Special Conditions: Airbus Helicopters Model AS350B2 and AS350B3 Helicopters; Installation of Garmin International, Inc., Autopilot System, 15945-15946 [2018-07655]
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15945
Rules and Regulations
Federal Register
Vol. 83, No. 72
Friday, April 13, 2018
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 27
[Docket No.FAA–2017–1130; Notice No. 27–
043–SC]
Special Conditions: Airbus Helicopters
Model AS350B2 and AS350B3
Helicopters; Installation of Garmin
International, Inc., Autopilot System
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
These special conditions are
issued for Airbus Helicopters Model
AS350B2 and AS350B3 helicopters.
These helicopters as modified by
Garmin International, Inc., (Garmin)
will have a novel or unusual design
feature associated with the Garmin
Flight Control (GFC) 600H autopilot
with stability and control augmentation
system (AP/SCAS). 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: The effective date of these
special conditions is April 13, 2018.
FOR FURTHER INFORMATION CONTACT:
George Harrum, Aerospace Engineer,
FAA, Rotorcraft Standards Branch,
Policy and Innovations Division, 10101
Hillwood Pkwy., Fort Worth, TX 76177;
telephone (817) 222–4087; email
George.Harrum@faa.gov.
SUPPLEMENTARY INFORMATION:
daltland on DSKBBV9HB2PROD with RULES
SUMMARY:
Background
On October 10, 2016, Garmin applied
for a supplemental type certificate (STC)
to install a GFC 600H AP/SCAS in
Airbus Helicopters Model AS350B2 and
AS350B3 helicopters. The Model
AS350B2 and AS350B3 helicopters are
VerDate Sep<11>2014
16:22 Apr 12, 2018
Jkt 244001
14 CFR part 27 normal category, single
turbine engine, conventional helicopters
designed for civil operation. These
helicopter models are capable of
carrying up to five passengers with one
pilot and have a maximum gross weight
of up to 5,220 pounds, depending on the
model configuration. The major design
features include a 3-blade, fully
articulated main rotor, an anti-torque
tail rotor system, a skid landing gear,
and a visual flight rule basic avionics
configuration.
Garmin proposes to modify these
model helicopters by installing a SCAS
with autopilot functions in 2 or 3 axes,
depending on the number of servos
installed. The possible failure
conditions for this system, and their
effect on the continued safe flight and
landing of the helicopter, are more
severe than those envisioned by the
present rules. The present 14 CFR
27.1309(b) and (c) regulations do not
adequately address the safety
requirements for systems whose failures
could result in ‘‘catastrophic’’ or
‘‘hazardous/severe-major’’ failure
conditions, or for complex systems
whose failures could result in ‘‘major’’
failure conditions. When these rules
were promulgated, it was not
envisioned that a normal category
rotorcraft would use systems that are
complex or whose failure could result in
‘‘catastrophic’’ or ‘‘hazardous/severemajor’’ effects on the rotorcraft. This is
particularly true with the application of
new technology, new application of
standard technology, or other
applications not envisioned by the rule
that affect safety. The Garmin AP/SCAS
controls rotorcraft flight control
surfaces. Possible failure modes
exhibited by this system could result in
a catastrophic event.
Type Certification Basis
Under 14 CFR 21.101 and 21.115,
Garmin must show that the Airbus
Helicopters Model AS350B2 and
AS350B3 helicopters, as changed,
continue to meet the applicable
provisions of the regulations
incorporated by reference in Type
Certificate No. H9EU or the applicable
regulations in effect on the date of
application for the change. The
regulations incorporated by reference in
the type certificate are commonly
referred to as the ‘‘original type
certification basis.’’ The regulations
PO 00000
Frm 00001
Fmt 4700
Sfmt 4700
incorporated by reference in Type
Certificate No. H9EU are as follows:
14 CFR 21.29 and part 27 effective
February 1, 1965, plus Amendments 27–
1 through 27–10.
For aircraft incorporating mod.
