spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Pt. 25, App. E

(5) Operation and monitoring of aircraft
engines and systems.
(6) Command decisions.
(b) Workload factors. The following workload factors are considered significant when
analyzing and demonstrating workload for
minimum flight crew determination:
(1) The accessibility, ease, and simplicity
of operation of all necessary flight, power,
and equipment controls, including emergency fuel shutoff valves, electrical controls,
electronic controls, pressurization system
controls, and engine controls.
(2) The accessibility and conspicuity of all
necessary instruments and failure warning
devices such as fire warning, electrical system malfunction, and other failure or caution indicators. The extent to which such instruments or devices direct the proper corrective action is also considered.
(3) The number, urgency, and complexity
of operating procedures with particular consideration given to the specific fuel management schedule imposed by center of gravity,
structural or other considerations of an airworthiness nature, and to the ability of each
engine to operate at all times from a single
tank or source which is automatically replenished if fuel is also stored in other tanks.
(4) The degree and duration of concentrated mental and physical effort involved in normal operation and in diagnosing
and coping with malfunctions and emergencies.
(5) The extent of required monitoring of
the fuel, hydraulic, pressurization, electrical, electronic, deicing, and other systems
while en route.
(6) The actions requiring a crewmember to
be unavailable at his assigned duty station,
including: observation of systems, emergency operation of any control, and emergencies in any compartment.
(7) The degree of automation provided in
the aircraft systems to afford (after failures
or malfunctions) automatic crossover or isolation of difficulties to minimize the need for
flight crew action to guard against loss of
hydraulic or electric power to flight controls
or to other essential systems.
(8) The communications and navigation
workload.
(9) The possibility of increased workload
associated with any emergency that may
lead to other emergencies.
(10) Incapacitation of a flight crewmember
whenever the applicable operating rule requires a minimum flight crew of at least two
pilots.
(c) Kind of operation authorized. The determination of the kind of operation authorized
requires consideration of the operating rules
under which the airplane will be operated.
Unless an applicant desires approval for a
more limited kind of operation. It is assumed

that each airplane certificated under this
Part will operate under IFR conditions.
[Amdt. 25-3, 30 FR 6067, Apr. 29, 1965]

APPENDIX E TO PART 25
I - Limited Weight Credit For Airplanes
Equipped With Standby Power
(a) Each applicant for an increase in the
maximum certificated takeoff and landing
weights of an airplane equipped with a typecertificated standby power rocket engine
may obtain an increase as specified in paragraph (b) if - 
(1) The installation of the rocket engine
has been approved and it has been established by flight test that the rocket engine
and its controls can be operated safely and
reliably at the increase in maximum weight;
and
(2) The Airplane Flight Manual, or the
placard, markings or manuals required in
place thereof, set forth in addition to any
other operating limitations the Administrator may require, the increased weight approved under this regulation and a prohibition against the operation of the airplane at
the approved increased weight when - 
(i) The installed standby power rocket engines have been stored or installed in excess
of the time limit established by the manufacturer of the rocket engine (usually stenciled on the engine casing); or
(ii) The rocket engine fuel has been expended or discharged.
(b) The currently approved maximum takeoff and landing weights at which an airplane
is certificated without a standby power rocket engine installation may be increased by
an amount that does not exceed any of the
following:
(1) An amount equal in pounds to 0.014 IN,
where I is the maximum usable impulse in
pounds-seconds available from each standby
power rocket engine and N is the number of
rocket engines installed.
(2) An amount equal to 5 percent of the
maximum certificated weight approved in
accordance with the applicable airworthiness
regulations without standby power rocket
engines installed.
(3) An amount equal to the weight of the
rocket engine installation.
(4) An amount that, together with the currently approved maximum weight, would
equal the maximum structural weight established for the airplane without standby rocket engines installed.
II - Performance Credit for Transport Category
Airplanes Equipped With Standby Power
The Administrator may grant performance
credit for the use of standby power on transport category airplanes. However, the performance credit applies only to the maximum certificated takeoff and landing

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