For Traini 

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1

B744 and 747-8 differences

GENERAL

Wing span

height distance from nose gear to main gear

The length The airplane

68.4M 19.4M 29.7 M 76.3M B747-8F

64.9M 19.1M 27.3M 70.7M B744

3.5M 0.3M 2.4M 5.6M The difference

The wing tip is racked.

THE COCKPIT DISPLAY

Each pilot console in the 747-8F is reconfigured with provision for the

Electronic flight bag.

The clocks and RMI are removed in the B747-8F.

The landing Gear lever is in two position lever.

An electronic checklist Cursor controls are added on the sides of the

control stands.

Some controls and lights have been removed and other have been

added.

The FMC control display units operate faster, hold more data and other

features are added.

The radio tuning panels have keypads to allow faster and easier

frequency selection.

All display units screens are liquid crystal display.

2

On the PDF, a Navigation Performance Scales(NPS) , an Integrated

Approach Navigation (IAN) , A Navigation Source Reference and, a

magenta speed band are added to provide additional information.

On the ND, a Vertical Situation Display (VSD) shows in the expanded map

mode, an Airport Map Display in the centre or expanded map mode

when the range is 5 miles or less, and a clock is added on the upper right

corner of the ND Display.

On the primary EICAS Display, a checklist icon shows for EICAS messages

that have a non-normal checklist, a single stabilizer trim indication to

replace the indicators on the control stand and, an ATC data block for

ATC messages replaced the Pressurization data block.

In the bottom of the STAT UTC time, DATE, and ELAPSED time are

displayed.

On the glareshield switches are added to accept or cancel ATC messages.

Inboard Display controls let you choose what to show on the inboard

displays, e.g. PFD, NAV, MFD, EICAS.

On the Display Select Panel three displays are designated as MFDs the

left inboard(L INBD), the lower EICAS(LWR CTR), the right inboard

displays (R INBD), for selecting the active MFD and the information

shown in it, an Electronic Checklist shows Normal and Non-Normal

checklist, a new Flight Control Synoptic shows control surface position

and status, also in the DSP the Status Page shows time and date

information at the bottom of the page.

3

Limitation

The FLAPS limit speed increased 5 knots as shown in the

placards.

Minimum width of pavement for 180 degrees turn:

52.4M on 747-8F and 46.6M on the 744.

The weight limitation

B747-8F B744

Max taxi Weight 449,056 kg 395,986 kg

Max Takeoff Weight 447,695kg 394,625 kg

Max landing Weight 346,090kg 295,742 kg

Max Zero Weight 329,761kg 246,073 kg

HZ-AI3 (747-8)

,100 feet pressure altitude42 Maximum Operating Altitude

HZ-AI4 (747-8)

,100 feet pressure altitude43 Maximum Operating Altitude

8)-747Door Mounted Power Assists and Escape Slides (

The upper deck escape slide must be in the forward locked position during taxi,

takeoff, and landing whenever the upper deck cabin is occupied.

Ladder Enclosure Door (747-8)

The ladder enclosure door must be closed during taxi, takeoff, and

4

landing. The ladder enclosure door must be closed in-flight except when

entering or leaving the main deck cargo compartment.

Main Deck Occupancy (747-8)

Occupancy of the main deck cargo area is prohibited during taxi, takeoff,

and landing.

747-8

#The autopilot must not be engaged below 200 feet after takeoff.

#Without LAND 2 or LAND 3 annunciated, the autopilot must be

disengaged below 100 feet RA.

Autoland capability may only be used for operations into runways at or

below 9,500 feet airport field elevation.

SATCOM Phone (747-8)

Non-AFM Operational Information

Do not use Swift Broadband service for ATC communications.

747-8

The maximum tank fuel temperature for Jet A, Jet A–1, JP–5, JP-8 or

TS-1 is 54°C (130°F).

The use of JET B and JP-4 fuels is prohibited.

In-flight tank fuel temperature must be maintained at not less than

-48°C (-55°F) or 3°C (5.4°F) above the fuel freezing point of the fuel

being used, whichever is higher. The use of Fuel System Icing Inhibitor

additives does not change the minimum fuel tank temperature limit.

Tailwind and Crosswind Ground Operations (747-8)

Non-AFM Operational Information

For tailwinds above 15 knots, limit engine power levels to taxi power.

For 90 degree crosswind components between 45 and 55 knots, limit

engine power levels to taxi power.

CAUTION: Engines must be shut down when the 90 degree

crosswind component exceeds 55 knots.

Flight Maneuvering Load Acceleration Limits (747-8)

Flaps Up : +2.5g to -1.0g.

Flaps Down : +2.0g to 0.0g.

Note: With flaps at 25 and 30, positive limits vary linearly from

+2.0g at Maximum Landing Weight to +1.5g at Maximum

Takeoff Weight.

Flight Instruments, Displays (747-8) Electronic Flight Bag (EFB)

The EFB portable keyboard and attaching cable must be stowed during

takeoff and landing.

ISFD In the event of loss of primary air data, standby system corrections must

be provided to, and applied by, the flight crew.

5

Normal Procedures Chapter NP

Electronic Checklist Operation (747-8) Operation with the electronic normal checklist is the same as the printed

normal checklist except that, there is no need to read aloud or visually

confirm items that are complete (green). For the BEFORE TAKEOFF

and LANDING checklists, the PM announces “___ CHECKLIST

COMPLETE,” the PF visually confirms that the CHECKLIST

COMPLETE indication is shown, and announces “CHECKLIST

COMPLETE.” Closed loop (sensed) checklist items change from white to

green when the action is taken. The PM is responsible to check off any

open loop (not sensed) item and to verify that all closed loop items are

green. See Chapter 10, Flight Instruments, Displays, for a complete

description of the electronic checklist system.

Checklist Content The checklist has the minimum items needed to operate the airplane safely.

