TCDS 1A8

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 38 36 36 31 31 31 31 35 31 31 31 34 31 38 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1A8 Revision 38 HELIO H-250 (USAF U-10D) H-295 HT-295 (USAF YL-24) H -391 H-391B (USAF L-28A or U-10B) H-395 H-395A H-700 H-800 March 30, 2020 TYPE CERTIFICATE DATA SHEET NO. 1A8 This data sheet, which is a part of Type Certificate 1A8, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations/Federal Aviation Regulations. Type Cert ificate Holder (See Note 4 for Holder Record) Physical Address: Helio A laska, Inc. 20150 Birchwood Spur Road Chugiak AK 99567 I. Model H-391 (USAF YL-24) (Courier), 4 PCL-SM (Normal Category), approved August 5, 1953 Model H-391B (Courier), 4 P CL-SM (Normal Category), approved June 29, 1954 Model H-391B same as model H-391 except for engine, propeller, semi-monocoque fuselage, minor fuel system changes, minor control system changes, and other miscellaneous minor changes. Engine Model H-391 - Lycoming GO-435-C2 Model H-391B - Lycoming GO-435-C2B, GO-435-C2B2, GO-435-C2B2-6 Fuel Model H-391 - 91/98 minimum grade aviation gasoline Model H-391B - 80/87 minimum grade aviation gasoline with standard ejector exhaust system Engine limits T akeoff 3400 r.p.m. (260 hp) All other operations 3000 r.p.m. (240 hp) Propeller a nd propeller Model H-391 - Hartzell controllable propeller HC12X20-8C, blades limits 9333C-0. Diameter: not over 93 in., not under 91 in. Pitch settings at 30 in. Sta: low 14° 15′, high 29° 15′ Placard re quired: "Continuous ground operation between 1675 and 2150 r.p.m. prohibited." Propeller gove rnor, Hartzell B-1 or B-3. Propeller spinner and mount, Hartzell D-164. Model H-391B - Ha rtzell controllable propeller hub HC82X20-1A or HC82X20-1B, blades 10133D. Diameter: not over 101 in., not under 95 in. Pitch settings at 30 in. Sta: Low 13°, high 31° S/N 001 through 081, except 075, as delivered by manufacturer. Mailing Address: P. O. Box 670641 Chugiak AK 99567 1A8 2 of 14 I. M odel H-391 (USAF YL-24), Model H-391B (cont'd) H- 391B (cont'd) Placard required: "Avoid continuous operation between 2600 and 2975 r.p.m." If engine is modified to GO-435-C2B2-6, placard may be removed. S/N 082 and up, no placard is required. P ropeller governor, Hartzell B-1 or B-3. Propeller spinner, Hartzell C-888 dome with C-807-2 bulkhead. A irspeed Limits LANDPLANE M aneuvering (2800 lbs.) 94 m.p.h. ( 82 knots) CAS Maneuvering (3000 lbs.) 98 m.p.h. ( 85 knots) CAS Maximum structural cruising 150 m.p.h. (134 knots) CAS Never exceed 189 m.p.h. (164 knots) CAS Flaps extended 80 m.p.h. ( 69 knots) CAS F LOATPLANE - with Edo Model 249-2870 floats (H-391B only) S/N 001 through 045, aircraft structural changes required per Helio modifications No. 5A or No. 13. Float installation per Helio modification No. 15. S/N 046 and up, no structural changes required. Float installation per Helio modification No. 15. M aneuvering 94 m.p.h. ( 82 knots) CAS Minimum structural cruising 130 m.p.h. (113 knots) CAS Never exceed 164 m.p.h. (143 knots) CAS Flaps extended 80 m.p.h. ( 70 knots) CAS C. G. Range LANDPLANE (+ 101.3) to (+106.4) at 3000 lbs. (+ 99.9) to (+106.4) at 2800 lbs. (+ 96.5) to (+106.4) at 2200 lbs. or less Straight line variation between