RFP - 15M300-21-R-A370-0001.pdf

For the best experience, open this PDF portfolio in

Acrobat X or Adobe Reader X, or later.

Get Adobe Reader Now!

http://www.adobe.com/go/reader

BOEING PROPRIETARY

CAGE Code 81205

737 Next Generation Series Change of Operator Demonstration Profile

DOCUMENT NUMBER: RELEASE/REVISION: RELEASE/REVISION DATE:

D6-85394 REV F NOVEMBER 2018

For Document Release Use

CONTENT OWNER:

BT&E Flight Operations, Commercial Transport (TGXX)

All revisions to this document must be approved by the content owner before release.

The data contained herein is under the jurisdiction of the U.S. Department of Commerce and the U.S. Export Administration regulations, Title 15 (15CFR). Transfer of this data to a foreign person, within or from the United States, must be in accordance with the Export Administration Regulations (EAR). Diversion contrary to U.S. law is prohibited.

Controlled by ECCN: 9E991 Uncontrolled when printed.

737NG

Page 2 of 61 D6-85394 REV F

ECCN: 9E991

Document Information Original Release Date

21 March 2014 Contract or CDRL Number (if required)

Limitations

Authorization for Release

AUTHOR: 9R-TE-TGXX

Ted W. Grady Production Test Pilot, 737

Org. Number Date

AUTHOR: 9R-TE-TGXX

Timothy A. Lehmann Lead Production Pilot, 737

REVIEWER: 9R-TE-TGXX

Peter Seidel Lead Systems Operator, 737

REVIEWER: 9R-TE-TGXX

Ralph Chaffin Senior Systems Operator

APPROVAL: 9R-TE-TGXX

Todd White Chief Pilot, Production Flight Test

DOCUMENT RELEASE:

Copyright © 2018 Boeing. All rights reserved.

737NG

REV F D6-85394 Page 3 of 61

Table of Contents

1. Introduction

1.1 Purpose and Scope

1.2 Demonstration Procedures Preface

1.3 737NG Change of Operator Demonstration Flight Profile

2. Flight Deck Check Procedures

2.1 Preflight

2.2 Engine Start

2.3 After Engine Start

2.4 Takeoff

2.5 Climb

2.6 Cruise

2.7 Descent

2.8 Low Altitude

2.9 Approach and Landing

2.10 Taxi In and Shutdown

3. Passenger Cabin Check Procedures

3.1 General Information

3.2 E & E Compartment and Cargo Compartments

3.3 Cabin Interior

3.4 Galleys and Equipment

3.5 Emergency Systems and Equipment

3.6 Lavatories

3.7 Communications

3.8 Cabin Lighting

3.9 Audio Entertainment System (as installed)

3.10 Fuselage Doors and Associated Light

Acronyms

Revision Record

INTRODUCTION 737NG

Page 4 of 61 D6-85394 REV F

1. Introduction

1.1 Purpose and Scope

This document is intended for use when an airplane is being transferred from one operator to a new operator. It is not intended to be used in conjunction with any maintenance actions that may require a check flight. There are no mandatory checks associated with this profile. All checks outlined in this document are optional. In nearly all cases any discrepancy found will be discovered during the course of normal operations and not as a result of any checks outlined in this profile.

This profile is based on the standard Boeing Acceptance profile, but all checks that would degrade normal systems performance or would require the airplane to be flown outside of its normal operating envelope have been eliminated because these checks are inappropriate for this type of demonstration flight. In some cases, checks have been retained to demonstrate redundancies or to demonstrate back-up systems that are rarely exercised in the course of normal operations.

This profile is meant to be flown by any experienced captain and first officer. No special training is required and no additional crew members are required or recommended. In-flight checks of any cabin or galley systems will require at least one additional crew member. There is no intent to restrict the number of people who can be carried on this flight because all phases of flight are meant to replicate normal operations.

The preflight portion of this profile is more extensive than a standard preflight and includes several checks done on a newly built airplane. One notable exception is the elimination of the flight control checks, which are meant only for a first flight out of the factory. Again, all of these checks are optional. They are only included for reference should there be a desire to complete them.

The flight portion of this profile includes a climb to altitude, cruise, descent, low altitude block, and an approach to landing. It is recommended that this profile be performed in daylight conditions. It is assumed that all standard procedures outlined in the Flight Crew Operations Manual will be complied with. It is also assumed that all aircraft limitations will be complied with. Some unique checks have been retained but these checks are only intended to demonstrate normal or back-up systems operations.

In the event that any discrepancy requires maintenance action, it is not cause for another flight. Reflight is only necessary if required by the aircraft maintenance manual (AMM). There are no special tolerances associated with this flight. If there is any question regarding the proper operation of any system, refer to the AMM.

Check sheets are included for reference, and their use is optional. There is no requirement to record any data associated with this flight unless it is done to facilitate the resolution of a discrepancy.

737NG INTRODUCTION

REV F D6-85394 Page 5 of 61

1.2 Demonstration Procedures Preface

This document is divided into phase of flight rather than ATA systems. The sequence of check steps defined within constitutes a suggested and efficient flow for completing the acceptance check profile in a timely manner. Circumstances will occasionally dictate revising the schedule of checks due to system discrepancies, meteorological conditions, air traffic control, or any other reason deemed necessary by the pilot in command. Take care when revising the presented schedule because some checks must follow a rigid sequence. Thorough system knowledge aids flight crews in determining appropriate techniques. Boeing recommends following this sequence to the best ability possible to minimize any risk associated with revising the schedule of checks.

Each check procedure is contained within a titled table of two columns and numerous rows. Individual control activations are listed in the left, or Action column;

expected results, messages and lights are listed in the right, or Response column.

For example:

Standby Power

L IRS MODE selector ‘ALIGN’ ON DC, MASTER CAUTION and IRS lights illuminate.

ECS warning horn sounds (20 second delay).

Individual controls, switches and levers in the Action column are listed by the exact panel or control name, type of control, and desired position or action. Where the new position is a named control position, the position name is enclosed in single quotes exactly as specified on the appropriate panel. For example:

R PACK switch 'AUTO'

L APU GEN switch 'ON'

Lights illuminating in the Response column are indicated with BOLD capital letters, the bold letters being the appropriate nomenclature on the actual jewel light. Lights extinguishing are referenced by their name in plain capital letters. For example:

APU GEN OFF BUS light extinguishes.

No. 1 & 2 GEN OFF BUS lights illuminate No. 1 SOURCE OFF light extinguishes.

No. 2 TRANSFER BUS OFF light illuminates.

Special fonts are used in three other instances in the Response column and for one case in the Action column. The bolded word RECORD is used whenever data is to be recorded, if desired, by the operator. In the Action column, the nominal panel and grid location of all circuit breakers required to be temporarily opened for a

INTRODUCTION 737NG

Page 6 of 61 D6-85394 REV F check are indicated in LineDraw text. The location is not repeated for closing the same circuit breakers. For example:

ENG 1 & 2 HYD SOV c/bs OPEN

(P6-2:C18 & C19)

RECORD engine minimum idle parameters.

TOLERANCE: See appropriate Aircraft Manuals

Occasionally, there will be a note in parentheses in either the Action or Response columns. Its purpose is to assist users in understanding a procedure when no particular Response is appropriate. As well, if a procedure is continued onto the next page, a note in parentheses and italicized font is inserted as the last step in the Response column. For example:

MANUAL EXTENSION BYPASS DOOR close (Gear will not retract if DOOR is open).

