+ or -2o) Left 27 o (+ or -2o) Right (Respect to Fin) Elevator Trim Tab 18 o (+3o -2o) Up 13 o (+ or - 2o) Down G-164B, (S/N 709B and up) Ailerons 27 o (+3.5o -2o) Up 13 1/2 o (+ or -2o) Down Elevator 25 o (+ or -2o) Up 15 o (+ or -2o) Down Rudder 30 o (+ or -2o) Left 30 o (+ or -2o) Right (Respect to Fin) Elevator Trim Tab 18 o (+3o -2o) Up 13 o (+ or - 2o) Down G-164B-15T, -34T, -20T Ailerons 27 o (+3.5o -2o) Up 13 1/2 o (+ or -2o) Down Elevator 25 o (+ or -2o) Up 15 o (+ or -2o) Down Rudder 18 o (+0 or -1o) Left 30 o (+ or -2o) Right (Respect to Fin) Elevator Trim Tab 18 o (+3o -2o) Up 13 o (+ or - 2o) Down G-164D Ailerons 27 o (+3.5o -2o) Up 13 1/2 o (+ or -2o) Down Elevator 25 o (+ or -2o) Up 15 o (+ or -2o) Down Rudder 14 o (+0 or -1o) Left 27 o (+ or -2o) Right (Respect to Fin) Elevator Trim Tab 18 o (+3o -2o) Up 13 o (+ or - 2o) Down Production Basis Production Basis - Production Certificate No. 101 Notice: Aircraft with the letter "E" prefix on the serial no., ie. E1B, were manufactured under license in Ethiopia. These aircraft are not eligible for certification in the United States. Notice: Prior to Revision 15, dated August 21, 1978, there was a single set of NOTES for all models. From Revision 15 and up each model has a separate set of NOTES. Pilots Operating G-164B - S/N 549B and subsequent. Handbook Required G-164B-15T, G-164B-34T, and G-164B-20T G-164C - S/N 43C and subsequent. G-164D - S/N 1D and subsequent. NOTES PERTINENT TO MODEL G-164 NOTE 1 Current weight and balance report including lists of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include unusable residual fluids of: R985: System Oil 14.5 lb. (+90.0) Unusable Fuel 1.8 lb. (+123.0) All other engines: System Oil 6.5 lb. (+80.0) Unusable Fuel 1.8 lb. (+123.0) 1A16 16 of 34 NOTE 2 The following placards must be displayed: for G-164 (a) In front of and in clear view of the pilot: (1) "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY." (2) "NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED." (3) "WINTER FRONT MUST BE INSTALLED IF OAT IS BELOW 35 oF. AND REMOVED IF OAT EXCEEDS 60oF." (Continental W-670 and Gulf Coast W-670-240 engines only). "WHEN WINTER FRONT IS INSTALLED AIRCRAFT MUST BE OPERATED IN ACCORDANCE WITH COLD WEATHER OPERATING INSTRUCTIONS FURNISHED AS PART OF THE WINTER FRONT INSTALLATION." (4) When McCauley propeller Models 41D5926 and D1093 are installed the following placard must be displayed: "AVOID CONTINUOUS OPERATION BETWEEN 1500 AND 1650 RPM." (5) When Continental W-670-240 engine is installed the following pl acard must be displayed: "THIS AIRCRAFT SHALL NOT BE OPERATED OVER CONGESTED AREAS AND IS NOT ELIGIBLE FOR A WAIVER TO CONDUCT SUCH OPERATIONS." (6) "FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G (7) With Item 1 or 2 propeller installed: "WEIGHT AND C.G. RANGE: Maximum Weight (a) W-670-240 engine, 9.7 o blade angle: 3,750 lb. for sprayer or duster (b) Jacobs R-755 engine, 3,750 lb. for sprayer or duster (c) All other engines: (except R-985) Configuration Prop Pitch Weight Sprayer 9 1/2 o 3700 lb. Sprayer 9 o, 10o, 10.5o or 11o 3350 lb. Duster 9 1/4 o 2600 lb. Duster 9 o, 10o, 10.5o or 11o 3450 lb. C. G. Range (+122.0) to (+124.0) at 3750 lb. (+122.0) to (+125.3) at 2460 lb. Straight line variation between points. (8) With Item 3 propeller (Ref. NOTE 6) installed: (9) With Item 4 propeller installed: "Maximum Weight and C.G. Range (+122.0) to (+124.0) at 3750 lb. (+122.0) to +125.3) at 2460 lb." Straight line variation between points. (10) When Jasco 12 volt alternator is installed the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 45 AMPS MAXIMUM." 1A16 17 of 34 Note 2 for (11) When Jasco 24 volt alternator is installed the following placard must be displayed: G-164 "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 35 AMPS MAXIMUM." (12) "SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT." (13) Adjacent to fuel control valve: (1) Aircraft S/N 1 through 400 with R-985 series powerplant "32.7 gal. usable capacity - 80/87 Minimum Octane" (Standard Tank) "46.0 gal. usable capacity - 80/87 Minimum Octane" (Optional Tank) (2) Aircraft S/N 1 through 400 with all other powerplants "32.7 gal. usable capacity - 80 Minimum Octane" (Standard Tank) "46.0 gal. usable capacity - 80 Minimum Octane" (Optional Tank) (a) On hopper compartment near filler opening: "MAXIMUM HOPPER CAPACITY 1200 LB." (S/N 1 through 300) "MAXIMUM HOPPER CAPACITY 2000 LB" (S/N 301 and Up) (b) Adjacent to hopper emergency dump cable: "EMERGENCY DUMP CABLE - PULL TO DUMP LOAD" (c) Printed on safe-flight battery shield: "DRY BATTERIES POWERING THIS UNIT MUST BE DATED AND REPLACED EVERY SIX MONTHS" NOTE 3 When the W-670-240 engine is installed, this airplane shall not be operated over congested areas and is not eligible for waiver to conduct special purpose operations over densely populated areas, and in congested airlanes, or in the vicinity of busy airports conducting passenger transport operations. NOTE 4 Approved in Patrolling and/or Surveying configuration without normally exposed portions of the dust and spray equipment, but with the hopper remaining installed, at the same gross weights, center of gravity range and powerplant limitations as presently applied to the Agricultural Configuration aircraft. NOTE 5 When the aircraft is operating with approved 7AA Flight Manual dated April 17, 1959, revised July 29, 1960, March 7, 1961, and September 6, 1961, placards in NOTE 2, Nos. (a)(6) and (a)(7) need not be displayed and placard Nos. (a)(1) and (a)(4) must be modified as follows: (a) (1) "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN ACCORDANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND FAA APPROVED MANUAL." (a) (4) "WINTER FRONT MUST BE INSTALLED IF OAT IS BELOW 35 oF AND REMOVED IF OAT EXCEEDS 60oF." (Continental W-670 series engines only) NOTE 6 (a) Jacobs R-755-A2M, R-755-A2M1, R-755-B2M, L-4M or L-4MB engine eligible for installation with short mount Gulfstream Drawing A1681, carburetor air filter box and funnel Gulfstream Drawing A1667 and Gulfstream (Sensenich) Model J5404/MA96K propeller in accordance with "LIST OF GULFSTREAM G-164 DRAWINGS. APPLICABLE TO JACOBS R-755 (SHORT MOUNT) P.P. KITS" Revised 12-2-63. 