TCDS A-717

Page No. 1 2 3 4 5 6 7 Rev. No. 7 7 7 6 7 7 6 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-717 Revision 7 HOWARD DGA-15P (Army UC-70; Navy GH-1, GH-2, GH-3, NH-1) DGA-15J (Army UC-70B) DGA-15W August 17, 2009 AIRCRAFT SPECIFICATION NO. A-717 Holder of Type Certificate: Howard Aircraft Foundation P.O. Box 649 Washington, OK 73093 Type Certificate Holder Record: Jobmaster Co. transferred ownership to Howard Aircraft December 10, 2003. I - Model DGA-15P (Army UC-70; Navy GH-1, GH-2, GH-3, NH-1), 5 PCLM, Approved Feb. 20, 1940 See NOTE 2 regarding conversion of military models. Engine P & W Wasp Jr. SB with one 4 1/2N and one 9N damper. See Item 113 for optional engines. Fuel 80 min. grade aviation gasoline. 87 min. grade for takeoff at 450 hp. Engine limits Maximum continuous, (Sea level) 34.5 in. Hg., 2200 rpm (400 hp) (Straight line manifold pressure variation with altitude to 5000 ft.) 33.5 in. Hg., 2200 rpm (400 hp) Takeoff (one minute), (80 grade fuel) 34.5 in. Hg., 2200 rpm (400 hp) (87 grade fuel) 36.5 in. Hg., 2300 rpm (450 hp) Airspeed limits Level flight or climb 200 mph (174 knots) True Ind. Glide or dive 270 mph (235 knots) True Ind. Flaps extended 108 mph ( 94 knots) True Ind. C.G. range (+10.5) to (+21.8) Empty weight C.G. range Not available Maximum weight Serials 500 to 574: 4350 lbs. (These serials eligible at 4500 lbs. when oil cooler, Item 105c, air scoop installation, Howard Dwg . E-215, and revised stabilizer screw, Howard Dwg. C-138, are installed. Serials 701 and up: 4500 lbs. (See Item 222 for increased wgts.) No. seats 5 (two at +14 and three at +56). See Item 401 for six-seat arrangement, and Item 402 for eight seat arrangement. Maximum baggage 125 lbs. (+84). Compartment aft of rear seats. Fuel capacity 151 gals. max. Three tanks in fuselage. See Item 206 for individual tank capacities (standard and optional). Oil capacity 8 gals. (-30) Control surface movements Elevators 26° Up 22° down (measured from centerline of stabilizer when chord line of stabilizer is parallel to thrust line) Rudder 28° right 28° left Rudder tab 19° right 19° left (Item 601) Ailerons 26° up 21° down Stabilizer 2° up 4° down (Serials 500 to 574) 2° up 9° down (Serials 701 and up) Wing flaps 45° down A-717 Page 2 of 7 Serial Nos. eligible 500 to 574, 701 and up, and all AAF and Navy serial numbers. Use manufacturer's model and serial number when converting from military to civil status. (See Notes A & 2) Required equipment In addition to the pertinent require d basic equipment specified in CAR 4(a) the following items of equipment must be installed: Items 101(a), 102, 103(a), (c), (d) or (e), 105(a) or (c) (Serial Nos. 500 to 574), 105(c) (Serial Nos. 701 and up); 106(a), (b) or (c), 107(a) or (b), 108, 109(a) and (b) or (d), 110 and 111. II - Model DGA-15J (Army UC-70B); 5 PCLM, Approved Feb. 20, 1940 See NOTE 2 regarding conversion of military model. Engine Jacobs L-6MB Fuel 80 min. grade aviation gasoline. Engine limits Maximum continuous, (Sea level) 24.5 in. Hg., 2100 rpm (300 hp) (Straight line manifold pressure variation with altitude to 3700 ft.) 23.5 in. Hg., 2100 rpm (300 hp) Takeoff (one minute), 26.0 in Hg., 2200 rpm (330) Airspeed limits Level flight or climb 190 mph ( 165 knots) True Ind. Glide or dive 261 mph ( 227 knots) True Ind. Flaps extended 108 mph ( 94 knots) True Ind. C.G. range (+10.5) to (+21.8) Empty weight C.G. range Not available Maximum weight 4350 lbs. No. seats 5 (two at +14 and three at +56). Maximum baggage 125 lbs. (+84). Compartment