Piper Cherokee Archer II Pilot Operating Handbook
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PILOT'S
OPERATING
HANDÉOOK
PIPER CHEROKEE
IRC-NCN
U
.-..-,.-,.t '. :
FAA
APPBOVED
IN
NORMAL AND
UTILITY
CATEGORIES BASED ON CAR 3
SUBPAFT
ANO FAR PART 21,
J.
THIS HANDBOOK INCLUOES THE
MATERIAL
REOUIRED TO BE FURNISHED TO THE
¡,.,)T
BY CAR 3 AND FAR PART 21, SUBPART
J
CONSTITUTES THE APPROVED AIRPI.ANE
FLIGHT MANUAL AND
MUST BE CARRIED IN THE
AIRPLANE AT ALLTIMES.
PA-28.1 I
1
REPORT: VB-790
FAA APPROVED BY:
AtRPLÀNEttt'oato.
ATF'LANE
._-
..
REGrsrRAroN
No.
0E-DKT '.+)\
\]
ctr
1Ç-
0J
o¡J-
Fvr
0,..¡,
WARD EVANS
D.O.A. NO.
SO-1
PIPER AI RCRAFT CORPORATION
VERO BEACH, FLORIDA
,._t{1,,j,1,/(
j
I
i
HANDBOOK PAHT NO. 761 624
pri.oT'
S
PA-28-l8l; CHEROKEE ARCHER
...":.:
II'
OPERATIÑ G IIANDB OOK 4ÞPvCP{i
/< vB-? e 0
REvrStoN
PR84n330 (Sì)
PIPER
.AIRCRÀFT
CORPORATON
ATPROVAL SIGNATURE AND
-
STAMP
REPORT: VB-790 ll
Publislted bY
PUBLICATI ON S
DEPARTT'IENT
Piper Aircraft CorPoration
Issued: June
l8'
1976
APPLIC.ASILITY
The aircraft scrial numbcr eligibiliry
28-7990589. dcsignarcd
The spccific application bracket
ofihis
hand by scrial number and registration num
This handbook cannot be uscd for operarional
REV
The i¡formation compiled distdbuted to the airplane
in
the Pilot:s Operating Handbook wiJJ be,iept õunent.Þi nvisions
owners. i
:
Revision material and/or will consist of information necessary to update t¡e text of the p¡eænt ha¡dbook to add information to cover added aþlane eqúpmént.
I.
Revisions be
Revisions inserted will be dist¡ibuted whenever irecessa¡y as complete page replacements into t¡e handbook in accordance wiür trre instn¡stibns given beiow: ot additions a¡d shall
l.
Revision pages will replace
o
2.
Insert all additional pages
in
3.
Page numbers followed
by
common numbered paç.
mber.
ach d section.
in
direct sequence wità the same
II.
ldentifìcation of Revised Material
Revised text and illusbations shall be indicated
Page, opPosite revised, added page number will indicate that an entire page was by added.
a black vertical line along the outside margir of the o¡ deleted material. A tire along the outside margin of the page opfosite rhe
Black lines will indicate only cu¡¡ent text and illustrations. Changæ in cåpitalizâtion, on â Dage will not be identjfìed by symbols.
revisions with changes ancl additions to or deletions ofexisting spelling, punctuation or the physical location of mate¡ial
ORIGINAL PA,GES ISSI,JED
The origi¡al pages issued fo¡ thjs handbook prior to ævision a¡e given below:
_ -_
Title, ü th¡oueh v,
l-l
through 1-14,2-l t¡roush 2-8,3-l
Gl
through 6-52,'1-l tlrough 7-26, th¡oueh 3-12,+l
ùl
through & 16, 9-l through 9-14, rhrough +16, 5-l
I
Gt ttrrougtr t O2.
rhroush
PILOÎS OPERÁTING H.ANDBOOK LOG OF REVISIONS
Cur¡ent Revisions jssued Ju¡e 18, to
19'16 the PA-2&l8l Che¡okee A¡che¡II Pilot's OperatingHandbook, REPORT: VB'790
Revision
Numbe¡ a¡d
Code
Rev.l-761624
(PR760804)
Revised
Pages
2.1
Gi
641
643
Description ôf Revision
Revised
'Neve¡ Exceed Speed" KIAS value.
Revised Ài¡spe¿d Indic¿tor MarkinSs.
Revised report numbe¡ at bottom of page.
Revised
Revised
Arrn and Moment for item 177.
items 193, 195 a¡d 197.
FAA App¡oval
Sigtature and
Date
S)6o[
E.*
Wa¡d Evans
August 4,
I
!
Rev.2-761624
(PR770r 20)
6-3s
6-37
æ4
æ8
7-21 l0t
tù2
34
3-l I
+7
+8
+t4
4.15
54
5-6
5-23
æ
ç5
6-2t
Revised O¡ren Door procedure.
Revised para. 3.27 nfo.
Added Caution to para- 4.9; IËlocated material to page 4-8.
Adcled ¡elocated material from page
47'
Àdded Note to para- 4.31,
Revised stall speed in para. 4.35.
Revised wording in pa¡a. 5.5 (c).
Revised fuel quantity figure ia para" 5.5 (s).
Revised 55% &TSVorange figures ia Fig. 5-25.
Ädded A & B values to Fig, 5.1.
Rwised weight and balance formul¿
Added added
Weight, Arm and Moment to item 29 a.; item 29 b.; changed existing item 29 b.
to 79 c.
Reviscd
Reviscd item 79 Arm and Moment.
item I l5 Dwg 99æ2-5
I l7 Dws 99003-5 to -7.
to'8
and item
Revised footnotc.
Revised item 257t. A¡rn and Moment.
Added info to para.7.25.
Revised t03(c);Ìelocatêd material to page
I
S2.
Âdded ¡elocated material f¡om paæ
lGI.
l*iarÅ66+
Ward Evans
Jan,20, 1977
Rev. 3 -'161 624
(PR?70225) l{
3-l I
44
+9
æ
649
7-25
Conectsd
Revised to "lvleteorol ogical,"
NOTE
Rcvjsad Hot Sta¡t procedure.
Reviscd
' Revised
4.13 G).
l¡veling Diag¡am illustr¿tion.
Revised Dwg. Nos. of items 287 and 289,
Added ELT test info,
Il*.J-€t*
Ward Evans
Feb. 25, 1977
REPORT: VB-790 iv
PILOTS OPERÄTING HÄNDBOOK LOc OF REVISIONS (cont)
Description of Revisi on
Rev.4 - 761 624
@R7707t2)
5-29
5-30
5-3
l
s-32
5-33
5-34
ù.17
6-33
645
1-3
1-1
t,
l-12, l-13, t-14
4-1 0
5-9
5-1
9
5-20
5-21
5-22
5-23
5-24
5-25
5-26
5-27
5-28
646
647
Added new propeller
Revised to 1.5 a¡d added fooûrote.
section 1.21, Conversion Facto¡s.
Ädded new propeller to 2.7, item footlote.
()
and added
Revised
4evised
Starting With Extemal powe¡ Sourci.
iþm 4.13 (d) Sra¡ting
Exte¡nal Power Sou¡ce.
E¡eine lvith
Added CAUTION.
Revised-page nos.; revised titles; added pages; added figures.
Added ser. nos.
Relocated Fig. 5-19 to page 5-21; added aew cha¡t (Fig. 5-18).
Relocated Fig. 5-2t to page 5-23; added ¡e.
located Fig. 5-19; added ser. nos.
Relocated Fig. 5-23 to page 5-25; added new chart (Fie
5-20).
Relocated Fig. 5-25 located Fig. 5-21; added ser. nos.
Relocated Fig.5-27 to page 5-27; added ¡eto page 5-29; added new cha¡t (Fie" 5-22).
Relocated.Fig. 5-29 to page 5-30; added relocated Fig. 5-23; added ser. nos.
Relocated Fig. 5-3 chart (Fis.
5-24).
I
to page 5-3
l;
added new
Relocated Fig. 5-33
926).
to page 5-32; added relocated Fig. 5-25; added se¡. nos.
Relocated Fig. 5-35 to page 5-33; cha¡t (Fie. added new
Added page (added relocated
ttu¡¡.t
Fig. 5-2?).
Added page (added relocated
Added page (added relocated
Added page (added reloeated
Fig. 5-29).
Fig. $31).
Fie $33).
Added page (added relocated Fig.
Added page (int.
5-35).
Added item 3.
Added items '16 a¡d
77 .
Added item 223;renumbered items; relocated item.
Added ¡elocated items; renumbered items; added new items; relocated items; removed footnotes; adde¿f foot¡ote.
Added ¡elocated items; renumbered items; added new item-s; relocaled items; added footrote.
REPORT: vB-790 iv'a
Revision
Number and
Code
Rev.4 - 761 624
(PR7'107 12)
(cont)
Rev.5-'161 624
(PR780703)
Revised
Pages
æ8
s-25
5-26
5-27
5-28
Çt
ç35
æl
642
æ3
644
6.50
'7-21
7-24
8-i
&15
l4
2-7
3-3
3-7
+5
+9
+t2
5-5
PILOTS OPERATING HÄNDBOOK LOG OF REVISIONS
(cont)
648a
#8b
æ9
6-50
1-l
7-r 8
Description of Revision
FAA Approval
Signature and
Date
Added ¡elocated items; renumbered items; adde¡t new items;ævised ifem 277;
¡elocated items; added footnotes'
Àdcled
Page new item).
(added relocated iterns and
Added
Page'
Renum-beied items; revised items 325 a¡d
329.
Renumbe¡ed
Âdded new propeller model
Revised items; ¡evised item to
349' para- 7'5' alte¡nate static source description npara- 7.21'
Revised note.
Revised proPelle¡ toler¿nce RPM'
Added additional
Ädded Primer
Takeoff Check List' i¡formation to "Engiae Power
Loss Duri¡g Taleoff ' check list.
Added Prime¡ i¡formation to "Engine Power
Loss During
Ädclect
Takeoff."
P¡imer information to "Befo¡e Takeoff' check list.
Deleted "pressing in" of magneto switch as necessafy.
Added Primer checked information to para' raph.
Changed item 5 f¡om Cruise Fuel to Cruise
Fuel Consumption.
Added note
Added note to graph.
to g¡aph.
Added note
,{dded note to gra.Ph.
to gra.ph.
Changed pa¡agaph.
Changed item 93.
Added Collins
Collins
VHF-250 to item 169, added
VIR-350 to item
l7l.
Relocated
189 and item 187, 189 a¡d l9l;added items to
l9l.
Relocated
Relocated item lE7, lE9 and 191, added items
194 and 195, changed items 201 item 195 to 196.
, 203 md 205, revised item
Added
Added vendor information to
"Caution" to'7.23.
iten 349.
2l I
Removed ELT inlormation îrom
7 '37'
Added 8.29 Cold Weather OPeration to table of contents.
Added 8.29 Cold Weather Operation.
U*J.6"-
Ward Evans
Júy 12, 1971
Ward Evans
July 3,
I 978
REPORT: vB'790 iv-b
PILOfs
OPERATING HANDBOOK LOC OF REVISIONS (cont)
Rcv.6-761624
(PR?90228)
Rev.7-761624
(PR7904r3)
Rev.8-761624
( PR 80052-:ì)
Description of Revision l-6 l-12, 1-13
|
|
Rcvised para-
Revised pan.
1.19.
1.21.
6l I Revisea para. 6.1.
633 |
Renumbered existiog items 75, 76,77 to 74,75,
|
?6; added new items 77 s¡d
?8.
Ç37 I
Revised item
ll3.
û41 I
Addcd item l?8.
7-lO I
Revised para- 7.15.
7-tl I Revised para.7.15.
7-24 |
Revised para. 7.37.
6.48 I
Revised item 279,
648a I
Ädded irem 280.
1-24,7-25 | Revised para.7.37.
D-Jfu
rJy'ard Evans
Feb. 28,
1979
LLe€*-
Ward
Evans
April 13, 1979 iii
l-3 |
Revised para.
1.3.
L4 |
Revised para. l. I l.
2-2
2-3
2-4
3-i
I
|
|
|
I
Revised
Revised
Revised applicabitity.
Revised para.2.7.
para. 2.1I para.2.l3.
naaea para.3.28.
.
34
3-ll
|
Added Carburetor lcing.
I eaaeO para.3.28.
4-i
4-S
4-6
4-13
I
Renumbered para.; added
I
Added descent para.4.28.
iñfo.: moved info. to pg.4-ó.
|
Relocared info. from pg.4-5.
|
aOaea pan. 4.28.
+14
5-l
|
I
Conti. para.4.28.
Added warning.
t3-5-6 I
Revised oara. 5.5.
ll8
|
|
Revised
Revised para.5.5
fig. 5-15.
5-25. I
Revised fiç. 5-23.
U26 | Revised fie.5-24.
5-27 |
Revised fig. 5-25.
t28 | Rcvised
Revised fig. 5-26.
fis.5-27.
t30 t3l
|
I
Revised
Rcvised fig. fig.
5-29.
5-31.
6.1
G3
|
Revised pãra.
Added caution.
6.1.
y!2
Ç37
|
Revised Fig. ó-t5.
|
|
Rqvised ¡rem
¡l:
added itcm
,aaaeOirem 122: pg.
ó--38.
17.
moved irems t29 and 13t ro
REPORT: VB-790 iv'c
Revision
Number and
Code
Rev.8-?61ó24
(PR 800s23)
(cont)
Revised
Pages
û38
A
HI
6-42
7-l
7- t0
8-t I rG.2
Description of Revision
FAA Approral
Signature and
Date
Relocated
Relocated irems 129 and
l3l
from pg.
6-37.
items
I
69 thru
I
77 from pg. 64
I : Revised items 173
Moved added and I75.
items 169 thru 177 to
Pg' G40; item 180; relocated item 183 from pg. û42'
Moved item 183 to
Pg.
ó-41.
Revised para. 7.5.
Revised para. 7.13.
Revised para.8.l9.
Added para. (j).
CI*S.
€--
Ward Evans
May 23,
1980
Rev.9-7óló24 r PR 840330) t-3
I
-ó.
t-7
2-l
CF1 b-s.
6.10
Gt7
7-lt
1-22
8-3
8-4
8-ll
8-l la.
8-ltb
9- r3
I
0-i
IÈI.
r
0-2
J-l
3-l
4-i
+s-
4-5.
4-6
4-8
4-t2
4-t4
4-t5
GI
G3
6-6
Revised Table of Contents
Revised
Revised para' 1.7
para.
l.l9
Revised para. 2. I
Revised
Revised
Para. 2'7
Table of Contents
Revised
Revised
Revised para. 3' I
Table of para. 4.5
Contents
Added Note
Added Note
Revised para. 4.29
Move para.4'31 from 4-14
Revised para. 6.1
Revised para. 6-3
Revised para. 6.5
Revised
Fig. G5
Revised Fig. fr7
Revised para. ó'9
Added Caution
Revised para. 7.31
Revised para.8.3
Revised Para. f{.5
Reviscd para. 8'21
Added new
Page
Revircd Sec. 3(a)
Reviscd Tahle of Contents
Changed Scc. Titlc
REPORT:
VB-790 iv-d tJ-i F-*,
Ward Evans
Mnrch 10. l9N4
)
Revision
Number and
Code
Kev. t0 - 761 624
(PR900608)
PILOT'S OPERATING HANDBOOK
LOc
OF REVTSTONS (cont)
Revised
Pages r-3
14
8-l
8-3
8-4
8-11
8-11a
9-9
Description of Revision
Moved iæm (c) Ìo ps.
1-4.
Relocared iæm (c)-fron pe.
1-3.
Revised item (c).
Revised para- 8.1.
Revised para- 8.3.
Revised para- 8.5.
Revised para.
8.19. Added Noæ.
Revised Fuel Grade Comparison
Revised Fhergency
Charr
Operarion, Item (a) (2).
FAA Appmval
Sigranrre and
Da¡e
REPORT; YB-?90
iv.e
ì
TABLE OF
CONTENTS
SECTION
1
GENERAL
SECTION
2
LIMITATIONS
JECTION
3
EMERGENCY PROCEDURES
SECTION4
'NORMALPROCEDURES
SECTION
5
SECTION
6
SECTION
7
PERFORMANCE
WEIGHT
AND
BALANCE
DESCRIPTION AND OPERATION
AIRPLANE AND ITS SYSTEMS
OF
THE
sEcTloN
I
A|RPLANE
HANDL|Nc,
MAINTENANCE
sEBvtctNG
AND
SECTION
9
sEcTloN
10
SUPPLEMENTS
oPERATING
TtPs
REPORT: V8790 v
SECTION
1
GENERAL
SECTION
1
GENERAL
Paragraph
No.
l.'
) 1.3
1.5
1.7
1.9
1.lt
r.l3
t.1 5
1.1'l
r.l9
1.21
Page
No.
1-l
1-3 l-3 l-3 l-3
14 l4
14 l4 t-5 l-11
REPORT: V8790
t-i
PIPER AIRCRAFT
CORP(
TTON
PÀ-28-l 81, CHEROKEE AkçdER
II
SECTION I
GENER,{L sEcTtoN
I
GENER,A,L
I.1
INTRODUCTION
It
p'ot
als
kn
no oP
i::-,åi?i zupplied by
:f:rï"i.",{i''.'il'r't'S:J;lli:
"i,iiår:iiii,iff,,'i;åiiïi".,ili,ffïå;:ï;.31flå,1ìî1,:Tiî;
ic
flig[t
instruction or a training manual current stâtus.
and should not U. ur.¿-ioi
Assurance comma.nd is responsible remairing ha¡dbook.
that the airplane is ia an airworthy conditio_n is the responsibility within
the
foi determining that the aþlane is operating limitations as outlined safe
by
rot dieht. instrument
ih.
of the owner. pilot i,
rrrLìngr,
.l.o
ïre
p.ilot in responsible placardi, a¡d lor rhis not
-AJthough be used the familia¡ize lúmself the airplane before arrangement so.lely as an with the limitations, performance, procedurei flight.
of th.is occasional
.handbook is intended operating refe¡ence. to
Tlre increase pilot and its .in-fligrt should capabilities, studyire it should enti¡e handbook to operational úancÌling characteristics of divide¡ handbook
for
quick has been reference. nonnal procedures, performance and otller scctiorls required
tle
Ïle in
füght' The delibe¡ate omission of divided intonumbered(arabic)sections,each provided
The lirnitations and emergerrcy procedures l¡avc to provitJc easier acccss
"Emergency Procedures" Sectiòn has been fumished prcsent an insta¡t ¡efe¡ence to the section. P¡ovisions for expansion of certain paragraph numbers, lìgurã numbers, being left blank intentionally.
tìe item with a,.lìnger-tip" bccn with placcd a¡cad to irrl'oi¡l¡rtion handbook numbers and tlrlt have been pages
of
rnuy a red tab divider made noted tab the
5c to by ai
ISSUED: JUNE 18, 1976
REPORT: VB-790
l-l
SECTION
1
GENERAL
PIPERA'
RAFTCORPORATION
PA-28.I8'. -ITEROKEE ARCHER
II
I
Wi¡g A¡ea (sq. ft.)
Min. Turnirg Radius
(ft.)
(from pivot Point to wingtiP) l7G0
30.0
REPORT: VB-790
l-2
ISSUED: JUNE
I8, 1976
PIPE-R AJRCRAFT
PA-28-181, cI ,oRATIoN
CHEROKEÈ;
oncnrn
n
. rJ
ENGINES
(a)
(b)
Numbe¡ of
Engines
EngineManufãcrurer lÐ Engine Model Number
Rared Horsepower t? Rared
Bore
Speed
(inches)
(rpm)
(e)
S¡¡oke (inches)
(U
Displacemenr icubic i¡ches)
Uompression Rado
C)
Engine Type
15
PROPELLERS
(a)
(b)
(c)
Number of propellers
Propeller Manufacturer
Model
(0)
(e)
(f)
Numbe¡ of
Blades
PropelJer
(l)
Diameþ¡ (inches)
Maximum
(2)
Minimurn
Propeller Tlpe
(a)
(b)
(c)
(r)
(2)
(3)
Minimum
Ocune
Specified Ocune
Altemare
Fuel
I.
îTL
(a)
(b)
Oil Capaciry (U.S. euaru) urt Specificarion
+Serial nos
2 g_ 7j gÐt thmugþ
2g-77 9l}fJ7.
nos. 2g-?g90001 and up.
ISSUED: JTINE tE,
REVISED:
JUNE &
1976
1990
SECTION
GENERA
-
O-36GA4A o¡
Lycomin
0-360_e¿¡ l8r
2'701
5.12:
4.37:
361 .0
,, Four Cylinder,
Opposed,
oir..,
jnlj
Ai¡
Cooled
Sensenich
76EM8S5{-60r or 76EM9s5462**
I
2
76
76
Fixed Pirch
50
-J.8--
I 00/l 30 Green
100/130
Green
_ Refer ¡o latesr issue of
Lycoaing lns¡¡ucrion No.
1070.
_ Refer to laÈ$ issue of
8
Lycoming Insrrucrion No.
1014.
REPORT: y8.790
1.3
SECTION I
GENERAL
PIPER
¿
ìRAFT CORPORATION
PA-28-18r, .IHEROKEE ARCHER
(c)'
Oil Viscosity per Average Ambient Temp. for Staning
MIL-L.60828
Mineral
SAE Gr¿de
(1)
(2)
(3)
(4)
(s)
(6)
(7)
All Temperaru¡es
Above 80'F
Above 60'F
30'F to 90'F
0'F to 70'F
0'F to 90'F
Below'10'F
-60
50
40
30
20w-50
20
When operadng remperatures overlap indicared ranges, use the lightel grade oil.
MIL-L-22851
Ashless Dspenan¡
SAE Grades l5W-50 or 20W-50
60
40 or 50
40
30,40 or 20W-40
20W-50 or 15W-50
30 or 20W-30
tr
1.11 MA)qMI.TM IVEIGHTS
UTILITY
2130
2130
0
[s
Maximum Taleoff Weight
Qbs)
Maximum Landing Weight (Ibs)
Maximum Weighs in Baggage Comparunent
1.13 STANDARD AIRPLANE IVEIGHTST
(a)
Standard Empty Weight 0bs): Weigh¡ of a s¡a¡rda¡d airplane including unusable fuel, tull operating fluids and ñ¡11 oil
(b)
Maximum Useful Load (Ibs): The difference berween the Maximr¡m Takeoff Weighl and rhe Standa¡d Empty Weight r,15 BAGGAGE SPACE
(a)
Compamnent Volume (cubic feet)
O)
En¡¡y Wid¡h (inches)
(c)
Entry Heigh (inches) r.17 SPECIFIC LOADINGS
(a)
Wìng Loading
Qbs per sq
O)
PowerLoading Qbsperhp) ft) r4 16
1r34 r5.0
14.2
24
))
20
+These values are approximale
Standard Empry Weighr value specifìed.
and may vary from one aircrafi to and Useful Load value ro b€ used ano¡her. Refe¡ to Figure 6-5 for the for C.G, calculation for the aircraft
REPORT: YB-790
l-4
ISSUED: JLINE 18' 1976
REYISED: JIJNE
I'
1990
PIPER AIRCR,A¡'T CORP/
PA.2Å.181, CHEROKEE Ä
\TION
.HER
II
SECTION I
GENERÀL
1.19 SYT{BOLS, ÀBBREVIÄTIONS AND
TERMINOLOGY
. -Tlle
following defi¡itions are and those which may be
of
symbols, ofadded abbreviations operational and ter¡ninology used throughout significance to the pilot.
the
(a)
Gene¡al Airspeed Terminology ald Symbols
I
I
c¡s
Calib¡ated ,{irspeed means the indicated speed
of ar
aircraft, co¡¡ected equaJ for position and instrument er¡or. Calib¡ated to true airspeed in sta¡dard atmosphere at sea level.
airspeed is
KCAS Calib¡ated Airspeed expressed in "K¡ots."
GS Ground Speed is the speed of an airplane relative to the ground.
IAS Indicated Airspeed is the speed of an ai¡c¡aft as shown on the airspeed i¡dicator published when corrected for instrument erro¡. IAS values in tiris handbook assume zero inst¡ument er¡o¡,
KIAS
Indicated Airspeed expressed in "Knots."
À{ }lach Numbe¡ .is the ratio of true airspeed to the speed of sounJ.
TAS True Airspeed is the airspeed
ai¡
wlúch of an airplane relative to undisturbed
is
the CAS cor¡ected
for
altitude, Lemperature and compressabilì ty.
Y rL
V¡¡/À4¡¡ vNo
vs
vso
Va lr,f aneuvering Speed is the rnaximum speed at which application of ftrll available aerodynamic cont¡ol will not overstress tite airplare.
Maximum Flap Extended Speed is the higlest speed permissible with wilg flaps in a prescribed extended position.
Neve¡ Exceed Speed or Mach Number is the speed limit rhat may not be exceeded at any time-
Itfaximum Structu¡al Cruising Speed is the be exceeded except speed that should not in smooth ah and then only with caution.
Stalling Speed
or
the minimum steady flight speed at whiclt the airplane is controllable.
Stalliitg Speed or the minimum steady flight speed at \yììich the airplane is controllable in the landing contìguration.
Best Angle-of-Climb Speed greatest gain
is the
airspeed which delivers the
of
altitude
in t¡e
shortest possible horizontal dista¡ce.
Best Rate-of-Climb Speed
is
the airspeed wjt.ich delivers greatest gain in altitude in tite shortest possibte time.
tl.ìe
ISSUED: JUNE 18, 1976 REPORT: VB-790 t _<
SECTION
1
GENER-AL
PIPER
A
'RAFT CORPORATION
PJ4,-28'18. JHEROKEE ARCHER
(b)
Meteorological TerminologY
ISA lnternational Standard Atmosphere in which: tr
OAT
Indicated P¡essu¡e
Altitude
Pressure
Altitud e
Sta tion Pressure
Wind
Outside
Ai¡
TemPeratu¡e
is the
free
ai¡
static temPe¡ature' oUtain"¿ eithe¡ f¡õm infìigþt temperature meteorological sources, adjusted indications or ground
for
instrument
erro¡ '-l
compressibilitY effects.
The number actually read suUsc.le has been lrom an altimeter when the barometric s.i to 29'92 inches of mercur)' (
I 0 I
3'2 millibars)' evel pressure (29.92
i¡'
Hg)
It
is the indicated
Pressure
ínstrument erro¡.
In
this a¡e assumed to be zero.
Actual atmospheric pressure at field elevation'
The
wi¡d
velocities handbook a¡e components
to
recorded be as variables u¡derstood as of the rePorted winds.
the on the chârts headwind
of
tlìis
or
tailwind
REPORT: \/B-?90
l-6
ISSUED: JUNE
l8'
1976
REVÌSED: N'I^'RCH 30' I984
PIPR, AIRCRÄFT
PA-æ-l I
CORP
\ÎON
I,
CEEROTTF .A;Ji-ffiR tr
SECTION
1
GÐ.[ER.AI
(c)
Power Terminology
Taleoff
Power
Maximum power permissible fo¡ taleoff.
Måximu¡r
Continuous
Maximum power permissible
Powe¡ continuously during flight.
Maximum Oimb
Powe¡
Maximum power permissibte during climb.
Maxi¡num Cmise
Powe¡
Maximum power permissible during cn:ise.
(d)
Engine lnsEuments
EGT
Gauge
Exhaust Gas Temperah:re
Gauge
(e)
.A.irplane Pe¡fo¡mance and Flight planning Terminology climb
G¡adient
The demonst¡ated a climb,
to
ratío of the change in height during a portion of the horizontal distanðe trave¡-sed
i¡
the same time interval.
DemonsFated
Velocity crosswind
The demonst¡ated crosswind c¡osswind component velocity rot wrrich
is
the
"ãequatJcÀuot velocify of the
of
the aþlane certification tests.
Äccelerate'Stop
Dista¡ce
The and, distance required to assumiag failu¡e
of
an an airplane to a specilied speed engine at ihe insta¡t that attained, to bring the airplane to e stop.
speâd
.is
Route
Segrnent
A part geogr_
of
a route. can be established.
Each aphical location; e¡d
of
that part is or (2) a point af which identihed a by:
(l)
defnite ,ã¿iò i.i, a
ISSUED: JUNE 18. 1976
REVISED: MARCH 30. r9B4
REPORT: v8.790
l-1
SECTION
1
GENER.AI, pü,ER AJP.ÈAFr CORPOR A'TION
PA.2&I8I
IEROIGE ARCHER
II
(l)
Weight a¡d Balance Terminology
Reference Datum
An imagi¡a¡y measu¡ed vertical plane f¡om for balance PurPoses.
which all horizontal distances a¡e
Station
A location aJong the airplane fuselage distarice f¡om the ¡eference datum' uzually given
in
terms of
Arm
Moment
Center of GravitY
(c.G.)
The horizontal distance rraviW
(C.G') of an item.
from the rpfe¡ence datum to the centerof
The product
niåri*t of
the wei8ht divicled
by a of
ari const¡¡t item multiplied
is
used
to
by simplify
its
arm' balance
àJcr¡ations bv ¡educing the number of digits')
The point at which an
aþlure
would balance
if
zuspended' lts
ñil;
i¡om the ¡eference datum is found by dividi¡g the lotal moment by the total weigþt of the airplare'
C.G..A'rm
C.G' Limits
The arm obtained dividing by adding the airplane's individu¿l moments a¡d tìe sum by the total weight.
The ext¡eme ænte¡ of g¡avity locations must be operated at a given weight.
within which the aþlane
Us¿ble Fuel
Unusable Fuel
Sta¡da¡d EmPtY Weight
Basic EmPtY
ìileight
Fuel available for flight planning'
Fuel
æmaini¡g after accordan ce
a
n¡nout test has been completed ia with governmentaJ regulations' lVeight
of a
standa¡d airplaae including unusable operating fluids and fi¡ll oil'
fuel'
full
Sta¡da¡d empty weight plus optional equipment'
PaYload
Useful Load
Maximum RamP Weight
Maximum
Weiehr
Takeoff
Weight ofoccupants, cargo ard baggage'
Difference between and basic takeoff emPty $'eight.
weight, or ramP weight
if
applicable'
Maximum weight approved weight
for
ground ma¡euve¡' of start, taxi and nrn up fuel,)
(It
i¡cl
Maximum r¡/eight approYed for t¡e sta¡t of the ta-keoff run'
Maximum
Weight
Larding Maximum weight approved for the landing touchdown'
Maximum weightexclusive of usable fuel'
Maximum Zero Fuel
Weieht
ISSUED: JUNE 18, 1976
REPORT: VB'790
1€
PIPER'.AIRCRAFTCO.RP' \TION
PA.2&1 8I, CHEROKEE A-. -IIER
II
T}TIS PAGE IIüENTIONALLY LEFT BLANK
ISSUED: JUNE 18, 1976
SECTION
1
GENERAI
PIPERA]
i,r-zgtei,
\.AFTCORPORATION
dERoKEE ARcHER
II
T1TIS PAGE INTENTIONALLY LEFT BLANK
REPORT: YB'790 l
-10
ISSUED: JUNE t8, 1976
PIPER áJRCR,A'FT
CORPC
TION
PA-28-181, CffROI.FF ARLdER tr
SECNON
GENERAL
I
1.2T CONVERSION FACTORS
MIJLTIPLY
ET
acles
0.404.7
43s60
0.001 5625 atrnæpheres
(atn)
16
29.92
1.0133
1.033
14.70
2tL6 bals
(ba¡)
0.98692
14.503768
British Thermal
(BTIÐ
Unit
0.2519958
cøtimeters
(cm)
0,3937
0.032808
centimeters mercury at
(cm
Hg) of
0.013 16
OoC
0.3937
0.1934
27.8s
13 5.9 5 centimeters second per
0.032808
(cm/sec.)
1.9685
0.02237
cubic
centimeteß
0.03381
(cm!)
0.06102
3.531 x l0-5
0.001
2.642
x
104 c. feet
(cu.ft.)
28317
0.028317
112E
0.037037
1.481
28.32
TO OBTA]N ha sq. ft.
sq. mi.
cm Hg in.Hg
ba¡ kçlcm" lb./sq. lb./sq. in.
ft.
aün.
lb./sq. in.
kecal
ùt.
ft.
atm in. Hg lb./sq. in.
lb./sq. kelm' ft.
ft./sec.
ft.imin.
mPh lL oz.
cu. in.
cu. ft.
I
U.S. cal.
cm¡ m3
I cu. in.
cû yd.
U.S. gal.
cubic feet per
(cu minute 0.472
ft./min.)
0.02831'l
I /sec.
mr/min.
MULTPLY cubic inches (cu.
i¡.)
cubic metes (m 3
)
BY TO OBTAIN
16.39
1.639
5.787
0.554
l x
10 x 10{
{
0.01 639
4.329
x
10'3
0.01132
cm3 m3 cu. ft.
f7. oz.
I
U.S. gal.
U.S. qL
61024
1.308
35.3t47
264.2
cu.
i¡.
cu- yd.
cu. ft.
U.S. gal.
cubic meters minute per
(m3/min.) cubic yards
(cu yd.)
35.3147
1'l
0.'t646
202 cu. ft./min.
cu. ft.
m3
U.S. gal.
degrees
(arc)
0.01 745 radia¡s degrees per second
(deg./sec.)
0.01745
radians/sec.
d¡ams, fluid (d¡. fl,) drams, avdp.
(dr. avdp.) feet
(ft)
0.125
0.0625
î1. oz.
oz. avdp.
30.48
0.3048
t2'
0.33333
0.0606061
1.894
1.645 x 10{ x l0¿ cm m m.
yd.
rod
ML
NM fæt per minute
(ftlrnin.)
0.0 r 136
0.0t 829
0.508
0.005 08 mph km/hr.
cm/sec.
m/sec.
ISSUED: JLJNE 18, 1976
REYISED: IULY 12,1977
REPORT: VB-790
l-l
I
SECTION
I
GСER,A'L
PIPER
AI-
.RAFT
CORPOR,A'TON
PA.2E18i
JEROKEEARCHERII
MULTIPLY BY TO OBTAIN feet per second
(ft/sec.)
0.68r
8 t.097
30.48
0.5921
mph kmfu.
cm/sec.
kts.
foot-pounds
(ft'-lb') 0.138255
3.24
x
l}a
m*g kg-cal foot-pounds Per minute
(ft.lb./min.)
3.030 x 10'5 foot-pounds
Per second
(fl-lb./sec.)
1.818 x 10s hp hp gallons, Imperial
Clmperiat eal.)
277.4
1.201
4.546
cu. in.
U.S.
Cal.
I gallons, U.S. dry
(U.S. câ]. dry) eallons, U.S.
(it.S.eal.) liquid
268.8
1.556 x
l0'r
t.lø
4.405
cu. ln.
cu. ft.
U.S. gat.
I
231
0.t337
4.951 x t0-3
3't85.4
3.785 x l0-3
3.785
0.83268
t28 cu. ln, cu. ft.
cu. yd.
cm3 m3
I
Imperial gal, fl. oz.
ullons per acre
(gal./acre)
9.353
I /ha rams G) fams per centimeter
(elcrn)
F¿ms per cubic centimeter
(s/"qtt
)
0.001
0.3527
2-205
x l0''
kg oz. avdp.
tb.
0.1
6.721
5.601
x
l1-z x
10'3
I
000
0.036 l3
62.43
kg/m
1b./fL lb.iin.
kglm'
Ib./cu. in.
lb.icu. ft.
