23.1551...........................  Oil quantity indicator....  23.1505..............  Instrument markings,
                                                                                control markings, and
                                                                                placards.

23.1553...........................  Fuel quantity indicator...  23.1505..............  Instrument markings,
                                                                                control markings, and
                                                                                placards.
23.1555...........................  Control markings..........  23.1505..............  Instrument markings,
                                                                                control markings, and
                                                                                placards.
23.1557...........................  Miscellaneous marking and   23.1505..............  Instrument markings,
                                     placards.                                          control markings, and
                                                                                placards.
23.1559...........................  Operating limitations       23.1505..............  Instrument markings,
                                     placard.                                           control markings, and
                                                                                placards.
23.1561...........................  Safety equipment..........  23.1505..............  Instrument markings,
                                                                                control markings, and
                                                                                placards.
23.1563...........................  Airspeed placards.........  23.1505..............  Instrument markings,
                                                                                control markings, and
                                                                                placards.
23.1567...........................  Flight maneuver placard...  23.1505..............  Instrument markings,
                                                                                control markings, and
                                                                                placards.
23.1581...........................  Airplane Flight Manual and  23.1510..............  Airplane flight manual.
                                     Approved Manual Material--
                                     General.
23.1583...........................  Operating limitations.....  23.1510..............  Airplane flight manual.
23.1585...........................  Operating procedures......  23.1510..............  Airplane flight manual.
23.1587...........................  Performance information...  23.1510..............  Airplane flight manual.
23.1589...........................  Loading information.......  23.1510..............  Airplane flight manual.
Appendix A........................  Simplified Design Load      Means of Compliance..
                                     Criteria.
Appendix B........................  [Reserved]................  .....................  --Deleted--
Appendix C........................  Basic Landing Conditions..  Means of Compliance..
Appendix D........................  Wheel Spin-Up and Spring-   Means of Compliance..
                                     Back Loads.
Appendix E........................  [Reserved]................  .....................  --Deleted--
Appendix F........................  Test Procedure............  Means of Compliance..
Appendix G........................  Instructions for Continued  Appendix A...........  Instructions for
                                     Airworthiness.                                     Continued Airworthiness.
Appendix H........................  Installation of An          Means of Compliance..
                                     Automatic Power Reserve
                                     (APR) System.
Appendix I........................  Seaplane Loads............  Means of Compliance..
Appendix J........................  HIRF Environments and       Means of Compliance..
                                     Equipment HIRF Test
                                     Levels.
----------------------------------------------------------------------------------------------------------------

Appendix 2 to the Preamble--Abbreviations and Acronyms Frequently Used
in This Document

AD Airworthiness Directive
AFM Airplane Flight Manual
ARC Aviation Rulemaking Committee
ASTM ASTM International
CAA Civil Aviation Authority
CAR Civil Aviation Regulations
Cf Confer (to identify a source or a usage citation for a word or
phrase)
CPS Certification Process Study
CS Certification Specification
CS-VLA Certification Specification--Very Light Aeroplanes
EASA European Aviation Safety Agency
ELOS Equivalent Level of Safety
FR Federal Register
GA General Aviation
HIRF High-Intensity Radiated Field
IFR Instrument Flight Rules
KCAS Knots Calibrated Airspeeds
LOC Loss of Control
NPRM Notice of Proposed Rulemaking
NTSB National Transportation Safety Board
OMB Office of Management and Budget
SAE SAE International
SLD Supercooled Large Droplet
TCDS Type Certificate Data Sheet
VA Design Maneuvering Speed
VC Design Cruising Speed
VD Design Dive Speed
VMC Minimum Control Speed
VMO/MMO Maximum Operating Limit Speed
VFR Visual Flight Rules
VSO Stalling speed or the minimum steady flight speed in the
landing configuration

List of Subjects

14 CFR Part 21

    Aircraft, Aviation safety, Recording and recordkeeping
requirements.

14 CFR Part 23

    Aircraft, Aviation Safety, Signs and symbols.

14 CFR Part 35

    Aircraft, Aviation safety.

14 CFR Part 43

    Aircraft, Aviation safety, Reporting and recordkeeping
requirements.

14 CFR Part 91

    Air traffic control, Aircraft, Airmen, Airports, Aviation safety,
Reporting and recordkeeping requirements.

14 CFR Part 121

    Aircraft, Airmen, Aviation safety, Reporting and recordkeeping
requirements.

14 CFR Part 135

    Aircraft, Airmen, Aviation safety, Reporting and recordkeeping
requirements.

The Proposed Amendment

    In consideration of the foregoing, the Federal Aviation
Administration proposes to amend chapter I of title 14, Code of Federal
Regulations as follows:

PART 21--CERTIFICATION PROCEDURES FOR PRODUCTS AND ARTICLES

0
1. The authority citation for part 21 is revised to read as follows:

    Authority: 42 U.S.C. 7572; 49 U.S.C. 106(f), 106(g), 40105,
40113, 44701-44702, 44704, 44707, 44709, 44711, 44713, 44715, 45303.

0
2. In Sec.  21.9, revise paragraphs (a)(5), (a)(6), (b), and (c)
introductory text, and add paragraph (a)(7) to read as follows:

Sec.  21.9  Replacement and modification articles.

    (a) * * *
    (5) Produced by an owner or operator for maintaining or altering
that owner or operator's product;
    (6) Fabricated by an appropriately rated certificate holder with a
quality system, and consumed in the repair or alteration of a product
or article in

accordance with part 43 of this chapter; or
    (7) Produced in any other manner approved by the FAA.
    (b) Except as provided in paragraphs (a)(1), (a)(2) and (a)(7) of
this section, a person who produces a replacement or modification
article for sale may not represent that part as suitable for
installation on a type-certificated product.
    (c) Except as provided in paragraphs (a)(1), (a)(2) and (a)(7) of
this section, a person may not sell or represent an article as suitable
for installation on an aircraft type-certificated under Sec.
21.25(a)(2) or Sec.  21.27 unless that article--
* * * * *
0
3. In Sec.  21.17, revise paragraph (a) introductory text to read as
follows:

Sec.  21.17  Designation of applicable regulations.

    (a) Except as provided in Sec. Sec.  25.2, 27.2, 29.2, and in parts
26, 34, and 36 of this subchapter, an applicant for a type certificate
must show that the aircraft, aircraft engine, or propeller concerned
meets--
* * * * *
0
4. In Sec.  21.24, revise paragraph (a)(1)(i) to read as follows:

Sec.  21.24  Issuance of type certificate: primary category aircraft.

    (a) * * *
    (1) * * *
    (i) Is unpowered; is an airplane powered by a single, naturally
aspirated engine with a 61-knot or less Vso stall speed as
defined in Sec.  23.49 of this chapter, at amendment 23-62, effective
on Jan 31, 2012; or is a rotorcraft with a 6-pound per square foot main
rotor disc loading limitation, under sea level standard day conditions;
* * * * *
0
5. In Sec.  21.35, revise paragraph (b)(2) to read as follows:

Sec.  21.35  Flight tests.

* * * * *
    (b) * * *
    (2) For aircraft to be certificated under this subchapter, except
gliders, and except for low-speed airplanes, as defined in part 23 of
this chapter, of 6,000 pounds or less maximum weight that are to be
certificated under part 23 of this chapter, to determine whether there
is reasonable assurance that the aircraft, its components, and its
equipment are reliable and function properly.
* * * * *
0
6. In Sec.  21.50, revise paragraph (b) to read as follows:

Sec.  21.50  Instructions for continued airworthiness and
manufacturer's maintenance manuals having airworthiness limitations
sections.

* * * * *
    (b) The holder of a design approval, including either a type
certificate or supplemental type certificate for an aircraft, aircraft
engine, or propeller for which application was made after January 28,
1981, must furnish at least one set of complete Instructions for
Continued Airworthiness to the owner of each type aircraft, aircraft
engine, or propeller upon its delivery, or upon issuance of the first
standard airworthiness certificate for the affected aircraft, whichever
occurs later. The Instructions for Continued Airworthiness must be
prepared in accordance with Sec. Sec.  23.1515, 25.1529, 25.1729,
27.1529, 29.1529, 31.82, 33.4, 35.4, or part 26 of this subchapter, or
as specified in the applicable airworthiness criteria for special
classes of aircraft defined in Sec.  21.17(b), as applicable. If the
holder of a design approval chooses to designate parts as commercial,
it must include in the Instructions for Continued Airworthiness a list
of commercial parts submitted in accordance with the provisions of
paragraph (c) of this section. Thereafter, the holder of a design
approval must make those instructions available to any other person
required by this chapter to comply with any of the terms of those
instructions. In addition, changes to the Instructions for Continued
Airworthiness shall be made available to any person required by this
chapter to comply with any of those instructions.
* * * * *
0
7. In Sec.  21.101 revise paragraphs (b) introductory text, and (c) to
read as follows:

Sec.  21.101  Designation of applicable regulations.

