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to allow removal of the exits inward when the airplane is not pressurized (on the
ground).
A. Main Entrance Door:
The main entrance door, shown in Figure 3, is located on the forward
section of the left fuselage approximately midway between the cockpit and
the wing leading edge, and is the primary access to the airplane. The thirty-
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-52-00
Page 1
October 11/02
Revision 8
six (36) inch by sixty-two (62) inch door is hinged at the bottom and is
equipped with a folding stairway and handrails integrated into the interior of
the door structure. The outside of the door conforms to the curvature of the
fuselage and is manufactured in a similar manner to the fuselage, with ribs
and a covering metallic skin. The integrated stairway folds at mid-point,
allowing the stairs to extend from the entranceway threshold to just above
ground level. The handrails unfold as the stairway extends, locking into
position at full stairway extension. When the main entrance door is closed,
the handrails unlock and the stairway folds into a secured position against
the interior of the door.
The door is closed hydraulically, using pressure supplied by the auxiliary
hydraulic system that is reduced for door operation to 1400 psi (± 100) by
a reducing valve in the door lines. The door is opened manually, with the
weight of the door and attached stairway rotating the door assembly out
and down by free fall. The door opening rate is moderated by a restrictor in
the hydraulic lines that uses trapped ßuid as a brake to slow door and
stairway operation.
Door operation may be controlled from either inside or outside of the
airplane. The mechanical door latches and locks are interconnected, so
that operating either the inside or outside handles also moves the other.
The electrical circuitry for closing the door is similarly interconnected, so
that either inside or outside controls may close the door.
To close the door from outside, switches within a covered door control
panel, located under the door beneath the oxygen servicing panel, are
used to power the Essential DC bus and auxiliary hydraulic system to
retract the stairway and close the door. A BATT SWITCH within the panel is
selected ON to power the Essential DC bus and the auxiliary hydraulic
system on airplanes Serial Number (SN) 1000-1155. The OUTSIDE DOOR
SWITCH is then positioned to CLOSE to retract the stairway and close the
door. On airplanes SN 1156 and subsequent, the OUTSIDE DOOR
SWITCH will automatically power the Essential DC bus and auxiliary
hydraulic system, and there is no need to turn on the BATT SWITCH to
operate the door.
NOTE:
On airplanes SN 1000-1155, the external BATT
SWITCH must be turned OFF after the door is closed
to prevent draining the airplane batteries.
To close the door from inside the airplane, a DOOR SAFETY SWITCH on
the lower outside of the pilot circuit breaker panel is moved from the SAFE
position, routing power to the INSIDE DOOR CONT SWITCH, located
above the DOOR SAFETY SWITCH for SN 1000-1279, or located on the
cockpit door edge behind the pilot seat for SN 1280 and subsequent. The
control switch may then be selected to CLOSE, powering the Essential DC
bus and auxiliary hydraulic system to close the door.
Once the door is closed, it must be latched and locked. From the outside of
the airplane, the door is locked by pushing in the outer locking handle, then
pushing in the inner latch to fair with the outside of the door. From inside
the airplane, the door is latched and locked by pulling up on the red ballshaped
latch and then rotating the locking handle inboard and over-center.
OPERATING MANUAL
2A-52-00 PRODUCTION AIRCRAFT SYSTEMS
Page 2
October 11/02
Revision 8
The red latch is then released.
The door is locked by the movement of the inner or outer locking handles
that position six bayonet-type Þttings from the door into openings in the
door frame. The bayonet Þttings lock the door in place and close
microswitches within the door frame openings. The microswitches provide
electrical inputs to the door warning system, door hydraulic system and to
the door seal pressurization system. The microswitches are connected in
series so that each switch must be in the correct position in order to
generate the proper signal.
Automatic activation of the main entrance door emergency lighting is
available on SN 1467 and subsequent through the use of a second set of
emergency batteries. If the main entrance door is open and the EMERG
POWER ARM switchlight (cockpit overhead panel) has been previously
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