TCDS H1WE

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION H1WE Revision 6 SIAM HILLER UH-12L UH-12L4 October 28, 2014 TYPE CERTIFICATE DATA SHEET NO. H1WE This data sheet which is a part of type certificate No. H1WE prescribes conditions and limi tations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder: Siam Hiller Holdings, Inc. 925 M. Street Firebaugh, California 93622-2234 Type Certification Ownership Record: Hiller Aircraft Corporation transferred to Fairchild Industries, Inc. on 10/2/1959 Fairchild Industries, Inc. transferred to Heli-Parts, Inc. on 12/28/1972 Heli-Parts, Inc. transferred to Hiller Aviation on 12/28/1972 Hiller Aviation transferred to Rogerson Aircraft Corporation on 6/26/1984 Rogerson Aircraft Corporation transferred to Hiller Helicopters, a wholly owned subsidiary of Rogerson Aircraft Corporation on 6/29/1984 Hiller Helicopters, a wholly owned subsidiary of Rogerson Aircraft Corporation transferred to Rogerson Hiller Corporation on 11/14/1985 Rogerson Hiller Corporation transferred to Siam Hiller Holdings, Inc. on 7/14/1994 I Model UH-12L, Approved February 28, 1964 Model UH-12L4, Approved February 28, 1964 Engine Lycoming VO-540-C2A or TIVO-540-A2A Fuel 100/130 min. grade aviation gasoline Engine limits for all MP operations Engine HP RPM IN.HG. ALT. FT. VO-540-C2A 305 3200 26.0 S.L. 305 3200 25.2 (F.T.) 3,000 TIVO-540-A2A 315 3200 F.T. S.L. 315 3200 F.T. 13,000 H1WE 2 I Model UH-12L, Approved February 28, 1964 Model UH-12L4, Approved February 28, 1964 (Cont’d) Rotor limits and Power Off (Rotor Tach.) Power On (Engine Tach.) engine operating speeds Maximum 370 r.p.m. Maximum 3,200 r.p.m. Minimum 285 r.p.m. Minimum (S.L. to (VO-540-C2A only 10,000 ft.) 3,000 r.p.m. Avoid continuous (Above 10,000 ft. increase operation between 210 min. r.p.m. by 10 r.p.m. for and 225 r.p.m.) each additional 1,000 ft. of altitude) Airspeed limits (IAS) Model UH-12L (Basic Vne (Never exceed speed) 107 m.p.h. Skid Gear Configuration) (93 knots) IAS The above airspeed applies from S.L. to 6,000 ft. Decrease Vne 4 m.p.h. (3.5 knots) per 1,000 ft. of altitude above 6,000 ft. For limits with accessories installed see FAA Approved Rotorcraft Flight Manual. Model UH-12L4 (Basic Skid Gear Configuration). Vne 106 m.p.h. (92 knots) IAS The above airspeed applies from S.L. to 6,000 ft. Decrease Vne 3 m.p.h. (2.6 knots) per 1,000 ft. of altitude above 6,000 ft. For limits with accessories installed see FAA Approved Rotorcraft Flight Manual. Altitude limits Avoid operational areas as shown in FAA Approved Rotorcraft Flight Manual. C.G. range (longitudinal) Model UH-12L Sta. (79.5) to (84.8) (Basic Skid Gear Configuration) Model UH-12L4 Sta. (79.5) to (86.4) (Basic Skid Gear Configuration) For range with accessories installed see FAA Approved Rotorcraft Flight Manual. C.G. range (lateral) Left of helicopter centerline, 3.28 in. (Basic Skid Gear Configuration) Right of helicopter centerline,1.82 in. (Basic Skid Gear Configuration) For range with accessories installed see FAA Approved Rotorcraft Flight Manual. Datum 107.25 in. fwd. of tail boom - fuselage upper mounting face. Leveling means Top face of flanges under seat Maximum weight 3100 pound No. of seats Model UH-12L: 3 (53) Model UH-12L4: 4 (3 at 53, 1 at 25) Maximum baggage See loading instructions in FAA Approved Rotorcraft Flight Manual. Fuel capacity Main tank 46 gal. (82.9). See Note 1 for data on unusable fuel. Oil capacity Engine oil - 2 gal. (94) or 2.75 gal. (94) with auxiliary fuel tanks installed. Transmission oil - 1.12 gal. (94) Other operating FAA Approved Rotorcraft Flight Manual. limitations Rotor blade & control (Measured with respect to the mast) (Note: When the mast is vertical the helicopter is movements 1° nose up). 3 H1WE I Model UH-12L, Approved February 28, 1964 Model UH-12L4, Approved February 28, 1964 (Cont’d) Main rotor blade +8 1/2° ±0.1° to +20 1/2° ±1/4° collective travel Wobble plate cyclic Model UH-12L4 Model UH-12L travel Lateral 6 1/4° ± 1/4° Lateral 7° 45' ± 1/4° left right and left 4° 42' ± 1/4° right Longitudinal Longitudinal 9 1/4° ± 1/4° 9 1/4° ± 1/4° forward and aft forward and aft Tail rotor collective -4° ± 1/2° to +20° ± 1/2° travel Horizontal stabilizer Model UH-12L -4° ±1° setting Model UH-12L4 +3° ± 1° Serial Nos. eligible Model UH-12L 3500 to 4499 (See Note 5 for additional serial nos. eligible). Model UH-12L4 2500 to 3499 Certification basis CAR 6 dated December 20, 1956 including Amendments 6-1 through 6-4. Type Certificate H1WE issued February 28, 1964. Date of Application for Type Certificate February 28, 1961. Production basis