TCDS 4H11

Page No. 1 2 3 4 5 6 7 8 9 10 11 Rev. No. 18 16 18 17 18 18 18 18 18 16 17 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4H11 Revision 18 SIAM HILLER UH-12E UH-12E-L (Army OH-23G) (Army H-23F) January 6, 2010 TYPE CERTIFICATE DATA SHEET NO. 4H11 This data sheet which is a part of type certificate No. 4H11 prescribes conditions and limitations 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 Hiller Aircraft Corporation transferred TC 4H11 to Records: Fairchild Industries, Inc. on 10/2/1959 Fairchild Industries, Inc. transferred TC 4H11 to Heli-Parts, Inc. on 12/28/1972 Heli-Parts, Inc. transferred TC 4H11 to Hiller Aviation on 12/28/1972 Hiller Aviation transferred TC 4H11 to Rogerson Aircraft Corporation on 6/26/1984 Rogerson Aircraft Corporation transferred TC 4H11 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 TC 4H11 to Rogerson Hiller Corporation on 11/14/1985 Rogerson Hiller Corporation transferred TC 4H11 to Siam Hiller Holdings, Inc. on 7/14/1994 I. Model UH-12E, Approved January 6, 1959 (Army OH-23G and H-23F) Engine Lycoming VO-540-A1A, VO-540-B1A, VO-540-B1D, VO-540-B1E, VO-540- C1A, VO-540-C1B, VO-540-B2D, VO-540-C2A, VO-540-B2E, VO-540-C2B, or VO-540-C2C. See Engine TCDS E-304 for more details. (Refer to appropriate Hiller Service Bulletin for requirements for interchanging engine models.) Fuel 100/100 Low Lead minimum grade aviation gasoline 4H11 2 Engine Limits for all Operations Maximum rpm: 3200 (305 hp) (All engines) Maximum manifold pressure: VO-540-A1A, -B1A Full Throttle VO-540-B1D, -B1E, -B2D, -B2E 27.2 in. Hg VO-540-C1A, -C1B, -C2A, -C2C 25.2 in. Hg Rotor Limits and Engine Operating Power Off (Rotor Tach.) Power On (Engine Tach.) Speeds Maximum 395 rpm Maximum 3200 rpm Minimum 314 rpm Minimum (sea level to 5000 ft.) 2900 rpm (above 5000 ft, increase minimum rpm by 20 rpm for each additional 1000 ft of altitude (See NOTE 13 for UH-12E with Main Rotor Blades P/N 53200-03) Airspeed Limits Configuration V NE (IAS) Skid Gear 96 mph (83 knots) Float Gear 86 mph (74 knots) The above airspeed applies from sea level to 5000 ft. Decrease V NE 2.5 mph (2.2 knots) per 1000 ft of altitude above 5000 ft. For limits with accessories installed, see the FAA-Approved Rotorcraft Flight Manual. (See NOTE 6 for 4-place configurations) Altitude Limits See FAA-Approved Rotorcraft Flight Manual C.G. Range (Longitudinal) Configuration Skid Gear Sta. (79.5) to (84.8) Float Gear Sta. (81.0) to (84.8) For range with accessories installed, see the FAA-Approved Rotorcraft Flight Manual. See NOTE 6 for 4-place configuration See NOTE 13 for UH-12E with Main Rotor Blades P/N 53200-03 Datum 107.25 in. fwd of tail boom-fuselage upper mounting face C.G. Range (Lateral) Left of helicopter centerline, 4.83 in. Right of helicopter centerline, 1.85 in. (See NOTE 13 for UH-12E with Main Rotor Blades P/N 53200-03) Leveling Means Top face of flanges under seat Maximum Weight 2750 lb (See NOTE 7 or NOTE 13 for increased maximum weight) Number of Seats 3 (sta. 53) (See NOTE 6 for 4-place configuration) Maximum Baggage See loading instructions in FAA-Approved Rotorcraft Flight Manual Fuel Capacity Total 46, 66, or 86 gal. One main tank 46 gal. (sta. 82.9). One or two auxiliary tanks installed per Hiller Service Bulletin 2008, 20 gal. each (sta. 85.8). See NOTE 1 for unusable fuel data. Oil Capacity 9.2 qt (sta. 94), or 12.3 qt (sta. 94) with auxiliary fuel tanks installed. Other Operating Limitations See FAA-Approved Rotorcraft Flight Manual 3 4H11 Rotor Blade and Control Measured with respect to the mast. Note: When the mast is vertical, the helicopter is 1° movement nose up Main Blades: Collective Pitch Low setting +1.0 °, total travel 