Hughes 269A Owner's Maintenance And Flight Manual

2.7 -Sept. 28, 1961 2.8 May 15, 1962 2.9 May 15, 1962 3.1 Sept. 28, 1961 3.2 May 15, 1962 SECTION Ill 3.3 May 15, 1962 APPROVED by ~ ~..: ~ ~hief Aircraft Engineering Branch Federal Aviation Agency 1.2 ' ) THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS AS SET FORTH IN SECTION I OF THIS HANDBOOK. MODEL 269A HELICOPTER Serial Numbers 0011 and subsequent TYPE CERTIFICATE NO. 4H12 REGISTRATION NO,______________ _ SERIAL NO. -------=- 0--= 0'--"~ "----'-- / ______ _ APPROVED BY--~--=-~----~--+-__:__• __ _ Nr.,, Chief Aircraft Engineering Branch tf- Federal Aviation Agency July 27, I 962 DATE OF APPROVAL_____________ _ NOTE: This manual supersedes Model 269A manual previously approved Sept. 28, 1961, and all sub- sequent revisions. This Handbook Must Be Kept In The Aircraft At All Times 1.1 HUGHES MODEL 269A HELICOPTER FAA APPROVED FLIGHT MANUAL LOG OF PAGES Page Date 1.1 Title Page 1.2 Log of Pages 1.3 Sept. 1, 1962 1.4 Sept. 1, 1962 1.5 Sept. 1, 1962 SECTION ! 1.6 Sept. 28, 1961 1.7 Sept. 1, 1962 1.8 Sept. 1, 1962 1.9 Sept. 1, 1962 2.1 Sept. 28, 1961 2 .2 Sept. 28, 1961 2.3 Sept. 28, 1961 2.4 Sept. 28, 1961 2.5 Sept. 1, 1962 -· SECTION II 2.6 Sept. 1, 1962 2.7 Sept. 1, 1962 2.8 Sept. 1, 1962 2.9 May 15, 1962 3.1 Sept. 1, 1962 3.2 Sept. 1, 1962 SECTION Ill 3.3 Sept. 1 , 1962 ~VED py ~ h 4r;.,,,fl 1.,111efAircraft Engineering ranc Federal Aviation Agency 1.2 I ) ) SECTION 1 OPERATINGLIMITATIONS 1. AIR SPEED LIMITATIONS a. The never exceed speed (Vne) is 86 mph IAS at sea level. b. Above sea level reduce (Vne) in accordance with Part 6, 2-d, Pg. 1.7; and Fig. B, Pg. 1.9. 2 . ROTORSPEED LIMITATIONS a. Maximum rpm: 530 b. Minimum rpm: 400 3. POWERPLANT LIMITATIONS Lycoming Engine 0-360-C2D a. Take off, five minutes, 2900 rpm, 26" mp, (165 HP at sea level varying linearly to 171 HP at 2500 feet.) b. Maximum continuous operation: 160 HP at 2700 rpm (26" mp at sea level, varying linearly to 24.8" mp at 4000 feet). c, Minimum operation: 2500 rpm to 9000 feet altitude. See Part 6, 2-d, Pg. 1.7 for airspeed vs. altitude/rpm limits. d. Range for idle and clutch engagement 1200 to 1600 rpm. e, Fuel: minimum octane 91/96. f. Oil: SAE 50 above 40°F. SAE 30 below 40°F. SAE 20 below 10°F. 4. FLIGHT LIMITATIONS a. Operate in accordance with Fig. A, Pg. 1.8 Airspeed vs. altitude limitations. 1.3 FAA approved Sept. 1, 1962 Model 269A Helicopter b. Instrument flight prohibited. c. Night flight prohibited when landing, navigation, map, or instrument lights are not installed. __ ~ight fli&ht operation is limited to visual contact flight conditions. Orientation shall be maintained through visual reference to ground objects solely as a result of lights on the ground or adequate celestial illumination. d. Rearward flight or hovering downwind can be conducted up to speeds of 23 mph IAS. Maxi- mum possible operating wind velocities have not been established. e. Minimum crew, one pilot. f. Continuous hover at 2700 rpm 5 feet maximum skid height permitted. 