TCDS A-782

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-782 Revision 51 NAVION Navion (L-17A) Navion A (L-17B) (L-17C) Navion B Navion D Navion E Navion F Navion G Navion H March 18, 2003 AIRCRAFT SPECIFICATION NO. A-782 Type Certificate Holder Sierra Hotel Aero, Inc. 1690 Aeronca Ln, Fleming Field South St. Paul, MN 55075 Type Certificate Holder Record North American Aviation, Inc. to Ryan Aeronautical Company (TC last dated February 3, 1949) Ryan Aeronautical Company to Navion, Division of Tusco Corporation (TC last dated April 2, 1958) Navion, Division of Tusco Corporation to Base Industries, Incorporated (TC last dated May 5, 1961) Base Industries, Incorporated to Navion Aircraft Corporation on November 19, 1964 Navion Aircraft Corporation to Cedric R. Kotowicz on June 16, 1972 Cedric R. Kotowicz to Navion Rangemaster Corporation on October 14, 1972 Navion Rangemaster Corporation to Jimmie Thompson on February 14, 1979 Jimmie Thompson to Charles L. Klinger on January 13, 1982 Charles L. Klinger to Diamond Aero Enterprises, Inc. on June 17, 1982 Diamond Aero Enterprises, Inc. to Navion Holdings, Inc. on January 9, 1995 Navion Holdings, Inc. to Navion Aircraft Company, Ltd on January 22, 1998 Navion Aircraft Company, Ltd. to Navion Aircraft LLC on July 14, 2001 Navion Aircraft LLC to Sierra Hotel Aero, Inc. on March 18, 2003 Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 51 51 47 51 47 47 47 47 51 51 51 47 47 47 51 47 47 47 47 47 A-782 2 of 20 I - Model Navion (Army L-17A); 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved January 28, 1947 Engine Continental E-185-3 or -9 (See Item 139 for optional engine.) Fuel 80 min. octane aviation gasoline Engine limits For all operations, 2,300 r.p.m. (185 hp.) Airspeed limits Maneuvering 124 m.p.h. (108 K) True Ind. Maximum structural cruising 160 m.p.h. (139 K) True Ind. Never exceed 190 m.p.h. (165 K) True Ind. Flaps and gear extended 100 m.p.h. ( 87 K) True Ind. Propeller limits With Item 1(a)(1) installed: Diameter 84 in. max., 82.4 in. min. Static r.p.m. 2,000, operating pitch settings at 30 in. sta.; Low 14°, High 23°. C.G. range (gear down) (See NOTE 5 for C.G. range with altered horizontal stabilizer angle of incidence.) Utility - (+93.9) to (+104.9) Normal - (+98.1) to (+104.9) at 2,750 lb. (+93.9) to (+104.9) at 2,350 lb. or less Straight line variation between points given. Effect of retracted landing gear (+1,480 in. lb.) Empty weight C.G. range (+93.9 to (+95.3) rega rdless of category. Range is not valid for nonstandard arrangement except that it may be used when auxiliary fuel tank per Item 110(a) or (b) is installed but not when Item 110(e) is installed. When E.W.C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Maximum weight Normal - 2,750 lb. Utility - 2,350 lb. No. seats 4 (2 at +96 and 2 at +132) Maximum baggage 180 lb. (+159) Fuel capacity 39.5 gal. (+103). See Item 110 for auxiliary fuel tank installation Oil capacity 10 qt. (+39) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 45° Stabilizer Fixed Serial Nos. eligible NAV-4-2 and up Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 1(a), 1(b), 102(a), 103(a), 104(a), 105, 106(a) or (b), 201, 202, 302, 401(a). II - Model Navion A (Army L-17B and L-17C); 4 PCLM (Normal Category), 2 PCLM (Utility Category), Approved February 3, 1949 (Same as Model Navion except for engine installation and revised fuel system) Model Navion airplanes may be converted to Model