销 售 合 同
No._________
根据现有文件所知：
卖方：同方股份有限公司（成立于1997年6月25日），注册地址为中华人民共和国北京市海淀区清华同方科技广场，邮政编码100085，以下简称“卖方”，代表人为计算机系统本部海外事业部总经理赵建武先生。
买方：__________ 公司，_______________以下简称“买方”，代表人_____________
买卖双方承认彼此的性质及合法地位（具有一切法律效力），经友好协商，本着平等、信任的原则，达成如下协议：
合同目的
卖方依照本合同附件二（视同本合同一部分）中规定质量、标准、模具、技术规格以及其他描述，向买方出售与产品技术说明相符的产品。
合同总金额
本合同总金额为上海离岸价 107,500,000 美圆(数量50000台，每台美元)。
本合同中约定价格包含包装、麦头费用。
本合同中约定金额使用欧美圆计算，交易金额与合同规定金额一致。
3. 运输条款
卖方在收到预付款60天内从中国任何港口以FOB形式发货，每月发货量5000台，10个月内货物交付完毕。
目的港为以色列特拉维夫，接受分装与转运。
在开具提单5日内，卖方需向买方提供以下文件的复印件：
形式发票
提单
卖方开具的装箱单
卖方开具的产品质量证明
卖方开具的原产地证明
另外，在收到提单后72小时以内，卖方向买方_________公司传真并电邮上述条款中提到的文件复印件，以及以下信息，传真号码：__________，E-mail: _______________。
提单号码
货轮号码
品名，数量
包装数量
集装箱数目和号码
以公斤为单位计量的毛重，净重。
货物将使用集装箱装载，这样可保证货物的物理完整性，并保护产品不会在搬运以及运输的过程中遭到损坏。
本合同中所有装载货物的包装盒、包裹、包装箱以及散装箱将由卖方负责标识。所做标识必须使用不可擦拭墨水标在容器相对的两面，至少具有以下英文标识：
合同号码： 目的地：以色列，特拉维夫
收 件 人 ：________ _，特拉维夫，以色列
装箱号码 ： 装箱数量：_________
毛 重 ： 净 重： （公斤）
尺 寸： （厘米）
根据产品特点，装货、卸货、海运以及陆运的不同要求，要在相应的盒子、箱子、包裹以及散装的外包装上注有明显、适当的International Prevention Signals以及象征符号。
合同规定之货物在到达目的港以后，买方应尽快将其提出，必要的话，可对运输数量以及包装情况进行一次初步检查。
4. 检查
． 对货物的清点以及卸载应由买方执行。
装船以前，卖方应先对货品进行检查测试，买方保留检验货物的权力。当买方需要检验货物的时候，卖方应协助买方检验人员在货物储存的工厂内进行检验，卖方有义务在准备发货的10天以内通知买方何时可以对货物进行检验。
卖方需在装箱日期10天前通知买方有关检验日期，以便后者安排检验公司进行检验。
若由于卖方原因而无法让买方的检验公司进行中提到的检验，由此引发的一切后果由卖方负责。
如果买方需对货物进行检验，则必须在估计装运日期20日以前向卖方确认。卖方需在装运日10天以前告之买方何时可以进行验货。
买方指定之检验人员应至少提前装运日7天确认检验事宜。卖方事先需向买方提交一份装箱单复印件，买方需向检验员提供货物清单。
所有货物都将进行检验，检验内容包括包装、数量、模具、品牌，已装集装箱的标志并确认一致及封上集装箱。双方在检验结果和确认一致的报告上签字，防止任何不同之处所造成的运输文件上面的不一致。
. 关于本合同所提供产品的技术指标应在附件二里面特别、详细地进行描述，并作为合同的一部分具有完全的法律效力，这一效力可保证产品具有买方要求之特性，保证买方购买该产品目的的实现，
考虑到卖方将约定向买方提供相关文件证明产品质量符合合同规定，如果买方指定检验员未按时进行检验，这将不影响按原计划发货。
一切有关在出口国仓库或港口进行货物检验所产生的费用，将由买方承担。
支付条款
条款2中规定的总合同金额将由买方向卖方先预付50％的TT，卖方收到合同全款后开始发货。
合同约定的支付金额将汇到卖方的银行帐户，地址如下：
银行：中国银行北京分行海淀支行
地址：中国，北京，雅宝路8号
户名：同方股份有限公司
公司地址：中国．北京．海淀区．清华同方科技广场
帐号：816603580508091014
SWIFT码：BKCHCNBJXXX
6. 质 量
根据附件二规定，卖方将保证产品严格符合本合同约定的技术指标；产品等级为一等品，
7. 担 保
产品担保为期1年。对于有质量问题的产品，经卖方确认后，将新的替代品随下批货物一同发出，但替代品的运输费用由买方承担。
8. 不可抗力
由于卖方控制范围以外的原因，如（并非局限于以下几个）战争、游行、自然灾害等，由此产生的未运、迟运，卖方将不负责任。这种情况下，卖方应在事件发生后5天内通知买方，在不可抗力消失后推迟发货或者在双方协议下取消合同。
9. 处 罚
. 如此合同中约定货物推迟发货，根据双方协议的条款，买方将对迟发的货物收取每天最多%的罚金，总罚金数额不得超过合同总金额的4%。由自然灾害、材料供应或运输以外而引发的推迟将不适合此条款。卖方将对推迟付款收取每天最多％的罚金，总罚金数额不得超过合同总金额的4%。
. 如果延迟发货超过3个月，买方有权终止这批货物的合同，需向卖方书面通知此事。
10. 索 赔
一旦数量出现不符，买方有权在收到货物的5天内对不符部分进行索赔，卖方在收到买方信息的60天内解决问题。
11 仲 裁
不论在合同签定前、履行中以及终止后，有关本合同的解释或履行若双方存在任何争议，一方代表应于10天以内向另一方出具书面申请安排会面，双方通过友好平和的努力解决争端，而不是诉之法律。
所有与合同或与其履行无关的争端，双方应通过友好的谈判解决。若谈判无果，双方将听从仲裁法庭的宣判，宣判结果具有权威性、不可上诉性并对双方具有强制性。
12. 合同的有效性以及有效期
本合同自双方代表签字之日起生效，并于所述双方义务均完成之时失效。
. 如果买方在签订本合同20天内未付50％的预付款，卖方有权终止合同。
