Though injury assessment is not generally associated with the
shoulder, the way the shoulder absorbs energy can affect the overall
kinematics of the dummy. This test assures that the shoulder acts
uniformly in the way it distributes the load under a direct lateral
impact.
    The shoulder exposed to a pendulum impact at 3.6 m/s is to exhibit
a peak shoulder deflection between 16 mm and 21 mm, and a peak
resistance force between 1,240 N and 1,350 N.
Thorax Impact Tests
    The thorax qualification tests are very similar to the SAE test
used to assess lateral thorax biofidelity. For qualification, however,
the test is conducted two ways: Without arm interaction (as in the SAE
test) and with the arm attached such that the impact probe strikes the
upper arm. Both tests utilize a lateral impact with a 3.8 kg probe.
    The thorax ``without arm'' test assures uniformity of the thorax
structure, including its mount to the spine, and its response to a
direct impact in terms of rib deflection. The arm is completely removed
from the dummy. The 3.8 kg test probe is aligned with the thorax
displacement IR-TRACC and impacts the thorax laterally at a speed of
3.3 m/s.
    For the ``arm attached'' test, the upper arm is positioned
vertically and aligned with the dummy's thorax. The lower arm is
positioned to make a 90 degree angle with the upper arm. The loading of
the ribcage goes through the arm. The impact speed of the probe is 5.0
m/s. This test assures uniformity of the arm in the way it absorbs
energy and interacts with the thorax under a direct lateral impact.
    The thorax exposed to a pendulum impact:
     At 3.3 m/s, without arm, is to exhibit a peak thorax
deflection between 24 mm and 31 mm, and a peak resistance force between
620 N and 770 N; and,
     at 5.0 m/s, with arm attached, is to exhibit a peak thorax
deflection between 23 mm and 28 mm, and a peak resistance force between
1,380 N and 1,690 N occurring after 5 ms from time zero.
    As explained previously, the peak probe force is taken after 5 ms
to separate the probe's initial inertial response during arm contact
from its response due to its interaction with the thorax. The net
effect of recording the peak probe force after 5 ms is the elimination
of the first peak.
Lumbar Tests
    The rubber lumbar column bends to some extent during a CRS side
impact test. This bending might affect the overall kinematics of the
dummy, including the excursion of the head. It could also affect
lateral loads and the deflection of the thorax. We believe that this
rubber element can be a source of variability, so we have included a
qualification test to assure the uniformity and integrity of this
component.
    Lumbar testing would consist of two types of pendulum tests: A
frontal test and a lateral test. For both tests, the lumbar spine
element containing the flexible column is removed from the dummy,
similar to the neck qualification tests. Lumbar tests are conducted
using the same Part 572 neck pendulum and headform device utilized in
the neck qualification tests. In the case of lumbar qualification, the
headform is not intended to represent the inertial properties of any
particular body region, but merely provides an apparatus that helps to
ensure a repeatable test condition. The frontal and lateral pendulum
tests are conducted at the same impact speed of 4.4 m/s and specify the
same pendulum impulse.
    We propose that the lumbar spine must allow the headform to
articulate:
     In frontal flexion, at not less than between 48 degrees
and 57 degrees occurring between 52 ms and 59 ms from time zero and
decaying back to zero angle between 50 ms and 56 ms after the peak
rotation; the value of the maximum moment must be between 78 N-m and 94
N-m occurring between 46 ms and 57 ms from time zero; and,
     in lateral flexion, at not less than between 47 degrees
and 59 degrees occurring between 50 ms and 59 ms from time zero and
decaying back to zero angle between 47 ms and 59 ms after the peak
rotation; the value of the maximum moment must be between 78 N-m and 97
N-m occurring between 46 ms and 57 ms from time zero.
Pelvis Impact
    A lateral impact with the 3.8 kg probe at 4.0 m/s is used to test
the pelvis. This test protocol is very similar to the SAE biofidelity
test. The pelvis exposed to a pendulum impact at 4.0 m/s is to exhibit
a peak pubic load between 700 N and 870 N, and a peak force measured by
the pendulum between 1570 N and 1810 N.
Other
    We have not included a qualification test aimed specifically at the
Q3s abdomen. We tentatively believe that any non-uniformity in
stiffness due to the absence of a qualification requirement for the
abdomen would have an insignificant effect on the overall kinematics of
the dummy in a side impact test. Also, the abdomen of the Q3s is
uninstrumented and is thus not generally used to assess injury
potential in a side impact.
    Nevertheless, comments are requested on the need for a
qualification test for the abdomen. The abdomen is made of a high
density, compressible foam material, whose compressive characteristics
can vary from one abdomen to another and whose properties can change
with aging and other factors. We request comments on an abdominal test
protocol similar to that which we used to assess the biofidelity of the
Q3s abdomen.

VII. Durability

    No durability problems arose with the Q3s dummies in any of the
sled tests or component tests.

a. High-Energy Component Tests

    We also conducted high-energy component tests to assess durability
and no durability problems arose in those. In these tests, we raised
the kinetic energy of the impact to levels that exposed the dummy to
loading conditions slightly greater than those that might be

expected in the dummy's regulatory application. High-energy tests were
conducted for the head, neck, shoulder, thorax (with and without arm),
lumbar, and pelvis. As discussed below, we found no damage to the
dummy's structural components or instrumentation.
High-Energy Head Drop Tests
    We performed frontal and lateral head drop tests using the
qualification test setup procedures, except the drop heights were
increased to achieve kinetic energy increases of 10 percent, 20
percent, and 30 percent, as compared to the standard qualification
test.
    Frontal head drop responses are summarized in Table 18. The peak
resultant head acceleration at 30 percent increased energy was 318.5 g.
This impact resulted in a HIC15 value of 1732.5, which is well above
the proposed injury criterion limit of 700 and demonstrates the
severity of the test. Post-test inspection of the head revealed no
structural damage to the synthetic skull material or to the vinyl skin.
    Lateral head drop responses are summarized in Table 19. For the
most severe condition, the peak resultant head acceleration was 146.6
g. No structural damage of the head was observed in the post-test
inspection of the head assembly.

                             Table 18--High-Energy Frontal Head Drop Test Responses
----------------------------------------------------------------------------------------------------------------
                                                                      Energy
                                                                     increase       Drop height        Peak
                            Test No.                                 (nominal)         (mm)          resultant
                                                                     (percent)                       accel (g)
----------------------------------------------------------------------------------------------------------------
Baseline........................................................               0             376           265.5
1...............................................................              10             414           284.6
2...............................................................              20             451           304.4
3...............................................................              30             489           318.5
----------------------------------------------------------------------------------------------------------------

                             Table 19--High-Energy Lateral Head Drop Test Responses
----------------------------------------------------------------------------------------------------------------
                                                                      Energy
                                                                     increase       Drop height        Peak
                            Test No.                                 (nominal)         (mm)          resultant
                                                                     (percent)                      accel  (g)
----------------------------------------------------------------------------------------------------------------
Baseline........................................................               0             200           121.5
1...............................................................              10             220           127.3
2...............................................................              20             240           141.6
3...............................................................              30             260           146.6
----------------------------------------------------------------------------------------------------------------

High-Energy Neck Pendulum Tests
    We conducted frontal, lateral, and torsional neck pendulum tests at
the increased impact speeds. Tests were conducted according to the
qualification procedures, except for the increase in impact speeds.
    Frontal Flexion Tests. The results of the high-energy frontal neck
flexion tests are summarized in Table 20. Three repeat tests were run
at 5.5 m/s. This speed represents a 34 percent increase in energy over
the qualification speed. We chose this condition because it is
consistent with the test protocol used to qualify the HIII-3C (a
frontal impact dummy). We found no signs of damage or unusual wear to
the Q3s neck or neck cable at the elevated speed. The response curves
were smooth, indicating that no unusual contact occurred during the
tests. The tests also demonstrate that the Q3s neck would be repeatable
if the dummy were used in a frontal impact mode.
    Lateral Flexion Tests. The results of the high-energy lateral neck
flexion tests are summarized in Table 21. Incremental tests were run at
impact speeds needed to achieve increases in kinetic energy of 10
percent, 20 percent, and 30 percent. In all cases, the response signals
were smooth with no indication of damage.
    Torsion Tests. The high-energy neck torsion tests were also run at
impact speeds needed to achieve energy increases of 10 percent, 20
percent, and 30 percent. The responses are summarized in Table 22. In
all cases, the response signals were smooth with no indication of
damage.

                                                 Table 20--Frontal Flexion Neck Pendulum Test Responses
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              Energy                                 Max angle                     Peak Y-moment
                                             increase      Impact speed, ---------------------------------------------------------------- Head  rotation
                Test No.                     (nominal)          m/s                                                                         decay  time,
                                             (percent)                       angle deg        time ms       moment  N-m       time ms           m/s
--------------------------------------------------------------------------------------------------------------------------------------------------------
Baseline................................               0             4.7            74.0            58.2            44.9            54.1            51.5
1.......................................              34             5.5            78.8            55.9            62.3            53.0            48.0
2.......................................              34             5.5            80.1            55.4            66.0            52.7            47.7
3.......................................              34             5.5            79.4            57.0            63.2            53.2            47.6
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                                 Table 21--Lateral Flexion Neck Pendulum Test Responses
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              Energy                                 Max angle                     Peak Y-moment
                                             increase      Impact speed, ---------------------------------------------------------------- Head  rotation
                Test No.                     (nominal)          m/s                                                                         decay  time,
                                             (percent)                       angle deg        time ms       moment  N-m       time ms           m/s
--------------------------------------------------------------------------------------------------------------------------------------------------------
baseline................................               0             3.8            80.9            68.7            26.9            70.2            64.8
1.......................................              10             4.0            82.3            68.9            27.1            70.1            65.5
2.......................................              20             4.2            85.1            67.2            31.9            66.8            63.2
3.......................................              30             4.3            86.8            66.8            34.3            66.3            62.3
--------------------------------------------------------------------------------------------------------------------------------------------------------

                                                     Table 22--Neck Torsion Pendulum Test Responses
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                               Impact            Max angle               Peak Z-Moment           Head
                                                                  Energy       speed    ----------------------------------------------------   rotation
                           Test No.                              increase  -------------    angle         time        moment        time      decay time
                                                                (nominal)               ----------------------------------------------------------------
                                                                (percent)       m/s          Deg           Ms          N-m           ms           ms
--------------------------------------------------------------------------------------------------------------------------------------------------------
baseline.....................................................            0          3.6         80.9         99.5         9.35         92.1         88.7
1............................................................           10          3.8         83.3        102.9         9.35         95.5         91.7
2............................................................           20          3.9         83.8        101.5         9.40         95.0         91.2
3............................................................           30          4.1         87.4        103.1         9.73         96.9         91.0
--------------------------------------------------------------------------------------------------------------------------------------------------------

High-Energy Shoulder Impact Tests
    The agency conducted shoulder impacts according to the
qualification test setup procedures, except the impact speeds were
increased to achieve increases in kinetic energy of approximately 10
percent, 20 percent, and 30 percent as compared to the qualification
test. Table 23 provides a summary of the responses for the high-energy
shoulder impact tests. At the 30 percent increased energy level, the
peak lateral shoulder deflection was 20.4 mm and the response curve was
smooth, indicating that the shoulder string pot did not reach its
maximum allowable stroke. The peak probe force was 1450 N. Post-test
inspections revealed no structural damage to the dummy or
instrumentation.

