Senies 3200 MAINTENANCE MANUAL. CHAPTER 31 TABLE OF CONTENTS INDICATING AND RECORDING SYSTEMS - GENERAL DESCRIPTION AND OPERATION General Description and Operation AIRCRAFT CLOCK - DAVTRON MODEL 811 DESCRIPTION AND OPERATION General Description DAVTRON 811 AIRCRAFT CLOCK REMOVAL/ INSTALLATION Remove Clock Battery R ep acement AIRCRAFT CLOCK - DAVTRON 811 ADJUSTMENT /TEST Clock Adjustment - Time Correction FLIGHT DATA RECORDER 31-00-00 31-25-00 31-25-00 aineaete 31-37-00 ALL 1 1 1 ALL ‘ 1 1 ALL 01 01 04 ALL 501 501 B41 844 846 848 851 853-855 857 859 861 864 BAO R7R 31-CONTENTS Page 1 Apr 15/08‘Sexies 3200 MAINTENANCE MANUAL. SUBJECT CH/SE/SU iis eee eataay: DESCRIPTION AND OPERATION 1 FAIRCHILD NON-EXTENDED PARAMETER SYSTEM 31-37-00 841 844 B46 848 851 853-855 857 859 861 864 869 878 Description 1 Operation 1 FLIGHT DATA RECORDER 31-37-00 B41 844 B46 848 851 853-855 857 859 861 864 869 878 REMOVAL/ INSTALLATION 401 FATRCHILD NON-EYTENDED PARAMETER SYSTEM 31-37-00 RL1 Rhb RA 848 851 853-855 857 859 861 864 869 878 Remove Flight Data Recorder 401 Flight Data Recorde 402 Remove Vertical Accelerometer 404 Install Vertical Accelerometer 405 31-CONTENTS Page 2 Apr 15/08Senies 3200 MAINTENANCE MANUAL. SUBJECT CHISE/SU FLIGHT DATA RECORDER ~ FAIRCHILD 31-37-00 NON-FXTENDFD PARAMFTFR SYSTFM ADJUSTMENT /TEST Operational Test of Flight Dat Recorder (FDR) System Functional Test of Flight Data Recorder (FDR) System FLIGHT DATA RECORDER - FAIRCHILD 31-37-00 NON-EXTENDED PARAMETER SYSTEM INSPECTION CHECK Do a Detailed Inspection of the Vertical Accelerometer (1UB2) FLIGHT DATA RECORDER - DESCRIPTION AND 31-38-00 OPERATION FAIRCHILD EXTENDED PARAMETER SYSTEM DESCRIPTION AND OPERATION GENERA Description Operation SAGs enn: 501 501 502 601 601 841 844 846 BGR R54 853-855 857 859 861 864 869 878 B41 B44 B46 848 851 853-855 857 859 861 864 869 878 31-CONTENTS Page 3 May 15/04‘Sexies 3200 MAINTENANCE MANUAL. SUBJECT CH/SE/SU = PAGE = EFFECTIVITY. FLIGHT DATA RECORDER - FAIRCHILD 31-38-00 910 912-916 FXTFNDFD PARAMFTFR SYSTFM O58: esa 930-931 934 941-942 946-949 951-953 957-959 961-969 REMOVAL/ INSTALLATION 401 Remove Flight Data Recorder 401 Install Flight Data Recorder 402 Remove Dual-Axial Accelerometer 405 Install Dual-axial Accelerometer 406 FLIGHT DATA RECORDER - FAIRCHILD 31-38-00 910 912-916 EXTENDED PARAMETER SYSTEM 919 927-928 SS 930-931 934 941-942 946-949 951-953 957-959 961-969 ADJUSTMENT/TEST 501 Operational Test of FDR System 503 Functional Test of FDR System 504 31-CONTENTS Page 4 Apr 15/05Senies 3200 MAINTENANCE MANUAL. SUBJECT CHISE/SU SAGs enn: FLIGHT DATA RECORDER ~ FAIRCHILD 31-38-00 910 912-916 FXTFNDFD PARAMFTFR SYSTFM 919 977-928 930-931 934 941-942 946-949 951-953 957-959 961-969 INSPECTION CHECK 601 Do a Detailed Inspection of the 601 Dual Axial Accelerometer (1UB2) UNDERWATER LOCATOR BEACON 31-38-05 910 912-916 919 927-928 930-931 934 941-942 946-949 951-953 957-959 961-969 REMOVAL / INSTALLATION 401 Remove Underwater Locator Beacon 401 (ULB) and Battery Install Underwater Locator Beacon 406 (ULB) and Battery 31-CONTENTS Page 5 Apr 15/05‘Sexies 3200 MAINTENANCE MANUAL. SUBJECT UNDERWATER LOCATOR BEACON ADJUSTMENT/TEST Functional Test of Underwater Locator Beacon (ULB) UNDERWATER LOCATOR BEACON CLEANING & PAINTING Clean Water Switch of Underwater Locator Beacon (ULB) CENTRAL WARNING SYSTEMS - DESCRIPTION AND OPERATION DESCRIPTION AND OPERATION GENERAL Description and Operation CENTRAL WAKNING SYSTEMS CH/SE/SU 31-38-05 31-38-05 31-50-00 31-50-UU 501 501 701 701 EEFECTIVITY 910 912-916 919 977-928 930-931 934 941-942 946-949 951-953 957-959 961-969 910 912-916 919 927-928 Saute ree 941-942 946-949 951-953 957-959 961-969 ALL ALL 31-CONTENTS Page 6 Apr 15/05Senies 3200 MAINTENANCE MANUAL. SUBJECT CHISE/SU SAGs enn: PEMo! 404 Remove Central Annunciator Panel 401 Install Central Annunciator Panel 406 Remove Test Junction Box 407 Install Test Junction Box 408 Remove Cap Individual Caption 410 Install CAP Individual Caption 4 CENTRAL WARNING SYSTEM 31-50-00 ALL ADJUSTMENT /TEST 501 Operational Test of Central Warning 501 System Central Annunciator Panel (CAP) 505 Dormant Fault Test 31-CONTENTS Page 7 May 15/04Page left intentionally blankSenies 3200 MAINTENANCE MANUAL. CHAPTER 314 LIST OF EFFECTIVE PAGES CONTENTS 1 Apr 15/08 CONTENTS 2 Apr 15/08 CONTENTS 3 May 15/04 CONTENTS 4 Apr 15/05 CONTENTS 5 Apr 15/05 CONTENTS 6 Apr 15/05 CONTENTS 7 May 15/04 31-00-00 1 May 15/04 31-25-00 1 Jul 15/02 . Jul 15/02 3 Jun 15/01 4 Jun 15/04 31-25-00 401 Jun 15/04 402 Jun 15/01 404 Jun 15/01 405 Jun 15/04 31-25-00 501 Jun 15/01 502 Jun 15/04 503 Jun 15/04 Page 1 Apr 15/08Senies 3200 MAINTENANCE MANUAL CHAPTER/SECTION/SUBJECT PAGE DATE lee ce a May 15/04 2 May 15/04 3 May 15/04 4 May 15/04 Pe ee 401 May 15/04 402 May 15/04 403 May 15/04 404 May 15/04 405 May 15/04 406 May 15/04 31-37-00 501 May 15/04 502 May 15/04 503 May 15/06 504 May 15/04 505 May 15/04 506 May 15/04 507 May 18/04 31-37-00 601 May 15/04 602 May 15/04 31-38-00 1 Apr 15/05 2 Apr 15/05 3 May 15/04 4 May 15/04 5 May 15/04 6 Apr 15/05 7 May 15/04 8 may 13/06 31-LEP Page 2 Apr 15/08‘Senies 3200 MAINTENANCE MANUAL CHAPTER/SECTION/SUBJECT PAGE DATE 9 Nay 15/04 40 Apr 15/05 4 May 15/04 2 Apr 15/05 3 Nay 15/04 14 May 15/04 BEE May 15/04 31-38-00 401 Apr 15/05 402 May 15/04 403 May 15/04 404 Nay 15/04 405 Nay 15/04 406 Nay 15/04 407 May 15/04 408 May 15/06 31-38-00 501 Apr 15/05 502 Apr 15/08 soz Apr 15/08 504 Apr 15/08 505 Apr 15/08 506 Apr 15/08 507 Apr 15/08 508 Apr 15/08 509 Apr 15/08 510 Apr 15/08 341 Apr 15/08 512 Apr 15/08 513 Apr 15/08 514 Apr 15/08 15 Apr 13/08 31-LEP Page 3 Apr 15/08Senies 3200 MAINTENANCE MANUAL CHAPTER/SECTION/SUBJECT PAGE DATE 516 Apr 15/08 eer Apr 15/08 518 Apr 15/08 519 Apr 15/08 520 Apr 15/08 men Apr 15/08 cam Apr 15/08 523 Apr 15/08 524 Apr 15/08 sea Apr 15/08 526 Apr 15/08 527 Apr 15/08 528 Apr 15/08 529 Apr 15/08 530 Apr 15/08 531 Apr 15/08 532 Apr 15/08 533 Apr 15/08 534 Apr 15/08 31-38-00 601 Apr 15/05 602 May 15/04 31-38-05 401 Apr 15/05 402 Apr 15/05 403 May 15/04 404 May 15/04 405 May 15/04 406 Apr 15/05 407 May 15/04 408 May 15/04 31-LEP Page 4 Apr 15/08CHAPTER/SECTION/ SUBJECT 31-38-05 31-38-05 31-50-00 31-50-00 Senies 3200 MAINTENANCE MANUAL. PAGE 501 503 701 702 703 401 402 4uS Apr May May Apr May May Nay Nay Nay Nay Ape Nay May May May Nay Nay Apr Ape Apr Nay Apr Apr Apr Apr May 31-LEP Page 5 Apr 15/08‘Senies 3200 MAINTENANCE MANUAL CHAPTER/SECTION/ SUBJECT PAGE DATE 404 Apr 15/05 405 May 15/04 406 Apr 15/05 407 Apr 15/05 408 May 15/04 409 May 15/04 410 May 15/06 ant Apr 15/05 412 Apr 15/05 413 May 15/06 31-50-00 501 May 15/04 502 Apr 15/05 503 Apr 15/05 504 Apr 15/05 505 Apr 15/05 506 Apr 15/05 507 Apr 15/05 508 Apr 15/05 509 Ape 15/05 31-LEP Page 6 Apr 15/083200 MAINTENANCE MANUAL #* For Aircraft ALL#e INDICATING AND RECORDING SYSTEMS - GENERAL DESCRIPTION AND OPERATION 1. General This chapter contains the information on the aircraft indicating and recording systems and flight data recorder. 