Special Conditions: Boeing Model 787-8 Airplane; Crashworthiness, 32021-32023 [E7-11153]
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Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Proposed Rules
amended (42 U.S.C. 2201(b), (i), (o), 2236,
2282); sec. 206, 88 Stat. 1246 (42 U.S.C.
5846). Section 2.205(j) also issued under Pub.
L. 101–410, 104 Stat. 90, as amended by
section 3100(s), Pub. L. 104–134, 110 Stat.
1321–373 (28 U.S.C. 2461 note). Sections
2.600–2.606 also issued under sec. 102, Pub.
L. 91–190, 83 Stat. 853, as amended (42
U.S.C. 4332). Sections 2.700a, 2.719 also
issued under 5 U.S.C. 554.
Sections 2.754, 2.760, 2.770, 2.780 also
issued under 5 U.S.C. 557. Section 2.764 also
issued under secs. 135, 141, Pub. L. 97—425,
96 Stat. 2232, 2241 (42 U.S.C. 10155, 10161).
Section 2.790 also issued under sec. 103, 68
Stat. 936, as amended (42 U.S.C. 2133), and
5 U.S.C. 552. Sections 2.800 and 2.808 also
issued under 5 U.S.C. 553. Section 2.809 also
issued under 5 U.S.C. 553, and sec. 29, Pub.
L. 85–256, 71 Stat. 579, as amended (42
U.S.C. 2039). Subpart K also issued under
sec. 189, 68 Stat. 955 (42 U.S.C. 2239); sec.
134, Pub. L. 97–425, 96 Stat. 2230 (42 U.S.C.
10154). Subpart L also issued under sec. 189,
68 Stat. 955 (42 U.S.C. 2239). Subpart M also
issued under sec. 184 (42 U.S.C. 2234) and
sec. 189, 68 stat. 955 (42 U.S.C. 2239).
Appendix A also issued under sec. 6, Pub. L.
91–560, 84 Stat. 1473 (42 U.S.C. 2135).
2. In § 2.4, a definition of Potential
party is added in alphabetical order to
read as follows:
§ 2.4
Definitions.
*
*
*
*
*
Potential party means any person who
has requested, or who may intend to
request, a hearing or petition to
intervene in a hearing under 10 CFR
part 2, other than hearings conducted
pursuant to Subparts J and M of Part 2.
*
*
*
*
*
3. Section 2.311 is revised to read as
follows:
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
§ 2.311 Interlocutory review of rulings on
requests for hearings/petitions to intervene,
selection of hearing procedure, and
requests by potential parties for access to
sensitive unclassified non-safeguards
information and safeguards information.
(a) An order of the presiding officer,
or if a presiding officer has not been
designated, of the Chief Administrative
Judge, or if he or she is unavailable, of
another administrative judge, or of an
administrative law judge with
jurisdiction pursuant to § 2.318(a), may
be appealed to the Commission with
respect to:
(1) A request for hearing,
(2) A petition to intervene, or
(3) A request for access to sensitive
unclassified non-safeguards information
(SUNSI), including, but not limited to,
proprietary, confidential commercial,
and security-related information, and
Safeguards Information (SGI). An appeal
to the Commission may also be taken
from an order of an officer designated to
rule on information access issues.
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12:18 Mar 07, 2011
Jkt 223001
(b) These appeals must be made in
accordance with the provisions of this
section, within ten (10) days after the
service of the order. The appeal must be
initiated by the filing of a notice of
appeal and accompanying supporting
brief. Any party who opposes the appeal
may file a brief in opposition to the
appeal within ten (10) days after service
of the appeal. The supporting brief and
any answer must conform to the
requirements of § 2.341(c)(2). No other
appeals from rulings on requests for
hearings are allowed.
(c) An order denying a petition to
intervene, and/or request for hearing, or
a request for access to the information
described in paragraph (a) of this
section, is appealable by the requestor/
petitioner on the question as to whether
the request and/or petition should have
been granted.
(d) An order granting a petition to
intervene, and/or request for hearing, or
a request for access to the information
described in paragraph (a) of this
section, is appealable by a party other
than the requestor/petitioner on the
question as to:
(1) Whether the request/petition
should have been wholly denied, or
(2) Whether the request for access to
the information described in paragraph
(a)(3) of this section should have been
denied in whole or in part.
