ANTI-COLLISION LIGHT SYSTEMS

INSTALLATION AND
SERVICE MANUAL,
SEPTEMBER 16, 1999
Approved under
STC SA6NE (March 21, 1974)
STC SA21NE (March 1, 1978)
STC SA615EA (June 18, 1999)
STC SA800EA (September 8, 1999)

ENGINEERING COMPANY, INC.

ROUTE 145, CHESTER, CT 06412-0684
PHONE: (860) 526-9504
FAX: (860) 526-2009
www.whelen.com

© 1999 Whelen Engineering Company, Inc.

 TABLE OF CONTENTS

PAGE

Introduction and Approved Techniques 3

Anti-Collision Light Requirements - Fig. 1, Fig. 2, Fig. 3, Fig. 4 3

Approved Method of Determining Adequate Coverage - Fig. 5, Fig. 6, Fig. 7 4

Description of Anti-Collision Light Hardware 4&5

Description of Strobe Light Power Supplies 6

Custom Anti-Collision Light Installation Procedures 7

Technical, Mechanical and Electrical Information 7

Installation Procedure for Whelen Strobe Lights 8

A650 Wingtip Strobe 8

A650 Wingtip Strobe on Late Model Cessna 8

A650-PR and -PG Position & Strobe Light 8

1972 and Later Single Engine Cessna - Fig. 8 & 9 8&9

Wiring Strobe Through Wingtip Tanks 9

A625 Strobe Assemblies in 300 & 400 Series Cessnas 9

Strobe Assembly Custom Installations 9

A500A Tail/Position & Strobe Light Replacement - Fig. 9, 10 & 11 10

A600-PR and -PG Strobe and Position Light 10

Rotating Beacon Replacement HR, A450, A470A 11

Quartz Type Flasher Replacement A450, A470A, 70509 12

Waterproofing 15

Installation of Remote Strobe Light Power Supply - Fig. 16, Fig. 17 & Fig. 18 13 & 14

Inter-connecting Cable Installation Instructions &

Trouble Shooting of Strobe Light Systems - Fig. 19, Fig. 20 & Fig. 21 15 & 17

RFI and EMI Problems, (Radio Noise) 16

Whelen Strobe Light Parts Breakdown - Fig. 22 thru Fig. 31 18 & 19

STC SA615EA and STC SA800EA Condition and Limitations 20 and 21

STC Eligibility List Reference 22 and 23

2
INTRODUCTION TO WHELEN ANTI-COLLISION FIVE LOCATIONS ON THE AIRCRAFT FOR
STROBE LIGHTING SYSTEMS, STC SA800EA / STC ANTI-COLLISION STROBE LIGHTS, TO COMPLY TO
SA615EA / STC SA6NE / STC SA21NE THE LIGHT PATTERN REQUIREMENTS.
Whelen’s Anti-Collision Strobe Light Systems are approved under
STC SA615EA, STC SA800EA, STC SA6NE, and STC SA21NE, manu-
factured under PMA as an approved anti-collision light for all aircraft,
when installation is accomplished in accordance with the following
instructions.
Whelen’s Anti-Collision Strobe Light Systems are designed and
approved specifically for General Aviation Aircraft, to comply to FAR
91.205(c) (3) (visual flight rule night) requirements.
Whelen’s approved Anti-Collision Strobe Light Systems can be
installed on all aircraft by completing the installation with reference
FIG. 1 FIG. 2
to this Installation and Service Manual, and the appropriate technical
data listed below:
One anti-collision strobe light Two wingtip strobe lights that
ADVISORY CIRCULAR 43.13-1B, Chapter 11, Sections 1, 2, 3
mounted on the vertical fin will protrude beyond the wingtip,
and 7, Electrical Systems.
meet the minimum require- their light converging in front
ADVISORY CIRCULAR 43.13-2A, Chapters 1 and 2, Radio and back of the aircraft within
ments on most aircraft. A half
Installations. 1200 ft. is an approved anti-
red and half white lens is rec-
ADVISORY CIRCULAR 43.13-2A, Chapter 4, Anti-Collision Light ommended. collision strobe light system.
Installations.
ADVISORY CIRCULAR 20.21, 12-3-64, Application of Glass
Fiber Laminates in Aircraft. OPTIONAL
L O C AT I O N

WHAT IS AN FAA APPROVED ANTI-COLLISION

LIGHT SYSTEM?
DESCRIPTION: An approved Anti-Collision Light System must pro-
duce an envelope of light of a minimum of 400 effective candles in
Aviation Red or Aviation White (Ref. FAR 23.1397), 360 degrees
around the aircraft’s vertical axis 75 degrees above and 75 degrees FIG. 3 FIG. 4
below the horizontal plane, with a maximum of 0.5 steradians (1642
sq. degrees) of solid angle blockage (Ref. FAR 23.1401(b)). Enclosed wingtip anti-colli- A fuselage mounted anti-col-
Described on this page are 5 basic types of installations approved sion strobe lights, require a lision strobe light system
by the administrator. See Fig. 1-4. third strobe light on the tail or requires a minimum of two
FLASH RATE REQUIREMENTS: A single anti-collision light or mul- vertical fin, to fill in the required strobe lights to get the required
tiple anti-collision light system flashing simultaneously, must flash at light envelope. This is an vertical coverage. This is an
a minimum of 40 flashes per minute and a maximum of 100 flashes approved anti-collision system. approved anti-collision system.
per minute.
A multiple anti-collision light system, each light flashing at a ran-
dom or controlled alternate flashing, can exceed 100 flashes per GENERAL AVIATION MINIMUM POSITION
minute, but not over 180 flashes per minute from any position
around the aircraft. LIGHTING REQUIREMENTS
EFFECTIVE INTENSITY REQUIREMENTS: Home-built and new For compliance to FAR Part 23.1385 through 23.1397, VFR flight
type design aircraft, which application for type certificate or operation rule night requirements on a General Aviation aircraft, you must have
limitations was applied for after August 11, 1971, will require an anti- a TSO,d Aviation Red forward position light on the left and an
collision light of 400 effective candles minimum, either in Aviation Aviation Green forward position light on the right. See Figure 7, page
Red or White per FAR 23.1401. All other aircraft require only 100 4.
effective candle power, prior to August 11, 1971. Position lights must These are normally mounted on the most outward extremity of the
meet the requirements of FAR 23.1385, FAR 23.1387, and FAR airframe so they can project their light directly in front of the aircraft
23.1389. 0 degree to 110 degrees left and right horizontally, and 180 degrees
up and down vertically, unobstructed by any part of the aircraft.
The tail position light must project its Aviation White light toward
the rear of the aircraft, 70 degrees horizontally left and right from 0
degree straight back behind the aircraft, 180 degrees up and down,
0.04 Steradian (131.36 sq. degrees) interference is allowable, refer-
ence FAR Part 23.1387(c). More than one light is acceptable.

© 1999 Whelen Engineering Company, Inc.

3
 POSITION LIGHTS AND ANTI-COLLISION LIGHT THE WHELEN A600-PG AND -PR COMPLETE
WINGTIP STROBE LIGHT HEAD
DISTRIBUTION PATTERNS REQUIREMENTS
ASSEMBLY WITH FORWARD AND
TAIL POSITION LIGHTS ready to
360 +7 5
˚ ˚ install on the wingtip of most General
+30 + 30
˚ ˚ Aviation aircraft using 3 mounting screws,
see reference installation instructions on page 10 of
this manual. Parts breakdown shown on Pg. 19, Fig. 28.

- 30 - 30 THE WHELEN A625 STROBE LIGHT HEAD

˚ ˚ ASSEMBLY is the same physical size as the
- 75
˚ Model S tail position light and will fit the same
FIG. 5. An approved anti-collision FIG. 6. An approved anti-collision mounting adapter. It is used in enclosed-type
strobe light system must project strobe light system must project wingtips. The unit fits nicely behind the position
light 360° around the aircraft’s ver- light + or - 30° above and below the light on conical camber wingtips, see reference
tical axis. One or more strobe lights horizontal plane of the aircraft. One installation instructions on page 9 of this manual.
can be used. or more strobe lights can be used.
The + or - 75° projected light is
Parts breakdown shown on Pg. 19, Fig. 25.
required since July 18, 1977. SUPERSEDES A430.
FIG. 7. Approved light
pattern in the horizontal 0 RI THE WHELEN A500A COMBINATION TAIL POSITION
B
E ˚ G
AND ANTI-COLLISION STROBE LIGHT HEAD
plane. The anti-collision
RO

HT

wingtip mounted lights POS. POS. ASSEMBLY replaces the Type S tail position
NG TIP ST

WIN

must converge within RED GREEN light, and provides a 3rd strobe light to the
1200 feet directly in 1 1 0˚ 1 1 0˚ anti-collision light system. The A500A is used
GT I P S

front and rear of the

aircraft on center line. If
in either the vertical or horizontal mounting
GE
IF RE

the wingtip strobe light TAIL TAIL position, reference installation instructions on
WI

POS.
ER

convergence is greater POS. page 10 of this manual, reference installation

T

than 1200 ft. in back of WHITE WHITE

RO

instructions on page 10 of this manual.