OP3369 (2370 kg/5225 lb mass
extension), the following 14 CFR part 27
Amendments 27–1 through 27–40 are
replacing the same requirement from the
certification basis above: §§ 27.1; 27.21;
27.25; 27.27; 27.33; 27.45; 27.51; 27.65;
27.71; 27.73; 27.75; 27.79; 27.141;
27.143; 27.173; 27.175; 27.177; 27.241;
27.301; 27.303; 27.305; 27.307; 27.309;
27.321; 27.337; 27.339; 27.341; 27.351;
27.471; 27.473; 27.501; 27.505; 27.521;
27.547; 27.549; 27.563(b); 27.571;
27.602; 27.661; 27.663; 27.695; 27.723;
27.725; 27.727; 27.737; 27.751; 27.753;
27.801(b)(d); 27.927(c); 27.1041;
27.1043; 27.1045; 27.1301; 27.1501;
27.1519; 27.1529; 27.1581; 27.1583;
27.1585; 27.1587; 27.1589.
For AS350B3 aircraft incorporating
mod. OP–4605 (installation of a fuel
system improving crashworthiness), 14
CFR 27.561(c) at Amendment 27–32
replaces the same requirement from the
certification basis above for the
following elements of the fuel tank
lower structure affected by this
modification: cradles, longitudinal
beams, X-stops and rods.
Additionally, Garmin must comply
with the equivalent level of safety
findings, exemptions, and special
conditions prescribed by the
Administrator as part of the certification
basis.
The Administrator has determined the
applicable airworthiness regulations
(that is, 14 CFR part 27), as they pertain
to this STC, do not contain adequate or
appropriate safety standards for the
Airbus Helicopters Model AS350B2 and
AS350B3 helicopters because of a novel
or unusual design feature. Therefore, we
propose to prescribe these special
conditions under § 21.16.
Special conditions are initially
applicable to the model for which they
are issued. Should the applicant apply
for an STC to change any other model
included on the same type certificate to
incorporate 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, Garmin must show that the
E:\FR\FM\13APR1.SGM
13APR1
15946
Federal Register / Vol. 83, No. 72 / Friday, April 13, 2018 / Rules and Regulations
Airbus Helicopters Model AS350B2 and
AS350B3 helicopters, as changed,
comply with the noise certification
requirements of 14 CFR part 36.
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 § 21.101.
Novel or Unusual Design Features
The Airbus Helicopters Model
AS350B2 and AS350B3 helicopter
incorporates the following novel or
unusual design features: A GFC 600H
AP/SCAS. This GFC 600H AP/SCAS
performs non-critical control functions.
The GFC 600H AP/SCAS is a two or
three axis system with the following
novel functions: Limit cueing, level
mode, and hover assist.
daltland on DSKBBV9HB2PROD with RULES
Discussion
These special conditions clarify the
requirement to perform a proper failure
analysis and also recognizes that the
severity of failures can vary. Current
industry standards and practices
recognize five failure condition
categories: Catastrophic, Hazardous,
Major, Minor, and No-Safety Effect.
These special conditions address the
safety requirement for systems whose
failures could result in catastrophic or
hazardous/severe-major failure
conditions and for complex systems
whose failures could result in major
failure conditions.
To comply with the provisions of the
special conditions, we require that
Garmin provide the FAA with a systems
safety assessment (SSA) for the final
GFC 600H AP/SCAS installation
configuration that adequately address
the safety objectives established by a
functional hazard assessment (FHA) and
a preliminary system safety assessment
(PSSA), including the fault tree analysis
(FTA). This ensures that all failure
conditions and their resulting effects are
adequately addressed for the installed
GFC 600H AP/SCAS. The SSA process,
FHA, PSSA, and FTA are all parts of the
overall safety assessment process
discussed in FAA Advisory Circular 27–
1B, Certification of Normal Category
Rotorcraft, and Society of Automotive
Engineers document Aerospace
Recommended Practice 4761,
Guidelines and Methods for Conducting
the Safety Assessment Process on Civil
Airborne Systems and Equipment.
These special conditions require that
the GFC 600H AP/SCAS installed on
Airbus Helicopters Model AS350B2 and
Model AS350B3 helicopters meet the
requirements to adequately address the
failure effects identified by the FHA,
and subsequently verified by the SSA,
VerDate Sep<11>2014
16:22 Apr 12, 2018
Jkt 244001
within the defined design integrity
requirements.
Comments
No comments were received in
response to the Notice of proposed
special conditions No. 27–043–SC (82
FR 57685, December 7, 2017). The
closing date for comments was January
22, 2018. Accordingly, the special
conditions are adopted as proposed.
Applicability
(2) The occurrence of any hazardous
failure condition is extremely remote;
and
(3) The occurrence of any major
failure condition is remote.
