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FEDERAL REGISTER, Friday, June 13, 1941
13.2024 Lubrication system. The manifold pressure, spark and mixture lubrication system of the engine shall settings, fuel and oil grades, and cylinder be so designed and constructed that the head, barrel, intake air, and oil inlet system will function properly in all flight temperatures.
attitudes and atmospheric conditions in 13.213 Calibration tests. The en which the engine is intended to be used. gine shall be subjected to such calibra In wet sump engines, such requirement tion tests as are necessary to establish shall be met when only one-half the its power characteristics and the condi maximum oil supply is in the engine. tions under which it is to be endurance The system shall be so designed and con tested. Such tests shall cover, but need structed that provision can readily be not be limited to, the proposed cruising, made for properly cooling the oil.
maximum-except-take-off, and take-off 13.2025 Engine cooling. The engine operating conditions.
shall be designed and constructed to pro 13.214 Operation tests. The engine vide satisfactory cooling when the engine shall be operated at various power out is properly installed, operated and main puts and speeds throughout the proposed tained in an aircraft.
operating range to demonstrate that the 13.2026 Engine and a c c e s s o r y engine has satisfactory running and vi mounting attachments, a The mount bration characteristics, and freedom from ing attachments and structure of the en detonation.
gine shall have sufficient strength when 13.215 Endurance tests. The endur the engine is properly supported by a ance tests shall consist of the following suitable engine mount structure, to meet 150 hours of testing on the same engine, the structural loading conditions of Part in the order stated: 1 50 hours at maxi04, and to withstand vibration forces mum-except-take-off power, 2 50 hours likely to occur.
at the most critical cruising conditions, b Accessory mounting provisions and 3 40 hours at 91 per cent take-off power drives shall be designed and constructed or at least maximum-except-take-off to provide for the safe operation of the power, and 4 10 hours at take-off power.
engine with the accessories attached. All Such endurance tests shall be conducted essential engine accessories which may in periods of not less than 30 minutes require inspection, adjustment, or re duration.
moval between engine overhauls shall be 13.2150 Engine adjustments and parts mounted in such manner that they may replacements, a External adjustments be readily inspected, adjusted or removed and replacements of minor parts such as without disassembly of the engine.
spark plugs, which are normally made 13.21 Block testing. The engine, in in servicing aircraft engines, may be per cluding at least essential accessories, shall formed at reasonably spaced servicing satisfactorily complete block testing as periods designated in advance by the ap hereinafter provided under power out plicant.
puts and conditions simulating the most b Minor internal adjustments and severe flight operations possible when the replacements qf minor parts, which are engine is properly installed, operated and normally made during a top overhaul, maintained in an aircraft. Separate en may be performed during the optional gines of identical design and construction 100-hour tear-down inspection.
may be used for the endurance, calibra c The tests shall not be considered tion, and operation tests.
satisfactory if excessive adjustments or 13.210 Testing equipment and per excessive replacements of minor parts sonnel. The applicant shall furnish suit are made, unless it is demonstrated that able testing equipment and facilities, and the causes therefor have been remedied.
competent personnel to conduct the re d Parts used to replace other parts, quired block tests.
except as permitted by paragraphs a 13.211 Witnessing of tests. An au and b hereof, shall satisfactorily meet thorized representative of the Adminis the 150-hour endurance tests: Provided, trator shall witness all block testing That the Administrator may accept other sufficiently to ascertain that the infor substantially equivalent proof of such mation presented in the applicants test parts.
report is substantially correct and com 13.2151 Forced stops. A forced plete. Such representative shall witness, stop is any malfunctioning of the engine in their entirety, the operation test, the or its essential accessories which would calibration test, the tear-down inspec cause or make advisable an engine stop, tions, and at least the last 50 hours of including, but not limited to, structural the endurance tests.
failure, excessive increase in vibration, 13.212 Engine operating conditions excessive leaking of fuel, oil, or coolant, and limitations. The engine operating or an appreciable decrease in perform conditions maintained within suitable ance not attributable to general wear tolerances or satisfactorily demonstrated or change in atmospheric conditions.
during the testing shall determine the When a forced stop occurs, appropriate operating limitations to be assigned the corrective measures shall be taken to engine by the Administrator. Such op insure insofar as possible that similar erating limitations shall include those malfunctioning will not reduce the re necessary or advisable for safe operation liability of the engine in service.
of the engine, and may be placed on the 13.216 Optional tear-doim inspec following and any necessary additional tion. The applicant may, but shall not items: Power output, crankshaft speed, be required to, conduct a tear-down in
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spection after the completion of the first 100 hours of endurance testing.
13.217 Final tear-dovm inspection.
a At the completion of the endur ance tests, the engine shall be completely disassembled and a detailed inspection made of the engine parts. Highly stressed parts shall be examined by suit able methods to determine the presence of hidden fatigue cracks. Wear meas urements shall be taken and a compari son made of the final condition of parts and their condition prior to the begin ning of the endurance tests or their di mensions as shown on the drawings.
A conformity check consisting of a com parison of the parts of the engine tested with the drawings may be required at this time.
b If any part shows evidence of fatigue or impending failure or is other wise not in a condition for safe opera tion, the engine will not be considered satisfactory unless appropriate correc tive measures are taken and proven sat isfactory by suitable testings: Provided, That the Administrator may accept other substantially equivalent proof.
13.218 Test report. The applicant shall prepare and submit a suitable re port completely covering the required testing of the engine and the tear-down inspections. Such report shall be signed by an authorized representative of the applicant and the authorized represen tative of the Administrator who wit nessed the testing and tear-down inspections.
13.22 Identification plate. A suita ble identification plate shall be perma nently attached to the engine in a loca tion which will be readily accessible when the engine is installed in an aircraft.
Such plate shall contain such pertinent information as may be prescribed by the Administrator.
13.23 Demonstration of compliance.
Compliance with the airworthiness re quirements of this Part shall be substan tiated insofar as practicable by pertinent technical data and inspections. Analy ses or additional tests satisfactory to the Administrator shall be made when war ranted by unconventional design fea tures or the results of block testing.
13.3 Type certificate. In order to obtain an aircraft engine type certificate an applicant shall comply with the fore going and following requirements:2
13.30 Data required. In addition to the data required to show compliance with the airworthiness requirements, the applicant for a type certificate shall sub mit descriptive data adequate for the reproduction of other engines of the same type.
13.31 Changes. When any change in design, construction or operating lim itations is made in an engine being man ufactured under a type certificate, suit able data describing the change shall be submitted for the approval of the Administrator.
For regu lations governing issuance of type certificates see Part 02.