13. 其他条款
. 任何条款的修订需经买卖双方签字才能生效。
. 本合同产生的所有费用，包括在卖方国境内产生的银行费用、税款及海关费用，都将由卖方承担，相反的情况，对于买方也同样成立。
. 本合同包含13项条款和2个附件，皆为合同的组成部分
其中一方对合同中某款项有修改意向，则应至少提前此款项生效日7天时间与另一方进行书面沟通。
一方收到另一方提议后，应在收到之日起10天以内给出答复，否则此提议视同接受。
卖方应保证本合同及其附件中所包含的技术规格以及其他条件等不变。
买方需对货物投保。
本合同一式两份，均具同等法律效力。
签字日期：2007年9月 日
卖 方：同方股份有限公司 买 方：
法定代表人： 法定代表人：
委托代理人： 委托代理人：
附件一：研发与差旅费
买方预先支付 10 万美元的研发经费给卖方。卖方在收到研发费用后开始研发进程，预计在 2 个月内完成样机研发测试并开始批量生产。研发经费最终将摊入每台产品。
产品研发前，需要中国的相关专家五人到以色列做技术交流，双方同意，专家的差旅费用由买方承担，差旅费用包括机票、食宿和出差补助（中国政府规定，出国补助每人每天88美元）。
附件二：产品的技术指标
Item Definition
The MFD shall have sufficient resolution and Gray levels to support current and future picture quality and wide viewing angles specially designed for cross-cockpit viewing for either portrait or landscape installations.
The live video from the DMC shall be presented in colour and monochrome formats without compromising the quality and the resolution of the video image received.
Each MFD have two digital video inputs. One input is connected to DMC #1; the second is connected to DMC #2.
In normal operation the MFD displays the input#1 video channel. The pilot can switch between video input#2 and input#1 channels by pushing on dedicated video switching button on the MFD bezel. It shall also possible to switch between the video inputs by the RS-485 communication command.
Each MFD have two RS-485 channels. One is connected to DMC #1; the second is connected to DMC #2. The two RS-485 shall be independent, and shall receive and transmit data from/to the two DMCs.
The MFD shall have:
Active Matrix Liquid Crystal Display (AMLCD) Colour Display Head NEC Part Number NL10276BC20-16 or eqvivalent upon Buyer's approval.
DVI/TMDS Digital Video channel links – Two Inputs
Serial communication data busses – Two channels
OSS s switches surrounding the display face
Brightness and contrast controls
ON/OFF controls
The MFD Software development shall be in accordance with RTCA- DO178B, level-C.
MFD Block Diagram
The MFD block diagram is as follows:
Figure 1: MFD Block Diagram
Interface definition
The MFD shall contain the essential interfaces to meet input and output requirements for common operation with two DMCs
28VDC power supply
0-5VAC, 400 HZ or 0-28VDC light panel
Digital Video DVI/TMDS between each DMC and the MFD
Serial link channel between each DMC and MFD according to RS-485 FD
Discrete inputs ON/OFF, NVG/Normal
28VDC Input
The MFD power supply accepts 28VDC according to the more severe conditions of both the MIL-STD -704A category B and MIL-STD-704D from the aircraft and produces all the necessary voltages to the MFD.