* * * * *
    (b) Except as provided in paragraph (g) of this section, if
paragraphs (b)(1), (2), or (3) of this section apply, an applicant may
show that the change and areas affected by the change comply with an
earlier amendment of a regulation required by paragraph (a) of this
section, and of any other regulation the FAA finds is directly related.
However, the earlier amended regulation may not precede either the
corresponding regulation incorporated by reference in the type
certificate, or any regulation in Sec. Sec.  25.2, 27.2, or Sec.  29.2
of this chapter that is related to the change. The applicant may show
compliance with an earlier amendment of a regulation for any of the
following:
* * * * *
    (c) An applicant for a change to an aircraft (other than a
rotorcraft) of 6,000 pounds or less maximum weight, to a non-turbine
rotorcraft of 3,000 pounds or less maximum weight, to a simple, to a
level 1 low speed, or to a level 2 low speed airplane may show that the
change and areas affected by the change comply with the regulations
incorporated by reference in the type certificate. However, if the FAA
finds that the change is significant in an area, the FAA may designate
compliance with an amendment to the regulation incorporated by
reference in the type certificate that applies to the change and any
regulation that the FAA finds is directly related, unless the FAA also
finds that compliance with that amendment or regulation would not
contribute materially to the level of safety of the product or would be
impractical.
* * * * *
0
8. Revise part 23 to read as follows:

PART 23--AIRWORTHINESS STANDARDS: NORMAL CATEGORY AIRPLANES

Sec.
Subpart A--General
23.1 Applicability and definitions.
23.5 Certification of normal category airplanes.
23.10 Accepted means of compliance.
Subpart B--Flight

Performance

23.100 Weight and center of gravity.
23.105 Performance data.
23.110 Stall speed.
23.115 Takeoff performance.
23.120 Climb requirements.
23.125 Climb information.
23.130 Landing.

Flight Characteristics

23.200 Controllability.
23.205 Trim.
23.210 Stability.
23.215 Stall characteristics, stall warning, and spins.
23.220 Ground and water handling characteristics.
23.225 Vibration, buffeting, and high-speed characteristics.
23.230 Performance and flight characteristics requirements for
flight in icing conditions.
Subpart C--Structures
23.300 Structural design envelope.
23.305 Interaction of systems and structures.

Structural Loads

23.310 Structural design loads.

23.315 Flight load conditions.
23.320 Ground and water load conditions.
23.325 Component loading conditions.
23.330 Limit and ultimate loads.

Structural Performance

23.400 Structural strength.
23.405 Structural durability.
23.410 Aeroelasticity.

Design

23.500 Structural design.
23.505 Protection of structure.
23.510 Materials and processes.
23.515 Special factors of safety.

Structural Occupant Protection

23.600 Emergency conditions.
Subpart D--Design and Construction
23.700 Flight control systems.
23.705 Landing gear systems.
23.710 Buoyancy for seaplanes and amphibians.

Occupant System Design Protection

23.750 Means of egress and emergency exits.
23.755 Occupant physical environment.

Fire and High Energy Protection

23.800 Fire protection outside designated fire zones.
23.805 Fire protection in designated fire zones.
23.810 Lightning protection of structure.
Subpart E--Powerplant
23.900 Powerplant installation.
23.905 Propeller installation.
23.910 Powerplant installation hazard assessment.
23.915 Automatic power control systems.
23.920 Reversing systems.
23.925 Powerplant operational characteristics.
23.930 Fuel system.
23.935 Powerplant induction and exhaust systems.
23.940 Powerplant ice protection.
23.1000 Powerplant fire protection.
Subpart F--Equipment
23.1300 Airplane level systems requirements.
23.1305 Function and installation.
23.1310 Flight, navigation, and powerplant instruments.
23.1315 Equipment, systems, and installations.
23.1320 Electrical and electronic system lightning protection.
23.1325 High-intensity Radiated Fields (HIRF) protection.
23.1330 System power generation, storage, and distribution.
23.1335 External and cockpit lighting.
23.1400 Safety equipment.
23.1405 Flight in icing conditions.
23.1410 Pressurized system elements.
23.1457 Cockpit voice recorders.
23.1459 Flight data recorders.
Subpart G--Flightcrew Interface and Other Information
23.1500 Flightcrew interface.
23.1505 Instrument markings, control markings and placards.
23.1510 Airplane flight manual.
23.1515 Instructions for continued airworthiness.
Appendix A to Part 23--Instructions for Continued Airworthiness

    Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704,
Pub. L. 113-53, 127 Stat. 584 (49 U.S.C. 44704) note.

Subpart A--General

Sec.  23.1  Applicability and definitions.

    (a) This part prescribes airworthiness standards for the issuance
of type certificates, and changes to those certificates, for airplanes
in the normal category.
    (b) For the purposes of this part, the following definitions apply:
    (1) Continued safe flight and landing means an airplane is capable
of continued controlled flight and landing, possibly using emergency
procedures, without requiring exceptional pilot skill or strength. Upon
landing, some airplane damage may occur as a result of a failure
condition.
    (2) Designated fire zone means a zone where catastrophic
consequences from fire in that zone must be mitigated by containing the
fire in that zone.
    (3) Empty weight means the weight of the airplane with fixed
ballast, unusable fuel, full operating fluids, and other fluids
required for normal operation of airplane systems.

Sec.  23.5  Certification of normal category airplanes.

    (a) Certification in the normal category applies to airplanes with
a passenger-seating configuration of 19 or less and a maximum
certificated takeoff weight of 19,000 pounds or less.
    (b) Airplane certification levels are:
    (1) Level 1--for airplanes with a maximum seating configuration of
0 to 1 passengers.
    (2) Level 2--for airplanes with a maximum seating configuration of
2 to 6 passengers.
    (3) Level 3--for airplanes with a maximum seating configuration of
7 to 9 passengers.
    (4) Level 4--for airplanes with a maximum seating configuration of
10 to 19 passengers.
    (c) Airplane performance levels are:
    (1) Low speed--for airplanes with a VC or VMO
<= 250 Knots Calibrated Airspeed (KCAS) (and MMO <= 0.6).
    (2) High speed--for airplanes with a VC or
VMO > 250 KCAS (or MMO > 0.6).
    (d) Simple--Simple is defined as a level 1 airplane with a
VC or VMO <= 250 KCAS (and MMO <=
0.6), a VSO <= 45 KCAS and approved only for VFR operations.
    (e) Airplanes not certified for aerobatics may be used to perform
any maneuver incident to normal flying, including--
    (1) Stalls (except whip stalls); and
    (2) Lazy eights, chandelles, and steep turns, in which the angle of
bank is not more than 60 degrees.
    (f) Airplanes certified for aerobatics may be used to perform
maneuvers without limitations, other than those limitations necessary
to avoid damage or injury.

Sec.  23.10  Accepted means of compliance.

    (a) An applicant must show the FAA how it will demonstrate
compliance with this part using a means of compliance, which may
include consensus standards, accepted by the Administrator.
    (b) A person requesting acceptance of a means of compliance must
provide the means of compliance to the FAA in a form and manner
specified by the Administrator.

Subpart B--Flight

Performance

Sec.  23.100  Weight and center of gravity.

    (a) The applicant must determine weights and centers of gravity
that provide limits for the safe operation of the airplane.
    (b) The applicant must show compliance with each requirement of
this subpart at each combination of weight and center of gravity within
the airplane's range of loading conditions using tolerances acceptable
to the Administrator.
    (c) The condition of the airplane at the time of determining its
empty weight and center of gravity must be well defined and easily
repeatable.

Sec.  23.105  Performance data.

    (a) Unless otherwise prescribed, an airplane must meet the
performance requirements of this subpart in--
    (1) Still air and standard atmospheric conditions at sea level for
all airplanes; and
    (2) Ambient atmospheric conditions within the operating envelope
for--
    (i) Level 1 high-speed and level 2 high-speed airplanes; and
    (ii) Levels 3 and 4 airplanes.
    (b) Unless otherwise prescribed, the applicant must develop the
performance data required by this subpart for the following conditions:
    (1) Airport altitudes from sea level to 10,000 feet (3,048 meters);
and
    (2) Temperatures from standard to 30[deg] Celsius above standard or
the maximum ambient atmospheric temperature at which compliance with
propulsion cooling requirements in climb is shown, if lower.

    (c) The procedures used for determining takeoff and landing
distances must be executable consistently by pilots of average skill in
atmospheric conditions expected to be encountered in service.
    (d) Performance data determined in accordance with paragraph (b) of
this section must account for losses due to atmospheric conditions,
cooling needs, and other demands on power sources.

Sec.  23.110  Stall speed.

    The applicant must determine the airplane stall speed or the
minimum steady flight speed for each flight configuration used in
normal operations, including takeoff, climb, cruise, descent, approach,
and landing. Each determination must account for the most adverse
conditions for each flight configuration with power set at idle or zero
thrust.

Sec.  23.115  Takeoff performance.

    (a) The applicant must determine airplane takeoff performance
accounting for--
    (1) Stall speed safety margins;
    (2) Minimum control speeds; and
    (3) Climb gradients.
    (b) For all airplanes, takeoff performance includes the
determination of ground roll and initial climb distance to 50 feet (15
meters) above the takeoff surface.
    (c) For levels 1, 2, and 3 high-speed multiengine airplanes,
multiengine airplanes with a maximum takeoff weight greater than 12,500
pounds and level 4 multiengine airplanes, takeoff performance includes
a determination the following distances after a sudden critical loss of
thrust:
    (1) Accelerate-stop;
    (2) Ground roll and initial climb to 50 feet (15 meters) above the
takeoff surface; and
    (3) Net takeoff flight path.

Sec.  23.120  Climb requirements.

    The applicant must demonstrate the following minimum climb
performance out of ground effect:
    (a) With all engines operating and in the initial climb
configuration--
    (1) For levels 1 and 2 low speed airplanes, a climb gradient at sea
level of 8.3 percent for landplanes and 6.7 percent for seaplanes and
amphibians; and
    (2) For levels 1 and 2 high-speed airplanes and all level 3
airplanes, a climb gradient at takeoff of 4 percent.
    (b) After a critical loss of thrust on multiengine airplanes--
    (1) For levels 1and 2 low-speed airplanes that do not meet single
engine crashworthiness requirements, a 1.5 percent climb gradient at a
pressure altitude of 5,000 feet (1,524 meters) in the cruise
configuration;
    (2) For levels 1 and 2 high-speed airplanes, and level 3 low-speed
airplanes, a 1 percent climb gradient at 400 feet (122 meters) above
the takeoff surface with the landing gear retracted and flaps in the
takeoff configuration;
    (3) For level 3 high-speed airplanes and all level 4 airplanes, a 2
percent climb gradient at 400 feet (122 meters) above the takeoff
surface with the landing gear retracted and flaps in the approach
configuration;
    (4) At sea level for level 1 and level 2 low-speed airplanes; and
    (5) At the landing surface for all other airplanes.
    (c) For a balked landing, a climb gradient of 3 percent with--
    (1) Takeoff power on each engine;
    (2) Landing gear extended; and
    (3) Flaps in the landing configuration.

