De Havilland Dash 7 Aircraft Operating Manual Download

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AIRCRAFT OPERATING MANUAL

DASH - 7

Summary of Contents for Dash 7

Page 1: ...AIRCRAFT OPERATING MANUAL DASH 7...

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Page 3: ...21 2012 LIST OF EFFECTIVE PAGE 5 of 5 6 February 21 2012 Revision to this Aircraft Operating Manual AOM for Dash 7 of Pelita Air Service has been reviewed and meets all applicable requirements set for...

Page 4: ...GM 4 2 2 2 2 2 4 2 6 FW OPERATION GM 5 3 3 3 5 3 7 RW OPERATION GM 6 4 6 4 8 DEPUTY OF MAINTENANCE 7 7 9 CHIEF PILOT 8 5 4 4 8 5 10 CHIEF FA 9 6 3 9 11 OPERATION CONTROL CENTER 10 7 3 4 5 5 10 6 12 TE...

Page 5: ...AIRCRAFT OPERATING MANUAL DHC 7 LIST OF HOLDER Revision Date 4 Mar 2011 PT PELITA AIR SERVICE AOM P a g e LOH 2 of 2 INTENTIONALLY LEFT BLANK PAGE...

Page 6: ...TION 0 INTRODUCTION 0 1 GENERAL 0 2 CONTENT 0 3 ORGANIZATION 0 4 LIST OF EFFECTIVE PAGES 0 5 REVISION 0 6 CONVENTION USED IN THE AOM SECTION 1 LIMITATION 1 1 GENERAL OPERATING LIMITATION 1 2 WEIGHT AN...

Page 7: ...CEDURE SECTION 3 NORMAL PROCEDURES 3 1 PREFLIGHT 3 2 BEFORE START 3 3 ENGINE START 3 4 AFTER START 3 5 TAXI 3 6 TAKE OFF 3 7 CLIMB AND CRUISE 3 8 DESCENT 3 9 APPROACH 3 10 LANDING 3 11 CIRCLING 3 12 M...

Page 8: ...NITION 7 3 AIRPLANE ACTUAL WEIGHTS AND BALANCE 7 4 PREPARATION FOR FLIGHT 7 5 USE OF FUSELAGE TAIL STEADY STRUT 7 6 WEIGHING INSTRUCTIONS SECTION 8 SYSTEM DESCRIPTIONS 8 1 AIRCRAFT GENERAL 8 2 ELECTRI...

Page 9: ...AIRCRAFT OPERATING MANUAL DHC 7 LIST OF CONTENT Revision D a t e 1 June 2007 PELITA AIR SERVICE AOM P a g e LOC 4 of 4 INTENTIONALLY LEFT BLANK PAGE...

Page 10: ...y 1 1999 0 7 July 1 1999 0 2 July 1 1999 0 8 July 1 1999 0 3 July 1 1999 0 9 July 1 1999 0 CASR 1 July 1 1999 0 10 July 1 1999 0 2 July 1 1999 0 11 July 1 1999 0 3 July 1 1999 0 12 July 1 1999 0 4 Jul...

Page 11: ...010 3 27 July 1 1999 0 41 Jun 26 2010 3 28 July 1 1999 0 42 Jun 26 2010 3 29 July 1 1999 0 43 Jun 26 2010 3 30 July 1 1999 0 44 Jun 26 2010 3 31 July 1 1999 0 45 Jun 26 2010 3 4 3 1 Jun 26 2010 3 46 J...

Page 12: ...99 0 7 July 1 1999 0 2 July 1 1999 0 8 July 1 1999 0 3 July 1 1999 0 9 July 1 1999 0 4 July 1 1999 0 10 July 1 1999 0 5 July 1 1999 0 11 July 1 1999 0 6 July 1 1999 0 12 July 1 1999 0 1 July 1 1999 0...

Page 13: ...0 14 July 1 1999 0 5 July 1 1999 0 15 July 1 1999 0 6 July 1 1999 0 8 14 1 July 1 1999 0 7 July 1 1999 0 2 July 1 1999 0 8 8 1 July 1 1999 0 3 July 1 1999 0 2 July 1 1999 0 4 July 1 1999 0 3 July 1 1...

Page 14: ...9 0 23 July 1 1999 0 24 July 1 1999 0 25 July 1 1999 0 26 July 1 1999 0 27 July 1 1999 0 28 July 1 1999 0 29 July 1 1999 0 30 July 1 1999 0 31 July 1 1999 0 8 16 1 July 1 1999 0 2 July 1 1999 0 9 1 Ma...

Page 15: ...DATE REV NO SECTION PAGE REVISION DATE 1 LEP 1 June 23 2007 1 1 4 June 23 2007 2 LEP 1 April 08 2010 2 LEP 2 April 08 2010 2 4 3 1 64 April 08 2010 3 LEP 2 June 23 2010 3 4 3 1 64 June 23 2010 4 LEP...

Page 16: ...7 Pilots Operating handling It is compiled and distributed by the FLIGHT OPERATION DEPARTMENT of PT Pelita Air Service Jakarta The contents of the DH 7 Aircraft Operating Manual must at all times com...

Page 17: ...S THE SECTIONS CARRY IDENTIFICATION NUMBERS AIRCRAFT OPERATING MANUAL DHC 7 1 INTRODUCTION AIRCRAFT TYPE Revision D a t e 1 Jun 2007 PT PELITA AIR SERVICE AOM P a g e F 2 of 12 USE OF ITS CONTENTS BY...

Page 18: ...DUCTION 1 LIMITATION 121 135 b 8 IV 121 135 b 9 2 EMERGENCY ABNORMAL PROCEDURES 3 NORMAL PROCEDURES 4 CHECKLIST 121 315 1 0 EXPANDED 2 0 NORMAL 3 0 EMERGENCY 5 PERFORMANCE 121 135 b IV b 9 6 FLIGHT PL...

Page 19: ...tion Safety Regulation and in the case of a flag or supplemental operation any applicable foreign regulation or the certificate holder s operations specifications or air operator certificate b The man...

Page 20: ...Section 121 403 16 Instructions and procedures for maintenance preventive maintenance and servicing 17 Time limitations or standards for determining time limitations for overhauls inspections and chec...

Page 21: ...arts of it accessible when performing assigned duties c For the purpose of complying with Paragraph a of this section a certificate holder may furnish the persons listed therein the maintenance part o...

Page 22: ...no certificate holder may use a person as a flight crewmember unless that person has completed windshear ground training and simulator training SUB PART T 121 539 Operations notices Each certificate...

Page 23: ...REQUIRED FOR SPECIFIC OPERATIONS BY THIS PART c Notwithstanding Paragraphs b 1 and b 3 of this section an airplane with inoperable instruments or equipment may be operated under a special flight permi...

Page 24: ...for implementing ground deicing anti icing operational procedures 121 647 Factors for computing fuel required Each person computing fuel required for the purposes of this subpart shall consider the fo...