(e) An order selecting a hearing
procedure may be appealed by any party
on the question as to whether the
selection of the particular hearing
procedures was in clear contravention
of the criteria set forth in § 2.310. The
appeal must be filed with the
Commission no later than ten (10) days
after issuance of the order selecting a
hearing procedure.
Dated at Rockville, Maryland, this 5th day
of June 2007.
For the Nuclear Regulatory Commission.
Annette L. Vietti-Cook,
Secretary of the Commission.
[FR Doc. 07–2884 Filed 6–8–07; 8:45 am]
BILLING CODE 7590–01–P
32021
Notice of proposed special
conditions.
ACTION:
SUMMARY: This notice proposes special
conditions for the Boeing Model 787–8
airplane. This airplane will have novel
or unusual design features when
compared to the state of technology
envisioned in the airworthiness
standards for transport category
airplanes. These novel or unusual
design features are associated with
carbon fiber reinforced plastic used in
the construction of the fuselage. For
these design features, the applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
for impact response characteristics to
ensure survivable crashworthiness.
These proposed 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.
Additional special conditions will be
issued for other novel or unusual design
features of the Boeing 787–8 airplanes.
DATES: Comments must be received on
or before July 26, 2007.
ADDRESSES: Comments on this proposal
may be mailed in duplicate to: Federal
Aviation Administration, Transport
Airplane Directorate, Attention: Rules
Docket (ANM–113), Docket No. NM368,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; or delivered in
duplicate to the Transport Airplane
Directorate at the above address. All
comments must be marked Docket No.
NM368. 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: Ian
Won, FAA, Airframe/Cabin Safety,
ANM–115, Transport Airplane
Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW.,
Renton, Washington 98057–3356;
telephone (425) 227–2145; facsimile
(425) 227–1320.
SUPPLEMENTARY INFORMATION:
Comments Invited
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM368 Special Conditions No.
25–07–05–SC]
Special Conditions: Boeing Model
787–8 Airplane; Crashworthiness
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
The FAA invites interested persons to
participate in this rulemaking by
submitting 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
E:\ERIC\11JNP1.SGM
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32022
Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Proposed Rules
contact with FAA personnel concerning
these proposed special conditions. The
docket is available for public inspection
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 notice
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 the proposed special
conditions based on comments we
receive.
If you want the FAA to acknowledge
receipt of your comments on this
proposal, include with your comments
a pre-addressed, stamped postcard on
which the docket number appears. We
will stamp the date on the postcard and
mail it back to you.
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
Background
On March 28, 2003, Boeing applied
for an FAA type certificate for its new
Boeing Model 787–8 passenger airplane.
The Model 787–8 airplane will be an
all-new, two-engine jet transport
airplane with a two-aisle cabin. The
maximum takeoff weight will be
476,000 pounds, with a maximum
passenger count of 381 passengers.
Type Certification Basis
Under provisions of 14 CFR 21.17,
Boeing must show that Model 787–8
airplanes (hereafter referred to as ‘‘the
787’’) meet the applicable provisions of
14 CFR part 25, as amended by
Amendments 25–1 through 25–117,
except §§ 25.809(a) and 25.812, which
will remain at Amendment 25–115. If
the Administrator finds that the
applicable airworthiness regulations do
not contain adequate or appropriate
safety standards for the 787 airplane
because of a novel or unusual design
feature, special conditions are
prescribed under provisions of 14 CFR
21.16.
In addition to the applicable
airworthiness regulations and special
conditions, the 787 airplane must
comply with the fuel vent and exhaust
emission requirements of 14 CFR part
34 and the noise certification
requirements of part 36. In addition, the
FAA must issue a finding of regulatory
adequacy pursuant to section 611 of
Public Law 92–574, the ‘‘Noise Control
Act of 1972.’’
Special conditions, as defined in
§ 11.19, are issued in accordance with
§ 11.38 and become part of the type
certification basis in accordance with
§ 21.17(a)(2).
