wx950 stormscop

8/11/2019 wx950 stormscop

1/65

Stormscope

Series II

Weather Mapping Sensor

WX-950InstallationManual

This manual contains installation and operating instructions

and recommended flightline maintenance information forthe WX-950 Stormscope. This information issupplemented and kept current by Change Notices andService Bulletins published by Goodrich Avionics Systems.

009-10950-001 (Rev. C)

Goodrich Avionics Systems, Inc. 11 October 20015353 52

ndStreet, S.E.

Grand Rapids, MI USA 49512


2/65

ARev. C

ABOUT THIS MANUAL

Chapter 1 General InformationThis chapter includes equipment specifications and a functional description. It describes the various hardware

configurations and includes a list of items furnished and items required but not supplied with the equipment.

Chapter 2 Installation

This chapter contains instructions for unpacking the equipment and inspection for in-shipment damage. It also

includes information required to locate, assemble and install the equipment.

Chapter 3 Installation Checkout

This chapter contains instructions for doing post-installation and return to service checkout of the WX-950 using

the Goodrich Avionics SystemsWX-PA Portable Analyzer Kit.

Chapter 4 Maintenance

This chapter contains general flightline maintenance procedures. It includes periodic maintenance and

troubleshooting; and instructions for the return of defective components.

Appendix A Signal and Cable Characteristics

This appendix defines the electrical characteristics of all input and output signals.

Copyr ight 1996-2001

Goodrich Avionics Sy stems, Inc.

____________________________

Trademarks

St ormscope is a regist ered tra dema rk of Goodrich Avionics Syst ems, Inc.

Mylar and Teflon are registered tradema rks of Dupont.


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WX-950Installation Manual

iRev. C

LIST OF EFFECTIVE PAGES

Dates of original and changed pages are: Original (Rev. 00)......................9 February 1996Republished (Rev. B).....................23 April 1999Republished (Rev. C)............... 11 October 2001

NOTE

The portion of the text affected by the change is indicated by a vertical line in

the outer margins of the page. Changes to illustrations (other than diagrams

and schematics) are identified with a miniature pointing hand. Shading is

used to highlight the ar ea of diagr am s and schemat ics conta ining a change.

Total number of pages in this publication consists of the following:

Page Change

No. No.

Title Page ......................................................... 0

A Page................................................................ 0

i thru Vi................................................................ 0

1-1thru 1-8........................................................... 0

2-1 thru 2-22........................................................ 0

3-1 thru 3-8.......................................................... 0

4-1 thru 4-14........................................................ 0

A-1 thru A-6......................................................... 0

INSERT LATES T CHANGED P AGE S, DE STROY SU PE RSE DED P AGE S.

Those responsible for maintaining this publication should ensure that all previous changes have been

received and incorporated.


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iiRev. C

FOREWORD

This ma nua l provides informa tion intended for use by persons wh o, pursua nt to current regulat ory

requirements, are qua lified to install this equipment. B eca use insta llations vary depending on a pa rticulara ircraft, t his ma nua l is intended a s a guideline. If further informa tion is required, conta ct:

Goodrich Avionics SystemsAttn: Customer Service5353 52nd Street, S.E.

Grand Rapids, MI USA 49512Tel. (800) 453-0288 or (616) 949-6600

We welcome your comments concernin g t his ma nua l. Although every effort ha s been ma de to keep it free of

errors, some ma y occur. When report ing a specific problem, plea se describe it briefly a nd include t he

ma nua l part number, the pa ra gra ph/figure/ta ble number, a nd t he page number. Send your comments to:

Goodrich Avionics SystemsAttn: Technical Publications

5353 52nd Street, S.E.Grand Rapids, MI USA 49512

REVISION C HIGHLIGHTS

Revision C is a republica tion. This r epublicat ion completely r eplaces the existing book. It incorpora tes t hebasic ma nua l and a ll previous changes. New a nd revised ma terial ha s been a dded. Discar d previous

editions of the old publica tion.

This r evision w ill be kept curr ent by chan ge notices. As you receive chan ge notices, repla ce cha nged pa ges

w ith t he corresponding num bered page. A new list of effective pa ges will be issued wit h ea ch cha nge. The

list sha ll reflect the current cha nges in a ddition to the ta bulation of all previous chan ges, thus providing a

complete history of th e ma nua l.


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iiiRev. C

TABLE OF CONTENTS

P a ra gra ph P a ge

Cha pter 1

G ENE RAL INFORMATION

1.1 INTRODU CTION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .1-1

1.2 FU NCTIONAL DE SC RIP TION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..1-2

1.3 P HYS IC AL DE SC RIP TION ...........................................................................................................1-3

1.3.1 Displa y/P rocessor ............................................................................................................................1-3

1.3.2 Ant enna ..........................................................................................................................................1-4

1.4 SPECIFICATIONS..........................................................................................................................1-5

1.5 INTER FACE ....................................................................................................................................1-6

1.6 EQU IP MENT REQU IRED NOT SUP P LIED ... . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. .1-6

1.7 INSTALLATION AP P ROVAL ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . ..1-6

1.8 WARRANTY INF ORMATION .......................................................................................................1-6

1.8.1 Wa rra nt y St a tement .......................................................................................................................1-6

1.8.2 Relat ed P olicies a nd P rocedures .....................................................................................................1-7

Cha pter 2

INSTALLATION

2.1 INTRODUCTION............................................................................................................................2-1

2.2 U NP ACK ING AND INS P EC TING ................................................................................................2-1

2.3 P RE-INSTALLATION TES T P ROCE DU RE ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..2-1

2.3.1 Eq uipment Requir ed .......................................................................................................................2-1

2.3.2 Test P rocedure .................................................................................................................................2-2

2.4 ANTEN NA LOC ATION ..................................................................................................................2-3

2.4.1 In ter ference S ources.......... .................. ................. .................. ................. ................. ................. ......2-4

2.4.2 Skin Cur rent ....................................................................................................................................2-4

2.4.3 Skinm a pping....................................................................................................................................2-4

2.4.4 G round P la ne...................................................................................................................................2-42.4.5 Alignment .....................................................................................................................................2-5

2.4.6 Slipst rea m .....................................................................................................................................2-5

2.4.7 Sit e Selection ...................................................................................................................................2-5

2.5 ANTENNA AND DOU BL ER INSTALLATION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .2-6

2.6 DIS P LAY/P ROCE SS OR LOCATION... . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .2-8

2.7 CABLE REQU IRE MENTS AND FABRIC ATION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .2-8

2.7.1 Ant enna Ca ble ..............................................................................................................................2-11

2.7.2 P ower Ca ble ...................................................................................................................................2-12

2.7.3 Hea ding Input Ca ble .....................................................................................................................2-12

2.7.4 Inh ibit Line ...................................................................................................................................2-15

2.7.5 Remote Clea r Line.........................................................................................................................2-15

2.8 MATING CONNE CTOR ASSE MBL Y ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..2-16

2.9 DIS P LAY/P ROCE SS OR INSTALLATION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .2-202.10 P ER FORM ANCE TES T................................................................................................................2-21


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ivRev. C

TABLE OF CONTENTS

P a ra gra ph P a ge

Cha pter 3

INSTALLATION CH EC KOU T

3.1 INTRODU CTION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .3-1

3.2 CONTROLS ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..3-1

3.3 P OST-INSTALLATION CH EC KOU T.... . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .3-2

Cha pter 4

MAINTENANCE

4.1 INTRODU CTION ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .4-1

4.2 CONTINU ED AIRWORTHI NES S.. . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .4-1

4.3 P ERI ODIC MAINTENANCE ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..4-1

4.3.1 Displa y/P rocessor ............................................................................................................................4-1

4.3.2 Ant enna ...........................................................................................................................................4-1

4.4 SE RVICE MENU ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .4-2

4.4.1 Sy stem Da ta ....................................................................................................................................4-24.4.2 Fa ult Log ......................................................................................................................................... 4-4

4.4.3 CR T Test P a tt ern ............................................................................................................................4-5

4.4.4 Noise Monitor ..................................................................................................................................4-6

4.5 FAU LT IS OLATION ................ .................. .................. .................. .................. ................... ............ 4-8

4.6 TROU B LE SH OOTING EL EC TRIC AL NOIS E .......................................................................... 4-12

4.7 FU SE RE P LACEME NT ............................................................................................................... 4-13

4.8 RETUR N TO SER VICE CH EC K ... .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. 4-14

4.9 DI SP OSI TION OF FAILE D ITEMS ............................................................................................ 4-14

Appendix A

WX-950 INTER FACE SI G NAL & CABL E CH ARACTER IS TIC SINTROD U CTION ....................................................................................................................................... A-1

SI G NAL CH ARACTER IS TIC S .................................................................................................................. A-1


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vRev. C

LIST OF ILLUSTRATIONS

Figure P a ge

1-1 Syst em Functiona l Diagr a m... . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..1-2

1-2 Displa y/P rocessor Un it (P/N 805-10950-001/002)........................................................................1-3

1-3 NY-163 Ant enna (P /N 805-10930-001/002) ..................................................................................1-41-4 Ant enna Doubler P la te (P /N 78-8060-5959-2)..............................................................................1-4