Notes applicable to an entire check are listed numerically immediately under the check title. For example:

Maximum Delta P

Note: Do not exceed 9.10 psi cabin differential pressure.

If a procedure is model-specific, it is differentiated in the title as such. For example:

Air Conditioning (-800)

In chapter 1, Flight Deck Check Procedures, controls and switches are presumed to be left in the position they occupied at the conclusion of the previous check. This facilitates an efficient flow in completing this complex section. Preflight checks are normally performed only once after a change of operator. Discrepancies noted in preflight should be rectified immediately, prior to the flight, thus the preflight section contains fewer entry and exit procedures. However, take care using individual preflight checks in isolation. Such practice is not recommended.

System lights are accompanied by Master Caution and system annunciator logic. It is expected that flight crews will verify that the correct system annunciator light illuminates for the check condition and either cancel the master caution or wait until the system anomaly is removed in the check sequence. In Flight Deck Check Procedures, the Master Caution and the individual system annunciator lights are often detailed in the check body for their first appearance for a particular system.

Subsequent repetitions for the same system do not list the Master Caution and system annunciations.

737NG INTRODUCTION

REV F D6-85394 Page 7 of 61

1.3 737NG Change of Operator Demonstration Flight Profile

FLIGHT DECK – PREFLIGHT 737NG

Page 8 of 61 D6-85394 REV F

2. Flight Deck Check Procedures

2.1 Preflight

All flight deck controls and switches are in the normal dispatch configuration with external electrical powering the aircraft.

2.1.1 Cockpit Lighting

Operate interior lighting controls with windshield blackout panels installed:

Capt's & F/O's MAIN PANEL, BACKGROUND, AFDS FLOOD, OUTBD DU, INBD DU, UPPER DU, LOWER DU, WXR, AISLE

STAND FLOOD & PANEL, DOME, CIRCUIT

BREAKER FLOOD, OVERHEAD PANEL,

COMPASS LIGHT

Operate HUD Lighting Controls (As installed)

All lighting controls rotate freely and extinguish at the OFF position.

Floods dim appropriately and illuminate the appropriate panel correctly.

DUs reduce to minimum intensity.

Individual panels are balanced.

LIGHTS Switch 'TEST', 'DIM' & 'BRT' Ensure appropriate lights illuminate at the correct intensity, jewels are properly labeled, all bulbs function.

GRD PWR Switch 'OFF' Verify the following lights function:

Capt's Main Panel Capt's Display Select Panel Capt's Clock BACKGROUND Flood (fixed) Standby Instruments and Communication Engine Control Panel Fire Control Panel Cargo Fire Detector Fault Light Aisle Stand Equipment Powered by

STBY Power Emergency Exits, Dome

737NG FLIGHT DECK – PREFLIGHT

REV F D6-85394 Page 9 of 61

2.1.2 Standby Power

Note: Performing checks out of sequence may lead to inaccurate configurations and inability to verify proper operation.

BAT switch 'ON' STANDBY POWER switch 'AUTO' EMER EXIT LIGHTS switch 'ARMED'

GRD PWR switch 'OFF' Emergency Exit lights illuminate.

BAT DISCHARGE, MASTER CAUTION(s) &

ELEC

light illuminates (25 sec delay).

DC METERS selector 'BAT' & ‘AUX BAT’ Battery and AUX BAT are 22 to 26 VDC, nega amps.

DC & AC METERS selectors 'STBY PWR' Standby power is 22 to 26 VDC, 110 to 120 VAC & 390 to 410 Hz.

EMER EXIT LIGHTS switch 'OFF' Emergency Exit lights extinguish.

STANDBY POWER switch ‘OFF’ STANDBY PWR OFF, MASTER CAUTION(s) & ELEC lights illuminate.

DC METERS selector ‘BAT BUS' Battery is 22 to 26 VDC.

DC & AC METERS selectors 'STBY PWR' Verify AC & DC voltmeters indicate 0 volts.

Engine 1 & 2 Start levers 'CUTOFF' Verify ENG VALVE CLOSED & SPAR VALVE CLOSED lights are illuminated dim.

FUEL SHUTOFF VALVES BUS

c/b OPEN (P6-3:C6)

Verify engine SPAR VALVE operates on back up battery and charger system.

Engine 1 & 2 Start Levers 'IDLE' Verify SPAR VALVE CLOSED lights are extinguished & ENG VALVE CLOSED lights are illuminated bright.

Engine 1 & 2 Fire Warning switches PULL Verify SPAR VALVE CLOSED & ENG

Engine 1 & 2 Fire Warning switches RESET Verify SPAR VALVE CLOSED lights are extinguished & ENG VALVE CLOSED lights are illuminated bright.

Engine 1 & 2 Start Levers 'CUTOFF' Verify SPAR VALVE CLOSED & ENG

FUEL SHUTOFF VALVES BUS

c/b CLOSED (P6-3:C6)

Page 10 of 61 D6-85394 REV F

GROUND SERVICE switch 'ON' Normal equipment cooling blower runs.

Passenger cabin lights illuminate.

(cont. on next page)

DC METERS selector to 'BAT' & ‘AUX BAT’ Battery and AUX BAT are 24 to 28 VDC, positive amps.

Remove the ground power cord Ground Service switch trips off.

Battery is 22 to 26 VDC discharging.

Fwd and Aft Overhead GEAR green lights illuminated.

FUEL CROSSFEED selector 'OPEN' Crossfeed VALVE OPEN light illuminates bright and then dim.

FUEL CROSSFEED selector 'CLOSE' Crossfeed VALVE OPEN light illuminates bright and then extinguishes.

L IRS MODE selector 'ATT' ON DC, MASTER CAUTION(s) & IRS lights illuminate. ECS warning horn sounds (20 sec delay).

STANDBY PWR OFF light extinguishes.

L IRS ON DC light extinguishes.

ECS warning horn stops.

Capt's OUTBD, Capt’s INBD (if FMC is powered) & CTR UPPER displays illuminate within 3 minutes (1.5 minutes norm).

WING ANTI-ICE switch ‘ON’ Wing anti-ice L&R VALVE OPEN lights illuminate.

PSEU interface to air mode

(FWD E BAY)

'CDS FAULT' message changes to 'DSPLY SOURCE' when in air mode.

DC & AC METERS selector 'STBY PWR' Standby power is 22 to 26 VDC, 110 to 120 VAC, 390 to 410 Hz.

REV F D6-85394 Page 11 of 61

Standby Power, cont.

Equipment on Standby Power (others, as installed)

Verify the following items: (As installed) Capt's Clock (illuminated)

Capt's OUTBD DU

Interphone and PA

VHF Comm 1, NAV 1 Control

ADF 1, IFF No. 1, ATC No. 1

Capt's INBOARD DU

Capt's Display Select Panel

Engine Control Panel

CTR UPPER DU

Fuel Quantity Indicators

Cargo Fire Detector Fault Light

Capt's EFIS Control Panel

Pressurization, Manual Mode

Standby ADI/ILS

Standby Altimeter Vibrator

Standby Compass and Light

Capt's Audio Control Panel

F/O Clock (no light)

Enter a heading on the IRS Control Panel Verify that the Capt’s flight instruments and Standby RMI align to the selection. (30 seconds delay)

PSEU interface to ground mode 'DSPLY SOURCE' message changes to

'CDS FAULT'

STANDBY POWER switch 'BAT' Standby powered equipment remains operative.

