[Federal Register Volume 73, Number 2 (Thursday, January 3, 2008)]
[Rules and Regulations]
[Pages 389-394]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-25466]
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Rules and Regulations
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Federal Register / Vol. 73, No. 2 / Thursday, January 3, 2008 / Rules
and Regulations
[[Page 389]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 23
[Docket No. CE273; Special Conditions 23-213-SC
Special Conditions; Adam Aircraft Industries Model A700; External
Fuel Tank Protection During Gear-Up or Emergency Landing
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final special conditions.
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SUMMARY: These special conditions are issued for the Adam Aircraft
Industries Model A700 airplane. This airplane will have a novel or
unusual design feature(s) associated with an External Centerline Fuel
Tank (ECFT) that increases the total capacity of fuel by 184 gallons.
The tank is located below the fuselage pressure shell immediately below
the wing. The Adam A700 ECFT is a novel, unusual and a potentially
unsafe design feature that may pose a hazard to the occupants during a
gear-up or emergency landing due to fuel leakage and subsequent fire.
Traditional aircraft construction places the fuel tanks in a protected
area within the wings and/or fuselage. Fuel tanks located in these
areas are well above the fuselage skin and are inherently protected by
the wing and fuselage structure. 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.
DATES: Effective Date: December 26, 2007.
FOR FURTHER INFORMATION CONTACT: Peter L. Rouse, Federal Aviation
Administration, Aircraft Certification Service, Small Airplane
Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri
64106; 816-329-4135, fax 816-329-4090.
SUPPLEMENTARY INFORMATION:
Background
On April 12, 2004, Adam Aircraft Industries applied for a type
certificate for their new model A700. The model A700 aircraft is a 6-8
seat pressurized, retractable-gear, carbon composite structure,
airplane with two turbofan engines mounted on the aft fuselage. The
A700 aircraft is a design evolution of the previously certificated Adam
A500, with the aft fuselage mounted turbofan engines replacing the two
centerline thrust, turbocharged, reciprocating engines. To maintain a
max cruise range similar to the A500 and consistent with other aircraft
in the same class as the A700, an external fuel tank located below the
fuselage pressure shell and immediately below the wing, has been
incorporated in to the A700 design. The A700 and its external fuel tank
location are shown in Figure 1:
[GRAPHIC] [TIFF OMITTED] TR03JA08.046
The Adam A700 ECFT is a novel, unusual and a potentially unsafe
design feature that may pose a hazard to the occupants during a gear-up
or emergency landing due to fuel leakage and subsequent fire.
Conventional aircraft construction places the fuel tanks in a protected
area within the wings and/or fuselage. Fuel tanks located in these
areas are well above the fuselage skin and are inherently
[[Page 390]]
protected by the wing and fuselage structure.
The A700 ECFT must meet the inherent qualities associated with the
protection of the fuel system as provided by 14 CFR part 23. The FAA
requires Adam Aircraft to address the following areas with their ECFT
design:
1. Load Path: Conventional design approaches establish independent
load paths from the keel/skid plate to the airframe major structure
where the fuel tanks are isolated from reacting to the gear-up or
emergency landing loads. The A700 ECFT design must react to the gear-up
or emergency landing loads in a similar manner.
2. Fuel Management: Conventional design approaches use fuel tanks
located outside of the wings, or wing centerbox, as auxiliary fuel
tanks, and not primary fuel tanks. The fuel in the auxiliary fuel tanks
is depleted before the primary fuel tanks, thus the auxiliary tanks are
usually empty upon landing. In a similar manner, the A700 ECFT must be
an auxiliary fuel tank, and not primary fuel tank. The A700 must
deplete the fuel in the ECFT before depleting the fuel in the primary
fuel tanks.
3. Location/Geometry: A700 must preclude the scenario where the
fuel tank is the first point of contact with the ground in a gear-up or
emergency landing.