points given. F LOATPLANE (+ 101.3) to (+106.4) at 3000 lbs. (+ 99.1) to (+106.4) at 2700 lbs. S KI INSTALLATION F ederal installation drawing 11R1241. Federal AWB-3500A main skis and AWT-3500 tailwheel ski including 20 lbs. fixed ballast on tail wheel ski. Eligible with hydraulic conversion on ground and in flight. Weight and balance shall be checked with ski in retracted and extended positions. (+101.3) to (+104.3) at 3000 lbs. (+ 99.9) to (+104.3) at 2800 lbs. (+ 96.5) to (+104.3) at 2200 lbs. or less Straight line variation between points given. E mpty Weight C.G. Range None M aximum Weight LANDPLANE (H-391 and H-391B, S/N 001 through 031) 2800 l bs. (eligible for 3000 lbs. when incorporating Helio modification 21, main landing gear assemblies 391-040-451-12 and -13, and tailwheel assembly 391-040-4101.) H-391B - S/N 032 and up: 3000 lbs. F LOATPLANE (H-391B only, S/N 001 through 031) 2800 l bs., when Helio modification No. 21 incorporated. S/N 032 and up: 3000 lbs. N o. of Seats 4 (2 at +103.5, 2 at +136. S/N 066 and up eligible for 5th seat at +165) 3 of 14 1A8 I. Model H-391 (USAF YL-24), Model H-391B (cont'd) M aximum Baggage 200 lb. (+163) F uel Capacity Model H-391 - 60 gal. total, 52.5 gal. usable (two 30 gal. tanks in wings at +113) Model H-391B - S/N 001 through 087 (except 075), 61 gal. total, 58.2 gal. usable two 30 gal. tanks in wings at +113. 1 gal. header tank in fuselage) S/N 088 and up, 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wing at +113. No header tank) See NOTE 1 for data on system fuel. O il Capacity Model H-391: 12 qt. (+37). Model H-391B: 10 qt. (+37) Cont rol Surface Movements LANDPLANE S tabilator (trailing edge) Up 19° Down 8° from neutral Neutral position is trailing edge down 2.5°. Stabilator trim tab (± 2°) Up 36° Down 20° Measured from stabilator chord line S tabilator antibalance tab Within ± 2° of neutral - measured from stabilator chord line A ileron (± 1°) Up 20° Down 20° Rudder (± 1°) S/N 001 through 049 Right 30° Left 30° S/N 050 and up Right 30° Left 25° Flaps Down 40° FL OATPLANE S tabilator (trailing edge) Up 17° Down 8° Anti-balance tab (trailing edge) Within ± 2° of neutral - measured from stabilator chord line Rudder Right 30° Left 20° S erial Nos. Eligible Model H-391 - 1 only Model H-391B - 001 and up II. Model H-395 (USAF L-28A or U-10B) (Courier), 5 PCL-SM (Normal Category), approved November 17, 1958 M odel H -395A (Courier), 5 PCL-SM (Normal Category), approved June 29, 1959 E ngine Model H-395 - Lycoming GO-480-G1D6 Model H-395A - Lycoming GO-435-G2B2-6 Fu el Model H-395 - 100/130 minimum grade aviation gasoline Model H-395A - 80/87 minimum grade aviation gasoline En gine Limits Model H-395 - Takeoff 3400 r.p.m. (295 hp) All other operations 3000 r.p.m. (280 hp) Model H-395A - Takeoff 3400 r.p.m. (260 hp) All other operations 3000 r.p.m. (240 hp) 1A8 4 of 14 II. Model H-395 (USAF L-28A or U-10B), Model H-395A (cont'd) Propeller and propeller limits Model H-395 - Hartzell controllable propeller (S/N 075, 502 through 514, 516 through 530) hub HC-93Z20-1B1, blades 10151C or 10151C-5 Diameter: not over 101 in., not under 95 in. Pitch settings at 30 in. Sta: Low 11.8°, high 30.8° Propeller governor, Hartzell B-3 Propeller spinner, Hartzell 836-15 