PIPER AIRCRAFT CORPORATION PA-28-161, CHEROKEE WARRIOR II SECTION 5 PERFORMANCE

Piper PA-28 Cadet · Performance Data

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Overview

This document provides comprehensive performance data for the Piper PA-28-161 Cherokee Warrior II. It includes essential performance information required by FAA regulations, as well as additional performance details for optional systems and equipment. The performance data is based on measured flight test data corrected to ICAO standard day conditions and is analytically expanded for various parameters such as weight, altitude, and temperature. The document serves as a critical resource for pilots, offering performance graphs, flight planning examples, and detailed calculations necessary for safe and efficient flight operations. It emphasizes the importance of adhering to specified procedures to achieve the stated performance metrics and provides warnings against extrapolating data beyond chart limits.

Maximum Takeoff Weight: 2325 lbs
Basic Empty Weight: 1391 lbs
Takeoff Distance Required (Headwind 15 KTS): 2100 ft
Climb Rate: 420 ft/min
Cruise Speed at 75% Power: 118 KTS TAS
Total Fuel Required for Example Flight: 22.4 gal
Endurance with 45 min reserve: 4.85 hrs

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Originally published by hasslo.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Performance Data
Year: 1976
Pages: 33
File size: 20 MB
Publisher: hasslo.org

Specifications & performance

Extracted from this document.

Specifications

Cruise speed (kt): 118
Empty weight (lb): 1,391
Fuel capacity (gal): 22.4
Max takeoff weight (lb): 2,325

Performance

Fuel burn (gph): 8.5
Takeoff distance (ft): 2,100

V-speeds

VS1: 44

Weight & balance

Useful load (lb): 934.4
Basic empty weight (lb): 1,391
Max takeoff weight (lb): 2,325

Documentation completeness

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In this document

General Performance Information

This section outlines the performance information required by FAA regulations for the Piper PA-28-161. It includes details on how performance is affected by various factors such as weight, altitude, and temperature, and emphasizes that the performance data is based on standard conditions.

Introduction to Performance and Flight Planning

The performance data presented is based on flight test data corrected to ICAO standard day conditions. The charts do not account for pilot proficiency or mechanical deterioration, and pilots must evaluate additional conditions such as runway surface and wind effects.

Flight Planning Example

This section provides a detailed flight planning example, including calculations for aircraft loading, takeoff and landing distances, climb, cruise, and descent performance. It emphasizes the importance of using the performance charts correctly to determine necessary distances and times.

Performance Graphs

The document includes various performance graphs that illustrate takeoff distances, landing distances, climb performance, and fuel consumption under different conditions. Each graph is accompanied by examples to guide pilots in their calculations.

Warnings and Safety Notes

The document warns against using performance information derived from extrapolation beyond the limits shown on the charts for flight planning purposes. It stresses the need for pilots to consider all existing conditions at departure and destination airports.

Safety notes

Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes.

Full document text

Paragraph No. 5.t 5.3 ).5 5.7 TABLE OF COT\NENTS SECTION 5 PERFORIUANCE ,U General Page No., 5-l : 5-l i 5-3 5:9 , lntroduction to Performance and Flight Ptanning Flight Planning Example' Performance Graphs List of Figures REPORT: vB-E80 ){ PIPER AIRCRAFT CORPORATION PA.2&I6I, CIIEROKEE WARRIOR II SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE 5.I GENERAL All of the required (FAA regulations) and compleme,ntary performance information applicable to this aircraft is provided by this section. Performance information associated with those optional systems and equipment which require handbook supplements is provided by Section 9 (Supplements). 5.3 INTRODUCTION TO PERFORMANCE AND FLIGHT PLANMNG The performance information presented in this section is based on measured Flight Test Data corrected tö I.C.A.O. standard day conditions and analytically expanded for the various parameters of weight. altitude, temperature, etc. The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of the aircraft. This performance, however, can be duplicated by following the stated procedures in a properly maintained airplane. Effects of conditions not considered on the charts must be evaluated by the pilot, such as the effect of soft or grass runway surface on takeoff and landing performance, or the effect of winds aloft on cruise and range perforrnance. Endurance can be gross§ affected by improper leaning procedures, and inflight fuel flow and quantity checks are recommended. REMEMBER! To gpt chart performance, follow the chart procedures. The information provided by paragraph 5.5 (Flight Planning Example) ouflines a detailed flight plan tusing the performance charts in this section. Each chart includes its own example to show how it is used. WARNING Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purpo§es. ISSLJED: DECEMBER 16, 1976 REVISED: JUNE 29, l9tl REPORT: VB-880 5-l §EqTroN 5 PERfOR}TAII{CE PIIER, AIRCRAFT CORPORATION PA.2&I6I, CtrEROKEE WARRIOR tr THIS PAGE I}MNTIONALTY I,EFT BIåNK REPIOBT: VB€e, '*2 I§SIIED: DECEIilSER ld, l yI6 PIPER AIRCRAFT CORPORATION PA-28-161, CHEROKEE WARR]OR tr SECTION 5 PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The lirst step in planning our flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook. The basic empty weight for the airplane as delivered from the factory has been entered in Figure 6-5. If any alterations to the airplane have been made effecting weight and balance, reference to the aircraft logbook and Weight and Balance Record (Figure 6-7) should be made to determine the current basic emp§ weight of the airplane. Make use of the Weight and Balance Loading Form (Figure 6-l l) and the C.G. Range and Weight graph (Figure 6-15) to determine the total weight of the airplane and the center of gravity position. After proper utilization of the information provided we have found the following weights for consideration in our flight planning example Thc lalrding weight cannot be determined until the weight of the fuel established [refer to item (gX l)]. (l) Basic Empty Weight (2) Occupants (4 x l70lbs.) (3) Baggage and Cargo (4) Fuel (6lbieal x 30) (5) Takeoff Weight (6) Landing Weight (a)(5) minus (g)(l), (2316 lbs. minus 134.4 lbs.) to bc uscd has been l39l lbs. 680lbs. 50lbs. 180 lbs. 23 l6 lbs. 2181.6 lbs. Our takeoff weight is below the maximum of 2325 lbs. and our weight and balance calculations have determined our C.G. position within the approved limits. (b) Takeoff and Landing Now that we have determined our aircraft loading, we must .consider all aspects of our takeoff and landing All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight. Apply the departure airport conditions and takeoff weight to the appropriate Takeoff Performance graph (Figures 5-5 and 5-6 or 5-7 and 5-8) to determine the length of runway necessory for the takeoff and/or the barrier distance. The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and, when established, the landing weight. ISSUED: DECEMBER 16, 1976 REVISED: JULY 3,'1979 REPORT: VB-880 5-3 SECTION 5 PERFORMAI.ICE PIPER AIRCRAFT CORPO RATION PA.28-161, CHEROKEE WARRIOR II The conditions and calculations for our example flight are listed below. landing distances required for our example flight have fallen well below the lengths. (l) Pressure Altitude (2) Temperature (3) Wind Component (4) Runway Length Available (5) Runway Required Departure Airport 1500 ft. 80'F (27"C) l5 KTS (Headwint) 4800 ft. 2100 ft.r, The takeoff :urd available runway Destination Airport 2500 ft. 75"F (24oC\ O KTS 7600 ft. I lg0** our flight planning 5000 ft. 60oF (16'c) 7.5 min.*** 10.0 miles*** 1.5 gal.*** NOTE The remainder of the performance charts used in this flight plan example assume a no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance. (c) Climb T[e next step in our flight plan is to detennine the necessary climb segment componcnts. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the iirst variables to be considered in determining the climb components from the Time, Distance, and Fuel to Climb graph (Figure 5-13). After the time, distance and fuel for the cruise pressure altitude and outside air temperature values have been established, apply the existing ionditions at the departure field to graph (Figure 5-13). Now,subtract thevalues obtained from the graph for the field of departure conditions from those for the cruise pressure altitude.