FT
Q

NV

7 0˚ 7 0˚
UI

the aircraft, a 3rd light

BE
LE Parts breakdown shown on Pg. 19, Fig. 23.
O

E
R

180
is necessary. ˚
C

D
TH E SUPERSEDES A500.
IRD OB
TA I L S T R
THE WHELEN A450 STROBE LIGHT HEAD
ASSEMBLY was designed for use in severe
environments (vibration, chemicals, oil,
DESCRIPTION OF ANTI-COLLISION LIGHT HARD- moisture). The unit mounts on the aircraft
using Whelen’s H102 “B” or H103 “A”
WARE, APPROVED UNDER STC SA800EA / mounting adapter (see Page 5), see
STC SA615EA / STC SA21NE reference installation instructions
on page 11& 12 of this manual.
Parts breakdown shown on Pg. 19, Fig. 26.
THE WHELEN A650 WINGTIP STROBE LIGHT HEAD
ASSEMBLY mounts on the back of the Whelen THE WHELEN A470A STROBE LIGHT HEAD
W1285 wingtip position light, replacing the ASSEMBLY is designed to produce light 360
position light lens retainer, reference degrees around the aircraft. The A470A
installation instructions on page 8 of incorporates a vibration proof strobe light flash
this manual. Parts breakdown tube which also allows flush mounting. The unit
shown on Pg. 19, Fig. 30. mounts on the aircraft using Whelen’s H102 “B”
or H103 “A” mounting adapter (see Page 5), see
SUPERSEDES A429. reference installation instructions on page
11 & 12 of this manual. Parts breakdown
THE WHELEN A650-PG AND -PR WINGTIP shown on Pg. 19, Fig. 27. SUPERSEDES A470.
POSITION AND STROBE LIGHT HEAD ASSEMBLY
ready to install on the wingtip with minimum THE WHELEN MODEL 70509 Halogen Flashing
modification to the aircraft’s Anti-Collision Light. Totally self-contained,
structure. Installation instructions flashing anti-collision light assembly with
are on page 8 of this manual. FAA TS0-C96a approval, reference installation
Parts breakdown shown on instructions on page 12 of this manual.
Pg. 19, Fig. 29.
NOTE: Model 70509 is not recommended for
use on helicopters.
SUPERSEDES A429-PG AND -PR.

4
THE WHELEN SA,CF SELF CONTAINED MODELS A612, A610. For Cessna Single
STROBE LIGHT HEAD ASSEMBLY. Engine Aircraft, 1972 and later.
Designed to fit any standard fairing or FAA/PMA APPROVED.
fuselage adapter previously used for A610 (strobe tube assembly)
rotating beacons. The SA,CF is A612 (magnifying lens)
available in Aviation White In this system the A610 and A612
only. See page 11. are mounted directly onto the
wingtip retainer. Use the A612
as a template for cutting a hole in
the existing light shield.
See page 9.

A612
Magnifying Lens

THE WHELEN HR,CFA SELF CONTAINED

STROBE LIGHT HEAD ASSEMBLY.
Designed to fit any standard fairing or
fuselage adapter previously used for A610
rotating beacons. The HR,CFA is Strobe Tube
Assembly)
available in Aviation Red or White,
or split Aviation Red and White.
See page 11.

SUPERSEDES HR,DF & HR,DFA

MODELS H102 AND H103.

FAA/PMA APPROVED.
These adapters are designed for the
A470A and A450. H102 allows direct
mounting of the strobe light head
assembly to the skin of the fuselage
or the top of a 2-1/2” diameter Cessna
vertical stabilizer fairing. H103 is designed
to allow strobe light head assemblies
to be installed in 3-3/4” diameter
standard rotating beacon mounting.

A440 MOUNTING ADAPTER Available for fuselage

installations of Models HR,CFA and SA,CF.
Mounting Adapter.
(3.75 opening, 3 screw mounting.)
H102

H103
A440 fuselage mount.

© 1999 Whelen Engineering Company, Inc.

5
 MODEL HT, CF
DESCRIPTION OF POWER SUPPLIES APPROVED FAA-PMA APPROVED
UNDER STC SA800EA / STC SA615EA / STC SA6NE P/N A490T-CF-14/28

MODEL HDA, CF
FAA-PMA APPROVED
P/N A413AHDA-CF-14/28

The HDA, CF is the

finest power supply
available. It has the capacity Our most compact, single-source power supply produces an
for simultaneous flashing, accumulated 19 joules of energy. See page 14.
alternate flashing or both. Wing outputs HT, CF SPECIFICATIONS:
can be disabled when trigger function is engaged. See page 13. Power Consumption: 1.7 Amps @14 volts DC;
HDA,CF SPECIFICATIONS: .85 Amps @28 volts DC; Weight: 1.2 lbs.; Length: 5.0”;
Power Consumption: Width: 3.12”; Height: 2.25”; Flash Rate: 50+/- 5 FPM.
7.0 Amps @ 14 volts DC, 3.5 Amps @28 volts DC;
Weight: 2 lbs.; Length: 5.50”; Width: 5.0”, Height: 2.37”;
Flash Rate: alternately at 90 +/- 5 FPM, MODEL HTC-CF
simultaneously at 50 +/- 5 FPM. FAA-PMA APPROVED
P/N A490TC-CF-14/28

MODEL HTS, CF
FAA-PMA APPROVED.
P/N A490ATS-CF-14/28

Same as Model HT-CF

but with a mounting plate that
can directly replace factory
The HTS, CF produces an accumulated 34 joules of energy. installed systems on S/E Cessnas,
It can be equipped to flash simultaneously with up to 5 S/E Aero Commanders and
other HTS, CF power supplies by connecting an 18 gauge wire S/E Grumman Americans. See page 14.
between the synchronization mechanisms in each power HTC-CF SPECIFICATIONS:
supply. An 18 gauge low voltage wire supplies power Power Consumption*: 1.7 Amps @ 14 volts DC;
to each HTS power supply. See page 14. .85 Amps @ 28 volts DC;
HTS, CF SPECIFICATIONS: Weight: 1.5 lbs.; Length: 5.0”; Width: 3.12”;
Power Consumption*: 4.0 Amps @ 14 volts DC; Height: 2.25”; Flash Rate: 50+/- 5 FPM.
2.0 Amps @ 28 volts DC;
Weight: 1.7 lbs.; Length: 5.0”; Width: 3.12”; Height: 3.06”;
Flash Rate: 50+/- 5 FPM.
See pages 13 & 14 for installation information.

6
 The solid angle blockage must be reviewed after installing any
masking that will disturb the 360 degrees by +/– 75 degrees pattern.
CUSTOM ANTI-COLLISION LIGHT INSTALLATION
The aforementioned type masking used on wingtip lighting seldom
PROCEDURES STC SA800EA / STC SA615EA / interferes with this pattern.
STC SA21NE ESTABLISHING SOLID ANGLE BLOCKAGE WITH REFERENCE
The following information is to assist in the installation of a custom TO AC 43.13-2A, CHAPTER 4.
Whelen anti-collision strobe light system on any aircraft, and how to 1. To determine the vertical angles to use with reference to Figure
return the aircraft back to service with compliance to FAR Part 7 and 8 of the aforementioned chapter 4, attach a long string
91.205(c) (3). to the subject light source location.
1. Choose from figures 1, 2, 3 or 4, on page 3, the anti-collision 2. Fix a navigational-type plotter or protractor to the string with
light system which is most applicable to the aircraft. weighted thread fixed to the center of the scale for a plumb bob.
2. With reference to the STC’s “Limitation and Conditions” for field 3. Level the aircraft or determine the offset angle.
of coverage requirements. Check the field of coverage of the pro- 4. Pull the string over the point of solid angle blockage (Ref. Figure
posed location. (Figures 5, 6 and 7 on page 4 define the required 6 page 4. Any angles greater than +/– 75 degrees vertical are not
field of coverage). a factor.
3. These STC’s document that Whelen’s anti-collision strobe lights 5. Apply the vertical and horizontal angles to the graph paper (Ref.
meet the requirements as specified in AC 43.13-2A, Chapter 4, Figure 4.8 and instructions in text of paragraph b6 and c of
PAR.51(a and b) (1). STC SA615EA covers replacement of orig- Chapter 4).
inal equipment, STC SA800EA and STC SA21NE cover installa-
A flight test will be performed by properly certified pilot with refer-
tion of new anti-collision light systems.
ence to paragraph 52(a) (b) of Chapter 4.
4. Vertical fin mounted anti-collision strobe beacons (Ref. Figure 1
page 3), will conform to the FAR 23.1401, 0.5 steradian (1642
sq. degrees) maximum solid angle blockage requirements on
most standard configurations (CAM 3 and FAR Part 23) high or
low wing type aircraft. An average solid angle blockage for an
installation of this type is 1324 sq. degrees.
5. Fuselage mounted anti-collision light systems require two (2)
anti-collision strobe beacons (Ref. Figure 4 page 3) to get
the +/– 75 degrees required. Two lights mounted in this manner
exceed the steradian requirements of 21,600 sq. degrees total
coverage.
6. Fuselage mounted anti-collision lights should be located on the
fuselage center line to reduce reflection on the wings as much as
possible. They should be mounted near the trailing edge of the
wing, to reduce cockpit reflection.

