DSHW-2024-005412

DEPARTMENT OF THE ARMY
TOOELE ARMY DEPOT/HEADQUARTERS
1 TOOELE ARMY DEPOT, BUILDING 1
TOOELE, UT 84074-5003
March 20, 2024
Subject: PROPULSION SECTION GM WPU-6B TACTICAL (AMRAAM) Treatability Study,
Tooele, Utah, EPA# UT3213820894
Doug Hansen
Director of the Utah Department of Environmental Quality
Division of Waste Management and Radiation Control
ATTN: Gabrielle Marini ck
195 North 1950 West
Salt Lake City, UT 84114-4880
Dear Mr. Hansen:
In accordance to Utah Admin Code R3 l 5-261.4(t).1, Tooele Army Depot North Area (TEAD-N)
is notifying you no less than 45 days before it intends to conduct a treatability study. The
installation will be performing a treatability study at the Rocket Static Fire Range to develop a
secondary ignition system to treat Propulsion Section GM WPU-6/B Tactical (AMRAAM)
rocket sections. Enclosed is a detailed description of the treatability study.
I certify under penalty oflaw that this document and all attachments were prepared under my
direction or supervision according to a system designed to assure that quality personnel properly
gather and evaluate the information submitted. Based on my inquiry of the person or persons
who manage the system, or those persons directly responsible for gathering the information, the
information submitted is, to the best of my knowledge and belief, true, accurate, and complete. I
am aware that there are significant penalties for submitting false information, including the
possibility of fine and imprisonment for knowing violations
Should you have any questions regarding this matter, please contact myself at (435) 833-
2526.
Sincerely,
Lonnie Brown
Chief, Environmental Management Division
Enclosures
TREATABILITY STUDY
DEMIL STUDY-Develop a secondary ignition system to treat PROPULSION SECTION GM
WPU-6/B TACTICAL (AMRAAM) at the TEAD North Area (N) static fire pad.
TEST PURPOSE:
The Directorate of Industrial Operation at Tooele Army Depot (TEAD), Utah, is tasked to
develop a secondary ignition system to treat PROPULSION SECTION GM WPU-6/B
TACTICAL (AMRAAM) rocket sections at TEAD's North Area (N) static fire pads.
OBJECTIVES:
TEAD-N treated the PROPULSION SECTION GM WPU-6/B TACTICAL (AMRAAM) during
normal operations and found that the rocket sections had a delayed ignition causing it to be
wedged inside the rocket carousels. In doing so, cause damaged to the rocket carousel making it
unusable as shown in figure 1.
Figure 1-Damaged to the Rocket Carousel
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MUNITION DESCRIPTION:
PROJECT DESCRIPTION:
TEAD-N contacted the manufactures, which they came up with a solution of placing 1 pounds of
HC-25FS propellent into a cheesecloth (100% cotton bag) and placing 1 cheesecloth inside the
front part of the rocket section. Then place the insulated forward plug on the front as shown in
Figure 2.
Figure 2-Configuration of the Front Section
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Next place 1 pounds of HC-25FS propellent into a cheesecloth (100% cotton bag) and place 1
cheesecloth inside the back part of the rocket section as shown in Figure 3. Finaly, connect all
the wiring for the electronic initiators.
Figure 3-Configuration of the Back Section
Verify everything is correct, then place the rocket section into the carousel and ignite the section.
CHARACTERIZATION DATA
The Propellant/Explosive/Pyrotechnic (PEP) components are derived from the MIDAS PEP
Summary Reports and are listed below in Table la and Table lb.
PROPULSION SECTION GM WPU-6/B (AMRAAM) PEP LBSPER
SUMMARY ROCKET
Butylated hydroxytoluene 0.000185
AMMONIUM PERCHLORATE 82.701087
BORON 0.000134
CALCIUM STEARA TE 0.000004
COBALT NAPHTHENATE 0.00000001
DI(2-ETHYLHEXYL)ADIPA TE 3.309272
DIBETANAPHTHYLPARAPHENYLENE 0.186250
DITRIDECYL THIODIPROPIONATE (P-711) 0.000093
IRON OXIDE 0.000278
GRAPHITE 0.000001
Hexamethylene diisocyanate 0.403995
HTPB (HYDROXYL TERMINATED POL YBUTADIENE) 6.243768
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LAMINAC 4116 0.000009
LEADAZIDE 0.000236
METHYL ETHYL KETONE PEROXIDE 0.00000001
METHYL ETHYL KETONE 0.00000001
2,2'-METHYLENEBIS(4-METHYL-6-TERT-BUTYLPHENOL) 0 .000046
N-BIS B-HYDROXYETHYL GL YCOLAMIDE (BHEGA) 0.004110
HTPB (HYDROXYL TERMINATED POL YBUTADIENE) 0.000458
POLYISOBUTYLENE 0.000001
POLYESTER RESIN 0.000022
POTASSIUM NITRATE 0.000399
POTASSIUM PERCHLORATE 0.000009
RDX 3.725334
SILICON CARBIDE 0.74500
TEPANOL 0.000093
ZIRCONIUM 0.000009
Table la-PEP Components of the Rocket Section
PROPELLENT FROM 30MM AMMO PEP SUMMARY 1 LBS BAG
2-NITRODIPHENYLAMINE 0.00009
DETERRENT COATING 0.03895
DIBUTYLPHTHALATE 0.03267
DIPHENYLAMINE 0.00765
GRAPHITE 0.00302
NITROCELLULOSE 0.64203
NITROGEN 0.13017
NITROGLYCERIN 0.08544
POLYESTER ADIP A TE 0.03900
POTASSIUM NITRATE 0.02092
Table lb-PEP Components of the Propellent from the 30MM
OBJECTIVES:
Performing these tests will determine if adding propellent to both the front and back end will
allow for a clean bum. If the rocket section detonates or does not properly burn, then the test will
be unsuccessful and TEAD will have to go back to the drawing board to come up with another
solution.