Navion A by installing the following: (1) Continental E-185-3 or -9 engine which is eligible for 205 hp. takeoff rating. (2) Fuel system in accordance with Ryan Dwg. 145-948021 or 154-948001 (Item 113). Airplanes serial numbers 1566 and 1628 and subsequent were equipped with these items when delivered. Engine Continental E-185-3 or -9 Only engines serial numbers 5122 and up are eligible for the one minute 2600 r.p.m. (205 hp.) takeoff rating, and these engines must have dampered crankshafts. (Suffix "D" to the engine serial number indicates dampered crankshafts.) (See Item 139 for optional engine.) Fuel 80 min. octane aviation gasoline Engine limits Takeoff (one min.), 2,600 r.p.m. (205 hp.) Maximum continuous, 2,300 r.p.m. (185 hp.) Airspeed limits Maneuvering 124 m.p.h. (108 K) True Ind. Maximum structural cruising 160 m.p.h. (139 K) True Ind. Never exceed 190 m.p.h. (165 K) True Ind. Flaps and gear extended 100 m.p.h. ( 87 K) True Ind. 3 of 20 A-782 Propeller limits With Item 1(a)(1) installed: Diameter 84 in. max., 82.4 in. min. Static r.p.m. 2,300, operating pitch settings at 30 in. sta.: Low 10.5°, High 23°. With Item 1(a)(2) installed: Diameter 84 in. max., 82.4 in. min. Static r.p.m. 2,325, operating pitch settings at 30 in. sta.: Low 12.5°, High 24.5° C.G. range (gear down) (See NOTE 5 for C.G. range with altered horizontal stabilizer angle of incidence.) Utility - (+93.9) to (+104.9) Normal - (+98.1) to (+104.9) at 2,750 lb. (+93.9) to (+104.9) at 2,350 lb. or less Straight line variation between points given. Effect of retracted landing gear (+1,480 in. lb.) Empty weight (+93.9 to (+95.3) regardless of category. Range is not valid for nonstandard arrangement except that it may be used when auxiliary fuel tank per Item 110(a) or (b) is installed but not when Item 119 is installed. When E.W.C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Maximum weight Normal - 2,750 lb. Utility - 2,350 lb. No. seats 2 (+96) and 2 (+132) Maximum baggage 180 lb. (+159) Maximum baggage permissible in Army L-17B and L-17C aircraft is 167 lb. at +159 due to the weight of radio equipment installed in these models. This is a structural limitation, and the full 180 lb. of baggage may be carried if the extra radio equipment is removed. Fuel capacity 39.5 gal. (+103). See Item 110 for auxiliary fuel tank installations. Army L-17B aircraft were equipped with Item 110(c) when delivered, increasing the fuel capacity for those aircraft to 59.9 gal. Oil capacity 10 qt. (+39) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 45° Stabilizer Fixed Serial Nos. eligible NAV-4-2 and up Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 1(a), 1(b), 102(a), 103(a), 104(a), 106(a) or (b), 113, 201, 202, 302, 401(b) or (c) depending on whether Item 409 is installed. III - Model Navion B; 4 PCLM (Normal Category), 1 PCLM (Utility Category), Approved March 13, 1950 Engine Lycoming GO-435-C2 (See Item 139 for optional engine) Fuel 91/98 min. octane grade aviation gasoline. 