1A16 18 of 34 NOTE 6 for (b) Static r.p.m. at Maximum Permissible Throttle Setting : G-164 (No additional tolerance permitted). Jacobs L-4M or L-4MB Not over 2010, not under 2010. Jacobs R-755-B2M Not over 2080, not under 2050 Jacobs R-755-A2M and -A2M1 Not over 2090, not under 1990 (c) Jacobs L-4MB engines must be modified for dual magneto ignition. (d) Left exhaust in accordance with Gulfstream ECO's S 164-1455,S164-1456 and S164-1457 all dated 4-13-64 is eligible as optional equipment. (e) Alternate right hand and/or left hand carburetor heat muffs per Gulfstream Drawing A1691 and ECO's S164-1526 dated 1-18-65. NOTE 7 Optional 46.3 gallon fuel tank eligible for installation per Gulfstream Drawing A1775. NOTES PERTINENT TO MODEL G-164A NOTE 1 Current weight and balance report including lists of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include unusable residual fluids of: R985 and R-1340 series: System Oil 14.5 lb. (+90.0) Unusable Fuel 1.8 lb. (+123.0) All other engines: System Oil 6.5 lb. (+80.0) Unusable Fuel 1.8 lb. (+123.0) NOTE 2 The following placards must be displayed: (a) In front of and in clear view of the pilot: (1) Aircraft S/N 401 through 1570, 1572 through 1582 and 1584 through 1615: "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY." (2) Aircraft S/N 401 through 1570, 1572 through 1582 and 1584 through 1615: MAXIMUM AIRSPEEDS S/N 401 and up with R-985 powerplant only and S/N 526 and up with R-985 or R-1340 powerplant only. NEVER EXCEED 147 MPH CAS (128 Knots) ABRUPT MANEUVERS 117 MPH CAS (102 Knots) MAXIMUM AIRSPEEDS S/N 401 and up with R-985 powerplant only and S/N 526 and up with R-985 or R-1340 powerplant only. NEVER EXCEED 131 MPH CAS (114 Knots) ABRUPT MANEUVERS 104 MPH CAS (90 Knots) (3) Aircraft S/N 401 through 1570, 1572 through 1582 and 1584 through 1615: "NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED." 1A16 19 of 34 NOTE 2 for (4) Aircraft S/N 401 through 1570, 1572 through 1582 and 1584 through 1615: G-164A "FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" (5) When Jasco 12 volt alternator is installed, the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 45 AMPS MAXIMUM." (6) When Jasco 24 volt alternator is installed, the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 35 AMPS MAXIMUM." (7) Aircraft S/N 526 through 1175: Adjacent to wobble pump handle when R-1340 series engines are installed. "EMERGENCY HAND WOBBLE FUEL PUMP MAINTAIN 3 TO 6 PSI FUEL PRESSURE." (8) Aircraft S/N 1571, 1583, and 1616 up (R-985 Only): "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS." THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 147 MPH CAS (128 Knots) ABRUPT MANEUVERS 117 MPH CAS (102 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND PACIFIC PROPELLER AG-100-2 BLADES INSTALLED ON R-985 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+125.4) AT 4500 LBS. (+122.0) TO (+125.4) AT 2970 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A2815-1) (9) Aircraft S/N 1571, 1583 and 1616 up (R-1340 only): "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. "FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" 1A16 20 of 34 NOTE 2 for MAXIMUM AIRSPEEDS: G-164A NEVER EXCEED 147 MPH CAS (128 Knots) ABRUPT MANEUVERS 117 MPH CAS (102 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. WITH HAMILTON STANDARD 12D40 PROPELLER HUB AND PACIFIC PROPELLER AG-100-2 BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+124.0) AT 4500 LBS. (+120.3) TO (+125.3) AT 3300 LBS. THROUGH 3525 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A2815-2) (b) Adjacent to fuel control valve: Aircraft S/N 401 and up with R-985 series powerplant and S/N 526 and up with R-1340 series powerplant. "46.0 gal. usable capacity - 80/87 minimum octane (Standard Tank) 64.0 gal. usable capacity - 80/87 minimum octane (Standard Tank plus two Optional wing tanks)" 80.0 gal. usable capacity - 80/87 minimum octane (Standard Tank plus two Optional wing tanks)" (c) On hopper compartment near filler opening: "MAXIMUM HOPPER CAPACITY 2000 LB." (d) Adjacent to hopper emergency dump cable: "EMERGENCY DUMP CABLE - PULL TO DUMP LOAD" (e) Printed on safe-flight battery shield: "DRY BATTERIES POWERING THIS UNIT MUST BE DATED AND REPLACED EVERY SIX MONTHS" (f) On tail ballast used with R-1340 powerplant installation: "Ballast - 54 lb. - Do Not Remove" (Aircraft S/N 526 through 1683) "Ballast - 51 lb. - Do Not Remove" (Aircraft S/N 1684 and Up) (g) Near entrance door: "RESTRICTED AGRICULTURAL AIRCRAFT" (h) On control stick lock A/C S/N 1686, 1695 and up "CONTROL LOCK/PARKING BRAKE WITH FLIGHT CONTROLS LOCKED, DEPRESS PEDALS FOR PARKING BRAKE, PARKING BRAKES OFF WHEN CONTROL LOCK STOWED" (i) Adjacent to oil heat control A/C S/N 1726 and up: "OIL HEAT - SHALL BE OFF FOR TAKEOFF" (j) When JASCO 24 volt alternator is installed the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 35 AMPS MAXIMUM" 1A16 21 of 34 NOTE 2 for (k) Stenciled on the inside of the baggage compartment door S/N 1571, 1583 and 1616 and up: G-164A "B AGGAGE COMPARTMENT 25 LBS. - SECURED LIMIT" (l) Located above the windshield: "WARNING - 3 POINT READING OF FUEL GAUGE NOT ACCURATE. READ IN LEVEL FLIGHT ONLY" (m) Located above the right hand window: "DO NOT OPEN RH WINDOW IN FLIGHT" (n) Located on the battery box cover (When 24V electrical system is installed) S/N 1701 and up: "TWIN 12V BATTERIES IN SERIES - OUTPUT 24 VOLTS" (o) Above the strobe light switch (When optional strobe lights are installed): WARNING: TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FIGHT THROUGH CLOUDS, FOG OR HAZE" (p) Located in the step hole on the left side of the fuselage below the cockpit. (When optional auxiliary power receptacle is installed): "24 VOLT STARTER POWER (NEG. GRD)" (q) Located on the right side of the cockpit. (When optional spray system is installed): "FAN BRAKE - PULL TO LOCK." (r) Located on the spray/spreader control handle adjustable limit stop rod. