JETSTREAM ‘Senits 3200 MAINTENANCE MANUAL CHAPTER 61 TABLE OF CONTENTS SUBJECT CH/SE/SU PAGE —-EFFECTIVITY BETA TUBE 61-00-01 ALL REMOVAL/INSTALLATION 401 Remove Beta Tube 401 Install Beta Tube 403 BETA TUBE 61-00-01 ALL ADJUSTMENT/TEST 501 Beta Tube Adjustment 501 PROPELLER ASSEMBLY 61-10-00 ALL DESCRIPTION AND OPERATION 1 General 1 SPINNER 61-10-05 ALL REMOVAL/INSTALLATION 401 Remove Spinner 401 PROPELLER 61-10-05 ALL ADJUSTMENT/TEST 501 Do a Functional Test of the 501 Negative Torque Sensing (NTS) System and the Automatic Engine Relight System SPINNER 61-10-05 ALL 61-CONTENTS Page 1 Apr 15/08JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL SUBJECT CH/SE/SU = PAGE = EFFECTIVITY INSPECTION CHECK 601 Inspect Spinner and Backplate, 601 External and Internal Inspect Slip Ring 603 PROPELLER 61-10-07 ALL SERVICING 301 Disengage Propeller Start Locks 301 Engage Propeller Start Locks 304 PROPELLER 61-10-07 ALL REMOVAL/ INSTALLATION 401 Remove Propeller 401 Install Propeller 403 PROPELLER 61-10-07 ALL ADJUSTMENT/TEST 501 Propeller Dynamic Balancing 501 PROPELLER 61-10-07 ALL INSPECTION CHECK 601 Inspect Left and Right Propeller 601 Assembly and Hub PROPELLERS, CONTROLLING 61-20-00 ALL DESCRIPTION AND OPERATION i General i Unfeathering pump 1 61-CONTENTS Page 2 Apr 15/08JETSTREAM ‘Senits 3200 MAINTENANCE MANUAL SUBJECT CH/SE/SU = PAGE «= EFFECTIVITY SYNCHROPHASER 61-20-02 ALL DESCRIPTION AND OPERATION 1 General 1 Description and Operation 1 SYNCHROPHASER 61-20-02 ALL NAINTENANCE PRACTICES 201 Remove Synchrophaser Control Unit 201 Install Synchrophaser Control Unit 201 Remove Monopole Speed Pickup 203 Install Monopole Speed Pickup 203 Synchrophaser System Functional 204 Test PROPELLER AND CONTROL 61-20-05 ALL NAINTENANCE PRACTICES 201 Remove Unfeathering Pump 201 Install Unfeathering Pump 202 Unfeathering Pump Function Test 203 61-CONTENTS Page 5 Apr 15/08Page left intentionally blankSenies 3200 MAINTENANCE MANUAL CHAPTER 61 LIST OF EFFECTIVE PAGES CHAPTER/SECTION/ SUBJECT PAGE DATE CONTENTS 1 Apr 15/08 CONTENTS 2 Apr 15/08 CONTENTS 3 Apr 15/08 61-00-01 401 Nov 15/01 402 Nov 15/01 403 Nov 15/01 404 Dec 15/99 405 Dec 15/99 61-00-01 501 Oct 30/98 502 Oct 30/98 505 oct 30/98 504 Oct 30/98 61-10-00 ‘] Feb 15/01 2 Oct 30/98 3 Feb 15/01 4 oct 30/98 5 Feb 15/01 6 Oct 30/98 61-10-05 401 Oct 30/98 402 Oct 30/98 403 Oct 30/98 404 oct 30/98 405 Oct 30/98 Page 1 Apr 15/08JETSTREAM ‘Sexies 3200 MAINTENANCE MANUAL CHAPTER/SECTION/ SUBJECT 61-10-05 61-10-05 61-10-07 61-10-07 61-10-07 PAGE 501 502 503 504 505 601 602 603 604 301 302 303 304 305 306 307 401 402 403 404 405 406 501 502 503 504 505 506 DATE Apr Apr Apr Apr Apr Nay May May May Apr Apr Apr Ap Apr Apr Apr Dec Dec Dec Dec Dec Dec Oct Oct Oct Oct Oct Oct 15/05 15/05 15/05 15/05 15/05 15/06 15/04 15/04 15/04 15/08 15/08 15/08 15/08 15/08 15/08 15/08 15/00 15/00 15/00 15/00 15/00 15/00 30/98 30/98 30/98 30/98 30/98 30/98 61-LEP Page 2 Apr 15/08JETSTREAM ‘Senits 3200 MAINTENANCE MANUAL. CHAPTER/SECTION/ SUBJECT PAGE DATE 507 Oct 30/98 508 oct 30/98 509 Oct 30/98 61-10-07 601 oct 30/98 602 oct 30/98 61-20-00 1 Oct 30/98 61-20-02 1 oct 30/98 2 oct 30/98 61-20-02 201 Apr 15/08 202 Dec 15/99 203 Dec 15/99 204 Apr 15/08 205 Dec 15/99 206 Dec 15/99 61-20-05 201 Dec 15/99 202 Dec 15/99 203 Dec 15/99 204 Dec 15/99 Page 3 Apr 15/08Page left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* BETA TUBE REMOVAL/INSTALLATION Remove Beta Tube WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT DC ————__ BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. A. Special tools and equipment Table No. 401 ITEM DESIGNATION None Warning notice 0379036P403 Angle tool assembly, propeller 0379038P extractor B. References Table No. 402 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 61-10-05 Page block 401 Spinner 61-10-07 Page block 301 Propeller - Servicing C. Procedure (1) De-energize aircraft de bus-bars (Ref, Chapter 24-00-00, page block 201 ). (2) Put a warning notice in the flight compartment, stating that propeller maintenance work is being done. 61-00-01 Page 401 Nov 15/01JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (3) Remove spinner (Ref. Chapter 61-10-05, page block 401 (4) Release start Locks and allow blades to feather (Ref. Chapter 61-10-07, page black 301. Use engine running o| engine static procedure as appropriate. ). (5) Remove split pin and cylinder plug from propeller hub. (6) Insert angle tool assembly through cylinder plug hole. (7) Locate tool sleeve on beta tube locking collar. (8) Press tool sleeve inwards, against Light spring pressure, to retract beta tube locking collar (9) Maintain pressure on beta tube locking collar and gently manoeuvre tool shaft to engage pin with slot in end of bela Lube. CO With beta tube Locking collar retracted, rotate tool shaft to unscrew beta tube from piston rod. (11)When beta tube is fully disengaged from piston rod threads, remove angle tool assembly . (12)Insert extractor through cylinder plug hole and screw into end of beta tube. (13)Gently withdraw beta tube. Remove extractor (14)Remove and discard O-ring seals from beta tube. 61-00-01 Page 402 Nov 15/01Sexies 3200 MAINTENANCE MANUAL 2. Install Beta Tube WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT DC ————__ BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. A. Special tools and equipment Table No. 403 ITeW DESIGNATION None Warning notice 0379036P403 Angle tool assembly, propeller 0379038P Extractor TL 5095 Spring compression tool B. References Table No. 404 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 61-00-01 Page block 501 Beta tube 61-10-05 Page block 401 Spinner 61-10-07 Page block 301 Propeller - Servicing 76-13-00 Page block 501 Engine/Airframe controls C. Procedure (1) Make sure aircraft dc bus-bars are de-energized (Ref Chapter 24-00-00, page biock 201 61-00-01 Page 403 Nov 15/01(2) «ay cay «nr 8) (9) JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL Make sure warning notice is displayed in flight compartment, stating that propeller maintenance work is being done. Nake sure start Locks are disengaged and propeller blades are in feathered position (Ref. Chapter 61-10-07, page block 301 ) Drain oil from cylinder prior to beta tube installation as follows: (a) Rotate propeller to position a cylinder drain plug at bottom of cylinder. Install O-ring seals on beta tube. Insert threaded end of beta tube through cylinder plug hole and gently manoeuvre beta tube through beta tube locking collar. Insert beta tube as far @s possible by hand. Insert angle tool assembly through cylinder plug hole and locate tool sleeve on beta tube locking collar. Press tool sleeve inwards, against spring pressure, to retract beta tube locking collar. (10)Maintain pressure on beta tube locking collar and gently manoeuvre tool shaft to engage pin with slot in end of beta tube. (11)Rotate tool shaft to screw beta tube fully home, using Uight hand pressure. (12)When beta tube bottoms, screw back 2.5 turns as an jnitial setting. (13)Using tool shaft to maintain beta tube setting, align flats on beta tube and beta tube locking collar by rotating tool sleeve. Correct alignment of flats will allow beta tube Locking collar to extend under Light spring pressure, when hand pressure on tool sleeve is released. Withdraw angle tool assembly . 