[Federal Register Volume 64, Number 229 (Tuesday, November 30, 1999)]
[Rules and Regulations]
[Pages 66721-66723]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-31041]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE145; Special Conditions No. 23-096A-SC]
Special Conditions: Raytheon Model 390 Airplane
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Amended final special conditions; request for comments.
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SUMMARY: This document amends special conditions issued to the Raytheon
Aircraft Company for the Raytheon Model 390 airplane and requests
comments on the revised portion of the amended special conditions. The
Small Airplane Directorate issued final special conditions for this
airplane on July 9, 1999, and published them on July 23, 1999 (64 FR
39899). The special conditions contained a requirement for operating
limitations for weight and loading distribution already covered by an
exemption issued to Raytheon Aircraft Company on December 12, 1996
(Exemption No. 6558, Docket No. 132CE). Accordingly, the portion of the
special conditions that covers the operating limitations has been
amended to remove the additional requirement. Only the revised sections
are contained in this document.
Additionally, the special condition for turning flight and
accelerated turning stalls has been amended to include a power-at-idle
condition. This condition is included to make these special conditions
consistent with previously approved special conditions for a similar
airplane.
DATES: The effective date of these special conditions is November 15,
1999. Comments must be received on or before December 30, 1999.
ADDRESSES: Comments on these special conditions may be mailed in
duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7,
Attention: Rules Docket CE145, 901 Locust, Room 506, Kansas City,
Missouri 64106; or delivered in duplicate to the Regional Counsel at
the above address. Comments must be marked: CE145. Comments may be
inspected in the Rules Docket weekdays, except Federal holidays,
between 7:30 a.m. and 4:00 p.m.
FOR FURTHER INFORMATION CONTACT: Lowell Foster, Aerospace Engineer,
Standards Office (ACE-110), Small Airplane Directorate, Aircraft
Certification Service, Federal Aviation Administration, Room 301, 901
Locust, Kansas City, Missouri 64106; telephone (816) 329-4125.
SUPPLEMENTARY INFORMATION: The FAA has determined that the substance of
these special conditions has been subject to the public comment process
and those comments were resolved. The FAA therefore finds that good
cause exists for making these special conditions effective upon
issuance.
Comments Invited
Interested persons are invited to submit 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
special conditions 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. Commenters wishing the FAA to acknowledge receipt of their
comments submitted in response to this notice must include a self-
addressed, stamped postcard on which the following statement is made:
``Comments to CE145.'' The postcard will be date stamped and returned
to the commenter.
Background
On August 1, 1995, Raytheon Aircraft Company (then Beech Aircraft
Corporation), 9707 East Central, Wichita, Kansas 67201, applied for a
type certificate for their new Raytheon Model 390 Airplane. The
Raytheon Model 390 has a composite fuselage, a metal wing with 22.8
degrees of leading-edge sweepback, and a combination composite/metal
empennage in a T-tail configuration with trimmable horizontal tail with
27.3 degrees of leading-edge sweepback. The airplane will accommodate
six passengers and a crew of two. The Model 390 will have a
VMO/MMO of 320 knots/m.83, and has two turbofan
engines mounted on the aft fuselage above and behind the wing.
Raytheon plans to incorporate certain novel and unusual design
features into the Model 390 airplane for which the airworthiness
regulations do not contain adequate or appropriate safety standards.
These features include turbofan engines, engine location, swept wings
and stabilizer, and certain performance characteristics necessary for
this type of airplane.
The final special conditions issued for this airplane on July 9,
1999, which were published on July 23, 1999 (64 FR 39899), contained a
requirement covered by an exemption issued to Raytheon Aircraft Company
on December 12, 1996 (Exemption No. 6558, Docket No. 132CE). The Small
Airplane Directorate has amended SC23.1583 in the special conditions to
remove the weight and loading distribution paragraph in the operating
limitations portion of the special condition and to add idle thrust
stalls to be consistent with past policy. The amended version of the
operating limitations and the idle thrust stalls special conditions are
published below.
Type Certification Basis
Under the provisions of 14 CFR part 21, Sec. 21.17, Raytheon
Aircraft Company must show that the Raytheon Model 390 meets the
applicable provisions of 14 CFR part 23, effective February 1, 1965, as
amended by Amendments 23-1 through 23-52, effective July 25, 1996; 14
CFR part 36, effective December 1, 1969, through the amendment
effective on the date of type certification; 14 CFR part 34;
exemptions, if any; and the special conditions adopted by this
rulemaking action.
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 Raytheon Model 390 because of a
novel or unusual design feature,
[[Page 66722]]
special conditions are prescribed under the provisions of Sec. 21.16.
Special conditions, as appropriate, are issued in accordance with
Sec. 11.49 after public notice, as required by Secs. 11.28 and
11.29(b), 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 Raytheon Model 390 will incorporate the following novel or
unusual design features: These features include turbofan engines,
engine location, swept wings and stabilizer, and certain performance
characteristics necessary for this type of airplane. These amended
special conditions only address the operating limitations and the
addition of idle thrust stalls. The remaining features are addressed in
the original special conditions published on July 23, 1999 (64 FR
39899)
Discussion of Previous Comments
A notice of proposed special conditions No. 23-98-01-SC for the
Raytheon Aircraft Company Model 390 airplanes was published on November
2, 1998 (63 FR 58660). Comments on the notice were discussed in the
final version published on July 23, 1999 (64 FR 39899).
