733 

Federal Aviation Administration, DOT 

§ 33.89 

during the periods specified in para-
graphs (g)(2)(ii) through (iv) of this sec-
tion; 

(ii) One period repeating the run 

specified in paragraph (g)(2)(i) of this 
section, except that it must be followed 
by 10 minutes at the thrust obtained 
with the power control lever set at the 
position for 80 percent of rated max-
imum continuous augmented thrust; 

(iii) One period repeating the run 

specified in paragraph (g)(2)(i) of this 
section, except that it must be followed 
by 10 minutes at the thrust obtained 
with the power control lever set at the 
position for 60 percent of rated max-
imum continuous augmented thrust 
and then 10 minutes at not more than 
15 percent of rated takeoff thrust; 

(iv) One period repeating the runs 

specified in paragraphs (g)(2)(i) and (ii) 
of this section; and 

(v) One period of 30 minutes with 25 

of the runs made at the thrust obtained 
with the power control lever set at the 
position for rated maximum contin-
uous augmented thrust, each followed 
by idle thrust and with the remaining 
5 runs at the thrust obtained with the 
power control lever set at the position 
for rated maximum continuous aug-
mented thrust for 25 minutes each, fol-
lowed by subsonic operation at not 
more than 15 percent or rated takeoff 
thrust and accelerated to rated takeoff 
thrust for 5 minutes using hot fuel. 

(3) 

Starts. 

One hundred starts must be 

made, of which 25 starts must be pre-
ceded by an engine shutdown of at 
least 2 hours. There must be at least 10 
false engine starts, pausing for the ap-
plicant’s specified minimum fuel drain-
age time before attempting a normal 
start. At least 10 starts must be normal 
restarts, each made no later than 15 
minutes after engine shutdown. The 
starts may be made at any time, in-
cluding the period of endurance test-
ing. 

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as 
amended by Amdt. 33–3, 32 FR 3737, Mar. 4, 
1967; Amdt. 33–6, 39 FR 35468, Oct. 1, 1974; 
Amdt. 33–10, 49 FR 6853, Feb. 23, 1984; Amdt. 
33–12, 53 FR 34220, Sept. 2, 1988; Amdt. 33–18, 
61 FR 31328, June 19, 1996; Amdt. 33–25, 73 FR 
48123, Aug. 18, 2008; Amdt. 33–30, 74 FR 45311, 
Sept. 2, 2009; Amdt. 33–32, 77 FR 22187, Apr. 
13, 2012] 

§ 33.88

Engine overtemperature test. 

(a) Each engine must run for 5 min-

utes at maximum permissible rpm with 
the gas temperature at least 75 

°

F (42 

°

C) higher than the maximum rating’s 

steady-state operating limit, excluding 
maximum values of rpm and gas tem-
perature associated with the 30-second 
OEI and 2-minute OEI ratings. Fol-
lowing this run, the turbine assembly 
must be within serviceable limits. 

(b) In addition to the test require-

ments in paragraph (a) of this section, 
each engine for which 30-second OEI 
and 2-minute OEI ratings are desired, 
that incorporates a means for auto-
matic temperature control within its 
operating limitations in accordance 
with § 33.28(k), must run for a period of 
4 minutes at the maximum power-on 
rpm with the gas temperature at least 
35 

°

F (19 

°

C) higher than the maximum 

operating limit at 30-second OEI rat-
ing. Following this run, the turbine as-
sembly may exhibit distress beyond the 
limits for an overtemperature condi-
tion provided the engine is shown by 
analysis or test, as found necessary by 
the FAA, to maintain the integrity of 
the turbine assembly. 

(c) A separate test vehicle may be 

used for each test condition. 

[Doc. No. 26019, 61 FR 31329, June 19, 1996, as 
amended by Amdt. 33–25, 73 FR 48124, Aug. 18, 
2008; Amdt. 33–26, 73 FR 48285, Aug. 19, 2008] 

§ 33.89

Operation test. 

(a) The operation test must include 

testing found necessary by the Admin-
istrator to demonstrate— 

(1) Starting, idling, acceleration, 

overspeeding, ignition, functioning of 
the propeller (if the engine is des-
ignated to operate with a propeller); 

(2) Compliance with the engine re-

sponse requirements of § 33.73; and 

(3) The minimum power or thrust re-

sponse time to 95 percent rated takeoff 
power or thrust, from power lever posi-
tions representative of minimum idle 
and of minimum flight idle, starting 
from stabilized idle operation, under 
the following engine load conditions: 

(i) No bleed air and power extraction 

for aircraft use. 

(ii) Maximum allowable bleed air and 

power extraction for aircraft use. 

VerDate Sep<11>2014 

12:50 Apr 30, 2019

Jkt 247046

PO 00000

Frm 00743

Fmt 8010

Sfmt 8010

Y:\SGML\247046.XXX

247046

spaschal on DSK3GDR082PROD with CFR