TCDS H2WE

Page No. 1 2 3 4 5 6 7 8 Rev. No. 11 6 6 6 6 7 6 8 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H2WE Revision 11 AIR SPACE DESIGN AND MANUFACTURING, LLC 1100(OH-5A) FH-1100 August 19, 2015 TYPE CERTIFICATE DATA SHEET NO. H2WE This data sheet which is part of Type Certificate No. H2WE prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulation. Type Certificate Holder: Type Certificate Ownership Record: AIR SPACE DESIGN AND MANUFACTURING, LLC 9 East Lockerman Street, Suite 3A Dover, Delaware 19901 FH1100 Manufacturing Corporation transferred TC to Air Space Design and Manufacturing, LLC on June 7, 2008. Siam Hiller Holdings, Inc. transferred TC to FH1100 Manufacturing Corporation, 6080 Industrial Boulevard, Century, Florida 32535 TC was transferred to Siam Hiller Holdings, Inc., 3200 Imjin Road, Marina, California 93933-5101 from unknown previous holder. I - HILLER MODEL 1100 (U.S. ARMY OH-5A), (Normal Category Helicopter) Approved May 22, 1964 (See Note 5 regarding modifications required for conversion of Military Models) Engine Allison 250-C10 (See Note 8 regarding engine model) Fuel MIL-J-5624 Grade JP-4 or JP-5, Commercial Kerosene Type A, or A1, or Allison Specification EMS 64, MIL-F-46005 Type 1 C.I.T.E. Fuel Engine Ratings Take-off (5 Min.) Max. Continuous Shaft H.P. Gas Producer rpm Output Shaft rpm Measured Gas Temp. 250 48950 6000 1240°F(671°C) 212 47350 6000 1165°F(630°C) NOTE: The above engine ratings are based on static sea level conditions. The maximum allowable torque as measured by the torque meter for below standard inlet air temperature and/or ram conditions is 240 ft. lb. (274 HP @ 100% N2) for take-off and 204 ft. lb. (233 HP @ 100% N2) for maximum continuous. H2WE Page 2 of 8 Engine Temperature Limits Measured Gas Temperature take-off (5 min.) Max. Continuous 1280°F (693°C) Max. Transient (not to exceed 6 Seconds) 1550°F (843°C) Oil Inlet Temperature -65°F to +200°F Motor Limits & Engine Operating Speeds Power Off (Rotor Tach) Maximum 390 rpm (106% NR) Minimum 295 rpm (80% NR) Power On Maximum 100% N2 Minimum 96% N2 Airspeed Limits Configuration Skid Gear VNE (IAS) 127 mph (110 knots) The above airspeed applies from S.L. to 5000 ft. Decrease VNE 5.2 mph (4.5 knots) per 1000 ft. of altitude above 5000 ft. For limits with accessories installed, see the FAA Approved Rotorcraft Flight Manual. Altitude Limits Avoid operational areas as shown in FAA Approved Rotorcraft Flight Manual. C.G. range (Longitudinal) Sta. (95.5) to (101.5) C.G. Range (Lateral) Left of helicopter centerline, 2.5 in. Right of helicopter centerline, 2.5 in. Maximum Weight 2530 lb. No. of Seats 2 (60.0), 2 (86.5) Maximum Cargo 860 lb. at 100 lb./sp. ft., Sta. (68.12) to (100.0). See loading instructions in FAA Approved Rotorcraft Flight Manual. Fuel Capacity Main tank 69 gallon (100.6) See NOTE 1 for unusable fuel. Oil Capacity Engine oil - 2.75 qt. (116) Transmission oil - 2.75 qt. (106) Main Rotor Blade Movements (Measured with respect to the mast) Collective Travel Set down stop to obtain 100% NR at 2530 pounds gross weight and standard sea level with 11° travel. Cyclic Travel Lateral 6.2° + or - .25° Right and Left Longitudinal 12.0° + or - .25° Forward 8.0° + or - .25° Aft Page 3 of 8 H2WE Tail Rotor Pitch Right 3.9° + or - .25° Left +14.1° + or - .25° Hydraulic System Pressure 900 psi nominal operating. Serial No. Eligible 1 and 4 through 8 when modifications specified in Hiller Report, "Model 1100 (ARMY OH-5A) Helicopter Design Changes - TIA to Type Certification", dated July 16, 1964, are incorporated, and forward engine mount assembly P/N 24-63113-1 and -3 is installed. (See NOTE 5 for eligibility of military models) II - Model FH-1100 (Normal Category Helicopter) Approved November 10, 1966 Engine Allison 250-C18, see NOTE 7 for alternate engine Fuel MIL-J-5624 Grade JP-4 or JP-5, Commercial Kerosene Type A or A1, or Allison Specification EMS 64, MIL.F. 46005 Type 1 C.I.T.E. Fuel. Engine Ratings Take-off (5 Min.) Max. Continuous Shaft H.P. Gas Producer rpm Output Shaft rpm Measured Gas Temp. 274 29940(97.6%) 6000(100%) 1290°F(699°C) 233 48250(94.4%) 6000(100%) 1206°F(652°C) NOTE: The above engine ratings are based on static sea level conditions. The maximum allowable