Schweizer 300c manual pdf

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. Check the helicopter performance data. Refer to Sections V, VI and vit. Determine that a Daily inspection in accordacce with the Lndbook of Maintenance Instructions HMD kas been accomplished within 24 hours prior to the first flight of cack day. Damage is defined as any condition that is not normal or not within limits, Fxamples of conditions to look for are: inoperable equipment, excessive leakage, discoloration duc to heat, dents, cracks, punctures, abrasion, chaffing, galling, nicks and evidence of corrosion.

Thesc are the most common types of damage; however, do not limit inspection to the above conditions. Late model helicopters have strobes in lieu of rotating beacon mounted with navi- gation lights. If any damage is ob- served, replace bact pricr to next flight. Observe bearing to determine if bearing inner race is a tight fit on lower pulley shaft. Idler pulley for smooth rotational movement and fore and aft freedom of movement Clutch control cable, spring assembly, and lower end of spring retainer Chutch engaged; With a flashlight care- fully check clutch cable where it enters spring assembly for any broken strands al the end of the internal swaged fitting No broken strands permitied; Check spring tension mark.

Clutch engaged and disengaged: Check lower ead of spring retainer tube for wear and wear deposits. Clutch disengaged: Check spring as- sembly for freedom. Check scourity and condition of pins Refer to Paragraph O Figure Figure Turn fuel boost pump to ON position; check for pressure indication.

Magneto switch to BOTH. Engage starter. NOTE: Idle mixture and rpm are set at home. Pilot's Flight Manual Mode! Disconnect external power if used. Set alternator switch in ON position. Proceed with normal starting sequence. NS After clearing engine, close throttle. Procced with normal starting sequence.

Model C Helicopter Check collective pitch stick for full down and locked condition. Check tail rotor pedals for neutral position. NOTE; Do not use trim controls to move cyclic stick into position; this practicc induces strain on the triin control system and may burn out the trim motors. Manus ily ccnter cyclic stick; use longitudinal and Jateral trim as nesessary to stabilize stick in center position, then tock friction.

Visually check aiicraft vicinity for personnel and equipment. Using throtite, set engine speed rpm. NOTE: Maintain fixed throttle during rotor engage- ment. NOTE: If practical, warm up engine before the clutch is engaged; do not cxceed rpm with clutch dis- engaged. After engaging clutch, increase rpm to , maintain rpm untit a definite rise in temperature is seen. Repeat this procedure uati! Chock engine oil emperature and pressure within green arcs.

Check press-to-test low fuel caution light OFF. Check operation of low voltage warning light if I installed. NOTE: Proper alternator operation is indicated by movement of ammeter needle. Raise collective pitch stick to 14 inches MP at rpm. Reissued: 2! Cheek throttle override. Do not raise collective. Check the following items for proper indication or position, before takeof!. NOIR: Boos: pump must be ON during takeoff and landing and when under feet AGL; operation of the pump during other engine operations is permissi- ble at the discretion of the pilot.

Cylinder head temperature. Engine oif pressure. Mixture control FULD. Adjust cyclic im controls as desired. NOE: When maximum performance is required, use. For climb out, apply only sufficient additional collective to maintain ground clearance until translational lift is obtained.

Que inch of MP above hover power is recommanded. Do not exceed MP placard limit Perform climb out at rpm. Lower nose and accelerate to clint spved following profile in with Hcight Velocity Diagram Figure , Above AGL, reduce rpm to to range NOTE: Above the critical altitude altitude at which full throuleis vbtained , exercise caution to assure that the throttle system is not in the override position when reducing collective o avert overspeed.

Avoid excessive nose down attitude. QS NOTE: Under no circumstances should the limiter be used as a governor to replace pilot skill; the occasions for limiter use should bo extremely rare and only to prevent a catastrophic engine overspeed Slow airspeed to approximately 60 mph for a normal approach and reduce collective for the desired rate of descent.

Maintain rpm. Sot at normal idle stop, do not override. NOTE: Engine specd will immediately decrease to idle level. Rotor speed, however, will decline gradu- ally. The next step must be performed before rotor tachometer necdle superimposes with engine tachome- ter needle. NOTE: Engine rpm rise is required to be between 25 and spm for this check.

Lf rpm rise is not within the required limits, notify the appropriate maintenance personne! Accomplish an idle speed check as follows: Operate helicopter at operational rpm with rotor systema chgaged, friction on the collective and cyclic controls, and governor disen- gaged. Rapidly rotate throttle closed and into full override position. NOTB: The first check throttle into full override should produce an idle speed no less then rpm.