TEST LOCATION:
The TEAD-N Static Fire Pad
TEST DATE:
Proposed dates for this test are from June-August 2024.
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TEST QUANTITIES:
NUMBER WEIGHT OF TOTAL
PER EACH TEST PEP
MUNITIONS TESTED (lbs) (lbs)
PROPULSION SECTION
GMWPU-6/B 9 97.32 875.7
TACTICAL (AMRAAM)
Propellent from 30MM 18 1 18
Table 2-Test Quantities
This Treatability Study will destroy approximately 893.7 lbs (405.4 kg) of non-acute hazardous
waste (see Table 2). This is below the 2,200 lbs (1000 kg) limit allowed by the Treatability
Study Exemption Rule 40 CFR 261.4 (e)-(f). As shown in Table 4, no more than 550 lbs (250
kg) of"as received" hazardous waste will be subject to initiation of treatment in a single day as
required by 40 CFR 261.4 (f)(3). To avoid the air modeling requirement established in the Air
Order, TEAD will only test one rocket section an hour making it less than 200 lbs an hour.
STATIC FIRE OPERATING CONDITIONS:
The Static Fire Range will be conducted under safe operating condition, but due to the weather
condition always changing and the sensitivity of the test TEAD is not going to operate in weather
restriction established by the RCRA Permit but still be restricted to no more than 550 lbs (250
kg) a day and one rocket section per hour.
WASTE DISPOSAL:
The ash collected from the test will be treated as hazardous waste pending results of the analysis.
Ash samples will be drawn and analyzed to determine a suitable disposal method. The ash will
be collected into marked containers and delivered to the 90-day collection yard pending
appropriate disposal procedure. The remaining material will be sent off to be recycled.
GOALS AND EXPECTATIONS ;
From this activity we will determine if the items described herein can be safely processed at a
sustained production rate using Static Fire and to determine what proper parameters will be used
to provide a viable option for destruction oflisted components.
EMISSON GENERA TED
Table 3a shows the emission generated from burning the 1 lb bags of 30 mm propellent during
the test. Table 3b shows the emission generated from burning the rocket sections described
above. Table 3c is the combined emissions generated during the test.
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PROPELLENT PEP EMISSON IN LBS NUMBER TOTAL EMISSON IN
COMBUSTION GENERA TED FROM BAGS OF LBS GENERA TED
PRODUCT 1 LB BAG OF PROP. PROP. USED DURING TEST
Particulate Matter 0.015 18 0.26
NOx 0.24 18 4.33
Table 3A-Shows the emission generated from burning the 1 lb bags of 30 mm propellent.
(Source: Generated from modifying the furnace feed rate model assuming no pollution abatement system )
EMISSON IN LBS NUMBER OF TOT AL EMISSON
ROCKET SECTION GENERATED ROCKET IN LBS
PEP COMBUSTION FROM 1 ROCKET SECTION GENERATED
PRODUCT SECTION USED DURING TEST
Particulate Matter 93 .60 9 842.38
Chlorine 24 .96 9 224.60
Semi-volatile metals 0.00168 9 0.0015
NOx 11.35 9 102.16
SOx 5.49E-06 9 4 .94E-05
Hazardous Air Pollutants l.68E-08 9 l.51E-07
Table 3b-Shows the emission generated from burning the rocket sections
(Source: Generated from modifying the furnace feed rate model assuming no pollution abatement system )
EMISSONLBS EMISSON LBS TOT AL EMISSON
GENERATED GENERATED IN LBS
TOTAL PEP FROM ROCKET FROM GENERATED
COMBUSTION SECTION TEST PROPELLENT DURING TEST
PRODUCT TEST
Particulate Matter 842 .38 0.26 842.64
Chlorine 224.60 0 22 4.60
Semi-volatile metals 0.0015 0 0.0015
NOx 102.16 4.33 106.49
SOx 4.49E-05 0 4.94E-5
Hazardous Air Pollutants 1.51E-07 0 1.51E-7
Table 3c-The combined emissions generated during the test.
PROPOSED TESTING SCHEDULE
The testing will be accomplished in 4 days . The first day will be a set up process to review
procedures and operations. Then later that day at least one rocket will be tested. Then a review
will be done on the effectiveness of the secondary ignition system. This will be continued into
the next day until a max of 3 rockets section are ignited daily. The fourth day is established as a
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contingency test day so if the other days could not process their daily quota, then this will be
makeup day up to 3 rocket sections as shown in Table 4.
Max Allowed Waste
Day/Stage Total Weight Waste Exceeding
Items Processed Allowed
(lbs.) (lbs.) (lbs.)
Day 1 Safety Feed ~3 305 550 0
Day 2 Safety Feed ~3 305 550 0
Day 3 Feed Recipe ~3 305 550 0
Day 4 Feed Recipe ~3 305 550 0
Table 4-Proposed Testing
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