Delta Air Lines MD-88 90 Aircraft Operations Manual

The MD-88 90 is a twin-engine, narrow-body, commercial jet airliner, which is used by Delta Air Lines for commercial passenger flights. It has a seating capacity of up to 149 passengers.

PDF

Document

MD-88/90

Operations Manual

Volume 2

Delta Air Lines, Inc.

REVIEWED BY: ___________________________________

Chris Manley

MD-88/90 - Technical Manager

APPROVED BY: __________________________________

Randall K. Flowers

MD-88/90 - Chief Line Check Pilot

APPROVED BY: __________________________________

Jim Reese

MD-88/90 - Fleet Captain

Revision Number: 2

Revision Date: August 11, 2008

MD-88/90 Operations Manual

Preface

Chapter P2

Section 0

Volume 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Chapter

Preface . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P2

Table of Contents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P2.0

Model Identification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P2.1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P2.2

Abbreviations. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P2.3

Revision Record / Highlights. . . . . . . . . . . . . . . . . . . . . . . . . . . P2.4

List of Effective Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . P2.5

Airplane General, Emergency Equipment, Doors, Windows . . . . . . . . 1

Air Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2

Anti–Ice, Rain . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3

Automatic Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4

Communications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Electrical . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6

Engines, APU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

Fire Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

Flight Instruments, Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

Flight Management, Navigation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

Fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

Hydraulics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

Landing Gear. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

Warning Systems. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

April 01, 2004 P2.0.1

Preface -

Table of Contents

MD-88/90 Operations Manual

Intentionally

Blank

P2.0.2

April 01, 2004

MD-88/90 Operations Manual

Preface

Model Identification

Chapter P2

Section 1 General

The airplanes listed in the table below are covered in the operations manual. The table information is used to distinguish data peculiar to one or more, but not all of the airplanes. Where data applies to all airplanes listed, no reference is made to individual airplanes.

Note:

The procedures and information contained in this manual also apply to aircraft acquired by Delta Air Lines subsequent to the current revision; however, this document may not address all pertinent information for these airplanes. In such instances, specific operating procedures and systems information can be found in appropriate Differences Chapter(s) and/or

Flight Crew Bulletin(s) prior to their incorporation in the next scheduled revision.

Airplane number is supplied by the operator. Registry number is supplied by the national regulatory agency. Serial number is supplied by Boeing.

0909

0910

0911

0912

0913

0914

0915

0916

0917

Airplane

Number

0904

0905

0906

0907

0908

Registry Number

N904

N905

N906

N907DL

N908

N909

N910

N911

N912

N913

N914

N915

N916DL

N917

Serial Number

49542

49543

49544

49545

49546

49591

49573

49535

49536

49537

49538

49539

49540

49541

Model

MD-88

August 11, 2008

P2.1.1

Preface -

Model Identification

MD-88/90 Operations Manual

Registry Number Serial Number

0939

0940

0941

0942

0943

0944

0945

0931

0932

0933

0934

0935

0936

0937

0938

0923

0924

0925

0926

0927

0928

0929

0930

Airplane

Number

0918

0919

0920

0921

0922

49720

49721

49722

49723

49810

49811

49812

49813

49814

49815

49816

49817

49818

49712

49713

49714

49715

49716

49717

49718

49719

49583

49584

49644

49645

49646

49705

49711

N918

N919

N920DL

N929DL

N930DL

N931DL

N932DL

N933DL

N934DL

N935DL

N936DL

N921DL

N922DL

N923DL

N924DL

N925DL

N926DL

N927DL

N928DL

N937DL

N938DL

N939DL

N940DL

N941DL

N942DL

N943DL

N944DL

N945DL

P2.1.2

August 11, 2008

Model

MD-88

0967

0968

0969

0970

0971

0972

0973

0959

0960

0961

0962

0963

0964

0965

0966

0951

0952

0953

0954

0955

0956

0957

0958

Airplane

Number

0946

0947

0948

0949

0950

MD-88/90 Operations Manual

Registry Number Serial Number

N961DL

N962DL

N963DL

N964DL

N965DL

N966DL

N967DL

N968DL

N969DL

N970DL

N971DL

N972DL

N973DL

N953DL

N954DL

N955DL

N956DL

N957DL

N958DL

N959DL

N960DL

N946DL

N947DL

N948DL

N949DL

N950DL

N951DL

N952DL

49980

49981

49982

49983

49984

53115

53116

53161

53172

53173

53214

53215

53241

49884

49885

49886

49887

49976

49977

49978

49979

49819

49878

49879

49880

49881

49882

49883

August 11, 2008

Preface -

Model Identification

P2.1.3

Model

MD-88

Preface -

Model Identification

MD-88/90 Operations Manual

Registry Number Serial Number

0995

0996

0997

0998

0999

9000

9001

0987

0988

0989

0990

0991

0992

0993

0994

0979

0980

0981

0982

0983

0984

0985

0986

Airplane

Number

0974

0975

0976

0977

0978

N989DL

N990DL

N991DL

N992DL

N993DL

N994DL

N995DL

N996DL

N997DL

N998DL

N999DN

N900DE

N901DE

N981DL

N982DL

N983DL

N984DL

N985DL

N986DL

N987DL

N988DL

N974DL

N975DL

N976DL

N977DL

N978DL

N979DL

N980DL

53341

53342

53343

53344

53345

53346

53362

53363

53364

53370

53371

53372

53378

53268

53273

53274

53311

53312

53313

53338

53339

53242

53243

53257

53258

53259

53266

53267

P2.1.4

August 11, 2008

Model

MD-88

9203

9204

9205

9206

9207

9208

9209

9015

9016

9017

9018

9019

9020

9201

9202

9007

9008

9009

9010

9011

9012

9013

9014

Airplane

Number

9002

9003

9004

9005

9006

MD-88/90 Operations Manual

Registry Number Serial Number

N917DE

N918DE

N919DE

N920DE

N901DA

N902DA

N903DA

N904DA

N905DA

N906DA

N907DA

N908DA

N909DA

N909DE

N910DE

N911DE

N912DE

N913DE

N914DE

N915DE

N916DE

N902DE

N903DE

N904DE

N905DE

N906DE

N907DE

N908DE

49958

49959

53422

53423

53381

53382

53383

53384

53385

53386

53387

53388

53389

53418

53419

49967

49997

49956

49957

53420

53421

53379

53380

53409

53410

53415

53416

53417

August 11, 2008

Preface -

Model Identification

Model

MD-88

MD-90-30

MD-88

P2.1.5

Preface -

Model Identification

MD-88/90 Operations Manual

Registry Number Serial Number Airplane

Number

9210

9211

9212

9213

9214

9215

9216

N910DN

N911DA

N912DN

N913DN

N914DN

N915DN

N916DN

53390

53391

53392

53393

53394

53395

53396

Model

MD-90-30

P2.1.6

August 11, 2008

Preface

Introduction

MD-88/90 Operations Manual

Chapter P2

Section 2 Purpose

The Boeing Company developed normal and non-normal procedures for the

MD-88/90 aircraft. Delta Air Lines has modified some of the procedures for simplification and standardization, when appropriate with other Delta aircraft.

Finally, the FAA has approved the procedures presented in the Operations Manual, with the exception of flight crew bulletins.

These procedures are company policy for pilots to follow during ground operations and in flight. Deviations from these policies and procedures should be made only with good cause and based on the safest course of action. If an abnormality occurs that is not covered by these procedures, the Captain must use his best judgement.

Manual Rights

The MD-88/90 Operations Manual has been prepared for the exclusive use of Delta

Air Lines Inc., Flight Operations personnel under the direction and authority of

Delta Air Lines, Inc. and shall, at all times, remain the property of Delta Air Lines,

Inc. The holder hereof acknowledges and agrees that this manual contains or may contain trade secrets, copyrighted material and commercial and proprietary information, privileged and confidential, to the interest of Delta Air Lines, Inc., and the holder hereof further agrees that this manual may not be reproduced, distributed or copied, in whole or in part, without the express prior written consent of Delta Air Lines, Inc.

• In the event this MD-88/90 Operations Manual is sold or distributed to any other party, no warranty or guarantee, expressed or implied, is made as to the accuracy, sufficiency or suitability of the materials contained herein or of any revision, supplement or bulletin hereto. It is understood and agreed to by such other party that it shall release indemnify and hold Delta Air

Lines, Inc., its officers, employees and agents harmless against any and all claims or actions of whatever nature which may arise or claim to arise from the use hereof.

August 11, 2008

P2.2.1

Preface -

Introduction

MD-88/90 Operations Manual

Corrections to the Manual

To correct any errors or discrepancies discovered in this manual, or to submit a suggested change to any Aircraft Operating Manual (Volume 1, Volume 2, QRH,

Flight Crew Training Manual), Normal Checklist, Airway Manual, Flight

Operations Manual (FOM), OE/TOE Guide, Flight Crew Bulletin (FCB), or Flight

Operations Bulletin (FOB):

Log on to the Delta Flight Operations Portal; http://dlnet.delta.com/portal and submit a Publications Change Request (PCR).

There are links to the PCR form on each fleet page and also on the Flight Ops

Manuals/Library Services page.

Once submitted, the PCR is automatically routed to the applicable Fleet Technical

Manager and Technical Writer for that manual.

Organization

The operations manual is organized in the following manner.

Volume 1

• Preface – contains general information regarding the manual’s purpose, structure, and content. It also contains lists of abbreviations, a record of revisions, a list of effective pages, and bulletins.

• Limitations and Normal Procedures chapters cover operational limitations and normal procedures. All operating procedures are based on a thorough analysis of crew activity required to operate the airplane, and reflect the latest knowledge and experience available.

• Supplementary Procedures chapter covers those procedures accomplished as required rather than routinely on each flight.

• Aircraft Differences chapter notes differences between aircraft types.

Volume 2 - Chapters 1 through 15 contain general airplane and systems information. These chapters are generally subdivided into sections covering controls and indicators and systems descriptions.

Quick Reference Handbook (QRH) - The QRH covers normal checklists, non-normal checklists, and non-normal maneuvers.

Flight Crew Training Manual (FCTM) - The Flight Crew Training Manual provides information and recommendations on maneuvers and techniques.

P2.2.2

August 11, 2008

MD-88/90 Operations Manual

Preface -

Introduction

Page Numbering

The operations manual uses a decimal page numbering system. The page number is divided into three fields; chapter, section, and page. An example of a page number for the hydraulics chapter follows: chapter 13, section 20, page 3.

Example Page Number

Chapter (Hydraulics)

Page Number

13.20.3

Section (Systems Description)

Warnings, Cautions, and Notes

The following levels of written advisories are used throughout the manual.

WARNING: An operating procedure, technique, etc., that may result in personal injury or loss of life if not carefully followed.

CAUTION: An operating procedure, technique, etc., that may result in damage to equipment if not carefully followed.

Note:

An operating procedure, technique, etc., considered essential to emphasize.

Information contained in notes may also be safety related.

August 11, 2008

P2.2.3

Preface -

Introduction

MD-88/90 Operations Manual

Intentionally

Blank

P2.2.4

August 11, 2008

MD-88/90 Operations Manual

Preface

Abbreviations

Chapter P2

Section 3

General

The following abbreviations may be found throughout the manual. Some abbreviations may also appear in lowercase letters. Abbreviations having very limited use are explained in the chapter where they are used. Since this list is compiled across several fleets, there may be some abbreviations that do not apply to this specific fleet.

ABV

ACARS

ACE

ACP

ACT

ADC

ADF

ADI

ADIRS

ADIRU

ADM

AED

AFDC

Above

Alternating Current or

Aircraft

Aircraft Communications

Addressing and

Reporting System

Actuator Control

Electronics

Audio Control Panel

Active

Air Data Computer

Automatic Direction

Finder

Attitude Director

Indicator

Air Data Inertial

Reference System

Air Data Inertial

Reference Unit

Air Data Module

Automatic External

Defribulator

Autopilot Flight Director

Computer

AFDS

AFE

AFM

Above Field Elevation

Airplane Flight Manual

(FAA approved)

AFM - DPI Airplane Flight Manual -

Digital Performance

Information

AFS

Autopilot Flight Director

System

Automatic Flight System

(Autopilot or

Autothrottle)

Air/Ground A/G

AGL

AHRS

Above Ground Level

Alert Height

Attitude Heading

Reference System

AIL

ALFA

ALT

Anti-Ice

Aileron

Safe Stall Margin Speed

Altitude

ALT ACQ Altitude Acquire

ALT HOLD Altitude Hold

ALTN

Alternate

Amplitude Modulation

August 11, 2008

P2.3.1

Preface - Abbreviations

AIMS

AMI

ANP

ANT

ANU

AOA

AOC

A/P

APL

APP

APU

ARINC

ARM

ARPT

ARR

ART

ASA

ASI

ASR

ASYM

A/T

ATA

Airplane Information

Management System

Airline Modifiable

Information

Actual Navigational

Performance

Antenna

Aircraft Nose Up

Angle of Attack

Airline Operational

Communication Data

Link

Autopilot

Airplane

Approach

Auxiliary Power Unit

Authorization Required

Aeronautical Radio,

Incorporated

Aircraft Restrictions

Manual

Airport

Arrival

Automatic Reserve

Thrust

Autoland Status

Annunciator

Airspeed Indicator

Airport Surveillance

Radar

Asymmetry

Autothrottle

Actual Time of Arrival

MD-88/90 Operations Manual

ATC

ATIS

ATM

ATT

AUTO

AUTO–

THROT

AUX

AVAIL

AWABS

Air Traffic Control

Automated Terminal

Information Service

Assumed Temperature

Method

Attitude

Automatic

Autothrottle

Auxiliary

Available

Automated Weight and

Balance System

BARO

BAT

Barometric

Battery

Back Course B/C or

B/CRS or

BAC or

BCS

BFO

BITE

BKR

BLD

BLW

BRG

BRT

Beat Frequency

Oscillator

Built-In Test Equipment

Breaker

Bleed

Below

Bearing

Bright

BTL

BTMS

Bottle

BTL DISCH Bottle Discharge (fire extinguisher)

Brake Temperature

Monitoring System

P2.3.2

August 11, 2008

Preface - Abbreviations

MD-88/90 Operations Manual

CHKL

CHR

CKD

CKT

CLB

CLMP

CCD

CDS

CDU

CFIT

Captain or

Celsius or

Center or

Cool

Civil Aviation Authority CAA

CADC

CALSEL Call Select

CANC/RCL Cancel/Recall

CANPA

Central Air Data

Computer

Constant Angle

Non-Precision Approach

CAP

CAPT

CAWS

Capture

Captain

Central Aural Warning

System

Circuit Breaker

Cursor Control Device

Common Display System

Control Display Unit

Controlled Flight Into

Terrain

Center of Gravity

Checklist

Chronograph

Checked

CLR

Circuit

Climb

Computer Lockout

Manual Power

Clear

CMD

COMM

COMP

COMPT

CON

CONFIG

CONT

COOL

CRM

Command

Company

Communication

Comparator

Compartment

Continuous

Configuration

Control

Cooling

Crew Resource

Management

Course CRS

CRT

CRZ

CTL

CTR

CWS

DA(H)

DCU

Cathode Ray Tube

Cruise

Control

Center

Control Wheel Steering

Decision Altitude

(Height)

Direct Current

Display Concentrator

Unit

D/D

DDA

DDG

Direct Descent

Derived Decision

Altitude (MDA +50 feet)

Dispatch Deviations

Guide

Delete DEL

DEP Departure

DEP ARR Departure Arrival

August 11, 2008 P2.3.3

DIFF

DIR

DISC

DISCH

DME

Preface - Abbreviations

DEPR

DES

DEU

DFCS

DFGC

DFGS

DPC

DSP

DSPL

DTG

DTW

EADI

ECON

E/D

E/E

Depressurize

Descent

Display Electronic Unit

Digital Flight Control

System

Digital Flight Guidance

Computer

Digital Flight Guidance

System

Decision Height

Differential

Direct

Disconnect

Discharge

Deck

Distance Measuring

Equipment

Down

Display Processing

Computer

Display Select Panel

Display

Distance to Go

Distance to Waypoint

Display Unit

Electronic Attitude

Director Indicator

Economy

End of Descent

Electrical/Electronic

MD-88/90 Operations Manual

EEC

EFI

Electronic Engine

Control

Electronic Flight

Instruments

EFIS

EGPWS

Electronic Flight

Instrument System

Enhanced Ground

Proximity Warning

System

Exhaust Gas Temperature EGT

EHSI

EICAS

Electronic Horizontal

Situation Indicator

Engine Indication and

Crew Alerting System

EIS

ELEC

ELEV

EMER

ENG

Electronic Instrument

System

Electrical

Elevator

Emergency

Engine

ENG OUT Engine Out

ENT Entry

EO or E/O Engine Out

EOAP Electronic Overhead

Annunciation Panel

EPR Engine Pressure Ratio

Equipment EQPT or

EQUIP

ETOPS

EVAC

EXEC

EXT

Extended Range

Operation with Twin

Engine Airplanes

Evacuation

Execute

Extend or External

P2.3.4

August 11, 2008

Preface - Abbreviations

MD-88/90 Operations Manual

FAC

FAA

FADEC

Fahrenheit

Final Approach Course

Federal Aviation

Administration

Full Authority Digital

Engine Control

Final Approach Fix FAF

FAR

FCB

FCC

FCTL

FCTM

Federal Aviation

Regulation

Flight Crew Bulletin

Flight Control Computer

Flight Control

Flight Crew Training

Manual

Flight Director FD, F/D or

FLT DIR

FF Fuel Flow

FFM

FGCP

Force Fight Monitor

Flight Guidance Control

Panel

Flight Guidance System FGS

FILT

FIR

Filter

Flight Information

Region

Flight Level Change FL CH or

FLCH

FLT Flight

FLT CTRL Flight Control

FLPRN Flaperon

FMA

FMC

Flight Mode Annunciator

Flight Management

Computer

GEN

GLS

GMT

GND

GNSS

FMS Flight Management

System

F/O or F O First Officer

FOM Flight Operations Manual

FPA

FPM

FPV

FREQ

Flight Path Angle

Feet Per Minute

Flight Path Vector

Frequency

F/S

FWD

FWSOV

Fast/Slow

Feet

Forward

Fire Wall Shut Off Valve

Fix

Go–Around

Generator

GNSS Landing System

Greenwich Mean Time

Ground

Global Navigation

Satellite System

Glide Path GP or

G/P

GPS

GPWS

G/S

HAA

Global Positioning

System

Ground Proximity

Warning System

Ground Speed

Glide Slope

Gross Weight

Height Above Airport

August 11, 2008 P2.3.5

Preface - Abbreviations

MD-88/90 Operations Manual

HAT Height Above

Touchdown

HDG Heading or

Hydraulic Driven

Generator

HDG REF Heading Reference

HDG SEL Heading Select

HF High Frequency

HGS Head-Up Guidance

System (HGS® is a registered trademark of

Flight Dynamics)

HLD

HPA

HPSOV

HSI

HUD

HYD

High

Hold

Hectopascals

High Pressure Shut Off

Valve

Horizontal Situation

Indicator

Head-Up Display

IAF

IAN

IAS

ICAO

Hydraulic

Initial Approach Fix

Integrated Approach

Navigation

Indicated Airspeed

International Civil

Aviation Organization

IDENT

IFE

IFR

IGN

Identification

In-Flight Entertainment

System

Instrument Flight Rules

Ignition

IGS

ILS

IMC

JAA

Instrument Guidance

System

Instrument Landing

System

Inner Marker

Instrument

Meteorological

Conditions

INBD

IND

IND LTS

ISDU

ISFD

ISLN

Inches

Inboard

Indicator

Indicator Lights

INOP

INIT

INSTR

INT or

INTPH

INTC

Inoperative

Initialization

Instrument

Interphone

Intercept

INTC CRS Intercept Course

IP Instructor Pilot

IRS Inertial Reference

System

IRU

ISA

Inertial Reference Unit

International Standard

Atmosphere

Inertial System Display

Unit

Intergrated Standby

Flight Display

Isolation

Joint Aviation Authority

P2.3.6

August 11, 2008

Preface - Abbreviations

MD-88/90 Operations Manual

LAT

LBS

LDA

K or KTS

KCAS

KGS

KIAS

LDG

LDG ALT

LIM

LIM SPD

LKD

L NAV or

LNAV

LRC

LRU

LSK

LOC

LOC-BC

LOM

LON

Localizer

Localizer Back Course

Locator Outer Marker

Longitude

Long Range Cruise

Line Replaceable Unit

Line Select Key

Light

LWR CTR Lower Center

LWR

DSPLY or

LWR DSPL

Lower Display

Knots

Knots Calibrated

Airspeed

Kilograms

Knots Indicated Airspeed

Left

Latitude

Pounds

Load

Localizer-type

Directional Aid

Landing

Landing Altitude

Leading Edge

Limit

Limit Speed

Locked

Lateral Navigation

MAG

MAHP

MAN

MAP

MASI

MAX

MCC

MCDU

MCO

MCP

MCT

MDA

MDA(H)

MDM

MEA

MEL

MFD

MHZ

MIC

MIN

MKR

Mach

Magnetic

Missed Approach

Holding Point

Manual

Missed Approach Point

Mach/Airspeed Indicator

Maximum

Maintenance Control

Center

Multi-purpose Control and Display Unit

Maintenance Carry Over

Mode Control Panel

Maximum Continuous

Thrust

Minimum Descent

Altitude

Minimum Descent

Altitude (Height)

Mechanical Dispatch

Manual

Minimum Enroute

Altitude

Minimum Equipment

List

Multifunction Display

Megahertz

Microphone

Minimum

Marker

August 11, 2008 P2.3.7

Preface - Abbreviations

MD-88/90 Operations Manual

NPS MLS

MMO

MNPS

MOCA

MOD

MORA

Microwave Landing

System

Middle Marker

Maximum Mach

Operating Speed

Minimum Navigation

Performance

Specification

Minimum Obstruction

Clearance Altitude

Modify

Minimum Off Route

Altitude

Minimum Safe Altitude

Message

Messages Received

MSA

MSG

MSGS

RCVD

MSL

MTRS

MUH

NADP

Mean Sea Level

Meters

Minimum Use Height

Normal

Noise Abatement

Departure Procedures

NAR

NAV

North American Route

Navigation

NAV RAD Navigation Radio

ND Navigation Display

NLT

NNC

NNM

No Later Than

Nautical Mile(s)

Non-Normal Checklists

Non-Normal Maneuvers

NORM

OAP

OAT

OCC

ODM

OFST

OHU

OUTBD

DSPL

OVHD

OVHT

OVRD

OVSPD

OXY or

Navigation Performance

Scales

Normal

Low Pressure Rotor

Speed

High Pressure Rotor

Speed (Pratt & Whitney and GE engines) or

Intermediate Pressure

Rotor Speed (Rolls

Royce Engines)

High Pressure Rotor

Speed (Rolls Royce

Engines)

Overhead Annunciator

Panel (a.k.a. EOAP)

Outside Air Temperature

Operations Control

Center

Operational Data Manual

Offset

Overhead Unit

Outer Marker

Open

Outboard Display

Overhead

Overheat

Override

Overspeed

Oxygen

P2.3.8

August 11, 2008

Preface - Abbreviations

MD-88/90 Operations Manual

PAPI

PAR

Precision Approach Path

Indicator

Precision Approach

Radar

PASS Passenger

PBE Protective Breathing

Equipment

PFC

PFD

PIP

PCP

PDC

Pilot Call Panel

Pitch Data Computer or

Performance Data

Computer or

Pre-Departure Clearance

Performance PERF

PERF INIT Performance

Initialization

PES Pitch Enhancement

System

Pilot Flying

Primary Flight Computer

Primary Flight Display

Performance Inflight

Product Improvement

Package

PLI

PMC

PNL

POS

POS INIT

POS REF

Pitch Limit Indicator

Pilot Monitoring

Power Management

Control

Panel

Position

Position Initialization

Position Reference

PPI

PPOS

PRES or

PRESS

PRI

PROG

PROX

P/RST

PRV

PSI

PTH

PTT

PTU

PWR

PWS

QFE

QNH

QRH

QTY

RAD

Planned Position

Indicator

Present Position

Pressure

Primary

Progress

Proximity

Push To Reset

Pressure Regulating

Valve

Pounds Per Square Inch

Path

Push To Talk

Power Transfer Unit

Power

Predictive Windshear

System

Quantity

Local Station Pressure

Altimeter Setting

Quick Reference

Handbook

Quantity

Right

Radio Altitude or

Resolution Advisory

Radio

August 11, 2008 P2.3.9

Preface - Abbreviations

RAT

RCL

RDMI

REC

RECIR or

RECIRC

REF

RET

REV

RMI

RNAV or

RNV

RNP

RPL

RPM

RPR

RSEP

RST

RSVR

R/T

RTE

RTO

RTP

RUD

RVR

MD-88/90 Operations Manual

RVSM Ram Air Temperature or

Ram Air Turbine

Request for Clearance

Radio Distance Magnetic

Indicator

Recorder

Recirculation

SAAAR

SAARU

Reference

Retract

Reverse

Radius-to-Fix (RF) Legs or

Refill

Radio Magnetic Indicator

Area Navigation

Required Navigational

Performance

Rudder Pressure Limiter

Revolutions Per Minute

Rudder Pressure Reducer

Rudder System

Enhancement Program

Reset

Reservoir

Radio Transmit

Route

Rejected Takeoff

Radio Tuning Panel

Rudder

Runway Visual Range

SAT

S/B

S/C

SDF

SEI

SEL

SELCAL

SENS

SERV

SPD

SPDBRK

STA

STAB

STAT

STBY

STD

SYS

T or TRU

Reduced Vertical

Separation Minimum

Special Aircraft and

Aircrew Authorization

Required

Secondary Attitude Air

Data Reference Unit

Static Air Temperature or

Satellite

Service Bulletin

Speedbrake

Step Climb

Simplified Directional

Facility

Station

Stabilizer

Status

Standby

Standard

System

True

Standby Engine Indicator

Select

Selective Calling

Sensitivity

Service

Symbol Generator

Speed

Speedbrake

P2.3.10

August 11, 2008

Preface - Abbreviations

MD-88/90 Operations Manual

T or TK or

TRK

TAA

TACAN

TAC

TAI

Track (to a Navaid)

Traffic Advisory

Terminal Arrival Area

Tactical Air Navigation

Thrust Asymmetry

Compensation

Thermal Anti–Ice

TEMP

TERR

TFC

TFR

THR

TAT

T/C

TCA

TCAS

T/D

TDZ

TDZE

Total Air Temperature

Top of Climb

Terminal Control Area

Traffic Alert and

Collision Avoidance

System

Top of Descent

Touch Down Zone

Elevation

Trailing Edge

Temperature

Terrain

Traffic

Transfer

Throttle or

Thrust

THR HOLD Throttle Hold

TMC Thrust Management

Computer

TMI Track Message Identifier

TMSP Thrust Mode Select Panel

TO or T/O Takeoff

TOC

TOD

TO/GA

TRK

TRP

TRU

TURB

Top of Climb

Top of Descent

Takeoff/Go–Around

Traffic Resolution

Track

Thrust Rating Panel

Transformer Rectifier

Unit

Turbine or

Turbulence

UNLKD

Unlocked

UNSCHD or

UNSCHED

Unscheduled

UPR DSPL Upper Display

U.S.

USB

UTC

UTIL

VAL

VANP

United States

Upper Side Band

Universal Time

Coordinated

Utility

Design maneuvering speed

Valve

Vertical Actual

Navigational

Performance

VASI

VDP

VEF

VERT

Visual Approach Slope

Indicator

Visual Descent Point

Speed at Engine Failure

Vertical

August 11, 2008 P2.3.11

Preface - Abbreviations

MD-88/90 Operations Manual

VFR

VHF

VIB

Visual Flight Rules

Vertical Gyro

Very High Frequency

Vibration

VLV

VMC

VMCA

VMCG

VMO

Valve

Visual Meteorological

Conditions

Minimum Control Speed

Air or

Single Engine Minumum

Control Airspeed

Minimum Control Speed

Ground

Maximum Operating

Speed

Vertical Navigation V NAV or

VNAV

VOR

VREF

VRNP

VHF Omnidirectional

Range

Rotation Speed

Reference Speed

Vertical Required

Navigation Performance

Vertical Speed V/S

VSCF

VSD

VSI

VTK

Variable Speed Constant

Frequency

Vertical Situation Display

Vertical Speed Indicator

Vertical Track

Takeoff Decision Speed

V1 (MCG) Minimum V1 for Control on the Ground

V2 Scheduled Takeoff Target

Speed

WATRS

WDR

WGS-84

WHL

WPT

WXR

X–FEED

XPDR or

XPNDR

XTK Cross Track

Warm

Western Atlantic Route

System

Weight Data Record

World Geodetic System of 1984

Wheel

Waypoint

Weight

Weather Radar

Crossfeed

Transponder

P2.3.12

August 11, 2008

Preface

Revision Record

MD-88/90 Operations Manual

Chapter P2

Section 4 Revision Transmittal Letter

To: All holders of Delta Air Lines, Inc. MD-88/90 Operations Manual, Volume 2.

Subject: Operations Manual Revision.

This revision reflects the most current information available to Delta Air Lines,

Inc. through the subject revision date. The following Revision Highlights explain changes in this revision. General information below explains the use of revision bars to identify new or revised information.

Revision Record

No.

Revision Date

April 01, 2004

August 11, 2008

Date

Filed

No.

Revision Date

February 28, 2005

Date

Filed

August 11, 2008

P2.4.1

Preface -

Revision Record

MD-88/90 Operations Manual

General

Delta Air Lines, Inc. issues operations manual revisions to provide new or revised procedures and information. Formal revisions also incorporate appropriate information from previously issued operations manual bulletins.

The revision date is the approximate date the revision material is distributed and considered current. The revision should be incorporated as soon as it is received, but may be incorporated as much as 21 days after the revision date.

Formal revisions include a Transmittal Letter, a new Revision Record, Revision

Highlights, and a current List of Effective Pages. Use the information on the new

Revision Record and List of Effective Pages to verify the operations manual content.

The Revision Record should be completed by the person incorporating the revision into the manual.

Filing Instructions

Consult the List of Effective Pages (P2.5). Pages identified with an asterisk (*) are either replacement pages, new (original) issue pages, or deleted pages. Remove corresponding old pages and replace or add new pages. Remove pages marked

DELETED; there are no replacement pages for deleted pages.

Be careful when inserting changes not to throw away pages from the manual that are not replaced. The List of Effective Pages determines the correct content of the manual.

P2.4.2

August 11, 2008

Preface -

Revision Record

MD-88/90 Operations Manual

Revision Highlights

This section (P2.4) replaces the existing section P2.4 in your manual.

Pages containing revised technical and non-technical material have revision bars associated with the changed text or illustration.

Repaginated material not containing technical revisions are identified only by a new page date.

Note:

This revision of the MD-88/90 Volume 2 has new formatting and fonts which have been adopted for use. This will bring the MD-88/90 Volume 2 into standardization with the rest of Delta’s fleets Volume 2s. These changes affect the appearance of the information, but not the technical information, and will not be identified by revision bars.

Note:

In this revision, for cross-fleet standardization purposes, “cockpit” is now

“flight deck.” The only exception to this rule is where a switch or selector is labeled using the term cockpit; e.g. “Cockpit Voice Recorder”. No revision bars are used to denote these changes.

Title Page

Revised to reflect latest revision information.

Chapter P2 - Preface

Section 2 Introduction

Manual Rights

P2.2.1 - Changed Operating to Operations.

Corrections to the Manual

P2.2.2 - Revised procedure for submitting changes to the manual.

Section 3 Abbreviations

Abbreviations

P2.3.1-12 - Updated abbreviations table to cross-fleet standard.

Section 4 Revision Record

Revision Highlights

P2.4.1-8 - Revised to reflect changes for Revision 2.

Section 5 List of Effective Pages

List of Effective Pages

P2.5.1-4 - Revised to reflect changes for Revision 2.

August 11, 2008

P2.4.3

Preface -

Revision Record

MD-88/90 Operations Manual

Chapter 1- Aircraft General, Emergency Equipment, Doors, Windows

Section 0 Table of Contents

Table of Contents

1.TOC.0.1-4 - Revised to reflect content changes.

Section 20 Instrument Panels

Forward Overhead Panel

1.20.1 - Changed the Blue Advisory Lights from "AHRS 1/2 BASIC MODE" to "IRS 1/2 ATT MODE."

Aft Overhead Panel

1.20.2 - Revised location and text of multiple circuit breakers.

Section 30 Controls and Indicators

Emergency Lighting Controls

1.30.8 - Under Emergency Lights Switch (FWD Cabin), revised description of the ARM position, per the Aircraft Maintenance Manual.

Doors

1.30.11 - Under Flight Deck Door, Door Louvers, revised description to close the louvers by raising the sliding panel.

Section 40 Systems Description

1.40.1-22 - Entire section reissued with new formatting and fonts.

Emergency Locator Transmitter (ELT)

1.40.17-18 - New section created. Incorporated FCB 08-01, New Portable

ELT Installation.

Emergency and Cabin Equipment Symbols

1.40.19 - Revised symbols for cross-fleet standardization.

Emergency and Cabin Equipment Locations

1.40.20-21 - Revised to distinguish between one and two class configurations. Added overwater configuration to the two class configuration.

Section 90 MD-90 Differences

1.90.1-12 - Entire section reissued with new formatting and fonts.

Systems Description

1.90.11 - Removed emergency equipment sympols table. Revised to update

MD-90 Emergency and Cabin Equipment Locations.

P2.4.4

August 11, 2008

Preface -

Revision Record

MD-88/90 Operations Manual

Chapter 4 - Automatic Flight

Section 0 Table of Contents

Table of Contents

4.TOC.0.1-2 - Revised to reflect content changes.

Section 20 System Description

4.20.1-18 - Entire section reissued with new formatting and fonts.

Digital Flight Guidance Computer

4.20.1 - Removed AHRS reference.

Speed Control

4.20.14 - Added exception for Takeoff/Go-Around Mode. Added

"Autothrottles Engaged" to Gust Integration.

Stability Augmentation

4.20.17 - Under Yaw Damper and Parallel Rudder, revised text for Boeing standardization.

Chapter 5 - Communications

Section 0 Table of Contents

Table of Contents

5.TOC.0.1-4 - Revised to reflect content changes.

Section 22 ACARS 201

5.22.1-36 - Remove entire section as it has been deleted. All aircraft have been retrofitted with ACARS 501.

Chapter 6 - Electrical

Section 50 Circuit Breaker Locations

Circuit Breaker Locations

6.50.2 - Removed AHRS circuit breakers.

6.50.18 - Revised locations of Service Interphone circuit breaker on the

MD-88.

Circuit Breaker Location by Panel

6.50.23 - Revised locations of Battery Bus circuit breakers on the MD-88.

August 11, 2008

P2.4.5

Preface -

Revision Record

MD-88/90 Operations Manual

Chapter 7 - Engines, APU

Section 0 Table of Contents

Table of Contents

7.TOC.0.1-4 - Revised to reflect content changes.

Section 11 Engine Controls and Indicators (JT8D-219)

Engine Display Panel

7.11.7 - Updated descriptions of panel for Boeing standardization.

Section 21 Engine System Description

7.21.1-6 - Entire section reissued with new formatting and fonts.

Engine Instruments

7.21.1 - Revised note to state that flashing EGT and fuel flow digits may indicate a possible hot start.

Thrust Rating Panel

7.21.4 - Removed methods for setting takeoff power, as they are stated in Vol.

1, NP.20.

Section 90 MD-90 Differences

Controls and Indications - Engine Display Panel

7.90.7-8 - Updated descriptions of panel for Boeing standardization.

Chapter 10 - Flight Instruments, Displays

Section 0 Table of Contents

Table of Contents

10.TOC.0.1-4 - Revised to reflect content changes.

Section 10 Controls and Indicators

Navigation Display (ND) ROSE Mode

10.10.15 - Added definition of dots for course deviation bar.

Navigation Display (ND) ARC Mode

10.10.18 - Added definition of dots for course deviation bar.

Navigation Display (ND) MAP Mode

10.10.22 - Removed AHRS reference.

P2.4.6

August 11, 2008

MD-88/90 Operations Manual

Section 20 System Description

10.20.1-6 - Entire section reissued with new formatting and fonts.

Electronic Flight Instrument System

10.20.2 - Removed AHRS references.

Attitude Heading Reference System

10.20.5 - Removed AHRS section.

Section 30 OAP Messages/Lights

Blue Advisory Lights

10.30.1 - Removed AHRS references.

Preface -

Revision Record

Chapter 11 - Flight Management, Navigation

Section 0 Table of Contents

Table of Contents

11.TOC.0.1-4 - Revised to reflect content changes.

Section 11 Controls and Indicators

Navigation Display (ND) ROSE Mode

11.10.7-8 - Remove pages from manual. Removed AHRS section.

Section 20 System Description

11.20.1-10 - Entire section reissued with new formatting and fonts.

General

11.20.1 - Removed AHRS reference.

Attitude Heading Reference System

11.20.1 - Removed AHRS section.

Radio Distance Magnetic Indicators

11.20.3 - Removed AHRS references.

Weather Radar System

11.20.4 - Removed AHRS reference.

Navigation Display (ND) Symbology

11.20.7 - Under Wind Speed and Direction, removed AHRS reference.

August 11, 2008

P2.4.7

Preface -

Revision Record

MD-88/90 Operations Manual

Section 21 Flight Management System Description

11.21.1-74 - Entire section reissued with new formatting and fonts.

FMS Components

11.21.1 - Removed AHRS reference.

FMS Flight Guidance Modes

11.21.3 - Under NAV Mode and Loss of Radio Position, removed AHRS references.

11.21.4 - Under NAV Engagement, removed AHRS reference.

11.21.8 - Under VNAV Mode, FMS Speed Override, clarified FMS OVRD mode.

Menu Page

11.21.10 - Removed AHRS reference.

Position Reference - IRS Aircraft

11.21.15 - Removed AHRS references.

Cruise

11.21.64 - Removed AHRS references.

Section 30 OAP Messages/Lights

Blue Advisory Lights

11.30.1 - Removed AHRS reference.

Chapter 12 - Fuel

Section 0 Table of Contents

Table of Contents

12.TOC.0.1-2 - Revised to reflect content changes.

Section 10 Controls and Indicators

12.10.1-6 - Entire section reissued with new formatting and fonts.

Fuel Quantity

12.10.2-3 - Updated descriptions of panel for Boeing standardization..

Section 20 System Description

12.20.1-4 - Entire section reissued with new formatting and fonts.

Fuel Feed

12.20.2 - Updated descriptions L/R INLET FUEL PRESS LOW message for

Boeing standardization.

P2.4.8

August 11, 2008

Preface -

Revision Record

MD-88/90 Operations Manual

Alternate Fuel Burn (AFB) System

12.20.2 - Added information for aircraft modified to change the Low Fuel

Warning from 2,500 to 2,000 pounds.

Chapter 14 - Landing Gear

Section 0 Table of Contents

Table of Contents

14.TOC.0.1-2 - Revised to reflect content changes.

Section 10 Controls and Indicators

Anti-Skid Controls and Brake Temperature Indication

14.10.8 - Revised diagram to more accurately show the location of the test band on the First Officer’s instrument panel.

Section 20 System Description

14.20.1-6 - Entire section reissued with new formatting and fonts.

Visual/Aural Indicating and Warning System

14.20.4 - Added note under periscope diagram to clarify location of the periscope.

Chapter 15 - Warning Systems

Section 20 System Description

TCAS Data Tags

15.20.26 - Revised description of Traffic Advisory from "Solid Yellow" to

"Solid Amber".

TCAS Components

15.20.28 - Removed AHRS reference.

Predictive Windshear System

15.20.50 - Under General, added guidance that right throttle must be advanced for the weather radar to being automatically scanning.

August 11, 2008

P2.4.9

Preface -

Revision Record

MD-88/90 Operations Manual

Intentionally

Blank

P2.4.10

August 11, 2008

Preface

MD-88/90 Operations Manual

List of Effective Pages

Chapter P2

Section 5

Page Date

2 Air Systems (tab)

* Title Page

Volume 2

August 11, 2008

2.TOC.0.1-4

2.10.1-3

April 01, 2004

Preface (tab)

2.10.4 February 28, 2005

P2.0.1-2 April 01, 2004

2.10.5-10 April 01, 2004

* P2.1.1-6

* P2.2.1-4

* P2.3.1-12

August 11, 2008

2.20.1-8

2.30.1-2

April 01, 2004

2.40.1-2 April 01, 2004

* P2.4.1-10 August 11, 2008

2.90.1-8 April 01, 2004

* P2.5.1-4 August 11, 2008

3 Anti-Ice, Rain (tab)

1 Airplane General, Emergency

Equipment, Doors, Windows (tab)

3.TOC.0.1-2

3.10.1-3

April 01, 2004

* 1.TOC.0.1-4

1.10.1-4

August 11, 2008

April 01, 2004

3.10.4 February 28, 2005

3.10.5-8 April 01, 2004

* 1.20.1-2

1.20.3-6

August 11, 2008

April 01, 2004

3.20.1-4

3.30.1

April 01, 2004

February 28, 2005

1.30.1-6

* 1.30.7-12

1.30.13-36

1.30.37

April 01, 2004

August 11, 2008

April 01, 2004

February 28, 2005

3.30.2

3.40.2

3.90.1-8

1.30.38-42

* 1.40.1-22

April 01, 2004

August 11, 2008

* 4.TOC.0.1-2

1.50.1 February 28, 2005

4.10.1-6

1.50.2 April 01, 2004

4.10.7

* 1.90.1-12 August 11, 2008

4.10.8-16

* 1.90.13-14

4.30.1-2

April 01, 2004

4 Automatic Flight (tab)

August 11, 2008

April 01, 2004

February 28, 2005

April 01, 2004

August 11, 2008

April 01, 2004

4.40.1-2

4.90.1

4.90.2

April 01, 2004

February 28, 2005

* = Revised, Added, or Deleted

August 11, 2008 P2.5.1

Preface -

List of Effective Pages

Page Date

5 Communications (tab)

* 5.TOC.0.1-4 August 11, 2008

5.10.1-12

5.20.1-4

5.21.1-2

MD-88/90 Operations Manual

February 28, 2005

April 01, 2004

Page Date

7 Engines, APU (tab)

* 7.TOC.0.1-4

7.11.4

7.11.5-6

* 7.11.7

7.15.1-4

* 7.21.1-6

August 11, 2008

April 01, 2004

February 28, 2005

April 01, 2004

August 11, 2008

April 01, 2004

August 11, 2008

5.23.1-18

5.23.19-37

5.23.38-62

5.90.1-2

April 01, 2004

February 28, 2005

April 01, 2004

6 Electrical (tab)

6.TOC.0.1-2 April 01, 2004

6.10.1-6

6.20.1-6

6.30.1-2

6.40.1-4

6.50.1

* 6.50.2

6.50.3-17

* 6.50.18

6.50.19-22

* 6.50.23

6.50.24-26

6.90.1

6.90.2

6.90.3-14

April 01, 2004

August 11, 2008

April 01, 2004

August 11, 2008

April 01, 2004

August 11, 2008

April 01, 2004

February 28, 2005

April 01, 2004

7.30.1-2

7.40.1-2

7.50.1-4

7.90.1-6

* 7.90.7-8

7.90.9-11

7.90.12-13

7.90.14-24

April 01, 2004

August 11, 2008

April 01, 2004

February 28, 2005

April 01, 2004

8 Fire Protection (tab)

8.TOC.0.1-2

8.10.1-4

8.20.1-2

8.20.3

8.20.4-6

8.30.1-2

8.90.1-4

April 01, 2004

February 28, 2005

April 01, 2004

* = Revised, Added, or Deleted

P2.5.2

August 11, 2008

Preface -

List of Effective Pages

MD-88/90 Operations Manual

Page Date Page Date

9 Flight Controls (tab)

9.TOC.0.1-4

9.10.1-5

9.10.6

9.10.7-14

9.20.1-10

April 01, 2004

February 28, 2005

April 01, 2004

12 Fuel (tab)

* 12.TOC.0.1-2

* 12.10.1-6

* 12.20.1-4

12.30.1-2

12.40.1-2

August 11, 2008

April 01, 2004

9.30.1-2 April 01, 2004 12.90.1-6 April 01, 2004

9.40.1-2 April 01, 2004

13 Hydraulics (tab)

9.90.1-8 April 01, 2004

13.TOC.0.1 February 28, 2005

10 Flight Instruments, Displays

(tab)

13.TOC.0.2 April 01, 2004

13.10.1-4 April 01, 2004

* 10.TOC.0.1-4 August 11, 2008

13.20.1-2 April 01, 2004

10.10.1-14 April 01, 2004

13.30.1-2 April 01, 2004

* 10.10.15-22 August 11, 2008

13.40.1-2 April 01, 2004

10.10.23 April 01, 2004

13.90.1-4 April 01, 2004

10.10.24 February 28, 2005

14 Landing Gear (tab)

10.10.25-32

* 10.20.1-6

April 01, 2004

August 11, 2008

* 14.TOC.0.1-2

14.10.1-7

* 14.10.8

* 10.30.1-2 August 11, 2008

14.10.9

10.40.1-2 April 01, 2004

14.10.10

10.90.1-2 April 01, 2004

* 14.20.1-6

August 11, 2008

April 01, 2004

August 11, 2008

April 01, 2004

February 28, 2005

August 11, 2008

11 Flight Management, Navigation

(tab)

* 11.TOC.0.1-4

11.10.1-6

August 11, 2008

April 01, 2004

14.30.1-2

14.40.1-2

14.90.1-2

April 01, 2004

* 11.20.1-10

* 11.21.1-74

August 11, 2008

* 11.30.1-2 August 11, 2008

* = Revised, Added, or Deleted

August 11, 2008 P2.5.3

Preface -

List of Effective Pages

MD-88/90 Operations Manual

Page Date

15 Warning Systems (tab)

15.TOC.0.1

15.TOC.0.2

15.TOC.0.3-4

15.10.1-22

15.20.1-17

15.20.18-25

* 15.20.26

15.20.27

* 15.20.28

15.20.29-49

* 15.20.50

15.20.51-52

15.30.1-2

15.90.1-2

April 01, 2004

February 28, 2005

April 01, 2004

February 28, 2005

August 11, 2008

February 28, 2005

August 11, 2008

February 28, 2005

August 11, 2008

February 28, 2005

April 01, 2004

* = Revised, Added, or Deleted

P2.5.4

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows

Chapter 1

Section 0

Principle Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10.1

Principle Dimensions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10.1

MD-88 Turning Radius . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.10.3

Instrument Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.20.1

Forward Overhead Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.20.1

Aft Overhead Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.20.2

Center Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.20.3

Aft Pedestal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.20.4

Captain’s Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.20.5

First Officer’s Instrument Panel. . . . . . . . . . . . . . . . . . . . . . . . . 1.20.6

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.1

Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.1

Cockpit Lighting Controls . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.1

Exterior Light Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.5

Emergency Lighting Controls . . . . . . . . . . . . . . . . . . . . . . . 1.30.7

Passenger Cabin Signs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.9

Passenger Information Signs . . . . . . . . . . . . . . . . . . . . . . . . 1.30.9

Doors and Windows. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.10

Flight Deck Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.10

Flight Deck Door Control Panel. . . . . . . . . . . . . . . . . . . . . 1.30.12

Remote Access System (RAS) Control Panel . . . . . . . . . . 1.30.13

Passenger Forward Entrance Door . . . . . . . . . . . . . . . . . . . 1.30.14

Forward and Aft Service Doors . . . . . . . . . . . . . . . . . . . . . 1.30.15

Passenger Aft Cabin Door and Stair. . . . . . . . . . . . . . . . . . 1.30.16

Emergency Exits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.20

Clearview Window . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.20

FWD Cabin Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.21

Aft Cabin Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.22

August 11, 2008 1.TOC.0.1

Airplane General, Emergency

Equipment, Doors, Windows -

Table of Contents

MD-88/90 Operations Manual

Tailcone Evacuation Slide . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.24

Overwing Emergency Exit (4) . . . . . . . . . . . . . . . . . . . . . . 1.30.28

Cockpit Seats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.29

Manual Pilot Seat Controls . . . . . . . . . . . . . . . . . . . . . . . . 1.30.29