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO CLOSE" (s) Located on the fan brake lever mounting bracket. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO OPEN" NOTE 3 Optional 18 gal. wing tanks eligible on S/N 401 and up when installed per Gulfstream Wing Modification Drawing A2003 and fuel Tank Installation Drawing A1730. NOTE 4 All R-985 Series Engine Installations S/N 401 through 458 made per Gulfstream Short Mount Drawing A1692. S/N 401 through 458 eligible for Long Mount Installation. NOTE 5 Gulfstream Exhaust System G88-42005-75 eligible for all R-1340 installations per Gulfstream Installation Drawing A1550. NOTE 6 Optional 8.7 gallon oil tank with integral hopper is eligible for installation on Model G-164A using R-985 or R-1340 engines installed on long engine mounts per Gulfstream Drawing A1360. (Note eligible for installation with R-985 engine in short engine mount). NOTE 7 All engines listed for the model G-164 are eligible for installation on Model G-164A. The model G- 164 limits, placards, weights and other data apply (See G-164 data and NOTES). NOTES PERTINENT TO MODEL G-164B NOTE 1 Current weight and balance report including lists of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include unusable residual fluids and fixed ballast: R-975, R985 and R-1340 series: System Oil 14.5 lb. (+90.0) Unusable Fuel 1.8 lb. (+123.0) 1A16 22 of 34 NOTE 1 for PT6A-15AG, PT6A-34AG, and PT6A-20B G-164B Unusuable Fuel 10.0 lb (+116.8) Fixed Ballast: PT6A-15AG, -34AG, & -20B xxx lb (+92.8) PT6A-15AG & -34AG xxx lb (+46.5) PT6A-20B xxx lb (+45.8) (use actual weight stamped on wts) NOTE 2 The following placards must be displayed: (a) In front of and in clear view of the pilot: (1) R-985 Engine through S/N 548B "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY." FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" MAXIMUM AIRSPEEDS: NEVER EXCEED 147 MPH CAS (128 Knots) ABRUPT MANEUVERS 117 MPH CAS (102 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND AG-100-2 BLADES INSTALLED ON R-985 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+125.0) AT 4500 lb. (+122.0) TO (+125.0) AT 3130 lb. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3615-1) (2) R-975-46/PA2 Engine through S/N 548B "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS." THIS AIRCRAFT SHALL NOT BE OPERATED OVER CONGESTED AREAS AND IS NOT ELIGIBLE FOR A WAIVER TO CONDUCT SUCH OPERATIONS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 147 MPH CAS (128 Knots) ABRUPT MANEUVERS 117 MPH CAS (102 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. 1A16 23 of 34 NOTE 2 for ALTITUDE LOSS IN STALL RECOVERY 200 FT. G-164B WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND PACIFIC PROPELLER AG-100-2 BLADES INSTALLED ON R-975 ENGINE, AVOID CONTINUOUS OPERATION BETWEEN 1300 AND 1450 RPM. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+124.8) AT 4500 LBS. (+122.0) TO (+124.8) AT 3170 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3616-1) (3) R-1340 Engine through S/N 548B "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. "FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" MAXIMUM AIRSPEEDS: NEVER EXCEED 147 MPH CAS (128 Knots) ABRUPT MANEUVERS 117 MPH CAS (102 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 12D40 PROPELLER HUB AND PACIFIC PROPELLER AG-100-2 BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+124.0) AT 4500 LBS. (+122.0) TO (+124.0) AT 3300 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3818-1) (4) R-985 Engine S/N 549B and Up "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND PILOT'S OPERATING HANDBOOK. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. "FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 145 MPH CAS (126 Knots) ABRUPT MANEUVERS 116 MPH CAS (101 Knots) 1A16 24 of 34 NOTE 2 for NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. G-164B WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND 6101A-12 BLADES OR PACIFIC PROPELLER AG-100-2/OR -45 BLADES INSTALLED ON R-985 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+125.0) AT 4500 LBS. (+122.0) TO (+125.0) AT 3170 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3615-3) (5) R-975 Engine S/N 549B and Up "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND PILOT'S OPERATING HANDBOOK. THIS AIRCRAFT SHALL NOT BE OPERATED OVER CONGESTED AREAS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" MAXIMUM AIRSPEEDS: NEVER EXCEED 145 MPH CAS (126 Knots) ABRUPT MANEUVERS 116 MPH CAS (101 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND AG-100-4S BLADES INSTALLED ON R-975 ENGINE. AVOID CONTINUOUS OPERATION BETWEEN 1300 AND 1450 RPM. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+124.8) AT 4500 LBS. (+122.0) TO (+124.8) AT 3170 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3615-3) (6) R-1340 Engine S/N 549B through 694B "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND PILOT'S OPERATING HANDBOOK. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. "FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" 1A16 25 of 34 NOTE 2 for MAXIMUM AIRSPEEDS: G-164B NEVER EXCEED 145 MPH CAS (126 Knots) ABRUPT MANEUVERS 116 MPH CAS (101 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND 610A-12 BLADES OR PACIFIC PROPELLER AG-100-2/ OR4S BLADES OR HAMILTON STANDARD 22D40 PROPELLER HUB AND PACIFIC PROPELLER AG-200-4S BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+125.4) AT 4500 LBS. (+122.0) TO (+125.4) AT 3625 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3618-3) (7) R-1340 Engine S/N 695 through 708B "THIS AIRCRAFT CERTIFICATED UNDER CAR 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND PILOT'S OPERATING HANDBOOK. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G" MAXIMUM AIRSPEEDS: NEVER EXCEED 145 MPH CAS (126 Knots) ABRUPT MANEUVERS 116 MPH CAS (101 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND 610A-12 BLADES OR PACIFIC PROPELLER AG-100-2/ OR4S BLADES OR HAMILTON STANDARD 22D40 PROPELLER HUB AND PACIFIC PROPELLER AG-200-4S BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+124.0) AT 4500 LBS. (+122.0) TO (+124.0) AT 3300 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3618-5) (8) R-1340 Engine S/N 709B and Up "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND PILOT'S OPERATING HANDBOOK. 1A16 26 of 34 NOTE 2 for R-1340 Engine S/N 709B and Up (cont’d) G-164B THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 145 MPH CAS (126 Knots) ABRUPT MANEUVERS 116 MPH CAS (101 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND 610A-12 BLADES OR PACIFIC PROPELLER AG-100-2/ OR4S BLADES OR HAMILTON STANDARD 22D40 PROPELLER HUB AND PACIFIC PROPELLER AG-200-4S BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+125.5) AT 5200 LBS. (+122.0) TO (+125.5) AT 3625 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3618-9) (9) R-985 Engine S/N 752B and Up THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND PILOT'S OPERATING HANDBOOK. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 145 MPH CAS (126 Knots) ABRUPT MANEUVERS 116 MPH CAS (101 Knots) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 2D30 PROPELLER HUB AND 610A-12 BLADES OR PACIFIC PROPELLER AG-100-2/ OR 4S BLADES INSTALLED ON R-985 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+126.0) AT 5200 LBS. (+122.0) TO (+126.0) AT 3100 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A3615-5) 1A16 27 of 34 NOTE 2 for (10) PT6A-15AG & PT6A-34AG, and PT6A-20B Engine G-164B THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 157 MPH IAS ABRUPT MANEUVERS 125 MPH IAS MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+122.0) TO (+125.7) AT 3500 LBS (+122.0) TO (+125.5) AT 5200 LBS. ALTITUDE LOSS IN STALL RECOVERY 200 FT. MAXIMUM OPERATING ALTITUDE 13,000 FT. NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. OPERATION IN VISIBLE MOISTURE CONDITIONS BELOW IAT OF 7oC OR IN PROXIMITY OF THUNDERSTORMS PROHIBITED. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A7618-3) (b) When Jasco 12 volt alternator is installed, the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 45 AMPS MAXIMUM" (c) When Jasco 24 volt alternator is installed, the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TEST TO 35 AMPS MAXIMUM" (d) Adjacent to fuel control valve: (1) R-985 and R-1340 "46.0 gal. usable capacity - 80/87 minimum octane (Standard Tank) 64.0 gal. usable capacity - 80/87 minimum octane (Standard Tank plus one Optional wing tank) 80.0 gal. usable capacity - 80/87 minimum octane (Standard Tank plus two Optional wing tanks)" 120.0 Gal usable fuel capacity 80/87 octane (S/N 828B and up eligible (2) R-975-46/PA2 "46.0 gal. usable capacity - 100 minimum octane (Standard Tank) 64.0 gal. usable capacity - 100 minimum octane (Standard Tank plus one Optional wing tank) 80.0 gal. usable capacity - 100 minimum octane (Standard Tank plus two Optional wing tanks)" (3) PT6A-15AG and -34AG, and PT6A-20B 80 gal. usable capacity - Jet A/Jet A-1/Jet B or Diesel grades DF1 or DF2. 120.0 Gal. usable fuel capacity - Jet A/JetA1/Jet B or Diesel Grades DF1 or DF2. (s/n 828B and up eligible) 1A16 28 of 34 NOTE 2 for G-164B (e) On hopper compartment near filler opening: "MAXIMUM HOPPER CAPACITY 2000 LB." (f) Adjacent to hopper emergency dump cable: (through S/N 659B) (S/N 752B and up with R-985 Eng.) "EMERGENCY DUMP CABLE - PULL TO DUMP LOAD" (g) Printed on safe-flight battery shield: "DRY BATTERIES POWERING THIS UNIT MUST BE DATED AND REPLACED EVERY SIX MONTHS" (h) On side of fuselage: "RESTRICTED AGRICULTURAL AIRCRAFT" (i) On control lock stick A/C S/N 138B, 142B, 177B through S/N 510B: "CONTROL LOCK/PARKING BRAKE WITH FLIGHT CONTROLS LOCKED DEPRESS PEDALS FOR PARKING BRAKE. PARKING BRAKE OFF WHEN CONTROL LOCK STOWED" (j) Adjacent to parking brake control S/N 511B and up.: "PARKING BRAKE: TO BE OFF PRIOR TO LANDING TO LOCK: PRESS PEDAL, PULL AND HOLD CONTROL TO UNLOCK: PRESS PEDAL, OR RELEASE CONTROL" (k) Adjacent to oil heat control A/C S/N 335B through S/N 659B "OIL HEAT - SHALL BE OFF FOR TAKEOFF" (l) Stenciled on the inside of the baggage compartment door: "BAGGAGE COMPARTMENT 25 LBS. - SECURED LIMIT" (m) Located above the right hand window: "DO NOT OPEN RH WINDOW IN FLIGHT" (n) Located on the battery box cover. (When optional 24V electrical system is installed): "TWIN 12V BATTERIES IN SERIES - OUTPUT 24 VOLTS" (o) Above the strobe light switch (When optional strobe lights are installed): "WARNING - TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT THROUGH CLOUDS, FOG OR HAZE" (p) Located above the windshield: "WARNING - 3 POINT READING OF FUEL GAUGE NOT ACCURATE. READ IN LEVEL FLIGHT ONLY" (q) Located in the step hole on the left side of the fuselage below the cockpit. (When optional auxiliary power receptacle is installed): "24 VOLT STARTER POWER (NEG. GRD.)" (r) Located on the right side of the cockpit (When optional spray system is installed): "FAN BRAKE - PULL TO LOCK" (s) Located on the spray/spreader control handle adjustable limit stop rod. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO CLOSE" (t) Located on the fan brake lever mounting bracket. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO OPEN" (u) Located on magneto switch bracket when locking tail wheel is installed): "TAIL WHEEL MUST BE LOCKED FOR TAKEOFF AND LANDING" 1A16 29 of 34 NOTE 2 for (v) Located on dust gate control stick (S/N 660B and up): (R-1340 ENG.) G-164B "EMERGENCY DUMP-PUSH TO DUMP LOAD" (w) On optional fixed tail ballast used with 73" wing gap: "BALLAST ___________LBS. -DO NOT REMOVE" (Aircraft S/N 709B and Up) (x) Located on left side panel adjacent to fuel valve control. (PT6A-15AG, PT6A-34AG, and PT6A-20B) CAUTION AUTOMOTIVE DIESEL FUEL APPROVED FOR AGRICULTURAL OPERATIONS WITH THE FOLLOWING RESTRICTIONS: AUTOMOTIVE DIESEL FUEL PERMITTED WHEN FREE AIR TEMPERATURE IS ABOVE: +5oC FOR GRADE DF-2 -4oC FOR GRADE DF-1 (y) Located on upper left hand side of instrument panel (PT6A-15AG, PT6A -34AG, and PT6A-20B Engine) WARNING DO NOT USE REVERSE POWER IN FLIGHT, USE REVERSE POWER ONLY ON LANDING ROLL OR TAXI WHEN TAIL WHEEL IS HELD FIRMLY ON THE GROUND. (z) Located on instrument panel adjacent to IAT Gauge (PT6A-15AG, PT6A-34AG, and PT6A-20B Engine) WARNING PX-PY HEAT SHALL BE TURNED ON FOR FLIGHT AND GROUND OPERATIONS WHEN IAT IS BELOW 6oC. (aa) Stenciled to the right of the fuel fill cap on the top of the center section fuel tank and near the fuel control valve: (PT6A-15AG, PT6A-34AG, and PT6A-20B Engine). 