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126 Cards in this Set

  • Front
  • Back

APPROVED OPERATIONS

The 737 aircraft are certified in the transport category (FAR 25 and 36) and are eligible for the following types of operation when the required equipment is installed and approved in accordance with the applicable FARs.
• Visual Flight (VFR)
• Instrument Flight (IFR)
• 737 aircraft are category “C” for Instrument Approaches except for Circling, which is category “D”.
• Night Flight
• Icing Conditions
• [7,8,9] Extended Over Water Operations (ETOPS)
PILOT REQUIREMENTS
Minimum Captain and First Officer
FLIGHT MANEUVERING LOAD ACCELERATION LIMITS
Flaps Up +2.5g to -1.0g
Flaps Down +2.0g to 0.0g
CONFIGURATION DEVIATION LIST (CDL)
When operating is scheduled with certain secondary airframe and engine parts missing, the aircraft must be operated in accordance with the limitations specified in the basic Aircraft Flight Manual, as amended by the CDL.
OPERATING LIMITATIONS
OPERATIONAL ENVELOPE
Maximum Operating Pressure Altitude
[7,8,9]41,000 feet
[5] 37,000 feet
Maximum Takeoff/Landing Pressure Altitude
[7,8,9] 10,000 feet
[5] 8,400 feet
Maximum Flight Operating Latitude
[7,8,9] 82° North and 82° South
[5]73° North and 60° South
Runway Slope
Maximum ±2%
Maximum Unrestricted Takeoff/Landing Tailwind Component
Tailwind 10 Knots
Maximum Restricted Takeoff/Landing Tailwind Component
Tailwind* 15 Knots *See Parameters for operating restrictions.
Maximum Airspeed
The maximum operating limit speed (VMO pointer/overspeed warning) shall not be deliberately exceeded in any phase of flight.
Note: All airspeed markings and placards in the aircraft are shown as indicated (IAS) values, and are not corrected for instrument error.
Note: VA is defined as the speed above which maneuvers involving full application of rudder, ailerons or elevator, or maneuvers involving angles of attack near stall, should be avoided.
VMO
Indicated by max airspeed pointer on airspeed indicator MMO .82 Mach
Maximum gear retraction speed
235 Knots
Maximum gear extension speed
270 Knots/.82M
Maximum gear operating/extended speed
320 Knots/.82M
Recommended Severe Turbulence Penetration Airspeeds
Cruise TURB N1 setting from cruise page.
[7,8,9] Climb & Descent 280 Knots/.76 Mach
[5] Climb & Descent 280 Knots/.73 Mach
Note: If severe turbulence is encountered at altitudes below 15,000 feet and the aircraft gross weight is less than the maximum landing weight, the aircraft may be slowed to 250 knots in the clean configuration.
Flap Speeds
Position [7] [8,9] [9er] [5]
01 230K 230K 230K 230K
02 230K 230K 230K 230K
05 225K 225K 225K 225K
10 210K 210K 205K 210K
15 195K 200K 200K 195K
25 170K 190K 195K 190K
30 165K 175K 180K 185K
40 156K 162K 170K 158K
Over Wing Exits
[7,8,9] Installation of handle covers on the over wing exits must be verified prior to departure whenever passengers are carried.
Windshear Alert Takeoff
Windshear Alert Takeoff with forward looking windshear warning alert annunciated is not approved.
Maximum Restricted Takeoff Tailwind Component Parameters [7,8,9]
Takeoffs and landings with tailwind components over 10 knots up to 15 knots are permitted with the following restrictions:
Takeoffs (Dispatch Requirements):
• Actual tailwind component does not exceed value authorized by Accuload Pilot Weight Manifest.
• Runway is clear and dry.
• Antiskid and thrust reversers are fully operational.
• Max takeoff rated thrust is used.
• Auto spoilers are used.
Maximum Restricted Landing Tailwind Component Parameters [7,8,9]
Landings (Dispatch Requirements)
• Antiskid and thrust reversers are fully operational.
• Landing Flaps 15/30/40.
• Auto spoilers are used (unless correction is taken).
• Braking action reported at least GOOD. Landings (In-flight equipment failure and/or unplanned tailwinds of 11-15 knots):
• Landing distances are verified by reference to Section 5, CONFIGURATION LANDING DISTANCE CHARTS (UNFACTORED).
OPERATING PARAMETERS DOOR-MOUNTED ESCAPE SLIDES
On revenue flights, the escape slide retention bar (girt bar) must be installed during taxi, takeoff and landing.
MINIMUM GROUND TIME AFTER LANDING
If landing weight exceeds the chart value in the Maximum Quick Turn Around Weight Limits chart, Section 5, wait at least:
[7,8,9] 67 Minutes
[5] 53 Minutes
then check wheel thermal plugs before making a subsequent takeoff. Maintenance may use an alternate approved procedure to ascertain acceptable brake temperatures for dispatch.