Production Certificate No. 423WE, Spare Parts Only Equipment: The basic required equipment as prescribed in the applicable air worthiness regulations (See Certification Basis) must be installed in the helicopter for certification. Hiller Report 63-109, "Model UH-12L Master Equipment List", and Report 63-108, "Model UH-12L4 Master Equipment List", contain a list of all required equipment that must be installed as well as optional equipment installations approved by the FAA. NOTES: NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions, must be provided for each helicopter at the time of original certification. Ballast, when necessary, must be carried in accordance with Loading Instructions in the FAA Approved Rotorcraft Flight Manual. Fuel capacity as indicated is total tank capacity over and above "Unusable Fuel". The fuel tan k capacity includes "Unusable" fuel of 0.3 gallon, Model UH-12L and 3.2 gallons, Model UH-12L4, which cannot be used safely in all flight attitudes, and which must be included in the empty weight. NOTE 2. The following placard must be installed on the Pilot's Checklist: "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 Rotorcraft Flight manual. NOTE 3. The retirement times of critical parts are listed in the following table. These values of retirement or service life cannot be increased without FAA Engineering Approval. FINITE LIFE COMPONENT PART NO. HOURS Blade Assy., Main Rotor 53100 9250 Cuff Assy., Main Rotor 51456 7300 Hub, Main rotor 51455 6300 H1WE 4 NOTE 3. (Cont’d) FINITE LIFE COMPONENT PART NO. HOURS Rod Assy., Drag Link, Main Rotor 52125 57250 Terminal, Drag Strut, Main Rotor (Blade End) 52124-3 63750 Terminal, Drag Strut, Main Rotor (Cuff End) 52122-7 53600 Bolt (Drag Strut, Blade End) NAS 1307-24 47600 Bolt (Drag Strut, Cuff End) NAS 1307-21 46850 Bar Assy., Tension-Torsion, Tail Rotor 55054 12500 Blade Assy., Tail Rotor 55073 3240 Shaft Assy., Output, Speed Decreaser 25202-5 5790 Gimbal Assy., Outer, Engine Mounting 63309 6360 Yoke Assy., Mixing, Cyclic & Collective Controls 30034 63850 Arm, Mixing, Cyclic and Collective Controls, 30036 10940 Assy. of Bracket Assy., Transmission, Cyclic Controls 33333-5 2120 Gimbal Ring, Wobble Plate 34008 73500 Ring Assy., Wobble Plate, Inner 34017 77980 Sleeve Assy., Wobble Plate, Cyclic Controls 34038 42910 Rod End (Conair) 8127 69060 Yoke, Tail Rotor 55046 2500 NOTE 4. These Helicopters must be serviced and maintained in conformance with instructions given by Fairchild Hiller Corporation, in the pertinent model inspection guide, repair handbook, and service and overhaul manuals. NOTE 5. Model UH-12E Helicopters (3 and 4 place configurations) may be converted to Model UH-12L or UH-12L4 by accomplishment of Hiller Service Bulletins No. 2040 (Dwg. 10060) or No. 2045 (Dwg. 10059) respectively. NOTE 6. The type certificate holder has demonstrated compliance with FAR 133.43 for the UH-12L and UH-12L4 Helicopters for Class B (Jettisonable Sling Load) Rotorcraft - load combination at a maximum overall weight of 3500 pounds and a maximum sling load of 1000 pounds, when modified to incorporate cargo hook installation per Hiller Dwg. 91012-23 (UH-12L4) and 91012-25 (UH-12L). The helicopter weight without sling load is not to exceed certificated weight of 3100 pounds. For limitations see pertinent FAA Approved Rotorcraft Flight Manual Revision and Rotorcraft - Load Combination Flight Manual to be submitted by applicant for external load operator's certificate in accordance with FAR part 133. NOTE 7. Certain part numbers used on this model helicopter may be used on other model helicopters in which their use is life limited. These part numbers are listed in TCDS 4H11, H1WE, 4H10, 6H1, and 6H2 and FAA approved Hiller Instructions for Continued Airworthiness. If a full and complete service history from manufacture forward is not available that demonstrates these parts were used only on a model helicopter for which the part is not life limited then those parts shall be life limited to the lowest number of hours given in those TCDS’s or ICAs. If a full and complete service history from the manufacturer forward is available, and any operating time has occurred in a life limited model helicopter, that part shall be considered life limited at the lowest life limit listed even if transferred and used on a helicopter model for which it is not life limited. Only those parts for which a full and complete service history from manufacture forward is available and which shows only operating time on a helicopter model for which it is not life limited are considered not life limited. ...END...