04_LIMITATIONS_747_400_V10

SPECIFICATIONS AND LIMITATIONS 4 - 1

PMDG 747-400 AOM DO NOT DUPLICATE Revision – 26JUL05

PERFORMANCE REQUIREMENTS AND LIMITATIONS

TABLE OF CONTENTS

SUBJECT PAGEAVIONICS ..................................................................................................................................3

AUTOLAND - MAXIMUM WIND COMPONENT.......................................................................3AUTOPILOT - MINIMUM ALTITUDE TO ENGAGE .................................................................3INERTIAL REFERENCE SYSTEM (IRS) .................................................................................3

EMERGENCY EQUIPMENT.......................................................................................................4

EMERGENCY ESCAPE SLIDES - DOOR MOUNTED ............................................................4OXYGEN PRESSURE - CORRECT RANGE...........................................................................4OXYGEN PRESSURE READING ADJUSTMENTS: ................................................................4

ENGINES....................................................................................................................................4

EICAS ENGINE INSTRUMENT SETTING INDICATORS ........................................................4EGT AND THRUST MAXIMUM ...............................................................................................4ENGINE INDICATING AND CREW ALERTING SYSTEM (EICAS) .........................................4CONTINUOUS ENGINE IGNITION .........................................................................................4OIL PRESSURE......................................................................................................................5OIL QUANTITY .......................................................................................................................5OIL TEMPERATURE...............................................................................................................5REVERSE THRUST................................................................................................................5RPM - MAXIMUM ALLOWABLE..............................................................................................5STARTER ENGAGEMENT LIMITATIONS ..............................................................................5

FIRE PROTECTION ...................................................................................................................5

CARGO FIRE PROTECTION ENVELOPE ..............................................................................5

FUEL ..........................................................................................................................................6

FUEL CAPACITY ....................................................................................................................6FUEL IMBALANCE - MAXIMUM LIMITS .................................................................................6FUEL JETTISON.....................................................................................................................6FUEL LOADING ......................................................................................................................6FUEL TEMPERATURE ...........................................................................................................6FUEL USAGE..........................................................................................................................7LANDING FUEL - MINIMUM ALLOWABLE .............................................................................7

4 - 2 SPECIFICATIONS AND LIMITATIONS

Revision – 26JUL05 DO NOT DUPLICATE PMDG 747-400 AOM

HYDRAULICS.............................................................................................................................8

AUTO-BRAKE SYSTEM..........................................................................................................8FLAPS/SLATS EXTENSION ALTITUDE - MAXIMUM..............................................................8HYDRAULIC QUANTITY - MINIMUM......................................................................................8INFLIGHT SPOILERS .............................................................................................................8TIRE PRESSURE....................................................................................................................8TIRE PRESSURE ADJUSTMENTS.........................................................................................8

ICE AND RAIN............................................................................................................................8

ANTI ICE SYSTEMS ...............................................................................................................8ENGINE ANTI-ICE ..................................................................................................................8KNOWN ICING CONDITIONS .............................................................................................. 10RAIN REPELLENT ................................................................................................................ 10APU STARTER LIMITATIONS .............................................................................................. 10

PNEUMATICS ..........................................................................................................................10

AVIONICS/EQUIPMENT COOLING (GROUND OPERATIONS) ........................................... 10PRESSURIZATION - CABIN DIFFERENTIAL LIMITS........................................................... 11

AUTOLAND / INSTRUMENT LANDING SYSTEM ...................................................................11

AUTOLAND/INSTRUMENT LANDING SYSTEM................................................................... 11AUTOLAND - FLAP SETTING LIMITS .................................................................................. 11AUTOLAND - APPROACH GLIDESLOPE SLOPE LIMITS.................................................... 11

SPEEDS ...................................................................................................................................12

MAXIMUM TURBULENT AIR PENETRATION SPEED ......................................................... 12STALL SPEEDS.................................................................................................................... 14STRUCTURAL WEIGHTS..................................................................................................... 14