61-00-01 Page 404 Dec 15/99Sexies 3200 MAINTENANCE MANUAL (14)To make sure beta tube locking collar is fully extended, attempt to re-engage shaft pin with slot in beta tuhe. Engagement should not be possible without using sleeve to retract beta tube Locking collar. (15)Install cylinder drain plug and washer. Torque tighten drain plug to 15 to 20 Lbf in. (1.7 to 2.3 Nm) and safety with lockwire to adjacent start lock cap nut. (16)Temporarily install cylinder plug in propeller hub and install split pin (17)D0 a propeller static blade angle setting check (Ref. Chapter 76-13-00, page block 501 ). Adjust beta tube setting as required (Ref. Chapter 61-00-01, page block 501). (18)If beta tube setting was adjusted to achieve required blade angle selling, install cylinder plug in propelle hub and install split pin (19) Install spinner (Ref. Chapter 61-10-05, page block 40 . (20)Remove warning notice . (21)Make sure work area is clean and clear ot tools and miscellaneous items of equipment. 61-00-01 Page 405 te cea aePage left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* BETA TUBE ADJUSTMENT/TEST 1, Beta Tube Adjustment NOTE : Procedures for left and right system are similar. This —— " procedure details the left system, references to th right system are shown in brackets. A. Special tools and equipment Table No. 501 ITEM DESIGNATION None Warning notices (@ty 2 0379036P403 Angle tool assembly, propeller B. References Table Wo. 502 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 61-10-05 Page block 401 74-00-00 Page block 501 76-13-00 Page block 501 Spinner Power plant Engine/airframe controls 61-00-01 Page 501 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT DC BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. Procedure ay (2) «a CAUTION - ALLOW ENGINE OIL TO ACHIEVE NORMAL OPERATING TEMPERATURE RANGE BEFORE ADJUSTING BETA TUBE. FAILURE TO DO SO WILL CAUSE SERIOUS INACCURACIES IN BLADE ANGLE SETTINGS. Start engine (Ref. Chapter 71-00-00, page block 501 ) Allow engine oil temperature to stabilize within normal operating range (69 to 110° C). Do a flight idle blade angle check (Ref. Chapter 76-13-00, page block 501 61-00-01 Page 502 Oct 50/98Sexies 3200 MAINTENANCE MANUAL (4) If flight idle blade angle is out of limits, adjust as follows: (a) De-energize aircraft dc bus-bars (Ref. Chapter 24-00-00, page block 201 ). (b) Open and tag 28V de ancillary bus-bar circuit breaker START/IGN - LEFT (RIGHT). (c) Position a warning notice in flight compartment stating that propeller maintenance work is being done. (d) Position a warning notice outside aircraft stating that personnel traffic on and off the aircraft is forbidden while propeller blade angle measurement is being done. (e) Remove spinner (Ref. Chapler 61-10-05, page block 401). (f) Remove split pin and cylinder plug from propelle hub. (g) Insert special tool through cylinder plug hole. Locate tool sleeve on beta tube locking collar. (h) Press tool sleeve inwards, against Light spring pressure, to retract beta tube locking collar. (i) Maintain pressure on beta tube locking collar and gently manoeuvre tool shaft to engage pin with slot in end of beta tube (j) With beta tube Locking collar retracted, rotate tool shaft to adjust beta tube, as require = Inwards to decrease flight idle blade setting - QOQutwards to increase flight idle blade setting NOTE : One full turn of beta tube equal ——— approximately two degrees of propeller pitch change. (k) Rotate tool sleeve to align splines and flats on beta tube locking collar with splines and flats on (L) Gently release tool sleeve and allow beta tube 61-00-01 Page 503 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL locking collar to extend, under Light spring pressure, and fully engage beta tube. (5) Make sure flight idle blade angle is within Limits (Ref. Chapter 76-13-00, page block 501). (6) Rotate propeller to position a cylinder drain plug at bottom of cylinder. (7) Remove lockwire , drain plug and washer, and allow oil to drain from cylinder. (8) Install cylinder drain plug and washer. Torque tighten drain plug to 15 to 20 lbf in. (1.7 to 2.3 Nm) and safety with Lockwire to adjacent start lock cap nut. (9) Install cylinder plug in propeller hub. Install split pin (10)Install spinner (Ref. Chapter 61-10-05, page block 401 te (11)Remove tag and close Z8V de ancillary bus-bar circuit breaker START/IGN - LEFT (RIGHT). (12)Remove warning notices . 61-00-01 Page 504 Oct 50/98Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER ASSEMBLY DESCRIPTION AND OPERATION General (Re Figure 1) (Ref. Figure 2 The propeller assembly is a four bladed, constant speed, variable pitch propeller. The propeller is a reversing and feathering type, the pitch changing mechanism being hydraulically operated towards fine and reverse pitch and mechanically assisted to coarse and feathering pitch, by coil springs and blade counterweights. The propeller assembl comprises the following sub assemblies. Spinner - Hub assembly - Blades and bearings = Cylinder - Slip ring assembly A. Spinner A cone shaped, light alloy spinner shell, encloses the blade roots and streamlines the propeller. The spinner has four blade apertures at the rear open end to locate over the blade roots. A shell support, riveted to the inside of the spinner shell, houses a rubber ring which locates on the propeller cylinder when the spinner is installed. The spinner is secured to the spinner backplate by twelve screus. B. Hub assembly This is a split assembly, consisting of tuo halves secured together by eight bolts. Eight threaded holes are provided in the hub rear wall to receive the mounting bolts, together with two plain holes for locating on the engine shaft flange dowels. Eight equally spaced threaded holes in the hub front face receive the cylinder attachment bolts. A sealing ring on the spigot diameter prevents Leakage at the hub/cylinder joint, and the bore of each half, houses a sealing ring. The hub assembly provides four blade ports to receive the blades. A seal in each blade port, prevents leakage of blade Learing grease between the blade root and hub arm. 61-10-00 Page 1 Feb 15/01iM ‘Senies 3200 MAINTENANCE MANUAL. 61-10-00 Page 2 Oct 30/98Sexies 3200 MAINTENANCE MANUAL Blades and bearings Each blade rotates about its axis on a bearing assembly during pitch change. Each is individually balanced by the insertion of lead wool in a central bore in the root and retained by a plug. Propeller de-icing boots are fitted to each blade and are connected by the de-icer harness to the slip ring assembly. A counterweight is fitted to each blade to assist in pitch changing to coarse and feather. The single-row blade bearing assembly ic of the split race type, incorporating a set of 21 matched balls. The large top thrust race locates in the hub, with the small bottom thrust race locating on the blade root. It is retained by a bearing sleeve, which is secured by a spring ring. An operating pin with a needle bearing assembly, is secured to the bottom face of the blade by a socket screw and is driven by the crosshead located in the hub cylinder The cylinder houses the coil springs and piston. Diametrically opposed on the cylinder are two spring loaded start Locks, which hold the piston and consequently the propeller blades, at or near 0° for engine starting. A plug titted in the bore at the front of the cylinder, provides access to the oil transfer (beta) tube. The beta tube screws into the crosshead and terminates in the beta sleeve on the engine. This tube carries the pressure/exhaust oil during all pitch change operations. Propeller static balance weights are fitted, as required, under the cylinder attachment bolt heads, to balance the propeller to within 0.29 ka cm (4 in oz.). Slip ring assembly The slip ring assembly is secured on the rear of the hub and transmits the electrical current from the brush gear to the Ce-icing boots of the blades. Operation (Ref. Figure 1) (Ref. Figure 3 The start locke hold the blades at the propeller ng for minimum starting torque. With the start locks released, the blades are hold in fine pitch by ofl pressure. 