PREPARED PIPER AIRCRAFT CORP CHECKED DEVELOPMENT …

P I P E R A I R C R A F T C O R P .D E V E L O P M E N T C E N T E R , V E R O B E A C H , F L A .

P A G E

P REPARED

C HEC KED

AP P ROVED REPORT VB-170

Airplane Flight Manual Model PA-28-235

FAA APPROVED 7/15/63

1 of 7

Piper Model PA-28-235Normal Category Only

AIRPLANE FLIGHT MANUAL

1. Limitations Section The following limitations must be observed in the operation of this airplane:

Engine Lycoming 0-540-B2B5 or 0-540-B1B5 or 0-540-B4B5

Engine Limits For all operations, 2575 rpm, 235 hp.

Fuel 80 minimum octane aviation fuel

Propeller McCauley 1P235PFA80, blade pitch 66 through 71. Maximum diameter 80 inches, minimum diameter 78. 5 inches.

Hartzell HC-C2YK-1/8468-4, pitch: high 27 degrees ± 2 degrees low 13. 5 degrees ± . 2 degrees at 30” station, maximum diameter 80 inches, minimum diameter 80 inches. NOTE: Constant speed propeller approved for use with 0-540-B4B5 engine only.

Sensenich M80BMM or 80BM8 blade pitch 69 through 71. Maximum diameter 80 inches, minimum diameter 78. 5 inches. NOTE: Constant speed propeller approved for use with 0-540-B4B5 engine only.

Power Instruments Oil Temperature: GREEN arc (normal operating range) 75OF to 245OF; RED line (maximum) 245OF.

Oil pressure: GREEN arc (normal operating range) 60 psi to 90 psi; YELLOW arc (caution range) 25 psi to 60 psi; RED line (minimum) 25 psi when installed or 60 psi when installed; RED line (maximum) 90 psi. Fuel pressure: GREEN arc (normal operating range) . 5 to 8 psi; RED line (minimum) . 5 psi; RED line (maximum) 8 psi.

Tachometer: GREEN arc (normal operating range) 500 to 2575 rpm; RED line (maximum continuous power) 2575 rpm.

Airspeed Limits Never Exceed . . . . . . . . . . . . . . . . . . . . . 197 (Calibrated Airspeed) Maximum structural cruise . . . . . . . . . . 156 (Miles per Hour) Maneuvering . . . . . . . . . . . . . . . . . . . . . 138 Flaps extended . . . . . . . . . . . . . . . . . . . . 115 Maximum positive load factor . . . . . . . . 3. 8 Maximum negative load factor . . . . . . . . No inverted maneuvers approved. Maximum Weight 2900 lbs.


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C. G. Range The datum used is 78. 4 inches ahead of the wing leading edge at the intersection of the straight and tapered section.

Weight Forward Limit Rearward Limit (Pounds) (In. Aft of Datum) (In. Aft of Datum) 2900 91. 5 93. 5 2100 81. 5 93. 5

(Serial Nos. 28-10001 thru 28-11378)

Weight Forward Limit Rearward Limit (Pounds) (In. Aft of Datum) (In. Aft of Datum) 2900 91. 5 93. 5 2600 86. 0 93. 5 2100 81. 5 93. 5

(Serial Nos. 28-7110001 to 28-7210023)

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.

Maneuvers No acrobatic maneuvers, including spins, approved.

Placards 1. 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 MANU- ALS. NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. "

2. Adjacent to upper door latch:

"ENGAGE LATCH BEFORE FLIGHT. "

3. On the inside of the baggage compartment door:

"MAXIMUM BAGGAGE 200 LBS. "

4. On the instrument panel in full view of the pilot:

"ROUGH AIR OR MANEUVERING SPEED 138 M. P. H. "


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3 of 7

Placards (Cont’d) 5. Adjacent to the throttle for AutoControl II installation:

"AUTOCONTROL LIMITATIONS. "