2. Description and Operation A. Aircraft clock Inis panel mounted instrument powered by an internal battery which powers its electronics, presents a digital display of time, tlight time or elapsed time. The digital display Lighting is powered from the aircraft 28V dc supply. B. Central warning system This system indicates the condition of systems and equipment. Most system warning indications are given on the annunciator panel which is mounted on the glareshield, centrally hetween the two pilots and contains red and amber annunciators which warn of a hazardous or cautionary state. The annunciator panel also incorporates red flashing attention getters which can be manually cancelled. te For Aircraft R41 Rhh BLA BUR RST _RSZ-RSS RST REO RAI _RKA RAY R7R 910 912-916 919 927-928 930-931+% C. Flight Data Recorder (FDR) The FDR is installed in the rear equipment and records and stores aircraft flight parameters. +* For Aircratt ALL#* 31-00-00 May 13706Page left intentionally blank3200 MAINTENANCE MANUAL #* For Aircraft ALL#e AIRCRAFT CLOCK - DAVTRON MODEL 811 DESCRIPTION AND OPERATION General A clock mounted on each pilot's main instrument panel is for general use by the pilots and is also used for navigation. Description (Ref. Figure 1) The clocks are powered from the Avionics Essential (LH) and the Avionics non Essential (RH). A battery provides continuity of operation when power 1s removed trom the atrcratt. Switches incorporated in the face of the clock operate as detailed below. AL Display select This switch marked TINE/FT/ET/ is a three position switch to select the function to be displayed. When set to TINE, the clock displays real time in hours, minutes and seconds. The time channel may be set to local time or GMT. When set to FT (flight time), the clock displays flight time in hours, minutes and seconds. The supply to activate the commencement and cessation of flight time is routed via the relay which is energized and de-energized via nosewheel oleo switch to give the actual flight time. The flight time can only be zeroed with the aircraft power OFF When cet to ET (elapsed time), the clock displays elapsed time in hours, minutes and seconds. Elapsed time recording is controlled by pilot operation of the elapsed time control switch to stop, start and zero the clock for approach, hole off, etc. Elapsed time control switch Position ZERO is a momentary position and sets the elapse: time to zero (when aircraft power is OFF). The switch returns to STOP when released. 31-25-00 Page 1 Jul 15/02JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. Setting the time control switch to STOP, will stop the elapsed time meter. Setting the time control switch to RUN, starts the elapsed time meter Dimmer switch The switch is marked B/DIM/1 hr up. Position B is the bright position for daylight use. Position DIM dims the internal lights for night operation. The 1 hr up po cleck one hour ahead every time the switch is position and released, Time correction switch The switch marked UP/D/SET is used to set the clock to the correct time. Selection UP is a momentary position and sets the clock one second up for every second held. When released the switch returns to the SET, normal position. With the switch set to position D, momentary position, the clock is set one second down tor each second held. When released, the switch returns to the SET, normal position. Power supplies (Ref. Figure 2) Power supply to the left main panel clock lighting circuit js taken from the avionics essential bus-bar, circuit breaker CLK-L 1UD1, and is routed to the clock via a voltage dropping resistor 4UD3 to reduce the voltage to 14V de. The power supply for the right main panel clock Lighting circuit is taken from the avionics main bus-bar circuit breaker CLK-R, 2UD1 and is routed to the clock via resistor Dung The power supply for the clock elapsed time function is taken from the same supply via diodes 1UD4, left clock and ZUD4, right clock and contacts B2 and B3 of relay 1RX11. 31-25-00 Page 2 Jul 15/02‘Senies 3200 MAINTENANCE MANUAL Aircraft Clock - Davtron Figure 1 31-25-00 Page 3 Jun 15/01MAINTENANCE MANUAL. - fy Aircraft Clocks ~ Schematic Figure 2 31-25-00 Page 4 Jun 15/013200 MAINTENANCE MANUAL #* For Aircraft ALL#e DAVTRON 811 AIRCRAFT CLOCK RENOVAL/ INSTALLATION 1. Remove Clock (Ref. Figure 401) A. Special tools and equipment Table No. 401 ITEM DESIGNATION None Warning notice None Blanking cap B. References Table No. 402 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General C. Procedure Removal procedures for left and right components are similar. References for right components are given in brackets. (1) De-energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201 ). (2) Open and tag avionics essential bus-bar circuit breaker CLK-L and avionics main bus-bar circuit breaker CLK-R. (3) Place @ warning notice on circuit breaker panel stating that circuit breakers must not be closed (4) Locate clock on left (right) instrument panel. 31-25-00 Page 401 Jun 15/01JETSTREAM ‘Scxies 3200 MAINTENANCE MANUAL (5) Remove eleven screws securing left (right) instrument panel, retain screws. (6) Ease left (right) instrument panel forward. (7) Remove four screws securing clock to instrument panel, retain screws. (8) Disconnect electrical connectors from clock. (9) Install blanking caps on electrical connectors. (10)Remove clock from instrument panel. A. Special tools and equipment Table No. 403 ITEM DESIGNATION Hone References Warning notice Table No. 404 REFERENCE DESCRLPILON 24-00-00 Page block 31-25-00 Page block C. Procedure Installation prace 201 Electrical power - General 501 Aircraft clock es for Left and right components are similar. References for right components are given in brackets. (1) Make sure clock battery voltage is more than 4.25V. If battery voltage is lower than 4.25V, replace battery (Ref. Section 3.) . 31-25-00 Page 402 Jun 15/01‘Senies 3200 MAINTENANCE MANUAL Davtron Clock Figure 401 31-25-00 Page 403 Jun 15/01a5 AL JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. (2) Make sure aircraft de bus-bars are de-energized (Ref. Chapter 24-00-00, page block 201 ). (3) Make sure avionics essential bus-bar circuit breaker Clk-l and avionics main hus-har circuit breaker C1K-R are open and tagged. (4) Make sure warning notice is in position on circuit breaker panels (5) Locate Left (right) instrument panel and clock position. (6) Ease left (right) instrument panel forward. (7) Position clock in rear face of left (right) instrument panel. (8) Secure clock to instrument panel with four screws. (9) Remove blanking caps and connect electrical connectors to clock (10)Ease left (right) instrument panel rearward and secure with eleven screws. (11)Remove tags and close avionics essential bus-bar circuit breaker CLK-L and avionics main bus-bar circuit breaker CLK-R.. (12)Remove warning notice from circuit breaker panel (13)Energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201 ). (14)Make sure clock indicates correct time. Adjust if required. Battery Replacement Procedure CAUTION - DO NOT ALLOW RED AND BLACK BATTERY LEADS TO TOUCH EACH OTHER, AS THIS WILL REDUCE BATTERY LIFE. (1) Remove clock from left (right) instrument panel (Ref. Section 1.) 31-25-00 Page 404 Jun 15/013200 MAINTENANCE MANUAL (2) Release tie-wrap securing battery to clock. (3) Cut battery leads, retaining enough length of cable from clock to enable new battery leads to be correctly spliced. (4) Attach new battery using butt splices to connect battery to clock leads. (5) Secure battery to clock with tie-wrap. (6) Set clock to correct time (Ref. Chapter 31-25-00, page block 201 ) NOTE : Change battery as close as possible to the hour, to reduce the length of time the set switch has to be held to reset clock. 