Table Of Contents Jeppesen-Books Pdf

TABLE OF CONTENTS Jeppesen
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PART A CALCULATOR SIDE, CR 2 and CR 3, 0 Unit Index. 0 Cursor Hairline 0 Top Disc, 0 Recovery CoefCicient 1 0 0 Temperature Conversion Scale. 0 Nautical Statute Conversion Arrows G Indicated Temperature Window. 0 Calibrated Air Speed Window 4D Mach Number Window. G Time Index G Temperature Rise ScalP, 0 True Air Speed Windows 0 True Altitude Window. 0 Base Disc G Latitude for Pressure Pattern Scale, Given Ground peed 200 I P H. Oistance 300 Stat l1, Time e nroute, Given Oi tanre 210 i.
Time 50 1 in, Time Speed Distance, Find Ground peed. Time speed and di tanre problems are solved with the CR. Computer in the conventional manner using the out idc scales. on the calculator side For the benefit ol tho e knot so inclined. the CR is knot knecessarily knaULical and you can get perfectly. good an wers in PH and stattHe Let s run through ome quickies. so s you won t figure Ole Sharp is spoofi ng you, fi rst a word about reading the sca les o n the C R Each figure Fig 2. o n the outer scales of the compu ter can stand for any number con. To find di tanre il you are given ground spe l and time pl re. taining the given digits T he poim marked 40 ca n tand lor I 1 time index A oppmite ground speed and read di tance on outside. 40 400 etc You must d etermine from the given problem which lale oppo ite time on imide scale. value is correct, Problems 1, Sec page 57 ror an wt r. T im c mud sp d istanre, I 2 180 kt, 2 I 4 tal mi, 3 l ltl k t 510 rwrrt mi. 4 I 10 IIi II H, I flO n llll 111 i, liliO Lat nli 1.
FUEL CONSUMPTION, Problems involving hr cl OrhtllllJHion arc worked in the amc. man ner a tirne pced di tancc prohlerm Simply plarc g lllcHh in. lead o miles on the olll ide ale a nd time o n the in idc talc. Gallon per hour instead ol urile per hour will he read oppmite. the time index J, II U S gallons ga olin c arc being uwd por rrHI per hour. may be read o n the o ut id e ale oppmite the SI C arrow at lli. on the inside scale CONVERSIONS, Thing arcrr t al ay what OU want them to he. But the C R will help Oll cha nge thcn1, An aircraft ha corl llllled 105 U S g lllorr ol g r olinc in I hr. 30 lllr ll Fo r in t rrHc il OU wan t to change, Na utica l mil es to tat11te miles or kilorneter.
f ind G allon J l r hour and potrrrd per hour, l l S gallon11 to imperial gallon 01 liter. Feet to ureters, Pound to l ilograllh, Or icc vcr a. Note the followirtg labc lc d arrow o n inside and o m sidc r rlc1. of the calculator ide ol the Ollll ltLCr, NAUTIC L rnile o near Ci i on both Cak. STATUTE rniles nc rr iii on bmh calC, K 1 kilom e te r nca1 I o n bnrh calc. 1 1p L nca r I I or 1 both sea lcs, S G L ncar 1 1 Oil both c k.
LITERS ncar IH Oil both sca l e, F 1 ncar I I o n Olll idc r rle. I ETI RS near J l Oil i n id c scale, LBS Ilea r li on mrt ide ric. KC kilograrm near 1f o n in id e sea lc, To convert between two different units or measure simply find Example. th e arrow for the first unit of measure o n one scale of the compu ter. Convert 40 nautical m iles to statute miles, and place it opposite the arrow for the second u nit of measure on. the other sca le Read corresponding va lues op posite each other o n. the two scules, Conven 40 n a utical mi les to sta tute miles.
2 Opposite 40 on outside, sca le read 46 on inside. This method may be used for converting among nautical. miles statute miles and kilometer s and among imperial gallons. U S gallons and liters It may not be used to convert between. feet and meters or pounds and kilograms because all arrows for. the Jailer conversions are on opposite scales, Celsius Fahren heit. A temperature conversion scale is located on the ca lculator. side of the CR Read temperature con versions directly from th is. Th is method is especia lly good il you h lVe series or yuamities. to conven Only one euing i necessary ror a series IJecausc every. yuantity on the out i dc cale rcprc f n nautical miles vr knots. and the correspondi ng values in Wit h 1niles or I P H tre fou nd. oppo ite on the imid e scale 80 n nttir tl nlilcs 9 stallttC 111 iles. 38 statu te miles 33 n l tttira l mi l e etc It would a lso have been. possible to 111atch the ST TU T E arrow on the out i clc c tl e with. the NAU TI CAL arrow on the in i dc s a lc reading lat u te mi les on. the outside scale and nauticd mi l e on the imide scale. Usc the same method or a ll other qu tntity otlversion Sintply. match the arrows lor tlw desired tjuantities, vV hen convening on ly one quantity instead ol a Cries of quan. titic the lo ll owing method may he prercrrcd Fig 6. Problems 2 Example, Change 2 500 meters to feet, 1 100 nautical miles statute miles. 2 196 statute miles nautical miles, 3 90 statute miles Kilometers.