CROSSWIND GUIDELINES
Note: Refer to Wind Component chart for determining Crosswind Component. Note: The crosswind guidelines presented below were derived through flight test data, engineering analysis, and piloted simulation evaluations; therefore, the use of these guidelines should be based on the current weather conditions and the pilot’s ability and experience level.
Recommended Crosswind Component Guidelines
Runway Condition Takeoff Crosswind Component (Kts) (2)/Landing Crosswind Component (kts)(3)
Dry 34/40
Wet 25/40
Standing Water / Slush 15/20
Snow – No Melting(1) 21/35
(1) Takeoff or landing on untreated snow should only be attempted when no melting is present.
(2) Assumes an engine failure RTO.
(3) Reduce landing crosswind guidelines by 5 knots on wet or contaminated runways when asymmetric reverse thrust is used.
Notes:
Include gusts when applying all wind limits.
Applicable for runways 148 ft (45 meters) or greater in width.
On slippery runways, crosswind guidelines are a function of runway surface condition, aircraft loading, and assume proper pilot technique.
Engine surge can occur with a strong crosswind component if takeoff thrust is set prior to brake release. Therefore, rolling takeoffs are strongly advised when crosswinds exceed 20 knots.
Sideslip only (zero crab) landings are not recommended with crosswind components in excess of 15 knots at flaps 15, 18 knots at flaps 30, or 21 knots at flaps 40. This recommendation ensures adequate ground clearance and is based on maintaining adequate control margin.
GROSS WEIGHT LIMITATIONS
1 Maximum landing weight and zero fuel weight increase will occur in the near future. Correct weight limits for each aircraft will be displayed in the computer flight plan weight categories and the ACCULOAD.
SYSTEM LIMITATIONS AND PARAMETERS
AIR SYSTEM LIMITATIONS
Pressurization
Maximum Cabin Pressure Differential
[7,8,9] 9.10 psi
[5] 8.65 psi
SYSTEM LIMITATIONS AND PARAMETERS
AIR SYSTEM LIMITATIONS
Pressurization
Maximum Differential Pressure For Takeoff and Landing
[7,8,9] .125 psi
SYSTEM LIMITATIONS AND PARAMETERS
AIR SYSTEM LIMITATIONS
Pressurization
Cabin Altitude Warning Takeoff Briefing
(Ref. AD 2008-23-07 & 2011-03-14)
• With the CABIN ALTITUDE and TAKEOFF CONFIG lights not installed, or installed but not activated:
As part of the Pilot Briefing before engine start for the first flight of the day or following any change of either flight crew member, the pilot - in - command will ensure the Cabin Altitude Warning indications and procedures are briefed in accordance with the procedures contained in the Normal Procedures section of this manual.
AIR SYSTEM PARAMETERS
Pack Operation During Takeoff, Approach, and Landing
When engine bleeds are on, do not operate air conditioning packs in high for takeoff, approach, and landing.
Operating Differential Pressure
[7,8,9] Above 37,000 ft. 8.35 ± .1 psi
28,000 through 37,000 ft. 7.8 ± .1 psi
Below 28,000 ft 7.45 ± .1 psi
Duct Pressure For Maximum Cooling
Duct pressure for maximum cooling 20-25 psi
Minimum Duct Pressure For Two Pack Operation From One Bleed Source
Minimum duct pressure for two pack operation from one bleed 20-25 psi
ANTI-ICE AND RAIN LIMITATIONS
Icing conditions exist on the ground and for takeoff when:
Icing conditions exist on the ground and for takeoff when:
Outside air temperature 10° C or below
AND visible moisture in any form is present (i.e., clouds, fog with visibility of 1 mile or less, rain, snow, sleet, or ice crystals),
OR
While operating on ramps, taxiways, or runways where snow, standing water, or slush may be ingested by the engines or freeze on the engines, nacelles, or engine sensor probes.
Warning: Do not rely on airframe visual icing cues to activate engine anti-ice. Delaying the use of engine anti-ice until ice build- up is visible from the flight deck may result in severe engine damage. Use the temperature and visible moisture criteria specified in this section.
ANTI-ICE AND RAIN LIMITATIONS
Icing conditions exist in flight when:
Total air temperature 10° C or below and  Visible moisture in any form is present (i.e., clouds, fog with visibility of 1 mile or less, rain, snow, sleet, or ice crystals).
Warning: Do not rely on airframe visual icing cues to activate engine anti-ice. Delaying the use of engine anti-ice until ice build- up is visible from the flight deck may result in severe engine damage. Use the temperature and visible moisture criteria specified in this section.
Takeoff in Moderate/Heavy Freezing Rain or Hail
Takeoff in Moderate / Heavy Freezing Rain or Hail is prohibited.
