Piper Cherokee Arrow II PA-28R-200 1973 User manual

I
WARNING
I
EXTREME CARE MUST BE EXERCISED TO LIMIT THE USE OF THIS MANUAL.
TO APPLICABLE AIRCRAFT THIS MANUAL REVISED AS lNDICATED BELOW
OR StJBSEQUENTLY REVISED IS VALID FOR USE WITH THE AIRPLANE
IDENTIFIED BELOW WHEN APPROVED BY PIPER AIRCRAFT CORPORATION.
SUBSEQUENT REVISIONS SUPPL.IED BY PIPER AIRCRAFT CORPORATION
MUST BE PROPERLY INSERTED.
MODEL PA-28R-200
AIRCRAFT SERIAL NO. 28R-7535277 REGISTRATION NO. N1lRB
PR750128
PILOT'S OPERATING MANUAL., PART NIJMBER 761 578 REVISION 1
- 28 - 75
PIPER AIRCRAFT CORPORATION
APPROVAL.SIGNATURE AND STAMP
G&#&4%
T.W. Reed, ~rw
Assurance that the airplane is in an airworthy condition is the responsibility of the owner.
The pilot in command is responsible for determining that the airplane is safe for flight. The pilot
is also responsible for remaining within the operating limitations outlined by the Airplane Flight
.g
Manual, instrument markings, and placards
This Pilot's Operating Manual is not designed as a substitute for adequate and competent
flight instruction, knowledge of the current airworthiness directives, applicable federal air
regulations, or advisory circulars. It is not intended to be a guide for basic flight instruction or a
training manual for tr
an
sition from single to multiengine flying.
It an inconsistency of information exists between the Pilot's Operating Manual and the
Airplane Flight Manual approved by the FAA, the Airplane Flight Manual shall be the
authority.
A complete or partial replacement of this manual, Part No.
761 578, may be obtained only from Piper Customer Services.
Published by
PUBL.ICATIONSDEPARTMENT
Piper Aircraft Corporation
761 578
Issued: July 1973

APPLICABILITY
This manual is applicable to Piper Model PA - 28R - 200 aircraft having serial numbers commencing with
28R
- 7435001 through 28R - 7635545. Contact Piper Customer Services for specific information on the
application of this manual.
WARNING
INSPECTION, MAINTENANCE
AND PARTS REQUIlU3MENTS FOR ALL NON - PIPER
APPROVEDSTC INSTALLATIONS
ARE NWINCLUDED IN THISHANDBOOK. WHEN
A NON - PIPER APPROVED STC INSTALLATION IS INCORPORATED ON THE
AIRPLANE, THOSE PORTIONS OF THE AIRPLANE AFFECTED BY THE
INSTALLATION MUST BE INSPECTED IN ACCORDANCE WITH THE INSPECTION
PROGRAM PUBLISRED
BY THE OWNER OF THESTC. SINCE NON - PIPER APPROVED
STC INSTALLATIONS MAY CHANGE SYSTEMS INTERFACE, OPERATING
CHARACTERISTICS AND COMPONENT LOADS OR STRESSES ON ADJACENT
STRUCTlJRES,PIPER PROVIDED INSPECTION CRITERIA MAY NOT BE VALID FOR
AIRPLANES
WITH NON - PIPER APPROVED STC INSTALLATIONS.
REVISIONS
The information compiled in the Pilot's Operating Manual will be kept current by revisions
distributed to the airplane owners.
Revision material will consist of information necessary to update the text of the present manual
and/or to add information to cover added airplane equipment.
L. Revisions
Revisions will be distributed whenever necessary as complete page replacements oradditions and shall
be inserted into the manual in accordance with the instructions given below:
1. Revision pages will replace only pages with the same page number.
2. Insert all additional pages in proper numerical order within each section.
3. Page numbers followed by a small letter shall be inserted in direct sequence with the same
common numbered page.
II. Identification of Revised Material
Revised text and illustrations shall be indicated by a black vertical line along the left hand margin of
the page, opposite revised, added or deleted material.
A line opposite the page number or section title and
printing date, will indicate that the text or illustration was unchanged but material was relocated to a
different page or that an entire page was added.
Black lines will indicate only current revisions with changes and additions to ordeletions of existing
text and illustrations. Changes in capitalization, spelling, punctuation or the physical location of material
on a page will not be identified by symbols.
III. Original Pages Issued
The original pages issued for this manual prior to revision are given below:
1
- 1 through 1 - 3, 2 - 1 through 2 - 24, 3 - 1 through 3 - 10, 4 - 1 through 4-8, 5 - 1 through 5 - 32, 7 - 1 through
7
- 10, 8 - 1 through 8-2.9-1 through 9 - 10, 10 - 1 through 10-15.
REVISED: FEBRUARY 7,2005