1. Automatic Pilot to be off during takeoff and landing. 2. Automatic Pilot use prohibited above 175mph C. A. S.

6. On the instrument panel in full view of the pilot when the Auto- Flite is installed:

"FOR HEADING CHANGES: PRESS DISENGAGE SWITCH ON CONTROL WHEEL. CHANGE HEADING. RELEASE DISEN- GAGE SWITCH. "

7. On the instrument panel in full view of the pilot when the Auto- Flite II is installed:

"TURN AUTOFLITE ON. ADJUST TRIM KNOB FOR MINIMUM HEADING CHANGE. FOR HEADING CHANGE, PRESS DISEN- GAGE SWITCH ON CONTROL WHEEL, CHANGE HEADING, RELEASE SWITCH. ROTATE TURN KNOB FOR TURN COM- MANDS. PUSH TURN KNOB IN TO ENGAGE TRACKER. PUSH TRIM KNOB IN FOR HI SENSITIVITY. LIMITATIONS AUTO- FLITE OFF FOR TAKEOFF AND LANDING. "

8. On the instrument panel in full view of the pilot when the supple- mentary 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. "

Airspeed RED radial line Never Exceed 197 mph (171 knots) Instrument Markings YELLOW arc Caution Range 156 to 197 mph Smooth Air Only (136 to 171 knots)

GREEN arc Normal Operating 70 to 156 mph Range (61 to 136 knots)

WHITE arc Flap Down Range 61 to 115 mph (53 to 100 knots)


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4 of 7

2. Procedures 1. The stall warning system is inoperative with the master switch off. Section 2. Electric fuel pump must be on for both landing and takeoff.

3. Except as noted above, all operating procedures for this airplane are normal.

4. (Automatic Pilot Installation Only)

The following emergency information applies in case of automatic pilot malfunction:

a. In case of malfunction, disengage automatic pilot controls.

b. In emergency, automatic pilot may be overpowered manually.

c. In cruise configuration, malfunction results in 55-degree bank and 100-ft. altitude loss. In approach configuration and malfunction results in 18-degree bank and 40-ft. altitude loss.

5. (Electric Pitch Trim Installation Without Pitch Trim Switch)

The following emeergency information applies in case of electric pitch malfunction:

a. In case of malfunction, disengage electric pitch trim by pulling out circuit breaker on instrument panel.

b. In emergency, electric pitch trim may be overpowered using manual pitch trim.

c. In cruise configuration, malfunctin results in 10O pitch change and 30 ft. altitude variation.


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5 of 7

2. Procedures 6. (AutoFlite Installation Only) Section The following emergency information applies in case of autoflite (Cont'd) malfunction:

a. In case of malfunction PRESS disconnect switch on pilot’s control wheel.

b. Rocker switch on instrument panel - OFF.

c. Unit may be overpowered manually.

d. In cruise configuration malfunction, 3 seconds delay results in 60O bank, and 100 ft altitude loss.

e. In approach configuration malfunction, 1 second delay results in 10O bank and 0 ft altitude loss.

7. (AutoControl III Installation Only)

I. Limitations:

Pilot off during takeoff and landing.

II. Procedures:

a. Normal Operation

Refer to Manufacturer’s Operation Manual.

b. Emergency

1. In case of malfunction, disengage manual controls.

2. In emergency, pilot may be overpowered manually.

3. In cruise configuration malfunction 3 seconds delay results in 60O bank, and 100 ft altitude loss.

4. In approach configuration malfunction, 1 second delay results in 10O bank, and 0 ft altitude loss.

8. (Electric Pitch Trim Installation With Pitch Trim Switch)

The following emergency information applies in case of electric Pitch Trim Malfunction:

a. In case of malfunction, disengage electric pitch trim by push- ing pitch trim switch on instrument panel to OFF position.

b. In an emergency, electric pitch trim may be overpowered using manual pitch trim.

c. In cruise configuration, malfunction results in 10O pitch change and 30 ft. altitude variation.


