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 a document 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, 1200 New Jersey Avenue SE, Washington DC 20590, telephone 202-366-9826, and is available from the sources listed in paragraphs (a) and (b) of this section. It is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email [email protected] or go to www.archives.gov/federal-register/cfr/ibr-locations.html.

(a) NHTSA Technical Information Services, 1200 New Jersey Ave. SE, Washington, DC 20590, telephone 202-366-5965.

(1) A parts/drawing list entitled, “Parts/Drawings List, Part 572 Subpart W, Q3s Three-Year-Old Child Side Impact Dummy” dated (and revised) January 2021 (Parts/Drawings List); IBR approved for § 572.211.

(2) A drawings and inspection package entitled, “Drawings and Specifications for Q3s Three-Year-Old Child Side Impact Dummy, Part 572 Subpart W” dated (and revised) January 2021 (Drawings and Specifications); IBR approved for §§ 572.211, 572.212, 572.213, 572.214, 572.215, 572.216, 572.217, 572.218, and 572.219.

(3) A procedures manual entitled “Procedures for Assembly, Disassembly, and Inspection (PADI) of the Q3s Child Side Impact Crash Test Dummy” dated January 2021 (PADI); IBR approved for §§ 572.211, 572.215(b), 572.216(b), and 572.219(a).

(b) SAE International, 400 Commonwealth Drive, Warrendale, PA 15096, call 1-877-606-7323, https://www.sae.org/.

(1) SAE Recommended Practice J211/1, Rev. Mar 95, “Instrumentation for Impact Tests—Part 1—Electronic Instrumentation,” (SAE J211); IBR approved for § 572.219;

(2) SAE Information Report J1733 of 1994-12, “Sign Convention for Vehicle Crash Testing,” December 1994, (SAE J1733); IBR approved for § 572.219.

[85 FR 69925, Nov. 3, 2020, as amended at 86 FR 66218, Nov. 22, 2021]

(a) The Q3s Three-Year-Old Child Test Dummy is defined by the following materials:

(1) The Parts/Drawings List (incorporated by reference, see § 572.210);

(2) The Drawings and Specifications (incorporated by reference, see § 572.210);

(3) The PADI (incorporated by reference, see § 572.210).

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

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(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).

(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 in accordance with paragraph (c) of this section, the peak resultant acceleration at the location of the accelerometers at the head CG shall have a value between 255 G and 300 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 in accordance with paragraph (c) of this section, the peak resultant acceleration at the location of the accelerometers at the head CG shall have a value between 114 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 15 G (zero to peak).

(c) The test procedure for the head assembly is as follows:

(1) Soak the head assembly in a controlled environment at any temperature between 20.6 and 22.2 °C 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 in appendix A to this subpart. The lowest point on the forehead must be 376.0 ± 1.0 mm 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 in appendix A to this subpart. 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 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 thick and 610 mm square. The impact surface shall be clean, dry and have a surface finish of not less than 0.2 microns (RMS) and not more than 2.0 microns (RMS).

(5) Allow at least 2 hours between successive tests on the same head.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(a)(1) The neck and headform assembly for the purposes of the fore-aft neck flexion and lateral neck flexion qualification tests, as shown in figures W3 and W4 in appendix A to this subpart, 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).

(2) The neck assembly for the purposes of the neck torsion qualification test, as shown in figure W5 in appendix A to this subpart, 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).

(b) When the neck and headform assembly as defined in paragraph (a)(1) of this section, or the neck assembly as defined in paragraph (a)(2) of this section, 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 in appendix A to this subpart, shall rotate in the direction of pre-impact flight with respect to the pendulum's longitudinal centerline between 69.5 degrees and 81.0 degrees. During the time interval while the rotation is within these angles, the peak moment measured by the neck transducer (drawing SA572-S8) shall have a value between 41.5 N-m and 50.7 N-m.

(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 45 to 55 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) = ∫ [(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).

(2) Lateral neck flexion qualification test. (i) Plane D, referenced in Figure W4 in appendix A to this subpart, shall rotate in the direction of pre-impact flight with respect to the pendulum's longitudinal centerline between 76.5 degrees and 87.5 degrees. During the time interval while the rotation is within these angles, the peak moment measured by the neck transducer (drawing SA572-S8) shall have a value between 25.3 N-m and 32.0 N-m.

(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 61 to 71 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) = ∫ [(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).