80/87 min. octane when equipped with modified M-4-5 Marvel-Schebler carburetors, Part No. 10-3391-1, and cowl flap extensions specified in Ryan Service Bulletin No. 20 dated March 17, 1953. Airplane Flight Manual revision, Item 401(1), required with 80/87 grade fuel. Engine limits Takeoff (2 minutes), 3,400 r.p.m. (260 hp.) Maximum continuous, 3,000 r.p.m. (240 hp.) Airspeed limits Maneuvering 124 m.p.h. (108 K) True Ind. Maximum structural cruising 169 m.p.h. (147 K) True Ind. Never exceed 190 m.p.h. (165 K) True Ind. Flaps and gear extended 100 m.p.h. ( 87 K) True Ind. C.G. range (gear down) (See NOTE 4 for C.G. range with altered horizontal stabilizer angle of incidence.) Utility - (+93.9) to (+103.5) Normal - (+98.1) to (+103.5) at 2,850 lb. (+93.9) to (+103.5) at 2,350 lb. or less Straight line variation between points given. Effect of retracted landing gear (+1,480 in. lb.) A-782 4 of 20 Empty weight C.G. range None. Maximum weight Normal Category - 2,850 lb. Utility Category - 2,350 lb. No. seats 2 at (+96) and 2 at (+132) Maximum baggage 180 lb. (+159) Fuel capacity 39.5 gal. (+103). See Item 110 for auxiliary fuel tank installations. Item 110(b) is installed at the factory. Oil capacity 12 qt. (+29.5) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 40° Stabilizer Fixed Serial Nos. eligible NAV-4-2B and up (Suffix "B" to the manufacturer's serial no. indicates eligibility as a Model Navion B.) Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 4 or 5, 102(b), 103(b), 104(b), 106(b) or (d), 127, 128, 201, 202, 302, 401(e) or (f). IV - Model Navion D; 4 PCLM (5th Place Optional), (Normal Category), Approved April 2, 1958 Engine Continental O-470-P Fuel 91/96 min. grade aviation gasoline. Engine limits Takeoff (5 minutes), 2,600 r.p.m. (240 hp.) Maximum continuous, 2,600 r.p.m. (240 hp.) Airspeed limits Maneuvering 132 m.p.h. (115 K) True Ind. Maximum structural cruising 169 m.p.h. (147 K) True Ind. Never exceed 198 m.p.h. (172 K) True Ind. Flaps extended 105 m.p.h. ( 91 K) True Ind. Gear extended 100 m.p.h. ( 87 K) True Ind. C.G. range (gear down) (+98.0) to (+103.4) at 3,150 lb. (+93.4) to (+103.4) at 2,350 lb. Straight line variation between points given. Effect of retracted landing gear (+1,467 in. lb.) Empty weight C.G. range None. Maximum weight 3,150 lb. No. seats 2 (+96) and 2 (+132) or (3 (+132) optional) Maximum baggage 180 lb. (+159) Fuel capacity 39.5 gal. (+103), 68 gal. (+107) Oil capacity 12 qt. total, 9 qt. usable (+32) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 40° Stabilizer Fixed Serial Nos. eligible NAV-4-2 and up Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 13, 101(e), 102(c) or (d), 103(c), 104(c), 106(b) or (d), 110(h), 113(c), 122(b), 129(b), 301(d), 302(b), 401(o) 5 of 20 A-782 V - Model Navion E; 4 or 5 PCLM, (Normal Category), Approved May 22, 1959 Engine Continental IO-470-C Fuel 91/96 min. grade aviation gasoline. Engine limits Takeoff (5 minutes), 2,600 r.p.m. (250 hp.) Maximum continuous, 2,600 r.p.m. (250 hp.) Airspeed limits Maneuvering 132 m.p.h. (115 K) True Ind. Maximum structural cruising 169 m.p.h. (147 K) True Ind. Never exceed 198 m.p.h. (172 K) True Ind. Flaps extended 105 m.p.h. ( 91 K) True Ind. Gear extended 100 m.p.h. ( 87 K) True Ind. C.G. range (gear down) (+98.0) to (+103.4) at 3,150 lb. (+93.9) to (+103.4) at 2,350 lb. Straight line variation between points given. Empty weight C.G. range None. Maximum weight 3,150 lb. No. seats 4 or 5 (2 at +96 and 2 at +132) or (2 at +96 and 3 at +132) Maximum baggage 180 lb. (+159) Fuel capacity 39.5 gal. (+103), 68 gal. (+107) Oil capacity 12 qt. total, 9 qt. usable (+32) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 40° Stabilizer Fixed Serial Nos. eligible NAV-4-2 and up Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 14, 101(f), 102(c) or (d), 103(c), 104(c), 106(b) or (d), 110(i), 122(b), 127(b), 129(b), 138, 301(d), 302(b), 