Page 25: ...ake off weight considering anticipated fuel and oil consumption that allows compliance with the maximum authorized design landing weight limitations on arrival at the destination airport 4 Maximum tak...

Page 26: ...ncerning the aircraft limitations procedures checklists performance flight planning weight balance and systems 3 ORGANIZATION The manual is divided into chapters an index page in front of the manual l...

Page 27: ...ion number will be increased by one 6 CONVENTIONS USED IN THE AOM Some of the most important conventions used in this AOM are Notes are used for information that is considered essential to emphasize C...

Page 28: ...ON The de Havilland DHC 7 is certificated in the Transport Category in compliance with F A R Part 25 up to and including Amendment 31 It is eligible for the following kinds of operations 1 Day and nig...

Page 29: ...m 25 to 27 M A C From 44 000 lb to 44 100 lb 27 M A C Aft limit For all weights 43 M A C 1 2 3 LOADING INSTRUCTIONS The aircraft can be loaded normally i e e crew passengers fuel freight and baggage t...

Page 30: ...between left and right tanks is 600 lb 1 3 PERFORMANCE 1 3 1 OPERATIONAL LIMITS FOR VARIABLE FACTORS Maximum Operating Altitude 25 000 ft Maximum Operating Altitude with passengers 20 400 ft 1 3 2 AM...

Page 31: ...aps 15 147 Flaps 25 120 Flaps 45 110 3 Maneuvering Speed VA Full application of rudder and aileron controls and maneuvers that involve angles of attack near the stall should be confined to speeds belo...

Page 32: ...AOM P a g e 1 5 of 10 1 5 POWER PLANT LIMITATIONS 1 5 1 ENGINES Model PT6A 50 Ambient Temperature Limitations 54 C 65 F to 51 6 C 125 F Maximum Altitude for Air start 20 000 ft Manufacturer Pratt and...

Page 33: ...uires preheat before engine start 4 Advance condition lever or reduce generator and bleed load to avoid exceeding this limit 5 This value is time limited to 5 seconds 6 This value time limited to 20 s...

Page 34: ...mixed with Kerosene type fuel may be used in emergency Useable fuel Fuel remaining in fuel tanks when quantity indicators show zero fuel is not usable in flight 1 5 5 OIL Oil grade Oils which conform...

Page 35: ...ndicators Maximum starting thin red radial 1000 C 5 sec limit Maximum normal operation wide red radial and light 800 C Normal operating green arc 490 C 800 C Propeller RPM Indicators Maximum transient...

Page 36: ...hered ENGINE BLEED switches must be at OFF or LOW when operating in this configuration and T5 temperatures must not exceed 750 C while oil temperatures must not excee d maximum normal limit 99 C Susta...

Page 37: ...necessary all four engines may be operated with condition levers at MAX Sustained reverse thrust operation is limited to 1 1 2 minutes to avoid high engine nacelle temperatures Engines must be operat...

Page 38: ...CAUTION This information is specific to the malfunction and is used to supplement the normal operation of the aircraft The Landing precaution must be reviewed as part of the approach briefing Followin...

Page 39: ...at the pilot detecting a take off malfunction use the phrase CAUTION LIGHT and follow this with a short phrase describing the observed problem i e CAUTION LIGHT Air stair Door A take off shall be abor...

Page 40: ...L T HANDLE PULL Appropriate FIRE EXT DISCHARGE Select Emergency lights to ON Advise ATC For Emergency Equipments Reason of FIRE Fuel onboard Persons onboard If Evacuation is necessary Command by PA EV...

Page 41: ...m has established the PF shall call for the appropriate memory items if applicable e g FIRE SHUT DOWN ENGINE 4 The PNF performs the memory items which are confirmed by the PF After the PNF has complet...

Page 42: ...otate 8 deg nose up for Flap 15 or 25 Command GEAR UP Climb at minimum V2 Monitor speed At V1 Call ROTATE Advance Power Levers to MAX TORQ limits Cancel Master Caution Warning light Announce POSITIVE...

Page 43: ...LAP 0 SET IAS ALT SEL Respond IAS SET Command SHUTDOWN Respond CONFIRMED Respond CONFIRMED Respond CONFIRMED Identify and announce POWER LEVER FLT IDLE Identify and announce CONDITION LEVER SHUT OFF I...

Page 44: ...Identify and announce POWER LEVER FLT IDLE Identify and announce COND LEVER SHUT OFF Identify and announce FUEL T HANDLE PULL If fire FORWARD BOTTLE DISCHARGE If fire persist after 30 sec s AFT BOTTL...

Page 45: ...control the propeller Command PROPELLER OVERSPEED memory items Respond CONFIRMED Respond CONFIRMED Reduce Altitude as necessary Identify and announce POWER LEVER FLT IDLE Identify and announce COND LE...

Page 46: ...or less leave as selected Call POSITIVE rate select GEAR UP At or above 400 ft AGL Accelerate through VFRI On profile Command FLAP 15 FLAP 0 Command SET HDG ALT ft and ALT SEL Accelerate to Vclimb V2...

Page 47: ...control jam Maintain Airspeed Assist to dislodge control jam If unable to dislodge control jam Relax force on control wheel Command PITCH DISCONNECT PULL Pull and Rotate PITCH DISC T handle BOTH PILO...

Page 48: ...ll and Rotate ROLL DISC T handle BOTH PILOTS WILL NOW ATTEMPT TO CONTROL THE AIRCRAFT PILOT WITH CONTROL WHEEL PILOT NON FLYING Announce I HAVE CONTROL Command ROLL CONTROL JAM checklist Respond YOU H...

Page 49: ...VICE AOM P a g e 2 12 of 15 2 10 FLAPLESS LANDING There is no change to the normal landing SOP after the checklist has been executed An ILS approach is recommended in the event of a Flapless configura...

Page 50: ...ER LEVERS FLT IDLE COND LEVERS MAXIMUM Set F D VS Contact ATC and inform CABIN CREW Select DOME light if required Select SYNCHROPHASE OFF Select IGNITION MASTER MANUAL SEATBELT and SMOKING SIGN ON Sel...

Page 51: ...ited an overshoot climb gradient of 2 7 is guaranteed to obstacle clearance height or a minimum of 400 ft AGL At this time acceleration to VFRI Flap retraction speed occurs after which flap retraction...

Page 52: ...R levers to TAKE OFF select FLAP 25 if Flap 45 set Caution If Flap is already set at 25 or less leave as selected Observe and Announce POSITIVE RATE Select Landing Gear UP On Profile Command FLAP 15 F...

Page 53: ...all required documentations are on board Cockpit preparation shall be accomplished as a geographic flow ensuring the required items are executed Once the aircraft is ready for flight the Captain shall...

Page 54: ...ion and task sharing in the early recognition and resolution of an emergency can not be overemphasized A thorough TAKE OFF EMERGENCY BRIEFING can help to eliminate any subsequent confusion in the flig...

Page 55: ...nce STARTING 3 Starter Light On Voltage Drop Hydraulic Lt Out Hydraulic Press Rising At 12 20 NG select Condition lever to START and FEATHER Monitor and Call for Fuel flow Rising T5 Rising Stabilized...