PILOT'S OPERATING MANUAL LOGOFREVISIONS
Current Revisions to the PA
- 28R - 200 Arrow I1 Pilot's Operating Manual, 761 578, issued July
Description
1 Date I
Rev. 1 - 761 578
I wJB I
Added Rev. 1 to Report:VB - 549. Oct. 29,1973
(PR731029)
Rev.
2 - 761 578
(PR740325)
Rev. 3 - 761 578
(PR740618)
2 - 20
A FJM
4 - 8
Added PAC Approval Form.
Added Applicability and Item
Ill. Original
Pages Issued.
Added Rev.
1 to Report VB-560.
Added Rev. 2 toReport VB - 549.
(NOTE:
AIRCRAFT DELIVERED WITH
MANUALS PRIOR TO THIS REVISION
DO NOT REQUIRE
THIS REVISION.)
Added MixtureControl Lock and Footnote.
Added MixtureControl Lock to Throttle
Quadrant Illustration.
Added AnnuncintorPanel and Footnote;
added Landing
Gear Light Dimming
Warning.
Revised AlternatorandStarterSchematic.
Added Alternatorand StarterSchematic
for 1975Models.
Added IntentionallyLeft Blank Page.
Added Annunciator Panel and Footnoteto
VacuumSystemDescription.
Added AnnunciatorPanel and Footnoteto
InstrumentPanel Description.
Added Annunciator Panel and Mixture
ControlLock to InstnunentPanel Illus
-
tration.
Added Rea~SeatRemoval Instiuctions.
Added Revision 2 to Report: VB - 560.
Revised Alternator FailureEmergency
March 25,1974 1
June18.1974
Procedures.
I I
Added Revision 3 to Report: VB - 549.
Revised Operating InstructionsIndex;
added Airspeed Data.
1 7-4 1
Revised Aii Conditioner Ground Check;
added AnnunciatorPanel
Check and Foot -
7 - 5 note; relocated info.
Added info from Page 7-4relocated
Cruisinginfo.

PI1,OT'S OPE,RATING MANUAI. LOG OF REVISIONS (cont)
1
Datc
- - -
.Jan 28. 1975
Description
Added Cruising info;added Mixture
Control Lock and Footnote;relocated
Approach and L.andinginfb.
Added Approach and Landing infb;added
Mixture Control Lock and Footnote;
relocated Moorings and Weight and Balance
infb.
Added Airspeed Data;added Moorings, and
Weight and Balance info; relocated ELT
info.
Added infb from Page 7
- 8; relocated Air
Conditioning info.
Added Air Conditioning info;relocated
info.
Added page; added relocated info.
Added Annunciator Panel to item
I I ;
moved Item 13 toPage 8-2.
Added Item 13 from Page 8-1.
Revised Performance Charts Index.
Revised Takeoff Chart.
Revised Climb Chart
Revised Airspeed Chart.
Revised Range Chart.
Revised Glide Chart.
Revised L.andingChart.
Added gear warning info.
Revised Stall Warning info.
Revision
Rev
3 (cont)
Rcv 4 - 761 578
(PR750178)
Revised
Pages
7
- 6
7
- 7
7
- 8
7
- 9
7
- 10
7
- 1 1
8 - 1
8 - 2
9
- i
9
- 2
9-.3
9 - 4
9
- 5
9
- 8
9
- 9
2
- 6
2-2 1