Pilot Eye Locator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.31

Oxygen Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.32

Crew O2 Mask (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.32

Passenger Oxygen Mask Switch . . . . . . . . . . . . . . . . . . . . 1.30.34

Passenger Cabin Portable Oxygen Bottle. . . . . . . . . . . . . . 1.30.35

Cabin Oxygen. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.36

Emergency Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.38

Fire Extinguishers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.38

Overhead Annunciator Panel. . . . . . . . . . . . . . . . . . . . . . . . . . 1.30.39

System Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.1

Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.1

Aircraft Dimensions/Turning Radius . . . . . . . . . . . . . . . . . . . . 1.40.1

Flight Deck . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.1

Pilot Seats. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.1

Windows. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.2

Lighting Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.3

Exterior Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.3

Interior Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.4

Emergency Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.5

Passenger Information Signs . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.6

Oxygen Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.6

Flight Crew Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.6

Passenger Oxygen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.8

Passenger Seats . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.9

Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.10

Flight Deck Door Control . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.10

Passenger Entrance Doors and Stairs and Service Doors . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.10

1.TOC.0.2

August 11, 2008

Airplane General, Emergency

Equipment, Doors, Windows -

MD-88/90 Operations Manual

Table of Contents

Galleys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.12

Lavatories. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.12

Potable Water System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.12

Emergency Exits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.13

Flight Deck Emergency Exits. . . . . . . . . . . . . . . . . . . . . . . 1.40.13

Cabin Emergency Exits . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.13

Portable Emergency Equipment . . . . . . . . . . . . . . . . . . . . . . . 1.40.14

PBE Container . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.14

Special Considerations . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.15

Flotation Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.16

Flashlights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.17

Fire Extinguishers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.17

Lavatory Trash Container Extinguisher . . . . . . . . . . . . . . . 1.40.17

Emergency Locator Transmitter (ELT) . . . . . . . . . . . . . . . . . . 1.40.17

Passenger Cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.17

Flight Deck . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.17

ELT Operation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.17

Portable ELT System Description . . . . . . . . . . . . . . . . . . . 1.40.18

Emergency and Cabin Equipment Symbols . . . . . . . . . . . . . . 1.40.19

Emergency and Cabin Equipment Locations . . . . . . . . . . . . . 1.40.19

Two Class Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.20

One Class Configuration . . . . . . . . . . . . . . . . . . . . . . . . . . 1.40.21

OAP Messages/Lights. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.50.1

Blue Advisory Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.50.1

Amber Caution Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.50.1

MD-90 Differences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.1

Principle Dimensions. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.1

MD-90 Turning Radius . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.2

Instrument Panels. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.3

Forward Overhead Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.3

Aft Overhead Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.4

August 11, 2008 1.TOC.0.3

Airplane General, Emergency

Equipment, Doors, Windows -

Table of Contents

MD-88/90 Operations Manual

Center Instrument Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.5

Aft Pedestal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.6

Captain’s Instrument Panel. . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.7

First Officer’s Instrument Panel . . . . . . . . . . . . . . . . . . . . . . 1.90.8

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.9

Lavatory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.9

Passenger Information Signs . . . . . . . . . . . . . . . . . . . . . . . . 1.90.9

EOAP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.10

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.11

Emergency and Cabin Equipment Locations . . . . . . . . . . . 1.90.11

Lavatory Smoke Detection . . . . . . . . . . . . . . . . . . . . . . . . . 1.90.12

Passenger Entertainment System . . . . . . . . . . . . . . . . . . . . 1.90.12

1.TOC.0.4

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows

Principle Dimensions

Chapter 1

Section 10

April 01, 2004

JB1-3-0857

1.10.1

Airplane General, Emergency

Equipment, Doors, Windows -

Principle Dimensions

MD-88/90 Operations Manual

1.10.2

JB1-3-0857

April 01, 2004

MD-88 Turning Radius

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Principle Dimensions

99'

Minimum Width

For 180

Turn

74.3 ft

65.9 ft

10.2 ft

73.9 ft

80.7 ft

Steering Angle

Maximum

April 01, 2004

JB1-3-0857

1.10.3

Airplane General, Emergency

Equipment, Doors, Windows -

Principle Dimensions

MD-88/90 Operations Manual

Intentionally

Blank

1.10.4

April 01, 2004

MD-88/90 Operations Manual

Aircraft General, Emergency

Equipment, Doors, Windows

Instrument Panels

Forward Overhead Panel

Chapter 1

Section 20

BOTH

ON 1

BOTH

ON 1

BOTH

ON 2

BOTH

ON 2

BOTH

ON 1

BOTH

ON 2

TEST ERASE

FORWARD

BOTH

FAULT

FIRE

ARMED

MID

BOTH

B A

FAULT

FIRE

ARMED

PRESS TO ARM

AFT

BOTH

FAULT

FIRE

ARMED

FWD

SQUIBBS

MID AFT

SYSTEM

TEST

BTL 1 BTL 2

DISCH

AGT LOW

DISCH

AGT LOW

N 1

ENG SYNC

OFF

N 2

DISC

RISE

100

OUTLET

ELEC PWR

RISE

100

OUTLET

DISC

COCKPIT VOICE RECORDER

100

AC VOLTS

150

380

400

420

FREQUENCY

OPS

ALN

NAV

ATT

OFF

IRS MODE SELECT

ALIGN

ON BAT

BAT FAIL

FAULT

ALIGN

ON BAT

BAT FAIL

FAULT

ALN

NAV

ATT

OFF

GND

PROX

WARN

OVRD

NORM

TEST

WNDSHR

TEST

NORM

TEST

TEMP

180

TEMP

180

NORM

EMER

LTS

OFF

ARM

SMOK

AUTO

OFF

SEAT

BELTS

ICE PROTECT

4 6

HEATER CUR

CAPT

METER SEL

& HEAT

AUX F/O

P ITOT

RUD

LIM

OFF

RAT

PROBE

STALL

PROBE

STATIC

NORM

1.0

0 .25

AC LOAD

1.5

GALLEY

OFF

L GEN

RESET

OFF

L AC

BUS

1.5

1.0

1.5

1.0

LOAD

APU L BUS

OFF

EXT PWR

L BUS

OFF

START

PUMP

OFF

SYS

OFF

ENG

SYS

BOTH

FUEL

HEAT

OFF

IGN

OVRD

PNEU

PRESS

XTO

PUSH FOR RISE

CSD TEMP

APU GEN

RESET

NORM

1.0

0 .25

AC LOAD

1.5

APU

PWR

AVAIL

EXT

PWR

AVAIL

AC BUS X TIE

OPEN

AUTO

DC BUS X TIE

CLOSE

OPEN

START

OFF R

APU R BUS

OFF

EXT PWR

R BUS

OFF

R GEN

RESET

1.0

0 .25

AC LOAD

1.5

EXT

PWR

VOLT/FREQ

APU

AC VOLT/FREQ

DC BUS VOLT

L R

BATT

VOLT

BATT

AMP

R AC

BUS

1.5

1.0

1.5

1.0

LOAD

AMPS

VOLTS

100

110

APU

EGT

% MAX

CONT

110

100

0 20

FIRE AGENT

NO. 1 NO. 2

OFF

APU

AIR

OFF

DISCH

FIRE CONT

NORM

OFF

AIR COND

COLDER

MASTER

OFF

RUN

NON

RAM

OFF &

AGENT ARM

EMER PWR

OFF ON

START

EMER

PWR

IN USE

DOORS

AUTO

RAM

OFF

BATT

CKPT

DOOR

LEFT

OFF

CTR

AFT PUMPS

FUEL TANKS

RIGHT

OFF

AUTO

OFF

ON ON

LOW PRESSURE

INHIBIT EQUIPPED

FWD PUMPS

AUTO

OFF

AIR FOIL

TAIL

WINDSHIELD

ANTI-FOG

OFF

ANTI-ICE

ENG

OFF

AUTO

UNLK

LOCK

FAIL

UNLK

AUTO

DENY

FLT DECK DOOR

CKT BKR

OFF

STBY COMP

DIM

BRT

OFF

PANEL

OVHD CONSOLE LTS

OFF

FLOOD

THNDRSTRM

OFF

CKPT

FLOOD

ALT

THNDRSTRM

ATTENDANT

CALL

ANTI-SKID

OFF

ARM

STALL

TEST

MAX SPD WARN

TEST

SYS 2

OFF

SYS 1

PA VOL

L VALVE

COLD

TEMP

HOT

CONTROL

CKPT TEMP

AUTO

COLD

STOP

MANUAL

HOT

ATTND

RESET

PSI x 100

OFF

TEST

PRESS

TEST CKT

OFF

OVRD

YAW

DAMP

AIR CONDITIONING

PSI

4 x 100

R VALVE

COLD

TEMP

HOT

CONTROL

NORM

OVRD

MACH

COMP

RESET

TEST

ICE

FOD

CABIN

SPLY

TEMP SEL

CABIN

RADIO

RACK

VENTURI

FAN

SUPPLY

CABIN TEMP

AUTO

OFF

HP BLD

OFF

150

SCHED APL

1000 FT CABIN

AUTO

TAKEOFF & LAND UNPRESSURIZED

20 25 30 35

4 6 8 +

COLD

STOP

MANUAL

HOT

CABIN TEMP

120

AIR

COND

SHUTOFF

OVRD

AUTO INOP

AUTO 1

INOP

AUTO 2

INOP

100 FT

LDG ALT

CABIN

PRESSURE

30.0

29.9

29.8

LDG

BARO

FLOW

RATE LIMIT

DIFF/PRESS

PSI

CAB ALT

5 AUTO

RAM AIR

OFF

REPELLENT

RAIN

WIPER

OFF

ANNUN/DIGITAL

LTS TEST

L RES R

PARK SLOW

FAST

CABIN

CLIMB

1.5

DESCEND

1000 FT/MIN

1.5

PULL TO DIM

FLT RECORDER OFF

R OIL PRESS LOW

R GEN OFF

R CSD OIL PRESS LOW

R HYD PRESS LOW

PARKING BRAKES ON

ELEC ICE ENG CTRL

AUTO SLAT FAIL

SPOILER DEPLOYED

L OIL PRESS LOW

DOOR AFT CABIN

L AC BUS OFF

L START VALVE OPEN

MISC HYD MON DOOR

IRS 1

ATT MODE

IRS 2

ATT MODE

RAIN REPELLENT

RESERVE IN USE

L ENG ANTI-ICE

IGNITION SYS

B SELECTED

WING ANTI-ICE

CABIN OXYGEN

R ENG ANTI-ICE

CARGO FIRE

AC EMER BUS

OFF

TAIL COMP

TEMP HIGH

APU FIRE

CABIN ALT

DC EMER BUS

OFF

August 11, 2008

1.20.1

Aircraft General, Emergency

Equipment, Doors, Windows -

Instrument Panels

MD-88/90 Operations Manual

Aft Overhead Panel

APU TA

R ENG LOOPS

ATA LINK MU

EMERGENCY INVERTER

EMERGENCY FLOOD LIGHT

APU PWR AV

MAINTENANCE INTERPHONE

EXT PWR AV

GROUND SER

MECH CALL

WHITE FLOOD LIGHTS

LIGHTS ARM AND CHARGE

GND TEST

POWER IN USE LIGHT

AIR CONDITION REGULA

DC BUS SENSING

CROSS TIE CONTROL

EPR, FF DISPLA

AIR CONDITION FLOW CONTROL

VHF NA

AC BUS SENSING

VERTICAL SPEED IND

VHF NA

AIRSPEED IND 28 V

LIGHTS 28 V

HEADING 28 V

EMERGENCY NA

V INSTR XFMR

1.20.2

August 11, 2008

MD-88/90 Operations Manual

Aircraft General, Emergency

Equipment, Doors, Windows -

Instrument Panels

Center Instrument Panel

VHF

NAV

CRS

OFF

FMS

OVRD

SPD

SEL

MACH

SEL

SPD MACH

EPR

LIM

NAV

AUTO

THROT

OFF

VOR

LOC

ILS

AUTO

LAND

HDG

AND

ANU

VERT

SPD

ALT

HOLD

IAS

MACH

AP ON

VNAV

1 2

ALT

OFF

TURB

VHF

NAV

AGENT

DISCH

PULL

AGENT 1

LOW

AGENT 2

LOW

LOOPS A

TEST

FIRE

BELL OFF

AGENT

DISCH

LOOPS B

TEST

PULL

PWS INOP

100

FT.

000

1 0 1 3

ALT

IN hg

2 9 9 2

BARO

IAS UNITS

0 60

IAS KNOTS

CMD EPR

PULL

REVERSE

THRUST

REVERSE

UNLOCK

1.2

1.4

1.0

1.6

1.0

2.2

2.0

2.00

EPR LIMIT

1.63

CMD

1.63

CMD

EPR

1.2

1.4

1.0

1.6

1.0

2.2

2.0

% RPM

REVERSE

THRUST

REVERSE

UNLOCK

2 1 2 1

EGT

3 2 5 3 2 5

% RPM

5 2 5 2

100

FUEL

FLOW USED x 10

PPH

PUSH

FUEL USED

RESET

CMD EPR

PULL

RAT

TEMP

FUEL

ENGINE OIL

PRESS

45 PSI 0

TEMP

QUANTITY

QTS

HYDRAULIC

PRESS

PSI x 100

QUANTITY

QTS 14

SLATS FLAPS

T/O

DISAG

AUTO

LAND

READY

ART

OVRD

FAIL

GPWS

TERRAIN

OVRD

AUTO

OFF

ART

FLOW

OFF

GEAR

DOOR

OPEN

LEFT NOSE RIGHT

T.O.

MCT

T.O.

FLX

ASSUMED

TEMP

CL CR

TEST

NO MODE

ART

MUST

OFF

WHEN

T.O.

FLX

SEL

A B

TEST

FUEL QTY

LBS

L MAIN R MAIN

CTR

TOTAL FUEL

GROSS WT C S

ZFW

GEAR

HDL

REL

DOWN

BRT

80 160 320

MIN

GAIN

OFF

TCAS

TEST

WX/TCAS

TURB

MAP

AUTO

CRS

RNG 80 MRK 20

RTE

PREV

PAGE

NEXT

PAGE

MENU

LEGS CLB

FIX

CRZ DES

HOLD PROG EXEC

1 2 3

4 5 6

M N O P Q

7 8 9

0 +

–

U V

DEL

BRT

CLR

RTE

PREV

PAGE

NEXT

PAGE

MENU

LEGS CLB

FIX

CRZ DES

HOLD PROG EXEC

1 2 3

4 5 6

M N O P Q

7 8 9

0 +

–

U V

DEL

BRT

CLR

April 01, 2004

1.20.3

Aircraft General, Emergency

Equipment, Doors, Windows -

Instrument Panels

MD-88/90 Operations Manual

Aft Pedestal

TAKE-OFF

CONDTN

LONG TRIM

FLAP

NOSE

SPD

BRK

RET

RUD

HYD

CONT

MAN

1/4

1/2

3/4

EXT

GEAR

HORN

OFF

FUEL

ALT

LONG TRIM

NOSE

FUEL

FEED

DESCEND

CABIN

ALT

FUEL

NOSE

OFF OFF

CLIMB

VALVE

CLOSE

UP UP/RET

T.O.

EXT

LAND

EXT

FLAP T.O.

SEL

FLAP/

SLAT

VALVE

OPEN

COMM

TFR

COMM

TFR

NORM

ADF

ANT

ALT OFF ALT ON

STBY TA

TEST TA/RA

ATC 1

ATC

FAIL

ATC

IDENT

SELCAL DATA LINK

ALT

VHF - 1 VHF - 2 VHF - 3

PRESS TO RESET

MSG PRINTER

PANEL

CTR INSTR & PED LTS

DIGITAL FLOOD

1 2 : 0 0

MAIN MENU

PREFLIGHT

ENROUTE

POSTFLIGHT

UTC TIME

FLT LOG

MSGS

RCVD

DOWNLINK

WX/ATIS

MAINT MENU MISC MENU

D 1 3 1 . 5 5

MAIN

LGHT

PAGE

OFF

STABILIZER TRIM

OFF

STOP

NORM

OFF

RIGHT

PNEU

X-FEED

VALVE

OPEN

RUDDER TRIM

PNEU

X-FEED

VALVE

OPEN

SOL

ARM

OFF

MIN

DISARM

LAND

MED

MAX

T.O.

AUTO BRAKE

LEFT

WING DOWN

RIGHT

1.20.4

AILERON TRIM

April 01, 2004

MD-88/90 Operations Manual

Aircraft General, Emergency

Equipment, Doors, Windows -

Instrument Panels

Captain’s Instrument Panel

CAUTION

MASTER

ARNING

MASTER

ABS

E T

April 01, 2004

1.20.5

Aircraft General, Emergency

Equipment, Doors, Windows -

Instrument Panels

MD-88/90 Operations Manual

First Officer’s Instrument Panel

MASTER

ARNING

MASTERCAUTION

ABS

12 9

E T

GMT

1.20.6

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows

Controls and Indicators

Chapter 1

Section 30 Lighting

Cockpit Lighting Controls (Sheet 1)

OFF

ANU

PANEL

OVHD CONSOLE LTS

FLOOD

OFF

MAP LIGHT (2)

CKT BKR

OFF

DIM

BRT

STBY COMP

THNDRSTRM

OFF

CKPT

FLOOD

OFF

ALT

THNDRSTRM

MAP LT

CENTER

GLARESHIELD

OFF

FORWARD OVERHEAD PANEL

JB1-3-0861

OVHD CONSOLE LTS Knobs

PANEL - provides on/off and intensity control for integral lights on overhead panel.

FLOOD - Provides on/off and intensity control for overhead panel flood lights.

CKT BKR LT Switch

Provides OFF, DIM, and BRT control for the CB panel floodlights.

STBY COMP LT Switch

Provides OFF, DIM, and BRT control for the standby compass light.

THNDRSTRM LT Switch

OFF - Returns control of lighting to individual controls

ON - Overrides individual lighting controls and illuminates all cockpit floodlights to full intensity.

April 01, 2004 1.30.1

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

CKPT FLOOD Lights Switch

OFF - Extinguishes cockpit overhead floodlights.

ON - Illuminates one light in both cockpit overhead floodlights.

ALT THNDRSTRM - Illuminates both lights in both cockpit overhead floodlights.

MAP LT knob

OFF - Extinguishes map light.

Clockwise rotation of knob controls intensity of Map light.

Light is located in the ceiling above each pilot.

FGCP Digital Lights Knob

Controls intensity of FGCP digital readouts.

FGCP Modes Buttons and Edge Lighting Knob

Controls intensity of FGCP mode buttons and panel background lighting.

1.30.2

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Cockpit Lighting Controls (Sheet 2)

CHART

HOLDER (2)

FLOOR LTS

BRT

DIM

OFF

PANEL

INSTR PANEL LTS

DIGITAL

FLOOD

CONTROL WHEEL

PANEL

CTR INSTR & PED LTS

DIGITAL FLOOD

OFF OFF OFF

CAPT AND F/O INSTRUMENT PANELS

OFF

PEDESTAL

OFF

BRIEFCASE

LIGHT (2)

GUSSET PANELS

JB1-3-0862

Chart Holder Light Knob

On/off switch and intensity control for chart holder light.

FLOOR LTS Switch (2)

Provides BRT, DIM, and OFF for cockpit floor lights.

INSTR PANEL LTS Knobs (CAPT& F/O)

PANEL - Provides on/off and intensity control for instrument integral lights.

DIGITAL - Provides on/off and intensity control for digital readouts on respective flight mode annunciator.

FLOOD - Dual on/off switch and intensity control for instrument panel fluorescent and flood lights. Small knob controls incandescent instrument floodlight. Large knob controls fluorescent instrument floodlights.

BRIEFCASE LT Knob

Provides on/off and intensity control for Flight Kit stowage area.

April 01, 2004

1.30.3

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

CTR INST & PED LTS Knobs

PANEL - Dual on/off switch and intensity control for center instrument panel and pedestal integral lights. Small knob controls the upper and center instrument panel lights. Large knob controls pedestal lights.

DIGITAL - Provides on/off and intensity control for digital readouts on fuel quantity display unit.

FLOOD - Provides on/off and intensity control for center instrument panel and pedestal floodlights.

1.30.4

April 01, 2004

Exterior Light Controls

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

WING LDG LTS

RET

EXT

OFF

EXT ON

FLOOD LTS

GRD

OFF

NOSE LTS

OFF

DIM

BRT

GLARESHIELD, LEFT SIDE

WING/NACL

OFF

ONLY

ANTI

COLLISION

OFF

POS/

STROBE

OFF

POS

BOTH

GLARESHIELD, RIGHT SIDE

WING LANDING

LIGHT (2)

AJNTI-COLLISION

LIGHT (2)

ENGINE

NACELLE

FLOODLIGHT (2)

AFT POSITION/

STROBE

LIGHT (2)

GROUND

FLOODLIGHT (2)

WING LEADING

EDGE FLOODLIGHT (2)

NOSE LANDING

AND TAXI LIGHTS (2)

FORWARD

POSITION

LIGHT (2)

FORWARD

STROBE

LIGHT (2)

April 01, 2004

1.30.5

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

WING LDG LTS Switch (L/R)

RET - Retracts wing landing lights.

EXT OFF - Extends wing landing lights with lamps off.

EXT ON - Extends wing landing lights with lamps on.

NOSE LTS Switch

OFF - Extinguishes nose gear landing and taxi lights.

DIM - Nose gear landing and taxi lights are dim.

BRT - Nose gear landing and taxi lights are bright level.

Nose gear landing and taxi lights automatically extinguish when landing gear handle is moved up.

FLOOD LTS GRD Switch (L/R)

OFF - Extinguishes ground flood lights.

ON - Illuminates ground flood lights.

WING/NACL Lights Switch

OFF - Extinguishes all wing leading edge and engine nacelle floodlights.

ON - Illuminates both wing leading edge and both engine nacelle floodlights.

R ONLY - Illuminates right wing leading edge and right engine nacelle floodlights.

ANTI-COLLISION Lights Switch

OFF - Extinguishes anti-collision lights.

ON - Illuminates upper and lower anti-collision lights.

POS/STROBE Lights Switch

OFF - Extinguishes forward and aft position and strobe lights.

POS - Illuminates forward and aft position lights only.

BOTH - Illuminates the forward and aft position lights, and strobe lights are activated when airborne.

1.30.6

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Emergency Lighting Controls

EMER

LTS

OFF

ARM

FLIGHT DECK OVERHEAD PANEL

EMERGENCY

LIGHT

ARM

OFF

FWD FLIGHT ATTENDANT PANEL

JB1-3-0787

August 11, 2008

1.30.7

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

EMER LTS Switch (Flight Deck)

OFF - Prevents emergency evacuation lights from illuminating. EMER

LIGHT NOT ARMED message is on. This position can be overridden and emergency lights switched ON at the EMERGENCY LIGHTS switch on the forward attendant’s panel.

ARM - Normal flight position. Emergency evacuation lights are off. Connects battery packs charging circuits to EMERGENCY DC BUS. Emergency evacuation lights illuminate automatically with loss of power to the EMER

DC bus.

ON - Simulates electrical power failure. All emergency evacuation lights and

EMER LIGHT NOT ARMED message illuminate.

CAUTION:

Emergency evacuation lights cannot be switched off unless DC TRANSFER BUS is powered.

EMERGENCY LIGHTS Switch (FWD Cabin)

OFF - Normal guarded position. Emergency evacuation lights are controlled by EMER LTS switch on the pilot’s overhead panel.

ARM - Momentarily placing this switch to ARM and releasing to ON illuminates the emergency evacuation lights, if the flight compartment EMER

LTS switch is in the OFF position.

ON - Illuminates emergency evacuation lights regardless of position of

EMER LTS switch on the pilot’s overhead panel.

1.30.8

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Passenger Cabin Signs

Passenger Information Signs

SMOK

AUTO

SEAT

BELTS

OFF

P L E A S E LO C K D O O R ED PI CU OC

RETURN T

O CABIN

Attendant Call

AFT L AVATORIES

OCCUPIED

NO SMOK Switch

AUTO - Chime sounds when landing gear is extended.

OFF - Deactivates chime.

ON - Activates chime in cabin attendant stations.

NOTE: NO SMOKING signs illuminate whenever cabin altitude exceeds

10,000 feet, regardless of switch position.

SEAT BELTS Switch

AUTO - FASTEN SEAT BELTS and RETURN TO CABIN signs illuminate when slats are extended. Chime sounds.

OFF - FASTEN SEAT BELTS and RETURN TO CABIN signs extinguish.

ON - Illuminates FASTEN SEAT BELTS and RETURN TO CABIN signs.

NOTE: Only FASTEN SEAT BELTS signs illuminate whenever cabin altitude exceeds 10,000 feet regardless of switch position.

NO SMOKING/SEAT BELT Sign (typical)

Lavatory Door Lock (Typical)

Lavatory OCCUPIED placard is visible when door is locked. Switch on door jamb is actuated by latching mechanism.

August 11, 2008

1.30.9

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Doors and Windows

Flight Deck Door

D-Ring Latch

Door Knob/Latch

A key can be used to lock and unlock the deadbolt from the cabin as required by ground personnel.

1.30.10

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Decompression Panels

Door Louvers

Used for equalization of pressure between flight deck and cabin. Louvers may be closed during smoke conditions by raising sliding panel on flight deck side of door.

Decompression Latches

Each of the two decompression panels is held on to the door by a decompression latch just above each panel. If rapid decompression occurs within the flight deck, the latches will release and the door panels will blow open towards the flight deck. Each decompression latch has an indicator that must be aligned with the green band.

View Window

Deadbolt Latch

A rotary latch is used to lock and unlock the deadbolt from the flight deck.

The rotary latch has three positions:

UNLOCKED

LOCKED - Denies cabin key access

LOCKED - Permits cabin key access (not used by flight crews).

August 11, 2008

1.30.11

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Flight Deck Door Control Panel

1 2

UNLK

AUTO

DENY

AUTO

UNLK

LOCK

FAIL

FLT DK DOOR

AURAL

ALERT

AUTO UNLK Light (Amber)

Indicates access code has been entered, 60 second delay has begun, and automatic flight deck door unlock is pending.

LOCK FAIL Light (Red)

Flight deck door is unlocked.

Door Control Selector

AUTO - Spring-loaded position. Locks the flight deck door and arms the system for a keypad entry request.

UNLK - Push and turn to select. Unlocks flight deck door. Manually overrides

DENY lockout period.

DENY - Turn to select. Cancels Keypad entry request.

NOTE:

There will be a five minute lock-out period before the access code can be re-entered, unless UNLK position is selected.

1.30.12

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Remote Access System (RAS) Control Panel

7 8

JB1-3-0867

Keypad LEDs

YELLOW - 60 second delay in progress.

RED - Entry denied or door re-locked.

GREEN - Door unlocked.

Keypad Entry Keys

Code Entry Keys - Ten numeric keys (0-9) for access code input and one enter

(#) key. The (*) key is not used.

April 01, 2004

1.30.13

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Passenger Forward Entrance Door

EXTERNAL

DOOR

HANDLE

PASSENGER

FORWARD

ENTRANCE DOOR

LATCHED OPEN

RELEASE

INTERNAL DOOR HANDLE

1.30.14

DOOR HOLD-OPEN

LATCH (TYPICAL)

PASSENGER FORWARD

ENTRANCE DOOR

JB1-3-0869

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Forward And Aft Service Doors

ESCAPE SLIDE

TO OPERATE

OPEN AIRPLANE ENTRY DOOR

ASSIST

HANDLE

SERVICE DOOR

INTERNAL HANDLE

FORWARD

SERVICE

DOOR

OPEN

EXIT

SERVICE DOOR

EXTERNAL HANDLE

(TYPICAL)

AFT

SERVICE

DOOR

WARNING

AUTOMATIC ESCAPE SLIDE

DISARM SLIDE BEFORE NORMAL

OPERATION OF DOOR

JB1-3-0871

April 01, 2004

1.30.15

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Passenger Aft Cabin Door And Stair (Sheet 1)

STAIRWAY

CONTROL PANEL

AFT ENTRANCE DOOR

HOLD-OPEN LATCH

(Lift up to release door, from open position.)

STAIR

LAVATORY

PARTITION

VIEW LOOKING AFT

DOOR

STAIR LIGHT SWITCH

(Aft cabin attendant's panel)

EXIT

LOWER TO ARM SLIDE

CENTER HEAD REST PAD

NOTE

When raised (as shown), normal door release handle and instructions are stenciled. When lowered, emergency door/stairway handle and instructions are stenciled.

AFT ATTENDANT'S SEAT.

SEAT BOTTOM IS SPRING-

LOADED TO FOLD INTO

DOOR RECESS TO ALLOW

THE DOOR TO OPEN.

VIEWING

WINDOW

OPTION

PASSENGER AFT

ENTRANCE DOOR

HANDLE

AND CONSTRUCTED SO THAT IT

CANNOT BE OPENED DURING FLIGHT

JB1-3-0872B

1.30.16

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Passenger Aft Cabin Door And Stair (Sheet 2)

PULL AND TURN

OPEN

STAIR OPERATING

HANDLE INSIDE

HANDLE NOT

INSTALLED

RETURN

TO OFF

OFF

SERVICE LIGHT

SWITCH

OPEN CLOSE

PASSENGER AFT ENTRANCE

STAIRWAY INTERIOR

CONTROL PANEL

STAIR

DOOR

OPEN

STAIR

DOWN

VIEWING

WINDOW

PASSENGER AFT

ENTRANCE DOOR

HANDLE (EXTERIOR)

OPTION

JB1-3-0873A

April 01, 2004

1.30.17

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Stairway Control Handle

Handle not installed.

STAIR DOOR OPEN Light

Illuminates to indicate stairway door is unlatched.

STAIR DOWN Light

Illuminates to indicate stairway is down and locked.

1.30.18

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Passenger Aft Cabin Door And Stair (Sheet 3)

RETURN TO OFF

CLOSE OFF OPEN

OPEN DOOR

FOR ACCESS

STAIR CONTROL

PASSENGER AFT ENTRANCE

STAIRWAY EXTERIOR

CONTROL PANEL

STAIR

LIGHT

SWITCH

JB1-3-0874B

JB1-3-0874A

Stairway Control Handle

OFF - Handle is spring-loaded to the OFF (center) position.

OPEN - Extends stairway. Hold in OPEN position until stairway is fully down and locked. If control handle resistance is encountered and no stair operation is observed, move handle to CLOSE and then to OPEN. Handle will return to

OFF (center) position when released.

CLOSE - Retracts stairway. Hold in CLOSE position until stairway is fully retracted and locked. If control handle resistance is encountered and no stair operation is observed, move handle to OPEN and then to CLOSE. Handle will return to OFF (center) position when released.

April 01, 2004 1.30.19

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Emergency Exits

Clearview Window

TO OPEN CLEARVIEW

WINDOW:

Pull handle aft to disengage overcenter lock.

Pull handle inboard to move window inboard.

Pull handle aft so that window slides aft to an open locked position.

EXTENDED POSITION

(COVER PLATE REMOVED)

ESCAPE LINE

PULL

COVER PLATE

CAG(IGDS)

CLEAR VIEW WINDOW

AND ESCAPE LINE (TYPICAL)

KB1-3-0017

KB1-3-0017

1.30.20

April 01, 2004

FWD Cabin Door

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

LIFT TO OPEN

ESCAPE

SLIDE

CONTAINER

ESCAPE SLIDE

TO OPERATE

OPEN AIRPLANE ENTRY DOOR

JERK HANDLE TO

INFLATE

AFT SERVICE DOOR

SLIDE BACK-UP MANUAL

INFLATION HANDLE.

SLIDE PRESSURE

GAGE INSPECTION

WINDOW

FWD

FLOOR

FITTING

GIRT BAR

AFT FLOOR

FITTING

GIRT BAR

TO INSTALL GIRT BAR:

Insert end of girt bar into forward floor fitting. Then push aft end of girt bar in against spring-loaded latch.

TO REMOVE GIRT BAR:

Push spring-loaded latch out and remove girt bar.

JB1-3-0788

JB1-3-0788

April 01, 2004

1.30.21

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Aft Cabin Door

FOR EMERGENCY USE ONLY

REMOVE COVER

AFT

CABIN

DOOR

VIEWING

WINDOW

FINGER

HOLE

EXIT

EMERGENCY EXIT CONTROL

HANDLE COVER REMOVED

LIFT TO DISARM SLIDE

1.30.22

AFT ATTENDANT’S SEAT (STOWED)

KB1-3-0018

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Emergency Exit Handle (Cover Removed)

Rotate Clockwise - Unlatches door. Tailcone is jettisoned and evacuation slide is automatically deployed when door is opened.

Center Head Rest Pad

Lowered - (Shown) Emergency exit handle with cover exposed.

Raised - Normal door handle exposed to latch and unlatch Aft cabin door.

April 01, 2004

1.30.23

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Tailcone Evacuation Slide (Sheet 1)

TAILCONE

LANYARD

PULL

PULL HANDLE

FOR EXIT

EXIT

LEFT SIDE TAIL COMPARTMENT

EMERGENCY

EXIT

FOR TAILCONE

JETTISON

PUSH DOOR

PULL HANDLE

PUSH

PULL

INSIDE LOCK CABLE

MUST BE RE-INSTALLED

IF HANDLE IS PULLED

EXTERIOR TAILCONE

JETTISON HANDLE

WARNING

IF DECAL

IS PUNCTURED

NOTIFY CAPTAIN

IMMEDIATELY

1.30.24

KB1-3-0018

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Back-Up Tailcone Jettison Handle (Tail Compartment)

PULL - Jettisons tailcone and deploys slide.

Emergency Walkway

Folds into ceiling when aft stairway is extended. When stairway is retracted, walkway is in the lowered position.

Tailcone Release Mechanism Placard

NOTE:

Punctured decal indicates need for tailcone release mechanism inspection.

Ceiling Stops

Emergency walkway is spring and cable operated and may be manually overridden by pulling down on the stops in the event of a malfunction.

April 01, 2004

1.30.25

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Tailcone Evacuation Slide (Sheet 2)

RELEASE

TAILCONE

LIFT RED

TAB

ROLL

SLIDE

OUT

RELEASE

LANYARD TAB

STEP

RELEASE

LIFT RED

ROLL

SLIDE

OUT

TAILCONE LANYARD

SLIDE PRESSURE

GAGE INSPECTION

WINDOW

STEP

SLIDE MAINTENANCE

SLIDE LATCH

(2 PLACES)

LANYARD

RELEASE RING

GIRT BAR LATCH

(2 PLACES)

GIRT BAR

WALKWAY

ASSIST

PLATFORM

TAILCONE

SLIDE IN DEPLOYED

POSITION

INFLATION

HANDLE

JERK HANDLE TO

INFLATE

PULL

GIRT BAR

AFT

WALKWAY

1.30.26

KB1-3-0018

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Tailcone Evacuation Slide

Normally the slide is automatically deployed and inflated when tailcone is jettisoned. If malfunction occurs after tailcone has been jettisoned, deploy slide manually per stenciled instructions.

Slide Manual Deployment Handle

LIFT - Releases slide from latches to deploy slide manually.

Slide Visual Indicator

Indicator erects showing green stripes indicating slide is usable.

April 01, 2004

1.30.27

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Overwing Emergency Exit (4)

EMERGENCY EXIT

PUSH HANDLE RELEASE.

PULL THE HANDLE AND AT

THE SAME TIME PUSH IN

ON TOP OF DOOR. LIFT UP

FORCIBLY.

OVERWING

EMERGENCY DOOR REMOVAL

FROM INSIDE AIRPLANE

(R/H DOOR SHOWN)

CAG(IGDS)

OVERWING

EMERGENCY DOOR REMOVAL

FROM OUTSIDE AIRPLANE

(L/H DOOR SHOWN)

KB1-3-0019

KB1-3-0019

1.30.28

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Cockpit Seats

Manual Pilot Seat Controls

LEFT SEAT SHOWN,

RIGHT SEAT SIMILAR

JB1-3-0858

April 01, 2004

1.30.29

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Dual Shoulder Harness

Arm Rest (2)

Both armrests can be stowed in vertical position parallel to seat back. When armrests are horizontal to seat cushion position, rotation of knob at forward end of armrest moves armrest up or down from horizontal.

Thigh Rest

Recline Control Lever

Pressing lever permits seat to be reclined.

Seat Vertical Adjustment Lever

Seat vertical height is adjusted by pressing button and lifting up on lever arm.

Desired seat height is maintained by releasing button and lever.

Thigh Pad Adjustment Knob

Rotation of knob adjusts thigh pad up or down.

Track Lock Control Handle

When handle is moved aft, seat may be moved froward or aft. When handle is released, seat should be moved until mechanism locks seat in desired position.

Lap Buckle

Inertial Reel Lock Handle

UP - Shoulder harness free to move until automatically locked by forces on inertial reel.

DOWN - Shoulder harness locked in forward extension at time handle is placed in DOWN position. Inertial reel will retract if forward pressure is released

10.

Lumbar Adjustment Knob (2)

Rotation of knob adjusts lumbar tension in or out.

1.30.30

April 01, 2004

Pilot Eye Locator

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

RIGHT EYE

TARGET DOT

RIGHT EYE TARGET

LOCATOR RING

Adjust seat until locator target dot is centered in locator ring.

JB1-3-0857

Pilot Eye Locator

Sit normally in seat.

Rotate head about vertical axis to look directly at locator.

Close left eye.

Adjust seat until locator target dot is centered in locator ring.

April 01, 2004

1.30.31

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Oxygen Systems

Crew O

Mask (3)

RESET

TEST

100%

PUSH

PRESS

TEST

EMERGENCY

OXYGEN

MASK

GOGGLE VENT

VALVE

MASK

MICROPHONE

REGULATOR

JB1-3-0876

INFLATED HARNESS

1 EACH CREWMEMBER STATION

1.30.32

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Flow Indicator

Shows a yellow cross when oxygen is flowing, black when not flowing.

Release Levers (red)

SQUEEZE AND PULL - Releases mask from storage box.

Oxygen flow begins when left storage box door is opened.

Flow indicator shows a yellow cross momentarily as harness inflates.

EMERGENCY/TEST Selector

ROTATE (in direction of arrow) - 100% oxygen is supplied under positive pressure at all cabin altitudes.

PUSH - Tests positive pressure supply to regulator.

Left Door

CLOSED - Turns oxygen off.

OPEN - Turns oxygen on.

RESET/TEST Slide Lever (spring-loaded)

PUSH - Mask stowed, turns oxygen on momentarily to test regulator. Mask not stowed and left stowage box door closed and reset turns oxygen off.

NORMAL/100% Selector

NORMAL - Air/oxygen mixture on demand. Ratio is dependent on cabin altitude.

100% - Supplies pure oxygen on demand.

April 01, 2004

1.30.33

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Passenger Oxygen Mask Switch

PASS OXY

MASK

EJECT

NORM

PASS OXY MASK SWITCH

(BEHIND F/O SEAT

)

PASS OXY MASK Switch

EJECT - (Momentary) Energizes circuit to release door latches and open all oxygen compartment doors at any altitude.

NORM - Door latches on all oxygen compartments will open automatically any time cabin altitude reaches approximately 14,000 feet.

CAUTION: Holding switch in EJECT position in excess of five seconds may cause damage to the oxygen compartment latches

1.30.34

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Passenger Cabin Portable Oxygen Bottle

PLACARD

1. Slip sling strap over head or shoulder or hold on lap while using.

2. Turn ON - OFF knob counterclockwise to release oxygen to regulator.

3. Fit mask to face and adjust with strap.

4. To determine flow of oxygen to mask, observe inflated green portion of breathing bag.

After using oxygen, remove mask from face and

Pressure Gauge

Minimum is 1600 psi.

Sling

ON - OFF Valve

ON - Provides a constant flow of oxygen to the continuous flow mask.

OFF - Shuts off flow of oxygen to the continuous flow mask.

Pressure Regulator

Regulates pressure of oxygen flow to continuous flow mask.

April 01, 2004

1.30.35

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MD-88/90 Operations Manual

Cabin Oxygen (Sheet 1)

OXYGEN

GENERATOR

OXYGEN

MASK (2)

ATTENDANT’S OXYGEN

COMPARTMENT (AFT)

OXYGEN

MASK (2)

OXYGEN

GENERATOR

1.30.36

LAVATORY OXYGEN

COMPARTMENT (TYPICAL)

KB1-3-0128

April 01, 2004

Cabin Oxygen (Sheet 2)

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

OXYGEN

GENERATOR

OXYGEN MASKS

PASSENGER OXYGEN

COMPARTMENT

(TYPICAL)

(ONE OVER EACH SEAT ROW)

KB1-3-0128

Manual Door Release (typical for all oxygen compartment doors)

Insert small rod to open door.

Permits manual operation of door.

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MD-88/90 Operations Manual

Emergency Equipment

Fire Extinguishers

LEVER

NOZZLE

RING PIN

HANDLE

TO OPERATE: PULL RING PIN.

HOLD EXTINGUISHER UPRIGHT.

AIM NOZZLE AT BASE OF FIRE.

LIFT HANDLE. PRESS LEVER.

USE SIDE TO SIDE MOTION.

HALON BCF FIRE EXTINGUISHER

HANDLE

TURN

DISCHARGE

NOZZLE

LEVER

NOTE:

FIRE EXTINGUISHERS

ARE INSTALLED IN

QUICK-DISCONNECT

SUPPORT BRACKETS

TO OPERATE

TURN HANDLE TO RIGHT AS FAR

AS POSSIBLE.

HOLD ERECT.

PRESS LEVER TO DISCHARGE.

DIRECT STREAM AT BASE

OF FLAME.

CAG(IGDS)

WATER FIRE

EXTINGUISHER

KB1-3-0025

1.30.38

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Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

Overhead Annunciator Panel

OAP (Sheet 1))

FLT RECORDER OFF

R OIL PRESS LOW

R GEN OFF

R CSD OIL PRESS LOW

R HYD PRESS LOW

PARKING BRAKES ON

ELEC ICE ENG CTRL

AUTO SLAT FAIL

SPOILER DEPLOYED

L OIL PRESS LOW

DOOR AFT CABIN

L AC BUS OFF

L START VALVE OPEN

MISC HYD MON DOOR

BAS

ELEVAT

RAIN R

RESER

L ENG

L FU

AC E

OAP Display Screens

Left display screen is filled from top with messages. After 6 messages, additional messages will appear at top right display screen. If both screens are full, latest message will appear at bottom of right screen.

Scroll Buttons

Appropriate scroll button will be illuminated to indicate messages stored off screen. Push to scroll messages up or down when messages are stored above or below those displayed on screens.

MON (Monitor) CUE Light

Illuminates to indicate fault exists in annunciator panel.

PUSH - Displays suspect annunciations on right screen.

Cue Light (7) (amber)

Associated system cue light flashes 4 times on detection of a caution and a new message is displayed on screen. Pushing cue light displays messages associated with that system. If cue light is pushed and held, messages will be displayed for 10 seconds. If cue light is pushed and released, messages will be displayed for 5 seconds. Messages will remain in message system until emergency or malfunction is corrected.

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MD-88/90 Operations Manual

OAP (Sheet 2))

IRS 1

ATT MODE

ELEVATOR

AT LIMIT

(B)

L ENG ANTI-ICE

ON (B)

L ENG ANTI-ICE

RESERVE IN USE

(B)

L ENG IGN

ON (B)

ENGINES COOL

APU STARTER

(B)

IGNITION SYS

ON (B)

TAIL DE-ICE

(B)

TAIL DE-ICE

ON (B)

IRS 2

ATT MODE

RUDDER TRAVEL

UNRESTRICTED

(B)

R ENG ANTI-ICE

ON (B)

CABIN OXYGEN

R ENG IGN

(B)

DOOR

AC EMER BUS

OFF

APU FIRE

INSTALLED ON SOME AIRPLANES

DC EMER BUS

OFF

ANNUN/DIGITAL

LTS TEST

MASTER

CAUTION

GLARESHIELD

MASTER

WARNING

GLARESHIELD

PULL TO DIM

JB1-3-0859

Advisory Lights

R - Red light - Brings on MASTER WARNING.

B - Blue light - Indicates an advisory. This is a normal condition.

Warning lights will stay illuminated until emergency or malfunction is corrected. Blue lights stay illuminated until corresponding system is off or condition no longer exists.

ANNUN/DIGITAL LTS Switch

TEST - Momentary. Push to test all OAP display elements (LED displays, annunciators, etc.) and the digital lights of the Captain’s and First Officer’s

FMA and VHF/NAV control panel, Flight Guidance Control Panel, Fuel

Quantity Panel, Engine Display Panel, and Systems Display Panel, Captain’s and First Officer’s Master Warning and Master Caution lights.

PULL TO DIM - Dims all messages except DOOR Cue light and all dimmable warning, caution, and advisory lights on the instrument panel that do not have individual controls.

MASTER WARNING Light (2) (red)

Both lights will illuminate when red lights on annunciator panel illuminate.

Pushing either light will extinguish both MASTER WARNING lights and reset the system for subsequent indications.

1.30.40

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Airplane General, Emergency

Equipment, Doors, Windows -

Controls and Indicators

MASTER CAUTION Light (2) (amber)

Both lights will illuminate when caution messages are displayed on the OAP.

Pushing either light will extinguish both MASTER CAUTION lights and reset the system for subsequent indications.

April 01, 2004

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Controls and Indicators

MD-88/90 Operations Manual

Intentionally

Blank

1.30.42

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows

Systems Description

Chapter 1

Section 40

Introduction

This chapter provides the flight crew with general airplane information and specific descriptive information for the following systems:

• Lavatories and galleys

• Passenger forward entrance door and stairway, forward service door

• Passenger aft entrance door and stairway, aft service door

• Oxygen systems

• Lighting systems

• Emergency exits and equipment

• Water and Waste Systems

Aircraft Dimensions/Turning Radius

Clearance for a turning aircraft is governed by the nose, wing tip, and tail of the aircraft. Nose clearance guarantees the tail or wing tip will clear, however, if the wing tip alone clears, the tail may not clear. When an aircraft attempts a turn, the nose tire slips throughout the turn. A conservative estimate of this slip is considered to be 3°. A perfect 180° turn, including this slip, requires 99 feet.

Therefore, a taxiway should be at least 125 feet in width to attempt a 180° turn.

Flight Deck

The flight deck is designed for operation by a flight crew of two with accommodations for an observer. The two man capability is made possible by locating all essential controls where they are accessible, and locating all visible indicators and legends where they may be viewed by either pilot.

Pilot Seats

This compartment provides flight stations for the Captain and First Officer. The seats are track mounted and are adjustable in fore and aft, up and down, and reclining planes. A folding seat is provided for an observer. All flight deck seats have safety belts and shoulder harnesses.

To aid each pilot in attaining a precise seat adjustment, an alignment device is provided under the glareshield on each side of the instrument panel. To properly adjust the seat, each pilot must look across the flight deck at the alignment target.

When the seat is properly adjusted, the pilot should see a white dot centered in the eye target locator

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Windows

There are four different types of windows in the flight deck.

• A center, left and right windshield.

• A clearview window on either side.

• An aft window on either side.

• Two upper (eyebrow) windows immediately above the clearview windows.

Flight Deck Windows

RIGHT

WINDSHIELD

RIGHT

CLEARVIEW

WINDOW

RIGHT

UPPER

WINDOW

(EYEBROW)

RIGHT AFT

WINDOW

1.40.2

CENTER

WINDSHIELD

LEFT

WINDSHIELD

LEFT

UPPER

WINDOW

(EYEBROW)

LEFT

CLEARVIEW

WINDOW

LEFT AFT

WINDOW

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Systems Description

Lighting Systems

Exterior Lighting

The exterior lights consist of wing and nose landing and taxi lights, ground floodlights, wing/nacelle lights, anti-collision lights, and position and strobe lights

Landing And Taxi Lights

The landing and taxi lights consist of the nose gear landing and taxi lights, and the wing landing lights. Two sealed beam, fixed position, combination landing and taxi lights are installed on the nose gear assembly. The light circuit is interlocked so that the nose lights illuminate only when the landing gear handle is in the

DOWN position. One sealed beam retractable landing light is installed on the lower surface of each wing tip. Each light assembly is enclosed in a housing and contains a motor to retract and extend the lights. Each light is controlled by a three position switch located on the Captain’s side of the glare shield panel.

With a single engine failure, when landing gear is retracted after takeoff or go-around, the wing landing lights will extinguish and retract automatically.

Ground Floodlights

The ground floodlights aid side and forward visibility when taxiing. These lights are controlled by a pair of two position switches located on the Captain’s side of the glareshield panel.

