Federal Aviation Administration (FAA), DOT.
Final special conditions.
These special conditions are issued for the Spectrum Aeronautical, LLC Model 40 (S-40) airplane. This airplane will have a novel or unusual design feature associated with the installation of lithium polymer (Li-Poly) batteries for emergency, main, and auxiliary power unit (APU) applications. 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.
Effective Date: April 7, 2009.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Jim Brady, Aerospace Engineer, Standards Start Printed Page 17383Office (ACE-111), Small Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone (816) 329-4132.End Further Info End Preamble Start Supplemental Information
On November 21, 2007, Spectrum Aeronautical, LLC applied for a type certificate for their new model 40 airplane. The model 40 (S-40) airplane is a 2+9 (pilots + passengers) conventionally configured low wing normal category twin-engine jet airplane manufactured primarily from advanced carbon fiber composite materials. The model S-40 is designed to be certified for a single pilot operation for day, night, VFR, IFR and flight into known icing operations at altitudes up to 45,000 feet. The company will show compliance with Reduced Vertical Separation Minimums (RVSM) requirements. Spectrum proposes to utilize lithium polymer (Li-Poly) batteries for emergency, main, and auxiliary power unit (APU) on the model S-40 airplane.
Type Certification Basis
Under the provisions of 14 CFR part 21, § 21.17, Spectrum Aeronautical, LLC must show that the model S-40 meets the applicable provisions of part 23, as amended by Amendments 23-1 through 23-57 thereto.
In addition, the certification basis includes certain special conditions, and exemptions that are not relevant to these special conditions.
In addition to the applicable airworthiness regulations and special conditions, the S-40 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.”
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 model S-40 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 § 21.17(a)(2).
Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same or similar novel or unusual design feature, the special conditions would also apply to the other model under § 21.101.
Novel or Unusual Design Features
The Spectrum S-40 will incorporate the following novel or unusual design features: Spectrum proposes to utilize lithium polymer (Li-Poly) batteries for emergency, main, and auxiliary power unit (APU) on the Spectrum S-40 airplane model. This type of battery possesses certain failure and operational characteristics, and maintenance requirements that differ significantly from that of the nickel cadmium (Ni-Cd) and lead acid rechargeable batteries currently approved for installation in small airplanes. Current regulations in 14 CFR part 23 do not address installation of Li-Poly batteries. This special condition is being proposed to require that all characteristics of the Li-Poly battery and its installation that could affect safe operation of the Spectrum S-40 airplane are addressed, along with establishing that appropriate maintenance requirements must be provided to ensure electrical power is available from the batteries when needed.
Discussion of Comments
Notice of proposed special conditions No. 23-08-05-SC for the Spectrum Aeronautical, LLC Model 40 (S-40) airplanes was published on December 2, 2008 (73 FR 73195). No comments were received, and the special conditions are adopted as proposed except for paragraphs (8), (9), and (10). In paragraph (8), we added the words “state of charge” to indicate the condition of the batteries. In paragraph (9), we added the word “manufacturer's” to indicate which maintenance manual we were discussing. Finally, in paragraph (10), we reworded the paragraph to clarify the intent.
As discussed above, these special conditions are applicable to the Spectrum S-40. Should Spectrum Aeronautical LLC apply at a later date for a change to the type certificate to include another model on the same type certificate incorporating the same novel or unusual design feature, the special conditions would apply to that model as well.
This action affects only certain novel or unusual design features on one model of airplane. 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.Start List of Subjects
List of Subjects in 14 CFR Part 23End List of Subjects Start Amendment Part
The authority citation for these special conditions is as follows:End Amendment Part
The Special ConditionsStart Amendment Part
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 Spectrum Aeronautical, LLC model S-40 airplanes.End Amendment Part
Spectrum Aeronautical, LLC Model 40 Lithium Polymer Battery Installation
In lieu of the requirements of 14 CFR part 23, § 23.1353(a) through (e), lithium polymer batteries and battery installations on the Spectrum S-40 airplane 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-Poly battery installation must be designed to preclude explosion or fire in the event of those failures.
(2) Li-Poly 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-Poly 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-Poly batteries that contain flammable fluids must comply with the flammable fluid fire protection requirements of 14 CFR part 23, § 23.863(a) through (d).
(5) No corrosive fluids or gasses that may escape from any Li-Poly battery may damage surrounding airplane structure or adjacent essential equipment.
(6) Each Li-Poly 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-Poly battery installations must have a system to control the charging Start Printed Page 17384rate of the battery automatically, so as to prevent battery overheating or overcharging, and
(i) 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,
(ii) 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-Poly 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 of the batteries have fallen below levels considered acceptable for dispatch of the airplane.
(9) The Instructions for Continued Airworthiness (ICAW) must contain recommended manufacturer's maintenance and inspection requirements to ensure that batteries, including single cells, meet a safety function level essential to the aircraft's continued airworthiness.
(i) The ICAW must contain operating instructions and equipment limitations in an installation maintenance manual.
(ii) The ICAW must contain installation procedures and limitation 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 limitation must identify any unique aspects of the installation.
(iii) The ICAW must contain corrective maintenance procedures to functionally check battery capacity at manufacturers recommended inspection intervals.
(iv) The ICAW must contain scheduled servicing information to replace batteries at manufacturers recommended replacement time.
(v) The ICAW must contain maintenance inspection requirements to visually check for a battery and/or charger degradation.
(10) The ICAW must contain maintenance procedures to check, at manufacturer's recommended inspection intervals, the function of any batteries in a rotating stock (spares) that experience degraded charge retention capability or other damage due to prolonged storage.
(11) System Safety Assessment process should address the software and complex hardware levels for the sensing, monitoring and warning systems, if these systems contain complex devices. The functional hazard assessment (FHA) for the system is required based on the intended functions described. The criticality of the specific functions will be determined by the safety assessment process for compliance with 14 CFR part 23, § 23.1309, and Advisory Circular 23.1309-1C contains acceptable means for accomplishing this requirement. For determining the failure condition, the criticality of a function will include the mitigating factors. The failure conditions must address the loss of function and improper operations.
It should be noted that these special conditions are not intended to replace 14 CFR part 23, § 23.1353 in the certification basis of the Spectrum model S-40 airplanes. The special conditions apply only to Li-Poly batteries and battery installations. The battery requirements of 14 CFR part 23, § 23.1353 would remain in effect for batteries and battery installations on the Spectrum airplane that do not utilize Li-Poly chemistry.Start Signature
Issued in Kansas City, Missouri on April 7, 2009.
Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-8582 Filed 4-14-09; 8:45 am]
BILLING CODE 4910-13-P