SD3-60 AIRCRAFT MAINTENANCE MANUAL (PT6A-67R ENGINES) - REMOVAL/INSTALLATION

Transcription

1 SD3-60 AIRCRAFT MAINTENANCE MANUAL z AMM POWER PLANT (PT6A-67R ENGINES) - REMOVAL/INSTALLATION 1. General Depending on aircraft operators requirements, replacement engines may be supplied to two build standards, (a) minimum and (b) 'dressed' i.e. quick engine change (QEC) standard. To conserve maintenance time, operators are recommended to obtain QEC unit/s from Bombardier Aerospace (Belfast) or alternatively to build and retain QEC units for standby installation as detailed in para. Refer to 3. CAUTION: ALL PIPE CONNECTIONS, ELECTRICAL PLUGS AND SOCKETS AND ACCESSORY DRIVE PADS MUST BE FITTED WITH BLANKS IMMEDIATELY ON REMOVAL; CONVERSELY, WHEN INSTALLING ENSURE THAT THE BLANKS ARE REMOVED. ENSURE THAT PIPES ARE CORRECTLY CLIPPED ON RE-INSTALLATION TO PREVENT FRETTING ON ADJACENT COMPONENTS. ALL PRE-FORMED PACKING 'O'-RINGS AND GASKETS FREED OR EXPOSED DURING REMOVAL OPERATIONS ARE TO BE DISCARDED AND NEWLY REPLACED ON RE-ASSEMBLY. (WHEN REPLACING LUBRICATE WITH FLUID TO BE USED IN APPROPRIATE SYSTEM OR LINE). UNLESS OTHERWISE STATED, ALL PIPE UNIONS AND ADAPTERS SHOULD BE TIGHTENED. REFER TO , PB1. Special Tools and Equipment:- Tail Steady Sling, engine lifting Stand, QEC build Setting Tool, LBA and reverse pitch indicating mechanism Torque spanners (set to required values) T T T T Removal A. Preparation for removal General actions: (1) Arrange for attendance of mobile hoisting gear or ensure aircraft is positioned beneath an overhead hoisting gantry. (2) Position tail steady under left or right horizontal stabilizer. Refer to , pb201. (3) Disconnect electrical power. Page 401 Apr 24/03

2 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (4) Disconnect restraint cable and carefully lower main intake cowl (420BB) to lowest possible position. Ensure cowl does not contact wing strut or foul on rear support structure adjacent to hinges (place suitable pad between strut and cowl). NOTE: To permit maximum lowering of cowl, disconnect electrics on rear bulkhead at:- (a) Engine terminal block ETB4 (b) Plug break EPB1 (5) Refer to , pb1. Remove the following engine cowls:- 430AT, 420AT, 410AT, 410AL and 410AR NOTE: Removal of panel 410AT will necessitate opening the oil filler access door contained within the panel assembly. This will provide access to detach starter/ generator cooling outlet vent from the panel. (6) Remove propeller as applicable. - Propeller Model HC-A6A-3. Refer to , pb Propeller Model HC-A6A-3A. Refer to , pb201. B. Left side of engine actions: Refer to Figure 401. NOTE: In the interests of clarity, it may occasionally be advantageous to refer to view relative to opposite engine (i.e. Where plumbing routeing obscures referred item/s on view under consideration). (1) Perform the following at the starter/generator:- (a) Disconnect flexible cooling inlet and outlet bellows from the unit. Retain freed outlet bellows and jubilee clips for refit. (b) Disconnect the bonding lead at the upper attachment point of the inlet duct. Retain the attaching parts for subsequent refit. (c) Remove the generator terminal block cover and clamp cable; disconnect cables and suitably insulate cable ends. Refit cover. (2) Disconnect compressor wash flexible pipe from adapter on aft face of rear inner fireshield. (3) Disconnect the four flexible hydraulic pipes idented MP, PI/INLET, CD/PCD and DRAIN where attached to hydraulic pump. (4) Disconnect the oil cooler supply and return to tank flexible pipes where respectively attached to engine. Page 402 Apr 24/03

3 SD3-60 AIRCRAFT MAINTENANCE MANUAL z (5) Locate the P2.5 bleed adapter (sited at 12 o'clock position immediately forward of compressor inlet screen, and:- (a) Detach flexible hoses attached thereto; retain attachment clips. NOTE: The right hand hose serves the aerofoil de-icing system and the left, the air conditioning system. (b) Break lockwire and remove the four bolts which secure the adapter. Retain adapter and discard gasket thus freed. NOTE: Fit blanking plate to exposed engine port employing the four adapter securing bolts. (6) Locate the P3 bleed adapter (sited at 9 o'clock position immediately forward of engine support ring) and:- (a) Disconnect air-conditioning flexible pipe which is clamp attached thereto; retain clamp. (b) Free electrical bonding lead from adapter and refit adapter securing bolt. (c) Remove and retain P-clip which secures flexible pipe to cleat on inner face of engine mounting ring. (d) Remove lagging and slacken clamp that secures aft end of flexible pipe (this will permit hose to be orientated through and over the engine mounting ring to facilitate engine removal access. (7) Disconnect fire sensor electrical connector WB11 from rear face of forward fireshield. (8) Locate the ignition exciter, idented KA7 (sited aft of rear fireshield and bracket attached to lower side of engine tubular support structure) and:- (a) Disconnect the two output connectors from installed rear face of unit. (b) Note positions and cut cable ties securing ignition leads to support structure. (9) Remove lower two portions of rear inner fireshield to provide subsequent optimum clearance with engine mounting ring when withdrawing engine. Page 403 Apr 24/03

4 z SD3-60 AIRCRAFT MAINTENANCE MANUAL C. Right side of engine actions: Refer to Figure 401. NOTE: 1. Unless otherwise stated, Refer to Figure 401 (viewing left or right installed engine as appropriate). 2. In the interests of clarity, it may occasionally be advantageous to refer to view relative to opposite engine (i.e. where plumbing routeing obscures referred item/s on view under consideration). (1) Disconnect oil breather flexible pipe where attached to connector on accessory gearcase. (2) Disconnect the following fuel flexible pipes:- (a) Fuel supply where attached to fuel heater. (b) Fuel purge line, where attached to upper connection on T-piece at top of fuel pump. (c) Fuel pump drain, where attached to adapter beneath pump. (3) Disconnect the starter/generator seal drain flexible pipe where attached to elbow in piping from unit mounting pad. (4) Disconnect oil pressure indication flexible pipe where attached to oil pressure adapter on engine. (5) Disconnect the undernoted flexible pipes from forward lower face of rear outer fireshield:- (a) Fuel blowdown system (b) Combustion drain system (c) Prop shaft oil seal drain (6) Remove the torque indication piping between the forward and rear fireshields. NOTE: (a) referred piping comprises the torquemeter oil pressure and reduction gearcase air pressure lines. (b) Apart from pipe disconnections it is necessary to remove and retain bulkhead seal assemblies and attachments. Page 404 Apr 24/03