31-25-00 Page 405 Jun 15/01Page left intentionally blank3200 MAINTENANCE MANUAL #* For Aircraft ALL#e AIRCRAFT CLOCK DAVTRON 811 ADJUSTHENT/TEST 1. Clock Adjustment - Time Correction (Ref. Figure 501) Make sure you have an accurate time check. A. Procedure (1) Set seconds (a) Set UP/D/SET switch to UP, to move clock one second forward for every second the switch is neid. (b) Set UP/D/SET switch to D, to move clock one second down for every second the switch is held. (c) Return UP/D/SET switch to SET when correct time is seconds in set. (2) Set minutes (a) Hold UP/D/SET switch to UP, to move clock forward. The minutes will move forward, every time the seconds display resets to zero seconds. (b) Hold UP/D/SET switch to D, to move clock minutes back. The minutes will move backward, every time the seconds display resets to zero seconds. (c) Return UP/D/SET switch to SET when correct time in minutes is set. (3) Set hours (a) Set B/DIM/1 hr up switch to 1 hr up, to move clock 1 hour forward for every time switch is operated. (b) R t n W tch to B or DIM when correct time in i (4) Corrections after battery replacement 31-25-00 Page 501 Jun 15/01JETSTREAM ‘Scxies 3200 MAINTENANCE MANUAL (a) If after battery replacement, clock readout shows jllegal numbers or blank digits, corrections can be made as follows: 1 Frrars in elapsed or flight time modes can he — corrected by resetting each channel by use of TERO/STOP/RUN switch id Errors in time mode can be corrected by use of = B/DIN/1 hr up switch to correct hour digits. If minutes have illegal numbers, clock will count through illegal numbers. After clock corrects itself, hold UP/SET/D switch to either UP or D position to bring minutes on clock into 31-25-00 Page 502 Jun 15/01‘Senies 3200 MAINTENANCE MANUAL Davtron Clock Figure 501 31-25-00 Page 503 Jun 15/01Page left intentionally blank3200 MAINTENANCE MANUAL ** For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878% FLIGHT DATA RECORDER DESCRIPTION AND OPFRATTON FAIRCHILD NON-EXTENDED PARAMETER SYSTEM 1. General If the aircraft is Post SB 31-JK2807 the aircraft will have b modified to an extended parameter system. Refer to Chapter 31-38-00 for all information. vertical accelerations, airspeed, and time. The Fairchild digital F underwater locating device. altitude, commu DR is complete w Description (Ref. Figure 1 The main components of the FDR system are a recorder unit and vertical accelerometer.The recorder is contained in a 1/2 ATR long case and is mounted in the fuselage tail section to the rear of the pressure bulkhead between STN 425 and 44 on the left of the aircraft. Within the FDR are a power supply (two-phase induction motor), interface, synchro/multiplexer, synchro/digital converter, pneumatic airspeed and altitude transducers, analogue/digital converter and record unit (write amplifier, read amplifier and built-in test equipment). The record unit records aircraft operating information for a maximum of 25 hours. All data is read out three seconds after recording and fed to the built-in test equipment which continuously monitors incoming data and power, and internal operation of the recorder f 2 Operation (R Figu main bus-bar via circuit breaker FDR, 1UB1, and from the 28V de avionics essential bus-bar via circuit breaker FDR FAIL, 1UB8. The parameters recorded by the FDR are derived from the vertical accelerometer, the pilot's radio magnetic indicator and timing of communication events from the cockpit voice recorder. 31-37-00 Page 1 May 15/04JETSTREAM MAINTENANCE MANUAL. Sb RSS 0) a0 ooh Universa \ Flight Data Recorder - Component Location Figu : 31-37-00 Page 2 May 15/043200 MAINTENANCE MANUAL Altitude and airspeed are sensed by the unit's own transducer from pitot and static pressures supplied to it. Pitot pressure is derived from system P2 and static pressure from system $5. The FDR is operative when the hus-hars are energized and the circuit breakers closed. If a fault is sensed in the FDR, the amber FDR FAIL indicator, on the right upper centre instrument panel, will illuminate. Pushing the indicator activates an jetegral switch to test the filaments. 31-37-00 Page 3 May 15/04JETSTREAM ‘Scxies 3200 MAINTENANCE MANUAL vsggte Le | fea] Universal Flight Data Recorder System - Schematic 31-37-00 Page 4 May 15/043200 MAINTENANCE MANUAL ** For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878% ae FLIGHT DATA RECORDER RFMOVAT /TNSTAII ATTON FAIRCHILD NON-EXTENDED PARAMETER SYSTEM Remove Flight Data Recorder (FDR) A. Spec jal tools and equipment Table No. 401 ITEM DESIGNATION None Warning notice None Blanking caps B. References Table No. 402 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General Cc. Procedure (1) De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). (2) Open and tag the following avionics bus-bar circuit breakers: = 115V ac main, FDR _ (3) Place a warning notice on avionics circuit breaker roof panel, stating that circuit breakers must not be closed. (4) Remove access panel F26 . 31-37-00 Page 40 May 15/04(5) (6) wn «ay «9 JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. Disconnect pitot and static connections from FDR. Install blanking caps on pipes and FDR connections. On FOR support structure, remove and retain holt, washer and stiffnut securing top of support. Lower support strut to permit removal of FDR On FDR mounting tray: (a) Remove and discard Lockwire from two hold-down mechanism knurled knobs. (b) Loosen and release knurled knobs from FDR hold-down Carefully pull FDR to disengage rear electrical connector from mounting tray connector. (10)Remove FDR from mounting tray. Install Flight Data Recorder (FDR) A. Special tools and equipment Table No. 403 ITEM DESIGNATION None Warning notice B. References Table No. 404 REFERENCE DESCRIPTION 24-00-00 Page biock 201 Bieciricai power - Generai 31-37-00 Page block 501 Flight data recorder - Adjustment/Test 34-11-00 Page block 501 Pitot/static system - General 31-37-00 Page 402 May 15/043200 MAINTENANCE MANUAL C. Procedure (1) De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). (2) Open and tag the following avionics bus-bar circuit breakers: = 115V ac main, FOR - 28V de essential switched, FDR FAIL (3) Make sure warning notice is in position on avionics circuit breaker roof panel. (4) Place FDR on mounting tray and carefully push back connector. (5) On FDR mounting tray: (6) Engage two hold-down mechanism knurled knobs with FDR hold=down hooks. (a) Tighten knurled knobs until FOR electrical connector is fully mated with mounting tray connector. (b) Satety knurled knobs with Lockwire . (7) On FDR support structure, raise support strut and secure with bolt, washer and stiffnut. (8) Remove blanking caps and connect pitot and static pipes to FDR. (9) Remove tags and close the following avionics bus-bar circuit breakers: = 145V ac main, FDR - 28V do essential switched, FDR FAIL (10)Remove warning notice from circuit breaker panel (11)No a Leak and cance tect af pitat cyctem P2 (Ref. Chapter 34-11-00, page block 501 ). (12)Do a leak and sense test of static system S5 (Ref. Chapter 34-11-00, page block 501 ). 31-37-00 Page 403 May 15/04JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. (13)Make sure work area is clean and clear of tools and miscellaneous items of equipment. (14)Install access panel F26 . (15)D0 an operational test of FDR system (Ref. Chapter 31-37-00, page block 501 ). ove Vertical Accelerometer A. Special tools and equipment Table No. 405 ITEM DESIGNATION None Warning notice B. References Table No. 406 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 53-20-10 Page block 201 Cabin floor panels C. Procedure (1) De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). (2) Open and tag the following avionics bus-bar circuit breakers: = 115V ac main, FOR (3) Place a warning notice on avionics circuit breaker roof panel, stating that circuit breakers must not be closed. 