B737-3 ATA 31-20, -30 L3 e

ATA 104 Level 3

Book No: B737-3 31 L3 E

Lufthansa

Lufthansa Base

Issue: August 1999For Training Purposes Only

Lufthansa 1995Technical Training GmbH

Training ManualB 737-300/-400/-500

ATA 31Instruments31-20 Clocks31-30 Recorders (DFDR/ACMS)

For training purpose and internal use only.

Copyright by Lufthansa Technical Training GmbH.

All rights reserved. No parts of this trainingmanual may be sold or reproduced in any formwithout permission of:

Lufthansa Technical Training GmbH

Lufthansa Base Frankfurt

D-60546 Frankfurt/Main

Tel. +49 69 / 696 41 78

Fax +49 69 / 696 63 84

Lufthansa Base Hamburg

Weg beim Jger 193

D-22335 Hamburg

Tel. +49 40 / 5070 24 13

Fax +49 40 / 5070 47 46

TABLE OF CONTENTS

Page: i

ATA 31 INSTRUMENTS 1. . . . . . . . . . . . . . . . . . . . . .

31-20 CLOCKS 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOCKS 2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CLOCK CONTROL 4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CLOCK DESCRIPTION 6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

31-30 RECORDERS 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DFDR/ACMS 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

COCKPIT LOCATION OF DFDR/ACMS 10. . . . . . . . . . . . . . . .

LRU LOCATION 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SENSOR LOCATION 14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

POWER DISTRIBUTION 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIGHT DATA ACQUISITION UNIT (FDAU) 18. . . . . . . . . . . . .

FLIGHT DATA RECORDER 20. . . . . . . . . . . . . . . . . . . . . . . . . . .

UNDERWATER LOCATOR BEACON (ULB) 20. . . . . . . . . . . . .

QUICK ACCESS RECORDER (QAR) 22. . . . . . . . . . . . . . . . . .

ACCELEROMETER 24. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FAULT MONITORING 26. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PWR DISTRIBUTION AND CONTROL 28. . . . . . . . . . . . . . . . .

DFDR ADJUSTMENT / TEST 30. . . . . . . . . . . . . . . . . . . . . . . . .

FLIGHT RECORDER TEST 32. . . . . . . . . . . . . . . . . . . . . . . . . . .

TESTS AFTER REMOVAL / INSTALLATION OF LRU S 34. .

ACMS GENERAL 36. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ACMS MENU 38. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ACMS MENU HANDLING 40. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

STATUS 42. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ACMS STATUS REPORT 44. . . . . . . . . . . . . . . . . . . . . . . .

ALPHA CALL UP 46. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ANALOG / DISCRETE 48. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DITS CALL UP 50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

INPUT PORTS 52. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PARAMETER MENU 54. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DMRU REPORTS 56. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DMRU REPORTS TEST/ PRINT 58. . . . . . . . . . . . . . . . . . . . . . .

DMRU PROGRAM 60. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

APU DATA 62. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SOFTWARE LOADING 64. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LOAD CONTROL 66. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PRINTER 68. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PRINTER DESCRIPTION 70. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PAPER ROLL CHANGE 72. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

TABLE OF FIGURES

Page: ii

Figure 1 Clocks 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 2 Clock Control 5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 3 Clock Interface 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 4 General Schematic 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 5 Location of DFDR/ACMS 11. . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 6 LRU Location 13. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 7 Sensor Location 15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 8 Power Distribution 17. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 9 FDAU 19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 10 Flight Data Recorder 21. . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 11 QAR 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 12 Accelerometer 25. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 13 FAULT Monitoring 27. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 14 PWR Distribution and Control 29. . . . . . . . . . . . . . . . . . . . . . Figure 15 DFDR Adjustment /Test 31. . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 16 Flight Recorder Test 33. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 17 Tests after Removal /Installation 35. . . . . . . . . . . . . . . . . . . . Figure 18 ACMS Schematic 37. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 19 ACMS Menu Handling 39. . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 20 ACMS Menu 41. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 21 Status/ Ident 43. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 22 ACMS STATUS REPORT 45. . . . . . . . . . . . . . . . . . . . . . . . . Figure 23 Alpha Call Up 47. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 24 Analog/Discrete 49. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 25 DITS Call Up 51. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 26 Input Ports 53. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 27 Parameter Menu 55. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 28 Reports 57. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 29 TEST/PRINT 59. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 30 DMRU Program 61. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 31 APU Data 63. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 32 Software Loading 65. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 33 Load Control 67. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 34 Printer Location 69. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure 35 Printer 71. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 36 Printer Roll Change 73. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Figure A Location A3 74. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y