Engine Anti-Ice must be ...
must be ON during all ground operations, including after landing, when icing conditions exist or are anticipated.
Must be ON during all flight operations when icing conditions exist or are anticipated, except during climb and cruise when the temperature is below –40°C SAT.
Must be ON prior to and during descent in all icing conditions, including temperatures below –40°C SAT.
Engine ignition must be selected to CONT prior to and during engine anti- ice operation.
Wing Anti-Ice
Use wing anti-ice during all ground operations between engine start and takeoff when icing conditions exist or are anticipated, unless the aircraft is or will be protected by the application of Type II or Type IV fluid.
Do not operate wing anti-ice on the ground when the OAT is above 10°C/50°F.
Do not use wing anti-ice as a substitute for ground de-icing/anti-icing.
ANTI-ICE AND RAIN PARAMETERS
Windshield Wiper Do not operate windshield wiper....
on a dry windshield.
Window Heat Window heat must be...
ON 10 minutes before takeoff.
[7,8,9] Probe/ [5]Pitot Heat
Probe/Pitot heat must be......
Probe/Pitot heat must be ON prior to takeoff.
Wing Anti-Ice During takeoff
Do not use wing anti-ice until after...
Do not use wing anti-ice until after the first thrust reduction.
AUTO-FLIGHT LIMITATIONS
Autopilot Engaged On takeoff or missed approach, do not engage autopilot below:
1000 feet AGL
AUTO-FLIGHT LIMITATIONS
Autoland - Maximum Winds
Headwind 25 knots
Crosswind 15 knots
Tailwind: [7,8,9] Flaps 30 and 40 - 10 knots
[9] (401-412) Flaps 40 - 10 knots
[9] (401-412) Flaps 30:
Field elevation 4000 feet or less: 10 Knots
Field elevation 4001-6000 feet: 5 Knots
Field elevation 6001 feet and above: 0 Knots
AUTO-FLIGHT LIMITATIONS
Aileron Trim
Use of Aileron Trim with the Autopilot engaged is prohibited.
AUTO-FLIGHT LIMITATIONS
Autopilot Use
Autopilot use prohibited below 100 feet radio altitude at airport pressure altitudes above 8400 feet.
AUTO-FLIGHT LIMITATIONS
Autopilot Minimum altitude for use of autopilot on approach:
ILS/GLS Coupled Approaches (no autoland)
50 feet AGL
Note: Autopilot must be disconnected before descending below 500 feet AGL without a published MDA or DA.
AUTO-FLIGHT LIMITATIONS
Autopilot Minimum altitude for use of autopilot on approach:
Non-precision approaches
50 feet below MDA/DA
Note: Autopilot must be disconnected before descending below 500 feet AGL without a published MDA or DA.
AUTO-FLIGHT LIMITATIONS
Autopilot Minimum altitude for use of autopilot on approach:
Autolandings
Touchdown
Note: Autopilot must be disconnected before descending below 500 feet AGL without a published MDA or DA.
AUTO-FLIGHT LIMITATIONS
Autolandings
• Autoland capability may only be used to runways at or below 8400 ft pressure altitude.
• The ILS autoland capability may only be used with flaps 30 and 40 with both engines operative.
• Maximum and minimum glideslope angles for autoland are 3.25° and 2.5° respectively.
AUTO-FLIGHT LIMITATIONS
AUTO-FLIGHT PARAMETERS
• The Autoland System should not be used for overweight landings.
• Do not use the autopilot or the autothrottle for approach if the associated radio altimeter is inoperative.
AUXILIARY POWER UNIT (APU) LIMITATIONS
APU bleed and electrical maximum altitude:
10,000 ft
AUXILIARY POWER UNIT (APU) LIMITATIONS
APU bleed maximum altitude:
17,000 ft
AUXILIARY POWER UNIT (APU) LIMITATIONS
APU electrical load maximum altitude:
41,000 feet [7,8,9]
35,000 feet [5]
AUXILIARY POWER UNIT (APU) LIMITATIONS
APU EGT Temperature [5]
Limits:
Max EGT - 760°C
Max Continuous - 710°C
AUXILIARY POWER UNIT (APU) PARAMETERS
APU Starter Duty Cycle
• [7,8,9] For both ground and in flight starts, 15 minute cooling is required after third start attempt.
• [5] For both ground and in flight starts, 5 minute cooling is required between the second and third start attempt. A wait of one hour is required after the third start attempt.
AUXILIARY POWER UNIT (APU) PARAMETERS
APU Warmup/Cooldown
Operate APU one minute before using APU bleed air.
[5] Operate APU one minute with APU bleed air off prior to shutdown.
AUXILIARY POWER UNIT (APU) PARAMETERS
APU Shutdown Wait a minimum
[7,8,9] 120 seconds
[5] 20 seconds
for APU shutdown cycle to complete, then turn battery switch to OFF.
