Special Conditions: Embraer S.A.; Model EMB 500; Single-Place Side-Facing Seat Dynamic Test Requirements, 17332-17334 [2011-7307]
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Federal Register / Vol. 76, No. 60 / Tuesday, March 29, 2011 / Rules and Regulations
primarily to Federal employees and a
limited number of Federal and business
entities.9
List of Subjects
12 CFR Part 1208
Administrative practice and
procedure, Claims, Debt collection,
Government employees, Wages.
12 CFR Part 1704
Administrative practice and
procedure, Debt collection.
PART 1208—DEBT COLLECTION
PART 1704—[REMOVED]
Authority and Issuance
Accordingly, the interim final rule
establishing 12 CFR part 1208 and
removing 12 CFR part 1704 that was
published in the Federal Register at 75
FR 68956 on November 10, 2010, is
adopted as a final rule without change.
Dated: March 18, 2011.
Edward J. DeMarco,
Acting Director, Federal Housing Finance
Agency.
[FR Doc. 2011–7341 Filed 3–28–11; 8:45 am]
BILLING CODE 8070–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE311; Special Conditions No.
23–251–SC]
Special Conditions: Embraer S.A.;
Model EMB 500; Single-Place SideFacing Seat Dynamic Test
Requirements
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
These special conditions are
issued for the installation of a singleplace side-facing seat/lavatory on
Embraer S.A. EMB 500 aircraft. Sidefacing seats are considered a novel
design, and their installation in a part
23 airplane was not envisaged and is not
adequately addressed in 14 CFR part 23.
The FAA has determined that the
existing regulations do not provide
adequate or appropriate safety standards
for occupants of single-place side-facing
seats. In order to provide a level of
safety that is equivalent to that afforded
to occupants of forward and aft facing
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
SUMMARY:
9 Id.
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Jkt 223001
seating, additional airworthiness
standards, in the form of special
conditions, are necessary.
DATES: The effective date of these
special conditions is March 22, 2011.
Comments must be received on or
before April 28, 2011.
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.
CE311, 901 Locust, Room 506, Kansas
City, Missouri 64106, or delivered in
duplicate to the Regional Counsel at the
above address. Comments must be
marked: Docket No. CE311. 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.
Bob Stegeman, Federal Aviation
Administration, Aircraft Certification
Service, Small Airplane Directorate,
ACE–111, 901 Locust, Kansas City,
Missouri, 816–329–4140, fax 816–329–
4090, e-mail Robert.Stegeman@faa.gov.
SUPPLEMENTARY INFORMATION: The FAA
has determined that notice and
opportunity for prior public comment
hereon are impracticable because these
procedures would significantly delay
issuance of the approval design and
thus delivery of the affected aircraft.
The FAA therefore finds that good cause
exists for making these special
conditions effective upon issuance.
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 ask that you send
us two copies of written comments.
We will file in the docket all
comments we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning these special conditions.
You can inspect the docket before and
after the comment closing date. If you
wish to review the docket in person, go
to the address in the ADDRESSES section
of this preamble between 7:30 a.m. and
4 p.m., Monday through Friday, except
Federal holidays.
We will consider all comments we
receive on or before the closing date for
comments. We will consider comments
filed late if it is possible to do so
without incurring expense or delay. We
may change these special conditions
based on the comments we receive.
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Background
On December 26, 2009, Embraer S.A.
submitted request for a change to type
certificate No. A59CE for a design
change application (DCA) for
installation of a side-facing belted toilet
in the EMB–500 airplane. The
implication of the term belted is that the
toilet will be used for a passenger seat
during takeoff and landing and so must
comply with the provisions of 14 CFR
§§ 23.562 and 23.785 (in addition to the
certification basis as established in type
certificate A59CE) and any additional
requirements that the FAA determines
are applicable. In this case, the approval
of a side-facing seat to these provisions
is considered new and novel and, as
such, will require special conditions
and specific methods of compliance to
certificate.
