Special Conditions: AeroMech, Incorporated; Hawker Beechcraft Corporation, Model B200 and Other Aircraft Listed in Table 1, Approved Model List (AML); Installation of MD835 Lithium Ion Battery, 50850-50853 [2010-20413]
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50850
Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
Signed in Washington, DC, on August 11,
2010.
Jonathan W. Coppess,
Executive Vice President, Commodity Credit
Corporation.
[FR Doc. 2010–20352 Filed 8–17–10; 8:45 am]
BILLING CODE 3410–05–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE307; Special Condition No.
23–247–SC]
Special Conditions: AeroMech,
Incorporated; Hawker Beechcraft
Corporation, Model B200 and Other
Aircraft Listed in Table 1, Approved
Model List (AML); Installation of MD835
Lithium Ion Battery
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
These special conditions are
issued for the AeroMech, Incorporated;
Hawker Beechcraft Corporation, model
B200 and other part 23 aircraft listed on
the AML. These airplanes as modified
by AeroMech, Incorporated will have a
novel or unusual design feature(s)
SUMMARY:
associated with installation of the MidContinent Instruments MD835 Lithium
Ion (Li-ion) battery. 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: August 9, 2010.
FOR FURTHER INFORMATION CONTACT:
James Brady, Regulations and Policy
Branch, ACE–111, Federal Aviation
Administration, Small Airplane
Directorate, Aircraft Certification
Service, 901 Locust, Kansas City, MO
64106; telephone (816) 329–4132;
facsimile (816) 329–4090.
SUPPLEMENTARY INFORMATION:
Background
On September 18, 2009, AeroMech,
Incorporated applied for a supplemental
type certificate AML for installation of
the Mid-Continent Instruments MD835
Li-ion battery in the Hawker Beechcraft
Corporation, B200 and other aircraft
listed on the AML. The AML covers part
23 aircraft that currently use the PS–835
lead-acid emergency battery.
The current regulatory requirements
for part 23 airplanes do not contain
adequate requirements for the
application of Li-ion batteries in
airborne applications. AeroMech,
Incorporated plans to replace an
existing L–3 Communications PS–835
lead-acid emergency battery with a MidContinent Instruments MD835 Li-ion
battery on part 23 aircraft currently
equipped with the PS–835 battery. This
type of battery possesses certain failure,
operational, and maintenance
characteristics that differ significantly
from that of the nickel cadmium (Ni-Cd)
and lead-acid rechargeable batteries
currently approved in other normal,
utility, acrobatic, and commuter
category airplanes.
Type Certification Basis
Under the provisions of § 21.101,
AeroMech, Incorporated must show that
the Hawker Beechcraft Corporation
B200 and other aircraft listed on the
AML, as changed, continues to meet the
applicable provisions of the regulations
incorporated by reference in the type
certificate of each model listed 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 certification
basis for each model qualified for this
modification is detailed below.
TABLE 1—APPROVED MODEL LIST
Certification basis for
alteration
Aircraft model
TCDS
Aero Vodochody ................
Ae 270 ..........................................................................
A58CE Rev 3 ....................
Cessna ...............................
441 ................................................................................
A28CE ...............................
Cessna ...............................
401, 402, 411, 414, 421, 425 .......................................
A7CE .................................
Cessna ...............................
501, 551 ........................................................................
A27CE Rev 17 ..................
Cessna ...............................
525, 525A, 525B ...........................................................
A1WI Rev 17 .....................
Cessna ...............................
510 ................................................................................
A00014WI Rev 3 ...............
Dornier ...............................
228–100/–101/–200/–201/–202/–212 ...........................
A16EU ...............................
Embraer .............................
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Aircraft make
EMB–500 ......................................................................
A59CE Rev 0 ....................
Embraer .............................
EMB–110P1, EMB110P2 .............................................
A21SO Rev 6 ....................
Hawker Beechcraft ............
C90, C90A, C90GT, B90, E90, H90, C90GTi ..............
3A20 Rev 69 .....................
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14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
50851
TABLE 1—APPROVED MODEL LIST—Continued
Certification basis for
alteration
Aircraft model
TCDS
Hawker Beechcraft ............
200, 200C, 200CT, 200T, B200, B200C, B200CT,
B200GT, B200CGT B200T, 300, 300LW, B300,
B300C, 1900C, 1900D.
99, 99A, A99, A99A, B99, C99 ....................................
A24CE Rev 98 ..................