80 GAL. USABLE CAP. JETA/JET A-1/JET B OR DIESEL GRADES DF1 OR DF2. With optional 120 gal. fuel capacity: "120 GAL USABLE CAPACITY JET A/JET A1/JET B OR DIESEL GRADES DF-1 OR DF-2" (ab) On fixed ballast at STA 46.5 used with PT6A-15AG & -34AG engine and at Sta. 45.8 with PT6A-20B Engine (BALLAST WEIGHT "DO NOT REMOVE" "WEIGHT___________LBS." (ac) On fixed ballast at Sta 92.8 with PT6A-15AG, -34AG and -20B engine, "BALLAST WEIGHT - DO NOT REMOVE. WEIGHT LBS." (ad) Stenciled to the right of the fuel fill cap on top of centersection fuel tank and near fuel control valve: (with optional 120 gal. fuel capacity, R-985 & R-1340, S/N 828B & up) "120 GAL. USABLE CAP. 80/87 OCTANE" (ae) Stenciled to the right of the fuel fill cap on top of centersection fuel tank and near fuel control valve: "46.0 gal usable capacity - 80/87 octane (standard tank) 64.0 gal usable capacity - 80/87 octane (standard tank plus one optional wing tank) 80.0 gal usable capacity - 80/87 octane (standard tank plus two optional wing tanks)" 1A16 30 of 34 164B (cont’d) NOTE 3 Optional 18 gal. wing tanks eligible on S/N 1B through 659B when installed per Gulfstream Wing Modification Drawing A2003 and Fuel Tank Installation Drawing A1730. NOTE 4 Gulfstream Exhaust System C88-42005-75 eligible for all R-1340 installations per Gulfstream Installation Drawing A1550. NOTE 5 73" Wing Gap eligible on S/N 1B through 708B with R1340 installations when reworked in accordance with Schweizer Retrofit Kits, Drawing Nos. A7175-1 or -3 (Wing) and 7175-5 (Vertical Tail) NOTE 6 Optional 120 gal. fuel system eligible on R-985, R-1340, PT6A-15AG, PT6A-34AG, and PT6A- 20B, S/N 828B & up. NOTES PERTINENT TO MODEL G-164C NOTE 1 Current weight and balance report including lists of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include unusable residual fluids of: System Oil 14.5 lb. (+72.0) Unusable Fuel 1.8 lb. (+123.0) NOTE 2 The following placards must be displayed: (a) In front of and in clear view of the pilot: (1) Through S/N 42C "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS AND MARKINGS." THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 147 MPH CAS (128 KNOTS) ABRUPT MANEUVERS 117 MPH CAS (102 KNOTS) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 12D40 PROPELLER HUB AND AG-100-2 BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+121.0) TO (+123.5) AT 6300 LBS. (+121.0) TO (+125.2) AT 4400 LBS. Straight line variation between points. SULPHER DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A5618-1) 1A16 31 of 34 NOTE 2 for (2) S/N 43C AND UP G-164C "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND PILOT'S OPERATING HANDBOOK. THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G MAXIMUM AIRSPEEDS: NEVER EXCEED 139 MPH IAS (121 KNOTS) ABRUPT MANEUVERS 112 MPH IAS (97 KNOTS) NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. ALTITUDE LOSS IN STALL RECOVERY 200 FT. WITH HAMILTON STANDARD 12D40 HUB AND 6101A-12 BLADES OR PACIFIC PROPELLER AG-100-2/4S BLADES INSTALLED ON R-1340 ENGINE. MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+121.0) TO (+123.5) AT 6300 LBS. (+121.0) TO (+125.2) AT 4400 LBS. Straight line variation between points. SULPHUR DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (P/N A5618-3) (b) When Jasco 24 volt alternator is installed, the following placard must be displayed: "THE ALTERNATOR IN THIS ELECTRICAL SYSTEM ONLY TESTED TO 35 AMPS MAXIMUM" (c) Adjacent to fuel control valve: 80.0 GAL. USABLE CAPACITY - 80/87 MINIMUM OCTANE (d) On hopper compartment near filler opening: "MAXIMUM HOPPER CAPACITY 4000 LB." (e) Adjacent to hopper emergency dump cable: "EMERGENCY DUMP CABLE - PULL TO DUMP LOAD" (f) Printed on safe-flight battery shield: "DRY BATTERIES POWERING THIS UNIT MUST BE DATED AND REPLACED EVERY SIX MONTHS" (g) Near entrance door: "RESTRICTED AGRICULTURAL AIRCRAFT" (h) Adjacent to parking brake control (A/C 1C through 37C) "PARKING BRAKE TO BE OFF PRIOR TO LANDING TO LOCK: PRESS PEDAL, PULL AND HOLD CONTROL TO UNLOCK: PRESS PEDAL, OR RELEASE CONTROL" (I) Adjacent to oil heat control A/C 1C through 37C) "OIL HEAT - SHALL BE OFF FOR TAKEOFF" 1A16 32 of 34 NOTE 2 for (j) Stenciled on the inside of the baggage compartment door: G-164C "B AGGAGE COMPARTMENT 25 LBS. - SECURED LIMIT" (k) Located above the windshield: "WARNING - 3 POINT READING OF FUEL GAUGE NOT ACCURATE. READ IN LEVEL FLIGHT ONLY" (l) Located on the top of the hopper aft fairing: "HYDRAULIC BRAKE RESERVOIR FILL TO MARK ON STICK" (m) Located above the right hand window: "DO NOT OPEN RH WINDOW IN FLIGHT" (n) Located on the battery box cover. (When optional 24V electrical system is installed): "TWIN 12V BATTERIES IN SERIES - OUTPUT 24 VOLTS" (o) Above the strobe light switch (When optional strobe lights are installed): "WARNING - TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT THROUGH CLOUDS, FOG OR HAZE" (p) Located in the step hole on the left side of the fuselage below the cockpit. (When optional auxiliary power receptacle is installed): "24 VOLT STARTER POWER (NEG. GRD.)" (q) Located on the right side of the cockpit (When optional spray system is installed): "FAN BRAKE - PULL TO LOCK" (r) Located on the spray/spreader control handle adjustable limit stop rod. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO CLOSE" (s) Located on the fan brake lever mounting bracket. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO OPEN" NOTE 3 Gulfstream Exhaust System G88-42005-75 eligible for all R-1340 installations per Gulfstream Installation Drawing A5510. NOTES PERTINENT TO MODEL G-164D AND G-164D (WITH 73" GAP) NOTE 1 Current weight and balance report including lists of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include unusable residual fluids of: Unusable Fuel 2.0 lb. (+123.0) NOTE 2 The following placards must be displayed: (a) In front of and in clear view of the pilot: "THIS AIRCRAFT CERTIFICATED UNDER PART 8 AS A SPECIAL PURPOSE AGRICULTURAL AIRCRAFT AND MUST BE OPERATED IN COMPLIANCE WITH OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND PILOTS OPERATING HANDBOOK." THIS AIRCRAFT APPROVED FOR DAY VFR FLIGHT ONLY. FLIGHT LOAD FACTORS: MAX. POSITIVE LOAD FACTOR +4.2G MAX. NEGATIVE LOAD FACTOR -1.0G 1A16 33 of 34 NOTE 2 for G-164D MAXIMUM AIRSPEEDS: NEVER EXCEED 164 MPH IAS ABRUPT MANEUVERS 131 MPH IAS G-164D MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+121.0) TO (+123.5) AT 6300 LBS. (+121.0) TO (+125.2) AT 4000 LBS. Straight line variation between points. G-164D (With 73" GAP) MAXIMUM WEIGHT AND C.G. RANGE (INCHES FROM DATUM) (+120.8) TO (+122.8) AT 6300 LBS. (+120.6) TO (+123.6) AT 4000 LBS. Straight line variation between points. ALTITUDE LOSS IN STALL RECOVERY 200 FT. MAXIMUM OPERATING ALTITUDE 13,000 FT NO ACROBATIC OR INVERTED MANEUVERS, INCLUDING SPINS, APPROVED. OPERATION IN VISIBLE MOISTURE CONDITIONS BELOW IAT OF 7oC OR IN PROXIMITY OF THUNDERSTORMS PROHIBITED. SULPHER DUSTING IS PROHIBITED UNLESS SPECIAL FIRE PREVENTION MEASURES HAVE BEEN INCORPORATED IN THE AIRCRAFT" (b) On lower RH instrument panel: "CAUTION - AUTOMOTIVE DIESEL FUEL APPROVED FOR AGRICULTURAL OPERATION WITH THE FOLLOWING RESTRICTIONS: Automotive diesel fuel permitted when free air temperature is above +5oC FOR GRADE DF-2 -4oC FOR GRADE DF-1 (c) Secured to the upper right hand side of the instrument panel: "WARNING - DO NOT REVERSE POWER IN FLIGHT, USE REVERSE POWER ONLY ON LANDING ROLL OR TAXI WHEN TAILWHEEL IS HELD FIRMLY ON THE GROUND. "WARNING - Px-Py HEAT SHALL BE TURNED ON FOR FLIGHT AND GROUND OPERATIONS WHEN IAT IS BELOW 6oC" (d) Secured to the lower left hand instrument panel: "PARKING BRAKE to BE OFF PRIOR TO LANDING TO LOCK: PRESS PEDAL, PULL AND HOLD CONTROL TO UNLOCK: PRESS PEDAL, OR RELEASE CONTROL" (e) Stenciled on the left hand side of the hopper: MAXIMUM HOPPER CAPACITY - 4000 LBS." (f) Stenciled to the right of the fuel fill cap on the top of the center section fuel tank and near the fuel control valve: "80 GAL. USABLE CAP. JET A/JET A-1/JET B OR DIESEL GRADES DF1 OR DF2" (h) Stenciled on the inside of the baggage compartment door: "BAGGAGE COMPARTMENT 25 LBS. - SECURED LIMIT" 1A16 34 of 34 NOTE 2 for (i) Adjacent to hopper emergency dump cable: G-164D "EMERGENCY DUMP CABLE - PULL TO DUMP LOAD" (j) Near entrance door: "RESTRICTED AGRICULTURAL AIRCRAFT" (k) Located on the battery box cover. “TWIN 12V BATTERIES IN SERIES - OUTPUT 24 VOLTS" (l) Above the strobe light switch (When optional strobe lights are installed): "WARNING - TURN OFF STROBE LIGHTS WHEN TAXIING IN VICINITY OF OTHER AIRCRAFT OR DURING FLIGHT THROUGH CLOUDS, FOG OR HAZE" (m) Located above the windshield. "WARNING - 3 POINT READING OF FUEL GAGE NOT ACCURATE. READ IN LEVEL FLIGHT ONLY" (n) Located on the top of the hopper aft fairing: "HYD. BRAKE RESERVOIR FILL TO MARK ON STICK" (o) Located above the right hand window: "DO NOT OPEN RH WINDOW IN FLIGHT" (p) Located in the step hole on the left side of the fuselage below the cockpit. (When optional auxiliary power receptacle is installed): "24 VOLT STARTER POWER (NEG. GRD.)" (q) Located on the right side of the cockpit (When optional spray system is installed): "FAN BRAKE - PULL TO LOCK" (r) Located on the spray/spreader control handle adjustable limit stop rod. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO CLOSE" (s) Located on the fan brake lever mounting bracket. (When optional spray system is installed): "SPRAY PUMP INTAKE VALVE - PULL TO OPEN" (t) G-164D (With 73" Gap) "BALLAST 68 LB. AT FUS. STA. 60.4 DO NOT REMOVE" NOTE 3 Rudder motion (relative to neutral) - position must be 14 o + or -2o left and 27o+ or -2o right. Neutral position is actually 3o right - Rudder measured from aircraft center line. .....END.... ``` ## ADs (25, in force first) - [AD 2023-08-07](https://openairdocs.org/ad/2023-08-07): Propeller Controlling System · Allied Ag Cat Productions G-164A and G-164B with STC SA7546SW or 4 others. Effective Jun 21, 2023 - [AD 2011-05-07](https://openairdocs.org/ad/2011-05-07): Stabilizers · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Mar 17, 2011 - [AD 2007-17-02](https://openairdocs.org/ad/2007-17-02): Fuel shut-off valve control · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Sep 18, 2007 - [AD 89-18-02 R1](https://openairdocs.org/ad/89-18-02-R1): Elevator Push-Pull Rods · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Nov 24, 1989 - [AD 82-13-06](https://openairdocs.org/ad/82-13-06): Aileron Bellcrank Inspection · Allied Ag Cat Productions G-164B, G-164B-15T, G-164B-20T and 5 more. Effective Jul 5, 1982 - [AD 73-19-10](https://openairdocs.org/ad/73-19-10): Elevator Control Horn · Allied Ag Cat Productions G-164A, G-164B, G-164B-15T and 3 more. Effective Aug 29, 1979 - [AD 78-23-11](https://openairdocs.org/ad/78-23-11): Aileron Balance Cables · Allied Ag Cat Productions G-164, G-164A, G-164B and 5 more. Effective Feb 28, 1979 - [AD 78-26-03](https://openairdocs.org/ad/78-26-03): Wing Fittings Corrosion Detection · Allied Ag Cat Productions G-164, G-164A, G-164B and 4 more. Effective Dec 20, 1978 - [AD 77-19-05](https://openairdocs.org/ad/77-19-05): Flying Wire Terminals · Allied Ag Cat Productions G-164A, G-164B, G-164B-15T and 3 more. Effective Sep 22, 1977 - [AD 75-14-04](https://openairdocs.org/ad/75-14-04): Rudder Cables · Allied Ag Cat Productions G-164, G-164A, G-164B and 4 more. Effective Jul 7, 1977 - [AD 