源自@張德浩沒(méi)有醉
駕駛艙理念 FCTM-AOP-10-20-10
空客飛機(jī)駕駛艙的設(shè)計(jì)通過(guò)飛機(jī)操作環(huán)境滿足飛行機(jī)組的操作需求， 同時(shí)保證電傳操縱家族最大的共性。
A320系列飛機(jī)駕駛艙面板布局
頂板 Overhead Panel
遮光板 Glareshield
主儀表板 Main Instrument Panel
中央操縱臺(tái) Pedestal
側(cè)操縱臺(tái) Lateral Consoles
腳蹬 Pedals
設(shè)計(jì)理念 FCTM-AOP-10-20-20
OVERHEAD PANEL 頂板
與發(fā)動(dòng)機(jī)相連的系統(tǒng)控制面板是垂直布局的，以便能直接并本能的完成正常/非正常程序。此外，這個(gè)布局的目的是盡可能減少飛行機(jī)組的錯(cuò)誤。
GLARESHIELD 遮光板
遮光板支持自動(dòng)飛行系統(tǒng)(AFS)的短期的策略控制?？梢浴疤ь^”進(jìn)行操縱并對(duì)于兩名飛行員都能容易進(jìn)行操縱。
MAIN INSTRUMENT PANEL 主儀表板
主儀表板主要支持對(duì)于以下功能是必須的顯示組件：
‐ FLY 飛行 (PFD )
‐ NAVIGATE 導(dǎo)航 (ND)
‐ COMMUNICATE 通訊 (DCDU（新飛機(jī)部分選裝）)
‐ MONITOR the various aircraft systems 監(jiān)控各個(gè)飛機(jī)系統(tǒng) (ECAM).
The display units are located in the full and non-obstructed view of both pilots.
顯示組件位于兩名飛行員全部并無(wú)遮擋的視野中。
PEDESTAL 中央操縱臺(tái)
中央操縱臺(tái)主要支持以下控制：
‐ 發(fā)動(dòng)機(jī)和推力（發(fā)動(dòng)機(jī)主電門，推力手柄）
‐ 飛機(jī)形態(tài)（減速板手柄，襟翼手柄，方向舵配平）
‐ 導(dǎo)航(MCDU, FMS)
‐ 通信(RMP).
風(fēng)擋參考 CCOM/05-020 Clearview Windows
fixed windows
sliding windows
側(cè)窗操作 參考FCOM/DSC-56-40 Sliding Windows
駕駛艙照明 FCOM/DSC-33-10 Cockpit Lighting
駕駛艙通風(fēng) CCOM/02-090 Cockpit Air Conditioning
駕駛艙應(yīng)急設(shè)備
FCOM/DSC-25-10 Flight Deck
FCOM/DSC-25-20 Emergency Equipment
撤離繩 CCOM/05-020 Escape Rope
氧氣 FCOM/DSC-35-20 Fixed Oxygen System for Cockpit
FCOM/PRO-NOR-SOP EMERGENCY EQUIPMENT
駕駛艙預(yù)先準(zhǔn)備檢查下列應(yīng)急設(shè)備
‐ 救生衣存放
‐ Xxx stowed
‐ 防煙罩或PBE存放
‐ 便攜滅火瓶保險(xiǎn)在位/壓力綠區(qū)
‐ 氧氣面罩存放
‐ 應(yīng)急手電筒存放
‐ 撤離繩存放
頂板信息索引（按SOP檢查操作順序）
風(fēng)擋雨刷 WIPER 參考 FCOM/DSC-30-60-20 Rain Removal
電源 ELEC 參考 FCOM/DSC-24-20 Electrical
火警 FIRE
參考 FCOM/DSC-26-20-20 Fire Protrction - Engines and APU
參考 FCOM/DSC-31-05-30 Attention - Getters
空調(diào) AIR COND
參考 FCOM/DSC-21-10 Air Conditioning
參考 FCOM/DSC-36-20 Peneumatic
A320
通風(fēng) Ventilation
參考 FCOM/DSC-21-30 Ventilation
貨艙加溫 CARGO HEAT （選裝）
參考 FCOM/DSC-21-40 Cargo
駕駛艙燈光 INT LT
參考 FCOM/DSC-33-10 Cockpit Lighting
艙音記錄器 RCDR
參考 FCOM/DSC-23-10-40 Cockpit Voice Recorder
參考 FCOM/DSC-31-60-20 FLT Recorders
撤離 EVAC 參考
FCOM/DSC-23-40-10 Emergency Evacuation
ADIRS 參考 FCOM/DSC-34-NAV-10-20 ADIRS
經(jīng)典款
時(shí)尚款
外部照明 EXT LT 參考 FCOM/DSC-33-20-20
旅客通知 SIGNS
參考 FCOM/DSC-33-30-20 Emergency Lighting
參考 FCOM/DSC-33-40-10 Signs
機(jī)艙增壓 CABIN PRESS
參考 FCOM/DSC-21-20-40 Pressurizition
燃油 FUEL 參考 FCOM/DSC-28-20 Fuel
構(gòu)型I
構(gòu)型II
(部分新飛機(jī)加裝額外中央油箱ACT)
音頻轉(zhuǎn)換 AUDIO SWITCHING
參考 FCOM-DSC-23-10-50 Audio Switching
RMP 參考 FCOM/DSC-23-10-20 Radio Management Panel
ACP 參考 FCOM/DSC-23-10-50 Audio Control Panel
使用原理 FCTM/AOP-10-20-30
頂板的暗艙概念
每個(gè)按鈕都有一盞或兩盞燈:
‐ 上部表示告警或系統(tǒng)狀態(tài)(e.g. FAULT light, OPEN light).
如果無(wú)需顯示警告或系統(tǒng)狀態(tài)，兩個(gè)灰點(diǎn)取代燈的位置
‐ 下部對(duì)應(yīng)于:
·在按鈕電門上，對(duì)應(yīng)系統(tǒng)控制的選項(xiàng)(e.g. ON, OFF, OVRD), or
·在按鈕上，對(duì)應(yīng)系統(tǒng)的狀態(tài)(e.g. MAN).
如果無(wú)需顯示系統(tǒng)控制的選項(xiàng)，兩個(gè)灰點(diǎn)取代燈的位置。
一般的操作規(guī)則是：燈滅原理。系統(tǒng)準(zhǔn)備好并適合飛行。
按鈕/按鈕電門燈
顏色編碼的，表示系統(tǒng)的狀態(tài):
‐ Amber:
‐ Red:
‐ Green:
‐ Blue:
‐ White:
‐ Blank 空的: 該系統(tǒng)適合飛行。
磁羅盤 FCOM/DSC-34-NAV-20 Compass
可收放的直讀磁羅盤位于風(fēng)擋以上中間位置
磁差牌置于磁羅盤之上
Note: 由于APU繼電器在駕駛艙中的位置，APU起動(dòng)過(guò)程可能干擾磁羅盤讀數(shù)。
目視結(jié)冰指示器 FCOM/DSC-30-70-10 Visual Ice Indicator
An external visual ice indicator is installed between the two windshields. 位于機(jī)身外兩風(fēng)擋之間。
There can be also an external ice detector light 磁羅盤和結(jié)冰指示器燈光使用同一個(gè)頂板電門 參考 FCOM/DSC-33-10-30
遮光板
FCU 參考 FCOM/DSC-22_10-40-20 FCU
其它遮光板指示燈/電門
FCOM/DSC-31-50 EFIS Control Panel & Chronometer
FCOM/DSC-31-30 Attention Getters
FCOM/DSC-27-20-30 SIDE STICK PRIORITY lt
FCOM/DSC-22_30-80-30-10 Autoland Warning Light
FCOM/DSC-46-10-40-10 ATC
主儀表面板顯示
PFD FCOM/DSC-22_10-40-40 Primary Flight Display
FCOM/DSC-31-40 Indications on PFD
FMA 參考 FCOM/DSC-22_30-100 Flight Mode Annunciator
飛行方式信號(hào)牌位于PFD的頂部，顯示自動(dòng)推力的狀態(tài)，AP/FD的垂直和水平方式，進(jìn)近能力以及AP/FD/自動(dòng)推力的接通狀態(tài)。
新的信號(hào)牌出現(xiàn)外圍會(huì)有白框顯示10秒。某些模式轉(zhuǎn)換情形下白框顯示延長(zhǎng)到15秒并伴有三下滴答聲。
左邊的三列
第一行以綠色顯示接通的模式。
第二行以藍(lán)色或洋紅色顯示預(yù)位的模式。
洋紅色表示預(yù)位或接通的模式存在限制。
第三行顯示特殊信息
‐ 飛行操縱相關(guān)的信息最優(yōu)先
· 紅色僅俯仰配平閃爍9秒后穩(wěn)定
· 琥珀色使用人工俯仰配平閃爍9秒后穩(wěn)定
‐ FMGS相關(guān)信息次優(yōu)先
THE FOURTH COLUMN
以白色顯示進(jìn)近能力。
以藍(lán)色顯示最低高度。
注：FMA的氣壓或無(wú)線電數(shù)值不取整：輸入在MCDU PERF APPR頁(yè)面上的精確數(shù)值顯示在FMA上。
THE FIFTH COLUMN 第五列
以白色顯示AP，F(xiàn)D和自動(dòng)推力的接通狀態(tài)。
FMGC自動(dòng)轉(zhuǎn)換在FD外圍顯示10秒的框
當(dāng)自動(dòng)推力預(yù)位而沒(méi)有激活以藍(lán)色顯示A/THR。
注：FMGS同步自動(dòng)推力模式，AP/FD模式和進(jìn)近能力在兩部PFD上顯示相同的信息。
中心區(qū)域
特定地面指示
參考 FCOM/DSC-17-20-30 Side Stick Indications On PFD
參考 FCOM/DSC-31-40 Specific Ground Indication
地面滑跑引導(dǎo)指令桿為綠色，如有航向信標(biāo)臺(tái)信號(hào)，飛機(jī)在地面或空中時(shí)低于無(wú)線電高度30ft，顯示該符號(hào)。它顯示飛行指引偏航指令，以保持飛機(jī)處于跑道中心線。
姿態(tài)信息
參考 FCOM/DSC-31-40 Attitude Data
參考 FCOM/DSC-22-30-20 Flight Director
Fixed Aircraft Symbol 固定飛機(jī)符號(hào)
This symbol is in black, and outlined in yellow. The yellow outline is dimmed if the flight crew selects TRK-FPA, unless the FMA is in TOGA or FLX mode. 符號(hào)為黑色，邊框是黃色，當(dāng)飛行機(jī)組選擇TRK-FPA黃色邊框暗淡，除非FMA在TOGA或FLEX模式。
Roll Scale 橫滾刻度
This scale is in white, and has markers at 0, 10, 20, 30, and 45 ° of bank.在坡度0, 10, 20, 30, 和45 °的位置標(biāo)有白色的刻度。
Roll Index (yellow) 橫滾指標(biāo)
This pointer indicates the bank angle. When the bank angle exceeds 45 °, all the PFD symbols except those for attitude, speed, heading, altitude, and vertical speed, disappear. The display returns to normal when the bank angle decreases below 40 °. 此游標(biāo)指示坡度。當(dāng)坡度超過(guò)45 °，PFD上除姿態(tài)，速度，航向，高度和垂直速度以外的其它符號(hào)都消失。當(dāng)坡度減小到低于40°時(shí)顯示恢復(fù)正常。