Hawker Beechcraft ............
A14CE Rev 37 ..................
Hawker Beechcraft ............
390 ................................................................................
A00010WI Rev 8 ...............
Learjet ................................
23 ..................................................................................
A5CE Rev 10 ....................
M7 Aerospace ....................
SA226–T, SA226–AT, SA227–AT, SA227–TT ............
A5SW Rev 26 ...................
Pacific Aerospace ..............
750XL ...........................................................................
A50CE Rev 3 ....................
Piaggio ...............................
P–180 ...........................................................................
A59EU Rev 18 ..................
Pilatus ................................
PC–12 ...........................................................................
A78EU Rev 19 ..................
Socata ................................
TBM 700 .......................................................................
A60EU Rev 18 ..................
Twin Commander ..............
680, 680E, 680F, 680FL, 680T, 680V, 680W, 681,
690, 690A, 690B, 690C, 690D, 695, 695A, 695B.
2A4 Rev 47 .......................
Viking Air ............................
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Aircraft make
DHC–6–1/–100/–200/–300 ...........................................
A9EA Rev 13 ....................
If the Administrator finds that the
applicable airworthiness regulations
(i.e., 14 CFR part 23) do not contain
adequate or appropriate safety standards
for the Hawker Beechcraft Corporation,
B200 and other aircraft listed on the
AML, because of a novel or unusual
design feature, special conditions are
prescribed under the provisions of
§ 21.16. The FAA issues special
conditions, as defined in § 11.19, under
§ 11.38 and they become part of the type
certification basis under § 21.101.
Special conditions are initially
applicable to the model for which they
are issued. Should the applicant apply
for a supplemental type certificate AML
to modify any other model 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, the B200 and other aircraft
on the AML 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.
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Jkt 220001
Novel or Unusual Design Features
The Hawker Beechcraft Corporation,
B200 and other aircraft listed on the
AML will incorporate the following
novel or unusual design features:
AeroMech, Incorporated proposes to
replace an existing L–3
Communications PS–835 lead-acid
emergency battery with a Mid-Continent
Instruments MD835 Li-ion battery on
part 23 aircraft currently equipped with
the PS–835 battery. This type of battery
possesses certain failure, operational
characteristics, and maintenance
requirements that differ significantly
from that of the Ni-Cd and lead-acid
rechargeable batteries currently
approved in other normal, utility,
acrobatic, and commuter category
airplanes.
Discussion
The applicable part 21 and part 23
airworthiness regulations governing the
installation of batteries in general
aviation airplanes, including § 23.1353
were derived from Civil Air Regulations
(CAR 3) as part of the recodification that
established 14 CFR part 23. The battery
requirements, which were identified as
§ 23.1353, were basically a rewording of
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14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
14 CFR part 23 amdt
except for 14 CFR
23.1308.
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
23–59,
the CAR requirements that did not add
any substantive technical requirements.
An increase in incidents involving
battery fires and failures that
accompanied the increased use of Ni-Cd
batteries in airplanes resulted in
rulemaking activities on the battery
requirements for business jet and
commuter category airplanes. These
regulations were incorporated into
§ 23.1353(f) and (g), which apply only to
Ni-Cd battery installations.
The planned use of Li-ion batteries on
the Hawker Beechcraft Corporation,
B200 and other aircraft listed on the
AML has prompted the FAA to review
the adequacy of the existing battery
regulations with respect to that
chemistry. As the result of this review,
the FAA determines the existing
regulations do not adequately address
several failure, operational, and
maintenance characteristics of Li-ion
batteries that could affect safety of the
battery installation and the reliability of
the electrical power supply on the
Hawker Beechcraft Corporation, B200
and other aircraft listed on the AML.
Li-ion batteries in general are
significantly more susceptible to
internal failures that can result in selfsustaining increases in temperature and
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Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
pressure (i.e., thermal runaway) than
their Ni-Cd and lead-acid counterparts.
This is especially true for overcharging
a Li-ion battery, which will likely result
in explosion, fire, or both. Certain types
of Li-ion batteries pose a potential safety
problem because of the instability and
flammability of the organic electrolyte
employed by the cells of those batteries.
The severity of thermal runaway
increases with increasing battery
capacity due to the higher amount of
electrolyte in large batteries.
If the discharge of the cells is below
a typical voltage of 3.0 volts on some
versions of Li-ion batteries, they will
subsequently no longer accept a charge.