APPROVED METHOD OF DETERMINING ADEQUATE COVERAGE

OF WINGTIP AND TAIL STROBE LIGHT INSTALLATIONS.
The most practical system is the approved wingtip anti-collision
strobe light system. These systems consist of two or more lights to
complete the anti-collision light requirement. There is no question as
to their complying to the field of coverage when the installation is
completed (Reference to the following instructions).
The acceptable distance for the two wingtip anti-collision strobe
lights to converge in front and back of the aircraft on center line is
1200 feet. If both wingtip anti-collision strobe lights can be seen at
1200 feet or less directly in front and back of the aircraft, it is con-
sidered a point of light source, therefore a third light is not necessary. Typical wing-tip installations.
The wingtip anti-collision light must be located in such a way that
it will project light +/– 75 degrees above and below the horizontal axis
of the aircraft, and the summation of the 2 or 3 lights will project light
360 degrees around the vertical axis.
PILOT AND CREW INTERFERENCE: In some installations it will be
necessary to mask the strobe light head assembly, to reduce pilot
annoyance. This interference problem varies from one aircraft to
another of the same model, due to paint schemes and colors. The
Navigation Light Detector will be a source of reflection and should be
reduced in size, or masked as necessary. A small aluminum or plas-
tic plate mounted between the navigation light and the wingtip pro-
truding up or down as required (like some plastic navigation light
detectors, and trimmed to shadow the objectionable reflected area),
is simple and very effective.

© 1999 Whelen Engineering Company, Inc.

7
 A650-PR (RED) AND A650-PG (GREEN) FORWARD POSITION
PROCEDURES FOR INSTALLING THE WHELEN ANTI-COLLISION LIGHT ASSEMBLY.
ANTI-COLLISION LIGHT HEAD ASSEMBLIES These assemblies are interchangeable with the
STC SA800EA / STC SA615EA / STC SA738EA / Grimes A1285 position light, using the original
STC SA21NE mounting hardware or appropriate
approved fasteners. To mount the
A650-PR and -PG on the wingtip,
A650 WINGTIP STROBE LIGHT. use the W1285-2 position light
The A650 strobe light head assembly was base plate as a template, drill the
designed to fit on the Whelen W1285-2 base three (3) mounting screw holes if
A650-PR/PG
light assembly, used on the majority of necessary, and open the 3/8 inch x
General Aviation aircraft. To install 1 inch opening in the center base
the Whelen A650 strobe light head plate through the wingtip for access
assembly on the aircraft, proceed to the strobe light flash tube interconnecting cable connector.
with the following instructions:
A650

1. Remove the wingtip navigation light and wingtip, when necessary.

2. Install the nylon three position AMP pin connectors A441 on the
end of the flash tube wires (RED in pin 1, BLACK in pin 2, and
WHITE in pin 3).
3. Assemble the navigation light assembly on the wingtip using the
A650 strobe light assembly as the navigation light lens retainer:
a. Install the rubber pad (supplied in kit) on the position light
base plate under the A610 flash tube, if necessary to make the
lens firm in its mounting.
4. In some installations it will be necessary to mask the A650 strobe
light, to reduce pilot annoyance. The Navigation Light Detector
BEFORE AFTER/WITH MODIFIED WINGTIP.
will be a source of reflection, and should be reduced in size or
masked as necessary. A small aluminum or plastic plate, mount-
ed between the navigation light and the wingtip, protruding up or A650 WINGTIP STROBE LIGHT INSTALLATION ON LATER
down as required (like some plastic navigation light detectors), MODEL CESSNA WINGTIPS WITH SHORTENED LIGHT BASE.
and trimmed to shadow the objectionable reflected area, is most Because Cessna has modified the Type E Series Wingtip Navigation
effective. This reflection problem varies from one aircraft to Light, by cutting off the back 1.3 inch, and designed their wingtip to
another, due to aircraft design and paint color scheme, and must fit in closer to the light, it will be necessary to do a little fiberglass
be checked on every installation. work when completing this installation. The A650 can be installed on
these Cessnas in the manner below, and instructions above.
1. Remove the wingtip and the navigation light assembly.
2. Take a complete Model W1285 navigation light with an A650 head
assembly installed, or an A650-PR or -PG, and place it in position
on the wingtip. Mark around the navigation light base plate to get
an outline of the navigation light profile on the wingtip.
3. File or trim away the excess wingtip material, to allow the naviga-
tion light and the A650 strobe light assembly to fit neatly in place.
Allow at least 0.060 inch clearance around the A650 strobe head
assembly and the wingtip.
4. To fill in the hole in the wingtip made by this trimming, and to pro-
BEFORE
vide a platform for the navigation and strobe light assembly,
mount the navigational light base plate on the wingtip using the
two (2) forward screws with a sheet of polyvinyl between the
wingtip and the base plate for a parting agent. Tape the polyvinyl
back over the wingtip to form a seal, so it is possible to apply a
polyester resin putty, or epoxy putty like “Bondo”, on the inside of
the tip. Build up the trimmed area with this putty, as to have about
1/4 inch of material under and in back of the base plate. Prepare
the surface and the putty material in accordance with the putty
manufacturer’s instructions, to assure a good bond to the
wingtip.
AFTER/WITH MODIFIED WINGTIP. 5. Remove the navigation light base plate and parting agent.
6. To improve the appearance of this installation, fill the indentation
on the outside of the wingtip with the aforementioned putty, and
file the excess material to a clean profile before painting.
7. Drill the third mounting screw hole for the navigation light, and
complete the installation, reference the enclosed information.

8
LATE MODEL SINGLE ENGINE CESSNA WINGTIP STROBE A625 STROBE LIGHT ASSEMBLY.
LIGHT INSTALLATION. The A625 strobe light head assembly
fits into a 1.1 inch hole. The mounting
screws are 1.75 inch center to center. It
protrudes 1.7 inch outside the aircraft’s
skin, and 1.1 inch inside the aircraft.
BEFORE When installing an A625 strobe light
head assembly on the rudder, refer to the
BEFORE aircraft’s MAINTENANCE and/or SER-
VICE MANUAL for accepted procedures
A625
AFTER
for balancing the rudder before returning
the aircraft to service.
Mount the anti-collision strobe light head assembly as close to the
stabilizer center line as practical, to eliminate backscatter as much as
possible for the horizontal surface.
AFTER
When installing the A625 strobe light head assembly in an
1. Remove the position light lens retainer being careful not to drop enclosed area like a Beech enclosed wingtip or tail cone, maintain at
the red or the green lens. least 0.060 inch clearance around the lens to the plastic cover. The
2. Establish a center line on the Cessna lens retainer, referencing to A625 mounts conveniently just behind the forward position light on
the lens retainer center mounting screw, and position light base Cessna’s conical camber wingtip. Make sure that the navigation light
plate rear mounting screw. pattern is not interrupted when installing the A625 strobe light head
on a wingtip. The A612 lens is not considered an obstruction.
A625 INSTALLATION IN CESSNA 300 OR 400 SERIES WINGTIP
CENTERLINE TANKS. The A625 fits just under the navigation light, on an adapter
plate of 0.032 inch aluminum, approximately 2-3/8 inches x 3-1/2
inches. Fit this plate between the navigation light and its mounting
surface, and locate the A625 strobe head below the navigation light.
File to fit
A612 lens
profile

FIG. 8

3. Scribe the A612 lens profile as shown in illustration above, the

object being to have the strobe light centered over the position
light base plate.
4. Trim or fit an opening to the scribe line to fit the A612 lens. Due
to the uneven surface of the Cessna lens retainer, the A612 will
contact only the front and rear radius. Bend and trim the adapter plate as necessary, so that the A625
clears the transparent window that covers the navigation light area
5. Place the sponge rubber pad supplied under the A610 flash tube
0.060 inch minimum.
to firm the assembly. RTV is recommended to secure lens in the
modified retainer. The conduit for the navigation light wire is very small. To get the
necessary wires to operate the strobe light and the navigation light
6. The flash tube interconnecting cable is routed through square
through this conduit, use a 20 gauge wire, with less that 0.060 inch
holes in the rear bulkhead of the position light area.
OD. It has been found that the Belden 8502 or 8308, has an 0.058
7. Install the modified position light lens retainer, A610 flash tube inch OD.
and A612 lens, using original hardware.
Photos below show typical installations.

© 1999 Whelen Engineering Company, Inc.

9
 A500A COMBINATION TAIL STROBE AND POSITION LIGHT.
A600-PG AND -PR ANTI-COLLISION WINGTIP
1. Remove the Model S tail position light by removing the two (2)
STROBE LIGHT HEAD ASSEMBLY WITH FORWARD retainer ring screws.
AND TAIL POSITION LIGHTS.
INSTALLATION INSTRUCTIONS
Remove two (#6-32 x .312LG) retainer screws and retainer for
installation of the A600PG/PR. BE CAREFUL NOT TO DROP THE
GLASS COVERS as they are held in position by the retainer. Attach
the base assembly to your wing-tip with 3 #6-32 countersunk
screws.

2. This unit fits directly in place of the

Grimes Model S tail position light. It
is however sometimes necessary to
open the mounting hole in the aircraft
fairing to 1.10 inch, to clear the body
of the A500A. The body protrudes
A500A
1.40 inch into the tail fairing.
3. Establish the proper light pattern of the A500A tail position light.
The retainer shield must be located so that the bottoms of the V
A600PG/PR notches are vertical (parallel to the rudder) to shadow the light so
it will produce a horizontal light pattern of 70 degrees left and
right of straight back of aircraft.

