83 FR 53168 - Special Conditions: Bombardier, Inc., BD-700-2A12 and BD-700-2A13 Airplanes; Multiple-Place Side-Facing Seats With Active Leg-Flail Restraint Device and Shoulder-Belt Airbags

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 83, Issue 204 (October 22, 2018)

Page Range		53168-53171
FR Document		2018-22929

These special conditions are issued for the Bombardier, Inc., (Bombardier) BD-700-2A12 and BD-700-2A13 airplanes, marketed respectively as Global 7000 and Global 8000. These airplanes, as modified by Bombardier, will have novel or unusual design features when compared to the state of technology envisioned in the airworthiness standards for transport-category airplanes. These design features are multiple-place side-facing seats with active leg-flail restraint devices and shoulder-belt airbags. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

Federal Register, Volume 83 Issue 204 (Monday, October 22, 2018)

[Federal Register Volume 83, Number 204 (Monday, October 22, 2018)]
[Rules and Regulations]
[Pages 53168-53171]
From the Federal Register Online [www.thefederalregister.org]
[FR Doc No: 2018-22929]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2018-0714; Special Conditions No. 25-734-SC]

Special Conditions: Bombardier, Inc., BD-700-2A12 and BD-700-2A13
Airplanes; Multiple-Place Side-Facing Seats With Active Leg-Flail
Restraint Device and Shoulder-Belt Airbags

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for the Bombardier, Inc.,
(Bombardier) BD-700-2A12 and BD-700-2A13 airplanes, marketed
respectively as Global 7000 and Global 8000. These airplanes, as
modified by Bombardier, will have novel or unusual design features when
compared to the state of technology envisioned in the airworthiness
standards for transport-category airplanes. These design features are
multiple-place side-facing seats with active leg-flail restraint
devices and shoulder-belt airbags. The applicable airworthiness
regulations do not contain adequate or appropriate safety standards for
this design feature. These special conditions contain the additional
safety standards that the Administrator considers necessary to
establish a level of safety equivalent to that established by the
existing airworthiness standards.

DATES: This action is effective on Bombardier on October 22, 2018. Send
comments on or before December 6, 2018.

ADDRESSES: Send comments identified by Docket No. FAA-2018-0714 using
any of the following methods:
Federal eRegulations Portal: Go to http://www.regulations.gov/ and follow the online instructions for sending
your comments electronically.
Mail: Send comments to Docket Operations, M-30, U.S.
Department of Transportation (DOT), 1200 New Jersey Avenue SE, Room
W12-140, West Building Ground Floor, Washington, DC 20590-0001.
Hand Delivery or Courier: Take comments to Docket
Operations in Room W12-140 of the West Building Ground Floor at 1200
New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Fax: Fax comments to Docket Operations at 202-493-2251.
Privacy: The FAA will post all comments it receives, without
change, to http://www.regulations.gov/, including any personal
information the commenter provides. Using the search function of the
docket website, anyone can find and read the electronic form of all
comments received into any FAA docket, including the name of the
individual sending the comment (or signing the comment for an
association, business, labor union, etc.). DOT's complete Privacy Act
Statement can be found in the Federal Register published on April 11,
2000 (65 FR 19477-19478).
Docket: Background documents or comments received may be read at
http://www.regulations.gov/ at any time. Follow the online instructions
for accessing the docket or go to Docket Operations in Room W12-140 of
the West Building Ground Floor at 1200 New Jersey Avenue SE,
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays.

FOR FURTHER INFORMATION CONTACT: Alan Sinclair, Airframe and Cabin
Safety Section, AIR-675, Transport Standards Branch, Policy and
Innovation Division, Aircraft Certification Service, Federal Aviation
Administration, 2200 South 216th Street, Des Moines, Washington 98198;
telephone and fax 206-231-3215; email alan.sinclair@faa.gov.

SUPPLEMENTARY INFORMATION: The substance of these special conditions
has been published in the Federal Register for public comment in
several prior instances with no substantive comments received. The FAA
therefore finds it unnecessary to delay the effective date and finds
that good cause exists for making these special conditions effective
upon publication in the Federal Register.

Comments Invited

We invite interested people to take part in this rulemaking by
sending written comments, data, or views. The most helpful comments
reference a specific portion of the special conditions, explain the
reason for any recommended change, and include supporting data.
We will consider all comments we receive by the closing date for
comments. We may change these special

[[Page 53169]]

conditions based on the comments we receive.

