Survey
* Your assessment is very important for improving the workof artificial intelligence, which forms the content of this project
* Your assessment is very important for improving the workof artificial intelligence, which forms the content of this project
A-26 LADY LIBERTY Aircraft - TB-26B: Light bombardment type, twin engine, mid-wing monoplane Dual control version of B-26B Wing Span: 70 feet Length: 50 feet 9 inches (six gun nose) Height: 18 feet 6 inches Max Gross Weight 36,000 Pounds Tread: 19 feet 6 inches Turning Radius: 44 feet 6 inches Minimum Crew: (3) Two Pilot and one crew member familiar with the systems of the aircraft. (Unit Requirement) - Load Limits: @26,000lbs +4.27 G’s -2.35 G’s (200mph) Engines - Pratt and Whitney R-2800-57 and -79 Radial 18-cylinder, double-row air-cooled engines Bendix-Stromberg injection-type carburetors Two-Speed integral engine superchargers (blowers) (one, High blower, disabled) CHT gage reading from No. 14 cylinder of each engine Ignition System - High-Tension magneto type Four Dual magnetos Four Distributors Two Shielded ignition harnesses Shielded Spark plugs Two induction vibrator Propellers - Hamilton Standard hydromatic, three blade, constant-speed full feathering One electrically-driven auxiliary feathering pump per engine Constant speed range of 1200 to 2700 RPM Feathering buttons: Actuate feathering pump, button will automatically remain in until the propeller is feathered. Button can be pulled out at any point - When un-feathering, hold button to 800 RPM and then release Oil - Self sealing oil tank in each nacelle Total Capacity: 39 US Gallons each Useable Capacity: 30 US Gallons each Standpipe provides a reserve supply of 1.25 US Gallons for feathering Oil Cooler Doors Operation Time: 16 seconds Vernotherms cause oil to bypass until 40 degrees Celsius Fuel - Two Main Tanks, two auxiliary tanks, and a bomb bay tank N9682C has both main tanks and right aux tank operational Two Main boosts pumps, two auxiliary boost pumps Main Tank Capacity: 300 US Gallons (600 Total) Auxiliary Tank Capacity: 100 US Gallons Two fuel tank selector valve levers mechanically actuate the fuel selector valves on the left and right main and auxiliary tanks. The levers have MAIN ON, AUX ON, and BOTH OFF Bomb Bay Tank and Cross-Feed Selector Valve: Positions LH ENG, OFF, BOTH ENG, OFF, RH ENG, OFF, ON CROSS-FEED, and OFF Fuel Booster Pump Switches: HIGH, OFF, and LOW positions HIGH Position: 17 to 19 PSI LOW Position: 6 to 9 PSI Electrical System - Basic 28-volt direct-current system - Supplementary 115-volt 400-cycle alternating-current system - The ground return for all electrical circuits other than near the compass are furnished by the aircraft structure. - Circuit breakers and fuses provide individual circuit protection - Two 200 ampere generators - Two 24-volt batteries: Mounted in gear wells - Two Voltage Regulators: Mounted on the floor of pilots compartment near right outboard wall. - Two Reverse Current Relays - External Power Receptacle located on outboard of left nacelle - AC power furnished by inverter located in the aft fuselage section Hydraulic System - Used to operate the landing gear, wheel brakes and the bomb bay doors Total Capacity: Approx 8 US Gallons Hydraulic Fluid Reservoir Capacity: 1.75 US Gallons HFRC supplies fluid, by gravity, to the engine-driven hydraulic pumps and the emergency hydraulic fluid reservoir. 3 sight gages for Emergency Hydraulic Fluid Reservoir EHFR supplies fluid to the hydraulic hand pump, one cell supplies fluid to open bomb bay doors, one to close, and one to extend the landing gear Two Engine-driven hydraulic pumps System Filter Hydraulic Pressure Regulator and Relief Valve opens at 1250 +/-25 PSI TEMP Relief Valve for Emergency System opens at 1300 PSI Emergency Hydraulic Selector Valve: SYSTEM, BOMB DOORS OPEN, LANDING GEAR DOWN and BOMB DOORS CLOSED positions Hydraulic Pressure Gage Flight Control System - Conventional controls are mechanically operated through two-way cable systems. Trim tabs controlled mechanically* *Right trim tab is preset prior to flight Aileron trim tabs provide automatic boosting action Wing Flap System - Wing Flaps are synchronously raised or lowered by a drive unit installed in the bomb bay. - Flaps fully lower in approximately 16 seconds and retract from full down in approximately 15 seconds. - Takeoff: 15 degrees of flaps - Land: 38 degrees of flaps - Full Flaps: 52 degrees - Wing Flap Switch: UP, OFF, and DOWN positions Landing Gear System - Tricycle type - Extend fully in approximately 10 seconds - Retract fully in approximately 15 seconds - Tail Skid protects rear fuselage during tail-low landings Landing Gear System Landing Gear Lever: (Cont’d) - Landing Gear Auxiliary Lever and Detent Pin: Alternate means of mechanically actuating the landing gear position selector valve. UP and DOWN positions. - Landing Gear Emergency Up-latch Release Handles: Main Gear releases located below the Landing Gear Auxiliary lever, nose gear located by pilot’s right leg. Full extension accomplished using hydraulic hand pump. - Landing Gear Warning Horn: Sounds when one or both throttles are closed past the one-quarter open position and any landing gear is not down and locked. Switch for horn has OFF and ON positions, spring loaded to ON. Horn silence by moving to OFF position - Gear Position Lights: Green light for each gear that is down and locked. Red light indicates when any gear is not locked in down