Sec. 23.562 - Emergency landing dynamic conditions.
(a) Each seat/restraint system for use
in a normal, utility, or acrobatic category airplane must be designed to
protect each occupant during an emergency landing when --
(1) Proper use is made of seats, safety
belts, and shoulder harnesses provided for in the design; and
(2) The occupant is exposed to the loads
resulting from the conditions prescribed in this section.
(b) Except for those seat/restraint
systems that are required to meet paragraph (d) of this section, each
seat/restraint system for crew or passenger occupancy in a normal,
utility, or acrobatic category airplane, must successfully complete
dynamic tests or be demonstrated by rational analysis supported by dynamic
tests, in accordance with each of the following conditions. These tests
must be conducted with an occupant simulated by an anthropomorphic test
dummy (ATD) defined by 49 CFR Part 572, Subpart B, or an FAA-approved
equivalent, with a nominal weight of 170 pounds and seated in the normal
upright position.
(1) For the first test, the change in
velocity may not be less than 31 feet per second. The seat/restraint
system must be oriented in its nominal position with respect to the
airplane and with the horizontal plane of the airplane pitched up 60
degrees, with no yaw, relative to the impact vector. For seat/restraint
systems to be installed in the first row of the airplane, peak
deceleration must occur in not more than 0.05 seconds after impact and
must reach a minimum of 19g. For all other seat/restraint systems, peak
deceleration must occur in not more than 0.06 seconds after impact and
must reach a minimum of 15g.
(2) For the second test, the change in
velocity may not be less than 42 feet per second. The seat/restraint
system must be oriented in its nominal position with respect to the
airplane and with the vertical plane of the airplane yawed 10 degrees,
with no pitch, relative to the impact vector in a direction that results
in the greatest load on the shoulder harness. For seat/restraint systems
to be installed in the first row of the airplane, peak deceleration must
occur in not more than 0.05 seconds after impact and must reach a minimum
of 26g. For all other seat/restraint systems, peak deceleration must occur
in not more than 0.06 seconds after impact and must reach a minimum of
21g.
(3) To account for floor warpage, the
floor rails or attachment devices used to attach the seat/restraint system
to the airframe structure must be preloaded to misalign with respect to
each other by at least 10 degrees vertically (i.e., pitch out of parallel)
and one of the rails or attachment devices must be preloaded to misalign
by 10 degrees in roll prior to conducting the test defined by paragraph
(b)(2) of this section.
(c) Compliance with the following
requirements must be shown during the dynamic tests conducted in
accordance with paragraph (b) of this section:
(1) The seat/restraint system must
restrain the ATD although seat/restraint system components may experience
deformation, elongation, displacement, or crushing intended as part of the
design.
(2) The attachment between the
seat/restraint system and the test fixture must remain intact, although
the seat structure may have deformed.
(3) Each shoulder harness strap must
remain on the ATD's shoulder during the impact.
(4) The safety belt must remain on the
ATD's pelvis during the impact.
(5) The results of the dynamic tests
must show that the occupant is protected from serious head injury.
(i) When contact with adjacent seats,
structure, or other items in the cabin can occur, protection must be
provided so that the head impact does not exceed a head injury criteria
(HIC) of 1,000.
(ii) The value of HIC is defined as --
Where:
t1 is the initial integration time,
expressed in seconds, t2 is the final integration time,
expressed in seconds, (t2− t1) is the time
duration of the major head impact, expressed in seconds, and a(t) is the
resultant deceleration at the center of gravity of the head form expressed
as a multiple of g (units of gravity).
(iii) Compliance with the HIC limit must
be demonstrated by measuring the head impact during dynamic testing as
prescribed in paragraphs (b)(1) and (b)(2) of this section or by a
separate showing of compliance with the head injury criteria using test or
analysis procedures.
(6) Loads in individual shoulder harness
straps may not exceed 1,750 pounds. If dual straps are used for retaining
the upper torso, the total strap loads may not exceed 2,000 pounds.
(7) The compression load measured
between the pelvis and the lumbar spine of the ATD may not exceed 1,500
pounds.
(d) For all single-engine airplanes with
a VSO of more than 61 knots at maximum weight, and those
multiengine airplanes of 6,000 pounds or less maximum weight with a VSO
of more than 61 knots at maximum weight that do not comply with
§23.67(a)(1);
(1) The ultimate load factors of
§23.561(b) must be increased by multiplying the load factors by the square
of the ratio of the increased stall speed to 61 knots. The increased
ultimate load factors need not exceed the values reached at a VS0
of 79 knots. The upward ultimate load factor for acrobatic category
airplanes need not exceed 5.0g.
(2) The seat/restraint system test
required by paragraph (b)(1) of this section must be conducted in
accordance with the following criteria:
(i) The change in velocity may not be
less than 31 feet per second.
(ii)(A) The peak deceleration (gp)
of 19g and 15g must be increased and multiplied by the square of the ratio
of the increased stall speed to 61 knots:
gp=19.0 (VS0/61)
2 or gp=15.0 (VS0/61) 2
(B) The peak deceleration need not
exceed the value reached at a VS0 of 79 knots.
(iii) The peak deceleration must occur
in not more than time (tr), which must be computed as follows:
