724-657-9940
Select Page

DO-160-Section-7-Operational-Shocks

RTCA DO-160 Section 7.0 Operational Shock and Crash Safety Testing

The purpose of RTCA DO-160 operational shock and crash safety test is to determine the ability of equipment to continue to operate during normal aircraft operations. Various shocks can occur during operations. Events such as taxiing, landing or when the aircraft encounters sudden gusts in flight can cause shocks on the aircraft and its components. Because of the frequency of these occurrences, it is important to tests equipment to ensure it will operate within performance standards after exposure to these shocks.

RTCA DO-160 shock testing applies to all equipment installed on fixed-wing aircraft and helicopters. The DO-160 test standard specifies two operational shock test curves. The first curve is a standard 11 ms pulse. The second curve is a low frequency 20 ms pulse. The 20 ms pulse may not be adequate to test against the effect of longer duration shocks on equipment that have its lowest resonance frequency below 100Hz. For such equipment, a pulse of 100 ms duration should be considered.

Why Are RTCA DO-160G Operational Shock Tests Important?

A shock curve can have an adverse impact on equipment. For example, certain equipment could detach from its mountings or separate in a manner that presents a hazard during an emergency landing. This applies to equipment installed in compartments and other areas of the aircraft. If this were to occur, the detached equipment could present a hazard to occupants, fuel systems or emergency evacuation equipment.

RTCA DO-160 Crash Safety Testing Equipment Categories:

RTCA DO-160 section 7.0 classifies equipment in one of four categories.

RTCA DO-160G Section 7.0 Operational Shock Testing Category A: This category is used to test equipment to what would be considered standard operational shocks. Equipment meeting this description must go through RTCA-DO-160 operational shock testing.

RTCA DO-160G Section 7.0 Operational Shock Testing Category B: This category tests equipment for both standard operational shocks and crash safety. Equipment meeting this description must go through RTCA-DO-160 shock testing.

RTCA DO-160G Section 7.0 Operational Shock Testing Category C: This category tests equipment for low-frequency operational shocks. Equipment meeting this description must go through RTCA-DO-160 crash safety testing.

RTCA DO-160G Section 7.0 Operational Shock Testing Category C: This category tests equipment for both low-frequency operational shocks as well as low-frequency crash safety. Equipment meeting this description must go through RTCA-DO-160 operational shocks and crash safety testing.

It is important to note that the RTCA/DO-160 Section 7.0 tests does not satisfy FAR requirements for all equipment. For instance, items such as seats and seat restraints. For fixed-wing aircraft: a complete installation demonstration must be accomplished. This includes aircraft acceleration loads such as flight maneuvering, gust and landing. Crash safety loads, may be accomplished by using the “Unknown or Random” orientations for the “sustained” test procedure. Using a dummy load on the shock test apparatus may be necessary. This ensures that the recorded shock pulse will be within the specified tolerances.

Keystone Compliance is a leader in shock compliance testing to military standards. As an RTCA DO-160G accredited test lab, we have the experience, equipment and resources to meet every testing need. In addition to being accredited to complete RTCA-DO-160G testing, Keystone is also accredited to all previous versions of the standard as well. Please contact us to see firsthand why so many manufacturers rely on Keystone Compliance to be their RTCA DO-160 test lab.

Looking for other testing to other sections of RTCA DO-160 testing? Click on the links below:

Modifications from one Version of RTCA DO-160 to the Next:

Changes from DO-160C Shock Testing to DO-160D Shock Testing

Equipment category definitions were added for fixed wing and helicopter installations.  Crash Safety levels were identified for helicopters (20g) and increased for fixed wing crash safety levels (20g).  Shock pulse was changed from half sine to saw tooth. Half-sine shock pulse curve changed to reflect saw-tooth profile.  Test levels were changed from DO-160C based on empirical data.

Changes from DO-160D Shock Testing to DO-160E Shock Testing

Fixed wing and helicopter operational and crash safety test requirements were made the same.

Changes from DO-160E Shock Testing to DO-160F Shock Testing

Category definitions were revised for clarification.  Text description and centrifuge definitions were revised in section 7.3.3 and figure 7.3, respectively, to reflect the correct setup direction for acceleration load.

Changes from DO-160F Shock Testing to DO-160G Shock Testing

Added in Section 7.2.1 “Unless otherwise stated in the EUT specification, the equipment shall be operating, and its temperature stabilized.  Apply to the test item three shocks having a terminal saw-tooth wave shape with an acceleration peak value of six (6) g’s in each orientation.”