Piper PA-39 Twin Comanche C/R User manual

TWIN COMANCHE
PILOT’S OPERATING MANUAL
BY
_’
.,PIPER.
-- .---- .I_d.__._
/’
This manualis’ incompletewithout a current FAA4PPROoJEDAIRPLANEFLIGHTMAY’ i-~

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 Flight Manual,
instrument markings, and placards.
This Pilot’s Operating Manual is not designed, nor can any operating
manual serve,as a substitute for adequate and competent flight instruction,
or knowledge of the current airworthiness directives, the applicable federal
air regulations, and advisory circulars. It is not intended to be a guide of
basic flight instruction, nor a training manual for transition from single
engine flying to multi-engine flying.
If there is any inconsistency between the Airplane Flight Manual
approved by the FAA, and the additional information in this manual the
Airplane Flight Manual shall govern.
Additional copies of this manual, Part No. 761 453, may be
obtained from your Piper Dealer.
Published by
PUBLICATIONS DEPARTMENT
Piper Aircraft Corporation
761 453
Issued: June 1970

NOTE
PermanentPilot’s Operating Manual Revision Only
This Is Not A Complete Manual
This Pilot’s Operating Manual revision, PR730516, shall be
inserted into the current PA-39 Pilot’s Operating Manual,
761 453, issued June 1, 1970.

RJ3’ISiONS
The information compiled in this manual will be kept current by revisions distributed to
the airplane owners through their local dealers or distributors.
There are two types of revisions used to keep the Pilot’s Operating Manual current:
Temporary Revisions and Permanent Revisions. The material compiled in the revisions will
consist of information necessary to update the present information or add information to cover
added equipment.
I. Temporary Revision
This revision will be distributed at any time it is necessary to forward information to the
owners and operators of the airplane. The revision will usually consist of one or two pages
which may be inserted in the appropriate section of the manual. This revision will include
deletions and/or additions of material pertinent to different paragraphs of the manual.
II. Permanent Revision
This revision will be distributed periodically and will supersede all previous temporary
revisions. These revisions will be complete page replacement and shall be inserted in the manual
in accordance with the instructions given below.
1. Replace the obsolete pages with revised pages of the same page number. -
3
A. Insert pages with page numbers followed by a small letter in direct sequence with the
same common numbered page.
III. 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 that material was relocated to a different page or that an entire page was added.
Symbols will indicate only current revisions with changes and additions to or deletions of
existing text and illustrations. Changes in capitalization, spelling, punctuation or the physical
location of the material on the page will not be identified by symbols.
.

Current Permanent and Temporary Revisionsto the PA-30 Pilot’s Operating Manual issued June
1970 are as follows:
761 453 (PR7 10317)
761 453 (PR710827)
Permanent Revision Dated March 17, 1971
Permanent Revision in F/M
Added propeller synchrophaser
11-10& added fuel pump revision
11-l1.
Dated August 27. 1971
761 453 (PR711115)
761 453 (PR720220)
761 453 (PR7203 17)
761 453 (PR720428)
761 453 (PR730330)
761 453(PR730516)
761 453(PR730632)
76.1-453(PR75032 1)
Permanent Revision
Permanent Revision
Permanent Revision
Misc. Revision to P/O/M;
Added nosewheel alternate to
Weight & Balance.
Misc. Revision to P/O/M,
F/M W/B.
Permanent Revision to F/M
(Rev. 10)
Permanent Revision to W/B
Permanent Revision to P/O/M,
added Rev. 11 to A F/M.
Dated Nov. 15, 1971
Dated Feb. 20, 1972
Dated March 17, 1972
Dated April 28, 1972
Dated March 30, 1973
Dated May 16, 1973
Dated June 22, 1973
Dated March 21, 1975