5 SD3-60 AIRCRAFT MAINTENANCE MANUAL z (7) Refer to Figure 404. Disconnect engine controls as follows:- (a) Power controls Disconnect Bowdenflex input system from the power input lever and from power control support bracket. (b) Fuel condition controls: Disconnect Eanco cable from the idle reset/cut-off lever at the top of the fuel control unit and from the fuel control support bracket. (c) Prop RPM controls: Detach Eanco cable at quick disconnect on the aft face of the rear fireshield. (8) Refer to Figure 402. Make the following electrical disconnection:- (a) Sockets at FW5, FW6 and FW7 on the forward face of the rear outer fireshield. Note positions and free clipping attaching harness to engine mount frame and support ring. (b) Connection to reserve power solenoid valve, idented QJ2. (c) Connection to fuel flow transmitter, idented QC5. (d) Connection to Ng tacho-generator, idented EG2. (e) Connection to oil temperature bulb, idented EA3. (9) Disconnect fire detection terminal from forward face of wing front spar fireshield. Also free fire sensor clip from engine mounting frame immediately forward of the terminal. D. Remove engine from airframe IMPORTANT: BEFORE REMOVAL OF ENGINE, INSPECT ALL FOUR FLEXIBLE MOUNTS (AS APPROPRIATE TO MOUNT TYPE), PAYING PARTICULAR ATTENTION TO DRIFT INDICATION. Refer to , pb201. Refer to , pb201. CAUTION: CHECK THAT MOUNTS NOW FORM THE ONLY CONNECTION BETWEEN THE ENGINE AND THE AIRFRAME. (1) Position hoisting gear. (2) Attach engine lifting sling to hook of hoisting gear. (3) Refer to Figure 403. Sling and remove engine as follows:- (a) Connect engine sling ropes A & B to engine lifting eyes and take up the slack. Page 405 Apr 24/03

6 z SD3-60 AIRCRAFT MAINTENANCE MANUAL Engine/Airframe Interface Figure 401 Page 406 Apr 24/03

7 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Engine/Airframe Electrical Interface Figure 402 Page 407 Apr 24/03

8 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (b) Remove the attachment bolt which secures each of the upper and lower, left and right mount assemblies to the engine mounting ring. (c) Move power plant forward to allow attachment of sling ropes C & D. (d) Connect sling ropes C & D to upper left and right engine mounts using attachments previously removed (operation (b)). (e) Disconnect sling rope B. (f) Carefully withdraw engine from mounting ring; reconnect rope B and lower clear. NOTE: If a QEC unit is not available for immediate installation, strip removed engine of accessories (para. C) and employ to build replacement engine to QEC standard (para. 3). CAUTION: IF ENGINE HAS BEEN REMOVED BECAUSE OF OIL SYSTEM METAL CONTAMINATION, THE OIL COOLER MUST ALSO BE REPLACED. ADDITIONALLY, ALL OIL PIPES INTENDED FOR RE-INSTALLATION MUST BE FLUSHED WITH KEROSENE (BRITISH SPEC. DEF2403A OR AMERICAN SPEC VV-K-211D) AND THOROUGHLY DRIED WITH COMPRESSED AIR BEFORE RE-ASSEMBLY. E. Remove power plant accessories Refer to Figure 404. Refer to Figure 405. (1) Refer to , pb201. Refer to , pb201. Remove bottom left and right engine mounts (as appropriate to type) and install engine in maintenance stand. (2) Remove top left and right engine mounts. (3) Remove fire sensor and associated clips and attachments. Refer to Figure 409. (4) Remove exhaust stubs. Refer to Figure 404. (5) Remove power control support bracket. (6) Remove fuel control support bracket. (7) Remove prop RPM control support bracket. (8) Remove power input lever. (9) Remove hydraulic pump. NOTE: Leave unions and seals in pump. Page 408 Apr 24/03

9 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Power Plant Slinging Figure 403 Page 409 Apr 24/03

10 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (10) Remove Ng tacho generator. (11) From oil pressure port on accessory gearcase, remove special adapter Pt. No. SD with sealing ring. (12) Remove fuel flow transmitter. NOTE: Fit Pratt & Whitney coupling tube, Pt. No in lieu. (13) Remove fuel heater inlet adapter and sealing ring. (14) Remove starter generator seal drain pipe SD as an assembly (i.e. including elbow). (15) Refer to Figure 405. Remove starter generator as follows:- CAUTION: ENSURE THAT THE WEIGHT OF THE UNIT IS NOT TAKEN BY THE SHAFT. (a) Support the unit and remove the mounting clamp. (b) Carefully withdraw unit rearwards to disengage shaft plines and remove. (c) Remove mounting flange and cooling exhaust box from accessory gearbox (secured by four self-locking nuts). (16) Make the following electrical disconnections:- (a) Refer to Figure Connections to proximity switches on LBA back up stop and reverse pitch indicating mechanism. 2 ITT wiring, detach from T 5 terminal block, idented ED4. 3 Connection to Np tacho generator, idented EF2. 4 Connection to propeller de-icing brush block, idented 2HA8. (b) Refer to Figure Connection to governor coil, idented KF4. 2 Connection to lock pitch solenoid, idented KD10. 3 Connection to autofeather valve, idented KC7. 4 Connection to overspeed governor reset valve, idented KB4. 5 Connection to propeller de-icing brush block, idented 1HA8. Page 410 Apr 24/03

11 SD3-60 AIRCRAFT MAINTENANCE MANUAL z 6 Connection to prop sync magnetic pick-up, idented KF3. 7 Detach lightning suppressors 1HA9 and 2HA9 from bracket on underside of engine at the reduction gearcase/exhaust section joint. Leave suppressors attached to harness. (17) Remove Np tacho generator. (18) Refer to Figure 405. Remove torque pressure reference piping as follows:- (a) Locate pipes SD and SD (b) Detach pipe clipping where attached to oil transfer tubes (note positions and arrangement for subsequent re-assembly). (c) Remove both pipes. (d) Remove special adapters and sealing rings from torquemeter oil pressure and static pressure ports. Discard sealing rings. (19) Remove upper portion of forward fireshield as follows:- (a) Detach peripheral seals upper retaining angle. (b) Detach upper to lower fireshield jointing angles. (c) Remove attachment bolts from engine bulkhead. (d) Retain attachments with fireshield. (20) Remove lower portion of forward fireshield as follows:- (a) Remove drain pipe sealing plates and seals from bottom aft face. (b) Remove attachments securing raceways (cable supports) to underside of engine. (c) Remove attachment bolts from engine bulkhead and remove lower forward fireshield complete with electrical harness. (d) Retain attachments with fireshield. (21) Remove the two upper portions of the rear inner fireshield (retain attachments with the fireshield). NOTE: The two lower portions of the fireshield were removed to facilitate engine detachment from airframe. Page 411 Apr 24/03