2-1 Test Ca ble.. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . . .. . . .. . . .. . . .. . . .. . .2-2

2-2 Test Set up.......................................................................................................................................2-2

2-3 Antenna Mounting Holes.. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .2-6

2-4 Antenna a nd Doubler Insta llation .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .2-7

2-5 Int erconnect Wiring .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .2-9

2-6 Antenna Ca ble... . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .2-11

2-7 Antenna Ca ble Prepar a tion.. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..2-11

2-8 Hea ding Input Ca ble.. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .2-13

2-9 Hea ding Input Ca ble P repara tion... . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..2-14

2-10 Ma tin g Connector.........................................................................................................................2-16

2-11 Hea ding Fla g (KC S55) Connection .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..2-292-12 Inst rument P a nel Cut out a nd Mounting Holes .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..2-20

2-13 Display/P rocessor Insta llation .. . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .2-21

3-1 Controls . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .3-1

3-2 Self-Test in P rogress .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .3-2

3-3 Self-Test P a ssed .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..3-2

3-4 Recoverable Er ror Message .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .3-3

3-5 Fa ta l E rror Messa ge .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .3-3

3-6 360 Weat her View a t 200 nmi Ra nge .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .3-4

3-7 Aircraft Test Setup.. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..3-5

3-8 WX-P A Antenna Alignment .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .3-6

4-1 Service Menu.. . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .4-2

4-2 Syst em Da ta , P a ge 1.. . . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..4-3

4-3 Syst em Da ta , P a ge 2.. . . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..4-4

4-4 Syst em Da ta , P a ge 3.. . . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . ..4-4

4-5 Fa ult Log .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .4-5

4-6 CRT Test P a tt ern .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .4-6

4-7 Noise Monitor . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . . .. . . . .. . . .. . . .. . . .. . . ..4-6

4-8 Test St rikes .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .4-7

4-9 Repla cing the Fuse.. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .4-13


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viRev. C

List of Tables

Ta ble P a ge

1-1 WX-950 Syst em P ar t Numbers .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .1-1

1-2 Antenna C a ble P a rt Numbers.. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .1-1

1-3 WX-950 Inst a llation Kit P /N 817-10950-001 .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .. . . ..1-11-4 Ha rdw a re P a cka ge P /N 817-10951-001.. . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .. . .. . . .. . . .. . . .. . . .1-1

2-1 Hea ding Input Cable Vendors .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. 2-13

2-2 St epper Input Connections (KI-525 Indicat or) . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .2-14

2-3 Syn chro Connections to Mat ing Connectors . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .2-15

2-4 Antenna Ca ble Connections.. . . . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. 2-16

2-5 Hea ding Input C onnections .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .. . . .. 2-17

2-6 Configurat ion J umpers .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . .2-17

2-7 J umper Configurat ion Resistance .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .2-18

4-1 Er ror Messages .. . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. . . .. .4-9


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1-1Rev. C

CHAPTER 1GENERAL INFORMATION

1.1 INTRODUCTION

This section cont a ins a functiona l description of th e St ormscope model WX-950 Series II w eat her

ma pping syst em, outlines the ma in featur es of the syst em, an d provides a functiona l block diagra m. The

basic WX-950 System (see table 1-1) consists of the following equipment:

D ispla y/P rocessor P /N 805-10950-001 (B la ck B ezel) or P /N 805-10950-002 (G ra y B ezel)

NY-163 Ant enn a P /N 805-10930-001 (Whi te) or P /N 805-10930-002 (B la ck)

In st a lla tion Kit P /N 817-10950-001

Antenna Ca ble (ordered sepa ra tely). Antenna cables, w ith t he an tenna connector pre-w ired to

one end, a re a va ilable in 6, 12, 25, 50 a nd 75 ft. length s (see ta ble 1-2). To meet different spa ce

requirements t he ant enna connector can be ordered with either a stra ight or right-a ngle

backshell. Most insta llations w ill require the right -a ngle backshell.

Components supplied with the installation kit are identified in tables 1-3 and 1-4.

Table 1-1. WX-950 System Part Numbers

BEZEL ANTENNA

SYSTEM P/N BLACK GRAY WHITE BLACK

830-10950-001 X X

830-10950-002 X X

830-10950-003 X X

830-10950-004 X X

Table 1-2. Antenna Cable Part Numbers

PART NUMBER

LENGTH

(ft.)

RIGHT-ANGLE

BACKSHELL

STRAIGHT

BACKSHELL

6 803-10950-004 803-10952-004

12 803-10950-005 803-10952-005

25 803-10950-001 803-10952-001

50 803-10950-002 803-10952-002

75 803-10950-003 803-10952-003

Table 1-3. WX-950 Installation Kit P/N 817-10950-001

QUANTITY PART NUMBER DESCRIPTION

1 78-8060-5979-2 Antenna Doubler Plate

1 78-8060-5977-6 Antenna Gasket

1 817-10951-001 Hardware Package (see table 1-4)

Table 1-4. Hardware Package P/N 817-10951-001

QUANTITY PART NUMBER DESCRIPTION

1 814-10956-001 Rear Cable Connector Assembly

1 814-10959-001 Connector Shell Assembly

1 78-8060-5733-3 Circuit Breaker Label

1 606-10010-001 Cable Clamp, 7/161 606-10009-001 Cable Clamp, 3/8

2 606-10012-001 Cable Tie, 5-5/8

2 101-10091-001 Brass Locking Terminal

4 100-10075-001 Screw, 6-32 x 1/2 PP SS Black Oxide UNC-2A

3 101-10098-001 Stop Nut, Elastic 10-32 S.S.

2 26-1004-1394-2 Washer, .2 ID x .325 OD S.S.

3 26-1004-9316-7 Stop Nut, Elastic 4-40

2 26-1004-9152-6 Screw, 10-32 x 1 1/2 PPH S.S.

2 26-1010-0057-3 Screw, 10-32 x 3/8 TRUS PH S.S.


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1-2Rev. C

1.2 FUNCTIONAL DESCRIPTION

The WX-950 is a TSO cert ified thu nderst orm ma pping syst em designed for a irborne use. The syst em ma ps

electrical discharge activity 360 degrees around the aircraft to a distance of 200 nautical miles. Figure 1-1

is a simplified functiona l diagra m t ha t shows how th e components a re connected to each other an d to other

aircraf t syst ems.

Figure 1-1. System Functional Diagram

The WX-950 is a passive system that listens for electromagnetic signals with a receiving antenna. The

a nt enna detects int ra -cloud, int er-cloud, or cloud-to-ground electr ical discha rges w ith in a 200-nmi r a dius of

th e aircra ft a nd sends t he resulting d ischar ge signa ls to the display /processor. The processor digit izes,

a na lyzes, an d converts t he discha rge signals into ran ge and bear ing dat a. This informa tion is stored in the

storm bu ffer. The display shows d ischar ges as cell or st rikes depending on t he display mode selected.

To maintain proper storm display orientation during turns, the WX-950 can be connected to an externalhea ding source. The hea ding source ma y be syn chro XYZ or st epper (King K CS 55) forma t.


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1-3Rev. C

1.3 PHYSICAL DESCRIPTION

The WX-950 S ys t em consis t s of tw o ma in compon ent s; D ispla y/P rocessor (P/N 805-10950-001/002) a nd NY-

163 Ant enna (P /N 805-10930-001/002).

1.3.1 Display/Processor

The displa y/processor (see figure 1-2) houses th e processing circuitr y a s w ell as th e CR T display pan el a ndth e pilots opera ting cont rols. The D isplay /processor ca n m ount in a 3ATI pa nel cutout from t he front or

rear. No mounting t ra y is required, although a mooring plate ma y be purcha sed for increa sed sta bility in

high-vibration environments. Refer to paragraphs 2.6 and 2.9 for guidelines relating to mounting location

an d insta llation. Connection is ma de through a ma ting connector a ssembly (refer to pa ra gra ph 2.8) tha t

attaches to a single 25 pin D-subminiature connector on the back panel.

Figure 1-2. Display/Processor Unit (P/N 805-10950-001/002)


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1-5Rev. C

1.4 SPECIFICATIONS

SIZE:Displa y/P rocessor (including ma ting connector a ssembly)

3.37 inches (8.56 centim eter s) high

3.37 inches (8.56 centimeters) wide

11.33 inches (28.78 cent imet ers) deep

Antenna

1.00 inches (2.54 centim eter s) high

3.45 inches (8.76 centimeters) wide

6.85 inches (17.40 cent imet ers) deep

WEIGHT:D ispla y/P rocessor

2.9 lb (1.3 kg)

Antenna (wit hout doubler)

0.84 lb (0.38 kg)

TEMPERATURE:D ispla y/P rocessor

-20 to + 55 degrees Celsius (-4 to + 131 degrees Fa hrenh eit)Antenna

-55 to + 70 degrees C elsius (-67 to + 158 degrees Fa hrenh eit)

ALTITUDE:D ispla y/P rocessor

35,000 feet (Maximum)

Antenna

55,000 feet (Maximum)

COOLING:Conduction and Forced Air (Internal Fan) Convection

DISPLAY RANGE:25, 50, 100, & 200 nmi

TSO COMPLIANCE:TSO-C110a

RTCA COMPLIANCE:Displa y/P rocessor E nvironment a l

D O-160C Ca teg ory C1-B A(NB M)XXXXXXZ(AB )AB ZTZAZE3XX

Displa y/P rocessor Softw a re

DO-178B Level D

Antenna

D O-160C Ca t egory F 2-AC(YCL M)XSFXXXXXXXZXZXXE3XX

POWER REQUIREMENTS:Input volta ge: 11 to 32 VDC

C ur rent : 2.0 A 0.5 A @ 12 VD C0.8 A 0.25 A @ 28 VDC


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1-6Rev. C

1.5 INTERFACE

The electrical characteristics of all input and output signals are detailed in Appendix A.