GENERAL LIMITATIONS.........................................................................................................14

CERTIFICATION STATUS .................................................................................................... 14FLIGHT CREW REQUIREMENTS ........................................................................................ 14FLIGHT LOAD ACCELERATION LIMITATIONS.................................................................... 14PRESSURE ALTITUDE - MAXIMUM..................................................................................... 14RUNWAY SLOPE LIMITATIONS .......................................................................................... 14

MINIMUM TURNING RADIUS ..................................................................................................15

MINIMUM TURNING RADIUS: .............................................................................................. 15



PERFORMANCE REQUIREMENTS AND LIMITATIONS

OVERVIEW: The following list of items have been accumulated from the aircraft manufacturer’sknown limitations and requirements for operating the 747-400 aircraft, as well as from industryoperators of the 747-400 and regulatory bodies responsible for the safe operation civil aircraft.This body of knowledge is brought together in this section in order to condense the variousaircraft requirements and performance limitations to a single reference for crew use.

The following list of items is not considered to be conclusive of all operating conditions, andcrews should use sound judgment and Standard Operating Principles to ensure the safeoperation of the aircraft.

The following list is organized alphabetically by major subject matter.

AVIONICS

Autoland - Maximum Wind ComponentMaximum Wind Component Wind Speed

True Headwind Component 25 KnotsTrue Tailwind Component 10 KnotsMaximum Crosswind Component 25 KnotsMaximum One Engine-Out Crosswind 5 KnotsMaximum CAT III Autoland Crosswind 10 Knots

Autopilot - Minimum Altitude to EngageAfter Takeoff Autopilot Engagement 250ft [76 meters] AGL or greaterNon-Precision Approach No Lower Than 360ft [110 meters] AGLILS Approach, Single Autopilot Okay down to 50ft [15 meters] below DH/MDA,

but not less than 50ft [15 meters] AGL.

Inertial Reference System (IRS)• The inertial Reference System is capable of providing magnetic heading and track

information between 73° North Latitude and 60° South Latitude while in NAV mode.• Crews are cautioned against operating in darkness or IFR conditions into airports north of

73° North Latitude or airports south of 60° South Latitude if the airport navigation aids arereferenced to Magnetic North, as this will result in dangerously unreliable navigation data.



EMERGENCY EQUIPMENT

Emergency Escape Slides - Door Mounted• Whenever passengers are carried, all door mounted evacuation slides must be armed and

engaged prior to taxi, and must remain so until the aircraft is being prepared for passengerdeplaning.

Oxygen Pressure - Correct RangeCrew Oxygen System 1,650 psiPassenger Oxygen System 1,600 psiPortable Oxygen Bottles 1,600 psi

Oxygen Pressure Reading Adjustments:• Temperature > 70°F: Add 3 psi per 1°F above 70°F

[Temperature > 21°C: Add 6 psi per 1°C above 21°C]

• Temperature < 70°F: Subtract 3 psi per 1° below 70°F[Temperature <21°C: Subtract 6 psi per 1°C below 21°C]

ENGINES

EICAS Engine Instrument Setting IndicatorsMaximum N1 Engine Operating Limitation REDMaximum Allowable Thrust (Cautionary) AMBERCurrent/Normal Thrust Settings WHITE/GREEN

EGT and Thrust Maximum

Engine Activity Time LimitEICAS Marking

Color EGT (°C)Ground Start 40 Sec Red Bar 870°CTakeoff. G/A 5 min Red Bar 960°CMax. Continuous EGT None Amber Bar 925°CStandard Flight EGT None White/Green 750°C

Engine Indicating and Crew Alerting System (EICAS)• If EICAS displays limit bars which are more conservative than the above book settings,

crews must observe the EICAS limits. EICAS limits are determined based on currentatmospheric and altitude conditions.

• Crews are advised not to blank the engine vibration display during takeoff, as this mayprovide an early indication of engine imbalance and or impending engine failure.