10.5° (Measured at Retention Plate) (Low setting is determined as the lowest which will preclude overspeeding in autorotation) Teetering Control rotor ±12°, Main Rotor ±9° Wobble Plate: Lateral 7.7 ° to 8.3° Longitudinal Fwd. 8.0 ° to 8.5°, Aft 9.0° to 9.2° Control Blades: Neutral ±9° incidence (Rotor hub and wobble plate perpendicular to mast) Tail Rotor Blade Flapping +17 ° to -17° Tail Rotor Pitch Rigging T.R. Gearbox P/N Travel (degrees) 25200 +15 to -3 25200-3 or -5 +16 to -4 25300-5 +20 to -4 Horizontal Stabilizer Setting Configuration(With helicopter level) Skid Gear 0° Float Gear -10° Float Pressure Differential 8.0 psi maximum (See NOTE 6 for 4-place configuration) Serial Nos. Eligible Model UH-12E; 942, 954, 2001 through 2166, 2172 through 2229, 2233 through 2241,2246 through 2248, 2253 through 2255, 2257 through 2282, 2286 through 2292, 2294 through 2306, 2309 through 2499, 2518, 5001 and up and S/N HA3001 through HA3999 for aircraft built from spare and surplus parts by Hiller Aviation. (See NOTE 12 for additional serial numbers.) Army OH-23G; 1439 through 1760 and 1762 through 1876. Army H-23F; 2167 through 2171, 2230 through 2232, 2242 through 2245, 2249 through 2252, 2256, 2283 through 2285, 2293, 2307, and 2308. In order for individual OH-23G or H- 23F helicopters procured under military cognizance and not having been issued a Form FAA970 "Conformity Certificate Military Aircraft", to be eligible for a Standard Airworthiness Certificate as a Model UH-12E, it must be determined in each case that the helicopter conforms to the Model UH-12E type design per CAR 1.67(d) or FAR 21.183(d). Certification basis CAR 6 dated December 20, 1956, including Amendments 6-1 and 6-2, Voluntary compliance with Amendment 6-3 has been established. Type Certificate 4H11 issued January 6, 1959. Date of Application for Type Certificate December 13, 1957. 4H11 4 Production Basis None. Before original airworthiness certification of each aircraft manufactured subsequent to April 23, 2003, an FAA representative must perform a detailed inspection for workmanship, materials, conformity with the approved technical data, and a check of the flight characteristics. In the event of an application for a standard airworthiness certificate or, if an applicant intends to produce new aircraft under 14 CFR § 21.183 (d), and the applicant is manufacturing, building, or assembling to another person’s type certificate, the applicant must provide written evidence of permission from the type certificate holder. Conduct of such activity without written evidence of permission may be a violation of 49 U.S.C. § 44704(a)(3). Equipment The basic required equipment as pr escribed in the applicable airworthiness regulations (See Certification basis) must be installed in the helicopter for certification. Hiller Report 59-30, "Model UH-12E Master Equipment List," contains a list of all required equipment that must be installed as well as optional equipment installations approved by FAA. (See NOTE 6 for 4-place configuration.) II. Model UH-12E-L, Approved September 18, 1963 Engine Lycoming VO-540-C2A. See Engine TCDS E-304 for more details. Fuel 100/100 Low Lead minimum grade aviation gasoline Engine Limits for all Operations Maximum rpm: 3200 (305 hp) Maximum manifold pressure: 26.0 in. Hg at sea level varying linearly to 25.2 in. Hg at 3000 ft. Rotor Limits and Engine Operating Power Off (Rotor Tach.) Power On (Engine Tach.) Speeds Maximum 370 rpm Maximum 3200 rpm Minimum 285 rpm Minimum (sea level to 10,000 ft.) 3000 rpm (above 10,000 ft, increase minimum rpm by 10 rpm for each additional 1000 ft of altitude Airspeed Limits Configuration V NE (IAS) Skid Gear 106 mph (92 knots) The