Gulfstream Aerospace 1978 AA 5A CHEETAH Pilot Operating Handbook Download

Page: 107 / 190

Summary of Contents for 1978 AA 5A CHEETAH

Page 1: ...TAH 1977 1197 11979 THIS HANDBOOK INCLUDES THE MATERIAL REQUIRED TO BE FURN SH 9 TO TI1E PILOT BY FA PART 23 SERIAL O _ _ _ _ __ REGISTRATION NO _ _ _ __ J QII Gulfstream e Corporation Ac arraa 91MPANY Savannah Georgie U S A Issued January 15 1977 Revision 4 March 2 1988 ...

Page 2: ...ht to reproduce this publication No part may be reproduced stored in any retrieval system or transmitted in any part or form or by any means electronic photoCopying microfilm microfiche mechanical or otherwise without prior written pe mission of Gulfstream Aerospace Corporation ...

Page 3: ...3 1 1 thru 1 2 0 1 3 3 L 1 4 1 1 5 thru 1 12 0 2 1 0 2 2 Blank 0 2 3 3 2 4 thru 2 5 0 2 6 4 2 7 thru 2 8 0 2 9 thru 2 12 1 3 1 thru 3 4 0 3 5 2 3 6 thru 3 17 0 3 18 1 4 1 thru 4 2 0 4 3 3 4 4 thru 4 7 0 4 8 thru 4 9 1 4 10 0 4 11 1 4 12 0 4 13 1 l 4 14 thru 4 21 0 I 4 22 1 Page No Revision No 4 23 0 4 24 1 4 25 0 4 26 Blank 0 5 1 0 5 2 Blank 0 5 3 thru 5 14 0 5 15 i 4 5 16 thru 5 18 0 5 19 2 5 20 ...

Page 4: ...e No Revision No 9 1 0 9 2 Blank 0 9 3 0 9 4 Blank 0 10 1 thru 10 2 0 10 3 3 104 thru 10 7 0 10 8 2 10 9 thru 10 16 0 Zero In this column Indicates an original page B GULFSTREAM AEROSPACE MODEL AA 5A CHEETAH Revised March 2 1968 ...

Page 5: ...usine s flying This handbook has been prepared to help you obtain the maximum pleasure and utility from your airplane Read it carefully review it frequently and keep it with you in the airplane at all times With proper operational techniques and good maintenance your Gulfstream I American Cheetah should serve you well Get to know your Gulfstream American Dealer He is equipped to provide any assist...

Page 6: ...12 650 FT TAKEOFF PERFORMANCE Ground Roll Total Distance Over 50 Ft Obstacle LANDING PERFORMANCE 880 Fl 1600 FT Ground Roll Total Distance Over 50 Ft Obstacle STALL SPEED CAS Flaps Up Power Off Flaps Down Power Off MAXIMUM GROSS WEIGHT STANDARD EMPTY WEIGHT BAGGAGE ALLOWANCE Normal Category WING LOADING Pouncls Sq Ft POWER LOADING Pounds HP TOTAL FUEL CAPACITY Standard Tanks Optional Long Range Ta...

Page 7: ...ITATIONS EMERGENCY PROCEDURES NORMAL PROCEDURES PERFORMANCE WEIGHT BALANCE EQUIPMENT LIST AIRPLANE SYSTEMS DESCRIPTION AIRPLANE HANDLING SERVICE MAINTENANCE SUPPLEMENTS Optional Systems Description Operating Procedures SAFETY INFORMATION Issued January 15 1977 SECTION 1 2 3 4 5 6 7 8 9 10 iii ...

Page 8: ...pply to or cover any products which are in GULFSTREAM AMERICAN s opinion damaged as a result of being in any manner altered or repaired outside of the factory of GULFSTREAM AMERICAN or that shall have been subject to misuse or negligence GULFSTREAM AMERICAN makes no warranty whatsoever with respect to en gines radios prorellers ignition apparatus st Jrting devices generators batteries or other tra...

Page 9: ...nd Entry Dimensions Baggage Space and Entry Dimensions Specific Loadings Symbols Abbreviations and Terminology General Airspeed Terminology and Symbols Meteorological TerminolQgy Engine Power Terminologv Airplane Performance and Flight Planning Terminology Weight and Balance Terminology Issued January 15 1977 SECTION 1 GENERAL Page 1 2 1 3 1 3 1 3 1 3 1 4 1 4 1 8 1 9 1 9 1 9 1 9 1 9 1 9 1 10 1 10 ...

Page 10: ...ECTION 1 GENERAL NOTES 1 Wheel base length 5 4 2 Minimum turning radius 19 11 3 Pivot point center of main gear tire GULFSTREAM AMERICAN MODEL AA 5A CHEETAH Figure Three View 1 2 Issued January lS fft j1 ...

Page 11: ... handling and routine preflight checking of the airplane Also included in this section are definitions and explanations of the symbols abbreviations and terminology used in this handbook DESCRIPTIVE DATA ENGINE NOTE Unless otherwise noted all perfor mance and operational data in this book are based on sea level standard day and airplane gross weight con ditions Number of Eng ines Manufacturer Avco...

Page 12: ...ons 140 Liters Optional Long Range Tanks I Total 52 6 U S Gallons 43 8 Imperial Gallons 199 0 Liters Each Tank 26 3 U S Gallons 21 9 Imperial Gallonsl 99 5 Liters Total Usable 51 U S Gallons 42 5 Imperial Gallons 193 Liters OIL Grade Specification 1 4 Aviation Grade Straight Mineral Oil MIL L 6b82 Figure 1 2 shall be used to replenish oil supply during the first 25 hours of operation and at the fi...

Page 13: ... FLUID Note 1 3125 HVD Oil Humblt Oil Refining Company Brayco Micronic 756C Bray Oil Company PE D 3337 3335 Standard Oil Company Royco 756A B Royal Lubricants Company XSL 7828 Shell Oil Company YT 283 Union Carbide VV P 236 PETROLATUM Note 1 Braycote 236 Bray Oil Company Parmo 70 Humble Oil Refining Company Royco 1R Royal Lubricants Company MIL L 7870 OIL Note 1 Brayco 363 Bray Oil Company Cosmolu...

Page 14: ...l Oil Company Aeroshell Oil 100 Shell Oil Company Chevron Aviation Oil 65 Chevron Oil Company Grade 1100 Chevron Oil Company Avrex 101 1065 Mobil Oil Company Avrex 101 1100 Mobil 011 Company Conoco Aero Oil 1065 Continental Oil Company Conoco Aero Oil 1100 Continental Oil Company Grade 1065 Champion Oil Refining Company Grade 1100 Champion Oil Refining Company MIL L 22851 ASHLESS DISPERSANT OIL EN...

Page 15: ... Inc Oi1E 120 Exxon Company Oil A l00 Exxon Company Oil E 80 Exxon Company Note 1 The vendor products listed in this chart have been selected as representative of the specification under which they appear Other equivalent products conforming to the same specifications may be used Note 2 Oils conforming to the latest revision of Lycoming Service Instruction No 1014 may be u l d Figure 1 2 Lubricant...

Page 16: ... 67 Imperial Quarts 1 89 Liters It is recommended that lubricating oil be changed at least every 50 hours of engine operation MAXIMUM CERTIFICATED WEIGHTS Takeoff Landing Normal Category Utility Category 2200 pounds 1850 pounds CAUTION THE REAR SEATS SHALL NOT BE OCCUPI E D DURING FLIGHT IN UTILITY CATEGORY OPERATIONS Normal Category Utility Category 2200 pounds 1850 pounds We ght in Baggage Compa...

Page 17: ...SIONS Baggage area and access dimensions are provided in Section 5 SPECI FIC LOADINGS Wing Loading Power Loading 15 7 pounds per square foot 14 7 pounds per B H P SYMBOLS ABBREVIATIONS AND TERMINOLOGY GENERAL AIRSPEED TERMINOLOGY AND SYMBOLS KCAS KIAS KTAS Knots Calibrated Airspeed is indicated airspeed corrected fOI position and instrument error and expressed in knots Knotl calibra d airspeed is ...

Page 18: ...the landing configuration Best Angle of Climb Speed is the speed which results in the greatest gain of altitude in a given liorizontal distance Vy 19 Best Rate of Climb Speed is the speed which results in the greatest gain in altitude in a given time_ METEOROLOGICAL TERMINOLOGY OAT Standard Temperature Pressure Altitude Outside Air Temperature is the free air static temperature It is expressed in ...

Page 19: ... Center of Gravity e g i c g Arm Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes Station is a location along the airplane longitudinal axis given in terms of the distance from the reference datum Arm is the horizontal distance from the reference datum to the center of gravity c g of an item Moment is the product of the weight of ...

Page 20: ...gine oil Basic Empty Weight is the standard empty weight plus the weight of optional equipm nt Useful Load is the difference between maximum gross weight and the basic empty weight Gross Weight is the maximum weight to which the airplane is certificated Maximum Takeoff Weight is the maximum weight approved for the start of the takeoff run Maximum Landing Weight is the maximum weight approved h the...

Page 21: ...ITATIONS Airspeed Indicator Mark ings Power Plant Limitations Power Plant Instrument Markings Weight Limits Center of Gravity Limits Maneuver Limits Flight Load Factor Limits Fuel Limitations Placards Issued January 15 1977 SECTION 2 LIMITATIONS Page 2 3 2 4 2 4 2 5 2 5 2 6 2 6 2 7 2 8 2 8 2 9 2 1 2 2 blank ...

Page 22: ... ...

Page 23: ...ni Americ n designed optional equipment are contained in Section 9 I The Gulfstream American Model AA 5A is certificated under FAA Type Certifi cate No A16EA The airplane is equipped for day VF R with standard equipment and may be equipped for night VFR and or IFR operations FAR Part 91 establishes the minimum required instruments and equipment for these operations The reference to types of flight...

Page 24: ...imum Canopy Open Speed 113 112 Do not exceed this speed 130 129 with canorY open Figure 2 1 Airspeed LimitatIOns AIRSPEED IND CATOR MARKINGS Airspeed indicator markings and their color code significance are shown in Figure 2 2 KCAS MARKING MPH CAS SIGNIFICANCE VALUE OR RANGE White Arc 53 104 Flap Operating Range Lower limit is maximum weight 61 120 Vso in landing configuration Upper limit is J J 9...