14 CFR part 23 was amended August
8, 1988, by Amendment 23–36, to revise
the emergency landing conditions that
must be considered in the design of the
airplane. Amendment 23–36 revised the
static load conditions in § 23.561, and
added a new § 23.562 that required
dynamic testing for all seats approved
for occupancy during takeoff and
landing. The intent of Amendment 23–
36 is to provide an improved level of
safety for occupants on part 23
airplanes. Because most seating is
forward-facing in part 23 airplanes, the
pass/fail criteria developed in
Amendment 23–36 focused primarily on
these seats. Since the regulations do not
address side-facing seats, these criteria
should be documented in special
conditions.
The FAA decided to review
compliance with these regulations
because the current regulations do not
provide adequate and appropriate
standards for the type certification of
this type of seat.
These requirements are substantially
similar to other single place side-facing
seat installations approved for use on
several different 14 CFR part 25
airplanes.
Type Certification Basis
Under the provisions of § 21.101,
Embraer S.A. must show that the model
EMB 500, as modified, continues to
meet the applicable provisions of the
regulations incorporated by reference in
Type Certificate No. A59CE 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.’’ The regulations
incorporated by reference in Type
Certificate No. A59CE are as follows:
E:\FR\FM\29MRR1.SGM
29MRR1
Federal Register / Vol. 76, No. 60 / Tuesday, March 29, 2011 / Rules and Regulations
Part 23 of the Code of Federal
Regulations effective February 1, 1965,
as amended by 23–1 through 23–55; Part
36 of the Code of Federal Regulations
effective December 1, 1969, as amended
by 36–1 through 36–28; Part 34 of the
Code of Federal Regulations effective
September 10, 1990, as amended by
34–1 through 34–3.
For the model 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., part 23 as amended) do
not contain adequate or appropriate
safety standards for the Embraer EMB
500 side-facing seat because of a novel
or unusual design feature. Therefore,
special conditions are prescribed under
the provisions of § 21.16.
Special conditions, as appropriate, as
defined in § 11.19, are issued in
accordance with § 11.38, and become
part of the type certification basis in
accordance with § 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
§ 21.101.
Novel or Unusual Design Features
The Embraer S.A., model EMB 500
will incorporate the following novel or
unusual design feature:
A side-facing lavatory seat intended
for taxi/takeoff and landing.
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Discussion
The seat is to incorporate design
features that reduce the potential for
injury in the event of an accident. In a
severe impact, the occupant will be
restrained by a 3-point seatbelt and bear
on an adjacent padded wall. In addition
to the design features intended to
minimize occupant injury during an
accident sequence, the installation will
also require operational procedures that
will facilitate egress after an accident,
including leaving the lavatory door
locked open during taxi, takeoff and
landing. The adjacent forward wall/
bulkhead interior structure will have
padding, which will provide some
protection to the head of the occupant.
The Code of Federal Regulations
states performance criteria for forward
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Jkt 223001
and aft facing seats and restraints in an
objective manner. However, none of
these criteria are adequate to address the
specific issues raised concerning sidefacing seats. 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 seat installation/
restraint.
Accordingly, these special conditions
are for the Embraer S.A. model EMB 500
side-facing seat location. Other
conditions may be developed, as
needed, based on further FAA review
and discussions with the manufacturer
and civil aviation authorities.
Applicability
As discussed above, these special
conditions are applicable to the EMB
500. Should Embraer S.A. apply at a
later date for a change to the type
certificate to include another model
incorporating the same novel or unusual
design feature, the special conditions
would apply to that model as well.
Conclusion
This action affects only certain novel
or unusual design features on the
previously identified Embraer S.A.
model. 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 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 the Embraer S.A.
model EMB 500, as changed to allow
installation of a single-place side-facing
seat.
The minimum acceptable standards
for dynamic seat certification of the
belted lavatory seat are as follows:
1. Existing Criteria. As referenced by
§ 23.785(b), all injury protection criteria
of §§ 23.562(c)(1) through (c)(7) apply to
the occupants of the side-facing seats.
Head injury criteria (HIC) assessments
are only required for head contact with
the seat and/or adjacent structures.