12 z SD3-60 AIRCRAFT MAINTENANCE MANUAL Quick Engine Change Unit (QEC) Figure 404 Page 412 Apr 24/03

13 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Quick Engine Change Unit (QEC) Figure 405 Page 413 Apr 24/03

14 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (22) Note position of clipping for subsequent re-installation on replacement powerplant. Refer to Figure 405. Free the assembled drain pipes (four rigid and three flexible) where attached to:- (a) Combustion drain valves. (b) Flow divider dump valve. (c) Propeller shaft oil seal seepage drain elbow (also remove elbow). (23) Refer to Figure 405. Remove overspeed governor. (24) Refer to Figure 404. Refer to Figure 405. Remove propeller de-icing brush block assemblies. (25) Refer to Figure 404. Remove LBA backup stop and reverse pitch indicating mechanism. (26) Refer to Figure 405. Remove carbon slipper block from propeller reversing lever. 3. Quick-engine change QEC build procedure Refer to Figure 404. Refer to Figure 405. A. General Notes (1) A QEC unit is equipped from spares holdings or a combination of spares and functional accessories taken from an unserviceable engine (para 2.E.). (2) The procedure is provided to:- (a) enable operators to build standby QEC units. (b) prepare an engine required for immediate installation to a convenient pre-installation state. (3) Torque tighten all bolts attaching support brackets, fireshields etc. to engine flanges to lb in. Where self-locking nuts are employed, note the torque necessary to turn the nut on the bolt before seating the nut and add this value to that quoted, using the newly established value as the installation figure. B. Procedure (1) Mount engine in QEC build stand T (2) Refer to Figure 404. Fit carbon slipper block Pt. No. A3044 to the propeller reversing lever which overhangs the propeller mounting flange. Page 414 Apr 24/03

15 SD3-60 AIRCRAFT MAINTENANCE MANUAL z (3) Refer to Figure 404. Fit LBA back-up stop and reverse pitch indicating mechanism to the thrust cover on the reduction gearbox. Torque tighten attachment nuts to in.lbs. NOTE: If engine is intended for immediate installation, rigging is performed postinstallation on airframe. (4) Refer to Figure 404. Refer to Figure 405. Fit propeller de-icing brush block assemblies. (5) Refer to Figure 405. Fit overspeed governor, using replacement gasket Woodward Pt. No or Pratt & Whitney Pt. No Torque tighten attachment nuts lb. in. NOTE: Coat gasket with Dow Corning 7 Compound release agent or equivalent. (6) Refer to Figure 404. Fit Np tacho-generator together with gasket MS (7) Refer to Figure 405. fit forward portion of engine drains system as follows:- (a) Fit elbow Pt. No. AN833-4K, sealing ring Pt. No. AS and locknut AN924-4K to propeller shaft oil seal drain port. NOTE: Observe installed engine for angular setting of elbow. (b) Connect pipe, Pt. No. SD to elbow and clip to adjacent pressure oil tranfer tube using clips Pt. No. HT0813/4C (2 off) and HT0813/10C (2 off). NOTE: Leave flexible pipe, Pt. No. SD hanging free. (c) Connect combustion drain valve piping assembly, comprising two rigid pipes, a teepiece and a flexible pipe as follows:- 1 Connect pipe Pt. No. SD to forward valve. 2 Connect pipe Pt. No. SD to rear valve. NOTE: Leave flexible pipe, Pt. No. SD hanging free. (d) Connect fuel manifold purge system piping (comprising one rigid pipe and one flexible pipe) to the flow divider dump valve as follows:- 1 Connect pipe, Pt. No. SD to valve and clip to adjacent fuel inlet line using clips HT0813/4C (2 off). NOTE: Leave flexible pipe, Pt. No. SD hanging free. (8) Fit the two upper portions of the rear inner fireshield. NOTE: Two lower portions of fireshield are fitted post-engine installation. (9) Fit lower portion of forward fireshield (complete with electrical harness) as follows:- Page 415 Apr 24/03

16 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (a) Ease free portion of peripheral seal over front of engine and manoeuvre fireshield into position on aft face of engine centre fireseal bulkhead. (b) Bolt fireshield to bulkhead. (c) Fit the two drain pipe sealing plates, Pt. No. SD and SD together with respective associated seals SD and SD to the bottom rear face of the fireshield. (d) Attach the electrical harness raceways (cable supports) to associated brackets on underside of engine). (10) Fit upper portion of forward fireshield as follows:- (a) Place in position on aft face of engine centre fireseal bulkhead. (b) Bolt to bulkhead. (c) Fit peripheral seal upper retaining angle, Pt. No. SD (11) Bolt upper to lower forward fireshield jointing angles together. (12) Arrange forward portion of electrical harness and connect to the following equipment:- NOTE: Where necessary, employ Dymotape to identify appropriate equipment with the idents quoted. (a) Refer to Figure Proximity switches on LBA back-up stop and reverse pitch mechanism. 2 ITT wiring, attach to T 5 terminal block, idented ED4. 3 Np tacho-generator, idented EF2. 4 Connection to propeller de-icing brush block, idented 2HA8. (b) Refer to Figure Connection to governor coil, idented KF4. 2 Lock pitch solenoid, idented KD10. 3 Autofeather valve, idented KC7. 4 Overspeed governor reset valve, idented KB4. 5 Prop de-icing brush block, idented 1HA8. 6 Prop synch magnetic pick-up, idented KF3. Page 416 Apr 24/03

