Cherokee SIX 260 Technical specifications

FLIGHT MAilUAL
r0R
KEE SIX 260
IYUMBERS 32.7 4O()O()I THROUGH 32.7600024
OHERO
APPLICABLE TO SERIAI,
AIRPLA}IE
,^
NOTE
THIS MANUAL MUST BE KEPT IN THE AIRPLA}IE AT ALL TIMES
FAA APPROVED FY'
PIPER AIRCRAFT CORPORATION
D. O. A. NO. SO-1
VERO BEACH, FLORIDA
DATE OF APPROVAL: MAY l4,lg73
APPROVAL BASIS: CAR 3
REPORT: VB-561
MODEL: PA-32-260
WARNING
EXTREME CARE MUST BE EXERCISED TO LTMIT THE USE OF THIS MANUAL
TO APPLICABLE AIRCRAFT. THIS MANUAL REVISED AS INDICATED BELOW
oR srrBSEeuENTLy REvrsgp rs vALrD FoR usE wrrH THE AIRpLANE
IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION.
SI,]BSEQUENT REVISIONS SUPPLIED BY PIPER AIRCRAFT COPJORATION
MODEL PA.32.260
32-7 400029
AIRCRAFT SERTAL NO.
AIRPLANE FLIGHT MANUAI, REPORT
PIPER AIRCRAFT CORPORATION
APPROVAL SIGNATURE AND STAIvIP
REGISTRATION NO.
ER VB.56I REVISION
.1{. BARNHOUSE
i.-

BLANK PAGE
-
v

n
AIRPTA}IE TtrcHI ilIA]IUAt
Log of Rwisions 3-iii
Limitations . .3-l
Procedures
Supplements
3-5
3-7
3-9
^
3-i

V
BLANKPAGE

CHEROKEE SIX-260
,..-
TABTE OF GO}ITE}ITS
Log of Revisions
SECIION I
Limitations
SECTIONU
Procedurts
SEqTION M
Performance
SECTION TV
Optional Equipment
A aaa
J-1ll
3-l
3-l
3-l
3-l
3-l
A. Enehe
B. Fugl ....... r...o............o.........
C. Propeller
D. Power Instnrments
E. Airspeed Limitations and Airspeed Instrument
F.
G.
H.'
r.
J.
Mukings (Calibrated Airsieed) 3-2
MaximumWeight 3-z
C. G. Ranep 3A
Manetners 34
Placards 3-3
Bear Cabin Doc or Rear Cabin Door and Cargo
DoorRemoved . ..; 34
Swenth-Passenger Operation 34
Nose Wheel Fairing Removed 94
K.
L.
3-5
3-7
A. Electric Pitdl Trim Installation
B. AutoFlite II Installation. . .
C. Piper AutoControl III and/or AutoControl IIIB Installation
D. Piper AltMatic IIIC Installation
3-g
3-1 I
3-r4
3-15
3-19
REPORT: VB-561 PAGE 3-i
MODEL: PA-32-260
FAA APPROVED MAY 14, 1973
REVISED: NOVEMBER 4, 1974
,

CHEROKEE SIX-260
V
THIS PAGE INTENTIONALLY LEFT BLANK
v
REPORT: VB-561 PAGE 3-ii
MODEL: PA-32-260 FAA APPROVE,D MAY 14, 1973
V

CHEROKEE SIX-260
n
AIRPLANE FLIGHT MANUAL LOG OF REVISIONS
Revision Revised Pages Description and Revision Efu{ Approved
Date
1
2
a
J
4
Title
3-i
3-9
3-15,3-16,
3-17,3-18
3-i
3-4
3-9
3-12
3-r3
3 -14
3-15
3-18
3-19,3-20,
3-21, 3-22"
3-23, 3-24,
3-25, 3-26
3-3,3-4
Added PAC Approval Form.
(NOTE: AIRCRAFT DELIVERED WITH
MANUALS PRIOR TO THIS REVISION
DO NOT REQUIRE THIS REVISION.)
Added Item D. (Installation of Piper Auto-
Control IIIB) to Supplements.
Added Item D. (Installation of Piper Auto-
Control IIIB).
Added pages (AutoControl IIIB Supplement).
Under Limitations - added item L. (Nose Wheel
Fairing Removed); changed Section IV title
from Supplements to Optional Equipment;
under Optional Equipment- deleted items B.
and C.; revised remaining items; added new
item D. (Piper AltiMatic IIIC Installation).
Added item L. (Nose Wheel Fairing Removed),
remove Airplane Flight Manual Supplement
Report No. VB-637 if attached to the Air-
plane Flight Manual.
Changed Section IV title from Supplements to
Optional Equipment; revised Note; deleted
items B. and C.; revised remaining items; added
new item D. (Piper AltiMatic IIIC Installation).
Deleted item B. AutoFlite Installation.
Deleted item C. AutoControl Installation.
Revised item letter (D. to B.).
Revised item letter; revised item title; added
AutoControl III to title.
Deleted IIIB designation from items c. (1) and
(2).
Added pages (AltiM atic IIIC), remove Airplane
Flight Manual Supplement Report No . YB-667
if attached to the Airplane Flight Manual.
Deleted seventh seat reference.
D. H. Trompler
June 19, 197 4
U*l €vur\.-
Ward Evans
Nov. 4, L97 4
A *J 6.,or,,
Ward Evans
Dec. 13 , L978
,ll
FAAAPPROVED MAY 14, 1973
REVISED: DECEMBER 13, 1978 REPORT: VB-561 PAGE 3-iii
MODEL: PA-32-260
/,u
D. H. Trompler
June 4, 197 4

