Rotate MD-11 Manual. Limitations
LIMITATIONS
INDEX:
WEIGHT AND BALANCE
CENTER GEAR
MINIMUM FLIGHT WEIGHT
CENTER OF GRAVITY
SPEED LIMITATIONS
TAXI SPEEDS
MAXIMUM DESIGN MANEUVERING SPEED - VA
MAXIMUM OPERATING LIMIT SPEED - VMO
FUEL DUMP
STRUCTURAL LIMIT SPEEDS
FLIGHT ENVELOPE
TEMPERATURE LIMITS
OPERATIONAL ALTITUDES
ACCELERATION LIMITS
WIND LIMITATIONS
SYSTEM LIMITATIONS
ENGINE EGT
REVERSE THRUST
FUEL SYSTEM
FUEL MANAGEMENT
BALLAST FUEL
HYDRAULIC
AIR
UNPRESSURIZED FLIGHT
ICE AND RAIN
ICING CONDITIONS
WINDSHIELD DEFOG
WINDSHIELD WIPERS
AUTOFLIGHT
FLIGHT MANAGEMENT SYSTEM
AUTOPILOT/FLIGHT DIRECTOR SYSTEM
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Rotate MD-11 Manual. Limitations
WEIGHT AND BALANCE
Maximum Weight (lbs.) with All Gear Extended
AIRCRAFT
MD-11(630.5
AIRCRAFT)1
TAXI
START OF
TAKEOFF
IN-FLIGHT (LANDING
FLAPS)
LANDING
ZERO
FUEL
633,00
0
630,500
484,500
481,500
451,300
CENTER GEAR
These aircraft are normally operated with the center gear extended for takeoff and landing. Special performance data
and weight limitations are required for operation with the center gear retracted.
Maximum Weight (lbs.) with Center Gear Retracted
TAXI
START OF
TAKEOFF
IN-FLIGHT (LANDING
FLAPS)
LANDING
ZERO FUEL
448,000
445,000
403,000
400,000
370,000
MINIMUM FLIGHT WEIGHT
Minimum Flight Weight
MINIMUM FLIGHT WEIGHT
257,000
CENTER OF GRAVITY
(MD-11 Center of Gravity Limits (Wt. vs. CG) (Gross weight in 1,000 lbs.)
WEIGHT
242
260
273 451.3 467 469 473 560 608.5 612.5
LIMITS
618
625.5
630.5
FWD -%
MAC
12.0
12.0
12.0 12.0
12.2
12.5 12.3
12.3
12.3
12.3
15.0
16.1
18.1
AFT -%
MAC
31.5
31.1
34.0
34.0
34.0 34.0
34.0
29.7
28.8
27.3
25.5
26.8
34.0
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Rotate MD-11 Manual. Limitations
SPEED LIMITATIONS
Tire Speeds
CONDITION
LIMIT
MD-11
204 Kts
TAXI SPEEDS
The following maximum taxi and turn speeds should be monitored on the PFD.
Maximum Taxi Speeds (All)
Type of Turn
Maximum Speed
Turns of 90°
10 Kts
Turns of 45°
15 Kts
High Speed Turnoff
20 Kts
Straight ahead, greater than or equal to 400,000 lbs
20 Kts
Straight ahead, less than 400,000 lbs
25 Kts
MAXIMUM DESIGN MANEUVERING SPEED - VA
Maximum Design Maneuvering Speed - VA
(Table 1 of 2)
Altitude
MD-11
SL
316
2000
4000
5000
6000
8000
320
326
330
333
336
10000
15000
20000
22000
337
337
330
327
Confine full application of rudder or aileron controls, as well as maneuvers that involve angles of attack near stall,
to speeds below the design maneuvering speed VA.
Maximum Design Maneuvering Speed - VA
(Table 2 of 2)
Altitude
24000
25000
25700
30000
33000
33700
35000
40000
42000
43200
MD-11
329
331
333
308
295
293
284
252
240
234
Confine full application of rudder or aileron controls, as well as maneuvers that involve angles of attack near stall,
to speeds below the design maneuvering speed VA.
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Rotate MD-11 Manual. Limitations
MAXIMUM OPERATING LIMIT SPEED - VMO
The maximum operating speed VMO/MMO may not be deliberately exceeded in any regime of flight (climb, cruise, or
descent.)
VLO landing gear retraction and VLO landing gear extension are the maximum speeds for which retraction and
extension of the aircraft landing gear can be safely flown.
The landing gear extended speed, VLE, is the maximum speed at which the aircraft can be safely flown with the gear
extended.
NOTE
For the following two tables, the transition between the two speed ranges begins when the tip tank fuel is below 90%
and decreases linearly until the tip tanks are 60% full.
