[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2006]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR33.49]
[Page 774-777]
TITLE 14--AERONAUTICS AND SPACE
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
PART 33_AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES--Table of Contents
Subpart D_Block Tests; Reciprocating Aircraft Engines
Sec. 33.49 Endurance test.
(a) General. Each engine must be subjected to an endurance test that
includes a total of 150 hours of operation (except as provided in
paragraph (e)(1)(iii) of this section) and, depending upon the type and
contemplated use of the engine, consists of one of the series of runs
specified in paragraphs (b) through (e) of this section, as applicable.
The runs must be made in the order found appropriate by the
Administrator for the particular engine being tested. During the
endurance test the engine power and the crankshaft rotational speed must
be kept within 3 percent of the rated values.
During the runs at rated take off power and for at least 35 hours at
rated maximum continuous power, one cylinder must be operated at not
less than the limiting temperature, the other cylinders must be operated
at a temperature not lower than 50 degrees F. below the limiting
temperature, and the oil inlet temperature must be maintained within
10 degrees F. of the limiting temperature. An
engine that is equipped with a propeller shaft must be fitted for the
endurance test with a propeller that thrust-loads the engine to the
maximum thrust which the engine is designed to resist at each applicable
operating condition specified in this section. Each accessory drive and
mounting attachment must be loaded. During operation at rated takeoff
power and rated maximum continuous power, the load imposed by each
accessory used only for an aircraft service must be the limit load
specified by the applicant for the engine drive or attachment point.
(b) Unsupercharged engines and engines incorporating a gear-driven
single-
[[Page 775]]
speed supercharger. For engines not incorporating a supercharger and for
engines incorporating a gear-driven single-speed supercharger the
applicant must conduct the following runs:
(1) A 30-hour run consisting of alternate periods of 5 minutes at
rated takeoff power with takeoff speed, and 5 minutes at maximum best
economy cruising power or maximum recommended cruising power.
(2) A 20-hour run consisting of alternate periods of 1\1/2\ hours at
rated maximum continuous power with maximum continuous speed, and \1/2\
hour at 75 percent rated maximum continuous power and 91 percent maximum
continuous speed.
(3) A 20-hour run consisting of alternate periods of 1\1/2\ hours at
rated maximum continuous power with maximum continuous speed, and \1/2\
hour at 70 percent rated maximum continuous power and 89 percent maximum
continuous speed.
(4) A 20-hour run consisting of alternate periods of 1\1/2\ hours at
rated maximum continuous power with maximum continuous speed, and \1/2\
hour at 65 percent rated maximum continuous power and 87 percent maximum
continuous speed.
(5) A 20-hour run consisting of alternate periods of 1\1/2\ hours at
rated maximum continuous power with maximum continuous speed, and \1/2\
hour at 60 percent rated maximum continuous power and 84.5 percent
maximum continuous speed.
(6) A 20-hour run consisting of alternate periods of 1\1/2\ hours at
rated maximum continuous power with maximum continuous speed, and \1/2\
hour at 50 percent rated maximum continuous power and 79.5 percent
maximum continuous speed.
(7) A 20-hour run consisting of alternate periods of 2\1/2\ hours at
rated maximum continuous power with maximum continuous speed, and 2\1/2\
hours at maximum best economy cruising power or at maximum recommended
cruising power.
(c) Engines incorporating a gear-driven two-speed supercharger. For
engines incorporating a gear-driven two-speed supercharger the applicant
must conduct the following runs:
(1) A 30-hour run consisting of alternate periods in the lower gear
ratio of 5 minutes at rated takeoff power with takeoff speed, and 5
minutes at maximum best economy cruising power or at maximum recommended
cruising power. If a takeoff power rating is desired in the higher gear
ratio, 15 hours of the 30-hour run must be made in the higher gear ratio
in alternate periods of 5 minutes at the observed horsepower obtainable
with the takeoff critical altitude manifold pressure and takeoff speed,
and 5 minutes at 70 percent high ratio rated maximum continuous power
and 89 percent high ratio maximum continuous speed.
(2) A 15-hour run consisting of alternate periods in the lower gear
ratio of 1 hour at rated maximum continuous power with maximum
continuous speed, and \1/2\ hour at 75 percent rated maximum continuous
power and 91 percent maximum continuous speed.
(3) A 15-hour run consisting of alternate periods in the lower gear
ratio of 1 hour at rated maximum continuous power with maximum
continuous speed, and \1/2\ hour at 70 percent rated maximum continuous
power and 89 percent maximum continuous speed.
(4) A 30-hour run in the higher gear ratio at rated maximum
continuous power with maximum continuous speed.
(5) A 5-hour run consisting of alternate periods of 5 minutes in
each of the supercharger gear ratios. The first 5 minutes of the test
must be made at maximum continuous speed in the higher gear ratio and
the observed horsepower obtainable with 90 percent of maximum continuous
manifold pressure in the higher gear ratio under sea level conditions.
The condition for operation for the alternate 5 minutes in the lower
gear ratio must be that obtained by shifting to the lower gear ratio at
constant speed.