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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 or similar novel
or unusual design feature, the special
conditions would also apply to the other
model under the provisions of § 21.101.
Novel or Unusual Design Features
The 787 airplane will incorporate a
number of novel or unusual design
features. Because of rapid improvements
in airplane technology, the applicable
airworthiness regulations do not contain
adequate or appropriate safety standards
for these design features. These
proposed special conditions for the 787
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.
The 787 fuselage will be fabricated
with carbon fiber reinforced plastic
(CFRP) semi-monocoque construction,
consisting of skins with co-cured
longitudinal stringers and mechanically
fastened circumferential frames. This is
a novel and unusual design feature for
a large transport category airplane
certificated under 14 CFR part 25.
Structure fabricated from CFRP may
behave differently than metallic
structure because of differences in
material ductility, stiffness, failure
modes, and energy absorption
characteristics. Therefore, impact
response characteristics of the 787 must
be evaluated to ensure that its
survivable crashworthiness
characteristics provide approximately
the same level of safety as those of a
similarly sized airplane fabricated from
traditionally used metallic materials.
The FAA and industry have been
working together for many years to
understand how transport airplane
occupant safety can be improved for
what are considered survivable
accidents. This work has involved
examining airplane accidents,
conducting tests to simulate crash
conditions, and performing analytical
modeling of a range of crash conditions,
all with the purpose of providing further
insight into factors that can influence
occupant safety. Results of this on-going
effort have enabled specific changes to
regulatory standards and design
practices to improve occupant safety.
This evolution is reflected in changes to
the part 25 Emergency Landing
Conditions regulations. For example,
airplane emergency load factors in
§ 25.561, General, have been increased.
Passenger seat dynamic load conditions
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
have been added (§ 25.562, Emergency
Landing Dynamic Conditions).
The seat dynamic conditions were
added to the regulations based on FAA
and industry tests and a review of
accidents. These seat dynamic
conditions reflect the environment for
passengers and the airframe during a
crash event. They are based on data
gathered from accidents of previously
certificated airplanes given conditions
that were survivable. Tests of previously
certificated airplanes demonstrated that
performance of the airframe was
acceptable in a survivable crash event.
We continually update our requirements
as such new information becomes
available. In the context of this
evolution of the regulations, there is at
present no specific dynamic regulatory
requirement for airplane-level
crashworthiness. However, the FAA
reviews the design of each new airplane
model to determine if it incorporates
novel or unusual design features that
may have a significant influence on the
crash dynamics of the airframe. The
Administrator prescribes special
conditions for the airplane model if the
applicable airworthiness regulations do
not contain adequate or appropriate
safety standards because of the novel or
unusual design feature. Because of the
novel design features of the 787, the
FAA intends to require Boeing to
conduct an assessment to ensure that
the 787 will not have dynamic
characteristics that differ significantly
from those found in previously
certificated designs.
The nature of this proposed design
assessment is largely dependent on the
similarities and differences between the
new type design and previously
certificated airplanes. Such an
assessment ensures that the level of
safety of the new type design is
commensurate with that implicitly
assumed in the existing regulations, and
achieved by airplane designs previously
certificated. If significant trends in
industry warrant change to the existing
regulations, the FAA may use its
rulemaking process in collaboration
with industry to develop an appropriate
dynamic regulatory requirement for
airplane level crashworthiness.
The FAA and industry have collected
a significant amount of experimental
data as well as data from crashes of
transport category airplanes that
demonstrates a high occupant survival
rate at vertical descent velocities up to
30 ft/sec. The majority of this data was
collected on narrow-body (single aisle)
transport category airplanes. Based on
this information, the FAA finds it
appropriate and necessary for an
assessment of the 787 to span a range of
E:\ERIC\11JNP1.SGM
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Federal Register / Vol. 72, No. 111 / Monday, June 11, 2007 / Proposed Rules
rmajette on DSK8KYBLC1PROD with MISCELLANEOUS
airplane vertical descent velocities up to
30 ft/sec.
The FAA is proposing this special
condition to maintain the level of safety
envisioned in the existing airworthiness
standards under foreseeable survivable
impact events.