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T[e remailing values are the true fuel, distance and time components for the climb segment of the flight plan corrected for field pressure altitude and temperature. The following values were determined from the above instructions in example. (l) Cruise Pressure Altitude (2) Cruise OAT (3) Time to Climb (10.0 min. minus 2.5 min.) (4) Distance to Climb (13.5 miles minus 3.5 miles) (5) Fuel to Climb (2 gal. minus .5 gal.) *reference Figure 5-6 **reference Figure 5-29 * **reference Figure 5-l 3 REPORT: VB-880 5-4 ISSUED: DECEMBER 16, 1976 RBVISED: JULY 3,1979 PIPER AIRCRAFT CORPORATION PA.28.161, CHEROKEE WARRIOR tr SECTION 5 PERFORMANCE (d) Descent The descent data will be determined priorto the cruise datato provide thc desccnt distancc for establishing the total cruise distance. Utilizing the cruise pressure altitude and OAT we determine the basic time, distance and fuel for descent (Figure 5-25\. These figures must be adjusted for the field pressure altitude and temperature at the destination airport. To find the necessary adjustment values, use the existing pressure altitude and temperature conditions at flre destination airport as variables to find the time, distance and fuel values from the graph (Figure 5-25). Now, subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true time, distance and fuel values needed for the fligltt plan. The values obtained by proper utilization of the graphs for the descent segment of our example are shown below. (l) Time to Descend (6.5 min. minus 3.5 min.) (2) Distance to Descend (14 miles minus 7.5 miles) (3) Fuel to Descend (1.0 gal. minus.5 gal.) 3.0 min.* 6.5 miles* .5 gal.* REPORT: VB-880 5-5 Cnrisc Usipg the total distance to be traveled during the flight, subtract the previously calculated distance to climb and distance to descend to establish the total cruise distance. Refer to the äiiiiöpiirt" Ätaö tycominc Operator's Manual when sälecting the cruise power sctting. 'l'hc eitiUtisnea pressure altitude and temperature values and the selected cruise power should now be utilized to äetermine the true airspeed from the Cruise Performance graph (Figures 5-15 through s-l 8). Calculate the cruise fuel consumption for the cruise power setting from the information provided by the Avco Lycoming Operator's Manual. The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel consumption by the cruise time. The cruise calculations established for the cruise segment of our flight planning example are as follows: (l) Total Distance 300 miles (2) Cruise Distance (e)(l)minus (c)(4) minus (d)(2), (300 minus l0 mitei rninur O.S mifeil 283.5 miles (3) Cruise Power, Best Economy Mixture 757o rated power (2641-RIlv! i+l Cruise Speed ll8 KTS TAS** iSl Cruise Fuel Consumption 8'5 GPH (6) Cruise Time (eX2) divided by (cX4), (283.5 miles divided bv I l8 KTS) 2'40 hrs' (7) Cruise Fuel (e)(5) multiplied by (e)(6), (8.5 GPH multiplied bv 2.40 hrs') 20'4 gal' *reference Figure 5-25 *xreference Figure 5- I 7 ISSUED: DECEMBER 16, L976 REV I SED : l4/\Y 30, 1980 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORFORATION PA-28.161, CHEROKEE WARRIOR II (0 Total Flieht Time The total flight time is deternrined by adding the time to climb, the tinre to dcscend and the cnrise tinrc. Ilcnrenrbcr! Thc tinrc valucs takcn fronr thc clirnb attd dcscctrt graplrs arc itr ntil'ttttcs and must be converted to hours belbre atlding them to the cruise time. The following flieht time is required for our flieht planning example. (l) Total Flight Time (c)(3) plus (dxl) plus (e)(6), (.13 hrs. plus .05 hrs. plus 2.40 hrs.) 2.58 hrs. (g) Total Fuel Required Determine the total fuel required by adding the fuel to climb, the fuel to descend ancl the "- cruise fuel. When the total fuel (in gallons) is determined, multiply this value by 6 lb/gal to determine the total fuel weight used for the flight. The total fuel calculations for our example fliEht plan are shown below. (l) Total Fuel Required \--./ .