1.6 EQUIPMENT REQUIRED NOT SUPPLIED

C ir cuit B rea ker Th e WX-950 is pr ot ect ed via a n in ter na l fuse (see pa r a 4.6). F or ext er na l

circuit brea ker protection, a 5 A circuit brea ker is recommended for 14 Va ircraft systems a nd a 3 A circuit breaker for 28 V systems.

12 to 28 VDC P ower Supply Power supply capable of providing 12 to 28 VDC a t 30 Wat ts is required to

do the pre-installation test procedure.

WX-950 Tes t C a ble Th is ca b le is req uir ed t o d o t h e pr e-in st a l la t i on t es t pr oced ur e. Th e ca b le

can be pur cha sed f rom G oodr ich Avionics S ys tem s (P /N 803-10950-001) or

fa bricat ed from the deta ils provided in figure 2-1.

WX-SM Skinmapper WX-SM Skinmapper (P/N 78-8060-5859-6 wi th Mod . 2 (P/N 816-10012-001)

inst a lled) is required t o verify t he suita bility of a selected WX-950 ant enna

location.

WX-P A P ortable Ana lyzer WX-P A P ortable Ana lyzer Kit (P /N 78-8060-5791-1) is required to do the

post installation checkout.

S ur fa ce P r epa r at ion Alodin e 1001, r eq uir ed for in st a lla t ion of t he Stormscope an ten n a .

Ant enna S ea la nt F or pr essur ized air cra ft , use a sea la nt meet ing the req uirement s of S AE

AMS-S-8802 such a s Fla mema ster C S3204 Cla ss B . For non-pressurized

a ircraft, use a non-corrosive sea lant tha t m eets t he physica l requirements

of MIL -A-46146 such a s G enera l E lectric R TV162.

H ea d in g I n pu t C a ble Th is ca b le pr ov id es a ir cr a ft h ea d in g in for m a t ion t o t h e WX-950. See

para gra ph 2.7.3. for cable specifica tion a nd requirement.

S ynchro Inverter I f 400H z synchro dr ive is not ava ila ble.

1.7 INSTALLATION APPROVAL

The insta llat ion ofStormscope systems, if not insta lled under a type certificate or supplementa l type

certificate, must be treat ed as a ma jor a lterat ion on F.A.A. form 337. Applica tion for a pproval ma y be ma de

a t a ny F.A.A. Air Ca rrier, Genera l Aviat ion, or Flight S ta nda rds district Office.

1.8 WARRANTY INFORMATION

The Stormscope WX-950 Weath er Mapping Syst em is wa rra nted for tw o year s from the da te of

inst a llat ion (not t o exceed 30 mont hs from t he da te of shipment from G oodrich Avionics Syst ems) subject t o

the following limitations.

1.8.1 Warranty Statement

Goodrich Avionics Systems, (hereinafter called Goodrich Avionics Systems), warrants each item of new

equipment ma nufa ctured or sold by G oodrich Avionics Syst ems to be free from defects in ma terial an d

w orkma nship, under norma l use a s intended, for a period of 30 months from da te of shipment by G oodrich

Avionics Sy stems to a n a uthorized fa cility, or 24 months from dat e of insta llation by a n a uthorized fa cility,

whichever occurs first. No claim for breach of warranties will be allowed unless Goodrich Avionics Systems

is notified thereof, in wr iting, wit hin th irty (30) da ys a fter th e mat erial or workman ship defect is found.

The obligation of Goodrich Avionics Systems shall be limited to replacing or repairing at its factory the

equipment found defective under t erms of this wa rra nty certificate; providing tha t such equipment is

returned in a n a pproved shipping conta iner, tra nsporta tion charges prepaid, to G oodrich Avionics Syst ems,

G ra nd Ra pids, Michiga n, or such other loca tion as G oodrich Avionics Sy stems ma y a uthorize. G oodrich

Avionics Systems r eserves the right to ha ve necessary repairs performed by a n a uthorized a gency.


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1-7Rev. C

This wa rra nty sha ll not a pply to any unit or part t hereof which has not been insta lled or ma inta ined in

a ccorda nce wit h G oodrich Avionics Systems instr uctions, or has been repaired or alt ered in a ny w a y so as

to a dversely a ffect it s performa nce or relia bility, or w hich ha s been subjected t o misuse, negligence or

accident.

This w a rra nty is exclusive and is a ccepted by buyer in lieu of a ll other gua ra nties or w a rra nties express orimplied, including with out limita tion the implied wa rra nties of mercha nta bility a nd fitness for a part icular

purpose. Buyer agrees that in no event will Goodrich Avionics Systems liability for all losses from any

cause, whether based in contract, negligence, strict liability, other tort or otherwise, exceed buyers net

purcha se price, nor w ill Goodrich Avionics Syst ems be lia ble for a ny special, incidenta l, consequentia l, or

exemplary damages.

Goodrich Avionics Systems reserves the right to make changes in design or additions to or improvements in

its equipment w ithout t he obligation to insta ll such a dditions or improvement in equipment theretofore

manufactured.

1.8.2 Related Policies and Procedures1. I f the orig inal registered owner of a WX-950 system sel ls the aircraf t in which the system is instal led

during the warranty period, the remaining warranty may be transferred. Written notification of the

tra nsa ction must be submitt ed by the initial recipient of the wa rra nty t o:

ATTE NTIO N: WARRANTY ADMI NI S TRATOR

G oodrich Avionics Sy stems

5353 52nd S tr eet, S.E .

G ra nd Ra pids, MI 49512

U.S.A.

2. Equipment must be insta l led by a G oodrich Avionics Systems authorized dealer or instal ler .

Insta llation of equipment by fa cilities not specifica lly aut horized will void the equipment w ar ra nty .

3. Notice of a claimed product defect must be given to Goodrich Avionics Syst ems or a designat ed

Goodrich Avionics Systems Service Agency within the specified warranty period.

4. A product which is defective in workmanship and /or ma terial sha ll be returned to Goodrich Avionics

Syst ems via an y Authorized D ealer w ith t ra nsporta tion charges prepaid. After correction of such

defects, the equipment will be returned to the Dealer, transportation prepaid by Goodrich Avionics

Syst ems via surfa ce tra nsporta tion. Any other means of tra nsporta tion must be paid by the customer.

The risk of loss or da ma ge to a ll products in t ra nsit sha ll be assum ed by the part y initia ting t he

tra nsporta tion of such products. All items repa ired or r eplace hereunder sha ll be wa rra nted for the

unexpired portion of the origina l wa rra nty .

5. G oodrich Avionics Systems is in no w a y obliga ted or responsible for supporting or part icipating in the

costs of th e insta llation w a rra nty . The entire responsibility lies w ith the G oodrich Avionics S ystems

Authorized Dealer making the installation. Goodrich Avionics Systems is only responsible for theproduct w ar ra nties outlined in para gra ph 1.8.1.

6. G oodrich Avionics Systems cannot a uthorize war rant y credit for t roubleshooting of other systems in

th e air cra ft in order to reduce noise interference wit h t he WX-950 syst em.


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This pa ge intentionally left blank.


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2-1Rev. C

CHAPTER 2

INSTALLATION

2.1 INTRODUCTION

Inst alla tion must be made by qua lified personnel, in conforma nce with a pplica ble government regulat ions.

The informa tion fu rnish ed is for convenience only.

NOTE

Tolerances(unless otherw ise indicat ed):

ANG LE S ARE 1

.00 TWO P LAC E DE C IMALS ARE .02

.000 TH R EE P L AC E D E CI MAL S AR E . 010

This section describes t he inst a llat ion of StormscopeSeries II Model WX-950, in a step by step procedure.

The insta llat ion activit ies in this section will be performed in th e follow ing order:

Det ermine component loca tions. Inst a ll the cables.

Inst a ll the system components.

2.2 UNPACKING AND INSPECTING

CAUTION

The display/processor a nd a nt enna a re sensitive to electr osta tic dischar ge

(ES D) an d ma y be da ma ged if not ha ndled correctly. Do not remove protective

covers fr om electr ical connectors durin g un packing. Touching a n exposed

connector ma y ca use electrosta tic da ma ge to equipment.

Ca refully unpack the syst em an d note any da ma ge to shipping conta iners or equipment. Visually inspect

each component for evidence of damage. Compare the equipment received with that noted on the packing

list. Immediat ely report an y m issing items or evidence of da ma ge to the carr ier m a king the delivery. To

justify a claim, reta in the origina l shipping conta iner and a ll packing mat erials.

