table of contents performance - flyforreal.com

Paragraph No.

TABLE OF CONTENTS

SECTION 5

PERFORMANCE

Page No.

5.1 General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5 .3 Introduction to Performance and Flight Planning . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 5.5 Flight Planning Example . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3 5.7 Performance Graphs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9

List of Figures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-9

REPORT: VB-790 5-i

PIPER AIRCRAFT CORPORATION PA-28-181, CHEROKEE ARCHER II

5.1 GENERAL

SECTION 5

PERFORMANCE

SECTION 5 PERFORMANCE

All of the required (FAA regulations) and complementary performance information applicable to the Cherokee Archer II 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 PLANNING

The performance information presented in this section is based on measured Flight Test Data corrected to 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 performance. Endurance can be grossly affected by improper leaning procedures, and inflight fuel flow and quantity checks are recommended.

REMEMBER! To get chart performance, follow the chart procedures.

The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using the performance charts in this section. Each chart includes its own example to show how it is used.

ISSUED: JUNE 18, 1976 REPORT: VB-790 5-1

SECTIONS PERFORMANCE

REPORT: VB-790 S-2


THIS PAGE INTENTIONALLY LEFT BLANK

ISSUED: JUNE 18, 1976

''----..-/


5.5 FLIGHT PLANNING EXAMPLE

(a) Aircraft Loading


The first 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 empty weight of the airplane.

Make use of the Weight and Balance Loading Form(Figure 6-11) 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.

The landing weight cannot be determined until the weight of the fuel to be used has been established [Jefer to item (g)( l)].

(1) Basic Empty Weight 1400 lbs. (2) Occupants (2 x 170 lbs) 340 lbs. (3) Baggage and Cargo 360 lbs. (4) Fuel (6 lb/gal x 50) 300 lbs. (5) Takeoff Weight 2400 lbs. (6) Landing Weight

( a)(5) minus (g)(l ), (2400 lbs. minus 136 lbs.) 2264 lbs.

Our takeoff weight is below the maximum of 2550 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 (Figure 5-5 or 5-7) to determine the length of runway necessary 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: JUNE 18, 1976 REPORT: VB-790 5-3



The conditions and calculations for our example flight are listed below. The takeoff and landing distances required for our example flight have fallen well below the available runway lengths.

( 1) Pressure Altitude (2) Temperature (3) Wind Component ( 4) Runway Length Available (5) Runway Required

NOTE

Departure Airport

2000 ft. 70°F

10 KTS 7000 ft. 950 ft.*

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

Destination Airport

2300 ft. 70°F

5 KTS 4500 ft.

825**

The next step in our flight plan is to determine the necessary climb segment components.

The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the Time, , __ / Distance, and Fuel to Climb graph (Figure 5-15). After the time, distance and fuel for the cruise pressure altitude and outside air temperature values have been established, apply the existing conditions at the departure field to the graph (Figure 5-15). Now, subtract the values obtained from the graph for the field of departure conditions from those for the cruise pressure altitude.

The remaining 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 our flight planning example.

(1) (2) (3) (4) (5)

Cruise Pressure Altitude Cruise OAT Time to Climb ( 12.5 min. minus 4.5 min.) Distance to Climb (17.5 minus 6.5 nautical miles) Fuel to Climb (3 gal. minus 1 gal.)

*reference Figure 5-11 **reference Figure 5-35

***reference Figure 5-15

REPORT: VB-790 5-4

6000 ft. 55°F

8 min.*** 11 nautical miles***

2 gal.***

ISSUED: JUNE 18, 1976 REVISED: JANUARY 20, 1977

.~.


(d) Descent


The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance.

Utilizing the cruise pressure altitude and OAT we determine the basic time, distance and fuel for descent (Figure 5-29). 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 the destination airport as variables to find the time, distance and fuel values from the graph (Figure 5-29). 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 flight plan.

The values obtained by proper utilization of the graphs for the descent segment of our example are shown below.

(1) Time to Descend (17 min. minus 10.5 min.) (2) Distance to Descend (35 minus 22 nautical miles) ( 3) Fuel to Descend (1. 7 gal. min us 1 gal.)

(e) Cruise

6.5 min.* 13 nautical miles*

. 7 gal.*

Using 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 appropriate Avco Lycoming Operator's Manual when selecting the cruise power setting. The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the appropriate Speed Power graph (Figure 5-19 or 5-21).

Calculate the cruise fuel flow 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 flow by the cruise time.

The cruise calculations established for the cruise segment of our flight planning example are as follows:

( 1) Total Distance (2) Cruise Distance

(e)(l) minus (c)(4) minus (d)(2), (314 minus 11minus13) (3) Cruise Power ( 4) Cruise Speed (5) Cruise Fuel Consumption ( 6) Cruise Time

(e)(2) divided by (e)(4), (290 nautical miles divided by 110 KTS) (7) Cruise Fuel

(e)(5) multiplied by (e)(6),(7.6 GPH multiplied by 2.64 hrs.)

314 nautical miles

290 nautical miles 65% r~ted power

110 KTS TAS** 7.6 GPH

2.64 hrs.

20 gal.

~ *reference Figure 5-29 **reference Figure 5-21

ISSUED: JUNE 18, 1976 REVISED: JULY 3, 1978

REPORT: VB-790 5-5

SF.cTION 5 PERFORMANCE

PIPER AIRCRAFT CORPORATION PA-2~181, CHEROKEE ARCHER II

(t) Total Flight Time

The total flight time is determined by adding the time to climb, the time to descend and the cruise time. Remember! The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time.

The following flight time is required for our flight planning example. (1) Total Flight Time

(c)(3) plus (d)(l) plus (e)(6), (.13 hrs. plus .11 hrs. plus 2.64 hrs.)

(g) Total Fuel Required

2.88 hrs.

Determine the total fuel required by adding the fuel to climb, the fuel to descend and 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 flight plan are shown below. ( 1) Total Fuel Required

(c)(S) plus (d)(3) plus (e)(7), (2 gal. plus . 7 gal. plus 20 gal.) (22.7 gal. multiplied by 6 lb/gal.)

22.7 gal. 136 lbs.

REPORT: VB-790 5-6

ISSUED: JUNE 18, 1976 REVISED: JANUARY 20, 1977

~···.·

PIPER AIRCRAFr CORPORATION PA-28-181, CHEROKEE ARCHER II

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--- ------- ------


REPORT: VB-790 5-7

,,..--.-' '

SF.cTION S PERFORMANCE

REPORT: VB-790 5-8


THIS PAGE INTENTIONALLY LEFr BLANK


.. ,_.,

.·~


5.7 PERFORMANCE GRAPHS

Figure No.