This loss of capacity may not be
detected by the simple voltage
measurements commonly available to
flight crews as a means of checking
battery status, a problem shared with
Ni-Cd batteries.
Unlike Ni-Cd and lead-acid cells,
some types of Li-ion cells employ
electrolytes that are known to be
flammable. This material can serve as a
source of fuel for an external fire in the
event of a breach of the cell container.
The intent of these special conditions
is to establish appropriate airworthiness
standards for Li-ion battery installations
in the Hawker Beechcraft Corporation,
B200 and other aircraft listed on the
AML. These special conditions adopt
the following requirements as a means
of addressing these concerns:
(1) Inclusion of those sections of
§ 23.1353 that are applicable to Li-ion
batteries.
(2) Inclusion of the flammable fluid
fire protection requirements of § 23.863.
In the past, this rule was not applied to
the batteries of business jet or commuter
category airplanes since the electrolytes
utilized in lead-acid and Ni-Cd batteries
are not considered to be flammable.
(3) Addition of new requirements to
address the potential hazards of
overcharging and over discharging that
are unique to Li-ion battery designs.
(4) Addition of maintenance
requirements to ensure that batteries
used as spares are maintained in an
appropriate state of charge (SOC).
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Discussion of Comments
Notice of proposed special conditions
No. 23–10–01–SC for the AeroMech,
Incorporated; Hawker Beechcraft
Corporation, model B200 and other
aircraft listed in Table 1, AML was
published in the Federal Register on
June 14, 2010, 75 FR 33553. No
comments were received, and the
special conditions are adopted as
proposed.
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16:57 Aug 17, 2010
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Applicability
As discussed above, these special
conditions are applicable to the Hawker
Beechcraft Corporation, B200 and other
aircraft listed on the AML. Should
AeroMech, Incorporated apply at a later
date to modify any other model and list
the model on the AML, the special
conditions would apply to that model as
well.
Under standard practice, the effective
date of final special conditions would
be 30 days after the date of publication
in the Federal Register; however, as the
supplemental type, certification date for
the Hawker Beechcraft Corporation,
model B200 and those airplanes listed
in the AML, as modified by AeroMech,
Inc., is imminent, the FAA finds that
good cause exists to make these special
conditions effective upon issuance.
Conclusion
This action affects only certain novel
or unusual design features on the
Hawker Beechcraft Corporation, B200
and other aircraft listed on the AML. It
is not a rule of general applicability, and
it affects only the applicant who applied
to the FAA for approval of these features
on the airplane.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and
symbols.
Citation
The authority citation for these
special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, and
44701; 14 CFR 21.16 and 21.101; and 14 CFR
11.38 and 11.19.
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 Hawker
Beechcraft Corporation, model B200 and
other airplanes on the AML modified by
AeroMech, Incorporated.
1. SC 23.1353, Storage battery design
and installation. The Federal Aviation
Administration issues the following
Special Conditions (SC), which apply to
Beechcraft Corporation, model B200 and
all aircraft listed on the AML equipped
with MD–835 Li-ion batteries in lieu of
the requirements of § 23.1353(a), (b), (c),
(d), and (e), Amendment 23–49 through
23–59. Li-ion batteries and battery
installations on part 23 airplanes
equipped with existing PS–835 batteries
must be designed and installed as
follows:
(1) Safe cell temperatures and
pressures must be maintained during
any probable charging or discharging
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condition, or during any failure of the
charging or battery monitoring system
not shown to be extremely remote. The
Li-ion battery installation must be
designed to preclude explosion or fire in
the event of those failures.
(2) Li-ion batteries must be designed
to preclude the occurrence of selfsustaining, uncontrolled increases in
temperature or pressure.
(3) No explosive or toxic gasses
emitted by any Li-ion battery in normal
operation or as the result of any failure
of the battery charging or monitoring
system, or battery installation not
shown to be extremely remote, may
accumulate in hazardous quantities
within the airplane.
(4) Li-ion batteries that contain
flammable fluids must comply with the
flammable fluid fire protection
requirements of § 23.863(a) through (d).
(5) No corrosive fluids or gases that
may escape from any Li-ion battery may
damage airplane structure or essential
equipment.
(6) Each Li-ion battery installation
must have provisions to prevent any
hazardous effect on structure or
essential systems that may be caused by
the maximum amount of heat the
battery can generate during a short
circuit of the battery or of its individual
cells.