(cX5) plus (d)(3) plus (e)(7), (1.5 gal. plus.5 gal. plus 20.4 gal.) 22.4 gal. (22.4 gal. multiplied by 6 lb/gal.) 134.4 lbs. \--/ REPORT: VB-880 5-6 ISSUED: DECEMBER 16, 1976 REVISED: JULY 3,1979 PIPffi AINCRÅFT C.gRFORÅTION P ll-z&.l 61, CHEROKEE ITARRIOR U SECTI§N 5 PERFORM.AI.ICE \-/ THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: DECEMBER 16, 1976 REPORT: VB€40 5-7 §tsgmoN 5 FER§CIAMÅT.ICE PITER AIRCRAF'T C{}RFO N.ÅTION. PA-2&151, CHEROKEE WARRIOR II "l' -THIS PAGE INTENTIONALLY LEFT BLANK 'v' \-/ , REPOBI: YB{80 $8 i ISSUED: DECEMBER 16, 1976 PIPER AIRCRAF-T CO RPORATION PA-28-161, CHEROKEE WARRIOR II SECTION 5 PERFORMANCE \-'' 5.7 PERFORMANCE GRAPHS LIST OF FIGURES Airspeed System Calibration Page No. 5-l I Stall Speed 5-12 Normal Short Field Ground Roll Distance - No Obstacle 5-13 Figure No. 5-l 5-3 5-5 5-6 5-7 5-8 5-9 5-l 0 5-l I 5-l 3 5-l 5 Obstacle Clearance Short Field Ground Roll Distance Obstacle Clearance Short Field Takeoff Distance Engine Performance (Serial Nos. 28-7716001 through 7716323) Engine Performance (Serial Nos. 28-78 16001 and up) Climb Performance Fuel, Time and Distance to Climb Best Power Cruise Performance (Serial Nos. 28-77 16001 through 7716323) 5-16 Best Power Cruise Performance (Serial Nos. 28-7816001 and up) 5-15 5- 16 5-t7 5-l 8 5- l9 5-20 5-21 s-22 5-17 Best Economy Cruise Performance (Serial Nos. 28-7716001 through 7716323) 5-23 5-18 Best Economy Cruise Performance (Serial Nos. 28-7816001 and up) 5-24 5-l 9 Best Power Mixture Range (Seriat Nos. 28-7716001 through 7716323) 5-25 5-20 Best Power Mixture Range (Serial Nos. 28-7816001 and up) 5-2(t 5-21 Best Economy Mixture Range (Serial Nos. 28-7716001 through 7716323) 5-27 , 5-22 Best Economy Mixture Range (Serial Nos. 28-7816001 and up) 5-28 \-' s-23 Endurance 5-29 5-25 Fuel, Time and Distance to Descend . . . 5-30 5-27 Glide Perforrnance 5-31 5-29 Landing Performance 5-32 ISSUED: DECEMBER 16, 1976 REVISED: JLJLY 11,1977 REPORT: Vl]-880 5-9 sEclIoN 5 PERFORMAITICE PIPER AIRCRAFT CT}BFO RATION PA.28-161, CIEROKEE WÅRRIOR II V THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-880 5-10 ISSUED: DECEMBER 16, 1976 \_-/ PIPER AIRCRAFT CORPORATION PA.28.1 6I,.CNTNOTEE WARRIOR II SECTION 5 PERFORMANCE PA-28-l 6I -l-|-t-l-l-l-.1-l i- l-l-l-l-+-,1 l-l-l-t l-l I I AORSPEED SYSTTåt}fl GALI]BRATI@N ffil H [D( ilD tt I ) tt TYIilG tl I TLAPI I 4 o 40 60 80 100 120 140 160 180 II{DICATED AIRSPEED . I(ilOTS AIRSPEED SY STEIT{ CALIBRATION Figure 5-l 180 r60 60 40 Srlt E r40 -, T GT lrl H l2o 3/t = EI l4l E loo e,CEl C,, 80 REPORT: VB-880 5-l I ISSUED: DECEMBER 16, 1976 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPO RATION PA.28.161, CHEROKEE WARRIOR II ltltttttI I l I-T-TTI STALL SPEED crLrshlrrnL lti n tntTFn TÅI I §PFFN §T I CpgFn tlrr lt 7 00 tt rLAP I { _l -''1 a ( 7 fi z7 I I 00 Fl I I .APS I I PA-29-I 6l 2400 2000 r 600 2400 2000 1000 0 20 {0 60 GROSS IYEIG1IT . tBS. A}IGLE OT BAilK . OEGREES Example: Gross weight: 2l70lbs. Angle