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17333
2. Body-to-wall/furnishing contact.
The seat must be installed aft of a
structure such as an interior wall or
furnishing that will contact the pelvis,
upper arm, chest, or head of an
occupant seated next to the structure. A
conservative representation of the
structure and its stiffness must be
included in the tests. It is required that
the contact surface of this structure
must be covered with at least two inches
of energy absorbing protective padding
(foam or equivalent), such as Ensolite.
3. Thoracic Trauma. Testing with a
Side Impact Dummy (SID), as defined
by 49 CFR part 572, subpart F, or its
equivalent, must be performed in order
to establish Thoracic Trauma Index
(TTI) injury criteria. TTI acquired with
the SID must be less than 85, as defined
in 49 CFR part 572, subpart F. SID TTI
data must be processed as defined in
Federal Motor Vehicle Safety Standard
(FMVSS) Part 571.214, section S6.13.5.
Rational analysis, comparing an
installation with another installation
where TTI data were acquired and
found acceptable, may also be viable.
4. Pelvis. Pelvic lateral acceleration
must not exceed 130g. Pelvic
acceleration data must be processed as
defined in FMVSS Part 571.214, section
S6.13.5.
5. Shoulder Strap Loads. Where upper
torso straps (shoulder straps) are used
for occupants, tension loads in
individual straps must not exceed 1,750
pounds. If dual straps are used for
restraining the upper torso, the total
strap tension loads must not exceed
2,000 pounds.
6. Compression Loads. The
compression load measured between the
pelvis and the lumbar spine of the ATD
may not exceed 1,500 pounds.
7. Emergency Evacuation. When
occupied, the lavatory door must be
latched open for takeoff and landing and
must remain latched under the
§ 23.561(b) loads. The airplane
configuration must meet the emergency
evaluation requirements of its
certification basis with the seat
occupied.
8. Lavatory Door Placard. A placard
specifying the lavatory door must be
latched open for takeoff and landing
when occupied must be displayed on
the outside of the door.
9. Test Requirements in § 23.562
dynamic loads. The tests in § 23.562(a),
(b) and (c) must be conducted on the
lavatory seat. Floor deformation is
required except for a seat that is
cantilevered to the bulkhead.
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17334
Federal Register / Vol. 76, No. 60 / Tuesday, March 29, 2011 / Rules and Regulations
Issued in Kansas City, Missouri on March
22, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2011–7307 Filed 3–28–11; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM452; Notice No. 25–424–SC]
Special Conditions: Boeing Model 747–
2G4B Airplane; Certification of
Cooktops
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions; request
for comments.
AGENCY:
These special conditions are
issued for the Boeing Model 747–2G4B
series airplane. This airplane, as
modified by Greenpoint Technologies,
Inc., will have a novel or unusual design
feature associated with the replacement
and re-certification of existing cooktops
with advanced technology induction
coil cooktops in the main deck galleys
on two Boeing Model 747–2G4B
airplanes. The proposed modification is
limited to removing the existing
cooktops and replacing them with new
technology cooktops. No changes to the
galley surfaces, smoke detection system,
ventilation system, warning systems,
and fire suppression systems are
included in this modification. 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: The effective date of these
special conditions is March 22, 2011.
We must receive your comments by
April 28, 2011.
ADDRESSES: You must mail two copies
of your comments to: Federal Aviation
Administration, Transport Airplane
Directorate, Attn: Rules Docket (ANM–
113), Docket No. NM452, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356. You may deliver two
copies to the Transport Airplane
Directorate at the above address. You
must mark your comments: Docket No.
NM452. You can inspect comments in
the Rules Docket weekdays, except
wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
SUMMARY:
VerDate Mar<15>2010
13:46 Mar 28, 2011
Jkt 223001
Federal holidays, between 7:30 a.m. and
4 p.m.
FOR FURTHER INFORMATION CONTACT:
Jayson Claar, FAA, Airframe/Cabin
Safety Branch, ANM–115, Transport
Airplane Directorate, Aircraft
Certification Service, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 227–2194;
facsimile (425) 227–1320.