MULTIPLY
BY hectares
(ha)
2'471
107639
10000 horsepirwer
(hP)
33000
550
'
76.U
l'014 horsepower, metric
75
0.9863
inches
(i¡-) 25.40
zs40
0.0254
0.08333
0.02'7771 inches of at
0
"C mercury
(i¡.
0'03342L
Hg)
0.4912
70.73
345.3
2'540
25-40 inch-pounds
(in.lb.)
0.01 1521 kilograms
(ke)
2.204622
35'21
1000
kilogram-calorÍes
3.9683
(kccâI)
3087
426.9
hlograms per meter (kg/m¡ cubic
0.06243
) 0'00I kilogtams
Per 0'892 hecta¡e (kg/ha) kilograms pet squa¡e 0.9678
centimeter (kel cm?
)
28.96
l4'22
2048
TO OBTAIN acres sq. ft.
m2 ft.-lb./min.
ft.-lb.i sec, m*g/sec, metric hp mJcg/sec.
hp mm cm m ft.
yd.
atn lb./sq. lb./sq. kg/m' in.
ft.
cm Hg mm Hg m*g lb.
oz. wdp.
c
BTU ft.-lb.
m*g
lb./cu. ft.
glcm3 lb./acre aEn in. Hg lb./sq. in.
lb./sq. ft.
REPORT: VB-790
t-tz
ISSUED: JIJNE 18, 197ó
REVISED: FEBRUARY 28, r979
PIPR.,A.IRCRÀFrcoRP( iTIoN
PA-28.1 81, CEEROICEE
/A,R'Cgrn
u
SECI]ON
1
GENERAL
MULTTPLY
RY
-
kilograms per meter (kglm
TO OBTAIN
2.g96
1.422 x
I
O
-i in. Hs
x l0-3
lu.lrol
0.2048 lb./sq'. irr.
rt.
kilometen
(km)
l
x
10.5 cm
3280.8 ft.
0.6214 mi.
0.53996
NM kjjômete¡s
perhour
'hr.)
O.9ll3 ft./sec.
s8.68
ü.i'".lil.
0.53996
kt
0.6214 mph
0.27j78 mfsec.
16.67 m/min.
k¡ots (kt) I
¡autical mph
1.689 ft./sec.
l.l516 statute mph
1.852 km/h¡.
51.48 m/sec.
ljten
(l)
1000
61,02 cmr cu. in.
0.03531 cu ft.
33.814 ft. oz.
0.264172
U.S. eal.
0.2200
Impeld
1.05669 qt.
eat.
liten per
(l/hâ) hectare
13.69
o.l37
f7. oz.lacre
ga.l./acre liten per
(l/sec.) second
2.12
cu. ft./min.
metæ (m) meter-kilogram
(m-ke)
7.23301
86.798
frlb.
in.-lb.
MULTIPLY meters per minute
(m/min.) rneters per second
(m/se¡.) mlc¡ons miles statute (mi.) rnilæ per
(mph) hour
BY
TOOBTAIN
0.06 km¡ú.
3.280840
fr./sec.
196.8504
ft./min.
2.237 moh
3.6
rri/t..
3.937 x
lO'5
in.
5280 ft.
1.6093 km
1609.3
0.8684 m
NM miles per squa¡e hour
(m/h¡. sq.) milliba¡s millimeten (mm) millimeters of mercury at
(mm Hg)
0'C nautical miles
0.¡M) ounces, avdp.
(oz avdp.) ounces, fluid
(fl. oz.)
2.151
ft./sec. sq.
2.953
x
lo-':
i¡.
Hg
0.03937 in.
0.03937 in.
Hg
1
6080 ft.
.1 51
6 statute mi.
1852 m
1.852 km
28.35
t6 o dr. avdp.
8
29.57
dr. fl.
cm
I.805
0.0296
I cu.
0.0078
3 i¡.
U.S. gal.
ISSUED: JUNE 18, 1976
REYISED: FEBRU,A,Ry 2t. rg7g
REPORT: VB-790
1-1 3
SECTION
1
GENER.AI.
PIPER
/4"
IAFT CORPORÂTION
iÃ-ãsrsr,
wEERoKEE ARcITER tr vÍULTIPLY runces, fluid
Per acre (f1. oz.l
ac¡e) pounds (lb.)
BY
0.073
o.453s92
453.6
3.108 x 10-' kg siug l.l2l
kc/ha pounds per
(lb.i acre) acre pounG
Per cubic foot 0b.icu. ft.) pounds per cubic i¡ctr Ob./cu'
i¡.)
pounds
Per square foot Ob./sq' ft.) pounds Per inch þsi or square lb.isq. in.) quart, U.S. (OL) radians radians Per second
(radians/sec') revolutiors (rev') revolutions Per minute (rPm or rev./mi¡-) revolutiors Per second
(rev./sec') t6.02
kg/m' t128
27.68
lb./cu. glcm3
0.1 41
4
4.88243
4.725 x lOa
i¡.
Hg kelm2 atm
ft'
s.l7l
5
2.036
0.06804
0.0689416
703.1
0.94635
57.'149
57.30
0.1592
em Hg in. Hg aün ba¡ kelm'
I cu. m.
deg.
(arc) reY,
57.30
0.r592
9.549
6.283
0.1
047 deg,/sec.
rev./sec.
rpm
.radians
radians/sec.
6.283
¡adians/sec'
MULTIPLY
BY TO OBTÀIN
¡od slug souare
(cm') centimeten squa¡e feet (sq.
ft')
16.5
5.5
5.029
ft.
yd.
m
32.114
0. I 550
0.001 076 tb.
sg.in.
sq. ft.
929
0.092903
t44
0.il11
2.296
x
10's cm2 m2 sq.in.
sq.yd.
åcres square
(sq. inches in.)
6.4516
6.944
x
lQ'3 cm2 sq. ft,
0.3 86
I sq. m¡.
square kilometers
(krn') squa¡e meters
(mz) l 0.7639
Lt96
0.0001
I square miles
(sC.mi) 2.590
&0
sq. ft.
sq.yd.
ha km2 acres sq.yd' square rods (sq. ¡ods) 30.25
square yards (sq.Yd.) 0.83 6
I
9
0.03305 79 ya¡ds (yd.) 0.9r44
JO
0.1 8l 8l 8 mz sq. ft.
sq. rods m ft.
in.
¡od
REPORT: YB-790
1-14
ISSUED: JLINE 18, 1976
REVISED: JULY 12'1977
SECTION
2
LIMITATIONS
SECTION
2
LIMITATIONS
2.1
'
2
2.t
2.'7
2.9
2.t1
2.13
2.15
2.17
t
ro
2.2r
2.23
General
Âirçeedlimitations
Àirspeedlntlicato¡Ma¡kin$..,,
Powe¡Plantli¡nitations..
Por¡¿e¡Plantlnstn¡mentMa¡kin$
Weight
Limib
Cenþ¡ofG¡avitylimits
. . .
.
Maneuve¡Limits
FlightloadFactors
Typesof0perations.,
Fuellimltations
....
Ptaca¡ds ..:...
........2-l
,,.,..2-I
....2-2
,.,.....2-2
. . . . , .
.
Z-3
2-3
...,
24
..,.,,..
24
.,,...24
,.,.2-5
....2-5
.......2-7
PIPER AI RCR.A,FT CORPr^
PA.28.ISI, CITEROKEEÀ
-
{TION iIER
II
SECT]ON 2
LIMITATIONS
SECTION 2
LIMITATIONS
2.1
CENERAI
This section provides the-"FAA Approved"-operating Iimitations. instrument markings. color coding and basic placards necessary for the operation of the airplane and its systems.
This airplane must be ope;ated as a normal completè handboók.
or utility
category airplane in
Iting limitations stated in the fo¡m of placards and markings a¡d those given in compliance wjth the this section and this
Limitations associated
with
those optional systems and equipment which require ha¡dbook supplements ca¡ be found in Section 9 (Supplements).
23 AIRSPEED LI]\IIT,A,TIONS
I
SPEED
Neve¡ Exceed
Speed any operatìon.
(V¡¡
) - Do not exceed this speed in
À4aximum exceed
Structu¡al Cruising Speed this speed except
(V¡q).
Do not
i¡
smooth air and then onJy with caution.
Des.ign Marreuvering Speed (Vo ) - Do not make full o¡ abrupt control movements above this speed.
At 2550 LBS. c.W.
At
1634 LBS. c.W.
KIAS
154
125
.l
13
89
CAU-TION l4aneuvering speed decreases
at
üghte¡ weigJrt as tjre effects of
aerodynamic fo¡ces
become
mo¡e
pronounced. Li¡ea¡ interpolation
may be
used
fo¡
inte¡mediate gross we.ights.
It{anuevering speed should
not
be exceeded whjle operatíng in rough air.
KCAS
148
l2l
ilt
89
Nfaliimum Flaps Extended tlús speed r¡,ith the flaps
Spe€d extended.
-
not exceed t02 100
ISSUED: JUNE 18, 1976
RE\/ISED: I\'IARCH 30. 1984
REPORT:
.\rB-?90
7-l
;ECTION 2
]TúITATIONS
¿.5 ÀIRSPEED INDICATORM.A.RKINGS
À{ARKING
Red Radial Line (Never Exceed)
Yellow A¡c (Caution Range - Smooth Ai¡ Only)
Green A¡c (Normal Operating Range)
Wlúte A¡c (FlaP Down)
2.7 PO\{ER PLANT LIMITÄTIONS
(a)
Number of Engines
iui rngi""
Manufacturer
(c)
Engine Model No.
(d)
Eneine OPerating Limits
(l)
Maximum HorsePower
iZi
t'l.ximum Rotation Speed
(3)
Maximum Oil TemPerature
(e)
Oil P¡essu¡e
Minimum (red line)
(RPM)
Maximum (red line)
(l)
Fuel Pressure
Minimum (red line)
Maximum (red [i¡e)
(g)
Fuel Grade
(AVCAS ONLY) (minimum octane)
(h)
Number of ProPellers
(i)
ProPellerMa¡ufacture¡
ú)
ProPeller Model
(k)
ProPeller Diamete¡
Minimum
Maximum
0)
Propeller Tolerance (static
Permissible throttle setti¡g)
RPM at maximum
No additional tolerance permitted'
PIPER
AI'
'AFT CORPOR.ATION
PA.28-181, -IEROKEE ARCHER tr
IAS
(ls4 KTS)
(12s KTS to I54 KT5)
(55 KTS to 125 KTS)
(49 KTS to 102 KTS)
I
LYcoming
0360-A4A or 0-360-A4M with carbu¡etor setti¡g
I G3 87 8
180
2't00
245'F
25 PSI
90 PSI
.5 PSI
100/ 130
8 PSI
- Creen
I
Sensenich
+
76EM855-G60
++ or 76EM8S5-G62
76 IN.
76 tN.
Not above 2425 RPI
Not below 2325 RPI:
Not above 2375 RPM*+
Not below 2275 RPM** fserial nos'
28-7']9OOO| through 28-779Ð601'
,.!.¡¡¡ nos. 28-7890001 and uP'
REPORT: \¡8-790
ISSUED: JUNE
I8' t976
REYISED: MARCH 30' 1984
PIPER
Pi4,-28-l
áJRCRJIT
81,
CORPC
TION
CHEROI(E
Äi
¡ER tr sEcTloN 2
LIMTTATIONS
2.9
POWER PLANT INSTRTJMENT MARKINGS
(a)
(b)
(c) d)
Tachometer
Green .4,¡c
(Normal Operating Range)
Red Line (Maximum Continuous Power)
Oil Temperature
G¡een A¡c (Normal Operating
Range)
Red Line (Maximum)
Oil hessu¡e
Green
.A,rc
(Normat
Operating Range)
Yellow.A,¡c (Caution Raage) fldle)
Red Line (Minimum)
Red Line (Maximum)
Fuel P¡essu¡e
Green Ä¡c (Normal Operating Range)
Red Line (Minimum)
Red Line (Maximum)
2.II
WEIGHT LIMITS
(a)
(b)
Maximum Weight
Maximum Baggage
NORMAL
2s50 LBS
200 I.BS
NOTE
Refe¡ to Section 5 (Performance) fo¡ maximum weight by performance.
a_s limited
500 to 2?00 RPM
27OO RPM
75'to245'F
245"F
60 PSI to 90 PSI
25 PSI to 60 PSI
25 PSI
90 PSI
.5 PSI to
8 PSI
.5 PSI
8 PSI
UTILTTY
2r30 LBS
I
O LBS
ISSUED: JUNE 18, 1976
REVISED: MAY
23, 1980
REPORT: VB-790
2-3
SECTION 2
LMITATIONS
2.13 CENTER OF GRAWTY LIMITS
(a)
Normal Category
Weight
Pounds
2550
2050 (and less)
Forwa¡d lnches
Limit
Aft of Datur4
88.6
82.0
(b)
UtiIitY Category
Weight
Pounds
I zo5o (a¡d less).
I
zrro
Forwa¡d lnches
Limit
Aft of Datum
82.0
83.0
PIPERÄ
RAFTCORPORATION
PA-2&I 8¡. -ffiROKEE ARCHER
II
Rearwa¡d
Inches
Limit
Aft of Datum
93.0
93.0
Rea¡ward lnches
Limit
Aft of Datum
93.0
93.0
NOTES
Str¿ight line va¡iation between poirts given'
Tlte datum used is ?8,4 inches ahead the inboa¡d intersection of the wing leading edge of the st¡aight and tapered section' at
Itistheresporsibilityoftheaþlarreow¡erandthepiJottoi¡su¡e thât the is properly loaded' See Section 6 (Weight a¡d
Balance)
2.1
5 MÄNEI.I\TER LIMITS
(a)
Normal Category -
All acrobatic maneuvers including spins prohibite-d-'
iul
Utility Categãry-App¡oved mareuvets for bank angjes exceeding
60''
SteeP
Lazi
Tums
Eishts chandelles
Entry Speed
I 13 KIAS
I 13 KIAS
I 13 KIAS
2.17 FLIGI T LOAD FACTORS
NORMAL
UTILITY
3.8
G
4.4 G
No invefed maneuvers aPProved
ISSUED: JIJNE 18, 1976
REVISED: MAY 23' l9t0
PIPERAIRCR,A,ETCORPI
PA-28-1
.
NON
81, CEEROKEE,AT--"IER
tr
SECTION 2
LIMITATIONS
2.I9
TI?ES OF OPER,A,TION
_
_
The aþlane is approved for the following operations when
FAR I35.
equipped
i¡
acco¡dance with FAR
9l
or
(a)
Day V.F.R
(b)
Nisht v.F.R
(c)
Day I.F.R
(d)
Nisht LF.R.
(e)
Non lcing
2
.:T'EL LI}ÍITATIONS
(a)
Total
(b)
Capacify
Unusable Fuel
(c)
The unusabþ fuel as 1.0 gallon for tå-is aþlane has been determi¡ed in each wing in c¡iticat flieht attirudes,
Usabte Fuel
ïhe usable fuel in this aþlane
24.0 gallons in each wing h-as been determi¡ed
æ
5O U.S, GAL
2 U.S, GAL
48 U.S. CÄ.L
ISSUED: JUNE 18, 1976
REPORT: VB-790
2-5
PIPERÄ
RAFTCORPORATION
PA.Z&I 8¡,
-EEROKEE ARCHER
II
THTS PAGE INTENNONATLY LEFT BLANK
ISSUED: JUNE 18, 1976
ITPERAIRCRAFTCORPOh iON
PA-28-r 8I, cmRoKEE
Anc¡l¡ñ u
SECTION 2
LIMITATIONS
2.23
PLAC.A.RDS
ln full view of the pilot:
.
OR
TH
OF
S
AND
PLé.CARDS
OPERATION
AS
ON THIS
A
UTILITf
är#i*iå
+ilB Hi'"'lt'
NO
NoRMA.l.
P R
ACROB4TIC oHIB
F o
MANEWERS
R No RMAL ANõ
ARE
.tr¡Iuiv
-sÞiñí nï.,
FOR ;ft liiiÏ
Ij:ü,,"":the pilot, one of the following takeoff checklists a¡d the foilowing landing check tisr
Fuel on p¡ope¡
Elect¡ic fuel te¡k pump on
Engine gauges checked
Flaps - set
Ca¡b heat off
Fuel on proper tank
Electric fuel pump on
Engine gauges checked
Ft-..ç - set
i
heat
ofl
TAKEOFF CHECK LIST
Àlixtu¡e set
Seat backs e¡ect
Fasten belts/harness
T¡im tab - set
Con t¡ols - f¡ee
Doo¡ - latched
Ai¡ Conditioner - off
TAKEOFF CHECK LIST
Mixtu¡e set
P¡imer locked
Seat back e¡ect
Fasten belts/harness
Trim tab - set
Cont¡ols - free
Doo¡ - latched
Ai¡ conditioner - off
LI.NDING CHECK L]ST
Fue.l on proper tank li{ixture rich
Elect¡jc fuel pump on
The
"AlR
COND OFF" conditioned aircraft onJy.
sear back
e¡ect
iiç;;i,!i3#.*s
Ai¡ Conditioner - off max') item
in
the above takeoff and landing check lists is mandatorv
fo¡
air
TSSUED: JUNE 18, 1976
REYISED: JULY 3, 1978
REPORÎ: VB-790
2-7
SECTION 2
LIMITATIONS
PIPERAi
IAFTCORPORATION
PÄ-2&1 8TT-TIEROKEE,ÀRCHER tr
In
full view of tJre piloi,
i¡
t¡e area of tire air conditioner control installed: panel when the air conditione¡ is
..WARNING
_
AIR CONDITIONER MUST BE
NORMAL TAKEOFF CLIMB
OFF
PERFORMANCE.''
TO INSURE
Adjacent to uPPer door latch:
..ENGAGE
LATCH BEFORE FLIGHT.''
On i¡side of the baggage comPartment doo¡:
..BAGGAGE MAXIMT]M
2OO
LBS''
..UTILITY CEiECONV
OPERÄTION
- NO BAGGAGE OR
AFT
PASSENCERí ¿'I_'OW¡N' NORMAL CATEGORY OPERATIO\
.
SEE
PILòT;IbPEN¡'TTNG
HANDBOOK WEIGHT AND
BALANCE SECT¡O TON S¡CCECE AND
AFI
PASSENGER
LIMITÀTIONS.''
In full view of the Pilot:
..MANEWERING
SPEED 113
KIAS
AT
2550 LBS' (SEE
P.O.H.)"
..L]-IILITY
CATEGORY
ALLOWED.''
OPERATON - NO AFT PASSENGERS
..DEMONSTRATED
CROSS WIND CON{PONENT
-
17 KTS''' on the instrument panel in full view of the pilot when the oil coole¡ winterization kit is installed:
..OIL
WHEN
COOLER WINTERIZATION PI.ÀTE TO BE
AMBIENT TET{PERATURE EXCEEDS
5O.F'''
RET{OVED
,f
- ;t)
In full view of the Pilot:
(1)
(2)
..UTILITY
CATEGORY OPERATION
ON LY.
NO
AFf
PASSENGERS
ALLOVED.
IðriösAîñ
MANEWERS ARE LIMITED
To rHE FoLLowING:
ENTRY SPEED
SPINS PROHIBITED
STEEP TURNS
LAZY EIGTTTS
C}IANDELLES
I ]3 KIAS
1] 3 KIAS
I13 KIAS
On the instrument panel in full view of the pilot:
"WARNING - TURN OFF STROBE
THROUGH CLOUD, FOG OR HAZE.''
LIGHTS WHEN TAXII¡ÑG
ñ'vìtrñriv
oF
orHER AIRcRAFT,
oR
DURING FLIGHT
ISSUED: JUNE 18,1976
REPORT: VB-790
1Q
TABLE OF
CONTENTS
SECTION
3
EMERGENCY PROCEDURES
Paragraph
No.
3.t
3.3
General
Emergency proåe¿uies
Engine
ô¡..t f¡.i :.
: .
Fire During Stari
'"
'
Engine Po-wer Loss In
Flighr
"":"'
.. ........
:::::::::::::::.::
Loss Of Oil Pressure..
.
Loss Of Fuel Pressure
Hìgh Oil
Alternator
. .
.
Temperature
Failure....
-. _.
Spin Recovery
Open Door
Carburetor lcing
.
.
EngineRoughnãss.....
Anrplified Emergency proced ures (Ceneral)
Engine Fire During
Srart
35
3.7
_1.9
3.tl
3 r3
3.r5
3.17
3.r9
3.2t
3.23
3.25
327
3.28
3.29
Eneine Roughness
.........
3
3 l
3
3
REPORT: \'B-?
PIPER .A,IRCRáFT
CORPG
PA.2&1
.-.,NON
8I, CEEROIGE,ÀRìÊER
tr
SECTION
3
EMERGE.ICY PROCEDURES
SECTION
3
EMERGENCY PROCEDURES
3.I
GENER,AI, pr'":ded by this-section. All of requircd (FAA regulations)
tì
p
The recom.mended procedures re)sn reration led.
of
the airplane for coping as determined with various types by the operating of emergencies and
ãnd
-däsign crirical siruarions are features rno,. n...rr^.y of the airplanJ
ioi
aie
Emergency procedurcs associated supplements are with thosc optional systems and equipment which require handbook
lrovi\ecrion
9 (Supplemenrs).
.
The first
Po-rtion action sequence of thisìection for critical situatíons consists of with linlc an abbreviated emcrgencv check emphasis on thc operat-ion list systems.
which supplies an
The remainder
of
the s.ection is devoted to amplified emergency procedures containing information ro provide the pilor wirh a more completi understand-ing ãf'rhe procedures.
addirional
.
These described. themselves procedures are suggested as but are not an emergencv an\e.
a substitute the best course of acrion for coping with the particular for sound judgment and common with the procedures given in this secrion and be prepared to sense. Piloti should condirion familiarize take appropriate action should
. .
Most basic emergency procedures. such as power otf landings.
Although these emergencies are discussed here. this informarion but only to provide a source of reference and review. and to provide information on piocedures which nor Ihe same
for all
aircraft.
It is
suggested periodicallv ro remain proficient in them.
that rhe
pilot ii
are a normal pan of pilor not intended ro review srandard ieplace rrainin-g.
iuch rrainin!.
aie emergenc!,procedures
ISSUED: JUNE
¡t.
1976
REVISED: MARCH 30.
1984
REPORT: vB-790
3-l
sEcTloN 3
EMERGENqY PROCEDURES
PIPERA
ÀAFTCORPORATION
PA-2&18¡, ¿'HEROKEE ÁRCHER
tr
THIS PAGE INTENTIONÁ,LLY LEFT BLANK
ISSUED: JlJl'¡E 18, 1976
PIPER AIRCRAFT COR?P
PA.28-I8I, CHEROKEE A,
-toN
IER
II
SECTION 3
EMERGENCY PROCEDURES
3.3
EMERCENCY PROCEDURES CHECK LIST
ENGINE FIRE DURING START
Starte¡
.
Mixrure
Th¡ottle
Electricfuelpump.
Fuelselector
Abandon
if
Iì¡e continues crank engine idle cut-off
.open
...OFF
.. ..,..OFF
If
power
is not
restored prepare for power off landing
T¡im fo¡ 76 KIAS
ENGINE POWER LOSS DURINC TAXEOFF
t.
*Ifìcient runway remains for a no¡mal landing, land straight ahead.
If
insufficient runway remains:
Maintai¡ safe airspeed
Make only shallow tum to evoid obstructions
Flaps as si¡uation requires
If
sufficient altitude has been gained to attempt a resla¡t:
Maintai¡ safe airspeed
Fuel
selecto¡
switch to tank
Elect¡ic fuel
Mixnrre pump
Carburctorheat
Primer.
contÀining fuel
. check ON
.....
checkRlCH
. . .. . .
.ON
...locked
If
power is not regained, proceed with power off landing.
ENGINE POWER LOSS IN FLIGHT
Fuel
selector .
switch to tank
Elect¡icfuelpump
Mi"ture
,retorheat
L,..,negauges
containing fuel
.
.....ON
...RICH
... ..
.ON
. .
..checkfo¡indication
Primer
of cause of power loss
.....checklocked
If
no fuel pressure is i¡dicated, check ta¡k selector position to be surc it is o¡ a tank containing fuel.
ìilhen power is reslo¡ed:
Ca¡bu¡elorheat
.
Elect¡icfuelpump
....OFF
.. ..OFF
POWER OFF LANDÍNC
Locate suitable l¡eld.
Establish spiral
1000 pattem.
ft.
above lìeld
at
downwind posirion for normal landing approach.
When fìeld can easily be ¡eached slow to 66 KIAS for slortest landing.
Touchdowns should normally be made at lowest possible airspeed with full flaps.
When committed to landing:
Ignition
Maste¡switch
Fuelselecto¡
Mixtu¡e
Seat belt and
hames
....OFF
.. .....OFF
..OFF
idle cut-off
. .
.tight
FIREIN FUGHT
Sourceoffi¡e..,
Elect¡ical fire (smoke in cabin):
Masterswitch
Vents
Cabinheat
La¡d as soon as prâcticable.
.. ...
.check
..OFF
. open
...OFF
Engine fìre:
Fuelseleclo¡
Th¡ottle
Mixture
Electic fuel
pump
Heatera¡ddef¡oste¡
P¡oceed with power off
. ....
..OFF
.
CI0SED idle cut-off check OFF
...OFF
l¡¡di¡e procedwe.
LOSS OF OIL PRESSURE
Land as soon âs possible and investigate cause.
Prepare for power off landing.
ISSUED: JIJNE 18, 1976
REVISED: JIJLY 3, 197E
RPORT: YÈ790
3'3
SECTION 3
EMERGENCY
PROCÐURES
PIPER./
]R.AFTCORPORATION
PA.aïIL
JHEROI(EE ARCHER
II
LOSS OF zuEL PRESSURE
Electric fuel
PumP
Fuel
selector ' '
'
' "
'ON check on full ta¡k
HIGH OILTHPER.ATURE
La¡d at nea¡est ai¡port and investigte
Prepare for Power off landing' the problem'
AITERNATOR FAJLURE
Verify failure neáuL elect¡ic¿l load as switch much as possible'
À;;;;t
cl¡cuit
breekers
Alt
OFF
" "
(fo¡ t checl
'rHlå';
If no ouÞut:
Alt switch
OFF
Reduce elect¡ical load a¡d land as soon æ practical'
OPH.I DOOR
If
both upper a¡d side latches are open, the door will trail slightJy open and ainpeeds will be ¡educed slightly.
To clo5e the doo¡
Slow
Cabi¡vents
Stormwi¡dow i¡
flight: aþlane to 87 KL{S
.......close
.."'@en
Ifupperlatchisopen
Ifsidelatchisopen
.
.. '.. ' '.I¡tch
. . . .'
pullonarm¡estwl-" moving latch hai to latched position
If both latches a¡e oÞen . latch side låtch then top latch
CARBURETOR ICING
CarburctorHeat'.. """ ON
Mixture '. Adjust for Max. Smoothness
SPIN RECOVERY
Throttle
Ajlerons
Rudder.
Conûol
Control
wheel
Rudder.
" "
' .
idle neutral
' . .
fulloPPositeto di¡ection óf
.
.
'
.
.full
¡otation forwa¡d neut¡al(when rotation stops)
wheel . . . .
.asrequired to smootNy regain level flight altitude
ENGINE ROUGHNESS
Ca¡buretorheat
. .....ON
If rouglmess conti¡ues after one mi¡: ca¡bu¡eto¡heat
Mixtu¡e
. " "oFF
....adjustformax.
smooth¡ess
....
'ON
ElectricfuelpumP
Fuel
selector
Engi¡egaugBs
tt¡as¡etósttit"h
.
switch tanks
. ' . ' . .
check
... '. "L"then"R"
then "BOTH"
If
operation is satisfactory on either one, contl on ihat magneto at ¡educed mixûrre to lust airPort.
power ard full "RICH
'
Prepare ior power off landing.
REFORT:
YÈ790
34
ISSUED: JIJNE 1E, 1976
REVISED: MAY 23' l9t0
)
PIPERAIRCR.{FTCORPO fON
PA-æ-l 81. CEEROKE .ÀREdER
tr
sEcnoN
3
EMERGENCY PROCEDURES
sEciloN
3
EMERGENCY PROCEDURES
PITER
A IAFT CORPORATION
PA.2&l II;'TEEROKEE A&CEER
tr
PIPERÂIRCRAFTCORP ITION
PÄ-28.18I, C}IEROKEE A,.JhER
II
sEcTtoN
3
EÀIERGENCY PROCEDURES
3.5
A-h{PLIFIED EMERGEI.{CY PROCEDU RES (GENERAL)
1.)te foUowing paragraphs are presented to supply additional information for the purpose ofproviding the pilot with a more complete understanding of the ¡ecommended cou¡se of action a:rd probable cause of a¡ emergency situation.
3.7
ENGINE FIRE DURING STÄRT is
Engine lìres during start are usually the result of overpriming. The first ettempt to extinguish the fìre to try to start tlìe engine and d¡aw the excess fuel back into the induction system.
If
a ll¡e is present befo¡e the engine has started, move the mixtu¡e cont¡ol to idle cut-off, open tlìe
;tle and c¡a¡k the engine. This is an attemPt to d¡aw the fi¡e back into the engine.
Ifthe engine has started, conti¡ue operating to try to pull the lre into the engire.
In either case (above),
if
h¡e the best available extemal means.
continues mo¡e than a few seconds, the fi¡e should be extinguished by
The fuel selectol valves should be
"OFF" a¡d
the mixture at idle cut-off exti¡guishing method is to be used.
if
a¡r exte¡nal lìre
3.9
ENGINE PO}YER LOSS DURING TÄ,KEOFF
The proper action to be taken if toss of power occurs rlurirtg takeoff will tlepcrt<J on llte circunìst¡¡Ì]cës of the particular situation.
If suflìcient¡unway remains to complete a normal landing, land straigltt ahead.
If
insufficient nrnway remai¡s, maintain a sâfe aírspeed a¡rd make only a shallow tum if necessary to avoid obstructiors. Use of flaps depends on the chcumstances. Normally, flaps should be fully extended for touchdown.
If
sufhcient altifude has been gained to attempt a restart, mairtain a safe airspeed and switch the fuel selector mixture to is another tank containing f]¡el,
"RICH." The ca¡buretor
Check heat should the Jlect¡ic fuel pump to
Ue i¡sure that it is
"oN"
and
"ON'; a¡¿ tfr. ptimer checked to insure that it is that the
locked'
I
If
engine f¿ilu¡e was caused by fuel exl¡austion, povr'er will not be regained after switching fuel tanks
.
, the empty fuel lines a¡e filled. This may ¡equhe up to len seconds.
check
If
power is not regained, p¡oceed with the Power Off Landing procedure (refer to the emergency list and pa¡ag¡aph 3.13).
ISSUED: JUI.-E 18, 1976
REVISED: JULY 3, 1978
REPORT: vB-790
3'7
SECTION 3
EMERCENCY PROCEDURES
PIPER
I
-R.AFT CORPORATION
PA-28-1T JHEROKEE ARCHER U
3.11
EI.IGINE POWER LOSS IN FLIGHT complete engire power loss is usually caused
orortlv-rä"i
.r.ig.""V
fu"l la¡di¡g is ¡"iior.d.
(¡efer to
If
powei
los
occurs at a low altitude, paragraph 3.13). An by fuel flow interruption-and ainpeed of
tle
at least 76 KLAS h¡st power step is will be ¡es-to¡ed to prepare should be maintahed.
for an
If altitud
pump
"ON.". ireiure
is
ind ctor
"Rl posi
fuel and turn the electricfuel
t
to "ON"' Check the engine containing fuel'
When power is ¡esto¡ed move the c¿rbruetor heat to the "OFF" position a¡d tum "OFF" tlìe elecf ic fuel pump.
lftheprecedingstepsdonot¡estolePower'P'ePareforanemergencylarrding.
If
time permits, tum the ignition switch to
"L"
then to
"R"
then back to "BOTH." Move a¡d mixture
lontrol
lea' a nrixture o¡
i[
levers to iltere is a dllferent settings. partial fuel system
ftis
may ¡estore power
¡estriction, Try
if
the otlrer fuel problem tanks. tal(e some water, time to be used up, and allowing the engine to windmill may lestore fuel pressure indications will be normal' is
Wate¡ too the tluottle
¡ich o¡ too ill tlte fuel couid power'
lf
poweris due to
If
engine failure was caused by fuel exhaustion power will not be rcstored after switclúrg fuel tanks until the empty luel lines a¡e fìlled. This may require up to ten seconds'
ll
power is not regained, proceed witlr tlle Power
Off
tanding check list and paraS¡aPh 3.13).
procedure (refer to thc emergency
3.I3
POWER OFF LANDING
If
loss of power occurs at altitude, t¡im the ai¡craft fo¡best gliding a¡gle 76 KIAS (Ai¡ Cond. off) and look
for
a suitãble l'leld.
If
measures taken to æstore power are not effective, and your clì¡rts
.ltitrdr. If
for airporls in the imnrediate vicinity; possible, notify the FAA by radio
it
ofyour may be possible difficulty and to land intentions. at
lf
one
if
time
if
you another perrnits. clteck have suflìcient pilot or
PassenBer is aboa¡d, let him helP.
When feet above easily be ¡eached, slow to 66 KL{S with flaps down fo¡ the s}¡ortest landing. Excess widening you have Iocated a suitable field, establish a spiral pattern a¡ound this field. Try to be at 1000
île
lìeld at the downwi¡d position, to make a normal landing approach. your pattern, using flaps or slipping, or a combination of these'
When altitude the fìeld may be
lo-
r
Touchdown should normally be made at the lowest possible airspeed' when committed to a landing, close the throttle control a¡d shut sn,itches. Flaps may be used as desúed.
"oFF"
the
Tum the fuel selector valve to "OFF" and move master and the ignition mixture to jdle cut-off.
ïìe
seat telts and shoulder hamess
(if
installed) should be tightened' Touchdown should be normalJy made at tlte lowest possible airspeed.
ISSUED: JU¡*E 18, 1976
REPORT: VB-790
3-8
PIPER AIRCRAFT
CORPO:
ION
PA-24-181, CIIEROKEE ÄRcrfER U
SECTION 3
EMERGENCY PROCEDURES
3.15
FIRE IN FLIGHT
'
The presence o.f the- since h¡e be of fue is noted through smoke, smell promptly identified through instrument the action to be taken diffe¡s somewhat
i¡
each a¡rd case.
heat readings, in the cha¡acter cabi¡. of
It is essential the smoke, o¡ that the source other indicatjons
Check for the soruce of the h¡e first.
cabi¡, p
If
vents should be opened and the cabin heat tumed ossible.
an electrical fì¡e is indicated (smoke in the cabin), the master switch should be turned
..OFF."
The
"OFF." A .landing should be made as soon as
_
'
an be "OFF." engine be at close tlÌe throttle. The mixtu¡e all cases, the heate¡ and def¡oster should
If
¡adio commr¡nication is not required, select maste¡ switch ';OFF." p¡oceed with power
ofi
landing procedure.
fue is present, switch the fuel selecto¡
to
idle cut-off. Turn the electric fuel pump "OFF."
"OFF"
In and
NOTE
The possibility determining of an engine fue in flight is extremely remote. The procedure given
is
general and pjlot judgment should be facto¡ for action in such an eme¡gency.
the
3.17
LOSS OF OIL PRESSURE
Loss of oil malfunction
P¡essure may be either partial or complete. A partial loss of oil p¡essure usually indicates
in
the oil pressue regulating system, and a landing should be mãde æ soon ai possible to a investigate the cause and prevent engine damage.