$
FAA APPROVED 1.
/
AIRPLANEFLIGHTMANUAL i
FOR I
4
PlPER”TWINCOMANCHEC/R”
NOTE
THIS MANUAL MUST BE KEPT IN THE AIRPLANE AT ALL TIMES
MANUFACTURER’SMODEL- PA-39
MANUFACTURER’SSERIAL-39. 25
REGISTRATION
- N w C%S-IPM
FAA APPROVED BY:
D. 0. A. No. EA-1
LOCK HAVEN, PENNSYLVANIA
DATE OF APPROVAL: NOVEMBER 28, 1969
APPROVAL BASIS: CAR 3 AND FAR PART 21, SUBPART J. - --
NORMALCATEGORYONLY ,.+- i
,,,’
/’

mI!‘i C%wcm C/R
-
TABLE OF CONTENTS
SECTION I
Log of Revisions
SECTION H
. . . . . . . . . . . . . . . . . . . , .. . . . . -. . . . Page
. . . . . . . . . . . . . . 1
Limitations . . . . . . . . . . . . . . . .
A. Engines ......._.. ::: :...*.:: :: :.‘...““““‘.......... 3
B. Fuel . . . . . *. --. . . . -‘- . . . . . . * . .c. Propellers .~;~~;........................~.............::: 3
. . ~
D. Cowl Flaps . . . . . : 1 1 1 . . . * . . . . . 3
- . . . * . * . *--.**-.**. * . * . . . . . . 3
E. Instrument Markings (Power Plant; . 1 1 * . . . . * . . * * * * - * . * . . . . * * . * * - . . . .
F. Airspeed Limitations and Indicator Markings (CaEbh;ed’Airspeed)’ * 1 1 1 : : 1 : 1 : : 1 1 1 3
G. Flight Load Factors . _
3
H. Maximum Weight . _ . : : : 1 1 : : 1 : : : : : 1 1 1 : : 1 1 : 1 : : : 1 : : : : 1 ’ - ’ . ’ . . ’
4
I. C. G. Range 4
,. Mane”“ers , : 1 1 : : : : . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . : : : : : : : : 5
K. Wing Flap Settings . . 1 . . . . 5
. . . . . . . : . . . . . . . . . . . . . . . . . . . . . . . . . . - . . .
L. UnusableFuel ..:;I: ....._.. :::::: . . . . . . . . . . . . . . . . . . . . . . . . 5
M. UsableFuel 5
.-- **- * - *. . . . . . * . . 1
-N. Placards . . II::;::: . . . . . . . . . . . . . . . . ..~ . . . . . . . . . . . . . . 1:::: 5
0. Instrument Markings . . . . . . . . . 5
. . . *. .. *‘- -*---*‘-** . . * . * * . . 5
P. LandingGearDownLigh;.::::::::::::::::::::::::::::::::‘..” 6”
. . . . .
SECTION III
Procedures . . . . . . . . . . . . . . . . .
A. Standard Procedures . . * . . * . . . * *----**.-* . . . - * -* *. *
1. StoppingEngines . . . . . . 7
2. Warning
.::::::::: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
. . * - . * * . . . . . . * . - *
3. Spins .::::: . . . . . .._................ ~...:::::::::::: 7
. . - . * . - . . 7
* *. . . . . *. * * * * * - - * * -
B. Systems Operation and Checks
. . . . . . : . . . . . 7
1. Voltage Regulating and Alternator System for’A&raft’skrial Numbers j9:1’ ’ . . ’ ’ .
thru 39-145 _ .
9
~*~~1*~~--* . . . . . . . . .
2. Alternator Paralleling System for Aircraft Serial Numbers 39-146 and up ’ : : 1 : : 1 1
3. Circuit Breakers . . . . . .’
9
4. FuelManagement 9
.;...:: . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
5. Manual Extension of: i&ding Gear . . . : : : : : : : : . ’ * ’ ’ * ’ ’ * * . . ’ . ’ * ’ . * lo
. . . . . . . . * - * * * * * *. * . 11
C. Emergency Procedures . .
1. Detecting a Dead Engine . 1 ; 1 : 1 : 1 1 : 1 : 1 . . . . . . - . . . . . . . . . . . . . . . . 13
2. Feathering Procedure . . . . . . . . . . . . . . . . . . . .
3. Unfeathering Procedure
. . 1 . . . . 13
. .
4. Engine Failure During Take-Off
. : 1 1 : 1 1 . . : : 1 : : 1 1 ’ ’ ’ . * * ’ ’ * . ’ . * ’ ’ . . ’ :3”
.-*--l-*m * - . * * * * . -
5* EngineFailureDuringaimb ..::::::::::‘.‘..-....‘.......... I4
6. Single Engine Landing . . * . . . . . **-***-*-- . . . 14
7. Single Engine Go-Around’ : 1 ; 1 : ; : 1 : ; 1 ; : 1 - * * * * * * * * * . . + - * . * - . . * l4
-**--.-.-- ----*--*** . 14
FAA APPROVED November 28, 1969
RElSSUED: June 1, 1970
REVISED: November 30,197l
REPORT: 1605 PART I P -- .-. -
MODE1 .+
/’