Continuous Engine Ignition• Continuous Ignition should be selected ON during inflight encounters with heavy

precipitation, and during severe turbulence. Continuous Ignition should be ON as a safetyconcern during takeoff and landing if birds are present in the airport vicinity.



Oil PressureMinimum Idle: 10

Other than Idle: 20Oil QuantityMinimum Before Engine Start 22 Quarts

Oil TemperatureEngine Activity Time Limit Temperature (°C)Maximum Continuous None 160°CMaximum Temporary 15 Min 175°CMaximum for Setting Takeoff Thrust N/A 50°C

Reverse ThrustFlight Condition Permissible Use of Reverse ThrustIn Flight ProhibitedOn Landing Rollout while still >80kts Full Reverse until 80kts, then reduce to idle.On Landing Rollout <80kts. Idle only.Power Back from Gate or Parking Prohibited per engine manufacturer.

RPM - Maximum AllowableN1 117.5%N2 112.5%

Starter Engagement LimitationsStarter Engagement Activity Required Cooling TimeStarter Engagement <=5 Minutes Until Engine De-spools to 0 RPM N2Starter Engagement =>5 Minutes Time Equal to Starter ON time (ex 6min=6min)

• Maximum Continuous Starter Engagement Limit: 15 Minutes without cooling.• Maximum Starter Re-Engagement RPM: 20% N2

FIRE PROTECTION

Cargo Fire Protection EnvelopeMaximum Recommended Flight Time fromSuitable Airport to ensure Cargo Fireprotection.

180 Min



FUEL

Fuel Capacity Pounds KgsOutboard Wing Tanks (Tanks 1 and 4) (each) 29,100lbs 13,200 kgInboard Wing Tanks (Tanks 2 and 3) (each) 83,800lbs 38,011kgReserve Tanks (Left and Right) (each) 8,800lbs 3,991kgStabilizer Tank 22,900lbs 10,387kgCenter Tank 119,500lbs 54,204kgTOTAL FUEL 386,000lbs 175,087kg

• These are structurally limited fuel quantities which can only be achieved with extremely highdensity fuel.

Fuel Imbalance - Maximum Limits Pounds KgsMaximum Allowable Fuel Weight Difference Between OutboardTanks 1 & 4

3,000lbs 1,361kg

Maximum Allowable Fuel Weight Difference Between InboardTanks 2 & 3

6,000lbs 2,722kg

Maximum Allowable Fuel Weight Difference Between Inboard andOutboard Tanks after Reaching ‘Fuel Tank to Engine’ Condition

6,000lbs 2,722kg

• Fuel Imbalance Warnings may not appear on EICAS until after limit is exceeded.

Fuel Jettison• Do not attempt to Jettison fuel with flaps in transit between 1° and 5°• Ensure fuel jettison is completed prior to selecting flaps to 25° or 30° to ensure proper FMC

calculated landing weights.

Fuel Loading• Load inboard and outboard wing tanks equally or within balance limits• Once outboard wing tanks are full, load inboard wing tanks.• Once all wing tanks are full, load reserve tanks.• After all wing and reserve tanks are full, load center tank.• While initially loading fuel into the center tank, note should be taken of the aircraft balance

and tip limits, with fuel being stored in the stabilizer tank in conjunction with the center tankwhenever balance limits permit.

Fuel TemperatureFuel Type Minimum MaximumJet A -37 +49JP5 -43 +49Jet A-1 -44 +49

• If fuel temperature approaches minimum temperature in flight, crews should consider a flightlevel change to warmer altitudes, or increasing speed to increase TAT.

• After bringing fuel temperature up to, or above minimum temperatures, crews shouldcarefully asses the use of higher, colder altitudes for flight.

• In cases where the fuel temperature indicator is inoperative, the fuel tank temperature shouldbe considered to equal True Air Temperature.