Hartzell controllable propeller (S/N 531 and up) hub HC-B3Z20-1, blades 10151C or 10151C-5 Diameter: not over 101 in., not under 95 in. Pitch settings at 30 in. Sta: Low 11.8°, high 30.8° Propeller governor, Hartzell B-3 Propeller spinner, Hartzell 836-15 Model H-395A - (S/N 515, 1002 through 1005) Hartzell controllable propeller, hub HC82X20-1A or HC82X20-1B, blades 10133D Diameter: not over 101 in., not under 95 in. Pitch settings at 30 in. Sta: Low 13°, high 31° Propeller governor, Hartzell B-1 or B-3 Propeller spinner, Hartzell C-888 dome with C-807-2 bulkhead (S/N 1006 and up) Hartzell controllable propeller, hub HC-A2X20-1, blades 10133D Diameter: not over 101 in., not under 95 n. Pitch settings at 30 in. Sta: Low 13°, high 31° Propeller governor, Hartzell B-1 or B-3 Propeller spinner, Hartzell C-888 dome with C-807-2 bulkhead Airspeed Limits LANDPLANE Maneuvering (2800 lbs.) 94 m.p.h. ( 82 knots) CAS Maneuvering (3000 lbs.) 98 m.p.h. ( 85 knots) CAS Maximum structural cruising 150 m.p.h. (134 knots) CAS Never exceed 189 m.p.h. (164 knots) CAS Flaps extended 80 m.p.h. ( 69 knots) CAS FLOATPLANE - with Edo Model 249-2870 floats H-395A (S/N 515, 1002 and up). Float installation per Helio modification no. 31. Maneuvering 95 m.p.h. ( 83 knots) CAS Minimum structural cruising 130 m.p.h. (113 knots) CAS Never exceed 164 m.p.h. (143 knots) CAS Flaps extended 80 m.p.h. ( 70 knots) CAS C.G. Range LANDPLANE (+101.3) to (+106.4) at 3000 lbs. (+ 99.9) to (+106.4) at 2800 lbs. (+ 96.5) to (+106.4) at 2200 lbs. or less Straight line variation between points given. FLOATPLANE (+101.3) to (+106.4) at 3000 lbs. (+ 99.1) to (+106.4) at 2700 lbs. or less 5 of 14 1A8 II. Model H-395 (USAF L-28A or U-10B), Model H-395A (cont'd) SKI INSTALLATION Federal installation drawing 11R1241. Federal AWB-3500A main skis and AWT-3500 tailwheel ski including 20 lb. fixed ballast on tailwheel ski. Eligible with hydraulic conversion on ground and in flight. Weight and balance shall be checked with ski in retracted and extended positions. (+101.4) to (+104.3) at 3000 lbs. (+ 99.9) to (+104.3) at 2800 lbs. (+ 96.5) to (+104.3) at 2200 lbs. Straight line variation between points given. Empty Wt. C.G. Range None Maximum Weight LANDPLANE 3000 lbs. FLOATPLANE (H-395A only) 3000 lbs. No. of Seats 5 (2 at +103.5, 2 at +136, 1 at +165) Maximum Baggage 200 lbs. (+163) Fuel Capacity 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113). (No header tank) See NOTE 1 for data on system fuel. Oil Capacity 10 qt. (+37) Control Surface Movements LANDPLANE Stabilator (trailing edge (±0°)) Up 19° Down 8° from neutral Neutral position is trailing edge down 2.5°. Stabilator trim tab (±2°) Up 36° Down 20° Measured from stabilator chord line Stabilator anti-balance Within ±2° of neutral - measured from tab (±2°) stabilator chord line Aileron (±1°) Up 20° Down 20° Rudder (±1°) Right 30° Left 25° Flaps (±1°) Down 40° FLOATPLANE Stabilator (trailing edge) Up 17° Down 8° Anti-balance tab (trailing edge) Within ±2° of neutral - measured from stabilator chord line Rudder Right 30° Left 20° Serial Nos. Eligible Model H-395 - 075, 502 through 514, 516 and up Model H-395A - 515, 1002 and up USAF U-10B airplanes are eligible for a civil airworthiness certificate when converted in accordance with Helio Drawing 395-000-050. 