(6) A 10-hour run consisting of alternate periods in the lower gear
ratio of 1 hour at rated maximum continuous power with maximum
continuous speed, and 1 hour at 65 percent rated maximum continuous
power and 87 percent maximum continuous speed.
(7) A 10-hour run consisting of alternate periods in the lower gear
ratio of 1 hour at rated maximum continuous
[[Page 776]]
power with maximum continuous speed, and 1 hour at 60 percent rated
maximum continuous power and 84.5 percent maximum continuous speed.
(8) A 10-hour run consisting of alternate periods in the lower gear
ratio of 1 hour at rated maximum continuous power with maximum
continuous speed, and 1 hour at 50 percent rated maximum continuous
power and 79.5 percent maximum continuous speed.
(9) A 20-hour run consisting of alternate periods in the lower gear
ratio of 2 hours at rated maximum continuous power with maximum
continuous speed, and 2 hours at maximum best economy cruising power and
speed or at maximum recommended cruising power.
(10) A 5-hour run in the lower gear ratio at maximum best economy
cruising power and speed or at maximum recommended cruising power and
speed.
Where simulated altitude test equipment is not available when operating
in the higher gear ratio, the runs may be made at the observed
horsepower obtained with the critical altitude manifold pressure or
specified percentages thereof, and the fuel-air mixtures may be adjusted
to be rich enough to suppress detonation.
(d) Helicopter engines. To be eligible for use on a helicopter each
engine must either comply with paragraphs (a) through (j) of Sec.
29.923 of this chapter, or must undergo the following series of runs:
(1) A 35-hour run consisting of alternate periods of 30 minutes each
at rated takeoff power with takeoff speed, and at rated maximum
continuous power with maximum continuous speed.
(2) A 25-hour run consisting of alternate periods of 2\1/2\ hours
each at rated maximum continuous power with maximum continuous speed,
and at 70 percent rated maximum continuous power with maximum continuous
speed.
(3) A 25-hour run consisting of alternate periods of 2\1/2\ hours
each at rated maximum continuous power with maximum continuous speed,
and at 70 percent rated maximum continuous power with 80 to 90 percent
maximum continuous speed.
(4) A 25-hour run consisting of alternate periods of 2\1/2\ hours
each at 30 percent rated maximum continuous power with takeoff speed,
and at 30 percent rated maximum continuous power with 80 to 90 percent
maximum continuous speed.
(5) A 25-hour run consisting of alternate periods of 2\1/2\ hours
each at 80 percent rated maximum continuous power with takeoff speed,
and at either rated maximum continuous power with 110 percent maximum
continuous speed or at rated takeoff power with 103 percent takeoff
speed, whichever results in the greater speed.
(6) A 15-hour run at 105 percent rated maximum continuous power with
105 percent maximum continuous speed or at full throttle and
corresponding speed at standard sea level carburetor entrance pressure,
if 105 percent of the rated maximum continuous power is not exceeded.
(e) Turbosupercharged engines. For engines incorporating a
turbosupercharger the following apply except that altitude testing may
be simulated provided the applicant shows that the engine and
supercharger are being subjected to mechanical loads and operating
temperatures no less severe than if run at actual altitude conditions:
(1) For engines used in airplanes the applicant must conduct the
runs specified in paragraph (b) of this section, except--
(i) The entire run specified in paragraph (b)(1) of this section
must be made at sea level altitude pressure;
(ii) The portions of the runs specified in paragraphs (b)(2) through
(7) of this section at rated maximum continuous power must be made at
critical altitude pressure, and the portions of the runs at other power
must be made at 8,000 feet altitude pressure; and
(iii) The turbosupercharger used during the 150-hour endurance test
must be run on the bench for an additional 50 hours at the limiting
turbine wheel inlet gas temperature and rotational speed for rated
maximum continuous power operation unless the limiting temperature and
speed are maintained during 50 hours of the rated maximum continuous
power operation.
[[Page 777]]
(2) For engines used in helicopters the applicant must conduct the
runs specified in paragraph (d) of this section, except--
(i) The entire run specified in paragraph (d)(1) of this section
must be made at critical altitude pressure;
(ii) The portions of the runs specified in paragraphs (d)(2) and (3)
of this section at rated maximum continuous power must be made at
critical altitude pressure and the portions of the runs at other power
must be made at 8,000 feet altitude pressure;
(iii) The entire run specified in paragraph (d)(4) of this section
must be made at 8,000 feet altitude pressure;
(iv) The portion of the runs specified in paragraph (d)(5) of this
section at 80 percent of rated maximum continuous power must be made at
8,000 feet altitude pressure and the portions of the runs at other power
must be made at critical altitude pressure;
(v) The entire run specified in paragraph (d)(6) of this section
must be made at critical altitude pressure; and
(vi) The turbosupercharger used during the endurance test must be
run on the bench for 50 hours at the limiting turbine wheel inlet gas
temperature and rotational speed for rated maximum continuous power
operation unless the limiting temperature and speed are maintained
during 50 hours of the rated maximum continuous power operation.
[Amdt. 33-3, 32 FR 3736, Mar. 4, 1967, as amended by Amdt. 33-6, 39 FR
35465, Oct. 1, 1974; Amdt. 33-10, 49 FR 6851, Feb. 23, 1984]