[Code of Federal Regulations]
[Title 10, Volume 1]
[Revised as of January 1, 2004]
From the U.S. Government Printing Office via GPO Access
[CITE: 10CFR32.101]
[Page 535-538]
TITLE 10--ENERGY
CHAPTER I--NUCLEAR REGULATORY COMMISSION
PART 32--SPECIFIC DOMESTIC LICENSES TO MANUFACTURE OR TRANSFER CERTAIN
ITEMS CONTAINING BYPRODUCT MATERIAL--Table of Contents
Subpart B--Generally Licensed Items
Sec. 32.101 Schedule B--prototype tests for luminous safety devices
for use in aircraft.
An applicant for a license pursuant to Sec. 32.53 shall conduct
prototype tests on each of five prototype luminous safety devices for
use in aircraft as follows:
(a) Temperature-altitude test. The device shall be placed in a test
chamber as it would be used in service. A temperature-altitude condition
schedule shall be followed as outlined in the following steps:
Step 1. The internal temperature of the test chamber shall be
reduced to -62 C. (-80 F.) and the device
shall be maintained for at least 1 hour at this temperature at
atmospheric pressure.
Step 2. The internal temperature of the test chamber shall be raised
to -54 C. (-65 F.) and maintained until
the temperature of the device has stabilized at -54 C. at
atmospheric pressure.
Step 3. The atmospheric pressure of the chamber shall be reduced to
83 millimeters of mercury absolute pressure while the chamber
temperature is maintained at -54 C.
Step 4. The internal temperature of the chamber shall be raised to -
10 C. (+14 F.) and maintained until the
temperature of the device has stabilized at -10 C., and
the internal pressure of the chamber shall then be adjusted to
atmospheric pressure. The test chamber door shall then be opened in
order that frost will form on the device, and shall remain open until
the frost has melted but not long enough to allow the moisture to
evaporate. The door shall then be closed.
Step 5. The internal temperature of the chamber shall be raised to
+85 C. (185 F.) at atmospheric pressure.
The temperature of the device shall be stabilized at +85
C. and maintained for 2 hours. The device shall then be
visually inspected to determine the extent of any deterioration.
Step 6. The chamber temperature shall be reduced to +71
C. (160 F.) at atmospheric pressure. The
temperature of the device shall be stabilized at +71 C.
for a period of 30 minutes.
Step 7. The chamber temperature shall be reduced to +55
C. (130 F.) at atmospheric pressure. The
temperature of the device shall be stabilized at this temperature for a
period of 4 hours.
Step 8. The internal temperature of the chamber shall be reduced to
+30 C. (86 F.) and the pressure to 138
millimeters of mercury absolute pressure and stabilized. The device
shall be maintained under these conditions for a period of 4 hours.
Step 9. The temperature of the test chamber shall be raised to +35
C. (95 F.) and the pressure reduced to 83
millimeters of mercury absolute pressure and stabilized. The device
shall be maintained under these conditions for a period of 30 minutes.
Step 10. The internal pressure of the chamber shall be maintained at
83 millimeters of mercury absolute pressure and the temperature reduced
to +20 C. (68 F.) and stabilized. The
device shall be maintained under these conditions for a period of 4
hours.
[[Page 536]]
(b) Vibration tests. This procedure applies to items of equipment
(including vibration isolating assemblies) intended to be mounted
directly on the structure of aircraft powered by reciprocating,
turbojet, or turbo-propeller engines or to be mounted directly on gas-
turbine engines. The device shall be mounted on an apparatus dynamically
similar to the most severe conditions likely to be encountered in normal
use. At the end of the test period, the device shall be inspected
thoroughly for possible damage. Vibration tests shall be conducted under
both resonant and cycling conditions according to the following
Vibration Test Schedule (Table I):
Vibration Test Schedule--Table I
[Times shown refer to one axis of vibration]
----------------------------------------------------------------------------------------------------------------
Vibration at 160 Vibration at -65
Vibration F. F.