Pitch Scale (white) 俯仰刻度
This scale has markers every 10 ° between 80 ° nose up and 80 ° nose down (every 2.5 ° between 10 ° nose down and 30 ° nose up). When pitch angle exceeds 25 ° nose up or 13 ° nose down, all the PFD displays except attitude, speed, speed trend, heading, altitude, and vertical speed disappear. Beyond 30 °, large red arrowheads indicate that the attitude has become excessive and show the direction to move the nose in order to reduce it. The display returns to normal when pitch angle becomes less than 22 ° nose up or 10 ° nose down. 在俯仰角±80°范圍內(nèi)每10°（30°抬頭和10°低頭范圍中間是每2.5°）有個(gè)刻度。當(dāng)俯仰角超出25°抬頭或13°低頭，PFD上除了姿態(tài)，速度，速度趨勢(shì)，航向，高度和垂直速度以外的其它顯示消失。超過(guò)30°，大紅箭頭表示姿態(tài)過(guò)量并指示移動(dòng)機(jī)頭的方向以減少幅度。當(dāng)俯仰角少于22°抬頭或10°低頭顯示恢復(fù)正常。
Flight Control Protection Symbols 飛行操縱保護(hù)符號(hào)
The display shows these symbols (=) in green:顯示器以綠色呈現(xiàn)(=)符號(hào)
· On the roll scale to mark the bank angle protection availability. 在橫滾刻度上標(biāo)記坡度保護(hù)的可用區(qū)間。
· On the pitch scale at 15 ° nose down or 30 ° nose up to mark the pitch limits. 在俯仰刻度上位于15°抬頭和30°低頭以標(biāo)記俯仰限制。
An amber x replaces these symbols if the corresponding protection is lost. 當(dāng)失去對(duì)應(yīng)的保護(hù)，琥珀色的x取代這些符號(hào)。
(參考 FCOM/DSC-27-20-10-20 Protections - General)
Sideslip Index (yellow) 側(cè)滑指標(biāo)
This trapezoidal index moves beneath the roll index. On ground, it represents the lateral acceleration of the aircraft. In flight, it shows sideslip (as computed by the FAC). One centimeter of displacement indicates 0.2 g. The sideslip index is against its stop at 0.3 g. 梯形指標(biāo)在橫滾指標(biāo)底下移動(dòng)。在地面上表示飛機(jī)的橫向加速度，飛行中則指示側(cè)滑（由FAC計(jì)算）。1厘米的偏移表示0.2 g。側(cè)滑指標(biāo)在0.3 g 達(dá)到量程極限。
In case of engine failure at takeoff or go around, the sideslip index changes from yellow to blue.在發(fā)動(dòng)機(jī)失效的起飛和復(fù)飛時(shí)，側(cè)滑指標(biāo)由黃變藍(lán)
In this case, the sideslip index is called β target. 在這種情況下，側(cè)滑指標(biāo)被稱為 β 目標(biāo)。
擦機(jī)尾俯仰限制指示
無(wú)線電高度
A value appears, when the aircraft is lower than 2 500 ft. 當(dāng)飛機(jī)高度低于2500ft時(shí)顯示無(wú)線電高度值。
‐ If a DH has been entered, the radio height appears: 輸入過(guò)DH后，無(wú)線電高度在以下情況出現(xiàn)
· In green, when DH 100 ft < RA < 2 500 ft
· In amber, when RA < DH 100 ft
If “NO” is entered as the DH on the MCDU APPROACH page, 0 ft becomes a default value. 當(dāng)MCDU APPROACH頁(yè)面的DH輸?shù)氖恰癗O”時(shí)，0 ft 成為默認(rèn)值。
When the aircraft reaches the decision height selected on the MCDU, DHletters flash amber for 9 s, then remain amber above the radio height indication. 當(dāng)飛機(jī)到達(dá)MCDU預(yù)選的決斷高度，DH在無(wú)線電高度指示之上以琥珀色閃爍9秒后保持。
‐ If no DH has been entered, or if both FMGCs fail, the radio height appears:
如果沒(méi)有輸入DH或雙FMGC失效，無(wú)線電高度以如下方式呈現(xiàn)
· In green, when 400 ft < RA < 2 500 ft
· In amber, when RA ≤ 400 ft
The radio height indication changes every 10 ft down to 50 ft, then every 5 ft down to 10 ft, then every foot. 無(wú)線電高度指示每10 ft變動(dòng)一次至下降到50 ft，每5 ft變動(dòng)一次至下降到10 ft，之下每英尺都變動(dòng)。
飛行航徑向量 Flight Path Vector
The Flight Path Vector (FPV) is the flight reference with the TRK and FPA as basic guidance parameters. 飛行航徑向量(FPV)是以TRK和FPA為基本向?qū)?shù)的飛行參考。
The FPV appears on the PFD as a symbol, known as the 'bird'. The bird indicates the track and flight patch angle in relation to the ground. PFD顯示的FPV符號(hào)也叫“小鳥(niǎo)”。小鳥(niǎo)指示相對(duì)地面的航跡和飛行航徑角。
The track is indicated on the PFD by a green diamond on the compass, in addition to the lateral movement of the bird in relation to the fixed aircraft symbol. PFD羅盤上的◇表示航跡，隨著小鳥(niǎo)相對(duì)固定飛機(jī)符號(hào)的水平運(yùn)動(dòng)。On the ND, the track is indicated by a green diamond on the compass scale. ND羅盤刻度上的◇表示航跡。The difference in angle between track and heading indicates the drift. 航跡和航向之差表示偏流。
The flight path angle is indicated on the PFD by the vertical movement of the bird in relation to the pitch scale. PFD上小鳥(niǎo)相對(duì)垂直刻度的移動(dòng)表示飛行航徑角。
With the flight directors (FD) ON, the Flight Path Director (FPD) replaces the HDG-VS Flight Director (FD). With both FD pb set to OFF, the blue track indexappears on the PFD horizon. 當(dāng)飛行指引(FD)接通時(shí)，飛行航徑指引(FPD)取代HDS-VS飛行指引(FD)。當(dāng)兩個(gè)FD按鈕都位于OFF，藍(lán)色的航徑指標(biāo)顯示在PFD地面線上。
The bird is the flying reference that should be used when flying a stabilized segment of trajectory, In dynamic manoeuvres, the bird is directly affected by the aircraft inertia and has a delayed reaction. As a result, the bird should not be used as a flight reference in dynamic manoeuvres. 小鳥(niǎo)應(yīng)該被用于在穩(wěn)定航段上作為飛行參考，比如非精密進(jìn)近或目視起落。在做機(jī)動(dòng)時(shí)小鳥(niǎo)直接受飛機(jī)慣性的影響有延遲效應(yīng)，所以小鳥(niǎo)不應(yīng)作為機(jī)動(dòng)飛行時(shí)的參考。
FCTM/AS-BIRD
The attitude flight reference should be used for dynamic manoeuvres, for example, take-off or go-around. An action on the sidestick has an immediate effect on the aircraft attitude. The flight crew can monitor this flight reference directly and accurately during these manoeuvres. 姿態(tài)飛行基準(zhǔn)應(yīng)用于動(dòng)態(tài)機(jī)動(dòng)飛行，比如，起飛或復(fù)飛。側(cè)桿上的一個(gè)動(dòng)作會(huì)立刻對(duì)飛機(jī)姿態(tài)產(chǎn)生影響。飛行機(jī)組在這些機(jī)動(dòng)飛行中能夠直接并準(zhǔn)確地監(jiān)控飛行基準(zhǔn)。
RELIABILITY 可靠性
The FPV is computed from IRS data, therefore, it is affected by ADIRS errors. An error may be indicated by a small track error, usually of up to ± 2 °. This can be easily determined during the approach.