AUXILIARY POWER UNIT (APU) PARAMETERS
APU bleed valve must be closed when:
• Ground pneumatic air connected and ISOLATION valve open
• Engine no. 1 bleed valve open (engine no. 1 running)
• ISOLATION valve open and engine no. 2 bleed valve open (engine no. 2 running)
Note: APU bleed valve may be open during engine start, but avoid engine power above idle.
COMMUNICATIONS LIMITATIONS
HF Radio Frequencies
Flights predicated on the use of these frequencies are prohibited:
MHz 11.133/22.434/22.683/22.766/29.489/29.490
Aircraft Communications and Reporting System
The Aircraft Communications And Reporting System (ACARS)
is limited to transmission and receipt of messages that will not create an unsafe condition if the message is improperly received, such as the following conditions:
• The message or parts of the message are delayed or not received,
• The message is delivered to the wrong recipient, or
• The message content may be frequently corrupted. However, Pre-Departure Clearances, Digital Automatic Terminal Information Service, Oceanic Clearances, Weight and Balance, and Takeoff Data messages can be transmitted and received over ACARS if they are verified per approved operational procedures.
Use of VHF-3 when ACARS is Operational
Do not use VHF-3 for ATC communications with ACARS operational.
ELECTRICAL LIMITATIONS
Maximum single engine drive generator load
75KVA – 215 amps (ground operations)
ELECTRICAL PARAMETERS
Minimum battery voltage for APU start
23 volts
ELECTRICAL PARAMETERS
Maximum engine driven generator load [5]
125 amps
ELECTRICAL PARAMETERS
Maximum TR load [5]
65 amps
50 amps (ground operation without cooling)
EMERGENCY LIGHTING LIMITATIONS
Photoluminescent Lighting
Photoluminescent floor emergency lighting (if installed) must be charged in accordance with procedures as specified in Chapter 3.
ENGINES LIMITATIONS
Engine Ignition Ignition must be on for:
• Takeoff
• Landing
• Engine Anti-Ice Operation
• Heavy Rain
ENGINES LIMITATIONS
Oil Pressure Oil pressure must be in normal range for takeoff.
Minimum Oil Pressure 13 psi
ENGINES LIMITATIONS
Oil Temperature
Oil Temperature Maximum 155°C 165°C
Oil Temperature Maximum Continuous 140°C 160°C
Oil Temperature Maximum Allowable 140°C – 155°C (45 minutes) 160°C – 165°C (15 minutes)
ENGINES LIMITATIONS
Engine Limit Display Markings
Red Line - Maximum and minimum limits
Amber Arc - Cautionary range
Whire Arc [7,8,9] - Normal operating range
Green Arc [5] - Normal operating rang
ENGINES LIMITATIONS
Maximum EGT Limits [7,8,9] / [5]
Maximum EGT Limits [7,8,9] / [5]
Takeoff (5 minutes) 950°C / 930°C
Takeoff (transient - 20 seconds) N/A / 931°C – 940°C
Maximum Continuous: 925°C / 895°C
Start: 725°C / 725°C
ENGINES LIMITATIONS
Engine Starter Duty Cycle
[7,8,9]
• Do not exceed 2 minutes during each start attempt.
• A minimum of 10 seconds is needed between start attempts.
[5]
• Do not exceed 2 minutes during each start attempt.
• A minimum of 20 seconds is needed between the first and second start attempts.
• A minimum of three minutes is needed after the second and subsequent start attempts.
ENGINES LIMITATIONS
RPM Maximum
RPM Maximum
Maximum [7,8,9] / [5]
Maximum N1 - 104.0% / 106%
Maximum N2 - 105.0% / 105%
ENGINES LIMITATIONS
Reduced Thrust
Takeoffs Operation with assumed temperature reduced takeoff thrust is not permitted with anti-skid inoperative.
Use of assumed temperature reduced takeoff thrust is not permitted when the runway is contaminated with standing water, ice, slush, or snow.
ENGINES LIMITATIONS
Reverse Thrust
Reverse thrust for ground use only, intentional use of reverse thrust in flight is prohibited.
ENGINES LIMITATIONS
Engine Control (EEC) [7,8,9]
• Both EECs must be either ON or ALT for takeoff.
• Operation with assumed temperature reduced for takeoff thrust is not permitted with the Electronic Engine Control (EEC) in ALT mode.
ENGINES LIMITATIONS
Power Management Computer (PMC) [5]
• Both PMCs must be either ON or OFF for takeoff.
• Operation with assumed temperature reduced takeoff thrust is not permitted with the Power Management Computer (PMC) in OFF mode.
ENGINES PARAMETERS
Minimum oil quantity prior to engine start
60% [7,8,9]
3.0 Gallons [5]

ENGINES PARAMETERS
Starter Engagement
^Do not engage starter above 20% N2.