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6 of 7

2. Procedures 9. (AutoFlite II Installation Only) Section (Cont'd) I Limitations: AutoFlite off for takeoff and landing.

II Procedures:

a. Normal Operation - Refer to Manufacturer’s Operation Manual.

b. Emergency

1. In case of malfunction PRESS disconnect switch on pilot’s control wheel.

2. Rocker switch on instrument panel - OFF.

3. Unit may be overpowered manually.

4. In cruise configuration malfunction, 3 seconds delay results in 60O bank, and 100' altitude loss.

5. In approach configuration malfunction, 1 second delay results in 10O bank, and 0' altitude loss.

10. Fuel System Pre-Flight 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:

a. 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.

b. Place a container under the fuel sump drain outlet, which is located under the fuselage.


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7 of 7

2. Procedures Section c. Drain the fuel strainer by pressing down on the lever located (Cont'd) 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 the 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.

d. Examine the contents of the container placed under the fuel sump drain outlet for water and sediment and dispose of the contents.

CAUTION: When draining any amount of fuel, care should be taken to insure that no fire hazard exists bedore 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.

3. Performance All performance is given for a weight of 2900 pounds. Section Loss of altitude during stalls can be as great as 350 feet, depending on configuration and power.

Stalling speed, in mph. (Calibrated Airspeed): Flaps Up . . . . . . . . . . . . 70 Flaps Down . . . . . . . . . . 60

Weight / Balance & Equipment List RevisionTech Aero Avionics, LLC - CRS# JYJR029Y

o",,',"f ?uf ?51'3i'rll 3?3i,lu1 uu,,A/C Make :

A/G Model :

A/G Serial# :

WO Ref #:WB Date:WB ID #:

Page#:1

PIPERPA-28-2352B-108973201Aug-12-2011302

A/C Tail#Register Name

Name 2

Address 1

Address 2

Gity, State, PC

N9229WLITTLE DOG AVIATION INC

227 MARINERS WAY

NEW CASTLE, DE 19701-2295

Previous data taken from document dated Apr-05-2001Previous useful load = 1307.90

Model#

REMOVED ITEMS604

REMOVED SUB TOTAL

INSTALLED ITEMSM800RES-401

DescriptionPrevious data ->

LORAN 604, AND 416 ANTENNA

1 ltem @

CLOCKMUSIC SWITCHER

( LB / rN I Weight CG/Arm

83.54

67.00

67.00

67.0058.00

Moment

133008.69

268.00

268.00

13.4023.20

36.60

132777.29

1592.10

4.00

4.00

0.200.40

INSTALLED SUB TOTAL 2 ltems @ 0.60 61.00

1588.70 83.58NEW DATA >> NEW USEFUL LOAD = 1311.30

THIS WEIGHT AND BALANCE RECALCULATION IS AGCURATE ONLY TO THE EXTENT OF THE ACCURACY OF THE DATAOBTAINED FROM THE PREVIOUS WEIGHT AND BALANCE FIGURES PROVIDED BY THE AIRCRAFT OWNER.

, !'f.n '. ^a

':-\ -!'i\- ,- ; it. i "'l-.-- ,t, L c. l(-----Authorized Individual : JYJR029Y TREVOR SMITH

'(-^'to-

\7U.S. Departmentof TransportationFsderal AviationAdministration

MAJOR REPAIR AND ALTERATION(Airframe, Powerplant, Propeller, or Appliance)

Form Approved I Electronic Tracking NumberOMB No.2120-0020111B0Doo7 |

For FAA Use Only

INSTRUCTIONS: Print or type all entries. See Tilte 14 CFR 543.9, Part 43 Appendix B, and AC 43.9-1 (or subsequent revision thereof) forinstructions and disposition of this form. This report is required by law (49 U.S.C. 544701). Failure to report can result in a civil penalty for eachsuch violation. (49 U. S. C. 546301(a))

1. Aircraft

Nationality and Registration Mark

usA N9229WSerial No.

28-]-0897Make

PIPERModel

PA-28-235Series

2. Owner

Name fAs shown on registration certificate)

LIITLE DOG AVTATION INCAddress (As shown on registration certificate)

227 MARINERS WAY

NEW CASTLE, DE

19701-2295 USA

3. For FAA Use Only

4. Type 5. Unit ldentification

Repair Alteration Unit Make Model Serial No.

