BE-76 Systems and Limitations

(From ATP PTS – Effective July 2008)

I. AREA OF OPERATION: PREFLIGHT PREPARATION

A. TASK: EQUIPMENT EXAMINATION

REFERENCES: AC 20-29, AC 20-117, AC 91-43, AC 91-51, AC 91-74, AC 120-60, AC 135-17, 14 CFR part 61; POH; AFM.

Objective. To determine that the applicant:

1. Exhibits satisfactory knowledge appropriate to the airplane; its systems and components; its normal, abnormal, and emergency procedures; and uses the correct terminology with regard to the following items—

a. gear—extension/retraction system(s); indicators, float devices, , antiskid, tires, nose- steering, and shock absorbers.

Extension/Retraction System Extended:

Landing Gear/Hydraulic System o Retractable Tricycle o Magnesium and aluminum o Fault Protection – Pitot tube switch (59-63 kts) keeps landing o Position Indicators (3 Greens, red light for gear-in-transit) o Time Delay Relay (after 30 secs operation stops, pilot must recycle gear lever to reset) o Control switch (2 position, must be pulled out) o (1) Electrically driven used for extension and retraction o Can be manually extended (See Emergency Gear Extension) o Electrically actuated power-pack (located in aft ) o Pressure of 1250-1550 (+/- 100) holds gear up in place o 2 Circuit Breakers (gear motor and control) o Control switch (2-position, must be pulled out)

Gear Down cycle o Current to pump o Fluid to o Gear down o Switches on gear, turn on lights o Pump off o System is depressurized o ***over-center brace & spring holds main gear down in place o ***nose locks down w/ brace & spring holds nose gear down in place o Landing Gear Retraction Momemt: -1177 in.-lb (per FAA Type Certificate Data Sheet)

Gear Up Cycle o Check pitot switch for 59-63 knots o Send electricity to pump o Pump sends fluid to actuators o Gear comes up o Pressure switch at 1550 psi shuts off pump (if pressure drops below 1250, pump back on)

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o ***if leak, time delay relay switch turns pump off after 30 seconds. Relay can be reset by cycling the switch o pressure is maintained to hold gear up by active pressure switch and check valve

Gear Warning Horn o Gear Horn Sounds – any below sufficient to maintain flight (approx. 12”) or flaps set beyond 16 degrees o Q switch quiets horn above 99-106 knots, optional warning horn silence button

Inadvertent Gear Retraction on the Ground o Pitot Safety Switch: Prevents inadvertent retraction of the landing gear on the ground. The switch deactivates the hydraulic pressure pump circuit when the impact air pressure is below 59- 63 knots so that the gear cannot be retracted

Tires: Pressure (all): 38 PSI Dimensions: 5x5 (front) 6x6 (mains)

Strut Pressure (nitrogen): o 250 PSI nose gear (see POH Section 8) o 300 PSI main

Landing Gear System Emergency Extension o Maximum Speed 100 KIAS o Gear Motor circuit breaker – off (pull out) o Gear handle (down) o Emergency Extension (90O counterclockwise, releases pressure) o NOTE 1: During Emergency extension, the hydraulic pressure, which retains the gear in the up position, is released, by opening the emergency extension valve, permitting the fluid to by-pass the pmp and flow directly into the reservoir o NOTE 2: During this emergency procedure, extension is accomplished more rapidly than during normal extension o NOTE 3: If emergency extension is attempted above 100 KIAS, the effect of the slipstream accelerates the process to the extent that fluid returning to the reservoir atop the gear pump will overflow into the section of the fuselage, immediately aft of the baggage compartment. This undesirable, as is corrosive. o NOTE 4: Not to be performed on training flights. Requires inspection.