61-10-00 Page 3 Feb 15/01iM ‘Senies 3200 MAINTENANCE MANUAL. 61-10-00 Page & Oct 50/98Sexies 3200 MAINTENANCE MANUAL If the propeller is not held on the start locks, the Locks can be engaged using an electrically driven unfeathering pump (Ref. Chapter 61-20-00). To increase blade pitch the pressure oil is vented to the drain side of the system. The springs and blade counterweights then assist the blades towards coarse pitch With the oil pressure further reduced, the blades continue towards coarse pitch until the feather stop is reached. Reverse pitch is obtained by increasing the oil pressure to force the piston against, and overcome the reverse spring. A stop is supplied for the full reverse blade angle. On engine shut down, selection of reverse pitch, at propeller speeds less than 300 RPM, makes sure that the start locks are engaged ready for Subsequent restarting. 61-10-00 Page 5 Feb 15/01iM ‘Senies 3200 MAINTENANCE MANUAL. 61-10-00 Page 6 Oct 30/98Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* SPINNER REMOVAL/INSTALLATION 1, Remove Spinner (Ref. Figure 401) A. Special tools and equipment Table No. 401 1TEN DESIGNATION None Warning notice B. References Table No. 402 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT ————~__ DC_BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. C. Procedure (1) De-energize aircraft de bus-bars (Ref. Chapter 26-00-00, page block 201 ). (2) Make sure the following main bus-bar circuit breakers are open and tagged: = PROP ICE PROT LEFT (RIGHT) - PROP SYNC PR DUMP (3) Position warning notice in flight compartment stating that bus-bars must remain de-energized while propeller maintenance work is undertaken. 61-10-05 Page 401 ae Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (4) Remove twelve screws and fibre washers securing spinner to backplate. Remove spinner Install Spinner (Ref. Figure 401) A. Special tools and equipment Table No. 403 LEM DESIGNATION NIL-L-23699¢ Lubricating oil Ns 4 Grease B. References Table No. 404 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT ————~ __ DC_BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE Procedure (1) Make sure aircraft de bus-bars are de-energized (Ref. Chapter 24-00-00, page block 201 ). (2) Make sure the following main bus-bar circuit breakers are open and tagged: - PROP ICE PROT LEFT (RIGHT) - PROP SYNC PR DUMP (3) Make sure warning notice is displayed in flight compartment. (4) Lubricate rubber ring of spinner shell support with specified grease 61-10-05 Page 402 Oct 50/98(5) (6) cra cB) om Sexies 3200 MAINTENANCE MANUAL Position propeller blade de-icing cables, to make sure any slack in cables is directed away from spinner blade cut outs when installed. Position spinner and press Lightly to seat spinner shell support on propeller cylinder. Install twelve securing screws lubricated with specified oil , and fibre washers. Adjust spinner position (Ref. Figure 402) Tighten securing screws. (10)Remove warning notices from flight compartment. 61-10-05 Page 403 Oct 50/98‘Senies 32 MAINTENANCE MANUAL Spinner - Installation Figure 401 61-10-05 Page 404 Oct 50/98JETSTREAM Sexies 3200 MAINTENANCE MANUAL smn nan i) Sekt Spinner ~ Adjustment Figure 402 61-10-05 Page 405 Oct 50/98Page left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER ADJUSTMENT/TEST Do a Functional Test of the Negative Torque Sensing (NTS) System and the Automatic Engine Relight System A. References Table No. 501 REFERENCE ITEM 2 -00-00 Page Block 201 Electrical Power - General B. Access Table No. 502 REFERENCE LTeM +# For Aircraft 884 890 892-895 897-901 904-909 9114s FCS Right sidewall panel &5 Access panel £6 Access panel C. Tools and Equipment D. Consumable Materials None E. Expendable Parts None 61-10-05 Page 501 Apr 15/05JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL F. Procedure NOTE : Procedures for left and right hand systems ar similar. This procedure details the left hand system, references to the right hand system are shown in brackets. (1) Display the warning notice in the flight compartment: DO NOT OPERATE THE ENGINE CONTROLS. (2) Energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201). (3) Open and tag circuit breakers: = PROP CONT LEFT (PROP CONT RIGHT) - START/IGN LEFT = (START/IGN RIGHT) - UNFEATHER PUMPS LEFT - CUNFEATHER PUMPS RIGHT). (4) Remove the left (right) engine access panels E5 and £6. ircraft 884 890 892-895 897-901 904-909 911** (5) In the flight compartment, remove the access panel FCS. I 4# For Aircraft 790 805 810 814 818 821 823 828 849-850++ (6) In the flight compartment, al the RH Aft Bulkhead (STN130), remove the Lower panel. (7) Install the equipment. (a) Install_a shorting Link between terminals L1 and L4 on terminal block I2AY in the right hand bulkhead, and another Link between terminals R4 and R1 on terminal block T2aY. I 4* For Aircraft 884 890 89 O09 911+ 95 897-901 90 (8) Install the equipment. (a) Install a shorting Link between terminals T2AG-R3 and TPAF-17 61-10-05 Page 502 Apr 15/05Sexies 3200 MAINTENANCE MANUAL (b) Install a shorting link between terminals T2AG-R10 and T2AF-L9. #* For Aircraft ALL#* (9) At the left (right) engine, disconnect the input (LT) electrical connectors from the ignition unit. (10)Connect a test lamp to the electrical connector of the input (LT) lead of the ignition unit (11)Remove the pressure cap from the beta pressure test port. C12)Remove the pressure cap from the tee-fitting in the Line between the NTS orifice assembly and the propeller governor. (13)Install a hose and pressure gauge 200 psi (13.8 bar) between the tee-fitting and the beta pressure test port. (14) Close the circuit breakers: = START/IGN LEFT - (START/IGN RIGHT) - UNFEATHER PUMPS LEFT - CUNFEATHER PUMPS RIGHT). (15)In the flight compartment, set the left (right) POWE lever above the flight idle position (this closes the NTS lockout valve). (16)0perate the left (right) unfeather pump. Make sure the pressure gauge shows a pressure of approximately 150 psi (10.35 bar), (17)Facing aft, turn the left (right) propeller clockwise then rapidly accelerate the turn and release the propeller. (18)Nake sure the pressure gauge shows a rapid drop of approximately 75 psi (5.17 bar), then quickly returns to 150 psi (10.35 bar). (19)Stop the left (right) unfeather pump. 61-10-05 Page 503 Apr 15/05JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (20)Make sure the the test lamp is illuminated and the left (right) IGN caption illuminates for a minimum of 5 seconds and then goes off. (21) 0pen the circuit breakers: - START/IGN LEFT - CSTART/IGN RIGHT) - UNFEATHER PUMPS LEFT - CUNFEATHER PUMPS RIGHT) (22)Remove the test Lamp. #* For Aircraft 790 805 810 814 818 821 823 828 849-850+% (23)Remove the equipment. (a) Remove the shorting Link from between