17 SD3-60 AIRCRAFT MAINTENANCE MANUAL z 7 Install lightning suppressors 1HA9 and 2HA9 on bracket beneath engine at the reduction gearcase/exhaust section joint. (c) Fit harness clipping. (13) Refer to Figure 405. install torque pressure reference piping as follows:- (a) Fit adapter, Pt. No. SD and sealing ring AS to torquemeter static pressure port; secure with two attachment bolts and washers. (b) Fit adapter, Pt. No, SD and sealing ring AS to torquemeter oil pressure port. Torque tighten to 400 ± 25 lb. in. (c) Fit pipes SD and SD to respective torquemeter oil pressure and static pressure adapters, orientating as shown. (d) At the positions noted during accessory removal process, fit pipe clipping to appropriate oil transfer tubes. (14) Refer to Figure 405. Fit starter generator as follows:- (a) Remove blanking plate from mount pad on accessory gearcase. (b) Position cooling exhaust box, Pt. No. SD on the four studs projecting from the mount pad (exhaust box outlet to top). (c) Install unit mounting flange on studs and secure with four self-locking nuts, Pt. No. AS8600-G. Torque tighten nuts to 150 lb. in. (d) Refer to , pb1. Lubricate splined shaft with clean engine oil to spec. referred. Install new O-ring Pt. No. MS CAUTION: MAINTAIN SUPPORT OF UNIT DURING (E) WHICH FOLLOWS I.E. DO NOT PERMIT WEIGHT OF UNIT TO BE TAKEN BY SHAFT. (e) Align the starter generator splined shaft with the drive on the engine and slide into place with the cooling inlet duct at rear orientated horizontally to left. (f) Fit attachment clamp; torque tighten clamp bolt to 70 lb. in. (15) Refer to Figure 404. Fit starter generator seal drain pipe assembly, Pt. No. SD NOTE: Orientate elbow to right as shown. (16) Fit fuel heater inlet adapter Pt. No. AN815-4C and sealing ring Pt. No. AS to fuel heater inlet port. Refer to Figure 404. (17) Refer to Figure 404. Fit flow transmitter in lieu of coupling tube Pt. No. MS (supplied with engine). Page 417 Apr 24/03

18 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (18) Refer to Figure 404. Locate oil pressure port and fit the following:- (a) Sealing ring AS (b) Special adapter, Pt. No. SD NOTE: Torque tighten adapter to 400 ± 25 lb.in. (19) Refer to Figure 404. Fit Ng tacho generator together with gasket MS (20) Refer to Figure 404. Fit hydraulic pump as follows:- NOTE: Pump ports should be equipped with relevant unions and seals in readiness for subsequent connection to airframe piping. (a) Replace bolts supplied with engine with studs, Pt. No. SD (4-off). Insert long-threaded end in engine and torque tighten to 54 lb. in. (b) Fit interface gasket supplied with engine or fit new gasket Pt. No. MS (c) Align pump shaft and slide pump into position, case drain connection uppermost. (d) Lubricate stud threads with engine oil and secure pump in position with four attachment nuts and washers. Torque tighten to 54 lb. in. and wirelock. (21) Refer to Figure 404. Fit propeller RPM control support bracket (22) Refer to Figure 404. Fit fuel control support bracket (23) Refer to Figure 404. Fit power control support bracket (24) Refer to Figure 404. Fit power input lever NOTE: If engine is required for immediate installation, lever is finally rigged postinstallation on airframe. (25) Fit exhaust stubs. (26) Refer to Figure 409. Install fire sensor and associated clips and attachments. NOTE: Operations (27) thru (30) which follow detail the rigging of a QEC which is being prepared as a standby unit. (27) Refer to Figure 406. Rig the LBA back-up stop and reverse pitch indicating mechanism as follows:- NOTE: The procedure will be adequate to permit flight, however the engine installed procedure should be performed at the next available opportunity. Refer to , pb201. Page 418 Apr 24/03

19 SD3-60 AIRCRAFT MAINTENANCE MANUAL z LBA Back-up Stop and Reverse Pitch Ind. Mech - Rigging (QEC build) Figure 406 Page 419 Apr 24/03

20 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (a) Fit pitch indication setting tool T on propeller mounting flange as shown on detail C. Secure with four propeller mounting bolts, Pt. No. B NOTE: 1. Propeller shaft should initially be rotated to a position which will permit 'cut outs' in rear wall of setting tool dummy low stop collar to accept slipper blocks of pitch indicating mechanism and propeller reversing lever. 2. Ensure setting tool is fully mated with flange. (b) Slacken attachments of both proximity switches. (c) Adjust setting tool such that the FP. BACK-UP face of bar gauge can contact respective rear faces of dummy low stop collar and propeller flange. (d) Adjust fine pitch proximity switch on its mounting plate slots such that just over 50% of the switch is now covered by target plate on camplate assembly. Tighten attachments. (e) Adjust setting tool to position determined by the REVERSE face of bar gauge and set reverse proximity switch on its slots such that just over 50% is covered by target plate on camplate assembly. Tighten attachments. NOTE: Leave setting tool installed to permit subsequent rigging of engine leakages. (28) Rig the front linkage. Refer to Figure 407. (a) Refer to Figure 406. Adjust setting tool T such that the FEATHER face of the bar gauge can just be inserted where shown. Maintain this setting. (b) Disconnect fuel governor reset arm (11) from fuel governor interconnecting rod (2). (c) Rig the cased wire-rope assembly (propeller reversing system) as follows:- 1 Back-off forward sliding link (9) to detach from the clevis attachment terminal. Unscrew and retain the wire-rope ball end (split collet) thus exposed. 2 Refer to Figure 408. Disconnect rear clevis (1) from propeller control cam. Lift clevis clear of cam and position alongside (nearest engine centreline). Withdraw rearwards sufficiently to permit sliding link (21) to be unscrewed from clevis attachment terminal. Wind exposed ball-end on wire rope forward and reintroduce wire-rope to 'bottom out' in clevis terminal; maintain this condition and wind back ball-end to seat in terminal and reconnect sliding link. 3 Push rear clevis forward to feed wire-rope through casing. Refit ball end retained at 1, winding back sufficiently to ensure rope 'bottoms out' when re-introduced to forward clevis attachment terminal; maintain this condition, wind ball end forward to seat in terminal and reconnect forward sliding link. Page 420 Apr 24/03

21 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Front Linkage - Rigging (QEC Build) Figure 407 Page 421 Apr 24/03

