700 

14 CFR Ch. I (1–1–24 Edition) 

§ 33.7 

prior to the issuance of the type cer-
tificate, and to the owner at the time 
of delivery of the engine, approved in-
structions for installing and operating 
the engine. The instructions must in-
clude at least the following: 

(a) 

Installation instructions. (1) The lo-

cation of engine mounting attach-
ments, the method of attaching the en-
gine to the aircraft, and the maximum 
allowable load for the mounting at-
tachments 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 en-
gine type design, the interface condi-
tions and reliability requirements for 
those components upon which engine 
type certification is based must be 
specified in the engine installation in-
structions directly or by reference to 
appropriate documentation. 

(6) A list of the instruments nec-

essary for control of the engine, includ-
ing the overall limits of accuracy and 
transient response required of such in-
struments 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 op-

erating limitations established by the 
Administrator. 

(2) The power or thrust ratings and 

procedures for correcting for non-
standard 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 en-
able the aircraft manufacturer to es-
tablish aircraft power assurance proce-
dures. 

(5) A description of the primary and 

all alternate modes, and any back-up 
system, together with any associated 
limitations, of the engine control sys-
tem 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 § 33.75(d) with respect to 
the reliability of safety devices, instru-
mentation, early warning devices, 
maintenance checks, and similar 
equipment or procedures that are out-
side the control of the engine manufac-
turer. 

[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] 

§ 33.7

Engine ratings and operating 

limitations. 

(a) Engine ratings and operating lim-

itations are established by the Admin-
istrator and included in the engine cer-
tificate data sheet specified in § 21.41 of 
this chapter, including ratings and lim-
itations based on the operating condi-
tions 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 estab-
lished 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 oper-
ation in each supercharger mode as ap-
plicable). 

(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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701 

Federal Aviation Administration, DOT 

§ 33.15 

(6) Accessory drive torque and over-

hang moment. 

(7) Component life. 
(8) Turbosupercharger turbine wheel 

r.p.m. 

(c) For turbine engines, ratings and 

operating limitations are established 
relating to the following: 

(1) Horsepower, torque, or thrust, 

r.p.m., gas temperature, and time for— 

(i) Rated maximum continuous power 

or thrust (augmented); 

(ii) Rated maximum continuous 

power or thrust (unaugmented); 

(iii) Rated takeoff power or thrust 

(augmented); 

(iv) Rated takeoff power or thrust 

(unaugmented); 

(v) Rated 30-minute OEI power; 
(vi) Rated 2

1

⁄

2

-minute OEI power; 

(vii) Rated continuous OEI power; 

and 

(viii) Rated 2-minute OEI Power; 
(ix) Rated 30-second OEI power; and 
(x) Auxiliary power unit (APU) mode 

of operation. 

(2) Fuel designation or specification. 
(3) Oil grade or specification. 
(4) Hydraulic fluid specification. 
(5) Temperature of— 
(i) Oil at a location specified by the 

applicant; 

(ii) Induction air at the inlet face of 

a supersonic engine, including steady 
state operation and transient over- 
temperature and time allowed; 

(iii) Hydraulic fluid of a supersonic 

engine; 

(iv) Fuel at a location specified by 

the applicant; and 

(v) External surfaces of the engine, if 

specified by the applicant. 

(6) Pressure of— 
(i) Fuel at the fuel inlet; 
(ii) Oil at a location specified by the 

applicant; 

(iii) Induction air at the inlet face of 

a supersonic engine, including steady 
state operation and transient over-
pressure and time allowed; and 

(iv) Hydraulic fluid. 
(7) Accessory drive torque and over-

hang moment. 

(8) Component life. 
(9) Fuel filtration. 
(10) Oil filtration. 
(11) Bleed air. 
(12) The number of start-stop stress 

cycles approved for each rotor disc and 
spacer. 

(13) Inlet air distortion at the engine 

inlet. 

(14) Transient rotor shaft overspeed 

r.p.m., and number of overspeed occur-
rences. 

(15) Transient gas overtemperature, 

and number of overtemperature occur-
rences. 

(16) Transient engine overtorque, and 

number of overtorque occurrences. 

(17) Maximum engine overtorque for 

turbopropeller and turboshaft engines 
incorporating free power turbines. 

(18) For engines to be used in super-

sonic aircraft, engine rotor 
windmilling rotational r.p.m. 

(d) In determining the engine per-

formance and operating limitations, 
the overall limits of accuracy of the 
engine control system and of the nec-
essary instrumentation as defined in 
§ 33.5(a)(6) must be taken into account. 

[Amdt. 33–6, 39 FR 35463, Oct. 1, 1974, as 
amended by Amdt. 33–10, 49 FR 6850, Feb. 23, 
1984; Amdt. 33–11, 51 FR 10346, Mar. 25, 1986; 
Amdt. 33–12, 53 FR 34220, Sept. 2, 1988; Amdt. 
33–18, 61 FR 31328, June 19, 1996; Amdt. 33–26, 
73 FR 48284, Aug. 19, 2008; Amdt. 33–30, 74 FR 
45310, Sept. 2, 2009] 

§ 33.8

Selection of engine power and 

thrust ratings. 

(a) Requested engine power and 

thrust ratings must be selected by the 
applicant. 

(b) Each selected rating must be for 

the lowest power or thrust that all en-
gines of the same type may be expected 
to produce under the conditions used to 
determine that rating. 

[Amdt. 33–3, 32 FR 3736, Mar. 4, 1967] 

Subpart B—Design and 

Construction; General 

§ 33.11

Applicability. 

This subpart prescribes the general 

design and construction requirements 
for reciprocating and turbine aircraft 
engines. 

§ 33.13

[Reserved] 

§ 33.15

Materials. 

The suitability and durability of ma-

terials used in the engine must— 

(a) Be established on the basis of ex-

perience or tests; and 

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