因?yàn)轱w行軌跡矢量(FPV)由IRS數(shù)據(jù)計(jì)算，因此它會(huì)受到ADIRS誤差的影響。這種誤差可由小的航跡誤差指示，通常最大為±2°。在進(jìn)近階段可比較容易確定。
The FPV is also computed from static pressure information. Therefore, the bird must be considered as not reliable, if altitude information is not reliable.
FPV計(jì)算還使用靜壓信息。因此，如果（氣壓）高度信息不可靠，那么小鳥(niǎo)必須被認(rèn)為是不可靠的
PRACTICAL USE OF THE BIRD 小鳥(niǎo)的實(shí)際使用
一般規(guī)則
When using the 'bird', the flight crew should first change attitude, and then check the result with reference to the 'bird'.
當(dāng)使用“小鳥(niǎo)”時(shí)，首先飛行機(jī)組應(yīng)改變姿態(tài)，然后參考“小鳥(niǎo)”來(lái)檢查結(jié)果。
WINDSHEAR 風(fēng)切變
FCOM/DSC-22_40-40 Windshear Detection Function
【記憶項(xiàng)目】FCOM/PRO-ABN-SURV [MEM] WINDSHEAR
The windshear detection function is provided by the Flight Augmentation Computer (FAC) in takeoff and approach phase in the following conditions: 風(fēng)切變探測(cè)由FAC提供，在以下情況
‐ At takeoff, 3 s after liftoff, up to 1 300 ft RA
‐ At landing, from 1 300 ft RA to 50 ft RA
‐ With at least CONF 1 selected.
The warning consists of:
‐ A visual “WINDSHEAR” red message displayed on both PFDs for a minimum of 15 s. PFD顯示“WINDSHEAR”至少15秒
‐ An aural synthetic voice announcing “WINDSHEAR” three times. 合成音響“WINDSHEAR”三次
W/S AHEAD前方風(fēng)切變
FCOM/DSC-34-SURV-30-30 Predictive Windshear System
【記憶項(xiàng)目】FCOM/PRO-ABN-SURV [MEM] WINDSHEAR AHEAD
W/S AHEAD message on the PFD
This message is displayed, when the Predictive WindShear system detects windshear ahead of the aircraft. 預(yù)測(cè)式風(fēng)切變系統(tǒng)探測(cè)飛機(jī)前方的風(fēng)切變，根據(jù)警告級(jí)別在PFD顯示琥珀色或紅色的“W/S AHEAD”
The message is in amber or red, depending on the level of the alert.
Predictive WindShear area indication
PWS SCAN message on the ND
空速 Airspeed
Actual Airspeed Reference Line and Scale 實(shí)際空速基準(zhǔn)線及刻度
A white scale, on a grey background, moves in front of a fixed yellow reference line (next to a yellow triangle) to indicate airspeed. The minimum airspeed indication is 30 kt. 最小的空速指示是30 kt。
Speed Trend (yellow) 速度趨勢(shì)
This pointer starts at the speed symbol. The tip indicates the speed the aircraft will reach in 10 s, if its acceleration remains constant. 速度變化穩(wěn)定時(shí)，箭頭指示空速在10秒后將要達(dá)到的位置。
It also disappears, if the FACs fail. 當(dāng)FAC失效也會(huì)消失。
Target Airspeed (magenta or blue) 目標(biāo)速度
This symbol gives the target airspeed, or the airspeed corresponding to the target Mach number. 目標(biāo)空速或目標(biāo)馬赫數(shù)對(duì)應(yīng)的空速。
The target airspeed is the airspeed computed by FMGC in managed speed mode (magenta), or the airspeed manually entered on the FCU in selected speed mode (blue). The target speed is indicated by a magentaor blue triangle.FMGC計(jì)算的管理速度，或FCU上手動(dòng)選擇的目標(biāo)速度，以洋紅色或者藍(lán)色三角表示。
When the target speed is off the speed scale, its value is displayed as numbers, either above or below the speed scale.當(dāng)目標(biāo)速度超出速度刻度以數(shù)字顯示在速度刻度頂上或底下。
Mach Number (green) 馬赫數(shù)
It is displayed, when it is greater than0.5. 當(dāng)馬赫數(shù)大于0.5時(shí)顯示
Speed Protection (green) 速度保護(hù)
This symbol indicates the speed (VMO 6 kt or MMO 0.01) at which overspeed protection becomes active
ECON Speed Range (magenta) 經(jīng)濟(jì)速度范圍
In descent mode with the ECON/AUTO SPD mode active, these two thick lines replace the selected speed symbol. It shows the upper and lower limits, calculated by the FMGC. 由FMGC計(jì)算，以兩條粗線顯示上下限制，在DES模式并且ECON.AUTO SPD模式激活時(shí)取代選擇速度的符號(hào)。
‐ The upper speed is target speed 20kt, limited to VMAX or VMO -3 kt or MMO -0.006, whichever is lowest. 上限是目標(biāo)速度 20 kt，限制在在VMAX，VMO-3kt或MMO-0.006三者中的最低值之下。
If a speed limit or a speed constraint applies, the upper margin is limited to ECON SPD 5 kt. 如果存在速度限制（limit飛機(jī)氣動(dòng)限制，constraint飛行程序限制，自己領(lǐng)會(huì)）上限是ECON SPD 5kt。
‐ The lower speed margin is the target speed -20 kt, limited to green dot, F, S, or VLS, whichever is higher. 下限是目標(biāo)速度 -20kt，限制在綠點(diǎn)速度，F，S，或最小可選速度四者最高值以上。
Minimum Selectable Speed (VLS) 最小可選速度
The top of the amber strip along the speed scale indicates this speed. It represents the lowest selectable speed providing an appropriate margin to the stall speed. 最小可選速度在失速速度之上提供適當(dāng)?shù)挠喽?Refer to DSC-27-20-10-20 Protections - High Speed Protection)
VLS information is inhibited from touchdown until 10 s after liftoff. VLS信息在接地以后到離地10內(nèi)被抑制。
Alpha Protection Speed 迎角保護(hù)速度
The top of a black and amber strip along the speed scale indicates this speed. It represents the speed corresponding to the angle of attack at which alpha protection becomes active 表示α保護(hù)被激活時(shí)的迎角所對(duì)應(yīng)的空速(Refer to DSC-27-20-10-20 Protections - General).
It is displayed when in pitch normal law. 俯仰正常法則下顯示。
Alpha MAX Speed 最大迎角速度
The top of a red strip along the speed scale indicates this speed. It represents the speed corresponding to the maximum angle of attack that the aircraft can attain in pitch normal law 表示飛機(jī)在俯仰正常法則下所能達(dá)到的最大迎角對(duì)應(yīng)的空速(Refer to DSC-27-20-10-20 Protections - General).
It is displayed when in pitch normal law. 俯仰正常法則下顯示。
VMAX 最大速度
The lower end of a red and black strip along the speed scale defines this speed.
It is the lowest of the following: 以下的最低值
‐ VMO or the speed corresponding to MMO
‐ VLE
‐ VFE
(Refer to DSC-27-20-10-20 Protections - High Speed Protection)
Stall Warning Speed (VSW) 失速警告速度
The top of a red and black strip along the speed scale defines this speed.