401(p) VI - Model Navion F; 4 or 5 PCLM, (Normal Category), Approved September 23, 1959 Engine Continental IO-470-H (See NOTE 6 for required structural modification) Fuel 100/130 min. grade aviation gasoline. Engine limits Takeoff (5 minutes), 2,625 r.p.m. (260 hp.) Maximum continuous, 2,625 r.p.m. (260 hp.) Airspeed limits Maneuvering 132 m.p.h. (115 K) True Ind. Maximum structural cruising 169 m.p.h. (147 K) True Ind. Never exceed 198 m.p.h. (172 K) True Ind. Flaps extended 105 m.p.h. ( 91 K) True Ind. Gear extended 100 m.p.h. ( 87 K) True Ind. C.G. range (gear down) (+98.0) to (+103.4) at 3,150 lb. (+93.9) to (+103.4) at 2,350 lb. Straight line variation between points given. Empty weight C.G. range None. Maximum weight 3,150 lb. No. seats 4 or 5 (2 at +96 and 2 at +132) or (2 at +96 and 3 at +132) Maximum baggage 180 lb. (+159) Fuel capacity 39.5 gal. (+103), 68 gal. (+107) Oil capacity 12 qt. total, 9 qt. usable (+32) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 40° Stabilizer Fixed Serial Nos. eligible NAV-4-2 and up (See NOTE 6 for required structural modification.) Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 15, 101(f), 102(c) or (d), 103(c), 104(c), 106(b) or (d), 110(i), 122(b), 127(b), 129(b), 138, 301(d), 302(b), 401(q). A-782 6 of 20 VII - Model Navion G; 5 PCLM, (Normal Category), Approved May 5, 1961 Engine Continental IO-470-H Fuel 100/130 min. grade aviation gasoline Engine limits Takeoff (5 minutes), 2,625 r.p.m. (260 hp.) Maximum continuous, 2,625 r.p.m. (260 hp.) Airspeed limits Maneuvering 132 m.p.h. (115 K) True Ind. (See NOTE 7) Maximum structural cruising 169 m.p.h. (147 K) True Ind. Never exceed 198 m.p.h. (172 K) True Ind. Flaps extended 105 m.p.h. ( 91 K) True Ind. Gear extended 130 m.p.h. (113 K) True Ind. C.G. range (gear down) (+99.0) to (+103.4) at 3,315 lb. (+93.9) to (+103.4) at 2,350 lb. Straight line variation between points given. Empty weight C.G. range None. Maximum weight Takeoff - 3,150 lb. (See NOTE 7) Landing - 3,150 lb. No. seats 5 (2 at +96 and 2 at +132, and 1 at +164) Maximum baggage 176 lb. (+164) See NOTE 2(i) Fuel capacity 39.5 gal. (+103), 68 gal. (+107) Oil capacity 12 qt. total, 9 qt. usable (+32) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 40° Stabilizer Fixed Serial Nos. eligible NAV-4-2351G and up (For NAV 4-2351 through 2497 See NOTE 7) Required equipment In addition to the pertinent basic equipment specified in CAR 3, the following items of equipment must be installed: 15(a), (b), (c); 101(g); 102(c) or (d); 103(c); 104(c); 106(b), (d), or (e); 110(i); 122(b); 127(b); 129(b); 138; 301(d) or (e); 302(b), (c), or (d); 401(s) or (u). VIII - Model Navion H; 5 PCLM, (Normal Category), Approved June 5, 1967 Engine Continental IO-520-B, See Item 142 for optional engine. Fuel 100/130 min. grade aviation gasoline Engine limits Takeoff (5 minutes), 2,700 r.p.m. (285 hp.) Maximum continuous, 2,700 r.p.m. (285 hp.) Airspeed limits Maneuvering 135 m.p.h. (117 K) True Ind. Maximum structural cruising 169 m.p.h. (147 K) True Ind. Never exceed 203 m.p.h. (176 K) True Ind. Flaps extended 108 m.p.h. ( 94 K) True Ind. Gear extended 130 m.p.h. (113 K) True Ind. C.G. range (gear down) (+99.0) to (+103.4) at 3,315 lb. (+93.9) to (+103.4) at 2,350 lb. Straight line variation between points given. Empty weight C.G. range None. Maximum weight Takeoff - 3,315 lb. Landing - 3,150 lb. No. seats 5 (2 at +96 and 2 at +132, and 1 at +164) Maximum baggage 