W0 = WA + Σ1 n(WJ) W0, WA, WJ - Exposure levels in acceleration spectral density (g²/Hz).
Aerodynamically induced vibration WA = a × b × c × (q)²
Jet engine noise induced vibration WJ = {[0.48 × a × d × cos²(θ)/R] × [Dc × (Vc / Vr )³ + Df × (Vf / Vr )³]}
a - Platform / Materiel interaction factor (see Annex A, paragraph 2.4). Note that this factor applies to Wo and not to the low frequency portion (15 Hz to break) of Figure 514.8D-1.     = 1. 0 for materiel mounted on vibration isolators (shock mounts) and materiel weighing less than 36.3 kg.     = 1. 0 ×10(0 6 - W / 60) for materiel weighing between 36.3 and 72.6 kg.(w = weight in kg) = 0. 25 for materiel weighing 72.6 kg or more.	Σ1 n - Jet noise contribution is the sum of the WJ values for each engine.
	d - Afterburner factor.     = 1. 0 for conditions where afterburner is not used or is not present.     = 4. 0 for conditions where afterburner is used.
b = Proportionality factor between vibration level and dynamic pressure (SI units).     = 2.96 ×10-6 for materiel mounted on cockpit instrument panels.     = 1.17 ×10-5 for cockpit materiel and materiel in compartments adjacent to external surfaces that are smooth and free from discontinuities.     = 6.11 ×10-5 for materiel in compartments adjacent to or immediately aft of external surface discontinuities (cavities, chines, blade antennae, speed brakes, etc.), fuselage aft of wing trailing edge, wing, empennage, and pylons.
	R - Vector distance from center of engine exhaust plane to materiel center of gravity, m (ft).
	θ - Angle between R vector and engine exhaust vector (aft along engine exhaust centerline), degrees For 70 °< θ ≤ 180 ° use 70 °.
c - Mach number correction. Note that this factor applies to W0 and not to the low frequency portion (15 Hz to varc or varo) of Figure 514.8D-1.     = 1. 0 for 0 ≤ Mach ≤ 0. 9 = (-4.8M + 5.32) for 0.9 ≤ Mach ≤1. 0 (where M = Mach number) = 0.52 for Mach number greater than 1.0	Dc - Engine core exhaust diameter, m (ft).
	Df - Engine fan exhaust diameter, m (ft).
	Vr - Reference exhaust velocity, m/sec (ft/sec).     = 564 m /sec (1850 ft/sec)
q - Flight dynamic pressure, kN / m² (lb/ft²).	Vc - Engine core exhaust velocity (without afterburner, m/sec (ft/sec))
	Vf - Engine fan exhaust velocity (without afterburner, m/sec (ft/sec))
	varc - intersection frequency for cockpit materiel based on 4dB/oct slope from W0
	varo - intersection frequency for all other materiel based on 4dB/oct slope from W0
If Dimensions are in feet and pounds then:
a = 1. 0 for materiel mounted on vibration isolators (shock mounts) and materiel weighing less than 80 lb.     = 1. 0 ×10(0 60 - 0 0075 W) for materiel weighing between 80 and 160 lb.     = 0. 25 for materiel weighing 160 lb. or more.
b = 6.78 ×10-9, 2. 70 ×10-8, or 1.40 ×10-7 in the order listed above.
Vr = 1850 feet / second