Every effort should be ma de to reta in the original shipping conta iners for st orage. If th e original conta iners

ar e not a va ilable, a separ at e ca rdboard conta iner should be prepa red tha t is lar ge enough to accommoda te

sufficient packing ma terial to prevent movement. The a mbient temperatur e of th e storage a rea should not

fall below -55 C (-65 F) or rise above 70 (158 F).

2.3 PRE-INSTALLATION TEST PROCEDURE

G oodrich Avionics Syst ems recommends t esting ea ch display/processor a nd a nt enna immedia tely uponreceipt. The pre-installation test procedure verifies operation of the system and may save valuable

insta llation time by detecting hidden da ma ge that ma y ha ve occurred during shipment.

2.3.1 Equipment Requireda . Sys tem components to be tested.

1). WX-950 Display/P rocessor

2). N Y-163 An ten na

b. DC P ower Supply: 12 to 28 VDC , 30W, or equivalent (not supplied).


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2-2Rev. C

c. WX-950 Test C a ble P/N 803-10951-001. The bench test ca ble may be purchased d irectly from G oodrich

Avionics System, or one ma y be fa brica ted (unterminat ed cable may be purcha sed from Electronic

Ca ble Specia lists - EC S P /N 312207) from th e deta ils provided in figure 2-1.

Figure 2-1 Test Cable

2.3.2 Test Procedure

CAUTION

B efore connecting/disconnecting cables, ensur e th a t a ll pow er is r emoved.

1. Connect the equ ipment as shown in f igure 2-2.

Figure 2-2 Test Setup2. Rotat e the OFF/B RT knob clockw ise a bout 180 degrees. After a pproximat ely 15 seconds, the

initializat ion screen w ill be displa yed. During init ializat ion, t he system r uns a series of self-tests t o

ensure tha t a ll functions ar e opera ting properly. These tests a re designed to check the an tenna ,

processor, an d a ssocia ted ha rdw a re.

3. I f no faults are detected, at completion of the sel f-test an ALL TESTS P ASSE D message wil l be

displayed.


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2-3Rev. C

4. After completion of the self-test, verify tha t t he WX-950 is in the w eat her mapping mode; 200 nmi,

360 view.

5. Verify tha t clockwise rota tion of the OFF/B RT knob increases display bright ness an d counter-

clockwise rota tion decreases brigh tn ess. The screen should be completely da rk w ith th e control fully

count er-clockwise. Adjust to a comforta ble viewing level.

NOTEP a ra gra ph 3.2 conta ins a description of all opera ting contr ols.

6. Veri fy opera t ion of the pushbut tons :

a . P ress sof tkey (A), i.e. , MENU . This should cause the system menu to be displayed with Weather

View m enu item h ighlighted.

b . Pr ess sof tkey (B) , i.e. , 360 . The display should return to the weather mapping mode, 360

Weat her View a t t he 200 nmi ra nge.

c. P ress sof tkey (C), i.e. , down-arrow. The weat her view ra nge should change to 100 nmi.

d . Pr ess sof tkey (D), i.e, up-ar row. The weather view range should return to 200 nmi.

7. I f correct results are obta ined, the system is operating properly. Immediate ly report a ny problems to

our Customer Service Department at 1-800-453-0288 or 1-616-949-6600.

2.4 ANTENNA LOCATION

Because Stormscopewea ther ma pping systems detect electrical discharge a ctivity, a ntenna placement

relative to other a ctive electrica l components is critical. The an tenna must be pla ced a t a location tha t is

free from excessive electr ical int erference. The ideal locat ion va ries from a ircra ft t o aircra ft. To ensur e an

interference-free ant enna location, every a ircraft must be skima pped prior to insta llation of the

Stormscope an tenna . The skinma p must be done with t he engines and a ll electrica l systems operat ing.

Refer t o th e WX-SM Sk inm a pper In st ruct ion Ma nua l (P/N 78-8060-5874-5).

NOTE

TheStormscope requirement for an a ntenna ground plan e and a noise free

environment complicates installation in aircraft with wood, fabric orcomposite constr uction. E a ch a ircraft needs t o be ana lyzed individually for

the best antenna location. Before starting an installation in one of these

types of aircraft, contact Goodrich Avionics Systems Field Service

E ng ineer ing a t (800) 453-0288 or (616) 949-6600.


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2-4Rev. C

2.4.1 Interference Sources

Avoid m ounting the a ntenna near a ctive electrical components wh enever possible. Genera l clear a nce

guidelines are:

St robe lamps a nd power supplies - 5 ft. (1.5 meters)

P itch trim servos and a mplifiers - 3 ft. (1 meter)

Fluorescent lam ps and ballast s - 5 ft. (1.5 meters)

Hea ter ignitors - 5 ft. (1.5 meters) Air condit ioner a nd hea ter blowers - 5 ft. (1.5 meters)

DME /Tra nsponder/TCAS a nt enna s - 4 ft., Minimum (1.2 meters)

Inflight t elephone a ntenna s - 4 ft. (1.2 meters)

VHF comm. a ntenna s - 1 ft. (.3 meters)

ADF a ntenna s - 1 ft. (.3 meters)

Any curr ent-car ryin g cable - 2 ft. (0.6 meters)

Stormscope sensors a re adversely affected by th e build up of sta tic cha rges. Do not mount the a ntenna

near any composite materials (e.g., plastic covers, radomes, fiberglass housings, windows, etc.) as these

devices can build up objectiona ble sta tic char ges.

2.4.2 Skin Current

Avoid mounting t he ant enna in t he ground returncurrent path betw een the batt ery and a l terna tor,

a nd the bat tery a nd blower motors or other heavy

current carr ying equipment. Aircra ft skin currents

ma y cause antenna interference.

ANTENNA

BATTERY

ALTERNATORSKIN CURRENT

2.4.3 Skinmapping

In order to reduce potential interference problems, some of which are evident only during flight, a skinmap

of the aircraft must be performed (with engines and all electrical systems operating) prior to everyinstal lat ion .This procedure will save insta llation time by a voiding the necessity for such things a s a ntenna

relocat ion. A WX-SM Sk inm a pper (Goodrich Avionics Sy st ems P /N 78-8060-5859-6, w ith Mod 2 inst a lled)

must be used t o verify th e suita bility of a selected a ntenna location before proceeding w ith t he insta llation.

This must be done even if all the other placement criteria are met.

2.4.4 Ground Plane

The ant enna must mount in a loca tion with a

minimum of 12 inches (30 cm) continuous

aluminum ground plane in all directions. Avoid

hinge lines, gear doors, and a ccess panels by a t

least 12 inches (30 cm). Do not mount th e an tenn a

on an a ccess panel. ACCESS PANEL

ANTENNA

12" MIN.


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2-5Rev. C

2.4.5 Alignment

The a nt enna need not be centered on the fusela ge

as long a s its longitudina l axis is w ithin 2 degrees

of para llel with the a ircraft longitudinal a xis. The

an tenna should be mounted w ithin 15 degrees of

horizonta l a nd ma y be mounted w ithin 6 inches (15

cm) of a vent ra l f in. The ant enna m a y mount on anupslope not to exceed 15 degrees of horizontal.

15 DEGREES

MAX

HORZ. AXIS

2.4.6 Slipstream

In general, the antenna should mount aft, where

the slipstream boundar y la yer is thick, to reduce

the effects of P-sta tic. Do not m ount the a ntenna

near any composite materials (e.g., plastic covers,

domes) a s th ey can build up st a tic char ges. Top or

bottom mounts provide equal performance.

ALTERNATE

LOCATION

ALTERNATE LOCATION

PREFERRED

LOCATIONS

2.4.7 Site Selection

Select an a ntenna location tha t sa tisfies the criteria outlined in the preceding para gra phs.

The ideal guidelines, of course, ca nnot a lwa ys be met. If the insta llation criteria can not be met, conta ct th e

G oodr ich Avionics S ys tem s C ust omer S ervice D epar tm ent a t 1-800-253-9525 or 1-616-949-6600, for

location a ssista nce.

NOTESince Goodrich Avionics Syst ems ha s no contr ol over a irfra me integrity or a ircraft

configuration, the authorized installer is responsible for insuring a noise free

insta llat ion. If a dditiona l la bor is required to correct a n int erference problem ca used

by another aircraft system or component, Goodrich Avionics Systems will not

reimburse the insta ller for th is labor under wa rra nty . For th is reason, the insta ller

should a nticipa te extra labor when quoting th e installa tion to the customer,

depending upon aircraft type and specific configuration.


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2-6Rev. C

2.5 ANTENNA AND DOUBLER INSTALLATION

Figure 2-3 shows the mounting holes a nd dimensions for the a ntenna a nd doubler plat e.

Figure 2-3. Antenna Mounting Holes

1. Use th e an ten n a d ou bl er pl a te a s a t e m pl a te to m ark h ol e l oca t i on s on th e a i r cr a f t ski n.

NOTE

Ensur e tha t t he location selected a llows a dequat e space inside the fuselage

for the doubler plate to clear ribs and aircraft structure. (It may be

necessa ry t o cut t he doubler pla te to ensure proper fit.)