5 VAC /28 VDC bezel lighting Input
The MFD shall accept 0 to 5VAC or 0-28VDC power as bezel illumination (finalize before PDR) .
DVI/TMDS digital video inputs
Each MFD shall contain two single link TMDS, uses DVI protocol, inputs. The video- in resolution can be VGA, SVGA or XGA resolution
The MFD shall display as default the video from input#1. The pilot can switch between video input#2 and input#1 channel by pushing on video switching button on the MFD bezel.
RS-485 Communication Data Bus
The MFD shall contain two RS – 485 communication data buss. The communication data bus shall be differential, bi-directional, full duplex over a two twisted pair cable, according to RS-485 standard. Load / Input impedance: 120 ohm. The communication rate will be 9600 baud
Two RS-485 communication busses are connected to two different DMCs
The RS-485 channels transfer commands, status, BIT data and the pilot selection on the MFD bezel. In case of Master DMC failure the second DMC takes control of the RS-485 communication controller.
The RS-485 communication data busses protocol shall be defined by IAI.
Power ON/OFF Discrete Input /Output
The MFD shall provide remote discrete Power ON/OFF discrete input to turn on the unit and additional echo discrete for power on status.
Voltage level: Unit OFF =High impedance
Unit ON = GND
DMC debug Discrete Input
The MFD shall provide DMC debug /Normal discrete input to indicate the DMC Debug state or Normal mode of the MFD.
In the DMC debug state (according the MFD debug discrete), the MFD will not display the Display Timeout page, if MFD video and RS-422 is not refreshed. As an option this capability shall implemented by the software command.
NVG/Normal Discrete Input
The CDU shall provide NVG/Normal discrete input to indicate the NVG mode or Normal mode of the CDU.
Voltage level: Normal =High impedance
NVG = GND
Characteristics
Performance
Operational performance
MFD modes
The MFD system shall operate in 3 different modes: Normal, INITIALIZATION and INIT BIT.
Transitions between the modes of operation will be upon internal MFD system events (failures), external events (communication failure), initialization process, or upon DMC serial link commands.
Warm Up Time
The MFD shall be fully operational and conform to the performance requirements listed in the following table:
Temperature
Degraded performance *
Full performance
> 15°C
10 seconds max
60 seconds max
0°C
Mandatory : 15 seconds max
Mandatory :
90 seconds max
-40° C
Mandatory : 2 minutes max
10 minutes max
* Electrically: Full performance. Optically: readable picture
Display Characteristics
The high quality fully sunlight readable display shall be provided by a ruggedized commercially available colour TFT AMLCD. The AMLCD module provides among other features heater and A/R coating compliant to MIL-C-14806A coated on the front display surface. The MFD shall be environmentally ruggedized.
Display Dimensions
The nominal display area of the MFD will be mandatory 6 inches by 8 inches at portrait oriented (8 inches by 6 inches for landscape).
Display Resolution
The MFD shall have mandatory 768 x 1024 RGB (XGA) pixels for portrait/landscape configuration.
Grey Shades
The MFD shall have at least 64 levels per colour (or 12 square root steps).
Viewing Angle
The Viewing Angles for Contrast Ratio>=11 for white color at night are as follows
Horizontal (For both landscape and portrait MFD): Not less than +/- 40 degrees
Vertical (For both landscape and portrait MFD): Not less than 45 degrees up and 15 degree down
The contrast ratio at night is defined as follows:
Cr=L2/L1
Where:
L2 is average luminance of activated display elements
L1 is average luminance when the display elements are not activated
The angles measured with respect to a line normal to the display surface.
The display information will be clear to the pilots and the flight engineer from their current seats on the platform under all ambient light conditions.
Contrast Ratio
The MFD display contrast ratio at ambient condition of 10,000 fc, for entire range of +/- 40 degrees Horizontal and +45/-15 Vertical viewing angles, shall be 3:1 or better for white color
Contrast Ratio is defined as (L2-L1)/L1 where L1 = average background luminance and L2 = average luminance of active display elements.
The actual contrast ratios at 10,000 FC at normal, at +/- 40 degrees Horizontal and +45/-15 Vertical viewing angles as well at ±45 degrees (Horizontal & Vertical) shall be specified by the vendor
Vendor to indicate contrast ratios for the 3 main colors (Green, Red and Blue) for color AMLCD at ambient condition of 10,000 fc and at dark ambient and normal , at +/- 40 degrees Horizontal and +45/-15 Vertical viewing angles as well at ±45 degrees (Horizontal & Vertical).