CHEROKEE SIX-260
Revision Revised Pages Description and Revision FAA Approved
Date
5Title Added Applicable Serial Numbers.
(NOTE: AIRCRAFT DELIVERED
WITH MANUALS PRIOR TO THIS
REVISION DO NOT REQUIRE THIS
REVTSTON.)
tJ*n
Ward Evans
March 22, 1979
AIRPLAI\E FLIGHT MANUAL LOG OF REVISIONS (cont) \-
V
REPORT: VB-561 PAGE 3-iv
MODEL: PA-32-260 FAA APPROVED MAY 14, 1973
REVISED: MARCII 22, 1979
-

CHEROKEE SIX-260
/^
SECTION I
LIMITATIONS
The following limitations must be observed in the operation of this airplane:
A. ENGINE
Lycoming 0-540-E4B5
ENGINE LIMITS
For all operations 2700 RPM, 260 HP
B. FUEL
100/130 minimum aviation grade fuel
C. PROPELLER
Hartzell Model HC-C2YK-l( )18477-2 or HC-C2YK-l( )F1F8477-2, low pitch stop
12.0" +.2",high pitch stop 32" + 2o, maximum diameter 82 inches, minimum diameter
80.5 inches.
D. POWER INSTRIJMENTS
OIL TEMPERATURE,
Green Arc (Normal Operating Range)
Red Line (Maximum)
OIL PRESSI]RE,
$: i,'"li:Ji.Tfi il,3ff ;ili - R an g e )
Red Line (Minimum)
Red Line (Maximum)
FUEL PRE tiy,Hrm al operatin g Range)
Red Line (Minimum)
Red Line (Maximum)
TACHOME,TER
Green Arc (Normal Operating Range)
Red Line (Maximum Continuous Power)
REPORT: VB-561 PAGE 3-1
MODEL: PA-32-260
7 5"F to 245 "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
500 to 2100 RPM
27OO RPM
EAA APPROVED MAY 14, 1973

CHEROKEE SIX-260
E. AIRSPEED LIMITATIONS AND AIRSPEED INSTRUMENT MARKINGS (CalibTated
Airspeed)
NE,VE,R EXCEE,D
MAXIMUM STRUCTIJRAL CRT]I SE
MANEIJVERING
FLAPS EXTENDED
MAXIMUM POSITIVE LOAD FACTOR
MAXIMIJM NE,GATIVE, LOAD FACTOR
AIRSPEED NSTRTJMENT MARKINGS
Red Radial Line (Never Exceed)
Yellow Arc (Caution Range)
(Smooth Air Only)
Green Arc (Normal Operating Range)
White Arc (Flap Down Range)
F. MAXIMI]M WEIGHT
212 MPH
168 MPH
149 MPH
125 MPH
3.8
No inverted maneuvers approved
212 MPH (184 KTS)
168 MPH to 21 2 MPH
(146 KTS to 184 KTS)
7l MPH to 168 MPH
(62 KTS to 146 KTS)
63 MPH to 125 MPH
(55 KTS to 109 KTS)
34OO LBS
wing leading edge at the intersection of the
Rearward Limit
(In. Aft of Datum)
95.5
96.2
96.2
96.2
G. C. G. RANGE
The datum used is
straight and tapered
Weight
(Pounds)
3400
3300
2900
2400
7 8.4 inches ahead of the
section.
Forward Limit
(In. Aft of Datum)
9t.4
89.0
80.0
7 6.0
V
..v
Straight line variation between points given.
NOTE
It is the responsibility of the airplane owner and the pilot to
insure that the airplane is properly loaded. See Weight and
Balance Section for proper loading instructions.
H. MANEUVERS
No acrobatic maneuvers including spins approved.
REPORT: VB-561 PAGE3-2
MODEL: PA-32-260 EAA APPROVED MAY 14, 1973 -