INSTRUMENTSFLIGHT DATA RECORDER SYSTEM

737-330 /430/530

31

Page: 1HAM US/F bo 21.04.97

ATA 31 INSTRUMENTS

Page: 1

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y

INSTRUMENTSINDEPENDENT INSTRUMENT

B737-300/400/500

31-20

Page: 2HAM US/F bo Aug 99

31-20 CLOCKS

CLOCKSGeneralThere are two identical electronic clocks one for the captain and one for thefirst officer.The clock system consists of

- two digital clocks- two remote push button

The following indications are possible:- GMT (Greenwich Mean Time also known as UTC)- DATE (day, month and year)- CHR Time (chronographic display)- ET (elapsed time)

The GMT and DATE is permanently send on digital busses to the FMC andDFDAU

Page: 2

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


B737-300/400/500

31-20


30

10

2040

ET/CHR

GMT

50

60

RESET

HLD

CHR

RUN

DAY MO/YR

DATE

FOs Clock

Remote SwitchRemote Switch

30

10

2040

ET/CHR

GMT

50

60

RESET

HLD

CHR

RUN

DAY MO/YR

DATE

Captains Clock

Page: 3Figure 1 Clocks

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-20


CLOCK CONTROL

Elapsed Time OperationThe elapsed time (ET) control switch is located in the lower left corner. Thisswitch operates as follows: In the RESET position, the ET display is blanked and the elapsed time in-

dication is set to zero. The RESET position is spring loaded to return theswitch to the HLD position.

The HLD (hold) position of the switch freezes the ET display at the presentindicated value.

In the RUN position, time is accumulated from the last hold or reset condi-tion. The display automatically advances from this indicated value.

Chrono Time OperationThe CHR switch is located in the upper left corner. This switch operates as fol-lows: The first press of the switch starts the chronograph running. A second press of the switch freezes the chronograph display at the present

indicated value. A third press of the switch resets the CHR accumulator to zero. The con-

tents of the ET accumulator is then displayed. If the ET accumulator con-tains zero, the elapsed time display is blanked and the sweep second handgoes to zero.

Chronograph operation replaces the display of the elapsed time, but does notaffect the internal operation of the ET accumulator.

GMT SettingThe GMT is adjusted by the SET switch. The RUN setting of this switch is the normal operating position for the clock.

GMT is shown continuously while in this mode. The HLD (hold) setting is used to freeze the GMT display. Setting the switch

to this position will hold the display at its present indicated value. The MS (minute slew) setting is used for slow slew operation. When set to

this position, the seconds display is reset to zero. The minute display auto-matically advances at a rate of 1 minute/second. The hours display is frozenat its present indicated value.

The HS (hour slew) setting is used for fast slew operation. When in thisposition, the hours display automatically advances at a rate of 1 hour/se-cond. The minutes display is frozen at its present indicated value.

Date SettingSetting the date can be accomplished by the combined use of the SET switchand the push button DATE switch. The day control function on the SET switchpositions are: D, M, and Y, which are located adjacent to HS, MS, and HLD ofthe GMT control, respectively. Each function is operated as follows: The D setting is used for changing the day display. When in this position,

the day display automatically advances at a rate of one day per second upto maximum value of 31, 30, 29, or 28 depending on the month setting andreincrementing from 01. The month display does not change.

The M setting is used for changing month display. When in this position, themonth display automatically advances at a rate of one month per second,up to maximum value of 12 and reincrementing from 01. The day displaydoes not change.

The Y setting is used for changing year display. Turning the SET switch to Yposition will cause the two right hand digits to update one year per secondup to maximum value of 99 and reincrementing from 00. The two left handdigits will be blank.

Page: 4

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-20


CHRONOGRAPH

SWITCH

GREENWICH MEAN

TIME CONTROL

SWITCH

ELAPSED TIME

CONTROL SWITCH

DATE PUSH

SWITCH

DAY MO/YR

GMT

ET/CHR

RESET

HLD

RUN

HSD

MSM

HLDY

RUN

HLD Y = Hold / Year

MS M = Minutes set / Month

HS D = Hours set / Day

RUN

Page: 5Figure 2 Clock Control

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-20


CLOCK DESCRIPTION

GeneralThe GMT output is provided in hours, minutes, and seconds. The time is accu-rate to 1 second per 200 hours at 25 C unless power to the clock is inter-rupted.The electronic clocks are located on the captains and first officers instrumentpanels, respectively. They are microprocessor controlled with two LCD dis-plays, controls, and a sweep second hand.The Flight Management Computer (FMC) and the Flight Recorder System useclock data.

Upper DisplayThe upper display (GMT) provides GMT continuously from 00 hours 00 min-utes to 23 hours 59 minutes.

Lower DisplayThe lower display provides elapsed time (ET) from 00 hours 00 minutes to 99hours 59 minutes or chronographic time (CHR) from 00 minutes 00 seconds to99 minutes 59 seconds. Control of this display is provided by the ET and CHRswitches.