A complete loss of oil pressu¡e indication may signify oil exhaustion or may be the ¡esu.lt of a faulty gauge.
In
either case, p¡oceed toward the nearest airport, and be prepared
fo¡
a forced landing.
lf
thl problem is not a pressure gauge malfunction, the engine may stop suddenJy. Maintain altitude until such time as a dead stick landing can be accomplished. Don't change power ættings unnecessarily, as this may hasten complete power loss.
Depending on the ci¡cumstances, avaiJable, particularly
if it
may be advisable to make an off airport landirg while power is still othe¡ i¡dications
ter
-râtures, or oil smoke, are apparent,
of
and an actual
oil
p¡essure
aþort
is not close.
loss, such as sudden increases
i¡
Ifengine stoppage occurs, proceed with Power OffLanding.
ISSLIED: JLINE 18, 1976
REPORT: VB-790
3-9
;ECTION 3
I,ÍERGENCY PROCEDURES
PIPER
PA-z&I
A
RA¡'T CORPORATION
8.
TIEROKEE ÄRCHER
II
,.19
LOSS OF FUEL PRESSURE
If
loss of fuel pressure occurs, tum
"oN'the
electric fuel pump full tank.
and check that the fuel selecto¡ is on
If
the problem is not an empty tank, nd fuel system checked.
la¡d as soon as practical a¡d have the engine-driven fuel pump
i.2I
HIGH OIL TEMPERATURE
,;l
.n
Ä¡abnormallyhighcausedbyalowoillevel,anobstructioninthe
;fu
ge, or other causes'
I¿nd as soon as
"""ì"i-ålî";;
and practical
"
A
steady, rapid rise n""r,u',i. in"ártigaìe the
in oil
problem. temPerature is a sign of t¡ouble. La¡rd at the nearcst airport and let a waich the oil pæssure gauge for an accompanying Ioss of pressure'
}.23
ALTERNATOR FAILURE
Loss rssumed.
of
alternator output
'ollowingprocedure,
t*i.", rîiL
"r
insure the íanding is detected through
i¡-ai1i";";ãhC
is ze¡Ja¡rd
iichi:-ii;;;t;ease i¡
zero reading the not merely on the ammete¡' Befo¡e executing the low by actuating ammeter reading is an elect¡icallv powered noted, alternator failure can be
The electrical load should be reduced æ much as possible' check the alternato¡ circuit breake¡s ropped circuit, fo¡ a
The next step is to attempt to ¡eset the overvg.l!1æ relay. witch to "OFF" for on"
,ä"ãiiå"
( ie
.i
uolts u,t¿
,".oiã -á t¡.n
,pi
i¡.ir to procedure should ¡etu¡n the
This is accomplished by moving the anmeter to a normal reading'
"A.LT"
"oN,"
Ifltre t¡óuule was caused by a momentary overvoltage he reing
If
the ammeter continues to indicate
"O"
output, o¡
if
the altemator will not ¡emain ¡eset' tu¡n off
,,ALT,, switch,
mai¡t$,nini-rr rl".trical
lðad'and land as soon supplied bY the battery' as practical.
All
electrical load is
I.25
SPIN RECOVERY he
Intent.ional th¡ottle to spirs are prohibited idle a¡d the ailerons in tHs to neutral' airplane.
If
a spin is inadvertently entered, immediately m
Full rudder should then be applied opposite o¡ward. when ú¡e fotation
,iãpi'n-.rt
moothly regain a level flieht attitude'
ui;e
to the dÍection ofrotation followed by control the rudder and ease back on the cont¡ol wheel wheel as required full to
ISSUED: JUNE 18, 1976
IEPORT: VB-790
,-1 0'
PIPERAIRCRÂFTCORPOI iON
PA-2&T 8I, CEEROIGE,A,RCEER
tr
SECTION 3
EMERGENCY PROCEDURES
3.27 OPEN DOOR
The both the latch, the open doo oPen.
If
both upper a¡d side latches a¡e open, the doo¡ will t¡ail slightly sliBfitly.
open, and airspeed will be ¡educed
\t la.
To w. close
If
-randle the door in lliBht, the top latch is open, slow the airplane latch to the latched position.
it. If
the to side
87 KIAS, close latch is open, the cabir vents md open t¡e storm pull on the arm¡est while
If both latches añ open, close thè side latch tlen movirg the top latch.
the
3.2t CARBURETOR ICING
Under cenain moist atmosphcric condirions at temperatures of
-5o C venturi and the absorption of heat from this air by vaporizarion of to 20" C, it is possible for ice to in the induction system, even in summer weathe¡. This is due to thc high airvelocitythrougb th1 fuel.
form the carbureror
To avoid this, c¿rburetorpreheat is provided to replace the heat lost by vaporization. Carburetor should be full on when cârburetor ice is encountered. Àdjusr mixture for maximum smoorhness.
heat
3.29 ENGINE ROUGIINESS
Engine roughness is usually due to ca¡bu¡etor icing which is indicated by accompanied by a slight loss of airspeed or altitude.
Il
too full power måy not be possible; therefore, prompt action much ic¿ is allowed is required.
io a drop
i¡
RpM, and may be accumutate, ¡ãstoration of
Turn ca¡bureto¡ heat on (See Note). RPM will dec¡ease stightly a¡d decrease in engine roughness o¡ a¡ inc¡ease in RPM, indicating ice roughness
¡emoval. one minute, return tÌ¡e c¿¡bu¡eto¡ heat
to
.,OFF." will i¡c¡ease. Wait for
â
if
no cbange in approximately
If
tåe engine is still rough, adjust the mixture for too rich o¡ too lean' The electric firel pump should the other tank to see
if
fuel contamination is tl¡e maximum problem.
If
any gauge readings are abnormal, proceed accordingly. smoothness. The engine will nrn rough
if
be switched to "ON" a¡d the fuel selector switcheã to
Check
Move the engine gauges for the magnetJswitch to abnormal readings.
',L"
then to
..R,"
th"- pl
back to "BOT}I."
lf
operation is satisfactory on either
, with mixture ñ¡ll "RICH," to a landing at the magneto, proceed on li¡st available airpõrt.
t¡at magneto at ¡educed
Ifroughress persists, prepare for a precautionary landing et pilot's disc¡etion.
ISSUED: JUNE 18, 1976
REVISED: MAY23, l9t0
REPORT: VR790
3lt
SECTION 3
ETúERGENCY PROCEDURES
PIPER
AJ
iÃ-zliar,
.I,A¡.T
CORPORATI'ON
*SERoKEE ARcEER
u
THIS PAGE INTENTIONALLY LEFT BLANK
ISSIJED: JUNE 18, 1976
SECTION
4
NORMAL PROCEDURES
SECTION
4.
NOBMAL PROCEDURES
TABLE OF CONTENTS
sËcrloN
4
NORMAL PROCEDURES
Paragraph
N
4.1 General
4.3
Airspeeds For Safe
Operations
4.5
Normal Procedures Check
List
Preflight Check
.
Before Staning Engine
.
StaningEngineWhenCold..
StaningEngineWhenHot...
Starting Engine When
Flooded
Source
Starting With External Power
Warm-Up
Taxiinc
Ground Check
Before
Takeoff
,.
Takeoff
Climb.
Cruising
Descent
(Normal)
Descent(PowerOFF)
Approach And
Landing
.
Stopping Engine
Parking
4.7
Amplified Normal Procedures
lGeneral)
4.9 PreflightCheck.
4.
ll BeforeStaningEngine.
4.
13 StaningEngine.
4 Warm-Up..,...
4. Taxiing
4.lg croundcheck.,
4.21 BeforeTakeoff
4.23 Takeoff
4.25 Climb.
4-27 Cruising
........
4.?8 Descent
4.29 Approachandlanding
4.31 SioþpingEngine.
4.33
earking-.
4.35 Stalls..
4.77
Turbulent Air
Operation
4.39
Weight and
Balance
.:......
.r......
Page
No.
....... ...
¿l-¡
...
. ,
, +l
.
..
'...
'
.
+3
....,.. '
4-3
...
.
.. . +4
.,'.4'4
....44
..
. . .. . . ..
.. .
..
.
+4
.
4'4
... -..
+4
..-..'..4'4
........
+4
....... '..
+5
4-5
........4-5
.......
+5
....."
4'5
....'......
+5
... '......
4'6
..
'
..'.'...
4'6
+ó
.
'
'...
+1
..........+1
'.'.48
.......".+9
.".......4-ll
.. .... '.. ' +ll
..........+ll
.. . ..
...-+12
... ..
4-t2
..........4-t3
-........
4-13
...'-..'.'4-l-r
...'+14
-..-...'.4-15
..........+15
. .
'
+16
'..
' ' '
'
4'16
REPORT: \'B-790
+i
PIPERATRCR¿FTCORPO fION
PA-æ.l 81, CHEROKEE ARCÉER
tr
SECTION 4
NORMÀL PROCEDURES
SECTION 4
NORMÂL
PROCEDURES
4.1
GENERAI
This section clearly des the Ore¡okee A¡cher tr.
.A.ll
or-
-tion of the aþlane as
Normal procedu¡es supplements are associated yit| those optional systems and provided by Section 9 (Supplements).
equipment wilch require ha¡dbook
These procedures are provided
on
procedures which a¡e not the procedures given jn rhis section to present a sou¡c¡ of ¡efe¡ence same
for
all in orde¡ to become
aircTft
ulots
pioficii"i
¿¡d oouiã
-iumilI""; i" th"-;;nn*al;;äiËr,
to supply information themselves wirh rhe of ràe aþtane.
The fì¡st portion of this section for normal operations wittr consísts linle emphasis
"r
The of a short form
ti,i
"e.iãtlffi check list
#-õi,äiruur¡
å'ir¿l
should
be
action sequence e
f,iïi!:ryïffi'djåïffiìi#:i
:tî:."1î:1"Í to the lengthly explanations. The short form check list
4.3
AIRSPEEDS FOR
SA.FE OPERåTIONS
The following fìgures are airspeeds a¡e-those fo¡ sta¡da¡d airplanes flown which a¡e sig¡rificant to the at gtoss
*"ighi;de¡
stand¿¡d safe operation of the
aþlale.
These conditions at sea level.
Pe¡forma¡ce installed, technique.
the for a specific airplane mây va¡y from published figures depelding condition
of
the engine,
¡tpu"á ÀJ
equipment, upon the equipment
;m;.pñ;;-;ónditions
and piloting
76 KIAS
64 KIAS
I 13 KIÀS
102
KLA.S
66 KIAS
I? KTS
ISSUED: JUNE 18, 1976
REPORT: VÈ790
+L
SEGTTON 4
NORMAI PROCEDURXS
PIPER.{/.
.RAFT
CORPOR.ATION
PA.2&18i. ÀEROKEE ARCEERII
THIS PAGEINTENTIONALLY LEFT BLANK
ISSLJED: JUNE 18, 19?6
PIPER AIRCR-A-FT
PA-28.1 81,
CORPORÄTON
CHEROIGE ÄRCIIER
II
sEcTloN 4
NO,. .AL PROCEDURES
WAIK.AROlJND
4.5 n-ORI\ÍAL PROCEDURES CHECK LIST
PREFLIGHT
Control wheel
Master
Fuel
Fuel quantity gauges
Master
lgnition
Exterior
Conrrol
Hinges
Wings
.
.
Stall
waming
Navigation
lights...
Fuel
tanks
Fuelvents
Tires,.
.. sq,itch switch surfaces
tank sumps
Main gear struts
.
..
........ )
..
releasebelts
...
ON
..
'check
..
OFF
. .
.. .. ..
..
OFF
..
check for damage check for interference lree of ice, snow, frost
.check for interference
. free of ice, snow, frost
. .
..
..,check
.....check
..
check supply
. . visuallv - secure caDs
.. ..díain and cheåk for water, sediment and proper fuel
....'
oPen
'. '..
ProPer inflation (4.50 in.)
..'.....check
I
I
I
Figu¡e 4-l
Brakeblocks
Pitot
head
...chcck
.....remove cover -
\\/indshield
Propellerand
spinner.
Fuelandoil.....
Oil
....
Dipstick
Cowling lnspectioncovers.
Nose wheel
tire....
Nosegearstrut...
Baggage
Fuel door
., strainer controls
Primary flight
Cabin
door
Required papers
Seat bclts and
. harness
..
. holes clear
,....
...check
......
checkforleaks
...checklevel
....
properly seated
.....,
secure
.....secure
.....check
.....propcr
Airinlets
Alternatorbelt,..
inllation (3 25 in.)
......
clear
.......check
tension
,.
'
'...stow
Tow bar and control locks
Baggage ....
. slou'ed
ProPerì-vsecu re
... ...
close and secure
. cìc¡n
'.
drain proper operation
,
close and secure
.
...on
board
. fastcned/ad.iust check inertia reel
ISSUED: JUNE 18, 1976
REYISED: MARCH 30, 1984
REPORT: vB-790
4-3
SECTION
4
NORTÍAL PROCEDURE.
PIPER AIRCRAFT CORPORATION
PA.2&I8I, CHEROKEE ARCHER U
BEFORE STARTING ENGINE
Brakes
Carbureto¡
Fuel
lìeat selector
..set
lult COLD desi¡ed tank
STARTING ENGINE WHn{ COLD
Throttle
Masterswitch pump
Electricfuel
Mixture starter
Th¡ottle
Oilpressure
' .
.
.
'l/4"
oPen
..
.
.
' '
'
.ON
".ON
full RICH
'engage
...adjust
... '
check
if
engine does not start within
l0
sec' prime and repea t startin g
Procedure'
STARTTNG 1YITH EXTERNAL PO\{iER SOURCE
Maste¡srvitch
Allclectriccl
Ternti¡alS eqLtiptnctrt
External power
pìug
""'
.
oFF
'... '.OFF
. coltllcct
' insert
i¡
fuseì a ge
Proceed with normal start
Th¡otfle
External power
plug
Maste¡switcli
Oil
pressure
. lowest
Possible
RPNf
. disconnect f¡om fusel age
.,..ON-clteckammeter
'
check
\TÀRM.UP
Th¡ottle .
. 800 to
I 200 RPI{
START]NG ENGINE ìYHEN HOT
Throttle
Masterswitch
Elect¡jcfuel
Mixture
Starter
Throttle pump
OiJpressure
.l12" open
.. ......ON
.....ON
full RICH .
.
. engage
...adjust
._..
"check
STA.R.TING ENGINE WHEN FLOOD ED
Throttle
Master switch
Elect¡ic fuel pump
I{ixtu re
S
lirtcr
Mix tu re
Throttle
OiJ pressure open full
.oN
...
..oFF
. idle cut-off
.
.cngage
.
. adva¡ce
.
. retard
.
check
TÄXIING
Chocks
Taxi
, area
Tluottle
Brakes
Steering
.removed
. clear
.. ' '.
aPPlYslowlY
'
check
. check
GROUND CHECK
Throttle
I{agnetos
2ooo RPì'{
.max. droP I75 RPltf
-max. diff. 50
RPN{
Vacuum
Oil
temp
Oilpresure
. '.. '5'0"Hg.r.l
. check
.'
check
Ai¡
conditione¡
Annunciatorpanel....
Carburcto¡
Engi¡e
heat .
check
'press'to-test cllcck
is
warm for taleoff when tluottle can be opened without engine faltering'
Elect¡ic fuel pump
Fuel
pressure
Tfr¡oitle
OFF
. check
. retard
REPORT: VF790
44
ISSUED: JUNE 18, 1976
REVISED: JULY 12,1977
PIP
ER I,IRCRÄ-FT CORPOR,A.TION
P.4.2&181, CEEROKEE ÀRCHER tr
SECTION
4
NORMAI. PROCEDURES
BtrORE T.A-IGOFF
Masterswitch
Flightinstmments
harness
Emptyseas
Fìaps..
Trimtâb
Contols
Doors
Ai¡conditioner
...,
Fuel
selecto¡
Electicfuelpump.
Enginegauges
Ca¡buætorheat
Seatbacks
Mixtu¡e
Primer.
Belts,
.....,..ON
....check
. .
.proper tank
....ON
. ...,
. check
..'...,OFF
. ,. .::.,
.e¡ect
.....:.
,....:...locked.
.s€t
, fasteñedladjusred
...i.
seatbelts
.....:
.....:
snú8jy fastened
..set
.set
t..
free
...latched
......OFf
I
T.Ä.KEOFF
NORMÀL
Flaps .
Tab,..
. set
.set
Accele¡ate
Cont¡ol to 52 to 65 KIAS
wheel
¡otate back pressure to to climb attitude
SHORT FIELD, OBSTI,CLE CLEÄRANCE
FLaps
, .
25o (second notch)
Accelcnte to 41 to 49 KIAS depending on ai¡cr¿ft weidrt
Conr¡olwheel ....backpressureto
rotate to climb attitude
After breaking ground, accelerate to 45 to 54 KIAS depending on aircraft weight
Accelerate
KJ-A,S, to best flaps up angJe of climb speed
- 64 slowly rerlact
t¡e
flaps and climb past the obstacle.
Accele¡ate
K]AS lo best flaps up rate of climb speed
- 76
SOFT FIELD
Flaps..
Acceler¿te
.25'(secondnotch) to 41 to 49 KIAS depending on aircraft weight
Conüol
p.heel
back preszuæ
1o rotate to climb attitude
After breaking gmu¡d, accelerate to 45 to 54 KIAS depending on aircraft weight
Accelerate to best flaps up rate of climb speed ?6
KIAS
Flaps .
retact slowly
CLIMB
Best ¡ate (flaps
Best angJe
(flaps
En
¡oute
Elect¡ic fuel
up) up)
pump
,
CRUISING
Refe¡en ce pe¡form an c€ charts an d Avco-Ly comin g
Operator's Ma¡ual.
Normalmaxpower
Power
ÌYtixture
set
,,.'15%
per power table
. adjusl
DESCENT
Norm¡l
Throttìe
Airspeed
Mixture
Carburetor Heat
,..
DESCENT
Power off
Carburetor Heat
Thrortle
Airspeed
Mixture
Power,.
...
. .
?6 KIAS
64 KIAS
87 KlÄS desi¡ed
OFF at altitude
...
2500 rpm
,,.126KI.AS
.
,.. ,.
Rìch
.,.
On if required
, ,
,,.
On if required
......Closed
As required
As requirél
.,.Verify with throttlé r.' every 30 seconds fSSUED: JUNE 18. t976
REvISED: MARCH 30. I984
REPORT: YB-790
4_5
SECTION 4
NORM,A,L PROCEDURE5
.A.PPROACH AND LÄNDING
Fuet
Seat selector backs
Beltsrharness
Electic fuet pumP
Mixture
Flaps
..'.
Ai¡conditioner
Trim to 75 KIAS
. .
'ProPer tanl<
'
'erect
.,,..fasten/adjust
":"'set'lO2KIASmax
Finalapproachspeed(flaps40") '
" "
'ON
' ' "
'set
" ' ' ' 'orr
'.. ' 66KIAS
STOPPING
T¡¡GNE
Flaps
,
Eleãtricfuelpump
Ai¡conditione¡
Radios
Th¡ottle
Mixtu¡e
:....'
Magnetos
Masterswitch
4
PARKING
Parkingbrake.
Conrolwheel
Flaps
..
Wheelchocks
Tiedowns
.
'
'retact
'. '
'OFF
"'.'OFF
,.OFF
' '
'fuuaft idle
.
cut-off
'
'OFF
' " ' ' "oFF
.'.'."set
....secu¡edwithbelts
. '
'fulluP
'.".inPlace
'
'secure
PIPER NRCRAFT CORPO R.ATION
PA-2&18I, CHEROICEE ARCHER
II
REPORT: YB-790
+6
ISSUED: JUNE lE. 197ó
REYISED: l\IARCH 30. 198'{
PIPER AIRCRÄFT
P,A,.æ.I 81,
CORPOI
ION
CHEROI(EE ARCTER
tr
sEcTloN 4
NORM,A,L PROCEDURES
4.7,A,MPLIFIED NORM¿,L PROCEDI,JRES (GENER,A,L)
The following paragr_aphs procedures nec€ssâry fo¡ the safe p¡ovided
!o supply detailed operatioa of the
ai:
lane.
info¡mation and explanations of the normal
4.9
PREFLIGHT CIIECK a
The
check in-flight
facto¡s
¡
aþlaae should be given a thorough preftight and walk-a¡ou¡d obtained
¡e takeoff.
foi
check. The the intended preflight should utation of weight and C.G. linúù, taËeoff distanã-anà flighi path, arrd
-y
i¡clude oth;;
CAUTION
The flap positiorì strould be
The flaps must be placed noted befo¡e in the
,,Up" lock and support weight on the step.
boarding the position before ai¡c¡aft.
tley will
Upon entering the cockpit,
¡elease the seat belts securing the control wheel. Turn ..ON" the maste¡ swjtch and check the fuet quantity gauçs for sufficient fuel. Aite¡'the fuel quantity maste¡ switch "OFF" and check that the ignition switch is
..OFF." check is made turn the
To begia the exterior walk-around, check fo¡ extemal damage
co¡tol
surfaces or hinges. Insue thåt the wings and contol surfãces a¡e oth er forei gn materials.
Ând operational interference fìee of the of snow, ice, frost or any
Á'n operational check maste¡ sr¡/itch "ON."
Uft
of the stall waming system and navigation lights should now the detector while checking to determine
if
the hom is be made. actuated a¡rd
Tum the check that the navigation lights are illuminated. The maste¡ switch should be ¡etumed to the "OFF" position afte¡ the checks are complete.
and
A visual check visually chect of the fuel tank quantity should be performed. Remove the fille¡ cap from each tank tÏe supply and colo¡. Be su¡e to secure the caps properly after the check is complete.
The fuel sysem sumps and straine¡ shoutd be drained daily p¡ior to the fi¡st flight a¡d after refueliag to avoid the accumulation of contamjnants zuch as water or sediment Eactr fuel tank is equipped with an individual quick drain located at the lowe¡ inboa¡d rea¡ comff of the tank.
The fuel strainei is equipped
wjr' r
quick d.rÀin located on the f¡ont lower come¡ of the fi¡ewall.
d- I
f¡¡st. Then the fuel sFainer should be d¡ained twice, once
Each with t}re of the fuel ta¡k sumps shouid be fuel selectorvalve on each tank.
Eacn time fuel is drained, zufficient fuel should be allowed to flow to ensu¡e removal fuel should be collected in a suitable contairer, examined for conta¡ninants, and of contaminants. then disc¿¡ded.
This
.
cÄurloN
When draining any amount of fuel, care should be taken to ensure that no fi¡e haz¿¡d exists before starting the engine.
Each quick d¡ai¡ should be checked after closing ít to make su¡e has closed comoletely and is not lealing.
it
ISSLJED: JIJNE 18,
1976
REVISED: JANUÄRY
2o,r977
REpORT: V8790
+7
;ECTION 4
IORMAL PROCEDURES
PIPERAII
AfTCORPORATION
iÃ-isler,
udERoKEE ARcHER
II
Check all of the fuel tank vents to make sure
Next. com
Therc should b for 3.25 inches visual chcck of thcy arc oPcn'
H[i:""'d.'Ìii"::H,j::fff''J;jii::få
J wear and insure propcr inflation. Make a tur.
Remove
iiî'itol.t
rhe covcr from thc pitot head on thc underside of thc optn and clear of obstruc¡ions'
"t.
Don\ forgct to clean and check thc windshield' lcft wing' check rhe pilot head to ma*e
Thc propeller and spinner should be checked for dcfecs or nicks'
Lift
rhc cowling and check
aipr,iJ'r*, näp;;ì"y;;"1.J';;;i
for any obvious fuel or oil leaks' check thc oil level'
.i*É"s.
Sccurc the cowling and
Make sure check the inspection covers' that the
Chcckthcairinlctsforforcignmatterandthealternatorbcltforpropcrtcnsion'
Stow the tow bar and chcck the baggage doors should be closed and securc' for propcr storage and security. The baggage companmen¡
,f,. uoon entcring the aircrafl,.asccrtain that
.ãtin"¿ããr anã check that all all primary flight controls.op...t:'-t,llPttly' the required
PaPers atÊ in order and ln the arrplane' close and secure
Fasren and sharply on rhe adjust rhe scat belts and shoulder harness and check tbe st¡aP. Fastcn scat belts on empty seals' funetion ofthe incnia reel by pulìing
NOTE
IfthcFucdshouldcrharness(non.ineíiarecltyPe)is.installed,it mustbcconnectedtotheseatbcltandadjustedtoallowproper accessibilitytoallcontrols.includingfuelsclcctor,llaps.tnm.
ctc.' whilc maintaining adequate restraint for the occupant'
Ifthcineniarecltypcshoulderharnessisinstalled,apulltestof
is
locking restraini icaturc should bc pelormcd'
4.TI BEFORE STARTING ENGINE
frll
Before
ðöiij starting the engine the brakes should bc set p*¡iióñ. f¡. fiil selector should rhen be
'oN'and
the carburctor heat lever moved to the moved to the desired tank'
ISSUED: JtINE
l8'
197ó
REVISED: MARCH 30'
1981
REPORT: VÞ790
+8
PIPER AIRCRA-FT CORPO,RÀTION
PÄ-2A.181, CHEROKEE ARCHER
II
SECTION
4
NORMAL PROCEDURES
4.13 STARTINGETGINE
(a)
Starting Engine When Cold open the th¡ottle leve¡ approximately J/4 inch. Tum fuel pump,
"oN"
the maste¡ switch and tÌ¡e
Move the mixtuæ cont¡ol to full
"RICII":nd
engage switch clockwise- When the engine fires, release the magneio desired setting.
the starter switch, and by rotating the magneto
iove
the ürcttle to the
If
the engine does not fi¡e within ûve to and repeat the starting procedure.
ten seconds, disengage the sta-rte¡, prime the engine
(b)
Sø¡ting Engine WTen Hot fuel
Open pump
magneto throttle to
s
(.j
Starting Engine llhen Flooded
ll2
leve¡ nch.Turn to
,.ON,, the maste¡ full RICH and ."g.g. switch and the electric
t¡r.,l"rte¡
engine fires, ¡elease the mãg¡eto by ¡otating the swjtch and rnouã th.
the
fte
tfuottre advance the reve¡ electic fuel pump' should be
Move the rotating the mag¡eto switch fult 'l)pEN." clockwise. mixture a¡d retard the th¡ottle.
Tum
..oN" mixtu¡e coni¡ol.reve¡ to the m¡ster switch
i¿È-.úì-"ï
\ryhen-th..ngi"" o¡d tum ,,oFF,,
-ä';;g"g"
the starre¡ by rnagìelo swjrch,
'(d)
Sta¡ting Engine With External power
Source
Aa optional featu¡e c¿lled.the extemal baftery to crá¡k the engine
Pjper External Power (PEp) allows the operato¡ witirout having to gain access to use a¡ to the airplane,s battery.
OFF and tum all rvE (-J electrical equipment OFF.
Con¡rect the
(+) rerminal e.that when the plug ruque.
is
oia¡
terminal. Inse¡t the plug irseried, the external eleðt¡ci l2:volt of ure jumpe¡ cable sysi"m
RED lead battery
i¡to
tñe and rhe socket is ON. ?roceed
¿¡
¡rr
IN
reduce power
OUTPUT..
to the lowest from the ai¡c¡aft. Tu¡n possib.le the mæter
O¡ Of OUtPUt. DO NOT ATTEMPT
RpM, to reduce sparking, s*itcÉ ON
FLTGHT IF and c¡ecl
THERE
r¡ï
]S NO
NOTE master ttery in
.longer
ISSUED: JUNE 18, 1976
REMSED: JULY 3, 1978
REPORT: VB-790
+9
SECTION 4
NORMÄI PROCEDURES
Ii:iå,fi."Sf
ä':8YßHI'f il
REPORT:
VÞ790
+70
ISSUED: JUNE
I8'
REVISED: JULY 12'
1976
1977
PIPER
PA.2&I
AIRC&{5T
CORPI
ITION
8I, CEEROTGE,{R'CEER tr sEçTroN 4
NORMAI PROCEDURES
4.15 }YÀRM.IJP
warrr-up the engine a-t
800 minutes in cold. Avoid prolonged
to
l2o0 idling at
RPM fo¡ not mo¡e than low RPM, as this practice trvo minutes in warm weathe¡ and fou¡ mayr"zuîin ro,rl"a spark plug.
Takeoff måy b€ mlde as soon æ the ground opened fully witrout backfiring or skipping, end check without is c.ompleEd, provided
","arr"åor, irr'"-rrgin"ì¡
Do not operate the stones, gravel or any loose engine at bigh RPM when running-up sqteriar th¿t may cause damage to trt" or taxürig
propri",
over
üi"ã.r.
that the tluottle may be pr"*.
grouad containing loose
TÆüING
Before attemptins t9 qualified person
Jaxi the aþlane, authorized by the ground o*n.ì. er""rt"in penomel should be instn¡cted and that the propeller back blast and approved by a taxi a¡eas.are clea¡.
. Power-should be determi¡e appüed slowly to start the taxi ¡oll. thei¡ effectiveness. Whjle taxäng, make rlight
Taxi a few feet forwa¡d and apply the brakes
tu-,
to ascertain ti,e.r¡.cuu.n.r, to of the steering.
observe wing observer clearances ouEide tl¡e airplar¡e.
when taxüng near buildings o¡ other stationa¡y objects.
If
posible, station an
Avoid holes and n¡ts when taxüag over uneven ground.
Do not stones, glavel qrelate the engine at high RPM or ary loose materiar thai may when runnirg_up cause dam age to o¡ taxü¡g over ground containing thi prope[er
ti"ãrr.
' loose
4.19
GROT,JNDCEEß
The magnetos should be checked
RPM and the difference between at 2000 RPM. Drop the magetos strã"ia shor¡ld not exceed
l0
æconds.
"ãt
off on either magneto should not exceed l?5
ã**.J'¡¿i'Ri'îi'cË¡aüon
on one magneto check the vâcuu¡n gauge; the indicato¡ should ¡ead 5.0" +
.l-
Hg at 2000 RpM.
Check the a¡¡unciatoiPanel lights with the press-to-test button. AIso check the ai¡ condiüone¡.
and
Ja¡bu¡eto¡ heat strould also be checked
to
cleã any ca¡bu¡eto¡ heat ice which may h_ave prior to takeoff to formid during taxüng.
"ON' as the ai¡ is unfltered, be su¡e the cont¡ol is operating properly
Ä";id
p;;L;;;ä
gouna operation wirh
_ The elecEic fuel pump should be. tumed .,OFF" afte¡ the engine driven pump is operating prevent loss oil pressure. of day' The p
The engine to takeoff the the engine driv
¡ some time if when the throttle can be opened without the engine falteiing.
ISSUED: JUNE 18, 1976
REPORT: vÈ790
+ll
SECTION 4
NORMÄL PROCEDURES
PIPERAJ
RAFTCORPORATION
PA.2&I8i.- dEROKEEARCEER U
4.2I BEFORE TAKEOFF
All aspccts of cach particular takcoff should bc considercd prior to excculing ¡hc t¿kcoff procldurc' iu.r
Turn
*ON'the masler switch
,iäïor-iå.;;i.';ñ
i;i;'-o-n
,il^.ö;;"ug"r. ñ. åtuuttror
and chcck and set
¡;;p.n!r.9n¡
(fullest)' Turn hcatihould be all in thc of the
;oN"
'oFF-
position' rhc elcctric
Check thc fuel pump and check
All scat backs should be erect'
The mixture should be
,¡ouijü ¡"in.",toul¿
set and thc primer.chccked uc fasiir¡ca and adjusted. Fasten to insure that
it
is locked' The the seat bêlts snugly seat belts and around the empty sears.'
NOTE
Ifthefixedshouldcrharness(non.inertiareeltyPe)isinslalled.it
must bc connected to the seat belt and adjusted to allow. proper accessibilitytoallcon¡rols'includingfuclseleaor,flaps,trim,etc'.
while maintaining adequate relraint for the occupant'
lf
the inenia reel type shoulder harness is installed' a pull test its locking restraini ieature should be performed' of
Exercise and set the flaps and trim tab. Insure proper flight control movement and response'
All doors should be properly secured and latched'
On air conditioned models. rhe air conditioner must b€
*OFF'to
insure normal takeoff performance.
{.23 TÀKEOFF
The normal takeoff technique is conventional
,l¡gfttiy
"fi
oineutral, with to 4g to 53
tt,i
KIÁS eiact setting for the Cherokee Archer determine.d
Jepending ãn the weight by the loading of rbe
ll'
The tab should airplane' Allow the be set airplane oÎthe aircrafiand ease back on the control wheel
:o rotate to climb attitude'
The procedure used for a short ficld
takeoff
,l¡gt,tivirãm rhe normal rc.nniqu"' The flaps
sho
,o-r..ilrot.
ro
4l
to 49 KIAS depending on
the
to 45 1o 54 KIAS.'de After breaking ground. accelerate rccelerating tã
:learance
ìh. fl"pt-rp
rare of climb speed- 76 Kl.
.. ii
a consideration. Slowly relract the flaps while climbing out' lÈ rs ft
ê
REPORT: VÞ790
+tz
ISSUED: JUNE
It.
19?ó
REVISED; MARCH 30' l98J
PI?ER AIRCR.AfT
CORP(
.TION
PA.28.181, CHEROKEE AR'CHER
II
SECTION 4
NORMAL PROCEDURES
4.25 CLIMB
The best ¡ate obtained of climb at gross weight will be obtai¡ed at 76 IilAS. The best angle of climb may be at 64 KIAS. At lighter than gross weight these s¡reeds are ¡educed somewhat. For cümbing en
¡oute, a speed of 87 ¡qAS is recommended. This will produce bette¡ forwa¡d speed and increased visibility over the nose during the climb.
When reaching the desired altitude, the electric fuel pump may be tumed off.
4,27
CRIJISING
IÏe
cnrising speed of the Che¡okee A¡cher II is determi¡ed by many facto¡s, including power setting,
a-..de,
tempelatu¡e, loading and equipment installed in the aþlane.
The normal maximum crujsing power provided by Section 5.
ß 75% oî the ¡ated horsepower of the engine. Airspeeds which may be obt¿ined at va¡ious altitudes and power settings can be determined f¡om thõ performãnce graphs
Use
of
the mixtu¡e cont¡ol
in
cnrising llight higher altitudes. The mixtu.re sirould be leaned during øuising operation pfot's discretion at lower altitudes when 15% poì¡r'er or less above-5000 is bãing used. gngurrt of power being used, the mixtu¡e should be
5000 feet.
reduces in the fuel consumption full 'RICH"
If
signifìcantly, any position ft.-altitude a¡ã at doubt ior all especially exists as to at the operations unde¡
To lean the mixture, dísengge the lock and pull the mixtu¡e cont¡ol until the engine becomes iadicating that the lean mixture pushing the cont¡ol towa¡ds the instnrment panel until engine operation becomes smooth.
rough, limit hes been ¡eached in the leane¡ cyli¡ders. Then enrich the mixture by
If
means
Þe aþlane is equipped of leaning is available with the optional exlaust gâs temperatu¡e (EGT) gauge, a more acculate
to
the pilot. For this procedure, ¡efer
to
the "Avco-Lycoming Operator's
Manual"
Always remembe¡ that the elect¡ic fuel pump should be tumed "ON" shor:ld be left on fo¡ a short period thereafte¡, before switching tank, a¡d
In
o¡de¡ to keep the aþlane in best lateral trim during cruising fli8ht' the fuel sl¡ould be used altemately from each tank. It is ¡ecommended tÌ¡at one tank be useà fo¡ one hou¡ after takeoff, then the othe¡ tank be used for two hours; then ¡eturn to the fust rank, which will have approximately one and one hålf hou¡s of fuel remaining se^nnd rs
:lectic fuel prmrp should be normally 'lOFF".so that any malfunction of the engine driveniuel pump should and tanT will contain approximately one half hou¡
-rrmediaæly aPParent.