above airspeed applies from sea level to 6000 ft. Decreases V NE 3 mph (2.6 knots) per 1000 ft of altitude above 6000 ft. (For limits with accessories see FAA-Approved Rotorcraft Flight Manual) Altitude Limits See FAA-Approved Rotorcraft Flight Manual C.G. range (Longitudinal) Configuration Skid Gear Sta. (79.5) to (84.8) (For limits with accessories see FAA- Approved Rotorcraft Flight Manual.) Datum 107.25 in. fwd of tail boom-fuselage upper mounting face. C.G. Range (Lateral) Left of helicopter centerline, 1.82 in. Right of helicopter centerline, 1.82 in. Leveling Means Top face of flanges under seat 5 4H11 Maximum Weight 3100 lb Gross weights of up to 3500 lb are permitted for Cargo Hook operations in accordance with Hiller FAA approved “Model UH-12E-L Helicopter Flight Manual 3500 lb Gross Weight Operation with Cargo Hook” dated April 4, 1966 or later FAA approved revisions. Operations above 3100 lb gross weights are in restricted category under FAR 133. Number of Seats 3 (sta. 53) Maximum Baggage See loading instructions in Flight Manual. Fuel Capacity Total 46, 66, or 86 gal. One main tank 46 gal. (sta. 82.9) one or two auxiliary fuel tanks installed per Hiller Service Bulletin 2008, 20 gal. each (sta. 85.8) See NOTE 1 for unusable fuel data. Oil Capacity Engine oil - 8 qt (sta. 94) or 11 qt (sta. 94) with auxiliary fuel tanks installed Transmission oil - 4.5 qt (sta. 94) Other Operating Limitations See FAA-Approved Rotorcraft Flight Manual Rotor Blade and Control Measured with respect to the mast. Note: When the mast is vertical, the helicopter is 1° movement nose up Main Rotor Blade Collective Travel +8 1/2 ° ±0.1° to +20 1/2° ±1/4° Wobble Plate: Lateral 7 ° 45' ±1/4° left and 4° 42' ±1/4° right Longitudinal 9 1/4 ° ±1/4° forward and aft Tail Rotor Blade Flapping +17 ° to -17° Tail Rotor Pitch Rigging T.R. Gearbox P/N Travel (degrees) 25300-3 +20 to -4 25300-5 +16 to -4 Horizontal Stabilizer Setting Configuration (With helicopter level) Skid Gear -4° ±1° Serial Nos. Eligible Model UH-12E; 942, 954, 2001 through 2166, 2172 through 2229, 2233 through 2241, 2246 through 2248, 2253 through 2255, 2257 through 2282, 2286 through 2292, 2294 through 2306, 2309 through 2499 limitations. Certification Basis CAR 6 dated December 20, 1956, including Amendments 6-1, 6-2, and 6-3. Compliance with Amendments 6-4 required for rotor and control systems only. Type Certificate 4H11 reissued September 18, 1963. Date of Application of Type Certificate February 28, 1961. Production Basis None. Before original airworthiness certification of each aircraft manufactured subsequent to April 23, 2003, an FAA representative must perform a detailed inspection for workmanship, materials, conformity with the approved technical data, and a check of the flight characteristics. In the event of an application for a standard airworthiness certificate or, if an applicant intends to produce new aircraft under 14 CFR § 21.183 (d), and the applicant is manufacturing, building, or assembling to another person’s type 4H11 6 certificate, the applicant must provide written evidence of permission from the type certificate holder. Conduct of such activity without written evidence of permission may be a violation of 49 U.S.C. § 44704(a)(3). Equipment The basic required equipment as pr escribed in the applicable airworthiness regulations (See Certification basis) must be installed in the helicopter for certification. Hiller Report 63-76, "Model UH-12E-L Master Equipment List" contains a list of all required equipment that must be installed as well as optional equipment installations approved by the FAA. Data Pertinent to all Models 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 tota l tank capacities over and above "Trapped Fuel and Oil." The main fuel tank capacity includes "Unusable" fuel of 0.3 gallon, which cannot be used safely in all flight attitudes, and which must be included in the empty weight. Unusable fuel in the optional auxiliary fuel tanks is negligible. 