Normal checklists have items that meet any of the following criteria:

• items essential to safety of flight that are not monitored by an

alerting system, or

items essential to safety of flight that are monitored by an alerting

system but if not done, would likely result in a catastrophic event if

the alerting system fails, or

• items needed to meet regulatory requirements, or

• items needed to maintain fleet commonality between the

747-400,777, and 787, or

• items that enhance safety of flight and are not monitored by an

alerting system (for example the autobrake), or

• during shutdown and secure, items that could result in injury to

personnel or damage to equipment if not done

Checklist Construction When a checklist challenge does not end with “switch or lever”, then the

challenge refers to system status. For example, “Landing Gear...Down”,

refers to the status of the landing gear, not just the position of the lever.

When a checklist challenge ends with “switch or lever”, then the challenge

refers to the position of the switch or lever. For example, “FUEL

CONTROL switches...CUTOFF” refers to the position of the switches.

CM2’s Preliminary Cockpit Preparation Procedure 747-8F (HZ-AI3, HZ-AI4; before SB, upgraded yaw dampers not installed)

YAW DAMPER switches .......................................................Verify Off.

(747-8F)

LOWER LOBE AFT CARGO HT selector.....................As needed.

TOWING POWER switch.........................................................OFF

Verify the ON BAT light is extinguished.

CM2’S CDU........................................................................Check and set

6

.........

NP.21.6 • *TAKEOFF line select key - PUSH.

•Make data entries on page 2/2 before page 1/2.

Enter (Normal Operation):

FLAP/ ACCEL HT- 10/1000 ft. or 20/1000 ft.As applicable.

E/O ACCEL HT - 800ft AGL or MFRH whichever is higher.

*Exterior Inspection

Right Wing Root, Pack, and Lower Fuselage( NP.21.10)

(747-8)

Ram Air Turbine Door....................................................................Check

Right Wing Tip and Trailing Edge (NP.21.11 )

(747-8)

Wing Tip Rear Facing Marker light................................................Check

Left Aft Fuselage (NP.21.12 )

(747-8F)

Side Cargo door and access panels (not in use)...........................Latched

CM2’s Cockpit Preparation Procedure

(747-8F) NP.21.14

APU GENERATOR 2 switch – Push when main deck cargo handling

equipment is no longer needed.

Verify that the ON light is illuminated.

(747-8F)

Note: If both external power 2 and APU generator 2 AVAIL lights

are illuminated, main deck cargo handling power is provided

by external power 2. Selecting external power 2 ON transfers

main deck cargo handling power to APU generator 2.

(747-8F)

CARGO INTERPHONE switch.............................................. As needed

(747-8F) NP.21.15

• CARGO FIRE DEPRESS/DISCH lights - Extinguished

• Cargo Fire ARM switches - off

Verify FWD and AFT lights extinguished. (747-8F)

Verify the MAIN DECK, FWD, and AFT lights are

extinguished.

(747-8) NP.21.17

FUEL XFER RESERVE 1&4 switch .................................Guard closed

WARNING:Do not push the RAM AIR TURBINE switch. The

7

switch causes deployment of the ram air turbine.

RAM AIR TURBINE UNLOCK light .....................Verify extinguished

CENTER ADC selector ...............................................................NORM

(747-8) NP.21.19

ELECTRONIC FLIGHT BAG .......................................................... Set

NP.21.20

INBOARD DSPL selector .............................................................MFD

(747-8) NP.21.22

CHKL display switch - Push

RESETS - Select

Verify the CHECKLIST DATABASE is current.

RESET ALL - Select

CM1’s Cockpit Preparation Procedure

(747-8) NP.21.24

ELECTRONIC FLIGHT BAG............................................................Set

(747-8) NP.21.27

Integrated standby flight display .................................................. Set

Verify the approach mode display is blank.

Set the altimeter.

Verify the flight instrument indications are correct.

Verify no flags or messages are shown.

Before Start Procedure

(747-8F) NP.21.29

• Ensure that the main deck nose cargo door Control Panel (PF)

and Latch Annunciator Panel lights have been verified to

confirm nose cargo door closed, latched, and locked.

Ensure that both APUGENERATOR ON lights are

illuminated.

Obtain a clearance to pressurize hydraulic systems.

(747-8) NP.21.31

Verify:

• main 1 + reserve 1 > main 2, or

• main 4 + reserve 4 > main 3, or

• main 2 or main 3 < approximately 20,700 kgs, and

• crossfeed valve 1 or 4 open

or, on ground and completion of one of the following and

• initial electrical power application, or

• refueling, or

• fuel system CMC ground test, and

• main 1 + reserve 1 + 500 kgs > main 2, and main 4 +

reserve 4 + 500 kgs > main 3, and crossfeed valve 1 or 4 open

8

OVERRIDE pumps 2 (both) switches - Off

OVERRIDE pumps 3 (both) switches - Off

CROSSFEED valve 1 and 4 switches - Off

• Cancel when review completed and Verify messages cancelled

(747-8F) NP.21.32

• Ensure that the main deck nose cargo door closed, latched,

and locked.

Engine Start Procedure NP.21.34

(747-8)

Autostart does corrective steps for:

• no EGT rise

• a hot start

• a hung start

• compressor stall

• no light-off

• starter shaft shear

• low/no starter pressure

• no N1 rotation

• starter duty cycle exceedance

• EGT exceedance

• no oil pressure rise

After All Engines are Started NP.21.36

Taxi NP.21.38

Airport Map Display 747-8

The ND airport map display is intended to enhance crew positional

awareness while planning taxi routes and while taxiing. The system is not

intended to replace normal taxi methods including the use of direct visual

observation of the taxiways, runways, airport signs and markings and

other airport traffic. Prior to taxi, NOTAMS and airport charts (using EFB

terminal charts or paper) should be consulted for the latest airport status to

include closed taxiways, runways, construction, etc., since these

temporary conditions are not shown on the airport map.

Note: Crews must avoid fixation on the display or distraction from

primary crew duties while using the airport map display.

Crews must use direct visual observation out flight deck windows as the

primary taxi navigation reference. Use the ND airport map mode to

provide enhanced positional awareness by:

• verifying taxi clearance and assisting in determining taxi plan (both

• pilots)

• monitoring taxi progress and direction (both pilots)

• alerting and updating the pilot taxiing with present position and

upcoming turns and required stops (pilot not taxiing).