Background

On June 10, 2015, Bombardier applied for a supplemental type
certificate for multiple-place side-facing seats equipped with active
leg-flail restraint devices and shoulder-belt airbags in the Model BD-
700-2A12 and BD-700-2A13 airplanes.
These airplanes are derivatives of the Model BD-700 series of
airplanes and are marketed as the Bombardier Global 7000 (Model BD-700-
2A12) and Global 8000 (Model BD-700-2A13). These airplanes are twin-
engine, transport-category, executive-interior business jets. The
maximum passenger capacity is 19 and the maximum takeoff weights are
106,250 lb. (Model BD-700-2A12) and 104,800 lb. (Model BD-700-2A13).

Type Certification Basis

Under the provisions of title 14, Code of Federal Regulations (14
CFR) 21.101, Bombardier must show that the Model BD-700-2A12 and BD-
700-2A13 airplanes, as changed, continue to meet the applicable
provisions of the regulations listed in type certificate no. T00003NY
or the applicable regulations in effect on the date of application for
the change, except for earlier amendments as agreed upon by the FAA.
If the Administrator finds that the applicable airworthiness
regulations (i.e., 14 CFR part 25) do not contain adequate or
appropriate safety standards for the Bombardier BD-700-2A12 and BD-700-
2A13 airplanes because of a novel or unusual design feature, special
conditions are prescribed under the provisions of Sec. 21.16.
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply for a supplemental type
certificate to modify any other model included on the same type
certificate to incorporate the same novel or unusual design feature,
these special conditions would also apply to the other model under
Sec. 21.101.
In addition to the applicable airworthiness regulations and special
conditions, the Bombardier Model BD-700-2A12 and BD-700-2A13 airplanes
must comply with the fuel-vent and exhaust-emission requirements of 14
CFR part 34, and the noise certification requirements of 14 CFR part
36.
The FAA issues special conditions, as defined in 14 CFR 11.19, in
accordance with Sec. 11.38, and they become part of the type
certification basis under Sec. 21.101.

Novel or Unusual Design Features

The Bombardier Model BD-700-2A12 and BD-700-2A13 airplanes will
incorporate the following novel or unusual design features:
Multiple-place side-facing seats with active leg-flail restraint
devices and shoulder-belt airbags.

Discussion

Many proposed airplane interior configurations include multiple-
place side-facing seats and single-place side-facing seats (hereafter
referred to as side-facing seats). Some of these side-facing seat
designs include an airbag system in the shoulder belt, and some may
also include leg-flail protection. The FAA has determined that the
existing regulations do not provide adequate or appropriate safety
standards for occupants of side facing seats. In addition, the FAA has
determined that the existing regulations do not provide adequate or
appropriate safety standards for the addition of airbag systems in the
shoulder belt on side-facing seats.
Side-facing seats are considered a novel design for transport-
category airplanes that include Sec. 25.562 in their certification
basis. The performance measures of Sec. 25.562(c) only address
forward- and aft-facing seats, and do not provide adequate or
appropriate safety standards for occupants of side-facing seats because
they do not consider the differences in the dynamic forces that apply
to a side-facing occupant.
The FAA issued Policy Statement PS-ANM-25-03-R1 to provide
technical criteria for approving side-facing seats, to be issued as
special conditions for the design approval of such seats. The technical
criteria set forth in that policy are the result of FAA research
findings and provide the level of safety envisioned in Sec. 25.562.
These technical criteria are applicable to all fully side-facing seats,
both multiple-place and single-place.
These special conditions contain the additional safety standards
that the Administrator considers necessary to establish a level of
safety equivalent to that established by the existing airworthiness
standards.

Applicability

As discussed above, these special conditions are applicable to the
Bombardier BD-700-2A12 and BD-700-2A13 airplanes. Should Bombardier
apply at a later date for a change to the type certificate to include
another model incorporating the same novel or unusual design feature,
these special conditions would apply to that model as well.

Conclusion

This action affects only certain novel or unusual design features
on the Bombardier BD-700-2A12 and BD-700-2A13 airplanes. It is not a
rule of general applicability.

List of Subjects in 14 CFR Part 25

Aircraft, Aviation safety, Reporting and recordkeeping
requirements.

Authority Citation

The authority citation for these special conditions is as follows:

Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701, 44702,
44704.

