Special Conditions: Approved Model List Installation of AmSafe Inflatable Restraints in Normal and Utility Category Non-23.562 Certified Airplanes, 20368-20374 [E6-5907]
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Federal Register / Vol. 71, No. 76 / Thursday, April 20, 2006 / Proposed Rules
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Dated: April 13, 2006.
Michael Chertoff,
Secretary.
[FR Doc. E6–5947 Filed 4–19–06; 8:45 am]
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above address. Comments must be
marked: CE242. Comments may be
inspected in the Rules Docket
weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
BILLING CODE 4410–10–P
Mr.
Mark James, Federal Aviation
Administration, Aircraft Certification
Service, Small Airplane Directorate,
ACE–111, 901 Locust, Kansas City,
Missouri, 816–329–4137, fax 816–329–
4090, e-mail mark.james@faa.gov.
FOR FURTHER INFORMATION CONTACT:
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE242; Notice No. 23–06–02–
SC]
Special Conditions: Approved Model
List Installation of AmSafe Inflatable
Restraints in Normal and Utility
Category Non-23.562 Certified
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Proposed special conditions;
request for comments.
hsrobinson on PROD1PC61 with PROPOSALS
AGENCY:
SUMMARY: This notice proposes special
conditions for the installation of an
AmSafe, Inc., Inflatable Two-, Three-,
Four or Five-Point Restraint Safety Belt
with an Integrated Airbag Device on
various airplane models. These
airplanes, as modified by AmSafe, Inc.,
will have novel and unusual design
features associated with the lap belt or
shoulder harness portion of the safety
belt, which contains an integrated airbag
device. 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: Comments must be received on
or before May 22, 2006.
ADDRESSES: Comments on these special
conditions may be mailed in duplicate
to: Federal Aviation Administration
(FAA), Regional Counsel, ACE–7,
Attention: Rules Docket, Docket No.
CE242, 901 Locust, Room 506, Kansas
City, Missouri 64106, or delivered in
duplicate to the Regional Counsel at the
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SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to
participate in the making of these
proposed special conditions by
submitting such written data, views, or
arguments as they may desire.
Communications should identify the
regulatory docket or notice number and
be submitted in duplicate to the address
specified above. All communications
received on or before the closing date
for comments will be considered by the
Administrator. The proposals described
in this notice may be changed in light
of the comments received. All
comments received will be available in
the Rules Docket for examination by
interested persons, both before and after
the closing date for comments. A report
summarizing each substantive public
contact with FAA personnel concerning
this rulemaking will be filed in the
docket. Commenters wishing the FAA to
acknowledge receipt of their comments
submitted in response to this notice
must include a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
CE242.’’ The postcard will be date
stamped and returned to the
commenter.
Background
On August 19, 2005, AmSafe, Inc.,
Aviation Inflatable Restraints (AAIR)
Division, 1043 North 47th Avenue,
Phoenix, AZ 85043, applied for a
supplemental type certificate for the
installation of an inflatable restraint in
various airplane models certificated
before the dynamic structural
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requirements as specified in 14 CFR part
23, section 23.562 took effect.
The inflatable restraint system is
either a two-, three-, four, or five-point
safety belt restraint system consisting of
a shoulder harness and a lap belt with
an inflatable airbag attached to either
the lap belt or the shoulder harness. The
inflatable portion of the restraint system
will rely on sensors to electronically
activate the inflator for deployment. The
inflatable restraint system will be made
available on the pilot, co-pilot, and
passenger seats of these airplanes.
In the event of an emergency landing,
the airbag will inflate and provide a
protective cushion between the
occupant’s head and structure within
the airplane. This will reduce the
potential for head and torso injury. The
inflatable restraint behaves in a manner
that is similar to an automotive airbag,
but in this case, the airbag is integrated
into the lap or shoulder belt. While
airbags and inflatable restraints are
standard in the automotive industry, the
use of an inflatable restraint system is
novel for general aviation operations.
The FAA has determined that this
project will be accomplished on the
basis of providing the same current level
of safety of the airplanes original
certification basis. The FAA has two
primary safety concerns with the
installation of airbags or inflatable
restraints:
• That they perform properly under
foreseeable operating conditions; and
• That they do not perform in a
manner or at such times as to impede
the pilot’s ability to maintain control of
the airplane or constitute a hazard to the
airplane or occupants.
The latter point has the potential to be
the more rigorous of the requirements.
An unexpected deployment while
conducting the takeoff or landing phases
of flight may result in an unsafe
condition. The unexpected deployment
may either startle the pilot, or generate
a force sufficient to cause a sudden
movement of the control yoke. Either
action could result in a loss of control
of the airplane, the consequences of
which are magnified due to the low
operating altitudes during these phases
of flight. The FAA has considered this
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when establishing these special
conditions.
The inflatable restraint system relies
on sensors to electronically activate the
inflator for deployment. These sensors
could be susceptible to inadvertent
activation, causing deployment in a
potentially unsafe manner. The
consequences of an inadvertent
deployment must be considered in
establishing the reliability of the system.
AmSafe, Inc. must show that the effects
of an inadvertent deployment in flight
are not a hazard to the airplane or that
an inadvertent deployment is extremely
improbable. In addition, general
aviation aircraft are susceptible to a
large amount of cumulative wear and
tear on a restraint system. It is likely
that the potential for inadvertent
deployment increases as a result of this
cumulative damage. Therefore, the
impact of wear and tear on inadvertent
deployment must be considered. Due to
the effects of this cumulative damage, a
life limit must be established for the
appropriate system components in the
restraint system design.
There are additional factors to be
considered to minimize the chances of
inadvertent deployment. General
aviation airplanes are exposed to a
unique operating environment, since the
same airplane may be used by both
experienced and student pilots. The
effect of this environment on
inadvertent deployment must be
understood. Therefore, qualification
testing of the firing hardware/software
must consider the following:
• The airplane vibration levels
appropriate for a general aviation
airplane; and
• The inertial loads that result from
typical flight or ground maneuvers,
including gusts and hard landings.
Any tendency for the firing
mechanism to activate as a result of
these loads or acceleration levels is
unacceptable.
Other influences on inadvertent
deployment include high intensity
electromagnetic fields (HIRF) and
lightning. Since the sensors that trigger
deployment are electronic, they must be
protected from the effects of these
threats. To comply with HIRF and
lightning requirements, the AmSafe,
Inc., inflatable restraint system is
considered a critical system, since its
inadvertent deployment could have a
hazardous effect on the airplane.
Given the level of safety of the
retrofitted airplane occupant restraints,
the inflatable restraint system must
show that it will offer an equivalent
level of protection in the event of an
emergency landing. In the event of a
deployment, the restraint must still be at
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least as strong as a Technical Standard
Order approved belt and shoulder
harnesses. There is no requirement for
the inflatable portion of the restraint to
offer protection during multiple
impacts, where more than one impact
would require protection.
The inflatable restraint system must
deploy and provide protection for each
occupant during emergency landing
conditions as specified in the original
certification basis. The seats of the
various airplane models were
certificated prior to the dynamic
structural requirements of section
23.562. Therefore, the emergency
landing loads conditions identified in
the original certification basis of the
airplane must be used to satisfy this
requirement. Compliance will be
demonstrated using the test condition
specified in the original certification
basis. It must also be shown that the
crash sensor will trigger when exposed
to a rapidly applied deceleration, like an
actual crash event. Therefore, the test
crash pulses identified in section 23.562
must be used to satisfy this requirement,
although, the peak ‘‘G’’ may be reduced
to a level meeting the original
certification requirements of the aircraft.
Testing to these pulses will demonstrate
that the crash sensor will trigger when
exposed to a rapidly applied
deceleration, like an actual crash event.
It is possible a wide range of
occupants will use the inflatable
restraint. Thus, the protection offered by
this restraint should be effective for
occupants that range from the fifth
percentile female to the ninety-fifth
percentile male.
In support of this operational
capability, there must be a means to
verify the integrity of this system before
each flight. As an option, AmSafe, Inc.
can establish inspection intervals where
they have demonstrated the system to be
reliable between these intervals.
It is possible that an inflatable
restraint will be ‘‘armed’’ even though
no occupant is using the seat. While
there will be means to verify the
integrity of the system before flight, it is
also prudent to require that unoccupied
seats with active restraints not
constitute a hazard to any occupant.
This will protect any individual
performing maintenance inside the
cockpit while the aircraft is on the
ground. The restraint must also provide
suitable visual warnings that would
alert rescue personnel to the presence of
an inflatable restraint system.
In addition, the design must prevent
the inflatable seatbelt from being
incorrectly buckled and/or installed
such that the airbag would not properly
deploy. As an alternative, AmSafe, Inc.
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20369
may show that such deployment is not
hazardous to the occupant and will still
provide the required protection.
The cabins of the various modeal
airplanes identified in these special
conditions are confined areas, and the
FAA is concerned that noxious gasses
may accumulate in the event of airbag
deployment. When deployment does
occur, either by design or inadvertently,
there must not be a release of hazardous
quantities of gas or particulate matter
into the cockpit.
An inflatable restraint should not
increase the risk already associated with
fire. Therefore, the inflatable restraint
should be protected from the effects of
fire, so that an additional hazard is not
created by, for example, a rupture of the
inflator.