1.75"

1.75"

The A600 Anti-Collision Strobe Light with Forward and Tail position
light is a complete exterior light package. When properly installed on FIG. 9. HORIZONTAL VERTICAL MOUNTING
the aircraft wingtips, it will comply to FAR Part 91.205(c-2) & (c-3). SURFACE
The A600 must be mounted on the aircraft extremities so that the
light distribution pattern is not obstructed by any parts of the aircraft 1.40"

(Reference figures 5, 6, and 7 on page 4). A limited amount of

obstruction is permitted (Reference Part 23.1401, Paragraph (b)
Anti-Collision Light Coverage, and Part 23.1387, Paragraph (e) Tail POSITION LIGHT PATTERN REQUIREMENTS
Light Coverage).
The convergence of the two wingtip tail position lights must occur
110 °
within 1200 feet directly behind the aircraft to comply with field of
coverage requirements. One may, but need not, remove the old tail GREEN

position light when using the A600.

The A600 base plate must be mounted parallel to the vertical and 180° WHITE 140°
horizontal center lines of the aircraft to project the light pattern prop-
erly.
Properly mounting the A600 on the most outward radius of each RED
wingtip will cover the required area appropriately without any solid 110 °
angle blockage. The A600 mechanically mounts on the wingtip using
the original three mounting holes and screws (Reference A1285 and FIG. 10. FIG. 11.
W1285 position lights). APPROVED LIGHT PATTERN APPROVED LIGHT PATTERN
IN THE VERTICAL PLANE IN THE HORIZONTAL PLANE
The RED wire applies power to the forward position light. The
BLUE wire applies power to the tail position light. The BLACK wire is
ground and one BLUE. The RED and one BLUE wires are wired in par- CONNECTING WIRING OF THE A500A TO THE A441 AMP 3 POSI-
allel to the existing wingtip position light wire. TION PIN CONNECTOR HOUSING, AND THE A444 AMP 2 POSITION
PIN HOUSING CONNECTOR.
The 14 volts forward position lights draw 1.9 amps each, the tail
position lights draw 1.8 amps each, for a total of 7.4 amps for a 14 Anode RED wire Pin 1 of A441
volts DC system. The 28 volts forward position lights draw 0.95 Cathode BLACK wire Pin 2 of A441
amps each, the tail position lights draw 0.90 amps each, for a total of Trigger WHITE wire Pin 3 of A441
3.7 amps for a 28 volts DC system. Position Light A+ BLUE wire Pin 1 of A444
The A600 weights 0.5 lbs. each. Position Light Ground BLUE wire Pin 2 of A444

10
ROTATING BEACON REPLACEMENTS.

BEFORE WITH ROTATING AFTER WITH STROBE LIGHT

BEACON

The A450 and A470A remote anti-collision strobe light head

assemblies are direct replacements for the rotating beacon, using the
H103 “A” mounting adapter. They are mounted on the aircraft using
the same type hardware and fastener originally used.
The “A” mounting adapter (H103) is a cup mounting adapter that
fits the standard 3.750 inches rotating beacon mounting, using the
same mounting hardware, three (3) 6-32 x 3/8 inch maximum length
screws.
The A440 mounting flange supports the “A” mounting adapter on
a flat surface such as the top or bottom of the fuselage. See
Reference AC 43.13-2A, Chapter 4 for approved location, mounting The photos above show typical installations
and installation procedures.

MODELS SA,CF-14/28 OR HR,CFA-14/28 STROBE LIGHTS FOR

ROTATING BEACON REPLACEMENT.

HR,CFA

SA,CF

A470A A450

6. FLASH TUBE REPLACEMENT. The A469B flash tube in the

HR,CFA-14/28 and the SA406 flash tube in the SA,CF-14/28 are
simple to replace by removing the A409 clamp ring and lifting the
lens. The flash tube plugs into the power supply (reference page
19), Parts Breakdown A450 and A470A.

1. These models are interchangeable with rotating beacons on any

aircraft having a 3.750 inch diameter fairing or mounting adapter.
2. Install strobe unit in place of the existing beacon, using three (3)
6-32 x 3/8 inch screws (maximum length) supplied in kit.
3. Connect the existing wiring, positive to the white wire and ground
to the black wire protruding from the power supply.
4. Check rudder balance with reference to the aircraft’s service man-
ual,when installing the strobe light unit on the rudder. The bal-
ance, weight and strobe light unit should equal the original rotat-
ing beacon and balance weight total.
5. When installing the strobe light unit in an inverted position, and
water collects inside the lens of the strobe light head assembly,
drill a #40 hole in the bottom of the A402A lens as indicated on
label affixed to lens. For model SA,CF-14 or 28 remove the RTV
plug from the hole in the SA402 lens.

1995 Whelen Engineering Company, Inc.

11
A450 AND A470A REMOTE STROBE QUARTZ TYPE FLASHER REPLACEMENTS.
LIGHT HEAD ASSEMBLIES.
The A450 and A470A strobe lighthead
assemblies, can be
mounted on the
aircraft fuselage or
vertical stabilizer,
provided the
specifications
in AC 43.13-2,
Chapter 4, Paragraph A450 A470A
52(a) are complied with.

VERTICAL FIN AND RUDDER MOUNTING OF ANTI-COLLISION BEFORE WITH QUARTZ LIGHT AFTER WITH REMOTE STROBE
STROBE LIGHTS. LIGHT

Rudder mounted anti-collision lights should be located top center

The A450 and A470A remote anti-collision strobe light head
of the rudder hinge center line, or rudder balance must be estab-
assemblies are direct replacement for the quartz-type flasher, using
lished after installation. Refer to AC 43.13-2A, Chapter 4, Paragraph
the original or the H102 “B” mounting adapter.
55(e), “Rudder Installation”. The rudder or fin cap is excellent for
The H102 “B” mounting adapter is mounted in the aircraft’s struc-
shadowing the prop and cabin area if the light is mounted far enough
ture, with four (4) MS 20470 AD4 rivets, or four (4) 6-32 screws and
back.
self-locking nuts. Drill out the center hole in the skin to allow access
to the strobe head connector.

MODEL 70509
Halogen Flashing Anti-Collision Light
Totally self-contained, flashing
anti-collision light assembly with
FAA TS0-C96a approval.

NOTE: Model 70509 is not

recommended for use
on helicopters.
NOTE: Mounting an A450 or A470A strobe light head assembly on
a vertical fin or rudder, can be accomplished by fabricating a mount- 70509-( )
ing adapter similar to the ones shown in illustrations below. 70509 SPECIFICATIONS:
A similar adapter can be fabricated for the A625, for a lower profile Power Consumption:
light installation. A section of streamline tubing works very nicely for 2.7 Amps @14 volts DC;
these adapters. 1.35 amps @28 volts DC;
Weight: 0.27 lbs.;
Height: 3.75”;
Diameter: 2.65 70509 Mounting Adapter
P/N 11-350519-001
Outside Dia. - 3.678” / fits 3.75” Hole

FIG. 14. FIG. 15.

Round or streamline tubing Metal bracket shaped to

cut to fit rudder or fit the vertical fin or
vertical fin welded to rudder with 2 1/2” OD .040”
2 /12” OD .40” thick disc. thick disc riveted in place.
(Reference AC 43.13-1B, (Reference AC 43.13-1B,
Chapter 2, Section 2). Chapter 2).
Fabrication and installation of these mounting brackets are refer-
enced in this approved installation manual, and AC 43.13-1B and 2A.
Documentation of structural integrity of the fabricated installation
must be approved by an “IA” or other representative of the FAA.
Conformity inspections will be performed with reference to approved
techniques, and procedures specified in this manual (see page 3). Model 70509 installation.

12
 THE WHELEN MODEL HDA,CF (A413A, HDA,CF-14/28) POWER
INSTALLATION OF THE REMOTE STROBE LIGHT SUPPLY is a 3 outlet, power source, flashing two remote strobe light
heads simultaneously, and a third remote strobe light head flashing
POWER SUPPLIES STC SA800EA / STC SA615EA alternately.
IMPORTANT NOTE... THE STROBE LIGHT POWER SUPPLY
SHOULD NOT BE MOUNTED CLOSER THAN 3 FEET OF THE ADF FIG. 16.
LOOP. Jumper with jumper

1
The Remote Strobe Light Power Supply will be installed using for pins to be inserted in
reference AC 43.13-2A, Chapter 4 for installation procedure, using outlet #1.

3 2
four (4) MS, AN or NAS 8/32 screws and self-locking nuts. Outlet #1, trigger
selector. Outlet #3 and #4
Outlet #2, third wingtip strobe lights.
strobe light (tail)
LOCATION.
1. Consider areas or locations designated by the aircraft manufac-
turer, to install the strobe light power supplies, or other optional PIN
equipment not already in use. 1 TYP.