L IRS MODE selector 'OFF'

Page 12 of 61 D6-85394 REV F

2.1.3 ENG/APU Overheat and Fire Warning

Note: Do not rotate fire switches. Rotating fire switches discharges fire extinguishers.

ENG 1 & 2 OVHT DET switches LOOP 'A' FAULT/INOP AND OVHT/FIRE TEST switch hold at 'FAULT/INOP' until responses are verified

FAULT, APU DET INOP, MASTER

CAUTION(s), & OVHT/DET lights illuminate.

hold at 'OVHT/FIRE' until responses are verified

Master FIRE WARN, MASTER CAUTION(s), & OVHT/DET lights illuminate.

ENGINE 1, ENGINE 2 & APU FIRE

WARNING switches illuminate.

ENG 1 OVERHEAT & ENG 2 OVERHEAT

lights illuminate.

The fire warning bell sounds in the cockpit.

The APU fire warning horn sounds in the wheel well.

The APU FIRE warning light flashes in the wheel well.

Capt's Master FIRE WARN switch PUSH Verify that the FIRE WARN lights and bell cancel.

The APU fire warning horn cancels and the APU FIRE warning light illuminates steady in the wheel well.

release

ENG 1 & 2 OVHT DET switches LOOP 'B' hold at 'FAULT/INOP'

Same indications as above.

hold at 'OVHT/FIRE'

F/O's Master FIRE WARN switch PUSH Same indications as above.

ENG 1 & 2 OVHT DET switch 'NORMAL' hold at 'FAULT/INOP' hold at 'OVHT/FIRE'

BELL CUTOUT switch PUSH Same indications as above.

Engine 1 & 2 and APU Fire Warning switches PULL

Verify locks are released.

REV F D6-85394 Page 13 of 61

ENG/APU Overheat and Fire Warning, cont.

Engine 1 & 2 and APU Fire Warning RESET ENGINES EXT TEST switch hold at '1' L, R & APU extinguisher test lights

ENGINES EXT TEST switch hold at '2' L, R & APU extinguisher test lights

2.1.4 APU Start

Note: The start cycle may take as long as 120 seconds.

All FUEL PUMP switches 'ON' DC METERS selector 'BAT' & AUX 'BAT' (if equipped) AC METERS selector 'APU GEN' BUS TRANSFER switch 'OFF' GEN 1, GEN 2 & APU GEN switches 'ON'

All WINDOW HEAT & PROBE HEAT switches

'ON'

All HYD PUMP switches 'ON'

(Resets IDG fields)

APU switch 'START' and release to 'ON' APU initiates a start sequence.

Verify AUX 'BAT' indicates 0 amps. (As installed) Monitor starter engage and cutout on DC ammeter.

APU generator output at idle is 110 to 120 VAC, and 390 to 410 Hz.

Verify the following lights are illuminated:

Left & Right TRANSFER BUS OFF, SOURCE OFF, GEN OFF BUS, and APU

GEN OFF BUS.

Page 14 of 61 D6-85394 REV F

2.1.5 Normal Electrical Power

Left APU GEN switch 'ON' APU GEN OFF BUS light is extinguished.

Left GEN OFF BUS light illuminated.

Left SOURCE OFF & TRANSFER BUS OFF lights extinguished.

Right TRANSFER BUS OFF, SOURCE OFF and Right GEN OFF BUS lights are illuminated.

Single Bat Config: 'BAT,' 22 to 26 VDC, negative amps.

Dual BAT Config: ‘BAT’ and ‘AUX BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

TR 1 is 22 to 30 VDC, positive amps.

TR 2 & 3, 0 VDC, 0 amps .

B Electric Pump LOW PRESSURE light is extinguished.

BUS TRANSFER switch 'AUTO' Right TRANSFER BUS OFF light is extinguished.

TR 3, 2 & 1, 22 to 30 VDC.

Battery Charger starts a charge cycle.

Single Bat Config: ‘BAT,’ 24 to 32 VDC, positive amps.

Dual Bat Config: ‘BAT’ and ‘AUX BAT,’ 24 to 32 VDC, Right APU GEN switch 'ON' Right SOURCE OFF light is extinguished. All buses and equipment are powered.

BUS TRANSFER switch 'OFF' No change should occur.

Left APU GEN switch 'OFF' Left TRANSFER BUS OFF & SOURCE OFF, MASTER CAUTION(s) and ELEC light illuminate. A Electric Pump LOW PRESSURE light is extinguished.

Single Bat Config: ‘BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

Dual Bat Config: ‘BAT’ and ‘AUX BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

TR 1, 0 VDC, 0 amps.

TR 2 & 3, 22 to 30 VDC with positive amps.

STANDBY POWER switch 'BAT' Single Bat Config: ‘BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

Dual Bat Config: ‘BAT’ and ‘AUX BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

REV F D6-85394 Page 15 of 61

Normal Electrical Power, cont.

BUS TRANSFER switch 'AUTO' Left TRANSFER BUS OFF light is extinguished.

TR 1 is 22 to 30 VDC, positive amps.

Single Bat Config: ‘BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

Dual Bat Config: ‘BAT’ and ‘AUX BAT,’ 24 to 28 VDC, and depending on the battery state-of-charge, the amp display may show either positive or negative amps.

STANDBY POWER switch 'AUTO' STANDBY PWR OFF light is extinguished.

Battery Charger starts a charge cycle.

Single Bat Config: ‘BAT,’ 24 to 32 VDC, positive amps.

Dual Bat Config: ‘BAT’ and ‘AUX BAT,’ 24 to 32 VDC, Left APU GEN switch 'ON' Left SOURCE OFF light is extinguished.

All PROBE HEAT switches 'AUTO' (Prevents premature wear) If ELEC discrete light is illuminated on the Electrical Metering Panel:

AC & DC METERS selector switches 'TEST' MAINT switch PRESS and RELEASE

MAINT switch PRESS and HOLD Verify ELEC discrete light and Fault Codes extinguish.

Turn both IRS mode selectors to

'NAV'

2.1.6 CAB/UTIL & IFE/PASS Seat

CAB/UTL/ Power switch 'OFF' Verify galley buses shed.

CAB/UTL/ Power switch 'ON' Verify galley buses are restored.

IFE/PASS SEAT power switch 'OFF' Verify power is removed from components of the passenger seats and in-flight entertainment systems (as installed).

IFE/PASS SEAT power switch 'ON' Verify power is restored from components of the passenger seats and in-flight entertainment systems (as installed).

Page 16 of 61 D6-85394 REV F

2.1.7 Wheel Well Fire Warning

FAULT/INOP & OVHT/FIRE TEST

switch to OVHT/FIRE

Verify WHEEL WELL fire warning lights illuminate.

Master FIRE WARN lights illuminate.

Fire warning bell sounds.

CAPT’s master FIRE WARN switch push.

Verify that the FIRE WARN lights and bell cancel.

2.1.8 Cargo Fire

FWD & AFT DET SELECT switches 'A'

Cargo fire TEST switch press and hold until responses are verified

Master FIRE WARN lights illuminate.

Fire warning bell sounds in the cockpit.

FWD & AFT extinguisher lights illuminate.