of bank: 20' Flap position: 40o Stall speed, indicated: 44 KTS STALL SPEED Figure 5-3 80 70?D 00 q, a,rfi trt 50: - REPORT: VB-880 s-t2 ISSUED : DECEMBER 16, 197 6 PIPER AIRCRAFT CORPORATION PA.2&I6I, CHEROKEE I{ARRIOR tr SECTION 5 PERFORMANCE -{0 0 10 80 0F :rttt!:ttttrr. -10 -20 0 20 0c OUTSIDE AIR TEMP. PA.28.I 6I 2325 2200 2000 t800 tIEISHT.LBS. 2400 2200 2000 r800 1600 I 400 1200 r 000 800 600 400 200 0 oCE o -, oCE C5 o Ll - 1600 0 5 r0 15 wtlttl.t$s. Example: Departure airport presure altitude: lS00 ft. Deparhrre airport temperature: 80" F Weight: 2325lbs. Wind: l5 KTS headwind Ground roll: I150 ft. Lift-off speed: 50 KIAS ISSLJED: DECEMBER 16, 1976 REVISED: JULY lt,1977 NORMAL SHORT FrFLD GROT ND ROLL DI§ITANCE - NO OB§TACLE Figtre 5-5 REPORT: v8880 5-l 3 SECTION 5 PERFORMAI{CE PIPER AIRCRÅFT CORPORATION PA-2&161, CHEROKEE WAR&roR tr I _,N@RMAt r§ $hx»RT F]ELD TAffiE.OFFDIS ffi- - N@ OBSTAGTE + l,fNl plyEo, LEvEL, onv nurwlvI i i N. lt+ ttttl PottER BEtoRE BRAKE -ltL\Hr- RELEASE FTAPS 0o T AN]CE \ \ t\r \ \ \ /" /, i at\ t\ i) lr J § / :§fr + {-t\+ .-f t\ {eF#!* r' I l-Y \ Ä { I '.1[ r. I I 1.,. Nl N *.Xt -\ .\ §) € J\t/t I I J(T_T_ \ v tY I Y tt - YT\ - ;1 :+ \ \[: )-< rtttttitttll 50tT. EtRnttR sPtto.ills s!ii51 I 52 5.0 18 {f 41 T=i Lltl.lltt sPtE0.rn i{E 16 44 I 12 F T1 PA-28-I 6t -40 0 40 80 oF 232.5 2200 2000 1800 t600 0 5 l0 15 lllrrl'rr'rr'' i,'r' IYEIGHT.LBS.wlilo.l(Ts.-40 -20 tl 20 oC OUTSII}E AIR TEMP. Example: Departure airport pressur€ altitude: 1500 ft. Departure airport temperature: 80o F Iileight: 2325lbs. Wind: 15 KTS headwind Distance over 50 ft. barrier: 2100 ft. Liftoff speed: 50 KIAS Barrier speed: 55 KIAS NORMAL SHORT FIELD TAKEOFF DISTANCE. NO OBSTACLE Fieure 5-6 4000 3500 ISSUED: DECEMBER 16, 1976 REVI§ED: JULY ll,1977 j +CE lra 3000 = 4 EI j 2500 E e >e Ll 2000 = ?et r500 ?t, -< 1 000 500 REFORT: rrB-880 tl4 PIPER AIRCRAFT CORPORATION PA.2&I61, CIIEROKEE WARRIOR II SECTION 5 PERFORMANCE PA.28.I 6I OBSTAGI GB( ll,l:ll:l:l PAYED, LEYEI, IIRY RUIIITAY I i - tutL P0WER BEF0RE ERAl(t RELEi _flÅp§r50_L liLi L,l CLEå\RAN( UND EOLL : tE slt@RT D]STANGE ,F] 0.Ins .tl I SPIE t.l : -t I lr i - I _J_ I l+ I -+ lilil li !r, i {öll {u lllt lr-zl i ,4 X/ n \l' x \ '-1, r§Y \ tl t \vl -/ \l x,/ V l\ § ,L I i,, .4 \ \ \ l\ -r v I iz ^]'* t t. , '\l v) :-! \ F*§iT L\ YiV .-I \ _2?V) Yl ,'/--S) Yl A la{ Vffi \ l= -+\ \i -> 4?\ - \- \r \ -\; -'r- - -'N ,/ ,.{ V 1.2 1 I \ \.1 \ -\ -»< -F- -, I i I ]-\ xI I -1'- l- >\-L 4 \l -40 0 {0 80 oF 2325 2200 2000 '1800 1600 0 5 l0 15 .rrrrlrirrllr -io ' -io ' ä ' io oC WEIGHT'LBS. IYlll0'KTS' \-. OUTSIOE AIR TEMP. Example: Deparhrre airport pressure altitude: 1500 ft. \v' Departure airport temperahrre: 80'F rfeight: 2l75lbs. Wind: 15 KTS headwind Ground roll: 975 ft. Lift-off speed: 48 KIAS OB§TACLE CLEARANCE SIIORT FIELD GROUND ROLL DISTANCE Fieure 5-7 2400 2200 2000 F 1800 : e 1600 4 e! -1400 =e(9 1200 rr ? 1000 = 800 600 400 ISSLJED: DECEMBER 16, 1976 REYI§ED: JULY ll,1977 REPORT: VB-880 5-1s SECTION 5 PERFOR}TAI{CE PIPER AIRCRAFT CORPORATION P4.28.I61. CHEROKEE I{ARRIOR II OBSTACTE CLEAI :TAKE-OFF D]STA lilililrti IAN]G Sh]@RT F]ELD NqB lti rtittttll PAYED, LEVET, IIRY RUIIITAYI I + RAKE RELI ltr :ASE N/ i\ i FUIL P0IIER BEF0RE E h l rrlrrt. nEol I I Xr § I\ L .! !§ i\ ',r^,r: r: I I I i f T Xr \ \ \ I -it u I i x. \ I J- { \ \ \l .l r§ ...i t\ \l I x.,{ \ \ \i :TTt I l_ tY l,/ | .l\ v§,l r .4\ lt t\ \ § i/ \ »r \ r' 7A \ I I "/l: ffi lt r.i k -l- Js I 1_[ -. 1 =1 -, J !