Special Conditions: Bombardier Aerospace, Models BD-500-1A10 and BD-500-1A11 Series Airplanes; Flight Envelope Protection: General Limiting Requirements, 32637-32639 [2014-13242]
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Federal Register / Vol. 79, No. 109 / Friday, June 6, 2014 / Rules and Regulations
The normal load factor limit on the
CSeries airplanes is unique in that
traditional airplanes with conventional
flight control systems (mechanical
linkages) are limited in the pitch axis
only by the elevator surface area and
deflection limit. The elevator control
power is normally derived for adequate
controllability and maneuverability at
the most critical longitudinal pitching
moment. The result is that traditional
airplanes have a significant portion of
the flight envelope wherein
maneuverability in excess of limit
structural design values is possible.
These special conditions for the
CSeries airplanes supplement the
applicable regulations, including
§ 25.143, to accommodate the unique
features of the flight envelope limiting
systems, and establish an equivalent
level of safety to the existing
regulations.
Discussion of Comments
Notice of proposed special conditions
No. 25–13–38–SC for the Bombardier
CSeries airplanes was published in the
Federal Register on December 11, 2013
(78 FR 75285). 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.
mstockstill on DSK4VPTVN1PROD with RULES
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.
VerDate Mar<15>2010
13:35 Jun 05, 2014
Jkt 232001
Flight Envelope Protection: Normal
Load Factor (g) Limiting
1. To meet the intent of adequate
maneuverability and controllability
required by § 25.143(a), and in addition
to the requirements of § 25.143(a) and in
the absence of other limiting factors, the
following special conditions based on
§ 25.333(b) apply:
a. The positive limiting load factor
must not be less than:
(1) 2.5g for the normal state of the
electronic flight control system with the
high lift devices retracted.
(2) 2.0g for the normal state of the
electronic flight control system with the
high lift devices extended.
b. The negative limiting load factor
must be equal to or more negative than:
(1) Minus 1.0g for the normal state of
the electronic flight control system with
the high lift devices retracted.
(2) 0.0g for the normal state of the
electronic flight control system with
high lift devices extended.
c. Maximum reachable positive load
factor wings level may be limited by the
characteristics of the electronic flight
control system or flight envelope
protections (other than load factor
protection) provided that:
(1) The required values are readily
achievable in turns, and
(2) That wings level pitch up is
satisfactory.
d. Maximum achievable negative load
factor may be limited by the
characteristics of the electronic flight
control system or flight envelope
protections (other than load factor
protection) provided that:
(1) Pitch down responsiveness is
satisfactory, and
(2) From level flight, 0g is readily
achievable or alternatively, a
satisfactory trajectory change is readily
achievable at operational speeds. For
the FAA to consider a trajectory change
as satisfactory, the applicant should
propose and justify a pitch rate that
provides sufficient maneuvering
capability in the most critical scenarios.
e. Compliance demonstration with the
above requirements may be performed
without ice accretion on the airframe.
These special conditions do not
impose an upper bound for the normal
load factor limit, nor do they require
that the limit exist. If the limit is set at
a value beyond the structural design
limit maneuvering load factor ‘‘n’’ of
§§ 25.333(b) and 25.337(b) and (c), there
should be a very obvious positive tactile
feel built into the controller so that it
serves as a deterrent to inadvertently
exceeding the structural limit.
■
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32637
Issued in Renton, Washington, on April 22,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–13241 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–2013–1040; Notice No. 25–
548–SC]
Special Conditions: Bombardier
Aerospace, Models BD–500–1A10 and
BD–500–1A11 Series Airplanes; Flight
Envelope Protection: General Limiting
Requirements
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 a new control
architecture and a full digital flight
control system that provides flight
envelope protections. 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 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:
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
E:\FR\FM\06JNR1.SGM
06JNR1
32638
Federal Register / Vol. 79, No. 109 / Friday, June 6, 2014 / Rules and Regulations
Model BD–500–1A10 and 144,000
pounds for the Model BD–500–1A11.
Bombardier has developed
comprehensive flight envelope
protection features integral to the
CSeries electronic flight control system
(EFCS) design. These flight envelope
protection features include limitations
on angle-of-attack, normal load factor,
bank angle, pitch angle, and speed. To
accomplish this flight envelope limiting,
a significant change (or multiple
changes) occurs in the EFCS control
laws as the limit is approached or
exceeded. When EFCS failure states
occur, flight envelope protection
features can likewise either be modified,
or in some cases, eliminated. The
current regulations were not written
with these comprehensive flight
envelope limiting systems in mind.
mstockstill on DSK4VPTVN1PROD with RULES
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
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).
provides comprehensive flight envelope
protections.