ARMED FWD, ARMED AFT & DISCH lights

Capt’s Master FIRE WARN switch PUSH Verify that the FIRE WARN lights and bell

Cargo fire TEST switch release

FWD & AFT DET SELECT switches 'B'

Cargo fire TEST switch PRESS and HOLD until responses are verified

F/O’s Master FIRE WARN switch PUSH Verify that the FIRE WARN lights and bell

Cargo fire TEST switch release

FWD & AFT DET SELECT switches 'NORM'

Cargo fire TEST switch PRESS and HOLD until responses are verified

BELL CUTOUT switch PUSH Verify that the FIRE WARN lights and bell

REV F D6-85394 Page 17 of 61

2.1.9 Fuel Pumps & Auto Shut Off

Ensure all Fuel Boost Pump Switches ‘ON’ All LOW PRESSURE lights extinguished.

Press the MASTER CAUTION(S) ‘RECALL’ Master Caution FUEL annunciation extinguished.

Press the MASTER CAUTION(s) ‘RESET’ Master Caution annunciations extinguish.

Push and Hold the LEFT FUEL TEST AUTO SHUTOFF switch to the ‘AUTO OFF’ position

Left pump shuts OFF and LOW PRESSURE light illuminates after 15 +/- 2 seconds.

Release the LEFT FUEL TEST AUTO SHUTOFF switch

MASTER CAUTION(s) AND FUEL annunciation illuminate 10 +/- 2 seconds after the LOW PRESSURE light illuminates.

Position the Left Center Fuel Tank Boost Pump to ‘OFF’ and back ‘ON’ (resets the AUTO OFF function)

LOW PRESSURE light illuminates briefly and remains extinguished when pump is cycled ON.

Press the MASTER CAUTION(s) ‘RECALL’ Master Caution FUEL annunciation extinguished.

Press the MASTER CAUTION(s) ‘RESET’ Master Caution annunciations extinguish.

Push and Hold the RIGHT FUEL TEST AUTO SHUTOFF switch to the ‘AUTO OFF’ position

Right Pump shuts OFF and the LOW PRESSURE light illuminates after 15 +/- 2 seconds.

Release the RIGHT FUEL TEST AUTO SHUTOFF switch

MASTER CAUTION(s) AND FUEL annunciation illuminate 10 +/- 2 seconds after the LOW PRESSURE light illuminates.

Position the Right Center Fuel Tank Boost Pump to ‘OFF’ and back ‘ON’ (resets the AUTO OFF function)

LOW PRESSURE lights illuminate briefly and remain extinguished when pumps are cycled ON.

Press the MASTER CAUTION(s) ‘RESET’ Resets the Master Caution.

Main Tank 1 AFT FUEL PUMP switch ‘OFF’ 1 AFT LOW PRESSURE light illuminates.

Press the MASTER CAUTION(s) ‘RECALL’ MASTER CAUTION(s) AND FUEL annunciation

Main Tank 1 FWD FUEL PUMP switch ‘OFF’ 1 FWD LOW PRESSURE, MASTER CAUTION(s), AND FUEL lights illuminate.

Main Tank 1 FWD AND 1 AFT FUEL PUMP switches ‘ON’

1 FWD AND 1 AFT LOW PRESSURE, MASTER

CAUTION(s) and FUEL lights extinguish.

Main Tank 2 AFT FUEL PUMP switch ‘OFF’ 2 AFT LOW PRESSURE light illuminates.

Press the MASTER CAUTION(s) ‘RECALL’ MASTER CAUTION(s) AND FUEL annunciation

Main Tank 2 FWD FUEL PUMP switch ‘OFF’ 2 FWD LOW PRESSURE, MASTER CAUTION(s), AND FUEL lights illuminate.

Main Tank 2 FWD AND 2 AFT FUEL PUMP switches ‘ON’

2 FWD AND 2 AFT LOW PRESSURE, MASTER

CAUTION(s), AND FUEL lights extinguish.

Page 18 of 61 D6-85394 REV F

2.1.10 Hydraulics

ELEC 2 & ELEC 1 HYD PUMP switches

'OFF'

Electric 2 & 1 hydraulic pump LOW PRESSURE, MASTER CAUTION(s), HYD and FLT CONT lights illuminate. System A & B hydraulic pressures decay below 100 psi.

2.1.11 Brake Accumulator

Ensure airplane is properly chocked.

Hydraulic BRAKE PRESSURE checked Pressure is 2800 PSI or greater.

PARKING BRAKE release PARK BRAKE light extinguishes.

Pump the brake pedals until the brake accumulator pressure no longer decreases

Verify brake pressure does not drop below accumulator precharge limit.

ELEC 2 HYD PUMP switch 'ON' Verify A system hydraulic pressure increases to nominal but brake accumulator pressure remains as above.

ELEC 1 HYD PUMP switch 'ON' Verify B system hydraulic pressure increases to nominal and brake accumulator pressure rises with B system.

PARKING BRAKE ‘SET’ PARK BRAKE light illuminates.

PARKING BRAKE ‘RELEASE’ and ‘SET’ from opposite side

PARK BRAKE light extinguishes and illuminates.

2.1.12 Aspirated TAT (as installed)

PROBE HEAT A & B switches 'OFF' APU BLEED switch 'OFF'

TAT TEST switch push Verify Total Air Temperature (TAT) indication increases and TEMP PROBE light extinguishes.

TAT TEST switch released TEMP PROBE light illuminates.

APU BLEED switch 'ON' Verify TAT indication decreases.

APU BLEED switch as required.

REV F D6-85394 Page 19 of 61

2.1.13 Pneumatics

L & R PACK switches 'OFF' Engine 1, 2 & APU BLEED switches 'OFF'

ISOLATION VALVE switch 'AUTO' L & R duct pressures within tolerance. Refer to

AMM.

APU BLEED switch 'ON' L & R duct pressures within tolerance. Refer to

APU BLEED switch 'OFF' L & R duct pressures bleed off slowly.

Engine 1 & APU BLEED switches 'ON'

DUAL BLEED, MASTER CAUTION(s) & AIR COND lights illuminate.

Engine 1 BLEED switch 'OFF' DUAL BLEED, MASTER CAUTION(s) & AIR COND lights extinguish.

Engine 2 BLEED switch 'ON' DUAL BLEED, MASTER CAUTION(s) & AIR COND lights illuminate.

Engine 1 BLEED switch 'ON'

Right pack operates and L & R duct pressures are within tolerance of each other. Refer to

ISOLATION VALVE switch 'CLOSE' Right pack shuts down and R duct pressure decreases.

ISOLATION VALVE switch 'AUTO' R duct pressure increases.

L PACK switch 'AUTO' Left pack operates Right pack shuts down and R duct pressure decreases.

ISOLATION VALVE switch 'OPEN' Both packs operate, and L & R duct pressures are normal and approximately equal.

MASTER CAUTION lights press MASTER CAUTION(s) & system annunciator lights extinguish.

OVHT TEST switch PUSH and HOLD Momentarily.

L & R WING-BODY OVERHEAT, MASTER

CAUTION(s) and AIR COND lights illuminate.

Page 20 of 61 D6-85394 REV F

2.1.14 Air Conditioning (-600/-700/700C)

AIR TEMP source selector 'SUPPLY DUCT'

RECIRC FAN switch 'OFF'

GASPER FAN switch (As installed) 'OFF'

L & R PACK switches 'AUTO'

Left & Right RAM DOOR FULL OPEN lights are illuminated.

CONT CABIN temperature selector to full

AUTO 'WARM'

CONT CABIN AIR MIX VALVE moves toward HOT.