Fuel UsageFuel Tank Condition Required Crew Action FSMC Logic ResultAll Tanks Full Select all Valve and

Pump switches ON.When Flaps Extended:FSMCs close crossfeed valves 2 &3. Override pumps fuel engines 1 &4, main tank pumps fuel engines 2 &3.

When Flaps Retracted:FSMCs open crossfeed valves 2 &3. Override pumps in center tankfuel all engines.

Center Tank <=36,287 Kgs None FSMCs activate transfer fromstabilizer tank to center tank(inhibited on ground). Overridepumps in center tank fuel allengines.

Stabilizer Tank Empty.EICAS message ‘FUEL PUMPSTAB’ is displayed and lowpressure lights are illuminated.

Confirm Tankquantities. Select bothStabilizer pumpswitches OFF.

Override Pumps in center tankprovide fuel to all four engines.

Center tank quantity reaches907 Kgs:EICAS message ‘FUEL OVRDCTR’ is displayed and lowpressure lights illuminate.

Confirm Tankquantities. Select bothCenter pump switchesOFF.

A scavenge pump operatesautomatically to transfer remainingfuel in center tank to main tank 2.(Inhibited on ground.)

FSMCs activate override pumps 2 &3. Main tank 2 fuels engines 1 & 2.Main tank 3 fuels engines 3 & 4.

Main Tank 2 or 3 quantityreaches 18,144 Kgs:

None FSMCs activate transfer fromreserve tanks 2 & 3 to associatedmain tanks.

Main Tank 2 quantity is equalto or less than main tank 1, ormain tank 3 is equal to or lessthan main tank 4:EICAS message ‘FUELTANK/ENG’ is displayed.

Confirm tank quantities.Select override pumpswitches OFF andcrossfeed switches 1 &4 OFF.

Main tank pumps fuel associatedengines until engine shutdown.

Landing Fuel - Minimum AllowableFuel On Board at Touchdown (Ensures adequate boost pump coverage.) 2,000lb 924kgFuel to Execute a Go-Around 4,800lb 2,176kgExpected Fuel Quantity Indicator Error (Max designed indicator error.) 2,450lb 1,100kgMinimum Desired Landing Fuel Total 9,250lb 4,200kg

• Minimum Desired Landing Fuel Total: Ensures a safe quantity of fuel on board at the timethe aircraft crosses the runway threshold. This is a worst case scenario considered withmaximum fuel quantity indicator error. Does not include fuel minimums required by FederalAviation Regulations and sound flight planning.



HYDRAULICS

Auto-Brake System• Use manual braking when anti-skid is inoperative or upon any indication of system fault.

Flaps/Slats Extension Altitude - MaximumMaximum Allowable Extension Altitude 20,000ft [6,100 M]

Hydraulic Quantity - MinimumMinimum Hydraulic Quantity at Dispatch Time 72% of system capacity

Inflight SpoilersVisual Meteorological Conditions Not recommended below 1,000ft [305 M] AGL.Instrument Meteorological Conditions Use not recommended after FAF

Tire PressureNose Gear Tires 195 - 205 psiMain Gear Tires 205 - 215 psi

• Tire mounted pressure indicators are only valid for pressure readings after tires, brakes andwheels have cooled to ambient temperature (allow approximately 1hr after parking for anormal landing, 2hrs after a hard braking condition.)

• Tire pressure requirements are based upon the design structural limit weight of the aircraft.

Tire Pressure Adjustments• Temperature >70°F: Add 1 psi per 3°F above 70°F

[Temperature >21°C: Add 2 psi per 3°C above 21°C]

• Temperature <70°F: Subtract 1 psi per 3°F below 70°F[Temperature <21°C: Subtract 2 psi per 3°C below 21°C]

ICE AND RAIN

Anti Ice Systems• Engine and Wing Anti-Ice systems should not be operated when OAT >10°C during ground

operations, or when TAT >=10°C during flight.