It is the speed corresponding to the stall warning. 失速警告對(duì)應(yīng)的空速(Refer to DSC-27-20-10-20 Protections - General).
VSW information is inhibited from touchdown until 5 s after liftoff. VSW在接地以后到離地五秒內(nèi)被抑制。
It is displayed when operating in pitch alternate or pitch direct law. 在俯仰備用法則或俯仰直接法則下顯示。
Decision Speed (V1) 決斷速度
This is a blue symbol (numeral one) that the crew manually inserts via the MCDU. When it is off the scale, the upper part of the scale shows it in numbers. 機(jī)組在MCDU手動(dòng)輸入，速度帶符號(hào)為數(shù)字1 ，超出空速帶刻度則以數(shù)字顯示在頂上。
It disappears after liftoff 離地后消失(Refer to DSC-22_10-50-50 Other Speeds).
Minimum Flap Retraction Speed 最小收襟翼速度
This is a green symbol (letter F).
It appears when the flap selector is in position 3 or 2. 當(dāng)襟翼手柄位于3或2出現(xiàn)(Refer to DSC-27-20-10-20 Protections - High Speed Protection).
Minimum Slat Retraction Speed 最小收縫翼速度
This is a green symbol (letter S).
It appears when the flap selector is in position 1. 當(dāng)襟翼手柄位于1時(shí)出現(xiàn)(Refer to DSC-27-20-10-20 Protections - High Speed Protection).
VFE NEXT 下一檔襟翼最大速度
The VFE next symbol is an amber equal sign showing the VFE corresponding to the next flap lever position. = 表示VFE最大襟翼速度，對(duì)應(yīng)下一檔襟翼手柄位置
It appears when the aircraft altitude is below 15 000 ft or 20 000 ft, depending upon the FAC standard 在20000ft出現(xiàn)(Refer to DSC-22_10-50-30 Limit Speeds).
Green Dot (Engine-out operating speed in clean configuration) 綠點(diǎn)（光潔形態(tài)單發(fā)操作速度）
This green dot appears, when the aircraft is flying in the clean configuration. 光潔形態(tài)下出現(xiàn)○It shows the speed corresponding to the best lift-to-drag ratio. 表示最佳升阻比對(duì)應(yīng)的空速。
Rotation speed: (VR) 抬輪速度
VR is entered on the PERF takeoff page of the MCDU, and is indicated by a cyan circle. MCDU的PERF takeoff頁(yè)面輸入VR，由○表示。
This cyan circle is visible during takeoff. ○起飛時(shí)可見(jiàn)
Note: V2 is represented by the target speed index during takeoff. V2代表起飛時(shí)的目標(biāo)速度指標(biāo)。
V2 is manually inserted by the crew via the MCDU. V2由機(jī)組在MCDU上手工輸入。
【記憶項(xiàng)目】不可靠空速指示 PRO-ABN-NAV [MEM] UNRELIABLE SPEED INDICATION
高度 Altitude
Altitude Indication 高度指示
This appears both as a white moving scale, and as a green digital readout on a grey background. Small white marks are positioned on the scale against the round values (e.g. 280, 290...). “NEG” appears in the window in white for negative values. The altitude window changes from yellow to amber, if the aircraft deviates from the FCU-selected altitude or flight
level. 當(dāng)飛機(jī)偏離FCU上選擇的高度或高度層，高度窗由黃色變?yōu)?span>琥珀色
On any approach for which an minimum is entered in the FMGS, the altitude numbers change from green to amber, when the aircraft goes below the minimum. 在FMGS輸入minimum后當(dāng)飛機(jī)下降通過(guò)該數(shù)值高度數(shù)字由綠色變?yōu)?span>琥珀色。
Linear Deviation (green filled circle)
This symbol appears next to the altitude corresponding to the theoretical vertical profile computed by the FMGC. It is displayed from the top of descent down to the MAP altitude. FMGC計(jì)算的理論垂直剖面對(duì)應(yīng)的高度以●符號(hào)呈現(xiàn)。從下降頂點(diǎn)之下到復(fù)飛點(diǎn)高度該符號(hào)都顯示。
Target Altitude or Selected Flight Level Symbol (blue)目標(biāo)高度或選擇高度層符號(hào)
This symbol shows the FCU selected altitude (if QNH or QFE BARO reference is selected) or the selected flight level (if STD BARO reference is selected.)
When the FMGC operates in the vertical managed mode, this symbol is magenta if it represents a flight plan altitude constraint that the FMGC will follow. If the target altitude or flight level is on the scale, the symbol is displayed and the numerical value appears inside the symbol. 垂直管理方式當(dāng)存在高度限制，符號(hào)為洋紅色。
If it is off the scale, the symbol is not displayed, and the numerical value appears above or underneath the scale. 超出刻度范圍，符號(hào)以數(shù)值顯示在刻度帶頂上或底下。
Barometric Reference 氣壓基準(zhǔn)
The display shows “STD” or it shows “QNH” or 'QFE' and the numerical setting in hectoPascals or inches of mercury.
It pulses when the selection made by the flight crew is not correct (STD not selected above transition altitude in climb or STD still selected in approach below transition level). 過(guò)渡高度以上未選STD或過(guò)渡高度層以下仍選STD會(huì)閃爍。
Metric Altitude Indication 米制高度顯示
Target altitude or selected flight level (magenta or blue)meters.米制顯示所選高度
Altitude indication (green) in meters. 米制顯示飛機(jī)當(dāng)前實(shí)際高度
進(jìn)近Minimum指示
Approach minimum is displayed on the altitude scale by an amber indication.在高度刻度上以琥珀色指示。
Radio Height 無(wú)線電高度
Landing Elevation (brown) 著陸標(biāo)高
The top of the brown surface on the altitude scale represents the landing elevation at the flight-planned destination. 棕色區(qū)域的頂端在高度表刻度上表示飛行計(jì)劃目的地機(jī)場(chǎng)著陸標(biāo)高。
It is displayed:
‐ during flight phases 7 and 8 and
‐ if the STD reference mode is not selected. 沒(méi)有選擇STD模式
Ground reference 地面基準(zhǔn)
A red ribbon on the right of the altitude scale represents the field elevation. This ribbon, which is driven by the radio altimeter signal, is displayed below 570 ft. 高度刻度右邊的紅帶表示無(wú)線電高度表對(duì)應(yīng)的機(jī)場(chǎng)標(biāo)高，在570ft以下顯示。
垂直速度 Vertical Speed
The displayed vertical speed information is normally based on both inertial and barometric data. 垂直速度顯示基于慣性和氣壓數(shù)據(jù)合成。If inertial data is not available, it is automatically replaced by barometric information. 當(dāng)慣性數(shù)據(jù)不可用，自動(dòng)由氣壓信息代替。
In this case, the window around the numerical value becomes amber.這種情況包圍數(shù)值的窗口顯示琥珀色。
Analog pointer 模擬指針
This pointer, which is normally in green, points to a white vertical speed scale, displayed on a grey background
Digital indication 數(shù)字指示
This number, normally in green, is the vertical speed in hundreds of feet per minute. 數(shù)字單位是100ft/min。It disappears, if the vertical speed is less than 200 ft/min. 垂直速度小于200ft/min時(shí)消失
The analog pointer and the digital indication become amber, if:
· V/S is greater than 6 000 ft/min, (climb or descent)
· V/S is greater than 2 000 ft/min, during descent when 1 000 ft < RA < 2 500 ft, or
· V/S is greater than 1 200 ft/min, during descent and RA < 1 000 ft.