If
signs of be suspected, at which time the fuel selector strould be immediately positioned to the the elecEic fuel pump switched fuel to of fuel. Do starvation should occu¡ tl¡e "ON" position.
at
if
the not run tanls were tanks completely any time during full at takeoff. flight, dry fuel
i¡
The flie¡t.
exhaustion oùe¡ ta¡k
4.2t DESCENT
NORMAL
To achicvc the pcformance on Figurc 5-29 the power on descent must be used. The rhrottle should be set for 2500 RPM, mixture full rich and maintain an airspeed of 122 KIAS. In case carburetor ice is encountered apply full carburctor heat.
ISSUED: JUNE 18. 1976
R
EvlS ED: MAY 23, 1980
RIPORT: vB-790
+13
SECTION 4
NORMAL PROCEDURES
PIPER
A iår"T CORPOR'{TION
iÃ.lcra r,-uffi'oKEE
ARcIIER tr il
th
POWER OFF llc ixt rrY as
4.29 APPROACH AND LANDING belrs and shoulder
nu-rrr rfãuîï. fJ;d'anã
ad¡ust.d'and tbe inenia
I{OTE
'trrt
U. tonntc¡ed ro the scat beh and adjusted
....rr¡uiiìiv"iã-"rl tonttolt'
including etc., while maintaining adequate
fuá
restraint to allow selector' flaps' trim' for the occupanr' proper
lf
the inertia reel type shoulder harness is installed' a pull test its locking rcsrraini ieature should be performed' of full
Turn
..Oli" rhe elecrric
"RICH"
Position.
fuel pump and lurn "oFF" the air conditioner' Thc mixrure should be set in the
The airplane should be trimmed ro an speed of ó6 KIAS
*irn
nup,
.ii.iãi¿. fft.
initial approach sPeed of about 75 KIAS wi¡h a final approach flaps cán ue fo*åe¿ ar speeds up to 102 KIAS. if desired'
CH" position to insure maximum rt.u,
"ñouiã acceleration noi üe applied unlesi there a is an indication v b e c r i t i c a r i if it should of n ca s e o r a
n:"1
;Ji""'l¿'i : iïi;i': l.m be
The amounr of flap used varied according ro the landing surface-and pracrice ro conracr,rrc during landings and the
gro*ãäirilãinitun:
speed
*nairiottt
of oiwìnd possiblc-saie the aircraft at conlact with the runway should and airplane ipeed consisrenr loading' lt isgenerallygood with existing conditions'
REPORT: vB'790
+14 tSSUEDT
JUNE lt'
1976
198'f
REYISED: MARCH 30'
PIPER
PA'.28-I
AIRCRÂFT
81 ,
CORI
,A,TTON
CHERoKEE I\RCTTER
II
sEcTtoN
NORMAL PROCEDURES
4
4.31 STOPPING ENGINE
Ar rhe piror's discrerion, the flaps shourd be raised and the erecrric fuer pump turned..oFF.,.
NOTE
The flaps musr be placed supporr weigh t. in the passengen shou
-up-
td b, posirion
J"i,i";;
j for the flap srep to
;"1å?jií!,i.
.
The mrxture air conditioner an.d. radios should conl¡ol lock and pulling avoid engine vibrarion
*irir.
the mixture rrãpp¡ne. be turned
*n,.åi'i""t il;;;;;;"ero
..OFF,,,
,"
iiL.lri-åä. ;ï:'l;:r;1,,.
and and rhe engine stopped by shourd disengaging the be reft fu,, aft ro masrer.witch"s murt be rurned
..oFF.,.
-J
PARKING
rf
necessary' the airolane provided with each airptane n the ground with the aid i.u..r.ã.,r. Th"
åì*n..rand
"it;;;;;;å
snug. of the nosc
,,äbil",o, wheer tow shoutd bar be rhe naps are rocked when
'i.,äLrti'liililå;T"ïiïyol,i
Tie downs can be secured posirion by its connection, to to rings provided under
t¡. nåii';;;iätÏ;
each
.nd wing and normàlry to the does tail skid. nor have
The rudder is held in to ue secured.
4.35 STALLS
The stall characteristics.of the cherokee Archer
lI
are conventio.nal.
lL'li:'iJ,?J,'lii"iil.ï,i¿i,:irui*${n*i::;::¿m:
mires
An approaching stall per hour above-s,ail is indicated
,;.;;
Mìt;
The gross weight stalling-s.peed of
):;'i,:l:rn:l'.:#!lïfl:'j
.the.cJr-erokee
j:jÎ:ïj;d;-Kîi' ä"ì
A¡che.r
Il
wirh power off and tuli f.laps is 49 KIAS.
"r..rii,"å"iï¡íËîiå,;"";;i.,
rrom ,00,o
350 ree,,
NOTE
The srall warning
"oFF.'
system is inoperarive with the masrer swirch
lit""g
the detector and checking to rhe ruring preflight, the stSll warning
"oFF"
to posirion àIter rhe-check system shourd
¿.t.i-ín.lï,h;;;;"
ì;-;;;;i.ì;. ""' bt
is checked by turning rhe masrer swirch,,oN,,, a,,uared. The mastei switch shourd be rerurned
ISSUED: JUNE 18,
1976
RE\/ISED: MARCH
30, 1984
REPORl: \'B-790
4-t 5
SECTION 4
NORMÂL PROCEDURES
PIPER.tr
ÀA¡'TCOR.PORATION
ÉÃ--icrar, cttERoKEE ARcHER tr
4.37
TURBULN'¡T ÀIR
OPER'ÀTION
In keeping is encounte¡ed caused by gusts wi or ar o¡ of dist¡actions c ction 2.-?)ì
4.39
i{EIGHT AND BATA}'ICE allowable weight vs. center
óf gravity envelope while i flieht.
For weight a¡d balance data' refer to Section 6 (Weight and Balance)' clecl that when turbulent ai¡ reduce the structural loads as a
¡esult of the tu¡bulence
REPORT: VB-790
4-16
ISSUED: JUNE 18' 1976
SECTION
5
PERFORMANCE
SECTION
5 -
PERFORMANCE
PIPER AIRCR,{¡'T
CORPC
PA-28-181, CIIEROKEE
¡]ON
Ali'-dER
II
SECTION
5
PERFORMÄNCE sEcTroN
5
PERFORMANCE
5.1
GÐ{ER,AI
ÄIl of
Che¡okee II is provided by this section.
applicable to the
hi
ìerfo¡mance i¡fo¡mation cok supplements is associated ì¡/ith those optional provided by Section
9 (Suppiements¡.
systems and equipment which require
5.3
INTRODUCTION TO PERFORI,I,{NCE ÄND FLIGHT PLANMNG
The performance corrected to
I'c'A.o.
information sta¡da¡d
'¿/eight, altitude, temperaturc, etc, day
Prcsented
ðonditions
in
this and section ana.lyrically is based on measu¡ed Flight Test
Data
.*pãã.¿-ïoi"ìüJ'varjous parameters of
The performance p¡oliciencv o¡ c.harts ale unfscto¡ed and mechanical detedoration following the stated procedures in a do not maJ<e any allowance for varying of the ai¡maft¡rnis
properly.¡nt"in.ã p.tiár-ãn;l;;;;.;;
airplane.
degrees can be of pilot duplicated by cha¡ts must be evaluated by the pilot, such as the effect of
ä5.ïå'".'iff
;hi:,i.",:'iï1,:i":ilti'"j,r"ffiïîtr1
REMEMBERI To get chart performance, follow the chart procedures.
The information using the performancæ provided clarts in by paragrapL5.5 (Flight this-sectiìn-. Each
Planning Example) outljnes a detailed flight plan cha¡i l¡cludes
iú
own
";;;1.;;1"*
how ir is used.
WÀRNING
Performance information derived by extraporation beyond charts should not be used for flighi planning purporÉr.
the limits shown on rhe
ISSUED: JUNE 18,1976
RE\¡ISED: MÄY23,
19E0
REPORT: vB-790
5_l
PIPER Jô.-CRÂFT COR}ORATION
PA-28'L
THEROKEEARCIIERtr
THIS PAGE INTENTIONALLY LEFT BLANK
REPORT: VB'790
5-Z
ISSUED: JUNE 18, I 976.
P1PER AIRCR,A,FT
CORPG
ÍION
PA.2&I 81, CHEROKEE ARCHER
tr
sEcTloN
5
PERFORMANCE
5.5
FLIGET PI¡{NNING EX.{}{PLE
(a)
,A,ircraft loading bv
The fi¡st utilizing the step in plaaning our flight is to cal*ate-the aþlane information piovided úy section e weight and center of gravity
fweigtianã'g¿ä;;ËiihL
h¡¡dbook.
in
1"J
Make use of the weight and Batance
(Fig're
6lsj
to determine
#1fåîtt
Loading Form(Figu¡e
ólr)
and the
t¡" tãt¡ i.ie¡'i àiiË. i'prliá ilä
tr,. c.G. Raage and
."nt.iorË""iiv
After proper u
:lîzation fo¡ consideration in ou¡ flight of the information plânning
.r;pl..
provided we have found the following weights ed until the weight of the fuel to be used hæ been
1400 lbs.
340 lbs.
333 ii:
(b)
(6)
Landi¡g
lveieit
24oo lbs.
(a)(5) ninus GXI), (2400 lbs. minus t29
tbs.)
22jt
tbs.
I oLlr takeoff weight is below the maximu¡n calcr¡l¿tions have
of
determined our
C.G. posltion wittLin
2550 lbs. and our weight and tfr.
"ppro".a
ti^ltr.
'
' bala¡ce
Takeoff a¡d Landi¡e
Now that we have determi¡ed oru takeoff a¡d laading.
ai¡qaft loading, we must conside¡ all aspecls of our
,4,11 evaluated of the existing conditions at the depa¡fu¡e a¡d maint¿ined throughout the niehi.
and destination Àirport must be acquired, conditions and takeoff weight
to
the appropriate Tal<eoff
r !7)
to detemine the length of runway necissary for the
The la¡ding distance conditio¡s at the destination calculations-
aþort
and, are performed whå
in
established, the t1.,. same manner using the
r-aing*.igi,t.
existing
ISSUED: JUNE 18, I976
REVISED: M,{Y
23, 1980
REPORT: VB-790
5-3
JECTION 5
?ERFORMANCE
PIPERÄT
I.AFTCORPORATION
PA-z&l8r; LjHEROIGE ARCIíER U
The conditions and calculations for ou¡ example landing distances requLed for our example flight have lengûs, flieht are listed below' The t¿Ìeoff and fatlen well below the avaüable runway
Departure
Akport
Desti¡ation
Aþort
(1)
(2)
Pæssu¡e
Altitude
TemPerature
(3)
Wind ComPonent
(4)
RunwaY længtÏ Ävailable
(5)
Runway Required
2000 ft.
70'F
IO KTS
7000
950 ft.
ft.*
2300 ft.
-
70'F
5 KTS
4500 ft.
825
r*
NOTE
The remainder of the performance charts used assume i¡ this flight plan a no wind condition. The effect of winds aloft
;;t b" descent conside¡ed by performance' the pilot when computing climb' cruise and
(c)
Ctimb
The next step in oul flight plan is to determine the necessary clirnb segrnent components'
The remaining values are the true fuel, distance a¡d of the flight plan corrected for field pressuæ aldrude and time components temPeraturc' forthe climb segment
The following values were determi¡ed from the above example.
(1)
Cruise Èessr¡¡e Altitude
(2)
Cruise OAT
(3)
Time to Climb (l l'5 min. minus 3 min')
(4)
Distancc to Climb (16 minus 4.5 nautical miles)
(5)
Fuel to Climb (2 gal. minus
I
gal.) ins[uctions in our flight planning
6000 fr.
550F
E.5 min.*^
I 1.5 nautical miles'
lgal''rrr
'r
*¡eference
Figwe 5-l I r*¡eference Figu¡e
5-35 treference Figu¡e
5'l
5
|-EPORT:
4
VB'790
ISSUED: JTINE 18, 1976
REVISED: MAY 23' 1980
PIPER
PA,-2&1
AIRCR,4,FT CORPO. .ION
8
T, CEEROKFT¡ ARL-EIEI
II
SECTION
5
PERFORMANCE
(d)
Descent
The descent data will be d.etermined prior for establishing the total cruise dista¡ce.
to the cruise data to provide the descent distance
The valuæ obtained by proper utilízation example a¡e shown below.
of the graphs fo¡
tìe
descent segment of our
(e)
Cruise flì I..
(3) to
Lrrsrance
Fuel
Descend to
(t6 min.
Descend (35 to Descend (2.0'gat. minus
"ri"";l
7.5 mi¡.) minus 14.5 nautical
;i:i-'¡vs'
20.5
8.5 min.* nautical miles*
1.0 gal.*
Calsulate tlre cnrise the
.A,vco q"I fo¡ the eruise power setting f¡om the information provided by
The cruise time is fuel is found by fou¡d by dividing the cruise distance multiplying th,
t*iæ
furi by ttre cruise speed and
ñ;ñ;rh. cruise rime.
the cruise
^,
,orffiri*
(l)
Total
(2)
Cruise calcurations established
Distance
Dista¡ce fo¡ trre cruise segÍEnt of our flight pranning example are
(3)
(4)
(c)(l) minus (c)(4) rninus (dX2), (314
Cruise Powe¡
Cruíse Speed
(5)
Cruise
(6)
Cruise
Fuel Consumption
Time minus
ll.5
minus
20.6)
(7)
G)(2)
Cruise divided by (e)(a), (282 nauticat
Fuel miles divided by
lt0
KTS)
(e)(5) multiptied by (e)(6), (7.ó
cpH
muttiplied by 2.5ó hrs.)
3 l4 nautical miles
282 naurical miles
65% rated power
IIOKTSTAST*
7.6 GPH
2.5ó hrs.
19.5 gal.
¡ r¡eference Figpre
¡¡efe¡ence Figure
5-29
5-2 I
ISSLjED: JLINE 18, 1976
REVISED: MAY23, 19t0
REPORT: vB-790
5-5
;ECTTON 5
?ERFORMÀNCE
PIPER pr.-z&l
A
R,,AFT
CORPORATION
Bt. iffi oKEE ARCEER
II
(Ð Total Fli8ht Time to descend a¡d the aPhs are in ¡ninutes
The following flight time is reguired iii
iãi¿
rts'iri'"'
(cX3) plus (dxl) plus (eX6), for our
flifit
Plånninc example'
('ta hrs' plus '14 hrs' ¡lus
2'56 hrs')
2'84 hrs'
(e) Total Fuel REquired
Determine the cnrise total tuel reguired bV tuel. When the
ãrt"*i"t the tot¿l fuel weight r:sed for the a!dþe. the fuel to climb' flight' the fuel to descend and tot.l"iuïitt
ãanäns) i¡ãetermbed, multiply this value bv 6lbigar
Thetotalfuelcalcu]ationsforourexanpleflightplana¡eslrownbelow'
\¡/
Total Fuel Required iÐõ;ñ ià)it;l"' (eX7),
(l
gal'
(2i.S plus gal.
I
.e1l:.plu: le'5 eal') multiplied bv 6 lb/gal')
21.5 gal.
I29 lbs.
REPORT: YB'790
54
ISSUED: JI.INE 18' 1976
REVISED: MAY 23' l9E0
PIPERATRCRAETCORP.
P.4,.2&I8I,
ffiEROKE
-{TION
ÁRCEER
tr
TIITS PAGE INTENTION/A,LLY LEFT BI-ANK
ISSUED: JUNE 18, 1976
PIPERÄ
R.ÀFTqORPORÄTION
P¡,.ZCT AT, CHEROICEE ARCEER tr
TT{IS PAGE INTENTIONALLY LEFT BTANK
ISSUED: JUNE 18, 1976
PIPER.AIRCR,A,FTCORPC
ITON
PA.28.I 81, CIIEROKEE .A,ìt=dER
tr
5.7 PEFJ'ORMÄNCE GRAPSS sEcnoN
5
PERFORMANCE
LIST OF FIGURES
Figure
No.
Page
No.
5-l
5-3
5-5
5-7
5-q
5-23
5-24
5-25
5-26
5-27
5-29
5-31
ç-? ?
5-35
5-l
5
5-17
5-l
8 tt9
5-20
5-21
<-t t
Airspeed System stattspeeas
Ca[bration
..
.-. .-:-.-.
:.:: ::.
. . .
,
Haps
Flaps zsï
nãishiteoir
CIr,"t
Engine
Engine
ûp ra:<eonpe*år¡nan";'
2sdFh;s
r;;¡ii;;;-*
Up TakeoffG¡ound
Time, Distance
óioìni'nu
.-:':
-¿
ru.ità
. cmu
Performance (Serial Nos. 28-7?90001
Performance (Sedal Nos. 2&7890001
" "'
: : : : : : : : : : : : : .
'
Best Economy
Best Economy
Mûture Range (Serial Nos. 2g-7jgt
Mixture Reage (Serial Nos. 2g-7gg(
Endu¡ance
S-29
ï:':."î:1':
:.::.:
:::
::.:::r:.............ii
i.]å
s-11 s-12 s'r3
5'14 s-rs s-r6
5-17
ISSUED; JUNE 18, 1976
REVISED:
IljLY
12- tg77
REPORT: VB-790
5-9
PIPERA.,RâFTCORPORATION i¡.-zara l.-cÆnoKEE ARcHER
II
TTIIS PAGE
INTENTIONALLY LEFT BLANK
ISSUED: JUNE
l8'
1976
PIPER ]A,IRCR.A¡.T
PA-23-181,
CORP(
.NON
CHERoKEE lRcirER
tr
PA-29-lBl
q..
9.Y$IE
2550
M
tBS.
6R0SS
cA
ri e-mÃvn
oT
sEcnoN
5
PERFORMANCE
150
110
J o
130
4
Ø
=
ê
--
ê
,
120 lr0 r
00
90
80
70
60
50
{0
0
ISSIIED: JUNE 18, 1976
Bo so
roo
lo
lzo
l¡o l¡o lio-liî l(IAS. HO I}ISTRUIIEIIT
TRROR
A-IRSPEED SYSTEM CA|JBRATION
Figu¡e 5-l
REPORT: vB-790
5-l I
;ECTION 5
]ER¡'ORMANCE
CALIBRÀTTD SPEEI)S
PA-28-l 8l
ATT
SPE
POlrER
OFT
fl"
FLAPS
25"
FLAPS
--- - 10"
TLAPS ltAx. BR. Hr. 2550 tBS.
PIPER
]RAFT CORPORAT]ON
PA-2&T b=, CÉIEROKEE
ARCIIER tr
50
15
20
10
AIIÊLE OT BAHI( 'DEÊREES
50
10
80 tl q
70
Ê5
60
Ø
E
ë
-
Þ
Ø lYElÊHT
.
100 LBs.
ixample:
Gross weiglrt: 2300 lbs.
Arlgle ofbank: 20'
Flap position: 25o
Stall speed: 46 k¡ots ('i¡dicated ainpeed)
'[il)tcllEI)
AlRsPEt0, li0 lHf)lcÄT()R tRR0R
STALL SPEEDS
Figure 5-3
TEPORT: i-t2
YB'790
ISSUED: JLINE 18, 1976
È
1$
P\O
IJJ O x
H
o
F
:l
.6
{
\o o\
;
c
2
d
(A
(D c id
tl
|l,
E
(h rX
ãH
ç
-t
Ð tsrt
o
ä
È l) t¡l
PA-29-lgl
-t0 -20 0 20 {0
f)uTstllt
AtR T[MP.
60
. "r
-õ
ÊRoss wflGHT
.
LBS.
il[
Exarnple:
Dcparture airport pressure altitude:
20OO
Temperature: ?0oF
Wind: l5 KT. (headwind) ft,
Gross weìglrt: 2400 lbs.
Takeoff distance: t
900 ft.
Ë
I 3800 l,uoo
| 3{oo
I
32 00
3000
2800
2600
2t00
2200
-
o ts o
-
o a q
É
É
E
6
Ë
o
@
É
2000
1800
¡É Ìt
ÞË
bJ lrl tsts
:F
f;F
ãT
xn
trt ll:ú
ÈF
9i fr,
:!
aZ
>ú x tsf
^Ø
ãä
àç
Irl q
q:E
¡h
F
Ft
<
E
$
\o o c
;
E e.
2.
d
-æ
{
\o o\ l.J
":
,rl l.
Þ
ã
È
'¡X
Ets
ã'fl ulll rJH
E
o
frl
PA -28-l 8l
25'IFLAIPS
llAffi
TULI THR(IIITT BIT{IRE
BRAI(I RTTIASI
PAYEII,
IEVTI, ORY RUIIWÀY
0ursl0t AIR
IEMP.
- "f
-rb -ztl
0UIS|0E AIR tl
ltl'lP.
'
'C
20
2rû0
GROSS WEIGHT
.
tBS.
tïilo
Example:
Departure airport prcssurc
Tcmperature: 70o F altitude: 2000 ft-
Gross l¡Vind: wciglrt: 2400 lbs.
I
knots
(lrcarlwintl)
T¿¡kco[f distancc: I 8(r0 l't.
.
1${0Is
' tr
2600
2t00
,2200
2000
1800
I rroo l,,oo o
Ë
É
e
É
É
G
@
-
o ts
12 o
-
o
I ç.
fit trl 4t
Fúx
rÈ
¡,J cP rfl io i rí>
F
O*l xô
rlF
>!
Éz
PIPER AIRCRÀFT
CORP
,.\TION
PA-28.I81, CHEROKEE ARCI{ER
II
EIJ
.
'll0u
0Hft0u9
lj0lyYI
SECTION
5
PERFORMANCE
F
æ
F
I
æ
N
¡
À
É<
-=
É4 o
Éê
(oJ
s;È
?4;.;
NÞU
-)J
"--
Ø o
Þ
=
Øö
ç
o
N
'l)^ô
ã ä *.'<-
=
3F3
Ëã
arc{vË
.! d !<:
..Eiìt-u
! h äø: o
SËE3E.Y
lll
iaÈo>È
o
F
-
q qi
æ
=
e
Ø
F
=
ñê tø
-
o
Þ
è'
ISSUED: JU^-E 18, 1976
FLAPS UP TAKEOFF GROUND ROLL
Fisure 5-9
REPORT: VÈ790
5-l 5
SECT]ON 5
PERFORMANCE
PIPER
/
;RAFT CORPORATION
PA.2&1 8'-, CHEROKEE ARCHER
II
F
æ
F
I
æ
(\
I zfrl
I
-+É5i
EË=
0&uE
ä
_Ë;
@E=
Gã ¡-.{
<¿F
t-É>
6-ù
-<
= d
À
-Lrll
' 'l'l0u
0Nn0u9 lj0l)lYr
=
25.FLAPS TAKEOFF GROUND ROLL
Figure 5-t1
-
=
qu i;=
I q e e
CJ o g
F
È
=
=
ê to
É
Þ!!
tõ
Þ
I
.-.¡
N o
"ó o E!
ø
R'tn
E =:..
-o
O= I
ør
I g >-9
õ.Í
ãøE e r¡l
FÃËöËÊ
=
ISSUED: JUNE 18,1976
REPORT: VB-790
5-1 6
PIPER AIRCR.AFT
CORPC
rION
PA-æ-l 81, CHEROKEE ARç.dER tr
PA-29-lgI
SECTION
5
PERFORMANCE
2550 tBS.ÊR0SS
|YEIGHI stnYtct cflUll6-l3.650
Fr.
l8soum ctuls-15,?50
FL ttrItD
100.f
0lIßlDE
AIR TtÀlP.-.C
Example:
Climb pressure
Rate of altitude: 3600 ft.
OAT: 30oF climb:
620 F.p.M.
CLIMB PERFORMAI{cE
Figure 5-13
ISSUED: JLJNE 18. 1976
100
600
RATE OT CUMB.F.P.M.
REPORT: V8790
5-17
SECTION 5
PERFORMANCE
PA-28-l8l
11ÛME,
DISTAN]GE
AND
FUEL TO
GTOMB
CUITB AT 7O I(IÂS À}ID
FUII THROTTIT.
2550 t3S.
ER0SS ITHEHI
PIPERA,RAFT
C]ORPOR,¡I'TION
PA-2&l
81
;CEEROIGE ARCHER U
INCI.IJDES
FUII AIIOIYANCE
TOR START,
TAXI AHD TAI(EOFF.
-20
0 20 10 50
E0
100
-20
-10 0 l0 20
30
üJßl0E ÀlR TElrlP'-'C
15
20 25
30
TIME, OISTAHCE AHO RJEL TO CUMB ixam ple:
Departure airport
Debanure airport
Cruise pressure prcssure altitude:2000 f¡' temperature: 70oF alritude: ó000 ft'
Cruise OAT: 55oF
ii..,o
climb: I 1.5 min. minus 3 min'
=
8'5 min'
öliiãn"tto
Fuel climb: ló miles minus ro climb: 2 gal. minus
4'5 miles
I
gal. =
I
gal'
=
ll'5
naurical miles
TI}{E
DISTA.I.¡CE AND FI,JEL TO CLJMB
Figu¡e 5-15
REORT: VB'790
5-1
I
35 {0 15
50
ISSUED: JUNE lE' 1976
REVISED¡ MAY 23' 19t0
PIPER AIRCRAFT CORPCL -TloN
P.4,.2&1
8
I,
CEEROKEE ÄR-CEER N
PA-29-lgl
PERF@RMANGE
BESI P0ìYER I'IIXTURE fI,IAHIS
T0
IOO'T RICll OF PEÂl( EßTI
SECTION 5
PERFORMANCE
¡t,fl. ¡t0lr
Ê.P.lr.
sl PowtR StsT tc0lloHY
7.8
55%
6.3
9.0 E5%
?.6
10.5 75%
8.8
0UTSIDE AIR TEllP.*'t flmll)E
AIR
T$lP.-'C
EHGIHE SPttD
-
R,P.l'1.
Example:
Cruise pressure
Cmise altitude: 5500 ft.
OAT: 40"F
Percenl. power:
65%
Engine RPM: 2440 RPM
ENGTNE PERFORMANCE (SERTAL NOS. 2&7790001 THROUCH
Figure 5-17
7790607)
ISSUED: JUNE 18, 197ó
REVISED: JVLY 12,1977
REPORT: VB-790
5-l 9
iEcfloN
5
?ERFORN{ÀNCE
PA- 28-l 8l
IFÍ-ro
T ¡n rtY
.0 prTe,' t
¡lu
ït'l'n
ì
if"'å,fi,'"+*'ËffiH'fì
2200
2{00
EHÊIHE
SPEEI¡
Pl'l
ì26 00
OlJTSIDE AIR TEMP.
Example:
- ð;G
pressue altitude: 5500
ft'
Cruisc
OAT:
4f
F
P¿rcenÍ Povrett
Engi¡e RPM:
6570
2440 RPM oF oc
REPORT: \.B-?90
5-20
ENGINE PERToRMANCE (sERlÀL
NOS' 28'7890001
AND uP)
Figure 5- I 8
ISSUED: JUNE
REVISED: JULY
l8'
1976
l2'
1977
PIPER
P,A,.28.1
A-IRCRAFT
81,
CORPOìì
ON
CITËROKEE ÀRLì¡ÉR tr
PA-29-lgl
SPEED
POWER
-
PERFORNlANCE
GRUÛSE
BTST POIYTR MIXTURE,
2550 LBS.
GROSS ITEIOllT
|l|.lxTqlE
IEANED
FlJLL RtCH AB0yE 75%,
IOO' F RICH Of
PEÂK EGI
BELO}T 75% POlyER. IVHEEL TAIRIIIGS
INSTALLID, SUETRACT 3
KI{OTS++
SECI]ON
5
PERFORM,AME
Ex'
rle: ie p¡essure
Cn:ise altitude: 5500 ft.
OAT: 30oF
Power:
557o
True airspeed: 97.5 k¡ots
SPEED POì\ER . PER-FORI{ANCE CRUISE (SERIAL NOS.
23.77}OOOI TTIROUGH 7790607)
Figure 5-19
ISSUED: JLINE 18, 1976
REVISED: IULY 12,1977
REPORT: VB-790
5-21
SECTION 5
PERFORMANCE
PA -28-l 8l
slst
PoYrrÄ
ülxitlnl
2550 LB. GR0SS YlT.
iiuttto pn
LYcoMtttg lilsntlcIloNs
PU'ER' iÃ-zì-i
-
-.ÇRAFT
CORPORATION
.bnEnoxrs
ARcIIER
II l0 120
130
TRUE
AIR SPEED ì(TS
OUTSIDE ÀIR TEMP.
cruise
Þressure altitude: 5500
bAT:
30'F
Power
True setting: 55% al-rsPeed:
I01
k¡ob ft'
REPORT:
<-1) spEED POWER-PERTORMÀNCE CRUISE (SERIALNOS' 28-789O001 AND UP)
Figure 5-20
YB'790
ISSUED: JUNE 18, 1976
REVISED: JULY 12,1977
PIPER,A-IRCR,A,FTCORPO fON
PÄ-æ-181, CHEROKEE ARvdER
II
PA-29-lgl
EED
P@WER.
BEST ICONOMY ìIIXTURE,
2550 tBS. MAX. GR. YtT.
MIXTURE LEAI{ED TO PEAK
EGT.
}YHEEI TAIRIIIGS INST
UBTRÀCT
3
KNOTS
If
SECTION
5
PERFORM,A.NCE
+
0 20 40 60 80
OUTSIDE AIR TEMP.
.
'F
-20
-10 0 l0 20
30
OUTSIDE ÀIR TTMP.
.
"C
100
-ix amp le:
Cruise pressure alrirude: 6000 ft.
Cruise OAT:
Pou'er:657o
55oF
True airspeed: I l0 k¡ols r00 1t0
120
TRUE AIRSPEIO
.
KNOTS
SPEED PO1VER . ECONOMY CRUISE
(SERI,A.L NOS, 28.77g}æl TIIROUGH 7790607)
Figure
5-21
ISSUED: JUNE
REVISED:
I8,1976
IULY 12,1977
REPORT: VB-790
5'23
ECTION 5
ERFORIIANCE
PA -28-l 8l
PIPER Á'-..IR.AFT CORPO
PA-2&1i
]HEROKEE
RÄTION
ÄRCHER
II
255018. MÀX, GRoSS
MINURE
M.
TIAHE! TO PEAI( EI
Y/llEIL TAIRIHGS IHSTALLED,
SUBTBACT
8 KTS IT
REI||OYED
-20
0
20
0
20
OUTSIDE
AIR TEMP, ot
0
0c
Exam Þle:
Cruìse pressure
Cruise aìtitude: 6000
OAT:55"F
Powersetting:657o
True airsPeed: I l6 k¡ots ft' lr0
120
TRUE AIRSPEED KTS.
SPEED POWER
- ECONOIÍY CRULSE (SERIÄL NOS. æ-7890001 AND UP)
Figure 5-22
REPORT: \E-790
5-24
-LïHEB1]UÌT i?. i3i9
PN'EIT ÂIRCR,AFT CORPO}. ,ION
PA.2&1 81, CIIEROKEE ÄRCHER
tr
PA-2lg-lgl
IIIXÌURE TIAIIEI) TO IOO'T
RICH OF PEAI( E8T
ìYHEttFArRtHÊsHSTArLED,
18 GAL USABI.I
25.50- LBS. iZER0
FUEI tytilD,
L
RAHEE
[{CtuDES CUilB
T+++++
ï¡i
t-lt+l-+
ti?;
iõilÌi"
x0lE
RIJIE
II¡I
SE NÉDUCTD sYUPm{7" tf Htfft ¡tntßs lRt fl()T tllstlilm
.
SECTION
5
PERFORMÄNCE
+
-30 -20
_t0 0 t0
20
30
0c
OUTSIDE AIR TEMP.
Example:
'sc
.se prtssure
OAT: altitude:
35oF
5500 fr.
Power setting: 75l¿
Range
Range
(with reser.ve): 480 nautical miles
(no reserve): 535 nautical miles
BEST POWER MDffURE RANGE (SERIAL
NOS. ?ß-77¡OOO1T}IROUCH
Figure 5-23
7190607\
ISSUED: JUNE 18, 1976
REVISED: MAY
23, 1980
REPORT: VB-790
5-25
ECTION 5
ERFORMANCE
PIPER
AI
I'AFT CORPORANCT{
¡Ã-zct
e t,
-¡IERoKEE
ARcnER
II
PA-28-l 8l
H|XTURE LIAIIED
T0 100"
t
i
-î'ì
-Ì'
I i0ft-f-.lJ-+nia
rrnnes ÂRt lû1 DlsTttu!
ïTTïHäïläiï
2550 P0lltDs, zER0
ñrxe¡ ìctuoËs o-
500
RÄHBE
HÄJNCAL
HIIIS
0UTSIDE AIR TEI'lP' lxample:
Cruise pressure altitude:
C¡uise OAT: 35oF
5500 ft'
Power se¡ting: 757o
Range
(withicserve): 505 nautical
Ranle (no resene): 560 nautic¿l miles miles
BEST POIVER MD(TURE R-ANGE (SERTAL
Ft$Íe
5-24
NOS' 2&7890001 AND uP)
REPORT: VB-790
5-26
ISSUED: JTINE
l8'
1976
REVISED; MAY 23' 1980
PIPERAIRCRAFTCOI\
P4,.28-181,
.TATION
CHEROKEE }.RCHER
II
SECTION
PERFORMANC
PA-29-llBl
BEST EG@NI@IVV
RAO$GE:
.,...¡!¡luRE
WHEET rEÂNr0 T0
PEAK
EGT,
FAIRIIIGS INSTALLED,4S GAI.
CLIMB
FUEL,
}IIIID
2550 L8S. ûR.
IYT.,
RANGE IIICLUDES
I
I
&
OESCTHT
DISTÀI{CE.
I0Tt
RAXÊT ¡ITY BT RIDUCI¡ 8Y
UP Tf) 1%
IF lyflEfl. fÂtRtll6s IRE fioT ìsilu¡0
60 80
I
+
-30
_20
_10
0 l0
20
30 0c
OUTSIOT AIR TEfiIP.
E.-
.ple:
Cruise pressure
Cruise altirude:
3000
OAT: 35oF ft.
Power setting: 65l¿
Range
Range
(with
(no reserve): 570 nautícal milés reserve): ó50 naut.ical miles.
BEST ECONOMY MDffURE RANGE (SERÌÄL
NOS. 28-77gOOOt THROUGH 7790601)
.rrgure
5-25
ISSUED: JUNE 18, 1976
REVISED: MÄ.y23,
1980
REPORT: VB-790
5_27
ECrloN 5
ERFORMANCE
PIPERA'
RAFTCORPORATION
PÀ-2&1
8i.
