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TM 1-1520-240-MTF - Chinook Helicopter

1. e e e o e e e e 20 v 3NION3 SECONDS TIME Figure 5 12 11 Engine Ground Starting Time vs Ambient Air Temperature Static Sea Level C25 5 26 2 19 5 26 2 20 gt blank 55 1520 240 Engine Torque Temperature Probable Cause Correct Low High Dirty inlet and or compressor Bleed bend leaking Leaks in anti icing Erosion Damaged combustor section PTIT indicating system Combustion chamber drain valve open Low Low Low Calculation error Engine not properly topped Fuel control adjustment High Correct High Calculation error Fuel control adjustment Correct Correct High N1 indicating system error Correct Low Correct Torque indicating system Torque transmitter malfunctioning Correct Correct Low PTIT indicating system Figure 5 13 Turbine Engine Analysis Check Troubleshooting Chart U S GOVERNMENT PRINTING OFFICE 1992 654 12260030 5 26 3 5 26 4 blank C16 55 1520 240 7564 712 90006 8000100 VIBRATION TEST BATA i e tte Lew Omoda Ar M T Tom L L D Va iy Ob tapae Posest on terms OON 18 720 90 2 15 234 RAM 00 ROTOR RPM 15 066 N APM 2 Menon elieweble oce vibrenes
2. E e Fa e 8 HR V esee t e es ZAE KA swar EAA d A RET Vers oeque E Le AAA l ir eg CAAA e rq scc sra sso AALI 7 7 E E IE as SD 8 Exec e E EE LL v Le 10 20 30 40 50 A42863 ALIN 0PC 0cSI SS 55 1520 240 51 9 ul oz us wH oz Zt ag 21 ALUATUL
3. 55 1520 240 4 Verify the trim slide ball on the DU agrees with the turn and slip indicator e Vertical speed engine torque and engine TGT check 1 Perform a 500 FPM climb Verify the vertical speed pointer on the DU indicates a 500 FPM climb 2 Verify the torque numeric and torque analog bar on the DU displays the increased engine torque as displayed on the PDU 3 Repeat steps 1 and 2 for 2000 FPM 4 Repeat steps 1 through 3 for rate of decent noting decreased engine torque 5 Verify the No 1 ENG PTIT and No 2 ENG PTIT displayed on the DU matches the PTIT values displayed on the enter instrument panel f Airspeed groundspeed and drift angle 1 Increase airspeed to 120 KIAS and stabilize Verify the IAS on the DU is 120 KIAS 2 Verify groundspeed on the DU matches groundspeed on the doppler 3 Repeat steps 1 and 2 for airspeeds of 80 40 and 25 KIAS 4 Verify the velocity vector on the DU is identical to course deviation bar on HSI g Low altitude check done during approach to landing 1 Set LOW altitude warning marker on the AN APN 209 to 200 feet From an altitude of greater than 200 feet AGL transition to a hover at approximately 100 feet AGL Verify a box is displayed around the radar altitude numeric on the DU after passing through 200 feet AGL C22 4 40 55 1520 240 2 Verify the radar altitude AGL analog bar is dis played on the DU as t
4. If the start is not normal abort it If a second start is to be attempted wait at least 15 seconds after the tachometer indicates zero before starting This will allow sufficient time for fuel to drain out of the combustion chamber 4 13 C15 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE CAUTION After starting the first engine the second engine must be started or motored for 10 seconds within 3 minutes When operat ing for extended periods with only one engine operating the second engine must be motored for 10 seconds every 30 minutes The N2 section of the second engine starts turning when the first en gine is started however the lubrication system of the second engine is driven by the N1 section which does not begin to turn until the START sequence is initi ated Delay in starting the second engine will result in excessive wear on the N2 bearing package and seals 2 Second engine Start by using the same 43 A7 method as first engine G 1 NO 1 AND NO 2 ENGINE START Reference TM 55 1520 240 10 NOTE Either engine may be started first CAUTION The flight controls must be manned any time the helicopter is on the ground with the rotors turning C25 4 14 PROCEDURE TM 55 1520 240 MTF TROUBLESHOOTING CAUTION If no oil pressure is indicated during the starting sequence shut down engine and investigate 1 First engine Start as follows a L FUEL P
5. TROUBLESHOOTING GUIDE A STARTING INCLUDES APU CONDITION A1 A2 A3 A4 PROBABLE CAUSE Apu fails to start or fails during operation Check bite indicators on apu control box Note tripped bite se quence Refer to label on apu control box for decoded bits information figure 3 1 Engine will not motor with START switch at MO TOR Dc power is available to panel if STARTER ON caution light is on a Engine circuit breaker out b Faulty start switch Faulty engine start solenoid valve d Faulty start relay Faulty starter motor Faulty utility hydraulic system No engine combustion during START Listen for SNAP sound of igniters during engine start a Ignition key not on b Ignition circuit breaker out c Faulty ignition exciter d Faulty ignition harness e No starting fuel Check FUEL PRESS caution lights are out Engine will not accelerate to 12 within 15 seconds during start cycle Check utility hydraulic system pressure at 3350 psi flight engineer response Check for START caution light a Faulty utility hydraulic start solenoid valve 3 2 6 6 uomneuuoju eig pepooeg 71 6 BETE e O e 9 O e o O e o e o e e e o O 0 e e e O O O O T 62T 2B DECODED BIFE INFORMATION RESET START FURL VALVE amp EXCITER SIGNAL OUT
6. 25 55 1520 240 f Raise THRUST CONT lever if required to obtain minimum while ensuring or PAT PTIT limits of figures 5 12 8 hnd 5 12 7 respec tively Refer to Section V are not exceeded g Allow conditions to stabilize and record the follow ing CD FAT 2 PA 3 NR 100 4 ENG PTIT 5 NI 6 TQ 7 FF h Recover engine not being checked Engine passes test if it meets or exceeds torque value from figurg 5 12 5 Refer to Section i Repeat steps a through h for engine not previously tested j engine fails test use MAX power conditions in Section V charts and follow steps below 1 Select an altitude FAT combination from figure 5 12 4 l Refer to Section that provides the highest practical torque while observing the applicable transmission limits 2 Determine required minimum TQ from figure 3 4 5 12 6 Refer to Section V1 ENG COND lever of engine not being checked Slowly retard towards GND Ensure that ENG PTIT for engine being checked does not exceed 899 degrees If PTIT of 899 degrees is reached prior to required minimum TQ being attained engine has failed and the PA Test should be terminated Raise THRUST CONT lever if required to obtain minimum while ensuring MP or MP PTIT limits of and 5 12 7 respectively Refer to Section V are not ex ceeded k Allow conditions to stabilize and record th
7. 55 1520 240 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER This copy is a reprint which includes current pages from Changes 1 through 10 HEADQUARTERS DEPARTMENT OF THE ARMY 8 SEPTEMBER 1982 URGENT TM 55 1520 240 MTF C26 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 26 WASHINGTON D C 29 DECEMBER 2000 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT A Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand R emove pages Insert pages 2 42 1 2 42 2 blank 2 42 1 2 42 2 blank 2 43 and 2 44 2 43 and Retain this sheet in front of manual for reference purposes 55 1520 240 26 By Order of the Secretary of the Army Official ERIC K SHINSEKI General United States Army Chief of Staff Jet BML JOEL B HUDSON Administrative Assistant to the Secretary of the Army 0101004 DISTRIBUTION To be distributed in accordance with Initial Distribution No IDN 310195 requirements fcr TM 55 1520 240 CL 55 1520 240 25 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 25 WASHINGTON D C 15 May 2000 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELIC
8. FAIL 1 only if computer installed 2 CIPHER ON 1 Pilot Copilot Instrument Panel 1 EMERG PWR 2 2 HSI MODE SELECT BRG and MKR BCN lights 8 on each pilot panel CANTED Console l HDG BARO and RAD hold 2 Deleted 3 ALQ 156 if installed Press STATUS for STANDBY light b Check CM JAM and CM INOP caution panel lights out 2 39 C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 20 Parking Brakes Swivel Locks a Wheel parking D6 brakes Reset Check PARK BRAKE ON and MASTER CAUTION light on b MASTER CAUTION light RESET C SWIVEL switch Check UNLOCK and LOCK flight engineer response E 20 1 Ramp Isolation Check as follows a Place ramp control lever in the DOWN position until ramp rests on the ground then STOP b RAMP isolation switch OFF c RAMP control lever UP Check that ramp does not move then STOP d RAMP isolation switch ON e Adjust ramp as necessary 21 Cruise Guide Indicator Test B9 B10 FWD and AFT Check pointer in p white test band within 8 seconds 22 Altimeters Set local barometric pressure setting and compare with field elevation If more than a 50 foot error is noted corrective action should be initiated Unreliable for flight if more than a 70 foot error exists 23 RAD ALT Set LO index to 100 feet Set HI index to 800 feet and allow 1 minute for warmup
9. 2 DECU CHECK BEFORE LEAVING CHECKS k Doppler COMPLETE UPDATE FORMS A63094 Figure 5 15 Maintenance Test Flight Check Sheet 2 of 2 5 31 5 32 blank C25 55 1520 240 HEADQUARTERS DEPARTMENT OF THE ARMY WASHINGTON D C 8 September 1982 By Order of the Secretary of the Army E C MEYER General United States Army Chief of ROBERT M JOYCE Major General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 five copies to each account operator Re quirements for CH 47B C amp D aircraft 2 e eL The Metric System and Equivalents Linear Measure centimeter 10 millimeters 39 inch decimeter 10 centimeters 3 94 inches meter 10 decimeters 39 37 inches dekameter 10 meters 32 8 feet hectometer 10 dekameters 328 08 feet kilometer 10 hectometers 3 280 8 feet Weights centigram 10 milligrams 15 grain decigram 10 centigrams 1 54 grains gram 10 decigrams 035 ounce dekagram 10 grams 35 ounce hectogram 10 dekagrams 3 52 ounces kilogram 10 hectograms 2 2 pounds quintal 100 kilograms 220 46 pounds metric ton 10 quintals 1 1 short tons Liquid Measure centiliter 10 milliters 34 fl ounce deciliter 10 centiliters 3 38 fl ounces liter 10 deciliters 33 81 fl ounces dekaliter 10 liters 2 64 gallons hectoliter 10 dekaliter
10. 5 Check marker beacon lights anti audio during approach Check high and low sensitivity 6 With pointers centered continue approach to runway to as certain that proper landing can be made f ADF 1 Tuning reception and volume 2 Check ADF ANT and LOOP operation 3 ADF on HSI MODE SELECT panel Engaged and lit 4 No 2 pointer on HSI within 3 of magnetic bearing to station 5 Total No 2 pointer fluctuation 5 6 Station passage g Marker beacon J15 1 Push to test any MKR BCN light One light tests all three 2 79 TM 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 2 Check audio high and low sensitivity over appropriate markers 3 Check light operation high and low sensitivity over ap propriate markers h Transponder AN APX J171J18 100 and Radar Signal Detecting Set AN APR 39 1 Transponder master switch STBY Allow 2 minutes for warmup Check CODE OFF flag on pilot s barometric altimeter out of sight 2 At a minimum altitude of 2 000 feet and distance of 30 miles request a transponder check from an appropriate radar facility 3 Check all modes including emergency Check AIMS altimeter 4 Obtain operation in formation from radar facility 5 While checking J18 transponder check operation of radar signal detecting set Check that detecting set displays bearing to all known radar facilities i H
11. Engine Ground Starting Time vs Ambient Air Temperature Static Sea Level 5 26 2 19 5 13 Turbine Engine Analysis Check Troubleshooting Chart 5 26 3 5 I4 Engine Vibration Test Data Sheet 5 27 Maintenance Test Flight Check Sheet 5 29 C25 iv 55 1520 240 LIST TABLES Number Title Instrument Range Markings Cockpit PRESS TO TEST Caution Lights v vi blank C25 55 1520 240 SECTION INTRODUCTION 1 PURPOSE The purpose of this manual is to provide com plete instructions for performing a maintenance test flight of CH 47D aircraft For the specific conditions which require a general or limited maintenance test flight refer to TM 55 1500 328 25 and TM 55 1520 240 23 2 DEFINITIONS a Maintenance Test Flight A functional test flight for which the primary purpose is to determine whether the airframe powerplant accessories and other equipment are functioning in accordance with predetermined requirements while subjected to the intended environment b Warnings Cautions and Notes Warnings Cautions and Notes are used to emphasize important and critical instructions and are used for the following conditions An operating procedure practice etc which if not correctly followed will result in personnel injury or loss of life An operating procedure prac
12. Joje nunooy Duueeis 65 6 en6i4 PRESSURE PSI 1 400 1 200 252 EE oe TEMPERATURE ALIN O02 02S1 SS INL LE G syw 1oyejnuinooy eyeig 79 6 PRESSURE PS 06 808 0 JLIWN 0tc 0cSL SS WL 9 oJnssaJg JeusinBunx3 Ambient Minimum Maximum Temperature Indication Indication Fahrenheit Centigrade Psi Psi 65 54 271 344 60 51 275 350 40 40 292 370 20 29 320 400 0 18 355 437 20 7 396 486 40 4 449 540 60 15 518 618 80 27 593 702 100 38 691 784 125 52 785 902 JLIWN Otc 0cSL SS WL PRESSURE ALTITUDE 1000 FEET TM 55 1520 240 MTF CH 47D FORWARD LCT INDICATOR SCHEDULE SHEET 1 OF 2 HEURE 18 Y 16 HH 20 BELOW 40 KNOTS THE SCHEDULE MAIN TAINS THE ACTUATORS AT THE EQUIVALENT EXTENSION FOR 40 KNOTS FOR THE APPROPRIATE ALTITUDE AIRSPEED INDICATOR TOLERANCE NOT INCLUDED ABET 4 or 2 91399 0 40 60 80 100 120 140 INDICATED AIRSPEED KNOTS i Figure 5 8 CH 47D FWD and AFT LCT Indicator Schedule Sheet 1 of 2 5 13 5 14 blank 55 1520 240 MTF CH 47D AFT LCT INDICATOR SCHEDULE SHEET 2 OF 2 BELOW 40 KNOTS THE SCHEDULE MAIN TAINS THE ACTUATO
13. NOTE Flight engineer check droop stops engaged before ENG No 1 shutdown 34 1 Overspeed Check a Place both engines in PRI b ENG No 1 and No 2 ENG COND levers GND Advance ENG 1 ECL from GND to set at 79 190 Allow RRPM and FUEL PLOW to stabilize d OSPD switch No 1 activate and hold switch Check that fuel flow drops to 300 PPH 25 C25 2 46 2 TM 55 1520 240 TROUBLESHOOTING PROCEDURE STARTING ENGINES Cont e ECL No 1 STOP f Release OSPD switch Advance ENG No 2 ENG COND lever from GND 79 190 h ENG No 1 Restart i Repeat steps d thru f for ENG No 2 1 Normal shutdown 34 2 MABE Engine Start Reversionary 35 36 37 Mode See Section IV XMSN OIL PRESS Check for minimum 7 psi HM ENG COND levers PLIGHT Check for 92 to 96 rotor rpm En gine acceleration should be smooth with no indication of roughness or surging ENGINE BEEP TRIM system operation No 1 and No 2 switch a Check Pilots NORMAL ENGINE BEEP TRIM operation b Check Copilots NORMAL EN GINE BEEP TRIM operation Es tablish 100 rotor rpm and match torque c Pilots and Copilot s rotor tachom eter readings 2 split max 2 46 3 2 46 4 blank REFERENCE FOE BSIBGIES 25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 38 Fluid drain lines Check flight en gineer
14. 3 2 maximum difference between pilot and copilot indica tors d VOR 1 Tuning reception and J17 volume HSI MODE SELECT panel VOR SEL and CMD SEL engaged and lit 9 HSI MODE SELECT Ens OR ADF engaged and it 2 77 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 4 No 2 pointer HSI 3 of correct magnetic course to station 5b Note course direction on HSI a Centered when on se lected VOR course b 10 off course gives full J13 deviation bar displacement 6 Station passage 7 Total No 2 pointer fluctua tion 5 8 VOR frequency Tune to 108 00 MHz VOR MB TEST switch Press and hold b On both HSI note TO arrow in view the deviation bar deflects within the 2 dot deflection and warning flags are concealed c Note all three marker beacon lights lit on HSI MODE SELECT panel d Release TEST switch and return VOR to operational frequency e ILS if available 1 At a distance of at least 9 nautical miles tune to the localizer fre quency Start on ILS approach C19 2 78 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 2 Check that NAV and GS warning flags are concealed 3 Steer right and left Check that the localizer pointer moves left and right respectively 4 Climb and descend Check that the glide slope pointer moves up and down respectively
15. 4 Speed Sweep Check a Increase and stabilize air H12 speed at 80 knots Record longitudinal stick position 5 Speed Sweep Check a Increase and stabilize air speed at 100 knots b Record longitudinal stick position NOTE Before selecting either AFCS trim the helicopter to 110 knots with both AFCS operation 6 AFCS Evaluation a Stabilize airspeed at 110 knots C9 2 68 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont b BARO ALT ENGAGED Check that altitude hold maintains altitude 100 feet during steps c through i c Directional pedal separation Check as follows 1 Insure aircraft is in trim ball centered AFCS SYSTEM SEL BOOTH 3 Switch from BOTH to NO 1 Measure pedal adjustment required to return aircraft to trim should not exceed 0 5 inch m AFCS SYSTEM SEL BOTH b Check NO 2 the same as NO 1 Yaw correction should not exceed 0 5 inch per system or 1 0 inch total d Pitch axis Check as follows 1 Establish trimmed airspeed and attitude at 110 knots Move the cyclic stick forward without operating the centering device release button Allow airspeed to increase to 120 khots Return the stick to trim position Airspeed should return to 110 knots and hold 5 knots 2 Repeat step 1 except move the stick aft to decrease airspeed to 100 knots 2 69 C15 55 1520 240 TROUBL
16. 8 NO 1 and NO 2 power dis tribution panels Check all circuit breakers and gang bar up Check for clearance between gang bar and cover 9 Spare lamp box Check 10 Mirror Adjust 11 FAT gage Check FAT condition and security 2 28 TM 55 1520 240 MTF PROCEDURE TROUBLESHOOTING REFERENCE BEFORE STARTING ENGINES Cont 12 Overhead switches and control panels set as follows O a EAPS ENG 1 and ENG 2 FAN switches OFF DOORS CLOSE b LIGHTING switches As required C COMPASS switch As required d TROOP WARN switches OFF HEATING switches OFF f WINDSHIELD WIPERS switch OFF g ELECT switches Set as follows 1 switch OFF P 2 switch OFF 3 1 and 2 GEN switches OFF 4 APU GEN switch OFF h FUEL CONTROL switches Set as follows 1 CROSSFEED FUEL VALVES switch CLOSE 229 C17 55 1520 240 TROUBLESHOOTING PROCEDURE BEFORE STARTING ENGINES Cont C25 2 REFUEL STATION switch OFF 3 FUEL PUMPS switches OFF i START switches OFF j ENG COND levers STOP jl FADEC switches Check or set as follows 1 NR switch 100 2 PRI REV switches PRI 3 B U PWR switch OFF 4 LOAD SHARE switch TQ 5 ECLs STOP k LIGHTING switches As re quired 1 ANTI ICE switches OFF m HOIST switches OFF n CARGO HOOK switches Set as follows 1 MASTER switch
17. C15 2 40 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 23 1 Operation Check both pilot s and co pilot s a Pitch roll adjustment and travel Check 8 minimum roll left and right 5 up 10 down minimum smooth operation b VGI switch EMER Check that OFF flag stays hidden c VGI switch As required 24 FIRE DETR switch TEST C25 check FIRE PULL handle warning lights on release switch and check FIRE PULL handle warning lights out 25 FIRE PULL handle flight engineer response a NO 1 FIRE PULL handle Pull b NO 1 FUEL VALVE C26 CLOSED Check FUEL VALVE in dicating light cycles from off to on then off as valve aligns with switch position selected c NO 1 FIRE PULL handle Push in d NO 1 FUEL VALVE in dication light on then off Check FUEL VALVE OPEN e Repeat check for NO 2 FIRE PULL handle 2 40 1 2 40 2 blank C13 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 25 1 Crossfeed Fuel Valve Check Check as follows flight engineer response a CROSSFEED FUEL VALVE switch OPEN Check that both crossfeed fuel valves open and indicating lights cycle on then off b CROSSFEED FUEL VALVE switch CLOSE Check that both crossfeed fuel valves close and indicating lights cycle on then off 26 FUEL QUANTITY Indica tor Check as follows a Check
18. Maintenance Test Flight Manual ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is in dicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 3 and 2 4 2 3 and 2 4 2 21 and 2 22 2 21 and 2 22 2 33 through 2 38 2 33 through 2 38 57 2 38 1 2 38 2 2 41 2 42 2 41 2 42 2 55 through 2 58 2 55 through 2 58 2 61 and 2 62 2 61 and 2 62 cop 2 62 1 2 62 2 2 63 through 2 72 2 63 through 2 72 ias 2 2 1 2 72 2 2 73 and 2 74 2 73 and 2 74 Ibi 2 74 1 2 74 2 3 37 and 3 38 3 37 and 3 38 4 25 and 4 26 4 25 and 4 26 4 26 1 and 4 26 2 4 26 1 and 4 26 2 5 29 5 30 5 29 5 30 5 31 5 32 5 31 5 32 55 1520 240 C6 2 Pages listed above which are pre ceded by an asterisk are being pro vided to replace unlaminated pages from previous URGENT changes 3 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army JOHN A WICKHAM JR General United States Army Official Chief of Staff R L DILWORTH Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF requirements for CH 47D Helicopter Cargo Transport URGENT TM 55 1520 240 MTF C5 CHANGE HEADQUARTERS DEPARTMENT OF THE AR
19. Mane 0 N Moum RPM ger ongune ewcrett spac fication Figure 5 14 Engine Vibration Test Date Sheet 5 27 5 28 blank ACFT MODEL amp SERIAL NUMBER DATE PURPOSE OF TEST FLIGHT PILOTS NAME amp UNIT OPERATING DENSITY WEIGHT ALTITUDE FT 18 FLT cont hyd LBS SYMBOLS SATISFACTORY X DEFICENCY 19 Control Interlock 20 Control Centering 21 Windshield Anti ice Pitot and AFCS Yaw ports 22 Control Breakout 24 No 1 ENG Start 8 Eng oil press psi b GND idle 45 c Bellows Check 8 3 gt gt m o c w d o a a 4 XFER swiones 25 No 2 ENG Ster 6 Cargo hooks winch a Eng oi press ztemaigwe 6 Parking brakosiawivoi Benawa cre o EE nevesionan _ 27 PRESS check 7 pai min Detector ighte 29 Beep operation P OF PULL handles 90 Eng oll prose fux A Not pal Sommer an minimum ees 1 17 Neutral pedal meseurement ason lt amp Ne TM 55 1520 240 MTF 32 Bleed band check 1 Mechanical Rig Checks ena tong Mesure E
20. OFF 2 SELECT switch As required 3 EMERG REL ALL switch OFF Cover down o HYDRAULIC switches Set as follows 1 POWER switches Off 2 FLT CONTR switch BOTH 3 BRAKE STEER switch ON Cover down 4 RAMP PWR switch ON 5 RAMP EMER switch HOLD Cover down 2 30 REFERENCE 55 152 240 TROUBLESHOOTING PROCEDURE REFERENCE BEFORE STARTING ENGINES Cont 13 Magnetic compass Check full of fluid no bubbles or dis coloration and compensated within last 12 months 14 AGENT DISCH switch Check spring loaded to the neutral position 15 FIRE PULL handles In 16 Systems instruments Check engine transmission and rotor systems for static indications slip page marks orientation and operating range markings Refer to 17 XMSN OIL PRESS switch SCAN 18 XMSN OIL TEMP switch SCAN 19 VHF ANT SEL As re quired 20 Flight instruments Check indications and set as follows a Turn and slip indicators Check race full of fluid needle and ball centered Alignment between indicators b Airspeed indicators Compare indicator readings c Vertical velocity indica tors Check indicators at zero d HSI Check as required C13 2 31 55 1520 240 Table 2 1 INDICATOR GAS PRODUCER TACHOMETER POWER TURBINE INLET TEMPERATURE ENG OIL TEMPERATURE HP ENGINE OIL PRESSURE GAS PRODUC
21. Reference TM 55 1520 240 23 NOTE Unsatisfactory bleed band cycling or compres sor stall may be encountered if bleed band closure is not within N1 speed range specified If N1 speed for bleed band closure is above that specified an increase in specified fuel con sumption will result until bleed band closes In an extreme case where bleed band does not close at all or may be open again at high power engine will suffer loss of maximum power NOTE This procedure requires two way communica tions between the pilot and the mechanic The pilot will run the engine and note the NI readings The mechanic will notify the pilot when the bleed band closes and adjust if necessary 4 14 7 4 14 8 blank C25 55 1520 240 1 Deleted 2 NO 1 amp 2 ENGINE BEEP TRIM DECREASE for 8 Seconds 3 Deleted 4 Note engine N1 readings 5 Use the appropriate beep system Normal or Emergency on the engine to be checked to indicate an engine N1 less than the minimum specified for the applicable ambient temperature as indicated on figure 5 9 NOTE CAUTION Bleed band must be open under this operating condition Do not allow engine speed to go below minimum N1 speed during this check 6 Slowly increase appropriate beep trim while maintaining rotor rpm within limits and determine N1 when bleed band has just closed NOTE Closure may be determined by inserting a 0 010 inch feeler gage under the bleed
22. US GOVERNMENT PRINTING OFFICE 1999 733 172 80014 2 10 1 2 10 2 blank C23 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE INTERIOR Cont Aft Cabin Cont 21 ENGINE NO 1 FUEL VALVE Check OPEN electrical plug secure 22 Ramp interphone control panel As required 23 Fire detect control unit Check con dition and security No 1 engine 24 Hand fire extinguisher Check seal security date and properly tagged EXTERIOR Aft Cabin 1 Navigation light Check condition 2 Fluid vent and drain lines Check clear 21 RARAS Engine wash system Check condition and security 3 Right aft landing gear Check as follows a Right aft landing gear support struc ture Check for cracks or distor tion b Tires for inflation and condition c Shock strut for proper extension cleanliness and static lock un locked d Power steering actuator wheel brakes and hoses for leakage chaf ing and security 2 11 C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Aft Cabin Cont e Electrical connections for condition and security f Landing gear proximity switch Condition linkage adjustment and security 4 Hydraulic system test panel Check all caps secure 5 Check No 2 engine lower side NOTE If TEAC PAT is to be performed all preflight inspection requirements checks required prior to TEAC PAT must be accomplished In
23. d Control centering improperly rigged extreme travel positions Control system will not stay displaced a Magnetic brakes inoperative b Balance springs defective Control travel incorrect a Bent distorted or broken component b Improperly adjusted stops Thrust detent improper position Thrust detent stop improperly rigged Improper breakout forces a Improperly set balance springs b Binding in controls c Improper spring installed Excessive control displacement a Aircraft incorrectly rigged 3 37 55 1520 240 CONDITION PROBABLE CAUSE b AFCS engagement error Verify with AFCS OFF H12 Longitudinal stick position is out of tolerance a Aircraft improperly rigged b DASH actuator not set at 36 inch c Longitudinal control position transducer cpt improperly adjusted d Proximity switch failure e Pitch change links improperly adjusted H13 Lateral stick position out of tolerance during into the wind hover Aircraft improperly rigged H14 Excessive pedal split a Aircraft improperly rigged b AFCS engagement error in yaw ILCA or AFCS malfunction Verify with AFCS OFF c Improperly positioned pedal adjustment RPM high or low Refer to VI a Aircraft improperly rigged b Pitch links improperly set c Test conducted outside of gross weight toler ance band d Test conducted outside of specified airspeed tolerance band H16
24. 0 86 186 8 271 520 968 543 1010 1850 46 50 58 11 88 190 4 277 530 986 549 1021 1868 40 40 40 2 90 194 0 282 540 1004 554 103 1886 4 30 22 3 92 197 6 288 550 1022 560 1040 190 29 20 4 4 94 201 2 293 560 1040 566 1050 1922 23 10 14 6 96 204 8 299 570 1058 571 1060 1940 17 8 0 32 98 208 4 3 580 1076 577 1070 1956 16 7 2 35 6 8 100 212 0 310 590 1094 582 1080 1976 110 230 316 600 1112 588 1090 199 120 248 321 610 1130 593 1100 2012 130 266 327 620 1148 599 1110 2030 15 6 39 2 14 4 6 42 8 13 3 8 46 4 RSSSLUNSSysseseveeess 12 2 10 50 0 140 284 332 630 1166 604 1120 2048 11 1 12 3 6 150 302 338 60 1164 610 1130 2066 10 0 14 7 2 160 320 343 650 1202 616 1140 2084 8 9 16 60 8 170 338 349 660 1220 621 1150 2102 7 8 18 66 4 180 356 3 670 1238 627 1160 2120 6 7 20 68 0 190 374 360 680 12 632 1170 2138 5 6 22 71 6 200 392 366 690 1274 638 1180 2156 4 4 24 75 2 210 410 371 700 1292 643 1190 21 3 3 26 78 8 220 428 377 710 1310 649 1200 2192 2 28 82 4 110 230 446 382 720 1328 654 1210 2210 1 1 30 86 0 116 240 664 388 730 1346 660 1220 2228 0 32 89 6 111 250 482 393 740 1364 666 1230 2246 1 34 93 2 127 260 00 399 750 1382 671 1240 2264 2 36 96 8 132 270 518 404 760 1400 677 1250 2282 3 38 100 4 138 280 536 410 770 1418 682 1260 2300 40 104 0 143 290 554 416 780 1436 688 1270 2318 42 107 6 149 300 72 421 790 1454 693
25. 4 LO caution light is on 5 caution light is off 6 OFF flags not in view 7 Pilot s Radar Altimeter Only Periodic audio warning ALTITUDE LOW TOO LOW heard in headsets pilot copilot flight engineer hoist operator C 20 2 54 TROUBLESHOOTING REFERENCE J4 J5 J35 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont 8 Momentarily depress PRESS TO TEST pilot s J36 a 1 Time Volume of the audio warning message decreases by one half b 2 Times Audio warning message is disabled and no longer heard in headsets 9 PRESS TO TEST hold and note NOTE Dial pointer and digital display indications may deviate somewhat farther than 100 feet from the 1 000 foot nominal a OFF flags not in view b Dial pointers 900 1 100 feet c Digital display 900 1 100 feet d LO caution light off e caution light on 2 54 1 C20 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont f Pilots Radar Altimeter Only Periodic audio warning ALTITUDEHIGH CHECK ALTITUDE heard headsets pilot copilot flight engineer hoist operator g Release PRESS TO TEST 10 Check dimming control for proper operation from DIM to BRT a Check digital display dims and goes out b Check LO caution lights dim but do not go out C 20 2 54 2 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Con
26. Both HYD FLT CONTR caution lights do not go out within 30 seconds after POWER XFR switches are set to ON a Faulty APU hydraulic pump motor Check for proper 3 000 psi output b Faulty PTU valve c Faulty solenoid valve d Faulty utility hydraulic isolate relay NO 1 or NO 2 HYD FLT CONTR caution lights are on and maintenance panel indicators show normal pressure Crosscheck evidence of pressure with cor responding AFCS OFF caution lights a Faulty pressure switch b Faulty wiring 3 30 55 1520 240 CONDITION G4 G5 G6 G7 G8 PROBABLE CAUSE NO 1 or NO 2 FLIGHT BOOST caution light on and maintenance panel indicator confirms low pressure rotors turning Faulty flight control pump Check maintenance panel pump and filter lights NO 1 or NO 2 FLIGHT BOOST pressure indicators show a high pressure indication a Faulty pressure transmitter b Faulty flight control pump UTIL HYD SYS caution light on Check utility pressure gage on maintenance panel for pressure in dication Faulty utility hydraulic motor pump if both indicators have low pressure Utility hydraulic system indicator pressure high Check APU start accumulator gage a Faulty utility hydraulic motor pump b Faulty pressure transmitter Fluctuating hydraulic pressure indicator a Faulty indicator b Faulty pressure transmitter c Faulty wiring d Trapped air in the system e Faul
27. ETIS DENSITY ALTITUDE ft AUTOROTATIONAL ROTOR SPEED CHECK TRANSIENT STABILIZED AUTOROTATION FULL DOWN COLLECTIVE PITCH AAS 75 5 Kt RPM Tolerance 2 5 100 225 rpm ROTOR RPM ALIN 0PCc 0cSI SS WL 4 9 c 9c s S c9c S Sco f j1eq spue 1591 ALTITUDE FEET 14000 eee eae eee eee E SS eee Ree eRe eee See ee LII ee 0 LLL DOM PON TT tere 77 E a HSN TORQUE EXCEEDANGE K NN 50 45 40 35 30 25 20 15 10 5 5 10 15 20 25 30 35 40 45 50 E C 13000 12000 11000 10000 9000 8000 7000 6000 5000 4000 3000 2000 1000 ALIN 0PC 0cSI SS WNL ULIA 8729 5 272790 lt Sco S CE S TR ENGINE TORQUE AT 100 NR snon 1591 BENE M MAXI CONTINUOUS F POWER 700 A NR Esp ee He sn I BR Er LT Peet 120 110 100 90 80 70 50 40 30 20 10 0