31-37-00 Page 404 May 15/043200 MAINTENANCE MANUAL (4) Remove cabin floor panel R2 (Ref. Chapter 53-20-10, page block 201 ). (5) Locate vertical accelerometer on mounting bracket under floor at right side STN 213. (6) Disconnect electrical connector from vertical accelerometer. CAUTION - DO NOT JAR OR DROP THE ACCELEROMETER AS ————_ INTERNAL DAMAGE MAY OCCUR. (7) Remove four bolts and four washers securing vertical accelerometer to mounting bracket. Remove vertical acceteromecer. Instatl Vertical Accelerometer A. Special tools and equipment Table No. 407 ITEM DESIGNATION None Warning notice B. References Table No. 408 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 31-37-00 Page block 501 Flight data recorder - Adjustment/Test 53-20-10 Page block 201 Cabin floor panels C. Procedure (1) De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). 31-37-00 Page 405 May 15/04(2) (3) «4 aed (8) oo JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. Open and tag the following avionics bus-bar circuit breakers: - 115V ac main, FDR - 28V dc essential switched, FDR FAIL Nake sure warning notice is in position on avionics circuit breaker roof panel. CAUTION - DO NOT JAR OR DROP THE ACCELEROMETER AS INTERNAL DAMAGE MAY OCCUR, Position vertical accelerometer on mounting bracket under floor at right side STN 213. Connect eteciricad connector iv verticai acceterometer. Remove tags and close the following avionics bus-bar circuit breakers: = 115V ac main, FOR - 28V dc essential switched, FDR FAIL Remove warning notice from circuit breaker panel Do a functional test of FDR vertical acceleration (Ref. Chapter 31-37-00, page block 501 ). Secure vertical accelerometer to mounting bracket with four bolts and four washers. (10)Make sure work area is clean and clear of tools and miscellaneous items of equipment. (11)Install floor panel RZ (Ref. Chapter 53-20-10, page block 501). 31-37-00 Page 406 May 15/04‘Senies 3200 MAINTENANCE MANUAL ** For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878% FLIGHT DATA RECORDER - FAIRCHILD NON-EXTENDED PARAMETER SYSTEM ANMWISTMENT/TFST 1. General If the aircraft POSTSB 31-JK2807 the aircraft will have been modified to an extended parameter system. Refer to Chapter 31-38-00 for all information. 2. Operational Test of Flight Data Recorder (FOR) System A. References Table No. 501 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General B. Procedure (1) Energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, Page block 201 ). (2) Open and tag the following avionics bus-bar circuit breakers: - 28V de essential switched, FDR FAIL - 115V ac main, FDR (3) Do the operational test of FDR STEP ACTION RESULT (1) Set AVIONICS MASTER switch On right upper centre ESSENTIAL to ON. instrument panel, FDR FAIL caption is extinguished. (2) Close avionics bus-bar circuit FDR FAIL caption illuminates breaker 28V dc essential switched, FOR FAIL 31-37-00 Page 501 May 15/043. JETSTREAM ‘Scxies 3200 MAINTENANCE MANUAL STEP ACTION RESULT nics bus-bar circuit FDR FAIL caption extinguishes. (3) Close avi (4) De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, Page block 201 ). (5) Make sure work area is clean and clear of tools and miscellaneous items of equipment. Functional Test of Flight Data Recorder (FDR) System General With the exception of operation of FDR fail lamp, the purpose of this test procedure is to generate flight data sensor inputs to the FDR, prior to its removal for overhaul at the frequency determined by the manufacturer. Subsequent laboratory analysis of FDR tape contents will appraise serviceability of FDR system components. The FDR system can also he tested at the frequency determined by local airworthiness authority. Chapter 31-38-00, gives details of the substitution of F800 FDR with F1000 FDR, so that a portable analysis unit can be used to monitor tests of the following parameters: - Vertical acceleration - Magnetic heading = Communication event 2 Atedeude - Airspeed. If required do the following tasks (Ref. Chapter 31-38-00, page block 501 ). = FDR system preparation - Copy and confirmation of F1000 FDR flight test data - Vertical and longitudinal acceleration test (omit steps that refer to longitudinal acceleration (LNG ACC)) Airspeed test Aititude test Nagnetic heading test Communication event test Completion. 31-37-00 Page 502 May 15/043200 MAINTENANCE MANUAL NOTE : Test will confirm interface between aircraft and FDR “——~ systems without the necessity of lengthy analysis of FDR tape contents. Table No. 502 ITEN DESIGNATION None Pitot/static test set , Wallace and Tiernan type, or equivalent us/gusers1y Adapter 11 0379032P421 Adapter 12 0379032P429 Blank R None Warning notice C. References Table No. 503 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General OO Page biock 401 D. Procedure (1) Flight data recorder - Removai/ Installation Make sure the following avionics bus-bar circuit breakers are closed: = 28V de main, RMI 1 115V ac main, COMP 2 26V ac main, RMI 1 26V ac main, HSI 2. (2) Open and tag the following avionics bus-bar circuit breakers: 31-37-00 Page 503 May 15/04(3) a) «sy (6) @ (8) ae JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. = 115V ac main, FDR - 28V dc essential switched, FDR FAIL Energize aircraft ac and dc bus-bars. (Ref. Chapter 24-00, Page black 701). Set AVIONICS MASTER switch ESSENTIAL to ON. Remove tag and close avionics bus-bar circuit breaker 28V de essential switched, FDR. Make sure, on right upper centre instrument panel, FDR FAIL caption is illuminated. Remove tag and close” avionics bus-t bar circuit breaker instrument panels FDR FAIL caption extinguishes. Test magnetic heading: (a) On left main instrument panel, set COMPASS BOTH T/NORM/BOTH 2 switch to NORM. (b) On right main instrument panel, set co-pilot”s COMP DG/MAG switch to DG. (c) Using co-pilot"s COMP DEC/INC switch, rotate heading dial on co-pilot"s Horizontal Situation Indicator (HSI) to the following headings in turn. Do not overshoot listed headings. Maintain each heading for 10 seconds: OOCN) 90° 180° 270°. (d) Make sure pilots Radio Magnetic Indicator (RMI) follows selected HSI headings Test communication event (a) Set and hold pilot"s I/C-OFF-R/T switch to R/T for 20 caconde. (b) Set and hold co-pilot"s I/C-OFF-R/T switch to R/T for 20 seconds. Test airspeed reading 31-37-00 Page 504 May 15/04(a) (b) e) (d) ed) ap (@) ch) @ 3200 MAINTENANCE MANUAL Open and tag the following circuit breakers, at right bulkhead STN 130: - Main dc bus-bar, PITOT HEAT RIGHT - Essential de bus-bar, PITOT HEAT RIGHT - Fesential de bus-har, OV SPFFD WRN Place a warning notice on circuit breaker panel, stating that circuit breakers must not be closed. Connect pitot/static test set to right upper (P2) pitot head, using adapter 12 . CAUTION - APPLY STATIC PRESSURE TO STATIC VENTS $2 ————__ AND $5, TO PREVENT DAMAGE TO FDR AND RIGHT ASI DUE TO REV SSURE. 