ARROW I1
THIS PAGE. INTENTIONALLY LEFT BLANK

ARROW 11
PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)
Revised Description
10
- 9 Added info. from page 10-8.
10-11 Revised Service Bulletin info.
...
U1
1 - 2
2
- 21
AFM
W/B
9 - i
10
- 7
2
- 5
2
- 6
2
- 16
AFM
4
- 2
Added includingserial number.
Revised fuel and oil info.
Revised para.
Added Rev. 6 toReport: VB
- 560.
Added Rev. 9 to~eport:VB
- 549.
Added Warning.
Added info., and fuel gradechart,
moved info. to page 10
- 8.
Relocated info. from pg. 10-7.moved
info. to page
10 - 9.
Relocated info. from page 10 - 8.
Revised para.
Revised preventivemaintenancepara.,
relocatedinfo. from page 10
- 13.
Moved info. topage 10
- 12.
Revised LandingGear.
Relocated Warning
Revised ThrottleQuadrant and
Consolefigures.
Revised Schematic.
Revised para. Added info.
Revised InstrumentPanelfig.
Added Rev.
7 to Report: VB - 560.
Revised Engine PowerLoss During
Takeoff para.
Revised EnginePowerLoss During
Takeoff.
Revised Power
Off Landing. Gear
Down Landing, and Gear Up Landing paras.
Moved info. from page
4-5.
Revised Emergency GearExtension para.
Moved info. to page 4-4.
Revised Note.
Revised footnote.
Revised item 12.
Revised Note.
Added Note.
Added note reference.
Date
--
Feb. 29,1984
Jan. 31,1987

PII,OT9SOPERATING MANUAL LOG OF REVISIONS (cont)
Revised
Pages
Revision
Rev. 12
- 761 578
(PR900730)
Rev. 13 - 761 - 578
(PR050207)
Rev..14 - 761 - 578
(PRO5 1 010)
Description
-
--"
Revised Oil info. Moved Dimensionsand
LandingGear to page 1-4.
Added page. Relocated Dimensions and
Landing Gearfrom page 1
- 2.
Revised Table of Contents.
Revised Oil Requirements.Moved info..
to page 10
- 8.
Relocated info..from page 10
- 7. Moved
Tire Inflation and Battery Sevice info. to
page 10
- 9.
Relocated Tire inflation and Battery Sevice
info. from page 10-8.
Revised Facts You Should Know.
Revised Preventive Maintenance.
Revised Required Serviceand
inspection
Periods.
Added Warning.
Added Rev.
8 to Report: VB - 560.
Revised Emergency Landing GearExtension.
Revised Table of Contents.
Added Warnings and moved info. to page
10-2.
Moved info.from page 10 - 1.
Revised Required Service And Inspection
Periods.
Added Rev. 9 to Report: VB
- 560
'Q=M -1 ....u---..p

TABLE OF CONTENTS
GENERAL SPEClFlCATlONS
DESCRIPTION - AIRPLANE AND SYSTEMS
AIRPLANE FUGR (TUAL F.A.W. APPROVED
EMERGENCY PROCEDURES F.A.A. APPROVED
EMERGENCY PROCEDURES
WEIGHT AND BALANCE
LOADING INSTRUCTIONS
OPERATING INSTRUCTlONS
OPERATING TIPS
PERFORMANCE CHARTS
HANDLING AND SIEWWCING

GENERAL SPECIFlCATlONS
Performance ............................................ 1 - 1
Weights
................................................ 1 - 2
Power Plant ............................................. 1 - 2
Fuel and Oil ............................................... 1 - 2
Baggage
............................................... 1 - 2
Dimensions
............................................... 1 - 2
.............................................
Landing Gear 1 - 2

