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|  MIL-T-18847C(AS)
3.5.5 Fins. Provisions. shall be made for the attachment of stabilizing
fins to the tail cone of the tank. These provisions shall be included to
permit future use of the tank on other aircrafts. The provisions shall permit
the fins to be mounted in either the horizontal or vertical positions, of
45 from the vertical position. The fin configuration shall be subject to
approval by the Naval Air Systems Command (see 6.2).
3.5.6 Thread connections. Screw threads shall be in accordance with
MIL-S-7742 or MIL-S-8879. The conditions governing the selection of the
applicable threads are described in SD-24. All threaded parts shall be
securely locked by safety wiring, metal type self-locking nuts, cotter pins,
or other means approved by the Naval Air Systems Command.
3.5.6.1 Pipe threads. Pipe threads shall only be used for permanently
installed pipe-threaded plugs.
3.5.6.2 Threaded safety. All threaded parts shall be positively locked or
safetied in accordance with MS33540 or other accepted practice. Wherever
loosening of a self-locking nut could possibly result in the nut or other
parts entering the fuel system plumbing, approval of the installation shall be
obtained from the procuring activity. The use of cotter pins on studs, or the
use of lockwashers or staking is prohibited.
Fasteners shall be selected and used in accordance with
3.5.7 Fasteners.
MIL-STD-1515.
3.5.8 Maintainability. The tank shall be designed for ease of repair,
Including complete overhaul. It shall be repairable by replacing defective
components with serviceable ones. No test or additional adjustments shall
be required other than a functional test. Special skills, techniques, non-
standard tools, or excessive task time shall not be required. Ease of
maintenance, accessibility, etc., will be major determinants in the design
selection for procurement. The contractor shall provide a repair procedure.
3.5.9 Structural flight performance. The tanks, at the weight specified
in 3.5.1.5.2. shall be designed to withstand the limit load factors of
MIL-A-8591 while pressurized to 25 psig without any deformation that might
adversely affect the aerodynamic characteristics as specified in 3.5.10 and
3.5.11.
3.5.10 Aerodynamic flight performance. The addition of external tanks to
an aircraft, at the weights specified in 3.5.1.5.2, shall not adversely affect
the characteristics of the aircraft on which they are installed to such an
extent as to result in an Inability to comply with the aerodynamic flight
performance requirements of MIL-D-8708 and MIL-F-8785.
3.5.11 Maximum permissible speeds. The change in maximum permissible
speed of an aircraft as defined in MIL-F-8785 shall be kept to a minimum due
to the addition of external fuel tanks.
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