aft of rear seats. Fuel capacity 151 gals. max. Three tanks in fuselage. See Item 206 for individual tank capacities (standard and optional). Oil capacity 8 gals. (-30) Control surface Elevators 28° Up 22° down (measured from centerline of stabilizer when chord line of stabilizer is parallel to thrust line). Rudder 28° right 28° left Ailerons 24° up 21° down Stabilizer 2° up 4° down Wing flaps 45° down Serial Nos. eligible 500 to 574, 701 and up, and all AAF and Navy serial numbers. Use manufacturer's model and serial number when converting from military to civil status. (See Notes A & 2) Required equipment In addition to the pertinent require d basic equipment specified in CAR 4(a) the following items of equipment must be installed: Items 101(b), 102, 103(b), 104(b), 105(b), 106, 107(a) 108, 109(a) and (c), 110 and 111. III - Model DGA-15W, 5 PCLM, Approved Feb. 3, 1941 Engine Wright R760-E2 Fuel 80 min. grade aviation gasoline. Engine limits Maximum continuous, 2200 RPM (320 HP) Takeoff (one minute), 2400 rpm (350) Airspeed limits Level flight or c limb 190 mph ( 165 knots) True Ind. Glide or dive 261 mph ( 227 knots) True Ind. Flaps extended 108 mph ( 94 knots) True Ind. C.G. range (+10.5) to (+21.8) Empty weight C.G. range Not available Maximum weight 4350 lbs. No. seats 5 (two at +14 and three at +56). Maximum baggage 125 lbs. (+84). Compartment aft of rear seats. Fuel capacity 151 gals. max. Three tanks in fuselage. See Item 206 for individual tank capacities (standard and optional). Oil capacity 8 gals. (-30) Page 3 of 7 A-717 Control surface Elevators 28° Up 22° down (measured from centerline of stabilizer when chor d line of stabilizer is parallel to thrust line) Rudder 28° right 28° left Ailerons 24° up 21° down Stabilizer 2° up 4° down Wing flaps 45° down Serial Nos. eligible 500 to 574, 701 and up, and all AAF and Navy serial numbers. Use manufacturer's model and serial number when converting from military to civil status. (See Notes A & 2) Required equipment In addition to the pertinent require d basic equipment specified in CAR 4(a) the following items of equipment must be installed: Items 101(b) and (c), 102, 103(b), 104(c), 105(b), 106, 107(a) 108, 109(a) and (b), 110 and 111. Specifications Pertinent to All Models Datum Leading edge of wing Leveling means Bottom longeron under stabilizer Certification basis Type Certifi cate No. 717 (CAR 4a requirements) Production basis None. Prior to original certifica tion of any aircraft manufactured subsequent to November 7, 1944, a FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved 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 lis ted 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 a FAA monitored or approved quality control system, and therefore conformity must be determined if the item is not identified by a Form FAA-186, PMA or other evidence of FAA production approval. Propellers and Propeller Accessories DGA-15P DGA-15J DGA-15W 101. Propeller (a) Ham. Std. hub 2D30 with: 152 lbs. (-64) ----- ----- Blades 6167-15 or 6167-16 Dia.: Max. 8' 3-1/8" Min. allowable for repairs 8' 7/8". No further reduction permitted. Low pitch setting 10.5° or Blades 6101-21 or 6101-22 152 lbs. (-64) ----- ----- Dia.: Max. 8' 3-1/8", Min. allowable for repairs 8' 7/8". No further reduction permitted. Low pitch setting 10.5° (b) Ham. Std. hub 2B20 with: 110 lbs. ----- (-66) ----- Blades 6135-9 or 6135-10 Dia.: Max. 8' 3-1/8", Min. allowable for repairs 8' 7/8". No further reduction permitted. Low pitch setting 