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Supplementary Procedures -
Airplane General, Emergency
Equipment, Doors, Windows
Boeing 737 Operations Manual
Intentionally
Blank
SP.1.6
Boeing 737 Operations Manual
Supplementary Procedures
Chapter SP
Air Systems
Section 2
Wing-Body Overheat Test
Wing-body OVHT TEST switch
Push
Hold for a minimum of 5 seconds.
Both WING-BODY OVERHEAT lights - illuminated
MASTER CAUTION - illuminated
AIR COND system annunciator - illuminated
Wing-body OVHT TEST switch
Release
Both WING-BODY OVERHEAT lights - extinguished
MASTER CAUTION lights - extinguished
AIR COND system annunciator - extinguished
External Air Cart Use
CAUTION: The BAT switch should always be on when using the
airplane air conditioning system since the protective
circuits are DC. This ensures protection in the event
of loss of AC power.
Note: For engine start with a ground air source, see section SP.7.
APU BLEED air switch
OFF
ISOLATION VALVE switch
OPEN
[737-600/700]
RECIRC FAN switch
AUTO
[737-800/900]
RECIRC FAN switches
AUTO
[737-800/900]
Trim Air Switch
ON
PACK switches
AUTO or HIGH
Cabin temperature selectors
AUTO
Set for desired temperature.
SP.2.1
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
Duct pressure
20 psi minimum
If external air cannot hold 20 psi minimum and the APU is operating:
ISOLATION VALVE switch
AUTO
APU BLEED air switch
ON
APU supplies left pack and external air source supplies right pack.
Ground Air Conditioning Cart Use
Before connecting ground air conditioning cart:
PACK switches
OFF
Allows cart to operate at maximum efficiency
After disconnecting ground air conditioning cart:
PACK switches
As required
Isolated Pack Operation during Engine Start
To improve cabin air quality between starting the first and second engine:
CAUTION: Moving engine BLEED air switches while a starter is
engaged can damage the starter.
Engine No. 2
Start
After engine No. 2 stabilized:
ISOLATION VALVE switch
CLOSE
Right PACK switch
AUTO
Duct pressure
Stabilized
Engine No. 1
Start
After engine No. 1 stabilized:
ISOLATION VALVE switch
AUTO
Pressurization System Manual Mode Test
PACK switches
OFF
Pressurization mode selector
MAN
SP.2.2
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
AUTO FAIL and ALTN lights - extinguished.
MANUAL light - illuminated.
Outflow valve switch
CLOSE
Verify outflow valve position indicator moves toward CLOSE.
Outflow valve switch
OPEN
Verify outflow valve position indicator moves toward OPEN.
Pressurization mode selector
AUTO
Verify outflow valve position indicator moves toward OPEN.
MANUAL light - extinguished.
Manual Mode Operation
CAUTION: Switch actuation to the manual mode causes an
immediate response by the outflow valve. Full range
of motion of the outflow valve can take up to 20
seconds.
Pressurization mode selector
MAN
MANUAL light - illuminated
CABIN/FLIGHT ALTITUDE placard
Check
Determine the desired cabin altitude.
If a higher cabin altitude is desired:
Outflow valve switch (momentarily)
OPEN
Verify the outflow valve position indicator moves right, cabin altitude
climbs at the desired rate, and differential pressure decreases. Repeat
as necessary.
If a lower cabin altitude is desired:
Outflow valve switch (momentarily)
CLOSE
Verify the outflow valve position indicator moves left, cabin altitude
descends at the desired rate, and differential pressure increases. Repeat
as necessary.
SP.2.3
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
During Descent
Thrust lever changes should be made as slowly as possible to prevent excessive
pressure bumps.
Outflow valve switch (momentarily)
CLOSE
During descent, intermittently position the outflow valve switch toward
CLOSE, observing cabin altitude decrease as the airplane descends.
