B737-3 ATA 31-20, -30 L3 e
description
Transcript of B737-3 ATA 31-20, -30 L3 e
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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)
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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
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TABLE OF CONTENTS
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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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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TABLE OF FIGURES
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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. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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INSTRUMENTSFLIGHT DATA RECORDER SYSTEM
737-330 /430/530
31
Page: 1HAM US/F bo 21.04.97
ATA 31 INSTRUMENTS
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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
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INSTRUMENTSINDEPENDENT INSTRUMENT
B737-300/400/500
31-20
Page: 3HAM US/F bo Aug 99
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
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INSTRUMENTSINDEPENDENT INSTRUMENT
B737-300/400/500
31-20
Page: 4HAM US/F bo Aug 99
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.
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INSTRUMENTSINDEPENDENT INSTRUMENT
B737-300/400/500
31-20
Page: 5HAM US/F bo Aug 99
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
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INSTRUMENTSINDEPENDENT INSTRUMENT
B737-300/400/500
31-20
Page: 6HAM US/F bo Aug 99
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.
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INSTRUMENTSINDEPENDENT INSTRUMENT
B737-300/400/500
31-20
Page: 7HAM US/F bo Aug 99
Captains Clock
First Officers Clock
FMC
DFDAU
Page: 7Figure 3 Clock Interface
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 8HAM US/F bo Aug 99
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).
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 9HAM US/F bo Aug 99
QAR(option)
Page: 9Figure 4 General Schematic
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 10HAM US/F bo Aug 99
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.
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 11HAM US/F bo Aug 99
SPARE PAPER ROLLS
Page: 11Figure 5 Location of DFDR/ACMS
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 12HAM US/F bo Aug 99
LRU LOCATIONDifferent types of Flight Recorders may be used: Tape Recorder or Solid StateFlight Data Recorder.
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 13HAM US/F bo Aug 99
Lockheed Martin /Fairchield
Lockheed Martin /
Page: 13Figure 6 LRU Location
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 14HAM US/F bo Aug 99
SENSOR LOCATIONIn the new 737-Generation additional sensors are installed for record purposeonly .
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 15HAM US/F bo Aug 99
Aileron Position Transmitter
Speddbrake HandlePosition Sensor
Rudder PositionTransmitter T469
Elevator Position TransmitterL: T467 R: T468
M1439
Page: 15Figure 7 Sensor Location
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 16HAM US/F bo Aug 99
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
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 17HAM US/F bo Aug 99
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
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 18HAM US/F bo Aug 99
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
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 19HAM US/F bo Aug 99
INDICATORS
LED FAULT
PLUG
TEST SET
Page: 19Figure 9 FDAU
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INSTRUMENTSRECORDERS
B737-300/400/500
31-30
Page: 20HAM US/F bo Aug 99
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.
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Page: 21HAM US/F bo Aug 99
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
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Page: 22HAM US/F bo Aug 99
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.
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Page: 23HAM US/F bo Aug 99
MOD
FLAG
LOWTAPE
CASSETTE CHANGE
MOVED CASSETTEEVER REINSTALL
CAUTION
OT OPEN EXCEPTSTOP
COMPTEURSSCHLUMBERGER
PC 6033
TRACKFIRST
Page: 23Figure 11 QAR
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Page: 24HAM US/F bo Aug 99
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.
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31-30
Page: 25HAM US/F bo Aug 99
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
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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.
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Page: 27HAM US/F bo Aug 99
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
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Page: 28HAM US/F bo Aug 99
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.
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Page: 29HAM US/F bo Aug 99 Page: 29Figure 14 PWR Distribution and Control
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Page: 30HAM US/F bo Aug 99
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.
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Page: 31HAM US/F bo Aug 99
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
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Page: 32HAM US/F bo Aug 99
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.
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Page: 33HAM US/F bo Aug 99
DFDAU DFDR
FLIGHT RECORDER MODULE
PWR ON
DFDR STATUSFDAU BITE
Page: 33Figure 16 Flight Recorder Test
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INSTRUMENTSFLIGHT DATA RECORDER SYSTEM
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).
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INSTRUMENTSFLIGHT DATA RECORDER SYSTEM
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
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Page: 36HAM US/F bo Aug 99
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.
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Page: 37HAM US/F bo Aug 99
SAR
DMU
DFDAMRU
Page: 37Figure 18 ACMS Schematic
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Page: 38HAM US/F bo Aug 99
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.
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31-30
Page: 39HAM US/F bo Aug 99 Page: 39Figure 19 ACMS Menu Handling
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31-00
Page: 40HAM US/F bo Aug 99
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
( )
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Page: 41HAM US/F bo Aug 99
engineeringhandling
Page: 41Figure 20 ACMS Menu
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Page: 42HAM US/F bo Aug 99
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
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Page: 43HAM US/F bo Aug 99
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
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Page: 44HAM US/F bo Aug 99
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 .
*
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Page: 45HAM US/F bo Aug 99
ACMS STATUS
>
>
>
>
PRINT
Page: 45Figure 22 ACMS STATUS REPORT
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Page: 46HAM US/F bo Aug 99
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
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Page: 47HAM US/F bo Aug 99
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
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Page: 48HAM US/F bo Aug 99
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.
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Page: 49HAM US/F bo Aug 99
DMRU DISPLAY DATA
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31-30
Page: 50HAM US/F bo Aug 99
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 ).
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Page: 51HAM US/F bo Aug 99
DMRU MENU
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Page: 52HAM US/F bo Aug 99
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.
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Page: 53HAM US/F bo Aug 99
DITS HS* SAR
DFDAMRU
Page: 53Figure 26 Input Ports
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Page: 54HAM US/F bo Aug 99
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.
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Page: 55HAM US/F bo Aug 99
DMRU DISPLAY DATA
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Page: 56HAM US/F bo Aug 99
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.
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Page: 57HAM US/F bo Aug 99
DMRU MENU
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Page: 58HAM US/F bo Aug 99
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.
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31-30
Page: 59HAM US/F bo Aug 99
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Page: 60HAM US/F bo Aug 99
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).
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Page: 61HAM US/F bo Aug 99
DMRU MENU
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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.
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Page: 63HAM US/F bo Aug 99
ACMS
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Page: 64HAM US/F bo Aug 99
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
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Page: 65HAM US/F bo Aug 99 Page: 65Figure 32 Software Loading
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Page: 66HAM US/F bo Aug 99
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.
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Page: 67HAM US/F bo Aug 99
ACMS MENU
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Page: 68HAM US/F bo Aug 99
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.
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Page: 69HAM US/F bo Aug 99 Page: 69Figure 34 Printer Location
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Page: 70HAM US/F bo Aug 99
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.
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Page: 71HAM US/F bo Aug 99 Page: 71Figure 35 Printer
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Page: 72HAM US/F bo Aug 99
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.
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Page: 73HAM US/F bo Aug 99
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