5-1 5-3 5-5 5-7 5-9 5-11 5-13 5-15 5-17 5-18 5-19 5-20 5-21 5-22 5-23 5-24 5-25 5-26 5-27 5-29 5-31 5-33 5-35

Airspeed System Calibration Stall Speeds . . . . . . . . . . . Flaps Up Takeoff Performance 25° Flaps Takeoff Performance . Flaps Up Takeoff Ground Roll .

LIST OF FIGURES

25 ° Flaps Takeoff Ground Roll .. . Climb Performance ......... . Time, Distance and Fuel to Climb . Engine Performance (Serial Nos. 28-7790001 through 7790607) Engine Performance (Serial Nos. 28-7890001 and up) . . . . . . . . . . ..... Speed Power - Performance Cruise (Serial Nos. 28-7790001 through 7790607) Speed Power - Performance Cruise (Serial Nos. 28-7890001 and up) ...... . Speed Power - Economy Cruise (Serial Nos. 28-7790001 through 7790607) Speed Power - Economy Cruise (Serial Nos. 28-7890001 and up) . . . . . Best Power Mixture Range (Serial Nos. 28-7790001 through 7790607) .. Best Power Mixture Range (Serial Nos. 28-7890001 anr:1 up) ....... . Best Economy Mixture Range (Serial Nos. 28-7790001 through 7790607) Best Economy Mixture Range (Serial Nos. 28-7890001 and up) ..... . Endurance ............... . Time, Distance and Fuel to Descend Glide Range . . . . . . . . . . . . Landing Performance . . . . . . Landing Ground Roll . . . . . . .



Page No.

5-11 5-12 5-13 5-14 5-15 5-16 5-17 5-18 5-19 5-20 5-21 5-22 5-23 5-24 5-25 5-26 5-27 5-28 5-29 5-30 5-31 5-32 5-33

REPORT: VB-790 5-9


REPORT: VB-790 5-10



1SSUED: JUNE 18, 1976

PIPER AffiCRAFf CORPORATION PA-28-181, CHEROKEE ARCHER II

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KIAS ..... NO INSTRUMENT ERROR


AIRSPEED SYSTEM CALIBRATION

Figure 5-1

REPORT: VB-790 5-11


PA-28-181 ~~~[!.[!. ~[p~~@~

POWER OFF 0° FLAPS

--- 25° FLAPS --- - 40° FLAPS

MAX. GR. WT. 2550 LBS.

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WEIGHT - 100 LBS.

Example: Gross weight: 2300 lbs. Angle of bank: 20° Flap position: 25 ° Stall speed: 46 knots (*indicated airspeed)

*INDICATED AIRSPEED, NO INDICATOR ERROR

REPORT: VB-790 5-12

STALL SPEEDS

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-40 0 40 80 2550 2450 2350 2250 2150 OUTSIDE AIR TEMP. • °F I I I I I I I I I I I I I I

-40 -20 0 20 OUTSIDE AIR TEMP .• °C

GROSS WEIGHT • LBS.

Example: Departure airport pressure altitude: 2000 ft. Temperature: 70°F Gross weight: 2400 lbs. Wind: 10 knots (headwind) Takeoff ground roll: 950 ft.

(

- - .... ,,, :z: ::::; ,, .... c.:»

I "\.. :z: ,__ - .... ao: , .... "'~ .... ... 1/~ - - ao:

= fl,~' :z: ,~, 11: ,,

J ..........

-..... r---... ' i

"' "' !"\.. ' '' ...

""

'

2400

2200

2000 t;;

1800 I.a.I .... ::I

1600 ~

!ii! -... ....... ....... l .......

-..!l'-ib"~ 1400 ; -

~

i--

.... --~"

I _::ij;I ... . --~ ... ~ 1200 - 17' ......... ...... ---- I

,.,. ~· f-.

1000

....... I""-.

~' -......... 800

- ,·· ~r---.

L 600 -- ....._.

-"""" ... 2i50 I . ·1 1400

0 5 10 15

WIND • KNOTS

.... .... a3 :.:::: c ......

(

~~ ~~ ~Ch

Q

~ .,, N~ qo := ~ i!: n~ =:= ~~ o~

~8

~a as t!j .... ~o =z



PA-28-181 I/ VI v v /

I VI~~ !/ I/ / II' /\ "'J ) / I

v I/ \ ~ J ~ ~" J ~-J J

I/ V1 I/ / .r / I/

J I/ v~ ~~ v II' I ) ~- ~~ v / ~

/ I v q_~~ / /

v II' J '\ )( J I ,. v / \ v ~J , " JV J

~~/ J / 1/1 v v II' I / / / v /

I/ I ~ L I/ I/ v / I a~~/ / /

v / • ~~C'S

) I ~ ~/ J / V~\/ , I/ v

II' J J iJ1 v v v ,, I J /~/ v ,

v / C'S

/ I/ J ) I "'Y I/ / ,v \1 ) /

/ / / I\ v I ,, J / / \ /~~ './ v ,

I J LJi "-Y- v. , - ....... ..__ -I / J J i/ / / / v ,

J \ /~~ J

J / v I \J ~ .,.,

I / 1/ ~ ~ I J J .I/ \V

-2 0 0 20 .~o //&O 80 100

I I · I I I -20 -UI Of 10 . 20 30

OUTSIOjlAIR TEMP."' °C /

Example: Climb pressure altitude: 3600 ft. OAT: 30°F Rate of climb: 620 F.P.M.


-

' 11111111111111

I\ ~~~~00 ~[§[ru~@[ru~~~~[§ ' FULL THROTTLE, FLAPS UP; 76 KIAS -\ l 2550 LBS. GROSS WEIGHT

\ SERVICE CEILING~13,650 FT.

\ ABSOLUTE CEILING~ 15, 7 50 FT. ' '

I\ l MIXTURE

.__ - - ........ . - - -

200

CLIMB PERFORMANCE

Figure 5-13

\

\

\

\

' \

'

- -- ... -

400

\

' ~

LEANED 100°r-,__ >--

RICH ,or PEAK EGT-~

MIXTURE FULL RICH

\ \ 1-~

L\ I \

I \ I

' 600 \.: ~D 10 DD

REPOflT: VB-790 5-17



PA-28-181 I/ VI v v I/ I I l )7 J...-'

I VI~~ I/ I.I / '_; '.r ...... ;, .. "'"\":I..,. ..... , ) ~ "'J ) ) ~

~ s ~~/ ~\!\.~\,,""" l/ ,

\.. , J ) ~ J ;;:, ~>/' .r~~

/ '\ II' i!:! ,, ~~~ , II' .r,/ . '/ ~

j I/ 1 /~ -w v I ,, ~~

/ ~'{:I,// ., ) j ~- ~~ v / . " ~" , §

/ ~ I/ I '1 '\~~ / MIXTURE l/ ,

J ~ 'A I ~ ~ I/ / LEANED 100°f v / \ /~~ If

., ),, I I/ RICH OF PEAK EGT ~

) I/ I '~ , II' , I/ MIXTURE • ., ) I / /- / / v / FULL RICH ,

)