TCAS RA FCOM/DSC-34-SURV-60-20
FCOM/PRO-ABN-SURV [MEM] TCAS WARNINGS
Red area 紅區(qū)
Indicates the vertical speed range, when there is a high risk of conflict. 沖突風(fēng)險(xiǎn)高的垂直速度區(qū)間
Green area 綠區(qū)
Indicates the recommended vertical speed range. It is wider than the red area. 推薦的垂直速度區(qū)間，比紅區(qū)要寬
TCAS message
Appears in amber provided that the TCAS is not in standby, when the TCAS cannot deliver RA data, or in case of an internal TCAS failure. TCAS無(wú)法提供RA信息或內(nèi)部失效，顯示“TCAS”
航向 Heading
Heading Reference Line and Scale
A white scale on a grey background moves in front of a fixed yellow reference line to indicate the actual magnetic heading. 通常指示實(shí)際的磁航向
“TRUE” appears, when the display indicates the true heading, rather than the magnetic heading (latitude above 73 ° North or below 60 ° South). 當(dāng)出現(xiàn)“TRUE”則顯示真航向。
Selected Heading or Track Index (blue)
This pointer is in blue, and indicates the heading or track displayed on the FCU HDG-TRK window. 同步顯示FCU HDG-TRK窗口。
If the FD pushbutton is OFF, a second heading/track symbol appears on the horizon line, and markers are displayed every 10 °. 當(dāng)FD按鈕處于OFF，第二個(gè)航向/航跡符號(hào)出現(xiàn)在地平線上，每10°顯示一個(gè)標(biāo)記。
Actual Track Symbol 實(shí)際航跡符號(hào)
This symbol is a small green diamond. 標(biāo)志是◇
PFD顯示的故障旗和信息
參考 FCOM/DSC-31-40 Flags and Messages Displayed on PFD
備用速度/高度帶 BUSS
The BUSS is displayed on both PFDs when the flight crew turn off all ADRs. 當(dāng)飛行機(jī)組關(guān)閉所有ADR后BUSS顯示在兩部PFD上。
The activation of this BUSS is not reversible. 啟用BUSS是不可逆的
The BUSS information is based on the angle of attack (AOA), and depends on the slat/flap configuration. BUSS信息基于迎角，并且參考襟縫翼構(gòu)型。
備用速度帶 Backup Speed Scale
Red FAST area
Amber FAST area
Green area
Target speed (green triangle)
Actual speed reference (yellow line)
Amber SLOW area
Red SLOW area
備用高度帶 Backup Altitude Scale
Current GPS altitude 當(dāng)前GPS高度
GPS ALT flag
GPS flag (displayed depending of the aircraft configuration)
Note: The vertical speed indication is no longer displayed. 垂直速度不再顯示
ND 導(dǎo)航顯示器
參考 FCOM/DSC-22_10-40-50 Navigation Display
FCOM/DSC-31-45 Indications on ND
The FMGS generates the following information, displayed on the EFIS Navigation Displays:
‐ Flight plan (active secondary, temporary, dashed) 飛行計(jì)劃
‐ Aircraft position and lateral deviation from the flight plan 飛機(jī)位置以及相對(duì)飛行計(jì)劃的水平偏移
‐ Pseudo-waypoints along the flight plan 沿飛行計(jì)劃的虛擬航路點(diǎn)
‐ Raw data from tuned Navaids and type of selected approach 所調(diào)諧的導(dǎo)航臺(tái)的原始數(shù)據(jù)以及所選的進(jìn)近類型
‐ Various display options (waypoints, Navaids, NDBs, airports, constraints)
‐ Wind information and various messages.
通過(guò)遮光板上的EFIS控制面板選擇ND顯示模式和顯示范圍
There are five different displays (five modes to display navigation information)五種不同的導(dǎo)航顯示模式 :
‐ ROSE LS
‐ ROSE VOR
‐ ROSE NAV
‐ ARC
‐ PLAN
The Navigation Display (ND) can provide a weather radar image in all modes, except PLAN.
PLAN MODE
Aircraft Position and True Track 飛機(jī)位置和真航跡
Map Reference Point 地圖基準(zhǔn)點(diǎn)
ARC MODE
ROSE NAV and ARC modes give the pilot the same information, but ARC mode limits it to the forward 90 ° sector. ROSE NAV和ARC給飛行相同信息，ARC模式只顯示前方90°扇區(qū)。
Waypoint: 航路點(diǎn)
Flight plan waypoints 計(jì)劃航路點(diǎn)
The ND displays these as green diamonds (white, for TO waypoints).
Pseudo waypoint 虛擬航路點(diǎn)
Point of the flight path where the aircraft is predicted to reach a selected altitude or speed. 預(yù)計(jì)飛機(jī)到達(dá)所選高度或速度的位置。
TO Waypoint
This is the next waypoint to be overflown, except when a DIR TO with ABEAM PTS has been performed (in this case, the DIR TO waypoint is displayed on the top of the screen instead of the NEXT ABEAM waypoint).
符號(hào)定義 參考 FCOM/DSC-31-45 ROSE NAV MODE/ARC MODE
ROSE MODES 通用符號(hào)
參考 FCOM/DSC-31-45 ROSE MODES
ROSE VOR 模式專屬符號(hào)
參考 FCOM/DSC-31-45 ROSE VOR MODE
ROSE LS MODE 專屬符號(hào)
參考 FCOM/DSC-31-45 ROSE LS MODE
ND其它顯示
氣象雷達(dá) & PWS FCOM/DSC-34-SURV-30-30
Weather Radar Picture 氣象雷達(dá)圖像
Tilt Angle 傾斜角
Gain Mode 增益模式
Failure Messages 故障信息
Path Attenuation Compensation (PAC) Alert PAC警告
Severe and Moderate Turbulence Display
Core Threat Assessment
Associated Threat Assessment
Predictive Overflight Function
GPWS FCOM/DSC-34-SURV-40-40 GPWS
Terrain on ND
These pushbutton are located on either side of the ECAM. Each pushbutton controls the onside terrain display.
ON : The terrain is displayed on the ND if the: 滿足以下條件ND顯示地形圖像
‐ TERR pb-sw is selected ON, and
‐ TERR FAULT light is not on.
‐ TERR STBY ECAM memo is not displayed.
‐ The FMGS navigation accuracy is high.
The ON light comes on.
OFF : The terrain data is not displayed on the ND.
同時(shí)參考 FCOM/DSC-31-45 GPWS terrain picture
圖自 ACSS T3CAS Traffic Management Computer Pilot’s Guide
ATSAW & TCAS
FCOM/DSC-34-SURV-20-30
FCOM/DSC-34-SURV-60-20
ND顯示的故障旗和信息
ECAM 顯示組件布局
The Engine Warning Display (E/WD) appears on the ECAM's upper Display Unit (DU). 參考 FCOM/DSC-31-15
‐ The upper part of this DU displays:
· Engine parameters 發(fā)動(dòng)機(jī)參數(shù)(Refer to DSC-70-90-40 Engine Warning Display)
· Feedback messages 反饋信息(Refer to DSC-31-05-60 Feedback Messages)
· Fuel On Board (FOB) 機(jī)載燃油(Refer to DSC-28-20 ECAM Upper Display)
· Slats/Flaps' position 縫翼/襟翼位置(Refer to DSC-27-30-20 ECAM Upper Display)
‐ The lower part of this DU displays messages generated by the FWC:
· Warning and caution messages, when a failure occurs 發(fā)生故障時(shí)的警告和注意信息
· Memos when there is no failure. 沒(méi)有故障顯示備忘信息
E/WD (CFM)
E/WD (IAE)
The lower part of the DU, dedicated to ECAM messages, is divided into two sections of several lines each.
Bottom left : ‐ Primary or independent warnings and cautions, or 主要或獨(dú)立的警告和注意，或
‐ Memo information. 備忘信息
Bottom right : ‐ Title of the system affected by a primary or independent warning or caution, in case of overflow on the bottom left part, or 左下角滿了顯示受主要或獨(dú)立警告或注意的系統(tǒng)標(biāo)題，或
‐ Secondary failure, or 次級(jí)故障，或
‐ Memo, or 備忘
‐ Special lines (such as “AP OFF”, “LAND ASAP”). 特殊行
故障的類型：Type of Failures
Independent : a failure that affects an isolated system or item of equipment without degrading the performance of others in the aircraft. 獨(dú)立：只影響單獨(dú)系統(tǒng)或設(shè)備而不會(huì)導(dǎo)致飛機(jī)其他部分性能降級(jí)的故障。
If there are too many ECAM messages for the amount of space available in the lower part of the E/WD, a green arrow appears at the bottom of the display, pointing down to show that the information has overflowed off the screen. The pilot can scroll down to view additional messages by pushing the CLR pushbutton on the ECAM control panel (on the pedestal, just below the lower ECAM DU). 消息太多了會(huì)有綠色↓指示飛行員用ECP的CLR翻頁(yè)
Primary : a failure of a system or an item of equipment that costs the aircraft the use of other systems or items of equipment. 主要：系統(tǒng)或設(shè)備的故障會(huì)牽連飛機(jī)的其它部分。
Secondary : the loss of a system or an item of equipment resulting from a primary failure. 次要：受其它主要故障牽連的系統(tǒng)或設(shè)備失效。
The ECAM DU displays a primary failure as a boxed title. 主要故障標(biāo)題帶框
It identifies a secondary failure by putting a star in front of the title of the affected system. 次級(jí)故障標(biāo)題前面帶★
Note: The DU displays the overflow symbol, if primary or secondary failures overflow. In case of ELEC EMER CONFIG, the secondary failures are inhibited. 應(yīng)急電氣形態(tài)，次級(jí)故障被抑制。
備忘 MEMO
Memos appear in the lower part of the E/WD. They are normally in green, but may be amber in abnormal situations.