The airbag is likely to have a large
volume displacement, and possibly
impede the egress of an occupant. Since
the bag deflates to absorb energy, it is
likely that the inflatable restraint would
be deflated at the time an occupant
would attempt egress. However, it is
appropriate to specify a time interval
after which the inflatable restraint may
not impede rapid egress. Ten seconds
has been chosen as reasonable time.
This time limit will offer a level of
protection throughout the impact event.
Finally, there is an elevated risk
associated with inadvertent deployment
for agricultural airplanes, which are
type certificated under the restricted
category. This is due to the unique
operating environment and low altitude
flying of these airplanes. The FAA is
still trying to understand the risk and
benefit associated with the installation
of these systems into restricted category
airplanes in general and agricultural
airplanes specifically. Therefore, the
installation of the AAIR system is
currently prohibited in agricultural
airplanes type certificated under the
restricted category.
Special conditions for the installation
of AAIR systems on other Non-23.562
certificated airplanes have been issued
and no substantive public comments
were received. Since the same special
conditions were issued multiple times
for different model airplanes with no
substantive public comments, the FAA
began issuing direct final special
conditions with an invitation for public
comment. This was done to eliminate
the waiting period for public comments
and AmSafe aviation could proceed
with the project, since no comments
were expected.
These previous special conditions
were issued for a single model airplane
or for variants of a model from a single
airplane manufacturer, and required
dynamic testing of each AAIR system
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installation for showing compliance.
The AML Supplemental Type
Certificate sought by AmSafe Aviation
has numerous airplane models and
manufacturers. Since AmSafe Aviation
has previously demonstrated by
dynamic testing, and has the supporting
data, that the Electronics Module
Assembly (EMA) and the inflator
assembly will function as intended in a
simulated dynamic emergency landing,
it is not necessary to repeat the test for
each airplane model shown in these
special conditions.
This is a departure from the method
of showing compliance used in the prior
special conditions. Testing is required
to show compliance, but it is not
necessary to repeat the testing for each
airplane installation. Existing test data
is adequate for showing compliance for
other airplanes where the AAIR
equipment is identical and the
installation is nearly identical. Since
this is a substantial change in the
philosophy of showing compliance, it is
prudent to give the public time to
comment on the special conditions prior
to moving forward with the project.
Type Certification Basis
Under the provisions of 14 CFR part
21, section 21.101, AmSafe, Inc., must
show that the affected airplane models,
as changed, continue to meet the
applicable provisions of the regulations
incorporated by reference in the Type
Certificate Numbers listed below or the
applicable regulations in effect on the
date of application for the change. The
regulations incorporated by reference in
the type certificate are commonly
referred to as the original ’’type
certification basis’’ and can be found in
the Type Certificate Numbers listed
below. The following models are
covered by this special condition:
LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS
Make
Model
Aerostar .....................
PA–60–600 (Aerostar 600),
PA–60–601 (Aerostar 601),
PA–60–601P (Aerostar 601P),
PA–60–602P (Aerostar 602P).
PA–60–700P (Aerostar 700P). Aerostar Aircraft Corporation.
10A .................................................................
ALL AMERICAN ........
American Champion
(Champion).
American Champion
(Bellanca) (Champion) (Aeronca).
American Champion
(Bellanca) (Trytek)
(Aeronca).
AMERICAN CHAMPION (Bellanca)
(Trytek) (Aeronca).
VARGA (Morrisey) .....
Bellanca .....................
TC holder
14 CFR PART 23.
All American Aircraft,
Inc.
American Champion
Aircraft Corp.
American Champion
Aircraft Corp.
A–792 .........................
CAR 3.
A3CE Revision 5 .......
CAR 3.
A–759 Revision 67 ....
CAR 4a.
American Champion
Aircraft Corp.
A–761 Revision 17 ....
CAR 4a.
11CC, S11CC ................................................
American Champion
Aircraft Corporation.
A–796 Revision 14 ....
CAR 3.
2150, 2150A, 2180 .........................................
14–13, 14–13–2, 14–13–3, 14–13–3W .........
Augustair, Inc .............
Bellanca Aircraft Corporation.
Bellanca Aircraft Corporation.
Cessna Aircraft Company.
4A19 Revision 9 ........
A–773 Revision 10 ....
CAR 3.
CAR 4a.
TC716 ........................
CAR 4a.
3A10 Revision 62 ......
CAR 3.
Cessna Aircraft Company.
Cessna Aircraft Company.
3A11 Revision 6 ........
CAR 3.
3A12 Revision 73 ......
CAR 3.
Cessna Aircraft Company.
3A17 Revision 45 ......
CAR 3.
Cessna Aircraft Company.
3A13 Revision 64 ......
CAR 3.
Cessna Aircraft Company.
3A21 Revision 46 ......
CAR 3.
402 .................................................................
7AC, 7ACA, 7EC, 7GCB, S7AC, S7EC,
7GCBA (L–16A), 7BCM, 7ECA, 7GCBC
(L–16B), 7CCM, 7FC, 7HC, S7CCM, 7GC,
7JC, 7DC, 7GCA, 7KC, S7DC, 7GCAA,
7KCAB.
11AC, S11AC, 11BC, S11BC ........................
14–9, 14–9L ...................................................
Cessna .......................
310, 310J, 310A(USAF U–3A), 310J–1,
310B, E310J, 310C, 310K, 310D, 310L,
310E(USAF U–3B), 310N, 310F, 310P,
310G, T310P, 310H, 310Q, E310H,
T310Q, 310I, 310R, T310R.
321 (Navy OE–2) ...........................................
Cessna .......................
CESSNA ....................
hsrobinson on PROD1PC61 with PROPOSALS
Cessna .......................
Cessna .......................
VerDate Aug<31>2005
Certification basis
A17WE Revision 22 ...
Bellanca .....................
Cessna .......................
TCDS
172, 172I, 172A, 172K, 172B, 172L, 172C,
172M, 172D, 172N, 172E, 172P, 172F
(USAF T–41A), 172Q, 172G, 172H,
(USAF T–41A).
175, 175A, 175B, 175C, P172D, R172E
(USAF T–41B) (USAF T–41C and D),
R172F (USAF T–41D), R172G (USAF T–
41C or D), R172H (USAF T–41D), R172J,
R172K, 172RG.
182, 182K, 182A, 182L, 182B, 182M, 182C,
182N, 182D, 182P, 182E, 182Q, 182F,
182R, 182G, R182, 182H, T182, 182J,
TR182.
210, 210K, 210A, T210K, 210B, 210L, 210C,
T210L, 210D, 210M, 210E, T210M, 210F,
210N, T210F, P210N, 210G, T210N,
T210G, 210R, 210H, P210R, T210H,
T210R, 210J, 210–5 (205), T210J, 210–5A
(205A).
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LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued
Make
Model
Cessna .......................
185, A185E, 185A, A185F, 185B, 185C,
185D, 185E.
320, 320F, 320–1, 335, 320A, 340, 320B,
340A, 320C, 320D, 320E.
140A ...............................................................
Cessna .......................
Cessna .......................
Cessna .......................
Cessna .......................
Cessna .......................
TC holder
180, 180E, 180A, 180F, 180B, 180G, 180C,
180H, 180D, 180J, 180E, 180K.
336 .................................................................
CESSNA ....................
206, U206B, TP206D, P206, U206C,
TP206E, P206A, U206D, TU206A, P206B,
U206E, TU206B, P206C, U206F, TU206C,
P206D, U206G, TU206D, P206E, TP206A,
TU206E, U206, TP206B, TU206F, U206A,
TP206C, TU206G.
337A (USAF 02B), T337E, 337B, 337F,
M337B (USAF 02A), T337F, T337B,
337G, 337C, T337G, T337C, 337H, 337D,
P337H, T337D, T337H, T337H–SP.
401, 411A, 401A, 414, 401B, 414A, 402,
421, 402A, 421A, 402B, 421B, 402C,
421C, 411, 425.
190 (LC–126A,B,C), 195, 195A, 195B ..........
Cessna .......................
170, 170A, 170B ............................................
CESSNA ....................
CESSNA ....................
150, 150J, 150A, 150K, 150B, A150K, 150C,
150L, 150D, A150L, 150E, 150M, 150F,
A150M, 150G, 152, 150H, A152.
177, 177A, 177B ............................................
CESSNA ....................
404, 406 .........................................................
Cessna .......................
208, 208A, 208B ............................................
Cessna .......................
441 .................................................................
Cessna .......................
120, 140 .........................................................
Commander Aircraft ...
Great Lakes ...............
Model 112, Model 114, Model 112TC, Model
112B, Model 112TCA, Model 114A, Model
114B, Model 114TC.
2T–1A, 2T–1A–1, 2T–1A–2 ...........................
Helio (Taylorcraft) ......
15A, 20 ...........................................................
LEARJET ...................
LOCKHEED ...............
23 ...................................................................
402–2 .............................................................
LAND-AIR (TEMCO)
(LUSCOMBE).
MAULE .......................
11A, 11E ........................................................
CESSNA ....................
hsrobinson on PROD1PC61 with PROPOSALS
CESSNA ....................
Mooney ......................
Interceptor (Aero
Commander) (Meyers).