~{ .. , ./ ./ J ) I I I v ,

) J. ....,J. ,_. -- ,_ i-.' I I I , - - --[/ , • ~flli& I v · li'~M~a ®~$1J ti\OO<C~ -

..... l) ) ~ , -I / Vil' , ,

) I · ti\00® ~M~~ i@ CC~~MOO -If j / i/1 If / / J ,

I , I /~/ / I I CLIMB AT 76 KIAS J j

I , flli& / I/ AND FULL THROTTL[ I I I \.)I I J '

/ v l' \/ I ,/ I I ) / v . 1-1 I/' J • , J

2155r ~B~. GROSS WEIGHT

I I i I I I I I I , ) / v \II ~ L ~ I I I I I I I I I I I I I .. - .. ,

I / I.,, flli& "''Y [/ THIS CHART INCLUDES FUEL ALLOWANCE

/ , - FOR START, TAXI AND TAKEOFF. . I

,~ If I

/ ,, ,

J I

J I/ . ) I'll I I

If j II ~ I , I

/ • 1, . v ~ •• t -2 0 100 5 10 15 20 25 30 35 40 45 0 2~ 0 80

OUTSID ,. EMP. ""° F 1\ TIME, DISTANCE AND FUEL TO CLIMB I I I

-210 -.ii 110 210 _310 \ OUT AIR TEMP ...... °C li

" ~ \ \ ., I

'

Example: 1 \

Departure airport pressure altitude: 2000 f,e Departure airport temperature: 70°F \ · Cruise pressure altitude: 6000 ft. \ \ Cruise OAT: 55°F \ \ Time to climb: 12.5 min. minus 4.5 min.\= 8 m~. "Distance ~o climb: 17.~ miles minus 6.5 IJ\iles = ll niru.tical miles Fuel to clunb: 3 gal. nnnus 1 gal.= 2 gal. \

\ \ ··•· ..... \ \.. ·,"'

TIME, DIST AN~ AND FltEL TO ~

50 55 go

---

.-,..._

REPORT: VB-790 5-18

F~S-15 ~ ~

, ·~ "1ssUED: JUNE 18, 1976


PA-28-181 / VI/ V L I I I I -- • I I I I

rJ ~ - - ~~©iU~~ -) v'1 ~y / / / ,

I 1 ~ J / l,L [f.> ~ lru lf!@lru ~~ ~ ~~( ~ 1--'/ / , II'~ f----

~BEST POWER MIXTURE !LEANED TO--\J I / ~'/ I

/ I\ V 'I' .rV v 100°F RICH OF PEAK EGT). -1 J / ,/ .$ ~.w v ,.

I J ~- .:§:-~ v / I ') --

I ) , v ~~ / / I / v /\ ~ / / I ---- --

/ / \V.$f f v J I j

J / /1 ~y v v I I , I

~ - - - ---

l I - r I_ f -- - - -- -

t rr I

' I L

'+-1- ---~ -- -----

---

---I---


- ----- -- - --

- --- --·-

I -I - - -

-- ---

---I-r- -- ----

---- ---- ---- -

/ / v v v PERCENT POWER- 5~ ) , I ~ .. --lL. I/ v -60 >-65-70-75

/ ,

I a¥~/ / / / v . ~~

/ I ...... 'I

J / VitV v v , I / ~ ----~ - l,L ~ - -,

/~/ v J / / '/ , ~

/ / J J ~1 - -

/ v , J II I J

/ / v ' v , v~~ ~ ~

--, / / / \ ,

) J j1 n..,y v J

/ , J / / / /

/ v , / / ~'o/ J

/ / / I \.J II' )-

J / / V\ ~ I I / / \V

...,.20 0 20 40 60 80 100 OUTSIDE AIR TEMP ....... ° F

11 I I I I I - I I I I -20 -10 0 10 20 30

OUTSIDE AIR TEMP."" ° C

Example: Cruise pressure altitude: 5 500 ft. Cruise OAT: 40°F Percent power: 65% Engine RPM: 2440 RPM

- ~- -

- --~ --1--

---- - - - -

2000

• I I I ----- - - -- -- -- ,_ - -~- --- - -- -J I I

I I I j -- --I---

I I I - - - - -- . ---

' ~ - ,__ /_ ,__ - j l I - --

I ------ ~-

I

-I -/ /I -I I

-- ---· ----~- --- --- - ----~ -FUEL FLOW G.P.H. L I I I - - -- - BEST POWER BEST ECONOMY -

I 1 I ' 7.8 55% 6.3 --j I I I 9.0 65% 7.6 -- - ---

I I } j 10.5 75% 8.8

I ' /1 I --~--

I I I I I / I I I -

I I J i 2200 2400 2600

ENGINE SPEED- R.P.M.

ENGINE PERFORMANCE (SERIAL NOS. 28-7790001 THROUGH 7790607)

Figure 5-17


REPORT: VB-790 5-19



PA-28-181 ./I v~ v I/ ,/ I I I I I I ! I ! .1 I [ J I I

I J v~~~ / / / ~~~~~~. [f),~OOlF~~M~lro~~ I I

"' / \ ''i / / BES_l_lllWER MIXTURE I I /

I v "' J I I / / ~·; / !LEANED PER LYCOMING INSTRUCTIONS! v V\ 'SiiV ~ Ir I I I I I I I I I I I I I I I I ; t§> - ,. ; /

/ v v ~' ~/ v FUEL FLOW GALLONS PER HOUR I / v '~ / I/ BEST POWER % POWER BEST ECONOMY I

I / V1 ~~ I/ / 7.8 55% 6.3 j I I J \~I/ 9.0 65% 7.6 I I

I I /

v v \/ ~ v / 10.5 75% 8.8 I I c:::i I ;

/ I/ / '/ v v r I I I I I I / J / / v / PERCENT POWER 55 60 65

I J /\ /Sil I/ I/ ' I / v C/13~ ~ J / / I J J

v / a (Q',,, / / I I . I j

/ I /~ / / / I I I J J ,.

J !; v v / I I J 'V''"~/ J J

/. .... ~ / I I j I

I/ / J / / / I I J /

/ / J \1 J / I I j

/ I v ~ v'~

/ I I I / / I/ v j I I J

I / J I/ "'~/ / I I I I v I J "' I v / v I I I

v v ; /\ / ~y j I I / I v \~ I I

I / / /\~ J I I I / / / / \V I I I ,,

-20 0 20 40 80 100 Of 2000 2200 2400 I I

I -20

I I I I

0

60 I

I I 20

I 11

I · 40 °C ENGINE SPEED RPM

OUTSIDE AIR TEMP.