VMO, Wing Tip Fuel Tanks 90% Full or More (MD-11)
Altitude
SL
5000
10000
25700
30000
35000
40000
43200
MD-11
350
357
365
365
334
299
266
248
MMO = 0.87 Mach
VMO/MMO, Wing Tip Fuel Tanks 60% Full or Less (MD-11)
AIRCRAFT
SEA LEVEL TO 30,704
ABOVE 30,704
VMO = 320 KIAS
MMO = 0.85 Mach
MD-11
FUEL DUMP
Maximum Fuel Dump Speed
BELOW 28,000 FT
ABOVE 28,000 FT
325 KIAS
0.82 Mach
STRUCTURAL LIMIT SPEEDS
Maximum Slat Operating Speed (KIAS/MACH)
Slats Extended (Takeoff)1
Slats Extended (Land)1
Autoslat Extended
280/.55
280/.55
280/.55
1. “Takeoff” means flaps less than 35°. “Land” means flaps 35° or more.
MD-11 Maximum Flap Operating Speed - VFE (KIAS/MACH)
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Rotate MD-11 Manual. Limitations
Flap Position
MD-11
*Gear Retracted
0 TO 15.0
15.1 TO 20.0
20.1 TO 25
255/.51
240/.51
220/.51
28
35
50
35*
50*
210/.51 190/.51 175/.51 187/.51 158/.51
Landing Gear Limit Speed (KIAS/MACH)
Landing Gear
Retraction (VLO)
Landing Gear
Extension (VLO)
230/.70
Landing Gear
Extended (VLE)
260/.70
Alt Landing
Gear Extended
Alt Landing
Gear Extension
260/.70
230/.70
300/.70
FLIGHT ENVELOPE
TEMPERATURE LIMITS
MD-11 Operational Temperature Limits
TAKEOFF & LANDING
EN ROUTE
ALTITUDE (FT.)
TEMPERATURE
ALTITUDE (FT.)
TEMPERATURE
-2000 TO 2500
-52.5° C to 50° C
Sea Level
-54° C to 50° C
-54° C to 35° C
43,200
-82° C to -36° C
10,000
Temperature limits vary linearly between altitudes shown.
OPERATIONAL ALTITUDES
Operational (Altitudes are pressure altitudes)
Maximum Altitudes and Slope
MAX OPERATING
ALTITUDE (FT.)
43,200
MAXIMUM T/O
ALTITUDE (FT.)
10,000
MAX SLOPE T/O /
LNDG
±2%
ACCELERATION LIMITS
Flight Maneuvering Load Acceleration Limits
FLAPS UP/SLATS
RETRACTED
+2.5g to -1.0g
FLAPS AND SLATS
EXTENDED
+2.0g to 0.0g
FLAPS OR SLATS
EXTENDED
+2.0g to 0.0g
The positive maneuvering limit load factors limit the angle of bank in turns and the severity of pull-up maneuvers.
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Rotate MD-11 Manual. Limitations
WIND LIMITATIONS
WIND LIMITS (knots)
CONDITIONS
WIND LIMIT
Max Rolling TKO/LND Xwind
31 Knots
Max Static TKO Xwind
23
Max TKO/LND Tailwind
10
Max TKO/LND Crosswind with Rwy Braking Action Poor
10
Autoland Crosswind
15
Autoland Headwind
25
CAT II/III Crosswind
10
SYSTEM LIMITATIONS
ENGINE EGT
EGT Limits
AIRCRAFT
MD-11GE
STARTING
EGT
TIME
LIMIT
LIMIT
7501,2
None
TAKEOFF
EGT
TIME
LIMIT
LIMIT
9602
5 Minutes
MAX CONTINUOUS
EGT
TIME
LIMIT
LIMIT
9254
None
ACCELERATION
EGT
TIME
LIMIT
LIMIT
9602
None
750-87
40 Sec
03
onds
All temperatures listed in the table are degrees Centigrade
Engine RPM
AIRCRAFT
MAXIMUM N1
MAXIMUM N2
MD-11GE
117.5
112.5
Oil System
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Rotate MD-11 Manual. Limitations
AIRCRAFT
MAX
CONTINUOUS
OPERATION
HIGH CAUTION
RANGE AND
TIME LIMIT
MD-11GE
160° C
160° C-175° C
for 15 Minutes
LOW OIL
PRESSURE
CAUTION
BAND
10-34 psid
MIN. OIL
PRESSURE
9.5 psid
MIN. OIL
TEMPERATURE
FOR TAKEOFF
n/a
REVERSE THRUST
Use of reverse thrust is prohibited in flight. Do not use reverse thrust to back the aircraft.
ENGINE IGNITION
Use Ignition OVRD for heavy rain or moderate/severe turbulence.
Ignition OVRD may be used at any time at the discretion of the Captain.
The OVRD position has no time limit, although excessive use will reduce service life.
Select engine ignition OVRD ON whenever conditions call for use of the engine or engine and airframe anti-ice.
Maintain OVRD ON for the duration of the icing conditions.
FUEL SYSTEM
Usable Fuel (@6.7 Lbs/Gal)
Tank 1
Tank 2
Tank 3
Upper Aux
Tank
40,700
65,400
40,700
87,100
Lower Aux
Tank
11,000
Tail Tank
Total
13,400
258,300
Allowable Fuel Temperature Range at Takeoff
Minimum Temp
Maximum Temp
-40°F (-40°C)
+122°F (+50°C)
FUEL MANAGEMENT
MD-11 Fuel will be transferred from the Upper Aux tank to each Main tank, keeping them full. Simultaneously, fuel
will be transferred from the Lower Aux tank, keeping the Upper Aux tank full until the Lower Aux tank is empty.