VerDate Aug<31>2005
Bee Dee M–4, M–5–180C, MXT–7–160, M–
4–180V, M–4 M–5–200, MX–7–180A, M–
4C, M–5–210C, MXT–7–180A, M–4S, M–
5–210TC, MX–7–180B, M–4T, M–5–220C,
M–7–235B, M–4–180C, M–5–235C, M–7–
235A, M–4–180S, M–6–180, M–7–235C,
M–4–180T, M–6–235, MX–7–180C, M–4–
210, M–7–235, M–7–260, M–4–210C,
MX–7–235, MT–7–260, M–4–210S, MX–
7–180, M–7–260C, M–4–210T, MX–7–
420, M–7–420AC, M–4–220, MXT–7–180,
MX–7–160C, M–4–220C, MT–7–235, MX–
7–180AC, M–4–220S, M–8–235, M–7–
420A, M–4–220T, MX–7–160, MT–7–420.
M20, M20A, M20B, M20C, M20D, M20E,
M20F, M20G, M20J, M20K (Up to S/N 25–
2000), M20L.
200, 200A, 200B, 200C, 200D, 400 ..............
14:56 Apr 19, 2006
Jkt 208001
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Cessna Aircraft
pany.
Cessna Aircraft
pany.
Cessna Aircraft
pany.
Cessna Aircraft
pany.
Cessna Aircraft
pany.
Cessna Aircraft
pany.
TCDS
Certification basis
Com-
3A24 Revision 37 ......
CAR 3.
Com-
3A25 Revision 25 ......
CAR 3.
Com-
5A2 Revision 21 ........
CAR 3.
Com-
5A6 Revision 66 ........
CAR 3.
Com-
A2CE Revision 7 .......
CAR 3.
Com-
A4CE Revision 43 .....
CAR 3.
Cessna Aircraft Company.
A6CE Revision 40 .....
CAR 3/14 CFR PART
23.
Cessna Aircraft Company.
A7CE Revision 46 .....
CAR 3.
Cessna Aircraft Company.
Cessna Aircraft Company.
Cessna Aircraft Company.
A–790 Revision 36 ....
CAR 3.
A–799 Revision 54 ....
CAR 3.
3A19 Revision 44 ......
CAR 3.
Cessna Aircraft Company.
Cessna Aircraft Company.
Cessna Aircraft Company.
Cessna Aircraft Company.
Cessna Aircraft Company.
Commander Aircraft
Company.
A13CE Revision 24 ...
14 CFR PART 23.
A25CE Revision 11 ...
14 CFR PART 23.
A37CE Revision 12 ...
14 CFR PART 23.
A28CE Revision 12 ...
14 CFR PART 23.
A–768 Revision 34 ....
CAR 4a.
A12SO Revision 21 ...
14 CFR PART 23.
Great Lakes Aircraft
Company, LLC.
Helio Aircraft Corporation.
Learjet Inc. .................
Lockheed Aircraft
International.
Luscombe Aircraft
Corporation.
MAULE AEROSPACE
TECHNOLOGY,
INC.
A18EA Revision 10 ....
3A3 Revision 7 ..........
Aeronautical Bulletin
No. 7–A.
CAR 4a.
A5CE Revision 10 .....
2A11 Revision 4 ........
CAR 3.
AR 3.
A–804 Revision 14 ....
CAR 3.
3A23 Revision 30 ......
CAR 3.
Mooney Airplane
Company, Inc.
2A3 Revision 47 ........
CAR 3.
Prop-Jets, Inc. ............
3A18 Revision 16 ......
CAR 3.
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LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued
Make
Model
BEECH .......................
BEECH .......................
35–33, J35, 35–A33, K35, 35–B33, M35,
35–C33, N35, 35–C33A, P35, E33, S35,
E33A, V35, E33C, V35A, F33, V35B,
F33A, 36, F33C, A36, G33, A36TC, H35,
B36TC, G36.
45 (YT–34), A45 (T–34A, B–45), D45 (T–
34B).
19A, B23, B19, C23, M19A, A24, 23, A24R,
A23, B24R, A23A, C24R, A23–19, A23–24.
3N, E18S–9700,3NM, G18S, 3TM, H18,
JRB–6, C–45G, TC–45G, D18C, C–45H,
TC–45H, D18S, TC–45J or E18S, UC–45J
(SNB–5) RC–45J (SNB–5P).
35, A35, E35, B35, F35, C35, G35, D35,
35R.
200, A100–1 (U–21J), 200C, A200 (C–12A),
200CT, A200 (C–12C), 200T, A200C (UC–
12B), B200, A200CT (C–12D), B200C,
A200CT (FWC–12D), B200CT, A200CT
(C–12F), B200T, A200CT (RC–12D), 300,
A200CT (RC–12G), 300LW, A200CT (RC–
12H), B300, A200CT (RC–12K), B300C,
A200CT (RC–12P), 1900, A200CT (RC–
12Q), 1900C, B200C (C–12F), 1900D,
B200C (UC–12M), B200C (C–12R),
B200C (UC–12F), 1900C (C–12J).
B95A, D55, D95A, D55A, E95, E55, 95–55,
E55A, 95–A55, 56TC, 95–B55, A56TC,
95–B55A, 58, 95–B55B (T–42A), 58A, 95–
C55, 95, 95–C55A, B95, G58.
60, A60, B60 ..................................................
BEECH .......................
58P, 58PA, 58TC, 58TCA ..............................
CESSNA ....................
SOCATA ....................
CESSNA F172D, CESSNA F172E, CESSNA
F172F,
CESSNA
F172G,
CESSNA
F172H, CESSNA F172K, CESSNA F172L,
CESSNA F172M, CESSNA F172N,
CESSNA F172P.
TB 9, TB 10, TB 20, TB 21, TB 200 ..............
Pitts ............................
S–1S, S–1T, S–2, S–2A, S–2S, S–2B, S–2C
Taylorcraft ..................
19, F19, F21, F21A, F21B, F22, F22A,
F22B, F22C.
BC, BCS12–D, BCS, BC12–D1, BC–65,
BCS12–D1, BCS–65, BC12D–85, BC12–
65 (Army L–2H), BCS12D–85, BCS12–65,
BC12D–4–85, BC12–D, BCS12D–4–85.
(Army L–2G) BF, BFS, BF–60, BFS–60, BF–
65, BFS–65, (Army L–2K) BF 12–65,
BFS–65.
8, 8D, 8A, 8E, 8B, 8F, 8C, T–8F ...................
BEECH .......................
BEECH .......................
BEECH .......................
BEECH .......................
RAYTHEON ...............
Beech .........................
TAYLORCRAFT .........
TAYLORCRAFT .........
LUSCOMBE ...............
PIPER ........................
hsrobinson on PROD1PC61 with PROPOSALS
PIPER ........................
PIPER ........................
PIPER ........................
VerDate Aug<31>2005
TC holder
PA–28–140, PA–28–151, PA–28–150, PA–
28–161, PA–28–160, PA–28–181, PA–28–
180, PA–28R–201, PA–28–235, PA–28R–
201T, PA–28S–160, PA–28–236, PA–
28S–180, PA–28RT–201, PA–28R–180,
PA–28RT–201T, PA–28R–200, PA–28–
201T.
PA–30, PA–39, PA–40 ...................................
PA–32–260, PA–32R–301 (SP), PA–32–300,
PA–32R–301 (HP), PA–32S–300, PA–
32R–301T, PA–32R–300, PA–32–301,
PA–32RT–300, PA–32–301T, PA–32RT–
300T, PA–32–301FT, PA–32–301XTC.
PA–34–200, PA–34–200T, PA–34–220T ......
14:56 Apr 19, 2006
Jkt 208001
PO 00000
Frm 00023
Fmt 4702
TCDS
Certification basis
Raytheon Aircraft
Company.
3A15 Revision 90 ......
CAR 3.
Raytheon Aircraft
Company.
Raytheon Aircraft
Company.
Raytheon Aircraft
Company.
5A3 Revision 25 ........
CAR 03.
A1CE Revision 34 .....
CAR 3.
A–765 Revision 74 ....
CAR 03.
Raytheon Aircraft
Company.
Raytheon Aircraft
Company.
A–777 Revision 57 ....
CAR 03.
A24CE Revision 91 ...
14 CFR PART 23.
Raytheon Aircraft
Company.
3A16 Revision 81 ......
CAR 3.
Raytheon Aircraft
Company.
Raytheon Aircraft
Company.
Reims Aviation S.A. ...
A12CE Revision 23 ...
14 CFR PART 23.
A23CE Revision 14 ...
14 CFR PART 23.
A4EU Revision 11 .....
CAR 10/ CAR 3.
SOCATA—GROUPE
AEROSPATIALE.
Sky International Inc.
(Aviat Aircraft, Inc.).
Taylorcraft Aviation
LLC.
Taylorcraft Aviation,
LLC.
A51EU Revision 14 ...
14 CFR PART 23.
A8SO Revision 21 .....
14 CFR PART 23.
1A9 Revision 19 ........
CAR 3.
A–696 Revision 22 ....
CAR 04.
Taylorcraft, Inc. ..........
A–699 Revision 5 ......
CAR 4a.
The Don Luscombe
Aviation History
Foundation, Inc.
The New Piper Aircraft, Inc.
