Download A26 Flight Engineer Systems Study Guide

A-26 LADY LIBERTY
Aircraft
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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
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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
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High-Tension magneto type
Four Dual magnetos
Four Distributors
Two Shielded ignition harnesses
Shielded Spark plugs
Two induction vibrator
Propellers
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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
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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
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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
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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
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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)
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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
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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
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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
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The aft limit is 32% MAC or Sta. XXX.XX