Page 25: ...imum 1 5 PSI Maximum 8 PSI Propeller Manufacturer McCauley Propeller Model Number 1C1721 BTM 7359 Propeller Diameter Maximum 73 Inches POWER PLANT INSTRUM NT MARKINGS Power plant Instrument markings and their color code slgnillcance are shown In Figure 2 3 RED LINE GREEN ARC RED LINE INSTRUMENT MINIMUM NORMAL MAXIMUM LIMIT OPERATING LIMIT Tachometer 2200 2700 RPM 2700 RPM 011 Temperature 75DF 245D...

Page 26: ...eat must not be occupied CENTER OF GRAVITY LIMITS Nonnal Category Center of Gravity Range Forward 81 0 Inches aft of datum at 1780 Ibs or less with a straight line varia lion to 85 6 Inches aft of datum at 2200 Ibs Aft 92 S Inches aft of reference datum at all weights up to 2200 Ibs a Reference Datum Located SO O Inches forward of the lower front face of the firewall Utility Category Center of Gra...

Page 27: ...ILITY CATEGORY This airplane is not designe for aerobatic flight However in the acquisition of various certificates such as commercial pilot instrument pilot and flight instructor certain maneuvers are required by the FAA All of these maneuvers except spins are ermitted in this airJ llane when operated in the Utility Category Maximum Design Weight 1850 Ibs Design Maneuvering Spe d 106 KCAS 122 MPH...

Page 28: ... stops As the rotation stops neutralize the anti spin rudder then apply s ooth elevator back pressure to bring the nose up to level flight FLIGHT LOAD FACTOR LIMITS NORMAL CATEGORY Flight Load Factors Gross Weight 2200 Ibs Flaps Up Flaps Down UTILITY CATEGORY Flight Load Factors Gross Weight 1850Ibs Flaps Up Flaps Down FUEL LIMITATIONS Standard Tanks 3 8g 1 52g 3 5g 4 4g 1 76g 3 5g 2 Tanks 19 U S ...

Page 29: ...FLIGHT LOAD FACTORS FLAPS UP____ 4 4 1 76 FLAPS DOWN ______ 3 5 REAR SEAT MUST NOT BE OCCUPIED ACROBATIC MANEUVERS ARE LIMITED TO THE FOLLOWING MANEUyER ENTRY SPEED CAS CHANDELLES _ _ _ _ _ _ _ _ _ _ _ _ _ _ 106 KNOTS LAZY EIGHTS _ _ _ _ _ _ _ _ _ _ _ _ _ _ 106 KNOTS STEEP TURNS _ _ _ _ _ _ _ _ _ _ ____106 KNOTS STALLS EXCEPT WHIP STALLsI______ SLOW DECELERATION SPINS PROHIBITED MAXIMUM ALTITUDE L...

Page 30: ... Left side of instrument panel FOR FLIGHT WITH REAR SEAT OCCUPANTS AND OR BAGGAGE CARGO CHECK WEIGHT BALANCE 5 AIt of fuel tank caps Standard Tank I FUEL MIN 80 87 OCT 19 0 U S GAL CAP Optional Long Range Tanks FUEL MIN 80 87 OCT 26 3 U S GAL TOTAL CAP 19 0 U S GAL TO TAB 6 On instrument panel if strobe lights are instalied TURN OFF STROBE IN CLOUD FOG OR HAZE TAXI WITH STROBE OFF _ _ 2 10 Revised...

Page 31: ...SEE WEIGHT AND BALANCE DATA NO HEAVY OBJECTS ON HAT SHELF Under rear seat base NO STEp BEFORE FLIGHT SEAT BACK MUST BE TURNED DOWN TO COVER THIS AREA L _ ___ _ ____ 10 Inside canopy rail lelt side 11 Interior of canopy adjacent to lock PUSH TO UNLOCK Revised December 15 1977 SECTION 2 LIMITATIONS On rear seat base NO PASSENGERS 340 POUNDS MAXIMUM CARGO OISTRIBUTE EVENL Y FOR ADDITIONAL LOADING INS...

Page 32: ...RE STARTING ANY WORK ON THIS UNIT CAUTlON l THIS UNIT Pul ARITY SENSITIVE WHITE OR RED LEAD POSITIVE LACK LE D A D on C E NEGATIVE 13 Adjacent to auxiliary powe r plug if installed CAUTION 12 VOL T D C ONl Y MASTER SW MUST BE OFF 14 On baggage door TO OPEN DOOR FROM INSIDE SLIDE HANDLE FORWARD 15 On glove box door TIRE PRESSURE NOSE 21 LBS MAIN 24 LBS 2 12 Revised December 15 1971 ...

Page 33: ...uring Flight Forced Landings Emergency Landing Without Engine Power Precautionary Landing With Engine Power Ditching Fires During Start On Ground Engine Fire In Flight Electrical Fire In Flight Cabin Fire Wing Fire Icing Inadvertent Icing Encounter Landing With a Flat Main Tire Landing With a Flat Nosewh 1 Tire Electrical Power Supply System Malfunctions Ammeter Shows Discharge Issued January 15 1...

Page 34: ...ergency Descent Through Clouds Recovery From a Spiral Dive Flight In Icing Conditions Static Source Blocked Spins Rough Engine Operation Or Loss Of Power Carburetor Icing Spark Plug Fouling Magneto Malfunction Low Oil Pressure Engine Overheat Electrical Power Supply System Malfunctions Overvoltage Protection Insufficient Output Brake Failure Windshield Obscuration 3 2 3 9 3 10 3 10 3 11 3 11 3 12 ...

Page 35: ...y emergency develop the guide lines in this section should be considered and applied as necessary to correct the problem AIRSPEEDS FOR SAFE OPERATIONS lAS Engine Failure Alter Takeoff Maneuvering Speed Maximum Glide Precautionary Landing With Engine Power Landing Without Engine Power OPERATIONAL CHECKLISTS ENGINE FAILURES Engine Failure During Takeoff Run 1 Throttle IDLE 2 8rakes APPLY 3 Mixture I...

Page 36: ...NGS E T1ergency Landing Without Engin e Power 1 Airspeed 65 KIAS 75 MPH 2 Radio TRANSMIT MAYDAY on 121 5 MHz giving location and intentions 3 Mixture IDLE CUT OFF 4 Fuel Selector Valve OFF 5 Ignition Switch OFF 6 Wing Flaps AS REQUIRED 7 Master Switch OF F 8 Canopy UNLATCH PRIOR TO TOUCHDOWN 9 Touchdown SLIGHTLY NOSE HIGH 10 Brakes AS REQUIRED Precautionary landing With Engine Power 1 Airspeed 65 ...

Page 37: ...BLISH 350 FT MIN DESCENT at 65 KIAS 75 MPH 6 Canopy FULL Y OPEN 7 Touchdown NOSE HIGH ATTITUDE AT MINIMUM DESCENT RATE AND AIRSPEED 8 Face CUSHION It touchdown with folded coat or seat cushion 9 Airplane EVAClIATE through canopy 10 Life Vests and Raft INFLATE FIRES During Start On Ground 1 Cranking CONTI NUE to get a start which would suck the flames and accumulated fuel through the carburetor and...

Page 38: ...ed Electrical Fire in Flight If fire is in engine compartment 1 Master Switch OF F 2 Vents Cabin Air Heat OFF CLOSED 3 Land airplane as soon as possible If fire is in cockpit 1 Master Switch OF F 2 All Other Switches except ignition switch OFF 3 Vents Cabin Air Heat CLOSED 4 Fire Extinguisher ACTIVATE lif available If fire appears to be out Lind electrical power is necessary to continue flight 5 M...

Page 39: ...ON as r quired IIJOTE Continuous engine operation with car buretor heat on is not recommended due to the decrease in engine efficiency If severe icing conditions require ex tended use of c lrburetor heat the en gine mi ture should be leaned during use of c rburetor heat 3 Cabin Heat ON 4 Defrosters OPEN 5 Engine Increase RPM do not exceed red line and periodically change RPM to mi iiimize ice buil...

Page 40: ...landing 11 Land in a slightly nose high attitude LANDING WITH A FLAT MAIN TIRE 1 Wing Flaps AS DESIRED 2 Elevator Control NOSE HIGH 3 Aileron Control BANK TOWARD GOOD TIRE 4 Touchdown GOOD TIRE FIRST hold airplane off flat tire as long as possible LANDING WITH A FLAT NOSEWHEEL TIRE 1 Wing Flaps AS DESIRED 2 Elevator Control NOSE HIGH 3 Touchdown Hold nose gear off runway as long as possible 4 Brak...

Page 41: ...eed can be maintained At low altitudes in most cas s the airplane should be flown straight ahead for a landing with only small qirectional changes to avoid obstructions or people on the ground Seldom are ttlere either the altitude or airspeed available for a 180 gliding turn back to the runway The following amplified checklists are based upon the assumption that the pilolwill have adequate time to...

Page 42: ...than an airport the landing area should be observed from a safe but low altitude Inspect the terrain for obstructions and surface conditions prior to attempting a landing Perform the landing as discussed in the PRECAUTIONARY LANDING WITH ENGINE POWER checklist If ditching is to be attempted heavy objects in the baggage area should be secured Folded coats or cushions should be available for occupan...

Page 43: ...ys mean that a flaming fire exists For example it may be engine oil on the exhaust system If in the pilot s judgement an engine fire exists the following procedures are suggested 1 Mixture IDLE CUTOFF 2 Fuel Selector Valve OFF 3 Master Switch OFF 4 Cabin Heat and Air OF F 5 Establish a maximum safe rate of descent Increasing speed may blow the fire out 6 Slide slip maneuvers may be used as necessa...

Page 44: ...ly powered turn coordinator or turn and bank indicator is operative and the pilot is not instrument rated Executing a 180 Turn in Clouds Upon inadvertently entering the clouds an immediate plan should be made to turn back as follows 3 12 1 Note the time of the minute hand and observe the pmition of the sweep second hand on the clock Note compass heading 2 When the sweep second hand indicates the n...