28. Faulty wiring d AC electrical failure 3 9 55 1520 240 TROUBLESHOOTING GUIDE C ELECTRICAL CONDITION C1 C2 C3 C4 C5 PROBABLE CAUSE No DC power supplied with BATT switch ON a Battery disconnected b Faulty battery c Faulty battery relay d Faulty battery switch Cockpit dome lights inoperative a Circuit breaker out b Faulty lamps c Faulty switch d Faulty wiring Cockpit dome lights will not dim a Faulty rheostat b Faulty wiring Cockpit white dome lights only inoperative a Faulty lamps b Faulty light selector switch c Faulty wiring Utility lights inoperative a Circuit breaker out b Fault light assembly c Faulty wiring 55 1520 240 CONDITION PROBABLE CAUSE C6 Instrument floodlights inoperative a Circuit breaker out b Faulty lamps c Faulty instrument floodlight switch d Faulty wiring C7 Jump lights and troop alarm inoperative a Circuit breaker s out b Faulty jump light relay c Faulty wiring d Jump light lamps burned out C8 Troop alarm bells inoperative a Circuit breaker out b Faulty alarm bell switch c Faulty wiring d Faulty alarm bell C9 Cabin and ramp lights inoperative a Circuit breaker out b Faulty cabin light relay c Faulty switch d Faulty wiring e No power to switched battery bus C10 Cabin and ramp lights inoperative in red a Faulty switch 3 11 55
29. HYDRAULIC TEMPERATURE RED RADIAL 120 C YELLOW ARC 95 TO 120 C 2 32 1 2 32 2 blank C25 55 1520 240 TROUBLESHOOTING PROCEDURE BEFORE STARTING ENGINES Cont 2 22 23 24 25 26 27 28 29 Deleted VGI switches NORM Deleted CYCLIC TRIM switch AUTO AFCS SYSTEM SEL switch OFF EMERG ENG TRIM switches AUTO covers down Avionics equipment Set as required SWIVEL switch LOCK HEAD UP DISPLAY Check opera tion as required Refer to Section IV STARTING ENGINES 1 Personal equipment Check 1 1 BATT switch ON Check 2 SYS MAL caution light out and the following caution panel lights on XMSN OIL PRESS L FUEL PRESS R FUEL PRESS XMSN AUX OIL PRESS NO 1 RECT OFF NO 2 RECT OFF NO 1 GEN Off NO 2 GEN OFF NO 1 HYD FLT CONTR NO 2 HYD FLT CONTR UTIL HYD SYS NO 1 AFCS OFF NO 2 AFCS Off FADEC 1 FA DEC 2 Interphone Check all stations 2 33 REFERENCE CIITH C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 3 MASTER CAUTION LIGHTS TEST 2102 switch TEST Check that all cau tion capsules and the two MASTER CAUTION lights on the instrument panel come on MASTER CAUTION Light PUSH TO RESET check both lights extin guish 31 Clocks Running Set as required 3 2 RAMI EMERG ENG TRIM switches INC for 3 seconds DECR for 6 seconds Check
30. O 22 EAPS 1 and EAPS 2 FAN switches 23 23 1 24 OFF POWER XFR NO 1 and NO 2 switches OFF B U PWR OFF APU GEN switch OFF after rotors have stopped 25 APU START switch OFF The apu 26 27 28 29 30 may be shut down when there is no further need to motor the engines Light switches OFF BATT switch Off Ignition lock switch OFF key re moved as required EMERGENCY POWER panel Check flag indicators for tripped posi tion and log time readings Before leaving helicopter check the following a Fluid levels b Bypass indicators and filter but tons c Jam indicators d Cabin and mission equipment se cured e Tiedowns grounding cables and covers 2 89 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE SHUTDOWN Cont 3 Check Sheet Signed 32 entries from Remarks column of Check Sheet Transcribed to DA Form 2428 13 and complete DA Form 2408 12 33 Maintenance Personnel Debriefed as necessary C25 2 90 55 1520 240 SECTION TROUBLESHOOTING General This section contains troubleshooting information that has been referenced Section TT bhecklists This section shall list possible conditions abnormal conditions and in dications and probable causes The information is to be used only as a quick reference and may not be all encompassing 3 1 55 1520 240
31. d Faulty fuel system C33 Heater inoperative blower operates Circuit breaker out Faulty air pressure switch Faulty ignition system igniters Faulty fuel system Faulty heater control switch C34 Blower stops when heater is turned off Faulty blower overrun switch No combustion in heater C35 PRESS TO TEST light inoperative Circuit breaker out Faulty bulb Faulty wiring C36 Bypass door opens but light is off Limit switch out of adjustment c e Limit switch is defective Faulty bulb Faulty wiring C37 Bypass doors will not open o Faulty actuator Limit switch shorted out oc Faulty wiring 3 17 C17 55 1520 240 CONDITION PROBABLE CAUSE C38 Ramp ramp door does not open using RAMP EMER switch a Circuit breaker out b Faulty down solenoid on ramp control valve c Faulty wiring d Faulty RAMP EMER switch C39 Ramp ramp door does not close using RAMP EMER switch a Circuit breaker out b Faulty up solenoid on ramp control valve c Faulty wiring d Faulty RAMP EMER switch C22 3 18 TM 55 1520 240 MTF TROUBLESHOOTING GUIDE D CAUTION PANEL CONDITION D1 D2 D3 04 PROBABLE CAUSE MASTER CAUTION panel lights inoperative a BATT switch OFF b Caution lights circuit breaker out c Faulty caution panel d Faulty wiring MASTER CAUTION lights do not come on when TEST switch is pre
32. 1520 240 CONDITION C11 PROBABLE CAUSE b Lamps burned out c Faulty relay d Faulty wiring No power to essential bus a ESSEN BUS FEEDER circuit breaker out b Faulty battery switch c Faulty essential bus relay d Faulty wiring C12 Engine emergency beep inoperative C13 C14 EMERG ENG TRIM circuit breaker out a b Faulty actuator o Faulty emergency trim relay Faulty switch e Faulty wiring Generator will not come on line a Faulty control unit b Faulty generator c Faulty wiring Windshield anti ice system inoperative a Faulty control switch b Faulty control relay c Faulty anti icing controller d Faulty sensing element 3 12 55 1520 240 CONDITION C15 C16 C17 PROBABLE CAUSE e Faulty heating element f Windshield anti ice ac or dc circuit breaker out g Faulty wiring Windshield anti ice system continues to operate above 45 C a Faulty anti icing relay b Faulty anti icing controller c Faulty sensing element No pitot and or sideslip port heat a Static port heater circuit breaker out b Faulty switch c Faulty heating elements d Faulty wiring Pilot s and or copilot s searchlight will not come on a Searchlight circuit breaker out o Faulty lamp o Faulty SLT FIL switch d Faulty searchlight unit e Faulty wiring C18 Pilot s and or copilot s searchlight will
33. 2 88 5p 2 88 1 2 88 2 blank 3 46 3 and 3 46 4 3 46 3 and 3 46 4 3 46 5 through 3 46 9 3 46 10 blank 2 Retain this sheet in front of manual for reference purposes 55 1520 240 24 By Order of the Secretary of the Army DENNIS J REIMER General United States Army Chief of Staff Official JOEL B HUDSON Administrative Assistant to the Secretary of the Army 051400 DISTRIBUTION To be distributed in accordance with Initial Distribution Number IDN 310195 requirements for TM 55 1520 240 MTF 55 1520 240 23 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 23 WASHINGTON D C 16 October 1998 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH47D HELICOPTER DISTRIBUTION STATEMENT A Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 9 and 2 10 2 9 and 2 10 2 10 1 2 10 2 blank 2 Retain this sheet in front of manual for reference purposes 55 1520 240 23 Order of the Secretary of the Army DENNIS J REIMER General United States Army Chief of Staff Official B HUDSON Administrative Assistant to the Secretary of the Army
34. 3 Fly from CP 4 to CP 1 at minimum safe speed greater than 20 knots of the helicopter Record the displayed present position coordinates at CP 1 3 Maximum cross track error is 5 of the distance of the leg Maximum error along the track is 296 of the distance of the leg C 20 2 84 TROUBLESHOOTING REFERENCE 55 1520 240 PROCEDURE INFLIGHT Cont GPS Doppler Flight Test Procedure 1 Verify proper system operation with MODE switch to TEST and display line 1 indicating TEST COMPLETE and line 2 TEST OK 2 Verify proper response of CDU panel lighting to aircraft dimmer control and Display lighting to CDU BRT control Adjust to comfortable level 3 Perform GPS system Start Up procedure Ensure four 4 satellite measurements SAT are being used and estimated position error EPE is 50 meters or less with keys loaded or 200 meters or less with a cold start 4 Fly helicopter over surveyed test course consisting of two 2 waypoints used as checkpoints CP a minimum of 20KM apart b To minimize errors in establishing positions over the checkpoints CP the altitude shall be the lowest compatible with safety standards 2 84 1 TROUBLESHOOTING REFERENCE J26 J27 J29 J30 J28 J31 J33 J34 C20 55 1520 240 PROCEDURE IN FLIGHT Cont 6 If checkpoint CP information was not entered through the data loader during Start Up with the Mode switch set to NAV enter
35. 5 MAIN FUEL VALVE SIGNAL OUT 147 START FUEL VALVE amp EXCITER SIGNAL OFF 704 90 RPM READY FON SERVICE PROCESSOR BOARD FAILURE SENSOR DATA FAILURE OVERTEMPERA TURE OVERSPEED UNDEHSPEED FAILURE START LOSS OF SPEED DATA SUORTED THERMOCOUPLE PROBE WARNING OPEN THERMOCOUPLE PROCESSOR SEQUENCE FAIL NO TEMP DATA 90 1 5 SEC START OPERATION SEQUENCE 0143 3 ALIN OV2 02S1 SS 55 1520 240 CONDITION A5 A6 AT PROBABLE CAUSE b Faulty starter motor Faulty utility hydraulic system d Compressor binding High PTIT during starting a Incorrect start procedures Advancing ECL to GROUND before 1096 N1 is indicated b Air inlet obstructed FOD c Faulty indicating system d Low starter motor speed e Start fuel solenoid valve stuck open f Excess fuel not purged following aborted start Engine will not accelerate to ground idle within 46 seconds a N1 actuator misrigged b Ground idle screw out of adjustment c P 3 air line clogged or disconnected Flameout Engine starts quits and N1 falls Check if fuel PRESS caution lights on a Main fuel valve closed b Main fuel line quick disconnect not connected tightly c Main fuel line restricted d Faulty fuel control 3 4 55 1520 240 CONDITION PROBABLE CAUSE APU precharge pressure cannot be incressed to 3 000 psi when require
36. Be careful when feeling bellcranks and idlers for vi bration Personnel can have fingers caught between bellcranks and idlers if care is not used 2 Listen for cracking or squeaking sounds Carefully feel bellcranks and idlers for vibration d Disconnect the links at the walking beams and idlers that may be binding Refer to TM 55 1520 240 23 Ch 11 1 Move the walking beam and idler by hand Feel for binding and roughness NOTE Disconnecting the links and moving the walking beam and idler by hand is the most accurate method of locating a binding component 2 if binding or roughness is found have the walk ing beam or idler bearings cleaned and lubricated 3 If necessary have the walking beam or idler re placed e Attach the connecting links to the walking beams and idler Refer to TM 55 1520 240 23 Ch 11 4 9 55 1520 240 Make sure area is clear of foreign objects before closing tunnel covers If not damage to components or systems could result in personal injury or death f Shut down ac and hydraulic power Pickup tools and clean area Close tunnel covers 2 Looseness Check Tolerances The following tolerances apply to the looseness check a Bearings with radial looseness in excess of 0 007 inch must be replaced b If each bearing in a series of hearings has less than 0 007 inch radial looseness but overall system looseness is in excess of 3 8 inch all or a portion of thes
37. DGNS memory NOTE Zeroize at termination of test flight or so dictated by operations Aircraft power must be connected or power applied to aircraft 1 Lift zeroize switch guard and toggle switch 2 Release toggle switch and close switch guard 16 Miscellaneous a Vertical velocity indicators b Turn and slip indicators c Pressure altimeters 1 Pilot and copilot difference 100 0 500 ft 150 1000 2000 ft 200 2000 4000 ft 300 4000 8000 ft 350 8000 10 000 ft 2 No pointer sticking at any altitude Change 24 2 84 11 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont q HF Radio AN ARC 220 COMSEC KY 100 1 AN ARC 220 Function J52 53 54 55 switch T R Mode switch PRE and Channel selector Appropriate preset 1 20 containing a frequency to transmit receive in USB 2 KY 100 Mode switch PT Preset Desired posi tion for plaintext operation Plaintext beeps are heard when system is idle or receiving 3 Transmit Receive and J57 58 evaluate communications through out a 360 degree turn J56 4 Repeat the process with ARC 220 operating on LSB and CW J59 5 KY 100 Mode switch CT Preset Desired position for ciphertext operation 158 6 Transmit Receive with ARC 220 in USB LSB AME or CW 7 ARC 220 Mode 160 61 switch ALE SQL switch 0 or 1 2 84 12 Change 24 55 1520 240 TROUBLESHOOTING PROCEDUR
38. ENG COND levers STOP F b DECU display Check for a 88 display 2 87 C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE SHUTDOWN Cont NOTE If DECU display is other than 88 ad vance respective ENG COND lever to GND without starting engines If 88 is displayed then a nuisance fault has been verified If other than 88 is displayed refer to maintenance 18 REFUEL STA switch As required 19 AVIONICS Set as required then J64 OFF a HF Radio AN ARC 220 J65 ZEROIZE then OFF ZEROIZED advisory is displayed b TSEC KY 100 ZEROIZE ZEROED advisory appears on display and a momentary tone is heard in headset 20 Radar altimeters OFF NOTE Record any tripped indicators before set ting GND TEST switch to TEST or RESET 21 Maintenance Panel Check for tripped indicators and lit PUMP FAULT or FILTER CHANGE lights GND TEST switch TEST then RESET Check indicators for proper operation FILTER CHANGE and PUMP FAULT lights PRESS TO TEST Flight Engineer C25 2 88 55 1520 240 TROUBLESHOOTING PROCEDURE ENGINE SHUTDOWN Cont CAUTION The flight controls must be at neutral and the thrust control at ground de tent prior to removal of hydraulic pressure for any reason Flight control positions other than neutral or ground detent may cause damage to the pitch control first stage mixing unit connect ing link in the forward pylon
39. ENG START switch Select first engine to be started and hold until accelerates to 10 Release switch 1 Check and record engine oil pres sure 5 PSI minimum C25 4 14 2 55 1520 240 Reference TM 55 1520 240 23 Cont TROUBLESHOOTING PROCEDURE REFERENCE 2 Check and record engine accelera tion speed to ground idle 50 to 59 within 45 sec CAUTION If no oil pressure is indicated during the starting sequence shut down engine and investigate 2 FADEC switch of engine started PRI 3 Second engine Start by using the same method as the first G 4 POWER ASSURANCE TEST CAUTION Do not exceed 899 C Time in exceedance of 899 degrees C will be recorded by the FADEC N1 111 Vne 149 kts TQ 123 1 Maximum Continuous Power Test a b Stabilize airspeed at 120 kts with RRPM 100 Pilot s altimeter set to 29 92 Select an altitude FAT combination from figure 5 12 4 Refer to Section V that provides the highest practical torque while observing the appli cable transmission limits Determine required minimum TQ from figurd Refer t ENG COND lever of engine not being checked Slowly retard towards GND Ensure that ENG PTIT for engine being checked does not exceed 806 degrees If PTIT of 806 degrees is reached prior to required minimum TQ being attained terminate the PA Test on this engine and proceed to step j 4 14 3 C25
40. Either AFCS OFF caution light does not go out within 20 seconds a Dash actuator failure b Associated AFCS unit failure c Proximity switch failure U S GOVERNMENT PRINTING OFFICE 1994 655 121 20003 C19 3 38 PIN 051400 019 55 1520 240 TROUBLESHOOTING GUIDE VIBRATIONS CONDITION 11 14 15 PROBABLE CAUSE 1 Rev vertical vibration a Blades out of track b Pitch link bearing worn c Loose or binding horizontal pin bearing d Faulty blade 1 Rev lateral vibration a Unbalanced condition caused by combination of new and eroded blades b Blades out of track aft c Unbalanced condition in rotor system d Vibrex weights incorrect 3 Rev vibration a Feedback from upper boost actuators only if bearings are loose b Excessive looseness in rod end bearings C Loose heavy dynamic component such as forward transmission aft vertical shaft combining trans mission or rotary wing heads Excessive 3 rev vibrations a STVA circuit breaker out b Faulty STVA system High frequerncy vibration a Faulty flight boost pump b Faulty generator 3 39 55 1520 240 WIF CONDITION PROBABLE CAUSE c Faulty transmission cooler fan d Faulty sync shaft hanger bearings 16 High frequency engine drive shaft area vibration a Engine drive shaft spline worn frozen or improperly lubricated b Faulty ttgine mounts c Combining transmission inpu
41. Hydraulic Troubleshooting Flight Controls Troubleshooting Vibrations Troubleshooting Communications Navigation Equipment Troubleshooting AFCS and Cyclic Trim Special Procedures A AFCS Bite Checks B Self Tuning Absorber Systems Check Control Breakout Forces Winch Operational Test Looseness Check Rotor Phasing No 1 and No 2 Engine Start Interstage Air Bleed Speed Adjustment for 55 1 712 AFCS Check J Heating Vent Blower Operation K Cargo Hook Operational Check C22 ii PAGE oo Co 1 1 1 1 _ 1 e D D 6 a5 BRE AS a COIN 55 1520 240 TABLE CONTENTS Continued SECTION Special Procedures Continued L Strobex Vibrex Tracking Procedure M Engine Vibration Check Turbine Engine Analysis Check teac 4 25 O Deleted P Deleted Q Differential Current Protection Circuit Check R Cargo Ramp and Door Check S Heads Up Display HUD Check V Charts and Forms NUMBER 8 ce m e mm Ree N IAI ol MNI E LIST OF ILLUSTRATIONS TITLE Test Course for Overland Doppler Accuracy Decoded APU Bite Information Temperature Conversion Chart Airspeed Operating Limits Inoperative CGI Airspeed Operating Limits Retracted LCT APU Start Accumulator Precharge Limits Flight Utility Power Stee
42. Symbolized Checks The procedures include items that may be checked by the flight engineer and that mayor may not be installed These items are annotated immediately preceding the check to which they are pertinent F for flight engineer and O to indicate a requirement if the equipment is installed Symbols preceding Numbered Steps F Indicates flight engineer function or response O Indicates If Installed 1 3 1 4 blank C17 55 1520 240 MTF SECTION Il MAINTENANCE TEST FLIGHT CHECKLIST General This section contains the maintenance test flight re quirements peculiar to Army Model CH 47D aircraft Condi tions requiring accomplishment of test flights shall be in ac cordance with TM 55 1500 328 25 The requirements contained herein are established to assure a thorough inspe tion of the aircraft before flight during flight and upon com pletion of the maintenance test flight The right side of the checklist Troubleshooting Reference is cross indexed to the troubleshooting guides contained dash between references means through a comma means The references list the possible abnormal conditions indica tions or malfunctions which could be ncountered while performing the procedure 2 1 55 1520 240 TROUBLESHOOTING PROCEDURE PRIOR TO MAINTENANCE TEST FLIGHT Before Interior Check Publications Check DA Forms 2408 12 13 14 18 DD For
43. TRIM switch CAUTION While performing this check do not exceed the following limits a PTIT 890 b N1 105 Airspeed 140 5 d Torque 12396 8 Continue increasing thrust and increasing NO 1 amp NO 2 ENGINE BEEP TRIM switch until gas producer N1 speed for engine being TEACed stabilizes at maximum and rotor rpm falls to 98 percent Maintain N 1 and 98 percent rotor rpm using thrust control and NO 1 amp NO 2 ENGINE BEEP TRIM switch 9 Stabilize the rotor speed at 98 percent then record the following a b e f N1 Deleted Free air temperature FAT Power turbine inlet temperature PITT Torque Pressure altitude 10 Determine Engine Trim 4 28 C16 55 1520 240 Below 5 C FAT it may be impossible to per form a TEAC below 10 000 feet pressure al titude Under these conditions enter a red dash in the aircraft forms and accomplish the TEAC when conditions permit O 4 Be sure the ENG ANTI ICE switch is OFF 5 Using NO 1 amp NO 2 ENGINE BEEP TRIM set rotor speed to 100 percent If during the check it becomes necessary to reduce engine power initially reduce power by operating the No 1 amp 2 ENGINE BEEP TRIM switch until rotor speed begins to decrease Then lower thrust Do not lower thrust until rotor rpm begins to decrease or an engine over speed may occur Also to prevent tripping the indicator and starting the timer do not allow
44. Zero 50 psi flight en gineer response c MASTER CAUTION D3 light On then RESET d With slow smooth flight H3 5 control inputs check each axis individual ly through full range of travel for smooth ness of operation 2 FLT CONTR HYDRAULIC G13 switch BOTH a FLT CONTR HYDRAULIC G3 G4 PRESSURE Check normal operating range flight engineer gt response b NO 2 HYD FLT CONTR D8 caution light Out 3 FLT CONTR HYDRAULIC switch to NO 2 ON Check as follows a NO 1 HYD FLT CONTR D7 G12 caution light On TM 55 1520 240 MTF PROCEDURE TROUBLESHOOTING REFERENCE STARTING ENGINES Cont b FLT CONTR NO 1 PRES G3 SURE Indicator Zero 50 psi flight en gineer response c MASTER CAUTION D3 light Check on then RESET d With slow smooth flight H3 5 control inputs check each axis individual ly through full range of travel for smooth ness of operation 4 FLT CONTR HYDRAULIC G4 G13 switch BOTH a NO 1 HYD FLT CONTR D8 caution light Out NOTE The flight engineer shall observe No 2 system returns to normal operating pressure as No 1 pressure drops below approximately 2000 psi The same is true for No 1 System when No 2 drops below 2000 psi 9 Control interlock Simulate failure of the NO and then NO 2 hydraulic boost systems by the following 1 FLT CONTR HYDRAULIC G13 switch NO 1 ON 1 1 POWER XFR NO Check NO HYD FLT CONTR caution light ou
45. aft hook and AFT HOOK caution lights as follows a Turn the HOOK SELECT switch to AFT b Repeat steps 11 d thru 11 r for aft hook operation 14 Check normal operation of forward and aft hooks in tandem and the forward and aft hook caution lights as follows a turn the HOOK SELECT switch to TANDEM b Check DUAL HOOK FAULT caution light OUT c Repeat steps 11 d thru 11 r for forward and aft hook operation 15 Check normal operation of all hooks and caution lights as follows a Turn the HOOK SELECT switch to ALL b Check DUAL HOOK FAULT caution light OUT c Repeat steps 11 d thru 11 r for operation of all hooks 4 20 TM 55 1520 240 MTF 16 Check the cockpit cargo book emergency release as follows a Check that the pressure gage on the center hook indi cates 2 100 psi b Check DUAL HOOK FAULT caution light OUT c Set the CARGO HOOK MASTER switch to OFF c Set the HOOK SELECT switch to ALL d Check DUAL HOOK FAULT caution light OUT e Note the position of the second hand on the clock Mo mentarily set the guarded EMERG REL ALL switch to REL ALL Check for the following 1 All three hooks open 2 The forward and aft hooks make sounds like a machine gun for about 12 seconds 3 Check that all hooks are closed after ap proximately 12 seconds 4 Check that the three HOOK OPEN caution lights light and the MID HOOK OPEN light goes out after approx 12 seconds b Ch
46. altitude check 1 Verify that the radar altitude AGL numeric on the DU matches the radar altitude displayed on the AN APN 209 0 1000 feet 2 Ply aircraft at 2000 feet AGL Verify that the barometric altitude MSL on the DU matches the barometric altitude displayed on the AIMS altimeter Various altitude levels may be chosen during flight and verify the DU barometric altitude matches what is displayed on the AIMS altimeter d Roll pitch and yaw check 1 Verify that the horizon line angle of roll scale and angle of pitch scale is present on the DU 2 Roll helicopter 20 to the left and verify the hori zon line and the angle of roll pointer on the DU indicate a 20 roll to the left Roll the helicopter 35 to the left and verify the horizon line indicates a greater roll to the left than before and the angle of roll pointer freezes at 30 and flashes Repeat for roll angles of 20 and 35 to the right 3 Pitch helicopter 10 up and verify the horizon line on the DU indicates a 10 pitch up Pitch helicopter 35 up If a 35 pitch angle exceeds safe operating limits pitch the aircraft to the maximum safe pitch limit instead Verify the horizon line on the DU corresponds to the actual pitch angle of the helicopter and the bottom tic mark flashes if the pitch angle exceeds 30 Repeat for similar downward pitch angles noting the top tic mark will flash for downward pitch angles of greater than 30 4 39 C22
47. and engines are operating a Circuit breaker out b Lamps burned out c Faulty caution panel d Faulty pressure switches e Faulty wiring D17 PWR STEER caution light comes on when wheel is in normal travel range a Faulty out of phase switch b Faulty caution panel c Failure in control system 3 21 55 1520 240 CONDITION D18 D19 D20 PROBABLE CAUSE NO 1 AFCS OFF and or NO 2 AFCS OFF caution lights do not go out with AFCS emgaged a Circuit breaker out AC DC b Faulty caution panel c Faulty flight boost pressure switch d Faulty AFCS computer NO 1 AFCS OFF caution light does not come on when selector switch is set in NO 2 ON pisition a Faulty caution panel capsule b Faulty selector switch c AFCS unit disconnected or faulty NO 1 AFCS OFF or NO 2 AFCS OFF caution light on wish AFCS selector switch in BOTH a Faulty flight boost system below 2000 psi b Faulty flight boost pressure switch c Faulty AFCS computer d Faulty caution panel D21 NO 2 AFCS OFF caution light does not come on when selector switch is set in NO 1 ON position a Faulty caution panel capsule b Faulty selector switch c AFCS computer disconnected or faulty 3 22 55 1520 240 TROUBLESHOOTING GUIDE E POWERPLANT CONDITION E1 E2 E3 E4 E5 PROBABLE CAUSE No engine oil pressure a b d e Circuit br
48. be considered as a require ment for readjustment NOTE NO 1 amp NO 2 ENGINE BEEP TRIM switch INCREASE then DECREASE if adjustments are made d NO 2 ENGINE CONDITION le ver FLIGHT NO 1 ENGINE CONDITION le ver GROUND Check NO 2 ENGINE for 91 94 rotor rpm and record data f NO 1 ENGINE CONDITION le ver FLIGHT 45 NO 1 amp NO 2 ENGINE BEEPTRIM switch 100 rotor rpm 56 Bleed Band Check See Seal ENGINE RUN UP VGI switches As required C25 2 48 REFERENCE 12 131 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont CAUTION If the heater is operating set the HEATER switch to VENT BLOWER ONLY and allow two minutes for the heater to purge This procedure will prevent a possible heater fire when generator power is lost in the following tests 1 4 HEATER switch Off Allow 2 minutes with HEATER switch in VENT BLOWER ONLY if heater has been in operation 2 Generators Check operation a Generator rectifier crosstie opera tion Check as follows 1 NO 1 GEN switch OFF CT3 D15 Check the NO 1 GEN OFF caution light comes on and the NO 1 RECT OFF caution light remains off NO 1 GEN switch TEST Check that the NO 1 GEN OFF caution light goes out NO 1 GEN switch ON Check that the NO 1 GEN Off caution light is out 2 Repeat step 1 for NO 2 GEN b Under frequency cutoff Chec
49. c Check both DECU displays read F 88 If other than 88 on either DECU then refer to DECU Fault Codes in Section IV for evaluation d Fire guard Posted Rotor blades clear e ENG START switch to 1 until N1 reaches 1046 and release f Prior to completion of start se quence 48 place ENG 1 ECL to STOP g Verify start was aborted and check for leaks h Repeat for ENG 2 NOTE Abort start if not normal Wait at least 15 seconds after N1 reaches zero before attempting another start This will allow time for fuel to drain out of the combus tion chamber i DECU Ensure reset to 88 34 Starting Engines Engine start Primary Mode See Section IV a Record ENG OIL PRESS and GND idle speed after 45 seconds for each engine b Check XMSN AUX OIL PRESS light out 2 46 1 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont c During rotor acceleration Check XMSN OIL PRESS caution light out at approximately 20 psi CAUTION Operation at NR RRPM below 45 is to he minimized Do notrelease the FADEC OSPD Switch until the associated ECL has been moved to STOP Excessively high engine tem perature may be generated Ensure that the No 1 engine is restarted before performing the overspeed check on the No 2 engine to allow flight engi neer to verify that the droop stops are engaged prior to shut down of both en gines
50. condition and security 10 Fwd aux fuel tank Check as required and security 11 fuel vent Check clear and fairing secure 2 21 C6 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Right Cabin Cont 12 Fwd ux fuel tank electrical connections and fuel line Check condition and security 13 Pressure refueling station Check as follows a PWR and LT switches OFF b All TEST switches PRI OFF C Refueling receptacle cover installed retainer wire condition and secure d PRESS REFUELING INSTRUCTIONS on panel Check condition e Landing gear support structure Check for cracks and distortion f Landing gear and pressure refueling panel cover Check posi tion light closed and secure 13 1 Static port Check clear 14 Forward landing gear Check as follows a Tires for inflation and con dition b Shock strut for extension and cleanliness c Hoses and wheel brakes for leakage chafing and security 15 Right lelectrical compart ment Check as follows a GEN CT FAULT bite Check all black 2 22 C6 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Right Cabin Cont b Transformer rectifier Check condition and security No 2 minimum beep resistor Check condition and security d Access door Check condition and security 16 Deleted Forward Cabin 1 Heater intake exhaus
51. er es dep E Tas etc wee uw 806 56 E op eme re prex ec X popu wen E E dug esp xs qr ee EE s dal 900 860 820 780 740 700 50 40 30 20 10 0 10 20 30 40 50 660 0 lt 1 66 ULI pr c9csy Erc9cs Sco N I poods sex 1594 zA Ny GENERATOR SPEED 90 PEDES EET I Ee aer ur Eius ng ee KERR ERE EE 114 110 106 102 94 50 40 30 20 10 0 10 20 30 40 50 FAT C 0 61 66 WL ULI 9rc9c s src9cs Sco wey UOISIZAUOD UIEN 1591 lt 671 PAT Number Margin Sea Level p M 10 000 ft EJ a ad 8 7 6 5 4 CH 47D T5
52. for actuator opera tion Flight engineer response 4 TROOP ALARM and JUMP LIGHTS Check operation a TROOP ALARM switch ON the alarm should sound then OFF b TROOP JUMP LTS PRESS TO TEST 1 Select RED 2 Select Green c CABIN AND RAMP LIGHTS Check then ALL OFF Check cabin jump lights go to dim bright then Off d CAUTION LIGHTS DIM Check MASTER CAUTION panel and TROOP JUMP LTS on over head panel go dim INTERIM dB NVG e TROOP JUMP LTS Off 5 Dome lights Check a Deleted C25 2 34 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE b DOME SELECT NVG or RED then WHITE Check caution lights on bright c DOME LIGHTS rheo stat Check intensity varies DIM through BRT INTERIM NVG d DOME SELECT OFF 6 Floodlights NVG Check FLOOD LTS rotary control switches ON b FLOOD LTS selection switches on INST PNL OVHD PNL ON c Check following lights on 1 6 under glareshield i 2 2 on overhead bulkhead sta 95 d FLOOD LTS rotary con trol switches OFF e FLOOD LTS selection switches OFF 6 1 Emergency Floodlights CGY C23j C24 Check as follows a Pilots FLT INST LTS rotary control switch ON b Check 6 emergency lights under glareshield and 2 on overhead bulkhead are on c Pilot s FLT INST LTS rotary control switch OFF 2 35 C6 55 1520 240 TROUBLESHOOTING PROC