                              Table 23--High-Energy Shoulder Impact Test Responses
----------------------------------------------------------------------------------------------------------------
                                           Energy increase                        Shoulder
                Test No.                      (nominal)     Impact speed (m/    displacement     Probe force (N)
                                              (percent)            s)               (mm)
----------------------------------------------------------------------------------------------------------------
baseline................................               0.0               3.6              17.6              1269
1.......................................                10               3.8              19.7              1348
2.......................................                20               4.0              20.1              1443
3.......................................                30               4.1              20.4              1450
----------------------------------------------------------------------------------------------------------------

High-Energy Thorax Impact Tests
    We conducted high-energy thorax impact tests with and without the
arm. We followed the set-up procedures used in the qualification tests,
except we increased the probe impact speeds to supply a corresponding
increase in the kinetic energy.
    For the ``with arm'' tests, we conducted one impact at 20 percent
increased kinetic energy and two at a 30 percent increase. Table 24
summarizes the responses for the high-energy thorax with arm impacts.
The highest lateral thorax displacement was 28.7 mm and the response
curve was smooth. Post-test inspections demonstrated that no damage
occurred to any portion of the dummy's torso.
    For the thorax ``without arm'' test condition (Table 25), because
thorax durability was a concern with earlier versions of the Q3s, we
conducted tests at higher severity levels to provide a rigorous
assessment of the durability of the thorax. For the thorax ``without
arm'' test condition, we conducted an impact at 50 percent increased
kinetic energy and another impact at a 70 percent increase. No
structural damage was observed during post-test inspections of the
dummy's thorax and IR-TRACC displacement transducer.
    In addition, for the thorax ``without arm'' test condition, we
conducted tests at increased severity levels to assess further the
durability of the IR-TRACC device. The maximum allowable lateral thorax
displacement before damage occurs to the IR-TRACC displacement
measurement device is approximately 40 mm. Considering this physical
limitation, we increased the probe impact speed until the lateral
displacement approached 38 mm. We found that the impact speed
corresponding to roughly 38 mm of displacement was 4.4 m/s
(approximately an 80 percent increase in kinetic energy). Accordingly,
we conducted two additional impact tests at that speed. For the three
tests conducted at 80 percent increased kinetic energy, the lateral
thorax displacement ranged from 37.1-37.9 mm and the response curves
were smooth, indicating that the transducer did not exceed its maximum
allowable stroke. No structural damage was observed during post-test
inspections of the dummy's thorax and IR-TRACC displacement transducer.

                           Table 24--High-Energy Thorax With Arm Impact Test Responses
----------------------------------------------------------------------------------------------------------------
                                           Energy increase                         Thorax
                Test No.                      (nominal)     Impact speed (m/    displacement     Probe force (N)
                                              (percent)            s)               (mm)
----------------------------------------------------------------------------------------------------------------
baseline................................                 0               5.0              25.0              1526
1.......................................                20               5.5              27.0              1663
2.......................................                30               5.7              28.3              1625
3.......................................  ................  ................              28.7              1652
----------------------------------------------------------------------------------------------------------------

                         Table 25--High-Energy Thorax Without Arm Impact Test Responses
----------------------------------------------------------------------------------------------------------------
                                           Energy increase                         Thorax
                Test No.                      (nominal)     Impact speed (m/    displacement     Probe force (N)
                                              (percent)            s)               (mm)
----------------------------------------------------------------------------------------------------------------
baseline................................                 0               3.3              26.0               732
1.......................................                50               4.0              32.8               784
2.......................................                70               4.3              36.2               772
3.......................................                80               4.4              37.9               799
4.......................................  ................  ................              37.3               814
5.......................................  ................  ................              37.1               815
----------------------------------------------------------------------------------------------------------------

High-Energy Lumbar Pendulum Tests
    We conducted high-energy frontal and lateral lumbar pendulum tests
according to the qualification test set-up procedures, except the
impact speeds were increased. For frontal pendulum tests, the impact
energy was increased up to approximately 30 percent greater than the
qualification test, while lateral tests were increased up to
approximately 40 percent greater than the qualification test.
    The frontal test results are summarized in Table 26 and the lateral
results are summarized in Table 27. The lumbar moment and rotation
responses did not indicate any unusual issues with the lumbar spine
element or load cell in either of the test conditions. No damage or
delamination was observed in post-test inspections of the lumbar
components.

                          Table 26--High-Energy Frontal Lumbar Pendulum Test Responses
----------------------------------------------------------------------------------------------------------------
                                      Energy                     Max angle       Peak Y-moment
                                     increase      Impact   -------------------------------------  Head rotation
             Test No.               (nominal)    speed, m/s   Angle            Moment N-          decay time, ms
                                    (percent)                  deg    Time ms      m     Time ms
----------------------------------------------------------------------------------------------------------------
Baseline.........................            0          4.4     53.3     56.6      85.7     53.9            54.2
1................................           20          4.8     57.5     56.8      88.6     51.9            55.0
2................................           30          5.0     60.3     57.5      95.6     53.5            55.0
----------------------------------------------------------------------------------------------------------------

                          Table 27--High-Energy Lateral Lumbar Pendulum Test Responses
----------------------------------------------------------------------------------------------------------------
                                      Energy                     Max angle       Peak Y-moment
                                     increase      Impact   -------------------------------------  Head rotation
             Test No.               (nominal)    speed, m/s   Angle            Moment N-          decay time, ms
                                    (percent)                  deg    Time ms      m     Time ms
----------------------------------------------------------------------------------------------------------------
Baseline.........................            0          4.4     53.9     56.0      83.5     50.3            49.2
1................................           20          4.8     59.0     57.3      95.7     54.0            54.0
2................................           30          5.0     60.7     57.4     100.8     54.0            54.0
3................................           40          5.2     62.9     56.6     107.7     53.3            53.3
----------------------------------------------------------------------------------------------------------------

High-Energy Pelvis Impact Tests
    We conducted high-energy pelvis impacts in accordance with the
qualification test set-up procedures, except we increased impact speeds
to achieve increases in kinetic energy of approximately 15 percent, 40
percent, and 55 percent. The responses for the high-energy pelvis
impact tests are summarized in Table 28. At the highest energy level,
the lateral pubic load was 1057 N (well beyond the 450 N maximum
observed in the Cozy Cline R&R series) and the probe force was 2357 N.
Analysis of the lateral pubic load response revealed a smooth curve,
indicating no unusual contact internal to the dummy. No damage to the
pelvis region was observed during post-test inspections.

           Table 28--High-Energy Pelvis Impact Test Responses
------------------------------------------------------------------------
                                    Energy
                                   Increase     Impact   Pubic    Probe
            Test No.               (nominal)    speed    force    force
                                   (percent)    (m/s)     (N)      (N)
------------------------------------------------------------------------
baseline.......................           0.0      4.0      796     1712
1..............................          15        4.3      843     1896
2..............................          40        4.7     1001     2209
3..............................          55        5.0     1057     2357
------------------------------------------------------------------------

b. Q3s Servicing and Maintenance

    In our experience with other Part 572 ATDs, deformable parts
typically have the shortest service lives. The two most often replaced
parts are the ribcage and the molded neck. For example, we have found
the typical service life for HIII-10C rib sets and neck assemblies to
be about thirty sled tests. Vinyl flesh materials--particularly the
chest flesh--are also replaced on a recurring basis as they become
aged, abraded, or torn.
    NHTSA owns four Q3s units of the final Build Level D version, which
include the updated parts to improve the durability of the thorax,
neck, and pelvis. There have been no durability problems with the ATDs
since they have been upgraded to the latest build level. Given the
record of low maintenance to our own Q3s units, we consider the dummy
to be highly suitable for proposed use in FMVSS No. 213 in terms of its
durability. Our records indicate that we have had relatively few
instances of Q3s part replacements of any sort.

VIII. Drawings and Patents

    Throughout the notice and comment period of this Part 572
rulemaking, the Q3s dummy will be available from Humanetics. The Q3s
engineering drawings used to fabricate the dummy are available in the
docket for public review and comment. The Q3s engineering drawings are
a proprietary product owned by Humanetics,\29\ with the exceptions
noted in this section. Thus, during the comment period most drawings
will display the Humanetics name in the title block and will have the
following restrictive note:
---------------------------------------------------------------------------

    \29\ FTSS/Humanetics' development of the Q3s dummy was not
performed directly under a government research and development
contract. NHTSA procured its Q3s units under a standard purchase
order in which the FTSS/Humanetics products were listed within a
catalog with a price schedule. Using this same purchase mechanism,
our units were periodically sent back to FTSS/Humanetics for
warranty maintenance and upgrades. As we performed subsequent tests
on our Q3s units, we routinely shared our results with FTSS/
Humanetics, and concurrently reported them in public and in SAE and
ISO committee meetings, providing test results, identifying
problems, and suggesting ways to correct problems. FTSS/Humanetics
produced parts based on this information, and periodically provided
new components to NHTSA for evaluation.

    This drawing is the sole property of Humanetics Innovative
Solutions, Inc. and is being provided to NHTSA and other related
organizations for evaluation and comment related to NHTSA's
rulemaking process. Except for commenting purposes pursuant to this
process, the drawing shall not be copied or used for any other
purpose without the written consent of Humanetics Innovative
---------------------------------------------------------------------------
Solutions, Inc.

    For the final rule, the note will be removed and the dummy drawings
and designs will be free from any restrictions. This includes their use
in fabrication and in building computer simulation models of the dummy.
    During this comment period, some drawings will not have the
Humanetics name in the title block and will not have the restrictive
note on them. In these cases, NHTSA contracted with Humanetics to
provide the part or expressly contributed to the design of the part. As
described earlier in this preamble, Humanetics fabricated the Build
Level D neck using detailed specifications provided by NHTSA. These
specifications included detailed engineering drawings and a prototype
of the neck itself. In addition, NHTSA also contributed to the design
of the femur, hip, and several other minor parts of the dummy.
    The list of drawings related to those agency's efforts is shown in
Table 29. On these drawings, the NHTSA name appears in the title block
and the restrictive note does not appear. These drawings are available
to the public for use during this NPRM stage without restriction.
    NHTSA is aware that Humanetics has filed a patent application with
the United States Patent and Trademark Office covering certain parts of
the Q3s dummy. Prior to the publication of any final rule, NHTSA plans
to meet with Humanetics and come to some agreement that ensures the
continued availability of the Q3s dummy to the general public at a
reasonable price. Notwithstanding the intellectual property issues
identified in this section, NHTSA emphasizes that readers should take
this opportunity to review the information provided in this NPRM and
provide responses on the substantive aspects of the proposal.