Page 56: ...her SELECT green Engine intake deflectors CHECK light and visually Radar CHECK STAND BY Flaps SET for take off as briefed Rudder travel CHECK FULL Autopilot Yaw damper TESTED ON Flight director GA HDG...

Page 57: ...lush snow sand or other debris which can be ingested by the engines 2 Do not power back in heavy rain or other conditions which could result in loss of visual contact with the ground crew 3 It may be...

Page 58: ...or via the rudder pedals Turn should be made at low speed with as large as possible in order to minimize side loads on gear and tires Center the nose wheels before coming to a stop In order to avert...

Page 59: ...uring the take off roll should it become necessary to abort the take off prior to V1 The PF should release his hand from the Power Levers at V1 called by the PNF thereafter both his her hand shall pla...

Page 60: ...flap 15 8 deg nose up for flap 25 Monitor airspeed at V1 Vr Call V1 ROTATE Positive Climb Command GEAR UP Accelerate to V2 10 Call POSITIVE RATE Select Landing Gear UP At 400 ft AGL On profile comman...

Page 61: ...hart 1070 rpm High Speed then 2 5 KIAS 1000 ft Type II 150 KIAS to 15 000 ft as per chart 1070 rpm Int mediate then 2 5 KIAS 1000 ft Type III 125 KIAS as per chart 1070 rpm Slow Speed CRUISE as per ch...

Page 62: ...ILOT FLYING PILOT NON FLYING Command DESCENT checklist Execute checklist and respond DESCENT checklist complete Respond SET and CROSS CHECKED At transition level Announce ALTIMETER SET INDICATING FT S...

Page 63: ...approach b Chart date and page number c Minimum sector altitude and airport elevation d Inbound course and Nav frequency e Procedure turn altitude f Minimums DH or MDA g Time for FAF to MAP based on...

Page 64: ...IDE SLOPE ALIVE At 1 Dot below G S Command LANDING GEAR DOWN Confirm On Profile On Glide Slope Command FLAP 25 and LANDING checklist Call 1 DOT BELOW Select Landing Gear DOWN and observe GEAR DOWN lig...

Page 65: ...m Select LANDING GEAR DOWN observe GEAR DOWN lights and announce DOWN 3 GREEN Final track on slope On Profile Command FLAP 25 and LANDING checklist Select FLAP 25 and observe Indicator respond FLAP 25...

Page 66: ...LO Select LANDING GEAR DOWN observe GEAR DOWN lights Announce DOWN 3 GREEN On profile on slope Command FLAP 25 and LANDING checklist Respond to checklist items Confirm VFE Select FLAP 25 observe indic...

Page 67: ...gn the aircraft with the runway heading Aim for a positive touch down on the upwind wheels Counter the tendency for the upwind wing to lift by decisive use of ailerons 3 11 CIRCLING Circling maneuveri...

Page 68: ...Adjust Power NOT to Exceed MAX TQ Select FLAP 25 if flap 45 set Caution If Flap is already set at 25 or less leave as selected Observe and call POSITIVE RATE Select LANDING GEAR UP At or above 400 ft...

Page 69: ...his call also indicates that the Captain shall now assume control of the aircraft 3 13 1 After landing procedure PILOT FLYING PILOT NON FLYING At taxi speed Command CONTROL LOCKS Engage CONTROL LOCKS...

Page 70: ...n 3 Command all condition levers to FUEL SHUT OFF 4 Command to switch the SEAT BELT sign OFF 5 Command the SHUTDOWN checklist In certain circumstances Engine NO 4 may be kept running provided 1 Smokin...

Page 71: ...ERATORS OFF 06 FDR ELT CVR NORMAL AUTO TEST 07 PANEL LIGHTING AS REQUIRED 08 FUEL T handles PULLED CHECK PUSH IN NORMAL 09 FIRE SMOKE WARNING TESTED 10 WINDSHIELD WIPER HEAT OFF 11 ICE CONT PITOT STAT...

Page 72: ...42 ALT SET preselector SET 43 PROP AUTOFEATHER OFF 44 ENG INTAKE DEFLECTORS RETRACTED 45 ENGINE INSTRUMENTS CHECKED 46 PITCH ROLL DISC handles IN LOCKED 47 RADAR TRANSPONDER CHECKED STBY 48 GPS NAV C...

Page 73: ...11 CABIN PRESS CONTROL AUTO AUTO SET 12 ENGINE BLEED OFF 13 FASTEN BELT NO SMOKING ON ON 14 FLIGHT TAXI switch TAXI 15 CLOCKS ZEROED SET 16 AUTOPILOT SYS CPLG SELECTED 17 FLIGHT INSTR DME SET X CHECK...

Page 74: ...LIGHT OUT 03 DC VOLTS LOAD meters CHECKED 04 BATTERY TEMP CHECKED 05 ENGINE BLEED AS REQUIRED 06 EMERGENCY light ARM 07 FLIGHT DIRECTORS GO AROUND HDG ALT SET 08 P F C S light TEST NORMAL 09 PROP AUT...

Page 75: ...TAXI CHECKLIST COMPLETE LINE UP CHECKLIST Read Aloud DO RH 01 CONDITION levers 4 MAX RPM 02 PITOT STATIC W SHIELD HEAT ON WARM UP 03 ANTI COLLISION WHITE 04 AC GENERATORS 4 ON 05 ENGINE BLEED LOW 06 P...

Page 76: ...SET 2500 11 FASTEN BELTS AS REQUIRED 12 AFTER TAKE OFF CHECKLIST COMPLETE CRUISE CHECKLIST Challenge Response PNF 01 DC VOLTS LOAD meters CHECKED 02 CABIN PRESS CONTROL CHECKED 03 ALTIMETER SET X CHE...

Page 77: ...e Response PNF 01 SYNCHROPHASE OFF 02 TAXI Light ON 03 LANDING GEAR DOWN 3 GREEN 04 FLAPS 25 45 INDICATED 05 CONDITION Levers MAX RPM 06 CABIN WARN 07 LANDING CHECKLIST COMPLETE AFTER LANDING CHECKLIS...

Page 78: ...4 CONDITION levers 30 second FEATHER 05 ENGINE BLEED OFF 06 FASTEN BELT EMERG light OFF 07 RADAR DME G P S OFF 08 STBY A H CAGED 09 STEERING OFF 10 CONDITION levers FUEL SHUT OFF 11 ANTI COLLISION POS...

Page 79: ...through regulator several times with air knob at DILUTE and 100 position return knob to 100 d Remove Mask and turn emergency control knob to EMERGENCY Check for audible flow of Oxygen Return knob to N...

Page 80: ...ON VOLTS CHECKED Place Left and Right Battery switches to ON if no external power this will connect the Left and Right Batteries to their respective buses Minimum of 20 Volts required for internal sta...