Discussion of Proposed Special
Condition
In order to provide the same level of
safety as exists with conventional
airplane construction, Boeing must
demonstrate that the 787 has sufficient
crashworthiness capabilities under
foreseeable survivable impact events. To
demonstrate this, Boeing would have to
evaluate the impact response
characteristics of the 787 to ensure that
its crashworthiness characteristics are
not significantly different from those of
a similarly sized airplane fabricated
from traditionally used metals. If the
evaluation shows that the 787 impact
response characteristics are significantly
different, Boeing would have to make
design changes to bring the different
impact response characteristics in line
with those of a similarly sized metal
construction airplane, or incorporate
mitigating design features.
Factors in crash survivability are
retention of items of mass, maintenance
of occupant emergency egress paths,
maintenance of acceptable acceleration
and loads experienced by the occupants,
and maintenance of a survivable
volume. In reviewing available data
from accidents, tests simulating crash
conditions, and analytical modeling of a
range of crash conditions, the FAA has
concluded that the airplane
performance should be evaluated over a
range of airplane level vertical impact
velocities up to 30 ft/sec.
If the 787 impact characteristics differ
significantly from those of a previously
certificated wide body transport, this
would result in a need to meet load
factors higher than those defined in 14
CFR 25.561 in order to maintain the
same level of safety for the occupants,
in terms of retention of items of mass.
In the cases of acceleration and loads
experienced by the occupants, means
would have to be incorporated to reduce
load levels experienced by those
occupants to the injury criteria levels of
§ 25.562, or load levels of a previously
certificated comparable airplane, in
order to maintain the same level of
safety for the occupants.
Applicability
As discussed above, these proposed
special conditions are applicable to the
787 airplane. Should Boeing apply at a
later date for a change to the type
certificate to include another model
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Jkt 223001
incorporating the same novel or unusual
design features, these proposed special
conditions would apply to that model as
well under the provisions of § 21.101.
Conclusion
This action affects only certain novel
or unusual design features of the 787
airplane. It is not a rule of general
applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
Special Conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
The Proposed Special Conditions
Accordingly, the Administrator of the
Federal Aviation Administration (FAA)
proposes the following special
conditions as part of the type
certification basis for the Boeing Model
787–8 airplane.
The Boeing Model 787–8 must
provide an equivalent level of occupant
safety and survivability to that provided
by previously certificated wide-body
transports of similar size under
foreseeable survivable impact events for
the following four criteria. In order to
demonstrate an equivalent level of
occupant safety and survivability, the
applicant must demonstrate that the
Model 787–8 meets the following
criteria for a range of airplane vertical
descent velocities up to 30 ft/sec.
1. Retention of items of mass. The
occupants, i.e., passengers, flight
attendants and flightcrew, must be
protected during the impact event from
release of seats, overhead bins, and
other items of mass due to the impact
loads and resultant structural
deformation of the supporting airframe
and floor structures. The applicant must
show that loads due to the impact event
and resultant structural deformation of
the supporting airframe and floor
structure at the interface of the airplane
structure to seats, overhead bins, and
other items of mass are comparable to
those of previously certificated widebody transports of similar size for the
range of descent velocities stated above.
The attachments of these items need not
be designed for static emergency
landing loads in excess of those defined
in § 25.561 if impact response
characteristics of the Boeing Model 787–
8 yield load factors at the attach points
that are comparable to those for a
previously certificated wide-body
transport category airplane.
2. Maintenance of acceptable
acceleration and loads experienced by
the occupants. The applicant must show
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
32023
that the impact response characteristics
of the 787, specifically the vertical
acceleration levels experienced at the
seat/floor interface and loads
experienced by the occupants during
the impact events, are consistent with
those found in § 25.562(b) or with levels
expected for a previously certificated
wide-body transport category airplane
for the conditions stated above.
3. Maintenance of a survivable
volume. For the conditions stated above,
the applicant must show that all areas
of the airplane occupied for takeoff and
landing provide a survivable volume
comparable to that of previously
certificated wide-body transports of
similar size during and after the impact
event. This means that structural
deformation will not result in
infringement of the occupants’ normal
living space so that passenger
survivability will not be significantly
affected.
