Goldy Posted March 19, Posted March 19, edited. Love the color scheme.. Need a garage to park it in for a few years? Goldy Edited March 19, by Goldy. As usual Thanks for sharing the photos and videos with us. ADRidge Posted March 19, That is a gorgeous helicopter, even when it's in pieces.
Is the panel out for avionics? Again, Great pics. Superglide Posted March 19, Best Regards, Jim. Posted March 20, Tom Morrison Posted March 21, Posted March 21, Richard: Awesome upgrade!!! HeloJunkie Posted March 22, Posted March 22, Here is yet another set of items we found as we got deeper into the annual.
HeloJunkie Posted April 5, Posted April 5, Click here for a bunch more pictures of it going back together And here is a picture of the new Sermatel coated exhaust: And here is the panel after some minor work has been started:.
Goldy Posted April 6, Posted April 6, Posted April 8, HeloJunkie Posted April 12, Posted April 12, Hopefully by next weekend I may be flying her again!!
HeloJunkie Posted April 17, Posted April 17, Hey Everyone - Just thought I would update you on what is happening with the CrashC Posted May 4, Posted May 4, HeloJunkie Posted May 5, Posted May 5, HeloJunkie: I have a question for you. Moving from the R44 to the right seat to left seat how has the transition gone for you? Your thoughts? Great job on the , by the way. The Guardian Posted May 6, Posted May 6, The right crew seat may be used for an additional pilot when the approved dual controls are installed.
The left crew seat may be used for an additional pilot when the approved dual controls are installed. Join the conversation You can post now and register later. Reply to this topic If no needle split occurs, check overrunning clutch for proper operation per HMI. To ensure throttle cutoff, hold twistgrip in cutoff position until N1 decelerates to zero and TOT is stabilized.
Check for TOT decrease. An engine fire recognized by a rapid increase in TOT can occur during shutdown if fuel cutoff is not complete. If an shutdown fire occurs, immediately engage starter and motor the engine to minimize the temperature encountered.
To extinguish the fire, continue motoring the engine with the twistgrip in the CUTOFF position and pull out the fuel shutoff valve. Observe TOT limits. The tail rotor control is minimized at less than normal operating RPM when the engine is not driving the rotor system.
Full control of the helicopter during these conditions may be limited. Damage to the rotor blades and strap pack can result from sudden stopping of rotor. Stop time as N1 passes through 65 percent. Observe elapsed time. Minimum allowable lapsed time is 2 seconds. NOTE: Practice or retakes may be required before proficiency can be obtained in deceleration timing.
If deceleration time is less than two seconds, make two more checks to confirm time. If engine flames out, refer to the HMI. If dual controls are installed, repeat procedure using copilot's twistgrip. Reduce TOT by motoring engine with starter. Speeds in excess of 15 percent N1 may be experienced. Utilize the following procedures only when they will not conflict with safe helicopter operation.
It is imperative that every pilot subject the public to the least possible noise while flying the helicopter. Takeoff: Takeoff using maximum takeoff power at the speed for best rate of climb. Proceed away from noise sensitive areas. If takeoff must be made over noise sensitive area, distance altitude is the best form of noise suppression. Cruise: Maintain feet minimum altitude where possible. Maintain speed of no more than knots over populated areas.
Keep noise sensitive areas to the left side of helicopter. Sharper turns reduce area exposed to noise. Approach: Use steepest glideslope consistent with passenger comfort and safety. Height Velocity Diagram. When any data is affected by model designation or engine configuration, that information will be so noted.
Be sure to select the appropriate performance data for model type, engine, and optional equipment installed. Controllability during downwind hovering, sideward and rearward flight has been demonstrated to be adequate in winds up to 20 knots. Use of Chart: Use the chart as illustrated by the example. Move up to the airspeed calibration line; move left and read approximately 83 knots, calibrated airspeed. By entering the chart from the opposite direction, calibrated airspeed may be converted to indicated airspeed.
This chart should be used for determining density altitude for use with gross weight limits for the HV Diagram and speed for Best Rate of Climb Chart. Use of Chart: To determine density altitude, the pilot must know pressure altitude and outside air temperature. NOTE: Pressure altitude is found by setting Read value on right of chart opposite known density altitude.
Multiply CAS by this value to determine true airspeed. Wanted: Find True Airspeed Method: First, find density factor by reading directly across from density altitude ft. Note density factor of 1. Use of Chart: Use the chart as illustrated by the example below. Conditions: The height velocity diagram is based on sea level, standard day conditions, over a smooth hard surface at pounds gross weight. Gross Weight Limits for Height Velocity Diagram: Description: The gross weight limits for this chart show the reduction in gross weight required as a function of density altitude in order for the Height Velocity curve to apply.