2. At ta ch the doubler pla te to the inside of the fuselage as shown in f igure 2-4.

3. M ou nt t h e a n t en na t o t h e a i rcr a ft a s sh ow n in fi gu re 2-4.

CAUTION

1. Do not pa int th e ant enna. It ha s been coa ted wit h a special conductive paint t o

inhibit t he build-up of precipita tion-sta tic.

2. Do not over-tight en the a ntenna mounting screw s during inst alla tion on convexsurfaces. Doing so may cause stress cracks and shorten the life of the a ntenna .

3. To ensure a good electrical ground connection (meta l-to-meta l cont a ct) remove thepaint from th e aircra ft skin under the double plat e mounting screws a nd prepa re the

surfa ce with Alodine No. 1001. Fa ilure to provide a good ground connection ma y

affect syst em performa nce.


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2-7Rev. C

Figure 2-4. Antenna and Doubler Installation

4. S ea l a rou nd t he en t ir e per im et er of th e a n t en na .

NOTE

The antenna should not be sealed until the sensor performance tests are complete.


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2-8Rev. C

a. For non-pressurized aircraf t , use a non-corrosive seala nt th at meets the physical requirements

of MIL -A-446146 such a s G enera l E lectric R TV162

b. For pressurized aircraf t , use a sealant tha t meets the requirements of SAE AMS-S-8802 such

as FlamemasterCS3204 class B.

2.6 DISPLAY/PROCESSOR LOCATION

The displa y/processor should be mount ed in a loca tion ea sily a ccessible and clea rly visible to th e pilot. In

selectin g a locat ion, consider the follow ing:

P a nel D ept h Adeq ua t e dept h must be a va ila ble behind t he inst rument pa nel t o a llow for

the display, t he ma ting connector a ssembly, a nd excess display ca ble.

Remember, a s ervice loop is necessar y t o allow a ccess to the displa y

connector w hen removing or inserting it int o the instr ument pa nel.

Cooling While t he displa y ha s no specia l cooling requirement s, it should be mounted

to permit a dequat e air circulation. Allow a t least inch of clea ra nce a bove

a nd below the instrum ent for a ir circulation.

View in g An gle Th e v iew in g a n gle for t he d ispla y is not a cr it ica l fa ct or . Th e m os t fa v or a ble

mounting position w ould be near eye level a nd no more tha n a rms length

from the principal user of the instr ument.

Rea da bilit y The displa y is designed to pr ovide sufficient lumina nce t o be rea da ble in

environments exposed to direct sunlight .

2.7 CABLE REQUIREMENTS AND FABRICATION

NOTES

1. All wiring must be in accordance with industry accepted methods,techniques and practices.

2. The length and routing of the external cables must be carefullystudied and planned before at tempting insta llation of the equipment.

3. U se of an y cable not meeting G oodrich Avionics Syst ems specifica tionsvoids al l wa rrant ies.

4. All system cables are terminated at the mating connector assembly(see pa ra gra ph 2.8).

Appendix A defines the electrical characteristics of all input and output signals and identifies the cable

requir ements for each signa l. Refer t o figure 2-5 for int erconnect w iring informa tion. Wire-ma rking

identification is at the discretion of the installer. The following paragraphs detail specific cable

requirements.


25/65

SENSEANT REF

+12V

X LOOP

-12V

ANT TEST

Y LOOP

ANT COMDRAIN22

GREEN

BLUE

YELLOW

10

11

25

24

13

12

23

ORANGE

RED

BLACKBROWN

18 SOFTKEY E

INHIBIT1

A/C POWER 14-220 AWG

20 AWG

20

7

21

8

WHITE

BLUE

ORANGE

BLUE

WHITE

BLUE

WHITE

BLUE

ORANGE

WHITE

19

16

3

6

17

4

5

SYNC_REF_HI

SYNC_REF_LO

HDG FLAG -

SYNC_X

SYNC_Z

HDG FLAG +

SYNC_Y

OPTIONAL

REMOTE CLEAR

1N4448

TO

WX-950 BACKSHELLCONNECTOR BOARD

(SEE FIGURE 2-9)

CABLE BFG P/N 803

GNDCASE

J1

AIRFRAMEGROUND

A/C GROUN

LIN

2

14

FUTURE USE 1

FUTURE USE 2

CONFIG. JUMPER

N/C

N/C

N/C

(NOT SUPPLIED - SEE NOTE 2)CIRCUIT BREAKER

HEADING IPARAGRAP

HP

CASEGND

DRIVE MOTOR 1

HDG FLAG +

HDG FLAG -

DRIVE MOTOR 3

UNREG +15

5

4

17

6

3

16

19

WHITE

BLUE

WHITE

ORANGE

BLUE

WHITE

BLUE

ORANGE

BLUE

WHITE

CASEGND

FUTURE USE 315 N/C

GNDCASE

9

20 AWG

20 AWG

AIRFRAMEGROUND

SEE NOTE 3

SEE NOTE 4

INTERNAL

SHIELD (FOIL)

EXTERNAL

SHIELD (BRAID)

SEE

NOTE 5

NORMALLY THE INHIBIT LINE IS NOT NEEDED IFTHESTORMSCOPE ANTENNA ANDTHE COMMUNICATIONSANTENNAS ARE ON OPPOSITE SIDES OFTHE AIRCRAFTFUSELAGE.IF THE INHIBIT LINE IS CONNECTED TO MULTIPLEMICROPHONE SWITCH LINES, EXTERNAL ISOLATION DIODESMUST BE INSTALLED BETWEEN THE SWITCH LINES ASSHOWN.

THE WX-950 IS PROTECTED VIA AN INTERNAL FUSE (SEE

PARA 4.7). FOR EXTERNAL CIRCUIT BREAKER PROTECTION,A 5 A CIRCUIT BREAKER IS RECOMMENDED FOR 14 VAIRCRAFT SYSTEMS AND A 3 A CIRCUIT BREAKER FOR 28 VSYSTEMS.

THE SECOND SHIELDED PAIR CABLE (CONNECTED TO PINS20 AND 21) IS NECESSARY ONLY IF POWER CABLE LENGTH ISGREATER THAN 15 FEET.

OPTIONAL REMOTE CLEAR SWITCH PROVIDES THE SAMEFUNCTION AS SOFTKEY B.

INTERNAL AND EXTERNAL SHIELDS ARE ISOLATED FROMEACH OTHER. DO NOT CONNECT THESE SHIELDSTOGETHER.

1.

2.

3.

4.

5.

NOTES


26/65


2-11Rev. C

2.7.1 Antenna CableAntenna cables, with the antenna connector pre-wired to one end, are available in 6, 12, 25, 50 and 75 ft.

lengths (see ta ble 1-2). To meet d ifferent spa ce requir ements t he a nt enna connector can be ordered w ith

either a straight or right-angle backshell (see figure 2-6). Most installations will require the right-angle

backshell. Cut cable to the desired length a nd prepare in a ccorda nce with t he guidelines shown in

figure 2-7.

Figure 2-6. Antenna Cable

Figure 2-7. Antenna Cable Preparation

The a nt enna cable ma y be susceptible to interference from outside sources a nd rout ing is subject t o the

follow ing guidelines.

Ca ble routing should be kept a s short a nd direct a s practical.

The cable should not be bundled w ith a ny other a ircraft cable except for short dista nces, a nd

then only w hen a bsolutely necessary.


27/65


2-12Rev. C

To prevent undo stra in on the shield ground w ire, when t he an tenna is top-mounted, clamp t hea ntenna cable to the a irfram e no further t ha n one foot (1 ft.) from t he an tenna connector.

If t he an tenna cable routes th rough a bulkhead connector, a dedicated connector must be used.

(The an tenna cable must not sha re a bulkhea d connector w ith a ny other conductors).

The an tenna cable may tie to other electrical cables at right a ngles.

The ant enna ca ble overall shield is termina ted a t t he ant enna end only

Refer to para gra ph 2.5 for a ntenna a nd doubler insta llation.

2.7.2 Power CableThe pow er cable (not supplied) run s from the ma tin g connector to the a ircra ft circuit brea ker pan el. For t he

pow er cable, use tw isted sh ielded pa ir, #20 AWG . The positive w ire connects t o the a vionics circuit brea ker.

The nega tive wire connects t o a irfra me ground. If a irfra me ground is not ava ilable, run a separa te wire to

power ground at the batt ery.

CAUTION

Reversing the power leads will cause an internal fuse to blow. Fuse

replacement procedures are detailed in chapter 4.

P ower ca ble routing is generally not critica l to system operat ion. Ca ble lengths great er tha n 15 feet r equire

a second shielded tw isted pa ir (to reduce the volta ge drop) connected t o pins 20 and 21 (refer t o figure 2-5).

Affix a circuit brea ker la bel (P /N 78-8060-5733-3, provided w ith th e ha rdw a re pa ckage) to t he circuit

breaker pan el.

2.7.3 Heading Input CableThe hea ding input cable connects t he WX-950 processor to t he a ircra ft h eadin g sy stem. This ca ble provides

XYZ a nd H C a ircra ft hea ding informa tion (or King KC S55 stepper signa ls) to th e WX-950 processor. FLAG

lines ar e also included in th e headin g input cable to provide the WX-950 processor w ith flag sta tus (or

heading va lid) informa tion.