Regulatory Review and Discussion
14 CFR parts 11, 21, 23 and 25 regulations that pertain to the
regulatory authority for special conditions, certification of unsafe
conditions, structural design criteria, testing and location of the
ECFT are Sec. Sec. 11.19, 21.16, 21.21(b)(2), 23.303, 23.473(d),
23.561, 23.721, 23.967, 23.994 and 25.963.
The following rules provide a regulatory framework in which to
apply additional requirements, beyond the existing requirements, in
order to address novel, unusual and potentially unsafe design features.
A special condition is defined in 14 CFR part 11, Sec. 11.19:
Section 11.19
A special condition is a regulation that applies to a particular
aircraft design. The FAA issues special conditions when we find that
the airworthiness regulations for an aircraft, aircraft engine, or
propeller design do not contain adequate or appropriate safety
standards, because of a novel or unusual design feature.
A special condition is applied via the criteria defined in 14 CFR
part 21, Sec. 21.16:
Section 21.16
If the Administrator finds that the airworthiness regulations of
this subchapter do not contain adequate or appropriate safety standards
for an aircraft, aircraft engine, or propeller because of a novel or
unusual design feature of the aircraft, aircraft engine or propeller,
he prescribes special conditions and amendments thereto for the
product. The special conditions are issued in accordance with part 11
of this chapter and contain such safety standards for the aircraft,
aircraft engine or propeller as the Administrator finds necessary to
establish a level of safety equivalent to that established in the
regulations.
An unsafe condition is defined in 14 CFR part 21, Sec.
21.21(b)(2):
Section 21.21
An applicant is entitled to a type certificate for an aircraft in
the normal, utility, acrobatic, commuter, or transport category, or for
a manned free balloon, special class of aircraft, or an aircraft engine
or propeller, if--
(b) The applicant submits the type design, test reports, and
computations necessary to show that the product to be certificated
meets the applicable airworthiness, aircraft noise, fuel venting, and
exhaust emission requirements of the Federal Aviation Regulations and
any special conditions prescribed by the Administrator, and the
Administrator finds--
(2) For an aircraft that no feature or characteristic makes it
unsafe for the category in which certification is requested.
External fuel tank installations below the wing or fuselage were
not envisioned in the development of 14 CFR part 23 fuel tank (and fuel
system) regulations. As such, regulations that are not directly
applicable to conventional fuel tank installations, but related to the
novel, unusual and potentially unsafe design features were reviewed.
The following 14 CFR part 23 certification requirements do contain
regulatory language that can be used to determine the adequate or
appropriate safety standards for novel, unusual and potentially unsafe
design features of the Adam A700 ECFT.
Section 23.303
Unless otherwise provided, a factor of safety of 1.5 must be used.
Section 23.473(d)
The selected limit vertical inertia load factor at the center of
gravity of the airplane for the ground load conditions prescribed in
this subpart may not be less than that which would be obtained when
landing with a descent velocity (V), in feet per second, equal to 4.4
(W/S)1/4 except that this velocity need not be more than 10
feet per second and may not be less than seven feet per second.
Section 23.721
For commuter category airplanes that have a passenger seating
configuration, excluding pilot seats, of 10 or more, the following
general requirements for the landing gear apply:
(a) The main landing-gear system must be designed so that if it
fails due to overloads during takeoff and landing (assuming the
overloads to act in the upward and aft directions), the failure mode is
not likely to cause the spillage of enough fuel from any part of the
fuel system to constitute a fire hazard.
(b) Each airplane must be designed so that, with the airplane under
control, it can be landed on a paved runway with any one or more
landing-gear legs not extended without sustaining a structural
component failure that is likely to cause the spillage of enough fuel
to constitute a fire hazard.
(c) Compliance with the provisions of this section may be shown by
analysis or tests, or both.
14 CFR part 23, Sec. Sec. 23.303 and 23.473(d) relate to the
associated margin of safety required above the limit loading condition
and the required limit ground loading conditions. 14 CFR part 23, Sec.