Move right to the line; move down and note pounds gross weight. Description: The hover ceiling charts show the hover ceiling in ground effect IGE for known conditions of gross weight and outside air temperature OAT.
The Hover Ceiling vs Temperature charts are based on: 1. Cabin heat and engine anti-ice OFF 3. Reduce takeoff gross weight by: Allison C18 33 pounds with particle separator. Allison C20 Reduce hover ceiling FT above critical altitude over and above any other hover reduction for any other installed kit or basic aircraft when the particle separator is installed.
To determine the maximum hover ceiling at 3. The primary purpose of this chart is its use as an engine performance trending tool to aid in determining whether the engine is producing specification power, or if engine power deterioration has occurred. NOTE Power check data taken at regular intervals should be plotted to monitor trends in engine condition.
The power check chart is based on the following conditions: percent N2. Cabin heat and engine anti-ice OFF. Engine bleed valve closed. Accessories required for safe flight should be operated during each check. Maintain separation from objects in air or on the ground. Reset altimeter if required after obtaining pressure altitude. Move right along the If the TOT observed had been higher than the specification TOT read from the chart, some power deterioration will have occurred and the performance data given in this manual may not be obtained.
NOTE Data obtained during engine operation with the bed valve not fully closed will result in incorrect comparisons of actual versus specification TOT. Move left along the Center of Gravity Envelope.
Balance Diagram Sheet 1 of 2. Balance Diagram Sheet 2 of 2. Station Diagram. Sample Weight and Balance Report Sheet 1 of 2. Sample Weight and Balance Report Sheet 2 of 2. Sample Surplus and Missing Items. Sample Basic Weight and Balance Record. Cargo Weight vs Loop Restraint. Cargo Restraint. Table and Figure Longitudinal Reference Datum inches forward of rotor centerline rotor hub centerline is located at Station See Figure and Figure Forward Aft L Enter chart at lb on fuel weight scale.
From that point, move to right along the lb line until reaching the fuel weight CG curve. Now move down to the longitudinal CG scale to find the fuel station CG of approximately Multiply Use the balance and station diagrams shown as an aid for weight and balance changes. Obtain aircraft delivered weight and moment from the Weight and Balance Record inserted in this section. Determine weights and moments of useful load items.
Add above items Ref. Example I. Determine corresponding center of gravity for gross weight by dividing total moment by gross weight. This computation must be done with zero fuel gross weight and with mission fuel gross weight Ref.
Weight and balance must be computed for minimum front seat weight prior to loading any passengers in rear seats with only pilot in front. Ballast, if required, must be carried. Ballast may consist of shot, sandbags, or similar material, adequately contained and secured. Zero Fuel Weight Add: Fuel 2.
Gross Weight Weight lb 1, 20 40 2, 2, Moment in. In general, the placement of cargo CG within 4 inches of the center of the compartment will ensure that the helicopter will be within the approved CG limits.
Establish the weight of the cargo load. Gross Weight Weight lb 1, 1, 2, Moment in. It is therefore imperative that lateral center of gravity control be exercised. All combinations of internal and external loadings are permissible if gross weight, longitudinal, and lateral center of gravity considerations permit. For pilot and passenger lateral center of gravity, see Figure Find weight of load. Determine lateral location station of load center of gravity. Obtain the lateral load moment as follows.
Example III. Rope, cable, or equivalent must have a minimum loop strength of 1, pounds. Restrain the cargo from shifting by using the correct number of restraining loops in accordance with Table Position restraining loop in accordance with Figure Cargo deck capacity is pounds not to exceed pounds per square foot.
View II shows typical tiedown for pound cargo. Helicopter Major Components. Servicing Materials Operating Supplies. Servicing Points. The right door must be open to use the receptacle.
Any source of external volt, direct-current power with sufficient amperage rating may be used. Before connecting external power, be sure that helicopter main electrical power selector switch is OFF.
After power is connected to receptacle, power switch must be set to EXT PWR position to connect external power to helicopter electrical system. Failure to follow the specified procedures may result in damage to aircraft components. The wheels are equipped with tow bar attach fittings. Attach ground handling wheels and hold tail up when lowering the wheels raising helicopter. Do not allow front end of skid tubes to drag on ground.