22 z SD3-60 AIRCRAFT MAINTENANCE MANUAL 4 Ensure that propeller reversing lever (3) is connected in the beta control valve clevis (4) and the carbon slipper block (5) is located in the dummy low stop collar. 5 Refer to Figure 408. Operate power input lever (33) to place follower lever (15) in a mid travel position between FLIGHT IDLE and max power. 6 Refer to Figure 408. Reconnect rear clevis 1, to the third hole from the top in the propeller control cam (23). Check clevis is in safety (through inspection hole). 7 Disconnect forward clevis (24) from the propeller reversing lever (3). NOTE: A sliding spacer is installed in the attachment hole. Do not lose when disconnecting. 8 Pull forward firmly on front sliding link (9) to eliminate cable backlash and adjust clevis end (24) such that when re-aligned with pick-up hole (spacer re-fitted) in reversing lever (3), the slot end face of the beta control clevis (4) is flush with the beta valve stop nut (10). NOTE: Ensure clevis end (24) is in safety (through inspection hole). (d) Adjust length of fuel governor interconnecting rod (2) to exactly align hole through it with the outer hole through fuel governor reset arm (11). Shorten the interconnecting rod by 1/2 turn and reconnect. (e) Tighten nuts and approriately lock (cotter pins/lockwire). (29) Rig the rear linkage. Refer to Figure 408. NOTE: The FCU is substantially pre-rigged by the engine manufacturer to minimize preengine run rigging activity; however the following aspects of the rigging should be checked. (a) Check that FCU interconnect rod (12) is set to nominal length of 8.25 in. between centres and is connected between the outer hole in arm (18) and the third hole from the top in FCU activating lever (20). (b) Check for free movement of input lever (33) between flight idle and max power (FCU max forward stop contacted). Return to flight idle and insert rigging pin in cambox assembly to maintain flight idle. (c) Check that input lever (33) is installed on cambox shaft (16) at 5 to 10' below horizontal; if necessary, remove and re-install to comply. Page 422 Apr 24/03

23 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Rear Linkage - Rigging (QEC Build) Figure 408 Page 423 Apr 24/03

24 z SD3-60 AIRCRAFT MAINTENANCE MANUAL 4. Installation (30) Remove setting tool T as follows:- (a) Remove the four mounting bolts. (b) Rotate setting tool and propeller shaft such that cut-outs on the rear wall of the setting tools dummy low stop collar permit tool to be extricated from slipper blocks. NOTE: Rigging and associated checks of the fuel condition and propeller RPM controls are performed post engine installation. (31) Assemble top left and right hand engine mounts and associated gaskets on engine. NOTE: Refer to , pb201. Refer to , pb201. As appropriate to mount type. Ignore references to aircraft attachment contained therein. (32) Place botton left and right hand mounts in a stowage bag and secure to engine until required immediately prior to installation on airframe. A. General Notes WARNING: THE FOUR BOLTS WHICH SECURE THE ENGINE MOUNTS TO THE MOUNTING RING MUST BE SUBJECTED TO NON-DESTRUCT TESTING BEFORE INSTALLATION, I.E. A MAGNETIC PARTICLE INSPECTION PER ASTM STANDARD E1444 (REPLACE PART IF CRACKS ARE FOUND). THIS IS ADDITIONAL TO THE BOLTS INSPECTION REQUIREMENTS DETAILED IN OR (AS APPROPRIATE TO MOUNT TYPE). If replacement engine is a standby QEC unit, the operations denoted thus * should be ignored. B. Preparation for installation (1) Refer to Figure 403. Connect sling ropes A, B, C & D to power plant and remove unit from build stand. (2) Ignoring references to airframe attachment, fit bottom left and right hand engine mounts and associated gaskets to engine, as appropriate to mount type. Refer to , pb201. Refer to , pb201. C. Install engine on airframe (1) Check that airframe mounted controls and equipment are clear of engine mounting ring. (2) Raise engine to a position immediately forward of installation position. (3) Disconnect sling rope B and carefully maneouvre engine rearwards until aft slinging point is passed through mounting ring. Reconnect sling rope B. Page 424 Apr 24/03

25 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Fire sensor - Removal/Installation Figure 409 Page 425 Apr 24/03

26 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (4) Free sling ropes C and D and further manoeuvre engine rearwards to align engine mounts with pickup brackets on inner face of engine support ring. (5) At each of the four locations, fit mount-to-airframe interfacing attachments as follows:- (a) With washer under head, insert support ring bracket to mount attachment bolt from rear; assemble washer and nut on bolt and torque tighten to lb. in. (b) Lock attachment nut with split pin. (6) Remove engine sling. D. Post installation procedures Initial actions: (1) Install propeller. - Propeller Model HC-A6A-3. Refer to , pb Propeller Model HC-A6A-3A. Refer to , pb201. (2) Fit two lower portions of rear inner fireshield. E. Left side of engine actions Refer to Figure 401. NOTE: In the interests of clarity, it may occasionally be advantageous to refer to view relative to opposite engine (i.e. where plumbing routeing obscures referred item/s on view under consideration. (1) Identify and connect ignition leads to ignition exciter, idented KA7 (unit is located on lower left side of engine tubular support structure). NOTE: Fit ignition lead ties at positions noted during engine removal procedure. (2) Identify and connect fire sensor connector WB11 to rear face of forward fireshield. (3) Reconnect air-conditioning P3 bleed supply flexible hose to P3 adapter (located at 9 o'clock position on engine) as follows:- (a) Connect free end of bonding lead which is attached to the bottom left mount pickup bracket on the engine support ring to the bottom aft attachment bolt securing the P3 adapter. NOTE: Torque tighten bolt to lb. in., then wirelock. Page 426 Apr 24/03

27 SD3-60 AIRCRAFT MAINTENANCE MANUAL z (b) Orientate flex hose through engine support ring and connect to P3 adapter using clamp Aeroquip Marman, Pt. No and gasket SD /B. NOTE: Initially torque clamp to 21 lb. in., then tap around periphery to ensure correct bedding. Finally tighten to 30 lb. in. (c) Fit P-clip which secures flex hose to cleat on inner face of engine support ring. (d) Torque tighten flex hose rear attachment clamp (immediately aft of rear fireshield). NOTE: Initially torque tighten to 25 lb. in., then tap around periphery to ensure bedding; finally tighten to 30 lb. in. (e) Refit aft clamp lagging. (4) Refit P2.5 bleed adapter and reconnect associated flex hoses as follows:- (a) Locate P2.5 bleed port (12 o'clock position immediately aft of engine mounting ring) and remove blanking plate. Retain four attachment bolts. (b) Fit P2.5 bleed adapter and gasket (respective Pt. Nos. SD and SD ) to bleed port employing bolts retained at (a). Wirelock attachments. (c) Re-attach flexible hoses to adapter employing clips retained during engine removal procedure. NOTE: The right hand hose serves the aerofoil de-icing system and the left, the air conditioning system. (5) Identify and reconnect the oil cooler flexible pipes (supply and return). Torque tighten connections to lb. in. and wirelock. (6) Connect the four flexible hydraulic pipes, idented MP, PI/INLET, CD/PCD and DRAIN to the hydraulic pump. NOTE: Torque tighten drain connection to lb. in. (remaining connections are not torque tightened until subsequent bleed operations are performed). (7) Reconnect compressor wash flexible pipe to adapter on aft face of rear inner fireshield. Wirelock. (8) Perform the following at the starter/generator:- (a) Remove the terminal block cover. (b) Remove the temporary insulation from the unit cables and connect to the terminal block according to the cable marker sleeves. Torque tighten in accordance with (c) Refit cable clamp and terminal block cover. Page 427 Apr 24/03