ENGINES PARAMETERS
Engine Starts In Ambient Temperatures Below -35°C
Idle engine 2 minutes before changing thrust lever position.
ENGINES PARAMETERS
Minimum Duct Pressure for Start [5]
30 psi at sea level decreasing ½ psi per 1000 ft. above sea level.
FIRE PROTECTION LIMITATIONS
Smoke Detection & Fire Suppression System [5]
(Ref. STC ST01674AT):
• The cargo compartment smoke detector and fire suppression system must be verified to be serviced and operational before cargo can be carried in the cargo compartments.
• The aircraft must land at the nearest suitable airport within 60 minutes after the activation of the suppression system.
FIRE PROTECTION PARAMETERS
Lavatory Fire Extinguishing
If evidence of over temperature as indicated by black placard dot(s) or nozzle discharge (nozzle tip turns aluminum color), maintenance action required.
FIRE PROTECTION PARAMETERS
Engine fire extinguisher bottle pressure
800 psi @ 70°F
FLIGHT CONTROLS LIMITATIONS
Flap Extension Altitude
Maximum 20,000ft.
FLIGHT CONTROLS LIMITATIONS
Holding In Icing Conditions
Holding in icing conditions with flaps extended is prohibited.
FLIGHT CONTROLS LIMITATIONS
Speed Brake Lever Operation In Flight
• In flight, do not extend the speed brake lever beyond the flight detent (Ref: A.D. 2003-03-22)
• Do not deploy the speed brakes in flight at radio altitudes less than 1,000 feet.
FLIGHT CONTROLS LIMITATIONS
Control Inputs
Avoid rapid and large alternating control inputs, especially in combination with large changes in pitch, roll, or yaw (e.g. large side slip angles) as they may result in structural failure at any speed, including below VA.
FLIGHT CONTROLS PARAMETERS
Alternate Flap Duty Cycle
• When extending or retracting flaps with the Alternate Flaps position switch, allow 15 seconds after releasing the Alternate Flaps position switch before moving the switch again to avoid damage to the alternate flap motor clutch.
• After a complete extend/retract cycle, i.e., 0 to 15 and back to 0, allow 5 minutes cooling before attempting another extension.
FLIGHT CONTROLS PARAMETERS
Maximum airspeed to extend flaps with alternate system:
230 knots
FLIGHT CONTROLS PARAMETERS
Speed Brake Lever Operation In Flight
Speed brakes should not be deployed with flaps extended beyond flaps 15.
FLIGHT CONTROLS PARAMETERS
Mach Trim Fail (both channels) Maximum Speed:
280 Knots / .82 Mach [7,8,9]
.74 Mach [5]

FLIGHT INSTRUMENTS, DISPLAYS PARAMETERS
Altitude Display Limits For RVSM Operations:
^• Standby altimeters do not meet altimeter accuracy requirements of RVSM airspace.
• The maximum allowable in-flight difference between Captain and First Officer altitude displays for RVSM operations is 200 feet.
• The maximum allowable on the ground display differences for RVSM operations are:
FLIGHT INSTRUMENTS, DISPLAYS PARAMETERS
Maximum Altimeter Differences
Field Elevation / Max Diff Btwn Capt & F/O / Max Diff Btwn Capt or F/O & Field Elevation
[7,8,9]
Sea Level to 5000 Feet - 50 Feet / 75 Feet
10,000 Feet - 60 Feet / 75 Feet
[5]
Sea Level - 40 Feet / 75 Feet
5000 Feet - 45 Feet / 75 Feet
10,000 Feet - 50 Feet / 75 Feet
FLIGHT INSTRUMENTS, DISPLAYS PARAMETERS
Weather Radar Use During Ground Operations
Do not operate weather radar during fueling, near fuel spills, or within 15 feet of people except in test mode.
FLIGHT INSTRUMENTS, DISPLAYS PARAMETERS
Maximum Allowable Altimeter Differences
SEE LIMITATIONS Sec 1 Pg 27
ALTITUDE CDS/CDS  ELEC/ELEC
CDS/STBY  ELEC/STBY
Sea Level 5000 feet 10,000 feet 15,000 feet 20,000 feet 25,000 feet 30,000 feet 35,000 feet 40,000 feet 41,000 feet
50 feet 50 feet 60 feet 70 feet 80 feet 100 feet 120 feet 140 feet 160 feet 170 feet
50 feet 80 feet 120 feet (See Note) (See Note) (See Note) (See Note) (See Note) (See Note) (See Note)
Note: Above 10,000 feet and 0.4 Mach, position error causes the tolerance to diverge rapidly and direct crosscheck becomes inconclusive. Between 10,000 and 29,000 feet, differences greater than 400 feet should be suspect and verified by ground maintenance checks. Between 29,000 feet and the maximum operating altitude, differences greater than 500 feet should be suspect and verified by ground maintenance checks.