§t I \ '/i It El \.1 \ 't/ ,4 rlrl { I -t- I I I I P 50 I. BARNER SPEI t.lilA 55.5.{ 52 I 5.0 l, { Lö 44 I trt.ort sPtED.l(tAs sh l' 18 16 1t t7 0 :.-l PA-29-I 6t -40 0 40 80 oF 2325 220{ 2000 t800 1600 0 5 l0 t5 -40 -20 0 is "C WtlGllT-tBS. Wlll0- l$S. OUT§IDE AIR TEMP. 4 000 3500 r 000 ISSUED: DECEMBER 16, 1976 REYISED: JULY ll,1977 j + 3000 E e OE CE! ; 2500 EIJ':' CE o 2000 ä -, an et 1500 E ?l*l - 500 Example: Departurö airport pressure altitude: 1500 ft. Departure airport temperature: 8f F Weight: 2175lbs. Wind: 15 KTS headwind Distance over 50 ft. barrier: 1600 ft. Uft-off speed: 48 KIAS Barrier speed: 53 KIAS REPORT: vB-880 5-16 OBSTACLE CLEARÅNCE STIORT FIELD TAKEOFF DISTANCE Figure 5-8 PIPER AIRCRAFT CORPORATION PA.28.I61, CIIEROKEE WARRIOR II SECTION 5 PERFORMANCE PA-28.I 6I -20 0 20 40 60 80 100 oF 220s 2300 2400 2500 2680 2700 tlrttlr _2h I d , 2,0 r 4,0 "c ENGII{E RPtl OUTSIDE AIR TEMP. Example: L . Cruise pressure altitude: 5000 ft.v Cruise OAT: 60" F Cruise power: 75% Engine RPM: 2645 ISSUED: DECEMBER 16, 1976 ITEVISED: JULY 11,1977 ENGINE PERFORMANCE (SERTAL NOS. 2&7716001 THROUGH 7716323\ Figure 5-9 REPORT: VB-880 5-17 +GROSS lfr !WI L ; l- :IG I t- IT 7/ r-l 23i 1 E !N LI L !i-- GtlNJE PERFORTMANIGIE- IS., BEST P(lWER MIXTURE PER TYC(}MI l-wnrn tAlnrilGs rNsTAuEö ffi Hl il iH-+Fl+i+ |{G - !tl IuL- RU E cl :- t-- I0r I§ 7 4 t/t Å § / ,1 / / []a.,V 14- -l 7 +11 ll <, -ILd I 7 I ot I 011 ER - I 5 B5 - 75 L?_,lla ,1, \7id- Y-\z /§ 7 7 / a §:)\ 7 J § ",/ / l.\9 /l-.--/ \ *Y / /t SECTION 5 PERFORMANCE PIPER AIRCRAFT CO RPORATION PA.28.16I, CHEROKEE WARRIOR II PA.28.I6I ffi F,T,$[$,F P-1$-E 9,P m,fl-tr -Pol{tR %P0IIER tc0t{0flY- lilsTRu8Tl0t{§ cR0ss wElGilT. 23 -t 7.8 --l o.s _.] r o.o 55% E5o/" 6.6 I}ISTATIED i:ts _ wHEEt t 15% 8.5 I I I r t-I t-t- 2f? =l5- t-[B- +-f I7) \1* 7 C\§ §}Z § r/lS v^*v tt IA aK- 'ss,, \r -evP\ 7a\ -l -l __.1 -l -..l - v* + -- 5l rF W i% t-- l= -€ /§ r:7r ,(: \,r,t r I I t/l A wY VT lt I I I -20 0 20 {0 60 80 100 ot, 2200 ,2300 2100 2500 2600 2700 o 'c RPit OUTSIDE AIR TEMP. Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60'F Cruise power 75% Engine RPM: 2620 ENGTNE PERFORMANCE (SERIAL NOS. 28-7816001 AND UP) ,E"GVE Figure 5-10 REPORT: VB-880 5-1 8 ISSUED: DECEMBER 16, 1976 REVISED: JULY ll,1977 PIPER AIRCRÅFT CORPORATION PA.2&161, CIIEROKEE }VARRIOR tr SECTION 5 PERFORMANCE -20 0 20 10 00 80 100 -20 0 20 10 OUISIBE AIR TEITP. Example: Climb pressure altitude: 5000 ft. Climb OAT: 60'F Rate of climb: 420 ftlmin. ISSUED: DECEMBER 16, 1976 REVISED: ILJNE 30, 1978 PA-28.I 6I 200 RATE OT CLIMB PERFORIT{A}.ICE Fieure 5-l I oI oc 100 cLfttB . 600 tPtt REPORT: vB-880 5-19 GLIMB PERF@RMANCE GR0SS WEtGttI 2325 tBS., tutt THR0TTIE [EAI{ MIXIURE PER LYCOilIIIIG I}ISTRUCTIOIIS s{ sERm ilumtns 28-7El§001 lflolP, mm[ uE 0r cUtB 8I 10 rPr wHor Ilf, TilE. FINilS ART RTTOYE!! SECTION 5 PERFORMAI.ICE PIPER AIRCRAFT CORPORATION PA.2&I6 I, CITEROKEE WAF§IOR II FUEL. TIME AND DISTANCE TO CLIMB WEIGHT 2325 LBS., FLAPS 0", FULL THROTTLE j-H M r xr u R E - L EA N7E Df E 3, .