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|  MIL-A-l9736A(Wep)
3.15.4 Mechanisms: Actuating mechanisms for retractable probes shall be simple and shall not require
complicated rigging or close adjustment of linkages. The probe shall be positively locked in the
extended position. Telescoping probes shall. not allow fuel between the inner and outer tubes.
3.15.5 Fuel line: The probe nozzle shall conform to Specification MIL-N-25161. A check valve shall
be installed between the probe and the aircraft fuel system. Installation of the fuel line shall be
in accordance with Specification MIL-I-18802. Unless specifically approved the fuel line shall not
pass through gun or rocket compartments. If such an arrangement is approved the line shall be pro-
tected from links, brass and rocket debris encountered during firing.
3.15.6 Light: A probe light in accordance with Specification MIL-L-006730 as a design objective shall
be provided. The probe light shall be controlled ON and OFF by a switch in the cockpit for that
purpose. The light shall be installed or shielded in such a manner as to prevent the light from being
a source of direct or reflected glare to the pilot or crew.
3.16 Marking: All marking shall be durable and not subject to effacing or obliteration in service.
The part number shall be located so as to be easily seen. Stamping shall be avoided. Identification
plates shall conform to Specification MIL-P-6906.
3.16.1 Equipment: An identification plate shall be securely fastened to each piece of air refueling
equipment and shall contain the following information:
Name of equipment
Manufacturers name or trademark, model
number, part number and serial number
Weight
Requirements of Specification MIL-D-8706 for design data are applicable.
3.l7 Engineering data:
3.17.1 Aerodynamic:
Aerodynmic investigations and models needed to meet the aerodynamic requirements
as specified in 3.15.1 shall be provided for and data and reports shall be submitted as part of and
in accordance with Specification MIL-D-8706 concerning aerodynamic investigations, supplemented if
necessary by additional reports.
4. Quality Assurance Provisions.
4.1 Unless otherwise specified herein the supplier is responsible for the performance of all in-
spection requirements prior to submission for Government inspection and acceptance. Except as
otherwise specified, the supplier may utilize his own facilities or any commercial laboratory
acceptable to the Government. Inspection records of the examinations and tests shall be kept complete
and available to the Government as specified in the contract or order.
4.2 Preliminary flight tests: If feasible, tanker and receiver aircraft shall be flight tested prior
to production of air refueling equipment to determine that the system affords a satisfactory formation
for ease of engagement and refueling. Dummy probes may be used to evaluate proposed locations.
Test-rig hose and drogue installations may be used. Fuel transfer is not necessary.
4.3 Tanker aircraft: The test program shall consist of two phases; ground and flight.
4.3.1 Ground tests: Ground tests shall include the following tests of the tanker package integrated
with the basic airplane fuel system.
4.3.1.1 Convertibility: Interchangeability and replaceability of the aircraft configuration from the
basic aircraft to a tanker version shall be made to determine that conversion time and time required
to functionally check the tanker equipment comply with 3.7.1.
4.3.1.2 Fuel calibration:
The total and usable capacities of tanker package fuel tanks shall be
determined.
4.3.1.3 Fueling: Pressure refueling and defueling rates of the tanker configured aircraft shall be
measured to determine compliance with requirements of Specification MIL-F-17874.
3.2
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