SPECIFICATIONS
PERFORMANCE
Published figures are for standard airplanes flown at gross weight under standard
conditions at sea level, unless otherwise stated. Performance for a specific airplane may vary
from published figures depending upon the equipment installed, the condition of the engine,
airplane and equipment, atmospheric conditions and piloting technique. Each performance
figure below is subject to the same conditions as on the corresponding performance chart from
which it is taken in the Performance Charts Section.
Takeoff Run (ft) 1025
Takeoff Run (Short field effort, 25' flaps) (ft) 770
Takeoff Distance Over 504Obstacle
(ft)
1800
Takeoff Distance Over50 - ft Obstacle (Short field effort. 25' flaps) (ft) 1600
Best Rate of Climb (mph) 95 (100*)
Rate of Climb(gear retracted) (ft permin) 9M)
Best Angle
of Climb (mph) 85 (96*)
ServiceCeiling (ft) 15,000
AbsoluteCeiling (ft) 17,000
Max Speed (mph) 175
Optimum CmisingSpeed (75% power, optimum altitude, 66M) ft) (mph) 165
CmiseSpeed at best powermixture(rnph)
65% power. 9,750
ft 159
55% power,
13.W R 150
Range at best power mixture(mi)**
75% power, 6600 ft 665
65% power,9750 ft 715
55% power,
13.W ft 765
CmiseSpeed at best economy mixture (rnph)
75% power. 6600
ft 156
65% power,9700
A 148
55% power, 13,100
A 141
Range
at best economy mixture(mi)**
75% power, 6600
A 740
65% power. 9700 ft 785
55% power, 13,100 ft 850
Stalling
Speed (flaps and geardown) (CAS) (mph)
64
Stalling Speed (flaps and gear up) (CAS) (mph) 7
1
Landing Roll (flaps down) (ft) 780
Landing
Roll Over 5Qft Obstacle(ft) 1380
*Gear reuacted
**Noreserve
GENERAL SPECWICATIQNS
ISSUED: JULY 13,1973

ARROW I1
Gmss Weight Obs)
StandardEmpty Weight Obs)
Maximum Useful Load (obs)
POWER PLANT
Engine (Lycoming)
Propeller
Rated Horsepower
Ra*edSpeed (rpm)
Bore (in)
Stmke(in.)
Displacement(cu. in)
CompressionRatio
Dry Weight (lbs)
FUEL (AVGAS ONLY)
CJsable Fuel Capacity (U.S. gal.)
Fuel, Aviation Grade (min octane)
OIL
Oil Capacity (qu) 8
Oil Specification Refer
to latest issueof
LycomingInstructionNo.
1014.
Oil V~scosityper Average Ambient Temp. forStarting
MIL-L-6082B MIL-L-2285 1
Mineral Ashless Dispersant
SAEGrade SAEGrades
All Tempermres - 15W-50 or 20W-50
Above 80'F 60 60
Above WF 50 40
or 50
30'F to 901: 40 40
0'F m 70'F 30 30.40
or 20W-QO
O'F m 903:
20W-50 20W-50 or 15W-50
Below 1O'F
20 30 or 20W-30
I
When operatingtemperatures overlap indicated ranges, use the lighter grade oil.
BAGGAGE
Maximum Baggage Obs)
BaggageSpace (cu ft)
Baggage LXmr Size(in)
I
GENERALSPECIFICATIONS
REVISED:
JULY 30,1990

ARROW LI
GENERAL SPECIFICATIONS
ISSUED: JULY 13, I973

ARROW n
DIMENSIONS
Wig Span (ft)
Wmg Area (sq ft)
Wmg Loading Obs per sq ft)
Length (ft)
Height (ft)
Power Loading Obs per hp)
LANDING
GEAR
Wheel Base (ft)
Wheel Tread (ft)
Tire Pressure @si) Nose
Main
lire Size Nose (four - ply rating)
Main (four-ply rating)
GENERAL SPECIFICATIONS
ISSUED: JULY 30,1990