DATE SwitchThe DATE is shown on the GMT display when the DATE push button ispushed.

SET SwitchThe GMT or date display is controlled by the SET switch. This switch is locatedin the lower corner of the indicator. The normal position is RUN.

Clock SwitchThe Captains and F/Os CLOCK switches (= remote clock switches) are lo-cated on either side of the glareshield.The CHR and remote clock switches are connected in parallel and operate thechronograph display. Both switches cycle the chronograph through the start,hold and reset functions of the chronograph mode.

BITEAll clock failures are indicated in the same manner. The clock displays go blankand the sweep second hand is frozen. In addition, transmission of GMT outputdata words is halted.

NOTE: WHEN THE MAIN BATTERY WAS DISCONNECTED, YOU HAVETO SET GMT AND DATE.

Page: 6

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-20


Captains Clock

First Officers Clock

FMC

DFDAU

Page: 7Figure 3 Clock Interface

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly

INSTRUMENTSRECORDERS

B737-300/400/500

31-30


31-30 RECORDERSDFDR/ACMS

GeneralIn this Instruments part you will find the chapter Flight Data Recorder System FDRS Aircraft Conditioning Monitoring System ACMS,

FDRS / ACMSBecause they put together the function of DFDRS and ACMS in one box, theunit is called DFDAMRU (Digital Flight Data and Management Recording Unit).In the question of power supply, location and some handling we cant divide thistwo systems, but generally they have two individually duties and use therefordifferent associated systems: The DFDRS (Digital Flight Data Recording System) fulfil assignments for

the authority, by recording of important (mandatory) Parameters, which arerealized by the FDAU-part of the DFDAMRU and the following systems- DFDR, Digital Flight Data Recorder- ACC, three axis accelerometer- Flight Recorder Test Module- Event Push Button.

An ULB (Under Water Locator Beacon) is strapped to the DFDR. The ACMS (Aircraft Conditioning Monitoring System) fulfil assignments of

continuous control of essential Engine-Data for Engine Condition Monitoringand other flight data and aircraft data, which is realized by the use of theDMU-part (Data Management Unit) of the DFDAMRU and the following sys-tems:- MCDU- Printer- Print Push Button- ADL, Airborne Data Loader- Diskettes.

Advice.Some airliners use the option of a QAR (Quick Access Recorder).

Page: 8

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


QAR(option)

Page: 9Figure 4 General Schematic

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


COCKPIT LOCATION OF DFDR/ACMS

SENSORSThe following Flight Control Sensors are only used for data recording: Control Wheel Position Sensor (M520) Control Column Position Sensor (M521) Rudder Pedal Position Sensor (M522) Horizontal Stabilizer Position Sensor (M1192)

DISKETTESFour diskettes are necessary for the program update. The diskettes are storedin board in a disc box..

SPARE PAPER ROLLSTwo spare paper rolls are stored in the cockpit.

Page: 10

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


SPARE PAPER ROLLS

Page: 11Figure 5 Location of DFDR/ACMS

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


LRU LOCATIONDifferent types of Flight Recorders may be used: Tape Recorder or Solid StateFlight Data Recorder.

Page: 12

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


Lockheed Martin /Fairchield

Lockheed Martin /

Page: 13Figure 6 LRU Location

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


SENSOR LOCATIONIn the new 737-Generation additional sensors are installed for record purposeonly .

Page: 14

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


Aileron Position Transmitter

Speddbrake HandlePosition Sensor

Rudder PositionTransmitter T469

Elevator Position TransmitterL: T467 R: T468

M1439

Page: 15Figure 7 Sensor Location

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


POWER DISTRIBUTION115V AC from 115 AC ELEX BUS 1 serves to SYSTEM-Power.. 28V DC from DC BAT BUS serves to RELAY-Power .26V AC from XFMR BUS 2 is used for the sensors.The DFDR (and in parallel the CVR) is powered by 115V AC under followingcondition : at least one ENG is running , or A/C in FLT , or TEST Button is pressed

Page: 16

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


GND

AIR

ENG 1

ENG 2

OFF

ON

OFF

ON

NO

RM

AL

TE

ST

SYSTEMTESTPLUG

SYSTEMSTATUSRELAY

SENSORSMULTIPORTPRINTER

DFDAMRU

FLIGHT

DATA

RECORDER

DIGITAL

28V DC

BAT BUS

115V AC

ELEX

PWR 1

26V AC

XFMR

BUS 2

GROUND

SENSING

RELAY

ENG

ACC

MODULE FLIGHT

RECORDER

MODULE

28V DC

POSN SENSORS

PRINTER

FLT REC AC

FLT REC DC

ACC

Page: 17Figure 8 Power Distribution

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


FLIGHT DATA ACQUISITION UNIT (FDAU)

FDAU processes and prepares all input signals for recording. Electronic cir-cuits in the FDAU provide isolation, perform the functions of preconditioning,multiplexing, scaling, synchronization, and converting input signals of variousforms to digital format and sending them to the flight data recorder and theQAR for storage. A test set plug and a BITE indicator are located on the front panel of theFDAU. The test set plug is provided to connect external test equipment. TheBITE indicator comes on when BITE circuitry within the FDAU detect a mal-function.The FDAU provides 28 volt dc power for the accelerometer excitation.