Engine Anti-Ice• Engine anti-ice must be selected ON during all ground and flight operations when icing

conditions exist or are anticipated.• Engine anti-ice does not need to be used during climb and cruise segments when the

temperature is less than -40°C SAT.• Engine anti-ice must be activated prior to, and operated during a descent in icing conditions.

Engine anti-ice should be activated even if the temperature falls below -40°C SAT during thedescent.

• During ground operations lasting more than ten minutes in icing conditions, engine anti-icecapabilities must be reinforced by momentarily selected a thrust setting of 50% N1 for each



engine (separately). Use caution for jet blast and FOD dangers associated with accumulatedice or snow on taxiways and runways.



Known Icing Conditions• Icing conditions are said to exist for taxi, takeoff and landing operations when:Outside Air Temperature 10°C (50°F) or below

and/or:

• Visible moisture of any form is present (clouds, fog, visibility of 1 mile or less, snow, rain,sleet or ice crystals).

• Standing water, snow, slush or ice accumulations are present in a form which may beingested by the engines or freeze to nacelles, blades or sensors.

• Icing conditions are said to exist in flight when:Total Air Temperature 10°C (50°F) or below

and:

• Visible moisture of any form is present (clouds, fog, visibility of 1 mile or less, snow, rain,sleet or ice crystals).

Rain Repellent• Do not apply repellent to a dry windshield. If repellent is inadvertently discharged onto

window, do not activate windshield wipers. Allow repellent to disperse in the aircraftslipstream.

• Apply repellent only in rain or snow conditions which restrict forward visibility through thecockpit windscreen.

• Crews are required to make appropriate logbook entries if rain repellent is used in flight.

APU Starter LimitationsTime off between APU start attempts 1 Minute

PNEUMATICS

Airplane altitude vs. Cabin Altitude

Avionics/Equipment Cooling (Ground Operations)OAT °F (°C) Cooling Required94 to 105°F[34° to 41°C]

At least one air conditioning pack or equivalentground cooling equipment operating, or at leastone forward and one aft entry doors open onopposite sides of the aircraft.

106 to 120°F[41° to 49°C]

At least on air conditioning pack or equivalentground cooling equipment operating.

Greater than 120°F [49°C]

Two air conditioning packs or equivalentground cooling equipment operating.



Pressurization - Cabin Differential LimitsTakeoff and Landing 0.11 psiMax Differential – Operating 9.4 psiMax Differential - During Climb 9.4 psi

AUTOLAND / INSTRUMENT LANDING SYSTEM

Autoland/Instrument Landing System

EquipmentCAT IIIbAutolandLand 3

CAT IIIaAutolandLand 3

CAT IIAutolandLand 2

CAT I

Autopilots 3 CMD 3 CMD 2 CMD1 Flight

Director or1 Autopilot

Electronic ADIs 2 2 2 1 for PilotFlying

ILS Deviation Indicator 2 2 2 1Radar Altitude Readout with DH 2 2 2 Not RequiredAFDS Mode annunciation 2 2 2 Not RequiredMissed Approach AttitudeGuidance

Required Required Not Required Not Required

Autoland Status Annunciators 2 2 1 for PilotFlying

Not Required

IRUs (in NAV mode) 3 3 2 Not RequiredAutothrottle 1 1 Not Required Not RequiredAC Electric Power Source 2 2 2 Not RequiredHydraulic Systems 3 3 3 2Rollout Guidance Required Not Required Not Required Not RequiredAutobrakes Required Not Required Not Required Not RequiredWindshield Wipers 2 2 2 Not RequiredMarker Beacons* 1 1 1 Not RequiredReversers 2 Not Required Not Required Not RequiredOperative Engines 3 3 2 1Antiskid Required** Not Required Not Required Not Required

*If approach to be flown requires Marker beacon use to determine DH or AH** If RVR is below 600ft [180 Meters.]

Autoland - Flap Setting Limits• Autoland is only approved for settings of flap 25 or flap 30.