Page 81: ...check 1 MASTER CAUTION light flashes CHECK FIRE DET caution light and all LOOP A and LOOP B light illuminate 2 Release SHORT TEST FIRE WARN switch and check all lights go out b SHORT TEST FIRE WARN sw...

Page 82: ...sition for 5 seconds 13 DC GENERATORS L ON Connects operating DC generators to respective main DC BUS TIE 14 DE ICE and ANTI ICE L CHECKED Ensure Pitot Heaters 1 and 2 and ACC switches are OFF Note Pi...

Page 83: ...er powered from the right essential DC bus to the Left 115 volt AC fixed frequency bus as a back up for the primary invert22er 20 AC GENERATORS R OFF The AC variable frequency system operates the prop...

Page 84: ...gency lights ON b Portable Emergency Light 1 With both EMER LTS switches select to ARM two charging indicator light become visible through emergency light reflection 3 Depress TEST button Airplane pow...

Page 85: ...M switch 1 Fire detection loops 2 Fuel auxiliary pumps 3 Ice control panel 4 Standby compass lighting 5 Engine fail 6 Propeller ground range 7 SPOILERS ROLL INBD ROLL OUTBD and GROUND 8 G N S annuncia...

Page 86: ...ll attitude information should reflect the aircraft attitude on the ramp approximately zero degrees in both axises 2 Flight Director attitude test switch press When press the sphere will show approxim...

Page 87: ...course indicator is also indicating same heading Compare heading with stand by magnetic compass 33 INTAKE DEFLECTOR L RETRACTED Intake deflectors should be retracted for normal operations 34 CONTROL D...

Page 88: ...elect ILS test switch to DN RT and note GS flag out of view Localizer needle indicates one dot right plus minus needle width Glide slope needle will indicate one dot down plus minus needle width d DME...

Page 89: ...instruments and air data computer to accessory and alternate no 3 static port 39 HYDRAULIC SYSTEM L CHECKED Gear down Flap zero Spoilers down should indicate approximately 3 qts 40 PARKING BRAKE L SE...

Page 90: ...SSES L R SECURED BEFFORE START I THROUGH FLIGHT 1 CIRCUIT BREAKERS L R CHECKED Each pilot checks the opposite overhead circuit breaker panels then check his own side circuit breaker panel 2 DC EXTERNA...

Page 91: ...generator with its switch at ON to supply it appropriate main bus At OFF position connects trip signal from each generator to its GCU to shutdown generating system 5 L and R BATTERIES L ON VOLTS CHECK...

Page 92: ...LEED AIR R OFF Ensure all Bleed air switches are selected OFF All engine bleed switches must be off for engine start 10 FASTEN BELT I NO SMOKING R ON Both Seat belt and No Smoking signs must be ON bef...

Page 93: ...liability engine s hours recording passenger manifest and a c load sheet 16 T O DATA BRIEFING PF COMPLETED Pre take off and emergency briefing shall be conducted to all flights All briefings should i...

Page 94: ...planes in close proximity that the engines are about to be started or are operating 2 DOORS WINDOWS L R CLOSED LIGHTOUT Verify that windows close and the Air stair Door and Emergency Bag Doors caution...

Page 95: ...ications to the ground personnel to disconnect the DC power line Power is supplied by internal aircraft generators 4 DC VOLT TEMP PF CHECKED a Check DC VOLTS indicator to all DC bus position b Check D...

Page 96: ...switch light is depressed momentarily SEL green lens illuminate to indicate system is powered b When Torque of all engines exceeds 2355 ft lbs and the no 1 and 4 power levers are advanced above 88 Ng...

Page 97: ...e autopilot controller 1 The autopilot should disengage and the AP ENGAGE switch light goes out 2 The AUTOPILOT DISENGAGED caution light illuminates b Monitor the PFCS indicator for rudder deflection...

Page 98: ...Turn the AC generators 1 and 4 ON and check the 1 and 4 AC GEN caution lights out TAXI 1 TAXI LIGHT R ON 2 BRAKES L R CHECKED Each pilot checks their respective brakes 3 FLAPS PF 15 25 INDICATED Chec...

Page 99: ...S HEAT R ON WARM UP 4 ALL AC GENERATORS R ALL 4 ON All AC GEN cautions light out 5 BLEED AIR R LOW All bleeds to low or OFF if required 6 GROUND RANGE LIGHTS L CHECKED Check blue ground range light 1...

Page 100: ...the cabin crew that the take off is imminent and they should take their seats AFTER TAKE OFF 1 LANDING GEAR PNF UP LIGHT OUT Check that Landing position Tail Bumper and Landing gear lever lights are a...

Page 101: ...I COLLISION PNF RED 2 PRESSURIZATION PNF CHECKED Check for maximum differential and cabin altitude 3 CRUISE POWER PNF SET DESCENT 1 MIN SECTOR ALT L R CHECKED Both pilots should check minimum Sector A...

Page 102: ...select POWER levers to DISC on towards MAX REVERSE ensuring torque limit is not exceeded in reverse Return POWER lever to DISC before airplane stops to prevent roll back 6 LDG DATA BRIEFING PF BUG SET...

Page 103: ...r lights out Note If Flap fails to extend following selection to 15 or 25 return FLAP selector lever to 0 to limit rudder travel appropriate to the zero flap position 3 FLAPS PNF 25 45 INDICATED Check...

Page 104: ...ition 9 ALL AC GENERATORS R OFF Switch 1 2 3 4 AC GEN switch to OFF AFTER PARKING Through Flight 1 PARKING BRAKE L SET Pull Emergency Park Brake Lever full aft to Park position 2 TAXY LIGHT L OFF 3 PO...

Page 105: ...f to engines 9 SEATBELT R OFF Turn the seatbelt sign OFF This notifies the passengers that may now prepare to disembark 10 EMERGENCY LIGHT R OFF Switch OFF the emergency light 11 L R BATTERIES L OFF D...

Page 106: ...SE LAST FLIGHT 1 E L T R OFF E L T is disarmed 2 ANTI SKID R OFF Anti skid is turned off and anti skid caution light are on 3 CLOCK L R RESET ZERO TRAFFIC PATTERN CHECKLIST Ldg Gear UP Flaps UP Auto F...

Page 107: ...NDICATED Check that flap selector lever is in zero position and flap position indicator indicates flap zero 3 PROP AUTO FEATHER PNF OFF Depress auto feather switch light Check SEL and ARM lights go cu...

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Page 173: ...64 0 60 deg Bank 0 45 deg Bank 15 20 deg Bank 25 20 deg Bank 136 115 80 73 02 MAXIMUM CONTINUOUS POWER For deflectors EXTENDED Subtract 0 25 Prop Np 1210 Press Alt 30 20 10 05 0 05 10 15 20 25 30 SL 2...

Page 174: ...180 245 235 225 210 200 44 000 42 000 40 000 38 000 36 000 34 000 155 145 130 120 100 170 160 145 135 115 185 170 160 150 130 195 185 175 165 145 210 200 190 180 165 225 215 205 195 180 04 TWO ENGINE...