Parameter InputsThe FDAU receives input signals from sensors and various airplane systems.The inputs are as follows:Analog inputs Accelerometer Control column position transmitter Control wheel position transmitter EGT indicators (Airplanes without EIS) Fuel flow indicators Horizontal stabilizer position transmitters N1 indicators N2 indicators Oil temperature bulbs Oil pressure indicators Rudder pedal position transmitter

Digital inputs Autothrottle computer Captains clock Digital air data computer Digital stall warning computer

Digital to analog adapters EFIS symbol generators Engine vibration signal conditioner First officers clock (option) Flight control computers Flight management computer Inertial reference units Mode control panel

Discrete inputs Airplane ID shorting receptacle APU control unit EFIS transfer relay Engine accessory unit Engine start valve Flight control module Ground proximity warning computer HF transceivers IRS transfer relay Landing gear logic shelf Leading edge flaps/slats position indicator module Marker beacon receiver Master warning lights Systems A and B elec pump low pressure switches Systems A and B eng pump low pressure switches VHF transceivers

Page: 18

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


INDICATORS

LED FAULT

PLUG

TEST SET

Page: 19Figure 9 FDAU

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


FLIGHT DATA RECORDERThe flight data recorder stores the output data for the last 25 hours of airplaneoperation. Data is stored on the 1/4-inch wide magnetic tape. The tape andtransport are located in a 1/2 ATR crash-proof container within the flight datarecorder.Some aircraft have Fairchild Recorders without a magnetic tape, but with asolid state memory.The Fairchild SSFDR uses data compression to store aircraft flight information.The data is compressed by the compression/store data acquisition circuit card.The data is stored in the crash survivable store unit. The crash survivablestore unit is a hardened cubical where the memory chips are located. TheSSFDR will store 25 hours of data.The tape transport assembly protects the recorded data against fire and im-pact. This protection includes an inner aluminum cover, isothermal protectionshield, an outer stainless steel casing and an exterior stainless steel dustcover. This design enables the flight data recorder to meet a test of 20,000pounds of crush per axis, and provides impact protection of 1000 gs for 5msec. When the equipment is subjected to high thermal environments the iso-thermal insulation maintains the inner chamber at a safe temperature.The front panel of the flight data recorder has a test connector and an under-water locator beacon (ULB). The test connector lets you attach a portable tes-ter or a copy recorder to the flight data recorder. The ULB transmits an ultra-sonic signal when it is under water. There are no electrical connectionsbetween the ULB and the flight data recorder. A battery within the ULB sup-plies the ULB with power.

UNDERWATER LOCATOR BEACON (ULB)The ULB is a battery operated unit that transmits pulses when immersed in wa-ter. The ULB has a detection range of 2,000 to 4,000 yards and an operatinglife of approximately 30 days.

Page: 20

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


947STA

RECORDERFLIGHT DATA

PANELCEILING

SUNDSTRAND FLIGHT DATA RECORDER

BEACONLOCATORUNDERWATER

RECORDERFLIGHT DATA

UNDERWATERLOCATOR BEACON

FAIRCHILD SOLID STATE FLIGHT DATA RECORDER

Page: 21Figure 10 Flight Data Recorder

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


QUICK ACCESS RECORDER (QAR)The QAR is a 3/8 ATR container weighing 6.25 kg and is on the electri-cal equipment shelf E2-1. The QAR records maintenance data from theFDAU through an electrical connector on the rear of the unit when theAIDS power is applied.The QAR consists of a removable tape cartridge, power supply, electronic con-trol circuits, and tape deck assembly with motor. The front panel containsthree indicator lights:The red FLAG indicator illuminates to indicate FAILURE DETECTED Thegreen TRACK 1 indicator illuminates while track 1 is in use The red TAPE LOWindicator illuminates at the beginning of track 12The QAR records the data sequentially on twelve tracks. The tape speed of1.19 cm/sec corresponds to a data rate of 768 bits per second (bps) for a totalrecording time of 50 hours.A memory circuit provides positive memory of tape direction and track numberduring power off periods.The tape drive stops automatically at the end of the last track to prevent eras-ing previously recorded data by re-recording the same segment of tape.When a tape cartridge is extracted, the track memory circuit is automaticallyreset to track 1. A front panel push button is also provided for manual reset totrack 1.The front panel access door must be properly closed before the QAR will oper-ate. The tape cartridge contains 180m of 1/2 inch wide 3M tape.