77-13-04](https://openairdocs.org/ad/77-13-04): Placard-Brake Warning · Allied Ag Cat Productions G-164A, G-164B, G-164B-15T and 3 more. Effective Jun 29, 1977 - [AD 76-13-10](https://openairdocs.org/ad/76-13-10): Landing Gear Strut · Allied Ag Cat Productions G-164 and G-164A. Effective Nov 30, 1976 - [AD 76-21-03](https://openairdocs.org/ad/76-21-03): Main Landing Gear Struts · Modified landing gear (Frenco STC SA647WE). Effective Oct 20, 1976 - [AD 66-27-06](https://openairdocs.org/ad/66-27-06): Right-Hand Elevator Torque Tubes · Allied Ag Cat Productions G-164 and G-164A. Effective Dec 16, 1975 - [AD 72-02-02](https://openairdocs.org/ad/72-02-02): Fuel Line Fitting Leakage · Allied Ag Cat Productions G-164A. Effective Oct 18, 1972 - [AD 67-29-04](https://openairdocs.org/ad/67-29-04): Elevator Forward Pushrod · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Oct 27, 1967 - [AD 67-09-04](https://openairdocs.org/ad/67-09-04): Control Surface Lock · Allied Ag Cat Productions G-164 and G-164A. Effective Mar 24, 1967 - [AD 66-01-02](https://openairdocs.org/ad/66-01-02): Propeller Cone and Spacer Sets · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Dec 28, 1965 - [AD 63-22-02](https://openairdocs.org/ad/63-22-02): Throttle Control Pivot Bolt · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Oct 26, 1963 - [AD 63-22-01](https://openairdocs.org/ad/63-22-01): Spray Pump Fan Blades · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Oct 25, 1963 - [AD 63-01-01](https://openairdocs.org/ad/63-01-01): Engine Mount Washers · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Jan 5, 1963 - [AD 62-08-07](https://openairdocs.org/ad/62-08-07): Aileron Control Cable Modification · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Apr 25, 1962 - [AD 2008-22-21](https://openairdocs.org/ad/2008-22-21) (historical): Main tubular spar · Allied Ag Cat Productions G-164, G-164A, G-164B and 7 more. Effective Dec 19, 2008 - [AD 82-07-04](https://openairdocs.org/ad/82-07-04) (historical): Fuel Shutoff Valve Modification · Allied Ag Cat Productions G-164A, G-164B, G-164B-15T and 6 more. Effective Apr 6, 1982 - [AD 78-08-09](https://openairdocs.org/ad/78-08-09) (historical): Rudder Assembly · Allied Ag Cat Productions G-164, G-164A, G-164B and 4 more. Effective Apr 21, 1978 ## Registered aircraft by registry model (OpenAirDocs) - [Grumman Acft ENG Cor-Schweizer G-164B](https://openairdocs.org/model/grumman-acft-eng-cor-schweizer-g-164b): 157 aircraft (registry code 3952802) - [Grumman Acft ENG Cor-Schweizer G-164A](https://openairdocs.org/model/grumman-acft-eng-cor-schweizer-g-164a): 150 aircraft (registry code 3952801) - [Grumman G-164A](https://openairdocs.org/model/grumman-g-164a): 63 aircraft (registry code 3952704) - [Schweizer G-164B](https://openairdocs.org/model/schweizer-g-164b): 56 aircraft (registry code 8059055) - [Grumman G-164](https://openairdocs.org/model/grumman-g-164): 52 aircraft (registry code 3952702) - [Gulfstream-Schweizer A/C GULFSTREAM AM G-164B](https://openairdocs.org/model/gulfstream-schweizer-a-c-gulfstream-am-g-164b): 33 aircraft (registry code 3979904) - [Grumman Acft ENG Cor-Schweizer G-164C](https://openairdocs.org/model/grumman-acft-eng-cor-schweizer-g-164c): 18 aircraft (registry code 3952803) - [Grumman American Avn. G-164B](https://openairdocs.org/model/grumman-american-avn-g-164b): 6 aircraft (registry codes 3960203, 3960204) - [Ag-Cat G-164B](https://openairdocs.org/model/ag-cat-g-164b): 5 aircraft (registry code 1260000) - [Grumman American Avn. G-164](https://openairdocs.org/model/grumman-american-avn-g-164): 3 aircraft (registry code 3960201) - [Grumman American Avn. G-164A](https://openairdocs.org/model/grumman-american-avn-g-164a): 3 aircraft (registry code 3960202) - [Gulfstream-Schweizer A/C GULFSTREAM AM G-164D](https://openairdocs.org/model/gulfstream-schweizer-a-c-gulfstream-am-g-164d): 3 aircraft (registry code 3979908) - [Schweizer G-164B-20T](https://openairdocs.org/model/schweizer-g-164b-20t): 3 aircraft (registry code 8059056) - [Grumman G-164B](https://openairdocs.org/model/grumman-g-164b): 2 aircraft (registry code 3952703) - [Grumman G164C](https://openairdocs.org/model/grumman-g164c): 2 aircraft (registry code 3950409) - [Grumman/Schweizer G-164D](https://openairdocs.org/model/grumman-schweizer-g-164d): 2 aircraft (registry code 3952804) - [Schweizer G164B-34T](https://openairdocs.org/model/schweizer-g164b-34t): 2 aircraft (registry code 8058057) - [Gulfstream Schweizer A/C GULFSTREAM AM G-164C](https://openairdocs.org/model/gulfstream-schweizer-a-c-gulfstream-am-g-164c): 1 aircraft (registry code 3979906) - [Schweizer G-164C](https://openairdocs.org/model/schweizer-g-164c): 1 aircraft (registry code 8059057) - [Schweizer G-164D](https://openairdocs.org/model/schweizer-g-164d): 1 aircraft (registry code 8059059) - [Schweizer G164A](https://openairdocs.org/model/schweizer-g164a): 1 aircraft (registry code 8059053) - [Grumman G-164B-15T](https://openairdocs.org/model/grumman-g-164b-15t): 0 aircraft (registry code 3952701) - [Grumman G-164D](https://openairdocs.org/model/grumman-g-164d): 0 aircraft (registry code 3952700) - [Schweizer G-164](https://openairdocs.org/model/schweizer-g-164): 0 aircraft (registry code 8059050) ## STCs approved under this data sheet (183, first 50) - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA1377GL](https://openairdocs.org/stc/SA1377GL): Replace existing Pratt & Whitney (P & W) Model R-985 or R-1340 reciprocating engine installation installation with P & W (Canada) turbopropeller engine (Model PT6A-6B, -11, -11AG, -15AG, -20, -20A, -20B, -6/C20, -21, -27, -28, -34, -34AG, or -135) and Hartzell propeller (Model HC-BJTN-3 Hub and Model T10282 (+4) or T10282(N) (+4) Blades). Hershey Flying and Spraying Service, Inc. - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA1102SO](https://openairdocs.org/stc/SA1102SO): Installation of a 360-gallon agricultural spray dispensing hopper. Texas Transland LLC - [STC SA1128SO](https://openairdocs.org/stc/SA1128SO): Installation