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having a middle glass pane. A failed middle pane usually appears shattered
and transparency is virtually lost. Window 3 is not electrically heated.
Window Heat Switch (Affected Window) ........................................OFF
· Limit maximum airspeed to 250 knots below 10,000 feet.
· Use crew and passenger oxygen, if required.
· A high speed descent should only be initiated if maximum cabin
pressure differential for the associated cracked pane cannot be
maintained or unless loss of cabin pressurization has occurred. A high
speed descent will increase the pressure on L1 and R1 when a load
carrying pane has failed. The outer pane is not a structural pane.
The flight crew can feel the cracks on a failed inner pane. If the flight crew
has limited obstruction to vision, then the outer pain is cracked. If
transparency is lost and the inner window feels smooth, then the middle
pain is cracked.
IF Window #1, 2, 4, Or 5 Is Affected:
CRACKED
PANE
MAX. DIFF
PRESSURE
APPROX. FLT.
ALTITUDE
Window 1, 2 or 5:
Outer
Inner
Both
No Restrictions
5 PSI
2 PSI
No Restriction
26,000 ft
15,000 ft
Window 4:
Outer
Middle
Both
No Restriction
5 PSI
2 PSI
No Restriction
26,000 ft
15,000 ft
(Continued)
~
OR
ANTI-ICE, RAIN
Sec. 2.3 Page 2
Rev. 11/15/02 #41
Continental
737
Flight Manual
IF There Is A Pressure Restriction:
Cabin Altitude Selector (As Installed)......................10,000 FT
Pressurization Mode Selector (As Installed) ..................STBY
Aircraft with the Digital Pressure Controllers:
Land Alt........................................................................10,000 FT
Reduce pressure differential by limiting flight altitude as
indicated in the table above.
Note: For MEA between 15,000 feet and 20,000 feet,
select a higher cabin altitude to maintain 2 PSI
differential. Above 20,000 feet, select MAN DC and
maintain 2 PSI differential.
* * * *
IF Window #3 Is Affected:
CRACKED
PANE
MAX. DIFF
PRESSURE
APPROX. FLT.
ALTITUDE
Window 3:
Outer
Inner
Both
No Restriction
No Restriction
0 PSI
No Restriction
No Restriction
>>@ 14,000 ft
BCD 13,000 ft
IF Both Panes Of Window #3 Are Affected:
Cabin Altitude Selector (As Installed)......................13,000 FT
Pressurization Mode Selector (As Installed) ..................STBY
Aircraft with the Digital Pressure Controllers:
Land Alt........................................................................10,000 FT
Reduce pressure differential by limiting flight altitude as
indicated in the table above.
* * * *
~
737
Flight Manual
Continental
ANTI-ICE, RAIN
Sec. 2.3 Page 3
Rev. 11/15/02 #41
OR
ENGINE COWL ANTI-ICE
The engine COWL ANTI-ICE light illuminated indicates:
· >>@ overtemperature or overpressure in the cowl anti-ice duct..
· BCD overpressure condition in the cowl anti-ice duct.
Flight Conditions Permitting:
Autothrottle (If Engaged)..........................................................DISENGAGE
Thrust Lever (Affected Side) ...........................................................RETARD
Reduce thrust until the COWL ANTI-ICE light extinguishes.
* * * *
ENGINE COWL VALVE OPEN
This condition is recognized by the COWL VALVE OPEN light remaining
illuminated bright blue in flight. This indicates that the cowl valve is in
disagreement with the engine anti-ice switch position.
IF Open Position:
IF Total Air Temperature Is Above 10°C:
Limit thrust of the affected engine to 80% N1 or less if possible.
* * * *
IF Closed Position:
Avoid icing conditions.
* * * *
ANTI-ICE, RAIN
Sec. 2.3 Page 4
Rev. 11/15/02 #41
Continental
737
Flight Manual
>>@ PITOT STATIC HEAT /
BCD PROBE HEAT MALFUNCTIONS
The following lights illuminated indicate associated pitot-static malfunctions:
Avoid icing conditions. Flight in icing conditions may result in erroneous flight
instrument indications.
CAPT P/S, 1 AUX STATIC Light:
Airspeed and static inputs may be unreliable, affecting the Captain’s Mach
/ airspeed indicator, altimeter, IVSI, and Standby Flight Instruments. The
cabin pressurization control, cabin altitude indicator, and cabin differential
pressure indicator may be affected.
F/O STATIC, 2 AUX P/S Light:
Inputs to the flap load limit airspeed switch may be affected.
　
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