Autoland - Approach Glideslope Slope LimitsMinimum Glideslope Angle 2.50°Maximum Glideslope Angle 3.25°



SPEEDS

VA - Design Maneuvering Speed (KIAS/ Mach)Sea Lvl 10,000ft

[3000M]20,000ft[6000M]

29,000ft[9000M]

30,000ft[9000M]

34,000ft[10000M]

36,000ft[11000M]

40,000ft[12000M]

300 315 330 336/.86 - - - -

VFE - Flaps Extension Speeds - Maximum (KIAS)Flaps 1 Flaps 5 Flaps 10 Flaps 20 Flaps 25 Flaps 30

280 260 240 230 205 180

VLO / VLE - Landing Gear Limit Speeds - Maximum (KIAS / Mach)VLO - Retraction 270 KIAS / .82M

VLO - Extension 270 KIAS / .82MVLE - Extended 320 KIAS /.82M

Maximum Tire Limit Speed 204 Knots Ground Speed

VMO / MMO - Maximum Operating Limit Speeds (KIAS / Mach)20,000ft & Lower[6000M & Lower]

25,000ft[7600 M]

30,000ft[9200 M]

35,000ft[10,700 M]

40,000ft[12,200 M]

365 365/.880 340/.900 309/.900 269/.900

• VMO / MMO - Shall not be exceeded during any phase of flight.

VMCG

- Minimum Controllable Ground Speed (Same as Minimum Allowable V1 Setting)

Pres. Alt. <50F<10C

60F15C

70F21C

80F27C

90F32C

100F38C

110F43C

120F43C

130F54C

13000ft [4000 M] 106 104 101 97 -- -- -- -- --10000ft [3000 M] 108 107 104 100 98 -- -- -- --8000ft [2400 M] 110 108 107 105 100 96 -- -- --6000ft [1800 M] 113 113 112 108 105 102 97 -- --4000ft [1200 M] 117 116 116 115 110 106 102 -- --2000ft [600 M] 118 117 117 117 113 110 106 100 --S.L. 119 118 118 118 117 115 112 106 100

Maximum Turbulent Air Penetration Speed15,000ft [4600 meters] and higher altitude 290 KIAS / .780M



15,000ft [4600 meters] and lower altitude 250 KIAS



Stall SpeedsFlapPOS

GearPOS 213 231 250 268 286 304 322 340 358 376 394

0 UP 152 159 166 172 178 184 189 196 202 208 2141 UP 136 140 147 152 157 162 167 172 177 183 1895 UP 129 132 137 143 147 152 157 163 167 176 180

10 UP 124 130 134 139 143 149 153 159 163 167 17220 UP 121 126 129 134 138 143 148 152 156 163 16625 DN 116 120 125 129 134 138 142 146 152 156 16030 DN 112 116 120 123 128 132 136 140 146 150 152

• ISA Conditions

Structural Weights Pounds KgsMaximum Taxi 877,000lb 397,800kgMaximum Takeoff 875,000lb 396,893kgMaximum In-flight Landing 650,000lb 294,835kgMaximum Landing 630,000lb 285,763kgMaximum Zero Fuel 535,000lb 242,671kg

GENERAL LIMITATIONS

Certification StatusThe 747-400 is certified under the 747 Type Certificate, in the Transport Category, US FARParts 25 and 36.

Flight Crew RequirementsMinimum Captain and First Officer

Flight Load Acceleration LimitationsFlaps Up +2.5 g to -1.0 gFlaps Down +2.0 g to 0.0 g

Pressure Altitude - MaximumTakeoff and Landing 8,400ft [2,560 Meters]Operating 42,000ft [12,800 Meters]

Runway Slope LimitationsMaximum +/- 2%



MINIMUM TURNING RADIUS

Minimum Turning Radius: 47 Meters for 180º TurnConducted using a slow continuous turn with functional body gear steering. No differentialbraking during turn. Nose and Tail will turn within arc traced by wing tip.

04_LIMITATIONS_747_400_V10

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