(c) Information concerning an unsafe
system operating condition must be
provided in a timely manner to the crew
to enable them to take appropriate
corrective action. An appropriate alert
must be provided if immediate pilot
awareness and immediate or subsequent
corrective action is required. Systems
and controls, including indications and
annunciations, must be designed to
minimize crew errors which could
create additional hazards.
As discussed above, these special
conditions are applicable to Airbus
Helicopters Model AS350B2 and
AS350B3 helicopters. Should Garmin
apply at a later date for an STC to
modify any other model included on
Type Certificate Number H9EU to
incorporate the same novel or unusual
design feature, these special conditions
would apply to that model as well.
Issued in Fort Worth, Texas, on March 30,
2018.
Jorge Castillo,
Acting Manager, Rotorcraft Standards
Branch, Policy and Innovation Division
Aircraft Certification Service.
Conclusion
[FR Doc. 2018–07655 Filed 4–12–18; 8:45 am]
This action affects only certain novel
or unusual design features on two
model helicopters. It is not a rule of
general applicability and affects only
the applicant who applied to the FAA
for approval of these features.
BILLING CODE 4910–13–P
List of Subjects in 14 CFR Part 27
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
The authority citation for these
special conditions is as follows:
PENSION BENEFIT GUARANTY
CORPORATION
29 CFR Part 4022
Benefits Payable in Terminated SingleEmployer Plans; Interest Assumptions
for Paying Benefits
Authority: 49 U.S.C. 106(g), 40113, 44701,
44702, 44704.
Pension Benefit Guaranty
Corporation.
ACTION: Final rule.
The Special Conditions
SUMMARY:
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 Airbus Helicopters
Model AS350B2 and AS350B3
helicopters modified by Garmin
International, Inc. (Garmin).
Instead of the requirements of 14 CFR
27.1309(b) and (c), the following must
be met for certification of the Garmin
Flight Control 600H autopilot with
stability and control augmentation
system:
(a) The equipment and systems must
be designed and installed so that any
equipment and system does not
adversely affect the safety of the
rotorcraft or its occupants.
(b) The rotorcraft systems and
associated components considered
separately and in relation to other
systems, must be designed and installed
so that:
(1) The occurrence of any catastrophic
failure condition is extremely
improbable;
PO 00000
Frm 00002
Fmt 4700
Sfmt 4700
AGENCY:
This final rule amends the
Pension Benefit Guaranty Corporation’s
regulation on Benefits Payable in
Terminated Single-Employer Plans to
prescribe interest assumptions under
the regulation for valuation dates in
May 2018. The interest assumptions are
used for paying benefits under
terminating single-employer plans
covered by the pension insurance
system administered by PBGC.
DATES: Effective May 1, 2018.
FOR FURTHER INFORMATION CONTACT:
Hilary Duke (duke.hilary@pbgc.gov),
Assistant General Counsel for
Regulatory Affairs, Pension Benefit
Guaranty Corporation, 1200 K Street
NW, Washington, DC 20005, 202–326–
4400 ext. 3839. (TTY users may call the
Federal relay service toll-free at 1–800–
877–8339 and ask to be connected to
202–326–4400, ext. 3839.)
SUPPLEMENTARY INFORMATION: PBGC’s
regulation on Benefits Payable in
Terminated Single-Employer Plans (29
CFR part 4022) prescribes actuarial
assumptions—including interest
assumptions—for paying plan benefits
E:\FR\FM\13APR1.SGM
13APR1
]]>Agencies
[Federal Register Volume 83, Number 72 (Friday, April 13, 2018)]
[Rules and Regulations]
[Pages 15945-15946]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07655]
========================================================================
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.
========================================================================
Federal Register / Vol. 83, No. 72 / Friday, April 13, 2018 / Rules
and Regulations
[[Page 15945]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 27
[Docket No.FAA-2017-1130; Notice No. 27-043-SC]
Special Conditions: Airbus Helicopters Model AS350B2 and AS350B3
Helicopters; Installation of Garmin International, Inc., Autopilot
System
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for Airbus Helicopters
Model AS350B2 and AS350B3 helicopters. These helicopters as modified by
Garmin International, Inc., (Garmin) will have a novel or unusual
design feature associated with the Garmin Flight Control (GFC) 600H
autopilot with stability and control augmentation system (AP/SCAS). 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: The effective date of these special conditions is April 13,
2018.