Sec.  23.125  Climb information.

    (a) The applicant must determine climb performance--
    (1) For all single engine airplanes;
    (2) For level 3 multiengine airplanes, following a critical loss of
thrust on takeoff in the initial climb configuration; and
    (3) For all multiengine airplanes, during the enroute phase of
flight with all engines operating and after a critical loss of thrust
in the cruise configuration.
    (b) For single engine airplanes, the applicant must determine the
glide performance of the airplane after a complete loss of thrust.

Sec.  23.130  Landing.

    The applicant must determine the following, for standard
temperatures at each weight and altitude within the operational limits
for landing:
    (a) The distance, starting from a height of 50 feet (15 meters)
above the landing surface, required to land and come to a stop, or for
water operations, reach a speed of 3 knots.
    (b) The approach and landing speeds, configurations, and
procedures, which allow a pilot of average skill to meet the landing
distance consistently and without causing damage or injury.

Flight Characteristics

Sec.  23.200  Controllability.

    (a) The airplane must be controllable and maneuverable, without
requiring exceptional piloting skill, alertness, or strength, within
the operating envelope--
    (1) At all loading conditions for which certification is requested;
    (2) During low-speed operations, including stalls;
    (3) With any probable flight control or propulsion system failure;
and
    (4) During configuration changes.
    (b) The airplane must be able to complete a landing without causing
damage or serious injury, in the landing configuration at a speed of
VREF minus 5 knots using the approach gradient equal to the
steepest used in the landing distance determination.
    (c) For levels 1 and 2 multiengine airplanes that cannot climb
after a critical loss of thrust, VMC must not exceed
VS1 or VS0 for all practical weights and
configurations within the operating envelope of the airplane.
    (d) If the applicant requests certification of an airplane for
aerobatics, the applicant must demonstrate those aerobatic maneuvers
for which certification is requested and determine entry speeds.

Sec.  23.205  Trim.

    (a) The airplane must maintain longitudinal, lateral, and
directional trim under the following conditions:
    (1) For levels 1, 2, and 3 airplanes, in cruise, without further
force upon, or movement of, the primary flight controls or
corresponding trim controls by the pilot, or the flight control system.
    (2) For level 4 airplanes in normal operations, without further
force upon, or movement of, the primary flight controls or
corresponding trim controls by the pilot, or the flight control system.
    (b) The airplane must maintain longitudinal trim under the
following conditions:
    (1) Climb.
    (2) Level flight.
    (3) Descent.
    (4) Approach.
    (c) Residual forces must not fatigue or distract the pilot during
likely emergency operations, including a critical loss of thrust on
multiengine airplanes.

Sec.  23.210  Stability.

    (a) Airplanes not certified for aerobatics must--
    (1) Have static longitudinal, lateral, and directional stability in
normal operations;
    (2) Have dynamic short period and combined lateral-directional
stability in normal operations; and
    (3) Provide stable control force feedback throughout the operating
envelope.
    (b) No airplane may exhibit any divergent longitudinal stability
characteristic so unstable as to increase the pilot's workload or
otherwise endanger the airplane and its occupants.

Sec.  23.215  Stall characteristics, stall warning, and spins.

    (a) The airplane must have controllable stall characteristics in
straight flight, turning flight, and accelerated turning flight with a
clear and distinctive stall warning that provides sufficient margin to
prevent inadvertent stalling.
    (b) Levels 1 and 2 airplanes and level 3 single-engine airplanes,
not certified for aerobatics, must not have a tendency to inadvertently
depart controlled flight.
    (c) Airplanes certified for aerobatics must have controllable stall
characteristics and the ability to recover within one and one-half
additional turns after initiation of the first control action from any
point in a spin, not exceeding six turns or any greater number of turns
for which certification is requested, while remaining within the
operating limitations of the airplane.
    (d) Spin characteristics in airplanes certified for aerobatics must
not result in unrecoverable spins--
    (1) With any use of the flight or engine power controls; or
    (2) Due to pilot disorientation or incapacitation.

Sec.  23.220  Ground and water handling characteristics.

    (a) For airplanes intended for operation on land or water, the
airplane must have controllable longitudinal and directional handling
characteristics during taxi, takeoff, and landing operations.
    (b) For airplanes intended for operation on water, the following
must be established and included in the Airplane Flight Manual (AFM):
    (1) The maximum wave height at which the aircraft demonstrates
compliance to paragraph (a) of this section. This wave height does not
constitute an operating limitation.
    (2) Any necessary water handling procedures.

Sec.  23.225  Vibration, buffeting, and high-speed characteristics.

    (a) Vibration and buffeting, for operations up to VD/
MD, must not interfere with the control of the airplane or
cause fatigue to the flightcrew. Stall warning buffet within these
limits is allowable.
    (b) For high-speed airplanes and all airplanes with a maximum
operating altitude greater than 25,000 feet (7,620 meters) pressure
altitude, there must be no perceptible buffeting in cruise
configuration at 1g and at any speed up to VMO/
MMO, except stall buffeting.
    (c) For high-speed airplanes, the applicant must determine the
positive maneuvering load factors at which the onset of perceptible
buffet occurs in the cruise configuration within the operational
envelope. Likely inadvertent excursions beyond this boundary must not
result in structural damage.
    (d) High-speed airplanes must have recovery characteristics that do
not result in structural damage or loss of control, beginning at any
likely speed up to VMO/MMO, following--
    (1) An inadvertent speed increase; and
    (2) A high-speed trim upset.

Sec.  23.230  Performance and flight characteristics requirements for
flight in icing conditions.

    (a) If an applicant requests certification for flight in icing
conditions as specified in part 1 of appendix C to part 25 of this
chapter and any additional atmospheric icing conditions for which an
applicant requests certification, the applicant must demonstrate the
following:
    (1) Compliance with each requirement of this subpart, except those
applicable to spins and any that must be demonstrated at speeds in
excess of--
    (i) 250 knots CAS;
    (ii) VMO or MMO; or
    (iii) A speed at which the applicant demonstrates the airframe will
be free of ice accretion.
    (2) The stall warning for flight in icing conditions and non-icing
conditions is the same.
    (b) If an applicant requests certification for flight in icing
conditions, the applicant must provide a means to detect any icing
conditions for which certification is not requested and demonstrate the
aircraft's ability to avoid or exit those conditions.
    (c) The applicant must develop an operating limitation to prohibit
intentional flight, including takeoff and landing, into icing
conditions for which the airplane is not certified to operate.

Subpart C--Structures

Sec.  23.300  Structural design envelope.

    The applicant must determine the structural design envelope, which
describes the range and limits of airplane design and operational
parameters for which the applicant will show compliance with the
requirements of this subpart. The applicant must account for all
airplane design and operational parameters that affect structural
loads, strength, durability, and aeroelasticity, including:
    (a) Structural design airspeeds and Mach numbers, including--
    (1) The design maneuvering airspeed, VA, which may be no
less than the airspeed at which the airplane will stall at the maximum
design maneuvering load factor;
    (2) The design cruising airspeed, VC or MC,
which may be no less than the maximum speed expected in normal
operations;
    (3) The design dive airspeed, VD or MD, which
is the airspeed that will not be exceeded by inadvertent airspeed
increases when operating at VC or MC;
    (4) Any other design airspeed limitations required for the
operation of high lift devices, landing gear, and other equipment or
devices; and
    (5) For level 4 airplanes, a rough air penetration speed,
VB.
    (b) Design maneuvering load factors not less than those, which
service history shows, may occur within the structural design envelope.
    (c) Inertial properties including weight, center of gravity, and
mass moments of inertia, accounting for--
    (1) All weights from the airplane empty weight to the maximum
weight; and
    (2) The weight and distribution of occupants, payload, and fuel.
    (d) Range of motion for control surfaces, high lift devices, or
other moveable surfaces, including tolerances.
    (e) All altitudes up to the maximum altitude.

Sec.  23.305  Interaction of systems and structures.

    For airplanes equipped with systems that affect structural
performance, either directly or as a result of failure or malfunction,
the applicant must account for the influence and failure conditions of
these systems when showing compliance with the requirements of this
subpart.

Structural Loads

Sec.  23.310  Structural design loads.

    The applicant must:
    (a) Determine structural design loads resulting from any externally
or internally applied pressure, force, or moment which may occur in
flight, ground and water operations, ground and water handling, and
while the airplane is parked or moored.
    (b) Determine the loads required by paragraph (a) of this section
at all critical combinations of parameters, on and within the
boundaries of the structural design envelope.
    (c) The magnitude and distribution of these loads must be based on
physical principles and may be no less than service history shows will
occur within the structural design envelope.

Sec.  23.315  Flight load conditions.

    The applicant must determine the structural design loads resulting
from the following flight conditions:

    (a) Vertical and horizontal atmospheric gusts where the magnitude
and gradient of these gusts are based on measured gust statistics.
    (b) Symmetric and asymmetric maneuvers.
    (c) For canted lifting surfaces, vertical and horizontal loads
acting simultaneously resulting from gust and maneuver conditions.
    (d) For multiengine airplanes, failure of the powerplant unit which
results in the most severe structural loads.

Sec.  23.320  Ground and water load conditions.