4. Maintenance of occupant
emergency egress paths. The evacuation
of occupants must be comparable to that
from a previously certificated widebody transport of similar size. To show
this, the applicant must show that the
suitability of the egress paths, as
determined following the vertical
impact events, is comparable to the
suitability of the egress paths of a
comparable, certificated wide-body
transport, as determined following the
same vertical impact events.
Issued in Renton, Washington, on May 31,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–11153 Filed 6–8–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM367 Special Conditions No.
25–07–04–SC]
Special Conditions: Boeing Model 787–
8 Airplane; Tire Debris Penetration of
Fuel Tank Structure
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed special
conditions.
AGENCY:
SUMMARY: This notice proposes special
conditions for the Boeing Model 787–8
airplane. This airplane will have novel
or unusual design features when
compared to the state of technology
envisioned in the airworthiness
E:\ERIC\11JNP1.SGM
11JNP1
Agencies
[Federal Register Volume 72, Number 111 (Monday, June 11, 2007)]
[Proposed Rules]
[Pages 32021-32023]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-11153]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM368 Special Conditions No. 25-07-05-SC]
Special Conditions: Boeing Model 787-8 Airplane; Crashworthiness
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
-----------------------------------------------------------------------
SUMMARY: This notice proposes special conditions for the Boeing Model
787-8 airplane. This airplane will have novel or unusual design
features when compared to the state of technology envisioned in the
airworthiness standards for transport category airplanes. These novel
or unusual design features are associated with carbon fiber reinforced
plastic used in the construction of the fuselage. For these design
features, the applicable airworthiness regulations do not contain
adequate or appropriate safety standards for impact response
characteristics to ensure survivable crashworthiness. These proposed
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.
Additional special conditions will be issued for other novel or unusual
design features of the Boeing 787-8 airplanes.
DATES: Comments must be received on or before July 26, 2007.
ADDRESSES: Comments on this proposal may be mailed in duplicate to:
Federal Aviation Administration, Transport Airplane Directorate,
Attention: Rules Docket (ANM-113), Docket No. NM368, 1601 Lind Avenue
SW., Renton, Washington 98057-3356; or delivered in duplicate to the
Transport Airplane Directorate at the above address. All comments must
be marked Docket No. NM368. 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: Ian Won, FAA, Airframe/Cabin Safety,
ANM-115, Transport Airplane Directorate, Aircraft Certification
Service, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone
(425) 227-2145; facsimile (425) 227-1320.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites interested persons to participate in this
rulemaking by submitting 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
[[Page 32022]]
contact with FAA personnel concerning these proposed special
conditions. The docket is available for public inspection 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 notice
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 the
proposed special conditions based on comments we receive.
If you want the FAA to acknowledge receipt of your comments on this
proposal, include with your comments a pre-addressed, stamped postcard
on which the docket number appears. We will stamp the date on the
postcard and mail it back to you.
Background
On March 28, 2003, Boeing applied for an FAA type certificate for
its new Boeing Model 787-8 passenger airplane. The Model 787-8 airplane
will be an all-new, two-engine jet transport airplane with a two-aisle
cabin. The maximum takeoff weight will be 476,000 pounds, with a
maximum passenger count of 381 passengers.
Type Certification Basis
Under provisions of 14 CFR 21.17, Boeing must show that Model 787-8
airplanes (hereafter referred to as ``the 787'') meet the applicable
provisions of 14 CFR part 25, as amended by Amendments 25-1 through 25-
117, except Sec. Sec. 25.809(a) and 25.812, which will remain at
Amendment 25-115. If the Administrator finds that the applicable
airworthiness regulations do not contain adequate or appropriate safety
standards for the 787 airplane because of a novel or unusual design
feature, special conditions are prescribed under provisions of 14 CFR
21.16.
In addition to the applicable airworthiness regulations and special
conditions, the 787 airplane must comply with the fuel vent and exhaust
emission requirements of 14 CFR part 34 and the noise certification
requirements of part 36. In addition, the FAA must issue a finding of
regulatory adequacy pursuant to section 611 of Public Law 92-574, the
``Noise Control Act of 1972.''
Special conditions, 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. 21.17(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 or similar
novel or unusual design feature, the special conditions would also
apply to the other model under the provisions of Sec. 21.101.