53. individual tank in dications coincide with known consents b Note digital readout remains constant during indi vidual tank readings c Select TOTAL Check pointer rotates behind mask Check total fuel indicated is within 420 pounds of known fuel on board 27 CYCLIC TRIM Indica tors Check both in GND posi tion 28 CYCLIC TRIM switch MANUAL a Check for proper operation and indicator movement by first retracting thc FWD then AFT ac tuator into thc RET position 2 41 Change 2 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont b Check actuators by fully extending the FWD then AFT ac tuator into the EXT range on the indicator Full RET to full EXT not to exceed 25 seconds c CYCLIC TRIM switch AUTO Observe both in dicators move from the full EXT position to the GND position 29 Rotor Blades Check posi tion CAUTION Prior to performing the static flight control check be sure that an aft rotor blade is not within 30 of the centerline of the fuselage since blade fuselage interference may occur In addition the rotor blades may rotate due to wind or APU operation 29 1 AFCS Check Section IV Not required if mechanical rig check is to be performed 30 Flight control travel and hy draulics Check a Control Interference 1 Both sets of pedals full aft Pilot and copilot pedal adjustment lever may contact the cockpit f
54. is at mid position then STOP Check that ramp moves to mid position and stops with cargo door fully ex tended 4 33 C22 TM 55 1520 240 MTF 26 Release knob on door override valve Check that cargo door retracts fully into ramp 27 RAMP CONTROL VALVE handle UP Check that ramp and cargo door move to the fully closed position in the proper sequence described above 28 RAMP CONTROL VALVE handle STOP 29 RAMP EMER switch on overhead panel Lift guard and move switch to the DN position momentarily then release switch Check that switch returns to the HOLD position when released Check that ramp does not move when switch is in the DN position 30 RAMP PWR switch on overhead panel EMERG Check that RAMP CONTROL VALVE handle is resistant to manual movement and returns to the STOP position if moved to either the UP or DN positions 31 RAMP EMER switch on overhead panel DN mo mentarily then release Check for the following a RAMP CONTROL VALVE handle moves to the DN position b Ramp and cargo door open and move downward in the proper sequence for approximately 5 seconds then stop c RAMP CONTROL VALVE handle returns to the STOP position 32 RAMP EMER switch on overhead panel DN mo mentarily then immediately to UP momentarily then release to HOLD Check for the following a RAMP CONTROL VALVE handle moves to DN then UP then STOP b Ramp moves downward momentarily then stops in le
55. not extend retract or rotate right or left a Searchlight circuit breaker out b Faulty searchlight control switch c Faulty pilot or copilot SLT cont switch 3 13 TM 55 1520 240 MTF CONDITION PROBABLE CAUSE d Faulty searchlight unit e Faulty wiring C19 Top and or bottom anticollision lights will not come on a Circuit breaker out b Faulty switch c Faulty light assembly s d Faulty wiring C20 Position and or formation lights inoperative a Circuit breaker out b Faulty switch c Faulty wiring d Lamps burned out C21 Position and or formation lights will not dim a Faulty switch b Faulty dimming resistor c Faulty wiring C22 Instrument lights inoperative a Circuit breaker out b Faulty rheostat c Faulty dimming rheostat d Faulty wiring 55 1520 240 CONDITION PROBABLE CAUSE C23 Instrument lights will bot brighten a Faulty rheostat b Dimming rheostat out of adjustment C24 No emergency floodlights when generator control and battery switches are off a Pilot s instrument light rheostat off b Secondary cockpit lights circuit breaker out c Faulty floodlight relay d Faulty wiring C25 Fire warning lights do not come on when tested C26 C27 a Burned out lamps b Faulty press to test switch e Circuit breaker s out d Faulty control unit e Faulty detection element f Faulty wiring Main fuel valve does not c
56. of the Army GORDON R SULLIVAN General United States Army Official Chief of Staff A blr MILTON H HAMILTON Administrative Assistant to the Secretary of the Army 07301 DISTRIBUTION To be distributed in accordance with DA Form 12 31 E block no 0195 requirements for TM 55 1520 240 MTF 55 1520 240 C 17 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 17 WASHINGTON D C 18 January 1994 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT public release distribution Approved for is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin illustration change is indicated by a miniature pointing hand Remove pages i and ii 1 3 1 4 blank 2 7 2 8 2 11 2 12 through 2 30 2 37 2 38 2 38 1 2 38 2 2 45 2 46 2 49 2 50 2 87 2 88 3 17 3 18 blank Insert pages i and ii 1 3 1 4 blank 2 7 and 2 8 1 and 2 12 2 1 2 12 2 blank 3 through 2 16 6 1 2 16 2 blank 6 1 2 26 2 blank 7 through 2 30 7 and 2 38 8 1 2 38 2 blank 5 and 2 46 6 1 2 46 2 blank 49 and 2 50 87 and 2 88 17 and 3 18 Qo IO IO IO IO PO PO IO 55 1520 240 17 2 Retain this sheet in front of manual for reference purpose
57. on the digital dis play and press the bite switch to proceed with the test When the test is completed the bite will shut down Refer to TM 55 1520 240 24 for the recommended maintenance actions for the failures detected There are programmed failures at bite test numbers 6 and 18 of system No 1 Results of bite test numbers 7 and 47 shall be disregarded 4 BITE numerical test numbers correspond to the malfunc tions as follows BITE TEST TABLE TEST NO MALFUNCTION 0 69 AFCS UNIT 70 74 PITCH ILCA 75 79 YAW ILCA 80 84 ROLL ILCA 85 86 DASH ACTUATOR 87 88 CCDA ACTUATOR 89 90 LONG CPT 91 92 PEDAL CPT 93 94 LATERAL CPT 95 96 RADAR ALTIMETER 97 AUTOMATIC STOP B SELF TUNING ABSORBER SYSTEMS CHECK NOTE Perform this test on the ground with the rotors stop ped If the absorbers are tested with the rotors turn ing the absorbers may be damaged 4 3 2 TM 55 1520 240 MTF 1 APU ON 2 APU generator control switch ON 3 Vibration absorber circuit breakers left right and center Pushed in 4 Selector swirco Left 5 Test switch Retract NOTE The meter pointer will move in direction selected Retractor extend The pointer may initially deflect offscale then return to the required average meter deflection and fall to approximately zero in the required time interval for ambient temperature as shown below Hold switch until the meter pointer indicates zero or stabilizes at approximately z
58. pilot valve for proper connec tions condition security leakage and extended jam indicators 27 1 Forward transmission oil level Check 28 Forward transmission Check mount bolts 29 CC I signal conditioner Check electrical connections and security 30 Flight control hydraulic cooler and module Check for extended filter contamination indicators leaks and that accumulator is precharged Section V Check PTU condition and security 31 No 1 Flight control hydraulic reservoir Check level indicator Right Cabin 1 Fuselage skitt Check for dents wrinkles and loose or miss ing rivets 2 Aft aux fuel tank Check as required and cap security 2 20 Change 1 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Right Cabin Cont 3 Fuel vent Check clear and fairing secure 4 Windows Check condition seals and proper installation cracks and cleanliness 5 AFT cargo hooks if in stalled Check the following a Hook properly installed with hook opening pointing for ward b Electrical connector properly installed Dust cap stowed c Emergency release cable properly connected Dust cap stowed d Hook clean and load beam closed Latch roller moves freely 6 Main fuel tank Cheek as re quired and cap security 7 Fuel vent Cheek clear and fairing secure 8 FWD cargo hook if in stalled Cheek as in step 5 above 9 Antennas Check
59. roll attitude The aircraft shall bold this level attitude within 23 2 Operate the roll beep trim switch left and right Roll at titude changes shall correspond to beep action Yaw axis test Check yaw axis response as follows 1 Apply a right pedal di rectional control input of 12 inch Do not operate the magnetic brake switch 2 Hold this input until a beading change of approximately 30 has accurred Return the pedals to trim and do not apply any force to the pedals The aircraft yaw rate shall diminish When the rate baa dropped to approximately 1 9 second a new heading shall he captured 3 Repeat steps 1 and 2 except apply left pedal 2 60 Change 1 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont NOTE The AFCS yaw axis heading hold function is dis abled when the SWIVEL switch is at UNLOCK or STEER 4 Set the SWIVEL switch to UNLOCK and repeat steps 1 thru 3 The air craft should not lock to any heading The heading hold function will be inoperative f Heading bold and bank angle hold cheek in sideward flight Perform as follows 1 SWIVEL switch LOCK 2 Trim to a stable hover Without operating the magnetic brake switch apply a 5 7 bank angle to produce a sideward ve locity Return longitudinal stick to the trim detent The helicopter shall maintain the commanded bank angle and hold its original beading 3 during si
60. slant range to destination line 2 2 04 5 C 20 55 1520 240 PROCEDURE IN FLIGHT Cont 22 With Data switch still set to DIS TG switch to destination mode and fly from CP 2 back to CP 1 While hovering over CP 1 store displayed present position at CP 1 by performing the following Depress the MARK key Press line select key 3 to store coordinates and altitude This will be Mark B Press the Clear key CLR to return to original screen 23 Set Data switch to POS and manually record present position coordinates 24 Set Data switch to DIS TG and manually record distance to CP 2 line two 25 Return to ground station C 20 2 84 6 TROUBLESHOOTING REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 1 GPS Doppler Flight Test Data Analysis Compare all MARK positions with the actual positions of the cor responding Check Point Compare differences if any with Allowable Navigation Error Limits outlined in TM 11 5826 308 12 If errors ex ceed the Allowable Navigation Error Limits use the self test of the GPS system and fault isolation procedures to determine the failure mode Zeroizing loaded keys from GPS memory NOTE e Zeroize at termination of test flight or so dictated by operations Aircraft power must be connected or power ap plied to aircraft 1 Lift zeroize switch guard and toggle switch 2 84 7 C20 55 15
61. switch LOCK Transponder NORMAL Crew and mission equipment Check C12 2 66 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE CRUISE 1 Systems Check normal NOTE Operating the maintenance panel test switch in flight will cause the caution panel lights to go on The flight engineer shall alert the pilot when the test switch is used in flight 2 Ramp area and maintenance panel Check every 30 minutes by flight ngineer IN FLIGHT 1 Fuel Consumption Check Initiate 2 Speed Sweep Check With inoperative do not exceed airspeed limits 5 2 NOTE FWD and AFT LCT schedules corrected for in pressure altitude are shown in Section V a Stabilize airspeed at 50 knots Observe both CYCLIC TRIM indicators are in the 60 knot RET range b Increase and stabilize air speed at 60 knots 1 Record longitudinal stick position 2 Record lateral stick position 3 Record directional pedal separation 2 67 Change 12 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 4 Compare pilot and co J6 pilot airspeed indicators 7 knots maximum difference 3 CYCLIC TRIM Check a Record initial CYLIC B11 K13J TRIM indicator lift off air speed Section V b Increase and stabilize airspeed at 70 knots c Observe that both CYCLIC TRIM indicators have moved out of the RET position
62. the EMERG PWR light to remain on longer than 5 seconds 6 Raise thrust lever slowly 7 Set ENGINE CONDITION LEVER of the engine not being checked to GROUND Maintain 100 percent rotor rpm using NO 1 amp NO 2 ENGINE BEEP TRIM switch 4 27 C14 55 1520 240 While performing this check do not exceed the following limits a Ptit 890 C b 1 105 c Airspeed 140 KIAS d Torque 12396 8 Continue increasing thrust and increasing NO 1 amp NO 2 ENGINE BEEP TRIM switch until gas producer N1 speed for engine being TEACed stabilizes at maxi mum and rotor rpm falls to 98 percent Maintain N1 and 98 percent rotor rpm using thrust control and NO 1 amp NO 2 ENGINE BEEP TRIM switch 9 Stabilize the rotor speed at 98 percent then record the following a 1 b Deleted c Free air temperature FAT d Power turbine inlet temperature PTIT e Torque f Pressure altitude 10 Determine Engine Trim 4 28 C14 55 1520 240 Entdr figure 5 12 at the recorded FAT proceed vertical ly to the curves which define the acceptable range of N1 values then horizontally to the topping N1 per cent scale b Establish the PTIT band off figure 5 12 1 follows Upper limit the upper limit of the PTIT band is the top most line as marked on figure 5 12 1 Lower limit from the engine lower limit baseline Establish Engine Lower Limit 1 Engine that have previous accept
63. this case EAPS must be moved forward of the engine to gain access for inspection If TEAC PAT is not required EAPS will remain locked into position in front of the engine a Inlet for foreign objects and condi tion O b EAPS for general condition Check vortex tubes for erosion and dam age Check seals for condition Check rail and slide mechanisms Inspect blower fan blades for dam age and erosion Check condition of electrical connectors harness c Check fuel oil hydraulic electrical and drain lines for connection and leaks d Check engine for chafing lines and condition and security of compo nents C25 2 12 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Top of Fuselage 1 No 2 engine Check as follows a Inlet for foreign objects and condi tion If FOD screens are installed check security and condition O 1 EAPS for general condition Check vortex tubes for erosion and damage Check seals for condition Check rail and slide mechanisms CAUTION If engine is to be operated with the engine transmission fairing removed be sure barrel nuts are secured or removed b level and cap secured Check N1 topping stop in stalled if required Check N2 limit stop installed and safetied e Tailpipe and diffuser for cracks hot spots and security 2 12 1 2 12 2 blank C25 55 1520 240 PROCEDURE TROUBLESHOOTING REFERENCE EXTER
64. validate the accuracy of the PTIT temperature measurement system as mentioned in the troubleshooting chart A PTIT temperature below the established lower limit with all other indications correct is an indication of temperature system problems c Enter figure 5 12 2 the recorded FAT proceed verti cally to the pressure altitude then horizontally to the torque available scale 11 The engine trim is acceptable if the following conditions are met a Recorded 1 is between the values from step 10a which define acceptability and Recorded PTIT is between the values fron step 10b which define acceptability and Recorded torque exceeds the value from step 10c OR 4 282 C16 55 1520 240 b Recorded PTIT is within band 1 5 12 1 Recorded torque exceeds the value from step 10 and Recorded N1 is within 596 but does not exceed the Max line of figure 5 12 12 If the criteria of step 11 are not met troubleshoot the engine indicating systems prior to trimming the engine to comply Do not trim the engine to exceed PTIT limits To increase N1 or PTIT turn the N1 trim adjustment clockwise To decrease N1 or PTIT turn N1 trim adjustment counterclockwise Trim sensitivity is 4 turn of screw changes 1 approximately 1 and PTIT approximately 25 If the recorded N1 is acceptable but the recorded PTIT is lower than it should be according to 11a a resistance check of the PTIT harne
65. 05604 DISTRIBUTION To be distributed in accordance with Initial Distribution Number IDN 310195 requirements for TM 55 1520 240 MTF 55 1520 240 C22 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 22 WASHINGTON D C 8 April 1998 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages i through iii iv blank i through iv 2 29 and 2 30 2 29 and 2 30 2 33 and 2 34 2 33 and 2 34 2 38 1 2 38 2 blank 2 38 1 2 38 2 blank 3 17 and 3 18 3 17 and 3 18 D CE ET 3 18 1 3 18 2 blank 3 35 and 3 36 3 35 and 3 36 4 1 and 4 2 4 1 and 4 2 4 31 4 32 blank 4 31 through 4 41 4 42 blank 2 Retain this sheet in front of manual for reference purposes TM 55 1520 240 4TF C22 By Order of the Secretary of the Army DENNIS J REIMER General United States Army Chief of Staff Official B HUDSON Administrative Assistant to the Secretary of the Army 04711 DISTRIBUTION To be distributed in accordance with Initial Distribution Number IDN 310195 requirements for TM 55 1520 240 MTF 55 1520 240 21 CHANGE HEA
66. 10 20 30 40 50 ALIN 0Pc 0cSI SS WNL Qr c9c s 6c9c s Sco PUEY 1591 e ueunssy 7494 74971 ENGINE TORQUE 100 NR H 9 H L HIILLLLLLLLLL Eq agg Max Power 100 NR a eer CERT PRESSURE ee D ail 120 110 100 90 80 50 40 30 20 10 0 10 20 30 40 50 ALIN 0PC 0cSI SS WL 1 9 5 11 9 5 Sco yey sjmur 1594 L CI S PTIT C 940 Eee c spese venu d ETE EI I seo spes T Max Power tmit 899 EO ER zt rad sees on pee Mel Was
67. 1280 23 44 111 2 154 310 590 427 800 1472 699 1290 2354 46 114 3 160 320 608 432 810 1490 704 1300 2372 48 118 4 166 330 626 amp 38 820 1508 710 1310 2390 9 00 0 0 SUNK OK WW PONE 10 0 50 122 0 171 30 644 453 830 1526 716 1320 2408 11 1 52 125 6 177 350 662 49 0 1544 721 1330 2426 12 2 54 129 2 182 0 680 454 850 1562 727 1340 2444 13 3 56 132 8 188 370 698 460 860 1580 732 1350 2462 14 4 58 136 4 193 380 716 466 870 1598 738 1360 2480 15 6 60 140 0 199 390 734 471 880 1616 743 1370 2498 62 143 6 204 400 752 877 890 1634 749 1380 2516 17 8 64 147 2 210 410 770 482 900 1652 7 1390 2534 18 9 66 150 8 216 420 768 488 910 1670 760 1400 2552 20 0 68 154 4 221 430 806 493 920 1686 766 1410 2570 21 1 70 158 0 227 440 824 499 930 1706 771 1420 2588 22 2 72 161 6 232 450 842 504 940 1724 777 1430 2606 23 3 74 165 2 238 460 860 510 950 1742 782 1440 2624 24 4 76 168 8 243 470 878 516 960 1760 768 1450 2642 25 6 78 172 4 249 480 896 521 970 1776 793 1460 2660 26 7 80 176 0 254 490 914 527 980 1796 27 8 82 179 6 260 00 932 32 990 1814 Figure 5 1 Temperature Conversion Chart 5 3 5 4 blank 55 1520 240 MTF AIRSPEED OPERATING LIMITS poem WITH MIGPERATIVE CRUISE GUIDE HIBICATOR LONGITUDINAL CYCLIC 100 NOTOR APH 479 40 30 WANTED MAX INDICATED AIRSPEED FOR GIVEN TEMP PRESS ALTITUDE AND GROSS WEIGH
68. 2 6 2 Change 24 55 1520 240 TROUBLESHOOTING PROCEDURE INTERIOR Cont Forward Cabin Cont c Lower step Check condition and static wire d Step lock Check Emergency escape ax Check condition and security Transformer rectifier air screens Check clear behind and under seat both sides Avionics equipment Check security of components and connections AFCS computers electrical and pneumatic connections Check for condition and security Troop alarm box Check condition Hand fire extinguisher Check seal security date and tagged Engine control boxes overhead at station 200 Check security Seats litters first aid kits cargo and jettisonable cabin windows Check con dition and security Cabin lights Check condition Emergency exit lights Check secure and operation Utility hatch door Check and position as necessary 2 7 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE INTERIOR Cont Forward Cabin Cont 18 Center cargo hook Check and po sition as required Check air charge Check forward and aft hook manual release Position lever in stowed posi t ion O 18 1 Forward center and aft cargo hook manual release mechanism Check for security position lever in stowed position 19 Lower rescue door Check position as required and hand crank stowed 20 Hoist control
69. 20 feet aft wheel height d Check 100 rotor rpm 0 1 0 maximum stabilized droop Maxi mum stabilized torque split 6 4 9 Deleted 94 FADEC REV CHECK 10 11 THRUST CONT At ground detent b Both engines FADEC REV e g NR 100 THRUST CONT lever Increase to maximum attainable power with out lifting off NR Maximum transient change is 5 and 4 Maximum sus tained change is 3 Colder OAT will result in higher NR during reversionary mode THRUST CONT lever Return to ground detent Both engines FADEC PRI Deleted Flight Instruments a b 0Q 0m2 HSI compass card 2 split be tween pilot and copilot indicators Magnetic compass 5 of HSI in dication VGI alignment Turn and slip indicator Vertical velocity indicators Clocks 2 65 REFERENCE IT 25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont Stop note fuel quantity in all 12 LH Fuel System check tanks a Land aircraft b RH FUEL PUMPS ON c CROSSFEED FUEL VALVES CLOSE 13 Cowling and Leak Check Performed BEFORE TAKEOFF 1 Systems Check indications of the following Oc BR c a Rotor b Torque c Engine d Transmissions e Fuel f Master caution panel PARKING BRAKE As required AFCS SYSTEM SEL BOTH CYCLIC AUTO SWIVEL
70. 20 240 TROUBLESHOOTING PROCEDURE REFERENCE 2 With the GPS receiver J32 turned on turn Data Switch to Stat Observe message on Page 1 Line 2 The message ZEROED indicates all keys have been erased from memory and the unit is unclassified O AN ASN 128B DOPPLER WITH EMBEDDED GPS n DGNS Flight Test Procedure 1 Verify proper J37 system operation with MODE switch to TEST Left display GO and Right display ALL MAL lamp is off 2 Verify proper J38 response of CDU panel lighting to aircraft BRT and DIM controls Adjust to comfortable level 3 Perform DGNS system Start Up procedure Ensure four 4 satellite measurements SAT are being used and estimated position error EPE is 50 meters or less with keys loaded or 200 meters or less with a cold start 4 Fly helicopter over surveyed test course consisting of two 2 waypoints used as check points CP a minimum of 20KM apart 5 To minimize errors in establishing positions over the checkpoints CP the altitude shall be the lowest compatible with safety standards C21 2 84 8 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE 6 If checkpoint CP information was not entered through the data loader during Start Up enter checkpoints using the CDU 7 Set MODE switch to MGRS or LAT LONG 8 Set DISPLAY switch to XTK TKE Observe standard Cross Track XTK and Track angle error TKE display 9 Depress GPS DOP sel
71. 240 23 Ch 14 s Troubleshooting Refer to TM 55 1520 240 23 Ch 14 E LOOSENESS CHECK Reference TM 55 1520 240 23 Keep head hands and other body parts clear of moving flight controls Hydraulic forces are strong enough to cause severe injury NOTE Impedance bolts have been installed in flight con trol connections These bolts are self retaining and require a special nut and torque Refer to chapter 1 of reference for information on the bolts NOTE To do a satisfactory looseness check all binding conditions within control system must be corrected Binding in some components will prevent detection of looseness in other components Also looseness or wear in some components can cause binding 1 Check for binding in the tunnel controls as follows Dirt on bellcranks and idlers can sift into the bear ings Dirty bearings will bind and cause jerky con trol movements a Open the forward fairing and work platforms Open the six tunnel covers 4 8 55 1520 240 b Apply and hydraulic boost pressure to the flight control system c Move the thrust control control stick and directional pedals to produce motion in the tunnel controls NOTE Thrust or pitch control input will move the idlers Roll or directional control input will move the walking beams 1 Observe the walking beams and idlers Check for jerking movements Observe component attaching bolts Check for jerky rotation
72. 39 NO 1 and NO 2 GEN ON Check C13 both GEN OFF caution lights out 40 APU GEN OFF 4 POWER XFR NO 1 and NO 2 OFF 42 APU switch OFF APU ON caution light out 42 1 DECU fault monitoring Check as follows a ECL of engine to be checked Retard 5 degrees b Check DECU display reads 88 Flight Engineer c ECL FLT NOTE If DECU display is not 88 shut down engine being checked and remove all power from the DECU by pulling the respective PRI CONT and REV CONT circuit breakers on the PDP Repeat en gine start sequence and DECU fault monitoring check If DECU display is not 88 shut down helicopter and refer to maintenance d Repeat steps a b and c with other engine 43 Systems Check a ENG OIL PRESS Check Fluc 9 141 tuation 5 psi maximum b Maintenance Panel Check as G5 G7 follows flight engineer 1 Hydraulic pressures and tern 2 08 211 peratures Check 2 Bite indicators Check all black and caution lights out 44 Minimum Beep Check a NO 1 amp NO 2 ENGINE BEEP C28 TRIM switch Full DECREASE 2 47 C25 55 1520 240 TROUBLESHOOTING PROCEDURE STARTING ENGINES Cont b NO 2 ENGINE CONDITION lever GROUND Check NO 1 ENGINE for 91 94 rotor rpm Record data NOTE Minimum rotor rpm is set during single engine operation only Dual engine op erating rpm will be somewhat higher This increase in minimum rotor rpm should not
73. 40 MTF TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Loft Cabin Cont 2 GPU access panel and con nections Check condition 3 Forward landing gear Check as follows a Tires for inflation and con dition b Shock strut for extension and cleanliness c Hoses and wheel brakes for leakage chafing and security 4 Fwd aux fuel tank Check as required and security 5 Fuel vent Check clear and fairing secure 6 Forward landing gear sup port structure Check as follows a Fwd aux fuel tank electrical connections and fuel lines Check condition and se curity b Position light Check wir ing and condition C Access panel Check con dition and security 7 Static port Check clear 8 Anticollision light Check condition 9 HF antenna Check antenna wire and standoffs condition and security Change 1 2 25 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Left Cabin Cont 10 11 12 13 14 15 Main fuel tank Check as required and security Fuel vent Check clear and fairing secure Aft aux fuel tank Check as required and security Fuel vent Check clear and fairing security Fuselage skin Check for dents wrinkles loose or missing rivets Windows Check condition seals and proper installation cracks and cleanliness 15 1 MEMBR Engine wash system connec 16 C25 tors Check condition and security
74. 40 MTF 8 September 1982 is changed as follows Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 53 and 2 54 2 53 and 2 54 2 54 1 2 542 2 55 and 2 56 2 55 and 2 56 2 56 1 2 56 2 blank 2 83 through2 83 through 2 84 8 2 84 1 2 84 2 blank 3 45 and 3 46 3 45 and 3 46 3 46 1 through 3 46 3 3 46 4 blank URGENT 55 1520 240 20 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army DENNIS J REIMER General United States Army Chief of Staff Official pe BAAD JOEL B HUDSON Administrative Assistant to the Secretary of the Army 03012 DISTRIBUTION To be distributed in accordance with DA Form 12 31 E block no 0195 requirements for TM 55 1520 240 MTF 55 1520 240 C19 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 19 WASHINGTON D C 30 November 1994 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT A Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove p
75. 5 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below or changed text material is indicated by a vertical bar in the mar gin illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 41 and 2 42 2 41 and 2 42 2 42 1 2 42 2 2 Retain these sheets in front of manual for reference purposes This is a reprint of change 11 55 1520 240 11 By Order of the Secretary of the Army CARL E VUONO TT General United States Army Chief of Staff WILLIAM J MEEHAN 1 Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF Maintenance requirements for CH 47D Helicopter Cargo Transport URGENT TM 55 1520 240 MTF C10 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 10 WASHINGTON D C 14 March 1988 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed test material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages i and ii i and ii 4 1 and 4 2 4 1 and 4 2 4 31 4 31 2 Retain these sheets in front of manual for reference purposes URGENT 55 1520 240 10 By Order of the Secr
76. 5 GA 714A Engine Engine Power Check Max Continuous Power Check Weather Screen 3 2 1 0 1 2 3 4 5 6 Torque Margin 96 eae eee C At aa eee 7 8 ese Seale 9 10 Ries arca sr EESTI Ya p leds ess sr er a cera FE DEDE ELIT E EJ Epic ANE 50001 ESL I qc dL t BEER RUE E pe sea hove 1 capa KES e Sieh SERES DD ER ALIA O0PC 0cSI SS WNL ULI SEC 9c S LVUC9CS Sco spueg WD API GAS GENERATOR SPEED 96 61 59 57 55 AT Adr vue ar A VV IAA 49 47 ecco sa ee are TESTI E A ER E RT CER UR prep serae Eus ero lee eer s a E a Eu 48 Tus EE EET y e Ba at 8
77. 6 2 blank 2 87 and 2 88 2 89 and 2 90 4 1 and 4 2 4 11 through 4 14 4 14 1 through 14 14 7 4 14 8 blank 4 25 and 4 26 5 1 and 5 2 5 17 5 18 blank 5 23 5 24 blank 5 25 5 26 blank 5 26 1 5 26 2 blank 5 26 2 1 5 26 2 2 blank through 5 26 2 10 5 26 2 20 blank 5 29 5 30 blank 5 31 5 32 blank 2 Retain this sheet in front of manual for reference 55 1520 240 25 By Order of the Secretary of the Army Official ERIC K SHINSEKI General United States Army Chief of Staff pl UA JOEL B HUDSON Administrative Assistant to the Secretary of the Army 0013101 DISTRIBUTION To be distributed in accordance with Initial Distribution Number IDN 310195 requirements for TM 55 1520 240 55 1520 240 24 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 24 WASHINGTON D C 29 January 1999 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 5 and 2 6 2 5 and 2 6 rag 2 6 1 and 2 6 2 2 84 11 2 84 12 blank 2 84 11 and 2 84 12 2 84 13 2 84 14 blank 2 87 and 2 88 2 87 and
78. 8 Torque indicator erratic Not function of indicator B9 pointer i e sluggish response pin wheels remains above 1096 with engines shut down or fluctuates from high toque to 30 a Faulty power supply b Faulty wiring c Align zero adjustment resistor Cruise guide indicator will not move in TEST position a Circuit breaker out b Faulty indicator c Faulty wiring 3 7 55 1520 240 CONDITION B10 B11 B12 PROBABLE CAUSE Cruise guide indicator moves upscale but not into white TEST band a Faulty strain gage on flight control link b Faulty switch c Faulty wiring d Faulty indicator e Rotors engaged during test CYCLIC TRIM indictor s does not indicate lift off at appropriate airspeed or reposition from GND to 0 60 KTS position on lift off to hover a CYCLIC TRIM switch in MANUAL position b Ground proximity switch malfunction c Faulty actuator s d Faulty indicator s e Faulty AFCS unit f Faulty pitot static system g Pitot line not connected at AFCS unit CYCLIC TRIM indicator s does not indicate full EXT at appropriate airspeed or show full EXT early a Actuator out of tolerance b AFCS malfunction 3 8 55 1520 240 CONDITION PROBABLE CAUSE B13 CYCLIC TRIM indicator s does not indicate RET at appropriate airspeed or does not RET or indicate GND position a Faulty speed trim actuator b Faulty AFCS unit c
79. Assistant to the Secretary of the Army 02669 DISTRIBUTION To be distributed in accordance with DA Form 12 31 E block no 0195 requirements for 55 1520 240 MTF 55 1520 240 15 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 15 WASHINGTON D C 30 April 1992 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 1 through 2 6 2 1 through 2 6 2 13 and 2 14 2 13 and 2 14 2 14 1 2 14 2 2 15 through 2 18 2 15 through 2 18 2 31 through 2 36 2 31 through 2 36 ip 2 36 1 2 36 2 2 37 through 2 40 2 37 through 2 40 2 47 through 2 50 2 47 through 2 50 2 53 and 2 54 2 58 and 2 54 2 58 1 2 58 2 2 58 1 2 58 2 2 61 2 62 2 61 2 62 2 65 2 66 2 65 2 66 2 69 through 2 74 2 69 through 2 74 2 87 and 2 88 2 87 and 2 88 3 37 and 3 38 3 37 and 3 38 4 11 through 4 14 4 11 through 4 14 4 14 1 4 14 2 4 15 4 16 4 15 4 16 2 Retain this sheet in front of manual for reference purposes 55 1520 240 15 By Order of the Secretary of the Army GORDON SULLIVAN General United States Army Chief of Staff Official 77 al MILTON H HAMILTON Adminis