Page 45: ...cent 3 Adjust the elevator trim control wheel for a stabilized descent at 70 KIAS 81 MPH 4 Use minimum control wheel motion and avoid abrupt mOVl ment 5 Monitor turn coordinator and make corrections by rudder alone 6 Check trend of compass card movement and make cautious corrections with rudder to stop turn 7 Upon breaking out of clouds resume normal cruising flight Recovery From a Spiral Dive If ...

Page 46: ...g procedures are suggested 3 14 1 Turn r itot heat ON 2 Turn cabin heat ON 3 Open windshield defroster vent 4 If IFR or under control of an In flight ground facility notify them of the condition and request assistance A change of altitude if possible or reversing course to fly out of the icing conditions may be desirable 5 Pilot technique is imr ortant in this situation A Increase and decrease eng...

Page 47: ...ort If it is necessary to continue the flight and particularly jf the flight is in marginal conditions a static source must be supplied to the airspeed indicator and altimeter A static source can be suPPljed to the airspeed indicator and altimeter by breaking the glass on the face of the iertical speed indicator If this is done remember the following SPINS 1 The vertical speed indicator will be in...

Page 48: ...flight may be caused by one or more spark plugs becoming fouled by carbon or lead deposits This may be verified by turning the ignition switch momentarily from BOTH to either L or R position An obvious power loss in single ignition operation is evidence of spark plug or magneto trouble Assuming that spark plugs are the most likely cause lean the mixture to the recommended lean setting for cruising...

Page 49: ...STEM MALFUNCTIONS The ammeter system on the AA 5A indicates current flow to or from the battery During normal operation with a fully charged battery the ammeter will indicate near zero or slightly toward the charge side This indication will be true even though all electrical systems are energized unless the capacity of the alternator 60 amps has been exceeded Failure of the alternator is e sily de...

Page 50: ...rve battery energy BRAKE FAILURE Brake failure is infrequent in any aircraft However if a brake failure is detected proceed to the nearest airport with adequate runway length to accommodate an emergency brake failure landing It is not recommended with a single brake fail ure that either brake be utilized during landing and roll out Plan the touchdown near the approach end ofi the runway The airpla...

Page 51: ...Wing Leading Edge Right Wing Right Wing Trailing Edge Right Side of Fuselage Empennage Left Side of Fuselage _ Night Flight Preflight Electrical Systems Preflight Cabin Left Wing Tip Nose Right Wing Right Wing Tip Empennage Cabin Before Starting Engine Starting Engine Before Takeoff Takeoff Normal Takeoff Obstacle Clearance Climb Issued January 15 1977 Page 4 3 4 3 4 5 4 5 4 5 4 5 4 5 4 5 4 6 _4 6...

Page 52: ...wer Check Normal Takeoff Soft Field Takeoff Short Field Takeoff Crosswind Takeoff Climb Cruise Descent Stalls Landing Normal Landing Soft Field Landing Short Field Landin Crosswind Landing Balked Landings Go Aroundsl Slips to Landings Ground Handling and Tiedown Cold Weather Operation Starting Starting With Preheat Starting Without Preheat Flight Operations Hot Weather Operation Noise Abatement 4 ...

Page 53: ...off distance the speed appropriate to the particular weight must be l ed Takeoff Normal Climb Out Maximum Performance TjI eoff Speed at 50 feet Enroute Climb Flaps Up Normal Best Rate of Climb Sea Li vel Best Rate of Climb 10 000 Feet Best Angle of Climb Sea Level Best Angle of Climb 10 000 Feet Landing Approach Normal Approach Flaps u p Normal Approach Flaps IN Short Field Approach Flaps DN Balke...

Page 54: ...f r 1 I PREFLIGHT INSPECTION ElECTRICAL SYSTEMS PREFLIGHT I I I _ _J NOTE Visually check airplane for general condition during walk around inspection In cold wea ther remove even small accumulations of frost ice or snow from wing tail and control surfaces Figure 4 1 Preflight Inspection 4 4 Issued January 1 5 1 977 ...

Page 55: ...weight Access Unobstructed 3 Wing Inspection Plates Secure 4 Tiedown Remov d 5 Pitot Tube Unobstructed 6 Fuel Tank Vent L nobstructed 4 Left Wing Leading Edge 1 Fuel Tank Full cap seal checked for damage cap secure 2 Tank Drain Fuel free of water and sediment drain secure 3 Sump Drain Fue free of water and sediment drain secure 4 Fuel Proper color 5 Landing Gear Wheel Fairing and Tire Undamaged ti...

Page 56: ...aged tire properly inflated mud scraper clear 6 Tow Bar Removed and stowed 7 Chocks Removed B Engine Cooling Openings Unobstructed 7 Right Cowl 1 Cowl Open 2 Engine Baffles Unobstructed undamaged 3 Engine Cooling Openings Unobstructed 4 Engine Oil Level 6 Quarts minimum capacity B quarts 5 Engine Oil Dipstick Secured finger tight 6 Vacuum Pump Vent Unobstructed 7 Battery Secllre B Alternator Belt ...

Page 57: ...age Undamag d 12 Empennage 1 Elevators Freedom of movement 2 Rudder Freedom of movement 3 Trim Tabs Secure undamaged 4 Tail Cone and Light Secur undamaged 5 Tie Dowfl Remove j 13 Left Side of Fuselage 1 Static Source Unobstructed 2 Fuselage Undamaged 3 Baggage Door Secure 14 Night Flight Preflight 1 Fuses and Circuit Breakers Check 2 Spare Fuses In Glove Compartment 3 Flashlight Aboard Required Ch...

Page 58: ...ion Light Illuminated 2 Strobe Light Flashing 6 Empennage 1 Navigation Light Illuminated 2 Flashing Beacon Operating 7 Cabin 1 Master Switch OF F 2 Navigation Lights OFF 3 Flashing Beacon OFF 4 Strobe Lights OFF 5 Pitot Heat OFF 6 Landing Light OFF BEFORE STARTING ENGINE 1 Preflight Inspection Complete 2 Seats Seat Belts and Shoulder I arness Adjusted locked 3 Radios Autopilot Electrical EqLJipmen...

Page 59: ...reen arc 4 Ammeter Charging 5 Vacuum Gage 4 6 to 5 4 in Hg 6 Magnetos Ch ck 175 RPM maximum drop not over 50 RPM difference between left and right magnetos 7 Carburetor Heat ON check for RPM drop then set to OF F 8 Throttle Set for 1000 RPM 9 Radios ON diecked Transponder STANDBY 10 Engine Idles moothly 11 Engine is ready for ta eoff when it will take throttle Without l hesitating or faltering and...

Page 60: ...S 58 MPH lift nose wheel at 55 KIAS 63 MPH 6 Climb Speed 63 KIAS 73 MPH CLIMB 1 Normal Climb Speed 85 KIAS 98 PH at full throttle 2 8est Rate of Climb Speed 79 KIAS 91 MPH at sea level full throttle 3 Best Angle of Climb Speed 68 KIAS 78 MPH at sea level full throttle CRUISE 4 10 1 Auxiliary Fuel Pump OFF 2 Power SET at 2200 to 2700 RPM 3 Trim Tab SET as required 4 Mixture SET as required Full ric...

Page 61: ...t and lock 2 Fuel Selector On fullest tank 3 Mixture FULL RICH 4 Auxiliary Fuel Pump ON 5 Carburetor Heat ON if required 6 Parking Brake of F 7 Flaps SET as required below 103 KIAS 119 MPH 8 Airspeed 65 KIA 75 MPH to 70 KIAS 80 MPH 9 Landing Light Ot as required BALKED LANDING 1 Power Full throttle 2 Carburetor Heat OFF 3 Airspeed 60 65 KIAS 69 75 MPH 4 Establish Climb At1 itude 5 Flaps Retract sl...

Page 62: ...ECUTE A NORMAL GO AROUND 2 Lower nosewheel slowly as speed decreases 3 Use rudder to maintain directional control down to approximately 17 KIAS 20 MPH 4 Brakes Use as required for stopping and directional control Obstacle Clearance Landing 1 Flaps Fully extended below 103 KIAS 119 MPH 2 Airspeed 61 KIAS 70 MPH 3 Touch down on main gear 4 Elevator Full up control 5 Flaps UP 6 Brakes As required for...

Page 63: ... all radios and lights off both to limit battery drain during the start and to protect avionics from voltage surges NOTE I Normally one to three strokes of the pnmlng pump is sufficient for quick starting In temperatures below 40 F 40 CI hOVllever four to six strokes may be neces ary During extremely cold days starling will be aided by pulling the propeller through four or five revo lutions by han...

Page 64: ...start As soon as engine starts set ignition to both Check the oil pressure when the engine starts If no oil pressure is indicated within 30 seconds 60 seconds on a very cold day siop the engine and determine the source of trouble Oil pressure should indicate approximately 25 PSI with the engine at idle Release parking brake by pushing parking brake knob and pressing brakes TAXIING NOTE Parking bra...

Page 65: ...H Quarter 3 Aft RH Quarter 4 AFT 5 Aft LH Quarter 6 FWD LH Quarter SECTION 4 NORMAL PROCEDURES CONTROL POSITION Wheel Neutral Back Wheel Right Back Wheel Left Forward Wheel Neutral Forward Wheel Right Forward Wheel Left Back Figure 4 2 Taxiing Diagram Issued January 15 1977 4 15 ...

Page 66: ...unups over loose gravel are espe ially harmful to propeller tips When takeoffs must be made over a gravel surface it is very important that the throttle he advanced slowly This allows the airplane to start rolling before high RPM is developed and the gravel will be blown back of the propeller rather than pulled into it Prior to takeoff from fields above 5000 feet elevation the mixture should be le...

Page 67: ...d prolo 1ged engine run up in loose gravel since the propeller will tend to pick up stones and debris causing pro peller blade landing gear and empen nage damagE After alignment in the takeoff direction hold the brakes to prevent movement and apply full throttle When full power is reached release brakes and begin the takeoff roll with the elevator neu tral Use light smooth brake pressures to main ...

Page 68: ...should be leaned to achieve best power maximum RPM The maximum recommended cruise power setting is 100 of the rated horse power True airspeeds which are determined by the particular altitude and power setting chosen can be obtained from the tables in Section 5 NOTE On new airplanes power should be maintained at 75 poWer or more until a total of 50 hours has accumu lated This is to ensure proper se...