A–694 Revision 23 ....
CAR 4a.
2A13 Revision 47 ......
CAR 3.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
A1EA Revision 16 ......
CAR 3.
A3SO Revision 29 .....
CAR 3.
The New Piper Aircraft, Inc.
A7SO Revision 16 .....
14 CFR PART 23.
Sfmt 4702
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20373
Federal Register / Vol. 71, No. 76 / Thursday, April 20, 2006 / Proposed Rules
LIST OF ALL AIRPLANE MODELS AND APPLICABLE TCDS—Continued
Make
Model
TC holder
TCDS
PIPER ........................
CAR 3.
A9SO Revision 9 .......
14 CFR PART 23.
PIPER ........................
PA–36–285, PA–36–300, PA–36–375 ...........
A10SO Revision 12 ...
PIPER ........................
PA–38–112 .....................................................
A18SO Revision 4 .....
14 CFR PART 21/14
CFR PART 23.
14 CFR PART 23.
PIPER ........................
PA–44–180, PA–44–180T .............................
A19SO Revision 9 .....
14 CFR PART 23.
PIPER ........................
A20SO Revision 10 ...
CAR 3.
PIPER ........................
PA–31, PA–31–300, PA–31–325, PA–31–
350.
PA–42, PA–42–720, PA–42–1000 .................
A23SO Revision 17 ...
14 CFR PART 23.
PIPER ........................
PA–46–310P, PA–46–350P, PA–46–500TP
A25SO Revision 14 ...
14 CFR PART 23.
Tiger Aircraft LLC
(American General).
Tiger Aircraft ..............
Twin Commander ......
AA–1, AA–1A, AA–1B, AA–1C ......................
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
The New Piper Aircraft, Inc.
Tiger Aircraft LLC ......
A8EA Revision 22 ......
PIPER ........................
PA–31P, PA–31T, PA–31T1, PA–31T2, PA–
31T3, PA–31P–350.
PA–36–285, PA–36–300, PA–36–375 ...........
A11EA Revision 10 ....
14 CFR PART 23.
Tiger Aircraft LLC ......
Twin Commander Aircraft Corporation.
Twin Commander Aircraft Corporation.
A16EA Revision 13 ....
6A1 Revision 45 ........
14 CFR PART 23.
CAR 3.
2A4 Revision 46 ........
CAR 3.
Twin Commander ......
Univair (Stinson) ........
Univair ........................
hsrobinson on PROD1PC61 with PROPOSALS
Univair (Mooney) .......
AA–5, AA–5A, AA–5B, AG–5B ......................
500, 500–A, 500–B, 500–U, 520, 560, 560–
A, 560–E, 500–S.
560–F, 681, 680, 690, 680E, 685, 680F,
690A, 720, 690B, 680FL, 690C, 680FL(P),
690D, 680T, 695, 680V, 695A, 680W,
695B.
108, 108–1, 108–2, 108–3, 108–5 .................
(ERCO) 415–D, (ERCO) E, (ERCO) G,
(Forney) F–1, (Forney) F–1A, (Alon) A–2,
(Alon) A2–A, (Mooney) M10.
(ERCO) 415–C, (ERCO) 415–CD .................
For all the models listed above, the
certification basis also includes all
exemptions, if any; equivalent level of
safety findings, if any; and special
conditions not relevant to the special
conditions adopted by this rulemaking
action.
The Administrator has determined
that the applicable airworthiness
regulations (i.e., CAR 3. or part 23 as
amended) do not contain adequate or
appropriate safety standards for the
AmSafe, Inc., inflatable restraint as
installed on these models because of a
novel or unusual design feature.
Therefore, special conditions are
prescribed under the provisions of
section 21.16.
Special conditions, as appropriate, as
defined in section 11.19, are issued in
accordance with section 11.38, and
become part of the type certification
basis in accordance with section
21.101.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,
the special conditions would also apply
to that model under the provisions of
section 21.101.
VerDate Aug<31>2005
14:56 Apr 19, 2006
Jkt 208001
Univair Aircraft Corporation.
Univair Aircraft Corporation.
A–767 Revision 27 ....
CAR 3.
A–787 Revision 33 ....
CAR 3.
Univair Aircraft Corporation.
A–718 Revision 29 ....
CAR 4a.
Novel or Unusual Design Features
The various airplane models will
incorporate the following novel or
unusual design feature:
The AmSafe, Inc., Inflatable Two-,
Three-, Four-, or Five-Point Restraint
Safety Belt with an Integrated Airbag
Device. The purpose of the airbag is to
reduce the potential for injury in the
event of an accident. In a severe impact,
an airbag will deploy from the restraint,
in a manner similar to an automotive
airbag. The airbag will deploy between
the head of the occupant and airplane
interior structure. This will, therefore,
provide some protection to the head of
the occupant. The restraint will rely on
sensors to electronically activate the
inflator for deployment.
The Code of Federal Regulations state
performance criteria for seats and
restraints in an objective manner.
However, none of these criteria are
adequate to address the specific issues
raised concerning inflatable restraints.
Therefore, the FAA has determined that,
in addition to the requirements of part
21 and part 23, special conditions are
needed to address the installation of this
inflatable restraint.
Accordingly, these special conditions
are adopted for the various airplane
models equipped with the AmSafe, Inc.,
PO 00000
Frm 00024
Fmt 4702
Certification basis
Sfmt 4702
two-, three-, four, or five-point inflatable
restraint. Other conditions may be
developed, as needed, based on further
FAA review and discussions with the
manufacturer and civil aviation
authorities.
Conclusion
This action affects only certain novel
or unusual design features on the
previously identified airplane models. It
is not a rule of general applicability, and
it affects only the applicant who applied
to the FAA for approval of these features
on the airplane.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
Citation
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113 and
44701; 14 CFR 21.16 and 21.101; and 14 CFR
11.38 and 11.19.
The Proposed Special Conditions
The FAA has determined that this
project will be accomplished on the
basis of not lowering the current level
of safety of the occupant restraint
system for the airplane models listed in
these proposed Special Conditions.
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Federal Register / Vol. 71, No. 76 / Thursday, April 20, 2006 / Proposed Rules
hsrobinson on PROD1PC61 with PROPOSALS
Accordingly, the FAA proposes the
following special conditions as part of
the type certification basis for these
models, as modified by AmSafe,
Incorporated.
Inflatable Two-, Three-, Four-, or FivePoint Restraint Safety Belt With an
Integrated Airbag Device Installed in an
Airplane Model.
1a. It must be shown that the
inflatable restraint will provide restraint
protection under the emergency landing
conditions specified in the original
certification basis of the airplane.
Compliance will be demonstrated using
the static test conditions specified in the
original certification basis for each
airplane.
1b. It must be shown that the crash
sensor will trigger when exposed to
arapidly applied deceleration, like an
actual emergency landing event.
Therefore, compliance may be
demonstrated using the deceleration
pulse specified in paragraph 23.562,
which may be modified as follows:
I. The peak longitudinal deceleration
may be reduced, however the onset rate
of the deceleration must be equal to or
greater than the emergency landing
pulse identified in paragraph 23.562.
II. The peak longitudinal deceleration
must be above the deployment
threshold of the sensor, and equal or
greater than the forward static design
longitudinal load factor required by the
original certification basis of the
airplane.
2. The inflatable restraint must
provide adequate protection for each
occupant. In addition, unoccupied seats
that have an active restraint must not
constitute a hazard to any occupant.
3. The design must prevent the
inflatable restraint from being
incorrectly buckled and/or incorrectly
installed such that the airbag would not
properly deploy. Alternatively, it must
be shown that such deployment is not
hazardous to the occupant and will
provide the required protection.
4. It must be shown that the inflatable
restraint system is not susceptible to
inadvertent deployment as a result of
wear and tear or the inertial loads
resulting from in-flight or ground
maneuvers (including gusts and hard
landings) that are likely to be
experienced in service.
5. It must be extremely improbable for
an inadvertent deployment of the
restraint system to occur, or an
inadvertent deployment must not
impede the pilot’s ability to maintain
control of the airplane or cause an
unsafe condition (or hazard to the
airplane). In addition, a deployed
inflatable restraint must be at least as
VerDate Aug<31>2005
14:56 Apr 19, 2006
Jkt 208001
strong as a Technical Standard Order
(C22g or C114) restraint.
6. It must be shown that deployment
of the inflatable restraint system is not
hazardous to the occupant or result in
injuries that could impede rapid egress.
This assessment should include
occupants whose restraint is loosely
fastened.
7. It must be shown that an
inadvertent deployment that could
cause injury to a sitting person is
improbable. In addition, the restraint
must also provide suitable visual
warnings that would alert rescue
personnel to the presence of an
inflatable restraint system.
8. It must be shown that the inflatable
restraint will not impede rapid egress of
the occupants 10 seconds after its
deployment.
9. For the purposes of complying with
HIRF and lightning requirements, the
inflatable restraint system is considered
a critical system since its deployment
could have a hazardous effect on the
airplane.
10. It must be shown that the
inflatable restraints will not release
hazardous quantities of gas or
particulate matter into the cabin.
11. The inflatable restraint system
installation must be protected from the
effects of fire such that no hazard to
occupants will result.
