[Federal Register Volume 67, Number 47 (Monday, March 11, 2002)]
[Proposed Rules]
[Pages 10858-10859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-5812]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. CE166; Notice No. 23-01-03-SC]


Special Conditions: CAP Aviation, Model CAP 222; Structural 
Design & Loads Criteria

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

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SUMMARY: This notice proposes special conditions for the CAP Aviation 
Model No. 222 airplane. This airplane will have a novel or unusual 
design feature(s) associated with structural design and loads criteria. 
The applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. These proposed 
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: Comments must be received on or before July 9, 2002.

ADDRESSES: Comments on this proposal may be mailed in duplicate to: 
Federal Aviation Administration, Regional Counsel, ACE-7, Attention: 
Rules Docket, Docket No. CE166, 901 Locust, Room 506, Kansas City, 
Missouri 64106, or delivered in duplicate to the Regional Counsel at 
the above address. Comments must be marked: Docket No. CE166. Comments 
may be inspected in the Rules Docket weekdays, except Federal holidays, 
between 7:30 a.m. and 4 p.m.

FOR FURTHER INFORMATION CONTACT: Mr. Mike Reyer, Federal Aviation 
Administration, Aircraft Certification Service, Small Airplane 
Directorate, ACE-111, 901 Locust, Kansas City, Missouri, 816-329-4131, 
fax 816-329-4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of 
these proposed special conditions by submitting such written data, 
views, or arguments as they may desire. Communications should identify 
the regulatory docket or notice number and be submitted in duplicate to 
the address specified above. All communications received on or before 
the closing date for comments will be considered by the Administrator. 
The proposals described in this notice may be changed in light of the 
comments received. All comments received will be available in the Rules 
Docket for examination by interested persons, both before and after the 
closing date for comments. A report summarizing each substantive public 
contact with FAA personnel concerning this rulemaking will be filed in 
the docket. Persons wishing the FAA to acknowledge receipt of their 
comments submitted in response to this notice must include with those 
comments a self-addressed, stamped postcard on which the following 
statement is made: ``Comments to CE166.'' The postcard will be date 
stamped and returned to the commenter.

Background

    On January 28, 2001, CAP Aviation applied for a type certificate 
for their new Model CAP 222. The CAP 222 is a two-place tandem seat, 
all carbon fiber composite made (wing and fuselage) low wing with no 
high lift devices. It is a fixed gear, unpressurized MTOW 1,600 pound 
airplane with aerobatic capabilities from -10g to +10g and a roll rate 
of 500 degrees per second. A single 200 horsepower Textron-Lycoming 
AEIO-360-A1E engine and two-bladed MT propeller, type MTV-12-B-C/C-183-
17e, comprise the propulsion system.
    Since the airplane is designed for high performance acrobatic 
maneuvers with a design flight envelope of +10g, special conditions are 
required to address the expanded flight envelope. Current 14 CFR Part 
23 acrobatic category design requires that the flight envelope shall 
not be less than +6.0g, -3.0g.

Type Certification Basis

    Under the provisions of 14 CFR Sec. 21.17, Sec. 21.29, and 
Sec. 21.183(c), CAP Aviation must show that the CAP Model 222 meets the 
applicable provisions of part 23, as amended by Amendments 23-1 through 
23-53; 14 CFR part 36, effective December 1, 1969, including amendments 
36-1 through the amendment effective on the date of type certification. 
In addition, the certification basis includes exemptions, if any, 
equivalent level of safety findings, if any, and the special conditions 
adopted by this rulemaking action.
    If the Administrator finds that the applicable airworthiness 
regulations (i.e., part 23) do not contain adequate or appropriate 
safety standards for the CAP Model 222 because of a novel or unusual 
design feature, special conditions are prescribed under the provisions 
of Sec. 21.16.
    Special conditions, as appropriate, 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 CAP Model 222 will incorporate the following novel or unusual 
design features:

[[Page 10859]]

Structural Design and Loads Criteria

    An analysis of world championship acrobatic sequences shows a 
significant number of occurrences of high load factors up to 
10g.