9

In flight, the ND airport plan mode may be used to aid in runway exit

planning and anticipating the taxi route to the gate or parking spot.

Note: During takeoff and landing, low map ranges may cause the

airport map position to jump, rather than to move smoothly.

Note: GPS position must be available to use the ND airport map mode.

747-8F

• both pilots verify that the correct airplane position is in the FMC

and the ND airport map display shows correct placement

• brief applicable items from airport diagrams and related charts to

include the location of hold short lines

• ensure both crewmembers understand the expected taxi route

• write down the taxi clearance when received

• an airport diagram should be readily available to each crewmember

during taxi

Initiating Takeoff Roll 747-8F

• if cleared for takeoff before or while entering the runway, maintain

normal taxi speed. When the airplane is aligned with the runway

centerline ensure the nose wheel steering tiller is released and

apply takeoff thrust by advancing the thrust levers to

approximately 45% N1. Allow the engines to stabilize

momentarily then promptly advance the thrust levers to takeoff

thrust (autothrottle TO/GA). There is no need to stop the airplane

before increasing thrust.

NP.21.51

Verify the automatic V1 callout or call

“V1”.

NP.21.53:Full maneuver capability is available at all

weights at or above the “UP” symbol.

Maximum Rate Climb

747-8F NP.21.54

• VREF 30 + 120 knots until intercepting 0.83M maneuver speed + 60

knots until intercepting 0.82 Mach Maximum Angle Climb

747-8F -flaps up maneuver speed.

Climb and Cruise Procedure

When the FUEL TANK/ENG message NP.21.56

747-8F

• main 1 + reserve 1 ≥ main 2,or

• main 4 + reserve 4 ≥ main 3,

11

and

• crossfeed valve 1 or 4 open

set both OVERRIDE pumps 2

switches - Off

set both OVERRIDE pumps 3

switches - Off set CROSSFEED valve 1 and 4

switches - Off

Before the top of

Approach Requirements Relating to RNP NP.21.73

RNP Approach Type

747-400 0.3 NM

747-8 0.1 NM

RNAV (GPS)/(GNSS)

Landing Procedure - IAN (747-8F)

This procedure is not authorized using QFE.

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.

Pilot Monitoring Pilot Flying

Notify supernumerary(s) to prepare

for landing. Verify that the cabin is

secure

Set the flap lever as directed. . Call “FLAPS __” according to the

flap extension schedule.

When on Final Approach Course intercept heading:

• verify the intended approach is indicated on the PFD

• verify the LOC/FAC and and GP pointers are shown in the correct

position

Arm the APP mode.

Note: When using LNAV to intercept the final approach course, LNAV

might parallel the localizer without capturing it. Use HDG SEL or

HDG HOLD to intercept the final approach course if needed.

11

Use appropriate roll mode to capture

FAC.

Verify that the LOC/FAC is captured.

Approximately 2 NM before the final

approach fix, call “APPROACHING

GLIDE PATH.”

• Approximately 2 NM before the final

approach fix, call:

• “GEAR DOWN”

“FLAPS 20”

Set the landing gear lever to DN.

Set the flap lever to 20.

Set the speedbrake lever to ARM.

Set the flap lever as directed. At glidepath capture, call “FLAPS __”

as needed for landing.

Pilot Flying Pilot Monitoring

Monitor the approach.

If suitable visual reference is established at MDA(H), DA(H), or the missed

approach point, disengage the autopilot in accordance with regulatory

requirements, and disconnect the autothrottle at the same time.

Maintain the glide path to landing.

At final approach fix or OM, verify the crossing altitude.

Do the LANDING checklist. Call “LANDING CHECKLIST.”

Set the missed approach altitude on the

MCP.

12

Secure Cockpit Procedure

(747-8F) NP.21.97

APU GENERATOR 2 switch - Push when main deck cargo

handling equipment is not needed.

Verify that the ON light is illuminated

(747-8F)

EXTERNAL POWER 1 switch - Push

EXTERNAL POWER 2 switch - Push when main deck cargo

handling equipment is not needed.

(747-8F) NP.21.98

Note:If both external power 2 and APU generator 2 AVAIL lights

are illuminated, main deck cargo handling power is provided

by external power 2. Selecting external power 2 ON

transfers main deck cargo handling power to APU generator 2.

(747-8F) NP.21.99

EFB CLOSE FLIGHT ................................................................... Select

Flight Termination Procedures

(HZ-AI3, HZ-AI4; before SB, upgraded yaw dampers not installed) NP.21.100

YAW DAMPER switches................................................OFF CM2

13

At DA(H) or MDA(H)

Glide path intercept

• Flaps 5

• Flaps 1

• Disengage autopilot in accordance with regulatory requirements and

Enroute to fix

On RADAR vectors

• Set missed approach altitude

• LNAV or other roll mode • VNAV or other pitch mode

• HDG SEL • Pitch mode (as needed)

Approaching intercept heading

• Flaps 5

Localizer/Final approach

heading

Intercept heading

• Flaps 10 optional

• Deviation pointers shown

• Arm APP

• Landing flaps

• Do the Landing checklist

disconnect autothrottle

• Final approach course

course capture

Fix

• (LOM, MKR, DME)

• Radios tuned (as needed)

• Verify crossing altitude

approximately 2 NM from

• Flaps 20 • Gear down

• Arm speedbrake

Glide path alive or

the FAF

Maneuvers Chapter MAN

Instrument Approach Using IAN

180 Degree Minimum Radius Turn Man.2.9

Note: Minimum width of pavement for 180° turn with body gear

steering is

747-400 153 feet (46.6m)

747-8F 172 feet (52.4m)

14

Supplementary Procedures Chapter SP

Low Gross Weight, Aft CG Takeoff (747-8F)

CM2 CM1

Before entering the departure runway, verify that the runway and runway entry

point are correct.

Confirm 15% (or greater) derate thrust

for takeoff, or the equivalent using

assumed temperature thrust reduction,

or the equivalent using any fixed

derate thrust and assumed temperature

thrust reduction.

Position Inboard Landing Lights and

Strobe Light switches ON.

Position Transponder Mode selector to

TA/RA.