28 z SD3-60 AIRCRAFT MAINTENANCE MANUAL (d) Connect the bonding lead at the upper attachment point of the inlet duct with the attachments retained on removal. Torque tighten the nut from 7 to 9 lbf. in. (e) Reconnect cooling inlet and outlet flexible bellows employing clipping retained during engine removal procedure. F. Right side of engine actions Refer to Figure 401. NOTE: 1. Unless otherwise stated, Refer to Figure 401 (viewing left or right engine as appropriate). 2. In the interest of clarity, it may occassionally be advantageous to refer to view relative to opposite engine (i.e. where plumbing routeing obscures referred item/s on view under consideration. (1) Refer to Figure 402. Identify and reconnect forward portion of engine harness to appropriate connectors FW5, FW6 and FW7 on forward face of rear fireshield. Fit clipping which secures harness to engine mounting ring. (2) Refer to Figure 402. Identify and attach free connectors of aft portion of engine harness to:- (a) Reserve power solenoid valve, idented QJ2. (b) Fuel flow transmitter, idented QC5. (c) Ng tacho-generator, idented EG2. (d) Oil temperature bulb, idented EA3. (3) Connect fire detection terminal to connector on wing front spar fireshield. Also attach fire sensor clip immediately forward of the terminal to the engine mounting frame. (4) Install torque indication pipes, SD (reduction gearcase air pressure datum) and SD (torquemeter oil pressure reference line) between appropriate connections respectively located immediately aft and forward of the rear outer and forward fireshields. Fit bulkhead seals and cover plates. NOTE: When fitting the two-ply seals at each of the referred fireshields, position such that pipe accommodating splits are not coincident. (5) Identify and connect the oil pressure indication flexible pipe to oil pressure adapter on engine. Torque tighten to lb. in and wirelock. Page 428 Apr 24/03

29 SD3-60 AIRCRAFT MAINTENANCE MANUAL z (6) Refer to Figure 405. Connect the three flexible pipes shown thereon to the appropriate adapters on the rear outer fireshield. The pipe systems and related torque tightening values are:- (a) Fuel blowdown (40-65 lb.in.). (b) Prop shaft seal drain (40-65 lb.in.). (c) Combustion drain ( lb.in). (7) Identify and connect the following fuel flexible pipes. (a) Fuel inlet-attach to inlet connection on fuel heater. Torque tighten to lb.in. and wirelock. (b) Fuel purge line-attach to upper connection of tee-piece on top of fuel pump. Torque tighten to lb. in. and wirelock. (c) Fuel pump drain - attach to adapter beneath pump. Torque tighten to lb. in. (8) Reconnect starter/generator seal drain flexible pipe to elbow in piping from unit mounting pad. (9) Reconnect flexible oil breather pipe to connection on accessory gearcase. Secure with hose clamp AGS (10) Connect and rig the fuel condition and propeller RPM control circuits (refer to power plant adjustment/test section). (11) *Connect and rig the power control circuit (refer to power plant adjustment/test section). NOTE: If engine was a standby QEC unit, engine mounted linkages will already be rigged and it should only be necessary to place flight compartment and related engine levers in compatible rigged positions to permit connection. Refer to , pb501. (12) *Rig the LBA back-up stop and reverse pitch indicating mechanism. Refer to , pb201. Page 429 Apr 24/03

30 z SD3-60 AIRCRAFT MAINTENANCE MANUAL G. Completion actions: (1) Perform those aspects of priming and bleeding the hydraulic power circuit which relate to the hydraulic pump. Refer to , pb301. NOTE: After priming and bleeding, tighten connections on pump to the following values:- Main Pressure MP - ( lb.in. and wirelock). Pump Inlet PI - ( lb.in and wirelock). Case Drain PCD - ( lb.in and wirelock). (2) Attach main intake cowl restraint cable and reconnect electrics on rear bulkhead at: (a) Plug break EPB1 (b) Engine terminal block ETB4 (3) Refit cowl panels, leaving main intake cowl open at this stage. NOTE: When fitting panel 410AT it will be necessary to open the oil filler access door contained within the panel. This will provide access to attach the starter generator cooling outlet vent to the panel. (4) Perform engine depreservation procedure. Refer to , pb301. (5) Perform ground check run including performance (power) checks. Refer to, pb501. Page 430 Apr 24/03

31 SD3-60 AIRCRAFT MAINTENANCE MANUAL z AMM POWER PLANT - ADJUSTMENT/TEST PT6A-67R ENGINES I M P O R T A N T IN ADDITION TO RUNNING LIMITATIONS AND ENGINE RUN-UP PROCEDURES, THIS SECTION CONTAINS THOSE ENGINE RIGGING INSTRUCTIONS AND RIGGING CHECKS AND ADJUSTMENTS WHICH ARE EITHER (a) NOT COVERED BY THE ENGINE MAINTENANCE MANUAL OR (b) THE INFORMATION CONTAINED IN THE ENGINE MANUAL DOES NOT CATER FOR ENGINE SETTINGS SPECIFIC TO THE SD3-60 AIRCRAFT. THOSE UNDER CATEGORY (b) ARE IDENTIFIED THUS * AND TAKE PRECEDENCE OVER CONFLICTING INFORMATION IN THE ENGINE MANUAL. NOTE: The rigging of the autofeather microswitches must be verified following an engine, major engine component, or power control cable change - that is, any maintenance that requires re-tensioning of the power control cables. Refer to , pb Power Plant Limitations A. Fuel B. Oil For approved types and anti-icing additives. Refer to , pb1. (1) Types. Refer to , pb1. (2) Temperature. As appropriate to operating conditions. Refer to Table 501. (3) Pressure. As appropriate to operating conditions. Refer to Table 501. C. Operating parameters Refer to Table 501. D. Propeller feathering POWER lever must not be below FLIGHT IDLE when feathering the propeller (overtemperaturing of the engine will occur if PROP lever is selected to FEATHER whilst POWER lever is in the Beta range. E. Electrics (Starting) A starting cycle shall not be attempted unless the indicated voltage on the aircraft voltmeters is within the following limits:- Internal Battery External Battery External Power Minimum voltage Maximum voltage Page 501