FOR FURTHER INFORMATION CONTACT: George Harrum, Aerospace Engineer,
FAA, Rotorcraft Standards Branch, Policy and Innovations Division,
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-4087;
email [email protected].
SUPPLEMENTARY INFORMATION:
Background
On October 10, 2016, Garmin applied for a supplemental type
certificate (STC) to install a GFC 600H AP/SCAS in Airbus Helicopters
Model AS350B2 and AS350B3 helicopters. The Model AS350B2 and AS350B3
helicopters are 14 CFR part 27 normal category, single turbine engine,
conventional helicopters designed for civil operation. These helicopter
models are capable of carrying up to five passengers with one pilot and
have a maximum gross weight of up to 5,220 pounds, depending on the
model configuration. The major design features include a 3-blade, fully
articulated main rotor, an anti-torque tail rotor system, a skid
landing gear, and a visual flight rule basic avionics configuration.
Garmin proposes to modify these model helicopters by installing a
SCAS with autopilot functions in 2 or 3 axes, depending on the number
of servos installed. The possible failure conditions for this system,
and their effect on the continued safe flight and landing of the
helicopter, are more severe than those envisioned by the present rules.
The present 14 CFR 27.1309(b) and (c) regulations do not adequately
address the safety requirements for systems whose failures could result
in ``catastrophic'' or ``hazardous/severe-major'' failure conditions,
or for complex systems whose failures could result in ``major'' failure
conditions. When these rules were promulgated, it was not envisioned
that a normal category rotorcraft would use systems that are complex or
whose failure could result in ``catastrophic'' or ``hazardous/severe-
major'' effects on the rotorcraft. This is particularly true with the
application of new technology, new application of standard technology,
or other applications not envisioned by the rule that affect safety.
The Garmin AP/SCAS controls rotorcraft flight control surfaces.
Possible failure modes exhibited by this system could result in a
catastrophic event.
Type Certification Basis
Under 14 CFR 21.101 and 21.115, Garmin must show that the Airbus
Helicopters Model AS350B2 and AS350B3 helicopters, as changed, continue
to meet the applicable provisions of the regulations incorporated by
reference in Type Certificate No. H9EU or the applicable regulations in
effect on the date of application for the change. The regulations
incorporated by reference in the type certificate are commonly referred
to as the ``original type certification basis.'' The regulations
incorporated by reference in Type Certificate No. H9EU are as follows:
14 CFR 21.29 and part 27 effective February 1, 1965, plus
Amendments 27-1 through 27-10.
For aircraft incorporating mod. OP3369 (2370 kg/5225 lb mass
extension), the following 14 CFR part 27 Amendments 27-1 through 27-40
are replacing the same requirement from the certification basis above:
Sec. Sec. 27.1; 27.21; 27.25; 27.27; 27.33; 27.45; 27.51; 27.65;
27.71; 27.73; 27.75; 27.79; 27.141; 27.143; 27.173; 27.175; 27.177;
27.241; 27.301; 27.303; 27.305; 27.307; 27.309; 27.321; 27.337; 27.339;
27.341; 27.351; 27.471; 27.473; 27.501; 27.505; 27.521; 27.547; 27.549;
27.563(b); 27.571; 27.602; 27.661; 27.663; 27.695; 27.723; 27.725;
27.727; 27.737; 27.751; 27.753; 27.801(b)(d); 27.927(c); 27.1041;
27.1043; 27.1045; 27.1301; 27.1501; 27.1519; 27.1529; 27.1581; 27.1583;
27.1585; 27.1587; 27.1589.
For AS350B3 aircraft incorporating mod. OP-4605 (installation of a
fuel system improving crashworthiness), 14 CFR 27.561(c) at Amendment
27-32 replaces the same requirement from the certification basis above
for the following elements of the fuel tank lower structure affected by
this modification: cradles, longitudinal beams, X-stops and rods.
Additionally, Garmin must comply with the equivalent level of
safety findings, exemptions, and special conditions prescribed by the
Administrator as part of the certification basis.
The Administrator has determined the applicable airworthiness
regulations (that is, 14 CFR part 27), as they pertain to this STC, do
not contain adequate or appropriate safety standards for the Airbus
Helicopters Model AS350B2 and AS350B3 helicopters because of a novel or
unusual design feature. Therefore, we propose to prescribe these
special conditions under Sec. 21.16.