1A8 6 of 14 III. Model H-250 (Courier), 6 PCL-SM (Normal Category), Approved November 6, 1964 Sam e as Model H -395 except for powerplant installation, increased gross weight, and minor structural changes. E ngine Lycoming O-540-A1A5 Fuel 100/130 minimum grade aviation gasoline Engine limits For all operations, 2575 r.p.m. (250 hp.) P ropeller and Hartzell controllable propeller, Hub HC-92WK-1D, blades W8847 propeller limits Diameter: not over 88 in., not under 86 in. Pitch settings at 30 in. Sta: Low 12° ± .2°, high 28.5° ± .5° Propeller governor, Hartzell F-6-8 (S/N 2501 through 2520), Hartzell F-6-8L (S/N 2521 and up). Propeller spinner, Hartzell C-2513-3. A irspeed limits Maneuvering 94 m.p.h. ( 82 knots) CAS Maximum structural cruising 150 m.p.h. (134 knots) CAS Never exceed 189 m.p.h. (164 knots) CAS Flaps extended 80 m.p.h. ( 69 knots) CAS C. G. Range LANDPLANE (+ 105.0) to (+110.0) at 3400 lbs. (+ 97.5) to (+110.0) at 2150 lbs. or less Straight line variation between points given. F LOATPLANE - with Edo model 582-3430 floats S /N 2501, 2506 and up. Installation per Helio drawing 250-000-015. (+ 102.5) to (+109.0) at 3400 lbs. (+ 99.4) to (+109.0) at 2900 lbs. (+ 97.6) to (+109.0) at 2460 lbs. or less Straight line variation between points given. E mpty Wt. C.G. Range None Maximum weight 3400 lbs. No. of seats 6 (2 at +103.5, 2 at +136, 2 at +162) M aximum baggage 340 lbs. (+162) when 2-passenger aft sling seat is unoccupied F uel capacity standard system 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113) O ptional auxiliary Additional 60 gal. wing installed auxiliary fuel system, Helio P/N 250-080-901 fuel system and wing assembly P/N 250-010-050 See NOTE 1 for data on system fuel. O il capacity 12 qt. (+22) Cont rol surface movements Stabilator (trailing edge (±1°)) Up 19° Down 10° from neutral Neutral position is trailing edge down 2.5°. Stabilator trim tab (±2°) Up 36° Down 20° Measured from stabilator chord line Stabilator anti-balance tab Within ±2° of neutral - measured from stabilator chord line Aileron (±1°) Up 20° Down 20° Rudder (±1°) Right 30° Left 25° Flaps (±1°) Down 40° S erial nos. eligible 2501 and up 7 of 14 1A8 IV. Model H-295 (USAF U10D, (Courier), 6 PCL-SM (Normal Category), approved April 15, 1965 Same as Model H-295 except for engine installation. Engine Lycoming GO-480-G1D6 - Slow speed (1.250:1) generator drive or Lycoming GO-480-G1A6 - High speed (2.577:1) generator drive Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff 3400 r.p.m. (295 hp) All other operations 3000 r.p.m. (280 hp) Propeller and propeller Hartzell constant speed propeller, Hub HC-B3Z20-1, blades 10151C limits Diameter: 96 in. (1 in. reduction permitted) Pitch settings at 30 in. Sta: Low 11.8°, high 30.8° Propeller governor, Hartzell B-3 Propeller spinner, Hartzell 836-15R (supersedes Hartzell 836-15) Airspeed limits Maneuvering 103 m.p.h. ( 89 knots) CAS Maximum structural cruising 160 m.p.h. (140 knots) CAS Never exceed 200 m.p.h. (174 knots) CAS Flaps extended 80 m.p.h. ( 69 knots) CAS C.G. Range LANDPLANE (+103.8) to (+110.0) at 3400 lbs. (+ 98.9) to (+110.0) at 2760 lbs. (+ 97.0) to +110.0) at 2330 lbs. or less Straight line variation