Give it a minute to download, it's well worth it. Anonymous April 26, at PM. Newer Post Older Post Home. Subscribe to: Post Comments Atom. I flew off and on through the years with approximately hours mostly flown in the Cessna , and the Piper Warrior. I am on my way to becoming a Certified Flight Instructor CFI helicopter pilot and this is my log of those experiences on this journey. Also included are other miscellaneous ramblings that may pop into my head along the way.
I'm retired from the Air Force, enlisted E View my complete profile. An airfoil which modi- fies the airflow asound the cabin, extends above and across the canopy upper windshield sevtion. The floot stricture supports the instrument panel aud provides for mounting the taif rotor direc tional control pedals.
The horizontal platform pro- vides mounting facilities and support for the seats and collective and cyclic flight controls, The vertical bulkhead forms the rear of the cabin and mounts the upright portions of the seats. At the center rear of the vertical bulkhead, the main totor mast is secured to the upper structural member of the bulkhead; additionaliy, the mast is rigidly at- tached to the center frame by three structural members.
The two door frames are riveted to each side of the struc- tural unit formed by the seat and floor structures, «A lower forwerd fairing is attached to the forward edge of the floor structure and extends downward and rearward to the forward cross- beam of the landing gear.
It provides for streamlining below the cabin and supports the engiie uir induction system A tailboom assembly extends rearward from its attachment to the cen- ter frame section. Ii is a monocoque structure of aluminum and houses the tail rotor drive shafl and tail rotor control rod. At the aft end, it supports the tail rotor gearbox and tail rotor, in addition to the horizon tal end vertical stabilizers. Fore and aft crossbcams attach to the underside of the center frame section and pro- yide for attachment of struts and oleo-type, shock-absoxbing dampers.
Right and left stabilizer asscmblies connect the outboard ends of the crossbeams end provide stepping areas for entry to each side of the cabin and for servicing and inspecting the helicopter. Skid tubes at- tached to contoured fittings af the lower ends of the struts provide at- tachment points for installation of ground handling wheels.
The engine is mounted horizontally on shack mounts within the center frame section. The engine transmits power through a belt drive transmission assembly to the main transmission and tail rotor drive shaft.
The lower pulley of the belt drive receives power ftom the engine crankshaft and directs the power to the upper pulley through a matched set of V-belts. An idler pulley running ageinst the set of belts and connected to a pi- Jot-controlled actuating mechanism operates as'2 clutch to engage and disengage the upper pulley with the lower pulley. The upper pulley at- taches to the input shaft of the main trensmission and incorporates en over running clutch that permits the main rotor to drive during the autorotation without engine power.
The main transmission mounts on the lower end of the nonrotating main rotor mast and is rigidly fixed in position by support members connected to the center frame section. The main roter drive shaft transmits power from the main transmission to the main xotor hub. A thrust bearing, acting upon 2 shoulder on the drive shaft, positions the shaft within the mast.
The three-bladed main rotor system is fully articulated vith flapping hinges and lead-lag hinged blade attachment. The blades are interconnected by a high-strength, ten sion-torsion strap assembly. The helicopter main fuel tank has a capacity of 30 or 33 U. The auxiliary fuel tank with 4 capacily of 19 U. The tanks main and auxiliary may be serviced from either filler neck by gravity. Main rotor geometric disc area Main rotor geometric solidity ratio 0. Vertical stabilizer area to tailboom 2. Model C Helicopter English Br eV W- yn Figure Table 1.
Model Helicopter Table 2. Table 4. Table 6. Auxiliary Fuel Quantity. Aircraft Instruments ALT x voooet. FT] FT. Remove R. Above soa level, reduce Va in accordance with Figure Lateral CG limits At Station 95 Note: Lateral datum line is the centerline of the helicopter through the main rotor.
The minimum cpm is With rator disengaged, avoid engine idle speed in excess of rpm. The initial clutch engagement speeds. Table Table , Fue! Quantity, see Table Table 2. The color coding is the sume, Early style instrument clusters may be replaced with current style instruments clusters. The color coding is the same Farly style instrament may be replaced with current style. Origin, fn Flight - J. At an altitude of 50 feet, begin steadily to apply back cyclic stick to docrease forward speed.
Inthe event of engine failure at night, do not turn on landing light above 1, feet above terrain in order to preserve battery power. Establish a level attitude prior to ground contact. Do not reduce collective pitch.
Apply tight pedal to prevent excessive yawing. Apply collective pitch as necessary in order to. Release seat bell and shouldcr harness. Release seat belt and shoulder harness, Open both doors and cxit helicopter.
Note: Indicator was factory-installed beginning with aireraft No. Indicator kits may be retrofitted on early aircraft. Reissued: 21 Seplember Model Helicopter Pick out landing spot. Lf less-than feet above terrain, proceed with autorotation landing.
Mixture - push to FULL RICH position when engine fires, Note: [f fuel hoost pump was on at time of engine stop- page, flooded condition may have resulted necessitat- ing additional use of the starter. Exit aircraft with fire extinguisher. Set battery switch in OFF position. Pilo 's Fiight Manual. Pilot's Preflight Guide 43 Figure Refer to Section Service the helicopter as required.
Determine that the helicopter loading is within limits. Refer to Section H and VI. Power on - to rpm Power off - to Section II Limitations Maximum operating altitudes. Enroute - 10,ft Density Alt. Maximum Gross Weight in the cabin: pounds Glove Box; 20 pounds.
Maximum Gross Weight lbs. Fuel capacity - Main and Aux. Lower collective pitch. Enter normal autorotation. Establish a steady glide of 52kt IAS Approximately. At approximately 10 feet, coordinate collective pitch with forward movement of cyclic stick to level aircraft and cushion landing. Make ground contact with aircraft level. Conduct takeoff operation in accordance with the restrictions shown on Height Velocity Diagram. In event of power failure during takeoff, lower collective pitch altitude permitting , in order to maintain the rotor speed.
The amount and duration of collective reduction depends upon the height above the ground at which the engine failure occurs. As the ground is approached, use aft cyclic and collective as needed to decrease forward and vertical velocity. Establish a level attitude prior to ground contact.
Apply collective pitch as necessary in order to cushion landing. A power failure is indicated by sudden yawing of the ship to the left. Apply right pedal to prevent excessive yawing and right stick to minimize drift. Follow the procedures for autorotation approach and landing. Upon contact with water, proceed as follow: 1. Lower collective pitch and apply sidewards cyclic stick after contact is made with water.
Release seat belt and shoulder harness. Open both doors and exit helicopter. Descend to hovering altitude over water; 2. Unlatch doors; 3. Passenger exit aircraft; 4. Fly a safe distance away; 5. Turn battery and alternator switches OFF; 6. Close twistgrip to idle position; 7. Allow aircraft to settle in a level altitude, apply full collective; 8. When aircraft begins to roll, reduce collective to full down. Release seatbelt and shoulder harness;
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