Example: Cruise pressure altitude: 5 5 00 ft. Cruise OAT: 40°F Percent power: 65% Engine RPM: 2450 RPM

ENGINE PERFORMANCE (SERIAL NOS. 28-7890001 AND UP)

Figure 5-18

' I I

I

I 70 75 I J I I

I

I I I

2600

REPORT: VB-790 5-20


~--


PA-28-181 L v ---- c-·- / ~~~~lW ~@ 1~Y~lr3 u

'\


1l~ / J ~ ) ,, ~ v ~ ~ ~ ~ @[f3 ~'JJ ~ ~ (( ~ ~ lfd l!!J ~ ~ ~ I \ 1~--- ~~-- I j / BEST POWER MIXTURE, -- --

- 1 v' -----'!II.I / k¥ 2550 LBS. GROSS WEIGHT

+- / /\c 1-------.ff> -- MIXTURE FULL RICH ABOVE 75%, -~ ~

~ -- --~I I I LEANED 100° F RICH OF PEAK EGT '\.· ! l/ ~ l I ~vi- - ~ BELOW 75% POWER. WHEEL FAIRINGS

(_~ - /~\ <\',

<:,·

I IL !

K~ / INSTALLED, SUBTRACT 3 KNOTS 1 I 1 -0 - c;s

/ IF REMOVED. : ' I/ . ~/

I I J /- c I , j / I I

/ f-- - \ f---~ -- -- - -- -- - ~--

,/ / / \ ~" " ,/ / / \ v - ---- -- -- - - - -

l/ / J ~ -- ----- --- - -- -- ··- -- --- - - - --

/' / ~

~ ~ I/' ---- 7 - - - - -- >-- - - - - - -

f---- -~ - .. J

/ I\ " I

-~-1-~- -- --I----- - 1------ - - --- ---

J '/ • /' / ~

I I v / / J ' ~ - --

7 -/ \

~ -

~

J I/ \ % / / I

-20 0 20 40 60 80 100 OUTSIDE AIR TEMP. - °F I I I I I t I I I I I

-20 -10 0 10 20 30 OUTSIDE AIR TEMP. - °C

Example: Cruise pressure altitude: 5500 ft. Cruise OAT: 30°F Power: 55% True airspeed: 97.5 knots

% POWER -- I--- -

I 90

- i--

7 I

-- I/ - 55

I I I

I I

I ---t/ -- - - -

' I ---+ --- ---- f--- - ---- )

' ff -- --- - -- l -- - 7

'

-- --- ---- 1 - - L I-----I I

I 65- - -75 I -

I I I

I I J

I I 100 110 120 TRUE AIRSPEED - KNOTS

11 I ,_

I ...,1 c: ~-

::: -_.. -~ -c::> _.. -_.. ~ -c::> ::a -.....,

--- ...... c::> c::> -::a ""Cl-3: --

·-

130

SPEED POWER- PERFORMANCE CRUISE (SERIAL NOS. 28-7790001 THROUGH 7790607)

Figure 5-19

ISSUED: JUNE 18, 1976 REVISED: JULY 1 2, 1977

REPORT: VB-790 5-21



PA-28-181 / v.1 / I/ 7 2>w~~lP.> w©w~~ ~ w~~~@~j\J~~~~~ rt~1w~2>~ _

I v:'\,~~ / / BEST POWER MlxTURE I I I I I I I i /

v j '% / / -I /

2550 LB. GRoss wT.+ 1 1 1 1 T I r -I / I "'-· _, i7

/ V\ / S:-, / \/ !LEANED PER LYCOMING INSTRUCTIONS) v /

1 I/ ~·~':/' v 1 1/ '~~l7V

I

I v WHEEL FAIRINGS INSTALLED, -~ I -/ I

--- L___

, SUBTRACT 8 KTS IF REMOVED v_ ~J ~-f; \i/:~Y -v f/ - -- ------ - -- - - ---- -- --- -- ... --

I c:s- / , , I/ / V1 ~/ i/ v v I I ii I/ V I/

- --- -- --~- -- - t--- ----

b1 I /\ v. L_ z t--

/ v "'N $; ·-; /

'--- , ____ - f-- - - - - ----j -- ~- --

J PERCENT POWER 55 l{_ i/

..... <()' / -!--? I I

~7 r7 [7 r;:\\V I v ~- r----~ ~- ---r----- -r- --,

~ v / v I --Y --lL rl$/ 17 ·- -· --f-- -t--- ··--

I

l~j v

L-I

I

/ ,___

-20 I

lL I

I

I I

v 0 I

I

I -

/

I v_jz \";~ "/ z -I I I I / / /1

Is:-. I 1 --

I / 5::) v / C:S I

I / '\.'; / v I v / /

I v" -/- ~/ -j f--

I ~ I/ / V\4-Y

II v \V 20 40 60

I 80 100 Of

I I I I

I - - - - - -ril I I I I I

I I

l I I - - -- --I I

I I I I I I I

If 100 110

-- -

- I 7

·- ~-

7 65

I I

I I

I 7 T

I

I 120

\ I

L -f\ t--

---,_ '

\

- ~ T\ I \

7 ' 75 I

I

I I

130 I

-20 I I

0 I I

20 I I

40 °C TRUE AIR SPEED KTS

OUTSIDE AIR TEMP.

Example: Cruise pressure altitude: 5500 ft. Cruise OAT: 30° F Power setting: 55% True airspeed: I 0 I knots

I

SPEED POWER - PERFORMANCE CRUISE (SERIAL NOS. 28-7890001 AND UP)

Figure 5-20

--~

f- -

-

~-

f--

140

REPORT: VB-790 S-22




PA-28-181 I/ I / lL -····· $W~~@ ~@1~Yll~OO ~ \I~~

~- -

- / ~··

/ v

\~ / t1~ -- -·

,I ,

IL __ y v v ~- -- t7 ·- -- -z<S- ~ <ff>

J ~ ~ f«:.---\7 - -- -- ~· --

j ~

v c.,·

v~~~ ~$ v i/ ~ "o/ v :.,,, [7' . -

J II' i\-~--~ V' ,

- ·-

I/ j . ~.I. .__ 1~ ~

v \ ~(f v r7 \V I v

J ./ ~ ~ ,[} j J v II \ J j

v \,II' ,I

I/ V\ I II' . ~.J --

I I/ I ~/ II J 1V J

/ '/ & ~

J ' v 1'' § I lJ' ~ '

) v v v I/ I/

-20 0 20 40 60 80 100 OUTSIDE AIR TEMP .. °F

I I I I I I I I I I I

-20 -10 0 10 20 30 OUTSIDE AIR TEMP. - °C

Example: Cruise pressure altitude: 6000 ft. Cruise OAT: 55°F Power: 65% True airspeed: 110 knots

