Whelen OR6002G - Manual

Page 1
2.04
White .........+28VDC (ACL)
Orange ......+28VDC (POS)
Yellow........SYNC
Black .........Ground
5.65
1.78
WIRING
1.00
1.70
1.75
2.35
Suggested
Mounting
Pattern
3X Mounting Hole
for #6, 100° c’sink
11” ±1.0”
20 AWG
MIL-22759/34 Wire
®
ENGINEERING COMPANY INC.
51 Winthrop Road
Chester, Connecticut 06412-0684
Phone: (860) 526-9504
Fax: (860) 526-2009
Internet: www.whelen.com
Sales/Service e-mail: [email protected]
Aviation
Installation Guide:
Aviation model(s) OR6002G, OR6002R
P/N 01-0771733-11, 01-0771733-12
Orion 600 Wingtip PTA
©2012 Whelen Engineering Company Inc.
Form No.14661A (042513)
SPECIFICATIONS:
Nominal Operational Voltage:..............................28VDC
(Operational from 22-32VDC)
Input Current:
Position Lights .....................................................0.17 Amps
Anti-Collision Light (Avg.) ....................................0.5 Amps
Anti-Collision Light (Pulse) ..................................2.6 Amps
Flashrate .............................................................45 ± 5 FPM
EQUIPMENT LIMITATIONS:
An approved forward position lighting system consists of two lights, one
located on each wingtip. The baseplate must be mounted parallel to the
vertical and horizontal centerlines of the aircraft to project the patterns
properly.
Certain types of installations may require additional testing.
CONTINUED AIRWORTHINESS:
The forward position light is designed with Green LEDs or Red LEDs.
The tail position light is designed with 2 White LEDs. The anti-collision
light is designed with 24 White LEDs. If any one LED fails, the unit must
be repaired or replaced.
Inspect the lens, replace if there is excessive scratching, pitting,
discoloration or cracking.
Note: To reduce eye strain, use an optical filter such as dark glasses or a
blue covering dome during LED inspection.
INSTALLATION PROCEDURES:
The following information is to assist you in installing a Whelen light
system. The installation procedure described in the following text will be
confined to a single light installation, but is identical for multiple light
installations.
1. Choose the appropriate light assembly.
2. Using the mounting detail information provided, prepare the aircraft
for means to secure the light assembly.
3. Carefully remove the #2 cap head screws and lens retainer.
Remove the lens from the light assembly by lifting the rear of the
lens approximately 1/2”. Now slide the lens rearward approximately
1/2” and lift upwards to remove. CAUTION! Do not touch the LED
lens surface with either fingers or sharp objects. This could
soil and/or damage the lens and affect the optical performance
of the LEDs. Remove the 3 black Phillips head screws securing
the baseplate to the light assembly. Remove baseplate.
4. Using the appropriate hardware install the baseplate to the aircraft.
5. Connect the light inputs according to the chart shown. Connect the
power lead to an appropriately sized breaker. Connections to be
according to FAA approved methods.
Note: SYNC is a low-power, bi-directional control signal.
Connecting to the synchronize signal of any Whelen LED anti-
collision assembly to another Whelen anti-collision assembly will
cause the lights to flash at the same time. If Synchronization is not
necessary, the connection may be left open.
6. Re-install the light assembly on to the baseplate and insure that all
leads are clear of any obstructions and secured as required. Note
that proper orientation is achieved with the drain hole down.
7. Install lens in the reverse order as removal, return the lens
retainer to its installed location, re-insert #2 cap head screw and
tighten firmly. Confirm proper gasket fit.
8. When necessary, waterproof the light base to aircraft. Apply
single-part Silicone (RTV) or equivalent around any open area
where water could get in. Do not cover the drain hole.
9. Check all avionics systems for interference from this installation.
10. A flight check should be performed by a properly certified pilot.
11. Update aircraft records, complete Form 337 and obtain FAA field
approval for installation, as required.
MADE IN THE U.S.A.
The conditions and tests required for TSO approval of this article are minimum
performance standards. It is the responsibility of those installing this article either on
or within a specific type or class of aircraft to determine that the aircraft installation
conditions are within the TSO standards. TSO articles must have separate approval
for installation in aircraft. The article may be installed only if performed under 14 CFR
part 43 or the applicable airworthiness requirements. TSO-C30c
TYPE I, II & III;
APPROVED
TSO-C96a
CLASS II;
APPROVED