Discussion
The applicable airworthiness
regulation is 14 CFR 25.143. The
purpose of § 25.143 is to verify that any
operational maneuvers conducted
within the operational envelope can be
accomplished smoothly with average
piloting skill and without exceeding any
structural limits. The pilot should be
able to predict the airplane response to
any control input. During the course of
the flight test program, the pilot
determines compliance with § 25.143
primarily through qualitative methods.
During flight test, the pilot should
evaluate all of the following:
• The interface between each
protection function;
• Transitions from one mode to
another;
• Airplane response to intentional
dynamic maneuvering, whenever
applicable, through dedicated
maneuvers;
• General controllability assessment;
• High speed characteristics; and
• High angle-of-attack.
Section 25.143, however, does not
adequately ensure that the novel or
unusual features of the CSeries
airplanes will have a level of safety
equivalent to that of existing standards.
These special conditions are therefore
required to accommodate the flight
envelope limiting systems in the CSeries
airplanes. The additional safety
standards in these special conditions
will ensure a level of safety equivalent
to that of existing standards.
Discussion of Comments
Notice of proposed special conditions
No. 25–13–39–SC for the Bombardier
CSeries airplanes was published in the
Federal Register on December 11, 2013
(78 FR 75287). 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.
Novel or Unusual Design Features
Conclusion
The CSeries airplanes will incorporate
the following novel or unusual design
features: New control architecture and a
full digital flight control system that
This action affects only certain novel
or unusual design features on two
model series of airplanes. It is not a rule
of general applicability.
VerDate Mar<15>2010
13:35 Jun 05, 2014
Jkt 232001
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
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.
1. General Limiting Requirements:
a. Onset characteristics of each
envelope protection feature must be
smooth, appropriate to the phase of
flight and type of maneuver, and not in
conflict with the ability of the pilot to
satisfactorily change airplane flight
path, speed, or attitude as needed.
b. Limit values of protected flight
parameters (and, if applicable,
associated warning thresholds) must be
compatible with the following:
i. Airplane structural limits;
ii. Required safe and controllable
maneuvering of the airplane; and
iii. Margins to critical conditions.
Unsafe flight characteristics/conditions
must not result if dynamic
maneuvering, airframe and system
tolerances (both manufacturing and inservice), and non-steady atmospheric
conditions, in any appropriate
combination and phase of flight, can
produce a limited flight parameter
beyond the nominal design limit value.
c. The airplane must be responsive to
intentional dynamic maneuvering to
within a suitable range of the parameter
limit. Dynamic characteristics such as
damping and overshoot must also be
appropriate for the flight maneuver and
limit parameter in question.
d. When simultaneous envelope
limiting is engaged, adverse coupling or
adverse priority must not result.
2. Failure States: Electronic flight
control system failures (including
sensor) must not result in a condition
where a parameter is limited to such a
reduced value that safe and controllable
maneuvering is no longer available. The
crew must be alerted by suitable means
if any change in envelope limiting or
maneuverability is produced by single
or multiple failures of the electronic
flight control system not shown to be
extremely improbable.
E:\FR\FM\06JNR1.SGM
06JNR1
Federal Register / Vol. 79, No. 109 / Friday, June 6, 2014 / Rules and Regulations
Issued in Renton, Washington, April 22,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–13242 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–2013–1038; Special
Conditions No. 25–549–SC]
Special Conditions: Bombardier
Aerospace, Models BD–500–1A10 and
BD–500–1A11 Series Airplanes; Flight
Envelope Protection: High-Speed
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 contains flyby-wire control laws, including
envelope protections, for the overspeed
protection and roll-limiting function.
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 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:
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
VerDate Mar<15>2010
13:35 Jun 05, 2014
Jkt 232001
takeoff weight is 131,000 pounds for the
Model BD–500–1A10 and 144,000
pounds for the Model BD–500–1A11.
The longitudinal control law design of
the Bombardier CSeries airplanes
incorporates an overspeed protection
system in the normal mode. This mode
prevents the pilot from inadvertently or
intentionally exceeding a speed
approximately equivalent to the
maximum speed for stability
characteristics (VFC) or attaining
demonstrated flight diving speed (VDF).
Current Title 14, Code of Federal
Regulations (14 CFR) part 25 standards
did not envision a high-speed limiter
that might preclude or modify flying
qualities assessments in the overspeed
region.
Type Certification Basis
Under the provisions of 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
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: An electronic flight control
system that contains fly-by-wire control
laws, including envelope protections,
for the overspeed protection and rolllimiting function. Current part 25
requirements do not contain appropriate
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
32639
standards for high-speed protection
systems.