DESCRIPTION
AIRPLANE AND SYSTEMS
...............................................
The Airplane 2 - 1
...............................................
Airframe 2 - 1
........................................
Engine and Propeller 2 - 2
.....
Landing Gear ...........................................
2 - 3
.............................................
Flight Controls 2 - 8
................................................
Fuel System 2 - 9
..........................................
Electrical System 2 - 11
..........................................
Vacu~~mSystem 2 - 14
..............................................
InstmmentPanel 2 - 15
.............................................
Pitot - Static System 2 - 15
..........................
Heating, Ventilating and Defrosting System 2
- 18
............................................
Csbin Features 2 - 20
.................................................
Baggage Area 2 - 21
................................................
Stall Warning 2 - 21
......................................................
Finish 2 - 21
...............................................
Air Conditioning 2 - 21
............................................
Piper External Power 2 - 24

ARROW I1
IIESCRIPTION
AIRPLANE. AND SYSTEMS
THE AIRPLANE
The Cherokee Arrow 11 is a single - engine, retractable landing gear, all metal aircraft
Increased fuselage lengtli has cnlisnced tlie comfort in the rear seats A large cabin door allows
composed entry and exit of tlie spacious interior Four individual seats allow individual comfort
for extended cross
- country flights Sound proofing has been built into the aircraft to reduce
fatigue and permit restful conversation. Simplicity of operation was designed into the aircraft to
allow the aircraft tooperate in
VFR or IFR conditions with unhurried en route planning
AIRFRAME.
Alumintlm alloy construction lias been used throughoi~tfor the primary structure except
fbr the steel tube engine mount, steel landing gear struts and isolated areas. Fiberglass and
thermoplastic are used extensively for wing tip, engine cowling and non-stntcture components.
Tlie airframe lias been designed to a positive limit load factor of
3.8.
Tlie fuselage is a co~iventionalsemi-monocoque stnicture. External stringerson the bottoni
of tlie fuselage extend the length of the cabin area, and are used to maximize cabin room. On
tlie right side of tlie aircraft are a large cabin door and a large baggage compartment door.
Maintenance has been redticed toa minimum with advanced fnselage design.
Tlie wing is of co~ivcntionaldesign incorporating a laminar flow NACA 65,
- 415 airfoil
section. This allows fbr locating the main spar
40% aft of the leading edge, an arrangement
whicli benefits the structtirc in two ways.
1
It provides unobstructed cabin space fbr tlie rear passengers.
?
It allows for a lighter wing strttcture to improve the useful load of the aircraft.
The wing also incorporates a rear spar ;tnd front stub spar. The main spar carries the
bending loads and the rear ;tnd stub spars cany torsional loads. The main sparsare bolted into a
spat carry through at both sides of tlie filselage. The rear and stub spars are bolted to
attachments at each side of tlie fi~selage.
The aileroiis are of modern metal construction i~icorporating a balance weight on the
outboard elid of each aileron, and are controlled by a right or left rotation of tlie control wheel.
Tlie flaps are also of metal constr~ictionWlicn tlit! llaps arc
in tlic retrautcd position, tlie
right flap acts as a step. The flap control is 1oi:ated between the front se:~ts.
The empennage consists of a vertical st;tbilizcr. ;I rudder ;~nd ;I lioriro~itnlst;~hilator.
Directional and pitch trim are providcd will1 tlie rudder i111lJ st;lhil:~Iortrill1 i;10sr~'s~)~ctiv~Iy.
Tlie trim tab on tlie stabilator also acts as an anti - servo control TIICclilpc!inag<s<:o~istr~~ctio~iis
of a modern lightweight design.
AIRPLANE AND SYSTEMS
ISSIJED: JULY
13,1973