T E AIRFRAME (As described in ltem 1 above)

r T POWERPLANT

I T PROPELLER

T u APPLIANCE

Type

Manutacturer

6. Conformity Statement

A. Agency's Name and Address B. Kind ofAgency

Tech Aero Avionics, LLC2080 SkyJ-ane Hangar E4Denton, Tx76207 USA

U. S. Certified Mechanic Manufacturer

Foreion Certified Mechanic C. Certificate No.

x Certified Repair Station FAA CRS* ;TTJRO2gYRadio, Li-nited Radio,Certifi ed Maintenance Organization

D. I certiry that the repair and/or alteration made to the unit(s) identified in item 5 above and described on the reverse or attachments heretohave been made in accordance with the requirements of Part 43 of the U. S. Federal Aviation Regulations and that the informationfurnished herein is true and correct to the best of my knowledge.

bdended ranoe fuelper 14 cFR P;rt 43 flApp.B

Signature/Date of Authorized'.lndividual -

,.=-" )'1;,r7' -i,-;..,tA"--tl TREVOR SMITH

12-August-2011

7. Approval for Return to Service

Pursuant to the authority given persons specified below, the unit identified in item 5 was inspected in the manner prescribed by theAdministrator of the Federal Aviation Administration and is ffi Approved Tl Rejected

FAA Flt. StandardsInspector

Manufacturer Maintenance OrganizationPersons Approved by CanadianDepartment of Transport

BYFAA Designee x Repair Station Insoection Authorization

Other (Specify)

certificate orDesignation No.

JT.]RO29Y

Signature/Date of AuthorizeF Individual

--=J'\.r.'" ;l'l rr:,,\ft.:*]TREVOR SMITH

12-Augrust-2011

FAA Form 337 (rooe)

NOTICEWeight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must becompatible with all previous alterations fo assure continued conformity with the applicable airworthiness requirements.

8. Description of Work Accomplished(lf more space 19 required, attach additional sheets. Identify with aircraft nationality and registration mark and date work compteted.)

USA N9229W

Nationality and Registration Mark DateRemovedLoransystemconsistingofll Morrow604,andAl6antenna. Fabricated'dollar-dime'skinpatch,usingthesuggestionsofAC43.l3-'1 BCh 4, to repair the hole left by antenna removal.

The aircraft's weight and balanQe, and equipment list have been revised to reflect these alterations.

f] ADDTTTONAL SHEETS ARE ATTACHED

FAA Form 337 (1 0-06)

FORM # CT|-006C (WO REPORT)

CUSTOMER WORK ORDERTech Aero Avionics, LLG

WO # 3201-FLR Task 2 AV pg 1

FAA Certified Repair Station # CRS# JYJR029Y

REPORT

CustCode:ROKE Phone:214-499-4654

ROBERT KEMBEL3820 LEISURE LNDENTON. TX 76210 USA

111111 111111 |ilil |ilil ilIil ililililililil ililililil ilililililililil|

Item

Part#

Model

Serial #

Mfgr.