5. WEIGHTAND CG LIMITATIONS a. Maximum takeoff and landing weight: 1550 pounds. NOTE: This helicopter is to be operated in accordance with the approved loading schedule (see Section IV). b. Forward CG limit station: 95.0. ~- Aft CG limit station: 100.0. d. Datum line (Station 100) is rotor centerline , 6.MARKINGSAND PLACARDS 1. Inst r umen t Ma r k i ngs General : Red radial lines; maximum and minimum limits . Yellow arc: cautionary range. Green arc: norma°l operating range. a. Engine Oil Temperature Red radial line: 104° and 244°F. Green arc: 160° to 244°F. Yellow arc : 104° to 160°F . b. Engine Oil Pressure Red radial lines: 60 and 85 psi. Green arc: 60 to 85 psi. c. Cylinder Head Temperature FM approved Sept. 1, 1962 Model 269A Helicopter 1.4 Red radial line: 500 ° F. Green arc : 230 ° to 450 ° F. Yellow arc: 450 ° to 500 ° F. d. Fuel Pressur.e Red radial lines: 9 and 15 psi. Green arc: 9 to 15 psi. e. Transmission Oil Temperature and Pressure Warning lights on the instrument panel come on when transmission oil pressure drops below 2½ ± ¼ psi or temperature exceeds 235 ° F. f. Engine Tachometer Red radial lines: 2500 and 2900 rpm . Green arc: 1200 to 1600 and 2500 to 2700 rpm. Yellow arc: 2700 to 2900 rpm. g. Rotor Tachometer Red radial lines: 400 rpm and 530 rpm. Green arc: 400 to 530 rpm . h. Air Speed Indicator Red radial line: 86 mph. Green arc: 40 to 86 mph. i. Manifold Pressure Red radial line: 26 inches j. Carburetor Air Temperature (optional) Red radial line: at 125 ° F. Green arc: 60 ° to 105° F. Yellow arc: 15° to 60°F . FAA approved . Sept . 1 , 1962 1.5 Model 269A Helicopter 2. Flight Limitation Placards ( a.) (b.) ( c-) CHECK LIST TAKE-OFF AND LANDING CARBURETOR HEAT FUEL BOOST PUMP ON SOLO FLIGHT PROHIBITED FROM LEFT SEAT 400 LBS. MAX. GROSS IN CABIN ACROBATIC MANEUVERS PROHIBITED CLUTCH ENGAGEMENT 1. SET 1500 RPM. 2. WITH THROTTLE FIXED MOVE CLUTCH FORWARD SLOWLY TO ENGAGE. NO ENGINE IDLING WITH CLUTCH DISENGAGED ABOVE 1600 RPM. DURING SHUTDOWN DECLUTCH AS SOON AS ENGINE SPEED IS BELOW 1600 RPM. THIS HELICOPTER MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS SPECIFIED IN THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL. FAA approved Sept. 28, 1961 Model 269A Helicopter 1.6 ) ( d.) NEVER EXCEED SPEEDS- MILES PER HOUR (IND. AIR SPEED) ALTITUDE 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 2700 2900 RPM 86 85 84 83 82 81 79 78 75 66 58 2500 RPM ( e.) 86 85 84 83 79 73 66 58 51 44 - NO SMOKING This placard not required if ash tray is installed (f.) 1. 2900 RPM below 200 feet (5 minute limit) See Rotorcraft flight manual for Hover RPM. 2. 2700 RPM minimum between 200 and 500 feet. 3. Heater Operation - Placard and Limits (Reference to Stewart -Warner Series 940 Heater installed in accordance with HTC Drawing No. 269A 4770.) ( a.)Placard FOR HEATER OPERATION ON GROUND WITH ENGINE NOT RUNNING, MIXTURE CONTROL MUST BE IN IDLE CUT-OFF ( b.)Limits HEATER OPERATION ON GROUND WITH ENGINE RUNNING MUST BE LIMITED TO 5 MINUTES DURATION 1.7 FAA approved .Sept. 1, 1962 Model 269A Helicopter 500 ________________ ,.. 2 700 RPM minimum - 350 lm~~~':':Bl~:1:-:--+--t-----,t--t--+--i :: ~:~~:.:~ ~;;,:: •ih RPM 0 10 20 30 40 50 60 70 80 90 INOICAll:O AIRSPEED- MPH NOTE: HUGHES MODEL 269A HELICOPTER Figure A AIRSPEED vs ALTITUDE LIMITATIONS Deter min ed only unde r following conditions: Smo oth Hard Surface Maximum Gros s Wei g ht C ,dm Wind Sea Level Altitude FAA approved Se pt. 1, 1962 Model 269A Helicopter 1.8 HUGHES MODEL 10 269A 9 HELICOPTER 8 ALTITUDE- 7 Figure B THOUSANDS 6 OF FEET 5 VARIATION 4 OF VNE WITH 3 ALTITUDE& RPM 2 Q ., .. "~100 2900 RP- M 2500 RPM\ ··."\. \ ~ ~~ \ .•. .. \. Never Exceed Speed limits . l o 10 20 30 4o so .~o 10 ao go 1.9 INDICATED AIR SPEED- MPH FAA approved Sept. 1 , 1962 Model 269A Helicopter OPERATING PROCEDURES Page 1 . Normal . . .. ... . . ..... .. . . ...... . . 2. 1 2. Take off and Landing ... ..... . . . . ... 2.5 3. Emergency .. ... ....... .. ... . .... . 