Page 69: ... time Higher airspeeds are perr 1issible in smooth air conditions Placarded airspeed limitations must be observed STALLS The AA 5A s stall characteristics are conventional in all configurations Elevator buffeting occurs approximately 2 KIAS 3 MPH above the stall and becomes more pronounced as the stair occurs An audible stall warning horn begins to blow steadily 5 KIAS to 10 KIAS above the actual ...

Page 70: ...idding when braking In gusty or crosswind conditions many pilots prefer to increase their airspeed slightly above the normal approach speed this decision however can only be made by the pilot in light of his own experience and training 4 20 NOTE A power off nose high touchdown atti tude is the beSt assurance of a porpoise free landing and excessive touchdown speed is not required with direct cross...

Page 71: ...ure immediately after touchdown and continu9usly increasing brake pressure just enough so the wheels do not skid Crosswind Landing When landing in a strong crosswind use the minimum flap setting required for the field length Although the crab or combination method of drift correction may be used the crab method gives the best control After touchdown hold a straight course with the rudder and occ s...

Page 72: ...sive pressures COLD WEATHER OPERATION Starting Prior to starting on a cold morning it is advisable t J pull the propeller through I several times by hand to break loose or Iimber the oil thus conserving battery energy Use auxiliary power if airplane is equipped for it WARNING WHEN PULLING THE ROPELLER THROUGH BY HAND TREAT IT AS IF THE IGNITION SWITCH IS TURNED ON A LOOSE OR BROKEN GROUND WIRE ON ...

Page 73: ... Area CLEAR 5 Master Switch ON 6 Ignition Switch ON LEFT 7 Pump Throttle r pidly to full open twice Return to 1 2 inch open position 8 Starter 8utton Press release when engine starts 9 Ignition Switch ON 80TH 10 Continue to prifT e the engine until it is running smoothly or alter nately pump the 1prottle rapidly oVer the first 1 4 of total travel until engine is running smoothly 11 Oil Pressure CH...

Page 74: ...o higher engine RPM If the engine accelerates smoothly and the oil pressure remains normal ilnd steady the airplane is ready for takeoff FLIGHT OPERATIONS Takeoff is fllilde normally with carburetor heat off and mixture set for prevailing altitude I When operating in temperatures below 18 F 28 CI avoid using partial car buretor heat Partial heat may increase the carburetor air temperature to the 3...

Page 75: ...00 feet above the surface 2 During climb out or descent to an airport attempt to plan the maneuver so that prolonged flight at low altitude can be minimized NOTE The above recommended procedures do not app v wher they would conflict with Air Traffic Control clearances or instructions or where in the pilot s judgment an altitude of less than 2000 feet is nlicessary for him to adequately exercise Hi...

Page 76: ... ...

Page 77: ...Component c hart Figure 5 5 Takeoff Distance Figure 5 6 Rate of Climb Figure 5 7 Time Fuel and Distance to Climb Figure 5 8 Cruise PerforrT1i1nce Figure 5 9 Cruise Speeds Figure 5 10 Range Profile 37 Gallons Fuel Figure 5 11 Range Profile 51 Gallons Fuel Figure 5 12 Endurance Profile 37 Gallons Fuel Figure 5 13 Endurance Profile 51 Gallons Fuel Figure 5 14 Landing Distance Issued January 15 1977 S...

Page 78: ... r J ...

Page 79: ...pon the recommended leaning procedure Some variables such as mixture leaning technique engine and propeller condition an air turbulence may affect ranqe and endurance by 10 or more USE OF PERFORMANCE CI1ARTS The performance data is presented in tabular or graphical form depending upon which presentation method lest portrays the specific data Each table or graph contains explanatory material when t...

Page 80: ...8500 Feet Feet DIR KTS DC 090 30 0 090 30 0 020 20 5 020 20 5 Alt Setting In Hg 29 75 29 75 29 85 29 85 AIRPORT OFK OBH LBF SNY DEN Norfolk Nebraska Wolbach Nebraska North Platte Nebraska Sidney Nebraska Denver Colorado To determine pressure altitude at origin and destination airports add 100 feet to field elevation for each 1 in Hg below 29 92 and subtract 100 feet froJDl field elevation for each...

Page 81: ...b Ibs 2000 ft pressure altitude and 20 C should be used to determine the takeotf istance from Figure 5 5 Ground roll Total Distance to clear a 50 foot obstacle 1101 Feet 1988 Feet A correction for the af fect qf wind may be made based on Note 1 of Takeoff Distance Figure 5 51 Using Figure 5 4 the headwind component is determined to be 9 5 Knots The distance correction for a 5 Knot headwind is 9 5 ...

Page 82: ...erformance tables Figure 5 B and 5 9 and the range and endurance profiles Figure 5 10 through 5 13 a power setting of 2600 RPM has been selected for this sample flight At 2600 RPM enter the cruise performance tables at BOOO and 9000 feet stan dard day and 20 C above standard STANDARD TEMPERATURE PRESSURE 045 FUEL FLOW ALTITUDE t FEET TEMP BHP KTS MPH GPH _ _ _ _ BOOO l C 69 121 140 7 9 31 F f 9000...

Page 83: ... BHP KTS MPH OFK LBF O c 68 121 139 32 F LBF DEN 5 C 67 120 138 4o F OTE The above are values for the assumed conditions Time and fuel used were calculated as follows Time Distance Ground Speed Fuel Used Time Fuel Flow 5t Ground Time at GPH 7 8 7 7 Fuel Used Speed Cruise Altitude For Cruise Route Distance Segment N M ins MPH HRS MIN GAL OFK OBH 32 39 160 14 1 8 OBH LBF 111 149 172 45 5 9 LBF SNY 1...

Page 84: ...0 Lbs Estimated fuel used from OFK to DEN 2 6 gal 141 3 Lbs Estimated landing weight 2130 141 1989 Lbs LANDING The landing distance required is determined in a similar manner to the procedure used in determining takeoff distance Using 2000 Ibs 6000 ft and 1 C the distance can be found from Figure 5 14 Ground roll Total distance to clear a 50 foot obstacle 413 Feet 1200 Feet A correction for the af...

Page 85: ...nd fI et Decrease in ground roll 1 13 x 16 Corrected ground roll Total landing distance to clear a 50 foot obstacle zero wind Decrease in total distance 1200 x 16 Corrected total distance t9 clear a 50 foot obstacle This distance is well within the landing distance available or 11 500 reet Issued January 15 1977 413 66 347 1200 192 1008 5 9 ...

Page 86: ... are not affected by flap position KNOTS MILES PER HOUR lAS CAS lAS CAS 50 51 60 61 60 61 70 71 70 71 80 81 80 81 90 91 90 91 100 101 100 101 110 111 110 111 120 121 120 121 130 131 130 131 140 141 140 141 150 151 150 151 160 161 160 161 170 171 170 170 180 181 180 180 190 191 200 201 210 211 Figure 5 1 Airspeed Calibration 5 10 Issued January 16Jl 1977 ...

Page 87: ...l t e a w a W t 5 0 0 0 0 M N Issued January 15 1977 0 0 0 0 0 N M f I I I J S33kHl3a 0 III I SECTION 5 PERFORMANCE 0 N 0 5 0 co 0 t r IO s U l c 0 iii 0 III cu c 0 0 u U cu en 0 W a M W a 10 I l 8 0 w N c E cu o l N iii 0 cu I CI 0 u I 0 N I 0 M I 0 0 III I 0 olD lDl I 5 11 ...

Page 88: ...8 KNOTS 67 MPH 2 Stall speeds apply for both calibrated and indicated airspeeds FLAPS 0 1i FLAPS 45 Q H w a 1 117 2200 2100 2000 1900 1800 1700 1600 0 10 20 30 40 50 WEIGHT POUNDS ANGLE OF BANK DEGREES Figure 5 3 Stall Speeds J KNOTS MPH 120 110 90 100 r 711 100 0 80 h90 r n J 70 L 80 i t r n 60 1 70 50 I 60 40 60 t 50 i en mm OCJ 1 0 0 0 s Z l 01 Z CJ m G s c Or 0 men r 1 c l m l l u s l l CJs Im...

Page 89: ...PERFORMANCE ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATI 20 HEADWIND COMPONENT 9 5 KNOTS CROSSWIND COMPONENT 3 5 KNOTS NOTE Demonstrated crosswind com ponent is 16 knots t O Z Z t Z w Z o 11 E o tJ o Z o w I 5 10 15 CROSSWIND COMPONENT IN KNOTS Figure 5 4 Crosswind Component Chart Issued January 15 1977 20 5 13 ...

Page 90: ...u a 00 wu 00 wu 00 wu 00 wu 00 D 0 0 0 0 0 OFF 50 FT a a u a a u a a u a a u a a u l l l l Cl l l l l 220 0 56 63 S L 754 1374 B36 1522 925 1681 10 20 lB5Q 1120 20 29 64 731 20 00 B97 1625 996 lBQl 10 1 19BB 1214 218B 1334 240 0 40 0 0 10 71 1927 l1B9 2135 1315 235B 1449 2595 1592 2B47 117 34 60 00 12B2 2290 1423 253B 1573 2BQ3 3QB4 190 5 3384 1797 80 0 0 153B 2730 30 25 i8BB 3340 20 80 3676 22B6 ...

Page 91: ...S L 79 91 744 629 534 2000 7 90 764 634 527 439 4000 77 89 646 523 424 343 8000 76 87 527 413 322 248 8000 75 66 409 303 219 152 10000 r 85 290 193 117 57 2000 S L 77 89 11 36 887 767 668 2000 76 87 Q09 771 659 568 4000 7 66 782 654 551 468 6000 74 85 655 536 444 368 8000 73 64 529 421 336 268 10000 72 83 402 305 228 168 1800 S L 7 66 1217 1058 931 827 2000 74 65 1081 934 816 721 4000 73 64 945 81...