                      Table 29--List of Q3s Drawings for Which No Restrictive Note Appears
----------------------------------------------------------------------------------------------------------------
               Drawing No.                          Description                          Used on
----------------------------------------------------------------------------------------------------------------
020-2400.................................  Neck assembly, Q3s..........  020-2400
020-2401.................................  Molded neck, Q3s............  020-2400
020-2402.................................  Neck plate, top Q3s.........  020-2400
020-2403.................................  Neck plate, middle, Q3s.....  020-2400
020-2404.................................  Neck plate, bottom, Q3s.....  020-2400
020-2405.................................  Retaining ring, Q3s neck....  020-2400
020-2406.................................  Square crimp, Q3s neck......  020-2400
020-2407.................................  Bottom crimp, Q3s neck cable  020-2400
020-2408.................................  Neck cable assembly, Q3s....  020-2400
020-2409.................................  Retaining nut, Q3s neck.....  020-2400
020-9611.................................  Femur, Right................  020-9616
020-9511.................................  Femur, Left.................  020-9516
020-9607.................................  Femur reinforcement, Right..  020-9616

020-9507.................................  Femur reinforcement, Left...  020-9516
020-3537.................................  Ball shoulder...............  020-9616, 020-9516
020-9903.................................  End stop....................  020-9616, 020-9516
020-7116.................................  Hip joint assembly, Right...  020-7116
020-7113.................................  Hip joint assembly, Left....  020-7113
020-7115.................................  Hip cup assembly, Right.....  020-7116, 020-7113
020-7114.................................  Hip cup assembly, Left......  020-7116, 020-7113
020-7117.................................  Hip cup, upper..............  020-7116, 020-7113
020-7118.................................  Hip cup, lower..............  020-7116, 020-7113
020-7103.................................  Detent peg..................  020-7116, 020-7113
020-7104.................................  Spring retainer plate.......  020-7116, 020-7113
020-9000.................................  Q3s positioning tool........  020-9000
020-9001.................................  Indicator arm...............  020-9000
020-9002.................................  Extension bracket...........  020-9000
020-9003.................................  Cross beam..................  020-9000
020-9004.................................  Knee spacer.................  020-9000
020-9005.................................  Pivot screw.................  020-9000
----------------------------------------------------------------------------------------------------------------

IX. Consideration of Alternatives

    We considered the merits of alternative test dummies for use in the
side impact test under consideration for FMVSS No. 213. The closest
viable alternatives were the modified Hybrid III 3-year-old child test
dummy (HIII-3C) and the Q3.
Consideration of the Modified HIII-3C (``3Cs'')
    The HIII-3C was originally developed in 1992. It is used in FMVSS
No. 208, ``Occupant crash protection,'' to evaluate air bag
aggressiveness or air bag suppression when a child is close to a
deploying air bag, and in FMVSS No. 213's frontal sled test for the
evaluation of child restraint performance. The HIII-3C was not designed
for lateral impacts. Under lateral loading, the shoulder and torso
exhibit highly stiff behavior and do not fully replicate a child's
kinematics. NHTSA considered using the HIII-3C in the 2002 FMVSS No.
213 ANPRM published in response to the TREAD Act (see footnote 4,
supra), but concluded that the ATD was not acceptable for use in side
impact testing.
    After the agency assessed the HIII-3C in side impacts, NHTSA
developed a retrofit package for the dummy to install a new head and
neck with better lateral biofidelity. The retrofitted dummy is referred
to as the ``3Cs.''
    NHTSA evaluated the 3Cs and the Q3s concurrently. Based on our
biofidelity evaluations, the 3Cs did not achieve nearly as good a
ranking as the Q3s. The technical report, ``Biofidelity Assessment of
the Q3s Three-Year-Old Child Side Impact Dummy,'' supra, discusses the
performance of the two ATDs. The Q3s outperformed or is equivalent to
the 3Cs in every aspect of biofidelity related to a dummy's response in
a side impact. Given the superior biofidelity of the Q3s, we believe
that it more accurately represents the response expected of a human
child.
    In addition, the Q3s has thorax deflection instrumentation, which
the 3Cs does not. We tentatively conclude that the Q3s is a better
dummy than the 3Cs to measure injury assessment values in side impacts
and is a preferable ATD for use in the proposed side impact upgrade to
FMVSS No. 213.
Consideration of the Q3
    As discussed in section II of this preamble, the design of the Q3s
was derived from the original Q3 dummy developed by the European
community. The Q3 is intended for use in frontal, side, and rear
impacts.
    Around the same time Humanetics was working to bring the Q3s up to
production level, the Q3 underwent a significant design revision.
Starting in 2003, a ``new'' Q3 took shape. Many of the new design
concepts included in the Q3s were also built into the Q3 as Humanetics
worked concurrently on both dummies (e.g., thorax string potentiometers
were replaced by IR-TRACCs in both dummies). Still, as reported by the
European Enhanced Vehicle-Safety Committee (Wismans, et al., 2008), the
new Q3 does not respond well in lateral biofidelity tests. Furthermore,
the thorax of the new Q3 has become even less biofidelic than the
original. Therefore, NHTSA does not consider the Q3 preferable to the
Q3s.
Conclusion
    The agency tentatively concludes that the improved biofidelity and
additional injury assessment capability of the Q3s compared to the
other commercially available child side impact test dummies supports a
decision to adopt the Q3s into 49 CFR Part 572. The Q3s dummy is a
state-of-the-art device that would allow for a better assessment of the
risk of injury to child occupants than the alternative test dummies.
The availability of Q3s's injury measuring capability also is important
to the design, development and evaluation of the side impact protection
of child restraint systems. The Q3s test dummy is available today, and
has been thoroughly evaluated for suitable reproducibility and
repeatability of results.

X. Rulemaking Analyses and Notices

Executive Order (E.O.) 12866 and E.O. 13563, and DOT Regulatory
Policies and Procedures

    NHTSA has considered the impacts of this regulatory action under
E.O. 12866 and E.O. 13563. This rulemaking action was not reviewed by
the Office of Management and Budget under E.O. 12866. The rulemaking
has also been determined to be non-significant under DOT's regulatory
policies and procedures.
    This document would amend 49 CFR Part 572 by adding design and
performance specifications for a test dummy representative of a 3-year-
old child that the agency would possibly use in FMVSS No. 213 side
impact compliance tests and possibly for research purposes. This Part
572 proposed rule would not impose any requirements on anyone.
Businesses are affected only if they choose to manufacture or test with
the dummy. Because the economic impacts of this proposed rule are
minimal, no further regulatory evaluation is necessary.
    There are benefits associated with this rulemaking but they cannot
be quantified. The incorporation of the test dummy into 49 CFR Part 572
would

enable NHTSA to use the ATD in a new dynamic side impact test that we
are considering adopting into FMVSS No. 213. Adoption of side impact
protection requirements in FMVSS No. 213 enhances child passenger
safety and accords with MAP-21. In addition, the availability of this
dummy in a regulated format would be beneficial by providing a
suitable, stabilized, and objective test tool to the safety community
for use in better protecting children in side impacts.
    The cost of an uninstrumented Q3s dummy is approximately $48,750.
The minimum set of instrumentation needed for qualification and
compliance type testing includes three uni-axial accelerometers (part
no. SA572-S4), one neck/spine load cell (SA572-S8), one shoulder
potentiometer set (SA572-S38 and S39), one single axis IR-TRACC (SA572-
S37), and one pubic load cell (SA572-S7). The cost of this
instrumentation adds approximately $18,200 for a total cost of about
$66,950.
    We have not estimated the costs of the equipment needed to perform
the qualification tests other than the instrumentation needed (two
angular rate sensors, $1,230 apiece; one test probe accelerometer,
$500; one rotary potentiometer, $500.) With the exception of the neck
torsion fixture, the angular rate sensors, and the 3.8 kg test probe,
all fixtures and instruments are common with those used to qualify
other Part 572 dummies.
    We recognize that dummy refurbishments and part replacements are an
inherent part of ATD testing. Various parts will likely have to be
refurbished or replaced, but we do not know which parts are likely to
be worked on the most. However, since the dummies are designed to be
reusable, costs of the dummies and of parts can be amortized over a
number of tests.

Regulatory Flexibility Act

    Pursuant to the Regulatory Flexibility Act (5 U.S.C. 601 et seq.,
as amended by the Small Business Regulatory Enforcement Fairness Act
(SBREFA) of 1996), whenever an agency is required to publish a proposed
or final rule, it must prepare and make available for public comment a
regulatory flexibility analysis that describes the effect of the rule
on small entities (i.e., small businesses, small organizations, and
small governmental jurisdictions), unless the head of the agency
certifies the rule will not have a significant economic impact on a
substantial number of small entities. The Small Business
Administration's regulations at 13 CFR Part 121 define a small
business, in part, as a business entity ``which operates primarily
within the United States.'' (13 CFR 121.105(a)).
    We have considered the effects of this rulemaking under the
Regulatory Flexibility Act. I hereby certify that this rulemaking
action would not have a significant economic impact on a substantial
number of small entities. This action would not have a significant
economic impact on a substantial number of small entities because the
addition of the test dummy to Part 572 would not impose any
requirements on anyone. NHTSA would use the ATD in agency testing but
would not require anyone to manufacture the dummy or to test motor
vehicles or motor vehicle equipment with it.

National Environmental Policy Act

    NHTSA has analyzed this proposed rule for the purposes of the
National Environmental Policy Act and determined that it would not have
any significant impact on the quality of the human environment.