~~©~©lrAl\U' re~11v.n~~-~-·

BEST ECONOMY MIXTURE, ~ 2550 LBS. MAX. GR. WT. __ ~ MIXTURE LEANED TO PEAK EGT,

WHEEL FAIRINGS INSTALLED, - ---

SUBTRACT 3 KNOTS IF REMOVED. -. - -·-- . - - --- -t - -

I - -- ~- -~-·- ---l -

- ~ -- - '- -~ - ~ ,_ - - -I I

-- I

~·

I % POWER - ~5

~-

I I

~·-

I

I I

I/ 90

.. /_ -·- - -

1'-['\ -~ ------

\. .. - - ,. - .. --

l \. ---

J

/ ·~ -· -· - ·-

~~ I -f

t;.~ ... r-~~~ ·- -----

~o - -1

I ;;.4 1P I- t-· t---l-------- '""""'..__

i;;. \

I I I ..

I I I I -~ ~

- - - ~-'-I I

J J

I I I I

I I

I 65 - ~ -75 I I I

I J I

I

I I I I ,,

100 110 120

TRUE AIRSPEED · KNOTS 130

SPEED POWER- ECONOMY CRUISE (SERIAL NOS. 28-7790001 THROUGH 7790607)

Figure 5-21


REPORT: VB-790 5-23



PA-28-181

I / / I/ V V PERCENT POWER 55 65 75 I J /\ v.~ L / I I

v v ~\L ~I / J ~~ ~ ~ ,_L_ - - - J, ' ' I -

~ [__ V ~\ co:(4 J / I I 1

I I /~IV 11 / I I J I ~ ~ ll~ / v I I

1 J I V ~/ / , I !/ / I / \ "I I I/ I I I I

/ / I \/' I / ' I I / / ,v V\ I, ~ / I I I

I / / 11'~ / / 1 I 1 1 I I v ~/A-+l/---,f---l-+-+--+-~-+---+-+-+-l--+-1-+-l--+---<~,-+---<+.+1-1+-+--+--+--+-+--4--+-1

/ J ,v I ~ /~/~--+--+--+--1--+--+--+-+-+-f+-/+-4-+--+-1-+-++~1-1-+-1-+-1--+---<--+-~ v v I /\ / ~"/ I / / v I ,_,,I ".'it-~r---t----t----t----1--+--t--+--1--+--t--+--++-+-/-+-+--+--+-/+t--+--+-t++---+--+--+--+---+-----4--+-----+---1

I IV I /~~ I v 1 II V 1\V>'+--+---i--+--+-+-+-+--+-+-+-+--+--.r--+--+--+--~f-+---+--C~~-+--+-1--+--+-+---+--+---l

-20 I

0 I

I -20

Example:

20 40 60 80 100 Of I I I I I

I I I I I I 0 20 40 °C

OUTSIDE AIR TEMP.

Cruise pressure altitude: 6000 ft. Cruise OAT: 55° F Power setting: 65% True airspeed: 116 knots

90 100 110 120 130 140

TRUE AIRSPEED KTS.

SPEED POWER- ECONOMY CRUISE (SERIAL NOS. 28-7890001 AND UP)

Figure 5-22

REPORT: VB-790 S-24




PA-28-181 I/ v I/ I I l l I l 5 5% I I I I I I I I I I I I I I 55% [;3~$li' ~©W~OO 00£!\lro@~ I ~/ /

45 MIN. RESERVE AT 55% POWER MIXTURE LEANED TO 100°F II'

\ "'~ / I

I/ \," " I RICH OF PEAK EGT I j

65% 6~%.n '--V\ I/ v WHEEL FAIRINGS INSTALLED,

I/ 1 ~ ~" 48 GAL. USABLE FUEL I I

/ ~ l/f.§ 2550 LBS., ZERO WIND, _ I I ~NO RESERVE I+ ,_____

J \/ /.."'-• RANGE INCLUDES CLIMB -1

v ~ ~ AND DESCENT DISTANCE. I I

J j C,· , v \ v.£-i v I I II

/ 1 #)~ v 75% 75% I l

cl'/ v -r I I

l' -:~ I/ l T .

I/ ~~/ I I j j

v ;. ~~ I' l l ..,, ~ . / / v 1 1

/ / v I I

j" J - ~/- -'--I I .. -,_ -...... - ,_ --- - --- - ,_ ,_ - ~ - - --- -- .

/ I T \~ / '? /

I \," ,I ! I/ I I\ NOTE I I

/ RANGE MAY BE REDUCED BY UP TO 4% f i 11

) If ~'/ ' ! J' fl WllEL FAllltGS ARE NOT INSTALLED . I I

J I I v ," I v v I j r I :

v I /\ ¢-~ 1 I I I

) I II' \ ~ n I )., Vi

~""/ , I -,

~7 ll I/ I/ 1 v I 1 !~ J I

-20 0 20 40 60 80 100 y 400 450 500 550 600 450 500 550 600 650 OUTSIDE AIR TEMP .• °F


-20 -10 0 10 20 30 OUTSIDE AIR TEMP: · °C

Example: Cruise pressure altitude: 5500 ft. Cruise OAT: 35°F Power setting: 75% Range (with reserve): 4 70 nautical miles Range (no reserve): 525 nautical miles

RANGE • NAUTICAL MILES

BEST POWER MIXTURE RANGE (SERIAL NOS. 28-7790001 THROUGH 7790607)

Figure 5-23


REPORT: VB-790 5-25


PIPER AIRCRAF'l CORPOR\TION PA-28-181, CHEROKEE ARCHER II

PA-28-181 /1 v.1 v I/ / I I I I I I I I I I I I I I I I I I I I

J vr~~ / / / [;)~~lJ [p@'W~lfil [M~)AlJ[lj)[fil~ [fil~~~~ RANGE WITH I -/ \ ""/ / / / MIXTURE LEANED T00 '100° 1F RICH OF I PEAK E0GT° NO RESERVE-

v I v / I ~- ,/ / WHEEL FAIRINGS INSTALLED, I / /' /I/~ ~ .c._. / / 48 GAL. USABLE FUEL INOTE I I

I/ / / ,~~ ~/ / 2550 POUNDS, ~RO WJ~D_ L - RANGE MAY BE REDUCED BY UP TO 8% I I

I / ~y V / RANGE INCLUDES CLIMB AND J WHEEL FAIRINGS ARE NOT INSTALLED...,,._ I _ _,____, 1 I Vl ~11 / / DESCENT DIST ANCE1 . I