Page: 22

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


MOD

FLAG

LOWTAPE

CASSETTE CHANGE

MOVED CASSETTEEVER REINSTALL

CAUTION

OT OPEN EXCEPTSTOP

COMPTEURSSCHLUMBERGER

PC 6033

TRACKFIRST

Page: 23Figure 11 QAR

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


ACCELEROMETERThe 3-axis accelerometer, M517, measures vertical, lateral and longitudinalacceleration and provides a separate output signal with respect to ground foreach. Excitation for the accelerometer is 28v dc supplied by the FDAU. Theaccelerometer is a self-contained sealed unit mounted on the aft side of theforward wall of the right wheel well at station 664.

Page: 24

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


ACCELEROMETER

MOUNTED ON SHELF

CONNECTOR

ACCELEROMETERTHREE AXIS

OUTBOARDLATERAL ORY AXIS

OR UPVERTICALZ AXIS

OR UPVERTICALZ AXIS

OR FORWARDLONGITUDINALX AXIS

BULKHEAD)WHEEL WELL FORWARD(AFT SIDE OF RIGHTACCELEROMETER

ELECTRICAL

SCREWS

Page: 25Figure 12 Accelerometer

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


FAULT MONITORINGThe OFF- or FAULT- Condition of DFDR and DFDAMRU can be seen: by illumination of the FR OFF Lamp by illumination of the lamp OVERHEAD in the Master Caution Six-pack by illumination of the lamp MASTER CAUTION by illumination of the lamps at the DFDAMRU front panel

- FDAU FAIL,- DFDR FAIL,- DMU FAIL,

Some Flight Recorders have additional a BITE-AnnunciatorA Fault condition of the Printer is pointed out by its integrated FAIL-Light.All detected failures are also visible by using the MCDU Menu

- ACMS- ACMS MENU- STATUS

A SYSTEM TEST PLUG in the Cockpit allows to measure the FR PWR source and the reading of the FR Data and FR Play Back Data.

Page: 26

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


DFDR MAINT FLAG

FDAU BITE

DATA

PLAYBACK

DFDR STATUS

( SUNDSTRAND )

SYSTEM TEST PLUG

FLIGHT RECORDER MODULE ( P5 )

( P 18 )

MASTERCAUTION

Page: 27Figure 13 FAULT Monitoring

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30


PWR DISTRIBUTION AND CONTROLThe status of the DFDR and the FDAU is indicated by the following discretes: DFDR :

- MAINT FLAG :

FAULT -> OPEN

OK -> GNDThe maintenance flag monitors the internal BITE.

- STATUS :

FAULT -> GND

OK -> 28V DCThe status discrete monitors

- internal BITE,- Data-input,- power supply,- FR-Mode.

DFDAMRU :- BITE OUT :

FAULT -> OPEN

OK -> GND.

Page: 28

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


B737-300/400/500

31-30

Page: 29HAM US/F bo Aug 99 Page: 29Figure 14 PWR Distribution and Control

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DFDR ADJUSTMENT / TESTThis procedure has many tasks. The first task is the Operational Test (BITETest) of the flight data recorder system.The second task is the is the System Test of the flight data recorder system.

Operational TestThe operational test will control the capability of the function or monitoring pos-sibilities of NORM-TEST-Switch, FR-OFF-Light, MASTER CAUTION Light, Oil Pressure Input, AIR / GND-Input, DFDR FAIL Light at the DFDAMRU.

System TestThe system test has procedures to do tests of all the inputs to the flight datarecorder system. You can do the tests out of sequence. You can do each testindependently.To do the system test, much time can be necessary. A different procedure,which makes sure the system writes the parameters correctly, is the copy re-corder procedure (Ref 31-24-00/201).The tests in the procedure are written to the BOEING standard application soft-ware. If customized software is installed part of the test may look different.

Page: 30

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DFDR FAIL

DFDR STATUSF

DA

U B

ITEMASTER

CAUTION

DATA

PLAYBACK

OPERATIONAL TEST SYSTEM TEST

ATECONNECTOR

FLIGHT LINE TESTER

Page: 31Figure 15 DFDR Adjustment /Test

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


FLIGHT RECORDER TESTOn ground, where the flight recorder system normally is OFF, the system canbe activated (power sourced) by selecting the capped Flight Recorder ModuleSwitch in TEST.If the function of the DFDR and DFDAMRU is correct, the OFF-Light will extin-guish.