0 WOT EXCEED INDICATED AIRSPEED OF 260 KNOTS, TO PREVENT DAMAGE TO OVERSIZED SWITCH. INCREASE/DECREASE TEST PRESSURES SLOWLY, TO PREVENT DAMAGE TO COMPONENTS. Slowly increase pitot pressure until test set indicates airspeed reading of 100 knots. Do not overshoot 100 knots. Maintain indication for 30 seconds. Increase pitot pressure until test set indicates airspeed reading of 260 knots. Do not overshoot 260 knots. Maintain indication for 30 seconds. CAUTION - RELEASE TEST PRESSURE SLOWLY. COMPONENTS WILL BE DAMAGED IF PRESSURE IS RELEASED WUICKLT. Slowly reduce pitot/static test set output to ambient air pressure. Disconnect adapter 12 and pitot/static test set from right upper (P2) pitot head. Remove tags and close the following circuit breakers. at right bulkhead STN 130: - Main dc bus-bar, PITOT HEAT RIGHT - Essential de bus-bar, PITOT HEAT RIGHT - Essential dc bus-bar, OV SPEED WRN. Remove warning notice from circuit breaker panel 31-37-00 Page 505 May 15/04JETSTREAM ‘Scxies 3200 MAINTENANCE MANUAL (10)Test altitude reading (a) Install blank R in static system $5 left static vent. (b) Connect pitot/static test set to $5 right static vent, using adapter 11 CAUTION - DO NOT ALLOW PRESSURE DIFFERENTIAL ———_ BETWEEN P2 AND S5 TO EXCEED 11.0 IN/HG CEQUIVALENT TO 450 KNOTS), TO PREVENT DAMAGE TO FDR ALTITUDE/AIRSPEED TRANSDUCER. DO NOT EXCEED A RATE OF CHANGE OF 4000 FT/MIN. COMPONENTS MAY BE DAMAGED IF PRESSURE IS INCREASED/ DECREASED TOO QUICKLY. (co) Using a reference pressure of 1013.25 mb (29.92 in/Hg), apply pressure to $5 static system to represent the following altitudes in turn. Do not overshoot listed altitudes. Maintain each pressure for 30 seconds. - 0 ft = 4000 Ft - 10,000 ft. CAUTION - RELEASE TEST PRESSURE SLOWLY. COMPONENTS ———_ WILL BE DAMAGED IF PRESSURE IS RELEASED QUICKLY. (d) Slowly reduce pitot/static test set output to ambient air pressure. (e) Disconnect adapter 11 and pitot/static test set from $5 right static vent. (¥) Remove blank R from $5 left static vent. (11)Test vertical acceleration. CAUTION - DO NOT JAR OR DROP THE ACCELEROMETER AS INTERNAL DAMAGE MAY OCCUR. (a) Remove four bolts and four washers securing vertical accelerometer to mounting bracket under floor at right side STN 213. 31-37-00 Page 506 May 15/043200 MAINTENANCE MANUAL NOTE : Do not electrically disconnect vertical accelerometer during removal procedure. (b) Rotate accelerometer 90° vertically from normal mounting pecition, Maintain this position for 30 seconds, using a flat surface for support. (c) Rotate accelerometer a further 90°, until it is 180° (upside down) from normal mounting position. Maintain this position for 30 seconds, using a flat surface for support. (d) Position accelerometer on mounting bracket and secure with four bolts and four washers. (12)0pen and tag the following avionics bus-bar circuit breakers: = 115V ac main, FOR - 28V dc essential switched, FDR FAIL. (13)De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, Page block 201 ). (14)Remove FDR (Ref. Chapter 31-37-00, Page block 501 ) and arrange analysis of its recorded test data by an approved agency. NOTE : The aircraft"s FDR system may be considered ——~" ‘suitable for service if laboratory analysis confirms that all recorded parameters conform to specification. (15)Make sure work area is clean and clear of tools and miscellaneous items of equipment. 31-37-00 Page 507 May 15/04Page left intentionally blank‘Senies 3200 MAINTENANCE MANUAL ** For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878% FLIGHT DATA RECORDER - FAIRCHILD NON-EXTENDED PARAMETER SYSTEM INSPECTION CHECK 1. Do a Detailed Inspection of the Vertical Accelerometer (1UB2) A. References Table No. 601 REFERENCE ITEM 25-00-00 Page Block 001 Equipment and Furnishing - General B. Access Table No. 602 REFERENCE ITtM R2 Floor panel C. Tools and Equipment None D. Consumable Materials None E. Expendable Parts F. Procedure (1) Remove equipment/furnishings necessary to gain access to floor panel R2 (Ref. Chapter 25-00-00, page block 001). 31-37-00 Page 60 May 15/04JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. (2) Remove the floor panel R2. (3) Do a detailed visual inspection of the vertical accelerometer. (a) Make sure the electrical connector is correctly attached to the vertical accelerometer. (b) Make sure the mounting structure of the vertical accelerometer has no signs of: - Corrosion = Cracks = Dents or damage cau eee UE eey g faste (c) Make sure the electrical connector and cable have no signs of: - Arcing or heat damage - Chafing > Corrosion oe - Fraying - Fretting - Loose wires or connections. (d) Make sure the vertical accelerometer has no signs of: Corrosion Cracks Dents or damage Loose or missing fasteners Scratches. (4) Make sure work area is clean and clear of tools and miscellaneous items of equipment. (5) Install the floor panel R2. (6) Install equipment/furnishings which were removed to get access to floor panel R2 (Ref. Chapter 25-00-00, page black 001) 31-37-00 Page 602 May 15/04‘Senies 3200 MAINTENANCE MANUAL ** For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878 CAB al ee i tee ee ee BE ee ek be 961-9694 FITGHT DATA RECORDER - DFSCRIPTION AND OPFRATION FATRCHTIN FXTFNDED PARAMETER SYSTEM DESCRIPTION AND OPERATION 1. GENERAL The extended parameter Flight Data Recorder (FDR) system converts, digitizes and formats data relating to aircraft flight parameters for storage. An Underwater Locator Beacon (ULB) is installed on the FDR +x For Aircraft 930-931 934 941-942 946-949 951-953 957-959 961-969 The FDR is an F1000 with internal solid - state recording. Storage data may be down - loaded after flight to a portable Analysis Unit (PAU). ** For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878 910 912-916 919% The FDR is an F800 with tape recording. The FDR must be removed from the aircraft tor data analysis. ee For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878 910 912-916 919 927-928 930-931 934 941-942 946-949 951-953 957-959 961-969e% 2. Description A. FDR system The FDR, 1UB3, is located in the rear equipment bay, on the left side, centre on STN 431. It is attached to a crash - proof structure, designed to withstand accelerations up_to 15g. It is connected pnematically to the P2 pitot and $ static systems. and electrically to the FDR system components and sensors. A ULB is securely attached to the FDR casting. The FDR CONTROL relay, 1UB9, GROUND POWER DISABLE relay, 1UB10 and BETA MODE CHANGE ~ OVER relay, 1UB42 are located in the nose bay relay box. This is located in the nose 31-38-00 Apr 13705MAINTENANCE MANUAL. equipment bay, on the centre spine, about STN 49. The FDR TEST switch, 1UB11, is Located on the right side shelf, at STN 9. The FDR FATI light, 11IR6, is located on the right upper centre instrument panel. 1 #* For Aircraft 930-931 934 941-942 946-949 951-953 957-959 ~789% 4 The preceding effectivity statement applies to the following figure(s). 31-38-00 Page 2 Apr 15/05‘Senies 3200 MAINTENANCE MANUAL Flight data recorder - component location Figure 1 31-38-00 May 13700JETSTREAM ‘Series 3200 MAINTENANCE MANUAL. «x For Fircraft 910 912-916 919%% The preceding effectivity statement applies to the following figure(s). 31-38-00 May 13704‘Senies 3200 MAINTENANCE MANUAL 31-38-00 Page 5 May 15/04JETSTREA. iM Senies 3200 MAINTENANCE MANUAL. #* For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878 Sime Spinae eee enema aian eek ee eee POOR iM ih enone 961-9694» Flight data parameters The following flight data parameters are recorded by the FOR: Table No. 1 Parameter Relative tine Vertical acceleration Longitudinal accereleration) Altitude Airspeed Nagnetic heading Pitch attitude) Roll attitude) Elevator position Flap position Left engine torque) Right engine torque) Left engine rpm) right engine rpn) Left engine thrust reverse Right engine thrust reverse Communication event Source Internally generated within FDR Dual - axial accelerometer 1UB2 $5 static system ( Ref. Chapter 34-11-00) P2 pitot and $5 static system (Ref. chapter 34-11-00) No.1 radio magnetic indicator (Ref Chapter 34-55-15) Vertical gyro (Ref. Chapter 34-20-41 Potentiometer 1UB18, on fin rear sub spar (Ref. Chapter 87-30-15 Potentiometer 1UB17, on flap position transmitter bracket (Ref. Chapter 27-50-17) Signal conditioning unit 1UB16 (Ref Chapter 77-10-23) Left Beta warning microswitch (Ref. garrett Maintenance Manual) Right Beta warning microswitch (Ref garrett Maintenance Manual) Pilot's/co-pilot's R/T switch (Ref. chapter 23-53-00) 31-38-00 Apr 137053200 MAINTENANCE MANUAL Power supplies Power to the FDR system is derived from the following avionics bus-bar circuit breakers: = 115V ae main hus-har FDR, 