(3) Neck torsion qualification test. (i) The neck twist fixture (drawing DL210-200), referenced in figure W5 in appendix A to this subpart, shall rotate in the direction of pre-impact flight with respect to the pendulum's longitudinal centerline between 74.5 degrees and 91.0 degrees, as measured by the rotary potentiometer (drawing SA572-S51). During the time interval while the rotation is within these angles, the peak moment measured by the neck transducer (drawing SA572-S8) shall have a value between 8.0 N-m and 10.0 N-m.

(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 85 to 102 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.

(c) 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 °C 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 paragraph (a)(1) of this section, on the pendulum, described in figure 22 to § 572.33, 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 as shown in figure W3 in appendix A to this subpart.

(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 in appendix A to this subpart. A left flexion test set-up would be depicted by a mirror image of all components beneath the pendulum interface plate in Figure W4. Mount the neck and headform assembly, defined in paragraph (a)(1) of this section, on the pendulum, described by figure 22 to § 572.33, 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 as shown in figure W4.

(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 in appendix A to this subpart. A left flexion test set-up would be a mirror image of that shown in figure W5. Mount the neck assembly, defined in paragraph (a)(2) of this section, on the pendulum, described by figure 22 to § 572.33, as shown in figure W5.

(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 for fore-aft flexion, 3.8 ± 0.1 m/s for lateral flexion, and 3.6 ± 0.1 m/s for torsion, measured by an accelerometer mounted on the pendulum 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 1 to this section. Integrate the pendulum accelerometer data channel to obtain the velocity vs. time curve beginning at time zero.

(iii) Time zero is defined as the time of initial contact between the pendulum striker plate and the honeycomb material.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(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.

(b) When the center of the shoulder of a completely assembled dummy (drawing 020-0100) is impacted laterally by a test probe conforming to § 572.219, at 3.6 ± 0.1 m/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 potentiometer assembly (drawing SA572-S38 or SA572-S39), must not be less than 17.0 mm and not more than 22.0 mm. The peak force, measured by the impact probe as defined in § 572.219 and calculated in accordance with paragraph (b)(2) of this section, shall have a value between 1123 N and 1437 N.

(2) The force shall be calculated by the product of the impactor mass and its measured deceleration.

(c) The test procedure for the shoulder assembly is as follows:

(1) The dummy is clothed in the Q3s suit (drawing 020-8001). 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 °C 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 in appendix A to this subpart. 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 to § 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) 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 apart. Position the arms so that the upper arms are parallel to the seat back (±2 degrees) and the lower arms are parallel to the dummy's sagittal plane and perpendicular to the upper arms. Move the elbows inward (medially) until initial contact occurs between the sleeve and the portion of the suit covering the thorax while maintaining the relationships between the arms, seat back, and sagittal plane.

(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 degree), and the centerline of the probe should be within 2 mm 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.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(a) The thorax assembly for this test consists of the torso assembly (drawing 020-4500) with an IR-TRACC (drawing SA572-S37) installed.

(b) When the thorax of a completely assembled dummy (drawing 020-0100) is impacted laterally by a test probe conforming to § 572.219 at 5.0 ± 0.1 m/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 (incorporated by reference, see § 572.210), shall have a value between 22.5 mm and 27.5 mm. The peak force occurring after 5 ms, measured by the impact probe as defined in § 572.219 and calculated in accordance with paragraph (b)(2) of this section, shall have a value between 1360 N and 1695 N.

(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) The test procedure for the thorax with arm assembly is as follows:

(1) The dummy is clothed in the Q3s suit (drawing 020-8001). 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 °C 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 in appendix A to this subpart. 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 to § 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) along the impact side of the bench.

(4) Position the dummy on the bench as shown in figure W7 in appendix A to this subpart, 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 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 paragraph (c)(5) of this section. The long axis of the upper arm is defined by section line A-A in drawing 020-9750. Both of the lower arms are set perpendicular to the upper arms and parallel to the dummy's sagittal plane. Move the elbows inward (medially) until initial contact occurs between the sleeve and the portion of the suit covering the thorax while maintaining the relationships between the arms, seat back, and sagittal plane.

(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 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 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.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(a) The thorax assembly for this test consists of the torso assembly (drawing 020-4500) with IR-TRACC (drawing SA572-S37) 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 § 572.219 at 3.3 ± 0.1 m/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 (incorporated by reference, see § 572.210), shall have a value between 24.5 mm and 30.5 mm. The peak force, measured by the impact probe as defined in § 572.219 and calculated in accordance with paragraph (b)(2) of this section, shall have a value between 610 N and 754 N.