I J I \ <1.:;r~1 I J / I RANGE WITH 45 MIN.' I

1 J \/~~J ,v /~-+--+--+-RESERVEAT55% /, _ / I/ /1 / v v POWER 55% I I 55%

I / / / V / 65%/ POWER 65% I

V 1 , "' ~I / I I I 1~1...~ I/ I/ 75,% 1' 1J.~ I 1' / I ~ ~/r-+-/----+-/ .......... -----+--<-+--+---+-+--+-+<i---+-</---+-+--+--+--+-....--+--+--+---<~,-+-+/H-+-+-t

I I /~'/ I / I 1 / ~ l/~V / I I

v 1 I r¢-~y- r ->- --- ->- -- -r-i -- _,___ __ ,___ ----;ri I l---+l--+-.''-+-+r--+---~-1'-+-+--+-+-r---+-+--+-+-lr---+-+-+-l--l-tt--t-+-+-t-t--+-+-r---+-+--tt--tt-+-1--+-+-;

I ,v I A \ I"/ I I/ I I JJ I / / / \; / / I I I II I

/ I/ v I\ I ~ / I I I I I I I 1/~/ v I I , ,

/ I I / '\/ I/ I I I I

/ / I V / ~/-4--4---1---+--+-+--~--+--+--+ll f--+---l--4--+--l--+--+--+--4---1--+-/ ~' ,__/ l+--+--+--+--1

:/ / I I\ / ~y I I ,· I I/ / / I \,I/ '!It-~....-+--+--+-+---+-+-~-+-+--+--</>+--fl/ f--t-+--+--+-+--+-+--+---+--t--+--tr-+-1 ..... ,~-+--+--+---<

I i I / I\ 4-1' I I I fl / I I / \l/,o<+---t--+--+--1--t--+--1--t--+--t---+-f/-t-/+-H-+-+-+-+-+-~.A--+--+--+--+-,-ll---+-+H--/ 1+-+-+-+--l

-20 0 I

20 40 60 80 100 Of 400 450 500 550 600 r 450 500 550 600 650 I

I -20

Example:


0 20 40 °C OUTSIDE AIR TEMP.

Cruise pressure altitude: 5500 ft. Cruise OAT: 35° F Power setting: 75% Range (with reserve): 500 nautical miles Range (no reserve): 570 nautical miles

RANGE NAUTICAL MILES

BEST POWER MIXTURE RANGE (SERIAL NOS. 28-7890001 AND UP)

Figure 5-24

REPORT: VB-790 5-26




PA-28-181 / I v v I I I I I I I I I I I I I I I I

I \ 1$/ / 45 MIN. RESERVE~ --- 00~~11 ~~@~@~V OOti\~~~ ' AT 55% POWER MIXTURE LEANED TO PEAK EGT, v \~ /

v " /v WHEEL FAIRINGS INSTALLED 48 GAl. !\ ~/ ~ USABLE FUEL, ~550 LBS. GR. WT., I

/ ~ /.~ ZERO WIND RANGE INCLUDES I ~ J

I / /..Ao...· CLIMB & DESCENT DISTANCE. ' J \/ /.'. ~ I I I I ' s· ' / '\ ~~ I

/ \ ~ q_~ v I I I I ' -J

NO R~SERVE / ' / v I I

J </>./ IV I I I . v -..

-~/ I I ' J

%~ .

/ j ~J / I I

/ ,__JV 75-65-55 % POWER-75-65 -55-~ ~ I I I I , ,.

/ v v I I

NOTE ' J I.I v I I I I I

51:> RANGE MAY BE REDUCED BY UP TO 4% IF J ~~ ' I

J WHEEL FAIRINGS ARE NOT INSTALLED . /

, \ / / I I

J

/ V' / I I I

/ I\ ~I ; I ;/

J I/ , ~.I' I I

/ J / I J I

I/ , v i/ I l

v J\ ~ ' I ~ .

/ v \ -...; I I ~I .

j I \ sy I ' I I . . v / / ' J I I

-20 0 20 40 60 80 100 OUTSIDE AIR TEMP.· ° F

y 500 550 600 650 550 600 650 700 750 800


-20 -10 0 10 20 30 OUTSIDE AIR TEMP.-°C

Example: Cruise pressure altitude: 3000 ft. Cruise OAT: 35°F Power setting: 65% Range (with reserve): 570 nautical miles Range (no reserve): 650 nautical miles

RANGE · NAUTICAL MILES

BEST ECONOMY MIXTURE RL\NGE ~ ... tUAL NOS. 28-7790001 THROUGH 7790607)

Figure 5-25


REPORT: VB-790 5-27

I



PA-28-181 I/ v~ I/ I/ / oo~~'if ~~© ~©~lf ~ainrrwoo ~ ooffei~©J ~

/ v!~~ / / / I I I I I I I I I I I I

I / \ "') / / / MIXTURE LEANED TO PEAK EGT v \, v I I I ~·1 / WHEEL FAIRINGS INSTALLED v I/\ v~v / v

48 GAL. USABLE FUEL : I v' ~ ._~ I

I/ v ~' ~ I/ I I v ' ~/ i/ I/ 2550 POUNDS, ZERO WIND I j

I Vl~~ I/ / RANGE INCLUDES CLIMB AND RANGE WITH I

I

v I I \ ~ ~I/ / .I DESCENT DISTANCE NO RESERVE I l v v \,I~/ 1

v v I flTflTI 11 55% 55% I/ I/ v ~/ v v RANGE WITH 45 MIN. RESERVE 65% I 65% I

I / / i/ v v ~ 1 155zo ~o~ER 75% I POWER 75% I I I I /I I I/ I/ I I I I I I

/ v v 1¥ .$'; / I 1 1 1 NOTE I 1 I RANGE MAY BE REDUCED BY v I ~ G:>'.1

/ I ? I I UP TO 8% IF WHEEL I

I I /~I / / v I

I ~ v v / FAIR~GS ARE NOT INSTALLED I I

"I'-$; / / I / 1/ / / \ "/ I / I I

/ v J \, / / I I I 7 / / / V\ I~ j I I I

I v I I /~/ i/ I I I/ I I I "-/ v I I

I I I/ i. - iL J L - ,_ - - ',....J ....... ,_ - - - - '- - ...._ -- '- ,_

/ / ,.

/ \ ;~Y 7 I

/ I / II \;V ~ 7 71 1 ./ V1 l\4Y ' I I I I I

v I I/ IV \V I I ' ' . l I

' -20 I

0 I

20 40 60 I I I

80 100 Of I I

500 550 600 650 550 600 650 700 750 800 I

-20 I I I I

0 20 I I

40 °C RANGE NAUTICAL MILES

OUTSIDE AIR TEMP.