The Special Conditions

Accordingly, pursuant to the authority delegated to me by the
Administrator, the following special conditions are issued as part of
the type certification basis for Bombardier BD-700-2A12 and BD-700-2A13
airplanes as modified by Bombardier.
1. Additional requirements applicable to tests or rational analysis
conducted to show compliance with Sec. Sec. 25.562 and 25.785 for
side-facing seats:
a. The longitudinal test(s) conducted in accordance with Sec.
25.562(b)(2) to show compliance with the seat-strength requirements of
Sec. 25.562(c)(7) and (8), and these special conditions must have an
ES-2re anthropomorphic test dummy (ATD) (49 CFR part 572, subpart U) or
equivalent, or a Hybrid-II ATD (49 CFR part 572, subpart B, as
specified in Sec. 25.562) or equivalent, occupying each seat position
and including all items contactable by the occupant (e.g., armrest,
interior wall, or furnishing) if those items are necessary to restrain
the occupant. If included, the floor representation and contactable
items must be located such that their relative position, with respect
to the center of the nearest seat place, is the same at the start of
the test as before floor misalignment is applied. For example, if floor
misalignment rotates the centerline of the seat place nearest the
contactable item 8 degrees clockwise about the aircraft x-axis, then
the item and floor representations must be rotated by 8 degrees
clockwise also to maintain the same relative position to the seat
place. Each ATD's relative position to the seat after application of
floor misalignment must be the same as before misalignment is applied.
To ensure proper loading of the seat by the occupants, the ATD pelvis
must remain supported by the seat pan, and the restraint system must
remain on the pelvis and shoulder of the ATD until rebound begins. No
injury-criteria evaluation is necessary for tests

[[Page 53170]]

