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Flap and Slat Sequencing
LE devices and TE flaps are normally extended and retracted by hydraulic power from system B. When the FLAP lever is in the UP detent, all flaps and LE devices are commanded to the retracted or up position. Moving the FLAP lever aft allows selection of flap detent positions 1, 2, 5, 10, 15, 25, 30 or 40. The LE devices deployment is sequenced as a function of TE flaps deployment.
When the FLAP lever is moved from the UP position to the 1, 2, or 5 position, the TE flaps extend to the commanded position and the LE:
.
flaps extend to the full extended position, and

.
slats extend to the extend position.

 

When the FLAP lever is moved beyond the 5 position the TE flaps extend to the
commanded position and the LE:

.
flaps remain at the full extended position, and

.
slats extend to the full extended position.
The LE devices sequence is reversed upon retraction.
Mechanical gates hinder inadvertent FLAP lever movement beyond flaps 1 for

 

one engine inoperative go–around, and flaps 15 for normal go–around.
Indicator lights on the center instrument panel provide overall LE devices position
status. The LE DEVICES annunciator on the aft overhead panel indicates the
positions of the individual flaps and slats.

Flap Load Relief
A flap load limiter provides a TE flap load relief function which protects the flaps from excessive air loads. This function is operative at the flaps 40 position only. The FLAP lever does not move, but the flap position indicator displays flap retraction and re–extension and on some airplanes a FLAP LOAD RELIEF light illuminates.
When the flaps are set at 40 the TE flaps:
.
retract to 30 if airspeed exceeds 158 knots

.
re–extend when airspeed is reduced to 153 knots.

Autoslats
At flap positions 1, 2 and 5 an autoslat function is available that moves the LE slats to FULL EXTEND if the airplane approaches a stall condition.
Copyright . The Boeing Company. See title page for details.
December 5, 2003  9.20.17
Flight Controls -System Description

737 Operations Manual
The autoslat system is designed to enhance airplane stall characteristics at high angles of attack during takeoff or approach to landing. When TE flaps 1 through 5 are selected, the LE slats are in the extend position. As the airplane approaches the stall angle, the slats automatically drive to the full extended position, prior to stick shaker activation. The slats return to the extend position when the pitch angle is sufficiently reduced below the stall critical attitude.
Autoslat operation is normally powered by hydraulic system B. An alternate source of power is provided by system A through a power transfer unit (PTU) if a loss of pressure is sensed from the higher volume system B engine driven pump. The PTU provides system A pressure to power a hydraulic motorized pump, pressurizing system B fluid to provide power for the autoslat operation. (Refer to Chapter 13, Hydraulics, Power Transfer Unit)
Alternate Extension
In the event that hydraulic system B fails, an alternate method of extending the LE devices, and extending and retracting the TE flaps is provided.
The TE flaps can be operated electrically through the use of two alternate flap switches. The guarded ALTERNATE FLAPS master switch closes a flap bypass valve to prevent hydraulic lock of the flap drive unit and arms the ALTERNATE FLAPS position switch. The ALTERNATE FLAPS position switch controls an electric motor that extends or retracts the TE flaps. The switch must be held in the DOWN position until the flaps reach the desired position. No asymmetry protection is provided through the alternate (electrical) flap drive system.
Note: The LE devices cannot be retracted by the standby hydraulic system.
When using alternate flap extension the LE flaps and slats are driven to the full extended position using power from the standby hydraulic system. In this case the ALTERNATE FLAPS master switch energizes the standby pump, and the ALTERNATE FLAPS position switch, held in the down position momentarily, fully extends the LE devices.
Copyright . The Boeing Company. See title page for details.
9.20.18  December 5, 2003
Flight Controls -
Leading Edge Devices and Trailing Edge Flaps Schematic

 

As installed
Flight Controls -System Description 737 Operations Manual

High Lift Device Protection and Indication Trailing Edge Flap Asymmetry
When a trailing edge asymmetry develops, a comparator switch closes the TE flap bypass valve, removing hydraulic power from the flap drive unit. The flap position will be displayed as a needle split on the flap position indicator.
Leading Edge Device Improper Position
When a leading edge device is in an improper position the LE FLAPS TRANSIT light remains illuminated and one of the following indications is displayed on the LE Devices Annunciator Panel:
　
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