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no battery contactor?

 
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jd(at)lawsonimaging.ca
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PostPosted: Wed Nov 01, 2006 6:01 am    Post subject: no battery contactor? Reply with quote

Greetings...

I'm just wondering what the justification for eliminating a
battery contactor as per Z17 or Z-20?

Also, if the S700-2-10 split master type switch can be
replaced by a 2-3, per appendix Z, how should it be wired,
exactly?

Thanks...

--
Regards, J.

flying: Zenith STOL CH701/912 C-IGGY, 350 hrs.
building: Sonex #325, Jabiru 3300/6, 85% completed

+-------------------------------------------------------+
| J. Davis, M.Sc. | (computer science) |
| *NIX consulting, SysAdmin | jd at lawsonimaging.ca |
| c/o Brandywine Aviation | voice: 519.289.1527 |
| 5507 Irish Dr., Appin, ON | http://www.cleco.ca |
| N42 47.33 W081 36.50 31/13 | 2000+ x 60', elev: 740' |
+-------------------------------------------------------+

To most people the sky is the limit.
To those who love aviation, the sky is home.

Take charge of your attitude. Don't let someone else choose
it for you.


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nuckollsr(at)cox.net
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PostPosted: Wed Nov 01, 2006 6:46 am    Post subject: no battery contactor? Reply with quote

At 08:59 AM 11/1/2006 -0500, you wrote:

Quote:


Greetings...

I'm just wondering what the justification for eliminating a battery
contactor as per Z17 or Z-20?


The engine drive power sources for a number of small
engines have limited output. The classic battery contactor
implementation consumes 0.7 to 1.0 amps for the
duration of flight. In most cases, there's energy-to-
burn while the main alternator is functioning but
for Rotax and Jabiru engines, this resource is small
(8-18 amps) and a builder may elect to avoid power
losses represented by the installation of a battery
contactor.

Indeed ANY airplane can use a manual switch in lieu
of a contactor . . . but recall that one of the design
goals for a contactor is that when the master switch
is OFF, the amount of hot wiring between battery and
battery switch is minimized.
Quote:
Also, if the S700-2-10 split master type switch can be replaced by a 2-3,
per appendix Z, how should it be wired, exactly?

A 2-3 is not progressive transfer . . . so the battery
and alternator come on and off together. This presents
a problem for conducting battery-only ground ops
where an alternator might come alive even with the engine
not running and load the battery unnecessarily during
ground testing.

If you use a 2-3, the pulling the alternator field
breaker during ground ops takes the place of the
progressive transfer feature of the 2-10 where
the system can be alive on battery only.

Looking at the back of the switch, the 2-3 is
wired just like a 2-10.

Bob . . .


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jd(at)lawsonimaging.ca
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PostPosted: Thu Nov 02, 2006 7:17 am    Post subject: no battery contactor? Reply with quote

Thanks, Bob. Clear, concise and timely, as usual ;')

do not archive
Robert L. Nuckolls, III wrote:
Quote:

<nuckollsr(at)cox.net>

At 08:59 AM 11/1/2006 -0500, you wrote:

>
>
> Greetings...
>
> I'm just wondering what the justification for eliminating a battery
> contactor as per Z17 or Z-20?


The engine drive power sources for a number of small
engines have limited output. The classic battery contactor
implementation consumes 0.7 to 1.0 amps for the
duration of flight. In most cases, there's energy-to-
burn while the main alternator is functioning but
for Rotax and Jabiru engines, this resource is small
(8-18 amps) and a builder may elect to avoid power
losses represented by the installation of a battery
contactor.

Indeed ANY airplane can use a manual switch in lieu
of a contactor . . . but recall that one of the design
goals for a contactor is that when the master switch
is OFF, the amount of hot wiring between battery and
battery switch is minimized.


> Also, if the S700-2-10 split master type switch can be replaced by a
> 2-3, per appendix Z, how should it be wired, exactly?

A 2-3 is not progressive transfer . . . so the battery
and alternator come on and off together. This presents
a problem for conducting battery-only ground ops
where an alternator might come alive even with the engine
not running and load the battery unnecessarily during
ground testing.

If you use a 2-3, the pulling the alternator field
breaker during ground ops takes the place of the
progressive transfer feature of the 2-10 where
the system can be alive on battery only.

Looking at the back of the switch, the 2-3 is
wired just like a 2-10.

Bob . . .







--
Regards, J.

flying: Zenith STOL CH701/912 C-IGGY, 350 hrs.
building: Sonex #325, Jabiru 3300/6, 85% completed

+-------------------------------------------------------+
| J. Davis, M.Sc. | (computer science) |
| *NIX consulting, SysAdmin | jd at lawsonimaging.ca |
| c/o Brandywine Aviation | voice: 519.289.1527 |
| 5507 Irish Dr., Appin, ON | http://www.cleco.ca |
| N42 47.33 W081 36.50 31/13 | 2000+ x 60', elev: 740' |
+-------------------------------------------------------+

To most people the sky is the limit.
To those who love aviation, the sky is home.

Take charge of your attitude. Don't let someone else choose
it for you.


- The Matronics AeroElectric-List Email Forum -
 

Use the List Feature Navigator to browse the many List utilities available such as the Email Subscriptions page, Archive Search & Download, 7-Day Browse, Chat, FAQ, Photoshare, and much more:

http://www.matronics.com/Navigator?AeroElectric-List
Back to top
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