    The applicant must determine the structural design loads resulting
from the following ground and water operations:
    (a) For airplanes intended for operation on land--taxi, takeoff,
landing, and ground handling conditions occurring in normal and adverse
attitudes and configurations.
    (b) For airplanes intended for operation on water--taxi, takeoff,
landing, and water handling conditions occurring in normal and adverse
attitudes and configurations in the most severe sea conditions expected
in operation.
    (c) Jacking and towing conditions.

Sec.  23.325  Component loading conditions.

    The applicant must determine the structural design loads acting on:
    (a) Each engine mount and its supporting structure resulting from
engine operation combined with gusts and maneuvers.
    (b) Each flight control and high lift surface, their associated
system and supporting structure resulting from--
    (1) The inertia of each surface and mass balance attachment;
    (2) Gusts and maneuvers;
    (3) Pilot or automated system inputs;
    (4) System induced conditions, including jamming and friction; and
    (5) Ground operations, including downwind taxi and ground gusts.
    (c) A pressurized cabin resulting from the pressurization
differential--
    (1) From zero up to the maximum relief valve setting combined with
gust and maneuver loads;
    (2) From zero up to the maximum relief valve setting combined with
ground and water loads if the airplane may land with the cabin
pressurized; and
    (3) At the maximum relief valve setting multiplied by 1.33,
omitting all other loads.

Sec.  23.330  Limit and ultimate loads.

    Unless special or other factors of safety are necessary to meet the
requirements of this subpart, the applicant must determine--
    (a) The limit loads, which are equal to the structural design
loads; and
    (b) The ultimate loads, which are equal to the limit loads
multiplied by a 1.5 factor of safety.

Structural Performance

Sec.  23.400  Structural strength.

    The applicant must demonstrate that the structure will support:
    (a) Limit loads without--
    (1) Interference with the operation of the airplane; and
    (2) Detrimental permanent deformation.
    (b) Ultimate loads.

Sec.  23.405  Structural durability.

    (a) The applicant must develop and implement procedures to prevent
structural failures due to foreseeable causes of strength degradation,
which could result in serious or fatal injuries, loss of the airplane,
or extended periods of operation with reduced safety margins. The
Instructions for Continued Airworthiness must include procedures
developed under this section.
    (b) If a pressurized cabin has two or more compartments separated
by bulkheads or a floor, the applicant must design the structure for a
sudden release of pressure in any compartment that has a door or
window, considering failure of the largest door or window opening in
the compartment.
    (c) For airplanes with maximum operating altitude greater than
41,000 feet, the procedures developed for compliance to paragraph (a)
of this section must be capable of detecting damage to the pressurized
cabin structure before the damage could result in rapid decompression
that would result in serious or fatal injuries.
    (d) The airplane must be capable of continued safe flight and
landing with structural damage caused by high-energy fragments from an
uncontained engine or rotating machinery failure.

Sec.  23.410  Aeroelasticity.

    (a) The airplane must be free from flutter, control reversal, and
divergence--
    (1) At all speeds within and sufficiently beyond the structural
design envelope;
    (2) For any configuration and condition of operation;
    (3) Accounting for critical degrees of freedom; and
    (4) Accounting for any critical failures or malfunctions.
    (b) The applicant must establish and account for tolerances for all
quantities that affect flutter.

Design

Sec.  23.500  Structural design.

    (a) The applicant must design each part, article, and assembly for
the expected operating conditions of the airplane.
    (b) Design data must adequately define the part, article, or
assembly configuration, its design features, and any materials and
processes used.
    (c) The applicant must determine the suitability of each design
detail and part having an important bearing on safety in operations.
    (d) The control system must be free from jamming, excessive
friction, and excessive deflection when--
    (1) The control system and its supporting structure are subjected
to loads corresponding to the limit airloads;
    (2) The primary controls are subjected to the lesser of the limit
airloads or limit pilot forces; and
    (3) The secondary controls are subjected to loads not less than
those corresponding to maximum pilot effort.

Sec.  23.505  Protection of structure.

    (a) The applicant must protect each part of the airplane, including
small parts such as fasteners, against deterioration or loss of
strength due to any cause likely to occur in the expected operational
environment.
    (b) Each part of the airplane must have adequate provisions for
ventilation and drainage.
    (c) For each part that requires maintenance, preventive
maintenance, or servicing, the applicant must incorporate a means into
the aircraft design to allow such actions to be accomplished.

Sec.  23.510  Materials and processes.

    (a) The applicant must determine the suitability and durability of
materials used for parts, articles, and assemblies, the failure of
which could prevent continued safe flight and landing. The applicant
must account for the effects of likely environmental conditions
expected in service.
    (b) The methods and processes of fabrication and assembly used must
produce consistently sound structures. If a fabrication process
requires close control to reach this objective, the applicant must
perform the process under an approved process specification.
    (c) Except as provided in paragraphs (f) and (g) of this section,
the applicant must select design values that ensure material strength
with probabilities that account for the criticality of the structural
element. Design values must

account for the probability of structural failure due to material
variability.
    (d) If material strength properties are required, a determination
of those properties must be based on sufficient tests of material
meeting specifications to establish design values on a statistical
basis.
    (e) If thermal effects are significant on an essential component or
structure under normal operating conditions, the applicant must
determine those effects on allowable stresses used for design.
    (f) Design values, greater than the minimums specified by this
section, may be used, where only guaranteed minimum values are normally
allowed, if a specimen of each individual item is tested before use to
determine that the actual strength properties of that particular item
will equal or exceed those used in the design.
    (g) An applicant may use other material design values if approved
by the Administrator.

Sec.  23.515  Special factors of safety.

    (a) The applicant must determine a special factor of safety for any
critical design value that is--
    (1) Uncertain;
    (2) Used for a part, article, or assembly that is likely to
deteriorate in service before normal replacement; or
    (3) Subject to appreciable variability because of uncertainties in
manufacturing processes or inspection methods.
    (b) The applicant must determine a special factor of safety using
quality controls and specifications that account for each--
    (1) Structural application;
    (2) Inspection method;
    (3) Structural test requirement;
    (4) Sampling percentage; and
    (5) Process and material control.
    (c) The applicant must apply any special factor of safety in the
design for each part of the structure by multiplying each limit load
and ultimate load by the special factor of safety.

Structural Occupant Protection

Sec.  23.600  Emergency conditions.

    (a) The airplane, even when damaged in an emergency landing, must
protect each occupant against injury that would preclude egress when--
    (1) Properly using safety equipment and features provided for in
the design;
    (2) The occupant experiences ultimate static inertia loads likely
to occur in an emergency landing; and
    (3) Items of mass, including engines or auxiliary power units
(APUs), within or aft of the cabin, that could injure an occupant,
experience ultimate static inertia loads likely to occur in an
emergency landing.
    (b) The emergency landing conditions specified in paragraph (a) of
this section, must--
    (1) Include dynamic conditions that are likely to occur with an
impact at stall speed, accounting for variations in aircraft mass,
flight path angle, flight pitch angle, yaw, and airplane configuration,
including likely failure conditions at impact; and
    (2) Not exceed established human injury criteria for human
tolerance due to restraint or contact with objects in the airplane.
    (c) The airplane must have seating and restraints for all
occupants. The airplane seating, restraints, and cabin interior must
account for likely flight and emergency landing conditions.
    (d) Each occupant restraint system must consist of a seat, a method
to restrain the occupant's pelvis and torso, and a single action
restraint release. For all flight and ground loads during normal
operation and any emergency landing conditions, the restraint system
must perform its intended function and not create a hazard that could
cause a secondary injury to an occupant. The restraint system must not
prevent occupant egress or interfere with the operation of the airplane
when not in use.
    (e) Each baggage and cargo compartment must--
    (1) Be designed for its maximum weight of contents and for the
critical load distributions at the maximum load factors corresponding
to the flight and ground load conditions determined under this part;
    (2) Have a means to prevent the contents of the compartment from
becoming a hazard by impacting occupants or shifting; and
    (3) Protect any controls, wiring, lines, equipment, or accessories
whose damage or failure would affect operations.

Subpart D--Design and Construction

Sec.  23.700  Flight control systems.

    (a) The applicant must design airplane flight control systems to:
    (1) Prevent major, hazardous, and catastrophic hazards, including--
    (i) Failure;
    (ii) Operational hazards;
    (iii) Flutter;
    (iv) Asymmetry; and
    (v) Misconfiguration.
    (2) Operate easily, smoothly, and positively enough to allow normal
operation.
    (b) The applicant must design trim systems to:
    (1) Prevent inadvertent, incorrect, or abrupt trim operation.
    (2) Provide a means to indicate--
    (i) The direction of trim control movement relative to airplane
motion;
    (ii) The trim position with respect to the trim range;
    (iii) The neutral position for lateral and directional trim; and
    (iv) For all airplanes, except simple airplanes, the range for
takeoff for all applicant requested center of gravity ranges and
configurations.
    (3) Except for simple airplanes, provide control for continued safe
flight and landing when any one connecting or transmitting element in
the primary flight control system fails.
    (4) Limit the range of travel to allow safe flight and landing, if
an adjustable stabilizer is used.
    (c) For an airplane equipped with an artificial stall barrier
system, the system must--
    (1) Prevent uncommanded control or thrust action; and
    (2) Provide for a preflight check.
    (d) For level 3 high-speed and all level 4 airplanes, an applicant
must install a takeoff warning system on the airplane unless the
applicant demonstrates the airplane, for each configuration, can
takeoff at the limits of the trim and flap ranges.

Sec.  23.705  Landing gear systems.