THEROKEE .ARCHER
II
PA -28-l 8l
EESI
ECONJ@bYIV N'IÜXT.UJ R Ig
BANIG II
MIXIURE IEÂNED TO PTAK EOT
YÍHEEL TAIRINGS IHSTALIID
48
GÂ1. USABLE FUEL
2550 P0UllDS, ZERo YilHo
RAIIGE IHCLUDES
Ctll'lB AH0
RA}{ßt rTITll 15
AT s5% PovltR lllll. RtstRvt
H0ït
R¡}ËE IÀAY
BI EIUCTI) BY tJP l0
8% lf ìtllEtt rÀnHGS
ÀE ll0Ï llsT^tltD
'
-åo
-zb
80
100
I, lt ot
-20 0 20 40 60
r I I I
,
I
,
-io ô lb io
io
4'o o c
OUTSIDT ÀI.R TEMP.
xample:
Cruise pressure altitude:3000 ft.
Cruise OAT: 35oF.
Power
Range selting: ó570
(with reserve): 600 nautical miles
Range
(no reserve): ó?0 nautical miles
700
RAHGE NAIJTICAL
600
I'l ILE S
EPORT:
28
BESTECONOI\IYMIXTUREx,qrr*GE(SERIALNOS.28-7890001ANDUP)
Figure 5-26 vB-790
ISSUED: JUNE 18' 19?6
REVISED: MAY23'
I980
r 2,0 00 l0
000
¡
8,ooo
=
6,000
4,000
2,000 stA ttYfl.
PIPER ¡,IRCRAFT
CORPO
UON
P4.28.1 81, CHEROKEE
,4,Ã. --¡ER
II
SECTION
5
PERFORMÄI.ICE
tttttl
-iltI)URA}ICt
llllll-
-45 Milt. RtSERYE-
PA-29-lEl
ENlDURAO{GE
BEST ECOIIOMY IIIXTIJRE
2550 tBS.
MAX GR0SS
IPEAI(
Ìn.
l.T-È.
.Tg-u'1ll!g-È
!_r,lulÐ r,umö yr!
Afiu yïñ
EGTI-
tTTT-f
| | | | I
I
I rtt
DURÀilCt
RESERVT rll ll
YITll
-
H-
Ë5% tt
-s5% lr tt
P()IT
¡t
E
R
561
I
55:
I
ENDlJRANCE. l]OURS
E:
rle:
¡se pressure altitude: 2000 ft.
Power setting: ó5l¿
Endurance (with reserve): 5.5
Endurance hrs.
(no reserve):6.1 hrs.
ENDURA-{CE
Figure 5-27
ISSUED:
luLY
12,1977
REYISED: I\'IAY 23, 1980
REPORT: V8790
5-29
]CTION 5
'RFORM,A,NCE
PA-28-l
ioME;ÞnSTANc-E^AND
r
8l
LA.S. AND 2500 R.P.M.
2550 LBS. GRoSS YlT.
PIPER
AI -R-AFT CORPORATION
P4.28-16
TIEROKEE ARCHER
II
,I c
-2r 0 20
40
#
-30 -20
-10 0 l0
20
30
0UTSIDE AIR TEI'IP.
t0 lt
20
25 30 35 10 15
50
TlìlE, DISTAI|CE, ÀHD ruEL T0 DESCEÏD ample:
3ruise pressure altitude: 6000 ft.
Sruise OAT: 55oF
Destination airport pressure altitùde: 2300 ft.
Destination
Fuel to airPort descend: temperature:
(2.0 gal. minus
l
70oF
Sal') = ¡.9 fime to descend: (16 min' minus 7.5 min.)
=
t"t'
8'5 min'
Dir,un". to desce;d (35 miles minus 14.5 miles) = 20'5 nautical miles
TI]\ÍE, DISTANCE AND FUEL TO DESCEND
Figu¡e 5-29
EPORT: VB-?90
30
ISSUED: JIJLY 12'1977
R
EYISED: MAY 23r 1980
PIPER AIRCR,A-FT
CORPOI
ION
PA-2&I 81, CHEROKTE ÄRLìIER tr
PA-29-l 8l
**f#lGLoDE
RANGE
H-+
-P0WER
0FF, frÄps llL, l.q [Ts.,tAs,.2550 rBs.-
I ttt ttttdutr¡tTu tt ttt tt lt w
+#
12000
1¡n00
i
8000 f.
z
6000
1000
2 000 str
LtYEt.
051015202530
ÊLIDT RANÊE
.}IAUTICAL
MILES
Example:
.
ise pressure altitude: 8000 ft.
ain pressurc
Gtrdc Range: alritudc: 1500 ft.
I3 miles minus 2.5 miles = I0.5 nautical rDilcs
SECTION 5
PERFORMANCE
-r
I
I
GLIDE RANGE
Figuæ
5-31
ISSUED: IULY 12,1977
REVISED: MAY23,
19E0
REPORT: V8790
5-3 r
JCTION 5
JRFORMANCE
F
æ
F
I
æ
c{
I
È
óë=-+-E
7--zã
(e) -
-o
=
PIPER
A] p¡.--lc-rfi;
ì,AFT CORPORATION
-HERoIcE
ARcHER
II
'U'ElUUfS
= = a
tl'\0
ISNYISI0 0NlOHn
,09
i
=j3-=:
6e
-
Ë
¿ó
.e{ s2
-
^..;
!
'=H
1
E*rrils
3=i
ã\òô ¡i..
é
3 ssR?g
EJo=.:: v,!=ÈYø
Ë.e3
È E
..Ë Ì bt
Ë
å3.?ÊËç
X
F<()F+¡ F fJ¡
REPORT: VB'79O
5-32
LANDING PERFORMÀNCE
Fieurc 5-33
ISSUED: tl..jilY 12,1917
*l
o
F
:l
F
0
r
NotJ-Cls rn
P
{{
\o
-
t c
ró
t-
z
Þ
ÈJ
Eo
uo
HE
Þ
F o
F
PA-29-l
rur,irff
rrîül0ÂcH,i0.
nAPs
_
..._tiilXtMljlit BRAtfl ilG uutstut
ÄlR T[MP. -
"c
Exarnple:
Àirport presure altitude:
Airport temperature: 70"F
Gross weight: 2264 lbs.
Wind: 5 knots (headwindl
Ground roll:
825 ft.
23OO
Ít.
lTilD
.
l(il0Is l3 00
tr
t200
J
J
il00 P
e
1000
=
@
c00
-
@
800
'o ìt
Þã
FF
8F
ãE
Xô
fr! trt
O
,rt
H=
EZ
800
¡Ú lÌ,
É hJ
^ø
ã9
Ðã
ãz db
PIPERA]
IAFTCIRPOR.ATION
iÃ.zcr
er, -ITERoKEE ARcIIER
tr
THIS PAGE INTENTIONALLY LEFT BLANK
)
SECTION
6 .
WEIGHT
&
BALANCE
SECTION
6 -
WEIGHT
&
BALANCE
TABLE OF CONTET\¡TS
SECTION 6
WEIGHT AND BAIANCE
(
6.1
c
6.7
6.9
Paragraph
No.
Gclrcral
Airpla'eWeigJúngProccdu¡e'
: : : :
Weight and Balance Data and Record
: : : : : : : : : : : .
.
Weight and Balance Determination
Equipment
(a)
List .
.
for Flight
Propeller and Propeller Accessories.
(b)
Engine and Engine Accessories
. .
.
.
(c)
Landing Cea¡ a¡d Brakes
.
(d)
ElectrjcalEquipment
(
(e)
lnstruments
l)
Miscellaneous
(g)
Engile and Engine Accessories
(Optional Equipment)
(lt)
Propeller ald Propcllcr Accesso¡ies (Optional E<luiprnent)
(i)
Lurding Gea¡ and Brakes (Optional Equipment)
û)
Electrical Equipment (Optional Equipment)
(k)
Instruments(OptionalEqu.ipment)
(l)
Autopilots(Optiona.lEquipment)
(m)
Radio Equipment (Optional Equipment)
(n)
Iliscellaneous(OptionalEquipment)
Page
No.
6-l
6-3
6-6
6-t I
6-t7
6-17
6-t9
6-21
6-23
6-25
6-27
6-29
6-3 I
6-33
6-35
6-31
6-39
6-4t
649
REPORT: VB-790
6-i
PIPER ÂIRCRâFT CORPO. JION
P,1,-2A.181, CI{EROKE ÄRCEER U
SECTION 6
WEIC,IIT AND BALANCE
SECTION
6
WEIGHT.A,ND BAIANCE
6,1 CENERAL
In order to achieve the performance and flying characteristics which are designed into rhe airplane. ir must be flown with the weight and center of gravily (C.C.) position rvithin the approved operaring range
(envelope). Although the airplane offers flexibility of loading. it cannot be flown with rhe maximum number of
a
passengers. full fuel tanks and maximum baggage. With the flexibility comes responsibility. the pilot
rr--.
ensìrre that the airplane is loaded witbin the loading enveìope before he makes a takeoff.
Misloading carríes consequences for any aircraft. An overloaded airplane will not take off. climb or cruise as u,ell as a properly loaded one. The heavier the airplane is loaded. the less climb performance it will have.
Center airplane. of gravity is a determining factor in flight characteristics.
lf
the C.G. is too lar for*,ard in any it mav be difficult to rotate for takeoff or Ianding. lf the C.C. is too far aft. the airplane may rotate prematurelv on takeoff or tend to pilch up during climb. Longitudinal srabilìty will bc reduced. This can lead to inadveñent stalls and even spins. and spin recovery becomes more of the approved limit.
difficult as the center ofgravity moves aft
A properly loaded airplane. however, will perform as intended. Before the airplane is licensed. a basic empty weight and C.C. location is computed (basic empry weight consists of rhe standard emptv weight of the airplaneplustheoptionalequipment). UsingthebasicemptyweightandC.G.location.thepilorcandetermine
the weight and C.C. position for the loaded airplane by compuring rhe toral weight and momenr and then determining u'hether they are wirhin the approved envelope.
The basic empty weight and C.G. location are recorded in rhe Weight and Balance Dara Form (Figure
û5) and the Weight and Balance Record (Figure ó-7). The current values should alwavs be used. S/henever new equipment is added or any modification work is done. the mechanic responsible for the work is required to compute
Weight a new basic empty weight and C.G. position and to \¡irite these in the Aircraft Log Book and the and Balance Record. The owner should make sure rhar
it
is done.
A weight and balance calculation is necessarv in derermining how much fuel or baggage can be boarded so as to keep within allowable ìimits. Check calculations prior to adding fuel to insure against improper
lr
rg.
The following paBes are forms used in weighing an airplane and in computing basic empr),weìght. C.G.
position. and uselul load. Note that the useful load incìudes usable fuel. baggage. cargo and passengers.
Follou,ing this is the method for comprting takeoff weight and C.G.
ISSUED: JUNE 18, I976
REVISED: MARCH 30, 1984
REPORT: VB-?90
6-l
SECTION 6
WEIGHTAND BALANCE
PIPER
Ä1
-RA,FT CORPORATION
PA.2&I8
-¡IEROKEE
ARCHER tr
)
THIS PAGE INTENTIONALLY LEFT BLANK
I,EPORTT
YÞ.79O
-2
ISSUED: JIJNE 18. r976
PIPER AIRCR-A-FT
CO
)RATION
PÀ.æ-1 81, CHEROKE^ .RCHERII
SECTION
6
WEIGHT AND BÀLÀNCE
6.3
ÄIRPLÀNE IìIEIGHING PROCEDURE
At the time of licensing, Piper Aircraft Corporation provides each airplane with the basic empty weight and center of gravity location. This data
.is supplied by Figure 6-5.
The ¡emoval o¡ addition of equipment or airplane modilications can affect the basic empty weight aad center of gravity. The following is a weighing procedurc to determine this basic empty weight and cente¡ of gravify locatíon:
(a)
Preparation
(l)
Be certain that all items checked in the airplane equipment list a¡e installed in the proper location in the aþlare.
(2)
Remove excessive dirt, greaæ, moisture, foreign items such as rags and tools from the airpla¡e before weighing.
(3)
Defuel aþlane. Then open all fuel drains until all remaining fuel is d¡ajned, Operate engine on each tank
u¡til
all undrainable fuel is used and engi¡e stops. Then add the unusable fuel
(2.0 gallöns total, 1.0 gallons each wing).
CAUTION
Whenever plenished the fuel system is completely drained and fuel is reit will be necessary to run the engine for aminimum of
3 minutes at 1000 supply lines.
RPM on each tank to ensùre no air exists in the fuel
(4)
Fill with oil to full capacity.
(5)
Place pilot and copilot seats in fourth (4th) notch, aft of fo¡ward position. Put flaps in the fully retracted position and all control su¡faces in theneutua.l position. Tow ba¡ should be in the proper location and all ent¡ance ard baggage doors closed.
(6)
Weigh the aþlane inside a closed buildi¡g to prevent ero¡s in scale readings due to wínd.
(b)
Leveling
(1)
\ryithairplaneonscales,blockmai¡gearoleopistonsinthefullyextendedposition.
(2)
Level airplane (refer to Figu¡e 6-3) defìating nose wheel tire, to center bubble on level.
ISSUED: JU¡-E
l8'
1976
RE\tlSED: I\'tARCH 30. 1984
REPORT: \¡B-790
6-3
SECTION 6
WEIGHT AND BALÄNCE
PIPER
A'.
^R,AFT CORPORATION
PA-àVIE
HEROKEEARCHERU
(c)
Weighi¡e - Airplane Basic Empty Weight
(l)
With the aþlane level and brakes the ta¡e,
if
anY, from each reading' released, reco¡d the weight shown on each scale' Deduct
Scale
Position and SYmbol
Nose
Whee] N)
Right Main
Wheel
(R)
t¡ft
Main
Wheel
(L)
Basic Empty Weight, as Weighed
(T)
WEIGHINGFORM
Figure 6-
l
(d)
Basic Empty Weight Center of Gravity
(l)
The lollowing geometry applies to the PA'28-181 pa¡ag¡aPh 6'3 (b).
airpla¡re when it is level' Refer to Leveling
C. G. A¡m
7
8.4
Level Po.ints
(Fuselage)
B
3 1.0
109.7
REPORT: VB-790
64
Wing Leading Edge
R+L
LEVELING DIAGRAM
Figure 6-3
The datum is ?8.4 inches alread of the wbg leading edBe at the intersection of the st¡aight and tapered sectìon'
ISSUED: JUNE 18' I 97ó
REVISED: FEBRUARY 25, 1971
PIPERATRCRA¡TCORPO' ¡ON
Pr4.-28-1 81, CHEROKEE AR-^ER
II
SECTION 6
WEIGHT AND BALÀNCE
(2)
Th9 basic empty and unusable weight center of gravity
(as weighed including optional equipment, fuel) ca¡ be dete¡mined by the following formula: full oil
C.G./C,Ín
= N(A)
+
(R+L)(B)
T inches
Whe¡e:
T =
N+R+L
ISSUED: JUNE 18, 197ó
REVISED: JANUARY 20,
197 7
SECTION 6
WEIGET AND BÄLANCE
PIPER
A
RA¡'T CORPORATION
PÃ-isier-
;UERoKEE ARCHER t
5,5 \ryEIGHT AND BALANCE DATA AND RECORD
The Basic Empry weight, center of cravity rirolane as licensed
",
,n.
'ejistr"rion number shown.
Location and usefuì Load iisted in Figure û5 are for ¡he i"lal. itt.se figures apply only to the specific airplane serial number and of the airp
BaThisformsta¡usoftheairplanebasicempty weofpreviouepermanentlyinstalledequipment
)r
*.ight
ot s been entered in the Weight and
Weight and Balance Record'
REPORT:
ç6
VB-790
ISSUED: JUNE lE. t976
REVISEDT MARCH 30' l9E'f
PIPE{ AIRCR"{FT
PÄ-28-1 81,
CORPOI
ION
CIÍEROKE ARcrlER
II
SECTION 6
WEIGHTAND BAIANCE
MODEL P¿,.2&I81 CIIEROI(EE ARCEER
II
Aþlane
Se¡ial Numbe¡
Regist¡ation Numbe¡
Date
ÄIRPLANE BÄSIC EMPTY WEIGHT
Item
Standard Empty Weight+
åompute¿
Optional Equipment
Basic Empty Weight
Weight
(Lbs) x
C. G. tum
(lnches Aft of Datum) rThe standa¡d empty weight includes full oil capacity and 2.0 gallons of unusable fuel.
Moment
(I¡-Lbs)
AIRPLANE USEFUL LOAD
(Gross Weight) - (Basic Empty Weight)
= Useful Load
Normal Category (2550 lbs)
-
( lbÐ =
Utility Category (2130 lbs)
-
( lbs) = lbs.
lbs.
j
-rls
BASIc EMPTY
wElcHT. c.c. At;D
usEFUL LOAD ARE FoR THE AtRpLANE AS
LICENSED
AT THE
FACTORY. REFER
ALTERATIONS HAVE BEEN MADE.
TO
APPROPRIATE AIRCRAFT RECORD WHEì\
ISSUED: JUNE 18, 1976
REVISED: MARCH 30, 1984
WEIGHT,A,ND B,AIA-I.ICE DATA FORM
Figure 6-5
REPORT: \¡8-790
ç7
sEcrIoN
6 _-
WEIGI{TAND BAIANCE
if.tå'åt
Hil':8f;iËHlfil
THIS PAGEINTENTONAILY LEFT BLANK
ISSUED: JIJNE 18, 1976
)
PIPER AIRCRA-FT CORPORATI ON
PA.2¡.1 8I, CHEROKEE ARC1TER
tr
WEIGHT AND
SECTION
6
BAIÄNCE
6.7
WEIGHT AND Bi{LANCE DETERMINATION FOR FLIGHT
(a)
Add the weight of all items to be loaded to the basic empty weight.
(b)
Uæ the Loading Graph (Figure 6-13) to determine th-e moment of all items to aþlane.
be carried
i¡
thr
(c)
Add the moment of all items to be loaded to the basic emply weight moment.
(d)
Divide the total moment by the total weight to determi¡e the C.G. location.
(e)
By using the figlres ofitem (a) a¡d item (d) (above), locate a point on the C.G. range and weighl g¡aph (Figu¡e 6-15).
If
the point falls withi¡ the C.G. envelope, the loadingmeets the weight
a¡i
ba.lance requirements.
Weight
(Lbs)
AÍri Àft
Datum
0nches)
Moment
(ln-Lbs)
Bæic Empty Weight
Pilot and Front Passenger
Passengers
(Rea¡ Seats)+
Fuel (48 Gallon Maximum)
Baggage r
Total Loaded
Aþlane
340.0
340.0
80.5
I r8.1
95.0
t42.8
2'1370
401 54
The cente¡
Locate this of gravity (C.G.) of this sample loadiag problem is point
.G. envelope,
( at
this loading meets the weiglt and balance requirements.
inches aft of the datum li¡e
) on the C.G. range and weight g¡aph. Si¡ce this point falls withi¡ the weight.
IT
IS THE RESPONSIBIUTY OF THE PILOT AND AIRCRAFI OWNER TO INSURE T}IAT T1ÌT
AIRPLÀNE IS LOADED PROPERLY.
'Ut.ility Cåtegory Operation - No baseage or rear passengen allowed.
ISSUED: JUNE 18, 1976
SAMPLE LOADING PROBLEM (NORMAI CATEC'ORY)
Figure 6-9
REPORT: VB-79{
Gt.
TION 6
GHTAND BAIANCE
PIPER,A,IRCRAFT CORPORÂTION
PA-2&I81, CHEROKEE ARCHER
II
Basic Empty Weight
Pilot and Front Passenger
Passengers
(Rear Seats)r
FueÌ (48 Gallon Maximum)
Baggage*
Total Loaded Ai¡Plane ls must be wit¡-in approved weight and C.G. limits, It is the responsibility of the aþlane owner a¡d the to insu¡e that the aþlane is loaded properly. The Basic Empty Weight C.G. is noted on the Weigùt
Bala¡ce Dat¿ Form (Figu¡e
65). If
the aþlane h¿s been aitered, refer to the Weight a¡d Balance
,rd for this i¡formation..
jty
Category Operation - No basgrgie or rea¡ passengen allowed'
WEIGHT AND BALAI.¡CE LOA-DING FORM
Figu¡e 6-l
I
)RT: VB-790
ISSUED: JLJNE 18, 1976
PIPER A,IRCR,A.FT CORPORÂTION
PA.28.181, CI{EROKEE I.RCHER tr WEIGHT.AND
SECTION 6
BAIANCE
I
450
400
350
ø
ô
3
3oo
F
î,ffi
J
õ
3
Q zoo
1æ
ñ*
I
^"j
."*
(ùò at p\-
.^d d
4
100
50
/¿
,./
À
/.
v
0
051015má303s404550
MOMENT/lOOO {POUNOS .
INCHES)
-+
lã'et
ISSUED: JUNE 18, 1976
LOADING GRAPH
Fisure 613
REPORT: VB-790
613
,CTION
6
:IGHTAND BAI.ÂNCE
PIPER A]RCRAFT CORPORATION
PA-2&18I, CITB,OKEE ARCHER
II
Ut
o
z
o
È
I
=
0
¡¡.t
B
NORMAL CATEGOBY
UTILITY CATEGOBY
)RT: VB-790
84 86 88
90
INCHES AFT OF DATUM
C. G, RANGE AND WEIGITT
Figure 6-15
ISSUED: JIJNE I8, 1976
REYISED: MAY 23, t9t0
PIPER AIRCR-A-FT CORPORATI ON
PA-28.18I, CHEROKEE ¿,RCTIER
II
WEIGHT AND
SECTION
6
BAIÂI.ICE
THIS P/A,GE INTENTIONATLY LEFT BLANK
ISSUED: JUNE 18, 1976
THIS PAGE INTENTIONALLY LEFT BLANK
PORT: VB'790
6
ISSUED: JUNE t8, 197ó
PIPER .A,IRCR,A.FT CORPORATTON
P4.28.18I, CIIEROKEE ARCHER
II
6.9
EQUIPÀíENT LIST
The licensin-q. rhe folìou,ing is a list of equipmenl which used for defining the confiÊuration ofan
Only those srandard items whjch åre certilìca-ting a.uthoriq,
ma airplane
(FAA) are presenred.lrems on the airplane described below as delivered
alt m
by rhe manufacturër.
SECTION
6
I{EIGHT AND BAIANCE of those items at rhe time
ã'U, of
ì¡riäJ W
ç*.
i"i,.llãå
PIPER ¡JRCRAFT CORPOR,A.T]ON
-RIÄL NO.
PA.28-I8I CHEROKEE ARCHER II
)t^
?r'/o 2'tÇ
REGrsrR-A.Tro N
No. OF' y'-
KT
D^-18.
-ç.3.7flc-1
(a)
Propeller and Propeller Accesso¡ies
Item
No.
I
Item
PropelJer,
Sensenich
76EM8S5-G60, Piper
Spec. PS50077-8
Cert. Basis - TC P4EA
Propeller, Sensenich
76EM8S5-G62, Piper
Spec. PS5007742
Ce¡t. Basis - TC P4EA
/
lrla¡k lnstl.
if
Weight
(Pounds)
Arm (In.)
Aft Datum
Moment
(Lb-ln.)
ISSUED: JUNE 18, 1976
REVISED: N{ARCH 30, 1984
REPORT: YB-790
6-17
PIPER AIRCRAFT CORPORÀTION
pÅ-zlïh,
cHERoKEE ARcHER tr
THIS PAGE TNTENTIONALLY LEI¡T BLANI(
ISSUED: JUNE18' 1976
PIPER ÂIRCR.A-FT CORPORATI ON
P4.28-I 8I, CHEROKEE,A,RCHER
II
(b)
Engine and Engi¡e Accessories
Item
No.
lt
IJ
I5
Item
Engine
a.
Piper Dwg. 62941-16
Lycoming Model O-360-A4M
Çert. Basis - TC E286 b. Piper Dwg6294l-17
Lycoming Model O-3ó0-A4A
Cert. Basis - TC 286
OiJ
Filter - Lycomirg No.
75s28 (AC'OF5s787?o)
Ccrt. lJosis
- TC 8286
Oil Filte¡ - Lycoming
'LW-13'143 (Champìon
'cH48 l l 0)
Cert. Bæis - TC E286
Alternaror ó0 Amp.
a. Chrysìer 3656624 b. Ghr¡'sler 4l
I l8l0
It{a¡k
if
lnstl.
i<
X
Weight
(Pounds)
281.0
285.0
5.3
2.8
12.4
r
3.5
WEIGHT AND
SECTION
BAIÄNCI
(
Arm
Aft
(In.)
À{omenr
Datum
(Lb-ln.)
20.9
20.9
35.5
35.5
t4.0
I
4.0
58 73
5957
ll7
99
114 r89
ISSUED: JUNE 18, 1976
RE\¡ISED: I\4Ä\'
23, 1980
REPORT: VB-?90
Gl9
ECT1ON ó
TEIGHT AND BAL¿"
PIPER AIRCRAFT CORPORATIOI'I
PA-2&I81, CHEROKEE ARCHER U
THIS PAGE INTENTIONALLY LË'FT BLANK
ISSUED: JUNE lE, 1976
PIPER,A,IRCRáFT CORPORÀTI ON
P4.23-1
8
1, CITEROKEE,A.RCHER
II
(c)
Landirg Gea¡ and B¡akes
Item
No.
2'l
29
Item
Two Main Wheel Assemblies
Piper Dwg. 63370-0 &
-l
a. Cleveland Ai¡craft P¡oducts
Wheel Assembly No. 4G86
Bra-ke Assembly No. 3G55
Cert. Basis - TSO C26a b. Two lrf
6.00-6 ain 4-Ply with Regular Tubes
Cert. Bæis - TSO
Rati¡g Tj¡es
C62
'
One Nose Wheel a. Clevel¿nd Ai¡craft P¡oducts
Wheel Assembly
(Less
Brake
No. 40-?68
Drum)
Ce¡t Bæis - TSO C26a b. McCauley Industrial Corp.
Wheel Assy. No. D-30625
Ce¡t. Basis - TSO C26b c.
One Nose Wheel 4Ply Rating
Tire 6.00-6 wjth Regular Tube
Ce¡t. Bcsis - TSO C62
It{a¡k lnstl.
.< if
We.igJrt
(Pounds)
4.3
55
SECTION
6
WEjGHTÂND BAIANCE
Arm
Aft
(ln.)
Momcnt
Datum
(LbJrr.)
31.0
31.0
133 l'71
ISSUED: JUNE
REVISED:
18,1976
JANUÄRY
ZO, 1977
REPORT: VB-790
ç21
ü:iü,f,:8fi
ffi
'?8å"^iHi'f
ìì
THIS PAGE INTENTIONALLY LEFT BLANK
ISSUED: JUNE
18' 1976
)
PIPER AIRCR,A,FI CORPORáÏON
PA.æ.l
8 1, CHEROKEE ARGHER
II
Item
No.
ì4.-
jHT
sEcTloN
6
AND BALANCE
ECTION 6
EIGHTÄND BALAN
PIPER AIRCRAFT
CO RPO
RATION
PA.2&I8I, CHEROKEE ARCHER
I]
THIS PAGE INTENTIONALLY LEFT BI.A,NK
ISSUED: JUNE I8, 1976
)
PIPER A.IRCRA-FT CORPOR,A,TION
PA.æ-l 81, CHEROKEE ÀRCHER
II
(e)
lnstruments
Item
No.
53
55
)t
Item
Airspeed Indicato¡.
Piper Spec. pS5O0¿9-30S
Cert. Basis - TSO C2b
Altimeter, Piper
Spec. PS50008-2 or -3
Cert. Basis - TSO Cl0b
Compass.
Cert. Basis=,-TSO C7c
SECTION
}TÈIGHT AND BÄLANC.
Ma¡k lnstl.
if
Weight
(Pounds)
Arm
Aft
(In.)
Moment
Datum
(Lb-In.)
ISSUED: JLJNE 18, 1976
REPORT: VB-790
625
PIPER AIRCRAFT CORPORATTON
PA-z&I81, CHEROKEE ARCHER U
THIS PÀGE ¡NTENTIONALLY LEFT BLA¡VK
ISSUED: JUNE 18' l9?6
)
PIPER AIRCR,A,FT CORPORÄTION
PA.28.T8T, CIÍEROKEE ARCHER U
(0
Ìvliscellaneous
Item
No.
65
Item
Foirva¡d
Seat Belts (2)
Piper Spec. PS500394-2A'
Cert.
Basis - TSO C22f
Rea¡ Seat Belts
Piper Spec.
(2).
PS500394-3
Cert. Basis - TSO C22f
Ma¡k
Instl.
if
sEcÍIoN
6
ì¡rsrGHT AND BAL.A,NCE
A¡m
Aft
(In.)
Moment
Datum
(Lb-ln.)
'ISSUED: JUNE 18,.1976
R-EPORT: VB-790
627
PIPER A¡RCRAFT CORPOR.A'TION
PÄ-2&1 81, CHEROKEE ARCHER
II
THIS PAGE INTENTIONALLY LEFT BLANK
ISSUED: JUNE
l8'
1976
PIPER AIRCRÅFT CORPORÂTION
PÄ.26-I8I, CEEROKEE ARCTIER
II
(g)
Engine and Engine Àccessories
(Optional Eqúipment)
Item sEcTloN
6
}IT¡GHTAND BALANCE
Ârm
Aft
(In.)
Moment
Datum
(Lbln.)
ISSUED: JUNE 18, 1976
)
PIPER AIRCRAFT CORPOR,A,TION
PÄ-28.181, CITEBOKEE t-
ÀRCHER tr
(h)
Propeller and Propeller Accessories
(Optional Equipment)
Item
No.
Item
Ma¡k
Instl.
if
SECTION 6
WÈIGHTÀND BAIANCE
Arm
Aft
(In.)
Moment
Datum
(Ltrln.)
ISSUED: JUNE 18, 1976
PIPER AIRCR.AFT CO RPO
PA.2&18I, CITEROKEE
RÄTION
ARCHER tr
THIS PAGE INTENTIONALLY LEFT BLANK
PORT:
1
VÞ?Ð
ISSUED: JUNE 18,1976
PIPER ÂIRCR-A,FT CORPORATION
PA.28.I 81, CIIEROKEE ARCHER
II
(i)
La¡di¡ig Gear and Brakes
(Optional Equipmenr)
Item
No.
't3
78
Item
Nose Wheel Fairing
Piper Dwg. 65348-2
Cert. B¿sis - TC 2À13
Main Wheel Fai¡ings
Piper Dwg. 6523?
Cert. Basis
-TC2Al3
Nose Wheel Fairing
Piper Dwg. 3'1896-3
Cert.
B¿sis - TC 2A13
Main tilheel Fairings
Piper Dwg. 37885-2, -3
Cert. Basis -TC2A13
Nose Wheel Fairing
Piper Dwg. 37896-3
Cen. Basis - TC 2Al3
Main Wheel Fairings
Píper Dwg. '19893-2,
Cert. Basis
-3
-TC2Al3
SECTION
6
WEIGHT AND BALANCE
X
K
Ma¡k
Instl.
if
lVeight
(Pounds)
Arm
Aft
(In.)
Moment
Datum
(Lb-In.)
103
20.6
38
J.b
'76
36.3
I 13.6
36.3
I 13.6
36.3
I 13.ó
863
3"14
2340
138
193 l
ISSUED: JUNE 18, 1976
RE\¡ISED: FEBRUARY
2E, tgTg
REPORT: VB-790
633
PIPER,A,IRCR,A,FT CORPOR,A,TI ON
PA-28.I81, CIIEROKEE ÄRCHER
II
(t)
ElectricalEquipment
(Optional Equipment)
Ite¡q
No, Item
Ma¡k
Instl.
if
lVeight
(Pounds)
9l
93
95
99
79
81
83
85
87
I¡strument Panel Li ghts
Cert. Basís - TC 2Ä13
Instrument Light
Grimes l5-0083-7
Cert. Basis - TC 2Al3
Cabin Light
Cert. Basis - TC 2Ä13
La¡ding Light, c.
E.
Model 4509
Cert.
Basis - TC 2A,13
Navigation Liehts (Wing) (2)
Grimes Model 41285
(Red and Green)
Cert. Basis -TC2A13
Navigation Lieht (Rea¡) (1),
Grimes Model 2064
Cert. Basis -TC
CWhire)
2Al3
Rotating Beacon
Cert . Basis - TC 2Al3
Arti-Collision Lights
0Ving Tip) (Whelen)
Cert.
Basis - STC SA800EÄ
Heated Pitot Head,
Piper Dwg. 69Ml-7
Cert. Basis -TC 2A,13
Pipe¡ Pitch Trim
Piper Dwg. 69378-3
Cert. Basis - TC
2.A,13
Battery l2V 35 Ä.H.
Rebat R35 (lVt. 2?,2 lbs.)
Cert. Basis -TC2A13
:<
\-
K
X
x
0.3
0.1
0.3
l5
57
4.'7
2
*
5.3
lWeight and moment diffe¡ence between standa¡d and optional equipment,
ISSUED: JUNE 18, 1976
REYISED: JULY 3. 1978
WEIGHT,A,ND
SECTION 6
BALANCE
Arm
Aft
(In.)
Moment
Datum
(LbIn.)
62.8
99.0
99.0
t
3.l
I
06.6
28 t.0
263.4
15'7.9
100.0
145.6
r
68.0
t9
30
+5
56
39s
900
684
REPORT: VB-790
63s
CTTON 6
'IGHTAND
BALÂNC¡
0) Elect¡icalEquipment
(Optional EquiPment) (cont)
:m fo.
Item
Cl
Auxiliary Power RecePtacle,
Pipe¡ Dwg. 68815
Cert. Basis' TC 2Al3
13
Extemal Power Cable,
Piper Dwg. 62355
Cert. Basis
-TC 2^13
15
Lighter,
Universal
Ç20M62,
l2Volt
Cert.
Bâ<is
- TC 2Al3
Mark if Weight
A¡m
(In.)
Moment
Instl. (Pounds)
Aft
Dafum (Lb-h.) v
X
PIPER AIRCRAFT
CO RPO
RATION
PA-z&I81, CHEROKEE ARCHER
II
4.6
.2
142.8
62.9
6s7 i3
I
'ORT: VÞ790 ISSUED: ruNE 18, 1976
PIPER AIRCRAFT CORPORATION
PA.28-181, CIIEROKEE ¡,RCHER
II
(k)
lnstruments
(Optional Equipment)
Item
No.
113
115
tl7
119
t2l
122
123
125
\2'l
Item
Vacuum System Installation a. With Airborne Model
2llcc
Pump b. W;th Edo-Aire Model lUl28A Pump
Cert. Basis - TC 2A¡3
Attitude Gyro, Piper
Dwg. 99002-2,
-3,4
ot -8
Ce¡t. Basis - TSO C4c
Directional Gyro, Piper
Dwg. 99003-2,
-3,4
or -1
Cert. Basis - TSO C5c
Tru-Speed
Spec.
Indicator, Piper
PS50049-307
Ccrt. Brsis - TSO C2b
Encoding Altimeter,
Piper PS50008-6 or -7
Ce¡t. Basis - TSO Cl0b, C88
Altitude Digitizer
(United lnstrument P/N 5125-P3)
Cert. Basis - TSO C88
Vertical Speed
Piper Drvg. 99010-2,-4
Cert. Basis
- TSO C8b
or'5
Altemate Static Source
Cert. Basis
-TC2A13
Tunl and Slip lndicator.
Piper PS50030-2 or -3
Cert. Basis - TSO C3b
À{ark lnstl.
if
WeigJrt
(Pounds)
.\-
>r
Y
4.5
4.9
2.2
26
*.9
t.0
1.0
.4
2.6
SECTION
\r-rGHT ÀND BÀLANC
Arm (ln.)
