[Federal Register Volume 60, Number 53 (Monday, March 20, 1995)]
[Proposed Rules]
[Pages 14698-14701]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-6688]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. 123CE, Notice No. SC-23-ACE-80]
Special Conditions; SIAI Marchetti Model S211A Airplane
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed special conditions.
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SUMMARY: This notice proposes special conditions for the SIAI Marchetti
Aircraft Company Model S211A airplanes. These airplanes will have novel
and unusual design features when compared to the state of technology
envisaged in the applicable airworthiness standards. These design
features include performance characteristics for which the applicable
regulations do not contain adequate or appropriate airworthiness
standards. This notice contains the additional airworthiness standards
that the Administrator considers necessary to establish a level of
safety equivalent to that provided by the current airworthiness
standards.
DATES: Comments must be received on or before May 19, 1995.
ADDRESSES: Comments on this proposal may be mailed in duplicate to:
Federal Aviation Administration, Office of the Assistant Chief Counsel,
ACE-7, Attention: Rules Docket Clerk, Docket No. 123CE, Room 1558, 601
East 12th Street, Kansas City, Missouri 64106. All comments must be
marked: Docket No. 123CE. Comments may be inspected in the Rules Docket
weekdays, except Federal holidays, between 7:30 and 4:00 p.m.
FOR FURTHER INFORMATION CONTACT:
Mike Downs, Aerospace Engineer, Standards Office (ACE-110), Small
Airplane Directorate, Aircraft Certification Service, Federal Aviation
Administration, 601 East 12th Street, Kansas City, Missouri 64106;
telephone (816) 426-5688.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of
these 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 specified above will be considered by the
Administrator before taking further rulemaking action on this proposal.
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 Docket No. 123CE.'' The postcard will be date stamped and returned
to the commenter. The proposals contained in this notice may be changed
in light of the comments received. All comments received will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested parties. A report
summarizing each substantive public contact with FAA personnel
concerned with this rulemaking will be filed in the docket.
Background
On July 9, 1993, the SIAI Marchetti Aircraft Co., VIA Indipendenza,
2, 21018 Sesto Calende (VA) [ITALY] made application for acrobatic
category type certification of the model S211A airplane. The S211A is a
two-place (tendem), all metal, mid-wing cantilevered, retractable gear,
pressurized, single turbofan engine airplane with a maximum weight of
6,394 pounds intended for specialized military operations as a 14 CFR
Part 23 airplane in the Acrobatic Category.
Type Certification Basis
Type certification basis of the SIAI Marchetti Model S211A airplane
is as follows: Federal Aviation Regulations (14 CFR Part 23), effective
February 1, 1965, through amendment 23-44, effective August 18, 1993;
Special Conditions in lieu of Part 23, amendment 23-44, as stated in
this document; Equivalent Level of Safety for Secs. 23.562, 23.677(a),
23.777(f)(1), 23.807(b)(5), 23.841 (a) and (b)(6), 23.971 (a) and (b),
23.1182, 23.1557(d); 14 CFR Part 34, effective September 10, 1990; 14
CFR Part 36, effective December 1, 1969, through amendment effective on
the date of type certification; exemptions if any; and any special
conditions that may result from this notice.
Discussion
SIAI Marchetti plans to incorporate certain novel and unusual
design features into the airplane for which the airworthiness
regulations do not contain adequate or appropriate safety standards.
These features include certain performance characteristics necessary
for this type of airplane that were not envisaged by the existing
regulations.
Special conditions may be issued and amended, as necessary, as part
of the type certification basis if the Administrator finds that the
airworthiness standards designated in accordance with 14 CFR Part 21,
Sec. 21.17(a)(1) do not contain adequate or appropriate safety
standards because of novel or unusual design features of an airplane.
Special conditions, as appropriate, are issued in accordance with 14
CFR Part 11, Sec. 11.49 after public notice, as required by Secs. 11.28
and 11.29(b), effective October 14, 1980, and become a part of the type
certification basis, as provided by 14 CFR Part 21, Sec. 21.17(a)(2).
Flight
Current standards in 14 CFR Part 23 did not envisage this type of
airplane and the associated performance capabilities. Based upon the
knowledge and experience gained during certification and operation of
previous 14 CFR Part 23 acrobatic jet airplanes and other acrobatic
airplanes, special conditions that include selected Joint Airworthiness
Regulations (JAR) 23, Issue 1, dated March 11, 1994, are proposed
instead of selected performance requirements of subpart B of part 23.
Operating Limitations and Information
Current standards in part 23 did not envisage this type of airplane
and the associated performance.