14° or Blades 6135-12 or 6135-13 110 lbs. ----- ----- (-67) Dia.: Max. 8' 1/8", Min. allowable for repairs 7' 9-7/8". No further reduction permitted. Low pitch setting 12° (c) Constant speed control 5 lbs. (-34) (-32) (-64) (d) Ham. Std. 2D30 hub with: 162 lbs. (-64) ----- ----- Blades 6101-12 to 6101-14 Dia.: Max. 9' 0", Min. allowable for repairs 8' 9-3/4". No further reduction permitted. Pitch setting: Low 9°, High 24° or Blades 6101-12S to 6101-14S 162 lbs. (-64) ----- ----- Dia.: Max. 9' 0" Min. allowable for repairs 8' 9-3/4". No further reduction permitted. Pitch setting: Low 8°, High 23° A-717 Page 4 of 7 Note: For installation of this propeller on landplane or skiplane with Item 223, the landing gear shock struts must be modified in accordance with Jobmaster Dwg. LG-44J to provide adequate ground clearance. Engines and Engine Accessories - Fuel and Oil System DGA-15P DGA-15J DGA-15W 102. Engine ring cowl (NACA type) 35 lbs. (-42) (-50) (-50) 103. Starter (a) Eclipse F-141 25 lbs. (-31) ----- ----- (b) Eclipse E-80 25 lbs. ----- (-37) (-37) (c) Eclipse E-160 32 lbs. (-31) ----- ----- (d) Eclipse 400-17 33 lbs. (-31) ----- ----- (e) Eclipse 401-17B 34 lbs. (-31) ----- ----- 105. Oil cooler (a) UAP U-3160-B3 15 lbs. (-29) ----- ----- (b) Howard Dwg. E-75 7 lbs. ----- (-48) (-48) (c) UAP U-6007-S30 19 lbs. (-31) ----- ----- 108. Carburetor air heater 7 lbs. (-37) (-37) (-37) 109. Fuel pumps (a) Hand (Romec D2-2) 5 lbs. (-30) (-30) (-30) (b) Pesco R-400 BMB 3 lbs. (-36) ----- (-36) (c) Pesco R-400 BLH 3 lbs. ----- (-36) ----- (d) AN Type H2E3 3 lbs. (-36) ----- ----- 113. Engines (a) Pratt & Whitney Wasp Jr. SB-2 Use act. wt. chg. ----- ----- (Limits same as for SB) (b) Pratt & Whitney Wasp Jr. SB-3 Use act. wt. chg. ----- ----- (Limits same as for SB) (c) Pratt & Whitney Wasp Jr. T1B3 Use act. wt. chg. ----- ----- Fuel: 87 min. grade aviation gasoline Limits: Maximum continuous, (Sea level) 34.2 in.Hg., 2300 rpm (400 hp) (Straight line manifold pressure variation with alt. to 5400 ft.) 32.5 in.Hg., 2300 rpm (400 hp) Takeoff (1 min.), 37.5 in.Hg., 2300 rpm (450 hp) (d) Pratt & Whitney Wasp Jr. T1B2 Use act. wt. chg. ----- ----- (Limits same as T1B3) (e) Military R-985-AN-4 (Limits same as SB) Use act. wt. chg. ----- ----- (f) Military R-985-AN-6 or -AN-6B Use act. wt. chg. ----- ----- (Limits same as SB) (g) Military R-986-AN-12B or -AN-12B Use act. wt. chg. ----- ----- (Limits same as SB) (h) Military E-985-AN-14B (Limits same as Use act. wt. chg. ----- ----- S B ) (i) Military R-985-25 (Limits same as T1B3) Use act. wt. chg. ----- ----- (j) Military R-985-AN-1 or -AN-3 Use act. wt. chg. ----- ----- (Limits same as T1B3) 206. Fuel tanks (a) Front tank (std.) - 30 gal. 17 lbs. (-10) ----- ----- (b) Main tank (std.) - 88 gal. (+29) ----- ----- (c) Rear tank (std.) - 33 gal. 16 lbs. (+65) ----- ----- (d) Main tank (opt.) - 74 gal. (+29) ----- ----- (e) Rear tank (opt.) - 18 gal. 12 lbs. (+65) ----- ----- Page 5 of 7 A-717 Landing Gear and Floats 110. 7.50-10 wheels (Goodyear 10HBM) 76 lbs. (-2) (-2) (-2) with 8.50-10 6-ply tires (wheels must be placarded for these tires) 111. 