Executive Order 13045 and 13132 (Federalism)

    Executive Order 13045 (62 FR 19885, April 23, 1997) applies to any
rule that: (1) Is determined to be ``economically significant'' as
defined under E.O. 12866, and (2) concerns an environmental, health, or
safety risk that NHTSA has reason to believe may have a
disproportionate effect on children. If the regulatory action meets
both criteria, we must evaluate the environmental health or safety
effects of the planned rule on children, and explain why the planned
regulation is preferable to other potentially effective and reasonably
feasible alternatives considered by us.
    This proposed rule is not subject to the Executive Order because it
is not economically significant as defined in E.O. 12866.
    NHTSA has examined today's proposed rule pursuant to Executive
Order 13132 (64 FR 43255, August 10, 1999) and concluded that no
additional consultation with States, local governments or their
representatives is mandated beyond the rulemaking process. The agency
has concluded that the proposed rule would not have federalism
implications because the proposed rule would not have ``substantial
direct effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.'' This
proposed rule would not impose any requirements on anyone. Businesses
will be affected only if they choose to manufacture or test with the
dummy.
    Further, no consultation is needed to discuss the preemptive effect
of today's proposed rule. NHTSA's safety standards can have preemptive
effect in two ways. This proposed rule would amend 49 CFR Part 572 and
is not a safety standard.\30\ This Part 572 proposed rule would not
impose any requirements on anyone.
---------------------------------------------------------------------------

    \30\ With respect to the safety standards, the National Traffic
and Motor Vehicle Safety Act contains an express preemptive
provision: ``When a motor vehicle safety standard is in effect under
this chapter, a State or a political subdivision of a State may
prescribe or continue in effect a standard applicable to the same
aspect of performance of a motor vehicle or motor vehicle equipment
only if the standard is identical to the standard prescribed under
this chapter.'' 49 U.S.C. 30103(b)(1). Second, the Supreme Court has
recognized the possibility of implied preemption: State requirements
imposed on motor vehicle manufacturers, including sanctions imposed
by State tort law, can stand as an obstacle to the accomplishment
and execution of a NHTSA safety standard. When such a conflict
exists, the Supremacy Clause of the Constitution makes the State
requirements unenforceable. See Geier v. American Honda Motor Co.,
529 U.S. 861 (2000).
---------------------------------------------------------------------------

Civil Justice Reform

    With respect to the review of the promulgation of a new regulation,
section 3(b) of Executive Order 12988, ``Civil Justice Reform'' (61 FR
4729, February 7, 1996) requires that Executive agencies make every
reasonable effort to ensure that the regulation: (1) Clearly specifies
the preemptive effect; (2) clearly specifies the effect on existing
Federal law or regulation; (3) provides a clear legal standard for
affected conduct, while promoting simplification and burden reduction;
(4) clearly specifies the retroactive effect, if any; (5) adequately
defines key terms; and (6) addresses other important issues affecting
clarity and general draftsmanship under any guidelines issued by the
Attorney General. This document is consistent with that requirement.
    Pursuant to this Order, NHTSA notes as follows.
    The issue of preemption is discussed above in connection with E.O.
13132. NHTSA notes further that there is no requirement that
individuals submit a petition for reconsideration or pursue other
administrative proceeding before they may file suit in court.

Paperwork Reduction Act

    Under the Paperwork Reduction Act of 1995, a person is not required
to respond to a collection of information by a Federal agency unless
the collection displays a valid control number from the Office of
Management and Budget (OMB). This proposed rule would not have any
requirements that are considered to be information

collection requirements as defined by the OMB in 5 CFR Part 1320.

National Technology Transfer and Advancement Act

    Section 12(d) of the National Technology Transfer and Advancement
Act of 1995 (NTTAA), Public Law 104-113, section 12(d) (15 U.S.C. 272)
directs NHTSA to use voluntary consensus standards in its regulatory
activities unless doing so would be inconsistent with applicable law or
otherwise impractical. Voluntary consensus standards are technical
standards (e.g., materials specifications, test methods, sampling
procedures, and business practices) that are developed or adopted by
voluntary consensus standards bodies. The NTTAA directs NHTSA to
provide Congress, through OMB, explanations when the agency decides not
to use available and applicable voluntary consensus standards.
    The following voluntary consensus standards have been used in
developing the Q3s:
     SAE Recommended Practice J211, Rev. Mar 95,
``Instrumentation for Impact Tests--Part 1--Electronic
Instrumentation''; and,
     SAE J1733 of 1994-12 ``Sign Convention for Vehicle Crash
Testing.''

Unfunded Mandates Reform Act

    Section 202 of the Unfunded Mandates Reform Act of 1995 (UMRA),
Public Law 104-4, requires Federal agencies to prepare a written
assessment of the costs, benefits, and other effects of proposed or
final rules that include a Federal mandate likely to result in the
expenditure by State, local, or tribal governments, in the aggregate,
or by the private sector, of more than $100 million annually (adjusted
for inflation with base year of 1995). Before promulgating a NHTSA rule
for which a written statement is needed, section 205 of the UMRA
generally requires the agency to identify and consider a reasonable
number of regulatory alternatives and adopt the least costly, most
cost-effective, or least burdensome alternative that achieves the
objectives of the rule.
    This proposed rule would not impose any unfunded mandates under the
UMRA. This proposed rule does not meet the definition of a Federal
mandate because it does not impose requirements on anyone. It amends 49
CFR Part 572 by adding design and performance specifications for a 3-
year-old child side impact test dummy that the agency could use in
FMVSS No. 213 and for research purposes. This proposed rule would
affect only those businesses that choose to manufacture or test with
the dummy. It would not result in costs of $100 million or more to
either State, local, or tribal governments, in the aggregate, or to the
private sector.

Plain Language

    Executive Order 12866 requires each agency to write all rules in
plain language. Application of the principles of plain language
includes consideration of the following questions:
    Has the agency organized the material to suit the public's needs?
    Are the requirements in the rule clearly stated?
    Does the rule contain technical language or jargon that is not
clear?
    Would a different format (grouping and order of sections, use of
headings, paragraphing) make the rule easier to understand?
    Would more (but shorter) sections be better?
    Could the agency improve clarity by adding tables, lists, or
diagrams?
    What else could the agency do to make this rulemaking easier to
understand?
    If you have any responses to these questions, please send them to
NHTSA.

Regulation Identifier Number

    The Department of Transportation assigns a regulation identifier
number (RIN) to each regulatory action listed in the Unified Agenda of
Federal Regulations. The Regulatory Information Service Center
publishes the Unified Agenda in April and October of each year. You may
use the RIN contained in the heading at the beginning of this document
to find this action in the Unified Agenda.

XI. Public Participation

How do I prepare and submit comments?

    Your comments must be written and in English. To ensure better that
your comments are correctly filed in the Docket, please include the
docket number of this document in your comments.
    Your comments must not be more than 15 pages long. (49 CFR 553.21).
We established this limit to encourage you to write your primary
comments in a concise fashion. However, you may attach necessary
additional documents to your comments. There is no limit on the length
of the attachments.
    Comments may also be submitted to the docket electronically by
logging into http://www.regulations.gov. Follow the online instructions
for submitting comments.
    Please note that pursuant to the Data Quality Act, in order for
substantive data to be relied upon and used by the agency, it must meet
the information quality standards set forth in the OMB and DOT Data
Quality Act guidelines. Accordingly, we encourage you to consult the
guidelines in preparing your comments. OMB's guidelines may be accessed
at http://www.whitehouse.gov/omb/fedreg/reproducible.html.

How can I be sure that my comments were received?

    If you wish the Docket Management Facility to notify you upon its
receipt of your comments, enclose a self-addressed, stamped postcard in
the envelope containing your comments. Upon receiving your comments,
the Docket Management Facility will return the postcard by mail.

How do I submit confidential business information?

    If you wish to submit any information under a claim of
confidentiality, you should submit three copies of your complete
submission, including the information you claim to be confidential
business information, to the Chief Counsel's office, NHTSA, at the
address given above under FOR FURTHER INFORMATION CONTACT. In addition,
you should submit two copies, from which you have deleted the claimed
confidential business information, to the Docket Management Facility at
the address given above under ADDRESSES. When you send a comment
containing information claimed to be confidential business information,
you should include a cover letter setting forth the information
specified in our confidential business information regulation. (49 CFR
Part 512.)

Will the agency consider late comments?

    We will consider all comments that the docket receives before the
close of business on the comment closing date indicated above under
DATES. To the extent possible, we will also consider comments received
after that date. If the docket receives a comment too late for us to
consider in developing a final rule (assuming that one is issued), we
will consider that comment as an informal suggestion for a future
rulemaking action.

How can I read the comments submitted by other people?

    You may read the comments received by the Docket Management
Facility at the address given above under ADDRESSES. The hours of the
Docket are indicated above in the same location. You may also see the
comments on the Internet. To read the comments on the

Internet, go to http://www.regulations.gov. Follow the online
instructions for accessing the dockets.
    Please note that even after the comment closing date, we will
continue to file relevant information in the docket as it becomes
available. Further, some people may submit late comments. Accordingly,
we recommend that you periodically check the docket for new material.
    Anyone is able to search the electronic form of all comments
received into any of our dockets by the name of the individual
submitting the comment (or signing the comment, if submitted on behalf
of an association, business, labor union, etc.). You may review DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (Volume 65, Number 70; Pages 19477-78).

List of Subjects in 49 CFR Part 572

    Motor vehicle safety, Incorporation by reference.

    In consideration of the foregoing, NHTSA proposes to amend 49 CFR
Part 572 as follows:

PART 572--ANTHROPOMORPHIC TEST DEVICES

0
1. The authority citation for Part 572 would be amended to read as
follows:

    Authority:  49 U.S.C. 322, 30111, 30115, 30117 and 30166;
delegation of authority at 49 CFR 1.95.

0
2. 49 CFR Part 572 would be amended by adding a new Subpart W
consisting of 572.210-572.219 to read as follows:
Subpart W--Q3s Three-Year-Old Child Test Dummy
Secs.
572.210 Incorporation by reference.
572.211 General description.
572.212 Head assembly and test procedure.
572.213 Neck assembly and test procedure.
572.214 Shoulder assembly and test procedure.
572.215 Thorax with arm assembly and test procedure.
572.216 Thorax without arm assembly and test procedure.
572.217 Lumbar spine assembly and test procedure.
572.218 Pelvis assembly and test procedure.
572.219 Test conditions and instrumentation.
Appendix--Figures to Subpart W of Part 572

Sec.  572.210  Incorporation by reference.