Brake System o Toe brakes o Wear down to 0.450 in. o Master for each set of pedals o Reservoir located inside of nose section on left o Cylinder on each main, applies pressure plate to produce friction for braking o Parking (pull handle, pump brakes to set, handle in to release) o reservoir (left side forward cabin bulkhead, access door, check dipstick)

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Powerplant o Right Engine: Avco-Lycoming O-360-A1G6D (rotates clockwise) o Left Engine: Avco-Lycoming LO-360-A1G6D (rotates counter-clockwise) o Horizontally-Opposed, Air-Cooled, Normally-Aspirated, Direct Drive, o 180 HP @ 2700 RPM o 8 Quart System (no flight below 6 quarts) o Dipsticks are not interchangeable o Oil Cooler (thermostatically controlled) o Ice Protection (Carb heat, heated, unfiltered air) o Cowl Flaps (CHT): max 500OF o Starters (maximum on time = 30 seconds on, 2 min. off) o Prime (Magnetos on both, push in to prime – 10 sec. for start) o Engaged Warning Light between magnetos (3733D only) o Oil: 1st 50 Hours MIL-L-6082C – Thereafter MIL-L-22851

Powerplant Instrument Markings

Oil Temperature Caution Range (Yellow Arc) – 60O – 120OF Normal Operating Range (Green Arc) – 120O-245OF Maximum – (Red Radial) – 245OF

Oil Pressure Minimum Idle (Red Radial) – 25PSI Caution Range (Yellow Arc) – 25-60PSI Normal Operating Range (Green Arc) -60-100PSI Maximum (Red Radial Line) 100psi

Manifold Pressure Normal Operating Range (Green Arc) – 15 to 29.6 inHG

Tachometer Normal Operating Range (Green Arc) – 2000-2700 RPM Maximum (Red Radial Line) – 2700 RPM

Fuel Pressure – Minimum (Red Radial) – 0.5 psi Normal Operating Range (Green Arc) – 0.5-8.0 psi Maximum (Red Radial) – 8.0 psi

Cylinder Head Temperature Normal Operating Range (Green Arc) – 200 to 500 OF Maximum (Red Radial) – 500 OF

c. Propellers—type, controls, feathering/unfeathering, , negative torque sensing, synchronizing, and synchrophasing.

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Propellers o Hartzell constant speed – 2-bladed aluminum alloy o HC-M2YR-2CEUF/FC7666A (Left) o HC-M2YR-2CLEUF/FJC7666A (Right) o Woodward hydraulic governor (L210650) and (R210652) o Diameter: 76in Normal o Minimum allowerd for repair: 74in o 2-Hartzell 76”-74”, counter-rotating, constant-speed props, full feathering o Governors (sends oil pressure to/from the hub) o Springs, dome pressure, counterweights send props to high-pitch, low-Rpm o Oil Pressure is acting against spring and dome pressure to set low pitch/high RPM o Underspeed (climb) – Flyweights in, pilot valve opens, oil into hub, sets low-pitch/Higher RPM o Overspeed (descent) – Flyweights out, pilot valve closes, oil out of hub, Nitrogen and spring pushes back, high pitch/low RPM o Feathered – Pilot valve opens, oil out of hub (spring, nitrogen, and flyweights), prop to highest pitch/low RPM to total stoppage o Feather Stops – latches come out at approx. 700 RPM and below to prevent feathering on the ground o Pitch Setting at 30in Station: o Low: 12.1O +/- 0.1O o High: 17O – 20O o Feather: 81O +/- 1O o Hartzell assembly C2285-3P and C2285-3PL o Springs and dome pressure hold props in high pitch/low RPM o Oil pressure holds props in low pitch/high RPM o Underspeed (Climb) o Flyweights come in o Pilot valve opens o Oil pressure into hub o Slides on groves less pitch, higher rpm o Oversped (Descent) o Flyweights out o Pilot valve closes o Oil pressure returns to reservoir o Nitrogen, spring pushes back o Props move to higher pitch, lower RPM o Feather o Pilot valve lets oil pressure drain o Spring, Nitrogen, Counterweights o Feather o Feathering latches o Constant speed props o Pros: less wear, more efficient, increased performance and fuel efficiency o Cons: maintenance, cost, complexity o Manifold Pressure o Potential power in intake o Avoide High Manifold (power) with Low RPM

Propellers

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o Two Hartzell constant speed, full-feathering, two-blade propellers. Right engine propellers are counter-clockwise turning, thus making propellers NOT interchangeable. Diameter 76” max, 74” min. Pitch settings at the 30” station: o Low 12.1 o High 17O-20O o Feathered: 81O +/- 1

d. fuel system—capacity; drains; ; controls; indicators; cross feeding; transferring; jettison; fuel grade, color and additives; fueling and defueling procedures; and fuel substitutions, if applicable.