    (a) For airplanes with retractable landing gear:
    (1) The landing gear and retracting mechanism, including the wheel
well doors, must be able to withstand operational and flight loads.
    (2) The airplane must have--
    (i) A positive means to keep the landing gear extended;
    (ii) A secondary means of extension for landing gear that cannot be
extended using the primary means;
    (iii) A means to inform the pilot that each landing gear is secured
in the extended and retracted positions; and
    (iv) Except for airplanes intended for operation on water, a
warning to the pilot if the thrust and configuration is selected for
landing and the landing gear is not fully extended and locked.
    (3) If the landing gear bay is used as the location for equipment
other than the landing gear, that equipment must be designed and
installed to avoid damage from tire burst and from items that may enter
the landing gear bay.
    (b) The design of each landing gear wheel, tire, and ski must
account for critical loads, including those experienced during landing
and rejected takeoff.
    (c) A reliable means of stopping the airplane must provide kinetic
energy absorption within the airplane's design specifications for
landing.

    (d) For levels 3 and 4 multiengine airplanes, the braking system
must provide kinetic energy absorption within the airplane's design
specifications for rejected takeoff.

Sec.  23.710  Buoyancy for seaplanes and amphibians.

    Airplanes intended for operations on water, must--
    (a) Provide buoyancy of 80 percent in excess of the buoyancy
required to support the maximum weight of the airplane in fresh water;
and
    (b) Have sufficient watertight compartments so the airplane will
stay afloat at rest in calm water without capsizing if any two
compartments of any main float or hull are flooded.
Occupant System Design Protection

Sec.  23.750  Means of egress and emergency exits.

    (a) The airplane cabin exit design must provide for evacuation of
the airplane within 90 seconds in conditions likely to occur following
an emergency landing. Likely conditions exclude ditching for all but
levels 3 and 4 multiengine airplanes.
    (b) Each exit must have a means to be opened from both inside and
outside the airplane, when the internal locking mechanism is in the
locked and unlocked position. The means of opening must be simple,
obvious, and marked inside and outside the airplane.
    (c) Airplane evacuation paths must protect occupants from serious
injury from the propulsion system.
    (d) Each exit must not be obstructed by a seat or seat back, unless
the seat or seat back can be easily moved in one action to clear the
exit.
    (e) Airplanes certified for aerobatics must have a means to egress
the airplane in flight.
    (f) Doors, canopies, and exits must be protected from opening
inadvertently in flight.

Sec.  23.755  Occupant physical environment.

    (a) The applicant must design the airplane to--
    (1) Allow clear communication between the flightcrew and
passengers;
    (2) Provide a clear, sufficiently undistorted external view to
enable the flightcrew to perform any maneuvers within the operating
limitations of the airplane;
    (3) Protect the pilot from serious injury due to high energy
rotating failures in systems and equipment; and
    (4) Protect the occupants from serious injury due to damage to
windshields, windows, and canopies.
    (b) For level 4 airplanes, each windshield and its supporting
structure directly in front of the pilot must--
    (1) Withstand, without penetration, the impact equivalent to a two-
pound bird when the velocity of the airplane is equal to the airplane's
maximum approach flap speed; and
    (2) Allow for continued safe flight and landing after the loss of
vision through any one panel.
    (c) The airplane must provide each occupant with air at a
breathable pressure, free of hazardous concentrations of gases and
vapors, during normal operations and likely failures.
    (d) If an oxygen system is installed in the airplane, it must
include--
    (1) A means to allow the flightcrew to determine the quantity of
oxygen available in each source of supply on the ground and in flight;
    (2) A means to determine whether oxygen is being delivered; and
    (3) A means to permit the flightcrew to turn on and shut off the
oxygen supply at any high-pressure source in flight.
    (e) If a pressurization system is installed in the airplane, it
must include--
    (1) A warning if an unsafe condition exists; and
    (2) A pressurization system test.
Fire and High Energy Protection

Sec.  23.800  Fire protection outside designated fire zones.

    Outside designated fire zones:
    (a) The following materials must be self-extinguishing--
    (1) Insulation on electrical wire and electrical cable;
    (2) For levels 1, 2, and 3 airplanes, materials in the baggage and
cargo compartments inaccessible in flight; and
    (3) For level 4 airplanes, materials in the cockpit, cabin,
baggage, and cargo compartments.
    (b) The following materials must be flame resistant--
    (1) For levels 1, 2 and 3 airplanes, materials in each compartment
accessible in flight; and
    (2) Any electrical cable installation that would overheat in the
event of circuit overload or fault.
    (c) Thermal acoustic materials, if installed, must not be a flame
propagation hazard.
    (d) Sources of heat that are capable of igniting adjacent objects
must be shielded and insulated to prevent such ignition.
    (e) For level 4 airplanes, each baggage and cargo compartment
must--
    (1) Be located where a fire would be visible to the pilots, or
equipped with a fire detection system and warning system; and
    (2) Be accessible for the manual extinguishing of a fire, have a
built-in fire extinguishing system, or be constructed and sealed to
contain any fire within the compartment.
    (f) There must be a means to extinguish any fire in the cabin such
that--
    (1) The pilot, while seated, can easily access the fire
extinguishing means; and
    (2) For levels 3 and 4 airplanes, passengers have a fire
extinguishing means available within the passenger compartment.
    (g) Each area where flammable fluids or vapors might escape by
leakage of a fluid system must--
    (1) Be defined; and
    (2) Have a means to make fluid and vapor ignition, and the
resultant hazard, if ignition occurs, improbable.
    (h) Combustion heater installations must be protected from
uncontained fire.

Sec.  23.805  Fire protection in designated fire zones.

    Inside designated fire zones:
    (a) Flight controls, engine mounts, and other flight structures
within or adjacent to those zones must be capable of withstanding the
effects of a fire.
    (b) Engines must remain attached to the airplane in the event of a
fire or electrical arcing.
    (c) Terminals, equipment, and electrical cables used during
emergency procedures must be fire-resistant.

Sec.  23.810  Lightning protection of structure.

    (a) For airplanes approved for instrument flight rules, no
structural failure preventing continued safe flight and landing may
occur from exposure to the direct effects of lightning.
    (b) Airplanes approved only for visual flight rules must achieve
lightning protection by following FAA accepted design practices.

Subpart E--Powerplant

Sec.  23.900  Powerplant installation.

    (a) For the purpose of this subpart, the airplane powerplant
installation must include each component necessary for propulsion,
affects propulsion safety, or provides auxiliary power to the airplane.
    (b) The applicant must construct and arrange each powerplant
installation to account for likely hazards in operation and
maintenance.
    (c) Except for simple airplanes, each aircraft power unit must be
type certificated.

Sec.  23.905  Propeller installation.

    (a) Except for simple airplanes, each propeller must be type
certificated.

    (b) Each pusher propeller must be marked so that it is conspicuous
under daylight conditions.
    (c) Each propeller installation must account for vibration and
fatigue.

Sec.  23.910  Powerplant installation hazard assessment.

    The applicant must assess each powerplant separately and in
relation to other airplane systems and installations to show that a
failure of any powerplant system component or accessory will not--
    (a) Prevent continued safe flight and landing;
    (b) Cause serious injury that may be avoided; and
    (c) Require immediate action by crewmembers for continued operation
of any remaining powerplant system.

Sec.  23.915  Automatic power control systems.

    A power or thrust augmentation system that automatically controls
the power or thrust on the operating powerplant, must--
    (a) Provide indication to the flightcrew when the system is
operating;
    (b) Provide a means for the pilot to deactivate the automatic
function; and
    (c) Prevent inadvertent deactivation.

Sec.  23.920  Reversing systems.

    The airplane must be capable of continued safe flight and landing
under any available reversing system setting.

Sec.  23.925  Powerplant operational characteristics.

    (a) The powerplant must operate at any negative acceleration that
may occur during normal and emergency operation, within the airplane
operating limitations.
    (b) The pilot must have the capability to stop and restart the
powerplant in flight.
    (c) The airplane must have an independent power source for
restarting each powerplant following an in-flight shutdown.

Sec.  23.930  Fuel system

    (a) Each fuel system must--
    (1) Provide an independent fuel supply to each powerplant in at
least one configuration;
    (2) Avoid ignition from unplanned sources;
    (3) Provide the fuel required to achieve maximum power or thrust
plus a margin for likely variables, in all temperature and altitude
conditions within the airplane operating envelope;
    (4) Provide a means to remove the fuel from the airplane;
    (5) Be capable of retaining fuel when subject to inertia loads
under expected operating conditions; and
    (6) Prevent hazardous contamination of the fuel supply.
    (b) Each fuel storage system must--
    (1) Withstand the loads and pressures under expected operating
conditions;
    (2) Provide a means to prevent loss of fuel during any maneuver
under operating conditions for which certification is requested;
    (3) Prevent discharge when transferring fuel;
    (4) Provide fuel for at least one-half hour of operation at maximum
continuous power or thrust; and
    (5) Be capable of jettisoning fuel if required for landing.
    (c) If a pressure refueling system is installed, it must have a
means to--
    (1) Prevent the escape of hazardous quantities of fuel;
    (2) Automatically shut-off before exceeding the maximum fuel
quantity of the airplane; and
    (3) Provide an indication of a failure at the fueling station.

Sec.  23.935  Powerplant induction and exhaust systems.

    The air induction system for each power unit and its accessories
must--
    (a) Supply the air required by that power unit and its accessories
under expected operating conditions; and
    (b) Provide a means to discharge potential harmful material.

Sec.  23.940  Powerplant ice protection.

    (a) The airplane design must prevent foreseeable accumulation of
ice or snow that adversely affects powerplant operation.
    (b) The powerplant design must prevent any accumulation of ice or
snow that adversely affects powerplant operation, in those icing
conditions for which certification is requested.

Sec.  23.1000  Powerplant fire protection.