Page 175: ...00 36 000 35 000 34 000 33 000 32 000 3450 3150 3050 2900 2800 2700 3400 3100 3000 2850 2750 2650 3350 3050 2950 2800 2700 2600 3300 3000 2900 2750 2650 2550 3250 2950 2850 2700 2600 2500 3200 2900 28...

Page 176: ...140 206 9 11 27 148 366 10 24 150 318 9 22 147 289 8 19 139 258 8 19 142 233 10 12 30 150 413 11 28 150 358 10 25 150 323 9 21 140 288 9 21 143 260 11 16 40 150 474 13 35 150 408 12 30 150 365 10 24...

Page 177: ...1 1870 223 1874 223 1875 224 1876 8 220 1821 222 1823 224 1826 225 1825 225 1828 9 220 1782 221 1776 223 1780 225 1783 225 1783 10 219 1733 221 1730 223 1734 225 1737 225 1739 11 218 1684 220 1684 222...

Page 178: ...1580 196 1540 194 1500 191 1460 8 201 1590 199 1550 197 1510 195 1470 193 1430 9 203 1568 201 1528 199 1488 197 1448 195 1408 10 205 1545 203 1505 201 1465 199 1425 197 1385 11 207 1523 205 1483 203...

Page 179: ...iate IAS 185 kts ISA 15 Flt Level Time minutes Distance nm TAS kts Fuel lbs R E M A R K S 100 07 24 206 120 Taxy 200 lbs 105 08 25 188 130 Approach 200 lbs 110 08 27 203 140 Holding 1250 lbs 115 09 28...

Page 180: ...B CRUISE and DESCENT The optimization process is based on the following enroute performance data a Climb 1 TYPE I High Speed ii TYPE II Intermediate Speed iii TYPE III Low Speed b Cruise i Maximum Cru...

Page 181: ...block time minimum block fuel and minimum cost technique MIN BLOCK TIME MIN BLOCK FUEL MIN COST TECHNIQUE TECHNIQUE TECHNIQUE Block Time 113 2 min 126 4 min 116 8 min Block Fuel 3638 lb 2875 lb 3141...

Page 182: ...AIRCRAFT OPERATING MANUAL DHC 7 6 FLIGHT PLANNING Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 6 3 of 8 6 5 MINIMUM BLOCK TIME TEHNIQUE Take Off Weight 44 000lbs...

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Page 188: ...AIRCRAFT OPERATING MANUAL DHC 7 7 WEIGHT BALANCE Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 7 1 of 17...

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Page 192: ...mum Landing Weight 42 000 lb Maximum Zero Fuel Weight 39 000 lb b JACKING All jacking points are designed for lifting an airplane at maximum ramp weight when loaded within the approved Center of Gravi...

Page 193: ...the Operational Weight Empty plus Payload and water methanol if applicable exceed the Maximum Zero Fuel Weight 7 2 4 MAXIMUM ZERO FUEL WEIGHT Maximum Zero Fuel Weight is the maximum weight authorized...

Page 194: ...AL ARM AND REFERENCE DATUM The term Horizontal Arm for the DHC 7 is synonymous with airplane station The Reference Datum Horizontal Arm 0 Airplane Station 0 is located 248 0 inches forward of fuselage...

Page 195: ...should be recorded in the Basic Weight Change Record so that an accurate current record of the weight and C G is available at all times The obligation that all changes must be recorded in the Basic W...

Page 196: ...Change Record form at the end of Section 2 of this manual The cargo passenger configuration is changed then the Basic Weight and Moment Change Record form must always be amended to suit example of suc...

Page 197: ...ding Manifest although accurate may be considered tedious the Weight and Balance Trim Sheet has therefore been devised as a more expeditious method of calculating loadings A sample Trim Sheet is shown...

Page 198: ...AIRCRAFT OPERATING MANUAL DHC 7 7 WEIGHT BALANCE Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 7 11 of 17...

Page 199: ...ing gear jacking points be used in preference to wing and fuselage Note It may be necessary to replace the nose gear jacking point fitting with special adaptor Pt No 71300167 101 when weighing the air...

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Page 203: ...Weight 44 000 lb Maximum Landing Weight 42 000 lb Maximum Zero Fuel Weight 39 000 lb GENERAL DATA Mean Aerodynamic Chord M A C 117 84 inches Distance from Fuselage Structural Datum to Leading Edge of...

Page 204: ...AIRCRAFT OPERATING MANUAL DHC 7 7 WEIGHT BALANCE Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 7 17 of 17...

Page 205: ...enger and cargo transportation and maritime reconnaissance It seats up to 54 passengers and one or two flight attendants in addition to the two pilots and flight observer In cargo configuration the ai...

Page 206: ...y exit on unmodified airplanes Baggage Compartment The pressurized baggage compartment is in the upswept aft section of the fuselage It is located aft of the cabin bulkhead and immediately forward of...

Page 207: ...ectrical output is 115 VAC 400 Hz and 26 VAC 400 Hz LIGHTING The lighting package used on the Dash 7 includes lighting for interior and exterior areas Interior lighting is used to illuminate the cockp...

Page 208: ...rotection and fire detection and extinguishing systems The engine is rated at 1 120 shaft horsepower The PT6A series engines are lightweight gas turbine engines which use two independent turbines moun...

Page 209: ...red for system operation is supplied by the engine bleed air system Pressurization is accomplished by limiting the escape of the conditioned air from the cabin by means of outflow valves which are con...

Page 210: ...spoiler system Aerodynamic assistance to aileron movement is provided by a geared tab on each aileron A trim tab located on the right aileron also provides roll trim Directional control is maintained...

Page 211: ...and the cabin altitude differential pressure indicator The static source selectors provide for the selection of an alternate static source to the flight instruments and ADCs AVIONICS Dual VHF COMMs a...

Page 212: ...ists of dual outlet portable cylinders and continuous flow masks in foam blocks stowed in bins under the wing in the cabin Each foam block contains three portable cylinders and six masks LIMITATIONS T...

Page 213: ...MAC From 42 000 to 44 000 lb Varies linearly from 25 to 27 MAC From 44 000 to 44 100 lb 27 MAC Aft limit for all weights 43 MAC Loading Limits Loading limits in the aft cargo compartment 2 200 lb NOT...

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Page 217: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 1 Jun 2011 PT PELITA AIR SERVICE AOM P a g e 8 1 13 of 22 LIST OF CARGO PASSENGER INTERIOR ARRANGEMENTS...

Page 218: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 1 Jun 2011 PT PELITA AIR SERVICE AOM P a g e 8 1 14 of 22 LIST OF CARGO PASSENGER INTERIOR ARRANGEMENTS...

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Page 227: ...ators operated by the No 3 and No 4 engines Each main bus is also connected to an associated 40 AH battery A bus tie connects the left and right main buses The contactors are controlled by a bus bar p...

Page 228: ...2 3 and 4 DC GEN if any of them illuminates indicate that the associated generator is not connected to its associated buses DC METER A DC voltmeter and load meter are located to monitor system perform...