Fuel System o 103 Total Gallons, 103 Usable o Approved Fuels – 100LL & 100 o 2 Tanks w/ 8 total sumps o 5 Fuel Pumps (2 engine driven, 2 auxiliary, 1 heater pump) o Selector Valve (Three position – ENGINE: ON, x-feed, OFF) o Feeding to the engine with selector on x-feed o Selector valve – three hoses off (1-tank, 1-x-feed, 1-engine) o Auxiliary pump provides pressure for priming, then push to allow flow o Priming goes to the #1, 2, and #4 cylinders o Fuel caps provide venting for proper fuel flow, with over-flow vents outboard the

Fuel Limitations o Type – 100LL (blue), or 100 (green) o Total Fuel – 103 gallons o Usable Fuel – 100 gallons o Two Main Tanks – Each with 51.5 total, 50 usable o Fuel Flow – Approximately 9 gph @ cruise 23” – 2300 RPM o Fuel Flow – Approximately 11 gph @ cruise 25” – 2500 RPM o Maximum Slip Duration – 30 seconds o No takeoffs below 9 gallons each tank (yellow arc on fuel gauge) e. oil system—capacity, grade, quantities, and indicators. Capacity

Grade

Quantities

Indicators f. hydraulic system—capacity, pumps, pressure, reservoirs, grade, and regulators.

See Landing Gear. g. electrical system—alternators, generators, battery, circuit breakers and protection devices, controls, indicators, and external and auxiliary power sources and ratings.

Electrical System (3733D) o 24 volt battery (vented) /28 volt-55amp (belt driven) (ME183 and after) o Alternators produce more voltage to compensate for loss in system before reahing battery.

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o Alternators are self-exciting at 1200-1400 RPM/50% load o Buses (Battery, Bus1, Bus2) o High Load Items (Gear, flaps, , transponder, Nav-Coms) o Over-voltage protection – over-voltage relay, voltage regulator & over-voltage warning light o Undervoltage/Alternator out – Under and Out warning light o Emergency Precautions – Isolation breakers, temp controlled bus tie (ME 103 and After) o Starter-Engaged Warning Light (3733D only)

Electrical Systems o 28 Volt single-wier, negative ground, direct current system, powered by two 28V 55amp belt driven alternators and two 12V/25amp hour lead acit batteries connected in series. o Starter Duty Cycle – 30 Seconds ON, 2 minutes OFF

Stall Warning System o Electric o (2) sensing vanes, 1 on each wing o Left wing vane: activated with flaps 0-16O o Right wing vane: activated with flaps set above 16O h. environmental systems—heating, cooling, ventilation, oxygen and pressurization, controls, indicators, and regulating devices.

Environmental o Janitrol Heater o 45,000 btu Janitrol Heater, located in nose section o Fuel is introduced when duct temperature gets below a value set by the pilot with the temp control knob . Fuel burn: 2/3 gallons per hour out of the right tank o Control (3 Position) . HEATER ON, BLOWER ONLY, OFF o Ground Operation – blower on first, then heater on (blower stops with gear retract) o In-Flight Operation – must have fresh air inlet set at least ½ open, monitor temp by heater pull knob o After landing/shutdown – keep blower on for two minutes o Overtemp switch . Shuts off the system at 300OF, must be reset by mechanic . Located on the heater . CAUTION: The entire system should be inspected and the malfunction determined and corrected before resetting the overheat switch (in nose section) o Fresh air: Tail (dorsal) inlet o Fresh air blower in aft cabin (shuts off with gear retraction) o Two cockpit screened inlets

i. and communications—; flight director; Electronic Flight Instrument Systems (EFIS); (s) (FMS); Doppler Radar; Inertial Navigation Systems (INS); Global Positioning System/Wide Area Augmentation System/Local Area Augmentation System (GPS/WAAS/LAAS); VOR, NDB,ILS, GLS, RNAV systems and components; traffic (MLS deleted) awareness/warning/avoidance systems, terrain awareness/warning/alert systems; other avionics or