To maintain a level of safety consistent with other acrobatic
category and jet powered airplanes, special conditions that include
selected JAR 23, Issue 1, dated March 11, 1994, are proposed instead of
the flight manual requirements of subpart G of Part 23.
Conclusion
In view of the design features and operational envelope discussed
for the [[Page 14699]] Model S211A airplane, the following special
conditions are proposed. This action is not a rule of general
applicability and affects only the model of airplane identified in
these proposed special conditions.
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: Secs. 313(a), 601 and 603 of the Federal Aviation Act
of 1958; as amended (49 U.S.C. 1354(a), 1421, and 1423), 49 U.S.C.
106(g); 14 CFR 21.16 ad 21.17; and 14 CFR 11.28 and 11.29(b).
The Proposed Special Conditions
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes the
following special conditions as part of the type certification basis
for the SIAI Marchetti Model S211A airplane.
1. Flight
Instead of compliance with the sections listed below contained in
subpart b of part 23, the following sections apply:
SC23.45 Performance--General.
(a) The performance requirements of this subpart must be met
for: Still air; and Ambient atmospheric conditions.
(b) Unless otherwise prescribed, performance data must be
provided over not less than the following ranges of conditions:
(1) Airport altitude from sea level to 10,000 feet; and
(2) Temperature from standard to 30 deg.C above standard, or the
maximum ambient atmospheric temperature at which compliance with the
cooling provisions 14 CFR Part 23, Secs. 23.1041 to 23.1045 is
shown, if lower.
(c) Performance data must be determined with the means for
controlling the engine cooling air supply in the position used in
the cooling tests required by Secs. 23.1041 to 23.1045.
(d) The available propulsive thrust must correspond to engine
thrust not exceeding the approved thrust, less:
(1) Installation losses; and
(2) The equivalent thrust absorbed by the accessories and
services appropriate to the particular flight condition.
(e) The performance as affected by engine thrust must be based
on a relative humidity of--
(1) 80 percent at and below standard temperature; and
(2) 34 percent at and above standard temperature plus 50 deg.F.
Between the two temperatures the relative humidity must vary
linearly.
(f) Unless otherwise prescribed in determining the takeoff and
landing distances, changes in the airplane's configuration, speed
and thrust must be made in accordance with procedures established by
the applicant for operation in service. The procedures must be able
to be executed consistently by pilots of average skill in
atmospheric conditions reasonably expected to be encountered in
service.
(g) The takeoff and landing distances must be determined on a
smooth dry hard-surfaced runway. The effect on these distances of
operation on other types of surface (for example, grass, gravel)
when dry, may be derived and these surfaces listed under
SC23.1583(o).
SC23.51 Takeoff speeds.
(a) The rotation speed VR, is the speed at which the pilot
makes a control input with the intention of lifting the airplane out
of contact with the runway. VR must not be less than VSl.
(b) The speed at 50 feet must not be less than the highest of--
(1) A speed that is shown to be safe under all reasonably
expected conditions, including turbulence and complete engine
failure; or
(2) 1.20 VSl
SC23.53 Takeoff distance.
(a) The takeoff distance must be determined in accordance with
subparagraph (b), using speeds determined in accordance with SC23.51
(a) and (b).
(b) The distance required to takeoff and climb to a height of 50
feet above the takeoff surface must be determined for each weight,
altitude an temperature within the operational limits established
for takeoff with--
(1) Takeoff thrust;
(2) Wing flaps in the takeoff position(s); and
(3) Landing gear extended.
SC23.63 Climb: General.
(a) Compliance with the requirements of SC23.65, SC23.69, and
SC23.77 must be shown:
(1) Out of ground effect; and
(2) At speeds that are not less than those at which compliance
with the powerplant cooling requirements of Secs. 23.1041 to 23.1045
have been demonstrated.
(b) Compliance must be shown, at weights, as a function of
airport altitude and ambient temperature, within the operational
limits established for takeoff and landing respectively, with--
(1) SC23.65 for takeoff; and
(2) SC23.77 for landing.
SC23.65 Climb: All engines operating.
The airplane must have a steady gradient of climb after takeoff
of at least 4 percent with--
(a) Takeoff thrust;
(b) Landing gear extended except that, if the landing gear can
be retracted in not more than 7 seconds, it may be assumed to be
retracted;
(c) Wing flaps in the takeoff position(s); and
(d) A climb speed not less than 1.2 VS1.
SC23.69 Enroute climb/descent.
(a) All engines operating.
The steady gradient and rate of climb must be determined at each
weight, altitude and ambient temperature within the operational
limits established by the applicant with--
(1) Not more than maximum continuous thrust;
(2) Landing gear retracted;
(3) Wing flaps retracted; and
(4) Climb speed not less than 1.3 VS1.