1IR1 28V de essential bus-bar FDR FAIL, 1UB8 28V de main bus-bar FDR, 1UB12 28V de main bus-bar FDR, 1UB13, Operation AL General The FDR contains a microprocessor system to convert, digitize and format flight data received from the airerafits flight data sensors. Twenty five hours of flight data can be recorded starting to over-write earlier data. Power Supplies The 115V ac main avionics bus-bar supplies the primary power to the FDR system. It is routed via avionics bus ~ bar circuit breaker FDR, 1UB1, and through the normally energized contacts of the FDR CONTROL relay, 1UB9. This relay is normally energized by a supply from the 28V dc main avionics bus-bar circuit breaker FDR, 1UB13. This supply is routed through the normally de-energized contacts of GROUND POWER DISABLE relay, 1UB10. In normal operation, the FDR automatically starts operating whenever the 115V ac and 28V dc main avionics bus-bars are energized. and ground power is not connected i.e. aircraft engines are running. The FDR automatically stops operating when the aircraft engines are stopped. If the AC CONTROL switch is set to TRANSFER, after an inverter failure, the FDR system will only Stop operating when the BATT MASTER switch is set to OFF (Ref.Chapter 24- 20-00, page block 501). When ground power is connected, GROUND POWER DISABLE relay CONTROL ‘relay! 1089, which desenergizes ond rempves the 115V ac primary power supply to the FDR. To enable testing of the FDR system with ground power, an FDR TEST switch, 1UB11, controls the operation of GROUND POWER DISABLE relay, 1UB10. When the switch is set to TEST, 31-38-00 May 13706tx Fo JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. the earth to the coil of the GROUND POWER DISABLE relay 1UB10 is removed. This relay de-energizes, and a supply energizes the coil of the FDR CONTROL relay, 1UB9. The relay energizes and the 115V ac primary power supply is therfore connected to the FDR Failure of the 115V ac supply to the FDR is indicated in two ways: = By illumination of the amber FDR FAIL Light, 1UB6, on the right upper centre instrument panel. The Light is independently supplied from the 28V dc essential avionics bus-bar, via circuit breaker FOR FAIL, 1UB8. Failure of the 115V ac power supply to the FDR causes a zero volt (ground) signal to be connected from the FDR to the FDR FAIL Light, caus to iLL The FDR FAIL Light incorporates a press-to-test facility, to test the light filament. - By illumination of an integral Built In Test Equipment (BITE) indicator, on the front of the FDR casing. Rircreft 910 912-916 919%« The preceding effectivity statement applies to the tollowing figure(s). 31-38-00 Page 8 May 15/04‘Senies 3200 MAINTENANCE MANUAL = Page 9 May 15/04 31-38-00 3 Extended parameter FOR system ~ schematic FigureJETSTREAM ‘Series 3200 MAINTENANCE MANUAL. I #* For Aircraft 930-931 934 941-942 946-949 951-953 957-959 The preceding effectivity statement applies to the following figures). 31-38-00 Page 10 Apr 15/05‘Senies 3200 MAINTENANCE MANUAL 31 “38- 00 Ma ay $5104JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. #* For Aircraft 841 844 846 848 851 853-855 857 859 861 864 869 878 Sime Spinae eee enema aian eek ee eee POOR iM ih enone 961-9694» c. Testing A BITE facility is incorporated within the FDR. Lt verifies data after storage (read after write), checks the status Condition of the FOR memory, and records BITE status in the memory. ABITE failure will also cause illumination of the FDR FAIL Light, 1UB6, and the integral BITE indicator. A PAU can be connected to the FDR, through a connector on the front of the FDR casing. D. Flight data sensing Table No. 2 Relative time Aprecision clock within the FOR generates a reference timing mark Additionally, since a data frame i recorded each second, the data frames become timing marks themselves. Vetical acceleration A dual-axial accelerometer is mounted Longitudinal acceleration on an internal bracket under the cabin floor, right side, at STN 217 It is supplied by the 28V de avionics main bus-bar, via circuit breaker FOR, 1UB13, Vertical accelerations of up to +6q -3a, and Longitudinal accelerations of #1g,are sensed. A 0 to 5V de output, proportional to eac! acceleration, is transmitted to the FDR via a two-wire electrical connector Altitude The $5 static system is connected to the FDR (Ref. Chapter 34-11-00). A the $5 air data into aircraft altitude. 31-38-00 Page 12 Apr 15/053200 MAINTENANCE MANUAL Relative time Airspeed Magnetic heading Pitch attitude Roll attitude Elevator position Flap position Aprecision clock within the FDR generates a reference timing mark Additionally, since a data frame is frames become timing marks themselves. The P2 pitot system is connected to the FDR (Ref. Chapter 34-11-00). The P2 and $5 air data are combined within the FDR transducer and converted to aircraft airspeed. No.1 RMI transmits aircraft magnetic heading to the FDR. as a three-wir synchro signal with a reference voltage (Ref. Chapter 34-55-15) The vertical gyro transmits aircraft pitch (+ 85°) and roll (360°) attitudes to the FDR, as a three-wire synchro signal (Ref. Chapter 34-20-41). A rotary potentiometer is mounted on a support bracket on the fin rear sub spar, between STN H41 and STN H50 (Ref. Chapter 27-30-15). A three-wir electrical connector transmits a +5V dc excitation voltage from the FDR to the Potentiometer. This returns a pick-off voltage proportional to elevator position, sensed via a Linkage to the elevator idle lever A rotary potentiometer is mounted on the existing flap position transmitter bracket, at STN 247.3, STR 177° Left (Ref. Chapter 27-50-17). A three-wire electrical connector transmits a +5V de excitation voltage from the FDR t the potentiometer. This returns @ pick-off voltage proportional to flap position, sensed vie mecianivat connection to the shaft of the ng flap position transmitter 31-38-00 May $$ roaJETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. Relative time Aprecision clock within the FDR generates a reference timing mark Additionally, since a data frame is recorded each secand, the data fra become timing marks themselves. Left (right) engine torque The Engine Signal Conditioning Uni (ESCU) is mounted on the right cabin bulkhead at STN 130 (Ref. Chapter 77-10-23). It is supplied by the 28V de avionics main bus-bar, via circui breaker FDR, 1UB12. It receives signal voltages fron the left and right engine torque signal conditioners. A Linear output of OV dc (0% torque) to +5 dc (120% torque) is transmitted from the ESCU to the FDR, via an electrical connecter. Left (right) engine rpm Engine ron input to the FDR is also derived from the ESCU (Ref. Chapter 77-10-23). Rpm data is received by the ESCU from each engine three phase tacho-generator. A Linear output of OV de (OX rpm) to +5V de (120% rpm) is transmitted from the ESCU to the FDR, via an electrical connector Left (right) engine reverse Indicatin to the FDR of reverse thrust thrust from each engine is via a electrical connector from eac existing engine Beta Mode microswitcn (Ref. Garrett Maintenance Manual) The 28V dc output from the let engine microswitch is inverted by the Beta Mode Change-over relay, 1Ub42, to provide a zero volt (ground) Signal to the FDR. The 28V de output from the right engine microswitch i applied directly to the FDR 31-38-00 May 95/043200 MAINTENANCE MANUAL Relative tine Aprecision clock within the FDR generates a reference timing mark Additionally, since a data frame is 2 d, the data frames ‘ing marks themselves. become tim Communication event The audio integrating system transmits @ cero volt (ground) signal to the FDR, via an electrical connector, whenever the pilot's and/ or co-pilot's R/T switch is pressed (Ref. Chapter 25-53-00). This input acts as a correlation event marker when the FDR memory 1s replayed with a recording from the aircraft cockpit voice recorder (Ref.Chapter 23-71-00). 