The airplane has two main landing gears and a single nose gear. The nose gear is a conventional steerable two–wheel unit. Each main gear has four wheels in tandem pairs.

Hydraulic power for retraction, extension, and steering is supplied by the left hydraulic system. An alternate extension system is also provided.

The normal/reserve brake hydraulic system is powered by the right hydraulic system. The alternate brake hydraulic system is powered by the left hydraulic system. Antiskid protection is provided with both systems, but the auto brake system is available only through the normal system.

The Landing Gear Panel houses the following Gear Indication lights:


There are three versions of the Gear Indication lights, two for the Boeing 757-200 and one for the Boeing 757-300.

757-200 Version 1 houses indication lights common to all 757 aircraft. The DOORS light (amber) is illuminated if a gear door is not closed. The landing gear disagree light (amber, marked GEAR) is illuminated if the gear position disagrees with the landing gear lever position. The landing gear down lights (marked NOSE, LEFT and RIGHT) are illuminated green when the associated landing gear is down and locked.

The BRAKE TEMP light, as fitted to some Boeing 757-200 aircraft, illuminates white if a wheel brake temperature is in high range (a value of 5 or more on the status page).

The 757-300 is fitted with a retractable tailskid device and the TAILSKID light (amber) illuminates any time the tailskid position disagrees with the landing gear position.

The landing gear lever has three positions, UP, OFF and DN. When placed in the UP position, the landing gear retracts. The OFF position removes hydraulic pressure from the landing gear system, and is used after retraction is complete. When the lever is placed in the DN position, the landing gear extends. The Alternate Gear Extend switch (marked ALTN GEAR EXTEND) is located below the landing gear lever. In the OFF position this allows the landing gear to operate normally. When placed in the DN position the landing gear extends by the alternate extension system. Finally to the right of the landing gear lever is the Landing Gear Lever Lock Override Switch (marked LOCK OVRD). Pushing this switch releases the landing gear lever lock.

A nose wheel steering tiller is located on each of the left and right sidewalls. This is however a customer option and some 757 aircraft therefore have only one steering tiller, on the left sidewall. Rotating the tiller turns the nose wheels up to 65 degrees in either direction, and overrides rudder pedal steering. The tiller position indicator shows the displacement from the straight-ahead, neutral position.

On the ground, pushing a full rudder pedal turns the nosewheel up to seven degrees in that direction. Pushing the top of the rudder pedal actuates the wheel brakes for that main gear. In flight pushing a rudder pedal deflects the rudder in the desired direction. A rudder pedal adjustment crank, between the two pedals, adjusts the rudder pedals forwards or aft as desired.

The Auto Brakes Selector is located on the centre forward panel. It comprises a selector knob allowing pre-selection of a desired deceleration rate of level 1, 2, 3, 4 or MAX AUTO. The DISARM position disengages the system and releases brake pressure. The OFF position deactivates the autobrake system. The RTO position automatically applies maximum brake pressure when the thrust levers are retarded to idle above 85 knots.

The Parking Brake Handle is located on the control stand. Pulling the handle sets the Parking Brake when both brake pedals are simultaneously depressed. In order to release the parking brake, simultaneously press both brake pedals. A Parking Brake Light is also fitted, which illuminates amber whenever the parking brake is set.

The Brake Pressure Indicator is located on the centre forward panel. It indicates Brake Accumulator pressure in psi (x 1,000). A BRAKE SOURCE light, also located on the centre forward panel, illuminates amber if both normal and alternate brake system pressures are low. An ANTISKID light, located on the overhead panel, illuminates amber if a fault is detected in the antiskid system.

The Reserve Brakes switch, located on the centre forward panel, when switched ON:   - allows use of reserve hydraulic fluid   - activates right electric hydraulic pump   - isolates the right electric hydraulic pump power to the normal brake system And when switched OFF (ON not visible):   - allows the right electric hydraulic pump switch to control the pump   - does not allow use of the reserve hydraulic fluid   - removes isolation of the right electric hydraulic pump power to only the normal brakes

The Brake Temperature (as installed) is shown on the EICAS Status Display, indicating a relative value of wheel brake temperature. Values range from 0 to 9   - 0 to 2 is the initial range, box and number are cyan   - 3 and 4 normal range, box is white for each brake that exceeds 2   - 5 to 9 high range, box and number are white for each brake that exceeds 5

In–flight and ground operation of various airplane systems are controlled by the air/ground sensing system and the nose air/ground sensing system.