Brightness Level
The maximum MFD brightness will be at least 130 fL white luminance brightness level, over the entire screen, for DAY mode.
Whereas the minimum brightness shall be less than fL luminance for night and NVG mode.
Night mode maximum illumination and Day mode minimum illumination should have about 2fl of overlap
Illumination Uniformity
White flat field luminance shall not vary by more than 25% over the display surface. The uniformity is defined as follows:
Uniformity = (MAX-MIN)/ ((MAX+MIN)/2)
NVIS Compatibility
The MFD display shall be mandatory compatible with Gen 2++/Gen 3 NVG per MIL-L- 85762A.
Chromaticity
Vendor shall provide the primary RGB color coordinates, including the coordinate tolerances, of the MFD display.
Rise time and fall time
AT 25 deg C, when measured from 0% black to 90% white transmission - the typical rise time shall be less than 30 ms and 50 msec max rise time.
When measured from 100% white to 10% black transmission the typical fall time shall less than 30 ms and 50 msec max fall time
Defects
The AMLCD (including filters) shall be examined for blemishes, surface scratches and pixel element defects as defined below.
A Blemishes
The number and size of blemishes shall be as defined below. Blemishes size for elongated blemishes is defined as:
Size = (length +width)/2
Blemish size(mm)
No of blemishes allowed
Minimum separation (mm)
Less than
Not considered blemish
28
10
25
3
25
Over
0
B. Scratches
When adding the length of all scratches (not including front surface) in each size category, the total length allowed is as the following table:
Scratch width
Max. total length allowed
Less than mm
Any length
to mm
25 mm
Over mm
Defective
C. Pixel Defects
Pixel defects refer to permanently lit, inoperative and intermittent defects, affecting any sub-pixel of a color pixel. The MFD display shall contain no full column or row defects, no two adjacent defective pixels and no more than 50 ppm sub-pixel defects (. 50ppm of : Vertical pixels x horizontal pixels x3) cumulative of all classifications Display element defects
A pixel is defined as a complete color group. A pixel defect shall be defined as one or more non-functioning sub-pixel elements within a pixel.
A non-functioning sub-pixel is defined as one not being under independent luminance
Video Processing
The MFD shall contain a scaler to The MFD shall adapt the video- in bit timing to the AMLCD resolution/bit timing.
Optical Performance Measurements
Optical performance defined in this section shall be measured in accordance with MIL L 85762A.
Display Quality
The display shall be mandatory free of jitter, flicker and toggling. The image shall be stable under all operation conditions.
Electrical Power Characteristics
The MFD shall operate mandatory from +28VDC aircraft power supply in accordance with MIL STD-704A category B and MIL-STD-704D, for normal and abnormal operation with the following exceptions:
The steady state voltage is mandatory 16 to VDC
The MFD shall be mandatory operated (during engine start) with 14 VDC for 45 seconds. During this time, the MFD shall operate normally, including display performance,
The MFD shall maintain full performance when using power with characteristics which are specified in curve 3 figure 9 of MIL-STD-704A and MIL-STD-704D.
The MFD shall full perform without re-initialization upon 50 m sec micro-power cuts and also in case of 0V for 50msec.
No damage and functional degradation will be observed when the power operates at its upper limits or high voltage intermittent extremes as defined in MIL STD-704A category B and MIL-STD-704D, for normal and abnormal operation.
When the display is powered up after long interruption the display shall turn to power up mode and initialization is performed.
Power consumption
The max power consumption shall be mandatory as follows:
Steady state (heater off): maximum 60 W
Cold start (at -45 deg C): maximum 180 W.
Light panel, max power consumption shall be maximum 9 watts.
Protection
Built-in protection against A/C power supply malfunctions to be provided.
All power supplies shall have short circuit, open circuit, and over-voltage protection. Power supply circuits shall recover and resume normal operating without recycling or re-installations when the condition is removed. No fuses or fusible links shall be used.
Overload Protection
In addition to the overload protection requirements according to Para of MIL-E-5400, the MFD shall be protected from chain reaction failures including those from external overloads (shorts) caused by grounding of external wiring. No damage to the MFD shall result from open circuits or grounding of wiring external to the MFD
Input Circuits
Input circuits shall not suffer damage when equipment that interfaces with the MFD is not installed or is in a power "OFF" condition.
Power On Removal and Replacement
Removal and replacement of the MFD with the power applied shall not damage the MFD.
Polarity Reversal
The MFD circuits shall not be damaged when subjected to a polarity reversal due to inadvertent reversal of 28VDC power input
Software
Any software within the MFD shall be mandatory developed in accordance with the requirements of RTCA/DO-178B, for Level C software.