Example: Cruise pressure altitude: 3000 ft. Cruise OAT: 35°F Power setting: 65% Range (with reserve): 600 nautical miles Range (no reserve): 660 nautical miles

BEST ECONOMY MIXTURE RANGE (SERIAL NOS. 28-7890001 AND UP)

Figure 5-26

REPORT: VB-790 5-28




PA-28-181 I/ VI v v I/ I I I I I I

VI~~ I/ I/ / ENDURANCE WITH

I 45 MIN. RESERVE 11 "'J ,

I / J AT 55% POWER , , ~ I/ v \_ 17

J j ~·~ J

/ 11 / II' J" / /

) I/ / ~ ~-$'· / I I ~- ~~ 7 7 Co)

I I v~~ / / J

/ ,

j '\j{ JI ~

/ / ' /~j , T ,

j ~

J I/ / '\,~ 7 7

I / / v v v v I I l.L I/ r7

v , j ~¥ ~/ J J

I/ , ~ ... c:s """ (Q) j ,

J v v~ v II' II' ..,, , I / i/1 I/ v I/ ,

I J ./ ~/ I/ , c:s / ,

j I' "-/' I I/ / v ,II' \1 I J

I I/ v ~ [/' J~ ~ '--, I / I/ \ V~, '/ v ,

I I A "''Y / / ,

j J i/ / I/ / v ,

J \ / ~"'/ , , ~ I I/ / II' \~ j

~ ) / I ~ I J / / \/

-20 0 20 40 60 80 100 OUTSIDE AIR TEMP . ...,of I 1 I l I I I I I I I

-20 -10 0 10 20 30

OUTSIDE AIR TEMP ...... °C

Example:

, y

Cruise pressure altitude: 2000 ft. Cruise OAT: 80°F Power setting: 65%

75%

._.. ..

Endurance (with reserve): 5.37 hrs. Endurance (no reserve): 6;1 hrs.

>--65%-

5

I I I I I I I I I I I I I l - ~ lro rID M lF3 Y-\ lro ~ ~ BEST ECONOMY MIXTURE !PEAK EGTI 2550 LBS. MAX GROSS WT.

I I I I I I I l T

- -- THE ENDURANCE SHOWN INCLUDES CLIMB AND I

I

DESCENT TIMES. l I

I I I I \ ENDURANCE WITH NO RESERVE I

II I

\ I I

f--I-- 55% POWER I;5%-1---&,5% 55%

I I

I I

T

I ' - - - .._ - .. - .._ .. .._ r: - i- I

I

I ' I I

I ' I I

I ' I . .. I

,, I It ' 6 y 7 5 6 7 ENDURANCE"" HOURS

ENDURANCE

Figure 5-27

ISSUED: JULY 12, 1977 REPORT: VB-790 5-29



PA-28-181 I/ VI v v I/ ~a lt¥~H~ 11 @a£)~ £~~rn £lroOO> ~Mrnl!. I/

I ill~~ I/ I/ / I v j ~ "°') J J ,/ i 1 ~© 00>~£)~rnlro00> I

v II ", II' ~II' ' DESCEND AT 122 KTS ) , __

) ) ~) )

I/ V1 v I/ .r / I/ l.A.S. AND 2500 R.P.M. I J I/ v $ "-.$'/ v j 2550 LBS. GROSS WT. J

I I ~- $~ v / _; ./ J i:JL II v q,~'-'l / /

cc It ~ - --

I = / ./ J '1 /( I / j

_, ~ rJ - .__ ...... - --v '/ v~j

, , )/ = ;::: ~

\ ) ..... .;:s

J / V1 ~~/ I/ / I --~-~~L~-/ / v v v I

---~~L---- -- - -- · ___ --r-- ~t-I ~J I I

v I l~V I/ I/ ~/ !

' ~~·- ---

/ / -~Cruise --

I ~t_ $1 J / I/ II .... (o/ • I j A ) I j

) v V~\ I/ I v I/ /l --~ ~--- ~

/ ~ ~- - -- ~- - --

, I / i/l l.i1' / v ~ L ,

/ /~/ / -- 1---.----I/ - - ---~-- --I-

J / I I ! / /

~ / I/ I I ,

I I "-Y ~-I '

/ v )' Destination ~ ~-

t - -- -- <----- - -1-~ ~- - -- -----

\/ ~ I / J

-1- / v "' v ---'. '-- ~l!f._ORJ_ -- -~ L - v

/ v \ ~ v / v - -- --- - -- - --- -

J II~' j /

/ J 1/1 "-Y v I t ,,v J 1 --

/ II II' y / / ) ,,v j / ~

/ v / J /~~ I /,

J / / j J , ...., I I/

j / / ' ~ I ';" / I ' v /' I/ I/ 'v r .. r ~ ~ -20 0 20 40 60 80 100

OUTSIDE AIR TEMP ...... ° F , 1 I I I I I I I I I

0 5 10 15 20 25 30 35 40 45 50 55

TIME, DISTANCE AND FUEL TO DESCEND -20 -10 0 10 20 30

OUTSIDE AIR TEMP."' °C

Example: Cruise pressure altitude: 6000 ft. Cruise OAT: 55 °F Destination airport pressure altitude: 2300 ft. Destination airport temperature: 70°F Fuel to descend: (1.7 gal. minus 1 gal.)= .7 gal. Time to descend: ( 17 min. minus 10.5 min.) = 6.5 min. Distance to descend (35 miles minus 22 miles)= 13 nautical miles

REPORT: VB-790 S-30

TIME, DISTANCE AND FUEL TO DESCEND

Figure 5-29

ISSUED: JULY 12. 1977


PA-28-181 /1

/11 '* i +-+ ((:j~~@~ ~j.\lro©)~ \ +-1 t \ t t---

J ~/ \ -~->---/ --~~ ---LV}'~ ~ - POWER OFF, FLAPS UP, 76 KTS. IAS, 2550 LBS.

t7 -- -~~--- NO WIND - - - --- - - -v'-· V\ /\~ / --- ~ p- -l7' - - - --- - ·- ·--- -- --- r----

/ J ~q; (; __ yk{ _ - - --- - - ._ -- - - -- - - - - -

\J

- -

--


I - --- - -- --~

J

- -- - l --- -- ~-

-F j

I - -

l ----

I "'

/\ -l_ /_ - -- CRUISE -- - - -- - - -- -- ·-!---· --~

- -- - -- -- - -

\ / \. - - ....._

~ ' I/ ' / / / v

J / I .L \ v \ J \ ~ /

' / \ ~/ \ /' J

\/ \V w J ./ ~/

/' / ~\ / \ Ir \ / \ / )

\ / \J y IA /\ J \

/ , I/ ' ~ ~ , J / J

/ \ , v )( ....