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 tables. These values of retirement or service life cannot be increased without FAA Engineering approval. Life limited components interchanged between UH-12 series models or configurations must be restricted to the lowest service life indicated for the models or configurations that the individual part has been used on. If previous service history does not identify the model or configuration, the lowest service life of all possible models or configurations must be used. Life limited components removed at retirement are to be destroyed or conspicuously marked to prevent inadvertent return to service. MODEL UH-12E FINITE LIFE COMPONENT NOMENCLATURE PART NO. REPLACEMENT PERIOD HOURS Rotors and Drives Blade Assy., main rotor (Parsons) 2253-1101-03 2500 Blade Assy., main rotor (Parsons) 2253-1101-04 2500 NOTE A Blade Assy., main rotor 53200-03 6670 NOTE H Shaft Assy., output speed decreaser 25202, -5 5790 Plate set, main rotor tension-torsion 51430-1, -3, -5 3350 (component of 51430-1 and -3 assembly) Hub Assy., main rotor 51437-9 1540 (Service Bulletin No. 2014 not complied with) Hub Assy., main rotor 51437-9 2500 NOTE B (Service Bulletin No. 2014 complied with) Hub Assy., main rotor 51437-11, -14, -901, -911 2500 7 4H11 MODEL UH-12E FINITE LIFE COMPONENT (continued) NOMENCLATURE PART NO. REPLACEMENT PERIOD HOURS Pin, main rotor outboard tension torsion 51452, -1 643 Fork, main rotor blade root 52110-3 2500 Drag strut, main rotor blade 52120, -5 2500 Drag strut, main rotor blade 52120-7 2500 NOTE H Bar Assy., tail rotor tension-torsion 55054, -1 12500 Blade Assy., tail rotor (3-place model) 55073 (All Dash Numbers) 5400 Blade Assy., tail rotor (4-place model) 55073 (All Dash Numbers) 3240 Yoke, Tail Rotor 55046 (All Dash Numbers) 2500 NOTE J Power Plant Snubber Assy., engine, longitudinal 63192-7, -11 4650 Snubber Assy., engine, lateral 63192-5, -9 4650 Bracket, engine snubber 63197 6160 Bracket, engine snubber 63197-5 9850 Attaching bolts, engine snubber AN3 600 (used to attach P/N 63197 bracket to engine deck and snubber) Gimbal outer engine mounting 63309, -3, -9, -11 6300 Gimbal outer engine mounting 63309, -3, -9, -11 5480 NOTE H One way clutch (Borg-Warner) X132591 375 NOTE C One way clutch (Borg-Warner) X132815 375 NOTE C Collective and Cyclic Controls Flyweight collective pitch ballast 31197-3 2500 Bellcrank, collective control 31318 15000 Tube, collective control 31319, -3 23500 Shaft, dual collective control 31321 10400 Block Assy., collective stick 31344, -3, -5, -7, -9 6400 NOTE I Push rod, collective control 31365 8150 NOTE H Arm, collective pitch blade incidence 31389 14500 NOTE H Incidence Arm 31113-13 13400 NOTE H (Old style-Includes Fafnir or Shafer Rod Ends) Incidence Arm 31333 WA7-75083-S1. 13400 Note H (Heim Rod Ends on Condition) Arm Assy., collective and throttle controls 31403 21500 (4-place model) Scissor, cyclic control, lower Spar and Blade 34141, -5 275 Note D Assy., Control Rotor (all faired Assys.) Fairing Blade Assy., Control Rotor 36003, 36129, 36129-25 2500 NOTE F Trunion, Control Rotor Hub 36116-4 5150 NOTE E Cuff Assy., Control Rotor (used with faired assy.) 36124 5150 NOTE G Cuff Assy., Control Rotor (used with unfaired assy.) 36124 6860 NOTE G Cuff Assy., Control Rotor (used with unfaired assy.) 36124 5550 NOTE H, G NOTE A - The replacement period for blade assemb lies S/N 4261 and subsequent is 6670 hours. The replacement period for blade assemblies S/N 3396 through S/N 4260 is extended to 6670 hours if these blades are returned to the manufacturer for installation of rolled-thread anti-node bar assembly P/N 2253-1124 before 2500 hours time in service. NOTE B - The 2500 hour service life total includes service time prior to compliance with Hiller Aviation Service Bulletin No. 2014. 