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1、INTERNATIONAL STANDARD IS0 10841 First edition 1996-06-I 5 Aircraft - Catering vehicle for large capacity aircraft - Functional requirements ABronefs - Camions commissariat pour akonefs gros porteurs - Exigences fonctionnelles - - = ggggg z b c) provide drainage to cater for elimination of any spill
2、ed fluids. 3.3.7 Both sidewalls shall be equipped with. a) protective devices to avoid deterioration by impact from fully loaded catering carts as defined in 3.3.5, and b) quick fastening restraint devices capable of en- suring proper restraint of a full complement of such catering carts under norma
3、l over-the-road horizontal and vertical accelerations. 3.3.8 The van body shall be equipped with two doors at the forward and rear ends, with a minimum usable width of 0,8 m (31 in) and a minimum clear height of I,9 m (75 in). 3.3.9 A lighting system shall be fitted within the van body, to provide a
4、 minimum illumination of 50 lx (4,65 ftcd) at any point on the floor. 2 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 20:31:09 MDTNo reproduction or networking permitted withou
5、t license from IHS -,-,- 0 IS0 3.4 Front platform 3.4.1 The vehicle shall be equipped with a front platform to be level with the van body floor within the specified working height range, consisting of. a) b) a fixed platform over the full width of the van, the length of which should be a minimum of
6、I,6 m (63 in), and a sliding bridge to allow alignment with the aircraft door The width of the sliding bridge should be at least 0,8 m (31 in) and shall not exceed 1 m (39 in). 3.4.2 The fixed front platform shall repeatedly withstand a distributed load of 600 kg (1 320 lb), or a 300 kg (660 lb) con
7、centrated load at either for- ward quarter area, without deflecting more than 6 mm (0,25 in). No permanent deflection is allowable. 3.4.3 A suitable safety shield shall be fitted vertically in front of the van body, the function of this shield being to close the gap between the body floor in the low
8、ered position and the upper floor line of the front platform. The safety shield shall be flush mounted, with a maximum 6 mm (0,25 in) clearance from the forward edge of the van body s floor. 3.4.4 The platform floor shall provide an anti-slip surface throughout its whole area. 3.4.5 A spotlight or e
9、quivalent shall be fitted on the front end of the van body to light the platform, and provide a minimum illumination of 50 lx (4,65 ftcd) at any point on its floor and the floor of the sliding bridge. 3.4.6 The sliding bridge shall: be adjustable over the whole width of the fixed front platform, and
10、 lockable at intermediate pos- itions, and have telescopic extension and retraction capability over a minimum length of 0,5 m (20 in). 3.4.7 The sliding bridge shall repeatedly withstand a distributed load of 350 kg (770 lb), or a 100 kg (220 lb) concentrated load at its forward end when fully exten
11、ded, without deflecting more than 6 mm (0,25 in). No permanent deflection is allowable. IS0 10841:1996(E) 3.4.8 The area directly below the sliding bridge shall be free from any components or protrusions within at least 0,3 m (12 in) from its forward end The bridge s thickness in this area shall be
12、kept to a mini- mum. 3.4.9 The forward edge of the sliding bridge shall be protected at aircraft interface by a full-width cylindrical rubber bumper. 4 Stability 4.1 A minimum of four stabilizers shall be provided for van body elevation. The stabilizers in the retracted position shall not protrude f
13、rom the vehicle s overall width as specified in 3.2.2. In addition, the stabilizers in the extended position should preferably not protrude from the overall width. 4.2 When supported by the fully extended stabil- izers, the vehicle in both the maximum gross weight and empty conditions shall meet the
14、 static and wind stability criteria of IS0 11995. 4.3 It shall not be possible: a) b) cl d) 5 to raise the van body beyond 2,54 m (100 in) height when the stabilizers are not fully extended and supporting the vehicle s weight against a supporting surface. to retract the stabilizers under normal cond
15、itions until the van body has been lowered to 2,54 m (100 in) (See 7.2 for emergency conditions ) to drive the vehicle when the stabilizers are not fully retracted or the van body is not in the fully down position. Manual override of the latter interlock shall be possible for emergency con- ditions.