position - Ground Safety Locks: Pins for both mains and nose gear - Auxiliary Lever is automatically locked at DOWN position by the detent pin when the aircraft is on the ground. Brake System - Pressure from Hydraulic System operates multiple disc brakes on each wheel of the main landing gear - Parking Brake Handle: Parking brake set by depressing brake pedals and pulling aft on the parking brake handle. - Pressure on the brakes should be released before releasing the parking brake handle by depressing the brake pedals. - Emergency Air Brake System: Independent of the hydraulically operated brake system. - EABS consists of an air bottle, pressure gage, air brake valve, and shuttle valves interconnected by tubing. Shuttle valves close the brake hydraulic system lines. - EABS activated by Emergency Air Brake Lever. - The Lever has RELEASE, NEUTRAL and ON positions - ON position applies air pressure equally to the mains, NEUTRAL holds the pressure in the lines. - Brake Hydraulic lines must be bled of air after air brake application before further hydraulic brake operation. - Desired EABS pressure is 575 PSI with a minimum of 450 PSI Pitot-Static System - Pitot head located on the left side of the nose section - Static pressure obtained through two orifices, one on each side of the fuselage aft section between the gunners compartment and the horizontal stabilizer. - Alternate source of static pressure is located on the left side of the pilot’s compartment adjacent to the pilots’ seat. - Static Pressure Selector Switch: Aft (AIRSPEED TUBE) for normal operation. ALTERNATE SOURCE position is forward Vacuum System - Two pumps, installed on the lower left side of respective engine - One pump utilized at a time - Vacuum Selector Valve Handle installed above and aft of pilots head Crew Service Minimum flight crew (3) - (2) Pilots - (1) one crew member familiar with the systems of the aircraft. (Unit Requirement) Minimum Ground start safety crew - Two - Minimum of two fire extinguishers Required Documentation Documentation for this aircraft is substantially more than a normal aircraft because of the restricted category, the air show utilization and the LHFE 6802 exemption for providing rides for hire. The required documentation to remain on the aircraft are; 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. Current Aircraft Registration Airworthiness certificate Current maintenance inspection report Weight and Balance report Pilot operating handbook Checklist Operating limitations Supplemental operating limitations Registration number exemption certificate 6802 exemption 11. 12. 13. 14. 15. 16. 17. Crew and passenger manifest forms Blank Hold harmless agreements for passengers Hold harmless agreements (on file for the members) Passenger briefing guide Pilot certificate Pilot medical certificate Copy of FAA notification of LHFE NOTES Discontinue Starting if there is evidence of propeller balk or stall, as damage to the engine may result from liquid(Hydraulic) lock. Do not engage starter for more than 30 seconds at a time. Allow to cool for one minute between attempts. Abnormally high oil pressure may exist until an oil temperature of 40 Celsius is obtained due to the thermostatic action of the oil pressure relief valve. Warm up engine at 1000 RPM until the oil temperature is 40 Celsius. Then increase throttle setting to 1200 RPM. Avoid prolonged engine speeds at which the generators cut in and out Do not use brakes to stop wheel rotation after takeoff, as abnormal stress will be placed on the main landing gear Descent: Maintain 1 inch Hg manifold pressure for each 100 RPM METO (Maximum Except Takeoff) Power: 42” 2400 RPM Simulated Zero-Thrust: 15” Hg / 1500 RPM Baro-Power Check: 29” Hg / 2150 +/- 50 RPM The landing gear structure will sustain a load factor of 2.0 at a gross weight of 44,660 pounds Normal Take Off Power Settings 2650 RPM 46” Tachometer LIMITATIONS (Cont’d) - 1500 RPM: Min Cruise 1500-2100 RPM: AUTO LEAN Permitted 2100-2400 RPM: AUTO RICH Required 2400 RPM: Max Continuous – above this limited to 5 minutes at TO Power and 30 minutes at military power - 2700 RPM: Maximum Manifold Pressure Gage - 23 in HG: Min Cruise 23 -33: AUTO LEAN Permitted 33-42: AUTO RICH Required 42 in HG: Max Continuous – above this allowed per above 52 in HG: Maximum Airspeed - 115 MPH: Vr - 120 MPH: Vmt – Max Tire - 170 MPH: Vy - 150 MPH: Vx - 160 MPH: Vyse - 132 MPH: Vmc - 102 MPH: Vs with power - 122 MPH: Vs power off - 105 MPH: Vso - 160 MPH: Vle - 160 MPH: Vfe Full Flaps - 208 MPH: Vfe to 15 - 190 MPH: Vll - 246 MPH: Va - 425 MPH: Max Permissible Diving - 425 MPH: Bomb-Bay Doors (with spoilers) - 350 MPH: Vbb (Lady Liberty) Carburetor Air Temperature Gage - -10 to 15 C : Caution – possible icing - 15 to 38 C : Operating Range - 38 C : MAX Cylinder Head Temperature Gage - 150 to 232 C : AUTO LEAN Permitted - 232 C : AUTO RICH Required - 260 C : MAX Oil Pressure Gages - 50 PSI : Minimum for flight 70 to 80 PSI : Operating range 100 PSI : MAX XXX0 F Max oil temp Fuel Pressure Gage - 17 PSI : Minimum for flight - 17 to 19 PSI : Operating range - 21 PSI : MAX Suction Gage - 3.75 in HG : Minimum - 3.75 to 4.25 in HG : Operating range - 4.25 in HG : MAX Hydraulic Pressure Gage - 850 to 1000 PSI : Operating range - 1200 PSI : MAX Oil Temperature Gage - 40 C : Min for flight - 60 to 85 C : Operating range - 100 C : MAX Weight and Balance - The forward CG limit is 18% MAC or Sta. XXX.XX - The aft limit is 32% MAC or Sta. XXX.XX