Wing/Nacelle Lights

The wing and nacelle floodlights are installed in each side of the fuselage to visually check the wing leading edge and engine nacelle for icing conditions.

These lights may also be used to facilitate ground servicing. These lights are controlled by a three position switch on the First Officer’s side of the glareshield panel.

Anti-collision Lights

Anti-collision lights are installed on the upper and lower fuselage surfaces. Both lights are controlled by a single switch located on the First Officer’s side of the glareshield panel.

Position And Strobe Lights

The wing tip position and strobe lights include forward position lights consisting of a red light on the left wing tip and a green light on the right wing tip. A white strobe light assembly is also installed in each wing tip adjacent to the forward position lights. A clear wing tip lens fairing covers each forward position/strobe light. A combination aft white position light and white strobe light assembly is installed in the trailing edge of each wing tip.

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MD-88/90 Operations Manual

Wing tip strobes operate only when POS/STROBE switch is in BOTH and the nose wheel is off the ground.

Interior Lighting

Flight Deck Lighting

Flight compartment lighting provides general and local lighting of the flight deck area, panels, instruments, and controls. Separate lighting control panels provide individual selection of intensity and the area to be lighted.

White incandescent floodlights are provided for the overhead panel and pedestal and the Captain’s, First Officer’s, and center instrument panels. White fluorescent floodlights are provided for the Captain’s and First Officer’s instrument panels.

Lighted digital readouts are provided at the digital flight guidance control panel,

Captain’s and First Officer’s flight mode annunciators, and the FUEL QTY

(quantity) indicator. Integral panel and instrument lighting is also provided.

The THNDRSTRM LT switch overrides individual lighting controls and selects all floodlights and digital lighting to maximum intensity.

A CKPT FLOOD (cockpit floodlight) switch operates two floodlight units in the ceiling to provide general flight deck floodlighting below the level of the thunderstorm lights. In the ON position, one light is illuminated in each unit. In the ALT THNDRSTRM position, one additional light illuminates in each unit.

Additional flight compartment lighting consists of floor, map, briefcase, circuit breaker, standby compass, and chart holder lights.

In the event of complete loss of normal electrical power with the BATT (battery) switch ON, minimal lighting is provided by the white pedestal floodlights

(incandescent) at the Captain’s overhead and center instrument panels. These lights receive power from the DC transfer bus. These lights can be adjusted using the CTR INSTR & PED LTS FLOOD knob (FLOOD knob just left and forward of rudder trim knob).

When the EMER PWR (emergency power) switch is moved to ON with normal electrical power off and BATT switch ON, standby lighting will continue to be provided by the Captain’s and First Officer’s instrument panel floodlights. These lights receive power from the emergency DC bus and the DC transfer bus. All floodlights can be individually controlled from minimum to maximum intensity using their respective floodlights knob. Immediate bright floodlighting can be obtained by moving the THDRSTRM LT switch to ON.

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Passenger Cabin Lighting

Passenger cabin lighting is provided by white incandescent and fluorescent lights.

General cabin illumination is provided by sidewall lights, ceiling lights, and entry lights. These are supplemented by reading lights, lavatory lights, and separately controlled galley lights. Controls are located on the forward and aft attendant’s panels.

The upper and lower sidewall fluorescent lights illuminate to full bright automatically whenever cabin altitude exceeds 14,000 feet to aid passengers with supplemental oxygen.

Cabin attendant’s lights are provided at the forward and aft cabin attendant’s stations and are controlled by light switches at the respective attendant’s panel.

Standby Lighting

A standby lighting system provides lighting in the main cabin whenever normal electrical power supply is not available. The system is comprised of separate bulbs located in the ceiling. The standby lights are powered from the aircraft batteries through the emergency DC bus and are controlled by selecting the EMER PWR switch located on the forward overhead panel to the ON position.

Emergency Lighting

Emergency evacuation lighting provides escape path lighting for the flight deck and passenger compartment. Flight deck emergency evacuation lighting consists of two peanut bulbs on the aft overhead panel in the flight deck. Passenger compartment emergency evacuation lighting consists of proximity escape path lighting and ceiling lights. In addition, overdoor exit, overwing exit, aft passenger stair and tail section, and exterior overwing lights are illuminated. Emergency evacuation lights are powered by individual rechargeable battery packs that supply power for approximately 15 minutes. The emergency evacuation light system is activated in one of 3 ways:

• Position EMER LTS (emergency evacuation lights) switch in flight deck to ARM and lose power to the EMERGENCY DC BUS.

• Position EMER LTS (emergency evacuation lights) switch in flight deck to ON.

• Position EMERGENCY LIGHTS switch at flight attendant’s panel to

ON.

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Emergency Evacuation Lighting

INTERIOR

CEILING EMERGENCY

EXIT LIGHT

FLOOR AISLE AND EXIT IDENTIFIERS

SERVICE DOOR

EXIT LIGHT

INTERIOR

EMERGENCY

EVACUATION LIGHTS

AFT EMERGENCY SLIDE

EVACUATION LIGHT

INTERIOR

TAIL SECTION LIGHTS

OVERWING

EVACUATION

LIGHT

AFT L SERVICE DOOR

EXIT IDENTIFIER

OVERDOOR

EXIT LIGHT

(BOTH SIDES)

MAIN ENTRANCE

EXIT IDENTIFIER

EMERGENCY

EXIT LIGHTS

(BOTH SIDES)

LEFT AFT AND FWD OVERWING

EXIT IDENTIFIERS

Passenger Information Signs

Illuminated pictographic type signs located throughout the passenger compartment provide specific instructions or pertinent information for the passengers and cabin attendants. These signs are controlled by the NO SMOK and

SEAT BELTS switches located on the forward overhead panel.

When cabin altitude exceeds 10,000 feet, both the NO SMOKING and FASTEN

SEAT BELTS signs illuminate regardless of switch position. The RETURN TO

CABIN signs in the lavatories, however, do not illuminate.

The LAVATORY OCCUPIED signs are illuminated when the lavatory door is locked.

Oxygen Systems

Flight Crew Oxygen

The flight crew oxygen system is completely separate from the passenger oxygen system. It uses quick donning mask regulators located at each crew station.

Oxygen is supplied from a single cylinder located behind the First Officer’s seat.

The cylinder is equipped with a bottle pressure gauge and a shutoff valve that controls oxygen supply to the system. System line pressure is indicated on the aft overhead panel. The absence of the green blow out disk on the forward right side of the fuselage provides a visual indication of an overpressurized oxygen bottle.

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A mask regulator is stored in a box at each crew station. The mask incorporates a manually operated goggle venting valve.

The mask may be used by squeezing the red release levers with the thumb and forefinger and removing from stowage. Squeezing and holding the release levers inflates the mask harness. The flow indicator shows yellow momentarily as the harness inflates. After placing the mask over your head, releasing the levers contracts the mask harness, fitting the mask to your head and face.

Oxygen flow is controlled by a regulator mounted on the mask. The regulator may be adjusted to supply 100% oxygen by pushing the NORMAL 100% switch.

Rotating the emergency selector to the EMERGENCY position on the mask regulator supplies 100% oxygen under positive pressure at all altitudes. The goggle vent valve will be supplied oxygen only when the emergency selector is rotated to the EMERGENCY position. The goggle vent valve is operated by sliding the vent selector on the mask downward. This action uncovers two red bands on the mask allowing 100% oxygen to flow from the vent in the mask. The smoke goggles, located in the stowage compartment outboard of each pilot’s seat, are designed to be used with the venting mask.

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MD-88/90 Operations Manual

PASSENGER OXYGEN

ALTERNATE RELEASE SWITCH

OXYGEN LINE

PRESSURE

GAUGE

(OVERHEAD

PANEL)

OBSERVER’S

OXYGEN MASK

CAPTAIN’S

OXYGEN

MASK

CREW OXYGEN SUPPLY

CYLINDER AND

REGULATOR Minimum dispatch is 1,000 psi.

FIRST OFFICER’S OXYGEN

MASK

BLOW OUT DISK

OVERBOARD

DISCHARGE LINE

Passenger Oxygen

The passenger oxygen system is supplied by individual chemical oxygen generators located at each passenger service unit (PSU).

WARNING: Oxygen generators become hot when activated. The presence of a burning odor is normal during use.

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Constant flow masks are connected to each generator - four masks on each left side generator, three at each right side generator. A generator with two masks is located above each flight attendant’s station and in each lavatory. The mask doors open automatically at a cabin altitude of approximately 14,000 feet. Mask doors may be opened at any time by selecting the OXYGEN MASK switch behind the

First Officer to EJECT.

Note:

When aircraft AC electrical power is lost, all the cabin mask doors must be opened manually.

Pulling any mask down in a unit activates that oxygen generator, and 100% oxygen begins to flow to all masks in that unit. A green flow indicator is visible in the transparent oxygen reservoir bag whenever oxygen is flowing to the mask.

The mask supplies a mixture of pure oxygen and ambient air to the passenger. If the passenger oxygen is activated and a PSU oxygen mask compartment does not open, the masks may be dropped manually. Oxygen will continue to flow for approximately 15 minutes and cannot be shut off once activated. Once used, there is no further supply of oxygen available to that particular PSU.

Passenger Seats

Each seat is equipped with a seat belt, ashtray, folding utility tray, and literature stowage pocket.

All seat backs, except on the outboard seats adjacent to each overawing exit, are adjustable in the recline position by means of a push-button control in the armrest.

The seat will return to the normal upright position when the push-button is pressed and no backward force is present.

Each seat back, except on the outboard seats adjacent to each overwing exit, can be forced by twenty-five pounds of force (approximate) to fold from its normal upright position to lay flush with the seat cushion. The seats may be returned to normal upright position by manually lifting with approximately ten pounds of force.

All armrests, except the one adjacent to the aisle and the ones mounted on the overwing exit doors, may be folded up flush with the seat back. The seat bottom cushions are equipped with hand straps to facilitate use as flotation gear.

On some airplanes, the aisle armrest of the second and thirtieth row of seats on the right side of the airplane may be raised to facilitate the seating of wheel chair passengers.

On some airplanes, the aisle armrest of the second row and twenty-ninth row of seats on the right side of the airplane may be raised to facilitate the seating of wheelchair passengers.

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Doors

Flight Deck Door Control

If a valid Access Code is entered into the remote keypad, a 60 second time delay will start during which the following will occur:

• A short aural alert will sound and the amber AUTO UNLK light will illuminate on the flight deck door control panel.

• After 30 seconds, a second short aural alert will sound.

• After 40 seconds, the aural alert will pulsate and the AUTO UNLK light will flash.

• After 60 seconds, the AUTO UNLK light will extinguish, the door will unlock for 5 seconds, the LOCK FAIL light will illuminate, and the aural alert will sound.

At any time during this sequence, the switch may be selected to UNLK to allow entry or DENY to prohibit entry.

Passenger Entrance Doors and Stairs and Service Doors

The passenger forward entrance door is installed on the left side of the fuselage, and the forward service door is installed on the right side. Either door can be opened from either inside or outside the airplane. The doors swing outward after the hinge has moved inward, permitting the doors to move edgewise through the doorway. An evacuation slide is installed on each door. Operating instructions for the door and the slide are stenciled on the door and slide container, respectively.

With the parking brakes set, the DOOR cue light will flash four times when first door is opened and remain on without flashing as other doors are opened.

Annunciations will not appear on display screen. With DOOR cue light on steady, push DOOR cue light to display door annunciations on screen. DOOR cue light extinguishes when all doors are closed.

When the parking brakes are released, the DOOR cue light will flash four times each time a new door annunciation is displayed on screen. Push DOOR cue light to display only door annunciations. If DOOR cue light is pushed and held, door annunciations will be displayed for 10 seconds and go off. DOOR cue light will be on steady to indicate door annunciations whether on or off screen. DOOR cue light cannot be dimmed.

1.40.10

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Passenger Aft Cabin Door

The passenger aft entrance door is mounted on the aft pressure bulkhead and hinged on the right side to swing forward against the lavatory wall. A viewing window is installed in the door handle recess to allow inspection of the stairway area with the door closed. The aft cabin attendant’s seat is attached to the door and automatically folds into a recess in the door when not in use. The seat bottom must be folded into the recess when the door is opened. A barrier strap is installed to be placed across the aisle forward of the door for takeoff and landing, to preclude passenger interference when opening the door. A hold open latch is installed on the right side of the aisle to hold door in the open position.

Door warning annunciations and door cue light on the annunciator panel will remain on when either door is not closed and locked.

Passenger Aft Entrance Stairway

The aft entrance stairway is hydraulically actuated and powered by the right hydraulic system. When retracted, the stairway is automatically locked in the up position by mechanical locks.

The stairway may be operated from the exterior of the airplane. The exterior control is located on the aft left fuselage adjacent to the stairway door jamb and is covered by a latched access door. There are no indicator lights at the external control station. Door warnings and DOOR cue light on the annunciator panel function when the stairway is operated from the external control station.

In the normal extended position, the stairway does not touch the ground. However, under certain conditions, such as an uneven runway apron, the folding step may touch, and the lower step extension will fold to accommodate the variations. If the airplane is subjected to extreme conditions, such as high winds over the nose or abnormal aft section loading, the airplane may tip aft causing the lower step extension to fold until the main step contacts the ground. The lower steps of the stairway are designed to absorb ground contact without damage. In addition, the stairway is equipped with shock absorbing tubes. If the shock absorbing tubes become deformed by stairway-ground contact, they must be replaced before normal operation can be resumed.

Tailcone

A jettisonable tailcone is attached to the fuselage. When jettisoned, the opening provides an emergency exit accessible from the passenger compartment through the aft cabin door and aft accessory compartment. The tailcone can be released from inside or outside the aircraft.

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Galleys

Four galley units are installed in the cabin. Galleys G1 and G2 are located forward on the right side of the cabin adjacent to the forward service door. Galleys G3 and

G4 are located aft of the cabin near the aft service door. Galleys G1 and G4 are wet galleys and water is supplied from the pressurized potable water system.

Lavatories

Three lavatories are installed in the cabin. One is located on the forward left side just aft of the forward passenger door and two are located aft on either side of the aft passenger door.

Note:

A locked lavatory door can be unlocked from the outside by inserting a screwdriver or other sharp instrument into a slot on the OCCUPIED sign on the door latch and sliding the sign to the vacant position. Water is supplied to the lavatories from the pressurized potable water system. A water shutoff valve is located under the washbasin to shut-off or adjust flow of water to the basin. Hot water is provided by a water heater located under the washbasin in each lavatory.

Note:

The lavatories contain integral waste tanks which are drained through exterior service panels.

Potable Water System

A pressurized potable water tank, located just forward of the mid cargo compartment door, supplies water to the galleys and lavatories.

The potable water tank is normally pressurized from the aircraft air conditioning system. On the ground when the air conditioning system is not operating, the tank can be pressurized from a ground source at the water service panel or by an integral standby electric pump. The standby pump is activated by using a push button switch located on the forward wall in both galleys. The time required to pressurize the tank is dependent upon volume of water in the tank. The pump shuts off after reaching the proper pressure, and will not restart automatically if the pressure drops. The pump is inoperable when the external potable water service door is open.

The water service panel, located on the lower right side of the fuselage, contains controls/indicators for determining automatic water fill levels.

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Systems Description

Emergency Exits

There are ten emergency exits on the aircraft:

• Two flight deck sliding windows.

• Forward cabin door.

• Forward galley door.

• Aft galley door.

• Aft cabin door (through tailcone).

• Four overwing exits.

Operating instructions for each door are located on its interior and exterior surface.

Flight Deck Emergency Exits

Normally, cabin exits will be utilized by flight crew members. However, two sliding clearview windows, adjacent to the windshields, provide an alternate escape route. Escape lines are provided adjacent to the clearview windows for use by crew members to lower themselves to the ground.

To open clearview window:

After aircraft is unpressurized,

• Pull handle aft to disengage overcenter lock.

• Pull handle inboard to move window inboard.

• Pull handle further aft so that window slides aft to an open locked position.

Cabin Emergency Exits

There are eight cabin emergency egress doors; a forward entrance door, service doors (right forward fuselage and left aft fuselage), four overwing emergency exit doors, (two each fuselage side), and, when the tail cone is jettisoned, the aft entrance door. Operating instructions for each door are located on the interior and exterior surface of each door. Both service doors and forward entrance door have identical handles and similar operating instructions. The overwing emergency exit doors have identical handles and emergency operating instructions.

The forward entrance door and both service doors are equipped with slides that deploy automatically when the door is opened with the girt bar installed in airplane floor fittings.

When the aft entrance door is opened using the emergency exit handle, the tail cone is jettisoned and a slide is automatically deployed and inflated. A back-up inflation handle is provided on the aft entrance door slide should the slide fail to inflate automatically. All door slides, except aft entrance door slide, have integral emergency lighting.

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MD-88/90 Operations Manual

Overwing Emergency Exits

The overwing exit hatches are removed by pulling inward on the upper handle which has the PULL label. The hatch is then lifted inside and stowed.

Escape Slides

The forward cabin door and both galley doors are equipped with slides that inflate and deploy automatically when the door is opened with the girt bar installed in airplane floor fittings. A back-up manual inflation handle is provided on each door slide should the slide fail to inflate automatically.

When the aft cabin door is opened using the emergency exit handle, the tailcone is jettisoned and a slide is automatically inflated. A back-up inflation handle is provided on the slide should the slide fail to inflate automatically. All door slides have integral emergency lighting.

Protective Breathing Equipment (PBE)

Four PBEs, one in the flight deck, and three in the passenger cabin are designed to protect crew members from the effects of smoke, carbon dioxide, or other harmful gases while combatting fires.

PBE Container

The preflight consists of inspecting the two red seals and ensuring the PBE is intact. If one seal is broken, the PBE is okay for flight, but the second seal must be installed at the next Delta maintenance station. There is no visual service indicator

To operate the PBE:

• Remove the pouch from the compartment.

• Open the pouch by pulling the loose ends apart.

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• Remove and unfold the hood.

• Position the hood so the clear side is facing downward, with the neck opening positioned toward you

• Activate the oxygen flow by pulling apart the two oxygen cylinders sharply. The cylinders are activated simultaneously when pulled apart.

One cylinder discharges rapidly to purge the hood of any contaminated air. In order to receive the full benefit of purging, you must get the hood on quickly (within 15 seconds). The second oxygen cylinder releases slowly, lasting 7 - 8 minutes. After both cylinders have fully discharged, the hood provides an additional 7 - 8 minutes of breathable air.

• Insert hands, palms together, into the neck opening and spread/separate hands to enlarge opening

• Slip hood over your head.

• Verify oxygen flow by illumination of the green light located inside lower front of mask. If flow were to stop, green light would still be on.

Special Considerations

Once the hood is activated and donned, be aware of the following:

• A good neck seal is important; long hair should be pushed into the hood.

• Your ears may pop as the hood is pressurized.

• You may experience light headedness; this is due to the relatively high oxygen content in the hood.

• You may feel warm inside the hood from the combined warmth of your body temperature, your exhaled breath and chemical process within the hood.

• Normal interphone and face-to-face communication procedures are recommended. Use the hand held mic with both flight deck speaker volumes high.

• A flashing red light illuminates after 15 minutes, indicating the oxygen supply depleted. Leave the area, if possible, then remove the hood.

August 11, 2008

1.40.15

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

MD-88/90 Operations Manual

Flotation Equipment

Red life vests are located adjacent to each crew seat. Passenger seat cushions may also be used as a flotation device. Straps are provided on the underside as handholds.

Yellow life vests are located under each passenger seat. Spare life vests are located behind the last row of first class seats on the left side of the aircraft.

LIFE VEST

(1) Put vest on over head with back piece behind.

LOCATOR

LIGHT

(2) Fasten snaps to ring in front.

(3) Pull straps snug.

1.40.16

(4) After leaving aircraft, inflate vest by pulling down sharply on red inflation tabs or by blowing into oral tubes.

For night use only - pull light tab to activate battery.

INFLATION TABS

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

Flashlights

Five emergency flashlights are located in the cabin. They are mounted in holders with an anti pilferage shield over each unit. A blinking red light on the flashlight indicates a serviceable battery in the unit. The flashlight illuminates continuously when removed from its holder.

CONDITION LIGHT

Fire Extinguishers

Portable fire extinguishers include three halon 1211 and two water extinguishers.

The halon 1211 extinguisher can be used on all types of fires. The water extinguishers are designed for use on smoldering trash fires and are more effective than halon on these fires.

Lavatory Trash Container Extinguisher

A self activating fire extinguisher is installed with the trash bin in each lavatory.

A temperature sensitive indicator is installed adjacent to each unit to show when it has been activated.

Emergency Locator Transmitter (ELT)

Passenger Cabin

One emergency locator transmitter is installed in the cabin.

Flight Deck

One emergency locator transmitter is installed in the flight deck.

ELT Operation

CAUTION: Use caution when removing ELT from support bracket. Whip antenna release can cause injury.

(1) To remove the ELT from the bracket, pull the fabric harness release to unsnap the straps and lift it out by pulling on one of the metal loop shaped handles while holding on to the antenna with the other hand.

(2) If the toggle switch is in the ARMED position and the ELT is submerged in water, the water sensor will activate transmission. The

ELT can be activated at any time by manually positioning the toggle switch to the ON position.

August 11, 2008

1.40.17

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

MD-88/90 Operations Manual

(3) When in use, check regularly that the antenna is vertical. For maximum transmission power, the antenna must be in an unobstructed area far from any metallic objects.

Note:

Due to its portability, the ELT can be taken with the crew after a ditching or land evacuation.

Portable ELT System Description

Harness Release

ELT Mode Switch (ARMED/OFF/ON)

Whip Antenna

Velcro Harness

Water Sensor/Identification Assembly

Float

Transmit LED

TEST Push Button

1.40.18

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

Emergency and Cabin Equipment Symbols

PORTABLE

OXYGEN BOTTLE

WATER

EXTINGUISHER

HALON

EXTINGUISHER

PORTABLE

BREATHING

EQUIPMENT

EXIT PATH

WITHOUT ESCAPE

STRAP

EXIT PATH

WITH ESCAPE

STRAP

EXIT PATH

WITH ESCAPE

SLIDE

LIFE RAFT

LIFE

VEST

RED

MEDICAL

ACCESSORY

POUCH

EMERGENCY

TRANSMITTER

AED

CRASH

AXE

ENHANCED

EMERGENCY

MEDICAL

KIT

FIRST AID

KIT

CDL

CABIN

DISCREPANCY

LOG

SECURITY

KIT

FLASHLIGHT

WHEELCHAIR

MEGAPHONE

NOTE: SOME SYMBOLS DO NOT APPLY TO ALL CONFIGURATIONS.

August 11, 2008

1.40.19

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

MD-88/90 Operations Manual

Emergency and Cabin Equipment Locations

Two Class Configuration

(2) (2)

(3)

CDL

3 DEMO

(2)

14 SPARE

7 SEAT BELT

EXTENSIONS

(2)*

(2)

A = ATTENDANT SEAT

L = LAVATORY

G = GALLEY

C = CLOSET

(2)*

(2)

(2) (2)

UNDER EACH

PASSENGER SEAT

(2)

BIN

RED

* Denotes overwater configuration.

1.40.20

August 11, 2008

MD-88/90 Operations Manual

One Class Configuration

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

(2) (2)

(3)

CDL

3 DEMO

(2)

14 SPARE

7 SEAT BELT

EXTENSIONS

BIN

(2)

A = ATTENDANT SEAT

L = LAVATORY

G = GALLEY

C = CLOSET

(2)

UNDER EACH

PASSENGER SEAT

(2)

BIN

RED

August 11, 2008

1.40.21

Airplane General, Emergency

Equipment, Doors, Windows -

Systems Description

MD-88/90 Operations Manual

Intentionally

Blank

1.40.22

August 11, 2008

MD-88/90 Operations Manual

Aircraft General, Emergency

Equipment, Doors, Windows

OAP Messages/Lights

Chapter 1

Section 50 OAP Messages/Lights

Blue Advisory Lights

CABIN OXYGEN ON - Left and right aft cabin oxygen door latches have been activated.

Amber Caution Messages

NOTE: The associated cue light is shown in parenthesis (XXX) following the message.

ACCESS COMPT DOOR (DOOR) - Access compartment door is not closed.

AFT CABIN DOOR (DOOR) - Passenger aft entrance door is open and/or unlatched.

AFT CARGO DOOR (DOOR) - Aft cargo door is not closed and/or latched.

AFT GALLEY DOOR (DOOR) - Aft galley door is not closed and/or latched.

AFT STAIRWAY DOOR (DOOR) - Stairway door is unlatched.

ALL DOORS CLOSED (DOOR) - DOOR cue light is pushed and all doors are closed and latched.

ELECT COMPT DOOR (DOOR) - Electrical compartment door is not closed and/or latched.

EMER LIGHT NOT ARMED (ELEC) - Indicates DC power is available to aircraft and EMER LTS switch on overhead panel is not at ARM position.

FWD CABIN DOOR (DOOR) - Forward cabin door is not closed and/or latched.

FWD GALLEY DOOR (DOOR) - Forward galley service door is open and/or unlocked.

FWD CARGO DOOR (DOOR) - Forward cargo door is not closed and/or latched.

FWD STAIRWAY DOOR (DOOR) - Forward stairway door is not closed and/or latched.

MID CARGO DOOR (DOOR) - Mid cargo door is not closed and/or latched.

TAILCONE UNSAFE (DOOR) - Tailcone is unlatched or compromised.

February 28, 2005 1.50.1

Aircraft General, Emergency

Equipment, Doors, Windows -

OAP Messages/Lights

MD-88/90 Operations Manual

Intentionally

Blank

1.50.2

April 01, 2004

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows

MD-90 Differences

Principle Dimensions

Chapter 1

Section 90

August 11, 2008

1.90.1

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

MD-88/90 Operations Manual

Turning Radius

125'

Minimum Width

For 180

Turn

76 ft 5 in

70 ft 6 in

15 ft 0 in

79 ft 6 in

86 ft 1 in

Steering Angle

Maximum

1.90.2

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

Instrument Panels

Forward Overhead Panel

100

AC VOLTS

150

TEST ERASE

HYD CONT

ELEV

CADC

NORM

BOTH

ON 1

FD CMD

NORM

BOTH

ON 2

BOTH

ON 1

EFIS

NORM

BOTH

ON 2

ELEC PWR

HEADSET

600 OHMS

COCKPIT VOICE RECORDER

380

400 420

FREQUENCY

OPS

GALLEY

OFF

START

PUMP

OFF

L GEN

RESET

OFF

1.0

1.5

.25

AC LOAD

2.0

L AC

BUS

1.5

1.0

1.5

1.0

LOAD

APU

R GEN

BUS

TIE

OPEN

APU

PWR

AVAIL

BUS

TIE

OPEN

ENG

START

EXT

ENG

IGNITION

AUTO

1.0

1.5

.25

AC LOAD

2.0

AUTO

APU GEN

RESET

OFF

EXT

PWR

AVAIL

OFF

AUTO

DC BUS X TIE

CLOSE

OPEN

N1 MODE

L-ENG R-ENG

SELECT

DEFAULT

SELECT

DEFAULT

PNEU

PRESS

PSI 2

6 x 10

R GEN

RESET

OFF

EXT

PWR

VOLT/FREQ

AC VOLT/FREQ

DC BUS VOLT

L R

BATT

VOLT

APU

BATT

AMP

1.0

1.5

.25

AC LOAD

2.0

APU

100

110

APU

EGT

% MAX

CONT

L GEN

EXT

R AC

BUS

1.5

1.0

1.5

1.0

LOAD

100

AMPS

50 50

VOLTS

100

110

0 20

100

PERCENT

RPM

FIRE AGENT

NO. 1 NO. 2

OFF

APU

AIR

OFF

DISCH

FIRE CONT

NORM

AIR COND

COLDER

OFF

MASTER

RUN

OFF &

AGENT ARM

START

EMER PWR

OFF ARM ON

EMER

PWR

IN USE

OFF

BATT

VIDEO

IN USE

LEFT

OFF

CTR

AFT PUMPS

FUEL TANKS

RIGHT

AUTO

OFF

LOW PRESSURE INHIBIT EQUIPPED

OFF

FWD PUMPS

AUTO

OFF

EMER

LTS

OFF

ARM

SMOK

AUTO

OFF

SEAT

BELTS

ICE PROTECT

OFF

AIR FOIL

4 6

HEATER CUR

METER SEL

& HEAT

AUX F/O

P ITOT

CAPT

RUD

LIM

OFF

RAT

PROBE

R L

STATIC

STALL

PROBE

TAIL

WINDSHIELD

ANTI-FOG ANTI-ICE

OFF

ENG

OFF

PANEL

OVHD CONSOLE LTS

FLOOD

OFF

N 1

ENG SYNC

OFF

INOP

OFF OFF

FORWARD

BOTH

FAULT

FIRE

ARMED

MID

BOTH

FAULT

FIRE

ARMED

PRESS TO ARM

B A

AFT

BOTH

FAULT

FIRE

ARMED

FWD

SQUIBBS

MID AFT

BTL 1

SYSTEM

TEST

BTL 2

DISCH

AGT LOW

DISCH

AGT LOW

GND

PROX

WARN

OVRD

NORM

TEST

HP BLD

OFF

150

COLD

STOP

MANUAL

HOT

AUTO

COLD

STOP

MANUAL

HOT

TAKEOFF & LAND UNPRESSURIZED

SCHED APL

1000 FT CABIN 0

AUTO INOP

100 FT

20 25 30 35

4 6 8 +

IN HG

30.1

FLOW

AUTO 1

INOP

30.0

29.9

29.8

RATE LIMIT

AUTO 2

INOP

LDG ALT LDG BARO

CABIN

PRESSURE

CABIN TEMP

120

0 1000

DIFF/PRESS

PSI

6 5

CAB ALT

WNDSHR

TEST

NORM

TEST

ALN

NAV

ATT

OFF

AUTO

UNLK

PA VOL

L VALVE

COLD

TEMP

HOT

CONTROL

CKPT TEMP

AUTO

IRS MODE SELECT

ALIGN

ON BAT

BAT FAIL

FAULT

ALIGN

ON BAT

BAT FAIL

FAULT

ALN

NAV

ATT

OFF

CKT BKR

OFF

STBY COMP

DIM

BRT

LOCK

FAIL

UNLK

AUTO

DENY

FLT DECK DOOR

THNDRSTRM

OFF

CKPT

FLOOD

ALT

THNDRSTRM

ATTENDANT

CALL

ANTI-SKID

OFF

ARM

STALL

TEST

MAX SPD WARN

TEST

SYS 2

OFF

SYS 1

ATTND

CALLING

RESET

FLOW

OFF

TEST

FLOW

TEST CKT

OFF

OVRD

AIR CONDITIONING

YAW

DAMP

R R VALVE

NORM

OVRD

MACH

TRIM

COMP

RESET

TEST

CABIN

SPLY

TEMP SEL

CABIN

RADIO

RACK

VENTURI

ICE

FOD

FLOW

COLD

TEMP

CONTROL

HOT

FAN

SUPPLY

OFF

CABIN TEMP

AUTO

AIR

COND

SHUTOFF

OVRD

AUTO

RAM AIR

OFF

RAIN ANNUN/DIGITAL

LTS TEST

REPELLENT

WIPER

OFF

L RES R

PARK SLOW

FAST

CLIMB

DESCEND

CABIN

CLIMB

1.5

1000 FT/MIN

1.5

PULL TO DIM

FLT RECORDER OFF

R OIL PRESS LOW

R GEN OFF

R HYD PRESS LOW

PARKING BRAKES ON

ELEC ICE ENG CTRL

AUTO SLAT FAIL

SPOILER DEPLOYED

L OIL PRESS LOW

DOOR AFT CABIN

L AC BUS OFF

L START VALVE OPEN

MISC HYD STATUS DOOR

IRS 1

ATT MODE

ELEVATOR

AT LIMIT

L ENG ANTI-ICE

RAIN REPELLENT

RESERVE IN USE

L ENG IGN

L TAIL

TEMP HIGH

AC EMER BUS

OFF

ENGINES COOL

WING ANTI-ICE

TAIL DE-ICE

CARGO FIRE

CABIN ALT

APU FIRE

IRS 2

ATT MODE

R ENG ANTI-ICE

CABIN OXYGEN

R ENG IGN

R TAIL

TEMP HIGH

DC EMER BUS

OFF

August 11, 2008

1.90.3

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

MD-88/90 Operations Manual

Aft Overhead Panel

APU TACH

GROUND BA

FLOOD LIGHTS

ARM AND CHARGE

AIR CONDITION FLOW CONTROL

MAG/TRU ANNUN-

IN USE LIGHT

DC BUS SENSING

CROSS TIE CONTROL

VHF NA

R. ENG THRUST R

EMERGENCY NA

A L T

F A U L T

1.90.4

August 11, 2008

MD-88/90 Operations Manual

Center Instrument Panel

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

VHF

NAV

CRS

OFF

FMS

OVRD

SPD

SEL

MACH

SEL

SPD MACH

EPR

LIM

NAV

AUTO

THROT

OFF

VOR

LOC

ILS

AUTO

LAND

HDG

AND

ANU

100

FT.

000

1 0 1 3

ALT

IN hg

2 9 9 2

BARO

IAS

UNITS

0 60

IAS KNOTS

MAN EPR

PULL

AGENT

DISCH

PULL

FIRE

TEST

AGENT 1

LOW

AGENT 2

LOW

FIRE

BELL OFF

FAULT

TEST

AGENT

DISCH

PULL

REVERSE

THRUST

REVERSE

UNLOCK

1.42

1.2

1.0

1.4

1.0

1.8

1.6

28K

TOGA

LIMIT

REVERSE

THRUST

REVERSE

UNLOCK

1.42

EPR

1.2

1.0

1.4

1.8

1.6

% RPM

21 O

EGT

325 15

% RPM

100

FUEL

FLOW USED x 10

PPH

PUSH

FUEL USED

RESET

MAN EPR

PULL

RAT

FUEL

TEMP

VIB

FLAPS

HYD

QTY

QTS

OIL

PRESS

PSI

OIL

TEMP

OIL

QTY

QTS

HYDRAULIC

PRESS

PSI

SLATS

T/O

DISAG

AUTO

LAND

BRT

80 160 320

10 MIN

GAIN

OFF

TCAS

TEST

WX/TCAS

TURB

MAP

AUTO

L MAIN

9250

A / B

CTR

2300

R MAIN

9250

TOTAL FUEL

20800

GROSS WT

137000

FLOW

OFF

GEAR

DOOR

OPEN

LEFT

NOSE

RIGHT

OVRD

FAIL

GPWS

TERRAIN

OVRD

28K 25K

MCT CR

1 2

ASSUMED

TEMP

NO MODE

GEAR

HDL

REL

DOWN

RNG 80 MRK 20

VERT

SPD

ALT

HOLD

IAS

MACH

AP ON

VNAV

1 2

ALT

OFF

TURB

VHF

NAV

CRS

INIT

REF

PREV

PAGE

DIR

INTC

NEXT

PAGE

RTE

MENU

LEGS

FIX

CLB

DEP

ARR

CRZ

HOLD

DES

PROG EXEC

A B C D E

1 2 3

G H I J K

4 5 6

M N O P Q

7 8 9

S T U V W

–

Y Z DEL /

BRT

CLR

INIT

REF

PREV

PAGE

DIR

INTC

NEXT

PAGE

RTE

MENU

LEGS

FIX

CLB

DEP

ARR

CRZ

HOLD

DES

PROG EXEC

A B C D E

1 2 3

G H I J K

4 5 6

M N O P Q

7 8 9

S T U V W

–

Y Z DEL /

BRT

CLR

August 11, 2008

1.90.5

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

MD-88/90 Operations Manual

Aft Pedestal

NOSE

TAKE-OFF

CONDTN

LONG TRIM

FLAP

LONG

TRIM

NOSE

PWR

OFF

SPD

BRK

RET

RUD

HYD

CONT

MAN

1/4

1/2

3/4

EXT

FUEL

FEED

FUEL

ALT

LONG TRIM

FUEL

DESCEND

GEAR

HORN

OFF

ALT

LONG TRIM

OFF

NOSE

CABIN

ALT

CLIMB

NLG IND

COMM

TFR

COMM

TFR

VALVE

CLOSE

UP UP/RET

T.O.

EXT

LAND

EXT

FLAP T.O.

SEL

FLAP/

SLAT

VALVE

OPEN

TFR

A1 ADF

NORM

ALT OFF ALT ON

STBY TA

TEST TA/RA

ATC 1

ANT

ATC

FAIL

ATC

IDENT

SELCAL DATA LINK

ALT

VHF - 1 VHF - 2 VHF - 3

PRESS TO RESET

MSG PRINTER

PANEL

CTR INSTR & PED LTS

DIGITAL FLOOD

1 2 : 0 0 MAIN MENU

PREFLIGHT

ENROUTE

POSTFLIGHT

UTC TIME

FLT LOG

MSGS

RCVD

DOWNLINK

WX/ATIS

MAINT MENU MISC MENU

D 1 3 1 . 5 5

MAIN

LGHT

PAGE

OFF

STABILIZER TRIM

OFF OFF

STOP

NORM

PNEU

X-FEED

VALVE

OPEN

LEFT

NOSE

RIGHT

RUDDER TRIM

PNEU

X-FEED

VALVE

OPEN

ARM

OFF

MIN

DISARM

LAND

MED

MAX

T.O.

AUTO BRAKE

LEFT

WING DOWN

RIGHT

1.90.6

AILERON TRIM

August 11, 2008

MD-88/90 Operations Manual

Captain’s Instrument Panel

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

M A N E U V

CAUTION

MASTER

ARNING ASTER

ABS

E T

TERR PEAKS GPWS TERRAIN

August 11, 2008

1.90.7

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

MD-88/90 Operations Manual

First Officer’s Instrument Panel

MASTER

ARNING

MASTERCAUTION

ABS

E T

1.90.8

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

Controls and Indicators

Lavatory

WASTE SYSTEM STATUS

WASTE

SYSTEM

PRESS TO TEST

RIGHT SIDE OF FWD PASS. DOOR

WASTE SYSTEM Switch/Light

Indicates the waste system is inoperative.

PRESS TO TEST - Pushing the switch initiates a waste system BITE test. A successful test is indicated by the illumination of the WASTE SYSTEM light 5 seconds after pushing the switch, then the extinguishing of the light.

Passenger Information Signs

CHIME

OFF

SEAT

BELT

FORWARD OVERHEAD PANEL

CHIME Switch

AUTO - Chime sounds when landing gear is extended.

OFF - Deactivates chime.

ON - Activates chime.

August 11, 2008

1.90.9

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

MD-88/90 Operations Manual

EOAP (Sheet 1))

STATUS

Status Cue Light (blue)

Status cue light illuminates when a second level message is stored in the status buffer (status requires no crew action). Status buffer messages may be reviewed by pressing STATUS cue.

EOAP (Sheet 2))

IRS 1

ATT MODE

(B)

ELEVATOR

AT LIMIT

(B)

L ENG ANTI-ICE

ON (B)

RAIN REPELLENT

RESERVE IN USE

(B)

L ENG IGN

ON (B)

L TAIL

AC EMER BUS

OFF

(R)

ENGINES COOL

(B)

APU STARTER

(B)

WING ANTI-ICE

(B)

TAIL DE-ICE

(B)

CARGO FIRE

CABIN ALT

APU FIRE

IRS 2

ATT MODE (B)

R ENG IGN

(B)

R ENG ANTI-ICE

(B)

CABIN OXYGEN

ON (B)

(B)

R TAIL

TEMP HIGH

DC EMER BUS

OFF

DOOR

INSTALLED ON SOME AIRPLANES

1.90.10

August 11, 2008

MD-88/90 Operations Manual

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

Systems Description

Emergency and Cabin Equipment Locations

(3)

(2)

(3)

CDL

(2)

3 DEMO

10 SEAT BELT

EXTENSIONS

(2)

A = ATTENDANT SEAT

L = LAVATORY

G = GALLEY

C = CLOSET

UNDER EACH

PASSENGER SEAT

10 SPARE

(2) (2)

G5 / LB

(2)

BIN

RED

August 11, 2008

1.90.11

Airplane General, Emergency

Equipment, Doors, Windows -

MD-90 Differences

MD-88/90 Operations Manual

Lavatory Smoke Detection

Each lavatory is equipped with a smoke detector. When smoke in a lavatory is detected, four chime-type tones will be sounded by the PA system and an amber light, located on the ceiling adjacent to the lavatory, will illuminate. A red light will also illuminate on the forward and aft cabin attendant’s call-light fixture.

These lights/annunciation will remain until the smoke in the lavatory has dissipated.

Passenger Entertainment System

Music may be played over the passenger address system. The music is turned on and off and the volume is controlled by operation of the MUSIC OFF/ON volume control located on the forward cabin attendants’ control panel.

A VU meter, located on the flight deck overhead panel and the forward and aft cabin attendants’ panels, provides an indication of passenger entertainment system audio output level.

Note:

PA and passenger entertainment system volume level is automatically boosted when either engine is started.

1.90.12

August 11, 2008

Air Systems

MD-88/90 Operations Manual

Chapter 2 Table of Contents Section 0

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.1

Major Component Location. . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.1

Cabin Pressure Components . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.2

Pneumatic Pressure Gauge and

Crossfeed Valve Levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.3

Air Conditioning Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.4

APU Air Switch and Air Flow Indicator . . . . . . . . . . . . . . . . . . 2.10.6

Cabin Altitude/Differential Pressure Gauge and Cabin Climb Gauge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.7

Air Conditioning Shutoff Switch and Ram Air Switch . . . . . . . 2.10.8

Cabin Pressure Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.9

Cabin Altitude Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.10.10

System Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.1

Pneumatic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.1

Air Conditioning Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.1

System Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.1

RAM Air. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.2

Air Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.2

Cockpit And Cabin Temperature Control . . . . . . . . . . . . . . . . . 2.20.2

Radio Rack Cooling Fans . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.3

Instrument Cooling Fans . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.3

Pack Cooling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.3

Ground Sources for Air Conditioning . . . . . . . . . . . . . . . . . . . . 2.20.4

APU Air Conditioning. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.4

Airplane Pressurization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.4

Pneumatic Air Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.5

Pneumatic Indication System . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.5

April 01, 2004 2.TOC.0.1

Air Systems -

Table of Contents

MD-88/90 Operations Manual

Air Conditioning Pneumatic Supply . . . . . . . . . . . . . . . . . . . . . 2.20.6

Airfoil Ice Protection And Engine Anti-ice

Pneumatic Supply. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.6

Ground Operation Pneumatic Supply . . . . . . . . . . . . . . . . . . . . 2.20.6

Pneumatic Supply Inflight. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.20.7

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.30.1

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.30.1

Red Warning Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.30.1

Amber Caution Messages . . . . . . . . . . . . . . . . . . . . . . . . . . 2.30.1

Functional Schematic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.40.1

MD-88 Pneumatic Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . 2.40.1

MD-88 Air Conditioning Schematic . . . . . . . . . . . . . . . . . . . . . 2.40.2

MD-90 Differences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.1

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.1

Air Conditioning Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.1

APU Air Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.2

Crossfeed Valve Lever . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.3

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.3

Air Conditioning System . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.3

Cabin Air Recirculation Fan . . . . . . . . . . . . . . . . . . . . . . . . 2.90.3

APU On-ground Air Conditioning . . . . . . . . . . . . . . . . . . . 2.90.4

Pneumatic Air Distribution . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.4

Pneumatic Indication System . . . . . . . . . . . . . . . . . . . . . . . 2.90.4

Pneumatic System Controller (PSC) . . . . . . . . . . . . . . . . . . 2.90.4

Pneumatic Precooler . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.4

Pneumatic Overheat Detection System (PODS) . . . . . . . . . 2.90.5

Airfoil Ice Protection and Engine Anti-Ice

Pneumatic Supply . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.5

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.5

Red Warning Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.5

Amber Caution Messages . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.5

2.TOC.0.2

April 01, 2004

Air Systems -

Table of Contents

MD-88/90 Operations Manual

Functional Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2.90.6

MD-90 Pneumatic Schematic. . . . . . . . . . . . . . . . . . . . . . . . 2.90.6

MD-90 Air Conditioning Schematic . . . . . . . . . . . . . . . . . . 2.90.7

April 01, 2004 2.TOC.0.3

Air Systems -

Table of Contents

MD-88/90 Operations Manual

Intentionally

Blank

2.TOC.0.4

April 01, 2004

Air Systems

MD-88/90 Operations Manual

Controls and Indicators

Major Component Location

LEGEND

COLD AIR DUCTS

CONDITIONED AIR DUCTS

STANDBY

RADIO RACK

COOLING FAN

Chapter 2

Section 10

RADIO RACK

OVERBOARD

VENTURI VALVE

CABIN PRESSURE

RELIEF VALVES

PRIMARY RADIO RACK

COOLING FAN

MIXING

CHAMBER

AFT

PRESSURE

BULKHEAD

April 01, 2004

RECIRCULATION

FAN

CABIN AIR

OUTFLOW

NOZZLE

CABIN AIR OUTFLOW

BUTTERFLY VALVE

JB1-3-0881

2.10.1

Air Systems -

Controls and Indicators

MD-88/90 Operations Manual

Cabin Pressure Components

JB1-3-0881

CABIN PRESSURE

CONTROLS

CABIN PRESSURE

SELECTOR PANEL

AUTOMATIC CABIN

PRESSURE CONTROLLER

GROUND

CONTROL

RELAY

AUTOMATIC CABIN

PRESSURE CONTROLLER

3

2 LEGEND

ELECTRICAL CONNECTION

MECHANICAL CONNECTION

1

JB1-3-0882

JB1-3-0882

Actuator

Automatic Pressurization Control - Receives input from the cabin pressure selector panel through either the primary or the standby controller. Adjusts the outflow butterfly valve and/or nozzle opening to maintain the required pressurization.

Manual Pressurization Control - The actuator is declutched.

Cabin Air Outflow Valve Nozzle

The variable opening controls pressurization.

NOTE: The outflow nozzle and the butterfly valve are mechanically interconnected in order to operate in proper sequence.

Cabin Air Outflow Butterfly Valve

Initially controls pressurization and provides for full depressurization.

NOTE: The butterfly valve and the outflow nozzle are mechanically interconnected in order to operate in proper sequence.

2.10.2

April 01, 2004

MD-88/90 Operations Manual

Pneumatic Pressure Gauge and Crossfeed Valve Levers

Air Systems -

Controls and Indicators

PNEU

PRESS

8 X 10

6

x 10

4

2

PNEU

X-FEED

VALVE

OPEN

PNEU

X-FEED

VALVE

OPEN

OVERHEAD PANEL

PEDESTAL

JB1-3-0958

JB1-3-0963

PNEU PRESS Gauge

Indicates pneumatic pressure in the crossfeed manifold available for systems operation.

L/R PNEU X-FEED VALVE Lever

OPEN - Opens respective X-FEED valve.

On the ground, supplies APU bleed air or air from a pneumatic ground source for operation of one or both air conditioning packs, and for engine start.

In flight, supplies the bleed air requirements for airfoil ice protection.

CLOSED - Closes respective X-FEED valve.

On the ground, shuts off APU bleed air or air from a pneumatic ground source used for operation of one or both air conditioning packs, or for engine start.

In flight, shuts off bleed air supply for the airfoil ice protection system and for opposite engine pneumatic starts. Air conditioning pack pneumatic supply is from its respective engine only.

NOTE:

Pneumatic crossfeed valve may be set in any position from fully open to fully closed.

April 01, 2004

2.10.3

Air Systems -

Controls and Indicators

MD-88/90 Operations Manual

Air Conditioning Panel

L VALVE

TEMP

COLD HOT

CONTROL

CKPT TEMP

AUTO

COLD

STOP

MANUAL

HOT

AIR CONDITIONING

PSI

4 x 100

PRESS

PSI

4 x 100

R VALVE

TEMP

COLD HOT

CONTROL

CABIN TEMP

AUTO

SUPPLY

OFF

HP BLD

OFF

AUTO

COLD

STOP

MANUAL

HOT

CABIN

SPLY

TEMP SEL

CABIN

RADIO

RACK

VENTURI

150

CABIN TEMP

120

FAN

OVERHEAD PANEL

JB1-3-0886A

L/R VALVE TEMP CONTROL Indicator

Indicates position of temperature control valve.

COLD - Temperature control valve is closed and blocking hot air supply.