80. BLESHOOTING PROCEDURE STARTING ENGINES Cont 32 NO 1 and NO 2 ENGINE BEEP TRIM switch DECREASE for 8 seconds 33 Area Clear for start NOTE If the start is not normal abort it If a second start is to be attempted wait at least 15 seconds after the N1 tachometer indicates zero before starting This will allow sufficient time for fuel to drain out of the combustion chamber CAUTION Sand and debris within the EAPS will be ejected when the EAPS fan is oper ating Personnel shall stand clear of the exhaust when the fan is turned on NOTE The EAPS fans have high start up elec trical power requirements To prevent an overload the fans must be turned on one at a time The first fan must be allowed to stabilize for 2 3 seconds before the second fan is turned on 033 1 EAPS FAN NO 1 and NO 2 switches C25 ON one at a time Allow first fan to stabilize for 2 3 seconds before the second fan is turned on CAUTION With the DASH actuator set to 36 inches and electrically disconnected neutral on the stick position is 3 4 inch aft of neutral 2 46 REFERENCE C28 55 1520 240 TROUBLESHOOTING PROCEDURE STARTING ENGINES Cont 33 2 DECU and Abort System Check Perform the following a Back up power switch ON Check FADEC 1 amp 2 capsules OUT Check REV 1 amp 2 and ENG FAIL 1 amp 2 capsules cycle ON then OUT b ENG COND levers GND F
81. Bit a Faulty wiring J44 SYSTEM NO GO displayed upon completion of P Bit a Keys or data not loaded for a particular mode of operation b Faulty HF Radio system component Set function switch to STBY press INOP line select switch and press LRU line select switch to acquire failed component listing J46 Radio control displays CDU FAIL a Faulty control display unit b Faulty wiring J46 Radio control displays a Faulty receiver transmitter b Faulty wiring Change 24 3 46 5 55 1520 240 347 LOAD FAIL displayed during Keyfill a Fill device improperly connected to key fill port b Fill amp vice not enabled c HF Radio component failure Perform BIT test to determine failed component d Fill connectors improperly connected between CDU and RT e Faulty wiring J48 COPY FAIL displayed during Datafill a Fill device improperly connected to key fill port b Fill device not enabled c HF Radio component failure Perform BIT test to determine failed component J49 KY 100 does not turn on a Circuit breaker out b Faulty Z AVH control c Faulty main processor d Faulty wiring J50 DEV ERR displayed and a fail tone heard In headset when loading KY 100 a Fill device not connected properly b Fill amp vice not configured properly 3 46 6 Change 24 55 1520 240 J51 KY 100 key loading unsuccessful a Faul
82. CE FS F6 F8IF9IF10 55 1520 240 TROUBLESHOOTING PROCEDURE ENGINE RUN UP Cont 6 Flight instruments Check as follows b Horizontal Situation Indicator HSI Check synchronized Cross check with magnetic com pass Attitude indicators Adjust as required 7 EMERG ENG TRIM System Check operation a NO 1 EMERG ENG TRIM AUTO MAN switch MAN b Note reading CAUTION Do not allow engine speed to go below minimum allowable N1 speed of 60 NO 1 EMERG ENG TRIM INC d DECR switch Full DECR En gine speed should decrease and sta bilize at 6076 N1 or above Ensure engine remains running NO 1 EMERG ENG TRIM INC DECR switch INC to previously noted N1 speed No 1 ENG TRIM AUTO MAN switch AUTO f Repeat steps a through e for NO 2 ENG 2 52 1 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont 7 1 FADEC system check FADEC NR check 1 FADEC NR switch 97 Check NR decreases to 9796 190 with torques matched within 4 2 FADEC NR switch 103 Check NR increases to 103 196 with torques matched within 4 3 FADEC switch 100 Check NR returns to 10096 with torques matched within 490 b FADEC Reversionary Mode Check 1 ENG 2 ENG COND lever GND 2 FADEC 1 switch REV 3 THRUST CONT lever In crease to obtain 9096 N
83. CS BITE CHECKS B SELF TUNING ABSORBER SYSTEMS 4 4 CHECK C CONTROL BREAKOUT FORCES D WINCH OPERATIONAL TEST E LOOSENESS CHECK 9 1 4 NO 2 ENGINE START G 1 MER NO 1 and NO 2 ENGINE START G2 BELLOWS CHECK L1LI G 3 NO 1 and NO 2 ENGINE REVER 142 SIONARY START G 4 RIESS POWER ASSURANCE TEST G 5 POWER ASSURANCE TEST TRIG 14 5 GER VALUE H INTERSTAGE AIR BLEED SPEED AD JUSTMENT L AFCS CHECK J HEATING VENT BLOWER OPERATION K CARGO HOOK OPERATIONAL CHECK L STROBEX VIBREX TRACKING PROCE DURE M ENGINE VIBRATION CHECK N B CHECK 4 25 O RAPI TURBINE ENGINE ANALYSIS CHECK TEAC P Deleted Q DIFFERENTIAL CURRENT PROTECTION CIRCUIT CHECK R CARGO RAMP AND DOOR CHECK 32 S HEADS UP DISPLAY HUD CHECK 4 1 C25 55 1520 240 AFCS BITE CHECKS Reference 55 1520 240 23 This test should only be preformed to verify a suspected AFCS discrepancy The bite test is performed by pressing the BITE switch on the AFCS computer The bite associated with sytems No 1 tests system No 1 only and system No 2 tests system No 2 only The engine condition levers provide a bite interlock which prevents inadvertent bite operation during flight The bite test cam be interrupted during operation by moving the engine condition level out of the STOP position and back again or by switching the AFCS to OFF 1 Prior to activating the bite t
84. D NO 2 ENGINE START Reference TM 55 1520 240 10 TROUBLESHOOTING PROCEDURE REFERENCE NOTE Either engine may be started first 1 First engine Start as follows a L FUEL PUMP MAIN switches py ON Check L FUEL PRESS cau tion capsule out b XFEED switch OPEN Check R p10 FUEL PRESS caution capsule out c ENG COND lever STOP d ENG START switch MTR 2 1 Avoid motoring in excess of 15 seconds before moving the ENG COND lever to GND These excess periods can have a detrimental effect on starter reliability e Motor engine to a minimum of 15 N 1 Set ENG COND lever GND ENG START switch to START imme diately Check STARTER ON light on C25 4 12 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE f Release START switch to MTR prior to PTIT reaching 200 When N1 is 5096 set START switch to OFF Check STARTER ON light out CAUTION If no oil pressure is indicated during the starting sequence shut down engine and investigate g ENGINE OIL PRESS Check 1 41 14 8 and record 20 psi Minimum h Engine instruments Check 71 91 141 8 Ground idle 60 0 to 63 0 percent 1 is the minimum speed at which the engine will operate satisfactorily for extended periods If the engine speed stabilizes below ground idle shut down the engine and investigate Ground idle speed after 45 seconds
85. DITION D10 D11 D12 D13 PROBABLE CAUSE With crossfeed switch open and left or right fuel pumps on only the L or R FUEL PRESS caution light for the pumps turned on goes out a Circuit breaker out b Faulty crossfeed valve c Faulty caution panel d Faulty wiring e Faulty pressure switch NO 1 or NO 2 ENG N1 CONT caution light does not come on when engine condition lever is moved out of detent a Circuit breaker out b Faulty caution panel c Faulty control box d Faulty actuator e Faulty wiring NO 1 or NO 2 ENG N1 CONT caution light stays on when engine condition lever is in detent a Faulty wiring b Faulty actuator c Faulty control box NO 1 or NO 2 ENG N1 CONT caution light flashes on and off as the engine condition lever is moved betwwen detent positions a Actuator mechanical linkage obstruction b Gas producer control actuator faulty 3 20 55 1520 240 CONDITION D14 D15 D16 PROBABLE CAUSE NO 1 or NO 2 GEN OFF caution light on and NO 1 or NO 2 RECT OFF caution light on a Circuit breaker out b Faulty bus tie relay c Faulty reverse current relay d Faulty wiring NO 1 or NO 2 RECT OFF caution light on a Circuit breaker out b Faulty reverse current relay c Faulty transformer rectifier d Faulty wiring Fuel pressure L or R FUEL PRESS caution lights do not come on when all fuel pumps are turned off
86. DQUARTERS DEPARTMENT OF THE ARMY NO 21 WASHINGTON D C 9 February 1998 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT A Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages i and ii i and ii 2 37 and 2 38 2 37 and 2 38 2 55 and 2 56 2 55 and 2 56 2 65 and 2 66 2 65 and 2 66 2 84 7 and 2 84 8 2 84 7 and 2 84 8 2 84 9 through 2 84 11 2 84 12 blank 3 46 3 3 46 4 blank 3 46 3 and 3 46 4 2 Retain this sheet in front of manual for reference purposes 55 1520 240 21 By Order of the Secretary of the Army DENNIS J REIMER General United States Army Chief of Staff Official JOEL B HUDSON Administrative Assistant to the Secretary of the Army 04505 DISTRIBUTION To be distributed in accordance with initial Distribution Number IDN 310195 requirements for TM 55 1520 240 MTF PIN 051400 021 URGENT TM 55 1520 240 MTF C 20 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 20 WASHINGTON D C 27 FEBRUARY 1997 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HEUCOPTER DISTRIBUTION STATEMENT A Approved for public release distribution is unlimited TM 55 1520 2
87. E REFERENCE IN FLIGHT Cont 8 Push PTT 9 ARC 220 displays CALLING 10 Wait for a short gong tone and LINKED on display before transmitting to a like con figured station 12 ARC 220 Mode switch ECCM Channel switch Desired channel SQL switch O or I 13 Transmit to a like J69 63 station by pressing PTT wait for preamble tones to cease and begin transmission 14 While still in ECCM 158 mode transmit a message from a like configured ground air station to aircraft ARC 220 HF radio PREAMBLE and or INCOMING CALL is displayed before incoming message is heard 2 84 13 2 84 14 blank Change 24 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont d Establish cruise flight and record 1 ENG OIL PRESS 2 ENG OIL TEMP 3 XMSN OIL PRESS 4 XMSN OIL TEMP 5 Hydraulic pressures flight engineer response 6 Hydraulic fluid temperatures BEFORE LANDING 1 Systems Check indications of the following a Rotor 100 b Torque c Engine d Transmission e Fuel f Master caution panel 2 AFCS HDG and ALT switches Disengaged 3 CYCLIC TRIM switch As required 4 PARKING BRAKE As re quired 2 85 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE BEFORE LANDING Cont 5 SWIVEL switch LOCK 6 Crew and mission equipment Check AFTER LANDING 1 Flight Co
88. EDURE REFERENCE STARTING ENGINES Cont 7 PILOT and COPILOT utility lights Check rheostat operation 8 Ground Power Unit Connect GPU for ground start Check EXT PWR caution light on 9 Fire guard Posted CAUTION If a start results in a roar with flame in the exhaust hot or torching start shut down the APU by setting the APU switch to OFF NOTE Allow one minute for cooling between APU shutdown and restart Failure to do so may result in a premature shut down on restart due to overtempera ture 10 APU switch RUN for 3 to 5 seconds Then START for 2 sec onds Then release to RUN 11 APU ON indicating light Check on after switch is released to RUN When the APU is running properly the APU ON light will come on 12 UTIL HYD SYS caution Check out If the light does not go out within 30 seconds of operation shut down the APU Have the utility hydraulic system checked C15 2 36 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 13 APU GEN switch ON Check NO 1 and NO 2 REC OFF caution lights out Check avionics cooling fan on NOTE VGI alignment within 90 seconds max imum 2 36 1 2 36 2 blank C15 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 14 GPU Disconnect if used Check EXT PWR light out 15 POWER XFR NO 1 and POWER XFR NO 2 switches ON 16 HYD FLT CONTR ca
89. EN 2 switch Off Check NO 1 GEN Off caution light is out and NO 2 GEN OFF caution light is on 4 GEN 2 switch ON Check both GEN OFF cau tion lights are out 5 HEATER WINDSHIELD ANTI ICE SLT FIL and FUEL PUMPS switch Set as desired 4 31 C22 55 1520 240 CARGO RAMP AND DOOR CHECK Reference TM 55 1520 240 T 1 Cargo ramp and door Check fully closed 2 Electrical and hydraulic power Off 3 APU START ACCUMULATOR guage Check 2 500 psi minimum If not use hand pump to charge accu mulator 4 EMERG UTIL PRESS valve OPEN 5 RAMP CONTROL VALVE handle DN and hold until ramp is level with cabin floor then STOP Check for the following sequence of actions a Ramp and cargo door open and move downward about IO inches then stop b Cargo door then retracts into ramp c Ramp then continues to move downward then stops when the RAMP CONTROL VALVE handle is moved to STOP 6 EMERG UTIL PRESS valve NORMAL 7 Apply electrical and hydraulic power 8 UTIL SYS CONT circuit breaker Check closed 9 RAMP EMER CONT circuit breaker Check closed 10 RAMP PWR switch on overhead panel ON 11 RAMP CONTROL SEQUENCE VALVE Turn pin to horizontal position 12 RAMP CONTROL VALVE handle DN Check that ramp moves to full down position resting on ground and cargo door remains retracted 13 RAMP CONTROL VALVE handle UP Check that ramp moves
90. ER TACHOMETER POWER TURBINE INLET TEMPERATURE meee ENG OIL TEMPERATURE mene ENGINE OIL PRESSURE XMSN OIL PRESSURE XMSN OIL TEMPERATURE TORQUEMETER meee TORQUEMETER ROTOR TACHOMETER AIRSPEED C25 Instrument Range Markings RANGE MARKING YELLOW RADIAL 60 RED RADIAL 10746 GREEN ARC 400 TO 780 C YELLOW ARC 781 940 C RED RADIAL 890 C BLUE RADIAL 810 C RED RADIAL 940 C RED RADIAL 140 C RED RADIAL 20 PSI RED RADIAL 35 PSI GREEN ARC 35 TO 90 PSI RED RADIAL 110 PSI RED DOT 150 PSI YELLOW RADIAL 50 RED RADIAL 110 GREEN ARC 400 TO 815 C YELLOW ARC 815 TO 940 C BLUE RADIAL 855 C RED RADIAL 900 C RED RADIAL 940 C RED RADIAL 149 C RED WHITE RADIAL 5 PSI GREEN ARC 5 TO 90 PSI YELLOW ARC 90 TO 110 PSI RED WHITE RADIAL 110 PSI RED DOT 150 PSI RED RADIAL 7 PSI RED RADIAL 20 PSI GREEN ARC 20 TO 90 PSI RED RADIAL 140 C RED RADIALS 100 AND 123 RED RADIALS 101 AND 123 RED DOT 91 RED RADIAL 96 Disregard Not applicable GREEN ARC 97 TO 101 YELLOW ARC 102 TO 105 RED RADIAL 106 RED RADIAL 108 RED DOT 115 RED RADIAL 170 2 32 55 1520 240 Table 2 1 Instrument Range Markings Continued INDICATOR RANGE MARKING MAINTENANCE PANEL INDICATORS FLT CONTROL HYDRAULIC RED RADIAL 2500 PSI PRESSURE GREEN ARC 2500 TO 3200 PSI RED RADIAL 3200 PSI UTILITY HYDRAULIC PRES RED RADIAL 2500 SURE GREEN ARC 2500 TO 3500 RED RADIAL 3500
91. ESHOOTING REFERENCE PROCEDURE IN FLIGHT Cont 3 Pitch beep trim check While trimmed level at 110 knots operate the four way switch on the cyclic stick without moving the Stick forward momentarily The aircraft shall respond smoothly and increase airspeed Do not allow airspeed to exceed 120 knots 4 Repeat using beep trim to attain 110 knots e Roll axis and coordinated turn Check roll axis operation by trimming the helicopter to level roll attitude at 110 knots 1 Trimmed attitude shall be maintained with 3 roll and heading within 3 The ball on the turn and slip indicator shall be centered within gt ball width 2 Move the cyclic stick out of detent to the right do not operate the centering device release button to generate a 20 bank angle Release stick back into detent Hold turn for 60 The newl acquired bank angle shall be hel within 5 During entry into the turn the ball shall not be off centered by more than one ball diameter When stabilized in the turn the ball in the turn and slip indicator shall be centered within Ye ball width C15 2 70 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 3 Using cyclic stick return aircraft to level attitude Aircraft shall hold level roll attitude 3 and heading within 3 with controls free Repeat steps 2 and 3 banking to the left f Roll beep trim Check as follows 1 W
92. F Radio AN ARC 102 1 Mode select switch AM 2 Allow 5 minutes for warm up 3 Key transmitter and J19 listen for 1000 Hz tone for no more than 30 seconds Change 2 2 80 55 1520 240 PROCEDURE IN FLIGHT Cont 4 Transmit and receive on AM USB and LSB 5 Evaluate communica tions throughout a 360 degree turn j Doppler Navigation Set AN ASN 128 1 Verify proper system operation with MODE switch at TEST and display indicates GO a Fly helicopter over surveyed test course figure 2 1 at cruise airspeeds The altitude should be low enough to minimize error in establishing position over checkpoints b Enter magnetic variations lateral and longitudinal coordinates of the checkpoints c With the MODE switch in UTM the DISPLAY switch in GS TK and the FLY TO DEST thumbwheel in position 0 take off and observe that the MEM and MAL lights are extin guished and ground speed GS and track angle TK are reasona ble d Set the DISPLAY switch to DIST BRG TIME and the FLY TO DEST thumbwheel to position 1 2 81 TROUBLESHOOTING REFERENCE J20 21 J22 25 55 1520 240 MIN 20 XM MIN ce 3 4 2 Figure 2 1 Test Course for Overhaul Accuracy Doppler 2 82 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont e Fly over the initial checkpoint CP 1 on a heading fo
93. GE HEADQUARTERS DEPARTMENT OF THE ARMY NO 13 WASHINGTON D C 18 OCTOBER 1990 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below or changed text material is indicated by a vertical bar in the mar gin illustration change is indicated by a miniature pointing hand Remove pages Insert pages i and ii i and ii 2 9 and 2 10 2 9 and 2 10 2 31 and 2 32 2 31 and 2 32 2 40 1 2 40 2 2 40 1 2 40 2 3 23 and 3 24 3 23 and 3 24 4 25 and 4 26 4 25 and 4 26 2 Retain this sheet in front of manual for reference purposes 55 1520 240 13 By Order of the Secretary of the Army CARL E VUONO General United States Army Chief of Staff Official THOMAS F SIKORA Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF Maintenance require ments for CH 47D Helicopter Cargo Transport 55 1520 240 12 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 12 WASHINGTON D C 1 November 1989 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin illustration change is indicated by a miniature poin
94. I 4 FADEC 1 INC DEC switch DEC and hold Check that NR stabilizes at 97 4196 2 If NR continues to decrease below 97 return NR to 100 by holding the switch in the INC position and releasing it at 100 NR Corrective maintenance action is required 5 FADEC 1 INC DEC switch INC and hold Check that NR stabilizes at 103 4 296 1 If NR continues to increase above 10346 return NR to 100 by holding the switch in the DEC position and releasing it at 100 NR Corrective maintenance action is required C25 2 52 2 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont 6 FADEC 1 INC DEC switch DEC as necessary to obtain 10096 NR 7 THRUST CONT lever In crease to maximum possible without lifting off the ground Check that NR stabilizes at 100 290 8 FADEC 1 switch PRI 9 THRUST CONT lever Ground detent 10 ENG 2 ENG COND lever FLT 11 Repeat steps 1 through 10 with the other engine 2 53 C25 55 1520 240 PROCEDURE ENGINE RUN UP Cont 8 Systems instruments Check engine transmission rotor and fuel systems indications Master caution panel Check 9 Altimeters Set Test Barometric altimeter Recheck tower setting Radar Altimeters Check 1 Dial pointers between 0 and 2 feet 2 Digital display indicates 0 2 feet 3 Set LO Set Index greater than 2 feet and HI Set Index 800 feet or less
95. IOR Cont Top of Fuselage Cont f Power turbine section Check upper portion of engine for condition security and leaks g Engine fairing condition and security h If EAPS is installed Check EAPS to fairing mating surface for evidence of wear or chafing 2 Utility and flight control modules and cooler assemblies Check for extended filter contamination indicators and leaks Check that accumulators are precharged Section V Check PTU condition and security 3 Aft rotor right side Check as follows Check lag damper lockouts removed b Check components for proper safety wiring and security C Check blade lightning protection straps and cables installed on top and bottom of each blade and condition d Check oil in rotor system reservoirs on right side Check droop stop weights and return mechanism and droop stops for condition and security 2 13 C17 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Top of Fuselage Cont f Check droop stop shrouds for condition and security if in stalled g Check rain shield and stiffener for condition and security Check pitch change links swash plate slider assembly and drive arm for condition and security Check upper boost actuator and pilot valve for proper connection condition security leakage ex tended jam indicators 4 Check thrust bearing and thrust bearing mount bolts a
96. IT ACK switch Release Display returns to operating mode 4 37 C22 55 1520 240 3 Ground Check perform prior to flight a Pilot DU select a Master Mode Display Verify that pilot DU is not changed as w pilot toggles through all available symbology and declutter modes b Repeat step a above for co pilot DU as pilot toggles through available display modes 4 In flight Operation NOTE Ensure that the AN APN 209 AN ASN 43 and AN ASN 128 are ON and operational a Heading 1 Ply the aircraft on a heading of 360 using the HSI 2 Verify that the compass heading scale on the DU displays a 000 heading 3 Repeat steps 1 and 2 for a heading of 045 090 135 180 225 270 315 b Hearing and distance check 1 Verify that the bearing to waypoint numeric on the DU matches the bearing to destination on the AN ASN 128 dis play 2 Verify that the bearing to waypoint pointer on the DU matches the bearing to waypoint numeric or is displayed far right or far left if bearing is beyond displayed compass heading scale C22 4 38 55 1520 240 3 Maneuver the aircraft in the direction of the waypoint until the hearing to waypoint pointer is centered Verify that the bearing to waypoint pointer matches the bearing to waypoint numeric on the DU 4 Verify that the distance to target on the DU matches the distance to destination on the AN ASN 128 display c High
97. Ib D WINCH OPERATIONAL TEST Reference TM 55 1520 240 T 1 Perform an operational test of the cargo hoisting system as follows a With the APU running apply hydraulic pressure and electrical power to the helicopter 4 5 Change 12 TM 55 1520 240 MTF b Route the winch cable in the hoist configuration Refer to TM 55 1520 240 10 c Plug in the cable curter at sta 120 or 325 d Check the HOIST CONT circuit breaker on the No 1 is closed Set the HOIST MASTER switch to REMOTE e Set the shifting lever on the winch to RESCUE If the shift lever fails to operate properly replace the winch Operate the winch from either of the auxiliary hoist opera tor s control panels Connect the winch control grip to the panel using the extension cord f Press the WINCH ARMING TRIGGER and rotate the WINCH CABLE switch to OUT Continue to operate the winch until it stops Check that the out limit switch stops the winch when 2 1 2 wraps of the first layer of cable remain on the drum If the winch does not stop within the specified limit readjust the out limit switch Refer to TM 55 1520 240 23 Ch 14 If the time required to reel the cable fully OUT is not about 90 seconds replace the winch In case of an in limit switch failure do not allow the end of the cable to reel in and jam in a pully The winch pulley or airframe maybe damaged 0 Operate the WINCH CABLE control switch to IN Continue to operate the winch
98. KNOTS 3 0 3 0 2 0 2 0 oe rl SH HE HE LONGITUDINAL STICK POSITION ENVELOPE 1 0 0281 99 WL 22 9 12 6 210 Z 19949 edojaau3 uonisog 195209 QZt HO 01 5 enb LATERAL STICK POSITION INCHES PEDAL DISPLACEMENT INCHES CROSS WEIGHT STANDARD ROTOR RPM 100 UNBALLASTED CONFIGURATION RATE OF CLIMB ZERO CYCLIC TRIM AUTO 8 100 110 120 130 140 150 160 INDICATED AIRSPEED KNOTS LATERAL STICK POSITION ENVELOPE Se SPP 800 A ES BEN 80 70 80 90 100 10 120 130 140 150 160 MIT 2 EN INDICATED AIRSPEED KNOTS DIRECTIONAL CONTROL PEDAL POSITION ENVELOPE 0140 185 0 2 029 1 99 WL DENSITY ALTITUDE FEET TM 55 1520 240 MTF TRIM HELECOPTER IN STABILIZED AUTOROTATION WITH FULL DOWN THRUST CONTROL GROSS WEIGHT 28000 LB x 1000 LB INDICATED AIRSPEED 70 KTS TO 100 KTS 6000 4000 eee oe 1 ROTOR BEER ER ER ILL A a See ARERR REE SRR 2 50 PEE T Viti itt tT Tite ee MU tT TTP TAP ee A Het tt 2000 NE EI LT TTT eT L SRR See Li ity yyy T TREE LTT Try HHH a q a EERE EB E gt Ed a a a L a LIT Ki ri TT T
99. Left aft landing gear Check as follows a Landing gear support structure Check for cracks or distortion b Tires Check for inflation and condition c Static ground wire Check wire secure and contacting the ground d Shock strut Check proper exten sion cleanliness and static lock unlocked e Electrical connections Check condition and security f Landing gear proximity switch Check condition linkage adjust ment and security 2 26 REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Left Cabin Cont 1 No 1 engine Check lower side as follows NOTE If TEAC PAT is to be performed all preflight inspection requirements checks required prior to TEAC PAT must be accomplished In this case EAPS must be moved forward of the engine to gain access for inspection If TEAC PAT is not required EAPS will remain locked into position in front of the engine O Inlet for foreign objects hinge latch secured and condition 1 EAPS for general condition Check vortex tubes for erosion and damage Check seals for condition Check rail and slide mechanisms Inspect blower fan blades for damage and erosion Check condition of electrical connectors and harness Check fuel oil hydraulic electrical and drain lines for connections leaks and condition Check engine for chafing lines and condition and security of compo nents Check 1 top
100. MY NO 5 WASHINGTON D C 15 April 1986 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 21 and 2 22 2 21 and 2 22 2 Retain these sheets in front of manual for reference purposes NOTE Laminated pages will be pro vided in next normal change URGENT 55 1520 240 C5 By Order of the Secretary of the Army JOHN A WICKHAM JR General United States Army Chief of Staff Official R L DILWORTH Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF requirements for CH 47D Helicopter Cargo Transport URGENT TM 55 1520 240 C 4 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 4 WASHINGTON 8 November 1985 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages cated below New or changed test material is indicated by a vertical bar in the margin illustration change 15 cated by a miniature pointing hand Remove pages Insert pages 2 63 and 2 64 2 63 and 2 64 2 Retain this sheet
101. NG GROUND OPER 3 Control Position Check 4 Generator X TIE amp iewmesmwe m a undertrequency b Lateral in 2 FUEL Pump and XFEED o Pedais split in 3 XMSN OIL PRESS ind __ 4 LH Fuel System Check 4 XMSN OIL TEMP ind 5 Torque Differential Emerg Eng Trim FADEC Disc 7 ELT FADEC sys check a FADEC NR Check b REV Min Max Check 6 Droop Eliminator a RRPM b Torque No 1 No 2 c REV Check REV Droop Check d OVERSPEED Check 8 Engine Anti ice amp Ammees e Fight netrumente CCS SSS dS en O e 3 Swivel locks check BEFORE HOVER CHECKS 1 RH Fuel system check m i 2 Ground instability REMARKS A63093 Figure 5 15 Maintenance Test Flight Check Sheet 1 of 2 5 29 5 30 blank C25 MODEL amp SERIAL NUMBER DATE PURPOSE OF TEST FLIGHT PILOTS NAME amp UNIT OPERATING DENSITY WEIGHT LBS ALTITUDE FT SYMBOLS SATISFACTORY X DEFICENCY IN FLIGHT CHECKS Speed Sweep Gheck 120K 7 i Fuetconeumption Long measure Speed sweep ok 60K b Emerg exit doors L stvaevaluation oes T 61 Rotor Droop Thrust Slippage Oreck ti tong measure 7 Speed Sweep Check tay tatmensure
102. OCEDURE REFERENCE 5 AFCS SYSTEM SEL OFF a NO 1 amp NO 2 AFCS OFF caution lights on 6 MASTER CAUTION light RESET J HEATING VENT BLOWER OPERATION Reference TM 55 1520 240 10 TROUBLESHOOTING PROCEDURE REFERENCE 1 HEATER function switch VENT BLOWER ONLY AIR CONTROL knobs PULL and check operation 2 COCKPIT AIR CONTROL knobs Pilot and copilot PULL 3 HEATER function switch HEATER ON 4 HEATER START switch Press Check ignition within 10 seconds 5 CABIN TEMP SELEC TOR Check hearer operation and rheostat from COLDER to WARMER 6 HEATER function switch C33 OFF Check that blower continues to run until combustion chamber cools 4 17 55 1520 240 K CARGO HOOK OPERATIONAL CHECK Reference TM 55 1520 240 23 1 CARGO HOOK PWR CONT NORM RELEASE circuit breakers on No 2 power distribution panel Check in 2 CARGO HOOK EMER RELEASE PWR CONT EMER RELEASE and CAUTION PANEL circuit breakers on No 1 power distribution panel Check in 3 Hoist operator cargo hook switch REMOTE 4 Apu On 5 Floor and rescue hatch doors Open 6 Mid cargo hook released from stowed position 7 Mid hook air charge 2 100 psi 8 Check that the forward and aft hooks are properly in stalled Check that the electrical and mechanical cables are connected to the hooks 9 Check the center hook by placing a length of wood ap proximately 2 by 4 inches on the tong
103. OFF switch OFF b Optical unit support clamps Check c Display unit lens Check Failure to remove the ANVIS neck cord prior to operation of the HUD may prevent egress from the aircraft in an emergency d ANVIS neck cord Removed e Optical unit Install on ANVIS Lightly turn OU thumbscrew clockwise f EYE SELECT switch L or R CCU ADJ ON OFF switch must be OFF before connecting or disconnecting quick release connector The 5 7 system should not be used if the quick release connector is not in working order C22 4 36 55 1520 240 PSOCU CONNECT Connect PSCU to quick release connector h PSCU Disconnect Pscu Reconnect Keep the protective caps on the ANVIS whenever it is not in use Operate the ANVIS only under darkened conditions NOTE Ensure ANVIS operator procedures have been completed j P PGM OP CP PGM switch OP k ADJ ON OFF switch ON SYS ON and FAIL lights illuminate and BIT will initiate automatically FAIL light Check Out after ten seconds is complete Allow 1 minute for warmup m BRT DIM switch as desired n DSPL POS control as required o Display aligned to horizon Check Tighten thumbscrew p Master Mode Display Check 2 Symbol generator Check as follows a switch Press BIT and hold Display unit will show all master symbols software version date and type aircraft b B
104. OPTER DISTRIBUTION STATEMENT Approved for public release distribution is unlimited TM 55 1520 240 8 September 1982 is changed as follows Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages and iv 2 1 through 2 4 2 7 2 8 2 11 2 12 2 12 1 2 12 2 2 15 and 2 16 2 23 through 2 2 26 2 26 1 2 26 2 blank 2 29 through 2 32 blank 2 33 and 2 34 2 39 and 2 40 2 45 and 2 46 2 46 1 2 46 2 blank Insert pages iii and iv v vi blank 2 through 2 4 2 7 and 2 8 2 11 and 2 12 2 12 1 2 12 2 blank 2 15 and 2 16 2 23 through 2 2 26 2 26 1 2 26 2 blank 2 29 through 2 32 2 32 1 2 32 2 blank 2 33 and 2 34 2 39 and 2 40 2 45 and 2 46 2 46 1 and 2 46 2 55 1520 240 25 Remove pages 2 55 and 2 56 2 63 and 2 64 2 65 and 2 66 2 73 and 2 74 2 75 and 2 76 2 87 and 2 88 2 88 1 2 88 2 blank 2 89 2 90 blank 4 1 and 4 2 4 11 through 4 14 4 25 and 4 26 5 1 and 5 2 5 17 5 18 blank 5 23 5 24 blank 5 25 5 26 blank 5 26 1 and 5 26 2 5 29 5 30 blank 5 31 5 32 blank purposes Insert pages 2 46 3 2 46 4 blank 2 47 through 2 50 2 51 1 and 2 52 2 2 53 and 2 54 2 54 3 2 54 4 blank 2 55 and 2 56 2 63 and 2 64 2 64 1 2 64 2 blank 2 65 and 2 66 2 73 and 2 74 2 75 and 2 76 2 76 1 7 7
105. RPM increase thrust as neces sary to stabilize airspeed at 140 knots with thrust brake trigger depressed 2 Maximum change in in rotor rpm shall be 2 or pm 1 3 Maximum thrust rod slippage with thrust brake applied shall be 246 dual engine torque 9 Speed Sweep Check a Stabilize airspeed at 140 knots 1 Record longitudinal stick posi HI2IKI2 tion 2 Record lateral stick position 3 Record directional pedal sepa Hal ration 4 Compare pilot and copilot air 7677 speed indicators 6 knots maxi mum difference 10 Speed Sweep Check a Increase and stabilize airspeed at 150 knots 1 Record longitudinal stick H12 position C25 2 74 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 2 Evaluate 1 Rev and 3 11 4 Rev vibration 3 Coordinated turns 11 CYCLIC TRIM Check a Observe both CYCLIC TRIM indicators have reached the leading edge of the EXT range 150 knots FWD and AFT LCT schedules corrections for increases in pressure altitude are shown in b Decrease and stabilize airspeed below extended envelope corrected for altitude section V 2 74 1 2 74 2 blank C6 55 1520 240 TROUBLESHOOTING PROCEDURE IN FLIGHT Cont 1 CYCLIC TRIM indicators Check both out of EXT range CAUTION Before entering autorotation ensure outside area is clear suitable forced landing area within range and crew