The RS-485 communication data busses protocol shall be defined by IAI and be developed based on RTCA DO178B Level C software requirements as well.
Growth potential
The MFD design shall include as follows:
100% spare computation power for CPUs
50% spare capacity and additional 100% expansion capabilities for memories
Physical characteristics
The physical characteristics of the MFD design shall reflect consideration of the human interface and environmental factors during the phases of equipment operation and maintenance Design and construction of the product shall comply with constraints as specified herein.
MFD Bezel
The MFD Bezel is 8X6 OSSs arrangement, comprised of Soft keys and specific functions keys . Additional four (4) OSS shall be 3 states rocker selection switch.
The dedicated hard keys shall be ON/OFF switch, , brightness control rocker, contrast/gamma control rocker, and video input switch. All other OSS shall be programmable soft keys, knobs for selection of parameters, etc.
All the push buttons on the MFDs should preferably be flush with the top face of the unit and the bezel thickness should be minimum.
The protrusion of control knobs/switches and the bezel with respect to the front face of the instrument panel shall be kept to a minimum and to be indicated in the proposal by the Vendor.
The optical performance shall be design and checked according to MIL-P-83335 and MIL-P-7788F
Portrait configuration (for reference only)
Landscape configuration(for reference only)
Figure 2: MFD Configurations
Unlighted Chromaticity
The color of the panel markings shall be white (as defined in FED-STD-595 color 37875) in daylight when the backlighting is not engaged.
The color of the bezel itself and the keys shall be matt black, color 37038 as defined in FED-STD-595.
The size of different marking characters and controls shall be mandatory in accordance with MIL-STD-1472B or equivalent standard.
All legends on MFD should be in English language
Unlighted Contrast
The daylight contrast between markings, legends, and indicia and the background on the panel shall be determined with the lighting system inoperative.
Contrast C is defined as:
C = (B2-B1)/B1
Where B1 is the average luminance of the background immediately surrounding the marking and B2 is the average luminance of the marking.
At 10000Fc ambient light the contrast ratio between the unlighted legend and the background shall be at least 9:1.
Panel Lighting Chromaticity
The chromaticity of the light transmitted through the panel markings of the bezel shall be mandatory compatible with Gen 2++/Gen 3 NVG. Lighting colour will be ANVIS green A according to the MIL-L-85762 requirements.
Luminance and Uniformity
The bezel lightning shall be powered by 0-5VAC or 0-28 VDC supplied by the air craft. The Bezel luminance at 5 VAC shall be plus or minus fL.
The luminance ratio between any two measurements on two different legends shall not exceed 2 to1.
The legend luminance uniformity shall be less than 25% at a legend surface when the uniformity is defined as Max BRT-Min BRT)/(Max BRT +Min BRT)/2
The bezels lightning shall be implemented by LEDs
Panel viewing angle
All the panel legends shall be clearly readable from the following viewing angle with respect to the normal to the MFD:
Horizontal: Not less than +/- 40 degrees
Vertical: Not less than 45 degrees up and 15 degree down
Keys Activation
The keys shall have:
Pre-travel of minimum
Over-travel of mm minimum
Total travel of mm maximum
Total travel includes 3 zones: pre travel (off position), snap zone (off or on) and over travel (on position)
The actuation force shall be: 700+/- 140 gr. Keys bounce time: 3 msec max.
If at the time of sampling two keys or more are simultaneously depressed, and no keys were depressed at the previous sampling, this shall be considered as an illegal operation. If at the previous sampling only one key was depressed and then additional key, or keys, is depressed, the additional key, or keys, shall be ignored. If a key is depressed for more than 30 sec, it will be identified as a “stuck key” and an additional key shall be accepted
Response time
The time between a MFD control pressing/releasing and the brightness/contrast changing shall be less than 50 msec.
The time between an OSS pressing/releasing and the reporting through the communication data bus shall be less than 50 msec
Dimensional and weight Limitations
a. WEIGHT: Enclosure weight shall mandatory not exceeds .
b. SIZE:
Width: 210 mm max for portrait and 260mm max for landscape configuration.
Height: 260mm max for portrait and 210 mm max for landscape configuration.
Depth: 200mm max (behind panel, excluding connector)
External Connectors
The MFD shall have circular, military type; connector(s).The connector(s) shall not cause any degradation in the MFD performance.
MFD Installation
The MFD shall be installed to the helicopter’s instrument panel(s) by 4 captive screws. No tray is required for installation.
The MFD shall be secured to its location by quick release fasteners without the need for special tools.