HOT - Temperature control valve is fully open to allow maximum hot air supply.

L/R PRESS Gauge

Indicates pneumatic supply pressure available for operation of each air conditioning system.

TEMP SEL Display Selector

CABIN SPLY - Selects cabin supply duct temperature to be displayed on the

CABIN TEMP gauge.

CABIN - Selects cabin temperature to be displayed on the CABIN TEMP gauge.

RADIO RACK Switch

NOTE:

On the ground, both primary and standby radio rack fans are on, and the venturi valve is closed.

VENTURI - (Inflight) Turns off radio rack fan. Opens venturi valve.

FAN - (Inflight) Turns on primary radio rack fan and closes venturi valve to cool radio rack and heat forward cargo compartment. If the primary fan fails in flight, the standby radio rack fan automatically comes on.

2.10.4

February 28, 2005

MD-88/90 Operations Manual

Air Systems -

Controls and Indicators

CABIN TEMP Gauge

Indicates cabin temperature or cabin supply duct temperature, as selected with the cabin TEMP SEL display selector.

CKPT/CABIN TEMP Selector

AUTO - Temperature automatically adjusts toward HOT or COLD when the selector is moved left or right of the index mark.

MANUAL (COLD/STOP/HOT) - Spring loaded to stop. In MANUAL, momentarily moving the selector toward HOT or COLD opens or closes the temperature control valve. This is displayed on the L/R VALVE TEMP

CONTROL indicator.

L/R SUPPLY Switch

OFF - Closes the air conditioning pressure regulator and flow control valve.

On the ground, turns off the heat exchanger cooling fan.

HP BLD OFF - Opens the air conditioning pressure regulator and flow control valve, and, when the airplane is on the ground, turns on the heat exchanger cooling fan. Closes the augmentation valve.

AUTO - Opens the air conditioning pressure regulator and flow control valve, and, when the airplane is on the ground, turns on the heat exchanger cooling fan. If the low stage pneumatic supply pressure is too low, the augmentation valve opens to supply the pressure.

NOTE:

During airfoil ice protection (PNEU X-FEED VALVE(s) OPEN and AIR FOIL switch in ON) the augmentation valve opens and temperature and pressure are provided by high stage bleed air regardless of the position of the air conditioning supply switch(es).

April 01, 2004

2.10.5

Air Systems -

Controls and Indicators

MD-88/90 Operations Manual

APU Air Switch and Air Flow Indicator

APU

AIR

OFF

AIR COND

COLDER

ON

FLOW

OFF

GLARESHIELD

OVERHEAD PANEL

JB1-3-0887

JB1-3-0887

APU AIR Switch

OFF - Closes APU air shutoff valve to isolate the APU from the airplane pneumatic system.

ON - Provides APU bleed air to the airplane crossfeed manifold.

AIR COND COLDER - Closes turbine bypass valves and increases differential pressure across the air conditioning turbine for additional cooling air capacity during ground operation.

Instrument Cooling Air FLOW Indicator (Ground Only)

ON - With both air conditioning packs OFF, indicates instrument cooling air flow provided by the instrument cooling fan.

OFF - With both air conditioning packs OFF, indicates a failure of the instrument cooling fan.

2.10.6

April 01, 2004

Air Systems -

Controls and Indicators

MD-88/90 Operations Manual

Cabin Altitude/Differential Pressure Gauge and Cabin Climb Gauge

0 1000

DIFF PRESS

PSI

CAB ALT

CLIMB

DESCEND

CABIN

CLIMB

1000

FT/MIN

1.5

OVERHEAD PANEL

JB1-3-0889

JB1-3-0889

CAB ALT/DIFF PRESS Gauge

CAB ALT - Indicates existing cabin altitude.

DIFF PRESS PSI - Indicates the differential pressure in psi between cabin pressure and ambient pressure.

CABIN CLIMB Gauge

Indicates the rate of change in cabin altitude.

April 01, 2004 2.10.7

Air Systems -

Controls and Indicators

MD-88/90 Operations Manual

Air Conditioning Shutoff Switch and Ram Air Switch

AIR

COND

SHUTOFF

OVRD

AUTO

RAM AIR

OFF

OVERHEAD PANEL

JB1-3-0888

JB1-3-0888

AIR COND SHUTOFF Switch

OVRD - Deactivates automatic shutdown of air conditioning packs.

AUTO - Automatically shuts down packs if either engine fails during takeoff.

RAM AIR Switch

OFF - Closes ram air valve.

ON - Opens ram air valve and allows ram air to enter the conditioned air ducts in the right air conditioning system at a point prior to the mixing chamber.

2.10.8

April 01, 2004

MD-88/90 Operations Manual

Cabin Pressure Control Panel

TAKEOFF & LAND UNPRESSURIZED

SCHED APL

1000 FT CABIN

20 25 30 35

4 6 8

AUTO INOP

100 FT

FLOW

AUTO 1

INOP

30.0

29.9

29.8

RATE LIMIT

AUTO 2

INOP

LDG ALT

LDG BARO

CABIN

PRESSURE

Air Systems -

Controls and Indicators

7 6

OVERHEAD PANEL

JB1-3-0890

CABIN PRESSURE System Selector Panel

AUTO INOP (amber) - Illuminates when both automatic systems fail.

Pressurization is manually monitored and controlled.

INOP (2) (blue) - Illuminates when that system fails. The standby system automatically controls pressurization.

APL/CABIN Altitude Scale

Scale shows relationship between airplane altitude and cabin altitude in thousands of feet.

FLOW Light (amber)

Illuminates with a closed outflow valve and a cabin climb rate is detected.

RATE LIMIT Control Knob

Adjusts cabin climb/descend rate. At index mark, climb rate is 700 fpm and descent rate is 300 fpm.

Cabin climb rates between 50 and 2000 fpm and descent rates between 21 and

857 fpm are available for selection.

LDG BARO Knob and Window

Turn to select destination barometric pressure. Selection displays in IN HG window.

April 01, 2004 2.10.9

Air Systems -

Controls and Indicators

MD-88/90 Operations Manual

LDG ALT Knob and Window

Turn to select destination airport altitude. Selection displays in 100 FT window.

CABIN PRESSURE System Selection Switch

Used to select either AUTO 1 or AUTO 2 as the primary system. The remaining system is the standby system.

Cabin Altitude Control

FWD

CLOSED

DESCEND

OPEN

CLIMB

CENTER PEDESTAL

JB1-3-0891

CABIN ALT Control Wheel

When cabin altitude control is selected to auto, the control wheel rotates as the cabin air outflow valve automatically adjusts to maintain cabin altitude.

When cabin altitude control is selected to manual, the control wheel is locked in position. To adjust cabin altitude, push down on the control wheel and rotate in the desired direction.

Outflow Valve Position Indicator

Indicates position of cabin air outflow valve.

CABIN ALT Control Lever

Used to select automatic or manual cabin altitude control.

When moved up, cabin altitude is automatically controlled. When moved down, cabin altitude is manually controlled by rotating the control wheel.

2.10.10

April 01, 2004

Air Systems

MD-88/90 Operations Manual

Chapter 2 System Description Section 20

Pneumatic System

In flight pneumatic pressure is supplied by the low (8th) or high (13th) stage compressors of both engines. Normally, bleed air from the left and right engines is supplied to the respective air conditioning systems. Bleed air from both engines is supplied to the ice protection system simultaneously. Pneumatic crossfeed valves permit operation of the air conditioning systems and ice protection system from either engine.

An augmentation valve automatically regulates the flow of high stage bleed air into the system when low stage bleed air is not sufficient to satisfy flow or temperature requirements.

APU bleed air is normally used only for engine starting and for ground air conditioning when the engines are not operating.

Air Conditioning Systems

The airplane has two identical air conditioning systems. Normally the right system operates from right engine bleed air and controls the cabin temperature.

The left system operates from left engine bleed air and controls the cockpit temperature. Either system is capable of supplying the requirements of both compartments.

Pack pressure gauges indicate air conditioning supply for each (L/R) system. A flow control valve for each operating pack limits maximum air flow. Two air conditioning SUPPLY switches, one for each system, open or close the respective pressure regulator and flow control valve. When moved to OFF, the pressure regulator and flow control valve closes. When moved to either the HP

BLD OFF or AUTO position, the pressure regulator and flow control valve opens.

System Protection

Both air conditioning packs automatically shutdown if an engine fails with a cabin differential pressure of less than 1.3 psid.

NOTE:

Excessive thrust during one engine taxi may activate this automatic shutdown circuit and shut off both packs. Subsequent thrust reduction will restart the packs.

April 01, 2004 2.20.1

Air Systems -

System Description

MD-88/90 Operations Manual

Thermal shutdown switches protect the air conditioning systems against overheating. When air conditioning temperatures are excessive, the air conditioning pressure regulator and flow control valve close, preventing bleed airflow to its respective system.

Finally, if cooling airflow is not registered across a heat exchanger, the respective pack flow control valve will close, tripping the pack. With this trip, supply pressure continues to be indicated on the respective AIR

CONDITIONING PRESS gauge.

RAM Air

In flight, with air conditioning packs inoperative, the RAM AIR system may be used to ventilate the airplane. Moving the RAM AIR switch on the overhead panel to ON opens the ram air valve located in the right heat exchanger cooling duct. This allows ram air to enter the mixing chamber for airplane ventilation.

Air Distribution

The air distribution system uses both cold air and conditioned air.

Cold air from the pack is ducted to individual eyeball outlets for each passenger and an overhead vent for each crew member.

Hot air is mixed with cold air to create conditioned air, which is distributed throughout the airplane to satisfy air conditioning requirements. Conditioned air from the air conditioning systems passes through a mixing chamber for distribution to the cabin and cockpit. Conditioned air for the cabin is discharged from outlets below the overhead bins, and from an overhead vent in the cabin entryway. Conditioned air for the cockpit is discharged through two adjustable nozzles adjacent to the instrument panel, and one adjustable overhead diffuser.

In flight, a recirculating fan, located forward of the rear pressure bulkhead, returns the cabin air to the overhead ducts for recirculation to the cabin only.

The recirculating fan has no cockpit controls or indicators.

Cockpit and Cabin Temperature Control

Cockpit and cabin temperatures are controlled from the cockpit. Temperatures may be adjusted in either AUTO or MANUAL mode with the CKPT TEMP and

CABIN TEMP selectors.

When operating in the AUTO mode, a temperature range of 65°F to 80°F is available.

When operating in the MANUAL mode, the CKPT TEMP and CABIN TEMP selectors are spring-loaded to the STOP position and must be momentarily held in HOT or COLD positions until the desired temperature is obtained.

2.20.2

April 01, 2004

Air Systems -

System Description

MD-88/90 Operations Manual

A CABIN TEMP gauge displays temperature in the cabin or cabin supply ducting, as selected by the cabin TEMP SEL switch.

When operating on emergency power, cabin and cockpit temperatures are controlled in the MANUAL mode only.

Radio Rack Cooling Fans

Cockpit exhaust air cools the electronic equipment in the electrical/electronic

(E/E) compartment. This air is drawn through the E&E compartment by a primary radio rack fan and a standby radio rack fan. During flight, only the primary fan operates.

In flight, with the RADIO RACK switch in FAN, failure of the primary fan causes the standby fan to automatically operate. A failure of both fans causes the RADIO FAN OFF message to be displayed on the overhead annunciator panel (OAP). With the RADIO RACK switch in VENTURI, the venturi valve

(normally closed with switch in FAN) opens, thus allowing the air to exhaust overboard. When VENTURI has been selected, the RADIO FAN OFF message is canceled.

During ground operation both fans operate. The RADIO FAN OFF message is displayed only when there is a failure of the primary fan.

Instrument Cooling Fan

Instrument cooling is normally provided by the air conditioning system; however, on the ground with neither pack operating, instrument cooling is provided by an integral fan (which operates only on the ground) located under the First Officer’s flight kit stowage area. Flow from the cooling fan is indicated by an indicator above the First Officer’s instruments.

Pack Cooling

The heat exchanger fans (which operate only on the ground) provide cooling air to the respective heat exchangers when the air conditioning systems are operating on the ground. With an air conditioning SUPPLY switch moved from

OFF, the respective fan automatically operates.

The left heat exchanger cooling fan draws cooling air from the ram air scoop at the base of the vertical stabilizer. To reduce tail compartment temperatures, the right heater exchanger cooling fan draws air from the tail compartment area. Air enters the tail compartment through louvers on the empennage.

In flight, cooling air enters the ram air scoop, then is ducted to the heat exchangers for both packs where it is exhausted overboard.

April 01, 2004 2.20.3

Air Systems -

System Description

MD-88/90 Operations Manual

Ground Sources for Air Conditioning

There are three methods used to cool the aircraft on the ground:

• using a conditioned air source connected at either the left side of the fuselage at the mid cabin area or at the right rear of the aircraft.

• using the APU pneumatics to operate the packs or,

• using an external pneumatic source connected at the aft left side of the fuselage to run the packs.

APU Air Conditioning

The APU can be used to supply pneumatics for air conditioning during ground operations only.

The APU AIR switch, in the ON position allows the APU to supply air to the pneumatic system. The OFF position shuts off supply air. The AIR COND

COLDER position closes both pack turbine bypass valves. This allows for reduced conditioned airflow at a cooler temperature. Since both valves close, the AIR COND COLDER position of the APU AIR switch may not be used in conjunction with engine operation which could overspeed the packs.

Airplane Pressurization

A pressurization system, consisting of two identical but independent controllers, is powered from different electrical sources. The selected system maintains primary control, while the other system serves as a standby.

With at least one pack operating, pressurization levels are maintained by regulating escape air through the cabin air outflow valves. Normally, the outflow valves are automatically positioned by the pressurization system.

For automatic operation of the outflow valves, the CABIN ALT control lever must be in the up position. The CABIN ALT control wheel rotates as the system automatically adjusts to maintain pressurization. An outflow valve position indicator next to the wheel moves to indicate valve position.

If the selected cabin pressure controller fails, a blue INOP light on the cabin pressure selector panel illuminates below the failed system and an automatic transfer occurs. If both systems have failed, a blue INOP light illuminates below each system and an amber AUTO INOP light also illuminates.

For manual operation, the CABIN ALT control lever must be placed to the down position. The wheel is pressed down and rotated in the desired direction.

The indicator moves in the same direction to indicate outflow valve position.

2.20.4

April 01, 2004

Air Systems -

System Description

MD-88/90 Operations Manual

Dual pressure relief valves protect the airplane structure from over pressurization. Inward movement of the galley service and passenger entrance door seals, and a negative pressure relief valve installed in the aft pressure bulkhead, relieves negative pressure.

When the pressurization system fails to maintain cabin altitude below 10,000 feet, a red CABIN ALT warning light on the OAP illuminates and a warning horn and vocal ("Cabin Altitude") sounds (5 seconds) .

With the airplane on the ground, the automatic system pressurizes the cabin when the throttles are advanced for takeoff. At this time, a 60-second timer is also started. If the airplane is not in flight within 60 seconds after throttles are advanced for takeoff, the cabin depressurizes. In the event of a rejected takeoff, the cabin automatically depressurizes when the throttles are retarded.

During climb and cruise, the cabin automatically pressurizes according to the climb schedule, as a function of airplane altitude. Once a descent has been detected, the pressurization system will begin its depressurization schedule to be depressurized at landing field elevation.

If landing altitude is set below actual field altitude, at airplane touchdown, a signal from the ground control relay will depressurize the cabin at a controlled rate for 20 seconds, at which time the cabin outflow valves will drive full open.

Pneumatic Air Distribution

Engine bleed air from either the low pressure (8th-stage) or high pressure

(13th-stage) compressors is ducted into separate air manifolds (low and high) and then into the pneumatic system ducting for distribution. Pneumatic air is regulated for pressure and temperature. Low stage bleed air use is utilized as much as possible to maximize engine performance. High stage bleed air is used only during reduced engine power to maintain pressure. High stage air is always utilized for temperature control during airfoil anti-ice operations.

The pneumatic system is divided into a left, a right, and a crossfeed manifold.

Left engine bleed air operates the left system, and right engine bleed air operates the right system. When both pneumatic crossfeed valves are closed, the crossfeed manifold is isolated from left and right engine bleed air. The pneumatic ground connection, the APU supply duct, the ice protection system supply duct, and the pneumatic pressure transmitter are located in the crossfeed manifold.

Pneumatic Indication System

The pneumatic indication system incorporates a PNEU PRESS gauge, red warning lights, and amber caution messages.

April 01, 2004 2.20.5

Air Systems -

System Description

MD-88/90 Operations Manual

The pneumatic pressure gauge, located on the cockpit overhead panel, displays crossfeed manifold pressure.

The red warning light (TAIL COMP TEMP HIGH), located on the overhead annunciator panel (OAP), indicates excessive tail compartment temperature.

Air Conditioning Pneumatic Supply

Pressure and temperature controlled engine bleed air is distributed into the pneumatic ducting from each engine and routed to the pneumatic manifold in the aft accessory compartment. It is then delivered to the respective air conditioning units.

Low stage bleed air is normally sufficient to supply the requirements of either the right or the left air conditioning system. High stage bleed air is automatically selected, as required, to maintain adequate air conditioning demands.

Hot air from the pneumatic system is mixed with cold air from the air conditioning system to provide temperature control for the cabin and cockpit.

Airfoil Ice Protection and Engine Anti-ice Pneumatic Supply

Hot air is used for the airfoil ice protection and engine anti-ice systems. High stage bleed air only is used for airfoil ice protection.

High and low stage bleed air provide engine anti-ice protection.

Depending on crossfeed valve(s) position, bleed air from the left, right, or both engines supplies the ice protection system.

Ground Operation Pneumatic Supply

Pneumatic pressure for ground operation and engine start is supplied by the

APU, by ground power equipment, or by an operating engine.

When the engines are not operating, APU bleed air or a ground source pressurizes the pneumatic crossfeed manifold for engine start and air conditioning. Selective positioning of the respective crossfeed valves (left or right system) pressurizes the left, right, or both systems. A check valve prevents backflow into the engine low stage manifold. The APU is equipped with a check valve to prevent air from entering the APU when the APU is not operating.

With both crossfeed valves open, engine bleed air pressure from one operating engine can be used to start the opposite engine, or to operate both left and right air conditioning systems.

2.20.6

April 01, 2004

Air Systems -

System Description

MD-88/90 Operations Manual

Pneumatic Supply Inflight

Generally, pneumatic pressure for air conditioning is supplied by the low stage compressors for takeoff, climb, and cruise. During low power settings and when using airfoil ice protection bleed air is supplied by the high stage compressors.

April 01, 2004 2.20.7

Air Systems -

System Description

MD-88/90 Operations Manual

Intentionally

Blank

2.20.8

April 01, 2004

Air Systems

MD-88/90 Operations Manual

Chapter 2 OAP Messages/Lights Section 30

OAP Messages/Lights

Red Warning Lights

CABIN ALT - Cabin altitude exceeds 10,000 feet.

TAIL COMP TEMP HIGH - Tail compartment temperature exceeds normal.

Amber Caution Messages

NOTE: The associated cue light is shown in parenthesis (XXX) following the message.

(L/R) AIR COND TEMP HIGH (MISC) - Indicates air conditioning pneumatic supply exceeds normal operating temperature. Indicates possible malfunction of augmentation valve. MASTER CAUTION lights also illuminate.

RADIO FAN OFF (MISC) - Illuminates in flight to indicate RADIO

RACK switch is in FAN position and primary and standby fans are inoperative. On ground, message illuminates if primary fan is inoperative.

April 01, 2004 2.30.1

Air Systems -

OAP Messages/Lights

MD-88/90 Operations Manual

Intentionally

Blank

2.30.2

April 01, 2004

Air Systems

MD-88/90 Operations Manual

Functional Schematic

MD-88 Pneumatic Schematic

Chapter 2

Section 40

LEFT

April 01, 2004

JB1-3-096

2.40.1

Air Systems -

Functional Schematic

MD-88/90 Operations Manual

MD-88 Air Conditioning Schematic

2.40.2

JB1-3-0962

April 01, 2004

Air Systems

MD-88/90 Operations Manual

Chapter 2

MD-90 Differences

Controls and Indicators

Air Conditioning Panel

L VALVE

TEMP

COLD HOT

CONTROL

CKPT TEMP

AUTO

COLD

STOP

MANUAL

HOT

FLOW

AIR CONDITIONING

FLOW

R VALVE

TEMP

COLD HOT

CONTROL

CABIN TEMP

AUTO

SUPPLY

OFF

HP BLD

OFF

AUTO

COLD

STOP

MANUAL

HOT

CABIN

SPLY

TEMP SEL

CABIN

RADIO

RACK

VENTURI

150

CABIN TEMP

120

FAN

Section 90

OVERHEAD PANEL

JB1-3-0886A

L/R FLOW Gauge

Indicates air conditioning supply flow from the respective system.

L/R SUPPLY Switch

NOTE: During airfoil ice protection (PNEU X-FEED VALVE OPEN and AIR FOIL switch in ON) the pressure regulator and shutoff valve opens and pressure is supplemented by the high stage valve regardless of the position of the AIR CONDITIONING SUPPLY switch.

OFF - Closes the air conditioning flow control valve. On the ground, turns off the heat exchanger cooling fan.

With the PNEU X-FEED VALVE lever fully closed, the switch in OFF closes the pressure regulator and shutoff valve and the high stage valve.

HP BLD OFF - Opens the air conditioning flow control valve, the pressure regulator and shutoff valve, and, when the airplane is on the ground, starts the heat exchanger cooling fan. Closes the high stage valve.

April 01, 2004

2.90.1

Air Systems -

MD-90 Differences

MD-88/90 Operations Manual

AUTO - Opens the air conditioning flow control valve, the pressure regulator and shutoff valve, and, when the airplane is on the ground, turns on the heat exchanger cooling fan. If the low stage pneumatic supply pressure is too low, the high stage valve opens to supplement the pressure.

NOTE:

Instrument cooling fan shuts down automatically when both pack switches are out of OFF.

CKPT/CABIN TEMP Selector

AUTO - Temperature automatically adjusts toward HOT or COLD when the selector is moved left or right of the index mark. The water separator temperature control valve regulates the cold air supply to 35°F.

NOTE:

In MANUAL, the water separator 35°F temperature control valve is inoperative, and the pneumatic control backup system prevents the water separator from freezing.

APU Air Switch

APU

AIR

OFF

AIR COND

COLDER

ON

FLOW

OFF

GLARESHIELD

OVERHEAD PANEL

JB1-3-0887

JB1-3-0887

APU AIR Switch

OFF - Closes APU air shutoff valve to isolate the APU from the airplane pneumatic system. Retracts ram air inlet door for clearance during takeoff and landing.

ON - Provides APU bleed air to the airplane pneumatic system. Opens the ram air inlet door during ground operation to maximize APU performance.

2.90.2

April 01, 2004

Air Systems -

MD-90 Differences

PNEU

PRESS

MD-88/90 Operations Manual

AIR COND COLDER - Closes turbine bypass valve and increases differential pressure across the air conditioning turbine for additional cooling air capacity during ground operation.

Crossfeed Valve Lever

8 X 10

6

4

2

OVERHEAD PANEL

X-FEED

VALVE

OPEN

PEDESTAL

JB1-3-0963

JB1-3-0963

L/R PNEU X-FEED VALVE Lever

OPEN - Opens respective X-FEED valve.

In flight, supplies the bleed air requirements for airfoil ice protection, single engine operation of both air conditioning packs, and an opposite engine pneumatic start.

System Description

Air Conditioning Systems

Cockpit FLOW (L/R) gauges indicate air conditioning supply from each (L/R) system.

Cabin Air Recirculation Fan

On the ground, on a moderate temperature day when maximum cabin cooling is not needed, the APU cuts back bleed air output, thus minimizing APU fuel consumption. To compensate for the cutback, the recirculation fan operates to increase the total cabin ventilation rate.

April 01, 2004

2.90.3

Air Systems -

MD-90 Differences

MD-88/90 Operations Manual

APU On-ground Air Conditioning

On the ground with AIR switch ON, the APU RAM door will open for enhanced

APU cooling.

Pneumatic Air Distribution

Engine bleed air from either or both the low pressure (7th-stage) or high pressure

(10th-stage) compressors is ducted into separate bleed air manifolds and then into the pneumatic system for distribution. Pneumatic air is regulated for pressure and temperature. Low stage bleed air is utilized as much as possible to minimize engine performance. High stage bleed air is used only during reduced engine power to maintain pressure and temperature demands.

Pneumatic Indication System

Red warning lights (L TAIL TEMP HIGH/R TAIL TEMP HIGH), located on the overhead annunciator panel (OAP), indicate excessive tail compartment or pylon temperatures.

The amber (L/R) PNEU SYSTEM FAULT message indicates excessive supply pressures in the supply ducting, or failure of the (L/R) manifold pressure sensor, or pneumatic system controller (PSC) failure to control the left/right pneumatic system, or a loss of controller power.

The amber TAIL TEMP FAULT message indicates both channels of the pneumatic overheat detection system (PODS) controller are unable to detect a high tail temperature.

Pneumatic System Controller (PSC)

The PSC, located in the electrical/electronics (E/E) compartment, controls pneumatic temperature and pressure, based on requirements for air conditioning and ice protection.

The PSC electronically monitors and controls pneumatic supply to the system through the high stage valve and pressure regulator and shutoff valve (PRSOV) on each engine.

Pneumatic Precooler

The pneumatic precooler is a heat exchanger, located downstream of the high and low stage engine bleed air ducts. Acceptable bleed air temperature is maintained by cooling it with fan air.

Fan air flow is regulated by the fan air valve. The PSC modulates the fan air valve by electronically controlling the fan air pilot valve.

2.90.4

April 01, 2004

Air Systems -

MD-90 Differences

MD-88/90 Operations Manual

At altitudes above 20,000 feet, when ice protection is not selected, the PSC controls bleed air temperature to a higher temperature, thus requiring less fan air for cooling, and reducing fuel consumption.

Pneumatic Overheat Detection System (PODS)

The pneumatic overheat detection system (PODS) records the locations of pylon and/or tail compartment overheat conditions, and any sensor failures.

The red (L/R) TAIL TEMP HIGH light(s) and MASTER WARNING lights illuminate whenever an overheat condition is detected, or, on takeoff, if both sensors have failed simultaneously just prior to takeoff.

The TAIL TEMP FAULT message indicates that PODS cannot detect an overheat condition. The message is displayed if one sensor fails, or both sensors on a side fail, or, if one or both controller channels fail.

Airfoil Ice Protection and Engine Anti-ice Pneumatic Supply

Depending on crossfeed valve(s) position, bleed air from the left, right, or both engines supplies the ice protection system. The PSC maintains adequate temperature and pressure to operate the system.

OAP Messages and Alerts

Red Warning Lights

L/R TAIL TEMP HIGH - Tail compartment or pylon temperature exceeds normal. Or, during takeoff, both PODS sensors have simultaneously failed just prior to the takeoff. Illuminates MASTER WARNING lights.

Amber Caution Messages

NOTE:

The associated cue light is shown in parenthesis (XXX) following the message.

(L/R) PNEU SYSTEM FAULT (MISC) - Supply pressure exceeds normal due to malfunction of pressure regulator and shutoff valve (PRSOV) and/or high stage valve, or, malfunction of L/R pneumatic system controller, or, failure of pneumatic manifold sensor, or, loss of controller pressure.

TAIL TEMP FAULT (MISC) - One or both channels of the tail temperature high controller is unable to detect a high tail temperature.

April 01, 2004

2.90.5

Air Systems -

MD-90 Differences

MD-88/90 Operations Manual

Functional Schematic

MD-90 Pneumatic Schematic

2.90.6

JB1-3-096

April 01, 2004

MD-88/90 Operations Manual

MD-90 Air Conditioning Schematic

Air Systems -

MD-90 Differences

April 01, 2004

JB1-3-09

2.90.7

Air Systems -

MD-90 Differences

MD-88/90 Operations Manual

Intentionally

Blank

2.90.8

Anti-Ice, Rain

MD-88/90 Operations Manual

Chapter 3

Section 0

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.10.1

Component Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.10.1

Ice Protection Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.10.2

OVERWING HEATER Switch . . . . . . . . . . . . . . . . . . . . . . . . . 3.10.4

ANTI-ICE and ANTI-FOG Electrical Resistance Heating . . . . 3.10.5

Pneumatic Pressure Gauge and Crossfeed Valve Levers. . . . . . 3.10.6

Windshield Wiper and Rain Repellent System . . . . . . . . . . . . . 3.10.7

System Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.1

General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.1

Air Foil Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.1

Engine Ice Protection. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.2

Probe Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.2

Overwing Heater System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.2

Warm Light Inhibit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.3

Warm Light Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.3

Load Shedding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.4

Rain Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.4

Windshield Wipers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .3.20.4

Windshield Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.20.4

Externally Powered Waterline Heater . . . . . . . . . . . . . . . . . . . . 3.20.4

OAP Messages/Lights. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.30.1

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.30.1

Amber Caution Messages. . . . . . . . . . . . . . . . . . . . . . . . . . . 3.30.1

Blue Advisory Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.30.1

April 01, 2004 3.TOC.0.1

Anti-Ice, Rain -

Table of Contents

MD-88/90 Operations Manual

Functional Schematic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.40.1

Schematics. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.40.1

MD-88 Ice and Rain System . . . . . . . . . . . . . . . . . . . . . . . . 3.40.1

MD-90 Differences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.1

Control and Displays . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.1

Component Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.1

Ice Protection Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.2

ICE FOD Switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.3

Description and Operation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.4

Pneumatics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.4

Ice and Rain Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.4

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.6

Amber Caution Messages . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.6

Blue Advisory Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.6

Functional Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.90.7

MD-90 Ice and Rain System . . . . . . . . . . . . . . . . . . . . . . . . 3.90.7

3.TOC.0.2

April 01, 2004

MD-88/90 Operations Manual

Anti-Ice, Rain

Controls and Indicators

Component Location

Chapter 3

Section 10

LEFT PITOT

(CAPTAIN’S)

LEFT

ANGLE-OF-ATTACK

VANE

3 WINDSHIELDS

(ANTI-ICING, ANTI-FOGGING)

LEFT STRAKE

LEFT AND RIGHT CLEARVIEW

AND EYEBROW WINDOWS

(ANTI-FOGGING ONLY)

CENTER PITOT

(AUXILIARY)

RIGHT PITOT

(FIRST OFFICER’S)

RIGHT

ANGLE-OF-ATTACK

VANE

RAM AIR TEMPERATURE PROBE

RIGHT STRAKE

LEFT AND RIGHT

WINDSHIELD WIPERS

LEFT AND RIGHT

STATIC PORTS

LEFT AND RIGHT

ALTERNATE STATIC PORTS

OVERWING HEATERS

WING LEADING

EDGE SLATS

ENGINE NOSE COWL

ENGINE INLET

GUIDE VANES

HORIZONTAL STABILIZER

LEADING EDGE

RAM AIR SCOOP

RUDDER PITOT

Ice and Rain Protection

April 01, 2004

JB1-3-0955

3.10.1

Anti-Ice, Rain -

Controls and Indicators

MD-88/90 Operations Manual

Ice Protection Panel

2 4 6 8

HEATER/CUR

ICE PROTECT

METER SEL

& HEAT

CAPT

AUX F/O

P I TO T

RUD

LIM

OFF

RAT

PROBE

R L

STATIC

STALL

PROBE

AIR FOIL

OFF

TAIL

WINDSHIELD

ANTI-FOG ANTI-ICE

OFF

ENG

OFF

OVERHEAD PANEL

JB1-3-0983

JB1-3-0983

HEATER/CUR Meter

Displays current flow to the respective heater, as selected by the METER SEL

& HEAT selector.

METER SEL & HEAT Selector

Moving the selector to any position except OFF energizes all heater circuits, except the RAT probe while on the ground.

AIR FOIL Anti-Ice Switch

OFF - Closes the ice protection pressure regulator valve.

ON - Opens the ice protection pressure regulator valve.

WINDSHIELD ANTI-FOG Switch

OFF - Deactivates the anti-fog system.

ON - Provides electrical heat to the inside surface of the windshields, the clearview windows, and the eyebrow windows.

WINDSHIELD ANTI-ICE Switch

OFF - Deactivates the windshield anti-ice system.

ON - Provides electrical heat to the outside of the three windshields.

3.10.2

April 01, 2004

Anti-Ice, Rain -

Controls and Indicators

MD-88/90 Operations Manual

L/R ENG Anti-Ice Switch

OFF - Closes the eighth and thirteenth stage valves to the respective engine anti-ice system.

ON - Opens the eighth and thirteenth stage valves to the respective engine anti-ice system.

TAIL De-Ice Pushbutton

Push - (Air foil system in-use) Closes the shutoff valve to the wing and opens the shutoff valve to the tail to allow 2.5 minutes of tail de-ice. The system automatically reverts to wing anti-ice function following the 2.5 minutes of tail de-ice function.

April 01, 2004

3.10.3

Anti-Ice, Rain -

Controls and Indicators

MD-88/90 Operations Manual

OVERWING HEATER Switch

FAIL

WARM

OVERWING

HEATER

OFF

ARM

CAPT’S INSTRUMENT PANEL

JB1-3-0983

L/R FAIL Lights (amber)

Illuminates when any fault is detected with power applied to the system. If a failure is detected, the WARM light will not illuminate or, if illuminated, will extinguish.

WARM Light (green)

Illuminates when both heaters are 40°F (4°C) or above.

OVERWING HEATER Switch

ARM - Provides electrical power to the wing heater control units when the airplane is on the ground. The switch is normally guarded to this position.

OFF - Removes electrical power from the heater control units.

3.10.4

February 28, 2005

MD-88/90 Operations Manual

ANTI-ICE and ANTI-FOG Electrical Resistance Heating

Anti-Ice, Rain -

Controls and Indicators

ANTI-ICE

RIGHT

WINDSHIELD

RIGHT

CLEARVIEW

WINDOW

RIGHT

UPPER

WINDOW

(EYEBROW)

RIGHT AFT

WINDOW

CENTER

WINDSHIELD

ANTI-FOG

LEFT

WINDSHIELD

LEFT

UPPER

WINDOW

(EYEBROW)

LEFT

CLEARVIEW

WINDOW

LEFT AFT

WINDOW

April 01, 2004

JB1-3-0957

3.10.5

Anti-Ice, Rain -

Controls and Indicators

MD-88/90 Operations Manual

Pneumatic Pressure Gauge and Crossfeed Valve Levers

PNEU

PRESS

8 8 X 10

6 x 10

PNEU

X-FEED

VALVE

OPEN

PNEU

X-FEED

VALVE

OPEN

OVERHEAD PANEL

PEDESTAL

JB1-3-0958

JB1-3-0963

PNEU PRESS Gauge

Indicates pneumatic pressure in the crossfeed manifold available for systems operation.

L/R PNEU X-FEED VALVE Lever

OPEN - Opens respective X-FEED valve.

CLOSED - Closes respective X-FEED valve.

3.10.6

April 01, 2004

MD-88/90 Operations Manual

Windshield Wiper and Rain Repellent System

Anti-Ice, Rain -

Controls and Indicators

REPELLENT

RES

RAIN

PARK

WIPER

OFF

SLOW

FAST

OVERHEAD PANEL

RAIN WIPER Selector

PARK - Positions wiper to parked.

OFF - Deactivates wiper.

SLOW/FAST - Controls wiper operating speed.

RAIN REPELLENT - Deactivated

JB1-3-0984

April 01, 2004 3.10.7

Anti-Ice, Rain -

Controls and Indicators

MD-88/90 Operations Manual

Intentionally

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3.10.8

April 01, 2004

Anti-Ice, Rain

System Description

MD-88/90 Operations Manual

Chapter 3

Section 20 General

The aircraft ice protection systems employ hot air and electrical resistance heating for anti-icing, de-icing, and anti-fogging functions. Rain removal is accomplished by electrically operated windshield wipers.

Heated air for anti-icing of wing leading edge slats, forward strakes, air conditioning ram air inlet, and de-icing of the horizontal stabilizer leading edge is supplied by engine bleed air.

A pneumatic crossfeed system allows 13th stage engine bleed air from either or both engines to supply heat for air foil ice protection. A separate system on each engine utilizes 8th and 13th stage air for anti icing of the EPR probe, nose bullet, inlet guide vanes and the nose cowl.

Electrical resistance heating elements provide anti-icing and anti-fogging of the pilot’s three windshields and for anti-fogging the clearview and eyebrow windows. The windshield anti-ice system also provides for bird impact resistance.

Electrical resistance heating elements are used for anti-icing the pitot tubes, static port areas, stall angle of attack vanes, and ram air temperature probe.

An overwing heater system is installed to prevent formation of ice on the upper wing surface due to cold-soaked fuel.

Air Foil Ice Protection

Air foil ice protection is only available in-flight.

The system utilizes 13th stage bleed air and is activated by selecting the AIR FOIL switch to ON and placing the crossfeed valve(s) to OPEN. This action provides a continuous cycle of heat for the leading edge of the wings (slats) and the forward strakes for fifteen minutes, followed by 2 1/2 minutes of heat to the horizontal stabilizer. The ram air inlet is heated during both cycles.

The automatic cycle can be overridden by the TAIL button which, when pushed, provides for 2 1/2 minutes of horizontal stabilizer de-icing, after which a new wing cycle starts. Placing the AIR FOIL switch in the OFF position causes the horizontal stabilizer de-icing cycle to be activated for 2 1/2 minutes. Closing the pneumatic crossfeed valves during air foil ice protection operation causes the de-icing airflow to be deactivated and illuminate the AIRFL ICE PRESS ABNML message. On the ground the air foil ice protection system is disabled.

April 01, 2004

3.20.1

Anti-Ice, Rain -

System Description

MD-88/90 Operations Manual

Engine Ice Protection

Engine anti-ice protection is provided by two independent systems controlled by individual switches located on the ice protection panel. Each system consists of three engine anti-ice valves, two eighth stage and one thirteenth stage. The eighth stage anti-ice valves control heat to the inlet guide vanes, EPR probe, and nose bullet. The thirteenth stage anti-ice valve controls heat to the engine nose cowl.

Control of the system is operated by a switch for each engine. When selected ON, an amber (L/R) ENGINE VALVE message will appear on the overhead annunciator panel indicating the valves are in transit and disagree with the switch position. When at least one valve is fully open, a blue (L/R) ENGINE ANTI-ICE

ON light on the overhead annunciator panel illuminates. When all three valves are fully open, the amber message extinguishes, and the blue light remains illuminated indicating normal system operation.

Probe Heat

Electrical resistance heat is used to anti-ice the pitot tubes, the static port areas, the stall angle of attack vanes, and the ram air temperature (RAT) probe.

Moving the METER SEL & HEAT selector out of OFF energizes the anti-ice heating circuits for the pitot tubes, including the rudder limiter pitot on the leading edge of the vertical stabilizer, the stall angle of attack probes, the static ports, and the RAT probe. The RAT probe heater functions only in flight.

Overwing Heater System

The overwing heater system prevents the buildup of ice on the inboard corner of the upper wing. The overwing heater system does not de-ice the entire wing nor does it provide anti-ice or de-ice capability for environmental icing conditions.

The heater blankets operate on the ground to warm the upper surface of the wing.

When the surface temperature of both heater blankets reaches 40°F (4°C) the

WARM light (located on the Captain’s instrument panel) illuminates indicating that all portions of the heater surfaces are clear of ice or frost. The WARM light is then on continuously regardless of power application to the heaters. When the aircraft is on the ground, power continues to be applied as necessary to maintain a heater surface temperature between 65°F (18°C) and 85°F (29°C). If the heater surface temperature exceeds 85°F (29°C), the heating function is terminated until the heater surface temperature drops to 65°F (18°C), when heating is then resumed.

3.20.2

April 01, 2004

Anti-Ice, Rain -

System Description

MD-88/90 Operations Manual

System operation is enabled with:

• Aircraft on the ground

• AC power on the buses

• OVERWING HEATER switch in ARM

System status is monitored by a WARM/FAIL light. The heater control units continuously monitor the system for electrical faults and will remove AC electrical power to the affected heater and deactivate the WARM light when a fault is detected. When any fault is detected, the associated L FAIL or R FAIL light will illuminate. The WARM/FAIL lights are tested using the ANNUN/DIGITAL LTS

TEST switch and dimmed using the ANNUN/DIGITAL LTS PULL TO DIM switch.

Warm Light Inhibit

The system is designed with a startup delay of approximately one minute before electrical power is applied to the heaters. Once power is applied and if no system faults or failures exist, the WARM light should illuminate within 12 minutes. If the WARM light does not illuminate within 12 minutes, the WARM light is inhibited (locked out). For this to occur, the aircraft must have been on the ground for an extended period and exposed to the conditions conducive for upper wing ice formation or environmental airframe icing.

Warm Light Reset

Once inhibited, the WARM light will remain inhibited until the heater surface reaches 40°F (4°C) and the flight crew presses the WARM/FAIL light assembly to reset the system. Once pressed, the WARM light will:

• Illuminate immediately indicating the heater blanket surfaces have reached 40°F (4°C); or

• Remain off, illuminating later when the heater blanket surfaces do reach

40°F (4°C). Should the WARM light need to be reset, a visual inspection for ice on the heater blanket surface (from the ground) will be required after the WARM light illuminates. If the WARM light does not illuminate, a tactile check (poles and ladders) will be required.

April 01, 2004 3.20.3

Anti-Ice, Rain -

System Description

MD-88/90 Operations Manual

Load Shedding

The electrical power required by the overwing heaters may require the automatic shedding of some non-essential loads, depending on the available power source.

With the APU or external power only, automatic shedding of #3 galley will occur whenever the heaters are in operation. There are no load-shedding requirements when two generators are operating (two engine-driven generators or one engine-driven generator and the APU).

NOTE: The overwing heater system is not designed to provide any environmental

anti-ice or de-ice capability and the switch must be OFF for environmental icing conditions. This is to prevent runback icing which is caused by melted precipitation re-freezing in the flap well area.

Rain Removal

Windshield Wipers

A windshield wiper is provided for the left and right windshield. Both wipers are electrically operated. The selector provides a selection of slow or fast speeds and controls the stowing of the wiper blades to the park position when the system is not in use.

Windshield Heat

Windshield anti-icing and anti-fogging are electric and automatically controlled.

There is a separate switch for each system.

The anti-icing system heats the outer surface of the Captain’s, Center, and First

Officer’s windshields. The anti-fog system heats the inner surface of all windows except the left and right aft windows.

Externally Powered Waterline Heater

An externally powered AC receptacle, located on the forward left side of the aircraft, is installed to provide heat for the potable water lines. Its use is primarily for freeze protection during extended layovers at cold temperatures.

3.20.4

April 01, 2004

MD-88/90 Operations Manual

Anti-Ice, Rain

OAP Messages/Lights

Chapter 3

Section 30 OAP Messages/Lights

Amber Caution Messages

NOTE: The associated cue light is shown in parenthesis (XXX) following the message.

AIRFL ICE PRES ABNML (ICE) - Low or unscheduled pressure in wing and/or duct to horizontal stabilizer. Malfunction of ice protection pressure regulator and shutoff valve if AIR FOIL switch selected OFF after tail cycle complete. MASTER CAUTION lights illuminate.

ANTI-ICE SUPPLY HIGH (ICE) - Malfunction of the ice protection pressure regulator and shutoff valve causing excessive duct pressure. MASTER

CAUTION lights illuminate.

L/R ENG VALVE (ICE) - One or more of the engine valve position disagrees with ENG anti-ice switch position.

L/R ICE PROT TEMP HIGH (ICE) - Malfunction of augmentation valve, resulting in high duct temperature. MASTER CAUTION lights illuminate.

L/R ICE PROT TEMP LOW (ICE) - Low engine power or malfunction of augmentation valve resulting in low duct temperature.

PITOT/STALL HEAT OFF (ICE) - Electrical power loss to one or more Pitot probes or Stall/AOA vanes. MASTER CAUTION lights illuminate.

WINDSHIELD OVERTEMP (ICE) - One or more windshield panes is overheated, resulting in the removal of anti-ice power from the overheated windshield(s). Requires ground maintenance to restore system.

Blue Advisory Lights

L/R ENG ANTI-ICE ON - One or more engine anti-ice valves open.

NOTE:

When any engine anti-ice valve(s) is open, R ENG ANTI-ICE ON or L ENG ANTI-ICE ON light will be illuminated regardless of ENG anti-ice switch position.

February 28, 2005

3.30.1

Anti-Ice, Rain -

OAP Messages/Lights

MD-88/90 Operations Manual

RAIN REPELLENT RESERVE IN USE - Deactivated.

TAIL DE-ICE ON - Horizontal stabilizer leading edge and ram air scoop de-ice heat selected. Will also be illuminated for 2.5 minutes after switch is turned OFF.

WING ANTI-ICE ON - Wing leading edge and ram air scoop anti-ice heat selected.

3.30.2

April 01, 2004

MD-88/90 Operations Manual

Anti-Ice, Rain

Functional Schematic

MD-88 Ice and Rain System

Chapter 3

Section 40

LEADING EDGE SLA

April 01, 2004 3.40.1

Anti-Ice, Rain -

Functional Schematic

MD-88/90 Operations Manual

Intentionally

Blank

3.40.2

April 01, 2004

Anti-Ice, Rain

MD-90 Differences

MD-88/90 Operations Manual

Controls and Displays

Component Location

TOTAL AIR TEMP (TAT)

PROBE

LEFT STRAKE

(ELECTRICAL)

Chapter 3

Section 90

RIGHT STRAKE

(ELECTRICAL)

ICE DETECTORS

April 01, 2004

M90 Top Ovrview

3.90.1

Anti-Ice, Rain -

MD-90 Differences

Ice Protection Panel

MD-88/90 Operations Manual

EMER

LTS

OFF

ARM

SMOK

AUTO

SEAT

BELTS

OFF

ICE PROTECT

OFF

AIR FOIL

4 6

HEATER CUR

METER SEL

& HEAT

CAPT

AUX F/O

P ITOT

RUD

LIM

OFF

TAT

PROBE

STATIC

STALL

PROBE

TAIL

WINDSHIELD

ANTI-FOG

OFF

ANTI-ICE

ENG

OFF

OVERHEAD PANEL

JB1-3-0983

AIR FOIL Anti-Ice Switch

With air foil ice selected to ON and flaps at 40, simultaneous Wing and Tail de-icing occurs.

L/R ENG Anti-Ice Switch

OFF - Closes the seventh stage valve to the respective engine anti-ice cowl.

ON - Opens the seventh stage valve to provide air for engine anti-icing to the cowl only. Activates electrically heated fuselage strakes.

METER SEL & HEAT Selector

The MD-90 has a total air temperature (TAT) probe for air data inputs. It is located on the forward left side of the fuselage. Ground control relays inhibit energizing the TAT probe heater circuit while on the ground.

3.90.2

April 01, 2004

ICE FOD Switch

MD-88/90 Operations Manual

Anti-Ice, Rain -

MD-90 Differences

RESET

ICE FOD

TEST

OVERHEAD PANEL

JB1-3-0957

JB1-3-0957

ICE FOD Switch (Ground Operation Only)

RESET - (Momentary) Resets system following ice FOD detection. Removes

L/R ICE FOD ALERT messages, as applicable, from OAP.

System will not reset until ice no longer exists on sensors.

TEST - (Momentary) Tests ice FOD alert system. Displays (L/R) ICE FOD

ALERT and (L/R) ICE FOD SYS INOP alerts on the OAP during the test sequence.

April 01, 2004

3.90.3

Anti-Ice, Rain -

MD-90 Differences

MD-88/90 Operations Manual

Description and Operation

Pneumatics

High Stage Bleed Air

The MD-90 system includes a pneumatic system controller which is located in the avionics compartment. The controller monitors and controls pneumatic supply to the system through a high stage valve on each engine high stage compressor.

A precooler, located downstream of the junction of high and low stage bleed air ducts, maintains acceptable high and low stage bleed air temperatures as they enter the system.

Tail Compartment Overheats

A pneumatic overheat detection system (PODS) provides overheat detection for the tail compartment and engine pylons. If the PODS detects an overheat condition in the tail compartment or in the pylons, it will generate either the red L or R TAIL TEMP HIGH annunciation on the OAP. The MASTER WARNING lights will also illuminate. During a L/R TAIL TEMP HIGH condition, PODS will close the APU bleed air valve except during engine start.

The TAIL TEMP FAULT message indicates that the PODS cannot detect an overheat condition.