FLIGHT INSTRUMENTS, DISPLAYS PARAMETERS
Integrated Standby Flight Display (ISFD)
The Integrated Standby Flight Display (ISFD) must be initialized in accordance with approved procedures.
FLIGHT MANAGEMENT, NAVIGATION PARAMETERS
Flight Management Computer System (FMCS)
• The Flight Management Computer has been demonstrated to meet the requirement of FAA Advisory Circular 20-130A for a multi-sensor area navigation system when operated with radio or Global Position System (GPS) (if installed) updating. When operated in this configuration, the FMCS may be used for enroute and terminal operations.
• The FMCS with dual FMC operations may be used as primary means for navigation for instrument approaches (excluding ILS, LOC, LOC-BC, LDA, SDF, GLS, MLS, VOR and NDB) with ACTUAL (ANP) less than RNP.
Note: The FMCS with dual FMC operations may be used as primary means of navigation for VOR and NDB final approach segments when authorized for use with RNAV substitution via a Company NOTAM or 10-7 page note.
• The FMCS with single FMC operations may be used as a supplement to the primary means of navigation for instrument approaches.
FLIGHT MANAGEMENT, NAVIGATION PARAMETERS
RNAV Approaches
Demonstrated Minimums
Mode of Flight / FMS Updated By GPS/ FMS Not Updated By GPS
Autopilot/Flight Director On:
LNAV/VNAV Engaged*/ 0.11 RNP** / 0.19 RNP
Flight Director On:
LNAV / VNAV Engaged* / 0.15 RNP / 0.24 RNP
Map Only: No LNAV/VNAV* / 0.64 RNP/ 0.72 RNP
* 10 mile scale or less required.
** RNAV (RNP) Two autopilots required to be functional from IAF to minimums for procedures less than 0.15.
FLIGHT MANAGEMENT, NAVIGATION PARAMETERS
RNAV (RNP) Procedures
[7,8,9]
Remote Altimeter settings...
Remote Altimeter settings (not taken at the local airport) not authorized for RNAV (RNP) procedures.
FLIGHT MANAGEMENT, NAVIGATION PARAMETERS
ADIRU Alignment must....
ADIRU alignment must not be attempted at latitudes greater than 78 degrees 15 minutes.
FUEL LIMITATIONS WARNING:
Do not reset a tripped fuel pump or fuel pump control circuit breaker.
FUEL LIMITATIONS WARNING:
Authorized Fuels and Temperatures
Fuel Type / Minimum (C) / Maximum (C)
JET A / -37 /+49
JET A-1 / -44 / +49
JP-5 / -43 / +49
JP-8 / -44 / +49
FUEL LIMITATIONS WARNING:
Authorized Fuels and Temperatures
The use of Jet B and JP-4 fuels is prohibited. Jet A and A1 fuels are approved for unlimited use in this engine. Fuels conforming to JP-5 or JP-8 are acceptable alternatives. The engines will operate satisfactorily with any of the approved fuels or any mixture thereof.
FUEL LIMITATIONS WARNING:
Authorized Fuels and Temperatures
Tank fuel temperature prior to takeoff....
Tank fuel temperature prior to takeoff must not be less than -43°C (-49°F) or 3°C above the fuel freezing point, whichever is higher.
FUEL LIMITATIONS WARNING:
Authorized Fuels and Temperatures
Inflight tank fuel temperature must be maintained...
Inflight tank fuel temperature must be maintained at least 3°C above the fuel freezing point of the fuel being used. Minimum temperature in chart above includes this requirement. The use of Fuel System Icing Inhibitor additives does not change the minimum fuel tank temperature limit.
FUEL LIMITATIONS WARNING:
Tank Capacity - Usable [7,8,9] / [5]
Wing tanks / 1,288 U.S. Gals - 8630 lbs. / 1,499 U.S. Gals - 10043 lbs.
Center tank / 4,299 U.S. Gals - 28803 lbs. /2,313 U.S. Gals -15497 lbs.
Fuel Density is 6.7 lb/gal.
FUEL LIMITATIONS WARNING:
Fuel Loading
Main wing tanks 1 and 2 must be scheduled to be full if the center wing tank contains more than 1000 lbs. of fuel. With 1000 lbs. of center tank fuel or less, partial wing tank fuel may be loaded provided the effects of balance have been considered.
FUEL LIMITATIONS WARNING:
Fuel Imbalance
Lateral fuel imbalance between wing tanks 1 and 2 must be scheduled to be zero.
Random fuel imbalance must not exceed 1000 lbs.
FUEL LIMITATIONS WARNING:
Fuel Crossfeed Valve Fuel Crossfeed valve must be...
Fuel Crossfeed Valve Fuel Crossfeed valve must be closed for takeoff and landing.
FUEL LIMITATIONS WARNING:
Center tank fuel pump switch operations, all aircraft.