Page: 32

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DFDAU DFDR

FLIGHT RECORDER MODULE

PWR ON

DFDR STATUSFDAU BITE

Page: 33Figure 16 Flight Recorder Test

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-330/430/530

31-24

Page: 34HAM US/F Bo 21.04.97

TESTS AFTER REMOVAL / INSTALLATION OF LRU S

After removal and installation of each LRU a subsequent test has to be made.The following advices gives only an idea of the complete tests:

Flight Recorder:- FR Test SW ON-OFF.

Advice: The ULB is a part of the aircraft. If a flight recorder must be changed, the ULB must be installed at the new recorder.

FR TEST MODULE:- FR Test SW ON-OFF,- Mach-A/S-Warning Test (1+2).

DFDAMRU (FDAU):- Install the Software (ACMS):

Operational Software Customer Software

Advice: The sequence of software installation has to be observed.

- FR System BITE Test (Operational Test).

EVENT / PRINT SW:- FR System BITE Test (Operational Test),- Weather Radar System Operational Test.

ACC:- FR System BITE Test (Operational Test),- FR System / ACC Signal Test, with

Inclinometer, Portable Tester (Flight Line Tester).

PRINTER:- SLEW Test (Paper Advanced),- FR System BITE Test (Operational Test),- TEST (Printer).

Page: 34

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-330/430/530

31-24

Page: 35HAM US/F Bo 21.04.97

FR Test Module

EVENT /PRINT Switch

PRINTER

DFDAMRUACC

ACMS

DFDR

ULB

Page: 35Figure 17 Tests after Removal /Installation

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30


ACMS GENERALThe main function of the ACMS (Aircraft Condition monitoring System) is toprocess continuously condition monitoring for various A/C systems to do an Engine Condition Monitoring (EGM), Aircraft Performance Monitoring (EPM), APU Condition Monitoring (ACM).

A part of the process is used for creating various A/C condition reports. Thesereports are available for maintenance purposes : as a hard-copy from the PRINTER, on ground via ACARS (if installed).

A Remote Print Button is installed on the cockpit pedestal. An activation ofthis button causes a flight phase dependent Print Report.The ACMS calculation and report management is realized in the DMU-part ofthe DFDAMRU.The SAR-function (Smart Airborne Recorder) is an integrated part of the DMU.This function is based on a nonvolatile Solid State Mass Memory module.Because of the use of SAR, no QAR is installed.SAR data are retrievable with floppy disks by using the MDDU (Multi Disc DriveUnit).The MDDU (or sometimes a Portable Data Loader, PDL) are used for automatic retrieving of reports and SAR files. loading of DMU software.

Page: 36

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30


SAR

DMU

DFDAMRU

Page: 37Figure 18 ACMS Schematic

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30


ACMS MENUPressing the LSk (Line Select Key) ACMS on the Menu Page and then ACMSMENU gives maintenance access to airplane parameter and reports or allowsprogramming, loading and trouble shooting.

Page: 38

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30

Page: 39HAM US/F bo Aug 99 Page: 39Figure 19 ACMS Menu Handling

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-00


ACMS MENU HANDLING

.By pushing the MENU-button on the MCDU, the ACMS-Menu is selectable.

MAIN MENU

ACMS

ACMS MENUFREE

REPORTSAPU DATA

ACMSSTATUS

LOAD /UNLOAD

DMRU MENU ACMS IDENT CONFIG

INSTALLED CONGIGURED

MAN INPUT

STATUSREPORT

DFDAUBITE

DFDRBITE

DMRUBITE

TESTPRINT

STOREDSTAT REP

DISPLAYDATA

DMRUREPORTS

PROGRAMDMRU

ALPHACALL UP

ANALOG /DISCRETE

DISCRETE ANALOG

DITS

CALL UP

PARAMETERMENU

FT MODE APU

REPORTHISTORY

STOREDREPORTS

TEST / PRINT

REMOTE PRTBUTTON

TEST PRT

ENGINEINIT

PREDEFINEDFUNCTION

TEMPORARYCHANGE

PRINTREPORT

ACCESSCODE

ACCESSCODE

( )

-

-

Page: 40

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-00


engineeringhandling

Page: 41Figure 20 ACMS Menu

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-00


STATUSThe STATUS-Menu makes a Fault-Recognition possible for DFDAU, the FDAU-part of the DFDAMRU, DFDR and DMRU, the DMU-part of the DFDAMRU.

In case of an inactive DFDR the advice OFF appears in Flight Mode 1 (A/C on GND), FAIL appears in Flight Mode 2-9 (A/C in FLT).

By selecting the sub menu

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-00


A CM S M E N U

< S T A T U S A CM S I D E N T >

< DM R U M E N U

< CO N F I G U R A T I O N

< L O A D / U N L O A D

< R E T U R N

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

ACMS STATUS

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


ACMS STATUS REPORT The menu REPORTS is divided into two sub menus: STORED REPORTS, which enables the access to the last 5 stored reports.