SECTION L’
Supplements .................
A. Oxygen System installation ....
1. Limitations ...........
2. Procedures ...........
3. Placards .............
4. Emergency ...........
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
. . .
.....................
19
..................... 21
..................... 21
..................... 21
..................... 21
..................... 21
B. Piper AutoControl III (Model AK161) Installation ....................... 23
1. Limitations ........................................... 23
’ Operating Instructions-. .................................... 23
3. Normal Operation ....................................... 23
4. Emergency Procedures .................................... 24
C. Brittain Industries, Inc. Model TT-5 Tip Tanks Installation .................. 25
1. Limitations ........................................... 25
’ Operating Procedures - Normal-. .............................. i 25
3. Performance .......................................... 26
4. Emergency ........................................... 26
D. Piper AltiMatic IILB Installation .................................. 27
1. Limitations ........................................... 27
1 Operating Instructions-. .................................... 27
3. Normal Flight Operation ................................... 28
4. With Glide Slope Coupler Installed (Flight) ........................ 28
5. Emergency Procedures .................................... 28
6. Placards ............................................. 29
E. Anti-Collision (Strobe) Light Installation ............................. 3 1
1. Operating Limitations ..................................... 3 1
F. Anti-Icing Equipment Installation ................................. 33
1. Placards ............................................. 33
2. Operating Instructions .................................... 33
G. Piper AltiMatic IIIB- 1 ........................................ 3 5
1. Limitations ........................................... 35
2. Procedures ........................................... 35
3. Performance .......................................... 40
FAA APPROVED November 28.1969
REISSUED: June 1.1970
REVISED: November 30,197 1

REVISIONS
The information compiled in this manual will be kept current by revisions distributed to
the airplane owners through their local dealersor distributors.
There are two types of revisions used to keep the Pilot’s Operating Manual current:
Temporary Revisions and Permanent Revisions. The material compiled in the revisions will
consist of information necessaryto update the presentinformation or add information to cover
addedequipment.
I. Temporary Revision
This revision will be distributed at any time it is necessaryto forward information to the
owners and operators of the airplane. The revision will usually consist of one or two pages
which may be inserted in the appropriate section of the manual. This revision will include
deletions and/or additions of material pertinent to different paragraphsof the manual.
II. Permanent Revision
This revision will be distributed periodically and will supersedeall previous temporary
revisions. These revisions will be complete pagereplacement and shall be inserted in the manual
in accordancewith the instructions given below.
1. Replacethe obsolete pageswith revised pagesof the same pagenumber.
2. Insert pageswith page numbers followed by a small letter in direct sequencewith the
samecommon numbered page.
III. Identification of RevisedMaterial
Revised text and iliustrations 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 that material was relocated to a different pageor that an entire pagewasadded.
Symbols will indicate only current revisions with changesand additions to or deletions of
existing text and illustrations. Changesin capitalization, spelling, punctuation or the physical
location of the material on the pagewill not be identified by symbols.
i ’
___--.-

REVISIONS ISSUED
Current Permanent and Temporary Revisions to the PA-39 Pilot’s Operating Manual issued June
1970 are as follows:
761 453 (PR710317)
761 453 (PR710827)
Permanent Revision Dated March 17, 1971
Permanent Revision in F/M
Added propeller synchrophaser
II-IO & added fuel pump revision
II-l 1.
Dated August 27, 1971
761 453 (PR7111 IS)
761 453 (PR720220)
761 453 (PR7203 17)
761 453 (PR720428)
761 453 (PR730330)
761 453 (PR730516)
761 453 (PR730622)
761 453 (PR750321)
761 453 (PR751226)
Permanent Revision
Permanent Revision
Permanent Revision
Misc. Revision to P/O/M;
Added nose wheel alternate to
Weight & Balance.
Misc. Revision to P/O/M,
F/M, W/B.
Permanent Revision to F/M
(Rev. 10)
Permanent Revision to W/B
Permanent Revision to P/O/M,
added Rev. 11 to A F/M.
Permanent Revision to P/O/M
Dated Nov. 15: 1971
Dated Feb. 20, 1972
Dated March 17, 1972
Dated April 28, 1972
Dated March 30, 1973
Dated May 16, 1973
Dated June 22, 1973
Dated March 2 1, 1975
Dated December 26, 1975