4H11 8 NOTE C - Unlimited life after incorporation of Hiller Aviation Service Bulletin No. 2027A. NOTE D - Any unfaired control rotor blade assembly with an "R" after the part number (reworked per Hiller Aviation Service Bulletin 36-1, Revision 2) must be replaced upon attaining 2500 additional operating hours after rework. NOTE E - 5150 hour limitation applicable to trunions used with control rotor fairing and blade assy. P/N 36003, 36129, or 36129-25. NOTE F - If any of these part numbers are reworked in accordance with Hiller Aviation Service Bulletin 36-1, Revision 3, the part must still be replaced upon attaining a total time of 2500 hours regardless of the replacement period shown in Hiller Aviation Service Bulletin 36-1, Revision 3. NOTE G - All control rotor cuff assemblies installed with control rotor blade assemblies (both faired and unfaired) with an "R" after the part number (reworked per Hiller Aviation Service Bulletin 36-1, Revision 3) must be replaced upon attaining the original retirement life, but not to exceed 2500 additional hours after rework. NOTE H - These new or revised replacement periods ar e for the "Hiller Model UH-12E with new main rotor blades 53200-03." (See NOTE 13 for installation of main rotor blade 53200-03.) NOTE I - Part number 31344 Collective Stick block asse mbly is a matched set consisting of 31344-3 and 31344- 5. Part number 31344-7 Collective Stick block assembly is a matched set consisting of 31344-5 and 31344-9. Serial number for both lower and upper blocks must be the same. NOTE J - Life limited applies only when increased pitch style tail rotor gearbox part number 25300-5 tail rotor speed decrease is used. MODEL UH-12E-L FINITE LIFE COMPONENT NOMENCLATURE PART NO. REPLACEMENT PERIOD HOURS Rotors and Drives Main Rotor Blade Assy 53100 9250 Cuff Assy., main rotor blade 51456 7300 Rod, drag strut, main rotor blade WS7-125083-14L-20B-083-856-HT 2080 Terminal, drag strut, main rotor blade 52122-3, -5 2100 Bolt, drag strut, main rotor blade AN177 710 Hub Assy., main rotor 51455 6300 Rod Assy., drag strut 52125 57250 Terminal, drag strut, main rotor (cuff end) 52122-7 53600 Terminal, drag strut, main rotor (blade end) 52124-3 63750 Bolt, drag strut, main rotor (blade end) NAS 1307-24 47600 Bar Assy., tension-torsion, tail rotor 55054, -1 12500 Blade Assy., tail rotor 55073 (All Dash Numbers) 5400 Bolt, drag strut, main rotor (cuff end) NAS 1307-21 46850 Yoke, tail rotor 55046 (All Dash Numbers) 2500 Power Plant Shaft Assy., output 25202, -5 5790 Engine outer gimbal ring 63309, -3, -9, -11 6360 9 4H11 MODEL UH-12E-L FINITE LIFE COMPONENT (continued) NOMENCLATURE PART NO. REPLACEMENT PERIOD HOURS Collective and Cyclic Controls Bracket Assy., transmission, cyclic controls 33333-5 2120 Bracket Assy., transmission, cyclic controls 33333-1 150 Bracket Assy., transmission, cyclic controls 33344-1 150 Inner Ring Assy., (wobble plate) 34017 77980 Sleeve Assy., wobble plate cyclic controls 34038 42910 Gimbal ring, wobble plate 34008 73500 Yoke Assy., mixing cyclic & collective controls 30034 63850 Push-Pull Rod Assy., collective 31468 150 Arm, Mixing Assy., cyclic & collective controls 30036 10940 Rod end MDV46-16TMC 150 Rod end (Conair) 8127 69060 NOTE 4. These helicopters must be serviced and maintained