Align airplane with runway

centerline*.

Verify that the airplane heading agrees with the assigned runway heading.

Release brakes*.

Advance Thrust levers to

approximately 45% N1.

Allow engines to stabilize.

Push TO/GA switch to advance Thrust

levers to takeoff thrust or manually

advance Thrst levers to takeoff thrust

Pilot Monitoring Pilot Flying

Monitor engine instruments throughout

takeoff.

Verify correct takeoff thrust set.

. Adjust takeoff thrust prior to 80

knots if required.

Apply full forward control column

deflection to approximately

80 knots to improve nose

wheel steering.

After takeoff thrust is set, the captain’s hand must be on Thrust levers until

V1.

15

* The airplane may be stopped (brakes set) after aligning with the runway and centerline,

but a rolling takeoff is recommended.

Air Conditioning Packs

APU-to-Pack Takeoff

After engine start:

LEFT and RIGHT ISOLATION valve switches - Off

Leave APU running to supply air to pack 2.

Before takeoff:

PACKS 1 and 3 switches - Off

After takeoff:

PACK switch (One only) - ON

Call “80 KNOTS.” Verify 80 knots.

Monitor airspeed noting V1.

Rotate at VR.

Establish a positive rate of climb.

Call “V1.”

At VR, call “ROTATE.”

Monitor airspeed and vertical speed

. Call for “GEAR UP” when positive

rate of climb established.

Verify positive rate of climb; then,

position Landing Gear lever UP.

Verify LNAV, VNAV active.

When above minimum altitude for

autopilot engagement, engage A/P.

Verify acceleration at acceleration

height.

Call for “FLAPS ____” according to

flap retraction schedule.

Position Flap lever as directed.

Verify climb thrust set.

Call for “AFTER TAKEOFF

CHECKLIST.”

Accomplish AFTER TAKEOFF

checklist.

16

After engine thrust is reduced from takeoff to climb, position one Pack switch to ON.

PACK switch (Remaining pack) - ON

When cabin pressurization stabilizes, position remaining Pack switch to ON.

LEFT and RIGHT ISOLATION valve switches - On

APU selector - OFF

Packs Off Takeoff

Before Takeoff:

Pack switches - Off

After takeoff:

Pack switch (One only) - ON

After engine thrust is reduced from takeoff to climb and prior to reaching 3,000 feet above

field elevation, position one Pack switch to ON.

Pack switches (Remaining packs) - ON

When cabin pressurization stabilizes, position remaining Pack switches to ON.

Ground Conditioned Air Use SP.2.3

Before connecting ground air conditioning cart:

PACK switches - Off

Prevents pack operation if bleed air is supplied to the airplane.

After disconnecting ground air conditioning cart:

PACK switches - ON

Flight Deck Fan SP.2.3

During preflight:

FLIGHT DECK FAN switch - As required

Turn Flight Deck Fan switch ON when extra cooling required.

Before takeoff:

FLIGHT DECK FAN switch - Off

During shutdown:

FLIGHT DECK FAN switch - As required

Turn Flight Deck Fan switch ON when extra

cooling required.

17

Weight and Balance (747-8F) SP.5.1 The flight crew shall verify the Weight and Balance numeric and

alphabetical values are identical. If the Weight and Balance numeric and

alphabetical values are different, the flight crew must not accept the

Weight and Balance data.

Takeoff Data (747-8F) The flight crew shall verify the Takeoff Data numeric and alphabetical

values are identical. If the Takeoff Data numeric and alphabetical values

are different, the flight crew must not accept the Takeoff Data message.

Engine/APU/Cargo Fire/Overheat Test SP.8.1 (747-8F)

Note: EICAS warning message FIRE WHEEL WELL may

momentarily display. A CHKL OVRD, RESET ALL, or

RESET NON-NORMAL for the FIRE WHEEL WELL

checklist may be required after the completion of the

Engine/APU/Cargo Fire/Overheat Test.

Heading Reference Switch Operation

Use TRUE when operating in regions where true referencing is needed. Use NORM in all

other regions.

HEADING reference switch

NORM or TRUE

If using HDG SEL and the HDG reference switch position is changed, the AFDS roll

mode will change to HDG HOLD. HDG SEL can be reselected.

If the HDG reference switch position must be changed for an approach, it must be changed

before the APP mode is armed.

If the HDG reference switch position is changed after the APP mode is armed:

The AFDS roll mode will not change from HDG SEL to HGD HOLD

The AFDS will not follow the MCP-selected heading

LOC and FAC capture, and tracking performance may be degraded

Exiting the APP mode restores normal operation of the HDG reference switch

and the AFDS. APP mode can be reselected.

Weather Radar Test (747-8F) SP.11.7 ND Mode selector............................................................................MAP

EFIS WXR switch ............................................................................Push

Weather Radar TEST switch ............................................................Push

Verify radar test pattern displays on ND.

Observe the following sequence (approximately 20 seconds).

Amber windshear caution light illuminates and the aural message

“monitor radar display” is initiated, then Master Warning lights

illuminate. The windshear fail message is displayed on the flight

deck, then Red windshear warning light will illuminate and the

aural message “go around, windshear ahead, windshear ahead,

windshear ahead” is initiated. During this time period the

18

“rainbow” (with embedded windshear icon) self-test is displayed.

EFIS WXR switch........................................................................... Push

Removes Captain’s and First Officer’s weather radar displays.

Weather Radar Mode selectorAs desired

Desired Mode switch........................................................................ Push

Cold Weather Operation SP.16.2 747-8F Preliminary Preflight Procedure - CM1 or CM2 Do the normal Preliminary Preflight Procedure - Captain or First Officer

with the following modifications:

If taxi-in on the previous flight occurred in visible moisture (fog with

visibility of one statute mile (1600 m) or less, rain, snow, sleet, ice

crystals, and so on), and the temperature stayed below 3°C, the taxi-in

time from the previous flight in the airplane logbook or other approved

document must be included in the total taxi time. If the engine is

considered free of ice before engine start, only the taxi-out time should

be included in the total taxi time. The engine is considered free of ice

before engine start if:

• the engine has been manually de-iced, or

• the engine has been visually inspected per the AMM

747-8F SP.16.3 Preflight Procedure - CM2 Do the normal Preflight Procedure - CM2 with the following

modifications:

If the ambient temperature is at or below -18 degrees C, and running

the hydraulic demand or auxiliary pumps is desired to help maintain

hydraulic system temperature:

WARNING: Ensure personnel and equipment remain clear of

all flight control surfaces, landing gear, and thrust

reversers when any hydraulic pump is operating.