2. For alternate locations consider areas or locations such as the 2 TYP.

cabin baggage compartments, on the floor under the seat, non- 3 TYP.
structural bulk-heads, fire walls, hat racks, etc. (1)+ 1 2 3 4
(2)- TAIL WING WING
3. If necessary, fabricate support brackets or shelves, and attach
(3) STROBE OUTLETS
them to the aircraft structure to provide a mounting that will with-
stand the inertia forces stipulated in Chapters 1 and 3 of AC
TYPICAL STROBE HOOK-UP
43.13-2A. Connector for PIN 1 - RED - ANODE
input power cable PIN 2 - BLACK - CATHODE
4. Documentation of structural integrity of the fabricated installation
must be approved by an “IA” or other representative of the PIN 3 - WHITE - TRIGGER
Federal Aviation Agency. Conformity inspections will be
performed with reference to approved techniques and procedures
specified in this manual (see page 3 and 4).
T3 FUNCTION
5. When installing the remote strobe light power supply in an invert-
Outlet #1 is a trigger selector. Jumping pins #1 and #2 on the
ed position, drill a 3/16 inch diameter hole in the lowest corner of
jumper plug produces an alternating flashing between outlet #2 and
the cover to provide for a water drain. Care must be taken not to
outlets #3 and #4, at 50 CometFlashes, +/–5, per minute. A switch in
let the drill protrude into the power supply, for it may inflict dam-
place of the jumper will permit turning off the wingtip strobe lights,
age to the electronic components.
while the tail light will remain ON. See Diagram in Figure 17 below.
6. Specifically call out the location of the strobe light power supply By using outlets #2 and #3, or #2 and #4, the unit produces a com-
and the strobe light heads on the FAA Form 337 for the anti-col- bined total of 44 Joules alternating at 90 CometFlashes per minute.
lision light installation. The A413A,HDA-CF-14/28 replaces the A413A,HDA-DF-14/28. HD,
HD,T2 and HD,T3 power supplies which have been discontinued.

FIG. 17.
WIRING INSTRUCTIONS. Switch normally closed
1/10 amp rated.
OFF
ON
WARNING: WHELEN STROBE LIGHT POWER SUPPLIES
ARE POLARITY SENSITIVE. REVERSING THE INPUT POLAR-
ITY WILL CAUSE SEVERE DAMAGE TO THE POWER SUPPLY.
Jumper inserted
in outlet #1.
Steps below: “Ref. AC 43.13-1B, Chapter 11, Sections 1, 2, 3 & 7”.
1. Choosing wire size of input A+ lead, refer to Paragraph 444
“Electric Wire Chart” Figure 11.7 and 11.7A, with reference to -
Strobe Light Model Current requirement chart on page 6 and 11 + 14V or 28V
of this manual, and “Wire and Circuit Protection Chart” Figure
11.1 of AC 43.13-1B.
2. Shielded wire is not generally necessary, but has proven helpful 4 3 2 1 POWER
when radio interference has been encountered. STROBE OUTLETS TRIGGER IN
HDA-CF
NOTE: One will not experience any radio interference caused by
the Whelen Strobe Light Systems, when the radios and strobe
light systems are properly installed.
3. For penetrating pressure hull refer to aircraft service manual. T3 OPTION DIAGRAM

© 1999 Whelen Engineering Company, Inc.

13
WHELEN MODEL HTS,CF POWER SUPPLY WHELEN MODEL HT,CF (A490,T,CF-14/28) POWER SUPPLY
THE WHELEN MODEL HTS,CF (A490A,TS,CF-14/28) POWER SUP- THE WHELEN MODEL HT,CF (A490,T,CF-14/28) POWER SUPPLY is
PLY replaces the old HS (A412A, HS,DF-14 or -28) and HTS-DF a single 10-3-3-3 joules remote strobe light power source for any
(A490ATS-DF). The HTS,CF is a 16-6-6-6 joules strobe light power Whelen strobe light head assemblies. Its size and weight make it
source, which can be used as an independent power source for any adaptable for wingtip installation. This power supply is approved for
of the Whelen strobe light head assemblies. This power supply is Aviation White only.
approved for use with an Aviation Red or White anti-collision strobe
light head assembly MODEL A490T, CF-14/28
The HTS,CF mechanically fits the same foot print as the old
A412A,HS,DF, A490ATS-DF and A490,T,DF-14/28 power supplies.
The HTS,CF can be synchronized by running an 18 gauge or larger
wire between pin’s 3 on each power supply. (See Picture)
The A490A,TS,CF-14/28 power supply has two connectors.

OUTPUT POWER
1-RED (1) +
2-BLACK (2) -
3-WHITE (3) SYNC
FIG. 18.
RED (ANODE) POSITION 1
BLACK (CATHODE) POSITION 2
1 1 WHITE (TRIGGER) POSITION 3
2 2
POS. NO. 1 (+), RED WHITE (+14/28 VDC)
3 3
P0S. NO. 2 (-), BLACK BLACK (GROUND)
POS. NO. 3 - SYNC
See Page 15, Figure 19 for connector assembly.

Looking at the power supply connectors with the mounting plate MODEL A490TC, CF-14/28
flat on a bench, the left connector is the strobe outlet. The right con-
nector is the power input and synchronization.
Left Connector. Is the strobe light power supply power output.
Pin 1. Top. Red wire, anode 450 volts DC nominally
Pin 2. Center. Black wire, strobe light ground.
Pin 3. Bottom. White wire, trigger. 200 volts DC nominally
Right Connector. Is the strobe light power supply power input
Pin 1. Top. Red Wire 13 to 30 volt, positive input.
Pin 2. Center. Black wire ground.
Pin 3. Bottom. Synchronization pin. If synchronization is desired
connect an 18 gauge wire between pin’s 3 on each power supply.

RED (ANODE) POSITION 1

BLACK (CATHODE) POSITION 2
WHITE (TRIGGER) POSITION 3

WHITE (+14/28 VDC)

BLACK (GROUND)

14
INTERCONNECTING CABLE.
TROUBLE-SHOOTING PROCEDURES FOR AVIATION
1. The interconnecting cable is supplied with one end unfinished so
that cable can be installed through small openings, and cut to ANTI-COLLISION STROBE LIGHT SYSTEMS
length before finishing off the power supply end. WHEN REPAIRING WHELEN ANTI-COLLISION STROBE LIGHT
2. The grey vinyl outer jacket on the cable supplied with a Whelen SYSTEMS, USE ONLY WHELEN FAA APPROVED HARDWARE. BE
Strobe Light, is an excellent chafe-resistant material, and addi- CAREFUL OF STROBE LIGHT PARTS THAT ARE SIMILAR IN
tional chafe protection is seldom necessary. The use of RTV to APPEARANCE!
secure the interconnecting cable in inaccessible locations is The Whelen Aviation Strobe Light is a condenser discharge strobe
acceptable. light system. A condenser is charged to approximately 450 volts DC,
3. High voltage leads shall not parallel ADF leads closer than 6 inch- then discharged across a xenon flash tube at controlled intervals. The
es, and shall not parallel gyro or flux gate compass leads closer condenser is parallel across the xenon flash tube that is designed to
than 3 inches. hold off the 450 volts DC applied, until the flash tube is triggered by
4. Reference should be made to AC 43.13-1B, Chapter 11, Sections an external pulse. This pulse is generated by a solid state timing cir-
3 and 7, when routing and fishing the interconnecting cable. cuit in the power supply.
5. Leave a service loop at the strobe light head end, to allow access When trouble-shooting a strobe light system first determine if the
to the connector for flash tube replacement without having to trouble is with the flash tube or the power supply. This can be accom-
disassemble the aircraft. plished by replacing the flash tube assembly with a good operating
flash tube, or with the use of a Whelen Strobe Check unit.
COLOR CODE ON PIN 1 RED - Anode+ 425 VDC Nominally Whelen’s power supplies are protected against a short or open cir-
INTERCONNECTING CABLE: PIN 2 BLACK - Flash tube ground cuit on the output. In either case the power supplies will effectively
PIN 3 WHITE - Trigger 200VDC
*Ground shield to aircraft. Ground at the power supply only. turn themselves off when subjected to a shorted output of a xenon
flash tube that refuses to flash.
CAUTION: CABLES CONNECTING REMOTE POWER WARNING: Strobe light power supplies are meant to be used, not
SUPPLY TYPE STROBE LIGHTS MUST to remain in an inactive state. Use them at all times, this will improve
BE CONNECTED CORRECTLY. their proper functioning. Any strobe light power supply that has been
FIG. 19. CLIP out of service for a long period of time is subject to failure because
the electrolytic condenser loses the polarity formation. A strobe light
SHIELD* power supply not having been used for one year or longer is vulner-
able to failure.
TE If this is the case, it is recommended to start operating the system
HI on a voltage that is reduced by 25 percent for 10 to 15 minutes before
W
K putting the power supply into normal service. This will prevent over-
AC
BL heating of the condenser while they reform. If the power supply, after
a long period of non use, is operated at full voltage immediately, there
A441 PINS POWER SUPPLY END is an excellent possibility that the condenser will become overheated.
A442 SOCKETS FLASH TUBE END
RED

OBSERVE COLOR AND PIN NUMBERS POWER SUPPLY TEST PROCEDURES:

The retaining clip on the side of each pin or socket of the A441 and THE POWER SUPPLY IS A HIGH VOLTAGE DEVICE. LET
A442 connector assemblies must be bent out (Reference illustration THE POWER SUPPLY BLEED DOWN FOR 10 MINUTES
shown above) so that they positively snap into the AMP 3 position AFTER TURNING OFF POWER BEFORE HANDLING.
socket nylon connector housing. WARNING: Reverse polarity of the input power, for just an
If it is not possible to get a good grip, it is recommended that the instant, will permanently damage the power supply. This
pins and sockets be soldered to prevent burning of the wires. damage is sometimes not immediately apparent, but will
CAUTION: When pins 1 and 2, or pins 2 and 3 are reversed, the cause failure later on.
system will appear to operate normally, but this condition will cause External trigger switching is not provided on the A413A,
early flash tube failure, and will void the flash tube warranty. HDA-DF Strobe Light Power Supply (Reference A413,T3-DF
old style strobe light power supply, outlet #1). Do not short
out high voltage for extended length of time; it will cause
COMPLETING THE ANTI-COLLISION LIGHT INSTALLATION. overheating of the output diodes and cause possible failure.
1. Check all avionics systems for interference from this installation,
reference AC 43.13-2A, Chapter 4, Paragraph 52(b).
2. A flight check will be performed by a properly certificated pilot A normal operating power supply emits an audible tone.If there is
with reference to AC 43.13-2A, Paragraph 52(a) and (b). no sound emitted, investigate.
3. If a solid angle blockage document must be established, it should 1. Determine that there is a proper input voltage at the power sup-
be performed after all masking has been installed and all flight ply. If this test is positive go to step 2.
testing is completed. See page 3 of this manual. 2. Clear all possible shorts at the power supply, by disconnecting the
4. WATERPROOFING OF STROBE LIGHT INSTALLATIONS: When output cables from the power supply outlets, and connect an
necessary to waterproof the installation of a strobe light mount- operating strobe light head assembly or a Strobe Check unit
ing to the aircraft, apply GE (silicone rubber) RTV 102 (or equiv- directly to the power supply outlet, then apply the required volt-
alent) around the open area where water could get in. age to the power supply input. If this application proves positive
5. Label all switches and breakers, install Pilot Warning Placard. the power supply is in working condition, and the problem may
6. Up-date aircraft records and complete form 337. be with the interconnecting cables.