SUPPLY DUCT temperature increases.

DUCT OVERHEAT light does not illuminate.

CONT CABIN temperature selector to full

AUTO 'COOL'

CONT CABIN AIR MIX VALVE moves toward COLD.

SUPPLY DUCT temperature decreases.

L PACK switch 'OFF'

PASS CABIN temperature selector to full

AUTO 'WARM'

PASS CABIN AIR MIX VALVE moves toward HOT.

SUPPLY DUCT temperature increases

DUCT OVERHEAT light does not illuminate.

PASS CABIN temperature selector to full

AUTO 'COOL'

PASS CABIN AIR MIX VALVE moves toward COLD.

SUPPLY DUCT temperature decreases .

PASS CABIN temperature selector toggle

MANUAL 'WARM' until the PASS CABIN AIR

MIX VALVE is at the 12 o'clock position

SUPPLY DUCT temperature increases slowly until the right DUCT OVERHEAT light illuminates at appropriate temperature. Refer to AMM.

MASTER CAUTION(s) & AIR COND lights illuminate.

RECORD the duct overheat temperature.

PASS CABIN AIR MIX VALVE moves COLD.

PASS CABIN temperature selector ‘AUTO’

TRIP RESET switch PUSH Right DUCT OVERHEAT light extinguishes.

R PACK switch 'OFF' L PACK switch 'AUTO'

CONT CABIN temperature selector toggle

MANUAL 'WARM' until an overheat condition occurs

Left DUCT OVERHEAT, MASTER CAUTION(s), & AIR COND lights illuminate.

CONT CABIN AIR MIX VALVE moves to COLD.

CONT CABIN temp selector ‘AUTO’

TRIP RESET switch PUSH Left DUCT OVERHEAT light extinguishes.

RECIRC FAN switch 'AUTO'

GASPER FAN switch 'ON' (As installed)

REV F D6-85394 Page 21 of 61

2.1.15 Recirc & Gasper Fans (-600/700/700C) (as installed)

AC meters selector switch 'APU GEN' RECIRC FAN switch 'OFF' AC AMMETER indicates a decrease in amps.

RECIRC FAN switch 'AUTO' AC AMMETER indicates an increase in amps.

2.1.16 Air Conditioning (-800/900ER)

Note: Press Master Caution Recall and verify there are no ZONE TEMPERATURE or PACK lights illuminated on the Overhead Panel.

AIR TEMP source selector SUPPLY DUCT

‘CONT CAB’

TRIM AIR switch 'ON' L & R RECIRC FAN switches ‘OFF’ L PACK switch 'HIGH'

R PACK switch 'OFF' Left & Right RAM DOOR FULL OPEN lights are illuminated.

CONT CAB temperature selector to full

AUTO 'W'

FWD CAB & AFT CAB temperature selectors to full AUTO 'C'

SUPPLY DUCT CONT CAB temperature increases, not to exceed max value. Refer to AMM ZONE TEMP light does not illuminate.

AUTO 'C'

FWD CAB temperature selector to full

SUPPLY DUCT FWD CAB temperature

ZONE TEMP light does not illuminate.

FWD CAB temperature selector to full

SUPPLY DUCT FWD CAB temperature

AFT CAB temperature selector to full

SUPPLY DUCT AFT CAB temperature

AFT CAB temperature selector to full

SUPPLY DUCT AFT CAB temperature

R PACK switch 'HIGH'

Page 22 of 61 D6-85394 REV F

Air Conditioning (-800/900ER), cont.

ISOLATION VALVE switch 'OPEN' L & R RECIRC FAN switches 'AUTO'

AIR TEMP source selector 'L' & 'R' PACK Verify both pack temperatures stabilize no lower than min value and are approximately equal.

Refer to AMM.

TRIM AIR switch 'OFF' CONT CAB temperature selector full

SUPPLY DUCT CONT CAB & L PACK

temperature increases.

SUPPLY DUCT CONT CAB & L PACK

temperature decreases.

FWD & AFT CAB temperature selectors full

SUPPLY DUCT FWD & AFT and R PACK temperature increases.

FWD & AFT CAB temperature selectors full

SUPPLY DUCT FWD & AFT and R PACK temperature decreases.

ISOLATION VALVE switch 'AUTO' TRIM AIR switch 'ON'

2.1.17 Recirc Fans (-800/-900ER)

L RECIRC FAN switch 'OFF' AC AMMETER indicates a decrease in amps.

L RECIRC FAN switch 'AUTO' AC AMMETER indicates an increase in amps.

R RECIRC FAN switch 'OFF' AC AMMETER indicates a decrease in amps.

R RECIRC FAN switch 'AUTO' AC AMMETER indicates an increase in amps.

ISOLATION VALVE switch ‘OPEN’ L & R PACK switch 'HIGH' AC AMMETER indicates a decrease in amps.

(L RECIRC FAN stops)

REV F D6-85394 Page 23 of 61

2.1.18 Pack High Flow

FMCS DISCRETES page 1/4 on the CDU

Verify 1, 2 and APU bleed switches are on

L & R PACK switches 'OFF' Verify L & R ECS PACK indicate OFF/HI

L PACK switch 'HIGH' Verify that the left pack has regulated to high flow by:

An increase in cockpit airflow Left ECS PACK H/L discrete HI

L PACK switch 'AUTO' Verify that the left pack has regulated to low flow by:

A decrease in cockpit airflow Left ECS PACK H/L discrete LO

R PACK switch 'HIGH' Verify that the right pack has regulated to high

An increase in cockpit airflow Right ECS PACK H/L discrete HI

R PACK switch 'AUTO' Verify that the right pack has regulated to low

A decrease in cockpit airflow Right ECS PACK H/L discrete LO

L PACK switch 'AUTO' Verify that the left pack has regulated to low flow by:

Left ECS PACK H/L discrete LO

Engine 1 BLEED switch 'OFF' Left and Right ECS PACK H/L discrete LO

Engine 2 BLEED switch 'OFF' Left and Right ECS PACK H/L discrete HI

Engine 1 BLEED switch 'ON' Left and Right ECS PACK H/L discrete LO

Engine 2 BLEED switch 'ON'

2.1.19 Equipment Cooling

EQUIP COOLING SUPPLY & EXHAUST

switches 'NORM' switches 'ALTN'

Verify proper equipment cooling with the alternate supply and exhaust fans for several minutes.

switches 'NORM'

Page 24 of 61 D6-85394 REV F

2.1.20 Pressurization

Note: A cabin exterior door must be open for this check if an AC PACK is operating.

#1 and #2 Engine Bleed Switches OFF

Pressurization Mode selector 'MAN' MANUAL light illuminates.

Outflow VALVE switch hold 'CLOSE' Verify valve closes.

AUTO 2 c/b OPEN/CLOSE (P6-4:F5) Resets Auto 1 as the controlling system.

Pressurization Mode selector 'AUTO' MANUAL light extinguishes.

The outflow valve moves towards open.

AUTO 1 c/b OPEN (P6-4:F3) The outflow valve stops.

AUTO FAIL, ALTN, MASTER CAUTION(s) and AIR COND lights illuminate.

After a few seconds the outflow valve continues towards open.

Pressurization Mode selector 'ALTN' AUTO FAIL, MASTER CAUTION(s) and AIR

COND lights extinguish.

ALTN light extinguishes.