Page 92: ...U IU 15 000 IU CI i 10000 i C IU II I 1 1 5 000 IU CLIMB SPEEDS lAS AS SCHEDULED TEMPERATlJRE STANDARD DAY liSA FUEL DENSlTY 8 0 US P R U s GAl WEIGHT 220D LBS ALTITUDE IN FEET s L 2500 260D 4500 4 iOD 6500 8IiDO B500 Il OO 10600 10600 12500 eUIi8SPEED KT15 MPH 7B BO 77 IS 78 B8 75 B7 74 B8 73 85 f NOTE Add 8 pounds of fuel for ltart tIIxi 1Ind _lOf 0 1 6 I 1b 15 20 rJ 10 1115 40 46 150 II I TIME ...

Page 93: ... 98 113 5 9 50 96 110 5 7 PRESSURE ALTITUDE 3000 FEET 11 c I12 FI 9 C 148 FI 29 C 184 FI 2700 90 130 149 10 4 85 129 149 9 8 80 129 148 9 2 2600 82 125 143 9 4 77 124 142 8 8 73 123 142 8 4 2500 73 119 137 8 4 70 118 136 8 0 66 117 134 7 6 2400 66 113 130 7 6 63 112 129 7 2 60 110 126 6 8 2300 60 107 123 6 8 57 105 121 6 5 54 103 118 6 2 2200 54 100 115 6 1 51 97 112 5 8 50 95 108 5 6 P RESSURE AL...

Page 94: ...6 0 2200 52 98 113 5 9 50 95 109 5 6 48 92 105 5 5 PRESSURE ALTITUDE 6000 FEET 17 C I2 FI 3 C 1311 FI 23 C 174 FI 2700 84 129 149 9 6 79 128 14B 9 1 75 128 147 8 6 2600 76 124 142 8 7 72 123 141 B 2 68 121 139 7 8 2500 69 lIB 136 7 9 65 116 134 7 4 62 114 131 7 1 2400 62 111 12B 7 1 59 109 125 6 7 56 107 123 6 4 2300 56 105 120 6 4 54 102 117 6 1 52 99 114 5 9 2200 51 97 112 5 8 49 94 108 5 6 48 B...

Page 95: ...J C 2T FI 17 C 63 FI 2700 7ii 126 145 8 7 73 126 145 8 3 70 125 144 8 0 2600 71 122 141 8 1 67 120 38 7 7 64 118 136 7 3 2500 64 116 133 7 3 61 113 130 7 0 59 111 128 6 6 2400 58 108 125 6 6 56 106 1 22 6 3 54 108 118 6 1 2300 53 101 116 6 0 51 98 112 5 8 50 93 107 5 7 PRESSURE ALTITUDE 10 000 FEET _25 l3 FI 5 C 2 fFI 15 C 59 FI F T 7i 123 142 8 1 69 123 142 7 9 68 123 142 7 7 li2 66 iiii 13j 7 5 ...

Page 96: ...wheel fairings Wheel fairings increase speed approximately 3 5 KTS 4 MPH POWER SETTING i i i i 83 BHP 155 MCP 12 HP 50 MCP ttl Ill III Ji 1000 98 BH 165 MCP FULL THROTTLE 800 6000 4000 2000 SL 75 I III Til 1113 BHP 75 MCP 80 85 90 95 100 105 110 115 120 125 130 KTS t i i i I i I I I I I 1 90 95 100 lOS 110 115 120 125 130 135 140 145 150 MPH TRUE AIRSPEED Figure 5 9 Cruise Speeds J 0 til mm oC l T...

Page 97: ... start taxi and climb with 45 minutes reserve at 50 MCP Cruise speeds are shown for airplane with wheel fairings Wheel fairings increase speeds approximately 3 5 KTS 14 MPH 14000 10000 8000 20 POWER SETTINGS CRUISE TRUE AIRSPEED IN KNOTS OWER SETTINGS I I I I 1 I I I I II I I I FULL THROTTLE 119 127 123 9 117tttttl104 II i I 65 MCP 114 102 IDID 55 MCP 119tp ttttttitttt 1 12I 1I11 III 101 440 450 4...

Page 98: ...t taxi and climb with 45 minutes reserve at 50 MCP I l 12000 1 000 uJ C 8000 i I c 6000 uJ a 4000 en uJ g 2000 SL 620 2 630 Cruise speeds are shown for airplane with wheel fairings Wheel fairings increase speeds approximately 3 5 KTS 4 MPH CRUISE TRUE AIRSPEED IN KNOTS FULL THROTTLE 19 105 r t 127 75 MCP I 123 114 102 119 112 101 i I I 640 650 660 670 680 690 700 710 720 730 740 750 760 770 RANGE ...

Page 99: ...es resenle fuel at 50 MCP 21 Cr Jise Speeds are shown for airplane equipped with wheel fairings Wheel fairi gs increase speed approximately 3 5 KTS 4 MPH 1400 w w CRUISE TRUEAIRSP EED IN KNOTS POW ER SETTING 12000 FULL THROTTLE I w o 1000 5 800 C I w Il en en w Il 6000 75 MCP 400n C1 200 S L 127 123 119 11 105 117 104 I 65 MCP 55 MCP 114 112 93 95 50 MCP 102 95 101 95 3 20 J JU 3 4U 3 bU 4 00 4 10...

Page 100: ...CP 2 Cruise speeds are shown for airplane equipped with wheel fairings Wheel f irings increase speed approximatelv 3 5 KTS 4 MPH POWER SETTING CRUISE TRUE AIRSPEED IN KNOTS 14000 I OWER SETTI NG 12000 FULL THROTTLE 1 II I I I Id 119 H 05 o f 1 f 127 0 1111111 j I t w c l on on w c Q 1 0 H r r MC I I I J tf I 123 I I rr A119 2000 65 MCP 114 f l II 1_l hI 11 104 95t I 55 MCP T 8 t t 50 MCP m 9 i 11I...

Page 101: ...1 70 S L 366 1057 375 108 385 1114 394 1144 404 1173 2000 385 1116 396 1148 406 1180 417 1212 428 1245 4000 432 1183 419 1218 431 1253 443 1289 455 1325 6000 32 1257 445 1296 458 1335 471 1375 485 1415 8000 460 1342 474 1384 489 1428 504 1472 518 1516 I 2000 60 69 S L 342 986 351 1011 359 1037 368 1063 377 1090 2000 360 1038 369 1067 379 1095 388 1125 398 1154 4000 379 1098 390 1130 400 1162 411 1...

Page 102: ... I ...

Page 103: ...6 WEIGHT BALANCE EQUIPMENT LIST TABLE OF CONTENTS Introduction Airplane Weighing Procedures Preparation Leveling the Airplane Weighing the Airplane Measuring Arm Computing Center of Gravity Weight and Balance Cargo Loading Equipment List Page 6 3 6 3 6 3 6 3 6 3 6 4 6 6 6 6 6 10 6 15 Issued January 15 1977 6 1 16 2 blank ...

Page 104: ......

Page 105: ...in all fuel from the tanks and fuel system 3 Drain all oil from the oil system 4 Move sliding seats to center of tra lel position 5 Raise flaps to fully retracted position 6 Place all controls in neutral position 7 Ensure that all objects not a part of the airplane or its accessories are removed from the airplane B Slide canopy to provide a 6 inch opening between canopy and wind shield LEVELING TH...

Page 106: ...tape measure the distance from the plumb bob to the string stretched between the main landing gear 11 Open the canopy approximately six inches 21 Level airplane longitudinaliy by placing a short spirit level on the right canopy rail forward of the pilot s seat and deflating nose tire or main gear tires to center the bubble 31 Level the airplane lateraliy by placing a 4 foot carpenter s level acros...

Page 107: ...NCHESI NOSE LANDING GEAR ARM IN INCHESI Net Weight 50 B AI L R N WEIGHT OF LEFT MAIN LANDING GEAR IN POUNDSI WEIGHT OF RIGHT MAiN LANDING GEAR IN POUNDSI WEIGI fT OF NOSE LANDING GEAR IN POUNDSI C G Arm 50 AI L RII 50 B All N L R N Momentl Item Weig t C G Arm 1000 Lbs In Airplane Net Wei lht W T Oil 8 Qt at 1 875 Lb lQt 15 0 32 0 4R Unusable Fuel 1 0 Gal at 6 Lb lGal 6 0 94 8 7 Equipment Changes A...

Page 108: ...moment in the appropriate column 51 Add the entries in the weight column to obtain the AIRPLANE BASIC EMPTY WEIGHT 61 Add the entries in the MOMENT lOoo Lbs In column to obtain the AI RPLANE BASIC EMPTY WEIGHT MOMENT WEIGHT AND BALANCE The following information will enable you to fly your AA 5A within the pre scribed weight and center of gravity limitations To calculate the weight and balance for ...

Page 109: ...120 Ibs 7 Cargo Area 16 4 Max allowable 3401bs 8 Total Airplane 2200 92 17 Weight loaded NOTE Change in moment from upright to fold down posit ion of rear seat is negligible MOMENT LB IN 10001 105 25 48 20 18 30 80 42 84 3 17 02 72 SECTION 6 WEIGHT BALANCEI EQUIPMENT LIST YOUR AIRPLANE WEIGHT AR MOMENT LBS I UN I LB IN 1000 32 0 90 9 94 81 90 6 126 0 151 0 116 4 Maximum allowable is 120 pounds if ...

Page 110: ...plane momentl1ooo Use Center of Gravity Envelope to determine acceptability CARGO PILOT CO PILOT STD fUEl 379al useable 61bs lgal OPT FUEL 51 gaCuseable 6Ibs gal 1 REAR SEAT PASSENGERS BAGGAGE 5 10 15 20 25 30 35 40 45 50 55 MOMENTI1000 INCH POUNDS Figure 6 4 Loading Graph V j m E en Omm C C 1 Gl tl J O S I Z QOCl ICJ rl r enl I Z C 1 m Gl S C or O Tl men r l c l m l l ci1 S l l C 1 S J m m c m_ I...

Page 111: ...0 0 0 0 N 0 N N r f 1 v r j r 8 0 0 o 0 OJ Xl r f I SECTION 6 WEIGHT BALANCE EQUIPMENT LIST 0 iN I IQ IN 10 I QI C 0 0 en Qi 0 c Z W 0 I J U Cl 8 0 0 QI 0 c I QI Z U w Iri E 0 ch QI 0 I 0 u 0 o 0 0 0 0 0 III o N saNnOd NI 1Hm3M 1 flfl l3l 1l 11 a3a l101 Issued January 15 1977 6 9 ...