(Per A.D. 2001-08-24)
• For ground operation, center tank fuel pump switches must not be positioned to ON unless the center tank fuel quantity exceeds 1000 pounds (453 kilograms), except when defueling or transferring fuel.
• Center tank fuel pump switches must not be positioned to ON unless personnel are available on the flight deck to monitor low-pressure lights.
• Center tank fuel pump switches must be positioned to OFF when both center tank fuel pump low-pressure lights illuminate. The intentional dry running of a center tank fuel pump (low pressure light illuminated) is prohibited.
• Once the center tank fuel pump switches are turned on, they do not need to be turned off once the fuel quantity depletes to less than 1000 lbs.
FUEL LIMITATIONS WARNING:
Center tank fuel pump switches.
Per AD 2002-19-52, AD 2002-24-51, and AD 2011-18-03 with AMOCs 140S-02-376 & 140S-03-189:
[7,8,9]
NORMAL PROCEDURES
General The limitations contained in this AD supersede any conflicting basic Aircraft Flight Manual limitations.
The center tank fuel quantity indication system must be operative to dispatch with fuel in the center fuel tank.
The center tank fuel pump switch(s) must be turned OFF at the first indication of fuel pump low pressure any time during flight. This includes LOW PRESSURE indications that may occur as a result of pitch attitude changes.
Note: One pump operation is required to produce flight deck alerting when a single low pressure light illuminates.
Right pump operation assumes:
1) All fuel in center tank is depleted prior to Top Of Descent.
2) Pump stager on some of the older aircraft will produce more available fuel from the right pump due to deck angle while in climb and cruise.
3) If fuel remains in center tank during descent or with an inoperative right pump, it is permissible to utilize the left pump instead of right pump due to deck angle.
Takeoff - If center tank fuel is less than 5000 lbs, both center tank fuel pump switches must be OFF for takeoff.
Initial Climb - If center tank fuel is less than 5000 lbs, and the pitch attitude has been reduced to begin acceleration to a climb speed of 250 Knots or greater, turn right center tank fuel pump switch ON and open fuel crossfeed valve to minimize fuel imbalance. When Master Caution, FUEL system annunciator and fuel pump low pressure illuminate, turn right center tank fuel pump switch OFF without delay and close fuel crossfeed valve. Fuel crossfeed valve must be closed for takeoff and landing.
Climb, Cruise, and Descent - If center tank fuel is more than 5000 lbs, prior to fuel quantity decreasing to approximately 5000 lbs, turn left center tank fuel pump switch OFF and open fuel crossfeed valve to minimize fuel imbalance. When Master Caution, FUEL system annunciator and fuel pump low pressure illuminate, turn right center tank fuel pump switch OFF without delay and close fuel crossfeed valve. Fuel crossfeed valve must be closed for takeoff and landing.
FUEL LIMITATIONS WARNING:
Center tank fuel pump switches
Per AD 2002-19-52, AD 2002-24-51, and AD 2011-18-03 with AMOCs 140S-02-376 & 140S-03-189:
NON-NORMAL PROCEDURES CONFIG Indication The CONFIG indicator will annunciate when center tank fuel exceeds 1,600 lbs. and the center tank fuel pump switches are OFF. Do not accomplish the CONFIG non-normal procedure prior to or during takeoff with less than 5,000 lbs. of center tank fuel or during descent and landing with less than 3,000 lbs. of center tank fuel. Fuel LOW Indication In a low fuel situation, both center tank pumps may be selected ON and all center tank fuel may be used regardless of the amount of fuel remaining in the tank. Pump Failure If one center tank fuel pump fails with fuel in the center tank, turn the failed pump switch OFF. Turn the operational pump ON, if previously OFF. Open the fuel crossfeed valve to prevent a fuel imbalance. Turn the remaining center tank fuel pump switch OFF when the Master Caution and FUEL system annunciator lights illuminate and close the fuel crossfeed valve. Fuel crossfeed valve must be closed for takeoff and landing.
FUEL LIMITATIONS WARNING:
Center tank fuel pump switches Per AD 2002-19-52, AD 2002-24-51, and AD 2011-18-03 with AMOCs 140S-02-376 & 140S-03-189:
ADDITIONAL INFORMATION Fuel Loading If the main tanks are not full, the zero fuel gross weight of the aircraft plus the weight of center tank fuel may exceed the maximum zero fuel gross weight by up to 5,000 lbs. for takeoff, climb, and cruise and up to 3,000 lbs. for descent and landing, provided that the effects of balance (CG) have been considered. There may be situations where dispatch will issue instructions on line 9 of the ACCULOAD for the flight crew to reduce ZFW in FMC for CG purposes. If the aircraft fuel quantity in the center tank is between 001 and 999 lbs and the main fuel tanks are not full, the load planner will not make any adjustments to ACCULOAD. When the aircraft fuel quantity in the center tank indicates 1000 lbs or more and the main fuel tanks are not full, Dispatch must be notified.