AUTO 2 c/b OPEN

AUTO 1 c/b CLOSE

AUTO 2 c/b CLOSE

Outflow VALVE switch hold 'CLOSE' Verify valve closes.

Pressurization Mode selector 'ALTN' The outflow valve moves towards open.

MANUAL light extinguishes.

ALTN light illuminates.

AUTO 2 c/b OPEN The outflow valve stops momentarily, then continues towards open.

ALTN light extinguishes.

Outflow VALVE switch ‘CLOSE/OPEN’ Verify that the outflow valve moves through the full range of full closed to full open.

AUTO 2 c/b CLOSE

Pressurization Mode selector 'AUTO' All pressurization lights are extinguished.

REV F D6-85394 Page 25 of 61

2.1.21 Window Heat

Note 1: Do not select PWR TEST when all green ON lights are illuminated.

Note 2: ON lights for windows in direct sunlight may not be illuminated.

Note 3: ON lights illuminating may be replaced by OFF lights extinguishing, as installed.

All WINDOW HEAT switches 'ON' Verify all window heat ON lights illuminate.

If any window heat ON lights are extinguished:

WINDOW HEAT TEST switch 'PWR TEST'

All window heat ON lights are illuminated.

WINDOW HEAT TEST switch 'OVHT' All window heat OVERHEAT lights

All window heat ON lights extinguish within

70 sec.

All WINDOW HEAT switches 'OFF' All window heat OVERHEAT lights extinguish.

All WINDOW HEAT switches 'ON'

2.1.22 Wing Anti-Ice

WING ANTI-ICE switch 'ON' Wing anti-ice L & R VALVE OPEN lights illuminate bright then dim. Duct pressure

NOTE: A DUCT OVERTEMPERATURE condition may occur if there is a delay between the next two steps.

No. 1 FORWARD THRUST lever advance towards 'INCREASE THRUST'

At approximately 30 degrees above idle:

Wing anti-ice L & R VALVE OPEN lights illuminate bright.

Duct pressure increases

No. 1 FORWARD THRUST lever retard illuminate dim.

Duct pressure decreases.

Repeat for No. 2 FORWARD THRUST lever (continued on next page)

Page 26 of 61 D6-85394 REV F

Wing Anti-Ice, cont.

PSEU interface to air mode

(LOCATION : FWD E BAY)

WING ANTI-ICE switch magnetically releases to OFF.

PSEU interface to ground mode

2.1.23 Instrument Switching

(Display) CAPT EFIS CONT PANEL c/b

OPEN

(P18-2:D1)

DISPLAYS CONTROL PANEL & ALT flags illuminate amber and altimeter display blanks on Capt's screens.

DISPLAYS CONTROL PANEL switch

'BOTH ON 2'

extinguish and altimeter display returns.

Verify F/O's EFIS Control Panel controls all DUs and Capt's EFIS Control Panel has no effect.

(Display) CAPT EFIS CONT PANEL c/b CLOSE

DISPLAYS CONTROL PANEL

switch 'NORMAL'

CDS screens return to normal.

(Display) F/O EFIS CONT PANEL c/b OPEN (P6-1:E13) illuminate amber and altimeter display blanks on F/O's screens.

DISPLAYS CONTROL PANEL switch

‘BOTH ON 1’

extinguish and altimeter display returns.

Verify Capt’s EFIS Control Panel controls all Dus and F/O’s EFIS Control Panel has no effect.

(Display) F/O EFIS CONT PANEL c/b

CLOSE

DISPLAYS CONTROL PANEL

switch ‘NORMAL’

CDS screens return to normal.

REV F D6-85394 Page 27 of 61

2.1.24 FMC Switching (dual FMC aircraft)

Select ‘MAP’ Mode on the both EFIS Control Panels

Position the FMC Source Select Switch to ‘Both on L’

The left and right map displays will annunciate

FMC L.

to ‘Both on R’

The left and right map displays will annunciate

FMC R.

to ‘NORMAL’

The FMC L and R annunciations should be displayed on the appropriate map display.

2.1.25 IRS Switching

Note: The mock test pattern consists of the following:

• 45° Roll

• 5° Pitch Up

• 15° Magnetic Heading

• -600 FPM Vertical Speed

• 10,000 Feet Altitude

• 137 Knots Airspeed

System DSPL selector 'L' DSPL SEL switch hold in 'TEST'

Overspeed warning clacker sounds.

Capt’s instruments display mock test pattern then flag.

NAVIGATION IRS switch 'BOTH ON R'

Capt’s displays are restored.

INSTR SWITCH annunciates.

DSPL SEL switch release NAVIGATION IRS switch 'NORMAL'

CDS displays return to normal.

INSTR SWITCH annunciation is removed.

System DSPL selector 'R' DSPL SEL switch hold in 'TEST'

Overspeed warning clacker sounds.

F/O’s instruments display mock test pattern then flag.

NAVIGATION IRS switch 'BOTH ON L'

F/O's displays are restored.

INSTR SWITCH annunciates.

DSPL SEL switch release NAVIGATION IRS switch 'NORMAL'

CDS displays return to normal.

INSTR SWITCH annunciation is removed.

Page 28 of 61 D6-85394 REV F

2.1.26 VHF NAV Switching

Tune VHF NAV 1 to an ILS frequency and ensure VHF NAV 2 is tuned to a VOR

G/S & LOC deviation scales or flags appear on Capt's PFD.

NAVIGATION VHF NAV switch 'BOTH ON 1' G/S & LOC deviation scales or flags appear on both PFDs.

NAVIGATION VHF NAV switch 'BOTH ON 2' G/S & LOC deviation scales or flags disappear from PFDs.

NAVIGATION VHF NAV switch 'NORMAL' G/S & LOC deviation scales or flags appear on Capt's PFD.

Tune VHF NAVs as desired

2.1.27 Display Select Panel

MAIN PANEL DUs & LOWER DU switches select all positions in turn

Verify operation of the Capt's & F/O's controls.

2.1.28 Engine Display Control Panel

N1 SET switch select '2', '1', and 'BOTH' in turn

Verify inner switch manually controls N1 bug on the appropriate N1 engine gauge.

N1 SET outer switch 'AUTO' FMC provides the N1 reference and the inner switch has no effect.

SPD REF outer switch 'V1', 'VR', 'WT', and '<'

(NOTE : VREF is inhibited on ground)

Verify inner switch manually controls the appropriate speed bug or weight input on the

MASIs.

SPD REF outer switch 'AUTO' FMC provides the reference speeds and the inner switch has no effect.

FUEL FLOW switch 'USED' FF/FU digital readout displays fuel used since last reset for 10 seconds then reverts to fuel flow rate.

FUEL FLOW switch 'RESET' Fuel used value resets to 0.00.

MFD switch 'ENG', 'SYS' (As installed) Verify correct selection of MFD indication.

MFD Cancel/Recall ‘C/R’ switch (As installed)

Push (once) Cancels autoland advisory messages.

Push (again) Recalls autoland advisory messages.

REV F D6-85394 Page 29 of 61

2.1.29 Alternate VMO/MMO Ground Check Procedure Gear Down

Dispatch

Note: Ensure aircraft is configured with flaps up prior to conducting this procedure. If aircraft is configured with flaps “out-of-up,” this lower placard speed will be displayed on the EFIS/MAP airspeed indicator, preventing display of the Alternate VMO speed indication. This does not apply to PFD/ND displays.