SC23.71 Glide (Single Engine Airplanes).
The maximum horizontal distance traveled in still air, in
nautical miles per 1,000 feet of altitude lost in a glide, and the
speed necessary to achieve this, must be determined with the engine
inoperative and with the landing gear and wing flaps in the most
favorable position available.
SC23.73 Reference landing approach speed.
The reference landing approach speed, VREF, must not be
less than 1.3 VSO.
SC23.75 Landing distance.
The horizontal distance necessary to land and come to a complete
stop from a point 50 feet above the landing surface must be
determined, for standard temperatures at each weight and altitude
within the operational limits established for landing, as follows:
(a) A steady approach at not less than VREF must be
maintained down to the 50-foot height and
(1) The steady approach must be at a gradient or descent not
greater than 5.2 percent (3 degrees) down to the 50-foot height; and
(2) In addition, an applicant may demonstrate by tests that a
maximum steady approach gradient, steeper than 5.2 percent, down to
the 50-foot height is safe. The gradient must be established as an
operating limitation and the information necessary to display the
gradient must be available to the pilot by an appropriate
instrument.
(b) A constant configuration must be maintained throughout the
maneuver.
(c) The landing must be made without excessive vertical
acceleration or tendency to bounce, nose-over, ground loop, or
porpoise.
(d) It must be shown that a safe transition to the balked
landing conditions of SC23.77 can be made from the conditions that
exist at the 50-foot height, at maximum landing weight or the
maximum landing weight for latitude and temperature of
SC23.63(b)(2), as appropriate.
(e) The brakes must not be used so as to cause excessive wear of
brakes or tires.
(f) Retardation means other than wheel brakes may be used if
that means--
(1) Is safe and reliable;
(2) Is used so that consistent results can be expected in
service
SC23.77 Balked landing.
The steady gradient of climb must not be less than 2.5 percent
with--
(a) Not more than the thrust that is available 8 seconds after
initiation of movement of the thrust controls from the minimum
flight idle position;
(b) The landing gear extended;
(c) The wing flaps in the landing position; and [[Page 14700]]
(d) A climb speed equal to VREF, as defined in SC23.73.
2. Operating Limitations and Information
Instead of compliance with the sections listed below contained in
subpart G of part 23, the following sections apply:
Airplane Flight Manual
SC23.1581 General.
(a) An FAA-Approved Airplane Flight Manual must be furnished
with each airplane and it must contain the following:
(1) Information required by SC23.1583 through SC23.1589.
(2) Other information that is necessary for safe operation
because of design, operating or handling characteristics.
(3) Further information necessary to comply with the relevant
operating rules.
(b) Each part of the Airplane Flight Manual containing
information prescribed in SC23.1583 through SC23.1589 must be
approved, segregated, identified, and clearly distinguished from
each unapproved part of that Airplane Flight Manual.
(c) The units used in the Airplane Flight Manual must be the
same as those marked on the appropriate instruments and placards.
(d) All Airplane Flight Manual operational airspeeds must,
unless otherwise stated, be presented as indicated airspeeds.
(e) Provisions must be made for stowing the Airplane Flight
Manual in a suitable fixed container that is readily accessible to
the pilot.
(f) Each Airplane Flight Manual must contain a means for
recording the incorporation of revisions and/or amendments.
SC23.1583 Operating limitations.
The Airplane Flight Manual must contain operating limitations
determined under the applicable regulations, including the
following:
(a) Airspeed limitations.
(1) Information necessary for the marking of the airspeed limits
on the indicator as required in Sec. 23.1545, and the significance
of each of those limits and of the color coding used on the
indicator.
(2) The speeds VO, VLE, and VLO and their
significance.
(b) Powerplant limitations.
(1) Limitations required by Sec. 23.1521.
(2) Explanation of the limitations, when appropriate.
(3) Information necessary for marking the instruments required
by Secs. 23.1549 through 23.1553.
(c) Weight.
(1) The maximum weight; and
(2) The maximum landing weight, if the design landing weight
selected by the applicant is less than the maximum weight.
(3) The maximum takeoff weight for each airport altitude and
ambient temperature within the range selected by the applicant not
exceeding the weight at which the airplane complies with the climb
requirements of SC23.63(b)(1).
(4) The maximum landing weight for each airport altitude and
ambient temperature within the range selected by the applicant not
exceeding the weight at which the airplane complies with the climb
requirements of SC23.63(b)(2).
(5) The maximum zero fuel weight, where relevant.