WARNING:Do not operate any hydraulic pump with the flight

deck unattended.

Note:The system 1 and 4 air driven demand

pumps generate significant ramp noise

Obtain a clearance to pressurize the hydraulic systems.

Hydraulic demand pump selectors .......................AUX or ON CM2

If the engines have been cold soaked for more than four hours at

ambient temperatures at or below -35°C:

GENERATOR CONTROL switches (all) ........................Off

Do not turn on the generator control switches until engines

have been at stable idle for a minimum of 2 minutes.

Before Taxi Procedure SP.16.5

Do the normal Before Taxi Procedure with the following modifications:

747-8F If the engines have been cold soaked for more than four hours at

19

ambient temperatures at or below -35°C:

After the engines have been at stable idle for a minimum of 2

minutes:

GENERATOR CONTROL switches (all)..........................ON

................................................

....................................................

747-8F CAUTION: Precautions must be taken for:

• Jet blast up to 700 feet (220 m) behind the aircraft.

• Snow and ice at the edge of the taxiway that can be ingested by the

engines.

• Slippery taxi surfaces.

• Airport noise restrictions.

When both of the following exist, do an engine run-up to minimize ice

build-up: C

• OAT is 3°C or below

• Visible moisture (fog with visibility of one statute mile (1600 m)

or less, rain, snow, sleet, ice crystals, and so on)

Use the following procedure:

Check that the area behind the airplane is clear.

Run-up to a minimum of 40% N1 for at least 5 seconds duration at

intervals no greater than 60 minutes.

Note: Operation in icing conditions may result in engine vibration

indications above the normal operating range during ice

shedding. If engine vibration indications are available and

high engine vibration indications occur, run-up to 55% N1

or higher for at least 20 seconds duration.

If takeoff is not completed within 120 minutes total taxi time (including

taxi-in, taxi-out, and ground holds), the engines must be inspected

according to the AMM before takeoff and, if needed, manually de-iced.

Takeoff Procedure

747-8F SP.16.8 Note:Operation in icing conditions may result in engine

vibration indications above the normal operating range

during ice shedding.

Run-up to a minimum of 55% N1 or higher for at least 20

seconds duration, confirm stable engine operation and,

if engine vibration indications are available, ensure engine

vibration indications are below 4 units before the start of the

takeoff roll

Wing Anti-ice Operation - In flight

747-8F SP.16.9 Wing anti-ice must be AUTO or ON during all flight operations when

icing conditions exist or are anticipated.

WARNING: If using the wing anti-ice system manually do not

rely on airframe visual icing cues before activating wing anti-ice.

21

Use the temperature and visible moisture criteria because late

activation of wing anti-ice may allow ice to accumulate on the

wing.

After Landing Procedure (747-8F) SP. 16.3

CAUTION: Precautions must be taken for:

• Jet blast up to 700 feet (220 m) behind the aircraft.

• Snow and ice at the edge of the taxiway that can be ingested

by the engines.

• Slippery taxi surfaces.

• Airport noise restrictions.

B747-400 to B747-8

DifferencesSystems Overview

§2

B747- 400 to B747-8 Systems Differences

• Flight Deck• Avionics• Environmental Control Systems• Primary Flight Controls• Highlift• Hydraulics• Landing Gear• Electrical Systems• Propulsion

§4

B747 Flight Decks

B747-400

B747-8

Primary Flight Display- Integrated Approach Navigation (IAN)- Global Navigation Satellite System

(GNSS) Landing System (GLS)- Navigation Performance Scales (NPS)

Navigation Display- Vertical Situation Display (VSD)- Navigation Performance (ANP/RNP)- Clock Functionality

Integrated Display System (IDS)New Basic Features

Three Multifunction Displays (MFD)- Electronic Checklists- Flight Controls Synoptics

Display

EICAS Display- Stab Trim Information- Dedicated ATC Datalink Block

Integrated Display System (IDS)New Basic Features

Inboard Display Selector Switch (2 Places)

- Allows the crew to configure the Navigation Display as a

PFD, MFD or EICAS display

Display Select Panel (DSP)- Selects the display format

on the MFD

Rotary Cursor Control PanelWiring Provisions for

Graphical Flight Planning(2 Places)

Integrated Approach Navigation (IAN)

§ Common crew procedures for all approach types

§ Common safety features

§ Implements Navigation Performance Scales (NPS) for precise LNAV / VNAV path display and awareness of sensor performance

§ New Terms for flight mode annunciatorsFinal Approach Course (FAC)Glide Path (G/P) was G/S on the -400

SPD FAC G/P

Add ½ RNP index

Navigation Performance Scales (NPS)

§ Precise presentation of the lateral and vertical paths

§ Concurrent display of allowable flight technical error

§ Indication of sensor performance (RNP vs. ANP)

§ Provides capability to fly precise RNP or RNAV procedures

Nav Source ID for Lateral and Vertical Scales

G/S Ghost Pointer

VNAV Deviation Pointer

Vertical ANP Scale

Lateral ANP ScaleLateral Deviation PointerLOC Ghost Pointer

Global Navigation Satellite System (GNSS) Landing System (GLS)

§ Path Indications - Common

§ Autoflight Status - Common

§ Mode Annunciation - Common

SPD LOC G/S

Vertical Situation Display

§ Energy management

§ Terrain avoidance

§ More predictable approaches

§ Terrain corridor ahead of the airplane

§ Increased safety

Electronic Checklist (ECL)

Electronic Checklist

§ Primary purpose is to eliminate errors associated with paper checklists

§ ECL crew coordination same as paper

§ Other benefits:

§ Faster checklist accomplishment

§ Lower workload

§ Decreased training time

NORMAL ITEMOVRD NOTES CHKL

OVRDCHKL

RESETEXIT

MENU

OXYGEN PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

PASSENGER SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

FLIGHT INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . .SET

AUTOBRAKE SELECTOR . . . . . . . . . . . . . . . . . . . . . . RTO

PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET

FUEL CONTROL SWITCHES . . . . . . . . . . . . . . . . . CUTOFF

NORMAL MENU RESETS NON-NORMAL MENU

ü

üü

ü

PREFLIGHT

ATS Datalink – New Basic Features

747 Advanced Additional Datalink CapabilityNew Accept/Reject/Cancel Switches

ATC DatalinkMessage Block

On EICAS Display

(777 Shown)

Model Feature Comparison ATS Datalink

747-400 747-8

New FeaturesATC Accept/Reject/Cancel Switches• ATC Message Block on EICAS• AOC & ATS Basic Features• FANS-2 (ATN) (Aeronautical Telecommunications Network)

ATS-DL Optional on 747-400

Display Select Panel747-400 747-8

New Features

• MFD Selection • Flight Controls Synoptics Display• Electronic Checklist• Combined CANC/RCL Switch

Display Management747-400 747-8

New Features

• Multifunction Displays (MFD)• 4 Position Inboard Display Switch

Stab Trim Indication747-400 747-8

New Features

• Stab Trim Indicator on EICAS Display• Stab Trim switch (Same

Location as 747-400)

2 places

747-400 747-8

New Feature

• Flight Controls Synoptics DisplayOptional on Secondary EICAS Page

Status Page

777 Display Shown for Ref

Flight Controls Synoptic

Clock Function on Navigation Display

747-400 747-8

New Features

• GPS-Based Clock Functions onNavigation Display

UTC Time

ET (Auto)orChrono

Pilot’s Main Panel UpdatesInboard Display Selector Switch – 777 Style

Display Select Panel (DSP)

(2 Places)

(2 Places)

Clock Deletion(Clock Functionality Integrated on ND)

Two Position Landing Gear Lever

Accept/Cancel/Reject Switches

(2 Places)

P5 Overhead Panel Updates

ECS Control PanelRam Air TurbineSwitchEngine Start Panel

Bleed Air Control Panel

Hydraulic Control Panel

Ignition and Autostart Switch Deletion

AC Pump Added to System 1RAT Added to System 3

AC Pump Aux & Demand System 4 Two Position Pack Switches

Combines Pack Reset Switches & AVSStudies:

L & R Trim Air, Recirculation Fan & System Simplification

Throttle Quadrant New Features

Rotary Cursor Panel(2 places) Stabilizer Trim

Indicator Informationon EICAS

UpdatedFMC CDUs (3 Places)

First Observer’s Side Console New Features

Maintenance Terminal• Portable Laptop device• LRU Data loading• Interface with CMCS• LRU Software Storage• Portable Maintenance Aid

Software

Airborne Data Loader (ADL) Replaced by Laptop Maintenance Terminal (MT)

Flight Deck Installation of Stowage Equipment that

meets latest Requirements

(Latches, Straps, etc..)

(Reference 747-400F Photo)

Pilot’s Consoles Electronic Flight Bag Partial Provisions

EFB Partial Provisions:Relocates: Oxygen Masks, Heater Switches, Speaker and Hand Microphone HolderDeletes: Map/chart stowage, Jeppesen Manual Stowage, Weather Radar Indicator

Space Provisions

747-8747-400

Differences Summary

• IDS displays• IDS control & display functions• Landing Gear Lever• P5 overhead panel changes• P9/P8 panel changes• Misc F/D panels• Approximate teach time is 2 hours

Integrated Display System (IDS)•Changes required to accommodate changes to other airplane systems:

– EFIS/EICAS Interface Unit (EIU):

• Buffer high speed engine data

• Add ARINC 615A high speed data load protocol

• Add discrete outputs to drive signals for the 2 position gear lever and the RAT deployment solenoid

– EICAS:

• Add/Revise EICAS messages per various other airplane changes

• Add Flight Controls Synoptic

• Indicate spoiler retraction when required due to maneuver load alleviation (MLA)

• Display Stabilizer Trim and Stab Greenbands

• Revise gear indication to account for two position electric landing gear lever

• Revise Synoptics and Maintenance pages to accommodate airplane changes

– ND:

• Add display of GPS time and chronograph.

747 New FMC

n Enables planned upgrade

n World Wide Database

n Faster response time

n Designed for Retrofitn FMC retrofittable

“Plug & Play”747-8 functionality

Central Maintenance Computer Function (CMCF)

• Revise the CMC hardware and software to add:• Fault messages for new or revised systems • Ground test modifications for new or revised systems • New configuration menus• Trade study determined existing CMC hardware does not have

sufficient processor capability to process 747-8 fault messages → New hardware required

Multi-mode Receiver (MMR)

• Upgrade MMR to provide differential-GNSS (DGNSS) and GLS capability using a ground-based augmentation system (GBAS) as follows:– Add 3rd system: GPS antenna and coax cable connected

to a C MMR– MMR wiring is revised for position program pin wiring of

the L-R-C MMR’s (approximately 5 wires for each MMR)– Add (1) inertial bus input into MMR-C– Delete the offside inertial input bus for MMR L and R

ARINC 781 SATCOM

– 6 MCU total (instead of 20 MCU for ARINC 741 systems)

– Flange mounted HPA– Simplified LRU installation – fewer LRUs installed

in the main equipment rack– A smaller and lighter antenna improves the

antenna installation

Air Data and Inertial Reference Unit (ADIRU)

• Replace three Inertial Reference Units (IRU) and Air Data Computers (ADC) with three ADIRUs and seven remote Air Data Modules (ADMs).

• Replace the triple IRU rack with a triple ADIRU rack.