31-38-00 May SoaPage left intentionally blank‘Senies 3200 MAINTENANCE MANUAL I #* For Aircraft 910 912-916 919 927-928 930-931 934 941-942 946-949 951-953 957-959 961-969e* FLIGHT DATA RECORDER - FAIRCHILD EXTENDED PARAMETER SYSTEM RFMOVAI /TNSTAII ATION 1. Remove Flight Data Recorder (FDR) (Ref. Figure 401) A. Special tools and equipment Table No. 401 ITEM DESIGNATION None Warning notice None Blanking caps None Drain container B. References Table No. 402 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General Cc. Procedure am eed De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). Open and tag avionics bus-bar circuit breaker 115V MAIN FDR. panel, stating that circuit breaker must not be closed. Remove access panel F26 . 31-38-00 Page 401 Apr 15/05JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. (5) Disconnect pitot P2 and static $5 connections from FDR. Install blanking caps on FDR front panel and on pitot and static connections. (6) On FDR support structure, remove and retain holt, washer and stiffnut securing top of support. Lower support strut to permit removal of FDR (7) On FDR mounting tray: (a) Remove and discard Lockwire from two butterfly nuts. (b) release two butterfly nuts from FDR (8) Carefully pull FOR to disengage rear electrical connector from mounting tray connector (GS) Remove FDR. 2. Install Flight Data Recorder (FDR) (Ref. Figure 401 A. Special tools and equipment Table No. 403 ITEM DESIGNATION NONE Warning notice References Table to. 404 REFERENCE DESCRIPTION 31-38-00 Page block 5: 1 Flight Data Recorder 34-11-00 Page block 501 Pitot/Static system 31-38-00 Page 402 May 15/04‘Senies 3200 MAINTENANCE MANUAL Figure Flight bata May 15/04a) (2) @) «ay aaa (6) om (8) ad: JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. Wake sure aircraft ac and de bus-bars are de-energized (Ref. Chapter 24-00-00, page block 201 ). Make sure avionics bus-bar circuit breaker 115V MAIN FDR is open and tagged Make sure warning notice is in position on avionics circuit breaker roof panel. Place FDR on mounting tray and carefully push back until FDR electrical connector mates with mounting tray connector. On FDR mounting tray: (a) Engage FDR hold-down hooks with two butterfly nuts. (b) Tighten two butterfly nuts until FDR electrical connector is fully mated with mounting tray connector. (c) Safety two butterfly nuts with lockwire On FDR support structure, raise support strut and secure with bolt, washer and stiffnut. Remove blanking caps and connect pitot P2 and static Sd connections to FDR. Remove tag and close avionics bus-bar circuit breaker 115V MAIN FDR. Remove warning notice from avionics circuit breaker roof panel. (10)Do a leak and sense test of _pitot P2 and static $5 systems (Ref. Chapter 34-11-00, page block 501 ) (11)Make sure work area is clean and clear of tools and (12.Inctall acces miscellaneous items of equipment. panel F246 (13)D0 an operational test of FDR system (Ref. Chapter 31-38-00, page block 501). (14)Make sure work area is clean and clear of tools and miscellaneous items of equipment. 31-38-00 Page 404 May 15/043200 MAINTENANCE MANUAL Remove Dual-Axial Accelerometer (Ref. Figure 402) A. Special tools and equipment Table Ne. 405 ITEM DESIGNATION None Warning notice B. References Table No. 406 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 53-20-10 Page block 201 Cabin floor panels C. Procedure a (2 3) mw “) 6) De-energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201 ). Open and tag avionics bus-bar circuit breaker 28V MAIN FDR, 1UB13. Place a warning notice on avionics circuit breaker roof panel, stating that circuit breaker must not be closed. Remove cabin floor panel R2 (Ref. Chapter 53-20-10, page block 201 ). Locate dual-axial accelerometer, identified as 1UB2, on mounting bracket under cabin floor, at right side STN 217 Disconnect electrical connector from dual-axial accelerometer. CAUTION - DO NOT JAR OR DROP THE ACCELEROMETER AS ————_ INTERNAL DAMAGE MAY OCCUR. 31-38-00 Page 405 May 15/04JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. (7) Remove four bolts and washers securing dual-axial Install accelerometer to mounting bracket. Remove accelerometer. Dual-avial Accelerometer (Ref. Figure 4? A. Special tools and equipment Table No. 407 ITEM DESIGNATION None Warning notice B. References Table No. 408 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power ~ General 31-38-00 Page block 501 Flight Data Recorder 53-20-10 Page block 201 Cabin floor panels Procedure (1) Make sure aircraft de bus-bars are de-eneraized (Ref. (2) «3 iv) Chapter 24-00-00, page block 201 ). Make sure avionics bus-bar circuit breaker 28V MAIN FDR, 1UB13 is open and tagged. Nake sure warning notice is in position on avionics circuit breaker roof panel CAUTION - DO NOT JAR OR DROP THE ACCELEROMETER AS ———_ INTERNAL DAMAGE MAY occUR. Position dual-axial accelerometer on mounting bracket under floor at right side STN 217. 31-38-00 Page 406 May 15/04‘Senies 3200 MAINTENANCE MANUAL age May 15/04(5) (6) a (8) wo JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. Connect electrical connector to dual-axial accelerometer. Remove tag and close avionics bus-bar circuit breaker PRV MAIN FDR, 111813 Remove warning notice from avionics bus-bar circuit breaker roof panel. Do a functional test of FDR vertical and longitudinal accelerations (Ref. Chapter 31-38-00, page block 501 ). Secure dual-axial accelerometer to mounting bracket with four bolts and washers. (10)Make sure work area is clean and clear of tools and miscellaneous items of equipment. (11) Install floor panel R2 (Ref. Chapter 53-20-10, page block 201 ). 31-38-00 Page 408 May 15/043200 MAINTENANCE MANUAL I #* For Aircraft 910 912-916 919 927-928 930-931 934 941-942 946-949 951-953 957-959 961-969e* FLIGHT DATA RECORDER - FAIRCHILD EXTENDED PARAMETER SYSTEM AD MISTHENT/TFST 1. General The FDR FAIL Light, situated on the centre instrument panel, indicates only incorrect operation of the recorders internal circuits or failure of system power supplies. A. Testing of Flight Data Recorder (FDR) system (1) Operational test An operational test, using the FDR/TEST switch in conjunction with the recorder BITE and the FDR FAIL light, provides a confidence check of: 28V de supplies to, and operation of, FDR system relays GROUND POWER DISABLE and FOR CONTROL 115V ac supply to the FDR FDR internal circuits FDR status output to FDR FAIL Light. tk For Aircraft 910 912-916 919%% To satisfy the requirement to assess correct operation of the FDR syslem, al the frequency specified in the maintenance schedule, analysis of the contents of the FDR memory is mandatory. Assessment may be done by one of the following methods, as appropriate. (a) Removal to authorized readout centre for download and print of Last Tlignt data Tor analysis. (b) Substitution with F1UU0 FDR to enable either of the following: 31-38-00 Page 501 nos Apr 15/05JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. - Flight generation of data for subsequent copy and confirmation - Functional testing, to generate data via sensor systems, monitored in real time with a Partable Analysis Unit (PAU). NOTE : To enable more efficient copying of data —— "generated during a flight, a memory marker can be put into the memory of F1000 FDR before flight. ** For Aircraft 927-928 930-951 934 941-942 946-949 951-953 957-959 961-9694 (3) Tests required by Maintenance Schedule F1000 FDR installed To satisfy the requirement to assess correct operation of the FDR system at the frequency specified in the Maintenance Schedule, test of fault light and analysis of the contents of the FDR memory is mandatory. Assessment is as follows: Test of FDR fault Light, using a Portable Analysis Unit (PAU) Monitor and analysis of data recorded during last flight, using a PAU to make sure all parameters have been recorded. Funciionai iesting, invoiving generation and monitoring of parameters in real time with a PAU, is optional. MMe betes Ae ete a se aaa es ee ne eee ee ed Ae J51-953_F57-959 961-IOI*E PAU monitoring is used to make sure of correct operation of sensor inputs. Data recorded in the FINND FDR colid-ctate memary can he copied to the PAU computer”s C drive (hard disk) or A drive (diskette) NOTE : Data recorded during flight can be compared with the —— "Calibration Flight Data document, provided with the aircraft on receipt from the manufacturer. 