Aft Datunl
39. I
39.1
59.4
59.'l
(same as standard equipment)
60.3
5t.5
65.9
61.0
59.'1
Itlonr er
(Lb-ln
176
192
131
155
54
57
6(
'),
J
+Weight a¡d moment difle¡ence between standa¡d and optional equípme¡t.
ISSUED: JUNE 18,1976
REVISED: l\{AY 23, 1980
REPORT: VB-79
63
:TION 6
IGHT AND BALAN{
(k)
Instruments
(Optional Equipment)
(cont) m o.
,_9
]l
Item
Exhaust Gas TemPerature'
Piper Dwg. 99026
Cert. Basis
- TC 2Al3
Manifold Pressure Gauge
Piper Spec. PS5003t'3 o¡
4
Cert. Basis
- TC 2^13
Engine Hour lleter
Piper Dyg. 79548-0
Cert. Basis
- TC 2413
Clock
Cert. Basis
- TC 2Al3
Âir Tenr¡crttturc Gcugc,
Piper Dwg. 99479-0 or -2
Cert, Basis
- TC 2Al3
PIPER
PA-z&I
AIRCRAFT CORPORAT]ON
8I, CHEROKEE ARCHER
II
Ma¡k
if
Weight
Instl.
(Pounds)
Y
Arm
Aft
(In.)
lvloment
Datum
(LFIn.)
55.4
39
60.8
09
03 18 6t.2
62.4
'12.6
IJ
PORT: VB-?90
8
ISSUED: JUNE 18,1976
REYISED: I\lAY 23' l9E0
PIPER
PA-28.1
AIRCRAFT CORPORATI ON
8I, CHEROKEE,A.RCHER
II
159
Item
AuloFlite
II
Cert.
Basis - STC SA3066SW-D
AutoControl IIIB a, Omni Coupler,
.lC38B
Cert. Basis - STC S/$065S1V-D
SECTION r
W¡TGHT ÄND B,A,LANCI-
Arm
Aft
(ln.) lr{ornclr
Datum
(LbJn.l
roN
6
;HT AND BALANC¡.
(m)
Radio EquiPment
(OPtional EquiPment)
;i:tå,fr
i8åÊfr
äf8fl^iHl'f il
Item
Coltins
VHF-25
VHF'250 or
I
Comm Transceive¡ a. Single
b.
Dual
Cert. Basis'TSO c38b
C37b'
Collins VIR-350 or
VIR-351 Nav Receiver a. Single
b.
DuaI
Cert. Basis -
TSO C40a,
C36c
Collins IND 350
( ) VOR/LOC
I¡dicato¡ a. Single
b.
Dual
Cert. Basis -
TSO C40a'
C36c
Collins IND 351 ( ) vOR/LOC
GS Indicrto¡
Cert. B¿sis
- TSO C40a,
C36c
Collins GLS-350
Glide SloPe Rec¿iver
Cert. Basis
- TSO C34c
Mark
Instl.
if
Weieht
(Pounds)
Arm
Aft
(ln.)
lr4oment
Datum
(LÞln.)
4.0
8'l s 6.9
56.9
228
461
3.9
1.9
10
20 l3
)o
> l.+
5',7.4
60.2
60.2
60.2
l 81.8
224
453
60 l?0
364
PORT: VB-790 i0
TSSUED: JUNE 18' 1976
REVISED: MAY 23' 19E0
'
PPETì AXICRJ4IT CORP OR,A.TION
PÀ-ã-i{, óri¡n-oxÈ¡
¡RcHER
rr
(m)
Radio Equipmenr
(Oprional Equipmenr) (cont)
Item
No.
Item
178
Collins DCE
400
Distance Computing Equipment
Cert. Basis _ TSO
C40a-
179
Co[ins RCR-650
Receiver and
ADF
A¡tenna
¿¡d IND650 Indic¿to¡
Cert. Basis - TSO C4lc
180
Coltins RCR - ó50A ADF
Receiver and antenna and
IND-6504 lndicaror
Cen. Basis - TSO C4lc l8l
Coli¡rs AMR-350
Audio/Marker panel
Cert. Basis - TSO C35d, c50b
183
Coli¡s TDR-950
Transponder
Cert.
Basis - TSO C74c
SE'
WEIGHTAND BI if Wejeht
Instl.
@ounds)
Arm (In.)
,A,ft Dàtum
2.t
58.9
6.6
104.8
7.3
I
00,3
"3.3
110.0
*2.8
62.9
t\Yeight
*rWeight ilcludes antenna.
includes anterìna and cable.
ISSUED: JUNE
18, 1976
REVISED: ItlAy23,
1980
RPORT: V
]CTION ó
EIGHT AND BALA].
(m)
Radio EquiPrrent
(OPtional Equipment) (cont) em
{o.
E7
89
9l
Item
Ki¡e KX 170
(
)
VHF
Comm/Nav a. Transceiver, Single
b.
T¡ansceíver, Dual
Cert' Basis
- TC 2413
Ki¡g KX 179,'( s ) a. Transceiver
VHF
b.
King KN 72 VOR/LOC
Converte¡
c.
King KN 73 Glide SloPe
Receive¡ d. King KN ?5 Glide SloPe e.
Receive¡
Ki¡s KN 77 VOR/LOC
Converter
f.
Kjng KI-204
VOR/ILS
Indicato¡
c.
Kinc KNI 520 VORÃLS
Indicator
Cert Basis
- TSO C36c' c37b, c38b, c40a
Ki¡e KX l?5
(
)
Vgr
a. T¡ansceiver (2nd)
b.
King KN 72 VOR/LOC
Converter
c.
Ki¡g KN ?7 VOR/LOC
Converte¡
d.
Ki¡e KI'203 VOR/ILS
Indicator e. King KNI 520 VORÂLS
Indicator
Cert. Basis - TSO C36c, c37b, c38b, c40a
PIPER AIRCRATT CORPORATION
PA-2&18I, CHEROKEE ARCHER tr
Mark
Instl.
if
\Yeight
(Pounds)
't.5
15.0
Arm
Aft
(h.)
Moment
Datum (Lb.In.)
56.6
56.6
425
849 k
9.4
1.3
J.¿
1.6
3.6
t.7
2.8
s6.6
r
83.6
184.3
184.3
183.6
6
0.5
60.5
661
103
169
532
239
590
295
8.6
i.3'
4.2
l6
28
56.6
I
83.6
183.6
60.5
60.5
487
239
'1'l
1
9'l r69
IIPORT: vÞ790
F42
ISSUED: JLINE lE' 197ó
REYISED: MAY 23' 1980
PIPER
PA.28.1
AIRCRÁFI CORPOR.A,TI ON
8I, CHEROKEE ARCHER
II
(m)
Radio Equipment
(OptlonaI Equipment) (cont)
Item
No.
193
Item
King KI 201
LOC Ind.
c. Siugle
(
) vOR/ b. Dual
Cert. Basis
-TC2A13 t94
195
96
197 t99
203
Kine KI 208 VOR/LOC
Indicato¡ a. Single b. Dual
Cert. Bæis - TSO C34c,
C36c, C40a
King KI 209 VOR/LOC/GS ln dicator
Cert. Bæis - TSO C34c,
C36c, C40a
Kine KI 213 VOR/LOC/GS
Indicator
Cert. Basis
-TC2Al3
Kins KI 214
(
)
voR/
LOC/GS ]nd.
Cert- Basis - ^ÎC 2A13
Ki¡e KN ?4 R-Nav
Cert. Basis - TC 24,13
King KN
6l
DME
Cert, Basis - TC 2413
King KN 65,4' DÀ,lE
Ce¡t. Bæis - TSO C66a
King KR 85 Djgitd ADF a. Audio ,{mplihe¡
Cert. Basis
- TSO C41b
N{ark
if
Instl.
Weight
(Pounds)
Arm
Aft
(ln.)
À{orncnt
Datum
(LbJn.)
2.5
5.0
s9.6
59.9
149
300
1.0
2.O
SECTION 6
W¡^<iHT AND BÄLANCE
59.6
59.9
60 t20
t2
25
12.5
13.0
86
08
33
47
59.9
60.4
59.9
5
6.6
r'79.0
1'7
4.9
8s.2
5 1.0
t5l
266
223'1
22't4
'133
4l
ISSUED: JLINE 18, 1976
RE\4SED: JULY 3, 1978
REPORT: Vß-r-9C
H3
cTtoN 6
JIGHTAND BALAN
PIPER AIRCRA-F'T
CORPO
RATION
PA.2&18I, CHEROKEE ARCHER II
:m o.
)7
)9
(m)
Radio EquiPment
(Optional EquiPmen t) (cont)
Item
King KR 86 ADF a.
Fint b.
Second
c.
Äudio Amplil-rer
Cert.
Basis
-TC 2Al3
King KMA 20
(
)
Audio
Panel
Cert. Basis
- TSO C35c' C50b
King KT 76
(
)178
(
Cert. Basis
- TSO C74b
) TransPonder
Mark
if
lnstl.
Weiglrt
(Pounds)
6,7
9.7
0.8
+3.7
*3.
I
Arm
Aft
(ln.) lt{or¡ent
Datum
(Lb-ln.)
9t.6
107.0
5 1.0
?
0.8
58.1
614
I
038
4t
262
80 eight includes antenna a¡d cable.
PORT: VB-790
4
ISSUED: JUNE
l8'
1976
REVISED: JULY
3' 1978
PIPER .A.IRCR.AFT CORPOR,A,TI ON
PA.2A.I 81, CIIEROKEE ARCÏIER tr
(m)
Radio Equipment
(Optional Equipment) (cont)
Item
No.
Item
213
Na¡co Comm l0A VFIF
T¡a¡sceive¡
Cert. Bæis - TC 2Al3
215
Na¡co Comm I lA VHF
T¡ansceive¡ a.
Single b. Dual
Cert. Basis - TC 2Al3
217
Na¡co Comm I lB VHF
Tra¡sceiver a.
Single b. Dual
219
Na¡co Comm I 1l VHF
T¡a¡sceíver a. Single b. Dual
Cert.
Bæis - TSO C37b, C38b
221
Narco Comm I l18 WIF
T¡a¡ sceive¡ a. Sirgle b. Dual
Cert. Basis - TSO C37b, C38b
?23
Na¡co Comm 1?0 VFIF
T¡a¡sceiver a.
Single b. Dual
Cert. Basis - TSO C37b, C38b
225
Na¡co Nav 10 VHF Receiver
Cert.
Basis - TC 2Al3
227
Na¡co Nav 11 WIF Receiver a. Single b. Dual
Cert. B¿sis
- TC 2Al3
229
Na¡co Nav l2 VHF Receiver
Cert. Basis
- TC 2Al3
ISSUED: JUNE 18, 1976
RIVISED: IULY 12,1971
SECTION
WEIGHT AND BAI-ANC
I{ark if Weight
Arm
(In.)
Momen
Instl. @ounds) Aft
Datum
(Lb-In..
3.9
3.6
7.1 s't.4
224 s7.4
20'l
51.4
408
3.9
't
.8
3.0
6.0
5'l.4
5't.4
57.4
51.4
224
448 t72
344
3.9
7.8
57
.4
5'1.4
224
448
4.8
8.6 t.9
2.8 s.6
3.4 s6.9
5'7.4
58.6 s8.6
58.6
58.6
2'13
494
199
REPORT: VB-7!
çt lll t64
328
m
),
I
]TION 6
IGIIT ÄND BALANu
(m)
Radio EquiPment
(Optional EquiPment)
(cont)
Item
Narco Nav l4 VHF Receiver
Cert. Bæis - TC 2Al3
Na¡coNavlll
Cert. Bæis - TSO C36c' C40a,
C66a
Na¡co Nav I
l2
Receive¡
Cert. Bæis - TSO C36c, C40a,
C66c,Cik
Narco Nav I l4 VHF Reeeiver
Cert. Basis'TSO C38b, C40a'
C36c, C34c' C66a
Na¡co Nav a.
Single
l2i
VgF Receiver
b.
Dual
Cert. BasÍs - TSO C36c, C40c'
C66a
Narco Nav a.
SingJe
b.
Dual
122YHF Receive¡
Cert. Bæis - TSO C35d, C36c,
C40c, C66a
Na¡co Nav l22AVHF Receiver a. Single
b.
Dual
Cert. Basis -
TSO C34c' C35d,
C36c, C40c, C66a
Na¡co Nav 124,4'
VIIF Receiver a. Single
b.
Dual
Cert. Basis - TSO C35d' C36c'
C40a, C66a
PIPER AIRCR,AFT CORPO
RATION
PA-2&18I, CHEROKEE ARCIIER N
Ma¡k
if
Instl.
We.ight
(Pounds)
Arm
Aft
(In,)
Moment
Datum (LÞIn.)
2.5
5',7.4
144
2.5
s
8.6
t4'1
3.3
58.6
193
2.5
3I
A) s7.4
58.4
58.4
144
l8r
362
+
5.1
+
8.6
*
5.2
*
8.8
+
6.2
*
10.9
994
829
98.5
82.2
92.3
11 a
507
113
5t2
1)'l
<11
841
:ight includes ma¡ker a¡tenna a¡d cable
PORT: VB-790
6
ISSUED: JUNE 18, 1976
REVISED: IULY 12,1977
PIPER A]RCR.AFT CORPORÄTION
P4.2J.181, CIIEROKEE ÄRCHER
II
(m)
Radio Equipment
(Optional Equipment) (cont)
Item,
No.
Item
247
Na¡co ID 124 VOR/LOC/GS
Indicator a. Sineje b. Dual
Cert. Bæis - TSO C34c, C35d,
C36c, C40c
249
Na¡co UGR-24 Glide Slope a.
SingJe b. Dual
Cert. Bæis - TSO C34b
251
Na¡co UGR-3 Glide Slope
Cert. Bæis - TC 2413
253
Na¡co MBT-I2-R, Marker
Beacon
Cert. Basis
- TC 2A13
255
Narco CP-125 Audio Selector
Panel
Cert. Bæis - TC 2À13
25'l
Narco CP-135 Audio Selecto¡
Panel
Cert.
Bæis - TSO C50b
259
Na¡co CP-l35M Audio Selector
Panel
Cert. Basis - TSO C50b, C35d
I
Narco DME-190
Cert. Bæis - TC 2Ä13
263
Na¡co DME-190 TSO
Cert.
Basis - TSO C66a
265
Narco DME-195
Receiver and Indicato¡
Cert. Bæis - TSO C66a tWeight includes marker a¡tenna a¡d cable.
"Weight íncludes a¡tenna and cable.
ISSLJED:'JUNE
REV-ISED:
18, 1976
IULY 12,1917
WETGHT AND
SECTION 6
BAIANCE
Ma¡k
if Weieht
Arm
(In.)
Moment
Instl. @ounds)
Afr
Darum
(Lb-In.)
1.2
2.4
60.5
60.5
73 t4s
*
+'
4.2
8.4
4.2
3.1
2.2
2.2
3.'t
*'5.9
5.9
'+13.2
154.0
220.0
154.0
69.1
55.0
55.0
114.3
60.9
60.9
154.5
641
1848
647
2t4
I ?1
l2l
2039
423
359
359
REPORT: VB-790
647
:CTION 6
EIGHT AND BALANUE
PIPER AIRCRAFT CORPORATION
PA-2&181, CHEROKEE ARCITER
II
(m)
Radio Equipment
(Optional EquiPment) (cont) lem
',1o.
Item
67
69
Na¡co ADF-140 a. Single
b.
DuaI
Cert. Basis - TSO C4lc
Narco ADF-I4l a. Singie
b.
Dual
Cert, Basis - TSO C4lc
7l
73
"t5
Na¡co AT50A TrarsPonder
Cert. Basis
- TSO C74b a. Na¡co AR-500 Altitude
Encoder
Cert . Basis
- TSO C88
Na¡co AT I
50 TrarsPonder
Cert. Basis
- TSO C74c a. Na¡co AR-500 Altitude
Encoder
Cert. Basis
- TSO C88
A¡tenna and Cable a. Nav Receivirg
b.
c.
'l
'2
VHF
VHF
Comm
Comm
d.
Güde Slope (Si¡gle) e. GIide Slope (Dual)
f.
Si¡eje ADF
Sense
Cert . Basis
- TC 2Al3
77 Anti Static A¡tenna and
Cable a. b.
'l
'2
VHF
VHF
Comm
Comm
c.
SinEJe A-DF Sense
Cen. Basis - TC 2,{13
'tg
Emergency Locator Transmitter
(C.C.C, Model CIR-l l-2) a. Antenna and Coax
b.
Shelf and Access Hole
Cen. Basis - TSO C9l tWeight includes dual antenna and cable.
tWeight i¡cludes anten¡a and cable' iPORT: VB-790
48
Mark
if
Instl.
Weight
@ounds)
6.0
+17.9
*m
Aft
(In.)
Moment
Dafum (Lb-In')
91.2
107.6
547 t926
6.0
*l'7.9
t'3.0
1.0
rr
3.0
1.0
t.4
0.7
0.8
0.9
2'8
0-4
91.2
107.6
5'1.3
51.5
57.3
51.5
t9 5.7
t25.7
147.5
120,0
154.0
r
50.0
547 t926 t'72 q':) t72
<t
214
88
I t8
108
431
60
1.4
1.5
0.5
t.7
0.2'-
0.
_-(
144.3
t70.7
147.5
236.2
224.4
235.4
202
256
74
402
45 l18
ISSUED: JUNE 18' 1976
REVISED: APRIL T3' 1979
PIPER ÂIRCRÄFT CORPORÄTI ON
PA-23-1 81 . CTIEROKEE ARCHER
II
(m)
Radio Equipment
(Optional Equipment) (cont)
Item
No.
280
281
¿öJ
28s
287 ltem
Emergency Locator Transmitter
(Narco Model ELT-t0) a. Antenna and Coax b. Shelf and Access Hole
Cert.
Basis - TSO C9l
Microphone a. PiperDwg.68856-10 b.. Piper Dwg. 6885611 c. PiperDwg.68856-12
Cert. Bæis - TC 2Al3
Boom Microphone - Headset
Piper Dwg. 3'1921-2
Ce¡t. Bosis
- TC ?413
Cabin Speaker
Cert. Basis - TC 2Al3
Headset, Piper Dwg.
68856-10
Cert. Bas.is - TC 2Al3
03
05
WT,IGHT AND
SECTION t
BALÄNCI
Ma¡k lnstl.
if
Weight
(Pounds)
Arm
(In.)
Motncnl
Aft
Datum
(Lb-ln.)
3.5
0.3
0.5
236.2
224.4
235.4
82'1
67
il8
0.3
0.6
0.3
64.9
69.9
64.9
l9
42 t9
80.5
99.0
60.0
24
ISSUED: JTJLY 12, 1977
RE\¡lSEDr APRIL I3,
I979
REPORT: VB-790
648a
Suppl.
Chpt 6
Equipment List
DiamOnd
Mass and Barance
MAINTENANCE
Reg.:
OE-DKï
Type.:
PA28-181
S/N.:
28-789024i
Man.:
PIPER
Date.;
22.02.06
Cert:
EODM-101; EMZ No.: RC/SA1 122 in conj. with FM-STC: SA00705W| a^k¡
PIPER AIRCR.AFT CORPORATION
P4.23.I8I, CHEROKEE ÂRCHER
II
(n)
lr{iscellaneous
(OptionaI Equipment)
Item
No.
Item
335
321
323
?1<
329
331
333
Zinc Ch¡omate Finish
Cert. Basis - TC 2Al3
Stainless
Cables
Steel Cont¡ol
Cert. Basis - TC
2,A,13
Air Conditioner,
Piper Dwg. 995?S-3
Cert. Basis - TC 2Al3
Ove¡head Vent System
Piper Dwg. '763U-9
Cert. Basis
-TC2Al3
Overhead Vent System with
Ground Ventilating Blower
Piper Dwg. 76304-tO
Cert.
Basis - TC 2À13
Assist Step,
Piper Dwg. 65384
Cert. Bæis - TC 2Al3
Super Cabin Sound
Piper Dwg.
796Tti
p¡oofi¡s
Cert. Basìs - TC
2,A,13
.Adjustable Front Seat (Left),
Piper Dwg.
79 59 t-0179 59 t-2
Cert. Basis - TC 2Al3
Adjustable F¡onr
Sear
(RiChÐ,
Piper Dw-e. 7959t-t l'r.959i-3
Cen. Basis - TC 2Al3 sEcTloN
6
WEIGHT AND
BAL,ANCE
À{a¡k
if
Instl.
Weighr
(Pounds)
5n
Arm
Aft
(In.)
Moment
Datum
(Lb-l¡J
158.0
79O
18.1
*6.6
14.9
1.8
*
6.8
68.3
64
103.6
t59.6
1',|2.2
156.0
86.8
80,7
80.0
707 6
1022
2566
281
1571
533
514
*Weiglt and moment difference between standa¡d and optional equipment.
ISSUED:
JTJNE
REVISED:
18, 1976
lULy
12.1977
REPORT: VB-790
A9
ECTION 6
EIGIil.AND BALA\W¿
(n)
Miscellaneous
(OptionaJ EquiPmen
¡) (cont) tem
No.
Item
39
4l
43
47 t49
Headæsts
(2) Front,
Piper Dwg. '7933'l-18
Cert. Basis -
TC 2Al3
Head¡ests (2) Rear'
Piper Dwg. 7933'l-18
Cert. Basis -
TC 2AI3
Inertia SafetY Belts
(Rea¡)
(2) 0.8 lbs. each, PiPer
PS50039¡-l 4
Cert. Basis -
TC ?Ai
3
Assist StraP, PiPer
Dwç79455
Cert. Basis - TC 2Al3
Deluxe CarPetirg
Ce¡t. Basis -
TC 2A l3
Fire Extinguisher, a. Piper Dwg.76161-?,
Scott 4221 l-00 b. Piper Dwe' 378'12-2,
Graviner ttAl0l4-01
Cert. Bæis
- TC 2Al3
PIPER AIRCRA-FT CORPO
RATION
PA.2&18I, CHEROKEE ÀRC}IER tr
Ma¡k
Instl.
if
Weight
(Pounds)
Arm
Afl
(In.)
Moment
Datum (LÞIn.)
11
22
t6
0.2
+2.8
4.6
5.6
94.5
132.1
t
40.3
r
09.5
10t.9
7 t.0
51.9
29t t85
32'l weight and moment difference between standa¡d and optional equiPment'
IEPORT: VB-790
-50
ISSUED: JUNE
REVISED:
18' 1976 ruLY 3' 1978
PIPER AIRCR,A,FT CORPOR-A,TION
PÄ.28.1 81, C}IEROKEE .ÄRCITER
II
'
(n)
Miscella¡eous
( Opüonal Equipment) (cont)
Item
No. ltem
WEIGHT AND
SECTION
6
BALANCE
Ma¡k
if
Instl.
.
Weight
Arm
(In.)
Moment
(pounas)
Aft
Darum
(Lb_In.)
) toTALOPTTONÀLEQUTPMENT
ISSUED: JUNE 18, 1976
PIPER AIRCRÁ¡T CORPORATION
PA.2&I8I, CIIEROKEE ARCHER tr
THIS PAGÐINTENTIONALLY LEFT BLANK
ISSUED: ruNE 18, l9?6
SECTION
7.
DESCRIPTION AND OPERATION
OF THE AIRPLANE AND ITS SYSTEMI
SECTION 7 - OESCRIPTION AND OPEBATION
OF THE AIRPLANE AND ITS SYSTEMS
I
Paragraph
TI.BLE OF CONTBTTS
SECTTON 7
DESCRTPTTON A}¡D OPER,A,TION
OF lUE rA.IRPL¿,¡{E AND ITS SYSTET\4S
1.37
Emergency LocatorTransmitter
Page
No.
'7
-l
7-l t-l t-J
'7-5
7-ó
't-8
7-10
7-t5
1-t
6
7-l8
7-21
7-21
't-22
7-22
7-22
't-23
'1-24
"t-24
REPORT: \¡B-790
f-i
IPR, AIRCRâ¡T CORPORATI ON
A-?*181, CEEROKEE iA.RCEER
tr
SECTION
7
DESCRIPTToN,AND OPERATION
SECTTON 7
DESCRIPTTON AND OPERATION
OF TEE AIRPLANE AND ITS bYSTN'IS
7.1
TIIEATRPLANE
The PA-28-181 Cherokee
'rur-place seating, two Ïundred is a singleængiae, pound baggage low-wing capacity, and monoplane a I 80
of
all metal ho¡sepowel engine.
construction.
It
hes
7.3
ÄIRFR,AME
The ba-çic airframe, except
for
a tubrfa¡ steel engine mount, steel landing gear st¡uts, a¡d othef miscell¿¡eous steel parts, is of aluminum alloy construction. The extrcmities stmcture is not designed fo¡ ae¡obatic loads.
.
the wing tips, the cowling, the tail su¡faces - are of fiberglass or ABS thermoplastic. Aerobatics are prohibíted irr this airplane si¡ce the
The semi-tapered wìngs have a lamina¡flow type NACA 651415 ai¡foil. The wings are attached to each síde
of
the fuselage by insertion of the butt ends of the reçective main çars into a spar box ca¡ry-1fuough which is an integral part of t¡e fuselage stuctu¡e, p¡oviding, in effect, a continuous mai¡ spar witå splices at each side of tåe fuælage. The¡e a¡e also fore a¡d aft attachmenE at t¡e rea¡ spâr a¡d at an auruliary front spar.
7.5
ENGINE AND PROPELLER
The Cherokee
l8l
is powered by a four cylinder, direct drive, horizontally opposed engine rared ar
180 horsepower at 2?00 rpm. vacuum pump drive, a
It
is furnished with a staner, at 60 ampere, l4 volt alternaror, a shielded ignirion, fuel pump, and a dry, automotivc typc cârburetor air filter,
The exhaust system is made entirely from stai¡less steel and is equipped with dual muffle¡s. A heate¡ sh¡oud a¡ound the mufflen is provided to snppìy heat fo¡ the cabin a¡d windshield defrosting.
The fixed-pitch propeller is made from a one-piece alloy forging.
ISSUED: JUNE 18, 1976
REvISED: MÀY 23;1980
REPORT: VB-790
7-l
ECTION 7
,ESCRIPTION AND OP¡,..ATION
PIPER AIRCRÁ¡'T CORPORATION
PA.2&181, CHR.OKEE ÀRCEER tr
REPORT: YB'790 h{.A,IN WHEEL ASSEMBLY
Figu¡e 7-l
ISSUED: JUNE 18, 1976
PIPER ÀIRCRAFT
C
ORPORáTI ON
P,{.2&I 81, CEEROKEE,A,RCEER
II
SECTION 7
DESCRIPTION,{ND OPER,A,TION
7.7
LÅNDING GE¡,R provided wjth bnl<e dn¡ms and Clevel¿nd single disc hydraulic
6,
Th9 tht g landing gears use Clevela¡d 6.00 four-ply rating, Type
III
ti¡es with tubes.
x
6 wheels, the main gear wheeis (Figure
7-l)
being brale assemblies. All tlree wñeet use'g.OO
i
and anduce tåe nose
gea¡.
The tl¡¡ee struts a¡e
0 inches of the ai¡-oil type, with a normal extension of 3.25 i¡ches fo¡ the nose for the main gear.
gear and
ISSUED: JUNE 18,
1976 REPORT: \IB-790
7-3
SECTION 7
DESCRIPTION Al{D OPg¡IATION
PIPER AIRCRAFT CORPO
RÄTION
PA.2&T 81, CEEROKEE ARCEER
II
REPORT: VB-790
74
THIS PAGE IMENTIONAILY LEFT BLANK
ISSUED: JUNE 18, 1976
)
PI?R AIRCR.{FT CORPOR,A,TION
PÄ.28.I81, CEEROI(EE ARCSER
II
SECTION
7
DESC RIPTION .A,ND OPER.A,TION
FLIGHT CONTROL CONSOLE
Figu¡e 7'3
7.9
FIJGHT CONTROIS
Dual confuols a¡e provided as standa¡d the zurfaces. The equipmen! with a cable system used between the cont¡ols and horizontal tail (stabilator) is of the all-movable slab type with a Eim lab mounted on the trailing edge of the stabilato¡ to ¡educe the cont¡ol system forces. This tab is acruated by a control wheel on the floor between tåe f¡ont seats
(Figure 7-3).
A rudder t¡im adjustment is mounted on the ri'ght side permits directional of the pedestal below the him as needed in flight (æfer to Fígu¡e 7-5).
throttle quadrant ard
The flaps are malually operated and æringloaded to rctum
-.corporated step ðn the in the actuating linkage holds the flap when it is right side. The flap will not support a step load except be'completeli ætrâcted when used æ a ltèp. The flaps have to the up posirion' in the up Position so-that
À it
Past'center may be used lock as a when in the full up position,-so it must three extended positions, 10, 25 a¡d 40 degrees.
ISSUED: JTJNrE
18,1976
REPORT: VB-790
7-5
SECTION 7
DESCRIPTION AND OPERÀTION
PIPER AIRCRI{FT CORPORÂTION
PA.2&18I, CEEROKEE ARCEER
tr
7.I1
ENGINECONTROLS
Engine contols consist of a thlottle control and a mixtur€ cont¡ol lever, These cont¡oh a¡e locaþd on the cont¡ol gu¿drüt on the lo\¡rer center of the instrumentpanel (Figuæ 7-5) whE¡e they are accessible to both the
pilot
and the copilot. The cont¡ols uti-lize teflon-lined contol cables to ¡educe friction and binding.
The tfuottle lever is used to adjust engine RPM. The mixtu¡e conþolleve¡ is used to adjust the ai¡ to fuel ratio. The engine is shut down by the placing of the mixture cont¡ol leYer in tIe full lean position. In addition,
tle
mixî¡¡e control lns a lock to prevent inadvertent activation of information on the lea¡ring procedure, see the Avco-Lycoming Operato¡'5 lvf¿¡ual.
the rnixtu¡e conEol, Fo¡
The dec¡ease frjction adjustment leve¡ on the ¡ight side ofthe conto¡ quadrart may be adjusted to inc¡ease c the friction holding the th¡ottle a¡d mixtu¡e controls o¡ to lock the cont¡ols in a selected positio.
The ca¡bu¡etor heat control leve¡ is locaþd panel. The control is placarded trith two posjtions: to the rigbt of the conùol quadrant on the instnrment
"ON' (dow¡), "OFF" (up).
REPORT:
\.Þ790
74
ISSUED: JIJNE 18, 1976
PIPER
P4.28-
1
ÂIRCRAFT CORPORÄTON
8 1, CHTROKEE AR'CIIER
II
SECTION
7
DESCRIMION AND OPERATION
ISSUED: JUNE 18,1976
CONTROL QU,A.DRANT ÀND CONSOLE
Figure 7-5
REPORT: vB-'190
7-7
SECTION
7
DESCRIPTION AND OPb\ATION
PIPER AIRCRAFT CORPORATION
PA.28-18I, CHEROKEE ARCHER
II
'a?
t:t,t-:----
4' l;-.--
4-;* j;¿ ,
FUEL SELECTOR
Figu¡e 7-7
7.13
FUELSYSTEM
Fuel is stored in two tu,enty-fìve gallon (24 gallons usable) tanks which a¡e secured to the leading edge structure of each wing by screws and nut plates'
The fuel selecto¡ control (Figure ?-7) is located on the left side-panel, fo¡wa¡d of the button on the selecto¡ court rnusi be depressed and held while the handle is moved pilot's to the seat- TTe
OFF position.
The button releases automatically when the handle is moved back into the ON position.
A¡
auxilia¡y electric fuel pump !s provided in case of failure of
tÏe
engine driven pump. The electric pump should be on for all takeoffs and landings, and when switching ta¡ks. The pump switch is located in the switch panel above the th¡ottle quadrant.
The fuel drains should be opened daily prior ras a¡r to
fìrit
individual drain at the bottom, inboaid rear comer' flìght to check for \¡/ater or sediment. Each
tmk
A
fuel st¡ai¡e¡, located on the lower left f¡ont of the lue wall, hæ a drai¡ which is accessible f¡om
>utside the nose se;don. The st¡aine¡ should also be drained befo¡e the raragraph 8.21 fo¡ the complete fuel cl¡airring procedu¡e.
hnt
flight of the day' Refe¡ to
ISSUED: JUNE 18,1976
REPORT: YB-790
7-8
PIPER,A,IRCR.dFT CORPOR,A,TION
PA-æ-I 8I. CEERO}'FF ARC:SER
tr
DESCRIPTION
SECTION
7
ÀI{D OPER.A.TION
LEFT XAIII TÄIT
PnlrtR sI n^HEt flJlt ÌÀtxstLtcTor
YÀ[Yt nt6HI
Hilll
T^llX
Ftjtt (lu^nfn
ÊruÊÊs
ISSUED: JUNE 18.1976
FUEL SYSTEM SC¡IEIì{.A,TIC
Figu¡e 7-9
REPORT: VB-790
7-9
SFITION 7
DESCRIPTION
AI{D O}..- áTION
Fuel guantity and instilment Panel' pressuæ a¡e indicated on gauges located
in
a cluster on the
left
side of the
An engine priming sysrcm is provided to lefi of thc facilitatc starting. Tlre primer pump is located to
ihtotìlt
quairant (refer to Figure 7-5)' the immediate
7,I5
ELECTRICAISYSTEM
The
elecfic
immediately forward lefi
aft side
alternator,
Panel a l2'volt battery' a voltage regulator' an
ovewoltagerelaylt).Thebatteryismountedj¡athermoplasticbox
Ie8iulatol and overvoltage ælay a¡e located on the
Electrical switches a¡e located located on t]le lo\4,e¡ right Lstrument
iL,
lights
;d
on the right center instilment panel, panel. Aiheostat switch on the radio Ug¡ts. frre si¡nilar switch on the right
-g F"
side ci¡cuit b¡eaken a¡E tÏe left side of t¡e s'¡¡itch panel controls controls and dims the panel
Sta¡dad etecuical accessories include a sta¡te¡, electric fuel pump, stall waming lighter, fuel gåuge, ammeter, ard annunciator panel' indicator, cigar
The a¡rnunciator panel includes a]ternator a¡rd syst"m is
íÁß ;"
,ñÑa
Lstalted, t¡¡å provided only a¡rnru¡aator as a
**¡ni
panel to also the low includes a pilot that oil a pressure
lol
indrcator vacuum system lights..When the indicato¡ may-not be lighl and monito¡ the appÍcable sistrm gangp to determine when or optional ryro
The annunciator panel operating properly, a¡d that he
if
any necessary action is required.
"¡è.f
Optional electrical acceso¡ies include navigtion
üChË';
and cabi¡ dome light. Ci¡cuits wilt handle equipment.
ligþts, anti+olli-sion tight, lariding light, instrument
th!
addition
of
communications a¡d navigational
WARNING
Strobe liglrts should not bc o and clouds silcc reflccred lig
Do not oPerate strobe lights takcoff and landing.
The words -rnaster switch'used hercafter in this manual indicatc both sides ofthe switch; battcry si'
-s,A,i.r,Jaiter¡ator
sideI'ALT- arc to bc depressed siroultaneously to OFF or ON as dirccted'
REPORT: vÞ790
7-1
0
ISSUED: JIJNE 18, 1976
REVISED: MAY 23' l9t0
PIPER AIRCR¿,FT CORPORATION
P4.28-l 81, CHEROKE,A,RCTEB
Ir
SECTION
7
DESCRIPTIU¡{ .A.ND OPER,A.TION
Unlike in ampeæs ammete¡ previors
ænerato¡ syste¡ns,
tle
will load be placed on tÌ¡e indicating the amou¡t the ammeter does not irdicate battery discharge;¡ather it displays altemator. With all of cha¡ging electrical equipment cuÍent shown dernanded on off (except mæter switch) by the battery. As each the ammete¡ will tell immediately the item of electical equipment is firrned on, the current will incrraæ to a total appearing on the ammete¡. This totat r uight flight, with radios on, is about 30 amperes.
for a fuJJy.charged battery, will appear continuously
if
the
t
of curent shown should equal the total amperage_
I un¡ec
æset
voltage relay.