ENGINE AND PROPELLER
'I lrc ('licroli'c Arrow II int:orlinr:rtcs ;I L.ycoriiing 10-100-('1(' tour - cylinder, direct drive.
iiclri?ti~it:~llvolilioscd fuel injected ellgine r;~tctf :lt 200 liorse~iowcr :it ,2700 RPM It is furnislied
with ;I st;irt~*r,(10 ompcrc 14 - volt :~lternator.slricl(icd ignition. vacuurii pt11ii1) drive. I'klel pump,
jrrcilh!ller govcrnor arid :I dry alltoniotivc type iliduction air iiltcr i\ rct:ommcndcd overhat11
period of 1400 Iio\lrs is based or1 Lyt:orning servicc experience Operation hcyond the
rcc:omrnendsd timc is the decision of the olierator Sincc Lycoming from timc to time rcvises
tlic rcconi~iic~idedoverhaul period, thc owner sliotlld clicck tlic latest L.ycorning Service
lirstr~~ctionat his Piper dealer for the latest recommended overlisl~lperiod and for any
ailtlitional infomlation,
The aircraft is equipped with a Hartzell constant speed, controllable pitch propeller. The
propeller controlis located on the power quadrant between the throttle and mixture controls
A
mixture control lock* is provided to prevent activation of the mixture control instead of the
pitch control,
Tl~cexl~atlstsysteni is a crossover tylrc. wliicli rrduccs hack trrrssure and improves
~ri~It is coristrtrctcd c~itirelyof st;linless steel :,rid is oc111ipli1.d with dilnl muiflcrs
C;~hinIie;~t:111dwi~idsliicltldel-rostingarc provided by :I liratcr sliroud around the mirfller
4n oil cooler is located 011 the forward 1owt:r riglit side oftlie tiruwall, with the air inlet for
tllc coolcr loc:~tcdon the riglit side of tlie bottom cowling A winterirt~tioliplate is provided to
rcstrict ;iir (luringwinter operation (SceWinterization in Handling and Servicing )
Tlie i~idirctionsystem incorporates a Bendix RSA-SAD1 type ftrel injector. The injector is
b:~sedon the principle of diff rential pressure, which balances air pressure against fuel pressure.
Tlie regirlated fuel pressure establislied by the servo vslv'e when applied across a firel control
(jetting system) makes tlie fuel flow proportional to airflow. F'~relpressure regulation by tlie
SCNO v;rIvt: causes a minimal drop in fuel prcsstrre throlrgllout the metering system. Metering
pressure is riiaintained above most vapor forming coriditions while file1 inlet pressure is low
c~io~~glito allow use of a diapliragni pump. The servo system feature also cliecks vapor lock arid
associated starting problems
The servo regrrlation meters fuel flow proportionally with airflow and maintains the
rniuture as manitally set for all engine speeds The fuel flow divider receives metered fuel and
drstributes ftrel to each cylinder fuel nozzle
The fuel flow portion of the manifold fuel flow gauge is connected to tlie flow divider and
~nonitorsfuel pressure This instrument converts fuel pressure to an indication of fuel flow in
g:rllons per hour and percentage of rated liorsepower
The alternate air source of the induction system contains a door that functions
automatic:~lly or manually If the primary soirrce is obstructed, tlie door will open
n~rtomatic:~lly It may be opened manually by moving the selector on the right side of the
cliradrant Tlie primary source sliould always be used for take - off.
Tlie pilot sliocrld rend and follow the procedures reconimended in the Lycoming Operator's
M:~iitlollor this engine, it1 order to obtain maximum engine efficiency and time between engine
ovcr1i:r~rIs
I *Serial nos '7535001 and up
AIRPLANE AND SYSTEMS
REVISED:
JUNE 18,1974