Novel or Unusual Design Features
The 787 airplane will incorporate a number of novel or unusual
design features. Because of rapid improvements in airplane technology,
the applicable airworthiness regulations do not contain adequate or
appropriate safety standards for these design features. These proposed
special conditions for the 787 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.
The 787 fuselage will be fabricated with carbon fiber reinforced
plastic (CFRP) semi-monocoque construction, consisting of skins with
co-cured longitudinal stringers and mechanically fastened
circumferential frames. This is a novel and unusual design feature for
a large transport category airplane certificated under 14 CFR part 25.
Structure fabricated from CFRP may behave differently than metallic
structure because of differences in material ductility, stiffness,
failure modes, and energy absorption characteristics. Therefore, impact
response characteristics of the 787 must be evaluated to ensure that
its survivable crashworthiness characteristics provide approximately
the same level of safety as those of a similarly sized airplane
fabricated from traditionally used metallic materials.
The FAA and industry have been working together for many years to
understand how transport airplane occupant safety can be improved for
what are considered survivable accidents. This work has involved
examining airplane accidents, conducting tests to simulate crash
conditions, and performing analytical modeling of a range of crash
conditions, all with the purpose of providing further insight into
factors that can influence occupant safety. Results of this on-going
effort have enabled specific changes to regulatory standards and design
practices to improve occupant safety. This evolution is reflected in
changes to the part 25 Emergency Landing Conditions regulations. For
example, airplane emergency load factors in Sec. 25.561, General, have
been increased. Passenger seat dynamic load conditions have been added
(Sec. 25.562, Emergency Landing Dynamic Conditions).
The seat dynamic conditions were added to the regulations based on
FAA and industry tests and a review of accidents. These seat dynamic
conditions reflect the environment for passengers and the airframe
during a crash event. They are based on data gathered from accidents of
previously certificated airplanes given conditions that were
survivable. Tests of previously certificated airplanes demonstrated
that performance of the airframe was acceptable in a survivable crash
event. We continually update our requirements as such new information
becomes available. In the context of this evolution of the regulations,
there is at present no specific dynamic regulatory requirement for
airplane-level crashworthiness. However, the FAA reviews the design of
each new airplane model to determine if it incorporates novel or
unusual design features that may have a significant influence on the
crash dynamics of the airframe. The Administrator prescribes special
conditions for the airplane model if the applicable airworthiness
regulations do not contain adequate or appropriate safety standards
because of the novel or unusual design feature. Because of the novel
design features of the 787, the FAA intends to require Boeing to
conduct an assessment to ensure that the 787 will not have dynamic
characteristics that differ significantly from those found in
previously certificated designs.
The nature of this proposed design assessment is largely dependent
on the similarities and differences between the new type design and
previously certificated airplanes. Such an assessment ensures that the
level of safety of the new type design is commensurate with that
implicitly assumed in the existing regulations, and achieved by
airplane designs previously certificated. If significant trends in
industry warrant change to the existing regulations, the FAA may use
its rulemaking process in collaboration with industry to develop an
appropriate dynamic regulatory requirement for airplane level
crashworthiness.
The FAA and industry have collected a significant amount of
experimental data as well as data from crashes of transport category
airplanes that demonstrates a high occupant survival rate at vertical
descent velocities up to 30 ft/sec. The majority of this data was
collected on narrow-body (single aisle) transport category airplanes.
Based on this information, the FAA finds it appropriate and necessary
for an assessment of the 787 to span a range of
[[Page 32023]]
airplane vertical descent velocities up to 30 ft/sec.
The FAA is proposing this special condition to maintain the level
of safety envisioned in the existing airworthiness standards under
foreseeable survivable impact events.
Discussion of Proposed Special Condition
In order to provide the same level of safety as exists with
conventional airplane construction, Boeing must demonstrate that the
787 has sufficient crashworthiness capabilities under foreseeable
survivable impact events. To demonstrate this, Boeing would have to
evaluate the impact response characteristics of the 787 to ensure that
its crashworthiness characteristics are not significantly different
from those of a similarly sized airplane fabricated from traditionally
used metals. If the evaluation shows that the 787 impact response
characteristics are significantly different, Boeing would have to make
design changes to bring the different impact response characteristics
in line with those of a similarly sized metal construction airplane, or
incorporate mitigating design features.