SUPPLEMENTARY INFORMATION:
The FAA has determined that notice
of, and opportunity for prior public
comment on, these special conditions is
impracticable because these procedures
would significantly delay issuance of
the design approval and thus delivery of
the affected airplanes. In addition, the
substance of these special conditions
has been subject to the public comment
process in several prior instances with
no substantive comments received. The
FAA therefore finds that good cause
exists for making these special
conditions effective upon issuance.
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 ask that you send
us two copies of written comments.
We will file in the docket all
comments we receive, as well as a
report summarizing each substantive
public contact with FAA personnel
concerning these special conditions.
You can inspect the docket before and
after the comment closing date. If you
wish to review the docket in person, go
to the address in the ADDRESSES section
of this preamble between 7:30 a.m. and
4 p.m., Monday through Friday, except
Federal holidays.
We will consider all comments we
receive on or before the closing date for
comments. We will consider comments
filed late if it is possible to do so
without incurring expense or delay. We
may change these special conditions
based on the comments we receive.
If you want us to acknowledge receipt
of your comments on this proposal,
include with your comments a selfaddressed, stamped postcard on which
you have written the docket number.
We will stamp the date on the postcard
and mail it back to you.
Background
On July 20, 2010, Greenpoint
Technologies, Inc., applied for a
Supplemental Type Certificate (STC) for
the replacement of existing cooktops in
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the Boeing Model 747–2G4B airplane.
The Boeing Model 747–2G4B currently
approved under Type Certificate No.
A20WE, is a Model 747–200 series
airplane with four CF6–80C2B1 engines.
The Model 747–200 series airplane is an
extended range passenger version of the
Model 747–100 airplanes with changes
to increase its strength and fuel
capacity.
The modification incorporates the
installation of an electrically heated
surface, called a cooktop. Cooktops
introduce high heat, smoke, and the
possibility of fire into the passenger
cabin environment. These potential
hazards to the airplane and its
occupants must be satisfactorily
addressed. Since existing airworthiness
regulations do not contain safety
standards addressing cooktops, special
conditions are therefore needed.
Type Certification Basis
Under the provisions of 14 CFR
21.101, Greenpoint Technologies Inc.,
must show that the Boeing Model 747–
2G4B, as changed, continues to meet the
applicable provisions of the regulations
incorporated by reference in Type
Certification No. A20WE, 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.’’ The regulations
incorporated by reference in Type
Certificate No. A20WE are part 25, as
amended by Amendments 25–1 through
25–8, with reversions to earlier
amendments, voluntary compliance to
later amendments, special conditions,
equivalent safety findings, and
exemptions listed in the type certificate
data sheet.
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 Boeing Model 747–2G4B because
of a novel or unusual design feature,
special conditions are prescribed under
the provisions of § 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 features,
the special conditions would also apply
to the other model.
In addition to the applicable
airworthiness regulations and special
conditions, the Boeing Model 747–2G4B
must comply with the fuel vent and
exhaust emission requirements of 14
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]]>Agencies
[Federal Register Volume 76, Number 60 (Tuesday, March 29, 2011)]
[Rules and Regulations]
[Pages 17332-17334]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-7307]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE311; Special Conditions No. 23-251-SC]
Special Conditions: Embraer S.A.; Model EMB 500; Single-Place
Side-Facing Seat Dynamic Test Requirements
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions; request for comments.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the installation of a
single-place side-facing seat/lavatory on Embraer S.A. EMB 500
aircraft. Side-facing seats are considered a novel design, and their
installation in a part 23 airplane was not envisaged and is not
adequately addressed in 14 CFR part 23. The FAA has determined that the
existing regulations do not provide adequate or appropriate safety
standards for occupants of single-place side-facing seats. In order to
provide a level of safety that is equivalent to that afforded to
occupants of forward and aft facing seating, additional airworthiness
standards, in the form of special conditions, are necessary.