in conformance with current Hiller Aircraft Corporation Instructions for Continued Airworthiness (Inspection Guide), repair handbook, and service and overhaul manuals for pertinent model. NOTE 5. Deleted May 10, 1960. NOTE 6. Model UH-12E 4-Place Conf iguration and 4-Place Modification Kit, Hiller Dwg. No. 10044, installed per Hiller Service Bulletin No. 2010. The following additional limitations apply: (For limits with accessories installed see FAA-Approved Rotorcraft Flight Manual.) (a) Airspeed limits Configuration V NE (IAS) Skid Gear 95 mph (82 knots) Float Gear 86 mph (74 knots) Decrease VNE 2.5 mph (2.2 knots) per 1000 ft above 5000 ft (b) C.G. range Skid Gear Sta. (79.5) to (84.8) (Longitudinal) Float Gear Sta. (81.0) to (84.8) (c) No. seats 1 (sta. 25), 3 (sta. 53) (d) Horizontal stabilizer P/N 37027 +3° (Measured with helicopter level) (e) 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 60- 60 "Model UH-12E (4-place) Master Equipment List" contains a list of all required equipment that must be installed as well as optional equipment installations approved by the FAA. NOTE 7. UH-12E, 3- and 4-place configurations are eligible at 2800 pounds maximum weight when items specified by Hiller Service Bulletin No. 2031 are installed. See FAA-Approved Rotorcraft Flight Manual for operation limitations. 4H11 10 NOTE 8. 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) and No. 2045 (Dwg. 10059) respectively. NOTE 9. Model UH-12E Helicopters (3 -place configuration only) may be converted to Model UH-12L by accomplishment of Hiller Service Bulletin No. 2039A (Dwg. 10060). NOTE 10. The Type Certificate holder has demonstrated compliance with FAR 133.43 for the UH-12E Helicopters for Class B (Jettisonable Sling Load) Rotorcraft - Load Combination at a maximum overall weight of 3100 pounds and a maximum sling load of 1000 pounds, when modified to incorporate cargo hook installation per Hiller Dwg. 91012. The helicopter weight without sling load is not to exceed certificated weight of 2750 pounds (2800 pounds if Hiller Service Bulletin No. 2031 has been complied with per NOTE 7. of this document). 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 11. The Type Certificate holder has demonstrated compliance with FAR 133.43 for the UH-12E-L Helicopters for Class B (Jettison 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. 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 133 NOTE 12. Certain Model UH-12D helicopters may be c onverted to Model UH-12E in accordance with Hiller Drawing No. 10054, Revision B, or subsequent FAA-Approved revisions thereto. Refer to this drawing for serial numbers eligible for such conversion. NOTE 13. The main Rotor Blades P/N 53200-03 ma y be installed on Hiller Model UH-12E by accomplishment of Hiller Service Bulletins No. 10-2 and No. 51-3. FAA-Approved Rotorcraft Flight Manual "Hiller Model UH-12E Helicopter with 53200-03 Main Rotor Blades" is required. The following limitations apply. (For limits with accessories installed, see FAA-Approved Rotorcraft Flight Manual "Hiller UH-12E Helicopter with 53200-03 Main Rotor Blades”.) (a) Rotor limits and engine operating speeds Power Off (Rotor Tach) Power On (Engine Tach) Maximum 395 rpm Maximum 3200 rpm Maximum 314 rpm Minimum (S.L. to 10,000 ft.) 3000 rpm (Above 10,000 ft increase minimum rpm by 20 rpm for each additional 1000 ft of altitude) (b) Airspeed limits Configurations V NE (IAS) Skid Gear 2801 to 3100 pounds 75 mph (65 knots) decrease VNE 2.5 mph (2.2 knots) per 1000 ft above 5000 ft (c) Altitude limits Configuration Skid Gear - 2800 lb S.L. to 15,000 feet Skid Gear-2801 to 3100 lb S.L. to 7400 feet 11 4H11 (d) C.G. Range Configuration Skid Gear