10 in. smooth contour tail wheel (Hayes 8 lbs. (+195) (+195) (+195) or General) with 6-ply tire (wheel must be placarded for this tire) 112. Wheel streamlines 24 lbs. (-2) (-2) (-2) +10 lbs. (-2) (-2) (-2) 207. Cactus proof tires and tubes Use act. wt. chg. ----- ----- 222. Edo Model Ya-6235, Yd-6470, 58-4580, or Use act. wt. chg. ----- ----- WA-4665 floats with or without water rudder and seaplane fins when installed on Model DGA-15P in accordance with FAA Approved J obmaster Technical Data. Airspeed limits Level flight or climb 152 mph (132 knots) (T.I.A.S.) Glide or dive 182 mph (158 knots) Flaps extended 108 mph ( 94 knots) C.G. range (+18.6) to (+21.4) at 5076 lbs. (+10.5) to (+21.4) at 4000 lbs. or less Straight line variation between points given Maximum weight 4800 lbs. (5076 lbs. when wing is reinforced per Dwgs. J-70 and J-71) Serial Nos. 701 and up and all AAF and Navy numbers. eligible Serial Nos. 500 to 574 eligible with installation of airscoop per Howard Dwg. E-215 and revised stabilizer screw per Howard Dwg. C-138. Required equip. 101(a) or (d), 101(c), 102, 103(a), (c), (d) or (e), 105(c), 106(a), (b) or (c), 107(a) or (b), 108, 109(a) and (b) or (d), 222. 223. Two Western Aircraft Equipment GS-5000A skis (complies with the supplementary conditions for skiplanes of CAR 3 when installed per Dwg. JS-A500). Electrical and Radio Equipment DGA-15P DGA-15J DGA-15W 104. Generator (a) Eclipse D-1 or 308 17 lbs. (-37) ----- ----- (b) Eclipse LV-180 17 lbs. ----- (-37) ----- (c) Eclipse G-2 17 lbs. ----- ----- (-37) (d) Eclipse E5A 21 lbs. (-37) ----- ----- (e) Eclipse NM-1B 25 lbs. (-38) ----- ----- 106. Battery (a) 12V (use actual wt) (+108) (+108) (+108) (b) 24V (use actual wt) (+108) ----- ----- (c) 2-12V (24V) (use actual wt) (+108) ----- ----- 107. Flap motor (a) Bodine NSE-12-Rh 8 lbs. (-22) (-22) (-22) (b) Dumore KLA-7 59 lbs. (-22) ----- ----- 201. Landing lights (Grimes ST-250) 8 lbs. (+19) (+19) (+19) 205. Electrical bonding 4 lbs. (+15) (+15) (+15) 213. Battery (Exide 6XT-13-1, 65A-Hours) + 28 lbs. (+108) (+108) (+108) 215. Generator (Eclipse 309) +5 lbs. (-37) (-37) (-37) Interior Equipment 202. Flares (Four 1 1/2 minute) 25 lbs. (+108) (+108) (+108) 203. Pressure fire extinguisher 10 lbs. (+14) (+14) (+14) 204. Cabin heater 3 lbs. (-35) (-35) (-35) 214. Combination rear seat and bed *33 lbs. (a) Right rear seat 19 lbs. (+56) (+56) (+56) (b) Left seat and bed - Folded 38 lbs. (+56) (+56) (+56) Extended 38 lbs. (+56) (+56) (+56) 216. Camera installation. Baggage compartment *25 lbs. (+84) (+84) (+84) and rear seats are removed for this installation. 217. Two rear seats. See NOTE 3 regarding eligibility for this item with Item 219, stretcher. (a) Right rear seat 18 lbs. (+59.5) (+59.5) (+59.5) (b) Left rear seat 18 lbs. (+44) (+44) (+44) A-717 Page 6 of 7 219. Stretcher installation. See NOTE 3 regarding eligibility for this item w ith Item 219, rear seats. (a) Lower stretcher 18 lbs. (+55) (+55) (+55) (b) Upper stretcher 18 lbs. (+60) (+60) (+60) * 220. Three-place rear seat kit - Dwg. No. 1-A-Hoffer's Flying Service, Camden, South Carolina (Seat kits to be installed in accordan ce with the manufacturer's installation instructions dated Dec. 31, 1946) * 221. Three-place rear seat kit - Model No. 1010 - DGA Incorporated, 617 Murray Bldg., Grand Rapids (2), Michigan. (Seat kits to be installed in accordance with the manufacturer's installation instructions dated March 10, 1947). 401. 6-seat arrangement in accordan ce with Jobmaster Use act. wt. chg. ----- ----- Dwg. 601 402. 