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WARNING: GROUND SPOILERS WILL DEPLOY IF POWER LEVERS
ARE RETARDED TO GROUND IDLE AND GND SPLR OFF/ARMED
SWITCH IS ARMED.
NOTE: With the nutcracker system not in the AIR mode after takeoff,
pressurization will remain at 0.25 psi differential and cabin altitude will
climb at approximately the same rate as the airplane. Manual control is
still available. If cabin rate of climb exceeds 3,000 feet per minute, rate
limiting will occur, driving the outflow valve fully closed.
NOTE: Stick shaker and stick pusher are inoperative if the nutcracker
system is not in the AIR mode after takeoff.
1. GND SPLR OFF/ARMED Switch ..............................................OFF
2. NUTCRKR SW TEST Switch......................DEPRESS AND HOLD
Continued on next page →
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 Page EG - 9
Nutcracker System Fails To Shift To Air Mode After Takeoff, ctd…
AFM 3-19-50
3. Landing Gear...............................................................................UP
4. NUTCRACKER Circuit Breaker (CPO, B-13)..........................PULL
5. NUTCRACKER BAT PWR Circuit Breaker (CPO, D-13)........PULL
(For airplanes having ASC 242.)
6. NUTCRKR SW TEST Switch..........................................RELEASE
NOTE: On airplanes SN 1000 through 1320 having ASC 381 and
airplanes SN 1321 and subsequent, wing anti ice air is exhausted
into the main landing gear wheel well area. If slush or ice is the
suspected cause of nutcracker failure, selecting WING ANTI ICE
ON may correct the problem. After heating the wheel well area for
a period of time, the flight crew may then elect to reset the
nutcracker system to determine if the problem is corrected.
To restore the nutcracker system to the ground for landing:
7. NUTCRACKER Circuit Breakers (as pulled)....................................
....................................RESET SHORTLY AFTER TOUCHDOWN
8. Speed Brakes............................................... MANUALLY EXTEND
Automatic deployment of ground spoilers will not be available.
END
‘G’ Monitor System OM 2A-31-32
Airplanes SN 1034, 1156 and subsequent and airplanes SN 1000
through 1155 with ASC 118 incorporated have a gravity force (’G’)
monitor system to record the maximum vertical acceleration
experienced by the airplane during landing. Data collected by this
system is used to assist in determining the requirement for either
overweight or hard landing inspections.
The monitoring system is activated during approach at 50 ft radio
altitude with the landing gear extended. The system is active until the
nose gear nutcracker signals weight-on-wheels. The maximum
acceleration sensed, while the system is active, is recorded by the
computer. Once deactivated by nutcracker logic, the system remains
deactivated until the subsequent approach and landing, when
activation criteria are again satisfied.
Continued on next page →
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EG - 10 May 30/02
‘G’ Monitor System, ctd… OM 2A-31-32
The recorded acceleration will be affected by normal occurrences
experienced between main gear touchdown and nose gear nutcracker
ground mode logic. These occurrences include but are not limited to:
• Ground spoiler deployment
• Rough, bumpy runways
• Travel through runway intersections
• Travel across arresting cable hardware housing
The above items can add 0.2 to 0.3 'G' to the touchdown acceleration
and are considered valid loads on the airplane structure. Normal
landing 'G' readings may vary from 1.3 to 1.6 'G'.
The established limit to determine the requirement for the hard landing
inspection for airplane weights up to and including maximum landing
weight is 2.0 'G' (2.3 'G' for airplanes SN 1214 and subsequent and
airplanes SN 1000 thru 1213 with ASC 190). The limit to determine the
requirement for an overweight landing inspection for airplane weights
exceeding maximum landing weight decreases on a linear scale from
2.0 'G' to 1.6 'G' (2.3 'G' to 1.7 'G' for airplanes SN 1214 and
subsequent and airplanes SN 1000 thru 1213 with ASC 190). The limit
depends on actual airplane weight and assumes that extremely high
side loads were not encountered during landing touchdown. If the
actual 'G' recorded for the landing is within limits and no extremely high
side loads were encountered at touchdown, no inspection is required. If
extremely high side loads were encountered at touchdown, or the 'G'
limit is exceeded, the flight crew shall log the event for maintenance
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