Ice and Rain Protection

Air Foil Anti-Icing

With air foil ice selected, moving the flaps to 40 will activate both wing and tail anti-ice valves simultaneously, and the WING ANTI-ICE ON and TAIL DE-ICE

ON lights will illuminate until the airplane is on the ground or flaps are repositioned to less than 40.

Engine Anti-Ice

Engine anti-ice is controlled by two switches on the overhead panel. Turning either switch on, activates respective engine anti-ice and ignition. Engine anti-ice is provided to the cowl only by seventh stage bleed air.

The rubber coated spinner tip is mounted slightly off-center to prevent ice build up. Both forward fuselage strakes, which are electrically heated, are activated at this time.

3.90.4

April 01, 2004

Anti-Ice, Rain -

MD-90 Differences

MD-88/90 Operations Manual

Ice FOD Alert System

An ice FOD alert system, active only on the ground, is designed to alert the pilots to the presence of wing upper surface ice caused by cold-soaked fuel. Overwing ice sensors, located near the inboard aft corner of each main wing tank, detect ice buildup in these areas. Four alert messages associated with this detection system may be displayed on the OAP. A ICE FOD RESET/TEST switch (spring-loaded to center) is located on the overhead panel to test and to reset this system.

The system and OAP message display may be tested by moving the switch out of the spring-loaded center position and holding it momentarily to the TEST position. Check for L/R ICE FOD ALERT and L/R ICE FOD SYS INOP messages. A successful test is indicated if all messages are displayed and then extinguish when the switch is released.

Any fault in the alert system activates the appropriate message(s), L/R ICE FOD

SYS INOP. The alert message(s) remain displayed.

L/R ICE FOD ALERT, when displayed, indicate the presence of ice build-up on the wing upper surface.

Following ice removal, the system must first be reset by moving the switch out of the spring-loaded center position and holding it momentarily to the RESET position. The alert messages extinguish until the sensors again detect the presence of ice. The system cannot be reset if ice continues to be detected.

April 01, 2004

3.90.5

Anti-Ice, Rain -

MD-90 Differences

MD-88/90 Operations Manual

OAP Messages/Lights

Amber Caution Messages

NOTE:

The associated cue light is shown in parenthesis (XXX) following the message.

ANTI-ICE FAULT or STRAKE ICE FAULT (ICE) - Anti-ice fault in left or right strake with no ice protection for one or both strakes when L and/or

R ENG anti-ice switch is selected ON.

L/R ICE FOD ALERT (ICE) - Ground advisory of ice buildup on wing upper surface.

L/R ENG VALVE (ICE) - The engine anti-ice valve position disagrees with

ENG anti-ice switch position.

L/R ICE FOD SYS INOP (ICE) - Ground advisory ice FOD alert system is inoperative.

WINDSHIELD OVERTEMP (ICE) - One or more windshield panes is overheated, resulting in the removal of anti-ice power from the overheated windshield(s). Requires ground maintenance to restore system.

Blue Advisory Lights

L/R ENG ANTI-ICE ON - Engine nose cowl and fuselage strakes anti-ice selected.

3.90.6

April 01, 2004

MD-88/90 Operations Manual

Functional Schematic

MD-90 Ice and Rain System

Anti-Ice, Rain -

MD-90 Differences

LEADING EDGE SLA

April 01, 2004 3.90.7

Anti-Ice, Rain -

MD-90 Differences

MD-88/90 Operations Manual

Intentionally

Blank

3.90.8

April 01, 2004

Automatic Flight

MD-88/90 Operations Manual

Chapter 4

Section 0

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10.1

Flight Guidance Control Panel (FGCP)

Autothrottle Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10.2

FGCP Navigation Arm and Roll Control Sections . . . . . . . . . . 4.10.4

FGCP Pitch Control Section . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10.6

Stability Augmentation and Autopilot. . . . . . . . . . . . . . . . . . . . 4.10.8

Flight Director (FD). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10.10

Altitude Alert . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10.11

Flight Mode Annunciator (FMA) . . . . . . . . . . . . . . . . . . . . . . 4.10.12

FMA Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.10.14

System Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.1

General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.1

Digital Flight Guidance Computer . . . . . . . . . . . . . . . . . . . . . . 4.20.1

Autothrottle Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.2

Arm Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.2

Roll Control Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.3

Pitch Control Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.3

Flight Mode Annunciator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.5

Autothrottle/Speed Control . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.11

Autothrottle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.11

Speed Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.14

Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.15

Flight Director . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.16

Stability Augmentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.17

Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.17

Mach Trim Compensation . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.17

Altitude Alert . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.18

Thrust Rating Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.20.18

August 11, 2008 4.TOC.0.1

Automatic Flight -

Table of Contents

MD-88/90 Operations Manual

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.30.1

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.30.1

Amber Caution Messages . . . . . . . . . . . . . . . . . . . . . . . . . . 4.30.1

Functional Schematic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.40.1

Automatic Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.40.1

MD-90 Differences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.90.1

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.90.1

Automatic Thrust Cut-back . . . . . . . . . . . . . . . . . . . . . . . . . 4.90.1

MACH Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4.90.1

Thrust Rating Panel (TRP). . . . . . . . . . . . . . . . . . . . . . . . . . 4.90.2

4.TOC.0.2

August 11, 2008

Automatic Flight

MD-88/90 Operations Manual

Controls and Indicators

Chapter 4

Section 10

Intentionally

Blank

April 01, 2004 4.10.1

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

Flight Guidance Control Panel (FGCP) - Autothrottle Section

FMS

OVRD

SPD

SEL

MACH

SEL

EPR

LIM

SPD MACH

NAV

AUTO

THROT

OFF

GLARESHIELD

ILS

NO AUTOLAND

THROTTLE

HORIZON

AP TRIM

INSTRUMENT

PANELS

FWD PEDESTAL

400

350

300

8 1

MAC

250

220

IAS

200

INSTRUMENT

PANELS

JB1-3-0898

Autothrottle SPD/MACH Readout

Indicates airspeed or Mach selected with SPD/MACH select knob.

JB1-3-0898

4.10.2 April 01, 2004

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

Autothrottle SPD/MACH Select Knob

Knob has three positions, spring returned to normal.

Normal - Selects SPD/MACH at a slow rate of 1 knot increments.

Pushed to Mid Detent - Selects SPD/MACH at a fast rate of 10 knot increments.

Pushed to Maximum Detent - Alternately switches SPD and MACH readout.

If other than SPD/MACH SEL mode is engaged, the SPD/MACH value will be stored in DFGC. Airspeed command bug on Mach/airspeed indicator is also set to airspeed appearing in readout.

AUTO THROT Switch

AUTO THROT - (Solenoid held) Engages autothrottle. Returns to OFF with a loss of electrical power, autothrottle disconnect button pressed, malfunction occurs, or when reverse thrust is selected.

Autothrottle Mode Select Buttons

SPD SEL - Push to select airspeed mode.

MACH SEL - Push to select Mach mode.

EPR LIM - Push to select EPR LIM mode.

FMS OVRD - Pushing button enables IAS selected by SPD/MACH knob to be used by FMS. Pushing button second time reverts to FMS computed

IAS.

THROTTLE Warning Light (red

)

Flashes when autothrottle is disengaged. Pushing autothrottle disconnect button on either throttle or re-selecting AUTO THROT switch to AUTO

THROT position extinguishes light.

Autothrottle Disconnect Button

Push - (Either Button) Disengages autothrottle. AUTO THROT switch automatically returns to OFF and THROTTLE warning light on FMA flashes. Pushing button second time extinguishes THROTTLE light.

Takeoff and Go-Around (TOGA) Button

Push - (Either Button) Initiates respective takeoff or go-around mode.

Airspeed Command Bug

Set with SPD/MACH select knob to airspeed set in SPD/MACH readout.

April 01, 2004 4.10.3

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

FGCP - Navigation Arm and Roll Control Sections

AUTO

THROT

OFF

NAV

VOR

LOC

ILS

AUTO

LAND

HDG

AND

ANU

GLARESHIELD

JB1-3-0899

HDG Readout

Digital readout of heading display, changed with HDG select knob.

HDG Select Knob

Knob has four position, spring-loaded to normal.

Normal - Provides fine heading adjustment.

Pushed to First Detent - Provides fast heading adjustment.

Pushed to Full Detent - Engages heading hold mode.

Pull - Engages heading select mode.

Bank Angle Select Knob

Sleeve provides selection of bank limits for HDG HLD, HDG SEL and

VOR.

Roll Mode Select Buttons

NAV - Pushing arms DFGS to capture and track an FMS generated course if the airplane is on intercept heading.

VOR LOC - Pushing arms DFGS to capture and track a selected VOR or

LOC course if the airplane is on intercept heading.

ILS - Pushing arms DFGS to capture and track a selected localizer course and glideslope capture and track, if the airplane is on intercept heading.

AUTO LAND - Pushing arms DFGS to establish AUTO LAND mode after localizer and glide slope capture and track, if the airplane is on intercept heading. ILS mode does not need to be selected prior to selecting AUTO

LAND.

4.10.4 April 01, 2004

MD-88/90 Operations Manual

Automatic Flight -

Controls and Indicators

Intentionally

Blank

April 01, 2004 4.10.5

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

FGCP - Pitch Control Section

HDG

AND

ANU

VERT

SPD

IAS

MACH

ALT

HOLD

AP ON

VNAV

1 2

ALT

OFF

TURB

GLARESHIELD

JB1-3-0900

JB1-3-0900

Pitch Profile Readout

First Window - Displays selected operating mode: V (vertical speed), M

(Mach), S (indicated airspeed), or P (turbulence, pitch).

Second Window - Displays pitch reference: + (climb/nose up) or -

(descend/nose down).

Remaining Windows - Display appropriate numerical values.

Pitch Mode Select Button

ALT HOLD - Pushing selects existing altitude for DFGS altitude hold mode.

VERT SPD - Pushing selects DFGS vertical speed mode.

IAS MACH - Pushing selects existing Indicated Airspeed (below 27,000 feet) or Mach (above 27,000 feet and above .5 Mach) for DFGS pitch mode. Mach is not available at any altitude if airspeed is below .5 Mach.

VNAV - Pushing selects FMS vertical guidance function if autothrottle is already engaged. Pitch commands are provided to FD and AP, while thrust commands are provided to the autothrottle.

ALT Preselect Readout

Digital readout of preselect altitude set with ALT set knob.

Symbology: =9000 (Below 10000); ==500 (Below 1000)

4.10.6 April 01, 2004

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

TURB Mode Select Button

Pushing commands DFGS to maintain existing pitch and wings level attitude for turbulence penetration. Also disengages autothrottle and altitude arm function.

ALT Set Knob

Knob has three positions, spring loaded to center.

Center - Provides 1000-foot increment altitude adjustments above 1000 feet or 100-foot increments below 1000 feet.

Pushing provides 100-foot increment altitude adjustments and resets altitude warnings.

Selecting a new altitude or pulling arms DFGS for preselected altitude capture.

Pitch Wheel

In IAS/MACH, VERT SPD or TURB modes, movement of pitch wheel adjusts values. In ALT CAP, ALT HLD or VNAV modes, movement of pitch wheel will change existing mode to VERT SPD mode.

FGCP Light Intensity Knobs

Left Knob - Controls light intensity for mode buttons and panel back lighting.

Right Knob - Controls light intensity for digital readouts. Readout intensity is overridden by thunderstorm light switch on overhead panel.

February 28, 2005 4.10.7

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

Stability Augmentation and Autopilot

OFF

ON

OVRD

YAW

DAMP

NORM

MACH

TRIM

COMP

FWD OVERHEAD PANEL

FLIGHT MODE ANNUNCIATOR

INSTRUMENT PANELS

T O

E L

4.10.8

CONTROL WHEEL

VERT

SPD

IAS

MACH

ALT

HOLD

AP ON

VNAV

ALT

OFF

TURB

GLARESHIELD

JB1-3-0901

JB1-3-0901

April 01, 2004

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

YAW DAMP Switch

OFF - Yaw damper operation is disabled if AP is disengaged. If AP is engaged, yaw damper operation is automatically provided.

ON - Yaw damper operation is provided with AP engaged or disengaged.

OVRD - Inhibits yaw damper operation with AP engaged or disengaged.

MACH TRIM COMP Switch

OVRD - System is deactivated.

NORM - Mach trim compensation mode is in operation.

AP Warning Light (red)

Flashes when AP is disengaged, accompanied by aural and vocal warnings.

AUTOPILOT REL Button

First push of the AUTOPILOT REL button disengages the autopilot.

Second push of the AUTOPILOT REL button on either control wheel resets light and applicable aural/vocal warning.

AP ON Switch

(Solenoid held) Engages autopilot (AP). Automatically disengages with a loss of electrical power, malfunction and disengages with AUTOPILOT release button.

AP ON 1/2 Selector Switch

Allows selection of AP 1 or AP 2.

April 01, 2004 4.10.9

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

Flight Director (FD)

1

BOTH

ON 1

CADC

NORM

BOTH

ON 1

BOTH

ON 2

FD CMD

NORM

BOTH

ON 2

BOTH

ON 1

EFIS

NORM

BOTH

ON 2

2

CADC

INSTRUMENT PANELS

3

OFF

TURB

VHF

NAV

GLARESHIELD

JB1-3-0902

JB1-3-0902

FD CMD Selector

NORM - Normal position. Digital Flight Guidance Computer (DFGC) -1 and -2 provide data to respective FD.

BOTH ON 1 - DFGC-1 provides data to both FDs.

BOTH ON 2 - DFGC-2 provides data to both FDs.

FD Light (amber)

Indicates FD CMD selector is out of NORM position.

FD Switch (2)

FD - Turns on respective Captain’s or F/O’s flight director and FMA.

OFF - Turns off respective Captain’s or F/O’s flight director. The FMA will operate if autothrottles or autopilot are engaged.

4.10.10 April 01, 2004

Altitude Alert

MD-88/90 Operations Manual

Automatic Flight -

Controls and Indicators

9

0

1

8

2

7 ALT

IN HG

1 0 1 3 2 9 9 2

6

5

4

3

INSTRUMENT PANELS

JB1-3-0903

JB1-3-0903

Altitude Alert Light (amber)

Illuminates when aircraft is within 750 feet of selected altitude.

In addition, the aural warning sounds.

Flashes when a deviation of 250 feet or more occurs from the selected altitude.

In addition to the aural warning, vocal warning “altitude” also sounds.

Warnings can be reset by returning to selected altitude or by setting a new altitude.

April 01, 2004 4.10.11

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

Flight Mode Annunciator (FMA)

ILS

NO AUTOLAND

THROTTLE

HORIZON

AP TRIM

HEADING

MONITOR

SET

INSTRUMENT PANELS

FMA Thrust Window (green)

Displays existing autothrottle mode.

FMA Arm Window (amber)

Displays armed mode for roll or pitch.

FMA Roll Window (green)

Displays existing roll mode.

FMA Pitch Window (green)

Displays existing pitch mode.

JB1-3-0906

4.10.12 April 01, 2004

MD-88/90 Operations Manual

Automatic Flight -

Controls and Indicators

Intentionally

Blank

April 01, 2004 4.10.13

Automatic Flight -

Controls and Indicators

FMA Lights

MD-88/90 Operations Manual

ILS

NO AUTOLAND

THROTTLE

HORIZON

AP TRIM

HEADING

MONITOR

SET

INSTRUMENT PANELS

JB1-3-0906

ILS (amber)

Lights illuminate on both FMAs to indicate a deviation between LOC/GS

-1 and -2 signals. When a failure is detected (flag in view), light on side that has failed will flash and light on opposite side will illuminate.

HORIZON (amber)

Lights illuminate on both FMAs to indicate a difference in pitch and roll attitude between Captain’s and F/O’s PFDs. When a failure is detected (flag in view), light on side that has failed will flash and light on opposite side will illuminate.

HEADING (amber)

Lights illuminate on both FMAs to indicate a difference between heading information. When a failure is detected (flag in view), light on side that has failed will flash and light on opposite side will illuminate.

RESET Button

Push - Resets ILS, HORIZON, HEADING, MONITOR, and NO

AUTOLAND lights, which can be recalled by pushing the button a second time.

FD (blue)

Indicates associated flight director is engaged.

AP1/AP2 (blue)

Indicates respective DFGC selected and engaged.

4.10.14 April 01, 2004

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

MONITOR (amber)

Lights illuminate on both FMAs to indicate a failure of comparator monitor. ILS, HORIZON, and HEADING lights are not reliable.

AP TRIM (amber)

Indicates a sustained out-of-trim horizontal stabilizer condition of autopilot. Light cannot be reset and will remain illuminated until condition is corrected or autopilot is disengaged.

NO AUTOLAND (amber)

Indicates autoland is not available.

April 01, 2004 4.10.15

Automatic Flight -

Controls and Indicators

MD-88/90 Operations Manual

Intentionally

Blank

4.10.16 April 01, 2004

MD-88/90 Operations Manual

Automatic Flight

System Description

Chapter 4

Section 20

General

Automatic flight is provided by the digital flight guidance system (DFGS). The system consists of two digital flight guidance computers (DFGC) to provide the following functions:

• Autothrottle/speed control

• Autopilot (AP)

• Flight director (FD)

• Stability augmentation (yaw damping, mach trim)

• Altitude alert

• Engine thrust rating selection (TRP)

• Engine synchronization

• Autothrottle Advance

• Windshear alert and guidance

Flight guidance information is displayed on the EFIS primary flight display

(PFD), navigation display (ND) and flight mode annunciator (FMA). The flight management system (FMS) can be coupled to the AP, FD and autothrottle to provide guidance and commands for roll, pitch, and thrust controls. Refer to

Engines chapter for description of engine synchronization and Autothrottle

Advance system.

Digital Flight Guidance Computer

Two DFGC's are provided, one of which functions while the other is in standby.

DFGC 1 or 2 is selected by placing the DFGC switch to the respective position.

The DFGC receives inputs from the central air data computers (CADC),VHF navigation systems (VOR/LOC), inertial reference systems (IRS), FMS, radio altimeters and airplane systems sensors.

A flight guidance control panel (FGCP), located on the glareshield, contains controls and indicators for automatic flight. The panel is divided into four different control sections: autothrottle, arm, roll, and pitch control. In addition, the

NAV, VNAV and FMS OVRD buttons are provided to couple the FMS to control lateral and vertical navigation, and allow for temporary pilot selected speeds

(FMS OVRD) without disengaging VNAV.

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4.20.1

Automatic Flight -

System Description

MD-88/90 Operations Manual

Autothrottle Section

The autothrottle section contains SPD/MACH select knob and window, SPD SEL,

MACH SEL, EPR LIM and FMS OVRD buttons, and AUTO THROT switch.

A three-position SPD/MACH select knob allows setting of the SPD/MACH readout, and positioning the command bug on the airspeed indicators. In the normal position, one knot adjustments are accomplished. In the first detent, fast slewing of the selected readout occurs. Pushing the knob to second detent alternately switches the speed or Mach readout which has no effect on the engaged mode of the autothrottle. If other than SPD/MACH SEL mode is engaged, the

SPD/MACH value will be stored in DFGC. Airspeed command bug on

Mach/airspeed indicator is also set to airspeed appearing in readout.

Airspeed control mode of the autothrottle is engaged by momentarily pushing the

SPD SEL button in flight. The FMA thrust window displays SPD and the airspeed selected in the SPD/MACH readout.

Mach control mode of the autothrottle is engaged by momentarily pushing the

MACH SEL button in flight. The FMA thrust window displays MACH and the

Mach number selected in the SPD/MACH readout.

EPR limit mode is engaged by momentarily pushing the EPR LIM button in flight.

Thrust is set to the limit computed by the thrust rating system. The FMA thrust window displays EPR and applicable thrust rating selected on the thrust rating panel (TRP). If a takeoff flex mode is selected, EPR and assumed temperature annunciation is displayed.

A two-position, spring-loaded and solenoid held, AUTO THROT switch allows engagement and disengagement of the autothrottle.

Arm Section

The arm section contains VOR/LOC, ILS and AUTO LAND buttons for selection of the various modes.

VOR/LOC mode is armed to capture and track a VOR or localizer course by momentarily pushing the VOR/LOC button.

ILS mode is armed to capture and track a selected localizer course and glide slope by momentarily pushing the ILS button.

Automatic landing mode is armed to capture and track an ILS for an automatic landing by momentarily pushing the AUTO LAND button.

NAV mode is armed to capture and track the FMS course by momentarily pushing the NAV button.

4.20.2

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

Roll Control Section

Roll control section contains HDG select knob and HDG window for lateral control.

The HDG select knob consists of a knob and sleeve. The knob (spring-loaded to normal) has four positions. Normal position provides fine tuning of heading.

When the knob is pushed to the first detent, fast rate of heading select is provided.

When the knob is fully pushed in, the heading hold mode is engaged. With this mode engaged, the AP/FD either maintains the existing heading or, if the bank angle is more than 3 degrees, rolls the airplane wings level and maintains that heading. Pulling the knob engages the heading select mode which acquires and maintains the heading selected in the HDG window. The sleeve, with five detents from 10 to 30 degrees, limits bank angle during HDG SEL, HDG HOLD and VOR modes. Bank angle limiting is inhibited during LOC CAP and FMS NAV modes.

At VOR or LOC CAP, the FD displays roll commands and the AP (if engaged) will maneuver to capture and track the selected course if the airplane is on an intercept heading. The FMA displays an amber VOR or LOC annunciation when armed, VOR or LOC CAP at course capture, VOR or LOC TRK when tracking course, and VOR CRS during station passage.

At ILS capture, the FD displays roll and pitch commands and the AP (if engaged) will maneuver to capture and track the localizer and glide slope. The FMA displays ILS annunciation when armed, LOC CAP at localizer capture, LOC TRK when tracking localizer, GS CAP at glide slope capture and GS TRK when tracking glide slope.

During Auto Land at 1500 feet radio altitude, the FMA displays AUT LND annunciation and all other AP control modes, except go-around, are inhibited. The

AP automatically executes a runway alignment maneuver at 150 feet radio altitude.

At main gear touchdown, automatic nose lowering takes place and the rudder will keep the airplane on localizer beam center. The AP will disengage automatically

5 seconds after nosewheel touchdown.

Pitch Control Section

The pitch control section contains a pitch profile window and pitch wheel, VERT

SPD, IAS/MACH, TURB, and ALT HOLD mode buttons. This section also contains the ALT window and set knob.

Control of the pitch profile is provided by the pitch wheel and the pitch profile window. On the first window, a constant vertical rate is indicated by a "V" symbol and the desired rate of change. Using pitch to control speed is indicated by an "S" or "M" symbol and the desired airspeed or Mach respectively.

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4.20.3

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System Description

MD-88/90 Operations Manual

The vertical speed mode is engaged by pushing the VERT SPD button, or if ALT

HLD or VNAV was engaged, by selecting a vertical speed with the pitch wheel.

The window displays "V" symbol followed by a "+" or "-" symbol for climb or descent respectively and the vertical speed readout. Vertical speed is changed by rotating the pitch wheel.

Vertical speed rate adjustments, after altitude capture, will disengage the altitude capture mode, and will revert to the vertical speed mode.

The PFD displays FD pitch commands and the AP (if engaged) will adjust pitch attitude to obtain the commanded vertical speed.

Indicated airspeed or Mach mode is engaged by pushing the IAS MACH button.

When the airplane altitude is below 27,000 feet, the pitch window displays an "S" symbol followed by existing airspeed which can be changed by rotating the pitch wheel. If the airplane altitude is above 27,000 feet, when IAS MACH button is pressed, the Mach mode is engaged. The PFD displays FD commands to maintain selected Mach or indicated airspeed and the AP (if engaged) will adjust pitch attitude to maintain selected speed. MACH or IAS annunciation is displayed on the FMA.

Altitude hold mode can be engaged by pushing the ALT HOLD button or selecting zero vertical speed in the pitch window. The PFD displays FD pitch commands and the AP (if engaged) will return to the altitude where the button was pushed.

ALT HLD annunciation is displayed on the FMA.

A preselected altitude can be set by the ALT set knob and displayed in the ALT window. The knob has three positions and spring-loaded to center.

The center position provides 1000 foot increments if greater than 1000 foot is selected, and 100 foot increment altitude adjustment if below 1000 foot selected.

Pushing and rotating provides 100 foot increment if the altitude selected is above

1000 feet. If the knob has been previously pushed in to select "100's" and is released to the center position, the next "click" is a 100 foot increment if done immediately. Thereafter, it reverts to 1000 foot increments.

The selected altitude is armed automatically after setting.

Pulling the knob also arms the selected altitude for capture.

Turbulence mode is engaged by momentarily pushing the TURB button which disengages the autothrottle and altitude hold mode and rolls the airplane wings-level. The THROTTLE warning light flashes and the pitch profile window displays "P" followed by a "+" or "-" symbol and the pitch attitude. The pitch attitude can be changed by rotating the pitch wheel. The PFD displays FD commands and the AP (if engaged) will maneuver to maintain the displayed pitch attitude. The FMA displays WNG LVL and TURB annunciations.

During autoland at 50 feet, the FMA will annunciate “FLAR” and the autopilot will flare the airplane until touchdown.

4.20.4

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

Flight Mode Annunciator

Two FMA's, each located at the top of the instrument panel, provide the following information:

• Flight instrument comparisons and failure indications (ILS, HORIZON and HEADING lights).

• AP/Autothrottle disengaged warning (AP, THROTTLE warning lights).

• AP out-of-trim indication (AP TRIM light).

• No autoland indication (NO AUTOLAND light).

• Throttle, arm, roll and pitch mode annunciations.

Throttle, Arm, Roll and Pitch (TARP) mode annunciations are displayed on the

FMA in four separate windows, corresponding to four applicable FGCP control sections, for autothrottle/thrust, arm, roll and pitch (TARP) functions.

An ANNUN/DIGITAL LTS TEST button on the overhead panel tests the annunciations and lights on both FMA's. When the button is pushed, all the lights on the FMA's illuminate and annunciations are displayed in the form of "starburst" symbols.

When the button is released, the lights and "starburst" symbols remain displayed for five seconds, except the THROTTLE and AP warning lights extinguish immediately. Refer to Airplane General chapter for complete description of the

ANNUN/DIGITAL LTS TEST button.

Autothrottle Mode Annunciations (Green)

ATS OFF. VNAV mode selected, autothrottle off. Light flashes as reminder to engage autothrottle.

CLMP

FMS.

Throttles clamped with FMS engaged in CRZ DES.

FMS

EPR.

FMS

SPD.

(FMS VNAV mode engaged.) Throttles being controlled by

FMS to maintain EPR.

(FMS VNAV mode engaged.) Throttles being controlled by

FMS to maintain speed.

FMS

IDLE.

AUTO

LND.

CLMP.

RETD.

(FMS VNAV mode engaged.) Throttles being controlled by

FMS for idle setting.

Autoland preflight ground test is in progress. Appears for approximately 20 seconds.

ATS in clamp mode. Power is removed from ATS servo

(throttles remain stationary).

ATS in retard mode. Throttles automatically retarded at 50 feet.

August 11, 2008 4.20.5

Automatic Flight -

System Description

MD-88/90 Operations Manual

ALFA

SPD.

MACH

784.

SPD 250.

FLAP

LIM.

Autothrottle Mode Annunciations (Green)

ATS in ALFA speed mode. Throttles controlled to maintain a safe margin above stall speed.

ATS in Mach select mode. Throttles controlled to maintain

.784 Mach as selected in SPD MACH readout.

ATS in speed select mode. Throttles controlled to maintain 250

KIAS as selected in SPD MACH readout.

ATS controlling throttles to prevent exceeding flap limit airspeed. Occurs automatically when a reference airspeed greater than flap design limit airspeed is selected.

SLAT

LIM.

VMO

LIM.

MMO

LIM.

SPD ATL/

MACH

ATL.

LOW

LIM.

EPR T/O.

ATS controlling throttles to prevent exceeding slat limit airspeed. Occurs automatically when a reference airspeed greater than slat design limit airspeed is selected.

Indicates that ATS is automatically limited to not exceed maximum operating airspeed (VMO).

Indicates that ATS is automatically limited to not exceed maximum operating Mach number (MMO).

ATS limit when operating in SPD SEL or MACH SEL mode, as applicable. Automatically occurs when ATS throttle command would exceed EPR limit.

Occurs automatically when ATS throttle command would require a throttle setting lower than the minimum authority limit.

ATS in EPR LIM mode with T/O thrust selected. Throttles controlled to maintain EPR limit takeoff thrust.

EPR 50.

EPR G/A. ATS in go-around mode with G/A thrust selected. Throttles controlled to maintain EPR G/A thrust limit.

EPR

MCT.

EPR CL.

ATS in EPR LIM mode with MCT thrust selected. Throttles controlled to maintain maximum continuous thrust.

ATS in EPR LIM mode with CL thrust selected. Throttles controlled to maintain climb thrust.

PWR.

ATS in EPR LIM mode with 50° selected on ASSUMED

TEMP Selector (assumed temperature selected will be displayed) and TO FLX thrust selected. Throttles controlled to maintain derated takeoff thrust.

WND

SHR.

Automatic power-up test in progress. (Occurs approximately 2 minutes after landing).

ATS is engaged and windshear is detected, a speed bias is being added by the windshear computer.

4.20.6

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

PRE.

LND.

ILS.

LOC.

VOR.

ATL.

LND

ATL.

ILS ATL.

LOC

ALT.

Arm Mode Annunciations (Amber)

Autoland preflight ground test in progress. Appears approximately 20 seconds.

Automatic landing mode armed for automatic capture of selected ILS for automatic landing.

ILS mode armed for automatic capture of localizer and glideslope of selected ILS.

LOC mode armed for automatic capture of selected localizer course.

VOR mode armed for automatic capture of selected VOR course.

Altitude preselect armed for automatic capture of selected altitude.

Automatic landing mode armed for automatic capture of selected ILS and altitude preselect armed for automatic capture of selected altitude.

ILS mode armed for automatic capture of selected ILS and altitude preselect armed for automatic capture of selected altitude.

LOC mode armed for automatic capture of selected localizer course and altitude preselect armed for automatic capture of selected altitude.

VOR

ALT.

VOR mode armed for automatic capture of selected VOR course and altitude preselect armed for automatic capture of selected altitude.

AUT G/A. Flight guidance system armed for full automatic go-around capability.

FD G/A. Flight guidance system armed for Flight Director command capability for manual go-around.

Flight guidance system not armed for go-around capability. MAN

G/A.

UP.

NAV.

Automatic power-test in progress (Occurs approximately 2 minutes after landing).

FMS LNAV mode is armed.

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4.20.7

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System Description

MD-88/90 Operations Manual

FLT.

VOR

CRS.

LOC

CAP.

LOC

TRK.

NAV

CAP.

HDG

HLD.

HDG

SEL.

VOR

CAP.

VOR

TRK.

NAV

HLD.

NAV

TRK.

TAK

OFF.

Roll Mode Annunciations (Green)

Autoland preflight ground test in progress. Appears for approximately 20 seconds.

Heading hold (roll basic mode) engaged and existing magnetic heading maintained.

Heading select mode engaged and heading selected in HDG readout maintained.

Capture of selected VOR course has occurred.

Airplane tracking selected VOR course.

Station passage is occurring. Airplane will maintain existing heading during station passage.

LOC, ILS, or LAND mode engaged and capture of localizer course has occurred.

LOC, ILS, or LAND mode engaged and airplane is tracking localizer course.

Nav engaged and capturing a new lateral course, or if bank angles greater than 10° are required.

NAV engaged and FMS is in an internal heading hold mode, e.g., in discontinuity and airplane on intercept track.

Nav engaged, tracking desired course.

Flight Director takeoff mode engaged. After lift-off, roll command bar on PFD will command wings level to maintain heading.

WNG

LVL.

Turbulence mode engaged. Roll command bar on PFD will command wings level.

GO RND. Go-around mode engaged. Existing magnetic heading maintained and roll command bar on PFD commands wings level.

AUT

LND.

LAND mode engaged. Logic for mode is satisfied to perform automatic landing.

4.20.8

August 11, 2008

ALN.

ROL

OUT.

TST.

Automatic Flight -

System Description

MD-88/90 Operations Manual

Roll Mode Annunciations (Green)

Align mode engaged. Airplane maneuvered to maintain runway alignment.

Main gear wheel spin-up has occurred. FD provides steering commands to maintain runway alignment. AP maintains runway alignment with nosewheel steering.

Automatic power-up test in progress. (Occurs approximately 2 minutes after landing.).

TEST.

VNAV

CLB.

VNAV

LVL.

VNAV

DES.

VNAV

CAP.

VERT

SPD.

Pitch Mode Annunciations (Green)

Autoland preflight ground test in progress. Appears for approximately 20 seconds.

(VNAV mode engaged.) Climb pitch attitude as determined by

FMS.

(VNAV mode engaged.) Altitude maintained by pitch attitude as determined by FMS.

(VNAV mode engaged.) Descent altitude maintained by pitch attitude as determined by FMS.

FMS is coupled with DFGC and is in the VNAV path capture mode.

Vertical speed (a pitch basic mode) engaged. Airplane vertical speed maintained by pitch attitude.

ATL CAP. Altitude preselect mode engaged and altitude capture has occurred.

ATL

HLD.

DFGS is providing Flight Director/Autopilot with guidance commands to maintain the steady state barometric altitude at which altitude hold mode was engaged. (A pitch basic mode).

IAS.

MACH.

IAS hold mode engaged and indicated airspeed maintained by pitch attitude.

MACH hold mode engaged and Mach number maintained by pitch attitude.

TURB.

TAK

OFF.

G/S CAP.

Turbulence mode engaged. Pitch attitude controlled by use of pitch wheel.

Flight Director takeoff mode engaged. After lift off, pitch command bar on PFD will display pitch commands to maintain

V2 or V2 + 10 KIAS.

ILS or LAND mode engaged and glideslope capture has occurred.

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Automatic Flight -

System Description

MD-88/90 Operations Manual

Pitch Mode Annunciations (Green)

G/S TRK. ILS or LAND mode engaged and airplane is tracking glideslope.

GO RND. Go-around mode engaged. Airplane controlled to maintain a safe margin above stall airspeed while establishing a climb attitude. Pitch command bar on PFD will display commands to maintain a safe margin above stall airspeed.

AUT

LND.

FLAR.

LAND mode engaged. Logic for mode is satisfied to perform automatic landing.

LAND mode engaged and flare mode initiated.

NO FLR.

ROL

OUT.

SPD

LOW.

BOX

1 (2).

WND

SHR.

ILS mode engaged and autopilot remains engaged at radio altitude of 100 feet. This is a flashing annunciation.

Main gear wheel spin-up has occurred. Annunciation remains until autopilot is disengaged.

The engaged pitch mode is commanding a pitch attitude that results in an airspeed below the ALFA reference speed. SPD

LOW annunciation will flash alternately with engaged pitch mode annunciation when airspeed decreases to 10 percent below the ALFA reference speed.

Automatic power-up test in progress (Occurs approximately 2 minutes after landing.).

Windshear pitch mode is engaged.

4.20.10

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

Autothrottle/Speed Control

The autothrottle/speed control function provides a full flight regime automatic throttle that can control airspeed, Mach number and engine thrust from takeoff to landing.

Appropriate annunciations including numerical values (when applicable) appear on the FMA to indicate existing operating mode of autothrottle/speed control.

Autothrottle

Autothrottle function is engaged by moving the AUTO THROT switch from OFF to AUTO THROT position. The switch will not remain in the AUTO THROT (on) position unless all interlocks and engage requirements are satisfied. The switch will automatically revert to OFF when electrical power is lost, a malfunction is detected or the autothrottle disconnect button on either throttle is pushed. The red

THROTTLE warning light on the FMA flashes when the above occurs or when the AUTO THROT switch is manually moved to OFF. Pushing either autothrottle disconnect button or manually turning the AUTO THROT switch on extinguishes the THROTTLE light. If autothrottle ON, the autothrottles will disconnect when reverse thrust is selected. The red throttle warning light will not illuminate with the use of reverse thrust.

Three primary autothrottle operational modes may be selected on the FGCP: speed select (SPD SEL); Mach select (MACH SEL) and EPR limit (EPR LIM).

The thrust rating panel (TRP) is used to select a thrust EPR for EPR LIM mode.

Secondary modes that occur automatically are: SPD ATL, MACH ATL, LOW

LIM, FLAP LIM, SLAT LIM, VMO LIM, MMO LIM, ALFA SPD, RETD, and

CLMP.

Thrust EPR that may be selected include takeoff (TO), takeoff flex (TO XX), go-around (GA), maximum continuous thrust (MCT), climb (CL) and cruise

(CR).

Airspeed/Mach Select (SPD/MACH SEL) Mode

The SPD SEL or MACH SEL mode can be engaged during any phase of flight except when TO, GA or TO FLX is selected on the TRP or retard mode is engaged.

With autothrottle in SPD SEL or MACH SEL mode, the autothrottle seeks and maintains reference speed/Mach selected in the SPD/MACH window except when the Alpha speed reference is a higher value. If the autothrottle is engaged in

SPD SEL or MACH SEL mode after the autopilot/flight director was engaged in either IAS or MACH mode, the autopilot/flight director will revert to the vertical speed mode at the existing vertical speed and the VERT SPD annunciation will flash for approximately 5 seconds on the FMA.

August 11, 2008

4.20.11

Automatic Flight -

System Description

MD-88/90 Operations Manual

EPR Limit (EPR LIM) Mode

Autothrottle EPR LIM mode is initiated by pressing the EPR LIM button if the autothrottle is already engaged; or by selecting TO, GA or TO FLX on the TRP, pushing the TO/GA button on either throttle, and engaging the autothrottle. The airplane must be on the ground more than 20 seconds to initiate takeoff mode.

Pushing either TO/GA button selects the TAK OFF mode of the flight director.

Go-around mode is also initiated by pushing either TO/GA button as for takeoff mode except airplane must be airborne or on the ground for less than 20 seconds.

Upper and lower authority limits are provided for throttle control. The autothrottle function provides upper authority limits by means of EPR limit control modes.

Lower limit authority is a function of the DFGC retarding the throttles to just above idle (when FMS mode is engaged, the throttles retard to idle stop). The upper limit protects against exceeding EPR limits. The lower limit prevents the throttles from being driven to the idle stops.

The autothrottle automatically reverts from EPR limit to airspeed or Mach control mode when preselected altitude capture occurs. The throttles are controlled to acquire and maintain the value preset in the SPD/MACH readout. Automatic reversion occurs at altitude capture and the pilot follows FD commands (autopilot disconnected). The transition is fully automatic when the autopilot is engaged.

Clamp (CLMP) Mode

The CLMP mode is engaged (power removed from throttle servo motor and

CLMP annunciation displayed on the FMA) when the following conditions exist:

• The airplane is on the ground for more than 20 seconds with autothrottle in EPR mode and airspeed is greater than 60 KIAS.

• In flight, the autothrottle is in SPD SEL or MACH SEL mode and IAS or

MACH mode is selected.

Alpha Speed (ALFA SPD) Mode

ALFA SPD mode is engaged automatically when the autothrottle is in SPD SEL or MACH SEL mode and the selected SPD/MACH value is less than the safe minimum airspeed for the existing slat/flap configuration. The FMA displays

ALFA SPD and the throttles are controlled to seek and maintain the Alpha speed reference indicated by the Fast/Slow display on the PFD.

Retard (RETD) Mode

The RETD mode is engaged as a function of radio altitude and landing flap configuration (autopilot/flight director may or may not be engaged). The FMA displays RETD and the throttles are retarded towards idle.

4.20.12

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

Autothrottle Limit Mode (SPD/MACH ATL)

The SPD ATL or MACH ATL mode is displayed when the autothrottle is engaged and a speed control input would cause a throttle command that would exceed the thrust rating EPR limit. The autothrottles will not exceed EPR limit and the FMA displays SPD ATL or MACH ATL. When the throttle command returns to the normal operating thrust range, the autothrottle will revert to the previously engaged mode.

Flap/Slat Limit Mode (FLAP/SLAT LIM)

The FLAP LIM or SLAT LIM mode is engaged when the autothrottle is in SPD

SEL or MACH SEL mode and the selected SPD/MACH value exceeds the design limit airspeed for the existing flap/slat configuration. The FMA displays FLAP

LIM or SLAT LIM. The autothrottle will seek and maintain the flap/slat design limit and the Fast/Slow display on the PFD will be centered when the design limit is achieved. When the selected SPD/MACH value is reduced below the flap/slat design limit, or the flap/slat configuration is changed, the FMA annunciation will revert to the engaged SPD/MACH mode.

Low Limit Mode (LOW LIM)

The LOW LIM mode is engaged when the autothrottle commands a throttle setting lower than the minimum authority limit. The FMA displays LOW LIM, and the throttles retard to just above idle. When the throttles are commanded to advance from the minimum authority stops, the FMA annunciation will revert to the original operating mode.

Speed Limit Mode (VMO/MMO LIM)

The VMO LIM or MMO LIM mode is engaged when the autothrottle is in SPD

SEL or MACH SEL mode and the indicated airspeed approaches the maximum operating limit. The throttles will be controlled to maintain airspeed below

VMO/MMO limit. The VMO LIM or MMO LIM annunciation is displayed on the

FMA. The annunciation will revert to the original mode when the indicated airspeed drops below the speed limit.

August 11, 2008

4.20.13

Automatic Flight -

System Description

MD-88/90 Operations Manual

Speed Control

Speed control inputs for attitude control are displayed by the command bar and fast/slow (F/S) display on the PFD during flight director takeoff and go-around modes. Full scale deflection is + /- 10 knots.

During takeoff, the command bar on the PFD commands a pitch attitude to maintain V2+10 KIAS for two-engine operation. In the event of an engine failure, pitch commands for one engine operation will be as follows: If the airspeed is at or below V2 KIAS at the time of engine failure, the command bar will command a pitch attitude to maintain V2 KIAS. If the airspeed is between V2 and V2+10

KIAS at the time of engine failure, the command bar will command a pitch attitude to maintain existing airspeed. If the airspeed is V2+10 KIAS or greater, the command bar will command a pitch attitude to maintain V2+10 KIAS.

During go-around mode, the command bar commands a pitch attitude to maintain

DFGC computed go-around speed (airspeed at TOGA switch activation, but not less than 1.3 VS + 5 KIAS or greater than 1.3 VS + 25 KIAS of the landing flap configuration).

The Fast/Slow (F/S) display indicates the deviation between actual and selected

Mach or indicated airspeed for the range of selected airspeeds between maximum limit and minimum safe (Alpha speed) airspeed for the existing flap/slat configuration. If the selected speed lies outside of this range, the F/S displays the deviation between actual and maximum limit or minimum safe airspeed as applicable. There are some exceptions, as follows:

• Takeoff/Go-Around Mode (TO/GA): During takeoff or go-around

(TO/GA selected), the F/S display indicated the speed deviation relative to the computed takeoff or go-around reference speeds.

• Retard Mode (RETD): In the RETD mode, the F/S display is removed.

• Flight Management System (FMS): With VNAV mode selected, the F/S display is referenced to the FMS target speed.

• Gust Integration (Autothrottles Engaged): During approach in turbulent conditions, with flaps set at 26 degrees or more, an automatic increase in reference speed, up to a maximum of 5 knots, is added to compensate for wind gusts. The F/S display reflects this change in the reference speed.

• Windshear Encounter: During a detected windshear encounter, the F/S display indicates relative angle of attack (Alpha).

Any desired airspeed can be selected on the FGCP but speed control inputs are limited to prevent commands which exceed flap/slat and VMO/MMO limit speeds and to prevent commands lower than minimum maneuvering speed (safe stall margin speed). Speed control inputs for F/S display and the autothrottle command the pilot or autothrottle to adjust the throttles to maintain the higher reference speed of either the minimum maneuvering speed (Alpha speed) or the airspeed selected on the FGCP.

4.20.14

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

Autopilot

The AP function, operating in conjunction with the yaw damper, automatically controls the airplane in pitch, roll, and yaw maneuvering axes. Appropriate control surfaces are actuated by the AP to fly a computed flight path automatically.

The AP includes functions to maintain an existing altitude; descend or climb to and maintain a preselected altitude; maintain a selected vertical speed, indicated airspeed, or Mach number; fly a FMS optimized profile; maintain an existing heading; fly to and maintain a preselected heading; fly to, capture, and track a selected VOR or localizer course; capture and track a glide slope; maintain runway alignment, flare and momentarily maintain rollout for automatic landing.

Appropriate annunciations appear on both FMA's to indicate existing AP operating modes.

The AP is engaged by placing the AP switch on the FGCP in AP ON position. The switch is spring loaded to off and solenoid held in AP ON position.

The AP is disengaged and the red AP warning light on the FMA flashes in the following conditions:

• AP switch is off.

• AP malfunction is detected.

• DFGC switch is moved from selected position.

• AUTOPILOT REL button on either control wheel is pushed.

• Primary horizontal stabilizer trim is manually operated.

• Activation of the stick pusher.

In addition, the flashing AP light is accompanied by aural and vocal warnings in all AP disengagements. The loss of electrical power will also disengage the autopilot. The red AP warning light will not illuminate and vocal warnings will not sound with loss of electrical power.

Pushing the AUTOPILOT REL button a second time will cancel the AP warning.

An AP TRIM light on the FMA illuminates to indicate the horizontal stabilizer is out of trim.

August 11, 2008

4.20.15

Automatic Flight -

System Description

MD-88/90 Operations Manual

Flight Director

The FD function provides visual guidance commands on the PFD to fly the airplane manually or to visually monitor AP response to the guidance commands.

Captain's and First Officer's FD switches are provided on the FGCP. When a FD switch is in FD, pitch and roll commands are displayed on the respective PFD and pitch and roll annunciations are displayed on the respective FMA. If the AP is engaged, both FMA's display AP armed and operating modes and the blue AP 1 or AP 2 lights on each FMA respectively illuminates to indicate the controlling

AP.

A FD CMD selector, located on the overhead panel, selects either DFGC-1 or -2 for control of the guidance commands and the fast/slow (F/S) displays. When the selector is in NORM, guidance commands and F/S display are provided by the respective DFGC. When the selector is placed in either BOTH ON 1 or BOTH ON

2, guidance commands and F/S displays are provided by the selected DFGC.

With AP disengaged, FD basic mode (heading hold and vertical speed if vertical speed is zero, Altitude hold) is provided by placing either FD switch to FD position. Guidance commands are displayed on the PFD to roll wings level for heading hold and then to maintain existing heading and vertical speed. All modes except VOR/ILS modes are interfaced with the opposite DFGC. When the opposite-side FD switch is then turned on, the FD will engage the previously selected and engaged mode. When VOR/ILS mode is selected, both FD switches are in FD and the FD CMD selector is in NORM, guidance commands are displayed to acquire and track radio courses selected by the respective VHF NAV control panel. For ILS modes, both VHF NAV control panels should be set to the

ILS frequency and inbound ILS course. Armed and operating modes of each FD are displayed on the respective FMA and the blue FD light illuminates.

With AP engaged, the FD is primarily used to monitor all AP operating modes from climb-out to automatic landing. Both FMA's display appropriate AP armed and operating modes and the respective blue AP 1 or AP 2 light illuminates to indicate the controlling AP.

4.20.16

August 11, 2008

Automatic Flight -

System Description

MD-88/90 Operations Manual

Stability Augmentation

The DFGS provides two-axis stability augmentation which includes yaw damper and Mach trim compensation.

Yaw Damper

The yaw damper function derives yaw rate to provide damping of the Dutch roll characteristic. In addition, the function provides automatic turn coordination except during coupled approach localizer track mode. The function is activated automatically with the AP engagement or may be controlled separately with the

YAW DAMP switch located on the overhead panel. Yaw damper operation is a function of both the YAW DAMP and AP switches. With AP switch in ON, yaw damping is engaged with the YAW DAMP switch in either ON or OFF position.

With AP switch off, yaw damping is engaged only with the YAW DAMP switch in ON. The OVRD position of YAW DAMP switch disables yaw damper, regardless of AP status.

Yaw damp and turn coordination functions are normally handled by a series rudder actuator. This means that the actuator does not move the rudder pedals.

This actuator has limited authority (+/- 2 degrees). In some critical modes (T/O,

Approach and G/A) the autopilot is capable of handling the yaw caused by an engine failure. This additional authority is achieved by the autopilot using parallel rudder servo. This means that the autopilot drives the rudder pedals. The parallel rudder servo has full rudder authority.