Page 229: ...generator to replace a failed one automatically A generator control unit GCU which governs the functions of voltage regulation over voltage under voltage under frequency differential current and gene...

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Page 237: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 2 11 of 11...

Page 238: ...nstalled in each wingtip together with the position lights WINGTIP STROBE LIGHTS A strobe light is located in each wingtip in the same housing as the red and green position lights The strobe lights ar...

Page 239: ...d console and the flight attendant s EMER LIGHTS switch located on the flight attendant s panel On airplanes with Mod 7 1697 the flight attendant s switch is replaced with a guarded two position switc...

Page 240: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 3 3 of 6...

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Page 244: ...The caution lights are triggered by a fault in the system being monitored or by actuating the TEST switch Amber caution lights indicate situations that require action appropriate to the associated sy...

Page 245: ...8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 4 2 of 3 AURAL WARNING SYSTEM The aural warning system produces various sounds associated with airplane conditions th...

Page 246: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 4 3 of 3...

Page 247: ...STORAGE Fuel is stored in four separate integral tanks two in each wing The outboard tanks have a greater capacity than the inboard tanks The inboard end of each tank is partitioned off to form a coll...

Page 248: ...el feed system Each valve is closed by pulling the associated PULL FUEL OFF handle on the overhead fire protection panel REFUELING DEFUELING SYSTEM The refueling defueling system provides for the pres...

Page 249: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 5 3 of 5...

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Page 251: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 5 5 of 5...

Page 252: ...propeller rpm Each power plant includes ice protection and fire detection and ex tinguishing systems ENGINE The PT6A 50 is a lightweight gas turbine engine which uses two independent turbines mounted...

Page 253: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 6 2 of 23...

Page 254: ...the mixture of air and fuel Turbine The compressor and compressor turbine together are termed the gas generator and supply expanding gases that are used for power extraction The power turbine is coupl...

Page 255: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 6 4 of 23 The direction of rotation is clockwise as viewed from the rear...

Page 256: ...he accessory case forms a cavity between the forward side of the case and the aft wall of the compressor inlet case This cavity forms the engine oil tank The gas generator turbine shaft extends throug...

Page 257: ...nd a high pressure bleed valve located on the left and right sides of the engine respectively The function of the surge bleed valves is to dump interstage compressor air overboard to prevent compresso...

Page 258: ...hedule in response to varying atmospheric conditions and power lever positions The governing section controls gas generator rpm N0 Power lever positions are transmitted as mechanical inputs to vary a...

Page 259: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 6 8 of 23...

Page 260: ...des warning of a critical decrease in fuel pressure and the necessity of switching on the appropriate auxiliary pump A fuel flow indicator shows the actual fuel flow at the engine fuel control unit IG...

Page 261: ...sensed as a fore and aft flexing of a helical ring gear balanced against oil pressure The movement modulates an oil pressure valve and the resultant oil pressure is sent from a transducer to an indica...

Page 262: ...speed propellers operate in three ranges under speed overspeed and on speed Under speed is the range of operation in which the actual rpm is less than the selected rpm Overspeed is the range of opera...

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Page 268: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 6 17 of 23...

Page 269: ...r spring position RPM is thus selected by the force exerted by the spring OVERSPEED GOVERNOR Propeller overspeed protection is supplied by an independent preset overspeed governor on each engine and i...

Page 270: ...nor and allows the counterweights and dome spring washers to feather the propeller An interlock feature prevents auto feathering of the remaining propellers once the system has feathered one propeller...

Page 271: ...FEATHER TEST switch Hold at TEST b Advance the power levers above 2 400 foot pounds of torque and check that The ARM light comes on c Retard one power lever to FLT IDLE and check that the propeller of...

Page 272: ...limit values for the markings TORQUE PRESSURE Engine torque pressure is the primary thrust indicator for the airplane Torque is sensed by the hydro mechanical torque meter in the first stage reduction...

Page 273: ...ever and the condition lever One additional control for all four engines which is normally operated automatically is the power lever flight idle gate POWER LEVERS Each of the four power levers control...

Page 274: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 6 23 of 23...

Page 275: ...l fire detection loops designated loop A and loop B The loops are sensing elements that show a change in resistance with a change in temperature The resistance of each element of the loop decreases pr...

Page 276: ...loop NOTE During single loop operation the monitoring circuit of the active loop will not warn of an electrical power failure Master Fire Warning A flashing red ENGINE FIRE switch light is located on...

Page 277: ...re Detection System Test On early airplanes the detection system is tested by a switch on the fire protection panel When held in the TEST position the ENGINE FIRE and MASTER CAUTION lights flash In ad...

Page 278: ...NG test switch Holding the switch in the TEST 1 or TEST 2 position illuminates the AFT BAG SMOKE light to indicate serviceability of each detector Circuit Lavatory Smoke Detection System The lavatory...

Page 279: ...n engine fire is indicated by the illumination of the PULL FUEL OFF light in the fire con trol T handle Pulling the handle accomplishes the following actions for that engine Fuel supply shutoff Hydrau...

Page 280: ...ights and prevent further illumination of the armed lights for that bottle until it is recharged Normally the forward bottle is discharged first If the fire persists as indicated by continued illumina...

Page 281: ...t cause cold burns harm fabrics or metals or leave residue The extinguishers are retained in quick release brackets Extinguisher operation consists of sliding a red safety latch down and pointing the...

Page 282: ...e compressors of all engines and is automatically supplemented as required by the high pressure HP compressors Bleed air is used for cabin pressurization air conditioning and wing tail and engine inta...

Page 283: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 8 2 of 4...

Page 284: ...vel the high bleed pressure switch opens and closes the high pressure bleed shutoff valve Temperature Control Valve The temperature control valve is electrically tied to the associated ENGINE BLEED sw...

Page 285: ...acelle which directs a greater flow of high pressure bleed air into the main duct This occurs only when the ENGINE BLEED switches are positioned to HIGH The normal rated takeoff performance is based o...

Page 286: ...ted thermostatically controlled electric heating blankets are installed around temperature control valves and deicer regulating valves Each thermostat closes at a decreasing temperature of 10 2 C 50 5...

Page 287: ...is above 10 C A three position propeller timer switch marked TIMERS is provided for selection of the timer 1 above 10 C cycle timer 1 below 10 C cycle or the backup No 2 timer When Mod 7 2339 is inco...

Page 288: ...will also come on un till both indicator thermostats reach operating temperature The indicator thermostats operate within a lower temperature range than the control thermostats so that normal cycling...

Page 289: ...ching on the system a WARM UP mode is selected which supplies 115 volts to both windshields series connected accordingly with reduced heat dissipation In the NORMAL operating mode each windshield circ...

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Page 293: ...by the automatic modulation of turbine bypass valves and pack bypass valves in response to signals from temperature sensors in the ducts cabin or flight compartment In manual mode the bypass valves a...

Page 294: ...the sills below the side windows An optional controlled diverter valve may be installed to permit additional heat to the flight compartment The valve is installed in the supply duct from the right pac...