terminals Li and L4 on terminal block T2AY, and the Link between terminals R4 and R1. +e For Aircratt 884 890 892-895 897-901 904-909 91148 (24)Remove the equipment. (a) Remove the shorting Link from between terminals T2AG-R3 and T2AF-L7. (b) Remove the shorting Link from between terminals T2AG-R10 and T2AF-L9. #* For Aircraft ALL+* (25)Reconnect the left (right) ignition unit input (LT) lead. (26)Remove the hose and pressure gauge from between Lhe tee-fitting and the beta pressure test port. (27)At the Left (right) engine, install the pressure cap at the beta pressure test port. (28)Install the pressure cap at the tee-fitting in the Line between the NTS orifice assembly and the propeller governor. (2¥)Remove tags and close circuit breaker = PROP CONT LEFT 61-10-05 Page 504 Apr 15/05ke + Sexies 3200 MAINTENANCE MANUAL - (PROP CONT RIGHT) = START/IGN LEFT - (START/IGN RIGHT) - UNFEATHER PUMPS LEFT - CUNFEATHER PUMPS RIGHT). (30)De-energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201). (31) Install the access panels. (a) Make sure work area is clean and clear of tools and miscellaneous items of cquipment. For Aircraft 884 890 892-895 897-901 904-909 911%« (b) Install the access panel FCS. For Aircraft ALL#* +t (c) Install the left (right) engine access panels E5 and E6. For Aircraft 790 805 810 814 818 821 823 828 849-850x* (d) Install lower RH Aft Bulkhead panel (STN130). For Aircraft ALL#* (32)Remove Lhe warning notice from the flight compartment: DO NOT OPERATE THE ENGINE CONTROLS. 61-10-05 Page 505 Apr 15/05Page left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* SPINNER INSPECTION CHECK 1, Inspect Spinner and Backplate, External and Internal NOTE : Procedures for left and right system are similar. This —— " procedure details the left system, references to th right system are shown in brackets. A. References Table No. 601 REFERENCE ITEM 51-11-00 Page Block 601 61-10-05 Page Block 401 B. Access None €. Tools and Equipment Visual Inspections - General spinner Table No. 602 REFERENCE ITEM None Warning notice: DO NOT CONNECT AN ELECTRICAL POWER SUPPLY None Warning notice: DO NOT START THE D. Consumable Materials None ENGINE/S 61-10-05 Page 601 May 15/04JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL E. Expendable Parts None F. Procedure (1) Make sure aircraft de bus-bars are de-energized (2) Open and tag the following main bus-bar circuit breakers: = PROP ICE PROT LEFT (PROP ICE PROT RIGHT) - ROP SYNC PR DUMP. (3) Display warning notices. (a) Display warning notice in flight compartment: DO NOT CONNECT AN ELECTRICAL POWER SUPPLY. (b) Display warning notice in (Light compartment: Do NOT START THE ENGINE/S. (4) Remove spinner (Ref. Chapter 61-10-05). (5) Inspect spinner (Ref. Chapter 51-11-00). (a) Inspect internal and external surfaces of spinner. (6) Inspect backplate (Ref. Chapter 51-11-00). (a) Inspect all visible surfaces. (7) Install spinner (Ref. Chapter 61-10-05). (8) Close circuit breakers. (a) Remove tags and close the following main bus-bar circuit breakers: - PROP ICE PROT LEFT (PROP ICE PROT RIGHT) - PROP SYNC PR DUMP. (9) Remove warning notices. 61-10-05 Page 602 May 15/04Sexies 3200 MAINTENANCE MANUAL 2. Inspect St ng A. References Table No. 603 REFERENCE ITEM 51-11-00 Page Block 601 Visual Inspection - General 61-10-05 Page Block 201 Spinner B. Access None C. Tools and Equipment Table No. 604 REFERENCE ITEM None Warning notice: DO NOT CONNECT AN ELECTRICAL POWER SUPPLY None Warning notice: DO NOT START THE ENGINE/S D. Consumable Materials None E. Expendable Parts None F. Procedure (1) Make sure aircraft dc bus-bars are de-energized. (2) Open and tag the following main bus-bar circui breakers: - PROP ICE PROT LEFT (PROP ICE PROT RIGHT) 61-10-05 Page 603 May 15/04(3) cay (5) (6) «? (8) JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL - PROP SYNC PR DUMP. Display warning notices. (a) Display warning notice in flight compartment: DO NOT CONNECT AN ELECTRICAL POWER SUPPLY. (b) Display warning notice in flight compartment: DO NOT START THE ENGINE/S. Remove spinner (Ref. Chapter 61-10-05). Inspect slip ring (Ref. Chapter 51-11-00). (a) Inspect all visible surfaces. Install spinner (Ref. Chapter 61-10-05). Close circuil breakers. (a) Remove lags and close the following main busbar circuit breakers: = PROP ICE PROT LEFT (PROP ICE PROT RIGHT) - PROP SYNC PR DUMP. Remove warning notices. 61-10-05 Page 604 May 15/04Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER SERVICING 1, Disengage Propeller Start Locks A. Special tools and equipment Table No. 301 ITEM DESIGNATION TL 5095 Spring compression tool None Warning notice B. References Table No. 302 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 61-00-01 Page block 401 Beta tube Several methods of disengaging propeller start locks are detailed in the procedures which follow. The method selected will depend upon the condition of the aircraft and the maintenance procedures being done NOTE : Procedures tor lett and right system are similar. —— This procedure details the left system, references to the right system are shown in brackets. C. Procedure (1) Disengage propeller start locks (engine running). (a) Set RPM Lever to TAXI. 61-10-07 Page 301 Apr 15/08JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (2) Retard POWER Lever slowly towards REVERSE, until an increase in torque and temperature indication occurs. (a) Advance POWER Lever slowly through GROUND IDLE, making sure torque and temperature indication decreases, then increases as POWER lever is moved towards FLIGHT IDLE (3) Disengage propeller start locks using unfeat (engine static). ing pump WARNING - BEFORE WORKING ON PROPELLERS, OPEN AND TAG ————_ START/IGNITION CIRCUIT BREAKERS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT, STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. (a) Open and tag 28V de ancillary bus-bar circuit breaker START/IGN-LEFT (RIGHT). (b) Display @ warning notice in flight compartment stating that propeller maintenance work is being done. (c) Set POWER Lever to REVERSE and hold (d) Run unfeathering pump until pump noise pitch change is heard. (e) Insert wire rod, or similar through holes in start locks and hold start locks in withdrawn position. (f) Stop unfeathering pump and allow blades to move to feather position under spring pressure. (g) Remove start lock withdrawal tools. (Ch) Remove tag and close 28V de ancillary bus-ba circuit breaker START/IGN-LEFT (RIGHT). (i) Remove warning notice from circuit breaker panel (4) Disengage propeller start locks using spring compression tool (engine static) (Ref. Figure 301) 61-10-07 Page 302 Apr 15/08Sexies 3200 MAINTENANCE MANUAL WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT DC BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. (a) De-energize aircraft dc bus-bars (Ref. Chapter 24-00-00, page block 201 ). (b) Display a warning notice in flight compartment forbidding use of electrical power. (c) Remove beta tube (Ref. Chapter 61-00-01, page block 401 ). (d) Insert spring compression tool through cylinder plug hole. (e) Screw spring compression tool into crosshead. Rotate shaft handle clockwise until thread is fully located and rotation ceases. (f) Locate spring compression tool cap over end of propeller cylinder. (g) Rotate spring compression tool nut handle clockwise until it comes into contact with cap and resistance is felt. Continue to rotate nut handle clockwise to pull piston forward, against spring pressure, relieving load on start Locks (h) Insert wire rod, or similar through holes in start Locks and hold start locks in withdrawn position (4) Rotate spring compression tool nut handle i counter-clockwise direction, allowing piston to travel to bottom of cylinder. (j) Remove start lock withdrawal tools (k) Rotate spring compression tool shaft handle in counter-clockwise direction, until thread releases from crosshead. (L) Remove spring compression tool (m) Instaii peta tube Ckef. Chapter 61 block 401 ). 