between points given. FLOATPLANE Float installation per Helio drawing 250-000-015 (+102.0) to (+109.0) at 3400 lbs. (+ 98.0) to (+109.0) at 2600 lbs. or less Straight line variation between points given. Empty weight C. G. range None Maximum weight 3400 lbs. No. of seats 6 (2 at +103.5, 2 at +136, 2 at +162) Maximum baggage 340 lbs. (+162) when 2-passenger aft sling seat is unoccupied Fuel capacity standard 60.7 gal., total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113) system Optional auxiliary fuel system Additional 60 gal. wing installed auxiliary fuel system, Helio P/N 250-080-901 and wing assembly P/N 250-010-050 See NOTE 1 for data on system fuel. Oil capacity 12 qt. (+37) Control surface movements Stabilator Up 19° Down 10° from neutral (trailing edge (±1°)) Neutral position is trailing edge down 2.5° Stabilator trim tab (±2°) Up 36° Down 20° Measured from stabilator chord line Stabilator anti-balance tab Within ±2° of neutral - measured from stabilator chord line Aileron (±1°) Up 20° Down 20° Rudder (±1°) Right 30° Left 25° Flaps (+0°, -2°) Down 40° Serial nos. eligible 1201 through 1233, 1278 and up; S/N 1234 through 1277 (USAF 66-14332 through 66-14375) eligible when converted in accordance with Helio drawing 295-000-020. 1A8 8 of 14 V. Model HT-295 (Courier), 6 PCLM (Normal Category), approved December 18, 1973 Tricycle Version of Model H-295 Engine Lycoming GO-480-G1D6 Lycoming GO-480-G1A6 Fuel 100/130 minimum grade aviation gasoline Engine limits Takeoff 3400 r.p.m. (295 hp) All other operations 3000 r.p.m. (280 hp) Propeller and propeller limits Hartzell constant speed propeller, Hub HC-B3Z20-1, blades 10151C Diameter: 96 in. (1 in. reduction permitted) Pitch settings at 30 in. sta: Low 11.8°, high 30.8° Propeller governor, Hartzell B-3 Propeller spinner, Hartzell 836-15R (supersedes Hartzell 836-15) Airspeed Limits Maneuvering 103 m.p.h. ( 89 knots) CAS Maximum structural cruising 160 m.p.h. (140 knots) CAS Never exceed 200 m.p.h. (174 knots) CAS Flaps extended 80 m.p.h. ( 69 knots) CAS C.G. Range LANDPLANE (+103.8) to (+110.0) at 3400 lbs. (+ 98.9) to (+110.0) at 2760 lbs. (+ 97.0) to (+110.0) at 2330 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None Maximum weight 3400 lbs. No. of seats 6 (2 at +103.5, 2 at +136, 2 at +162) Maximum baggage 340 lbs. (+162) when 2-passenger aft sling seat is unoccupied. Fuel capacity 60.7 gal. total, 58.2 gal. usable (two 30.35 gal. tanks in wings at +113) See NOTE 1 for data on system fuel. Oil capacity 12 qt. (+37) Control surface movements Stabilator Up 19° Down 10° from neutral (trailing edge (±1°)) Neutral position is trailing edge down 2.5°. Stabilator trim tab (±2°) Up 36° Down 20° Measured from stabilator chord line Stabilator anti-balance tab Within ±2° of neutral - measured from stabilator chord line Aileron (±1°) Up 20° Down 20° Rudder (±1°) Right 30° Left 25° Flaps (+0°, -2°) Down 40° Serial Nos. eligible 1701 and up 9 of 14 1A8 VI. Model H-800 (Courier), 4 PCSM (Normal Category), approved July 19, 1983; 6 PCLM (Normal category), approved September 28, 1983 Same as Model HT-295 except for powerplant installation, increased gross weight, structural changes, and miscellaneous minor changes. Engine Lycoming IO-720-A1B Fuel 100/100LL