Before entering the landing pattern, slowly position the outflow valve
switch to full open to depressurize the airplane. Verify differential
pressure is zero.
Pressurization Control Operation - Landing at Alternate
Airport
At top of descent:
LAND ALT Indicator
Reset
Reset to new destination field elevation.
Automatic Pressurization Control - Landing Airport Elevation
Above 6000 Feet
[Option - High Altitude Landing switch]
If flight is less than one hour and landing altitude is less than 9500 feet:
Use Normal Procedures.
If flight is more than one hour or landing altitude is more than 9500
feet:
Use Normal Procedures except as modified below.
Prior to takeoff:
LAND ALT indicator
6000 feet
At initial descent or approximately 20 minutes prior to landing:
LAND ALT indicator
Destination field elevation
SP.2.4
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
If landing elevation above 9500 feet:
High altitude landing switch
ON
Note:CABIN ALTITUDE warning is inhibited to 14,000
feet. The need for crew oxygen may be unannounced
prior to landing
Unpressurized Takeoff and Landing
When making a no engine bleed takeoff or landing with the APU inoperative:
Takeoff
PACK switches
AUTO
ISOLATION VALVE switch
CLOSE
Engine BLEED air switches
OFF
After Takeoff
Note: If engine failure occurs, do not position engine BLEED air
switches ON until reaching 1500 feet or until obstacle clearance
height has been attained.
At not less than 400 feet, and prior to 2000 feet above field elevation:
Engine No. 2 BLEED air switch
ON
When CABIN rate of CLIMB indicator stabilizes:
Engine No. 1 BLEED air switch
ON
ISOLATION VALVE switch
AUTO
Landing
When below 10,000 feet and starting final approach turn:
Engine BLEED air switches
OFF
Avoid high rates of descent for passenger comfort.
No Engine Bleed Takeoff and Landing
When making a no engine bleed takeoff or landing with the APU operating.
SP.2.5
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
Takeoff
Note: If anti-ice is required for taxi, configure for a “No Engine Bleed
Takeoff” just prior to take-off.
Note: If anti-ice is not required for taxi, configuration for a “No
Engine Bleed Takeoff” may be accomplished just after engine
start.
Right PACK switch
AUTO
ISOLATION VALVE switch
CLOSE
Left PACK switch
AUTO
Engine No. 1 BLEED air switch
OFF
APU BLEED air switch
ON
Engine No. 2 BLEED air switch
OFF
[737-800/900]
Trim Air Switch
ON
After Takeoff
Note: If engine failure occurs, do not position engine BLEED air
switches ON until reaching 1500 feet or until obstacle clearance
height has been attained.
Engine No. 2 BLEED air switch
ON
APU BLEED air switch
OFF
When CABIN rate of CLIMB indicator stabilizes:
Engine No. 1 BLEED air switch
ON
ISOLATION VALVE switch
AUTO
Landing
If additional go-around thrust is desired, configure the pressurization system for
a no engine bleed landing.
When below 10,000 feet:
Right PACK switch
AUTO
ISOLATION VALVE switch
CLOSE
SP.2.6
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
Left PACK switch
AUTO
Engine No. 1 BLEED air switch
OFF
APU BLEED air switch
ON
Engine No. 2 BLEED air switch
OFF
SP.2.7
Supplementary Procedures -
Air Systems
Boeing 737 Operations Manual
Intentionally
Blank
SP.2.8
Boeing 737 Operations Manual
Supplementary Procedures
Chapter SP
Anti-Ice, Rain
Section 3
Anti-Ice Operation
Requirements for use of anti-ice and operational procedures for engine and wing
anti-ice are contained in Supplementary Procedures, Adverse Weather Section
SP.16.
Window Heat System Tests
Overheat Test
The overheat test simulates an overheat condition to check the overheat warning
function of the window heat system.
