[Federal Register Volume 60, Number 126 (Friday, June 30, 1995)]
[Rules and Regulations]
[Pages 34104-34107]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-16163]



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[[Page 34105]]


DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. 123CE, Special Condition 23-ACE-80]


Special Conditions; SIAI Marchetti Model S211A Airplane

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

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SUMMARY: These special conditions are being issued 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. These special conditions contain the 
additional airworthiness standards that the Administrator considers 
necessary to establish a level of safety equivalent to that provided by 
the current airworthiness standards.

EFFECTIVE DATE: June 16, 1995.

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: 

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 (tandem), 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; 
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 the special conditions 
adopted by this rulemaking action.

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 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.

Discussion of Comments

    Notice of Proposed Special Conditions, Notice No. 23-ACE-80, was 
published in the Federal Register on March 20, 1995, and no comments 
were received. These special conditions are adopted as proposed with 
minor editorial corrections.
    Under standard practice, the effective date of these special 
conditions would be 30 days after publication in the Federal Register. 
As the intended U.S. type certification date for the SIAI Marchetti 
Model S211A is imminent, the FAA finds that good cause exists to make 
these special conditions effective upon issuance.

Conclusion

    This action is not a rule of general applicability and affects only 
the model of airplane and the manufacturer identified in these 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 and 21.17; and 14 CFR 11.28 and 11.49.

Adoption of Special Conditions

    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 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 ambient atmospheric 
conditions and the particular flight condition. 

[[Page 34106]]

    (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 VS1.
    (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 VS1.


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 take off and climb to a height of 
50 feet above the takeoff surface must be determined for each 
weight, altitude and temperature within the operational limits 
established for takeoff with--
    (1) Takeoff thrust;
    (2) Wing flaps in the takeoff positions(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) Act 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 study 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 study 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 altitude 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
    (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 form 
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.

[[Page 34107]]

    (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.


Sec. 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.

    Issued in Kansas City, Missouri on June 16, 1995.
Henry A. Armstrong,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 95-16163 Filed 6-29-95; 8:45 am]
BILLING CODE 4910-13-M