.-.¡ninate
"ALT'
switc̡
for I
second to æset the
If
am¡nete¡ continues to indicate no output, maintaín minimum elect.ical load a¡d flight as soon æ practical.
ammeter during flight, reduce the electrical load by tuming off ck both 5 ampere field breake¡ and 60 ampere er ís open, tu¡n off the all ouþut brealer ard
CAUTION
Do not use cigar lighter receptacles as powersources for an¡,devices other than the cigar lighrers supplied wirh rhe airplane. Any other device plugged into these recepracles may be damaged.
ISSUED: JUNE I8, 1976
RE\rlSED: MARCH 30, I984
REPORT: \'B-790
7-11
sEcTtoN 7
DESCRIPTION
Al{D O'-.LATION
s1r¡fEi â ¡acessoñEs
PIPER AIRC RAFT CORPO RATION
PÄ-2&I8I, CEEROKEE ARCIIER
II
c^ÞrH
LIqT
ãfER& ffiR s*Eroro I
REW EIEIE¿ING CIM rltlEl sÍlÞi
REPORT: V8790
7-12
AITERNATOR AND STARTER SCHElYfrA'TlC
Figure 7-l I
ISSUED: JUNE 18, 1976
PIPER AJRCRÄFT CORPOR,A,TION
PA.æ.I EI. CEEROKEE ARCTER tr
.
SECTION 7
DESCRIPTIOI AND OPERATION
ISSUED: JIJNE 18. 1976
. -i.
RFORT: VB-790
7-13
SECTION 7
DESCRIPTION AND OPÞ'dTION
PIPER ÀIRCRAFT CORPORATION
iÃ-ãliat,
cEERoKEE ARcEER
II
TTTIS PAGE IMENTIONALLY LEFT BLANK
I
PIPER AIRCR,AFT CORPORATION
PA-2¡.18I, CTIEROKEE ARCSER
II
SECTION 7
DESCRIPTION AND OPER,A,TION
7.17 V,A,CLUM SYSTB{
The lac di¡ectional vacuum
'¡'m
system
is
designed and attitude gy¡os,when regulator, a filter and the
to
i¡stall..eg. necessary operate
Þlumbine the
ai¡
d¡iven
The system consists
glro
instruments. This i¡cludes the of an engine dri""n u".uu¡¡ pump;;
_
The vacuum pump is z plumbing' inoperative.
dry lype pump r,vhich elimi¡ates'the need for an air/oil æpæator and its
A
shear drive
Protects the pump from damage,
If tïe
drive shea¡s, the gytår
*iX b;.;;;
ent panel to the right ofthe radios, provides valuable to prevent possible damage to the system componenb
A vacuu vacuum at thei¡ rhe
¡eads
¡ated
regurator
p¡otect the
g/
provides
suffici
flåäir?j?å
normal e gy¡os eliibre.
ISSUED: JUNE 18,1976
REPORT: VR790
7_15
SECTION 7
ofSCrumOX
AND OPLTLATION
7.r9
INSTRUIYIENT PAI'IEL systems.
alfunction
in
the altemator' oil pressuæ' o¡ vacuum
REPORT: YF790
7-16
ISSUED: JIJNE
l8'
1976
ì.I
H\O
{o
:i t
H l¡
TN
I
H
2
lrl
-æ
{
\o o\
OLD Version
¡d ¡ú
ÞE
FH
FÈ
^a)
HT
ãT
Xl,) hrl trl
O
ã
L3 fiã
FO
nz
2
3
¡1 F qt
Ì3
È l'rt r.
t. cLocK
2. TURN INOICAIOR
¡. AIRSPEED INDICATOR
.. DIRECTIONAL OYRO
5. ATTITUOECYRO
6. VERTICALSPEED INOICAIOR
I. ALTIMETER
¡. ANNUNCIATOR PANEL
MAGNETICCOMPAS
', OMNI
&
GLIDE
SLOPE INOICAIORS
I I. TRANSPONDER
I2. MARKER BErcON
IJ. AUOIO SELECTOR PANEL
I'. VHF TRANSCEIVERS
II. ADF RECEIVER
I5. DME RECEIVER
I'. ENGINEHOURMEIER
!. SUCTION OAUOE I
I9. HEAT¿ DEFROSI
CONTROL
¡0. CIGAR LIGHTER
2I. MIKE JACK
22. PHONE JACK
23. AUTOP|LOI
2
I. ENGINE INSTRUMENT CLUSTER
2S. OMN¡ COUPLER
26. NAVSWTTCH
Z'. MAGNETO& sTARTER SWITCH
2I. PITCH CONTROL
29. MANIFOLO PRESURE
IO. TACHOMEIER
3I. FUELGAUOE
]2. PRIMER
I¡. MICROPHONE
¡I. THROTTLEOUADRANT
J5. FRICTION LOCK
J6. CAREUREIOR
GAUOE
!7. EOT INDICATOR
HEAT
C ONTROL
]I. INSTRUMENI
PANEL LIGHTS
¡9. CIRCUII
EREAKER PANEL
IO. CLIMATECONTROL
I
lrt
E
(t
H oj
z''
à
U
o rlF'
fg
å2
Z*¡
SECTION 7
DESCRIPTION
AND OP.
-
^TION
7,21
PITOT.STATIC SYSTEM.
The system supplies optional vertical speed both
pitot
and static i¡dicato¡ (Figrue 7'17)'
Ptessuæ
for
the airspeed indic¡tor, altimeter, and the
Pitot and static Pressu¡e are picked up by carriJ tlgough pitot and st¿tic
ünà wittrin-Ure a pitothead instaled on the bottom of the left wi¡g and wing and fuselage to the gauges on the i¡strument panel'
An alternåte static source is available æ optional equipment' left side of tjre instrument pa"rr,
;;l;;r-;ã
,hp"r¿
ittdicatoi
wrr*
will tl¡e be valviis using set cabin in aj¡ the for
The conbolvalve is located below the altemate position, tlle static pressurc' The altimeter, vertical speed stonn wi¡dow and cabi¡
In*t
be clos-ed an¿ tf¡e caUin heate¡ andãefroster must be
ff,. Ati-tt"t
erro¡ is less th¿n 50 feet u¡less otlterwise placarded' on during alternate statíc sou¡ce operation' side
Both the pitot and static lines of the fuselage interio¡.
c¿n be d¡ained th¡oueh sepa¡ate d¡ain valves located on tl¡e left lowe:
A
heated
pitot
head, which alleviaþs prcblsms with icing and heavy rain,- is available as optional
,quip.rf nr'r*it.h
foi
the heated pitot head is locaæd on the electrical switch panel right conþol wheel.
to tl¡e left of the ourt
To prevent bug5 aad water from entering the pitot a¡¡d static pressure holes-, a
tfti'pitot
treaA]A partialy or completeþ blocked pitot head will give e¡¡atic cove¡ should be placed or zero ¡eadi¡Es on the i¡st¡uments.
NOTE
During the prefüght, check to
¡emoved, make su¡e the
pitot
cove¡ is
REFORT: YB-790
7-18
ISSUED: JUNE 18, 1976
REVISED: IULY 12.1977
PIPER AIRCRAFI CORPORAT¡ON
PÄ.24.1 81, CHEROKEE ARCHER
II
.
DESCzuPTìdN AND OPER,A,TION f¿ sEcTloN
7
ISSUED: JUNE 18,1976
PITOT.STÄTIC SYSTEM
Fieure 7-17
EU ou cÃø
Eo-
{l
UO iïf; u¡9r-:
'f;
I q
ËãÞ5ãH
.J;J;;J
REPORT: vB-79
7-11
sEcTroN 7
DESCRIPIION,A,ND
OPi,ATION
PIPER AIRCRAFT CORPORATION
PA.28.I8I, CHEROKEE Ä'RCHER tr
J
ú ts
Lo , !
d,
6 o
,;
5bãP
.Fd
¡
äüsüËËEEäã
üããgñrEäEË;r
ÍËieË5BdËiÜË
iñÉ-ú tr<
-U
-z tr<
BO
õÕ
t-
HEATING AND VENTILATING SYSTET'I
Figure 7-19
ISSUED: JUNE
l8'
1976
REPORT: VB-790
7-20
PIPER AIRCRÂFT CORPORATION
PA.2&18I, TFFROKE
ARCEER
tr
DESCRIPTION
SECTION 7
AND OPER.A,TION
7.23 EEATING A¡{D YENTTLATING SYSTEM
Heat for the c¿bin inJgrigr and the def¡oste¡ system is provided by exhaust system fa¡ rieht side
(Figu¡e
7-19). The amount of the instnrment panel.
I
heåter muff attached ofheat desi¡ed can be regulatedwith the contols located to the on the ducts
The next ai¡ flow caa be regulated between the front a¡d rea¡ seats to the console.
by leve¡s located on top of the heat
Fæsh ai¡ located rtional
.rcorporated opemted by a inlets a¡e located. on t}le side of
equipment. in the
ventilating system
\À,i
"FAN"
the
i¡
cabin the leadilg nea¡ edge the ftoo¡ ãt of the each seat outlet rying able
æ
'
,.I¡W
near the fixelage. Aa adjustable outlet is lõcation; ove¡head-ai¡
o"lJt -.-ofLr"lÃ
CATJTION lVhen cabin heat is operated, heat duct su¡face becomes could ¡ezult
in
bums hot. This
if
arms o¡ legs are placed too close to heat duct outlets o¡ su¡face.
7.25 CÄBIN¡EÄTURES optional verticål adjustment may be added to tt¡e
, the f¡ont seats a¡e adjrstable fore a¡d aft.
Rea¡ seat installations incoçorate the ¡ea¡ seats can be removed. g the latching mechanjsms
90.
leg
Relãasing the with a
The retainers coin n late¡ models by depressing the plunger behjnd
ttt
available with optional o¡ each
tonlss#l.tttt'
head¡ests a¡d
The cabin interior includes a pockets on Îl¡e bacla of eech front pilot seat.
storm window, two sun visors, æh trays, two map pockets, and
A single strap shoulder_hamess is offe¡ed as an option cont¡olled by an inertia ¡eel is standa¡d equipment for the front for the ¡ea¡ seats. The shoulder strap is ¡outed over'thå shoulder adjacent
'¿¿indows and attached to the lap belt in the general area of the ienon's i¡boa¡d hip.
seats, to the place and
A
check under of the inerlia this test and prevent the strap from extending. Under iormal .ou"rn"-nt the strap will
¡et¡act as required.
reel mechanism is made by pulling sharply on the strap. The reel will lock
i¡
extend
ISSUED: JLJNE 18, 1976
REVISED: JULY 3, 1978
REPORT: VB-790
7_21
SECTION 7
DESCRIPTION A},f
D OPE.TÌ,A'TION
PIPER ÀIRCRAFT CORPO pÀ-zstet,
RÀTION cEERoKEE ARcHER tr
7.27 BAGGAGEAREA
A 24
otbic through an outside Urgguæ"äõt-'on the right
ütJl*"ittpu foot are baggage area, provided and located behind the lear seats, should be used side of at all times' is accessible eithe¡ f¡om the cabi¡ or the ai¡c¡aft' Maximum capacity is 200 pounds'
NOTE
It is the pilot's responsibility to be suæ
Uot to Section 6'Weight and Balance)' when the baggage is loaded t¡t'Ãotft
i'C.
f¿t
within the allowable C'G' Range
(æfer
7.29 STATLWARNING
7.3I FINISH
Aìl exterior surfaces are primed with etching primer and fìnished with acn4ic lacquer'
REPORT: VB'790
7-22
TSSUED: JUNE lE. l9?6
REVISED: MARCH 30. l9E4
PIPER AIRCRáFT CORPOR,A,TION
PA.2&181, CEEROKEÉ ARCIIER tr
DESCRIPTIOÑ
SECTION 7
AND OPERATION
7.33 AIRCONDITONING'
The ah conditioning sysæ1 is a recirculating air system. The major items i¡clude: condenser, compæsso¡, blower, switches and temperatu¡e cont¡ols.
evaporâtor,
The evaporator is Jocated is used for ai¡ conditioning.
behi¡d the left ¡ear side of the baggage compartment. This cools the ai¡ that
The condenæ¡ is mounted on
Â
¡et¡actâble scoop located on the bottom of the fuselage and to of the baggage compartment a¡ea, The scoop extends when the air conditione¡ is "ON"-a¡a flush position when the system is
.,OFF." the ¡eai
t.to.t iol
The compresso¡ is mounted on the forwa¡d right undenide of the engine.
'ch automatically engages or disengages the compressor to the belt drive system
It
has an of t¡e electric clutch
compressor.
-
An electrical blower is mounted on the aft side of the ¡ear cabin panel. drawa.t¡rough the evaporator by the blower located adjacent to eech occupant.
and distributed through
Air anìverhead f¡om the duct to baggage area is individual outles
Ïhe switches and temperature contol center contol a¡e located panel. The tempemtuæ on contol the lower right
¡egulates thJ side of the instrument panel in the clim¿te desi¡ed tempelatu¡e
Tum the control clockwise fo¡ increased cooling cou¡terclockwise fo¡ dec¡eased
"ooling, of the cabin.
Located
"oN'oFF'
fo¡ ai¡ condenser
inbo switch. conditione¡
doo¡.
Co is
the fan
çeed
switch
a¡d
the air conditioning dently of the a'r conditioning. However, it must be on' ff wri dise¡gaæ the compreõor clutch a¡d ¡eûact t¡e
¡ninute aftei the ai¡ conditioner is turned on.
NOTE
If
the sysæm is not operating
in
5 minutes,
tum
the system
"OFF" until the fault is cor¡ected.
The "FAN" switch allows operation of the fan with the ai¡ conditione¡ turned "OFF" to ci¡culation
if
outlets located desi¡ed.
.A' "LOW," "MED" or "HIGH" flow of ai¡ can be in the ove¡head ducl The outlets ca¡ be adjusted o¡ tumed off by i¡ dividual coolin g effect.
selected to each the aid cabin ai¡
¿i¡ conditione¡ occupânt to regulate
The "DOOR OPEN" indicator light is located to the left of the
Li"r't illumi¡ates wheneve¡ the condense¡ door is open and ¡emains on
¡ad.io stack in f¡ont of the pilot.
The until the doo¡ js closed.
A ci¡cuit b¡eaker located on the ci¡cuit breaker panel protects the ai¡ conditioning electrical system.
compæssor
]he
\'Vheneve¡ is ¡eta¡ded dry ai¡.
the th¡ottle is in the full tluottle position,
it
actuates a mic¡o switch a¡d retacts the scoop. Thi! is done to obtain maximum power and maximum fan conti¡ues to operate a¡d the ai¡ will ¡emai¡ cool for approximately one which disengages
¡ate the
òfitimU.
minute. when the thottle approximately 114 nch, the clutch will engaç atrd th" scoop will extend, again supplying cool, rOptionaJ equipment
ISSUED: JUNE I8, 1976
REPORT: vB-790
7-23
sEcrloN
7
DESCRTPTION
Æ{D OT..,áTION
7.35 PIPER
Þ(TERNAI POWERI
An
optional starting i¡stallation known as Piper External Power
,...piãålr io.áiã
on
gr.iigitî
s¿t of trt. fuselage aft õf the wing Aa
(PEP) external is accessible through a battery can be connected to t̡e socket, thus allowing
tiri.p"ãt*.t"
c¡'a"f'Oe engi¡e withóut having to gair acces to the airplane's battery.
7.37 EMERGENCY LOCATOR TRANSMITTERT the requirements
Lo lea led em be
of FAR 9l'52'
ocated
on ese
the scr
lagejust his Plare d with a lade, etc, lfthere are no tools available in an emergency
ELT is an emergency locator transmilter which meet: ate is marked on the t¡ansmitter to comply with FAA regulatioDs, the battery this date. The battery must also be replacèdif the transmittcr has been used in a¡ accumulated test time exceeds one iour, or if the unit has been inadvertently d time period.
NOTE
If
for any reason a test transmission is necessary'
tle
test lransmission should be couducted only in tbc
fint
five minutes of any hour and limited to three audio sweeps. If the tests lnust be made at any other time, tbe tests should be coordinated with the nearest
FAA tower or flight service statiou'
NARCO ELT IO OPERATION sers
On the the
ELT unit itself is a threc position switch placarded
"ON,'"OFF
and'ARM"'TheARM position
ÈlT
so rhat ir will transmit after impact and- will continue to transmit until its battery is drained' The
ÂñV !ãti,i""
is selected when the ELT
ii
installed in thc airplanc and it should remain in that position'
To use the ELT as a
Portable mounting base.
The antenna cable is tus on the lwo small wires will break mãrked
'PULL
FULLY TO EXTE
In the event the transminer is activated by an impact, it can only be turned off by moving
ELT unit to OFF. Normal operation c¿n located on the top of rhc front face of the ELT and then moving thc switch to ARM.
the switch on tl then bc icstored by pressing the small clear pìastic reset buÌtoh
A pilot's remore switch located on the lcft side panel is
¡ror¡riniiAe the c¿bin. The pilot's rcmore switch is
;;.-ÁRñD
position. Moïing thc switch to ON placardeù-ON- will provided to aI_o1v tlrg aaivatc the and
-ARMED.- transmitter. t¡1¡¡milter to be turned on
The swi'.ch is
Moving normalìy in the switch.back
ÄRMED;;rition
will turn oif thc rransmitter only if the impact switch has not becn aclivated.
lo the rOptional equipment
REPORT: VB-790
7-24
ISSUED: JLNE 18, t976
REYISED: APR¡L 13. 1979
PIPER AIRCR¿FT CORPOR,A,TION
PA.28-181, CHEROKE /A,RCIIER tr
_ sEcTloN
7
DESCRIPTION AND OPERATION receiver bc
.50 nd
check
MHz shoul
OFF,
tb
to ascertain thc transnitter is silent.
CCC CIR
I
I.2 OPERATION r.
uni
If iare
g the ton a¡d ¡cturn the swirch to ARM. ground check.
soundlthe ELT may be access
.ou.,
Recheck aná with the
On the unit itself is a th position is provided to ser the continue to transmit until the position. The
-¡ain
ARM position in that position whenever the unit is installed be used as a ponablc transmitte¡ or in the event pcriodically test rhe funcrion of the transmitter.
Select the any reason,
OFF position wben changing the battery, when rearming or to discontinue tÌansrnission.
rhe unit if ir has been activated for
NOTE
If the switch has been placed in the ON position for any reason, the
OFF position has ro be selccted before selecting selected transmit direaly f¡om the ON position, in thc ARM posirion.
the
ent,í.
uñit will
If
eni¿
is continue ro
A pilot's remote s from inside the cabin.
switch is normally left to the OFF/RESETp the transmilte¡ fo¡ tests or other reasons, move the switch upwârd position as long as transmissio¡ is desired.
to the ON position and leave it in that
-
Tbe unit is equipped with a portable antenne to allow the locator to be removed of an emergency and used as a portable signal transmitter.
f¡om the aircraft in case
The locator should be checked during the ground activated. check by luning a radio reccivir
tolzl.so
chcck to make
MHz. have been activated and should be turned off immediately.
i.'',re
against outside interference.
If iheie
Reset certain the unit has not been accidentally
i";;;;ilt;;i;;
sound, the locator may to the ARM pårTtlon and check again tá
ISSUED: JUNE 18, 1976
REVISED: APRIL
13, 1979
REPORT: V8790
7-25
sEclrON 7
DESCRIPTION AND OPER.ATTON
PIPER
iÀ-zer
AIRCRAFT CORPORÂTION er, cEERoKEE ARcI{FR
u
TTIIS PAGE, INTENTIONÄLLY LEFT BLANK
J
SECTION 8 - AIRPLANE HANDLING, SERVICE & MAINTENANCE
SECTION 8 - AIRPLANE HANDLING. SERVICE & MAINTENANCE
TA¡LE
OF CONTB.IIS
sEcTtoN
8
AIRPLANE HANDIING,
SERYICING ANb À{ÄINTE}IANCE
Pa-ragraph
No.
8t
Gene¡al
.
Aþlane Inçection
Periods
8.9
8.1 I
8.13
8.1 5
8.1 7
P¡even tive Maintena¡ ce
Àþlane Alte¡ations
Ground Handling
Engine Air Filter
B¡akeService
....
Landing Gea¡ Se¡vjce
Propeller
Service
Oil Requirements 8.1 9
8.21
8.23
8.25
8.2'l
8.29
Fuel System
Ti¡e Inflation
Battery Sewice
Cleaning
Cold lVeathe¡ Operation
8-t I
8-l
I
8-l3
8-l3
8-t5
|
Page
No.
8-l
8-3
84 oa
8-6
8-8
8-8
REPORT: VB-790
8-i
PIPER A_TRCR, ,FT CORPORATION t
PA.28.I81, CHEROKEE ÀRCHER
tr
SECTION
E
HANDLIN G, SERYICING ÀND MÄINTENANCE
SECTTON
8
AIRPLANE HANDLING,
SERVICIN G, AND M,A.INTENANCE
E.I
GENERAL
This
Archer section provides general guidelines relaring lI. For complere mainrenance to the ins¡ruc¡ions, ¡efer to ¡he handling, servicing, and maintena¡ce pA-2g
Sèrvice Manual.
of rhe
Every owner should stay in close conLact with an autho¡ized Piper Service
ìervices Deparunent to obtain the latest informerion penaining
Cenrer or pipels
Cusromer to rheir airplane, and ro avail themselves of piper
.A.ircraft's suppon syslems.
Piper Aircraft Corporarion takes a conrinuing inære$ in having owners get airplane and keeping service releases it
i¡
includíng the best mechanical condidon. Consequendy,
Service Bu.llerins, Service
úre most effcieru use f¡om rheir eipei,Lircraft, from dme rc ri¡ne, issues læners, Service
Spares Lerærs, and oûlers reladng ro rhe airplane.
PiPe¡
direcdy
to
Depending
all
auùoriz
na¡ce rhe and
and
Unite labor
mandarcry. These are senr t ervice Cei¡en worldwide-
I i¡formarion is orovided lo
I
Service are sent ro
Lenen deal wirh product improvemens
Pþr
Sewice Cenren and, if necessary, give carefirl anention
¡o Service Lener informadon.
and servicing rechniques pe¡Éining
¡o gts 1x¡ss¡
n
the airplane. They
¡Ar{-registered owners in Oe U.S. Owners stroUá
I
|
I
Service Spares Ler¡ers offe¡ improved pans, kirs, and oprional equipmenr which were originally, ard which may be of inerest
!o r¡e owner.
nor available
Piper Aircraft Corporation offen a subscription service for Service Bultetins,
Spares Leners. Tbjs service is available [o inreresred persons such as
Service Lene¡s, and Service oulers, pilos, and mechanics a¡ a nomina] fee, and may be ob¡ained through an auúrorized Piper Sewice Center or Pipe/s Cus¡omer Services Deparrnenr.
Service ma¡uals, paru cauJogs, and revisions
Customer Services Deparunent.
þ
both, a¡e available from Piper Service Cenren or piper,s
A¡y correspondence regarding ùe ai¡plane should oper response.
include the aþlane model and serial number to ensurc
ISSUED: JUNE 18,1976
REVISED: JLINE 8, 1990
REPORT: vB-790
8-1
SECTION
I
HANDLING,
SERVICL
AND
MAINTENANCE pIpER
AIRCRT{,¡-[ CORPORATION
PA.28.18L CHEROKEE ARCIüR
tr
THIS PAGE INTENTIONALLY LEFT BLANK
)
PIPER A-IRCRAFT
CO RPORATION
PA.2E.T81, CHEROKEE ÄRCI{ER
tr
sEcTtoN
8
HANDLING, SERYIC¡
TG AND M,A.INTENANCE
83
AIRPLANE INSPECTION PERIODS on irems and requircd in_specdon intervals
2g Servic¿ Manual conrains appropriate for the pA-2g forms, and all perly uained, klowledgeable, and qualified mechanic ar tion ca¡not accept engine, propeuer, or accessory manufacpre¡s, o¡
Ai
, and,/o¡ not broughr ctions.issued
-by the
A owner'
Progresive
This
Inspecrion, approved involves ¡outine and deailed inspections ¡o inspecdon costs are reduced' and ùe by the Fe-rleral Aviation Administrarion trA,q,), is also available to allow maximum u¡ilizarion of maximum sEndard derails are available from piper Aircra-fr
Coçorationof continued airwonhiness the airplane. Maintena¡ce is
úe mainuined. complere the ln addirion, but in conjuncrion
Airwonhiness Cenifica¡e wirh
ûre in effect. The owner is respons requiremenrs a¡d for mainraining proper above, ûre
FAA
¿o.u,n.n,r.ioï in on all aircraft
;tljï:.**tt* o keep
A specrmgraphic analysis propedy' provides a good check be clea¡ed of rhe engine oil is available from of the intem¿l condirion orcharged regularly, and oil samples musr ofthe be raken sever¿l sources. engine.
This inspectiorr if performed
To be accura¡e.inducdon air file¡s must ind senr in ar regularinrervals.
ISSUED: JIJNE 18, 1976
REVISED: JUNE
& 1990
REPORT: VB-790
8-3
SECTION 8
HANDLING, SERVICING AND M.A,INTENANCE
PIPER AIRCRA¡-T CORPORATION
PA.2&18I, CIIEROKEE ARCI{ER tr
8.5
PREVENITI¡E MAINTENANCE
I
I
I
|
*. holder of a pilot cenificate issu cenain prevendve maintena¡ce æ which defined
tle
pilot owns and operates, and service.
arions (FAR) pan
61 may perfonn ay be performed orùy on an aircraff or air taxi/commercial operarions
I All other aircraft maintenance must be accomplished by a penon or faciliry appropriaæly ænificared by the
I
Federal AviaÉon Adminisration (FAA) to perform thar work
I
I Anytime mainlenance is accomplished, an entry must be made records. The entry shall include:
(t)
The date the work was accomplisheC.
(2)
Descriprion of the work-
(3)
Number of houn on tÌ¡e ai¡cr¿ft"
(4)
Tt¡e cenificare nunber of pilot performing
¡he woÈ.
(5)
Signaruæ of rhe inclividual doing rhe workin rhe appropriate aircraft mainrenance
REPORT: YB-790
8-4
ISSLJED: JIJNE 18, 1976
REYISED: JIJNE 8, 1990
PIPER .A,IRCRAFT COR.PORATI ON
PA-æ.I81, CHEROKEE ÄRCHER
II
SECTION 8
H]{NDLING, SERVICINL'-ÂND
}IAINTEI\ANCE
8.7 AIRPLANE ALTER.A,TTONS
lf
the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration.
lrlajor alte¡ations accomplished in acco¡dance r¡rith Advisory Circula¡ 43.13-2, when pcrforrncd by an A & l' mechanic, may be approved by the local FAA office. Majoralte¡ations to the basic airframe o¡ systems not covered by AC 43.13-2 require a Supplemental Type Ce¡tificate..
The owne¡ or pilot is required to ascertain that flre following Ai¡c¡aft Papers are in order antl in the ai¡craft.
(a)
To be displayed in the ai¡c¡aft at all times:
(l)
Ai¡c¡aft Ai¡wo¡thiness Ce¡tifìcate Fo¡m FAA-810G2.
. (2)
Ai¡c¡aft Registration Certificate Form FAA-8050-3.
(3)
Ai¡c¡aft Radio Station License
if
transmitters a¡e installed.
(b)
To be carried in the aì¡craft at all times:
(l)
Pilot's OperatingHardbook.
(2)
Weight and Balance data plus
a
copy
of
the latest Repair and Alte¡ation Form
FAA-337
, if applicable.
(3)
Ai¡c¡aft equipment list.
ÄlthougJr avaìlable the ai¡c¡aft a¡d engine logbooks are not required to be in the aircraft, they should be made upon request. Logbooks should be complete and
up
1o date. Good ¡ecords
will
¡educe m¡-i¡teua:tce cost by giving the mecha¡ic information about what has or has not been accomplislted.
ISSUED: JUNE 18,1976
REPORT: VB-790
8-5
SECTION 8
H¿NpLÛVC, SER\¡ICI\ ..,,{ND MAINTENANCE
PIPER AIRCRAFT CORPORATION
PÄ-2&181, CHEROKEE ARCHER tr
8.9
GROUND }IANDLING
(a)
Towing on of the ground by the use of the nose wheel steering ba¡ the baggge cómpartment that is or by power equipment that will tlle nose gea¡-steerinã assembly'
Towing lugs are incorporated as
Part of the nose gear fork'
CATIIION
\ilhentowingwithpowerequipment,donottum.the-rosegear ueyondits sierring iaclius in eithe¡ di¡ection, damage as to the nose gear and steering mecha¡rism' this will result in
CAUTION
Do not tow the airplane when the cont¡ols a¡e secured'
Intheeventtowinglinesaænecessary'tobothmaingearstrutsas
higjr up on u," tuuJr'Ã-pot less than fifteen iul.' Lintt
tttoi'i feei,ãd
a qualifìed
person
the nose and/or seat tail by not to mailtain cont¡ol by usc of the b¡akes.
(b)
Taxü¡g be i¡structed and aPProved utdown
Procedures as well roPeller back blast and taxi following cliecks should be performed:
' ill
(2)
Taxi a few feet forward
(3)
ouserve
-Jiíå-;Ë;;;r
Possible,
stati
(4)
When
taxüng
and slight apply
turni
p
tle
brakes to determine thei¡ effectivenes' ascertai¡ tlte e airPlane' effectiveness when taxüng nea¡ buildinss d holes and ruts' of the steeri¡g.
or othe¡ stationarv objects
(5)DonotoperRPMwhenrunninguportaxiìngover¡found containingloyloosematerialthatmaycausedamagetothe lf
ProPeller blades.
it i
,
ISSUED: JUNE 18' 1976
REPORT: YB,'790
8{
PIPER AIRCR-A,FT CORPOR,A,TION
PA.æ-l81, CHEROKEE ARCHER
TI
(c)
Parki:rg* sEcTtoN
H.{NDLING, SERVICING AND MAINTENANCE
I
CAI.IIION
Ca¡e should be taken when setting b¡akes that are overheated o¡ during cold lveâthe¡ when accumulated moisture mÃy freeze b¡ake.
^
(3)
Äileron used and stabilato¡ contols should be secu¡ed with the front seat belt and to properly block the wheels.
chocks
(d)
À{oori¡g
The procedures aþlane should be moo¡ed fo¡ immovability, security and protection. should be used fo¡ the proper mooring of the airplané:
(
l)
(2)
Head the airyla¡e
Ret¡act the into the wind flaps.
(3)
Immobilize the aile¡ons and if possible.
The following it snug.
stabilato¡ by looping tÌ¡e seat belt through t¡e control
(5)
wheel and pulling
(4)
Block the wheels.
Secu¡e tie-down loPes
45 degree angles
to to
the wing tie-down rings the ground. sufficient slack to avoid damage
When using and rope to the airplanJshou.td to the tail skid at approximately of non-syntìetjc th. rop.s contract.
material, leavã
cAuiloN
Use bowli¡e knots, square knots o¡ locked slip knots. Do plain slip knots.
not use
NOTE
Additional prepa¡ations ropes for Ëigh winds include using tie{own from the landing gea¡ fo¡ks and securing the rudde¡.
(6)
Install â pitot head flight.
(7)
Cabi¡ and cove¡
if
available. Be su¡e to remove the pitot head cover befo¡e baggage doors should be locked when the airplane is unattended.
ISSUED: JUNE 18,1976
REPORT: vB-790
8-7
SECTION 8 r¡,Al.fprn'¡C, SERvICINtt AND }ÍÀINTENANCE
PIPER AIRCRAFT CORPO
RATION
PÄ.2&I81. CHEROKEE ARCIIER tr
8.IT
E]'IGINEAIRFILTER
(a)
Removing Engine Àir Filter
(l)
Remove the lowe¡ cowl' izjR''o"ethel¡/ingnutssecuringthefilter'Removethef¡lter'
(b)
Cleaning Engine
Air Filter
Theinductionairf¡]te¡mustbecleanedatleastonceevery50hor¡n,andmo¡eoften,-even be daiJy, kepi when on hand oprräi¡ü fo¡ use ir, as a
ã"rty
rapid
.""ations.
replacement'
Ext¡a filte¡s a¡e inexpensive, and a spare
To clean the f¡lter:
(t)
Taptrreñlt-eigentlvtofemovedirtparticleqbeingcarefulnottodamagethefrlter'Di
¡lof *arî'ürJ;,í;r i"
any [qujd. bO
nOf
attempt to blow out di¡t with compressed
Àk.
(2)lftheorshowsanydamage,¡eplacc.itimmedialely.
(3) Wipc fiJte¡
clcan cloth and inslall the filte¡. Tlre usablc e: ear or 500 hours' whichever comes fi¡st' life of tlte
(c)
Instatlation Of Engine Ai¡ Filter
After cleaning or when replacing the fìlter, install the filterin the ¡eve¡se o¡der of ¡emoval'
8,T3 BR.AKE SERVICE
No adjustment of the brake cleara¡lces is necessary. excessively
ïorn,
they should be replaced with new $
Ernents'
lf
afte¡ extended service b¡ake blocks become
ISSUED: JUNE
18' l9?6
REPORT: VB'790
8-8
PIPER AIRCRAFT CORPOR,I,TI ON
P4.28-1 81, CHEROKEE ARCIIER
II
SECTION
8
HANDLING, SERVICINU AND I\IAINTE}IANCE
\\
\_J
\\
_)
"J
)
(J
ô<
Eo
UC
OU
G]
I oc
Eâ2
ø YU
{ d óE
ö¿
l"
ÍdHCÞ
r=òf;3iü
=öff?5õõ
JU>ótsUO
-'; ci -.:
ñ; j ud
OUd
38xr
F z
O
É)zo J
Ã:oif !l
;{Zú>ul(
UYUYU:..I
üÍTÍÍÉH irlrlVd
(âi!;iiL(z
OtrJEJ@I
\¿.
_
_._J
ì
BRáKE SYSTET{
Figure 8-l
ISSUED: JUNE 18, 1976 REPOIIT: vß-790
8_9
SECTION
8
HANDLING,
SERVIflÌ..
.åND MAINTENANCE
PIPER
PA.2&1
ÄIRCRAFT CORPO
RÀTION
8I, CHEROKEE .ARCHER tr
8.15
LANDING GEAR SERVICE
The tluee la¡rding gea¡s use cleveland tubes. (Refer to paragraph 8'23')
Atcraft P¡oducts 6.00 x 6, four-ply ratirrg, type
III
tires a¡d
\vheels a¡e ¡emoved brake segnent
in
place. by taking
M"tk tË
off the hub-cap, cotte¡ pin, axle nut,. and the two bolts and wheel fo¡ ¡ei¡stallation; then dismount
;;;;;;;-th; tL;"
intougn-totts from the wheel and separating the wheel halves' holding the by deflating the ti¡e' hould be serviced acco¡di¡g to the instructions ön aJ static load until 4'50
r'
'25 the i¡ches of oleo piston
t.25
inches' Should the strut exposure be below that the aþiane on jacks.