WINDOW HEAT switches
ON
WINDOW HEAT TEST switch
OVHT
OVERHEAT lights - On
[Option - Green ON light]
ON lights - Extinguish
Lights extinguish after approximately 1 minute.
[Option - Amber OFF light]
OFF lights - Illuminated
Lights illuminate after approximately 1 minute.
MASTER CAUTION - On
ANTI-ICE system annunciator - On
WINDOW HEAT switches
Reset
Position the WINDOW HEAT switches OFF, then ON.
Power Test
[Option - Green ON light]
The power test verifies operation of the window heat system. The test may be
accomplished when any of the window heat ON lights are extinguished and the
associated WINDOW HEAT switch is ON.
WINDOW HEAT switches
ON
Note: Do not power test when all ON lights are illuminated
SP.3.1
Supplementary Procedures -
Anti-Ice, Rain
Boeing 737 Operations Manual
WINDOW HEAT TEST switch
PWR
The controller is forced to full power, bypassing normal temperature
control. Overheat protection is still available.
WINDOW HEAT ON lights
Illuminated
If any ON light remains extinguished, the window heat system is
inoperative. Observe the maximum airspeed limit of 250 kts below 10,000
feet.
Power Test
[Option - Amber OFF light]
The power test verifies operation of the window heat system. The test may be
accomplished when any of the window heat OFF lights are illuminated and the
associated WINDOW HEAT switch is ON.
WINDOW HEAT switches
ON
Note: Do not power test when all OFF lights are extinguished
WINDOW HEAT TEST switch
PWR
The controller is forced to full power, bypassing normal temperature
control. Overheat protection is still available.
WINDOW HEAT OFF lights
Extinguished
If any OFF light remains illuminated, the window heat system is
inoperative. Observe the maximum airspeed limit of 250 kts below 10,000
feet.
SP.3.2
Boeing 737 Operations Manual
Supplementary Procedures
Chapter SP
Automatic Flight
Section 4
Level Change Climb/Descent
ALTITUDE selector
Set desired altitude
Note: If a new MCP altitude is selected while in ALT ACQ, the
AFDS engages in V/S and the existing vertical speed is
maintained.
LVL CHG switch
Push
Verify FMA display:
Thrust mode (climb) - N1
Thrust mode (descent) - RETARD then ARM
Pitch mode - MCP SPD
IAS/MACH Selector
Set desired speed
Vertical Speed (V/S) Climb/Descent
ALTITUDE selector
Set desired altitude
Note: If a new MCP altitude is selected while in ALT ACQ, the
AFDS engages in V/S and the existing vertical speed is
maintained.
V/S thumbwheel
Set desired vertical speed
Verify FMA display:
Thrust mode (climb or descent) - MCP SPD
Pitch mode - V/S
IAS/MACH Selector
Set desired speed
To transition to the vertical speed mode from another engaged climb or
descent mode:
V/S mode switch
Push
V/S climb mode engages at existing V/S.
V/S thumbwheel
Set desired vertical speed
SP.4.1
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
Verify FMA display:
Thrust mode (climb or descent) - MCP SPD
Pitch mode - V/S
IAS/MACH Selector
Set desired speed
Temporary Level-Off during Climb or Descent (Not at FMC
Cruise Altitude)
MCP altitude selector
Set desired altitude
MCP N1 light will extinguish if leveling from a climb.
N1 Limit changes to CRZ if leveling from a climb.
To continue climb/descent:
MCP altitude selector
Set desired altitude
VNAV switch
Push
Observe climb or descent initiated. Mode annunciations appear as
initial climb or descent.
Intervention of FMC Altitude Constraints during VNAV Climb
[Option - Speed and altitude intervention]
MCP altitude selector
Set new altitude
New altitude must be higher than the FMC altitude constraint(s) to be
deleted.
ALT INTV switch
Push
Each push of the ALT INTV switch will delete an FMC altitude constraint.