Deleted Pitot/Static TubesLAOA

RAOA

LTAT

RTAT

STANDBY PS

STANDBY PS

To Standby Altimeter and

Airspeed Indicator

LMAINL

C

R

L

CR

IRS

IRS

CAPT-AD

FO-AD

L/R

C

L/R

C

LC

R

L

CR

AIRDATA

AIRDATA

#1#2

#1 #2 #1

#2#1

C

L/R

PITOT/STATIC

SOURCE SELECT VALVE

FP

AP 2

AP 2

AP 1

RAUX

To Elevator Feel Computer

CAPT PITOT

AUX STATIC 1

CAPT STATIC

AUX PITOT 2

LAUX

RMAIN

AUX PITOT 1

F/O STATIC

AUX STATIC 2

F/O PITOT

To Standby Air Speed & Elevator Feel

Computer

TAT

R*L*

Pt

CDADC

}

AOA

Ps

TAT

R*L*

Pt

LDADC

}

AOA

Ps

TAT

R*L*

Pt

RDADC

}

AOA

Ps

RADIRU

CADIRU

LADIRU

ADM

ADM

ADM

ADM

ADM

ADMPri

STATICSec

PriPITOT

SecADM

Service Interphone Jacks

Remove 13 under utilized Service Interphone Jacks

– 787 trade study results show a majority of service interphone jacks are not used.

– Simplifies manufacturing and post delivery maintenance

747- 8F / 8I Data Load Baseline

747-8 ONS

NFS (Network File Server)

A. Boeing/ Suppliers distribute software updates via electronic feed or storage media.

B. Airlines receive software updates by validating Boeing/Suppliers digital signature. Airlines apply digital signature to match key loaded on the airplane.

C. Airline loads software to an on-board mass storage via:• Electronic feed via terminal wireless lan unit (TWLU) OR• Media/Hard Drive via a maintenance laptop

D. Airlines use the maintenance laptop to initiate data load to systems

20x3 Switch

A 429

A 429

ARINC 615-3/4 LRUs

AirlinesOn AirplaneOR

Ethernet

Ethernet

ARINC 615A LRUs

Software Parts

10011101001110

1001110

Vault SW

Legacy Media Parts

Electronic feed

Ground station

ORC

Data load initiated

Portable laptop

Load to mass storage

D

B

A

Boeing / Suppliers

Airline Software Vault

Software Parts1001110

10011101001110

747- 8 Future Optional Data Load

§BOEING PROPRIETARY

option

Optional data loader (est late 2010)• Airline loads software to a mass storage via a

storage media through a mounted display terminal• Airlines use the mounted display terminal to initiate

dataload to systems

AirlinesOR

Software Parts

10011101001110

1001110

Vault SW

Legacy Media Parts

Electronic feed

Ground station

B

A

747-8 ONS

NFS (Network File Server)

20x3 Switch

A 429

A 429

ARINC 615-3/4 LRUs

Ethernet

Ethernet

ARINC 615A LRUs

OR

Data load initiated

Portable laptop

Load to mass storage

D1

On Airplane

OR

Mounted display terminal

C

D2

Boeing / Suppliers

Airline Software Vault

Software Parts1001110

10011101001110

Autopilot System

ADIRU

ADIRU

YSM – YAW DAMPER/STAB TRIM/RUDDER RATIO MODULE/PACS

Cabin & Network Systems Overview

E Enabled provision and Options TWLN Terminal Wireless LANEFB Electronic Flight Bag features (Opt)ODN Open Data Network

Off board digital connectivity • Larger Bandwidth connection • More data traffic

Differences Summary• Flight Deck Approximate teach time is 2 hours• Avionics

– Navigation Systems– CMCF– Communication Systems– Data Loading– Auto Flight– Cabin Systems– Approximate teach time is 4 hours

747- 8F ECS Walkaround

Cargo Fire Protection • Revise main deck cargo smoke detection - area type S/T 747-400SF• Cargo smoke detection system –area detection• Additional cargo fire suppressant and nozzles – stretch

Ice & Rain• New duct routing, valves, and pressure sensors to support new engine inlet definition and lip-skin temperatures.• Recertify wing anti-ice performance

Changes Relative to 747-400F

60-in aft stretch

160-in forward stretch

Cargo Air Supply • Modify FCAC & ACAC for larger cargo volume• Modify Lower Lobe cargo heating systems for larger volumes

Cabin Pressure and Decompression • Decompression analysis - strengthened wing box, modified wheel well envelope.• Relocate PPRVs and Remote Sensor Port• Additional NPRV(s)

CACTCS and Air Distribution • Modify the flow control - rate based on Freighter cargo volume.• New Subfreezing Packs• New recirc fans and filters• Mix bay and recirc fan ducting• New riser installation - additional pair of risers -accommodate increased airflow requirements.• New air distribution ducting to accommodate added risers and airflow• (New) CTC & additional temp sensors• Change ducting lengths - body stretch• Larger forward overboard valve/venturi

E/E Cooling • Revise Fwd E/E cooling supply and exhaust systems: 160” stretch, unique Freighter changes, and additions to equipment racks in E/E bay

Air Supply• New Digital Bleed and Precooler• New Ram Air Inlet / Outlet & reschedule

CPCS Overview

CPCS Overview 747-8 and 747-8F

• Changes from 747-400:– Relocate positive pressure relief valves and sensor

port due to the stretch of Section 42– Install additional negative pressure relief valve(s)

due to larger interior volumes – Change cabin pressure repressurization rate to

1000 fpm for the lower lobe cargo fire mode, similar to 747-400 910k airplane

• Normal repressurization rate is 300 fpm

Crew Rest Smoke Detection SystemOverview

• 747-8F– Upper Deck Crew Rest

• No additional smoke detectors required

• 747-8F– Ionization-type smoke detectors in crew rests are replaced with

photoelectric smoke detectors due to obsolescence, environmental concerns, and regulatory requirements

Wing Anti-ice

747-8 F - Primary Flight Controls Changes

Primary Flight ControlsElevator Add PACS, Revise Feel Computer, Add Feel Shift for

Stall I.D.Rudder Re-sized upper and lower Rudder PCUs. Lateral Re-sized Inboard Ailerons, new FBW Outboard

Aileron PCUs, new FBW Spoilers, Aileron Droop Function, Outbd Aileron Limiting

Cables Revised length and routing in wing and body

High Lift Leading Edge Re-size Drive SystemTrailing Edge Re-size Drive System, Add Flap Skew

Detection Flap Control Unit Add Flap Skew Detection

Flight Control Electronics YSM Combine SRM and YDM and add

PACS functionLCE New Lateral Control Electronics for

FBW Spoilers and OB aileron

Autoflight • Update for new A/P Characteristics• Add GLS and IAN

Section 41 Revise Aisle stand for CCDStab Trim Indicator on EICASAdd FBW Control Wheel and Speed Brake Handle Sensors

Horizontal Trim System

YSM 1

YSM 2

Moved to EICAS to allow room for cursor control device.