The air/ground sensing system receives air/ground logic signals from tilt sensors located on each main landing gear. These signals are used to configure the airplane systems to the appropriate air or ground status.

A nose air/ground sensing system receives air/ground logic signals from nose gear strut compression sensors. These signals are for controlling stall warning and portions of the caution and warning system.

An EICAS advisory message AIR/GND SYS or NOSE A/G SYS indicates that some portion of the sensing system failed. Affected equipment and systems will not operate normally and therefore takeoff is not allowed.

The landing gear are normally controlled by the landing gear lever. On the ground, the lever is held in the DN position by an automatic lever lock. The lever lock can be manually overridden by pushing and holding the landing gear lever LOCK OVRD switch. In flight, the lever lock is automatically released through air/ground sensing.

When the landing gear lever is positioned to UP, the landing gear begins to retract. The landing gear doors open and the main gear wheels tilt to the retract position. Automatic wheel braking occurs during gear retraction. The GEAR and DOORS lights illuminate as the landing gear retracts into the wheel wells. After retraction, the landing gear are held up by uplocks. The GEAR and DOORS lights extinguish. The landing gear lever is placed in the OFF position to depressurize the landing gear system.

The GEAR light remains illuminated and the EICAS caution message GEAR DISAGREE display if any gear is not up and locked up after the normal transit time. The affected gear’s, gear down light, remains illuminated if the gear never unlocked from the down position. The DOORS light remains illuminated and the EICAS advisory message GEAR DOORS display if any hydraulically actuated door is not closed after normal transit time.

When the landing gear lever is moved to DN, the landing gear doors open, the gear are unlocked, and the GEAR and DOORS lights illuminate. The gear are hydraulically powered to the down and locked position. The downlocks are powered to the locked position, all hydraulically actuated gear doors close, and the main gear trucks hydraulically tilt to the flight position. When all gear are down and locked, the gear down lights illuminate and the GEAR and DOORS lights extinguish.

The GEAR light remains illuminated and the EICAS caution message GEAR DISAGREE display if any gear is not locked down after the normal transit time. The extinguished gear down light indicates the affected gear. The DOORS light remains illuminated and the EICAS advisory message GEAR DOORS display if any hydraulically actuated door is not closed after the normal transit time.

The alternate landing gear extension system uses a dedicated DC powered electric hydraulic pump. Fluid within the supply line to the pump is sufficient for alternate gear extension operation. This fluid is isolated from the left hydraulic system. Selecting the ALTN GEAR EXTEND switch releases all door and gear uplocks. The landing gear free–fall to the down and locked position.

When all gear are down and locked, the gear down lights illuminate and the GEAR light extinguishes. During alternate extension, the DOORS light remains illuminated and the EICAS advisory message GEAR DOORS display because all the hydraulically powered gear doors remain open.

Nose wheel steering is powered by the left hydraulic system.

Primary steering control is provided by the left sidewall nose wheel steering tiller. Limited steering control is available through the rudder pedals. The tiller can turn the nose wheel up to 65 degrees in either direction. A pointer on the tiller assembly shows tiller position relative to the neutral setting. The rudder pedals can be used to turn the nose wheels up to seven degrees in either direction. Tiller inputs override rudder pedal inputs.

Each main gear wheel has a multiple disc brake. The nose wheels have no brakes.

The brake system includes:
  - normal/reserve brake hydraulic system
  - alternate brake hydraulic system
  - brake accumulator
  - antiskid protection
  - auto brake system
  - parking brake

The normal brake hydraulic system is powered by the right hydraulic system. The brake pedals provide independent control of the left and right brakes.

Alternate brake hydraulic system selection is automatic. If the right hydraulic system pressure is low, the left hydraulic system automatically supplies pressure to the alternate brake system. Pushing a brake pedal then sends hydraulic pressure through the alternate antiskid valves to the brakes.

The BRAKE SOURCE light illuminates and the EICAS advisory message BRAKE SOURCE displays if both the normal and the alternate brake system pressures are low.

Pressing the RESERVE BRAKES switch provides reserve hydraulic fluid to the right system electric pump. Pump pressure is then supplied exclusively to the normal brakes system. The BRAKE SOURCE light extinguishes when pressure is available.