(7) Li-ion battery installations must
have—
(i) a system to control the charging
rate of the battery automatically so as to
prevent battery overheating or
overcharging, or
(ii) a battery temperature sensing and
over-temperature warning system with a
means for automatically disconnecting
the battery from its charging source in
the event of an over-temperature
condition, or
(iii) a battery failure sensing and
warning system with a means for
automatically disconnecting the battery
from its charging source in the event of
battery failure.
(8) Any Li-ion battery installation
whose function is required for safe
operation of the airplane must
incorporate a monitoring and warning
feature that will provide an indication
to the appropriate flight crewmembers
whenever the capacity and state of
charge (SOC) of the batteries have fallen
below levels considered acceptable for
dispatch of the airplane.
(9) The Instructions for Continued
Airworthiness (ICA) must contain
recommended manufacturers
maintenance and inspection
requirements to ensure that batteries,
including single cells, meet a safety
function level essential to the aircraft’s
continued airworthiness.
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Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations
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(i) The ICA must contain operating
instructions and equipment limitations
in an installation maintenance manual.
(ii) The ICA must contain installation
procedures and limitations in a
maintenance manual sufficient to
ensure that cells or batteries, when
installed according to the installation
procedures, still meet safety functional
levels essential to the aircraft’s
continued airworthiness. The
limitations must identify any unique
aspects of the installation.
(iii) The ICA must contain corrective
maintenance procedures to functionally
check battery capacity at manufacturer’s
recommended inspection intervals.
(iv) The ICA must contain scheduled
servicing information to replace
batteries at manufacturers
recommended replacement time.
(v) The ICA must contain
maintenance and inspection
requirements to visually check for a
battery and/or charger degradation.
(vi) The ICA must contain
instructions that batteries in a rotating
stock (spares) that have experienced
degraded charge retention capability or
other damage due to prolonged storage
must be functionally checked at
manufacturer’s recommended
inspection intervals.
(10) If the Li-ion battery application
contains software and/or complex
hardware, in accordance with AC 20–
115B and AC 20–152, they should be
developed to the standards of DO–178B
for software and DO–254 for complex
hardware.
(11) The Li-ion battery must meet
TSO C179.
These special conditions are not
intended to replace § 23.1353 in the
certification basis of the Hawker
Beechcraft Corporation, B200 and other
aircraft listed on the AML. These special
conditions apply only to Li-ion batteries
and battery installations. The battery
requirements of § 23.1353 would remain
in effect for batteries and battery
installations on Hawker Beechcraft
Corporation, B200 and other aircraft
listed on the AML that do not use Liion batteries.
Issued in Kansas City, Missouri, on August
9, 2010.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–20413 Filed 8–17–10; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE308; Special Conditions No.
23–248–SC]
Special Conditions: Cirrus Design
Corporation Model SF50 Airplane;
Function and Reliability Testing
Federal Aviation
Administration (FAA), DOT.
ACTION: Final special conditions.
AGENCY:
These special conditions are
issued for the Cirrus Design Corporation
SF50 airplane. This airplane will have
a novel or unusual design feature(s)
associated with the complex design and
performance features consistent with
larger airplanes. 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: September 17,
2010.
SUMMARY:
J.
Lowell Foster, Federal Aviation
Administration, Small Airplane
Directorate, Aircraft Certification
Service, 901 Locust, Room 301, Kansas
City, MO 64106; telephone (816) 329–
4125; facsimile (816) 329–4090.
SUPPLEMENTARY INFORMATION:
FOR FURTHER INFORMATION CONTACT:
Background
On September 9, 2008, Cirrus Design
Corporation applied for a type
certificate for their new model SF50
‘‘Vision’’ Jet. The SF50 is a low-wing,
five-plus-two-place (2 children), singleengine turbofan-powered aircraft. It
incorporates an Electronic Flight
Information System (EFIS), pressurized
cabin, retractable gear, and a V-tail. The
turbofan engine is mounted on the
upper fuselage/tail cone along the
aircraft centerline. It is constructed
largely of carbon and fiberglass
composite materials. Like other Cirrus
products, the SF50 includes a
ballistically deployed airframe
parachute.
The model SF50 has a maximum
operating altitude of 28,000 feet, where
it cruises at speeds up to 300 Knots True
Air Speed (KTAS). Its VMO will not
exceed 0.62 Mach. The maximum
takeoff weight will be at or below 6,000
pounds with a range at economy cruise
of roughly 1,000 nm. Cirrus intends for
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50853
the model SF50 to be certified for
single-pilot operations under 14 CFR
part 91 and 14 CFR part 135 operating
rules. The following operating
conditions will be included:
• Day and Night VFR.