106. RS AT THE EQUIVALENT EXTENSION FOR 40 KNOTS FOR THE APPROPRIATE ALTITUDE TOLERANCE NOT INCLUDED 140 2 AIRSPEED INDICATOR 120 KNOTS It age 100 INDICATED AIRSPEED att as 2 TE ERES 25 HHHH o N 1333 0001 34n883uUd Figure 5 8 CH 47D FWD and AFT LCT Indicator Scghedule Sheet 2 of 2 5 15 5 16 blank 81 5 41 5 yABYD 4 EH 6 S GAS PRODUCER ROTOR SPEED N PERCENT Sco EJIIS ENENESENNEKNENNE Ss pee LA a eT ILLAE III ee 30 20 10 0 10 20 30 40 50 AMBIENT TEMPERATURE DEG C 78 76 74 ALIN 0Pc 0cSI SS WAL 02 5 61 5 2 10 1 12245 503000 9 200 01 8 anbig 55 1520 240 INTERSTAGE AIR BLEED CLOSURE CHART LONGITUDINAL STICK POSITION NDICATOR INCHES T55 L 712 ROTOR RPM 100 RATE OF CLIMB ZERO CYCLIC TRIM AUTO GROSS WEIGHT STANDARD UNBALLASTED CONFIGURATION Hi er te Lue 1 111 am HARM HITS en REEL EE RI siti EEE a EET EE ae EHE EHE EN 150 60 5o 60 80 100 110 120 130 140 INDICATED AIRSPEED
107. Reset the center hook by hand Apply a force to the tongue of the hook Set CARGO HOOK MASTER to RESET Check that the FWD MID and AFT caution lights are out e Repeat steps 17 e and 17 1 4 22 1 4 22 2 blank Change 12 55 1520 240 f With the handle in the ready vertical position check that all three hooks remain closed Check that the fwd and aft hooks are latched by applying a force to the load beams It may be necessary to relatch the hooks by opening the load beams fully and releasing it 18 Check the FWD and AFT HOOK LOADED lights as follows a On the overhead panel check that the MASTER switch is OFF b At the forward hook rotate the release knob to its maximum clockwise position Pull the hook open The FWD HOOK OPEN caution light shall light c While holding the hook open release the release knob d Allow the hook to close slowly On the overhead panel the FWD HOOK LOADED light shall momentarily come on before the hook is full closed e Pull on the hook to check that it is latched closed If it is not pull the hook fully open and then release it Place the test load on the hook The hook remains closed The FWD HOOK OPEN caution light shall remain on f At the aft hook rotate the release knob to its maximum clockwise position Pull the hook open The AFT HOOK OPEN caution light shall come on 0 While holding the hook open release the release knob h Allow the hook to close s
108. S tT ROTOR SPEED RPM TT TT TT PT Ty TT PEt ERA 63092 Figure 5 11 4 Autorotational RPM Chart for CH 47D 5 23 5 24 blank C25 9c sysc s Sco IN WAI sis euy ouiqun En 1 6 1 T 55 L 712 Turbine Analysis Check Chart 20 10 0 10 AMBIENT TEMPERATURE 34465 ALIN OPC OCST SS WNL T55 L 712 Turbine Engine Analysis Check PTIT Chart TM 55 1520 240 MTF TRE mI m LOWER AND ee ee i mid Ll a m e D ESI prm 122 2721 mami 25 E EE MER e ae xe UPPER BAND LIMIT rey aE 074 TITULUS UA s 33883 2 2 883 PIS aunivHuadw3i LIQNI aii Figure 5 121 Turbine Engine Analysis Check PTIT Chart 5 26 1 5 26 2 blank C25 2 10 AMBIENT TEMPERATURE FAT C A34466 14 292 5 1729 5 Sco anbioy sissqeuy ourqing omnia l 3 3u TORQUE PERCENT E T55 L 712 Turbine Engine Analysis Check Torque Chart e 20 10 20 AMBIENT TEMPERATURE FAT C ALIA OPC 0cSI SS WNL AULI pc 9c s c9cs Sco
109. T cnown 3 FAT e 30 C PRESS ALTITUDE 8800 FT GROSS WEIGHT 3600018 a0 ENTER AT 30 MOVE RIGHT TO 30 PRESS ALTITUDE 8800 FT MOVE DOWN TO GROSS WEIGHT LINE 38 000 18 MOVE LEFT AND 40 READ IAS 148 KT MOVE DOWW TO TEMP LINE 30 C MOVE LEFT AND READ IAS 126 KT USE INSERT GRAPH TO ADJUST TEMP SPEED FOR CHANGE IN GROSS WEIGHT ENTER AT GW 26 000 18 MOVE RIGHT THEN DOWN TO READ INCREMENTAL SPEED INCREASE 4 KT HAS NOW IAS 125 44 0 120 69086 WEIGHT 3800018 USE LOWER VALUE AS IAS 8 129 KT WEIGNT 1000 LO 2 Figure 5 2 Airspeed Operating Limits With Inoperative Cruise Guide Indicator 5 5 5 6 blank 55 1520 240 MTF AIRSPEED OPERATING LIMITS WITH RETRACTED LOUSITUBIMAL CYCLIC Cw Heo EE AA 5 CONOY ALTITUDE 1090 Figure 5 3 Airspeed Operating Limits With Retracted Longitudinal Cyclic Trim 5 7 5 8 blank 6 9 SWI Joyejnuunooy anliy PRESSURE PSI USE LIMITS SET BY BROKEN LINE WHEN OPERATING TEMPERATURES BELOW 25 F ARE ANTICIPATED F 40 20 0 20 40 60 100 120 140 C 29 19 7 4 16 37 49 6 TEMPERATURE D143 201 1 ALIN O02 02S1 SS WL 1 800 rTTITITTITITIM 01 4 syu
110. T beep NO 1 ENGINE to minimum beep using the NO 1 and NO 2 ENGINE BEEPTRIM switch Move NO 2 ECL from GROUND to FLIGHT and allow NO 2 en gine to stabilize Move NO 1 ECL from FLIGHT to GROUND beep NO 2 ENG to 100 rotor rpm using the NO 1 and NO 2 ENGINE BEEP TRIM switch after N 1 has sta bilized record N1 and torque b Beep NO 2 ENG to minimum beep while placing THRUST in ground detent Move NO 1 ECL from GROUND to FLIGHT After NO 1 ENG has stabilized match torques and beep both engines to 100 rrpm c Torque differential should not ex ceed 6 a Both FADEC PRI REV SW PRI Torque Differential Check 2 64 REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont b f 5 1 1 k 1 ENG 2 ECL GND Incr thrust to 5 foot hover Activate Power Assurance Test SW Record TQ DECU value and FAT Without moving the thrust advance ENG 2 ECL FLT ENG 1 ECL GND Activate Power Assurance Test SW Record TQ DECU value and FAT j Advance ENG 1 ECL FLT Land helicopter Difference will be no greater than 696 between ENG 1 and ENG 2TQ values 2 64 1 2 64 2 blank C25 55 1520 24 TROUBLESHOOTING PROCEDURE HOVER Cont 8 Droop Eliminator a b Establish 100 percent rotor rpm in the ground detent AFCS SYSTEM SEL BOTH c Lift off to stabilized hover 15 to
111. TED IN THE MANUAL AND USED UPON RE CEIPT OF THE EARLIER SEQUENCED CHANGE INSURE A MORE CURRENT CHANGE PAGE IS NOT REPLACED WITH A LESS CURRENT PAGE URGENT TM 55 1520 240 MTF C7 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 7 WASHINGTON D C 5 January 1987 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 4 25 and 4 26 4 25 and 4 26 4 26 1 and 4 26 2 4 26 1 and 4 26 2 4 27 and 4 28 4 27 and 4 28 5 1 and 5 2 5 1 and 5 2 5 25 and 5 26 5 25 and 5 26 5 26 1 5 26 2 5 26 1 5 26 2 DEP 5 26 3 5 26 4 URGENT 55 1520 240 7 2 Retain these sheets in front of manual for reference purposes NOTE Laminated pages will be pro vided in next normal change By Order of the Secretary of the Army JOHN A WICKHAM JR General United States Army Chief of Staff Official R L DILWORTH Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 AVUM and AVIM Maintenance re quirements for CH 47D Helicopter Cargo Transport 55 1520 240 C6 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 6 WASHINGTON D C 26 September 1986
112. The left AUX PRESS caution light should come on momentarily then go out Then switch OFF d LEFT AFT MAIN TANK FUEL PUMP switch ON the L and R FUEL PRESS caution light should go out Then switch OFF Check caution lights on e Remaining FUEL PUMPS switches Check as in steps and d above f CROSSFEED FUEL VALVES switch CLOSED 0 Turn LEFT MAIN fuel 1091 016 pump ON Check that the L FUEL PRESS caution light goes out Ob serve R FUEL PRESS caution light stays on There should be no bleed over to pressurize the opposite system LEFT MAIN fuel pump OFF Change 1 2 51 55 1520 240 TROUBLESHOOTING PROCEDURE ENGINE RUN UP Cont h Turn RIGHT MAIN fuel pump ON Check that the R FUEL PRESS caution light goes out Ob serve L FUEL PRESS caution light stays on There should be no bleed over to pressurize the opposite System 4 All FUEL PUMP Switches ON 5 XMSN OIL PRESS and TEMP Indicator Operation a Check individual XMSN OIL PRESS readings Allow able fluctuation of oil pressure readings shall not exceed 10 of actual readings b XMSN OIL PRESS SCAN Reading 3 psi of low transmission c XMSN OIL PRESS TEST Check to 0 psi or below d XMSN OIL PRESS switch SCAN e Check all XMSN OIL TEMP readings f XMSN OIL TEMP SCAN Reading 50 of high temperature xmsn g XMSN OIL TEMP TEST Check to 70 or below Change 12 2 52 REFEREN
113. UMP MAIN switches ON Check L FUEL PRESS caution capsule out XFEED switch OPEN Check R FUEL PRESS caution capsule out ENG COND lever GND d FADEC ENG 1 and FADEC ENG 2 switch PRI FADEC ENG START switch Select first engine to be started and hold until accelerates to 10 Release switch Check and record engine oil pressure 5 PSI minimum Check and record engine acceleration speed to ground idle 50 to 59 within 45 sec 2 Second engine Start by using the same method as the first 2 BELLOWS CHECK 1 First engine a b Engine 1 FADEC PRI REV switch started engine REV FADEC Caution ON N1 Maximum change 3 4 14 1 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE d FADEC PRI REV switch started engine PRI e FADEC FAIL caution OUT f Repeat for Engine 2 G 3 NO 1 AND NO 2 ENGINE REVERSION ARY START Reference TM 55 1520 240 23 NOTE Either engine may be started first CAUTION The flight controls must be manned any time the helicopter is on the ground with the rotors turning 1 First engine Start as follows a L FUEL PUMP MAIN switches 09 ON Check L FUEL PRESS caution capsule out b XFEED switch OPEN Check R 010 FUEL PRESS caution capsule out c ENG COND lever GND d FADEC ENG 1 and FADEC ENG 2 switch REV e FADEC
114. WRSTEER caution light Out 1 Check10 degree deviation maximum in 100 feet 4 switch LOCK Check 5 degree deviation 12 Check power STEERING CONTROL inoperative with SWIVEL at LOCK 2 56 11 2 56 2 blank C20 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE BEFORE HOVER 1 Systems Check indications of the following a Rotor b Torque c Engine d Transmission e Fuel f Master caution panel 2 PARKING BRAKE As re quired 3 AFCS SYSTEM SEL BOTH 4 CYCLIC TRIM AUTO 5 SWIVEL switch LOCK 6 Crew and mission equip mcac Check Monitor all fuel tanks for overpressurization NOTE During the fuel system check observe the following 1 No fuel will be pumped into any AUX tank 2 At 1650 50 pounds the main tank with its pumps on will start receiving fuel from its respective AUX tanks and stop when main tank capacity reaches 1800 50 pounds 2 57 Change 2 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE BEFORE HOVER Cont 7 RH Fuel System Check Start note fuel quantity in all tanks a CROSSFEED FUEL VALVE S OPEN b LH FUEL PUMPS OFF Fuel selector Monitor RH tank fuel level 8 Ground Instability Check a Apply brakes and lift front pou off the ground and check rear rakes b Check flight control response in all axes HOVER NOTE After work has been done on the flight con trol syste
115. Y 100 not configured properly c Faulty KY 100 main processor d Faulty wiring J60 HF radio displays ALE DATA a No ALE data loaded J61 HF radio displays ALE NO KEYS a No ALE keys loaded 3 46 6 Change 24 55 1520 240 362 HF radio displays ECCM NO a No ECCM data loaded J63 HF radio displays NO KEYS a No ECCM keys loaded J64 ZEROIZED advisory not displayed a Faulty receiver transmitter b Faulty control display unit c Faulty wiring J65 ZEROED not displayed nor a tone heard CAUTION KY 100 encryption keys are still loaded handle as classified a Faulty Z AVH control b Faulty main processor c Faulty wiring Change 24 3 46 9 3 46 10 blank PIN 9916611 024 TM 55 1520 240 MTF CER DING GUIDE K AFCS AND CYCLIC RIM CONDITION PROBABLE CAUSE K1 NO 1 and or NO 2 AFCS OFF caution panel light on a Circuit breaker s our b Hydraulic pressure low c Faulty AFCS solenoid valve d Vertical gyro invalid e Faulty AFCS unit or panel switch f Vertical gyro interlock relay malfunction K2 No 1 AFCS or No 2 AFCS system fails to respond normally no AFCS OFF caution panel light on a Faulty caution panel b Faulty AFCS solenoid valve K3 CYCLIC TRIM indicators not in GND position a CYCLIC TRIM in MANUAL position b Proximity switch activated by excessive nosedown attitude light o
116. able TEAC checks within the upper PTIT band shall continue to have the band 1 lower limit Certain engines have performance improvements These engines will be N1 limited and shall be trimmed to the acceptable N1 speed band limits The thermocouple assemblies shall have a resis tance check performed to assure serviceability prior to the initial TEAC baseline Subsequent TEAC checks do not require resistance checks 3 The TEAC performed following Step 2 shall deter mine the engine lower limit baseline A tolerance of 20 C shall be subtracted from the recorded PTIT 4 To determine the lower limit baseline enter figure at the prevailing FAT proceed vertically to a value 20 C less than the measured PTIT The lower limit baseline is identified as the number of degrees above the applicable reference line 1 2 3 or 4 on figure 5 12 1 When the engine lower limit baseline has been determined record the line num ber and the number of degrees above the line in the remarks section of the Historical Record For Aircraft Form 2408 15 TEAC overprint 4 28 1 C16 55 1520 240 Example During the TEAC PTIT was recorded at 800 N1 speed was 103 FAT was 14 PTIT 800 C Tolerance 20 C Engine Lower Limit Baseline 780 C The engine lower limit is 5 C above line 3 at all ambients Record lower limit in the Historical Record For Aircraft as shown below NOTE The purpose of the lower limit is to
117. ages Insert pages 2 37 and 2 38 2 37 and 2 38 2 43 through 2 46 2 43 through 2 46 2 46 1 2 46 2 blank 2 46 1 2 46 2 blank 2 65 and 2 66 2 65 and 2 66 2 77 and 2 78 2 77 and 2 78 3 37 and 3 38 3 37 and 3 38 2 Retain this sheet in front of manual for reference purposes 55 1520 240 C19 By Order of the Secretary of the Army GORDON R SULLIVAN General United States Army Official Chief of Staff 1 H HAMILTON Administrative Assistant to the Secretary of the Army 75 DISTRIBUTION To be distributed in accordance with DA Form 12 31 E block no 0195 requirements for TM 55 1520 240 MTF 55 1520 240 18 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 18 WASHINGTON D C 31 AUGUST 1994 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER DISTRIBUTION STATEMENT Approved for public release distribution is unlimited TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 58 1 2 58 2 blank 2 58 1 2 58 2 blank 2 65 and 2 66 2 65 and 2 66 2 72 1 2 72 2 blank 2 72 1 2 72 2 blank 2 73 and 2 74 2 73 and 2 74 2 Retain this sheet in front of manual for reference purposes 55 1520 240 18 By Order of the Secretary
118. and temperature range markings Refer to table 1 O 15 1 Fuzz burn off module Check for condition and security 2 9 REFERENCE C23 55 1520 24 TROUBLESHOOTING PROCEDURE INTERIOR Cont Aft Cabin Cont O 15 2 AFT POS LIGHT switch Set as required 16 AFT transmission Check as fol lows 17 18 19 a Check for oil level and condition Check filter contamination button in Aft transmission mount bolts Check condition and security Aft sync shaft adapter assemblies lord mounts and support brackets Check for condition security and foreign objects connecting bolts for proper installation Oil cooler Check condition and security Exhaust duct installed Aft transmission oil pressure trans ducer Check condition and se curity f Aft transmission drip pan for proper installation and security Left and right access doors closed before flight Engine tire extinguisher bottles Check squib installation dates and pressure refer to Section V engine fire extinguisher pressure Troop alarm box Check condition Compass flux valve Check security Area clear of stored materials 19 1 Fuel flow power supply Check condition and security C23 2 10 REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE INTERIOR Cont Aft Cabin Cont 20 CROSSFEED FUEL VALVE Check CLOSED electrical plug se cure
119. anels Check condition and security 2 17 REFERENCE C15 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Top of Fuselage Cont 17 18 19 Drive shafting mounts adapter as semblies and support brackets Check for condition security and foreign objects Connecting bolts for proper installation Formation lights Check wiring clear of drive shaft and condition Push pull tubes bellcranks hydrau lic lines and electrical wiring Check condition and security 19 1 Baffles Check condition and se 20 21 22 curity Drive shaft fairing Check secu rity and any looseness of fairings after being secured by fasteners Top of fuselage Check skin con dition VHF antenna and foreign objects removed Forward rotor left side Check as follows a Check lag damper lockouts re moved b Check components for proper safety wiring and security c Check blade lightning protection straps and cables installed on top and bottom of each blade and condition d Check oil in rotor system reser voirs on left side e Check droop stops rain shield and stiffener for condition and security C15 2 18 REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Top of Fuselage Cont f Check pitch change links swashplate slider assembly and drive arm for condition and se curity g Check u
120. ator Schedule Interstage Air Bleed Closure 5 17 Chart 0 CH 47D Cockpit Controls Position D I9 Envelope Autorotational RPM Chart for 5 23 CH 47D 5 17 Turbine Engine Analysis 5 25 Check N1 Chart Turbine Engine Analysis 5 26 1 Check PTIT Chart 5 12 2 Turbine Engine Analysis 52621 Check Torque Chart 5 12 3 Autorotational RRPM Chart 5 26 23 5 1 C25 55 1520 240 FIGURE NUMBER TITLE PAGE 2 4 Power Assurance Test B 26 2 5 Altitude Bands Chart 2 5 Power Assurance Test Maximum Continuous Power Chart 12 d HERE Power Assurance Test Maximum Power Chart 6 22 BE Power Assurance Test 56 26211 Engine Temperature Limits Chart B IZRI Power Assurance Test p 262 13 1 Gas Generator Speed Chart b 12 0 TARAS Power Assurance Test 5262 13 PAT Number Margin to Torque Margin Conversion Chart 5 12 10 NI Idle Check Altitude Bands Chart BIZ 01 Engine Ground Starting 26 2 9 Time vs Ambient Air Temperature Static Sea Level Turbine Engine Analysis Check Troubleshooting Chart 5 T4 Engine Vibration Test Data Sheet 3 27 5 15 Maintenance Test Flight 5 29 Check Sheet C25 5 2 55 1520 240 Look up reading in middle column if in degrees Centrigrade read Fahrenheit equivalent in right hand column if in degrees Fahrenheit read Centrigrade equivalent in left hand column c F 54 65 85 9 84 183 2 266 510 950 538 1000 1632 51 60 76
121. b Hydraulic cooler fan inoperative c Faulty pump d Excessive internal leakage in system component G22 Ramp ramp door will not open and or close a Circuit breaker out b Faulty ramp control valve c Faulty wiring d Faulty RAMP PWR switch 3 35 C22 55 1520 240 TROUBLESHOOTING GUIDE H FLIGHT CONTROLS CONDITION H1 H2 H3 H4 H5 PROBABLE CAUSE Cockpit flight controls immovable 8 No pressure in either flight control hydraulic System b Rigging pins installed Obstructions in the cockpit control linkage or the cockpit transfer bellcranks Thrust control requires excessive force to move a Faulty thrust brake trigger switch b Faulty thrust cockpit controlled driver actuator Binding in flight controls Improper rigging b Low hydraulic pressure c Binding in controls below ILCA d Faulty ilca e Loose bolts Noise when moving controls a Faulty bearing s b Bent connecting link c Distorted bellcrank d Broken support Control movements are binding or jump a Fluctuating hydraulic pressure 3 36 55 1520 240 CONDITION H6 H7 H8 H9 H10 H11 PROBABLE CAUSE b Faulty actuating cylinder high value friction c Binding at rotary wing head controls Control centering will not hold a Faulty magnetic brake or cockpit control driver actuator b Circuit breaker out c Faulty centering spring
122. band 7 The N1 at the bleed band closure point must be within the limits specified on the chart on figure 5 9 8 If adjustment is necessary turn adjusting screw on the fuel control in 1 8 turn increments If the bleed band is closing too soon turn the adjusting screw counterclockwise to increase the N1 speed at which the bleed band closes If the bleed band closes too late turn the adjusting screw clockwise to decrease the N1 at which the bleed band opens 4 15 C15 55 1520 240 The adjustment of the interstate air bleed system shall be recorded in the fuel control service record One full revolution of the adjustment screw equals approximately 5 percent N1 9 EMERG ENG TRIM AUTO to restore normal opera tion if required 10 Repeat steps 1 through 9 for second engine if required 11 Regain 10096 rpm upon completion of check l AFCS CHECK Reference TM 55 1520 240 10 TROUBLESHOOTING PROCEDURE REFERENCE 1 AFCS SYSTEM SEL switch OFF a NO 1 amp NO 2 AFCS cau tion lights ON b Controls centered longi tudinal Neutral on longi tudinal stick position indicator 2 AFCS SYSTEM SEL NO 1 a NO 2 AFCS OFF caution D22 light ON 3 AFCS SYSTEM SEL BOTH a NO 1 amp NO 2 AFCS OFF 019 D21 caution lights off 4 AFCS SYSTEM SEL NO 2 a NO 1 AFCS OFF caution light on U S G P O 1992 654 121 41121 4 16 55 1520 240 TROUBLESHOOTING PR
123. book 4 14 5 C25 55 1520 240 i Minimum acceptable value for the Power Assur ance Test is the PAT Trigger Value and represents a minimum specification engine Compare the results of subsequent to this Trigger Value and enter in the aircraft log book Example A Maximum Continuous Power Check was performed under Ambient Conditions of Altitude Sea Level Temperature 12 C Results ENGINE 2 TORQUE NI Following the Engine Power Check a Power Assurance Test baseline was performed The DECU values were ENG 1 28 ENG 42 28 Entry into the PAT Limits Chart at 12 indicates the maximum continuous N1 Limit is 103 9 Entry into the PAT ENG TEMP Limits Chart at the same temperature shows a PTIT limit of 806 C Thus both engines are operating on the PTIT limit Entry into the PAT Maximum Continuous Power Chart at 12 C and Sea Level shows Maximum Continuous Torque to be 111 The recorded datum shows Engine 1 providing 121 torque The Torque Margin is 121 minus 111 10 Entry into the PAT Number vs Torque Margin chart at 10 Torque Margin and Sea Level shows a PAT Number Margin of 7 Subtracting the PAT Number Margin from the DECU Power Assurance Value yields the PAT Trigger Value PAT Trigger Value 28 minus 7 21 The PAT Trigger Value for ENG 1 is 21 C25 4 14 6 55 1520 240 H INTERSTAGE AIR BLEED SPEED ADJUSTMENT
124. c Increase the thrust rod to set the No 1 engine speed to 92 d Using the No 1 ECL retard the N1 speed to 7096 while maintaining a constant thrust position e Rapidly advance the No 1 ECL to flight while timing the N1 speed acceleration to 90 4 25 C25 55 1520 240 f Repeat the above two steps and numerically aver age the two times The average time from ECL advance to 90 percent N1 shall NOT exceed the values given below OAT Max Time From Deg Celsius 70 N1 to 90 seconds 40 24 30 2 6 20 2 8 10 3 0 0 3 2 10 3 4 20 3 8 30 4 3 40 4 7 6 Place thrust in ground detent position and decrease the No 1 and No 2 engine beep trim switch for 8 seconds h Place the No 2 auto manual switch to the auto position 3 To check acceleration of the No 2 engine repeat the steps of paragraph 2 using the No 1 auto manual switch and the No 2 ECL 4 Upon completion of the acceleration check return both ECLs to flight and RRPM to 100 5 If the average time from ECL advance to 90 percent 1 exceeds the values given above the fuel selector switch must be set to JP 4 or the acceleration schedule adjusted to decrease acceleration time to within limits TURBINE ENGINE ANALYSIS CHECK FERC Reference TM 55 1520 240 23 C25 4 26 55 1520 240 Insure that engine indicating systems are operating properly before performing TEAC 1 Make sure the engin
125. check that both MASTER CAUTION and AFCS OFF caution lights come on 2 72 1 2 72 2 blank C18 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 6 Accelerate to 110 knots and trim the helicopter 7 Set the AFCS switch to BOTH Em and check that both MASTER CAUTION and both AFCS OFF caution lights go out within 20 seconds 7 Speed Sweep Check a Increase and stabilize airspeed at 120 knots 1 Record longitudinal stick posi HI2IK12 tion 2 Check jettisonable doors for se curity and vibration 8 STVA evaluation CAUTION Do not operate the self tuning ab sorber test feature in flight In flight operation may damage the absorber a Stabilize airspeed at 120 knots 1 Check rotor rpm at 100 2 Increase rotor rpm to 102 and start clock FADEC switch In crease RRPM to 102 and start clock Absorbers should retune within 60 seconds Increase and stabilize airspeed at 140 knots 4 Decrease rotor rpm to 9890 and start clock um FADEC NR switch De crease RRPM to 98 and start clock Absorbers should retune within 60 seconds 3 2 73 25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 8 1 Rotor RPM Droop Check and Thrust Rod Slippage Check a Stabilize airspeed at 125 knots straight and level b Rotor rpm 10046 1 Maintaining altitude and direc tion without beeping rotor
126. checkpoints using the CDU 7 Set Mode switch to NAV 8 Depress GPS DOP select button on HSI Mode Select Panel 9 Set Data switch to MSN Depress waypoint key WP until gt is displayed in upper left corner of display meaning destination mode On Page 1 ensure that an arrow 4 is in front of Doppler Only DOP ONLY and GPS Only GPS ONLY on lines 3 and 4 respectively 10 Set the Data switch to OPT a Select the Doppler backup mode on Page 1 Line 1 Back Up displayed C20 2 84 2 TROUBLESHOOTING REFERENCE 55 1520 240 PROCEDURE INFLIGHT Cont b 0 down to Page 3 c Verify an arrow is in front of STATIONARY on line one This means that Stationary operation is not selected An asterisk in front would mean that Stationary operation was selected 11 Set the Data switch to POS Observe that the present position displayed on lines two and three is changing 12 Set the Data switch on the CDU to DIS TG a Select waypoint examination mode by depressing WP key b Open line one of Page 1 and enter waypoint identifier by number alphanumeric name or frequency of the destination CP CP 1 c Verify the values for the distance to go DIS displayed line two and bearing BRG displayed on line four are accurate 2 84 3 TROUBLESHOOTING REFERENCE C 20 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont d Depress WP key
127. craft wiring J31 GPS Alert light is always illuminated a The Threshold value on the Mission MSN page may be set too low Check b Radio Receiver R 2400 A is defective GPS Alert light is defective Check for a short to ground d Faulty aircraft wiring 3 46 1 C 20 932 933 934 J35 TM 55 1520 240MTF GPS system fails to zeroize loaded keys Radio Receiver R 2400 A is defective b GPS zeroize switch is defective c Faulty aircraft wiring GPS system does not accept KYK 13 key load a different KYK 13 key loader b Radio Receiver R 2400 A is defective c Faulty aircraft wiring d Defective receptacle GPS system does not accept Data Loader fill a Try a different Data Loader Module b Radio Receiver R 2400 A is defective c Faulty aircraft wiring d Data Loader receptacle defective No Audio Voice Warning Message heard in Pilot Copilot or Flight Engineer Hoist Operator s headset when altimeter pointer is below or above preset altitude limits pilot s a Audio absent in all above mentioned headsets 1 Faulty altimeter pilot s 2 Check Terminal Board 4 Block 9 3 Check wire between Terminal Board TB4 Block 9 and 195P2 pilot s radar altimeter connector C 20 3 46 2 55 1520 240 b Audio Present in at least one of the headsets 1 Faulty ICS panel s 2 Check wiring between Terminal Board TB4 Block 9 and affected ICS pa
128. d by ambient temperature charts in Section V Low air precharge in apu accumulator 3 5 55 1520 240 TROUBLESHOOTING GUIDE B INSTRUMENTS CONDITION PROBABLE CAUSE B1 Maintenance panel hydraulic pressure indicators inoperative with generators on a HYD PRESS IND circuit breaker out b Faulty wiring B2 No fuel quantity indication at all positions a FUELING STATION PWR switch at ON b FUEL QTY IND circuit breaker out c Faulty indicator d Faulty selector switch e Faulty transmitter unit f Faulty wiring B3 Fuel quantity pointer erratic or static a Faulty selector switch circuit or indicator not aligned with tank selected b Faulty wiring B4 Indicated total does not equal computed total by 420 pounds a Fuel quantity system requires calibration b Faulty selector switch c Faulty tank unit B5 Pilot s or copilot s rotor tachometer indicator in operative a ROTOR TACH circuit breakers out Change 3 3 6 55 1520 240 CONDITION B6 B7 a b d e f g PROBABLE CAUSE b Faulty indicator c Faulty generator d Faulty wiring Greater than 2 split between pilots and copilot s rotor tachometer indicators a Faulty indicators No torque indication Ac or dc circuit breakers out Faulty wiring Faulty indicator Engine failed Transmission clutch failed Faulty engine torque meter system Faulty power supply B
129. deward flight 3 Repeat step 2 flying sidewards in the opposite direc tion 9 1 APCS With the aircraft trimmed in pitch roll and yaw AFCS SYSTEM SEL NO 1 and repeat the tests in steps b thru f Then set AFCS SYSTEM SEL switch to BOTH b Hover check NO 2 AFCS With the aircraft trimmed in pitch roll and yaw AFCS SYSTEM SEL NO 2 and repeat the tests in steps b thru f Then set AFCS SYSTEM SEL switch to BOTH 2 61 Change 12 55 1520 240 PROCEDURE HOVER Cont TROUBLESHOOTING REFERENCE Barometric altitude hold shall not be used in a hover Rotor downwash and turbulence changes the reference pressure to the altitude hold transducer i Radar altitude hold RAD ALT ENGAGED Check segment lighted Check radar altitude hold response while hovering at a known true altitude of at least 25 30 feet Altitude shall be held within 5 feet 1 Displace helicopter approximately 5 feet above known altitude by slipping THRUST CONT do not use mag brake and then ees the THRUST CONT Helicopter shall return to original altitude within 5 feet 2 Repeat test slippin THRUST CONTE P feet below pong altitude and after releasing THRUST CONT note helicopter a to original altitude within 5 eet 3 RAD ALT HOLD OFF 3 Controls positions Refer to Section V a Longitudinal 1 Perform crosswind hover 2 Stick position g indicator Ch
130. e bearings must be re placed to reduce looseness to within the 3 8 inch overall loose ness tolerance 3 Check for control system looseness at forward upper con trols as follows a Apply a manual force of about 10 pounds up and down to connecting link attaching points of right and left bellcranks Refer to TM 55 1520 240 23 Ch 11 b Measure distance that either bellcrank end moves If a bellcrank moves more than 3 8 inch there is excess looseness in this portion of the control system c Isolate the cause of excess looseness Refer to TM 55 1520 240 23 Ch 11 4 Check for control system looseness at the aft upper con trols as follows a Apply a force of about 10 pounds up and down to link attaching points of right and left pylon upper bellcranks Refer to TM 55 1520 240 23 Ch 11 b Measure distance that either bellcrank end moves If a bellcrank moves more than 3 8 inch there is excess looseness in this portion of control system Isolate cause of excess looseness Refer to TM 55 1520 240 23 Ch 11 4 10 55 1520 240 F ROTOR PHASING Reference TM 55 1520 240 23 Improper phasing can result in injury to personnel and serious damage to the helicopter Whenever the rotary wing system has been dephased or compo nents of the drive system except the engine drive shahs or ngine XMSN s have been removed or disconnected the system must be properly phased before the system is operat