Page 112: ...r other suitable material under all high density cargoes to distribute the loads and prevent damage to the floors or supporting structures Figure 6 7 shows alternate seating or cargo arrangements and provides the moment arms to various loading points within the airplane Figure 6 B shows cargo belt arrangements for USe in restraining cargo in both the rear seat area and in the baggage compartment T...

Page 113: ...i 1 I I I GULFSTREAM AMERICAN MODEL AA 5A CHEETAH Figure 6 6 Rear Seat Stowage Issued January 15 1977 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST 6 11 ...

Page 114: ...ANCE EQUIPMENT LIST GULFSTREAM AMERICAN MODEL AA 5A CHEETAH 90_6 126 0 151 0 6 12 SEATING CARGO ARRANGEMENTS REAR PASSENGERS Arms measure to center of area shown Figure 6 7 Seating Cargo Arrangements Issued January 15 1977 ...

Page 115: ...CAN MODEL AA 5A CHEETAH SECTION 6 WEIGHT BALANCE EQUIPMENT LIST LAP BELT ATTACHMENT POINTS LAP BELT ATTACHMENT POINTS 0 RING CARGO BELT ALTERNATE ARRANGEMENTS Figure 6 8 Cargo Belt Arrangement Issued January 15 1977 6 13 ...

Page 116: ...ENT LIST GUlFSTREAM AMERICAN MODEl AA 5A CHEETAH DIMENSIONS IN INCHES CANOPY OPENING 34 INCHES CANOPY UN OPEN POSITION BAGGAGE DOOR BAGGAGE DOOR OPENING 14 X 24 X 12 INCHES Figure 6 9 Internal Cabin Dimensions 6 14 Issued January 15 1977 ...

Page 117: ...T If additional equipr 1ent is to be installed it must be done in accordance with the reference drawing accessory kit instructions or a separate FAA approval Refer to applicable FAR s for a listing of specific equipment r quired for each mode of airplane operation Columns showing weight in pounds and arm in inches provide the weight and center of gravity location for the equipment NOTE Unless othe...

Page 118: ... Propeller McCauley lCl72 BTM 7359 With Aluminum Spacer B 4381 36 78 8 01 With Steel Spacer B 4425 48 23 8 64 Spinner 2 67 4 32 Battery 12V 25 Ampere hour 22 30 47 00 Voltage Regulator 12V 80 49 00 Standard Wiring System 1 36 41 30 Main Wheel Tire Brake two 6 00 X 6 Type III 34 90 100 15 Nose Gear Shock Absorber Installation 4 31 46 55 Nose Wheel Tire Tube 5 00 X 5 8 70 36 10 Wheel Hub Covers 07 7...

Page 119: ...Drain Oil Valve Exchange Magnetic Compass Heated Pitot Exchange Cabin Dome Light Instrument Lights Navigation Lights OPTIONAL EQUIPM NT Altimeter Sensitive Feet MB or Altimeter Se si ive Feet In Hg Encoding Altimeter AR BOO Narco or B040B 15K A lH Mach or 5035PZ P 5 Uni ed Inst or 5035P P22 Unite n Issued January 15 1977 SECTION 6 WEIGHT BALANCEI EQUIPMENT LIST WEIGHT ARM 54 126 BO 5 2B 52 39 2 2B...

Page 120: ...stallation Glider Tow Hitch Installation Narco AT 50A Transponder AT 150 Transponder Com 10 Nav 10 Com Nay Transceiver Com 11 A Nav 11 C m Nav Transceiver GULFSTREAM AMERICAN MODEL AA 5A CHEETAH WEIGHT ARM 10 55 59 69 2 40 66 56 1 50 44 50 25 75 00 33 69 50 3 38 110 00 38 69 20 4 60 83 50 40 69 25 2 00 136 00 33 119 00 1 00 105 04 58 80 25 1 04 231 60 3 10 101 96 25 79 40 16 36 99 76 4 30 35 01 2 ...

Page 121: ...lideslope lridicator Collins VHF 251 VIR 351 IND 350 VHF 251 VHF 251 V1 R 351 IND 351 GLS 350 RCR 650 IND 650 ANT 650 TDR 950 Antenna AM R 350 Antenna Sidetone Intercom Century I Autopilot Century liB Alltopilot Microphone In tallation Turn and Bank Installation Pantionics H F DX10RA Bendix ADF Revised December 15 1977 SECTION 6 WEIGHT BALANCE EQUIPMENT LIST WEIGHT ARM 1 69 67 55 3 62 233 40 2 70 ...

Page 122: ... I ...

Page 123: ...age Compartment Seats and Belts Cargo Configuration Canopy Control Locks Engine Engine Controls Engine Instruments _ New Engine Break in and Operation Engine Oil System Ignition Starter System Air Induction System Exhaust System _ Carburetor and priming System Cooling System Propeller Fuel System Brakes Issued January 15 1977 Page 7 3 7 3 7 4 7 4 7 4 7 4 7 6 7 6 7 6 7 7 7 B 7 B 7 B 7 9 7 9 7 9 7 1...

Page 124: ...osting System Heating Defrosting System Ventilation Pitot Static System and Instruments Airspeed Indi cator Vertical Speed Rate of Climbllndicator Altimeter Vacuum System and Instruments Attitude Indicator Directional Indicator Suction Gauge Stall Warning System Avionics Support Equipment 7 2 GULFSTREAM AMERICAN MODE L AA 5A CHEETAH Pa 7 15 7 15 7 17 7 17 7 17 7 18 7 18 7 18 7 18 7 18 7 18 7 19 7 ...

Page 125: ...t and passengers Access to the baggage compart ment behind the rear se ts is provided by a baggage door on the left side of the fuselage A tubular spar carry through located beneath the pilot s seat provides the attach ment points for the wings and main landing gear This arrangement provides the AA 5A airplane with an xtremely strong center section The full cantilever modified laminar flow Vl ings...

Page 126: ...or shows the desired flap angle when released it returns to neutral and flap travel stops CAUTION A B RU PT LY RELEASING THE SWITCH MAY CAUSE IT TO SNAP THROUGH THE NEUTRAL DETENT INTO THE RETRACT POSITION INSTRUMENT PANEL The instrument panel Figure 7 1 employs a unique eyebrow design which shields the windshield from panel reflections during night flights The eyebrow also houses the instrument p...

Page 127: ... R H L H 26 CIRCUIT BREAKERS 27 PARKING Bf AKE 2B PRIMER 31 32 33 34 35 36 37 3B 39 40 41 42 43 44 45 46 47 4B 49 50 51 52 53 54 55 56 SECTION 7 AI RPLANE SYSTEMS DESCRIPTIONS MIXTURE CONTROL FUEL GAUGES R H L H FUEL SELECTOR ASH TRAY CIGARETTE LIGHTER OPT FLAP SWITCH TRIM TAB CONTROL TRIM POSITION INDICATOR FLAP POSITION INDICATOR MICROPHONE MICROPHONE SWITCH THROTTLE CABIN HEAT CONTROL CARBURETO...

Page 128: ...ing gear struts are of tough laminated fiberglass to achieve outstanding shock absorption and good ground stability The nose gear is free castering to approximately 90 on either side of the centerline which gives good maneuverability on the groiJnd BAGGAGE COMPARTMENT The baggage compartment occupies the area extending from the back of the rear seats to the aft cabin bulkhead This bulkhead also co...

Page 129: ...E SIN THE V E RTIC A l DI RECTION THE SEAT ADJUST MENT MECHANISM MAY BE DAM AGED NOTE SHOULDER BELTS ARE PROVIDED FOR YOUR SAFETY BE SURE TO USE THEM THE SHOULDER BELT FASTENS TO THE ND OF THE OUTBOARD lAP BELT AllOWING BOTH BELTS TO BE FASTENED OR REMOVED IN ONE OPERATION lAP AND SHOULDER PELTS MAY BE NEATLY STOWED BY HANGING THEM ON THE SID PANEL SUP PORTS PROVIDED lAP BELTS SHOULD BE ADJUSTED T...

Page 130: ...des a means of externally locking the canopy The canopy is designed to open a longitudinal distance of 34 inches and is limited by stops See Section 6 for canopy entrance dimensions The canopy may be partially opened rn flight to provide ventilation or better visibility However THE CANOPY MUST BE COMPLETELY CLOSED AND LOCKED WHEN FLYING AT AIRSPEEDS IN EXCESS OF 113 KCAS 130 MPH The cabin windows ...

Page 131: ...ound the circumference The i ich position is full forward and full aft is the idle cut off position To adjust the mixture move the control forward or aft The carburetor heat control is the square knob mounted to the left of the throttle When this control is pushed in ambient air is routed through the air filter and into the carburetor When the control is pulled out the ambient air is routed throug...

Page 132: ...umulated This will ensure proper seating of the rings The airplane is delivered from the factory with corrosion preventive oil in the engine If during the first 25 hours oil must be added use only aviation grade straight mineral oil conforming to Specification No MI L L 60B2 Figure 1 21 ENGINE OIL SYSTEM Oil for engine lubrication is supplied from a sump on the bottom of the engine The capacity of...

Page 133: ...by engine driven dual magnetos and two spark plugs for each cylinder The right magneto fires the lower right and upper left spark plugs and the left magljeto fires the lower left and upper right spark plugs Normal operation is conducted with both magnetos due to the more complete burning of the fuel air mi ture with dual igni ion Ignition is controlled by a rotary key actuated switch located near ...

Page 134: ...ipped with an enclosed ac celerator pump simplified fuel passages to pre lent vapor locking alJ idle cut off mechanism and a manual mixture control Fuel is delivered from the fuel system to the carburetor by an engine driven fuel pump oj an auxiliary electric fuel pump In the carburetor fuel is atomized proportionally mixed with intake air and delivered to the cylinders through intake manifold tub...

Page 135: ...o the right of the radio section of the instrument panel The electric pump should be turned J on if the engine driven pump fails as noted by a loss of fuel pressure The electric fuel pump can also be used to provide fuel pressure redundancy during low altitude operation such as uring takeoff and landing There are four fuel drains on the airplane One is located in each fuel tank and one in each sum...