Discrep. MISC SQUAWKS

A/C Tail # N9229W

A/C Make PIPER

A/C Model PA-28-235 | Ser* 128-10897

Job Status FINISHED

Job type STANDARD

Open Date Jun-15-201'1 Wednesday

Promised Aug-12-2011 Friday

Started Jul-06-2011 Wednesday

Finished Aug-12-2011 Friday

Printed Aug-12-2011 Friday 21 :19

- Discrepancyt'li sc squawks

- Preliminary lnspectionOK

- Hidden Damage lnspectiqnOK

- Progressive lnspectionOK

- AD's / SB's Complied withNone

- Correctivernsta'lled clock p/n u800-14BAT s/n D29488 rAW current manufacturer's installation instructions. Tested foroperation. neplaced magnet'ic compass with p/n c2300-14 s/n As-07910. performed compass swing and adjusted asnecessary. rnstalled customer supp'lied a'ircraft power cable for cPStuAP696. neplaced KN-65 DME p/n 066-1029-01with s,/n 9494, and tested for operation. Removed Kr-213 p/n 066-3025-00 s/n ]-712 for repair, reinstalledrepaired unit and tested for operation. Reference cRs# KG2R951K work order 48994. Removed Kx\758 p/n069-1019-00 s/n 23826 for nepair, reinstalled repaired unit and tested for operation. Reference cRs# KG2R951Kwork order 48995. Removed 604 t-oran, and 416 Loran Antenna. see updated weight and ba'lance, and 337 dated2-12-2010.

- Labor Date

- Empl

- Description Hrs -- Rate - OTX

- Total Lbr

27:ul 2011 wed27:ul2OLL wedl-4: ul 2011 rhu13:u'I2011 wedL3:u]2011 tlled

M800-14BAT \ D29488c2300-14 \ AS-07910066-L029-0r- \ 9494

SHIP UPS

O.W. PARTS

O.W. LABOR

O.W. SHIPPINGO.lr/, PARTS

O.W. LABOR

rnstall clockneplace compass, Swing compaRepai r chafed wj ri ng696 cableRemove Loran

LABOR TOTALS

cl ockCOMPASS

KN-65 DME

1 190.00! tl,,uu1 s00.00

EQUIPMENT TOTALS

2.00 RG

2. 50 RG

6.00 RG

2. 50 RG

3. 50 RG

16. 50

70.0070.0070.0070.0070.00

140.00175.00420.0017s.0024s.001,155.00

- Equip wlsclgl

-

Description Oty

-

Sell_Ea

- Sell_Ext

190.00tl'.vvs00.00915.00

- Other type

-- Description Oty

-

Sell

-

Sell ExtoutboundKX-175BKX-l-758KX_1758Kr-213Kr-213

1.00l.. UU

I. UU

l_.001.00r_.00

OTHER TOTALS

8.2740.00

380.00l_5 . zb16.00

555.00

8.2740.00

380.00ts.2616.00

))).vut-, 014. 53

Task Total 3,084.53

THE AIRCRAFT, COMPONENT, PROPELLER OR APPLIANCE IDENTIFIED ABOVE WAS REPAIRED IN ACCORDANCE

WITH CURRENT VIATION AGENCY REGULATIONS AND IS HEREBY APPROVED FOR RETURN TO

INSPECTOR / AUTHO SIGNATURECRS# JYJRO2gYCERTIFICATE #

//711

FORM # CTt-oo6c (wo REPoRT)

CUSTOMER WORK ORDER REPORT wo # 3201-FLR Task 3 AV ps ITech Aero Avionics, LLC

Cust Code: ROKE Phone: 214-499-4654

ROBERT KEMBEL3820 LEISURE LNDENTON, TX 76210 USA

r lil|| ]ilil ilil| lilll lllll llilr ilil! lllll illll lllil lllll lllll llll lll

A/C Tail# N9229W

A/G Make PIPER

A/C Model PA-28-235 | Ser# 128-10897

Job Status FINISHED

Job type STANDARD

Open Date Jun-15-2011 Wednesday

Promised Aug-12-2011 Friday

Started Jul14-2011 Thursday

Finished Jul26-2011 Tuesday

Printed Aug-12-2011 Friday 21'.02

Item

Part #

Model

Serial #

Mfgr.

Discrep. MUSIC SWITCHER

- DiscrepancyMUSIC SWITCHER

- Preliminary lnspectionOK

- Hidden Damage lnspectionOK

- Progressive InspectionOK

- AD's / SB's Complied withNOne

- Correctivernstal I ed si gtroni cs REs-401 l,tusi c swi tcher s,/lldated 1-17-2007. Tested for operation.

