Page 1
1.67
White .........+28VDC (ACL)
Orange ......+28VDC (POS)
Yellow........SYNC
Black .........Ground
WIRING
10”±1.0”
20 AWG
MIL-22759/43 Wire
1.79
3.95
.500
Ø.800
3X Ø.150
(for #6 Screw,
100° C’sink)
Label
1.000
.72
1.750
Mounting Detail
®
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: aviation@whelen.com
Aviation
Installation Guide:
Aviation model(s) OR6502G, OR6502R
P/N 01-0790725-11, 01-0790725-12
Orion 650
Wingtip Position/Anti-Collision Lighthead
©2013 Whelen Engineering Company Inc.
Form No.14719A (062414)
SPECIFICATIONS:
Nominal Operational Voltage:...........................28VDC
(Operational from 22-32VDC)
Input Current:
Position Lights ..................................................0.2 Amps
Anti-Collision Light (Avg.) .................................0.28 Amps
Anti-Collision Light (Pulse) ...............................1.5Amps
Flashrate ..........................................................45 ± 5 FPM
EQUIPMENT LIMITATIONS:
An approved forward position lighting system consists of three lights,
one located on the tail and one located on each wingtip. Model
OR650( ) is a wingtip forward position and anti-collision light.The
assembly should be mounted as far outboard on the aircraft as
practical. 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 or Red LEDs. The
anti-collision light is designed with 18 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.
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 #4 phillips head screw 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 1/4” and lift upwards to remove. CAUTION! To
avoid potential damage, do not touch the LEDs with either
fingers or sharp objects. Remove the 3 Phillips head screws
securing the baseplate to the light assembly. Remove baseplate.
4. Using the appropriate hardware install the baseplate directly to
the aircraft.
5. Route the wires through the opening in the baseplate. 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 and return the lens
retainer to its installed location. Note: Visually confirm that the
lens and retainer are fully and properly seated. Re-insert #4
phillips head screw and tighten firmly.
8. When necessary, seal the light to the aircraft. Apply sealant
around the perimeter of the base. 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, if 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;
APPROVED
TSO-C96a
CLASS III;
APPROVED