61-10-07 Page 303 Apr 15/08JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (n) Remove warning notice from flight compartment. 2. Engage Propeller Start Locks A. Special tools and equipment Table No. 303 ITEM DESIGNATION None Warning notice TL 5095 Spring compression tool B. References Table No. 304 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 61-00-01 Page block 401 Beta tube C. Procedure (1) Engage propeller start locks on normal shut down Cengine running). (a) During normal engine shut down make sure: = At 50% rpm, POWER lever retarded to REVERSE = At less than 10% rpm, POWER Lever advanced to GROUND IDLE (2) Engage propeller start Locks on manual shut down (engine running). (a) During manual engine shut down after propeller rotation ceases, make sure: - Feather lever’set to IN (b) Run unfeathering pump until propeller start locks 61-10-07 Page 304 Apr 15/08SETSTS 10 ‘Senies 720 MAINTENANCE MANUAL cnumoep iva ae verndows Start Locks - Spring Compression Tool Figure 301 61-10-07 Page 305 Apr 15/08«3 (4) JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL engage in piston and pump noise pitch change is heard. CAUTION - IF UNFEATHERING PUMP IS OPERATED FOR ————_ LONGER THAN 90 SECONDS, PULL PROPELLER THROUGH APPROXIMATELY 15 TURNS TO SCAVENGE OIL FROM GEARBOX AND RETURN IT TO TANK. DO NOT PERMIT ENGINE TO STAND WITH GEARBOX FULL OF OIL. (c) Set unteathering pump to OFF Engage propeller start locks using unfeathering pump (engine static) (Ref. Figure 301) NOTE : This procedure is identical to (Ref. Step Gomme 2 CeCe) ae Engage propeller start locks using spring compression tool, gine static) WARNING - BEFORE WORKING ON PROPELLERS, OPEN AND TAG ————__ START/IGNITION CIRCUIT BREAKERS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT, STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. (a) De-energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201 ). (b) Display @ warning notice in flight compartment forbidding use of electrical power. (c) Remove beta tube (Ref. Chapter 61-00-01, page block 401 >. (d) Insert spring compression tool through cylinder plug hole. (e) Locate securing thread of spring compression tool jn crosshead. Rotate chaft handle clockwise until thread is fully located and rotation ceases. compression tool cap over end of (f) Locate sprini (gq) Rotate spring compression tool nut handle clockwise 61-10-07 Page 306 Apr 15/08Sexies 3200 MAINTENANCE MANUAL until it comes into contact with cap and resistance is felt. Continue to rotate nut handle clockwise to pull piston forward, allowing oil in front of piston to drain away through drain hole. (h) Continue tightening spring compression tool nut handle until piston engages in start locks. (4) Rotate spring compression tool nut handle in counter-clockwise direction to relieve tension on tool. (J) Rotate spring compression tool shaft handle in counter-clockwise direction, until thread disengages from crosshead. (k) Remove spring compression toot . CU) Install cylinder drain plug and washer. Torque tighten drain plug to 15 to 20 Lbf in. (1.7 to 2.3 Wm) and safety with lockwire to adjacent start lock cap nut. (m) Install beta tube (Ref. Chapter 61-00-01, page block 401 ). (n) Remove warning notice trom tlight compartment. 61-10-07 Page 307 Apr 15/08Page left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER REMOVAL/INSTALLATION Remove Propeller (Ref. Figure 401) WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT DC ————__ BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. NOTE : Procedures for Left and right system are similar. This ——~ procedure details the left system, references to the right system are shown in brackets. NOTE : When removing a propeller that has been dynamically balanced, angular relationship between propeller hub mounting flange and engine shaft flange must be marked. Only work of a minor nature may take place for existing dynamic balance to be correct when propeller is re-installed. A. Special tools and equipment Table No. 401 ITEM DESIGNATION None Warning notice None Hoist or similar TL 5061 Torque spanner B. References Table No. 402 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 61-10-07 Page 401 Dec 15/00JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL REFERENCE DESCRIPTION 30-60-05 Page block 201 Nodular brush assembly 61-00-01 Page block 401 Beta tube 61-10-05 Page block 401 Spinner 61-10-07 Page block 301 Propelle! C. Procedure a) (2) (3) ca) «s) (6) «7 a) De-energize aircraft dc bus-bars (Ref. Chapter 24-00-00, page block 201 ). NOTE : To avoid unnecessary pressure on start locks, i —— is normal practice to remove propeller in feathered condition. Nake sure start locks are disengaged and propeller blades are feathered (Ref. Chapter 61-10-07, page block 301). Open and tag the following main bus-bar circuit breakers: = PROP ICE PROT LEFT (RIGHT) - PROP SYNC PR DUMP Position a warning notice on circuit breaker panel, stating that circuit breakers must not be closed because propeller maintenance work is being done. Remove spinner (Ret. Chapter 61-10-05, page block 501 ) Remove modular brush assembly (Ref. Chapter 30-60-05, page block 201 ) Remove beta tube (Ref. Chapter 61-00-01, page block 40 ) Remove lockwire from eight mounting bolts securing propeller to engine shaft flange 61-10-07 Page 402 Dec 15/00Sexies 3200 MAINTENANCE MANUAL (9) Using a suitable hoist , or similar, support propeller and, using specified torque spanner , remove eight mounting bolts. (10)Remove propeller and sealing ring from engine shaft flange. 2. Install Propeller (Ref. Figure 401 A. Special tools and equipment Table No. 403 ITEM DESIGNATION None Warning notice None Hoist, or similar TL 5061 Torque spanner None Torque wrench B. References Table No. 404 REFERENCE DESCRIPTION 24-00-00 Page block 201 Electrical power - General 30-60-05 Page block 201 Modular brush assembly 61-00-01 Page block 401 Beta tube 61-10-05 Page block 401 Spinner 61-10-07 Page block 301 Propeller 76-13-00 Page block 501 Engine/Airframe control: 61-10-07 Page 403 Dec 15/00‘Senies 32 MAINTENANCE MANUAL Propeller Assembly - Removal/Installation Figure 401 61-10-07 Page 404 Dec 15/00Sexies 3200 MAINTENANCE MANUAL WARNING - BEFORE WORKING ON PROPELLERS, DE-ENERGIZE AIRCRAFT ————~__ DC_BUS-BARS AND DISPLAY A WARNING NOTICE IN FLIGHT COMPARTMENT STATING THAT PROPELLER MAINTENANCE WORK IS BEING DONE. NOTE : Procedures for left and right system are similar. This procedure details the left system, references to the right system are shown in brackets. NOTE : When installing a propeller which was previously ——" dynamically balanced, attention must be paid to alignment marks on propeller huh mounting flange and engine shaft flange to maintain dynamic balance. only work of a minor nature may have been done for existing dynamic balance to