Factors in crash survivability are retention of items of mass,
maintenance of occupant emergency egress paths, maintenance of
acceptable acceleration and loads experienced by the occupants, and
maintenance of a survivable volume. In reviewing available data from
accidents, tests simulating crash conditions, and analytical modeling
of a range of crash conditions, the FAA has concluded that the airplane
performance should be evaluated over a range of airplane level vertical
impact velocities up to 30 ft/sec.
If the 787 impact characteristics differ significantly from those
of a previously certificated wide body transport, this would result in
a need to meet load factors higher than those defined in 14 CFR 25.561
in order to maintain the same level of safety for the occupants, in
terms of retention of items of mass. In the cases of acceleration and
loads experienced by the occupants, means would have to be incorporated
to reduce load levels experienced by those occupants to the injury
criteria levels of Sec. 25.562, or load levels of a previously
certificated comparable airplane, in order to maintain the same level
of safety for the occupants.
Applicability
As discussed above, these proposed special conditions are
applicable to the 787 airplane. Should Boeing apply at a later date for
a change to the type certificate to include another model incorporating
the same novel or unusual design features, these proposed special
conditions would apply to that model as well under the provisions of
Sec. 21.101.
Conclusion
This action affects only certain novel or unusual design features
of the 787 airplane. It is not a rule of general applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping
requirements.
The authority citation for these Special Conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704.
The Proposed Special Conditions
Accordingly, the Administrator of the Federal Aviation
Administration (FAA) proposes the following special conditions as part
of the type certification basis for the Boeing Model 787-8 airplane.
The Boeing Model 787-8 must provide an equivalent level of occupant
safety and survivability to that provided by previously certificated
wide-body transports of similar size under foreseeable survivable
impact events for the following four criteria. In order to demonstrate
an equivalent level of occupant safety and survivability, the applicant
must demonstrate that the Model 787-8 meets the following criteria for
a range of airplane vertical descent velocities up to 30 ft/sec.
1. Retention of items of mass. The occupants, i.e., passengers,
flight attendants and flightcrew, must be protected during the impact
event from release of seats, overhead bins, and other items of mass due
to the impact loads and resultant structural deformation of the
supporting airframe and floor structures. The applicant must show that
loads due to the impact event and resultant structural deformation of
the supporting airframe and floor structure at the interface of the
airplane structure to seats, overhead bins, and other items of mass are
comparable to those of previously certificated wide-body transports of
similar size for the range of descent velocities stated above. The
attachments of these items need not be designed for static emergency
landing loads in excess of those defined in Sec. 25.561 if impact
response characteristics of the Boeing Model 787-8 yield load factors
at the attach points that are comparable to those for a previously
certificated wide-body transport category airplane.
2. Maintenance of acceptable acceleration and loads experienced by
the occupants. The applicant must show that the impact response
characteristics of the 787, specifically the vertical acceleration
levels experienced at the seat/floor interface and loads experienced by
the occupants during the impact events, are consistent with those found
in Sec. 25.562(b) or with levels expected for a previously
certificated wide-body transport category airplane for the conditions
stated above.
3. Maintenance of a survivable volume. For the conditions stated
above, the applicant must show that all areas of the airplane occupied
for takeoff and landing provide a survivable volume comparable to that
of previously certificated wide-body transports of similar size during
and after the impact event. This means that structural deformation will
not result in infringement of the occupants' normal living space so
that passenger survivability will not be significantly affected.
4. Maintenance of occupant emergency egress paths. The evacuation
of occupants must be comparable to that from a previously certificated
wide-body transport of similar size. To show this, the applicant must
show that the suitability of the egress paths, as determined following
the vertical impact events, is comparable to the suitability of the
egress paths of a comparable, certificated wide-body transport, as
determined following the same vertical impact events.
Issued in Renton, Washington, on May 31, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-11153 Filed 6-8-07; 8:45 am]
BILLING CODE 4910-13-P