NOTE

U se of a ny ca ble not m eetin g G oodrich Avionics Sys tems specificat ions voids all

w ar ra nties, and ma y be cause for termina tion of Authorized Insta ller sta tus.

Ta ble 2-1 lists some U .S. vendors w ho sell the requ ired cable by th e foot.

The synchro cable consists of the following (refer to figure 2-8):

1. Tw i st ed , S h ield ed , J a cket ed Tr ia d #24 AWG

Colors: White , Blue, Ora nge

Shield: Tin Pla ted Copper Bra id, 90%min.

J a cket: FE P .007 in. min., White

2. Tw is ted , S hield ed , J a cket ed P a ir #24 AWG

Colors: White , Blue

Shield: Tin P lat ed Copper B ra id, 90%min.

J a cket: FE P .007 in. min., B lue

3. S a me a s I tem 2, except Or a nge ja cket .

4. Aluminized Myla r Wra p.

5. #34 AWG bra ided shield .

6. FE P Teflon jacket .013 in. - .023 in., clear (translucent).

7. Ma rker ta pe w it h vendor P /N.


28/65


2-13Rev. C

Table 2-1. Heading Input Cable Vendors

US

COMPANY

CABLE

P/N

Dallas Avionics

1-800-527-2581

214-320-9776FAX 214-320-1057

Electronic Cable

Specialists

414-421-5300

FAX 414-421-5301

A.E. Petsche

1-800-777-9280

817-461-9473

FAX 817-277-2887

EDMO Distributors

1-800-235-3300

509-535-8280FAX 1-800-828-0623

FAX 509-535-8266

PIC Wire and Cable

1-800-742-3191

414-246-0500

FAX 414-246-0450

WX-5

(6.84 lbs/

100 ft)

3N6607

(7.5 lbs/

100 ft)

TZGYR

(6.84 lbs/

100 ft)

WX-1000

SYNCHRO

WM25807

(7.2 lbs/

100 ft)

Figure 2-8. Heading Input Cable


29/65


2-14Rev. C

The sub-cable color-coded jackets and shields should be left on the sub-cables as close to the connector as

practical to provide the required shielding and to identify the sub-cables. Guidelines for preparing the cable

for connection t o the WX-950 ma ting connector (see pa ra gra ph 2-8) a re show n in figure 2-9. Gr ound t he

overa ll shield at both ends. The WX-950 End sh ould be grounded w ithin th e ma ting connector assembly.

G round the sub-cable shields only at the ma ting connector subassembly. Ca ble routing an d length a re not

critical to syst em operat ion.

Figure 2-9. Heading Input Cable Preparation

Ta bles 2-2 and 2-3 provide head ing source interconnect informa tion. Refer to th e applicable ma nufa cturers

publica tion for specific interconnect guidelines t o be follow ed.

NOTE

Every effort ha s been ma de to correctly identify t he pin numbers a nd signa l na mes used

by t he var ious ma nufa cturers. However, Goodrich Avionics Systems ca nnot be

responsible for cha nges ma de by others. Please consult t he a ppropria te ma nufa cturers

documenta tion for t he lat est informa tion.

Table 2-2. Stepper Input Connections

(KI-525 Indicator)

WIRE COLOR BACKSHELL KI-525

SIGNAL SUB-CABLE WIRE PIN NUMBER INDICATOR

WHITE WHITE 5 N/C

WHITE BLUE 4 N/C

DRIVE MOTOR 1 WHITE ORANGE 17 P2-A (BOTTOM)

HDG FLAG + ORANGE WHITE 6 FLAG +

HDG FLAG - ORANGE BLUE 19 FLAG -

UNREG +15 BLUE WHITE 16 P1-v (TOP)

DRIVE MOTOR 3 BLUE BLUE 3 P2-H (BOTTOM)

SIGNAL GND* GROUND P1- j (TOP)

*Connect outer shield at KI-525, P1- j (TOP)


30/65


2-15Rev. C

Table 2-3 Synchro Connections to Mating Connector

SYNCHRO CONNECTION TO WX-950 MATING CONNECTOR BACKSHELL

SIGNAL HDG

FLAG +

HDG

FLAG -

SYNC

X

SYNC

Y

SYNC

Z

SYNC

REF HI

SYNC

REF LO

PIN 6 19 5 17 4 16 3

SUB-CABLE ORANGE ORANGE WHITE WHITE WHITE BLUE BLUE

WIRE COLOR WHITE BLUE WHITE ORANGE BLUE WHITE BLUE

Cessna ARC 200-9BC N/A N/A A E D C B

Cessna ARC 40840-0204 N/A N/A N M L B L

Cessna Slaved DG N/A N/A E D A C B

AIM Type 289-1-2 N/A N/A E D A H C

AIM Type 2892D N/A N/A M N K L K

AIM Type 2892ED N/A N/A M N K L K

Collins Type 331P-1V N/A N/A N M D B L

Collins Type 331P-1 N/A N/A N M D B L

Century NSD360 DG & 722/755 N/A N/A 1* 2* 3* 7* 5*

Century NSD360A DG & 722/755 36 1 1* 2* 3* 7* 5*

Century Slaved DG N/A N/A N M L B L

King KCS-55 w/KI-525A-01 N/A N/A P2-s P2-v P2-t P2-r P2-u

King KCS-55A w/KI-525A-01 P1-v P2-P P2-s P2-v P2-t P2-r P2-uSperry C6E, C6J N/A N/A 39 38 40 37 36

Sperry C6, C6A, C6C N/A N/A 18 19 20 21 41

Sperry C-14d e GND a b Z X Y

*Connections to 722/755.

2.7.4 Inhibit LineNOTE

Normally the inhibit line is not needed if the Stormscope an tenna and

communications antennas are mounted on opposite sides of the fuselage.

The inhibit line is #22 AWG unsh ielded, a nd n eed be connected only if commun icat ion tra nsmit ters

interfere w ith t he WX-950 when in t he wea th er ma pping mode. This line ca n be included in t he

insta llation, but need be connected only if the testing of the final insta llation indica tes tr an smitt er

interference. Inh ibit line routing a nd length is not critical to syst em operat ion.

2.7.5 Remote Clear LineWhen activated, the remote clear switch performs the same function as the lower left softkey. The remote

clea r line is #22 AWG unsh ielded. Remote clear line routin g a nd lengt h a re not critical t o system opera tion,

nor is the location of the a irfra me ground point a t w hich the remote clea r sw itch termina tes.


31/65


2-16Rev. C

2.8 MATING CONNECTOR ASSEMBLY

All syst em cables a re term ina ted a t t he ma tin g connector a ssembly (see figure 2-10). This connector

a ssembly a lso conta ins jumpers to select syst em configur a tion. The locking mecha nism ha s been designed

to a llow blind ma ting to t he 25-pin D -sub-minia tur e connector on th e back pa nel of the displa y/processor.

Figure 2-10 Mating Connector

When t ermina tin g w ires observe specified color d esigna tions. Tie points a re identified on t he cable

termina tion PC B . If necessary, t his P CB can be removed to simply ma king the solder connections. After th e

wiring connections have been completed, use the interconnect diagram to verify continuity between each

pin and its opposite end termination. Tables 2-4 and 2-5 provides this information for the antenna and

heading inputs.

Table 2-4. Antenna Cable Connections

CONNECTOR PIN NUMBER

SIGNAL WIRE COLOR BACKSHELL ANTENNA

XLOOP ORANGE 24 C

+12V RED 12 D

SENSE BROWN 13 B

ANTREF BLACK 23 J

-12 YELLOW 11 F

YLOOP GREEN 25 G

ANTTEST BLUE 10 H

ANTCOM DRAIN 22 A


32/65


2-17Rev. C

Table 2-5. Heading Input Connections

SYNCHRO STEPPER WIRE COLOR BACKSHELL

INPUT INPUT SUB-CABLE WIRE PIN NUMBER

SYNC-X WHITE WHITE 5

SYNC-Z WHITE BLUE 4

SYNC-Y DRIVE MOTOR 1 WHITE ORANGE 17

HDG FLAG + HDG FLAG + ORANGE WHITE 6

HDG FLAG - HDG FLAG - ORANGE BLUE 19

SYNC REF HI UNREG +15 BLUE WHITE 16

SYNC REF LO DRIVE MOTOR 3 BLUE BLUE 3

Ca bles termina ting a t ma ting connector must be secured wit h a cable clam p at ta ched to one of the

mounting studs (see figure 2-10). Shields terminating at the mating connector can be attached to one of the

unused mounting studs wit h a locking termina l. Secure the cable cla mp a nd locking termina ls w ith 10-32

stop nuts. Tie wra ps, ca ble clam ps, locking termina ls, and stop nuts a re supplied with the ha rdw a re

pa ckag e (see ta ble 1-2).

Option J umpers, a s shown in figur e 2-10, ar e inst a lled on th e mat ing connector as sembly. The jumpers,(22 AWG bus w ire) a re cut, a s deta iled in ta ble 2-6, to ena ble/disa ble the different configura tions. J umper

configura tion can be verified w ith a resista nce check betw een pins 9 (CON FIG J U MP ER ) a nd 11 (-12V).

Simply compare the resistance measured between pins 9 and 11 with that shown in table 2-7. Table 2-7

lists th e resistance va lue identified wit h ea ch jumper configura tion.