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Page 296: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 10 4 of 6...

Page 297: ...h a check valve which connects the ram air plenum directly to the conditioned air outlet duct from the pack by passing the air cycle machine OPERATION During normal operation on the ground with engine...

Page 298: ...lane provide air circulation for cooling the avionics equipment A switch on the first officer s side panel provides for automatic or manual control of the fans and a caution light indicates an avionic...

Page 299: ...lue sufficiently to cause a greater air discharge through the emergency outflow valve and a consequent purging of the air forward through the cabin and flight compartment Such disruption of normal air...

Page 300: ...titude OPERATION DURING DESCENT AND LANDING During descent cabin altitude decreases at the rate determined by the rate of change selected towards a cabin altitude selected for the destination On appro...

Page 301: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 11 3 of 3...

Page 302: ...quantity indicator for each system are located on the captain s instrument panel Low pressure warning is provided by an ENG HYD PUMP caution light which is illuminated on a decreasing pressure of 200...

Page 303: ...l located on the overhead panel The handle is pulled to close the valve in the event of engine fire or for maintenance purposes AUXILIARY HYDRAULIC SYSTEM GENERAL The auxiliary hydraulic system is pro...

Page 304: ...s include landing gear wheel brakes and antiskid emer gency parking brakes nose wheel steering roll spoilers ground spoilers wing flaps rudder boost and tail bumper Application of hydraulic power to t...

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Page 309: ...ition Series connected landing gear weight switches prevent retraction of the gear before the shock struts reach full extension on take off Landing gear indicator lights denote locked up and down cond...

Page 310: ...c sub circuit closes and opens the doors with the gear extended Two sequence valves in the sub circuit are actuated mechanically by the nose gear to direct hydraulic pressure in a sequential manner to...

Page 311: ...rn is automatically silenced b Flaps selected to either 25 or 45 degrees power levers No 1 and or No 4 retarded below 80 Ng and any landing gear unit not locked down In this configuration the horn can...

Page 312: ...a maximum range of 7 50 each side of center position The nose wheel steering system is controlled by a STEERING ON OFF switch located on the captain s left console When the switch is selected to ON an...

Page 313: ...peeds below a threshold speed of 5 15 knots when full brake pressure is available to the main wheels Safety features of the system provide protection from wheel lock tire damage at touchdown and autom...

Page 314: ...ion Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 13 6 of 15 Pilot control of the anti skid system is from an ANTI SKID switch on the glare shield panel Caution lights provide indication of fai...

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Page 324: ...operated by both No 1 and No 2 hydraulic systems to augment aileron roll control ROLL CONTROL In conjunction with hydraulically powered roll spoilers conventional cable and pulley operated ailerons ef...

Page 325: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 14 2 of 12...

Page 326: ...YD caution light illuminates the appropriate ROLL SPOILER PRESSURE switch should be selected to OFF Illumination in flight of a ROLL SPLIR INBD GND or ROLL SPLIR OUTBD GND caution light is indicative...

Page 327: ...ich requires operation of both valves to allow hydraulic pressure to extend the appropriate inboard or outboard pair of spoilers Failure affecting an inboard roll spoiler results in the outboard spoil...

Page 328: ...eration of the fore rudder is restricted to 11 50 left or right of center with flaps at 0 by an interconnect mechanism between flap selector lever and rudder pedals At speeds in excess of 130 knots ya...

Page 329: ...rudder quadrant speed signals from the air data computer systems restrict the yaw damper authority to 1 5 rudder di splacement to left and right at speeds exceeding 130 knots Below 130 knots the yaw...

Page 330: ...does not occur until trailing flaps have retracted to 250 To arrest an uncontrolled flap retraction and consequent runaway condition at large flap angles caused by separation of the primary transmiss...

Page 331: ...r lever on the right end of the center console moves in a slot with marked 0 15 and 25 degree positions The 45 degree position is obtained by pulling the lever upward at the 25 degree position and the...

Page 332: ...t to flight mode indicated by the three SPOILERS advisory lights going out The FLIGHT TAXI switch TAXI position is held magnetically through the micro switches operated by No 2 and No 3 power levers i...

Page 333: ...event possible shaker operation during taxiing Landing gear down lock relays interrupt pendulous accelerometer signals during flight with landing gear retracted The lift transducers are electrically h...

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Page 336: ...rry 26 VAC 400 Hz 115 VAC 400 Hz and 28 VDC The pitot static system includes three pitot tubes and four static vents The system is integral with the dual air data system The air data system uses air m...

Page 337: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 15 2 of 31...

Page 338: ...pitot tube and supplies the overspeed switch A static vent plate is mounted on each side of the forward fuselage Each plate has four static ports corresponding left and right side static ports are int...

Page 339: ...es the signals for the copilot s altimeter and flight director computer No 2 ATC transponder if installed autopilot yaw damper and flight data recorder FLIGHT INSTRUMENTS GENERAL The pilot s and copil...

Page 340: ...annunciator An altitude alert light is located in the upper right corner of the instrument bezel It illuminates when the airplane is within 1 000 feet of the preselected altitude and extinguishes when...

Page 341: ...00 feet by a digital counter and a pointer read against a dial The pointer makes one revolution of the dial per 1 000 feet Gradations in 20 foot increments are numbered at 100 foot intervals The count...

Page 342: ...by the pilot The fast erection mode may be used when it is suspected that a gyro has drifted or tumbled When the VG FAST ERECT switch on the left or right GYRO CONT panel is pressed and held in the o...

Page 343: ...pilot s instrument panel The left and right units are powered from the left and right essential DC buses respectively A red failure flag comes into view when power falls below a minimum required pres...

Page 344: ...viding three axis reference which may be used for flight control during climb cruise descent and terminal area guidance The AFCS may be used for Fully automatic flight control The autopilot responds t...

Page 345: ...ed visually to the pilots on the ADI and are avail able for use by the autopilot A full complement of horizontal vertical radio aid tracking and air data oriented modes are available The flight direct...

Page 346: ...tional DME indicators and also incorporated into multipurpose displays Actuation of the MLS button on the mode selector transfers the source of displayed deviation signals on the The MLS will initiall...

Page 347: ...ding hold mode If the autopilot is engaged while the airplane is in a bank the system engages wings level once the bank angle is less than 3 0 for ten seconds the heading hold mode is engaged Roll hol...

Page 348: ...AIRCRAFT OPERATING MANUAL DHC 7 8 SYSTEM DESCRIPTION Revision Date 0 July 1999 PT PELITA AIR SERVICE AOM P a g e 8 15 13 of 31...

Page 349: ...nchronizes the flight director pitch command bar to the new airplane pitch attitude SOFT RIDE Switch The SOFT RIDE function provides lowered autopilot gains for operation in turbulence TRIM Annunciato...

Page 350: ...he autopilot TEST EACH FLT pushbutton on the autopilot controller when below 130 KIAS Selection of go around mode Pulling the AP DC circuit breaker Pulling the YD AC circuit breaker Transferring AFCS...