Discussion
The overspeed protection
functionality includes multifunction
spoilers (MFS) that will automatically
deploy as speed brakes once the
airspeed exceeds a small tolerance
above maximum operating limit speed
(Vmo/Mmo); the MFS will retract
automatically when speed is
subsequently reduced. Special
conditions are necessary in addition to
the requirements of § 25.143 for the
operation of the high-speed protection.
The general intent is that the overspeed
protection does not impede normal
maneuvering and speed control, and
that the overspeed protection does not
restrict or prevent emergency
maneuvering.
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.
Discussion of Comments
Notice of proposed special conditions
No. 25–13–38–SC for the Bombardier
CSeries airplanes was published in the
Federal Register on December 11, 2013
(78 FR 75284). We received one
comment in favor of the proposed
special conditions as written.
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
E:\FR\FM\06JNR1.SGM
06JNR1
]]>Agencies
[Federal Register Volume 79, Number 109 (Friday, June 6, 2014)]
[Rules and Regulations]
[Pages 32637-32639]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-13242]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 25
[Docket No. FAA-2013-1040; Notice No. 25-548-SC]
Special Conditions: Bombardier Aerospace, Models BD-500-1A10 and
BD-500-1A11 Series Airplanes; Flight Envelope Protection: General
Limiting Requirements
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 a
new control architecture and a full digital flight control system that
provides flight envelope protections. 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 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:
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
[[Page 32638]]
Model BD-500-1A10 and 144,000 pounds for the Model BD-500-1A11.
Bombardier has developed comprehensive flight envelope protection
features integral to the CSeries electronic flight control system
(EFCS) design. These flight envelope protection features include
limitations on angle-of-attack, normal load factor, bank angle, pitch
angle, and speed. To accomplish this flight envelope limiting, a
significant change (or multiple changes) occurs in the EFCS control
laws as the limit is approached or exceeded. When EFCS failure states
occur, flight envelope protection features can likewise either be
modified, or in some cases, eliminated. The current regulations were
not written with these comprehensive flight envelope limiting systems
in mind.
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 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: New control architecture and a full digital
flight control system that provides comprehensive flight envelope
protections.
Discussion
The applicable airworthiness regulation is 14 CFR 25.143. The
purpose of Sec. 25.143 is to verify that any operational maneuvers
conducted within the operational envelope can be accomplished smoothly
with average piloting skill and without exceeding any structural
limits. The pilot should be able to predict the airplane response to
any control input. During the course of the flight test program, the
pilot determines compliance with Sec. 25.143 primarily through
qualitative methods. During flight test, the pilot should evaluate all
of the following:
The interface between each protection function;
Transitions from one mode to another;
Airplane response to intentional dynamic maneuvering,
whenever applicable, through dedicated maneuvers;
General controllability assessment;
High speed characteristics; and
High angle-of-attack.
Section 25.143, however, does not adequately ensure that the novel
or unusual features of the CSeries airplanes will have a level of
safety equivalent to that of existing standards. These special
conditions are therefore required to accommodate the flight envelope
limiting systems in the CSeries airplanes. The additional safety
standards in these special conditions will ensure a level of safety
equivalent to that of existing standards.
Discussion of Comments
Notice of proposed special conditions No. 25-13-39-SC for the
Bombardier CSeries airplanes was published in the Federal Register on
December 11, 2013 (78 FR 75287). 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.
1. General Limiting Requirements:
a. Onset characteristics of each envelope protection feature must
be smooth, appropriate to the phase of flight and type of maneuver, and
not in conflict with the ability of the pilot to satisfactorily change
airplane flight path, speed, or attitude as needed.
b. Limit values of protected flight parameters (and, if applicable,
associated warning thresholds) must be compatible with the following:
i. Airplane structural limits;
ii. Required safe and controllable maneuvering of the airplane; and
iii. Margins to critical conditions. Unsafe flight characteristics/
conditions must not result if dynamic maneuvering, airframe and system
tolerances (both manufacturing and in-service), and non-steady
atmospheric conditions, in any appropriate combination and phase of
flight, can produce a limited flight parameter beyond the nominal
design limit value.
c. The airplane must be responsive to intentional dynamic
maneuvering to within a suitable range of the parameter limit. Dynamic
characteristics such as damping and overshoot must also be appropriate
for the flight maneuver and limit parameter in question.
d. When simultaneous envelope limiting is engaged, adverse coupling
or adverse priority must not result.
2. Failure States: Electronic flight control system failures
(including sensor) must not result in a condition where a parameter is
limited to such a reduced value that safe and controllable maneuvering
is no longer available. The crew must be alerted by suitable means if
any change in envelope limiting or maneuverability is produced by
single or multiple failures of the electronic flight control system not
shown to be extremely improbable.
[[Page 32639]]
Issued in Renton, Washington, April 22, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-13242 Filed 6-5-14; 8:45 am]
BILLING CODE 4910-13-P
