[Federal Register: September 12, 2003 (Volume 68, Number 177)]
[Rules and Regulations]
[Page 53672-53674]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12se03-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM254; Special Conditions No. 25-246-SC]
Special Conditions: Cessna Model 680 Sovereign; Side-Facing
Single-Occupant Seats
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
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SUMMARY: These special conditions are issued for the Cessna Model 680
Sovereign airplane. This airplane will have a novel or unusual design
feature(s) associated with side-facing single-occupant seats. 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.
EFFECTIVE DATE: October 14, 2003.
FOR FURTHER INFORMATION CONTACT: Mark Quam, FAA, Standardization
Branch, ANM-113, Transport Airplane Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW., Renton, Washington, 98055-4056;
telephone (425) 227-2145, facsimile (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Background
On November 24, 1999, Cessna Aircraft Company, One Cessna
Boulevard, Wichita, KS 67277, applied for type certificate for their
new Cessna Model 680 Sovereign airplane. The Model 680 Sovereign is a
twin-engine pressurized executive jet airplane with standard seating
provisions for 12 passenger/crew and allowance for baggage and optional
equipment. This airplane will have a maximum takeoff weight of 30,000
pounds with a wingspan of 63.1 feet and will have two aft-mounted Pratt
& Whitney 306C engines.
The Cessna Model 680 offers interior arrangements, which include
single-occupant side-facing seat installations. These seats are
installed on the LH and RH side of the cabin's forward section, forward
of and opposite to the entry door respectively. Dynamic testing of all
seats approved for occupancy during takeoff and landing is required by
14 CFR 25.562. The pass/fail criteria for the testing developed in
Amendment 25-64
[[Page 53673]]
to Sec. 25.562 focused primarily on fore/aft-facing seats. Side-facing
seating installations were not adequately addressed for transport
category airplanes in this Amendment.
These special conditions are applicable to single-occupant side-
facing seats only. They are not intended to be used for multiple-
occupant side-facing divans or sofas, as they do not account for
possible interaction among the occupants.
Type Certification Basis
Under the provisions of 14 CFR 21.17, the Cessna Aircraft Company
must show that the Model 680 Sovereign airplane meets the applicable
provisions of 14 CFR part 25, effective February 1, 1965, as amended by
Amendments 25-1 through 25-98; 14 CFR part 34, effective September 10,
1990, as amended by any amendment in effect on the date of
certification.
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 Cessna Model 680 Sovereign
airplane because of a novel or unusual design feature, special
conditions are prescribed under the provisions of Sec. 21.16.
In addition to the applicable airworthiness regulations and special
conditions, the Cessna Model 680 Sovereign must comply with the fuel
vent and exhaust emission requirements of 14 CFR part 34 and the noise
certification requirements of 14 CFR part 36, and the FAA must issue a
finding of regulatory adequacy pursuant to Sec. 611 of Public Law 92-
574, the ``Noise Control Act of 1972.''
Special conditions, as defined in 14 CFR 11.19, are issued in
accordance with Sec. 11.38 and become part of the type certification
basis in accordance with Sec. 21.17(a)(2).
Special conditions are initially applicable to the model for which
they are issued. Should the type certificate for that model be amended
later to include any other model that incorporates the same novel or
unusual design feature, the special conditions would also apply to the
other model.
Novel or Unusual Design Features
The Cessna Model 680 offers interior arrangements, which include
single-occupant side-facing seat installations. These seats are
installed on the LH and RH side of the cabin's forward section, forward
and opposite to the entry door respectively. Dynamic testing of all
seats approved for occupancy during takeoff and landing is required by
Sec. 25.562. The pass/fail criteria for the testing developed in
Amendment 25-64 to Sec. 25.562 focused primarily on fore/aft-facing
seats. Side-facing seating installations were not adequately addressed
for transport category airplanes in this Amendment.
Discussion
The following injury criteria and testing represent the minimum
acceptable standards for certification of the Model 680 single-occupant
side-facing seats, and are to be included as requirements in these
special conditions. However, the existing requirements call for a ``no
yaw'' test condition. Cessna will demonstrate values of thoracic trauma
index (TTI) and lateral pelvic acceleration (LPA) for a ``10 degree
yaw'' for which it has some test data. In this case, Cessna must show
the ``10 degree yaw'' yields results that will only differ slightly
from the ``no yaw'' condition and that these differences would not be
of such magnitude as to exceed the maximum allowable.
Proposed Injury Criteria
(a) Existing Criteria. As referenced by Sec. 25.785(b), all injury
protection criteria of Sec. Sec. 25.562(c)(1) through (c)(6) apply to
the occupants of the single-occupant side-facing seats. Head injury
criteria (HIC) assessments are only required for head contact with the
seat and/or adjacent structures.
(b) 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 recommended, but not
required, that the contact surface of this structure be covered with at
least two inches of energy absorbing protective padding (foam or
equivalent), such as Ensolite.
(c) Thoracic Trauma. Testing with a Side Impact Dummy (SID), as
defined by 49 CFR Part 572, Subpart F, or its equivalent, must be
conducted and TTI injury criteria acquired with the SID must be less
than 85, as defined in 49 CFR Part 572, Subpart F. Side Impact Dummy
TTI 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.
(d) 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
(f) Shoulder Strap Loads. Where upper torso straps (shoulder
straps) are used for sofa 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.
Discussion of Comments
Notice of Proposed Special Conditions No. 25-03-03-SC for the
Cessna Model 680 Sovereign airplane was published in the Federal
Register on May 15, 2003 (68 FR 26237). No comments were received.
Applicability
As discussed above, these special conditions are applicable to the
Cessna Model 680 Sovereign airplane. Should Cessna Aircraft Company
apply at a later date for a change to the type certificate to include
another model incorporating the same novel or unusual design feature,
these special conditions would apply to that model as well.
Conclusion
This action affects only certain novel or unusual design features
on the Cessna Model 680 Sovereign airplane. 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 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
0
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Special Conditions
0
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 Cessna Aircraft Company Model 680
Sovereign airplane.
The minimum acceptable standards of injury criteria and testing
requirements for dynamic certification of the Model 680 side-facing
single-occupant seats are as follows:
(a) Existing Criteria. As referenced by Sec. 25.785(b), all injury
protection criteria of Sec. Sec. 25.562(c)(1) through (c)(6) 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.
(b) Body-to-wall/furnishing contact. The seat must be installed aft
of a structure such as an interior wall or
[[Page 53674]]
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
recommended, but not 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.
(c) Thoracic Trauma. Testing with a Side Impact Dummy (SID), as
defined by 49 CFR Part 572, Subpart F, or its equivalent, must be
conducted and TTI injury criteria acquired with the SID must be less
than 85, as defined in 49 CFR Part 572, Subpart F. SID TTI 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.
(d) 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
(f) 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.
Issued in Renton, Washington, on September 3, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-23293 Filed 9-11-03; 8:45 am]
BILLING CODE 4910-13-P