K /\ .I~" / \ v \ ~I \

) , / , '1'(

/ / v 20 ~u~ ~ 4~0 80 Tiii

AIR MP.-°F I I I I I I

I I :,/, I I I -20 -10 r. 10 20 30

OUTS pt AIR TEMP.-°C

Ex ample: Cruise pressure altitude: 8000 ft. Cruise OAT: S0°F

-

Terrain pressure altitude: 1500 ft. Terrain temperature: 70°F

- - ~ -- - - - - -- -

TERRAIN

Glide Range: 14.5 miles minus 3.5 miles= 11 nautical miles

ISSUED: JULY 12, 1977

GUDE RANGE

Figure 5-31

..__ -

--r---

--

-

- - ...._ - -I --- ··-

I -- --~

j I

I I

I I

J A fl

I I GLIDE I I RANGE I t ,

I 5 10 15 20 25 3 0

GLIDE RANGE - NAUTICAL MILES

REPORT: VB-790 5-31

VI :;::l I tTl

~~ :;::l ~ < o:i

I -...J

'° 0

~ z 0 -z

~ 0 ~ "'Cl '"1 tT1 (1) ~ VI "!j w 0 VJ ~

s:: ~ (') tr!

-Cll Cll c: ~ """' ~ -N -'° -...J -...J

(

PA-28-181 -

1110 l l '

1 1 r r 1 1 1 ---1 1 T

1

~~~[IDJ ~~ ~~~~@~~~~~~ -+--+-~· t--t--+--+--+-+---+--+-+--+---t--t--+--+- POWER OFF AP PRO AC H, 4 0 ° FLAPS =tJ

I I I !

66 KIAS APPROACH SPEED FULL STALL TOUCH DOWN

MAXIMUM BRAKING l-r---t~t---+--t-.....,...--+--t~t---+-+--1---l

1 PAVE~, ~EVELi DRYI RUN~AY I --4---1-, -+---+-

I I I I I I I I I I I I I 1 I I I ~ ~--:+-4-T-n-+-~ --.- · I I r I r I 1T I I I I I I ~I I I I I +-t--1---I I I I I I I I I I I I J l~a==t#4t±--H+l I f I 11 I l~Vkl I I 1

I I Y0·rnrpii~ I i=m=r=:+m+ffi[t-f~~t-J ~f{, ,

~ I 1 111111111111 ~= --~~-~~--~ LL.j_+---l--J--.l--+-+--f-+-t-t--+-t-i-1---j___j....._;_-+~--l ~_J, -~'ls" I I i 11--ili-·T-~'T't

1800

1700

1600

1500

1400

1300

1200

1100

lLJ_ JI -•t-tt. +-ff I I I I I N'f'FfN 1000 ' 0 5 . 10 15 -40 -20 0 20 40 60 80 2550 2500 2400 2300 2200

OUTSIDE AIR TEMP .. °F I I I I I I I

I I I I I I I -40 -20 0 20

OUTSIDE AIR TEMP. · °C

GROSS WEIGHT · LBS.

Example: Airport pressure altitude: 2300 ft. Gross weight: 2264 Temperature: 70° F Wind: 5 knots (headwind) Landing distance: 1290 ft.

(

2100

WIND · KNOTS

...... ..... a:: ..... i52 a:: cc CCI

.... C) Lt')

a:: ..... > C)

..... ~ :z: cc ...... "' = CD :z: Cl :z: cc ......

(

.,, v.i tTl tr!

~~ o-~~ ~VI (') tTl

"'Cl "'Cl >' "'Cl N tr! qo~ -~ i!:: ~ ::io (j (') = ::io ~ 2i; 0 ...., ~ (')

tTl ~ >~ ~ ::io (j> = ...., tT1 -~o =z

.-; tll tll c:: ~ .. c... c:: ~ -~N -\0 -...) -...)

- :;i::l

~ 0

~ <

VI tjl:' I -...)

t..J\O wo

)

~ ~

'Tj 0 ~- 0 a ~ Y' ~ w z Ul 0

~ ~

)

PA-28-181 I I I I I I I I I I I I I I

[!. ffel ~[ID~~@ @[IB@[!)J ~[ID [IB@[b [!. I

+POWER OFF APPROACH, 40° FLAPS FULL STALL TOUCHDOWN

MAXIMUM BRAKING PAVED, LEVEL, DRY RUNWAY

I I I I I

I

..... I

:!: I I ..... ..... I ~ :z: ..... = .....

STD. TEMP.-~ '\~~ ...... i---~ ~~~

_ ..... = ~ r--...._ -I 1 ..... "( _....v v ....... .....- ..... -::c r-r- i--_ ....... CD -I ~"\ :-~:.---- .......,,..,,.,~ ...... ...... ,..... v--=. , ..... ~ - -r-- --~ - I i-- --->- ~

I ~,_\1:;,~ v .......... v'"=....f)(,_..... / ':>'""'i.--:::;..- --- --- I -x ..J.--1 .....,.,,,,.... ,.,,-.......... ~ ---~ I :..--1_...... ...... I ;-- -.,,,,,, ~ -- -_...... - - --~~_.....-v ... V~' - -- --=::::::::.,,

~ ~-.'~ ,_...... ..... - -_&,'\!,'\!.'\!. ~~~i~f-\'\!.~, ~.\.· --l--_,__ • ---~--i--- -- I ----I --i--

I I ~ i--

I I

• I -4 0 0 40

OUTSIDE AIR TEMP .. °F I I I I I I; I I I I I I I I

GROSS WEIGHT · LBS. -40 -20 0 20

OUTSIDE AIR TEMP. - °C

Example: Airport pressure altitude.: 2300 ft. Airport temperature: 70°F Gross weight: 2264 lbs. Wind: 5 knots (headwind) Ground roll: 825 ft.

j

:

I I

I

l !

I I

1500 i

I

1400 I ~· , ..... ~I ':z: :::! '

1300 ..... ~ I ..... ~

I I I I :z:

1200 .....

I I : = ..... ...... I i .....

= 1100

1000

900

" ..... ! c :!: ,/ ,(' ~~bf-~ r-- i-- !'.....I/ -r- 1-:-...... I~-i--

i-- i I N !'.... -/'":..._/ I"', -800

, ... i<:::+----* I- ,'~ I"""' -

700 - i, r-...... r...... - .......... ...._ I ~'

600 I I ....... "'.....

I i " r-...1 T"- 500

0 5 10 15

WIND · KNOTS

r

)

I

I

I ...... ..... ...I ...I 0 er:: Cl :z: :::::> 0 er:: CD

CD :z: Cl :z: cc ...I

"Cl "Cl ~~ ~~ -> ~;3 (i (i

~~ ~~ ~(i tT1 0 tT1 ~ >o ~~ (i>

;;~ ~o t::Z

""Cl tTl

~ 0 tll

~~ ~g (i z tT1 Vo


REPORT: VB-790 5-34



ISSUED: JULY 12, 1977

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