MFD s shall be interchangeable without any harmonisation requirements.
Further installation details and requirements will be provided in the preliminary design.
Cooling
Cooling shall be self contained
Reliability
Vendor to demonstrate readability of MFDs under different ambient light conditions as well as display quality of monochrome video on colour display
MTBF
The minimum MFD MTBF shall be mandatory as follows:
Field MTBF: 4,000 hours
Calculated MTBF @ 200C: 15,000 hours
Calculated MTBF @ 350C: 12,000 hours
Calculated MTBF @ 550C: 10,000 hours
The Calculated MTBF shall be according -HDBK-217F.
Operational Service Life
As a design goal, the MFD shall have a total operational life of at least 50000 hours when, operated in any of the operation modes or an applicable combination thereof and exposed simultaneously to any applicable combination of the environmental conditions listed in this document. Operational service life is defined as the time interval from the start of the operation of the MFD until wear out. Wear out is defined as the state where the cost of overhaul or repair exceeds the cost of replacement of the MFD.
Useful Life
As a design goal, the MFD shall have a useful life of at least twenty five (25) years for any applicable combination of operation, endurance, performance and storage requirements in cases where the operation hours as defined in the previous paragraph were not exceeded. Useful life is defined as the total time elapsed from date of receiving the MFD until date of its wear out.
Storage Life
The MFD shall have no shelf limitation
Maintainability
Definitions for Maintainability Terms
Mct or MTTR mean active corrective maintenance time.
Mct max. - The maximum time within which any of all corrective maintenance tasks can be accomplished.
LRU - Line Replaceable Unit -is defined as any item whose flight line removal and replacement with a like serviceable item is considered the optimum corrective method.
SRU-Shop Replaceable Unit-is defined as a sub unit of an LRU which is normally removed and replaced to effect the repair of the LRU.
Corrective Maintenance Task - is defined as the work performed as a result of a failure, for the purpose of restoring an item to a serviceable condition. The steps of a corrective maintenance task are:
Fault isolation.
Fault correction.
Adjustment
Calibration and checkout
This includes the task of connecting and employing . but excludes the tasks of positioning . and obtaining spares.
Quantitative Maintainability Requirements
The design of the MFD shall be such that unscheduled active corrective maintenance time (means Mct or MTTR) and the maximum corrective maintenance task time shall not exceed, as a design goal, the following:
O-LEVEL
I-LEVEL
D-LEVEL
MTTR
MCTmax
MTTR
MCTmax
MCTmax
MTTR
hour
hour
hour
hour
hour
hour
Note: The above times are on the assumption that there is free access to the installed unit.
Built-In Test (BIT)
Adequate initial and continuous BIT should be incorporated with appropriate failure annunciators.
The MFD shall include built-in test provision for failure detection and fault isolation BIT shall be design as internal part of the MFD design. BIT shall require no external stimuli or measurement equipment to perform its function.
Reliability or BIT circuitry and devices shall be an allocated portion of the electronic system, LRU or SRU reliability.
Any fault detected by the MFD BIT, shall be transited to the DMC via the RS-422 control channel.
The bidder will describe the tests performed during the BIT modes
BIT failure capability
The MFD shall have three BIT modes:
Periodic/Continuous BIT
Initiated BIT
Power up bit
Periodic/Continuous BIT
The Periodic Bit shall be performed automatically and simultaneously on a non-interference basis alongside the normal system operation.
The Periodic Bit monitor and/or test all the functions and/or signals on a sequential basis, except for signals and/or functions, which can not be tested during flight due to safety or other constraints.
Power up BIT
During the MFD power up cycle (system initialization) an automatic power up BIT shall be performed. At the end of the BIT process the MFD analyses the results and transmits the MFD BIT results via serial link to the DMC or the on the ground.
Initiated BIT
The Initiated BIT function comprised the automatic BIT and the test pattern. . The Initiated BIT is activated by the operator which sends instructions through the DMC, or the on the ground, to MFD for activating the Initiated BIT routine which is stored in the MFD.
At the end of the BIT process the MFD analyses the results and transmits the BIT results via the serial link to the DMC or the on the ground.
A test pattern is generated in the DMC, or the on the ground, and shall be presented on the MFD screen during part of the IBIT process. During IBIT the OSSs shall be tested for open and close operation by a build in video generator.
The software configuration shall be displayed during the push button test.
BIT Performance Requirements
Operator participation in detection and isolation of MFD display failures is required to achieve the herein specified percentages of failure detection and isolation
As a design goal, the BIT shall detect at least 98% of the all failures (at their predicted frequencies).