CHEROKEE SIX-260
n
n
I. PLACARDS
In full view of the pilot:
..THIS AIRPLANE MUST BE OPERATED AS A NORMAL
CATEGORY AIRPLANE IN COMPLIANCE WITH THE
OPERATING LIMITATIONS STATED IN THE FORM OF
PLACARDS, MARKINGS AND MANUALS. NO ACROBATIC
MANEUVERS, INCLUDING SPINS, APPROVED."
..THIS AIRCRAFT APPROVED FOR NIGHT IFR NON-ICING
FLIGHT WHEN EQUIPPED IN ACCORDANCE WITH FAR 91
OR FAR I35."
On the instrument panel in full view of the pilot:
.ROUGH AIR OR MANEUVERING SPEED 149 MPH."
On the instrument panel in full view of the pilot:
..DEMONSTRAIED CROSSWIND COMPONENT 20 MPH."
In full view of the pilot: (For operation with the rear door removed)
..FOR FLIGHT WITH THE DOOR REMOVED, SEE THE
LIMITATIONS AND PROCEDURES SECTIONS OF THE
AIRPLANE FLIGHT MANUAL."
On the instrument panel in full view of the pilot when the AutoFlite is installed:
..FOR HEADING CHANGES: PRESS DISENGAGE SWITCH
ON CONTROL WHEEL. CHANGE HEADING. RELEASE
DISENGAGE SWITCH."
On the fuel selector valve cover:
..ALL WEIGHT IN EXCESS OF 3I12 POUNDS MUST BE
FUEL WEIGHT ONLY. FILL TIP TANKS FIRST. USE MAIN
TANKS FIRST."
On the instrument panel in full view of the pilot when the AutoFlite II is installed:
..TURN AUTOFLITE ON. ADJUST TRIM KNOB FOR
MINIMUM HEADING CHANGE. FOR HEADING CHANGE,
PRESS DISENGAGE SWITCH ON CONTROL WHEEL,
CHANGE HEADING, RELEASE SWITCH. ROTATE TURN
KNOB FOR TURN COMMANDS. PUSH TURN KNOB IN TO
ENGAGE TRACKER. PUSH TRIM KNOB IN FOR HI
SENSITIVITY. LIMITATIONS AUTOFLITE OFF FOR
TAKEOFF AND LANDING."
EAA APPROVED MAY 14, 1973
REVISED: DECEMBER 13, 1978 REPORT: VB-561 PAGE 3-3
MODEL: PA-32-260
,^

CHEROKEE SIX.26O
On the instrument panel in full view of the pilot when the supplementary white strobe
lights are installed:
..WARNING - TURN OFF STROBE LIGHTS WHEN TAXIING
IN VICINITY OF OTHER AIRCRAFT, OR DURING FLIGHT
THROUGH CLOUD, FOG OR HAZE,."
J. REAR CABIN DOOR OR REAR CABIN DOOR AND CARGO DOOR REMOVED
The following limitations must be observed in the operation of this airplane with the rear
cabin door or rear cabin door and cargo door removed:
1. The airplane may be flown with the rear cabin door or rear cabin door and cargo
door removed. Flight with the front door removed is not approved.
2. Maximum speed - 165 mph.
3. No smoking.
4. All loose articles must be tied down and stowed.
5. Jumper's static lines must be kept free of pilot's controls and control surfaces.
6. Operation approved VFR flight conditions only.
K. LOADING LIMITAIIONS
The following limitations must be observed in the operation of this airplane:
l. Fill tip tanks first; use main tanks first.
2. This airplane must not be operated at gross weights in excess of 3ll2 pounds
unless the weight over 3l 12 pounds is fuel weight only.
3. Remove fuel from the main tanks first when required for proper weight and
balance.
L. NOSE WHEEL FAIRING REMOVED
When the nose wheel fairing is removed, two nose wheel centering springs (part number
67168) must be installed.
v
-
REPORT: VB-561 PAGE 3-4
MODEL: PA-32-260 EAA APPROVED MAY t4,tg73
REVISED: DECEMBER 13, 1978
-