12. There must be a means to verify
the integrity of the inflatable restraint
activation system before each flight or it
must be demonstrated to reliably
operate between inspection intervals.
13. A life limit must be established for
appropriate system components.
14. Qualification testing of the
internal firing mechanism must be
performed at vibration levels
appropriate for a general aviation
airplane.
15. The installation of the AmSafe
Aviation Inflatable Restraint (AAIR)
system is prohibited in agricultural
airplanes type certificated under the
Restricted Category.
Issued in Kansas City, Missouri on April 6,
2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E6–5907 Filed 4–19–06; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–23872; Airspace
Docket No. 06–AAL–9]
RIN 2120–AA66
Proposed Establishment of Offshore
Airspace Area 1485L; and Revision of
Control 1485H; Barrow, AK
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This action proposes to
establish Control 1485L and revise
Control 1485H offshore airspace in the
vicinity of Barrow, AK. These proposed
actions would establish controlled
airspace outside of 12 nautical miles
(NM) of the U.S. shoreline upward from
1,200 feet mean sea level (MSL) along
the North Slope of Alaska. Additionally,
this proposal would revise the altitudes
of Control 1485H from FL 230/FL 450 to
FL 180/FL 600. The FAA is proposing
these actions to provide additional
controlled airspace for aircraft executing
instrument flight rules (IFR) operations
at the airfields along the North Slope of
Alaska in anticipation of establishing
Terminal Arrival Areas associated with
Area Navigation (RNAV) Standard
Instrument Arrival Procedures (SIAPs).
DATES: Comments must be received on
or before June 5, 2006.
ADDRESSES: Send comments on this
proposal to the Docket Management
System, U.S. Department of
Transportation, Room Plaza 401, 400
Seventh Street, SW., Washington, DC
20590–0001. You must identify FAA
Docket No. FAA–2005–23872 and
Airspace Docket No. 06–AAL–09, at the
beginning of your comments. You may
also submit comments through the
Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Ken
McElroy, Airspace and Rules, Office of
System Operations Airspace and AIM,
Federal Aviation Administration, 800
Independence Avenue, SW.,
Washington, DC 20591; telephone: (202)
267–8783.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested parties are invited to
participate in this proposed rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
E:\FR\FM\20APP1.SGM
20APP1
Agencies
[Federal Register Volume 71, Number 76 (Thursday, April 20, 2006)]
[Proposed Rules]
[Pages 20368-20374]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-5907]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE242; Notice No. 23-06-02-SC]
Special Conditions: Approved Model List Installation of AmSafe
Inflatable Restraints in Normal and Utility Category Non-23.562
Certified Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Proposed special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: This notice proposes special conditions for the installation
of an AmSafe, Inc., Inflatable Two-, Three-, Four or Five-Point
Restraint Safety Belt with an Integrated Airbag Device on various
airplane models. These airplanes, as modified by AmSafe, Inc., will
have novel and unusual design features associated with the lap belt or
shoulder harness portion of the safety belt, which contains an
integrated airbag device. 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: Comments must be received on or before May 22, 2006.
ADDRESSES: Comments on these special conditions may be mailed in
duplicate to: Federal Aviation Administration (FAA), Regional Counsel,
ACE-7, Attention: Rules Docket, Docket No. CE242, 901 Locust, Room 506,
Kansas City, Missouri 64106, or delivered in duplicate to the Regional
Counsel at the above address. Comments must be marked: CE242. Comments
may be inspected in the Rules Docket weekdays, except Federal holidays,
between 7:30 a.m. and 4 p.m.
FOR FURTHER INFORMATION CONTACT: Mr. Mark James, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Kansas City, Missouri, 816-329-4137,
fax 816-329-4090, e-mail mark.james@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of
these proposed special conditions by submitting such written data,
views, or arguments as they may desire. Communications should identify
the regulatory docket or notice number and be submitted in duplicate to
the address specified above. All communications received on or before
the closing date for comments will be considered by the Administrator.
The proposals described in this notice may be changed in light of the
comments received. All comments received will be available in the Rules
Docket for examination by interested persons, both before and after the
closing date for comments. A report summarizing each substantive public
contact with FAA personnel concerning this rulemaking will be filed in
the docket. Commenters wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include a self-
addressed, stamped postcard on which the following statement is made:
``Comments to CE242.'' The postcard will be date stamped and returned
to the commenter.
Background
On August 19, 2005, AmSafe, Inc., Aviation Inflatable Restraints
(AAIR) Division, 1043 North 47th Avenue, Phoenix, AZ 85043, applied for
a supplemental type certificate for the installation of an inflatable
restraint in various airplane models certificated before the dynamic
structural requirements as specified in 14 CFR part 23, section 23.562
took effect.
The inflatable restraint system is either a two-, three-, four, or
five-point safety belt restraint system consisting of a shoulder
harness and a lap belt with an inflatable airbag attached to either the
lap belt or the shoulder harness. The inflatable portion of the
restraint system will rely on sensors to electronically activate the
inflator for deployment. The inflatable restraint system will be made
available on the pilot, co-pilot, and passenger seats of these
airplanes.
In the event of an emergency landing, the airbag will inflate and
provide a protective cushion between the occupant's head and structure
within the airplane. This will reduce the potential for head and torso
injury. The inflatable restraint behaves in a manner that is similar to
an automotive airbag, but in this case, the airbag is integrated into
the lap or shoulder belt. While airbags and inflatable restraints are
standard in the automotive industry, the use of an inflatable restraint
system is novel for general aviation operations.
The FAA has determined that this project will be accomplished on
the basis of providing the same current level of safety of the
airplanes original certification basis. The FAA has two primary safety
concerns with the installation of airbags or inflatable restraints:
That they perform properly under foreseeable operating
conditions; and
That they do not perform in a manner or at such times as
to impede the pilot's ability to maintain control of the airplane or
constitute a hazard to the airplane or occupants.
The latter point has the potential to be the more rigorous of the
requirements. An unexpected deployment while conducting the takeoff or
landing phases of flight may result in an unsafe condition. The
unexpected deployment may either startle the pilot, or generate a force
sufficient to cause a sudden movement of the control yoke. Either
action could result in a loss of control of the airplane, the
consequences of which are magnified due to the low operating altitudes
during these phases of flight. The FAA has considered this
[[Page 20369]]
when establishing these special conditions.
The inflatable restraint system relies on sensors to electronically
activate the inflator for deployment. These sensors could be
susceptible to inadvertent activation, causing deployment in a
potentially unsafe manner. The consequences of an inadvertent
deployment must be considered in establishing the reliability of the
system. AmSafe, Inc. must show that the effects of an inadvertent
deployment in flight are not a hazard to the airplane or that an
inadvertent deployment is extremely improbable. In addition, general
aviation aircraft are susceptible to a large amount of cumulative wear
and tear on a restraint system. It is likely that the potential for
inadvertent deployment increases as a result of this cumulative damage.
Therefore, the impact of wear and tear on inadvertent deployment must
be considered. Due to the effects of this cumulative damage, a life
limit must be established for the appropriate system components in the
restraint system design.
There are additional factors to be considered to minimize the
chances of inadvertent deployment. General aviation airplanes are
exposed to a unique operating environment, since the same airplane may
be used by both experienced and student pilots. The effect of this
environment on inadvertent deployment must be understood. Therefore,
qualification testing of the firing hardware/software must consider the
following:
The airplane vibration levels appropriate for a general
aviation airplane; and
The inertial loads that result from typical flight or
ground maneuvers, including gusts and hard landings.
Any tendency for the firing mechanism to activate as a result of
these loads or acceleration levels is unacceptable.
Other influences on inadvertent deployment include high intensity
electromagnetic fields (HIRF) and lightning. Since the sensors that
trigger deployment are electronic, they must be protected from the
effects of these threats. To comply with HIRF and lightning
requirements, the AmSafe, Inc., inflatable restraint system is
considered a critical system, since its inadvertent deployment could
have a hazardous effect on the airplane.
Given the level of safety of the retrofitted airplane occupant
restraints, the inflatable restraint system must show that it will
offer an equivalent level of protection in the event of an emergency
landing. In the event of a deployment, the restraint must still be at
least as strong as a Technical Standard Order approved belt and
shoulder harnesses. There is no requirement for the inflatable portion
of the restraint to offer protection during multiple impacts, where
more than one impact would require protection.
The inflatable restraint system must deploy and provide protection
for each occupant during emergency landing conditions as specified in
the original certification basis. The seats of the various airplane
models were certificated prior to the dynamic structural requirements
of section 23.562. Therefore, the emergency landing loads conditions
identified in the original certification basis of the airplane must be
used to satisfy this requirement. Compliance will be demonstrated using
the test condition specified in the original certification basis. It
must also be shown that the crash sensor will trigger when exposed to a
rapidly applied deceleration, like an actual crash event. Therefore,
the test crash pulses identified in section 23.562 must be used to
satisfy this requirement, although, the peak ``G'' may be reduced to a
level meeting the original certification requirements of the aircraft.
Testing to these pulses will demonstrate that the crash sensor will
trigger when exposed to a rapidly applied deceleration, like an actual
crash event.
It is possible a wide range of occupants will use the inflatable
restraint. Thus, the protection offered by this restraint should be
effective for occupants that range from the fifth percentile female to
the ninety-fifth percentile male.