131. e follow ing FAT 2 PA 4 14 4 55 1520 240 3 NR 100 4 ENG PTIT 5 NI 6 TQ T FF 1 Recover the engine not being tested Engine passes test if it meets or exceeds torque value from Refer to Section V m Return to step i if required G 5 POWER ASSURANCE TEST PAT BASE LINE AND TRIGGER VALUE After performing a Power Assurance Test at Maximum Con tinuous Power or Maximum Power subtract the required torque from the measured torque to determine Torque Margin Round off to the closest whole number NOTE The PAT Baseline shall be used in conjunction with the Engine Power Check Maximum Maximum Continuous to determine the PAT pass fail trigger value Perform the PAT Base line check as soon as possible after the Engine Power Check 1 Power Assurance Test PAT Baseline and Trigger Value a Stabilize flight with 100 on the ground b Adjust ECLs as required to maintain 60 8096 torque on engine being checked Stabilize for 15 seconds Activate Power Assurance Test Switch Record DECU Power Assurance Value Repeat for the other engine Enter the PAT Number vs Torque Margin Chart Section V with the torque margin determined from the Engine Performance Check to determine the PAT Number Margin h Subtract PAT Number Margin from DECU Power Assurance value to obtain the PAT Trigger Value Enter this value in the aircraft log
132. e trim stops are installed on the N1 controls 4 26 1 4 26 2 blank C16 55 1520 240 2 Set the copilot s altimeter at 29 92 barometric pressure to determine pressure altitude CAUTION To prevent tripping the indicator and starting the timer do not allow the EMERG PWR light to remain on longer than 5 seconds 3 Climb to an altitude where topping can be accomplished at 120 KIAS to 140 KIAS not to exceed Vne at 98 percent rotor rpm NOTE At cold ambient temperatures it may be impracti cal to perform a TEAC due to high pressure altitudes Under these conditions enter a red dash in the aircraft forms and accomplish the TEAC when conditions permit O 4 Be sure the ENG ANTI ICE switch is OFF 5 Using NO 1 amp NO 2 ENGINE BEEP TRIM set rotor speed to 100 percent CAUTION If during the check it becomes necessary to reduce engine power initially reduce power by operating the No 1 amp 2 ENGINE BEEP TRIM switch until rotor speed begins to decrease Then lower thrust Do not lower thrust until rotor rpm begins to decrease or an engine overspeed may occur Also to prevent tripping the indicator and starting the timer do not allow the EMERG PWR light to remain on longer than 5 seconds 6 Raise thrust lever slowly 4 27 C16 55 1520 240 7 Set ENGINE CONDITION LEVER of the engine not being checked to GROUND Maintain 100 percent rotor rpm using NO 1 amp NO 2 ENGINE BEEP
133. eaker out Transmitter disconnected Faulty transmitter Faulty indicator Clogged pressure line or F fitting filter Faulty wiring Engine oil pressure gage reads in opposite direction a Engine oil pressure gage line connected to vent port b Faulty wiring During No 1 start No 2 engine oil pressure indicator reads normal but No 1 does not Indicator connectors reversed Engine oil pressure below 20 psi a Faulty transmitter b Faulty indicator c Clogged oil filter No 2 bearing d Incorrect oil pump relief valve pressure setting No engine oil temperature indication a Circuit breaker out b Faulty indicator c Faulty temperature bulb 3 23 55 1520 240 CONDITION PROBABLE CAUSE E6 Engine oil temperature indicator pointer swings abruptly against upper stop a Faulty or open temperature sensing bulb b Faulty indicator E7 Erratic engine oil temperature indications Intermittent short or open circuit in wiring tempera ture bulb or indicator E8 Engine will not accelerate from ground idle to flight a N1 actuator faulty b Faulty control box c Faulty P 3 air system d Faulty fuel control e Faulty wiring E9 Engine oil pressure fluctuates in excess of 5 psi a Faulty indicator b Faulty pressure transmitter c Main oil filter bypass button out d Faulty oil pump 0 10 Engine anti ice switch on no decrease 1 and no rise in ptit Fli
134. eat steps d thru k for the copilot s control stick CARGO HOOK RELEASE switch m Set the CARGO HOOK MASTER switch to OFF n Place the load on the forward hook o Press and hold the CARGO HOOK RELEASE switch on the hoist operators grip Check that the forward hook remains closed Release the switch p Set the CARGO HOOK switch on the hoist operators panel to ARM Press the CARGO HOOK RELEASE switch on the hoist operators grip Check that the hook remains closed q Set the CARGO HOOK MASTER switch on the overhead panel to ARM Set the CARGO HOOK switch on the hoist operator s panel to RMTE Press and hold the CARGO HOOK RELEASE switch on the hoist operators grip Check that the forward hook remains closed Release the CARGO HOOK RELEASE switch 4 19 TM 55 1520 240 MTF r Set the CARGO HOOK switch on the hoist operator s panel co ARM Press and release the CARGO HOOK RELEASE switch on the hoist operator s grip Check that the forward hook opens and closes Check that the FORWARD HOOK OPEN and the MASTER CAUTION lights are lit Momentarily set the CARGO HOOK switch on the hoist operator s panel to RESET Check that the FORWARD HOOK OPEN and the MASTER CAUTION lights go out 12 Check normal operation of the mid hook and MID HOOK OPEN caution lights as follows a Turn the HOOK SELECT switch on the CARGO HOOK control panel to MID b Repeat steps 11 d thru 11 r for center hook operation 13 Check normal operation of the
135. eck N 14 inch b Lateral 1 Hover into the wind C15 2 62 121 K 12 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont 2 Measure position from H 13 copilot s door post placard 3 O to inch right of neutral position c Directional 1 Hover into the wind 2 Measure pedal separation 3 inch maximum separation Page 2 62 1 2 62 2 blank Change 12 55 1520 240 TROUBLESHOOTING PROCEDURE HOVER Cont 4 75 6 7 Land helicopter THRUST CONT ground detent RH Fuel System check Stop note fuel quantity in all tanks LH Fuel System CHECK START note fuel quantity in all tanks a LH FUEL PUMPS ON b CROSSFEED FUEL VALVES Recheck OPEN Flight Engineer Response c RH FUEL PUMPS OFF d Fuel selector Monitor LH fuel tank level Torque Differential Check a Recheck rotor rpm at 100 2 63 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE HOVER Cont C25 1 Move NO 2 ECL from FLIGHT to GROUND Using the No 1 and No 2 ENGINE BEEP TRIM switch beep NO 1 en gine to 100 rotor rpm In crease THRUST to point where aircraft is light on the gear and a minimum of 60 SINGLE ENGINE TORQUE is indi cated Forward landing gear may be off the ground Maintain operating rpm with beep After N1 has stabilized record N1 and torque 2 Maintaining a constant THRUS
136. eck that the MASTER CAUTION lights are on 6 Release the EMERG REL ALL switch Check all three hooks are closed and that FWD and AFT HOOK OPEN caution lights remain on 7 Place HOOK MASTER switch to RESET Check all hooks closed 8 Recharge the center hook Replace the loads on the forward and aft hooks 9 Check all caution lights are out f Set the HOOK MASTER switch to ARM g Set the EMERG REL ALL switch to REL ALL Repeat step e 4 21 TM 55 1520 240 MTF 17 Check the cargo book cabin manual release as follows a Set the CARGO HOOK MASTER switch to ARM Do not operate the center hook from the cock it during the following test Damage to the hook can result b Apply 10 to 20 pounds of force to the hook tongue c Pull the center hook emergency release handle Check that the force on the handle to open the hook is less than 20 pounds Check that the MID HOOK OPEN and the MASTER CAUTION lights are on When the center cargo hook is opened using the manual emergency release handle the hook must be closed manually No attempt should be made to close the hook using the normal hydraulic or pneu matic method since damage to the cargo hook can result d Reset the hook by hand Apply a force to the tongue of the hook Set CARGO HOOK MASTER to RESET Check that the MID HOOK OPEN caution light is out e Rotate the hook to the right until the upper attach ment fitting contacts the support beam Be sure the h
137. ect button on HSI Mode Select Panel 10 To display Ply To destination number depress the INC key or DEC key or depress the first number key and the second number key 11 Ply shortest J39 distance to first destination from present position set DISPLAY switch to DIST BRG TIME position and steer helicopter to bearing displayed As an aid to maintaining course set DISPLAY switch to XTK TKE position and steer the helicopter to keep track angle error TKE nominally zero If the display indicates a L left TKE the aircraft must be flown to the left to zero the error 2 84 9 21 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE 12 At the first destination set DISPLAY switch to PP and KYBD key is depressed and released note the position altitude and magnetic variation 13 Fly to the remaining destinations using the procedures described in 11 and 12 above 14 Return to ground station o DGNS Flight Test Data Analysis Compare all MARK positions with the actual positions of the corres ponding Check Point Compare differences if any with Allowable Navigation Error Limits outlined in TM 11 5841 305 12 If errors exceed the Allowable Navigation Error Limits use the self test of the GPS system and fault isolation procedures to determine the failure mode 21 2 84 10 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont p Zeroizing loaded keys from
138. ed The method of check ing or obtaining proper phase relationship of the rotors is given in the above reference wAnNING phasing requires alignment of the swiveling actua tors with the rotating swashplates Do not perform any alignments using pivoting actuators The swiveling actuator on the forward rotor is located on the left side of the swashplate and the swiveling actuator on the aft rotor is on the right side of the swashplate NOTE Phasing the rotary wing system shall be accom plished with a minimum crew of two one crewman to install the phasing blocks and one to turn the for ward rotor blades 1 Rotor Phasing a Obtain two phasing blocks If necessary locally manufacture them from aluminum alloy sheet 3 8 inch thick b Gain access to the right side of the aft swashplate Rotate the rotor head to align a pitch link lug on the rotating swashplate with the upper flange of the swiveling actuator c Install one phasing block over the lug and the flange Leave it in place 4 11 55 1520 240 d Gain access to the left side of the forward swash plate If the rotor system is properly phased a pitch lug on the rotating swashplate will align with the upper flange of the swiveling actuator Install a phasing block over the lug and flange to verify alignment e If the lug and flange are not in alignment the rotor system must be phased Refer to TM 55 1520 240 23 for procedures NO 1 AN
139. ering release switch on co pilot s cyclic HDG switch shall release 7 bad step 3 for co pilot s HSI 8 Depress CMD SEL switch on pilot s mode select panel HDG switch shall release AY Engage HDG switch Depress HDG switch to insure it will release j Barometric altitude hold test TROUBLESHOOTING REFERENCE PROCEDURE TM 55 1520 240 MTF TROUBLESHOOTING REFERENCE IN FLIGHT Cont 1 BARO ALT ENGAGED 2 Note ENGAGED switch lighted Trim to level flight at a selected altitude Then without THRUST CONT magnetic brake switch increase alti tude by 75 feet by pulling against the brake Release RUST CONT The heli copter shall then return to the selected altitude within 25 feet in not more than 30 seconds Repeat this step re ducing altitude 75 feet below selected altitude Release THRUST CONT The heli copter shall return as above Press the BARO ALT EN GAGED switch to disengage altitude hold k DASH Actuator Low Rate Op eration Check 1 2 3 4 Trim helicopter at 110 knots Set the AFCS switch to ei ther OFF position Check that both MASTURE CAU TION and NO 1 and NO 2 AFCS OFF caution lights come on then reset MAS TER CAUTION lights Slow to 90 knots and trim the helicopter Set the AFCS switch to BOTH and check that both AFCS OFF caution lights go out within 20 seconds Reset the AFCS switch to either OFF position and
140. ero 6 Test switch Extend 7 Test switch Retract AVG METER TIME INT TEMPERATURE DEFLECTION SECONDS 10 C and above 05 to 20 50 to 300 20C to 10C 04 to 20 50 10 360 55 C to 20C 02 to 20 50 to 480 8 Selector switch Center 9 Repeat steps 5 thru 7 10 Selector switch Right 11 Repeat steps 5 thru 7 12 Selector switch off Change 2 4 4 55 1520 240 CONTROL BREAKOUT FORCES Reference TM 55 1520 240 23 The control breakout forces check is intended to detect improper installation of close tolerance bolts overtorqued hardware or dirty bearings NOTE A push pull type fish scale can be used to check these forces All forces measured from zero stick position and magnetic brake on 1 Longitudinal forward and aft 1 8 to 2 5 Ib Breakout force forward must be greater than breakout force aft 2 Lateral left and right 1 2 to 2 Ib 3 Directional left and right 7 to 12 4 4 1 4 4 2 blank Change 12 55 1520 240 4 THRUST CONTROL SYSTEM POUNDS MEASURE MAG BRAKE DIRECTION REQUIRED MENT NOTE Thrust breakout to be measured when output rod of lower boost actuator starts to move Switch depressed and taped down Breakout forces up and down must be within 1 5 lbs of each other 5 ENGINE CONDITION levers a Move either lever to a position between GROUND and FLIGHT b Position scale below lever knob Force required to move lever 4 to 5
141. est perform the following Start apu and apply electrical and hydraulic power b Claw all circuit breakers c AFCS SYSTEM SEL NO 1 or NO 2 do not select BOTH d CYCLIC TRIM AUTO stick and directional pedals Center f STEERING CONTROL panel Knob centered g SWIVEL switch LOCK b Radar altimeter Set LO knob to 100 feet i Heading bug to bending of helicopter then 30 clockwise j ENG CONDITION levers STOP k Ensure left and right aft lending gear is in ground contact Not on jacks The bite check results in flight control motions Keep bonds and body clear moving controls Severe injury can occur 55 1520 240 2 Press and release the bite switch on the AFCS computer for the system to be tested A light in the push button switch will flash to show that the test is in progress The digital dis play will indicate the test number of the current circuit under test Should a failure be present the flashing light will turn to a steady glow 20 seconds after the failure is detected Bite test numbers 0 1 2 and 3 are bite tests allocated to the self check ing of reinterrogation circuits When bite is initiated it will run quickly thru these first tests and after approximately 20 seconds the flashing light will become steady with 3 shown in the digital display Press and release thc bite switch again to allow the test to proceed 3 If a failure occurs record the number
142. etary of the Army CARL E VUONO General United States Army Chief of Staff Official R L DILWORTH Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF requirements for CH 47D Helicopter Cargo Transport 55 1520 240 C9 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 9 WASHINGTON D C 8 December 1987 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indicated below New or changed test material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages i and ii i and ii 2 1 and 2 2 2 1 and 2 2 2 7 through 2 10 2 7 through 2 10 2 31 and 2 32 2 31 and 2 32 2 37 and 2 38 2 37 and 2 38 2 43 through 2 46 2 43 through 2 46 2 58 and 2 54 2 58 and 2 54 2 59 and 2 60 2 59 and 2 60 2 67 and 2 68 2 67 and 2 68 2 75 and 2 76 2 75 and 2 76 2 85 through 2 88 2 85 through 2 88 4 1 and 4 2 4 1 and 4 2 4 13 and 4 14 4 13 and 4 14 4 25 and 4 26 4 25 and 4 26 4 26 1 and 4 26 2 4 26 1 and 4 26 2 55 1520 240 C 9 Remove pages Insert pages 4 27 through 4 30 4 27 4 31 and 4 32 4 31 through 4 42 5 1 and 5 2 5 1 5 2 5 25 5 26 5 25 5 26 5 26 1 5 26 2 5 26 1 5 26 2 5 26 3 5 26 4 5 26 3 5 26 4 2 Retain these sheets in front of manua
143. ft vertical shaft and support structure for con dition and security 5 Check top of aft transmission for condition and leakage 6 Check thrust deck air baffles for security 6 1 CGI signal processor Check elec trical connections and security 7 Anticollision and formation lights Check condition 8 Aft pylon fairing Check condi tion and security right side 9 Right aft work parom and inspec tion panels Check condition security 10 Combining transmission area Check as follows a Chip detector Check condi tion and security g C15 2 14 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Top of Fuselage Cont c Push pull tubes bellcranks and rod end bearing Check condi tion and security Sync shaft and adapter Check condition Engine to transmission drive shafting For three piece drive shaft check indexed properly condition and security For one piece driveshaft check for condi tion and security Oil level Check engine and combining transmission sight gage Oil filters and contamination but tons Check both engines and combining transmissions Oil pressure transducers and temp bulbs Installed properly Transmission fan exhaust duct Check for cooler fan and stator blades retainer nut obstructions and debris Oil coolers and lines Condi tion security and FOD Chec
144. ght engineer check for valve activation by feel etc a Faulty switch b Faulty valve s c System blocked 3 24 C13 55 1520 240 CONDITION PROBABLE CAUSE E11 Droop greater than 295 a Droop potentiometers improperly adjusted b C Faulty droop potentiometers Engine N2 actuator improperly rigged E12 Minimum beep does not roach required rpm a Minimum beep trim resistor out of adjustment b Engine N2 actuator improperly rigged E13 Unable to adjust minimum beep a N2 engine controls improperly rigged b Minimum beep trim resistor faulty C Fuel control minimum 2 stop set too high E14 Low engine oil pressure ECL s flight a b C Faulty indicator Faulty transmitter Oil pump out of adjustment Clogged oil line s Main oil filter bypass button out Internal oil leak in engine 3 25 55 1520 240 TROUBLESHOOTING GUIDE F POWERTRAIN CONDITION F1 F2 F3 F4 PROBABLE CAUSE Transmission oil pressure indicating system in operative a Circuit breaker out b Faulty selector switch c Faulty indicator d Faulty pressure transmitter e Faulty wiring Transmission oil pressure does not indicate above 7 psi during start a Faulty pressure transducer b Faulty indicator c Faulty wiring d Low service level Indicator goes to 0 when selecting one individual transmission a SCAN selector sw
145. gyro e Faulty HSI J10 VHF AM FM radio inoperative a Circuit breaker out 3 42 55 1520 240 CONDITION J11 J12 J13 J14 J15 PROBABLE CAUSE b Faulty radio set c Faulty antenna FM homing will not center always gives full right or left deflection a Faulty antenna b Faulty signal comparator c Faulty quadrature hybria module d Faulty receiver HSI compass card will not hold sync a Faulty control b Faulty gyro c Faulty flux valve d Faulty indicator VOR course deviation indicator does not give 10 sweep a Receiver requires adjustment b Faulty indicator ADF will not home a Circuit breaker out b Faulty receiver Marker beacon functions inoperative a VOR circuit breaker out b Faulty MB SENS switch 3 43 55 1520 240 CONDITION PROBABLE CAUSE c Faulty AN ARN 123 receiver d Faulty control pastel J16 VOR inoperative a VOR circuit breaker s out b Faulty AN ARN 123 receiver c Faulty antenna d Faulty control panel J17 Transponder inoperative a Circuit breaker out b Faulty fuse c Faulty transponder J18 Radar warning system inoperative a RADAR WARN circuit breaker out b Defective antenna s c Defective indicator d Defective comparator e Defective control Defective receiver 3 44 55 1520 240 J19 HF 1 000 cps tone is not heard when radio trigger swi
146. he aircraft descends below 200 feet AGL 3 Verify the radar altitude AGL analog bar on the DU matches the AN APN 209 h Warnings and messages check 1 CARGO HOOK MSTR SWITCH ARM 2 HOOK SEL switch Rotate to hook to be re leased 3 CARGO HOOK RELEASE switch Press and release 4 Verify DU hook message is on b CCU BIT ACK switch ACK Verify DU hook message extinguishes 6 Land aircraft 7 Verify DU MEM message is on 8 APU CONTR switch ON Verify the DU MST message is on 9 APU CONTR switch OFF Verify DU MST message extinguishes 10 CCU BIT ACK switch ACK Verify DU MEM message extinguishes 11 HUD OFF U S GOVERNMENT PRINTING OFFICE 1998 637 411 80009 4 41 4 42 blank C22 55 1520 240 SECTION V CHARTS AND FORMS 1 GENERAL This section contains the necessary charts and forms required to ascertain that the aircraft is performing to established standards and to record readings pressures rpm etc obtained during maintenance test flight 2 LIST OF CHARTS FIGURE NUMBER TITLE PAGE Temperature Conversion Chart 5 3 5 2 Airspeed Operating Limits with 5 5 Inoperative CGI 3 3 Airspeed Operating Limits with 5 7 Retracted LCT 5 4 APU Start Accumulator Precharge 5 9 Limits Flight Utility Power Steering Accu mulator Precharge Limits Brake Accumulator Precharge Lim its Engine Fire Extinguisher Pressures 5 81 CH 47D FWD and AFT LCT Indic
147. hile trimmed level operate the four way conical switch on the control stick grip to the right to attain a 20 bank angle The aircraft shall respond smoothly to beep inputs The system shall the attitude acquired within 15 2 Operate the four way switch to the left to attain a 20 left bank angle The system shall hold this angle within 5 3 Return aircraft to level trimmed flight using the roll beep trim switch g Repeat steps 2d through 2f first with NO 1 then NO 2 AFCS selected h AFCS SYS SEL BOTH Heading select test Check as follows 1 Trim to level flight at 110 kts Set the cursor on the Pilots HSI indicator 45 to the right Engage pilot s CMD 55 1520 240 PROCEDURE IN FLIGHT Cont SEL switch on the HSI mode select panel press the AFCS HDG switch to engage Helicopter shall enter into a standard rate turn and shall roll out smoothly onto the selected heading and maintain this heading within 5 2 Depress centerin release switch on pilot s cyclic HD switch shall release 3 Set the cursor on the pilots HSI 45 to the left Engage HDG switch Helicopter shall enter into a standard rate turn to the left and shall roll out smoothly onto the selected heading It shall maintain the new heading 5 4 Select CMD SEL on co pilot s mode select panel HDG switch shall release 5 Repeat step 1 for co pilot s HSI e 6 Depress cent
148. ications and Blank Forms or DA Form 2028 2 located in the back of the ap plicable operators manual when using the 2028 2 from the operator s manual ensure the publication number and title reflect this MTF direct to Commander U S Army Aviation and Missile Command ATTN AMSAM MMC LS LP Redstone Arsenal AL 35898 5230 A reply will be furnished to you You may also send in your com ments electronically to our e mail address Is Ip redstone army mil or by fax 205 842 6546 DSN 788 6546 Instruc tions for sending an electronic 2028 may be found at the back of the Aircraft Operator s manual TABLE OF CONTENTS SECTION PAGE Introduction Ii Maintenance Test Right Checklist 2 1 Prior to Maintenance Test flight 2 2 Interior 2 5 Forward Cabin 2 5 AR Cabin 2 6 Exterior Aft Cabin 2 11 Top of Fuselage Right Cabin 2 20 Forward Cabin Left Cabin Before Starting Engines Starting Engines o 4 Engine Run Up 48 2 55 Before Hover Hover Before Takeoff Cruise In Flight Before Landing After landing Engine Shutdown i C21 55 1520 240 TABLE CONTENTS Continued SECTION Troubleshooting Troubleshooting Starting Includes APU Troubleshooting Instruments Troubleshooting Electrical Troubleshooting Caution Panel Troubleshooting Powerplant Troubleshooting Guide F Powertrain Troubleshooting
149. if required Disconnect electrical connectors from DASH actuator Change 12 2 4 55 1520 240 PROCEDURE PRIOR TO MAINTENANCE TEST FLIGHT Cont Before Interior Check Cont 18 Flight Controls Neutral THRUST ground detent If Neutral Rig Check not performed 19 Flight control looseness Check See 19 1 HF Radio Setup AN ARC 220 Turn Radio Set function switch to STAY and allow system to go thru self tests SYSTEM TESTING is displayed during test and SYSTEM GO if system passes 19 2 Perform data and key fills and setup as necessary LOADING is displayed during and LOAD COMPLETE after successful fill 19 3 Turn HF radio OFF 19 4 TSEC KY 100 Setup Turn system ON load keys and set up as necessary pass tone is heard in headset and KEY N where N is the key location displayed on Z AVH for a successful load 19 5 Turn OFF 2 5 TROUBLESHOOTING REFERENCE J41 42 43 44 45 46 J47 48 J49 50 51 Change 24 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE INTERIOR Cont 20 POWER XFR NO I and POWER XFR NO 2 switches OFF Check NO I and NO 2 HYD FLT CONTR caution lights on 2 APU GEN switch Off Check NO I and NO 2 RECT Off caution lights on 22 APU START switch OFF Check APU ON caution light out 23 switch OFF INTERIOR Forward Cabin 1 Hight Control Closet a Hydraulic lines Chec
150. ight Engineer b EAPS ENG 1 DOORS switch 36 OPEN Check both doors open and BYPASS DOORS OPEN light is on Flight Engineer c EAPS ENG 1 DOORS switch CLOSE Check both doors closed and BYPASS DOORS OPEN light is off Flight Engineer d Repeat steps b and c for EAPS ENG 2 C21 2 38 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 18 CARGO HOOKS WINCH Check operation Refer to 18 1 CARGO RAMP AND DOOR Check operation Refer to F 19 Lights flight engineer WARNING NVG Helicopters have an infrared filter on co pilots searchlight Check filament operation for presence of heat Do not touch or look direct ly into light a SLT FIL switch ON C17 1 Light EXTEND RETRACT and rotation from both THRUST CONT positions 2 PLT and CO PLT SLT CONT AUTO RETR Check operation from both switches 3 Searchlight Set as desired and OFF b ANTI COLL LTS TOP and c POSITION and FORMATION LTS Check operation then OFF Operate rheostat to vary FORMATION LT intensity from DIM to BRT d Cockpit PRESS TO TEST lights Check Table 2 2 2 38 1 2 38 2 blank C22 55 1520 240 Table 2 2 Cockpit PRESS TO TEST Caution Lights Overhead Panel Land R AUX FUEL PRESS 2 2 ENG 1 and 2 STARTER ON 2 3 Deleted 4 FWD and AFT HOOK LOADED 2 Center Instrument Panel 1
151. in atong measure tay Pedal separation in b Lateral measure in Pedal separation in Alrapeed incioatore sicr motSpeed rwo AFT E etegmesr i WReaRevibcK o teng measure in Coordnatedums 4wek ewucrmw exr tong measure m onmo SS check 0 8 Peai separation c E ie Heaaing select Peal separation eeano acr noo noasHtowratecheck TM 55 1520 240 MTF 10 Engine TEAC entry TQ a Engine Topping No 1 2 13 Record Instrument Indications FAT Pressure altitude ft Torque No 1 No 2 PTIT Eng E 3 TORQUE FAT PRES ALT 11 0 Power Assurance Test a FAT C ine oil temp EE L ew s 6 art m Reng P mpencine2 Hydraulic boost Flight Engineer 12 amp Comm NO 1 NO 2 psi Utility psi BEFORE LANDING AFTER LANDING ENGINE SHUTDOWN 1 Coastdown time c HSI and Mag Compass e ILS f ADF ANT LOOP g Marker Beacon HIGH amp LOW h Transponder
152. in front of manual for reference purposes NOTE Laminated pages will be pro vided in next normal change URGENT 55 1520 240 4 By Order of the Secretary of the Army JOHN A WICKHAM JR General United States Army Chief of Staff Official MILDRED E HEDBERG Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF requirements for CH 47D Helicopter Cargo Transport 55 1520 240 maintenance test flight is an xceptionally de manding operation and requires a thorough flight readiness Inspection PREFLIGHT The flight readiness inspection is prescribed in TM 55 1520 240 10 operators manual and must be completed prior to each maintenance test flight Emergency procedures are found in the applicable 10 or checklist CL and are not duplicated in this publication Prior o ach maintenance test flight the pilot will contact maintenance quality control personnel to determine the maintenance that has been performed This manual should be used only by qualified maintenance test flight pilots as re quired in AR95 1 and TM 55 1500 328 25 a b blank 55 1520 240 REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS You can help improve this manual If you find any mistakes or if you know of any way to improve the procedures please let us know Mail your letter DA Form 2028 Recommended Changes to Publ
153. itch change links must be adjusted 1 RRPM 2 PA C25 2 76 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 3 FAT 4 Fuel quantity 5 Pedals 2 inches maximum separation f Note any abnormal vibrations NOTE Autorotation above 102 RRPM will be accompanied by an overall increase in vibration 6 Prior to reaching 1000 feet AGL make a power recovery h Reestablish 10096 RRPM safe air speed and altitude i FADEC RRPM Switch 100 j Compare data to chart in for proper RRPM 13 HE Engine TEAC check if required Section IV 13 1 839 Power Assurance Test if re quired 4 Fuel consumption check STOP 15 Navigation and Communication a UHF 1 Transmit and receive 2 Preset and manual tune J10 3 Check both a high and low frequency e g over 300 MHz and under 300 MHz b VHF AM FM 1 Transmit and receive 2 76 1 2 76 2 blank C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 2 Check both AM and FM bands at high medium and low frequencies 3 FM Homing MODE SEL DF b HSI MODE SELECT panel FM SEL check FM SEL lit c Course deviation bar on HSI Check response in turns d TO FROM arrows concealed on HSI e GS and NAV OFF flags concealed on HSI c HSI and Magnetic Com J12 pass 1 HSI synchronized 2 Magnetic compass 5 of HSI
154. itch set midway between se lections b Faulty transducer c Faulty wiring Pressure on low individual indication exceeds the 3 psi of scan indication a Faulty indicator b Faulty selector switch c Faulty pressure transmitter 3 26 55 1520 240 CONDITION F5 F6 7 8 9 PROBABLE CAUSE Indicator does not move when selecting the test posi tion a Faulty pressure transducer b Faulty switch c Faulty indicator Transmission oil pressure reading too high or too low a Faulty pressure transducer b Faulty selector switch c Faulty wiring d Faulty indicator Fluctuation is more than 10 of actual reading 1 a Faulty pressure transducer b Faulty pressure relief valve c Faulty wiring Transmission oil temperature indicating system inoperative a Circuit breaker out b Faulty indicator c Faulty selector switch d Faulty wiring Transmission oil temperature indication too high or too low a Faulty temperature bulb b Faulty selector switch 3 27 Change 12 55 1520 240 MTF CONDITION F10 F11 F12 F13 PROBABLE CAUSE c Faulty wiring d Low service level e Faulty oil cooler bypass valve f Obstructed oil cooler temperature too high One transmission oil temperature does not indicate when selected a Faulty indicator b Faulty temperature bulb c Faulty selector switch d Faulty wiring Te
155. ity f If EAPS is installed check EAPS to fairing mating surface for evidence of wear or chafing 13 Aft rotor left side Check as follows a Check lag damper lockouts removed b Check components for proper safety wiring and security Check blade lightning protection straps and cables installed on top and bottom of each blade and condition d X Check oil in rotor system reservoirs on left side 2 16 1 2 16 2 blank C17 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Top of Fuselage Cont 14 15 16 e Check droop stop weights and return mechanism and droop stops for condition and security f Check droop stop shrouds for condition and security if in stalled g Check rain shield and stiffener for condition and security h Check pitch change links swash plate slider assembly and drive arm for condition and security Check upper boost actuator and pilot valve for proper connec tions condition security leak age and extended jam indica tors Check aft longitudinal cyclic trim actuator for condition and secu rity k Cruise guide link and processor Check for condition and secu rity Check thrust bearing and thrust bearing mount bolts aft vertical shaft and support structure for con dition and security Aft pylon fairing Check condi tion and security left side Left aft work platform and inspec tion p