(2) The force shall be calculated by the product of the impactor mass and its measured deceleration.

(c) The test procedure for the thorax without arm assembly is as follows:

(1) The dummy is clothed in the Q3s suit (drawing 020-8001). 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 °C 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 in appendix A to this subpart. 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 to § 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) along the impact side of the bench.

(4) Position the dummy on the bench as shown in figure W8 in appendix A to this subpart, 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 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 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.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(a) The lumbar spine and headform assembly for the purposes of the fore-aft lumbar flexion and lateral lumbar flexion qualification tests, as shown in Figures W9 and W10 in appendix A to this subpart, 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).

(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 in appendix A to this subpart, shall rotate in the direction of pre-impact flight with respect to the pendulum's longitudinal centerline between 47.0 degrees and 58.5 degrees. During the time interval while the rotation is within these angles, the peak moment measured by the neck/lumbar transducer (drawing SA572-S8) shall have a value between 78.2 N-m and 96.2 N-m.

(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 49 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) = ∫ [(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).

(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 46.1 degrees and 58.2 degrees. During the time interval while the rotation is within these angles, the peak moment measured by the neck/lumbar transducer (drawing SA572-S8) shall have a value between 79.4 N-m and 98.1 N-m.

(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 48 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) = ∫ [(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).

(c) 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 °C 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 paragraph (a) of this section, on the pendulum described Figure 22 to § 572.33 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 in appendix A to this subpart. A left flexion test set-up would be depicted by a mirror image of all components beneath the pendulum interface plate in Figure W10. Mount the lumbar spine and headform assembly, defined in paragraph (a)(1) of this section, on the pendulum described in figure 22 to § 572.33 so that the midsagittal plane of the headform is vertical and perpendicular to the direction 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, measured by an accelerometer mounted on the pendulum as shown in Figure 22 to § 572.33 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 1 to this section. Integrate the pendulum accelerometer data channel to obtain the velocity vs. time curve beginning at time zero.

(iii) Time zero is defined as the time of initial contact between the pendulum striker plate and the honeycomb material.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(a) The pelvis assembly (drawing 020-7500) for this test may include either a uniaxial pubic load cell (drawing SA572-S7) or a pubic load cell structural replacement (drawing 020-7150) installed on the non-impact side of the pelvis.

(b) When the center of the pelvis of a completely assembled dummy (drawing 020-0100) is impacted laterally by a test probe conforming to § 572.219 at 4.0 ± 0.1 m/s according to the test procedure in paragraph (c) of this section:

(1) The peak force, measured by the impact probe as defined in § 572.219 and calculated in accordance with paragraph (b)(2) of this section, shall have a value between 1587 N and 1901 N.

(2) The force shall be calculated by the product of the impactor mass and its measured deceleration.

(c) The test procedure for the pelvis assembly is as follows:

(1) The dummy is clothed in the Q3s suit (drawing 020-8001). 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 °C (69 and 72 °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 in appendix A to this subpart. 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 to § 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) along the impact side of the bench.

(4) Position the dummy on the bench as shown in figure W11 in appendix A to this subpart, 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 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 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 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.

All assemblies and drawings referenced in this section are contained in Drawings and Specifications, incorporated by reference, see § 572.210.

(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 and a minimum mass moment of inertia of 560 kg-cm 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 long, and has a flat, continuous, and non-deformable 70.0 ± 0.25 mm diameter face with an edge radius between 6.4-12.7 mm. 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 (incorporated by reference, see § 572.210).

(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.

(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.

(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 and are mounted in the headform and on the pendulum as shown in figures W3 and W4 in appendix A to this subpart.

(5) The string potentiometer 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.

(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.

(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.

(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 and are mounted in the headform and on the pendulum as shown in figures W9, W10 in appendix A to this subpart.

(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.

(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.

(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.

(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.

(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.

(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.

(7) 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.

(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 J211 (incorporated by reference, see § 572.210) except as noted, with channel frequency classes (CFCs) 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,

(8) Shoulder deflection, CFC 180,

(9) Thorax deflection, CFC 180,

(10) Upper spine accelerations, CFC 180,

(11) T1 acceleration, CFC 180,

(12) Pubic force, CFC 180,

(13) Pelvis accelerations, CFC 1000.

(d) Coordinate signs for instrumentation polarity are to conform to SAE J1733 (incorporated by reference, see § 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.