16、 (See 7.3.) for the stabilizers to collapse in case of a system failure. Controls 5.1 Controls for raising and lowering the van body and the front platform shall be located in the van body and the vehicle cabin. 5.2 The control panel in the van body shall be lo- cated at the forward end. 3 Copyright
17、 International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 20:31:09 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 10841:1996(E) 0 IS0 5.3 Controls for extending and r
18、etracting the stabil- izers shall be located in the vehicle cabin only, and shall be protected against inadvertent activation. Positive confirmation by a warning light or equivalent device ,indicating that the stabilizers are either fully retracted or fully extended and supporting the ve- hicle s we
19、ight against a supporting surface shall be provided next to the controls. 5.4 Emergency stop buttons which kill the engine shall be provided at both control panels. 5.5 It shall be possible to start and stop the engine from both the vehicle cabin and the van body control panels. 5.6 The engine shall
20、 be equipped with a demand throttle providing high idle whenever one of the hy- draulic functions is actuated. 5.7 All controls shall be identified by the appropriate pictographic symbols as described in IS0 7000. 5.8 The control panels layout should insofar as practical meet the requirements of IAT
21、A AHM 915, section 2 c) an adequate opening to gain access to and from the platform, to and from the access ladder. 6.5 The handrails geometry shall be designed to allow opening and closure of the aircraft doors while the sliding bridge is fully retracted, regardless of the relative positions of the
22、 vehicle and the aircraft 6.6 All moveable, adjustable or extendable parts of the handrails shall have a means for positive locking in as many intermediate positions as may be necess- ary. 6.7 The vehicle chassis at ground level shall be en- tirely surrounded by a rigid protective structure in or- d
23、er to prevent any possibility of inadvertent access of personnel or equipment (e g. dollies) under the van body while elevated. 7 Emergency 7.1 The vehicle shall be fitted with an emergency auxiliary system allowing: a) the platform and the van body to be lowered, b) the stabilizers to be retracted,
24、 6 Persbnnel protection c) the vehicle to be towed away, 6.1 The equipment shall meet the appropriate re- quirements of IS0 6966. 6.2 A ladder shall be provided to give access from the ground to the front platform when in the lowered position. The ladder shall not extend beyond the overall width of
25、the vehicle as specified in 3.2.2. It shall be fitted with anti-slip rungs and adequate handholds. 6.3 Steps shall be provided at the rear of the body to allow easy access to and from the body in the lowered position. The steps shall have an anti-slip surface and be fitted with adequate handholds. 6
26、.4 Rigid handrails including knee rails and footrails shall be provided on both sides of the front platform. They shall include: a) adjustable elements between the platform and the sliding bridge. b) extendable elements along both sides of the slid- ing bridge. in the event of primary power loss, in
27、 order to allow safe evacuation of personnel and removal of the ve- hicle from the aircraft. 7.2 Emergency lowering shall not compromise ve- hicle stability, i.e. it shall not be possible to retract the stabilizers using the emergency system while the platform or van body are above 2,54 m (I 00 in)
28、height. 7.3 Whenever the chassis propulsion is still avail- able while the van body cannot be completely low- ered, it shall be possible to manually override the interlock preventing the vehicle being driven while the van body is not fully down as specified in 4.3 (c) The override control shall be l
29、ocated together with other emergency controls and sealed or otherwise pro- tected against inadvertent or unauthorized use 7.4 The emergency auxiliary system may be either manual (hand pump) or, as an option, have an inde- pendent power source. Its controls shall be located at ground level and protec
30、ted by a cover or equivalent device. 4 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 20:31:09 MDTNo reproduction or networking permitted without license from IHS -,-,- 0 IS0 IS
31、0 10841:1996(EI 8 Options The following optional additional features may be considered. a) Capability of servicing aircraft with cabin door sill heights as low as 1,9 m (75 in). b) Sliding or folding canopy over the front platform. The canopy shall not interfere with opening and closure of aircraft
32、doors. c) Thermally insulated van body General guidance on thermal insulation efficiency and performance can be found in IS0 1496-2 and IS0 8058. performance assessment can be found in IS0 1496-2 (see 8.3). el Folding tailgate lift to allow loading and unloading of the vehicle from the ground at its
33、 rear end f) Emergency operation system (see clause 7) with an independent power source g) Detection device on top of the platform below the aircraft door, that initiates a flashing light or aud- ible warning in case the clearance between the platform and the door becomes too small. h) Automatic lev
34、eiling system for platform height adjustment during aircraft height changes d) Refrigerated van body. General guidance on self- contained refrigeration units classification and 5 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical S
35、tandards 1/9972545001 Not for Resale, 04/23/2007 20:31:09 MDTNo reproduction or networking permitted without license from IHS -,-,- IS0 10841:1996(E) Annex A (informative) Bibliography I IATA AHM 915, Standard controls, Section 1 - Pictograms for Identification of Ground Support Equipment Controls,
36、and Section 2 - Standard Layout.2l 2 IATA AHM 927, Functional Specification, Catering Vehicles 2, 2) Specifications AHM 915 and AHM 927 are part of International Air Transport Association (IATA) Airport Handling Manual, which can be obtained from - IATA Publications Dept , 2000 Peel Street, Montreal
37、 Quebec H3A 2R4, Canada, or - IATA Publications Dept , route de I ABroport 33, P.0 Box 672, CH-1215 Gen&ve 15 Abroport, Switzerland 6 Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2
38、007 20:31:09 MDTNo reproduction or networking permitted without license from IHS -,-,- Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 20:31:09 MDTNo reproduction or networking p
39、ermitted without license from IHS -,-,- IS0 10841:1996(E) ICS 49.100 Descriptors: airport equipment, aircraft ground servicing, catering services, delivery van, specifications, operating requirements, safety requirements, dimensions, overall dimensions. Price based on 6 oases Copyright International Organization for Standardization Provided by IHS under license with ISO Licensee=NASA Technical Standards 1/9972545001 Not for Resale, 04/23/2007 20:31:09 MDTNo reproduction or networking permitted without license from IHS -,-,-