176 lb. (+164) See NOTE 2(i) Fuel capacity 39.5 gal. (+103), 68 gal. (+107) Oil capacity 12 qt. total, 9 qt. usable (+32) Control surface movements Elevator Up 30° Down 20° Elevator tab Up 25° Down 30° Rudder (measured from centerline of fin chord): Right 23° Left 17° Aileron Up 25° Down 17° Flaps Down 40° Stabilizer Fixed Serial Nos. eligible NAV-4-2500H, NAV 4-2500T, and up Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 16(a), (b), and (c) or 17(a), (b), and (c); 101(g); 102(c) or (d); 103(c); 104(c); 106(b), (d), or (e); 110(i); 122(b); 127(b); 129(b); 138(b); 301(d) or (e); 302(b), (c), or (d); 401(v). 7 of 20 A-782 Specifications Pertinent to All Models Datum Fuselage station 0, located 93.25 in. forward of the forward bolt centerline (jig point), wing lower surface bolting angle. Leveling means External lugs on right side of fuselage at stations 58 and 89.43. Certification basis Type Certificate No. 782 (CAR 3 effective November 13, 1945); Model D, E, and F wing, landing gear and flight test requirements (CAR 3 effective May 15, 1956); Model G and H, all except power plant (CAR 3 effective May 15, 1956). Applied for Type Certificate November 5, 1945. Production basis None. Prior to original certification, an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the technical data and a check of the flight characteristics. Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An item marked with an asterisk may not have been manufactured under an FAA monitored or approved quality control system. Conformity must be determined if the item is not identified by a Form FAA-186, PMA, or other evidence of an FAA production approval. Propellers and Propeller Accessories Eligible Model 1. (a) Propeller - Hartzell, variable pitch, hub Model Navion HC-12X20-1, -5, -7, 7B, or -7C and either: (For interchangeable blades, see NOTE 6 Navion of Propeller Spec. P-845) Navion A (1) Blade Model 8428, or 62 lb. (+7) as noted (2) Blade Model 8433 (to be used only with engines 65 lb. (+7) having dampered crankshafts. Suffix "D" to the engine serial number indicates dampered crankshafts.) Minimum clearance between the propeller hub spider and the propeller control piston Jack Plate should be 1/16 inch for the -1 and -5 propellers, and 1/8 inch for the -7 propellers. On the -7 propellers, this clearance must be determined by observation while the engine is running. Low pitch stop is on the control lever per Ryan Dwg. No. 145-44054 for the -1 and -5 propellers and on Ryan Dwg. No. 145-44060 for -7 propellers. The propeller counterweight length required with the above is as follows: Airplane Propeller Counterweight Model T.O. Hp. Item Length Navion 185 1(a)(1) 4 1/2 in.* Navion 185 1(a)(2) 4 1/8 in. Navion A 205 1(a)(1) 4 5/16 in. Navion A 205 1(a)(2) 4 1/8 in. *On Model Navion airplanes equipped with propeller Item 1(a)(1), and having Continental E-185-3 engines, serial nos. 4389-D through 5110-D, or engines which have been equipped with Tri-metal front main bearing inserts and bronze thrust washers at overhaul, the counterweight length must be adjusted in accordance with Ryan Field Service Bulletin No. 5 unless the rework outlined in Continental Motors Corp. Service Bulletin No. M48-30 has been accomplished. (b) Propeller control - Manual control for hydraulic 2 lb. (+56) unit on Hartzell Propellers, Ryan Dwg. No. 145-43020 (for Hartzell HC-12X20-1 and -5 propellers.) A-782 8 of 20 2. (a) Propeller - Koppers Aeromatic, variable