• IFR.
• Flight Into Known Icing.
Discussion
Before Amendment 3–4, Section 3.19
of Civil Air Regulation (CAR) part 3
required service testing of all airplanes
type certificated on or after May 15,
1947. The purpose of the testing was to
‘‘ascertain whether there is reasonable
assurance that the airplane, its
components, and equipment are
reliable, and function properly.’’
Amendment 3–4 to CAR part 3
became effective January 15, 1951, and
deleted the service test requirements in
Section 3.19 for airplanes of 6,000
pounds maximum weight or less. The
introductory text published in
Amendment 3–4 explained that most of
the significant changes in the
amendment stemmed from ‘‘the desire
for simplification of the rules in this
part with respect to the smaller
airplanes, specifically those of 6,000
pounds maximum weight or less, which
would be expected to be used mainly as
personal airplanes.’’ The introductory
material also stated the service test
requirement was removed for airplanes
of 6,000 pounds maximum weight or
less because ‘‘experience seems to
indicate that this rule imposes a burden
upon the manufacturers not
commensurate with the safety gained.’’
The requirement for Function and
Reliability (F&R) testing, and the
exception for airplanes of 6,000 pounds
or less maximum weight, is now found
in 14 CFR part 21, section 21.35(b)(2).
The decision to exempt airplanes of
6,000 pounds maximum weight or less
from F&R testing was based on the state
of technology envisioned in 1951. At
that time, airplanes of 6,000 pounds
maximum weight or less were expected
to be used mainly as personal airplanes.
They used simple, ‘‘stand-alone’’
systems whose failure was more likely
to be an inconvenience than an
accident. The situation is different
today. Technological advances allow
airplanes weighing less than 6,000
pounds to be more complex and
integrated than some transport
airplanes. New part 23 airplanes can
incorporate sophisticated equipment not
previously used in a part 23 aircraft.
Additionally, part 23 airplanes are being
used for business and commercial
transportation. They should no longer
be envisioned mainly as personal
airplanes. Therefore, a special condition
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]]>Agencies
[Federal Register Volume 75, Number 159 (Wednesday, August 18, 2010)]
[Rules and Regulations]
[Pages 50850-50853]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-20413]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE307; Special Condition No. 23-247-SC]
Special Conditions: AeroMech, Incorporated; Hawker Beechcraft
Corporation, Model B200 and Other Aircraft Listed in Table 1, Approved
Model List (AML); Installation of MD835 Lithium Ion Battery
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
-----------------------------------------------------------------------
SUMMARY: These special conditions are issued for the AeroMech,
Incorporated; Hawker Beechcraft Corporation, model B200 and other part
23 aircraft listed on the AML. These airplanes as modified by AeroMech,
Incorporated will have a novel or unusual design feature(s) associated
with installation of the Mid-Continent Instruments MD835 Lithium Ion
(Li-ion) battery. 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: August 9, 2010.
FOR FURTHER INFORMATION CONTACT: James Brady, Regulations and Policy
Branch, ACE-111, Federal Aviation Administration, Small Airplane
Directorate, Aircraft Certification Service, 901 Locust, Kansas City,
MO 64106; telephone (816) 329-4132; facsimile (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Background
On September 18, 2009, AeroMech, Incorporated applied for a
supplemental type certificate AML for installation of the Mid-Continent
Instruments MD835 Li-ion battery in the Hawker Beechcraft Corporation,
B200 and other aircraft listed on the AML. The AML covers part 23
aircraft that currently use the PS-835 lead-acid emergency battery.
The current regulatory requirements for part 23 airplanes do not
contain adequate requirements for the application of Li-ion batteries
in airborne applications. AeroMech, Incorporated plans to replace an
existing L-3 Communications PS-835 lead-acid emergency battery with a
Mid-Continent Instruments MD835 Li-ion battery on part 23 aircraft
currently equipped with the PS-835 battery. This type of battery
possesses certain failure, operational, and maintenance characteristics
that differ significantly from that of the nickel cadmium (Ni-Cd) and
lead-acid rechargeable batteries currently approved in other normal,
utility, acrobatic, and commuter category airplanes.