    (a) Certain material is incorporated by reference (IBR) into this
part with the approval of the Director of the Federal Register under 5
U.S.C. 552(a) and 1 CFR part 51. To enforce any edition other than that
specified in this section, NHTSA must publish notice of change in the
Federal Register and the material must be available to the public. All
approved material is available for inspection at the Department of
Transportation, Docket Operations, Room W12-140, telephone 202-366-
9826, and is available from the sources listed below. The material is
available in electronic format through Regulations.gov, call 1-877-378-
5457 or go to www.regulations.gov. It is also available for inspection
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-741-
6030 or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html.
    (b) NHTSA Technical Information Services, 1200 New Jersey Ave. SE.,
Washington, DC 20590, telephone<PHONE_NUMBER>.
    (1) A parts/drawing list entitled, ``Parts/Drawings List, Part 572
Subpart W, Q3s Three-Year-Old Child Test Dummy, May 2012,'' IBR
approved for Sec.  572.211.
    (2) A drawings and inspection package entitled, ``Parts List and
Drawings, Part 572 Subpart W, Q3s Three-Year-Old Child Test Dummy, May
2012,'' IBR approved for Sec.  572.211, including:
    (i) Drawing No. 020-0100, Complete Assembly Q3s, IBR approved for
Sec. Sec.  572.211, 572.212, 572.213, 572.214, 572.215, 572.216,
572.217, 572.218, and 572.219.
    (ii) Drawing No. 020-1200, Head Assembly, IBR approved for
Sec. Sec.  572.211, 572.212, 572.214, 572.215, 572.216, 572.218, and
572.219.
    (iii) Drawing No. 020-2400, Neck Assembly, IBR approved for
Sec. Sec.  572.211, 572.213, 572.214, 572.215, 572.216, 572.218, and
572.219.
    (iv) Drawing No. 020-9050, Headform, IBR approved for Sec. Sec.
572.211, 572.213, 572.217 and 572.219.
    (v) Drawing No. DL210-200, Neck Twist Fixture, IBR approved for
Sec. Sec.  572.211, 572.213, and 572.219.
    (vi) Drawing No. 020-4500, Torso Assembly, IBR approved for
Sec. Sec.  572.211, 572.214, 572.215, 572.216, 572.218 and 572.219.
    (vii) Drawing No. 020-6000, Lumbar Spine Assembly, IBR approved for
Sec. Sec.  572.211, 572.217 and 572.219.
    (viii) Drawing No. 020-7500, Pelvis Assembly, IBR approved for
Sec. Sec.  572.211, 572.214, 572.215, 572.216, 572.218, and 572.219.
    (ix) Drawing No. 020-8001, Q3s Suit, IBR approved for Sec. Sec.
572.211, 572.214, 572.215, 572.216, 572.218, and 572.219.
    (x) Drawing No. 020-9500, Complete Leg Assembly--left, IBR approved
for Sec. Sec.  572.211, 572.214, 572.215, 572.216, 572.218, and 572.219
as part of a complete dummy assembly.
    (xi) Drawing No. 020-9600, Complete Leg Assembly--right, IBR
approved for Sec. Sec.  572.211, 572.214, 572.215, 572.216, 572.218,
and 572.219 as part of a complete dummy assembly.
    (xii) Drawing No. 020-9700, Complete Arm Assembly--left, IBR
approved for Sec. Sec.  572.211, 572.214, 572.215, 572.216, 572.218,
and 572.219 as part of a complete dummy assembly.
    (xiii) Drawing No. 020-9800, Complete Arm Assembly--right, IBR
approved for Sec. Sec.  572.211, 572.214, 572.215, 572.216, 572.218,
and 572.219 as part of a complete dummy assembly.
    (3) A procedures manual entitled ``Procedures for Assembly,
Disassembly and Inspection (PADI) of the Q3s Child Side Impact Crash
Test Dummy, September 2013,'' IBR approved for Sec. Sec.  572.211 and
572.219.
    (c) SAE International, 400 Commonwealth Drive, Warrendale, PA
15096, call 1-877-606-7323.
    (1) SAE Recommended Practice J211, Rev. Mar 95, ``Instrumentation
for Impact Tests--Part 1--Electronic Instrumentation,'' IBR approved
for Sec.  572.219;
    (2) SAE Information Report J1733 of 1994-12, ``Sign Convention for
Vehicle Crash Testing,'' IBR approved for Sec.  572.219.

Sec.  572.211  General description.

    (a) The Q3s Three-Year-Old Child Test Dummy is defined by drawings
and specifications containing the following materials:
    (1) The parts enlisted in ``Parts List and Drawings, Part 572
Subpart W, Q3s Three-Year-Old Child Test Dummy, September 2013''
(incorporated by reference, see Sec.  572.210).
    (2) The engineering drawings and specifications contained in
``Parts List and Drawings, Part 572 Subpart W, Q3s Three-Year-Old Child
Test Dummy, September 2013,'' which includes the engineering drawings
and specifications described in Drawing 020-0000, the titles of which
are listed in Table A, and,
    (3) A manual entitled ``Procedures for Assembly, Disassembly and
Inspection (PADI) of the Q3s Child Side Impact Crash Test Dummy,
September 2013.''

                        Table A to Sec.   572.211
------------------------------------------------------------------------
           Component assembly                     Drawing number
------------------------------------------------------------------------
(i) Head Assembly......................  020-1200
(ii) Neck Assembly.....................  020-2400
(iii) Torso Assembly...................  020-4500
(iv) Lumbar Spine Assembly.............  020-6000
(v) Pelvis Assembly....................  020-7500

(vi) Complete Leg Assembly--left.......  020-9500
(vii) Complete Leg Assembly--right.....  020-9600
(viii) Complete Arm Assembly--left.....  020-9700
(ix) Complete Arm Assembly--right......  020-9800
------------------------------------------------------------------------

    (b) The structural properties of the dummy are such that the dummy
conforms to this Subpart in every respect before use in any test.

Sec.  572.212  Head assembly and test procedure.

    (a) The head assembly for this test consists of the complete head
(drawing 020-1200) with head accelerometer assembly (drawing 020-
1013A), and a half mass simulated upper neck load cell (drawing 020-
1050) (all incorporated by reference, see Sec.  572.210).
    (b) When the head assembly is tested according to the test
procedure in paragraph (c) of this section, it shall have the following
characteristics:
    (1) Frontal head qualification test. When the head assembly is
dropped from a height of 376.0  1.0 mm (14.8
0.04 in) in accordance with subsection (c) of this section, the peak
resultant acceleration at the location of the accelerometers at the
head CG shall have a value between 250 G and 297 G. The resultant
acceleration vs. time history curve shall be unimodal; oscillations
occurring after the main pulse must be less than 10 percent of the peak
resultant acceleration. The lateral acceleration shall not exceed 15 G
(zero to peak).
    (2) Lateral head qualification test. When the head assembly is
dropped from a height of 200.0  1.0 mm (7.87
0.04 in) in accordance with subsection (c) of this section, the peak
resultant acceleration at the location of the accelerometers at the
head CG shall have a value between 113 G and 140 G. The resultant
acceleration vs. time history curve shall be unimodal; oscillations
occurring after the main pulse must be less than 10 percent of the peak
resultant acceleration. The X-component acceleration shall not exceed
20 G (zero to peak).
    (c) Test procedure: The test procedure for the head assembly is as
follows:
    (1) Soak the head assembly in a controlled environment at any
temperature between 18.9 and 25.6 [deg]C (66 and 78 [deg]F) and a
relative humidity from 10 to 70 percent for at least four hours prior
to a test.
    (2) Prior to the test, clean the impact surface of the skin and the
impact plate surface with isopropyl alcohol, trichloroethane, or an
equivalent. The skin of the head and the impact plate surface must be
clean and dry for testing.
    (3)(i) For the frontal head test, suspend and orient the head
assembly with the forehead facing the impact surface as shown in Figure
W1. The lowest point on the forehead must be 376.0  1.0 mm
(14.8  0.04 in) from the impact surface. Assure that the
head is horizontal laterally. Adjust the head angle so that the upper
neck load cell simulator is 28  2 degrees forward from the
vertical while assuring that the head remains horizontal laterally.
    (ii) For the lateral head test, the head is dropped on the aspect
that opposes the primary load vector of the ensuing full scale test for
which the dummy is being qualified. A left drop set up that is used to
qualify the dummy for an ensuing full scale left side impact is
depicted in Figure W2. A right drop set-up would be the mirror image of
that shown in Figure W2. Suspend and orient the head assembly as shown
in Figure W2. The lowest point on the impact side of the head must be
200.0  1.0 mm (7.87  0.04 in) from the impact
surface. Assure that the head is horizontal in the fore-aft direction.
Adjust the head angle so that the head base plane measured from the
base surface of the upper neck load cell simulator is 35  2
degrees forward from the vertical while assuring that the head remains
horizontal in the fore-aft direction.
    (4) Drop the head assembly from the specified height by means that
ensure a smooth, instant release onto a rigidly supported flat
horizontal steel plate which is 50.8 mm (2 in) thick and 610 mm (24 in)
square. The impact surface shall be clean, dry and have a micro finish
of not less than 203.2 x 10-6 mm (8 micro inches) (RMS) and
not more than 2,032.0 x 10-6 mm (80 micro inches) (RMS).
    (5) Allow at least 2 hours between successive tests on the same
head.

Sec.  572.213  Neck assembly and test procedure.

    (a)(1) The neck and headform assembly (refer to Sec.
572.210(b)(2)(iii) and Sec.  572.210(b)(2)(iv)) for the purposes of the
fore-aft neck flexion and lateral neck flexion qualification tests, as
shown in Figures W3 and W4, consists of the headform (drawing 020-9050,
sheet 1) with angular rate sensor installed (drawing SA572-S58), six-
channel neck/lumbar load cell (drawing SA572-S8), neck assembly
(drawing 020-2400), neck/torso interface plate (drawing 020-9056) and
pendulum interface plate (drawing 020-9051) with angular rate sensor
installed (drawing SA572-S58) (all incorporated by reference, see Sec.
572.210).
    (2) The neck assembly (refer to Sec.  572.210(b)(2)(iii) and Sec.
572.210(b)(2)(v)) for the purposes of the neck torsion qualification
test, as shown in Figure W5, consists of the neck twist fixture
(drawing DL210-200) with rotary potentiometer installed (drawing SA572-
S51), neck adaptor plate assembly (drawing DL210-220), neck assembly
(drawing 020-2400), six-channel neck/lumbar load cell (drawing SA572-
S8), and twist fixture end plate (drawing DL210-210) (all incorporated
by reference, see Sec.  572.210).
    (b) When the neck and headform assembly as defined in Sec.
572.213(a)(1), or the neck assembly as defined in Sec.  572.213(a)(2),
is tested according to the test procedure in paragraph (c) of this
section, it shall have the following characteristics:
    (1) Fore-aft neck flexion qualification test.
    (i) Plane D, referenced in Figure W3, shall rotate in the direction
of pre-impact flight with respect to the pendulum's longitudinal
centerline between 70 degrees and 82 degrees, which shall occur between
55 and 63 ms from time zero. The peak moment, measured by the neck
transducer (drawing SA572-S8) (incorporated by reference, see Sec.
572.210) shall have a value between 41 N-m (30.2 ft-lbf) and 51 N-m
(37.6 ft-lbf) occurring between 49 and 62 ms from time zero.
    (ii) The decaying headform rotation vs. time curve shall cross the
zero angle with respect to its initial position at time of impact
relative to the pendulum centerline between 50 to 54 ms after the time
the peak rotation value is reached.
    (iii) All instrumentation data channels are defined to be zero when
the longitudinal centerline of the neck and pendulum are parallel.
    (iv) The headform rotation shall be calculated by the following
formula with the integration beginning at time zero:
Headform rotation (deg) = [int] [(Headform Angular Rate)y-
(Pendulum Angular Rate)y] dt

    (v) (Headform Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the headform (drawing 020-9050, sheet
1), and (Pendulum Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the pendulum interface plate (drawing
020-9051) (incorporated by reference, see Sec.  572.210).

