391 

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 work-

load 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 emer-
gency 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 sys-
tem malfunction, and other failure or cau-
tion indicators. The extent to which such in-
struments or devices direct the proper cor-
rective action is also considered. 

(3) The number, urgency, and complexity 

of operating procedures with particular con-
sideration given to the specific fuel manage-
ment schedule imposed by center of gravity, 
structural or other considerations of an air-
worthiness nature, and to the ability of each 
engine to operate at all times from a single 
tank or source which is automatically re-
plenished if fuel is also stored in other tanks. 

(4) The degree and duration of con-

centrated mental and physical effort in-
volved in normal operation and in diagnosing 
and coping with malfunctions and emer-
gencies. 

(5) The extent of required monitoring of 

the fuel, hydraulic, pressurization, elec-
trical, 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, emer-
gency operation of any control, and emer-
gencies in any compartment. 

(7) The degree of automation provided in 

the aircraft systems to afford (after failures 
or malfunctions) automatic crossover or iso-
lation 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 re-
quires a minimum flight crew of at least two 
pilots. 

(c) 

Kind of operation authorized. 

The deter-

mination 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] 

A

PPENDIX

E 

TO

P

ART

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 type- 
certificated standby power rocket engine 
may obtain an increase as specified in para-
graph (b) if— 

(1) The installation of the rocket engine 

has been approved and it has been estab-
lished 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 Adminis-
trator may require, the increased weight ap-
proved under this regulation and a prohibi-
tion against the operation of the airplane at 
the approved increased weight when— 

(i) The installed standby power rocket en-

gines have been stored or installed in excess 
of the time limit established by the manu-
facturer of the rocket engine (usually sten-
ciled on the engine casing); or 

(ii) The rocket engine fuel has been ex-

pended or discharged. 

(b) The currently approved maximum take-

off and landing weights at which an airplane 
is certificated without a standby power rock-
et 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 cur-

rently approved maximum weight, would 
equal the maximum structural weight estab-
lished for the airplane without standby rock-
et 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 trans-
port category airplanes. However, the per-
formance credit applies only to the max-
imum certificated takeoff and landing 

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