Type Certification Basis
Under the provisions of Sec. 21.101, AeroMech, Incorporated must
show that the Hawker Beechcraft Corporation B200 and other aircraft
listed on the AML, as changed, continues to meet the applicable
provisions of the regulations incorporated by reference in the type
certificate of each model listed 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 certification
basis for each model qualified for this modification is detailed below.
Table 1--Approved Model List
----------------------------------------------------------------------------------------------------------------
Aircraft make Aircraft model TCDS Certification basis for alteration
----------------------------------------------------------------------------------------------------------------
Aero Vodochody................ Ae 270................ A58CE Rev 3...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Cessna........................ 441................... A28CE............ 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Cessna........................ 401, 402, 411, 414, A7CE............. 14 CFR part 23 amdt 23-59, except for
421, 425. 14 CFR 23.1308.
Cessna........................ 501, 551.............. A27CE Rev 17..... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Cessna........................ 525, 525A, 525B....... A1WI Rev 17...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Cessna........................ 510................... A00014WI Rev 3... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Dornier....................... 228-100/-101/-200/-201/ A16EU............ 14 CFR part 23 amdt 23-59, except for
-202/-212. 14 CFR 23.1308.
Embraer....................... EMB-500............... A59CE Rev 0...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Embraer....................... EMB-110P1, EMB110P2... A21SO Rev 6...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Hawker Beechcraft............. C90, C90A, C90GT, B90, 3A20 Rev 69...... 14 CFR part 23 amdt 23-59, except for
E90, H90, C90GTi. 14 CFR 23.1308.
[[Page 50851]]
Hawker Beechcraft............. 200, 200C, 200CT, A24CE Rev 98..... 14 CFR part 23 amdt 23-59, except for
200T, B200, B200C, 14 CFR 23.1308.
B200CT, B200GT,
B200CGT B200T, 300,
300LW, B300, B300C,
1900C, 1900D.
Hawker Beechcraft............. 99, 99A, A99, A99A, A14CE Rev 37..... 14 CFR part 23 amdt 23-59, except for
B99, C99. 14 CFR 23.1308.
Hawker Beechcraft............. 390................... A00010WI Rev 8... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Learjet....................... 23.................... A5CE Rev 10...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
M7 Aerospace.................. SA226-T, SA226-AT, A5SW Rev 26...... 14 CFR part 23 amdt 23-59, except for
SA227-AT, SA227-TT. 14 CFR 23.1308.
Pacific Aerospace............. 750XL................. A50CE Rev 3...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Piaggio....................... P-180................. A59EU Rev 18..... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Pilatus....................... PC-12................. A78EU Rev 19..... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Socata........................ TBM 700............... A60EU Rev 18..... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
Twin Commander................ 680, 680E, 680F, 2A4 Rev 47....... 14 CFR part 23 amdt 23-59, except for
680FL, 680T, 680V, 14 CFR 23.1308.
680W, 681, 690, 690A,
690B, 690C, 690D,
695, 695A, 695B.
Viking Air.................... DHC-6-1/-100/-200/-300 A9EA Rev 13...... 14 CFR part 23 amdt 23-59, except for
14 CFR 23.1308.
----------------------------------------------------------------------------------------------------------------
If the Administrator finds that the applicable airworthiness
regulations (i.e., 14 CFR part 23) do not contain adequate or
appropriate safety standards for the Hawker Beechcraft Corporation,
B200 and other aircraft listed on the AML, because of a novel or
unusual design feature, special conditions are prescribed under the
provisions of Sec. 21.16. The FAA issues special conditions, as
defined in Sec. 11.19, under Sec. 11.38 and they become part of the
type certification basis under Sec. 21.101.
Special conditions are initially applicable to the model for which
they are issued. Should the applicant apply for a supplemental type
certificate AML to modify any other model 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, the B200 and other aircraft on the AML 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.
Novel or Unusual Design Features
The Hawker Beechcraft Corporation, B200 and other aircraft listed
on the AML will incorporate the following novel or unusual design
features:
AeroMech, Incorporated proposes to replace an existing L-3
Communications PS-835 lead-acid emergency battery with a Mid-Continent
Instruments MD835 Li-ion battery on part 23 aircraft currently equipped
with the PS-835 battery. This type of battery possesses certain
failure, operational characteristics, and maintenance requirements that
differ significantly from that of the Ni-Cd and lead-acid rechargeable
batteries currently approved in other normal, utility, acrobatic, and
commuter category airplanes.