© 1999 Whelen Engineering Company, Inc.

15
CABLE CONTINUITY CHECK PROCEDURES. R.F.I. AND E.M.I. PROBLEMS (Radio Noise).
If pins 1 and 3 are reversed, or if there is a short between pins 1 Whelen Engineering strobe light power supplies are designed with
and 2 of the interconnecting cable, the power supply will be rendered a low pass filter built in to keep R.F.I. and E.M.I. down to a minimum,
non-operable until the short is cleared. A short of this type will not however, sometimes there will be interference in the radios by the
cause any permanent damage to the power supply. However a dis- strobe light system. Most always, this is an installation problem, not
charge of the condenser across pin 1 and pin 3 will destroy the trig- a strobe light power supply problem.
ger circuit in the power supply. The power supply should acquire its power from a low impedance
1. Check for continuity between the connectors of each intercon- source, such as the alternator or generator end of the electrical buss.
necting cable: Historically, the rotating beacon or strobe light circuit breaker is
Pin 1 to pin 1 (red wire = anode +). added on the electrical buss at the opposite end, with the radio in
Pin 2 to pin 2 (black wire = flash tube ground -). between the strobe breaker and the low impedance end of the elec-
Pin 3 to pin 3 (white wire = trigger). trical buss. Any noise generated by the power supply will be trans-
mitted into the radio through the A+ input lead to the radio. Most of
2. Check for shorts between pins 1 and 2, pins 1 and 3, and pins 2
the new radio equipment manufactured today has inadequate input
and 3 of the interconnecting cable.
filtering, and any noise on the electrical buss is amplified in the radio
NOTE: When pins 1 and 2, or pins 2 and 3 are reversed, the sys- and produced through the speaker and/or head phones loud and
tem will appear to operate normally, but these conditions will cause clear.
early flash tube failure, and void the flash tube warranty.
Two things can be done to alleviate the problem...
1. Connect the strobe light circuit breaker to the low impedance end
XENON FLASH TUBE PROCEDURES. of the electrical buss, using a 16 gauge jumper, as close to the
1. A xenon flash tube can be very photosensitive. One will flash battery as possible.
normally when exposed to an external light source, but may 2. Install additional filtering in the radio A+ line, or provide an iso-
become hard to fire when subjected to darkness. lated A+ source for the radios by installing a filter choke in series
2. They will become hard firing with age, or when exposed to a very with the radio input power lead and a filter adapter to ground and
high temperature. A hard firing tube will sometimes operate with reference all radios to their filter. This will also improve the radio
the engine running, but will fail when operated on a low battery. system from other line noises.
3. They can develop a leak through eggshelling of the glass, or a leak Frequently, the noise is not on the A+ lead but is conducted through
can develop around the seal of the wire to the glass. This is the ground circuit. Alternator, electrical motor, fuel pumps and strobe
caused by hot and cold cycling of normal operating of the system. light power supplies draw heavy current through the ground circuit
of the aircraft’s frame. Any voltage drop in the ground circuit between
4. They can go into self-ionization (continuously glow a light blue),
the battery ground and the radio ground can look like a signal to the
thus rendering the entire system non-operational until flash tube
radios. When the speaker, head phone and microphone use the air-
is replaced. This most likely occurs when the input voltage is
craft’s ground for return to the radios, one will always experience
highest. This can be checked by turning the system off. When
some interference. The amount of interference depends upon how
turning the system back on, it generally will operate normally for
much potential difference there is between the two ground points. By
a few flashes before going back into self-ionization.
isolating the audio grounds from the airplane ground at the speaker,
ANY OF THE ABOVE MENTIONED CONDITIONS ARE REASONS head phone and microphone junctions, and grounding the aforemen-
FOR REPLACEMENT OF THE XENON FLASH TUBE. tioned with the radio at one central ground point, will eliminate the
NOTE: Installing one new flash tube in any multi-head strobe light majority of all ground inducted radio noise.
system, will sometimes cause the remaining old flash tube to misfire Do not parallel any audio leads with any power lead supplying ener-
or skip. This signifies that the old flash tube is nearing the end of it’s gy to a noise generator; (i.e.) alternator, electric motor or DC chop-
service life. However, to check the questionable flash tube, install it pers such as inverters and strobe light power supplies.
in a system and apply a reduced voltage, approximately 20 percent,
The interconnecting cable between the power supply and the
to the input to the power supply. If the flash tube will operate at this
remote strobe light head assembly radiate very little, for the output
reduced level, it still has a great deal of service life in it.
circuit of the power supply is very low impedance. They can radiate
RF like an antenna if the shield is not terminated to ground. The radi-
WHELEN’S (CometFlash® “CF” Strobe Light System) ation of RF energy is reduced to a minimum by properly terminating
the shield at one end or the other, generally the power supply end,
consists of four high energy pulses per burst of light, 45
but which ever proves the quietest ground. Do not terminate both
bursts of light per light. ends.
When installing a strobe light system, provide a good ground and
a low impedance source to the strobe light power supply. Eliminate
NOTE: Whelen Engineering does not recommend attempting to
ground loops in audio circuits by using a centrally located ground
repair their strobe light power supplies in the field. It is recommend-
point for all audio grounds.
ed to take advantage of our 24-hour Repair Service.
Whelen Engineering has available RF shielded flash tubes and
strobe light head assemblies to suppress the trigger pulse or clicking
sometimes heard in the radios.
If noise problems persist, and the procedures described have not
cleared them up, please contact the Whelen Engineering Company
for assistance.

16
 INTERMIXING ANTI-COLLISION
STROBE LIGHT SYSTEM EQUIPMENT
OBSERVE COLOR AND PIN NUMBERS. CABLES CONNECTING REMOTE
POWER SUPPLY TYPE STROBE LIGHTS MUST BE CONNECTED CORRECTLY!
Whelen Engineering and Aero-flash wiring Grimes and SDI (Hoskins) wiring between
between light assemblies and remote light assemblies and remote power sup-
power supplies are identical as pictured plies are identical as pictured below.
below. CLIP
FIG. 21.
FIG. 20. SHIELD
CLIP
SHIELD K
AC
BL
E
E IT
T WH
HI
W
K
AC
BL
RED

Both Grimes and SDI sometimes use MS

RED
(Cannon Type) connectors:
A = RED (Anode), B = White (Trigger),
C = Black (Ground)

CAUTION: WIRING SEQUENCE VARIES BETWEEN COMPARABLE EQUIPMENT MADE BY

DIFFERENT COMPANIES. WHEN INTERMIXING ANTI-COLLISION STROBE
LIGHT SYSTEM EQUIPMENT, MAKE SURE TO CHECK WIRE COLOR AND TO
CONNECT RED TO RED, WHITE TO WHITE, BLACK TO BLACK.

WHELEN STROBE
CAUTION SYSTEM TESTER
THE WHELEN STROBE LIGHT
POWER SUPPLY IS A HIGH
VOLTAGE DEVICE. DO NOT
REMOVE OR TOUCH TUBE
ASSEMBLY WHILE IN OPERA-
TION. WAIT 5 MINUTES
AFTER TURNING OFF POWER A strobe system tester designed to determine the reason the strobe
light system is not working properly. This kit contains an instruction
BEFORE STARTING WORK. sheet and a trouble shooting procedure sheet. Test power supplies
and interconnecting cables. It also comes with an adapter for testing
Grimes and Hoskins strobe light systems.

© 1999 Whelen Engineering Company, Inc.

17
 PARTS BREAKDOWN - AIRCRAFT STROBE BEACONS
* PARTS OUT OF PRODUCTION (AVAILABLE ON SPECIAL REQUEST). A457B-D-H Radio Shielded Tail Light Lens Assembly
** PARTS REPLACED BY NEW PRODUCTION COMPONENTS. for Horizontal Mounting.
# H102 OR H103 MOUNTING ADAPTER IS REQUIRED.
* A469A Xenon Strobe Flash Tube Assembly.
A402A Red Optic Lens. A469B Xenon Strobe Flash Tube Assembly.
A402A White Optic Lens. A469D Radio Shielded Xenon Strobe Flash
A402A Split Red/White Lens. Tube Assembly.