(d) Center of gravity. The established center of gravity limits.
(e) Maneuvers. The following authorized maneuvers, appropriate
airspeed limitations, and unauthorized maneuvers, as prescribed in
this section:
(1) A list of approved acrobatic flight maneuvers demonstrated
in the type flight tests, together with recommended entry speeds and
any other associated limitations.
(2) Spin recovery procedure established to show compliance with
Sec. 23.221.
(f) Maneuver load factor. The positive and negative limit load
factors in g's.
(g) Minimum flight crew. The number and functions of the minimum
flight crew determined under Sec. 23.1523.
(h) Kinds of operation. A list of the kinds of operation to
which the airplane is limited or from which it is prohibited under
Sec. 23.1525, and also a list of installed equipment that affects
any operating limitation and identification as to the equipment's
required operational status for the kinds of operation for which
approval has been granted.
(i) Maximum operating altitude. The maximum altitude established
under Sec. 23.1527.
(j) Allowable lateral fuel loading. The maximum allowable
lateral fuel loading differential, if less than the maximum
possible.
(k) Baggage 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.
(l) Systems. Any limitations on the use of airplane systems and
equipment.
(m) Ambient temperatures. Where appropriate, maximum and minimum
ambient air temperatures for operation.
(n) Smoking. Any restrictions on smoking in the airplane.
(o) Types of surface. A statement of the types of surface on
which operations may be conducted must be provided.
SC23.1585 Operating procedures.
Information concerning normal, abnormal (if applicable) and
emergency procedures, and other pertinent information necessary for
safe operation and the achievement of the scheduled performance,
must be furnished, including:
(a) An explanation of significant or unusual flight or ground
handling characteristics.
(b) The maximum demonstrated values of crosswind for takeoff and
landing and procedures and information pertinent to operations in
crosswinds.
(c) Procedures, speeds, and configuration(s) for making a normal
takeoff in accordance with SC23.51 and SC23.53 and the subsequent
climb in accordance with SC23.65 and SC26.59.
(d) Procedures for abandoning a takeoff due to engine failure or
other cause.
(e) A recommended speed for flight in rough air. This speed must
be chosen to protect against the occurrence, as a result of gusts,
of structural damage to the airplane and loss of control (for
example, stalling).
(f) Procedures, speeds, and configuration(s) for making a normal
approach and landing in accordance with SC23.73 and SC23.75 and a
transition to the balked landing condition.
(g) Procedures for restarting the engine in flight, including
the effects of altitude.
(h) The procedures, speeds and configurations for a glide
following engine failure in accordance with SC23.71 and the
subsequent forced landing, must be furnished.
(i) For each airplane showing compliance with Sec. 23.1353
(g)(2) or (g)(3), the operating procedures for disconnecting the
battery from its charging source must be furnished.
(j) Information on the total quantity of usable fuel for each
fuel tank and the effect on the unusable fuel quantity as a result
of a failure of any pump, must be furnished.
(k) Procedures for the safe operation of the airplane's systems
and equipment, both in normal use and in the event of malfunction,
must be furnished.
SC23.1587 Performance information.
Unless otherwise prescribed, the following information must be
furnished over the altitude and temperature ranges required by
SC23.45(b):
(a) The stalling speeds VSO, and VS1 with the landing
gear and wing flaps retracted, determined at maximum weight under
Sec. 23.49 and the effect on these stalling speeds of angles of bank
up to 60 degrees.
(b) The takeoff distance, determined under SC23.53 and the type
of runway surface for which it is valid.
(c) The steady rate and gradient of climb with all engines
operating, determined under SC23.69(a).
(d) The landing distance, determined under SC23.75, and the type
of runway surface for which it is valid.
(e) The effect on takeoff and landing distances of operation on
other than smooth hard surfaces, when dry, determined under
SC23.45(g).
(f) The effect on takeoff and landing distances or runway slope
and 50 percent of the headwind component and 150 percent of the
tailwind component.
(g) The steady gradient of climb/descent, determined under
SC23.66.
(h) The glide performance determined under SC23.71.
SC23.1589 Loading information.
The following loading information must be furnished:
(a) The weight and location of each item of equipment that can
easily be removed, relocated, or replaced and that is installed when
the airplane was weighed under Sec. 23.25.
(b) Appropriate loading instructions for each possible loading
condition between the maximum and minimum weights established under
Sec. 23.25, to facilitate the center of gravity remaining within the
limits established under Sec. 23.23.
[[Page 14701]] Issued in Kansas City, Missouri on March 7, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-6688 Filed 3-17-95; 8:45 am]
BILLING CODE 4910-13-M