^I3 ir^l§ I N srR u cfl o * r ++ @.1 iOI Lh' [e h.9 J»ry i) rn :! ,. L* I PA -29- 1 61 .20 0 20 40 60 80 100 0 10 20 30 40 50 c -2O -1O O 10 20 30 40 OUTSIDE AIR TEMPERATURE Example: Departure airport pressure altitude: 1500 ft. Departure airport temperature: 80ö F (27"C) Cruise pressure altitude: 5000 ft. Cruise OAT: 60'F (16oC) Time to climb (10 min. minus 2.5 min.): 7.5 min. Distance to climb (13.5 miles minus 3.5 miles): l0 nautical miles Fuel to climb (2 gal. minus .5 gal.): 1.5 gal. FUEL, TIMEAI.ID DISTANCE TO CLIMB Fieure 5-13 FUEL, TIME AND DISTANCE TO CLIMB REFORT: VB€80 5-20 ISSUED: DECEMBER 16, 1976 REVISED: JULY 3,1979 PIPER AIRCRAFT CORPORATION PA.2&I6I, CHEROKEE WARRJOR tr SECTION 5 PERFORMANCE E§T P@WER GRUISE PERFORMANGE GROSS IIEIGHT 2325 TBS. WHEET FAIRI}IGS TNSTAIIED BEST POWER MIXTURE PER LYCOMIIIG LEAIIING IIISTRUCTIOI{S tUEL C0l{SutlPTl0ll 757o = 10.0 8PH 65% = 8.8 GPH 55% = 7.8 GPll r+)-§4 6* PA-28.I 6I -20 0 20 {0 60 80 t00 0F +ffi'C 0UTSI0E AIR TEilP. TRUE AIRSPEED . IfiS II(ITE: SUBTRTCT 2I(TS. T UHTET Flnil8s AnE il(ll ilsTAu.E0. Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60'F Cruise power: TSVob«it powef, mixture Cruise speed: 116.5 KTS TAS ISSUED: DECEMBER 16, 1976 REVISED: ruLY ll,1977 BEST POWER CRUISE PERFORMAI{CE (SERIAL NOS. 2&77 r 6001 THROUGH 7 7 t 63231 Figure 5-i5 REPORT: VB-880 5-21 SECTION 5 PERFORMAI{CE PIPER AIRCRAFT CO RPORATION PA.2&I6I, CHEROKEE WARRIOR tr BEST POW,Ets GRU]SE PERF GROSS WEIGHT 232 IIHEtt FA|RN0S HStAttEIt EEST POIYER IilIXTURE PIR LYC0MrflG LEAilHG ilSTRUCT0ilS r,,.J. l^.,r..,].-.1.^.1 I I I I I I 75% = 10.0 BPH.I 65% = 8.8 EPH PA-28-I 6t -20 0 20 10 60 80 r00 -20 0 20 40 oc (lUTSIIlE AIR TEMP. Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 60'F Cruise power: T1Vobest power mixture Cruise speed: 122.5 KTS TAS TRUE AIRSPEED I$S. ll0Tt: SUBTRICT 7 l(TS. r WHtEt ilrRilr0s AnE ilol rilsTrlL$. BEST POWER CRI.IISE PERFORMAI.{CE (SERIAL NOS. 28.781600I AND UP) Figure 5-16 5V-Lv€ REPORT: 5-22 ISSUED: DECEMBER 16, 1976 REVISED: JULY ll,1977 vB-880 PIPER AIRCRAF'T CORPORATION PA-28-I61, CHEROKEE WARRIOR II SECTION 5 PERFORMANCE PA-28-l 6I -20 0 20 40 60 80 100 oF 80 90 100 n0 120 "c TRUE AIRSPEEI}-KTS. -20 0 20 40 "u il,Tt: suBTRAcT zt(Ts. tr wilEEL 0UTSI[)E AIR TEMP. rAntltcs ARr toT r{sTArLrD. Example: \--l Cruise pressure altitude: 5000 ft. Cruise OAT: 60'F Cruise power: 71%best economy mixture Cruise speed: 112.5 KTS TAS ISSUED: DECEII{BER 16, 1976 REVISED: JULY ll,1977 BEST ECONOMY CRUISE PERFORMAI\CE (SERIALNOS. 28-7716001 THROUGH 7716323) Figure 5-17 REPORT: VB-880 5-23 BEST EG@N@[V]V CRUISIE PIERIFOR MIAINGE l]-_L Gnoss wETGttT z3z5 rBs., vlnrEr rAtntilGs tilsTArrED - -BEST ECOI{OMY MIXTURE PER TYCOMING IEAI{ING IilSTRUCTIONS - \- tutl c0t{suMPTrl)}t 75% = 8.5 0PH 65% = 7.5 GPH 55% = 6.6 GPH 7a 7 § '-f, 1- rPL lä/t\1-ll€ fr9- l-\zl {* V 55 I 5 I 75 tt% Pt]t{ R + 4o§,^ fd l lI fl/1 v* §) 7 I I I § v: P /l,raY I-\-/T- s/l L \, il)_ SECTION 5 PERFORMAT.{CE PIPER AIRCRAFT CORPO RATION PA:28.161; CHEROKEE WARRIOR II {* BEST EG@N@0,{ VGR UJ IISE puinrom {14 t'te E IEST EC0il0MY ilIIXTURE PER tY LEAI{tilG tilsnucTttlils-l--J_]_.] ER0SS WETG}IT 2325 LB.# IYHEEL TATRTNGS rlrsTALrEo -l c0Mil #II§ 7 4A +\ "/ r- 7 7 rV ls{ ^e7 l:utl c0t{su}tPTrolt _15% = g.S ePfi -65% = l.S ePrl 55% = 6.6 GPH a--lz- I 1l ssl 1 I 6o, §r + { + 4: I t I I l'fr rVl PA-28-l 6I 100 ot 4'o oC -20 0 -20 r00 g0 20 40 60 80 fl0 I 20 130 TRUE AIRSPEED I(TS. il0Tt: SUBTRACT 7 l(TS. lF IYHEET rArRffiGS ARt ll0T lllsTAu.tll. 0 ()UTSIDE 20 AIR TEMP. Example: Cruise pressure altitude: 5000 ft. Cruisc OAT: 60'F Cruise power: 757obest power mixture Cruise speed: I 18 KTS TAS REPORT: VB-880 s-24 BEST ECONOMY CRUISE PERFORMANCE (SERIAL NOS. 28-7816001 AND UP) 5€ 6vG Figure 5- 18 ISSUED : DECEMBER 16, 197 6 REVISED: JULY ll,1977 PIPER AIRCRAFT CORPORATION P4.28.161, CHEROKEE WARRIOR tI SECTION 5 PERFORMANCE PA-29-161 Example: Cruise pressure altitude: 5000 ft. Cruise