23.721 is applicable to commuter category airplanes; however, the
intent is to ensure that the failure of the landing gear does not cause
the spillage of enough fuel from any part of the fuel system to
constitute a fire hazard. The location of the ECFT, in direct line
behind the nose landing gear, makes it particularly vulnerable to
failures of the nose landing gear.
14 CFR part 23 contains a limited scope of regulatory requirements
pertaining to fuel tank (and fuel system) protection during a gear-up
or emergency landing. These current regulations pertaining to the fuel
tank (and fuel system) state:
Section 23.561(b)
The structure must be designed to [give each occupant every
reasonable chance of escaping serious injury when--
(1) Proper use is made of seats, safety belts, and shoulder
harnesses provided for in the design;
(2) The occupant experiences the static inertia loads corresponding
to the following ultimate load factors--
(i) Upward, 3.0g for normal, utility, and commuter category
airplanes, or 4.5g for acrobatic category airplanes;
[[Page 391]]
(ii) Forward, 9.0g;
(iii) Sideward, 1.5g; and
(iv) Downward, 6.0g when certification to the emergency exit
provisions of Sec. 23.807(d)(4) is requested; and
(3) The items of mass within the cabin, that could injure an
occupant, experience the static inertia loads corresponding to the
following ultimate load factors--
(i) Upward, 3.0g;
(ii) Forward, 18.0g; and
(iii) Sideward, 4.5g.
Section 23.561(c)
Each airplane with retractable landing gear must be designed to
protect each occupant in a landing--
(1) With the wheels retracted;
(2) With moderate descent velocity; and
(3) Assuming, in the absence of a more rational analysis--
(i) A downward ultimate inertia force of 3g; and
(ii) A coefficient of friction of 0.5 at the ground.
Section 23.967(a)
Each fuel tank must be able to withstand, without failure, the
vibration, inertia, fluid, and structural loads that it may be
subjected to in operation.
Section 23.967(e)
Fuel tanks must be designed, located, and installed so as to retain
fuel:
(1) When subjected to the inertia loads resulting from the ultimate
static load factors prescribed in Sec. 23.561(b)(2) of this part; and
(2) Under conditions likely to occur when the airplane lands on a
paved runway at a normal landing speed under each of the following
conditions:
(i) The airplane in a normal attitude and its landing gear
retracted.
(ii) The most critical landing gear leg collapsed and the other
landing gear legs extended.
Section 23.994
Fuel system components in an engine nacelle or in the fuselage must
be protected from damage which could result in spillage of enough fuel
to constitute a fire hazard as a result of a wheels-up landing on a
paved runway.
The regulatory requirements of Sec. 23.967(e)(1) refer to Sec.
23.561(b)(2), which is an occupant protection rule. The requirements of
Sec. 23.561(b)(2) do not have a downward component for non-commuter
category airplanes. To comply with the requirements of Sec.
23.967(e)(2), the moderate descent velocity identified in Sec.
23.561(c)(2), which is also an occupant protection rule, has been used
as an acceptable means of compliance for traditional fuel tank designs
that do not have novel, unusual and potentially unsafe design features.
These regulations have historically demonstrated an acceptable level of
safety for traditional fuel tank designs that do not have novel,
unusual and potentially unsafe design features. Existing aircraft
designs with this satisfactory service history have the fuel tanks
located well above the fuselage skin and are inherently protected by
the wing and the fuselage structure, thus providing a ``crush zone.''
The intent of 14 CFR part 23, Sec. 23.994 is to minimize the
hazard to the airplane due to fuel system components that are affected
(those which are traditionally located in the fuselage or engine
nacelle) when the underside of the airplane contacts the ground in a
wheels-up landing. The intent is applicable to those components below
the fuselage.