    (a) A powerplant may only be installed in a designated fire zone.
    (b) Each component, line, and fitting carrying flammable fluids,
gases, or air subject to fire conditions must be fire resistant, except
components storing concentrated flammable material must be fireproof or
enclosed by a fireproof shield.
    (c) The applicant must provide a means to shut off fuel or
flammable material for each powerplant that must--
    (1) Not restrict fuel to remaining units; and
    (2) Prevent inadvertent operation.
    (d) For levels 3 and 4 airplanes with a powerplant located outside
the pilot's view that uses combustible fuel, the applicant must install
a fire extinguishing system.
    (e) For levels 3 and 4 airplanes, the applicant must install a fire
detection system in each designated fire zone.
    (f) Each fire detection system must provide a means to alert the
flightcrew in the event of a detection of fire or failure of the
system.
    (g) There must be a means to check the fire detection system in
flight.

Subpart F--Equipment

Sec.  23.1300  Airplane level systems requirements.

    (a) The equipment and systems required for an airplane to operate
safely in the kinds of operations for which certification is requested
(Day VFR, Night VFR, IFR) must be designed and installed to--
    (1) Meet the level of safety applicable to the certification and
performance level of the airplane; and
    (2) Perform their intended function throughout the operating and
environmental limits specified by the applicant.
    (b) Non[hyphen]required airplane equipment and systems, considered
separately and in relation to other systems, must be designed and
installed so their operation or failure does not have an adverse effect
on the airplane or its occupants.

Sec.  23.1305  Function and installation.

    (a) Each item of installed equipment must--
    (1) Perform its intended function;
    (2) Be installed according to limitations specified for that
equipment; and
    (3) Be labeled, if applicable, as to its identification, function
or operating limitations, or any combination of these factors.
    (b) There must be a discernable means of providing system operating
parameters required to operate the airplane, including warnings,
cautions, and normal indications to the responsible crewmember.
    (c) Information concerning an unsafe system operating condition
must be provided in a timely manner to the crewmember responsible for
taking corrective action. Presentation of this information must be
clear enough to avoid likely crewmember errors.

Sec.  23.1310  Flight, navigation, and powerplant instruments.

    (a) Installed systems must provide the flightcrew member who sets
or monitors flight parameters for the flight, navigation, and
powerplant the information necessary to do so during each phase of
flight. This information must include--

    (1) Parameters and trends, as needed for normal, abnormal, and
emergency operation; and
    (2) Limitations, unless the applicant shows each limitation will
not be exceeded in all intended operations.
    (b) Indication systems that integrate the display of flight or
powerplant parameters to operate the airplane or are required by the
operating rules of this chapter must--
    (1) Not inhibit the primary display of flight or powerplant
parameters needed by any flightcrew member in any normal mode of
operation; and
    (2) In combination with other systems, be designed and installed so
information essential for continued safe flight and landing will be
available to the flightcrew in a timely manner after any single failure
or probable combination of failures.

Sec.  23.1315  Equipment, systems, and installations.

    For any airplane system or equipment whose failure or abnormal
operation has not been specifically addressed by another requirement in
this part, the applicant must:
    (a) Examine the design and installation of airplane systems and
equipment, separately and in relation to other airplane systems and
equipment to determine--
    (1) If a failure would prevent continued safe flight and landing;
and
    (2) If any other failure would significantly reduce the capability
of the airplane or the ability of the flightcrew to cope with adverse
operating conditions.
    (b) Design and install each system and equipment, examined
separately and in relation to other airplane systems and equipment,
such that--
    (1) Each catastrophic failure condition is extremely improbable;
    (2) Each hazardous failure condition is extremely remote; and
    (3) Each major failure condition is remote.

Sec.  23.1320  Electrical and electronic system lightning protection.

    For an airplane approved for IFR operations:
    (a) Each electrical or electronic system that performs a function,
the failure of which would prevent the continued safe flight and
landing of the airplane, must be designed and installed such that--
    (1) The airplane system level function continues to perform during
and after the time the airplane is exposed to lightning; and
    (2) The system automatically recovers normal operation of that
function in a timely manner after the airplane is exposed to lightning
unless the system's recovery conflicts with other operational or
functional requirements of the system.
    (b) Each electrical and electronic system that performs a function,
the failure of which would reduce the capability of the airplane or the
ability of the flightcrew to respond to an adverse operating condition,
must be designed and installed such that the function recovers normal
operation in a timely manner after the airplane is exposed to
lightning.

Sec.  23.1325  High-intensity Radiated Fields (HIRF) protection.

    (a) Electrical and electronic systems that perform a function, the
failure of which would prevent the continued safe flight and landing of
the airplane, must be designed and installed such that--
    (1) The airplane system level function is not adversely affected
during and after the time the airplane is exposed to the HIRF
environment; and
    (2) The system automatically recovers normal operation of that
function in a timely manner after the airplane is exposed to the HIRF
environment, unless the system's recovery conflicts with other
operational or functional requirements of the system.
    (b) For airplanes approved for IFR operations, the applicant must
design and install each electrical and electronic system that performs
a function, the failure of which would reduce the capability of the
airplane or the ability of the flightcrew to respond to an adverse
operating condition, so the function recovers normal operation in a
timely manner after the airplane is exposed to the HIRF environment.

Sec.  23.1330  System power generation, storage, and distribution.

    The power generation, storage, and distribution for any system must
be designed and installed to--
    (a) Supply the power required for operation of connected loads
during all likely operating conditions;
    (b) Ensure no single failure or malfunction will prevent the system
from supplying the essential loads required for continued safe flight
and landing; and
    (c) Have enough capacity, if the primary source fails, to supply
essential loads, including non-continuous essential loads for the time
needed to complete the function, for--
    (1) At least 30 minutes for airplanes certificated with a maximum
altitude of 25,000 feet (7,620 meters) or less; and
    (2) At least 60 minutes for airplanes certificated with a maximum
altitude over 25,000 feet (7,620 meters).

Sec.  23.1335  External and cockpit lighting.

    (a) The applicant must design and install all lights to prevent
adverse effects on the performance of flightcrew duties.
    (b) Any position and anti-collision lights, if required by part 91
of this chapter, must have the intensities, flash rate, colors, fields
of coverage, and other characteristics to provide sufficient time for
another aircraft to avoid a collision.
    (c) Any position lights, if required by part 91 of this chapter,
must include a red light on the left side of the airplane, a green
light on the right side of the airplane, spaced laterally as far apart
as space allows, and a white light facing aft, located on an aft
portion of the airplane or on the wing tips.
    (d) The applicant must design and install taxi and landing lights
so they provide sufficient light for night operations.
    (e) For seaplanes or amphibian airplanes, riding lights must
provide a white light visible in clear atmospheric conditions.

Sec.  23.1400  Safety equipment.

    Safety and survival equipment, required by the operating rules of
this chapter, must be reliable, readily accessible, easily
identifiable, and clearly marked to identify its method of operation.

Sec.  23.1405  Flight in icing conditions.

    (a) If an applicant requests certification for flight in icing
conditions, the applicant must demonstrate that--
    (1) The ice protection system provides for safe operation; and
    (2) The airplane is protected from stalling when the autopilot is
operating in a vertical mode.
    (b) The demonstration specified in paragraph (a) of this section,
must be conducted in atmospheric icing conditions specified in part 1
of appendix C to part 25 of this chapter, and any additional icing
conditions for which certification is requested.

Sec.  23.1410  Pressurized systems elements.

    (a) The minimum burst pressure of hydraulic systems must be at
least 2.5 times the design operating pressure. The proof pressure must
be at least 1.5 times the maximum operating pressure.
    (b) On multiengine airplanes, engine driven accessories essential
to safe operation must be distributed among multiple engines.
    (c) The minimum burst pressure of cabin pressurization system
elements must be at least 2.0 times, and proof pressure must be at
least 1.5 times, the maximum normal operating pressure.

    (d) The minimum burst pressure of pneumatic system elements must be
at least 3.0 times, and proof pressure must be at least 1.5 times, the
maximum normal operating pressure.
    (e) Other pressurized system elements must have pressure margins
that take into account system design and operating conditions.

Sec.  23.1457  Cockpit voice recorders.