OAT: l6oC (l l"C above standard) Cruise power: 75Vo best power mixture Range w/45 min. reserve @ 55Vo power: 476+(.6 x I l) =482.6 nauticalmiles Range w/no reserve:533 + (.6 x ll) = 539.6 nautical miles 440 460 480 500 520 540 500 520 540 560 580 600 RANGE _ NAUTICAL MILES (INCLUDES DISTANCE TO CLIMB AND DESCEND) 28-7 7 l6OOl THROUGH 7 7 | 6323) BEST POWER MIXTURE RANGE (§ERIAL NOS. Figure 5-19 ISSUED: DECEMBER 16, 1976 REVISED: JULY 3,1979 REPORT: VB-880 5-2s BEST POWER MIXTURE RANGE (MIXTUBE LEANED PER LYCOMING INSTRUCTIONS) GROSS WEIGHT 2325 LBS.. NO WIND 48 GAL. USABLE FUEL 45 MIN, RESERVE @s5% POWEB BEST ECONOMY MIXTUBE ADD ,6 NAUTICAL MILES FOR EACH DEGREE CENTIGRADE AEOVE STANDARD TEMP- ERATURE AND SUBTRACT 1 NAUTICAL MILE FOB EACH DEGREE CENTIGBADE BELOW STANDARD TEMP- ERATURE. NOTE BANGE MAY BE FEDUCED BY UP TO 2% IF WHEET FAIBTNGS ARE NOT INSTAL. SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPO RATION PA-28.I6I, CHEROKEE WARRIOR U PA-29-161 BEST POWER MIXTURE RANGE (MIXTUBE LEANED PER LYCOMING INSTRUCTIONS) GROSS WEIGHT 2325 LBS., NO WIND 48 GAL. USUABLE FUEL, WHEEL FAIRTNGS INSTALLED @55% POWER BEST ECONOMY MIXTURE BANGE MAY BE REOUCEO 8Y UP TO 7 % IF WHEEI FAIR]NGS ABE NOT INSTAL. ADD .O NAUTICAL MILE FOR EACH DEGREE CENTIGRADE ABOVE STANOABD TEMP- ERATURE AND SUBTRACT 1 NAUTICAL MILE FOR EACH DEGREE CENTIGRAOE BELOW STANDARO TEMP- 460 480 500 520 540 560 520 540 560 580 600 620 BANGE _ NAUTICAL MILES (INCLUDES DISTANCE TO CLIMB AND DESCEND) Example: Cruise pressure altitude: 5000 ft. Cruise OAT: l6"C (ll"C above standard) Cruise power: 757o best power mixture Range w/45 min. reserve @ 55Vo power: 501 + (.6 x ll) = 507.6 nautical miles Range w/no reserve:561 + (.6 x lll = 567.U nautical miles. BEST POWER MD(TURE RANGE (SERIAL NOS. 2&7816001 AND. UP) Figure 5-20 REPORT: VB-880 s-26 ISSUED: DECEMBER 16, 1976 REVISED: MAY 30, 1980 PIPER AIRCRAF'T CORPORATION PA.28.I61, CHEROKEE IryARRIOR tr SECTION 5 PERFORMANCE BEST ECONOMY MIXTURE RANGE {MIXTUBE LEANED PER LYCOMING INSTRUCTIONS) GROSS WEIGHT 2325 LBS., NO WIND GAL. USABLE FUEL. WHEEL FAIRINGS IN 48 GAL. USABLE FUEL. WHEEL FAIRINGS INSTALLED NO RESERVE 45 MIN. RESERVE NOTE RANGE MAY BE BEDUCED BY UP TO 2% IF WHEET FAIBINGS AFE NOT INSTAL- LED. NOTE: ADD .7 NAUTICAL MILE FOB EACH DEGBEE CENTIGBADE ABOVE STANDABD TEMP- ERATURE AND SUBTRACT 1.1 NAUTICAL MILE§ FOB EACH DEGREE CENTIGBADE BELOW STANDABD TEMP. ERATURE SEA LEVEL RANGE _ NAUTICAL MILES (INCLUDES DISTANCE TO CLIMB AND DESCEND) \ Example: Cruise pressure altitude: 5000 ft. Cruise OAT: l6"C (lloC above standard) Cruise power: 7 570 best economy mixture Range w/45 min. reserve @ 55Vo power: 540 + (.7 x I l) = 547 .7 nautical miles Range w/no reserve:602 + (.7 x ll) = 699.7 nautical miles ISSUED: JULY ll,1977 REVISED: JULY 3,1979 BEST ECONOMY MD(TURE RANGE (SERIAL NOS. 28-7716001 TTIROUGH 7716323) REPORT: VB8B0 5-27 Figure 5-21 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA.28.16I, CHEROKEE WARRIOR II PA-28-161 520 540 560 580 600 620 600 620 640 660 680 700 RANGE - NAUTICAL MILES (INCLUDES DISTANCE TO CLIMB AND DESCEND) .t Example: Cruise pressure altitude: 5000 ft. Cruise OAT: 16"C (ll"C above standard) Cruise power: 75%obest economy mixture Range wi 45 min. reserve @ 55Vo power: 567 +(.7 x I l) = 574.7 nauticalmiles Range w/ no reserve: 635 + (.7 x ll\ = 642., nautical miles REFORT: VB-880 5-28 BEST ECONOIT{Y MIXTURE RANGE (SERIAL NOS. 28-7816001 AND UP) Figure 5-22 ISSUED: JULY ll' 1977 RBVISED: JULY 