CHEROKEE SIX.26O
,^
SECTION II
PROCEDURES
The stall warning system is inoperative with the master switch off.
Electric fuel pump must be on for both landing and takeoff.
Except as noted above, all operating procedures for this airplane are normal.
When operating with the rear cabin door removed, it is recommended that all
occupants wear parachutes.
Fuel System Preflight Procedure:
The fuel system should be drained daily prior to first flight and after refueling to
avoid the accumulation of water or sediment. Each fuel tank is equipped with an
individual quick drain located at the lower inboard rear corner of the tank. The fuel
strainer and a system quick drain valve are located in the fuselage at the lowest point
of the fuel system. It is important that the fuel system be drained in the following
manner:
Drain each tank through its individual quick drain located at the lower
inboard rear corner of the tank, making sure that enough fuel has been
drained to insure that all water and sediment is removed.
Place a container under the fuel sump drain outlet, which is located under
the fuselage.
Drain the fuel strainer by pressing down on the lever located on the right
hand side of the cabin below the forward edge of the rear seat. The fuel
selector must be positioned in the following sequence: off position, left tip,
left main, right main, and right tip while draining the strainer to insure that
the fuel lines between each tank outlet and fuel strainer are drained as well
as the strainer. When the fuel tanks are full, it will take approximately 11
seconds to drain all the fuel in one of the lines between a tip tank and the
fuel strainer and approximately six seconds to drain all the fuel in one of
the lines from a main tank to the fuel strainer. When the fuel tanks are less
than full, it will take a few seconds longer.
Examine the contents of the container placed under the fuel sump drain
outlet for water and sediment and dispose of the contents.
REPORT: VB-561 PAGE 3-5
MODEL: PA-32-260
1.
2.
a
J.
4.
5.
a.
b.
c.
d.
n
EAA APPROVED MAY L4, 1973

CHEROKEE SIX.26O
v
CAUTION
When draining any amount of fuel, care should be taken to insure
that no ftehazard exists before starting engine.
After using the under-seat quick drain, it should be checked from outside to
make sure it has closed completely and is not leaking.
REPORT: VB-561 PAGE 3-6
MODEL: PA-32-260 EAA APPROVED MAY 14,,tg73
v

CHEROKEE SIX-260
n
SECTION III
PERFORMANCE
All performance is given for a weight of 3400 pounds.
Loss of altitude during stalls can be as great as 350 ft depending on configuration and
power.
Stall speed, in mph (Calibrated Airspeed):
Flaps Up - 7l
Flaps Down - 63
Flap deflection versus handle position is:
1st notch - l0 degrees
2nd notch - 25 degrees
3rd notch - 40 degrees
REPORT: VB-561 PAGE3-7
MODEL: PA-32-260
EAA APPROVED MAY 14, 1973

CHEROKEE SIX.26O v
THIS PAGE INTENTIONALLY LEFT BLANK
REPORT: YB-561 PAGE 3-8
MODEL: PA-32-260 EAA APPROVED MAY 14, 1973

CHEROKEE SIX-260
1
a\
'^
SECTION IV
OPTIONAL EQUIPMENT
NOTE
THE INFORMATION CONTAINED IN THIS SECTION
APPLIE,S WHEN THE RELATE,D EQIJIPMENT IS INSTALLED
IN THE AIRCRAFT.
A. Electric Pitch Trim Installation
B. AutoFlite II Installation
C. Piper AutoControl III and/or AutoControl IIIB Installation
D. Piper AltiMatic IIIC Installation
EAA APPROVED MAY 14, 1973
REVISED: NOVEMBER 4, 1974 REPORT: VB-561 PAGE 3-9
MODEL: PA-32-260

CHEROKEE SIX.26O
THIS PAGE INTENTIONALLY LEFT BLAI{K
REPORT: YB-561 PAGE 3-10
MODEL: PA-32-260 EAA APPROVED MAY 14, 1973
--
.-

A
CHEROKEE SIX-260
A. ELECTRIC PITCH TRIM INSTALLATION
The following emergency information applies in case of electric pitch trim
malfunction:
l. In case of malfunction, disengage electric pitch trim by operating push button
trim switch on instrument panel.
2. In emergency, electric pitch trim may be overpowered using manual pitch trim.
3. In cruise configuration, malfunction results in 10o pitch change and 50 ft
altitude variation.
REPORT: VB-561 PAGE 3-11
MODEL: PA-32-260
EAA APPROVED MAY 14, 1973
n'

CHEROKEE SIX-260
THIS PAGE INTENTIONALLY LEFT BLANK
REPORT: VB-561 PAGE 3-12
MODEL PA-32-260 FAA APPROVED MAY 14, 1973
REVISED: NOVEMBER 4, 1974
-
-
-