Applicability
As discussed above, these amended special conditions are applicable
to the Raytheon Model 390 Airplane. Should Raytheon Aircraft Company
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 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.
The substance of these special conditions has been subjected to the
notice and comment period and those comments were resolved. It is
unlikely that further public comment on the original special conditions
would result in a significant change from the substance contained
herein. For that reason, and since a delay would significantly affect
the certification of the airplane, which is imminent, the FAA has
determined that good cause exists for adopting these special conditions
upon issuance. However, the FAA is requesting comments to the revisions
in the amended special conditions to allow interested persons to submit
such written data, views, or arguments as they may desire.
List of Subjects in 14 CFR Part 23
The authority citation for these special conditions is as follows:
49 U.S.C. 106(g); 40113, 44701, 44702, and 44704; 14 CFR 21.16 and
21.17; and 14 CFR 11.28 and 11.49.
The Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the following amended special conditions are issued as
part of the type certification basis for Raytheon Aircraft Company
Model 390 airplane.
SC23.203 Turning flight and accelerated turning stalls
Instead of compliance with Sec. 23.203(c), the following apply:
(c) Compliance with the requirements of this section must be
shown with:
(1) Flight idle thrust and the thrust necessary to maintain
level flight at 1.6 VS1 (where VS1 corresponds
to the stalling speed with flaps in the approach position, the
landing gear retracted, and maximum landing weight).
(2) Flaps, landing gear, and deceleration devices in any likely
combination of positions.
(3) Trim at 1.4VS1 or at the minimum trim speed,
whichever is higher.
(4) Representative weights within the range for which
certification is requested.
SC23.1583 Operating limitations
Instead of the requirements of Sec. 23.1583, the following
apply:
(a) Airspeed limitations. The following airspeed limitations and
any other airspeed limitations necessary for safe operation must be
furnished:
(1) The maximum operating limit speed, VMO/
MMO, and a statement that this speed limit may not be
deliberately exceeded in any regime of flight (climb, cruise, or
descent) unless a higher speed is authorized for flight test or
pilot training.
(2) If an airspeed limitation is based upon compressibility
effects, a statement to this effect and information as to any
symptoms, the probable behavior of the airplane, and the recommended
recovery procedures.
(3) The maneuvering speed, VO, and a statement that
full application of rudder and aileron controls, as well as
maneuvers that involve angles of attack near the stall, should be
confined to speeds below this value.
(4) The maximum speed for flap extension, VFE, for
the takeoff, approach, and landing positions.
(5) The landing gear operating speed or speeds, VLO.
(6) The landing gear extended speed, VLE if greater
than VLO, and a statement that this is the maximum speed
at which the airplane can be safely flown with the landing gear
extended.
(b) Powerplant limitations. The following information must be
furnished:
(1) Limitations required by Sec. 23.1521.
(2) Explanation of the limitations, when appropriate.
(3) Information necessary for marking the instruments, required
by Sec. 23.1549 through Sec. 23.1553.
(c) Maneuvers. A statement that acrobatic maneuvers, including
spins, are not authorized.
(d) Maneuvering flight load factors. The positive maneuvering
limit load factors for which the structure is proven, described in
terms of accelerations, and a statement that these accelerations
limit the angle of bank in turns and limit the severity of pull-up
maneuvers must be furnished.
(e) Flightcrew. The number and functions of the minimum
flightcrew must be furnished.
(f) Kinds of operation. The kinds of operation (such as VFR,
IFR, day, or night) and the meteorological conditions in which the
airplane may or may not be used must be furnished. Any installed
equipment that affects any operating limitation must be listed and
identified as to operational function.
(g) Additional operating limitations must be established as
follows:
(1) The maximum takeoff weights must be established as the
weights at which compliance is shown with the applicable provisions
of part 23 (including the takeoff climb provisions of special
condition SC23.67(a) through (c) for altitudes and ambient
temperatures).
(2) The maximum landing weights must be established as the
weights at which compliance is shown with the applicable provisions
of part 23 (including the approach climb and balked landing climb
provisions of special conditions SC23.67(d) and SC23.77 for
altitudes and ambient temperatures).
(3) The minimum takeoff distances must be established as the
distances at
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which compliance is shown with the applicable provisions of part 23
(including the provisions of special conditions SC23.55 and SC23.59
for weights, altitudes, temperatures, wind components, and runway
gradients).
(4) The extremes for variable factors (such as altitude,
temperature, wind, and runway gradients) are those at which
compliance with the applicable provision of part 23 and these
special conditions is shown.
(h) Maximum operating altitude. The maximum altitude established
under Sec. 23.1527 must be furnished.
(i) Maximum passenger seating configuration. The maximum
passenger seating configuration must be furnished.
(j) Ambient temperatures. Where appropriate, maximum and minimum
ambient air temperatures for operation.
(k) Allowable lateral fuel loading. The maximum allowable
lateral fuel loading differential, if less than the maximum
possible.
(l) Baggage and cargo loading. The following information for
each baggage and cargo compartment or zone.
(1) The maximum allowable load; and
(2) The maximum intensity of loading.
(m) Systems. Any limitation on the use of airplane systems and
equipment.
(n) Smoking. Any restriction on smoking in the airplane.
Issued in Kansas City, Missouri, on November 15, 1999.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-31041 Filed 11-29-99; 8:45 am]
BILLING CODE 4910-13-P
