What is claimed is:
1. A method for treating lips of a human subject for prevention or repair of xeric stress, said method comprising applying to said lips a barrier function maintaining amount of a composition comprising the following components as the only lipids in the composition:
(a) one or more ceramides,
(b) one or more essential free fatty acids, and
(c) one or more nonessential free fatty acids of 12 to 20 carbon atoms each,
at (a):(b):(c) mole ratios of about (1-5):(1-5):(1-5).
2. A method in accordance with claim 1 in which said one or more essential free fatty acids are members selected from the group consisting of linoleic and linolenic acids.
3. A method in accordance with claim 1 in which said component (b) is linoleic acid.
4. A method in accordance with claim 1 in which said one or more nonessential free fatty acids are those having 16 to 18 carbon atoms each.
5. A method in accordance with claim 1 in which said one or more nonessential free fatty acids are members selected from the group consisting of palmitic and stearic acids.
6. A method in accordance with claim 1 in which component (c) is palmitic acid.
7. A method in accordance with claim 1 in which said one or more ceramides are members selected from the group consisting of bovine ceramides, types III and IV.
8. A method in accordance with claim 1 in which said mole ratios are about (1-3):(1-3):(1-3).
9. A method in accordance with claim 1 in which component (a) is a bovine ceramide, component (b) is linoleic acid, and component (c) is palmitic acid.
10. A method for treating lips of a human subject for prevention or repair of xeric stress, said method comprising applying to said lips a barrier function maintaining amount of a composition comprising one or both of the following components:
(a) a member selected from the group consisting of -glucocerebrosidase and analogs thereof with substantially similar activity in converting glucosylceramides to ceramides, and
(b) a member selected from the group consisting of secretory phospholipase A2 and analogs thereof with substantially similar activity in converting phospholipids to free fatty acids.
11. A method in accordance with claim 10 comprising applying both of components (a) and (b).
12. A method in accordance with claim 11 in which component (a) is -glucocerebrosidase.
13. A method in accordance with claim 11 in which component (b) is phospholipase A2 secreted by mammalian pancreas.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. An aircraft comprising at least one inertial reference unit and a reference unit support fixed to a structural element of the aircraft, wherein the aircraft comprises, for each inertial reference unit:
a memory including recorded support installation angles representative of angular positioning errors relative to an aircraft coordinate system of the reference unit support corresponding to said inertial reference unit, said support installation angles being determined beforehand on a basis of measurement of coordinates of points of a reference coordinate system and of characteristic points of said reference unit support; and
calculating module to calculate corrected data on a basis of data measured by the inertial reference unit and corresponding support installation angles, wherein each reference unit support comprises:
a platen to extend substantially horizontally in the aircraft, said platen defining a vertical direction of the support orthogonal to the platen, an axial direction and a transversal direction of the support extending in a plane of the platen and to extend substantially parallel to the pitch and roll directions of the aircraft respectively;
a rear wall extending from a rear side of the platen;
at least two centering pins, one of the centering pins being a front pin carried by a front edge of the platen opposite the rear wall, and another one of the centering pins being a rear pin carried by the rear wall, said front and rear pins having axes extending in the axial direction of the support, the rear pin comprising a contact surface to be integrally in contact with a case of the inertial reference unit; and
two contact plates formed on the platen close to a front side of the platen opposite the rear wall, said contact plates being spaced apart in the transversal direction of the support, said contact plates being integrally in contact with the case of the inertial reference unit.
2. An aircraft according to claim 1, wherein at least one an extender is fixed on the reference unit support and has larger dimensions than the reference unit support.
3. An aircraft according to claim 2, wherein the extender includes a transversal dimension at least five times larger than a transversal dimension of the reference unit support and an axial dimension at least two times larger than an axial dimension of the reference unit support.