2.6 4. Heater .. .. .. .. ...... .. .. .. . .. . . . 2.8 SECTION II OPERATING PROCEDURES I. Normal Operating Instructions A. Before Entering Cockpit 1. Have a thorough understanding of operating limi- tations (Section I). 2. Ensure that the loading is in accordance with Section IV. 3. Determine that a Preflight Inspection has been conducted. 4. Check Section Ill for Performance Information. B. Upon Entering Cockpit 1. Adjust rudder pedals. 2. Inspect and adjust safety belts. 3. Check movement of flight controls and establi .sh that rotor blades are in pattern, as evidenced by low cyclic stick force. 4. Set longitudinal cyclic trim t0_ full forward and lateral cyclic trim to full left. 5. Apply moderate friction to cyclic stick to maintain position. 6. Collective stick down, friction full on. 7. Set altimeter. 8. All electrical switches off; fuses in place. 9. External power plugged in if available. 10. Battery switch on. FAA approved Sept. 28 , 1961 2.1 Model 269A Helicopter 11. Check fuel quantity. 12. Press-to-test transmission oil temperature light- check transmission oil pressure light on. 13. Belt drive disengaged (clutch lever aft). CAUTION: MAINTAIN HAND PRESSURE AGAINST PRELOAD ON LEVER WHILE DISENGAGING CLUTCH. C. Starting the Engine 1. Carburetor air on cold. 2. Fuel shut-off valve on. 3. Mixture control in. 4. Throttle fully closed or slightly cracked. CAUTION: Do not open throttle excessively as engine overspeed may result. 5. Ignition switch to both to start. NOTE: Starting system actuates ignition vibrator on left magneto and grounds out right magneto during start. 6. Press starter button to engage starter . 7. After four or five revolutions of the engine by starter, engine hasn't fired, turn fuel boost switch to on and continue cranking. CAUTION: Turn fuel boost switch to off when starter switch is not depressed . Continued operation of boost pump with engine stopped will flood the carburetor. NOTE: It may be necessary in · extremely cold FAA approved Sept. 28, 1961 Model 269A Helicopter 2.2 weather (20 ° F and below) to prime the engine. The procedure is as follows : a. Mixture control out (idle cut off). b. Boost pump switch on. c. Pull primer out and hold for two seconds before pushing in, repeat a second time . After pushing primer in the second time be sure primer is in locked position. d. Boost pump off. e. Mixture control in (full rich). f. Proceed with starting procedure as noted above. CAUTION. DO NOT OVER-PRIME. Prime r is pres- sure operated and priming continues as long as primer is not full in. 8. When engine starts, idle at minimum speed pos- sib le to keep engine running smoothly (900-1100 rpm). NOTE: Avoid continuous idling above 1600 rpm with rotor disengaged. Such operation will result in resonance in the engine output shaft. CAUTION: If minimum of 25 psi oil pressure is not indicated within thirty seconds after engine starts , shut down engine and determine the cause. 9. Disconnect external power if used. 10. Generator switch on. D. Rotor Engagement 1. Collective pitch stick full down, friction full on. FAA approved Sept. 28, 196 1 2 .3 Model 269A Helicopter 2. Rudder pedals and cyclic stick in neutral. 3. Engine speed 1500 rpm. 4. While maintaining fixed throttle, slowly move clutch lever forward until rotor begins to turn. Control rate of engagement so that engine rpm does not fall below 1100 rpm (do not increase throttle). Continue to engage until lever is down in fully engaged position. 