4 250 kilometers nautical miles, 5 53 U S gallons imperial gallons. 6 80 imperial gallons U S gallons, 7 198 imperial gallons Hters. 8 140 liters U S gallons, 9 117 pounds kilograms, 10 90 kilograms pounds. 11 20 C oF, 12 50 F oc, To check the reasonableness of your answer remember that 1 meter. equals approximately 3 3 feet, To help in checking reasonableness of your.
answer NOTE, Prob lems 3, 1 km approx 5 naut mi, 41iters approx 1 U S gal. 1 230 feet meters, 1 kg app rox 2 lbs, 2 3 500 meters feet. 1 imp gal approx 1 2 U S gal, 3 82 feet meters, 4 5 500 meters feel. Meters to Feet, WEIGHT OF FUEL AND OIL, Are you perplexed because the constant pressure charts issued by the. National Weather Service express altitudes in meters instead of feet That Want to know how much your fuel and oil weigh Use the following. is no trouble at all The CR makes the conversion by lining up the meters. labeled arrows, arrow near 44 on the inner scale and the feet arrow near 14 on the outer.
scale This sets up the correct proportion of feet and meters Then all. values on the inner scale represent meters and those on the outer scale FUEL LBS near 77 on outside scale. represent corresponding values in feet OIL LBS at 96 on outside scale. Find weight of 18 U S gal of gasoline, To find the weigln of imperial gallons match the FUEL LBS. arrow with the l IP C L alTO on the imide scale and proceed. To find the weight of oil use the O IL LBS arrow at 96 on the. outside sca le and match with the proper GAL arrow on the inside ALTITUDE. scale using the same method as in finding fuel weight Altitude comes in assorted V ll ieties Ever wonder how high. 1s up No need for confusion if you remember the followinl. Problems 4 points, Find the weight of, I 35 U S g l gasoline lndlcalt d Altitude is the altitude reading on the altimeter. 3 50 imp gal oil, 2 500 imp gal gasoline assuming it is correctly set It shows the approximate height of. L 18 U S gal oil, the aircraft above mean sea level MSL. Calibrated Alt1tude is the indicated altitude corrected for. Minutes to Seconds instrument position and installation errors. At 36 on the imide sc tlc i an arrow marked SEC T o convert True Altllude is computed by eorrectinl calibratt d altitude. minutes lO seconds p lace the time index A opposite the number for nonstandard atmosphet ic conditions It is the actual height of. of minutes and read eronds opposite SEC arrow the aircraft a hove st a level. Example Pressur Altitude is the reading on the altimeter when it is. Find number of second in 13 V2 minutes Place time index set to 29 92 Pressure altitude is an important factor for determin. A opposite 1312 Oppo itc SEC a11ow ncar 3G on inside scale ing aircraft performance. Density Altitude is pressure al itude corrected for non stan. Answe r 1312 minute 810 SC 011 1 dard temperature Aircraft performance is affected by density. DENSITY ALTITUDE Example, Near the center of the computer a t the bottom left is the density Given Pressure a Iti tude I0 000.
altitude window Calibrated altitude 9 000, T rue air temperaturc 20 C. Example Ground station altitude 5 000, Given Pressure altitude 3000 Find True a ltitude. True ai r tempera ture 25 C, Find Density a ltitude. Problems 5, Find density altitude for the following conditions. Pressure Altitude True Air Temperature, 1 1500 35 C fig 10.