installed torque as measured by the torque meter is 240 ft. lb. (274 H.P. @ 100% N2) for takeoff and 204 ft. lb. (233 H.P. @ 100% N2) for maximum continuous. Engine Temperature Limits Measured Gad Temperature take-off (5 min.) 1380°F (749°C) Max. Continuous 1280°F (693°C) Max. Transient (not to exceed 6 seconds) 1550°F (843°C) Max. Starting Transient (not to exceed 1 second) 1700°F (927°C) Oil Inlet temperature -65°F to +225°F Rotor Limits & Engine Operating Speeds Power Off (Rotor Tach) Maximum 390 rpm (106% NR) Minimum 295 rpm (80% NR) Power On Maximum 102% NR Minimum 98% N2 Airspeed Limits Configuration Skid Gear VNE (IAS) 127 mph (110 Knots) Altitude Limits Avoid operational areas as shown in FAA Approved Rotorcraft Flight Manual. H2WE Page 4 of 8 C.G. Range (Longitudinal) Sta. (95.5) to (101.5) C.G. range (Lateral) Left of helicopter centerline, 2.5 in. Right of helicopter centerline, 2.5 in Maximum Weight 2750 lb. No. of Seats 2 (55.2), 2 (89.0), 1 (86.0) Maximum Cargo 1100 lb. at 100 lb./sq. ft., Sta. (68.12) to (100.0). See loading instruction in FAA Approved Rotorcraft Flight Manual. Baggage Compartment Capacity 150 lb. Fuel Capacity Main tank 68.5 gallon (100.6). (See NOTE 1 for unusable fuel) Oil Capacity Engine Oil - 2.76 qt. (116) Transmission Oil - 2.6 qt. (106) Main Rotor Blade Movements (Measured with respect to the mast) Collective Travel Set down stop to obtain 102% NR at 2750 pounds gross weight and standard sea level with 12° travel. Cyclic Travel Lateral 7.4° + or - .5° Right and Left Longitudinal 12.0° + or - .5° Forward 8.0° + or - .5° Aft Tail Rotor Pitch Right -1.5° + or - .5° Left +16.5° + or - .5° Horizontal Stabilizer Setting -2° + or - .5° Hydraulic System Pressure 950 psi nominal operating. Serial No. Eligible 9 and up. Data pertinent to All Models Datum 100 in. Forward of Station 100 bulkhead (main rotor centerline). Leveling means Top face of rear seat deck. Other Operating Limitations FAA Approved Rotorcraft Flight Manual. Page 5 of 8 H2WE Certification Basis CAR 6, dated December 20, 1956, including amendments 6-1 through 6-4 and Special Conditions, "Conditions Establishing Compensating Factors Providing an Equivalent Level of Safety under Civil Air Regulations, Section 6.10 for Light Turbine Powered Helicopters", dated October 2, 1962, except condition 15a. Type Certificate H2WE issued May 22, 1964. Date of application for Type Certificate November 13, 1961. FAA Exemption No. 596 issued October 18, 1966, grants exemption from FAR 6.328 to the extent necessary to permit the Type Certification of The Fairchild Hiller Model FH-1100 without the necessity of considering the jamming of a control valve or the cracking of the actuator cylinder as possible failures. Production Basis None. Prior to original certification of each aircraft manufactured subsequent to April 20, 1994, an 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 The basic required equipment as prescribed in the applicable airworthiness regulations (See certification basis) must be installed in the helicopter for certification. Hiller Report 63-96, "Master Equipment List, Model 1100" and Hiller Report 66-19 "Basic Weight Equipment List", Model FH-1100, contain a list of all required equipment that must be installed as well as optional equipment installations approved by the FAA. NOTE 1 Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions must be in each helicopter at the time of original certification and at all times thereafter (except in the case of operators having an approved weight control system). Ballast, when necessary, must be carried in accordance with Loading Instructions in the FAA Approved Rotorcraft Flight Manual. Fuel and Oil capacities as indicated are total tank capacities over and above "Trapped Fuel and Oil". The fuel tank capacity includes "Unusable" fuel of 2.5 gallons, for Model 1100 and 1.6 gallons (10.8 lbs.) for Model FH-1100 which cannot be used safely in all normal expected flight attitudes and must be included in the empty weight. NOTE 2 The following placard must be installed in clear view of the pilot: "This Helicopter must be operated in compliance with the operating limitations specified in the FAA Approved Rotorcraft flight Manual". For additional