156. k for leaks and security b Ilca 4 Check condition security and for extended jam indicators Check area for foreign objects c Blectrical wiring and lugs Check condition and security NOTE If Mechanical Rig is to be performed electrical connectors disconnected and secured d Dash actuator Check electrical connections condition and security Change 24 2 6 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE INTERIOR Cont Forward Cabin Cont e Flight controls Check all push pull tubes actuators mag netic brakes and viscous dampers for condition and security Rigging pins removed f Fwd transmission tempera ture bulb and chip detector Check for proper installation Fwd transmission Check filter button in and oil cooler condition 2 Troop commander s seat and belt Check condition and security 3 Cabin and ramp lights fwd control switch 3 Check operation 4 Interior Check for loose equipment and stowed 5 Heater compartment Check security of components vibrator contact position and ignition circuit fuse a STVA test box Check b STVA switch OFF 2 6 1 Change 24 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE INTERIOR Cont c Winch and winch accessories Check security and proper storage 6 Cabin Door a Condition Check b Upper section escape panel Check security and condition of seals
157. k No 2 and utility hydraulic exhaust coolers for condition se curity and FOD Combining transmission access doors Check condition seal around exhaust duct when doors are closed and security 11 Perform rotor phasing check Sec 2 19 REFERENCE C15 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Top of Fuselage Cont C25 12 No 1 engine Check as follows NOTE If TEAC PAT is to be performed all preflight inspection requirements checks required prior to TEAC PAT must be accomplished In this case EAPS must be moved forward of the engine to gain access for inspection If TEAC PAT is not required EAPS will remain locked into position in front of the engine a Inlet for foreign objects and condi tion If FOD screens are installed check security and condition O 1 EAPS for general condition Check vortex tubes for erosion and damage Check seals for condition Check rail and slide mechanisms CAUTION If engine is to be operated with the engine transmission fairing removed be sure barrel nuts are secured or removed b Oil level and cap secured c Tailpipe and diffuser for cracks hot spots and security d Power turbine section Check upper portion of engine for condi tion security and leaks 2 16 TM 55 1520 240 MTF PROCEDURE TROUBLESHOOTING REFERENCE EXTERIOR Cont Top of Fuselage Cont e Engine faking condition and secur
158. k as follows O 1 EAPS ENG 1 and ENG 2 FAN switches OFF 1 1 ENG BEEPTRIM switch No 1 and 2 Full decrease 2 49 C25 55 1520 240 TROUBLESHOOTING PROCEDURE ENGINE RUN UP Cont 2 3 4 5 6 7 8 ENGINE CONDITION lever of either engine GROUND Other ENGINE CONDITION lever Slowly move toward GROUND until rotor rpm is 88 Hold this rpm for 7 sec onds Ensure both GEN Off caution lights remain out Continue reducing rpm with the ENGINE CONDITION lever until rpm is 82 and check that NO 1 and NO 2 GEN OFF and REC OFF caution lights are on ENGINE CONDITION levers FLIGHT Check NO 1 and NO 2 GEN OFF and REC OFF caution lights out NO 1 amp NO 2 ENGINE BEEP TRIM switch set 100 rotor rpm EAPS ENG and ENG 2 FAN switches ON one at a time c Differential current protection cir cuit Check as required Refer to Section IV 2 1 Transponder Master Switch STBY Check TEST MON NO GO light on within 30 seconds Check PRESS TO TEST lights C25 2 50 REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont 3 FUEL PUMPS and 1 CROSSFEED VALVES Operation a CROSSFEED FUEL VALVES switch OPEN b FUEL PUMP switches D16 All OFF both L and R FUEL PRESS caution lights should be on Check fuel pumps one at a time as follows c LEFT AFT AUX TANK FUEL PUMP switch ON
159. l for reference purposes By Order of the Secretary of the Army CARL E VUONO General United States Army Official Chief of Staff R L DILWORTH Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF requirements for CH 47D Helicopter Cargo Transport URGENT TM 55 1520 240 MTF C 8 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 8 WASHINGTON D C 1 May 1987 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 37 and 2 38 2 37 and 2 38 2 85 and 2 86 2 85 and 2 86 2 Retain these sheets in front of manual for reference purposes NOTE Laminated pages will be pro vialed in next normal change URGENT 55 1520 240 C 8 By Order of the Secretary of the Army JOHN A WICKHAM JR General United States Army Chief of Staff Official R L DILWORTH Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF requirements for CH 47D Helicopter Cargo Transport NOTICE THIS CHANGE HAS BEEN PRINTED AND DISTRIBUTED OUT OF SEQUENCE IT SHOULD BE INSER
160. loor structure when pedals are in the rearmost ad justment position and full pedal travel is made in either left or right direction NOTE This contact is permissible provided the yaw bellcrank in the first stage mixing unit has al ready contacted its stop Change 12 2 42 55 1520 240 PROCEDURE TROUBLESHOOTING REFERENCE STARTING ENGINES Cont 2 The cyclic stick contact with Hi the pedal adjust lever is also possible and permissible with the above pedal conditions 3 Reset pedals for flight b Pedal adjustment Matched c Obtain neutral pedal measure ment d Set cyclic to placard measure ment Ensure position indicator is 1 in e Control Breakout Forces See H10 Section IV FLT CONTR HYDRAULIC H3 H5 switch BOTH With slow smooth flight control inputs check each axis individual ly for smoothness of operation and full travel While mixing pitch roll and yaw axis control inputs check for smoothness of operation Check for a minimum cyclic stick travel of 7 inches forward and 4 inches aft 2 42 1 2 42 2 blank C26 55 1520 240 PROCEDURE TROUBLESHOOTING REFERENCE STARTING ENGINES Cont NOTE Mixing of flight control inputs during ground operation on single hydraulic system should be avoided 1 FLT CONTR HYDRAULIC switch to NO Check as follows a NO 2 HYD FLT CONTR D7 D8 612 caution light ON b FLT CONTR NO 2 PRES SURE indicator
161. lose when FIRE CONTROL handle is pulled out a Faulty T handle microswitch b Faulty valve c Faulty wiring Crossfeed valve does not open when switch is placed to on a Circuit breaker out 3 15 55 1520 240 CONDITION C28 C29 C30 C31 PROBABLE CAUSE b Faulty switch c Faulty valve d Faulty wiring Pilot s and or copilot s normal or emergency engine beep trim switches inoperative Circuit breaker out p b Faulty switch c Faulty wiring d Faulty remote positioning control box While beeping engines to match torque No 1 engine beeps up much faster than No 2 causing an excessive torque split and No 1 engine must be beeped in the opposite direction to match torques engine stabilized torques matched a Excessive difference in N2 actuator speeds between No 1 and No 2 engines b Faulty N2 actuator c Faulty remote positioning control box Excessive engine torque split during power changes a Improperly rigged N2 system b Faulty N2 actuator c Faulty indicator d Faulty fuel control e Faulty torque transmitter Generators come off line earlier than predetermined time and or prior to desired rotor rpm Faulty generator control unit 3 16 TM 55 1520 240 MTF CONDITION PROBABLE CAUSE C32 Heater does not light off within 10 seconds a lgniter plug fouled b Igniter fuse blown Faulty igniter Vibrator contact failure Select RESERVE
162. lowly On the overhead panel the AFT HOOK LOADED light shall momentarily come on before the hook is fully closed i Pull on the hook to check that it is latched closed If it is not pull the hook fully open and then release it Place the test load on the hook The hook remains closed The AFT HOOK OPEN caution light shall remain on j On the overhead panel set the MASTER switch to RESET The HOOK OPEN light shall go out Set the MASTER switch to ARM 4 23 Change 12 55 1520 240 At the forward hook rotate the release knob to its maximum clockwise position Pull the hook open On the cau tion panel the FWD HOOK OPEN light shall come on While holding the hook open release the release knob m Allow the hook to close slowly On the overhead panel the FWD HOOK LOADED light shall momentarily come on before the hook is fully closed n Pull hook fully open If necessary rotate release knob The FWD HOOK LOADED light shall remain out The FWD HOOK OPEN light shall remain on Release the hook Pull on the hook to check that it is latched closed If it is not pull the hook fully open and then release it Place the test load on the hook The hook remains closed The FWD HOOK OPEN light shall remain on p On the overhead panel set the MASTER switch to RESET The FWD HOOK OPEN light shall go out q Set the MASTER switch to ARM r At the aft hook rotate the release knob to its maximum clockwise
163. m the dash actuators should be set to 36 0 inches and electrically disconnected A mechanical rig check is not required if no ad justment has been made to the flight controls or the pitch links 1 Mechanical Rig Check If no adjustments have been made to the flight controls or pitch change links proceed to step 2 a DASH actuators Set to 36 0 inches Electrically disconnect NOTE Even though the AFCS selector switch is in the BOTH ON position during the check the AFCS OFF caution lights may stay on Change 12 2 58 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont b Perform crosswind hover Check cyclic position of 34 inch inch c Check Ground Contact An nunciator Maintenance Panel light out d Land helicopter e AFCS selector switch OFF Electrically reconnect DASH ac tuators 2 AFCS function check Conduct from 15 to 20 feet aft wheel height NOTE All of the following tests must be started from a precisely trimmed con dition If this is not done unsymmet rical or poor response will result and the intent of this test will not be met The performance criteria of this test are based on flight in smooth to light turbulent air 2 58 1 2 58 2 blank C18 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont a CYCLIC TRIM check BKA 8 Note CYCLIC TRIM indicators move from the GND position to the 60 knot RET
164. m 365F and DD Form 1896 locally required forms and publications and availabil ity of operators manual 10 and maintenance test flight manual Ignition lock switch ON BATT switch OFF Emergency power panel Check trip indicators and timers 5 Topping stops Check stowed 6 7 8 9 10 11 12 C25 unless TEAC is to be performed Cockpit area Check condition of bottom half inertia reel Deleted Fuel sample Check before first flight of the day Deleted Rotor blade tracking targets installed if tracking STROBEX is required Accelerometers installed if rotor blade balance check VIBREX is required Tiedowns locking devices covers and ground cables Removed and se cured 2 2 REFERENCE 55 1520 240 TROUBLESHOOTING PROCEDURE PRIOR TO MAINTENANCE TEST FLIGHT Cont Before interior Check Cont 13 Flight crew briefing on purpose duration 14 15 16 and objectives of test flight BATT switch ON Check MASTER CAUTION LIGHTS for proper indication no chip detectors CAUTION LIGHTS TEST for illumination of all caution light segments NOTE If topping stop is installed ensure CONT caution light is out with ECL in FLT Move 1 ENG ECL from STOP to GROUND to FLIGHT Verify that fuel control pointer is in proper band through out range Check 2 ENG the same Flight Engineer response APU start Fire guard pos
165. mperature indication of highest transmission selected exceeds 5 of seen indication a Faulty indicator b Faulty temperature bulb c Faulty selector switch d Faulty wiring With selector switch in the test position the indicator moves toward but not below 70 C Faulty selector switch Maintenance panel magnetic indicator does not trip when gnd test switch is set to TEST a Circuit breaker out b Faulty indicator 3 28 55 1520 240 CONDITION PROBABLE CAUSE c Faulty test diode d Faulty test switch e Faulty wiring F14 Maintenance panel magnetic indicator s do not reset when gnd test switch is set to RESET a Indicated fault may be real Check associated sensor b Circuit breaker out c Faulty indicator d Faulty test diode e Faulty test switch f Faulty wiring 3 29 55 1520 240 MTF TROUBLESHOOTING GUIDE G HYDRAULIC CONDITION PROBABLE CAUSE GENERAL Verify any MASTER CAUTION panel hydraulic faults with the maintenance panel for actual pressure indica tions The panel can also be used to confirm proper system servicing and pump condition G1 G2 G3 UTIL HYD SYS caution light doss not go out and indi cator does not increase to normal operating range within 30 seconds after apu start a Faulty hydraulic pump motor b Reservoir fluid level low c Air in system d Faulty or low precharged utility reservoir boot strap accumulator
166. n 3 feet of cable remain extended If the cargo mode in limit switch does not stop the winch when thc specified length of cable is extended adjust the cargo mode in limit switch or have it replaced Refer to TM 55 1520 240 23 Ch 14 Place the shifting lever to RESCUE Unplug the cable cutter from the stowage receptacle and connect it to the overhead receptacle above the rescue hatch NOTE RESCUE operation mode is used to reduce reelout time Keep tension on the cable while it is reeling out m Operare the winch to reel out the cable Continue to operate the winch until the cable is fully extended n Set the shifting lever to CARGO Unplug the cable cutter from the overhead receptacle and connect it to the sto wage receptacle Attach a 3 100 to 3 300 pound load to the winch ca ble p Operate the winch to reel in the cable Check that the overload limit switch stops the winch when the second layer of cable wraps start on the cable drum If the winch does not stop operating on the second layer of cable adjust the overload limit switch and repeat this step Refer to TM 55 1520 240 23 Ch 14 4 7 55 1520 240 Check the winch for leakage of hydraulic oil or lubri cating grease from the housing If other than minor seepage is noted replace the winch r Stow the winch cable and its related equipment Set the HOIST MASTER switch in the cockpit to OFF Shut down the apu Refer to TM 55 1520
167. n aft gear c Ground proximity switch malfunction d AFCS malfunction K4 CYCLIC TRIM indicators stay in G ND position a Ground proximity malfunction both gear b CYCLIC TRIM in MANUAL position 3 47 5 6 K7 K8 9 55 1520 240 Pitch attitude hold inoperative a AFCS malfunction DASH b DASH actuator malfunction c Hover longitudinal position out of tolerance d Vertical gyro malfunction Pitch attitude return oscillatory more than one and one half residual oscillations a Longitudinal ILCA malfunction b Faulty AFCS unit c Vertical gyro malfunction d Ground proximity switch malfunction Pitch beep inoperative a Defective beep switch b Longitudinal CCDA malfunction Roll attitude hold inoperative a Control centering not holding b Vertical gyro malfunction c AFCS malfunction d Lateral ILCA malfunction Roll beep trim inoperative a Defective beep switch b Control centering not holding c Control looseness d AFCS malfunction 3 48 55 1520 240 CONDITION K10 K11 K12 K13 PROBABLE CAUSE New heading not captured heading hold inoperative a Swivel lock Unlocked or malfunctioning b Control looseness c Heading gyro malfunction d Yaw ILCA malfunction Radar altitude hold inoperative a Pilot s radar altimeter inoperative b Collective CCDA malfunction c AFCS malfunction d Faulty AFCS panel s
168. nel s Interphone Stations 3 Check Terminal Board TB4 Block 9 J 36 Audio Voice Warning Message volume does not fluctuate when PRESS TO TEST knob is depressed on altimeter pilot s Faulty altimeter pilot s J37 DGNS Mode Switch to TEST GO ALL not Displayed a If GO P 1 Defective vertical gyro 2 Faulty aircraft wiring b If NG 1 Defective CDU 2 Defective SDC power supply c If DN 1 GPS failed Doppler can be used for navigation 2 Replace SDC 8 Replace CDU d If GN 1 Doppler failed GPS can be used for navigation 2 Replace SDC 8 Replace CDU 3 46 3 C21 J38 TM 56 1520 240 MTF DGNS data display lighting does not vary with BRT and DIM controls J39 J40 341 b Faulty aircraft wiring DGNS functions Inoperative a Replace CDU b Replace SDC c Faulty aircraft wiring d Replace Antenna DGNS system fails to zeroize a Replace CDU b Replace SDC c Zeroize switch defective d Faulty aircraft wiring No characters displayed on HF Radio Display a Circuit breaker s out b Radio function switch is OFF c Faulty wiring 3 46 4 Change 24 55 1520 240 J42 HF Radio circuit breaker does not remain pressed a Faulty Power Amplifier Coupler b Faulty Control Display Unit c Faulty Receiver Transmitter d Faulty wiring J53 SYSTEM NO GO RT CDU COMM FAIL displayed during Power up Bit P
169. notified 12 m Autorotation RPM a Stabilize airspeed 70 to 100 knots b EMERG ENG TRIM AUTO MANUAL switches MANUAL c THRUST CONT Reduce d EMERG ENG TRIM INC DECR switches DECR while reducing THRUST CONT to ensure engines do not drive rotor system e When in stabilized autorotation with full down THRUST CONT Record following data Refer to 1 Rotor RPM 2 Pressure altitude 3 Free air temperature 4 Fuel quantity 5 Pedals 2 inches maximum separation 2 75 REFERENCE H14 C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont f Note any abnormal vibrations 61 Autorotation at rotor rpm above 102 rotor rpm will be accompanied by an overall increase in vibration g Make power recovery 1 Load rotor 2 EMERG ENG TRIM AUTO MANUAL switches AUTO covers down one at a time 3 Reestablish safe airspeed and altitude 12 1 Autorotation RRPM Check NOTE Confirm that the aircraft gross weight and density altitude parameters are within the constraints of Figure 5 12 3 Autoro tational RRPM chart a Stabilize airspeed at 75 5 kts b THRUST CONT lever lower to ground detent c FADEC RRPM switch 97 d THRUST CONT lever full decr e When in stabilized autorotation with thrust full down record the following data NOTE Rotor RPM must be at 98 or higher If it is not at or above 98 the p
170. ntrols Neutralize 2 AFCS System Sel switch As re quired 3 Swivel switch As required 4 Searchlights As required 5 Transponder As required 6 GND contact annunciator lights ON Flight Engineer If installed 7 Cyclic Trim indicators Check GND indication ENGINE SHUTDOWN 1 SWIVEL switch LOCK 2 PARKING BRAKE Set a Check PARK BRAKE ON Caution Light ON 3 HEATING switches OFF 4 ANTI ICE switches OFF 5 EMERG EXIT LTS switch DISARM 6 Flight controls Set Position the pedals and cyclic at neutral N on the stick position indicator and the THRUST CONT at ground detent 7 AFCS SYSTEM SEL switch OFF Change 8 2 86 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE SHUTDOWN Cont 8 Ramp As required 9 Wheels Choked 10 Fire guard Posted 11 APU Start For apu starting proce dures refer td page 2 3 12 APU GEN switch ON 13 NO 1 and NO 2 GEN switches Off 14 POWER XFR switches NO 1 and NO 2 ON 15 CYCLIC TRIM indicators Check both in GND position manually pro gram if necessary 16 ENGINE CONDITION levers GROUND Ensure 2 minutes cool down is met 17 FUEL CONTROL switches SET 17 1 ENGINE CONDITION levers STOP Check that engine coastdown time is 25 seconds minimum CAUTION Check droop stops engaged 17 2 RARAS DECU Check Perform as follows a
171. ook does not open f Rotate the hook to the left until the upper attachment fitting contacts the support beam Be sure the hook does not open g Pull the tandem hook release lever to the operating position Check that the lever is approximately perpendicular to the floor h Pull the lever to the rear of the helicopter Check that the forward and aft hooks open then close Check that the FORWARD and AFT HOOK OPEN and the MASTER CAUTION lights are on 4 22 55 1520 240 i Return the lever to the operating position Check that the forward and aft hooks remain closed Check that the hooks are latched by applying a force to the load beam It may be necessary to relatch the hooks by opening the load beam fully and releasing it 17 1 Check the triple hook manual release as follows a Set the CARGO HOOK MASTER switch to ARM Do not operate the center hook from the cock pit during the following test Damage to the hook can result b Apply 10 to 20 pounds of force to the hook tongue c Pull the emergency cargo hook manual release handle aft Check that the FWD MID AFT HOOK OPEN and MASTER caution lights are on The fwd and aft hooks should open then close When the center cargo hook is opened using the manual emergency release handle the hook must be closed manually No attempt should be made to close the hook using the normal hy draulic or pneumatic method since damage to the cargo hook can result d
172. panel Check switches and stow grip 20 1 DECU 2 Check condition and security O 20 2 NO 1 and NO 2 EAPS control box Check condition and security 2 Loose equipment Check stowed 22 Static line Check condition and security 23 Crew safety harness Rig and adjust as required Aft Cabin 1 Combining transmission area Check mount bolt exposure by thread count 1 to 2 threads and slippage marks as required 2 CABIN and RAMP LIGHT switches As required 3 Fire detect control unit Check con dition and security No 2 engine C25 2 8 55 1520 240 TROUBLESHOOTING PROCEDURE INTERIOR Cont Aft Cabin Cont 4 5 6 7 IO 11 12 13 14 15 Ramp Check condition Ramp control lever STOP Power steering module Check ENGINE NO 2 FUEL VALVE Check OPEN and electrical plug se cure CROSSFEED FUEL VALVE Check CLOSED and electrical plug secure Manual defueling valve Check CLOSED and cap secure UTILITY hand pump Check con dition and leaks EMERG UTILITY PRESS control lable check valve Check NOR MAL HYD fill module Check condition flud level cover secure and valve CLOSED Ramp area hydraulic lines Check for leaks and filter button position Utility pressure and return modules Check condition and pump filter but tons extended Maintenance panel Check hydrau lic reservoir levels and pressure
173. ping stop in stalled if required Check N2 limit stop installed and safetied 2 26 1 2 26 2 blank REFERENCE C25 TM 55 1520 240 MTF PROCEDURE TROUBLESHOOTING REFERENCE EXTERIOR Cont Left Cabin Cont 18 All access doors and covers Check closed and secure 19 If NO 1 and NO 2 EAPS are installed check that they are aft and secured to engine inlets BEFORE STARTING ENGINES 1 Seat belts and shoulder harness Check condition fasten and tighten NOTE Seat belt locking device should be installed on the left side 2 Shoulder harness locks Check inertia reel functions properly i e the shoulder harness should lock automatically when given a sharp pull 227 C17 TM 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE BEFORE STARTING ENGINES Cont 3 Seats and pedals Adjust Check seat fore and aft vertical and tilt adjustments lock in place 4 Jettisonable door release bandies Cheek that the top and bottom latches engage the door supports locking devices removed 5 Jettisonable door latches Check through door latch plate in holes upper and lower that door latches are centered in the latch plate detents 6 Fire extinguisher Check seal security date and properly tagged 7 Pilot s and copilot s sliding windows Check condition Open and close 50 105 maximum force b Slide operation 15 Ibs maximum force
174. position Pull the hook open On the cau tion panel the AFT HOOK OPEN light shall come on s While holding the hook open release the release knob t Allow the hook to close slowly On the overhead panel the FWD HOOK LOADED light shall momentarily come on before the hook is fully closed Pull hook fully open If necessary rotate release knob The AFT HOOK LOADED light shall remain out The AFT HOOK OPEN light shall remain on v Release the hook Pull on the hook to check that it is latched closed If it is not pull the hook fully open and then release it Place the test load on the hook The hook remains closed The AFT HOOK OPEN light shall remain on w On the overhead panel set the MASTER switch to RESET The AFT HOOK OPEN light shall go out 4 24 55 1520 240 L STROBEX VIBREX TRACKING PROCEDURE Reference TM 55 1520 240 23 To be provided M ENGINE VIBRATION CHECK Reference TM 55 1520 240 23 ACCELERATION CHECK 1 With both Engine Condition Levers ECL flight and the thrust rod in the ground detent position take both engines to minimum beep using the No 1 and No 2 engine beep trim switch WARNING Do not exceed any operation limits during the following steps 2 Check the acceleration of the No 1 engine as follows a Place the No 2 engine auto manual switch to the manual position b Using the No 1 and No 2 engine beep trim switch set the RRPM to 100
175. pper boost actua tors and pilot valve for proper con nections condition security and leakage Check for extended jam indicators h Check longitudinal cyclic trim actuator for condition and se curity i Cruise guide link and signal conditioners Check for condition and security 23 Forward transmission Check mount bolts Check oil cooler inlet for obstructions a Forward transmission pressure transducer Check for leaks and security b Hydraulic cooling fan Check for obstructions condition and security c Forward transmission cooler shroud Check security 24 Brake accumulator Check precharge and security 25 First and second stage mix ing units Check for rod end con dition security and rigging pins removed 26 Forward pylon fairing Check condition and security left and right sides 26 Forward rotor right side Check as follows Change 1 2 19 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE EXTERIOR Cont Top of Fuselage Cont a Check lag damper lockouts removed b Check components for proper safety wiring and security c Check blade lightning pro tcction straps and cables installed on top and bottom of each blade and condition d Check droop stops rain shield and stiffener for condition and security e Check pitch change links swashplate slider assembly and drive arm for condition and se curity f Check upper boost actuator and
176. pply brakes a Faulty master cylinder b Faulty transfer valve c Faulty pressure reducer valve d Faulty parking brake valve G16 Power steering fails to operate Faulty power steering module a b Faulty wiring o Faulty steering actuator Swivel lock switch in the lock or unlock position e Faulty power steering control box G17 Power steering system does not operate within normal limits a Trapped air in the system b Zero trimpot out of adjustment 3 33 Change 12 55 1520 240 CONDITION G18 G19 G20 PROBABLE CAUSE c Improper rigging d Faulty power steering actuator assembly e Faulty wiring f Faulty power steering control box Wheels will not center with swivel locks locked a Faulty centering cam b Faulty power steering module Aircraft deviation exceeds 10 with swivel locks released Check tolerance with swivels locked to eliminate steps a and b as probable factors a Struts uneven b Tire pressure uneven c Power steering improperly adjusted d Faulty power steering actuator e Crosswind component Aircraft deviation exceeds 5 with swivel locks locked a Struts uneven b Tire pressure uneven c Swivel locks not locked d Crosswind component 3 34 TM 55 1520 240 MTF CONDITION PROBABLE CAUSE G21 Utility and or flight boost hydraulic system over heats Hydraulic cooler air inlet or outlet obstructed
177. r the first destination checkpoint CP 3 As CP 1 is flown over depress first the KYBD key and then the ENTR key f Set the FLY TO DEST thumbwheel to position 3 5 Use the track angle error TKE display DIST BRG TIME display or an independent NAV aid to steer the helicopter to the first CP 3 destination h As the first CP 3 checkpoint is located change the helicopter heading as necessary to fly over the checkpoint Set the DISPLAY switch to PP and depress KYBD as the checkpoint is overflown Record the displayed present position coordinates or depress TGT STR i For leg number 2 steer the helicopter and fly over checkpoint CP 3 on a heading for destination checkpoint CP 4 Set the DISPLAY switch to DIST BRG TIME and as CP 3 is flown over depress the KYBD key and then the ENTR key j Set the FLY TO DEST thumbwheel to position 4 Repeat step g for destination CP 4 1 Repeat step h for checkpoint CP 4 2 83 Change 12 55 1520 240 PROCEDURE IN FLIGHT Cont 2 Navigation Accuracy Test Legs The following navigation legs shall be flown in the indicated numerical sequence a Leg Number 1 Fly from CP 1 to CP 3 at normal cruising speed Record the displayed present position coordinates at CP 3 flyover b Leg Number 2 Fly from CP 3 to CP 4 at the maximum helicopter speed Record the displayed present position coordinates at CP 4 flyover c Leg Number
178. range on pick up to hover a 1 Engagement Error Check as follows 1 AFCS SYSTEM SEL NO 1 Move switch from NO 1 to OFF then back to NO 1 Check for engagement error 2 AFCS SYSTEM SEL NO 2 Move switch from NO 2 to OFF then back to NO 2 Check for engagement error 3 AFCS SYSTEM SEL BOTH b Pitch axis test AFCS SYSTEM SEL BOTH Check pitch axis response as follows NOTE During AFCS function check insure that both the pilot s and copilot s pitch and roll beep trim switches are opera tional 1 While trimmed for a stabilized hover raise the nose of the helicopter 3 above hover at titude and without retrimming longitudinal control or releasing the mag brake return the stick to detent The aircraft shall return to its approximate original pitch at titude with no more than one and one half residual oscillations and bold attitude within 2 2 Repeat test for a 3 nose down trim displacement 2 59 C9 TM 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE HOVER Cont c PITCH BEEP TRIM Check Check pitch beep trim as follows 1 While trimmed for hover operate the four way conical switch on the longi tudinal stick grip to forward posi tion A small nose down pitch change shall be noted 2 Operate the four way switch to aft position A small nose up change shall occur d Roll axis test Check roll axis response as follows 1 Trim the aircraft to a level
179. ring Accumulator Precharge Limits Brake Accumulator Precharge Limits Engine Fire Extinguisher Pressures FWD and AFT Indicator Schedule iii C22 PAGE 4 25 4 25 4 31 E PAGE 82 e 4 N CY 192 102 A A A eo 55 1520 240 LIST OF ILLUSTRATIONS Continued Number Title Page Interstage Air Bleed Closure Chart T55 L TA Cr 5 17 5 10 CH 47D Cockpit Controls Position Envelope 5 19 fama Autorotational RPM Chart for CH A7D eere mehr me 5 23 p 5 12 Turbine Engine Analysis Check N 1 Chart 251 Turbine Engine Analysis Check PTIT 152288 Turbine Engine Analysis Check Torque R 5 26 2 1 Autorotational RRPM Chart 5 26 2 3 ARAJ Power Assurance Test Altitude Bands Chart meme Power Assurance Test Maximum Con tinuous Power Chart 5 26 2 7 12 6 Power Assurance Test Maximum Power Chart gerrr ber RESET 5 26 2 9 Power Assurance Test Engine Tem perature Limits Chart 5 26 2 11 Power Assurance Test 1 Gas Gen erator Speed Chart 5 26 2 13 5 12 9 MBA Power Assurance Test PAT Number Margin to Torque Margin Conversion Chart 5 26 2 15 5 12 TOMBE M N 1 Idle Check Altitude Bands CHALE E 5 17 17
180. s By Order of the Secretary of the Army GORDON R SULLIVAN General United States Army hief Official Chief of Staff A LES MILTON H HAMILTON Administrative Assistant to the Secretary of the Amy 06334 DISTRIBUTION To be distributed in accordance with DA Form 12 31 E block no 0195 require ments for TM 55 1520 240 MTF 55 1520 240 16 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 16 WASHINGTON D C 30 SEPTEMBER 1992 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 38 1 2 38 2 2 38 1 2 38 2 2 72 1 2 72 2 2 72 1 2 72 2 4 25 and 4 26 4 25 and 4 26 4 26 1 and 4 26 2 4 26 1 4 26 2 4 27 and 4 28 4 27 and 4 28 4 28 1 4 28 2 4 29 4 30 4 29 4 30 5 25 5 26 5 25 5 26 5 26 1 5 26 2 5 26 1 and 5 26 2 5 26 3 5 26 4 5 26 3 5 26 4 2 Retain this sheet in front of manual for reference purposes DISTRIBUTION STATEMENT Approved for public release distribution is unlimited 55 1520 240 16 By Order of the Secretary of the Army GORDON R SULLIVAN General United States Army Chief of Staff Official MILTON H HAMILTON Administrative