14 CFR part 23 guidance materials recognize that there may be
situations when the installation of an auxiliary fuel tanks will
require special conditions because of a novel, unusual and potentially
unsafe design feature. Advisory Circular (AC) 23-10, Auxiliary Fuel
Systems for Reciprocating and Turbine Powered Part 23 Airplanes, states
in paragraph 5:
5. Certification Basis
a. New Type Certificates. For the issuance of a new type
certificate, an airplane must be shown to comply with the certification
basis established in accordance with Sec. 21.17 of the Federal
Aviation Regulations (FAR). If the regulations do not provide adequate
or appropriate standards because of a novel or unusual design feature,
special conditions will be prescribed in accordance with Sec. 21.16.
c. Unsafe Features or Characteristics. Notwithstanding compliance
with the established certification basis, Sec. 21.21 precludes
approval if there is any feature or characteristic that makes the
airplane unsafe. The applicant should recognize that it may be
necessary, because of such a feature or characteristic, to impose
special requirements which exceed the standards of the certification
basis, to eliminate the unsafe condition.
Since 14 CFR part 23 airworthiness regulations do not contain
adequate or appropriate safety standards for the external fuel tank
design, a review of the safety standards contained in 14 CFR part 25
was conducted to evaluate their applicability to the novel, unusual and
potentially unsafe design feature of the ECFT. 14 CFR part 25, Sec.
25.963 has regulatory requirements that ensure that fuel tanks within
the fuselage contour are in a protected position.
Section 25.963(d)
Fuel tanks within the fuselage contour must be able to resist
rupture, and to retain fuel, under the inertia forces prescribed for
the emergency landing conditions in Sec. 25.561. In addition, these
tanks must be in a protected position so that exposure of the tanks to
scraping action with the ground is unlikely.
Section 25.963(e)(1)
Fuel tank access covers must comply with the following criteria in
order to avoid loss of hazardous quantities of fuel:
(1) All covers located in an area where experience or analysis
indicates a strike is likely must be shown by analysis or tests to
minimize penetration and deformation by tire fragments, low energy
engine debris, or other likely debris.
14 CFR part 25, Sec. 25.963(d) is applicable to transport category
airplanes; however, the intent is to ensure that in the event of an
emergency landing, the fuel tank is in a protected position so that
exposure of the tank to scraping action with the ground is unlikely.
The location of the ECFT, located below the fuselage, makes it
particularly vulnerable to scraping action with the ground in the event
of a gear-up landing.
14 CFR part 25, Sec. 25.963(e) is applicable to transport category
airplanes, and only applies to the access panels; however, the intent
is to prevent a hazard as a result of the impact by tire fragments or
debris. This philosophy would be applied to the ECFT (not just access
panels) to prevent hazardous leakage of fuel in the event of impact
from tire fragments or other likely debris.
14 CFR part 25 guidance materials also recognize the need to
protect the auxiliary fuel tanks beyond the velocities used as an
acceptable means of compliance. The first chapter of AC 25-8, Auxiliary
Fuel Systems Installations, is titled ``Fuel System Installation
Integrity and Crashworthiness'' and the first paragraph states the
following:
``Survivable accidents have occurred at vertical descent velocities
greater than the 5 feet per second (f.p.s.) referenced in Sec. 25.561.
The energy from such descents is absorbed by the structure along the
lower fuselage. As the limits of survivable accidents are approached,
structure under the main
[[Page 392]]
cabin floor is crushed and deformed and the volume below the floor,
where the auxiliary fuel tanks are frequently located, may be reduced
and reshaped. For this reason the tank material chosen by the applicant
should provide resilience and flexibility; or, in the absence of these
characteristics, the tank installation should provide extra clearance
from structure that can be crushed or be protected by primary structure
not likely to be crushed.''
Due to the concern of the Adam A700 ECFT to potentially contact the
ground in a gear-up or emergency landing, we contacted the FAA Office
of Accident Investigation, Safety Analysis Branch to determine the
number of incidents/accidents where an aircraft landed with the landing
gear retracted or the landing gear collapsed on the ground. The search
used was conducted over a 25 year period from January 1982 thru January
2007, and queried all N-registered aircraft that were not 14 CFR parts
121, 135, or 129 and that had at least one of the following occurrence
codes:
Gear Collapsed
Main Gear Collapsed
Nose Gear Collapsed
Tail Gear Collapsed
Complete Gear Collapsed
Other Gear Collapsed
Gear Not Extended
Gear Not Retracted
Gear Retraction On Ground
During the queried timeframe, there were 740 reported incidents/
accidents, which yields an average of 30 reported incidents/accidents
per year. There were no injuries or fatalities associated with the 740
reported incidents/accidents. All of the reported incidents/accidents
involved aircraft having fuel in the center section of the wing area
confined by the front and rear spars and the side of body wing ribs.
The data shows a high probability for a landing gear failure,
malfunction or not being extended during landing and that there is a
good safety record for configurations involved in these incidents/
accidents. The certification standards for the Adam A700 ECFT need to
consider the placement of the ECFT outside of the protective wing area
confined by the front and rear spars and the side of body wing ribs
configurations, and the high probability of the ECFT contacting the
ground.
Because of the Adam A700 ECFT's novel, unusual and potentially
unsafe design features, it is necessary to impose a specific vertical
velocity requirement that exceed the 5 feet per second requirement
normally imposed on conventional airplane fuel tank designs.
Conventionally installed fuel tanks, located within the fuselage and
wing primary structure, have used Sec. 23.561(c)(2) as an acceptable
means of compliance to the requirements of Sec. 23.967(e)(2). Fuel
tank installations are not bound by regulatory requirements to use
Sec. 23.561(c)(2) as an acceptable means of compliance to the
requirements of Sec. 23.967(e)(2). The standards contained in Sec.
23.561(c)(2), which is an occupant protection rule, provided adequate
or appropriate standards for conventionally installed fuel tanks.
Initially, the FAA proposed to use the vertical velocity requirements
(26.8 feet per second) contained in Sec. 23.562 as a means of
compliance to the requirements of Sec. 23.967(e)(2), as this rule is
also an occupant protection rule. The velocities cited in the two
occupant protection rules range from 5 feet per second to 26.8 feet per
second. The velocity cited in Sec. 23.561(c)(2) is the velocity for a
minor crash landing, where the velocity in Sec. 23.562 is the upper
limit of a survivable crash landing. The requirements contained in
Sec. 23.967(e)(2) allow for the conditions likely to occur, and the
range of velocities likely to occur during a survivable crash landing
(5 feet per second--26.8 feet per second). Given that there is a range
of velocities that define a survivable crash landing, there is ample
regulatory room in which to determine an acceptable means of
compliance. The FAA proposal to use the vertical velocity requirements
contained in Sec. 23.562 as a means of compliance to the requirements
of Sec. 23.967(e)(2) for the initially proposed ECFT design, was
withdrawn by the FAA due to Adam Aircraft proposing to redesign the
ECFT. As such, the FAA researched the standards within 14 CFR part 23
to determine a vertical velocity within the range of velocities likely
to occur that provide adequate or appropriate standards, mitigate
potential unsafe conditions, and do not exceed the intent of the rule.
The normal precision approach speed for the Adam A700 will be
approximately 120 KIAS. This approach speed will result in a normal
vertical descent velocity of 10.6 feet per second. The normal precision
approach speed is a speed that falls within the speeds that are likely
to occur when the airplane lands on a paved runway at a normal landing
speed. 14 CFR part 23, Sec. 23.473(d) requires that the aircraft be
able to absorb a limit load imposed by a vertical descent velocity of
10 feet per second for landing conditions. Combining the velocity
requirements of Sec. 23.473(d) and a commensurate 1.5 factor of
safety, as required by Sec. 23.303, would result in a vertical descent
velocity of 12.25 feet per second. The derivation used to determine the
ultimate velocity based upon the Sec. 23.473(d) limit vertical inertia
load and the factor of safety defined in Sec. 23.303 is shown below:
The relationship between velocity, acceleration and distance is
shown by the equation:
V22 = V12 + 2 a d
The relationship between force and acceleration is shown by the
equation:
F = ma
The relationship between limit force (load) and ultimate force
(load) is shown by the equation:
FUltimate = FLimit CFactorofSafety
Assuming a constant mass of the object, an ending velocity of zero
and grouping the terms:
[GRAPHIC] [TIFF OMITTED] TR03JA08.044
Thus, the relationship between limit velocity and ultimate velocity
is shown by the equation:
[GRAPHIC] [TIFF OMITTED] TR03JA08.045
[[Page 393]]
Conventional airplanes with fuel tanks located below the fuselage
are designed such that the ground impact loads are not absorbed by the
tanks. Fuel tanks in these locations are especially vulnerable to these
ground impact loads if design precautions/mitigations are not taken. If
the ECFT is designed such that it absorbs gear-up landing loads, a
gear-up landing could damage the ECFT and result in the spillage of
enough fuel to constitute a fire hazard. The location of the A700 ECFT
must be evaluated for ground impact in a gear-up landing, and design
precautions/mitigations must be taken such that load paths do not go
through the fuel tanks. The location of the A700 ECFT must be evaluated
for exposure of the tank to impact from runway debris or from fragments
emanating from failures of the tires. The location of the ECFT, below
and in direct line behind the nose landing gear, makes it particularly
vulnerable to debris from failures of the nose landing gear tires.
The A700 ECFT, compared to other designs that have fuel tanks
located outside of the wings, was the only design that contained a
significant percentage of the total fuel quantity of fuel below the
fuselage. Existing designs, that have fuel tanks located outside of the
wings, have their relatively smaller percentage of the total fuel
quantity in their lower fuselage tanks and it is transferred out to the
primary fuel tanks, so they are emptied early in the flight. The
existing designs, that have fuel tanks located outside of the wings,
use the fuel tanks below the fuselage as auxiliary fuel tanks, and they
do not feed the engines directly, but rather are used to replenish the
primary fuel tanks. The A700 ECFT design indicates the ECFT is an
auxiliary fuel tank, does not feed the engines directly, but rather is
used to replenish the primary fuel tanks. If the ECFT design is an
auxiliary fuel tank, and it does not feed the engines directly, but
rather is used to replenish the primary fuel tanks, it would provide
mitigation by using the fuel quantity located in the ECFT, thus the
ECFT is emptied early in the flight.
Based on our current understanding of the A700 ECTF design, the FAA
agrees that Adam Aircraft may have provided the following mitigating
design features:
1. The keel and truss assembly that make up the protective
structure in current A700 ECFT design configuration affords the
equivalent level of protection as currently certificated aircraft with
fuel tanks located in the wings, or wing centerbox. The keel and truss
assembly provide a structurally independent load path that does not
transmit the ground impact forces through the ECFT during a gear-up or
emergency landing, and also protects the ECFT from ground contact by
providing protective structure.
2. The ECFT is an auxiliary fuel tank, and it does not feed the
engines directly, but rather is used to replenish the primary fuel
tanks. The fuel in the ECFT will be used before the fuel in the wing
tanks.
The mitigating features offered by Adam Aircraft: independent load
path, fuel management, and location/geometry, coupled with dynamic drop
testing and a subsequent rational structural analysis using static test
results and the dynamic drop test results, provide the FAA with
sufficient justification to reduce the descent velocity from 12.25 feet
per second to no less then 5 feet per second.
Type Certification Basis
Under the provisions of 14 CFR 21.17, Adam Aircraft Industries must
show that the model A700 meets the applicable provisions of 14 CFR part
23, as amended by Amendments 23-1 through 23-55 thereto.
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 model A700 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 model A700 must comply with the fuel vent and
exhaust emission requirements of 14 CFR part 34 and the noise
certification requirements of 14 CFR part 36, and the FAA must issue a
finding of regulatory adequacy pursuant to Sec. 611 of Public Law 92-
574, the ``Noise Control Act of 1972''.
Special conditions, as appropriate, as defined in Sec. 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 A700 will incorporate the following novel or unusual
design features:
External Centerline Fuel Tank (ECFT)
Discussion of Comments
Notice of proposed special conditions No. 23-07-03-SC for the Adam
Aircraft Industries Model A700 airplanes was published in the Federal
Register on Tuesday, September 18, 2007, Vol. 72, No. 180. No comments
were received, and the special conditions are adopted as proposed.
Applicability
As discussed above, these special conditions are applicable to the
Adam Aircraft Industries Model A700. Should Adam Aircraft Industries
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).
[For Final Special Conditions Effective Upon Issuance]
Under standard practice, the effective date of final special
conditions would be 30 days after the date of publication in the
Federal Register; however, as the certification date for the Adam
Aircraft Industries Model A700 is imminent, the FAA finds that good
cause exists to make these special conditions effective upon issuance.
Conclusion
This action affects only certain novel or unusual design features
on one model of airplanes. 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
0
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
0
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 Adam Aircraft Industries Model A700
airplanes.
1. SC 23.561(c): Each airplane with retractable landing gear and
external fuel tank system(s) located beneath the fuselage must be
designed to protect each occupant in a landing--
1. With the wheels retracted;
[[Page 394]]
2. With descent velocity of 12.25 feet per second UNLESS mitigating
design features are incorporated that address:
i. Independent load path
ii. Fuel management
iii. Location/Geometry
iv. Other safety enhancing design features as proposed by the
applicant.
If adequate mitigation is demonstrated for all the above design
features, the FAA will reduce the descent velocity to no less then 5
feet per second; and
3. By defining, based on a rational analysis, supported by tests:
i. A downward ultimate inertia force; and
ii. A coefficient of friction of 0.5, or a rational analysis for a
coefficient of friction, at the ground.
Compliance with SC 23.561(c)(2) will be demonstrated by dynamic
drop test.
2. SC 23.721: The following general requirements for the landing
gear apply:
1. The landing-gear system must be designed so that if it fails due
to overloads during takeoff and landing (assuming the overloads to act
in the upward and aft directions), the failure mode is not likely to
cause the spillage of enough fuel from any part of the external fuel
tank system(s) located beneath the fuselage to constitute a fire
hazard.
2. The airplane must be designed so that, with the airplane under
control, it can be landed on a paved runway with any one or more
landing-gear legs not extended without sustaining a structural
component failure that is likely to cause the spillage of enough fuel
to constitute a fire hazard.
3. Compliance with the provisions of this section may be shown by
analysis or tests, or both.
3. SC 23.994: Fuel system components in external fuel tank
system(s) located beneath the fuselage must be protected from damage
which could result in spillage of enough fuel to constitute a fire
hazard as a result of a wheels-up landing on a paved runway.
4. SC 23.XXX: Fuel tanks within and below the fuselage contour must
be installed in accordance with the requirements prescribed in Sec.
23.967. External fuel tank system(s) located beneath the fuselage must
have the following design mitigations:
1. The external fuel tank system(s) must be in a protected position
so that exposure of the tank to scraping action, or impact, with the
ground is unlikely during a gear-up landing of the most critical
landing gear or landing gears, when landing on a paved runway.
2. The external fuel tank system(s) must be protected by dedicated
protective structure, and the protective structure load paths must be
independent of the fuel system during a gear-up landing of the most
critical landing gear or landing gears, when landing on a paved runway.
3. The hazard to the external fuel tank system(s) that results from
impact by landing gear tire fragments or other likely debris must be
minimized.
4. The fuel management of the external fuel tank system(s) must be
such that fuel in the external fuel tank system(s) is to be emptied
prior to fuel in the main tanks.
Issued in Kansas City, Missouri on December 26, 2007.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-25466 Filed 1-2-08; 8:45 am]
BILLING CODE 4910-13-P