MIL-DTL-9479E (USAF)
c. Ejection control forces.
4.4.2.1 Inspection lot. An inspection lot shall be expressed in units of complete ejection seat
systems manufactured under essentially the same conditions and submitted for acceptance at
substantially the same time.
4.4.2.2 Sampling plan. Sample seats shall be selected at random from each lot on the same
material order, in the quantities specified below:
a. Two seats from each lot of 400 or fraction thereof.
b. Three seats from each lot of 401 to 800.
c. One seat from each additional 800 or fraction thereof, above 800.
4.4.2.3 Rejection and retest. Failure of any seat to pass the acceptance tests shall be cause for
rejection of the entire lot represented. If in the opinion of the inspector, such failure is attributable
to faulty workmanship or other defects not likely to occur throughout the lot, the contractor must
test three additional seats selected at random from the lot. Failure of any one of these additional
seats shall be cause for the rejection of the entire lot represented.
4.5 Inspection methods.
4.5.1 Design verification. On-going verification of the seat system escape design shall be
accomplished through use of a 6-degree-of-freedom (6DOF) computer program. The computer
simulation program shall be presented at all program reviews, internal and external, at the request
of the government. The program shall be employed as a design growth display reflecting the
maturing design approach, materials, and test plan basis. A maximum amount of actual test data
available from system tests shall be used to refine the computer program.
4.5.2 Examination of product. Each seat system shall be carefully examined to determine
conformance to this specification and applicable drawings with respect to materials, workmanship,
standard parts, weight, finish, adjustments, dimensions, and markings. Special attention shall be
given to the ejection control mechanism.
4.5.3 Ballistic gas transmission. The ballistic gas transmission hose and fittings shall be subjected
to a flow test, based upon the design schematic of the ballistic subsystem. The plumbing
connections to the propellant-actuated devices shall be disconnected for the performance of this
test. The testing material used shall be dry air or dry nitrogen at a pressure not greater than 450
psig. There shall be no flow condition or restriction of flow which is not in accordance with the
design schematic (see 3.2.14).
4.5.4 Structural strength. The ejection seat shall be mounted on the ejection rails and retained in
a test jig which simulates the attachments and interfaces of the ejection seat and rails within the
aircraft structure. Under these conditions, the seat system shall be subjected to and shall
withstand the required ultimate loads for preproduction inspection and the required proof loads
for sampling inspection as specified (see 3.4.5.3 and 3.4.5.4). These loads shall be applied to the
seat without cushions. The loads may be applied by means of hydraulic or pneumatic presses,
jacks, shot bags, or other suitable methods. The restraint subsystem shall be tested by applying
the loads to a block or frame fitted within the seat and held in place by the restraint subsystem.
The block or frame shall be formed to simulate operational use of the restraint subsystem.
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