Memos list functions or systems that are temporarily used in normal operations. 備忘列出正常操作下臨時(shí)使用的功能或系統(tǒng)。
TO AND LDG MEMOS 起飛著陸備忘
During the takeoff and landing phases, the right side of the memo area displays specific TO INHIBIT or LDG INHIBIT (magenta) memos.
Takeoff and landing memos are displayed, as follows, during the related flight phases:
(★) This line disappears when the test is completed. It is replaced by “TO CONFIG NORMAL”, if aircraft configuration is correct.
The test is requested again, if the configuration becomes abnormal.
(★) “CONF 3” is displayed in alternate or direct law, or if the GPWS LDG FLAP 3 pushbutton is ON.
Note: After a go-around, if the aircraft does not climb above 2 200 ft RA, the landing memo appears only below 800 ft RA during the subsequent approach.復(fù)飛后飛機(jī)沒(méi)有爬到2200ft RA以上，接下來(lái)進(jìn)近到低于800ft RA才出現(xiàn)著陸MEMO。
SD 系統(tǒng)顯示器 參考 FCOM/DSC-31-20
The system/status display (SD) uses the lower ECAM DU to display :
‐ pages showing synoptic diagrams of the aircraft systems, or 飛機(jī)系統(tǒng)的示意圖，或
‐ the status page. 狀態(tài)頁(yè)
系統(tǒng)頁(yè)面 Syetem Page
The lower ECAM DU can display 12 system pages (For description see relevant FCOM chapter): 一共有12個(gè)系統(tǒng)頁(yè)面
‐ ENGINE (secondary engine parameters) 次要發(fā)動(dòng)機(jī)參數(shù)
‐ BLEED (air bleed) 引氣
‐ CAB PRESS (cabin pressurization) 客艙增壓
‐ ELEC (electric power) 電源
‐ HYD (hydraulic) 液壓
‐ FUEL (fuel) 燃油
‐ APU (auxiliary power unit) 輔助動(dòng)力單元
‐ COND (air conditioning) 空調(diào)
‐ DOOR/OXY (doors/oxygen) 艙門/氧氣
‐ WHEEL (landing gear, braking, ground spoilers, etc.) 起落架，剎車，擾流板等
‐ F/CTL (flight controls) 飛行操縱
‐ CRUISE (cruise) 巡航
The relevant system page automatically appears, as soon as any fault or malfunction triggers a caution or warning message. 當(dāng)任何故障或異常觸發(fā)注意和警告消息相關(guān)系統(tǒng)頁(yè)面自動(dòng)出現(xiàn)。
· The relevant system page automatically appears, when a parameter drifts out of its normal range. 當(dāng)參數(shù)偏出正常范圍相關(guān)系統(tǒng)頁(yè)面自動(dòng)出現(xiàn)。
· The value (shown in green) pulses, as long as it is outside its limits. 數(shù)值超限，以綠色閃爍。
· The advisory mode is inhibited in some flight phases. 某些飛行階段抑制咨詢模式。
· If no other mode is engaged, the SD displays the system page related to the present flight phase, as shown in the following diagram. 飛行階段示意圖
· Phase 2 : The F/CTL page replaces the WHEEL page for 20 s when either pilot moves his sidestick (more than 3 ° in pitch or roll) or when the rudder pedal deflection is more than 22 °. 階段2側(cè)桿移動(dòng)超過(guò)3°或腳蹬偏轉(zhuǎn)超過(guò)22° F/CTL頁(yè)面取代WHEEL頁(yè)面顯示20秒。
· The APU page appears when the APU MASTER switch is ON. It disappears when APU RPM has been above 95 % for 10 s, or when the APU MASTER switch is switched OFF.
· The ENGINE page appears at the beginning of start sequence or when a pilot selects “CRANK”. It disappears 10 s after the end of the start sequence, when the ENG MODE sel is set to NORM.
狀態(tài)頁(yè)
固定數(shù)據(jù)
Temperature 溫度
G LOAD 載荷
UTC
GW 總重
EIS 系統(tǒng)構(gòu)成參考 FCOM/DSC-31-05-30
ADIRS 參考FCOM/DSC-34-NAV-10-10
DMC再構(gòu)型 參考FCOM/DSC-31-05-50
In normal operation, each DMC drives the following Display Units :
‐ DMC 1 drives the CAPT PFD, CAPT ND and the ECAM DUs.
‐ DMC 2 drives the F/O PFD and F/O ND.
‐ DMC 3 is on standby, ready to drive any DU.
If DMC 1 or 2 fails (the “INVALID DATA” message is displayed on the DUs), the crew manually selects the DMC 3 source (“CAPT 3” or “F/O 3”).
If DMC 1 fails (or DMC 3, if “CAPT 3” was selected), DMC 2 automatically drives the ECAM.
DU再構(gòu)型 參考 FCOM/DSC-31-05-60
應(yīng)急電氣形態(tài) 參考 [QRH] ELEC EMER CONFIG SYS REMAINING
顏色編碼 參考 FCOM/DSC-31-10 Color Code
The ECAM display uses a color code that indicates the importance of the failure or the indication.
RED : The configuration or failure requires immediate action. 需要立即采取措施
AMBER : The flight crew should be aware of the configuration or failure, but need not take immediate action. 應(yīng)當(dāng)知曉情況，不必馬上行動(dòng)
GREEN : The item is operating normally. 正常
WHITE : These titles and remarks guide the flight crew, as they execute various procedures. 標(biāo)題和執(zhí)行程序的說(shuō)明。
BLUE : These are actions to be carried out, or limitations. 限制或?qū)⒁扇〉拇胧?/span>
MAGENTA : These are particular messages that apply to particular pieces of equipment or situations (inhibition messages, for example). 特定情況下的信息，例如抑制信息。
告警 FCTM/AOP-10-20-20 Alerts
ALERT TRIGGERING 告警觸發(fā)
As a general rule, an alert is required when:一般情況下，當(dāng)出現(xiàn)下列情況時(shí)觸發(fā)告警
‐ A system failure occurs 出現(xiàn)系統(tǒng)失效
‐ The aircraft violates the normal flight envelope 飛機(jī)違反正常飛行包線
‐ An unexpected event related to safety occurs 出現(xiàn)安全有關(guān)的以外事件(e.g. TCAS, TAWS)
‐ An outside message is coming up 出現(xiàn)來(lái)自外界的信息(e.g. cabin 客艙, ATC)
‐ A system automatically changes its mode of operation 系統(tǒng)自動(dòng)改變操作方式(e.g. AP auto-disconnection AP自動(dòng)斷開(kāi), mode reversion 模式轉(zhuǎn)換).
The alerts:該告警
‐ Trigger visual and/or aural indications 觸發(fā)目視和/或音響指示
‐ Are ranked by severity and priority 根據(jù)嚴(yán)重性和優(yōu)先性排序
‐ Are inhibited when not relevant in some specific flight phases.與某些特定的飛行階段無(wú)關(guān)時(shí)被抑制。
ALEART INDICATION 告警指示
The alerts indications are presented to the flight crew as follows 告警指示以下列方式呈現(xiàn)給飛行機(jī)組:
‐ Initial indication (visual or aural) via the MASTER CAUTION or MASTER WARNING
視覺(jué)或聽(tīng)覺(jué)初始指示
‐ The Engine Warning Display (EWD) displays the title of the alert related to the failure
發(fā)動(dòng)機(jī)警告顯示器(EWD)顯示與失效有關(guān)的告警標(biāo)題
‐ The System Display (SD) automatically displays the affected system
系統(tǒng)顯示器(SD)自動(dòng)顯示受影響的系統(tǒng)
‐ On the overhead panel, the pushbutton/pushbutton-switch light of the affected system comes on in amber or red. 在頂板上，受影響系統(tǒng)的按鈕燈亮琥珀色或紅色
警告/注意分級(jí) 參考 FCOM/DSC-31-10 Warning/Caution Classification
優(yōu)先原則：There are three priority levels for warnings and cautions :
- A level 3 warning has priority over a level 2 caution which has priority over a level 1 caution. 3級(jí)警告優(yōu)先于2級(jí)注意優(yōu)先于1級(jí)注意。
The FWC observes these priorities. FWC監(jiān)控這些優(yōu)先級(jí)。
The following outlines the ECAM’s operating modes:
Normal Mode: 正常模式
Failure Mode: 故障模式
Advisory Mode: 咨詢模式
Manual Mode: 人工模式
Most warnings and cautions are inhibited during critical phases of flight (T/O INHIBIT – LDG INHIBIT), because most system failures will not affect the aircraft’s ability to continue a takeoff or landing. 大多數(shù)警告和注意在飛行關(guān)鍵階段被抑制，因?yàn)榇蠖鄶?shù)系統(tǒng)故障不影響飛機(jī)繼續(xù)起飛或著陸的能力。
飛行警告計(jì)算機(jī) FCOM/DSC-31-05-30 Flight Warning Computer (FWC)
The two identical FWCs generate alert messages 警告消息, memos 備忘, aural alerts 音響警告, and synthetic voice messages 合成語(yǔ)音消息. For this purpose they acquire data:
‐ Directly from aircraft sensors, or systems, to generate red warnings
‐ Through the SDACs to generate amber cautions.
