[Federal Register Volume 66, Number 150 (Friday, August 3, 2001)]
[Rules and Regulations]
[Pages 40580-40581]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-19365]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE165; Special Conditions No. 23-109-SC]


Special Conditions: Ayres Corporation; Model LM 200, 
``Loadmaster''; Flight

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are issued for the Ayres Corporation, 
Model LM 200 airplane. This airplane will have novel or unusual design 
feature(s) associated with centerline thrust. 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: September 4, 2001.

FOR FURTHER INFORMATION CONTACT: Lowell Foster, Federal Aviation 
Administration, Aircraft Certification Service, Small Airplane 
Directorate,

[[Page 40581]]

ACE-111, 901 Locust, Room 301, Kansas City, Missouri, 816-329-4125, fax 
816-329-4090.

SUPPLEMENTARY INFORMATION:   

Background

    On February 9, 2001, Ayres Corporation applied for a type 
certificate for their new Model LM 200 ``Loadmaster.'' The Model LM 200 
operates with a multiengine/single propeller propulsion system and 
fixed landing gear. The system consists of two turbine engines driving 
a single propeller through a combining gearbox. The aircraft is 
conventional, semi-monocoque, aluminum construction with a high 
cantilever wing, fixed gear, mechanical and electro-mechanical 
controls, and it will be unpressurized. Certification will include 
single pilot and IFR operations.
    It is not possible for this airplane to have literal compliance 
with some commuter category flight test regulations. The Model LM 200 
must comply with all commuter category multiengine requirements; 
however, since this propulsion system will result in centerline thrust, 
this airplane will not have a VMC or VMCG. The 
propeller is independent of both or either engine such that, with the 
failure of an engine, the propeller will continue to operate normally 
but with less torque input. The propeller control system does have 
failure modes independent of both engines that need to be considered 
when determining airplane performance. 14 CFR part 23 does not contain 
adequate or appropriate requirements to address a multiengine/single 
propeller design that results in centerline thrust.

Type Certification Basis

    Under the provisions of 14 CFR 21.17, Ayres Corporation must show 
that the Model LM 200 ``Loadmaster'' meets the applicable provisions of 
part 23, as amended by Amendments 23-1 through 23-53, thereto.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., part 23) do not contain adequate or appropriate 
safety standards for the Ayres Corporation Model LM 200 ``Loadmaster'' 
because of a novel or unusual design feature, special conditions are 
prescribed under the provisions of Sec. 21.16.
    In addition to the applicable airworthiness regulations and special 
conditions, the Model LM 200 must comply with the part 23 fuel vent and 
exhaust emission requirements of 14 CFR part 34 and the part 23 noise 
certification requirements of 14 CFR part 36, and the FAA must issue a 
finding of regulatory adequacy pursuant to section 611 of Public Law 
92-574, the ``Noise Control Act of 1972.''
    Special conditions, as appropriate, as defined in 11.19, are issued 
in accordance with Sec. 11.38, and become part of the type 
certification basis in accordance with Sec. 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 novel or 
unusual design feature, the special conditions would also apply to the 
other model under the provisions of Sec. 21.101(a)(1).

Novel or Unusual Design Features

    The Model LM 200 will incorporate the following novel or unusual 
design features: The Model LM 200 will operate with a multiengine/
single propeller propulsion system.

Applicability

    As discussed above, these special conditions are applicable to the 
Model LM 200. Should Ayres Corporation 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 under the provisions of Sec. 21.101(a)(1).

Discussion of Comments

    Notice of proposed special conditions No. 23-01-02-SC for the Ayres 
Corporation Model LM 200 ``Loadmaster'' airplane was published on May 
8, 2001 (66 FR 23199). No comments were received, and the special 
conditions are adopted as proposed.

Conclusion

    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.

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 
21.17; and 14 CFR 11.38 and 11.19.

The Special Conditions

    Accordingly, as delegated to me by the Administrator, the 
following special conditions are issued as part of the type 
certification basis for the Ayres Corporation Model LM 200 
airplanes.

Flight Test Special Conditions

    1. In addition to the requirements in Sec. 23.51(c)(1)(i), VEF 
is also a propeller control system failure speed where the propeller 
primary control system fails to the configuration most critical to 
producing thrust, considering all single point failures. The 
applicant must establish VEF to be related to the stall 
speed, and it must not be less than 1.05 VS1 or greater 
than 1.2 VS1.
    2. In addition to the requirements in Sec. 23.51(c)(3), to 
determine a single value for VR, the applicant must 
determine and use the most critical of either the one engine 
inoperative (OEI) configuration or the most critical failed 
propeller primary control system configuration, whichever is worse. 
The failed propeller control system configuration must consider all 
single point failures with both engines operating normally.
    3. In addition to the requirement in Sec. 23.51(c)(5), the 
applicant must determine and use the most critical of either the OEI 
configuration or the most critical failed propeller primary control 
system configuration, whichever is worse. The failed propeller 
control system must consider all single point failures, with both 
engines operating normally.
    4. In Sec. 23.63, where the OEI configuration is required, the 
applicant must also assume the condition where both engines are 
operating normally and the propeller primary control system has 
failed. In the failed propeller primary control system 
configuration, the applicant must consider all single point failures 
that result in a propeller configuration most critical to producing 
thrust.
    5. In addition to the requirements in Sec. 23.75(g), the 
applicant must also determine the increase in landing distance due 
to failure of the propeller primary control system. This 
configuration includes both engines operating normally and the 
propeller primary control system failed to the most critical thrust 
producing condition considering all single point failures.

    Issued in Kansas City, Missouri on July 16, 2001.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 01-19365 Filed 8-2-01; 8:45 am]
BILLING CODE 4910-13-P