Trim control moved from SRM to YSM

Lateral System – Fly By Wire

P6

P514 P615

P515

APU BAT

Hyd Sys 2

Hyd Sys 4

Hyd Sys 3

Hyd Sys 1

IDG 1

IDG 2 IDG 3

IDG 4

P614

1

55

4

3

2

6 7 8

9

10

11

12

LCE LCE

Ele. Power

Capt Whl Sensor

F/O WhlSensor

Spd Bk Hndl Sensor

O/B Aileron

O/B Aileron

I/B Aileron

I/B Aileron

Gen Pwr Cntr Pnls Gen Pwr Cntr Pnls

DC Bu s 3

DC Bu s 2

DC Bu s 4

Hot A P U B at Bus

OB

Spoilers

IB Spoilers

OB Spoilers

IB Spoilers

FBW Inboard Spoiler Actuator

•Design Features: •Sized for 60 degree spoiler deflection •Based on 777 actuator (biased to retract for hydraulic and electrical failure) •No surface droop

747-8 F - High Lift Control System Changes

Primary Flight ControlsElevator Add PACS, Revise Feel Computer, Add Feel Shift for

Stall I.D.Rudder Re-sized upper and lower Rudder PCUs. Lateral Re-sized Inboard and FBW Outboard Aileron PCUs,

new FBW Spoilers, Aileron Droop Function, Outbd Aileron Limiting

Cables Revised length and routing in wing and body

High Lift Leading Edge Re-size Drive SystemTrailing Edge Re-size Drive System, Add Flap Skew

Detection Flap Control Unit Add Flap Skew Detection

Flight Control Electronics YSM Combine SRM and YDM and add

PACS functionLCE New Lateral Control Electronics for

FBW Spoilers and OB aileron

Autoflight • Update for new A/P Characteristics• Add GLS and IAN

Section 41 Revise Aisle stand for CCDStab Trim Indicator on EICASAdd FBW Control Wheel and Speed Brake Handle Sensors

Hydraulic System Changes

• Ram air turbine added for all-engine-out controllability

• Add RAT ground deploy/stow module in the right side-of-body area for on-ground deployment

• Extend hydraulic tubing runs and wiring associated with hydraulic system to accommodate increased fuselage length• Add tubing in tail (Section 48) for pitch

augmentation system actuator and elevator feel shift

• Add electric demand pumps to Systems 1 and 4 to meet required landing gear retract time

• Revision of hydraulic system routing to accommodate changed airplane threats

• Increase tubing size for new, larger aileron PCUs, flight spoiler PCUs, and rudder PCUs

• Revised aft engine strut installations

Ram Air Turbine (RAT)

Interconnect valves

Ram Air Turbine (RAT)

Wing leading edge

§ Add RAT to System 3 in right wing leading edge to provide all-engine-out controllability (windmilling power inadequate)

Landing Gear Systems Changes

Increased Gear Retract Actuation Capability• Body and Wing Gear Retract Actuators - New• Main Gear Uplock Actuators - New• Body and Wing Gear Downlock Actuators - New• Main Gear Alternate Extend Systems - Revised

•Uplock Alt Ext Motors - New•Uplock Alt Ext Mechanisms - New•Cables & Pulleys - Revised & Possible Rerouted

• LG Hydraulic Lines - New• LG Selector Valves - Using 777 MLG Valves

•737 Solenoid Valve - Accommodate 747 Alt Ext•777 Two-Position LG Lever - Accommodate Electric Cmd•Auto-Off Logic - Accommodate Two-Position LG Lever

• Wing Gear Pressure Operated Restrictor Ck Valves - Revised• Body and Wing Gear Truck Positioners - Possible Overtravel Changes

Landing Gear Door Integration• Body and Wing Gear Door Actuators - New• Door Operated Sequence Valves - New• Uplock Operated Sequence Valves - Revised• Downlock Operated Sequence Valves - Revised• Door Safety Valves - Revised

Wheels, Tires & Brakes• 50”x20” Radial Tire - New RRR NLG Delivery Tire• 22” NLG Wheel - Lightened Delivery Wheel• 52”x21” Radial Tire - New RRR MLG Delivery Tire• 22” MLG Wheel - New• Carbon Brake - New

Brake Control System• Antiskid Tuning - Revised• Brake Torque Limiting - Revised• TPIS & BTMS - Revised & Combined• Three System Loss SRP - Systems solution in-work• Brake Control Cables - Lengthened & Possibly Rerouted

Steering System• No Changes

Change Drivers• Increased Loads• Increased Hyd Flow Demands• Changed Kinematics• Fuselage Stretch• Airplane Threats• Cost and/or Weight Savings

Component Installation• Valves - Possibly Relocated• Tubing - Possibly Rerouted

Overview – EE Subsystems

Relocate/Add Fuel Probes

48 amp-hour main and APU battery

Flight Deck –777 Dimmer Control Unit777 Master Dim & Test777 Style Window Heat

New integrated anticollision / position light assembly

Dual Taxi lights on nose gear basic

Revised weight and balance system

Main Deck – (Freighter Only)Add Main Deck Signaling SystemAdditional Cargo PDUsAdditional Lighting

Repackage engine electrical systemsAdapt electrical systems to interface with Digital Bleed Air Controls

90 KVA Generators(same as 747-400)

777/787 Service Light

787 LED Anticollision Lights

787 LED Position and Anticollision Lights

Lower Lobe (Fore & Aft)Additional LightingAdditional Cargo PDUs