5. After rotor is engaged, engine will be running at about 1200 rpm. Avoid continuous operation below 1200 rpm with rotor engaged, as tail rotor drive shaft may develop resonance. CAUTION: Rotor rpm and engine rpm indicator needles must always be superimposed when engine is driving rotor. Any other condition indicates belt slippage , tachometer system malfunctioning, or other mechanical drive failure. If this condition exi sts , shut down engine and investigate. E. Warm-up and Ground Check 1. Warm up at 1800 rpm until oil temperature and pressure are within the green arcs. Check trans- mission oil pressure and temperature warning lights, which should be out. 2. Carburetor heat as required. 3. Open throttle to increase engine speed to 2000 rpm . Check ammeter for proper indication (0 to + 20 amperes normally). FAA approved Sept. 28, 1961 Model 269A Helicopter 2.4 4. Check response of controls at 2000 rpm full low pitch by gently moving cyclic stick . Observe rotor tip for correct movement and track. 5. Check magnetos at 2000 rpm engine speed and slight collective pitch (15 inches manifold pres- sure) . Maximum allowable drop is 125 rpm on either magneto, With no engine roughness. 6. With engine rpm stabilized at 2000 rpm (collec- tive full down), close throttle to check separation of tachometer needles for proper overrunning clutch operation . II. Takeoff and Landing A. Takeoff 1. Follow normal helicopter takeoff procedure at 2900 rpm . (Five minute limit.) 2 . Climb out .speed for takeoff is 70 mph IAS up to 300 feet. Reduce to best climb speed ( 45 mph IAS) above 300 feet. See Height-Velocity Dia- gram, Sec. I, Pg. 1.8, Fig. A. NOTE: 2900 RPM five minute limit. Then reduce to 2700 RPM 160 hp (26" mp sea level, varying linearly to 24.8" mp at 4000 feet). B. Approach to Landing. Increase engine RPM to 2900. C. Running Landing 1. Maximum recommended ground contact is 35 mph IAS for smooth hard surface. 2 . After ground contact, avoid rapid lowering of col- lective pitch. FAA approved Sept. 1, 1962 2.5 Model 269A Helicopter D. Stopping Engine and Rotors 1. Declutch rotor. (To avoid ratcheting of overrunning clutch, declutch as soon as engine speed is below 1600 rpm.) 2. Idle engine at 1500 rpm until a definite decrease of engine cylinderhead temperature is obtained. 3. Turn ignition switch to off. 4. Set all electrical switches to off position. 5. Do not use collective pitch to stop rotor. Ill. Emergency Operating Instructions A. Engine Failure 1. Engine failure while hovering or on takeoff below 10 feet: A power failure is indicated by a sudden yawing of the ship to the left. In the event of such failure, do not reduce Collective pitch. Apply right pedal to prevent excessive yawing. Apply coll,ective pitch as necessary in order to cushion landing. 2 . Engine failure during takeoff; altitude above 10 feet, below 500 feet: CAUTION: In order to effect a safe autorotation landing in the event of engine failure, takeoff operation should be conducted in accordance with the restrictions shown on Height- Velocity diagram, Section I, Pg. 1.8, Fig. A. In the event of power failure during takeoff, the collective pitch must be initially lowered in order that the rotor speed may be maintained. The amount and dura- tion of collective reduction depends upon the height above the ground at which the engine failure occurs. FAA approved Sept. 1, 1962 Model 269A Helicopter 2 .6 As the ground is approached, back cyclic and col- lective should be used as needed to decrease for- ward and vertical velocity. Ground contact should be established with a slight nose high attitude. 