conducted only to assess seat-strength requirements.
b. The longitudinal test(s) conducted in accordance with Sec.
25.562(b)(2), to show compliance with the injury assessments required
by Sec. 25.562(c) and these special conditions, may be conducted
separately from the test(s) to show structural integrity. In this case,
structural-assessment tests must be conducted as specified in paragraph
1a, above, and the injury-assessment test must be conducted without yaw
or floor misalignment. Injury assessments may be accomplished by
testing with ES-2re ATD (49 CFR part 572, subpart U) or equivalent at
all places. Alternatively, these assessments may be accomplished by
multiple tests that use an ES-2re at the seat place being evaluated,
and a Hybrid-II ATD (49 CFR part 572, subpart B, as specified in Sec.
25.562) or equivalent used in all seat places forward of the one being
assessed, to evaluate occupant interaction. In this case, seat places
aft of the one being assessed may be unoccupied. If a seat installation
includes adjacent items that are contactable by the occupant, the
injury potential of that contact must be assessed. To make this
assessment, tests may be conducted that include the actual item,
located and attached in a representative fashion. Alternatively, the
injury potential may be assessed by a combination of tests with items
having the same geometry as the actual item, but having stiffness
characteristics that would create the worst case for injury (injuries
due to both contact with the item and lack of support from the item).
c. If a seat is installed aft of structure (e.g., an interior wall
or furnishing) that does not have a homogeneous surface contactable by
the occupant, additional analysis and/or test(s) may be required to
demonstrate that the injury criteria are met for the area which an
occupant could contact. For example, different yaw angles could result
in different injury considerations and may require additional analysis
or separate test(s) to evaluate.
d. To accommodate a range of occupant heights (5th percentile
female to 95th percentile male), the surface of items contactable by
the occupant must be homogenous 7.3 inches (185 mm) above and 7.9
inches (200 mm) below the point (center of area) that is contacted by
the 50th percentile male size ATD's head during the longitudinal
test(s) conducted in accordance with paragraphs a, b, and c, above.
Otherwise, additional head-injury criteria (HIC) assessment tests may
be necessary. Any surface (inflatable or otherwise) that provides
support for the occupant of any seat place must provide that support in
a consistent manner regardless of occupant stature. For example, if an
inflatable shoulder belt is used to mitigate injury risk, then it must
be demonstrated by inspection to bear against the range of occupants in
a similar manner before and after inflation. Likewise, the means of
limiting lower-leg flail must be demonstrated by inspection to provide
protection for the range of occupants in a similar manner.
e. For longitudinal test(s) conducted in accordance with Sec.
25.562(b)(2) and these special conditions, the ATDs must be positioned,
clothed, and have lateral instrumentation configured as follows:
f. ATD positioning:
i. Lower the ATD vertically into the seat while simultaneously:
ii. Aligning the midsagittal plane (a vertical plane through the
midline of the body; dividing the body into right and left halves) with
approximately the middle of the seat place.
iii. Applying a horizontal x-axis direction (in the ATD coordinate
system) force of about 20 lb (89 N) to the torso at approximately the
intersection of the midsagittal plane and the bottom rib of the ES-2re
or lower sternum of the Hybrid-II at the midsagittal plane, to compress
the seat back cushion.
iv. Keeping the upper legs nearly horizontal by supporting them
just behind the knees. Once all lifting devices have been removed from
the ATD:
1. Rock it slightly to settle it in the seat.
2. Separate the knees by about 4 inches (100 mm).
3. Set the ES-2re's head at approximately the midpoint of the
available range of z-axis rotation (to align the head and torso
midsagittal planes).
4. Position the ES-2re's arms at the joint's mechanical detent that
puts them at approximately a 40 degree angle with respect to the torso.
Position the Hybrid-II ATD hands on top of its upper legs.
5. Position the feet such that the centerlines of the lower legs
are approximately parallel to a lateral vertical plane (in the aircraft
coordinate system).
g. ATD clothing: Clothe each ATD in form-fitting, mid-calf-length
(minimum) pants and shoes (size 11E) weighing about 2.5 lb (1.1 Kg)
total. The color of the clothing should be in contrast to the color of
the restraint system. The ES-2re jacket is sufficient for torso
clothing, although a form-fitting shirt may be used in addition if
desired.
h. ES-2re ATD lateral instrumentation: The rib-module linear slides
are directional, i.e., deflection occurs in either a positive or
negative ATD y-axis direction. The modules must be installed such that
the moving end of the rib module is toward the front of the aircraft.
The three abdominal-force sensors must be installed such that they are
on the side of the ATD toward the front of the aircraft.
2. The combined horizontal/vertical test, required by Sec.
25.562(b)(1) and these special conditions, must be conducted with a
Hybrid II ATD (49 CFR part 572, subpart B, as specified in Sec.
25.562), or equivalent, occupying each seat position.
3. Restraint systems:
a. If inflatable restraint systems are used, they must be active
during all dynamic tests conducted to show compliance with Sec.
25.562.
b. The design and installation of seat-belt buckles must prevent
unbuckling due to applied inertial forces or impact of the hands/arms
of the occupant during an emergency landing.
4. Additional performance measures applicable to tests and rational
analysis conducted to show compliance with Sec. Sec. 25.562 and 25.785
for side-facing seats:
a. Body-to-body contact: Contact between the head, pelvis, torso,
or shoulder area of one ATD with the adjacent-seated ATD's head,
pelvis, torso, or shoulder area is not allowed. Contact during rebound
is allowed.
b. Thoracic: The deflection of any of the ES-2re ATD upper, middle,
and lower ribs must not exceed 1.73 inches (44 mm). Data must be
processed as defined in Federal Motor Vehicle Safety Standards (FMVSS)
571.214.
c. Abdominal: The sum of the measured ES-2re ATD front, middle, and
rear abdominal forces must not exceed 562 lbs (2,500 N). Data must be
processed as defined in FMVSS 571.214.
d. Pelvic: The pubic symphysis force measured by the ES-2re ATD
must not exceed 1,350 lbs (6,000 N). Data must be processed as defined
in FMVSS 571.214.
e. Leg: Axial rotation of the upper-leg (femur) must be limited to
35 degrees in either direction from the nominal seated position.
f. Neck: As measured by the ES-2re ATD and filtered at CFC 600 as
defined in SAE J211:
i. The upper-neck tension force at the occipital condyle (O.C.)
location must be less than 405 lb (1,800 N).
ii. The upper-neck compression force at the O.C. location must be
less than 405 lb (1,800 N).
iii. The upper-neck bending torque about the ATD x-axis at the O.C.