pitch, hub 53 lb. (+7) Navion model 220 or 220-1, blade model O-85 Navion A Limits: as noted Model Navion: Diameter 85 in. max., 83.3 in. min. Static r.p.m. 2,200, operating pitch settings at 30 in. sta: Low 13.3°, high 27° Model Navion A: Diameter 85 in. max., 83.3 in. min. Static r.p.m. 2,500, operating pitch settings at 30 in. sta: Low 10.2°, high 27° Minimum allowable clearance between the propeller thrust plate and the thrust bracket screws is 0.094 in. when propeller blades are held in the full low pitch position and the control is in the full forward position. (See Koppers' approved "installation Procedure and Operating Limitations" No. 23.) (b) Altitude compensator - Koppers Aeromatic Model 11 lb. (+14) 4349-C, Ryan Dwg. 145-89100. When this item is installed on Model Navion aircraft, approved operating instructions covering operation with this item must be included in the Approved Operating Limitations (Airplane Flight Manual). (The Flight Manual page contained in Koppers' approved "Installation Procedure and Operating Limitations" No. 23 covers these instructions.) 3. Propeller - Hartzell, two-position automatic, hub model 64 lb. (+6) Navion HC-52X20-1, blades m odel 8433-0. as noted Eligible on model Navion with E- 185-3 engine having serial no. 5122D Eligible Model and above only. Low pitch blade angle meas ured at 30 in. sta. 17.7°. Pitch range 6° equivalent to 3/16 in. gap between adjusting screws and high pitch stop. Count erweight length 3 5/8 in. Low to high pitch trip r.p.m. 2,450, high to low pitch latch r.p.m. not less than 1,700. Item 401(d), Operating Limitations Supplement, must be added to 401(a) when this propeller is installed. 4. Propeller - Koppers Strato-Cruise, va riable pitch, hub model 220H, Navion B blades model O-93, with No. 4390 pitch control assy. Diameter 93 in. Static r.p.m. at maximum permissible throttle setting: Not over 3,300, not under 3,200. No additional tolerance permitted. Operating pitch settings at 30 in. sta: Low 14° to 14.5°, control 16°, high 29.7°. Koppers' "Adjustment Instructions and Operating Limitations No. 60" pertains to the use of this propeller on Navion B airplanes. 5. Propeller, Hartzell, variable pitch, hub mode l HC-12X20-8C, blades 76 lb. (+7) Navion B model 9333C, including control. Reference Ryan Dwg. 146-44002. Diameter 93 in. max., 91.2 in. min. Static r.p.m. at maximum permissible throttle setting: Not over 3,250, not under 3,150. No additional tolerance permitted. Operating pitch settings at 30 in. sta: Low 16.5°, high 31.5°. Propeller counterweight length is 4.25 in. See Hartzell Installation Instructions for this propeller. Minimum clearance between the propeller hub spider and the propeller control piston Jack Plate should be 1/ 16 in. This clearance must be determined by observation while the engine is running. Low pitch stop is shown on Ryan Dwg. No. 146- 44002. Placard required: "Avoid Continuous Ground Operation Betw een 1,675 and 2,150 Engine R.P.M." 6. Propeller spinner, Hartzell Model D-164. Eligible on Hartzell HC-12X20 3 lb. (+7) Noted propeller. Hartzell "Installation and Service Instructions" dated January 6, 1951, pertains to the us e of this spinner on Navion B aircraft. 9 of 20 A-782 7. Propeller - Hartzell, constant speed, hub model HC-12X20-7 Navion or -8 series, and either: Navion A (a) Blade model 8433 eligible on model Navion (185 hp. 65 lb. (+7) as noted for T.O.) and model Navion A (205 hp. for T.O.)