DePress the uP filler
Plug and slowlY rais" to the bottom ofthe fiL should fluid be below the valve co¡e removed; attacr¡ bottom
Jeaill"rti"
of the hot" f-dle¡ to plug the hole, oil valve stem should.be added' Replace the plug w-itJt of the fi1le¡ plug and submerge the otlle¡ end in a contai¡er from the contai¡er the main Bear strut rni¡imum
of I0
in extend more than again check
l2
inches. When air bubbles ceæe
fluid
level. Reinstall the valve core disconnected.
with fluid
^ir"b;; i¡
the stn¡t housing at the correct level, attach
;;
Û.r. c¡ou¡d, inflate the oleo strut to the cc rrect height' a used.
In jackj¡g the
Ät
least 250
ai¡c¡aft
Pounds
jacked up. The hYdraulic ai¡plane jacked uP until
ja
th strut pumP to the ai¡ valve a¡d with the
O; he is aitached a¡d the b¡llast add
Þ
.Oo
+
2' i¡
either di¡ection and is limited by stops the bottom of
tÏe
forging'
Therudde¡peda.larmstopsshouldbecarefullyadjustedsothattheq:du]T-'contactthestopsjust afrer the rudde¡ hits
itr rt;;;:il;;g"t;;t*,
6tat
¡tt
rudde¡
will
be allowed to move ttuoue¡ its full travel.
g
ISSUED: JUNE
I8'
1976
R-EPORT:
VB-790
8-1 0
PIPER AJRCRAFT
PA-28-181,
CORPORATION
CHEROKXE ARCHER
tr
8.T7 PROPELLER SERVICE
SECTION
I
HANDLING, SERWCING ÀND MAINTENANCT endy clea¡ed and inspected scrarches, and ce a corrosion.
lf
for cracks. Before eacl found, rhey should b( nick or scratch causes an area of incieased srresl eller dp, The back face
. of ùe blades should be painrec
To prévent cor¡osion, Ìhe surface should be
äleanec
8.19 OIL REQUIREMENTS
ùrar
The minim engine oil be drained and ¡enewed èvery 50 hours. hou¡s oJ operarion. monrhs. oil capaciry of rhe e¡gine is g quans and ¡he rtte
ìn¡.*a
under unfavorable dusry be¡ween
oil
condidons, and
¡¡. ol
oil
î
The filrer e fl fouowing seasonal aviail-on lr is recommended changed every 5c iåiirtfu!"tt
n,
-á
ol
I¡
Textron
ìs recommended that single
Lycoming Sewice ambient temperature or
lulti
viscosity aviadon grade oils in'dccordance wirh latest
Insm:ition
1014 be used. ranges are recommended: oit issue of
$âdes and seasonal
Avemge Ambien¡
Air Temper¿rure
For Sraning
All Temperarures
Above 80'F
.Above 60'F
30'F ¡o 90'F
0'F ro 70'F
0'F ro 90'F
Below 10'F
MIL-L.60828
Mineral
SA-E Grade
60
50
40
30
20w-s0
20
Mn--L-2285r
Ashless Dispersant
SA-E Grades
15W-50 or 20W-50
60
40 or 50
40
30, 40 or 20W40
20W-50 or 15W-50
30 or 20W-30 when operadng remperarures overrap ildicated ranges, use the lighrcr grade oil.
NOTE
Refer to the latest issue of Text¡on Lycoming
1014 (Lubricaúng OiI Recommen¿adons) for
Service lnsrrucrion dnher informadon.
8.21 FUEL SYSTEM
(a)
Servicing Fuel
Sysrem
Refer to the PA-28
Che¡okee sewicing and inspecrion
Service Manual and Period.ic Inspecr.ion Repon for fuel system
O)
Fuel Requiremenß (ÀVGAS ONLÐ
_. Aviation grade fuel with a minimum octille
of
100/130 must be used
in
rhis airp.lane.
Since the use warranty is invalidated
Insrruc¡ion of lower grades ca¡ cause serious damage by the use of lower octanes. in
Refer ro a
¡he shon period larest issue
No. 1070 for altemare fuets a¡d addidonal informarion.
of of rime, rhe
Lycoming eigine
Seriice
ISSUED:
JUN'E
REVISED:
18,1976
JLNE & 1990
REPORT: v8.790
8-1
I
SECTION
E
H,A.NDLING, SERYICIII¡r' AND MAINTENANCE
PIPER AIRCRAFT CORPORATION
PA-2E.18I, CHEROKEE ARCHER
II
A summary of
tle
current grades as well as rhe previous fuel designations is shown in folìowing charl:
ûle
FUEL GRADE COMPARISON CHART
Prevìous Commercial
Fuel Grades
(ASTM-D910)
Curren¡ Com¡nercial
Fuel Grades (ASTM-D9
10-75)
Cuæntlvfiliury
Fuel Grades
(MIL-G-5572Ð
100/130
115/145 green
Max. TEI
Grade
Color
mYU.S.
80/87 red
0.5
9t/96 blue
2.0
3.0
puqple
4.6
gi
Max. TEL
Grade Color mW.S. gal.
80 red
*l00LL blue
0.5
2.0
100 green
**3.0
none none none
Max. TEL
Grade Coior
mW.S. gal.
8Al8'1 rcd
0.5
none none none
100/130
115/145 blue
2.0
purple
4.6
-
'
Grade l00LL
Commercial approved fuel in fuel some overseas grade 100 and counlries is currenlly colored green and designared as grade 100/130 for use in all engines ce¡rifica¡ed for having use wi¡h grade 100/130 fuel.
"100L."
TEL con!en! of up ro
.! ml¡U.S. gallon are
The operarion of ¡he aircraft is approved wirh an anri-icing addidve in rhe fuel. When a¡ a¡uiicing addidve is used, it must ¡eflec¡ ¡he specificadon MIL-I 27ó86, mu$ be uniformally
ùe fuel while refueling, mus! not exæed .157o by volurne of rhe refueled quaùiry, blended wirh and ro ensu¡e
is
effectiveness mu$ be blended at not less than .lIvo by volume. One and one half liquid ozs. per ren gallons of fuel would fa.ll witiLin ùis rarge. A blender supplied by rhe addidve ma¡ufacrurer should be used. Except for the informarion contained in rhis secüon, rhe manufacrurels mixing or blending insrucrions should be carefully followed.
CAUTIONS
Assure tha¡ rhe addirive is direcred inro rhe flowing fuel slream. The additive flow should start after rhe srop before rhe fuel florv. Do not permir the concentrated additive to come in contact with the aircraft painred surfaces or the in¡erior surfaces of ¡¡e fueI tanks.
Some fuels have anri-icing addirives preblended in ùe fueI a¡ the refinery, so no furrher blending should performed.
be
REPORT: VB-790
3-l 1a
ISSUEDT MARCH 30, 1984
REYISED: JIJNE & 1990
PIPER AIRCRAFT
CORPORAT¡ON
PÄ.28.I8I CHEROKEE ARCHER ¡T
SECTION
8
HÄNDLING, SERVICING
. -,Ð MAINTENANCE
(c)
Fillìng Fuel Tanks
Observeall requiredprecautionsforhandlinggasoline.Fueljsstoredintwotwenty-fitegallon neck
There is approxi indicaror.
mately
I 7 gâllons in
I he fuel ra¡k whei fuel level is even wirh bott om of filler
ISSUED: I'IARCH 30, 1984
SECTION 8
H,A,NDLING. SERVICNi.
ND MAINTENANCE
PIPER AIRCRAFT CORPO Rr¿\TION
PA-2&18I, CHEROKEE ARCHER tr
FUEL DRAIN
Figure 8-3
(d)
Draini¡g Fuel Strainer' Sumps and Lires
REPORT: YB'790
8-12
CAUTION
When draining any amouÌìt of fuel, care shor¡ld be taken 1o ensure that no frre haza¡á exists befoæ starti¡g the enghe'
Each quick drain should be checked has closed completely and is after ciosing not leaking'
it
to make suæ
it
ISSUED: JIJNE 18' 1976
PIPER ÄIRCR,1.FT
CORPORTA,TION
PA.28-181, CIIEROKEE ARCHER
II
TIANDLING, SERYICING-AND
SECTION
8
MÂINTENANCE
(e)
D¡aining Fuel System end
The of bulk 9f t¡q each fu"l fuel ta¡k. may be drained
Pustr up on the th9 d¡ain open. The remaining fuel i¡dividual tank may be drained by in f¡om a¡ms
1]re the system ofthe system d¡ain by opening the valve-a¡á may be d¡ained closing tÍre selector valve and turn counte¡clockwise to hold through va.lve the at filte¡ the inboard
b;*i A"t
then draining the desi¡ed tank.
8.23
TTRE INFL,A,TION gear
For maximum service f¡om the tires, keep a¡rd 24 psi for the main gear. All wheels
the a¡d
'elationshjp of tire, tube a¡¡d wheel should be
maint
'
'(treme vib¡ation in the landiry gear; therefore, in the installation of new components, it may to ¡ebalance the wheels with the tires mounted. When checking cuts, bnrises, aad slippage.
p¡essuies - lg psi for the nose originâl instaliation, a¡d the
Unbalanced
*fr..t á*
tire pressureiexamine the be
"rr."
L", i;;;;;i
8.25 Bi4.TTERY SERVICE
,A'ccess
to the
compartment. The l2-voll bâttery
is
through en access battery box has a plastic tube which be.opcned gcga¡io,qitly fluid level. DO NOT only. Ä hydromete¡
äll
to drain the check off any accumulatíon of liquid. The battery strould battery above the baffle is parel at normally closed plates. DO NOT the right ¡ea¡ side fill oflwith the will determi¡e tJle percent oì charye in the battery.
a battery
of
cap and the baggage wtric¡ *iãuî¿
u..frr.t.a
with acid -
iãìpiãp.i
urJ*ri.,
^
. .If
F"
battery is not up to charge, recharge sta¡ting at a
Quick charges a¡e not ¡ecommended.
4
amp ¡ate and fi¡ish-ing with a 2 a¡¡p ¡ate.
8,27 CLEANING
(a)
Clea¡Ling Engine Compartment
Before cleaning the engine compa¡tment, place a strip pævent aay solvent from entering these units.
(l)
Place
(2)
With a large pan unde¡ the engine to catch waste.
the engiae cowling rernoved, spray of solvent and degreaser. or of tape on the magneto vents to brush the engine it may be necessary to brush a¡eas that were sprayed.
with solvent o¡
ã mixture
In o¡de¡ to remove especially heavy dirt and grease deposits,
CAT]-IION
Do not spray solvent into the altemator, vacuum pump, starte¡, o¡ ai¡ intakes.
(3)
Allow the solvent to remai¡ on the engine f¡om five to ten minutes. Then rinse engine clean with additional solvent and allow
it
to dry.
the
ISSUED: JUNE 18,1976
REPORT: VB-790
&r3
SFITION 8
HÄñiÑG,
SERVICIÌI
..NDMAINTENANCE
PIPER AIRCRAFT
iÃ-zcrar,
CORPORATION cHERoKEE ARcIIER tr
CAUTION
Do not operate the engine otherwise been removed' until excess solvent has evaporated or
l4l
ì;í
Remove the protective tape from
Lit;;;d-ini-"onuor.,'bearine
Chart.
the magnetos' su¡faces,
etc'' in
accordance with the Lubrication
(b)
Clea¡Ling
Landing Gear
(c)
Beforecleanjngthelandinggear,placeaplasticcoYerorsimila¡materialove¡thewheela¡d brake assemblY.
(1)
Plac! a pan under the gear to catch- was-te'
(2)
Sp¡ay o¡ bn¡sh
utîlE t *t
with.solvent desi¡ecl. wirere brush areas
rrå'avfþ;;d
d.irt o¡ a mixtwe of solvent and degreaser' as deposits have that weæ sprayed, in o¡der to clear them' collected,
it
may be necessary to
(3)
Àllow tt e
solveniî
ä;ú-ä;
the gear f¡om fìve to with additional solvent and allow to dry' ten minutes' Then ¡i¡se the gear
(4)
Remove the cover from the wheel and rem-ove
iS)
I-uU¡cate the gear the catch pan' in accordance with the Lubrication Cha¡t'
Clea¡ri¡g Exterior Surfaces or
The aþtane should be washed with a mild detergents could metal. Cover a¡eas make;";.1.-h; on
s paiated-
wherc cleaning solution
coul
ives or alkaline soaps d cause corrosion of the airplane' use the a sponge or a soft bristle brush' on to ¡emai¡ on the surface longer' a cloth damPened with naPhtla' d srufaces' Soft cleanirg n clean-ing or Polishing'
A the abrasion Problems in these areas.
(d) Clea¡ri¡g Wi¡dshield and Windows o)
(2)
(3)
CAUTION
Do not ur"
à"rolir,", alcohol, benzene, carbon thinne¡, acetone, or window cleanìrg sprays' tetracho¡ide'
,TiTlilüi,i,ili""
ISSLJED: JUNE 18' 1976
REPORT: vB-790
8-14
PIPER .ÀIRCR-A,FT CORPORÀTION
PA.2ß.181, CITEROKEE ARCHER
II
SECTION
8
HANDLING, SERYICING AND MAINTEN ANCE
(4)
Âfte¡ cleaning plastic surfaces, apply a
thi¡
coat of hard polishing wax. Rub ¡ìghtly with a soft cloth. Do not use a ci¡cula¡ motion.
(5) A
severê sc¡atch o¡ mar jeweler's rouge. Smooth
in
plastic can be ¡emoved by mbbing out the scratch with both sides and apply wax.
(e)
Cleanine Headliner,
Side Panels and Seats
(l)
Clea¡ headliner, side panels, and seats necessafy.
with a stiff bristle brush, and vacuum wÌæ¡e
(2)
Soiled upholstery, except leather, may be clea¡ed suitable soaking
fo¡
the material. Ca¡efully or harsh rubbing.
follow with a good upholstery cleaner the manufachrre¡'s instnrctions. Avoid
CAUTION
Solvent cleane¡s requte adequate ventilation.
(3)
Leathe¡ should be clea¡red with saddle soap o¡ a mild hand soap and wate¡.
(f)
Cleaning Carpets
To clean ca¡pets, fì¡st ¡emove loose di¡t with a whisk b¡oom or vacuuÍf, For soiled spotË and stubborn stains use a noninflammable dry cleaning fluid. Floor carpets may be removed a¡d cleaned like any household carpet.
8.29 COLD WEÄTHER OPERATION
Fo¡ cold weather operation a winterization plate is installed on the inlet opening ofthe oil coole¡ duct on the rigltt rear engine baffle. This plate should be installed whenever the ambjent temperature reaches
50o
F
o¡ less. exceeds 50o F
The plate should be ¡emoved and sto¡ed
in
the cockpit when the ambient temperature
It
is ¡ecommended that an optional Engine Breather Tube lVinterization
Kit
be installed for cold weathe¡ ope¡ation. This kit is available through you¡ Piper Deale¡/Distributor.
ISSUED: JLINE 18, 1976
RE\{ISED: JULY 3, 1928
REPORT: VB-790
&15
SECTION
8
Hñbtñô,
SERVIcIN
ND
MÄINTENANcE
PIPER AIRCR.AFT CORPORâTION
PA-28'1 81, cIIERoKEE ARcHER
II
)
THIS PAGEINTENTIONALLY LEFT BLANK
REPORT: VB-?9C
8-1 6
ISSUED: JUNE 18, 1976
SECTION
9.
SUPPLEMENTS
SECTION
9 -
SUPPLEMENTS
9.1
GENER,{L
This ;ïï,:îî. re
PIPER AIRCR.A.FT
P,A.-æ-l 81,
CORPOR,A,TI ON cHERoKEE ÁRcuËa
u
sEcTtoN
9
SUPPLEMENTS
SECTION
9
SI,JPPLEMENTS
Lî,ff""i:T;:,:îi"fi;låJi;1"ilî
J:::iffijxï:iiïlll
.d-Pl
The f: information airplane.
section a¡e
.,FAA.Approved,,and consecutively numbered contained iri
ãr.rr-sìppí.-r*t
applies only when as t¡e
ISSUED: JUNE 18, r976
REPORT: VB-790
9-l
ISSUED: JUNE
18' 1976
ì
PIPER AIRCRáFT CORPORATION
PÀ.æ.181, CIIEROKEE .A,RCHER
II
SECTION 9
SUPPLEMENTS
SI.JPPLEMENT
1
AIR CONDITIONING INSTAILATION
SECTION
I.
GENER.A,L
This supplement supplies information nec€ssary fo¡ the efficient operation of the airplane when optional air condìtioning system is installed. The information contained within t}ris used "as described" in conjunction with the complete handbook.
suppiement is to the be this
Tl.is supplement has been "FAA App¡oved" as a permanent pa¡t of this handbook a¡d ha¡dbook at all times when the optiona.l air conditioning system is installed.
must remai¡
i¡
SECTION 2. LIMITATIONS
(a)
To insu¡e prior maximum climb performance the aj¡ conditioner must be tu¡ned "OFF" manually
to
takeoff
to
disengage the compressor ând ¡etract the condenser door. Also the ajr conditioner must be tumed "OFF" manually befo¡e the landing approach in preparation for possible go-around.
a
(b)
Placa¡ds.
In
full view of the pilot, in the a¡ea of the ai¡ conditioner cont¡ols when the ai¡ conditione¡ installed: is
..WARNING
- AIR CONDITIONER MUST BE OFF TO INSURE
NORMAL TAKEOFF CUMB PERFORMANCE.''
In fr:ll view of the pi.lot, to the right of the engine gauges (condenser door light):
..4]R
COND DOOR
OPEN''
SECTION 3. E}IERGENCY PROCEDURES
No changes
to tle
basic Emergency P¡ocedu¡es provided
by
Section
3 of
this Pilot's Operating
-¿ndbook a¡e necessary for this supplement.
ISSUED: JUNE 18,1976 REPORT: VB-790
9-3
SECTION 9
STJPPLEì{EMS
PIPER AIRCRÂFT CORPORÁTION
PA-2&181, CHEROKEE ÀRCHER tr
SECTION 4. NORN{ÄL PROCEDURES
Prio¡ to takeoff, lhe air conditionef should be checked for proper operation as follows:
(a)
Check ai¡craft master switch "ON'" t-' Turn the ai¡ conditione¡ control switch
p"rit"",
- tfr" ai¡ conditione¡ condense¡ door actuation'
to
"ON" md
CONO OOOR OPEN" warning the fan switch
to
one of the operating light wi]l tum on, the¡eby indicating proper
(c)
Tum the ai¡ conditione¡ cont¡ol switch.to
"oFF" -
the "AIR COND DOOR OPEN" warning light will go orrt, t¡"trUy i¡dicating t¡e aii conditioner condenser doo¡ is in the up position'
, '
If
the "AIR COND DOOR OPEN" lig¡t does not respond as specified above, an ai¡ conditioner
,yri"*
or i¡alicato¡ Ur¡b malfunctio¡iis indicated and furthe¡ investigation should be conducteo p¡io¡ to flight.
The above operational check may be performed during flight ifan in flight failure is suspected'
The condenser
The doo¡ door light is located to the right of the engine instrument cluster lieht illuminates ri¡en the door is open a¡d is off when the door is closed'
i¡
front of the piJot'
SF,CTION 5
- PERFORMANCE
Operation of engine is required drag. When the rarge performance t air of the aþlane.
slight decreases co-ndenser door re is normally n ower f¡om the
Eht i¡c¡ease in limb' cruise or
NOTE
To insu¡e maximum climb performance the ai¡ conditioner must be turned and off manuaJly before takeoff to disengage the compressor ret¡act tite condJnse¡ door' Also the ai¡ conditioner must be turned
off
manually befo¡e t}te landing approach in preparation for a Possible go-around.
t¡,
A.ltliouflr the cruise speed ar¡d range
r¡ãíld
Ue
Ëo.prrrror is
extremely co'siAeieãlpi"fUcÃt operatinf hot weather' a¡e
.oni""ã'ùrv
only sli_ehtly affected by the 'ir-c.onditioner operation, p1¿"nine. while
fo
bã consewative, airplane the following is ai¡borne. This figures these
æsume.that
will
be the case only
'
(a)
The decrease in true airspeed is approximately 4 KTS at all power se-ttings.
iùi nr dec¡easein t-gr.áy be as much as
32 nautical miles fo¡ tJre
48 ga.llon caPacity'
ISSUED: JUNE 18,1976
REPORT: VB-790
94
PTPER .CIRCR,A.FT CORPORAT1ON
P4.28.181. CIIEROKEE i4.RC¡IER
II
SECTION
9
SUPPLEMENTS
The climb compressor performance is is declutched and the condense¡ position is selected. When the
$'ould cause the compressot not full compromised measurab.ly doo¡ is ¡euacled, both automatically, th¡ottle position js to operate and the not condenser with ihe ai¡ cond.itione¡ operating since tl¡e used door o¡ in the event óf whìn a a
fùI
malfu¡ction tluottle wlúc¡ to be extended, a dec¡ease in ¡ate of cljnlb
of
as much
æ
100 fpm can be expected. Should a malfunction occur whiciì prevents
¡et¡actio¡ when the compresso¡ is tumed off, a decrease in rate of climb of asmuch as expected.
condenser
50 doo¡ fpm can be
ISSUED: JUNE 18,1976 REPORT: W-790
9-5
PIPER AIRCRåFT CORPORÄTION
PA.2&I81, CHEROKEE ARCHER
II
TTIIS PAGE INTENTIONAILY LEFI BLANK
ISSUED: JUNE 18, r976
PIPER AIRCR.A.FT CORPORATTON
P.A.2E.I 8I, CHEROKEE
ÄRCTTER
II
sECnoN
SUPPLEh{ENTS
9
SUPPLEMENT 2
AUTOFLITE tr
AUTOPILOT INSTALLATION
SECTION
1
. GENR,4,I
rutoFlil
ìTtÏfffiÏi described,,in cory.unction the operation of the aþtane when the optional tained within this srpplement is ro be
";ã-"r.
.ris
This supplement hæ been "FA'A ha¡dbook at alr rimes when
1åe
App¡oved" as a p-e¡ma¡ent part optiäna AutoFriie'Ill,utopitåt is of this handbook inrt.n-rä:"-" and must remai¡ in
SECTTON 2.. IJÞÍITATIONS
(a)
,{utopilot uæ prohibited
(b)
Autopilot
..OFF" during above 149 KIAS.
takeoff and laniing.
SECTION 3 . EMERGENCY PROCEDURES
Disconnect switch on piJot,s control wheel.
å'iiî:lï J*
; i
oä0".",1*.
*'^ i.i
(e) ln
I approach configuration
8'
ba¡k and 10, altitude a malfu¡ction with a loss.
I
second delay in recovery
:?
ìï3 initiation ¡esulls in
SECTION 4 - NORM.A,L PROCEDURES
(a)
Engagement
( I
)
Rocke¡ Switch on instrument panel -
(
l)
Disconnect switch on reft h¡¡d side
ON.
of pilot's contor wheel - RELEASED.
(b)
Disengagement
(l)
(2)
Dep¡es Discon¡ect Switch on
Rocke¡ Switch on pilot's control wheel (or) instument janel . OFF.
(c)
Heading
(!)
(2)
(3)
Changes
Denres
Move
Move
Disconnect
Trim Knob switch, make Heading change, release Discon¡ect
.
"o^tÃi
s,ritch.
on instrument
Tum command fo¡ D¡ift-cor¡ecÉón f¡om
K¡ob on ínstument fo¡ ir""ai.g.
¡ig¡t o¡ lert ua¡ie¿ turns.
ISSUED: JUNE 18, 1976
RPORT: vB-790
9_7
SECTION 9
STJPPLEMENTS
(d)
OMM Tracker
'-'
¿it-
Crnæt to-
Comma¡d l(nob and pusir IN to engage iiÍ
ftit"
Ihob 'push IN for high sensitivity'
T¡acker'
SECTION
5. PERFORMÀNCE
No changes necessa¡Y
to
the basic for this suPPlement' performance provided by section 5 of this Pilot's operating Handbook are
REPORT: \¿8'790
9-8
ISSUED: JIJNE 18' 1976
PIPER AIRCRAFT CORPORATION
PA.28.18I, CHEROKEE
ARCHER
tr
SECTION
I
SUPPLEMENT¡
SL?PLEMENT
3
AUTOCONTROL rnB
^4,UTOpILOT INSTAILATION
SECTION
1 - GENERAL
Piper
This
Autoconrol used "as supplement cupplies
IIIB information necessary for
Autopilo,
it
i"r,nu.ã. described" in conjuncrion wi¡h rhe r¡.
.ornpi",.
tie
i.åfo.m"rion-conr¡nea iL¿¡oor..
operadon of ¡be airprane when úe optionar witrrii irLis suppr"-"nt
i.
ro uJ
This supplemen¡ has been rhis handbook ar
a'
¡imes wirh
"FAA Approved" rhe oprioni as a permanenr
rip* ar.ð*rror
pan of this handbook a¡d
I'IB
Auropilor is ins¡ared.
musl remain in
SECTION 2. LI}trTATIONS
(a)
(b)
Auropilor use prohibired above
AuropiloÌ ,,OFF, during ¡akeoff
149 and
KIAS.
lanahg.
SECTION 3
. EMERGENCY OPERATION
(a) In an emergency
(1)
(2)
Pushiig
Pu.lling the Auropilor Circu onty)
Lhe Autoconrol
r¡. rol oÑ-órr
no
L'gu
(b)
(c)
Y: nos' 28-7790001 through 28-789u151
I iniriation of recovery while operaring
45ô ba¡k a¡cl 1g0, ahitude in loss. Maximum a
(d) e initiation of recovery, during an approach
8o bank and l0,aldrude loss.
SECTION 4
.
NORM, .L PROCEDURES
PREFLIGHT
(a)
AUTOPILOT
(t)
Place
(2) the
Radìo
"oN"
set conect couprer in "HDG" Mode position to observe råat conrrol compass mode rocker engage heading on switch a¡d ¡otare
(if
insraüed) rou secrion. Ro¡are wheel describes a and roII àommand corresponding place rhe Ap ,,oN-oFF,, swirch left and right rum, t]len
D.G. and rum HDG bug ro
HDG bug left and same direction as bug. Grasp conrol whãel ana ai¡cra--ñ k¡ob teft rightl Ai¡craft coru¡ol manuatty override servo, bol¡ and righr cente¡ di¡ections.
ro and knob.
heading. Engage .,HDG,, wheel should rum
ISSUED:
Jt ,E 18,
1976
REWSED: JUNE
8, r990
REPORT: v8.790
9.9
SECTION 9
SUPPLEMENTS
PIPER AIR CR,A,FT CORPO RATI
O N
PA-2&I8I, CHEROKEE ARCIIER
tr
o)
RADrO COT.JPLER - (OPTTONAL)
(1)
Tune and identify VOR or VOT s¡a¡ion. Position Radio Coupler ro OMNI Mode. Engage
Autopilot ROLL and HDG switches. Set HDG bug to aircrafr heading and rorare O.B.S. ro cause OMNI indicator Needle to swing lefr and right slowly. Observe rha¡ conrrol wheel rotates in direction of needle Eovement.
(2)
Dsengage AP "ON-OFF' Swirctr. Res€r Radio Coupler conrrol ro HDG.
IN FLIG}IT
(a)
Trim airplane (batl cenæred).
(b)
Check air pressure vaa¡um to ascenain that ùe directional gyro and ani$de gyro are receiving sufficient air.
(c)
Roll Secdon.
(1)
To engage, center ROLL krob, push AP "ON-OFF" swirch ¡o "ON" position. To turn, rolate console ROLL knob in desired direction. (Maximum angle of barl should nor exceed
(2)
30".)
For heading mode, set directional gyro with magnetic compass. Push directional gyro HDG k¡ob in, rotrte bug to aircraft heading. Push console heading ¡ocker (HDG) switch ro "ON" position. To select a new ai¡craft heading, push D.G. heading knob
"IN"
and ro¡are, in desired direcrion of rum, ro the desired heading.
(d)
Radio Coupling
(1)
For VOR
-
VORIILS with Sråndad directional gf,ro. (Optíonaf)
Intercepts and Tracking:
Select the desired VOR course and set üe HDG bug ro the same heading. Selecr OMM mode on the coupler and HDG Mode on rhe auropilor console.
(2)
For ILS Fron¡ Course lnærceprs and Tracbng:
Tune the localizer frequency and place the HDG bug on ¡he inbound, front course heading. Select LOC-NORM mode on the coupler and HDG mode on the auropilor console.
(3)
For LOC the
Back Course Inærc€prs and Tracking:
T\¡¡e tle localizer frequency and place the HDG bug on rhe inbou¡d course heading to airport. Select LOC-REV mode with coupler and HDG mode on the autopilot console.
SECTION 5 - PERFORMANCE
No changes to the basic performance provided by Section 5 of rhis Pilot's Operating Handbook arî necessary for this supplement.
REPORT: VB-790
9-10
ISSUED: JIJNE 1& 1976
PIPER AIRCRJA,FT CORPORá.TION
PÄ.28.I8I, CUEROKE ARWER II
THIS PAGE INTENTIONALLY LEFT BLANK
ISSLJED: JIJNE 18, tg7d
TI{IS PAGE INTENTIONAILY LEFT BI-ANK
PIPER ÄIRCRATT CORPOR.A,TION
PÄ.28.I81, CHEROKEE ARC¡IER
II
SECTION
9
SUPPLEMENTS
SUPPLE}ÍENT 4
PIPER ELESIRIC PITCH TRIM
SFCTTON 1
- GENERAL
This supplement
Piper Electric described" supplies r1þya_tion necessary for the operation
Pitch T¡im is i¡stalled. The informatiån in conjunction with ttre complete handbook.
contained of the airplane when the optìonal
*ithir tlú;;";lement
is to be used
.,as
"-,a
This supplement has been handbook at a[ times when
"FAA App¡oved" the optiònar piper as a permanent
Ereitric pitch part of this handbook a¡d must ¡emain
rri-
i. i"rãù;d-
i¡
SFCTION 2. LIMITATIONS
No changes necessâry
of
the bæic limitations provided for this supplement.
by Section 2
of
this Pilot's Operating Handbook are
SECTION 3 - EJ\IERGENCY PROCEDURES
(a)
In case of malfunction, ACTIVATE disconnect su,irch locared above the ignition swiLch. ro OFF
(b)
(c)
POStt¡ ln
On.
case ofmalfunction,
Maximum altitude overpo\\¡er change the electric trim at either control q,heel.
with a 4 second delay in recovery iniriarion is 800 leet the descenI configuration. Maximum ahitude óhange second recove¡, delay is 100 feet.
in
the approach and occurs in configuration u,ith a
4
SECTTON 4
. NORìÍÄL PROCEDURES
.
trim
The elect¡ic trim system may be turned ON o¡ OFF by pitch bim may be changed when the e.lechic trim contol speed increase tition wheel o¡ by operating the does in the not event of an affect the manual trim cont¡ol electric trim trim system.
s-vstem a switch located above the ignition switch. The is turned on either by movin! the manual pitch switch on run-au'ay disconnect feature which ¡enden thesystem inoperative the pi.lot's malfunctiãn, abôve control yoke. To prevent excessiye the system-incorporates an automatic approximatily
143 KIAS. The disconnecteá
SECTION 5 - PERFORMANCE
No changes necessarlr
to
the basic performance provided by Section 5 of this for this supplement.
PiJot's Operating Handbook are
ISSUED: JUNE 18. 1976
REYISED: IIIARCH 30, ¡984
REPORT: \/B-790
9-r3
PIPER AIRCR.A.FT CORPO
RATION
PA.2&I 81, CHEROI(EE ÄRCHER U
THIS PAGEINTENTIONALLY
IEFT BLANK
ISSUED: JUNE 18, 1976
SECTION
1O
SAFETY TIPS
SECTION
1O
SAFETY TIPS
Paragraph
No.
0.1 General
.0-i OperatingTips....
TABLE OF CONTENTS
SECTION IO
OPERATIn-G TIPS
Page
No
.........
l0-l
.......
l0-l
REPOR.T: VE-790
1Gi
PIPER A¡RCRAFT CORPORATION
PÄ.28.I8I, CHEROKEE ARCHER II
SECTION
IO
OPNRATINC TIPS
SECTION IO
OPERATINC TTPS
IO.I CENERAL
This section provides operating tips of particular lalue in rhe operarion of the Cherokee Archer
ll.
.0.3
OPERATINC TIPS
(a)
Leam to trim for takeoff so that only a tö
lift
the aþlane off the ground.
very light back pressure on the control wheel is requrred
(b)
The best speed fo¡ takeoff js about 53 KIAS off the ground ât too low an ainpeed dec¡eæes the cont¡ollability of the airplani in the engine failure.
unde¡ normal conditions. Tryirg to pull tJre airpla¡e
evùt
of
(c)
Flaps may to have be lowe¡ed at airspeeds up to
I 02 KIAS. 1o reduce flap operating loads, it js desirable
tie
airylane ât a slower speed before extending the flaps. The flap slep w.ill not support weigltt
ifthe
flaps are in a¡y extended position. The flaps must be placed in the "UP" position before they will lock and support weight on tle step.
(d)
Before attempting to reset a¡y ci¡cuit breaÌer, allow a two to five minute cooling off period.
(e)
Before starti:rg are the engine, check that all radio switches, light switches and the pitot heat s*,itch in t¡le offposition so as not to create an overloaded condition when the sta¡ter is engaged.
(l)
Strobe ligJrts sholtld rtot be operating s'lten llying through ovcrcast arrd cìoucls, sincc rcflcctcc.l
lig.ltt can produce spacial disorientation. Do not operate strobe lig|ts when taxiing in the vicinity of other ai¡c¡aft.
(g)
The rudder pedals should are suspended from a torque tube which extends across the fuselage. The pilot becomefamilia¡withtheproperpositioningof lúsfeetontherudderpedalssoastoayoid interference with the torque tube when moving the rudder pedals or operating the toe brakes.
(h)
In
a¡ effo¡t to avoid accidents, pilots should obtain and study the safety related information made available in FAA publications such as regulations, advisory circulars, Aviation Nervs, AIM and safety aids.
(Ð
The shape of tlre wing fuel ta¡ks is such that in certajn maneuvers the fuel nlay move away lrom the tanÌ outl€t. nìarteuvers
lf
the outlet is uncovered, the fuel flow will be interrupted and a temporary loss
of
power may result. Pilots can prevent i¡adve¡tent. uncoveri¡g
of
the outlet
by
avoiding which could ¡esult in uncovering the outlet.
ISSUED: JUNE I8, 1976
REYISED: N'l,,\RCH 20,
1984
REPORT: \'B-790 r0-l
ECTIoN 10
PERATINC TIPS
PIPER AIRCRAFT CORPORATION
PA-28-I8I, CHEROKEE ARCHER
II
Extreme running turning takeoffs should be avoided as fuel flow intemrption may occur.
P¡olonged
.iitrri
slips or skids which result in excess
*rnãuur6 which could cauæ intem.rption may occur when tank
of
2000
ft.
of a]titude loss, or other radical o¡ uncovering of the being used is not full' fuel outlet must be avoided as fuel Oow
Ú)
Hand
sra
er, should hand starting of the engine. be
required,rocedure'Themagnetoselectorshouldbe placedtotheprobabilityof..KickBack.'.Placethe
ígnition
s
started'
EPORT: VB-790 vz
ISSUED: JUn*E 18. I976
REVISED: À'IARCH 30'
I984

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