    (2) Lateral neck flexion qualification test.
    (i) Plane D, referenced in Figure W4, shall rotate in the direction
of pre-impact flight with respect to the pendulum's longitudinal
centerline between 77 degrees and 88 degrees, which shall occur between
65 and 72 ms from time zero. The peak moment, measured by the neck
transducer (drawing SA572-S8) (incorporated by reference, see Sec.
572.210) shall have a value between 25 N-m (18.4 ft-lbf) and 32 N-m
(23.6 ft-lbf) occurring between 66 and 73 ms from time zero.
    (ii) The decaying headform rotation vs. time curve shall cross the
zero angle with respect to its initial position at time of impact
relative to the pendulum centerline between 63 to 69 ms after the time
the peak rotation value is reached.
    (iii) All instrumentation data channels are defined to be zero when
the longitudinal centerline of the neck and pendulum are parallel.
    (iv) The headform rotation shall be calculated by the following
formula with the integration beginning at time zero:

Headform rotation (deg) = [int] [(Headform Angular Rate)y-
(Pendulum Angular Rate)y] dt

    (v) (Headform Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the headform (drawing 020-9050, sheet
1), and (Pendulum Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the pendulum interface plate (drawing
020-9051) (incorporated by reference, see Sec.  572.210).
    (3) Neck torsion qualification test.
    (i) The neck twist fixture (drawing DL210-200), referenced in
Figure W5, shall rotate in the direction of pre-impact flight with
respect to the pendulum's longitudinal centerline between 75 degrees
and 93 degrees, as measured by the rotary potentiometer (drawing SA572-
S51), and shall occur between 91 and 113 ms from time zero. The peak
moment, measured by the neck transducer (drawing SA572-S8) shall have a
value between 8 N-m (5.9 ft-lbf) and 10 N-m (7.4 ft-lbf) occurring
between 85 and 105 ms from time zero) (all incorporated by reference,
see Sec.  572.210).
    (ii) The decaying neck twist fixture rotation vs. time curve shall
cross the zero angle with respect to its initial position at time of
impact relative to the pendulum centerline between 84 to 103 ms after
the time the peak rotation value is reached.
    (iii) All instrumentation data channels are defined to be zero when
the zero pins are installed such that the neck is not in torsion.
    (iv) Time zero is defined as the time of initial contact between
the pendulum striker plate and the honeycomb material. All data
channels shall be at the zero level at this time.
    (c) Test procedure: The test procedure for the neck assembly is as
follows:
    (1) Soak the neck assembly in a controlled environment at any
temperature between 20.6 and 22.2 [deg]C (69 and 72 [deg]F) and a
relative humidity between 10 and 70 percent for at least four hours
prior to a test.
    (2)(i) For the fore-aft neck flexion test, mount the neck and
headform assembly, defined in subsection (a)(1) of this section, on the
pendulum described in Figure 22 of 49 CFR 572 so that the midsagittal
plane of the headform is vertical and coincides with the plane of
motion of the pendulum, and with the neck placement such that the front
side of the neck is closest to the honeycomb material.
    (ii) For the lateral neck flexion test, the test is carried out in
the direction opposing the primary load vector of the ensuing full
scale test for which the dummy is being qualified. A right flexion test
set-up that is used to qualify the dummy for an ensuing full scale
right side impact is depicted in Figure W4. A left flexion test set-up
would be a mirror image of that shown in Figure W4. Mount the neck and
headform assembly, defined in subsection (a)(1) of this section, on the
pendulum described in Figure 22 of 49 CFR 572 so that the midsagittal
plane of the headform is vertical and coincides with the plane of
motion of the pendulum, and with the neck placement such that the right
(or left) side of the neck is closest to the honeycomb material.
    (iii) For the neck torsion test, the test is carried out in the
direction opposing the primary load vector of the ensuing full scale
test for which the dummy is being qualified. A right torsion test set-
up that is used to qualify the dummy for an ensuing full scale right
side impact is depicted in Figure W5. A left flexion test set-up would
be a mirror image of that shown in Figure W5. Mount the neck assembly,
defined in subsection (a)(2) of this section, on the pendulum described
in Figure 22 of 49 CFR 572, as shown in Figure W5 of this subpart.
    (3)(i) Release the pendulum and allow it to fall freely from a
height to achieve an impact velocity of 4.7  0.1 m/s (15.6
 0.3 ft/s) for fore-aft flexion, 3.8  0.05 m/s
(12.5  0.2 ft/s) for lateral flexion, and 3.6
0.1 m/s (11.8  0.3 ft/s) for torsion, measured by an
accelerometer mounted on the pendulum as shown in Figure 22 of this
Part 572 at time zero.
    (ii) Stop the pendulum from the initial velocity with an
acceleration vs. time pulse that meets the velocity change as specified
in Table B of this section. Integrate the pendulum accelerometer data
channel to obtain the velocity vs. time curve beginning at time zero.

                                            Table B to Sec.   572.213
----------------------------------------------------------------------------------------------------------------
               Fore-aft flexion                       Lateral flexion                           Torsion
  Time   ----------------------------   Time   ----------------------------   Time   ---------------------------
  (ms)         m/s          ft/s        (ms)         m/s          ft/s        (ms)         m/s          ft/s
----------------------------------------------------------------------------------------------------------------
      10       1.1-2.1       3.6-6.9        10       1.7-2.2       5.6-7.2        10       0.9-1.3       3.0-4.3
      20       2.8-3.8      9.2-12.5        15       2.5-3.0       8.2-9.8        15       1.4-2.0       4.6-6.6
      30       4.1-5.1     13.5-16.7        20       3.4-3.9     11.2-12.8        20       2.0-2.6       6.6-8.5
----------------------------------------------------------------------------------------------------------------

Sec.  572.214  Shoulder assembly and test procedure.

    (a) The shoulder assembly for this test consists of the torso
assembly (drawing 020-4500) with string pot assembly (drawing SA572-S38
or SA572-S39) installed (incorporated by reference, see Sec.  572.210).
    (b) When the center of the shoulder of a completely assembled dummy
(drawing 020-0100) (incorporated by reference, see Sec.  572.210) is
impacted laterally by a test probe conforming to Sec.  572.219, at 3.6
 0.1 m/s (11.8  0.3 ft/s) according to the test
procedure in paragraph (c) of this section:
    (1) Maximum lateral shoulder displacement (compression) relative to
the spine, measured with the string pot assembly (drawing SA572-S38 or
SA572-S39) (incorporated by reference, see Sec.  572.210), must not be
less than 16 mm (0.63 in) and not more than 21 mm (0.83 in). The peak
force, measured by the impact probe as defined in Sec.  572.219

and calculated in accordance with paragraph (b)(2) of this section,
shall have a value between 1.24 kN (279 lbf) and 1.35 kN (303 lbf).
    (2) The force shall be calculated by the product of the impactor
mass and its measured deceleration.
    (c) Test procedure: The test procedure for the shoulder assembly is
as follows:
    (1) The dummy is clothed in the Q3s suit (drawing 020-8001)
(incorporated by reference, see Sec.  572.210). No additional clothing
or shoes are placed on the dummy.
    (2) Soak the dummy in a controlled environment at any temperature
between 20.6 and 22.2 [ordm]C (69 and 72 [ordm]F) and a relative
humidity from 10 to 70 percent for at least four hours prior to a test.
    (3) The shoulder test is carried out in the direction opposing the
primary load vector of the ensuing full scale test for which the dummy
is being qualified. A left shoulder test set-up that is used to qualify
the dummy for an ensuing full scale left side impact is depicted in
Figure W6. A right shoulder set-up would be a mirror image of that
shown in Figure W6. Seat the dummy on the qualification bench described
in Figure V3 of 49 CFR 572.194, the seat pan and seat back surfaces of
which are covered with thin sheets of PTFE (Teflon) (nominal stock
thickness: 2 to 3 mm) (3/32- to 1/8-inch) along the impact side of the
bench.
    (4) Position the dummy on the bench as shown in Figure W6, with the
ribs making contact with the seat back oriented 24.6 degrees relative
to vertical, the legs extended forward along the seat pan oriented 21.6
degrees relative to horizontal with the knees spaced 40 mm (1.57 in)
apart, and the arms positioned so that the upper arms are parallel to
the seat back ( 2 degrees) and the lower arms are
perpendicular to the upper arms.
    (5) The target point of the impact is a point on the shoulder that
is 15 mm above and perpendicular to the midpoint of a line connecting
the centers of the bolt heads of the two lower bolts (part
5000010) that connect the upper arm assembly (020-9750) to the
shoulder ball retaining ring (020-3533).
    (6) Impact the shoulder with the test probe so that at the moment
of contact the probe's longitudinal centerline should be horizontal
( 1 degrees), and the centerline of the probe should be
within 2 mm (0.08 in) of the target point.
    (7) Guide the test probe during impact so that there is no
significant lateral, vertical, or rotational movement.
    (8) No suspension hardware, suspension cables, or any other
attachments to the probe, including the velocity vane, shall make
contact with the dummy during the test.

Sec.  572.215  Thorax with arm assembly and test procedure.