Parallel rudder engagement automatically occurs when the A/P is engaged in the takeoff mode. The parallel rudder provides automatic yaw compensation in case of engine failure, however; the autopilot should not be engaged in T/O mode if an engine has already failed. The parallel rudder servo will be phased out when a new roll mode is selected. If parallel rudder is engaged during the transition to windshear mode, it will remain engaged.

In approach mode (LAND/ILS), parallel rudder engagement is available when radio altitude is less than 1,500 feet radio altitude and in LOC TRK, G/S TRK mode. If parallel rudder is engaged during the transition to auto G/A or windshear mode, it will remain engaged. The parallel rudder is disengaged when the A/P is disconnected at DH or upon exit from ground rollout mode.

Mach Trim Compensation

Mach trim compensation provides nose-up trim to compensate for the normal pitch down (tuck) characteristic encountered at high Mach operation. The function is controlled by the MACH TRIM COMP switch located on the overhead panel.

With the switch in NORM, the mach trim compensator positions the First

Officer’s control column aft at speeds greater than .80 mach.

August 11, 2008 4.20.17

Automatic Flight -

System Description

MD-88/90 Operations Manual

Altitude Alert

The altitude alert functions when the airplane is approaching a preselected altitude or deviating from an acquired altitude. An amber alert light on each altimeter indicates the alert for the above situations.

In addition, the aural warning, which consists of a continuing series of 1-second aural tones, and the vocal warning "altitude" are generated.

The DFGC receives and monitors altitude information from both CADC's to provide the altitude alert function.

Selected altitude alert is set by the ALT set knob on the FGCP and is automatically armed by selecting a new altitude.

In addition, the selected altitude is also armed manually by pulling the set knob.

Engaging the AP/FD into any pitch mode other than go-around, from glide slope capture or track mode, will automatically arm the preselected altitude. In go-around mode, the preselected altitude is automatically armed whenever the preselected altitude is at least 1000 feet above ground level (AGL).

The alert lights illuminate (steady) and the aural warning sounds when the airplane is between 750 feet and 250 feet from the preselected altitude.

If the airplane deviates more than 750 feet from the preselected altitude after the

750-foot threshold has been reached and before the 250-foot threshold has been reached, the lights will flash and the aural and vocal warnings will sound. If the airplane deviates more than 250 feet from the preselected altitude after the

250-foot threshold has been reached, the lights will also flash and the aural and vocal warnings will sound.

A different desired altitude may be preselected at any time. The warnings can be reset by selecting another altitude or by maneuvering the airplane within 250-foot capture limit.

The altitude alert function is inhibited at glide slope capture.

The altitude alert function is also inhibited if the flaps are extended to landing configuration.

Thrust Rating Panel

The engine thrust rating panel selects engine thrust rating modes for a specific phase of flight. The EPR limit for the selected mode is computed by the TRP and is based on existing RAT or assumed temperature, altitude and engine bleed air.

The EPR limit is also supplied to the autothrottle to be used as upper throttle authority limit when operating in the SPD SEL or MACH SEL modes, or as the commanded EPR when operating in the EPR LIM mode. The EPR limit for the flex takeoff mode is less than maximum or normal EPR but not less than CL

(climb) EPR.

4.20.18

August 11, 2008

Automatic Flight

MD-88/90 Operations Manual

OAP Messages/Lights

Chapter 4

Section 30 OAP Messages/Lights

Amber Caution Messages

NOTE: The associated cue light is shown in parenthesis (XXX) following the message.

MACH TRIM FAULT (CONT) - Indicates mach trim system is inoperative, as detected by DFGC, when MACH TRIM COMP switch is in NORM.

MACH TRIM OFF (CONT) - Indicates MACH TRIM COMP switch is

OFF.

YAW DAMP OFF (CONT) - Indicates yaw damper is inoperative or YAW

DAMP switch is in OVRD.

April 01, 2004 4.30.1

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OAP Messages/Lights

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Intentionally

Blank

4.30.2 April 01, 2004

Automatic Flight

MD-88/90 Operations Manual

Functional Schematic

Automatic Flight

Chapter 4

Section 40

CAPT'S FD

SWITCH

FLIGHT

GUIDANCE

CONTROL

PANEL

OFF

FMS

OVRD

SPD

SEL

MACH

SEL

EPR

LIM

SPD MACH

NAV

VOR

LOC

OFF

ILS

AUTO

LAND

HDG

AND

ANU

VERT

SPD

IAS

MACH

ALT

HOLD

AP ON

VNAV

1 2

ALT

OFF

TURB

F/O'S FD

SWITCH

FLIGHT CONTROLS

RUDDER

AILERON

ELEVATOR

HORIZONTAL

STABILIZER

THRUST RATING

PANEL

AUTOTHROTTLE

SERVO DRIVE

ELECTRIC

ALTIMETERS

CENTRAL AURAL

WARNING UNIT

THROTTLES

PITCH/ROLL/STAB AUG

DFGC 1 SIGNALS

DFGC 1 OR 2

AP ON

DFGC 2 SIGNALS

1 2

FLIGHT MODE

ANNUNCIATORS

FLIGHT

DIR.

FAST-SLOW/PITCH/ROLL

COMMANDS

FAST-SLOW/PITCH/ROLL

COMMANDS

FLIGHT

DIR.

YAW DAMP AUTO STAB AUG SPD CO

DIGITAL

FLIGHT

GUIDANCE

COMPUTER 1

YAW DAMP AUTO STAB AUG SPD CO

DIGITAL

FLIGHT

GUIDANCE

COMPUTER 2

RADIO

ALTITUDE

RADIO ALTITUDE 1

FAST-SLOW/PITCH/ROLL

SYMBOL

GENERATOR

DFGC

1 OR 2

FD CMD

NORM

BOTH

ON 2

DFGC

1 OR 2

RADIO ALTITUDE 2

FAST-SLOW/PITCH/ROLL

ATTITUDE

IRS-1

IRS-2

ATTITUDE

SG-1 VIDEO

EFIS

NORM

BOTH

ON 2

CAPT

PFD

SG-1 OR -2 VIDEO

WINDSHEAR

COMPUTER

SG-1 OR -2 VIDEO

SG-2 VIDEO

F/O

PFD

SYMBOL

GENERATOR

RADIO

ALTITUDE

AFMC-1

AFMC-2

OPTION

April 01, 2004

JB1-3-0909

JB1-3-0909

4.40.1

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Intentionally

Blank

4.40.2 April 01, 2004

Automatic Flight

MD-90 Differences

MD-88/90 Operations Manual

Chapter 4

Section 90 System Description

Automatic Thrust Cut-Back

An automatic thrust cutback function is available for takeoff noise abatement.

Prior to takeoff, a cutback EPR and altitude above field elevation (AFE) are entered into the multipurpose control display unit (MCDU). An armed status is displayed on the MCDU and in the throttle mode window of the FMA. Normal takeoff procedures are conducted. Approximately two seconds prior to reaching the cutback altitude (alert point), an aural warning "CUTBACK" is annunciated and additional cutback EPR limit bugs are displayed on the EDP. Upon reaching the cutback altitude, the autothrottle unclamps and retards the throttles to maintain the preselected cutback EPR limit. Autopilot/flight director guidance is provided to maintain the takeoff reference speed. The pilot may override/cancel an automatic thrust cutback by momentarily holding the throttles at or following the cutback initiation. In addition, an automatic thrust cutback is disarmed if any of the following occur:

• DFGC/AFMC/EEC/IRU failure detected

• FD takeoff pitch guidance not available

• TRP mode change

• Engine failure

• Windshear (Caution or Warning)

• Engine fire warning activated

• Master warning activated

• A/T disconnect

• Stick shaker activated

• TCAS RA activated

• Either throttle is moved from position at liftoff

• Gear handle is lowered after being raised

• Negative climb rate for 5 seconds

• Indicated airspeed < (Takeoff reference speed-5 knots) at alert point

MACH Trim

With the switch in NORM, the DFGC commands alternate trim motor, through the elevator load feel system, to schedule required alternate trim.

April 01, 2004 4.90.1

Automatic Flight -

MD-90 Differences

MD-88/90 Operations Manual

Thrust Rating Panel (TRP)

The engine thrust rating panel selects engine thrust rating modes for a specific phase of flight. The EPR limit for the selected mode is computed by each EEC based on existing total air temperature (TAT) or assumed temperature, altitude and engine bleed. Refer to Chapter 7, Engines, APU, Section 90, for further discussion on the TRP.

4.90.2 February 28, 2005

MD-88/90 Operations Manual

Communications

Chapter 5

Section 0

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.1

Audio Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.2

Flight Interphone System MIC Switches/Speakers . . . . . . . . . . 5.10.3

VHF COMM Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.4

SELCAL Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.5

Flight Attendant Handset. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.6

External Electrical Power Receptacle Panel . . . . . . . . . . . . . . . 5.10.7

Jack Box Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.7

Service/Interphone Communications . . . . . . . . . . . . . . . . . . . . 5.10.8

Cockpit Voice Recorder. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.9

ATC Transponder/TCAS Control Panel . . . . . . . . . . . . . . . . . 5.10.10

ACARS Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.11

ACARS Printer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.10.12

System Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.1

General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.1

Flight Interphone System. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.1

Audio Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.1

VHF Communication System . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.1

Selective Calling (SELCAL) System . . . . . . . . . . . . . . . . . . . . 5.20.2

Service Interphone System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.2

Call System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.2

Passenger Address System . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.3

Voice Recorder System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.20.3

ACARS System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.21.1

ACARS Touchscreen DATA LINK . . . . . . . . . . . . . . . . . . . . . . 5.21.1

System Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.21.1

Coverage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.21.2

Operational Overview . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.21.2

August 11, 2008 5.TOC.0.1

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MD-88/90 Operations Manual

ACARS 501 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.1

Interactive Display Unit (IDU) . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.1

IDU Lighting Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.3

Automatic Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.4

Crew Generated Messages . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.4

Message Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.5

Alert Advisory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.5

Informational Advisory . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.6

Touchscreen Keyboards. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.7

ACARS Keystroke Entry. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.11

DATA LINK INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.12

PREFLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.13

INIT DATA. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.14

FLT PLN RQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.15

CLEARANCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.15

OCEANIC RQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.16

PREDEPART RQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.16

ATC LOG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.17

PDC COMPANY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.18

AWABS 1/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.18

AWABS 2/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.20

UTC TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.21

DEPT DELAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.22

GND SERVICE RQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.23

WEATHER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.23

ATIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.25

FUEL RPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.26

FLIGHT PHASE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.27

ICE INSPECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.27

ENROUTE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.28

DIVERSION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.29

AIRBORNE RTN. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.30

POS RPT 1/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.31

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MD-88/90 Operations Manual

POS RPT 2/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.32

EN RTE DELAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.33

REV FLT PLN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.34

IN RANGE 1/2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.35

IN RANGE 2/2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.36

POSTFLIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.38

FLT SUMMARY 1/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.38

EMPLOYEE NUMBER . . . . . . . . . . . . . . . . . . . . . . . . 5.23.39

FLT SUMMARY 2/2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.40

ARRIVAL DELAY. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.41

MISC MENU. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.42

UNDEL MSGS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.43

MISC RPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.44

PRN PAPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.45

LINK STATUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.45

VHF CONTROL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.47

VHF VOICE CONTROL . . . . . . . . . . . . . . . . . . . . . . . 5.23.48

7500 RPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.49

ATC LOG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.50

FLT LOG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.51

DOWNLINKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.52

MTC COORD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.53

CALSEL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.54

ENGINE RPT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.56

FLT CTRL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.57

OTHER. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.58

MSGS RCVD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.59

SELCAL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.23.60

501 Touchscreen (Quick Reference) . . . . . . . . . . . . . . . . . . . . 5.23.61

MD-90 Differences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.90.1

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5.90.1

ACARS Automatic Messages . . . . . . . . . . . . . . . . . . . . . . . 5.90.1

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5.TOC.0.4

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MD-88/90 Operations Manual

Communications

Controls and Indicators

Chapter 5

Section 10

Intentionally

Blank

February 28, 2005 5.10.1

Communications -

Controls and Indicators

Audio Control Panel

MD-88/90 Operations Manual

MIC SELECTOR

1 –VHF– 2 –VHF– 3

INOP INOP

INT PA

1– NAV –2

CAB/SER

INT

I/C

AMP–2

AMP–1

MKR

R/T MASKS

V B R

I/C BOOM

JB1-3-0928

Microphone Switchlights

Push to select desired transmitter. Integral light illuminates. VHF switchlights also select respective receive function without independently selecting the corresponding receive switch.

A mechanical interlock prevents the selection of more than one transmitter at a time.

Control Knobs

Push to monitor audio. Push again to discontinue monitoring audio. All receivers may be simultaneously monitored.

Rotate knob to adjust volume.

Amplifier Switch

Used to select the desired amplifier for the audio selector panel.

Radio/Intercom Switch

Momentary in either position.

R/T - Keys radio transmitter for mask or boom microphone operation.

I/C - Keys flight interphone for mask or boom microphone operation.

5.10.2 February 28, 2005

Communications -

Controls and Indicators

MD-88/90 Operations Manual

MASKS/BOOM Microphone Switch

MASKS - Oxygen mask microphone connected to communications system.

BOOM - Boom microphone connected to communications system.

Voice/Range Selector

V - (Voice) Morse code signals filtered out.

B - (Both) Unfiltered reception. Morse code, voice, and DME is received.

R - (Range) Voice signals filtered out.

Flight Interphone System MIC Switches/Speakers

VOL

(Captain’s/First Officer’s) Speaker

VOL - Turn to adjust volume.

(Captain’s/First Officer’s) Control Wheel MIC Switch

Aft - Hold for radio transmission.

Center (Spring-loaded) - Off.

Forward - Hold for interphone transmission.

JB1-3-0975

JB1-3-0975

February 28, 2005 5.10.3

Communications -

Controls and Indicators

MD-88/90 Operations Manual

VHF COMM Control Panel

COMM

TFR

AFT PEDESTAL

Active/Standby Frequency Readout (2)

Tuned frequency, which is either active or standby, as selected.

Annunciator Lights (2) (green)

Illuminates to show readout of frequency in use.

TFR Switch

Selects either of the tuned frequencies.

VHF Frequency Selector Knobs

Outer Knob - Selects second and third digits of frequency.

Inner Knob - Selects fourth and fifth digits of frequency.

JB1-3-0932

5.10.4 February 28, 2005

SELCAL Control Panel

MD-88/90 Operations Manual

Communications -

Controls and Indicators

SELCAL

2 3

DATA LINK

VHF-1 VHF-2 VHF-3

PRESS TO RESET

MSG

AFT PEDESTAL

PRINTER

JB1-3-0933

VHF-1/VHF-2 Switchlights (blue)

Respective switchlight illuminates with chime from CAWS when called by a ground station.

Push respective switchlight to reset switchlight and chime.

VHF-3 Switchlights (blue)

Flashes in conjunction with a single chime when an ACARS uplink message is received. Will also indicate a SELCAL if VHF-3 is in VOICE mode and tuned to proper frequency.

Push respective switchlight to reset switchlight and chime.

MSG

Illuminates when an ACARS message has been received and is intended for display on the touchscreen. Pushing indicator resets system.

PRINTER

Illuminates when an ACARS message has been received and is intended for the printer. Pushing the indicator or the reset button on the printer resets the system.

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Flight Attendant Handset

ATT

P/A

PLT

PUSH & TALK

PASSENGER COMPARTMENT

ATT Call Switchlight

Push - Actuates chime for attendant-to-attendant call.

PLT Call Switchlight

Push - Actuates chime and ATTND CALLING light in cockpit.

P/A Switchlight

Push - Connects handset to passenger address system.

JB1-3-0936

JB1-3-0936

5.10.6 February 28, 2005

MD-88/90 Operations Manual

External Electrical Power Receptacle Panel

Communications -

Controls and Indicators

EXT PWR

NOT

IN USE

EXT

PWR

AVAIL

WHEEL WELL

LIGHTS PILOTS

OFF CALL

EXTERNAL ELECTRICAL

POWER RECEPTACLE PANEL

Mechanic-To-Pilot Call Button

PILOTS CALL - Push to call pilot. Chime sounds in cockpit.

JB1-3-0937

JB1-3-0937

Jack Box Control Panel

BOOM

HEADSET MICROPHONE

MICROPHONE Jack

Used to plug the boom microphone into the communication system.

HEADSET Jack

Used to plug the headset into the communication system.

JB1-3-0977

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MD-88/90 Operations Manual

Service/Interphone Communications

MAINTENANCE

INTERPHONE

OFF

PA

PA VOL

ATTND

CALLING

RESET

MECH

CALL

ATTENDANT

CALL

OVERHEAD PANEL

JB1-3-0939

JB1-3-0939

MAINTENANCE INTERPHONE Switch

OFF - Disconnects all maintenance interphone jacks from the service interphone.

ON - Connects all maintenance interphone jacks to the service interphone.

MECH CALL Button

Push - Horn sounds in nose wheel well.

ATTENDANT CALL Button

Push - Actuates chime and pink master call lights in the cabin.

ATTND CALLING/RESET Switchlight

ATTND CALLING - Illuminates simultaneously with chime when flight attendant pushes handset PLT switchlight.

RESET - Resets switchlight when pushed.

PA VOL Meter

Needle indicates output level of passenger address.

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PA Switchlight

When PA switchlight is momentarily pushed (handset off hanger), handset connects to passenger address system and the switchlight illuminates.

The switchlight extinguishes and the handset reverts to service interphone function when replaced on its hanger.

Cockpit Voice Recorder

TEST ERASE

HEADSET

600 OHMS

COCKPIT VOICE RECORDER

OVERHEAD PANEL

Cockpit Voice Recorder Microphone

The microphone picks up all audible sounds on the flight deck.

Monitor Indicator

Needle in green band during testing indicates normal system operation.

JB1-3-0978

TEST Button

When pushed, initiates a self test of all input channels.

ERASE Button

When pushed, disables playback of previously stored data.

The airplane must be on the ground with the parking brake set and normal power for the ERASE button to function.

Cockpit Monitor Headphone/Headset Jack

With a headset plugged into the jack, audible tones indicate proper operation of each function.

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ATC Transponder/TCAS Control Panel

ALT OFF ALT ON

STBY TA

TEST

TA/RA

ATC 1 R

ATC

FAIL

2 7

ATC

IDENT

ALT

4 5

AFT PEDESTAL

JB1-3-0978

Display Window

Indicates selected four digit code.

Displays ATC active channel code.

A blinking R is a reply of transponder interrogation.

Transponder Function Selector

TEST - Initiates transponder and TCAS test.

STBY - Power applied for warm-up only.

ALT OFF - Altitude reporting inhibited; PWS enabled.

ALT ON - Activates altitude reporting. TCAS system in standby; PWS enabled.

TA - Normal transponder operation, enables TCAS traffic advisories; PWS enabled.

TA/RA - Normal transponder operation, enables TCAS traffic and resolution advisories; PWS enabled.

Reporting Transponder

ATC 1 - # 1 Mode S transponder.

ATC 2 - # 2 Mode S transponder.

CODE Selectors (2)

Rotate two pairs to selected code.

ATC IDENT Button

Press for positive identification on controller’s scope.

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AIR Data Source

Indicates which CADC is being used for altitude reporting.

ATC FAIL Light

Indicates failure of selected transponder.

ACARS Control

AFT PEDESTAL

ACARS Touchscreen Interactive Display Unit (IDU)

JB1-3-0978

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ACARS Printer

MD-88/90 Operations Manual

POW

SLE

TES

RE-

JB1-3-0978

POWER Indicator (green)

Indicator lights when POWER is applied to the printer.

SLEW

Push-button activates paper feed process. Each time SLEW is pressed, paper is advanced through the printer. Pressing and holding down SLEW advances the paper continuously.

TEST

Push-button automatically prints test data.

RESET

Push-button resets the MSG indicator.

NOTE:

If the MSG Indicator is extinguished, continuously holding down the RESET push-button for 4 seconds clears the print queue.

MSG (green)

The MSG indicator illuminates whenever a complete message is received by the printer.

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MD-88/90 Operations Manual

Communications

System Description

Chapter 5

Section 20 General

The airplane communication systems consists of a flight interphone system and audio control panels, VHF communication systems and control panels, selective calling (SELCAL) system, service interphone system, call system, passenger address (PA) system, and cockpit voice recorder (CVR) system.

Flight Interphone System

The flight interphone is activated by pressing the INT MIC selector and the I/C

RECEIVER switches to allow the crew to use microphones and handsets for cockpit communications. Two speaker assemblies are installed overhead in the flight compartment to monitor all audio signals selected by the Captain and First

Officer. Operation of the microphone at either station mutes the speaker at that station. Speakers are not muted when the pedestal handset is keyed on passenger address (PA).

Audio Selector Panel

An audio selector panel is installed at the Captain’s, First Officer’s, and aft overhead panels. The audio selector panel permits two way communication capability from the flight interphone, cabin/service interphone and VHF comm radios systems. It provides voice and identification monitoring of selected navigation aids. Receiver volumes and microphone selections are controlled from this panel.

Selection of oxygen masks or boom microphones is controlled at the audio selector panel. Transmissions using the oxygen mask or boom microphone are keyed with the PUSH-TO-TALK switch or the control wheel microphone switch.

VHF Communication System

Three communications radios are installed. Two control panels are provided on the pedestal for normal operations. The transmitting and receiving frequency selection for VHF-1 and 2 is controlled from the VHF COMM control panels.

The VHF-3 frequency selection is controlled from the ACARS control unit when voice mode is selected.

Each VHF COMM panel has two frequency readouts and a transfer switch for selection of the active frequency, a light emitting diode above each frequency readout to indicate the active frequency, and two frequency selector knobs.

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On some airplanes, with the microphone continuously keyed, VHF transmission is available for 30 seconds. Four warning beeps sound during the last 5 seconds prior to transmit capability cutoff. On these airplanes, transmit capability may be continued beyond the 30-second segment by releasing and then re-keying the microphone switch.

Selective Calling (SELCAL) System

The selective calling (SELCAL) system operates in conjunction with the VHF system and provides a visual and aural indication when the airplane is being called. SELCAL enables ground facilities to selectively call an individual airplane.

When a SELCAL is received, the respective SELCAL switchlight illuminates and a chime from the central aural warning system (CAWS) sounds, indicating that the ground station is calling the airplane. Audio is controlled at the audio control panel. Changes in receiver volume do not affect SELCAL operation.

Communication with the calling station is established by pushing the appropriate

MIC button on the audio control panel. The SELCAL switchlight and chime are reset to receive a new call when the applicable switchlight is pushed, or when the respective transceiver is keyed for transmission.

Service Interphone System

The service interphone system allows communication between the various service and maintenance areas, the cockpit and the cabin attendant stations. Handsets in the cockpit and at the forward, mid and aft attendant panels are used for both the service interphone and the PA system.

The MAINTENANCE INTERPHONE switch on the aft overhead panel, when in

OFF, disconnects all external maintenance interphone jacks from the service interphone system except the ground power panel. When the switch is ON, all service interphone jacks are active.

Call System

Call lights and aural signals alert the flight crew, cabin attendants or ground maintenance personnel of a call from another station. A visual and aural signal alerts the cabin attendants of passengers requiring assistance at the passenger seats or in the lavatories.

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Passenger Address System

The passenger address (PA) system enables the pilots and cabin attendants to address passengers from the cockpit or the cabin through speakers located in the cabin, galleys and lavatories. PA announcements from the cockpit have priority over the passenger entertainment system and announcements made from any cabin station.

PA announcements from the cockpit are made through the service interphone handset, the mask or boom microphones, or the handheld microphone.

When using the service interphone handset for PA announcements, the PA switchlight on the overhead panel must be momentarily pushed. The blue PA light illuminates to indicate the PA has been activated.

With the PA microphone switchlight on the audio control panel selected, announcements using the mask or boom microphones are made by pulling the control wheel microphone switch aft for transmission or by selecting the radio transmitter position of the radio/intercom switch. The handheld microphone may also be used to make PA announcements by keying the hand microphone PTT switch (PA microphone switchlight selected).

PA announcements are made from the cabin attendant panels through the service interphone handsets. A PA push-to-announce switch on the handset, when pushed, connects the handset to the PA system for announcements.

Voice Recorder System

The cockpit voice recorder (CVR) continuously records the last 30 minutes of cockpit sounds and communications, any time there is normal electrical power available.

All sounds and communications are recorded through the cockpit voice recorder monitor microphone. All communications through the Captain's and First

Officer's audio control panels, as well as the cockpit handset, are also recorded.

The cockpit monitor unit of the voice recorder contains a microphone to record cockpit sounds, two separate push-buttons (a TEST pushbutton to test the recorder and an ERASE pushbutton to erase previous recordings), a headset jack (used to monitor a system test), and a test indicator.

The TEST pushbutton activates a self test. A successful self test is indicated by the needle moving into the green band.

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Whenever the airplane is on the ground with the parking brake set and normal electrical power, the erase function may be activated by pushing the ERASE pushbutton. When activated, the last 30 minutes of sounds and communications are erased.

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MD-88/90 Operations Manual

Communications

ACARS System Description

ACARS Touchscreen DATA LINK

ARINC DATA

LINK CONTROL

ARINC DATA

LINK STATION

LAND LINE CONNECTING

ARINC CONTROL AND

COMMUNICATIONS CONTROL

DATA

131.55MHz

Chapter 5

Section 21

VOICE

COMMUNICATIONS

CONTROL

VOICE

STATION

ACARS (ARINC Communications Addressing and Reporting System) is a data communications system which allows flight information to be transmitted between individual aircraft and the company host computer.

There are currently two different software versions of ACARS installed on

MD-88 aircraft. The -201 software is being replaced by the -501 version. Both are detailed in the following sections.

System Information

ACARS consists of the following aircraft components:

• The management unit (MU) which contains system memory, message transmission logic, and a UTC clock.

• An Interactive display unit (IDU) that provides crew input and control of the system.

• A VHF-3 comm radio which normally serves as the primary transceiver for ACARS.

• A data link panel with annunciators to alert the crew of ACARS message activity.

• A cockpit printer which provides hardcopy capability.

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Coverage

ACARS is designed for domestic and international use. The system will automatically scan for VHF communications and will automatically utilize any available authorized air/ground system depending on aircraft position.

Operational Overview

ACARS normally operates in the DATA mode and assumes control of the

VHF-3 radio. In this mode, a frequency is automatically selected and the VHF transceiver is unusable for voice communications. When the VHF-3 comm radio is in the DATA mode, ACARS transmissions occur:

• Automatically for OUT, OFF, ON and IN reports.

• When the SEND prompt is selected.

• When transmitting and receiving messages for cockpit printers.

• When communications are re-established after a period of NO COMM, if there are stored messages present.

• When transferring from VOICE to DATA mode if stored messages are present.

VOICE Mode

• May be selected on the IDU, the frequency tuned on the VHF 3 COMM panel and then utilized for voice communication.

• If VOICE mode is selected, the system must be manually returned to the DATA mode.

ACARS Printer Unit

A cockpit printer (summit full format), is mounted aft of the First Officer’s briefcase holder in a vertical fashion. The printer allows hardcopys of company transmissions, as well as crew requested messages, to be printed when requested.

The printer includes: the front panel controls, an access door, and paper exit.

April 01, 2004

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Communications

Chapter 5

Section 23 ACARS 501

Interactive Display Unit (IDU)

The touchscreen interactive display unit has a flat display screen activated by objects which break the infrared grid projecting over the screen. As finger tips or pencils touch the screen, the grid calculates the location and expands the displayed selection into an outlined mode. When the finger tip is lifted off the screen, the prompt displaying an outlined mode will be entered in the computer.

This allows the crew to slide a finger over the screen to select the desired function without inadvertently entering the wrong selection.

The basic menu and sub-menu page displays are divided into two horizontal sections as shown below:

UPPER SECTION

DISPLAY

LOWER SECTION

DISPLAY

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The upper section can contain the following during normal system operations.

• Menu or sub-menu title.

• Menu items listed in two columns.

• PRINT prompt will send pages or messages to the aircraft printer and only appears if printer is operative.

• SEND prompt will initiate a downlink from the cockpit. This prompt only appears after all required entries have been completed.

• RETURN prompt which will return the system to the previous menu or page.

• Alert advisory messages.

• Informational advisory messages.

The lower section can contain the following selections during normal system operations:

• INDX prompt returns the system to the DATA LINK INDEX page.

• PREV prompt returns the system to the previously displayed screen.

• NEXT prompt moves the system to the next display screen.

• LGHT prompt displays the lighting control screen.

• The system to the MENU page.

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IDU Lighting Control

The AUTO/MAN prompt toggles between AUTO and MAN mode for screen lighting control. During normal operation, it is recommended that crews leave the lighting control in the AUTO mode so that the screen will automatically adjust to ambient light conditions. However, the screen brightness level can be adjusted in MAN mode by touching and holding the DECREASE or

INCREASE prompt. Continually touch either prompt until the lighting is optimal.

NOTE:

If the brightness has been turned down so far that the display cannot be seen, touch and hold the screen in the uppermost left hand corner to increase the brightness.

The NORM / INV prompt toggles between NORM and INV mode of background and character contrast. The INV mode is recommended for night use as the lighter characters on a dark background are more easily seen. The

NORM mode displays dark characters on a lighter background.

The lighting control screen is shown below:

H H : M M L I G H T I N G

S C R E E N M O D E

A U T O / M A N

AAAA

N O R M / I N V

AAAA

B R I G H T N E S S L E V E L

DECREASE INCREASE

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Automatic Messages

OUT, OFF, ON, and IN reports are automatically transmitted based on signals from the cabin doors, anti-collision light, and air-ground sensing. Minimum requirements for automatic transmission of these times are:

• Entry of initialization data.

• Manually or automatically (INIT RQ).

• Available communication link

• ACARS in DATA mode.

All the communication networks can be operationally tested at any time by using the LINK TEST on the LINK STATUS page.

OUT time processing:

• The OUT time is automatically recorded and transmitted immediately when all cabin doors are closed and the anti-collision light has been turned ON. Fuel on board is also transmitted with the OUT time if entered on the INIT DATA page during pre-flight.

OFF time processing:

• is recorded at lift-off and transmitted immediately.

After attaining a stable cruise condition, the flight data acquisition unit will collect engine data and automatically transmit this data via ACARS.

ON time processing:

• The ON time is recorded at touchdown and transmitted immediately.

IN time processing:

• The IN time is immediately recorded and transmitted anytime any cabin door is opened or when the anti-collision light is turned OFF.

OUT, OFF, ON, and IN messages that cannot be transmitted due to a NO

COMM condition will be stored up to a total of 5 more flight segments or until a communication link is established.

Crew Generated Messages

In addition to the automatic messages, ACARS is used to send other messages.

Prepared menus and prompts are provided as described in the following pages.

Refer to section 5 of the QRH or the FOM for proper usage of ACARS messages.

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Message Indications

Flight crews are notified of incoming messages by the flashing MESSAGE advisory on the touchscreen, the MSG light on the data link annunciator panel, and chime.

Alert Advisory

The flashing advisory messages on the touchscreen alert the flight crew to abnormal conditions or annunciate the need for necessary crew actions. On menu pages, the alerts appear in the lower right corner above the LGHT prompt.

Touching the advisory will automatically access the required menu.

The messages shown below are listed in order from highest to lowest priority:

FAIL

POWER

SELCAL

ATC MSG

OCEANCL

DEPT CL

MESSAGE

INIT

DATAMD

ATIS

INRANGE

ARRDLA

Internal failure of Management Unit. Refer to QRH

Section 5.

Power interruption resulting in loss of initialization data.

SELCAL uplink message received.

New ATC uplink message received and ready for display.

New ATC oceanic clearance uplink message received and ready for display.

New ATC predeparture clearance message received and ready for display.

New company uplink message received and ready for display.

Initialization data incomplete.

Data Link attempted with ACARS in VOICE Mode or

ACARS in VOICE Mode for greater than 3 minutes.

ATC ATIS message received and ready for display.

In Range Report should be sent.

Arrival Delay Report should be sent.

SUMMARY minutes after OUT if no OFF.

Summary Report should be sent.

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ALERT ADVISORY AREA

RETURN

INDX

SELCAL

LGHT

Informational Advisory

Informational advisory messages appear on the touchscreen to display operational status of ACARS. On menu pages, these messages appear on the immediate right of the RETURN prompt. On the keyboard displays, these messages appear in the top right-hand corner next to the ENT prompt.

The messages shown below are listed in order from highest to lowest priority:

IN PROG

UTC OK

VOICE

NO COMM

Message is actively being sent.

UTC TIME updated by uplink.

VHF is in voice mode.

No DATA LINK is available.

NOTE: If the data link is functioning normally in the DATA mode, there will be no advisory shown.

INFORMATIONAL ADVISORY AREA

RETURN

I N P R O G

INDX

LGHT

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Touchscreen Keyboards

There are two different categories of input keyboards: data input and free text.

The data input keyboards include alphabetical, numeric, and hexadecimal. The free text keyboards include alphabetical, numeric, and symbolic. The appropriate keyboard will automatically appear depending on the prompt that is selected from the displayed page.

Each keyboard will have some of the following functions:

CLR

• Used on data input keyboards. Clears the character under the cursor and all characters to the right of the cursor.

ESC

• For optional fields - aborts current data entry and returns to calling page.

• For required (auto-sequence) fields, aborts data entry for current field entry and goes to calling page while retaining data for all previously filled fields of the auto-sequence list.

• For free text fields, aborts current free text entry and returns to calling page.

DEL

• Used on free text keyboards.

• Deletes the character under the cursor. If the cursor is at the end of the text, deletes the character to the left of the cursor.

DFT

• Used on data input keyboards.

• Restores the field’s default value if one exists. If no default value exists, the field is cleared.

ENT

• For optional fields, accepts entered data and returns to calling page.

• For required (auto-sequence) fields - accepts entered data for current field and proceeds to data entry for next field in sequence.

• For free text entry, start new line in message.

SYM - Selects the free text symbolic keyboard.

NUM - Selects the free text numeric keyboard.

ALP - Selects the free text alphabetic keyboard.

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Data Input Keyboards

These keyboards include alphabetical, numerical, and hexadecimal.

The area above each keyboard displays three lines: the title of the menu page in use, the prompt selected and the data input line (or scratchpad). Entered data or text appears on the scratchpad with an underscore character to act as an entry cursor and a rectangle character to act as an overwrite cursor. Touching the ENT prompt will enter the data into the message. The left and right arrows allow movement of the cursor across the scratchpad.

Alphabetic Keyboard

ALERT ADVISORY MESSAGE

INFORMATIONAL ADVISORY

TITLE LINE

PROMPT LINE:

SCRATCHPAD

A B C

E /

CLR

T NUM

DFT

Y Z SP

5.23.8 April 01, 2004

Numeric Keyboard

MD-88/90 Operations Manual

ALERT ADVISORY MESSAGE

INFORMATIONAL ADVISORY

TITLE LINE

PROMPT LINE:

SCRATCHPAD

1 2 3

“

CLR

N ALP DFT

S E SP

Hexadecimal Keyboard

ALERT ADVISORY MESSAGE

INFORMATIONAL ADVISORY

TITLE LINE

PROMPT LINE:

SCRATCHPAD

D 1

/ /

CLR

DFT

Communications -

ACARS 501

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MD-88/90 Operations Manual

Free Text Keyboards

These keyboards include alphabetical, numeric, and symbolic. The area above each keyboard displays three lines: the title of the menu page in use and two text lines. Up and down arrows are provided to scroll through the text message.

Alphabetic Keyboard

ALERT ADVISORY MESSAGE

INFORMATIONAL ADVISORY

TITLE LINE

TEXT LINE 1

TEXT KUBE 2

A B C

E .

DEL

T NUM

SYM

Y Z

Numeric Keyboard

ALERT ADVISORY MESSAGE

INFORMATIONAL ADVISORY

TITLE LINE

TEXT LINE 1

TEXT LINE 2

1 2 3

L R

+ –

C X

DEL

N ALP SY

’ " W

S E SP

5.23.10 April 01, 2004

Symbolic Keyboard

MD-88/90 Operations Manual

ALERT ADVISORY MESSAGE

INFORMATIONAL ADVISORY

Communications -

ACARS 501

TITLE LINE

TEXT LINE 1

TEXT LINE 2

( ) ?

‘

;

“

DEL

ALP

NUM

ACARS Keystroke Entry

For all ACARS IDU page depictions, the following key applies:

Acars Keystroke Entry Table

Example Entry Allowed

AAAA

NNNN

Use alpha characters only.

Use numeric characters only.

XXXX

ZZZZ

Alpha or numeric characters may be used.

Alpha or numeric characters or symbols may be used.

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Data Link Index

The DATA LINK INDEX is the initial screen displayed and provides access to the following menus and function:

H H

M M

D A T A L I N K I N D EX

PRE F L I GHT

E N ROUT E A T I S

POST F L I GH T

M I SC MENU

A T C L OG

W E

D O W N

M G

A T

L I NK S

R CVD

MENU INDX LGHT

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PREFLIGHT

Selecting PREFLIGHT from the DATA LINK INDEX page accesses the

PREFLIGHT page. This provides the crews access to items normally used prior to takeoff.

H H

M M

P R E F

I GH T

I N I T DA T A

D E PT D E L AY

F L T PL N R Q

GND SVC RQ

CL EA RANCE S

W E A T

FUE L R P T

UT C T I M E

ICE INSPECT

U N

MENU INDX

LGHT

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INIT DATA

This prompt allows the crew to load initialization data for the DATA LINK.

Selecting INIT RQ automatically inputs all fields, except GW, FOB, FUEL

BOARDED, and ETE, through a downlink/uplink message exchange with the host computer if ground network and initialization data are available. GW, FOB,

FUEL BOARDED, and ETE must be manually input. Required entries may also be entered manually on the INIT DATA page, paying close attention to the correct flight number, date, and city pair on the flight plan. The destination is automatically transferred to the IN RANGE page and the ATIS page after

“OFF” is sent. The ETE is also used together with OFF time to calculate the

ERT displayed on the IN RANGE page and the FLIGHT LOG page. All entries are required to complete this page. If any items are missing, the INIT advisory will appear at the OUT event. If this occurs, touch INIT to access the INIT

DATA page and fill in any incomplete data.

H H

M M

F L T N O

I N I T DAT A

O R I G

F O B

G W

D A T E

F U E L

D E S T

A T I S

B O A R D E D

PR I N T

U N

MENU INDX

I N I T RQ

LGHT

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FLT PLN RQ

This prompt allows the delivery of the flight plan to the cockpit printer, provided ground computer link and programming are available.

H H

M M F LT P L N R Q

INDX

S E ND

LGHT

CLEARANCES

This prompt allows access to the CLEARANCES menu page.

H H

M M

C L E A R ANC E S

OC EA N I C RQ

DEP A R T RQ

AT C LO G

P D C ( CO M P

)

U N

MENU INDX

LGHT

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OCEANIC RQ

[NOT FUNCTIONAL AT THIS TIME]

H H

M M

E N T R Y

M A C H

O C E N I C

F I X

C L E A R N C E

E T A

F L I GH T L E V E L

F L

]

F AC I L I T Y

E D I T T E X T

]

S E ND

U N

INDX

LGHT

PREDEPART RQ

[NOT FUNCTIONAL AT THIS TIME]

H H

F L

M M

N O

P R E DE P A RT C LX

1 / 2

O R I G

A T I

A C T Y P E

F AC I L I T Y

GA T E

- -

S E ND

INDX PREV NEXT

LGHT

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Communications -

ACARS 501

H H

M M P R E DE

]

L R T E X T

A CLX

2 / 2

E D I T T E X T

]

S E ND

INDX PREV NEXT

LGHT

AC TYPE

FACILITY

MD-88

MD-90

ATC facility for predeparture clearance request.

ATC LOG

[NOT FUNCTIONAL AT THIS TIME]

H H

M M A T C L O G N N / N N

H H

M M A A A A A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M A A A A

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M

A A A A A A A A

X X X X X X X X X X X X X X X X X X X X X X

U N

INDX PREV NEXT

LGHT

April 01, 2004 5.23.17

Communications -

ACARS 501

MD-88/90 Operations Manual

PDC COMPANY

Selecting PDC (COMPANY) from the CLEARANCES page causes delivery request message to be readied for downlink

H H

M M P D C ( CO MPANY )

INDX

S E

LGHT

AWABS 1/2

Selecting AWABS provides access to two pages of AWABS data

H H

M M

S N / /

WA B S

F C / C C / Y C

- -

1 / 2

T E MP

/ F

/ D

W I N D ( D I R / V E L )

- - / - -

T O L

- -

E R A N C E

A L T I M E T E R

- - -

PR I N T

INDX PREV NEXT LGHT

5.23.18 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

SN Sequence number - (for future use). To satisfy ACARS requirements, enter 88 when utilizing this screen.

RWY Runway identifier. Enter desired takeoff runway. AWABS data will only be sent for this runway. The runway label must be recognizable by AWABS (consult the existing WDR for the exact label). Some examples:

26 R

26 LTWYE13 - 26 Left at Taxiway E 13.

25 LPOSNF - 25 Left at Position NF.

If the runway ID is not recognized, ACARS will uplink a message with a list of possible runway labels.

CONT Contamination code. Enter contamination code for the condition you desire.

Dry (default entry)

Wet

Icy

Quarter Clutter 25 CTR

H Half Clutter 50 CTR

If you are overweight for the requested contaminant, you will receive a message uplink advising you of this, but you will not receive a

WDR uplink.

The remaining fields are optional and should only be used if you desire a change from the existing WDR conditions.

Temp Current Temp / F or C

Default = F

FC/CC/YC Passenger loading distribution. Enter only changes from the existing WDR passenger distribution. Example: to change

12/30/183 (WDR) to 12/20/183, enter /20/. Express aircraft will fill FC and CC fields with zero.

February 28, 2005 5.23.19

Communications -

ACARS 501

Wind

MD-88/90 Operations Manual

Wind direction and velocity.

Toggle through selections:

- - -:(default) will leave the tolerance as it was on the latest

WDR.

OFF: forces the tolerance off.

ON: forces the tolerance on.

Refer to FOM (if desired) for a detailed explanation of tolerance.

Altimeter Current altimeter setting.

Range of entries is:

850 - 1150 hPa.

2700 - 3300 inHg.

Any entry greater than 2000 is considered inches of mercury

(inHg) while any entry less than or equal to 2000 is considered

Hectopascals (hPa).

AWABS 2/2

The entries on AWABS page 2 are for future use and should be left blank.You

must move to page 2 in order to access the SEND prompt.

H H

C G O

M M

A WA

F U L

B S

E 1

/ /

C G O -

F U L E 2

/ -

I N C A D J

M E L

Z F W

2 / 2

C D L

PR I N T

INDX

S E ND

PREV NEXT

LGHT

5.23.20 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

UTC TIME

Selection provides access to UTC TIME page and allows flight crews to update the ACARS UTC clock. Touching UTC RQ sends a message to automatically synchronize the internal ACARS clock with UTC. When the update is complete a UTC OK message is displayed at the screen bottom.

H H

M M

T I ME

: -

U T C

I M E

U N

INDX

U T C RQ

LGHT

Manual input allowed only when system is not in communication with authorized ground facility.

February 28, 2005 5.23.21

Communications -

ACARS 501

MD-88/90 Operations Manual

DEPT DELAY

Selection allows access to revise the estimated time off (ETO). Workload permitting, the reason for the delay should be entered in the EDIT TEXT field.

H H

M M

E S T T I

D E P T DEL A Y

M E O F F

]

PR I N T

E D I T T E X T

S E ND

]

INDX

LGHT

5.23.22 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

GND SERVICE RQ

All the fields that are “AAA” are either yes or no fields and are mandatory in order to get the SEND prompt. This report is sent directly to dispatch.

WEATHER

Selection provides access to weather request pages.

February 28, 2005

H H

M M

W E A HER

HOURLY W X T

A E F CS T

F L D COND

A TI S

V E

R E W X

INDX

LGHT

5.23.23

Communications -

ACARS 501

MD-88/90 Operations Manual

Selection of any weather type on menu provides access to WEATHER RQ page with selected type provided in type selection area.

H H

M M

T Y P E

W EA T

A A A A A A A A A

HE R RQ

S T A 1

S T A 2

- -

S T A 3

- -

S END

PR I N T

INDX

LGHT

STA1 Defaults to departure station prior to OFF event.

Defaults to destination station after OFF event.

Enter the desired station of interest.

STA 2

STA 3

Enter other stations, if desired.

For area forecast, the city used must be ANC, BOS, SHI, DFW, FIA,

HNL, JNU, MIA, SFO, or SLC. Enter the city as a 4 character input, with the 4th character being one of the following:

H - will report hazards

S - Synopsis

T - Turbulence

C - Clouds

I - Icing

Blank - all of the above.

For example, to obtain icing forecast for SLC, input SLCI.

5.23.24 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

ATIS

Selecting this prompt from the DATA LINK INDEX page accesses the ATIS page.

H H

A I

M M

R P O R T

T I S

A T I S MS G

T Y P E

A A A A A A A A A A A A A A A A A A A A

A U T O

A A A A A

U P D A T E

INDX

S END

LGHT

AIRPORT

Defaults to departure station prior to “OFF” event.

Defaults to destination station after the “OFF” event.

TYPE

Enter airport for which ATIS is desired.

Arrival.

Departure.

Arrival/Departure.

Enroute info service.

(Toggle selection).

AUTO

UPDATE

Start.

Stop.

(Toggle selection, START should be entered).

ATIS MSG Allows access to ATIS display page (only available if uplink message has been received).

SEND

Displayed only when required information has been entered.

February 28, 2005 5.23.25

Communications -

ACARS 501

MD-88/90 Operations Manual

FUEL RPT

Selection provides access to FUEL RPT page.

H H

F O B

M M

FUEL RPT

F LT P H A S E

F LT L E V E L A LT

T I M E

S AT

H O U R S . . . . . A P U . . . . .

- - - - -

C Y C L E S

- -

PR I N T

S E N D

INDX LGHT

FOB

FLT PHASE

APU

Enter current fuel on board.

Enter the current phase of flight, i.e.,

BLOCK OUT, TAKEOFF,

TOP OF CLIMB, etc. Default value is current flight phase. Selection of this item accesses the FLIGHT PHASE

Page described below.

Inputs are optional.

5.23.26 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

FLIGHT PHASE

Selection of any item inserts that phase into the FLT PHASE area of FUEL RPT page and returns display to FUEL RPT page.

H H

M M

F L I G HT P H AS E

BL OCK OUT

BL OC K I N

T OP OF CL I MB

CR U I S E

T OP OF DE SNT

R E T UR N

INDX

LGHT

ICE INSPECT

[NOT FUNCTIONAL AT THIS TIME]

H H

M M I C E I N P T RQ

INDX

S END

LGHT

Selection of SEND allows request for ice inspection data to be transmitted if in data link communications.

February 28, 2005 5.23.27

Communications -

ACARS 501

MD-88/90 Operations Manual

EN ROUTE

Selecting EN ROUTE from the DATA LINK INDEX page accesses the

EN ROUTE page. This provides the crew with the necessary prompts for en route operation.

H H

M M E N R

DI V E RS IO N

A B E RT N

POS I T I ON RP T

I N

W E A

A T I S

EN R T E DE L AY

RE V F L T P L N

F UEL

D O W N L I NK S

RET URN

INDX

LGHT

5.23.28 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

DIVERSION

Selecting this prompt accesses the DIVERSION page. Enter the divert field in the DIVERTING TO area. All other data is helpful to Flight Control, but not necessary to send the message. The SEND prompt will appear after the divert field is entered. The EDIT TEXT prompt is provided to allow any additional pertinent information or requests. After sending, the divert to airport automatically replaces the destination on the INIT, FLT LOG, ATIS pages, and all subsequent downlinks. If this report is sent, the IN RANGE menu will have the ERT and DESTINATION updated to reflect these inputs.

]

H H

M M

D I V E R T

D I V E RS I O N

I N G T O

E R T

- : - -

PR I N T

F OB

E D I T T E X T

S E ND

]

INDX

LGHT

FOB

ERT

Enter current fuel on board.

Estimated ramp time. The default value is the ETA shown on page 1 of the FLT LOG plus 5 minutes.

February 28, 2005 5.23.29

Communications -

ACARS 501

MD-88/90 Operations Manual

AIRBORNE RTN

Selecting this prompt accesses the AIRBORNE RTN page. Touching the SEND prompt will relay a message that the crew has decided to return and land at the previous departure station.