If right/reserve, and alternate brake hydraulic power is lost, the brake accumulator can provide several braking applications or parking brake application.

Antiskid protection is provided in the normal/reserve and alternate brake hydraulic systems.

The normal/reserve brake hydraulic system provides each main gear wheel with individual antiskid protection. When a wheel speed sensor detects a skid, the associated antiskid valve reduces brake pressure until skidding stops.

The alternate brake hydraulic system provides antiskid protection to laterally paired wheels.

Touchdown, hydroplaning, and locked wheel protection is provided. The ANTISKID light illuminates and the EICAS advisory message ANTISKID displays to indicate a fault is detected in the antiskid system.

The auto brake system provides automatic braking at pre–selected deceleration rates for landing.

The system operates only when the normal/reserve brake system is functioning. Antiskid system protection is provided during auto brake operation.

The AUTO BRAKES light illuminates and the EICAS advisory message AUTOBRAKES displays if the auto brake system is disarmed or inoperative.

Selecting RTO prior to takeoff arms the auto brake system. The RTO mode can be selected only on the ground. The RTO auto brake setting commands maximum braking pressure if:

  - the airplane is on the ground
  - groundspeed is above 85 knots, and
  - both thrust levers are retarded to idle

Maximum braking is obtained in this mode. If an RTO is initiated below 85 knots, the RTO auto brake function does not operate.

Five levels of deceleration can be selected for landing. However, on dry runways, the maximum auto brake deceleration rate in the landing mode is less than that produced by full pedal braking.

After landing, auto brake application begins when:

  - both thrust levers are retarded to idle, and
  - the wheels have spun up

Auto brake application occurs slightly after main gear touchdown. Deceleration is limited until the pitch angle is less than one degree, then deceleration increases to the selected level. The deceleration level can be changed (without disarming the system) by rotating the selector.

To maintain the selected airplane deceleration rate, auto brake pressure is reduced as other controls, such as thrust reversers and spoilers, contribute to total deceleration. The system provides braking to a complete stop or until it is disarmed.

The system disarms immediately, the AUTO BRAKES light illuminates and the EICAS advisory message AUTOBRAKES displays if any of the following occur:

  - pedal braking applied
  - either thrust lever advanced after landing
  - speedbrake lever is moved from the full up position after the speedbrakes have deployed on the ground
  - DISARM or OFF position selected on the AUTO BRAKES selector
  - auto brake fault
  - normal antiskid system fault

When the auto brake system disarms after landing, the auto brakes selector automatically moves to the DISARM position, the AUTO BRAKES light illuminates, and power is removed from the auto brake system. When the auto brake system disarms during takeoff, the auto brakes selector remains in the RTO position. After takeoff, the AUTO BRAKES selector automatically moves to OFF.

The parking brake can be set with the normal/reserve or alternate brake hydraulic system. If the normal/reserve and alternate brake systems are not pressurised, parking brake pressure is maintained by the brake accumulator. The brake accumulator is pressurized by the right hydraulic system. Accumulator pressure is shown on the BRAKE PRESS indicator.

The parking brake is set by depressing both brake pedals fully, while simultaneously pulling the parking brake handle up. This mechanically latches the pedals in the depressed position and commands the parking brake valve to close.

The parking brake is released by depressing the pedals until the parking brake handle releases.

The PARK BRAKE light illuminates and the EICAS advisory message PARKING BRAKE displays when the parking brake is set.

Wheel brake temperatures are displayed on the EICAS status page. Numerical values related to wheel brake temperature are displayed for each main gear brake.

Brake temperature values range from 0 to 9. Temperature values are not instantaneous and tend to build for 10 to 15 minutes after brakes are applied.

Initial range values of 0 to 2 are cyan numbers in a cyan box. For normal range values of 3 and 4, the number is cyan and the box is white for the first per truck that exceeds 2. Values in the high range of 5 to 9 have a white number and box.

The BRAKE TEMP light illuminates for values of 5 and above.

The 757-300 is equipped with a tailskid system. The tailskid extends for takeoff and landing and retracts during flight. It helps to protect the pressurised part of the airplane from contact with the runway. The tailskid uses the main landing gear actuation system.

The TAILSKID light illuminates and the EICAS advisory message TAILSKID is displayed when the tailskid position disagrees with the landing gear lever.