DATES: The effective date of these special conditions is March 22,
2011. Comments must be received on or before April 28, 2011.
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. CE311, 901 Locust, Room 506,
Kansas City, Missouri 64106, or delivered in duplicate to the Regional
Counsel at the above address. Comments must be marked: Docket No.
CE311. 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. Bob Stegeman, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Kansas City, Missouri, 816-329-4140,
fax 816-329-4090, e-mail Robert.Stegeman@faa.gov.
SUPPLEMENTARY INFORMATION: The FAA has determined that notice and
opportunity for prior public comment hereon are impracticable because
these procedures would significantly delay issuance of the approval
design and thus delivery of the affected aircraft. The FAA therefore
finds that good cause exists for making these special conditions
effective upon issuance.
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 ask
that you send us two copies of written comments.
We will file in the docket all comments we receive, as well as a
report summarizing each substantive public contact with FAA personnel
concerning these special conditions. You can inspect the docket before
and after the comment closing date. If you wish to review the docket in
person, go to the address in the ADDRESSES section of this preamble
between 7:30 a.m. and 4 p.m., Monday through Friday, except Federal
holidays.
We will consider all comments we receive on or before the closing
date for comments. We will consider comments filed late if it is
possible to do so without incurring expense or delay. We may change
these special conditions based on the comments we receive.
Background
On December 26, 2009, Embraer S.A. submitted request for a change
to type certificate No. A59CE for a design change application (DCA) for
installation of a side-facing belted toilet in the EMB-500 airplane.
The implication of the term belted is that the toilet will be used for
a passenger seat during takeoff and landing and so must comply with the
provisions of 14 CFR Sec. Sec. 23.562 and 23.785 (in addition to the
certification basis as established in type certificate A59CE) and any
additional requirements that the FAA determines are applicable. In this
case, the approval of a side-facing seat to these provisions is
considered new and novel and, as such, will require special conditions
and specific methods of compliance to certificate.
14 CFR part 23 was amended August 8, 1988, by Amendment 23-36, to
revise the emergency landing conditions that must be considered in the
design of the airplane. Amendment 23-36 revised the static load
conditions in Sec. 23.561, and added a new Sec. 23.562 that required
dynamic testing for all seats approved for occupancy during takeoff and
landing. The intent of Amendment 23-36 is to provide an improved level
of safety for occupants on part 23 airplanes. Because most seating is
forward-facing in part 23 airplanes, the pass/fail criteria developed
in Amendment 23-36 focused primarily on these seats. Since the
regulations do not address side-facing seats, these criteria should be
documented in special conditions.
The FAA decided to review compliance with these regulations because
the current regulations do not provide adequate and appropriate
standards for the type certification of this type of seat.
These requirements are substantially similar to other single place
side-facing seat installations approved for use on several different 14
CFR part 25 airplanes.
Type Certification Basis
Under the provisions of Sec. 21.101, Embraer S.A. must show that
the model EMB 500, as modified, continues to meet the applicable
provisions of the regulations incorporated by reference in Type
Certificate No. A59CE 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.'' The regulations incorporated by
reference in Type Certificate No. A59CE are as follows:
[[Page 17333]]
Part 23 of the Code of Federal Regulations effective February 1, 1965,
as amended by 23-1 through 23-55; Part 36 of the Code of Federal
Regulations effective December 1, 1969, as amended by 36-1 through 36-
28; Part 34 of the Code of Federal Regulations effective September 10,
1990, as amended by 34-1 through 34-3.
For the model 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., part 23 as amended) do not contain adequate or
appropriate safety standards for the Embraer EMB 500 side-facing seat
because of a novel or unusual design feature. Therefore, special
conditions are prescribed under the provisions of Sec. 21.16.
Special conditions, as appropriate, as defined in Sec. 11.19, are
issued in accordance with Sec. 11.38, and become part of the type
certification basis in accordance with Sec. 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 Sec. 21.101.
Novel or Unusual Design Features
The Embraer S.A., model EMB 500 will incorporate the following
novel or unusual design feature:
A side-facing lavatory seat intended for taxi/takeoff and landing.