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply for an STC to change any
other model included on the same type certificate to incorporate 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, Garmin must show that the
[[Page 15946]]
Airbus Helicopters Model AS350B2 and AS350B3 helicopters, as changed,
comply with the noise certification requirements of 14 CFR part 36.
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. 21.101.
Novel or Unusual Design Features
The Airbus Helicopters Model AS350B2 and AS350B3 helicopter
incorporates the following novel or unusual design features: A GFC 600H
AP/SCAS. This GFC 600H AP/SCAS performs non-critical control functions.
The GFC 600H AP/SCAS is a two or three axis system with the following
novel functions: Limit cueing, level mode, and hover assist.
Discussion
These special conditions clarify the requirement to perform a
proper failure analysis and also recognizes that the severity of
failures can vary. Current industry standards and practices recognize
five failure condition categories: Catastrophic, Hazardous, Major,
Minor, and No-Safety Effect. These special conditions address the
safety requirement for systems whose failures could result in
catastrophic or hazardous/severe-major failure conditions and for
complex systems whose failures could result in major failure
conditions.
To comply with the provisions of the special conditions, we require
that Garmin provide the FAA with a systems safety assessment (SSA) for
the final GFC 600H AP/SCAS installation configuration that adequately
address the safety objectives established by a functional hazard
assessment (FHA) and a preliminary system safety assessment (PSSA),
including the fault tree analysis (FTA). This ensures that all failure
conditions and their resulting effects are adequately addressed for the
installed GFC 600H AP/SCAS. The SSA process, FHA, PSSA, and FTA are all
parts of the overall safety assessment process discussed in FAA
Advisory Circular 27-1B, Certification of Normal Category Rotorcraft,
and Society of Automotive Engineers document Aerospace Recommended
Practice 4761, Guidelines and Methods for Conducting the Safety
Assessment Process on Civil Airborne Systems and Equipment.
These special conditions require that the GFC 600H AP/SCAS
installed on Airbus Helicopters Model AS350B2 and Model AS350B3
helicopters meet the requirements to adequately address the failure
effects identified by the FHA, and subsequently verified by the SSA,
within the defined design integrity requirements.
Comments
No comments were received in response to the Notice of proposed
special conditions No. 27-043-SC (82 FR 57685, December 7, 2017). The
closing date for comments was January 22, 2018. Accordingly, the
special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to
Airbus Helicopters Model AS350B2 and AS350B3 helicopters. Should Garmin
apply at a later date for an STC to modify any other model included on
Type Certificate Number H9EU to incorporate the same novel or unusual
design feature, these special conditions would apply to that model as
well.
Conclusion
This action affects only certain novel or unusual design features
on two model helicopters. It is not a rule of general applicability and
affects only the applicant who applied to the FAA for approval of these
features.
List of Subjects in 14 CFR Part 27
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 Airbus Helicopters Model AS350B2 and
AS350B3 helicopters modified by Garmin International, Inc. (Garmin).
Instead of the requirements of 14 CFR 27.1309(b) and (c), the
following must be met for certification of the Garmin Flight Control
600H autopilot with stability and control augmentation system:
(a) The equipment and systems must be designed and installed so
that any equipment and system does not adversely affect the safety of
the rotorcraft or its occupants.
(b) The rotorcraft systems and associated components considered
separately and in relation to other systems, must be designed and
installed so that:
(1) The occurrence of any catastrophic failure condition is
extremely improbable;
(2) The occurrence of any hazardous failure condition is extremely
remote; and
(3) The occurrence of any major failure condition is remote.
(c) Information concerning an unsafe system operating condition
must be provided in a timely manner to the crew to enable them to take
appropriate corrective action. An appropriate alert must be provided if
immediate pilot awareness and immediate or subsequent corrective action
is required. Systems and controls, including indications and
annunciations, must be designed to minimize crew errors which could
create additional hazards.
Issued in Fort Worth, Texas, on March 30, 2018.
Jorge Castillo,
Acting Manager, Rotorcraft Standards Branch, Policy and Innovation
Division Aircraft Certification Service.
[FR Doc. 2018-07655 Filed 4-12-18; 8:45 am]
BILLING CODE 4910-13-P