Avoid sudden stops and starts and short turns which could cause helicopter to turn over. Allow inside wheel to turn not pivot while helicopter is being turned. Safe minimum turning radius is approximately 20 feet. Tow helicopter on ground handling wheels by attaching suitable tow bar to tow bar fittings. If tow bar is not equipped to keep front ends of skid tubes from dragging, have an assistant balance helicopter at tailboom. Figure : CAUTION To prevent rotor damage from blade flapping droop stop pounding as a result of air turbulence from other aircraft landing, taking off or taxiing or sudden wind gusts, rotor blades should be secured whenever helicopter is parked.
Locate helicopter slightly more than one blade length clearance from nearby objects on the most level ground available. Secure main rotor blades as follows. Turn blades until one blade is directly above tailboom. Install blade socks on all blades. Secure other blade sock tiedown cords to fuselage jack fittings. Figure : Whenever severe storm conditions or wind velocities higher than 40 knots are forecast, helicopter should be hangared or evacuated to safer area.
If these precautions are not possible, moor helicopter as follows. Install pitot tube cover. Fill fuel tank if possible. Apply friction to lock cyclic and collective sticks.
Secure helicopter to ground by attaching restraining lines cable or rope between jack fittings and stakes or ground anchors. Fuels, oils, other servicing materials and capacities are listed in Table Locations of servicing points are shown in Figure Servicing Materials Operating Supplies 1. Tail Rotor Transmission - Capacity 0. Main Transmission - Capacity: 4.
Engine - Capacity: 3. Exxon Gallows Rd. Oil Products Ltd. Fuel Cells - Standard Nonself-sealing, Capacity: For blending information and authorized fuels, refer to the appropriate Rolls-Royce Operation and Maintenance Manual. Overrunning Clutch - Capacity: , , 1. Oz 45cc , , 1. One-Way Lock - Capacity: 0.
Anderol Inc. NYCO, S. Battery NiCad - Capacity: As required MS Footnotes: 1 Oils approved for use in main transmission and tail rotor transmission are synthetic lubrication oils that have a certified Ryder Gear Value in excess of pounds per inch.
Not a preferred lubricant for transmissions. For Model Series engine oil change requirements and restrictions on mixing of oils, refer to the Rolls-Royce Operation and Maintenance Manual. Refer to SBH Use of mixed oils from different series in an engine is limited to five hours total running time during one overhaul period. Adequate maintenance records must be maintained to ensure that the five hour limit is not exceeded.
Failure to comply with oil mixing restrictions can result in engine failure. Comply with the following precautions when servicing the fuel system. Electrically ground helicopter prior to refueling or defueling. Static discharge spark in presence of fuel vapors can cause fire or an explosion. Refer to Allison Operation and Maintenance Manual for additional cold weather fuel mix and blending instructions.
Filling: The fuel system has two fuel cells that are interconnected for simultaneous flow and venting. Fuel system filler is on right side of helicopter. Keep fuel nozzle free of all foreign matter. Check filler cap for security after refueling. Fuel system may be defueled in two ways: One is to defuel through filler port, using a pump. Fuel cell drain valve is spring-loaded closed and is opened by depressing internal plunger. After defueling, be sure to check drain valves for leakage.
NOTE: Oil level should be checked within 15 minutes after shutdown. Replenish with correct oil until oil level is FULL on sight gauge. Make certain that oil tank filler cap is securely tightened immediately after servicing.
Replenish with correct oil until oil level is at the dashed lines above the ADD mark on sight gauge. Replenish oil as necessary. This purges air from the oil cooling system and ensures that entire oil cooling system is full.
Fill main transmission by lifting breather-filler cap and inserting funnel into opening. Check that spring-loaded cap closes when funnel is removed. A liquid level sight gauge for checking oil level is located on the transmission housing. Check oil level.
Servicing of the tail rotor transmission should be performed by maintenance personnel. Avoid complete soaking of upholstery and trim panels. Remove imbedded grease or dirt from upholstery and carpeting by sponging or wiping with an upholstery cleaning solvent recommended for the applicable fabric nylon, vinyl, leather, etc. NOTE: If necessary, seat upholstery may be thoroughly dry-cleaned with solvent. Never use volatile solvents or abrasive materials. Never apply bending loads to blades or blade tabs during cleaning.
CAUTION Wash helicopter exterior, including fiberglass and rotor blades, when necessary, using a solution of clean water and mild soap. NOTE: Avoid directing soapy or clean water concentrations toward engine air intake area and instrument static ports.