Discussion
The seat is to incorporate design features that reduce the
potential for injury in the event of an accident. In a severe impact,
the occupant will be restrained by a 3-point seatbelt and bear on an
adjacent padded wall. In addition to the design features intended to
minimize occupant injury during an accident sequence, the installation
will also require operational procedures that will facilitate egress
after an accident, including leaving the lavatory door locked open
during taxi, takeoff and landing. The adjacent forward wall/bulkhead
interior structure will have padding, which will provide some
protection to the head of the occupant.
The Code of Federal Regulations states performance criteria for
forward and aft facing seats and restraints in an objective manner.
However, none of these criteria are adequate to address the specific
issues raised concerning side-facing seats. 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
seat installation/restraint.
Accordingly, these special conditions are for the Embraer S.A.
model EMB 500 side-facing seat location. Other conditions may be
developed, as needed, based on further FAA review and discussions with
the manufacturer and civil aviation authorities.
Applicability
As discussed above, these special conditions are applicable to the
EMB 500. Should Embraer S.A. apply at a later date for a change to the
type certificate to include another model incorporating the same novel
or unusual design feature, the special conditions would apply to that
model as well.
Conclusion
This action affects only certain novel or unusual design features
on the previously identified Embraer S.A. model. 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 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 the Embraer S.A. model EMB 500, as
changed to allow installation of a single-place side-facing seat.
The minimum acceptable standards for dynamic seat certification of
the belted lavatory seat are as follows:
1. Existing Criteria. As referenced by Sec. 23.785(b), all injury
protection criteria of Sec. Sec. 23.562(c)(1) through (c)(7) apply to
the occupants of the side-facing seats. Head injury criteria (HIC)
assessments are only required for head contact with the seat and/or
adjacent structures.
2. Body-to-wall/furnishing contact. The seat must be installed aft
of a structure such as an interior wall or furnishing that will contact
the pelvis, upper arm, chest, or head of an occupant seated next to the
structure. A conservative representation of the structure and its
stiffness must be included in the tests. It is required that the
contact surface of this structure must be covered with at least two
inches of energy absorbing protective padding (foam or equivalent),
such as Ensolite.
3. Thoracic Trauma. Testing with a Side Impact Dummy (SID), as
defined by 49 CFR part 572, subpart F, or its equivalent, must be
performed in order to establish Thoracic Trauma Index (TTI) injury
criteria. TTI acquired with the SID must be less than 85, as defined in
49 CFR part 572, subpart F. SID TTI data must be processed as defined
in Federal Motor Vehicle Safety Standard (FMVSS) Part 571.214, section
S6.13.5. Rational analysis, comparing an installation with another
installation where TTI data were acquired and found acceptable, may
also be viable.
4. Pelvis. Pelvic lateral acceleration must not exceed 130g. Pelvic
acceleration data must be processed as defined in FMVSS Part 571.214,
section S6.13.5.
5. Shoulder Strap Loads. Where upper torso straps (shoulder straps)
are used for occupants, tension loads in individual straps must not
exceed 1,750 pounds. If dual straps are used for restraining the upper
torso, the total strap tension loads must not exceed 2,000 pounds.
6. Compression Loads. The compression load measured between the
pelvis and the lumbar spine of the ATD may not exceed 1,500 pounds.
7. Emergency Evacuation. When occupied, the lavatory door must be
latched open for takeoff and landing and must remain latched under the
Sec. 23.561(b) loads. The airplane configuration must meet the
emergency evaluation requirements of its certification basis with the
seat occupied.
8. Lavatory Door Placard. A placard specifying the lavatory door
must be latched open for takeoff and landing when occupied must be
displayed on the outside of the door.
9. Test Requirements in Sec. 23.562 dynamic loads. The tests in
Sec. 23.562(a), (b) and (c) must be conducted on the lavatory seat.
Floor deformation is required except for a seat that is cantilevered to
the bulkhead.
[[Page 17334]]
Issued in Kansas City, Missouri on March 22, 2011.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011-7307 Filed 3-28-11; 8:45 am]
BILLING CODE 4910-13-P