32 z SD3-60 AIRCRAFT MAINTENANCE MANUAL NOTE: For an external power start, internal battery power must not be less than 14V. The starting cycle must be abandoned if it is evident that engine ignition has not been achieved by 25 seconds from the selection of an engine START - STOP switch to START. The number of starts in any 20 minute period must not exceed three. A ventilation cycle (dry motoring run) is to be considered as a start; i.e. in the event of an unsuccessful start, followed by a ventilation cycle and another unsuccessful start, a 20 minute period must elapse before a further ventilation cycle and starting attempt is carried out. After starting one engine, a generator-assisted start of the second engine must not be attempted until the load on the generator driven by the running engine is less than 250 amperes. F. Instrument limit markings The following is an explanation of the markings on the power plant instruments: Instrument Marking Explanation Propeller speed indicator Red radial line Maximum value 1700 rpm Green arc Normal operating range 1200 to 1700 rpm Gas generator speed Red radial line Maximum value 104.0% indicator Green arc Normal operating range 56% to 104.0% Torquemeter Red radial line Maximum value 4400 lb.ft. Yellow arc Precautionary range 3825 to 4400 lb.ft. Green arc Normal operating range 0 to 3825 lb.ft. Inter turbine temperature Red radial line Maximum value 855 C gauge Yellow arc Precautionary range 840 to 855 C Green arc Normal operating range 400 to 840 C Oil temperature gauge Red radial line Maximum value 110 C Yellow arc Precautionary range 105 to 110 C Green arc Normal operating range 20 to 105 C Oil pressure gauge Red radial line Minimum value 60 psi Maximum value 135 psi Yellow arc Precautionary range 60 to 90 psi Green arc Normal operating range 90 to 135 psi Page 502

33 SD3-60 AIRCRAFT MAINTENANCE MANUAL z Operating Conditions Gearbox Torque lb.ft. Power Plant Operating Limitations Table 501 Propeller Speed (Np) prpm Gas Generator Speed (Ng)% Inter Turbine Temp (ITT) C Oil Pressure psig Oil Temp C Starting or relight max. 0 to to 99 (5 sec.) Flight idle flight fuel (2) Ground operation unless otherwise specified Ground operation below 1000 prpm Ground operation Ng below 62% 3760 max. 0 to 500 (3) 950 to to max. 90 to to max max max. 60 to to 110 Reverse 2900 max max max. - - flight 3760 max max. 90 to to 105 conditions unless otherwise specified RTOP 4400 max ± max. 90 to to 110 (5 minutes) MCP ± max. 90 to to 110 MTOP 3960 max ± max. 90 to to 110 (5 minutes) Transient (except Starting) 5100 max. (20 sec.) 1870 max max. (20 sec.) 40 to max. NOTES: (1) 100% Ng corresponds to rpm. (2) bleeds OFF (3) 0 to 500 prpm is only permissible with propeller feathered. (4) Times in brackets refer to maximum times for which associated conditions may prevail. Page 503

34 z SD3-60 AIRCRAFT MAINTENANCE MANUAL 2. Ground check run CAUTION: DO NOT RUN AN ENGINE WITHOUT THE PROPELLER SPINNER DOME INSTALLED. WITHOUT THE OPPOSING SUPPORT OF THE SPINNER DOME, THE CENTRIFUGAL FORCE PROVIDED BY THE SPINNING PROPELLER COULD DAMAGE THE DE-ICER WIRE HARNESS. NOTE: The conditions under which check run is performed and the results obtained should be recorded on a Ground Run Check Sheet. Refer to Figure 506. A. Action prior to ground running (1) Position aircraft facing into wind. (2) Chock wheels (3) Position serviceable fire fighting equipment adjacent to the aircraft. (4) Ensure area around aircraft is free of loose objects. (5) Check engine oil level. Refer to , pb301. (6) Check engine intakes and exhausts are free from foreign objects. (7) Ensure danger areas around aircraft are clear of personnel. (8) Refer to emergency procedures (Refer to para. 10.). B. Pre-start checks:- (1) EXTERNAL Engine Blanks removed Engine cowls Secure Engine vents Check Propellers Feathered and free to rotate Engine fire bottle discs Green (4) Landing gear locking pins Fitted (2) INTERNAL Cabin doors Portable fire extinguishers 1D and 2D circuit breakers Parking brake Landing gear lever Closed Stowed In On DOWN Page 504

35 SD3-60 AIRCRAFT MAINTENANCE MANUAL z EMERGENCY BRAKE On LEFT and RIGHT ENGINE L.P. VALVES OPEN CROSSFEED VALVE LANDING GEAR Operation free, set SHUT DOWN EMERGENCY handle Up (not selected) Control locks Engaged 4P panel: ELECTRICS (dc. power) LEFT and RIGHT BATTERY switches ELECTRICAL MASTER switch Left and right voltages Tail battery voltage ESSENTIAL SERVICES switch/indicators SHEDDING BUS switches GENerator switches For starting with external electrical supply:- ELECTRICAL MASTER switch Busbars coupled Voltages GROUND SUPPLY, GROUND SERVICES BUS indicators ON INTERNAL 22V min. (internal start) 14V min. (external start) Check 14V min. Normal (vertical) EMERGENCY OFF EXTERNAL Check indicator Check (22-28V) Appropriate to supply 4P panel: ELECTRICS (A.C. power) L, R & STANDBY INVerter switches Press 'on' (OFF display goes out) Inverter voltages V Inverter frequencies Hz L & R INV switches 'off' in turn, check standby takes over, then 'on'. START MASTER switch NORMAL IGNITION LEFT and RIGHT switches OFF FIRE EXTINGUISHER discharge lights out RESERVE POWER switches left and right OFF As required 10P panel: LIGHTING Aircraft lights Page 505

36 z SD3-60 AIRCRAFT MAINTENANCE MANUAL 4P panel: ANTI-ICING Services ANTI-ICE VANE switches Other anti-ice systems 4P panel: FUEL Services FWD and AFT tank contents LEVELLING VALVES switch/indicator BOOSTER PUMP switches, left and right FILTER warning lights 7P: HYDRAULIC SERVICES CONTENTS PUMP INLET VALVE switches L & R NOSEWHEEL STEERING switch HYDRAULIC SERVICES pressures 1P panel: Audio Outside air temperature Engine instruments Landing gear indicators Centre console: POWER levers and ground/air lever PROP levers FUEL levers 9P panel: AIR CONDITIONING Services ENGINE bleed switch/indicators, left and right Non-bleed systems ON (ANTI-ICE indicated) then OFF (NORMAL displayed) As required As required Press for 'in line' (open) display if AFT tank contents less than 1800 lb. (820 Kg.) OFF out Correct OPEN ON Noted As required Noted Serviceable 3 greens Exercised up to control lock balk, then set to FLIGHT IDLE Exercised and set to FEATHER OFF Off-line (OFF) As required Page 506