Discussion
The applicable part 21 and part 23 airworthiness regulations
governing the installation of batteries in general aviation airplanes,
including Sec. 23.1353 were derived from Civil Air Regulations (CAR 3)
as part of the recodification that established 14 CFR part 23. The
battery requirements, which were identified as Sec. 23.1353, were
basically a rewording of the CAR requirements that did not add any
substantive technical requirements. An increase in incidents involving
battery fires and failures that accompanied the increased use of Ni-Cd
batteries in airplanes resulted in rulemaking activities on the battery
requirements for business jet and commuter category airplanes. These
regulations were incorporated into Sec. 23.1353(f) and (g), which
apply only to Ni-Cd battery installations.
The planned use of Li-ion batteries on the Hawker Beechcraft
Corporation, B200 and other aircraft listed on the AML has prompted the
FAA to review the adequacy of the existing battery regulations with
respect to that chemistry. As the result of this review, the FAA
determines the existing regulations do not adequately address several
failure, operational, and maintenance characteristics of Li-ion
batteries that could affect safety of the battery installation and the
reliability of the electrical power supply on the Hawker Beechcraft
Corporation, B200 and other aircraft listed on the AML.
Li-ion batteries in general are significantly more susceptible to
internal failures that can result in self-sustaining increases in
temperature and
[[Page 50852]]
pressure (i.e., thermal runaway) than their Ni-Cd and lead-acid
counterparts. This is especially true for overcharging a Li-ion
battery, which will likely result in explosion, fire, or both. Certain
types of Li-ion batteries pose a potential safety problem because of
the instability and flammability of the organic electrolyte employed by
the cells of those batteries. The severity of thermal runaway increases
with increasing battery capacity due to the higher amount of
electrolyte in large batteries.
If the discharge of the cells is below a typical voltage of 3.0
volts on some versions of Li-ion batteries, they will subsequently no
longer accept a charge. This loss of capacity may not be detected by
the simple voltage measurements commonly available to flight crews as a
means of checking battery status, a problem shared with Ni-Cd
batteries.
Unlike Ni-Cd and lead-acid cells, some types of Li-ion cells employ
electrolytes that are known to be flammable. This material can serve as
a source of fuel for an external fire in the event of a breach of the
cell container.
The intent of these special conditions is to establish appropriate
airworthiness standards for Li-ion battery installations in the Hawker
Beechcraft Corporation, B200 and other aircraft listed on the AML.
These special conditions adopt the following requirements as a means of
addressing these concerns:
(1) Inclusion of those sections of Sec. 23.1353 that are
applicable to Li-ion batteries.
(2) Inclusion of the flammable fluid fire protection requirements
of Sec. 23.863. In the past, this rule was not applied to the
batteries of business jet or commuter category airplanes since the
electrolytes utilized in lead-acid and Ni-Cd batteries are not
considered to be flammable.
(3) Addition of new requirements to address the potential hazards
of overcharging and over discharging that are unique to Li-ion battery
designs.
(4) Addition of maintenance requirements to ensure that batteries
used as spares are maintained in an appropriate state of charge (SOC).
Discussion of Comments
Notice of proposed special conditions No. 23-10-01-SC for the
AeroMech, Incorporated; Hawker Beechcraft Corporation, model B200 and
other aircraft listed in Table 1, AML was published in the Federal
Register on June 14, 2010, 75 FR 33553. No comments were received, and
the special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
Hawker Beechcraft Corporation, B200 and other aircraft listed on the
AML. Should AeroMech, Incorporated apply at a later date to modify any
other model and list the model on the AML, the special conditions would
apply to that model as well.
Under standard practice, the effective date of final special
conditions would be 30 days after the date of publication in the
Federal Register; however, as the supplemental type, certification date
for the Hawker Beechcraft Corporation, model B200 and those airplanes
listed in the AML, as modified by AeroMech, Inc., is imminent, the FAA
finds that good cause exists to make these special conditions effective
upon issuance.
Conclusion
This action affects only certain novel or unusual design features
on the Hawker Beechcraft Corporation, B200 and other aircraft listed on
the AML. It is not a rule of general applicability, and it affects only
the applicant who applied to the FAA for approval of these features on
the airplane.
List of Subjects in 14 CFR Part 23
Aircraft, Aviation safety, Signs and symbols.
Citation
The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106(g), 40113, and 44701; 14 CFR 21.16 and
21.101; and 14 CFR 11.38 and 11.19.