Intervention of FMC Cruise Altitude during VNAV Cruise
[Option - Speed and altitude intervention]
MCP altitude selector
Set
ALT INTV switch
Push
If a higher altitude is selected, a CRZ climb will be initiated.
If a lower altitude is selected, an early descent will be initiated.
SP.4.2
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
Intervention of FMC Altitude Constraints during VNAV
Descent
[Option - Speed and altitude intervention]
MCP altitude selector
Set new altitude
New altitude must be lower than the FMC altitude constraint (s) to be
deleted.
ALT INTV switch
Push
Each push of the ALT INTV switch will delete an FMC altitude constraint.
If all FMC altitude constraints are deleted, the descent mode will revert to
a VNAV speed descent.
Intervention of FMC Airspeed Constraints during VNAV
[Option - Speed and altitude intervention]
SPD INTV switch
Push
MCP IAS/MACH display shows current FMC target speed.
IAS/MACH Selector
Set desired speed
VNAV remains engaged.
To resume former FMC speed:
SPD INTV switch
Push
MCP IAS/MACH display blanks and FMC commanded VNAV speed
is active.
Altitude Hold
Altitude HOLD switch
Push
Verify FMA display:
Pitch mode - ALT HOLD
Heading Select
Heading selector
Set desired heading
Heading select switch
Push
Verify FMA display:
SP.4.3
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
Roll mode - HDG SEL
VOR Navigation
VHF NAV radio(s)
Tune and Identify
COURSE selector
Set desired course
When on an intercept heading to the VOR course:
VOR LOC mode switch
Push
Verify VOR LOC armed mode annunciates.
A/P automatically captures the VOR course.
Verify VOR LOC engaged mode annunciates upon course capture.
Note: If change to a localizer frequency is desired when captured in
the VOR mode, disengage VOR LOC mode prior to selection of
the localizer. VOR LOC mode can then be reengaged.
Instrument Approach using VNAV
Note: This procedure is not authorized using QFE.
Note: Operational approval required for the use of an MDA as a DA.
If required to remain at or above MDA during the missed
approach, a missed approach must be initiated at least 50 feet
above MDA.
Recommended roll modes for final approach:
• RNAV, GPS or TACAN approach: LNAV
• LOC-BC, VOR or NDB approach: LNAV or HDG SEL
• LOC, SDF or LDA approach: VOR/LOC or LNAV.
For LOC, LOC-BC, SDF or LDA approaches, ensure appropriate navaids are
tuned and identified prior to commencing the approach and monitor raw data
throughout the approach. For VOR and NDB approaches, raw data should be
monitored, if available.
FMC approach procedure
Select
Select the approach procedure on the ARRIVALS page. Do not
manually build the approach or add waypoints to the selected FMC
procedure. Add cold temperature corrections to waypoint altitude
constraints as appropriate.
SP.4.4
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
Verify VNAV glide path angle is displayed on the final approach
segment of the LEGS page.
RNP appropriate for approach (if required)
Verify/Enter
[Allows appropriate alerting to occur if ANP exceeds RNP.]
Within 1.5 miles prior to the FAF and after ALT HLD or VNAV PTH is
engaged:
MCP altitude
Set MDA/DA
[Allows VNAV to command descent in VNAV PTH. If the MDA/DA
does not end in zero zero, for example, 1820, set MCP ALTITUDE
window to the closest 100 foot increment above the constraint.]
Note: There may be a level segment beyond the FAF before
intercepting the descent path.
Prior to reaching FAF:
AFDS roll mode
Verify/select
Verify appropriate roll mode annunciates.
VNAV switch (if required)
Push
Select VNAV if in ALT HLD. Verify VNAV PTH annunciates.
Speed Intervention
Select
Autopilot
Verify engaged
[Autopilot should remain engaged until suitable visual reference is
established.]
Prior to reaching MDA/DA and when the airplane is at least 300 feet
below the missed approach altitude:
MCP altitude
Set missed approach altitude
At MDA/DA/Missed approach point:
If suitable visual reference is not established, execute a missed
approach.