    (a) Each cockpit voice recorder required by the operating rules of
this chapter must be approved and must be installed so that it will
record the following:
    (1) Voice communications transmitted from or received in the
airplane by radio.
    (2) Voice communications of flightcrew members on the flight deck.
    (3) Voice communications of flightcrew members on the flight deck,
using the airplane's interphone system.
    (4) Voice or audio signals identifying navigation or approach aids
introduced into a headset or speaker.
    (5) Voice communications of flightcrew members using the passenger
loudspeaker system, if there is such a system and if the fourth channel
is available in accordance with the requirements of paragraph
(c)(4)(ii) of this section.
    (6) If datalink communication equipment is installed, all datalink
communications, using an approved data message set. Datalink messages
must be recorded as the output signal from the communications unit that
translates the signal into usable data.
    (b) The recording requirements of paragraph (a)(2) of this section
must be met by installing a cockpit-mounted area microphone, located in
the best position for recording voice communications originating at the
first and second pilot stations and voice communications of other
crewmembers on the flight deck when directed to those stations. The
microphone must be so located and, if necessary, the preamplifiers and
filters of the recorder must be so adjusted or supplemented, so that
the intelligibility of the recorded communications is as high as
practicable when recorded under flight cockpit noise conditions and
played back. Repeated aural or visual playback of the record may be
used in evaluating intelligibility.
    (c) Each cockpit voice recorder must be installed so that the part
of the communication or audio signals specified in paragraph (a) of
this section obtained from each of the following sources is recorded on
a separate channel:
    (1) For the first channel, from each boom, mask, or handheld
microphone, headset, or speaker used at the first pilot station.
    (2) For the second channel from each boom, mask, or handheld
microphone, headset, or speaker used at the second pilot station.
    (3) For the third channel--from the cockpit-mounted area
microphone.
    (4) For the fourth channel from:
    (i) Each boom, mask, or handheld microphone, headset, or speaker
used at the station for the third and fourth crewmembers.
    (ii) If the stations specified in paragraph (c)(4)(i) of this
section are not required or if the signal at such a station is picked
up by another channel, each microphone on the flight deck that is used
with the passenger loudspeaker system, if its signals are not picked up
by another channel.
    (5) And that as far as is practicable all sounds received by the
microphone listed in paragraphs (c)(1), (2), and (4) of this section
must be recorded without interruption irrespective of the position of
the interphone-transmitter key switch. The design shall ensure that
sidetone for the flightcrew is produced only when the interphone,
public address system, or radio transmitters are in use.
    (d) Each cockpit voice recorder must be installed so that:
    (1) (i) It receives its electrical power from the bus that provides
the maximum reliability for operation of the cockpit voice recorder
without jeopardizing service to essential or emergency loads.
    (ii) It remains powered for as long as possible without
jeopardizing emergency operation of the airplane.
    (2) There is an automatic means to simultaneously stop the recorder
and prevent each erasure feature from functioning, within 10 minutes
after crash impact.
    (3) There is an aural or visual means for preflight checking of the
recorder for proper operation.
    (4) Any single electrical failure external to the recorder does not
disable both the cockpit voice recorder and the flight data recorder.
    (5) It has an independent power source--
    (i) That provides 101 minutes of electrical power to
operate both the cockpit voice recorder and cockpit-mounted area
microphone;
    (ii) That is located as close as practicable to the cockpit voice
recorder; and
    (iii) To which the cockpit voice recorder and cockpit-mounted area
microphone are switched automatically in the event that all other power
to the cockpit voice recorder is interrupted either by normal shutdown
or by any other loss of power to the electrical power bus.
    (6) It is in a separate container from the flight data recorder
when both are required. If used to comply with only the cockpit voice
recorder requirements, a combination unit may be installed.
    (e) The recorder container must be located and mounted to minimize
the probability of rupture of the container as a result of crash impact
and consequent heat damage to the recorder from fire.
    (1) Except as provided in paragraph (e)(2) of this section, the
recorder container must be located as far aft as practicable, but need
not be outside of the pressurized compartment, and may not be located
where aft-mounted engines may crush the container during impact.
    (2) If two separate combination digital flight data recorder and
cockpit voice recorder units are installed instead of one cockpit voice
recorder and one digital flight data recorder, the combination unit
that is installed to comply with the cockpit voice recorder
requirements may be located near the cockpit.
    (f) If the cockpit voice recorder has a bulk erasure device, the
installation must be designed to minimize the probability of
inadvertent operation and actuation of the device during crash impact.
    (g) Each recorder container must--
    (1) Be either bright orange or bright yellow;
    (2) Have reflective tape affixed to its external surface to
facilitate its location under water; and
    (3) Have an underwater locating device, when required by the
operating rules of this chapter, on or adjacent to the container, which
is secured in such manner that they are not likely to be separated
during crash impact.

Sec.  23.1459  Flight data recorders.

    (a) Each flight recorder required by the operating rules of this
chapter must be installed so that--
    (1) It is supplied with airspeed, altitude, and directional data
obtained from sources that meet the aircraft level system requirements
of Sec.  23.1300 and the functionality specified in Sec.  23.1305;
    (2) The vertical acceleration sensor is rigidly attached, and
located longitudinally either within the approved center of gravity
limits of the airplane, or at a distance forward or aft of these limits
that does not exceed 25 percent of the airplane's mean aerodynamic
chord;
    (3)(i) It receives its electrical power from the bus that provides
the

maximum reliability for operation of the flight data recorder without
jeopardizing service to essential or emergency loads;
    (ii) It remains powered for as long as possible without
jeopardizing emergency operation of the airplane;
    (4) There is an aural or visual means for preflight checking of the
recorder for proper recording of data in the storage medium;
    (5) Except for recorders powered solely by the engine-driven
electrical generator system, there is an automatic means to
simultaneously stop a recorder that has a data erasure feature and
prevent each erasure feature from functioning, within 10 minutes after
crash impact;
    (6) Any single electrical failure external to the recorder does not
disable both the cockpit voice recorder and the flight data recorder;
and
    (7) It is in a separate container from the cockpit voice recorder
when both are required. If used to comply with only the flight data
recorder requirements, a combination unit may be installed. If a
combination unit is installed as a cockpit voice recorder to comply
with Sec.  23.1457(e)(2), a combination unit must be used to comply
with this flight data recorder requirement.
    (b) Each non-ejectable record container must be located and mounted
so as to minimize the probability of container rupture resulting from
crash impact and subsequent damage to the record from fire. In meeting
this requirement, the record container must be located as far aft as
practicable, but need not be aft of the pressurized compartment, and
may not be where aft-mounted engines may crush the container upon
impact.
    (c) A correlation must be established between the flight recorder
readings of airspeed, altitude, and heading and the corresponding
readings (taking into account correction factors) of the first pilot's
instruments. The correlation must cover the airspeed range over which
the airplane is to be operated, the range of altitude to which the
airplane is limited, and 360 degrees of heading. Correlation may be
established on the ground as appropriate.
    (d) Each recorder container must--
    (1) Be either bright orange or bright yellow;
    (2) Have reflective tape affixed to its external surface to
facilitate its location under water; and
    (3) Have an underwater locating device, when required by the
operating rules of this chapter, on or adjacent to the container, which
is secured in such a manner that they are not likely to be separated
during crash impact.
    (e) Any novel or unique design or operational characteristics of
the aircraft shall be evaluated to determine if any dedicated
parameters must be recorded on flight recorders in addition to or in
place of existing requirements.

Subpart G--Flightcrew Interface and Other Information

Sec.  23.1500  Flightcrew interface.

    (a) The pilot compartment and its equipment must allow each pilot
to perform his or her duties, including taxi, takeoff, climb, cruise,
descent, approach, landing, and perform any maneuvers within the
operating envelope of the airplane, without excessive concentration,
skill, alertness, or fatigue.
    (b) The applicant must install flight, navigation, surveillance,
and powerplant controls and displays so qualified flightcrew can
monitor and perform all tasks associated with the intended functions of
systems and equipment. The system and equipment design must make the
possibility that a flightcrew error could result in a catastrophic
event highly unlikely.

Sec.  23.1505  Instrument markings, control markings, and placards.

    (a) Each airplane must display in a conspicuous manner any placard
and instrument marking necessary for operation.
    (b) The applicant must clearly mark each cockpit control, other
than primary flight controls, as to its function and method of
operation.
    (c) The applicant must include instrument marking and placard
information in the Airplane Flight Manual.

Sec.  23.1510  Airplane flight manual.

    The applicant must provide an Airplane Flight Manual that must be
delivered with each airplane that contains the following information--
    (a) Operating limitations and procedures;
    (b) Performance information;
    (c) Loading information; and
    (d) Any other information necessary for the operation of the
airplane.

Sec.  23.1515  Instructions for continued airworthiness.

    The applicant must prepare Instructions for Continued
Airworthiness, in accordance with appendix A of this part, that are
acceptable to the Administrator prior to the delivery of the first
airplane or issuance of a standard certification of airworthiness,
whichever occurs later.

Appendix A to Part 23--Instructions for Continued Airworthiness

A23.1 General

    (a) This appendix specifies requirements for the preparation of
Instructions for Continued Airworthiness as required by this part.
    (b) The Instructions for Continued Airworthiness for each airplane
must include the Instructions for Continued Airworthiness for each
engine and propeller (hereinafter designated ``products''), for each
appliance required by this chapter, and any required information
relating to the interface of those appliances and products with the
airplane. If Instructions for Continued Airworthiness are not supplied
by the manufacturer of an appliance or product installed in the
airplane, the Instructions for Continued Airworthiness for the airplane
must include the information essential to the continued airworthiness
of the airplane.
    (c) The applicant must submit to the FAA a program to show how
changes to the Instructions for Continued Airworthiness made by the
applicant or by the manufacturers of products and appliances installed
in the airplane will be distributed.

A23.2 Format

    (a) The Instructions for Continued Airworthiness must be in the
form of a manual or manuals as appropriate for the quantity of data to
be provided.
    (b) The format of the manual or manuals must provide for a
practical arrangement.

A23.3 Content

    The contents of the manual or manuals must be prepared in the
English language. The Instructions for Continued Airworthiness must
contain the following manuals or sections and information:
    (a) Airplane maintenance manual or section.
    (1) Introduction information that includes an explanation of the
airplane's features and data to the extent necessary for maintenance or
preventive maintenance.
    (2) A description of the airplane and its systems and installations
including its engines, propellers, and appliances.
    (3) Basic control and operation information describing how the
airplane components and systems are controlled and how they operate,
including any special procedures and limitations that apply.
    (4) Servicing information that covers details regarding servicing
points, capacities of tanks, reservoirs, types of fluids to be used,
pressures applicable

to the various systems, location of access panels for inspection and
servicing, locations of lubrication points, lubricants to be used,
equipment required for servicing, tow instructions and limitations,
mooring, jacking, and leveling information.