Wing

    For airplanes capable of performing ``flick rolls'' (snap rolls), 
the wing should be designed for 100/0 percent maximum wing load 
distribution, in addition to the roll maneuver criteria of 
Sec. 23.349(b), unless lower values can be substantiated. These load 
conditions are based on a VA and Cr max 
corresponding to the selected positive 10g design load factor. 
Unbalanced aerodynamic moments about the center of gravity must be 
reacted in a rational or conservative manner, considering the principal 
masses furnishing the reacting inertia forces. Furthermore, 
consideration should be given to the fact that pilots may make 
significant aileron control input above VA; therefore, a 
warning prohibiting unrestricted control system input above 
VA should be included in the Pilot Operating Handbook/
Airplane Flight Manual (POH/AFM) and on a cockpit placard.

Empennage

    For airplanes capable of performing ``flick rolls'' (snap rolls), 
the empennage should be designed for 100/0 percent maximum load 
distribution unless lower values can be substantiated. The use of 
rational flight test results is preferred as a basis for design. Pilots 
may make significant rudder and elevator controls inputs above 
VA, therefore, adequate pilot warnings such as discussed 
above are necessary.
    Rational chord load distributions should be used for the vertical 
and horizontal tail surfaces. These may be developed by flight test 
data, wind tunnel test data, theoretical analysis, or a combination 
thereof.

Gyroscopic Forces

    Since the airplane will be performing maneuvers that generate high 
pitch and yaw rates, the airplane, including the engine, engine mount, 
and fuselage attachment, must be designed for rational gyroscopic 
forces generated in specific acrobatic maneuvers.

Fatigue

    The fatigue load should be developed from representative sequences 
and cross country flight profiles.

Applicability

    As discussed above, these special conditions are applicable to the 
Model CAP 222. Should CAP Aviation 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).

Conclusion

    This action affects only certain novel or unusual design features 
on the CAP Model 222 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 11.28 and 11.29(b).

The Proposed Special Conditions

    Accordingly, the Federal Aviation Administration (FAA) proposes the 
following special conditions as part of the type certification basis 
for CAP Model 222 airplanes.

Structural Design and Loads Criteria

    1. Wing. For the ``flick roll'' condition in Sec. 23.347(b), a 100/
0 percent wing load distribution should be used for wing design. 
Accurate flight test load measurements may be used in lieu of the 100/0 
percent maximum airload distribution. A notation shall be placed in the 
Limitations Section of the POH/AFM, and an appropriate warning placard 
shall be installed on the main instrument panel prohibiting full or 
abrupt control inputs above VA.
    2. Empennage. The horizontal tail and its attachments to the 
fuselage, and the aft fuselage must be designed for the worst case load 
condition using either accurate flight test load measurements or an 
acceptable analytical method. Unsymmetrical load combinations acting on 
the wing and on the horizontal tail are assumed to be turning the 
airplane in the same direction around the roll axis. A notation shall 
be placed in the limitation section of the POH/AFM, and an appropriate 
warning placard shall be installed on the main instrument panel 
prohibiting full or abrupt control inputs above VA. Rational 
chord load distributions should be used for the vertical and horizontal 
tail surfaces. Appropriate data must be used to develop unsymmetrical 
loading of the horizontal tail surface and as a basis for fuselage 
torsion. This must include simultaneous application of full rudder and 
elevator input.
    3. Gyroscopic Forces. The airplane, including the engine, engine 
mount, and fuselage attachment, must be designed for rational 
gyroscopic forces generated in acrobatic maneuvers.
    4. Fatigue. Representative acrobatic sequences and cross-country 
flight profiles must be used in establishing a rational fatigue load 
spectrum.

    Issued in Kansas City, Missouri on February 21, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-5812 Filed 3-8-02; 8:45 am]
BILLING CODE 4910-13-U