H H

M M A I R ORNE R T N

U N

INDX

S E ND

LGHT

5.23.30 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

POSITION REPORT Page 1 of 2

This prompt is used to enter company position report information. This report consists of 2 pages, the second of which can be accessed through the use of the

PREV or the NEXT prompt. If NEXT POSITION and ETA are entered, they will automatically move to POSITION and TIME for the next POSITION RPT once SEND is pressed. Partially completed pages will retain entered data until report is sent or the end of the flight.

H H

M M P O S I T

P O S

I T I

O N

F L T

F L

L E V E L

I O N RP T

A L T

1 / 2

T I M E

MA C H

- -

F O B

- - -

N E X

S I

T I O

E N S

I N G

S I

T I O N

- - :

T A

- -

U N

INDX PREV NEXT

LGHT

Position, flight level, Mach number, and FOB are automatically input on MD-90 only.

February 28, 2005 5.23.31

Communications -

ACARS 501

MD-88/90 Operations Manual

POSITION RPT Page 2 of 2

SAT must be entered manually, but ICING, TURBULENCE, and SKY COND have scroll through selections which change at the touch. Select SEND to downlink the report before leaving the second page.

H H

M M P O S I T

W I N D

- - -

( D

/ - - -

I R

U R

B U L E

A A A A A

A A

I O

/ V E L )

N RP T

2 / 2

S A T

- -

A A A A

I C I N G

A A A A

S K

A A

C ON D

A A A A

I T

U N

INDX

S E N D

PREV NEXT

LGHT

The TURBULENCE scroll through selections are:

• SMOOTH

• LT CHOP

• LT TURB

• MOD CHOP

• MOD TURB

• SEV TURB

• EXT TURB

The ICING scroll through selections are:

• NONE

• TRACE

• LIGHT

• MODERATE

• SEVERE

5.23.32 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

The SKY COND scroll through selections are:

• CLEAR

• SCATTERED

• BROKEN

• OVERCAST

• UNDERCAST

• IN CLOUD

• BTWN LAYER

• CIRRUS

EN RTE DELAY

This prompt is used to report enroute delays which affect arrival time. The report provides space for expect further clearance (EFC) time. The SEND prompt appears when the EFC TIME is entered. Use of EDIT TEXT field is optional.

]

H H

M M

E F C T

E N O

M E

E D E L A Y

PR I N T

INDX

E D I T T E X T

S E ND

]

LGHT

February 28, 2005 5.23.33

Communications -

ACARS 501

MD-88/90 Operations Manual

REV FLT PLN

Request flight plan from dispatcher.

]

H H

M M

I N I T

R E V F L T

A L T

P L N

PR I N T

INDX

E D I T T E X T

S E ND

]

LGHT

5.23.34 February 28, 2005

Communications -

ACARS 501

MD-88/90 Operations Manual

IN RANGE 1/2

This screen is used to provide arrival assistance information and the estimated ramp time at the gate. This report consists of 2 pages, the second of which can be accessed through the use of the PREV or the NEXT prompt. Enter the appropriate information and execute the downlink with the SEND prompt. The destination and ERT will be automatically filled in using information from the

INIT DATA Page or DIVERSION page (if this report has been sent). Page 2 provides a text format for sending special requests not listed in the menu sections of page 1. WHEEL CHR and UNACC MINOR fields should reflect numbers over that required in Flight Attendant departure report.

H H

M M

D E S T

I N

W H E

- -

E L C H R

R E D

A A A

S E

A A

C U

A T

T Y

RA N G E

U N A C C

1 / 2

E R T

M I N O R

- -

M E D I C A

A A A

L A N G A S S I S

A A

PR I N T

INDX

PREV NEXT LGHT

The RED COAT, MEDICAL, SECURITY, and LANG ASSIST fields are toggle

YES or NO selections.

February 28, 2005 5.23.35

Communications -

ACARS 501

IN RANGE 2/2

MD-88/90 Operations Manual

]

H H

L A

A A

M M

I N

S R V C

C A B I N

2 / 2

S RV C

E D I T T E X T

]

S E ND

PR I N T

INDX

PREV NEXT LGHT

The LAV SRVC and CABIN SRVC fields are toggle YES or NO.

5.23.36 February 28, 2005

MD-88/90 Operations Manual

Communications -

ACARS 501

Intentionally

Blank

February 28, 2005 5.23.37

Communications -

ACARS 501

MD-88/90 Operations Manual

POSTFLIGHT

Selection from DATA LINK INDEX page allows access to the POSTFLIGHT menu page.

H H

M M

P O S T F L I G H T

F L T S UMMA RY

F U E L RP T

R I VAL D EL AY

INDX

LGHT

FLT SUMMARY 1/2

Selection provides access to the FLT SUMMARY pages. This page is automatically displayed after the IN event if no pilot entry is in progress.

H H

M M F L T S U MAR

E M P N O

X X X X X X X

T A K E O F F

1 / 2

PW R

A A A A A

O T H E R

P W R

- - - - -

E M P

X X X

N O -

X X X X

L A N D I N G F O

H OU R S

- - -

. -

H I

X X

I N

X X X

F U E L

X X X X

A P U

C Y CL E S

- - - - -

INDX

PREV NEXT

LGHT

5.23.38 April 01, 2004

Communications -

ACARS 501

EMP NO

T/O PWR

OTHER PWR

FOB

HI MAIN FUEL

APU

MD-88/90 Operations Manual

Selection displays EMPLOYEE

NUMBER page containing the employee numbers from the INIT RQ uplink. If the desired Employee Number is not listed, input the correct number on the

EMPLOYEE NUMBER page.

MAX

AT 45

AT 50

OTHER

This is only available if OTHER is selected in T/O PWR.

Enter the actual AWABS setting.

Enter on Board. (90) Auto Fill.

NO DATA

0 - 5.5

5.5 - 9.9

(Toggle through selection)

Enter applicable 2 digit APU use code.

EMPLOYEE NUMBER

H H

M M

E MP L

X X X X X X X

M BE R

X X X X X X X

E M

P N O

- - - - -

INDX

LGHT

February 28, 2005 5.23.39

Communications -

ACARS 501

MD-88/90 Operations Manual

FLT SUMMARY 2/2

Selecting NEXT allows input of autoland and IRU error information.

H H

M M

A U T O L

A A A

F L T

A N D

A I R P O R T

S U MAR Y

I R U

2 / 2

E R R OR

- - -

R U N W A Y

S A T / U N S A T

A A A A A

PR I N T

- - -

S E ND

INDX

PREV NEXT

LGHT

AUTOLAND

AIRPORT

RUNWAY

SAT/UNSAT

YES

(Toggle Selection)

Enter arrival airport.

Enter Runway identifier (8R, 9L,

25L, 24R, etc.).

SAT

UNSAT

(Toggle Selection)

Input appropriate IRU errors.

IRU ERROR

NOTE: Must enter YES in AUTOLAND Prompt for AIRPORT,

RUNWAY, and SAT/UNSAT to be available.

5.23.40 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

ARRIVAL DELAY

Selection provides access to ARRIVAL DELAY Page. Enter the estimated gate time and any relevant information for the dispatchers. Press SEND Prompt. This message is for use when experiencing taxi delays after landing.

H H

M M

E S T G A T

A R R I

E T I

V AL

M E

DEL A Y

]

PR I N T

E D I T T E X T

S E ND

]

INDX

LGHT

April 01, 2004 5.23.41

Communications -

ACARS 501

MD-88/90 Operations Manual

MISC MENU

Selection from DATA LINK INDEX page provides access to the MISC MENU page.

H H

M M

M I S C MEN U

UNDE L MSG S L I NK

S T A TUS

M I S C R P T

7 5 0 0 R P T

U TC T I ME

M A I N T M E NU

INDX LGHT

5.23.42 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

UNDEL MSG

Selection provides access to the UNDEL MSGS pages. This page displays the messages currently being held in the downlink message buffer. Select the message for display. Typically this page will display no cued messages unless the aircraft is in NO COMM, VOICE mode, or the air/ground network is highly congested.

H H

M M

U N D E L

MS G 1 T I T L E

M S GS

H H

M M

MS G 2 T I T L E

H H

M M

MS G 3 T I T L E

H H

M M

MS G 4 T I T L E

H H

M M

MS G 5 T I T L E

INDX

PREV NEXT

0 1 / N N

LGHT

April 01, 2004 5.23.43

Communications -

ACARS 501

MD-88/90 Operations Manual

MISC RPT

This is a special prompt for unit program testing, which requires a specific format code (FRMT NO). Flight crews should not use this selection unless specifically requested to do so.

]

H H

M M

F R M T NO

Z Z

I S C RPT

PR I N T

INDX

E D I T T E X T

S E ND

]

LGHT

5.23.44 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

PRN PAPER

Selection provides access to PRINTER PAPER page, which will advise Delta’s host computer that the aircraft is out of paper. This downlink, if sent, will prevent Delta personnel and systems from attempting to uplink messages directly to the cockpit printer.

H H

M M PA PER

U N

INDX

S E ND

LGHT

LINK STATUS

This prompt is available from the MISC MENU page and is used to check the status or invoke a test of the air/ground communication link.

H H

M M

V H F

L I N K

S A T C OM

I N K

T E S T

S T

L I N K T E ST

H F

L I N K T E ST

V H F

V H F C N T R L

S T A T U S

A V A I L

S T A T U S

N O C OM M

S T A T U S

M O

N O C OM M

D E / F R E Q

A /

N N

INDX

LGHT

April 01, 2004 5.23.45

Communications -

ACARS 501

MD-88/90 Operations Manual

Selecting the LINK TEST prompt initiates a test on the respective link. The

STATUS is displayed, and the options are:

STATUS AVAIL

UPLINK

DNLINK

UP/DNLINK

NO COMM

VHF CNTRL page can be invoked from this menu. If VHF is in VOICE mode, selecting will cause the VHF VOICE CNTRL page to be displayed. The current

VHF mode and frequency is also displayed. The mode definition is as follows:

V data mode voice mode frequency search or establishment in progress

Alternate tuned frequency. This occurs when ground network has automatically tuned the radio to alternate data frequency.

This is also a normal data mode of operation.

5.23.46 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

VHF CONTROL

This prompt is activated from the LINK STATUS page. The current mode

(DATA, VOICE, SCAN, ATUNE) and active VHF frequency are displayed.

CHANGE MODE will toggle VHF-3 from data to voice. A VHF LINK TEST can also be performed from this page. The various worldwide ACARS VHF frequencies are displayed along the right side.

H H

M M

M O D E

A A A

V HF

F R E Q

N N

C H A N G E M O DE

U S / P A C I

1 3 1

F I C

5 5

E U

A S I A

7 2

1 3

J A

P A N

4 5

L I N K T E S T

INDX

LGHT

April 01, 2004 5.23.47

Communications -

ACARS 501

MD-88/90 Operations Manual

VHF VOICE CONTROL

The page is displayed by selecting the VHF CONTROL prompt on the LINK

STATUS page while VHF-3 is in VOICE mode or from the CHANGE MODE selection on the VHF CNTRL page. VHF-3 frequencies can be entered on this page and the active voice frequency altered by touching TRANSFER (similar to a dual head radio).

The CHANGE MODE will toggle from VOICE to DATA mode and invoke the

VHF CNTRL page.

H H

M M

V HF VO I C E N R

C H A N G E M O DE

T R A N S F E R

F R E Q

N N N

N N < N

F R E Q

N N

INDX

LGHT

5.23.48 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

7500 RPT

This prompt supplies the crew a way to report a hijacking emergency. As you can see below, the prompts are displayed backwards to confuse any understanding by the hijackers. The SEND prompt appears immediately to allow transmittal of the message with no other data entries required. The 7500

Page will remain (even after SEND is selected) until the crew selects RETURN.

Do not send this message unless the situation warrants it. This screen is active and Flight Control will respond accordingly.

H H

M M

E L A M

P A E

A A A

T P C N I

A A A

]

PR I N T

7 5 0 0 RPT

INDX

M E F

P M E T

A A A A

T A E S

S E ND

]

LGHT

The list below provides an explanation of each prompt:

ELAM

PAEW

TPCNI

MEF

PMET

TAES

Number of males?

Are weapons involved?

SEY (Yes) or ON (No) - Toggle Selection.

Are the hijackers in the cockpit?

SEY (Yes) or ON (No) - Toggle Selection.

Number of females?

Temperament: - unknown. - calm. - intense.

NKNU - unknown.

MLAC - calm.

NTNI - intense.

(Toggle selection)

Seat numbers of hijackers, if known.

April 01, 2004 5.23.49

Communications -

ACARS 501

MD-88/90 Operations Manual

ATC LOG

[NOT FUNCTIONAL AT THIS TIME]

H H

M M

A T C L O G

N N / N N

H H

M M A A A A

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M A A A A

A A A A

X X X X X X X X X X X X X X X X X X X X X X

H H

M M

A A A A

X X X X X X X X X X X X X X X X X X X X X X

INDX

PREV NEXT

LGHT

5.23.50 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

FLT LOG

Selection allows access to the FLT LOG pages. Information is included for present flight leg as well as the previous four flight legs. All data is entered automatically at event times. This page is automatically displayed after the OFF event if no pilot entry is in progress

H H

M M

F L T

- - - -

F L T L O G

N O

/ - -

/ D A T

E T A

- - : - -

E V T

O U T

O F F

O N

PR I N T

T I M E

- - : - -

- - :

- -

N / 5

O R I G

- - - -

/ D E S T

- - - -

- - :

B L K

- - :

T M

F O B

- - -

U N

INDX PREV NEXT LGHT

April 01, 2004 5.23.51

Communications -

ACARS 501

MD-88/90 Operations Manual

DOWNLINKS

This prompt allows access to the menu items displayed below. Selection is available on the DATA LINK INDEX page as well as the EN ROUTE page.

H H

M M

D O W L I N K S

M TC CO ORD

C A L SEL

F L T CT RL

O T H ER

ENG I NE RP T

R ETU R N

INDX

LGHT

5.23.52 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

MTC COORD

Selection allows access to MTC COORD page. This message will be sent to the

ATL Technical Management Center with a copy to Flight Control. Enter text in the text fields or enter a FRM code to get send prompt.

]

H H

M M

FRM/FIM/CDL/ CODE

/ /

C L R T E X T

E D I T T E X T

PR I N T

INDX

S E ND

]

LGHT

The FRM/FIM code must be input in the free text block. Do not use the

FRM/FIM code field. A detailed discussion of the required entry procedure is provided in the Fault Reporting Manual, provided on-board the aircraft.

April 01, 2004 5.23.53

Communications -

ACARS 501

MD-88/90 Operations Manual

CALSEL

[NOT FUNCTIONAL AT THIS TIME]

H H

M M

WH O

A A A A A A

C A L S

A A

E L

M E D

A A A

I U M

S T A T U S

A A A A A A A A

A A

U B

A A

E C T

A A A

V H F

H F

F R E Q

S A T

C H A N

A A A A

S E ND

INDX

LGHT

WHO

MEDIUM

STATUS

DISPATCH

TMC

FLT OPS

RADIO

(Toggle selection)

VHF

SAT

(Toggle selection)

ROUTINE

PRIORITY

(Toggle selection)

Continued on Next Page

5.23.54 April 01, 2004

SUBJECT

VHF FREQ

SAT CHAN

MD-88/90 Operations Manual

ALTN

REROUTE

ACS

METRO

If the WHO is TMC:

AVIONICS

SYSTEMS

(Toggle selection)

Frequency to call back on.

AORW

AORE

POR

IOR

Communications -

ACARS 501

April 01, 2004 5.23.55

Communications -

ACARS 501

MD-88/90 Operations Manual

ENGINE RPT

Selection allows access to the ENGINE RPT page.

H H

M M

AUT O RQ

I E R P T

A A A AA A A A AA

R E U

INDX

LGHT

AUTO RQ

STATUS

MANUAL

Selection causes an automatic engine report to be generated and sent to ground station when in communication.

INACTIVE

REQUESTING

ACCEPTED

NO DATA

INACTIVE

Used to enter engine data manually should the automatic feature be inoperative.

NOTE: Engine data is sent automatically. Do not use AUTO RQ unless requested by Maintenance or Flight Control.

5.23.56 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

FLT CTRL

Selection allows access to the FLT CTRL communications page. This downlink is automatically routed to the correct dispatcher.

]

H H

M M

F L T C T RL

PR I N T

U N

INDX

E D I T T E X T

]

S E ND

LGHT

April 01, 2004 5.23.57

Communications -

ACARS 501

MD-88/90 Operations Manual

OTHER

Selection allows access to OTHER communications page.

H H

M M O T H E R

A D DR E S S

]

PR I N T

INDX

E D I T T E X T

S E ND

]

LGHT

The address should be the teletype address used to route the downlink.

NOTE: Game score requests can be sent via the OTHER page. Use the address ATLXGDL for game day listings, and place appropriate information in the EDIT TEXT field.

5.23.58 April 01, 2004

Communications -

ACARS 501

MD-88/90 Operations Manual

MSGS RCVD

Selection allows access to the MSGS RCVD pages and is available on the DATA

LINK INDEX page.

STAT

H H

M M MS GS R C V D

H H

M M

MS G 1 T I T L E

H H

M M

MS G 2 T I T L E

H H

M M

MS G 3 T I T L E

H H

M M

MS G 4 T I T L E

H H

M M

MS G 5 T I T L E

U N

INDX PREV NEXT

0 1 / N N

S T A T

A A A

LGHT

Status

NEW

OLD

April 01, 2004 5.23.59

Communications -

ACARS 501

MD-88/90 Operations Manual

SELCAL

SELCAL advisory displayed on control screen along with chime and light on radio panel. Selection provides access to SELCAL page.

H H

M M

S E L C A L

V O I CE F R E QU E N CY

N N

VO I CE MOD E

INDX

LGHT

5.23.60 April 01, 2004

MD-88/90 Operations Manual

501 Touchscreen (Quick Reference)

Communications -

ACARS 501

April 01, 2004 5.23.61

Communications -

ACARS 501

MD-88/90 Operations Manual

Intentionally

Blank

5.23.62 April 01, 2004

MD-88/90 Operations Manual

Communications

Chapter 5 MD-90 Differences Section 90

System Description

ACARS Automatic Messages

After attaining a stable cruise condition, the flight data acquisition unit will collect engine data and automatically transmit this data via ACARS.

Additionally, ACARS will collect present position, time, weather, and engine exceedance reports and automatically transmit this data. These functions are transparent to the flight crew.

April 01, 2004 5.90.1

Communications -

MD-90 Differences

MD-88/90 Operations Manual

Intentionally

Blank

5.90.2 April 01, 2004

Electrical

MD-88/90 Operations Manual

Chapter 6

Section 0

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.10.1

Overhead Electrical Panel Controls and Indicators . . . . . . . . . . 6.10.2

Electrical Power Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.10.4

System Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.1

General. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.1

AC Power Generating System . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.2

AC Power Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.2

DC Power Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.3

Batteries . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.4

Battery Charger . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.4

Emergency AC and DC Power . . . . . . . . . . . . . . . . . . . . . . . . . 6.20.5

OAP Messages/Lights. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.30.1

OAP Messages/Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.30.1

Red Warning Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.30.1

Amber Caution Messages. . . . . . . . . . . . . . . . . . . . . . . . . . . 6.30.1

Functional Schematic. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.40.1

MD-88 Power Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.40.2

Circuit Breaker Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.50.1

Circuit Breaker Locations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.50.1

MD-90 Differences . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.1

Controls and Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.1

Electrical Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.2

Electrical Power Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.4

Ground Service Electrical Power Control Panel . . . . . . . . . 6.90.6

Emergency Power Selector and Battery Switch . . . . . . . . . . 6.90.7

System Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.8

April 01, 2004

6.TOC.0.1

Electrical -

Table of Contents

MD-88/90 Operations Manual

General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.8

AC Generation and Control . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.8

AC Power Distribution . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.9

Auxiliary Power. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.9

External Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.9

DC Generation and Control. . . . . . . . . . . . . . . . . . . . . . . . 6.90.10

Emergency DC and AC Power Supply . . . . . . . . . . . . . . . 6.90.10

Ground Service Bus. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.11

OAP Messages/Lights. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.12

Amber Caution Messages . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.12

Functional Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.90.13

MD-90 Power Distribution . . . . . . . . . . . . . . . . . . . . . . . . 6.90.13

6.TOC.0.2

April 01, 2004

MD-88/90 Operations Manual

Electrical

Controls and Indicators

Chapter 6

Section 10

Intentionally

Blank

April 01, 2004

6.10.1

Electrical -

Controls and Indicators

MD-88/90 Operations Manual

Overhead Electrical Panel Controls and Indicators

GROUND SERVICE ELEC PWR

APU PWR

OFF

APU

PWR

AVAIL

GROUND

SERVICE

BUS

EXT PWR

OFF

EXT

PWR

AVAIL

100

AMPS

VOLTS

100

DC BUS X TIE

CLOSE

OPEN

1.5

1.0

LOAD

1.5

1.0

EMER PWR

OFF ON

EMER

PWR

IN USE

OFF

BATT

8 9

OVERHEAD PANEL

10 11

JB1-3-0853

APU PWR Switch

OFF - Removes APU generator from ground service bus.

ON - Selects APU generator to ground service bus. (EXT PWR switch must be OFF)

Ground Service Bus Power In Use Light (2) (blue)

Indicates power source selected is connected to ground service bus.

6.10.2

April 01, 2004

Electrical -

Controls and Indicators

MD-88/90 Operations Manual

APU PWR AVAIL Light (blue)

Indicates APU generator power is available.

EXT PWR AVAIL Light (blue)

Indicates external power is available.

EXT PWR Switch

OFF - Removes external power from ground service bus.

ON - Selects external power to ground service bus (APU PWR switch must be OFF).

DC VOLT/AMPS Meter

Indicates DC voltage when indicator selector is selected to BATT VOLT or

L/R. Indicates DC current in amps to or from batteries when BATT AMP is selected.

DC BUS X TIE Switch

CLOSE - Closes DC cross-tie relay and connects the left and right DC buses.

Supplies DC power from one side to the other in case both transformer rectifiers fail on either the left or right system.

OPEN - (Normal position) Left and right DC buses are isolated.

L/R DC LOAD Meter

Dual scale, one for each of the four transformer rectifiers (TR). Indicates current output proportional to TR rating, 1.0 is 100 percent.

EMER PWR Switch

OFF - Removes batteries as source of emergency power.

ON - Connects batteries as source of emergency AC and DC power. Power to

DC emergency bus is now supplied from battery direct bus. AC power is supplied to AC emergency bus by emergency inverter. Inverter is powered from battery direct bus, standby lights illuminate.

10.

EMER PWR IN USE Light (white)

Indicates emergency power is on.

11.

BATT Switch (Pull And Twist To Lock On)

OFF - Removes batteries from battery bus, battery charger, and DC transfer bus.

ON - Connects battery direct bus to battery bus. Selects batteries to battery charger, and DC transfer bus. White line, positioned horizontally, indicates locked.

April 01, 2004

6.10.3

Electrical -

Controls and Indicators

MD-88/90 Operations Manual

Electrical Power Panel

2 3

ELEC PWR

RISE

100

140

CSD

DISC

100

AC VOLTS

150

20 180

TEMP

L PUSH FOR RISE

CSD TEMP

APU GEN

RESET

NORM

OFF

R GEN

RESET

1.0

.25

AC LOAD

1.5

EXT

PWR

VOLT/FREQ

APU

AC VOLT/FREQ

DC BUS VOLT

L R

BATT

VOLT

BATT

AMP

380

400

420

FREQUENCY

OPS

APU

PWR

AVAIL

APU R BUS

OFF

R AC

BUS

EXT

PWR

AVAIL

AC BUS X TIE

OPEN

AUTO

EXT PWR

R BUS

OFF

OVERHEAD PANEL

JB1-3-0854

L/R CSD OIL TEMPERATURE Gauge

Indicates CSD oil outlet temperature or oil temperature rise across the drive.

L/R CSD DISCONNECT Switch

NORM - Guarded switch normally in this position.

DISC - (Momentary) Disconnects CSD from engine drive.

AC VOLTS Meter

Indicates voltage output of generators or external power.

FREQUENCY Meter

Indicates frequency output of generator or external power in cycles per second.

6.10.4

April 01, 2004

Electrical -

Controls and Indicators

MD-88/90 Operations Manual

CSD TEMP PUSH FOR RISE Button

When pushed, temperature rise (outlet temperature minus inlet temperature) is displayed on outer scale of indicator.

APU GEN Switch

RESET - (Momentary) Resets generator control circuit.

NORM - For normal operation.

Indicator Selector Switch

APU or EXT PWR - Selects AC voltage on AC VOLTS meter and frequency on FREQUENCY CPS meter.

L/R - Selects AC voltage on AC VOLTS meter and frequency on

FREQUENCY CPS meter. Also selects DC bus voltage on DC VOLTS meter.

BATT VOLT - Selects DC voltage of batteries on DC VOLTS meter.

BATT AMP - Selects DC current in amps to or from batteries on DC VOLTS meter.

L/R GEN Switch

RESET - (Momentary) Resets generator control circuit.

OFF - Disconnects generator from AC power distribution system.

ON - Connects generator to AC power distribution system.

A/C LOAD Meter

Indicates load each AC generator is delivering to distribution system.

Indicates from 0 to 1.5 with 1.0 indicating 100% of generator rated capacity.

10.

APU PWR AVAIL Light (blue)

Indicates APU power is available.

11.

EXT PWR AVAIL Light (blue)

Indicates external power is available.

12.

L/R APU BUS Switch

OFF - Removes APU power from respective buses.

ON - Selects APU power to respective buses.

13.

POWER IN USE Light (blue)

Indicates selected power source is connected to respective bus.

April 01, 2004

6.10.5

Electrical -

Controls and Indicators

MD-88/90 Operations Manual

14.

L/R EXT PWR BUS Switch

OFF - Removes external power from respective buses.

ON - Selects external power to respective buses.

15.

A/C BUS X TIE Switch

OPEN - Opens AC crosstie relay, isolates left and right generator buses.

Prevents closing of relay.

AUTO - The AC crosstie relay will operate automatically.

NOTE: Under certain fault conditions, AC crosstie relay will lock open.

6.10.6

April 01, 2004

Electrical

System Description

MD-88/90 Operations Manual

Chapter 6

Section 20 General

The airplane electrical power system consists of a 115 volt, 3-phase, 400 Hz, constant-frequency alternating current (AC) system and a 28-volt direct current

(DC) system.

For instrument bus power, 115 volt single phase AC power from the AC buses is reduced to 28 volt AC power by step down transformers.

Battery power can be used for a portion of the DC distribution system when the main DC power distribution system is not powered. Power for APU control and starting is supplied by the aircraft batteries. Battery power will also supply power for engine ignition and indication when the main power distribution system is not powered.

An emergency inverter, powered from the battery direct bus when the EMER

PWR switch is ON, supplies single phase 115 volt, 400 hz AC power to the emergency AC bus. If normal AC power is unavailable, selecting the

IGNITION switch to A, B, BOTH (with FUEL CONTROL lever and

BATTERY Switch ON), or OVERRIDE also powers the emergency inverter.

During ground refueling operation, the emergency inverter will supply fuel indicator power when normal electrical power is not available.

A battery charger, powered by the ground service bus, maintains the batteries in a fully charged condition. For a fully operational battery charger, the BATT switch must be ON with the EMER PWR switch OFF.

April 01, 2004

6.20.1

Electrical -

System Description

MD-88/90 Operations Manual

AC Power Generating System

The APU generator is mounted directly on the APU and is driven at a constant speed by the APU governing system. It is capable of supplying sufficient power for operation of electrical systems.

Each engine generator is capable of supplying sufficient power for operation of electrical systems.

Each engine driven generator is driven through a constant speed drive (CSD). The

CSD's maintain a constant voltage and frequency output from the generators regardless of varying engine speeds and electrical loads.

An oil indicating system for each CSD shows the oil outlet temperature and the oil temperature rise across the drive. The rise indication is used primarily for maintenance evaluation and is not normally used by the cockpit crew. Each CSD has a disconnect switch which will uncouple the CSD from the engine if required.

Once disconnected, a CSD can only be reengaged manually at the engine, after engine shutdown.

Fault protection is incorporated in each generator control circuit to automatically remove the generator from its bus and de-energize the generator in the event of certain circuit malfunctions. Pulling the ENG FIRE handle also de-energizes the generator. The generator may be restored to operation by the reset function of the

L or R GEN (generator) switch when the malfunction is corrected (ENG FIRE handle must be reset first, if pulled).

AC Power Distribution

The AC power distribution system is divided into left and right independent systems with crosstie capabilities. Engine driven generators supply power directly to their respective generator bus for distribution. Power from the APU generator may be selected to either or both generator buses, or directly to the ground service bus. When desired, all buses may be energized through an external power receptacle.

Each generator bus supplies heavy load items such as galley power, air conditioning cooling fans and wing heater blankets. They also supply subordinate left and right AC buses respectively. The right generator bus also supplies the ground service bus. The left generator bus also powers the primary trim motor and the auxiliary hydraulic pump.

6.20.2

April 01, 2004

Electrical -

System Description

MD-88/90 Operations Manual

The ground service bus provides power to only those circuits necessary for ground servicing. If the right engine generator is not powering the right generator bus, external power or the APU generator may provide power for this bus. The ground service bus supplies power to the battery charger and the right #2 TR. When the right generator bus is powered, the ground service bus functions as a part of the right AC distribution system, receiving power directly from the right generator bus.

There is a priority control of the AC power distribution system. The order of operation is as follows.

• Respective engine driven generator.

• APU generator.

• External power.

• Opposite generator (crosstie).

The deselection of a generator, for any reason other than a fault on its generator bus, automatically transfers the load from that generator to the remaining operating generator, through the AC crosstie relay. The AC Crosstie system attempts to use 2 aircraft generators if possible. The AC Crosstie system has 3 functions:

• Prevents paralleling.

• Powers unpowered generator bus.

• Isolates generator bus faults.

Should a generator become inoperative because of a fault on its own bus, or due to fault protection, the AC crosstie relay locks open, isolating that bus from the rest of the system. Items connected to the bus will remain deenergized until the fault is cleared. Electrical loads on the other generator are not affected. Galley power is shed when the AC crosstie relay is closed and regained when at least two generators are operating.

The #3 galley power is also shed if the overwing heater blankets are energized and the aircraft is operating from a single power source such as the APU or external power.

DC Power Distribution

The function of the DC power distribution system is similar to the AC system in that the right and left systems function independently. The DC system has manual crosstie capability in the event of a failure of either system. In addition to the left and right systems, DC power can be supplied by the batteries.

April 01, 2004

6.20.3

Electrical -

System Description

MD-88/90 Operations Manual

Power is supplied to the left DC system by two TR's, both receiving power from the left AC bus. In the right system, the #1 TR is powered from the right AC bus, and the #2 TR is powered from the ground service bus. When the ground service bus is receiving power from the generator bus, the two TR's are connected through the DC ground service tie relay to supply power to the right DC bus. When the ground service bus is powered directly from either external power or the APU generator, the right #1 TR is isolated and only the right #2 TR supplies power to the DC transfer bus.

The DC bus crosstie differs from the AC bus crosstie in that the DC bus crosstie is not automatic and must be operated manually. In addition to supplying power to the respective DC buses, the TR's supply power to the emergency DC bus, and the DC transfer bus. The DC crosstie system incorporates a built-in fuse to protect either the left or right side should a fault exist when attempting to crosstie.

Batteries

Two 14 volt batteries, connected in series, supply DC power to the battery direct bus regardless of BATT switch position. When the BATT switch is positioned to

ON, the battery bus is powered. When no other source of power is available, the

DC transfer bus is powered by the batteries with the BATT switch ON.

Battery Charger

The battery charger will operate when:

• BATT switch is ON.

• EMER PWR switch is OFF.

• Ground service bus is powered.

When the battery is fully charged, the battery charger will be in a pulsating mode.

If the battery is in a low state of charge, the ammeter will indicate approximately

40 amperes and transition into a pulsating mode as the batteries becomes fully charged. Pulse intervals will range from 5 seconds to 30 minutes.

NOTE: Some aircraft have pulse chargers which cycle the ammeter to the left and back to zero until the battery is fully charged. Others have constant current chargers which show a steady charge until the battery is fully charged.

6.20.4

April 01, 2004

Electrical -

System Description

MD-88/90 Operations Manual

Emergency AC and DC Power

During normal operation, the emergency AC bus receives power from the left AC bus, and the emergency DC bus receives power from the left DC bus. Loss of power to the left generator bus will transfer the emergency AC bus to the right AC bus, and the emergency DC bus to the right DC bus.

In the event of complete loss of power, the ship's batteries will provide both AC and DC emergency power when the EMER PWR switch is ON. The DC emergency bus will be powered from the battery direct bus, which will also power the emergency inverter to provide power to essential equipment for approximately

30 minutes. When emergency electrical power is in use, the battery charger is not available.

April 01, 2004

6.20.5

Electrical -

System Description

MD-88/90 Operations Manual

Intentionally

Blank

6.20.6

April 01, 2004

MD-88/90 Operations Manual

Electrical

OAP Messages/Lights

Chapter 6

Section 30 OAP Messages/Lights

Red Warning Lights

AC EMER BUS OFF - Indicates emergency AC bus is not powered.

MASTER WARNING lights illuminate.

DC EMER BUS OFF - Indicates emergency DC bus is not powered.

MASTER WARNING lights illuminate.

Amber Caution Messages

NOTE:

The associated cue light is shown in parenthesis (XXX) following the message.

AC CROSSTIE LOCKOUT (ELEC) - Indicates AC crosstie relay is locked open and automatic AC crosstie is inoperative.

APU GEN OFF (ELEC) - Indicates the APU generator power is available but not selected. MASTER CAUTION lights illuminate.

DC BUS OFF (ELEC) - Indicates a DC bus is de-energized. MASTER

CAUTION lights illuminate.

DC XFER BUS OFF (ELEC) - Indicates DC transfer bus is de-energized.

L/R AC BUS OFF (ELEC) - Indicates the respective AC bus is not powered. MASTER CAUTION lights illuminate.

L/R CSD OIL PRESS LOW (ELEC) - Indicates oil pressure in left/right

CSD is below operating limits. MASTER CAUTION lights illuminate.

L/R GEN OFF (ELEC) - Indicates the respective generator relay is open, disconnecting generator from its bus. MASTER CAUTION lights illuminate.

NO ELEC FAULTS (ELEC) - Illuminates when ELEC cue light is pushed if no electrical system faults exist.

April 01, 2004

6.30.1

Electrical -

OAP Messages/Lights

MD-88/90 Operations Manual

Intentionally

Blank

6.30.2

April 01, 2004

MD-88/90 Operations Manual

Electrical

Functional Schematic

Chapter 6

Section 40

Intentionally

Blank

April 01, 2004 6.40.1

Electrical -

Functional Schematic

MD-88/90 Operations Manual

MD-88 Power Distribution

6.40.2 April 01, 2004

MD-88/90 Operations Manual

Electrical -

Functional Schematic

April 01, 2004 6.40.3

Electrical -

Functional Schematic

MD-88/90 Operations Manual

Intentionally

Blank

6.40.4 April 01, 2004

MD-88/90 Operations Manual

Electrical

Circuit Breaker Locations

Chapter 6

Section 50

A 1* to D 21*

A 1 to Z 42

Lt GB

Rt GB

L CON

C, or F CON

STEP

E & E

EXT

CABIN

COCKPIT OVERHEAD C/B PANEL

ELECTRICAL POWER CENTER (BEHIND

CAPTAIN)

LEFT GENERATOR BUS

RIGHT GENERATOR BUS

LEFT CONSOLE (CAPTAIN’S LEFT SIDEWALL)

CAPTAIN, OR F/O CONSOLE (FORWARD OF

FLIGHT KITS)

FLIGHT DECK STEP

E & E COMPARTMENT

EXTERNAL POWER PANEL

VARIOUS CABIN LOCATIONS

BUS CIRCUIT BREAKER

AC Bus, Left

AC Bus, Right

AC Bus Sensing, Left

AC Bus Sensing, Right

AC Bus Sensing, EPCU, Left

AC Bus Sensing, EPCU, Right

AC Bus Warning Lights, Left

AC Bus Warning Lights, Right

ACARS

ACARS Aux Unit

ACARS Datalink IDU

ACARS Datalink DC

ACARS Datalink MU

ACARS Printer

ACU-1

ACU-2

ACU-1 Excitation

88

Lt GB

Rt GB

Lt GB

Rt GB

CB REF

90

Lt GB

Rt GB

Lt GB

Rt GB

Lt GB

Rt GB

X40

X39

F18

F22

F26

B18*

B18* & F25

F18

F14

B19*

F23

S42

R37

A7*

GENERATOR

DC TRANSFER

LEFT RADIO AC

BATT DIR

LEFT RADIO AC

DC TRANSFER

RIGHT DC

EMERGENCY AC

April 01, 2004

6.50.1

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

ACU-2 Excitation

ACU Battery-1

ACU Battery-2

ADF-1

ADF-2

Air Cond Auto Shutoff

Air Cond Flow Valve, Left

Air Cond Flow Valve, Right

Air Cond Purging Relay

Air Cond Reg Valve, Left

Air Cond Reg Valve, Right

Air Cond Turbine Nozzle

Air Data Computer-1

Air Data Computer-2

Air Data Switching Unit

Airfoil Advisory

Airfoil Ice Prot, Auto

Airfoil Ice Prot Control, Left

Airfoil Ice Prot, Control, Right

Airfoil Ice Prot, Tail, Timer

Air Fone

Airspeed, Capt

Airspeed, F/O

Alternate Fuel Burn

Altimeter, Capt

Altimeter, F/O

Altitude Alert

Altitude Alert, Capt

Altitude Alert, F/O

Altitude Bias Control, Left

Altitude Bias Control, Right

Angle Of Attack Heater, Left

CIRCUIT BREAKER

88 CB REF

M37

A3*

R38

G15

N30

N31

L29

A5*

C10*

M21

N29

M30

S25

X34

C1*

F12

C14*

C15*

U28

T25

E17

D12

U28

D19*

D21*

F24

90

R38

G15

U24

X22

M30

N30

N31

D16

A5*

M37

A3*

B13*

B14*

X34

C1*

F12

C9*

M21

N29

C15 & F24

E17

C6 & D 12

U28

C13*

C14*

U28

X22

BUS

EMERGENCY DC

LEFT DC

RIGHT DC

LEFT DC

RIGHT DC

LEFT RADIO AC

EMERGENCY AC

RIGHT RADIO

LEFT DC

EMERGENCY AC

RIGHT RADIO

RIGHT DC

LEFT RADIO DC

RIGHT RADIO DC

LEFT DC

RIGHT DC

LEFT AC

RIGHT INST

LEFT RADIO DC

RIGHT RADIO DC

LEFT RADIO AC

LEFT RADIO DC

RIGHT RADIO AC

RIGHT RADIO DC

LEFT DC

EMERGENCY DC

LEFT DC

EMERGENCY DC

DC TRANSFER

EMERGENCY AC

RIGHT RADIO AC

6.50.2

April 01, 2004

MD-88/90 Operations Manual

CIRCUIT BREAKER

88

Angle of Attack Heater, Right Z22

Annunciator Lights, Spare, Test N35

Annunciator Panel

U35

U34

Annunciator Panel

Anti-Collision Light, Lower

Anti-Collision Light, Upper

Anti-Fog, CAPT, F/O, CTR

T24

K11

L11

X26

Anti-Fog, Clearview & Eyebrow Z26

Anti-Fog, Clearview, Control Z25

Anti-Ice Valve Caution, Left

Anti-Ice Valve Caution, Right

S37

T37

Anti-Icing Valve, Left Cowl

Anti-Icing Valve, Left Engine

Anti-Icing Valve, Right Cowl

K30

K32

K31

L30

Anti-Icing Valve, Right Engine

Anti-Skid Power, Inboard

Anti-Skid Power, Outboard

Anti-Skid, Test

Approach Idle Control

APU Control

APU Door Control U39

APU Fire Central Aural Warning W33

APU Fire Warning Horn

APU Left Engine Start

W34

APU Maintenance Light

APU Power

APU Starter

APU Tach

ART Solenoid, Left

ART Solenoid, Right

E & E

A21* or

B19*

X32

Z32

L32

L31

P40

R40

A12

R41

S40

B21*

CB REF

Z22

N35

U35

S33

T33

P40

T38

R41

T24

K11

L11

X26

Z26

Z25

90

B22*

U39

W33

W34

U32

C19*

E & E

A22*

April 01, 2004

Electrical -

Circuit Breaker Locations

BUS

RIGHT AC

RIGHT DC

DC TRANSFER

RIGHT DC

LEFT AC

RIGHT AC

LEFT AC

RIGHT AC

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

LEFT DC

RIGHT DC

LEFT INST

RIGHT DC

LEFT DC

BATTERY

DC TRANSFER

BATTERY

MISCELLANEOUS

BATTERY

DC TRANSFER

6.50.3

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

ART Status Lights

ATC-1

ATC-2

Audio Control

Auto Brake Annunciation

Auto Slat Extend

Autobrake System

Autoland Light Retract

Autopilot and Alt Long Trim

Autopilot - 1

Autopilot - 2

Autopilot OFF Lights

Autothrottle - 1

Autothrottle - 2

Autothrottle OFF Lights

Aux Hydraulic Pump

Aux Hydraulic Pump Control

Battery Backup Bus

Battery Backup Bus EPCU

Battery Bus OFF

Battery Charger

Battery Direct Bus Feed

Battery Relay

Bleed Air Filter

Boarding Music

Brake Pressure, Left

Brake Pressure, Right

Brake Temp Indicator

CIRCUIT BREAKER CB REF BUS

88 90

W32

D13

E13

D13

E13

DC TRANSFER

LEFT RADIO AC

LEFT RADIO DC

RIGHT RADIO AC

R30

R36

P30

D10

D11

E24

E12

G19

R30

R36

P30

M35

D10

D11

E24

E12

RIGHT RADIO DC

LEFT RADIO AC

RIGHT DC

LEFT DC

RIGHT RADIO AC

LEFT RADIO DC

RIGHT RADIO DC

W31 & Z31 W31 & Z31 DC TRANSFER

D18

E18

C16

E18

LEFT RADIO AC

LEFT RADIO DC

H17

RIGHT RADIO DC

RIGHT RADIO AC

W31 & Z31 W31 & Z31 DC TRANSFER

Lt GB Lt GB GENERATOR BUS

H17

C20*

LEFT AC

BATTERY

L Con

STEP

C17*

U25

B20*

B21*

L Con

D17*

C18*

U25

B4*

B11

BATTERY BUS

BATTERY

GROUND SERVICE

MISCELLANEOUS

BATT DIR

LEFT DC

EMERGENCY AC

LEFT INST B11

P25

RIGHT INST

LEFT DC

6.50.4

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

Bus Out Light, DC Transfer

Bus Out Light, Emergency AC

Bus Out Light, Emergency DC

Bus Tie, Left

C21*

C19*

Bus Tie, Right

Cabin Altitude Warning

Cabin Interphone

Cabin Low Pressure Warning

P38

W21

Cabin Manual Temp Ctrl

Cabin Medical Outlet (2)

Cabin Oxygen Light

Cabin Pressure Chime

Cabin Pressure Control-1

Cabin Pressure Control-2

Cabin Standby Lights

Cabin Temp

Cabin Temp Ctrl

CADC 1

CADC 2

CADC Switching Unit

CADC Switched Light

Call System (chime)

Cargo Compt Heater (Fwd)

L Con

U30

P23

U22

W22

A13*

W27

C1*

F12

C9*

G17

P37

J14

J12

J13

Cargo Compt Heater Fan (Mid) H13

Cargo Compt Heater Fan (Mid) H14

Cargo Compt Heater Fan (Mid) H12

Cargo Fire Aural Alert

Cargo Fire Left Bus Supply

R33

P36

Cargo Fire Right Bus Supply

CAWS Ovspd, Eng Fire, Stab

R37

U31

88 CB REF

H11

H12

P27

P29

J14

J12

J13

H13

R40

U31

F12

G17

P37

A14*

W27

C1*

LCon

U30

P23

U22

W22

X37

C22*

C21*

S40

T39

P38

W21

90 BUS

EMERGENCY DC

RIGHT DC

RIGHT AC

EMERGENCY AC

RIGHT RADIO AC

EMERGENCY DC

LEFT RADIO DC

LEFT DC

RIGHT AC

LEFT AC

RIGHT DC

LEFT DC

RIGHT DC

DC TRANSFER

BATTERY

LEFT DC

DC TRANSFER

LEFT DC

RIGHT RADIO DC

RIGHT DC

EMERGENCY AC

GROUND SERVICE

LEFT DC

LEFT AC

RIGHT AC

RIGHT DC

April 01, 2004

6.50.5

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER CB REF

88 90

CAWS SSRS-2 Alt Alert

CAWS Ldg Gr, T/O, A/P, SB,

Cab Alt

R38

P38

Charger and Transfer Relay C16*

Charger and XFER Bus Interlock L Con

Charger Relay Control

Clock, Electronic

N38

B17*

Clocks

Cockpit Door Unlock

Cockpit Voice Recorder

Course and Heading, Capt

Course and Heading, F/O

CSD Disconnect, Left

CSD Disconnect, Right

CSD Oil Temp, Left

T26

S26

S25

S38

P24

A1*

CSD Oil Temp, Right

Data Link DC

Data Link IDU

Data Link MU

Data Link Printer

DC Bus Cross Tie Control

DC Bus Off Sensing

DC Transfer Bus Feed

DC Trans Bus Feed (Bat)

DC Transfer Bus Sensing

DC Voltmeter, Left

DC Voltmeter, Right

DCAS, Capt

DCAS, F/O

DCAS, Obsv. 1

DCAS, Obsv. 2

Dead Bus Slave Relays, Left

Dead Bus Slave Relays, Right

DFDAU

DFG, Switch A

T25

B18*

F26

B19*

F14

B18* & F25 F18

F18

B11*

F23

B12*

R23

N36

E & E

X37

P22

R22

R23

N36

E & E

X37

P22

R22

S39

G12

T42

X40

X39

C17

R38

P38

S34

P24

A1*

C17*

L Con

N38

B18*

F22

C17

6.50.6

BUS

RIGHT DC

LEFT DC

BATT DIR

GROUND SERVICE

DC POWER FEED

BATT DIR

LEFT DC

RIGHT RADIO AC

EMERGENCY AC

RIGHT RADIO

RIGHT DC

LEFT DC

RIGHT DC

BATTERY DIR

LEFT RADIO AC

EMERGENCY DC

RIGHT DC POWER

DC POWER FEED

MISCELLANEOUS

DC TRANSFER

LEFT DC POWER

RIGHT DC POWER

LEFT DC

RIGHT RADIO AC

RIGHT RADIO DC

DC TRANSFER

LEFT RADIO AC

28 VAC

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

DFG, Switch B

DFG, Switch C

DFGC ALPHA-1

DFGC ALPHA-2

DFGC Flap Position-1

DFGC Flap Position-2

DFGC-1

DFGC-2

DFGS Light Control

Digital Audio System, CAPT

Digital Audio System, F/O

Digital Audio System, OBSV-1

Digital Audio System, OBSV-2

Digital Display, CAPT

Digital Display, Center

Digital Display, F/O

M32

N32

N33

Digital Display, Warn Lt & Tes N34

Digital Flight Guidance Sys-1

D20

E21

C11

L16

C10

C13

E20

D20

C18

C19

C12

Digital Flight Guidance Sys-1

Digital Flight Guidance Sys-2

DME-1

DME-2

Door Warning

E20

E21

D14

88 CB REF

90

C18

D14

R24

E20

E21

N32

N33

N34

D20

G12

T42

M32

L16

S39

E21

C11

E20

D20

C10

C12

C13

BUS

RIGHT AC

DC TRANSFER

RIGHT RADIO AC

RIGHT RADIO DC

DC TRANSFER

LEFT DC

RIGHT DC

LEFT RADIO AC

RIGHT RADIO DC

LEFT RADIO DC

RIGHT RADIO DC

RIGHT RADIO AC

LEFT RADIO A

RIGHT RADIO AC

RIGHT DC

28 VAC

LEFT RADIO

RIGHT RADIO

LEFT RADIO

RIGHT RADIO

LEFT RADIO DC

LEFT RADIO AC

RIGHT RADIO

LEFT RADIO

RIGHT RADIO

LEFT RADIO DC

LEFT RADIO

RIGHT RADIO AC

RIGHT RADIO DC

April 01, 2004

6.50.7

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

88

Drain Mast Heater, Aft

Drain Mast Heater, Fwd

Drain Mast Htr, Ann.