The identifier tr marks the kind of transmission:- A for ACARS,- P for printing (hard copy).

A report is printable if a caret ( >) exists. TEST PRINT, activates a STATUS REPORT for DFDAU and DMRU

with actual MAINT-Word-Information (down linked via ACARS).If the test passes, GENERATION OK is written in the scratch .

*

Page: 44

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


ACMS STATUS

>

>

>

>

PRINT

Page: 45Figure 22 ACMS STATUS REPORT

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


ALPHA CALL UP

The Alpha Call Up Menu is selectable via < DMRU Menu and < DISPLAY DATA.

If a required parameter is listed in the the Alpha Call Up List ( a part of it isshown below) put it in first into the Scratch Pad and after that push the LSK1L.The source, value and unit of the parameter is indicated than.

LIST OF AVAILABLE ALPHA CALL-UP

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


A CM S M E NU

< S T A T U S A CMS I D E N T >

< DMRU ME N U

< CO N F I GU R A T I ON

< L O A D / UN L O A D

< R E T U R N

1L

2L

3L

4L

5L

6L

1R

2R

3R

4R

5R

6R

DMRU MENU

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


ANALOG / DISCRETEAnalog and discrete inputs into the DFDAMRU are selectable via the sub menu< ANALOG / DISCRETE and than < ANALOG PARAM or < DISCRETE PARAM

An activation of the LSK 6R prints out the whole list.

Page: 48

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU DISPLAY DATA

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DITS CALL UPEvery aircraft parameter, received on a ARINC 429 bus, is selectable by using BUS-number (the port number of the DFDAMRU input port), LABEL and SDI (optional).

The raw value of the parameter is displayed and if the parameter has an alphacall-up, it is displayed with the engineering unit value.The parameter value is refreshed once per second.If the parameter hasnt been refreshed on the ARINC 429 bus in previous twoseconds then the display field contains dashes (---).

NOTE: IF THE FIELDS ARE NOT CORRECT, TWO TYPES OF MES-SAGES MAY BE DISPLAYED:

INVALID FORMAT, if the character do not correspond to what is expected ( letter, label not octal, , sdi not binary, not enough fields).

INVALID DATA, if the data itself are not significant ( label greater than 377,bus that does not exist ).

Page: 50

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU MENU

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


INPUT PORTSBy selecting the menu DITS CALL UP, it is necessary to chose the BUS-Num-ber of the respective system.The BUS-Number is the input port number of the DFDAMRU.The association between BUS-Number and connected system differs betweenthe aircraft types.

Page: 52

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DITS HS* SAR

DFDAMRU

Page: 53Figure 26 Input Ports

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


PARAMETER MENU FLMOD-Menu shows the actual stage of those parameter which are used

for the flight phase calculation (flight mode 1 to 9). APU -Menu shows actual APU-Parameter.

Page: 54

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU DISPLAY DATA

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU REPORTSThis menu contains the sub menus REPORTS HISTORY, in which the last 20 stored reports are listed with the

following information- NB : Number of Report,- COUNT: Report Counts,- DATE,- FLT NO

STORED REPORTS, which indicated in the first instance a list of possiblereports.

Selecting one of these report number via LSK, a list of all stored reports ofthis number are shown in a sequent way, with the last on top

The advice ENTER ACCESS CODE FOR PRINTING AUTHORIZATIONmakes clear that the access code has to be inserted first before activatingthe hard copy print out.

Page: 56

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU MENU

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y

INSTRUMENTSRECORDER

737-300/400/500

31-30


DMRU REPORTS TEST/ PRINT

REMOTE PRINT BUTTONThis page show which print report will be generated according to the flightphases by pushing the remote print button..This programming is realized by the GSE and loaded in the OBPM.Format of displayed data: REP : Number of the report. EP : Engine selected

- 0 : no selection required.- 1 : Engine one (or left) is in first position.- 2 : Engine 2 (or right) is in first position.

TEST PRINTThis page enables the operator to trigger a report to verify its format. The re-ports are effectively programmed by the GSE that are available for triggering.When the request is effective, the message generated OK is printed in thescratch pad.

Page: 58

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y

INSTRUMENTSRECORDER

737-300/400/500

31-30


Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU PROGRAMA program change is only possible after insertion of an access code. After thatthe following parameter may be changed: Engine SN, Engine HRS, Engine CYC, RESET EGT EDM (after ENG-Change), REQUEST FOR

- RPT 01 (for the next Take Off),- RPT 02 ( for the next Take Off),- RPT 03 (for the next 5 Take Offs).