When the Upper Aux tank is empty, fuel will be transferred from Tank 2 to 1 and 3 until all three Main tanks are
equal. Fuel is then used equally from each tank. The fuel quantity in the Tail tank is controlled automatically by the
fuel system controller (FSC).
Lower Aux tank and Tail tank transfer pumps must be OFF for takeoff and landing.
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Rotate MD-11 Manual. Limitations
With an operative fuel quantity indication system, fuel remaining in the fuel tanks when the quantity indication
reaches ZERO is not usable in flight.
The maximum lateral fuel imbalance is 2,500 lbs.
When operating aircraft at a MTOGW of 630,500 lbs on the ground with a total of 9,000 lbs or more of fuel in the
Aux and Tail tanks, manage the fuel system to maintain a ratio of approximately 7.5 to 1 between the Aux tank
quantity and Tail tank quantity.
BALLAST FUEL
All ballast fuel must be entered in the FMS FUEL INIT. Refer to Supplemental Procedures Chapter 4.
Ballast fuel may not be loaded in more than one tank at the same time.
Ballast fuel must remain in the appropriate tank.
The Tail tank can not contain both ballast and usable fuel. It must be either all ballast or all usable.
HYDRAULIC
Hydraulic Quantity
SYSTEM 3 MINIMUM HYDRAULIC QUANTITY FOR
DISPATCH
6 Gallons
AIR
UNPRESSURIZED FLIGHT
For unpressurized flight the cabin pressure control must be in MANUAL and the outflow valve between 1/ 2 to
2/3 open.
Cabin Air Differential and Relief Pressure Limitations
MAX RELIEF VALVE
DIFFERENTIAL
PRESSURE
MAX
DIFFERENTIAL PRESSURE
DURING
TAKEOFF AND LANDING
9.1 PSI
.5 Psi
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Rotate MD-11 Manual. Limitations
ICE AND RAIN
ICING CONDITIONS
Icing conditions exist when the outside air temperature (OAT) on the ground and for takeoff, or total air
temperature (TAT) in-flight, is 6° C or below, and visible moisture in any form is present.
ENGINE ANTI-ICE, WING ANTI-ICE, and TAIL ANTI-ICE must be ON when any of the following are true:
• An “ICE DETECTED” alert is displayed from the ice detecting system. (MD-11)
• When icing conditions are expected or encountered.
WINDSHIELD DEFOG
Windshield defogging should be operated for all flight conditions.
WINDSHIELD WIPERS
Do NOT operate the windshield wipers at high speed for more than 30 minutes or on a dry windshield
AUTOFLIGHT
FLIGHT MANAGEMENT SYSTEM
Before takeoff, any changes which affect V speeds require the V speeds to be recomputed and re-entered.
The accuracy of the FMS performance predictions have not been demonstrated, therefore (for dispatch
purposes only), aircraft range calculations, fuel management, and engine out terrain clearance must not be
predicated on FMS information.
For ILS and IGS approaches, with an inoperative glideslope, FMS PROF mode and its Vertical Deviation
Indicator must not be used for descent after the Final Approach Fix (FAF).
FMS PROF mode must not be used in descent/approach below the Minimum Descent Altitude/Height
(MDA/H) or Decision Altitude/Height (DA/H).
• Basic autoflight modes (e.g., LVL, CHG, V/S, or FPA) are used to recapture the path when the PROF mode is
engaged and the airplane is:
- Above or below the path and the FMA indicates PITCH [XXX] IDLE, or
- Below the path and the FMA indicates THRUST [XXX] V/S.
Do not enter more than 100 waypoints into the FMS ACT F-PLAN.
The FMS amber VMIN foot must not be used for setting an approach or landing target speeds if the aircraft has
not transitioned through the acceleration altitude as defined on the FMS TAKEOFF page under the title ACCEL.
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Rotate MD-11 Manual. Limitations
If the pilot modifies the FMS NAV DataBase Approaches, the modified approach must comply with the
approved published procedures.
AUTOPILOT/FLIGHT DIRECTOR SYSTEM
For nonprecision approaches, the autopilot must be disengaged no lower than the applicable minimums
minus 50 feet.
Do not exceed 200 KIAS with Single Land or Dual Land modes of the autopilot engaged.
AUTOMATIC LANDINGS
The minimum threshold crossing height is 47 feet.
Three hydraulic systems must be operative for dual land operations.
Automatic Landings
The maximum altitude for AutoLand (SINGLE LAND or DUAL LAND) is 8,000' msl.
SINGLE LAND AutoLands allow hydraulic system #1 or #2 to be inoperative.
DUAL LAND AutoLands require 3 operating hydraulic systems. Hydraulic systems may operate via auxiliary or
reversible motor pumps.
MD-11 automatic landings are prohibited at weights greater than 481,500 lb.
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