Select ‘INIT/REF’ on CDU

Select 6L <INDEX INIT/REF page

Select 6R <MAINT MAINT BITE INDEX page

FMC switch to ‘BOTH ON L’ (On dual FMC equipped aircraft only)

Select 2L <DFCS DFCS BITE TEST MAIN MENU

Select 4L <EXTENDED MAINTENANCE EXTENDED MAINTENANCE page

Select 4L <SENSOR VALUES SENSOR VALUES

Select 2L <DIGITAL SIGNALS DIGITAL INPUT BUS page 1/2

Select 2L <ADIRU-LCL

(ADC-BUS)

ADIRU (ADC)-LCL INPUT BUS page ½:

L-ADIRU DATA TO L-FCC (A)

R-ADIRU DATA TO R-FCC (B)

Select ‘NEXT PAGE’ on CDU ADIRU (ADC)-LCL INPUT BUS page 2/2

Select 3L <MAX ALLW A/S (207)

Select VMO/MMO switch to ‘ALTN’ (forward equipment bay, E5-2 panel)

Verify MAX ALLOWABLE AIRSPEED

(207/KTS)

A= 270 B= 270 Verify airspeed tape RED BARBER POLE displays 270 KIAS. (EFIS Map aircraft only)

Select VMO/MMO switch to ‘NORMAL’ (forward equipment bay, E5-2 panel)

Verify MAX ALLOWABLE AIRSPEED

(207/KTS)

A = 340 B = 340 Verify airspeed tape RED BARBER POLE displays 320 KIAS. (gear down placard speed).

(EFIS Map aircraft only)

Select 6L <EXIT

Return FMC switch to ‘NORMAL’ (On dual FMC equipped aircraft only)

Page 30 of 61 D6-85394 REV F

2.1.30 Engine EEC

Engine Start levers 'CUTOFF'

ENGINE 1 & 2 START switches 'CONT' Verify EGT, FF/FU, OIL PRESS and OIL

TEMP displays unblank.

Verify ENGINE CONTROL & FILTER

BYPASS lights remain extinguished.

ENGINE 1 & 2 START switches 'OFF' Verify EGT, FF/FU, OIL PRESS, and OIL

TEMP displays blank.

2.1.31 Reinforced Cockpit Door

Note: After completion on the Flight Deck Door Access System checks, perform an operational check of the Flight Deck Door Deadbolt Security System in accordance with the door placard.

Position personnel on both sides of the flight deck door

Flight Deck Access System switch

‘NORM’

Press to test the AUTO UNLK and

LOCK FAIL indicators

Close flight deck door Verify the flight deck door can not be opened from the cabin side and that access light door locked

(RED) is illuminated.

Enter 3 to 8 digit emergency numeric access code

Verify the flight deck chime sounds and illumination of the amber AUTO UNLK light.

Select ‘UNLK’ position on the FLT DK

DOOR selector

Verify the flight deck chime stops, AUTO UNLK light extinguished and the access light door unlocked

(GREEN) is illuminated.

Flt Deck Door is unlocked.

Close Flt Deck Door

Enter 3 to 8 digit emergency numeric access code

Verify the flight deck chime sounds and illumination of the amber AUTO UNLK light.

Select ‘DENY’ position on the FLT DK

DOOR selector

Verify the flight deck chime stops, AUTO UNLK light is extinguished, door does not unlock and door locked access light (RED) remains illuminated.

REV F D6-85394 Page 31 of 61

2.1.32 Communication

Check all O2 masks (As installed) Functions properly in Normal & Alternate.

Mask Mic functions properly in I/C and PA.

The mask can be extracted and donned with one hand and in one smooth motion.

Check all boom mics (As installed) Transmission and reception are clear.

2.1.33 Inertial Reference System (IRS)

Perform normal preflight Confirm all IRS functions are operative using normal preflight items.

2.1.34 Navigation

Capt's & F/O’s EFIS CONTROL PANELs Verify for proper operation.

DH & LRRA display Verify the selected DH is annunciated and the radio altimeter reads appropriately. Refer to

VOR/ILS/DME/ATC TRANSPONDER Perform appropriate self-tests as installed.

ADF Verify proper operation.

WX RADAR Verify test pattern.

Page 32 of 61 D6-85394 REV F

2.1.35 Autopilot Disconnects

Note: For all disconnect conditions A/P P/RST lights flash red and an aural warning sounds. (Reset)

A & B HYD PUMP switches 'ON'

DISENGAGE bar push

A/P ENGAGE switches CMD A, CMD B, CWS A & CWS B push in turn

FCCs will not engage.

DISENGAGE bar reset

A/P ENGAGE switches CMD A, CMD B, CWS A & CWS B push in turn, disengaging each with the Capt's & F/O's control column disengage switches

Check that all FCCs disconnect with single push from both pilot's columns.

Double push silences aural WARNING &

AUTOPILOT DISENGAGE lights extinguish.

Repeat using Capt's & F/O's control column electric trim switches to disconnect

Check that FCCs disconnect and visual and aural warnings occur as above.

Repeat using STAB TRIM AUTOPILOT

CUTOUT switch to 'CUTOUT'

Check that FCCs disconnect and visual and aural warnings occur as above.

CMD A switch push

ELEC 2 HYD PUMP switch 'OFF' After System A hydraulic pressure bleeds off then A FCC disconnects in approximately 5 seconds.

Repeat last two steps for CMD B & ELEC 1

HYD PUMP switches

After System B hydraulic pressure bleeds off then B FCC disconnects in approximately 5 seconds.

2.1.36 Exterior Lights

Select all exterior lights 'ON’ (As installed)

EMER EXIT, LANDING, L & R RUNWAY

TURNOFF, TAXI, LOGO, STROBE,

POSITION, ANTI-COLLISION, WING, WHEEL

WELL

Ground observer responds by reporting that a light is illuminated.

(NOTE: Attempt to limit LANDING light illumination time to less than 5 minutes.)

Following ground report of a light ON, turn respective switch 'OFF'

Ground observer reports that light

REV F D6-85394 Page 33 of 61

2.1.37 Instruments and Furnishings

Instruments Verify all instruments, indicators, annunciators, switches and placards for compliance and readability.

Instruments and indicators which have mechanical failure flags are evaluated for appropriate response.

Furnishings Verify all cockpit seats, harnesses, windows, roller sun shades, clocks, gasper outlets, Grimes lights, rudder pedals adjustment, etc, operate freely and perform their intended function.

2.1.38 Cockpit Voice Recorder (CVR)

CVR TEST switch PUSH CVR self tests.

Verify area mic audio pickup.

2.1.39 Flight Management System (FMS)

Perform normal preflight Confirm all FMC functions are operative using normal preflight items.

2.1.40 RVSM Altimeter

RVSM compliance check Verify Captain’s and F/O’s altitude is within 75 ft. of field elevation and max difference between Captain’s and F/O’s from sea level to 5,000 ft. is 50 ft. RECORD altimeter values.

2.1.41 Stall Warning Check

Note 1: Stall Warning Check requires that AC transfer busses are powered for up to 4 minutes.

Note 2: With hydraulic power off, the leading edge flaps may droop enough to cause an asymmetry signal, resulting in a failure of the stall warning system test. Should this occur, retract the flaps by placing the “B” system electric hydraulic pump ON.

When flaps are retracted, repeat the check.

Stall warning test switches

PUSH

Verify control column vibration when each switch is PUSHED.

