spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 33.71

Section 33.70 Engine life-limited parts.
By a procedure approved by the FAA,
operating limitations must be established which specify the maximum allowable number of flight cycles for
each engine life-limited part. Engine
life-limited parts are rotor and major
static structural parts whose primary
failure is likely to result in a hazardous engine effect. Typically, engine
life-limited parts include, but are not
limited to disks, spacers, hubs, shafts,
high-pressure casings, and non-redundant mount components. For the purposes of this section, a hazardous engine effect is any of the conditions listed in Section 33.75 of this part. The applicant
will establish the integrity of each engine life-limited part by:
(a) An engineering plan that contains
the steps required to ensure each engine life-limited part is withdrawn
from service at an approved life before
hazardous engine effects can occur.
These steps include validated analysis,
test, or service experience which ensures that the combination of loads,
material properties, environmental influences and operating conditions, including the effects of other engine
parts influencing these parameters, are
sufficiently well known and predictable
so that the operating limitations can
be established and maintained for each
engine life-limited part. Applicants
must perform appropriate damage tolerance assessments to address the potential for failure from material, manufacturing, and service induced anomalies within the approved life of the
part. Applicants must publish a list of
the life-limited engine parts and the
approved life for each part in the Airworthiness Limitations Section of the
Instructions for Continued Airworthiness as required by Section 33.4 of this part.
(b) A manufacturing plan that identifies the specific manufacturing constraints necessary to consistently
produce each engine life-limited part
with the attributes required by the engineering plan.
(c) A service management plan that
defines in-service processes for maintenance and the limitations to repair for
each engine life-limited part that will
maintain attributes consistent with
those required by the engineering plan.
These processes and limitations will

become part of the Instructions for
Continued Airworthiness.
[Amdt. 33-22, 72 FR 50860, Sept. 4, 2007]

Section 33.71

Lubrication system.

(a) General. Each lubrication system
must function properly in the flight attitudes and atmospheric conditions in
which an aircraft is expected to operate.
(b) Oil strainer or filter. There must be
an oil strainer or filter through which
all of the engine oil flows. In addition:
(1) Each strainer or filter required by
this paragraph that has a bypass must
be constructed and installed so that oil
will flow at the normal rate through
the rest of the system with the strainer
or filter element completely blocked.
(2) The type and degree of filtering
necessary for protection of the engine
oil system against foreign particles in
the oil must be specified. The applicant
must demonstrate that foreign particles passing through the specified filtering means do not impair engine oil
system functioning.
(3) Each strainer or filter required by
this paragraph must have the capacity
(with respect to operating limitations
established for the engine) to ensure
that engine oil system functioning is
not impaired with the oil contaminated
to a degree (with respect to particle
size and density) that is greater than
that established for the engine in paragraph (b)(2) of this section.
(4) For each strainer or filter required by this paragraph, except the
strainer or filter at the oil tank outlet,
there must be means to indicate contamination before it reaches the capacity established in accordance with
paragraph (b)(3) of this section.
(5) Any filter bypass must be designed and constructed so that the release of collected contaminants is
minimized by appropriate location of
the bypass to ensure that the collected
contaminants are not in the bypass
flow path.
(6) Each strainer or filter required by
this paragraph that has no bypass, except the strainer or filter at an oil
tank outlet or for a scavenge pump,
must have provisions for connection
with a warning means to warn the pilot
of the occurance of contamination of

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