Limitations - Boeing

Boeing The Boeing philosophy governing the content of the Operations Manual Limitations Section is a function of EICAS messages and cockpit placards. Any item that generates an EICAS message or is a limitation that is covered by a cockpit placard is not listed in the limitations section. The Operations Manual Limitations Section content, in general, is restricted to those items the crew must commit to memory in order to safely and efficiently operate the airplane.

Operational Limitations

    • Runway Slope ±2%
       • Maximum Operating Altitude 42,000 ft pressure altitude
  • Maximum Take-Off and Landing Altitude

8,400 ft pressure altitude

HI ALT OPS
9,500 / 13,500 ft pressure altitude

  • Maximum Take-Off and Landing Tailwind Component

15 kts

10 kts

Miscellaneous Limitations

Emergency Lighting

Photo luminescent Floor Emergency Lighting must be charged in accordance with approved procedures.

ACARS

ACARS is limited to the transmission and receipt of messages which 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, 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.

Air Conditioning

When the airplane is electrically powered for more than 20 minutes on the ground, equipment cooling must be provided as shown below:

Temperature (OAT) COOLING REQUIRED
34° C to 40° C
(94° F to 105° F)
One forward and one aft entry door on opposite sides open, or at least one Air Conditioning pack or equivalent ground cooling operating.
41° C to 49° C
(106° F to 120° F)
At least one Air Conditioning pack or equivalent ground cooling operating.
More than 49° C
(120° F)
Two Air Conditioning packs or equivalent ground cooling operating.

APU

Auto Flight

Headwind 25 kts
Crosswind 25 kts
Tailwind

15 kts

10 kts

Autoflight - General Limitations

Automatic Landing

DH Below 200 Feet but not less than 100 feet

DH Below 100 Feet but not less than 50 feet

DH 50 Feet or Less

Autothrottle

Bird Strike Protection

Communications

Crosswind Limitation

Door Mounted Escape Slides

Engine Fuel System

Engine Ignition

Time Limits for TO/GA Thrust for Take-Off

The time limits on the use of TO/GA thrust following loss of thrust on one engine or engine failure are as follows:

Engine Vibration

Fire Protection

Flight Controls

Flight Deck Security Door

Cockpit Door Surveillance System (CDSS)

Icing Conditions

ILS Approaches

The airplane is approved only for the following kinds of ILS approach and landing:

Decision height 200 feet or more:

Decision height below 200 feet but not less than 100 feet:

Decision height below 100 feet but not less than 50 feet:

Decision height 50 feet or less:

No decision height:

Flight Instruments

Electronic Flight Bag (EFB)

  • Do not use the Airport Map display as primary navigation reference.
  • The EFB portable keyboard and attaching cable, if installed must be stowed during takeoff and landing.

Navigation

Precipitation on the Runway

The maximum precipitation depth allowable on the runway for Takeoff:

Reduced Vertical Separation Minimum (RVSM) Altimeter Cross Check Limits

Field
Elevation
IAS/
Mach
Max Difference
Between Captain's and First Officer's Altimeters
Max Difference
Between Captain's or First Officer's Altimeters and Field Elevation
Sea Level 0 40 ft 75 ft
5,000 feet 0 45 ft 75 ft
10,000 feet 0 50 ft 75 ft

Max Difference between Captain's and
First Officer's Altimeters - Inflight
200 ft

Reverse Thrust

Turbulent Air Penetration Speed

Warning Systems

Ground Proximity Warning System (GPWS) Look-Ahead Alerting

Do not use the terrain display for navigation.

The use of look-ahead terrain alerting and terrain display functions is prohibited within 15 nm of takeoff, approach or landing at an airport or runway not contained in the GPWS terrain database. Refer to Honeywell Document 060-4267-000 for airports and runways contained in the installed GPWS terrain database.

Look-ahead Terrain alerting and terrain display functions must be inhibited by selecting the Ground Proximity Terrain Override switch to OVRD if:

  • operating outside United States National Airspace and the FMS database and charts are not referenced to the WGS-84 reference datum, unless the FMS has been found to be suitable for navigation in that airspace
  • the FMS is operating in IRS NAV ONLY
  • prior to takeoff, FMS position updating is not accomplished or actual runway position is not verified by ensuring, with the 5 or 10 nm range selected on the EFIS control panel, the airplane symbol is displayed at the appropriate point on the runway symbol.

The use of look-ahead terrain alerting and terrain display functions is prohibited during QFE operations.

Weather Radar

Weight Restrictions

Limitations 757-200
(Light)
757-200
(Heavy)
757-300
Maximum Taxi Weight (MTW) 100,243 kg
(221,000 lbs)
116,119 kg
(256,000 lbs)
118,387 kg
(261,000 lbs)
Maximum Take Off Weight (MTOW) 99,790 kg
(220,000 lbs)
115,893 kg
(255,500 lbs)
117,934 kg
(260,000 lbs)
Maximum Landing Weight (MLW) 89,811 kg
(198,000 lbs)
95,253 kg
(210,000 lbs)
101,604 kg
(224,000 lbs)
Maximum Zero Fuel Weight (MZFW) 83,460 kg
(184,000 lbs)
85,000 kg
(187,400 lbs)
95,254 kg
(210,000 lbs)

Other Weight Restrictions

Note: These weights may be further restricted by Company registered limits, field length limits, climb limits, tire speed limits, brake energy limits, obstacle clearance, or enroute and landing requirements.

Company Limitations

Minimum Flight Crew Oxygen Quantity

Prior to despatch from a main base the minimum Oxygen pressure shall be 1300 psi.

Engine Oil Quantity

Prior to despatch the minimum indicated Engine Oil Quantity shall be 16 US quarts.

Engine, IDG and APU Oil Specification

Mobil Jet II

Hydraulic Oil Specification

Skydrol 500 B4

Approved Fuel Specifications

Fuel Type Specification Comments Freezing
Point
Flash
Point
Kerosene
(AVTUR)
Jet A
Jet A1 [NATO F35]
JP-8 Grade [NATO 34]
British DERD 2453
British DERD 2494
Canadian CAN 2-3.23
ASTM D1655-75
ASTM D1655-75
MIL-T-83133


 
-40
-47
-47
-47
-47
-47
+38
+38
+38
+38
+38
+38
Wide Cut Fuel
(AVTAG)
[used in
cold climates]
Jet-B
JP-4 Grade [NATO F40]
British DERD 2454
British DERD 2486
Canadian CAN 2-3.22
ASTM D1655-75
MIL-T-5624K


 
-50
-58
-58
-50
-50
-18
-18
-18
-18
-18
High Flash
Point Fuel
(AVCAT)
JP-5 Grade [NATO F44]
British DERD 2498
MIL-T-5624K
 
-46
 
+60
 

Aircraft Category

For the purposes of instrument approach procedures and landing minima, B757-200 aircraft are Category 'C'.

For the purposes of instrument approach procedures and landing minima, B757-300 aircraft are Category 'D'.