In support of this operational capability, there must be a means to
verify the integrity of this system before each flight. As an option,
AmSafe, Inc. can establish inspection intervals where they have
demonstrated the system to be reliable between these intervals.
It is possible that an inflatable restraint will be ``armed'' even
though no occupant is using the seat. While there will be means to
verify the integrity of the system before flight, it is also prudent to
require that unoccupied seats with active restraints not constitute a
hazard to any occupant. This will protect any individual performing
maintenance inside the cockpit while the aircraft is on the ground. The
restraint must also provide suitable visual warnings that would alert
rescue personnel to the presence of an inflatable restraint system.
In addition, the design must prevent the inflatable seatbelt from
being incorrectly buckled and/or installed such that the airbag would
not properly deploy. As an alternative, AmSafe, Inc. may show that such
deployment is not hazardous to the occupant and will still provide the
required protection.
The cabins of the various modeal airplanes identified in these
special conditions are confined areas, and the FAA is concerned that
noxious gasses may accumulate in the event of airbag deployment. When
deployment does occur, either by design or inadvertently, there must
not be a release of hazardous quantities of gas or particulate matter
into the cockpit.
An inflatable restraint should not increase the risk already
associated with fire. Therefore, the inflatable restraint should be
protected from the effects of fire, so that an additional hazard is not
created by, for example, a rupture of the inflator.
The airbag is likely to have a large volume displacement, and
possibly impede the egress of an occupant. Since the bag deflates to
absorb energy, it is likely that the inflatable restraint would be
deflated at the time an occupant would attempt egress. However, it is
appropriate to specify a time interval after which the inflatable
restraint may not impede rapid egress. Ten seconds has been chosen as
reasonable time. This time limit will offer a level of protection
throughout the impact event.
Finally, there is an elevated risk associated with inadvertent
deployment for agricultural airplanes, which are type certificated
under the restricted category. This is due to the unique operating
environment and low altitude flying of these airplanes. The FAA is
still trying to understand the risk and benefit associated with the
installation of these systems into restricted category airplanes in
general and agricultural airplanes specifically. Therefore, the
installation of the AAIR system is currently prohibited in agricultural
airplanes type certificated under the restricted category.
Special conditions for the installation of AAIR systems on other
Non-23.562 certificated airplanes have been issued and no substantive
public comments were received. Since the same special conditions were
issued multiple times for different model airplanes with no substantive
public comments, the FAA began issuing direct final special conditions
with an invitation for public comment. This was done to eliminate the
waiting period for public comments and AmSafe aviation could proceed
with the project, since no comments were expected.
These previous special conditions were issued for a single model
airplane or for variants of a model from a single airplane
manufacturer, and required dynamic testing of each AAIR system
[[Page 20370]]
installation for showing compliance. The AML Supplemental Type
Certificate sought by AmSafe Aviation has numerous airplane models and
manufacturers. Since AmSafe Aviation has previously demonstrated by
dynamic testing, and has the supporting data, that the Electronics
Module Assembly (EMA) and the inflator assembly will function as
intended in a simulated dynamic emergency landing, it is not necessary
to repeat the test for each airplane model shown in these special
conditions.
This is a departure from the method of showing compliance used in
the prior special conditions. Testing is required to show compliance,
but it is not necessary to repeat the testing for each airplane
installation. Existing test data is adequate for showing compliance for
other airplanes where the AAIR equipment is identical and the
installation is nearly identical. Since this is a substantial change in
the philosophy of showing compliance, it is prudent to give the public
time to comment on the special conditions prior to moving forward with
the project.
Type Certification Basis
Under the provisions of 14 CFR part 21, section 21.101, AmSafe,
Inc., must show that the affected airplane models, as changed, continue
to meet the applicable provisions of the regulations incorporated by
reference in the Type Certificate Numbers listed below or the
applicable regulations in effect on the date of application for the
change. The regulations incorporated by reference in the type
certificate are commonly referred to as the original ''type
certification basis'' and can be found in the Type Certificate Numbers
listed below. The following models are covered by this special
condition:
List of All Airplane Models and Applicable TCDS
----------------------------------------------------------------------------------------------------------------
Certification
Make Model TC holder TCDS basis
----------------------------------------------------------------------------------------------------------------
Aerostar........................ PA-60-600
(Aerostar 600),
PA-60-601
(Aerostar 601),
PA-60-601P
(Aerostar 601P),
PA-60-602P
(Aerostar 602P).
PA-60-700P A17WE Revision 22. 14 CFR PART 23.
(Aerostar 700P).
Aerostar Aircraft
Corporation.
ALL AMERICAN.................... 10A............... All American A-792............. CAR 3.
Aircraft, Inc.
American Champion (Champion).... 402............... American Champion A3CE Revision 5... CAR 3.
Aircraft Corp.
American Champion (Bellanca) 7AC, 7ACA, 7EC, American Champion A-759 Revision 67. CAR 4a.
(Champion) (Aeronca). 7GCB, S7AC, S7EC, Aircraft Corp.
7GCBA (L-16A),
7BCM, 7ECA, 7GCBC
(L-16B), 7CCM,
7FC, 7HC, S7CCM,
7GC, 7JC, 7DC,
7GCA, 7KC, S7DC,
7GCAA, 7KCAB.
American Champion (Bellanca) 11AC, S11AC, 11BC, American Champion A-761 Revision 17. CAR 4a.
(Trytek) (Aeronca). S11BC. Aircraft Corp.
AMERICAN CHAMPION (Bellanca) 11CC, S11CC....... American Champion A-796 Revision 14. CAR 3.
(Trytek) (Aeronca). Aircraft
Corporation.
VARGA (Morrisey)................ 2150, 2150A, 2180. Augustair, Inc.... 4A19 Revision 9... CAR 3.
Bellanca........................ 14-13, 14-13-2, 14- Bellanca Aircraft A-773 Revision 10. CAR 4a.
13-3, 14-13-3W. Corporation.
Bellanca........................ 14-9, 14-9L....... Bellanca Aircraft TC716............. CAR 4a.
Corporation.
Cessna.......................... 310, 310J, Cessna Aircraft 3A10 Revision 62.. CAR 3.
310A(USAF U-3A), Company.
310J-1, 310B,
E310J, 310C,
310K, 310D, 310L,
310E(USAF U-3B),
310N, 310F, 310P,
310G, T310P,
310H, 310Q,
E310H, T310Q,
310I, 310R, T310R.
Cessna.......................... 321 (Navy OE-2)... Cessna Aircraft 3A11 Revision 6... CAR 3.
Company.
Cessna.......................... 172, 172I, 172A, Cessna Aircraft 3A12 Revision 73.. CAR 3.
172K, 172B, 172L, Company.
172C, 172M, 172D,
172N, 172E, 172P,
172F (USAF T-
41A), 172Q, 172G,
172H, (USAF T-
41A).
CESSNA.......................... 175, 175A, 175B, Cessna Aircraft 3A17 Revision 45.. CAR 3.
175C, P172D, Company.
R172E (USAF T-
41B) (USAF T-41C
and D), R172F
(USAF T-41D),
R172G (USAF T-41C
or D), R172H
(USAF T-41D),
R172J, R172K,
172RG.
Cessna.......................... 182, 182K, 182A, Cessna Aircraft 3A13 Revision 64.. CAR 3.
182L, 182B, 182M, Company.
182C, 182N, 182D,
182P, 182E, 182Q,
182F, 182R, 182G,
R182, 182H, T182,
182J, TR182.
Cessna.......................... 210, 210K, 210A, Cessna Aircraft 3A21 Revision 46.. CAR 3.
T210K, 210B, Company.
210L, 210C,
T210L, 210D,
210M, 210E,
T210M, 210F,
210N, T210F,
P210N, 210G,
T210N, T210G,
210R, 210H,
P210R, T210H,
T210R, 210J, 210-
5 (205), T210J,
210-5A (205A).
[[Page 20371]]
Cessna.......................... 185, A185E, 185A, Cessna Aircraft 3A24 Revision 37.. CAR 3.
A185F, 185B, Company.
185C, 185D, 185E.
Cessna.......................... 320, 320F, 320-1, Cessna Aircraft 3A25 Revision 25.. CAR 3.
335, 320A, 340, Company.
320B, 340A, 320C,
320D, 320E.
Cessna.......................... 140A.............. Cessna Aircraft 5A2 Revision 21... CAR 3.
Company.
Cessna.......................... 180, 180E, 180A, Cessna Aircraft 5A6 Revision 66... CAR 3.
180F, 180B, 180G, Company.
180C, 180H, 180D,
180J, 180E, 180K.
Cessna.......................... 336............... Cessna Aircraft A2CE Revision 7... CAR 3.
Company.
Cessna.......................... 206, U206B, Cessna Aircraft A4CE Revision 43.. CAR 3.
TP206D, P206, Company.
U206C, TP206E,
P206A, U206D,
TU206A, P206B,
U206E, TU206B,
P206C, U206F,
TU206C, P206D,
U206G, TU206D,
P206E, TP206A,
TU206E, U206,
TP206B, TU206F,
U206A, TP206C,
TU206G.
CESSNA.......................... 337A (USAF 02B), Cessna Aircraft A6CE Revision 40.. CAR 3/14 CFR PART
T337E, 337B, Company. 23.