    (a) The thorax assembly for this test consists of the torso
assembly (drawing 020-4500) with IR-TRACC (drawing SA572-S37)
(incorporated by reference, see Sec.  572.210) installed.
    (b) When the thorax of a completely assembled dummy (drawing 020-
0100) (incorporated by reference, see Sec.  572.210) is impacted
laterally by a test probe conforming to Sec.  572.219 at 5.0  0.1 m/s (16.4  0.3 ft/s) according to the test
procedure in paragraph (c) of this section:
    (1) Maximum lateral thorax displacement (compression) relative to
the spine, measured with the IR-TRACC (drawing SA572-S37) and processed
as set out in the PADI (all incorporated by reference, see Sec.
572.210), shall have a value between 23 mm (0.91 in) and 28 mm (1.10
in). The peak force occurring after 5 ms, measured by the impact probe
as defined in Sec.  572.219 and calculated in accordance with paragraph
(b)(2) of this section, shall have a value between 1.38 kN (310 lbf)
and 1.69 kN (380 lbf).
    (2) The force shall be calculated by the product of the impactor
mass and its measured deceleration.
    (3) Time zero is defined as the time of contact between the impact
probe and the arm. All channels should be at a zero level at this
point.
    (c) Test procedure: The test procedure for the thorax with arm
assembly is as follows:
    (1) The dummy is clothed in the Q3s suit (drawing 020-8001)
(incorporated by reference, see Sec.  572.210). No additional clothing
or shoes are placed on the dummy.
    (2) Soak the dummy in a controlled environment at any temperature
between 20.6 and 22.2 [ordm]C (69 and 72 [ordm]F) and a relative
humidity from 10 to 70 percent for at least four hours prior to a test.
    (3) The test is carried out in the direction opposing the primary
load vector of the ensuing full scale test for which the dummy is being
qualified. A left thorax test set-up that is used to qualify the dummy
for an ensuing full scale left side impact is depicted in Figure W7. A
right thorax set-up would be a mirror image of that shown in Figure W7.
Seat the dummy on the qualification bench described in Figure V3 of 49
CFR 572.194, the seat pan and seat back surfaces of which are covered
with thin sheets of PTFE (Teflon) (nominal stock thickness: 2 to 3 mm
(3/32- to 1/8-inch)) along the impact side of the bench.
    (4) Position the dummy on the bench as shown in Figure W7, with the
ribs making contact with the seat back oriented 24.6 degrees relative
to vertical, the legs extended forward along the seat pan oriented 21.6
degrees relative to horizontal with the knees spaced 40 mm (1.57 in)
apart. On the non-impact side of the dummy, the long axis of the upper
arm is positioned parallel to the seat back ( 2 degrees).
On the impact side, the upper arm is positioned such that the target
point intersects its long axis as described in (5) below. The long axis
of the upper arm is defined by section line A-A in drawing 020-9750
(incorporated by reference, see Sec.  572.210). Both of the lower arms
are set perpendicular to the upper arms.
    (5) The target point of the impact is the point of intersection on
the lateral aspect of the upper arm and a line projecting from the
thorax of the dummy. The projecting line is horizontal, runs parallel
to the coronal plane of the dummy, and passes through the midpoint of a
line connecting the centers of the bolt heads of the two IR-TRACC bolts
(part 5000646). The projected line should intersect the upper
arm within 2 mm (0.80 in) of its long axis.
    (6) Impact the arm with the test probe so that at the moment of
contact the probe's longitudinal centerline should be horizontal
( 1 degrees), and the centerline of the probe should be
within 2 mm (0.80 in) of the target point.
    (7) Guide the test probe during impact so that there is no
significant lateral, vertical, or rotational movement.
    (8) No suspension hardware, suspension cables, or any other
attachments to the probe, including the velocity vane, shall make
contact with the dummy during the test.

Sec.  572.216  Thorax without arm assembly and test procedure.

    (a) The thorax assembly for this test consists of the torso
assembly (drawing 020-4500) with IR-TRACC (drawing SA572-S37)
(incorporated by reference, see Sec.  572.210) installed.
    (b) When the thorax of a completely assembled dummy (drawing 020-
0100) with the arm (drawing 020-9700 or 020-9800) on the impacted side
removed is impacted laterally by a test probe conforming to Sec.
572.219 at 3.3  0.1 m/s (10.8  0.3 ft/s)
according to the test procedure in paragraph (c) of this section:
    (1) Maximum lateral thorax displacement (compression) relative to

the spine, measured with the IR-TRACC (drawing SA572-S37) and processed
as set out in the PADI (all incorporated by reference, see Sec.
572.210), shall have a value between 24 mm (0.94 in) and 31 mm (1.22
in). The peak force, measured by the impact probe as defined in Sec.
572.219 and calculated in accordance with paragraph (b)(2) of this
section, shall have a value between 620 N (139 lbf) and 770 N (173
lbf).
    (2) The force shall be calculated by the product of the impactor
mass and its measured deceleration.
    (c) Test procedure: The test procedure for the thorax without arm
assembly is as follows:
    (1) The dummy is clothed in the Q3s suit (drawing 020-8001)
(incorporated by reference, see Sec.  572.210). No additional clothing
or shoes are placed on the dummy.
    (2) Soak the dummy in a controlled environment at any temperature
between 20.6 and 22.2 [deg]C (69 and 72 [deg]F) and a relative humidity
from 10 to 70 percent for at least four hours prior to a test.
    (3) The test is carried out in the direction opposing the primary
load vector of the ensuing full scale test for which the dummy is being
qualified. A left thorax test set-up that is used to qualify the dummy
for an ensuing full scale left side impact is depicted in Figure W8. A
right thorax set-up would be a mirror image of that shown in Figure W8.
Seat the dummy on the qualification bench described in Figure V3 of 49
CFR 572.194, the seat pan and seat back surfaces of which are covered
with thin sheets of PTFE (Teflon) (nominal stock thickness: 2 to 3 mm
(\3/32\- to \1/8\-inch)) along the impact side of the bench.
    (4) Position the dummy on the bench as shown in Figure W8, with the
ribs making contact with the seat back oriented 24.6 degrees relative
to vertical, the legs extended forward along the seat pan oriented 21.6
degrees relative to horizontal with the knees spaced 40 mm (1.57 in)
apart, and the arm on the non-impacted side positioned so that the
upper arm is parallel ( 2 degrees) to the seat back and the
lower arm perpendicular to the upper arm.
    (5) The target point of the impact is the midpoint of a line
between the centers of the bolt heads of the two IR-TRACC bolts (part
5000646).
    (6) Impact the thorax with the test probe so that at the moment of
contact the probe's longitudinal centerline should be horizontal
( 1 degrees), and the centerline of the probe should be
within 2 mm (0.08 in) of the target point.
    (7) Guide the test probe during impact so that there is no
significant lateral, vertical, or rotational movement.
    (8) No suspension hardware, suspension cables, or any other
attachments to the probe, including the velocity vane, shall make
contact with the dummy during the test.

Sec.  572.217  Lumbar spine assembly and test procedure.

    (a) The lumbar spine and headform assembly (refer to Sec.
572.210(b)(2)(iv) and Sec.  572.210(a)(2)(vii)) for the purposes of the
fore-aft lumbar flexion and lateral lumbar flexion qualification tests,
as shown in Figures W9 and W10, consists of the headform (drawing 020-
9050, sheet 2) with angular rate sensor installed (drawing SA572-S58),
six-channel neck/lumbar load cell (drawing SA572-S8), lumbar spine
assembly (drawing 020-6000), lumbar interface plate (drawing 020-9062)
and pendulum interface plate (drawing 020-9051) with angular rate
sensor installed (drawing SA572-S58) (all incorporated by reference,
see Sec.  572.210).
    (b) When the lumbar spine and headform assembly is tested according
to the test procedure in paragraph (c) of this section, it shall have
the following characteristics:
    (1) Fore-aft lumbar flexion qualification test.
    (i) Plane D, referenced in Figure W9, shall rotate in the direction
of pre-impact flight with respect to the pendulum's longitudinal
centerline between 48 degrees and 57 degrees, which shall occur between
52 and 59 ms from time zero. The peak moment, measured by the neck/
lumbar transducer (drawing SA572-S8) (incorporated by reference, see
Sec.  572.210) shall have a value between 78 N-m (57.5 ft-lbf) and 94
N-m (69.3 ft-lbf) occurring between 46 and 57 ms from time zero.
    (ii) The decaying headform rotation vs. time curve shall cross the
zero angle with respect to its initial position at time of impact
relative to the pendulum centerline between 50 to 56 ms after the time
the peak rotation value is reached.
    (iii) All instrumentation data channels are defined to be zero when
the longitudinal centerline of the lumbar spine and pendulum are
parallel.
    (iv) The headform rotation shall be calculated by the following
formula with the integration beginning at time zero:
Headform rotation (deg) = [int] [(Headform Angular Rate)y -
(Pendulum Angular Rate)y] dt

    (v) (Headform Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the headform (drawing 020-9050, sheet
2), and (Pendulum Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the pendulum interface plate (drawing
020-9051) (all incorporated by reference, see Sec.  572.210).
    (2) Lateral lumbar flexion qualification test.
    (i) Plane D, referenced in Figure W10, shall rotate in the
direction of pre-impact flight with respect to the pendulum's
longitudinal centerline between 47 degrees and 59 degrees, which shall
occur between 50 and 59 ms from time zero. The peak moment, measured by
the neck/lumbar transducer (drawing SA572-S8) (incorporated by
reference, see Sec.  572.210) shall have a value between 78 N-m (57.5
ft-lbf) and 97 N-m (71.5 ft-lbf) occurring between 46 and 57 ms from
time zero.
    (ii) The decaying headform rotation vs. time curve shall cross the
zero angle with respect to its initial position at time of impact
relative to the pendulum centerline between 47 to 59 ms after the time
the peak rotation value is reached.
    (iii) All instrumentation data channels are defined to be zero when
the longitudinal centerline of the lumbar spine and pendulum are
parallel.
    (iv) The headform rotation shall be calculated by the following
formula with the integration beginning at time zero:

Headform rotation (deg) = [int] [(Headform Angular Rate)y-
(Pendulum Angular Rate)y] dt

    (v) (Headform Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the headform (drawing 020-9050, sheet
2), and (Pendulum Angular Rate)y is the angular rate about
the y-axis in deg/sec measured on the pendulum interface plate (drawing
020-9051) (all incorporated by reference, see Sec.  572.210).
    (c) Test procedure: The test procedure for the lumbar spine
assembly is as follows:
    (1) Soak the lumbar spine assembly in a controlled environment at
any temperature between 20.6 and 22.2 [deg]C (69 and 72 [deg]F) and a
relative humidity between 10 and 70 percent for at least four hours
prior to a test.
    (2)(i) For the fore-aft lumbar flexion test, mount the lumbar spine
and headform assembly, defined in subsection (a) of this section, on
the pendulum described in Figure 22 of 49 CFR 572 so that the
midsagittal plane of the headform is vertical and coincides with the
plane of motion of the pendulum, and with the lumbar spine placement
such that the front side of the lumbar spine is closest to the
honeycomb material.

    (ii) For the lateral lumbar flexion test, the test is carried out
in the direction opposing the primary load vector of the ensuing full
scale test for which the dummy is being qualified. A right flexion test
set-up that is used to qualify the dummy for an ensuing a full scale
right side impact is depicted in Figure W10. A left flexion test set-up
would be a mirror image of that shown in Figure W10. Mount the lumbar
spine and headform assembly, defined in subsection (a)(1) of this
section, on the pendulum described in Figure 22 of 49 CFR 572 so that
the midsagittal plane of the headform is vertical and coincides with
the plane of motion of the pendulum, and with the lumbar spine
placement such that the right (or left) side of the lumbar spine is
closest to the honeycomb material.
    (3)(i) Release the pendulum and allow it to fall freely from a
height to achieve an impact velocity of 4.4  0.1 m/s (14.4
 0.3 ft/s), measured by an accelerometer mounted on the
pendulum as shown in Figure 22 of this Part 572 at time zero.
    (ii) Stop the pendulum from the initial velocity with an
acceleration vs. time pulse that meets the velocity change as specified
in Table C of this section. Integrate the pendulum accelerometer data
channel to obtain the velocity vs. time curve beginning at time zero.