Page 34 of 61 D6-85394 REV F

2.1.42 Mach Airspeed Warning Check

MACH Airspeed warning test switches PUSH Verify clacker sounds.

FLIGHT DECK – ENGINE START

REV F D6-85394 Page 35 of 61

2.2 Engine Start

2.2.1 Engine Start

Fuel quantity check RECORD fuel quantities.

Engine oil quantity check RECORD engine oil quantities.

Hydraulic quantity check RECORD hydraulic quantities. RF is displayed when below min value. Refer to AMM.

Start engines using normal procedures.

Monitor engine parameters during start.

Verify EEC powers up as the engine start switch is selected to 'GRD' & EGT, FF/FU, OIL PRESS, OIL TEMP displays unblank.

Verify duct pressures increase during start.

Verify ENG VALVE CLOSED light illuminates “BRIGHT” and extinguishes within 2 seconds and SPAR VALVE CLOSED light illuminates bright and extinguishes.

2.2.2 Fuel/Center Tank Configuration

L & R CTR FUEL PUMP switches ‘OFF’ CONFIG annunciation and fuel digits and arc illuminate amber depending on amount of fuel in center tank. Refer to AMM.

CONFIG annunciation is inhibited depending on amount of fuel in center tank. Refer to AMM.

L & R CTR FUEL PUMP switches ‘ON’ as required.

2.2.3 Engine Ground Idle

L & R PACK switches 'OFF' All ANTI-ICE switches 'OFF' Minimum electrical load

RECORD stabilized N2 values, OAT

FLIGHT DECK – ENGINE START

Page 36 of 61 D6-85394 REV F

2.2.4 Electrical

DC METERS selector 'All positions' Verify amps and DC voltage remain within limits.

AC METERS selector 'All positions' Verify DRIVE lights extinguish.

Verify frequency and AC voltage remain within limits.

2.2.5 Hydraulics

ELEC 2 & 1 HYD PUMP switches 'OFF' ELEC 2 & 1 hydraulic pump LOW

PRESSURE lights illuminate.

Verify engine hydraulic pumps, A & B system pressures remain normal.

TOLERANCE: See appropriate Aircraft

Manuals

ELEC 2 & 1 HYD PUMP switches 'ON' LOW PRESSURE lights extinguish.

System pressures are normal.

ENG 1 & 2 HYD PUMP switches ‘OFF’ ENG 1 & 2 hydraulic pump LOW PRESSURE lights illuminate. Verify electric hydraulic pumps A & B system pressures remain normal.

ENG 1 & 2 HYD PUMP switches ‘ON’ LOW PRESSURE lights extinguish. System pressures are normal.

FLIGHT DECK – AFTER ENGINE START

REV F D6-85394 Page 37 of 61

2.3 After Engine Start

2.3.1 Engine Anti-Ice

ENG ANTI-ICE 1 switch 'ON' Engine 1 COWL VALVE OPEN light illuminates bright then dim. L duct pressure decreases.

Engine 1 EGT increases. TAI annunciates.

ENG ANTI-ICE 2 switch 'ON' Engine 2 COWL VALVE OPEN light illuminates bright then dim. R duct pressure decreases.

Engine 2 EGT increases. TAI annunciates.

ENG ANTI-ICE 1 & 2 switches 'OFF' COWL VALVE OPEN lights illuminate bright then extinguish. EGTs return to previous values.

TAI annunciations are removed.

2.3.2 Pneumatics/Engine Bleed

ISOLATION VALVE switch 'CLOSE'

L & R Pack switches 'AUTO'

L & R duct pressure approximately 20 psi.

Engine 1 BLEED switch 'OFF' L duct pressure decreases to approximately 0 psi.

R duct pressure does not change.

Engine 1 BLEED switch 'ON' L duct pressure returns to previous value.

Engine 2 BLEED switch 'OFF' R duct pressure decreases to approximately 0 psi.

L duct pressure does not change.

Engine 2 BLEED switch 'ON' R duct pressure returns to previous value.

2.3.3 Pressurization

Pressurization Mode selector 'AUTO' Verify that the outflow valve is full open and all pressurization lights are extinguished.

2.3.4 Flight Data Recorder

FLIGHT RECORDER switch ‘NORMAL’ OFF light remains extinguished after first engine is started.

FLIGHT DECK – TAKEOFF

Page 38 of 61 D6-85394 REV F

2.4 Takeoff

2.4.1 Autoflight 1

Note 1: HDG SEL option shown. LNAV & WINGS LEVEL options, as installed.

Note 2: Use normal flight procedures.

FMA INDICATION PFD/ND DISPLAYS

F/D switches ‘ON’ and A/T switch ‘ARM’ ARM

TO/GA switch push: N1 HDG SEL TO/GA

-Fwd thrust levers advance together. FD -Flight Director initially 10° nose-down then at 60 KIAS 15° nose-up.

At 84 KIAS: THR HLD HDG SEL TO/GA

After lift-off: FD -Flight Director command 15° nose-up then MCP speed +20.

At 800 feet BARO altitude above runway elevation.

ARM HDG SEL TO/GA

FD

At Thrust Reduction altitude:

(As installed) -CLB annunciates on TMA and thrust reduces.

-From N1 LIMIT page or 1500 AGL (As installed).

N1 HDG SEL TO/GA

FD

A/P switch ‘CMD A’ or ‘CMD B’:

(When desired)

N1 HDG SEL MCP SPD

CMD

FLIGHT DECK – CLIMB

REV F D6-85394 Page 39 of 61

2.5 Climb

2.5.1 Autoflight 2

Note: Using normal flight procedures, verify the following throughout the flight for proper operation and observe integrated A/P, A/T, F/D, FMA, TMD and MCP for correct responses and indications.

A/T switch 'ARM' A/T activates in ARM mode.

MCP SPEED switch PUSH A/T tracks MCP speed.

Verify A/T speed and Mach tracking throughout the course of the flight. Placard speeds can not be exceeded.

Capt's & F/O's F/D switches 'ON' F/D cues appear and track FMA modes.

MCP LVL CHG - airplane tracks selected IAS/MACH and will not descend when commanded to accelerate.

HDG SEL - verify bank angle limit selector.

V/S & VERT SPEED selector.

VOR LOC switch for VOR tracking.

LNAV.

VNAV & SPD INTV and ALT INTV, as installed.

FMC N1 LIMIT - CLB, CRZ, CON, GA and CLB-1 & CLB-2.

(Derates revert to CLB at 15,000 ft. PA.)

CLB, CRZ & DES modes.

DIR INTC mode.

DEP ARR functions.

FMC LEGS airspeed and altitude constraints.

Ancillary FMC functions as desired.

2.5.2 APU Fire Warning Switch Shutdown

Airplane altitude > 10,000 ft.

APU Fire Warning switch override and PULL

APU shuts down (immediate EGT decrease).

APU FAULT, MASTER CAUTION(s) & APU lights illuminate. Fault light extinguishes approx. 6 min.

APU switch 'OFF'

APU Fire Warning switch RESET

L or R APU GEN switch 'ON' (Resets APU IDG generator field)

Page 40 of 61 D6-85394 REV F

2.5.3 Altitude Alert (as configured)

Note 1: Amber box around airplane altitude, aural tone and A/P P/RST lights flashing, as installed.

Note 2: This procedure depicts the Standard Altitude Alert Option. Consult the Flight Crew Operations Manual or CSOS List for Customer Specific Option

Airplane climbing (or descending) toward an altitude set…