After suitable visual reference is established:
A/P disengage switch
Push
Disengage the autopilot before descending below MDA/DA.
SP.4.5
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
A/T disengage switch
Push
Disengage the autothrottle before descending below
MDA/DA.
Instrument Approach using Vertical Speed (V/S)
Note: Autopilot use is recommended until suitable visual reference is
established.
Recommended roll modes:
• RNAV, GPS, TACAN, LOC-BC, VOR or NDB approach: LNAV
or HDG SEL.
• LOC, SDF or LDA approach: LOC or LNAV.
Ensure appropriate navaids (VOR, LOC or NDB) are tuned and
identified prior to commencing approach.
Before descent to MDA:
MCP altitude
Set
Set the first intermediate altitude constraint or the MDA. When
the current constraint is assured, the next constraint may be set
prior to ALT HOLD is engaged to achieve continuous descent
path.
If constraints or MDA do not end in zero zero, for example,
1820, set MCP ALTITUDE window to the closest 100 foot
increment above the constraint.
At descent point:
Desired V/S
Set
Set desired V/S to descend to MDA. Use a V/S that results in
little or no level flight segment at the MDA.
Verify V/S mode annunciates.
Approaching MDA:
MCP altitude
Set missed approach altitude
At MDA/missed approach point:
If suitable visual reference is not established, execute a missed
approach.
SP.4.6
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
After a suitable visual reference is established:
A/P disengage switch
Push
Disengage the autopilot before descending below MDA.
A/T disengage switch
Push
Disengage the autothrottle before descending below MDA.
Circling Approach
Note: Autopilot use is recommended until intercepting the landing
profile.
MCP altitude selector
Set
If the MDA does not end in zero zero, for example, 1820, set MCP
ALTITUDE window to the closest 100 foot increment above the
MDA.
Accomplish an instrument approach, establish suitable visual reference
and level off at MCP altitude.
Verify ALT HLD mode annunciates.
Verify ALT HLD or VNAV ALT mode annunciates.
MCP altitude selector
Set missed approach altitude
HDG SEL switch
Push
Verify HDG SEL mode annunciates.
Intercepting the landing profile:
Autopilot disengage switch
Push
Autothrottle disengage switch
Push
SP.4.7
Supplementary Procedures -
Automatic Flight
Boeing 737 Operations Manual
Intentionally
Blank
SP.4.8
Boeing 737 Operations Manual
Supplementary Procedures
Chapter SP
Communications
Section 5
Aircraft Communication Addressing and Reporting System
(ACARS)
The following procedures are applicable to the noted ACARS functions from the
company pages.
Pre-Departure Clearance
The flight crew shall manually verify (compare) the filed flight plan versus the
digital pre-departure clearance and shall initiate voice contact with Air Traffic
Control if any question/confusion exists between the filed flight plan and the
digital pre-departure clearance.
Digital-Automatic Information Service
The flight crew shall verify that the D-ATIS altimeter setting numeric value and
alpha value are identical. If the D-ATIS altimeter setting altimeter numeric value
and alpha values are different, the flight crew must not accept the D-ATIS
altimeter setting.
Oceanic Clearances
The flight crew shall manually verify (compare) the filed flight plan versus the
digital oceanic clearance and initiate voice contact with Air Traffic Control if any
questions/confusion exists between the filed flight plan and the digital oceanic
clearance.
Cockpit Voice Recorder Test
[Option - Voice Recorder switch]
Note: The Cockpit VOICE RECORDER switch must be in the ON
position or at least one engine must be operating to perform this
test.
Test switch
Push
After a slight delay:
[Option]
Monitor indicator
Green band
A tone may be heard through a headset plugged into the headset jack.
[Option]
Test light
ON
A tone may be heard through a headset plugged into the headset jack.
SP.5.1
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