8-seat arrangement in accordan ce with Jobmaster Use act. wt. ch. ----- ----- Dwgs. J-6208, J-6209 and J-6210. Miscellaneous (not listed above) 208. Special cabin door (left) 5 lbs. (+30) (+30) (+30) 209. Multi-purpose door +5 lbs. (+32) (+32) (+32) 218. Special baggage door +2 lbs. (+79) (+79) (+79) 300. (a) Aileron trim tab inst allation per (no weight change) Dwg. I-00,001 601. Rudder trim tab installation (Serial Nos. 7 lbs. (+88) ----- ----- 701 and up) 602. Rear controls installation 22 lbs. (+49) ----- ----- NOTE A. Contact the Howard Aircraft Foundation for info rmation on eligible manufacturer’s serial numbers and corresponding civilian model. The HAF maintains a list of all model DGA-15 aircraft manufactured from 1939 to 1944, including all military versions either impressed into Army service or produced under contract for the Navy. NOTE 1. Current weight and balance report including list of e quipment included in certificated empty weight, and loading instructions when necessary, must be in each aircraft at the time of original certification. NOTE 2. (a) Navy Models GH-1, GH-2, GH-3 and NH-1 are eligible for certification as Model DGA-15P when finger strainers having not more than 10 meshes per inch are installed in outlets of all fuel tanks and selector valves are placarded as required by pertinent weight and balance report. Each airplane must be weighed to determine its we ight and balance and loading instructions provided, if necessary. To achieve proper weight and balance, with changes in equipment, either the method described under (1) or under (2) may be used. (1) It is permissible to remove the following airplane placards: At filler caps - "Fill front tank first, main tank second, rear tank last". At the fuel selector valve. "Use rear tank first, ma in tank second, front tank last". Placards governing the sequence of fuel tank filling a nd use and loading schedules will be determined by the individual airplane weight and balance report. (2) Lead ballast (not to exceed 33 lbs.) may be installe d at the tail post to conform with the specified C.G. range, provided a placard is installed in full view of the pilot, reading "Intentional spins prohibited". Upon completion of the conversion to certif icated status, the manufacturer's nameplate on the aircraft should be altered to include the new commercial model designation. In case the original nameplate is not sufficiently large to include this Page 7 of 7 A-717 additional information a similar plate should be installed near the original plate. The original or any succeeding nameplate should not be removed from the aircraft. (b) Navy GH-1 is identical to DGA-15P. (c) Navy GH-2 (Ambulance) is id entical to DGA-15P except as follows: (1) 24 volt electrical system. (2) No. passengers 4 (front +14, right rear +70, lower litter +64) or (3) No. passengers 3 (front +14, right rear +70, left rear +64). (d) Navy GH-3 (General Purpose) is identical to DGA-15P except as follows: (1) Fuel capacity 122 gals. (If main fuselage tank capacity varies from 74 gals. use actual capacity) (Items 206(a), (d), and (e). (2) No. passengers 3 (front +14, right rear +70, left rear +64). (e) Navy NH-1 (Blind Flying Trainer) is identical to DGA-15P except as follows: (1) Fuel capacity 122 gals. (if main fuselage tank capacity varies from 74 gals. use actual capacity) (Items 206(a), (d) and (e). (2) No. passengers 2 (front +14, rear +70). (3) A third set of controls and in struments in rear cockpit (See Item 602). (f) Army Models UC-70 and UC-70B are identi cal to models DGA-15P and DGA-15J, respectively. NOTE 3. Serial Nos. 550, 551 and 552 eligible with st retcher installation (Item 217(a) and 219) as follows: No. Passengers 4 (front +14, right rear +60, lower stretcher +55, upper stretcher +60) Baggage None and with 217(a) and (b) as follows: No. Passengers 3 (front +14, right rear +60, left rear +45) Baggage None .....END.....