Table 2-6. Configuration Jumpers

J U MP E R FU NC TION C U T J U MP E R

T/B ANTENNA LOCATION TOP YE S

ANTENNA LOCATION B OTTOM NO

SYNC ENAB LE SYNCH RO H EADING INP U T YE S1

STE P E NAB LE STEP P ING H E ADING INP U T YE S 1

IF NO VALID HEADING INP UT IS AVAILABLE

YE S

FLAG2

IF L OW LEVEL INP UT ON HDG FLAG+ (P IN 6) WITH

RES P EC T TO HD G F LAG - (P IN 19) INDI CATES VALID

HEADING

IF HI GH LEVEL INP UT ON HDG FLAG+ (P IN 6) WITH

RES P EC T TO HD G F LAG - (P IN 19) INDI CATES VALID

HEADING

NO

SP ARE NOT U SED NO

1Only one hea ding input should be ena bled (unless NO HE ADI NG is

connected, then cut neither).2

Figur e 2-11 shows th e WX-950 headin g va lida tion circuit a long w ith a

typical connection of a na vigat iona l system (such a s the King K CS 55) tha t

provides a hea ding va lid signa l to th e WX-950.

The shell an d cable connector suba ssemblies ar e joined w ith tw o 4-40 stop nut s (provided wit h t he

hardware package, see table 1-2).


33/65


2-18Rev. C

Table 2-7. Jumper Configuration Resistance Check

RESISTANCE J UMP ER - CU T (C) or NOT CU T (NC)

(k-OH M 1%) T/B SYNC STEP FLAG SP ARE

5.17 NC NC NC NC NC

5.34 NC NC NC NC C

5.52 NC C NC NC NC5.72 NC C NC NC C

5.93 NC NC C NC NC

6.16 NC NC C NC C

6.97 NC NC NC C NC

7.28 NC NC NC C C

7.63 NC C NC C NC

8.01 NC C NC C C

8.43 NC NC C C NC

8.90 NC NC C C C

10.7 C NC NC NC NC

11.5 C NC NC NC C

12.3 C C NC NC NC

13.4 C C NC NC C

14.6 C NC C NC NC16.0 C NC C NC C

23.0 C NC NC C NC

26.8 C NC NC C C

32.2 C C NC C NC

40.2 C C NC C C

53.8 C NC C C NC

80.6 C NC C C C

NOTE

RES ISTANCE MEASU RED B ETWEE N P INS 9 AND 11 WITH MATING

CONNE CTOR REMOVED FROM DIS P LAY/P ROCE SS OR.


34/65


2-19Rev. C

Figure 2-11. Heading Flag (KCS55) Connection


35/65


2-20Rev. C

2.9 DISPLAY/PROCESSOR INSTALLATION

The display /processor is designed t o mount into a sta nda rd 3 ATI inst rum ent pa nel cutout. The inst rum ent

pan el cutout a nd mount ing holes are shown in figure 2-12.

Figure 2-12. Instrument Panel Cutout and Mounting Holes

G oodrich Avionics S yst ems r ecommends fr ont-mountin g t he displa y/processor using 6-32 rivet-nut s t o

secure the unit to the instr ument pa nel. For increased sta bility, in h igh-vibrat ion environments, t he

display /processor ca n be secured t o the inst rum ent pan el wit h a mooring plat e (see figure 2-13). A mooringplate w ill accommodat e mounting t o the instrument pa nel from t he front or from the rea r.

A mooring plat e ca n be ordered from G oodrich Avionics Sys tems.

P /N 78-8060-5856-2

3ATI mooring plates are also available from:

MSP , Incorpora ted

P .O. B ox 1196

R.R. 4, Box 383A

Nash ville, India na 47448

(812) 988-6623 FAX (812) 988-6181


36/65


2-21Rev. C

Figure 2-13. Display/Processor Installation

The mating connector assembly has been designed for easy blind mating. Simply align the connector

a ssembly w ith t he guide pins a t t he rear of th e displa y/processor a nd slide it in place. Lock by tur ning t he

thumbscrew in a clockwise direction.

2.10 PERFORMANCE TEST

After the installation is completed do the installation checkout procedures detailed in chapter 3.


37/65


2-22Rev. C

This pa ge intentionally left blank.


38/65


3-1Rev. C

CHAPTER 3

INSTALLATION CHECKOUT

3.1 INTRODUCTION

This section conta ins in str uctions for post-inst a llat ion checkout of the WX-950. Complete opera ting

inst ructions for the WX-950 are provided in the P ilots G uide supplied w ith ea ch syst em.

NOTE

The post-installation check procedures in this chapter assume familiarity

with the set-up and operation of the WX-PA Portable Analyzer Kit

(P /N 78-8060-5791-1).

3.2 CONTROLS

All operat ing cont rols ar e locat ed on the front of the indicat or. Figure 3-1 shows t he locat ion of the cont rols.

Figure 3-1. Controls

OF F/B RT

Switch

P ow er is applied by rotat ing the knob clockwise past the detent. C ontinued

clockwise rotation increases display brightness.

A, B, C , & D

Pushbuttons

Also referred t o as softkeys (A), (B ), (C), a nd (D). In every opera ting mode a la bel

identifying the butt on function will be display ed next to the but ton.


39/65


3-2Rev. C

3.3 POST INSTALLATION CHECKOUT

This procedure w ill valida te t he inst a llat ion an d ret urn to service of the WX-950.

1. Rotat e the OFF/B RT knob clockw ise a bout 180 degrees. After a pproximat ely 15 seconds, the

initialization screen (see figure 3-2) will be displayed. During initialization, the system runs a series of

self-tests to ensure that all functions are operating properly. These tests are designed to check the

antenna, processor, and associated hardware.

Figure 3-2. Self-Test in Progress

2. I f no faults are detected, at completion of the sel f-test an ALL TESTS P ASSE D message wil l be

displayed (see figure 3-3). Proceed to step 4.

Figure 3-3. Self-Test Passed


40/65


3-3Rev. C

3. I f a fault is detected, an error message wil l be displayed indicat ing which test fai led and w hich

functions may be inoperative.

a . I f con t inued opera t ion is poss ib le, the message Press any key to continue will appear (see

figure 3-4). To continue operation, press any key.

Figure 3-4. Recoverable Error Message

b. I f a fata l (i .e. , non-recoverable) error is detected, the message Continued operation is not

possible w ill appea r (see figure 3-5). In this circumstan ce, turn the syst em OFF a nd refer to

the ma intenan ce procedures detailed in chapter 4.

Figure 3-5. Fatal Error Message

Ta ble 4-1 lists a ll the possible error messa ges, the probable cau ses, an d t he recommended a ctions.


41/65


3-4Rev. C

4. After completion of the self-test, verify tha t t he WX-950 is in t he wea ther ma pping mode (i.e. , 360

Weat her View a t th e 200 nmi ra nge, see figure 3-6).

Figure 3-6. 360 Weather View at 200 nmi Range

5. Verify tha t clockwise rota tion of the OFF/B RT knob increa ses displa y brightness and counter-

clockwise rota tion decreases brigh tn ess. The screen should be completely da rk w ith th e cont rol fully

count er-clockwise. Adjust to a comforta ble viewing level.

6. Verify opera tion of the pushbuttons (figure 3-1 shows location of softkeys):

a . P ress sof tkey (A), i .e ., MENU. This should cause the system menu to be displayed with Weather

View menu item highlighted.

b . P ress sof tkey (B) , i .e. , 360 . The display should return to the weather mapping mode, 360

Weat her View a t t he 200 nmi ran ge.

c . P ress sof tkey (C), i.e. , down-arrow. The weather view range should change to 100 nmi.

d . P ress sof tkey (D), i.e. , up-arr ow. The weather view range should return to 200 nmi.

7. Access the Service Menu (refer to para gra ph 4.4) a nd verify the informa tion (i.e. , hea ding source,

heading fla g, jumper sense, heading, inhibit line and a ntenna mounting location) identified on S ystem

Da ta P a ge 2 of 3).

NOTE

If stepper heading is used, the heading w ill not agr ee wit h th e HSI. S tepper

heading is rela tive to a ircraft hea ding.

8. From the Service Menu, enter the noise monitor mode.

9. Repeatedly key the aircra f t communicat ions radio microphone:

a. I f keying the tra nsmitter does not cause str ike dat a to appear on the CRT, proceed to step 13.

b . I f s t r ike da ta appears on the CRT when the t ransmi t ter i s keyed , wire the inh ibi t l ine to the

microphone key s w itch (see figur e 2-5).

10. From the Service Menu, access System Da ta P age 2 of 3 and veri fy that when the tra nsmitter is keyed

the sta te of the Inhibit Line tra nsistions from off to on.

11. From the Service Menu, enter th e noise monitor mode.


42/65


3-5Rev. C

12. Repea tedly key the aircra ft communicat ions radio microphone:

a. I f keying the tra nsmitter does not cause str ike dat a to appear on the CRT, proceed to step 13.

b . I f st r ik e d a t a a p pear s on th e C R T wh e n th e t r an sm it t er i s k eyed :

Verify separa tion of the NY-163 and aircra ft communica tion system a ntenna s.