The ECAM display units display the alert messages generated by the FWCs.
The FWCs also generate:
‐ Radio height callouts 無(wú)線電高度喊話（參考 FCOM/DSC-34-NAV-40-10 Automatic Callout）
‐ Decision height callouts 決斷高喊話
‐ Landing distance and landing speed increments. 著陸距離和著陸速度增量。
The communications loudspeakers announce aural alerts and voice messages, and do so even when they are turned off. 揚(yáng)聲器播放音響警告和語(yǔ)言消息，即使被關(guān)閉依然如此。
低能量警告 參考FCOM/DSC-22_40-30 Low - Energy Aural Alert
音響指示 參考 FCOM/DSC-31-10 Audio Indicators
高度警告 參考 FCOM/DSC-31-40 Altitude Alert
EGPWS (Refer to DSC-34-SURV-40-10 Overview)
TCAS (Refer to DSC-34-SURV-60-20 Aural Messages)
側(cè)儀表面板
FCOM/DSC-34-SURV-40-40 PULL UP – GPWS pushbutton
FCOM/DSC-31-50 OFF/BRT knobs & PFD/ND Pushbutton
FCOM/DSC-23-10-50 Loudspeaker Volume Knob
FCOM/DSC-33-10-30 CONSOLE/FLOOR sw
FCOM/DSC-34-SURV-20-30 Traffic Selector (目前公司A321全部選裝)
起落架指示 FCOM/DSC-32-10-40 Landing Gear Indicator Panel
This panel is connected to LGCIU1, which receives signals from proximity detectors.
? light: comes on green if the gear is locked down.
UNLK light: comes on red if the gear is not locked in the selected position.
剎車風(fēng)扇 FCOM/DSC-32-30-20 Brake Fan
ON light : The brake fans run if the lefthand main landing gear is down and locked
Off : The brake fans stop
HOT light : This amber light comes on when the brakes get too hot (A caution appears on ECAM, also)
自動(dòng)剎車 FCOM/DSC-32-30-20 Auto Brake Panel
The springloaded MAX, MED, and LO pushbutton switches arm the appropriate deceleration rate. 預(yù)位大致的減速率
ON light : comes on blue to indicate positive arming 預(yù)位顯示ON
DECEL light : comes on green when the actual deceleration is 80 % of the selected rate 實(shí)際減速率達(dá)到所選檔位的80%
Off : The corresponding autobrake mode is not armed
防滯&前輪轉(zhuǎn)彎 FCOM/DSC-32-30-20 A/SKID & N/W STRG sw
ON : If green hydraulic pressure is available, then antiskid is available. 綠液壓可以，防滯可用
OFF : The yellow hydraulic system supplies pressure to the brakes. 黃液壓系統(tǒng)供應(yīng)剎車壓力
時(shí)鐘 DSC-31-55 Clock
UTC (GMT) counter
Elapsed Time (ET) 經(jīng)過(guò)時(shí)間
Chrono (CHR) counter 計(jì)時(shí)器
CHR pushbutton 計(jì)時(shí)器按鈕
Reset (RST) pushbutton 重置按鈕
ET selector 經(jīng)過(guò)時(shí)間選擇器
DATE/SET pushbutton 日期/設(shè)置按鈕
UTC selector UTC選擇器
起落架選擇手柄
FCOM/DSC-32-10-40 Landing Gear Selector Lever
L/G LEVER
UP : This position selects landing gear retraction.
DOWN : This position selects landing gear extension.
RED ARROW 紅色箭頭↓
This red arrow lights up if the landing gear is not locked down when the aircraft is in the landing configuration, and a red warning appears on ECAM. 著陸形態(tài)起落架沒(méi)有放下鎖定，ECAM顯示紅色警告
剎車和儲(chǔ)壓器壓力指示
FCOM/DSC-32-30-20 BRAKES and ACCU PRESS indicator
Brake pressure is only indicated when the yellow hydraulic system controls the brake pressure, This is when the: 剎車壓力只顯示黃液壓系統(tǒng)控制的剎車壓力，當(dāng)
‐ Alternate braking system is activated, or 啟用備用剎車，或
‐ Parking brake is applied. 設(shè)置了停留剎車
ACCU PRESS : Indicates the pressure in the yellow brake accumulator. 顯示黃剎車儲(chǔ)壓器壓力
BRAKES : Indicates the yellow pressure delivered to the left and right brakes, as measured upstream of the alternate servovalves. 分別顯示左右剎車上游備用伺服活門壓力。
ISIS FCOM/DSC-34-NAV-20 Integrated Standby Instrument System
基礎(chǔ)功能（類似PFD）
游標(biāo)功能
FCOM/DSC-34-NAV-20 Bugs Function
BUGS function selection pushbutton
Pressing the BUGS pushbutton will activate the BUGS function and display the bug values to be selected.
故障旗 FCOM/DSC-34-NAV-20 Flags
DDRMI FCOM/DSC-34-NAV-30-30 Digital Distance and Radio Magnetic Indicator
DCDU FCOM/DSC-46-10-40-20 Datalink Control and Display Unit
小桌板 Sliding Table
放這張圖的意思是導(dǎo)軌也能掉東西進(jìn)去
中央操縱臺(tái)
MCDU FCOM/DSC-22_10-40-10 Multipurpose Control and Display Unit
MCDU 信號(hào)牌
FM 1 and FM 2 (amber) The onside FM is failed
IND (amber) The onside FM detects an independent mode of operation while both FM are healthly.
RDY (green) MCDU has passed its power up test after it was turned off using its DIM key.
FAIL (amber) Indicates that the Multipurpose Control and Display Unit (MCDU) has failed.
MCDU MENU (white) Indicates that the flight crew should call up a peripheral linked to the MCDU (such as ACARS, ATSU or CFDS).
FM (white) Comes on while the flight crew is using the MCDU to display peripherals.
MCDU飛行管理操作
FCOM/DSC-22_20-50-10-28
MCDU AOC功能
FCOM/DSC-22_45
MCDU ADS-B IN操作
FCOM/DSC-34-SURV-20-40 ATSAW
MCDU CFDS集中故障顯示/維護(hù)系統(tǒng)操作
FCOM/DSC-45-20 Maintenance System
MCDU ACARS數(shù)據(jù)鏈頁(yè)面
FCOM/DSC-46-10-40-30 MCDU Datalink Pages
氣象雷達(dá)
FCOM/DSC-34-SURV-30 Weather Radar
減速板 FCOM/DSC-27-20-30 Speed Brake
駕駛艙門 FCOM/DSC-52-40
切換旋鈕
FCOM/DSC-34-NAV-10-20 ADIRS
FCOM/DSC-31-05-40 EIS
ECAM 控制 FCOM/DSC-31-30 ECAM Control Panel
推力手柄
FCOM/DSC-22_10-40-30 Thrust Levers
FCOM/DSC-70-90-20 Thrust Levers
FCTM/AOP-10-30-10 電傳操縱設(shè)計(jì)原理
NON BACK-DRIVEN THRUST LEVER CONCEPT 非自動(dòng)驅(qū)動(dòng)收回推力手柄的概念
Airbus has selected the non-back-driven thrust lever concept 空客選擇了非自動(dòng)驅(qū)動(dòng)收回推力手柄的概念:
‐ The flight crew can easily and intuitively monitor the energy of the aircraft via current energy cues (speed, speed trend, engine parameters), and not via ambiguous thrust levers movement飛行機(jī)組可以通過(guò)當(dāng)前的飛機(jī)能量提示（速度、速度趨勢(shì)、發(fā)動(dòng)機(jī)參數(shù)）方便、直觀地監(jiān)控飛機(jī)的能量而不是通過(guò)不精確的推力手柄的移動(dòng)。
‐ When the autothrust is engaged, the Thrust Lever Position determines the maximum authorized thrust that may be commanded by the autothrust 接通自動(dòng)推力時(shí)，推力手柄的位置決定自動(dòng)推力可以指令的最大允許推力。
‐ When the flight crew uses manual thrust, the Thrust Lever Position determines the current thrust (as on any aircraft not equipped with autothrust). 當(dāng)飛行機(jī)組使用人工推力時(shí)，推力手柄的位置決定當(dāng)前的推力（如同其它沒(méi)有安裝自動(dòng)推力的飛機(jī)）
俯仰配平輪
FCOM/DSC-27-20-30 Pitch Trim Wheel
發(fā)動(dòng)機(jī)
FCOM/DSC-70-90-20 ENG MODE selector and ENG MASTER Levers
方向舵配平 FCOM/DSC-27-20-30
停留剎車 FCOM/DSC-32-30-20 PARKING BRK handle
重力放輪 FCOM/DSC-32-10-40 Landing Gear Gravity Extension
手持電話 FCOM/DSC-23-20-40 Passenger Address
DFDR EVENT pushbutton
FCOM/DSC-31-60-20
Pressing this button (briefly) sets an event mark on the Flight Data records.