3. Engine failure above 500 feet altitude: a. Enter normal autorotation. b. Establish a steady glide of 65 to 70 mph IAS. c. At an altitude of about 50 feet, begin to steadily apply back cyclic stick to decrease forward speed. d. At approximately 10 feet, coordinate collective pitch with aft movement of cyclic stick to cushion landing . At ground contact a slight nose-high I.and- ing on the skid is accomplished. e. Avoid rapid lowering of collective pitch. f. In event of engine failure at night, do not turn on landing light above 1000 feet above terrain in order to preserve battery power. B. Ditching with Power 1. Descend to hovering attitude over water. 2. Turn battery and generator switches off; leave ignition switch on. 3. Maintain level attitude and accomplish normal landing . As contact is made with water, apply side- ward stick causing rotor blades to strike water. 4. Release safety belt. 5. Climb out door and clear aircraft as quickly as possible. FAA approved Sept. 1 , 1962 2. 7 Model 269A Helicopter C. Ditching Without Power l. Turn off battery and ignition switches. 2. Make autorotative glide at 65 to 70 mph IAS. 3. Apply back pressure on cyclic to arrest forward flight before contact. 4. Apply collective pitch to cushion landing. 5. As contact is made with water, level helicopter and apply sideward stick, causing rotor blades to strike water. 6. Release safety belt. 7. Climb out door and clear aircraft as quickly as possible. D. Tail Rotor Failure Tail rotor failure is indicated by a sudden yawing to the right . The only way to prevent this yawing is to close the throttle. Th'ereafter, follow the same pro- cedure as for an engine failure. IV. Heater Operating Instructions A. Stewart-Warner Heater Ground Operating Instructions- Engine Not Running l. Place mixture control in idle cut-off. 2. Fuel boost pump to ON position. 3 . Heater control switch to prime (2 seconds) . 4. Heater control switch to ON position . 5. Regulate push pull control for temperature desired in cabin . 6. Return heater control switch to OFF position to discon- tinue heater operation . FAA approved Se pt. 1, 1962 Model 269A Helicopter 2.8 B. Stewart -Warner Heater Operating Instructions-Engine Running (Limit Operation to 5 Minutes on Ground) 1. Heater control switch to prime (2 seconds). 2. Heater control switch to ON position. 3. Regulate push pull control for temperature desired in cabin. 4. Return heater control switch to OFF position to discon- tinue heater operation. -:3 > 2.9 FAA approved 15 May 1962 Model 269A Helicopter ( ( SECTION Ill PERFORMANCE DATA The following performance data are based on normal gross weight (1550 lbs .) and standard conditions. Speed for best rate of climb Hovering ceiling (3-foot skid height) 40 -45 mph IAS 6,300 feet Estimated hovering ceiling, out of ground effect 4,000 feet Air Speed Calibration Indicated Air Speed (IAS) corrected for position and instru- ment error equals Calibrated Air Speed (CAS) . Determine corrected IAS from the Airspeed Calibration Curve on Pg. 3.2 . . FAA approved Sept. 1 , 1962 3 . 1 Model 269A Helicopter I. _,__ Figure C QJ '"O ;:l .IJ 'M .IJ 16 Skid Height - 3 Feet - No Muffler HOVER N 14 ___ ..,_____.._. - - Wllh 269A8801 Muffler lnstallatlon CEILING <r! vs QJ TEMPERATURE 1-1 ;:l MAXIMUM U) 12 U) PERFORMANCE QJ 1-1 P-, .IJ 10 QJ Q) J:%.