be maintained when propeller is installed. C. Procedure (1) Make sure aircratt dc bus-bars are de-energized (Ret. Chapter 24-00-00, page block 201 ). (2) Make sure the following main bus-bar circuit breakers are open and tagged: - PROP ICE PROT LEFT (RIGHT) - PROP SYNC PR DUMP (3) Make sure warning notice is in position on circuit breaker panel (4) Install sealing ring on engine shaft flange (5) Smear engine shaft flange and mounting bolts, on thread and under head, with clean engine oil (6) Using a suitable hoist, or similar , position propeller and locate on locating dowels of engine shaft flange If installing propeller previously removed, make sure marks made during removal, are in alignment. (7) Install eight mounting bolts and, using specific torque spanner and a torque wrench , wet torque tighten to 63 to 67 bf ft (85 to 91 Nm). ety mounting bolts in with 61-10-07 Page 405 Dec 15/00JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL «9 Install beta tube (Ref. Chapter 61-00-01, page block (10)Install cylinder plug and lock with split pin. (11)Install modular brush assembly (Ref. Chapter 30-60-05, page block 201 ) (12)Install spinner (Ref. Chapter 61-10-05, page block 404 . (13)Remove warning notice from circuit breaker panel (14)Make sure the following main bus-bar circuit breakers are closed: = PROP ICE PROT LEFT (RIGHT) PROP SYNC PR DUMP (15)d0 a propeller ground run Lest (Ref. Chapler 76-13-00, page block 501). (16)dynamically balance propeller, if required (Ref. Chapter 61-10-07, page block 301 ). 61-10-07 Page 406 Dec 15/00Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER ADJUSTMENT/TEST 1. Propeller Dynamic Balancing A. Special tools and equipment Table No. 501 ITEM DESIGNATION None Balancer - Chadwick Helmuth 3382 Accelerometer bracket - Chadwick Helmuth 4a77A Accelerometer - Chadwick Helmuth 4184 Interrupter - Chadwick Helmuth 4673 Universal balance chart - Chadwick Helmuth None Magnetic pick-up bracket - Chadwick Helmuth 3030 Nagnetic pick-up - Electro None Weighing scales (to weigh accurately for # 0.5 grams) None Adhesive tape None Cable ties None Access platform 3 ft (1 m) None Warning notices (aty 2) 61-10-07 Page 501 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL B. References Table No. 502 REFERENCE DESCRIPTION 10-00-00 Page block 001 Parking and mooring 20-10-00 Page block 201 Standard practices - Torque tightening techniques 24-00-00 Page block 201 Electrical power ~ General 52-20-00 Page block 401 Emergency exi 71-00-00 Page block 501 Power plant - General WARNING - OBEY ALL APPLICABLE SAFETY PRECAUTIONS. NOTE : Procedures for left and right component are similar. This procedure details the left component, references to the right component are shown in brackets. C. Aircraft preparation procedure ag (2) (3) (4) (5) 6) Move aircraft to ground running area. Nake sure ground Locks are installed in Landing gear (Ref. Chapter 10-00-00, page block 001 ). Make sure the following warning notices are displayed jn flight compartment: - DO NOT OPERATE THE ENGINE CONTROLS - DO NOT START THE ENGINE(S). Nake sure access platform is in position at left (right) nacelle Open and tag circuit breaker ENG START L (ENG START R) Remove left (right) lower half cowling. install accelerometer bracket 5382 to bolt adjacent to filter blockage indicator on engine. Torque load (Ref. Chapter 20-10-00, page block 201 ). 61-10-07 Page 502 Oct 50/98Sexies 3200 MAINTENANCE MANUAL (8) Install accelerometer 4177A to accelerometer bracke 3382 with its connector pointing upwards. Torque Load (Ref. Chapter 20-10-00, page black 201 ). (9) Install interrupter 4184 to spinner. Interrupter mus be located under screw directly ahead of blade (in direction of rotation). Blade that immediately follows interrupter becomes target blade (Ref. Figure 501) (10)Install washer(s) to serve as a counterweight under spinner screw directly opposite interrupter Counterweight must weigh same as interrupter . (11) Install magnetic pick-up 3030 on cowling just to rear of spinner, so that interrupter will cross face o magnetic pick-up . Gap between interrupter and magnetic pick-up should be 0.005 in. (0.127 mm) maximum. C12)Install accelerometer and magnelic pick-up cables. Use cable ties to make sure cables are routed away from hot components in engine compartment. Tape cables along inboard leading edge and over wing to emergency exit (13)Remove Left (right) emergency exit (Ref. Chapter 52-20-00, page block 401 ) (14)Make sure cables lay flat over sill ot emergency exit, and do not obstruct aisle of aircraft through cabin to flight compartment. (15) Install left (right) emergency exit (Ref. Chapter 52-20-00, page block 401 ) (16)Install left (right) lower half cowLing. (17)Position balancer in flight compartment. (18)Connect balancer to flight compartment flood light, using 28V dc adapter cable in order to obtain 28V dc power. (19) Connect accelerometer and magnetic pick-up cables to balancer (Ref. Figure 502) (20)Remove access platform from left (right) nacelle 61-10-07 Page 503 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL NOTE : If both propellers are to be balanced, connect cables from LEFT (RIGHT) engine into Channel A (Channel B) (Ref. Figure 502) . Configuring balancer a nd (3) ca) (5) Set TRACK switch to Channel A for Left propeller (Channel B for right propeller). Set INTERRUPTER LOGIC switch to SINGLE. Set MAGNETIC PICK-UP switch to: = INDEPENDENT, if two propellers are being balanced - COMMON, if one propeller is being balanced. Set RPM RANGE switch to X10. Set RPM TUNE dial to propeller RPM (i.e. 159 for Jetstream 32). NOTE : Propeller(s) to be balanced should be —— serviceable, and statically balanced. Balancing propeller ay ay (3) (4) (5) (6) Position aircraft into wind Sketch location of interrupter , counterweight and target blade. Allocate blade number or names (Ref. Figure 501) to be used in connection with universal balance chart 4673 . Start left (right) engine (Ref. Chapter 71-00-00, page block 501). Run propetler(s) to be balanced at 100% RPM, with an engine torque setting of 60%. Propeller must have moved off start locks for all belance readings. Record vibration amplitude clock angle and Inches Per Second (IPS). Plot readings on appropriate clock face of universal balance chart . Label it Point 1. Shut down lett (right) engine (Ket. Chapter /1-UU: page block 501 ). 61-10-07 Page 504 Oct 50/98Sexies 3200 MAINTENANCE MANUAL (8) Place access platform in position at left (right) nacelle. (9) Add 20g to each side of one blade on spinner. Record amount, and to which blade weight was added. (10)Remove access platform from left (right) nacelle. NOTE : If using bolts, other than those normally used —— "on spinner, make sure change in weight is taken into account when attaching test weights. (11)Start Left (right) engine (Ref. Chapter 71-00-00, page block 501 ) (12)Run propeller(s) to be balanced at 100% RPM with an engine torque setting of 60% and record readings. Plot on universal balance chart . Label it Point 2 (13)Draw a Line between Points 1 and 2 with an arrow in the direction of Point 2. This becomes the move line. (14)Rotate graph under clock face so that arrow along edge of araph is parallel to line just drawn between the 2 points, and in same direction. For example, if weight was added to target blade, the target arrow on edge of graph must be parallel to move line and in same direction. (15)Scale length af move line and use it to estimate required weight changes necessary to bring propeller(s) into balance (i.e. to bring move lines into centre o universal balance chart ). (16)Shut down Left (right) engine (Ref. Chapter 71-00-00, page block 501 ). (17)Place access platform in position at left (right) nacelle. (18)Install test weights in positions calculated in step UO ecm mees care dae (19) Remove access platform from Left Cright) nacelle. C203Siari tefi Cright) engine (Ref block 501). + Chapter T4-00-00, page 61-10-07 Page 505 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (21)Run propeller(s) to be balanced at 100% RPM, with an engine torque setting of 60%. (22)Record vibration amplitude readings. (23)Plot readings on appropriate clock face of universal balance chart (24)Shut down Left (right) engine (Ref. Chapter 71-00-00, page block 501 ). (25)Repeat (Ref. Step 1.