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j. ice protection—anti-ice, deice, pitot-static system protection, propeller, windshield, wing and tail surfaces.

o o Pitot-heat o Windshield defrost o No other anti-ice/de-ice equipment k. crewmember and passenger equipment—oxygen system, survival gear, emergency exits, evacuation procedures and crew duties, and quick donning oxygen mask for crewmembers and passengers.

l. flight controls—, (s), (s), control tabs, balance tabs, , flaps, spoilers, leading edgeflaps/slats and trim systems.

Flight Controls o Elevators – Cables & Pulleys o Rudder – Cables & Pulleys, push-pull rods (steering) o Aileron – Cables & push-pull rods, pulleys o Flaps – Electric motor (loc: center fuselage, aft front seats, connected by tube o Trim – Cables & Bungees o Push/pull rods and cable system o Dual controls o Control Surface Movements (From Type Certificate Data Sheet) o Wing Flaps . Down: 35O +/- 1O o Aileron . Up: 20O +/- 1O . Down: 15O +/- 1O o Rudder . Right 30O +/- 1O . Left 30O +/- 1O o Elevator . Up: 20O +1O / - 0O . Down: 15O +1O / - 0O o Rudder Tab . Right 20O +/- 1O . Left 20O +/- 1O o Elevator Tab (with Elevator Neutral) . Up 4O +/- 1/2O . Down 20O +/- 1O

Trim Types o deflects to relieve pressure o Balance tab – connected to . The yoke moves it to move the elevator o Antiservo – yoke moves it to move the o Antiservo tabs – leads in the direction of the control surface o Moves more quickly than the manual control surface

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Flaps o Landing Gear Warning sounds when flaps are extended beyond 16 degrees with gear up o Wing motor located on the right side of the aircraft (under the copilot’s seat) o Limit switches o Up limit switch at 0O o Down limit swithch at 35O o Stall warning horn o Left wing warning horn operates with flaps set 0O-16O o Right wing warning horn operates beyond 16O

m. pitot-static system (BE-76 pressure system) with associated instruments and the power source for the flight instruments.

Pitot-Static System o Powers Airspeed, , and VSI o Pitot Heat o Should be off on the ground except for testing o (2) Static Ports o One on each side of the aft fuselage o Alternate Static . Located on pilot side cabin wall, above landing gear extension tool. . Reads static pressure from inside the cabin (lower pressure) o Altimeter reads higher o Airspeed shows higher o VSI shows momentary climb . Positions: OFF NORMAL – ON ALTERNATE

Presure System o (2) Pressure pumps, (1) on each engine interconnected to form a single system o Powers and o Check Valve allows for continued operation with one pump inoperative o Normal Operating Range (Green Arc) – 4.3 – 5.9 inHg o Pressure Gauge (InHG) o 2 red buttons for failure indication

2. Exhibits satisfactory knowledge of the contents of the POH or AFM with regard to the systems and components listed in paragraph 1 (above); the Minimum Equipment List (MEL)and/or configuration deviation list (CDL), if appropriate; and the operations specifications, if applicable.

BE-76 General Information

Weights o Maximum Ramp Weight: 3916 lbs. o Maximum Takeof Weight: 3900 lbs.

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o Maximum Landing Weight: 3900 lbs. o Maximum Zero Fuel Weight: 3500 lbs. o Maximum weight of plane, people, baggage, and no fuel must not exceed 3500 lbs. o Standard Empty Weight – 2446 lbs. o Baggage Compartment – 200 lbs. o Flight Limit Load Factors o Flaps up: +3.8g / -1.52g o Flaps down: +2.0g

Service Ceiling o Twin Engine: 19,600 @ 3900lbs o Single-Engine: 6,200 @ 3900lbs o Single-Engine: 10,300 @ 3400lbs

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