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 Hawker Beechcraft Corporation,
model B200 and other airplanes on the AML modified by AeroMech,
Incorporated.
1. SC 23.1353, Storage battery design and installation. The Federal
Aviation Administration issues the following Special Conditions (SC),
which apply to Beechcraft Corporation, model B200 and all aircraft
listed on the AML equipped with MD-835 Li-ion batteries in lieu of the
requirements of Sec. 23.1353(a), (b), (c), (d), and (e), Amendment 23-
49 through 23-59. Li-ion batteries and battery installations on part 23
airplanes equipped with existing PS-835 batteries must be designed and
installed as follows:
(1) Safe cell temperatures and pressures must be maintained during
any probable charging or discharging condition, or during any failure
of the charging or battery monitoring system not shown to be extremely
remote. The Li-ion battery installation must be designed to preclude
explosion or fire in the event of those failures.
(2) Li-ion batteries must be designed to preclude the occurrence of
self-sustaining, uncontrolled increases in temperature or pressure.
(3) No explosive or toxic gasses emitted by any Li-ion battery in
normal operation or as the result of any failure of the battery
charging or monitoring system, or battery installation not shown to be
extremely remote, may accumulate in hazardous quantities within the
airplane.
(4) Li-ion batteries that contain flammable fluids must comply with
the flammable fluid fire protection requirements of Sec. 23.863(a)
through (d).
(5) No corrosive fluids or gases that may escape from any Li-ion
battery may damage airplane structure or essential equipment.
(6) Each Li-ion battery installation must have provisions to
prevent any hazardous effect on structure or essential systems that may
be caused by the maximum amount of heat the battery can generate during
a short circuit of the battery or of its individual cells.
(7) Li-ion battery installations must have--
(i) a system to control the charging rate of the battery
automatically so as to prevent battery overheating or overcharging, or
(ii) a battery temperature sensing and over-temperature warning
system with a means for automatically disconnecting the battery from
its charging source in the event of an over-temperature condition, or
(iii) a battery failure sensing and warning system with a means for
automatically disconnecting the battery from its charging source in the
event of battery failure.
(8) Any Li-ion battery installation whose function is required for
safe operation of the airplane must incorporate a monitoring and
warning feature that will provide an indication to the appropriate
flight crewmembers whenever the capacity and state of charge (SOC) of
the batteries have fallen below levels considered acceptable for
dispatch of the airplane.
(9) The Instructions for Continued Airworthiness (ICA) must contain
recommended manufacturers maintenance and inspection requirements to
ensure that batteries, including single cells, meet a safety function
level essential to the aircraft's continued airworthiness.
[[Page 50853]]
(i) The ICA must contain operating instructions and equipment
limitations in an installation maintenance manual.
(ii) The ICA must contain installation procedures and limitations
in a maintenance manual sufficient to ensure that cells or batteries,
when installed according to the installation procedures, still meet
safety functional levels essential to the aircraft's continued
airworthiness. The limitations must identify any unique aspects of the
installation.
(iii) The ICA must contain corrective maintenance procedures to
functionally check battery capacity at manufacturer's recommended
inspection intervals.
(iv) The ICA must contain scheduled servicing information to
replace batteries at manufacturers recommended replacement time.
(v) The ICA must contain maintenance and inspection requirements to
visually check for a battery and/or charger degradation.
(vi) The ICA must contain instructions that batteries in a rotating
stock (spares) that have experienced degraded charge retention
capability or other damage due to prolonged storage must be
functionally checked at manufacturer's recommended inspection
intervals.
(10) If the Li-ion battery application contains software and/or
complex hardware, in accordance with AC 20-115B and AC 20-152, they
should be developed to the standards of DO-178B for software and DO-254
for complex hardware.
(11) The Li-ion battery must meet TSO C179.
These special conditions are not intended to replace Sec. 23.1353
in the certification basis of the Hawker Beechcraft Corporation, B200
and other aircraft listed on the AML. These special conditions apply
only to Li-ion batteries and battery installations. The battery
requirements of Sec. 23.1353 would remain in effect for batteries and
battery installations on Hawker Beechcraft Corporation, B200 and other
aircraft listed on the AML that do not use Li-ion batteries.
Issued in Kansas City, Missouri, on August 9, 2010.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-20413 Filed 8-17-10; 8:45 am]
BILLING CODE 4910-13-P