minimum grade aviation gasoline Engine limits 2650 r.p.m. (400 hp) Propeller and propeller limits Hartzell constant speed propeller, Hub HC-C3YR-1RF, blades F8475R Diameter: 86 in. Pitch settings at 30 in. sta: Low 11.8°, high 30.8° Propeller governor, Hartzell FA-3A Propeller spinner, Hartzell A2295-1 Airspeed limits (CAS) Maneuvering 93 knots Maximum structural cruising 133 knots Never exceed 168 knots Flaps extended - 40° 83 knots Flaps extended - 15° 96 knots C.G. Range LANDPLANE (+102.0) to (+109.0) at 4000 lbs. (max. takeoff weight) (+101.0) to (109.0) at 3800 lbs. (max. landing weight) (+ 98.0) to (+109.0) at 3200 lbs. or less Straight line variation between points given. FLOATPLANE Floatplane Model: Edo-Aire 696-3500 (+104.0) to (+110.0) at 3888 lbs. (+101.0) to (+110.0) at 3200 lbs. or less Edo-Aire 582-3430 (+104.0) to (+110.0) at 3800 lbs. (+101.0) to (+110.0) at 3200 lbs. or less Empty Weight C.G. Range None Maximum Weight LANDPLANE 4000 lbs. takeoff 3800 lbs. landing FLOATPLANE Edo-Aire 696-3500 amphibious Water operations: 3888 lb. takeoff 3800 lb. landing Land operations: 3790 lb. takeoff 3600 lb. landing Edo-Aire 582-3430 3800 lb. takeoff and landing 1A8 10 of 14 VI. Model H-800 (Courier) (cont'd) Zero Fuel Weight 3800 lbs. No. of Seats LANDPLANE 6 (2 at +103.5, 2 at +136.0, 2 at +162.0) FLOATPLANE 696-3500 amphibious 4 (2 at +103.5 and 2 at +136.0, restricted to 306 lb. total weight) 582-3430 4 (2 at +103.5 and 2 at +136.0), restricted to 213 lb. total weight) Maximum Baggage LANDPLANE Total load AFT of pilot's seat - 40 lb. per sq. ft. 10 lb. per sq. ft. in luggage compartment See AFM for loadings. FLOATPLANE 40 lb. per sq. ft. rear seat and cargo area Combined loadings rear passenger seats - 218 lb. See AFM for loadings. Fuel Capacity LANDPLANE 121.4 gal. total, 120.5 gal. usable (four 30.35 gal. tanks in wing at +113) See NOTE 1 for data on fuel system. FLOATPLANE 696-3500 amphibious and 582-3430 floats 60.7 gal. total, 60.2 gal. usable at +113 Oil Capacity 19 qt. maximum, 17 qt. normal (+37) Control Surface Movements Stabilator Up 10° Down 21° from neutral Leanding edge (±1°) Neutral position is trailing edge down 2.5°. Stabilator trim tab (±2°) Up 30° Down 28° Measured from stabilator chord line Stabilator anti-balance tab Within ±2° of neutral - measured from stabilator chord line Aileron droop 0.87" (±.07") Aileron (±1°) Up 20° Down 20° Rudder (±1°) Right 30° Left 25° Flaps (±1°) Down 40° Interceptor retracted position Below surface of wing, 0.38" to 0.50" Serial nos. eligible H-1 and up 11 of 14 1A8 VII. Model H-700 (Courier), 6 PCLM (Normal Category), approved January 24, 1984 Same as Model HT-295 except for powerplant installation, increased gross weight, structural changes, and miscellaneous minor change. Engine Lycoming TIO-540-J2B Fuel 100/100LL minimum grade aviation gasoline Engine limits 2575 r.p.m. (350 hp) 49 inches M.P. Propeller and propeller limits Hartzell constant speed propeller, Hub HC-E3YR-1RF, blades: F9587A-10 Diameter: 87 in. Pitch settings at 30 in. sta: Low 12.7°, high 31.0° Propeller governor, Hartzell FA-13 Serial No. H-7 through H-10 Hartzell F4-30 Serial No. H-11 and subsequent Service replacement H-7 through H-10 Propeller governor, Hartzell A2295-1 