< Chart 1 4-l 0 5 · Applicable lo Model 269A U) '"O Helicopters with Lycoming i:: 0-360-C2D Engine Serial (lj Nos. l -4600-36, l -4641-36 U) 6 ;:l and subsequent 0 p I oO i:: HUGHES 'M N MODEL 'M QJ 2 269A u HELICOPTER 1-1 QJ :> 0 0 ::i::: HUGHES MODEL 269A HELICOPTER 100 90 Figure D AIRSPEED CALIBRATION CURVE 80 ~ 70 UJ 0.. ~ 60 < ~ 50 .."'~ 40 .. u . 30 20 JO 0 20 40 60 TEMPERATURE- DEGREESF. /, /" l/ V V V V 80 100 I .,/ i, / O O 10 20 30 · 40 50 60 70 80 90 JOO INDICATED AIRSPEED FAA approved Sept. 1, 1962 3.2 Q) 'Cl ::, ,1..1 •r-l ,1..1 ~ <fl Q) H ::, ti] ti] Q) H P--l ,1..1 Q) Q) Ii-I l+-l 0 ti] 'Cl i:: ell ti] ::, 0 ~ I ~•r-l ~ •r-l 16 Skid Height - 3 Feet -No Muffler 14 - -With 269A8801 Muffler Installation 12 10 8 6 8 2~---½-----l------l--+- - --+---~ H Q) >o o ·+-..--+--r---,1.._ __ .a+_._ __ ..., ____ ~ ~ 0 20 40 60 80 100 TEMPERATURE-DEGREESF. Figure E HOVER CEILING vs TEMPERATURE ALTERNATE PERFORMANCE Chart 2 Applicable to Model 269A Helicopters with Lycoming 0-360-C2D Engine Serial Nos. L-3818-36 through L-4599-36 and L-4601-36 through L-4640 -36 HUGHES MODEL 269A HELICOPTER 3.3 FAA approved Se pt • 1 , 1962 WEIGHT AND LOADING INFORMATION Page 1 . General . . . . .... . .. .. ...... . ...... 4. 1 2. Balance Diagram .... .. . ..... ...... 4.2 3. Center of Gravity Chart ... . .. . . .. ... 4.4 4. Loading Chart .... . ............... 4.5 5. Weight and Balance Report .... .... .. 4. 7 6. Equipment List . ......... .. ...... . . 4.7 WEIGHT AND LOADING INFORMATION GENERAL All helicopters are designed for certain limit loads and bal- ance conditions . Changes in equipment which affect the empty weight and empty weight center of gravity must be entered on the repair and alteration report form ACA-337, in accordance with Civil Air Regulations, which shall then become part of the helicopter file. To determine that your gross weight and center of gravity for a given flight are within limits, use the following procedure: (1) From the weight and balance report (or the current form 337) for your helicopter, determine basic weight and basic weight moment. (2) Determine the weights and moments of your disposable load items, using the load chart. (3) Add these items , as shown in the sample problem. (4) Plot the totals on the center of gravity chart. Moment Sample Problem " Weight 1000/in. lb. Basic Weight 935 94.3 Fuel (full tank-25 gal.) 150 16.0 I ,.Pilot 170 14.2 la Passenger 70 14.2 -- -- 1425 138.7 Locate this point (1425-138. 7) on the center of gravity chart. Since the point falls within the shaded area between fines A & B (full fuel computation limit) the above loading meets all balance requirements. 4.1 100 80 60 40 7" N> 20 0 0 20 40 60 ) I I I (STA\ v:v 80 I I I (ill) @ 6 7 100 120 140 160 BALANCE DIAGRAM I I I I I I I I I I @ I @) 0 9 180 200 220 240 260 280 BALANCEDIAGRAM The horizontal reference datum is located 100 inches for- ward of the centerline of the rotor . The approved center of gravity limits are Station 95 and Station 100. All flight loadiings must fall on or between these limits throughout the flight. For convenience in measuring during aircraft weighing, Sta· tion 100 is marked on the fore and aft fuselage tubes, and Station 267 is marked on the bottom end of the tail boom . The approved levelling pad is clearly marked on the rotor mast housing . If passenger seat is not occupied, cargo or baggage may be carried thereon up to 200 pounds, provided it is properly secured. 4.3 155 150 145 140 135 130 MOMENT IN THOUSANDS 125 OF INCH - POUNDS 120 115 110 105 100 95 90 1000 1100 269A CENTER OF GRAVITY CHART Figure F ~ Fwd CG Limit Full Fuel ' 1200 1300 1400 1500 Al RCRAFT WEIGHT- POUNDS 4.4 '.)