- Labor Date

- Empl

- Description

26lul 2011 rue rnstall N4usic switcherLABOR TOTALS

- Part Number Used

-

SKU DescriptionRES-401 18276 MUSTC SWITCHER

- Other type

-

Description

1004489 rAW ST-400/ST-600 Stereocom rnstal'lation rnstructions

Hrs

-

Rate - OTX

- Total Lbr

6.00 RG 70.006.00

420.00420.00

Oty

-

Sell

-

Sell Ext1.00

PARTS USED TOTALS

149.00

Oty

-

Sell

-

Sell Ext

149.00149.00

SHIP UPS tnbound

MAINTENANCE RELEASE/ RETURN TOSERVICE CRS#JYJRO29Y

THE AIRCRAFT, COMPONENT, PROPELLER OR APPLIANCE IDENTIFIED ABOVE WAS REPAIRED IN ACCORDANCE

WITH CURRENT FEDFRAL AVIATION AGENCY REGULATIONS AND IS HEREBY APPROVED FQR RETURN TO

INSPECTOR / AUTHORIZED SIGNATURECRS# JYJRO29YCERTIFICATE #

1-.00 12.80OTHER TOTALS

1_2.80r_2.80

Task Total 581. 80

FORM # CT|-006C (WO REPORT)

CUSTOMER WORK ORDER REPORT Wo # szl1-FLR Task 1 AV ps 1

Tech Aero Avionics, LLC

Cust Code: ROKE Phone: 214-499-4654

ROBERT KEMBEL3820 LEISURE LNDENTON. TX 76210 USA

ilililililililililffiill ililililililil ilil il]il||il ilililililt|A/C Tail# N9229W

A/C Make PIPER

A/C Model PA-28-235 | Ser# 128-10897

Job Status FINISHED

Job type STANDARD

Open Date Jun-15-2011 Wednesday

Promised Aug-12-2Q1 1 Friday

Started Jun-15-201 1 Wednesday

Finished Jul-29-2011 Friday

Printed Aug-12-2011 Friday 21:02

Item

Parl#

Model

Serial #

Mfgr.

Discrep. Kr-201C

- DiscrepancyKr-201-c

- Preliminary InspectionOK

- Hidden Damage InspectionOK

- Progressive InspectionOK

-AD's / SB's GompliedwithNone

- CorrectiveRemoved Kr-201c p/n 066-3008-02 s/nReference cRs# KG2R951K work order

- Labor Date

-

Empl -

Description

repai r. neinstalled repaired unit and tested for operat'ion.

Hrs

-

Rate - OTX

- Total Lbr

0.00 70.00

Oty

-

Sell- Sell Ext

24867 for48784.

FLAT RATE LABOR TOTALS

- Other type

-

DescriptionO.W. SHIPPTNGO.W, PARTS

O.W, LABOR

O,W, SHIPPING

KI-201C OUTBOUND

Kr-201cKr-201cKr-201c

1.001.00r_.00r_.00

OTHER TOTALS

6.8422.30

266.70 266.701,4 .54

6.8422.30

t4.54310. 38

Task TotalMAINTENANCE RELEASE/ RETURN TO SERVICE CRS#JYJRO2gY

THE AIRCRAFT, COMPONENT, PROPELLER OR APPLIANCE IDENTIFIED ABOVE WAS REPAIRED IN ACCORDANCEWITH CURRENT FEDERAL AVIATION AGENCY REGULATIONS AND IS HEREBY APPROVED FOR RETURN TO

CRS# JYJRO2gYCERTIFICATE #

380.38

DATE

.l

FRANK X. RUIZ AVIONICS970 West Chrrnd lar Blvd,Fregrro , eA . 937 06FAA Approvd Rpr SEe DF3R447t

ADDITIONAL EQUIPMENT LIST / REVISED WEIGTIT AND BALANCE

REGA/eA/eA/C

NOtiiIAKE:MODEL r

S/N:

9229wPI PERPA28-23528 -10897

DATE:TAEH:WoRK ORDER # ISUPERCEDED DATE:

WEIGHT

1596.30

04-05-2001L62L.66089907-19-1989

ARM

83.87

MOMENT

133878.00

t*trrtataitritittt**ttrtttt*t*t*tr*rr*rtrrrtrr*rrrrrrr

PREVIOUS A/C EMPTY

REMOVED ITEMS

AT5AAT5A REMOTE

INSTALLED ITEMS

KT76A XPDR

NEI{ A/C EMPTY

NEW A,/C E.W. !