Page: 60

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


DMRU MENU

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


APU DATAThis page displays real time APU-Parameter, ACTUAL APU BITE Informationen in clear language, like

- APU abnormal shutdown, or- ECU BITE,

APU BITE HISTORY.The quantity of the detected BITEs determines the quantity of required pages(1/1 to X/X).

Real time APU-parameter are also available by selecting the following menus: ACMS MENU, DMRU MENU, DMRU DISPLAY DATA, PARAMETER MENU, APU.

Page: 62

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


ACMS

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


SOFTWARE LOADINGThe systems FMC, ACARS and ACMS get their actual software via diskette-loading.This loading will be made by an AIRBORNE DATA LOADER

or, if no data loader is installed, by a PORTABLE DATA LOADER, inclusive DATA LOAD CONTROL PANEL.

Three types of softwares can be loaded: DFDR Data Frame Software Operational Software (DMU Ops Program Software) and Customer Software (Data Base Software)

ADVICE:Have attention to the procedure, which software loading shall be used after Re-moval/Installation of the DFDAMRU.

DFDR Data Frame Software

DFDAMRU P/N ED44B310

DFDAMRU P/N ED44B510

DMU Ops Program Software

Data Base Software

All

All

6

M

2

Page: 64

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30

Page: 65HAM US/F bo Aug 99 Page: 65Figure 32 Software Loading

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


LOAD CONTROLThe implanted software is controllable via the menu LOAD / UNLOAD.During the load sequence following information are given: a) Information as long diskette is not inserted. b) Information 2-3 sec after insertion. c) PERFORMED tells (in this example) that 05 of 64 Files are already loaded. d) Loading has finished.ADVICE:After LOAD COMPLETED appear, it is advisable to monitor the just insertedsoftware via the menu ACMS IDENT.

Page: 66

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


ACMS MENU

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30


PRINTER

GeneralThe printer is connected to the following systems

- ACMS- ACARS

The printer is a nonimpact thermal dot-matrix printer in the aft electronicspanel P8. Controlled by the FDAU, it prints a 40 column line at the rate of 2lines/second.

Page: 68

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30

Page: 69HAM US/F bo Aug 99 Page: 69Figure 34 Printer Location

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30


PRINTER DESCRIPTIONThe front of the printer contains: Panel Release Knob, to open the printer panel and release the paper roll. FULL EMPTY PAPER, indicates the remaining paper supply mechanically. the lamps

- MSG, indicates that a message is received from ACMS or ACARS.- PAPER, illuminates if the paper comes to the end.- FAIL, illuminates in case of a Printer BITE FAULT.

By pushing the following button- SLEW, the. paper moves to advanced position,- RESET, the MSG Light will extinguish,- TEST, a self test starts, followed by a test print,- TEST, and RESET at the same time, a self test starts, followed by an

expanded test print.

Page: 70

Lufth

ansa

Tec

hnic

al T

rain

ing

F

or T

rain

ing

Pur

pose

s O

nly


737-300/400/500

31-30

Page: 71HAM US/F bo Aug 99 Page: 71Figure 35 Printer

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


PAPER ROLL CHANGE

If red mark appear on the paper, or the lamp PAPER illuminates, the paper rollhas to be changed.

To remove the paper roll: the CB PRINT has to be pulled, the door (2) has to be release and opened by quick access device (3), the spring loaded rod (7) has to be release and the paper roll (5) has to be

removed.

To insert a new paper roll: slide the paper roll on the spring loaded rod (7) and lock it (3),

ADVICE: Have attention to the right winding ! shut the door (2) and lock it (3), close the CB PRINTER, push SLEW button (4) for paper advance, remove the advanced paper by tearing it across the paper cutter (1).

ATTENTION:Take care on the thermal-print-strip if door is open. Its very sensitive.

MonitoringThe printer function is affected by loss of paper transport, if the FAIL light illuminates.

The fault status of the printer is pointed out by the STATUS menu of the ACMS.

Page: 72

Lufth

ansa

Tec

hnic

al T

rain

ing

For

Tra

inin

g P

urpo

ses

Onl

y


737-300/400/500

31-30


A

B

C

56

7

23

7

5

4

1

Page: 73Figure 36 Printer Roll Change

Nur zur Schulung

HAM TS 32 Bo 09.94 Seite: 74

INS

TR

UM

EN

TS

FL

IGH

T D

ATA

RE

CO

RD

ER

SY

ST

EM

737-

330/

430/

530

XX

X

31-2

0

Lu

fth

ansa

TE

CH

NIS

CH

E S

CH

UL

UN

G

SPARE PAPER ROLLS

Figure A Location A3

Emty page A3 01.pdfTabelle1

Date post:	11-Sep-2015
Category:	Documents
Upload:	meda
View:	701 times
Download:	94 times

B737-3 ATA 31-20, -30 L3 e

Documents