Drain Valve

EEC 1, Ch A

EEC 1, Ch B

EEC 1 Relay

EEC 2, Ch A

EEC 2, Ch B

EEC 2 Relay

EGT, Left

EGT, Right

Elevator Power On Advisory

ELFA-1

Z27

N27

X27

M27

LCon

B15*

X35

P27

ELFA-2

Emergency AC Bus Feed

Emergency AC Bus Feed-Alt

Emergency AC Bus Sensing

Emergency Bus Warning Light

Emergency DC Bus Feed

Emergency DC Bus Sensing

Emergency Inverter

C7*

Z40

N37

B12*

C18*

Emergency Lights Arm & Charge A14*

Emergency Lights Charging

Emergency Nav Instrument

XFMR

Z37

C4*

Emergency Power In Use Light A12*

EMER Power Auto Transfer

Reset

Engine Cooldown

Engine Inst Display Pnl, Left

Engine Inst Display Pnl, Right

X36

B15*, S34

X35

CB REF BUS

90

B13*

D13*

A15*

Z37

C5*

Z27

X27

M27

L Con

W32

X32

U41

B14 *

B15*

C9*

RIGHT AC

RIGHT DC

LEFT AC

LEFT DC

GROUND SERVICE

DC TRANSFER

EMERGENCY DC

B16*

X35

EMERGENCY DC

DC TRANSFER

T40

R33

C8*

Z40

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

EMERGENCY AC

DC TRANSFER

D15* or N37 DC POWER FEED

EMERGENCY DC

BATT DIR

EMERGENCY DC

DC TRANSFER

EMERGENCY AC

A13*

T37

X36

B16*, S32

X35

EMERGENCY DC

BATTERY

DC TRANSFER

LEFT DC

6.50.8

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Engine Fire Warning

Engine Start Switch, Left

Engine Start Switch, Right

Engine Sync

Engine Thrust, Ch A

Engine Vibration Monitor

EPCU Battery Backup Bus

EPR, Fuel Flow Display, Left

EPR, Fuel Flow Display, Right

EPR, Left (Transmitter)

EPR, Right (Transmitter)

External Power

External Power Control

External Power Relay

Fill Drain Valve Control

Fill Valve

Fire Agent Low Light

Fire Detectors, APU, Loop A

Fire Detectors, APU, Loop B

Fire Detectors, Left, Loop A

Fire Detectors, Left, Loop B

Fire Detectors, Right, Loop A

Fire Detectors, Right, Loop B

Fire Extinguishing, Bottle 1

Fire Extinguishing, Bottle 2

Fire Warning, APU, Aural

Fire Warning, Aural

Fire Warning Horn, APU

Fire Warning, Lights

Flap Position, Left

Flap Position, Right

Flight Display (PFD), CAPT

CIRCUIT BREAKER CB REF

88 90

C15*, T34

U31

C16*, T32

U31

U34

X39

T40

W38

X41

X42

W33

W41

W34

W42

A11

B4*

X36

C15*

C8*

L25

E & E

EXT

E & E

X38

S37

K30

B20*

X36

C16*

EXT

Z33

L Con

Z33

L Con

R26 or U32 R26

W35 W35

W36

W39

W40

W37

W36

W39

W40

W37

W38

X41

X42

W33

W41

W34

W42

A11

B7*

BUS

RIGHT DC

DC TRANSFER

RIGHT DC

DC TRANSFER

LEFT AC

BATTERY

DC TRANSFER

EMERGENCY DC

EMERGENCY AC

RIGHT AC

MISCELLANEOUS

DC TRANSFER

GROUND SERVICE

RIGHT DC

DC TRANSFER

LEFT INST

RIGHT INST

EMERGENCY AC

April 01, 2004

6.50.9

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Flight Display (PFD), F/O

Flight Guidance Status

Flight Interphone-1

Flight Interphone-2

Flight Recorder

Flush Motors/Vacuum Blowers

FMA/Mode Select, Capt

FMA/Mode Select, F/O

FMS Data Loader

FMS-1 CDU

FMS-1 Computer

FMS-2 CDU

FMS-2 Computer

FMS Switching

Fuel Boost Pump, CTR AFT

Fuel Boost Pump, CTR FWD

Fuel Boost Pump, LT AFT

Fuel Boost Pump, LT FWD

Fuel Boost Pump, RT AFT

Fuel Boost Pump, RT FWD

Fuel Filter Press Drop, Left

Fuel Filter Press Drop, Right

Fuel Flow, Left

Fuel Flow, Right

CIRCUIT BREAKER CB REF

88 90

D22

D21

F10

L Con

E19

H15

C14

G21

F21

F11

G25

A10*

T42

F11

A11*

G21

F21

J19

H19

S35

T35

J21

H21

H23

J23

K27 & X36 X36

L27 & C15* C16*

A12*

J21

H21

H23

J23

J19

H19

D22

D21

F10

L Con

E19

H15

Fuel Heat, Left, Control

Fuel Heat, Left, Timer

Fuel Heat ON, Left

Fuel Heat ON, Right

Fuel Heat, Right, Control

Fuel Heat, Right, Timer

Fuel Press, CTR Low Press

6.50.10

K28

K29

S36

T36

L28

L29

T41 T41

BUS

RIGHT RADIO AC

LEFT RADIO DC

EMERGENCY DC

DC TRANSFER

LEFT RADIO

LEFT RADIO DC

LEFT RADIO AC

RIGHT RADIO

GROUND SERVICE

LEFT RADIO DC

RIGHT RADIO DC

LEFT AC

LEFT RADIO AC

RIGHT RADIO AC

RIGHT AC

LEFT AC

RIGHT AC

GROUND SERVICE

LEFT AC

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC/

EMERG DC

LEFT AC

LEFT DC

RIGHT DC

RIGHT AC

DC TRANSFER

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Fuel Qty XFMR, Alternate

Fuel Quantity Power Transfer

Fuel Level Low

Fuel Shutoff Solenoid, Left

Fuel Shutoff Solenoid, Right

Fuel Switch, Left

Fuel Switch, Right

Galley Control

Galley-1 Power, Fwd

Galley-2 Power, Fwd

Galley-3 Power, Aft

Galley-4 Power, Aft

Generator Control, APU

Generator Control, Left

Generator Control, Right

GPS-1

GPS-2

GPWS Computer

GPWS Lights

GPWS Terrain Switching

Ground Air Cond Regulator

Ground Battery Control

Ground Control Relay, Left

Ground Control Relay, Right

Ground Refuel

Ground Refueling

Ground Service Bus Control

Ground Service Power

Handrail Lighting Controller

Heat Exchanger Fan, Left

Heat Exchanger Fan, Left, Ctrl

Heat Exchanger Fan, Right

Heat Exchanger Fan, Rt, Ctrl

CIRCUIT BREAKER

K33

L33

Z38

B16*

Rt GB

F20

G20

G11

U27

Lt GB

Rt GB

Lt GB

U36

U38

U37

H16

J17

88 CB REF

90

S41

U36

U38

U37

D18

Lt GB

Rt GB

Lt GB

J17

H14

S41

Z32

B11*

U42

X40

F20

G20

Lt GB

H11

Rt GB

J11

U27

A20*

K33

L33

Z38

B17*

Rt GB

P36

Lt GB

H10

Rt GB

J11

BUS

LEFT RADIO AC

RIGHT RADIO AC

LEFT RADIO AC

RIGHT RADIO DC

LEFT DC

BATTERY

LEFT AC

RIGHT AC

DC TRANSFER

BATT DIR

RIGHT AC

GENERATOR

LEFT DC

GENERATOR

LEFT AC

GENERATOR

RIGHT AC

LEFT AC

GROUND SERVICE

LEFT AC

DC TRANSFER

EMERGENCY DC

DC TRANSFER

RIGHT AC

GENERATOR

DC TRANSFER

April 01, 2004

6.50.11

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

Heater, Pneu. Pilot Valve, Left

Heater, Pneu. Pilot Valve, Right

Heater, Pri Trim Motor

Heater, Strake, Right

H10

Heater, Strake, Left

Horizontal Stabilizer Warning

Hydraulic Oil Quantity, Left

Hydraulic Oil Quantity, Right

Hydraulic Power Xfer, Ctrl

Hydraulic Press Low, Left

Hydraulic Press Low, Right

Hydraulic Pump, Aux

Hydraulic Pump, Aux Control

Hydraulic Pump Control, Left

U31

B12

R27

P28

R28

Lt GB

H17

S27

Hydraulic Pump Control, Right T27

Hydraulic System Press, Left

Hydraulic System Press, Right

B10

Ice Detection, Wing

Ice Protect Aug Valve, Left

Ice Protect Aug Valve, Right

Ice Protection System

Ignition A Advisory

Ignition B Advisory

Ignition, Left

Ignition, Right

M34

M23

N23

S32

T32

K26

L26

Ignitor, L1

Ignitor, L2

Ignitor, R1

Ignitor, R2

Inst Cooling Fan

Inst XFMR, Left

Inst XFMR, Right

Instrument Vibrator

Interphone

P31

A10*

88 CB REF

90

H17

S 2

T27

B10

R27

P28

R28

Lt GB

M34

K24

L24

Rt GB

Lt GB

U31

B12

C3*

P31

A11*

L26

B2*

C2*

B3*

L10

S31

T31

K26

BUS

RIGHT INST

LEFT DC

RIGHT DC

RIGHT AC

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

EMERGENCY AC

LEFT AC

RIGHT AC

LEFT DC

EMERGENCY DC

LEFT AC

RIGHT AC

LEFT AC

GENERATOR

DC TRANSFER

LEFT INST

RIGHT INST

RIGHT DC

LEFT DC

RIGHT DC

GENERATOR

LEFT AC

LEFT DC

RIGHT DC

LEFT INST

6.50.12

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

IRS - 1 Annun

IRS - 2 Annun

IRS 1 - BAT

IRS 2 - BAT

IRU 1

IRU 1 Synchro Excitation

IRU 2

Landing Gear Warning

Landing Gear Warning, Aural

Lavatory Smoke Detector

Lavatory Water Htr, Left, Aft

Lavatory Water Htr, Left, Fwd

Lavatory Water Htr, Right, Aft

Light Control, DFGS

Light Test

Lights, Bagrack

Lights, Briefcase

Lights, Cabin

Lights, Cabin, Standby

Lights, Cabin and Lavatory

Lights, CAPT Inst Panel

Lights, Cargo

Lights, Capt White Floods

Lights, Ceiling (3)

Lights, Cockpit White Floods

Lights, F/O Inst Panel

Lights, F/O White Floods

Lights, Galley Work

Lights, Ground Flood (2)

Lights, Handrail

Lights, Handrail Controller

Lights, Inst, Capt, Integral

Lights, Inst, F/O, Integral

Lights, Inst Panel, Fluorescent

CIRCUIT BREAKER

W29

Cabin

A13*

L Con

K15

L Con

A15*

L Con

Z39

L17

A15*

L Con

X28

X29

Z28

L16

F15

A6*

P26

P38

G18

E14

88 CB REF

90

E14

F15

C Con

F Con

L18

A16*

L Con

Z39

L17

A16*

L Con

L20

P36

C Con

F Con

L18

X38

L20

W29

Cabin

A14*

L Con

K15

L Con

X28

X29

Z28

L16

P26

P38

R34

BUS

RIGHT RADIO DC

LEFT RADIO DC

RIGHT RADIO DC

LEFT RADIO AC

EMERGENCY DC

RIGHT RADIO AC

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

DC TRANSFER

RIGHT AC

RIGHT DC

MISCELLANEOUS

EMERGENCY DC

GROUND SERVICE

LEFT AC

GROUND SERVICE

EMERGENCY DC

GROUND SERVICE

DC TRANSFER

RIGHT AC

EMERGENCY DC

GROUND SERVICE

RIGHT AC

LEFT DC

MISCELLANEOUS

RIGHT AC

April 01, 2004

6.50.13

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

88

Lights, Instrument Panel, CTR

Lights, Landing, Left Wing

Lights, Landing, Lt Wing, Ctrl

Lights, Landing, Nose, Left

K18

K12

K13

K14

Lights, Landing, Nose, Right

Lights, Landing, Right Wing

Lights, Landing, Rt Wing, Ctrl

Lights, Lavatory Mirror (3)

Lights, Map

Lights, Observer

Lights, Overhead Flood

Lights, Overhead Panel

Lights, Overhead Panel AFT

Lights, Overhead Panel FWD K16

Lights, Overhead Sw. Panel, Aft H29

M33

H29

H30

K17

L14

L12

L13

L Con

W29

Lights, Overhead Sw. Panel, Aft J29

Lights, Overhead Sw. Panel, Aft H30

Lights, Overhead Sw. Panel, Fwd J30

Lights, Overhead Sw. Panel, Fwd J31

Lights, Overhead Sw. Panel, Fwd J32

Lights, Panel, Integral, Ctr C Con

Lights, Panel, Integral, F/O

Lights, Passenger Entrance Str

F Con

L Con

Lights, Passenger Warning

Lights, Pax Reading, AFT

Lights, Pax Reading, CTR

Lights, Pax Reading FWD

Lights, Pedestal

Lights, Position

Lights, Reading

Lights Retract, Auto. Land

Lights, Sidewall (6/3)

Lights, Taxi, Nose, Left

K23

K22

K21

K20

K19

L Con

Cabin

M35

L Con

K14

CB REF

90

K23

K22

K21

K20

K19

L Con

Cabin

M35

L Con

K14

J29

H30

J30

J31

J32

C Con

F Con

L Con

H30

K17

K16

H29

W29

R29

M33

H29

K18

K12

K13

K14

L14

L12

L13

L Con

BUS

LEFT AC

RIGHT AC

GROUND SERVICE

RIGHT DC

LEFT DC

MISCELLANEOUS

LEFT AC

MISCELLANEOUS

GROUND SERVICE

LEFT AC

GROUND SERVICE

MISCELLANEOUS

LEFT DC

GROUND SERVICE

LEFT AC

6.50.14

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

Lights, Taxi, Nose, Right

Lights, Thunderstorm, Alt

Lights, Wheelwell & Utility

Outlet

L14

W28

L Con

Lights, White Flood, Capt

Lights, White Flood, F/O

A15*

Lights, Wing and Nacelle Flood L Con

Longitudinal Trim, A/P and Alt D11

Longitudinal Trim, A/P and Alt D10

Longitudinal Trim, A/P and Alt D9

Longitudinal Trim, Primary

Longitudinal Trim, Primary,

Brake

Lt GB

G23

G22 Longitudinal Trim, Primary,

Cntrl

Longitudinal Trim, Pri Mtr Htr

Mach Airspeed Ind, Capt

Mach Airspeed Ind, F/O

Mach Trim Inop Light

Mach Trim Override

Mach Trim-1

Mach Trim-2

Mag/True Annun

Marker Beacon

Master Caution

H10

A5*

U33

X33

G26

G12

A9*

Z42

Master Caution, Capt

Master Caution, F/O

Master Warning

Master Warning, Capt

Master Warning, F/O

N1 Gauge, Left

N2 Gauge, Left

N1 Gauge, Right

N2 Gauge, Right

Nav Display, Capt

Z41

B15*

X35

B3*

88 CB REF

90

L14

W28

L Con

G22

A5*

U33

A10*

Z42

T22

A16*

L Con

D11

D10

Lt GB

G23

Z41

T23

B16*

X35

B6*

BUS

RIGHT AC

MISCELLANEOUS

GROUND SERVICE

EMERGENCY DC

GROUND SERVICE

RIGHT RADIO AC

GENERATOR

LEFT RADIO DC

LEFT AC

EMERGENCY AC

RIGHT RADIO

DC TRANSFER

LEFT RADIO DC

RIGHT RADIO DC

EMERGENCY DC

RIGHT RADIO DC

DC TRANSFER

RIGHT DC

DC TRANSFER

RIGHT DC

EMERGENCY DC

DC TRANSFER

EMERGENCY AC

April 01, 2004

6.50.15

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER CB REF BUS

88 90

Nav Display, F/O

Nav Inst XFMR-1

Nav Inst XFMR-2

Oil Pressure, Left

F16

F13

A10

F16

F13

S21

RIGHT RADIO AC

LEFT RADIO AC

RIGHT RADIO AC

LEFT INST/DC

Oil Pressure, Right

Oil Quantity, Left

T21

S21

RIGHT INST/DC

LEFT DC

Oil Quantity, Right

Overheat Wheelwell Sensor

Overspeed Warning

Overwing Heater, Left

Overwing Heater, Right

Overwing Heater, Left Control

U21

U31

LTGB

RTGB

P29

Overwing Heater, Right Control R29

Oxygen Release, Passenger

Oxygen Release, Passenger, Alt

Parking Brake Control

Passenger Address

Passenger Music

Passenger Oxygen Control

Passenger Oxygen Control, Alt

Passenger Oxygen Release

Passenger Oxygen Release, Al

Passenger Warning Signs

K34

L34

M36

A8*

G19

F19

P32

R32

K34

L34

T21

U21

U31

K34 & P32

RIGHT DC

LEFT DC

DC TRANSFER

GENERATOR

LEFT DC

RIGHT DC

LEFT AC

L34 & R32 RIGHT AC

M36

A9*

G19

F19

P32

R32

K34

L34

LEFT DC

EMERGENCY DC

LEFT RADIO DC

LEFT RADIO AC

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

K23 & W30 W30 & K23 RIGHT DC

Pitot Heater, Aux

Pitot Heater, Capt

Pitot Heater, F/O

Pneumatic Pilot Valve Htr, Left

M28

C12*

N28

M28

C13*

N28

K24

LEFT DC

EMERGENCY DC

RIGHT DC

LEFT AC

Pneumatic Pilot Valve Htr, Right

Pneumatic Pressure

Pneumatic Pres. Reg/Shutoff

Valve, Left

Pneumatic Pres. Reg/Shutoff

Valve, Right

Pneumatic Protection System

B1*

L24

B1*

S25

T25

L10

RIGHT AC

EMERGENCY AC

LEFT DC

RIGHT DC

RIGHT AC

6.50.16

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Pneumatic System, Ctrl, Left

Pneumatic System Ctrl, Right

Prerecorded Announcements

Pressure Abnormal Light

Primary Flight Display, Capt

Primary Flight Display, F/O

Primary Long Trim, Brake

Primary Long Trim, Control

Printer

Probe Heat, Left Engine

Probe Heat, Right Engine

Proximity Switch Cont, Left

Proximity Switch Cont, Right

Radio Altimeter-1

Radio Altimeter-2

Radio DC Bus Feed, Left

Radio DC Bus Feed, Right

Radio Rack Fan Caution

Radio Rack Fan, Power

Radio Rack Fan, Standby

Radio Rack Fan, Stby Control

Radio Rack Fan, Venturi

Rain Repellent, Left

Rain Repellent, Right

Ram Air Exhaust Control

Ram Air Probe Heater

Ram Air Temp Probe

Ram Air Valve

Razor Outlets, Fwd & Aft

RDMI, Capt

CIRCUIT BREAKER

M21

B4*

F11

G23

G22

F18

88 CB REF

90

R21

U29

M26

N26

R39

F17

P21

F23

K27

L27

P39

B7*

F11

G23

G22

S26

T26

B4*

M21

M26

N26

Z29

P21

R21

U29

P39

R39

F17

Z29

L Con

BUS

LEFT DC

RIGHT DC

EMERGENCY AC

LEFT DC

EMERGENCY AC

RIGHT RADIO AC

LEFT RADIO DC

LEFT RADIO AC

EMERGENCY AC

RIGHT AC

LEFT DC

RIGHT DC

LEFT RADIO AC

RIGHT RADIO AC

LEFT DC POWER

RIGHT DC POWER

LEFT DC

LEFT AC

RIGHT AC

LEFT AC

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

RIGHT RADIO AC

April 01, 2004

6.50.17

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

88

RDMI, F/O

Recirculation Fan

Recirculation Fan, Control J7

Remote Access System Keypad P24

Remote Access System Control R34

Reverse Thrust, Left, Ch A

B7*

J10

Reverse Thrust, Left, Ch B

Reverse Thrust, Right, Ch A

Reverse Thrust, Right, Ch B

Reverse Thrust Light, Left

Reverse Thrust Light, Right

Reverser Accum Low, Left

Reverser Accum Low, Right

S31

T31

S29

T29

Reverser Accum Shut-Off, Left S28

Reverser Accum Shut-Off, Right T28

Reverser Unlock Light, Left S30

Reverser Unlock Light, Right

Rudder Q-Limiter Heater

T30

Z30

Rudder Travel Unrestricted Lt

SAT Indicator

SELCAL

Service Interphone

W25

G14

G8 or C9

Smoke Detector Fan

Speed Brake Warning

Spoiler Control

Spoiler Deployed Indicator

P38

P33

X30

R31

Spoiler Flap Extended Advisory P34

Spoiler Lockout

SSRS-1 Aural Warning

M31

P38

SSRS-2 Aural Warning

Stabilizer Motion Indicator

R38

G24

CB REF

S38

C11*

C12*

S30

T30

S28

T28

P24

T36

S37

B8*

J10

90

S29

T29

Z30

G14

J15

P38

P33

X30

R31

P34

M31

P38

R38

BUS

EMERGENCY AC

RIGHT AC

Left DC

Right DC

DC TRANSFER

EMERGENCY DC

LEFT DC

RIGHT DC

LEFT DC

RIGHT DC

LEFT DC

RIGHT DC

LEFT DC

RIGHT DC

RIGHT AC

RIGHT DC

RIGHT RADIO

LEFT RADIO DC

RIGHT RADIO DC

RIGHT AC

LEFT DC

RIGHT DC

LEFT RADIO DC

6.50.18

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

Stabilizer Warning U31

Stair Doors and Stairs Indicator R24

Stall Warning Alpha Flap-1

Stall Warning Alpha Flap-2

A13

Stall Warning, Auto Slat-1

Stall Warning, Auto Slat-2

Stall Warning, CAPT

Stall Warning, F/O

P35

R 35

X23

Z23

Standby Compass Light

Standby Horizon

Standby Horizon Light Control

Start Pump

A2*

X31

E16

U40

Start Valve, Left

Start Valve, Right

Static Air Temperature

Static Port Heater, Left

Static Port Heater, Right

Strake Heater, Left

Strake Heater, Right

Strobe Lights

Supply Air High Press Aug, Lt

Supply Air High Press Aug, Rt

Supply Air Press Regulator

Supply Air Press/Flow, Left

Supply Air Press/Flow, Right

Supply Air Temp Caution, Left

K10

U23

W23

N21

B14

M22

Supply Air Temp Caution, Right N22

U42

U41

X21

Z21

Supply Air Temp High, Left

Supply Air Temp High, Right

U26

W26

Supply Press High Light, Left M22

Supply Press High Light, Right N22

Symbol Generator - 1

Symbol Generator - 2

Systems Display Panel, Left

C3*

S34

88 CB REF

90

U42

X39

X21

B2*

X31

E16

U40

P35

R35

X23

Z23

U31

R24

A13

A 9

Z21

Lt GB

Rt GB

K10

N22

C4*

S 32

N21

S35

T35

M22

N22

U26

W26

M22

BUS

RIGHT AC

GENERATOR

LEFT AC

LEFT DC

RIGHT DC

LEFT INST

RIGHT INST

LEFT DC

RIGHT DC

LEFT DC

RIGHT DC

LEFT DC

RIGHT DC

EMERGENCY AC

RIGHT RADIO AC

LEFT DC

DC TRANSFER

RIGHT DC

LEFT INST

RIGHT INST

LEFT DC

RIGHT DC

LEFT AC

RIGHT AC

EMERGENCY AC

DC TRANSFER

LEFT RADIO DC

DC TRANSFER

RIGHT RADIO

LEFT AC

April 01, 2004

6.50.19

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER CB REF

88

Systems Display Panel, Right T34

Tail Compt Temp High Warning N24

Tail Comp Temp High Warn, Left

Tail Comp Temp High Warn,

Right

Tail Deice Timer

Tail Deice Valves

Tail Temp Ovht Ctrl, Left

Tail Temp Ovht Ctrl, Right

Takeoff Warning

TAS Indicator

TA/VSI, Capt

TA/VSI, F/O

N31

M24

Taxi Speed

TCAS Computer

Telephone, Passenger

Temp Control, Cabin

Temp Control, Cockpit

Temp Control, Manual, Cabin

C6*

Temp Control, Manual, Cockpit C5*

Temp Control Valve Posit, Lt B13

P38

A7*

L10 or J16

R34

K8 or H25

D16

Temp Control Valve Posit, Rt

Thunderstorm Light, Alternate

Transfer Relay Control

Transformer Rectifier, Left-1

Transformer Rectifier, Left-2

Transformer Rectifier, Right-1

Transformer Rectifier,

Right-2 (3)

W28

N38

L Con

T 32

M 23

N 23

N 31

M 24

K 8

L 19

P 38

B 6

A 8*

J 16

90

W28

N 38

H 16

L 29

J 1

C7*

C 6*

B13

L Con

BUS

RIGHT DC

LEFT DC

RIGHT DC

LEFT DC

LEFT AC

RIGHT AC

LEFT DC

RIGHT RADIO

EMERGENCY AC

RIGHT AC

RIGHT DC

LEFT AC

RIGHT AC

LEFT AC

EMERGENCY AC

LEFT INST

RIGHT INST

RIGHT DC

DC POWER FEED

LEFT AC

RIGHT AC

GROUND SERVICE

6.50.20

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

Transponder-1

Transponder-2

True Airspeed

Utility Outlet

Vacuum Waste Vent Htr

Venturi

VHF COMM-1

VHF COMM-2

VHF COMM-3

VHF NAV-1

VHF NAV-2

Video Control

Voice Recorder

VSCF Cooling Fan, Left

VSCF Cooling Fan, Right

VSCF Drain Mast Heater

VSI, Capt-See TA/VSI

VSI, F/O-See TA/VSI

Warning Light Dimming

Water Heater

Water Pump, Aux (3)

Water Quantity

Water Sys Freeze Prot, Aft

Water Sys Freeze Prot, Fwd

R25

EXT

L Con

Weather Radar Indicator

Weather Radar Transceiver

Windshear Computer

Windshear Warn & Caut, Left

E23

Windshear Warn & Caut, Right E11

Windshield Anti-Fog, Control Z25

L Con

D13

E13

L Con

A4*

B9*

B8*

G16

88

E23

E11

Z25

R25

EXT

L Con

CB REF BUS

90

D13

E13

B9*

G16

A4*

L Con

L23

LEFT RADIO AC

LEFT RADIO DC

RIGHT RADIO AC

RIGHT RADIO DC

RIGHT RADIO

GROUND SERVICE

RIGHT AC

LEFT AC

EMERGENCY DC

RIGHT RADIO DC

LEFT RADIO DC

EMERGENCY AC

B10*

EMERGENCY DC

RIGHT RADIO DC

B5 RIGHT RADIO

G19 & F25 LEFT RADIO AC/DC

Lt GB

Rt GB

L15

RIGHT RADIO AC

GENERATOR

RIGHT AC

RIGHT DC

MISCELLANEOUS

GROUND SERVICE

RIGHT RADIO AC

LEFT/RIGHT AC

LEFT RADIO DC

RIGHT RADIO DC

RIGHT AC

April 01, 2004 6.50.21

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

CIRCUIT BREAKER

Windshield Anti-Fog, Power

Windshield Anti-Ice, Center

Windshield Anti-Ice, Left

Windshield Anti-Ice, Right

Windshield Overheat

Windshield Wiper, Left

Windshield Wiper, Right

Wing Deice Valves

Wing Ice Detection

Yaw Damper Off Light

Yaw Damper-1

Yaw Damper-2

Z26

X26

X25

X24

Z24

M31

M25

N25

M24

M34

U33

G27

G13

88 CB REF

90

Z26

X26

X25

X24

Z24

M25

N25

M24

M34

U33

G27

G13

BUS

RIGHT AC

LEFT AC

RIGHT AC

LEFT DC

RIGHT DC

LEFT DC

DC TRANSFER

LEFT RADIO DC

RIGHT RADIO DC

6.50.22

April 01, 2004

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Circuit Breaker Location by Panel

BATT DIR BUS

OVERHEAD PANEL

B16 - B18 A17 - A19

OVERHEAD PANEL

BATT DIR BUS

BATTERY BUS

DC TRANSFER BUS

EMERG AC BUS

EMERG DC BUS

GENERATOR BUS

AC Bus, Left

AC Bus, Right

AC Bus Sensing, Left

AC Bus Sensing, Right

April 01, 2004

OVERHEAD PANEL

B16 - B18

C16 - C18

A17 - A19

B17 - B19

C19 - C20

C17 - C18

OVERHEAD PANEL

B19, B20 A20 - A22

B20 - B22

C19 - C22

LOWER EPC CB PANEL

T41, T42 S37 - S42

W31 - W42

X31 - X42

Z 1 - Z42

T37 - T4

U31 - U42

W31 - W42

X31 - X42

Z31 - Z42

OVERHEAD PANEL

A1 - A7 A1 - A8

B1 - B7

C1 - C8

B1 - B8

C1 - C8

OVERHEAD PANEL

A8 - A15 A9 - A16

B8 - B15

C9 - C15

LOCATION

Lt GB

B9 - B16

C9 - C16

Rt GB

Lt GB

Rt GB

Lt GB

Rt GB Rt GB

6.50.23

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Galley-1 Power, Fwd

Galley-1, Fwd

Ground Service Power

Heat Exchanger Fan, Left

Heat Exchanger Fan, Right

Hydraulic Pump, Aux

Longitudinal Trim, Primary

Overwing Heater, Left

Overwing Heater, Right

GROUND SERVICE

LEFT AC BUS

LEFT DC BUS

LEFT INST BUS

LEFT RADIO AC BUS

LEFT RADIO BUS

LEFT RADIO DC BUS

RIGHT AC BUS

88 90

Lt GB

Rt GB

Lt GB

Rt GB

Lt GB

Rt GB

Lt GB

Rt GB

Lt GB

Rt GB

LOCATION

J17, J19

L Con

J17, J19

L Con

UPPER/LOWER EPC CB PANEL

H1 - H25 H1 - H23

K1 - K34

X21 - X30

K1 - K39

X21 - X30

LOWER EPC CB PANEL

M21 - M36 M21 - M37

P21 - P40

S21 - S40

P23 - 40

S21 - S36

U21 - U30 U21 - U30

UPPER EPC CB PANEL

A10 - A13

B10 - B16

A10 - A13

B10 - B16

UPPER EPC PANEL

D13 - D20 D13 - D22

F14 - F26 F14 - F26

UPPER EPC CB PANEL

C10 - C16 C10 - C16

UPPER EPC CB PANEL

E13 - E24

G14 - G27

D13 - D22

E13 - E24

G14 - G27

UPPER/LOWER EPC CB PANEL

J1 - J23 J1 - J17

6.50.24

April 01, 2004

Electrical -

Circuit Breaker Locations

RIGHT DC BUS

RIGHT INST BUS

RIGHT RADIO AC BUS

RIGHT RADIO BUS

28 VAC

D.C. POWER FEED

MD-88/90 Operations Manual

RIGHT RADIO DC BUS

88 90

L1 - L34

Z21 - Z30

J21 - J23

L1 - L36

Z21 - Z30

LOWER EPC CB PANEL

N21 - N35

R21 - R41

N21 - N35

R24 - R41

W21 - W30 W21 - W30

UPPER EPC CB PANEL

A1 - A9 A1 - A9

UPPER EPC CB PANEL

D1 - D12

E11

D1 - D12

F1 - F13

UPPER EPC CB PANEL

B1 - E12

C1 - C9

B1 - B9

C1 - C9

UPPER EPC CB PANEL

E1 - E12 D1 - D12

G1 - G13 E1 - E12

G1 - G13

UPPER EPC CB PANEL

C17 - 19 C17 - C19

LOWER EPC CB PANEL

N26 - N38 N36 - N38

April 01, 2004 6.50.25

Electrical -

Circuit Breaker Locations

MD-88/90 Operations Manual

Intentionally

Blank

6.50.26

April 01, 2004

Electrical

MD-90 Differences

MD-88/90 Operations Manual

Chapter 6

Section 90

Intentionally

Blank

April 01, 2004 6.90.1

Electrical -

MD-90 Differences

MD-88/90 Operations Manual

Controls and Indicators

Electrical Control Panel

ELEC PWR

100

VOLTS

150

380

400

FREQUENCY

CPS

420

L GEN

RESET

OFF

2.5

. 5

1.0

1.5

AC LOAD

2.0

APU

GEN

RESET

OFF

2.5

1.0

1.5

AC LOAD

2.0

2.5

R GEN

RESET

OFF

EXT

PWR

VOLT/FREQ

APU

AC VOLT/FREQ

DC BUS VOLT

L R

BATT

VOLT

BATT

AMP

1.0

1.5

AC LOAD

2.0

100

P S

50 100

25 50

-VOLTS+

5 FORWARD OVERHEAD PANEL

JB1-3-0853

AC VOLTS Meter

Indicates voltage output of the source selected by the indicator selector.

FREQUENCY Meter

Indicates frequency output of the source selected by the indicator selector.

JB1-3-0853

DC VOLTS/AMPS Meter

Indicates DC voltage when indicator selector is selected to BATT VOLT or

L/R. Indicates DC current in amps to or from batteries when BATT AMP is selected.

Indicator Selector

APU or EXT PWR - Selects AC voltage on AC VOLTS meter and frequency on FREQUENCY CPS meter.

L/R - Selects AC voltage on AC VOLTS meter and frequency on

FREQUENCY CPS meter. Also selects DC bus voltage on DC VOLTS meter.

BATT VOLT - Selects DC voltage of batteries on DC VOLTS meter.

BATT AMP - Selects DC current in amps to or from batteries on DC VOLTS meter.

6.90.2

February 28, 2005

Electrical -

MD-90 Differences

MD-88/90 Operations Manual

L/APU/R AC LOAD Meter

Indicates load each AC generator is delivering to distribution system.

Indicates from 0 to 1.5 with 1.0 indicating 100% of generator rated capacity.

L/APU/R GEN Switch

RESET - (Momentary) Resets the generator.

OFF - Results in generator disconnecting from AC generator bus.

ON - (Normal position) Generator supplies power to respective generator bus, providing all protection circuits are satisfied, and generator is operating.

April 01, 2004 6.90.3

Electrical -

MD-90 Differences

Electrical Power Panel

9 10

MD-88/90 Operations Manual

GALLEY

OFF

APU

R GEN

BUS

TIE

OPEN

APU

PWR

AVAIL

BUS

TIE

OPEN

APU

L GEN

EXT

AUTO

EXT

PWR

AVAIL

AUTO

EXT

L AC

BUS

1.5

LOAD

1.5

OFF

DC BUS X TIE

OPEN

6 5

FORWARD OVERHEAD PANEL

R AC

BUS

1.5

LOAD

1.5

JB1-3-0854

JB1-3-0854

BUS TIE Switches (2)

OPEN - Isolates the L/R generator bus from the tie bus.

AUTO - (Normal position) EPCU automatically opens and closes bus tie relays as required to maintain electrical power to respective buses.

APU POWER AVAIL Light (blue)

Indicates APU generator switch is ON, APU generator frequency and voltage are within required limits.

EXT PWR AVAIL Light (blue)

Indicates external power switch is ON and external power frequency and voltage are within the required limits.

L/R DC LOAD Meter

Dual scale, one for each of the four transformer rectifiers (TR). Indicates current output proportional to TR rating, 1.0 is 100 percent.

DC BUS X TIE Switch

CLOSE - Closes DC cross-tie relay and connects the left and right DC buses.

Supplies DC power from one side to the other in case both transformer rectifiers fail on either the left or right system.

OPEN - (Normal position) Left and right DC buses are isolated.

6.90.4

April 01, 2004

Electrical -

MD-90 Differences

MD-88/90 Operations Manual

External Power Switch

OFF - Results in opening of the main external power relay (MEPR) removing external power from the AC tie bus.

ON - Enables closure of the MEPR. External power is supplied to the AC tie bus when external power has priority.

EXT Power In-Use Light (2) (blue)

Indicates external power is powering the respective generator bus.

GALLEY Switch

OFF - Galley power is off.

ON - Galley power is on. In flight, if only one AC generator is providing power, the system automatically sheds power to the galleys.

L/R GEN Power In-Use Light (blue)

Indicates opposite generator is powering both generator buses.

10.

APU Power In-Use Light (2) (blue)

Indicates APU generator is powering respective generator bus.

April 01, 2004 6.90.5

Electrical -

MD-90 Differences

MD-88/90 Operations Manual

Ground Service Electrical Power Control Panel

GROUND SERVICE ELEC PWR

APU

PWR

AVAIL

GROUND

SERVICE

BUS

OFF

EXT

PWR

AVAIL

AFT OVERHEAD PANEL

JB1-3-0855

JB1-3-0855

APU POWER AVAIL Light (blue)

Indicates APU generator switch is ON, APU generator frequency and voltage are within required limits.

EXT PWR AVAIL Light (blue)

Indicates external power switch is ON and external power frequency and voltage are within the required limits.

Ground Service Power Switch

OFF - Disconnects APU or external power from the AC tie bus to the ground service bus.

ON - Connects APU or external power from the AC tie bus to the ground service bus, providing the right generator bus is not powered. APU power has priority over external power for powering the ground service bus.

EXT Ground Service Power In-Use Light (blue)

Indicates external power is supplying power to the ground service bus.

APU Ground Service Power In-Use Light (blue)

Indicates APU generator is powering the ground service bus.

6.90.6

April 01, 2004

MD-88/90 Operations Manual

Emergency Power Selector And Battery Switch

Electrical -

MD-90 Differences

OFF

EMER PWR

ARM

ON

EMER

PWR

IN USE

OFF

BATT

ON

OVERHEAD PANEL

JB1-3-0856

JB1-3-0856

EMER PWR IN USE Light (white)

Indicates emergency power is being supplied.

BATT Switch (Pull And Twist To Lock On)

OFF - Disconnects battery bus from battery direct bus, prevents the battery charger operation and disconnects the DC transfer bus from the batteries.

ON - Connects battery bus to battery direct bus and enables connections of the DC transfer bus to the batteries.

EMER PWR Selector

OFF - Disarmed and resets the Automatic Emergency Power System.

ARM - (Normal position) Emergency power relay is placed in the standby mode for automatic activation (requires at least one FUEL switch ON) when the electrical power control unit (EPCU) detects a power loss to the emergency AC, DC or DC transfer bus.

ON - Emergency power is energized, prevents battery charger operation. The battery supplies power for AC emergency bus (through the emergency inverter), DC emergency bus and DC transfer bus.

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System Description

General

The airplane electrical power system consists of a 115 volt, 3-phase, 400 Hz, constant-frequency alternating current (AC) system and a 28-volt direct current

(DC) system. The system incorporates a no break power transfer function which allows uninterrupted power switching under normal conditions.

AC Generation and Control

The primary source of AC power is two variable speed constant frequency

(VSCF) generating systems (left and right). Each system consists of an oil cooled engine driven generator on each engine and it's associated converter. The converter unit for the left engine is located in the right tunnel area (forward of the wing) and the right engine converter is located in the right nosewheel well. The converter units supply 115 volt, 3-phase, 400 Hz power to their respective left and right generator bus for system distribution.

Each system has an AC LOAD meter located on the overhead panel and a generator relay between the converter, generator bus and the bus tie relays. The

AC LOAD meters indicate the percentage of load demand from 0 to 2.0 (1.0

represents 100% full load rating). The generator relays are controlled by the generator (L/R GEN) switches, one for each generator, on the overhead panel. The

RESET position is momentary and is used to reset a generator that has tripped off line. The OFF position results in opening of the relay to prevent power flow to the respective buses. The ON position enables closure of the relay to supply power from the converter to the respective generator bus.

The systems normally operate independently of each other. When required, a single generator can power both systems through the two bus tie relays and the AC tie bus. The bus tie relays may be controlled manually by the BUS TIE switches, or automatically by the electrical power control unit (EPCU). The OPEN position opens the respective relay isolating the associated AC generator bus from the AC tie bus. The AUTO position (which is the normal position), permits automatic operation of the relays through the EPCU. The EPCU opens and closes the relays as required to maintain electrical power to the respective buses. The converters prevent power that does not meet the proper quality from powering any bus.

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An AC voltmeter (AC VOLTS), and a frequency (FREQUENCY) meter located on the overhead panel, indicate voltage and frequency of the source selected by the Indicator Selector (APU, EXT PWR L,R). External power and APU power available lights (EXT PWR AVAIL, and APU PWR AVAIL) located on the overhead panel illuminate when power is available from the respective source.

There are six blue power in-use (two APU, R and L GEN, and two EXT) lights that illuminate to indicate which alternate power source is providing power to the associated generator bus. The priority for the generator buses are: associated engine generator, APU generator, external power, and the opposite side main engine generator (cross-tie).

There is one GALLEY switch that controls power to the galleys. Galley power is shed automatically when only one power source is available in flight with both bus tie relays closed.

AC Power Distribution

The left and right generator buses are the main distribution buses for the AC system. Loads are distributed independently for each system. Power from the left generator bus is distributed to the left AC bus then to the left transformer rectifiers

(TR No.'s 1 and 2) for DC power. AC power from the right generator bus is distributed to the right AC bus then to the right TR No. 1 for DC power. Power to the right TR No. 2 is provided through the ground service AC bus.

Auxiliary Power

When APU power is available, the APU power available (APU PWR AVAIL) lights illuminate. When the APU generator (APU GEN) switch, located on the overhead panel, is in ON, the APU-Generator relay will open or close as required for system operation.

The APU generator relay allows power from the APU generator to power the AC tie bus. When the APU GEN switch is in OFF, the generator relay opens isolating the generator from the tie bus. The RESET position is momentary and is used to reset the generator.

External Power

External power is provided through the ground power receptacle located in the left forward fuselage, and controlled by the EPCU. The EPCU ensures that the external power is within voltage and frequency limits. When power of the proper phase and voltage is supplied to the airplane, and the external power (EXT PWR) switch located on the overhead panel is in ON (normal position), the external power available (EXT PWR AVAIL) lights illuminate.

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MD-88/90 Operations Manual

When the EXT PWR switch is in ON, external power is supplied to the AC tie bus automatically through the main external power relay (MEPR). The OFF position of the EXT PWR switch results in opening of the MEPR disconnecting external power from the AC tie bus. To power the ground service bus only, the ground service switch must be selected ON and AC TIE BUS switches opened.

DC Generation and Control

DC power is provided by four TR's (left No. 1 and No. 2, and right No. 1 and No.

2) that convert AC to 28 VDC power. The output from the left TR's supply power to the left DC bus. Under normal conditions the left DC bus powers the DC transfer bus and the emergency DC bus. The output from the right TR's supply power to the right DC bus. When the ground service AC bus is powered by external power or the APU on the ground, right TR No. 2 supplies power to the

DC transfer bus.

A manually controlled DC bus cross-tie (DC BUS X-TIE) switch, located on the overhead panel, controls the cross tie relay. When the switch is in OPEN, the left and right DC buses are isolated from each other. When the switch is in CLOSE, the left and right DC buses are connected together. Two DC LOAD meters with dual scales located on the overhead panel indicate the percentage of load output from the TR's from 0 to 1.5 (1.0 is 100% load output).

The DC VOLTS/AMPS meter on the overhead panel indicates DC bus voltage as selected by the indicator selector (DC BUS VOLT L and R, BATT VOLT, BATT

AMP).

Emergency DC and AC Power Supply

Emergency DC power is provided by three 9-volt batteries installed in the E/E compartment, connected in series that supply power directly to the battery direct bus.

When the battery (BATT) switch, located on the overhead panel, is ON, the battery direct bus powers the battery bus. When the BATT switch is OFF, the battery relay opens preventing power to the battery bus. The batteries provide power for approximately 45 minutes. The batteries are charged by a 28-volt charger when power is on the ground service AC bus, the BATT switch is ON, and emergency power is off.

Emergency AC power is provided to the emergency AC bus by a single phase AC inverter that converts 28-volt DC power from the batteries to 115-volt, 400 Hz AC power.

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Emergency power may be selected manually or armed for automatic operation by the emergency power selector (EMER PWR), located on the overhead panel.

When the selector is in ARM, emergency power is transferred automatically when normal power is lost to the emergency AC, emergency DC, or DC transfer buses.

During normal operation, the emergency AC bus is powered from the left AC bus.

If power is lost to the left AC bus, the emergency power transfer relay shifts and power will be supplied to the emergency AC bus from the right AC bus. If the normal and alternate sources of power fail, emergency power is activated automatically. The ON position permits testing of the emergency power system, and serves as a manual backup by closing the emergency power relay allowing power transfer. The emergency power in use (EMER PWR IN USE) light located on the overhead panel, will illuminate when emergency power is on. When the emergency power is being supplied, the battery charger is inhibited. Automatic emergency power activation is inhibited when both fuel switches are in OFF to preclude accidental battery discharge. When emergency power is on, in addition to the battery bus and battery direct bus, the emergency AC, emergency DC and

DC transfer buses are powered.

Ground Service Bus

Electrical supply for ground servicing is provided by the ground service bus. The bus normally receives power from the right generator bus. If the right generator bus is unpowered, the ground service bus may be powered from the APU or external power through the AC tie bus.

The GROUND SERVICE ELEC PWR panel is located on the aft overhead panel.

When the ground service switch is OFF, the ground service bus is powered from the right AC bus. With the right generator bus unpowered, the ON position will allow power from the APU or external power to be applied to the bus directly from the tie bus. The APU PWR AVAIL and EXT PWR AVAIL lights illuminate when power is available from the respective source. The blue APU or EXT ground service power in-use lights illuminate to indicate which unit is supplying power to the bus.

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MD-88/90 Operations Manual

OAP Message/Alerts

Amber Caution Messages

NOTE: The associated cue light is shown in parenthesis (XXX) following the message.

BATTERY BUS OFF (ELEC) - Indicates battery bus is de-energized.

EMER POWER ON (ELEC) - Indicates emergency power is in use.

EMER PWR AUTO FAULT (ELEC) - Indicates EMER PWR selector is in

ARM and the electrical power control unit (EPCU) unsuccessfully attempted to switch the emergency power in use automatically.

EMER PWR SW OFF (ELEC) - Indicates EMER PWR selector is in OFF.

L/R/APU AC PWR FAULT (ELEC) - Indicates an "out-of-limit" condition on the respective bus feed, converters, generator, or generator feed which has or may result in power loss.

L/R BUS TIE LOCKOUT (ELEC) - Indicates the respective bus tie is locked out from closing due to a fault in the distribution system.

TIE BUS FEEDER FAULT (ELEC) - Indicates a feeder fault in the tie bus.

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MD-88/90 Operations Manual

MD-90 Power Distribution

Electrical -

MD-90 Differences

. 5

1.5

TR #1

TR #2

APU PWR AVAIL

EXT PWR AVAIL

APU GEN CNT

APU GEN

1.5

. 5

APU PW

EXT PW

EMER PW

TR #2

AC EM

TR #1

1.5

. 5

April 01, 2004

JB1-3-0305E

JB1-3-0305E

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MD-88/90 Operations Manual

Intentionally

Blank

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April 01, 2004

Key features

Twin-engine
Narrow-body jet
Commercial passenger transport
Safe and reliable
Comprehensive operations manual

Frequently asked questions

The Delta Air Lines MD-88/90 Operations Manual provides pilots with normal and non-normal procedures for operating the MD-88 and MD-90 aircraft. It is company policy for pilots to follow these procedures during ground operations and in flight.

The MD-88/90 Operations Manual covers a wide range of procedures, including normal checklists, non-normal checklists, non-normal maneuvers, and operational limitations. It also includes information on aircraft systems and emergency equipment.

The MD-88/90 Operations Manual is organized into two volumes. Volume 1 covers normal and non-normal procedures, while Volume 2 contains general airplane and systems information.

Specific operating procedures and systems information for the MD-88/90 aircraft can be found in the appropriate chapter in Volume 2 of the manual. Each chapter is generally subdivided into sections covering controls and indicators, and systems descriptions.

The MD-88/90 Operations Manual has been revised twice. The first revision was released on April 01, 2004, and the second revision was released on August 11, 2008.