Page 136: ...VEN AUXILIARY FUEL PUMP FUEL PUMP 1 1 AUXILlARY JJ FUEL PUMP Z 0 SWITCH l l TO ENGINE j 1 i J FUEL TANK SELECTOR fi ENGINE PRIMER FUEL QUANTITY GAUGES 0 FUEL FUEL TA JJ tll TFUEL r FUEL TANK I _ FUEL STRAINER SUMP TANK VENT SUMP TANK QUICK DRAIN VENT FLUSH FLUSHI 7 14 CODE c JFUEL SUPPLY c JVENT MECHANICAL LINKAGE ELECTRICAL CONNECTION Figure 7 2 Fuel System Issued January 15 1977 ...

Page 137: ...breaker Should ither of these breakers open due to excessive current in the system they should be reset after waiting at least 15 seconds If either breaker will not reset the alternator side of the master switch should be turned OFF and the airplane systems then operated on existing battery voltage Overvoltage protection is provided by a diode attached to the field circuit breaker forward of the i...

Page 138: ...SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS AUX POWER RECEPTACLE 7 16 BATTERY Figure 7 3 GULFSTREAM AMERICAN MODEL AA 5A CHEETAH MAGNETO SWITCH Electrical System Sheet 1 of 2 Revised December 15 1977 ...

Page 139: ...AV IGHTS TURN 1Io BANK LANDING I IGHT FLASHER BEACON FUEL GAUGES STALL HORN OIL TEMP FLAPS PITOT HEAT FUEL PUMP STROBE STARTER NOTES SECTION 7 AIRPLANE SYSTEMS DESCRIPTIONS 1978 Model and subsequent CODE t CIRCUIT BREAKER PUSH TO RESET 0 FUSE DIODE Fiqure 7 3 Electrical System Sheet 2 of 2 Revised December 15 1977 7 16a 7 16b blank ...

Page 140: ... ...

Page 141: ...age NOTE When external power is used voltage transients may be intrQduced into the elect ical system Ensure that all radios and other electronic equipment remain deenergized when external power is be ing applied to the airplane Just before connecting an external power source generator type or battery cartl the master switch should be turned off LIGHTING SYSTEMS EXTERIOR LIGHTING Conventional navig...

Page 142: ...he master switch position INSTRUMENT PANEL LIGHTS The instrument panel lights are controlled by a rheostat mounted directly above the throttle This control turns off the instrument panel lights when it is rotated fully counterclockwise As the rheostat is rotated clockwise the bri lhtness of the instrument lights is increased MAP LIGHT An optional map light may be installed on the AA 5A airplane Th...

Page 143: ...eat occupants Maximum ventilation can be obtained by sliding the canopy open to the placard marker on the canopy tr ck at speeds up to 11 KI AS 130 MPHI Fresh air ventilation for the rear cabin area Ptional is provided by adjustable vents located just forward of the rear arm rests They are operated by a twisting motion and air may be directed by positioning the vent in the desired direction To obt...

Page 144: ...UTlET CABIN HEAT CONTROL 7 20 CODE C VENTILATING AIR HEATED AIR CONDITIONED AIR MECHANICAL CONNECTION MODEL AA 5A CHEETAH EXHAUST MUFFLER DEFROSTER OUTlET BOTH SIDES CABIN AIR CONTROL BOTH SIDES CABIN AIR VENT BOTH SIDES REAR CABIN AIR VALVE NOZZLE BOTH SIDES REAR AIR VENT BOTH SIDES Figure 7 4 Heating Defrosting System Issued January 15 1977 ...

Page 145: ... and miles per hour inner scale The limitat ons and range markings are as follows Marking Significance KCAS MPH White Arc Flap operating range 53 104 61 120 Green Arc Normal operation 55 130 63 150 Yellow Arc Caution range 130 165 150 190 Red Line Never exceed speed 165 190 If a true airspeed indicator is installed it i equipped with a movable ring which works in conjunction with the airspeed indi...

Page 146: ...a suction gauge on the instrument panel ATTITUDE INDICATOR An attitude indicator is available and gives a visual indication of flight attitude Bank attitude is presented by a pointer at the top of the indicator relative to a bank scale which is marked in increments of 10 20 30 60 and 90 either side of the center mcrk Pitch attitude is presented by a miniature airplane in relation to the horizon ba...

Page 147: ...i GULFSTREAM AMERICAN MODEL AA 5A CHEETAH SUCTION GAUGE SECTiON 1 AIRPLANE SYSTEMS DESCRIPTIONS dJ VACUUMSYSTEM AIR FILTER Figure 7 5 Vacuum System ISsued January 15 1977 7 23 ...

Page 148: ...ORN OIL TEMP fuse from the airplane electrical system A lift detector located on the leading edge of the right wing actuates the stall warning system As the airspeed and angle of attack of the wing change to the extent that a stall condition is imminent a portion of the air flow over the wing leading edge lifts the tab on the lift detector_ The lift detector then completes a circuit that applies e...

Page 149: ...ilot Conducted Preventive Maintenance Alterations or Repairs Ground Handling Towing Parking Tie Down Jacking Leveling Flyable Storage Servicing Engine Oil Oil Change Fuel Tire Service Brake Service Battery Service Cleaning and Care Exterior Care Windshield Canopy and Window Care Propeller Care Interior Care Issued January 15 1977 Page 8 3 8 3 8 3 8 3 8 4 8 5 8 5 8 5 8 5 8 6 8 6 8 6 8 7 8 8 8 8 8 9...

Page 150: ... ...

Page 151: ...is number together with the model number typ certificate number and produc tion certificate number are tamped on the iqentification plate attached to the left side of the fuselage beneath the horizontal s tabilizer On the upper left corner of the firewall is a plate giving the finish and trim code number of the particular airplane This code number qescribes the interior color scheme and exterior p...

Page 152: ...re owners of airplanes not registered in the United States should check with their own aviation officials to determine the requirements of the nation the airplane is to be flown in lin addition to the forms listed Gulfstream American suggests that the Pilo1 Operating Handbook be kept in the airplane at all times AIRPLANE II ISPECTION PERIODS As required by Federal Aviation Regulations all civil ai...

Page 153: ...ce to ensure that proper procedures are followed Your Gulfstream I American Dealer should be contacted for further information or for required maintenance which must be accomplished by appropriatilly licensed personnel ALTERATIONS OR REPAIRS It is essential that the FAA be contacted prior to any alterations on the airplane to ensure that airworthiness of the airplane is not violated Alterations or...

Page 154: ...ions tie the airplane down as outlined in the following paragraph CAUTION WHEN USING CHOCKS ENSURE THAT THE CHOCKS DO NOT CON TACT THE LANDING GEAR WHEEL FAIRINGS USING CHOCKS THAT ARE TOO HIGH COULD RESULT IN DAMAGE TO WHEEL FAIRINGS TIE DOWN Proper tie down procedure is the best precaution against damage to the parked airplane by gusty or strong winds To tie down the airplane securely proceed as...

Page 155: ...THE GROUND AS TAIL CONt AND OR ELEVATOR DAMAGE MAY RESULT NOTE Do not apply pressure on the outboard horizontal stabilizer surfpces When pushing on the tail cone a iways apply pressure at the root of the horizontal stabilizer to avoid buckling the skin Ensure that the nose will be held off the ground under all conditions by means of suitable stands or supports under the firewall of the airplane Se...

Page 156: ...WHILE TURNING THE PROPELLER After 30 days in storage the airplane should be flown for at least 30 minutes or a ground runup should be made just long enough to produce an oil temperature within the lower green arc range Excessive ground runup should be avoided Engine runup helps to eliminate excessive accumulations of water in the oil sys tem and other air spaces in the engine Keep fuel tanks full ...

Page 157: ...n use only aviation grade straight mineral oil conforming to Specification No MI L L 60B2 Figure f 2 CAPACITY OF ENGINE SUMP 8 QUARTS Do not operate on less than 6 quarts To minimize loss of oil through the breather fill to 7 quart level for normal flighJs of less than 3 hours For extended flight fill to Bquarts These quantities refer to oil dipstick level readings OIL CHANGE After the first 25 ho...

Page 158: ...e Figure 1 2 Change engine oil every 50 hours Add oil as required to maintain safe level See Section 8 for recommended seasonal grades 4 NOSE WHEEL BEARINGS Grease with MIL G 25760 Figure 1 2 grease after the first 100 hours and every 500 hours thereafter NOSE WHEEL TIRE Inflate to 21 PSI as required 5 NOSE FORK SWIVEL AND BELLVILLE WASHERS Grease with MIL G 7711 Figure 1 2 grease every 100 hours ...

Page 159: ...th MIL L 787Q Figure 1 21 oil as required CANOPY LATCH Grease with white grease Lubriplate 501 or equivalent as required FLAP DRIVE JACKSCREW Oil with MiL L 7870 Figure 1 21 oil Coat with a light film for corrosion prevention only FLAP POSITION INDICATOR CABLE Grease with MI L G 21164 Figure 1 21 Molybdenum Disulphide grease as required BRAKE RESERVOIRS Fill to within 1 4 inch of top with MIL H 56...

Page 160: ... brake system reservoirs located on the pilot s brake master cylinders should be filled to within 1 4 inch of the reservoir top with hydraulic fluid conforming to MI L H 5606 Figure 1 2 BATTERY SERVICE The battery which is accessible by opening the top cowl is equipped with an overboard vent and drain It is rated at 12 volt 25 ampere hours and should be inspected periodically for proper fluid leve...

Page 161: ...n the canopy windshield and cabin windows clean and unscratched by usin the following procedures 1 If large deposits of mud andlor dirt have accumulated on the plexiglas flush with clean water Rubbing with your hand is recommended to dislodge excess dirt and mud without scratching the plexiglas 2 Wash with soap and water Use a sponge or heavy wadding of a soft cloth DO NOT rub as the abrasive acti...

Page 162: ... blot it up promptly with cleansing tissue or rags Continue blotting until no more liquid is taken up Sticky materials may be scraped up with a dull knife then cleaned up with a spot remover Oily spots may be cleaned with household spot removers used sparingly Before using any solvent read the instructions on the container and test it on an obscure place on the fabric to be cleaned Never saturate ...