Page 351: ...OR and RNAV are controlled by individual controls on the center pedestal and glareshield The DME s are selected simultaneously by respective VOR receiver selection An optional microwave landing system...

Page 352: ...erational when a VOR frequency is set on either NAV control unit When a VOR frequency is set in NAV 1 a DME frequency is paired and automatically tuned to it When a LOC frequency is set in either NAV...

Page 353: ...r transmitter the digital indicator and the antenna unit The Dash 7 weather radar is an X band radar designed for weather detection and analysis The indicator displays storm intensity levels in bright...

Page 354: ...e eyes and tender organs of the body therefore personnel should remain at a distance greater than six feet from the radiating antenna For radar operation the No 2 vertical gyro must be erect to provid...

Page 355: ...system provides the pilot copilot and observer with the means of monitoring all the airplane communications and navigation receivers The system allows transmission on the communications radios from t...

Page 356: ...nsmitter top pushbuttons is selected by pressing the appropriate pushbutton and canceled by pushing any other transmitter pushbutton The desired receiver is selected by pushing the receiver pushbutton...

Page 357: ...ght attendant s service interphone panel is located on the inboard edge of the bulkhead forward of the airstair door A handset is also located adja cent to the flight attendant s folding seat on the l...

Page 358: ...the radio altimeter No 1 ADC No 1 glide slope receiver and landing gear and flap position switches The inputs are continuously processed to provide airplane flight path surveillance when between 50 an...

Page 359: ...Takeoff Penetration of the altitude loss warning threshold results in both PULL UP lights coming on and a repeating aural don t sink The warning envelope is active from 65 to 700 feet AGL during takeo...

Page 360: ...etween the altitudes of 1 000 and 50 feet The mode will not function again until 1 000 feet or 50 feet have been transitioned No visual warnings are associated with mode 6 The mode 6 voice alert can b...

Page 361: ...DFDR RECORDER caution light goes out indicating that the system is operational COCKPIT VOICE RECORDER The cockpit voice recorder CVR microphone and controls are located on the overhead console The re...

Page 362: ...on the unit comes on to indicate that the ELT is transmitting Maximum range is assured if the antenna is held vertically never point the antenna toward search aircraft because transmission will be de...

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Page 367: ...nger on the bulkhead behind the pilot and copilot s seats Each crewmember s mask incorporates a dynamic microphone a diluter demand regulator a diluter demand valve and a flexible oxygen line The dilu...

Page 368: ...ating an on off selector The regulator body also includes a pressure gage safety discharge indicator with a frangible disc and two outlets with quick disconnects A carrying strap is attached to each c...

Page 369: ...BS Air Traffic Control Radar Beacon System MODE A MODE C and MODE SELECT MODE S interrogations The MODE S function is capable of being discretely addressed so that interrogation can be directed to a s...

Page 370: ...intruder and an aural and visual traffic advisory is issued This level calls attention to a developing collision threat using the traffic advisory TA indicator and the voice message TRAFFIC TRAFFIC I...

Page 371: ...If the flight crew is advised by ATC to disable transponder altitude reporting TCAS will be turned off by returning MODE selector switch on the MODE S control to ON and TOAS OFF will be displayed on T...

Page 372: ...Once a RA has been issued safe separation could be compromised if current vertical speed is changed except as necessary to comply with the RA This is because TCAS Il to TOAS II coordination may be in...

Page 373: ...2 The altitude displayed during test should be the same as the altimeter 3 The TA RA VSI indicators should present a test pattern display like Figure 3 on page 21 4 After completion of self test TOAS...

Page 374: ...is condition occurs the TCAS II system will automatically go into the TA ONLY mode the TCAS audio alerts will be inhibited and any displayed RA s will become TA s 7 TRAFFIC ADVISORY TA ONLY SELECTION...

Page 375: ...command without flying into stall warning or buffet Conditions where this may occur include but are not limited to Bank angle in excess of 15 degrees Operation at airports outside 0 5300 feet MSL or...

Page 376: ...GO AROUND THRUST FLAPS RETRACT TO GO AROUND POSITION PITCH AS REQUIRED TO COMPLY WITH RA GEAR UP WITH POSITIVE RATE OF CLIMB If a stick shaker occurs during an RA maneuver immediately abandon the RA...

Page 377: ...ing MODE switch to ON on the ATC MODE S control panel will automatically cause TCAS to be in standby TCAS OFF on TA RA VSI indicators 9 TCAS II SYSTEM TRAFFIC ADVISORY TA ANNUNCIATIONS Traffic advisor...

Page 378: ...of 20 10 TCAS II SYSTEM RESOLUTION ADVISORY RA ANNUNCIATIONS Resolution advisories RA threat aircraft are shown on the TAIRNVSI indicator Figure 3 on page 21 as RED filled squares representing the in...

Page 379: ...11 of 20 11 TCAS II SYSTEM ENHANCED RESOLUTION ADVISORY RA ANNUNCIATIONS Enhanced resolution advisories RA will be annunciated aurally and on the TA RA VSI indicator when the initial resolution adviso...

Page 380: ...No 1 is no longer available turn TCAS to STBY or OFF TCAS will no longer be operable c If the ACT light flashes continuously on the ATC control panel when 1 2 switch is in either position select STBY...

Page 381: ...ating an RA or TA but which is within six nautical miles nm slant range and within 1200 feet vertically d Traffic Advisory TA Information given to the pilot pertaining to the position of intruding air...

Page 382: ...AIRCRAFT OPERATING MANUAL DHC 7 9 SUPLEMEN Revision Date 0 Mar 2011 PT PELITA AIR SERVICE AOM P a g e 9 14 of 20 2 ATC CONTROL FUNCTIONS...

Page 383: ...AIRCRAFT OPERATING MANUAL DHC 7 9 SUPLEMEN Revision Date 0 Mar 2011 PT PELITA AIR SERVICE AOM P a g e 9 15 of 20...

Page 384: ...AIRCRAFT OPERATING MANUAL DHC 7 9 SUPLEMEN Revision Date 0 Mar 2011 PT PELITA AIR SERVICE AOM P a g e 9 16 of 20 3 TCAS CONTROL FUNCTIONS...

Page 385: ...UAL DHC 7 9 SUPLEMEN Revision Date 0 Mar 2011 PT PELITA AIR SERVICE AOM P a g e 9 17 of 20 TCAS II TA RAA SI RESOLUTION ADVISORY F OR FUNCTIONS TCAS II TA RA VSI Traffic and Resolution Advisory TA RAI...

Page 386: ...extreme 6000 FPM to 1 500 FPM as shown in Figure 4 page 23 The GREEN fly to area appears from 1500 FPM to 2000 FPM A Preventive Resolution Advisory is issued when the TCAS aircraft s present vertical...

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Page 388: ...AIRCRAFT OPERATING MANUAL DHC 7 9 SUPLEMEN Revision Date 0 Mar 2011 PT PELITA AIR SERVICE AOM P a g e 9 20 of 20...

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De Havilland Dash 7, Aircraft Operating Manual

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