The second check throttle et normal idle stop should produce an idle speed no greater then cpm. If engine idle speed is not within the Fequired limits, notify the ap- propriate maintenance personnel to perform adjustments in accor dance with the Basic HML Perform a fuel boost pump check.

Operate helicepter at idle rpm with fuel boost pump ON. Ifa change in cagine rpm is observed, ground helicopter end trou- bleshoot fuel system. After landing, maintain rpm with full Gown collective pitch for two minutes; watch for cylinder head temperature to decrease and stabilize. Tighten all friction controls. Sct magneto switch in OFF position. Set alternator switch in OFF position. Sct fuel shutoff valve to OPEN position. Set fuel boost pump switch in ON position.

Set hicater control switch in HEAT position. Position push-pull control to regulate cabin temperature. A Awe YD. Set heater control switch to OFF position to discontinue beater operation.

Sct beater control switch in HEAT position. Set heater control switch to OFF position to discontinue heater j operation, f Use the handle to direct the searchlight beam. Check that the red warning light is out. Noise Level Figure Airspeed Calibration Curve Figure See Figure , Airspeed Calibration Curve. Psoa Center of Gravity Envelope Balance Diagram Sample Weight and Balance.

Worksheets ee 6S , Figure Skid Mounted Ballast Weight-Leteral Skid Mounted Ballast Weight - Longitudinal. Sind diese Inhalte unangemessen? Dieses Dokument melden. Markieren Sie unangemessene Inhalte. Jetzt herunterladen. Zu Seite. Im Dokument suchen. Each section is provided with an INDBX, listing the data by paragraph number, title, and the page number. A page number and date summary lists the numbers and date of the most recent change.

The summary for aon-PAA approved data is taken care of in the front matter preceding this section ; a similar sumunary is provided for FAA approved data in Section Il, for all in- formation in Sections Il through V. FAA regulations require that limitations not to be exceeded, Reissued: 21 September 2. The original weight and balance report and the equipment list, equipment both required and optional installed on the helicop- tor af the time of licensing are also contained in this section.

The subjects chosen are those with which the pilot will have direct involvement, either while at a normal baso of operations or in the field. A number of pieces of optional equipment are available for the performance of specific tasks. In addition, there is a tabular listing of all options and modifica- tion kits in part number sequence, Notation is made as to whether an FAA approved supplement is supplied. A table shows the compatibility of the various options with one another.

Other information is given in step by step procedures, graphs, charts or tabular form The informetion ia the step by step procedure is presented in the imporative mode; each statement describes a particular operation to be accomplished.

New or changed information is designated by a heavy black change bar in the margin. Advanced technology has been used in the design and construction of the helicopter, resulting in excellent handling capabilities, high payload to empty-weight ratio, passenger and crew safety, and per formance capabilities of the higher order even when operating dur- ing adverse density altitude conditions.

Low maintenance requirements are another bonus feature. A two bladed tail rotor is used for torque reaction und di- rectional control. Power is supplied by a Textron I. The engine power is transmitted through a belt drive transmission assembly to the main transmission and taif rotor drive shaft.

The belt drive assembly incorporates ant overrmning clutch to permit autorotation with out driving the belts or engine The fuselage with a central, tubular steel, open feame forms the load- carrying structure for the helicopter.

The center frome provides attach- ments for and supports all helicopter components above the landing gear, which is attached to the underside of the frame. Seat cush- jons and backs are contoured for personnel comfort, The seat support, to which the cushions are affixed, provides an installation of maximum personnel safety as a result of the impact-yielding capability. Seat belts are provided for the pilot and passenger positions, and addition ally, « shoulder haraess is provided for the center passenger.

Ox later holicopters shoulder harnesses are provided for pilot and right hand position also. An instrument panel is located forward of the seals at the helicopter centerline.

The panel includes flight and engine instruments in addi- tion to warning and caution lights and varions switches and controls. Space provisions exis! Later configuration instrument consoles have » stowage compariment glove box which can accommodate up to 20 lbs.

Contol System. The pedals ate udjustable. The cyclic and collective con- trol system is the mechanically linked, solid type, using tubular push-pull rods. The tail rotor coatrol system utilizes cables and pul- leys in one link of its otherwise solid system of tubular push-pull rods. 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. Check the helicopter performance data. Refer to Sections V, VI and vit. Determine that a Daily inspection in accordacce with the Lndbook of Maintenance Instructions HMD kas been accomplished within 24 hours prior to the first flight of cack day.