Page 163: ...M AMERICAN MODEL AA 5A CHEETAH SECTION 9 SUPPLEMENTS SECTION 9 SUPPLEMENTS Optional Systems Description Operating Procedure TABLE OF CONTENTS Page Introduction 9 3 Supplements Issued January 15 1977 9 1 9 2 blank ...

Page 164: ... ...

Page 165: ...h may be installed in the airplane Each supplement contains a brief description and when applicable operating limitations emergency and normal procedures and performance Other routinilly installed items of optional equip ment whose function and operational procequres do not require detailed instruct ions are discussed in Section 7 Issued January 15 1977 9 3 9 4 blank ...

Page 166: ... ...

Page 167: ...s Informatiqn Manual Advisory Information General Information or Specific Topics Flight Planning Inspection Maintenance Special Conditions and Precautions Walk Around Inspections Cockpit Checks Flight Operations General Engine Operation in Flight Turbulent Weather Flight in Turbulent Air Flight in Icing Conditions Mountain Flying VFR Low Ceilings VF R at Night Issued January i 5 1977 Page 10 3 10 ...

Page 168: ...rtices Wake Turbulence Takeoff and Landing Conditions Medical Facts for Pilots General Fatigue Hypoxia Hyperventilation Alcohol Drugs Scuba Diving Additional Information 1 2 GULFSTREAM AMERICAN MODEL AA 5A CHEETAH Page 1 12 1 12 1 13 10 13 10 14 10 14 1 14 10 14 10 15 10 15 10 15 1 15 10 16 Issued January 15 1977 ...

Page 169: ...cts We strongly recommend these subjects be reviewed periodically along with other documents required for opera tion of the airplane Topics in this publication are mostly excerpts from FAA Documents and other articles pertaining to the subject of safe flying They are not limited to any particular make or model airplane and do not replace instructions for particular types of airplanes Your Gulfstre...

Page 170: ...takeoff ensure that the airplane weight and C G are within limits for the type of flying intended Be sure that articles and baggage are secured Check freedom of all controls Maintain an appropriate airspeed in takeoff climb descent and landing Remain alert to see and avoid other aircraft traffic Avoid big airplane wake turbulence Switch fuel tanks before you have to Keep your airplane in good mech...

Page 171: ...lities as a pilot are clearly defined by government reguilitions Since these regulations are designed for your own protection compliance with them is not only mandatory but beneficial to you RULES AND REGULATIONS F lderal Aviation Regulatiofls Part 91 General Operating and Flight Rules is a document of law governing operation of aircrah and the owner s and pilot s responsibilities Part 91 includes...

Page 172: ...lms of flight including navigation ground procedures and medical information Among the subjects discussed are Controlled Air Space Services Available to Pilots Radio Phraseology and Technique Airport Operations Clearances and Separations Pre flight Departures IF R Enroute IF R Arrival IF R Emergency Procedures Weather Wake Turbulence Medical Facts for Pilots Bird Hazards Good Operating Practices A...

Page 173: ...Flight Service Station even though the flight may be VF R Also advise Flight Service Stations of changes or delays of one hour or more in flight plans and remember to close the flight plan at your destination The pilot must be completely familiar with the performance of his airplane in cluding performance data in the airplane manuals and placards The resultant effect of temperature and pressure al...

Page 174: ...n and its effects must be treated at the ea liest possible opportunity A clean dry surface is virtually immune to corrosion Make sure that all drain holes remain unobstructed Protective films and sealants help to keep corrosive agents from contacting metallic surfaces Corrosion inspections should be made most frequently under high corrosion risk operating conditions such as in areas of high airbor...

Page 175: ...nufacturer concerning the airplane He is required by FAA regulations to oper ate in accordance with the placards installed ENGINE OPERATION IN F UGHT In addition to leaning the following techniques should be considered to minimize spark plug lead fouling 1 Exchange top spark plugs with bottom spark plugs at mid spark plug servicing periods 50 hours 2 Avoid closed throttle idle operation on the gro...

Page 176: ... just as tornados destroy nearly every thing in their path on the ground A roll cloud ahead of a squall line or thunderstorm is visible evidence of violent turbulence However the absence of a roll cloud should not be interpreted as denoting the lack of turbulence FLIGHT IN TURBULENT AIR Even though flight in severe turbulence is to be avoided flight in turbulent air may be encountered under certai...

Page 177: ...evel of the ridge exceeds 50 knots a strong mountain wave is probable with strong up and down drafts and severe or extreme turbulence The worst turbulence will be encountered in and below the rotor zone wl1ich is usually 8 to 10 miles downwind from the ridge This zone is characterized by the presence of roll clouds if sufficient moisture is available altocumulus standing lenticular clouds are also...

Page 178: ...zon as a reference can override the illusions Under low visibility conditions night f09 clouds haze etc the illusions predominate Only through awareness of these illusions and proficiency in instrument f ght procedures can an airplane be operated safely in a low visibility environment Flying in fog dense haze or dust cloud banks or very low visibility with strobe lights and particularly rotating b...

Page 179: ...more depending on wind conditions and may extend several miles behind the airplane Plan to fly slightly above or to the sid of the other airpl nes Because of the wide variety of conditions th t can be encountered there is no set rule to follow to avoid wake turbulence in all situations however the Airman s Flight Information Manual goes into considerable detail for a number of vortex avoidance pro...

Page 180: ...inancial worries and family problems can be important contributing factors If your fatigue is marked prior to a given flight don t fly To prevent fatigue effects during long flights keep mentally active by making ground checks and radio navigation position plots HYPOXIA Hypoxia in simple terms is a lack of suffiCient oXY len to keep the brain and other body tissues functioning properly Wide indivi...

Page 181: ...ing rate Breathing can be slowed by breathing into a bag or talking loud ALCOHOL Common sense and scientific evidence dictate that you not fly as a crew member while under the influence of alcohol Even small amounts of alcohol in the human system can adversely affect judgment and decision making abilities FAR 91 11 states Ia No person may act as a crew member 1 within 8 hours after the consumption...

Page 182: ...ty and in greater detail These can be obtained at FAA Offices Weather Stations Flight Service Stations or Airport Facilities These are very good sources of information and are highly recom mended for study Some of these are titled Airman s Information Manual 12 Golden Rules for Pilots Weather or Not Disorientation Plane Sense Weather Info Guide for Pilots Wake Turbulence Don t Trust to Luck Trust ...

Page 183: ...iedown Removed Pitot Tube Unobstructed Fuel Tank Vent Unobstructed 4 Left Wing Leading Edge Fuel Tank Full cap seal checked for damage cap secure Tank Drain Fuel free of water and serliment drain secure Sump Drain Fuel free of water and sediment drain secure Fuel Proper color Landing Gear Wheel Fairing and Tire Undamaged tire properly inflater Chocks Removed 5 Left Cowl Windshield Clean undamaged ...

Page 184: ...acuum Pump Vent Unobstructed Battery Secure Alternator Belt Proper tension Cowl Closed latches secured flush with surface Windshield Clean undamaged 8 Right Wing Leading Edge Fuel Tank Full cap seal checked for damage cap secured Tank Drain Fuel free of water and sediment drain sl1c recJ Sump Drain Fuel free of water and sediment drain secure Fuel Proper color Landin Gear Wheel Fairing and Tire Un...

Page 185: ...cuit Breakers Ch eck Spare Fuses In Glove Compartment Flashli lht Ahoard Required Charts Ahoard ELECTRICAL SYSTEMS PREFLIGHT 1 Cabin Master Switch ON Instrument Li lhts Che k Rheostat OF F Navi lation Li lhts _ ON Flashin l Beacon ON Strobe Li lhts ON Pitot Heat ON Landing Li lht ON 2 Left Wing Tip Navigation Light Illuminated Strobe Light Flashing Pitot Tube Check for heat 3 Nose Landing Light Il...

Page 186: ...CH Carburetor Heat 0 FF Fuel Selector Valve Set to fullest tank Prime As required Flaps UP Auxiliary Fuel Pump ON Check pressure 0 5 8 PSI Propeller CLEAR Ignition Switch ON LEFT Throttle Open approximately 1 4 inch Starter Button PR ESS release when engine starts Ignition Switch ON BOTH Oil Pressure Check if no pressure within 30 seconds shut down engine Engine Warm up at 1000 to 1200 RPM Auxilia...

Page 187: ...rectional gyro altimeter radios Lights ON as required Parking Brake OFf TAKEOFF Normal Takeoff Flaps UP Carburetor Heat OFF Auxiliary Fuel Pump ON Throttle FULL OPEN Elevator Control Raise nosewheel at 50 KIAS 58 MPH to 55 KIAS 63 MPH Climb Speed 85 KIAS 98 MPH Turn Transponder td ON after takeoff Obstacle Clearance Takeoff Flaps UP Carburetor Heat OFF Auxiliary Fuel Pump ON Throttle FULL OPEN Ele...

Page 188: ...at Belts and Shoulder Harness Adjust and lock Fuel Selector On fullest tank Mixture FULL RICH Auxiliary Fuel Pump ON Carburetor Heat ON if required Parking Brake OF F Flaps SET as required below 103 KIAS 119 MPH Airspeed 65 KIAS 75 MPH to 70 KIAS 80 MPH Landing Light ON as required BALKED LANDING Power Full throttle Carburetor Heat OF F Airspeed 60 65 KIAS 69 75 MPH Establish Climb Attitude FI ps ...

Page 189: ... Brakes As required for directional control and stopping AFTER LANDING Flaps UP Auxiliary Fuel Punip OFF Landing Light OFF if used Carburetor Heat 0 FF Strobe Light OFF iif used SHUT DOWN SECURING AIRPLANE Electrical Equipment Radios Lights OF F Mixture IDLE CUTOFF Ignition OF F after propeller has stopped Master Switch 0 FF Control Lock Installed Parking Brake SET Chocks Tiedowns Installed Parkin...

Page 190: ... _1 1 f1 I ...

Search results

Summary of Contents for 1978 AA 5A CHEETAH

Reviews:

Related manuals for 1978 AA 5A CHEETAH

Brands by name

Popular brands

Gulfstream Aerospace 1978 AA 5A CHEETAH, Pilot Operating Handbook

Search results

Summary of Contents for 1978 AA 5A CHEETAH

Reviews:

Related manuals for 1978 AA 5A CHEETAH

Brands by name

Popular brands