AIDS PRINT pushbutton
FCOM/DSC-31-60-30
Pushing this pushbutton causes the immediate printing of a specific report, depending on the flight phase. The crew may then use the MCDU to select another report for immediate printing.
ATC FCOM/DSC-34-SURV-10-20
襟翼 FCOM/DSC-27-30-20
Before selecting any position, the pilot must pull the lever out of the detent. Balks at positions 1 and 3 prevent the pilot from calling for excessive flap/slat travel with a single action. 選擇任何位置之前必須將手柄從卡位中拉起。位置1和3有阻擋，防止飛行員一次動(dòng)作導(dǎo)致過(guò)多的襟縫翼行程。
Note: The pilot cannot select an intermediate lever position. 飛行員無(wú)法選擇手柄檔位之間的位置
打印機(jī) FCOM/DSC-45-30 Printer
更換打印紙請(qǐng)教機(jī)長(zhǎng)，手冊(cè)沒(méi)寫
側(cè)操縱臺(tái)
側(cè)桿 FCOM/DSC-27-20-30 Sidesiticks
Each pilot has on his lateral console a sidestick he can use to control pitch and roll manually. Each sidestick is springloaded to neutral. 側(cè)桿彈性回到中立
When the autopilot is engaged, a solenoid-operated detent locks both sidesticks in the neutral position. 當(dāng)接通自動(dòng)駕駛，側(cè)桿電磁鎖定在中立位。If the pilot applies a force above a given threshold (5 daN in pitch, 3.5 daN in roll) the stick becomes free and the autopilot disengages. 飛行員在側(cè)桿上施加力量超過(guò)閾值（俯仰50 N，橫滾35 N）側(cè)桿被釋放同時(shí)自動(dòng)駕駛解除。
The hand grip has two switches: 手柄有兩個(gè)開(kāi)關(guān)
‐ Autopilot disconnect and sidestick takeover pushbutton. 自動(dòng)駕駛解除和側(cè)桿接管按鈕
‐ Push-to-talk button.
Sidestick priority logic 側(cè)桿優(yōu)先邏輯
‐ When only one pilot operates the sidestick, it sends his control signals to the computers. 只有一個(gè)飛行員操作側(cè)桿，信號(hào)傳輸給計(jì)算機(jī)。
‐ When the pilots move both side stick simultaneously in the same or opposite direction and neither takes priority, the system adds the signals of both pilots algebraically. The total is limited to the signal that would result from the maximum deflection of a single sidestick. 當(dāng)倆飛行員同時(shí)移動(dòng)側(cè)桿并且沒(méi)有取得優(yōu)先權(quán)，系統(tǒng)代數(shù)疊加兩邊的信號(hào)。疊加的信號(hào)和單側(cè)桿偏轉(zhuǎn)的信號(hào)極限相同。
A pilot can deactivate the other stick and take full control by pressing and keeping pressed his priority takeover pushbutton. 飛行員可以通過(guò)持續(xù)按壓優(yōu)先權(quán)接管按鈕抑制另一個(gè)側(cè)桿獲得完全操縱。
For latching the priority condition, it is recommended to press the takeover push button for more than 40 s. 為了保持優(yōu)先權(quán)，建議按壓接管按鈕40秒以上。
如圖所示，雙側(cè)桿輸入量都大于2°，伴有“DUAL INPUT”音響提示
如圖所示，左側(cè)桿接管操縱，右側(cè)桿被抑制，伴有“PRIORITY LEFT”音響提示
FCTM/AOP-10-30-10 電傳操縱設(shè)計(jì)原理
OPERATIONAL BENEFITS 操作優(yōu)勢(shì)
The main operational benefits of the side-mounted stick 側(cè)桿的主要操作優(yōu)勢(shì):
‐ It enables a non-obstructed view of the main instrument panel 主儀表面板視線不受遮擋得以實(shí)現(xiàn)
‐ It is adapted for emergency situations (e.g. incapacitation, stick jamming, control failures) 適應(yīng)緊急的情形（例如：失能、側(cè)桿卡阻、操縱失效）
‐ It fits comfortably into the hand with a correct adjustment of the armrest 適當(dāng)調(diào)節(jié)扶手即可與手舒適配合
‐ It makes the sliding table installation possible (e.g. for maps, documents, meals). 可以安裝滑動(dòng)桌板（例如：用于地圖、文件、用餐）
When the autopilot is engaged 當(dāng)自動(dòng)駕駛儀接通時(shí):
‐ The sidesticks are locked in neutral position (immediate tactile feedback) 側(cè)桿鎖定于中立位置（即時(shí)觸覺(jué)反饋）
‐ There is no possibility of simultaneous input from the flight crew and the autopilot 飛行機(jī)組和自動(dòng)駕駛儀不可能同時(shí)輸入操縱
‐ The autopilot can be disconnected instinctively, at any time, by a firm pressure on the sidestick. 自動(dòng)駕駛儀可本能脫開(kāi)，通過(guò)在側(cè)桿上施加一定程度的壓力。
FCTM-AOP-10-30-20 電傳操縱使用原理
側(cè)桿的使用
Only one pilot flies at a time. 同一時(shí)間只能一個(gè)飛行員操縱。
If the PM wants to act on the sidestick, he/she must 如果PM想操縱側(cè)桿，則必須:
‐ Clearly announce “I have control' 清晰報(bào)告“我操縱”
‐ Press and maintain his/her sidestick pushbutton, in order to get full control of the Fly-By-Wire system.按壓并保持自己的側(cè)桿按鈕，以完全操縱電傳系統(tǒng)。
The flight crew should keep in mind that sidestick inputs are algebraically added. Therefore dual inputs must be avoided, and will trigger aural and visual alerts.飛行機(jī)組應(yīng)牢記側(cè)桿輸入是代數(shù)疊加的。因此必須避免側(cè)桿雙輸入，否則會(huì)觸發(fā)音響和目視告警。
Either pilot can make an input on their sidestick at any time. 任何時(shí)候兩名飛行員的其中一個(gè)可以在其側(cè)桿上輸入。
Either pilot can deactivate the other pilot’s sidestick by pressing on their sidestick pb.兩名飛行員的其中一個(gè)可通過(guò)按壓其側(cè)桿按鈕使另一名飛行員的側(cè)桿被抑制。
轉(zhuǎn)彎手輪 FCOM/DSC-32-20-20 Steering Hand Wheel
The steering handwheels, which are interconnected, can steer the nose wheel up to 75 ° in either direction. 內(nèi)部相連的轉(zhuǎn)彎手輪何以偏轉(zhuǎn)前輪到雙側(cè)的75°
Note: The steering system centers the nose wheel automatically after liftoff. 轉(zhuǎn)彎系統(tǒng)在離地后自動(dòng)使前輪中立。
Rudder PEDALS DISC pb
Pressing this button on either handwheel removes control of nose wheel steering from the rudder pedals until the button is released. 按壓任一手輪上的方向舵腳蹬斷開(kāi)按鈕將脫開(kāi)方向舵腳蹬對(duì)前輪的控制，直到松開(kāi)按鈕。
腳蹬
FCOM/DSC-27-10-10
Two pairs of pedals, which are rigidly interconnected, give the pilot mechanical control of the rudder. 飛行員通過(guò)兩副剛性連接的腳蹬機(jī)械控制方向舵。
FCOM/DSC-27-10-20 RUDDER ACTUATION
There is no feedback to the rudder pedals from the yaw damping and turn coordination functions. 方向舵腳蹬沒(méi)有偏航阻尼和協(xié)調(diào)轉(zhuǎn)彎的反饋。
FCOM/DSC-32-20-10
The BSCU receives orders from: BSCU接收以下指令
‐ Captain's, and the First Officer’s steering hand wheels (orders added algebraically), or 機(jī)長(zhǎng)和副駕轉(zhuǎn)彎手輪代數(shù)疊加的指令，或
‐ Rudder pedals, or 方向舵指令，或
‐ Autopilot. 自動(dòng)駕駛指令
The BSCU transforms these orders into nose wheel steering angle. That angle has the following limits, which depend on ground speed and the origin of the orders. BSCU根據(jù)以下基于地速和指令來(lái)源的限制，將指令轉(zhuǎn)換成前輪轉(zhuǎn)彎角。
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