337F, M337B (USAF
02A), T337F,
T337B, 337G,
337C, T337G,
T337C, 337H,
337D, P337H,
T337D, T337H,
T337H-SP.
CESSNA.......................... 401, 411A, 401A, Cessna Aircraft A7CE Revision 46.. CAR 3.
414, 401B, 414A, Company.
402, 421, 402A,
421A, 402B, 421B,
402C, 421C, 411,
425.
CESSNA.......................... 190 (LC-126A,B,C), Cessna Aircraft A-790 Revision 36. CAR 3.
195, 195A, 195B. Company.
Cessna.......................... 170, 170A, 170B... Cessna Aircraft A-799 Revision 54. CAR 3.
Company.
CESSNA.......................... 150, 150J, 150A, Cessna Aircraft 3A19 Revision 44.. CAR 3.
150K, 150B, Company.
A150K, 150C,
150L, 150D,
A150L, 150E,
150M, 150F,
A150M, 150G, 152,
150H, A152.
CESSNA.......................... 177, 177A, 177B... Cessna Aircraft A13CE Revision 24. 14 CFR PART 23.
Company.
CESSNA.......................... 404, 406.......... Cessna Aircraft A25CE Revision 11. 14 CFR PART 23.
Company.
Cessna.......................... 208, 208A, 208B... Cessna Aircraft A37CE Revision 12. 14 CFR PART 23.
Company.
Cessna.......................... 441............... Cessna Aircraft A28CE Revision 12. 14 CFR PART 23.
Company.
Cessna.......................... 120, 140.......... Cessna Aircraft A-768 Revision 34. CAR 4a.
Company.
Commander Aircraft.............. Model 112, Model Commander Aircraft A12SO Revision 21. 14 CFR PART 23.
114, Model 112TC, Company.
Model 112B, Model
112TCA, Model
114A, Model 114B,
Model 114TC.
Great Lakes..................... 2T-1A, 2T-1A-1, 2T- Great Lakes A18EA Revision 10. Aeronautical
1A-2. Aircraft Company, Bulletin No. 7-A.
LLC.
Helio (Taylorcraft)............. 15A, 20........... Helio Aircraft 3A3 Revision 7.... CAR 4a.
Corporation.
LEARJET......................... 23................ Learjet Inc....... A5CE Revision 10.. CAR 3.
LOCKHEED........................ 402-2............. Lockheed Aircraft 2A11 Revision 4... AR 3.
International.
LAND-AIR (TEMCO) (LUSCOMBE)..... 11A, 11E.......... Luscombe Aircraft A-804 Revision 14. CAR 3.
Corporation.
MAULE........................... Bee Dee M-4, M-5- MAULE AEROSPACE 3A23 Revision 30.. CAR 3.
180C, MXT-7-160, TECHNOLOGY, INC.
M-4-180V, M-4 M-5-
200, MX-7-180A, M-
4C, M-5-210C, MXT-
7-180A, M-4S, M-5-
210TC, MX-7-180B,
M-4T, M-5-220C, M-
7-235B, M-4-180C,
M-5-235C, M-7-
235A, M-4-180S, M-
6-180, M-7-235C,
M-4-180T, M-6-
235, MX-7-180C, M-
4-210, M-7-235, M-
7-260, M-4-210C,
MX-7-235, MT-7-
260, M-4-210S, MX-
7-180, M-7-260C,
M-4-210T, MX-7-
420, M-7-420AC, M-
4-220, MXT-7-180,
MX-7-160C, M-4-
220C, MT-7-235,
MX-7-180AC, M-4-
220S, M-8-235, M-
7-420A, M-4-220T,
MX-7-160, MT-7-
420.
Mooney.......................... M20, M20A, M20B, Mooney Airplane 2A3 Revision 47... CAR 3.
M20C, M20D, M20E, Company, Inc.
M20F, M20G, M20J,
M20K (Up to S/N
25-2000), M20L.
Interceptor (Aero Commander) 200, 200A, 200B, Prop-Jets, Inc.... 3A18 Revision 16.. CAR 3.
(Meyers). 200C, 200D, 400.
[[Page 20372]]
BEECH........................... 35-33, J35, 35- Raytheon Aircraft 3A15 Revision 90.. CAR 3.
A33, K35, 35-B33, Company.
M35, 35-C33, N35,
35-C33A, P35,
E33, S35, E33A,
V35, E33C, V35A,
F33, V35B, F33A,
36, F33C, A36,
G33, A36TC, H35,
B36TC, G36.
BEECH........................... 45 (YT-34), A45 (T- Raytheon Aircraft 5A3 Revision 25... CAR 03.
34A, B-45), D45 Company.
(T-34B).
BEECH........................... 19A, B23, B19, Raytheon Aircraft A1CE Revision 34.. CAR 3.
C23, M19A, A24, Company.
23, A24R, A23,
B24R, A23A, C24R,
A23-19, A23-24.
BEECH........................... 3N, E18S-9700,3NM, Raytheon Aircraft A-765 Revision 74. CAR 03.
G18S, 3TM, H18, Company.
JRB-6, C-45G, TC-
45G, D18C, C-45H,
TC-45H, D18S, TC-
45J or E18S, UC-
45J (SNB-5) RC-
45J (SNB-5P).
BEECH........................... 35, A35, E35, B35, Raytheon Aircraft A-777 Revision 57. CAR 03.
F35, C35, G35, Company.
D35, 35R.
RAYTHEON........................ 200, A100-1 (U- Raytheon Aircraft A24CE Revision 91. 14 CFR PART 23.
21J), 200C, A200 Company.
(C-12A), 200CT,
A200 (C-12C),
200T, A200C (UC-
12B), B200,
A200CT (C-12D),
B200C, A200CT
(FWC-12D),
B200CT, A200CT (C-
12F), B200T,
A200CT (RC-12D),
300, A200CT (RC-
12G), 300LW,
A200CT (RC-12H),
B300, A200CT (RC-
12K), B300C,
A200CT (RC-12P),
1900, A200CT (RC-
12Q), 1900C,
B200C (C-12F),
1900D, B200C (UC-
12M), B200C (C-
12R), B200C (UC-
12F), 1900C (C-
12J).
Beech........................... B95A, D55, D95A, Raytheon Aircraft 3A16 Revision 81.. CAR 3.
D55A, E95, E55, Company.
95-55, E55A, 95-
A55, 56TC, 95-
B55, A56TC, 95-
B55A, 58, 95-B55B
(T-42A), 58A, 95-
C55, 95, 95-C55A,
B95, G58.
BEECH........................... 60, A60, B60...... Raytheon Aircraft A12CE Revision 23. 14 CFR PART 23.
Company.
BEECH........................... 58P, 58PA, 58TC, Raytheon Aircraft A23CE Revision 14. 14 CFR PART 23.
58TCA. Company.
CESSNA.......................... CESSNA F172D, Reims Aviation A4EU Revision 11.. CAR 10/ CAR 3.
CESSNA F172E, S.A..
CESSNA F172F,
CESSNA F172G,
CESSNA F172H,
CESSNA F172K,
CESSNA F172L,
CESSNA F172M,
CESSNA F172N,
CESSNA F172P.
SOCATA.......................... TB 9, TB 10, TB SOCATA--GROUPE A51EU Revision 14. 14 CFR PART 23.
20, TB 21, TB 200. AEROSPATIALE.
Pitts........................... S-1S, S-1T, S-2, S- Sky International A8SO Revision 21.. 14 CFR PART 23.
2A, S-2S, S-2B, S- Inc. (Aviat
2C. Aircraft, Inc.).
Taylorcraft..................... 19, F19, F21, Taylorcraft 1A9 Revision 19... CAR 3.
F21A, F21B, F22, Aviation LLC.
F22A, F22B, F22C.
TAYLORCRAFT..................... BC, BCS12-D, BCS, Taylorcraft A-696 Revision 22. CAR 04.
BC12-D1, BC-65, Aviation, LLC.
BCS12-D1, BCS-65,
BC12D-85, BC12-65
(Army L-2H),
BCS12D-85, BCS12-
65, BC12D-4-85,
BC12-D, BCS12D-4-
85.
TAYLORCRAFT..................... (Army L-2G) BF, Taylorcraft, Inc.. A-699 Revision 5.. CAR 4a.
BFS, BF-60, BFS-
60, BF-65, BFS-
65, (Army L-2K)
BF 12-65, BFS-65.
LUSCOMBE........................ 8, 8D, 8A, 8E, 8B, The Don Luscombe A-694 Revision 23. CAR 4a.
8F, 8C, T-8F. Aviation History
Foundation, Inc.
PIPER........................... PA-28-140, PA-28- The New Piper 2A13 Revision 47.. CAR 3.
151, PA-28-150, Aircraft, Inc.
PA-28-161, PA-28-
160, PA-28-181,
PA-28-180, PA-28R-
201, PA-28-235,
PA-28R-201T, PA-
28S-160, PA-28-
236, PA-28S-180,
PA-28RT-201, PA-
28R-180, PA-28RT-
201T, PA-28R-200,
PA-28-201T.
PIPER........................... PA-30, PA-39, PA- The New Piper A1EA Revision 16.. CAR 3.