Type at room (71 C.) (minutes) eq>C.) (minutes)
(minutes)
----------------------------------------------------------------------------------------------------------------
Resonance.................................................. 60 15 15
Cycling.................................................... 60 15 15
----------------------------------------------------------------------------------------------------------------
(1) Determination of resonance frequency. Individual resonance
frequency surveys shall be conducted by applying vibration to each
device along each of any set of three mutually perpendicular axes and
varying the frequency of applied vibration slowly through a range of
frequencies from 5 cycles per second to 500 cycles per second with the
double amplitude of the vibration not exceeding that shown in Figure 1
for the related frequency.
(2) Resonance tests. The device shall be vibrated at the determined
resonance frequency for each axis of vibration for the periods and
temperature conditions shown in table I and with the applied double
amplitude specified in Figure 1 for that resonance frequency. When more
than one resonant frequency is encountered with vibration applied along
any one axis, the test period may be accomplished at the most severe
resonance or the period may be divided among the resonant frequencies,
whichever is considered most likely to produce failure. When resonant
frequencies are not apparent within the specified frequency range, the
specimen shall be vibrated for periods twice as long as those shown for
resonance in table I at a frequency of 55 cycles per second and an
applied double amplitude of 0.060 inch.
[[Page 537]]
[GRAPHIC] [TIFF OMITTED] TC02OC91.056
(3) Cycling. Devices to be mounted only on vibration isolators shall
be tested by applying vibration along each of three mutually
perpendicular axes of the device with an applied double amplitude of
0.060 inch and the frequency cycling between 10 and 55 cycles per second
in 1-minute cycles for the periods and temperature conditions shown in
table I. Devices to be installed in aircraft without vibration isolators
shall be tested by applying vibration along each of three mutually
perpendicular axes of the device with an applied double amplitude of
0.036 inch or an applied acceleration of 10G, whichever is the limiting
value, and the frequency cycling between 10 and 500 cycles per second in
15-minute cycles for the periods and temperature conditions shown in
table I.
[[Page 538]]
(c) Accelerated weathering tests. The device shall be subjected to
100 hours of accelerated weathering in a suitable weathering machine.
Panels of Corex D glass shall surround the arc to cut off the
ultraviolet radiation below a wave-length of 2,700 angstroms. The light
of the carbon arcs shall fall directly on the face of the device. The
temperature at the sample shall be maintained at 50 C.
plus or minus 3 C. Temperature measurements shall be made
with a black panel thermometer.
(d) Shock test. The device shall be dropped upon a concrete or iron
surface in a 3-foot free gravitational fall, or shall be subjected to
equivalent treatment in a test device simulating such a free fall. The
drop test shall be repeated 100 times from random orientations.
(e) Hermetic seal and waterproof test. On completion of all other
tests prescribed by this section, the device shall be immersed in 30
inches of water for 24 hours and shall show no visible evidence of water
entry. Absolute pressure of the air above the water shall then be
reduced to 1 inch of mercury. Lowered pressure shall be maintained for 1
minute or until air bubbles cease to be given off by the water,
whichever is the longer. Pressure shall then be increased to normal
atmospheric pressure. Any evidence of bubbles emanating from within the
device, or water entering the device, shall be considered leakage.
(f) Observations. After each of the tests prescribed by this
section, each device shall be examined for evidence of physical damage
and for loss of tritium or promethium-147. Any evidence of damage to or
failure of any device which could affect containment of the tritium or
promethium-147 shall be cause for rejection of the design if the damage
or failure is attributable to a design defect. Loss of tritium or
promethium-147 from each tested device shall be measured by wiping with
filter paper an area of at least 100 square centimeters on the outside
surface of the device, or by wiping the entire surface area if it is
less than 100 square centimeters. The amount of tritium or promethium-
147 in the water used in the hermetic seal and waterproof test
prescribed by test paragraph (e) of this section shall also be measured.
Measurements shall be made in an apparatus calibrated to measure tritium
or promethium-147, as appropriate. The detection on the filter paper of
more than 2,200 disintegrations per minute of tritium or promethium-147
per 100 square centimeters of surface wiped or in the water of more than
0.1 percent of the original amount of tritium or promethium-147 in any
device shall be cause for rejection of the tested device.
[30 FR 8192, June 26, 1965]