TWIN COMANCHE C/R
SECTION 1
LOG OF REVISIONS
Revision RevisedPages Description and Revision FAA Appi oved
Date
This manual, which was completely revisedJune 1, 1970, applies to
Piper Model PA-39-1 and up.
1.
3
1.
I-ii
I-19
PageI-32 added
PagesI-33 & 34
added
II-2 1
II-24
I-26
I-28
I-29
II-5
II-6
II-24
II-29
Under Section V, added Item F. Nov. 2, 1970
Added Item F.
Added information for Supplement F.
Added Supplement F.
Heated GlassPanel Installation added.
Appropriate was appropriated. March 17, 1971
Revised Supplement D - Item 2. - d.
Added to Supplement D Item 6. - f.
C. G. Chart Clarified.
Basic weight was basisweight.
Added Radair Exhaust GasTemperature Indicator
and Delta Mixture Control Indicator.
Added Narco ATS-A Transponder and King
Digital ADF KR-85.
3.
4.
5.
6.
7.
II-29
II-29
II-I 0
II-I 1
I-3
H-9
II-IO
I-9
Added Bendix ADF-T 12D. April 19, 1971
Added Marker Beacon Installation MBT-R-I 2. June 1, 1971
Added Propeller-Synchrophaser. August 13, 1971
Added Piper Dwg. Nos. to Fuel Pumps.
Added additional Hartzell Propellers. Sept. 3, 1971
Added additional Hartzell Propellers.
Added additional Hartzell Propellers to Spinners.
Revisedinstructions for Voltage Regulating Nov. 1, 1971
System item e. and g.
FAA APPROVED November 28,1969
REISSUED: June 1,197O
REVISED: November 1,197l
REPORT: 1605 PART I PAGE 1’
MODEL: PA-39

TWIN COMANCHE C/R
LOG OF REVISIONS (cant)
Revision , Revised Pages Description and Revision FAA Approved
Date
8. Revised Section III Item B. .
i
ii Added Supplement G. AltiMatic IIIB-1. Nov. 30, 1971
9 Under B. Systems Operation and Checks- Items
1 and 2 combined to 1. a & 1. b, added Ser.
Nos. 39-1 thru 39-145. Reviseditem 2 to
Alternator Paralleling information for Ser. Nos.
39-146 and up.
10 Added information from page9.
11 Added information from page 10.
13 Emergency Proceduresfor Feathering and
Unfeathering revised to include Alternator
Paralleling.
19 Added Supplement G. AltiMatic IIIB-1.
Pages35-36-37
38-3940
added
9. 6
10. 11
Added Warning Placard information.
-Added item (b) to Cruising under Crossfeed
Operation and Single Engine Operation.
Mar. 30,1973
May 16, 1973
11. 6 RevisedWarning Placard information. March 21: 1975
c,
’ r*; .s ,*
. I
%. Everly
rsec .+t-
REPORT: 1605 PART I PAGE 2
MODEL: PA-39
FAA APPROVED November 28,1969
REISSUED: June 1,197O
REVISED: March 21.,1975

TWIN COMANCHE C/R
SECTION I
LOG OF REVISIONS
Revision RevisedPages Description and Revision FAA
Approved
Date
This manual, which was completely revisedJune I, 1970, applies to
Piper Model PA-39-l and up.
1.
2.
I-ii
I-19
PageI-32 added
PagesI-33 & 34
added
II-2 1
II-24
I-26
I-28
I-29
II-5
II-6
II-24
II-29
Under Section V, added Item F. Nov. 2, 1970
Added Item F.
Added information for Supplement F.
Added Supplement F.
HeatedGlassPanelInstallation added.
App>opriate was appropriated. March 17, 1971
RevisedSupplement D - Item 2. - d.
Added to Supplement D Item 6. - f.
C. G. Chart Clarified.
Basic weight wasbasisweight.
Added Radair Exhaust GasTemperature Indicator
and Delta Mixture Control Indicator,
Added Narco ATS-A Transponder and King
Digital ADF KR-85.
3.
4.
5.
6.
7.
II-29
II-29
II-I 0
II-1 1
I-3
II-9
II-IO
I-9
Added Bendix ADF-T 12D. April 19, 1971
Added Marker BeaconInstallation MBT-R-12. June 1, 1971
Added Propeller Synchrophaser. August 13, 1971
Added Piper Dwg. Nos. to Fuel Pumps. .
Added additional Hartzell Propellers. Sept. 3, 1971
Added additional Hartzell Propellers.
Added additional Hartzell Propellers to Spinners.
Revisedinstructions for Voltage Regulating Nov. 1, 1971
System item e. and g.
FM APPROVED November 28,1%9
REISSUED: June 1.1970
REVISED: November 1,197l
REPORT: 1605 PART I Py- ---
MODE! ,’ #--- I
I