                                            Table C to Sec.   572.217
----------------------------------------------------------------------------------------------------------------
                                                                  Fore-aft flexion           Lateral flexion
                          Time (ms)                          ---------------------------------------------------
                                                                  m/s          ft/s         m/s          ft/s
----------------------------------------------------------------------------------------------------------------
10..........................................................      1.3-1.7      4.3-5.6      1.3-1.7      4.3-5.6
20..........................................................      2.7-3.7     8.9-12.1      2.7-3.7     8.9-12.1
30..........................................................      4.1-4.9    13.5-16.1      4.0-4.8    13.1-15.7
----------------------------------------------------------------------------------------------------------------

Sec.  572.218  Pelvis assembly and test procedure.

    (a) The pelvis assembly (drawing 020-7500) for this test includes a
uniaxial pubic load cell (drawing SA572-S7) installed on the non-impact
side of the pelvis (all incorporated by reference, see Sec.  572.210).
    (b) When the center of the pelvis of a completely assembled dummy
(drawing 020-0100) (incorporated by reference, see Sec.  572.210) is
impacted laterally by a test probe conforming to Sec.  572.219 at 4.0
 0.1 m/s (13.1  0.3 ft/s) according to the test
procedure in paragraph (c) of this section:
    (1) Maximum pubic load, measured with the uniaxial pubic load cell
(drawing SA572-S7) (incorporated by reference, see Sec.  572.210),
shall have a value between 700 N (157 lbf) and 870 N (196 lbf). The
peak force, measured by the impact probe as defined in Sec.  572.219
and calculated in accordance with paragraph (b)(2) of this section,
shall have a value between 1.57 kN (353 lbf) and 1.81 kN (407 lbf).
    (2) The force shall be calculated by the product of the impactor
mass and its measured deceleration.
    (c) Test procedure: The test procedure for the pelvis assembly is
as follows:
    (1) The dummy is clothed in the Q3s suit (drawing 020-8001)
(incorporated by reference, see Sec.  572.210). No additional clothing
or shoes are placed on the dummy.
    (2) Soak the dummy in a controlled environment at any temperature
between 20.6 and 22.2 [deg]C (69 and 72 [deg]F) and a relative humidity
from 10 to 70 percent for at least four hours prior to a test.
    (3) The pelvis test is carried out in the direction opposing the
primary load vector of the ensuing full scale test for which the dummy
is being qualified. A left pelvis test set-up that is used to qualify
the dummy for an ensuing full scale left side impact is depicted in
Figure W11. A right pelvis test set-up would be a mirror image of that
shown in Figure W11. Seat the dummy on the qualification bench
described in Figure V3 of 49 CFR 572.194, the seat pan and seat back
surfaces of which are covered with thin sheets of PTFE (Teflon)
(nominal stock thickness: 2 to 3 mm (\3/32\- to \1/8\-inch)) along the
impact side of the bench.
    (4) Position the dummy on the bench as shown in Figure W11, with
the ribs making contact with the seat back oriented 24.6 degrees
relative to vertical, the legs extended forward along the seat pan
oriented 21.6 degrees relative to horizontal with the knees spaced 40
mm (1.57 in) apart. The arms should be positioned so that the arm on
the non-impacted side is parallel to the seat back with the lower arm
perpendicular to the upper arm, and the arm on the impacted side is
positioned upwards away from the pelvis.
    (5) Establish the impact point at the center of the pelvis so that
the impact point of the longitudinal centerline of the probe is located
185 mm (7.28 in) from the center of the knee pivot screw (part
020-9008) and centered vertically on the femur.
    (6) Impact the pelvis with the test probe so that at the moment of
contact the probe's longitudinal centerline should be horizontal
( 1 degrees), and the centerline of the probe should be
within 2 mm (0.08 in) of the center of the pelvis.
    (7) Guide the test probe during impact so that there is no
significant lateral, vertical, or rotational movement.
    (8) No suspension hardware, suspension cables, or any other
attachments to the probe, including the velocity vane, shall make
contact with the dummy during the test.

Sec.  572.219  Test conditions and instrumentation.

    (a) The following test equipment and instrumentation is needed for
qualification as set forth in this subpart:
    (1) The test probe for shoulder, thorax, and pelvis impacts is of
rigid metallic construction, concentric in shape, and symmetric about
its longitudinal axis. It has a mass of 3.81  0.02 kg (8.40
 0.04 lb) and a minimum mass moment of inertia of 560 kg-
cm\2\ (0.407 lbf-in-sec\2\) in yaw and pitch about the CG. One-third
(\1/3\) of the weight of the suspension cables and their attachments to
the impact probe is included in the calculation of mass, and such
components may not exceed five percent of the total weight of the test
probe. The impacting end of the probe, perpendicular to and concentric
with the longitudinal axis, is at least 25.4 mm (1.0 in) long, and has
a flat, continuous, and non-deformable 70.0  0.25 mm (2.76
 0.01 in) diameter face with an edge radius between 6.4-
12.7 mm (0.25 to 0.5 in). The probe's end opposite to the impact face
has provisions for mounting of an accelerometer with its sensitive axis
collinear with the longitudinal axis of the probe. No concentric
portions of the impact probe may exceed the diameter of the impact
face. The impact probe shall have a free air resonant frequency of not
less than 1000 Hz, which may be determined using the procedure listed
in the PADI.
    (2) Head accelerometers have dimensions, response characteristics,

and sensitive mass locations specified in drawing SA572-S4 and are
mounted in the head as shown in drawing 020-0100, sheet 2 of 5
(incorporated by reference, see Sec.  572.210).
    (3) The upper neck force and moment transducer has the dimensions,
response characteristics, and sensitive axis locations specified in
drawing SA572-S8 and is mounted in the head-neck assembly as shown in
drawing 020-0100, sheet 2 of 5 (incorporated by reference, see Sec.
572.210).
    (4) The angular rate sensors for the fore-aft neck flexion and
lateral neck flexion qualification tests have the dimensions and
response characteristics specified in drawing SA572-S58 (incorporated
by reference, see Sec.  572.210) and are mounted in the headform and on
the pendulum as shown in Figures W3, W4 of this subpart.
    (5) The string pot shoulder deflection transducers have the
dimensions and response characteristics specified in drawing SA572-S38
or SA572-S39 and are mounted to the torso assembly as shown in drawing
020-0100, sheet 2 of 5 (all incorporated by reference, see Sec.
572.210).
    (6) The IR-TRACC thorax deflection transducers have the dimensions
and response characteristics specified in drawing SA572-S37 and are
mounted to the torso assembly as shown in drawing 020-0100, sheet 2 of
5 (incorporated by reference, see Sec.  572.210).
    (7) The lumbar spine force and moment transducer has the
dimensions, response characteristics, and sensitive axis locations
specified in drawing SA572-S8 and is mounted in the torso assembly as
shown in drawing 020-0100, sheet 2 of 5 (incorporated by reference, see
Sec.  572.210).
    (8) The angular rate sensors for the fore-aft lumbar flexion and
lateral lumbar flexion qualification tests have the dimensions and
response characteristics specified in drawing SA572-S58 (incorporated
by reference, see Sec.  572.210) and are mounted in the headform and on
the pendulum as shown in Figures W9, W10 of this subpart.
    (9) The pubic force transducers have the dimensions and response
characteristics specified in drawing SA572-S7 and are mounted in the
torso assembly as shown in drawing 020-0100, sheet 2 of 5 (incorporated
by reference, see Sec.  572.210).
    (b) The following instrumentation may be required for installation
in the dummy for compliance testing. If so, it is installed during
qualification procedures as described in this subpart:
    (1) The optional angular rate sensors for the head have the
dimensions and response characteristics specified in any of drawings
SA572-S55, SA572-S56, SA572-S57 or SA572-S58 and are mounted in the
head as shown in drawing 020-0100, sheet 2 of 5 (all incorporated by
reference, see Sec.  572.210).
    (2) The upper spine accelerometers have the dimensions, response
characteristics, and sensitive mass locations specified in drawing
SA572-S4 and are mounted in the torso assembly as shown in drawing 020-
0100, sheet 2 of 5 (all incorporated by reference, see Sec.  572.210).
    (3) The pelvis accelerometers have the dimensions, response
characteristics, and sensitive mass locations specified in drawing
SA572-S4 and are mounted in the torso assembly as shown in drawing 020-
0100, sheet 2 of 5 (all incorporated by reference, see Sec.  572.210).
    (4) The T1 accelerometer has the dimensions, response
characteristics, and sensitive mass location specified in drawing
SA572-S4 and is mounted in the torso assembly as shown in drawing 020-
0100, sheet 2 of 5 (incorporated by reference, see Sec.  572.210).
    (5) The lower neck force and moment transducer has the dimensions,
response characteristics, and sensitive axis locations specified in
drawing SA572-S8 and is mounted to the neck assembly as shown in
drawing 020-0100, sheet 2 of 5 (incorporated by reference, see Sec.
572.210).
    (6) The tilt sensor has the dimensions and response characteristics
specified in drawing SA572-S44 and is mounted to the torso assembly as
shown in drawing 020-0100, sheet 2 of 5 (incorporated by reference, see
Sec.  572.210).
    (c) The outputs of transducers installed in the dummy and in the
test equipment specified by this part are to be recorded in individual
data channels that conform to SAE Recommended Practice J211
(incorporated by reference, see Sec.  572.210) except as noted, with
channel frequency classes as follows:
    (1) Pendulum acceleration, CFC 180,
    (2) Pendulum angular rate, CFC 60,
    (3) Neck twist fixture rotation, CFC 60,
    (4) Test probe acceleration, CFC 180,
    (5) Head accelerations, CFC 1000,
    (6) Headform angular rate, CFC 60,
    (7) Neck moments, upper and lower, CFC 600,
    (7) Shoulder deflection, CFC 180,
    (8) Thorax deflection, CFC 180,
    (9) Upper spine accelerations, CFC 180,
    (10) T1 acceleration, CFC 180,
    (11) Pubic force, CFC 180,
    (12) Pelvis accelerations, CFC 1000.
    (d) Coordinate signs for instrumentation polarity are to conform to
SAE Information Report J1733 (incorporated by reference, see Sec.
572.210).
    (e) The mountings for sensing devices have no resonant frequency
less than 3 times the frequency range of the applicable channel class.
    (f) Limb joints are set at one G, barely restraining the weight of
the limb when it is extended horizontally. The force needed to move a
limb segment is not to exceed 2G throughout the range of limb motion.
    (g) Performance tests of the same component, segment, assembly, or
fully assembled dummy are separated in time by not less than 30 minutes
unless otherwise noted.
    (h) Surfaces of dummy components may not be painted except as
specified in this subpart or in drawings subtended by this subpart.
BILLING CODE 4910-59-P

Appendix--Figures to Subpart W of Part 572

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    Issued on: November 8, 2013.
Christopher J. Bonanti,
Associate Administrator for Rulemaking.
[FR Doc. 2013-27438 Filed 11-20-13; 8:45 am]
BILLING CODE 4910-59-C