Check the routing of th e stormscope ant enna cable with respect to th e aircra ft

communicat ion system a ntenna cables. Conta ct customer service for a dvice and a ssista nce.

13. To verify ant enna orientat ion and the in tegrity o f the antenna w iring , a a ntenna phase check must be

performed usin g a t lea st t he four ca rdina l head ings (000, 090, 180, an d 270) a nd using t he follow ing

WX-P A ra nges: 120, 75, an d 30 nmi. R efer t o figure 3-7 for t he t est s etup.

Figure 3-7. Aircraft Test Setup

a . C on n ect th e WX-P A cab le to th e WX-P A an ten n a .

b . Refer to f igure 3-8 and posi t ion the WX-P A ant enna on the system ant enna. Make sure the

connection is tight . If necessa ry, us e ta pe to secure the WX-P A a nt enna .


43/65


3-6Rev. C

Figure 3-8. WX-PA Antenna Alignment

c. Secure the WX-PA cab le to the a i rcra f t w i th the a t ta ched suct ion cup and rou te the cab le to the

cockpit.

d . Connect t he remain ing end of the WX-PA an tenna cab le to the WX-PA.

e. P ow er up t he WX-P A.

f . P ower up the WX-950. After completion of the sel f-test , veri fy that the WX-950 is in the weather

ma pping mode (i.e., 360 Weat her View a t th e 200 nmi r a nge, see figure 3-6).

g . Set the WX-950 to the STRIKE display mode; 100 nmi range. To toggle betw een the cel l and

strike modes, press the button labeled CE LL or STRIK E. P ress the a rrow keys to step throughthe operat ing ran ges.

h . Select the Continuous Out mode displayed on the WX-P A menu and press MENU/ENTR.

NOTE

Dur ing cont inuous out put mode, the st rike counter should rea d betw een 560 a nd 600.

i . Select a top mount or a bottom mount a ntenna configurat ion on the WX-P A keyboard (A key),

as appropriate.

j. S elect a c a rd in a l bea r in g a n d a r a n ge of 120 n mi.

k . Use the F1 and F2 keys to ad jus t range and the F3 and F4 keys to ad jus t bear ing .

NOTE

The WX-950 w ill plot da ta a t one-ha lf t he ra nge selected on th e WX-P A.

l. P r es s ME NU /E NTE R to s ta r t t he t es t.

NOTE

Adjustments to ra nge and bearing can be ma de while the test is in progress.


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m. Observe the display to ensure the proper posi t ioning of the test s tr ikes, based on ra nge and

a zimut h sett ings on th e WX-P A. The str ikes should be w ith in 10 degrees of th e selected a zimut h

an d should plot a t 60 nmi ( 120 nmi).

NOTE

THE WX-PA IS U SED ONLY TO CHEC K SYSTEM FU NCTIONS . IT IS NOT CONSIDE RED A

CALIBRATION STANDARD .n . After test ing for al l ranges and bearings indicated, press 2ND, then MENU/ENTER to return to

the Main Menu.

14. To check range an d a zimuth plott ing accuracy set up the WX-P A to simulate a series of strikes at 30

degree increments a t WX-P A ran ges of 120, 55, a nd 15 nmi:

a . Select Circular P at tern mode on the WX-P A Mode Menu and press MENU /ENTR.

b. Select a top mount or a bottom mount a ntenna configurat ion on the WX-PA keyboar d (A key),

as appropriate.

NOTE

The WX-950 display should be set at 100 nmi on the 360 degree weather screen

a nd in st rike display m ode.c. Use the F1 and F2 keys to select a 120 nmi range and press "MENU/ENTR" to s tar t the test .

The system should plot discharge points at approximately 60 nmi.

d . Observe the display t o ensure the proper posi t ioning of the test s tr ikes. The str ikes should be

w ith in 10 degrees of th e 30 degree azimut h increment a nd w ith in 12 naut ical miles (20%) of 60

nmi.

NOTE

THE WX-PA IS U SED ONLY TO CHEC K SYSTEM FU NCTIONS . IT IS NOT CONSIDE RED A

CALIBRATION STANDARD .

e . When complete, set th e WX-P A for 55 nmi, set th e WX-950 displa y for 50 nmi an d repeat t he

test .

1) The System should plot points just outside of the 25 nmi ring .

2) The str ikes should be within 10 degrees of the 30 degree az imuth increment a nd within 5

nmi of 27.5 nmi.

f . Repeat , sett ing the WX-950 display for 25 nmi and the WX-P A for 15 nmi.

g . Again , observe the display to ensure the proper posi t ioning of the test s tr ikes within 10 degrees

of a zimuth a nd w ithin 2 nmi of 7.5 nmi.

15. To test t he synchro functions:

a . Set the WX-950 range to 200 nmi, and use the WX-P A (at any desired range and bearing) to plot

cont inuous discha rge point s on the C RT.

NOTE

Du ring continuous output m ode, the st rike counter should rea d betw een 560 a nd 600.

b . With the compass sys tem turned on , phys ica l ly tu rn the a i rcra f t 45 to the r igh t (or manua l ly

slew t he compa ss clockwise), an d verify t ha t t he previously plotted discha rge points m ove 45

counterclockwise.

16. Test for electrical noise a nd interference by running the noise monitor an d strike test a s deta iled in

paragraph 4.4.4. The noise monitor is accessed from the SERVICE MENU (refer to paragraph 4.4).


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NOTE

This test ma y be performed w ith t he aircra ft in flight or on the ground, as long

as i t is running at h igh RPM w ith a l l systems powered.

An offending int erference source can be isolat ed by shut ting dow n one system a t a time, then clearing

th e display a nd observing t he noise monitor screen. Refer t o troubleshooting electr ical noise,

paragraph, 4.6.17. This completes th e post inst a llation checkout procedure.


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CHAPTER 4

MAINTENANCE

4.1 INTRODUCTION

This cha pter cont a ins genera l flightline ma intena nce procedur es. These procedures a re intend ed to aid in

test ing a complete, interw ired WX-950 system a nd t o isolat e a fa ult t o the display /processor, a nt enna , or

cable.

4.2 CONTINUED AIRWORTHINESS

No scheduled m aint enance is required t o ensure continued a irworthiness.

4.3 PERIODIC MAINTENANCE

NOTE

U pon delivery to a customer, the dea ler should recommend a n a nnua l checkout of t he system,especially prior to the thunderstorm season.

4.3.1 Display/Processor

1. Check tha t cab le i s p roper ly mated and secured .

2. Check to ensure unit is properly placed and secured to the instrument panel.

CAUTION

Do not use clea ning solvents on th e view ing fa ce.

3. Check faceplat e for clean liness. Wipe the viewing fa ce w ith a da mp lint-free, stat ic-free cloth. If

necessary, clean w ith a soft cloth moistened with a mild solution of soa p and wa ter. Ta ke ca re to

prevent cleaning solution from running down inside the case.

4.3.2 Antenna

1. Check for den ts , cracks , and punctures .

CAUTION

Do not paint t he antenna.

Do not use cleaning solvents on t he an tenna .

2. Remove al l d irt a nd grease from surface areas. Clean with a sof t cloth moistened with mild soap and

water .

3. Visual ly inspect sea lan t a round the an tenna base. Reapply sea lan t i f requ ired.


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4.4 SERVICE MENU

The Service Menu is int ended a s a n a id in inst a lling, testin g a nd t roubleshooting th e WX-950. Service

Menu items a re to be used only for t esting a nd t roubleshooting a n inst alla tion. They a re not intended to be

used by the pilot during normal system operation. While in the Service Menu, the internal self-test and

run-time counter are not operational; therefore, any system errors will not be detected or displayed.

The S ervice Menu is a ccessed by h olding softkeys (A) an d (B) (th e left t w o but tons) depressed as t he syst emis tur ned on. Hold the butt ons until t he Service Menu is displa yed. The Service Menu is show n in

figure 4-1.

Figure 4-1. Service Menu

The butt ons perform t he following operat ions in t his mode:

EXIT - causes th e system t o exit the Serv ice Menu an d run t he pow er on self-test . SELECT - selects the highlight ed item.

steps t o the previous item.

steps to the next item.

The Service Menu provides the following choices:

System Dat a

Fa ult Log

CRT Test P at tern

Noise Monitor

The individual menu items a re explained in t he follow ing par a gra phs.

4.4.1 System Data

Sy stem D a ta screens (see figures 4-2 through 4-4) cont a in a record of setup informa tion. If you ha ve

problems with the WX-950, have this information available when contacting Goodrich Avionics Systems

Customer Service. The Customer Service specialist must have adequate information to diagnose a problem.

System Data screens are accessed by selecting that option from the Service Menu (i.e., press SELECTwi th

System Datahigh-light ed). The da ta is upda ted once per second.


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The butt ons perform t he follow ing opera tions in t his mode:

EXIT - ret ur ns t o th e Service Menu (figur e 4-1).

NEXTsteps to the next pa ge. PREVsteps to the previous page. Softkey (B) is not used.

Page 1 identifies (see figure 4-2): System Model (Model)

Main Software Version (Main SW Ver)

Main Boot Software Version (Main Boot SW Ve

wx950 stormscop

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