37 SD3-60 AIRCRAFT MAINTENANCE MANUAL z 11P panel: DOORS/SYSTEMS - TEST DOORS warning indicators LIGHT FILAMENT test switch ENGINE FIRE WARNING LEFT & RIGHT SMOKE DETECTORS test switches Throttle full power switches (Reserve Power System) Flying control locks POWER levers RESERVE POWER switches (4P) POWER levers Flying control locks SHUT TEST, check all warning lights; red bright, all others dim. Set BRT or DIM as required. TEST and hold in turn, checking:- (a) Fire bell rings and is cancelled when the relevant (illuminated) FIRE P to C (press-to-cancel) module on panel 1P is operated. (b) The undernoted warning lights (left or right as appropriate) are lit during test:- FIRE FAULT module (panel 1P) FIRE EXTINGUISHER SHOT 1 & 2 buttons (panel 4P). Red light in FUEL lever (centre console) TEST in turn. Check appropriate SMOKE warning module illuminates. Disengaged Advance to 90% Ng alignment marks (orange). ARM, check associated indicators (panel 1P) display RTOP ON. Slowly retard and check that indicator captions immediately go out. Return levers to FLIGHT IDLE. Engage C. Starting checks:- SHEDDING BUS switches START MASTER switch EMGY ARMED Page 507

38 z SD3-60 AIRCRAFT MAINTENANCE MANUAL D. Start first engine BOOSTER PUMP switch ON Start switch START IGNITION switch NORMAL, above 10% Ng FUEL lever GROUND, when Ng stabilised (min. 12%). 'Light Up' Within 10 seconds ITT Monitor (855 to 1000 C) for 5 sec. Start and ignition lights Extinguished above 50% Ng Oil Pressure 90 psi. minimum (warning light out) CAUTION: WHENEVER GAS GENERATOR FAILS TO LIGHT UP WITHIN 10 SECONDS AFTER MOVING THE FUEL CONDITION LEVER TO GROUND, SHUT OFF FUEL, STARTER AND IGNITION. ALLOW A 30 SECOND FUEL DRAINING PERIOD, FOLLOWED BY 15 SECOND VENTILATION CYCLE (DRY MOTORING RUN - REFER TO PARA. 4.) BEFORE ATTEMPTING ANOTHER START. IT IS NOT NECESSARY TO ALLOW RUNDOWN AFTER DRY MOTORING RUN BEFORE RESUMING START. IF, FOR ANY REASON, STARTING ATTEMPT IS DISCONTINUED, ALLOW ENGINE TO COME TO COMPLETE STOP AND THEN ACCOMPLISH DRY MOTORING RUN. REPEAT COMPLETE STARTING SEQUENCE (OBSERVING STARTING LIMITS - REFER TO PARA. 1.). HYDRAULIC SERVICES pressures: MAIN SYSTEM NORMAL WHEEL BRAKES LEFT AND RIGHT EMERGENCY WHEEL BRAKES EMERGENCY LANDING GEAR GENERATOR switch (1st engine) psi psi psi psi ON (internal start only) E. Start second engine Generator ammeter (1st engine) Start as for 1st engine Below 250 amp (internal start only) Page 508

39 SD3-60 AIRCRAFT MAINTENANCE MANUAL z F. After start checks START MASTER switch NORMAL IGNITION switches LEFT and RIGHT OFF GENERATOR switches left and right ON ELECTRICAL MASTER switch INTERNAL SHEDDING BUSBAR switches NORMAL Generator voltage left and right 27-28V Generator current left and right Decreasing External supply Disconnected (if applicable) indicators Correct Avionics As required PROP levers cycle Taxi RPM-FEATHER-Taxi RPM Flaps 30 WARNING: (A) POWER LEVER MUST NOT BE BELOW FLIGHT IDLE WHEN FEATHERING THE PROPELLER (OVER-TEMPERATURING OF THE ENGINE WILL OCCUR IF FEATHER IS SELECTED WHILST POWER LEVER IS IN BETA RANGE). (B) RESTRICT IDLING TIME IN FEATHER TO AVOID EXCEEDING OIL TEMPERATURE MAX. LIMIT (110 C). FUEL LEVELLING VALVES Warning lights Shut, indicators vertical. Clear, except for CONTROL LOCKS, PITOT and BLEED. Perform rigging checks (Refer to para. 7.). WARNING: ENSURE ENGINE IS SHUTDOWN BEFORE PERFORMING ANY ADJUSTMENTS ON ENGINE-MOUNTED EQUIPMENT. THIS IS ESSENTIAL DUE TO CLOSE PROXIMITY OF PROPELLER AND EXHAUST NOZZLES. Perform system checks (Refer to para. 8.). Carry out performance checks (if appropriate) - Refer to para. 9. Page 509

40 z SD3-60 AIRCRAFT MAINTENANCE MANUAL 3. Engine Shutdown POWER levers FUEL levers PROP levers Lighting ELECTRICAL MASTER switch Battery switches BOOSTER PUMP switches GROUND FINE (allow engines to stabilise for 1 minute at minimum ITT) then levers to FLIGHT IDLE. OFF FEATHER As required OFF (unless required for lighting) OFF (unless required for lighting) OFF 4. Dry Motoring Run (ventilation cycle) General This procedure is used at any time it is necessary to remove internally trapped fuel or vapour e.g. following an unsuccessful start attempt, or if there is evidence of a fire within the engine gas path. Air passing through the engine serves to purge fuel, vapour or fire from the combustion section, compressor turbine, power turbines and exhaust nozzles. Procedure A details the actions required if motoring run is initiated as a maintenance function or if there is evidence of fire within the engine gas path. Procedure B details the actions required if motoring run is as a result of an unsuccessful start attempt and another start attempt is made. NOTE: For procedure B it is not necessary to allow engine to run down after motoring run before resuming start. Procedure A:- With electrical power for starting available (see pre-start checks, Refer to para. 2.), the motoring run is accomplished as follows:- FUEL lever IGNITION switch BOOSTER PUMP switch Start switch OFF OFF ON START Page 510