181. s 26 42 gallons kiloliter 10 hectoliters 264 18 gallons U S GOVERNMENT PRINTING OFFICE 1990 0 236 938 RECOMMENDED CHANGES TO EQUIPMENT TECHNICAL PUBLICATIONS SOMETHING WRONG WITH PUBLICATION FROM PRINT YOUR UNIT S COMPLETE ADDRESS THEN JOT DOWN THE DOPE ABOUT IT ON THIS FORM CAREFULLY TEAR IT QUT FOLD IT AND DROP IT IN THE MAIL VA SENT ibtd uii IN THIS SPACE TELL WHAT IS WRONG AND WHAT SHOULD BE DONE ABOUT IT PRINTED NAME GRADE OR TITLE AND TELEPHONE NUMBER SIGN HERE TRAR ALONG FRARKORATED LANE DA 2028 2 PREVIOUS EDITIONS P S IF YOUR OUTFIT WANTS TO KNOW ABOUT YOUR JUL 79 ARE OBSOLETE RECOMMENDATION MAKE A CARBON COPY OF THIS AND GIVE IT TO YOUR HEADQUARTERS 051400 026
182. ss should be performed If the PTIT indicating system is OK the engine is acceptable 13 After completion of the check reduce engine power initially by operating the No 1 amp 2 ENGINE BEEP TRIM switch to decrease rotor rpm N1 and torque Do not lower thrust until rotor rom and N1 begins to decrease CAUTION Do not move the ENGINE CONDITION lever of the other engine from GROUND to FLIGHT until N1 speed and torque of the engine being TEACed has been reduced 4 29 C16 55 1520 240 14 Move the ENGINE CONDITION lever of the next engine to be TEACed from GROUND to FLIGHT 15 Repeat steps 6 thru 15 for the other engine Failure to remove the topping stops following a topping check will prevent the engines from achieving emergency power on subsequent flights P Deleted 4 30 C14 55 1520 240 Q DIFFERENTIAL CURRENT PROTECTION CIRCUIT CHECK Reference TM 55 1520 240 23 Perform this check whenever maintenance has been performed on a generator a generator control unit a current transformer or the wiring between these units Perform the check as follows 1 Set the following switches to the specified positions a HEATER VENT BLOWER ONLY b CPLT CTR and PLT WINDSHIELD ANTI ICE ON c CPLT and PLT SLT FIL ON d FUEL PUMPS All ON 2 GEN 1 switch OFF Check NO 1 GEN OFF caution light is on and NO 2 GEN OFF caution light is out 3 GEN 1 switch ON G
183. ss than 5 seconds 33 RAMP EMER switch on overhead panel DN and hold until ramp is fully open resting on ground then re lease to HOLD Check that ramp remains fully open 34 RAMP EMER switch on overhead panel UP and hold until ramp is in level position then release to HOLD Check that ramp remains in level position C22 4 34 TM 55 1520 240 MTF 35 RAMP EMER switch on overhead panel UP and hold until ramp and cargo door are fully closed then release to HOLD Check that ramp and cargo door close in proper sequence and remain fully closed 36 Place the RAMP EMER switch guard in the closed cover down position 37 RAMP PWR switch on overhead panel OFF 38 Remove hydraulic and electrical power 39 UTILITY RESERVOIR DEPRESSURIZE valve OPEN 40 Press depressurization valve on apu start module Check that utility system depressurizes 41 UTILITY RESERVOIR DEPRESSURIZE valve NORMAL 42 RAMP CONTROL VALVE handle DN Check that ramp does not move 43 RAMP CONTROL VALVE handle STOP 4 35 C22 55 1520 240 S HEADS UP DISPLAY CHECK HUD Reference TM 55 1520 240 23 Perform this cheek on helicopters equipped with Heads Up Display AN AVS 7 System to be used with the Aviator s Night Vision Imaging System ANVIS Flight test will consist of display comparisona between panel displays and data displayed on the AN AVS 7 HUD 1 Starting procedure a ADJ ON
184. ssed a Faulty test switch b Faulty caution panel c Faulty wiring MASTER CAUTION light will not cancel when Faulty master caution light b Master caution light sticking in panel c Faulty wiring MASTER CAUTION lights do not dim a Faulty dim switch b Faulty dimming relay e Faulty caution panel Faulty wiring D Dome light switch in white position U S GOVERNMENT PAINTING OFFICE I994 555 121 80052 3 18 1 3 18 2 blank C22 55 1520 240 CONDITION PROBABLE CAUSE D5 When dome light switch is set to thie caution lights dimmed the caution lights do not go to bright a Faulty dimming lockout relay b Faulty wiring D6 PARK BRAKE ON caution light does not come on when brakes a re set a Rod incorrectly rigged b Faulty microswitch D7 Hydraulic boost off HYD FLT CONTR NO 1 or NO 2 caution light does not come on with low pressure in the system a Faulty pressure switch b Faulty wiring c Faulty caution panel D8 Hydraulic boost off HYD FLT CONTR NO 1 or NO 2 caution light on with system pressurized a Faulty pressure switch b Faulty wiring c Faulty caution panel D9 Left or right fuel pressure or R FUEL PRESS cau tion light does not go out with fuel pumps on a Circuit breaker out b Faulty pressure switch c Faulty fuel pump d Faulty wiring e Faulty caution panel 3 19 55 1520 240 CON
185. t 10 Blade Track If not performed earlier See Section IV HIT Check Complete if TEAC is not required NOTE Hit check may be deferred until arrival in test flight hover area if conditions in runup area preclude accurate or safe completion of check Hit check must be completed before takeoff 11 1 83 Power Assurance Check First flight of the day NOTE If ambient conditions or aircraft weight precludes conducting this check on the ground the check may be deferred and conducted at a hover If conducted at a hover the ECL of the engine not being checked can be reduced until the PAC Engine torque is between 60 to 80 NR switch 100 b ENG 1 ENG COND lever Ad just c THRUST CONT lever Raise until reads 60 to 8096 Sta bilize for 30 seconds d TEST switch ENG 2 PWR AS SURANCE Check DECU display Flight Engineer An A means that the engine is operating at a cooler temperature than a baseline spec engine Record results 2 54 3 2 54 4 blank C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont e THRUST CONT lever Adjust f ENG 1 ENG COND lever PUT Repeat check with ENG 2 ENG COND lever at GND 12 AN ASN 128 Doppler Program doppler with UTM or latitude longitude coordinates for checkpoints in test course Enter magnetic varia tion O 12 1 AN ASN 128B DGNS a Load several known local way points in
186. t then on NO 2 HYD FLT CONTR caution light out Flight engineer check pressure approximately 2000 psi 2 POWER XFR NO Check NO 1 HYD FLT CONTR caution light out NO 2 HYD FLT CONTR caution light 3 FLT CONTR HYDRAULIC switch NO 2 on C26 2 44 55 1520 240 MTF TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 4 POWER XFR NO 2 OFF Check NO 2 HYD FLT CONTR caution light out then on NO 1 HYD FLT CONTR caution light out Flight en gineer check pressure approximately 2 000 psi 5 POWER XFR NO 2 ON Check NO 2 HYD FLT CONTR caution light out NO 1 HYD FLT CONTR caution light on 6 FLT CONTR HYDRAU G13 LIC switch BOTH h Control Centering Control centering will hold cyclic and pedals within gt inch from stops heck ability to override control centering in all quad rants 30 1 Pitot and Windshield Anti ice Sys tem Check as follows CAUTION Do not leave the pitot heaters on for more than 5 minutes Ground opera tion shortens service life a PITOT and AFCS yaw ports heat Check ON then OFF flight en gineer response CAUTION Do not operate windshield anti ice system above a free air temperature of 24 b WINDSHIELD ANTI ICE switches ON Check heating elements feel warm to the touch then OFF 31 HEATING NT BLOWER Op eration Check Section IV 2 45 C19 55 1520 240 TROU
187. t and fuel drain 2 outlets Check clear Pilot s jettisonable door Check con dition and security Free air temperature gage Check Pilot s hydraulic brake lines Check for leakage Antennas underside of helicopter Check security condition and free of dirt and oil Searchlights Check condition Nose access panel Check secure Windshield wipers Check condi tion Windshields Check for cracks and cleanliness Glide slope and IFF antennas Check condition 2 23 REFERENCE C25 55 1520 240 TROUBLESHOOTING PROCEDURE EXTERIOR Cont Forward Cabin Cont 11 Pitot tubes Check condition and security 12 AFCS yaw ports Check clear 13 Copilot s hydraulic brake lines Check for leakage 14 Copilot s jettisonable door Check condition and security 15 HYD SYS TEST panel Check ca pacities and fairing secure 16 Emergency escape panel Check condition and security Left Cabin 1 Left electrical compartment Check C25 as follows a GEN CT FAULT bite Check all black b Transformer rectifier Check condition and security c No 1 minimum beep resistor Check condition and security d Battery for security sump jar and vent lines e Battery CHARGING and CHARGED lights Check f BAIT CHG FAULT bite Check all black 6 Access door Check condition and security 2 24 REFERENCE 55 1520 2
188. t bearing 3 40 55 1520 240 TROUBLESHOOTING GUIDE J COMMUNICA TIONS NAVIGATION EQUIPMENT CONDITION PROBABLE CAUSE J1 No interphone a Faulty interphone control box b Faulty headset c Control box switches off d Circuit breaker out J2 UHF radio inoperative a Faulty radio set b Faulty wiring c UHF radio circuit breaker out J3 VGI will not erect a Circuit breaker out b Faulty indicator c Faulty gyro 44 Altimeter error in excess of 70 feet a Altimeter set wrong b Static ports blocked c Faulty altimeter J5 Radar altimeter error in excess of 5 foot a Faulty altimeter pilot s b Faulty antenna c Slingload reflecting signal 3 41 55 1520 240 CONDITION PROBABLE CAUSE J6 Pointer indicates incorrectly airspeed and vertical ve locity indicators and or pressure altimeter a Moisture in pitot static lines b Damaged pitot static lines C Obstructed pitot static lines d Indicator not properly connected to pitot static system e Faulty indicator J7 Airspeed indicator fluctuates excessively or greater than 7 knot difference between pilot s and copilot s indicator a Faulty indicator b Leak in pitot static lines J8 Turn and slip indicator inoperative a Circuit breaker out b Faulty indicator J9 Excessive error in gyro compass a Improper compensation b Abnormal magnetic influence c Faulty flux valve d Faulty
189. tch is pressed a Microphone or trigger switch defective b Receiver transmitter improperly tuned c Antenna coupler is defective J20 No HF background noise heard in headset a RF SENS knob fails to control volume b Communication panel controls are improperly set c Power source or connections are defective d Defective headset J21 HF radio channel interference after desired frequency has been set a Interconnecting cabling or connector is defective b Frequency set knobs are defective c Tuning circuits in receiver transmitter are defec tive J22 Doppler left display does not indicate GO after 15 seconds with MODE select switch at TEST a Right display is P pitch or roll data in error or missing Check copilot attitude gyro warning flag and AFCS 1 caution light on b Right display is MN or NG Recycle MODE select switch to OFF then TEST and note nature of malfunction from display codes in Chapter 3 of TM 55 1520 240 10 J23 Doppler left display indicates EN during LAMP TEST following interruption of power to unit a Dry cell battery has insufficient voltage to retain previously entered data b Re enter present position spheroid variation and destination 3 45 924 J25 J26 J27 TM 55 1520 240 MTF Doppler MEM and or MAL indicator lamps fail to light with MODE switch at LAMP TEST a Unit is powered and other displays are lighted b Defective indicator lamp c Fault
190. ted a APU start accumulators charged according to chart b APU Check condition and servicing c EMERGENCY APU FLUID SHUT OFF VALVE Check OPEN d APU control box Condition and security e APU START switch RUN for 3 to 5 seconds Then START for 2 seconds Then release to RUN Operation of the apu is controlled by the electronic con trol unit REFERENCE eei C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE PRIOR TO MAINTENANCE TEST FLIGHT Cont Before Interior Check Cont NOTE Do NOT turn the BATT switch OFF if the APU ON caution light does not come on or if the start is automatically shutdown Set the APU switch to OFF and check the bite indicators on the control unit for the cause of the shutdown f APU ON caution light Check on 10 12 seconds after APU switch is released to RUN g UTIL HYD SYS caution light Check out 30 seconds maximum h APU GEN switch ON Check NO 1 and NO 2 RECT OFF caution lights out i POWER XFR NO 1 and POWER XFR NO 2 switches ON Check NO 1 and NO 2 HYD FLT CONTR caution lights out WARNING If either FLT CONTR caution lights do not go out in 30 seconds after POWER XFR switches are set to ON set the POWER XFR switches to OFF Do not fly the helicopter 17 Neutral Rig Check After Phase Maintenance inspection or flight control maintenance Set DASH actuator to 36 inches for mechanical rig
191. tice etc which if not strictly observed will result in damage or destruc tion of equipment NOTE An operating procedure condition etc which is essential to highlight TM 55 1520 240 MTF 3 GENERAL INFORMATION a This mutual covers only maintenance test flight of CH 47D aircraft and in no way supersedes any information contained in TM 55 1520240 10 or applicable CL but is to be used in conjunction with the 10 or CL For the purpose of maintenance test flights only this manual satisfies all the re quirements of the CL from Interior Check through Engine Shutdown b Crew requirements will be as specified in TM 55 1500 326 25 and TM 55 1520 240 10 c The duration of a general or limited test flight will be in accordance with the requirements d TM 55 1500 328 25 4 SPECIAL INSTRUCTIONS a Cargo and Passengers Cargo and passengers are pro hibited on maintenance test flights b Forms and Records Forms and records will be checked prior to the maintenance test flight to determine what maintenance has bees performed and the typed maintenance test flight required i e general or limited c Configuration The configuration of the aircraft should be determined prior to each maintenance test flight in order to determine performance parameters d Post Test Flight Inspection A thorough visual inspec tion will be performed to the extent necessary to assure that deficiencies or shortcomings that may have de
192. ting hand Remove pages Insert pages 2 3 through 2 10 2 3 through 2 10 2 31 through 2 38 2 31 through 2 38 2 39 and 2 40 2 39 and 2 40 2 40 1 2 40 2 2 40 1 2 40 2 2 41 and 2 42 2 41 and 2 42 2 42 1 2 42 2 2 42 1 2 42 2 2 45 through 2 48 2 45 through 2 48 2 b1 and 2 52 2 51 and 2 52 2 55 through 2 58 2 55 through 2 58 mew aii 2 58 1 2 58 2 2 61 and 2 62 2 61 and 2 62 2 62 1 2 62 2 2 62 1 2 62 2 2 63 through 2 70 2 63 through 2 70 2 71 and 2 72 2 71 and 2 72 2 73 and 2 74 2 73 and 2 74 2 83 and 2 84 2 83 and 2 84 55 1520 240 12 Remove pages 3 27 and 3 28 3 33 and 3 34 Insert pages 2 84 1 2 84 2 3 27 and 3 28 3 33 and 3 34 3 37 and 3 38 4 4 1 4 4 2 4 5 and 4 6 4 5 and 4 6 vlog wx 4 22 1 4 22 2 4 23 and 4 24 4 23 and 4 24 3 37 and 3 38 4 26 1 and 4 26 2 4 26 1 and 4 26 2 5 29 5 30 5 29 5 30 5 31 5 32 5 31 5 32 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army CARL E VUONO General United States Army Official Chief of Staff WILLIAM J MEEHAN I Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF Maintenance requirements for CH 47D Helicopter Cargo Transport 55 1520 240 11 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 11 WASHINGTON D C 14 October 1988 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 5
193. to DGNS either through CDU or through Data Loader Mod u le b Load SA AS variables into DGNS through SA AS port on SDC 13 AN ASN 149 V GPS with AN ASN 128 Doppler a Power Up b Perform Self test c Program waypoint coordinates for checkpoints in test course Enter magnetic variation and DTM if co ordinate entry is manual 2 55 C25 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE ENGINE RUN UP Cont d Verify SA AS entry e Verify present position f Select destination way point TAXI 1 SWIVEL switch UNLOCK then STEER 2 AFCS SYSTEM SEL As required 3 CYCLIC TRIM indicators k3 GND position 4 Chocks removed and secured 5 Ramp and cabin door Secured 6 FUEL VALVE and CROSSFEED VALVES indicating lights Out flight engineer response 7 Crew Check ready for taxi 8 Taxi director and blade watchers Positioned as depicted in TM 55 1520 240 10 C20 2 56 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE TAXI Cont 9 PARKING BRAKE Release a Check handle seated b PARKBRAKE ON caution light out 10 Wheel brakes Check pilot s and copilot s right and left pedals for smooth 15 operation and no fade upon application 11 Power steering Check a Directional control SWIVEL switch STEER b Left and right turns 30 degree turns Check HSI magnetic G16 compass and turn needle for proper operation c Check P
194. to IN until the winch stops Check that the rescue mode in limit switch stops the winch when 287 gt feet of cable remain extended Measure the distance from the outer roller on the level wind mechanism to the ball end of the cable If the winch does not stop auto matically within the specified limit readjust the rescue mode in limit switch Refer to TM 55 1520 240 23 Ch 14 If the time required to reel the cable in to the limit switch is not about 90 seconds or if there is binding or uneven spooling of the cable drum replace the winch h Operate the winch to reel out the cable Connect the cable hook to a 600 pound weight Raise the weight with the winch and release the WINCH CABLE switch to OFF Check that the hoist remains in the stopped position and the weight does not creep downward If the weight creeps downward re place the winch 4 6 55 1520 240 i Lower the weight and remove it from the cable Remove the winch cable from the pulleys Remove the pulleys and return them to the stowage container Unplug the cable cutter from the overhead connector Connect it to the cable cutter stowage receptacle j Set the shifting lever on the winch to CARGO In case of an in limit switch failure do not allow the end of the cable to reel in and jam in the reel assembly The winch may be damaged k Operate the winch to reel in the remaining length of cable Check that the cargo mode in limit switch stops the winch whe
195. to select destination mode 13 Fly towards CP 1 14 When GPS set indicates arrival at CP 1 set Data switch to POS 15 While hovering over CP 1 depress the MARK key Press line select key 3 to store coordinates and altitude This will be Mark A 16 Depress CLR key to exit Mark operation 17 Set Data switch to MSN Open line three and enter an arrow in front of Doppler Only ONLY Ensure that an arrow is also in front of GPS ONLY on line four GPS DOP GPS Doppler mode of operation is selected 18 Set Data switch to DIS TG WP mode While still hovering over CP 1 open line 1 and select CP 2 Record distance and bearing to CP 2 lines 2 and 4 Slew 3 down to Page 2 and record slant range to destination line 2 C 20 2 84 4 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE IN FLIGHT Cont 19 With Data switch still set to DIS TG switch to destination mode and fly from CP 1 to CP 2 While hovering over CP 2 record displayed present position at CP 2 by performing the following Depress the MARK key Press line select key 3 to store coordinates and altitude This will be Mark B Press the Clear key CLR to return to original screen 20 Set Data switch to POS and record the present position coordinates 21 Set Data switch to DIS TG WP mode While still hovering over CP 2 open line 1 and select CP 1 Record distance and bearing to CP 1 lines 2 and 4 Slew down to Page 2 and record
196. to the full up position and cargo door remains retracted 14 RAMP CONTROL VALVE handle DN and hold until ramp is at mid position then STOP Check that ramp stops at mid position with cargo door fully retracted C22 4 32 55 1520 240 CAUTION Do not manually operate cargo door ramp tongue with ramp in full up position Dam age to door and fuselage will occur 15 RAMP CONTROL SEQUENCE VALVE Turn pin to vertical position 16 RAMP CONTROL SEQUENCE VALVE MANUAL OPER knob Pull up and hold Check that cargo door ex tends fully 17 RAMP CONTROL SEQUENCE VALVE MANUAL OPER knob Release Check that cargo door retracts fully into ramp 18 RAMP PWR switch on overhead panel OFF 19 RAMP CONTROL VALVE handle UP Check that ramp does not move 20 RAMP CONTROL VALVE handle STOP 21 RAMP PWR switch on overhead panel ON 22 RAMP CONTROL VALVE handle DN Check that ramp moves to the full down position resting on ground and cargo door remains retracted 23 RAMP CONTROL VALVE handle UP Check for the following sequence of actions a Ramp moves upwards and stops approximately 8 inches from the fully closed position b Cargo door then extends fully from ramp c Ramp and door then move up into the fully closed position 24 Press and hold knob on door override valve Per form the next step while holding knob 25 RAMP CONTROL VALVE handle DN and hold till ramp
197. trative Assistant to the Secretary of the Army 01434 DISTRIBUTION To be distributed in accordance with DA Form 12 31 E block no 0195 MTF mainten ance requirements for TM 55 1520 240 MTF URGENT NOTICE THIS CHANGE HAS BEEN PRINTED AND DISTRIBUTED OUT OF SEQUENCE IT SHOULD BE INSERTED IN THE MANUAL AND USED RECEIPT OF THE EARLIER SEQUENCED CHANGE ENSURE A MORE CURRENT CHANGE PAGE IS NOT REPLACED WITH A LESS CURRENT PAGE TM 55 1520 240 MTF C14 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO 14 WASHINGTON D C 28 August 1990 MAINTENANCE TEST FLIGHT MANUAL ARMY MODEL CH 47D HELICOPTER TM 55 1520 240 MTF 8 September 1982 is changed as follows 1 Remove and insert pages as indi cated below New or changed text material is indicated by a vertical bar in the mar gin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 4 25 and 4 26 4 25 and 4 26 4 26 1 and 4262 4 27 4 27 through 4 30 2 Retain this sheet in front of manual for reference purposes URGENT 55 1520 240 14 By Order of the Secretary of the Army CARL E VUONO General United States Army Chief of Staff Official THOMAS F SIKORA Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 MTF Maintenance requirements for CH 47D Helicopter Cargo Transport 55 1520 240 13 CHAN
198. ty APU motor pump with APU running f Low service level high fluid temperature g Faulty utility pump If rotors are rurning 3 31 TM 55 1520 240 MTF CONDITION PROBABLE CAUSE G9 Parking brakes will not release PARK BRAKE ON caution light remains on Faulty parking brake valve or improperly adjusted G10 Parking brake will not lock a Improperly adjusted rod b Faulty parking brake valve c Leak in system G11 Swivel locks do not operate a Faulty swivel lock manifold solenoid valve b Faulty swivel lock actuator assembly C Low precharge pressure in swivel lock accumula tor d Faulty wiring G12 HYD FLT CONT caution light for opposite system does not illuminate when NO 1 or NO 2 is selected Flight boost hydraulic indicator pressure remains at 2500 to 3200 psi when system is OFF a Pressure in other system is low b Faulty pressure switch c Faulty solenoid valve or pressure operated valve in power control module d Faulty wiring G13 NO 1 or NO 2 HYD FLT CONT caution lights remain on 5 seconds after switch is turned on a Faulty switch b Faulty module 3 32 TM 55 1520 240 MTF CONDITION PROBABLE CAUSE c Faulty wiring d Faulty pump G14 One or more wheel brakes will not engage or brake pedal s spongy a Air in system b Faulty transfer valve c Faulty master cylinders d Fluid leakage e Faulty brakes G15 Excessive force needed to a
199. ty Z AVH control b Faulty main processor J52 HF radio displays a fault advisory during operation a Faulty HF radio set component Perform BIT check to locate failed component J53 HF radio displays INOP MODES EXST a Keys or data for that mode not loaded b Faulty component Press LRU line select switch to locate failed component J54 HF radio displays MAN INOP a Faulty HF radio set component In STBY press INOP line select switch then press LRU line select switch to identify failed component J55 HF radio displays PRE NO DATA a No preset data loaded J56 Plaintext communication not received transmitted a CT ONLY mode selected b Faulty ARC 220 receiver transmitter c Faulty KY 100 main processor d Faulty wiring e Faulty ARC 220 Power Amplifier Coupler 3 46 7 Change 24 15 1520 240 J57 HF radio displays CHANNEL INOP a Propagation condition may not allow communications on channel selected b Faulty component Perform BIT check to locate failed component J58 Excessive background noise in headset a Squelch not set properly b Faulty antenna c Faulty ARC 220 Antenna Interface Adapter d Faulty ARC 220 Power Amplifier Coupler e Faulty HF receiver transmitter f Faulty KY 100 main processor g Faulty wiring J59 Cipher text messages not received transmitted plaintext is received transmitted a Mode switch still in PT position b K
200. ue of the hook and pressing down The hook shall not open 10 Apply a test load force of 18 to 22 pounds on the forward and aft hooks NOTE The forward and aft hooks will not open unless a load of 18 to 22 pounds is on the hook 11 Check normal operation of the forward hook as follows a CARGO HOOK MASTER switch OFF b CARGO HOOK EMERG REL ALL switch OFF c HOOK SELECT switch FWD d Press the CARGO HOOK RELEASE switch on the pilot s cyclic control stick Check that the hooks remain closed 4 18 55 1520 240 e Set the CARGO HOOK MASTER switch to ARM Press the hook release switch on the pilot s control stick Check that the forward hook opens and closes and the FWD HOOK OPEN and MASTER CAUTION lights come on f MASTER CAUTION LIGHT PUSH TO RESET g Set the CARGO HOOK MASTER switch to RESET Check that the hooks remain closed and the FORWARD HOOK OPEN caution and the MASTER CAUTION lights are out h Replace the load on the forward hook i Set the CARGO HOOK MASTER switch to ARM Press the CARGO HOOK RELEASE switch on the pilots con trol stick Check that the forward hook opens and closes Check that the FORWARD HOOK OPEN and the MASTER CAUTION lights come on j MASTER CAUTION LIGHT PUSH TO RESET k Momentarily set the CARGO HOOK switch on the hoist operators panel to RESET Check that the hooks remain closed and the FORWARD HOOK OPEN and the MASTER CAUTION lights are our 1 Rep
201. ution lights Check out If either HYD FLT CONTR caution light does not go out in 30 seconds after PWR XFR switches are set to ON set switches to OFF Do not fly the aircraft a Check indicators on maintenance panel as follows flight engineer response b HYD FLT CONTR hydraulic PRESSURES stabilized at 2500 to 3200 psi c UTILITY hydraulic PRESSURE stabilized at 2500 to 3500 psi d Maximum fluctuation 50 G8 e NO 1 NO 2 APU and UTILITY PUMP FAULT lights Out f Maintenance panel Check as follows flight engineer response 1 GND TEST switch TEST Check all magnetic bite indicators are tripped black and white indication Check XMSN OIL HOT NO 1 ENG CHIP DET XMSN CHIP DET AND NO 2 ENG CHIP DET caution panel lights on in cockpit 2 GND TEST switch RESET Check all bite indicators have reset all black indications 2 37 C9 55 1520 240 TROUBLESHOOTING PROCEDURE REFERENCE STARTING ENGINES Cont 3 FILTER CHANGE and PUMP FAULT lights PRESS TO TEST Check all lights come on when pressed 4 MAIN OIL PRESS and AUX OIL PRESS lights Check all on 5 GROUND CONTACT lights Check both on Flight Engineer 16 1 XMSN OIL PRESS gage Check 0 5 psi all positions 17 Avionics ON except transponder ALQ 156 note status light on F O 17 1 EAPS Bypass Door Check a NO 1 and NO 2 EAPS control boxes Press to test EAPS BYPASS DOORS OPEN light Fl
202. veloped as a result of the maintenance test flight are detected e References When a maintenance test flight is required to assure proper operation of a specific system s refer to the applicable maintenance manual for the limits of that system f Asterisked Checks An asterisk prior to a check re quires that the Test Flight Check Sheet be attotated with a specific reading Also a check for satisfactory perfor mance or an X for problem detected will be recorded and a statement catered in the remarks block of the Check heet 1 2 TM 55 1520 240 MTF g Maintenance Test Flight Check Sheet The Check Sheet contained Section V will be used for all test flights When a test flight is performed to determine if specific equip ment or systems are operating properly completion of only that portion of the maintenance test flight Check Sheet applicable to the specific equipment or systems being tested is required The aircraft test flight Check Sheets may be locally reproduced Continuation sheets may be used when necessary Items that prove to be unsatisfactory during the test flight and require cor rective action shall be listed in the remarks block during flight and transferred to DA Form 2408 13 immediately after ter mination of the flight The sheet will be attached to the DA Form 2408 13 upon completion After accumulation of two or more sheets the data should be reviewed to determine if trends are developing h
203. witch Longitudinal control position out of tolerance a AFCS malfunction DASH b longitudinal control position tolerance CPT incorrectly pulled c DASH actuator malfunction d Squat switch malfunction Airspeed signal inoperative fwd flt Pitot system or AFCS airspeed transducer CYCLIC TRIM inoperative in the AUTO position a Circuit breaker out b Faulty AFCS computer c Faulty LCT actuator s d Faulty wiring e Faulty AFCS panel switch 3 49 55 1520 240 CONDITION PROBABLE CAUSE K14 MANUAL CYCLIC TRIM inoperative K15 K16 K17 K18 a Circuit breaker out b Faulty LCT actuator c Faulty AFCS panel switch Airspeed does not return and hold a DASH actuator malfunction b AFCS malfunction C Airspeed system malfunction Lateral stick only turns not coordinated a AFCS malfunction Sideslip stabilization b Sideslip ports not open Heading selector inoperative a Aircraft not properly trimmed in level flight prior to engagement b HSI malfunction c AFCS panel switch malfunction d AFCS malfunction Barometric attitude hold out of tolerance a Collective CCDA malfunction b AFCS malfunction c Faulty AFCS panel switch 3 50 55 1520 240 SECTION IV SPECIAL PROCEDURES SPECIAL PROCEDURES This section contains special procedures which were referenced in Section II LIST OF PROCEDURES TITLE PAGE A AF
204. y computer display CDU Doppler MAL and MEM indicator lamps light in TEST MODE a Pitch roll or magnetic heading missing or in error b Signal converter faulty GPS Control Display Unit CDU C 1 1702 UR when in TEST mode does not display TEST IN PROG on display line 1 after one 1 minute Replace CDU C 11702 UR Display line 1 of GPS Control Display Unit CDU C 11702 UR displays anything but TEST COMPLETE after four 4 minutes of turning MODE switch of CDU to TEST a Replace Receiver R 2400 A CDU display line 2 reads RCV b Replace Control Display Unit CDU C 11702 UR CDU display line 2 reads CDU 1 c Replace Antenna Amplifier AM 7314 URN CDU display line 2 reads AE d Memory Batteries in Radio Receiver R 2400 A are low CDU display line 2 reads BT1 C 20 3 46 TM 55 1520 240 MTF J28 GPS system Four 4 satellites SAT not being tracked and estimated position error EPE less than 50 meters MI with keys loaded or less than 200 meters M with a cold start cannot be attained after Start Up a Replace Fixed Reception Pattern FRPA 3 Antenna AS 38221URN b Troubleshoot repair aircraft antenna cables J29 Data Display lighting on GPS Control Display Unit CDU C 11702 UR does not vary with CDU BRT Brightness control rotation Replace CDU C 117021UR 430 Panel lighting on GPS CDU C 1 1702 UR does not vary with aircraft dimmer control a Replace CDU C 117021UR b Faulty air

TM 1-1520-240-MTF - Chinook Helicopter

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