Proble ms 6, 3 8000 Fitzd true altitude, Pressu re True Air Calibrated Stat ion. TRUE ALTITUDE A ltitude T emp Altitude 1 Iti tude, To find the approximate true altitude use calibrated altitude or I 10 000 25 C 11 400 4 200. indicated if calibrated is not available and true air temperature 2 5 000 0 C 6 000 Sea Level. Greater accuracy can be obtained if you also know the altitude of 3 7 000 JOOC 7 400 1900. the ground station giving your altimeter setting 4 20 000 15 C 1 000 Unknown. While either knots or MPH can be used with the CR Modern. True Air Speed Solution more accurate true air speed answers. will result from using knots when dealing with speeds over 200. The following quantities are necessary for true air speed deter. m ination calibrated air speed indicated air speed corrected for. instrument and position errors pressure altitude altitude read. from altimeter when instrument is set at 29 92 and in dicated. outside air temperature in degrees Celsius If calibrated air speed. and pressure altitude are not available in a problem indicated air. speed and a ltitude may be used instead Remember however the. CR contains no crystal ball and gives answers only as accurate. as the data fed into it, TRUE AIR SPEED, In Lhe old days pilols listened lo Lhe wind in Lhe wires and were. happy to be flying at any speed Today we have accurate air speed THE CR CURSOR. indicators It s a mighty fine gadget but its reading is affected by Tru e air speed calculations arc affected by a temperature re. various items such as temperature pressure compressibility and. accidental misreading by the pilol who may be thinking of somclhing covery coefficient CT which varies with installalion and design. else The CR computer is effective in correcting for all errors except the of the temperature probe on the individual a irplane Recovery. last coefficients vary from 6 to l O Once a recovery coeffic ient is. A fasl flyin g aircraft pushes through the atmosphere so rapidly determined for a particular airplane the coefficient wil l not vary. that the air can t get out of the way fast enough Hence the air is greatly with speed or altitude. compressed in front of the aircraft and is heated by compression As a. result an outside air temperature bulb feels a higher air temperature The cursor on the CR is marked with a straight hairline and. than really exists in the surrounding non compressed a ir Also the rush a curved lin e to the right of it see Fig 11 with recovery coeffi. of air over the outside air temperature bulb creates friction causing. further heating and a still higher fal se reading The amount of this cients plotted for CT values of 8 and 1 0. higher reading of the thermometer is called temperature l ise and The recovery coefficient of CT 8 is the straight line On. must be considered when computing accurate true air speed the CR 2 and CR 3 there are two lines pl otted for the CT value of. An automatic compensation for compressibility temperature 1 ise. and air friction is built into the CR Computer so that no reference to 1 0 The solid line is for the standard stratosphere temperature. graphs and tables and no separate figuring is necessary for correct rue of 55 C 35 000 and a dashed line is for the standard sea. air speed solutions For this reason the CR is especially adapted to the level tempe1 ature of li C When Oying between sea level and. problems of modern aircraft 35 000 feet it is necessary to interpolate between the two lines. For instance at an altitude of 17 500 feet with a CT of 1 0 note. Some lircraft manufacturers prm ide air speed conversion tables that already that 17 500 feet is one half the way between sea leve l and 35 000. inrlurlt correCtions for the tcmpcrawre rise effect of compressibility in addition feet Hence one half of the space between the sea level curve. w co rrect ion for position and i11s11 t1111CIH error The usc of such tables or other. a ir speed data dread cmTcctcd for tcmperatmc rise will result in a double and stratosphere curve of CT 1 0 must be used for the correct. correction with erroneous rc ulls from the C R computer CT curve. In all problems in this book it is assumed that the recovery MACH NUMBER. coefficient is the more common 1 0 unless otherwise stated In figu re 12 read r Jach Number 78 at the poi nter on the. scale di rectly beneath the T rue Air Speed scale T his value indi. Example cates that the aircralt is flying at 78 times the speed ol sound Since. Given Calilmtled air specd 100 kts 1 rath Number is dependent upon the speed of sound which varies. P res u re a 1ti wde l5 000 only wi th tempera ture the same 1 Iach Number represents di ffer. Indic ated air temperawre 30 C erll true air speeds at different tcnrperawres. Find True air peed, True Air Speed From Mach Number and Temperature. Jn aircraft having a l ach indicator it is possible to get true air. speed from l l ach lllllber and ll mperature, Given 1 I ach um her 1 16.
Indicated air tcrnperalllre l0 C, Find True air speed. Problems 7, Find I lit 11i1 S JI I d, C tl i bra ted P rc surc Indicated ir Fig 13. ir Speed ltiwde 1 cnr pentllr rc, I 180 l JP l 5 5 C If outside air temperature is not av tilable it i po sible to find. i kb I li OOO I 5 C true air speed by using reported or estimated a ir Lcnr pent ttr rc in. ii PART A CALCULATOR SIDE CR 2 and CR 3 0 Unit Index 0 Cursor Hairline 0 Recovery CoefCicient 1 0 0 Nautical Statute Conversion Arrows 0 Calibrated Air Speed Window G Time Index 0 True Air Speed Windows 0 Base Disc CR 5 0 Top Disc 0 Temperature Conversion Scale G Indicated Temperature Window 4D Mach Number Window G Temperature Rise ScalP

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