£.(11)) to (Ref. Step 1.£.(18)) , until propeller IPS reading is less than 0.1 and clock angle is indeterminate. Record total weight and position. (26)Put access platform in position at left (right) nacelle. (27)Remove test weights. (28)Install permanent weights to rim of propeller backplate. NOTE : Make sure weight of all screws used to install ——" permanent balance weights, is included in overall weight required to achieve propeller balance. Aircraft recovery (1) Disconnect accelerometer and magnetic pick-up cables from balancer . (2) Remove balance 28V dc adapter cable from flight compartment flood light. (3) Remove warning notices from flight compartment. (4) Remove balancer and adapter cable from flight compartment. (5) Remove Left (right) emergency exit (Ref. Chapter 52-20-00, page block 401). 6) Remove acceierometer and magnetic pick-up cabies from aircraft. 61-10-07 Page 506 Oct 50/98Sexies 3200 MAINTENANCE MANUAL (7) Install left (right) emergency exit (Ref. Chapter 52-20-00, page block 401 ). (8) Remove Left (right) Lower half cowling. (9) Disconnect accelerometer and magnetic pick-up cables from accelerometer and magnetic pick-up 10) ove cables complete with adhesive tape and cable jes from engine and wing. (11)Remove accelerometer 4177A from accelerometer bracket 3382 installed on left (right) engine. (12)Remove accelerometer bracket 3382 from bolt, adjacent to filter blockage indicator on left (right) engine. (13)Install bolt and torque Load (Ref. Chapter 20-10-00, page block 201 ). (14) Make sure work area is clean and clear of tools and miscellaneous items of equipment. (15) Install left (right) lower half cowling. (16)Remove interrupter 4184 from spinner. (17)Remove counterweight from spinner. (18)Remove magnetic pick-up 3030 from engine cowling. (19)Record any change in propeller Log book. 61-10-07 Page 507 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL y Allocation of Blade Names Figure 507 61-10-07 Page 508 Oct 50/98Sexies 3200 MAINTENANCE MANUAL fe | ro LT Chadwick - Helmuth Propeller Balancer Figure 502 61-10-07 Page 509 Oct 50/98Page left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER INSPECTION CHECK 1, Inspect Left and Right Propeller Assembly and Hub NOTE : Procedures for left and right system are similar. This —— " procedure details the left system, references to the right system are shown in brackets. A. References Table No. 601 REFERENCE ITEM 51-11-00 Page Block 601 Visual Inspections - General 61-10-05 Page Block 201 Spinner B. Access None €. Tools and Equipment Table No. 602 REFERENCE ITEM None Warning notice: DO NOT CONNECT AN ELECTRICAL POWER SUPPLY None Warning notice: DO NOT START THE ENGINE/S D. Consumable Materials None 61-10-07 Page 601 Oct 50/98JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL E. Expendable Parts None F. Procedure (1) Make sure aircraft de bus-bars are de-energized (2) Open and tag main bus-bar circuit breakers - PROP ICE PROT LEFT (PROP ICE PROT RIGHT) - PROP SYNC PR DUMP. (3) Display warning notices (a) Display warning notice in flight compartment: D0 NOT CONNECT AN ELECTRICAL POWER SUPPLY. (b) Display warning notice in flight compartment: DO NOT START THE ENGINE/S. (4) Remove spinner (Ref. Chapter 61-10-05) (5) Inspect propeller and hub (Ref. Chapter 51-11-00) (a) Inspect propeller assembly. (b) Inspect split hub tor signs ot cracking or distortion. (6) Install spinner (Ref. Chapter 61-10-05). (7) Close circuit breakers (a) Remove tags and close the following main bus-bar circuit breakers: - PROP ICE PROT LEFT (PROP ICE PROT RIGHT) = PROP SYNC PR DUMP. (8) Remove warning notices. 61-10-07 Page 602 Oct 50/98Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLERS, CONTROLLING DESCRIPTION AND OPERATION 1, General Information concerning propeller pitch control and the propeller governor is contained in Chapter 76-13-00. A synchrophaser system is provided for each engine. It automatically matches the two engine rotational speeds, and positions Lheir associaled propellers al the correct phase relationship. 2. Unfeathering pump This electrically driven pump pressurizes and directs engine oil to unfeather the propeller. 61-20-00 Page 1Page left intentionally blankSexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* SYNCHROPHASER DESCRIPTION AND OPERATION 1, General The synchrophaser system comprises a monopole speed pickup and propeller governor on each engine and a synchrophaser control unit in the left bulkhead panel (fuselage STN 130), automatically matches the rotational speeds of the two engines and positions the propellers at a pre-set phase relationship. 2. Description and Operation (Ref. Figure 1) Left and right monopole speed pickups, 1KB4 and 2KB4, are mounted in brackets attached to the propeller de-ice brush assemblies. They generate electrical pulses induced from a target located on the de-icing slip ring at the rear of the propeller. The targets on both the left and right engines are aligned with a propeller blade. Phase differences are fed into the synchrophaser control unit, 1KB3. Any differences in the phase relationship will cause the control unit to output a signal to electro-magnetic coils, mounted in the propeller governor of the affected engine. The varying voltage on the coil of the affected engine influences the operation of flyweights. These control the flow of oil to the propeller, to change the pitch and thus control the engine speed The system ic controlled by a PROP SYNCHRO ON/OFF cwitch (1KB2) and supplied from the 28V dc main bus-bar via circuit breaker PROP SYNC PR DUMP 1KB1. The PROP SYNCHRO ON/OFF switch is located in the roof panel. 61-20-02 Page 1iM ‘Senies 3200 MAINTENANCE MANUAL. Mecooon .o1@ [a] mma} coool Oac0000 Sojfoo Ose o te) UaUULEO y pega % A® TooKINa FORWARG Component Location Figure 1 61-20-02 Page 2Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* SYNCHROPHASER MAINTENANCE PRACTICES 1, Remove Synchrophaser Control Unit (Ref. Figure 201 A. Procedure (1) De-energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201 ) (2) Open and lag main bus-bar circuit breaker PROP SYNC PR DUMP. (3) Locate synchrophaser control unit on fuselage bulkhead STN 130 Left side. (4) Disconnect electrical connector from control unit. (5) Remove two bolts, washers and nuts securing control unit to bulkhead, support control unit and remove two remaining bolts, washers and nuts. (6) Remove control unit. 2. Install Synchrophaser Control Unit (Ref. Figure 201 A. Procedure (1) Make sure aircraft dc bus-bars are de-energized (Ref Chapter 24-00-00, page block 201 ) (2) Make sure main bus-bar circuit breaker PROP SYNC PR DUMP is open and tagged. (3) Secure control unit on fuselage bulkhead STN 130 with four bolts, washers and nuts. (4) Connect electrical connector to control unit. (5) Remove Lag and close main bus-ber circuil breaker PROP SYNC PR DUMP. (6) Do a functional test of synchrophaser system (Ref. Section 5.) « 61-20-02 Page 201 Apr 15/08‘Senies 32 MAINTENANCE MANUAL 61-20-02 Page 202 Dec 15/993. 