1 Inertial navigation systems and specially designed components thereof, as follows— a inertial navigation systems which are certified for use on civil aircraft by civil authorities of a State participating in the Wassenaar Arrangement, and specially designed components thereof, as follows— i inertial navigation systems (INS) (gimballed or strapdown) and inertial equipment designed for aircraft, land vehicle, vessels (surface or underwater) or spacecraft for attitude, guidance or control, having any of the following characteristics, and specially designed components thereof— aa navigation error (free inertial) subsequent to normal alignment of 0.8 nautical mile per hour (nm/hr) Circular Error Probable (CEP) or less (better); or bb specified to function at linear acceleration levels exceeding 10 g; ii hybrid Inertial Navigation Systems embedded with Global Navigation Satellite Systems(s) (GNSS) or with Data-Based Referenced Navigation (DBRN) System(s) for attitude, guidance or control, subsequent to normal alignment, having an INS navigation position accuracy, after loss of GNSS or DBRN for a period of up to four minutes, of less (better) than 10 metres Circular Error Probable (CEP); iii inertial Equipment for Azimuth, Heading, or North Pointing having any of the following characteristics, and specially designed components thereof: aa designed to have an Azimuth, Heading, or North Pointing accuracy equal to, or less (better) than 6 arc minutes RMS at 45 degrees latitude; or bb designed to have a non-operating shock level of at least 900 g at a duration of at least 1 msec. b theodolite systems incorporating inertial equipment specially designed for civil surveying purposes and designed to have an Azimuth, Heading, or North Pointing accuracy equal to, or less (better) than 6 arc minutes RMS at 45 degrees latitude, and specially designed components thereof; c inertial or other equipment using accelerometers specified in Dual-Use code 7A001 or 7A101, where such accelerometers are specially designed and developed as MWD (Measurement While Drilling) sensors for use in down-hole well services operations. 2 The parameters set out in sub-paragraph (1)(a)(i) and (ii) are applicable with any of the following environmental conditions— a input random vibration with an overall magnitude of 7.7 g rms in the first half hour and a total test duration of one and a half hours per axis in each of the three perpendicular axes, when the random vibration meets the following— i a constant power spectral density (PSD) value of 0,04 g2/Hz over a frequency interval of 15 to 1 000 Hz; and ii the PSD attenuates with a frequency from 0,04 g2/Hz to 0,01 g2/Hz over a frequency interval from 1 000 to 2 000 Hz; b a roll and yaw rate equal to or greater than + 2,62 radian/s (150 deg/s); or c according to national standards equivalent to (i) or (ii) above. 3 Sub-paragraph (1)(a)(ii) refers to systems in which an Inertial Navigation System and other independent navigation aids are built into a single unit (embedded) in order to achieve improved performance. 4 In this paragraph— a the following terms have the meaning given to them in the Dual-Use Regulation— “aircraft”; “circular error probable”; “civil aircraft”; “Data-Based Referenced Navigation” ; “spacecraft”.