269 

Federal Aviation Administration, DOT 

§ 23.903 

(1) Ensure safe operation to the max-

imum altitude for which approval is re-
quested. 

(2) Be accessible for necessary inspec-

tions and maintenance. 

(c) Engine cowls and nacelles must be 

easily removable or openable by the 
pilot to provide adequate access to and 
exposure of the engine compartment 
for preflight checks. 

(d) Each turbine engine installation 

must be constructed and arranged to— 

(1) Result in carcass vibration char-

acteristics that do not exceed those es-
tablished during the type certification 
of the engine. 

(2) Ensure that the capability of the 

installed engine to withstand the in-
gestion of rain, hail, ice, and birds into 
the engine inlet is not less than the ca-
pability established for the engine 
itself under § 23.903(a)(2). 

(e) The installation must comply 

with— 

(1) The instructions provided under 

the engine type certificate and the pro-
peller type certificate. 

(2) The applicable provisions of this 

subpart. 

(f) Each auxiliary power unit instal-

lation must meet the applicable por-
tions of this part. 

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as 
amended by Amdt. 23–7, 34 FR 13092, Aug. 13, 
1969; Amdt. 23–18, 42 FR 15041, Mar. 17, 1977; 
Amdt. 23–29, 49 FR 6846, Feb. 23, 1984; Amdt. 
23–34, 52 FR 1832, Jan. 15, 1987; Amdt. 23–34, 52 
FR 34745, Sept. 14, 1987; Amdt. 23–43, 58 FR 
18970, Apr. 9, 1993; Amdt. 23–51, 61 FR 5136, 
Feb. 9, 1996; Amdt. 23–53, 63 FR 14797, Mar. 26, 
1998] 

§ 23.903

Engines. 

(a) 

Engine type certificate. (1) Each en-

gine must have a type certificate and 
must meet the applicable requirements 
of part 34 of this chapter. 

(2) Each turbine engine and its in-

stallation must comply with one of the 
following: 

(i) Sections 33.76, 33.77 and 33.78 of 

this chapter in effect on December 13, 
2000, or as subsequently amended; or 

(ii) Sections 33.77 and 33.78 of this 

chapter in effect on April 30, 1998, or as 
subsequently amended before Decem-
ber 13, 2000; or 

(iii) Section 33.77 of this chapter in 

effect on October 31, 1974, or as subse-
quently amended before April 30, 1998, 

unless that engine’s foreign object in-
gestion service history has resulted in 
an unsafe condition; or 

(iv) Be shown to have a foreign object 

ingestion service history in similar in-
stallation locations which has not re-
sulted in any unsafe condition. 

N

OTE

: § 33.77 of this chapter in effect on Oc-

tober 31, 1974, was published in 14 CFR parts 
1 to 59, Revised as of January 1, 1975. See 39 
FR 35467, October 1, 1974. 

(b) 

Turbine engine installations. For 

turbine engine installations— 

(1) Design precautions must be taken 

to minimize the hazards to the airplane 
in the event of an engine rotor failure 
or of a fire originating inside the en-
gine which burns through the engine 
case. 

(2) The powerplant systems associ-

ated with engine control devices, sys-
tems, and instrumentation must be de-
signed to give reasonable assurance 
that those operating limitations that 
adversely affect turbine rotor struc-
tural integrity will not be exceeded in 
service. 

(3) For engines embedded in the fuse-

lage behind the cabin, the effects of a 
fan exiting forward of the inlet case 
(fan disconnect) must be addressed, the 
passengers must be protected, and the 
airplane must be controllable to allow 
for continued safe flight and landing. 

(c) 

Engine isolation. The powerplants 

must be arranged and isolated from 
each other to allow operation, in at 
least one configuration, so that the 
failure or malfunction of any engine, or 
the failure or malfunction (including 
destruction by fire in the engine com-
partment) of any system that can af-
fect an engine (other than a fuel tank 
if only one fuel tank is installed), will 
not: 

(1) Prevent the continued safe oper-

ation of the remaining engines; or 

(2) Require immediate action by any 

crewmember for continued safe oper-
ation of the remaining engines. 

(d) 

Starting and stopping (piston en-

gine).  (1) The design of the installation 
must be such that risk of fire or me-
chanical damage to the engine or air-
plane, as a result of starting the engine 
in any conditions in which starting is 
to be permitted, is reduced to a min-
imum. Any techniques and associated 
limitations for engine starting must be 

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