Airspeed limits (CAS) Maneuvering 93 knots Maximum structural cruising 133 knots Never exceed 168 knots Flaps extended - 40° 83 knots Flaps extended - 15° 96 knots C.G. Range LANDPLANE (+101.0) to (+108.5) at 3800 lbs. (+ 98.0) to (+108.5) at 2600 lbs. or less Straight line variation between points given. Empty Weight C.G. Range None Maximum weight 3800 lbs. No. of seats LANDPLANE 6 (2 at +103.5, 2 at +136.0, 2 at +162.0) Maximum Baggage LANDPLANE Total load AFT of pilot's seat - 40 lb. per sq. ft. 10 lb. per sq. ft. in luggage compartment. See AFM for loadings. Fuel Capacity LANDPLANE 121.4 gal. total, 120.5 gal. usable (four 30.35 gal. tanks in wing at +113). See NOTE 1 for data on fuel system. Oil Capacity 12 qt. maximum, 10 qt. normal (+37) Control Surface Movements Stabilator Up 10° Down 21° from neutral Leading edge (±1°) Neutral position is trailing edge down 2.5°. Stabilator trim tab (±2°) Up 30° Down 28° Measured from stabilator chord line Stabilator anti-balance tab Within ±2° of neutral - measured from stabilator chord line Aileron droop 0.87" (±.07") Aileron (±1°) Up 20° Down 20° Rudder (±1°) Right 30° Left 25° Flaps (±1°) Down 40° Interceptor retracted position Below surface of wing, 0.38" to 0.50" Serial Nos. Eligible H-1 and up 1A8 12 of 14 DATA PERTINENT TO ALL MODELS Datum 60 in. forward of fuselage station 0. (Sta. 0 is at upper attachment of engine mount to fuselage). For weight and balance purposes, Station 100.25 is the centerline of wing spar (midway between two rows of bolts in wing root fitting on bottom side of wing). L eveling Means Model H-391: Plumb line markers at top and bottom of right door frame (fuselage station 60). Models H-250, H-295, H-391B, H-395A, H-700, H-800: Two leveling studs at lower forward corner of right door frame. Ce rtification Basis Part 3 of the Civil Air Regulations effective November 1, 1949, as amended to May 16, 1953. Type Certificate No. 1A8 issued August 5, 1953. Application for Type Certificate dated May 1, 1951. P roduction Basis None. Prior to original certification, an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, a final inspection of the completed aircraft, and a check of the flight characteristics. E quipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. The equipment portion of Aircraft Specification 1A8, Revision 18, dated July 7, 1969, or the equipment list provided with each airplane should be used for equipment references on Helio Models H-391, H-391B, H-395, H-395A, H-250, and H-295 (prior to serial number 1458). Refer to the applicable equipment list for Model H-295, serial number 1458 and on, Model H-700, and Model H-800. In addition, the following FAA approved Airplane Flight Manuals and Airplane Flight Manual Supplements are required. (a ) FAA Approved Airplane Flight Manual dated February 9, 1956 (H-391B, S/N 001 through 031); dated November 3, 1956 (H-391B, S/N 032 and up and for those S/N 001 through 031 modified oer Helio Modification 21). (b) F AA Approved Airplane Flight Manual Supplement dated January 24, 1956 (H-391B, H-395, H-395A) required when Federal AWB-3500A main and AWT-3500 tailwheel skis are installed. Federal Installation drawing 11R1241. (c ) FAA Approved Airplane Flight Manual Supplement dated July 18, 1956