40. Aircraft, Inc.
PIPER........................... PA-32-260, PA-32R- The New Piper A3SO Revision 29.. CAR 3.
301 (SP), PA-32- Aircraft, Inc.
300, PA-32R-301
(HP), PA-32S-300,
PA-32R-301T, PA-
32R-300, PA-32-
301, PA-32RT-300,
PA-32-301T, PA-
32RT-300T, PA-32-
301FT, PA-32-
301XTC.
PIPER........................... PA-34-200, PA-34- The New Piper A7SO Revision 16.. 14 CFR PART 23.
200T, PA-34-220T. Aircraft, Inc.
[[Page 20373]]
PIPER........................... PA-31P, PA-31T, PA- The New Piper A8EA Revision 22.. CAR 3.
31T1, PA-31T2, PA- Aircraft, Inc.
31T3, PA-31P-350.
PIPER........................... PA-36-285, PA-36- The New Piper A9SO Revision 9... 14 CFR PART 23.
300, PA-36-375. Aircraft, Inc.
PIPER........................... PA-36-285, PA-36- The New Piper A10SO Revision 12. 14 CFR PART 21/14
300, PA-36-375. Aircraft, Inc. CFR PART 23.
PIPER........................... PA-38-112......... The New Piper A18SO Revision 4.. 14 CFR PART 23.
Aircraft, Inc.
PIPER........................... PA-44-180, PA-44- The New Piper A19SO Revision 9.. 14 CFR PART 23.
180T. Aircraft, Inc.
PIPER........................... PA-31, PA-31-300, The New Piper A20SO Revision 10. CAR 3.
PA-31-325, PA-31- Aircraft, Inc.
350.
PIPER........................... PA-42, PA-42-720, The New Piper A23SO Revision 17. 14 CFR PART 23.
PA-42-1000. Aircraft, Inc.
PIPER........................... PA-46-310P, PA-46- The New Piper A25SO Revision 14. 14 CFR PART 23.
350P, PA-46-500TP. Aircraft, Inc.
Tiger Aircraft LLC (American AA-1, AA-1A, AA- Tiger Aircraft LLC A11EA Revision 10. 14 CFR PART 23.
General). 1B, AA-1C.
Tiger Aircraft.................. AA-5, AA-5A, AA- Tiger Aircraft LLC A16EA Revision 13. 14 CFR PART 23.
5B, AG-5B.
Twin Commander.................. 500, 500-A, 500-B, Twin Commander 6A1 Revision 45... CAR 3.
500-U, 520, 560, Aircraft
560-A, 560-E, 500- Corporation.
S.
Twin Commander.................. 560-F, 681, 680, Twin Commander 2A4 Revision 46... CAR 3.
690, 680E, 685, Aircraft
680F, 690A, 720, Corporation.
690B, 680FL,
690C, 680FL(P),
690D, 680T, 695,
680V, 695A, 680W,
695B.
Univair (Stinson)............... 108, 108-1, 108-2, Univair Aircraft A-767 Revision 27. CAR 3.
108-3, 108-5. Corporation.
Univair......................... (ERCO) 415-D, Univair Aircraft A-787 Revision 33. CAR 3.
(ERCO) E, (ERCO) Corporation.
G, (Forney) F-1,
(Forney) F-1A,
(Alon) A-2,
(Alon) A2-A,
(Mooney) M10.
Univair (Mooney)................ (ERCO) 415-C, Univair Aircraft A-718 Revision 29. CAR 4a.
(ERCO) 415-CD. Corporation.
----------------------------------------------------------------------------------------------------------------
For all the models listed above, the certification basis also
includes all exemptions, if any; equivalent level of safety findings,
if any; and special conditions not relevant to the special conditions
adopted by this rulemaking action.
The Administrator has determined that the applicable airworthiness
regulations (i.e., CAR 3. or part 23 as amended) do not contain
adequate or appropriate safety standards for the AmSafe, Inc.,
inflatable restraint as installed on these models because of a novel or
unusual design feature. Therefore, special conditions are prescribed
under the provisions of section 21.16.
Special conditions, as appropriate, as defined in section 11.19,
are issued in accordance with section 11.38, and become part of the
type certification basis in accordance with section 21.101.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, the special
conditions would also apply to that model under the provisions of
section 21.101.
Novel or Unusual Design Features
The various airplane models will incorporate the following novel or
unusual design feature:
The AmSafe, Inc., Inflatable Two-, Three-, Four-, or Five-Point
Restraint Safety Belt with an Integrated Airbag Device. The purpose of
the airbag is to reduce the potential for injury in the event of an
accident. In a severe impact, an airbag will deploy from the restraint,
in a manner similar to an automotive airbag. The airbag will deploy
between the head of the occupant and airplane interior structure. This
will, therefore, provide some protection to the head of the occupant.
The restraint will rely on sensors to electronically activate the
inflator for deployment.
The Code of Federal Regulations state performance criteria for
seats and restraints in an objective manner. However, none of these
criteria are adequate to address the specific issues raised concerning
inflatable restraints. Therefore, the FAA has determined that, in
addition to the requirements of part 21 and part 23, special conditions
are needed to address the installation of this inflatable restraint.
Accordingly, these special conditions are adopted for the various
airplane models equipped with the AmSafe, Inc., two-, three-, four, or
five-point inflatable restraint. Other conditions may be developed, as
needed, based on further FAA review and discussions with the
manufacturer and civil aviation authorities.
Conclusion
This action affects only certain novel or unusual design features
on the previously identified airplane models. It is not a rule of
general applicability, and it affects only the applicant who applied to
the FAA for approval of these features on the airplane.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and
21.101; and 14 CFR 11.38 and 11.19.
The Proposed Special Conditions
The FAA has determined that this project will be accomplished on
the basis of not lowering the current level of safety of the occupant
restraint system for the airplane models listed in these proposed
Special Conditions.
[[Page 20374]]
Accordingly, the FAA proposes the following special conditions as part
of the type certification basis for these models, as modified by
AmSafe, Incorporated.
Inflatable Two-, Three-, Four-, or Five-Point Restraint Safety Belt
With an Integrated Airbag Device Installed in an Airplane Model.
1a. It must be shown that the inflatable restraint will provide
restraint protection under the emergency landing conditions specified
in the original certification basis of the airplane. Compliance will be
demonstrated using the static test conditions specified in the original
certification basis for each airplane.
1b. It must be shown that the crash sensor will trigger when
exposed to arapidly applied deceleration, like an actual emergency
landing event. Therefore, compliance may be demonstrated using the
deceleration pulse specified in paragraph 23.562, which may be modified
as follows:
I. The peak longitudinal deceleration may be reduced, however the
onset rate of the deceleration must be equal to or greater than the
emergency landing pulse identified in paragraph 23.562.
II. The peak longitudinal deceleration must be above the deployment
threshold of the sensor, and equal or greater than the forward static
design longitudinal load factor required by the original certification
basis of the airplane.
2. The inflatable restraint must provide adequate protection for
each occupant. In addition, unoccupied seats that have an active
restraint must not constitute a hazard to any occupant.
3. The design must prevent the inflatable restraint from being
incorrectly buckled and/or incorrectly installed such that the airbag
would not properly deploy. Alternatively, it must be shown that such
deployment is not hazardous to the occupant and will provide the
required protection.
4. It must be shown that the inflatable restraint system is not
susceptible to inadvertent deployment as a result of wear and tear or
the inertial loads resulting from in-flight or ground maneuvers
(including gusts and hard landings) that are likely to be experienced
in service.
5. It must be extremely improbable for an inadvertent deployment of
the restraint system to occur, or an inadvertent deployment must not
impede the pilot's ability to maintain control of the airplane or cause
an unsafe condition (or hazard to the airplane). In addition, a
deployed inflatable restraint must be at least as strong as a Technical
Standard Order (C22g or C114) restraint.
6. It must be shown that deployment of the inflatable restraint
system is not hazardous to the occupant or result in injuries that
could impede rapid egress. This assessment should include occupants
whose restraint is loosely fastened.
7. It must be shown that an inadvertent deployment that could cause
injury to a sitting person is improbable. In addition, the restraint
must also provide suitable visual warnings that would alert rescue
personnel to the presence of an inflatable restraint system.
8. It must be shown that the inflatable restraint will not impede
rapid egress of the occupants 10 seconds after its deployment.
9. For the purposes of complying with HIRF and lightning
requirements, the inflatable restraint system is considered a critical
system since its deployment could have a hazardous effect on the
airplane.
10. It must be shown that the inflatable restraints will not
release hazardous quantities of gas or particulate matter into the
cabin.
11. The inflatable restraint system installation must be protected
from the effects of fire such that no hazard to occupants will result.
12. There must be a means to verify the integrity of the inflatable
restraint activation system before each flight or it must be
demonstrated to reliably operate between inspection intervals.
13. A life limit must be established for appropriate system
components.
14. Qualification testing of the internal firing mechanism must be
performed at vibration levels appropriate for a general aviation
airplane.
15. The installation of the AmSafe Aviation Inflatable Restraint
(AAIR) system is prohibited in agricultural airplanes type certificated
under the Restricted Category.
Issued in Kansas City, Missouri on April 6, 2006.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-5907 Filed 4-19-06; 8:45 am]
BILLING CODE 4910-13-P