[[Page 53171]]

location must be less than 1,018 in-lb (115 Nm).
iv. The upper-neck resultant shear force at the O.C. location must
be less than 186 lb (825 N).
g. Occupant (ES-2re ATD) retention: The pelvic restraint must
remain on the ES-2re ATD's pelvis during the impact and rebound phases
of the test. The upper-torso restraint straps (if present) must remain
on the ATD's shoulder during the impact.
h. Occupant (ES-2re ATD) support:
i. Pelvis excursion: The load-bearing portion of the bottom of the
ATD pelvis must not translate beyond the edges of its seat's bottom
seat-cushion supporting structure.
ii. Upper-torso support: The lateral flexion of the ATD torso must
not exceed 40 degrees from the normal upright position during the
impact.
5. For seats with an airbag system in the shoulder belts, show that
the airbag system in the shoulder belt will deploy and provide
protection under crash conditions where it is necessary to prevent
serious injury. The means of protection must take into consideration a
range of stature from a 2-year-old child to a 95th percentile male. The
airbag system in the shoulder belt must provide a consistent approach
to energy absorption throughout that range of occupants. When the seat
system includes an airbag system, that system must be included in each
of the certification tests as it would be installed in the airplane. In
addition, the following situations must be considered:
a. The seat occupant is holding an infant.
b. The seat occupant is a pregnant woman.
6. The airbag system in the shoulder belt must provide adequate
protection for each occupant regardless of the number of occupants of
the seat assembly, considering that unoccupied seats may have an active
airbag system in the shoulder belt.
7. The design must prevent the airbag system in the shoulder belt
from being either incorrectly buckled or incorrectly installed, such
that the airbag system in the shoulder belt would not properly deploy.
Alternatively, it must be shown that such deployment is not hazardous
to the occupant, and will provide the required injury protection.
8. It must be shown that the airbag system in the shoulder belt is
not susceptible to inadvertent deployment as a result of wear and tear,
or inertial loads resulting from in-flight or ground maneuvers
(including gusts and hard landings), and other operating and
environmental conditions (vibrations, moisture, etc.) likely to occur
in service.
9. Deployment of the airbag system in the shoulder belt must not
introduce injury mechanisms to the seated occupant, or result in
injuries that could impede rapid egress. This assessment should include
an occupant whose belt is loosely fastened.
10. It must be shown that inadvertent deployment of the airbag
system in the shoulder belt, during the most critical part of the
flight, will either meet the requirement of Sec. 25.1309(b) or not
cause a hazard to the airplane or its occupants.
11. It must be shown that the airbag system in the shoulder belt
will not impede rapid egress of occupants 10 seconds after airbag
deployment.
12. The airbag system must be protected from lightning and high-
intensity radiated fields (HIRF). The threats to the airplane specified
in existing regulations regarding lightning, Sec. 25.1316, and HIRF,
Sec. 25.1317, are incorporated by reference for the purpose of
measuring lightning and HIRF protection.
13. The airbag system in the shoulder belt must function properly
after loss of normal aircraft electrical power, and after a transverse
separation of the fuselage at the most critical location. A separation
at the location of the airbag system in the shoulder belt does not have
to be considered.
14. It must be shown that the airbag system in the shoulder belt
will not release hazardous quantities of gas or particulate matter into
the cabin.
15. The airbag system in the shoulder-belt installation must be
protected from the effects of fire such that no hazard to occupants
will result.
16. A means must be available for a crewmember to verify the
integrity of the airbag system in the shoulder-belt activation system
prior to each flight, or it must be demonstrated to reliably operate
between inspection intervals. The FAA considers that the loss of the
airbag-system deployment function alone (i.e., independent of the
conditional event that requires airbag deployment) is a major-failure
condition.
17. The inflatable material may not have an average burn rate of
greater than 2.5 inches/minute when tested using the horizontal
flammability test defined in part 25, appendix F, part I, paragraph
(b)(5).
18. The airbag system in the shoulder belt, once deployed, must not
adversely affect the emergency-lighting system (i.e., block floor
proximity lights to the extent that the lights no longer meet their
intended function).

Issued in Des Moines, Washington, on October 10, 2018.
Victor Wicklund,
Manager, Transport Standards Branch, Policy and Innovation Division,
Aircraft Certification Service.
[FR Doc. 2018-22929 Filed 10-19-18; 8:45 am]
BILLING CODE 4910-13-P