As a design goal, 100% of the detected failures shall be indicated by sending an appropriate signal to the status monitoring function, At least 98% of the detected failures shall be isolated by the faulty MFD by providing the required outputs
BIT Data Reporting
MFD shall report all failures detected by Periodic/Continuous, Power up and Initiated bit to the DMC via serial link for storage, or to the on ground. The data reporting will consist of the failed function and test step code.
False Alarm
As a design goal, no less than 98% of the indicated BIT failures shall be caused by actual MFD failure (no more than 2% will be false alarm). A failure being defined as any fault which prevents the MFD from meeting its specified performance.
BIT Timing
As a design goal, the time required for completion of a full periodic BIT cycle shall not exceed 2 sec.
Environmental Condition
The MFD shall be mandatory qualified to Environmental conditions as defines in the following table.
No.
TEST
REQUIREMENTS
I.
Environmental Tests: As per MIL-STD-810C/810D/810E or equivalent
1.
Temperature
Continuous operation: -20°C to +55°C Short term operation (30 minutes): -30°C to +71°C Storage temperature: -40°C to +85°C
High temperature
Method , Procedure I
Low temperature
Method , Procedure I
2.
Pressure Altitude
-500 m to 7000 m Method , Procedure I, Equipment Cat. 4
3.
Humidity
As per MIL-STD-810C Method , Procedure III with relative humidity 100%
4
Vibration
As per MIL-STD-810D, Method , , (3) Table -IV
Note: 1. (3) with low-level random background added to sinusoids.
Unit to be switched "On" during the test.
Duration: 3 hours / axis
Axes of exposure: 3 orthogonal axes
Main rotor frequency: 21 Hz Tail rotor frequency: 105 Hz
5.
Gun fire vibration
As per MIL-STD-810C, Method , Procedure I sine super imposed on random vibration Firing rate f1, 2f1, 3f1, 4f1. Eqpt. Cat. II
6
Shock
As per MIL-STD-810C, Method , Procedure I.
7
Acceleration
As per MIL-STD-810C, Method , Procedure I and II
8
Salt fog
As per MIL-STD-810C, Method , Procedure I.
9
Fungus
As per MIL-STD-810C, Method , Procedure I.
10
Sand and dust
As per MIL-STD-810C, Method , Procedure I.
11
Drip proof test
As per MIL-STD-108E, Para with 45° inclination or equivalent
12
Solar Radiation
As per MIL-STD-810C, Method , Procedure I.
Radiation, if any, from MFDs should not be hazardous to the crew
Design and Construction Constrains
Materials Process and Parts
Material, Selection Limitations
All organic materials having either linkages shall be tested for hydrolytic stability shall be tested for hydrolytic stability. The use of natural leather, fixed paper and plastic dielectric capacitors, microcircuits sockets, asbestos, mercury, magnetic materials and magnesium alloys is prohibited. All materials to be used have to be of aeronautical quality.
Dissimilar Metals
Grouping of similar and dissimilar metals shall be in accordance with MIL-STD-454. Protection of dissimilar metals combinations shall be in accordance with requirement 16 of MIL-STD-454.
Corrosion Prevention and Control
The requirements of MIL-E-5400, Para are applicable.
Finish
The interior surfaces of the MFD shall be finished in accordance with MIL-E-5400 with absorbent dull black material. The interior finish of the MFD shall be to the Seller's standard practice consistent with the requirements. Exterior surfaces shall be finished in accordance with MIL-E-5400, MIL-P-23377.
Parts
All parts shall be of good quality and shall be procured to high-grade specification from qualified manufactures.
First selection priority shall be given to those parts, which are at least in industrial grade.
Flex Printed Wiring Boards
Flex printed wiring board shall meet the requirement of MIL-P-50884.
Electromagnetic Interface and Compatibility
The subject equipment shall meet MIL-STD-461 category A1B and shall be tested in accordance with MIL-STD-462 Notice 2. The generation and susceptibility to electromagnetic interference shall meet MIL-STD-461 requirements as follows:
Para.
Test
CS01
Conducted susceptibility, 30 Hz to 50 kHz, power leads as per MIL-STD-461B/462
CS02
Conducted susceptibility, 50 kHz to 400 MHz, power leads as per MIL-STD-461B/462
CS06
Conducted susceptibility, spike power leads
CE01
Conducted emission, 30 Hz to 15 kHz, power leads as per MIL-STD-461B/462
CE03
Conducted emission, to 15 MHz, power leads as per MIL-STD-461B/462
CE07
Conducted emission, spikes power leads as per MIL-STD-461B/462
RS02
Radiated susceptibility, spikes and power frequency, magnetic fields as per MIL-STD-461B/462*
RS03
Radiated susceptibility, 14 kHz to 18 GHz, electric field (Limit: 200 V/m) as per MIL-STD-461B/462.