3,1979 BEST ECONOMY MIXTURE RANGE (MIXTURE LEANED PER LYCOMING INSTRUCTIONS) GROSS WEIGHT 2325 LBS., NO WIND 48 GAL USUABLE FUEL, WHEEL FAIRINGS INSTALLED NO RESERVE AT 55% POWER BANGE MAY BE REOUCED BY UP TO 7% IF WHEET FAIRINGS ARE NOT INSTAL. NOTE ADD .7 NAUTICAL MILE FOR EACH DEGREE CENTIGRADE ABOVE STANDABO TEMPER- ATUBE AND SUBTRACT 1.1 NAUTICAL MILES FOR EACH DEGREE CENTTGRADE BELOW STANDARD TEMPER. PIPER AIRSRAF-T CORPORATION PA.28.161, CHEROKEE WARRIOR tr SECTION 5 PERFORMANCE F]I- I IJJ o f F F UJ E f o oIJJ E o- SEA LEVEL ISSUED: JULY ll,1977 REVISED: JULY 3,1979 PA-28-161 ENDURANCE - HOUBS (TNCLUDES TIME TO CLIMB & DESCEND) ENDURANCE Figure 5-23 Example: Cruise pressure altitude: 5000 ft. Cruise power: 7570 best economy mixture Endurance w/45 min. reserve @ 5570 power: 4.85 hrs. Endurance w/no reserve: 5.45 hrs. REPORT: VB-880 5-29 ENDURANCE BEST ECONOMY MIXTURE PER LYCOMING INSTRUCTIONS . 48 GALLONS USEABLE FUEL NO RESERVE 45 MIN. RESER AT 55% POWER :S+-;s lol lo iri SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPO RATION PA.28.I61, CHEROKEE WARRIOR II FUEL TIMI llltrtt : AND DISTANCE TO -_tttl DEI ll S c E ND_ tLl lllllll I I t<i,\,L,nrrualaol\!ADI I I I I I I r r rrarrrrrrn I I I I I I ll tLttttttt I I I I t':-,"I"i-t I I I I I tt +, lu, --+F J3/ -§l -ll- EF *l_ \t\ z -o H# §;N _l _ Lr.t )_tt FF N9 \gri.: +-'§, tl PA-29-161 -20 0 20 40 60 80 100 .F 0102030 FUEL, TIME DISTANCE TO DESCEND -20 -10 0 10 20 30 40 "c OUTSIDE AIR TEMP. Example: Destination airport pressure altitude: 2500 ft. Destination airport temperature: 75oF (24oC) Cruise pressure altitude: 5000 ft. Cruise OAT: 60"F (l6oc) -J Time to descend (6.5 min. minus 3.5 min.): 3 min. Distance to descend (14 miles minus 7.5 miles): 6.5 nautical miles Fuel to descend: (l gal. minus .5 gal.): .5 gal. FUEL, TIME AND DISTANCE TO DESCEND Figure 5-25 REPORT: VB-880 5-30 ISSUED: JULY ll,1977 RBVISED: JULY 3, 1979 PIPER AIRCRAFT CORPORATION P4.28.I61, CHEROKEE WARRIOR U SECTION 5 PERFORMANCE I 2000 1 1000 1 0000 9000 8000 7000 5000 5000 4000 3000 2000 1000 FIL I ul o :) F F Lu G f oU' uJ IE Å PA-28-161 GLIDE PERFORMANCE WEIGHT 2325 LBS. PROP WINDMILLING -rT-rr, F $ q s_ 9". -ry-o-Yr T D, -rTl-r TTTTTT-T /r l\'rA§ rrl_rT-l--r o5101520 GLIDE RANGE _ NAUTICAL MILES SEA LEVEL Example: Cruisc prcssurc altitudc: 5000 ft. Terrain pressure altitude: 2000 ft. Glide distance (9.5 miles minus 3.8 miles): 5.7 nautical miles GLIDE PERFORMANCE Fieure 5-27 ISSUED: JULY ll,1977 REVISED: JULY 3,1979 REPORT: VE8B0 5-31 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA.28-161, CHEROKEE WARRIOR IT llllllllllllllrr ILAIN D tl INIG IPIE RF@ tE IMIA tNG tT GR()SS Y{EIGHT 2325 TBS., POWER (tTT, FLAPS . 40' PAVEtt TEYEL DRY'RUI{WAY, MAXIMUM BRAI(I]IG APPR()ACH SPEED 63 I(IAS TUIL STATL T(IUCH I}()Wil rtritttttlltlrlllllll --l I-(§ .J, x 7 -l ,1 ,4 Ä) t\ I )I I5 I(TS HEADWITID \ llu lt lllu - 5 I(TS TAIL WI]ID c7 v IIIII GR(}Uill} RI}LL _ I 0Yt tttl R 50 FT. BARR ER z{ -s iP -) 'a I /_ T" ) 7 I I II Y 1 I I I t |- 7 7 ll*7 I II I I slc"i{r I PA-28-I 6I -20 0 20 40 60 80 100 oF 400 600 800 t000 1200 1400 ,rrllll -2b I ö '' 2'0 | 4'0 oC LANDTNG I}ISTAN0E ' FEET OUTSIOE AIR TEMP. Example: Dcstirratiort airport prcssurc altitutlc: 2500 ft. Destination airport temperature: 75"F Destination airport wind: 0 KTS Ground roll: 660 ft. Distance over 50 ft. barrier: I190 ft. LANDING PERFORMANCE Figure 5-29 REPORT: VB-880 5;32 ISSUED: JULY ll,1977

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