53170 Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations

conducted only to assess seat-strength that support in a consistent manner occurs in either a positive or negative
requirements. regardless of occupant stature. For ATD y-axis direction. The modules
b. The longitudinal test(s) conducted example, if an inflatable shoulder belt is must be installed such that the moving
in accordance with § 25.562(b)(2), to used to mitigate injury risk, then it must end of the rib module is toward the
show compliance with the injury be demonstrated by inspection to bear front of the aircraft. The three
assessments required by § 25.562(c) and against the range of occupants in a abdominal-force sensors must be
these special conditions, may be similar manner before and after installed such that they are on the side
conducted separately from the test(s) to inflation. Likewise, the means of of the ATD toward the front of the
show structural integrity. In this case, limiting lower-leg flail must be aircraft.
structural-assessment tests must be demonstrated by inspection to provide 2. The combined horizontal/vertical
conducted as specified in paragraph 1a, protection for the range of occupants in test, required by § 25.562(b)(1) and these
above, and the injury-assessment test a similar manner. special conditions, must be conducted
must be conducted without yaw or floor e. For longitudinal test(s) conducted with a Hybrid II ATD (49 CFR part 572,
misalignment. Injury assessments may in accordance with § 25.562(b)(2) and subpart B, as specified in § 25.562), or
be accomplished by testing with ES–2re these special conditions, the ATDs must equivalent, occupying each seat
ATD (49 CFR part 572, subpart U) or be positioned, clothed, and have lateral position.
equivalent at all places. Alternatively, instrumentation configured as follows: 3. Restraint systems:
these assessments may be accomplished f. ATD positioning: a. If inflatable restraint systems are
by multiple tests that use an ES–2re at i. Lower the ATD vertically into the used, they must be active during all
the seat place being evaluated, and a seat while simultaneously: dynamic tests conducted to show
Hybrid-II ATD (49 CFR part 572, subpart ii. Aligning the midsagittal plane (a compliance with § 25.562.
B, as specified in § 25.562) or equivalent vertical plane through the midline of the b. The design and installation of seat-
used in all seat places forward of the body; dividing the body into right and belt buckles must prevent unbuckling
one being assessed, to evaluate occupant left halves) with approximately the due to applied inertial forces or impact
interaction. In this case, seat places aft middle of the seat place. of the hands/arms of the occupant
of the one being assessed may be iii. Applying a horizontal x-axis during an emergency landing.
unoccupied. If a seat installation direction (in the ATD coordinate 4. Additional performance measures
includes adjacent items that are system) force of about 20 lb (89 N) to the applicable to tests and rational analysis
contactable by the occupant, the injury torso at approximately the intersection conducted to show compliance with
potential of that contact must be of the midsagittal plane and the bottom §§ 25.562 and 25.785 for side-facing
assessed. To make this assessment, tests rib of the ES–2re or lower sternum of seats:
may be conducted that include the the Hybrid-II at the midsagittal plane, to a. Body-to-body contact: Contact
actual item, located and attached in a compress the seat back cushion. between the head, pelvis, torso, or
representative fashion. Alternatively, iv. Keeping the upper legs nearly shoulder area of one ATD with the
the injury potential may be assessed by horizontal by supporting them just adjacent-seated ATD’s head, pelvis,
a combination of tests with items having behind the knees. Once all lifting torso, or shoulder area is not allowed.
the same geometry as the actual item, devices have been removed from the Contact during rebound is allowed.
but having stiffness characteristics that ATD: b. Thoracic: The deflection of any of
would create the worst case for injury 1. Rock it slightly to settle it in the the ES–2re ATD upper, middle, and
(injuries due to both contact with the seat. lower ribs must not exceed 1.73 inches
item and lack of support from the item). 2. Separate the knees by about 4 (44 mm). Data must be processed as
c. If a seat is installed aft of structure inches (100 mm). defined in Federal Motor Vehicle Safety
(e.g., an interior wall or furnishing) that 3. Set the ES–2re’s head at Standards (FMVSS) 571.214.
does not have a homogeneous surface approximately the midpoint of the c. Abdominal: The sum of the
contactable by the occupant, additional available range of z-axis rotation (to measured ES–2re ATD front, middle,
analysis and/or test(s) may be required align the head and torso midsagittal and rear abdominal forces must not
to demonstrate that the injury criteria planes). exceed 562 lbs (2,500 N). Data must be
are met for the area which an occupant 4. Position the ES–2re’s arms at the processed as defined in FMVSS
could contact. For example, different joint’s mechanical detent that puts them 571.214.
yaw angles could result in different at approximately a 40 degree angle with d. Pelvic: The pubic symphysis force
injury considerations and may require respect to the torso. Position the Hybrid- measured by the ES–2re ATD must not
additional analysis or separate test(s) to II ATD hands on top of its upper legs. exceed 1,350 lbs (6,000 N). Data must be
evaluate. 5. Position the feet such that the processed as defined in FMVSS
d. To accommodate a range of centerlines of the lower legs are 571.214.
occupant heights (5th percentile female approximately parallel to a lateral e. Leg: Axial rotation of the upper-leg
to 95th percentile male), the surface of vertical plane (in the aircraft coordinate (femur) must be limited to 35 degrees in
items contactable by the occupant must system). either direction from the nominal seated
be homogenous 7.3 inches (185 mm) g. ATD clothing: Clothe each ATD in position.
above and 7.9 inches (200 mm) below form-fitting, mid-calf-length (minimum) f. Neck: As measured by the ES–2re
the point (center of area) that is pants and shoes (size 11E) weighing ATD and filtered at CFC 600 as defined
contacted by the 50th percentile male about 2.5 lb (1.1 Kg) total. The color of in SAE J211:
size ATD’s head during the longitudinal the clothing should be in contrast to the i. The upper-neck tension force at the
test(s) conducted in accordance with
daltland on DSKBBV9HB2PROD with RULES