* A406 Strobe Xenon Flash tube Assembly, A469-D-K Radio Shielded Kit for A469A.
replaced by A469. # A470A-R or W Strobe Light Head Assembly, Red or
01-0450685-00 Clamp Ring Assembly. White Lens.

** A413A,HDA,DF-14/28 HDA,DF Strobe Light Power Supply. Replaced by # 470A-R/W Strobe Light Head Assembly with Split
A413A,HDACF Red/White Lens.

A413A,HDA,CF-14/28 HDA,CF Strobe Light Power Supply ** A490,T,DF-14/28 HT Strobe Power Supply. Replaced by
A490,T,CF-14/28
A417-1 Interconnecting cable.
** A490,TC.DF-14/28 HT-C Strobe Power Supply. Replaced by
A424 Tail Strobe Light Mounting Cup. A490TC,CF-14/28
A425 Tail Strobe Light Lens Retainer. ** A490A,TS,DF HTS Strobe Power Supply. Replaced by
A425A-V Tail Strobe Light Lens Retainer Mask for A490A,TS,CF
A500A, Vertical mounting. A490A,TS,CF HTS-CF Strobe Power Supply.
A425A-H Tail Strobe Light Lens Retainer Mask for A500A Tail Position and Strobe Light Head, Specify
A500A, Horizontal Mounting. voltage, vertical or horizontal mounting.
* A426 Wingtip Strobe Light Lens Retainer. A504 Disc Lamp Socket for A555A.
* A427 Wingtip Strobe Xenon Flash Tube. A506 Strobe Xenon Flash Tube and Socket
A427-4 Rubber Pad Spacer. Assembly for A500A.

* A428 Wingtip Strobe Light Lens. A507 Lamp Socket Assembly for A555A.

* A428-C Wingtip Strobe Light Radio Shielded Lens. A508-14 or 28 Halogen Lamp for A500A, A555A, A600.

* A428-D Wingtip Strobe Light Radio Shielded Lens, A555A V or H Tail Position Light Head Assembly,Specify
plus A426 Retainer Assembly. voltage, vertical or horizontal mounting.

** A429 Wingtip Strobe Light Head Assembly, A600-PG or -PR Wingtip Strobe Light Head with forward
replaced by A650. and Tail Position Light. Specify voltage.

** A429-PG or -PR Wingtip Position and Strobe Light Head, A605 Base Plate Assembly.
replaced by A650-PG and -PR. A606 Retainer.
A430 Tail Strobe Light Head Assembly. A610 Strobe Xenon Flash tube Assembly.
A435 Tail Strobe Xenon Flash Tube Assembly. A612 Lens for A625.
A436 Tail Strobe Light Gasket. A612-D Lens Retainer Assembly (Radio Shielded).
A438 Lens Masking Strip. A615 Lens for A600 Tail Light.
A440 WRM-65 Mounting Flange, A616 Gasket for A600 Tail Light.
3-3/4 inches diameter for HR,SA.
A626 Retainer Lens.
A441 AMP 3 Position Pin Connector with 3 Pins.
A626-D Lens Retainer Assembly (Radio Shielded).
A442 AMP 3 Position Socket Connector with
3 Sockets. A650 Wingtip Strobe Light Head Assembly.

M441 Molex 3 Position Pin Connector with A650-PG or -PR Wingtip Position and Strobe Light Head.
3 Pins for Piper Installation. Specify voltage of position light.

M442 Molex 3 Position Socket Connector with H102 “B” Mounting Adapter.
3 Sockets for Piper Installation. H103 “A” Mounting Adapter, 3-3/4 inch diameter.
A443 AMP Connector T3 Jumper Plug. ** HR,DF 200-14/28 HR or SA Strobe Power Supply. Replaced
A444 AMP 2 Position Pin Connector with 2 Pins. by HR,CF 200-14/28

M444 Molex 2 Position Pin Connector with HR,CF 200-14/28 HR or SA Strobe Power Supply.
2 Pins for Piper Installation. SA402 Lens Assembly for SA and A450.
A446 AMP 2 Position Socket Connector SA406 Strobe Xenon Flash Tube Assembly for
Housing with 2 Sockets. SA and A450.
# A450 Strobe Light Head Assembly. SA418-2 Gasket 1/32 inch for SA and A450.
A455 Gasket. W1282 Forward Position Light Lens Retainer.
** A456 A460 Tail Position Light Socket and W1283 Forward Position Light Gasket.
strobe light Assembly, replaced by A506.
W1284-R or G Forward Position Light Lens, Red or Green.
A457A Tail Light Lens for A500A and
A555A. W1285-PR or -PG Forward Position Light Assembly,
Red or Green. Specify voltage.
A457A-D Radio Shielded Tail Light Lens Assembly
for A500A. W1285-2 Forward Position Light Base.
A457B-D-V Radio Shielded Tail Light Lens Assembly W1290-14 or 28 Forward Position Lamp. Specify voltage.
for Vertical Mounting.

18 A copy of the famous Whelen warranty regarding products described on these pages may be obtained free of charge from the Whelen Engineering Company, Inc., Chester, Connecticut 06412.
© 1999 Whelen Engineering Company, Inc.
 PARTS NOT ILLUSTRATED ARE OUT OF PRODUCTION
(CONTACT WHELEN ENGINEERING CO., INC).

A628
A425 A425A
A425A

A457A-D A457B-D A628-D

OPTIONAL OPTIONAL OPTIONAL

A457A A457A A612 SA402

A457A

A402A- ( )
A455 01-0450685-00
A455
A455 01-0450685-00
A629
A508
A508

A435 A507
SA418-2
A506
A627
A467
A504

A441 SA406
A424
SA469B
FIGURE 22 A441
A441 A444
A430
FIGURE 23
FIGURE 25 A441 A441
A500A A444
IMPORTANT NOTE: A625 FIGURE 26 FIGURE 27
When ordering models A500A and A555A, A450 A470A
or lens assembly part number A457B-D, FIGURE 24
make sure to SPECIFY HORIZONTAL A555A
OR VERTICAL.
REF. Page 10
of this manual.

W1282
A626 A626
A606

A612-D A626-D A626-D

OPTIONAL OPTIONAL OPTIONAL
W1284

W1284
W1284
A612 A612 A612
W1283

W1283
W1283 A610 A610
A610

W1290 W1290
W1290
A507
A427-3 A427-3
A427-4
A508

A616
A605 W1285-2

W1285-2
A441 A441
A441
A615
FIGURE 28 FIGURE 29 FIGURE 30 FIGURE 31
A600-PR A650-PR A650 W1285-PR
A600-PG A650-PG W1285-PG

© 1999 Whelen Engineering Company, Inc.

19
CONTINUED PAGE 2.
Limitations and Conditions (Cont’d): 6. The approval of this change in type design applies basically to aircraft listed on the
attached eligibility list. This approval should not be extended to other aircraft of these
2. Install the following placard Whelen Part No. A421, or other FAA approved equivalent: models on which other previously approved modifications are incorporated unless it is
“WARNING TO AVOID OPTICAL ILLUSION AND SEVERE VERTIGO, TURN redetermined by the installer that the interrelationship between this change and any of
ANTI-COLLISION LIGHTS OFF UPON ENTERING CLOUDS, FOG OR HAZE.” those other previously approved modifications will introduce no adverse effect upon
the airworthiness of the aircraft. This determination should include a night flight check
3. Minimum required operating voltage is 13.2 volts for 14 volt systems. as specified in AC 43.13-2, Chapter 4, Paragraph 42a.
Minimum required operating voltage is 26.4 volts for 28 volt systems.
NOTE: Aircraft whose application for type certificate was made before April 1. 1957, may,
4. The aircraft listed on the eligibility list are those which have had both the physical but need not, comply with the field of coverage requirements of FAR 23 (27).1401(b).
installation of the lights substantiated and the field of coverage checked including the Compliance with Far 91.33(c) may not be shown provided the light installation is in accor-
20” mask. Aircraft not included in the list can use these lights when the physical dance with data approved prior to August 11, 1971, and applicable criteria of Advisory
installation and field of coverage is substantiated as indicated in; Whelen’s Installation Circular 43.13-2 are met.
and Service Manual for Whelen Aviation Anti-Collision Strobe Light Systems dated
November 7, 1972, in the portion entitled “Aircraft Not Specifically Mentioned on the
Eligibility List”.
5. HD or HD, power ;supplies may be used in; place of an HS or HD power supply
respectively in order to also provide power for other Whelen strobe lights installed in
accordance with STC SA800EA. The preceding is a statement of compatibility of power
supplies only. Refer to STC SA800EA for installation of the other Whelen Strobe Lights
acceptable in combination with this STC.

20
CONTINUED PAGE 2 AND 3.
c. A408W and 470W with power supplies approved under STC SA615EA meet 4. On all helicopter installations, install the following placard in view of the pilot:
FAR 23.1401 (f) effective August 11, 1971.
“THE WHITE STROBE LIGHT MUST BE TURNED OFF DURING ALL NIGHT
d. A650 or A625 with power supplies producing a minimum of 20 joules per flash TAKEOFFS AND LANDINGS.”
meets FAR 23.1401 (f) effective August 11, 1971.
5. The modification approved by this STC can be installed in conjunction with those
2. To complete the approval of those lights as anti-collision light systems, the installation approved by STC SA615EA or STC SA738EA as delineated in the “Installation and
on individual aircraft must be checked to show compliance with FAR 23.1401(b) (Field Service Manual for Whelen Anti-collision Strobe Light System’s”
of Coverage); unless the “Installation and Service Manual for Whelen Anti-Collision
Strobe Light Systems”, dated 28 September 1978 specifically indicates that a particular 6. On Mitsubishi MU-2B, MU-2B-10, -20, -15, -30 aircraft: Whelen’s “Mitsubishi MU-2B,
installation has been checked for compliance with the aforementioned sub-section -10, -20, -15, -30 Wing Tip and Tail Strobe Light Installation Procedure”, dated
(Example: Bell 206A with lights installed at he specified locations). 19 February 1971, is required in addition to the “Installation and Service Manual for
Whelen Anti-Collision Strobe light System”.
NOTE: The aforementioned installation and Service Manual contains an acceptable
method for checking the adequacy of coverage when using two lights (wing-tip) or three 7. This approval should not be incorporated in any aircraft of these specific models on
lights (wing tips and tail lights). For some other acceptable methods see Advisory which other approved modifications are incorporated, unless it is determined that the
Circular AC 43.13-2 Chapter 4 Paragraph 46b(2). Installation made in accordance with interrelationship between this change and any of those previously incorporated
STC SA800EA Amendments prior to 9/14/71 need only be checked for obstructed approved modifications will not introduce any adverse effect upon the airworthiness of
visibility to meet anti-collision light requirements. the aircraft. This determination should include a night flight check as specified in AC
43.13-2 Chapter 4, Paragraph 42A.
3. Install the following placard, Whelen Part No. A421-1, or other FAA approved
equivalent, in view of the pilot: NOTE: Aircraft whose application for type certification was made before April 1, 1957, may,
but need not, comply with the field of coverage requirements of FAR 23(27).1401(b).
“WARNING TURN OFF STROBE LIGHTS WHEN TAXING IN VICINITY OF OTHER Compliance with FAR 91.33(c) may be shown provided the light installation is in accor-
AIRCRAFT OR DURING FLIGHT THROUGH CLOUDS, FOG OR HAZE. STANDARD dance with data approved prior to August 11, 1971, and applicable criteria of Advisory
POSITION LIGHTS TO BE ON FOR ALL NIGHT OPERATIONS.” Circular 43.13-2 are met.

1999 Whelen Engineering Company, Inc.

21
 (THIS IS A COMBINED REPRINT OF TWO STC.)
CONTACT WHELEN ENGINEERING COMPANY, INC. FOR THE LATEST ELIGIBILITY LIST.
NOTE: This eligibility list is for reference only. Whelen’s PMA hardware can be installed on any aircraft using
approved techniques and procedures found in this manual, and appropriate advisory circulars.
United States of America
Department of Transportation - Federal Aviation Administration

Supplemental Type Certificate

(Continuation Sheet)

Number SA615EA SA800EA

Date Amended: June 18, 1999

ELIGIBILITY LIST
The following aircraft have been approved for installation of the Whelen H Series (HS, HD, HR, HD, T, HT, AND SA-14 or -28 volt) Aviation
Red or Aviation White Anti-Collision Strobe Light Systems,. Aircraft identified by ## are not included on STC SA615EA Eligibility list.
June 18, 1999

AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE

AERO COMMANDER 100. 100-180 1A21

111 A11SO

112 A12SO

500, 500-A, -B, -S, -U, 520, 560, 560A, 560E 6A1

560F, 680, 680E, -F, 720, 680FL, 680FL(P), 680T, V, W, 681, 690, 685 2A4

AMERICAN AVIATION AA-1, *AA-1A A11EA

AA-5 A16EA

BEECH 23, A23, A23A, A23-19, -24, -19A, B19, M19A, B23, C23, A24, A24R, C24R A1CE

35, A35, B35, C35, D35, E35, F35, G35, 35R A-777

H35, J35, K35, M35, N35, P35, S35, V35, V35A, V35B, 35-33, 35-A33, 35-B33, 35-C33, 35-C33A, 36, A36,
E33, E33A, E33C, F33, F33A, F33C 3A15

50(L-23A), B50(L-23B), C50, D50(L-23E), D50A, D50B, D50C, D50E, E50(L-23D, RL-23D), F50, G50, H50, J50 5A4

95-55, 95-A55, 95-B55, (T45A) 95-B55D, 95C55, 95, B95, B95A, D95A, E95, D55, D55A, E55, E55A, 56TC,
A56TC, A56TC,58 3A16

65(L23F), A65, A65-8200, 65-8200, 65-80, 65-A80-8800, 65-B80, 65-88, B90, 65-90, 65-A90, 65-A90-1,
(U21A, RU-21A, RU-21D), E90, 65-A90-2, (RU-21B), 65-A90-3 (RU-21C), 70 3A20

60, A60 A 12CE

99, 99A,100, 200 A14CE

BELLANCA 14-19-3A, 17-30, 17-30A, 17-31A, 17-31ATC 1A3

7EC, 7ECA, 7FC, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7JC, 7KCAB A-759

BELL 206A, 206B, 206L, 206L-1, 206L-3, 206L-4, 407 H2SW

47B, B3, D, D1, E, G, G-2, H1 H-1

47G-2A, -2A-1, -3, -3B, -3B1, -3B-27, -4, -4A, -5, -5A 2H3

47J, K, J-2, J-2A 2H1

BRITTEN NORMAN BN-2, -2A, -2A-2, -2A-6, -2A-8 A17EU

BN-2A, MK.III A29EU

CESSNA 120, 140 A-768

##140A 5A2

150, 150A, B, C, D, E, F, G, H, J, K, L, M, A150K, A150L, A150M, 152, A152 3A19

##170, 170A, 170B A-799

172, 172A, B, C, D, E, F, G, H, I, K, L, M, N, P, P172D, R172K 3A12

22
AIRCRAFT MANUFACTURER MODEL TYPE CERTIFICATE
CESSNA (continued) P172D, 172RG, 175, 175A, B, D 3A17

177, 177A, B A13CE

177RG A20CE

180, 180A, B, C, D, E, F, G, H, J, K 5A6

182, 182A, B, C, D, E, F, G, H, J, K, L, M, N, P, Q, R, T182, R182, TR182 3A13

185, 185A, B, C, D, E, A185E, A185F 3A24

188, 188A, B, A188, A188A, A188B, A188C A9CE

##190, 195, 195A, B A-790

206, P206, P206A, B, C, D, E, TU206A, B, C, D, E, F, G, TP206A, B, C, D, E, U206, U206A, B, C, D, E, F, G A4CE

207, 207A, T207, T207A A16CE

210, 210A, B, C, D, E, F, G, H, J, K, L, N, T210F, G, H, J, K, L, M, N, 210-5(205, 210-5A(205A), 210-5A, P210N 3A21

310, 310A, B, C, D, E, F, G, H, I, J, 310J-1, E310J, 310K, L, N, P, 310Q, T310P, Q, 310R 3A10

*320, 320A, B, C, D, E, F, 320-1, 340, 340A 3A25

*336 A2CE

337, 337A, B, C, D, E, F, T337D, E, F, G A6CE

*401, 401A, B, 402, 402A, B, 411, 411A, 421, 421A, 414, 421B A7CE

DeHAVILLAND OF CANADA DHC-2 MK.I, MK.II, MK.III A-806

DHC-3 A-815

DHC-6, Models 1, 100, 110, 200, 210, 300 A9EA

FAIRCHILD HILLER FH-1100 H2WE

GRUMMAN ##G-164, G-164A, G-164B 1A16

HELIO H-250, H-295, H-391, H-391B, H-395, H-395A 1A8

HUGHES 269A, B, C, 269A-1 4H12

369, 369A, H, HM, HS, HE H3WE

PIPER PA-11 A-691

PA-12 A-780

PA-14 A-797

PA-15 A-800

PA-16 1A1

PA-17 A-805

PA-18 Series, PA-19 1A2

PA-20 1A4

PA-22 Series 1A6

PA-25 Series 2A8

PA-23, PA-23-160. *PA-23-235, *PA-23-250, *PA-E23-250 1A10

PA-24-180, PA-24, -24-250, -24-260, -24-400 1A15

PA-28-140, -28-150, -28-151, -28-160, -28-161, -28-180, -28-235, -28S-160, -28R-180, -28S-180, -28-181,
-28R-200, -28R-201, -28R-201T, -28RT-201, -28RT-201T, -28-201T, -28-236 2A13

PA-30, PA-39, 151, 161 A1EA

PA-31P A8EA

PA-31, PA-31-300, 325, 350 A20SO

PA-32-260. -300, PA-32S-300, R300, R301T A3SO

MOONEY ##M20B, C, D, E, F, G, J, K, L, M 2A3

MITSUBISHI ##MU-2B, MU-2B-10, -15, -20, -30 A2PC

UNIVAIR (STINSON) ##108, 108-1, -2, -3, -5 A-767

NOTES TO ELIGIBILITY LIST:

* Aircraft as marked require specific attention to proper balancing of the rudder. Refer to the Manufacturer’s Service Manual for balancing instructions.

© 1999 Whelen Engineering Company, Inc.

23
 ®

ENGINEERING COMPANY, INC.

ROUTE 145, CHESTER, CT 06412-0684

PHONE: (860) 526-9504
FAX: (860) 526-2009

11051A-092499 REV 1 © 1999 Whelen Engineering Company, Inc.