31-38-00 Page 502 sos Apr 15/083200 MAINTENANCE MANUAL Operational Test of FDR System A. References REFERENCE DESCRIPTION 24-00-00 Page block 201 B. Procedure Electrical power - General (1) Make sure the following avionics bus-bar circuit breakers are closed: - 115V MAIN FDR feet ee ee) ea be = 28 MAIN FDR (Qty 2). (2) Energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). (3) Do the test. STEP ACTION RESULT a) Set AVIONICS MASTER switch FDR FAIL Light illuminates. ESSENTIAL to ON. (2) Open nose bay access panel F2 FDR FAIL Light extinguishes » Set FDR/TEST switch to TEST (3) Open and then close each of FDR FATL light illuminates the following avionics bus-bar when any single circuit circuit breakers: breaker is opened, and (a) 115V MAIN. FDR extinguishes when same circuit (b) 28V MAIN FDR, 1UB13. breaker is closed. Close nose bay access panel F2 (5) Set AVIONICS MASTER switch FDR FAIL Light extinguishes. ESSENTIAL to OFF. 31-38-00 Page 503 Apr 15/08JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. (4) De-energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201). Functional Test of FDR System Only EDR system preparation, mandatory checks and completion procedures are mandatory. The following procedures allow individual parameters to be checked as necessary: Flap position test - Outside Air Temperature (OAT) test - Pitch and roll attitude test Vertical, lateral and longitudinal acceleration test Airspeed iesi Altitude test Magnetic heading test Communication event test Engine rpm, torque and reverse thrust test Engine reverse thrust test (without engines running). A. Special tools and equipment Table No. 502 ITEM DESIGNATION 17TES0010 Fairchild PAU , with following software installed: = 08/2 operating system > LORAL 63/2 application program = Configuration disk Part No. 0379095P. BA033012 Pitot/Static test set , Wallace and Tiernan type or equivalent 0379032P419 Adapter 1 0379032P21 Adapter 12 0379032P29 Blank R None Gyro tilt table None Gyro extension cable 31-38-00 Page 504 Apr 15/08‘Senies 3200 MAINTENANCE MANUAL ITeW DESIGNATION 037121P409 Rigging pin None Warning notices None Hydraulic ground power ri #* For Aircraft 910 912-916 919** $703-1000-00 Fairchild F1000 FOR ears Meera ee eee ee eee ees ee FhO-949 951-955 9D/-9D9 9O1-JOER B. References Table No. 503 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 27-30-15 Page block 201 Elevator position potentioneter 27-50-17 Page block 201 Flap position potentioneter 29-10-00 Page block 201 Nain hydraulic system 31-38-00 Page block 401 Flight Data Recorder 31-38-00 Page block 501 Flight Data Recorder 34-20-41 Page block 401 Vertical ayro 53-20-10 Page block 201 Cabin floor panel 71-00-00 Page block 501 Power plant - General 31-38-00 Page 505 Apr 15/08JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL. C. Procedure (1) Remove rear equipment bay access panel F26 . +e For Aircraft 919 917-916 919%% (2) Remove F800 FDR and install F1000 FDR (Ref. Chapter 31-38-00, page block 401 ). ah FOr Areras® 24e 9e ie oes Seren Seeks Uee Dh eee Sake 951-953 957-959 961-969ex (3) Connect PAU port RS232 to FDR front panel 25-pin connector, using PAU interface cable. (4) Make sure the following avionics bus-bar circuit breakers are closed: = 115V_MAIN FDR = 28V ESS SW FDR FAIL - 28V MAIN (Qty 2). (5) Energize aircraft ac and de bus-bars. (Ref. Chapter 24-00-00, page block 201 ). (6) Set AVIONICS MASTER switch ESSENTIAL to ON. Make sure FDR FAIL Light illuminates. (7) Open nose bay access panel F2 . (8) Set FDR/TEST switch to TEST. Make sure FDR FAIL Light extinguishes. NOTE : FDR/TEST switch must be at TEST position —— "throughout functional test. D. Do mandatory checks. NOTE : These mandatory checks consist of a test of the FDR ——" fail facility and copy/analysis of recorded flight test data. STEP ACTION RESULT (1) Set PAU power switch to ON. 31-38-00 Page 506 Apr 15/083200 MAINTENANCE MANUAL STEP ACTION RESULT (2) (3) Using PAU keyboard cursor and ENTER keys, follow display instructions and select the following: (a) SELECT AIRCRAFT CONFIGURATION (b) JETSTREAN 32 542A "A" NARKE (c) TEST FLIGHT RECORDER (d) TEST FAULT LIGHT (4) Using PAU, togale recorder On right upper centre fault Light ON and OFF. instrument panel, FDR FAIL Light illuminates when fault light is selected ON by PAU (5) Make sure recorder fault light FDR FAIL light on right upper is selected OFF using PAU. centre instrument panel is extinguished. (6) On PAU , follow display instructions to return to 6S/2 COMMAND MENU display. (7) Select COPY FLIGHT DATA. PAU requests source and destination of data to be copied. (8) Select FLIGHT RECORDER as source and INTERNAL DISK as destination, 31-38-00 Page 507 Apr 15/08TREAM Senies 3200 MAINTENANCE MANUAL. STEP ACTION RESULT (9) (10) any (12) a3) (14) (15) ions, do ther o ing, 3 propriate: 2 If memory marker was sel prior to last flight of FDR, select DATA RECORDED SINCE MEMORY MARKER WAS SET. (b) Tf memory marker was not set prior to last flight of FDR, select LAST X HOURS OF FLIGHI DAIA and follow screen prompts to request required amount of data. Enter the following filenane information as requested by PAU prompts: (a) Aircraft construction number: (b) Title FLIGHT TEST (c) Date of test Press ESC key. REPORT ANALYZE DATA and strech prompis & required reports of flight data. Select select copied Compare screen reports with Calibration Flight Data document. Confirm that all parameters have been correctly recorded by FDR. On PAU , press ESC key On PAU , select QUIT (a) PAU displays COPY COMPLETED and number of bytes copied (b) Filename is allocated to file created PAU display returns to COMMAND NENU. (a) If all paraneters have been correctly recorded, do completion procedure. (b) If any parameters have not been correctly recorded, do appropriate test in this page block. 31-38-00 Page 508 Apr 15/083200 MAINTENANCE MANUAL STEP ACTION RESULT (16) PAU , set power switch to (17) Depending on result, do either of the following as appropriate: (a) If all parameters have been correctly recorded, do completion procedure. (b) If any parameters have not been correctly recorded, do appropriate test in this page block. NOTE Due to compaction of flight data within FDR solid state memory, a request for last 30 minutes can result in copying of up to last 1 1/2 hours of actual flight time. E. Flap position test STEP ACTION RESULT (1) Connect hydraulic ground power rig to aircraft and pressurize hydraulic system (Ref. Chapter 29-10-00, page block 201 ). (2) Wake sure FLAPS selector is set to RETD, and flaps are retracted (3) Set PAU power switch on ON (4) Wait for PAU to boot up. 31-38-00 Page 509 Apr 15/08