i,!3,‘:‘
,-’
lr~h~COMANCHE
C/R
LOG OF REVISIONS (cant)
Revision Revised Pages Description and Revision FAA Approved
Date
8. .
i Revised Section III Item B. Nov. 30. 197 1
ii Added Supplement G. AltiMatic IIIB-1.
9 Under B. Systems Operation and Checks - Items
1 and 2 combined to 1. a & 1. b, added Ser.
Nos. 39-l thru 39-145. Revised item 2 to
Alternator Paralleling information for Ser. Nos.
39-146 and up.
10 Added information from page 9.
11 Added information from page 10.
13 Emergency Procedures for Feathering and
Unfeathering revised to include Alternator
Paralleling.
19 Added Supplement G. AltiMatic IIIB-I.
Pages 35-36-37
38-39-40
added
9.
6
10. 11
Added Waming Placard information.
. Added item (b) to Cruising under Crossfeed
Operation and Single Engine Operation.
Mar. 30,1973
May 16, 1973
11. 6
Revised Warning Placard information. March 21, 1975
p;; >{*
m Everly’
L REPORT: 1605 PART I PAGE 2 FM APPROVED November 28,1%9
REISSUED: June 1,197O
REVISED: March 21,1975

TWIN COMANCHE C/R
SECTION 11
LIMITATIONS
The following limitations must be observed in the operation of this airplane:
A.
ENGINES
Lycoming LIO-320-BIA (Right)
Lycoming 10-320-B1A (Left)
ENGINE LIMITS
For all operation 2700 RPM, 160 HP (SeeManeuvers)
B.
C.
I
I
I
I
D.
E.
FUEL
1OO/130 Octane Aviation Gasoline(Minimum)
PROPELLERS
Hartzell HC-E2YL-2B or HC-E2YL-2BF or HC-E2YL-2BS or HC-E2YL-2BSF (Left)
Constant Speed
Full Feathering; Blades7663-4 or F7663-4
Pitch Settings at 30 in. station
Station: High 76’ - 77 ‘, Low 12’
Diameter: Not over 72 inches
Not under 70 inches
(No further reduction permitted)
Hartzell HC-E2YG2BL or HC-E2YL-2BLF or HC-E’LYL-2BLS or HC-E2YL-2BLSF (Right)
Constant Speed
Full Feathering; Blades J7663-4 or FJ76634
Pitch Settings at 30 in. station
Station: High 76” - 77 ‘, Low 12’
Diameter: Not over 72 inches
Not under 70 inches
(No further reduction permitted)
COWL FLAPS
Cowl flaps are provided to allow manual control of engine temperatures. The cowl flaps should be
open during ground operations and in climbs. In no caseshould the cylinder head temperatures be
allowed to exceed500” F. and the oil temperatures allowed to exceed245” F.
INSTRUMENT MARKINGS (POWER PLAN?)
One
One
I
One
One
OIL TEMPERATURE
Green Arc (Normal Operating Range)
Yellow Arc (Caution)
Red Line (Maximum)
120” to 245°F
60” to 120’F
245” F
FAA APPROVED November 28,1969
REISSUED: June 1,197O
REVISED: September 3,197l
REPORT: 1605 PART I PAGE 3
MODEL: !A-39