of replacement fiberglass fuselage skin panels. Approval limited to serial number 1107 ONLY.. Texas Transland LLC - [STC SA1129SO](https://openairdocs.org/stc/SA1129SO): Installation of a 320 gallon agricultural spray dispensing hopper. Texas Transland LLC - [STC SA1131SO](https://openairdocs.org/stc/SA1131SO): Installation of replacement fiberglass fuselage skin panels. Texas Transland LLC - [STC SA01240SE](https://openairdocs.org/stc/SA01240SE): Installation of secondary voltage indication system. Visual Instruments LLC - [STC SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA02266SE](https://openairdocs.org/stc/SA02266SE): Installation of a Lever Throttle Quadrant. Kawak Aviation Technologies Inc - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings Inc. - [STC SA5783NM](https://openairdocs.org/stc/SA5783NM): Fabrication of Onboard Systems Model 7 CROPHAWK spray flow measuring system.. Onboard Systems International - [STC SA1151NW](https://openairdocs.org/stc/SA1151NW): Installation of the Flight Grip Model 135 Control Stick Grip. Air Products & Parts LLC - [STC SA00711CH](https://openairdocs.org/stc/SA00711CH): Install replacement tail landing gear spring described by Drawing 5480, rev. E, dated August 12, 1996, or later FAA approved revisions.. Hershey Flying Service Inc - [STC SA00881CH](https://openairdocs.org/stc/SA00881CH): Install rudder servo tab. Hershey Flying Service Inc. - [STC SA431CH](https://openairdocs.org/stc/SA431CH): Install replacement main landing gear spring (leg).. Hershey Flying Service Inc. - [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA01027CH](https://openairdocs.org/stc/SA01027CH): Installation of GE Aviation Czech s.r.o. Model M601E-11, M601D-11, H75-100, H75-200, H80, H80-100 and H80-200, Pratt & Whitney Canada Corp. Models PT6A-34, PT6A-34AG, PT6A-42 and PT6A-42AG, the AVIA Propeller Ltd. Models V510, V510AG and V508E-AG and Hartzell Propellers Models HC-B4TW-3, HC-B3TN-3AE and HC-B3TN-3 in accordance with Turbine Conversions Drawing List, Report 3000, Revision C, dated September 27, 2018, or later FAA approved revision.. Turbine Conversions Ltd - [STC SA01688WI](https://openairdocs.org/stc/SA01688WI): Installation of Pratt & Whitney R-985-AN14B or R-985-AN1 engine modified for fuel injection. A & L Aircraft Parts Inc - [STC SA5190NM](https://openairdocs.org/stc/SA5190NM): Installation of Gustin Aviation chip detector light system.. A & L Aircraft Parts Inc - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA1292NW](https://openairdocs.org/stc/SA1292NW): Installation of Blue Mountain Aviation Night Lights Kit (including instrument panel lights) for spraying. Blue Mountain Aero LLC - [STC SA02135SE](https://openairdocs.org/stc/SA02135SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data). Electronics International Inc. - [STC SA6070NM](https://openairdocs.org/stc/SA6070NM): Installation of a 'quick-disconnect drain plug' on the engine rocker sump for the oil drain retrieval system after engine shutdown.. West Coast Air Creations - [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation - [STC SA01406NY](https://openairdocs.org/stc/SA01406NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K017 on single and multi-engine fixed light aircraft and rotary wing. Airwolf Filter Corporation - [STC SA00009WI](https://openairdocs.org/stc/SA00009WI): Change belly skins from aluminum to stainless steel.. Hershey Flying Service Inc - [STC SA1754GL](https://openairdocs.org/stc/SA1754GL): Install aileron servo tabs. Hershey Flying Service Inc - [STC SA2226CE](https://openairdocs.org/stc/SA2226CE): Convert the vertical fin and rudder to the configuration of the Model G-164B (S/Ns above 708B). (G-164B S/N'S BELOW 709B). Hershey Flying Service Inc - [STC SA2254CE](https://openairdocs.org/stc/SA2254CE): Installation of replacement wing tips.. Hershey Flying Service Inc - [STC SA2271CE](https://openairdocs.org/stc/SA2271CE): Installation of additional wing fuel tanks.. Hershey Flying Service Inc - [STC SA2273CE](https://openairdocs.org/stc/SA2273CE): Installation of G-164B wings on aircraft previously modified by STC SA3645SW.. Hershey Flying Service Inc - [STC SA3645SW](https://openairdocs.org/stc/SA3645SW): Widen fuselage hopper in accordance with data listed on S & R Aircraft FAT-CAT Drawing List Revision J dated August 8, 1986. Limited to serial numbers 1B through 548B only.. Hershey Flying Service Inc - [STC SA5923SW](https://openairdocs.org/stc/SA5923SW): Installation of modifications to align the vertical control surface with airplane centerline.. Hershey Flying Service Inc - [STC SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [STC SA663GL](https://openairdocs.org/stc/SA663GL): To install a scavenge oil filter system in G-164A and G-164B aircraft with P&W R985 or R1340 engines.. Airwolf Filter Corp - [STC SA2486CE](https://openairdocs.org/stc/SA2486CE): Operation of airplane on water or alcohol (methanol) and water mixture injected into engine as a cooling agent.. Petersen Aviation Inc - [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley - [STC SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [STC SA01669CH](https://openairdocs.org/stc/SA01669CH): Installation of Challenger Reusable Air Filter. Challenger Aviation Products Inc. - [STC SA2015WE](https://openairdocs.org/stc/SA2015WE): The 12 volt 24 volt D.C. electrical generating system is replaced by an alternator system. Hartzell Engine Technologies, LLC - [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC ST03554CH](https://openairdocs.org/stc/ST03554CH): Installation of Rotary Gatekeeper and provisions equipment. Turbine Conversions Ltd - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. - [STC SA2444SW](https://openairdocs.org/stc/SA2444SW): Installation of P&WACL PT6A-34, -34AG, -15AG, -20A, -41, -41G, -36, -135, -135A, or -28 engine. Turbine Conversions Ltd All 183: https://openairdocs.org/tcds/1A16/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.