TCDS 1H10

Page No 1 2 3 Rev No 1 - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 1H10 Revision 1 DOMAN LZ-5 March 19, 1975 HELICOPTER SPECIFICATION NO. 1H10 Type Certificate Holder Berlin Doman Helicopters, Inc. New Garden Flying Field Toughkenamon, Pennsylvania 19374 I - Model LZ-5, 2-6 PCLH, Approved December 30, 1955 Engine Lycoming SO-580-A1A or SO-580-A1B modified per Doman Dwg. X5Z-15001 Fuel 100/130 min. grade aviation gasoline Engine limits Maximum continuous, (Sea level) 37.5 in.Hg., 3000 rpm (350 hp) (Straight line manifold pressure variation with altitude to 5800 ft.) 36.3 in.Hg., 3000 rpm (350 hp) Take-off (five minutes), (Sea level) 41.5 in.Hg., 3300 rpm (400 hp) (Straight line manifold pressure variation with altitude to 4000 ft.) 40.8 in.Hg., 3300 rpm (400 hp) Rotor limits Maximum 226 rpm Minimum 175 rpm Airspeed limits Never exceed speed (Vne) 66 knots @ 5200 lb. gross weight (CAS) Never exceed speed (Vne) 78 knots @ 4400 lb. gross weight C.G. range (+242) to (+247) Empty weight C.G. range None Maximum weight 5200 lbs. No. of seats Pilot and copilot (+206) Maximum cargo (See NOTE 3 for cargo capacity) Fuel capacity Main tank 76 gal. (+249), auxiliary tank 43 gal. (+246) (See NOTE 1 for unusable fuel) Oil capacity 8 gal. (+155) Rotor blade movements For rigging information, refer to the Maintenance Manual Serial Nos. eligible LZ-5-1-001 and up Required equipment In addition to the pertinent required basic equipment specified in CAR 6, the following items of equipment must be installed: 102, 103, 104, 105, 106, 201(a), 202(a), 205(a), 206(a), 301(a), 401(a) and 402 1H10, Rev 1 2 Specifications Pertinent to All Models Datum 300 in. forward of aft cabin attachment (Sta. 300) Leveling means Leveling lugs in fuselage Certification basis Type Certificate No. 1H10 (CAR 6, dated January 15, 1951) Production basis None. Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Engine and Engine Accessories - Fuel and Oil Systems 101. One auxiliary fuel pump, electric, Thompson Products TF 36500-4 3 lb. (+205) 102. One engine fuel pump, CE 9141 2 lb. (+169) 103. Starter, Pioneer Type 756 19 lb. (+167) 104. Oil cooler (Engine), #AP1ZAV13-0, Harrison Radiator 12 lb. (+359) 105. Oil cooler (Transmission), #8517955 7 lb. (+273) Landing Gear 201. Four main wheels - two with brake assemblies, 5.00-5, Type III 18 lb. (+270) (a) Goodyear model L5HBM Inboard - Wheel assembly No. 95202653 Brake assembly No. 9531597 Outboard - Wheel assembly No. 9520654 202. (a) Four main wheel 6-ply rating tires, 5.00-5, Type III, 22 lb. (+270) with regular tubes inflated to 6 5 lb. pressure 205. Two nose wheels, 10 in., SC (a) Goodyear 510646M assembly 3 lb. (+177) 206. (a) Two nose wheel 6-ply rating tires, 10:00 SC, with 5 lb. (+177) regular tubes inflated to 65 lb. pressure Electrical Equipment 301. Generator 19 lb. (+165) (a) EZCZ63 C-7 302. Battery, AN 3151-Z 53 lb. (+210) 303. Landing lights, G360A Grimes (AN3130-4562), installed per Doman Dwg. 5Z21610 (a) One adjustable 5 lb. (+193) (b) One fixed 2 lb. (+193) Interior Equipment 401. (a) CAA Approved Helicopter Flight Manual, dated December 30, 1955 402. Variable Vne airspeed indicator, Doman Dwg. X5Z-19637 NOTE 1. Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). When changes are made to the helicopter which affect weight and balance, see instructions contained in Section IV of the Flight Manual. NOTE 2. The following placards must be displayed on the instrument panel in full view of the pilot: (a) "This helicopter must be operated in compliance with the Operating Limitations Specified in the CAA Approved Rotorcraft Flight Manual." (b) "Decrease Vne 5 knots per 1000 ft. altitude above 1500 ft." "Before take-off, set Vne index to gross weight at T.O." NOTE 3. The cabin floor area between Stations 214 and 299 is structurally satisfactory for a uniformly distributed loading of 235 p.s.f. when used for cargo purposes. Maximum cargo 1400 lb. with only unusable fuel. 3 1H10, Rev 1 NOTE 4. Information essential to the proper maintenance of the helicopter including retirement time of critical parts is contained in the Doman LZ-5 Maintenance Manual provided with each helicopter. These values of retirement or service life cannot be increased without FAA engineering approval. .....END.....