Special Conditions: Airbus Model A380-800 Airplane, Transient Engine Failure Loads, 61869-61871 [E6-17534]
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61869
Rules and Regulations
Federal Register
Vol. 71, No. 203
Friday, October 20, 2006
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM322; Special Condition No.
25–333–SC]
Special Conditions: Airbus Model
A380–800 Airplane, Transient Engine
Failure Loads
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
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AGENCY:
SUMMARY: These special conditions are
issued for the Airbus A380–800
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. Some of these novel or
unusual design features are associated
with the high bypass engines used on
the Model A380. For these design
features, the applicable airworthiness
regulations do not contain adequate or
appropriate safety standards regarding
transient engine failure loads. 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 Airbus Model A380–800 airplane.
DATES: Effective Date: The effective date
of these special conditions is October 6,
2006.
FOR FURTHER INFORMATION CONTACT:
Holly Thorson, FAA, International
Branch, ANM–116, Transport Airplane
Directorate, Aircraft Certification
Service, 1601 Lind Avenue, SW.,
Renton, Washington 98055–4056;
telephone (425) 227–1357; facsimile
(425) 227–1149.
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SUPPLEMENTARY INFORMATION:
Background
Airbus applied for FAA certification/
validation of the provisionallydesignated Model A3XX–100 in its
letter AI/L 810.0223/98, dated August
12, 1998, to the FAA. Application for
certification by the Joint Aviation
Authorities (JAA) of Europe had been
made on January 16, 1998, reference AI/
L 810.0019/98. In its letter to the FAA,
Airbus requested an extension to the 5year period for type certification in
accordance with 14 CFR 21.17(c).
The request was for an extension to a
7-year period, using the date of the
initial application letter to the JAA as
the reference date. The reason given by
Airbus for the request for extension is
related to the technical challenge,
complexity, and the number of new and
novel features on the airplane. On
November 12, 1998, the Manager,
Aircraft Engineering Division, AIR–100,
granted Airbus’ request for the 7-year
period, based on the date of application
to the JAA.
In its letter AI/LE–A 828.0040/99
Issue 3, dated July 20, 2001, Airbus
stated that its target date for type
certification of the Model A380–800 had
been moved from May 2005, to January
2006, to match the delivery date of the
first production airplane. In a
subsequent letter (AI/L 810.0223/98
issue 3, dated January 27, 2006), Airbus
stated that its target date for type
certification is October 2, 2006. In
accordance with 14 CFR 21.17(d)(2),
Airbus chose a new application date of
December 20, 1999, and requested that
the 7-year certification period which
had already been approved be
continued. The FAA has reviewed the
part 25 certification basis for the Model
A380–800 airplane, and no changes are
required based on the new application
date.
The Model A380–800 airplane will be
an all-new, four-engine jet transport
airplane with a full-length double-deck,
two-aisle cabin. The maximum takeoff
weight will be 1.235 million pounds
with a typical three-class layout of 555
passengers.
Type Certification Basis
Under the provisions of 14 CFR 21.17,
Airbus must show that the Model A380–
800 airplane meets the applicable
provisions of 14 CFR part 25, as
amended by Amendments 25–1 through
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
25–98. If the Administrator finds that
the applicable airworthiness regulations
do not contain adequate or appropriate
safety standards for the Airbus A380–
800 airplane because of novel or
unusual design features, special
conditions are prescribed under the
provisions of 14 CFR 21.16.
In addition to the applicable
airworthiness regulations and special
conditions, the Airbus Model A380–800
airplane 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. In addition, the FAA must issue
a finding of regulatory adequacy
pursuant to section 611 of Public Law
93–574, the ‘‘Noise Control Act of
1972.’’
Special conditions, as defined in 14
CFR 11.19, are issued in accordance
with 14 CFR 11.38 and become part of
the type certification basis in
accordance with 14 CFR 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
under the provisions of 14 CFR 21.101.
Discussion of Novel or Unusual Design
Features
The Model A380 will have very large
high bypass ratio engines with 110 inch
diameter bypass fans, representing the
latest in a trend toward increasing
engine size. Engines of this size were
not envisioned when § 25.361—
pertaining to loads imposed by engine
seizure—was adopted in 1965. Worst
case engine seizure events become
increasingly more severe with
increasing engine size because of the
higher inertia of the rotating
components.
Section 25.361(b)(1) requires that for
turbine engine installations, the engine
mounts and the supporting structures
must be designed to withstand a ‘‘limit
engine torque load imposed by sudden
engine stoppage due to malfunction or
structural failure.’’ Limit loads are
expected to occur about once in the
lifetime of any airplane. Section 25.305
requires that supporting structures be
able to support limit loads without
detrimental permanent deformation,
meaning that the supporting structures
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Federal Register / Vol. 71, No. 203 / Friday, October 20, 2006 / Rules and Regulations
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should remain serviceable after a limit
load event.
Since the adoption of § 25.361(b)(1),
the size, configuration, and failure
modes of jet engines have changed
considerably. Current engines are much
larger and are designed with large
bypass fans. In the event of a structural
failure, these engines are capable of
producing much higher transient loads
on the engine mounts and supporting
structures.
As a result, modern high bypass
engines are subject to certain rare-butsevere engine seizure events. Service
history shows that such events occur far
less frequently than limit load events.
Although it is important for the airplane
to be able to support such rare loads
safely without failure, it is unrealistic to
expect that no permanent deformation
will occur.
Given this situation, the Aviation
Rulemaking Advisory Committee
(ARAC) 1 has proposed a design
standard for today’s large engines. For
the commonly-occurring deceleration
events, the proposed standard requires
engine mounts and structures to support
maximum torques without detrimental
permanent deformation. For the rarebut-severe engine seizure events (i.e.,
loss of any fan, compressor, or turbine
blade), the proposed standard requires
engine mounts and structures to support
maximum torques without failure, but
allows for some deformation in the
structure.
The FAA concludes that modern large
engines, including those on the Model
A380, are novel and unusual compared
to those envisioned when § 25.361(b)(1)
was adopted and thus warrant special
conditions. The special conditions
contain design criteria, as recommended
by the ARAC.
The ARAC proposal would revise the
wording of § 25.361(b), including
§§ 25.361(b)(1) and (b)(2), removing the
language pertaining to structural failures
and moving it to a separate requirement
that discusses the reduced factors of
safety that apply to these failures. The
revised wording of § 25.361(b) would
also include non-substantive changes
recommended by ARAC to clarify the
existing requirement. The FAA is using
this ARAC text in these special
conditions, because it clarifies the
supplementary conditions for engine
torque.
1 Industry members of the ARAC group included
Embraer, Dassault Aviation, Airbus, Gulfstream,
Lockheed Martin, Boeing, Cessna, Bombardier,
Raytheon, Rolls Royce, Pratt & Whitney, and
General Electric. In addition to the FAA, aviation
authorities included CAA-UK, Transport Canada,
DGAC-France, CTA-Brazil, and CAA-Netherlands.
VerDate Aug<31>2005
13:58 Oct 19, 2006
Jkt 211001
Discussion of Comments
Notice of Proposed Special
Conditions No. 25–05–17–SC,
pertaining to transient engine failure
loads, was published in the Federal
Register on August 9, 2005 (70 FR
46104). Comments were received from
the Boeing Company and the Airline
Pilots Association (ALPA).
Requested change 1: The Boeing
Company recommends that the
proposed special conditions be
withdrawn, for the following reasons:
(1) The engines on the Model A380
are not novel or unusual design features,
and
(2) The proposed special conditions
would provide a level of safety greater
than that established by the regulations,
rather than an equivalent level as safety,
as specified by § 21.16.
Specifically, Boeing states the
following:
‘‘These proposed Special Conditions
address transient engine loads resulting
from sudden engine stoppage, because
of the large size of the engines being
used on the Model A380. The FAA
references a report submitted by the
Aviation Rulemaking Advisory
Committee (ARAC) that addresses
design standards for large engines and
contains suggested associated regulatory
changes. The FAA has taken the ARACproposed regulations and has applied
them, essentially verbatim, to the Model
A380 as Special Conditions.
‘‘We consider this ‘general rulemaking
by Special Conditions.’ The engines on
the Model A380 are not novel or
unusual compared to other large engines
used on other large transports.
‘‘In addition, 14 CFR § 25.361 already
contains engine torque standards.
Section 21.16 enables the FAA to issue
special conditions ‘‘to establish a level
of safety equivalent to that established
in the regulations.’’ It does not authorize
the FAA to issue special conditions to
upgrade a level of safety already in the
regulations.
‘‘In sum, we believe the FAA has
failed to comply with two necessary
conditions for the issuance of a Special
Condition, and the proposal should be
withdrawn.’’
FAA response: The FAA does not
agree with this comment. The regulation
that specifies design criteria pertaining
to engine torque effects resulting from
sudden engine stoppage was developed
in 1957 (as Civil Aviation Regulations
(CAR) 4b.216(a)(4), Amendment 4b–6).
In 1964 the regulation was recodified as
14 CFR 25.361. The design criteria were
developed for turbojet and low by-pass
ratio turbofan engines.
The new large high-bypass ratio
turbofan engines being developed for
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Frm 00002
Fmt 4700
Sfmt 4700
the Model A380 have very large fans
that produce failure modes and torque
loads that were not envisioned when the
regulatory design criteria were
developed. The FAA has determined
that this new generation of large highbypass turbofan engines is sufficiently
different from engines envisioned in
1957 as to justify issuance of special
conditions to establish appropriate
design standards. The design standards
in these special conditions provide a
level of safety for large high by-pass
turbofan engines equivalent to that
which the current regulations provide
for turbojet or low-bypass ratio turbofan
engines.
The fact that the special conditions
consist of draft regulations proposed by
ARAC is not relevant to their suitability
or appropriateness in this circumstance.
The FAA considers the regulations
proposed by ARAC to be acceptable for
addressing the effects of sudden engine
torque for large high-bypass turbofan
engines and has issued similar special
conditions for other airplane models.
Section 21.16 requires the
Administrator to issue special
conditions in this circumstance and
does not restrict her from using
language contained in the ARACproposed regulations.
Requested change 2: The Airline
Pilots Association (ALPA) supports the
intent of the special conditions, as
proposed, but offers the following
comment:
‘‘The subject special condition does
not address potentially serious
aerodynamic effects resulting from a
total engine failure and seizure. Engine
seizure could introduce engine support
structure deformation that may
ultimately affect the aerodynamics of
the airframe. The special conditions
should require some sort of analysis to
ensure that any drag changes due to a
seized engine will not adversely affect
the support structures of the
aerodynamics such that safe operation
of the aircraft is degraded.’’
FAA response: The FAA agrees.
Although not specifically stated, it was
the intent of the proposed special
condition that the airplane be capable of
continued safe flight after the load
conditions specified in b.1.
Accordingly, the FAA has revised the
final special conditions to clarify this
point.
Applicability
As discussed above, these special
conditions are applicable to the Airbus
A380–800 airplane. Should Airbus
apply at a later date for a change to the
type certificate to include another
model incorporating the same novel or
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Federal Register / Vol. 71, No. 203 / Friday, October 20, 2006 / Rules and Regulations
unusual design features, these 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 Airbus
A380–800 airplane. It is not a rule of
general applicability.
Issued in Renton, Washington, on October
6, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E6–17534 Filed 10–19–06; 8:45 am]
BILLING CODE 4910–13–P
List of Subjects in 14 CFR Part 25
DEPARTMENT OF TRANSPORTATION
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
Federal Aviation Administration
14 CFR Part 71
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
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 Airbus A380–800 airplane.
a. In lieu of compliance with
§ 25.361(b), the following special
condition applies:
For turbine engine installations, the
engine mounts, pylons, and adjacent
supporting airframe structure must be
designed to withstand 1 g level flight
loads acting simultaneously with the
maximum limit torque loads imposed
by each of the following:
1. Sudden engine deceleration due to
a malfunction which could result in a
temporary loss of power or thrust; and
2. The maximum acceleration of the
engine.
b. In addition to the requirements of
14 CFR part 25, the following special
condition applies:
1. For engine supporting structure, an
ultimate loading condition must be
considered that combines 1 g flight
loads with the transient dynamic loads
resulting from:
(a) The loss of any fan, compressor, or
turbine blade; and
(b) Separately, where applicable to a
specific engine design, any other engine
structural failure that results in higher
loads.
2. The ultimate loads developed from
the conditions specified in paragraph
b.1. above are to be:
(a) Multiplied by a factor of 1.0 when
applied to engine mounts and pylons;
and
(b) Multiplied by a factor of 1.25
when applied to adjacent supporting
airframe structure.
3. The airplane must be capable of
continued safe flight considering the
aerodynamic effects on controllability
due to any permanent deformation that
results form the conditions specified in
b.1.
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Jkt 211001
[Docket No. FAA–2006–25069; Airspace
Docket No. 06–AWP–9]
RIN 2120–AA66
Modification of Class E Airspace;
Honolulu International Airport, HI
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This action modifies the Class
E airspace area at Honolulu
International Airport, HI. The
establishment of an Area Navigation
(RNAV) Required Navigation
Performance (RNP) Instrument
Approach Procedure (IAP) to Runway
(RWY) 08L and 26L to Honolulu
International Airport, Honolulu, HI has
made this action necessary. Additional
controlled airspace extending upward
from 700 feet or more above the surface
of the earth is needed to contain aircraft
executing this RNAV (RNP) IAP to RWY
08L and 26L to Honolulu International
Airport. The intended effect of this
action is to provide adequate controlled
airspace for Instrument Flight Rules
operations at Honolulu International
Airport, Honolulu, HI.
DATES: Effective Date: 0901 UTC January
18, 2007. The Director of the Federal
Register approves this incorporation by
reference action under title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.9 and publication of conforming
amendments.
The
Office of the Regional Western Terminal
Operations, Federal Aviation
Administration, at 15000 Aviation
Boulevard, Lawndale, California 90261,
telephone (310) 725–6502.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
History
On August 2, 2006, the FAA proposed
to amend 14 CFR part 71 by modifying
the Class E airspace area at Honolulu
International Airport (06 FR 43680).
Additional controlled airspace
extending upward from 700 feet or
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Frm 00003
Fmt 4700
Sfmt 4700
61871
move above the surface is needed to
contain aircraft executing the RNAV
(RNP) IAP RWY 08L and 26L to
Honolulu International Airport. This
action will provide adequate controlled
airspace for aircraft executing the RNAV
(RNP) IAP RWY 08L and 26L to
Honolulu International Airport,
Honolulu, HI.
Interested parties were invited to
participate in this rulemaking
proceeding by submitting written
comments on the proposal to the FAA.
No comments to the proposal were
received. Class E airspace designations
for airspace extending from 700 feet or
more above the surface of the earth are
published in paragraph 6005 of FAA
Order 7400.9P, dated September 1,
2006, and effective September 15, 2006,
which is incorporated by reference in 14
CFR 71.1. The Class E airspace
designation listed in this document will
be published subsequently in the Order.
The Rule
This amendment to 14 CFR part 71
modifies the Class E airspace area at
Honolulu International Airport, HI. The
establishment of a RNAV (RNP) IAP
RWY 08L and 26L to Honolulu
International Airport has made this
action necessary. The effect of this
action will provide adequate airspace
executing the RNAV (RNP) IAP RWY
08L and 26L to Honolulu International
Airport, Honolulu, HI.
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. Therefore, this regulation—(1)
Is not a ‘‘significant regulatory action’’
under Executive Order 12866; (2) is not
a ‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034; February 26, 1979); and (3)
does not warrant preparation of a
Regulation Evaluation as the anticipated
impact is so minimal. Since this is a
routine matter that will only affect air
traffic procedures and air navigation, it
is certified that this rule will not have
a significant economic impact on a
substantial number of a small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (air).
Adoption of the Amendment
In consideration of the foregoing, the
Federal Aviation Administration
amends 14 CFR part 71 as follows:
I
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Agencies
[Federal Register Volume 71, Number 203 (Friday, October 20, 2006)]
[Rules and Regulations]
[Pages 61869-61871]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17534]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 71, No. 203 / Friday, October 20, 2006 /
Rules and Regulations
[[Page 61869]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. NM322; Special Condition No. 25-333-SC]
Special Conditions: Airbus Model A380-800 Airplane, Transient
Engine Failure Loads
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Airbus A380-800
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. Some of these novel or
unusual design features are associated with the high bypass engines
used on the Model A380. For these design features, the applicable
airworthiness regulations do not contain adequate or appropriate safety
standards regarding transient engine failure loads. 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 Airbus Model A380-800 airplane.
DATES: Effective Date: The effective date of these special conditions
is October 6, 2006.
FOR FURTHER INFORMATION CONTACT: Holly Thorson, FAA, International
Branch, ANM-116, Transport Airplane Directorate, Aircraft Certification
Service, 1601 Lind Avenue, SW., Renton, Washington 98055-4056;
telephone (425) 227-1357; facsimile (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Background
Airbus applied for FAA certification/validation of the
provisionally-designated Model A3XX-100 in its letter AI/L 810.0223/98,
dated August 12, 1998, to the FAA. Application for certification by the
Joint Aviation Authorities (JAA) of Europe had been made on January 16,
1998, reference AI/L 810.0019/98. In its letter to the FAA, Airbus
requested an extension to the 5-year period for type certification in
accordance with 14 CFR 21.17(c).
The request was for an extension to a 7-year period, using the date
of the initial application letter to the JAA as the reference date. The
reason given by Airbus for the request for extension is related to the
technical challenge, complexity, and the number of new and novel
features on the airplane. On November 12, 1998, the Manager, Aircraft
Engineering Division, AIR-100, granted Airbus' request for the 7-year
period, based on the date of application to the JAA.
In its letter AI/LE-A 828.0040/99 Issue 3, dated July 20, 2001,
Airbus stated that its target date for type certification of the Model
A380-800 had been moved from May 2005, to January 2006, to match the
delivery date of the first production airplane. In a subsequent letter
(AI/L 810.0223/98 issue 3, dated January 27, 2006), Airbus stated that
its target date for type certification is October 2, 2006. In
accordance with 14 CFR 21.17(d)(2), Airbus chose a new application date
of December 20, 1999, and requested that the 7-year certification
period which had already been approved be continued. The FAA has
reviewed the part 25 certification basis for the Model A380-800
airplane, and no changes are required based on the new application
date.
The Model A380-800 airplane will be an all-new, four-engine jet
transport airplane with a full-length double-deck, two-aisle cabin. The
maximum takeoff weight will be 1.235 million pounds with a typical
three-class layout of 555 passengers.
Type Certification Basis
Under the provisions of 14 CFR 21.17, Airbus must show that the
Model A380-800 airplane meets the applicable provisions of 14 CFR part
25, as amended by Amendments 25-1 through 25-98. If the Administrator
finds that the applicable airworthiness regulations do not contain
adequate or appropriate safety standards for the Airbus A380-800
airplane because of novel or unusual design features, special
conditions are prescribed under the provisions of 14 CFR 21.16.
In addition to the applicable airworthiness regulations and special
conditions, the Airbus Model A380-800 airplane 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. In addition, the
FAA must issue a finding of regulatory adequacy pursuant to section 611
of Public Law 93-574, the ``Noise Control Act of 1972.''
Special conditions, as defined in 14 CFR 11.19, are issued in
accordance with 14 CFR 11.38 and become part of the type certification
basis in accordance with 14 CFR 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 under the provisions of 14 CFR 21.101.
Discussion of Novel or Unusual Design Features
The Model A380 will have very large high bypass ratio engines with
110 inch diameter bypass fans, representing the latest in a trend
toward increasing engine size. Engines of this size were not envisioned
when Sec. 25.361--pertaining to loads imposed by engine seizure--was
adopted in 1965. Worst case engine seizure events become increasingly
more severe with increasing engine size because of the higher inertia
of the rotating components.
Section 25.361(b)(1) requires that for turbine engine
installations, the engine mounts and the supporting structures must be
designed to withstand a ``limit engine torque load imposed by sudden
engine stoppage due to malfunction or structural failure.'' Limit loads
are expected to occur about once in the lifetime of any airplane.
Section 25.305 requires that supporting structures be able to support
limit loads without detrimental permanent deformation, meaning that the
supporting structures
[[Page 61870]]
should remain serviceable after a limit load event.
Since the adoption of Sec. 25.361(b)(1), the size, configuration,
and failure modes of jet engines have changed considerably. Current
engines are much larger and are designed with large bypass fans. In the
event of a structural failure, these engines are capable of producing
much higher transient loads on the engine mounts and supporting
structures.
As a result, modern high bypass engines are subject to certain
rare-but-severe engine seizure events. Service history shows that such
events occur far less frequently than limit load events. Although it is
important for the airplane to be able to support such rare loads safely
without failure, it is unrealistic to expect that no permanent
deformation will occur.
Given this situation, the Aviation Rulemaking Advisory Committee
(ARAC) \1\ has proposed a design standard for today's large engines.
For the commonly-occurring deceleration events, the proposed standard
requires engine mounts and structures to support maximum torques
without detrimental permanent deformation. For the rare-but-severe
engine seizure events (i.e., loss of any fan, compressor, or turbine
blade), the proposed standard requires engine mounts and structures to
support maximum torques without failure, but allows for some
deformation in the structure.
---------------------------------------------------------------------------
\1\ Industry members of the ARAC group included Embraer,
Dassault Aviation, Airbus, Gulfstream, Lockheed Martin, Boeing,
Cessna, Bombardier, Raytheon, Rolls Royce, Pratt & Whitney, and
General Electric. In addition to the FAA, aviation authorities
included CAA-UK, Transport Canada, DGAC-France, CTA-Brazil, and CAA-
Netherlands.
---------------------------------------------------------------------------
The FAA concludes that modern large engines, including those on the
Model A380, are novel and unusual compared to those envisioned when
Sec. 25.361(b)(1) was adopted and thus warrant special conditions. The
special conditions contain design criteria, as recommended by the ARAC.
The ARAC proposal would revise the wording of Sec. 25.361(b),
including Sec. Sec. 25.361(b)(1) and (b)(2), removing the language
pertaining to structural failures and moving it to a separate
requirement that discusses the reduced factors of safety that apply to
these failures. The revised wording of Sec. 25.361(b) would also
include non-substantive changes recommended by ARAC to clarify the
existing requirement. The FAA is using this ARAC text in these special
conditions, because it clarifies the supplementary conditions for
engine torque.
Discussion of Comments
Notice of Proposed Special Conditions No. 25-05-17-SC, pertaining
to transient engine failure loads, was published in the Federal
Register on August 9, 2005 (70 FR 46104). Comments were received from
the Boeing Company and the Airline Pilots Association (ALPA).
Requested change 1: The Boeing Company recommends that the proposed
special conditions be withdrawn, for the following reasons:
(1) The engines on the Model A380 are not novel or unusual design
features, and
(2) The proposed special conditions would provide a level of safety
greater than that established by the regulations, rather than an
equivalent level as safety, as specified by Sec. 21.16.
Specifically, Boeing states the following:
``These proposed Special Conditions address transient engine loads
resulting from sudden engine stoppage, because of the large size of the
engines being used on the Model A380. The FAA references a report
submitted by the Aviation Rulemaking Advisory Committee (ARAC) that
addresses design standards for large engines and contains suggested
associated regulatory changes. The FAA has taken the ARAC-proposed
regulations and has applied them, essentially verbatim, to the Model
A380 as Special Conditions.
``We consider this `general rulemaking by Special Conditions.' The
engines on the Model A380 are not novel or unusual compared to other
large engines used on other large transports.
``In addition, 14 CFR Sec. 25.361 already contains engine torque
standards. Section 21.16 enables the FAA to issue special conditions
``to establish a level of safety equivalent to that established in the
regulations.'' It does not authorize the FAA to issue special
conditions to upgrade a level of safety already in the regulations.
``In sum, we believe the FAA has failed to comply with two
necessary conditions for the issuance of a Special Condition, and the
proposal should be withdrawn.''
FAA response: The FAA does not agree with this comment. The
regulation that specifies design criteria pertaining to engine torque
effects resulting from sudden engine stoppage was developed in 1957 (as
Civil Aviation Regulations (CAR) 4b.216(a)(4), Amendment 4b-6). In 1964
the regulation was recodified as 14 CFR 25.361. The design criteria
were developed for turbojet and low by-pass ratio turbofan engines.
The new large high-bypass ratio turbofan engines being developed
for the Model A380 have very large fans that produce failure modes and
torque loads that were not envisioned when the regulatory design
criteria were developed. The FAA has determined that this new
generation of large high-bypass turbofan engines is sufficiently
different from engines envisioned in 1957 as to justify issuance of
special conditions to establish appropriate design standards. The
design standards in these special conditions provide a level of safety
for large high by-pass turbofan engines equivalent to that which the
current regulations provide for turbojet or low-bypass ratio turbofan
engines.
The fact that the special conditions consist of draft regulations
proposed by ARAC is not relevant to their suitability or
appropriateness in this circumstance. The FAA considers the regulations
proposed by ARAC to be acceptable for addressing the effects of sudden
engine torque for large high-bypass turbofan engines and has issued
similar special conditions for other airplane models. Section 21.16
requires the Administrator to issue special conditions in this
circumstance and does not restrict her from using language contained in
the ARAC-proposed regulations.
Requested change 2: The Airline Pilots Association (ALPA) supports
the intent of the special conditions, as proposed, but offers the
following comment:
``The subject special condition does not address potentially
serious aerodynamic effects resulting from a total engine failure and
seizure. Engine seizure could introduce engine support structure
deformation that may ultimately affect the aerodynamics of the
airframe. The special conditions should require some sort of analysis
to ensure that any drag changes due to a seized engine will not
adversely affect the support structures of the aerodynamics such that
safe operation of the aircraft is degraded.''
FAA response: The FAA agrees. Although not specifically stated, it
was the intent of the proposed special condition that the airplane be
capable of continued safe flight after the load conditions specified in
b.1. Accordingly, the FAA has revised the final special conditions to
clarify this point.
Applicability
As discussed above, these special conditions are applicable to the
Airbus A380-800 airplane. Should Airbus apply at a later date for a
change to the type certificate to include another model incorporating
the same novel or
[[Page 61871]]
unusual design features, these 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 Airbus A380-800 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 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 Airbus A380-800 airplane.
a. In lieu of compliance with Sec. 25.361(b), the following
special condition applies:
For turbine engine installations, the engine mounts, pylons, and
adjacent supporting airframe structure must be designed to withstand 1
g level flight loads acting simultaneously with the maximum limit
torque loads imposed by each of the following:
1. Sudden engine deceleration due to a malfunction which could
result in a temporary loss of power or thrust; and
2. The maximum acceleration of the engine.
b. In addition to the requirements of 14 CFR part 25, the following
special condition applies:
1. For engine supporting structure, an ultimate loading condition
must be considered that combines 1 g flight loads with the transient
dynamic loads resulting from:
(a) The loss of any fan, compressor, or turbine blade; and
(b) Separately, where applicable to a specific engine design, any
other engine structural failure that results in higher loads.
2. The ultimate loads developed from the conditions specified in
paragraph b.1. above are to be:
(a) Multiplied by a factor of 1.0 when applied to engine mounts and
pylons; and
(b) Multiplied by a factor of 1.25 when applied to adjacent
supporting airframe structure.
3. The airplane must be capable of continued safe flight
considering the aerodynamic effects on controllability due to any
permanent deformation that results form the conditions specified in
b.1.
Issued in Renton, Washington, on October 6, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-17534 Filed 10-19-06; 8:45 am]
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