(b) Maintenance Instructions

    (1) Scheduling information for each part of the airplane and its
engines, auxiliary power units, propellers, accessories, instruments,
and equipment that provides the recommended periods at which they
should be cleaned, inspected, adjusted, tested, and lubricated, and the
degree of inspection, the applicable wear tolerances, and work
recommended at these periods. However, the applicant may refer to an
accessory, instrument, or equipment manufacturer as the source of this
information if the applicant shows that the item has an exceptionally
high degree of complexity requiring specialized maintenance techniques,
test equipment, or expertise. The recommended overhaul periods and
necessary cross reference to the Airworthiness Limitations section of
the manual must also be included. In addition, the applicant must
include an inspection program that includes the frequency and extent of
the inspections necessary to provide for the continued airworthiness of
the airplane.
    (2) Troubleshooting information describing probable malfunctions,
how to recognize those malfunctions, and the remedial action for those
malfunctions.
    (3) Information describing the order and method of removing and
replacing products and parts with any necessary precautions to be
taken.
    (4) Other general procedural instructions including procedures for
system testing during ground running, symmetry checks, weighing and
determining the center of gravity, lifting and shoring, and storage
limitations.
    (c) Diagrams of structural access plates and information needed to
gain access for inspections when access plates are not provided.
    (d) Details for the application of special inspection techniques
including radiographic and ultrasonic testing where such processes are
specified by the applicant.
    (e) Information needed to apply protective treatments to the
structure after inspection.
    (f) All data relative to structural fasteners such as
identification, discard recommendations, and torque values.
    (g) A list of special tools needed.
    (h) In addition, for level 4 airplanes, the following information
must be furnished--
    (1) Electrical loads applicable to the various systems;
    (2) Methods of balancing control surfaces;
    (3) Identification of primary and secondary structures; and
    (4) Special repair methods applicable to the airplane.

A23.4 Airworthiness limitations section

    The Instructions for Continued Airworthiness must contain a section
titled Airworthiness Limitations that is segregated and clearly
distinguishable from the rest of the document. This section must set
forth each mandatory replacement time, structural inspection interval,
and related structural inspection procedure required for type
certification. If the Instructions for Continued Airworthiness consist
of multiple documents, the section required by this paragraph must be
included in the principal manual. This section must contain a legible
statement in a prominent location that reads ``The Airworthiness
Limitations section is FAA approved and specifies maintenance required
under Sec. Sec.  43.16 and 91.403 of Title 14 of the Code of Federal
Regulations unless an alternative program has been FAA approved.''

PART 35--AIRWORTHINESS STANDARDS: PROPELLERS

0
9. The authority citation for part 35 is revised to read as follows:

    Authority: 49 U.S.C. 106(f), 106(g), 40113, 44701-44702, 44704.

0
10. In Sec.  35.1, revise paragraph (c) to read as follows:

Sec.  35.1  Applicability.

* * * * *
    (c) An applicant is eligible for a propeller type certificate and
changes to those certificates after demonstrating compliance with
subparts A, B, and C of this part. However, the propeller may not be
installed on an airplane unless the applicant has shown compliance with
either Sec.  23.905(c) or Sec.  25.907 of this chapter, as applicable,
or compliance is not required for installation on that airplane.
* * * * *
0
11. In Sec.  35.37, revise paragraph (c)(1) to read as follows:

Sec.  35.37  Fatigue limits and evaluation.

* * * * *
    (c) * * *
    (1) The intended airplane by complying with Sec.  23.905(c) or
Sec.  25.907 of this chapter, as applicable; or
* * * * *

PART 43--MAINTENANCE, PREVENTIVE MAINTENANCE, REBUILDING, AND
ALTERATION

0
12. The authority citation for part 43 is revised to read as follows:

    Authority: 42 U.S.C. 7572; 49 U.S.C. 106(f), 106(g), 40105,
40113, 44701-44702, 44704, 44707, 44709, 44711, 44713, 44715, 45303.

0
13. In part 43, appendix E, revise the introductory text and paragraph
(a)(2) to read as follows:

Appendix E to Part 43--Altimeter System Test and Inspection

    Each person performing the altimeter system tests and inspections
required by Sec.  91.411 must comply with the following:
    (a) * * *
    (2) Perform a proof test to demonstrate the integrity of the static
pressure system in a manner acceptable to the Administrator. For
airplanes certificated under part 25 of this chapter, determine that
leakage is within the tolerances established by Sec.  25.1325.
* * * * *

PART 91--GENERAL OPERATING AND FLIGHT RULES

0
14. The authority citation for part 91 continues to read as follows:

    Authority: 49 U.S.C. 106(f), 106(g), 1155, 40101, 40103, 40105,
40113, 40120, 44101, 44111, 44701, 44704, 44709, 44711, 44712,
44715, 44716, 44717, 44722, 46306, 46315, 46316, 46504, 46506-46507,
47122, 47508, 47528-47531, 47534, articles 12 and 29 of the
Convention on International Civil Aviation (61 Stat. 1180), (126
Stat. 11).

0
15. In Sec.  91.205, revise paragraphs (b)(13) and (b)(14), and remove
paragraph (b)(16) to read as follows:

Sec.  91.205  Powered civil aircraft with standard category U.S.
airworthiness certificates: Instrument and equipment requirements.

* * * * *
    (b) * * *
    (13) An approved safety belt with an approved metal-to-metal
latching device, or other approved restraint system for each occupant 2
years of age or older.
    (14) For small civil airplanes manufactured after July 18, 1978, an
approved shoulder harness or restraint system for each front seat. For
small civil airplanes manufactured after December 12, 1986, an approved
shoulder harness or restraint system for all seats. Shoulder harnesses
installed at flightcrew stations must permit the flightcrew member,
when seated and with the safety belt and shoulder harness fastened, to
perform all

functions necessary for flight operations. For purposes of this
paragraph--
    (i) The date of manufacture of an airplane is the date the
inspection acceptance records reflect that the airplane is complete and
meets the FAA-approved type design data; and
    (ii) A front seat is a seat located at a flightcrew member station
or any seat located alongside such a seat.
* * * * *
0
16. In Sec.  91.313, revise paragraph (g) introductory text to read as
follows:

Sec.  91.313  Restricted category civil aircraft: Operating
limitations.

* * * * *
    (g) No person may operate a small restricted-category civil
airplane manufactured after July 18, 1978, unless an approved shoulder
harness or restraint system is installed for each front seat. The
shoulder harness or restraint system installation at each flightcrew
station must permit the flightcrew member, when seated and with the
safety belt and shoulder harness fastened or the restraint system
engaged, to perform all functions necessary for flight operation. For
purposes of this paragraph--
* * * * *
0
17. In Sec.  91.323, revise paragraph (b)(3) to read as follows:

Sec.  91.323  Increased maximum certificated weights for certain
airplanes operated in Alaska.

* * * * *
    (b) * * *
    (3) The weight at which the airplane meets the positive maneuvering
load factor n, where n = 2.1 + (24,000/(W + 10,000)) and W = design
maximum takeoff weight, except that n need not be more than 3.8; or
* * * * *
0
18. In Sec.  91.531, revise paragraphs (a)(1) and (a)(3) to read as
follows:

Sec.  91.531  Second in command requirements.

    (a) * * *
    (1) A large airplane or normal category level 4 airplane, except
that a person may operate an airplane certificated under SFAR 41
without a pilot who is designated as second in command if that airplane
is certificated for operation with one pilot.
    * * *
    (3) A commuter category airplane or normal category level 3
airplane, except that a person may operate those airplanes
notwithstanding paragraph (a)(1) of this section, that have a passenger
seating configuration, excluding pilot seats, of nine or less without a
pilot who is designated as second in command if that airplane is type
certificated for operations with one pilot.
* * * * *

PART 121--OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL
OPERATIONS

0
19. The authority citation for part 121 continues to read as follows:

    Authority: 49 U.S.C. 106(f), 106(g), 40103, 40113, 40119, 41706,
42301 preceding note added by Pub. L. 112-95, Sec. 412, 126 Stat.
89, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717,
44722, 44729, 44732; 46105; Pub. L. 111-216, 124 Stat. 2348 (49
U.S.C. 44701 note); Pub. L. 112-95, 126 Stat. 62 (49 U.S.C. 44732
note).

0
20. In Sec.  121.310, revise paragraph (b)(2)(iii) to read as follows:

Sec.  121.310  Additional emergency equipment.

* * * * *
    (b) * * *
    (2) * * *
    (iii) For a nontransport category turbopropeller powered airplane
type certificated after December 31, 1964, each passenger emergency
exit marking and each locating sign must be manufactured to meet the
requirements of Sec.  23.811(b) of this chapter in effect on June 16,
1994. On these airplanes, no sign may continue to be used if its
luminescence (brightness) decreases to below 100 microlamberts.
* * * * *

PART 135--OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS
AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT

0
21. The authority citation for part 135 continues to read as follows:

    Authority: 49 U.S.C. 106(f), 106(g), 41706, 40113, 44701-44702,
44705, 44709, 44711-44713, 44715-44717, 44722, 44730, 45101-45105;
Pub. L. 112-95, 126 Stat. 58 (49 U.S.C. 44730).

0
22. In Sec.  135.169, revise paragraphs (b) introductory text, (b)(6),
and (b)(7), and add paragraph (b)(8) to read as follows:

Sec.  135.169  Additional airworthiness requirements.

* * * * *
    (b) No person may operate a small airplane that has a passenger
seating configuration, excluding pilot seats, of 10 seats or more
unless it is type certificated--
* * * * *
    (6) In the normal category and complies with section 1.(b) of
Special Federal Aviation Regulation No. 41;
    (7) In the commuter category; or
    (8) In the normal category, using a means of compliance accepted by
the Administrator equivalent to the airworthiness standards applicable
to the certification of airplanes in the commuter category found in
part 23 of this chapter through amendment 23-62, effective January 31,
2012.
* * * * *

    Issued under authority provided by 49 U.S.C. 106(f), 44701(a),
44703 and Pub. L. 113-53 (127 Stat. 584; 49 U.S.C. 44704 note) in
Washington, DC, on March 7, 2016.
Dorenda D. Baker,
Director, Aircraft Certification Service.
[FR Doc. 2016-05493 Filed 3-9-16; 11:15 am]
 BILLING CODE 4910-13-P