NEUI A/C C.c. tNEW UgEFUL LOAD

2.005.30

65.30L77.40

130.60940.22

altattaattattata*tttt*taata

3.r.0 65.00 201 .50

1592.10 83 .54 133008.69

X RUIZ

.l AUTTIORIZED SIGNATUREFRANK X. RUIZ AVIONI,CS9?0 Wegt Chandler BIvd.Frccno, CA. 93706FAA APProvd RPr sta DF3R 4?L

*aaa*aitrtlltatl*ltttlialtl

1592.1083.54

130?.90

ABOVE INSTALI,ATIIN ACCORDANCE WISPECIPICATIONSFON NETURN TO 8

FRANK

*

MODEL:

'SEAIRl" r.ro:

iiLci 'r.iii'

t't

t,'' -)ts

897

I

iI

I

,

!

'

It

I

,

)t

I

{

'. I.?'-

MOMEN T

- I,t tBO6.672.0

AIRCRAFTD-L26-P2T ENCOER

'|'

TOTALS:

NdV{

NEW E.C'.G 85;85

.l,rof.5oNEI{ USEFUL'LOAD:

COIPUTED

'!.

')l ,

lrr:.,, i

,(^

'{r

7OO TIOGA DRIVE #5MoDEsTo, cA 95154

404-52

it.r'- i,

. .t.. .

WEIGHT AI{D BALANCE REPORT

-SUPPLEMENTAL EQUIPMENT LIST.

AIRCRAFT:

DATE: 5-11-88

NAME:

ADDRESS!

DAN OATES

2444 BROOKDALE CT.'l

MERCED, CA. 95340

lr9229Vl

' ':'I(I) INSTALLEDEQUIPMENT (R) REMOVED

E}'IPTY WEIGHT:

:.

1,595:50

I{EIGHT ARM

1595.t 83,8750.0

TODEST VIONICS

irf$"rt\[Jt I'A|,E ll 1 cf '2 - -. 1

jDttroction - Chart,_:rs - BerrtaliAt J r, )ve(! f or V;:tr,rans

Itr.'l'l i:

i.I 9229tr

$D7?,

i1lo

l) i

':ll.!",

.') / \j.l .

a

n--';1..- rI

rr l'

f-.t

S 'it -. St'rr. l\, r't O tl it:..

' . r,')\ ':"3.34I ttt :1i,. ,.?.4

l!uv IStl;.!) r,l(lLl J i'l4.liijT

liii,;.1li'llJliUi) ()l.llli,;li n.h Oa+.a

wr>E A/c. pd€1-E ',;/t:z 28-70897

4/ro/8t

Fr,',Loi1l1N .t liduIP,vldil.T .iruDri) oR iL.l,,iL,,/d J Aii liiiotil.:

LeSSnaL-plt 0I ctlftt

EUPTY WEIGHT FROM FACTORY: 8t.48 129159.11'l'X4 J.!OMEIIT

. rrrc jon 2q

KINd 'IO( 17OB

KING IO( 17OB

nNG ICt 201C 2.8

457.to

45?.t

782.84

KIT{G KI 214

KLnc KN 65 ( rndlcator )

KI}{G KN 55 reEote

KING KN 74

GEIIAVE SIGt'lA 1500

1.4

7.6

65.3 ' g!.42

r77.4 r3la,z+

.3 241 .61

65.3

2.

65

(rcc )

L

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L-*...

I

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MOM1,.il.rl': i;RiJ'JI;Etr'I.]L LOAD:

f,!,R ltltPl\lil :lTriljOl; 404-9:AtJ'l 0lt t zt,)t) jil(iuA1'('il!)

contq

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PREPARED PIPER AIRCRAFT CORP CHECKED DEVELOPMENT …