spaschal on DSK3GDR082PROD with CFR

Section 33.7

14 CFR Ch. I (1-1-19 Edition)

prior to the issuance of the type certificate, and to the owner at the time
of delivery of the engine, approved instructions for installing and operating
the engine. The instructions must include at least the following:
(a) Installation instructions. (1) The location of engine mounting attachments, the method of attaching the engine to the aircraft, and the maximum
allowable load for the mounting attachments and related structure.
(2) The location and description of
engine connections to be attached to
accessories, pipes, wires, cables, ducts,
and cowling.
(3) An outline drawing of the engine
including overall dimensions.
(4) A definition of the physical and
functional interfaces with the aircraft
and aircraft equipment, including the
propeller when applicable.
(5) Where an engine system relies on
components that are not part of the engine type design, the interface conditions and reliability requirements for
those components upon which engine
type certification is based must be
specified in the engine installation instructions directly or by reference to
appropriate documentation.
(6) A list of the instruments necessary for control of the engine, including the overall limits of accuracy and
transient response required of such instruments for control of the operation
of the engine, must also be stated so
that the suitability of the instruments
as installed may be assessed.
(b) Operation instructions. (1) The operating limitations established by the
Administrator.
(2) The power or thrust ratings and
procedures for correcting for nonstandard atmosphere.
(3) The recommended procedures,
under normal and extreme ambient
conditions for - 
(i) Starting;
(ii) Operating on the ground; and
(iii) Operating during flight.
(4) For rotorcraft engines having one
or more OEI ratings, applicants must
provide data on engine performance
characteristics and variability to enable the aircraft manufacturer to establish aircraft power assurance procedures.

(5) A description of the primary and
all alternate modes, and any back-up
system, together with any associated
limitations, of the engine control system and its interface with the aircraft
systems, including the propeller when
applicable.
(c) Safety analysis assumptions. The
assumptions of the safety analysis as
described in Section 33.75(d) with respect to
the reliability of safety devices, instrumentation, early warning devices,
maintenance
checks,
and
similar
equipment or procedures that are outside the control of the engine manufacturer.
[Amdt. 33-6, 39 FR 35463, Oct. 1, 1974, as
amended by Amdt. 33-9, 45 FR 60181, Sept. 11,
1980; Amdt. 33-24, 47 FR 50867, Sept. 4, 2007;
Amdt. 33-25, 73 FR 48123, Aug. 18, 2008; Amdt.
33-26, 73 FR 48284, Aug. 19, 2008]

Section 33.7 Engine ratings and operating
limitations.
(a) Engine ratings and operating limitations are established by the Administrator and included in the engine certificate data sheet specified in Section 21.41 of
this chapter, including ratings and limitations based on the operating conditions and information specified in this
section, as applicable, and any other
information found necessary for safe
operation of the engine.
(b) For reciprocating engines, ratings
and operating limitations are established relating to the following:
(1) Horsepower or torque, r.p.m.,
manifold pressure, and time at critical
pressure altitude and sea level pressure
altitude for - 
(i) Rated maximum continuous power
(relating to unsupercharged operation
or to operation in each supercharger
mode as applicable); and
(ii) Rated takeoff power (relating to
unsupercharged operation or to operation in each supercharger mode as applicable).
(2) Fuel grade or specification.
(3) Oil grade or specification.
(4) Temperature of the - 
(i) Cylinder;
(ii) Oil at the oil inlet; and
(iii) Turbosupercharger turbine wheel
inlet gas.
(5) Pressure of - 
(i) Fuel at the fuel inlet; and
(ii) Oil at the main oil gallery.

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