color of the restraint system. The ES–2re occipital condyle (O.C.) location must
paragraphs a, b, and c, above. jacket is sufficient for torso clothing, be less than 405 lb (1,800 N).
Otherwise, additional head-injury although a form-fitting shirt may be ii. The upper-neck compression force
criteria (HIC) assessment tests may be used in addition if desired. at the O.C. location must be less than
necessary. Any surface (inflatable or h. ES–2re ATD lateral 405 lb (1,800 N).
otherwise) that provides support for the instrumentation: The rib-module linear iii. The upper-neck bending torque
occupant of any seat place must provide slides are directional, i.e., deflection about the ATD x-axis at the O.C.

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Federal Register / Vol. 83, No. 204 / Monday, October 22, 2018 / Rules and Regulations 53171

location must be less than 1,018 in-lb 9. Deployment of the airbag system in Issued in Des Moines, Washington, on
(115 Nm). the shoulder belt must not introduce October 10, 2018.
iv. The upper-neck resultant shear injury mechanisms to the seated Victor Wicklund,
force at the O.C. location must be less occupant, or result in injuries that could Manager, Transport Standards Branch, Policy
than 186 lb (825 N). impede rapid egress. This assessment and Innovation Division, Aircraft
g. Occupant (ES–2re ATD) retention: should include an occupant whose belt Certification Service.
The pelvic restraint must remain on the is loosely fastened. [FR Doc. 2018–22929 Filed 10–19–18; 8:45 am]
ES–2re ATD’s pelvis during the impact 10. It must be shown that inadvertent BILLING CODE 4910–13–P
and rebound phases of the test. The deployment of the airbag system in the
upper-torso restraint straps (if present) shoulder belt, during the most critical
must remain on the ATD’s shoulder part of the flight, will either meet the DEPARTMENT OF TRANSPORTATION
during the impact. requirement of § 25.1309(b) or not cause
h. Occupant (ES–2re ATD) support: Federal Aviation Administration
i. Pelvis excursion: The load-bearing a hazard to the airplane or its occupants.
portion of the bottom of the ATD pelvis 11. It must be shown that the airbag 14 CFR Part 39
must not translate beyond the edges of system in the shoulder belt will not
[Docket No. FAA–2018–0834; Product
its seat’s bottom seat-cushion impede rapid egress of occupants 10
Identifier 2018–SW–058–AD; Amendment
supporting structure. seconds after airbag deployment. 39–19421; AD 2018–16–51]
ii. Upper-torso support: The lateral 12. The airbag system must be
flexion of the ATD torso must not RIN 2120–AA64
protected from lightning and high-
exceed 40 degrees from the normal intensity radiated fields (HIRF). The Airworthiness Directives; Bell
upright position during the impact. threats to the airplane specified in
5. For seats with an airbag system in Helicopter Textron Canada Limited
existing regulations regarding lightning, Helicopters
the shoulder belts, show that the airbag § 25.1316, and HIRF, § 25.1317, are
system in the shoulder belt will deploy incorporated by reference for the AGENCY: Federal Aviation
and provide protection under crash purpose of measuring lightning and Administration (FAA), Department of
conditions where it is necessary to HIRF protection. Transportation (DOT).
prevent serious injury. The means of 13. The airbag system in the shoulder ACTION: Final rule; request for
protection must take into consideration belt must function properly after loss of comments.
a range of stature from a 2-year-old child normal aircraft electrical power, and
to a 95th percentile male. The airbag after a transverse separation of the SUMMARY: We are publishing a new
system in the shoulder belt must fuselage at the most critical location. A airworthiness directive (AD) for Bell
provide a consistent approach to energy separation at the location of the airbag Helicopter Textron Canada Limited
absorption throughout that range of system in the shoulder belt does not (Bell) Model 429 helicopters. This AD
occupants. When the seat system have to be considered. was sent previously to all known U.S.
includes an airbag system, that system owners and operators of these
must be included in each of the 14. It must be shown that the airbag helicopters as Emergency AD 2018–16–
certification tests as it would be system in the shoulder belt will not 51, dated July 26, 2018, which