y TWIN COMANCHE C/R
F.
G:
OIL PRESSURE
GreenArc (Normal Operating Range)
Yellow Arc (Caution)
Red Line (Minimum)
Red Line (Maximum)
60 PSI to 90 PSI
25 PSI to 60 PSI
and 90 PSI to 100 PSI
‘8 PSI
100PSI
TACHOMETER
GreenArc (Normal Operating Range)
Red Line (Maximum)
500 RPM to 2700 RPM
2700 RPM
FUEL FLOW
GreenArc (Normal Operating Range)
Red Line (Maximum at SeaLevel)
OGPHto16GPH
16 GPH (7 PSI)
CYLINDER HEAD TEMPERATURE
Green Arc (Normal Range)
Red Line (Maximum)
200” to 500” F
500” F
AIRSPEED LIMITATIONS AND INDICATOR MARKINGS (Calibrated Airspeed) Normal Category
NEVER EXCEED SPEED
MAXIMUM STRUCTURAL CRUISING SPEED
DESIGN MANEUVERING SPEEDS
- Minimum Weight (2825 lbs.)
0 Maximum LWeight(3600 lbs.)
230 MPH
194MPH
1.45MPH
162MPH
FLAPS EXTENDED SPEEDS 70 MPH to 125MPH
MAXIMUM GEAR EXTENDED SPEED 150MPH
MINIMUM CONTROL SPEED (Single Engine) 80 MPH
STALL SPEED
Gear and Flaps Up
Gear and Flaps Down
76 MPH
70 MPH
AIRSPEED INDICATOR MARKINGS
Green Arc (Normal Operating Range)
Yellow Arc (Caution Range- Smooth Air)
White Arc (Flaps Extended Range)
Radial Red Line (Never Exceed - Smooth Air)
Radial Red Line (Minimum Control Speed- Single Engine)
Radial Blue Line (Best R/C Speed Single Engine)
76 MPH to 194MPH
194 MPH to 230 MPH
70 MPH to 125 MPH
230 MPH
80 MPH
105 MPH
FLIGHT LOAD FACTORS
Positive Load Factor (Maximum)
Negative Load Factor (Maximum)
(No Inverted ManeuversApproved)
3.8 G
REPORT: 1605 PART I PAGE 4
; MODEL: PA-39 ,
FAA APPROVED November 28,1969
REISSUED: June 1.1970

H. SlAXIMUM WEIGHT
TWIN COMANCHE C/R
IT IS THE RESPONSIBILITY OF THE AIRPLANE OWNER
AND THE PILOT TO ASSURE THAT THE AIRPLANE IS
PROPERLY LOADED. MAXIMUM ALLOWABLE GROSS
WEIGHT 3600 POUNDS. SEE “WEIGHT AND BALANCE
SECTION” FOR PROPER LOADING INSTRUCTIONS.
1. C. G. RANGE
Weight Forward Limit
Pounds InchesAft of Datum
Aft Limit
Inches Aft of Datum
I
3600 86.5 92
3200 83.0 92
2825 82.0 92
1. Straight line variation between the points given.
2. Datum is 79 inches ahead of the wing leading edge at
spanwise Station 97.0 (First leading edge skin lap outboard
of enginenacelle).
J. MANEUVERS
All intentional acrobatic maneuvers]including spins) are prohibited. Avoid abrupt maneuvers.When
performing power on stalls do not exceed2 100 RPM.
K. WING FLAP SETTINGS
Take-Off 0” to 15”
Landing 27”
The flaps are electrically operatedand the deflection is displayed on a flap position indicator. Take-off
rangeindicated by White Arc on flap indicator.
L. UNUSABLE FUEL
The unusable fuel in this aircraft has been determined as 3 gallons in each inboard tank inn
flight attitudes.
-
M. USABLE FUEL
Inboard tanks - 27 gallons each
Auxiliary tanks (outboard) for usein level flight only - 15 gallons each.
N. PLACARDS
On instrument panel in full view of the pilot:
THIS AIRPLANE MUST BE OPERATED AS A NORMAL
CATEGORY AIRPLANE IN COMPLIANCE WITH THE
AIRPLANE FLIGHT MANUAL. ACROBATIC MANEUVERS
(INCLUDLN_C;SPINS)PROHIBITED.
FAA APPROVED November 28,1969
REISSUED: June 1. 1970
REPORT: 1605 PART I PAGE 5
MODEL: PA-39

‘WIN COMANCH
OIL PRESSC
GreenA
Yellow ,
Red Lin
Red Lin
TACHOMET
GreenA
Red Lir
FUEL FLOW
Green P
Red Lir
CYLINDER
Green1
Red Lir
AIRSPEED :
NEVER EX(’
MAXIMUM
DESIGN Mb
* &&.&.&
0 Maxim1
FLAPS EXT
MAXIMUM ;
MINIMUM c
STALL SPE
Gear ai,
Gearai
AIRSPEED
Green I
Yelloi
White,
Radial
Radial
Radial’
FLIGHT Li
Positive Loi
NegativeL?
:No Inverte
.i
,RT: 16d
EL: PA-39 ‘.
On the baggagecompartment door:
EMERGENCY EXIT
HOLD KNOB UP
TURN LATCH CLOCKWISE
On landing gearoperating motor accessdoor:
EMERGENCY GEAR EXTENSION. REMOVE COVER,
EXTENSION INSTRUCTIONS ON REVERSE SIDE.
Orfinstrument panel:
STALL WARNING
The stall warning system is inoperative when the master switch is off.
At the fuel strainer compartment:
FUEL STRAINERS DRAIN ‘ONLY TANK INDICATED BY
FUEL SELECTOR. ALLOW SUFFICIENT DRAIN TIME.
On fuse panel accessdoor:
FUSE PANEL ACCESS DOOR
On right rear window moulding in baggagearea:
MAXIMUM BAGGAGE AND/OR PASSENGER WEIGHT 250
LBS. IN BAGGAGE AREA INCLUDING SEATS. SEE WEIGHT
AND BALANCE.
On the instrument panel;
MINIMUM SINGLE ENGINE CONTROL SPEED
MANEUVERING SPEED
MAXIMUM GEAR DOWN SPEED
On the instrument panel:
80 MPH
162 MPH
150 MPH
WARNING - UNCOORDINATED MANEUVERS, INCLUDING
SIDE SLIPS OF 30 SECONDS OR MORE, FOR ANY
REASON, AND FAST TAXI TURNS JUST PRIOR TO
TAKE-OFF CAN CAUSE LOSS OF POWER IF FUEL
TANKS IN USE ARE LESS THAN l/4 FULL
INSTRUMENT MARKINGS
Wing Flap Setting
Take-Off (White Arc) 0” to 15”
Landing (Full) 27 ’
P. LANDING GEAR DOWN LIGHT
The green gear down light on the instrument panel indicates the landing gear is down and lock1
GEAR INDICATORLIGHTS ARE DIMMED WHILE THE INSTRUMENT LIGHTS ARE ON. 1
REPORT: 1605 PART 1 PAGE 6
MODEL: PA-39
1
FAA APPROVED November 28,Ig
REISSUED: June 1, I4
REVISED: March 21,1$

BW 98-05
PIPER, THE NEW
AIRWORTHINESS DIRECTIVE
SMALL AIRCRAFT & ROTORCRAFT
98-04-27 * THE NEW PIPER AIRCRAF’T CORPORATION: Amendment 39- 10339; Docket
_ No. 97-CE-61-AD.
Applicability: Models PA-23, PA-23-160, PA-23-235, PA-23-250, PA-E23-250, PA-30, PA-39,
PA-40, PA-31, PA-31-300, PA-31-325, PA-31-350, PA-34-200, PA-34-200T, PA-34-220T, PA-42,
P&42-720, PA-42- 1000 airplanes (all serial numbers), certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision,
regardless of whether it has been modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified, altered, or repaired so that the
performance of the requirements of this AD is affected, the owner/operator must request approval
for an alternative method of compliance in accordance with paragraph (d) of this AD. The request
should include an assessment of the effect of the modification, alteration, or repair on the unsafe
condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request
should include specific proposed actions to address it.
Compliance: Required as indicated, unless already accomplished.
To minimize the potential hazards associated with operating the airplane in severe icing
conditions by providing more clearly defined procedures and limitations associated with such
conditions, accomplish the following:
(a) Within 30 days after the effective date of this AD, accomplish the requirements of
paragraphs (a)(l) and (a)(2) of this AD.
NOTE 2: Operators should initiate action to notify and ensure that flight crewmembers are
apprised of this change.
(1) Revise the FAA-approved Airplane ,Flight Manual (AFM) by incorporating the
following into the Limitations Section of the AFM. This may be accomplished by inserting a copy of
this AD in the AFM.
“WARNING
Severe icing may result from environmental conditions outside of those- for which the airplane
is certificated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (supercooled
liquid water and ice crystals) may result in ice build-up on protected surfaces exceeding the
capability of the ice protection system, or may result in ice forming aft of the protected
surfaces. This ice may not be shed using the ice protection systems, and may seriously
degrade the performance and controllability of the airplane.
. During flight, severe icing conditions ‘that exceed those for which the airplane is
certificated shall be determined by the following visual cues, If one or more of these visual
cues exists, immediately request priority handling from Air Traffic Control to facilitate a route
or an altitude change to exit the icing conditions.
Unusually extensive ice accumulation on the airframe and windshield in areas not
normally observed to collect ice.
Accumulation of ice on the upper surface of the wing, aft of the protected area.
.- Accumulation of ice on the engine nacelles and propeller spinners farther aft than
normally observed.
. Since the autopilot, when installed and operating, may mask tactile cues that indicate
adverse changes in handling characteristics, use of the autopilot is prohibited when any of
the visual cues specified above exist, or when unusual lateral trim requirements or autopilot
trim warnings are encountered while the airplane is in icing conditions,
l
All wing icing inspection lights must be operative prior to flight into known or forecast
icing conditions at night. JNOTE: Thissupersedesany relief provided by the Master Minimum
Equipmei~kList(MMEL).)"

2 98-04-27 .I
“THE FOLLOWING WEqTeR CONjXTIONS
MAY BE ~C@@VE TO SEVERE
IN-FLIGHT ICtiG:
.
Visible rain at temperatures below 0 degrees Celsius ambient air temperature.
. Droplets that splash or splat&- on impact at temperatures below 0 degrees Celsius
ambient air temperature.
PROCEDURES FOR EXITING
THE SEVE,j?J3 ICtiG ENWROtiENT:
I, ..,.
These procedures are applicable to all flight phtises from takeoff to landing. Monitor the
ambient air temperature. While severe icing may form at temperatures as cold as -18 degrees
Celsius, increased vigilance is warranted at temperatures around free+ng with visible
moisture present. If the visual cues specified in the Limitations Section of the AFM for
identifying severe icing conditions are observed, accomplish the following:
Immediately request priority handling from Air Traffic Control to facilitate a route or an
Altitude change to exit the severe icing conditions in ‘order to avoid extended exposure to flight
conditions more severe than those for which the airplane has been certificated.
. Avoid abrupt and excessive maneuvering that may exacerbate control difficulties.
t’
. Do not engage the autopilot.
. If the autopilot is engaged, hold the control wheel firmly and disengage the autopilot.
If an unusu& roll response
;le angle-of-attacti.’
or uncommanded roll control movement is observed, reduce
. Do not extend flaps when holding in icing conditions. Operation with flaps extended
can result in a reduced wing angle-of-attack, with the possibility of ice forming on the upper
surface further aft on the wing than normal, possibly aft of the protected area.
. If the flaps are extended, do not retract them until the airframe is clear of ice.
. Report these weather conditions to Air Traffic Control.”
(b) Incorporating the AFM revisions, as required by this AD, may be performed by the
owner/operator holding-at least a private pilot certificate as authorized by section 43.7 of the
Federal Aviation Regulations (14 CFR, 43.7), and must be entered into the aircraft records showing
compliance with this AD in accordance with section 43.9 of the Federal Aviation Regulations
(14 CFR 43.9).
(c) Special flight permits may be issued in accordance with sections 2 1.197 and 2 1.199 of
the Federal Aviation Regulatioxis (14 CFR 21.197 and 21.199) to operate the airplane to a location
where the requirements of this AD can be accomplished.
(d) An alternative method of compliance or adjustment of the compliance time that provides
an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, FAA,
1201 Walnut, suite’.900,; Kansas City, Missouri 64106. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager,
Small Airplane Dire&orate.
NOTE 3: Information concerning the existence of approved alternative methods of compliance
with this AD, if any, mayibe obtained from the Small Airplane Directorate.
(e) All persons affected by this directive may examine information related to this AD at the
FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64 106.
(r) This amend&nt (39-10339) becomes effective on March 13, 1998.
YFOR FURTHER INFORMATION CONTACT:
Ns, John R* Dow, Sr,, Aerospace Engineer, Small Airplane Directorate, Aircraft Certification Servisls,
1201 w&mt, aujte 900, Kansas City, Missouri 64106; telephone [phone]; f~imiiet
[phone], . 4
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