4 ‘Senies 3200 MAINTENANCE MANUAL, Remove Monopole Speed Pickup (MSP) (Re gure 202) A. Procedure (1) De-energize aircraft de bus-bars (Ref. Chapter cs) install 24-00-00, page block 201 ). Open and tag main bus-bar circuit breaker PROP SYNC PR DUMP. Remove access panel E2 . Idenlify end cul MSP cables each side of in-line crimp splices and discard splices. Slacken Locknut and remove MSP from attachment bracket assembly. Monopole Speed Pickup (MSP) (Ref. Figure 202) A. Procedure a (2) (3) (4) nee o (7) Make sure aircraft dc bus-bars are de-energized (Ref. Chapter 24-00-00, page block 201 ). Make sure main bus-bar circuit breaker PROP SYNC PR DUMP is opened and tagged. Nake sure access panel E2 is removed. Screw replacement MSP into attachment bracket assembly. Adjust locknut to give a 0.030 in. (0.762 mm) clearance between MSP probe and target screw on propeller de-icing ring (Ref. Figure 202) CAUTION - DO NOT BEND ATTACHMENT BRACKET TO GAIN ———— CORRECT CLEARANCE Torque locknut to 25 (bf in. (2.875 Nm). Safety locknut with lockwire Make sure there is a minimum of 0.10 in. (2.54 mm) clearance between MSP,lockwire and locknuts, and spinner backplate. 61-20-02 Page 203 te cea ae5. (8) o>) JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL Cut MSP cables as required for re-splicing. Connect cables and re-splice. Remove tag and close main bus-bar circuit breaker PROP SYNC PR DUMP. (10)Make sure work area is clean and clear of tools and miscellaneous items of equipment. (11)d0 a functional test of synchrophaser system (Ref. Section 5.) ). (12)Install access panel E2 Synchrophaser System functional Test A. Procedure a (ay (3) «ay (5) (6) ng (8) Set PROP SYNCHRO switch to OFF. Start and stabilize engines at normal cruise rpm (Ret. Chapter 71-00-00, page block 501 ). Manually synchronize propellers by reducing rpm of faster propeller to minimize effect of lost motion in governor control linkage. If necessary, reduce power to a point where torque limiting is not operating. Set PROP SYNCHRO switch to ON and allow system to stabilize for a few seconds. Very slowly, reduce left propeller rpm unti synchronization is just lost. Note rpm difference Very slowly, reduce right propeller rpm until synchronization is regained and again lost. Note rpm difference (+1% MAXIMUM), Set PROP SYNCHRO switch to OFF. Set Left and right propeller rpm to within differential noted at (Ref. Step 5.A.(5)) or (Ref. Step 5.A.(6)) . Set PROP SYNCHRO switch to ON, make sure synchronization is established and need within a few seconds. Make sure slower propelter achieve synchronization. 61-20-02 Page 204 Apr 15/08JETSTREAM Sexies 3200 MAINTENANCE MANUAL Monopole Speed Pickup - Installation Figure 202 61-20-02 Page 205 te cea aeJETSTREAM ‘Senies 3200 MAINTENANCE MANUAL (10)Set PROP SYNCHRO switch to OFF. (11)Shut down engines (Ref. Chapter 71-00-00, page block 501). 61-20-02 Page 206 Dec 15/99Sexies 3200 MAINTENANCE MANUAL #* For Aircraft ALL+* PROPELLER AND CONTROL MAINTENANCE PRACTICES 1, Remove Unfeathering Pump (Ref. Figure 201) A. Procedure NOTE : Procedures for left and right system are similar. —— " This procedure details the left system, references to the right system are shown in brackets. (1) De-energize aircraft dc bus-bars (Ref. Chapter 24-00-00, page block 201 ) (2) Open and tag essential bus-bar circuit breaker UNFEATHER PUMP LEFT (RIGHT). (3) Remove access panels E6 , E7 , E9 and E10 . (4) Locate unfeathering pump on engine firewall STN 189.05. (5) Remove lockwire and disconnect electrical connector from unfeathering pump. (6) Disconnect drain, inlet pipe and outlet hose connectors. Install blanking caps to pipes, hose and pump drain connectors. (7) Remove and retain two nuts and washers securing pump to firewall bulkhead, (8) Remove and retain bolt, nut and washer securing bracket to engine mounting strut attachment. Install blanking caps on pump inlet and outlet unions. (9) Remove pump complete with securing bracket and inlet and outlet union. (10)Remove inlet and outlet unions complete with packers and bushing. Installblanking caps to pump inlet and outlet connections. (11)Remove Lockwire and remove four bolts and washers securing bracket to pump. Kemove bracket trom pump and retain bolts and washers. 61-20-05 Page 201 te cea ae2. A JETSTREAM ‘Senies 3200 MAINTENANCE MANUAL Install Unfeathering Pump (Ref. Figure 201) Procedure ay imal «2 ca) (5) (6) ic) a) « Make sure aircraft dc bus-bars are de-energized (Ref. Chapter 24-00-00, page block 201 ). Nake sure essential bus-bar circuit breaker UNFEATHER PUMP LEFT (RIGHT) is opened and tagged. Make sure access panels £6 , E7 , E9 and E10 are removed. Install bracket on pump, with four bolts and washers. Safety the bolts withlockwire Remove bianking caps from pump inlet and outiet connections. Install unions and packers on pump inlet and outlet connections. Remove blanking caps trom pump inlet and outlet unions. Install pump to firewall bulkhead using two nuts and Washers. Install bushing to outlet union. Secure pump bracket to engine mounting strut attachment with bolt, washer and nut. Remove blanking caps from pipe and hose connectors. Connect inlet pipe connector to pump inlet union and outlet hose connector to pump outlet union. Connect electrical connector to unfeathering pump and safety with Lockwire (10)Remove tag and close essential bus-bar circuit breaker UNFEATHER PUMP LEFT (RIGHT). (\1)Energize aircraft de bus-bars (Ref. Chapter 24-00-00, page block 201 ). (12)d0 a functional test of unfeathering pump (Ref. Section ce (13)Make sure work area is clean and clear of tools and miscellaneous items of equipment. (14)Install access panels £6 , E7 , E9 and E10. 61-20-05 Page 202 Dec 15/99Sexies 3200 MAINTENANCE MANUAL 3. Unfeathering Pump Function Test A. Procedure NOTE om (2) (3) ) cs) (6) m : Procedures for left and right system are similar. This procedure details the left system, references lo the right system are shown in brackets Energize aircraft de bus-bars (Ref. Chapter 24-00-00 page block 201 ) Set the left (right) POWER Lever to the REVERSE position. CAUTION - IF UNFEATHERING PUMP IS OPERATED FOR LONGER THAN 90 SECONDS, PULL PROPELLER THROUGH APPROXIMATELY 15 TURNS TO SCAVENGE OIL FROM GEARBOX AND RETURN IT TO TANK. DO NOT PERMIT ENGINE TO STAND WITH GEARBOX FULL OF OIL. On the centre console, hold the UNFEATHER switch to the L (CR) position. The propeller blades should move to the reverse pitch position. Release the UNFEATHER switch to the centre position. Set the left (right) POWER Lever to the GROUND START position. The propelier blades should move to the fine pitch position. Check the unfeathering pump and associated pipelines tor leaks. De-energize aircraft dc bus-bars (Ref. Chapter 24-00-00, page block 201 ) 61-20-05 Page 203 te cea ae‘Senies 32 MAINTENANCE MANUAL Unfeathering Pump Figure 201 61-20-05 Page 204 Dec 15/99