RE02
Radiated emission, 14 kHz to 10 GHz, electric field as per MIL-STD-461B/462
Power Supply
As per MIL-STD-704A, MIL-STD-704D and DO-160C,sec 16 Cat B
Compass Safety
Compass safe distance shall be 305 mm (12 inches) for a deflection of 1 degree on magnetic compass. Procedure as per Section 15, Cat. Z of DO-160C (or equivalent)
* RS02 and RS03 to include system level tests using interface hardness to be supplied by "buyer"
Note: Electrical bonding shall be in accordance with MIL-B-5087.
Lightning Protection
Following tests have to be conducted as per SAE. AE4L (AE4L-87-3):
Lightning induced transient susceptibility
Lightning damage strength
Critical pins – Level 4 others – Level 3.
Note: In the event of the above environmental and EMI/EMC tests being conducted as per any other equivalent specification, the supplier shall provide the details for IAI's consideration, explaining the details of equivalence deviation, if any.
Bonding
Bonding shall be in accordance with MIL-B-5087. The MFD shall be designed to bond to airplane structure. The DC resistance of the bound from MFD chassis to the mounting structure shall be ohm or less.
Marking of Parts and Assemblies
Parts and assemblies shall be marked in accordance with MIL-E-5400, Para. .
Workmanship
Workmanship shall conform to MIL-STD –454 requirements 5 and 9.
DOCUMENTATION
All documents shall be in English language. Drawing shall be supplied in metric units. Documentation will be in accordance with the requirements of .
All software development documents shall be according RTCA DO-178B standard requirements.
Integrated Logistic support
The MFD shall be designed with a goal of minimizing the cost of operation and maintenance and to enhance the accomplishment of required maintenance
Maintenance
The maintenance concept is based on 3 maintenance levels: organizational, intermediate and depot.
1. The maintenance concept for the organizational level requires easy access to MFD, with the design for quick removal/replacement including BIT capability for fault detection isolation and system checkout.
2. Intermediate level maintenance shall consist of repairing MFD sent from the organization level. Repairs shall be accomplished by replacing shop, replaceable units (SRUs) The MFD shall be designed with external and internal test points as required to enable connection of equipment to test equipment performed end to end testing, calibration/adjustments and fault isolation.
3. Depot level maintenance shall consist of verification test of SRUs fault isolation of defective SRUs to component or active element group level, repair of SRUs and final check-out (including calibrations/adjustments).
Organizational Level Maintenance
The organization maintenance can be carried out using a minimum of support equipment.
Equipment Handling
Weight restriction shall be in accordance with the requirements setout in chapter in MIL-STD-1472 specification.
The MFD handling or protective equipment is needed for maintenance or protective equipment is needed for maintenance or for transport between the local maintenance and/or supply facility and aircraft (display face and external connectors).
Adjustments
On-board adjustment alignment or calibration shall not be permitted for the MFD. Any adjustments, alignment or calibration that may be required shall be carried out only at intermediate level. SRUs shall be designed in such a manner that all SRUS replacements, when installed in the LRU, shall immediately be operable at design accuracy without requiring, functional adjustment or calibration of the replaced SRU or LRU
Reversibility Restrictions
The MFD design and construction shall incorporate features so that it would mechanically and electrically, be impossible to incorrectly install it, or to attach cables, electrical plugs, or any other items to in an improper manner. Mechanical keyed mating, different size connectors, etc. shall be incorporated to eliminate all such possibilities.
Preventive Maintenance
There shall be no Preventive Maintenance (including maintenance inspections and forced replacement).
Intermediate and Depot Level Maintenance
Compatibilities between MFD and TE
The MFD shall be designed to be compatible with the TE in accordance with the requirements specified herein. The MFD will be capable of being tested by TE, except for visual observation of display and manual settings/adjustments, which exceed the programmable capabilities of TE.
The MFD have a functional /test connector, which shall provide all the necessary access to testing and diagnostic fault isolation as specified herein.
.
Accessibility
The MFD shall be constructed in a manner that will enable removal and replacement of any SRU (except for the mother board) without removing or disconnecting any other assembly in the MFD whenever possible.
All SRU, assembly and subassembly installation hardware and the covers, which are required to be removed for SRUs assembly, or subassembly replacement, shall employ captive-type hardware to prevent loss during normal and field maintenance.
All MFD installation hardware shall be captive to prevent loss during aircraft maintenance.
The construction of the MFD shall provide easy access to test points and ability to easy adjustment and replacement items in the shop.
Guides shall be provided for board alignment. As required, circuit boards shall be provided with reinforced eyelets to prevent damage to boards during removal or installation.
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