ARROW 11
LANDING GEAR
The Cherokee Arrow 11 is equipped with a retractable tricycle landing gear, wl~icliis
liydraulically actuated by an electrically powercd reversible p~imp.TIlc pump is controlled by a
selector switch on the instn~mentparlel to tlie left
01' the control quadrant. Tllc landing gear is
retracted or extended in about seven seconds
Also incorporated in tile system is a pressure sensing device whicll lowets tllc gear
regardless of gear sclector position, depending upon airspeed and engine power (propeller
slipstream). Gear extension is designed to occur, even if the selector is in tlie up position, at
i~irspeedsbelow approximately 105 MPH witli power off The extension speeds will vary from
;~ppraximately85 MPH to approximately 105 MPll depending on power settings and altitude
Tlic device irlso prevents the gear from retracting at airspeeds below approximately 85 MPH
with 1~111 though the selector switch may be in the up position.Tliis speed increases with
rcduccd power aidlor increased altitude. Manual override of
tile dcvicc is provided by an
crnargericy gear lever located between the front seats to tlle left of the flap haidle. The sensing
device operation is controlled by differential air pressure across a flexible diaphragm whicli is
mechanically linked to a Ilydraulic valve aid an electrical switch wliicll actuates tlie pump
motor A liigli pressure aid static air sourcc for actuating the diapluagln is provided in a mast
mounted on thc left side of the fuselage above the wing. Any obstruction ol tile lioles in this
mast will cause the gear to kxtend. An optional heated mast is available to alleviate obstructio~i
in icing conditions. The optional heated mast is'turned on whenever tlie "PITOT HEAT " is
turned on.
I
WARNING
Avoid ejecting objects out of the pilot storm window whicli
could possibly enter or obst~.uctthe lioles in the mast.
The emergency gcar lever, used lor emergency extension of tlie gear, manually releascs
i~ydraulicpressure to permit the gear to free-fall with spring assistance on the nose gear. Tlie
~Ievermust he held in the downward position for emergency extension. Tlus same lever, wlien
l~eldui the raised position, can be used to override the system, aid gear position
is tlien
controlled by tlie selector switcll regardless of airspeedlpower combinations. The emergency
gear lever is provided witli a latclling device which may be used to lock the override lever in the
LI~ position. The latcli is located on the left side panel of the console below tlie level of tile
m;~riualoverride lever. To lock the override lever in the up position. raise the override lever to
tlie fuU
LIP positioli and push in tile latcli A yellow warning light located below the gear selector
switcll flashes to warn the pilot that the ai~toniaticgear lowering systeln is disabled The latch is
spring loaded to the off position to aid disengagement.Todisengage the latch raise the override
lever and release. The lever will return to its normal position and the yellow flashing ligllt will
cxtinguisl~The lever must also be latched in the raised (up) position wllen gear - up stalls are
practiced.
Gear down and locked positions arc indicated by three green liglits located below the
selector, and a yellow light for in - transit positions is located at the top of the panel. An all lights
out condition indicates tile gear is up. The landing gear should not be retracted above a speed of
125 MPH and sho~lldnot be extended above a speed of 150 MPH.
AIRPLANE AND SYSTEMS
REVISED: DECEMBER 8,1975

ARROW 11
MIXTURECONTROL LOCK
/+ -
lScrisl nor. 7536001 nnd up)
/
Throttle Quadrant
I!
OVERRIDE LATCH
Console
AIRPLANE AND SYSTEMS
REVISED: JUNE
18. 1974

ARROW 11
HVUAULK PUIB RtStRrOa
FILTER HWIPRESSURE CONTROL
LOW PRESSURE COWlROL,
EEU UP CMCK VALVE
6fAR WWW SWUMER
AUTOUATK 6UR DOWN L
EYERGEWCY FREE FAU
r
ROY PRESSURE HEAD OU RSEUEE SIDE
I I NOSE 6EAR
HYDRAULIC CYLINDER
Landing Gear Hydraulic Schematic
AIRPLANE AND SYSTEMS
ISSUED: JULY
13,1973