installed in the airplane. In addition, the release hazardous quantities of gas or superseded Emergency AD 2018–15–51,
following situations must be considered: particulate matter into the cabin. dated July 20, 2018. This AD requires
a. The seat occupant is holding an 15. The airbag system in the shoulder- inspecting the tail rotor (T/R) gearbox
infant. belt installation must be protected from installation, inspecting the T/R gearbox
b. The seat occupant is a pregnant the effects of fire such that no hazard to retaining hardware and support
woman. occupants will result. attachment point areas, and replacing
6. The airbag system in the shoulder 16. A means must be available for a each nut. This AD is prompted by two
belt must provide adequate protection crewmember to verify the integrity of reports of T/R gearbox assemblies
for each occupant regardless of the the airbag system in the shoulder-belt loosely attached to the gearbox support.
number of occupants of the seat activation system prior to each flight, or The actions of this AD are intended to
assembly, considering that unoccupied it must be demonstrated to reliably address an unsafe condition on these
seats may have an active airbag system operate between inspection intervals. products.
in the shoulder belt. The FAA considers that the loss of the
7. The design must prevent the airbag DATES: This AD becomes effective
airbag-system deployment function November 6, 2018 to all persons except
system in the shoulder belt from being alone (i.e., independent of the
either incorrectly buckled or incorrectly those persons to whom it was made
conditional event that requires airbag immediately effective by Emergency AD
installed, such that the airbag system in deployment) is a major-failure
the shoulder belt would not properly 2018–16–51, issued on July 26, 2018,
condition. which contains the requirements of this
deploy. Alternatively, it must be shown
that such deployment is not hazardous 17. The inflatable material may not AD.
to the occupant, and will provide the have an average burn rate of greater than We must receive comments on this
required injury protection. 2.5 inches/minute when tested using the AD by December 21, 2018.
8. It must be shown that the airbag horizontal flammability test defined in ADDRESSES: You may send comments by
system in the shoulder belt is not part 25, appendix F, part I, paragraph any of the following methods:
susceptible to inadvertent deployment (b)(5). • Federal eRulemaking Docket: Go to
daltland on DSKBBV9HB2PROD with RULES

as a result of wear and tear, or inertial 18. The airbag system in the shoulder http://www.regulations.gov. Follow the
loads resulting from in-flight or ground belt, once deployed, must not adversely online instructions for sending your
maneuvers (including gusts and hard affect the emergency-lighting system comments electronically.
landings), and other operating and (i.e., block floor proximity lights to the • Fax: 202–493–2251.
environmental conditions (vibrations, extent that the lights no longer meet • Mail: Send comments to the U.S.
moisture, etc.) likely to occur in service. their intended function). Department of Transportation, Docket

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Document Created: 2018-10-20 01:49:59
Document Modified: 2018-10-20 01:49:59

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Rules and Regulations
Action		Final special conditions; request for comments.
Dates		This action is effective on Bombardier on October 22, 2018. Send comments on or before December 6, 2018.
Contact		Alan Sinclair, Airframe and Cabin Safety Section, AIR-675, Transport Standards Branch, Policy and Innovation Division, Aircraft Certification Service, Federal Aviation Administration, 2200 South 216th Street, Des Moines, Washington 98198; telephone and fax 206-231-3215; email [email protected]
FR Citation		83 FR 53168
CFR Associated		Aircraft; Aviation Safety and Reporting and Recordkeeping Requirements

83 FR 53168 - Special Conditions: Bombardier, Inc., BD-700-2A12 and BD-700-2A13 Airplanes; Multiple-Place Side-Facing Seats With Active Leg-Flail Restraint Device and Shoulder-Belt Airbags

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 83, Issue 204 (October 22, 2018)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration