Special Conditions: Bombardier Aerospace, Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Electronic Flight Control System: Control Surface Awareness and Mode Annunciation, 32635-32636 [2014-13240]
Download as PDF
Federal Register / Vol. 79, No. 109 / Friday, June 6, 2014 / Rules and Regulations
Issued in Renton, Washington, on April 4,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–13239 Filed 6–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA–2013–1041; Notice No. 25–
546–SC]
Special Conditions: Bombardier
Aerospace, Models BD–500–1A10 and
BD–500–1A11 Series Airplanes;
Electronic Flight Control System:
Control Surface Awareness and Mode
Annunciation
Federal Aviation
Administration (FAA), DOT.
ACTION: Final Special Conditions.
AGENCY:
These special conditions are
issued for the Bombardier Aerospace
Models BD–500–1A10 and BD–500–
1A11 series airplanes. These airplanes
will have a novel or unusual design
feature associated with control surface
awareness and mode annunciation of
the electronic flight control system. 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: Effective Date: July 7, 2014.
FOR FURTHER INFORMATION CONTACT: Joe
Jacobsen, FAA, Airplane and Flightcrew
Interface Branch, ANM–111, Transport
Airplane Directorate, Aircraft
Certification Service, 1601 Lind Avenue
SW., Renton, Washington 98057–3356;
telephone 425–227–2011; facsimile
425–227–1149.
SUPPLEMENTARY INFORMATION:
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
Background
On December 10, 2009, Bombardier
Aerospace applied for a type certificate
for their new Models BD–500–1A10 and
BD–500–1A11 series airplanes (hereafter
collectively referred to as ‘‘CSeries’’).
The CSeries airplanes are swept-wing
monoplanes with an aluminum alloy
fuselage sized for 5-abreast seating.
Passenger capacity is designated as 110
for the Model BD–500–1A10 and 125 for
the Model BD–500–1A11. Maximum
takeoff weight is 131,000 pounds for the
VerDate Mar<15>2010
13:35 Jun 05, 2014
Jkt 232001
Model BD–500–1A10 and 144,000
pounds for the Model BD–500–1A11.
Type Certification Basis
Under the provisions of Title 14, Code
of Federal Regulations (14 CFR) 21.17,
Bombardier Aerospace must show that
the CSeries airplanes meet the
applicable provisions of 14 CFR part 25
as amended by Amendments 25–1
through 25–129 thereto.
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 CSeries airplanes 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 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 § 21.101.
In addition to the applicable
airworthiness regulations and special
conditions, the CSeries airplanes 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 under § 611 of Public Law 92–
574, the ‘‘Noise Control Act of 1972.’’
The FAA issues special conditions, as
defined in 14 CFR 11.19, in accordance
with § 11.38, and they become part of
the type-certification basis under
§ 21.17(a)(2).
Novel or Unusual Design Features
The CSeries airplanes will incorporate
the following novel or unusual design
features: A fly-by-wire electronic flight
control system (EFCS) and no direct
coupling from the flightdeck controller
to the control surface. As a result, the
pilot is not aware of the actual control
surface position as envisioned under
current airworthiness standards.
Discussion
These special conditions require that
the flightcrew receive a suitable flight
control position annunciation when a
flight condition exists in which nearly
full surface authority (not crewcommanded) is being used. Suitability
of such a display must take into account
that some pilot-demanded maneuvers
(e.g., rapid roll) are necessarily
associated with intended full
performance, which may saturate the
surface. Therefore, simple alerting
systems function in both intended and
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
32635
unexpected control-limiting situations.
As a result, they must be properly
balanced between providing necessary
crew awareness and being a potential
nuisance to the flightcrew. A monitoring
system that compares airplane motion
and surface deflection with the demand
of the pilot side stick controller could
help reduce nuisance alerting.
These special conditions also address
flight control system mode
annunciation. Suitable mode
annunciation must be provided to the
flightcrew for events that significantly
change the operating mode of the
system but do not merit the classic
‘‘failure warning.’’
These special conditions establish a
level of safety equivalent to that
provided by a conventional flight
control system and existing regulations.
Discussion of Comments
Notice of proposed special conditions
No. 25–13–40–SC for the Bombardier
CSeries airplanes was published in the
Federal Register on December 12, 2013
(78 FR 75511). No comments were
received, and the special conditions are
adopted as proposed.
Applicability
As discussed above, these special
conditions are applicable to the Models
BD–500–1A10 and BD–500–1A11 series
airplanes. Should Bombardier
Aerospace 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 two
model series of airplanes. 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
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 Bombardier
Aerospace Models BD–500–1A10 and
BD–500–1A11 series airplanes.
E:\FR\FM\06JNR1.SGM
06JNR1
32636
Federal Register / Vol. 79, No. 109 / Friday, June 6, 2014 / Rules and Regulations
Electronic Flight Control System:
Control Surface Awareness and Mode
Annunciation
1. In addition to the requirements of
§§ 25.143, 25.671, and 25.672, the
following requirements apply:
a. The system design must ensure that
the flightcrew is made suitably aware
whenever the primary control means
nears the limit of control authority.
■
Note: The term ‘‘suitably aware’’ indicates
annunciations provided to the flightcrew are
appropriately balanced between nuisance
and that necessary for crew awareness.
b. If the design of the flight control
system has multiple modes of operation,
a means must be provided to indicate to
the flightcrew any mode that
significantly changes or degrades the
normal handling or operational
characteristics of the airplane.
Issued in Renton, Washington, on April 22,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–13240 Filed 6–5–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA–2013–1039; Notice No. 25–
547–SC]
Special Conditions: Bombardier
Aerospace, Models BD–500–1A10 and
BD–500–1A11 Series Airplanes; Flight
Envelope Protection: Normal Load
Factor (g) Limiting
Federal Aviation
Administration (FAA), DOT.
ACTION: Final Special Conditions.
AGENCY:
These special conditions are
issued for the Bombardier Aerospace
Models BD–500–1A10 and BD–500–
1A11 series airplanes. These airplanes
will have a novel or unusual design
feature associated with an electronic
flight control system that prevents the
pilot from inadvertently or intentionally
exceeding the positive or negative
airplane limit load factor. 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: Effective Date: July 7, 2014.
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
13:35 Jun 05, 2014
Jkt 232001
FOR FURTHER INFORMATION CONTACT:
Joe
Jacobsen, FAA, Airplane and Flight
Crew Interface Branch, ANM–111,
Transport Airplane Directorate, Aircraft
Certification Service, 1601 Lind Avenue
SW., Renton, Washington 98057–3356;
telephone 425–227–2011; facsimile
425–227–1149.
SUPPLEMENTARY INFORMATION:
requirements of 14 CFR part 36, and the
FAA must issue a finding of regulatory
adequacy under § 611 of Public Law 92–
574, the ‘‘Noise Control Act of 1972.’’
The FAA issues special conditions, as
defined in 14 CFR 11.19, in accordance
with § 11.38, and they become part of
the type-certification basis under
§ 21.17(a)(2).
Background
On December 10, 2009, Bombardier
Aerospace applied for a type certificate
for their new Models BD–500–1A10 and
BD–500–1A11 series airplanes (hereafter
collectively referred to as ‘‘CSeries’’).
The CSeries airplanes are swept-wing
monoplanes with an aluminum alloy
fuselage sized for 5-abreast seating.
Passenger capacity is designated as 110
for the Model BD–500–1A10 and 125 for
the Model BD–500–1A11. Maximum
takeoff weight is 131,000 pounds for the
Model BD–500–1A10 and 144,000
pounds for the Model BD–500–1A11.
The design of the electronic flight
control system for the CSeries airplanes
incorporates normal load factor limiting
on a full time basis that prevents the
flightcrew from inadvertently or
intentionally exceeding the positive or
negative airplane limit load factor. This
feature is considered novel and unusual
in that the current regulations do not
provide standards for maneuverability
and controllability evaluations for such
systems.
Novel or Unusual Design Features
Type Certification Basis
Under the provisions of Title 14, Code
of Federal Regulations (14 CFR) 21.17,
Bombardier Aerospace must show that
the CSeries airplanes meet the
applicable provisions of part 25 as
amended by Amendments 25–1 through
25–129 thereto.
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 CSeries airplanes 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 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 § 21.101.
In addition to the applicable
airworthiness regulations and special
conditions, the CSeries airplanes must
comply with the fuel vent and exhaust
emission requirements of 14 CFR part
34 and the noise certification
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
The CSeries airplanes will use a flyby-wire electronic flight control system
(EFCS). This system provides an
electronic interface between the pilot’s
flight controls and the flight control
surfaces for both normal and failure
states; and it generates the actual surface
commands that provide for stability
augmentation and control about all
three airplane axes.
The design of the EFCS incorporates
the following novel or unusual design
feature: Normal load factor limiting on
a full-time basis that will prevent the
flight crew from inadvertently or
intentionally exceeding the positive or
negative airplane limit load factor. This
feature is considered novel or unusual
because the current regulations do not
provide standards for maneuverability
and controllability evaluations for such
systems. Therefore, special conditions
are needed to ensure adequate
maneuverability and controllability
when using this design feature.
Discussion
Title 14, Code of Federal Regulations,
part 25 does not specify requirements or
policy for demonstrating maneuver
control that impose any handling
qualities requirements beyond the
design limit structural loads.
Nevertheless, some pilots have become
accustomed to the availability of this
excess maneuver capacity in case of
extreme emergency such as upset
recoveries or collision avoidance.
As with previous fly-by-wire
airplanes, the FAA has no regulatory or
safety reason to prohibit a design for an
electronic flight control system with
load factor limiting. It is possible that
pilots accustomed to this feature feel
more freedom in commanding full-stick
displacement maneuvers because of the
following:
• Knowledge that the limit system
will protect the structure,
• Low stick force/displacement
gradients,
• Smooth transition from pilot
elevator control to limit control.
These special conditions will ensure
adequate maneuverability and
controllability when using this design
feature.
E:\FR\FM\06JNR1.SGM
06JNR1
Agencies
[Federal Register Volume 79, Number 109 (Friday, June 6, 2014)]
[Rules and Regulations]
[Pages 32635-32636]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-13240]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2013-1041; Notice No. 25-546-SC]
Special Conditions: Bombardier Aerospace, Models BD-500-1A10 and
BD-500-1A11 Series Airplanes; Electronic Flight Control System: Control
Surface Awareness and Mode Annunciation
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final Special Conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the Bombardier
Aerospace Models BD-500-1A10 and BD-500-1A11 series airplanes. These
airplanes will have a novel or unusual design feature associated with
control surface awareness and mode annunciation of the electronic
flight control system. 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: Effective Date: July 7, 2014.
FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and
Flightcrew Interface Branch, ANM-111, Transport Airplane Directorate,
Aircraft Certification Service, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; telephone 425-227-2011; facsimile 425-227-1149.
SUPPLEMENTARY INFORMATION:
Background
On December 10, 2009, Bombardier Aerospace applied for a type
certificate for their new Models BD-500-1A10 and BD-500-1A11 series
airplanes (hereafter collectively referred to as ``CSeries''). The
CSeries airplanes are swept-wing monoplanes with an aluminum alloy
fuselage sized for 5-abreast seating. Passenger capacity is designated
as 110 for the Model BD-500-1A10 and 125 for the Model BD-500-1A11.
Maximum takeoff weight is 131,000 pounds for the Model BD-500-1A10 and
144,000 pounds for the Model BD-500-1A11.
Type Certification Basis
Under the provisions of Title 14, Code of Federal Regulations (14
CFR) 21.17, Bombardier Aerospace must show that the CSeries airplanes
meet the applicable provisions of 14 CFR part 25 as amended by
Amendments 25-1 through 25-129 thereto.
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 CSeries airplanes because of a
novel or unusual design feature, special conditions are prescribed
under the provisions of Sec. 21.16.
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 Sec. 21.101.
In addition to the applicable airworthiness regulations and special
conditions, the CSeries airplanes 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 under Sec. 611 of Public Law 92-574,
the ``Noise Control Act of 1972.''
The FAA issues special conditions, as defined in 14 CFR 11.19, in
accordance with Sec. 11.38, and they become part of the type-
certification basis under Sec. 21.17(a)(2).
Novel or Unusual Design Features
The CSeries airplanes will incorporate the following novel or
unusual design features: A fly-by-wire electronic flight control system
(EFCS) and no direct coupling from the flightdeck controller to the
control surface. As a result, the pilot is not aware of the actual
control surface position as envisioned under current airworthiness
standards.
Discussion
These special conditions require that the flightcrew receive a
suitable flight control position annunciation when a flight condition
exists in which nearly full surface authority (not crew-commanded) is
being used. Suitability of such a display must take into account that
some pilot-demanded maneuvers (e.g., rapid roll) are necessarily
associated with intended full performance, which may saturate the
surface. Therefore, simple alerting systems function in both intended
and unexpected control-limiting situations. As a result, they must be
properly balanced between providing necessary crew awareness and being
a potential nuisance to the flightcrew. A monitoring system that
compares airplane motion and surface deflection with the demand of the
pilot side stick controller could help reduce nuisance alerting.
These special conditions also address flight control system mode
annunciation. Suitable mode annunciation must be provided to the
flightcrew for events that significantly change the operating mode of
the system but do not merit the classic ``failure warning.''
These special conditions establish a level of safety equivalent to
that provided by a conventional flight control system and existing
regulations.
Discussion of Comments
Notice of proposed special conditions No. 25-13-40-SC for the
Bombardier CSeries airplanes was published in the Federal Register on
December 12, 2013 (78 FR 75511). No comments were received, and the
special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
Models BD-500-1A10 and BD-500-1A11 series airplanes. Should Bombardier
Aerospace 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 two model series of airplanes. 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
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 Bombardier Aerospace Models BD-
500-1A10 and BD-500-1A11 series airplanes.
[[Page 32636]]
Electronic Flight Control System: Control Surface Awareness and Mode
Annunciation
0
1. In addition to the requirements of Sec. Sec. 25.143, 25.671, and
25.672, the following requirements apply:
a. The system design must ensure that the flightcrew is made
suitably aware whenever the primary control means nears the limit of
control authority.
Note: The term ``suitably aware'' indicates annunciations
provided to the flightcrew are appropriately balanced between
nuisance and that necessary for crew awareness.
b. If the design of the flight control system has multiple modes of
operation, a means must be provided to indicate to the flightcrew any
mode that significantly changes or degrades the normal handling or
operational characteristics of the airplane.
Issued in Renton, Washington, on April 22, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-13240 Filed 6-5-14; 8:45 am]
BILLING CODE 4910-13-P