FUEL LIMITATIONS WARNING:
Defueling and Fuel Transfer Prior to transferring fuel or defueling
conduct a lamp test of the respective fuel pump LOW PRESSURE lights. When transferring fuel or defueling from either the center or main wing tanks, monitor the fuel pump LOW PRESSURE lights and turn the fuel pumps OFF at the first indication of fuel pump low pressure. Fuel may be transferred from tank to tank or the aircraft may be defueled with passengers on board, provided the fuel quantity in the tank from which fuel is being taken is maintained at not less than 2000 lbs. Deplane all passengers and non-essential crew when defueling or transferring fuel from a tank that has a fuel quantity less than 2000 lbs. Wait until the process has been completed and the respective fuel pumps turned OFF before reloading non-essential crew and passengers.
FUEL LIMITATIONS WARNING:
(ETOPS)
Perform an operational check of the fuel crossfeed valve during the last hour of cruise flight during each extended range operation. Enter valve failure conditions resulting from the operational check in the aircraft logbook.
FUEL PARAMETERS
Center Tank Fuel Usage
• If a center tank LOW PRESSURE light(s) illuminates during takeoff or initial climb, the center tank pump(s) may remain on until the climb attitude is reduced and the light(s) extinguishes or workload allows for the pump(s) to be positioned OFF. When established in a level attitude at cruise, if the center tank contains usable fuel and the center tank switches are OFF, the center tank pump switches should be positioned ON again.
• If the center tank contains more than 1000 lbs., the center tank switches must be turned ON. Verify the LOW PRESSURE lights extinguish and position both switches OFF when both LOW PRESSURE lights illuminate.
• Use center tank fuel to depletion, followed by main wing tank fuel. However, a maximum of 1000 lbs. may be retained in the center tank.
HYDRAULIC POWER PARAMETERS
Electric Hydraulic Pump Operations On Ground Minimum fuel for stationary ground operations of electric hydraulic pumps on ground is...
1,676 lbs. in each wing tank.
Hydraulic Quantity
Maximum Quantity 105%
Minimum Quantity 76%
LANDING GEAR PARAMETERS
Tire Groundspeed
Maximum tire groundspeed
195 knots
LANDING GEAR PARAMETERS
Brake Operation
Do not apply brakes until...
after touchdown.
LANDING GEAR PARAMETERS
Autobrakes
Arming the RTO feature is...
required on all takeoffs, if operable. Position the RTO selector to OFF if the autobrake system is inoperative.
LANDING GEAR PARAMETERS
Brake Wear Brake wear indicators should...
Brake Wear Brake wear indicators should extend beyond the brake flange (with parking brake set).
OXYGEN PARAMETERS
Oxygen Bottle Pressure
The graph below is used to determine proper pilot oxygen bottle pressure for variations of ambient temperature:
Operating Ambient Temperature
Number of Pilots Using Oxygen
C F 2 3 4 -10 14 430 600 770 -5 23 440 610 785 0 32 445 620 800 5 41 455 635 815 10 50 460 645 830 15 59 470 655 840 20 68 480 670 860 25 77 485 680 870 30 86 495 690 885 35 95 505 700 900 40 104 510 715 915 45 113 520 725 930 50 122 530 735 945 Note: Required pressure for 114 ft3 cylinder.
OXYGEN PARAMETERS
Portable Oxygen Bottle
Minimum number of cabin portable oxygen bottles aboard:
At least one for each assigned Flight Attendant (one Flight Attendant for each 50 seats or part thereof).
WARNING SYSTEMS LIMITATIONS
Enhanced Ground Proximity Warning System
• Do not use the terrain display for navigation.
• The uses of terrain awareness alerting and terrain display functions are prohibited within 15 nm and approaching to land at an airport not contained in the EGPWS terrain database.
Note: ALL United Ops Spec Authorized Airports have been verified to be included in the EGPWS terrain database.
• The use of Terrain Awareness and Terrain Display functions are prohibited when the FMC is in IRS only operation.
• For takeoff, the use of Terrain Awareness and Terrain Display functions are prohibited until position verification has been accomplished.
• For ditching, or other off-airport landings, the terrain awareness alerting and terrain display functions should be inhibited by selecting the TERR INHIBIT switch in INHIBIT.
WARNING SYSTEMS LIMITATIONS
Cabin Altitude Warning Takeoff Briefing (Ref. AD 2008-23-07 & 2011-03-14):
• With the CABIN ALTITUDE and TAKEOFF CONFIG lights not installed, or installed but not activated: As part of the Pilot Briefing before engine start for the first flight of the day or following any change of either flight crew member, the pilot-in-command will ensure the Cabin Altitude Warning indications and procedures are briefed in accordance with the procedures contained in the Normal Procedures section of this manual.