Clean surface stained with fuel or oil by wiping with soft cloth dampened by solvent, followed by washing with clean water and mild soap. Rinse washed areas with water and dry with soft cloth.
Use mild soap and water solution or aircraft type plastic cleaner to remove oil spots and similar residue. To do so causes any abrasive particles lying on plastic to scratch or dull surface. Wiping with dry cloth also builds up an electrostatic charge that attracts dust particles from air.
After dirt is removed from surface of plastic, rinse with clean water and let air dry or dry with soft, damp chamois. Clean inside surfaces of plastic panels by using aircraft type plastic cleaner and tissue quality paper wipers or soft cloth. An acceptable alternate rate of leakage from either transmission is if oil loss is not more than from full to the add mark on sight gauge within 25 flight hours. Repair leaks according to instructions in the HMI.
If seepage continues at rate of one drop per minute or less, seal may be continued in service. Check transmission oil level and observe seepage rate after every 2 hours of operation.
Shorter inspection periods may be required is seal leakage appears to be increasing. If leakage is present, damper assembly should be overhauled as required and a serviceable unit installed. NOTE: It is normal for a thin hydraulic oil film to remain on damper piston as a result of wiping contact with piston seal. Newly installed dampers may also have slight oil seepage from oil trapped in end cap threads during damper assembly. Neither of these should be considered damper leakage or cause from damper replacement.
NOTE: Tape for all four blades should be equal in length and carefully applied to maintain a balanced rotor. Ensure that fuel cells are full topped off , and that oil in engine oil tank and main and aft transmissions is at FULL level.
Perform daily pre-flight check. Start engine Section IV. After idle stabilizes, accelerate engine to flight idle. Operate until oil temperature shows an increase and ammeter reads zero. Replenish fuel as necessary. Open movable air vents in each cargo door; positioning air vent openings downward. Install covers and equipment used to park and moor helicopter. Install static ground. Before next flight: Remove covers and equipment used to park and moor helicopter.
Perform daily preflight check Ref. Section IV. The following information is provided for pilots assisting qualified personnel in the cleaning process. The starter-generator can be used to motor the Allison Series engine for compressor cleaning cycle. Input voltage should be 24 vdc, but it is permissible to use 12 vdc. Water injection will be started three seconds prior to starter engagement. Water injection will continue during coast down until N1 stops.
Allow engine to drain through the outer combustion case drain valve. This table may be used for planning flights with external loads. When using this table for OGE hover data with internal loads, the maximum certified gross weight is limited to LBS.
Optional Equipment. Optional Equipment Kit Compatibility. Cargo Hook Release - Electrical and Mechanical. Cargo Hook. Cargo Hook Loading Data. Anti-Ice Airframe Fuel Filter. Minimum Float Operational Temperature for Over-water Flight Permissible Hoist Loads. Loading Examples. The ground school segment covers publications, aircraft systems, operational procedures, and preflight inspection procedures.
Four to five hours of flight time includes practice of normal flight and selected emergency procedures. PLEASE NOTE: For those customers who require English interpreters, the length of the transition course will be increased to one and a half to two-weeks in length, with flight training extended to a minimum of seven 7 hours.
This is due to the delays and other issues arising from the requirement to translate both the ground and flight instruction. The assigned flight instructor will determine the actual length of ground and flight training. Additional flight training hours greater than five will be priced at the hourly flight cost listed on the pricing page. The extra ground instruction will be included in the original course cost.
The recurrent course utilizes flight review, proficiency checks or other checks whose purpose is to review rules, maneuvers and procedures to demonstrate a pilot's existing skills. This three-day course includes ground school and two to three hours of flight time.
The BFR must be requested at the time of registration. Lifting loads reacted by the static mast are prevented from being imposed through the drive shaft onto the main transmission, thus eliminating thrust loading of transmission parts. Main rotor blade tracking of new blades may be required Main rotor hub assembly Lead-lag damper Main rotor drive shaft Main rotor mast Main transmission Overrunning clutch Main drive shaft Engine assembly This is accomplished by two slots along the tailboom that energize the downwash flow from the main rotor.
The result is lift in a horizontal direction that replaces the push of a conventional tail rotor. These Technical Representatives are backed up by a factory team of MDHI Product Support Engineers who can be called upon at any time to support specific tech- nical issues or questions that may arise. This 2-week course will require the student to learn and demonstrate the skill and knowledge required to safely perform selected maintenance tasks on the MD series. This manual is also suitable for: Mde Mdf Mdn.
Print page 1 Print document 91 pages.
0コメント