placards, see the FAA Approved Flight Manual. NOTE 3 The retirement times of critical parts are listed in the following tables. These values of retirement of service life cannot be increased without FAA Engineering approval. H2WE Page 6 of 8 COMPONENT PART NO. SERVICE LIFE HOURS MODEL 1100 MODEL FH-1100 Blade Assy., Main Rotor 24-53000-01 & -03 24-53100-01 & -02 24-53100-11, -13, & -15 6100 -- 6100 5970 -- 5970 Cuff Assy., Main Rotor 24-51402 24-51402-5 & -11 18350 -- -- 16350 Terminals, Main Rotor Drag Link 24-52002-7 & -9 29000 17900 Drag Link Assy., Main Rotor 24-52003 25000 13750 Bolts, Main Rotor Drag Attachment NAS1306-16 or 24-51447-3 24-51447-5 5570 4100 -- 4100 Tension-Torsion Bar Assy., Tail Rotor 24-55106 4670 4670 Spar, Tail Boom Fin Assy. 24-62030-7 24-62030-43 11255 -- -- 11255 Housing Assy., Tail Rotor Gear Box 24-25002 14120 14120 Output Housing, Tail Rotor Gear Box 24-25023 24-25023-3 & -5 7385 -- -- 7385 Output Shaft Assy., Tail rotor Gear Box 24-25031 2800 2800 Strut, Vertical, Transmission Mount 24-28030-1 & -2 24-28030-11 & -12 47835 47800 -- 47800 Gimbel Ring, Transmission 24-28020 -- 18050 Strut, Left Rear Transmission Mount 24-28046-1 20350 20350 Fitting Assy., Engine Bearer 24-61032-1 & -2 7000 7000 Isolation Link Assy., Upper Controls 24-30233-1 1263 800 Page 7 of 8 H2WE COMPONENT . PART NO SERVICE LIFE HOURS MODEL 1100 MODEL FH-100 Collective Arm Assy., Upper 24-31280-1 1722 1700 Incidence arm, Main Rotor 24-51406 1500 2700 Outer Ring Assy., Swashplate 24-34211 49250 49250 Ring Assy., Swashplate Cyclic Input 24-34205 24-34221 1411 750 -- 2960 Isolation Bracket Assy., Upper Controls 24-30200 24-30200-5 2850 2300 -- 2300 Link Assy., Collective Arm Support 24-31282-1 2850 2300 Sleeve Assy., Swashplate Support 24-34200 24-34200-11 22450 22450 -- 22450 Yoke Assy., Swashplate Drive 24-34207 12800 2800 Link Assy., Swashplate Drive 24-34209 36950 4450 Bellcrank Assy., Forward Lateral Cyclic 24-33304-1 4115 4100 Bellcrank Assy., Forward Longitudinal Cyclic 24-33305-1 4115 4100 Bendix Coupling Diaphragm and Flange Assy., Transmission End 19E49-3E 2489046 -- *1200 Diaphragm and Flange Assy., Transmission End 2489047 -- *1200 *One 600 hour extension allowed after compliance with Service Letter FH-1100-24-9. Lower Housing Assy., Transmission 24-23030-7 -- 3600 H2WE Page 8 of 8 NOTE 4a 4b There is not a Rotorcraft Maintenance Manual for the Model 1100 helicopter. Prior to civil airworthiness certification of the Model 1100 the applicant must prepare a rotorcraft Maintenance Manual containing all information essential for proper maintenance. The Model FH-1100 helicopter(s) must be serviced, maintained in accordance with instructions specified in the Model FH-1100: Service Manual, Inspection Guide, Structural repair Manual, and Overhaul Manual or Instructions for Continued Airworthiness for type design changes or other methods, techniques and practices acceptable to the Administrator. NOTE 5 Prior to issuance of FAA Certificate of Airworthiness for Model 1100 (Military Model OH-5A) helicopters, conformance with the approved Type Design Data must be established, including modifications for the commercial approved equivalent in accordance with Hiller Aircraft Corp. Engineering Report 64-54, "Deviation Report, Model 1100 Helicopter (Army OH-5A)". NOTE 6 These helicopters are approved for flight in non-icing conditions only. See FAA Approved Rotorcraft Flight Manual. NOTE 7 Model FH 1100, Serial Nos. 15, 206, 500 and subsequent, when modified to Master Drawing List (Hiller Report No. 66-13) Rev. D plus later E.O. Revisions. Once converted to the Model 250- C20B from the Model 250-C18, reverting back is not approved. Engine Allison Model 250-C20B Fuel ASTM Type Jet B (JP-4) and ASTM Type Jet A or A-1 (JP-5). See Rotorcraft Flight Manual for Fuel Mixture and Fuel Temperature Limitations. Engine Limits Torque Pressure Output Shaft Speed Take-off (5 min.) Max. Continuous 100% (274 SHP) 85% (233 SHP) 100% (6,000 rpm) 100% (6,000 rpm) Turbine Outlet Temp. Gas Gen. Speed N1 Take-off (5 min.) Max. Continuous 749°C (1380°F) 693°C (1280°F) 104% (53,000 rpm) 104% (53,000 rpm) NOTE 8 Allison Model 250-C10 (T63-A-5) engine is installed in Army Model OH-5A helicopters. ------END------